c5 c10 c12 c14 c15 c16 c17 c18 c20 c25 c35 c40 c90 c100 c110 c120 c130 c140 c150 c152 c160 c170 c180 c190 c192 c200 c210 c220 c230 c240 c250 c260 c270 c280 c290 c300 c310a c310b c310c c310d c314a c314b c314c c314d c320a c320b c320c c324a c324b c324c c330 c332 c340 c350 c360 c370 c380 c390 c400 c410 c420 c430 c440 c450 c460 c490 c510a c510b c510c c510d c510e c510f c602 c604 c606 c608 c610 c612 c614 c616 c620 c640 c652 c654 c660 eof 2008011100135 20080111 00135 SO 2008 1 11 0001 2 20070925 G 8530 AEC631397 CYLINDER CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO RT ENGINE CRACKED B FCPR O OTHER O OTHER CR CRUISE 1 NM 09 919FA 1120 414A0628 276632R PILOT WAS INFORMED BY LINE PERSONNEL DURING TAXI TO TIE DOWN, THAT ENGINE WAS MAKING A LOUD (AIR PULSING) SOUND. PILOT C OULD ONLY HEAR THE SOUND AFTER REMOVING NOISE CANCELLING HEAD SET. PILOT THEN SHUTDOWN ENGINE. INSPECTION REVEALED THE N R 4 CYLINDER TO BE CRACKED AT THE PARTING SURFACE. EXHAUST WAS ESCAPING FROM THE CRACK CAUSING THE (AIR PULSING) SOUND. 1 L 7 2 3O 3 O A7CE E8CE 2007050400163 20070504 00163 GL 2007 5 4 050207 1 20070502 G 5210 649 ROD END CIRRUS CIRRUS SR SR22 2130001 GL CONT O550 IO550* SO CABIN DOOR BROKEN G B EMER. DESCENT D INFLIGHT SEPARATION CR CRUISE 1 SO 13 299JW 300 1034 CABIN DOOR DEPARTED AIRCRAFT IN FLIGHT DUE TO THE ROD END HINGE FAILURE. IT APEARS THE ROD END FAILED DUE TO FATIGUE. TH E ROD END SHOULD BE MADE OF A STRONGER MATERIAL. 1 L 7 1 3O 3 O NT A00009CH E3SO 2007062500013 20070625 00013 CE 2007 6 25 061371 1 20070613 G 3397 NTE5916 DIODE RAYTHN DH125 HAWKER800XP 7150012 CE LIGHTS OVERHEATED B O OTHER O OTHER AP APPROACH 1 CE 01 800RC 745 745 258660 PILOT'S NOTED THAT LANDING AND TAXI PULSE LIGHT SYSTEM WAS INOPERATIVE ... LIGHTS WOULD NOT PULSE IN FLIGHT. SYSTEM HAD BEEN UPDATED PER RAYTHEON MANDATORY SERVICE BULLETIN 33-3682. UPON INSPECTION AND TROUBLE SHOOTING SYSTEM, THE CONNECT ORS ATTACHED TO THE DIODES (CR1 THRU CR4) THAT WERE ADDED TO THE SYSTEM AS A RESULT OF THE BULLETIN, WERE LOOSE AND APPE AR TO HAVE OVERHEATED. IN DISCUSSIONS WITH RAYTHEON, IT WAS DETERMINED THAT POSITION OF THE DIODE INSULATORS ON PAGE 25 OR 39 OF THE SERVICE BULLETINS IS INCORRECT AND SHOWN OPPOSITE OF WHAT THEY SHOULD BE. AS A RESULT, THE THINNER INSULAT OR CRACKS AND ALLOWS THE TERMINAL TO SHORT TO GROUND AND OVERHEAT. VISUALLY INSPECT DIODE PANEL AND VERIFY THAT THE 2 L 7 2 4F RT A3EU 2007091700014 20070917 00014 WP 2007 9 17 090107 2 20070904 G 7200 TFE7312B ENGINE LEAR 35 36A 5170603 CE GARRTT TFE731 TFE73122B 01518 WP UNKNOWN E ESPA A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CL CLIMB 1 SO 11 545PA 11017 14 028 74118 DURING CLIMB OUT SHORTLY AFTER TAKEOFF LT ENGINE QUIT. CREW DECLARED AN EMERGENCY WITH DEPARTURE CONTROL, THEY VECTOR A IRPLANE TO PROPER MSA ALTITUDE AND RETURN FOR LANDING. CREW ELECTED, IN FLIGHT ENGINE START CHECK LIST, THE LT ENGINE ST ARTED, AND WAS OPERATING NORMAL. AT THIS POINT CREW NOTIFIED ATC THAT LT ENGINE WAS BACK UNDER NORMAL OPERATING CONDITIO NS. AIRPLANE LANDED UNEVENTFULLY. 2 L 7 2 4F 4 F A10CE E6WE 2008010800358 20080108 00358 CE 2008 1 8 102N07110026 1 20071015 G 3597 CABLE BEECH 56 56TC 1152736 CE LYC O541 TIO541* 41536 EA OXYGEN SYSTEM CHAFED F K NONE B SMOKE/FUMES/ODORS/SPARKS UK UNKNOWN 1 NM 09 420S 463 463 TG74 ISSUE WITH THE FIXED OXYGEN SYSTEM DISPLAY FOR STC SA01078SE WHERE THE DISPLAY (NOT IN CONTACT WITH OXYGEN) RIBBON CABLE CHAFED AND CREATED A SHORT TO GROUND WHERE THE RIBBON CABLE SMOKED BUT DID NOT FAIL, THE INDICATOR LIGHT OF THE SYSTEM, NOR FAILED TO OPERATE. ISSUE WAS NOTED DURING ANNUAL INSPECTION AND NOT REPORTED AT THE TIME OF INCIDENT. MFG HAS BEE N IN CONTACT WITH THE ACO AND IS ISSUING A SERVICE BULLETIN. 1 L 7 2 3O 3 O 3A16 E10EA 2007120500060 20071205 00060 SO 2007 12 5 110107 1 20071120 G 6320 WARNING LIGHT ROTOL GULSTM G159 G159 3952202 SO RROYCE DART DART529 54507 EU GEARBOX ILLUMINATED C E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 SO 11 810CB 148599 023 DURING CRUISE FLIGHT MISSION, THE RT GEARBOX LIGHT CAME ON STEADY. THE ENGINE WAS SHUTDOWN IAW AFM PROCEDURES. THE AIRCR AFT LANDED UNEVENTFULLY, AND TAXIED TO THE RAMP. NO EMERGENCY WAS DECLARED. 2 L 7 2 4T 4 T 1A17 E297 2007061500196 20070615 00196 GL 2007 6 15 110DJ0507 1 20070515 G 5522 SKIN AMTR 500 ECLIPSE500 05614K5 GL RT ELEVATOR CRACKED C K NONE O OTHER IN INSP/MAINT 1 EA 27 110DJ 117 203452 000007 DURING REMOVAL OF THE ELEVATORS, A SMALL CRACK WAS DISCOVERED ON RT ELEVATOR SKIN BY OB MOST HINGE BRACKET ATTACH POINT. 1 L 7 2 3F RT EXPA1L72 2008010900392 20080109 00392 EU 2008 1 9 120107 2 20071217 G 7200 ENGINE GULSTM G1159 G1159 3953505 SO RROYCE SPEY SPEY511* 54523 EU LEFT VIBRATION E ESPA A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 SO 11 183PA 108 8571 AFTER LANDING, TEMP.AROUND -12C, FREEZING FOG, CREW ELECTED TO TURN OFF ANTI-ICE AFTER LND. AIRCRAFT SAT FOR 1 HR,ENG'S STARTED. LT ENG HAD VIBRATION HUMMING, RT ENG WAS STABLE.TAXIED OUT W/ANTI-ICE ON THRUOUT. A/C TOOKOFF, IT SEEMED TO B E SMOOTH ON THE ROLL AND INITIAL CLIMB, HOWEVER, OUT OF 10,000 FT LT ENG VIB WAS AROUND 1.5 MILS,ABNORMAL FOR THIS AIRPL ANE. CREW ELECTED TO DIVERT (MAINT.BASE). LANDING WAS UNEVENTFUL. BOTH ENG'S HAD VISUAL CKS, NOTHING NOTED. CONCLUSION I T MUST HAVE BEEN AN ICING/MELTING PROBLEM. 2 L 7 2 4F 4 F RT A12EA E2EU 2007121400345 20071214 00345 EA 2007 12 14 120507 1 20071205 G 6310 A1902 V-BELT BLANCA 1413 14132 1201004 EA ENGINE TO TRANS DISINTEGRATED C A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 SO 19 413R 503 1531 DURING IFR TRAINING FLIGHT WHILE IN CROSS COUNTRY CRUISE, LOUD NOISES FROM ENGINE AREA PROMPTED CREW TO MAKE UNSCHEDULED LANDING TO SAFE AREA OF FLORIDA STATE ROAD 80 MEDIAN TURN AROUND PAVEMENT. UPON LANDING FOUND AFT BELT OF MAIN DRIVE BE LT HAD SHED ITS OUTER LAYER AND DISINTEGRATED, CAUSING DAMAGE ONLY TO THE FAN SHROUD BEHIND THE ENGINE OIL COOOLER, AND MINOR SKIN DENT BEHIND THE FUEL TANK IN OUTER SKIN. ONE MULTIFUNCTION ANTENNA RG58 TNC CONNECTOR DAMAGED. AIRCRAFT TRAIL ERED TO HANGAR AND AFFECTED AREAS DISSASSEMBLED. REPLACEMANT SERVICABLE FAN SHROUD ASSEMBLY TO BE INSTALLED WITH NEW PAR TS ORDERED FROM ROBINSON. NO ENGINE OR ROTOR OVERSPEED OCCURED. AUTOROTATION WAS NOT REQUIRED. PART 91 FLIGHT TRAINING O 1 L 7 1 3O A773 2007121400347 20071214 00347 GL 2007 12 14 15DR 1 20070411 G 2421 BC4101 ALTERNATOR CIRRUS SR SR22 2130001 GL CONT O550 IO550* SO NR 2 DESTROYED B ODAR O OTHER J WARNING INDICATION NR NOT REPORTED 1 EA 21 15DR 0394 OWNER REPORTED NR2 ALTERNATOR LIGHT ILLUMINATED. REMOVED TOP COWLING TO INSPECT NR2 ALTERNATOR. FOUND NR2 ALTERNATOR B ROKEN OFF AT MOUNTING PLATE BY (3) STUDS. ONE STUD STILL ATTACHED WITH NUT, BUT LOOSE. REMOVED P/N BC410-1, S/N 092140 3. 1 L 7 1 3O 3 O NT A00009CH E3SO 2007040200167 20070402 00167 2007 4 2 200345493 1 20070316 G 7920 4012T16P01 OIL FILTER OIL SYSTEM DEFECTIVE D O OTHER O OTHER NR NOT REPORTED 1 GL 25 INTERNAL BORE TO EACH END OF THE OIL FILTER ASSEMBLIES ARE SHARP AND UNSMOOTH. THIS CONDITION WAS NOTED ON 3 ADDITIONAL FILTERS IN OUR STOCK, LOT 583085. THIS CONDITION CAUSES THE PACKINGS ON THE OIL FILTER BODY TO SHEAR UPON INSTALLATION OF THE FILTER ELEMENT AND COULD CAUSE OIL BYPASS TO OCCUR. THIS FILTER ELEMENT IS USED. (K) 2007020100031 20070201 00031 SO 2007 2 1 200600073 1 20070131 G 5730 SKIN LKHEED 282 C130A 5262502 SO WING CRACKED B KGBR K NONE Z SIGNIFICANT FAILURE REPORT IN INSP/MAINT 1 NM 04 131HP 20233 56534 2EA CRACKS WERE DETECTED WHILE PERFORMING AD 2002-19-14, 1 CRACK EMANATING FROM A FASTENER HOLE LOCATED AT FS 543 RT CW STA 70 LOWER WING AND 1 CRACK EMANATING FROM A FASTENER HOLE AT FS 569, LT CW STA 57, LOWER WING. BOTH CRACKS ARE .125 0 INCH LONG. 2 H 7 4 4T A31NM 2007020100015 20070201 00015 WP 2007 2 1 200600083 1 20070131 G 5711 SPAR CAP CVAC PB4Y2 PB4Y2 2421102 WP WRIGHT R2600 R260035 67050 EA HAMSTD 23E 23E50 NE WING CRACKED B KGBR K NONE O OTHER IN INSP/MAINT 1 NM 04 2872G 7162 66300 WHILE PERFORMING THE REQUIREMENTS IN AD 2003-18-01, CRACKS WERE NOTED THRU-OUT THE WING. THE MAJOR CRACK IS A 4-5 INCH CRACK IN THE FWD LT LOWER SPAR CAP AFT ANGLE AT THE WING ATTACH POINT TO THE BELT FRAME. THE CRACK IS IN THE ANGLE (SPA R CAP AFT LEG), DOUBLER AND SPAR WEB. THERE ARE ALSO CRACKS .1250-.2500 INCH EMANATING FROM 3 OF THE 4 BELT FRAME CUTOU TS ON THE LOWER WING. 2 H 7 4 4R 4 R RT PAGE42 6 C P603 2007110100188 20071101 00188 NM 2007 11 1 200700026 1 20071017 G 2797 WMBMS136OT7C4G20 WIRE BOEING 737 737205 1384456 NM PWA JT8 JT8D17 52049 NE TE FLAPS CHAFED C SROM O OTHER S AFFECT SYSTEMS AP APPROACH 1 AL 03 733PA 38672 23466 TRAILING EDGE FLAPS ASYMMETRY LOCKOUT BETWEEN ZERO AND ONE DEGREE. THERE IS A SPLIT IN T/E FLAP INDICATION, LT T/E FLAP S INDICATE ONE DEGREE AND RT T/E FLAPS INDICATE ZERO. FLIGHT CREW EXPERIENCED AN UNEVENTFUL LANDING AND NO UNCOMMANDED ROLL. MAINTENANCE DISCOVERED RT T/E FLAP POSITION TRANSMITTER WIRE HARNESS HAD CHAFED WIRES. REPLACED WIRE HARNESS FRO M RT TRANSMITTER TO DISCONNECT STATION 720R CONNECTOR D4876P. 2 L 7 2 4F 4 F RT A16WE E2EA 2007080700167 20070807 00167 SW 2007 8 7 2007001 1 20070717 G 5714 SPAR CAP CVAC P4Y P4Y2TRANSAIR 2421102 SW WRIGHT R2600 R260035 67050 EA HAMSTD 23E 23E50 NE CENTER WING CRACKED B KGBR K NONE O OTHER IN INSP/MAINT 1 NM 04 2872G 7162 66300 WHILE PERFORMING AD 2003-18-01, CRACKS WERE FOUND UNDER THE LT LOWER, FWD, SPAR CAP DOUBLER IN THE CAP, SPAR WEB AND THE DOUBLER ITSELF. CRACKS WERE ALSO FOUND IN THE WING SKIN CUTOUTS AT ALL 4 LOWER CENTER WING BELT FRAME CUT-OUTS. RT FWD LOWER SPAR CAP CRACKED IN (2) PLACES UNDER THE DOUBLER. 2 H 7 4 4R 4 R AR29 PAGE42 6 C P603 2007020100014 20070201 00014 WP 2007 2 1 200700105 1 20070131 G 5711 SPAR CAP CVAC PB4Y2 PB4Y2 2421102 WP WRIGHT R2600 R260035 67050 EA HAMSTD 23E 23E50 NE WING CRACKED B KGBR K NONE O OTHER IN INSP/MAINT 1 NM 04 2871G 7192 66302 WHILE PERFORMING THE REQUIREMENTS IN AD 2003-18-01, CRACKS WERE NOTED THRU-OUT THE WING. THE MAJOR CRACK IS A 1.5 INCH CRACK IN THE FWD LT LOWER SPAR CAP AFT ANGLE AT THE WING ATTACH POINT TO THE BELT FRAME. THE CRACK IS IN THE ANGLE (SPA R CAP AFT LEG), DOUBLER AND SPAR WEB. THERE ARE ALSO CRACKS .1250-.2500 INCH EMANATING FROM THE 4 BELT FRAME CUTOUTS ON THE LOWER WING. 2 H 7 4 4R 4 R RT PAGE42 6 C P603 2007013100168 20070131 00168 EU 2007 1 31 200700114 1 20070130 G 5720 2121151091 STIFFENER CASA C212 C212 2410200 EU GARRTT TPE331 TPE33110R 0517 WP ROTOL R334 R334482F13 GL LT WING CRACKED B KGBR K NONE O OTHER IN INSP/MAINT 1 NM 04 515RL 5409 405 WHILE PERFORMING CASA COM LETTER 212-224 AND CASA SB 212-57-57-30, A CRACK WAS NOTED FROM THE 4TH RIVET TO THE 5TH RIVET FROM THE BOTTOM, ON THE VERTICAL STIFFINER LOCATED ON THE LT WING AT STA 4700, AFT SPAR WEB. THREE STIFFINERS NEXT TO THE ORIGINAL ARE CRACKED EXACTLY THE SAME, CRACKS ARE LOCATED INT HE SAME POSITIONS, BETWEEN THE 4TH AND 5TH RIVIT FROM THE BOTTOM. THIS TOTALS 4EA CRACKED STIFFINERS. 2 H 7 2 4T 4 T A43EU E4WE 6 C P61GL 2007022600165 20070226 00165 CE 2007 2 26 2007001HAGGAN 1 20070223 G 5740 2322330177 SUPPORT BRACKET GARKENYON 26044 LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE ZONE 500 FAILED B H51R O OTHER F FLT CONT AFFECTED AP APPROACH 1 NM 03 252FX 5936 0295 196 DURING FLAP OPERATION, FLAP ACTUATOR SUPPORT BRACKETS FAILED CAUSING FLAP ACTUATOR TO DAMAGE LEFT WING RIB SEGMENT. 2 L 7 2 4F 4 F RT A10CE E35NE 2007080700170 20070807 00170 WP 2007 8 7 2007002 1 20070717 G 5714 SPAR CAP CVAC PB4Y2 PB4Y2 2421102 WP CENTER WING CRACKED B KGBR K NONE O OTHER IN INSP/MAINT 1 NM 04 2871G 7192 66302 WHILE PERFORMING AD 2003-18-01, CRACKS WERE FOUND UNDER THE LT LOWER, FWD, SPAR CAP DOUBLER IN THE CAP, SPAR WEB AND THE DOUBLER ITSELF. CRACKS WERE ALSO FOUND IN THE WING SKIN CUTOUTS AT ALL 4 LOWER CENTER WING BELT FRAME CUT-OUTS. RT FWD LOWER SPAR CAP CRACKED IN ONE PLACE UNDER THE DOUBLER. 2 H 7 4 4R RT 2007040900153 20070409 00153 NE 2007 4 9 200701 2 20070328 G 7210 311300001 GEARBOX ACQCOR F22 F22 8850908 EA PWA JT15 JT15D4 52112 NE ACCESSORY G/B MISDRILLED B LM1R K NONE O OTHER IN INSP/MAINT 1 EA 09 ENGINE WAS ROUTED TO OUR FACILITY FOR OVERHAUL AND DURING A FLUSHING PROCESS WE DISCOVERED A WALL IN AN ACCESSORY GEARBO X WITH A MISDRILLED OIL PASSAGE. THE OIL PASSAGE DID SUPPLY OIL TO THE REQUIRED AREA BUT IT BROKE THROUGH THE WALL DURI NG THE MANUFACTURING PROCESS RESTRICTING THE OIL SUPPLY. THE ENGINE HAS BEEN OPERATING WITH THIS CONDITION WITH NO APPAR ENT EFFECT. THE AGB COMPONENTS WAS INSPECTED AND NO DAMAGE WAS FOUND AS A RESULT OF THIS CONDITION. 1 H 7 1 3O 4 F NC 1A9 E1NE 2007012900391 20070129 00391 NE 2007 1 29 20070125 2 20070124 G 8520 GEAR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE WORN B EVGR K NONE O OTHER IN INSP/MAINT 1 SO 33 622 10003 L2845148A DURING INSPECTION OF THE ENGINE WHILE REPLACING THE CRANKSHAFT IAW SB 569A, IT WAS OBSERVED THAT (PN 13519647) CRANKSHAF T GEAR WAS EXCESSIVELY WORN. THE GEAR WAS REPLACED WITH A NEW PART. 1 G 7 1 3O 3 O H11NM 1E4 2007110100185 20071101 00185 NM 2007 11 1 20073 1 20071016 G 6720 A3592 ATTACH BRACKET ROBSIN R22 R22BETA 7640110 NM LYC O320 O320* 41508 EA T/R PEDAL CRACKED B LJER A UNSCHED LANDING F FLT CONT AFFECTED HO HOVERING 1 NM 09 721HH 12846 1484 TAIL ROTOR PEDALS JAMMED DURING FLARE TO A HOVER. AIRCRAFT LANDED WITHOUT INCIDENT. UPON INSPECTION IT WAS FOUND THAT TH E TAIL ROTOR PEDAL BLOCK SUPPORT BRACKET ON THE RT SIDE HAD CRACKED AT THE AFT PEDAL BLOCK ATTACH POINT ALLOWING THE PED AL BLOCK TO PIVOT DOWN AND JAM THE PEDALS. REPLACED BRACKET WITH NEW. 1 G 7 1 3O 3 O H10WE E274 2007090600021 20070906 00021 SO 2007 9 6 2007ADP828001 1 20070823 G 3230 159SCH1151 SELECTOR VALVE GULSTM G159 G159 3952202 SO RROYCE DART DART5298X 54507 EU ROTOL R4304 R1844304 EU RT MLG BYPASSING C E ENGINE SHUTDOWN J WARNING INDICATION AP APPROACH 1 SO 11 198PA 1253 027 AIRCRAFT WAS ENROUTE, FLYING THE APPROACH FOR RUNWAY 03. ONCE THE CREW PERFORMED THE APPROACH CHECKLIST, AND GEAR DOWN W AS SELECTED BEFORE LANDING CHECKLIST THEY GOT THE RT MAIN AND NOSE GEAR LIGHT ONLY. CREW TRY THE EMERGENCY PROCEDURES DE SCRIBED ON CHECKLIST. THIS PROCEDURE DID NOT GET THE (3) GREEN GEAR LIGHTS. AIRCRAFT LANDED WITH (2) GEARS DOWN ON RUNW AY 21, AND SLID INTO THE GRASS. NO INJURIES TO CREW OR PASSENGERS. 2 L 7 2 4T 4 T 1A17 E297 6 C P899 2007082100203 20070821 00203 CE 2007 8 21 2007AP080901 1 20070809 G 5521 043200185 SPAR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA RT ELEVATOR CRACKED B LJER K NONE O OTHER IN INSP/MAINT 1 NM 09 48440 15375 15280910 RT ELEVATOR SPAR FOUND BROKEN/CRACKED AT OB ATTACH POINT. OB HINGE BRACKET PULLED AWAY FROM SPAR. 1 H 7 1 3O 3 O NT 3A19 E223 2007082100209 20070821 00209 CE 2007 8 21 2007AP081001 1 20070810 G 2730 1016100190014 TORQUE TUBE BEECH BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA ELEVATOR WORN B K NONE O OTHER IN INSP/MAINT 1 SW 17 7166P 11959 11959 BB482 BB482 WHILE UNDERGOING A SCHEDULED INSPECTION, FOUND THE RT ELEVATOR HAD DEVELOPED VERTICAL PLAY WHEN GRASPED FROM THE TRAILIN G EDGE. FOUND THE ELEVATOR TORQUE TUBE HAD ROTATIONAL WHERE THE 6 EACH OB BLIND RIVETS ATTACH THE TORQUE TUBE TO THE MOU NT PLATE. 1 L 7 2 4T 4 T A24CE E4EA 2007083000020 20070830 00020 CE 2007 8 30 2007AP0821001 1 20070809 G 2497 36153 TERMINAL BEECH 200 B200 1152922 CE RT GCU BROKEN D B A EMER. DESCENT UNSCHED LANDING B G H SMOKE/FUMES/ODORS/SPARKS MULTIPLE FAILURE ELECT. POWER LOSS-50 PC CR CRUISE 1 CE 07 1925P 9715 BB1094 WIRE NUMBER P73G16N AT RT ENGINE FIREWALL GROUND POINT GS15 SEPARATED FROM THE WIRE TERMINAL DURING CRUISE FLIGHT. THIS WIRE CONNECTS GROUND TO THE GCU PIN G. THE RT GENERATOR OUTPUT SPIKED AND OPENED THE 325 AMP RT BUSS CURRENT LIMITER, TH E 50 AMP RT INVERTER CURRENT LIMITER, AND DAMAGED RADIOS, THE GCU AND SYSTEMS WIRED TO THE RT BUSS. UPON INSPECTION, THE INSULATION OF P73G16N WAS FOUND STRIPPED TOO FAR FROM THE WIRE END THEREBY GIVING NO SUPPORT OF THE WIRE INTO THE TERMI NAL AT THE INSULATION CRIMP AREA. 1 L 7 2 4T A24CE 2007091400201 20070914 00201 EU 2007 9 14 2007F00052 1 20070904 G 7714 AG34 TACH GENERATOR DORNER DO228 DO228202 2992030 EU GARRTT TPE331 TPE33110T WP HARTZL HCB4T HCB4TN5 GL LEFT ENGINE FALSE INDICATION E E ENGINE SHUTDOWN O OTHER CR CRUISE 1 EA 21 403VA 8171 LEFT RPM INDICATION ABNORMAL PERFORMED PRECAUTIONARY SHUTDOWN. INSPECTION FOUND TACH GENERATOR SHAFT BROKEN. REMOVED A ND REPLACED TACH GENERATOR IAW AMM 77-11-03. ENGINE GROUND PERFORMANCE RUN C/W AND PASSED. ALL PARAMETERS NORMAL. AIR CRAFT APPROVED FOR RETURN TO SERVICE. 2 H 7 2 4T 4 T RT A16EU E4WE 6 C P40EA 2007113000144 20071130 00144 CE 2007 11 30 2007F00064 1 20071018 G 3220 13889 BEARING RACE BEECH 100 B100 1152919 CE NLG CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 25 500KD 200 BE79 FOUND BOTH NOSE WHEEL BEARINGS PN 13889, AND RACES, PN 13836 TO BE CORRODED. CHANGED THESE SAME BEARINGS AND RACES AT L AST INSPECTION DUE TO SAME PROBLEM. BEARINGS HAVE 200 HOURS OR 4 MONTHS ON THEM. NOSE WHEEL IS AN STC WHEEL AND BRAKE ASSEMBLY. WE ALSO REPLACED THESE SAME BEARINGS AND RACES 1 YEAR PRIOR. (K) 1 L 7 2 4T A14CE 2007110500011 20071105 00011 SW 2007 11 5 2007F00065 1 20071016 G 6320 204040016005 TRANSMISSION BELL 204 UH1F 1181411 SW GE T58 T58GE3 NE MAIN ROTOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 05 4040P 657911 CRACK FOUND ON MAIN GEARBOX (TRANSMISSION IN VERTICAL CAST WEBBING ABOVE ENGINE TO TRANSMISSION DRIVE QUILL. MILITARY T ECHNICAL MANUAL ALLOWS .2500 INCH RADIUS/POLISH INTO WEBBING THIS CRACK HAS BEEN FOUND ON THREE (3 EACH) TRANSMISSIONS O N OTHER AC WITH ONE PENETRATING THE GEARBOX AND LEAKING FLUID. (K) 1 G 7 1 4U 4 U EXPA1G71 2007010800148 20070108 00148 CE 2007 1 8 2007FA0000001 1 20070102 G 2810 10092004115 LINE BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE FUEL SYSTEM CHAFED C O OTHER O OTHER NR NOT REPORTED 1 NM 08 155AV BB1216 DURING A SCHEDULED PHASE INSPECTION P/N 100-920041-15 ALUMINUM MAIN FUEL LINE WAS FOUND CHAFED IN THE LT MAIN LANDING GE AR WHEEL WELL WHERE IT ENTERS INTO THE BACK OF THE WING. THE EDGES OF THE HOLE THAT THE LINE PASSES THROUGH WAS PROTECTE D WITH PLASTIC ANTI CHAFE MATERIAL THAT WE CALL TANK TRACKS, OR RAILROAD TRACK, AND HAS A PN MS21266-1N. THIS ANTI CHAF E MATERIAL WAS INSTALLED AT THE FACTORY. THIS ANTI CHAFE MATERIAL CAUSED P/N 100-920041-15 ALUMINUM MAIN FUEL LINE TO BE CHAFED ALMOST THROUGH ITS .030 INCH SIDEWALL THICKNESS. THERE ARE OTHER AC THAT HAVE CHAFED FUEL LINES DUE TO THE CLOS E TOLERANCE OF THE FUEL LINES PASSING THROUGH THE STRUCTURE IN THE MAIN LANDING GEAR WHEEL AREA. 1 L 7 2 4T 4 T A24CE E4EA 2007011600044 20070116 00044 EA 2007 1 16 2007FA0000031 2 20070103 G 8520 13B37024 CRANKSHAFT PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA ENGINE CORRODED D GICR O OTHER O OTHER NR NOT REPORTED 1 NM 01 5347M 2372 2842136 L1949939A A59073 THE ENGINE CURRENTLY UNDERGOING ITS FIRST OVERHAUL SINCE NEW. THE CRANKSHAFT WAS CLEANED, URETHABOND 104 COATING REMOVE D AND CORROSION PITTING WAS DISCOVERED BENEATH COATING. THE PITTING EXCEEDED (SERVICEABLE LIMITS) AS STATED IN SB NR 50 5B. THIS CAUSED THE CRANKSHAFT THE BE REMOVED FROM SERVICE. THE ENGINE AVERAGED 39.5 HOURS/ MONTH SINCE IT WAS NEW . MFG AD COVERS THIS SUBJECT WITH THE COMPLIANCE WITH FAR, BEING TERMINATING ACTION FOR THE REPETITIVE INSPECTION. THE CRANKSHAFT (FROM THE FACTORY) HAD THE COATING AND (PID) STAMPING. NOTE: DUE TO THE URETHABOND 104 COATING, THIS SHOULD HAVE PREVENTED THE CORROSION PITTING WHICH IS A CONCERN OF THIS AD. THE ENGINE OVERHAULER STATED THE COATING WAS NOT W 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2007012500042 20070125 00042 SO 2007 1 25 2007FA0000036 2 20070102 G 8520 LIFTER CESSNA 206 U206C 2073332 CE CONT O520 IO520F 17032 SO NR 6 CYLINDER DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 AL 03 29114 U2061084 1683457 AFTER DRAINING OIL AND INSPECTING FILTER, LARGE FLAKES OF METAL WERE FOUND. DISASSEMBLED VALVE TRAIN AND FOUND SPALLING ON CYLINDER NR 6 INTAKE LIFTER. DAMAGE OCCURRED TO THE CORRESPONDING CAM LOBE AND CLYINDER NR 5 INTAKE LIFTER DUE TO D ETERIORATION OF CYLINDER NR 6 INTAKE LIFTER. UPON INSPECTION IT WAS DETERMINED THAT THE LIFTER HAS BAD METALLURGY. ALL OTHER LIFTERS NOT NOTED, SHOWED PROPER WEAR, AND HARDNESS TESTING MARKS. THE CAM SHOWED DAMAGE ON CORRESPONDING LOBE, NOT DETERIORATION, AND OTHER LOBES SHOWED PROPER WEAR. THE ENGINE HAS 228.06 HOURS SINCE FACTORY REMANUFACTURE. MFG WA S CONTACTED ABOUT SITUATION, AND NO INTEREST WAS NOTED ON POSSIBLE PROBLEMS. ENGINE WAS SENT TO LOCAL REPAIR STATION FO 1 H 7 1 3O 3 O A4CE E5CE 2007012500250 20070125 00250 EA 2007 1 25 2007FA0000038 1 20070115 G 3233 2953310095200 SEAL ROTOL CNDAIR CL600 CL6002B16 1900305 EA ACTUATOR PISTON POROUS B K NONE K J FLUID LOSS WARNING INDICATION IN INSP/MAINT 1 GL 13 DCL28293 GREEN TWEED SEAL P/N 295-33100-952-0050 INSTALLED ON PISTON ASSEMBLY IN MFG SIDE BRACE ACTUATOR P/N: 6500-3 HAVE BEEN FO UND WITH VOIDS ON THE INNER RAISED SURFACE CAUSING FLUID LEAK. THESE VOIDS ARE UNDETECTED AT INSTALLATION OF NEW SEAL A S THE VOIDS ARE NOT ON THE SURFACE AND DO NOT BECOME VISIBLE UNTIL AFTER MONTHS OF OPERATION. SEAL CONDITION NOTED DURI NG WARRANTY REPAIR. SUBJECT ACTUATOR RETURNED FOR WARRANTY REPAIR AFTER 11 MONTHS OPERATION. 2 L 7 2 4F RT A21EA 2007012400183 20070124 00183 SO 2007 1 24 2007FA0000039 1 20070116 G 2497 WIRE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA UNKNOWN WORN C O OTHER O OTHER NR NOT REPORTED 1 SO 17 456M 318152081 THE WIRING THAT PASSES THROUGH THE NOSE RIB GROMMETS HAVE WORN TO THE EXTENT THAT THE INSULATION IS GONE AT PLACES CAUSI NG THE METAL CONDUCTOR TO SHOW THROUGH. IT APPEARS THAT THIS IS WORSE WITH THE GREATER AMOUNT OF CABLES IN THE BUNDLE. BUNDLES OF ONLY 2 WIRES DO NOT HAVE THIS PROBLEM. APPARENTLY THE BUNDLE IS (SLAPPED) UP AND DOWN WITH VIBRATION. THIS IS CAUSE FOR CONCERN DUE TO SPARKING NEAR THE FUEL TANK. 1 L 7 2 3O 3 O A20SO E14EA 2007012900346 20070129 00346 SO 2007 1 29 2007FA0000040 1 20070116 G 3233 400872 CLEVIS BOLT PIPER PA28 PA28R201 7102816 SO LYC O360 IO360A1A 41514 EA NLG SHEARED B A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CR CRUISE 1 GL 21 289ND 4558 2844039 DURING CRUISE FLIGHT, CREW REPORTED LOUD BANG FOLLOWED BY A NOSE GEAR DOWN AND LOCKED INDICATION. AIRCRAFT LANDED WITHOU T INCIDENT. UPON INSPECTION BY MX PERSONNEL NOSE GEAR ACTUATOR ROD END CLEVIS BOLT (AN23-21A) MISSING WITH EVIDENCE OF B OLT FAILURE. 1 L 7 1 3O 3 O 2A13 1E10 2007012600251 20070126 00251 SO 2007 1 26 2007FA0000041 1 20070116 G 3233 400872 CLEVIS BOLT PIPER PA28 PA28R201 7102816 SO LYC O360 IO360A1A 41514 EA NLG SHEARED B OG5R A UNSCHED LANDING F D J FLT CONT AFFECTED INFLIGHT SEPARATION WARNING INDICATION CR CRUISE 1 GL 21 289ND 4558 2844039 DURING CRUISE FLIGHT, CREW REPORTED LOUD BANG FOLLOWED BY A NOSE GEAR DOWN AND LOCKED INDICATION. AIRCRAFT LANDED WITHOU T INCIDENT. UPON INSPECTION BY MX PERSONNEL NOSE GEAR ACTUATOR ROD END CLEVIS BOLT (AN23-21A) MISSING WITH EVIDENCE OF B OLT FAILURE. 1 L 7 1 3O 3 O 2A13 1E10 2007012900347 20070129 00347 SO 2007 1 29 2007FA0000042 1 20070116 G 2497 WIRE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ELECTRICAL SYS CHAFED C O OTHER O OTHER NR NOT REPORTED 1 SO 17 456M 318152081 THE WIRING THAT PASSES THROUGH THE NOSE RIB GROMMETS HAS WORN TO THE EXTENT THAT THE INSULATION IS GONE AT PLACES CAUSIN G THE METAL CONDUCTOR TO SHOW THROUGH. IT APPEARS THAT THIS IS WORSE WITH THE GREATER AMOUNT OF CABLES IN THE BUNDLE. BUNDLES OF ONLY 2 WIRES DO NOT HAVE THIS PROBLEM. APPARENTLY THE BUNDLE IS (SLAPPED) UP AND DOWN WITH VIBRATION. THIS I S CAUSE FOR CONCERN DUE TO SPARKING NEAR THE FUEL TANK. 1 L 7 2 3O 3 O A20SO E14EA 2007012600006 20070126 00006 CE 2007 1 26 2007FA0000046 1 20070105 G 5713 05112821 STRINGER CESSNA 170 170B 2072306 CE CONT O300 O300* 17022 SO WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 03 3436D 4200 26979 CRACKED AT FORWARD END AND PROGRESSES AFT. PROP STRIKE, OUT OF BALANCE PROP. EXAMPLE FROM C-170B WITH THE ENGINE INSTA LLED. (K) 1 H 7 1 3O 3 O A799 E253 2007012500346 20070125 00346 CE 2007 1 25 2007FA0000047 1 20070105 G 5713 0511282 STRINGER CESSNA 170 170B 2072306 CE CONT O300 O300* 17022 SO WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 03 3436D 4200 26979 CRACKED AT FWD END AND PROGRESSES AFT. PROP STRIKE, OUT OF BALANCE PROP? AIRCRAFT HAS A HISTORY OF WING REPAIRS FROM G ROUND LOOPS BUT HAS SINCE HAD A ENGINE UPGRADE TO MFG. (K) 1 H 7 1 3O 3 O A799 E253 2007012500347 20070125 00347 CE 2007 1 25 2007FA0000048 1 20070105 G 5713 0511282 STRINGER CESSNA 170 170B 2072306 CE WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 03 CRACKED AT FORWARD END AND PROGRESSES AFT. PROP STRIKE, OUT OF BALANCE PROP. (K) 1 H 7 1 3O A799 2007012500281 20070125 00281 EU 2007 1 25 2007FA0000049 1 20070104 G 4980 MY20240035005A3 SEAL MICROTURBO AMD FALC20 FALCON20F5 2730105 EU GARRTT TFE731 TFE731* 01518 WP APU EXHAUST DETERIORATED B JGVR O OTHER S AFFECT SYSTEMS NR NOT REPORTED 1 CE 09 189RB 1673 592 262 DETERIORATED APU EXHAUST DUCT SEAL BETWEEN THE DUCT FLANGE AND AIRCRAFT SKIN ALLOWED HOT EXHAUST GASSES TO ENTER THE TAI LCONE AREA RESULTING IN HEAVY SOOT BUILDUP AND HEAT DAMAGE TO WIRE BUNDLES AND ELECTRICAL CONNECTORS AND STRUCTURAL COMP ONENTS ADJACENT TO THE APU EXHAUST OPENING. ULTRASOUND INSPECTION REVEALED HEAT DAMAGE TO THE AC SKIN ABOVE THE EXHAUST OPENING. THE APU EXHAUST OPENING DOUBLER AND STRINGERS ADJACENT TO THE OPENING. PERIODIC INSPECTION OF THE APU INSTAL LATION, INCLUDING THIS SEAL, IS REQUIRED EVERY A-CHECK IAW MM. (K) 2 L 7 2 4F 4 F RT A7EU E6WE 2007012500197 20070125 00197 SO 2007 1 25 2007FA0000050 1 20070110 G 5521 510229615 ATTACH ANGLE AMRGEN AA5 AA5A 3960106 SO LYC O320 O320* 41508 EA STABILIZER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 17 9962U 3163 AA5A0362 DURING INSPECTION, ANGLE PN 5102296-15 AND PN 5102296-16, WERE FOUND CRACKED IN THE UPPER END OF THE ANGLE AS INSTALLED. CAUSE OF CRACKING IS BELIEVED TO BE DUE TO HIGHT STRESS LOADS IN THIS AREA. (K) 1 L 7 1 3O 3 O A16EA E274 2007012500198 20070125 00198 CE 2007 1 25 2007FA0000051 1 20070107 G 5230 DOOR CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE CARGO BAY OPEN D K NONE O OTHER LD LANDING 1 WP 01 480DG 5294 5600015 108029 RT BAGGAGE DOOR POPPED OPEN ON ROLLOUT WITHOUT WARNING. COULD NOT DUPLICATE CIRCUMSTANCES, SUGGEST INSPECTING LATCHES A ND DOOR WARNING. ON A MORE REGULAR BASIS. AIRCRAFT RETURNED WITHOUT PROBLEM. (K) 2 L 7 2 4F 4 F RT A22CE E25EA 2007012900355 20070129 00355 EU 2007 1 29 2007FA0000054 1 20070102 G 2435 BEARING LUCAS 23080005 BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE731* 01518 WP STARTER GEN FAILED C D RETURN TO BLOCK E VIBRATION/BUFFET CR CRUISE 1 EA 09 180NE 710 95274 NA0401 P91312 FORWARD BEARING FAILED 2 L 7 2 4F 4 F RT A3EU E6WE 2007012500134 20070125 00134 SO 2007 1 25 2007FA0000056 1 20070110 G 5521 510229615 ATTACH ANGLE AMRGEN AG5B AG5B 3990100 SO LYC O360 O360* 41514 EA STABILIZER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 17 11966 1190 10121 DURING INSPECTION, ANGLE PN 5102296-15 AND PN 5102296-16, WERE FOUND CRACKED IN THE BEND RADIUS OF THE UPPER END OF THE ANGLE AS INSTALLED. CAUSE OF CRACKING IS BELIEVED TO BE DUE TO HIGH STRESS LOADS IN THIS AREA. (K) 1 L 7 1 3O 3 O NT 1L71 E286 2007012500063 20070125 00063 GL 2007 1 25 2007FA0000057 1 20070105 G 5210 ATTACH FITTING DIAMON DA40 DA40 2990002 GL AFT CABIN DOOR BENT D GO3S A UNSCHED LANDING D INFLIGHT SEPARATION NR NOT REPORTED 1 NM 07 422FP 212 40FC022 AFT CABIN DOOR ASSY SEPARATED FROM AC DURING FLIGHT. CONTROL OF THE AC WAS MAINTAINED AND LANDED SAFELY AT DEPARTURE AI RPORT. DOOR WAS EVENTUALLY RECOVERED AND UPON VISUAL INSPECTION OF THE DOOR, THE AFT DOOR LATCH PIN WAS NOT ENGAGED. T HE FRONT DOOR LATCH PIN WAS PROPERLY ENGAGED AND THE DOOR LATCH WAS CLOSED. NO (DOOR OPEN) ANNUNCIATION WAS INDICATED B ECAUSE THE DOOR OPEN SWITCH IS ACTUATED FROM THE FRONT DOOR LATCH PIN. UPON DISASSEMBLY OF THE DOOR, THE AFT DOOR LATCH ROD WAS DETACHED FROM THE LATCH MECHANISM. THE ATTACHMENT CLIP, (PN AND NAME NOT GIVEN; NR 215 IN THE PARTS BOOK) WAS BENT ALLOWING THE ROD TO BECOME SEPARATED FROM THE LATCH. A MUCH STRONGER MATERIAL IS RECOMMENDED FOR THE ATTACHMENT CL 1 L 7 1 3O NT A47CE 2007012500307 20070125 00307 EA 2007 1 25 2007FA0000058 2 20070105 G 8540 61098 GEARSHAFT DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA ENGINE SEIZED D GO3S O OTHER O OTHER NR NOT REPORTED 1 NM 07 423FP 234 40FC023 L4037236A REMOVED VACUUM DRIVE ASSEMBLY AND FOUND DRIVE GEAR SHAFT SEIZED AND (3) TEETH BROKEN OFF OF DRIVE GEAR. FURTHER INSPECT ION REVEALED NO LUBRICATION PORT FOR PRESSURIZED ENGINE OIL TO LUBRICATE THE DRIVE GEAR SHAFT. ALL (3) TEETH WER FOUND IN THE OIL PUMP INLET SCREEN. (K) 1 L 7 1 3O 3 O NT A47CE E286 2007012500138 20070125 00138 SO 2007 1 25 2007FA0000059 1 20070110 G 5521 510229615 ATTACH ANGLE AMRGEN AA5 AA5B 3960105 SO LYC O360 O360* 41514 EA STABILIZER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 17 4521A 2194 AA5B1070 DURING INSPECTION, ANGLE PN 5102296-15 AND PN 5102296-16, WERE FOUND CRACKED IN THE BEND RADIUS OF THE UPPER END OF THE ANGLE AS INSTALLED. CAUSE OF CRACKING IS BELIEVED TO BE DUE TO HIGH STRESS LOADS IN THIS AREA. (K) 1 L 7 1 3O 3 O A16EA E286 2007012500149 20070125 00149 CE 2007 1 25 2007FA0000063 1 20070110 G 5730 05230294 SKIN CESSNA 172 172N 2072434 CE RT WING MISMANUFACTURED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 09 A5OR DURING AN RECEIVING INSPECTION OF NEW RT OB LEADING EDGE SKIN, IT WAS FOUND TO HAVE BEEN DRILLED UP INCORRECTLY SINCE NO NE OF THE NOSE RIBS WOULD LINE UP AND THE SET UP WOULD HAVE LT INSUFFICIENT EDGE DISTANCE ON THE LOWER MAIN WING SPAR RI VET LINE. THIS IS ZND TIME WE HAVE RECEIVED THIS SAME PART. WE ASKED THAT THE PART NOT BE PUT BACK INTO MFG STOCK SINC E PART IS NON-CONFORMING. THE PART CAME WITH 8130-3 AIRWORTHINESS APPROVAL TAG. RECOMMEND MFG PERFORM CLOSE CONFORMITY INSPECTION OF PARTS. (K) 1 H 7 1 3O NT 3A12 2007012500292 20070125 00292 SO 2007 1 25 2007FA0000064 1 20070109 G 3213 6531904 CYLINDER PIPER PA28 PA28140 7102802 SO LYC O320 O320* 41508 EA LT MLG DAMAGED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 15715 3501 287325144 DURING AN ANNUAL INSPECTION FO THE LT MLG CYLINDER ASSY PN 6531904, IT WAS FOUND TO BE LOOSE IN THE MAIN WING SPAR. THE LT MLG WAS REMOVED FOR FURTHER INSPECTION OF THE LT MAIN WING SPAR ASSY GEAR ATTACHING BOLT HOSES AND ATTACH POINTS. C LOSE INSPECTION FO THE WING SPAR SHOWED THAT THE LOWER (4) BOLTS HOLES HAD BEEN ELONGATED. THE HOLES IN THE LT LANDING GEAR CYLINDER WERE FOUND TO BE ELONGATED ALSO. IT APPEARED THAT ALL BOLTS WERE TIGHT AND THIS CONDITION HAD BEEN LOOSE FOR SOME TIME. AIRCRAFT WING SPAR WS REPAIRED AND THE LT MLG CYINDER WAS REPLACE WITH A LATER MODEL CYLINDER ASSY FROM MFG SINCE THE ORIGINAL PART WAS NO LONGER AVAILABLE. RECOMMEND CLOSE INSPECTION OF LANDING GEAR ATTACH POINTS DURING AL 1 L 7 1 3O 3 O 2A13 E274 2007013000176 20070130 00176 EU 2007 1 30 2007FA0000065 1 20070103 G 2742 ACTUATOR PARTEN P68 P68C 6780105 EU LYC O360 IO360A1A 41514 EA PITCH TRIM SEIZED D O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 GL 03 3832Q 274 (REF NR: PT202781) AIRCRAFT ARRIVED WITH PITCH TRIM ACTUATOR SEIZED IN FULL NOSE UP POSITION. ACTUATOR IS DRIVEN BY TRI M CABLE LOOPED OVER ACTUATOR PULLEY WITH NO MEANS OF PREVENTING CABLE FROM SLIPPING ON THE PULLEY. IT IS POSSIBLE TO RU N TRIM TO FULL TRAVEL ALLOWING ACTUATOR TO BIND. WHEN TRIM CONTROL IS REVERSED THE CABLE CAN SLIP OVER PULLEY WITH OUT MOVING ACTUATOR IF PROPER CABLE TENSION IS NO PRESENT. SUGGEST REVISION TO POH/AFM ADVISING CREW TO VISUALLY CHECK OPER ATION OF PITCH TRIM SYSTEM PRIOR TO FLIGHT. (K) 1 H 7 2 3O 3 O A31EU 1E10 2007013100033 20070131 00033 CE 2007 1 31 2007FA0000070 1 20070108 G 2520 5514551129 ATTACH FITTING CESSNA CESSNA 500 500CESSNA 2076602 CE PWA JT15 JT15D1 52060 NE CABIN CRACKED B ESER O OTHER O OTHER NR NOT REPORTED 1 SO 11 117TW 5000059 UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. CHAIR WAS REPAIRED IAW STC ST01042WI STRUCTURAL SEAT REP AIR. (K) 1 L 7 2 4F 4 F A22CE E1NE 2007020100001 20070201 00001 NE 2007 2 1 2007FA0000071 1 20070110 G 6220 7610208051105 TIE BOLT SKRSKY S76 S76B 8143007 NE PWA PT6 PT6* 52043 EA MAIN ROTOR BROKEN D O OTHER O OTHER NR NOT REPORTED 1 EA 17 411JW 3392 760357 WHILE PERFORMING A ROUTINE INSPECTION OF THE MAIN ROTOR SPINDLES, A SPINDLE TIE BOLT WAS FOUND BROKEN AT THE THREADED EN D OF THE BOLT WHERE THE NUT ATTACHES. THE NUT WAS FOUND INSIDE THE SPINDLE CUFF WHERE THE ROTOR BLADE IS ATTACHED. A B ROKEN SECTION OF THE BOLT WAS STILL THREADED INTO THE NUT. IT IS UNCLEAR WHY THE BOLT BROKE. THE BOLT AND SPINDLE HAVE BEEN REMOVED AND SENT TO MFG AIRCRAFT FOR FURTHER INVESTIGATION TO DETERMINE CAUSE OF FAILURE. (K) 1 G 7 2 4U 3 T H1NE E2NE 2007012900120 20070129 00120 EU 2007 1 29 2007FA0000072 1 20070102 G 2435 BEARING BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE731* 01518 WP STATER GEN FAILED C O OTHER E VIBRATION/BUFFET CR CRUISE 1 EA 09 180NE 710 95274 NA0401 P91312 FORWARD BEARING FAILED. 2 L 7 2 4F 4 F RT A3EU E6WE 2007012900357 20070129 00357 2007 1 29 2007FA0000073 1 20070126 G 8011 ES6462751 STARTER ENGINE LEAKING C WS9R O OTHER K FLUID LOSS NR NOT REPORTED 1 NM 07 2 SUBMITTED TO SLC-FSDO BY (WS9R). STARTER LEAKING OUT OF REAR OF STARTER PLATE. 2007013100066 20070131 00066 SO 2007 1 31 2007FA0000074 1 20070123 G 5312 624403 BULKHEAD PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA SNSNCH 76E 76EM8 EA FUSELAGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 09 7095W 4309 28882 L148936C 15028K THE BULKHEAD, BRACKETS, AND DOUBLERS AT STA. 228.3 WERE SEVERELY CORRODED. THIS BULKHEAD IS THE FRONT SUPPORT FOR THE VE RTICAL STABILIZER/RUDDER ASSEMBLY. THE CORROSION COVERED AN AREA APPROXIMATE THE SIZE OF THE FRONT RUDDER ATTACHMENT BRA CKET THAT IS PART OF THIS BULKHEAD ASSEMBLY. THE CORROSION WAS FOUND DURING AN ANNUAL INSPECTION AND WAS ONLY VISIBLE, W ITHOUT DISASSEMBLY, AS SLIGHT BUBBLING OF THE METAL ON THE BRACKETS FACING REARWARD THAT ARE ATTACHED TO THE AFORE MENTI ONED BULKHEAD ASSEMBLY. 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA 2007013100067 20070131 00067 SO 2007 1 31 2007FA0000075 1 20070123 G 5312 624403 BULKHEAD PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA SNSNCH 76E 76EM8 EA FUSELAGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 09 7095W 4309 28882 L148936C 15028K THE BULKHEAD, BRACKETS, AND DOUBLERS AT STA. 228.3 WERE SEVERELY CORRODED. THIS BULKHEAD IS THE FRONT SUPPORT FOR THE VE RTICAL STABILIZER/RUDDER ASSEMBLY. THE CORROSION COVERED AN AREA APPROXIMATE THE SIZE OF THE FRONT RUDDER ATTACHMENT BRA CKET THAT IS PART OF THIS BULKHEAD ASSEMBLY. THE CORROSION WAS FOUND DURING AN ANNUAL INSPECTION AND WAS ONLY VISIBLE, W ITHOUT DISASSEMBLY, AS SLIGHT BUBBLING OF THE METAL ON THE BRACKETS FACING REARWARD THAT ARE ATTACHED TO THE AFORE MENTI ONED BULKHEAD ASSEMBLY. 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA 2007013100073 20070131 00073 SO 2007 1 31 2007FA0000076 1 20070117 G 2434 635796 COUPLING CONT PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO MCAULY 3AF32C 3AF32C508 GL ALTERNATOR FAILED C B EMER. DESCENT H G ELECT. POWER LOSS-50 PC MULTIPLE FAILURE CR CRUISE 1 GL 09 321AK 4479 869 B020128 3447021 811403R 960254 ALTERNATOR DRIVE COUPLING FAILED ON LT AND RT ALTERNATORS, IN IMC SIMULTANEOUSLY. 1 PIECE COUPLING WITH A RUBBER LORD B USHING BONDED/INTERFERENCE FIT SLIPPED, CAUSING THE ALTERNATORS FAILURES. PILOTS LOST ELECTRICAL AND DESCENDED THROUGH ICE, UNABLE TO SHED MODERATE TIME ICE ACCUMULATION. TOTAL COMM AND AVIONICS FAILURE, PARTIAL PANEL WITH NO PITOT HEAT AV AILABLE. 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 2007013100075 20070131 00075 SO 2007 1 31 2007FA0000077 1 20070117 G 2434 635796 COUPLING CONT PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO MCAULY 3AF32C 3AF32C508 GL ALTERNTOR FAILED C B EMER. DESCENT H G ELECT. POWER LOSS-50 PC MULTIPLE FAILURE CR CRUISE 1 GL 09 321AK 4479 869 B020128 3447021 811403R 960254 ALTERNATOR DRIVE COUPLING FAILED ON LT AND RT ALTERNATORS, IN IMC SIMULTANEOUSLY. 1 PIECE COUPLING WITH A RUBBER LORD B USHING BONDED/INTERFERENCE FIT SLIPPED, CAUSING THE ALTERNATORS FAILURES. PILOTS LOST ELECTRICAL AND DESCENDED THROUGH ICE, UNABLE TO SHED MODERATE RIME ICE ACCUMULATION. TOTAL COMM AND AVIONICS FAILURE, PARTIAL PANEL WITH NO PITOT HEAT A VAILABLE. 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 2007013000179 20070130 00179 CE 2007 1 30 2007FA0000081 1 20070119 G 3245 850X1000 TUBE CESSNA 208 208B 2073701 CE TIRE DAMAGED C K NONE O OTHER IN INSP/MAINT 1 GL 21 1293E 4 208B0537 RIGHT MAIN GEAR TIRE REPORTED LOW. REMOVED TIRE TO CHECK THE TUBE. THE TUBE APPEARED TO LOOK OLD AND CHECKED. TECHNIC IAN REPLACED WITH NEW TUBE. ONE WEEK LATER TIRE REPORTED LOW AGAIN ON SAME POSITION. REMOVED THE TIRE AND INSPECTED TH E TUBE. THE TUBE LEAKING ON ONE SIDE AND ALMOST WORN THRU ON THE OPPOSITE SIDE. AFTER FURTHER INVESTIGATION DETERMINED THAT THE STICKERS INSIDE THIS 8.50 X 10.00 FC III P/N 850T86-2 S/N 62570185 TIRE HAD CAUSED THE FAILURE. THIS WAS THE SECOND FAILURE ON THE SAME GEAR POSITION WITH THE SECOND NEW TUBE WITHIN 7 WEEKS. AFTER CONTACTING MANUFACTURER TIRE PR ODUCT SUPPORT, SENT A NOTE AND PICTURES ABOUT THE PROBLEM AND THE FAA PMI FROM THE FARGO FSDO. THE MANUFACTURER RESPOND 1 H 7 1 3T A37CE 2007013100100 20070131 00100 2007 1 31 2007FA0000082 2 20070119 G 7414 K3823 DISTRIBUTOR BLK SLICK 6314 MAGNETO MELTED B K NONE M OVER TEMP IN INSP/MAINT 1 GL 21 408ND 493 05100422 DURING TEARDOWN INSPECTION OF 2 SLICK 6314 MAGNETOS THE DISTRIBUTOR BLOCK AND GEAR ASSY PN K3823 WAS FOUND TO BE MELTED TO THE POINT OF EMANATE FAILURE. THE MAGS WERE FROM 2 SEPARATE AIRCRAFT BUT WITH NEAR IDENTICAL TOTAL TIMES ONE AT 493.3 HRS AND THE OTHER AT 498.8.THE MANUFACTURE WAS CONTACTED AND THEY REQUESTED THE MAGS FOR EVALUATION. 2007013100103 20070131 00103 CE 2007 1 31 2007FA0000083 1 20070123 G 7160 07520161011 SEAL CESSNA 180 180J 2072622 CE INTAKE MISSING D K NONE O OTHER IN INSP/MAINT 1 NE 05 9986N 18052641 INTAKE SEALS FOUND MISSING. AD 77-04-05 PERTAINING TO THIS DEFECT HAD BEEN PREVIOUSLY ACCOMPLISHED IN 1977. DUE TO THE A GE OF THE FLEET I BELIEVE THAT THE ONE TIME INSPECTION IAW THIS AD IS INSUFFICIENT. AS THIS IS NOT THE FIRST TIME I HAVE FOUND THE SAME CONDITION ON OTHER AIRCRAFT I WOULD CONSIDER UPDATING THE AD TO INCLUDE REPETITIVE INSPECTIONS AT ANNUAL /100 HOUR INTERVALS. 1 H 7 1 3O 5A6 2007013100104 20070131 00104 CE 2007 1 31 2007FA0000084 1 20070119 G 3245 850X1000 TUBE CESSNA 208 208B 2073701 CE LANDING GEAR WORN C K NONE O OTHER IN INSP/MAINT 1 GL 21 1293E 4 208B0537 RT MAIN GEAR TIRE REPORTED LOW. REMOVED TIRE TO CHECK THE TUBE. THE TUBE APPEARED TO LOOK OLD AND CHECKED. TECHNICIAN RE PLACED WITH NEW TUBE. 1 WEEK LATER TIRE REPORTED LOW AGAIN ON SAME POSITION. WE REMOVED THE TIRE AND INSPECTED THE TUBE. THE TUBE LEAKING ON ONE SIDE AND ALMOST WORN THRU ON THE OPPOSITE SIDE. AFTER FURTHER INVESTIGATION WE DETERMINED THAT THE STICKERS INSIDE THIS 8.50 X 10.00 FC III P/N 850T86-2 S/N 62570185 TIRE HAD CAUSED THE FAILURE. THIS WAS THE SECOND FAILURE ON THE SAME GEAR POSITION WITH THE SECOND NEW TUBE WITHIN 7 WEEKS. AFTER CONTACTING MFG WHO GAVE ME AN E-MAIL FOR THEIR PRODUCT SUPPORT CONTACT WE GOT INFORMATION VERY QUICKLY. I SENT HIM A NOTE AND PICTURES ABOUT THE PROBLEM AND 1 H 7 1 3T A37CE 2007013100106 20070131 00106 SO 2007 1 31 2007FA0000085 1 20070117 G 2434 635796 COUPLING CONT PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO MCAULY 3AF32C 3AF32C509 GL ALTERNATOR FAILED C B EMER. DESCENT H G ELECT. POWER LOSS-50 PC MULTIPLE FAILURE CR CRUISE 1 GL 09 321AK 4479 869 3447021 812128R 961321 ALTERNATOR DRIVE COUPLING FAILED ON LT AND RT ALTERNATOR, IN IMC SIMULTANEOUSLY. COUPLING FAILURE RESULTED IN TOTAL ELEC TRICAL FAILURE, RT ENGINE. 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 2007013100107 20070131 00107 CE 2007 1 31 2007FA0000086 1 20070126 G 3260 1003810061 DOWNLOCK SWITCH BEECH 200 B200 1152922 CE PWA PT6 PT6A60A 52043 NE LANDING GEAR FAILED E A UNSCHED LANDING N FALSE WARNING LD LANDING 1 GL 07 200EW 7169 70 BB1163 NOSE LANDING GEAR DID NOT HAVE A DOWN AND LOCKED INDICATION GEAR WARNING SYSTEMS ACTIVATED (LIGHT IN SELECTOR HANDLE AND GEAR HORN). AN UNEVENTFUL LANDING HAS MADE VISUAL CHECK OF NOSE GEAR SHOWED TO BE IN THE DOWN AND LOCKED POSITION. SWIT CH REMOVED AND REPLACED WITH A NEW UNIT AND THE SYSTEM CHECKED NORMAL. 1 L 7 2 4T 4 T A24CE E4EA 2007013100256 20070131 00256 CE 2007 1 31 2007FA0000090 1 20070102 G 2730 355246516 CONTROL CABLE BEECH 35 V35 1151538 CE CONT O520 IO520* 17032 SO ELEVATOR SYS BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 23 767TM 2801 D8556 FOUND BROKEN STRANDS ON ELEVATOR CABLE BEHIND INSTRUMENT PANEL ABOUT 10 INCHES ABOVE THE (PN 535521242-13) BOBWEIGHT. ( K) 1 L 7 1 3O 3 O 3A15 E5CE 2007013100257 20070131 00257 EA 2007 1 31 2007FA0000091 2 20070118 G 7314 AC40295 PUMP AMRGEN AA5 AA5 0631410 SO LYC O320 O320E2G 41508 EA ENGINE LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 01 24AU 302 AA50588 AT ANNUAL FUEL STAINS WERE FOUND ON ENGINE LOWER COWLING. IN AN ATTEMPT TO FIND THE LEAK THE ELECTRIC FUEL PUMP WAS TUR NED ON TO PRESSURIZE THE FUEL SYSTEM BUT NO LEAKAGE WAS FOUND. WHILE TURNING ENGINE OVER BY HAND DURING THE COMPRESSION CHECK A LARGE FLOW OF GAS WAS FOUND LEAKING OUT THE SIDE OF THE FUEL PUMP ABOVE THE OUTLET PORT BETWEEN THE DIAPHRAGM A ND PUMP CASTINGS. REPAIR STATION WAS CONTACTED AND THY INDICATED THAT THE SCREWS THAT HOLD THE PUMP TOGETHER ARE ASSEMB LED AT 25 INCH LBS TORQUE + OR - 5 INCH LBS . PUMP SCREWS WERE CHECKED AND THEY WERE FOUND TO BE TIGHTENED TO ONLY 2-3 INCH LBS OF TORQUE. ALL OF THE SCREWS HAD TORQUE PUTTY ON THEM WHICH INDICATED THE SCREWS HAD NOT BACKED OUT. GUESS IS 1 L 7 1 3O 3 O A16EA E274 2007021500169 20070215 00169 WP 2007 2 15 2007FA0000092 2 20070115 G 7250 31021069 TURBINE WHEEL GULSTM 690TP 690B 7630516 SW GARRTT TPE331 TPE33110T WP HARTZL HCB3T HCB3TN5 GL ENGINE DAMAGED B IZ2R O OTHER O OTHER NR NOT REPORTED 1 SW 15 690LL 2245 11544 P99112C BVA7239 INSPECTION OF ENGINE REVEALED DAMAGE TO 3RD STAGE TURBINE ROTOR VISIBLE THROUGH ENGINE TAILPIPE. ENGINE WAS REMOVED FRO M AIRCRAFT AND THE TURBINE SECTION MODULE REMOVED TO INVESTIGATE FOR CAUSE OF DAMAGE. UPON INSPECTION 4 EA PINS WERE FO UND MISSING FROM 2ND STAGE TURBINE ROTOR ASSEMBLY CAUSING SIGNIFICANT DAMAGE TO VARIOUS TURBINE SECTION COMPONENTS, SEVE RAL OTHER PINS WERE ALSO FOUND LOOSE AND DAMAGED. SB ADDRESSES REMOVAL OF 2ND STAGE TURBINE ROTORS PN 310210610 UTILIZI NG AN IMPROVED PIN DESIGN. FURTHERMORE MFG HAS INDEPENDENT SERVICE CENTER SPECIAL PROGRAM IN PLACE TO COVER PIN REPLACE MENT ON AFFECTED TURBINE ROTORS AT NO CHARGE, COVERING SECONDARY DAMAGE ON A PRORATED BASIS. (K) 1 H 7 2 3T 4 T 2A4 E4WE 6 C P15EA 2007021300165 20070213 00165 EA 2007 2 13 2007FA0000095 2 20070109 G 8520 AEL321031 CRANKSHAFT CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA ENGINE BROKEN B VA1R O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION DE DESCENT 1 SW 19 15RA 410 17259568 L2207127A ENGINE BEGAN RUNNING ROUGH AND BECAME SMOOTH AGAIN DURING DESCENT. TROUBLESHOOTING FIRST FOUND BRASS METAL PARTICLES IN AIR FILTER AND OIL. CRANKSHAFT WAS APPARENTLY BROKEN OR CRACKED BUT STILL TOGETHER. AFTER NUMEROUS GROUND RUSN AND KN OCKING NOISES HEARD, THE CRANKSHAFT BROKEN AND ROD THROWN THROUGH CASE. THE BREAK WAS BETWEEN NR 3 AND NR 4 ROD JOURNAL S. SENG BACK TO ENGINE COMPONENTS FOR WARRANTY AND ANALYSIS. (K) 1 H 7 1 3O 3 O NT 3A12 E274 2007021400083 20070214 00083 SO 2007 2 14 2007FA0000096 1 20070103 G 3230 455180 CONDUIT PIPER PA24 PA24250 7102404 SO LYC O540 O540* 41532 EA LT MLG PUSH PULL SEPARATED D O OTHER O OTHER NR NOT REPORTED 1 EA 63 6632P 3200 241755 THE LT MAIN LANDING GEAR PUSH PULL CONDUIT SEPARATED AT THE BALL END WHERE IT IS ATTACHED TO THE SUPPORT STRUCTURE IN TH E WHEEL WELL. BELIEVE THIS FAILURE OCCURRED AT THE PREVIOUS LANDING GEAR RETRACTION. (K) 1 L 7 1 3O 3 O 1A15 E295 2007021300176 20070213 00176 2007 2 13 2007FA0000101 2 20070124 G 7414 6320 MAGNETO ENGINE FROZEN B WS9R O OTHER O OTHER NR NOT REPORTED 1 NM 07 SHAFT IN MAGNETO FROZEN, WOULD NOT MOVE. (K) 2007021300189 20070213 00189 EA 2007 2 13 2007FA0000102 1 20070109 G 5755 BRACKET CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF343B1 NE FLT SPOILER CRACKED B RO3R O OTHER O OTHER NR NOT REPORTED 1 CE 03 684TS 5384 WHILE PERFORMING A 96 MONTH AIRFRAME INSPECTION, DISCOVERED THE LT FLIGHT SPOILER TRANSMITTER BRACKET WAS CRACKED. UPON REMOVING BRACKET, DISCOVERED MATTING SURFACE WITH TRANSMITTER WAS CORRODED. DECIDED TO REMOVE TO INSPECT RT TRANSMITTE R BRACKET AND FOUND THE RT SIDE CORRODED AS WELL. REMOVED AND REPLACED BOTH BRACKETS. RT AND LT HAVE THE SAME PN. (K) 2 L 7 2 4F 4 F RT A21EA E15NE 2007021300164 20070213 00164 EA 2007 2 13 2007FA0000103 1 20070109 G 5755 600913563 BRACKET CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF34* NE RT FLT SPOILER CRACKED B RO3R O OTHER O OTHER NR NOT REPORTED 1 CE 03 267DW 5391 RT FLIGHT SPOILER POSITION INDICATION WOULD NOT OPERATE PROPERLY. UPON FURTHER INVESTIGATION, FOUND THE FLIGHT SPOILER TRANSMITTER BRACKET WAS CRACKED AND UNABLE TO HOLD POSITION TRANSMITTER. REMOVED AND REPLACED BRACKET. (K) 2 L 7 2 4F 4 F RT A21EA E15NE 2007020500043 20070205 00043 CE 2007 2 5 2007FA0000104 1 20070201 G 2710 S394 CONTROL CABLE CESSNA 172 172S 2072439 CE AILERONS FRAYED B K NONE O OTHER IN INSP/MAINT 1 SO 15 5275S 3179 100 172S9203 DURING A ROUTINE INSPECTION THE AILERON CONTROL DIRECT CABLE WAS FOUND SERIOUSLY WORN IN THE CABIN OVERHEAD AREA. THE AI LERON BALANCE AND DIRECT CABLES ARE SEPARATED AND GUIDED BY 3 PULLIES, P/N-S394, INDEX NR 30, CHAPTER 27-10-00, FIG 3 IN THE CESSNA PARTS MANUAL. THE CENTER CABLE WAS WORN EXTENSIVELY AND HAD BROKEN STRANDS. THE WEAR IS CAUSED BY CONTACT WI TH THE PULLEY. IT IS DIFFICULT TO SEE WITHOUT ROTATING THE CABLE AND EXPOSING THAT PORTION OF THE CABLE THAT CONTACTS TH E PULLEY DURING LEVEL FLIGHT. THE CABLE AT FIRST APPEARS SHINY, BUT WITH THE AID OF A POWERFUL MAGNIFYING GLASS REVEALS MUCH MORE SERIOUS WEAR. OBVIOUSLY, THE FAILURE OF THIS CABLE WOULD LIKELY RESULT IN THE LOSS OF THE AIRCRAFT WITH LITTLE 1 H 7 1 3O NT 3A12 2007020500030 20070205 00030 CE 2007 2 5 2007FA0000105 1 20070202 G 5711 51220311 SPAR CAP CESSNA 310 T310R 2074246 CE CONT O520 TSIO520BB 17040 SO MCAULY 3AF32C 3AF32C87 GL LT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 EA 17 465DL 1132 310R1622 LT TOP WING SPAR CAPS AND TOP SKINS SEVERELY CORRODED IN AREA OF FACTORY NACELLE FUEL BLADDERS. LT-PN 5122031-1. 1 L 7 2 3O 3 O 3A10 E8CE 5 C P22EA 2007021300174 20070213 00174 GL 2007 2 13 2007FA0000106 1 20070111 G 7603 FRICTION LOCK AMTR LANCAR LANCAIR 05616TS GL WALTER M601 M601E EU POWER LEVER INOPERATIVE G O OTHER O OTHER NR NOT REPORTED 1 SW 11 750TL 154 LIV555 913008 AIRCRAFT EXPERIENCED LOSS OF POWER DURING TAKEOFF AND LANDED WITH LANDING GEAR RETRACTED DEPARTING RUNWAY FROM WHICH TAK EOFF WAS MADE. INVESTIGATION REVEALED FRICTION LOCK WAS NOT EFFECTIVE. (K) 1 L 7 1 3O 3 T RT EXPA1L71 EXPE3T 2007021300063 20070213 00063 EU 2007 2 13 2007FA0000107 1 20070125 G 5210 333045181 SEAL ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE731* 01518 WP CABIN DOOR LEAKING D A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SW 09 300XL 9015 276 THE AIRCRAFT DEPARTED, CLIMBING THROUGH 30000. THE CABIN ALT BEGAN TO CLIMB WITH THE AIRCRAFT. THE PILOTS REQUESTED TO DESCEND. CENTER DECLARED EMERGENCY AND GAVE CREW 12000 FT. AIRCRAFT PRESSURIZED PROPERLY AT THAT ALT. PILOT REQUESTE D DEVIATION AND TO HAVE EMERGENCY CANCELED. THIS WAS GRANTED BY CENTER. AFTER LANDING, CREW LOOKED OVER THE AC AND COU LD NOT FIND ANYTHING WRONG, PROCEEDED, AT 19000 FT. AIRCRAFT PRESSURIZED PROPERLY. IN MAINTENANCE CREW INSPECTED THE A IRCRAFT AND PERFORMED NUMEROUS GROUND PRESSURIZATION RUNS AN COULD NOT DUPLICATE PROBLEM. PILOT MADE STATEMENT THAT THE DOOR MAY NOT OF SEALED PROPERLY. MAINTENANCE LOOKED AT THAT ASPECT AND FOUND THAT THE DOOR CAN BE CLOSED IN A MANOR TH 2 M 7 2 4F 4 F A2SW E6WE 2007021300060 20070213 00060 NE 2007 2 13 2007FA0000108 2 20070101 G 7200 CFM563B1 POWERPLANT BOEING 737 737300 1384610 NM GE CFM56 CFM563B1 13802 NE OIL SYSTEM CONTAMINATED B UOXR A UNSCHED LANDING R Y J PARTIAL RPM/PWR LOSS ENGINE STOPPAGE WARNING INDICATION NR NOT REPORTED 1 SO 19 XAMAA 44927 3514 720721 ENGINE SUFFERED AN IFSD DUE TO POWER LOSS AND A COMMANDED ENGINE SHUTDOWN WAS CARRIED OUT. ENGINE RESTART WAS ATTEMPTED , UNSUCCESSFULLY. FURTHER INVESTIGATION REVEALED THAT NR 10 STRUT ON FAN FRAME (9 O`CLOCK STRUT AFT LOOKING FWD) WHICH RADIAL DRIVE SHAFT IS LOCATED WAS PUNCTURED, BOTH ON UPPER AND LOWER SURFACES OF STRUT. IT WAS AGREED TO CARRY OUT ENGI NE REMOVAL AND RETURN ENGINE TO REPAIR FACILITY. HYDRAULIC FLUID WAS FOUND IN OIL SYSTEM, AIR STARTER AND CSD OIL SUMPS . ALL OIL WETTED ITEMS REQUIRE INSP. ENGINE HAD UNDERGONE TROUBLESHOOTING FOR HIGH OIL CONSUMPTION FOLLOWING REPORTS O N 2 FLIGHTS AND RETURN ON DEC 22, 2006. LEVELS OF 2.08 GALLON QUARTERS/HOUR WERE REPORTED AND AVERAGE OIL CON WAS 0.15 2 L 7 2 4F 4 F RT A16WE E2GL 2007021300055 20070213 00055 CE 2007 2 13 2007FA0000109 1 20070131 G 2730 50524401 BELLCRANK BEECH 90 65A901 1152901 CE PWA PT6 PT6* 52043 EA ELEVATOR FAILED C NBFG O OTHER O OTHER NR NOT REPORTED 1 EA 27 87V LM130 FOUND BROKEN FORK ON ELEVATOR BELLCRANK SUPPORT ARM AT FWD END OF ELEVATOR LT PUSHROD. FOUND THE PUSH ROD FWD ATTACH BO LT HAD BEEN OVER-TORQUED SO MUCH AS TO CREATE A 0.016 INCH -0.021 INCH DEPRESSION IN EACH (MAGNESIUM) FORK WHERE THEY PR ESSED INTO THE ROD END BEARING. MFG SB2231R2 INCLUDES: INSPECTION FOR CRACKS IN THIS AREA OF ELEVATOR BELLCRANK. PROPE R GAP BETWEEN ROD END AND SUPPORT ARM FORKS (0.00 INCH TO 0.01 INCH GAP) PROPER TORQUE OF PUSHROD ATTACH BOLT (70-108 IN CH LBS) RECOMMEND FOLLOWING PROPER INSPECTION, INSTALLATION AND TORQUE WHEN INSTALLING THE BELLCRANK AND PUSHRODS. FOL LOW THE INSTRUCTIONS IN THE MM AND SB2231R2. (K) 1 L 7 2 3T 3 T 3A20 E2NE 2007020900036 20070209 00036 CE 2007 2 9 2007FA0000112 1 20070108 G 7160 1116 AIR FILTER CESSNA 172 R172K 2072431 CE CONT IO360 IO360* 17025 CE TWISTED G K NONE O OTHER IN INSP/MAINT 1 SO 15 758EJ R1723034 DURING REMOVAL OF THE AIR FILTER THE CENTER WIRE MESH SCREEN WAS FOUND TWISTED AND BENT. SOME OF THE WELDS WERE BROKEN. SCREEN DEFORMATION CAN LEAD TO UNFILTERED AIR AND FOD ENTERING THE ENGINE. APPARENT CAUSE IS EITHER OVERTORQUEING WIN G NUT AND/OR INSUFFICIENT STRENGTH OF SCREEN. RECOMMEND UTILIZING A STRONGER MESH/PERFORATED SCREEN OR EVALUATING INSTA LLATION INSTRUCTIONS/TORQUEING PROCEDURES. 1 H 7 1 3O 3 O 3A17 E1CE 2007021200156 20070212 00156 GL 2007 2 12 2007FA0000113 1 20070205 G 6500 E181150P V-BELT AMTR ROTWAY EXEC162F 056037T GL TAIL ROTOR BROKEN G R AUTOROTATION F FLT CONT AFFECTED CR CRUISE 1 CE 07 113JD 80 6107 V BELT PREMATURELY FAILED. THIS IS A 250 HOUR CHANGE OUT PART. 1 G 7 1 3O O EXPA1G71 2007031200062 20070312 00062 SO 2007 3 12 2007FA0000114 1 20070206 G 2820 W70120TE CONNECTOR GULSTM GV GULFSTREAMGV 3980116 SO FUEL LINE LOOSE C K NONE K FLUID LOSS IN INSP/MAINT 1 GL 15 83M 557 FUEL LINE CONNECTOR IN MAIN WHEEL WELL COMING LOOSE, RESULTING IN FUEL LEAKING INTO WHEEL WELL.REFERENCE MFG ILLUSTRATED PARTS CATALOG; 28-26-00, FIGURE 5, PAGE 2, ITEM 205, PN W701-20TE. WE ARE HAVING THIS PROBLEM ON MORE THAN ONE OF OUR AIRCRAFT. THERE IS NO WAY TO SAFETY THIS FITTING. THIS SITUATION COULD RESULT IN FUEL BEING SPRAYED ON A HOT BRAKE RES ULTING IN A FIRE. 2 L 7 2 4F RT A12EA 2007022000010 20070220 00010 CE 2007 2 20 2007FA0000115 1 20070111 G 7120 MOUNT BEECH 36 A36 1151604 CE CONT O550 IO550B SO MCAULY 3A32C D3A32C* GL ENGINE CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 13 1562F E2857 687034 940159 PERFORMED ANNUAL INSPECTION ON ENGINE, FOUND BLACK (FRETTING) CORROSION BELOW CENTER 2 (LT AFT) ENGINE MOUNT BOLTS. BOL TS WERE LOOSE IN MOUNT, BUT THE NUTS WERE TIGHT ON BOLTS. PROBLEM IS THAT THE BOLTS ARE A LITTLE TOO LONG AND THE NUTS WERE RUNNING OUT OF THREADS ON THE BOLTS. SOLUTION WAS TO ADD ANOTHER WASHER BELOW THE NUTS, THEN RETORQUE BACK TO SPEC S. (K) 1 L 7 1 3O 3 O 3A15 E3SO 5 C P21EA 2007051100144 20070511 00144 2007 5 11 2007FA0000119 1 20070208 G 2435 23085001 STARTER GEN OUT OF TOLERANCE B K NONE O OTHER IN INSP/MAINT 1 EA 65 603W 36 36 S/G SUSPECTED TO HAVE IMPROPER DRIVE SHAFT INSTALLED. DRIVE SHAFT MEASURES LONGER THAN ANOTHER S/G WITH SAME PN. ENGINE HAVE THEIR STARTER MOUNT BEARING FAIL. 2007021300067 20070213 00067 CE 2007 2 13 2007FA0000120 1 20070129 G 3340 CM358910 SWITCH CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA TAXI LIGHT ODOR B ODAR A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 EA 21 321ME 172S8566 PILOT REPORTED TO APPROACH THAT THERE WAS AN ELECTRICAL SMELL IN CABIN. AN EMERGENCY WAS DECLARED AND AIRCRAFT LANDED W ITHOUT INCIDENT. UPON INSPECTION, FOUND THE TAXI LIGHT CIRCUIT BREAKER/SWITCH WAS SLIGHTLY DISCOLORED, SMELLED BURNED A ND IT WAS INOPERATIVE. THERE WAS NO APPARENT OTHER DAMAGE TO CIRCUIT OR ANY OTHER PART. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2007022000016 20070220 00016 2007 2 20 2007FA0000121 4 20070130 G 3418 C528072 TRANSDUCER PIPER PA46 PA46500TP 7104622 SO STALL WARNING FAILED G O OTHER O OTHER NR NOT REPORTED 1 CE 07 5337N 320 4697102 THIS UNIT WAS INSTALLED 12 MONTHS AGO. THIS IS A TYPICAL LIFE SPAN. CAUSE OF MALFUNCTION IS UNIT BEING OVERHEATED IN F LIGHT. THEY CAN`T TURN DOWN THE HEAT BECAUSE OF THE WAY IT WAS CERTIFIED. MOST PILOTS DO NOT KNOW THIS UNIT IS INOPERA TIVE. THE STALL WARNING HORN WILL SOUND EVEN THOUGH THE UNIT IS BAD. (K) 1 L 7 1 3O RT A25SO 2007021300057 20070213 00057 EA 2007 2 13 2007FA0000122 2 20070105 G 8530 NUT CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA ARM RETAINER LOOSE B ONFR O OTHER O OTHER NR NOT REPORTED 1 EA 05 5123E 1788 17271722 RL8312761 THE NR 3 CYLINDER EXHAUST ROCKER ARM RETAINING NUT BECAME LOOSE, REDUCING LIFT ON THE EXHAUST VALVE, NOT ALLOWING SUFFIC IENT AIR TO EXIT THE CYLINDER. PRESSURE IN THE CYLINDER EXCEDED THE STRENGTH OF THE INTAKE VALVE SYSTEM TO OPEN, CAUSIN G THE INTAKE PUSHROD TO FALL (BEND). RECOMMEND A SIMPLE LOCKPLATE BE ADDED UNDER THE ROCKER ARM RETAINING NUT WITH A LO CK TAB TO ELIMINATE THIS POSSIBLE FAILURE. (K) 1 H 7 1 3O 3 O NT 3A12 E274 2007030900126 20070309 00126 CE 2007 3 9 2007FA0000141 1 20070205 G 2820 0500106326 FUEL LINE CESSNA 180 180 2072602 CE FUEL SYS WORN D O OTHER W INADEQUATE Q C NR NOT REPORTED 1 AL 05 4000 FLAP CABLE WEARING INTO FUEL LINE. FUEL LINE WAS INCORRECTLY ASSEMBLED. VISUAL INSPECTION OF AREA AT ANNUAL OR 100 HR INSPECTIONS. (K) 1 H 7 1 3O NC 5A6 2007022600185 20070226 00185 SO 2007 2 26 2007FA0000144 1 20070205 G 3230 6741102 SWITCH PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA MLG FROZEN C O OTHER O OTHER NR NOT REPORTED 1 EA 17 1533E 347350050 UPON LANDING, GEAR EXTENSION, DURING APPROACH TO LANDING, PILOT NOTED AN EXCEPTIONALLY LONG TIME BETWEEN GEAR SWITCH AC TUATION AND INDICATION OF ALL DOWN AND LOCKED. OUTSIDE TEMP +9 F. BELIEVE THAT SWITCH ARM FOR DOWNLOCK HAD FROZEN IN P LACE (UP) AND REQUIRED TIME TO ACTUATE. (K) 1 L 7 2 3O 3 O A7SO 1E10 2007022600076 20070226 00076 CE 2007 2 26 2007FA0000145 1 20070215 G 7810 02R3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA LT ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 09 6162 731 PCE85441 WHILE PERFORMING SCHEDULED MAINTENANCE, REMOVED LT ENGINE EXHAUST STACKS TO FACILITATE INSPECTING THE EXHAUST DUCT. FOU ND A 14 INCH CRACK FOLLOWING THE CIRCUMFERENCE OF THE SKI SLOPE WITH A 3 INCHES CRACK PROPAGATING LONGITUDELY AT THE 10 O'CLOCK POSITION FROM THE 14 INCHES CRACK. EXHAUST DUCT HAD PWA SB 3380 COMPLIED WITH 731 HOURS EARLIER. BECAUSE OF THE REMAINING ENGINE TIME, IT WILL BE PULLED FOR OVERHAUL. 1 L 7 2 4T 4 T A24CE E4EA 2007022300288 20070223 00288 CE 2007 2 23 2007FA0000147 1 20070201 G 2571 HOSE BEECH 95 B95 1153404 CE BATTERY BOX DISCONNECTED C K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 9631R TD314 BATTERY ELECTROLYTE RESIDUE FOUND ON LEFT NOSE GEAR DOOR AND LOWER FORWARD FUSELAGE. INSPECTION REVEALED BATTERY BOX DR AIN HOSE DISCONNECTED AND HANGING IN LOWER NOSE STRUCTURE AREA BELOW THE BAGGAGE FLOOR. ACCESS IS HINDERED BY NUMEROUS FASTENERS THAT ARE HARD TO REMOVE. AT SOME TIME IN THE PAST THE ADF ANTENNA MAST, WHICH DOUBLED AS THE BATTERY DRAIN MA ST, HAD BEEN REMOVED AND THE BATTERY DRAIN HOSE WAS NOT RECONNECTED TO A SUITABLE DRAIN. THIS COULD CAUSE CORROSION DAM AGE TO NOSE AREA LOWER STRUCTURE ON TRAVEL AIR AND BARON AIRPLANES, WHICH HAVE SIMILAR DESIGN. BEECH MODEL 95 PARTS AND SHOP MANUALS CARRY NO REFERENCES ABOUT THE BATTERY DRAIN SYSTEM. SUGGEST REVIEW OF ANY RAYTHEON SERVICE BULLETINS DISC 1 L 7 2 3O 3A16 2007030100236 20070301 00236 SO 2007 3 1 2007FA0000148 1 20070214 G 3234 761213 LEVER PIPER PA23 PA23250 7102308 SO LYC O540 TIO540* 41532 EA COCKPIT BROKEN D F7HS O OTHER O OTHER CL CLIMB 1 WP 13 31PD 7657 277654016 LANDING GEAR LEVER BROKE AT THE RIVET DURING TAKEOFF, AFTER RAISING LANDING GEAR LEVER UP TO RETRACT LANDING GEAR. (K) 1 L 7 2 3O 3 O 1A10 E14EA 2007030100201 20070301 00201 2007 3 1 2007FA0000149 2 20070209 G 7414 6310 MAGNETO ENGINE MALFUNCTIONED B WS9R K NONE R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 NM 07 MAGNETO IS MISSING AT HIGH ALTITUDE. (K) 2007030100202 20070301 00202 2007 3 1 2007FA0000150 2 20070209 G 7414 6310 MAGNETO ENGINE MALFUNCTIONED B WS9R K NONE R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 NM 07 2 MAGNETO`S MISSING AT HIGH ALTITUDE. (K) 2007030900152 20070309 00152 SW 2007 3 9 2007FA0000151 1 20070214 G 5712 FASTENER BBAVIA 7 7ECA 21101NN SW LYC O235 O235* 41505 EA WING OUT OF POSITION D O OTHER O OTHER NR NOT REPORTED 1 NE 05 5505N 126678 RIB NAILS PULLING OUT IN ALMOST EVERY RIB. RT TIP RIB HAS ALL NAILS PULLED OUT AND A SPACE BETWEEN RIBS AND SPARS, BOT H FRONT AND REAR LOCATIONS. LT WING HAS ONE NAIL THAT IS ABOUT TO FALL OUT AS IT IS PULLED/WORKED OUT .4375 INCH. 80 P ERCENT OF RIBS HAVE AT LEAST ONE NAIL OUT OVER .1250 INCH, AND ONLY APPROX 10 PERCENT OF TOTAL NAILS ARE NOT MOVING. HA VE NOT DISASSEMBLE YET FOR SPAR DAMAGE, BUT HAVE SEEN A FEW NAILS THAT ARE (SMOKING) WHERE THEY CONTACT THE ALUMINUM RIB . ALL FOUND DURING ROUTINE INSPECTION AT ANNUAL IAW AD AND APPLICABLE SB`S IAW THE AD. (K) 1 H 7 1 3O 3 O A759 E223 2007030900114 20070309 00114 SO 2007 3 9 2007FA0000155 2 20070212 G 8530 CYLINDER CESSNA 206 U206B 2073322 CE CONT O520 IO520F 17032 SO ENGINE CRACKED D O OTHER O OTHER NR NOT REPORTED 1 AL 03 4988F U2060688 CRACKED CYLINDER HEAD BETWEEN 4TH AND 5TH FIN IB OF TOP SPARK PLUG. CRACKS HEADED TOWARD VALVE SEAT. (K) 1 H 7 1 3O 3 O A4CE E5CE 2007032900296 20070329 00296 SO 2007 3 29 2007FA0000156 2 20070212 G 8530 CYLINDER CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO ENGINE CRACKED D O OTHER O OTHER NR NOT REPORTED 1 AL 03 7711D U20603170 CRACKED CYLINDER LEAD BETWEEN 4TH AND 5TH FIN IB AT UPPER SPARK PLUG. CRACK NOT VISIBLE INSIDE CYLINDER. (K) 1 H 7 1 3O 3 O A4CE E5CE 2007030900046 20070309 00046 SO 2007 3 9 2007FA0000157 2 20070212 G 8530 AEC63139 CYLINDER CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO ENGINE CRACKED D O OTHER O OTHER NR NOT REPORTED 1 AL 03 7711D 10226 U20603170 CRACKED CYLINDER BETWEEN 2ND AND 3RD FIN IB OF UPPER SPARK PLUG ORIENTED DOWN SIDE OF CYL HEAD. LARGE NEAR SEPARATION. (K) 1 H 7 1 3O 3 O A4CE E5CE 2007030900127 20070309 00127 SO 2007 3 9 2007FA0000158 2 20070212 G 8530 AEC631397 CYLINDER CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO ENGINE CRACKED D O OTHER O OTHER NR NOT REPORTED 1 AL 03 7711D U20603170 CYLINDER HEAD CRACKED AT UPPER SPARK PLUG HOLE THRU BEND TO EXHAUST SEAT. (K) 1 H 7 1 3O 3 O A4CE E5CE 2007030900303 20070309 00303 CE 2007 3 9 2007FA0000162 1 20070206 G 5511 233201015 SPAR CAP LEAR LEAR 35 35A 5170602 CE GARRTT TFE731 TFE731* 01518 WP HORIZ STAB CORRODED C BHKR K NONE O OTHER IN INSP/MAINT 1 EA 21 96FN 17284 1187 186 VISUAL CONDITION CHECK PERFORMED ON HORIZONTAL STABILIZER AFT SPAR CAP AND ELEVATOR HINGE BRACKETS FOR CORROSION, BROKEN FASTENERS, ETC. FOUND SEVERE CORROSION ON UPPER SPAR CAP ASSEMBLY ALONG ENTIRE LENGTH. THIS REQUIRED REMOVAL AND REPL ACEMENT OF UPPER SPAR CAP. CORROSION CAUSED BY OPERATING CONDITIONS, LACK OF CONSISTENT WASHING PROGRAM AND POSSIBLE EX POSED, UNPROTECTED METAL. RECOMMENDA CONSISTENT AIRCRAFT WASHING PROGRAM WHEN OPERATIONS ARE IN OR NEAR COSTAL REGIONS AND ENSURING ALL EXPOSED SURFACES ARE PROPERLY TREATED AND PAINTED. (K) 2 L 7 2 4F 4 F A10CE E6WE 2007030900161 20070309 00161 SO 2007 3 9 2007FA0000163 1 20070201 G 8120 FITTING PIPER PA32 PA32301T 7103209 SO LYC O540 TIO540S1AD 41532 EA HARTZL HCE3Y HCE3YR1 GL TURBOCHARGER CRACKED D O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 05 8185Y 522 328024018 L699564A FM1408B THIS PART IS BOLTED TO THE TURBOCHARGER ASSY BETWEEN THE HOT AND COLD SECTIONS. THE HIGH PRESSURE OIL LINE CONNECTS TO THIS PART VIA A FITTING IN THE TOP OF THE PART. AFTER AN ANNUAL INSP, THE ENG WAS RUN-UP AND SYSTEM CHECKED. AN OIL SE EP WAS NOTED IN THE TURBOCHARGER AREA. THE HIGH PRESSURE OIL LINE AND FITTING WAS REMOVED. PN LW 14465 WAS REMOVED AND CLEANED. THE CRACK WAS NOTED. THE PART WAS REPLACED WITH NEW. AFTER RESEARCHING THE AC RECORDS, IT WAS NOTED THAT EXH AUST SYS, INCLUDING TURBOCHARGER WASTE GATE AND CONTROL ROD END WAS NOT OVERHAULED WITH THE ENGINE CORE AS REQUIRED BY M FG. TURBOCHARGER WAS REPLACED WITH NEW UNIT AT TIME OF O/H. UNKNOWN IF PN LW-14465 WAS REPLACED AT THAT TIME. PART IS 1 L 7 1 3O 3 O A3SO E14EA 5 C P33EA 2007032900265 20070329 00265 EA 2007 3 29 2007FA0000164 2 20070206 G 8500 ENGINE CESSNA 206 T206H 2073303 CE LYC O540 TIO540A1A 41532 EA MAKING METAL D K NONE O OTHER IN INSP/MAINT 1 GL 21 3543B T20608330 L1123761A UNDER NORMAL CONDITIONS AND UNDER OIL SAMPLE PROGRAM, ENGINE HAS HAD (6) HIGH BAD SAMPLES, HIGH IRON, COPPER AND ALUMINU M. AC IS A PUBLIC USE AIRCRAFT WITH CUSTOMS AND BORDER PROTECTION, BUT AM REPLACING ENGINE WITH NEW/ OVERHAUL. CONTACT ED MFG ABOUT PROBLEM BUT WAS TOLD TO KEEP CHANGING OIL AND FILTERS. RECOMMEND THA THIS TYPE ENGINE BE INVESTIGATED CLOS ER. THIS ENGINE WAS CHANGED IN 2005 DUE TO SIMILAR PROBLEM. (K) 1 H 7 1 3O 3 O RT A4CE E14EA 2007031200262 20070312 00262 CE 2007 3 12 2007FA0000165 1 20070206 G 5511 233201015 SPAR CAP LEAR 35 36LEAR 5170601 CE GARRTT TFE731 TFE731* 01518 WP HORIZ STAB CORRODED C BHKR K NONE O OTHER IN INSP/MAINT 1 EA 21 12FN 15719 016 VISUAL CONDITION CHECK PERFORMED ON HORIZONTAL STABILIZER AFT SPAR CAP AND ELEVATOR HINGE BRACKETS FOR CORROSION, BROKEN FASTENERS, ETC. FOUND MODERATE CORROSION ON UPPER SPAR CAP ASSY AT LT OB ELEVATOR HINGE AREA. THIS REQUIRED REMOVAL A ND REPLACEMENT OF UPPER SPAR CAP. CORROSION CAUSED BY OPERATING CONDITIONS, LACK OF CONSISTENT WASHING PROGRAM AND POSS IBLE EXPOSED, UNPORTECTED METAL. RECOMMEND A CONSISTENT AC WASHING PROGRAM WHEN OPERATIONS ARE IN OR NEAR COASTAL REGIO NS AND ENSURING ALL EXPOSED SURFACES ARE PROPERLY TREATED AND PAINTED. (K) 2 L 7 2 4F 4 F A10CE E6WE 2007022600030 20070226 00030 EU 2007 2 26 2007FA0000166 1 20070223 G 6230 1090110677 FITTING AGUSTA A109 A109A2 0260120 EU ALLSN 250C 250C20 03013 GL MAIN ROTOR WORN D K NONE O OTHER IN INSP/MAINT 1 EA 35 745HA 32 7413 MAIN ROTOR DRIVELINK UPPER FITTING STEEL BUSHES (109-0110-70-1) AND UPPER SLEEVE (109-0110-69-1) SEVERELY WORN. SLEEVE STEPPED TO LESS THAN HALF MANUFACTURED DIAMETER AT BOTH ENDS. STEEL BUSHES WORN THROUGH COMPLETELY, WEAR EXTENDING INTO FITTING. HOLE IN BOTH ENDS OF FITTING FOR STEEL BUSHES ELONGATED. PHOTOGRAPHS AND DISCREPANT PARTS AVAILABLE IF REQUI RED. DEFECTIVE PARTS REPLACED. 1 G 7 2 3U 3 U H7EU E4CE 2007030900122 20070309 00122 SO 2007 3 9 2007FA0000168 1 20070206 G 5711 SPAR PIPER J3 J3C65 7100510 SO WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 05 6609H 2884 19808 DURING REMOVAL OF LT WING FOR INSTALLATION OF WING FUEL TANK, A QUESTIONABLE PREVIOUS REPAIR WAS FOUND AT THE FRONT WOOD SPAR ROOT. FURTHER INVESTIGATION FOUND LONGNATUDINAL CRACKS OF THE LT AND RT, FOR AND AFT WOOD WING SPARS. THESE CRAC KS WERE VISIBLE WITH A BARE EYE WHEN THE FRONT SPAR CARRY ATTACH INSPECTION PANEL WAS REMOVED AND INSPECTED FROM THE FRO NT CABIN AREA. CRACKS ARE NOT UNCOMMON AFTER 60 YEARS OF HARD SERVICE AND NATURAL DEGRADATION OF THE WOOD. (K) 1 H 7 1 3O A691 2007022600170 20070226 00170 SO 2007 2 26 2007FA0000169 1 20070223 G 5751 86562025 AILERON PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA RIGHT MISREPAIRED B O OTHER W INADEQUATE Q C NR NOT REPORTED 1 WP 07 576ER 3598 4496152 DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD LEAD TO A SPIN. AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI GHTS BOTH BY COMPANY PILOTS AND MFG FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET. MFG HAS A HISTORY OF AILERON SKIN CRACKING. (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM.) O NCE THE CRACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON. DURING SKIN REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE T/E TAKES ON A (FAT) CONDITION. THIS LEADS 1 L 7 2 3O 3 O A19S0 E286 2007022700048 20070227 00048 CE 2007 2 27 2007FA0000171 1 20070220 G 3230 504501033 TORQUE TUBE CESSNA CESSNA 340 340A 2076405 CE CONT O550 IO550* SO MLG BINDING D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 15 467DB 340A0467 DURING REPLACEMENT OF ORIGINAL EQUIPMENT TORQUE TUBE (P/N 5045010-18/19) WITH MFG REPLACEMENT P/N 5045010-32/33 INTERFER ENCE BETWEEN THE TORQUE TUBE AND AIRFRAME ATTACHMENT FITTING WAS DISCOVERED. RIGGING THE MLG TO ACHIEVE A .1250 DROP OF F WAS IMPOSSIBLE DUE TO THE INTERFERENCE BETWEEN THE TORQUE TUBE AND THE ATTACHMENT FITTING. DROP OFF IS ACHIEVED ONCE T HE TORQUE TUBE ROTATES FAR ENOUGH OVER CENTER TO ALLOW THE GEAR TO DROP .1250 BACK DOWN FROM ITS MAXIMUM HEIGHT. MFG TE CHNICAL SUPPORT INDICATED THAT THE ORIGINAL TORQUE TUBE (-18/19) HAD A FLAT SPOT BETWEEN THE AFT HINGE ARMS DESIGNED TO CLEAR THE AIRCRAFT STRUCTURE. THIS FLAT SPOT WAS ORIENTED AT A 33 DEGREE OFFSET. THE TORQUE TUBES WERE REDESIGNED IN 197 1 L 7 2 3O 3 O 3A25 E3SO 2007022700051 20070227 00051 2007 2 27 2007FA0000173 2 20070222 G 7414 6310 MAGNETO ENGINE MALFUNCTIONED C O OTHER O OTHER NR NOT REPORTED 1 NM 07 2 MAGNETO CAUSING HIGH ALTITUDE MIS-FIRE. 2007022700087 20070227 00087 CE 2007 2 27 2007FA0000174 1 20070201 G 2432 HOSE BEECH 95 B95 1153404 CE LYC O360 O360* 41514 EA BATTERY DRAIN DISCONNECTED C K NONE K FLUID LOSS IN INSP/MAINT 1 NM 01 9631R TD314 BATTERY ELECTROLYTE RESIDUE FOUND ON LT NOSE GEAR DOOR AND LOWER FORWARD FUSELAGE. INSPECTION REVEALED BATTERY BOX DRAI N HOSE DISCONNECTED AND HANGING IN LOWER NOSE STRUCTURE AREA BELOW THE BAGGAGE FLOOR. ACCESS IS HINDERED BY NUMEROUS FA STENERS THAT ARE HARD TO REMOVE. AT SOME TIME IN THE PAST THE ADF ANTENNA MAST, WHICH DOUBLED AS THE BATTERY DRAIN MAST , HAD BEEN REMOVED AND THE BATTERY DRAIN HOSE WAS NOT RECONNECTED TO A SUITABLE DRAIN. THIS COULD CAUSE CORROSION DAMAG E TO NOSE AREA LOWER STRUCTURE ON TRAVEL AIR AND BARON AIRPLANES, WHICH HAVE SIMILAR DESIGN. PARTS AND SHOP MANUALS CAR RY NO REFERENCES ABOUT THE BATTERY DRAIN SYSTEM. SUGGEST REVIEW OF ANY MFG SB DISCUSSING BATTERY BOX DRAIN COMPONENTS, 1 L 7 2 3O 3 O 3A16 E286 2007030200033 20070302 00033 CE 2007 3 2 2007FA0000175 1 20070216 G 1100 070507109 PLACARD CESSNA 206 206CESSNA 2073302 CE LYC O540 TIO540AJ1A EA MCAULY 3D36C B3D36C432 GL WING FADED D K NONE O OTHER IN INSP/MAINT 1 EA 27 150 T20608291 L1083261A 002324 P/N 0705071-9) FUEL QUANTITY AND TYPE PLACARDS HAVE BEEN REPLACED ABOUT ONCE A YEAR DUE TO FADING. THIS AIRCRAFT IS HAN GARED. THIS FADING HAS BEEN NOTED WITH OTHER MFG AIRCRAFT. RETAIL COST LAST YEAR NR 50.00+. THIS HAS NOW DOUBLED. OW NERS DON'T PLACARD IMPORTANCE FOR AIRWORTHINESS. 1 H 7 1 3O 3 O A4CE E14EA 5 C P58GL 2007031200032 20070312 00032 CE 2007 3 12 2007FA0000176 1 20070222 G 2752 55651904 ROLL PIN CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE SPROCKET BROKEN B K NONE O OTHER IN INSP/MAINT 1 SW 13 797CW 8177 1200 5500232 DURING A PHASE 5 INSPECTION THE FLAPS SEAMED TO BE SLOW AND BINDING. AT CLOSER INSPECTION IT WAS FOUND THAT THE ROLL PIN HAD BROKEN ALLOWING THE SPROCKET TO MOVE FWD. ON THE P/N 5565190-9 BRAZE ASSY-DRIVE THIS CAUSED BINDING AND ALLOWED THE SPROCKET TO EVEN DROP DOWN ON TO THE P/N 6565193-9 CHAIN GUARD-LOWER FWD. THIS IS A HARD AREA TO LOOK AT EVEN WITH A MI RROR. A FEW MORE ACTIONS WITH THE FLAP WOULD HAVE LED TO TOTAL FAILURE OF THIS SYSTEM. 1 L 7 2 4F 4 F A22CE E1NE 2007030200034 20070302 00034 SO 2007 3 2 2007FA0000177 1 20070223 G 5751 86562025 AILERON PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA WING MISREPAIRED D O OTHER W F INADEQUATE Q C FLT CONT AFFECTED CR CRUISE 1 WP 07 570ER 3583 4496146 DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD LEAD TO A SPIN. AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI GHTS BOTH BY COMPANY PILOTS AND MFG FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET. MFG HAS A HISTORY OF AILERON SKIN CRACKING. (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM). O NCE THE CRACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON. DURING SKIN REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE TRAILING EDGE TAKES ON A (FAT) CONDITION. 1 L 7 2 3O 3 O A19S0 E286 2007030800056 20070308 00056 SO 2007 3 8 2007FA0000178 1 20070223 G 5751 86562025 AILERON PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA WING MISREPAIRED B O OTHER W F INADEQUATE Q C FLT CONT AFFECTED CR CRUISE 1 WP 07 571ER 3801 4496147 DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD LEAD TO A SPIN. AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI GHTS BOTH BY COMPANY PILOTS AND PIPER FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET. PI PER HAS A HISTORY OF AILERON SKIN CRACKING. (IT HAS BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM). ONCE THE C RACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON. DURING SKIN REPLACEME NT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE TRAILING EDGE TAKES ON A (FAT) CONDITION. THIS LEAD 1 L 7 2 3O 3 O A19S0 E286 2007030800057 20070308 00057 SO 2007 3 8 2007FA0000179 1 20070223 G 5751 86562025 AILERON PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA WING MISREPAIRED A O OTHER W F INADEQUATE Q C FLT CONT AFFECTED CR CRUISE 1 WP 07 572ER 3160 4496148 DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD LEAD TO A SPIN. AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI GHTS BOTH BY COMPANY PILOTS AND MFG FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET. MFG HAS A HISTORY OF AILERON SKIN CRACKING. (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM.) O NCE THE CRACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON. DURING SKIN REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE TRAILING EDGE TAKES ON A (FAT) CONDITION. 1 L 7 2 3O 3 O A19S0 E286 2007030800058 20070308 00058 SO 2007 3 8 2007FA0000180 1 20070223 G 5751 86562025 AILERON PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA WING MISREPAIRED B O OTHER W F INADEQUATE Q C FLT CONT AFFECTED CR CRUISE 1 WP 07 573ER 3969 4496149 DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD LEAD TO A SPIN. AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI GHTS BOTH BY COMPANY PILOTS AND PIPER FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET. MF G HAS A HISTORY OF AILERON SKIN CRACKING. (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM). ONCE THE CRACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON. DURING SKI N REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE TRAILING EDGE TAKES ON A (FAT) CONDITION. 1 L 7 2 3O 3 O A19S0 E286 2007030800059 20070308 00059 SO 2007 3 8 2007FA0000182 1 20070223 G 5751 86562025 AILERON PIPER PA44 PA44180 7104402 SO LYC O320 O320* 41508 EA WING MISREPAIRED B O OTHER W F INADEQUATE Q C FLT CONT AFFECTED CR CRUISE 1 WP 07 577ER 3881 4496153 DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AIRCRAFT WOULD SUDDENLY BREAK LT AND IF NOT IMMEDIATELY STOPPED COULD LEAD TO A SPIN. AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLI GHTS BOTH BY COMPANY PILOTS AND MFG FACTORY TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET. MFG HAS A HISTORY OF AILERON SKIN CRACKING. (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLEM.) O NCE THE CRACK IS PAST A CERTAIN POINT YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON. DURING SKIN REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE THE TRAILING EDGE TAKES ON A (FAT) CONDITION. 1 L 7 2 3O 3 O A19S0 E274 2007022700060 20070227 00060 EA 2007 2 27 2007FA0000183 2 20070211 G 8540 13S19646 GEAR CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL CRANKSHAFT LOOSE D A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 GL 15 242SP 1855 172S8226 L2830651A SK039 DURING TAKEOFF AT 400 FT AGL ENGINE QUIT FORCING AN OFF AIRPORT EMERGENCY LANDING. INITIAL INSPECTION FOUND NO MOVEMENT OF ACCESSORIES AND VALVE MOVEMENT. REMOVED ACCESSORIES CASE AND FOUND DRIVE GEAR ON CRANKSHAFT MOUNT BOLT LOOSE AND PI N SHEARED. MARKS SHOW THAT BOLT AND GEAR WERE LOOSE FOR SOME TIME ALLOWING WEAR ON PIN UNTIL FAILURE. SUSPECT INCORRECT TORQUE OR INCORRECT SEATING OF GEAR TO FLANGE. ALSO WITH GEAR LOOSE BOLT COULD BE TURNED IN LOCKING TAB. HOLE IN LOCKI NG TAB TOO LOOSE ON BOLT. ENGINE NEW FROM MFG. WITH 1855.3 HOURS. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2007032900295 20070329 00295 EA 2007 3 29 2007FA0000185 2 20070222 G 7414 ESIO357424 BUSHING BENDIX MOONEY M20 M20D 5870210 SW LYC O360 O360A1D 41514 EA MAGNETO LOOSE D O OTHER O OTHER NR NOT REPORTED 1 WP 17 6914U 31 1060379 246 BRONZE BUSHING VERY LOOSE IN DISTRIBUTOR BLOCK AND MAG WOULD NOT OPERATE CORRECTLY. AN EMERGENCY LANDING WAS MADE. (K) 1 L 7 1 3O 3 O 2A3 E286 2007030900172 20070309 00172 SO 2007 3 9 2007FA0000186 2 20070222 G 7414 BUSHING BENDIX CESSNA 172 172D 2072410 CE CONT O300 O300D 17022 SO MAGNETO LOOSE D K NONE O OTHER NR NOT REPORTED 1 WP 17 2948U 194 17250548 BRONZE BUSHING, VERY LOOSE IN DISTRIBUTOR BLOCK AND DISTRIBUTOR ARM WAS CONTACTING PINS IN BLOCK. MAG WOULD NOT OPERATE CORRECTLY. (K) 1 H 7 1 3O 3 O NT 3A12 E253 2007030900140 20070309 00140 EU 2007 3 9 2007FA0000187 1 20070222 G 2910 285683 COUPLING AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE7312 01518 WP HYDRAULIC SYS DEFECTIVE D O OTHER O OTHER NR NOT REPORTED 1 GL 03 43EC 9017 168 THIS COUPLING IS A QUICK-DISCONNECT TYPE FITTING THAT IS IN LINE OF THE ENGINE DRIVEN HYDRAULIC PUMP AND LOCATED IN THE ENGINE PYLON. THERE IS ONLY ONE ON EACH ENGINE AND ONLY ON THE SUCTION LINE. THESE FITTINGS HAVE NO TIME CHANGE REQUIR EMENT. WHEN THIS PART WAS CHANGED (DUE TO EXTERNAL LEAKAGE) IT WAS EXTREMELY DIFFICULT TO SEPARATE. ONCE SEPARATED, TH E LOCKING BALLS HAD DUG SO DEEPLY INTO THE LOCK RING THAT PARTIAL UNSEATING OF THE O-RING HAD OCCURRED. THERE QUICK DIS CONNECT COUPLINGS (LT AND RT) SHOULD BE REQUIRED TO BE INSPECTED AT EACH ENGINE REMOVAL AND REPLACED IF WEAR IS DETECTED . (K) 2 L 7 2 4F 4 F A33EU E6WE 2007032900294 20070329 00294 CE 2007 3 29 2007FA0000188 1 20070215 G 2510 551900922 SEAT CESSNA CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE COCKPIT CRACKED D O OTHER O OTHER NR NOT REPORTED 1 CE 05 404BS 5500403 UPPER CHAIR BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAI R WAS REPAIRED IAW STC 01042WI STRUCTURAL SEAT REPAIR. (K) 1 L 7 2 4F 4 F A22CE E1NE 2007032600101 20070326 00101 CE 2007 3 26 2007FA0000189 1 20070226 G 2750 051010593 CONTROL CABLE CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA TE FLAPS FRAYED B O OTHER O OTHER NR NOT REPORTED 1 GL 05 31SZ 13729 13729 17267732 PILOT REPORTED EXCESSIVE MOVEMENT IN LT FLAP DURING PRE-FLIGHT WALK AROUND OF AIRCRAFT. INITIAL INVESTIGATION BY MAINTE NANCE PERSONNEL CONFIRMED FINDINGS. MAINTENANCE PERSONNEL DISCOVERED THAT CABLE P/N 0510105-93 HAD MULTIPLE BROKEN STRA NDS/FRAYING NEAR THE TURNBUCKLE END. SUSPECTED CAUSE OF DAMAGE TO CABLE IS DUE TO EXCESSIVE FLEXING BETWEEN TURNBUCKLE END AND FLAP POSITION INDICATOR CLAMP, P/N 0560037-1. AD 80-06-03 HAD BEEN COMPLIED WITH ON 10/11/1982 BY INSTALLATION OF KIT SK172-60A. 1 H 7 1 3O 3 O NT 3A12 E274 2007030100205 20070301 00205 GL 2007 3 1 2007FA0000190 3 20070221 G 6114 C4201C58 HUB MCAULY MCAULY 2A34C D2A34C58 GL PROPELLER CRACKED B LT4R K NONE O OTHER IN INSP/MAINT 1 SO 19 720009 720009 HUB RECEIVED DISASSEMBLED, CLEANED AND ANODIZED WITH NO CERTIVICATION. BLADE RETENTION THREADS EDDY CURRENT INSPECTED. NR 1 BLADE RETENTION THREAD, 4 THREADS IN AT APPROXIMATELY 6 O`CLOCK POSITION FOUND CRACKED. HUB REMOVED FROM SERVICE. (K) 5 C P3EA 2007030900119 20070309 00119 EU 2007 3 9 2007FA0000191 1 20070227 G 5730 S25WS3001 SKIN BRAERO DH125 HS125700A 4230170 EU GARRTT TFE731 TFE731* 01518 WP RT WING CORRODED D O OTHER O OTHER NR NOT REPORTED 1 WP 23 224EA 9121 257088 RT WING LEADING EDGE(S) HAD SEVERE CORROSION WHERE THE TKS PANELS ATTACH. AFTER COMPLETE DISASSEMBLY IT WAS DETERMINED TO BE BEYOND ECONOMICAL REPAIR. RT WING LEADING EDGE HAD BEEN INSPECTED AT MFG 2.5 YEAR PRIOR TO THIS DISCOVERY. (K) 2 L 7 2 4F 4 F A3EU E6WE 2007032600144 20070326 00144 EU 2007 3 26 2007FA0000192 1 20070227 G 5754 S25WS3002 SKIN BRAERO DH125 HS125700A 4230170 EU GARRTT TFE731 TFE731* 01518 WP RT WING LE CORRODED D O OTHER O OTHER NR NOT REPORTED 1 WP 23 224EA 9121 257088 RT WING LEADING EDGE(S) HAD SEVERE CORROSION WHERE THE TKS PANELS ATTACH. AFTER COMPLETE DISASSEMBLY, IT WAS DETERMNED TO BE BEYOND ECONOMICAL REPAIR. RT WING LEADING EDGE HAD BEEN INSPECTED AT MFG 2.5 YEARS PRIOR TO THIS DISCOVERY. (K) 2 L 7 2 4F 4 F A3EU E6WE 2007040200170 20070402 00170 2007 4 2 2007FA0000193 2 20070213 G 7414 6350 ROTOR MAGNETO BROKEN D O OTHER O OTHER NR NOT REPORTED 1 SW 99 ROTOR AT ROTOR GEAR AND BROKEN. (K) 2007030900133 20070309 00133 EU 2007 3 9 2007FA0000194 1 20070221 G 5512 25TP1001A SKIN BRAERO DH125 HS125700A 4230170 EU GARRTT TFE731 TFE731* 01518 WP HORIZ STAB CORRODED C O OTHER O OTHER NR NOT REPORTED 1 WP 01 224EA 9121 257088 LT AND RT HORIXONTAL STABILIZER LEADING EDGES HAD SEVERE CORROSION WHERE THE TKS PANELS ATTACH. AFTER COMPLETE DISASSEM BLY, IT WAS DETERMINED TO BE BEYOND ECONOMICAL REPAIR. THIS AREA HAD BEEN INSPECTED AT MFG 2.5 YEARS PRIOR TO THIS DISC OVERY. (K) 2 L 7 2 4F 4 F A3EU E6WE 2007032900299 20070329 00299 CE 2007 3 29 2007FA0000195 1 20070129 G 3233 LIMIT SWITCH CESSNA 310 310J 2074226 CE CONT O470 IO470* 17026 SO NLG ACTUATOR FAILED G O OTHER O OTHER NR NOT REPORTED 1 SO 15 3091L 310J0091 UP LIMIT SWITCH FAILED ON LANDING GEAR ACTUATOR, CAUSING OVER EXTENSION OF NOSE GEAR SYSTEM. THIS CAUSED THE INTERMEDIA TE TORQUE TUBE TO BEND. (K) 1 L 7 2 3O 3 O 3A10 E1CE 2007040200168 20070402 00168 WP 2007 4 2 2007FA0000196 2 20070220 G 7261 8961051 COVER BEECH 100 B100 1152919 CE GARRTT TPE331 TPE3316 01514 WP LT ENGINE BROKEN D O OTHER O OTHER NR NOT REPORTED 1 WP 09 241CW BE54 P27188 PILOT REPORTED HIGH OIL CONSUMPTION, INSPECTED LT ENGINE SCAVENGE PUMP AND FOUND THE PUMP COVER BROKEN AND MISSING PIECE S. ALSO FOUND THE SCAVENGE PUMP OIL TUBE COVER BROKEN AND CHAFING A HOLE THROUGH THE OIL TUBE. RECOMMEND REMOVING EXHA UST PIPE AT INSPECTIONS TO INSPECT PUMP COVER AND TUBE ASSY FOR DEFECTS. (K) 1 L 7 2 4T 4 T A14CE E4WE 2007030900116 20070309 00116 CE 2007 3 9 2007FA0000199 1 20070301 G 2571 07120591P SUPPORT CESSNA 182 182T 2072703 CE LYC O540 IO540* 41532 EA BATTERY BOX CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 15 3539G 18281039 FOUND BATTERY SUPPORT CRACKED. TOTAL AIRFRAME TIME 1075. THIS IS THE 3RD ONE THAT WE FOUND. SUPPORTS NEED TO BE BEEFE D UP, THEY ARE TOO LIGHT FOR THE APPLICATION. (K) 1 H 7 1 3O 3 O NT 3A13 1E4 2007030900157 20070309 00157 CE 2007 3 9 2007FA0000200 1 20070301 G 2571 07120591P SUPPORT CESSNA 182 182T 2072703 CE LYC O540 IO540* 41532 EA BATTERY BOX CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 15 65KC 18281015 FOUND BATTERY SUPPORT CRACKED. TOTAL AIRFRAME TIME 1716. THIS IS THE THIRD ONE THAT WE FOUND SUPPORTS NEED TO BE BEEFE D UP, THEY ARE TOO LIGHT FOR THE APPLICATION. (K) 1 H 7 1 3O 3 O NT 3A13 1E4 2007031200254 20070312 00254 EA 2007 3 12 2007FA0000201 2 20070221 G 8520 V53793493 CRANKSHAFT CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE CORRODED B YYBR K NONE O OTHER IN INSP/MAINT 1 GL 03 982BT 4744 2196 17280307 L1466351A THIS CRANKSHAFT WAS LAST INSPECTED AND PID COATED AT THE FACTORY APRIL 23, 2002, YET 6 YEARS AND 2196 HOURS LATER, IT WA S PITTED, AND REQURIED FURTHER MACHINING. THE PID COATING DOES NOT SEEM TO HOLD UP, OR BLOCK THE CORROSION. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2007031200253 20070312 00253 EA 2007 3 12 2007FA0000202 2 20070223 G 8520 V537925914 CRANKSHAFT CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE CORRODED B YYBR K NONE O OTHER IN INSP/MAINT 1 GL 03 988BC 4170 2211 17280472 L2494851A DURING SCHEDULED OVERHAUL, THIS CRANKSHAFT WAS FOUND PITTED IN THE INNER BORE. THIS ENGINE WAS A FACTORY OVERHAUL JULY 2002, AND DID HAVE THE PID COATING. THE COATING DOES NOT SEEM TO BLOCK THE CORROSION. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2007030900154 20070309 00154 EU 2007 3 9 2007FA0000203 1 20070213 G 8120 LW18607 STRUT PARTEN P68 P68TCOBS 6780108 EU TURBO BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 01 737 40004OTC RL20464A UPON REMOVING ENGINE FROM SHIPPING CRATE, FOUND (NEW) TURBO SUPPORT STRUT CRACKED. THESE BRACKETS CRACK ALL THE TIME ON THE AIRPLANE. VERY POOR DESIGN! (K) 1 H 7 2 3O RT A31EU 2007030900155 20070309 00155 EU 2007 3 9 2007FA0000204 1 20070213 G 8120 LW18607 STRUT PARTEN P68 P68TCOBS 6780108 EU TURBO BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 01 737 40004OTC RL20364A UPON REMOVING ENGINE FROM SHIPPING CRATE, FOUND (NEW) TURBO SUPPORT STRUT, CRACKED. THESE BRACKETS CRACK ALL THE TIME I N THE AIRPLANE. VERY POOR DESIGN! (K) 1 H 7 2 3O RT A31EU 2007032900292 20070329 00292 CE 2007 3 29 2007FA0000205 1 20070222 G 3610 1H1069 MIXING VALVE LEAR 60 60LEAR 5170707 CE PWA 305 PW305 NE BLEED AIR SYS INTERMITTENT C A UNSCHED LANDING J B WARNING INDICATION SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 GL 11 500 83 306 SHORTLY AFTER TAKEOFF, AIRCRAFT (L BLEED AIR) WARNING ILLUMINATED, AND (R BLEED AIR) WARNING ILLUMINATED APPROX 5 SEC LA TER, SMELLED ODOR IN CABIN. REDUCED POWER AND WARNING WENT OUT. AIRCRAFT DIVERTED FOR MAINTENANCE. UNABLE TO DUPLICAT E MALFUNCTION ON GROUND RUN, LT MIXING VALVE WAS SUSPECTED, SO REPLACED. PERFORMED GROUND RUN FUNCTIONAL TEST OF BLEED AIR SYSTEM, AND FLIGHT TEST. NO FURTHER BLEED AIR WARNINGS. (K) 2 L 7 2 4F 4 F RT A10CE E35NE 2007030800083 20070308 00083 SO 2007 3 8 2007FA0000206 1 20070223 G 5751 86562025 AILERON PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA WING MISREPAIRED B BF8X O OTHER W F INADEQUATE Q C FLT CONT AFFECTED CR CRUISE 1 WP 07 575ER 3448 4496151 DURING POWER OFF (CLEAN CONFIGURATION) STALLS, THE AC WOULD SUDDENLY BREAK LEFT AND IF NOT IMMEDIATELY STOPPED COULD LEA D TO A SPIN. AFTER RERIGGING ALL FLIGHT CONTROLS, CHECKING THE AIRCRAFT ALIGNMENT WITH A LASER AND SEVERAL TEST FLIGHTS BOTH BY COMPANY PILOTS AND MFG TEST PILOT, IT WAS DETERMINED THAT WE HAD (FAT) AILERONS ON OUR FLEET. THIS MAKE OF AIR CRAFT HAS A HISTORY OF AILERON SKIN CRACKING. (FOR US, IT HAS JUST BEEN THE RT AILERON THAT HAS HAD THE CRACKING PROBLE M). ONCE THE CRACK IS PAST A CERTAIN POINT , YOU EITHER HAVE TO REPLACE THE AFFECTED SKIN OR REPLACE THE AILERON. DURI NG SKIN REPLACEMENT, IF THE PREFORMED FACTORY SKIN IS SPREAD APART EVEN A LITTLE, THE TRAILING EDGE TAKES ON A (FAT) CON 1 L 7 2 3O 3 O A19S0 E286 2007030900004 20070309 00004 CE 2007 3 9 2007FA0000207 1 20070301 G 2432 G35 BATTERY CESSNA 180 180 2072602 CE CONT O470 O470* 17026 SO LEAKING D O OTHER O OTHER NR NOT REPORTED 1 GL 15 9198C 34 31297 BATTERY ACID LEAKED OR TRANSFERRED TO AFT, LOWEST CELL (AIRCRAFT TAIL WHEEL) AND SPILLED OUT. CORRODED HOLE IN BATTERY BOX AND SPILLED INTO BELLY OF AIRCRAFT. 1 H 7 1 3O 3 O NC 5A6 E273 2007030900005 20070309 00005 CE 2007 3 9 2007FA0000208 1 20070301 G 2432 G35 BATTERY CESSNA 180 180 2072602 CE CONT O470 O470* 17026 SO LEAKING D O OTHER O OTHER NR NOT REPORTED 1 GL 15 9198C 34 31297 BATTERY ACID LEAKED OR TRANSFERRED TO AFT, LOWEST CELL (AIRCRAFT TAIL WHEEL) AND SPILLED OUT. CORRODED HOLE IN BATTERY BOX AND SPILLED INTO BELLY OF AIRCRAFT. 1 H 7 1 3O 3 O NC 5A6 E273 2007032200025 20070322 00025 2007 3 22 2007FA0000209 4 20070306 G 2350 9903334446 AUDIO CONTROL GULSTM G1159 G1159 3953505 SO PWA 530 PW530A NE COCKPIT SHORTED C O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 EA 21 685SF 94 UNIT WAS MANUFACTURED IN AUGUST 06 AND WAS INSTALLED IN DECEMBER 06. THE UNIT POPPED THE CIRCUIT BREAKER ON THE FIRST TR IP. THE UNIT WAS SENT IN FOR REPAIR AND REINSTALLED IN FEBRUARY 07 AND FAILED AGAIN ON THE FIRST FLIGHT. 2 L 7 2 4F 4 F RT A12EA E00053EN 2007030900041 20070309 00041 SO 2007 3 9 2007FA0000210 2 20070220 G 8530 639614639615 ROCKER CONT O300D CESSNA 172 172H 2072424 CE CONT O300 O300D 17022 SO ENGINE INCORRECT D K NONE R PARTIAL RPM/PWR LOSS CR CRUISE 1 EA 17 8848Z 110 64805D6D 17255498 64805D6D PILOT REPORTED LOSS OF POWER (600 RPM DROP) SIGNIFICANT ENGINE ROUGHNESS DURING CLIMB. ENGINE RECOVERED SHORTLY AFTERWAR DS. PILOT ELECTED TO CONTINUE AND HAD SAME PROBLEM AGAIN DURING CRUISE FLIGHT. ENGINE RECOVERED ON ITS OWN ONCE AGAIN. P ILOT SAID CARB HEAT DID NOT MAKE ANY IMPROVEMENT DURING BOTH OCCURRENCES. AIRCRAFT WAS TURNED OVER TO MAINTENANCE. THE ONLY ABNORMALITY DISCOVERED WAS THAT THE EXHAUST VALVES ON 4 OF THE 6 CYLINDERS HAD INCORRECT ROCKER INSTALLED (639614, INTAKE ROCKER). PARTS MANUAL CALLS FOR 639615 (EXHAUST ROCKER) TO BE INSTALLED ON EXHAUST POSITION. 1 H 7 1 3O 3 O NT 3A12 E253 2007030900073 20070309 00073 CE 2007 3 9 2007FA0000214 1 20070307 G 8011 85562020 STARTER CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE SPINNING G O OTHER O OTHER NR NOT REPORTED 1 WP 05 767CL 57 172S9987 STARTER SPINS AND WILL NOT ENGAGE. 1 H 7 1 3O 3 O NT 3A12 1E10 2007032200081 20070322 00081 CE 2007 3 22 2007FA0000215 1 20070301 G 3230 MS2764816 BEARING BEECH 90 F90 1152909 CE PWA PT6 PT6A135 52043 NE MLG SEIZED B K NONE O OTHER IN INSP/MAINT 1 SO 07 19RK 9280 LA12 PERFORMING A ROUTINE 6 YEAR LANDING GEAR OVERHAUL, THE LT LANDING GEAR GEARBOX-ACTUATOR TORQUE TUBE HAD A SEIZED MAIN SU PPORT BEARING. THIS MADE THE TORQUE TUBE EXTREMELY HARD TO TURN. THE BEARING WAS FOUND TO BE RUSTED, AND SEIZED. BEARING WAS REPLACED WITH NEW. 1 L 7 2 4T 4 T A31CE E4EA 2007040200169 20070402 00169 EA 2007 4 2 2007FA0000218 2 20070202 G 8550 56G23399 BAFFLE PIPER PA32 PA32301 7103207 SO LYC O540 TIO540AH1A 42003 EA OIL SUMP CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 07 447KC 85 3255047 L1239361A DURING ENGINE OIL CHANGE FOUND RIVET HEAD IN OIL SUMP SCREEN. REMOVED ENGINE AND OIL SUMP ASSY. FOUND OIL SUMP BAFFLE ASY RIVETS SHEARED OFF AND ATTACH HOLES BROKEN OUT AND BAFFLE ASSY CRACKED. RETRIEVED RIVET STEMS AND HEADS. REMOVED A ND REPLACED OIL SUMP BAFFLE ASSY WITH NEW PART. REASSEMBLED ENGINE AND REINSTALLED. (K) 1 L 7 1 3O 3 O A3SO E14EA 2007032900269 20070329 00269 EA 2007 3 29 2007FA0000219 2 20070302 G 7310 B-NUT CESSNA 182 182T 2072703 CE LYC O540 IO540AB1A5 EA FUEL SYSTEM LOOSE D K NONE O OTHER IN INSP/MAINT 1 SO 11 38AL 18281450 L2980148A IN THIS CASE, FOUND THAT THE B-NUT CONNECTING TO THE FUEL CONTROL FROM THE SPIDER WAS LOOSE. IT WAS NOT LEAKING, BUT RE QUIRED A THIRD OF A TURN TO TORQUE DOWN TO PROPER TORQUE. NO OTHER WORK HAS BEEN DONE TO THE SPIDER OR FUEL CONTROL BEC AUSE I HAVE DONE THE WORK SINCE NEW ON THIS AIRCRAFT. TT 228.8. REMEMBER FINDING A LOOSE FIREWALL FITTING ON THE FIRST INSPECTION. THIS IS THE SECOND INSPECTION DONE ON THIS AIRCRAFT. IT WAS CERTIFIED 11/11/2004. (K) 1 H 7 1 3O 3 O NT 3A13 1E4 2007032900280 20070329 00280 CE 2007 3 29 2007FA0000220 1 20070223 G 2510 551900921 SEAT CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE COCKPIT CRACKED D O OTHER O OTHER NR NOT REPORTED 1 CE 05 630CC 5500130 UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW ST01042WI STRUCTURAL SEAT REPAIR. (K) 1 L 7 2 4F 4 F A22CE E1NE 2007040200237 20070402 00237 EA 2007 4 2 2007FA0000221 2 20070222 G 8520 CRANKSHAFT CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE CORRODED B YYBR K NONE O OTHER IN INSP/MAINT 1 GL 03 2199 L130951A DURING NORMAL OVERHAUL, CRANKSHAFT FOUND PITTED IN THE INTERNAL BORE. THIS ENGINE WAS LAST OVERHAULED BY THE FACTORY, J ULY 2002.. THE PID COATING DOES NOT SEEM TO PREVENT PITTING OR CORROSION. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2007050400165 20070504 00165 CE 2007 5 4 2007FA0000222 1 20070215 G 2821 99120154 FUEL FILTER CESSNA 500 500CESSNA 2076602 CE PWA JD15 JT15D1A NE RT WING SEPARATED D J7BR O OTHER O OTHER NR NOT REPORTED 1 SW 01 409S 10045 5000238 THE RT FUEL FILTER ASSY SEPARATED FROM THE STANDPIPE DUE TO THE SNAP-RING BECOMING DISLOGED AND RESULTED IN A SUBSTANTIA L FUEL LEAK. (K) 1 L 7 2 4F 4 F A22CE E25EA 2007032900273 20070329 00273 EA 2007 3 29 2007FA0000223 2 20070124 G 7261 OIL FILTER PIPER PA32 PA32R300 7103213 SO LYC O540 IO540* 41532 EA ENGINE COLLAPSED D K NONE K FLUID LOSS NR NOT REPORTED 1 SW 99 OIL LEAK NOTED AFTER OIL CHANGE. REMOVED OIL FILTER AND DISCOVERED PARTIAL COLLAPSE OF THE OIL FILTER ELEMENT. IT WAS DETERMINED THAT THE ENGINE MOUNTED INTERNAL BY-PASS VALVES OPERATION. PREVIOUS TO THIS OCCURRENCE THE SB MENTION HAD NO T BEEN COMPLIED WITH. AFTER THIS OCCURRENCE, SB WERE COMPLIED WITH AND A NEW OIL FILTER OF THE SAME MAKE AND MODEL WAS INSTALLED AND THE SYSTEM FUNCTIONED PROPERLY. SUBMITTER SUGGESTS THAT DUE TO THE SIGNIFICANT NR OF OCCURRENCES OF THIS TYPE THAT SB SI-1442 AND 1453 BECOME MANDATORY THROUGH AD FOR ADDED SAFETY. (K) 1 L 7 1 3O 3 O A3SO 1E4 2007040200127 20070402 00127 CE 2007 4 2 2007FA0000224 1 20070215 G 2821 99120154 FUEL FILTER PUROLATOR CESSNA 500 500CESSNA 2076602 CE PWA JD15 JT15D1A NE RT WING SEPARATED B J7BR O OTHER O OTHER NR NOT REPORTED 1 SW 01 409S 10045 5000238 76509 THE RT FUEL FILTER ASSY SEPARATED FROM THE STANDPIPE DUE TO THE SNAP-RING BECOMING DISLODGED AND RESULTED IN A SUBSTANTI AL FUEL LEAK. 1 L 7 2 4F 4 F A22CE E25EA 2007032900297 20070329 00297 SO 2007 3 29 2007FA0000225 1 20070215 G 2750 62679000 BRACKET PIPER PA28 PA28* SO COCKPIT CRACKED D O OTHER O OTHER NR NOT REPORTED 1 NE 03 THIS BRACKET IS RIVETED IN THE CENTER TUNNEL AND ACCEPTS (2) BOLTS AT THE FORWARD SIDE OF THE FLAP HANDLE SUPPORT MOUNT. THIS IS A DIFFICULT AREA TO SEE, EVEN WITH A MIRROR. WE HAVE FOUND (6) CRACKED BRACKETS SO FAR TO DATE. SUSPECT FATI GUE AND AIR LOADS CAUSING CRACKS. (K) 1 L 7 1 3O 2A13 2007040200158 20070402 00158 SO 2007 4 2 2007FA0000226 2 20070220 G 8500 ENGINE CESSNA 404 404 2075901 CE CONT O520 GTSIO520M 17032 SO FAILED D O OTHER O OTHER NR NOT REPORTED 1 CE 03 442EH 4040202 604103 THIS ENGINE FAILED TO THE TERMINOLOGY OF CATASTROPHIC AT THE NR 1 AND NR 2 CYLINDER CONNECTING ROD LOCATIONS DURING A MA INTENANCE TEST FLIGHT WITHIN TEN MINUTES INTO THAT FLIGHT WITH A MECHANIC ON BOARD MONITORING THE ENGINE INSTRUMENTS. T HE OIL PRESSURE SUDDENLY DROPPED TO ZERO, THE PROPELLER STARTED TO FEATHER AND DURING SHUTDOWN AND SECURING, THE ENGINE LOCKED UP. PRIOR TO THIS, THE OIL FILTER WAS REMOVED, CUT OPEN AND INSPECTED WITH NO DEFECTS NOTED. AN OIL SOAP SAMPLE WAS TAKEN. THE OIL PUMP AND AIRCRAFT OIL PRESSURE GAUGE WAS CHECKED FOR A POSITIVE OIL PRIME AND INDICATION. AN EXTEN DED ENGINE GROUND RUN WAS DONE AT LOW AND HIGH POWER SETTINGS WITH NO OIL PRESSURE DISCREPANCIES NOTED. THESE CHECKS WE 1 L 7 2 3O 3 O RT A25CE E7CE 2007031300197 20070313 00197 CE 2007 3 13 2007FA0000227 1 20070119 G 8011 85A34117 STARTER CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE STUCK G O OTHER O OTHER NR NOT REPORTED 1 WP 05 767CL 527 172S9987 STARTER STUCK IN ENGAGED POSITION. 1 H 7 1 3O 3 O NT 3A12 1E10 2007050400138 20070504 00138 NM 2007 5 4 2007FA0000228 1 20070306 G 3260 SENSOR BOEING 747 747230B 1384889 NM GE CF6 CF650* 30018 NE MLG MALFUNCTIONED B GJPY O OTHER O OTHER NR NOT REPORTED 1 WP 33 760SA 21221 DURING TAKEOFF, THE LANDING GEAR HANDLE WILL NOT GO TO UP OR RETRACT POSITION. AIRCRAFT RETURNED TO BASE. PERFORMED TR OUBLESHOOTING ON THE LANDING GEAR SYSTEM AND FOUND THAT LT WING GEAR TRUCK ROTATION SENSOR AT FAULT. ADJUSTED THE LT WI NG GEAR TRUCK ROTATION SENSOR IAW AMM 32-61-04. PERFORMED LANDING GEAR SYSTEM EXTENSION AND RETRACTION SEVERAL TIMES IA W AMM 32-32-00/501, TEST NORMAL. (K) 2 L 7 4 4F 4 F A20WE E23EA 2007041200027 20070412 00027 EU 2007 4 12 2007FA0000229 1 20070308 G 2820 653014 VALVE ISRAEL 1124 1124A 4500103 EU GARRTT TFE731 TFE731* 01518 WP RT LWR FUEL CELL CRACKED B JGVR O OTHER O OTHER NR NOT REPORTED 1 CE 09 328PC 8597 328 CRACK IN INTERCONNECT VALVE MOTOR HOUSING. FOUND DURING BAG REMOVAL AND REINSTALLATION. CAUSE OF CRACK, UNKNOWN. (K) 2 M 7 2 4F 4 F A2SW E6WE 2007032900293 20070329 00293 SO 2007 3 29 2007FA0000230 1 20070220 G 5521 4602003 RIB PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA LT ELEVATOR BROKEN B K NONE O OTHER IN INSP/MAINT 1 SO 09 112ED 31T8020060 1 INCH CRACK NOTED ON LOWER SKIN THRU RIVET. DRILLED OPEN SKIN AND FOUND 5 INCH OF RIB FLANGE BROKE OFF 2 INCHS FROM TR AILING EDGE. SKIN AND RIB HAVE TO BE REPLACED. (K) 1 L 7 2 3T 4 T A8EA E4EA 2007032900298 20070329 00298 SO 2007 3 29 2007FA0000231 1 20070215 G 2910 HYDRAULIC LINE PIPER PA23 PA23250 7102308 SO LYC O540 IO540* 41532 EA HYDRAULIC SYS CHAFED G O OTHER K FLUID LOSS NR NOT REPORTED 1 SO 19 144CN 5200 278054036 AIRCRAFT HYDRAULIC SYSTEM RT GEAR DOWN ALUMINUM LINE LOCATED UNDER COCKPIT FLOOR WAS CHAFING AGAINST CONTROL CABLE AND W AS PENETRATED CAUSING LEAK AND DEPLETION OF HYDRO FLUID WHICH RESULTED IN AIRCRAFT LANDING WITH UNSAFE NOSE GEAR AND DAM AGE TO AIRCRAFT NOSE SECTION. THIS AREA SHOULD BE INSPECTED AT LEAST DURING ANNUAL INSPECTIONS. (K) 1 L 7 2 3O 3 O 1A10 1E4 2007050700186 20070507 00186 SO 2007 5 7 2007FA0000232 1 20070305 G 2432 RG380E44 BATTERY LKHEED 1329 1329* SO GARRTT TFE731 TFE7313 01518 WP MASTER FAILED B VXWR O OTHER O OTHER NR NOT REPORTED 1 EA 21 58TS 5079 75238 THESE 2 EA PN RG-380E/44 MAIN SHIP BATTERIES WERE INSTALLED ON 10/30/2006. THESE BATTERIES WERE REPLACEMENTS FOR 2 EA B ATTERIES THAT HAD BEEN IN SATISFACTORY SERVICE IN THIS AC FOR APPROX 48 MONTHS BUT FAILED A CAPACITY CHECK DURING A REGU LAR SCHEDULED INSPECTION. LESS THAN 2 MONTHS AFTER INSTALLATION THE PILOTS WERE UNABLE TO START THE MAIN ENGINES USING THESE BATTERIES. AT THIS TIME THE BATTERIES HAD A TOTAL FLIGHT TIME OF 16 HOURS AND HAD PERFORMED 26 MAIN ENGINE STARTS AND 8 APU STARTS. THE MAIN ENGINES WERE STARTED USING A GROUND POWER UNIT. ALL CHARGING AND ELECTRICAL OPERATIONS APP EARED NORMAL. THE BATTERIES WERE REMOVED AND GIVEN TO REPAIR STATION FOR TESTING. BOTH BATTERIES WERE TESTED IAW (INST 2 L 7 4 4J 4 F 2A15 E6WE 2007032900290 20070329 00290 EA 2007 3 29 2007FA0000233 2 20070312 G 7414 M3081 SPRING SLICK CESSNA 182 T182T 2072738 CE LYC O540 TIO540AK1A EA RT MAGNETO BROKEN D K NONE O OTHER IN INSP/MAINT 1 WP 29 5198G 658 66LC35SDNP T18208150 L1121761A NEW POINTS (PN M3081) WERE INSTALLED IN BOTH MAGNETOS AT THE ANNUAL INSPECTION ON 2/22/07, TT 649.2. ON 3/10/07, TT 658 .2, PART TT - 9.0 HOURS, THE PILOT/OWNER PERFORMED MAG CHECK AND THE ENGINE QUIT. A MECHANIC REMOVED THE RT MAG AND FOU ND THAT THE SPRING THAT HOLDS HALF THE POINTS HAD SNAPPED OFF. THE MECHANIC TOLD THE OWNER THAT HE HAD NEVER SEEN POINT S FAIL LIKE THIS IN HIS 30 YEARS OF AC MAINTENANCE. TOLD HIM THAT I HAD NEVER SEEN THIS TYPE OF MALFUNCTION IN MY 10 YE ARS OF MAINTENANCE. IT APPEARS THAT THE METAL SPRING THAT MAKES UP THE POINT KIT FAILED JUST AFT OF THE AREA WHERE THE METAL IS BENT ON BOTH EDGES FOR STRENGTHING PURPOSE. THE BREAK IS IN A SEMICIRCLE FRO ONE SIDE TO THE OTHER. THE METAL 1 H 7 1 3O 3 O NT 3A13 2007040900162 20070409 00162 GL 2007 4 9 2007FA0000234 3 20070317 G 6111 F8483 BLADE HARTZL HCC3Y HCC3YR GL PROPELLER MISREPAIRED B ME4R O OTHER W INADEQUATE Q C NR NOT REPORTED 1 SO 19 DY5121B (REF NR: 38430A) 2 OF 3 PROPELLER BLADES WERE PREVIOUSLY REPAIRED USING AN UNAPPROVED WELD METHOD IN SEVERAL LOCATIONS O N THE BLADE AIRFOIL. THE BLADES HAVE BEEN SCRAPED PENDING DISPOSITION INSTRUCTIONS FROM MFG. THE CUSTOMER HAS BEEN CON TACTED FOR HISTORICAL RECORDS. (K) 5 C P25EA 2007050700183 20070507 00183 GL 2007 5 7 2007FA0000235 3 20070317 G 6111 F8483 BLADE HARTZL HCC3Y HCC3YR GL PROPELLER MISREPAIRED B ME4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 DY5121B (REF NR 38430A) 2 OF 3 PROPELLER BLADES WERE PREVIOUSLY REPAIRED USING AN UNAPPROVED WELD METHOD IN SEVERAL LOCATIONS O N THE BLADE AIRFOIL. THE BLADES HAVE BEEN SCRAPED PENDING DISPOSITION INSTRUCTIONS FROM MFG. THE CUSTOMER HAS BEEN CON TACTED FOR HISTORICAL RECORDS. (K) 5 C P25EA 2007032900284 20070329 00284 EU 2007 3 29 2007FA0000236 1 20070121 G 2434 TERMINAL SOCATA TB20 TB20TRINIDAD 8680695 EU LYC O540 IO540C4D5 41532 EA ALTERNATOR BROKEN D O OTHER O OTHER NR NOT REPORTED 1 WP 05 711RP 1081 L1813148A FIELD WIRE TERMINAL END BROKEN AT ALTERNATOR TERMINAL LUG CAUSED FAILURE OF ALTERNATOR TO CHARGE BATTERY. (K) 1 L 7 1 3O 3 O RT A51EU 1E4 2007040200214 20070402 00214 CE 2007 4 2 2007FA0000237 1 20070301 G 5610 10138402524 WINDSHIELD BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL COCKPIT CRACKED B AHTR A UNSCHED LANDING O OTHER CR CRUISE 1 GL 11 200VC 728 FL316 AT AN ALTITUDE OF 17,000 FT OAT -6 DEGREES C, THE RT WINDSHIELD CRACKED FROM THE CENTER OB FROM THE TOP TO THE BOTTOM AB OUT 2 INCHES OB ON THE OUTER PANE. RETURNED TO THE DEPARTING AIRPORT WITHOUT ANY PROBLEMS. WINDSHIELD WAS REPLACED AND NO KNOWN CAUSE FOR THE WINDSHIELD TO CRACK. (K) 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 2007032200037 20070322 00037 CE 2007 3 22 2007FA0000238 1 20070316 G 3242 RA66109 BRAKE PADS CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL MLG FRACTURED D K NONE O OTHER IN INSP/MAINT 1 EA 07 6440V 49 172RG0701 L2783136A 951039 DURING A 50 HR OIL CHANGE AND INSPECTION, FOUND BOTH LT AND RT BRAKE PADS FALLING APART, SEVERELY CRACKED WITH LARGE PIE CES MISSING. BOTH SIDES WERE CHANGED AT THE PREVIOUS 100 HOUR INSPECTION. THIS HAS BEEN A FREQUENT PROBLEM WITH THESE BRAKE PADS ON ALL OF OUR AIRCRAFT (2 C152, 1 C172, 1 C172RG), NEW PADS FAILING WITHIN 200 HOURS OR LESS SINCE WE STARTED USING THEM. PREVIOUSLY, WE USED OTHER MFG PADS WITH VERY FEW PROBLEMS. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2007032200092 20070322 00092 CE 2007 3 22 2007FA0000243 1 20070226 G 5310 VP10 ANTENNA BEECH 33 35B33 1151406 CE CONT O470 IO470* 17026 SO VHF SYSTEM MISINSTALLED B A UNSCHED LANDING W D INADEQUATE Q C INFLIGHT SEPARATION CR CRUISE 1 CE 03 1768G 94 94 CD509 THE DOUBLER FOR THE VHF ANTENNA APPEARS TO HAVE BEEN TOO SMALL(SLIGHLY LARGER THAN THE BASE OF THE ANTENNA)AND WAS NOT R IVITED TO THE FUSELAGE,ALLOWING THE ANTENNA TO FLUTTER WHILE AIRBORNE.ON POST FLIGHT INSPECTION THE PILOT DISCOVERED TEA RING ON THREE SIDES ON TOP OF THE FUSELAGE AROUND THE BASE OF THE ANTENNA.NOTE THE TACH ONLY READS 94.5 1 L 7 1 3O 3 O 3A15 E1CE 2007032200093 20070322 00093 CE 2007 3 22 2007FA0000244 1 20070301 G 5551 071204221 BRACKET CESSNA 185 A185F 2072821 CE CONT O520 IO520* 17032 SO HORIZONTAL STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 07 4640E 18503824 DURING A DETAILED INSPECTION OF THE EMPENAGE, THE RT HORIZONTAL STABILIZER HINGE BRACKET P/N 0712042-2 WAS FOUND CRACKED AND HAD (2) SHEARED RIVETS. UPON DISASSEMBLY THE LT BRACKET P/N 0712042-1 WAS FOUND TO HAVE (2) SHEARED RIVETS. THESE PARTS ARE IN THE MFG 180/185 IPC FIG 32 INDEX NR 36 AND NR 37.THERE IS NOTHING IN THE RECORDS THAT SHOW THESE PARTS CHA NGED, HOWEVER THE RT BRACKET DID HAVE (2) NR 5 RIVETS WHERE ALL OF THE REST ON BOTH BRACKETS WERE NR 4S. LEADING US TO BELIEVE THAT IT MAY HAVE BEEN REPLACED BEFORE. 1 H 7 1 3O 3 O 3A24 E5CE 2007032200098 20070322 00098 CE 2007 3 22 2007FA0000246 1 20070313 G 2820 050011849 LINE CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA FUEL SYSTEM CHAFED D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 30LU 847 17281257 DURING PREFLIGHT INSP. PILOT FOUND FUEL ON RAMP UNDER CENTER FUSELAGE MECHANIC INVESTIGATED INSIDE COCKPIT FLOOR AND FO UND ALUMINUM FUEL LINE CHAFING AGAINST RT STEERING TUBE, CAUSING THE FUEL LEAK. MECHANIC INSPECTED 6 OTHER 2005/2006 172 R AIRCRAFT IN OUR FLEET AND FOUND CHAFING IN (3) OTHER AIRCRAFT, WITH ANOTHER LEAK IMMINENT. ALL AC UNDER 900 HRS AFTT. OUR AIRCRAFT CAME FROM THE FACTORY WITH THIS FUEL LINE/STEERING TUBE CONFIGURATION. SUBMITTER SUGGESTS IMMEDIATE INSPECT ION FOR THIS CONDITION. NOTE: FUEL WAS NOT SMELLED IN COCKPIT. 1 H 7 1 3O 3 O NT 3A12 1E10 2007032200140 20070322 00140 CE 2007 3 22 2007FA0000247 1 20070227 G 7160 11702 CLAMP BEECH 58 58P 1152744 CE CONT O520 TSIO520L 17040 SO LT ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 25 25RL TJ232 0 LT ENGINE REPORTED TO BE ROUGH RUNNING. INDUCTION HOSE CLAMP(P/N-RAM 1170-2)FAILED; ALLOWING INDUCTION COUPLER(P/N-6323 23) TO SEPARATE FROM INDUCTION TUBE. THIS INDUCTION LEAK OCCURRED BETWEEN THE Y AND INTAKE TUBES TO CYLINDERS NR 2, NR 4 AND NR 6. 1 L 7 2 3O 3 O A23CE E8CE 2007032600107 20070326 00107 CE 2007 3 26 2007FA0000253 1 20070307 G 2720 65651412 ACTUATOR CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ELEVATOR BINDING C K NONE O OTHER IN INSP/MAINT 1 SW 13 797CW 8177 300 0232 WHILE REPLACING TRIM ACTUATOR P/N 6565141-2 WITH WHAT MFG SAID WAS AN APPROVED SUB PART P/N 5565450-92. IT WAS FOUND T HAT THE LOLLIPOPS (JACK SCREWS) WERE 5.5 INCHES LONG AND THE ORIGINAL LOLLIPOPS ARE 5.75 INCHES LONG. IF YOU LOOK AT THE COMPONENT MANUAL FOR THIS ACTUATOR 6565141-2 IT SHOWS 4 DIFF. DASH NUMBERS. -4 AT 5.5 INCHES, -7 AT 5.5 INCHES, -15 AT 4.85 INCHES, AND -21 AT 5.75 INCHES ALL WHICH IS TO THE SAME LOLLIPOP P/N. THE -92 ACTUATORS FITS UNITS 692 TO 924, WHIL E OUR UNIT IS 232. MFG NEEDS TO FIX THESE P/NS AND CLEAR THE WAY THESE MANUALS ARE WRITTEN FOR CLARITY. TO MANY ACTUATOR S ARE TO ANOTHER P/N WITH INCORRECT JACKSCREW LENGTHS. 1 L 7 2 4F 4 F A22CE E1NE 2007032600116 20070326 00116 CE 2007 3 26 2007FA0000256 1 20070314 G 7810 655503011 DUCT CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE EXHAUST ASSY MISMANUFACTURED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 13 797CW 5500232 DURING INSPECTION MULTIPLE PATCHES WERE FOUND ON EXHAUST DUCT ASSY P/N 6555030-11. A REPLACEMENT WAS ORDERED AND FOUND T O HAVE 2 HOLES MISDRILLED BY 2 DEGREES. MFG WAS CONTACTED AS TO WHAT COULD BE DONE AND AFTER CONFIRMING THAT IN TRUTH 2 HOLES WERE NOT PROPERLY PLACED WE WERE TOLD THAT IN FACT 4 DUCTS WERE FOUND NOT BUILT CORRECTLY AND 1 HAD GOTTEN TO THE FIELD. MFG HAS AGREED TO ACCEPT THE DUCT BACK FOR REPAIR BUT WANTS TO BILL US FOR THE FIX ON A NEW PART. AFTER REPAIR, W E ARE TO SUBMIT FOR FINANCIAL REIMBURSEMENT FOR THERE ENGINEERING REPAIR. 1 L 7 2 4F 4 F A22CE E1NE 2007032600125 20070326 00125 EA 2007 3 26 2007FA0000257 2 20070224 G 8530 ROCKER SHAFT UNIVAR 108 1081 9230404 NM FRNKLN 6A4150 6A4150* 27024 EA NR 3 CYLINDER BROKEN G B EMER. DESCENT R PARTIAL RPM/PWR LOSS CR CRUISE 1 WP 11 9088K 1082088 THE NR 3 CYLINDER ROCKER ARM SHAFT FAILED (BROKE) AT THE CENTER SUPPORT POSITION. ADDITIONALLY, (2) OF THE (3) ROCKER A RM BOSS SECURING BOLTS FAILED AND THE THIRD BOLT PULL OUT OF THE HEAD. 1 H 7 1 3O 3 O A767 E238 2007032600127 20070326 00127 CE 2007 3 26 2007FA0000258 1 20070301 G 3210 MS2764816 BEARING BEECH 90 F90 1152909 CE PWA PT6 PT6A135 52043 NE LT MLG SEIZED B O OTHER O OTHER NR NOT REPORTED 1 SO 07 19RK 9280 LA12 PERFORMING A ROUTINE 6 YEAR LANDING GEAR OVERHAUL, THE LT LANDING GEAR GEARBOX-ACTUATOR TORQUE TUBE HAD A SEIZED MAIN SU PPORT BEARING. THIS MADE THE TORQUE TUBE EXTREMELY HARD TO TURN. THE BEARING WAS FOUND TO BE RUSTED, AND SEIZED. BEARING WAS REPLACED WITH NEW. 1 L 7 2 4T 4 T A31CE E4EA 2007032600128 20070326 00128 SO 2007 3 26 2007FA0000259 1 20070301 G 8000 PM1201 STARTER PIPER PA28 PA28236 7102815 SO LYC O540 O540J3A5 41532 EA HARTZL HCF3Y HCF3YK1 GL ENGINE WORN G K NONE O OTHER IN INSP/MAINT 1 SO 05 2177Z 28 28 287911154 L2117640A CM288 THIS AIRCRAFT HAS HAD (5) PM1201 STARTERS INSTALLED SINCE 03-08-2004. THE STARTERS HAD TO BE REPLACED AT THE FOLLOWING I NTERVAL: 58 HOURS TIME IN SERVICE, 18 HOURS TIME IN SERVICE, 11 HOURS TIME IN SERVICE, 5 HOURS TIME IN SERVICE, 28 HOURS TIME IN SERVICE. ALL STARTERS SUFFER THE SAME PROBLEM. AFTER THE ENGINE IS STARTED AND THE AIRCRAFT HAS FLOWN FOR A SH ORT PERIOD OF TIME, (LESS THAN ONE HOUR) THE BENDIX GEAR WILL BEGIN TO CREEP OUT AND TRY TO ENGAGE/RUB THE RING GEAR. I N FEW FLIGHT HOURS THE BENDIX GEAR WILL START SHOWING WEAR ON BOTH THE BENDIX GEAR AS WELL AS THE RING GEAR ON THE FLYWH EEL. ALL THE STARTERS WERE REPORTED TO HAVE HAD THE SAME PROBLEM. THE OWNER DECIDED TO REMOVE THE STARTER FROM HIS AIR 1 L 7 1 3O 3 O 2A13 E295 5 C P31EA 2007040300082 20070403 00082 2007 4 3 2007FA0000260 3 20070219 G 6111 3BLADEWOOD68 PROPELLER AMTR KITFOX KITFOX41200 05626LB GL PROPELLER BROKEN G A UNSCHED LANDING O OTHER CR CRUISE 1 SW 11 880BW 219 6 C96010137 OWNER REPORTED 5 MINUTES AFTER TAKEOFF AT 2500 ASL, ALL 3 PROPELLER BLADES DEPARTED. THERE WAS ONE VIOLENT SHAKE AND TH EN SMOOTH GLIDING TO SAFE LANDING OFF AIRPORT. PRELIMINARY EXAM INDICATES ENGINE MOVED ENOUGH TO CAUSE CARBURETOR TO SE PARATE PREVENTING OVERSPEED. SEPARATED BLADES WERE NEVER LOCATED. PROPELLER TO BE REPLACED BY OWNER, THIS IS AN EXPERI MENTAL HOMEBUILT AIRCRAFT. 1 H 7 1 3I NC EXPA1H71 2007032600060 20070326 00060 CE 2007 3 26 2007FA0000261 1 20070322 G 5210 99120754 SEAL CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE CABIN DOOR SEAL MISMANUFACTURED B K NONE O OTHER IN INSP/MAINT 1 SW 13 797CW 8177 300 5500232 WHILE INSTALLING THIS FACTORY NEW SEAL IT WAS NOTED THAT THE SEAL WAS VERY TIGHT GOING AROUND THE DOOR. UPON CABIN PRESS TEST THE SEAL WILL NOT INFLATE DUE TO BEING TO TIGHT. (2) SEAL FROM STOCK WERE TRIED WITH THE SAME AFFECT. THE LAST SE AL WAS INSTALLED AND INFLATED AS SHOULD BE. THE FACTORY NEEDS TO CHECK THERE SEALS CLOSER UPON RECEIPT FROM THERE VENDOR S. 1 L 7 2 4F 4 F A22CE E1NE 2007032600085 20070326 00085 CE 2007 3 26 2007FA0000262 1 20070322 G 7810 655503011 DUCT CESSNA 500 550 2076604 CE ENGINE UNKNOWN B K NONE O OTHER IN INSP/MAINT 1 GL 19 797CW 8177 300 5500232 UPON RECEIVING THE NEW PART P/N 6555030-11 IT WOULD NOT FIT THE ENGINE. THE ORIGINAL DUCT IS 27 .2500 INCH OUTSIDE AND 2 5.5 INCH INSIDE. THE NEW UNIT IS A FULL .5 INCH SMALLER IN DIAMETER ALL AROUND. THIS IS THE SECOND ISSUE WITH THESE DUCT S THE FIRST WERE MIS-DRILLED BY 2 DEGREES AT THE 1 AND 5 O’CLOCK POSITION. THIS NEW DUCT IS NOT EVEN CLOSE TO FITTING. 1 L 7 2 4F A22CE 2007040300037 20070403 00037 EU 2007 4 3 2007FA0000263 1 20070321 G 7600 L810BQ54 SOLENOID SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B NE AUTO THROTTLE UNSERVICEABLE B N37R K NONE O OTHER IN INSP/MAINT 1 SW 15 186AE 189 3872 22484 (REF NR: 186AE-2007-I-0032) WHILE PERFORMING A CHECK OF THE TWIST GRIP SOLENOID, ENGAGED THE SOLENOID BY PLACING THE AUT O/MAN SWITCH TO MAN MODE FOR A TOTAL OF 10 MINUTES. AFTER THE 10 MINUTE PERIOD HAD ELAPSED, RETURNED THE AUTO/MAN SWIT CH TO AUTO. AFTER 15 MINUTES MOVED AUTO/MAN SWITCH BACK TO MAN, THE PISTON FROM THE SOLENOID FAILED TO MOVE. THE PISTO N SHOULD HAVE RETRACED IMMEDIATELY. PROBABLE CAUSE: SOLENOID OVERHEATING AND MALFUNCTIONING. RECOMMENDATION TO PREVENT RECURRENCE: REPLACING CURRENT PN OF SOLENOID WITH ONE THAT CAN EITHER RUN COOLER OR WITHSTAND THE HEAT. (K) 1 G 7 1 3U 3 U H9EU E00054EN 2007040200157 20070402 00157 SO 2007 4 2 2007FA0000264 1 20070306 G 5350 1159B541014 FAIRING GULSTM GV GULFSTREAMGV 3980116 SO RROYCE BR700 BR700715A130 NE FUSELAGE DEPARTED G A UNSCHED LANDING D INFLIGHT SEPARATION NR NOT REPORTED 1 CE 07 401HF 1300 5039 ON MARCH 6, 2007, DURING A FLIGHT, THE SUBJECT AIRCRAFT EXPERIENCED AN IAPPARENT IN-FLIGHT STRUCTURAL FAILURE OF THE RIG HT WING-TO FUSELAGE FORWARD FAIRING. THE INCIDENT OCCURRED AT FLIGHT LEVEL 400 AT 90 DME ON THE (LNK) VOR 220 RADIAL AT .85 MACH. AFTER ONE HOUR AND 45 MINUTES INTO THE FLIGHT (APPROX 2115Z), THE CREW NOTED AN AUDIBLE (THUMP) FOLLOWED BY A (CHANGE IN WIND NOISE). AS THE AIRCRAFT IS EQUIPPED WITH PROXIMITY CAMERAS, THE FIGHT CREW WAS ABLE TO SEE A (HOLE OF SIGNIFICANT SIZE) IN THE AREA OF THE SINGLE POINT REFUELING ACCESS DOOR USING THE LOWER AFT-FACING FUSELAGE CAMERA. TH E FLIGHT CREW NOTIFIED AND REQUESTED EMERGENCY LANDING, WHERE THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. THE FSDO WA 2 L 7 2 4F 4 F RT A12EA E00061EN 2007040200134 20070402 00134 CE 2007 4 2 2007FA0000265 1 20070322 G 2910 270213 REGULATOR LEAR 60 60LEAR 5170707 CE HYD SYS PRESSURE LEAKING C O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 GL 11 500 105 306 IN-FLIGHT FAILURE OF BOTH ENGINE HYDRAULIC PUMPS, AND LOSS OF MAIN HYDRAULIC SYSTEM FLUID. AC DIVERTED TO HOME BASE, DE CLARED EMERGENCY LANDING, UNEVENTFUL. FOUND PRESSURE HOSE ON R ENGINE HAD FAILED, DUE TO OVER-PRESSURE. FOUND RESERVOI R AIR-PRESSURE REGULATOR (PN 2702-12) HAD FAILED, CAUSING LOSS OF HEAD PRESSURE IN RESERVOIR, AND SUBSEQUENT PRESSURE SP IKES IN ENGINE PUMPS, WHICH BURST FLEX LINE ON R ENGINE HYD PUMP, AND DAMAGED FLEX LINE ON L HYD PUMP AS WELL. REPLACED L AND R ENGINE HYDRAULIC PUMPS, ALL FLEX PRESSURE LINES IN ENGINE HYDRAULIC CIRCUIT, HYDRAULIC FILTERS, RESERVOIR PRESS URE REGULATOR, CHECK VALVE, AND FILTER. BLED AIR FROM HYDRAULIC SYSTEM, PERFORMED FUNCTIONAL TESTS AND GROUND RUN, REPL 2 L 7 2 4F RT A10CE 2007050700003 20070507 00003 CE 2007 5 7 2007FA0000266 1 20070315 G 5510 HINGE BRACKET BEECH 23 A23 1151204 CE CONT O346 IO346A 17033 SO SNSNCH 74DC M74DC EA STABILATOR CRACKED B MS2R O OTHER O OTHER NR NOT REPORTED 1 CE 09 3573R 3596 M756 1002075A 8623 UPON REMOVAL OF THE HORIZONTAL STABILATOR FOR BEARING REPLACEMENT, A CRACK WAS NOTED COMING OUT FROM UNDER THE LEFT HING E BRACKET THAT IS RIVETED TO THE SPAR OF THE HORIZONTAL STABILATOR. (K) 1 L 7 1 3O 3 O A1CE E3CE 5 N P88614 2007040200222 20070402 00222 EU 2007 4 2 2007FA0000267 1 20070228 G 8120 4066109031 BEARING SOCATA TB20 TB21 8680697 EU LYC O540 TIO540AB1A 41533 EA TURBOCHARGER FAILED B BNGR O OTHER O OTHER NR NOT REPORTED 1 GL 19 189GT 685 2022 21052261A IN FLIGHT, DROP IN MANIFOLD PRESSURE, TROUBLESHOT, FOUND TURBOCHARGER BEARING FAILURE. FOUND METAL IN OIL FILTER. ENGI NE REMOVED FOR REPAIR. (K) 1 L 7 1 3O 3 O RT A51EU E14EA 2007032900291 20070329 00291 SW 2007 3 29 2007FA0000268 1 20070308 G 2910 20144 B-NUT GULSTM 500 500S 0141107 SW LYC O540 TIO540A1A 41532 EA LT MLG LOOSE D O OTHER O OTHER NR NOT REPORTED 1 GL 19 280MB 3255 PILOT NOTICED A FLUCTUATION AND LOSS OF HYDRAULIC PRESSURE IN FLIGHT, AFTER INSPECTION THE FORWARD HYDRAULIC HOSE B-NUT ON THE LT GEAR ACTUATOR WAS FOUND TO BE LOOSE. THE B-NUT WAS TIGHTENED AND TORQUE SEAL WAS PUT ON THE B-NUT. SERVICED HYDRAULIC RESERVOIR WITH H-5606. AC WAS TEST FLOWN AND LEAK CHECK GOOD. (K) 1 H 7 2 3O 3 O 6A1 E14EA 2007040200129 20070402 00129 CE 2007 4 2 2007FA0000269 1 20070321 G 6100 NONE BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA HARTZL HCD4N3 HCD4N3A GL PROPELLER UNKNOWN B O OTHER O OTHER NR NOT REPORTED 1 SO 13 427DM LJ804 AIRCRAFT HAS RAISEBECK STC SA3593NM INSTALLED WHICH STATES THE PROPS ARE NOT TO BE OPERATED BELOW THE SET MINIMUM RPM. PRE PHASE INSPECTION RUNS REVEALED THIS CONDITION. IAW MFG SERVICE LETTER 61-254 THIS CAN CAUSE NO REACTION MODE VIBRAT ORY RESONANCE AND MAY RESULT IN HIGH STRESS IN THE BLADES. IT WAS RECOMMENDED THAT THE PROPELLERS BE REMOVED AND BE SENT TO A PROPELLER SHOP FOR INSPECTION. CUSTOMER DECLINED RECOMMENDATION. NO FURTHER ACTION WAS TAKEN AT THIS INSPECTION. BOTH THE LT AND RT PROPELLERS HAVE A TSO OF 957.9 AND A TT OF 2615.2 1 L 7 2 3T 4 T 3A20 E4EA 5 C STC 2007040300049 20070403 00049 CE 2007 4 3 2007FA0000270 1 20070326 G 2710 35524314 CONTROL CABLE BEECH 35 N35 1151528 CE CONT O470 IO470* 17026 SO AILERONS WORN C O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 WP 23 1363Z 7541 D6787 (REF MODEL 35 SERIES IPC FIG. 27) LT AILERON CABLE FOUND RIDING ON PROP CONTROL CABLE SHEATH, ABOUT 2 INCHES AFT OF FIR EWALL. AILERON CABLE WAS WORN ABOUT HALF THROUGH, AND THE PROP CABLE WAS WORN THROUGH THE SHEATH TO THE INNER STEEL CAB LE. (VERY DIFFICULT TO ACCESS THIS AREA FOR VISUAL INSPECTION.) NO INDICATION OF RUBBING OR DRAGGING DURING GROUND CONT ROL SYSTEM CHECKS, OR IN FLIGHT. IT IS RELATIVELY EASY TO HAVE THE PROP CONTROL CABLE DISPLACED INTO CONTACT WITH THE A ILERON CABLE WHEN WORKING IN THIS AREA DURING, FOR EXAMPLE, PANEL MODIFICATIONS OR AVIONICS UPGRADES. RECOMMEND VISUAL AND TACTILE INSPECTION IN THIS AREA TO CONFIRM CLEARANCE. UPON REMOVAL OF CABLE ASSEMBLY FOR REPLACEMENT, FOUND ADDITIO 1 L 7 1 3O 3 O 3A15 E1CE 2007040300039 20070403 00039 CE 2007 4 3 2007FA0000274 1 20070322 G 2910 270213 REGULATOR LEAR 60 60LEAR 5170707 CE HYD SYSTEM LEAKING C O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 GL 11 500 105 306 IN-FLIGHT FAILURE OF BOTH ENGINE HYDRAULIC PUMPS, AND LOSS OF MAIN HYDRAULIC SYSTEM FLUID. AIRCRAFT DIVERTED TO HOME BA SE, DECLARED EMERGENCY LANDING, UNEVENTFUL. FOUND PRESSURE HOSE ON R ENGINE HAD FAILED, DUE TO OVER-PRESSURE. FOUND RE SERVOIR AIR-PRESSURE REGULATOR (PN 2702-12) HAD FAILED, CAUSING LOSS OF HEAD PRESSURE IN RESERVOIR, AND SUBSEQUENT PRESS URE SPIKES IN ENGINE PUMPS, WHICH BURST FLEX LINE ON R ENGINE HYD PUMP, AND DAMAGED FLEX LINE ON L HYD PUMP AS WELL. RE PLACED L AND R ENGINE HYDRAULIC PUMPS, ALL FLEX PRESSURE LINES IN ENGINE HYDRAULIC CIRCUIT, HYDRAULIC FILTERS, RESERVOIR PRESSURE REGULATOR, CHECK VALVE, AND FILTER. BLED AIR FROM HYDRAULIC SYSTEM, PERFORMED FUNCTIONAL TESTS AND GROUND RUN, 2 L 7 2 4F RT A10CE 2007040200160 20070402 00160 GL 2007 4 2 2007FA0000276 1 20070306 G 5551 BOLT DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA HORIZ STAB BROKEN D O OTHER O OTHER NR NOT REPORTED 1 NM 03 921DA C0395 650218 AG5429 AC, RETURN FROM FLIGHT WITH BOTH BOLTS BROKEN; ATTACHING THE FORWARD HORIZONTAL STABILIZER MOUNT BRACKETS. ATT 1) GIVES FLIGHT INFO. ATT 2 AND 3) SHOW THE IPB BRAKE DOWN OF THE BOLTS AND LOCATION FROM MFG PARTS BOOK. ATT 4) PICTURES OF B OLTS AND AIRCRAFT. ATT 5) THE NTSB PAPERWORK. ATT 6) IS SOME EMAIL TRAFFIC. WE REMOVED THE RUDDER AND HORIZONTAL STAB ILIZER TO INSPECT ENTIRE AREA. WE REPLACE THE AFT MOUNT PLATE AND FORWARD MOUNT BRACKET ALONG WITH ALL NEW BOLTS, WASHER S AND NUTS. WE ALSO INSPECTED OUR OTHER 9 AC AND REPLACED BOTH BOTH ON ALL 9 AC. NO OTHER ISSUES WERE FOUND ON OUR OTH ER AC. MFG HAS BEEN BRIEFED AND IS WORKING WITH THE NTSB. (K) 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2007050700023 20070507 00023 SO 2007 5 7 2007FA0000277 2 20070322 G 8520 A049405N CRANKSHAFT CONT O360 TSIO360EB 17025 SO ENGINE FAILED B LU4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 A049405U CRANKSHAFT FAILED NDI SB MSB96-10. (K) 3 O E9CE 2007040900058 20070409 00058 CE 2007 4 9 2007FA0000279 1 20070228 G 3220 45A3952211 UPLOCK BEECH MU300 400A 1155402 CE NLG OUT OF ADJUST B E81R O OTHER O OTHER NR NOT REPORTED 1 GL 03 123QS 243 RK486 FLIGHT CREW REPORTED RED LANDING GEAR HANDLE WARNING LIGHT STAYING ILLUMINATED AFTER GEAR RETRACTION. LANDING GEAR CYCL ED SEVERAL TIMES, HANDLE WARNING LIGHT STAYED ILLUMINATED. FOUND NOSE LANDING GEAR UPLOCK NOT FULLY ENGAGING ADJUSTED N OSE LANDING GEAR UPLOCK AS REQUIRED IAW THE MM. LANDING GEAR RETRACT/ EXTENSION CHECKS OK, NO FAULTS NOTED. HAVE NOTED THIS FAULT ON LOW TIME AC SEVERAL TIMES, PARTICULARLY DURING COLD WEATHER OPERATION UPLOCK ADJUSTMENT FAULTS USUALLY SH OW UP DURING MM FUNCTIONAL TESTS DURING THE LOW PRESSURE/LOW FLOW TESTS. (K) 2 H 7 2 4F RT A16SW 2007040200164 20070402 00164 2007 4 2 2007FA0000280 1 20070312 G 3230 452552 BEARING LANDING GEAR INACCURATE D O OTHER O OTHER NR NOT REPORTED 1 NE 03 PN 96522-00, CENTERING SPRING ASSY, HAS A ROD END BEARING ON THE END OF THE SHAFT, WHICH BOLTS TO THE IMOVABLE PORTION O F THE NOSE GEAR. ORIGINAL ROD END BEARING IS .375 INCH THICK WHERE BOLT GOES THRU. NEW ROD END BEARING THAT COMES WITH PN 96522-00 ASSY, IS .433 INCH THICK AND RELOCATES CLEVIS BOLT PN AN24-20A .0625 INCH DOWNWARD (UNFAVORABLE) AND CONTRA DICTS REQUIREMENTS OF MFG MSB 893. (K) 2007050400162 20070504 00162 CE 2007 5 4 2007FA0000284 1 20070317 G 5740 NAS1738B ATTACH FITTING BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE WING LOOSE B KX5R K NONE O OTHER IN INSP/MAINT 1 GL 15 1525C 5500 FL88 MANY OF THE BLIND RIVETS, PN NAS1738B6, ATTACHING THE WING SKIN TO THE LOWER FORWARD WING ATTACHMENT FITTING WERE FOUND TO BE LOOSE. CONDITION EXISTED ON BOTH WINGS. CONDITION ALSO FOUND ON AC SN FL59 (8100 HRS). (K) 2 L 7 2 4T 4 T A24CE E4EA 2007050400205 20070504 00205 GL 2007 5 4 2007FA0000285 2 20070319 G 7323 23065121 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE FROZEN B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 CGPHC 293 180257D DURING AN INSPECTION IT WAS NOTED THAT THE BEAING RETAINING WASHER FOR THE ROD END WAS INCORRECT. AFTER THE BOLT WAS RE MOVED IT WAS THEN DISCOVERED THAT THE THROTTLE ARM WAS SEIZED UP ON THE GOVERNOR, REPLACED GOVERNOR. (K) 1 G 7 1 3U 3 U H3WE E4CE 2007040200159 20070402 00159 GL 2007 4 2 2007FA0000286 1 20070322 G 7120 11925003 MOUNT CIRRUS SR SR20 05628AJ GL ENGINE BROKEN D O OTHER O OTHER NR NOT REPORTED 1 SO 11 155CD 2058 1058 ENGINE MOUNT RT FRONT CROSSOVER TUBE BETWEEN LT AND RT ENGINE SUPPORTS FOUND BROKEN AT THE WELD RT SIDE. ENGINE WAS CHA NGED ABOUT 250 HRS AGO, NO MENTION OF ENGINE MOUNT DAMAGE. COULD HAVE BEEN A HARD LANDING, BUT NO OTHER SIGNS WERE NOTE D. CONTACT WITH MFG SAYS NO OTHER REPORTS HAVE BEEN FILLED. (K) 1 L 7 1 3O NT A00009CH 2007040200166 20070402 00166 SW 2007 4 2 2007FA0000287 1 20070322 G 7110 RIVET MOONEY M20 M20J 5870219 SW LYC O360 IO360A1A 41514 EA COWLING CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 11 9156X 243253 OWNER BROUGHT COWLINGS IN FOR REPAIR BECAUSE THE THROUGH SKIN RIVETS WERE CORRODING AND SHEARING OFF AT THE MFG HEAD AS EXHIBITED BY BLISTERING PAINT AT THE RIVET LOCATIONS. INSPECTION REVEALED MOST OF THE AD TYPE RIVETS WERE SEVERELY CORR ODED BECAUSE THE COWLINGS WERE CONSTRUCTED WITH A HYBRID COMPOSITE LAMINATE OF E-GLASS AND CARBON GRAPHITE PLIES. IT IS STANDARD INDUSTRY PRACTICE TO USE CORROSION RESISTANT FASTENERS SUCH AS RIVETS THROUGH CARBON GRAPHITE STRUCTURE AND IT IS UNKNOWN WHY ALUMINUM RIVETS ARE USED IN THIS CASE. AFFECTED AREAS: UPPER COWL/ OIL DOOR CUTOUT DOUBLER RIVETS COOLI NG AIR INLET AFT EDGE RIVETS. LOWER COWL/ BOTH UPPER CAMLOCK RECEPTACLE GANG STRIPS (SEVERELY CORRODED AND CONCEALED BY 1 L 7 1 3O 3 O 2A3 1E10 2007040300032 20070403 00032 SO 2007 4 3 2007FA0000288 1 20070402 G 5321 37829007 FLOOR PANEL PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FUSELAGE DEBONDED D IBIR K NONE O OTHER IN INSP/MAINT 1 EA 27 682JK 968 3449154 322291 FLOOR PANEL BETWEEN FORWARD AND REAR WING SPARS ON WHICH AFT FACING CENTER SEATS ARE MOUNTED IS DELAMINATING. THE FLOOR PANEL CONSISTS OF 2 SHEETS OF ALUMINUM (.040 INCH) WITH A SOUND DEADENING STIFF FOAM BETWEEN THEM. THE SEAT MOUNTING BR ACKETS ARE BOLTED THRU BOTH SHEETS, BUT THIS STILL MAY BE A STRUCTURE ISSUE. CALLED MFG FOR GUIDANCE, BUT HAVE NOT HEAR D ANYTHING AS YET. 1 L 7 2 3O 3 O A7SO E9CE 2007040300033 20070403 00033 SO 2007 4 3 2007FA0000289 1 20070402 G 5321 37829007 FLOOR PANEL PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE ZONE 100 DEBONDED D IBIR K NONE O OTHER IN INSP/MAINT 1 EA 27 682JK 968 3449154 322291 FLOOR PANEL BETWEEN FORWARD AND REAR WING SPARS ON WHICH AFT FACING CENTER SEATS ARE MOUNTED IS DELAMINATING. THE FLOOR PANEL CONSISTS OF 2 SHEETS OF ALUMINUM (.040 INCH) WITH A SOUND DEADENING STIFF FOAM BETWEEN THEM. THE SEAT MOUNTING B RACKETS ARE BOLTED THRU BOTH SHEETS, BUT THIS STILL MAY BE A STRUCTURE ISSUE. CALLED MFG FOR GUIDANCE, BUT HAVE NOT HEA RD ANYTHING AS YET. 1 L 7 2 3O 3 O A7SO E9CE 2007040300034 20070403 00034 SO 2007 4 3 2007FA0000290 1 20070402 G 5321 37829007 FLOOR PANEL PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE ZONE 100 DEBONDED D IBIR K NONE O OTHER IN INSP/MAINT 1 EA 27 682JK 968 3449154 322291 FLOOR PANEL BETWEEN FORWARD AND REAR WING SPARS ON WHICH AFT FACING CENTER SEATS ARE MOUNTED IS DELAMINATING. THE FLOOR PANEL CONSISTS OF 2 SHEETS OF ALUMINUM (.040 INCH) WITH A SOUND DEADENING STIFF FOAM BETWEEN THEM. THE SEAT MOUNTING BR ACKETS ARE BOLTED THRU BOTH SHEETS, BUT THIS STILL MAY BE A STRUCTURE ISSUE. HAVE CALLED MFG FOR GUIDANCE, BUT HAVE NOT HEARD ANYTHING AS YET. 1 L 7 2 3O 3 O A7SO E9CE 2007040300035 20070403 00035 SO 2007 4 3 2007FA0000291 1 20070402 G 5321 37829007 FLOOR PANEL PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE ZONE 100 DEBONDED D IBIR K NONE O OTHER IN INSP/MAINT 1 EA 27 682JK 968 3449154 322291 FLOOR PANEL BETWEEN FORWARD AND REAR WING SPARS ON WHICH AFT FACING CENTER SEATS ARE MOUNTED IS DELAMINATING. THE FLOOR PANEL CONSISTS OF 2 SHEETS OF ALUMINUM (.040 INCH) WITH A SOUND DEADENING STIFF FOAM BETWEEN THEM. THE SEAT MOUNTING B RACKETS ARE BOLTED THRU BOTH SHEETS, BUT THIS STILL MAY BE A STRUCTURE ISSUE. HAVE CALLED MFG FOR GUIDANCE, BUT HAVE NO T HEARD ANYTHING AS YET. 1 L 7 2 3O 3 O A7SO E9CE 2007040300036 20070403 00036 SO 2007 4 3 2007FA0000292 1 20070402 G 5321 37829007 FLOOR PANEL PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE ZONE 100 DEBONDED D IBIR K NONE O OTHER IN INSP/MAINT 1 EA 21 682JK 968 3449154 322291 FLOORPANEL BETWEEN FORWARD AND REAR WING SPARS ON WHICH AFT FACING CENTER SEATS ARE MOUNTED IS DELAMINATING. THE FLOOR PANEL CONSISTS OF 2 SHEETS OF ALUMINUM (.040 INCH) WITH A SOUND DEADENING STIFF FOAM BETWEEN THEM. THE SEAT MOUNTING BRA CKETS ARE BOLTED THRU BOTH SHEETS, BUT THIS STILL MAY BE A STRUCTURE ISSUE. HAVE CALLED MFG FOR GUIDANCE, BUT HAVE NOT HEARD ANYTHING AS YET. 1 L 7 2 3O 3 O A7SO E9CE 2007050400135 20070504 00135 CE 2007 5 4 2007FA0000293 1 20070322 G 7830 LINK CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE THRUST REVERSER CORRODED D O OTHER O OTHER NR NOT REPORTED 1 GL 15 413LC 6894 5600003 PCE108003 ALL DRIVE LINK PIVOT BOLTS AND OVER CENTER LINKS SEVERELY CORRODED AND WORN. PROBABLE CAUSE IS INADEQUATE LUBE. MANUAL STATES TR`S MUST BE TORN DOWN AND LUBED UPON ASSEMBLY AT SPECIFIC INTERVALS. ENGINEERING STATES THAT TEARDOWN IS NOT N ECESSARY AND ON WING LUBRICATION IS ADEQUATE. THESE FINDINGS INDICATE OTHERWISE. (K) 2 L 7 2 4F 4 F RT A22CE E25EA 2007050400141 20070504 00141 CE 2007 5 4 2007FA0000294 1 20070222 G 3610 1H1069 MIXING VALVE LEAR 60 60LEAR 5170707 CE PWA 305 PW305 NE LT ENGINE INTERMITTENT C O OTHER O OTHER NR NOT REPORTED 1 GL 11 500 83 306 SHORTLY AFTER TAKEOFF, AIRCRAFT (LT BLEED AIR) WARNING ILLUMINATED, AND (RT BLEED AIR) WARNING ILLUMINATED APPROX 5 SEC LATER, SMELLED ODOR IN MAINTENANCE. UNABLE TO DUPLICATE MALFUNCTION ON GROUND RUN; LT MIXING VALVE WAS SUSPECTED, SO RE PLACED. PERFORMED GROUND RUN FUNCTIONAL TEST OF BLEED AIR SYSTEM, AND FLIGHT TEST. NO FURTHER BLEED AIR WARNINGS. (K) 2 L 7 2 4F 4 F RT A10CE E35NE 2007040600160 20070406 00160 CE 2007 4 6 2007FA0000295 1 20070320 G 8120 BEARING CESSNA 414 414A 2075907 CE CONT O520 TSIO520* 17040 SO TURBOCHARGER WORN D O OTHER O OTHER NR NOT REPORTED 1 GL 13 3247M 1031 FKL00044 414A0828 FAILURE OF RT TURBOCHARGER SEAL AND CENTER BEARING CAUSED SMOKE OUT OF EXHAUST AND SQUEALING NOISE RESULTING IN THE FLIG HT CREW TO FEATHER PROPELLER AND SHUTDOWN THE ENGINE. CAUSE OF FAILURE DO TO WEAR. (K) 1 L 7 2 3O 3 O A7CE E8CE 2007040900008 20070409 00008 SW 2007 4 9 2007FA0000297 1 20070305 G 6410 HAC473 BLADE BELL 47 47G5 1181032 SW LYC O435 VO435* 41516 EA TAIL ROTOR DAMAGED B ECGR O OTHER O OTHER NR NOT REPORTED 1 EA 13 1202W 7857 THE STAINLESS STEEL ABRASION STRIP ON THE LEADING EDGE OF THE COMPOSITE TAIL ROTOR BLADE SEPARATED FROM BLADE IN FLIGHT. PILOT NOTED A VIBRATION IN A SPRAY TURN AND ELECTED TO LAND; AND LANDED SAFELY (NO INJURIES). 1 G 7 1 3O 3 O 2H3 E279 2007050400145 20070504 00145 SO 2007 5 4 2007FA0000298 1 20070320 G 2400 100201021346 INVERTER GULSTM GVSP GVSPG550 3980203 SO GE CF34 CF343A 30066 NE SHORTED D O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 GL 05 5PG 1383 5046 WHEN TURNING MAIN BATTERY SWITCHES ON, MECHANIC HEARD A LOUD POPPING SOUND, FOLLOWED BY THE AROMA OF SMOKE IN THE ENTRAN CE AREA OF THE AIRCRAFT. THE FLOORBOARD WAS REMOVED AND FOUND THAT WATER FROM THE FORWARD LAVATORY AREA HAD BEEN RUNNIN G ONTO THE TOP OF THE EMERGENCY INVERTER CAUSING H2O AND AC VOLTAGE TO MEET (H2O WON). THE LAV AREA ON BOTH OF OUR AC W ERE INSPECTED FOR LEAKS AND FOUND AREAS WHERE WATER HAD BEEN SITTING, EVEN THROUGH THERE WERE NO LEAKS. IT IS POSSIBLE THAT WHEN STOWING THE SINK (HINGED AND FOLDS UP INTO A CLOSEOUT) RESIDULE WATER IS DUMPING INTO THE CLOSEOUT. THE INVER TER WAS REPLACED AND WE SHUT THE WATER SUPPLY OFF FOR THE FORWARD LAY SINK ON BOTH. THERE IS NO PREFLIGHT OR SCHEDULED 2 L 7 2 4F 4 F RT A12EA E15NE 2007050400148 20070504 00148 CE 2007 5 4 2007FA0000299 1 20070326 G 2820 050011849 LINE CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FUEL SYSTEM CHAFED D O OTHER O OTHER NR NOT REPORTED 1 EA 23 2470N 400 172S10070 FOUND FUEL LINE PN 05001( 8-49, FUEL RETURN LINE TO RESERVOIR WORN BY RUBBING ON NOSE STEERING ROD JUST BEHIND FIREWALL . INSTALLED NEW LINE SO AS NOT TO RUB ON STEERING. INSTALLED SPIRAL WRAP ON AREA WHERE RUBBING HAD OCCURRED. NOTE: FU EL LINE WAS WORN TO POINT OF LEAKING. RECOMMEND INSPECTING NEW AC FOR PROPER LINE INSTALLATION. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2007050400144 20070504 00144 CE 2007 5 4 2007FA0000300 1 20070327 G 3240 16011800 HOUSING CLEVELAND CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL BRAKE CALIPER DEFECTIVE D O OTHER O OTHER NR NOT REPORTED 1 WP 21 PKMPS 017 208B0656 PCEPC0548 001276 THE MAIN CASTING, WHICH HOUSES THE BRAKE CALIPER PISTONS LEAKS FLUID UNDER NORMAL BRAKING PRESSURE. THE LEAKS ARE FROM EXCESSIVE POROSITY IN THE CASTING. CASTING THIS IS THE SECOND OCCURRENCE IN OUR OPERATIONS. THE FIRST WAS NOT REPORTE D. (K) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2007040600163 20070406 00163 CE 2007 4 6 2007FA0000301 1 20070406 G 1400 NUT CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA MISMANUFACTURED B O OTHER O OTHER NR NOT REPORTED 1 EA 07 949SP 172S8145 WHILE INSTALLING KIT MK172-25-10C TO COMPLY WITH SB 04-25-01 R4 AND AD 2007-05-10, ONE OF THE PARTS IN THE KIT WAS MACHI NED IMPROPERLY. THE HEIGHT ADJUSTING NUT HAD THE THRU HOLE FOR THE ULTRALOC WITH MIS FORMED THREADS. THE MINOR DIAMETER OF THE THREAD WAS GREATER THAN THE MAJOR DIAMETER OF THE THREADS ON THE ULTRALOC. THE CROSS HOLE FOR MOUNTING WAS INCORR ECTLY LOCATED WITH INSUFFICIENT EDGE DISTANCE, AND THE PILOT HOLE WAS OFFSET GIVING AN EGG SHAPED HOLE. 1 H 7 1 3O 3 O NT 3A12 1E10 2007040900036 20070409 00036 CE 2007 4 9 2007FA0000302 1 20070403 G 2731 65651412 ACTUATOR CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ELEVATOR TRIM BINDING B K NONE O OTHER IN INSP/MAINT 1 SW 13 5314J 5592 300 5500663 AFTER A PHASE 1-4 INSPECTION THE ELEVATOR TRIM WAS FOUND TO BE BINDING. INSPECTION OF THIS SYSTEM FOUND THAT THE WILKIE BUTTON IN THE BACK OF THE ACTUATOR TRIM JACK SCREWS HAD COME OUT AND WAS BINDING THE TRIM CHAIN AND SPROCKETS. WHEN THE ACTUATORS ARE LUBED THE WILKIE BUTTONS HAVE A TENDENCY TO POP OUT OF THERE PLACE IF YOU DONT LOOK CLOSELY AFTER LUBING T HESE ACTUATORS THE GREASE PUSHES THESE PLUGS OUT AND THEY STICK TO THE INTERCONNECT CHAIN CAUSING A BINDING CONDITION. T HIS COULD ALSO HAPPEN IN FLIGHT CAUSING A LIKE CONDITION WITH MORE DIRE PROBLEMS. I THINK MFG SHOULD REMOVE THIS PLUG OR MORE SECURELY FIX THIS PLUG IN PLACE. 1 L 7 2 4F 4 F A22CE E1NE 2007040900037 20070409 00037 CE 2007 4 9 2007FA0000303 1 20070403 G 2731 65651412 ACTUATOR CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ZONE 200 BINDING B K NONE O OTHER IN INSP/MAINT 1 SW 13 5314J 5592 300 5500663 AFTER A PHASE 1-4 INSPECTION THE ELEVATOR TRIM WAS FOUND TO BE BINDING. INSPECTION OF THIS SYSTEM FOUND THAT THE WILKIE BUTTON IN THE BACK OF THE ACTUATOR TRIM JACK SCREWS HAD COME OUT AND WAS BINDING THE TRIM CHAIN AND SPROCKETS. WHEN THE ACTUATORS ARE LUBED THE WILKIE BUTTONS HAVE A TENDENCY TO POP OUT OF THERE PLACE IF YOU DONT LOOK CLOSELY AFTER LUBING T HESE ACTUATORS THE GREASE PUSHES THESE PLUGS OUT AND THEY STICK TO THE INTERCONNECT CHAIN CAUSING A BINDING CONDITION. T HIS COULD ALSO HAPPEN IN FLIGHT CAUSING A LIKE CONDITION WITH MORE DIRE PROBLEMS. I THINK MFG SHOULD REMOVE THIS PLUG OR MORE SECURELY FIX THIS PLUG IN PLACE. 1 L 7 2 4F 4 F A22CE E1NE 2007040900020 20070409 00020 CE 2007 4 9 2007FA0000308 1 20070402 G 3211 508103437 PIN BEECH 200 B200 1152922 CE LT MLG BROKEN E O OTHER J WARNING INDICATION AP APPROACH 1 SW 05 65TW 6551 6551 BB902 UPON EXTENDING THE LANDING GEAR, THE PILOTS GOT A RED GEAR UNSAFE LIGHT IN THE HANDLE, AND THE LT DOWN AND LOCKED LIGHT WAS NOT LIT UP. THE PILOTS TRIED TO EXTEND THE GEAR MANUALLY, BUT THE HANDLE WOULD NOT EXTEND THE GEAR ANY FURTHER, THE PILOTS RETRACTED THE GEAR AND THE RED LIGHT STAYED ILLUMINATED, THE GEAR WAS EXTENDED AGAIN, STILL THE LT DOWN AND LOCKE D LIGHT WAS OFF AND THE RED LIGHT IN THE HANDLE WAS ON. THE PILOTS DECLARED AN EMERGENCY AND LANDED THE AIRCRAFT, WITH N O OTHER EVENTS. THE AIRCRAFT WAS JACKED UP, AND THE LANDING GEAR WAS INSPECTED. THE LT MAIN DOWN LOCKING ASSY PIN WAS FO UND TO BE BROKEN AND HANGING OUT OF THE LOCK HOLES, PREVENTING THE GEAR FROM FULLY EXTENDING AND RETRACTING. THE PIN WAS 1 L 7 2 4T A24CE 2007040900021 20070409 00021 CE 2007 4 9 2007FA0000309 1 20070402 G 3210 508103437 PIN BEECH 200 B200 1152922 CE ZONE 700 BROKEN E O OTHER J WARNING INDICATION AP APPROACH 1 SW 05 65TW 6551 6551 BB902 UPON EXTENDING THE LANDING GEAR, THE PILOTS GOT A RED GEAR UNSAFE LIGHT IN THE HANDLE, AND THE LT DOWN AND LOCKED LIGHT WAS NOT LIT UP. THE PILOTS TRIED TO EXTEND THE GEAR MANUALLY, BUT THE HANDLE WOULD NOT EXTEND THE GEAR ANY FURTHER, THE PILOTS RETRACTED THE GEAR AND THE RED LIGHT STAYED ILLUMINATED, THE GEAR WAS EXTENDED AGAIN, STILL THE LT DOWN AND LOCKE D LIGHT WAS OFF AND THE RED LIGHT IN THE HANDLE WAS ON. THE PILOTS DECLARED AN EMERGENCY AND LANDED THE AIRCRAFT, WITH N O OTHER EVENTS. THE AIRCRAFT WAS JACKED UP, AND THE LANDING GEAR WAS INSPECTED. THE LT MAIN DOWN LOCKING ASSY PIN WAS FO UND TO BE BROKEN AND HANGING OUT OF THE LOCK HOLES, PREVENTING THE GEAR FROM FULLY EXTENDING AND RETRACTING. THE PIN WAS 1 L 7 2 4T A24CE 2007040900032 20070409 00032 CE 2007 4 9 2007FA0000310 1 20070406 G 1400 07900072 NUT CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA KIT MISMANUFACTURED B O OTHER W INADEQUATE Q C NR NOT REPORTED 1 EA 07 949SP 172S8145 WHILE INSTALLING KIT MK172-25-10C TO COMPLY WITH SB 04-25-01 R4 AND AD 2007-05-10, ONE OF THE PARTS IN THE KIT WAS MACHI NED IMPROPERLY. THE HEIGHT ADJUSTING NUT HAD THE THRU HOLE FOR THE ULTRALOC WITH MALFORMED THREADS. THE MINOR DIAMETER O F THE THREAD WAS GREATER THAN THE MAJOR DIAMETER OF THE THREADS ON THE ULTRALOC. THE CROSS HOLE FOR MOUNTING WAS INCORRE CTLY LOCATED WITH INSUFFICIENT EDGE DISTANCE, AND THE PILOT HOLE WAS OFFSET GIVING AN EGG SHAPED HOLE. 1 H 7 1 3O 3 O NT 3A12 1E10 2007040900022 20070409 00022 NE 2007 4 9 2007FA0000311 2 20070305 G 7314 REGULATOR NAMER T6 AT6D 6400416 GL PWA R1340 R1340AN1 52016 NE HAMSTD 12D 12D40 NE FUEL PUMP STUCK P O OTHER Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 NM 03 8541B THE PRESSURE REGULATOR (IN THE WOBBLE PUMP) STUCK IN THE (BYPASS) POSITION CAUSING LOSS OF FUEL PRESSURE AND POWER LOSS DUE TO LACK OF FUEL. 1 L 7 1 3R 3 R A2575 5E2 5 C P257 2007040900081 20070409 00081 WP 2007 4 9 2007FA0000313 2 20070330 G 7210 31030351 BEARING GARRTT TPE331 TPE33110U 01514 WP IDLER GEAR MISINSTALLED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 723 P44218C SUBASSEMBLY BEARINGS TO 2ND IDLER GEAR ASSEMBLED BACKWARDS, CAGE FAILED. 4 T E4WE 2007040900028 20070409 00028 CE 2007 4 9 2007FA0000315 1 20070402 G 3610 1H1068 MIXING VALVE LEAR 60 60LEAR 5170707 CE PWA 305 PW305 NE LT BLEED AIR SYS OUT OF TOLERANCE B C ABORTED TAKEOFF B SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 GL 09 706CR 168 DURING TAKEOFF ROLL CREW EXPERIENCED A RUSH OF WARM OILY SMELLING AIR IN THE COCKPIT. CREW ABORTED TAKEOFF AND RETURNED TO BASE. MAINTENANCE CREW RAN AIRCRAFT AND DUPLICATED PROBLEM FINDING THE DUCT OVRHT LIGHT AND LT BLEED LIGHT ON AT FULL POWER. FURTHER TROUBLESHOOTING FOUND THAT THE LT BLEED AIR MIXING VALVE WAS ALLOWING MORE THAN 200PSI OUT PUT OF AIR. L T BLEED AIR MIXING VALVE WAS REPLACED WITH A SERVICEABLE INSPECTED VALVE AND OPS CHECKED GOOD. 2 L 7 2 4F 4 F RT A10CE E35NE 2007041000035 20070410 00035 2007 4 10 2007FA0000316 4 20070406 G 2200 0111 TRANSDUCER CESSNA 180 180 2072602 CE AUTO PILOT MALFUNCTIONED D H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CR CRUISE 1 WP 28 460 ALTITUDE HOLD WAS INOP. WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMMEDIATELY, OR THE A/C WOULD MAINTAIN ALTI TUDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC OF TESTING. BOTH UNITS WERE RETURNED AS SERVICEABLE. AFTER INSTALLATION THE PROBLEM WAS STILL THERE. REPLACED THE TRANSDUCER WITH A KNOWN GOOD PART AND PROBLEM WAS SOLVED. STEC ACTED ASTONISHED THAT THEIR BENCH CHECK WOULD NOT FIND THE PROBLEM! 1 H 7 1 3O NC 5A6 2007041000036 20070410 00036 2007 4 10 2007FA0000317 4 20070406 G 2200 0111 TRANSDUCER STEC CESSNA 180 180 2072602 CE AUTO PILOT MALFUNCTIONED D H DEACTIVATE SYST/CIRCUITS O OTHER CR CRUISE 1 WP 28 460 ALTITUDE HOLD WAS INOPERATIVE. WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMMEDIATELY, OR THE A/C WOULD MAINTA IN ALTITUDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC FOR TESTING. BOTH UNITS WERE RETURNED AS SERVICEABLE. AFTER INSTALLATION THE PROBLEM WAS STILL THERE. REPLACED THE TRANSDUCE R WITH A KNOWN GOOD PART AND PROBLEM WAS SOLVED.STEC ACTED ASTONISHED THAT THEIR BENCH CHECK WOULDN'T FIND THE PROBLEM! 1 H 7 1 3O NC 5A6 2007041000037 20070410 00037 2007 4 10 2007FA0000318 4 20070406 G 2215 0111 TRANSDUCER STEC CESSNA 180 180 2072602 CE ZONE 200 MALFUNCTIONED D H DEACTIVATE SYST/CIRCUITS O OTHER CR CRUISE 1 WP 28 460 ALTITUDE HOLD WAS INOP. WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMEDIATLEY, OR THE A/C WOULD MAINTAIN ALTIT UDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC FO TESTING. BOTH UNITS WERE RETURNED AS SERVICEABLE. AFTER INSTALLATION THE PROBLEM WAS STILL THERE. REPLACED THE TRANSDUCER WITH A KNOWN GOOD PART AND PROBLEM WAS SOLVED.STEC ACTED ASTONISHED THAT THEIR BENCH CHECK WOULDN'T FIND THE PROBLEM! 1 H 7 1 3O NC 5A6 2007041000038 20070410 00038 2007 4 10 2007FA0000319 4 20070406 G 2215 0111 TRANSDUCER STEC CESSNA 180 180 2072602 CE ZONE 200 MALFUNCTIONED D H DEACTIVATE SYST/CIRCUITS O OTHER CR CRUISE 1 WP 28 460 ALTITUDE HOLD WAS INOPERATIVE. WHEN SELECTED THE A/C WOULD PITCH EITHER UP OR DOWN IMMEDIATELY, OR THE A/C WOULD MAINTA IN ALTITUDE FOR A SHORT TIME AND THEN PITCH IN EITHER DIRECTION. COMPUTER AND PRESSURE TRANSDUCER WERE SENT TO STEC FOR TESTING. BOTH UNITS WERE RETURNED AS SERVICEABLE. AFTER INSTALLATION THE PROBLEM WAS STILL THERE. REPLACED THE TRANSDUCE R WITH A KNOWN GOOD PART AND PROBLEM WAS SOLVED.STEC ACTED ASTONISHED THAT THEIR BENCH CHECK WOULDN'T FIND THE PROBLEM! 1 H 7 1 3O NC 5A6 2007050400155 20070504 00155 GL 2007 5 4 2007FA0000321 2 20070401 G 7412 6870885 EXCITER HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE INOPERATIVE B EOOR O OTHER O OTHER NR NOT REPORTED 1 AL 03 CGBUY 6109580 CAE833577 PILOT WENT TO START THE AIRCRAFT AND THERE WAS NO IGNITION. FOUND IGNITION EXCITER INOPERATIVE, REPLACED. (K) 1 G 7 1 3U 3 U H3WE E4CE 2007050400152 20070504 00152 SO 2007 5 4 2007FA0000322 1 20070330 G 5730 427 SKIN GULSTM G1159 G1159A 3970109 SO RROYCE SPEY SPEY511* 54523 EU RT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 05 300WY 427 DURING A WING NDT INSPECTION OF THE UPPER RT WING PLANK AT FS 452 AND BL 33, CORROSION WAS NOTED IN THIS AREA. ENGINEER ING HAS DETERMINED THIS CORROSION IS EXCESSIVE ENOUGH TO REQUIRE ACCOMPLISHMENT OF ASC 229, WHICH REMOVES THE CORROSION ON THE PLANK AND INSTALLS A DOUBLER PLATE AND A NEW STYLE WING ATTACH PIN AS A CORRECTIVE ACTION. (K) 2 L 7 2 4F 4 F A12EA E2EU 2007050700006 20070507 00006 SO 2007 5 7 2007FA0000323 1 20070301 G 3220 95829000 DRAG LINK PIPER PA34 PA34200 7103405 SO LYC O360 IO360A1A 41514 EA NLG JAMMED G R2LS O OTHER O OTHER NR NOT REPORTED 1 SO 15 15338 347350051 THE NOSE GEAR LINK ASSEMBLY JAMS INTERMITTENTLY, KEEPING THE FWD AND AFT NOSE GEAR DRAG LINKS FROM LOCKING COMPLETELY. REFER TO SB NR 1123B. (K) 1 L 7 2 3O 3 O A7SO 1E10 2007050400140 20070504 00140 GL 2007 5 4 2007FA0000324 1 20070317 G 3240 PLATE TCRAFT BC BC12D 8850316 GL CONT O200 O200A 17020 SO MCAULY 1A100 1A100* GL LT BRAKE LOOSE D O OTHER O OTHER NR NOT REPORTED 1 GL 15 43336 1669 6995 666377A G1885 WHEN BRAKES WERE APPLIED AFTER LANDING. IT APPEARS THAT THE PINS HOLD THE BACK PLATE ALLOW IT TO SHIFT ENOUGH TO HAVE P OSSIBLY MADE CONTACT WITH THE BRAKE ACCUATOR ARM AND NOT ALLOW IT TO RELEASE. (K) 1 H 7 1 3O 3 O A696 E252 5 N P918 2007042500263 20070425 00263 CE 2007 4 25 2007FA0000325 1 20070325 G 7810 EXHAUST PIPE CESSNA 182 182A 2072704 CE CONT O470 O470* 17026 SO MCAULY 2A34C 2A34C203 GL RT EXHAUST BROKEN D O OTHER O OTHER NR NOT REPORTED 1 CE 03 5848B 33848 668686L 891146 RT EXHAUST BROKE AT ELBOW, PART HAD BEEN REPAIRED 544 HRS AGO. DID NOT SHOW ANY CRACK 50 HRS EARLIER. DO NOT REPAIR EX HAUST PARTS THAT HAVE 1000 HRS ON THEM. (K) 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2007042500255 20070425 00255 EU 2007 4 25 2007FA0000328 1 20070406 G 5554 T700A5340023100 FITTING SOCATA TBM TBM700 8682000 EU PWA PT6 PT6A64 EA HARTZL HCE4N HCE4N3 NE RUDDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 05 704QD 188 PCEPM0073 HH463 DURING A 6000HR/10 YEAR CORROSION INSPECTION AD2007-06-11 WAS BEING COMPLIED IAW AD AND MANDATORY SB70-=104, AMENDMENT 2 . AFTER COMPLETING THE PENETRANT INSPECTION NO CRACKS WERE DETECTED IN THE SPECIFIED AREAS HOWEVER THE FITTINGS LISTED IN BLOCK 5 WERE REMOVED FROM SERVICE FOR LIGHT PITTING CORROSION. RECENTLY IN OUR FACILITY, THERE WAS A LEVEL 3 NDT REC URRENT COURSE BEING GIVEN AND THE REMOVED FITTINGS WERE CRACK CHECKED USING A ROTARY TOOL FOR BOLT HOLE EDDY CURRENT SET UP ON .030 CORNER EDM NOTCH AS A REFERENCE STANDARD. AT THIS TIME THERE WERE CORROSION PITTING CRACKS DETECTED IN BOTH FITTINGS. THE INSPECTION CRITERIA STATED IN AD AND SB ARE INSUFFICIENT FOR CRACK DETECTION IN THIS AREA. POSSIBLY THE 1 L 7 1 3T 4 T RT A60EU E4EA 5 C P10NE 2007050400168 20070504 00168 EU 2007 5 4 2007FA0000329 1 20070406 G 5510 T700A5530072102 FITTING SOCATA TBM TBM700 8682000 EU PWA PT6 PT6A64 EA HARTZL HCE4N HCE4N3 NE STABILIZER CORRODED D O OTHER O OTHER NR NOT REPORTED 1 EA 05 704QD 5980 188 PCEPM0073 HH463 DURING A 6000HR/10 YEAR CORROSION INSPECTION AD2007-06-11 WAS BEING COMPLIED IAW AD AND MANDATORY SB70-104, AMENDMENT 2. AFTER COMPLETING THE PENETRANT INSPECTION, NO CRACKS WERE DETECTED IN THE SPECIFIED AREAS HOWEVER THE FITTINGS LISTED IN BLOCK 5 WERE REMOVED FROM SERVICE FOR LIGHT PITTING CORROSION. RECENTLY IN OUR FACILITY, THERE WAS A LEVEL 3 NDT REC URRENT COURSE BEING GIVEN AND THE REMOVED FITTINGS WERE CRACK CHECKED USING A ROTARY TOOL FOR BOLT HOLE EDDY CURRENT SET UP ON /030 CORNER EDM NOTCH AS A REFERENCE STANDARD. AT THIS TIME THERE WERE CORROSION PITTING CRACKS DETECTED IN BOTH FITTINGS. THE INSPECTION CRITERIA STATED IN AD AND SB ARE INSUFFICIENT FOR CRACK DETECTION IN THIS AREA. POSSIBLY THE 1 L 7 1 3T 4 T RT A60EU E4EA 5 C P10NE 2007050400171 20070504 00171 GL 2007 5 4 2007FA0000330 2 20070403 G 7240 23031260 COMBUSTION CASE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE CRACKED B EOOR O OTHER O OTHER NR NOT REPORTED 1 AL 03 CGPHC 180257D CAE831562 PILOT NOTICED CRACK IN COMBUSTION CAN ON PREFLIGHT CHECK REPLACED UNIT. (K) 1 G 7 1 3U 3 U H3WE E4CE 2007050400190 20070504 00190 SO 2007 5 4 2007FA0000331 2 20070404 G 7200 629340 ROD BOLT CESSNA 310 310R 2074245 CE CONT O520 IO520MB 17032 SO LT ENGINE BROKEN D O OTHER O OTHER NR NOT REPORTED 1 GL 23 2641D 740 310R1678 829015R PRELIMINARY INSPECTION FINDINGS: IN FLIGHT, LT ENGINE FAILURE ON CLIMB OUT. LT ENGINE HAD 737.1 HOURS AND PUT IN SERVI CE 05/2003. LARGE HOLE IN CASE AROUND NR 5 AND 6 CYLINDER. NR 5 ROD SEPARATED FROM CRANK AND BROKEN IN TWO PIECES A FE W INCHES FROM PISTON PIN. SUBSEQUENT FINDINGS FROM ENGINE TEARDOWN REPORT PERFORMED BY MFG. THE SIGNATURES PRESENT ON THE NR 5 CYLINDER BORE AND THE DAMAGE TO THE NR 5 CONNECTING ROD ARE CONSISTENT WITH A HYDROSTATIC LOCK EVENT. PRELIMIN ARY INFORMATION WAS BASED ON A SB CE-00-07, AND SDR REPORTS ISSUED BETWEEN 1995 AND PRESENT, ON SAME MODEL ENGINE WITH S IMILAR BOLT FAILURES. (K) 1 L 7 2 3O 3 O 3A10 E5CE 2007050400198 20070504 00198 SO 2007 5 4 2007FA0000332 2 20070401 G 8500 SNAP RING CESSNA 180 180A 2072604 CE CONT O470 IO470* 17026 SO ENGINE MISMANUFACTURED D O OTHER O OTHER NR NOT REPORTED 1 AL 03 4145 32840 CS76646PF SNAP RING USED TO RETAIN PLATE PN 643629 AND COUNTERWEIGHT PIN 643626-101 WAS BEING INSTALLED IN COUNTERWEIGHT. UPON IN STALLING, THE LAST SNAP RING, IT WAS NOTICED THAT THE SNAP RING DID NOT HAVE ANY RETAINING PROPERTIES. IT LACKED TEMPER TO SPRING BACK AND COULD BE FORMED INTO ANY POSITION WHICH COULD HAVE ALLOWED THE PLATE AND PIN TO FALL OUT OF THE COUN TERWEIGHT CAUSING ENGINE FAILURE.. THE SNAP RING WAS PURCHASED ON 12 MARCH, 2007. THE BATCH NR LISTED FOR THE SNAP RIN G WAS 0000070137 UNDER API`S PO NR 4500018586. (K) 1 H 7 1 3O 3 O 5A6 E1CE 2007050400137 20070504 00137 EA 2007 5 4 2007FA0000333 2 20070406 G 8530 LW15014 ROCKER CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA ENGINE CYLINDER BROKEN B YYBR O OTHER O OTHER NR NOT REPORTED 1 GL 03 2994E 17271398 L717976T THE STAMPED EXHAUST STEEL ROCKER ARM WAS FOUND BROKEN THROUGH AT PUSH ROD, AND THE INTAKE ROCKER ARM WAS CRACKED, AND TH E PUSH ROD WAS BENT BADLY. THE ENGINE HAD 120 HR TSO AND NEW FACTORY CYLIDERS WERE INSTALLED. (K) 1 H 7 1 3O 3 O NT 3A12 E274 2007042500258 20070425 00258 CE 2007 4 25 2007FA0000334 1 20070402 G 5312 07126161 BULKHEAD CESSNA 182 182L 2072726 CE CONT O470 O470* 17026 SO FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 09 42053 4571 18258832 SMALL CRACK AT RUDDER CABLE CUTOUT IB, APPROX .2500 INCH, NO CAUSE. 1 H 7 1 3O 3 O NT 3A13 E273 2007042500257 20070425 00257 EA 2007 4 25 2007FA0000335 2 20070417 G 7414 SPRING SLICK PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA IMPULSE COUPLING BROKEN D O OTHER R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 NE 05 1603 38 PILOT STARTED AIRCRAFT NORMALLY AND DID RUN UP WITH A BAD MAGNETO CHECK. PILOT DID NOT FLY AIRCRAFT AND RETURNED TO HANG ER. AIRCRAFT WOULD NOT RESTART. IMPULSE COUPLE DID NOT MAKE ANY NOISE, TIMING WAS WAY OFF. FOUND IMPULSE COUPLE SPRING B ROKEN A TURN AND A HALF FROM OUTER END. 1 L 7 1 3O 3 O 2A13 E286 2007042500273 20070425 00273 2007 4 25 2007FA0000336 4 20070416 G 2312 0464105430 RADIO BOLKMS 117 BK117A1 5626010 EU LYC LTS101 LTS101650B1 41560 NE NR 2 COMM SHORTED E BAQR K NONE B SMOKE/FUMES/ODORS/SPARKS AA AIR AMBULANCE 1 EA 03 952CJ S7052 WHILE SHUTTING DOWN AIRCRAFT THE CREW NOTED A WHIFF OF SMOKE AND ELECTRICAL SMELL IN THE COCKPIT. FOUND THE NR (2) COMM RADIO INTERNALLY SHORTED. 1 G 7 2 3U 3 U H13EU E5NE 2007042500247 20070425 00247 GL 2007 4 25 2007FA0000337 1 20070418 G 2710 CONTROL SYSTEM CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO AILERON SYS OUT OF RIG B K NONE O OTHER IN INSP/MAINT 1 EA 07 636ST 2153 DURING INSPECTION, FOUND AILERON RUDDER INTECONNECT OUT OF RIG AND CAUSING INTERFERENCE BETWEEN RUDDER AND AILERON. THIS IS THE FOURTH AIRCRAFT WE'VE FOUND WITH THIS PROBLEM AND ONE ACTUALLY HAD THE RUDDER AND AILERON LOCK IN FULL OPPOSITE DEFLECTIONS JUST PRIOR TO TAKEOFF. 1 L 7 1 3O 3 O NT A00009CH E3SO 2007042400085 20070424 00085 GL 2007 4 24 2007FA0000339 1 20070419 G 2720 ARM CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO RUDDER MISRIGGED B LC1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 07 927SE 2238 EACH AC THAT CAME INTO THE SHOP WAS INSPECTED FOR THE SAME CONDITION WITH THE AILERON/RUDDER INTERFERENCE. INSPECTION FO UND RUDDER/AILERON INTERCONNECT MISRIGGED RESULTING IN THE BOLT CONNECTING THE BUNGEE TO THE RUDDER/AILERON INTERCONNECT ARM HITTING THE FORWARD CABLE CLAMP AND DEFLECTING THE RT AILERON CABLE. THE CONTROLS DID NOT LOCK BUT THERE WAS DEFIN ITE INTERFERENCE. IN THE NEUTRAL POSITION, THE DISTANCE FROM THE C/L OF THE ARM IS SUPPOSED TO BE 4.5 INCHES. ON THIS AI RPLANE IT ABOUT 3.75 INCHES. THERE WAS NO EVIDENCE OF ANYONE MOVING THE CLAMP OR THE CLAMP SLIDING. RECORDS SHOW THAT TH ERE WAS NO FLIGHT CONTROL RIGGING DONE SINCE THE AIRCRAFT LT THE FACTORY. 1 L 7 1 3O 3 O NT A00009CH E3SO 2007042400083 20070424 00083 GL 2007 4 24 2007FA0000340 1 20070419 G 2720 ARM CIRRUS SR SR20 05628AJ GL CONT O550 IO550N 17042 SO RUDDER MISRIGGED B LC1R D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 EA 07 636ST 1720 PILOT WAS TURNING ONTO RUNWAY IN CROSSWIND WITH FULL OPPOSITE AILERON AND RUDDER CONTROLS. CONTROLS LOCKED IN CROSSED PO SITION AND WOULD NOT RETURN TO NEUTRAL. PILOT RETURNED TO RAMP. INSPECTION FOUND RUDDER/AILERON INTERCONNECT MISRIGGED R ESULTING IN THE BOLT CONNECTING THE BUNGEE TO THE RUDDER/AILERON INTERCONNECT ARM LOCKING OVER THE BOLT GOING THROUGH TH E FORWARD CABLE CLAMP. IN THE NEUTRAL POSITION, THE DISTANCE FROM THE C/L OF THE ARM IS SUPPOSED TO BE 4.5 INCHES. ON TH IS AIRPLANE IT WAS JUST OVER 3 INCHES. THERE WAS NO EVIDENCE OF ANYONE MOVING THE CLAMP OR THE CLAMP SLIDING. RECORDS SH OW THAT THERE WAS NO FLIGHT CONTROL RIGGING DONE SINCE THE AIRCRAFT LEFT THE FACTORY. 1 L 7 1 3O 3 O NT A00009CH E3SO 2007042500246 20070425 00246 GL 2007 4 25 2007FA0000341 1 20070416 G 2750 RELAY CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO T/E FLAP FAILED P A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 SW 01 105SR 1866 DURING A TRAINING FLIGHT, THE FLAPS BECAME STUCK IN THE DOWN POSITION. THE AIRCRAFT RETURNED TO THE AIRPORT WITHOUT INC IDENT AND THE AIRCRAFT WAS SENT TO MAINTENANCE FOR TROUBLESHOOTING. MAINTENANCE DISCOVERED THE FLAPS DOWN RELAY FAILED. 1 L 7 1 3O 3 O NT A00009CH E3SO 2007042500259 20070425 00259 SO 2007 4 25 2007FA0000342 2 20070421 G 8520 655910 CONNECTING ROD CONT TSIO520E CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF34C 3AF34C* GL RT ENGINE FAILED E E ENGINE SHUTDOWN E VIBRATION/BUFFET CL CLIMB 1 NM 05 8FB 176257 402B1372 176257 DURING CLIMB AFTER THE POWER HAD BEEN REDUCED FROM THE TAKEOFF SETTING, THE RT ENGINE STARTED TO VIBRATE. THE PILOT COU LD SEE OIL SPLASHING FROM AROUND THE OIL ACCESS DOOR AND RUNNING BACK ON THE TOP COWLING. THE PILOT SHUTDOWN THE ENGINE AND FEATHERED THE RT PROPELLER. THE PILOT RETURNED TO THE DEPARTURE AIRPORT AND LANDED WITHOUT FURTHER INCIDENT. UPON INITIAL INVESTIGATION, A LARGE HOLE WAS FOUND IN THE CRANKCASE ABOVE THE NR 4 ROD JOURNAL. THE NR 4 CONNECTING ROD WAS SEPARATED FROM THE CRANKSHAFT AND PROTRUDING FROM THE HOLE IN THE CASE. THE NR 4 CONNECTING ROD CAP WAS ALSO SEPARATED FROM THE CONNECTING ROD AND WAS STICKING UP OUT OF THE HOLE. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2007050400146 20070504 00146 WP 2007 5 4 2007FA0000343 2 20070411 G 7261 31080261 SCAVENGE PUMP CESSNA 441 441 2076020 CE GARRTT TPE331 TPE33110 01514 WP LT ENGINE FLUCTUATES B E ENGINE SHUTDOWN J WARNING INDICATION NR NOT REPORTED 1 GL 25 835MA 4410343 P77725 COMMANDED IN-FLIGHT SHUTDOWN OF LT ENGINE DUE TO FLUCTUATING OIL PRESSURE. UNEVENTFUL SINGLE ENGINE LANDING. ENGINE LO ST OIL. OIL EXITED ENGINE FROM TURBINE AIR/OIL SEAL AS A RESULT OF TURBINE SCAVENGE PUMP FAILURE. RECOMMEND COMPLIANCE WITH SB 72-2074R1. (K) 1 L 7 2 3T 4 T RT A28CE E4WE 2007050400173 20070504 00173 EA 2007 5 4 2007FA0000344 2 20070323 G 7320 25765362 SERVO CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL ENGINE FUEL WORN B HUNR O OTHER O OTHER NR NOT REPORTED 1 NM 01 9522S 1938 17280432 RL30493351A SF010 PILOT REPORTS THAT ENGINE DIED ON FINAL APPROACH. ADJUSTED IDLE STOP SLIGHTLY AND MIXTURE SLIGHTLY. RAN ENGINE AND FOU ND THAT SLIGHT ADJUSTMENTS MADE TO FUEL SERVO CREATED LARGE CHANGES IN THE ENGINE OPERATION. UNABLE TO ADJUST THE FUEL SERVO TO MEET PERFORMANCE REQUIREMENTS STATED IN AD2001-06-17, (D)(2). THIS IS THE SECOND ATTEMPT TO ADJUST THE FUEL SE RVO. THE FUEL SERVO WAS REMOVED FROM THE AIRCRAFT AND FORWARDED FOR REPAIR UNDER THEIR W/O NR 07-00900. ORIGINAL FUEL SERVO, PN 25765362, SN 70148401, REINSTALLED ON AC UPON COMPLETION OF REPAIR, WITH REFERENCE TO MM, CHAP 73. IDLE AND M IXTURE ADJUSTMENT COMPLETED WITH REFERENCE TO MM, CHAP 73. OPERATIONAL/LEAK CHECK GOOD AT THIS TIME. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2007050400204 20070504 00204 2007 5 4 2007FA0000345 4 20070117 G 3417 702490031304 ADC LEAR 35 35A 5170602 CE GARRTT TFE731 TFE731* 01518 WP LT AVIONICS BAY MALFUNCTIONED B O OTHER N FALSE WARNING NR NOT REPORTED 1 GL 07 700SJ 082 WHILE ENROUTE, THE PILOTS ALTIMETER (FROZE UP) AT ABOUT 8000 FT AND THE OVERSPEED HORN WENT OFF. THE PILOT RECYCLED THE ADC AND ITS OPERATION WAS RESTORED. THE ADC WAS TESTED AND NO DEFECTS WERE FOUND. THERE WAS NO EVIDENCE OF WATER OR M OISTURE IN OR AROUND THE ADC. THE ADC WAS REPLACED AND TESTED. THERE HAS BEEN NO PREVIOUS REPORTED FAILURES OF THIS SY STEM IN THIS AIRCRAFT. (K) 2 L 7 2 4F 4 F A10CE E6WE 2007042600267 20070426 00267 2007 4 26 2007FA0000346 4 20070122 G 3417 702490031304 ADC LEAR 35 35A 5170602 CE GARRTT TFE731 TFE731* 01518 WP MALFUNCTIONED B O OTHER O OTHER NR NOT REPORTED 1 GL 07 813AS 167 DURING PRE-FLIGHT, THE CREW NOTED THAT THE PILOTS ALTIMETER AND ALTITUDE ALERTER WERE FLAGGED. ATTEMPTS TO RECYCLE THE SYSTEM WERE NOT SUCCESSFUL. THE CREW GROUNDED THE AIRCRAFT. AN AVIONICS TECH WAS DISPATCHED TO THE AIRCRAFTS LOCATION AND DETERMINED THAT THE ADC HAD FAILED. THE ADC WAS REPLACED. THE SYSTEM WAS TESTED AND INSPECTED AND FOUND TO COMPLY WITH FAR 91.411, PART 43 AND TO REMAIN RVSM COMPLIANT. (K) 2 L 7 2 4F 4 F A10CE E6WE 2007050400186 20070504 00186 CE 2007 5 4 2007FA0000348 1 20070330 G 3240 LINE CESSNA 170 170B 2072306 CE CONT C145 C145* 17012 SO BRAKE CHAFED D O OTHER O OTHER NR NOT REPORTED 1 WP 09 4696C 2611 25640 DURING AN ANNUAL INSPECTION, THE RT BRAKE SUPPLY LINE WAS FOUND CHAFED BY THE ELEVATOR CONTROL CABLE. THE CHAFING OCCUR RED WHEN THE ELEVATOR IS OPERATED NEAR THE (UP) LIMIT OF TRAVEL. THE LOCATION OF CHAFE IS VIEWED DIRECTLY BELOW THE ELE VATOR TRIM WHEEL, LOOKING SLIGHTLY FORWARD. THE BRAKE TUBE WAS NOT SUPPORTED BY ANY CLAMPING MEANS TO SECURE THE TUBE. A REPLACEMENT TUBE WAS FABRICATED AND INSTALLED WITH ADEQUATE CLAMPING TO INSURE NO FURTHER CHAFING ACTION. THE BRAKE WAS SERVICED AND A SATISFACTORY LEAK CHECK WAS ACCOMPLISHED. THE ELEVATOR CONTROL CABLE WAS CHECKED FOR DAMAGE AND IS A CCEPTABLE FOR SERVICE. PHOTOS DETAILING THE CHAFED AREA AND MFG IPC FOR INSTALLATION DETAIL. (K) 1 H 7 1 3O 3 O A799 E253 2007050400172 20070504 00172 SO 2007 5 4 2007FA0000349 1 20070401 G 5753 3087B SPAR MAULE M4 M4210C 5460112 SO CONT IO360 IO360* 17025 CE RT FLAP LOOSE D O OTHER O OTHER NR NOT REPORTED 1 WP 09 9810M 5341 1020C DURING AN ANNUAL INSPECTION, THE RT FLAP IB HINGE/CONTROL BRACKET WAS FOUND TO BE LOOSE. FURTHER INSPECTION REVEALED TH AT THE FLAP SPAR WAS CRACKED AT THE UPPER RIVET ATTACH POINTS. THE CRACK IS 3.5 INCH LONG AND EXTENDS PAST THE RIVET HO LES IN BOTH DIRECTIONS. ADDITIONALLY, BOTH CLOSURE RIBS, AT THEIR ATTACH ANGLES TO THE SPAR. THE SPAR PN IS 3078B, RIB PNS 3046-2 AND 3046-1, RIVET PNS SS/SS 34D AND SS/SS 32D (MFG SUPPLIED). THE FLAP SPAR AND RIBS WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (K) 1 H 7 1 3O 3 O 3A23 E1CE 2007050400149 20070504 00149 NE 2007 5 4 2007FA0000350 2 20070401 G 7250 1767M75G03 SHAFT GE BOEING 777 777224 1385225 NM GE GE90 GE9090B NE LPT FAN UNSERVICEABLE B QEMY O OTHER O OTHER NR NOT REPORTED 1 EA 35 78017 36785 T900253 31679 900238 AIRCRAFT TAKEOFF WAS ABORTED, A 147 KNOTS AFTER ENGINE LOST POWER. AC WAS STOPPED SAFELY AND ALL PASSENGERS AND CREW DE PLANED SAFELY. UPON INSPECTION OF THE ENGINE, THE FAN ROTATED FREELY, BUT THE LPT DID NOT ROTATE. BS1 OF THE ENGINE SH OWED THAT THE HPT WAS CLEAN, BUT THE LPT WAS HEAVILY DAMAGED. THE ENGINE WAS SHIPPED TO MFG. INITIAL INSPECTIONS SHOWE D THAT THE FAN MID SHAFT WAS SEPARATED IN THE AXIAL PLANE OF THE HPC S3 DISC. THE CENTER VENT TUBE WAS SEPARATED IN 3 P LACES ALL AFT OF FMS SEPARATION. AND INVESTIGATION IS ON GOING. (K) 2 L 7 2 4F 4 F RT T00001SE E00049EN 2007050700051 20070507 00051 NE 2007 5 7 2007FA0000351 2 20070424 G 8560 230319303 THRUST BEARING LYC LF507 LF5071F NE SUPERCHARGER FAILED B O OTHER O OTHER NR NOT REPORTED 1 WP 07 LF07712 NR 8 THRUST BEARING FAILURE RESULTED IN FAN AND SUPERCHARGER ROTORS TO SHIFT FORWARD CAUSING DAMAGE TO SUPERCHARGER 2ND DISK TO CONTACT THE STATORS MACHINING THROUGH THE 2ND SUPERCHARGER DISK WEB, RESULTING IN IN-FLIGHT SHUTDOWN OF NR 1 E NGINE. OPERATIONAL DESCRIPTION OF EVENT DID NOT INDICATE LOW OIL PRESSURE PRIOR TO THE FAILURE. WARNING SEQUENCE WAS D ESCRIBED AS (1) SMELL IN THE CABIN, HIGH VIBRATIONS WARNING AND VISUAL SPARKES COMING FROM ENGINE, THEN SHUT-DOWN. BEAR ING APPEARS TO BE STARVED OF OIL UPON DISASSEMBLY, ALONG WITH VERY LOW OIL CONTENT IN ADJACENT NR 9 BEARING AND PLANETAR Y REDUCTION GEAR CARRIER. CURRENTLY INVESTIGATING CAUSE OF OIL STARVATION. LUBE PUMP IS FROZEN, BUT ENGINE NR 2 AND NR 4 F E6NE 2007050100116 20070501 00116 SO 2007 5 1 2007FA0000352 2 20070424 G 7322 3801552 CARBURETOR CONT A65 A65* 17003 SO ENGINE MALFUNCTIONED B O OTHER O OTHER NR NOT REPORTED 1 EA 07 CARBURETOR WAS SENT IN FOR AN OVERHAUL BECAUSE IT WOULD NOT ACCEPT THROTTLE. THERE WAS VERY LITTLE TIME ON THE CARBURET OR SINCE IT'S LAST OVERHAUL. UPON DISASSEMBLY, IT WAS FOUND THAT THE CARBURETOR HAD THE WRONG VENTURI INSTALLED AND THE RE WAS OLD CORROSION IN THE FLOAT CHAMBER THAT WAS NOT REMOVED DURING THE PREVIOUS OVERHAUL. IT HAD THE WRONG SEAT INST ALLED FOR THE TYPE NEEDLE THAT WAS BEING USED. IT WAS OBVIOUS THAT SOMEONE WHO THOUGHT THEY KNEW CARBURETORS HAD ATTEMP TED TO OVERHAUL THE UNIT UNSUCCESSFULLY. 3 O E205 2007050400199 20070504 00199 CE 2007 5 4 2007FA0000354 1 20070402 G 2697 MS24266R12B12SN CONNECTOR BEECH 200 B200 1152922 CE PWA PT6 PT6* 52043 EA FIRE DETECTION CORRODED D GONR A UNSCHED LANDING N FALSE WARNING NR NOT REPORTED 1 SW 01 200VU 3534 BB1393 THE AIRCRAFT WAS FLYING THROUGH IMC, WITH ALOT OF RAIN ON THEIR WAY TO DESTINATION. AS THE CREW WAS LETTING DOWN TO LAN D THE LT ENGINE FIRE LIGHT LIT UP. THE CREW SCANNED ALL THE GAGES, AND DETERMINED THAT THIS WAS A FALSE LIGHT. THE AC LANDED WITHOUT COMPLICATION. UPON INSPECTION OF THE LT ENGINE FIRE DETECT SYSTEM, THE TECH FOUND SOME VERY LIGHT CORROS ION AND MOISTURE ON THE J102 CONNECTOR PLUG, LOCATED ON THE LT ENGINE FIRE WALL. THE MOISTURE AND CORROSION WAS REMOVED AND THE FIRE DETECT SYSTEM TESTED PROPERLY, THE AC WAS RETURNED TO SERVICE. APPLING A THIN COATING OF DC-4 GREASE IN T HE CONNECTOR PLUG WOULD PREVENT MOISTURE FROM ENTERING THE PLUG AND THEREFORE KEEP THE CORROSION OUT. (K) 1 L 7 2 4T 3 T A24CE E2NE 2007050700005 20070507 00005 CE 2007 5 7 2007FA0000355 1 20070417 G 7810 265401416 EXHAUST DUCT CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE CRACKED D O OTHER O OTHER NR NOT REPORTED 1 AL 01 4365U 208B0253 CRACKING OCCURRED IN A SHORT TIME SPAN, DURING NORMAL OPERATION. CRACKS WERE OVER AN AREA APPROX 7 INCHES X 7 INCHES. ONE PIECE APPROX 3 INCHES X 3 INCHES SEPARATED FROM THE PART. AFTER CRACKING, DEFORMATION OF LOWER TRAILING EDGE OCCURR ED BECAUSE IT WAS NO LONGER RIGID. IF THIS PROBLEM HAD GONE UNNOTICED, HEAT DAMAGE WOULD PROBABLY HAVE OCCURRED TO ADJA CENT PARTS. MATERIAL OR MFG PROCESS COULD BE SUSPECT. RECENT MFG BULLETIN CAB 07-2 AFFECTS SOME PRIMARY EXHAUST DUCTS DUE TO IMPROPER MFG, BUT IT DOES NOT APPLY TO THIS ONE. (MFG HAS BEEN MADE AWARE OF THIS PROBLEM, PART WAS RETURNED TO THEM ON REQUEST FOR EVALUATION). (K) 1 H 7 1 3T 3 T A37CE E4EA 2007050700185 20070507 00185 SO 2007 5 7 2007FA0000356 2 20070418 G 8530 FRCN68OACA01 CYLINDER HEAD CESSNA 182 182A 2072704 CE CONT O470 O470L 17026 SO NR 1 SEPARATED D FO7R K NONE O OTHER IN INSP/MAINT 1 SO 13 5162D 145 51262 PERFORMED CYLINDER COMPRESSION TEST AND FOUND NR 1 CYLINDER READING 0 PSI AND FOUND LEAKING AROUND CYLINDER HEAD AND BAR REL FINS. UPON REMOVAL THE HEAD IS COCKED SIDEWAYS ON THE BARREL. THE HEAD WAS SEPARATING FROM BARREL. THE CYLINDER P N FRCN68. OACA/01 CL68 CERMINIL FREEDOM. CYLINDER ONLY HAD 145.6 HRS TIME IN SERVICE OVERHAUL IN DEC 2003. (K) 1 H 7 1 3O 3 O NT 3A13 E273 2007042700004 20070427 00004 CE 2007 4 27 2007FA0000357 1 20070425 G 3220 LANDING GEAR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL NOSE BROKEN D O OTHER O OTHER LD LANDING 1 WP 09 757CM 10768 15279633 RL2072615 770307 NOSE LANDING GEAR BROKE AT HARD NOSE LANDING, NO EVIDENCE OF PREVIOUS CRACKS. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2007050400154 20070504 00154 CE 2007 5 4 2007FA0000359 1 20070403 G 5510 12320131 FITTING CESSNA 207 T207A 2073614 CE CONT O520 TSIO520M 17040 SO MCAULY D3A34 D3A34C401 GL STABILIZER CRACKED D O OTHER O OTHER NR NOT REPORTED 1 WP 07 803AN 11657 20700570 248811R 765815 FWD RT STABILIZER FITTING CRACKED. FOUND CRACKED FITTING UPON ANNUAL INSPECTION OF EMPENNAGE. (K) 1 H 7 1 3O 3 O A16CE E8CE 5 C P47GL 2007050400212 20070504 00212 EU 2007 5 4 2007FA0000360 1 20070407 G 5340 N325400A BRACKET SNIAS 350 AS350B3 8680954 EU FUSELAGE BROKEN B EOOR O OTHER O OTHER NR NOT REPORTED 1 AL 03 C6YPN 480 3688 DURING 100 HR INSPECTION, THE MECHANIC REACHED TO UNSCREW THE OIL FILTER AND THE BRACKET BROKE OFF IN HIS HAND. REPLACE D UNIT, THE ENTIRE BREAK LOOKED FRESH EVEN WITH 10X MAGNIFICATION. IT IS A POT METAL BRACKET. (K) 1 G 7 1 3U H9EU 2007050400229 20070504 00229 CE 2007 5 4 2007FA0000361 1 20070419 G 2420 COUPLING CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO ALTERNATOR WORN B YYBR O OTHER O OTHER NR NOT REPORTED 1 GL 03 63332 15077241 250316 ALTERNATOR DRIVE COUPLING WAS WORN AND SEVERELY LOOSE WITH EXCESSIVE PLAY DUE TO SOFT, UNDERCUT BUSHINGS PN 632050. IN ADDITION, THE DRIVE HUB KEY WAY WAS SEVERELY WORN CAUSING EXCESSIVE PLAY OF THE HUB ON THE SHAFT. CONTINUED OPERATION W OULD RESULT IN DRIVE COUPLING RETAINER PN 352030 FAILING AND POTENTIALLY CAUSING CATASTROPHIC ENGINE FAILURE. THE CURRE NT RUBBER BUSHINGS ARE SOFT AND ALLOW THE DRIVE GEAR TO CRUSH AND DEFORM THEM WHICH REDUCES SHOCK ABSORPTION AND LEADS T O DRIVE COUPLING FAILURE WHEN DRIVE GEAR BEGINS TO CONTACT THE RETAINER CUP DIRECTLY. THIS IS A RECURRING PROBLEM AS FO UND ON OTHER ALTERNATORS USING THIS TYPE OF DRIVE COUPLING AS LISTED IN SB 95-3B. (K) 1 H 7 1 3O 3 O 3A19 E252 2007050400225 20070504 00225 CE 2007 5 4 2007FA0000362 1 20070419 G 2910 98811281 POWERPACK CESSNA 172 172RG 2072438 CE LYC O360 O360* 41514 EA HYD SYSTEM MISREPAIRED D O OTHER O OTHER NR NOT REPORTED 1 SW 03 413EB 172RG0113 INSTALLED A NEWLY OVERHAULED COMPLETE HYDRAULIC POWER PACK UNIT AS RECEIVED. AFTER INSTALLING THE UNIT IN THE AIRCRAFT AND PERFORMING A RETRACT TEST THE NEW OVERHAULED GEAR MOTOR WAS JERKY AND ACTING LIKE IT WAS SHORTING OUT. REMOVED MOTO R AND INSTALLED ANOTHER NEW OVERHAULED MOTOR AND SYSTEM WORKED FINE. (K) 1 H 7 1 3O 3 O 3A17 E286 2007050400233 20070504 00233 CE 2007 5 4 2007FA0000363 1 20070411 G 3210 05412024 BUSHING CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA RMLG UNSERVICEABLE B NU7R O OTHER O OTHER NR NOT REPORTED 1 GL 13 106RA 3586 172S8241 BUSHING LINER SEPARATED FROM METAL SHELL, SLID OUT OF SHELL CAUSING AC TO LEAN RT WING TIP LOW. BETTER BONDING ADHESIVE FOR LINER TO SHELL. NEED TO GO TO A TIME SCHEDULE FOR INSPECTION. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2007050700182 20070507 00182 CE 2007 5 7 2007FA0000364 1 20070420 G 3230 LANDING GEAR CESSNA 500 S550 2076607 CE PWA JT15 JT15D4 52112 NE MALFUNCTIONED B EBVR O OTHER O OTHER NR NOT REPORTED 1 GL 09 32TX S5500026 EMERGENCY LANDING GEAR DEPLOYMENT SYSTEM INSPECTED DURING ROUTINE PHASE INSPECTION. EMERGENCY GEAR CABLES CHECKED FOR C ORRECT RIGGING, AND EMERGENCY GEAR SYSTEM FUNCTION TESTED WITH AIRCRAFT ON JACKS. SYSTEM FUNCTION TESTED PROPERLY. PIL OT ELECTED TO PERFORM IN FLIGHT CHECK OF SAME SYSTEM AND FOUND THAT MAIN GEAR WOULD NOT DEPLOY. PILOT EXTENDED GEAR USI NG NORMAL HYDRAULIC SYSTEM OPERATION AND LANDED WITHOUT INCIDENT. AC WAS FLOWN TO SERVICE CENTER FOR EVALUATION. (K) 1 L 7 2 4F 4 F RT A22CE E1NE 2007050400213 20070504 00213 CE 2007 5 4 2007FA0000366 1 20070412 G 7921 652065 GASKET CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO OIL COOLER BROKEN D O OTHER O OTHER NR NOT REPORTED 1 CE 01 42776 322 421B0394 607077 AIRCRAFT DEPARTED ON A CHARTER , PILOT WAS OVER LAKE WHEN HE NOTICED ENGINE OIL COMING OUT OF TOP ENGINE COWLING COOLING LOUVERS. PILOT NOTIFIED CONTROL HE WAS LOSING OIL. FEATHERED THE RT ENGINE AND DIVERTED . PILOT MADE UNEVENTFUL SING LE ENGINE LANDING AND TAXIED TO MAINTENANCE HANGAR. DISCOVERED THE ENGINE WAS SEIZED AND THE COWLING AND NACESSE BOTTOM COVERED WITH OIL. STARTED DISASSEMBLY AND FOUND THE OIL COOLER GASKET, PN 652065, HAD .1250 INCH SECTION MISSING FROM THE UPPER FORWARD AREA OF THE GASKET. (K) 1 L 7 2 3O 3 O A7CE E7CE 2007050400214 20070504 00214 CE 2007 5 4 2007FA0000367 1 20070420 G 5100 6213011139 DOUBLER CESSNA 650 650 2076802 CE UNKNOWN FATIGUED B CNQR O OTHER O OTHER NR NOT REPORTED 1 CE 07 THE 6213011139 LT DOUBLER AND THE 6213011140 RT DOUBLER FATIGUE CRACKING ON BOTH. THE 6213011139 LT DOUBLER AND THE 621 3011140 RT DOUBLER, ON MODEL 650 IS PART OF THE NOSE WHEEL WELL ASSY, HAS BEEN FOUND WITH FATIGUE CRACKING ON MULTIPLE S N. CURRENTLY THE PART IS BEING REMOVED AND REPLACED AS NEEDED AND A SERVICE CONDITION REPORT (SCR) HAS BEEN SUBMITTED T O ENGINEERING FOR REVIEW. (K) 2 L 7 2 4F A9NM 2007050400227 20070504 00227 CE 2007 5 4 2007FA0000368 1 20070420 G 5310 6213011140 DOUBLER CESSNA 650 650 2076802 CE FS 92-94 FATIGUED D CNQR O OTHER O OTHER NR NOT REPORTED 1 CE 07 THE 6213011-139 LT DOUBLER AND THE 6213011-140 RT DOUBLER FATIGUE CRACKING ON BOTH. THE 6213011-139 LT DOUBLER AND THE 6213011-140 RT DOUBLER, ON MODEL 650 IS PART OF THE NOSE WHEEL WELL ASSY, HAS BEEN FOUND WITH FATIGUE CRACKING ON MULTIP LE SN. CURRENTLY THE PART IS BEING REMOVED AND REPLACED AS NEEDED, AND A SERVICE CONDITION REPORT (SCR) HAS BEEN SUBMIT TED TO ENGINEERING FOR REVIEW. (K) 2 L 7 2 4F A9NM 2007050400223 20070504 00223 CE 2007 5 4 2007FA0000369 1 20070404 G 3210 084100097 LANDING GEAR CESSNA 310 310D 2074212 CE CONT O470 IO470* 17026 SO LT MLG MALFUNCTIONED D O OTHER O OTHER NR NOT REPORTED 1 NM 03 6981T 39281 THE PILOT NOTED THAT SOMETHING WAS HANGING DOWN UNDER THE AC IN CRUISE FLIGHT AND THAT THE AC WAS NOT GOING AS FAST AS I T NORMALLY DID. ANOTHER AC NOTED THAT THE GEAR WAS UP, BUT THAT THE LEFT IB GEAR DOOR WAS HANGING DOWN PART WAY. THE T OWER CONFIRMED THAT THE GEAR APPEARED TO BE DOWN AND LOCKED, BUT THAT THE LT IB GEAR DOOR WAS PART WAY DOWN. ALL INDICA TIONS OF THE GEAR IN THE AC WERE NORMAL AND THE GREEN LIGHT WAS ON WHEN THE AC LANDED. THE AIRCRAFT LANDED NORMALLY AND ROLLED ABOUT 800 FT DOWN THE RUNWAY WHEN THE LEFT MAIN GEAR BROKE OUT OF THE WHEEL WELL. IT WENT STRAIGHT BACK BEHIND THE WING AND THE AC WENT AROUND TO THE LEFT AND OFF THE RUNWAY. THE LT IB DOOR WILL MOVE SOME BY HAND AND SEEMED TO OPE 1 L 7 2 3O 3 O 3A10 E1CE 2007050400133 20070504 00133 2007 5 4 2007FA0000370 4 20070427 G 2562 MN1300 BATTERY ACK PIPER PA28 PA28236 7102815 SO LYC O540 O540J3A5 41532 EA HARTZL HCF2Y HCF2YR1 GL ELT LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 01 12 020150 28791146 L2113440A CM285 BATTERIES LEAKED ACID/ALKALII, CORRODING CONTACTS SERVERLY AND RENDERING ELT INOPERABLE. BATTERIES WERE INSTALLED IN 20 06. SHELF DATE ON BATTERIES WERE MAR 2011. ELT WAS NOT FOUND ACTIVATED. THIS IS THE THIRD CASE OF THIS I HAVE SEEN IN 20 06/2007 AND THERE HAVE BEEN SEVERAL OTHERS IN THE PAST 5 YEARS. IN ALL CASES THE BATTERIES RENDERED THE ELT INOP PRIOR TO THE REPLACEMENT DATE (HALF OF SHELF LIFE IAW FAR 91.207 (C)). ALL PROBLEMS WERE DETECTED DURING ANNUAL INSPECTIONS OF ELT IAW FAR 91.207 D. 1 L 7 1 3O 3 O 2A13 E295 5 C P27EA 2007050400134 20070504 00134 2007 5 4 2007FA0000371 4 20070427 G 2562 MN1300 BATTERY ACK PIPER PA28 PA28236 7102815 SO LYC O540 O540J3A5 41532 EA HARTZL HCF2Y HCF2YR1 GL ELT LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 01 12 020150 28791146 L2113440A CM285 BATTERIES LEAKED ACID/ALKALII, CORRODING CONTACTS SERVERLY AND RENDERING ELT INOPERABLE.BATTERIES WERE INSTALLED IN 2006 . SHELF DATE ON BATTERIES WERE MAR 2011. ELT WAS NOT FOUND ACTIVATED. THIS IS THE THIRD CASE OF THIS I HAVE SEEN IN 2006 /2007 AND THERE HAVE BEEN SEVERAL OTHERS IN THE PAST 5 YEARS. IN ALL CASES THE BATTERIES RENDERED THE ELT INOP PRIOR TO THE REPLACEMENT DATE (HALF OF SHELF LIFE I/A/W FAR 91.207 (C)). ALL PROBLEMS WERE DETECTED DURING ANNUAL INSPECTIONS OF ELT I/A/W FAR 91.207 D. 1 L 7 1 3O 3 O 2A13 E295 5 C P27EA 2007050400153 20070504 00153 2007 5 4 2007FA0000372 4 20070502 G 2562 MN1300 BATTERY AMERIKING CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA ELT LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 01 12 12 353328 01165 BATTERIES LEAKED INSIDE ELT UNIT PREVENTING ELT OPERATION AND DESTROYING CONTACTS INSIDE UNIT. THIS IS ONE OF SEVERAL TI MES THIS PROBLEM HAS BEEN SEEN IN THE NEWER OR MORE RECENTLY MANUFACTURED BATTERIES THIS PARTICULAR SET HAD AN EXPIRATIO N OF 2012 AND HAD ONLY BEEN INSTALLED IN THE UNIT FOR ONE YEAR. RECOMMEND BAT REPLACEMENT EVERY 6 MONTHS UNTIL THIS PRO BLEM IS ADDRESSED BY ELT MANUFACTURES OR THE BATTERY COMPANY NOTE OLDER BATTERIES DID NOT EXHIBIT THIS PROBLEM. 1 H 7 1 3O 3 O RT 3A13 E295 2007050400161 20070504 00161 GL 2007 5 4 2007FA0000375 1 20070427 G 2720 CONTROL CABLE CIRRUS SR SR22 2130001 GL CONT O550 IO550* SO AILERONS INTERFERENCE B K NONE O OTHER IN INSP/MAINT 1 EA 07 220SR 0391 DURING INSPECTION FOUND INTERFERENCE BETWEEN RUDDER/AILERON INTERCONNECT SYSTEM AND RT AILERON CABLE. CHECKED RIGGING AN D FOUND CABLE CLAMP ON RT AILERON CABLE OUT OF POSITION. VISUAL INSPECTION INDICATES NO MOVEMENT BETWEEN CABLE AND CLAMP AND RECORDS REVIEW INDICATE THAT NO RIGGING HAS TAKEN PLACE SINCE THE AIRPLANE LEFT THE FACTORY. 1 L 7 1 3O 3 O NT A00009CH E3SO 2007050400170 20070504 00170 CE 2007 5 4 2007FA0000377 1 20070426 G 3232 ROD GARKENYON LEAR 60 60LEAR 5170707 CE WRIGHT R3350 R3350* 67040 EA ACTUATOR FAILED D O OTHER J WARNING INDICATION LD LANDING 1 SO 09 718A 0290 065 WHEN LANDING GEAR WAS CYCLED DOWN, THE RT RED IB GEAR DOOR OPEN LIGHT WOULD NOT EXTINGUISH. GEAR DOWN LOCK LIGHTS WERE G REEN. NORMAL LANDING. INSPECTION REVEALED THAT THE ACTUATOR SHAFT HAD UNSCREWED FROM THE PISTON NOT ALLOWING THE DOOR TO CLOSE. FURTHER EXAMINATION REVEALED THAT THE ROLL PIN SECURING THE SHAFT TO THE PISTON WAS SHEARED. THE LT ACTUATOR WA S INSPECTED AND THE ACTUATOR ROD WAS FOUND TO BE 2.5 TURNS FROM DISENGAGING FROM THE PISTON. 6-7 TURNS BOTTOMS THE ROD I N THE PISTON. REPLACED BOTH DOOR ACTUATORS. 2 L 7 2 4F 4 R RT A10CE E272 2007050400188 20070504 00188 CE 2007 5 4 2007FA0000378 1 20070426 G 3232 66000858 ACTUATOR LEAR 60 60LEAR 5170707 CE WRIGHT R3350 R3350* 67040 EA MLG FAILED D O OTHER J WARNING INDICATION LD LANDING 1 SO 09 718A 4200 065 WHEN LANDING GEAR WAS CYCLED DOWN, THE RT RED IB GEAR DOOR OPEN LIGHT WOULD NOT EXTINGUISH. GEAR DOWN LOCK LIGHTS WERE GREEN. NORMAL LANDING. INSPECTION REVEALED THAT THE ACTUATOR SHAFT HAD UNSCREWED FROM THE PISTON NOT ALLOWING THE DOOR TO CLOSE. FURTHER EXAMINATION REVEALED THAT THE ROLL PIN SECURING THE SHAFT TO THE PISTON WAS SHEARED. THE LT ACTUATOR W AS INSPECTED AND THE ACTUATOR ROD WAS FOUND TO BE 2.5 TURNS FROM DISENGAGING FROM THE PISTON. 6-7 TURNS BOTTOMS THE ROD IN THE PISTON. REPLACED BOTH DOOR ACTUATORS. 2 L 7 2 4F 4 R RT A10CE E272 2007050400206 20070504 00206 CE 2007 5 4 2007FA0000381 1 20070404 G 7810 02R3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA RT ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 09 13510 514 PCE81382 WHILE PREFORMING SCHEDULED MAINTENANCE, REMOVED LT ENGINE EXHAUST STACK TO FACILITATE INSPECTING THE EXHAUST DUCT. FOUND CRACK FOLLOWING THE CIRCUMFERENCE OF THE SKI SLOPE. THE EXHAUST DUCT HAD SB 3380 COMPLIED WITH 514 HOURS EARLIER.POWER SECTION WAS REMOVED AND SENT FOR REPAIR. 1 L 7 2 4T 4 T A24CE E4EA 2007050400215 20070504 00215 SO 2007 5 4 2007FA0000383 1 20070430 G 5520 2039700 HORN PIPER PA24 PA24250 7102404 SO LYC O540 O540* 41532 EA STABILIZER CRACKED D O OTHER O OTHER NR NOT REPORTED 1 WP 07 5977P 6000 241070 FOUND STABILATOR HORN P/N 20397-00 SEVERELY CRACKED FROM THE INSIDE WHERE THE ATTACH BOLTS CONNECT THE BALANCE WEIGHT TU BE P/N 20398-02 AND STABILATOR TORQUE TUBE ASSEMBLY P/N 20203-03. 1 L 7 1 3O 3 O 1A15 E295 2007061300266 20070613 00266 2007 6 13 2007FA0000385 2 20070501 G 7320 FADEC DIAMON DA40 DA40 2990002 GL MALFUNCTIONED C O OTHER O OTHER NR NOT REPORTED 1 SW 99 103 THE ECU WARNING LIGHTS HAVE COME ON MULTIPLE TIMES NOW. ACCRODING TO THE MANUFACTURER, EACH TIME THESE ANNUNCIATORS COM E ON THE AIRCRAFT MUST BE SERVICED BY AN APPROVED MECHANIC. BY THIELERTS EXPLANATION, IF THE AIRCRAFT GOES INTO A STEEP BANK OR UN-COORDINATED TURN THAN AN AIR BUBBLE CAN GET INTO THE FUEL LINE AND CAUSE UNEVEN PRESSURES BETWEEN THE TWO ENG INES. THE FADEC SENSES THIS AS A PROBLEM AND THE ECU WANRINGS TRIP. ACCORDING TO THIELERT THIS HAS BEEN HAPPENING FREQ UENTLY ON AIRCAFT WITH THEIR FADEC ENGINES. THREE TIMES ALREADY ON OUR WITHIN 100 HOURS. IT IS A NUISANCE BECAUSE AN A IRCRAFT CAN EASILY BE STRANDED IN A LOCATION WITHOUT A THIELERT APPROVED MECHANIC. OR WORSE, IF A GENUINE PROBLEM EXISTE 1 L 7 1 3O NT A47CE 2007050700184 20070507 00184 2007 5 7 2007FA0000386 2 20070501 G 7320 FADEC DIAMON DA40 DA40 2990002 GL MALFUNCTIONED C O OTHER O OTHER NR NOT REPORTED 1 SW 03 103 THE ECU WARNING LIGHTS HAVE COME ON MULTIPLE TIMES NOW. ACCORDING TO THE MANUFACTURER, EACH TIME THESE ANNUNCIATORS COM E ON THE AIRCRAFT MUST BE SERVICED BY AN APPROVED MECHANIC. BY THIELERTS EXPLANATION, IF THE AIRCRAFT GOES INTO A STEEP BANK OR UN-COORDINATED TURN THAN AN AIR BUBBLE CAN GET INTO THE FUEL LINE AND CAUSE UNEVEN PRESSURES BETWEEN THE TWO ENG INES. THE FADEC SENSES THIS AS A PROBLEM AND THE ECU WARNINGS TRIP. ACCORDING TO MANUFACTURE THIS HAS BEEN HAPPENING F REQUENTLY ON AIRCRAFT WITH THEIR FADEC ENGINES. THREE TIMES ALREADY ON OUR WITHIN 100 HOURS. IT IS A NUISANCE BECAUSE AN AIRCRAFT CAN EASILY BE STRANDED IN A LOCATION WITHOUT A THIELERT APPROVED MECHANIC. OR WORSE, IF A GENUINE PROBLEM EX 1 L 7 1 3O NT A47CE 2007052100146 20070521 00146 CE 2007 5 21 2007FA0000388 1 20070413 G 3233 99101368 ACTUATOR CESSNA 414 414A 2075907 CE CONT O520 TSIO520* 17040 SO LT MLG CORRODED D O OTHER O OTHER TX TAXI/GRND HDL 1 EA 61 6672C 7623 414A0053 LT LANDING GEAR ACTUATOR FAILED WHILE TAXING. COLLAPSED LT WING. DAMAGED LT PROP AND WING TIP. ACTUATOR INSPECTED AND FOUND WATER INSIDE. ACTUATOR OVERHAULED AND REINSTALLED NOSE AND RT LG ACTUATOR REMOVED FOR INSPECTION AND CHECKED GOO D. (K) 1 L 7 2 3O 3 O A7CE E8CE 2007052100114 20070521 00114 EA 2007 5 21 2007FA0000389 2 20070420 G 8530 5L32006WA1 CYLINDER CESSNA 172 172N 2072434 CE LYC O320 O320D2J 41508 EA ENGINE CRACKED D O OTHER O OTHER NR NOT REPORTED 1 NM 01 4801D 1400 17272362 CRACK FROM EXH STUD AROUND CYLINDER TO UPPER SPARK PLUG. (K) 1 H 7 1 3O 3 O NT 3A12 E274 2007051400210 20070514 00210 GL 2007 5 14 2007FA0000390 2 20070412 G 7323 369A7701 BRACKET HUGHES 369 369D 4470706 WP ALLSN 250C 250C20 03013 GL GOVERNOR DAMAGED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 1151D DURING A PREFLIGHT, THE PILOT NOTICED THE GOVENOR BELCRANK HAD SOME SLOP SUBSEQUENT INSPECTION DISCLOSED THAT THE BELCRA NK PIVOT BOLT WAS MOVING IN THE BRACKET BECAUSE THE HOLE WAS ELONGATED, REPLACED BRACKET. (K) 1 G 7 1 3U 3 U H3WE E4CE 2007052100147 20070521 00147 SO 2007 5 21 2007FA0000391 2 20070411 G 7414 6310 MAGNETO BEECH 33 F33A 1151425 CE CONT O520 IO520BA 17032 SO LEFT FAILED D O OTHER O OTHER NR NOT REPORTED 1 GL 19 11BX 26 CE388 814263R DURING NORMAL FLIGHT, VFR CONDITIONS, LT MAGNETO FAILED TO CONTINUE FIRING. AC LANDED WITHOUT INCIDENT. UPON TROUBLESH OOTING LT MAGNETO FOUND TO ONLY FIRE ON ONE LEAD. MAGNETO REPLACED WITH NEW UNIT. DEFECTIVE MAGNETO FOUND TO HAVE LOOS E PARTS RATTLING INSIDE AFTER REMOVAL FROM ENGINE. MAGNETO NOT DISASSEMBLED DUE TO WARRANTY STATUS OF MAGNETO. (K) 1 L 7 1 3O 3 O 3A15 E5CE 2007051400183 20070514 00183 2007 5 14 2007FA0000392 1 20070301 G 1430 TAB CRACKED B UO2R O OTHER O OTHER NR NOT REPORTED 1 GL 19 WHEN TECH WENT TO BEND THE TAB ATTACHED TO THE WASHER AT THE RADIUS OF THE BEND, THEY WOULD CRACK. (K) 2007052100084 20070521 00084 CE 2007 5 21 2007FA0000393 1 20070409 G 7921 LW10025 OIL COOLER BEECH 60 A60 1153604 CE LYC O541 TIO541E1C4 41536 EA LT ENGINE CRACKED G A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 SO 09 1873W 142 P231 ON APRIL 9, 2007, MADE A PRECAUTIONARY LANDING, AL (TCL) DUE TO LOW OIL PRESSURE ON THE LEFT ENGINE. MAINTENANCE PERSON NEL REPORTED THAT THE OIL COOLER HAD FAILED DUE TO CRACKS, THE OIL LEVEL WAS DOWN (4) QUARTS, AND THE OIL FILTER WAS INS PECTED WITH NO CONTAMINATION FOUND. ENGINE MAINTENANCE LOG RESEARCH SHOWED THE FAILED OIL COOLER WAS OVERHAULED AND INS TALLED BY FIREWALL FORWARD. THE COOLER WAS REPLACED WITH A NEW PART ON 4/13/2007 AT 1770.6 HOBBS. THE FAILED OIL COOLE R HAD 142.1 HOURS SINCE OVERHAUL. NO DETERMINATION COULD BE MADE OF OIL COOLER TOTAL TIME. (K) 1 L 7 2 3O 3 O A12CE E10EA 2007051400208 20070514 00208 CE 2007 5 14 2007FA0000394 1 20070406 G 3233 98820152 ACTUATOR CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL LT MLG CRACKED D H2US O OTHER O OTHER AP APPROACH 1 SW 11 9353D 172RG1131 L1868036A 801202 PILOT REPORTED LOUD POP JUST BEFORE INTERING THE PATTERN AT M89. WHEN HE EXTENDED THE GEAR THE GREEN GEAR DOWN LIGHT WO ULD NOT COME ON. FLY BY REVEALED THE LEFT GEAR WAS IN TRANSIENT. GEAR UP LANDING FOLLOWED. INSPECTION OF LT MAIN GEAR ACTUATOR REVEALED THE ACTUATOR HOUSING WAS CRACKED ACROSS THE FORWARD ATTACH BOLT HOLE. THE CRACKED HOUSING ALLOWED TH E PISTON RACK TO JUMP GEARS ON THE PINION GEAR ATTACHED TO MAIN GEAR LEG. THIS AREA IS INSPECTED EACH 100 HR FOR CRACKS AND DEFECTS VERY CAREFULLY WITH LIGHTS AND INSPECTION MIRROWS. TIME SINCE LAST INSPECTION WAS 25 HRS. AD 2001-06-06 W AS CW 8-13-2001 TACH 497, TOTAL TIME 4516 WITH NO DEFECTS FOUND. (K) 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2007051400224 20070514 00224 CE 2007 5 14 2007FA0000395 1 20070423 G 3246 13685 BEARING BEECH 1900 1900D 1154162 CE MLG LACK OF LUBE B HY1R K NONE O OTHER IN INSP/MAINT 1 EA 23 733DC 360 UE307 WHILE PERFORMING ROUTINE PREVENTATIVE MAINTENANCEON THE RT IB WHEEL AND TIRE ASSEMBLY (TO CHANGE A WORN TIRE) ONE OF THE WHEEL BEARING ROLLERS CAME OUT OF THE OUTER WHEEL BEARING ONCE THE WHEEL BEARING WAS REMOVED FROM THE WHEEL ASSEMBLY. THE WHEEL BEARING CAGE WAS FOUND TO BE DEFORMED WITH ONE PART OF THE CAGE BROKEN ALLOWING THE ROLLER TO FALL OUT. PIECE S OF METAL WERE FOUND IN THE BEARING SEAL. THE BEARING APPEARS TO HAVE BEEN OVERHEATED. PROPER LUBRICATION WOULD HAVE PREVENTED THIS BEARING FROM OVERHEATING. IT IS IMPERATIVE THAT EACH OPERATOR BE AWARE THAT THE INSPECTION AND LUBRICATI ON REQURIEMENT/INTERVAL FOR THE WHEEL BEARINGS MAY BE LESS THAN THE MFG RECOMMENDATIONS BASED ON THE OPERATORS OWN SPECI 2 L 7 2 4T RT A24CE 2007051400182 20070514 00182 2007 5 14 2007FA0000396 4 20070430 G 3400 593250101 SWITCH CESSNA 414 414 2075908 CE CONT O520 TSIO520* 17040 SO COCKPIT STUCK B YLMR O OTHER O OTHER NR NOT REPORTED 1 WP 23 42SG 2972 4140927 AVIONICS MASTER SWITCH STUCK IN THE ON POSITION AD 2005-20-25 WAS PREVIOUSL COMPLIED WITH AND DID NOT APPLY. DATE CODE OF THE SWITCH WAS 7647. THERE WAS NO BURNING SMELL WHEN THE SWITCH BECAME STUCK. (K) 1 L 7 2 3O 3 O RT A7CE E8CE 2007052100141 20070521 00141 SO 2007 5 21 2007FA0000397 1 20070331 G 3210 BEARING PIPER PA24 PA24250 7102404 SO LYC O540 AEIO540* EA MLG BROKEN D O OTHER O OTHER NR NOT REPORTED 1 EA 61 7178P 242347 L259640 BEARING ROD END BROKEN AT THREAD EXP BEARING (452377) CONDUIT BENT. CONTROL ASSY (455180). 1 L 7 1 3O 3 O 1A15 1E4 2007052100075 20070521 00075 SO 2007 5 21 2007FA0000398 2 20070418 G 7414 6320 MAGNETO CESSNA 210 T210N 2073456 CE CONT O520 TSIO520R 17040 SO MCAULY D3A34 D3A34C402 GL ENGINE CORRODED G A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 EA 13 5361Y 525 21064183 517975 871106 EMERGENCY RETURN TO FIELD: INSPECTION REQUIREMENTS FOR MAGNETO (PN 6320) ARC NOT ADEQUATE TO INSURE PROPER VENTING (PRE SSURIZED MAG). SB 2-80C SPECIFIES ONLY EXTERNAL INSPECTION IS REQUIRED EVERY 100 HOURS AND AN INTERNAL INSPECTION AFTER 500 HOURS. THE SUBJECT MAGNETOS WITH 525 AND 438 CONTAINED MOISTURE AND EXCESSIVE CORROSION INTERNALLY BECAUSE THE PRE VIOUS REQUIREMENTS TO TEST PRESSURIZED MAGNETOS CONTAINED IN SB 1-88A DO NOT APPLY TO THE 6300 SERIES MAGNETOS. (K) 1 H 7 1 3O 3 O 3A21 E8CE 5 C P47GL 2007052100115 20070521 00115 SO 2007 5 21 2007FA0000399 2 20070418 G 7414 6320 MAGNETO CESSNA 210 T210N 2073456 CE CONT O520 TSIO520R 17040 SO MCAULY D3A34 D3A34C402 GL ENGINE CORRODED G O OTHER O OTHER NR NOT REPORTED 1 EA 13 5361Y 438 21064183 517975 871106 EMERGENCY RETURN TO FIELD: INSPECTION REQUIREMENTS FOR MAGNETO (PN 6320) ARC NOT ADEQUATE TO INSURE PROPER VENTING (PRE SSURIZED MAG). SB2-80C SPECIFIES ONLY EXTERNAL INSPECTION IS REQUIRED EVERY 100 HOURS AND AN INTERNAL INSPECTION AFTER 500 HOURS. THE SUBECT MAGNETOS WITH 525 AND 438 CONTAINED MOISTURE AND EXCESSIVE CORROSION INTERNALLY BECAUSE THE PREVI OUS REQUIREMENTS TO TEST PRESSURIZED MAGNETOS CONTAINED IN SB 1-88A DO NOT APPLY TO THE 6300 SERIES MAGNETOS. (K) 1 H 7 1 3O 3 O 3A21 E8CE 5 C P47GL 2007051400200 20070514 00200 GL 2007 5 14 2007FA0000400 2 20070425 G 7230 BEARING HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE FAILED B EOOR O OTHER J WARNING INDICATION NR NOT REPORTED 1 AL 03 511SB 504 1090592D CAE830001 DURING FLIGHT THE UPPER CHIP PULL ILLUMINATED, IT WAS CLEANED IAW MM AND RETURNED TO SERVICE. A COUPLE OF HOURS LATER, A SECOND LIGHT ILLUMINATED. FOUND LOTS OF FINE CHIPS. REPLACED ENGINE. FOUND NR 1 BEARING BAD. (K) 1 G 7 1 3U 3 U H3WE E4CE 2007061500173 20070615 00173 2007 6 15 2007FA0000401 1 20070521 G 5100 31699042 HOUSING UNKNOWN CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 CRACK IN PART ID. 2007061500174 20070615 00174 CE 2007 6 15 2007FA0000402 1 20070522 G 2750 CONTROL CABLE SYMPHO SA160 SA160 05619SU CE TE FLAPS CHAFED P K NONE O OTHER IN INSP/MAINT 1 SO 15 DURING PREFLIGHT INSPECTION, FOUND FLAP CONTROL CABLES CHAFING ON THE FLAP TRACK. DEPTH OF INTERFERENCE BETWEEN CABLE A ND TRACK WAS ABOUT THE DIAMETER OF THE CABLE. 1 H 7 1 3O NT A46CE 2007061500175 20070615 00175 CE 2007 6 15 2007FA0000403 1 20070522 G 5750 CONTROL CABLE SYMPHO SA160 SA160 05619SU CE TE FLAPS CHAFED P K NONE O OTHER IN INSP/MAINT 1 SO 15 DURING PREFLIGHT INSPECTION, FOUND FLAP CONTROL CABLES CHAFING ON THE FLAP TRACK. DEPTH OF INTERFERENCE BETWEEN CABLE A ND TRACK WAS ABOUT THE DIAMETER OF THE CABLE. 1 H 7 1 3O NT A46CE 2007061500176 20070615 00176 EU 2007 6 15 2007FA0000404 1 20070522 G 5330 SKIN ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE73131G 29003 NE FUSELAGE CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 23 600NY 231 FOUND SEVERE PITTING CORROSION ON BOTH THE LT AND RT SIDES BETWEEN FRAME, STATIONS 184 AND 194 BELOW EMERGENCY ESCAPE DO ORS. BELIEVE THIS IS DUE TO WATER LEAKING AROUND THE EMERGENCY ESCAPE DOORS AND SOAKING THE SOUND DAMPENING INSULATION. THE PITTING WAS SO BAD IT CORRODED THROUGH THE SKIN ON THE RT SIDE. THIS CORROSION WAS FOUND DURING AN RVSM INSTALLAT ION WHILE WE WERE MARKING OUT THE CRITICAL REGION AROUND THE STATIC PORTS. WE REPAIRED THE DAMAGE FOLLOWING APPROVED DA TA FROM A STRUCTURAL ENGINEER AND RETURNED TO SERVICE IAW FAA FORM 8110-3. 2 M 7 2 4F 4 F A2SW E6WE 2007061500177 20070615 00177 EU 2007 6 15 2007FA0000405 1 20070522 G 5330 SKIN ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE73131G 29003 NE FUSELAGE CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 23 600NY 231 FOUND SEVERE (PITTING CORROSION) ON BOTH THE LT AND RT SIDES BETWEEN FRAME, STATIONS 184 AND 194 BELOW EMERGENCY ESCAPE DOORS. THIS IS DUE TO WATER LEAKING AROUND THE EMERGENCY ESCAPE DOORS AND SOAKING THE SOUND DAMPENING INSULATION. THE PITTING WAS SO BAD IT CORRODED THROUGH THE SKIN ON THE RT SIDE. THIS CORROSION WAS FOUND DURING AN RVSM INSTALLATION WH ILE WE WERE MARKING OUT THE CRITICAL REGION AROUND THE STATIC PORTS. REPAIRED THE DAMAGE FOLLOWING APPROVED DATA FROM A STRUCTURAL ENGINEER AND RETURNED TO SERVICE IAW FAA FORM 8110-3. 2 M 7 2 4F 4 F A2SW E6WE 2007061400237 20070614 00237 CE 2007 6 14 2007FA0000410 1 20070110 G 3245 0923540 TUBE BEECH 18 D18S 1151004 CE PWA R985 R985* 52008 NE TIRE BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 500MK 50 THIS IS THE THIRD NEW MFG INNER TUBE THAT HAS SPLIT ALONG CIRCUMFERENTIAL WELDED SEAMS. 1 L 7 2 3R 3 R A765 5E1 2007061500171 20070615 00171 EU 2007 6 15 2007FA0000411 1 20070515 G 3210 5321012110 BOLT PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL LANDING GEAR BROKEN B K NONE O OTHER IN INSP/MAINT 1 EA 65 624AF 1576 AM090 624 PR0499 KX227 DURING A 100 HOUR INSPECTION, A VISUAL INSPECTION FOUND A BROKEN BOLT ON THE RT MLG. THE BOLT ATTACHED THE LOWER PART OF THE SHOCK ABSORBER TO LANDING GEAR LEG. THE PN OF THE BOLT IS MOST LIKELY 532.10.12.110. THERE IS A LATER PN 532.10.12. 205 BUT THIS WAS PROBABLY NOT THE PART INSTALLED. THEIR WAS NO MARKING ON THE BOLT ITSELF MAKING IT DIFFICULT TO DETERMI NE THE PN. THIS PROBLEM WAS PREVIOUSLY ADDRESSED BY AD 04-06-05 AND SB 32-015, BUT THIS AIRCRAFT AND SN OF THE LANDING G EAR IN QUESTION ARE WELL BEYOND THE AFFECTIVITY OF BOTH THE AD AND THE SB. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007061500192 20070615 00192 EU 2007 6 15 2007FA0000412 1 20070515 G 3210 5321012110 BOLT PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL LANDING GEAR BROKEN B K NONE O OTHER IN INSP/MAINT 1 EA 65 624AF 1576 AM090 624 PR0499 KX227 DURING A 100 HOUR INSPECTION, A VISUAL INSPECTION FOUND A BROKEN BOLT ON THE RT MLG. THE BOLT ATTACHED THE LOWER PART OF THE SHOCK ABSORBER TO LANDING GEAR LEG. THE PN OF THE BOLT IS MOST LIKELY 532.10.12.110. THERE IS A LATER PN 532.10.12. 205 BUT THIS WAS PROBABLY NOT THE PART INSTALLED. THEIR WAS NO MARKING ON THE BOLT ITSELF MAKING IT DIFFICULT TO DETERMI NE THE PN. THIS PROBLEM WAS PREVIOUSLY ADDRESSED BY AD 04-06-05 AND SB 32-015, BUT THIS AIRCRAFT AND SN OF THE LANDING G EAR IN QUESTION ARE WELL BEYOND THE AFFECTIVITY OF BOTH THE AD AND THE SB. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007061500193 20070615 00193 EU 2007 6 15 2007FA0000413 1 20070515 G 3210 5321012110 BOLT PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ZONE 700 BROKEN B K NONE O OTHER IN INSP/MAINT 1 EA 65 624AF 1576 AM090 624 PR0499 KX227 DURING A 100 HOUR INSPECTION, A VISUAL INSPECTION FOUND A BROKEN BOLT ON THE RT MLG. THE BOLT ATTACHED THE LOWER PART OF THE SHOCK ABSORBER TO LANDING GEAR LEG. THE PN OF THE BOLT IS MOST LIKELY 532.10.12.110. THERE IS A LATER PN 532.10.12. 205 BUT THIS WAS PROBABLY NOT THE PART INSTALLED. THEIR WAS NO MARKING ON THE BOLT ITSELF MAKING IT DIFFICULT TO DETERMI NE THE PN. THIS PROBLEM WAS PREVIOUSLY ADDRESSED BY AD 04-06-05 AND SB 32-015, BUT THIS AIRCRAFT AND SN OF THE LANDING G EAR IN QUESTION ARE WELL BEYOND THE AFFECTIVITY OF BOTH THE AD AND THE SB. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007061500194 20070615 00194 EU 2007 6 15 2007FA0000414 1 20070515 G 3210 5321012110 BOLT PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ZONE 700 BROKEN B K NONE O OTHER IN INSP/MAINT 1 EA 65 624AF 1576 AM090 624 PR0499 KX227 DURING A 100 HOUR INSPECTION, A VISUAL INSPECTION FOUND A BROKEN BOLT ON THE RT MLG. THE BOLT ATTACHED THE LOWER PART OF THE SHOCK ABSORBER TO LANDING GEAR LEG. THE PN OF THE BOLT IS MOST LIKELY 532.10.12.110. THERE IS A LATER PN 532.10.12. 205 BUT THIS WAS PROBABLY NOT THE PART INSTALLED. THEIR WAS NO MARKING ON THE BOLT ITSELF MAKING IT DIFFICULT TO DETERM INE THE PN. THIS PROBLEM WAS PREVIOUSLY ADDRESSED BY AD 04-06-05 AND SB 32-015, BUT THIS AIRCRAFT AND SN OF THE LANDING GEAR IN QUESTION ARE WELL BEYOND THE AFFECTIVITY OF BOTH THE AD AND THE SB. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007053000002 20070530 00002 EA 2007 5 30 2007FA0000416 2 20070415 G 7322 103103 CARBURETOR AMTR VAN HATZVAN 0561383 GL LYC O235 O235C1 41505 EA SNSNCH 76AM M76AM EA ENGINE CONTAMINATED C E ENGINE SHUTDOWN Y J ENGINE STOPPAGE WARNING INDICATION AP APPROACH 1 GL 15 899P 313 335915 12242 DURING INSPECTION OF THE CARBURETOR, DISCOVERED FLAKES OF WHAT APPEARS TO BE METAL IN THE GASCOLATOR SCREEN. ALSO, OBSE RVED SOME SPECS OF RED MATERIAL ABOUT THE SIZE OF PEPPER. WHEN WE PULLED THE CARB APART WE OBSERVED A LINE ON THE BOTTOM OF THE BOWL WHERE SEDIMENT HAD PREVIOUSLY SETTLED IN THE BOWL. HOWEVER, NOTHING SIGNIFICANT WAS NOTED IN THE BOWL DURIN G OUR INSPECTION. FURTHER INSPECTION REVEALED THAT ONCE THE NEEDLE VALVE WAS SEATED BY LIGHTLY PRESSING THE FLOAT UPWAR D, IT WOULD THEN REMAIN SEATED EVEN IF AIR WAS BLOWN IN THE FUEL INLET PORT. HOWEVER, IF THE FLOAT WAS MANIPULATED UP A ND DOWN A FEW TIMES, THE NEEDLE VALVE WOULD THEN NOTICEABLY POP FREE. AND ALTHOUGH NO OBVIOUS DEBRIS WAS NOTED UPON DISA 1 H 7 1 3O 3 O EXPA1H71 E223 5 N 1P210 2007061500195 20070615 00195 CE 2007 6 15 2007FA0000417 1 20070511 G 5711 SPAR BBAVIA 11 11AC 0191102 CE LYC O235 O235* 41505 EA SNSNCH 76AK M76AK EA LT WING DELAMINATED G O OTHER O OTHER NR NOT REPORTED 1 GL 09 3581E 11AC1813 108715 11544 DELAMINATION OCCURRING AT LT FRONT WING SPAR / STRUT LOCATION. CRACK AT BOTTOM EDGE, AT WING ROOT FITTING. POSSIBLE AG E OF SPAR CAUSING DELAMINATION. LONGITUDINAL CRACK AT WING ROOT POSSIBLE EARLIER DAMAGE. REPLACED WITH NEW WOOD SPAR P /N 5146L. 1 H 7 1 3O 3 O A761 E223 5 N 1P210 2007061300214 20070613 00214 CE 2007 6 13 2007FA0000419 1 20070410 G 7810 02R3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 09 13510 365 WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE.THE EXHAUST DUCT SB 3380 HAD BEEN COMPLIED WITH 365 HOURS PRIOR.POWER SECTION WAS REMOVED FOR REPAIR. 1 L 7 2 4T 4 T A24CE E4EA 2007061300205 20070613 00205 SO 2007 6 13 2007FA0000420 1 20070510 G 2571 352020035201 BATTERY BOX PIPER PA28 PA28181 7102807 SO BROKEN B LC1R K NONE O OTHER IN INSP/MAINT 1 EA 07 6151H 287890211 PLASTIC BATTERY BOX BROKE INTO SEVERAL PIECES. LID WOULD NO LONGER HOLD SECURLY ON THE BOX ALLOWING BATTERY TO BE UNSECU RED IN THE AIRCRAFT. PIPER REPIORTED THAT P/N 35201-00 LID AND 35202-00 WAS NO LONGER AVAILABLE. INSTALLED STC'D BATTERY BOX TO REPLACE THE DAMAGED ONE. 1 L 7 1 3O 2A13 2007061500197 20070615 00197 CE 2007 6 15 2007FA0000425 1 20070515 G 5511 0432001466 RIB CESSNA 150 150E 2071812 CE CONT O200 O200A 17020 SO HORIZONTAL STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 01 2586J 8600 15061086 DURING LT LEADING EDGE SKIN REPLACEMENT OF HORIZONTAL STABILIZER DUE TO BIRD STRIKE FOUND BOTH IB LEADING EDGE RIBS PN 0 432001-46/ -6 CRACKED THROUGH UPPER AND LOWER MOUNTING TABS. WORKING RIVETS WERE FOUND AT THE TABS AND 2 RIVETS OB ON FO RWARD SPAR. BIRD STRIKE DID NOT CAUSE CRACKS. THESE TABS ARE DIFFICULT TO INSPECT WITHOUT DISASSEMBLY OF TAIL. ANY EVIDE NCE OF DEFECTS IN THE TAIL STRUCTURE SHOULD BE INVESTIGATED THOROUGHLY AS THEY ARE PRONE TO CRACKING AND WEAR. 1 H 7 1 3O 3 O 3A19 E252 2007061500198 20070615 00198 CE 2007 6 15 2007FA0000426 1 20070515 G 5511 0432001466 RIB CESSNA 150 150E 2071812 CE CONT O200 O200A 17020 SO HORIZONTAL STAB CRACKED D O OTHER O OTHER NR NOT REPORTED 1 CE 01 2586J 8600 15061086 DURING LT LEADING EDGE SKIN REPLACEMENT OF HORIZONTAL STABILIZER DUE TO BIRD STRIKE FOUND BOTH IB LEADING EDGE RIBS PN 0 432001-46/ -6 CRACKED THROUGH UPPER AND LOWER MOUNTING TABS. WORKING RIVETS WERE FOUND AT THE TABS AND 2 RIVETS OB ON FO RWARD SPAR. BIRDSTRIKE DID NOT CAUSE CRACKS. THESE TABS ARE DIFFICULT TO INSPECT WITHOUT DISASSEMBLY OF TAIL. ANY EVIDEN CE OF DEFECTS IN THE TAIL STRUCTURE SHOULD BE INVESTIGATED THOROUGHLY AS THEY ARE PRONE TO CRACKING AND WEAR. 1 H 7 1 3O 3 O 3A19 E252 2007061500199 20070615 00199 CE 2007 6 15 2007FA0000427 1 20070515 G 5511 0432001466 RIB CESSNA 150 150E 2071812 CE CONT O200 O200A 17020 SO HORIZONTAL STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 01 2586J 8600 15061086 DURING LT LEADING EDGE SKIN REPLACEMENT OF HORIZONTAL STABILIZER DUE TO BIRDSTRIKE FOUND BOTH IB LEADING EDGE RIBS PN 04 32001-46/ -6 CRACKED THROUGH UPPER AND LOWER MOUNTING TABS. WORKING RIVETS WERE FOUND AT THE TABS AND 2 RIVETS OB ON FOR WARD SPAR. BIRDSTRIKE DID NOT CAUSE CRACKS. THESE TABS ARE DIFFICULT TO INSPECT WITHOUT DISASSEMBLY OF TAIL. ANY EVIDENC E OF DEFECTS IN THE TAIL STRUCTURE SHOULD BE INVESTIGATED THOROUGHLY AS THEY ARE PRONE TO CRACKING AND WEAR. 1 H 7 1 3O 3 O 3A19 E252 2007061500200 20070615 00200 CE 2007 6 15 2007FA0000428 1 20070515 G 5511 0432001466 RIB CESSNA 150 150E 2071812 CE CONT O200 O200A 17020 SO HORIZONTAL STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 01 2586J 8600 15061086 DURING LT LEADING EDGE SKIN REPLACEMENT OF HORIZONTAL STABILIZER DUE TO BIRDSTRIKE FOUND BOTH IB LEADING EDGE RIBS PN 04 32001-46/ -6 CRACKED THROUGH UPPER AND LOWER MOUNTING TABS. WORKING RIVETS WERE FOUND AT THE TABS AND 2 RIVETS OB ON FOR WARD SPAR. BIRDSTRIKE DID NOT CAUSE CRACKS. THESE TABS ARE DIFFICULT TO INSPECT WITHOUT DISASSEMBLY OF TAIL. ANY EVIDENC E OF DEFECTS IN THE TAIL STRUCTURE SHOULD BE INVESTIGATED THOROUGHLY AS THEY ARE PRONE TO CRACKING AND WEAR. 1 H 7 1 3O 3 O 3A19 E252 2007061500202 20070615 00202 CE 2007 6 15 2007FA0000429 1 20070515 G 7820 E477001 MUFFLER CESSNA 150 150E 2071812 CE CONT O200 O200A 17020 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 01 2586J 3128 15061086 PILOT REPORTED FATIGUE WHILE FLYING. NO OBVIOUS EXTERNAL SIGNS OF MUFFLER FAILURE WERE FOUND, SHROUD REMOVAL REVEALED A TIGHT CRACK FROM NR 2 RISER INTO BODY, 3 INCHES LONG THAT LEFT VERY LITTLE STAINING ON INSIDE OF SHROUD. MUFFLER BODY WA S DEFORMED WHERE RISER IS WELDED INTO BODY, NEW MUFFLER HAD NO DEFORMATION IN THIS AREA. 1 H 7 1 3O 3 O 3A19 E252 2007061500201 20070615 00201 CE 2007 6 15 2007FA0000434 1 20070515 G 7820 E477001 MUFFLER CESSNA 150 150E 2071812 CE CONT O200 O200A 17020 SO ENGINE CRACKED E O OTHER O OTHER NR NOT REPORTED 1 CE 01 2586J 3128 15061086 PILOT REPORTED FATIGUE WHILE FLYING. NO OBVIOUS EXTERNAL SIGNS OF MUFFLER FAILURE WERE FOUND, SHROUD REMOVAL REVEALED A TIGHT CRACK FROM NR 2 RISER INTO BODY, 3 INCHES LONG THAT LT VERY LITTLE STAINING ON INSIDE OF SHROUD. MUFFLER BODY WAS DEFORMED WHERE RISER IS WELDED INTO BODY, NEW MUFFLER HAD NO DEFORMATION IN THIS AREA. 1 H 7 1 3O 3 O 3A19 E252 2007061300225 20070613 00225 CE 2007 6 13 2007FA0000435 1 20070209 G 7810 02R3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 09 13502 422 WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE. EXHAUST DUCT SB HAD BEEN COMPLIED WITH 422 HOURS PRIOR. POWER SECTION WAS REMOVED FOR REPAIR. 1 L 7 2 4T 4 T A24CE E4EA 2007053000005 20070530 00005 SO 2007 5 30 2007FA0000436 2 20070410 G 8530 649169 CYLINDER CONT O520 IO520* 17032 SO ENGINE CRACKED C O OTHER O OTHER NR NOT REPORTED 1 SW 17 PARTIAL HEAD AND BARREL SEPARATION. LARGE CRACK STARTING AT THE FUEL INJECTOR PORT RUNNING INTO THE CYLINDER HEAD COMBUS TION CHAMBER, THROUGH THE INTAKE SEAT BOSS AND CONTINUING AROUND TO THE LOWER SPARK PLUG BOSS. 3 O E5CE 2007061500204 20070615 00204 EU 2007 6 15 2007FA0000437 1 20070522 G 5330 SKIN ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE73131G 29003 NE FUSELAGE CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 23 600NY 231 FOUND SEVERE PITTING CORROSION ON BOTH THE LT AND RT SIDES BETWEEN FRAME STATIONS 184 AND 194 BELOW EMERGENCY ESCAPE DOO RS. THIS IS DUE TO WATER LEAKING AROUND THE EMERGENCY ESCAPE DOORS AND SOAKING THE SOUND DAMPENING INSULATION. THE PIT TING WAS SO BAD IT CORRODED THROUGH THE SKIN ON THE RT SIDE. THIS CORROSION WAS FOUND DURING AN RVSM INSTALLATION WHILE WE WERE MARKING OUT THE CRITICAL REGION AROUND THE STATIC PORTS. REPAIRED THE DAMAGE FOLLOWING APPROVED DATA FROM A ST RUCTURAL ENGINEER AND RETURNED TO SERVICE IAW FAA FORM 8110-3. 2 M 7 2 4F 4 F A2SW E6WE 2007061500205 20070615 00205 GL 2007 6 15 2007FA0000443 3 20070525 G 6110 ROD CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER FAILED B O OTHER O OTHER NR NOT REPORTED 1 CE 09 001922 RECEIVED PROPELLER FOR OVERHAUL. DURING PREFUNCTION TEST FOUND BLADE NR 1 WAS NOT LINKED TO THE PITCH CHANGE ROD. AFTER DISASSEMBLY OF PROPELLER FOUND NR 1 BLADE ACTUATING PIN PN B5072-1 DISCONNECTED FROM BLADE. ACTUATING PIN ATTACHMENT SCR EWS WERE SAFETIED AND HAD ANTISABOTAGE ON THE SCREW HEADS. THE THREADS HAD BEEN PULLED OUT OF THE BLADE. THERE WAS NO OB VIOUS SIGNS OF SUDDEN STOPPAGE OR A STRIKE. ALL BLADES SHOWED SIMILAR EROSION FROM ROCK DAMAGE. BLADE TRACK WAS .0625 IN CH PLUS OR MINUS AND DIAMETER WAS 106 INCHES.IAW THE RECORD, THIS WAS THE FIRST OVERHAUL EVENT. MANUFACTURE HAS REQUESTE D BLADE, ACTUATING PIN AND LINK BE RETURNED TO THEM FOR EVALUATION. 1 H 7 1 3T NT A37CE 5 C P60GL 2007061800104 20070618 00104 2007 6 18 2007FA0000444 2 20070421 G 8500 12501 ENGINE MALFUNCTIONED C O OTHER O OTHER NR NOT REPORTED 1 SW 03 620TS 20 AIRCRAFT ECU WARNING LIGHT COME ON FREQUENTLY. WE SPOKE WITH THIELERT ABOUT THE PROBLEM AND THEY SAY THAT DURING STEEP BANKS OR YAW THE FUEL PRESSURE CAN BE DIFFERENT BETWEEN THE RAILS ON EACH ENGINE. THE ECU CAN INTERPRET THIS AS A PROBL EM AND TURN ON THE ANNUNCIATOR. THIS IS MOSTLY A NUISANCE BECAUSE EVERYTIME THE AN ANNUNCIATOR TURNS ON WE MUST BRING T HE AIRCRAFT TO A MECHANIC WHO MUST CLEAR THE PROBLEM FORM THE COMMPUTER. WHILE THE ANNUNCIATOR IS ON WE HAVE NO WAY OF KNOWING IF A REAL PROBLEM DEVELOPS BECAUSE THE ANNUCIATOR IS STILL ON. IN ADDITION AS A FLIGHT SCHOOL IT COSTS US SIGNIF ICANT AMOUNTS OF LOST REVENUE EVERY TIME THAT WE MUST TAKE THE AIRPLANE OFF-LINE UNTIL OUR MECHANICE CAN INSPECT IT. O 2007060100116 20070601 00116 EU 2007 6 1 2007FA0000447 1 20070508 G 2150 5700700A HOSE SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B NE A/C SYSTEM BURST D K NONE K J FLUID LOSS WARNING INDICATION IN INSP/MAINT 1 EA 01 849BP 3554 22310 HIGH PRESSURE AIR CONDITIONER HOSE BURST. 1 G 7 1 3U 3 U H9EU E00054EN 2007053000016 20070530 00016 EA 2007 5 30 2007FA0000450 2 20070328 G 8530 LW19279 CYLINDER CESSNA 206 206H 2073301 CE LYC O540 TIO540AJ1A EA ENGINE SCRATCHED B O OTHER O OTHER NR NOT REPORTED 1 WP 28 1023 1023 T20608350 172S08719 SET OF 6 CYLINDERS CAME IN WITH 2 BROKEN CONTROL RINGS. CYLINDERS HAD RING STEPS ON TOP AND BOTTOM OF CYLINDER BARRELS. CORROSION WAS PRESENT IN BARRELS FROM THE MIDDLE UP TO THE HEAD OF THE CYLINDERS. EXHAUST GUIDES WERE FAR OUT OF LIMITS AND DIFFICULT TO REMOVE RESULTING IN HAVING TO OVERSIZE 3 BOSSES TO P05 GUIDES AND THE OTHER 3 TO P10. 2 EXHAUST SEATS F ELL OUT DURING THE HEAT SOAK FOR INSTALLING THE EXHAUST GUIDES. BROKEN RINGS DAMAGED 2 PISTONS WHICH HAD TO BE REMOVED F ROM SERVICE. 4 OTHER PISTONS WERE DAMAGED IN THE PISTON PIN BOSSES. THE BROKEN RINGS ALSO CAUSED MODERATE SCRATCHING TO THE BARREL OF THE CYLINDERS WHICH WAS REMOVABLE BY POWER HONING. 2 CYLINDERS HAD TO BE OVERSIZED FROM THE CORROSION AND 1 H 7 1 3O 3 O RT A4CE E14EA 2007061300167 20070613 00167 EA 2007 6 13 2007FA0000451 2 20070328 G 8530 LW19279 CYLINDER CESSNA 206 206H 2073301 CE LYC O540 TIO540AJ1A EA ENGINE SCRATCHED B O OTHER O OTHER NR NOT REPORTED 1 WP 07 1023 1023 T20608350 172S08719 SET OF 6 CYLINDERS CAME IN WITH 2 BROKEN CONTROL RINGS. CYLINDERS HAD RING STEPS ON TOP AND BOTTOM OF CYLINDER BARRELS. CORROSION WAS PRESENT IN BARRELS FROM THE MIDDLE UP TO THE HEAD OF THE CYLINDERS. EXHAUST GUIDES WERE FAR OUT OF LIMITS AND DIFFICULT TO REMOVE RESULTING IN HAVING TO OVERSIZE 3 BOSSES TO P05 GUIDES AND THE OTHER 3 TO P10. 2 EXHAUST SEATS F ELL OUT DURING THE HEAT SOAK FOR INSTALLING THE EXHAUST GUIDES. BROKEN RINGS DAMAGED 2 PISTONS WHICH HAD TO BE REMOVED F ROM SERVICE. 4 OTHER PISTONS WERE DAMAGED IN THE PISTON PIN BOSSES. THE BROKEN RINGS ALSO CAUSED MODERATE SCRATCHING TO THE BARREL OF THE CYLINDERS WHICH WAS REMOVABLE BY POWER HONING. 2 CYLINDERS HAD TO BE OVERSIZED FROM THE CORROSION AND 1 H 7 1 3O 3 O RT A4CE E14EA 2007060700007 20070607 00007 SO 2007 6 7 2007FA0000453 1 20070407 G 5610 1159SCB31023 WINDSHIELD GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU COCKPIT FAILED B JUOR O OTHER O OTHER NR NOT REPORTED 1 WP 27 495RS 2735 1161 CREW REPORTS WINDSHIELD FAILURE DURING PART 91 MAINTENANCE POSITIONING FLIGHT. EMERGENCY DECLARED WITH UNEVENTFUL LANDI NG. AIRCRAFT CONTINUED TO DESTINATION AIRPORT UNDER CDL RESTRICTIONS. UNKNOWN CAUSE. (K) 2 L 7 2 4F 4 F RT A12EA E25NE 2007060100107 20070601 00107 SO 2007 6 1 2007FA0000454 2 20070501 G 7414 BRUSHES CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO MAGNETO WORN B YYBR O OTHER O OTHER NR NOT REPORTED 1 GL 03 154WF 423 1638 360136 THIS MAGNETO WAS MISFIRING, AND APPEARS TO HAVE CAUSED DETONATION IN THE NR 5 CYLINDER. PISTON MATERIAL WAS FOUND IN TH E OIL FILTER AND OIL COOLER. ENGINE HAD TO BE REMOVED, INSPECTED, AND REPAIRED DUE TO THE DETONATION. THE MAGNETO WAS FOUND TO HAVE A SEVERELY WORN BRUSH (K3215), THE BRUSH BLOCK WAS MELTED (K3823), THE COIL WAS BURNED CLOSE TO THE BRUSH CONTACT POINT (K3975), AND THE POINTS WERE BADLY BURNED (M3081). THIS IS THE (3RD) OCCURRENCE FOUND WITH THIS SAME PROB LEM. (K) 1 L 7 1 3O 3 O NT A00009CH E1CE 2007060100112 20070601 00112 CE 2007 6 1 2007FA0000455 1 20070505 G 3230 08940002 GEARBOX CESSNA 340 340A 2076405 CE CONT O520 TSIO520* 17040 SO MLG DAMAGED B O OTHER O OTHER NR NOT REPORTED 1 SW 17 2745F 340A0949 GEAR MOTOR, REDUCTION GEAR BOX AND GEAR TRANSMISSION WERE REMOVED AND SENT OUT TO FOR INSPECTION. WHEN THEY OPENED GEAR REDUCTION BOX, THEY DISCOVERED THAT ONE OF THE MOUNTING BOLTS HAVE BEEN OF THE IMPROPER LENGTH CAUSING THE THREAD PATTE RN. TBOLT SHOWS SLIGHT WEAR WHERE IT TOUCHED THE GEAR SYSTEM. ACCORDING TO MFG THERE WAS ONLY A SLIGHT TRANSFER TO GEA R, WHICH THEY FEEL WOULD NOT HAVE CAUSED A PROBLEM. CANNOT DETERMINE HOW LONG THIS CONDITION EXISTED. THE BOLTS LOOK T O BE OLD AND THE INTERNAL GEAR BOX SEEMS ALSO TO BE OLD. THE INSTALLATION CALLED FOR A .8750 INCH BOLT FOR THIS MOUNTIN G HOLE, AND REMOVED A 1 INCH BOLT. THE CORRECTIVE ACTION IS TO INSTALL THE REPAIRED GEAR BOX AND THE CORRECT MOUNTING H 1 L 7 2 3O 3 O 3A25 E8CE 2007060700031 20070607 00031 GL 2007 6 7 2007FA0000456 3 20070516 G 6110 B24573 FORK BNORM BN2 BN2 1520202 EU HARTZL HCC2Y HCC2YK2 GL PITCH CHANGE UNSERVICEABLE B ME4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 AU9949B STEEL FATIGUE CRACK NDT (MAGNETIC PARTICLE) DETECTED. PROPELLER ASSY RECEIVED FOR STANDARD OVERHAUL AND DEFECT FOUND IN PROPELLER ASSY (PN C2K00500, DESCRIPTION HC-C2YK-2CUF/FC8477A-4, SN AU9949B), UNDER WO NR 38425A. 1 H 7 2 3O A17EU 5 C P920 2007060700009 20070607 00009 GL 2007 6 7 2007FA0000457 3 20070516 G 6111 F8468A6R BLADE PZLWAR WILGA PZL104W35A 7360104 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC3Y HCC3YR GL PROPELLER CRACKED B ME4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 424HD 00030015 DY2965A ALUMINUM FATIGUE CRACK VISUALLY AND NDT DETECTED. PROPELLER ASSY RECEIVED FOR OVERHAUL AND BLADE NR 2 OF 3 REMOVED FROM PROPELLER ASSY (HC-C3YR-1RF/ F8468A-6R, UNDER WO NR 38598A. NOTE: MANDATORY OVERHAUL REQUIRED DUE TO GROUND STRIKE, HO WEVER, BLADE SUBMITTED WAS NOT BENT AND LEAST DAMAGED. (K) 1 H 7 1 3R 3 O NC EXPA1H71 1E4 5 C P25EA 2007060100113 20070601 00113 WP 2007 6 1 2007FA0000458 2 20070502 G 7321 307080026 FUEL CONTROL AMD FALC90 FALCON900B 2730171 EU GARRTT TFE731 TFE7315BR WP ENGINE FAULTY C O OTHER O OTHER NR NOT REPORTED 1 EA 03 4MB 5476 1861 146 P101199 PILOTS REPORTED THAT ENGINE THAT THIS FUEL CONTROL UNIT WAS INSTALLED ON COULD NOT BE CONTROLLED BY NORMAL COMPUTER MODE , AND THAT WHEN THEY WENT TO MANUAL MODE THAT THEY COULD NOT CONTROL ENGINE SPEED FUNCTIONS EITHER. IT SEEMS THAT THIS FUEL CONTROL HAS SOME INTERNAL FAULT. REPLACEMENT FUEL CONTROL RESOLVED THIS PROBLEM. (K) 2 L 7 3 4F 4 F RT E6WE 2007060600001 20070606 00001 CE 2007 6 6 2007FA0000459 1 20070404 G 2720 04140161532 BRACKET CESSNA 172 172F 2072414 CE CONT O300 O300* 17022 SO RUDDER CONTROL BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 09 8879U 2961 17252796 DURING ANNUAL INSPECTION BRACKET (PN 04140616-1-532). FOUND BROKEN AND CRACKED IN OTHER LOCATIONS. LOCATED UNDER FLOOR CENTER SECTION AT FLIGHT CONTROL BELL CRACK. REPLACED WITH NEW PART. REQUEST INSPECTORS CHECK THIS AREA OF THE FLIGHT CONTROLS CAREFULLY DURING 100/ANNUAL INSPECTION. (K) 1 H 7 1 3O 3 O NT 3A12 E253 2007060100115 20070601 00115 CE 2007 6 1 2007FA0000460 1 20070430 G 3297 D3899924WD19 CONNECTOR RAYTHN 390 390 7150030 CE WILINT FJ44 FJ44 66000 GL ANTI SKID SYS FAULTY B E81R O OTHER O OTHER NR NOT REPORTED 1 GL 03 972PF 976 RB38 TROUBLESHOT INTERMITTENT ANTI-SKID SYSTEM FAIL ANNUNCIATION, CABIN DOOR SEAL STAYING INFLATED ON GROUND, AND LIFT DUMP H ANDLE OPERATION. FOUND BAD CRIMP ON PIN (L) FOR WIRE G117B24 IN LT MLG SQUAT SWITCH CONNECTOR. FUNCTIONAL CHECKS OK. (K) 1 L 7 2 3F 4 F RT A00010WI E3GL 2007060100114 20070601 00114 SO 2007 6 1 2007FA0000461 2 20070309 G 7414 1051324 SPRING CONT BEECH 58 58 1152740 CE CONT O550 IO550C SO MAGNETO BROKEN E MKWA O OTHER O OTHER NR NOT REPORTED 1 GL 03 7293R 827 F02CA139R TH590 824323R WHILE TROUBLESHOOTING ENGINE RUNS ROUGH AND WON’T RUN AT ALL OVER 1200 RPM. WE DISCOVERED THE IMPULSE COUPLING SPRINGS ON BOTH MAGS WERE BROKEN. (IMPULSE COUPLING , PN 10-400309) (K) 1 L 7 2 3O 3 O 3A16 E3SO 2007060700033 20070607 00033 SO 2007 6 7 2007FA0000462 2 20070309 G 7414 1051324 SPRING CONT BEECH 58 58 1152740 CE CONT O550 IO550C SO MAGNETO BROKEN D O OTHER O OTHER NR NOT REPORTED 1 GL 03 7293R 827 F02CA164R TH590 824323 WHILE TROUBLESHOOTING ENGINE RUNS ROUGH AND WON`T RUN AT ALL OVER 1200 RPM. WE DISCOVERED THE IMPULSE COUPLING SPRINGS ON BOTH MAGS WERE BROKEN. (IMPULSE COUPLING PN 10400309) (K) 1 L 7 2 3O 3 O 3A16 E3SO 2007060600002 20070606 00002 CE 2007 6 6 2007FA0000463 1 20070514 G 5711 SPAR BBAVIA 11 11BC 0191106 CE LYC O235 O235* 41505 EA SNSNCH 76AK M76AK EA LT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 09 3581E 11AC1813 108715 11544 DELAMINATION OCCURRING AT WING STRUT ATTACH LOCATION. CRACK AT BOTTOM EDGE AT ROOT FITTING. POSSIBLE AGE OF SPAR CAUSI NG DELAMINATION. LONGITUDINAL CRACK AT WING ROOT POSSIBLE EARLIER DAMAGE REPLACE WITH NEW WOOD SPAR (PN 5146L). (K) 1 H 7 1 3O 3 O A761 E223 5 N 1P210 2007061500103 20070615 00103 2007 6 15 2007FA0000464 1 20070430 G 6100 BOLT LYC O360 O360* 41514 EA MCAULY 1A200 1A200* GL PROPELLER SHORT D O OTHER W INADEQUATE Q C NR NOT REPORTED 1 AL 05 866MM 400 YI46003 INSPECTING PROPELLER DURING ANNUAL, FOUND PROPELLER BOLTS 0.25 IN SHORT OF BACK SIDE OF FLANGE INSERTS. ALL BOLT THREAD ENGAGEMENT WAS FORWARD OF INSERT BOSS. AFT .2500 INC OF INSERT, MATERIAL BEHIND CRANK FLANGE, HAD NO THREAD ENGAGEMENT . WRONG BOLTS INSTALLED, CORRECTED BY INSTALLING PROP BOLT KIT (PN 76EM8) WHICH PROVIDED (2) THREADS THROUGH INSERT WHE N TROQUED. (K) 3 O E286 5 N P874 2007060700014 20070607 00014 EU 2007 6 7 2007FA0000465 1 20070509 G 3411 PITOT LINE AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE731* 01518 WP NR 2 LOOSE B EBVR O OTHER O OTHER NR NOT REPORTED 1 CE 09 160FJ 160 WHILE TROUBLESHOOTING A LEAK IN NR 2 STATIC SYSTEM, THE RT SIDE STATIC PLATE HAD TO BE TAKEN LOOSE. UPON REMOVAL OF THE PLATE, SILICONE RTV WAS FOUND ON THE FITTING FOR THE NR 1 STATIC SYSTE. WHEN THE FITTING WAS LOOSENED, FOUND A LAGRE A OUNT OF TEFLON PIPE TAPE WRAPPED AROUND THE NIPPLE OF THE STATIC PLATE, AND THE FLARE OF THE ALUMINUM HARD LINE GOING TO THE STATIC PLATE WAS BROKEN OFF AND LAYING LOOSE IN THE ASSY. A TECH IN THE PAST HAD POSSIBLY EXPERIENCED A LEAK ON TH IS SYSEM, AND LOADED THE NIPPLE WITH TEFLON TAPE AND RTV TTO GET THE SYSTEM TO SEAL, INSTAD OF REPAIRING THE HARD LINE. THESE LINES SHOULD BE REPAIRED IAW STANDARD PRACTICE TO PREVENT PREMATURE FAILURE. (K) 2 L 7 2 4F 4 F A33EU E6WE 2007060500272 20070605 00272 CE 2007 6 5 2007FA0000466 1 20070201 G 3310 LIGHT CESSNA 340 340A 2076405 CE CONT O520 TSIO520* 17040 SO COMPASS FIRE D O OTHER O OTHER NR NOT REPORTED 1 CE 03 340JH 340A0771 COMPASS LIGHT/SOCKET OVERHEATED DURING TAXI AND CAUGHT FIRE BEFORE THE CIRCUIT BREAKER TRIPPED. PILOT EXTINGUISHED FIRE WITH HANDKERCHIEF. CAUSE UNKNOWN, NO DAMAGE TO AIRCRAFT INTERIOR OR STRUCTURE. (K) 1 L 7 2 3O 3 O 3A25 E8CE 2007060700035 20070607 00035 CE 2007 6 7 2007FA0000467 1 20070316 G 5532 SKIN BEECH 1900 1900D 1154162 CE PWA PT6 PT6A6 52043 EA VERTICAL STAB DAMAGED B E81R O OTHER O OTHER NR NOT REPORTED 1 GL 03 135YV UE135 VERTICAL STABILIZER LEADING EDGE SKIN ATTACH RIVETS WORKING. FOUND THAT THE ORIGINAL UNIVERSAL HEAD RIVETS WERE REPLACE D WITH FLUSH RIVETS. THE SKIN WAS COUNTERSUNK TO ACCOMMODATE THE RIVETS, HOWEVER THE SKIN WAS TOO THIN TO COUNTERSINK A ND EVENTUALLY WORKED LOOSE. SKIN WAS REPAIRED IAW DER ENGINEERING REPORT AND CORRECT RIVETS INSTALLED. STRICT ADHERENC E TO PUBLISHED DATA WOULD HAVE PREVENTED DAMAGE. (K) 2 L 7 2 4T 3 T RT A24CE E4EA 2007060700034 20070607 00034 EU 2007 6 7 2007FA0000468 1 20070501 G 5610 D25W343001009 WINDSHIELD ISRAEL 1125 ASTRASPX 4500205 EU COCKPIT CRACKED B UO2R O OTHER O OTHER NR NOT REPORTED 1 GL 19 411MM 080 THE WINDSHIELD ON THE PILOT`S SIDE CRACKED DURING FLIGHT AT F/L 41,000 FT ON 4/24/2007. THE WINDSHIELD HAD 3104.6 TT. (K) 2 L 7 2 4F RT A16NM 2007060700026 20070607 00026 CE 2007 6 7 2007FA0000469 1 20070227 G 3220 C611300518 LINK BEECH 90 F90 1152909 CE NLG DAMAGED B E81R O OTHER O OTHER NR NOT REPORTED 1 GL 03 189JR LA61 THIS REPORT IS A RESULT OF REPLACEMENT OF THE FORWARD NOSE GEAR RETRACT CHAIN. TO REPLACE OR TO REINSTALL THIS CHAIN, A NEW PN C-6113005-18, CONNECTING LINK MUST BE USED. A NEW LINK SHOULD HAVE FIVE PIECES. ONE LINK ASSY WITH (2) SHAFTS SWAGED INTO AN END PLATE, TWO CENTER PLATES THAT SHOULD SLIP ONTO THE SHAFTS, ONE END PLATE, AND ONE SPRING CLIP RETAINE R. THE END PLATE SHOULD HAVE SMALLER HOLES IN IT AND REQUIRE PRESSING FOR PROPER ASSY. THIS PRESSED FIT REQUIRES DISTR UCTION OF THE LINK DURING ASSY. WHEN INSTALLING THE NEW CHAIN AND INSTALLING THE NEW LINK, FOUND THAT ALL THREE PLATES HAD THE HOLE SIZE THAT WOULD ALLOW THEM TO BE SLIPPED ONTO THE SHAFTS WITHOUT PRESSING. CHECKED ANOTHER NEW LINK ASSY. 1 L 7 2 4T A31CE 2007060500273 20070605 00273 CE 2007 6 5 2007FA0000470 1 20070226 G 2170 1013840245 EVAPORATOR BEECH 200 B200 1152922 CE AIR CONDITIONER UNSERVICEABLE D E81R O OTHER O OTHER NR NOT REPORTED 1 GL 03 AFT CABIN AIR CONDITIONER EVAPORATOR RECEIVED FROM VENDER IN OVERHAULED CONDITION. INITIAL INSPECTION REVEALED HARD LIN E. WHICH SHOULD RUN PARALLEL TO HEAT EXCHANGER, WAS INSTALLED APPROXIMATELY 25 DEGREES TO HEAT EXCHANGER. THE EVAPORAT OR COULD NOT HAVE BEEN INSTALLED WITHOUT STRESSING AIRCRAFT HARD LINES. THIS LINE HAD BEEN REPAIRED (BY WELDING?) HOWEV ER, THE INSIDE SURFACE STILL SHOWED SEVERE PITTING. THE UNIT WAS RETURNED TO VENDER AS WELL AS VENDER SHOULD HAVE CAUGH T THESE DEFECTS. (K) 1 L 7 2 4T A24CE 2007060700032 20070607 00032 SW 2007 6 7 2007FA0000471 1 20070404 G 3213 12984 LOCK NUT BBAVIA 7 7ECA 21101NN SW LYC O290 O290* 41506 EA MLG LEG STRIPPED G O OTHER O OTHER NR NOT REPORTED 1 NM 13 6096F 1642 7ECA352 LOCK NUT THREADS FAILED, MLG STRUT EXTENDED ON TAKEOFF ALLOWING MLG TO SWING FREE. DURING LANDING, MLG WAS UNDER FUSELA GE CAUSING DAMAGE TO LOWER LONGERONS, CONDITION OF THREADS CANNOT BE DETERMINED WITHOUT DISASSEMBLING THE MLG STRUT ASSY . THEREFORE, THE THREADS MAY DETERIORATE SIGNIFICANTLY WITHOUT DETECTION. SUGGEST SPECIAL EMPHASIS INSPECTION ROUTINE AT (5) YEAR INTERVALS TO INCLUDE DISASSEMBLY OF MLG STRUT ASSY. (K) 1 H 7 1 3O 3 O A759 E229 2007060400015 20070604 00015 2007 6 4 2007FA0000472 2 20070510 G 7322 105018 BOWL CARBURETOR DAMAGED B NE2R O OTHER O OTHER NR NOT REPORTED 1 CE 07 A44695 RECEIVED CARBURETOR FROM CUSTOMER WITH THE REQUEST (PLEASE INSPECT UNIT FOR PROPER OPERATION, AIRCRAFT ON GROUND. HAVE BEEN BOMBARDED WITH SERIOUS PROBLEMS TO JUST ABOUT EVERY CARBURETOR WE HAVE) PILOT STATED THAT HE ALMOST CRASHED HELICOP TER DUE TO LACK OF ENGINE RESPONSIVENESS AFTER ROLLING THROTTLE IN AFTER TEST AUTO ROTATION. INSPECTION OF CARBURETOR R EVEALED VENT PORTS IN BOWL AND THROTTLE BODY WERE NOT IN THE NORMAL POSITION NOR THE NORMAL SIDE FOR THIS CARBURETOR MOD EL. COULD NOT POSITIVELY IDENTIFY THE IDLE TUBE AND NOZZLE AS OEM PARTS. THE ACCELERATOR PUMP DISCHARGE CHECK VALVE DI D NOT FUNCTION IN THE MANNER NORMALLY SEEN BY THIS REPAIR STATION. THROTTLE BODY HAS ECONOMIZER JET INSTALLED WHICH IS 2007060600003 20070606 00003 EU 2007 6 6 2007FA0000473 1 20070511 G 6210 1090103019 BLADE AGUSTA A109 A109 0260109 EU ALLSN 250C 250C20B 03013 GL MAIN ROTOR CRACKED D O OTHER E VIBRATION/BUFFET LD LANDING 1 NM 01 109CJ 2031 7280 SKIN CRACKS WERE DISCOVERED IN THIS BLADE UPON INVESTIGATION OF AN UNUSUALLY HIGH VIBRATION LEVEL AS REPORTED BY THE PIL OT. THE ONE-PER-REV VERTICAL VIBRATION WAS ESPECIALLY NOTICEABLE DURING THE LANDING PHASE OF FLIGHT. INSPECTION OF THI S BLADE REVEALED CORD-WISE CRACKS IN THE TOP AND BOTTOM SKINS WHICH EXTEND FROM THE TRAILING EDGE AT STA 3135 TO THE AFT EDGE OF THE SPAR AT STA 3123. THE CRACKS THEN EXTEND SPAN-WISE FROM STA 2940 TO STA 3225. THE CRACK IN THE LOWER SKIN BISECTS A SKIN REPAIR AT STA 3130, APPROXIMATELY 2 INCHES FORWARD OF THE TRAILING EDGE. THIS REPAIR WAS ACCOMPLISHED W ITH AD 2000-15-20 AND BT 109-111 UNDER WO NR 8-080132-84, DATED 4/24/2006. BT 109-50, PART I REQUIRES DAILY VISUAL INSP 1 G 7 2 3U 3 U H7EU E4CE 2007060600004 20070606 00004 NE 2007 6 6 2007FA0000474 2 20070507 G 7420 IGNITION LEAD CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE LT ENGINE OUT OF POSITION B O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 EA 25 228PC 5600310 WHILE DEPARTING, ENCOUNTERED A 75 PERCENT THROTTLE SPLIT WITH THE LEFT ENGINE ACHIEVING ONLY 93 PERCENT N1. A MFG PHAS E B INSPECTION WAS PERFORMED ON THE AIRCRAFT ON 5/5/2007. WHILE PERFORMING THE PHASE B INSPECTION ITEM B742001, TASK 74 -31-00-210 (ENGINE IGNITERS OPERATIONAL TEST), IT WAS DETERMINED THAT THE RT IGNITER LEAD ON THE LT ENGINE WAS RE-INSTAL LED IN A POSITION THAT AFFECTED THE THROTTLE LINKAGE AND PREVENTED FULL TRAVEL OF THROTTLE LEVER IN THE FLIGHT DECK. FU RTHER INVESTIGATION REVEALED THAT THERE IS NO REFERENCE OR PRECAUTIONS IN THE MM AS TO THE RE-INSTALLATION POSITION OF T HE LEAD UPON REMOVAL AND RE-INSTALLATION OF THE IGNITER PLUG. INSTALLING THE IGNITER LEAD END TO THE IGNITER WITH A 90 2 L 7 2 4F 4 F RT A22CE E25EA 2007060700003 20070607 00003 EU 2007 6 7 2007FA0000475 1 20070430 G 2520 4311935 HOUSING AMD FALC50 FALCON900 2730160 EU GARRTT TFE731 TFE731* 01518 WP SEAT ROLLER MISMANUFACTURED B UO2R O OTHER W INADEQUATE Q C NR NOT REPORTED 1 GL 19 678CH 47 (8) SEATS, MODEL 5004 (SINGLE) WERE PURCHASED. THE SEATS HAVE (3 FT) ON EACH CORNER (12 TOTAL) THAT ARE TO FIT INTO THE SEAT RAIL. SAID PURCHASED SEATS DID NOT FIT INTO THE EXISTING MFG SEAT RAIL. MFG WAS CONTACTED. IT WAS DETERMINED BY THE MFG THAT THE (3 FEET) BY THE MFG THAT THE (3 FEET) ON EACH CORNER (12 TOTAL) WERE BEING MFG INCORRECTLY. THE SEATS ARE DESIGNED TO FIT INTO (2 TRACKS). THE FRONT 3 AND BACK 3 FEET ON THE LT SIDE OF THE CHAIR ARE PART OF A (ROLLER HOU SING). EACH CHAIR HAS (2) ROLLER HOUSINGS. MFG IS PROVIDING 16 REPLACEMENT ROLLER HOUSINGS (PN 431193-5). (K) 2 L 7 3 4F 4 F RT A46EU E6WE 2007061300166 20070613 00166 GL 2007 6 13 2007FA0000476 1 20070504 G 7160 BA24 AIR FILTER CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO HARTZL HCJ3Y PHCJ3YF1 GL ENGINE INTAKE DEBONDED B K NONE O OTHER IN INSP/MAINT 1 EA 17 711KW 1348 917594 FP3492B APPEARS THAT THE FOAM AIR FILTER ELEMENT, THAT IS CYLINDER SHAPED AND BONDED TOGETHER, DID NOT HAVE SUFFICIENT GLUEUU OR CAME UNBONDED AND WAS ALLOWING UNFILTERED AIR TO ENTER THE ENGINE INTAKE. 1 L 7 1 3O 3 O NT A00009CH E3SO 5 C P36EA 2007061300168 20070613 00168 GL 2007 6 13 2007FA0000477 1 20070507 G 2720 BUNGEE CIRRUS SR SR22 2130001 GL RUDDER MISRIGGED B K NONE O OTHER IN INSP/MAINT 1 EA 07 519SR 2072 DURING INSPECTION FOUND RUDDER AILERON INTERCONNECT BUNGEE MISRIGGED AND INTERTFERING WITH THE AILERON CONTROLS. THERE I S NO EVIDENCE THAT THIS AIRCRAFT HAS HAD ANY MAINTENANCE TO THIS SYSTEM SINCE LEAVING THE FACTORY. ANOTHER AIRCRAFT WITH THIS CONDITION HAD THE CONTROL SYSTEM JAM WITH FULL OPPOSITE RUDDER AND AILERON. IT APPEARS THAT THIS CONDITION IS CAUS ED BY IMPROPER RIGGING OF THE INTERCONNECT SYSTEM AT THE FACTORY. 1 L 7 1 3O NT A00009CH 2007061300204 20070613 00204 EA 2007 6 13 2007FA0000478 2 20070510 G 8530 LW12987 CYLINDER LYC O540 IO540* 41532 EA ENGINE ERODED B O OTHER O OTHER NR NOT REPORTED 1 SW 17 AFTER REMOVAL OF THE CYLINDER BARREL FROM THE CYLINDER HEAD, SEVER ERROSION WAS NOTED JUST ABOVE THE SEAL BAND AREA. IF THE BARREL HAD NOT BEEN REMOVED, THIS ERROSION WOULD HAVE BEEN UNDETECTED AND WOULD HAVE CAUSED A HEAD AND BARREL SEPERA TION. 3 O 1E4 2007061800105 20070618 00105 CE 2007 6 18 2007FA0000479 1 20070516 G 2510 04101342 SEAT CESSNA 150 150F 2071814 CE CONT E185 E185* 17014 SO COCKPIT CRACKED D O OTHER O OTHER NR NOT REPORTED 1 CE 01 8095S 15061695 SEAT PAN WAS FOUND CRACKED AT THE FORWARD END OF PILOTS OB SEAT RAIL STIFFENER, APPROXIMATELY 1 NR LONG ACROSS SCREW HOL ES. STIFFENER PN 0411546-1 WAS ALSO CRACKED AT CUTOUT FOR FUEL LINE. TOTAL AIRFRAME TIME UNKNOWN, BUT GREATER THAN 1300 HOURS. THESE CRACKS ARE SOMEWHAT COMMON ON 3000 TO 5000 HOUR AIRPLANES. 1 H 7 1 3O 3 O 3A19 E246 2007061500224 20070615 00224 SO 2007 6 15 2007FA0000480 1 20070523 G 5711 6707003 SPAR CAP PIPER PA28 PA28140 7102802 SO LYC O320 O320* 41508 EA RT WING CORRODED G K NONE O OTHER IN INSP/MAINT 1 SO 15 4579R 3465 2821321 FUEL TANK REMOVED DUE TO LEAKING VENT LINES. UPON REMOVAL, DISCOVERED RT WING UPPER SPAR CAP SEVERLY CORRODED. MAJOR EXF OLIATION TO THE SPAR CAP AT THE OB SECTION OF THE FUEL TANK OPENING. 1 L 7 1 3O 3 O 2A13 E274 2007061800106 20070618 00106 CE 2007 6 18 2007FA0000481 1 20070523 G 5311 051212497 SPAR CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL FUSELAGE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SW 15 5145U 14529 100 172RG0258 L2767336A 961976 FOUND SMOKING RIVETS ON TOP OF FUSELAGE IN AREA OF THE REAR CENTER SECTION SPAR. REMOVED RIVETS (APPROX. EIGHT ON EACH END OF SPAR) AND FOUND RIVET HOLES SEVERELY ELONGATED. FACTORY ORIGINAL RIVETS WERE .1250 INCH DIA. AND SEVERAL HAD BEE N REPLACED IN THE FIELD WITH .1562 INCH RIVETS. ALL OF THE AFFECTED RIVET HOLES HAD BECOME OVERSIZED TO AN EXTENT THAT RENDERED THE SPAR AND OVERLAPPING FUSELAGE SKINS UNSERVICEABLE. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2007061500213 20070615 00213 SO 2007 6 15 2007FA0000482 1 20070523 G 5711 6205401 SPAR PIPER PA28 PA28R180 7102809 SO RT WING CORRODED G K NONE O OTHER IN INSP/MAINT 1 SO 15 3208R 14400 28R3113 RT WING REMOVED DUE TO DAMAGE. WING WAS SCRAPPED AND DEALER WANTED STEEL FITTINGS REMOVED. UPON REMOVAL OF REAR SPAR ATT ACH PLATE, SEVERE CORROSION WAS FOUND ON THE SPAR UNDER THE PLATE. CONDITION WAS VERY SERIOUS AND COULD HAVE LEAD TO AN INFLIGHT FAILURE. 1 L 7 1 3O 2A13 2007061500214 20070615 00214 CE 2007 6 15 2007FA0000483 1 20070525 G 2400 UNKNOWN BEECH 35 K35 1151524 CE CONT O470 IO470N 17026 SO MCAULY 2A36C 2A36C23 GL UNKNOWN C H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC CR CRUISE 1 CE 07 6061E D5996 096827R 7710181 LOST ELECTRICAL POWER. 1 L 7 1 3O 3 O 3A15 3E1 5 C P880 2007061500216 20070615 00216 EA 2007 6 15 2007FA0000484 2 20070525 G 7322 MA45 CARBURETOR PIPER PA24 PA24 7102402 SO LYC O360 O360* 41514 EA ENGINE WORN D E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 EA 23 7204P 748 748 242374 THE ACCELERATOR PUMP IN THE CARBURETOR FAILED. INSPECTION SHOWED THAT THE PUMP HEAD GLAND HAD SHRUNK, SO THAT IT DID NO T PROVIDE A SEAL BETWEEN THE CARBURETOR BODY AND THE PUMP ITSELF. THE RESULT WAS THAT ADVANCING THE THROTTLE DID NOT CA USE FUEL TO BE SQUIRTED FROM THE PUMP EXIT ORIFICE. REPLACEMENT OF THE PUMP RESOLVED THE PROBLEM. 1 L 7 1 3O 3 O 1A15 E286 2007061500210 20070615 00210 EU 2007 6 15 2007FA0000486 1 20070530 G 2752 1391T1008 ACTUATOR ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE731* 01518 WP FLAP MISALIGNED B K NONE O OTHER IN INSP/MAINT 1 CE 09 27TZ 213 INSTALLED REBUILT FLAP ACTUATOR IN RT OB POSITION; PN 1391T100-8, SN 387AB. FLAP OPERATION WAS NORMAL. WHILE CHECKING AILERON TRAVELS IT WAS DISCOVERED THAT AILERON TRAVELS WERE LIMITED BY THE REBUILT FLAP ACTUATOR. A COVER PLATE ON THE FLAP ACTUATOR HAD BEEN INDEXED INCORRECTLY AND WAS INTERFERING WITH THE AILERON BELLCRANK. PROBABLE CAUSE WAS INCORRECT ASSEMBLY OF FLAP ACTUATOR. 2 M 7 2 4F 4 F A2SW E6WE 2007061500211 20070615 00211 EU 2007 6 15 2007FA0000487 1 20070530 G 2752 1391T1008 ACTUATOR ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE731* 01518 WP FLAP MISALIGNED B K NONE O OTHER IN INSP/MAINT 1 CE 09 27TZ 213 INSTALLED REBUILT FLAP ACTUATOR IN RT OB POSITION; PN 1391T100-8, SN 387AB. FLAP OPERATION WAS NORMAL. WHILE CHECKING AILERON TRAVELS IT WAS DISCOVERED THAT AILERON TRAVELS WERE LIMITED BY THE REBUILT FLAP ACTUATOR. A COVER PLATE ON THE FLAP ACTUATOR HAD BEEN INDEXED INCORRECTLY AND WAS INTERFERING WITH THE AILERON BELLCRANK. PROBABLE CAUSE WAS INCORRECT ASSEMBLY OF FLAP ACTUATOR. 2 M 7 2 4F 4 F A2SW E6WE 2007061800108 20070618 00108 2007 6 18 2007FA0000489 2 20070530 G 7414 CAPACITOR MAGNETO FAILED C O OTHER O OTHER NR NOT REPORTED 1 SW 15 IN READING AN ALERT FROM APRIL 2007 REFERRING TO SLICK MAGNETO CAPACITOR FAILURE PN M-3984 STATES THAT OIL/DIELECTRIC FL UID LEAKED FROM THE CAPACITOR. THAT IS A DRY CAPACITOR AND CONTAINS NO FLUID. HAVE CUT OPEN SEVERAL FOR TRAINING AIDS A ND NO LIQUID EXISTS IN THAT PART. 2007061500218 20070615 00218 SO 2007 6 15 2007FA0000490 2 20070525 G 8520 IO240A CRANKSHAFT CONT O240 IO240B 17063 SO ENGINE CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 17 CRANKSHAFT HAD A VERY LARGE, DEEP FORGING LAP ON THE NR 3 CRANK CHEEK. AN EFFORT WAS MADE TO REMOVE THE LAP BY LOCALIZE D GRINDING BUT THE IT WAS TOO DEEP TO REMOVE. CRANKSHAFT WAS DETERMINED UNAIRWORTHY BY ENGINEERING. 3 O E7SO 2007061500221 20070615 00221 2007 6 15 2007FA0000491 4 20070429 G 2215 065001790100 SERVO CESSNA 182 182S 2072701 CE LYC O540 IO540* 41532 EA AILEONS BINDING D O OTHER F FLT CONT AFFECTED AP APPROACH 1 SW 09 9875F 1056 18280141 PILOT/OWNER REPORTED TO MX THAT ON APPROACH AFTER DISENGAGING AUTOPILOT, AILERONS WERE DIFFICULT TO MOVE. NO WINDS AND S TABLE APPROACH MINIMIZED PROBLEM. MX NOTED AILERONS WERE EXTREMELY DIFFICULT TO MOVE, AND FURTHER MOVEMENT COULD HAVE CA USED EVEN GREATER DIFFICULTY OR COMPLETE IMMOBILIZATION OF THE AILERONS. AILERON SERVO WAS REMOVED AND SENT OUT FOR EXCH ANGE. IT WAS NOTED ON REMOVAL THE OUTPUT SHAFT SUPPORT BEARING WAS LOOSE AND BINDING. 1 H 7 1 3O 3 O NT 3A13 1E4 2007061500222 20070615 00222 CE 2007 6 15 2007FA0000492 1 20070531 G 5753 07620382 BELLCRANK CESSNA 182 182S 2072701 CE LYC O540 IO540* 41532 EA TE FLAPS BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 09 9875F 1056 18280141 DURING ANNUAL INSPECTION, IT WAS NOTED THAT THE (BELLCRANK ASSY) ON THE FLAP FEEDBACK LEVER, BEHIND THE INSTRUMENT PANEL , WAS BROKEN IN TWO, IT CONSIST OF A PLASTIC BLOCK WITH A SLOT IN IT WHICH MOVES THE MICROSWITCH ASSY TO ACTIVATE, OR DE ACTIVATE THE FLAP DRIVE MOTOR. THE BLOCK IS ATTACHED WITH 2 RIVETS OF SOME TYPE. THE END OF THE BLOCK IS CRACKED COMPLET ELY THROUGH ALLOWING SEPARATION OF THE UPPER AND LOWER HALVES. THIS ALSO STRESSED THE ATTACHING RIVETS CAUSING CRACKS, A ND EXCESSIVE MOVEMENT. (PICS ARE AVAILABLE) IF PART COMPLETELY FAILED IT COULD ALLOW COMPLETE UNCOMMANDED FLAP DEPLOYM ENT OR INABILITY TO RETRACT FLAPS, SUCH AS A BALKED LANDING. 1 H 7 1 3O 3 O NT 3A13 1E4 2007061500223 20070615 00223 2007 6 15 2007FA0000493 2 20070530 G 7414 M3984 CAPACITOR MAGNETO NONE C O OTHER O OTHER NR NOT REPORTED 1 SW 15 IN READING AN ALERT FROM APRIL 2007 REFERING TO SLICK MAGNETO CAPACITOR FAILURE PART NR M-3984 STATES THAT OIL/DIELECTR IC FLUID LEAKED FROM THE CAPACITOR. THAT IS A DRY CAPACITOR AND CONTAINS NO FLUID. I HAVE CUT OPEN SEVERAL FOR TRAININ G AIDS AND NO LIQUID EXSISTS IN THAT PART. 2007061800211 20070618 00211 2007 6 18 2007FA0000494 4 20070604 G 2216 6565001197 CABLE CESSNA 500 550 2076604 CE AUTOPILOT FRAYED B K NONE O OTHER IN INSP/MAINT 1 SW 01 4614N 7737 300 5500659 WE HAVE FOUND THE ELEVATOR CABLE AT THIS SERVO P/N 4006719-904 SHOWING EXCESSIVE WEAR ON AIRCRAFT UNDERGOING PHASE 1-4 A ND ALSO PHASE 5 INSPECTIONS. THE CABLE WAS FOUND WHERE IT PASSES THROUGH AT FS. 428.50 AND IS DIFFICULT TO SEE. THIS CAB LE HAD APROX. 3 STRANDS TO GO TO TOTAL FALURE. THE IPC REFERENCE FOR THE CABLE IS 22-10-00, FIGURE 1, PAGE 3, ITEM 85 1 L 7 2 4F A22CE 2007061800222 20070618 00222 NM 2007 6 18 2007FA0000495 1 20070606 G 3060 SMR2263 HEATER HARTZL LANCAR LC40 LC40550FG 5150000 NM CONT O550 TSIO550C SO PROP BLADES DEBONDED D K NONE O OTHER IN INSP/MAINT 1 SW 07 1439C 226 LX197B 41618 914411 INBOARD PORTION OF ALL THREE PROP DEICE BOOTS DEBONDED AGAIN. ON THIS PROP, NEW BLADES WERE SENT FROM HARTZELL DUE TO D EBOND OF PREVIOUS BOOTS AT 28.4 HRS TT AND AGAIN AT 28.9 HRS TT. RETAINER STRAP AND BOOT DEBONDS DUE TO CENTRIFUGAL FOR CE PULLING DEICE BOOT LEAD ON EACH PROP BLADE. THIS HAS HAPPENED ON FIVE OR MORE LANCAIR COLUMBIA AIRCRAFT. THE SEALIN G PROCESS FOR THE RETAINER STRAP IS LACKING. SMR TECHNOLOGIES AND HARTZELL NEED A BETTER STRAP OR A GOOD TY-RAP. 1 L 7 1 3O 3 O RT A00003SA E5SO 2007061800224 20070618 00224 SO 2007 6 18 2007FA0000496 2 20070530 G 8500 STUD CONT O520 TSIO520* 17040 SO ENGINE CASE CHAFED D O OTHER O OTHER NR NOT REPORTED 1 SW 99 532343 DURING BUILD UP OF A NEW ENGINE FOR INSTALLATION, IT IS ROUTINE FOR US TO R&R THE OIL COOLER TO INSTALL THE GASKET WITH SEALANT AND TO INSPECT THE ADAPTER PLATE MOUNTING STUD HEIGHT. ON THIS PARTICULAR ENGINE, ALL OF THE STUDS WERE INSTALL ED TOO HIGH, SO THAT THEY PROTRUDED ABOVE THE GASKET MOUNTING SURFACE. TWO OF THEM HAD MADE IMPRESSIONS IN THE COOLER S EALING SURFACE. 3 O E8CE 2007061800265 20070618 00265 SO 2007 6 18 2007FA0000497 2 20070607 G 8530 EC646144CN CYLINDER CESSNA 210 210C 2073412 CE CONT O470 IO470S 17026 SO ENGING DAMAGED G A UNSCHED LANDING A FLAME/FIRE CL CLIMB 1 WP 21 3622Y 501 21058122 CS1024292S CYLINDER HEAD DETACHED FROM CYLINDER BARREL CAUSING INJECTOR FUEL LINE TO RUPTURE. A INFLIGHT FIRE OCCURED CAUSING DAMA GE TO WIREING, MAG.,AND OTHE ENGINE COMPONENTS. 1 H 7 1 3O 3 O 3A21 3E1 2007061800266 20070618 00266 CE 2007 6 18 2007FA0000498 1 20070527 G 5610 WINDSHIELD CESSNA 421 421C 2076016 CE COCKPIT BROKEN G B EMER. DESCENT D INFLIGHT SEPARATION CR CRUISE 1 SO 15 237SM 421C0237 MAJOR PORTION OF RT WINDSHIELD SEPARATED FROM AIRCRAFT. 1 L 7 2 3O A7CE 2007061800267 20070618 00267 EA 2007 6 18 2007FA0000501 2 20070607 G 8520 LW13683 MAIN BEARING PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA ENGINE DELAMINATED B K NONE O OTHER IN INSP/MAINT 1 SW 99 1100 318052122 L110868A CUSTOMER FOUND METAL IN FILTER DURING ROUTINE MAINTENANCE. TOOK ENG. APART AND FOUND 2 CENTER MAIN BRGS. WHERE DELAMINAT ED. 1 L 7 2 3O 3 O A20SO E14EA 2007062700015 20070627 00015 NM 2007 6 27 2007FA0000503 1 20070618 G 6510 A04111 BEARING ROBSIN R22 R22BETA 7640110 NM LYC O320 O320* 41508 EA DRIVESHAFT ROUGH B O OTHER O OTHER NR NOT REPORTED 1 NM 09 461H 161 1460 PILOT REPORTS GRINDING NOISE FROM TAIL ROTOR DRIVESHAFT. REMOVED DRIVESHAFT ASSY AND DISCOVERED ROUGH A041-11 DAMPER BEA RING. REPLACED BEARING ASSY. CLOSER EXAMINATION SHOWED PAINT USED DURING DRIVESHAFT ASSEMBLY ON LIP OF SEAL. OVER TIME THIS DAMAGED THE LIP OF THE SEAL AND ALLOWED GREASE TO PURGE FROM BEARING. THIS IS THE SECOND OCCURRENCE OF THIS IN THE PAST 12 MONTHS. MFG NOTIFIED EACH TIME. SUGGEST BETTER QC DURING DRIVESHAFT BUILD UP AT MFG. 1 G 7 1 3O 3 O H10WE E274 2007071100021 20070711 00021 CE 2007 7 11 2007FA0000505 1 20070504 G 5340 24130023 ATTACH FITTING CESSNA 172 172RG 2072438 CE LYC O360 O360* 41514 EA MCAULY 2D34C B2D34C220 GL NLG ACTUATOR CRACKED B BGSR K NONE O OTHER IN INSP/MAINT 1 EA 21 169EC 1345 172RG0515 L2843836A 804955 L/W SEB 93-8 ON NOSE GEAR ACTUATOR ATTACH FITTING AND SOUND CRACK ON LT, LOWER, IB BOLT HOLE OF FITTING. ALSO, BOLT HOL ES IN LOWER SKIN WERE IN EXCESS OF .030. REPLACED ATTACH FITTING, LOWER SKIN AND DOUBLER IAW SK 172-142 AND SK 172-159. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2007071100022 20070711 00022 CE 2007 7 11 2007FA0000506 1 20070517 G 5753 95160000XX SKIN BEECH 60 B60 1153605 CE LYC O541 TIO541* 41536 EA LT TE FLAP CRACKED B HSRR K NONE O OTHER IN INSP/MAINT 1 NM 06 837RJ 5859 P355 BOTH FLAPS CRACKED AT ACTUATOR ATTACH POINT. LT FLAP SKIN AND RIB CRACKED. RT FLAP RIB CRACKED. RIGGING WAS OK, PROBA BLY AN OPERATOR INDUCED PROBLEM. BELIEVE THE FLAPS HAVE BEEN LOWERED AT TOO HIGH AN AIRSPEED. (K) 1 L 7 2 3O 3 O A12CE E10EA 2007071100029 20070711 00029 CE 2007 7 11 2007FA0000507 1 20070515 G 2130 AN8186D NUT BEECH BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE TUBE LOOSE B E81R O OTHER O OTHER NR NOT REPORTED 1 GL 03 132QS RK427 CREW REPORTED PRESSURIZATION CONTROL INEFFECTIVE, CABIN RATE CLIMBING AND DESCENDING, WHILE DESCENDING IN AUTOMATIC MODE . STABILIZED BRIEFLY WHILE IN MANUAL MODE. TROUBLESHOT IAW FIM 21-30-00, EXCESSIVE LEAK RATE NOTED AT TEST PORT 2. FO UND LOOSE (B) NUT ON CONTROL LINE TUBE ASSY. AT TEE FITTING FOR MANUAL CONTROL VALVE. CORRECTED LOOSE FITTING AND SYST EM TESTS OK. RESTORED AC TO NORMAL CONFIGURATION, PRESSURIZATION SYSTEM TESTS SATISFACTORY ON GROUND RUN-UP. UNKNOWN I F PREVIOUS MAINTENANCE PERFORMED IN THIS AREA. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007062700007 20070627 00007 WP 2007 6 27 2007FA0000510 1 20070618 G 6520 269A6029 LOCK NUT HUGHES 269 269C 4470504 WP LYC O360 HIO360* 41514 EA T/R GEARBOX BACKED OUT B C ABORTED TAKEOFF O OTHER TX TAXI/GRND HDL 1 NM 09 27YS 1573 DURING GROUND RUNUP, PILOT NOTICED TAIL ROTOR NOT SPINNING. AIRCRAFT SHUTDOWN AND RETURNED TO HANGER. UPON DISASSEMBLY I T WAS NOTED THAT THE NUT PN 269A6029 THAT ATTACHES THE DRIVE COUPLING TO THE GEARBOX HAD BACKED OUT COMPLETELY AND WORN A HOLE THROUGH THE ALUMINUM BUMPER PN 269A5712 THAT IS INSIDE THE TAIL ROTOR DRIVESHAFT. THREADS INSIDE THE TAIL ROTOR G EARBOX INPUT SHAFT PN 269A5626-5 WERE ALSO DAMAGED. PARTS WERE FORWARDED TO MFG FOR EVALUATION. 1 G 7 1 3O 3 O 4H12 1E10 2007071100062 20070711 00062 CE 2007 7 11 2007FA0000511 1 20070530 G 5730 552275563 PANEL CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE WING DELAMINATED B H00R K NONE O OTHER IN INSP/MAINT 1 EA 21 100DS 4430 5500639 DURING COMPLETION OF MFG PROGRAM PHASE 5 INSPECTION, NOTICEABLE DEPRESSION WAS OBSERVED IN UPPER SURFACE OF LT AND RT WI NG SKINS IN AREA OF MLG UPLOCK HOOK ASSY ATTACHMENT. DURING COMPLETION OF LANDING GEAR OPERATIONAL CHECK, IT WAS NOTED THAT DEPRESSION AREA SIZE GREW WHILE MLG WAS IN UP AND LOCKED POSITION. USING THE COIN TAP TEST METHOD CONFORMATION WAS MADE THAT BOTH BONDED PANELS WERE DELAMINATED. IAW TECH SUPPORT, NO DELAMINATION IS ALLOWED ON THESE PANELS. OPTIONS AVAILABLE FOR REMEDY WERE REMOVED AND REPLACED, POSSIBLE REPAIR DEFINITION AND ASSOC 8110FORM, OR POSSIBLE TEMPORARY REP AIR WITH FLIGHT EXTENSION. (K) 1 L 7 2 4F 4 F A22CE E1NE 2007071100063 20070711 00063 CE 2007 7 11 2007FA0000512 1 20070530 G 5730 552277564 PANEL CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE LT WING DELAMINATED B H00R K NONE O OTHER IN INSP/MAINT 1 EA 21 100DS 4430 5500639 DURING COMPLETION OF MFG PROGRAM PHASE 5 INSPECTION, NOTICEABLE DEPRESSION WAS OBSERVED IN UPPER SURFACE OF LT AND RT WI NG SKINS IN AREA OF MLG UPLOCK HOOK ASSY ATTACHMENT. DURING COMPLETION OF LANDING GEAR OPERATIONAL CHECK, IT WAS NOTED THAT DEPRESSION ARE SIZE GREW WHILE MLG WAS IN UP AND LOCKED POSITION. USING THE COIN TAP TEST METHOD. CONFORMATION WA S MADE THAT BOTH BONDED PANELS WERE DELAMINATED. IAW TECH SUPPORT, NO DELAMINATION IS ALLOWED ON THESE PANELS. OPTIONS AVAILABLE FOR REMEDY WERE REMOVED AND REPLACED, POSSIBLE REPAIR DEFINITION AND ASSOC 8110 FORM, OR POSSIBLE TEMPORARY R EPAIR WITH FLIGHT EXTENSION. (K) 1 L 7 2 4F 4 F A22CE E1NE 2007062500003 20070625 00003 2007 6 25 2007FA0000513 4 20070608 G 2562 E0109 CONNECTOR ACK E01ELT PIPER PA16 PA16 7101602 SO ELT MISSING D K NONE O OTHER IN INSP/MAINT 1 SO 25 5834H 1277 87 021767 16453 DURING 100 HOUR INSPECTION IT WAS NOTED THAT THE BNC CONNECTOR ATTACHED TO THE ELT PORTABLE ANTENNA WAS MISSING. AN IN-D EPTH SEARCH OF THE AIRCRAFT BELLY FAILED TO TURN UP THE CONNECTOR. THE CONNECTOR IS ATTACHED TO THE PORTABLE COLLAPSIBLE ANTENNA BY A 6-32 SCREW IN THE BOTTOM OF THE ANTENNA. THERE IS NO PROVISION TO LOCK THIS THREADED ATTACHMENT. 1 H 7 1 3O 1A1 2007062500006 20070625 00006 GL 2007 6 25 2007FA0000516 1 20070612 G 5753 13431004 HINGE CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO HARTZL HCJ3Y PHCJ3YF1 GL FLAP CORRODED G K NONE O OTHER IN INSP/MAINT 1 SW 13 122GH 543 0175 FLAP HINGE ASSEMBLY HAS INTERGRANULAR CORROSION ON THE FORWARD EDGE OF THE HINGE JUST BELOW THE BOTTOM WING SKIN ABOVE T HE HINGE FAIRING. 1 L 7 1 3O 3 O NT A00009CH E3SO 5 C P36EA 2007062500007 20070625 00007 GL 2007 6 25 2007FA0000517 1 20070612 G 5753 13432002 HINGE CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO HARTZL HCJ3Y PHCJ3YF1 GL FLAP CORRODED G K NONE O OTHER IN INSP/MAINT 1 NE 03 122GH 543 0175 FLAP HINGE ASSEMBLY HAS INTERGRANULAR CORROSION ON THE FORWARD EDGE OF THE HINGE JUST BELOW THE BOTTOM WING SKIN ABOVE T HE HINGE FAIRING. 1 L 7 1 3O 3 O NT A00009CH E3SO 5 C P36EA 2007062500025 20070625 00025 SO 2007 6 25 2007FA0000524 2 20070511 G 8500 ENGINE BEECH 36 A36 1151604 CE CONT O550 IO550* SO RIGHT FAILED G B A EMER. DESCENT UNSCHED LANDING J Y T WARNING INDICATION ENGINE STOPPAGE ENGINE CASE PENETRATION CR CRUISE 1 SO 11 814JG 14 E2622 675591 ON MAY 11, 2007 AT APPROXIMATELY 1815 EST, 2205Z, A BEECH BE-36-A36 BONANZA, N814JG, S/N E-2622, AT CRUISE HAD A DECREAS E IN ENGINE CYLINDER TEMPERATURE, FOLLOWED BY A LOSS OF OIL PRESSURE AND ENGINE POWER WITH SUBSEQUENT ENGINE FAILURE. TH E AIRCRAFT MADE AN EMERGENCY LANDING. PILOT WALKED AWAY FROM THE AIRCRAFT WITH NO INJURIES. A VISUAL INSPECTION OF THE A IRCRAFT REVEALED A HOLE IN THE UPPER RIGHT HAND ENGINE COWLING APPROXIMATELY 3 INCHES IN DIAMETER WHICH WAS LIMITED TO S HEET METAL DAMAGE. UPON INSPECTION OF THE ENGINE COMPARTMENT THE FORWARD UPPER CASE OF THE ENGINE WAS HEAVILY DAMAGED RE VEALING SEVERAL DAMAGED PISTONS, PISTON CONNECTING RODS BROKEN AND NR 6 CONNECTING ROD MISSING, ALONG WITH SEVERAL CRANK 1 L 7 1 3O 3 O 3A15 E3SO 2007062500027 20070625 00027 EA 2007 6 25 2007FA0000525 2 20070615 G 7414 M3548 ROTOR SLICK 4370 PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA MAGNETO SHEARED C O OTHER O OTHER NR NOT REPORTED 1 CE 01 335 335 06052245 RIGHT MAGNETO ROTOR SHEARED DIRECTLY UNDER THE MAGNETO CAM. SECOND IDENTICAL FAILURE IN 335 HRS ON THE AIRCRAFT. AIRCR AFT DYNAMIC PROP BALANCE WAS CHECKED AFTER THIS FAILURE AND CHECKED EXCELLENT. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2007062500028 20070625 00028 SO 2007 6 25 2007FA0000526 1 20070615 G 2420 TERMINAL CHRYSLER PIPER PA28 PA28180 7102808 SO LYC O360 O360A4A 41514 EA SNSNCH 76E 76EM8S5 EA ALTERNATOR LOOSE C O OTHER O OTHER NR NOT REPORTED 1 CE 01 F082472 217 HOURS AFTER OVERHAUL, THE OUTPUT TERMINAL BECAME LOOSE IN THE BUSS STRAP INSIDE THE ALTERNATOR, CAUSING COMPLETE FA ILURE. LIKELY THIS FIT (NORMALLY A PRESS FIT) WAS NOT AS TIGHT AS IT NEEDED TO BE WHEN THIS UNIT LEFT KELLY. 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA 2007071100061 20070711 00061 GL 2007 7 11 2007FA0000530 1 20070622 G 3222 11907005 STRUT CIRRUS SR SR20 05628AJ GL CONT O550 IO550N 17042 SO NLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 07 961CD 623 1610 NOSE LANDING GEAR STRUT HAS A CRACK AT THE TOP. THE STRUT COMES UP TO A Y FOR MOUNT. AT THE YOKE OF THE Y IS A WELDED RE INFORCEMENT, AND THE CRACK IS AT THE TOP WHERE THIS REINFORCEMENT MEETS THE LEGS OF THE Y ON BOTH SIDES. 1 L 7 1 3O 3 O NT A00009CH E3SO 2007062700020 20070627 00020 EU 2007 6 27 2007FA0000531 1 20070615 G 2750 9450202205 FLEX DRIVE PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TE FLAPS BROKEN B O OTHER O OTHER DE DESCENT 1 EA 65 591AF 2329 591 PR0454 KX164 DURING APPROACH WHEN THE FLAPS WERE SELECTED TO 15 DEGREES THE FLAPS FAILED TO EXTEND AND A FLAP CAUTION ANNUNCITOR WAS DISPLAYED ON THE CAWS PANEL. THE FLIGHT CREW FOLLOWED THE APPROPRIATE POH PROCEDURES AND LANDED UNEVENTFULLY. INVESTIGAT ION INTO THE FLAP PROBLEM AFTER THE AIRCRAFT LANDED DETERMINED THAT THE LT IB FLAP FLEX DRIVE PN 945.02.02.205, SN S2532 , HAD BROKEN JUST IB OF THE LT IB FLAP ACTUATOR. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007071100023 20070711 00023 2007 7 11 2007FA0000532 1 20070620 G 3220 608200185 TORQUE KNEE BEECH T34 NLG MISMANUFACTURED B O OTHER O OTHER NR NOT REPORTED 1 CE 09 GL210 PURCHASED BRAND NEW PART. DURING ASSEMBLY IT WAS FOUND THAT THE TORQUE ARM PIN LUGS ARE OF DIFFERENT THICKNESSES. THEY ARE SUPPOSED TO BE THE SAME. THIS DEFECT CAUSED THE HOLES IN THE HOUSING AND THE TORQUE PIN TO NOT ALIGN. 2007071100059 20070711 00059 GL 2007 7 11 2007FA0000533 1 20070622 G 3222 11907004 STRUT CIRRUS SR SR20 05628AJ GL CONT IO360 IO360* 17025 CE NLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 07 217JH 562 1320 NOSE LANDING GEAR STRUT HAS A CRACK AT THE TOP. THE STRUT COMES UP TO A Y FOR MOUNT. AT THE YOKE OF THE Y IS A WELDED RE INFORCEMENT, AND THE CRACK IS AT THE TOP WHERE THIS REINFORCEMENT MEETS THE LEGS OF THE Y. 1 L 7 1 3O 3 O NT A00009CH E1CE 2007062700019 20070627 00019 CE 2007 6 27 2007FA0000534 1 20070619 G 3246 D30257 HUB CESSNA 206 U206F 2073333 CE WHEEL FAILED C O OTHER O OTHER NR NOT REPORTED 1 AL 03 1191V D30 U20602506 WHEEL-BROKE AT CENTER, CASTING FAILED AT BOLT HOLES-8:00X6 TIRES AND TUBES 190-200" NRS AT CAP SCREWS INSTALLED 7-23-03 TACH 1709 CURRENT TACH 2052. 1 H 7 1 3O A4CE 2007071100073 20070711 00073 EU 2007 7 11 2007FA0000535 2 20070501 G 7314 AN9113D NIPPLE NANCNG CJ6A CJ6A 056183N WP VEDENY M14P EU MUHBR MTV MTV9* EU FUEL PUMP UNKNOWN D O OTHER O OTHER NR NOT REPORTED 1 WP 07 552CY 20 4332008 KR822009 FUEL INJECTION FUEL SUPPLY FROM FUEL PUMP FITTING THAT COMES OUT OF PUMP. FIX WOULD BE CHANGE TO STEEL AND SUPPORT LINE WITH BRACKET OR CHANGE TO FIREWALL MOUNT OF FUEL PRESSURE TRANSDUCER. (K) 1 L 7 1 3R RT EXPA1L71 USSR 5 C P24NE 2007071100088 20070711 00088 CE 2007 7 11 2007FA0000536 1 20070530 G 3500 510010746 LINE CESSNA 441 441 2076020 CE CONT O520 GTSIO520* 17032 SO OVERHEAD CABIN CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 03 377CA 5341 4410289 DURING INSPECTION, HEARD A FAINT GAS LEAK IN OVERHEAD. PULLED O2 OUTLETS IN SUSPECTED AREA, AND CHECKED B-NUTS, ALL SE CURE. PULLED HEADLINER FOR A CLOSER INSPECTION. FOUND O2 LINE JUST FWD OF THE CABIN DOOR CORRODED AND LEAKING. CORR OSION ON THE LINE OCCURRED WHERE THE DUCTING PASSED UNDER IT. EVERYWHERE THIS DUCTING TOUCHED AN O2 LINE THERE WAS CO RROSION. THE LINES & FLEX DUCTING WAS REPLACED WITH NEW. (K) 1 L 7 2 3T 3 O RT A28CE E7CE 2007071100092 20070711 00092 NE 2007 7 11 2007FA0000537 2 20070531 G 7321 312064401 FCU PWA BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE LT ENGINE MALFUNCTIONED B VG4R O OTHER O OTHER NR NOT REPORTED 1 SO 15 609BG 403 234 PCEPK0709 FL468 PCEPK0709 ENGINE POWER LOSS AT ALTITUDE. ENGINE ROLLED BACK FROM 50 PERCENT. MFG TECH SUPPORT RECOMMENDS FCU REPLACEMENT. CAUSE UNKNOWN AT THIS TIME. (K) 2 L 7 2 4T 4 T RT A24CE E4EA 2007071100093 20070711 00093 CE 2007 7 11 2007FA0000538 1 20070604 G 5320 FLOOR SUPPORT CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE FS 151 CRACKED B JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 905CW 9359 5500072 CABIN FLOOR SUPPORT WEB CRACKED AND BROKEN, FUSELAGE STATION 151. FOUND CRACK DURING PHASE INSPECTION. UNABLE TO FIND PN IN MFG PARTS CATALOG. (K) 1 L 7 2 4F 4 F A22CE E1NE 2007071100094 20070711 00094 EU 2007 7 11 2007FA0000539 1 20070530 G 2752 1391T1008 ACTUATOR ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE731* 01518 WP TE FLAPS MISALIGNED D JGVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 27TZ 213 INSTALLED REBUILT FLAP ACTUATOR IN RT OB POSITION; PN 1391T1008, SN 387AB. FLAP OPERATION WAS NORMAL. WHILE CHECKING A ILERON TRAVELS IT WAS DISCOVERED THAT AILERON TRAVELS WERE LIMITED BY THE REBUILT FLAP ACTUATOR. A COVER PLATE ON THE F LAP ACTUATOR HAD BEEN INDEXED INCORRECTLY AND WAS INTERFERING WITH THE AILERON BELLCRANK. PROBABLE CAUSE; INCORRECT ASS Y OF FLAP ACTUATOR. (K) 2 M 7 2 4F 4 F A2SW E6WE 2007071100098 20070711 00098 SO 2007 7 11 2007FA0000540 1 20070625 G 7500 M1213400 RING ALIDSG GULSTM G1159 G1159A 3970109 SO RROYCE SPEY SPEY* NE PRECOOLER MISSING C O OTHER O OTHER NR NOT REPORTED 1 SW 09 2NA 309 THE COMPONENT OEM (REPORT 4-193), THE MM (CHAPTER 36-02-00), IPC (CHAPTER 36-10-00) AND THE CMP WORK CARDS (364040, 3640 45) ARE MISSING THE REQUIREMENT TO INSPECT AND INSTALL GAMMA RING (PN) M1213-400 DURING THE INSTALLATION OF THE PNEUMATI C SYSTEM PRECOOLER. FAILURE TO INSTALL THE GAMMA RING COULD CAUSE THE HIGH PRESSURE DUCT TO SEPARATE FROM THE PRECOOLER AND CAUSE SIGNIFICANT HEAT DAMAGE TO THE AIRCRAFT SKIN AND STRINGERS. 2 L 7 2 4F 4 T A12EA E2EU 2007071100082 20070711 00082 SO 2007 7 11 2007FA0000543 2 20070625 G 7322 NEEDLE VALVE CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO CARBURETOR MISSING D K NONE O OTHER IN INSP/MAINT 1 SW 99 51 AT THE END OF THE FLIGHT, PILOT REPORTED THAT THE ENGINE WOULD NOT IDLE. DURING INSPECTION OF THE CARBURETOR, MECHANIC FOUND THE MIXTURE ADJUSTMENT NEEDLE VALVE MISSING. CARBURETOR WAS REMOVED AND SENT BACK FOR REPAIR. 1 H 7 1 3O 3 O NT 3A13 E273 2007071100026 20070711 00026 EU 2007 7 11 2007FA0000547 1 20070620 G 2760 69023617 PULLEY BRACKET GLASFL H301 H301LIBELLE 3800337 EU CONT O360 TSIO360E 17025 SO SPOILER CHAFED B K NONE O OTHER IN INSP/MAINT 1 CE 09 301Q 2343 35 ROLL SPOILER CABLE PN:S3779-4P233.7M WAS ROUTED INCORRECTLY OVER LOW FRICTION PULLEY P/N:S3504-4.5 (THROUGH A TOOLING H OLE) IN PULLEY BRACKET P/N:6960236-17. THIS CAUSED AN INTERFERENCE AND WEAR IN THE PULLEY BRACKET, AND FLAT AREAS TO TH E CABLE. CABLE AND BRACKET WERE REPLACED WITH NEW. 1 K 0 0 3 O G12EU E9CE 2007071100027 20070711 00027 CE 2007 7 11 2007FA0000548 1 20070620 G 2760 S37794P2337M CONTROL CABLE CESSNA 680 680CE 2076811 CE SPOILER MISINSTALLED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 301QS 2343 6800010 ROLL SPOILER CABLE P/N S3779-4P233.7M WAS ROUTED INCORRECTLY OVER LOW FRICTION PULLEY. CABLE WAS FOUND ROUTED THROUGH TO OLING HOLE IN BRACKET P/N 6960236-17 RATHER THAN ENGAGING PULLEY. THE BRACKET TOOLING HOLE EXHIBITED WEAR FROM THE CABL E RIDING (CUTTING) INTO THE TOOLING HOLE. 2 L 7 2 4F RC T00012WI 2007071100043 20070711 00043 CE 2007 7 11 2007FA0000550 1 20070621 G 3230 50410015 BELLCRANK CESSNA 310 310R 2074245 CE CONT O520 IO520* 17032 SO ZONE 700 BROKEN D O OTHER O OTHER LD LANDING 1 SO 19 1771G 310R0040 LT MAIN GEAR BELLCRANK ASSY BROKE IN MARCH OF 2007. THE PART WAS REPLACED BY A USED SERVICABLE PART WHICH LASTED APPROXI MATLY 58 HRS. THEN FAILED AT THE SAME LOCATION ON THE PART. 1 L 7 2 3O 3 O 3A10 E5CE 2007071100052 20070711 00052 SO 2007 7 11 2007FA0000552 1 20070622 G 2910 177662 HOSE PIPER PA31T PA31T 7103124 SO HYD SYSTEM RUPTURED D O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 GL 27 970PS 6349 31T8020023 LT MLG IB GEAR DOOR ACTUATOR HYDRAULIC HOSE, HAD A PRESSURE FAILURE, THUS DRAINING HYDRAULIC FLUID IN FLIGHT, RESULTING IN FAILURE OF PROPER GEAR EXTENSION, EMERGENCY GEAR EXTENSION, AND CAUSING AIRCRAFT GEAR UP LANDING. HYDRAULIC HOSE P/N 17766-2 AND PIPER P/N 465-138. HOSE IS ORIGINAL EQUIPMENT INSTALL. 1 L 7 2 3T A8EA 2007071100116 20070711 00116 WP 2007 7 11 2007FA0000553 2 20070626 G 7200 30751604 ENGINE RAYTHN DH125 HAWKER800XP 7150012 CE GARRTT TFE731 TFE7315BR WP NR 2 BINDING C E ENGINE SHUTDOWN E VIBRATION/BUFFET CR CRUISE 1 WP 07 1781 258593 P107918 IFSD OCCURRED ON JUNE 21ST 2007. AN EMERGENCY WAS DECLARED WHEN THE NR 2 ENGINE ITT CLIMBED TO 1066C FOR 5 SECONDS AT F L 260 AND A HIGH VIBRATION WAS FELT. THE PILOT SHUTDOWN THE ENGINE. ALL PARAMETERS WERE FINE UNTIL THIS EVENT. AN OVE RWEIGHT LANDING INSPECTION WAS PERFORMED ON THE AIRCRAFT WITH NO ABNORMALITIES REPORTED. DISASSEMBLY FINDINGS OF THE EN GINE REVEALED LPC2 DISC POST SEPARATIONS AS LISTED IN SB TFE731-72-3711. 2 L 7 2 4F 4 F RT A3EU E6WE 2007071100127 20070711 00127 2007 7 11 2007FA0000554 4 20070628 G 3457 12744001 ANTENNA CIRRUS SR SR20 05628AJ GL CONT IO360 IO360* 17025 CE GPS DISCONNECTED B O OTHER O OTHER CR CRUISE 1 EA 07 5959A 127 1526 WHILE IN CRUISE FLIGHT THE NR 1 GPS STOPPED RECEIVING A SIGNAL. AFTER LANDING, REMOVED THE MFD AND FOUND THE GLUE HOLDIN G THE VELCRO TO THE GPS ANTENNA HAD COME UNDONE. BOTH GPS ANTENNAS ARE HELD IN PLACE WITH VELCRO STRIPS AND IN THE HEAT OF SUMMER, THE GLUE SOFTENS AND COMES UNDONE. 1 L 7 1 3O 3 O NT A00009CH E1CE 2007071200120 20070712 00120 EA 2007 7 12 2007FA0000555 2 20070616 G 8530 EXHAUST VALVE AMERAC S1 S1AAMERAC WP LYC O235 O235C2C 41505 EA MCAULY 1A105 1A105SCM GL ENGINE BENT G A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CL CLIMB 1 GL 03 5651L 1749 1749 AA10051 L961915 52473 EXHAUST VALVE WAS FOUND STUCK IN THE OPEN POSITION ON TEARDOWN OF THE ENGINE. VALVE STEM HAD A SLIGHT BEND. ENGINE TEA RDOWN WAS DUE TO AN AIRCRAFT ACCIDENT. 1 L 7 1 3R 3 O ATC521 E223 5 N P918 2007071100140 20070711 00140 EU 2007 7 11 2007FA0000556 1 20070628 G 6320 305A32031002 GEARBOX SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B1 60056 NE UNKNOWN B A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 EA 17 808CP 161 4151 23335 MGB CHIP LIGHT CAME ON IN FLIGHT. INSPECTED CHIP PLUGS IAW AEC MWC AND SPM. NO FURTHER ACTION REQUIRED. 1 G 7 1 3U 3 U H9EU E00054EN 2007071100141 20070711 00141 EU 2007 7 11 2007FA0000557 1 20070628 G 6320 305A32031002 GEARBOX SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B1 60056 NE UNKNOWN B PN1R A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 EA 17 808CP 161 4151 23335 MGB CHIP LIGHT CAME ON IN FLIGHT. INSPECTED CHIP PLUGS IAW AEC MWC AND SPM. NO FURTHER ACTION REQUIRED. 1 G 7 1 3U 3 U H9EU E00054EN 2007071100150 20070711 00150 CE 2007 7 11 2007FA0000558 1 20070510 G 3240 LINE CESSNA 185 A185F 2072821 CE CONT O520 IO520* 17032 SO BRAKE LOOSE D O OTHER O OTHER LD LANDING 1 GL 13 4845E 18503887 RT MAIN BRAKE FAILED ON AIRCRAFT ROLLOUT OF NORMAL CROSSWIND LANDING. BRAKE LINE B-NUT FOUND COMPLETELY LOOSE. (K) 1 H 7 1 3O 3 O 3A24 E5CE 2007071100152 20070711 00152 CE 2007 7 11 2007FA0000559 1 20070525 G 5280 45A303794 DOUBLER BEECH MU300 400BEECH CE PWA JT15 JT15D5 52112 NE MLG DOOR CRACKED B E81R O OTHER O OTHER AP APPROACH 1 GL 03 406TS RJ6 FLIGHT CREW REPORTED RED GEAR UNSAFE INDICATION LIGHT AFTER GEAR EXTENSION FOR APPROACH, ALL (3) LANDING GEARS INDICATIN G DOWN AND LOCKED. PERFORMED ALTERNATE GEAR EXTENSION IAW CHECKLIST. AIRCRAFT FERRIED WITH LANDING GEAR DOWN IAW PERMI T TO FACILITY FOR REPAIRS. AFTER NORMAL LANDING, RT MLG FUSELAGE DOOR UNLATCHED AND DRAGGED ON TAXIWAY DURING TAXI-IN. FOUND DOUBLER UNDER RT FUSELAGE DOOR FORWARD HINGE BRACKET CRACKED, ALSO CRACK IN PN 45A30314-6 FRAME ( U-CHANNEL) AT F ORWARD HINGE AREA. SUSPECT CRACKED AREA ALLOWED ENOUGH PLAY IN DOOR ASSY FOR DOOR UPLOCK NOT TO FULLY ENGAGE. DOOR ASS Y APPEARS TO HAVE BEEN REPAIRED PREVIOUSLY. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007071100192 20070711 00192 EU 2007 7 11 2007FA0000560 1 20070521 G 5302 STRUCTURE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1 60030 NE TAIL BOOM CRACKED B QS7R K NONE O OTHER IN INSP/MAINT 1 NM 09 352EV 2542 2555 A CRACK APPROXIMATELY 170 MM LONG WAS FOUND ON THE LEADING EDGE, AFT OF FWD MOUNT POINT. (K) 1 G 7 1 3U 3 U H9EU E19EU 2007071100196 20070711 00196 WP 2007 7 11 2007FA0000561 1 20070525 G 7600 BUSHING HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA THROTTLE LINKAGE WORN B NTBR K NONE O OTHER IN INSP/MAINT 1 NM 05 1666S 192 S1898 L3316351A ENGINE MOUNTED THROTTLE LINKAGE BUSHINGS WORN. FOUND ON INSPECTION WITH EXCESSIVE PLAY. PROBABLY OCCURRED DUE TO EXCES SIVE VIBRATION OR LACK OF SUBRICATION. RECOMMENDATION TO PREVENT WOULD BE TO LUBRICATE MORE FREQUENTLY OR DIFFERENT DES IGN OF LINKAGE. (K) 1 G 7 1 3O 3 O 4H12 1E10 2007071100198 20070711 00198 EA 2007 7 11 2007FA0000562 2 20070629 G 8550 AE3663162J0230 LINE CESSNA 182 T182T 2072738 CE LYC O540 TIO540A1A 41532 EA ENGINE OIL CRACKED B LJER K NONE O OTHER IN INSP/MAINT 1 NM 09 1328N T18208403 L1196661A 30 DEGREE FITTING HAS CRACK ON WRENCH FLAT. (K) 1 H 7 1 3O 3 O NT 3A13 E14EA 2007071100201 20070711 00201 EA 2007 7 11 2007FA0000563 1 20070507 G 3240 SHAFT SCWZER G164 G164A 3952704 EA BRAKE ROUGH D K NONE O OTHER IN INSP/MAINT 1 SW 15 5149 1123 ON DISASSEMBLY, THE SHAFT WAS FOUND TO BE QUIET ROUGH, WHERE THE PARKING BRAKE TAB LEVER 149-1 ENGAGES WITH THE SHAFT. THIS IS NOT APPARENT UNTIL IT IS REMOVED AND TAKEN APART, AS SPRING 02-9 OBSCURES THE NEW OF IT. TO PREVENT REOCCURRED THE SHAFT SHOULD BE CHECKED AND SMOTHERED OR REPLACED. (K) 1 Q 7 1 3R 1A16 2007071100202 20070711 00202 CE 2007 7 11 2007FA0000564 1 20070519 G 7400 4370 ARM CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA POINTS BROKEN D M90R K NONE O OTHER IN INSP/MAINT 1 GL 09 61953 133 17264910 L4116127A POINTS ARM BROKE IB OF POINTS AFTER ONLY 133.1, TIME SINCE INSTALLATION. (K) 1 H 7 1 3O 3 O NT 3A12 E274 2007071100204 20070711 00204 CE 2007 7 11 2007FA0000565 1 20070606 G 2910 41344 VALVE CESSNA 525 525A 2076615 CE WILINT FJ44 FJ44 66000 GL HYD SYSTEM LEAKING D O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 CE 07 301PG 525A0301 PERFORMED AN EMERGENCY LANDING DUE TO LOSS OF HYDRAULIC PRESSURE. THE EMERGENCY BOTTLE WAS USED TO LOWER THE GEAR AND L AND WITHOUT INCIDENT. THE CAUSE HAS BEEN DETERMINED TO BE THE HYDRAULIC LOADING VALVE (PN 4134-4, SN 781) FAILING IN CL OSED POSITION, RESULTING THE HYDRAULIC FLUID IN THE SYSTEM TO BE DUMPED OUT THE VENT TUBE CAUSING THE LOSS OF HYDRAULIC PRESSURE. IT IS ALSO SUSPECTED THAT THE LOADING VALVES FAILURE, CAUSED THE PCB N2108 (CIRCUIT BOARD) TO FAIL AS WELL. THE PCB 2108 WAS REPLACED. THE AIRCRAFT HYDRAULIC SYSTEM HAS BEEN LEAK CHECKED, OPS CHECKED AND HAS BEEN RETURNED TO SE RVICE WITH NO FURTHER INCIDENTS. 1 L 7 1 4F 4 F RT A1WI E3GL 2007071100209 20070711 00209 CE 2007 7 11 2007FA0000566 1 20070608 G 2800 FUEL CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL CONTAMINATED C O OTHER O OTHER LD LANDING 1 EA 65 41YP 5250122 PERFORMED AN EMERGENCY LANDING, DUE TO A FUEL BYPASS LIGHT COMING ON IN FLIGHT. THE AIRCRAFT LANDED AND TAXIED TO THE S ERVICE CENTER WITHOUT INCIDENT. THE CAUSE OF THE LIGHT HAS BEEN DETERMINED TO BE THE FUEL ITSELF. THE FUEL IS CONTAMIN ATED WITH VISIBLE DEBRIS AND HAS A CLOUDY TINT TO IT. THE CAUSE OF THE BYPASS LIGHT IS FROM THE PARTICLES IN THE FUEL C LOGGING THE ENGINE FILTERS. THE FUEL FILTERS ON BOTH THE LT AND THE RT ENGINES HAVE BEEN REPLACED IAW MM. THE AIRCRAFT HAS BEEN RETURNED TO SERVICE. NOTE: THE FUEL WAS NOT PURCHASED FROM SERVICE CENTER. (K) 1 L 7 2 4F 4 F RT A1WI E3GL 2007071100210 20070711 00210 CE 2007 7 11 2007FA0000567 1 20070629 G 6100 9696001123 LINE BEECH 58 58 1152740 CE CONT O550 IO550C SO PROPELLER LEAKING D K NONE O OTHER IN INSP/MAINT 1 SO 11 658RA 1501 TH1892 BAD OIL LEAK: DETERMINED METAL ID PLATE ON MP HOSE WORE HOLE INTO PROP UNFEATHERING ACCUMULATOR TUDE. NOTE: THIS IS TH E SUBJECT OF AD 2007-06-07 AND MANDATORY SB 61-3806 BUT DOES NOT COVER THIS AC SN. (K) 1 L 7 2 3O 3 O 3A16 E3SO 2007071100212 20070711 00212 CE 2007 7 11 2007FA0000568 1 20070629 G 3260 602EN6026 UPLOCK SWITCH CESSNA 650 650 2076802 CE NLG DEFECTIVE B EWCR O OTHER N FALSE WARNING CL CLIMB 1 EA 39 750CK 6507015 GEAR SELECTED UP AFTER TAKEOFF. UNSAFE LIGHT WOULD NOT GO OUT AND AIR NOISE FROM NOSE GEAR DOORS OPEN. 2 GEAR CYCLE AT TEMPTS WITH NO CHANGE. RETURNED TO GSO (PTI) AIRPORT, LANDED WITH NORMAL GREEN LIGHTS. AIRCRAFT TURNED OVER TO MFG SER VICE CENTER FOR REPAIR. NOSE GEAR UPLOCK SWITCH FOUND DEFECTIVE. REPLACED SWITCH OPERATION CHECKED NORMAL. (K) 2 L 7 2 4F A9NM 2007071100214 20070711 00214 EU 2007 7 11 2007FA0000569 1 20070517 G 7700 642795431 TRANSMITTER AMD FALC90 FALCON900EX 2730009 EU GARRTT TFE731 TFE73160 NE ENGINE READS LOW B UO2R O OTHER N FALSE WARNING CL CLIMB 1 GL 19 127SF 5144 013 P112149 THE AIRCRAFT WAS CLIMBING AND THE NR 3 ENGINE OIL PRESSURE INDICATION STARTED TO DROP. AT 46 PSI IT WENT RED AND THE PI LOT SHUTDOWN THE ENGINE AND LANDED THE AIRCRAFT. THE OIL LEVEL WAS IN LIMITS AND NO EXTERNAL LEAKS WERE FOUND. A DIRE CT READING PRESSURE GAGE WAS INSTALLED AND SHOWED GOOD OIL PRESSURE AND THAT THE INDICATOR WAS READING LOW. A NEW OIL P RESSURE TRANSMITTER WAS INSTALLED AND CORRECTED THE LOW READING PROBLEM. (K) 2 L 7 3 4F 4 F RT A46EU E1NM 2007071100215 20070711 00215 CE 2007 7 11 2007FA0000570 1 20070529 G 5311 5511118200 FRAME CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE FUSELAGE DAMAGED C JGVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 905CW 9359 5500072 FUSELAGE FRAME WEB DAMAGED BY DRILL BIT FROM THE BEND RADIUS OF THE OUTER (SKIN) FLANGE. REPLACEMENT REQUIRED SRM, CHAP TER 53-12-27. PROBABLE CAUSE: INCORRECTLY DRILLED AT AIRCRAFT MFG. (K) 1 L 7 2 4F 4 F A22CE E1NE 2007071100218 20070711 00218 SO 2007 7 11 2007FA0000571 1 20070531 G 3220 67107000 BRACKET PIPER PA28 PA28R200 7102811 SO CONT IO360 IO360* 17025 CE NOSE GEAR FAILED H O OTHER O OTHER LD LANDING 1 SO 33 56066 28R7335346 THE PILOT STATED NOSE GEAR COLLAPSED ON LANDING. AFTER AIRCRAFT REMOVED FROM RUNWAY AND PUT ON JACKS. THE NOSE GEAR WO ULD NOT EXTEND OR RETRACT. THE GEAR WAS EXTENDED BY EMERGENCY EXTENSION. THE NOSE GEAR ALIGNER BRACKET FELL OFF THE GE AR. AGAIN THE NOSE GEAR WAS EXTENDED AND RETRACTED SEVERAL TIMES. THE TT OF THE NOSE GEAR ALIGNER BRACKET COULD NOT BE DETERMINED. (K) 1 L 7 1 3O 3 O 2A13 E1CE 2007071100219 20070711 00219 CE 2007 7 11 2007FA0000572 1 20070525 G 2720 S16751 BEARING CESSNA 210 T210M 2073451 CE RUDDER PEDAL BROKEN D K NONE O OTHER IN INSP/MAINT 1 WP 23 808FS 2721 21061586 WHILE PERFORMING RUN UP OF AIRCRAFT DURING ANNUAL INSPECTION IT WAS NOTICED THAT PILOT RT RUDDER PEDAL HAD AN UNUSUAL FE EL WHILE BRAKING. DURING THE INSPECTION OF THE RUDDER PEDALS IT WAS FOUND THT THE EACH OF THE PILOT SIDE S1675-1 RUDDER IB BEARING HALF HAD BROKEN INTO SEVERAL PARTS. THE S1675-1 BEARING HALFS ARE CONSTRUCTED OF PLASTIC, AND THE LIKELY RE ASON FOR BREAKING WOULD BE DUE TO THE AGING AND EMBRITTLEMENT OF THE PLASTIC. I WOULD RECOMMEND THAT THE BEARINGS BE CO NSTRUCTED OF A MATERIAL OTHER THAN PLASTIC, OF HAVE A PART REPLACEMENT INTERVAL BEFORE BREAKAGE COULD OCCUR. (K) 1 H 7 1 3O 3A21 2007071100220 20070711 00220 CE 2007 7 11 2007FA0000573 1 20070606 G 2720 25137911 PIN CESSNA 208 208B 2073701 CE PWA PT6 PT6* 52043 EA RUDDER PEDAL UNSERVICEABLE B ES4R K NONE O OTHER IN INSP/MAINT 1 AL 01 4365U 18129 208B0253 ON A ROUTINE INSPECTION, A MECHANIC FOUND THAT THE PILOTS RT RUDDER PEDAL PIN WAS ABOUT TO FALL OUT OF THE RUDDER PEDAL. FURTHER INSPECTION FOUND THAT THE ROLL PIN PN: NAS561C318 HAD FALLEN OUR OF ITS HOLE CAUSING THE RUDDER PEDAL PIN TO M IGRATE FROM ITS POSITION. INSPECTION OF RUDDER PEDAL ASSY FOUND THAT THE ROLL PIN HOLE IN THE RUDDER PEDAL HAD BECOME E NLARGED, DUE TO AN UNKNOWN REASON. RECOMMENDATION TO PREVENT RECURRENCE: ATTENTION TO ROLL PIN INSTALLATION FOR ADEQUA TE PRESS FIT AND ADDITIONAL ATTENTION OF ROLL PIN ON ROUTINE INSPECTION. (K) 1 H 7 1 3T 3 T A37CE E2NE 2007071100221 20070711 00221 CE 2007 7 11 2007FA0000574 1 20070629 G 3244 265F868 TIRE BEECH B300 B300 1159232 CE PWA PT6 PT6* 52043 EA NLG UNBALANCED B FTUR K NONE O OTHER IN INSP/MAINT 1 NE 05 5XM 408 FL115 PILOT REPORTED A NOSE SHIMMY, UPON INVESTIGATION IT WAS DETERMINED THAT THE MFG BALANCE WEIGHT HAD COME LOOSE. THIS IS THE SECOND OCCURRENCE OF THIS TYPE FOR THE OPERATOR. (K) 2 L 7 2 4T 3 T RT A24CE E2NE 2007071100222 20070711 00222 NE 2007 7 11 2007FA0000575 2 20070602 G 7321 0292858360 HMU UROCOP EC130 EC130B4 8680989 EU TMECA ARRIEL ARRIEL2B1 60056 NE ENGINE FAILED D O OTHER O OTHER NR NOT REPORTED 1 CE 01 151AC 1609 3732 23065 THE PILOT REPORTED A LOUD THUD AND A SUBSEQUENT YAWING OF THE AC, WITH CONTINUED YAWING OF THE AC, AND NO INDICATION ON THE COCKPIT INSTRUMENTATION THAT HE NOTICED. THE PILOT DECLARED AN EMERGENCY AND PERFORMED AN AUTORATATIVE LANDING AT T HE AIRPORT. THE VEHICLE AND ENGINE MULTIFUNCTION DISPLAY, DISPLAYED FAILURE OF CHANNEL A. THE EC130 IS EQUIPPED WITH A DUAL CHANNEL FADEC SYSTEM WITH A MECHANICAL BACKUP. IN THE FOLLOWING TROUBLESHOOTING PROCESS IT WAS FOUND THAT THE RES OLVER MOTOR ON THE FUEL CONTROL (HMU) HAD A RESISTANCE VALUE THAT WAS OUT OF TOLERANCE. A FIELD TECH WAS BROUGHT IN FR OM MFG TO PERFORM FURTHER TESTING, SINCE THE FAILURE OF ONE CHANNEL OF THE FADEC AND THE SUBSEQUENT SWITCHING TO THE OTH 1 G 7 2 3U 3 U H9EU E00054EN 2007071100232 20070711 00232 CE 2007 7 11 2007FA0000576 1 20070611 G 5300 STRUCTURE BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE FUSELAGE MISINSTALLED B BWVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 07 7262U FL532 THE AIRCRAFT ARRIVED NEW FROM THE FACTORY FOR AVIONICS MODIFICATIONS AND DURING OUR INCOMING INSPECTION A TECH NOTED MIS SING RIVETS IN (2) STRINGER CLIPS. THE CLIPS ARE LOCATED AT FS 386 ON THE RT NR3 AND RT NR 5 STRINGERS AS NOTED USING T HE UPPER CENTERLINE STRINGER AS STRINGER NR 1. EACH CLIP WITH (6) RIVETS EACH WERE EITHER MISSING RIVETS AND/OR THE RIV ETS WERE NOT BUCKED SITTING IN THE HOLES. ADVISED MFG OF DISCREPANCY. (K) 2 L 7 2 4T 4 T RT A24CE E4EA 2007071100233 20070711 00233 SO 2007 7 11 2007FA0000577 1 20070512 G 3220 6715003 DOWNLOCK PIPER PA28 PA28R200 7102811 SO CONT IO360 IO360* 17025 CE NLG BROKEN G K NONE O OTHER IN INSP/MAINT 1 GL 03 5094S 3220 28R7135094 THE LOWER LATCH HOOK WAS BROKEN OFF ALLOWING THE NOSE GEAR TO COLLAPSE. (K) 1 L 7 1 3O 3 O 2A13 E1CE 2007071100246 20070711 00246 CE 2007 7 11 2007FA0000578 1 20070605 G 5343 FMI32345010B BUSHING CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C GL TRUNNION GOUGED B NOZR K NONE O OTHER IN INSP/MAINT 1 WP 23 22NG 7500204 BUSHINGS WHERE OLEO ATTACHES TO TRUNNION. OLEO ATTACH BOLT WAS SEIZED AND HARD TO REMOVE. INNER BORE OF BUSHINGS WERE GOUGED. NO MEANS TO LUBRICATE THESE BUSHINGS EXCEPT AT ASSY. SUGGEST USE OF ANT SEIZE COMPOUND DURING ASSY INSTEAD OF AEROSHELL 17. (K) 2 L 7 2 4J 4 F RT T00007WI TE6CH 2007071100247 20070711 00247 CE 2007 7 11 2007FA0000579 1 20070605 G 5343 67410261 TRUNNION CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C GL MLG MISALIGNED B NOZR K NONE O OTHER IN INSP/MAINT 1 WP 23 22NG 7500204 AFT TRUNNION ATTACH PIN LOCK PIN HOLE MISALIGNED. LOCK PIN HOLES DRILLED IN TRUNNION DO NOT LINE UP WITH HOLE DRILLED I N MOUNTING PIN. (K) 2 L 7 2 4J 4 F RT T00007WI TE6CH 2007071100249 20070711 00249 CE 2007 7 11 2007FA0000580 1 20070427 G 8011 MHB4016R STARTER CESSNA 182 R182 2072734 CE LYC O540 O540* 41532 EA ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 03 182MS 18200791 REMOVED THIS STARTER FROM AIRCRAFT DUE TO BENDIX FAILURE. TIME ON THIS STARTER IS UNKNOWN. (K) 1 H 7 1 3O 3 O RT 3A13 E295 2007071100257 20070711 00257 CE 2007 7 11 2007FA0000581 1 20070518 G 8011 MHB4016R STARTER CESSNA 182 R182 2072734 CE LYC O540 O540* 41532 EA ENGINE MALFUNCTIONED D K NONE O OTHER IN INSP/MAINT 1 SW 03 182MS 62 18200791 REMOVED THIS STARTER FROM SAME AIRCRAFT FOR THE 3RD TIME WITH 62.3 HRS SINCE OVERHAUL. STARTER BENDIX WOULD NOT ENGAGE ANYMORE DURING START UP. NO PROBLEM COULD BE FOUND WITH AIRCRAFT ELECTRICAL SYSTEM. (K) 1 H 7 1 3O 3 O RT 3A13 E295 2007071100258 20070711 00258 CE 2007 7 11 2007FA0000582 1 20070430 G 8011 MHB4016R STARTER CESSNA 182 R182 2072734 CE LYC O540 O540* 41532 EA ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 03 182MS 18200791 REMOVED THIS STARTER WITH 3.3 HOURS SINCE OVERHAUL. STARTER BENDIX STAYED ENGAGED DURING START UP. NO PROBLEM COULD BE FOUND WITH AIRCRAFT ELECTRICAL SYSTEM. (K) 1 H 7 1 3O 3 O RT 3A13 E295 2007071100259 20070711 00259 CE 2007 7 11 2007FA0000583 1 20070524 G 8011 MHB4016R STARTER CESSNA 182 R182 2072734 CE LYC O540 O540* 41532 EA ENGINE DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 SW 03 182MS 18200791 REMOVED THIS STARTER FROM SAME AIRCRAFT FOR THE 4TH TIME WITH 11.3 HOURS SINCE OVERHAUL. STARTER BENDIX WOULD NOT ENGAG E ANYMORE DURING STARTUP. NO PROBLEM COULD BE FOUND WITH AIRCRAFT ELECTRICAL SYSTEM. INSTALLED ON ANOTHER AIRCRAFT TO VERIFY PROBLEM AND FOUND THAT THE STARTER WAS DEFECTIVE. (K) 1 H 7 1 3O 3 O RT 3A13 E295 2007071100265 20070711 00265 CE 2007 7 11 2007FA0000584 1 20070521 G 3231 HM4 ROD END CESSNA 310 310P 2074238 CE CONT O470 IO470* 17026 SO NOSE GEAR DOOR FAILED D O OTHER O OTHER CR CRUISE 1 SO 15 5918M 310P0218 ROD END FAILED, ALLOWING NOSE GEAR DOOR TO PARTIALLY CLOSE IN FLIGHT. WHEN GEAR WAS RETRACTED, JAMMED NOSE GEAR ASSY AL ONG WITH GEAR DOOR UP IN GEAR WELL. (K) 1 L 7 2 3O 3 O 3A10 E1CE 2007071100266 20070711 00266 EA 2007 7 11 2007FA0000585 1 20070507 G 5100 AN837A BOLT SCWZER G164 G164A 3952704 EA PWA R1340 R1340AN1 52016 NE UNKNOWN BROKEN C O OTHER O OTHER LD LANDING 1 SW 15 5149 1123 THE BOLTS FAILED DUE TO LANDING WITH WHEEL LOCKED. THINK THE BOLTS WERE FINE BEFORE THIS INCIDENT. (K) 1 Q 7 1 3R 3 R 1A16 5E2 2007071100268 20070711 00268 NM 2007 7 11 2007FA0000588 1 20070413 G 3240 BRAKE DISC BOEING 727 727200 138407E NM LT MLG MALFUNCTIONED H K NONE O OTHER IN INSP/MAINT 1 SW 99 HP161 20780 (REG NR: HP1610) DURING PREFLIGHT INSPECTION, FOUND MAIN TIRE NR 2 WITH FLAT SPOT. ON THIS AIRCRAFT OP SPECS APPROVED BY THIS DGAC, OPERATING BY DHL OF GUATEMALA UNDER THEM. REMOVED AND REPLACED MWA AND BRAKE ASSY. NR 2 DUEL TO DAMAGED , ALSO MAIN WHEEL ASSY NR 1 WAS REPLACED , BECAUSE IT RAN WITH THE TIRE NR 2 DEFLATED. (K) 2 L 7 3 4F RT A3WE 2007071200121 20070712 00121 2007 7 12 2007FA0000589 2 20070622 G 7414 1068256013 GEAR MAGNETO DAMAGED G K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 CE 01 720 REPAIR STATION RECEIVED MAGNETO FOR REPAIR. WHEN THE UNIT WAS DISASSEMBLED IT WAS NOTED BOTH DISTRIBUTOR GEARS TCM PN 10 -682016 WERE MISSING TEETH. IT WAS NOTED THAT A PATTERN OF TEETH THAT WERE MISSING COULD BE SEEN. A TOTAL OF 5 TEETH WER E MISSING FROM BOTH GEARS. WHAT SEEMS TO HAPPEN IS WHEN THE IMPULSE SNAPS THE IMPULSE SNAPS THAT TOOTH OFF THE GEAR? WHE N ASSEMBLED TO VIEW THE GEAR POSITION IT WAS NOTED THAT ONE TOOTH WAS MISSING WITH FIVE EACH OF THE SIX TOTAL ENGAGEMENT S OF THE IMPULSE. ITEMS THAT COULD CONTRIBUTE TO THIS PROBLEM CAN BE FOUND IN SB658. IT IS RECOMMENDED TO FOLLOW SB658 A ND TO INSPECT THE DISTRIBUTOR GEARS ON ALL IMPULSE D-3000 OR D-2000 UNITS FOR WEAR AT EVERY 100 HRS BY REMOVING THE MAGN 2007071200122 20070712 00122 SO 2007 7 12 2007FA0000590 2 20070527 G 7414 10382585 CONTACTOR D4LN2021 CONT O360 IO360A 17025 SO MAGNETO MELTED D E B A ENGINE SHUTDOWN EMER. DESCENT UNSCHED LANDING G Y MULTIPLE FAILURE ENGINE STOPPAGE CR CRUISE 1 NM 03 134DC 114 R2388K L1176351A AIRCRAFT HAD DEPARTED FOR A SIGHT SEEING TRIP. ON THE RETURN, ALL ENGINE POWER WAS LOST, THE AIRCRAFT WAS LANDED IN A ME ADOW WITH MINIMAL DAMAGE TO THE AIRCRAFT. UPON INSPECTION OF THE ENGINE, FOUND THAT THE MFG DUAL MAGNETO D4LN-2021 WAS NOT FUNCTIONAL ON EITHER MAG. UPON FURTHER INVESTIGATION IT WAS DETERMINED THAT THE CAM FOLLOWERS OF THE POINTS HAD GOT TEN TOO HOT AND MELTED TO A POINT THAT RENDERED THE CONTACT ASSEMBLY INOPERATIVE, CAUSING A DUAL FAILURE OF THE MAG. IT WAS NOTED THAT THE SCREW THAT HOLDS THE POINTS CAM IN PLACE HAD A TORQUE CHECK PAINTED ON IT AND HAD TURNED BLACK FROM HEAT. DUE TO THE FACT THAT THE DUAL MAG HAS MORE POSSIBILITIES TO PRODUCE MORE HEAT JUST FROM THE ELECTRICAL PART OF MA 3 O E1CE 2007071200125 20070712 00125 SO 2007 7 12 2007FA0000592 2 20070703 G 8530 SA10203 CYLINDER CESSNA 172 172E 2072412 CE CONT O300 O300D 17022 SO MCAULY 1C172 1C172EM GL NR 5 SEPARATED G E ENGINE SHUTDOWN D INFLIGHT SEPARATION CR CRUISE 1 EA 63 5436T 850 17251336 34640D6D 78634 CYLINDER BARREL SEPARATED APPROXIMATELY 2 NR ABOVE THE CYLINDER BASE FLANGE. 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 2007071200132 20070712 00132 NM 2007 7 12 2007FA0000593 1 20070703 G 5751 25W171124 SUPPORT FITTING ISRAEL 1125 1125 NM GARRTT TFE731 TFE731* 01518 WP AILERONS DAMAGED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 49MN 7037 019 AFTER REMOVAL OF AILERON AND SERVICE SUPPORT FITTING AT BL 9R FUSELAGE STATION 199.579. FOUND SEVERAL MISSED DRILLED/EL ONGATED /FILLED FASTENER HOLES IN T CASTING P/N:25W17124, ANGLE P/N:25W171126 AND AILERON AND SERVICES SUPPORT FITTING CASTING P/N:25W353216 2 L 7 2 4F 4 F RT A16NM E6WE 2007071700012 20070717 00012 NM 2007 7 17 2007FA0000594 1 20070703 G 5751 25W171124 SUPPORT FITTING ISRAEL 1125 1125 NM GARRTT TFE731 TFE731* 01518 WP AILERON MISMANUFACTURED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 49MN 7037 019 AFTER REMOVAL OF AILERON AND SERVICE SUPPORT FITTING AT BL 9R FUSELAGE STATION 199.579. FOUND SEVERAL MISSED DRILLED/ELO NGATED /FILLED FASTENER HOLES IN T CASTING P/N:25W17124, ANGLE P/N:25W171126 AND AILERON AND SERVICES SUPPORT FITTING CA STING P/N:25W353216 2 L 7 2 4F 4 F RT A16NM E6WE 2007071800219 20070718 00219 EU 2007 7 18 2007FA0000599 1 20070616 G 2701 103B4411 CONTROL COLUMN GROB 103TWN G103ATWINII 1660206 EU COCKPIT FRACTURED D B A EMER. DESCENT UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 NM 07 4446Y 2650 3825 ON SECOND FLT OF DAY, & WHILE STILL ON AERO-TOW, PILOT WHO WAS FLYING FROM THE REAR SEAT WITH A NON-PILOT PASSENGER IN F RONT, NOTICED THAT IT REQUIRED APPROXIMATELY 20 DEGREES OF RT-STICK CORRECTION TO MAINTAIN LEVEL FLT. PILOT ALSO OBSERV ED AILERONS TO BE IN A NEUTRAL POSITION WITH THIS RT-STICK CORRECTION. PILOT RELEASED FROM TOW, & RETURNED TO AIRPORT & EXECUTED A SUCCESSFUL, UNEVENTFUL LANDING USING MINIMAL, LIGHT CONTROL STICK INPUTS. POST FLT INSPECTION OF AFT CONTROL STICK REVEALED CONTROL COLUMN BASE UNIT TUBING STUB OVER WHICH DETACHABLE REAR CONTROL STICK MOUNTS, TO BE FRACTURED, AP PROXIMATELY 80 PERCENT OF ITS TOTAL CIRCUMFERENCE. IT REQUIRED ONLY MINIMUM FURTHER (BENDING) OF THE CONTROL STICK TO AC 1 K 0 0 3O 0 G39EU 2007071800235 20070718 00235 SO 2007 7 18 2007FA0000601 1 20070710 G 2910 MS21911D6 FITTING GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6108 NE HYD LINE CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 177BB 1073 FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK WAS GOOD, NO LEAKS NOTED. 2 L 7 2 4F 4 F RT A12EA E25NE 2007071800237 20070718 00237 SO 2007 7 18 2007FA0000602 1 20070710 G 2910 MS21911D6 FITTING GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6108 NE HYD LINE CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 177BB 1073 FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK WAS GOOD, NO LEAKS NOTED. 2 L 7 2 4F 4 F RT A12EA E25NE 2007071800238 20070718 00238 SO 2007 7 18 2007FA0000603 1 20070710 G 2910 MS21911D6 FITTING GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6108 NE HYD LINE CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 177BB 1073 FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILLIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK WAS GOOD, NO LEAKS NOTED. 2 L 7 2 4F 4 F RT A12EA E25NE 2007071700013 20070717 00013 SO 2007 7 17 2007FA0000604 1 20070710 G 2910 MS21911D6 TEE FITTING GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6108 NE HYD SYSTEM CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 177BB 1073 FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK WAS GOOD, NO LEAKS NOTED. 2 L 7 2 4F 4 F RT A12EA E25NE 2007071700014 20070717 00014 SO 2007 7 17 2007FA0000605 1 20070710 G 2910 MS21911D6 TEE FITTING GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6108 NE HYD SYSTEM CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 177BB 1073 FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHEC K WAS GOOD, NO LEAKS NOTED. 2 L 7 2 4F 4 F RT A12EA E25NE 2007071700018 20070717 00018 EU 2007 7 17 2007FA0000606 1 20070712 G 2913 350A35109221 SHAFT SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE HYD PUMP WORN B K NONE O OTHER IN INSP/MAINT 1 SW 15 186AE 545 3872 22484 DURING DAILY INSPECTION DISCOVERED EXCESSIVE PLAY IN HYDRAULIC PUMP DRIVE PULLEY. HYDRAULIC PUMP DRIVE WAS THEN REMOVED FOR FURTHER INSPECTION. IT WAS DISCOVERED THAT THE DRIVE PULLEY SHAFT HAD WORN EXCESSIVELY WHERE THE DRIVE BEARING HAD B EEN SPINNING AROUND IT. THE DRIVE BEARING APPEARED TO BE FINE WITH NO BINDING NOTICED. IT APPEARS THAT THE FIT OF THE BE ARING ONTO THE PULLEY WAS NOT TIGHT ENOUGH TO KEEP THE BEARING RACE FROM SPINNING. 1 G 7 1 3U 3 U H9EU E00054EN 2007071700019 20070717 00019 EU 2007 7 17 2007FA0000607 1 20070712 G 2913 350A35109221 PULLEY SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE HYD PUMP WORN B K NONE O OTHER IN INSP/MAINT 1 SW 15 186AE 545 3872 22484 DURING DAILY INSPECTION DISCOVERED EXCESSIVE PLAY IN HYDRAULIC PUMP DRIVE PULLEY. HYDRAULIC PUMP DRIVE WAS THEN REMOVED FOR FURTHER INSPECTION. IT WAS DISCOVERED THAT THE DRIVE PULLEY SHAFT HAD WORN EXCESSIVELY WHERE THE DRIVE BEARING HAD B EEN SPINNING AROUND IT. THE DRIVE BEARING APPEARED TO BE FINE WITH NO BINDING NOTICED. IT APPEARS THAT THE FIT OF THE BE ARING ONTO THE PULLEY WAS NOT TIGHT ENOUGH TO KEEP THE BEARING RACE FROM SPINNING. 1 G 7 1 3U 3 U H9EU E00054EN 2007071700015 20070717 00015 SO 2007 7 17 2007FA0000608 1 20070710 G 2910 MS21911D6 TEE FITTING GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6108 NE HYD SYSTEM CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 177BB 1073 FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK WAS GOOD, NO LEAKS NOTED. 2 L 7 2 4F 4 F RT A12EA E25NE 2007071700016 20070717 00016 SO 2007 7 17 2007FA0000609 1 20070710 G 2910 MS21911D6 TEE FITTING GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6108 NE HYD SYSTEM CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 177BB 1073 FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHE CK WAS GOOD, NO LEAKS NOTED. 2 L 7 2 4F 4 F RT A12EA E25NE 2007071700017 20070717 00017 SO 2007 7 17 2007FA0000610 1 20070710 G 2910 MS21911D6 TEE FITTING GULSTM G1159 GIV 3980115 SO HYD SYSTEM CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 177BB 1073 FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK WAS GOOD, NO LEAKS NOTED. 2 L 7 2 4F RT A12EA 2007071800239 20070718 00239 SO 2007 7 18 2007FA0000611 1 20070710 G 2910 MS21911D6 FITTING GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6108 NE HYD LINE CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 177BB 1073 FOUND CRACKED HYDRAULIC TEE FITTING, PN MS21911D6, IN AUXILIARY HYDRAULIC SYSTEM FILTER RETURN LINE. CRACK WAS FOUND AT THE MALE END WHERE END AND TEE BODY COME TOGETHER. REPLACED FITTING AND PRESSURIZED AND LEAK CHECKED SYSTEM. OP'S CHECK WAS GOOD, NO LEAKS NOTED. 2 L 7 2 4F 4 F RT A12EA E25NE 2007071800246 20070718 00246 EU 2007 7 18 2007FA0000612 1 20070711 G 2741 EM40112 ACTUATOR PIAGIO P180 P180 6960204 EU PWA PT6 PT6A66 52043 NE PITCH TRIM FAILED C O OTHER F FLT CONT AFFECTED AP APPROACH 1 WP 15 5166P 61 1129 ON APPROACH PITCH TRIM ACTUATOR FAILED TO MOVE. AIRCRAFT LANDED WITH PARTIAL FLAPS WITHOUT FURTHER INCIDENT. ONE HOUR LATER TRIM ACTUATOR GROUND TESTED REVEALING NO DEFECTS. ACTUATOR SENT TO MFG FOR INVESTIGATION. 1 H 7 2 3O 4 T RT A59EU E26NE 2007071800270 20070718 00270 CE 2007 7 18 2007FA0000613 1 20070713 G 3350 BATTERY BEECH B300 B300 1159232 CE EMERGENCY LIGHT MELTED B K NONE L NO TEST IN INSP/MAINT 1 NE 05 122RG FL448 AIRCRAFT WAS IN MAINTENANCE FOR AN INSPECTION AND 12 MONTH EMERGENCY LIGHT BATTERY CHANGE. FOUND BATTERIES SEVERELY COR RODED AND HEAT DAMAGED. BATTERIES INSTALLED WERE P/N MN1400. THESE BATTERIES HAVE A TEST STRIP EFFECTIVELY SHORTS THE BATTERY TO CHECK THE CHARGE CONDITION. THE BATTERY HOLDER IN THE EMERGENCY LIGHT ASSEMBLY CLAMPS THE BATTERY. THE BATTE RIES WERE INSTALLED SO THE TEST STRIP WAS CLAMPED SHORTING THE BATTERIES CAUSING THE BATTERIES TO MELT AND CORROD IN THE HOLDERS, DESTROYING THE LIGHT ASSEMBLIES. THE P/N FOR THE BATTERIES FOR THE EMERGENCY LIGHT IS 14A, BATTERIES WHICH HAV E NO TEST STRIP. USE THE CORRECT P/N BATTERIES. 2 L 7 2 4T RT A24CE 2007071900120 20070719 00120 CE 2007 7 19 2007FA0000617 1 20070718 G 2731 556545098 ACTUATOR CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE RT STAB WORN B K NONE O OTHER IN INSP/MAINT 1 SW 13 26494 9131 1200 0605 AT THE PHASE 5 INSPECTION THE ELEVATOR FAILED THE FREE PLAY CHECK. A OVERHAULED UNIT P/N 5565450-98 S/N 0320-63 WAS INST ALLED AND COULD NOT GET THE UP AND DOWN LIMITS TO COME IN TO SPECS. ON CLOSER INSPECTION IT WAS FOUND THAT THE PRIMARY D RIVE GEAR HAS 16 TEETH AND THE ORIGINAL UNIT HAS 14 TEETH. THIS UNIT WAS OVERHAULED 6/8/2007. AS OF THIS WRITING WE ARE IN THE PROCESS OF INSTALLING ANOTHER UNIT WITH THE CORRECT NUMBER OF TEETH. 1 L 7 2 4F 4 F A22CE E1NE 2007071900142 20070719 00142 CE 2007 7 19 2007FA0000618 1 20070717 G 2700 07136242 ANCHOR CESSNA CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL MASTER CYLINDER WORN D K NONE O OTHER UK UNKNOWN 1 SO 09 3140 172S9480 L1306651A XB23004 ANCHOR PN 0713624-2, FOUND WORN ALMOST THROUGH BY THE STEEL PIN USED TO HOLD MASTER CYLINDER. ANCHOR IS ALUMINUM WHICH W AS QUICKLY WORN OUT BY THE STEEL PIN. IF PIN BREAKS FREE FROM THE ANCHOR THE MASTER CYLINDER CAN STOP MOVEMENT OF THE R UDDER PEDAL. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2007071900144 20070719 00144 NM 2007 7 19 2007FA0000619 1 20070717 G 5714 F13147LR SKIN UNIVAR 415 415C 0420302 NM CONT A75 A75* 17005 SO CENTER WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 01 2048H 2500 10 2671 (5) MISSING AN426-3 RIVET HEADS ON LOWER CENTER SECTION SKINS PN F13147-L/-R PROMPTED INSPECTION HOLE INSTALLATION IAW S B-31 FOR REPAIR ACCESS. LIGHT SURFACE CORROSION WAS FOUND ON LOWER SKINS AND STIFFENERS. BOTH SIDES WERE CLEANED AND TRE ATED FOR CORROSION. DURING CLEANING FOUND A 2 INCH SKIN CRACK IN AFT SECTION OF F13147-L AND A .5 INCH CRACK AT THE LOW ER FWD TAB OF RIB PN F13016L, BOTH REPAIRED IAW AC 43.13-1B GUIDELINES. FUEL TANKS WERE REMOVED IAW SB-31 REQUIREMENTS A ND 4 SMALL PATCHES OF LIGHT SURFACE CORROSION WERE FOUND ON THE RT OB END OF FWD FACE OF MAIN SPAR. CORROSION CLEANED AN D TREATED. INSPECTION HOLE INSTALLATION ALLOWS MUCH BETTER VISUAL ACCESS FOR THE INSPECTION OF THE CENTER SECTION THAN W 1 L 7 1 3O 3 O A718 E213 2007071900149 20070719 00149 SO 2007 7 19 2007FA0000620 1 20070525 G 2820 MILH25579 LINE PIPER PA44 PA44180 7104402 SO LYC O360 IO360E1A 41514 EA FUEL SYSTEM LEAKING D O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 13 255ER 5 448195004 L47872T HOSE LEAK, ENGINE CAUGHT FIRE NOT DUE TO HOSE. FUEL FED FIRE OFTEN STARTING AT NR 1 EXHAUST PORT. (K) 1 L 7 2 3O 3 O A19S0 1E10 2007071900150 20070719 00150 WP 2007 7 19 2007FA0000621 2 20070611 G 7261 31011607 SEAL SCWZER G164 G164B 3952802 EA GARRTT TPE331 TPE33143 01514 WP COMPRESSOR LEAKING B G6CR O OTHER O OTHER NR NOT REPORTED 1 SW 09 48429 19B THE COMPRESSOR SEAL WAS LEAKING AND THE REAR SCAVENGE PUMP GEAR SHEARED OFF CAUSING IT TO FAIL. THIS CAUSED MAJOR OIL L OSS AND THE PROP TO FEATHER. HAVE REPLACED THE COMPRESSOR SEAL AND REAR PUMP TO PREVENT RECURRENCE. (K) 1 Q 7 1 3R 4 T 1A16 E2WE 2007071900125 20070719 00125 WP 2007 7 19 2007FA0000622 2 20070611 G 7261 GEAR SCWZER G164 G164B 3952802 EA GARRTT TPE331 TPE33143B 01514 WP SCAV PUMP SHEARED B G6CR O OTHER O OTHER NR NOT REPORTED 1 SW 09 48429 19B P80151 THE COMPRESSOR SEAL WAS LEAKING AND THE REAR SCAVENGE PUMP GEAR SHEARED OFF CAUSING IT TO FAIL. THIS CAUSED MAJOR OIL L OSS AND THE PROP TO FEATHER. HAVE REPLACED THE COMPRESSOR SEAL AND REAR PUMP TO PREVENT RECURRENCE. (K) 1 Q 7 1 3R 4 T 1A16 E2WE 2007071900266 20070719 00266 SO 2007 7 19 2007FA0000623 1 20070616 G 2810 FUEL PIPER PA25 PA25 7102502 SO LYC O320 O320A2B 41508 EA SNSNCH 74D 74DM EA UNKNOWN CONTAMINATED D O OTHER O OTHER NR NOT REPORTED 1 EA 17 6195Z 25229 A61128 WATER IN FUEL. (K) 1 L 7 1 3O 3 O 2A10 E274 5 N P88614 2007071900148 20070719 00148 CE 2007 7 19 2007FA0000625 1 20070622 G 3230 08421022 BELLCRANK CESSNA 310 T310Q 2074244 CE CONT O520 TSIO520* 17040 SO MLG FAILED B MYNR O OTHER O OTHER NR NOT REPORTED 1 GL 11 372CC 4771 310Q1071 FAILED DUE TO MECHANICAL OVERLOAD, NOSE GEAR JAMMED. (K) 1 L 7 2 3O 3 O 3A10 E8CE 2007071900152 20070719 00152 CE 2007 7 19 2007FA0000626 1 20070606 G 2910 EM9159REVC VALVE RAYTHN 390 390 7150030 CE HYDRAULIC SYS STICKING B E81R O OTHER O OTHER NR NOT REPORTED 1 GL 03 18RF 85 RB127 PILOT REPORTED RT HYDRAULIC SHUTOFF VALVE INITIALLY STUCK DURING PREFLIGHT TEST, THEN OPENED. REPLACED VALVE WITH NEW U NIT, FUNCTIONAL TESTS, OK. REMOVED VALVE ASSY, PN 39045AS65014-003, MANUFACTURED 11/2005. (K) 1 L 7 2 3F RT A00010WI 2007071900154 20070719 00154 SO 2007 7 19 2007FA0000627 1 20070606 G 3230 455180 CONDUIT PIPER PA24 PA24250 7102404 SO LYC O540 O540A1D5 41532 EA RT MLG SEPARATED G O OTHER O OTHER NR NOT REPORTED 1 EA 61 7178P 242347 L359640 RT MLG EXTEND/RETRACT CONDUIT PUSH-PULL TUBING SEPARATED AT THE SWEDGE CONNECTION JUST OB OF THE LANDING GEAR CONTROL SU PPORT BRACKET. THERE WERE NO INDICATIONS OF IMPROPER INSTALLATION. (K) 1 L 7 1 3O 3 O 1A15 E295 2007080700156 20070807 00156 CE 2007 8 7 2007FA0000628 1 20070718 G 5711 NUT PLATE CESSNA 340 340A 2076405 CE CONT O520 TSIO520* 17040 SO SPAR DAMAGED G O OTHER O OTHER NR NOT REPORTED 1 SW 11 345BK 340A0113 WHILE UNDERGOING A ANNUAL INSPECTION INVESTIGATION OF NOISE COMPLAINT FROM THE LANDING GEARBOX IT WAS DISCOVERED THAT TH E FOUR AN3-6A BOLTS THAT ATTACH THE PART 5011013-3 (BRACKET ACUATOR MOUNTING) & GEARBOX TO THE FRONT SPAR WAS LOOSE. AN ATTEMPT AT TIGHTEN THEM REVEALED THAT THE NUT PLATES BUILT INSIDE THE SPAR WERE STRIPPED. ALLOWED THE GEARBOX TO MOVE BACK FROM THE SPAR BY 1/8" AND REAR BULKHEAD FLEXING THE 1/8". (FS152.75) 1 L 7 2 3O 3 O 3A25 E8CE 2007071900117 20070719 00117 CE 2007 7 19 2007FA0000629 1 20070718 G 5340 NUT PLATE CESSNA 340 340A 2076405 CE SPAR LOOSE G K NONE O OTHER IN INSP/MAINT 1 SW 11 60WH 340A0083 WHILE UNDERGOING A ANNUAL INSPECTION INVESTIGATION OF NOISE FROM THE LANDING GEARBOX, IT WAS DISCOVERED THAT THE (4) AN3 -6A BOLTS THAT ATTACH THE PN 5011013-3 (BRACKET ACTUATOR MOUNTING) AND GEARBOX TO THE FRONT SPAR WAS LOOSE. AN ATTEMPT AT TIGHTEN THEM REVEALED THAT THE NUT PLATES BUILT INSIDE THE SPAR WERE STRIPPED. ALLOWED THE GEARBOX TO MOVE BACK FROM THE SPAR BY .1250 INCH AND REAR BULKHEAD FLEXING THE .1250 INCH. 1 L 7 2 3O 3A25 2007080700159 20070807 00159 EU 2007 8 7 2007FA0000630 1 20070524 G 7921 369D25830101 BLOWER HUGHES 369 369FF 4470709 EU ALLSN 250C 250C30 03013 GL OIL COOLER DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 13 97FF 475 0097F OIL COOLER BLOWER APPEARS TO BE FOD`D OUT. ONE BLADE WAS FOUND ENABLED IN THE HOUSING. THE OUT OF BALANCE SITUATION BR OKE ALL (4) BEARING CARRIER LEGS. DAMAGED BLOWER WAS REPLACED AND AC WAS RETURNED TO SERVICE. (K) 1 G 7 1 3U 3 U H3WE E1GL 2007080700162 20070807 00162 SW 2007 8 7 2007FA0000631 1 20070628 G 5711 5262 SPAR BBAVIA 7 7GCAA 21101N8 SW LYC O320 O320A2B 41508 EA RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 11 11666 23572 L31251278 (2) LONGITUDINAL CRACKS AT SPAR HINGE FITTING. SHAKING AND EXPANDING OF WOOD FIBERS DUE TO MOISTURE OR LACK OF. RECOMM END USING ALUMINUM SPARS OF SUFFICIENT SIZE AND STRENGTH. (K) 1 H 7 1 3O 3 O A759 E274 2007080700164 20070807 00164 CE 2007 8 7 2007FA0000632 1 20070629 G 7830 545300319 LINK ROD RAYTHN DH125 HAWKER800XP 7150012 CE GARRTT TFE731 TFE731* 01518 WP THRUST REVERSER CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 09 245SM 258567 PERFORMED EDDY CURRENT INSPECTION OF 8 EA THRUST REVERSER LINK ROD. FOUND A CRACK IN (1) LINK ROD. VERIFIED FINDING US ING MAGNETIC PARTICLE INSP METHOD. DURING MP INSP, NOTED ANOTHER CRACK, NOT DETECTED USING EDDY CURRENT. DECIDED TO PE RFORM MP INSP OF ALL RODS AND FOUND 3 MORE CRACKED. CRACKS APPEAR TO BE ON THE INNER SURFACE AND WOULD NOT BE DETECTABL E WITH NDT INSP PRESCRIBED IN THE MM. CURRENT INSPECTION REQUIREMENTS ARE NOT ADEQUATE FOR FINDING THESE TYPES OF DEFEC TS. CRACKS IDENTIFIED ARE ORIENTED LONGITUDINALLY O THE RODS AND VARY IN LENGTH FROM .500 IN TO 3.0 INCH. IT SHOULD BE NOTE THAT MAG PARTICLE INSP IS NOT A REQUIREMENT OF AIR FRAME MFG. (K) 2 L 7 2 4F 4 F RT A3EU E6WE 2007080700169 20070807 00169 CE 2007 8 7 2007FA0000634 1 20070520 G 7160 0750288 SUPPORT CESSNA 182 182E 2072712 CE CONT O470 O470R 17026 SO AIRBOX CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SO 11 2803Y 18253803 MECH DISCOVERED ON A 50 HR INSP, THE SUPPORT COLLAR ON THE AIRBOX MOUNTED TO THE CARBURETOR WAS CRACKED. THIS COULD LEA D TO THE SEPARATION OF THE AIRBOX FROM THE CARBURETOR AND LOSS OF POWER. PN 0750288 WAS REPLACED WITH NEW SUPPORT COLLA R PN 0750288-1 IAW SRM. (K) 1 H 7 1 3O 3 O NT 3A13 E273 2007080700171 20070807 00171 GL 2007 8 7 2007FA0000635 1 20070629 G 2420 646843 ALTERNATOR CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO HARTZL HCJ3Y PHCJ3YF1 GL ENGINE FAILED B T9ZR O OTHER O OTHER NR NOT REPORTED 1 NM 09 769PC 1619 FP3952B UPON RECEIPT OF CURRENT ALTERNATOR, NOTICED THAT SLIP-RING HOUSING WAS CLOCKED 180 DEGREES OUT OF ALIGNMENT OUT OF THE B OX. THIS PLANE HAS HAD SEVERAL REPAIRED ALTERNATORS INSTALLED ON IT. THE MOST RECENT ALTERNATOR HAD ONLY 131.1 HOURS B EFORE IT FAILED AND THE ONE PREVIOUS TO THAT ONE HAD 67.2 HOURS ON IT BEFORE IT FAILED. (K) 1 L 7 1 3O 3 O NT A00009CH E3SO 5 C P36EA 2007080700172 20070807 00172 SW 2007 8 7 2007FA0000636 1 20070701 G 6410 206016201127M BLADE BELL 206 206B 1181511 SW ALLSN 250B 250B* GL TAIL ROTOR DEPARTED D O OTHER D INFLIGHT SEPARATION CR CRUISE 1 SO 15 357DC 1803 THE CENTER TIP WEIGHT SLUNG OUT OF SUBJECT TAIL ROTOR BLADE DURING FLIGHT, CAUSING A VIOLENT VIBRATION. THE VIBRATION C AUSED (3) OF THE TAIL ROTOR GEAR BOX STUDS TO SHEAR BEFORE THE AIRCRAFT COULD AUTO ROTATE TO THE GROUND. IF THE HELICOP TER HAD NOT MADE IT TO THE GROUND WHEN IT DID THE OTHER STUD WOULD HAVE SHEARED AND THE TAIL ROTOR GEAR BOX WOULD HAVE L EFT THE AIRCRAFT AND THE RESULTS WOULD HAVE BEEN DISASTROUS. RECOMMEND THE TIP BLOCKS BE MFG FROM MATERIAL THAT CAN WIT HSTAND THE CENTRIFUGAL FORCES THAT ARE APPLIED TO THE TIP WEIGHTS DURING FLIGHT. RECOMMEND THAT HELICOPTER TAIL ROTOR BL ADE TIPS BE INSPECTED AS SOON AS POSSIBLE AND EVERY 100 HR INSPECTION. (K) 1 G 7 1 3U 3 T H2SW E10CE 2007080700173 20070807 00173 SO 2007 8 7 2007FA0000637 2 20070613 G 8520 SA640518 PISTON CESSNA 182 182H 2072718 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL NR1 CYLINDER FRACTURED D O OTHER O OTHER NR NOT REPORTED 1 EA 17 1858X 4765K06552 18255958 1308944R 733700 AFTER INSTALLING NEW CYLINDER ASSY SA47006S-A20P WITH NEW PISTON ASSY PN SA640518, WE WERE PERFORMING BREAK IN RUN AT LO W POWER, FIRST AT 800 RPM FOR 2 MIN. SHUTDOWN ENGINE, CLEANED FOULED PLUGS DUE TO OIL IN CYLINDER FROM ASSY. RAN ENGIN E AT 1000 RPM FOR 3 MIN. SHUTDOWN AND CLEANED SPARK PLUGS AGAIN. RESTARTED ENGINE AND ADVANCED TO 1200 RPM, THE CYLIND ER CLEARED OUT AND THEN STOPPED AFTER A FEW SECONDS. AFTER REMOVING THE OIL PAN AND NR 1 CYLINDER THE PISTON APPEARED T O HAVE FRACTURED ALONG A CASTING FAULT IN THE PISTON PIN BOSS. THE RESULTING DEBRIS BENT THE CAM SHAFT, BROKE BOTH CRAN KSHAFT HALVES. (K) 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2007080700174 20070807 00174 NE 2007 8 7 2007FA0000638 2 20070625 G 7250 BLADES UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206B 0 NE ENGINE DAMAGED B HDNR A UNSCHED LANDING E R Y VIBRATION/BUFFET PARTIAL RPM/PWR LOSS ENGINE STOPPAGE CR CRUISE 1 SW 03 911SV 0015 BB0113 DURING FLIGHT, A LOUD BANG WAS HEARD AND THEN ALL ENGINE INSTRUMENTS SHOWED AN INDICATION OF A TOTAL ENGINE FAILURE. TH E ENGINE WAS SECURED AND A SINGLE ENGINE LANDING WAS INITIATED WITHOUT INCIDENT. UPON INSPECTION, IT WAS NOTICED THAT T HE EXHAUST AREA OF THE ENGINE, THERE WERE PT ROTOR BLADES MISSING OR DAMAGED. THE ENGINE WILL BE SENT BACK TO THE MFG F OR EVALUATION. (K) 1 G 7 2 3U 3 U O H88EU E42NE 2007080700175 20070807 00175 CE 2007 8 7 2007FA0000639 1 20070507 G 3233 12810013 HOUSING CESSNA 172 172RG 2072438 CE LYC O360 O360* 41514 EA MCAULY 2D34C B2D34C220 GL MLG ACTUATOR CRACKED C O OTHER J WARNING INDICATION CL CLIMB 1 GL 09 4604V 172RG0337 L2232D38A 801046 ON A DUAL TRAINING FLIGHT, STUDENT AND INSTRUCTOR HEARD A NOISE WHEN LANDING GEAR WAS RETRACTED. LT LANDING GEAR REMAIN ED IN A PARTIALLY RETRACTED/ EXTENDED POSITION, UNABLE TO ACTUATE UP OR DOWN. THE LT LANDING GEAR ACTUATOR BODY HAD FAI LED (CRACKED) AT THE FWD MOUNTING BOLT HOLE, ALLOWING THE ACTUATOR BORE TO OPEN ENOUGH SO THAT PISTON WOULD NOT ENGAGE THE LANDING GEAR PIVOT SECTOR GEAR SUFFICIENTLY TO MOVE THE LANDING GEAR. (K) 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2007080700176 20070807 00176 SW 2007 8 7 2007FA0000640 1 20070702 G 3250 SOLENOID VALVE SWRNGN SA226 SA226T 8780122 SW GARRTT TPE331 TPE33110U 01514 WP NLG STEERING FAILED B O9IR K NONE O OTHER IN INSP/MAINT 1 NM 09 749L T306 THE NOSE WHEEL STEERING WAS TESTED PRIOR TO FLIGHT, AD TESTED SATISFACTORY. AT AROUND 60 TO 70 KNOTS DURING THE TAKEOFF ROLL, THE AC STEERING FAILED IN A MANOR THAT RESULTED IN THE AC PULLING HARD TO THE LEFT. USING HARD RT BRAKE AND RT R EVERSE THRUST THE AC WAS STOPPED BEFORE RUNNING OFF THE RUNWAY. WHEN THE SPEED LEVER WAS RETARDED THE STEERING , RE-ENG AGED, AS IT SHOULD HAVE, AND THE AC OPERATED NORMALLY. 2 L 7 2 4T 4 T RT A5SW E4WE 2007080800015 20070808 00015 CE 2007 8 8 2007FA0000641 1 20070706 G 2820 16864 LINE CESSNA 210 T210N 2073456 CE CONT O520 TSIO520R 17040 SO FUEL SYSTEM MISMANUFACTURED D O OTHER W INADEQUATE Q C NR NOT REPORTED 1 SW 13 4631C 394 21063582 NEW FUEL INJECTOR LINE NR 5 CYL RAM PMA REPLACEMENT. INSTALLED ON ENGINES, WELD DEFECT ALLOWED DEVIPER END BAIL TO COME LOOSE FROM LINE. NOTED FUEL LEAN ON TOP OF ENGINE AT ANNUAL 100 HR INSP. (K) 1 H 7 1 3O 3 O 3A21 E8CE 2007080800016 20070808 00016 CE 2007 8 8 2007FA0000642 1 20070703 G 2820 L2891948A LINE CESSNA 182 182T 2072703 CE LYC O540 IO540* 41532 EA FUEL SYSTEM LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 21 818CP 923 18281258 L2891948A FOUND HEAVY FUEL STAIN FROM OIL COOLER NR 5 INTAKE PIPE AND ON FIREWALL APPROVED TO BE NR 5 INTAKE PIPE. FURTHER INSPEC TION FOUND NR 5 FUEL INJECTION LINE LOOSE AT INJECTOR. FOUND AND SNUGGED SEVERAL OTHER INJECTOR LINES AT INJECTOR AND F LOW DIVIDER AD-02-01, AD LAST C/W 5-3-07. (K) 1 H 7 1 3O 3 O NT 3A13 1E4 2007080800017 20070808 00017 CE 2007 8 8 2007FA0000643 1 20070613 G 3246 G129 WHEEL CESSNA 172 R172K 2072431 CE NLG STRUT MISREPAIRED G O OTHER O OTHER TO TAKEOFF 1 GL 13 736MV 120 R1722642 DURING TAKEOFF FROM A GRASS STRIP AS THE AIRCRAFT APPROACHED 30 TO 40 KNOTS, BOTH NOSE WHEELS INSTALLED ON THE FLOATS FA ILED, CAUSING THE AIRCRAFT TO FLIP ON TO ITS BACK. UPON EXAMINATION OF THE FLOAT NOSE WHEEL STRUTS THE FAILURE OCCURRED AT THE WELD JOINT OF BOTH LT AND RT WHEEL STRUTS. IT APPEARS THAT THE WELDS DID NOT HAVE ADEQUATE PENETRATION. INVEST IGATION OF MFG IN PROCESS. (K) 1 H 7 1 3O 3A17 2007080700163 20070807 00163 CE 2007 8 7 2007FA0000646 1 20070719 G 2710 05232182 PUSHROD CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA AILERON BENT B K NONE O OTHER IN INSP/MAINT 1 EA 07 2277T 172S9958 AILERON PUSHROD WAS FOUND BENT DURING PREFLIGHT. REMOVED PUSHROD AND WENT TO INSTALL NEW ROD AND FOUND THAT ALL FOUR RO DS IN STOCK HAD BAD THREADS- PD WAS OVERSIZED. 1 H 7 1 3O 3 O NT 3A12 1E10 2007080800010 20070808 00010 EA 2007 8 8 2007FA0000647 2 20070720 G 8520 AE75089 PISTON CESSNA 172 172M 2072418 CE LYC O360 O360A4M 41514 EA NR 2 CYLINDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 27 20858 1522 17263857 L4988127A PISTON SKIRT CRACKED ON 2 CYLINDERS. 1 H 7 1 3O 3 O NT 3A12 E286 2007080800026 20070808 00026 2007 8 8 2007FA0000648 4 20070720 G 3457 GNS530W DISPLAY CESSNA 414 414A 2075907 CE GPS MALFUNCTIONED C O OTHER O OTHER CR CRUISE 1 WP 05 25 SETTING AN EVENT IN THE AUX PAGE FOR A FUTURE TIME CAUSES AUX EVENTS PAGE TO NO LONGER FUNCTION. SELECTING THIS PAGE CA USES THE NAV6, GPS SATELLITE STATUS PAGE TO DISPLAY FOR 1 SECOND, THEN NAV2 PAGE(MAP) TO BE SELECTED. AS A SIDE EFFECT, THE FLIGHT TIMER IS RESET EVERY TIME THE AUX PAGE IS ATTEMPTED TO BE SELECTED. IT APPEARS THAT THE FIRMWARE BECOMES LO ST, BUT RECOVERS. 1 L 7 2 3O A7CE 2007080800027 20070808 00027 CE 2007 8 8 2007FA0000651 1 20070722 G 2810 FUEL CAP CESSNA 185 185F 2072820 CE CONT O520 IO520D 17032 SO WING LEAKING P O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 13 5 18503193 FUEL LEAKING FROM BASE OF NEWLY INSTALLED PREMIUM FUEL CAPS. LOCATION ON WINGS IRRELEVANT. LEAK FROM BOTH IB AND OB CAPS . COMPLIED WITH MFG INSTRUCTIONS IAW VENT LOCATION WITHOUT EFFECT. EVIDENTLY NOT UNCOMMON PROBLEM, AS BLOGS ON MFG CLUB FORUM AND PILOTS ASSOC. FORUM WILL ATTEST. MFG SENT NEW O-RINGS, BUT HAVEN'T TRIED THEM. NEVERTHELESS, CAPS SHOULD BE F OOL-PROOF FROM FACTORY. HARDLY AN IMPROVEMENT OVER MY OLD MFG RAISED INLET CAPS. 1 H 7 1 3O 3 O 3A24 E5CE 2007080800049 20070808 00049 SO 2007 8 8 2007FA0000657 1 20070629 G 2720 480572 ROLL PIN PIPER PA42 PA421000 7104225 SO RUDDER PEDAL SHEARED B GW1R O OTHER O OTHER NR NOT REPORTED 1 EA 03 411BG 5362 425527004 PILOTS RT RUDDER PEDAL ROLL PINS SHEARED. REFERENCE IPC PN 761792, FIG. 103, INDEX 14, PN 480572. FAILURE MAY CAUSE LO SS OF DIRECTIONAL CONTROL OR BRAKING ACTION DURING GROUND OPERATION. (K) 1 L 7 2 4T RT A23SO 2007080800050 20070808 00050 CE 2007 8 8 2007FA0000658 1 20070612 G 2820 052355912 VENT CESSNA CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA LT WING TANK OBSTRUCTED D O OTHER O OTHER NR NOT REPORTED 1 SW 07 52119 9458 0301 17274418 L1058239A ENGINE QUIT IN FLIGHT WITH HALF TANK OF FUEL REMAINING. UPON VISUAL INSPECTION OF LT WING, FOUND THE FUEL VENT LINE PN 052355912 OBSTRUCTED WITH INSET REMAINS (WASP). PHYSICALLY REMOVED OBSTRUCTION AND OPS TESTED ENGINE ON ALL TANK SETTIN GS. UPON SUCCESSFUL OPS CHECK OF FUEL SYSTEM, MADE LOG ENTRY AND RETURNED THE AIRCRAFT TO SERVICE. AIRCRAFT HAS SUCCES SFULLY FLOWN 50 HRS SINCE 6/12/07 WITH NO FURTHER INCIDENT. 1 H 7 1 3O 3 O NT 3A12 E274 2007080800051 20070808 00051 CE 2007 8 8 2007FA0000659 1 20070712 G 3230 HMXL6G ROD END BEECH 58 58 1152740 CE CONT O520 IO520* 17032 SO NLG UNSERVICEABLE G K NONE O OTHER IN INSP/MAINT 1 AL 01 820GW TH13 DURING EXAMINATION OF AIRCRAFT POST INCIDENT, IT WAS DISCOVERED THAT ROD END (PN HMXL6G) ATTACHED TO THE NOSE GEAR RETRA CT ARM (PN 35825172-2) WAS SHEARED OFF BELOW THE BEARING. IT APPEARS THE FAILURE STARTED IN A CRACK IN THE THREADS. TH IS MOST LIKELY RELEASED THE OVER CENTER TENSION ON THE NOSE GEAR DOWNLOCK ALLOWING THE NOSE GEAR TO RETRACT AND SUBSEQUE NTLY THE MAIN LANDING GEAR. RECOMMEND ANNUAL PENETRANT INSPECTION OF ALL LANDING GEAR RETRACTION ROD ENDS. (K) 1 L 7 2 3O 3 O 3A16 E5CE 2007080800052 20070808 00052 EA 2007 8 8 2007FA0000660 2 20070526 G 8530 EXHAUST VALVE PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA NR 4 CYLINDER BROKEN D O OTHER O OTHER NR NOT REPORTED 1 SO 13 7342J 3339 941 2824671 L2283027A NR 4 EXHAUST VALVE BROKE DURING FLIGHT, DAMAGING PISTON CAUSING OIL TO LEAK OUT EXHAUST PORT CREATING OIL SMOKE. (K) 1 L 7 1 3O 3 O 2A13 E274 2007080800057 20070808 00057 SO 2007 8 8 2007FA0000661 1 20070701 G 1210 FUEL MAULE M5 M5210C 5460134 SO CONT O360 IO360A 17025 SO CONTAMINATED D A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 AL 05 62045 3 6078C WHILE PERFORMING BI-ANNUAL REVIEW. ON LAST TAKEOFF, THE ENGINE BEGAN TO RUN ROUGH. ENGINE DRIVEN FUEL PUMP FAILED AND INSTALLED A FRESHLY OVERHAULED PUMP. ATTEMPTED A RUN UP WITH THE SECOND PUMP AND FOUND THE COVER PLATE AT THE MIXTURE C ONTROL LEVER TO BE LEAKING. REMOVED SECOND PUMP. OVERHAUL SHOP FOUND EVIDENCE OF WATER IN THE FUEL SYSTEM, LIGHT RUST IN THE ORIGINAL PUMP BODY, AND A WHITE FILM UNDER THE PRESSURE VALVE SEAT THAT DISINTEGRATED INTO A WHITE POWDER WHEN I T DRIED. THE PUMP WAS NOT ABLE TO PRODUCE THE PROPER PRESSURE WITH THIS FILM HOLDING THE VALVE OPEN. DECIDED TO FLUSH THE FUEL SYSTEM AND TRY TO DETERMINE THE SOURCE OF CONTAMINATION. FLUSHED ALL OF THE FUEL LINES. THERE WAS LIGHT S 1 H 7 1 3O 3 O 3A23 E1CE 2007080800058 20070808 00058 2007 8 8 2007FA0000662 1 20070628 G 8011 MZ422 STARTER BURNED D O OTHER O OTHER NR NOT REPORTED 1 SW 99 STARTER BURNED UP ON TEST CELL RUN. (K) 2007080800061 20070808 00061 CE 2007 8 8 2007FA0000664 1 20070628 G 3213 07416302 SPRING ASSY CESSNA 182 182R 2072731 CE CONT O470 O470* 17026 SO AXEL FITTING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 09 5544N 14045 18267782 DURING NDI OF MAIN LANDING GEAR SPRING ASSY, THE RT FITTING WAS FOUND CRACKED. DURING WFPT FOR ASTM E1417. PART WAS RE PLACED WITH A SERVICEABLE UNIT. SUSPECT CRACK WAS DUE TO CORROSION BETWEEN THE SPRING AND ALUMINUM FITTING. (K) 1 L 7 1 3O 3 O NT 3A13 E273 2007080800064 20070808 00064 CE 2007 8 8 2007FA0000665 1 20070726 G 1100 PLACARD CESSNA 172 172S 2072439 CE CABIN INCORRECT C K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 07 AIRCRAFT WITH AVIONICS: LOCATION OF INTERIOR ELT PLACARD IN BAGGAGE COMPARTMENT INDICATES THAT THE ELT IS BEHIND THE LOW ER ACCESS PANEL TO THE AFT FUSELAGE. THAT IS INCORRECT. THE ELT ACCESS IS FROM THE UPPER PANEL. REMOVED PLACARD AND F ABRICATED NEW PLACARD AND PLACED IT ON THE UPPER ACCESS PANEL. 1 H 7 1 3O NT 3A12 2007080800066 20070808 00066 EA 2007 8 8 2007FA0000667 2 20070726 G 8530 AEL85099 CYLINDER HEAD HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA NR 2 CYLINDER SEPARATED B A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 WP 27 2021G 1046 0095 L3725036A NR 2 CYLINDER HEAD SEPARATED FROM CYLINDER BARREL IN FLIGHT. 1 G 7 1 3O 3 O O 4H12 E286 2007080800068 20070808 00068 EU 2007 8 8 2007FA0000669 2 20070710 G 7200 DN3351053050 DAMPER CFMINT CFM56 CFM563C1 13802 EU ENGINE FAILED B UOXR O OTHER O OTHER NR NOT REPORTED 1 SO 19 ESN725219 WAS NOTIFIED BY TEST CELL OPERATOR THAT DAMPER ASSY PN DN335-105-305-0 CAME APART DURING ENGINE TEST CELL OPERATIONS OF ENGINE DURING ENGINE TEST AND AFTER POST ENGINE ADJUSTMENT. THE DAMPER ASSY WAS DISCOVERED IN THE ENGINE INLET AREA. (K ) 4 F E21EU 2007080800069 20070808 00069 CE 2007 8 8 2007FA0000670 1 20070309 G 2460 IN31X100050CM358 MASTER SWITCH CESSNA 402 402C 207590R CE FAILED C O OTHER O OTHER CL CLIMB 1 SW 99 J8VBL 0640 LOST POWER TO THE AVIONICS BUSS. CARRIED OUT THE REQUIRED CHECKS AND TRIED REPEATEDLY TO RESTORE POWER TOT THE AVIONICS BUSS VIA THE EMERGENCY AVIONICS BUSS SWITCH, TO NO AVAIL. LANDED, CONTACTED MAINTENANCE, WHO CONFIRMED THE AVIONICS BU SS FAILURE. (K) INVESTIGATE AVIONICS BUSS SYS FAILURE AND FOUND AVIONICS MASTER SWITCH DEFECTIVE. MASTER SWITCH REMOVE D AND REPLACED WITH NEW ITEM IAW MEB 05-1. FUNCTION CHECK OF MASTER AVIONICS SWITCH AND EMERGENCY AVIONICS BUSS SWITCH CARRIED OUT SATISFACTORY. (K) 1 L 7 2 3O A7CE 2007080700033 20070807 00033 EU 2007 8 7 2007FA0000671 1 20070727 G 5310 A741210N BRIDGE LET L23 L23 1360308 EU CRACKED B O OTHER O OTHER NR NOT REPORTED 1 NM 03 431BA 1693 029013 DURING A ROUTINE DYE-PENETRANT INSPECTION ON TG-10B CRACKS WERE DISCOVERED AT SEVERAL WELDS ON THE A741 210N BRIDGE ASSE MBLY. A REPLACEMENT BRIDGE ASSY CANNIBALIZED FROM ANOTHER TG-10B IN AN EFFORT TO PLACE THE FIRST NOTED AIRCRAFT BACK IN SERVICE. AS A PRECAUTIONARY STEP, DECIDED TO DYE-PENETRANT THE CANNIBALIZED ASSEMBLY AND DISCOVERED IT TOO WAS CRACK ED. DECIDED TO INSPECT THE REST OF THE ACFT. 12 OUT OF 12 ACFT REVEALED CRACKS. 1 K 0 0 RC G24EU 2007080800093 20070808 00093 EU 2007 8 8 2007FA0000672 1 20070727 G 5101 A741210N BRIDGE LET L23 L23 1360308 EU ZONE 100 CRACKED B O OTHER O OTHER NR NOT REPORTED 1 NM 03 431BA 1693 029013 ON JULY 23, 2007 DURING A ROUTINE DYE-PENETRANT INSPECTION ON TG-10B (L-23 SUPER BLANIK, S/N 029013) CRACKS WERE DISCOVE RED AT SEVERAL WELDS ON THE A741 210N BRIDGE ASSEMBLY. IT IS A MAINTENANCE MANUAL REQUIREMENT THAT THIS PART BE DYE-PEN ETRANT INSPECTED EVERY 1000 HOURS. A REPLACEMENT BRIDGE ASSEMBLY WAS CANNIBALIZED FROM ANOTHER TG-10B (L23, S/N 029015) IN AN EFFORT TO PLACE THE FIRST NOTED AIRCRAFT BACK IN SERVICE. AS A PRECAUTIONARY STEP, WE DECIDED TO DYE-PENETRANT T HE CANNIBALIZED ASSEMBLY AND DISCOVERED IT TOO WAS CRACKED. AT THIS POINT IT WAS DECIDED TO INSPECT THE REST OF THE AIR CRAFT HERE AT USAFA. 12 OUT OF 12 AIRCRAFT REVEALED CRACKS. 1 K 0 0 RC G24EU 2007080800096 20070808 00096 CE 2007 8 8 2007FA0000674 1 20070717 G 2910 SA7670024001 LINE RAYTHN DH125 HAWKER800XP 7150012 CE HYD SYSTEM RUPTURED C H DEACTIVATE SYST/CIRCUITS K J FLUID LOSS WARNING INDICATION CL CLIMB 1 EA 27 50AE 1848 258650 FLEXIBLE HYDRAULIC LINE TO THE RT MAIN GEAR IB DOOR ACTUATOR RUPTURED IN FLIGHT. CREW EXTENDED LANDING GEAR AND FLAPS US ING THE AUXILIARY HYDRAULIC SYSTEM AND LANDED WITHOUT INCIDENT. DURING INSPECTION BY MAINTENANCE DEPARTMENT NO APPARENT CAUSE WAS DETERMINED FOR THE LINE FAILURE. MFG HAS BEEN ADVISED OF THE DEFECT. NEW HYDRAULIC LINE WAS INSTALLED, SYSTEM WAS SERVICED WITH FLUID AND BLED, AIRCRAFT WAS RETURNED TO SERVICE. 2 L 7 2 4F RT A3EU 2007080800113 20070808 00113 CE 2007 8 8 2007FA0000675 1 20070712 G 5730 08220009 SKIN CESSNA 340 340A 2076405 CE CONT O520 TSIO520* 17040 SO LT WING CRACKED D O OTHER O OTHER NR NOT REPORTED 1 CE 07 8647K 6580 340A0605 CRACK IN THE TOP SKIN OF THE LT WING AT THE LANDING GEAR SIDE BRACE ATTACHMENT LOCATION, APPROXIMATELY WS 63.45. THE SK IN IS 2024-T63 ALUMINUM, .032 THICK. THE CRACK IS ABOUT 3 INCHES LONG OR LONGER. CANNOT DETERMINE THE TOTAL LENGTH OF THE CRACK. (K) 1 L 7 2 3O 3 O 3A25 E8CE 2007080800111 20070808 00111 EA 2007 8 8 2007FA0000677 2 20070715 G 8530 AEL85099IR CYLINDER HEAD HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA ENGINE SEPARATED G A UNSCHED LANDING E D K VIBRATION/BUFFET INFLIGHT SEPARATION FLUID LOSS CL CLIMB 1 WP 27 2021G 1046 1046 0095 L3725036A 2 NR CYLINDER HEAD ASSEMBLY APPEARS TO HAVE FAILED DURING FLIGHT RESULTING IN A SEVERE ENGINE VIBRATION AND A FORCED LAN DING. EXAMINATION OF UPPER HALF OF FAILED CYLINDER ASSEMBLY REVEALS THAT A CRACK OCCURRED AND PROPAGATED SYMMETRICALLY A ROUND THE CYLINDER APPROXIMATELY .3750 BENEATH WHERE THE CYLINDER BARREL MEETS THE CYLINDER HEAD. NO INTERNAL CYLINDER / PISTON DAMAGE WAS VISUALLY OBSERVED. 1 G 7 1 3O 3 O O 4H12 E286 2007080800110 20070808 00110 GL 2007 8 8 2007FA0000678 1 20070624 G 3230 1956750 SHUTTLE VALVE BLANCA 17 1730A 1220433 GL CONT O520 IO520K 17032 SO HARTZL HCC3Y HCC3YF1 GL MLG MALFUNCTIONED G O OTHER O OTHER LD LANDING 1 SW 01 8847V 1527 4 30359 THE AIRCRAFT LOST ELECTRICAL POWER AND PILOT TRIED TO EXTEND THE LANDING GEAR USING THE EMERGENCY LEVER. THE EMERGENCY LOWERING OF THE LANDING GEAR DID NOT TAKE PLACE AND THE PILOT HAD TO LAND THE AIRCRAFT WITH THE LANDING GEAR IN THE FULL UP POSITION. DAMAGE; PROP STRIKE, LOWER FUSELAGE SKIDDING DAMAGE, LOWER FUSELAGE FUEL DRAIN GROUND OFF, SUDDEN STOPPAG E OF THE ENGINE. 1 L 7 1 3O 3 O A18CE E5CE 5 C P25EA 2007082100024 20070821 00024 SW 2007 8 21 2007FA0000680 1 20070729 G 7933 35C155103 SENSOR ECLIPS EA500 ECLIPSEEA500 3350000 SW PW610FA OIL TEMP FAULTY C O OTHER O OTHER TX TAXI/GRND HDL 1 EA 27 116DJ 32 000021 LA0009 RT ENG HIGH OIL TEMPERATURE CAS MESSAGE UPON LANDING. EXCEEDANCE (OIL TEMP) AFTER LANDING-ENGINE SHUTDOWN DURING TAXI. F OUND FAULTY MOT/MOP SENSOR REPLACED WITH NEW UNIT AND OPERATIONALLY CHECKED SATISFACTORY IAW EMM 79-30-04. 1 L 7 2 4J RT A00002AC 2007080800109 20070808 00109 NE 2007 8 8 2007FA0000681 2 20070731 G 8560 13814 SEAL PWA R1340 R1340AN1 52016 NE SUPERCHARGER LEAKING B O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 15 DISASSEMBLY OF THE ENGINE AND OR REAR SECTION AFTER CUSTOMERS REPORTED SMOKING AND INCREASE IN OIL CONSUMPTION. DURING T HE DISASSEMBLY IT WAS FOUND THAT BLOWER SEALS HAVE FAILED AND BEEN LEAKING. 3 R 5E2 2007082100064 20070821 00064 CE 2007 8 21 2007FA0000683 1 20070712 G 5730 08220009 SKIN CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520* 17040 SO RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 07 5152J 3400542 CRACK IN THE TOP SKIN OF THE RT WING AT THE LANDING GEAR SIDE BRACE ATTACHMENT LOCATION, APPROX WS 63.45. THE SKIN IS 2 024-T3 ALUMINUM, .032 THICK. THE CRACK IS ABOUT 4.5 INCHES LONG. (K) 1 L 7 2 3O 3 O 3A25 E8CE 2007082100065 20070821 00065 EA 2007 8 21 2007FA0000684 2 20070712 G 8520 CRANKSHAFT CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE CORRODED B YYBR K NONE O OTHER IN INSP/MAINT 1 GL 03 175AF 4363 17281175 L3097351A FOUND CRANKSHAFT TO BE PITTED, LAST INSPECTION WAS DONE BY MFG (4) YEARS AGO. THIS ENGINE HAD HIGH UTILIZATION AND FREQ UENT OIL CHANGES. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2007082100067 20070821 00067 SO 2007 8 21 2007FA0000685 2 20070712 G 8550 ES48109 OIL FILTER CONT O520 IO520M 17032 SO ENGINE CONTAMINATED C K NONE O OTHER IN INSP/MAINT 1 GL 11 560171 THE ENGINE OIL SYSTEM WAS CONTAMINATED BY OIL FILTER SEAL DEBRIS. (K) ON DISASSEMBLY OF THE ENGINE RUBBER DEBRIS WAS FOU ND: IN THE OIL PASSAGE THAT FEEDS THE STARTER ADAPTER WITH THE ADAPTER PILOT BEARING PLUGGED. UPON SPLITTING OF THE EN GINE CASE DEBRIS WAS FOUND IN THE OIL PASSAGE TO THE NR 3 MAIN BEARING. BOTH OIL COOLING JETS TO NR 3 MAIN BEARING WERE PLUGGED WITH RUBBER DEBRIS. THE RIGHT WAS PLUGGED WITH A PIECE .6250 INCH LONG AND THE LT WITH A PIECE .1875 INCH LONG . ONE PIECE OF RUBBER DEBRIS WAS LOCATED IN THE OIL PASSAGE TO THE NR 5 BEARING. (K) 3 O E5CE 2007082100068 20070821 00068 CE 2007 8 21 2007FA0000686 1 20070713 G 5510 45A2110422 RIB BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE HORIZONTAL STAB CRACKED B KX5R K NONE O OTHER IN INSP/MAINT 1 GL 15 52AW 4500 RK115 HORIZONTAL STABILIZER LEADING EDGE IB RIBS ARE CRACKED AT THE ROLLER BRACKET ATTACHMENT POINTS. SAFETY COMMUNIQUE NR 70 IS ONLY PUBLISHED CRITERIA CONCERNING THIS PROBLEM. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007082100070 20070821 00070 GL 2007 8 21 2007FA0000687 1 20070724 G 3230 105932B POWERPACK BLANCA 17 1731A 1220435 GL LYC O540 IO540K1E5 41532 EA MLG BURNED OUT D O OTHER J WARNING INDICATION CL CLIMB 1 SW 15 14746 18 7532156 THIS COMPONENT WAS INSTALLED FRESHLY OVERHAULED ON APRIL 6, 2006 AND HAS A TOTAL IN USE TIME OF 18.0 HOURS. AFTER TAKEO FF THE PILOT NOTICED THE LANDING GEAR WOULD NOT RETRACT. TROUBLESHOOTING OF THE LANDING GEAR SYSTEM FINDS THE HYDRAULIC POWER PACK MOTOR WINDINGS ARE OPEN, MOTOR WILL NOT RUN. UNIT WAS OVERHAULED UNDER WO NR AH-16326. (K) 1 L 7 1 3O 3 O A18CE 1E4 2007080800114 20070808 00114 WP 2007 8 8 2007FA0000688 1 20070710 G 2400 BRACKET HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA ALTERNATOR LOOSE C O OTHER O OTHER NR NOT REPORTED 1 WP 05 9988F S1791 RL2203051A ALTERNATOR BRACKET LOOSE AT ENGINE BOSS. BOLT CAUSES DAMAGE TO ENGINE CRANKCASE WHEN LOOSE. FRETTING OF ARM AND ENGINE CRANKCASE OCCURS. (K) 1 G 7 1 3O 3 O 4H12 1E10 2007082100072 20070821 00072 CE 2007 8 21 2007FA0000689 1 20070701 G 2497 S159660L CIRCUIT BREAKER CESSNA 172 172M 2072418 CE LYC O320 O320* 41508 EA COCKPIT FAILED D K NONE O OTHER IN INSP/MAINT 1 CE 01 80213 17266449 PILOT STATED SMOKE IN COCKPIT. INSPECTION REVEALED ALTERNATOR OUTPUT C/B FAILED, ALTERNATOR HAD BROKEN AND LOOSE PARTS INTERNALLY, AND VOLTAGE REGULATOR FAILED. OPENED C/B AND FOUND INTERNAL PARTS HAD MELTED CAUSING SMOKE. NO SIGNS OF WI RE OVERHEATING, OR SECONDARY DAMAGE WAS FOUND. (K) 1 H 7 1 3O 3 O NT 3A12 E274 2007082100074 20070821 00074 CE 2007 8 21 2007FA0000690 1 20070707 G 5312 07126161 BULKHEAD CESSNA 182 182K 2072724 CE CONT O470 O470* 17026 SO BS 230 CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 28 2787Q 4575 18257987 DURING INSPECTION OF THE AFT TAILCONE BULKHEAD (STATION 230.187) A CRACK APPROX .375 INCH LONG WAS DISCOVERED. THE CRAC K LOCATION WAS ON THE LT SIDE EMANATING FROM THE RUDDER CUTOUT HOLE AND PROGRESSING TOWARD THE BULKHEAD FLANGE. (K) 1 H 7 1 3O 3 O NT 3A13 E273 2007082100076 20070821 00076 CE 2007 8 21 2007FA0000691 1 20070625 G 2420 991059111RX ALTERNATOR CESSNA 182 182T 2072703 CE LYC O540 IO540AB1A5 EA ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 03 232AF 573 18281180 L2860348A AC ARRIVED AT 1R4 WITH A FAILED ALTERNATOR. SYSTEM WAS TESTED TO CONFIRM THAT THE ALTERNATOR WAS THE PROBLEM. ON 6/25/ 07 THE ALTERNATOR IN QUESTION WAS REMOVED FROM THE AC. UPON REMOVING THE ALTERNATOR THE TECHNICAN FOUND THE SAFETY LOCK WIRE FOR THE ALTERNATOR HOUSING HALVES WAS BROKEN AND ONE OF THE FOUR CAP SCREWS WAS MISSING AND THE OTHER (3) WERE LOO SE. THE AC WAS INSPECTED AGAIN TO DETERMINE IF ANY OTHER PART COULD HAVE COME IN CONTACT WITH THE ALTERNATOR TO CAUSE T HE SAFETY LOCK WIRE TO BREAK. NO CONFLICTS WERE NOTED DURING THIS INSPECTION. DIGITAL PICTURES HAVE BEEN TAKEN FOR REC ORD AND ARE AVAILABLE UPON REQUEST. (K) 1 H 7 1 3O 3 O NT 3A13 1E4 2007080800116 20070808 00116 SW 2007 8 8 2007FA0000692 1 20070706 G 5302 206020123048 RIB BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TAIL BOOM CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 05 245AR 4398 DURING THE COURSE OF A SCHEDULED INSPECTION, THE RT HORIZONTAL STABILIZER WAS REMOVED TO TROUBLESHOOT A PROBLEM WITH AN AUXILIARY STROBE LIGHT THAT IS ATTACHED TO THE STABILIZER. DURING REMOVAL, THE FLANGE ON THE IB RIB THAT ATTACHES THE S TABILIZER TO THE TAILBOOM WAS FOUND CRACKED AND SEPARATED INTO 2-PIECES. DUE TO THE LOCATION OF THE CRACK IT WAS NOT VI SIBLE WITH THE STABILIZER INSTALLED. (K) 1 G 7 1 3U 3 U H2SW E4CE 2007082400138 20070824 00138 EA 2007 8 24 2007FA0000693 3 20070621 G 6110 BOLT PIPER PA18 PA18150 7101828 SO LYC O360 O360* 41514 EA SNSNCH W80 W80CM8 EA PROPELLER LOOSE H O OTHER O OTHER NR NOT REPORTED 1 GL 17 530AK 184385 AF5140 PILOT REPORTED SLIGHT VIBRATION DURING FLIGHT OF APPROX (1) HOUR. WHEN POWER WAS REDUCED FOR LANDING, VIBRATION BECAME MORE EVIDENT. INITIAL INSP FOUND (1) PROP BOLT HAD COME OUT FWD AND THROUGH SPINNER AND PROP WAS LOOSE. WITH REMOVAL O F SPINNER, FOUND (2) BOLTS BACKED OUT, (1) THROUGH THE SPINNER AND (1) NEXT TO IT. (2) BOLTS REMAINED SAFETIED, BUT NOT TIGHT. THE REMAINING PAIR OF BOLTS, THE SAFETY WIRE WAS BROKEN BETWEEN THE BOLTS AND THE BOLTS WERE BACKED OUT APPROX (1) INCH. AFTER COMPLETE REMOVAL OF PROP, WHICH REQUIRED CUTTING THE HEAD OFF OF (1) BOLT, THE ATTACHMENT BUSHING FOR T HIS BOLT WAS BROKEN OFF FLUSH WITH THE CRANKSHAFT FLANGE. ANOTHER ATTACHMENT BUSHING WAS ALSO BROKEN OFF, FLUSH WITH TH 1 H 7 1 3O 3 O 1A2 E286 5 N P27NE 2007082100142 20070821 00142 CE 2007 8 21 2007FA0000695 1 20070718 G 5311 SPAR CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO MLG WW DAMAGED G W1NR O OTHER O OTHER NR NOT REPORTED 1 SW 11 60WH 340A0083 WHILE INVESTIGATING A NOISE IN THE LANDING GEAR ACTUATOR GEARBOX, IT WAS DISCOVERED THA THE AN3-6A BOLTS ATTACHING THE A CTUATOR MOUNTING BRACKET, PN 50110133, TO THE FRONT CENTER SPAR WERE LOOSE. AN ATTEMPT TO TIGHTEN THE BOLTS REVEALED TH AT THE NUTPLATES INSIDE THE SPAR WERE STRIPPED. THE NUTPLATES ARE NOT REFERENCED IN THE IPM AND APPEARS HAVE BEEN INSTA LLED INSIDE THE SPAR DURING THE MFG PROCESS (INACCESSIBLE). AS A RESULT OF THE ABOVE CONDITION, WHEN THE GEAR IS RAISED OR LOWERED, THE BRACKET AND GEARBOX PULL AWAY FROM THE FWD CENTER SPAR AND TRANSMIT ALL THE FORCES TO THE AFT ATTACHMEN T BULKHEAD, FLEXING THAT BULKHEAD BY MORE THAN .1250 INCH. NO INSTRUCTIONS FOR REPLACEMENT OF NUTPLATES IN MM. (K) 1 L 7 2 3O 3 O 3A25 E8CE 2007082100267 20070821 00267 EA 2007 8 21 2007FA0000697 2 20070711 G 7414 M3816 CONDENSER SLICK HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA LT MAGNETO DISCONNECTED B K NONE O OTHER IN INSP/MAINT 1 NM 05 7508H 63008049 S1628 2594851A SPRING CLIP ON TERMINAL WIRE CAME OFF ALLOWING WIRE TO DISCONNECT. (K) 1 G 7 1 3O 3 O 4H12 1E10 2007082100268 20070821 00268 SO 2007 8 21 2007FA0000698 2 20070730 G 8530 TISN712ACA CYLINDER BEECH 55 D55 1152730 CE CONT O520 IO520CB 17032 SO NR 6 CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 69RP 744 TE766 NR 6 CYLINDER WAS NEW ECI REV 3 E SERIES CRACKED BETWEEN FINS 1-3 BEHIND FUEL INJECTOR. THIS IS 6TH ECI REV 3 E SERIES TO CARCK IN THE SAME LOCATION. (K) 1 L 7 2 3O 3 O 3A16 E5CE 2007082100269 20070821 00269 CE 2007 8 21 2007FA0000699 1 20070703 G 2910 EM0159 SHUTOFF VALVE RAYTHN 390 390 7150030 CE HYD SYSTEM JAMMED B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 18RF RB127 PILOT REPORTED RT ENGINE HYDRAULIC SHUTOFF VALVE WOULD NOT CLOSE FOLLOWING PREFLIGHT CHECKS. FOUND VALVE ASSY STUCK OPE N. REPLACED VALVE ASSY WITH NEW VALVE ASSY, OPERATIONS NORMAL. VALVE ASSY (PN 45AS65014003) HAVE NOTICED THESE VALVE A SSY TENDING TO FAIL WITH SHORT TIE SINCE NEW IN MFG INSTALLATIONS. VALVE ASSY SEEMS FAIRLY RELAIBLE WHEN USED IN OTHER INSTALLATIONS. (K) 1 L 7 2 3F RT A00010WI 2007082100270 20070821 00270 CE 2007 8 21 2007FA0000700 1 20070711 G 3220 04425037 FORK CESSNA 150 152 2071835 CE LYC O235 O235* 41505 EA NOSE GEAR CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SO 05 68246 15282208 DURING INSPECTION, FOUND NOSE GEAR FORK CRACKED (1.5 INCH LONG) ON LT UPPER RADIUS OF FORK. AIRCRAFT IS USED FOR TRAINI NG. (K) 1 H 7 1 3O 3 O NT 3A19 E223 2007082100272 20070821 00272 EU 2007 8 21 2007FA0000701 1 20070709 G 3233 ROD ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE731* 01518 WP MLG ACTUATOR CRACKED B X6UR O OTHER O OTHER TX TAXI/GRND HDL 1 SW 15 40TA 11851 194 75131 (REF CNTRL NR WW1045) RECOVERED AIRCRAFT FROM TAXI WAY AFTER A LANDING WITH NO MLG GREEN LIGHTS. LT GEAR STARTED RETRA CTING DURING TAXI. FOUND LT AFT GEAR RETRACT ACTUATOR PISTON ROD BROKEN INSIDE PISTON WHICH HAD CAUSED A MIS-DIRECT OF GEAR DOWN FLOW TO ROUTE INTO RETURN AND UNLOCKING THE GEAR JURY BRACE. THE PISTON ROD HAD BEEN CRACKED FOR A PERIOD OF TIME APPROX .3333 THROUGH PRIOR FAILURE. (K) 2 M 7 2 4F 4 F A2SW E6WE 2007082100146 20070821 00146 SW 2007 8 21 2007FA0000702 1 20070803 G 3250 S18233 BEARING BBAVIA 7 7GCB 2110130 SW LYC O320 O320* 41508 EA STEERING ROD CRACKED G O OTHER O OTHER LD LANDING 1 AL 01 2423 3342 7GCB55 NOSE LANDING GEAR STEERING ROD END BEARING (P/N S-1823-3) FAILED IN THREADED PART OF ROD, ALLOWING NOSE GEAR TO TURN SID EWAYS, RESULTING IN EXCESSIVE SIDE LOAD ON NOSE LANDING GEAR ASSEMBLY, CAUSING IT TO FAIL AND SEPARATE FROM THE AIRCRAFT RESULTING IN MINOR DAMAGE TO COWLING, PROPELLER, EXHAUST PIPES. THIS ROD END BEARING SHOWS SIGNS OF CORROSION, PITTING AND IS PROBABLY THE ORIGINAL 1963 PART. 1 H 7 1 3O 3 O A759 E274 2007082100171 20070821 00171 CE 2007 8 21 2007FA0000703 1 20070806 G 3411 STATIC LINE LEAR 35 35A 5170602 CE GARRTT TFE731 TFE731* 01518 WP COCKPIT MISINSTALLED B K NONE O OTHER IN INSP/MAINT 1 CE 09 621RB 211 THIS RVSM AIRCRAFT HAD AN ALTIMETRY SYSTEM SPLIT. CONTACTED STC GROUP HOLDER FOR PROPER ROUTING OF STATIC SYSTEM PLUMBIN G. FOUND CO-PILOTS STATIC SYSTEM INSTALLATION WAS NOT CROSS-COUPLED WITH PILOTS SYSTEM. INSTALLED FABRICATED HOSES TO TH E CO-PILOTS SYSTEM TO MEET THE INTENT OF STC NR ST00563DE-D IAW MASTER DOCUMENT LIST. CO-PILOTS STATIC SYSTEM NOT INSTA LLED CORRECTLY AT STC INSTALLATION OR SYSTEMS HAVE BEEN ALTERED/MODIFIED POST-STC AND DID NOT FOLLOW APPROVED DRAWINGS. 2 L 7 2 4F 4 F A10CE E6WE 2007082100194 20070821 00194 NE 2007 8 21 2007FA0000704 2 20070809 G 7310 LINE BOEING 737 7373T0 1384582 NM GE CFM56 CFM563B1 13802 NE FUEL CONTROL LEAKING D O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 SO 19 1732 320 23372 FLOAT STICKS, CAUSING FUEL TO COME OUT OF CARBURETOR SPLIT LINE. LEAKING FUEL FROM GASKET. 2 L 7 2 4F 4 F RT A16WE E2GL 2007082100195 20070821 00195 SO 2007 8 21 2007FA0000705 1 20070809 G 2434 KELLY4111810 ALTERNATOR PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA ENGINE FAILED D O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 SO 19 17324 17 287916050 ALTERNATOR FAILED AFTER 17.6 HOURS. 1 L 7 1 3O 3 O 2A13 E274 2007082100197 20070821 00197 SO 2007 8 21 2007FA0000706 1 20070809 G 2434 KELLY4111810 ALTERNATOR PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 19 17324 174 287916050 ALTERNATOR FAIL AFTER 174 HOURS OF NORMAL OPERATION. 1 L 7 1 3O 3 O 2A13 E274 2007090600030 20070906 00030 WP 2007 9 6 2007FA0000708 1 20070813 G 5250 LOCK DOUG DC8 DC8* WP COCKPIT DOOR MALFUNCTIONED C O OTHER O OTHER NR NOT REPORTED 1 SW 99 NOTIFY BY AIR SECURITY REPORT THAT OUR COCKPIT LKD SYSTEM INFORMS US ONLY IF IT'S ARMED OR NOT, BUT NOT IF THE DOOR IS C ORRECTLY CLOSED AND LOCKED. DURING ONE OF THE LAST FLT'S MY COCKPIT DOOR HAS BEEN OPENED BY THE PURSER WITHOUT MY PERMI SSION. THE DOOR SEEMED CLOSED BUT IT WASN’T AND HE COULD OPEN IT EASILY. IT IS UNSAFE FOR US ON BOARD AND FOR ALL PEOP LE THAT WE FLY OVER.EUROPEAN AVIATION SAFETY AGENCYPOSTFACH 10 12 53D-50452 KOELN, GERMANYI'M MD80 CPT OF ALITALIA , I NOTIFY BY AIR SECURITY REPORT THAT OUR COCKPIT LKD SYSTEM INFORMS US ONLY IF IT'S ARMED OR NOT, BUT NOT IF THE DOOR IS CORRECTLY CLOSED AND LOCKED.DU 2 L 7 4 4J F 4A25 2007082100289 20070821 00289 EA 2007 8 21 2007FA0000710 2 20070603 G 7322 30804 FLOAT AMTR COZY COZY 05613R8 GL LYC O290 O290* 41506 EA CARBURETOR SATURATED B K NONE O OTHER IN INSP/MAINT 1 EA 11 369CZ ENGINE FAILED ON SHORT FINAL DUE TO CARB FLOODING FLOAT IN CARB HALF FULL OF GAS. 1 M 7 1 3O 3 O NT EXPA1M71 E229 2007082400247 20070824 00247 GL 2007 8 24 2007FA0000711 1 20070710 G 2497 RESISTOR DIAMON DA40 DA40 2990002 GL CONT IO360 IO360* 17025 CE ALTERNATOR DAMAGED D MZER K NONE O OTHER IN INSP/MAINT 1 GL 15 187DS 169 40574 MFG FABRICATED AN IN-LINE RESISTOR FROM THE ALTERNATOR TO THE VOLTAGE REGULATOR. THE RESISTOR WAS LOCATED APPROXIMATELY 2 INCHES FROM AUX TERMINAL ON ALTERNATOR. IT WAS STRENGTHENED WITH MULTIPLE LAYERS OF HEAT-SHRINK AND TERMINAL WAS CRI MPED ON THE SOLID WIRE LEAD OF THE RESISTOR. THE AIRCRAFT HAD INTERMITTENT ALT FAIL WARNING BUT HAD NORMAL, POSITIVE SY STEM CHARGING. UPON DISCOVERY OF THE FAULT, THE RESISTOR LEAD WAS HELD IN THE TERMINAL CRIMP BY THE HEAT SHRINK BUT THE SOLID WIRE WAS BROKEN, MOMENTARILY MAKING CONTACT CAUSING THE FAULT. THE PROBLEM WAS CORRECTED BY SOLDERING A SMALL SE CTION OF WIRE TO THE RESISTOR AND INSTALLING A NEW TERMINAL TO WIRE. MFG CUSTOMER SUPPORT WAS CONTACTED AND THEY WERE A 1 L 7 1 3O 3 O NT A47CE E1CE 2007082400266 20070824 00266 CE 2007 8 24 2007FA0000712 1 20070727 G 2621 SQUIB BEECH 300 300BEECH 1152930 CE FIRE BOTTLE GROUNDED B ML2R K NONE O OTHER IN INSP/MAINT 1 GL 11 350RK FL516 DURING COMPLETION OF THE INITIAL 200 HOUR PHASE 1 INSPECTION, THE RT ENGINE FIRE BOTTLE SQUIB WAS FOUND TO BE IN A GROUN DED CONDITION. THE TERMINALS WERE WIRED TOGETHER WITH SAFETY WIRE AND A TAG THAT STATED (DISCONNECT AT INSTALLATION, TH E AIRCRAFT SQUIB WIRING WAS ATTACHED OVER THE SAFETY GROUND WIRE. THIS GROUNDED CONDITION IS TYPICALLY FOUND ON SQUIBS THAT ARE PACKAGED FROM THE VENDOR FOR SHIPPING. DURING INSTALLATION OF THE SQUIB ONTO THE FIRE BOTTLE, THE SAFETY GROUN D IS REMOVED. IN THIS CONDITION, THE SQUIB CANNOT DETONATE TO PUT OUT AN ENGINE FIRE. LOG BOOKS WERE NOT AVAILABLE FOR RESEARCH AT THE TIME THE DISCREPANCY WAS DISCOVERED, ALTHOUGH THE AIRCRAFT WAS NEW ENOUGH THAT IT WAS UNLIKELY ANY ENGI 2 L 7 2 4T A24CE 2007082400269 20070824 00269 SO 2007 8 24 2007FA0000713 2 20070731 G 8530 CYLINDER CESSNA 310 T310Q 2074244 CE CONT O520 TSIO520NB 17040 SO NR 6 LEAKING B FTUR K NONE O OTHER IN INSP/MAINT 1 NE 05 7714Q 310Q0214 521496 WHILE PERFORMING OTHER MAINTENANCE A FUEL STAIN WAS NOTICED BETWEEN THE SECOND AND THIRD COOLING FIN AFT OF THE FUEL INJ ECTOR ON THE NR 6 CYLINDER OF THE RT ENGINE. THIS CONDITION PROMPTED A CLOSER INSPECTION OF THE ENGINE RESULTING IN THE DISCOVERY OF SIMILAR STAINING ON THE NR 1 AND NR 5 CYLINDERS. EACH CYLINDER WAS INDIVIDUALLY PRESSURIZED AND LEAK CHEC KED WITH A SOAPY WATER SOLUTION, NR 6 CYLINDER PRODUCED LARGE BUBBLES. THE CYLINDERS ARE ECI CASTING NR AEC65385 AND TH ERE WAS (A) STAMPED ON THE ROCKER BOX FLANGE WHICH REQUIRES NO FURTHER ACTION IAW AD 04-08-10. BY THE PILOTS STATEMENT THEY BELIEVE THERE IS APPROX. 1000 HOURS ON THESE CYLINDERS. RECOMMEND THAT A GOOD VISUAL INSPECTION BE PERFORMED AT 10 1 L 7 2 3O 3 O 3A10 E8CE 2007082400298 20070824 00298 SW 2007 8 24 2007FA0000714 1 20070726 G 5711 5146R SPAR BBAVIA 7 7FC 2110124 SW CONT C90 C90* 17009 SO WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 04 9032B 3177 123 AIRCRAFT WAS BEING MODIFIED TO INCLUDE THE INSTALLATION OF WING SPAR INSP HOLE KITS AS SUPPLIED IAW STC NR SA00527SE. A PORTION OF THE WING LEADING EDGE SKIN WAS REMOVED AND THE WING SPAR WAS VISUALLY INSPECTED AS SPECIFIED IN THE INSTALLA TION INSTRUCTIONS SUPPLIED WITH THE STC. DURING THIS VISUAL INSPECTION, A CRACK WAS OBSERVED ON THE TOP SURFACE OF THE RT WING FRONT SPAR. THE CRACK WAS OBSERVED ON THE TOP SURFACE OF THE RT WING FRONT SPAR. THE CRACK ORIGINATES AT THE I B END OF THE AFT PLYWOOD REINFORCEMENT PLATE. REINFORCEMENT PLATE IS LOCATED ON THE AFT SIDE OF THE FRONT SPAR, UNDER T HE LIFT STRUT ATTACHMENT FITTING. THE CRACK PROGRESSES OB ALONG THE TOP SURFACE OF THE SPAR AT A SLIGHT FWD ANGLE (CRAC 1 H 7 1 3O 3 O A759 E252 2007082400307 20070824 00307 CE 2007 8 24 2007FA0000715 1 20070807 G 2910 8907021 ACCUMULATOR BEECH 76 76 1153005 CE LYC O360 LO360A1G6 41514 EA HARTZL HCM2Y HCM2YR GL HYS SYS RUPTURED C XPTS A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 SO 19 61265 1440 ME135 DURING TRAINING FLIGHT IN PREP FOR COMMERCIAL/AMEL, PILOT PERFORMED INTENTIONAL SHUTDOWN OF LT ENGINE (FEATHERED). WAS UNABLE TO RESTART WITH ACCUMULATOR AND BEGAN PROCEDURE TO RESTART WITHOUT ACCUMULATOR WHICH WAS UNSUCCESSFUL. PILOT RET URNED TO DEPARTURE AND LANDED. AN INVESTIGATION OF THE ACCUMULATOR REVEALED A RUPTURED DIAPHRAGM. REPLACED LT ACCUMULA TOR AND RT ACCUMULATOR WAS REPLACED AS A PRECAUTIONARY METHOD. (K) 1 L 7 2 3O 3 O A29CE 1E10 5 C P43GL 2007082400308 20070824 00308 NE 2007 8 24 2007FA0000716 1 20070801 G 3340 SB4580 LAMP SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL2S1 60057 NE SEARCH LIGHT BURNED OUT C K NONE O OTHER IN INSP/MAINT 1 EA 25 554L 760567 POSSIBLE MFG PARTS NOT TO SPECIFICATIONS. MFG OF ORIG UNKNOWN. (GENERIC) LESS THAN 7 FLT HOURS IAW LAMP (AVERAGE) FROM INSTALLATION TO REPLACEMENT. HAVE REPLACED AT LEAST 5 LAMPS IAW AIRCRAFT IN LESS THAN 30 FLIGHT HOURS EACH. NO CIRCUIT BREAKERS POPPING. TROUBLESHOOTING SHOWS NO DISCREPANCIES ON EITHER AIRCRAFT. NO MFG INFORMATION ON PARTS BOX OR ON TH E PART. (K) 1 G 7 2 3U 4 U NC H1NE E00054EN 2007082400309 20070824 00309 NE 2007 8 24 2007FA0000717 1 20070801 G 3340 SB4580 LAMP SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL2S1 60057 NE LANDING LIGHT BURNED OUT C O OTHER O OTHER NR NOT REPORTED 1 EA 25 552J 760518 POSSIBLE MFG PARTS NOT TO SPECIFICATIONS. MFG OF ORIGIN UNKNOWN. (GENERIC) LESS THAN 7 FLT HOURS PER LAMP (AVERAGE) FRO M INSTALLATION TO REPLACEMENT. HAVE REPLACED AT LEAST 5 LAMPS PER AC IN LESS THAN 30 FLIGHT HOURS EACH. NO CIRCUIT BRE AKERS POPPING. TROUBLESHOOTING SHOWS NO DISCREPANCIES ON EITHER AC. NO MFG INFO ON PARTS BOX OR ON THE PART COPY OF OR IGINAL CERTIFICATION ATTACHED. (K) 1 G 7 2 3U 4 U NC H1NE E00054EN 2007082400249 20070824 00249 2007 8 24 2007FA0000718 2 20070821 G 7322 25765362 FUEL CONTROL CESSNA 172 172S 2072439 CE ENGINE OUT OF LIMITS B D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 SO 15 471ER 134 61 172S10511 DURING PRE TAKEOFF RUN UP, THE MAG DROP (BOTH MAGS) WAS BEYOND LIMITS. THIS AIRCRAFT HAD A RECENT HISTORY OF RICH SERVO OPERATION FOLLOWED BY ADJUSTMENTS, WHICH WOULD NOT STABILIZE. THE SERVO WAS CHANGED. THIS PROBLEM IS COMMON ON MANY OF T HE AIRCRAFT IN THIS FLEET AND HAS CAUSED FLEET-WIDE ADJUSTMENTS WHEN SUBSTANTIAL CHANGES IN ATMOSPHERIC TEMPERATURE OCCU R. IN MANY CASES THE SERVO MUST BE CHANGED WITH ONLY A FEW HOURS SINCE NEW. 1 H 7 1 3O NT 3A12 2007082400265 20070824 00265 EA 2007 8 24 2007FA0000719 2 20070821 G 7300 25765362 FUEL CONTROL CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE OUT OF LIMITS B C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 SO 15 471ER 134 61 172S10511 L3340351E DURING PRE TAKE OFF RUN UP, THE MAG DROP (BOTH MAGS) WAS BEYOND LIMITS. THIS AIRCRAFT HAD A RECENT HISTORY OF RICH SERVO OPERATION FOLLWED BY ADJUSTMENTS, WHICH WOULD NOT STABILIZE. THE SERVO WAS CHANGED. THIS PROBEM IS COMMON ON MANY OF TH E AIRCRAFT IN THIS FLEET AND HAS CAUSED FLEET-WIDE ADJUSTMENTS WHEN SUBSTANTIAL CHANGES IN ATMOSPHERIC TEMPERATURE OCCUR . IN MANY CASES THE SERVO MUST BE CHANGED WITH ONLY A FEW HOURS SINCE NEW. 1 H 7 1 3O 3 O NT 3A12 1E10 2007082400268 20070824 00268 CE 2007 8 24 2007FA0000720 1 20070821 G 2710 0510105364 CONTROL CABLE CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA AILERONS FRAYED B K NONE O OTHER IN INSP/MAINT 1 SO 15 454ER 987 172S10256 L3283951E DURING A ROUTINE INSPECTION, THE AILERON BALANCE CABLE WAS FOUND BADLY WORN IN THE LT WING AT STATION 71.125. THE CABLE IS DIRECTED OVER A FAIRLEAD AT THIS LOCATION AND TYPICALLY WEARS VERY BADLY AT THIS CONTACT POINT. BECAUSE THE WEAR PATT ER IS OVER A STRAIGHT RUN OF CABLE THERE IS NO BENDING OF THE CABLE WHICH WOULD CAUSE THE STRANDS TO FRAY OUTWARD. BECAU SE OF THIS, THE CABLE CAN BE WORN THROUGH MANY STRANDS AND YET APPEAR NORMAL. ONCE THE CABLE IS REMOVED FROM THE AIRCRAF T AND BENT AS SHOWN IN THE AC43.13-1B, PAGE 7-35, FIGURE 7-16, THE BROKEN STRANDS BECOME READILY APPARENT. THIS HAS BEEN AN ISSUE FOR A LONG TIME ON THIS MODEL AIRCRAFT. IF NOT INSPECTED CAREFULLY THE CABLE CAN DETERIORATE TO A DANGEROUS CO 1 H 7 1 3O 3 O NT 3A12 1E10 2007082400320 20070824 00320 GL 2007 8 24 2007FA0000721 1 20070822 G 2497 CABLE DIAMON DA40 DA40 2990002 GL ALTERNATOR BROKEN G A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 WP 05 541AJ 265 40541 ALTERNATOR CABLE INSTALLED AT THE FACTORY WAS TOO SHORT. CABLE CONNECTS TO ALTERNATOR CIRCUIT BREAKER. 1 L 7 1 3O NT A47CE 2007082400321 20070824 00321 SO 2007 8 24 2007FA0000722 1 20070812 G 5520 HORN PIPER PIPER PA18 PA18180 7101880 SO LYC O320 O320* 41508 EA ELEVATOR DAMAGED D A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 WP 23 4363Z 39 188682 AFTER DEPARTURE PILOT NOTED UNUSUAL STICK RESTRICTION AND ABORTED TOW OF GLIDER. RETURNED FOR LANDING. UPON INSPECTION T HE LOWER ARM/HORN OF THE RT ELEVATOR HORN HAD BROKEN. ALL (3) OTHER ARMS WERE UNDAMAGED AND SHOWED NO SIGN OF CRACKS. BO LTS WERE INTACT AND HOLDING CONTROL CABLE. 1 H 7 1 3O 3 O 1A2 E274 2007082400322 20070824 00322 SO 2007 8 24 2007FA0000723 2 20070823 G 8550 S23611 CHECK VALVE CESSNA 206 TU206C 2073334 CE CONT O520 TSIO520C 17040 SO ENGINE OIL WORN D O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 17 71924 4839 U2061226 178337R AFTER FLIGHT A/C SITTING ON RAMP DEVELOPED LARGE OIL LEAK FROM TURBOCHARGER. FOUND OIL CHECK VALVE FLAPPER VALVE SEVERE LY WORN. 1 H 7 1 3O 3 O A4CE E8CE 2007090600088 20070906 00088 CE 2007 9 6 2007FA0000725 1 20070808 G 2410 CS3100 SENSOR CESSNA 172 172R 2072401 CE LYC O360 IO360A1A 41514 EA MASTER CNTRL BOX INTERMITTENT B MYNR O OTHER N FALSE WARNING TX TAXI/GRND HDL 1 GL 11 9424F 658 17280390 CURRENT SENSOR INDICATES 60A AND WHEN MASTER IS TURNED ON FUNCTIONS NORMALLY FROM TIME TO TIME, TAP ON UNIT AND IT FLUCT UATES THEN ACTS PROPERLY. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2007090600087 20070906 00087 CE 2007 9 6 2007FA0000726 1 20070703 G 3260 903610373 DOWNLOCK SWITCH RAYTHN C90 C90GT 7150062 CE MLG FALSE INDICATION B E81R O OTHER O OTHER NR NOT REPORTED 1 GL 03 106ML 203 LJ1757 PILOT REPORTED LT MAIN LANDING GEAR DOWN AND LOCKED INDICATION WITH LANDING GEAR RETRACTED. FOUND SWITCH ASSY INDICATOR SHOWING GREEN DOWN AND LOCKED INDICATION IN GEAR RETRACTED POSITION. REPLACED SWITCH ASSY WITH NEW UNIT. LANDING GEAR RETRACTION/ EXTENSION SYSTEM TESTS NORMAL. (K) 1 L 7 2 3T RT 3A20 2007090600073 20070906 00073 NE 2007 9 6 2007FA0000727 3 20070620 G 6111 6533A12 BLADE HAMSTD AIRTRC AT300 AT301 0390103 SW PWA R1340 R1340AN1 52016 NE HAMSTD 22D 22D40 NE PROPELLER BROKEN G A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 GL 15 23667 84119 3010410 20788 PP810268 (9 INCHES) OF PROP BLADE BROKE OFF IN FLIGHT. THE SEVERE VIBRATION CAUSED PILOT TO LAND IN MUDDY FIELD. AIRCRAFT WAS T OTALED. (K) 1 L 7 1 3R 3 R A9SW 5E2 5 C P736 2007090600078 20070906 00078 CE 2007 9 6 2007FA0000728 1 20070731 G 2420 DOFF10300B ALTERNATOR CESSNA 182 182R 2072731 CE CONT O470 O470U 17026 SO MCAULY 2A34C C2A34C204 GL SHORTED D O OTHER O OTHER NR NOT REPORTED 1 NM 09 9628X 88 18268567 470887 851589 ALTERNATOR SHORTED, THIS UNIT IS (1) OF (3) REPLACED IN THE LAST MONTHS. (K) 1 L 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2007090600070 20070906 00070 CE 2007 9 6 2007FA0000729 2 20070803 G 8520 538684 BUSHING CONT PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE CONNECTING ROD MISINSTALLED D O OTHER O OTHER NR NOT REPORTED 1 NE 03 19WE 3449037 819271R DURING THE PROCESS OF INSPECTING (6 EA) CONNECTING RODS IAW SB 07-1 AND SB 00-3, IT WAS FOUND THAT ALL WRIST PIN BUSHING S WERE INSTALLED NOT IAW THEIR POSITIONS AS REQUIRED IN THE APPLICABLE SB AS REFERENCED. SPLIT LINE OF BUSHING ON WRONG SIDE OF CENTERLINE. PARTS AS RECEIVED FROM MFG. (K) 1 L 7 2 3O 3 O A7SO E9CE 2007090600036 20070906 00036 2007 9 6 2007FA0000730 4 20070813 G 3444 ADS430101AC ANTENNA PIAGIO P180 P180 6960204 EU FUSELAGE SEPARATED B KKQR O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 11 395KT 3985 1044 RADAR ALTIMETER REPORTED INOPERATIVE. FOUND ANTENNA SENSOR GONE FROM THE BASE, LEAVING .2500 INCH HOLE THROUGH THE COAX CONNECTION. THE FLAT ANTENNA MOUNTS TO A CURVED FUSELAGE WITHOUT CONTOUR ADAPTATION. (K) 1 H 7 2 3O RT A59EU 2007090600090 20070906 00090 SW 2007 9 6 2007FA0000731 1 20070625 G 2120 2784187019 PIPE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE331* 01514 WP RT WING BLEED AI ARCED G O OTHER O OTHER NR NOT REPORTED 1 SW 11 160WA TC399 IB OF RT NACELLE, BLEED AIR PIPE (PN 2784187019), CHAFED OR BURNED THROUGH THE ASBESTOS SLEEVE SURROUNDING THE STARTER R ELAY WIRING, WHICH THEN ARCED A HOLE IN THE BLEED PIPE, WHICH THEN BURNED THE SHIELDING FROM THE STARTER RELAY WIRES, WH ICH THEN ARCED A HOLE IN A HYDRAULIC LINE (PN 2781032403), RESULTING IN A FIRE. 2 L 7 2 4T 3 T RT A8SW E2WE 2007090600055 20070906 00055 CE 2007 9 6 2007FA0000732 1 20070517 G 2432 6041H274 RELAY CESSNA 310 T310R 2074246 CE CONT O520 TSIO520* 17040 SO BATTERY FAILED D A8XR O OTHER O OTHER NR NOT REPORTED 1 SO 05 16EZ 310R1277 AIRCRAFT EMERGENCY LANDED WITH COMPLETE ELECTRICAL FAILURE, LG EMERGENCY EXTENDED AND LANDED SAFELY. FOUND BATTERY RELA Y FAILURE. UNIT REMOVED 200 AMP FOUND TO BE INCORRECT (PN). SB MEB99-4 ADDRESS THIS PROBLEM, HAD NOT BEEN COMPLIED WIT H, CORRECT RELAY 100 AMP PN 0850469-1 (6041H193) INSTALLED, OPS CHECK OK. (200 AMP RELAY HAD TO HAVE BEEN REPLACED PRIO R TO 1999 WHEN AC IPC REVERSED BATTERY AND STARTER RELAY PN COMPLIANCE WITH SB WOULD HAVE PREVENTED THIS PROBLEM. (K) 1 L 7 2 3O 3 O 3A10 E8CE 2007090600056 20070906 00056 GL 2007 9 6 2007FA0000733 3 20070810 G 6114 PHCC3YF1RF HUB HARTZL CESSNA 207 207 2073602 CE CONT O550 IO550F 17042 SO HARTZL HCC3Y PHCC3YF1 GL PROPELLER CRACKED B LU4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 EE2379A HUB, NDI SHOWS RELEVANT INDICATION OF CRACK.(K) 1 H 7 1 3O 3 O A16CE E3SO 5 C P25EA 2007090600050 20070906 00050 CE 2007 9 6 2007FA0000735 1 20070809 G 2497 36153 GROUND WIRE BEECH 200 B200 1152922 CE PWA PT6 PT6A6 52043 EA GCU BROKEN D B A EMER. DESCENT UNSCHED LANDING B G H SMOKE/FUMES/ODORS/SPARKS MULTIPLE FAILURE ELECT. POWER LOSS-50 PC CR CRUISE 1 CE 07 1925P 9715 BB1094 WIRE NR P73G16N AT RT ENGINE FIREWALL GROUND POINT GS15 SEPARATED FROM THE WIRE TERMINAL DURING CRUISE FLIGHT. THIS WIRE CONNECTS GROUND TO THE GCU PIN G. THE RT GENERATOR OUTPUT SPIKED AND OPENED THE 325 AMP RT BUSS CURRENT LIMITER, THE 50 AMP RT INVERTER CURRENT LIMITER, AND DAMAGED RADIOS, THE GCU AND SYSTEMS WIRED TO THE RT BUSS. UPON INSPECTION, THE INS ULATION OF P73G16N WAS FOUND STRIPPED TOO FAR FROM THE WIRE END THEREBY GIVING NO SUPPORT OF THE WIRE INTO THE TERMINAL AT THE INSULATION CRIMP AREA. 1 L 7 2 4T 3 T A24CE E4EA 2007090600053 20070906 00053 CE 2007 9 6 2007FA0000736 1 20070823 G 3246 178K481 TIRE LEAR 60 60LEAR 5170707 CE LT MLG DEFLATED D D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 WP 27 903AM 269 NOTIFIED BY FLIGHT CREW LT MAIN LANDING GEAR IB AND OB TIRES SEPARATED FROM WHEELS DURING TAXI. TIRES DETACHED FROM WHE EL ASSEMBLIES BUT DID NOT SEPARATED FROM AIRCRAFT. TIRES WERE NOT BLOWN. DAMAGED TIRES AND WHEELS ASSEMBLIES WERE REMO VED. UPON INSPECTION, NO OTHER DAMAGES NOTED ON LANDING GEAR OR SURROUNDING STRUCTURE. NO FOD DAMAGE TO AIRCRAFT. REP LACED WITH SERVICEABLE WHEELS/TIRES ASSEMBLIES. 2 L 7 2 4F RT A10CE 2007091200003 20070912 00003 NM 2007 9 12 2007FA0000741 1 20070828 G 3246 AN535A BOLT PARKERHANFIN COLUMB LC41 LC41550FG400 5150011 NM WHEEL ASSY BROKEN B O OTHER E VIBRATION/BUFFET LD LANDING 1 EA 25 1469W 143 143 MFG406 41733 ON LANDING PILOT FELT AND HEARD A VIBRATION AND BUMPING SOUND. REMOVED RT LANDING GEAR FAIRING AND INSPECTED BRAKE ASSY . ON THE WHEEL FOUND ONE WHEEL HALF ATTACH BOLT MISSING AND ONE BROKEN AND EXTENDING OUT OF THE WHEEL TO THE EXTENT OF CAUSING A GOUGE IN THE BRAKE MASTER CYLINDER AND TORQUE PLATE. ONE BOLT OUT OF THREE WAS HOLDING THE WHEEL HALVES TOGET HER. 1 L 7 1 3O NT A00003SE 2007090600022 20070906 00022 NE 2007 9 6 2007FA0000747 2 20070817 G 7310 3011849 TUBE BEECH 90 F90 1152909 CE PWA PT6 PT6A135 52043 NE LT ENGINE CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 03 50AW 15 LA142 PCE92358 FUEL LEAK NOTED ON SHUTDOWN OF LT ENGINE. FUEL TUBE P/N 3011849 CRACKED AT CONNECTION TO START CONTROL UNIT. 1 L 7 2 4T 4 T A31CE E4EA 2007090600035 20070906 00035 EA 2007 9 6 2007FA0000748 2 20070718 G 7310 3011849 TUBE PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA LT ENGINE CRACKED B K NONE K FLUID LOSS IN INSP/MAINT 1 EA 03 100CM 5 31T8020073 FUEL LEAK NOTED ON SHUTDOWN. FUEL TUBE P/N 3011849 WAS CRACKED AT CONNECTION TO START CONTROL UNIT. 1 L 7 2 3T 4 T A8EA E4EA 2007090600059 20070906 00059 CE 2007 9 6 2007FA0000749 1 20070829 G 7810 K99102991 EXHAUST PIPE CESSNA 414 414 2075908 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C93 GL ENGINE CRACKED B W99R K NONE O OTHER IN INSP/MAINT 1 WP 09 22MG 1900 4140533 DURING COMPLIANCE WITH AD 2000-01-16 THE TAIL PIPE ON THE RT ENGINE WAS FOUND WITH A 6 INCH CRACK. THE LAST INSPECTION WAS 40 HRS PRIOR. 1 L 7 2 3O 3 O RT A7CE E8CE 5 C P22EA 2007090600012 20070906 00012 NE 2007 9 6 2007FA0000752 2 20070725 G 7200 ENGINE BEECH 90 E90 1152914 CE PWA PT6 PT6A60A 52043 NE LEFT FAILED D A UNSCHED LANDING R X J PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 SW 13 71WB LW127 AIRCRAFT IN CRUISE AT 22,000 WITH ALL ENGINE INDICATIONS NORMAL. A LOUD NOISE FOLLOWED BY POWER LOSS AND REDLINE ITT ON THE LT ENGINE. THE CT BLADES, ITT PROBES, PT VANE AND PT BLADES ALL MELTED AND WENT THROUGH THE EXHAUST STACKS. COMPR ESSOR STATOR AND SPACER RUB. POSSIBLE COMPRESSOR UNSTACK FAILURE. THIS IS THE FIRST COMPLETE MELT DOWN FAILURE HAVE EV ER SEEN AT ALTITUDE. (K) 1 L 7 2 3T 4 T 3A20 E4EA 2007090600058 20070906 00058 EU 2007 9 6 2007FA0000753 1 20070724 G 2910 704A34412938 LINE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE HYD SYSTEM LEAKING B PG9R O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 WP 19 170PA 2637 AC HAD HYDRAULIC LIGHT, PILOT PERFORMED A PRECAUTIONARY LANDING AT THE AIRPORT. UPON INSP FOUND HYDRAULIC LINE FROM PUM P TO MANIFOLD LEAKING AT THE BOTTOM OF THE SWEDGE FITTING. HYDRAULIC LINE WAS REPLACED WITH NEW LINE. HYDRAULIC SYSTEM WAS SERVICED, GROUND RUN, AND LEAK CHECK NORMAL. FLIGHT CONTROL CHECK NORMAL. AC WAS RETURNED TO SERVICE. (K) 1 G 7 1 3U 3 U H9EU E19EU 2007090600057 20070906 00057 EA 2007 9 6 2007FA0000754 1 20070803 G 2740 604923063 MOTOR CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF34* NE HORIZ STAB TRIM UNSERVICEABLE C K NONE O OTHER IN INSP/MAINT 1 GL 13 43R 5334 WHILE OPERATING HORIZ STAB TRIM ON CHANNEL NR 2 ONLY THE FOLLOWING OCCURS. PUSHING BUTTON ON CONTROL WHEELS TO NOSE UP, HORIZONTAL ACTUALLY WENT DOWN THEN DISCONNECTED. REPEATED ATTEMPTS, KEPT TRIMMING TO NOSE DOWN POSITION. COULD NOT GE T HORIZONTAL TO TRIM NOSE UP ON JUST CHANNEL NR 2. ONCE CHANNEL NR 1 WAS ENGAGED HORIZONTAL STAB TRIM WORKED CORRECTLY. THIS PART WAS SENT TO THE MFG BY THE PREVIOUS OPERATOR FOR THIS EXACT PROBLEM. MFG REPLACED PARTS AND RETURNED IT TO SERVICE. PROBLEM REOCCURRED, UNIT REMOVED AND SENT BACK TO MFG. (K) 2 L 7 2 4F 4 F RT A21EA E15NE 2007090600002 20070906 00002 CE 2007 9 6 2007FA0000755 1 20070802 G 8011 85070213 STARTER CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA ENGINE FAILED D O OTHER O OTHER NR NOT REPORTED 1 EA 05 865SP 172S8124 STARTER WAS INTERMITTENT AND FAILED COMPLETELY. AVERAGE LIFE FOR THE LAST (2) STARTERS HAS BEEN 115 HRS EACH. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2007090600076 20070906 00076 NE 2007 9 6 2007FA0000758 2 20070828 G 7314 DRIVE SHAFT SUNDSTRANDEM BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE FUEL PUMP SHEARED D E ENGINE SHUTDOWN X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 SO 11 544P 1340 9489 BB1265 PCE94081 WHILE AT CRUISE FLIGHT, LT ENGINE SHUTDOWN WITHOUT WARNING. LANDED WITHOUT INCIDENT. FOUND HIGH PRESSURE FUEL PUMP SHAFT SPLINES SHEARED ON INSIDE OF DRIVE COUPLING RENDERING FUEL PUMP AND FUEL CONTROL INOPERABLE. INSPECTION WOULD NOT BE PO SSIBLE WITHOUT PUMP REMOVAL AND DISASSEMBLY OF DRIVE COUPLING. 1 L 7 2 4T 4 T A24CE E4EA 2007090600038 20070906 00038 NE 2007 9 6 2007FA0000759 2 20070831 G 7220 BRR40289 FAIRING RROYCE GULSTM GV GULFSTREAMGV 3980116 SO RROYCE BR700 BR700710A110 NE LP FAN CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 15 73M 3889 547 11204 DURING INSPECTION OF THE AIR INTAKE ROTATING FAIRING, WE FOUND A CRACK BETWEEN THE MOUNT BOLT HOLE AND THE ADJACENT ALIG NMENT PIN HOLE. 2 L 7 2 4F 4 F RT A12EA E00057EN 2007091700020 20070917 00020 EA 2007 9 17 2007FA0000760 2 20070716 G 8550 LW13383 BAFFLE LYC FOUND FBA FBA2C1 3640103 EA LYC O540 IO540L1A5 41532 EA OIL SUMP CRACKED B K NONE O OTHER IN INSP/MAINT 1 AL 03 796 600 50 L2947748A ENGINE OIL SUMP BAFFLE CONTACTED BOTTOM OF OIL SUMP CRACKING BAFFLE SUPPORT ATTACH POINTS AND SHEARING RIVETS ATTACHING BAFFLE CENTER REINFORCEMENT. SHEARED RIVET LODGED IN OIL PRESSURE RELIEF VALVE CAUSING LOSS OF OIL PRESSURE. ENGINE RE MOVED FOR OVERHAUL. 1 H 7 1 3O 3 O NC A7EA 1E4 2007091700024 20070917 00024 EA 2007 9 17 2007FA0000761 2 20070716 G 8550 LW13383 BAFFLE FOUND FBA FBA2C1 3640103 EA LYC O540 IO540L1A5 41532 EA OIL SUMP CRACKED B K NONE O OTHER IN INSP/MAINT 1 AL 03 794 500 51 L29544548A ENGINE OIL SUMP BAFFLE CONTACTED BOTTOM OF OIL SUMP CRACKING BAFFLE SUPPORT ATTACH POINTS AND SHEARING RIVETS ATTACHING BAFFLE CENTER REINFORCEMENT. 1 H 7 1 3O 3 O NC A7EA 1E4 2007091700025 20070917 00025 GL 2007 9 17 2007FA0000768 1 20070804 G 2810 CAP AMTR SKRAID SKYRAIDER 05610GI GL ROTAX 447 ROTAX447 55555 EU FUEL TANK OUT OF ADJUST G A UNSCHED LANDING W J INADEQUATE Q C WARNING INDICATION DE DESCENT 1 GL 25 31711 35 SK1966 AT CONCLUSION OF 2 HOUR FLIGHT, APPROXIMATELY 2 MILES FROM DESTINATION AIRPORT, PILOT REPORTED AN UNCOMMANDED SIGNIFICAN T POWER REDUCTION. A PRECAUTIONARY LANDING WAS EXECUTED ON A COUNTY ROAD. SUBSEQUENT INVESTIGATION FOUND 1.5 GALLON FU EL IN RT TANK, NONE IN LT TANK. EVIDENCE OF FUEL SIPHONING FROM RT FUEL CAP. PILOT STATED WHEN LT FUEL CAP WAS REMOVED , HISSING NOISE WAS HEARD. PROBABLE THAT COMBINATION OF SIPHONING RT TANK/CAP AND NO VENTING OF LT TANK/CAP CAUSED A FU EL IMBALANCE AND INTERRUPTION OF FUEL FLOW TO HEADER TANK/ENGINE, RESULTING REDUCTION OF ENGINE OPERATION. RECOMMEND AN Y EXPERIMENTAL AIRCRAFT USING FUEL CAPS WITH THREADED CENTER STEM/(O) RING ASSEMBLY FOR VENTING BE MODIFIED TO INCLUDE A 1 H 7 1 3 I EXPA1H71 EXPE3I 2007091700070 20070917 00070 SW 2007 9 17 2007FA0000769 1 20070905 G 5711 SPAR BBAVIA 7 7GCBA 21101PH SW LYC O320 O320* 41508 EA RT WING FRACTURED D K NONE O OTHER IN INSP/MAINT 1 EA 23 9902Y 1480 9 7GCBA8 RT WING MAIN SPAR FOUND FRACTURED IB OF STRUT ATTACH. CURRENT AD INADEQUATE TO PREVENT FURTHER FAILURES. THIS AIRCRAFT H AS LESS THAN 14 HR SINCE LAST ANNUAL INSPECTION.. 1 H 7 1 3O 3 O A759 E274 2007091700008 20070917 00008 SW 2007 9 17 2007FA0000770 1 20070905 G 5711 SPAR BBAVIA 7 7GCBA 21101PH SW RT WING BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 23 9902Y 1480 9 7GCBA8 RT WING MAIN SPAR FOUND FRACTURED IB OF STRUT ATTACH. CURRENT AD INADEQUATE TO PREVENT FURTHER FAILURES. THIS AIRCRAFT H AS LESS THAN 14 HR SINCE LAST ANNUAL INSPECTION.. 1 H 7 1 3O A759 2007091700059 20070917 00059 CE 2007 9 17 2007FA0000772 1 20070401 G 3210 NAS464P426 BOLT CESSNA 320 320E 2074514 CE CONT O520 TSIO520B 17040 SO MCAULY 3AF32C 3AF32C* GL RT MLG SHEARED D O OTHER O OTHER NR NOT REPORTED 1 WP 17 3424Q 320E0024 AIRCRAFT HAS EXPERIENCED A RT LANDING GEAR FAILURE UPON LANDING. PRIOR TO THIS INCIDENT, THE LANDING GEAR HAD BEEN CHEC KED DURING THE AIRCRAFT ANNUAL INSPECTION AND FOUND TO BE OUT OF RIG IAW SERVICE MANUAL D508-3-13 STANDARDS. THE AIRCRAF T EXPERIENCED A PARTIAL POWER FAILURE UPON THE FIRST FLIGHT AFTER THE AIRCRAFT HAD BEEN RIGGED. SUSPECT THE LANDING GEA R WAS NOT LOCKED PROPERLY UPON LANDING ON THE FIRST FLIGHT DUE TO THE PARTIAL ELECTRICAL POWER FAILURE. UPON THE THIRD FLIGHT LANDING, THE RT GEAR COLLAPSED. PROBABLE CAUSE MAY HAVE BEEN FROM THE FIRST LANDING WHERE GEAR MAY NOT HAVE BEEN ALL THE WAY DOWN. THE BOLT TO THE LANDING GEAR STRUT SHEERED AT THE ATTACH POINT OF THE STRUT, AND ONE ATTACH POINT BR 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2007091700023 20070917 00023 CE 2007 9 17 2007FA0000778 1 20070906 G 2820 3011849 LINE BEECH 90 F90 1152909 CE PWA PT6 PT6A135 52043 NE FUEL SYS CRACKED B A UNSCHED LANDING K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 EA 03 50AW 6848 LA142 PCE92358 FUEL TUBE CRACKED AT BACKSIDE OF B-NUT SLEEVE LOCATION, CAUSING FUEL TO LEAK UNDER PRESSURE INTO ENGINE NACELLE AREA FOR WARD OF FIREWALL. TUBE FAILED IN FLIGHT CAUSING INITIAL CHANGES IN FUEL FLOW INDICATIONS TO BE NOTICED. 1 L 7 2 4T 4 T A31CE E4EA 2007091700003 20070917 00003 CE 2007 9 17 2007FA0000780 1 20070812 G 2910 AE1011889G0116 LINE CESSNA 750 750 2076810 CE ALLSN AE300 AE3007A GL HYDRAULIC SYS RUPTURED B CNQ3 O OTHER K FLUID LOSS NR NOT REPORTED 1 GL 13 912QS 7516 7500012 THE NOSE WHEEL STEERING CENTERING FLEXIBLE HYDRAULIC HOSE RUPTURED WHERE THE HOSE BODY IS SWEDGED TO A 45 DEGREE FITTING WHICH ATTACHES TO A BULKHEAD FITTING IN THE NOSE WHEEL WELL. THIS CONDITION ALLOWED THE LOSS OF HYDRAULIC FLUID IN THE (A SYSTEM). AIRCRAFT LANDED WITHOUT INCIDENT. THIS HOSE IS CURRENTLY CONSTRUCTED OF KEVLAR AND IS BEING REPLACED WITH STAINLESS STEEL BRAIDED VERSION ALONG WITH OTHER HOSES WHICH ATTACH TO THE NOSE GEAR. (K) 2 L 7 2 4J 4 F RT T00007WI TE6CH 2007091700069 20070917 00069 SO 2007 9 17 2007FA0000781 2 20070810 G 8520 CRANKSHAFT CONT O520 GTSIO520L 17032 SO ENGINE FAILED B LU4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 A511M2 CRANKSHAFT FAILED NDI SB MSB96-10. (K) 3 O E7CE 2007091700019 20070917 00019 GL 2007 9 17 2007FA0000782 3 20070810 G 6114 HUB HARTZL CESSNA 207 207 2073602 CE CONT O550 IO550F 17042 SO HARTZL HCC3Y PHCC3YF1 GL PROPELLER CRACKED B LU4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 EE2379A EE2379A HUB, NDI SHOWS RELEVENT INDICATION OF CRACK. (K) 1 H 7 1 3O 3 O A16CE E3SO 5 C P25EA 2007091700072 20070917 00072 SO 2007 9 17 2007FA0000783 1 20070816 G 2730 62701153 CONTROL CABLE PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA ELEVATOR BROKEN D O OTHER O OTHER NR NOT REPORTED 1 SO 05 30521 447995076 AFT LOWER ELEVATOR CONTROL CABLE BROKE AT TURN BUCKLE BETWEEN CRIMPED BARREL AND END THREADS. SENT CABLE ASSY TO NTSB F OR LAB REPORT. (K) 1 L 7 2 3O 3 O A19S0 E286 2007091700026 20070917 00026 EA 2007 9 17 2007FA0000784 2 20070708 G 7322 30804 FLOAT PRECISION AMTR VANS RV9A 05614C3 GL LYC O320 O320D2A 41508 EA SNSNCH 70C 70CM6 EA CARBURETOR FAILED D O OTHER O OTHER NR NOT REPORTED 1 SO 03 12HE 33 75992004 91367 L2005739A 38893K THE ENGINE DIED ON FINAL TO AIRPORT, PUMPED THE THROTTLE, AND THE ENGINE STARTED RUNNING AGAIN, RETARDED THROTTLE, AND T HE ENGINE DIED AGAIN. LANDED WITHOUT INCIDENT. COULD NOT GET THE ENGINE TO RESTART ON THE GROUND. ENGINE WAS STARTED THE NEXT DAY, THE FUEL FLOW WAS SHOWING 11 TO 12 GPH AT IDLE. REMOVED THE CARBURETOR AND ONE PONTOON OF THE PLASTIC FLO AT WAS 90 PERCENT FULL OF FUEL. (K) 1 L 7 1 3O 3 O NT EXPA1L71 E274 5 N P28NE 2007091700034 20070917 00034 CE 2007 9 17 2007FA0000785 1 20070807 G 2612 61423473275 SENSOR BEECH 200 A200 1152921 CE PWA PT6 PT6A41 52043 EA MCAULY 4HFR34 4HFR34C752 NE FIRE DETECTION FAULTY E O OTHER O OTHER NR NOT REPORTED 1 EA 05 636B 754 BC61 AT APPROXIMATELY 1635 LOCAL, IN CLOUDY CONDITIONS, ON A MAINTENANCE TEST FLIGHT, THE NR 1 ENGINE FIRE LIGHT BRIEFLY ILLU MINATED, THEN EXTINGUISHED. ALL ENGINE GAUGES INDICATED NORMALLY. ALREADY IN DESCENT, THROUGH 4,500 FT, AND CONTINUED TO A SAFE LANDING. MAINTENANCE DISCOVERED FAULTY LOWER AFT SENSOR AND REPLACED IT. (K) 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2007091700010 20070917 00010 GL 2007 9 17 2007FA0000786 1 20070516 G 7160 D4F732612001 AIR BOX DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA ENGINE BROKEN D O OTHER O OTHER NR NOT REPORTED 1 NM 07 425FP 357 40FC025 CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA KE. (K) 1 L 7 1 3O 3 O NT A47CE E286 2007091700067 20070917 00067 GL 2007 9 17 2007FA0000787 1 20070521 G 7160 D4F732612001 AIR BOX DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA ENGINE BROKEN D O OTHER O OTHER NR NOT REPORTED 1 NM 07 422FP 383 40FC022 CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA KE WHILE IN FLIGHT. (K) 1 L 7 1 3O 3 O NT A47CE E286 2007091700032 20070917 00032 NE 2007 9 17 2007FA0000788 2 20070810 G 7320 8168776007 EEC UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206B 0 NE ENGINE FAILED B HDNR O OTHER O OTHER NR NOT REPORTED 1 SW 03 911KB 0013 BB0027 EEC CAUSED ENGINE TO DROP FROM FULL POWER TO IDLE IN CRUISE FLIGHT WITH AN ENGINE FAILURE AND ENGINE MANUAL HORN AND LIG HT. (K) 1 G 7 2 3U 3 U O H88EU E42NE 2007091700006 20070917 00006 SO 2007 9 17 2007FA0000789 2 20070809 G 8520 530196A1 CRANKSHAFT CONT C85 C8512 17008 SO ENGINE DESTROYED G O OTHER O OTHER NR NOT REPORTED 1 GL 13 21407612 DURING LEVEL FLIGHT THIS AIRCRAFT SUSTAINED LOSS OF PROPELLER. AIRCRAFT LANDED ON A COUNTY HIGHWAY SATISFACTORILY WITH NO DAMAGE OR INJURIES. INVESTIGATION REVEALED THE ENGINE CRANKSHAFT FAILED IMMEDIATELY AFT OF THE PROPELLER ATTACH POIN T (THIS CRANKSHAFT HAS A TAPERED SHAFT, NOT A FLANGE). THE PROPELLER WAS LOCATED AT A LATER TIME BY A HIKER IN A STATE PARK. INSPECTION OF THE ENGINE AND PROPELLER INDICATES THE PROBABILITY THAT THE ENGINE HAD SUSTAINED SUDDEN STOPPAGE AT A PRIOR TIME. THIS MAY HAVE RESULTED IN A MINUTE CRACK/FRACTURE THAT EVENTUALLY PROPAGATED INTO THE TOTAL FAILURE OF T HIS CRANKSHAFT. SINCE THERE WAS NO DAMAGE TO THE AIRCRAFT OR OCCUPANTS, THIS SITUATION HAD BEEN DETERMINED TO BE AN INC 3 O E233 2007091700013 20070917 00013 SW 2007 9 17 2007FA0000790 1 20070901 G 3610 2784187015 PIPE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE331* 01514 WP BLEED AIR DAMAGED D O OTHER O OTHER NR NOT REPORTED 1 SW 11 226AM TC229 NOTE: AIRCRAFT HAS BEEN PARKED FOR 2 YEARS AFTER BEING DAMAGED IN HURRICANE. AIRCRAFT WAS BEING DISASSEMBLED FOR SALVAG E. IB OF RT NACELLE, BLEED AIR PIPE, PN: 27-84187-015, HAS CHAFED/BURNED THROUGH THE ASBESTOS SLEEVE SURROUNDING THE ST ARTER RELAY WIRING AND HAS ARCED A HOLE IN THE BLEED PIPE, WHICH THEN ALLOWED BLEED AIR TO MELT THE SHIELDING FROM ONE O F THE WIRES. (K) 2 L 7 2 4T 3 T RT A8SW E2WE 2007091700033 20070917 00033 WP 2007 9 17 2007FA0000794 1 20070901 G 5730 SKIN DOUG DC9 DC915 3022036 WP PWA JT8 JT8D7 52053 NE WING DAMAGED D C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 SO 17 305PA 45740 BIRD STRIKE ON LT LEADING EDGE, CAUSING DEEP DENT AMD A TEAR 5 INCHES VERTICAL AND 4 INCHES HORIZONTAL, FOUND ON POST FL IGHT INSPECTION. REPAIRED IAW SRM CHAPTER 57-06. 2 L 7 2 4F 4 F A6WE E2EA 2007091700036 20070917 00036 CE 2007 9 17 2007FA0000797 1 20070809 G 2810 FC100 FUEL CAP CESSNA 182 182P 2075816 CE CONT O470 O470* 17026 SO FUEL CELL VENTING G B EMER. DESCENT Y J ENGINE STOPPAGE WARNING INDICATION DE DESCENT 1 GL 15 58776 40 40 18262288 FUEL CAPS WERE INSTALLED ON AIRCRAFT IAW STC SA2376CE AND HAD BEEN IN SERVICE FOR ABOUT 40 HOURS IN A 4 MONTH PERIOD. TH EY BEGAN VENTING FUEL FROM BOTH TANKS RESULTING IN A FORCED EMERGENCY LANDING DUE TO FUEL STARVATION. 1 H 7 1 3O 3 O NT TA13 E273 2007091800102 20070918 00102 EA 2007 9 18 2007FA0000798 2 20070603 G 7322 30804 FLOAT AMTR COZY COZYIII 05605BK GL LYC O290 O290 41506 EA CARBURETOR SATURATED B JULR O OTHER O OTHER NR NOT REPORTED 1 SW 01 369CZ 40 1517 ENGINE FAILED ON SHORT. FINAL DUE TO CARB: FLOODING FLOAT IN CARB, HALF FULL OF GAS. (K) 1 M 7 1 3O 3 O RT EXPA1M71 E229 2007091700007 20070917 00007 SO 2007 9 17 2007FA0000799 1 20070905 G 7820 MUFFLER PIPER PA18 PA18150 7101828 SO LYC O320 O320* 41508 EA EXHAUST BROKEN G K NONE O OTHER IN INSP/MAINT 1 GL 15 7066B 36 185140 ENGINE EXHAUST TAIL PIPE FAILED AT THE MUFFLER WELD. WITH 36 HOURS TOTAL TIME SINCE NEW. LEADING EDGE EXHAUST SYSTEM W AS INSTALLED BY STC SA02200AK. 1 H 7 1 3O 3 O 1A2 E274 2007091700027 20070917 00027 EU 2007 9 17 2007FA0000800 1 20070809 G 3233 485034 ACTUATOR BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE7315BR WP RT MLG UNSERVICEABLE D O OTHER O OTHER NR NOT REPORTED 1 WP 01 919SS NA0473 RT MLG ACTUATOR CRACKED ATTACH HOUSING DISCOVERED DURING WHEEL WELL INSPECTION, PART WAS NOT LEAKING BUT COULD SEPARATE AT ANY MOMENT AND CAUSE SEVERE DAMAGE TO AIRCRAFT DATE OF ASSY OF ACTUATOR 1/92. (K) 2 L 7 2 4F 4 F RT A3EU E6WE 2007091700018 20070917 00018 EU 2007 9 17 2007FA0000801 1 20070809 G 5343 25FC5801A SUPPORT BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE7315BR WP LT MLG CORRODED D O OTHER O OTHER NR NOT REPORTED 1 WP 01 919SS 5860 NA0473 LT MLG DOOR IB AFT SUPPORT REMOVED FOR OTHER MAINTENANCE AND SEVERE INTERGRANULAR CORRODION DISCOVERED FROM LAVATORY LEA KAGE AS INDICATED BY STAINING ON PART LOCATION WHERE BONDING STRAP ATTACHES. CORROSION SEVERE AND IS ENOUGH TO CAUSE PA RT TO FAIL. (K) 2 L 7 2 4F 4 F RT A3EU E6WE 2007091700074 20070917 00074 2007 9 17 2007FA0000802 1 20070910 G 3245 6006 TUBE TIRE DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 6.00 X 6 TIRE TUBES WILL NOT FIT IN 6.00 X 6 WHEEL. STEM APPEARS TO NOT BE IN CENTER AND SIZE OF TUBE IS SMALLER THAN NO RMAL. (2) TUBES FOUND TO BE IN THIS CONDITION. WHEN WE ATTEMPTED TO RETURN THE TUBES TO OUR VENDOR, WOULD NOT ACCEPT A RETURN AND THAT THE TUBES WERE NOT DEFECTIVE. 2007091700040 20070917 00040 NM 2007 9 17 2007FA0000805 1 20070911 G 2910 82970009325 LINE DHAV DHC8 DHC8106 2809020 NM PWA PW121 PW121 52124 NE HYDRAULIC SYS LEAKING H A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 SW 99 387BC 351 PILOT NOTED LOSE HYDRAULIC LINE. DECLARED EMERGENCY AND LANDED. NO NOSE WHEEL STEERING ON GROUND. INSPECTED ALL HYDRAUL IC LINES AND FITTINGS. NOTED EDP LINE GOING TO PRESSURE MANIFOLD B NUT WAS ABLE TO GET HALF A TURN. SYSTEM SERVICED AND FUNCTIONAL CHECKED SERVICEABLE. 2 H 7 2 4T 4 T RT A13NM E20NE 2007091700063 20070917 00063 2007 9 17 2007FA0000809 1 20070912 G 3220 13022101 TAIL WHEEL WORN G O OTHER O OTHER NR NOT REPORTED 1 SW 17 912S TAILWHEEL SPRING P/N 13022.101 SHOWED EVIDENCE OF LOOSENESS AND ELONGATION OF THE FORWARD ATTACH POINT HOLE. THE ATTACH BOLT P/N AN5-22A EXHIBITED SIGNS OF FRETTING WEAR CONTRIBUTING TO THE TAILWHEEL LOOSENESS. IT WOULD APPEAR THAT THIS C ONDITION COULD INDUCE A SIGNIFICANT SIDE LOAD ON THE TAILWHEEL SPRING AFT ATTACHMENT CLAMP AND HARDWARE. THIS CONDITION WOULD BE DIFFICULT TO DETECT WITH THE WEIGHT OF THE AIRCRAFT ON THE TAILWHEEL. IT IS RECOMMENDED THAT THE CONDITION IN SPECTION INCLUDE SUPPORTING THE FUSELAGE FORWARD OF THE TAILWHEEL SPRING FORWARD ATTACHMENT POINT AND CHECKING THE TAILW HEEL ASSEMBLY FOR SECURITY AND TIGHTNESS. 2007092500184 20070925 00184 CE 2007 9 25 2007FA0000810 1 20070731 G 3222 STRUT CESSNA 182 182T 2072703 CE LYC O540 IO540* 41532 EA NLG LEAKING B AQHR O OTHER K FLUID LOSS NR NOT REPORTED 1 WP 11 5348E 18281212 FOUND NOSE STRUT ASSEMBLY LEAKING. REMOVED STRUT ASSEMBLY FROM AIRCRAFT. ASSEMBLED WITH PN TCNS-1 SEAL KIT IWA SRM AND MM. RELEASED TO AC OWNER. OWNER FOUND FLUID NR 4 ON WHEEL FAIRING AFTER TAXI TO HANGAR. INSPECTION FOUND FLUID COMIN G FROM BEHIND NOSE GEAR STEERING ASSEMBLY. CONTACTED TECH SERVICE, RECOMMENDED THA WE REPLACE THE STRUT TUBE (PN 074309 01). REMOVED LEAKING STRUT TUBE FROM AIRCRAFT. INSTALLED NEW 07430901 TUB USED NEW SEAL KIT TCNC-1 AND SERVICED. INSP ECTED OLD TUBE FOR DAMAGE. FOUND THA THE TUBE WAS LEAKING BETWEEN THE INNER TUBE AND THE OUTER-MACHINED PART. FOUND PI NHOLE IN BRAZING OF THE PARTS. (K) 1 H 7 1 3O 3 O NT 3A13 1E4 2007092500181 20070925 00181 NM 2007 9 25 2007FA0000811 1 20070906 G 2410 B1731 BELT ROBSIN R22 R22BETA 7640110 NM LYC O360 O360C1F 41514 EA ALTERNATOR BROKEN D H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 WP 23 8372G 852 2782 ALTERNATOR LIGHT CAME ON DURING CRUISE FLIGHT. FOLLOWED HELICOPTER FLIGHT MANUAL PROCEDURES AND RETURNED TO LANDING. U PON INSPECTION IT WAS DISCOVERED THAT THE ALTERNATOR BELT HAD BROKEN AND DEPARTED THE AIRCRAFT IN FLIGHT. NO OTHER DAMA GE RESULTED 1 G 7 1 3O 3 O H10WE E286 2007092500249 20070925 00249 SW 2007 9 25 2007FA0000812 1 20070919 G 6320 20401077503 QUILL ASSY BELL 204 UH1H 1181407 SW LYC T53 T53* 41549 NE WORN B O OTHER O OTHER NR NOT REPORTED 1 WP 17 3053Q 82 661104 QUILL INTERNAL SPLINES WORN AND DAMAGED IN QUILL TUBE CONTACT AREA 1 G 7 1 4U 4 U EXPA1G71 E1EA 2007092500089 20070925 00089 SO 2007 9 25 2007FA0000813 1 20070920 G 5712 7847504 RIB PIPER PA28 PA28R200 7102811 SO LYC O360 IO360A1A 41514 EA WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 13 2702R 6441 28R35252 CRACKS FOUND DURING INSPECTION. CRACKS FOUND IN LOWER RELIEF EDGE MADE USE OF REPAIR KIT P/N: 767 - 397 NOT POSSIBLE. T HE CRACK REQUIRED REPLACEMENT OF ENTIRE RIB ASSY WITH NEW PART 78475-004 (AN IMPROVED PART). HAVE DIGITAL PHOTOS OF THE CRACKED RIB, THE CRACKS ARE CAUSED BY FLEXING OF THE SPAR BY THE LANDING GEAR SIDE BRACE DUE TO SIDE LOADS DURING LANDIN G. IF NO REPLACED I DON'T SEE AN INFLIGHT FAILURE, BUT COULD SEE POSSIBILITY OF LANDING GEAR COLLAPSE. 1 L 7 1 3O 3 O 2A13 1E10 2007092500110 20070925 00110 SO 2007 9 25 2007FA0000815 1 20070920 G 5712 7847504 RIB PIPER PA28 PA28R200 7102811 SO LYC O360 IO360A1A 41514 EA WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 13 2702R 6441 28R35252 CRACKS FOUND DURING INSPECTION, CRACKS FOUND IN LOWER RELIEF EDGE MADE USE OF REPAIR KIT P/N: 767 - 397 NOT POSSIBLE. TH E CRACK REQUIRED REPLACEMENT OF ENTIRE RIB ASSY. WITH NEW MFG PART 78475-004 (AN IMPROVED PART). HAVE DIGITAL PHOTOS OF THE CRACKED RIB, THE CRACKS ARE CAUSED BY FLEXING OF THE SPAR BY THE LANDING GEAR SIDE BRACE DUE TO SIDE LOADS DURING L ANDING. IF NO REPLACED I DON'T SEE AN INFLIGHT FAILURE, BUT COULD SEE POSSIBILITY OF LANDING GEAR COLLAPSE. 1 L 7 1 3O 3 O 2A13 1E10 2007092500142 20070925 00142 SO 2007 9 25 2007FA0000816 1 20070917 G 3810 91000106 SOCKET GULSTM GV GULFSTREAMGV 3980116 SO RROYCE BR700 BR700710A110 NE BURNED B K NONE B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 GL 15 23M 3606 579 THE SOCKET ON ONE OF THE (2) LAMPS BURNED CAUSING AN ELECTRICAL ODOR IN THE BAG BIN WHERE THE STERILIZER IS LOCATED. TH E 2 AMP CIRCUIT BREAKER WHICH CONTROLS THE POWER TO THE STERILIZER DID NOT POP. 2 L 7 2 4F 4 F RT A12EA E00057EN 2007092500145 20070925 00145 CE 2007 9 25 2007FA0000817 1 20070917 G 2434 DOFF10300B ALTERNATOR CESSNA 210 T210M 2073451 CE CONT O520 TSIO520* 17040 SO FAILED D D RETURN TO BLOCK H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 SW 15 732YK 458 21061879 OVERHAULED DOFF10300B ALTERNATOR FAILED AFTER 458 HOURS IN 35 MONTHS OF USE. 1 H 7 1 3O 3 O 3A21 E8CE 2007092500163 20070925 00163 SO 2007 9 25 2007FA0000818 2 20070919 G 8530 639614639615 ROCKER CESSNA 172 172H 2072424 CE CONT O300 O300D 17022 SO VALVE ROCKER MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 25 4960R 287 17256296 025668R ROCKER COVERS REMOVED DURING 100 HOUR INSPECTION TO INSPECT INTAKE AND EXHAUST ROCKERS FOR CORRECT INSTALLATION. FOUND N R1 AND NR6 CYLINDERS HAD INTAKE ROCKER (P/N 639614) INSTALLED IN THE EXHAUST VALVE POSITION. PARTS MANUAL CALLS FOR P/N 639615 ROCKER TO BE INSTALLED IN EXHAUST VALVE POSITION. THIS IS THE SECOND ENGINE DISCOVERED WITH THE SAME ABNORMALITY AFTER RECENT OVERHAULS FROM SAME OVERHAUL FACILITY. 1 H 7 1 3O 3 O NT 3A12 E253 2007092500170 20070925 00170 EA 2007 9 25 2007FA0000819 2 20070924 G 7414 LW14227 BEARING LYC PIPER PA28 PA28180 7102808 SO LYC O360 O360A4A 41514 EA MAGNETO DESTROYED D K NONE O OTHER IN INSP/MAINT 1 GL 19 5147L 857 857 284432 L3421136A BEARING LW14227 CAGE DESTROYED AND APPROXIMATELY 50 PERCENT MISSING. THIS IS THE ENGINE SIDE BEARING OF THE LW15416 MAG NETO DRIVE ADAPTER (MAGNETO ISOLATION DRIVE FOR RT MAGNETO)ENGINE HAS 857 HOURS SINCE FACTORY OVERHAUL IN 2000. 1 L 7 1 3O 3 O 2A13 E286 2007092500171 20070925 00171 EA 2007 9 25 2007FA0000820 2 20070924 G 8540 LW14227 BEARING PIPER PA28 PA28180 7102808 SO LYC O360 O360A4A 41514 EA ENGINE DESTROYED D K NONE O OTHER IN INSP/MAINT 1 GL 19 5147L 857 857 284432 L3421136A BEARING LW14227 CAGE DESTROYED AND APPROXIMATELY 50 PERCENT MISSING. THIS IS THE ENGINE SIDE BEARING OF THE LW15416 MAG NETO DRIVE ADAPTER (MAGNETO ISOLATION DRIVE FOR RIGHT HAND MAGNETO). ENGINE HAS 857 HOURS SINCE FACTORY OVERHAUL IN 200 0. 1 L 7 1 3O 3 O 2A13 E286 2007092500250 20070925 00250 CE 2007 9 25 2007FA0000822 1 20070904 G 3210 AN39227 PIN BEECH 36 A36 1151604 CE CONT O550 IO550* SO MLG SHEARED G A UNSCHED LANDING O OTHER LD LANDING 1 GL 13 998PL 848 100 E3036 THE LOWER IB BUSHING ON THE LOWER TORQUE LINK KNEE WAS DRY AND THE PIVOT PIN WHICH RIDES IN THE BUSHING WAS VERY TIGHT P OSSIBLY DUE TO A PLUGGED GREASE ZERK FITTING. THIS APPARENTLY CAUSED THE CLEVIS RETAINING PIN TO SHEAR (AS EVIDENCED BY THE SHEAR MARKS ON THE REMAINING PORTION OF THE PIN), THE PIVOT PIN TO FALL OUT AND THE GEAR TO EXTEND TO THE POINT WHER E IT WAS ONLY BEING HELD BY THE BRAKE LINE. ONCE THE AIRCRAFT TOUCHED DOWN THE UNRESTRAINED WHEEL ASSEMBLY TURNED AND WA S TORN FROM THE REST OF THE GEAR. 1 L 7 1 3O 3 O 3A15 E3SO 2007100200050 20071002 00050 EA 2007 10 2 2007FA0000823 2 20070824 G 7414 M3548 ROTOR CESSNA 172 172N 2072434 CE LYC O360 O360A4M 41514 EA SHAFT FAILED C E92R O OTHER O OTHER NR NOT REPORTED 1 GL 09 733XN 367 05120929 17268632 PILOT DEPARTED ON A VFR, DAY FLIGHT. DURING THE CLIMB FROM DEPARTURE, THE PILOT NOTICED A SLIGHT ENGINE ROUGHNESS THAT LASTED ONLY A SECOND. THE ENGINE SMOOTHED OUT UNTIL THE AC WAS LEVELED OUT AT CRUISE ALTITUDE AND CRUISE POWER SETTINGS THE ENGINE BEGAN RUNNING ROUGH. THE PILOT PERFORMED A MAGNETO CHECK IN FLIGHT FINDING THE RT MAGNETO INOPERATIVE. THE PILOT SWITCHED TO LT MAGNETO AND RETURNED TO LAND AT DEPARTURE WITHOUT INCIDENT. UPON OPENING THE MAGNETO, THE ROTO GE AR PN M3827 AND THE GEAR IN THE DISTRIBUTOR BLOCK ASSY PN K3822 WERE NOT DAMAGED AND WERE FREE OF OBSTRUCTION AND MOVED WITHOUT BINDING. THE SHAFT BROKE JUST BELOW THE SLOT IN THE SHAFT THAT HOLDS THE CAM WHICH OPENS THE CONTACTS. THERE D 1 H 7 1 3O 3 O NT 3A12 E286 2007100200052 20071002 00052 CE 2007 10 2 2007FA0000824 1 20070826 G 5343 05430161 FITTING CESSNA 172 172P 2072436 CE LYC O320 O320* 41508 EA NLG CRACKED D O OTHER O OTHER NR NOT REPORTED 1 GL 25 97873 11305 17276236 AC WAS BEING TAXIED FROM THE RAMP TO THE TAXIWAY, AND DURING TAXI, THE PILOTS REPORTED THAT THE NOSE GEAR STEERING SEEME D TO BE MALFUNCTIONING. UPON INSPECTION, THE NOSE GEAR STRUT APPEARED TO BE PRESSED UP AGAINST THE REAR HALF OF THE LOW ER COWLING. THE LOWER NOSE GEAR FITTING (PN 0543016-1) WAS INSPECTED AND FOUND TO BE CRACKED COMPLETELY OFF ON THE RT S IDE. THE LT SIDE OF THE NOSE GEAR FITTING WAS STILL INTACT. THE CAP PN 05430181 WHICH CLAPS THE NOSE GEAR STRUT TO THE LOWER NOSE GEAR FITTING WAS FOUND TO BE MISSING FROM THE AIRCRAFT. THE HARDWARE WHICH ATTACHED THE LT SIDE OF THE CAP TO THE LOWER NOSE GEAR FITTING WAS FOUND TO BE MISSING ALONG WITH THE CAP. (K) 1 H 7 1 3O 3 O NT 3A12 E274 2007100200058 20071002 00058 SO 2007 10 2 2007FA0000825 2 20070821 G 7314 64936849A1 PUMP DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA FUEL SYSTEM FAILED C B4VS O OTHER O OTHER NR NOT REPORTED 1 WP 07 708DC C0408 650211 AG9712 THE MIXTURE CONTROL SHAFT ON THE ENGINE DRIVEN FUEL PUMP FROZE UP AT HALF TRAVEL BETWEEN FULL RICH AND IDLE CUT OFF. TH IS CREATED A LEAN MIXTURE CONTROL WAS DISCONNECTED FROM THE FUEL PUMP, THEN THE FUEL PUMP CONTROL SHAFT HAD TO BE FREED UP. THE MIXTURE CABLE WAS COMPLETELY FREE WITH NO BINDING ONCE DISCONNECTED FRO THE FUEL PUMP. THE FUEL PUMP WAS REPLA CED AND SENT BACK TO MFG. (K) 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2007100200086 20071002 00086 CE 2007 10 2 2007FA0000826 1 20070808 G 2731 NAS302261510 CONTROL CABLE BEECH 300 300BEECH 1152930 CE ELEVATOR TRIM FRAYED D K NONE O OTHER IN INSP/MAINT 1 NE 05 122RG 389 FL448 DURING SCHEDULED INSPECTION OF THE AC, THE MECHANIC FOUND THE LT ELEVATOR PITCH TRIM CONTROL CABLE CHAFING ON THE ELEVAT OR CABLE PASS THROUGH HOLE LOCATED IN SKIN PN 101-620000-3. THE ELEVATOR CABLE PASS THROUGH HOLE REQUIRED TRIMMING TO A LLOW PROPER CLEARANCE. ADJUSTMENTS TO PASS THROUGH HOLE ACCOMPLISHED IAW IAW MFG. (K) 2 L 7 2 4T A24CE 2007100200087 20071002 00087 CE 2007 10 2 2007FA0000827 1 20070814 G 7500 4536102150V431 MANIFOLD LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE731* 01518 WP LT ENGINE DAMAGED B KKQR O OTHER O OTHER NR NOT REPORTED 1 GL 11 858MK 2402 141 LT PYLON OVERHEAT INDICATION OCCURRED IN FLIGHT. FOUND HIGH PRESSURE BLEED AIR MANIFOLD MATING FLANGE DEFORMED. REPLAC ED ASSY 4536102150V43-1 WITH NAV ASSY 45361020228-001. CAUSE MAY BE AGE OR REPEATED CLAMPING. ORIGINAL PART HAS BEEN S UPERSEDED BY THE MFG. (K) 2 L 7 2 4F 4 F RT T00008WI E6WE 2007100300004 20071003 00004 SO 2007 10 3 2007FA0000828 2 20070906 G 8530 SA52000A20P CYLINDER CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO NR 2 CRACKED D O OTHER O OTHER NR NOT REPORTED 1 AL 03 4891Z 1790 U20606044 818885R CYLINDER HEAD HAS A CRACK. BEGINNING AT INTAKE PORT AND EXTENDING TO UPPER SPARK PLUG HOLE. (K) 1 H 7 1 3O 3 O A4CE E5CE 2007100200090 20071002 00090 WP 2007 10 2 2007FA0000829 1 20070831 G 6720 369D21800501 CONTROL SYSTEM HUGHES 369 369D 4470706 WP T/R PITCH ROUGH B EOOR O OTHER O OTHER NR NOT REPORTED 1 AL 03 C6DCM 1181 DURING 100 HR INSPECTION, PLAY WAS NOTICED BETWEEN THE ROTATING AND NOT-ROTATING SWASH PLATES OF THE TAIL ROTOR PITCH CO NTROL AFTER REMOVAL, IT WAS NOTED THAT THE BEARING WAS DRY AND ROUGH. RECORDS INDICATE IT WAS REGREASED IN DEC OF 2006. (K) 1 G 7 1 3U H3WE 2007100300006 20071003 00006 CE 2007 10 3 2007FA0000830 1 20070912 G 5755 COVER BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE SPOILER MIXER CORRODED B KX5R K NONE O OTHER IN INSP/MAINT 1 GL 15 156DH RK36 WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND SPOILER MIXER ASSEMBLY BOX COVER NOT SEALED. REMOVED COVER AND FOUND CORROSION ON ACTUATOR AND MIXER ASSEMBLY. RECOMMEND THAT THE SPOILER MIXER AREA BE INSPECTED THOROUGHLY THE BOX COVER R EMOVED. INSTALLED THE BOX COVER WITH THE APPROPRIATE SEALANT. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007100300007 20071003 00007 CE 2007 10 3 2007FA0000831 1 20070912 G 2120 45A63517073 AIR DUCT BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE BLEED AIR CRACKED B KX5R K NONE O OTHER IN INSP/MAINT 1 GL 15 156DH RK36 WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND THE LEFT AFT FUSELAGE BLEED AIR LINE BELLOWS BLOWN APART PN 45A63517-0 73 AND THE RT AFT FUSELAGE BLEED AIR LINE BELLOWS BRAIDING FRAYING PN 45A63517-075. WHEN THE LT BLEED AIR LINE BLEW APA RT IT CRACKED A FUSELAGE BULKHEAD AT UPPER FRAME STATION 329.92 AND BP 29.92L. WOULD RECOMMEND THAT DETAILED INSPECTION S OF THESE BLEED AIR LINES BE PERFORMED AT SCHEDULED INTERVALS AND THE UPPER FRAME STATION IN THE AREA AROUND THE BLEED AIR LINES BE CAREFULLY INSPECTED FOR DAMAGE. IT IS SUSPECTED THAT BOTH THE BLEED AIR LINES FAILED DUE TO FATIGUE OR TIM E IN SERVICE. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007100300008 20071003 00008 CE 2007 10 3 2007FA0000832 1 20070912 G 5610 45AS3101012 WINDOW BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE COPILOT CRACKED B KX5R K NONE O OTHER IN INSP/MAINT 1 GL 15 141DR RK184 WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND COPILOT COCKPIT SIDE WINDOW CRACKED USING THE PRISM INSPECTION METHOD. THE D-INSPECTION REQUIRES THAT BOTH WINDSHIELDS BE INSPECTED BY REMOVING THE WINDSHIELD RETAINERS OR USING OPTICAL PRI SM INSPECTION METHOD. THERE IS NO STATEMENT IN THE AC MM OR IN THE A-D INSPECTION CHECKLIST THAT REQURIES YOU TO INSPEC T THE COCKPIT SIDE WINDOWS IN THE SAME MANNER AS THE WINDSHIELDS. ALL OF THE WINDOWS IN THE COCKPIT AREA ARE INSTALLED OR FASTENED IN THE SAME MANNER AS THE WINDSHIELDS. IT IS SUSPECTED THAT THE COPILOT SIDE WINDOW CRACKED FROM FATIGUE, O R TOTAL TIME INSTALLED. THE WINDOW WAS MFG MAY OF 1997. WOULD RECOMMEND THAT INSPECTION OF ALL COCKPIT WINDOWS WITH A 2 H 7 2 4F 4 F RT A16SW E25EA 2007100300010 20071003 00010 CE 2007 10 3 2007FA0000833 1 20070912 G 5510 STRUCTURE BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE HORIZONTAL STAB DAMAGED B KX5R K NONE O OTHER IN INSP/MAINT 1 GL 15 141DR RK184 WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND 6 SHEARED RIVETS AND 2 LOOSE RIVETS IN THE FORWARD RIVET LINE OF THE A TTACHMENT PIVOT FITTING PN 45A21183-11 ON THE BOTTOM OF THE HORIZONTAL STABILIZER. IT IS SUSPECTED THAT THE MISSING RIV ETS FAILED FROM FATIGUE. RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION, CONTACTING MFG FOR REPAIR OPTIONS. T HIS IS SECOND AC THAT THE SAME DISCREPANCY HAS BEEN FOUND. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007100300011 20071003 00011 CE 2007 10 3 2007FA0000834 1 20070912 G 5510 STRUCTURE BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE HORIZONTAL STAB DAMAGED B KX5R K NONE O OTHER IN INSP/MAINT 1 GL 15 156DH RK36 WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND 8 SHEARED RIVETS IN THE FORWARD RIVET LINE OF THE ATTACHMENT PIVOT FIT TING PN 45A21183-11 ON THE BOTTOM OF THE HORIZONTAL STABILIZER. IT IS SUSPECTED THAT THE MISSING RIVETS FAILED FROM FAT IGUE. RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007100300012 20071003 00012 CE 2007 10 3 2007FA0000835 1 20070802 G 2760 3321209 ADJUSTER LEAR LEAR 25 25D 5170514 CE BRAKE VALVE DAMAGED B O OTHER O OTHER NR NOT REPORTED 1 CE 09 9711105 UPON VISUAL INSPECTION OF THE POWER BRAKE VALVE PN 60810741-804, SN 9711105, IT WAS FOUND THAT THE ADJUSTMENT SCREW HAD BEEN GROUND DOWN AND MODIFIED. AS WE BEGAN TO LOOK THROUGH SB 23/24/25-32-12 AND FOUND THAT THIS UNIT PN WAS NOT IN TH IS SB. WE THEN FOUND THAT THIS UNIT WAS FOR A LEAR 60. WE THEN LOOKED INTO THE MFG PARTS BREAKDOWN AND FOUND THAT THE LEVER AS WELL AS THE MODIFIED ADJUSTMENT SCREW, THE STOP SCREW AND PIN DID NOT BELONG ON THIS PN OF POWER BRAKE VALVE. THISE PARTS ARE FOR A PN 2380002 OR PN 2381443 OR PN 3321200-3 POWER BRAKE VALVE. WE CONTACTED OUR CUSTOMER AND FOUND T HAT THIS UNIT WAS REMOVED FROM LEAR 25D. 2 L 7 2 4J A10CE 2007100300013 20071003 00013 CE 2007 10 3 2007FA0000836 1 20070806 G 3411 STATIC SYSTEM LEAR 35 35A 5170602 CE GARRTT TFE731 TFE731* 01518 WP MISINSTALLED B O OTHER W INADEQUATE Q C NR NOT REPORTED 1 CE 09 621RB 211 THIS RVSM AIRCRAFT HAD AN ALTIMETRY SYSTEM SPLIT. CONTACTED STC GROUP HOLDER FOR PROPER ROUTING OF STATIC SYSTEM PLUMBI NG. FOUND CO-PILOTS SYSTEM WAS NOT CROSS COUPLED WITH PILOTS SYSTEM. INSTALLED FABRICATED HOSES TO THE CO-PILOTS SYSTE M TO MEET STC NR ST 00563DE-D. PROBABLE CAUSE: CO-PILOTS STATIC SYS NOT CROSS-COUPLED AT STC INSTALLATION OR SYSTEM WAS MODIFIED/ ALTERED POST-STC WITHOUT APPROVED DATA. (K) 2 L 7 2 4F 4 F A10CE E6WE 2007100300014 20071003 00014 NE 2007 10 3 2007FA0000837 2 20070822 G 7230 BLADE BOEING 737 737800* NM CFMINT CFM56 CFM567B26US NE HPC DAMAGED B QEMY O OTHER O OTHER NR NOT REPORTED 1 EA 35 EIDCN XAEF2436 892123 ENGINE SURGED ON WING AND WAS INDUCTED INTO SHOP FOR I/V. DURING STRIP IT WAS NOTED THAT 1 OFF HPC STAGE 3 BLADE HAD BE EN LIBERATED TOGETHER WITH A SECTION OF THE DOVETAIL FROM THE STG 3 DISK. SECONDARY DAMAGE WAS ALSO NOTED ON THE HPC RO TOR AND STATORS. INSPECTION OF THE FRONT STATOR CASES REVEALED THAT A VSV STAGE 3 LEVER ARM WAS MISSING AND APPEARED NO T TO HAVE INSTALLED. NB ESN 892123 INPUTTED AS 1ST SV SINCE NEW. (K) 2 L 7 2 4F 4 F RT A16WE E00055EN 2007100300015 20071003 00015 GL 2007 10 3 2007FA0000838 2 20070815 G 7230 6898607 BEARING SCWZER 269 269D 8059501 EA ALLSN 250C 250C20 03013 GL NR 1 FAILED C O OTHER O OTHER NR NOT REPORTED 1 SW 03 411HV 0040A CAE845096 PILOT REPORTED CHIP LIGHT CAME ON DURING TRAINING FLIGHT. LANDED AS SOON AS POSSIBLE AND PROBE REMOVED AND CLEANED. GR OUND RUN MADE IAW MM AND CHIP PULLED AND INSPECTED. MORE METAL FOUND SO ENGINE REMOVED FROM AC AND INSPECTED. FOUND NR 1 BEARING OF COMPRESSOR ASSY FAILING. NO EVIDENCE OF OVERHEATING OR OIL STARVATION. PILOT REPORTED NO LOSS OF OIL PRE SSURE DURING FLIGHT. (K) 1 G 7 1 3U 3 U 0 4H12 E4CE 2007100300018 20071003 00018 SO 2007 10 3 2007FA0000840 2 20070818 G 7322 1048931 CARBURETOR CESSNA 182 182G 2072716 CE CONT O470 O470R 17026 SO ENGINE FAILED D O OTHER O OTHER NR NOT REPORTED 1 WP 19 2347R 18255447 1316145R PILOT REPORTED THAT AFTER A NORMAL START, HE WAS UNABLE TO ADVANCE THE THROTTLE CONTROL TO CRUISE OR TAKEOFF POWER. A P ARTIAL DISASSEMBLY OF THE CARBURETOR REVEALED THAT THE AIR METERING PIN/AIR METERING JET WAS BLOCKING THE THROTTLE SHAFT TRAVEL. THE CARBURETOR WAS SENT FOR REPAIR. (K) 1 H 7 1 3O 3 O NT 3A13 E273 2007100300019 20071003 00019 EA 2007 10 3 2007FA0000841 2 20070818 G 8530 AEL65102 CYLINDER CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA NR 4 FAILED D A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 GL 13 9815L 17276618 DURING CRUISE FLIGHT, THE PILOT REPORTED A LOUD BANG FOLLOWED BY EXCESSIVE VIBRATION, INCREASED POWER TO FULL TO MAINTAI N ALTITUDE AND MADE A WELL-EXECUTED,, PRECAUTIONARY LANDING. AFTER SHUTDOWN THERE WAS A LARGE OIL PUDDLE DEVELOPING UND ER THE AIRCRAFT. AIRPLANE COWL REMOVED AND NR 4 CYLINDER WAS FOUND TO HAVE THE TOP HALF SEPARATED FROM THE BOTTOM. THI S CYLINDER REPORTED TO BE IN SERVICE LESS THAN A YEAR. THE CYLINDER HAS THE CASTING NR AEL85099 WHICH IS NOT SUBJECT TO AD2006-12-07 OR SB NR 05-8. ENGINE HAS (3) OTHER CYLINDERS WITH THE SAME CASTING NUMBER INSTALLED. IT IS ESTIMATED TH AT ENGINE LOST 2.5 QUARTS OF OIL DURING THE FEW MINUTES BETWEEN THE SEPARATION AND THE SHUTDOWN. MECHANIC SUGGEST FAA L 1 H 7 1 3O 3 O NT 3A12 E274 2007100300020 20071003 00020 SO 2007 10 3 2007FA0000842 2 20070907 G 8530 654375 ROCKER SHAFT CONT O200 O200* 17020 SO CYLINDER LOOSE D K NONE O OTHER IN INSP/MAINT 1 SO 03 977CC 256314 IAW OWNERS REQUEST, REMOVED ALL (4) ROCKER COVERS TO INSPECT THE ROCKER SHAFT AND SET SCREWS. AFTER REMOVING THE ROCKER COVERS. FOUND ALL(4) SET SCREWS LOOSE AND ALL (4) SHAFTS MOVED TOWARD THE INTAKE SIDE OF THE BOSSES. NONE HAVE CUT THE ROCKER COVERS YET, IN ANOTHER 20 HOURS OR SO THEY WOULD. NOTE: THE NEW ENGINE HAVE A FLAT CUT INTO THE ROCKER SHAFT, A ND A SET SCREW IN THE CENTER BOSS, TO RETAIN THE SHAFT. ALSO, THE SHAFT IS SHARP ON THE END, UNLIKE THE OLD STYLE, AND HAVE A CUT MARK ACROSS THE END OF THE SHAFT FOR USE IN ALINING THE FLAT FOR THE SET SCREW. THE SET SCREW IS A MS51963-6 4, AND USES NO LOCKTITE, OR MECHANICAL TYPE LOCK. THE FLAT IN THE ROCKER SHAFT IS NOT DEEP ENOUGH TO PROVIDE ADEQUATE L 3 O E252 2007100300022 20071003 00022 GL 2007 10 3 2007FA0000844 1 20070813 G 2731 700232 CABLE WACO YMF YMFF5C 9600425 GL JACOBS R755 R7557 35003 EA HAMSTD 2B 2B20 NE PITCH SERVO INOPERATIVE C O OTHER O OTHER NR NOT REPORTED 1 GL 09 919TT F5C111 22353 31606 THE PITCH SERVO BRIDLE CABLE WAS FOUND TO BE LOOSE AND NOT CONNECTED TO THE CAPSTAN. IT WAS WOUND BETWEEN THE BOTTOM EN D OF THE CAPSTAN AND THE CAPSTAN END PLATE WITH THE CLAMP TO THE ELEVATOR CABLE HAVING BEEN SLIDING ON THE ELEVATOR CABL E. THE ELEVATOR WAS FOUND TO BE FREE TO MOVE NORMALLY IT IS NOT KNOWN HOW THIS MALFUNCTION OCCURRED. IT IS POSSIBLE TH AT THE BRIDLE CABLE CLAMP WAS NOT SUFFICIENTLY TIGHT ALLOWING THE BRIDLE CABLE TO BECOME SLACK AND COMING LOOSE IN THE C APSTAN. (K) 1 Q 7 1 3R 3 R ATC542 5E11 5 C P255 2007100300023 20071003 00023 SO 2007 10 3 2007FA0000845 2 20070817 G 7414 6314 MAGNETO CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO ENGINE ARCED D K NONE O OTHER IN INSP/MAINT 1 SO 05 814RA 444 1663 FP4677 DURING ANNUAL INSPECTIO, 500 HR MAG INSP COMPLIED WITH EARLY DUE TO NR OF HOURS PREVIOUSLY FLOWN. BOTH MAGNETOS SHOWED SAME INTERNAL ARCING, SO SEVERE, THAT BRUSH HOLDER PN K3823 WAS MELTED/ BURNED UP, CONTACTED SLICK TECH SUPPORT 904-739- 4360, OUR MAG S/N`S WERE MATCHED TO PROBLEM MAGS WHICH SLICK WAS AWARE OF CARBON USED IN MFG OF BRUSHES TOO SOFT, CARBON DUST CAUSED ARCING. IT IS A WONDER THIS CUSTOMERS ENGINE CONTINUED TO RUN. (K) 1 L 7 1 3O 3 O NT A00009CH E1CE 2007100300026 20071003 00026 CE 2007 10 3 2007FA0000846 1 20070913 G 5520 05341221 HORN CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA ELEVATOR LOOSE D O OTHER O OTHER NR NOT REPORTED 1 NE 05 672EB 1827 172S8672 ELEVATOR HORN BEARING LOOSE IN BORE OF HORN, PN 0534122-1, BEARING ITSELF IS NOT WORN OUT BUT THERE IS PLAY BETWEEN THE TWO PARTS. 1 H 7 1 3O 3 O NT 3A12 1E10 2007100300017 20071003 00017 GL 2007 10 3 2007FA0000849 1 20070926 G 5350 18583002 FAIRING CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO RT WING ROOT SEPARATED D O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 EA 21 631SR 200 200 2442 LOWER SECTION OF RT WING ROOT FAIRING SEPARATED FROM AIRCRAFT IN FLIGHT. FAIRING IS RETAINED WITH JUST A FEW SCREWS AND AN AREA OF THE LOWER PORTION OF FAIRING IS RETAINED WITH DOUBLE SIDED TAPE AND AN AREA OF DOUBLE SIDED TAPE CAME DEBOND ED AND AIR GOT UNDER IT AND IT RIPED OFF. 1 L 7 1 3O 3 O NT A00009CH E3SO 2007100300025 20071003 00025 CE 2007 10 3 2007FA0000850 1 20070927 G 7810 02R3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA RT ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 12033 280 PCE85195 WHILE PERFORMING SCHEDULED MAINTENANCE, REMOVED RT EXHAUST STACKS TO FACILITATE INSPECTING THE EXHAUST DUCT. FOUND A 1 INCH CRACK IN THE SKI SLOPE. SB 3380 WAS COMPLIED WITH 711 HOURS EARLIER. POWER SECTION WAS PULLED AND SENT OFF FOR RE PAIR. 1 L 7 2 4T 4 T A24CE E4EA 2007101100208 20071011 00208 CE 2007 10 11 2007FA0000851 1 20071001 G 3250 S11073 ROD END CESSNA 182 182A 2072704 CE CONT O470 O470* 17026 SO MLG BROKEN G O OTHER J WARNING INDICATION LD LANDING 1 SO 15 2145G 51445 ROD END AT STEERING COLLAR SHEARED CAUSING LOSS OF DIRECTIONAL CONTROL. 1 H 7 1 3O 3 O NT 3A13 E273 2007101100211 20071011 00211 NE 2007 10 11 2007FA0000852 3 20070924 G 6114 MS24665134 COTTER PIN RKWELL OV10 OV10A 6402512 GL HAMSTD 33LF 33LF NE PROP SPINNER MISSING G O OTHER O OTHER CR CRUISE 1 SO 15 614V 33813 SPINNER WAS LOST FROM RT ENGINE WHILE IN A RT TURN AT 7000 FT DAMAGING ONE PROPELLER BLADE. SPINNER NOT RECOVERED. 1 H 7 2 4T RT EXPX1H72 5 C P20EA 2007101100220 20071011 00220 CE 2007 10 11 2007FA0000853 1 20070920 G 7810 310103901 FLANGE BEECH 90 E90 1152914 CE PWA PT6 PT6A135 52043 NE EXHAUST CRACKED D O OTHER O OTHER NR NOT REPORTED 1 GL 15 90XS LW342 (2) NEW ENGINES WERE INSTALLED IAW MFG MODIFICATIONS, WITH 938.0 HRS SINCE NEW. AIRCRAFT WAS IN FOR A PHASE INSPECTION AND FOUND 3 OUT OF L1 EXHAUST FLANGES ON THE ENGINE CRACKED. ACCORDING TO THE MFG PARTS MANUAL, EXHAUST STIFFENERS ARE NOT USED ON THIS SN AC AND ARE NOT USED WITH MFG INSTALLATION INSTRUCTIONS. (K) 1 L 7 2 3T 4 T 3A20 E4EA 2007101500227 20071015 00227 CE 2007 10 15 2007FA0000854 1 20070809 G 7810 40B22318 EXHAUST STACK CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA MCAULY 3D36C B3D36C432 GL ENGINE LOOSE B Z08R O OTHER O OTHER NR NOT REPORTED 1 CE 07 168JS 98 T20608735 L1266161E DURING AN INSPECTION, FOUND THE EXHAUST STACK AT NR 2 CYLINDER, PULLED DOWN .0625 INCH APPROX. FURTHER INVESTIGATION FO UND THE NR1, NR3, NR5 AND NR 6 ENGINE CYLINDERS EXHAUST STACKS PULLED DOWN, BUT NOT AS MUCH. AFTER RECOMMENDATIONS FROM ENGINE MFG ALSO, THE SUPPLIER EXHAUST SYSTEM (WHICH IS ONE IN THE SAME). DURING THE ENGINE CYLINDER REMOVAL PROCESS FO UND LOWER FWD, .7500 INCH STUD NUT UNDER TORQUED. FURTHER INVESTIGATION REVEALED THE FORWARD 2 STUDS BOTH BELOW, MFG RE COMMENDED DRIVING TORQUE OF CYLINDER HOLDDOWN STUDS IN CASE. INSTALLED NEW OVERSIZE (.003) STUDS IAW ENG MFG RECOMMENDA TIONS. INSTALLED NEW NR 2 ENGINE CYLINDER AND NEW EXHAUST CROSSOVER PIPE AS REQUIRED. TIGHTENING THE EXHAUST FLANGE NU 1 H 7 1 3O 3 O RT A4CE E14EA 5 C P58GL 2007101500229 20071015 00229 GL 2007 10 15 2007FA0000855 2 20070906 G 7320 23072790 FADEC BELL 407 407 1182206 SW ALLSN 250C 250C47B GL FAILED B VK1R O OTHER O OTHER NR NOT REPORTED 1 SW 19 509PD 350 53703 CAE847760 AIRCRAFT WAS STARTED IN A NORMAL MANNER. JUST PRIOR TO LIFT OFF THE (FADEC FAIL), (AUTO RELIGHT) WARNING LIGHTS ILLUMIN ATED AND THE FADEC FAIL HORN SOUNDED. NO LIMITATIONS WERE RECORDED OR OBSERVED. THE FADEC CONTROL ASSY WAS RETURNED TO MFG FOR ANALYSIS. (K) 1 G 7 1 3U 3 U O H2SW E1GL 2007101500233 20071015 00233 2007 10 15 2007FA0000856 4 20070911 G 3457 066011480102 RECEIVER CESSNA 208 208B 2073701 CE PWA PT6 PT6* 52043 EA GPS SMOKE D A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 GL 25 24MG 1664 208B0850 SHORTLY AFTER TAKEOFF FROM ISP THE PILOT NOTICED SMOKE IN THE COCKPIT. THE PILOT IMMEDIATELY RETURNED TO DEPARTURE AND LANDED. THE PILOT REPORTED THAT THE SMOKE APPEARED TO BE CAUSED BY AN ELECTRICAL PROBLEM. THE PILOT REPORTED THAT THE GPS NO LONGER OPERATED. ON 9/12/2007, MECHANIC INSPECTED THE AIRCRAFT, REMOVED THE GPS AND FOUND THAT IT SMELLED OF ELE CTRICAL SMOKE, THE MECHANIC EXAMINED THE RADIO RACK, WIRING HARNESSES AND ENTIRE INSTRUMENT PANEL AREA AND FOUND NO PROB LEM. THE ENGINE COMPARTMENT AND ELECTRICAL EQUIPMENT BOX WERE INSPECTED WITH NO PROBLEMS FOUND. THE AIRCRAFT WAS GROUN D RUN AND ALL ELECTRICAL EQUIPMENT WAS OPERATIONAL TESTED WITH THE GPS UNIT REMOVED AND ALL OPERATED NORMALLY. THE GPS 1 H 7 1 3T 3 T A37CE E2NE 2007102300058 20071023 00058 CE 2007 10 23 2007FA0000858 1 20070427 G 5711 1369 SPAR BBAVIA 11 11CC 9140404 CE CONT C85 C85* 17008 SO RT WNG DETERIORATED D O OTHER O OTHER NR NOT REPORTED 1 NM 05 4546E 11CC249 REPORT IAW AD 200-25-02R1 PARAGRAPH D (4) LOOSE, MISSING AND RUSTED NAILS IN RIBS ALLOWING RUSTY MOISTURE INTO SPAR, FRE TTING ON TOP CAP GREATER THAN .0625 INCH ON LOOSE RIBS, CRACKS AT AILERON BELLCRANK BRACKET, CAUSED FROM OVER TORQUING O F BOLTS, PREVIOUS WING TIP DAMAGE, LOGS MISSING HISTORY, SPARS REPLACED. (K) 1 H 7 1 3O 3 O A796 E233 2007101600001 20071016 00001 SW 2007 10 16 2007FA0000859 1 20070726 G 5711 5146R SPAR BBAVIA 7 7FC 2110124 SW CONT C90 C90* 17009 SO RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 06 9032B 3177 7FC123 AC WAS BEING MODIFIED TO INCLUDE THE INSTALLATION OF WING SPAR INSPECTION HOLE KIT IAW STC NR SA005278E. A PORTION OF T HE WING LEADING EDGE SKIN WAS REMOVED AND THE WING SPAR WAS VISUALLY INSPECTED AS SPECIFIED IN THE INSTALLATION INSTRUCT IONS SUPPLIED WITH THE STC. DURING THIS VISUAL INSPECTION, A CRACK WAS OBSERVED ON THE TOP SURFACE OF THE RT WING FRONT SPAR. THE CRACK ORIGINATES AT THE IB AND OF THE AFT PLYWOOD REINFORCEMENT PLATE. REINFORCEMENT PLATE IS LOCATED ON TH E AFT SIDE OF THE FRONT SPAR, UNDER THE LT STRUT ATTACHMENT FITTING. THE CRACK PROGRESSES OB ALONG THE TOP SURFACE OF T HE SPAR AT A SLIGHT FORWARD ANGLE (CRACK ANGLE TOWARD THE FORWARD PLYWOOD REINFORCEMENT PLATE). THE SURFACE OF THE CRAC 1 H 7 1 3O 3 O A759 E252 2007101600002 20071016 00002 SO 2007 10 16 2007FA0000860 1 20070815 G 3297 CONNECTOR GULSTM GV GULFSTREAMGV 3980116 SO RROYCE BR700 BR700710A110 NE NLG STEERING CORRODED D O OTHER O OTHER NR NOT REPORTED 1 EA 11 509QS 6740 637 EXCESSIVE CORROSION AT CONNECTOR PINS CAUSING NWS FAIL MSG. SUGGEST PERIODIC INSPECTION AND CLEANING OR IMPROVED CONNEC TOR SEALING FROM MOISTURE. (K) 2 L 7 2 4F 4 F RT A12EA E00057EN 2007101600003 20071016 00003 GL 2007 10 16 2007FA0000861 1 20070820 G 7810 15070001 EXHAUST HEADER CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO NR 5 CRACKED D UV4R O OTHER O OTHER NR NOT REPORTED 1 SO 15 516CR 306 1309 NR 5 EXHAUST HEADER HAS CRACKED OFF AT FLANGE, JUNE 6/06 AT 440.6, NOV 18/06 AT 636.1 HOBBS, MAY 18/07 AT 746.7 HOBBS AN D AGAIN AUG 20/07 HOBBS NOT AVAILABLE. AFTER INSPECTING HEADER IT WOULD SEEM THAT A HEAVER GAUGE PIPE WOULD RESOLVE THE PROBLEM. THE LAST HEADER WAS INSTALLED WITH BACK UP FLANGES WELDED TO PIPE AT FLANGE SECTION WITH NO EFFECT. (K) 1 L 7 1 3O 3 O NT A00009CH E3SO 2007101600004 20071016 00004 GL 2007 10 16 2007FA0000862 2 20070815 G 7230 672332390 RETAINING RING RROYCE ALLSN 250C 250C20B 03013 GL COMPRESSOR FRACTURED C O OTHER O OTHER NR NOT REPORTED 1 SO 05 2 CAC37235 OPERATOR REPORTED ENGINE CHIP LIGHTS AND A PRECAUTIONARY LANDING WAS MADE. INSPECTION OF ENGINE CHIP DETECTORS REVEALED ONE SMALL PIECE OF THE FAILED RETAINING RING HAD CAUSED THE LIGHT. THE COMPRESSOR WAS REMOVED FROM THE ENGINE AND FURT HER INVESTIGATION REVEALED THE RETAINING RING HAD FRACTURED INTO 5 PIECES. 3 PIECES WERE CONTAINED IN THE RETAINING RIN G GROOVE OF THE IMPELLER, 1 PIECE WAS IN THE GEARBOX SUMP AREA AND THE 5TH PIECE WAS RECOVERED FROM THE CHIP DETECTOR. THE FAILED RETAINING RING SCORED THE SPUR ADAPTER GEAR ADJACENT TO THE RETAINING RING GROOVE IN THE IMPELLER. NO FURTHE R DAMAGE WAS NOTED. A NEW SPUR ADAPTER GEAR AND RETAINING RING WERE INSTALLED AND THE COMPRESSOR RETURNED TO SERVICE. 3 U E4CE 2007101600009 20071016 00009 GL 2007 10 16 2007FA0000863 1 20070814 G 2720 30730501 RUDDER PEDAL AVIAT A1 A1B 2210406 GL LYC O360 O360* 41514 EA COCKPIT FAILED D O OTHER O OTHER NR NOT REPORTED 1 AL 03 304C 2113 RUDDER PEDAL OPERATION CAN LEAD TO NO BRAKE OPERATION AT FULL TRAVEL OF RUDDER. SENDING IN THIS FIELD APPROVAL REQUEST FOR A VERNIER MIXTURE CONTROL. BELIEVE THAT THE LT RUDDER PEDAL WHEN PRESSED FULLY ALLOWS YOU TO DEPRESS THE RT BRAKE OV ER CENTER THUS GIVING YOU NO BRAKE AND DILEMMA WHEN APPLYING THE BRAKE. THE SAME THING HAPPENS IN REVERSE WHEN THE RT P EDAL IS DEPRESSED FULLY AND THEN THE LT BRAKE WILL GO OVER CENTER AND BECOME USELESS. THIS AC, AS AN EXAMPLE WAS GROUND LOOPED AT 68 HRS TT. IF THIS CONDITION CAN BE ACHIEVED EASILY ON THE GROUND THEN IT COULD HAPPEN ON LANDING, IN A CRO SSWIND OR TURN. FURTHER MORE THE BRAKE PEDAL IN THE OVER CENTER CONDITION WILL BE POINTED FORWARD AND AT A 90 DEGREE AN 1 H 7 1 3O 3 O NC A22NM E286 2008011400199 20080114 00199 EU 2008 1 14 2007FA0000864 2 20070809 G 8530 02722001002R1 CYLINDER HEAD DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE12501 59300 EU ENGINE FAILED D O OTHER O OTHER NR NOT REPORTED 1 SW 99 240TS 42072 ENGINE BEGAN LOSING COOLANT BY PRESSURIZING THE COOLING SYSTEM WITH COMBUSTION PRESSURE AND BLOWING COOLANT OVERBOARD. WHEN CYLINDER HEAD WAS REMOVED, EACH CYLINDER HAD A CRACK BETWEEN THE GLOW PLUG AND EXHAUST VALVE RECESS. THE ENGINE HA D PASSED A COMPRESSION CHECK AND IT IS SUSPECTED THAT THE CRACKS WOULD ONLY LEAK WHEN THE ENGINE WAS WARMED TO OPERATING TEMPERATURE. THE RESULTANT COOLANT LOSS ONLY INCREASES THE PROBABILITY OF FURTHER TEMPERATURE EXCURSIONS. A PROBABLE CAUSE WOULD BE INADEQUATE DISTANCE IN THE CASTING OF THE CYLINDER HEAD BETWEEN THE EXHAUST VALVE RECESS AND THE GLOW PLU G. ALTERNATE CAUSES INCLUDE INADEQUATE COOLING PROVIDED BY THE AIRFRAME MFG, INADEQUATE WATER JACKETING IN THE ENGINE R 1 L 7 2 3I 3 B RT A57CE E00069EN 2008011400200 20080114 00200 EU 2008 1 14 2007FA0000865 2 20070809 G 8530 02722001002R1 CYLINDER HEAD DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE12501 59300 EU ENGINE FAILED D O OTHER O OTHER NR NOT REPORTED 1 NM 11 350TS 42061 ENGINE BEGAN LOSING COOLANT BY PRESSURIZING THE COOLING SYSTEM WITH COMBUSTION PRESSURE AND BLOWING COOLANT OVERBOARD. WHEN CYLINDER HEAD WAS REMOVED, EACH CYLINDER HAD A CRACK BETWEEN THE GLOW PLUG AND EXHAUST VALVE RECESS. THE ENGINE HA D PASSED A COMPRESSION CHECK AND IT IS SUSPECTED THAT THE CRACKS WOULD ONLY LEAK WHEN THE ENGINE WAS WARMED TO OPERATING TEMPERATURE. THE RESULTANT COOLANT LOSS ONLY INCREASE THE PROBABILITY OF FURTHER TEMPERATURE EXCURSIONS. A PROBABLE C AUSE INCLUDE INADEQUATE COOLING PROVIDED BY THE AIRFRAME MFG, INADEQUATE WATER JACKETING IN THE ENGINE RESULTING IN HOT SPOTS WHICH COULD LEAD TO CRACKING, AND ENGINE RUNNING AT A HIGHER RPM THAN THE COOLING SYSTEM COULD HANDLE. 1 L 7 2 3I 3 B RT A57CE E00069EN 2007101600010 20071016 00010 CE 2007 10 16 2007FA0000866 1 20070907 G 2497 691835432 BUSS BAR CESSNA 680 680CE 2076811 CE PWC PW306 PW306C 52169 NE LT JBOX LOOSE D O OTHER O OTHER NR NOT REPORTED 1 EA 03 227DH 655 6800086 THE AIRCRAFT WENT TO START ENGINES, 6 CAS MESSAGES APPEARED ON THE DISPLAY. TROUBLESHOT PROBLEM AND FOUND MOUNTING STUD FOR EMERGENCY BUSS BAR WAS LOOSE CAUSING ARCING AND WELDING OF THE STUD. THIS STUD WAS LOOSE FROM FACTORY. DO AN INSP ECTION OF ALL STUDS TORQUE CHECK) (K) 2 L 7 2 4F 4 F RC T00012WI E35NE 2007101600011 20071016 00011 CE 2007 10 16 2007FA0000867 1 20070911 G 6100 AN520C8R6 SCREW BEECH 58 58 1152740 CE PROPELLER UNSAFETIED B EHHR O OTHER O OTHER NR NOT REPORTED 1 EA 17 755P 63 TH2162 HAVE SEEN THIS ATTACHMENT ARRANGEMENT ON MANY AC. FOUND NON SAFETIED SCREWS ATTACHING PROPELLER DEICE BRUSH ASSY TO MOU NTING. REMOVED NON SAFETIED SCREWS WITHOUT LOCKING DEVICES WITH MS35265-44 SCREW THAT CAN BE LOCKED WITH SAFETY WIRE. (K) 1 L 7 2 3O 3A16 2007101600012 20071016 00012 EU 2007 10 16 2007FA0000868 1 20070911 G 6210 10901030115 BLADE AGUSTA A109 A109 0260109 EU ALLSN 250C 250C20B 03013 GL MAIN ROTOR CRACKED D O OTHER O OTHER NR NOT REPORTED 1 NM 01 2MF 663 7277 CAE834542 EXCESSIVE 1 PER REVOLUTION VIBRATION NOTICED IN MAIN ROTOR SYSTEM. THE AIRCRAFT WAS LANDED WITHOUT INCIDENT. INVESTIGA TION REVEALED CORD WISE CRACKS IN UPPER AND LOWER SKINS AT STATION 1979 EXTENDING FROM THE TRAILING EDGE TO THE AFT SIDE OF THE SPAR. THE HONEYCOMB CORE OF THE BLADE IS ALSO SEPARATED AND DAYLIGHT CAN BE SEEN THROUGH CRACKS IN THE BLADE. THE CRACKS IN BOTH SKINS THEN EXTEND SPAN-WISE ALONG THE SPAR FROM STA 1925 TO STA 2075. THESE CRACKS ARE EXACTLY AS DE SCRIBED IN TECH BULLETIN 109-50, PART 1 REQUIRES DAILY VISUAL INSPECTIONS OF BLADES WITH GREATER THAN 500 HOURS OF OPERA TION BETWEEN STATIONS 1550 AND 3100. BT 109-50, PART II REQUIRES INSPECTION OF THIS AREA WITH A 3X MAGNIFYING GLASS EVE 1 G 7 2 3U 3 U H7EU E4CE 2007101600013 20071016 00013 GL 2007 10 16 2007FA0000869 1 20070801 G 5542 SKIN DIAMON DA40 DA40 2990002 GL RUDDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 07 469JP 654 40469 FOUND 3 INCH CRACK AFT OF RUDDER BALANCE WEIGHT IN COMPOSIT SKIN FWD OF UPPER ATTACH POINT. AIRCRAFT WAS BASED OUT OF A HEAT RELATED AREA. (K) 1 L 7 1 3O NT A47CE 2007101600014 20071016 00014 NE 2007 10 16 2007FA0000870 2 20070912 G 7200 30606266 BLADE AMD FALC50 FALCON50MYST 2730106 EU GARRTT TFE731 TFE73140 29001 NE 3RD STG ROTOR BROKEN D O OTHER O OTHER NR NOT REPORTED 1 GL 11 115SK 1855 330 BROKEN TURBINE BLADE. ENGINE SENT TO MFG FOR INVESTIGATION. (K) 2 L 7 3 4F 4 F A46EU E1NM 2008011400201 20080114 00201 EU 2008 1 14 2007FA0000871 2 20070809 G 8530 02722001002R1 CYLINDER HEAD DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE12501 59300 EU ENGINE DAMAGED C O OTHER O OTHER NR NOT REPORTED 1 NM 11 240TS 421 42072 ENGINE BEGAN LOSING COOLANT BY PRESSURIZING THE COOLING SYSTEM WITH COMBUSTION PRESSURE AND BLOWING COOLANT OVERBOARD. WHEN THE ENGINE WAS REMOVED AND THE OIL DRAINED, COOLANT WAS FOUND IN THE OIL AND FILLING UP CYLINDER NR 3. IT IS SUSPE CTED THAT IF THE CYLINDER HEAD WOULD HAVE BEEN REMOVED, EACH CYLINDER WOULD HAVE HAD A CRACK BETWEEN THE GLOW PLUG AND E XHAUST VALVE RECESSES. THE ENGINE HAD PASSED A COMPRESSION CHECK AND IT IS SUSPECTED THAT THE CRACKS WOULD ONLY LEAK WH EN THE ENGINE WAS WARMED TO OPERATING TEMPERATURE. THE RESULTANT COOLANT LOSS ONLY INCREASES THE PROBABILIITY OF FURTHE R TEMPERATURE EXCURSIONS. A PROBABLE CAUSE WOULD BE INADEQUATE DISTANCE IN THE CASTING OF THE CYLINDER HEAD BETWEEN THE 1 L 7 2 3I 3 B RT A57CE E00069EN 2007101600015 20071016 00015 CE 2007 10 16 2007FA0000872 1 20070719 G 5730 SKIN CESSNA 421 421C 2076016 CE CONT O520 GTSIO520* 17032 SO WINGS CORRODED D BX4R O OTHER O OTHER NR NOT REPORTED 1 NM 03 648SB 421C0648 LT AND RT WING UPPER SKINS UNDER THE NACELLE FUEL BLADDER TANKS HAD CORROSION PRESENT TO THEM AND RELATED AREA AROUND TH E BLADDER BAYS. WO NR 10688. (K) 1 L 7 2 3O 3 O A7CE E7CE 2007101600016 20071016 00016 EA 2007 10 16 2007FA0000873 2 20070827 G 7414 6361 MAGNETO PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540AH1A 42003 EA LT DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SO 03 691MA 3257291 THIS AIRCRAFT HAD A SET OF MAGS INSTALLED AT APPROXIMATELY 400 HRS TT, AT 596 HRS TT, INSTALLED ANOTHER O/H MAG ON THE L T, DUE TO AN OVERHEAT SITUATION. IT APPEARS THAT THE COIL HAS BROKEN DOWN DUE TO EXCESS HEAT, DURING NORMAL OPERATION. NEW AC SHOULD HAVE AIR BLAST TUBES INSTALLED FOR EACH MAGNETO, AS WELL AS A COOLING KIT FOR THE VACUUM PUMP. THE MAGS, NOR THE VACUUM PUMP CAN OPERATE UNDER THESE CONDITIONS WITHOUT AN OUTSIDE AIR SUPPLY. SB 1157A AFFECTS AC FOR THE TACH OMETER SENSOR ALLOWING MOISTURE TO DAMAGE THE MAGNETO. (K) 1 L 7 1 3O 3 O A3SO E14EA 2007101600021 20071016 00021 CE 2007 10 16 2007FA0000874 1 20070728 G 3250 MC05430221 ROD END CESSNA 172 172D 2072410 CE CONT O300 O300* 17022 SO NLG STEERING BROKEN D O OTHER O OTHER NR NOT REPORTED 1 AL 01 2423U 17250023 LT SIDE STEERING ROD WITH 215.92 HRS SINCE NEW HAD THE REAR BALL END THAT ATTACHES TO THE RT RUDDER BAR ASSY BREAK. THE BALL ROD END BROKE AND LEFT THE T/R STEERING ROD AS THE ONLY STEERING FOR THE NOSE GEAR. THE RODS ARE NOT SOLID RODS, THEY ARE DESIGNED TO PUSH AND NOT TO PULL THAT SLIP INSIDE WHEN PULLED ON. IT REQUIRES BOTH RODS TO STEER THE RT PEDAL AND LT ROD WILL TURN NOSE TO THE RT AND LT PEDAL AND RT ROD WILL TURN IT TO THE LT. ON LANDING ROLL OUT, THE PLANE STAR TS TO DRIFT TO THE LT AND WITH THE LT RUDDER PEDAL TO NOSE GEAR DISCONNECTED. NOSE GEAR WOULD NOT RESPOND AND THE PLANE WAS SLOWING UP TO THE POINT OF LOSING ENOUGH AIR FLOW OVER THE RUDDER FOR IT TO CONTROL THE PLANE. THE PILOT STARTED TO 1 H 7 1 3O 3 O NT 3A12 E253 2007101600018 20071016 00018 SO 2007 10 16 2007FA0000875 1 20071003 G 5530 BOLT PIPER PA28 PA28181 7102807 SO LYC O360 O360* 41514 EA VERTICAL STAB LOOSE D K NONE O OTHER IN INSP/MAINT 1 WP 09 6365C 1776 1776 287890366 LOSE VERTICAL ATTACH BOLTS ON AFT BULKHEAD. 1 L 7 1 3O 3 O 2A13 E286 2007101600041 20071016 00041 GL 2007 10 16 2007FA0000876 1 20070919 G 7931 PT100GA TRANSMITTER RYAN NAVION NAVION 6150160 GL CONT O520 IO520B 17032 SO ENGINE OIL PRESS UNRELIABLE D K NONE N FALSE WARNING IN INSP/MAINT 1 NM 04 4131K NAV41131 1212867B AIRCRAFT LANDED WITH ZERO OIL PRESSURE INDICATION. AFTER TESTING WITH DIRECT READING GAUGE IT WAS DETERMINED THAT THE AC TUAL ENGINE OIL PRESSURE WAS WITHIN LIMITS SPECIFIED BY THE MFG. FURTHER TESTING REVEALED PRESSURE INDICATING SYSTEM WO ULD OPERATE NORMALLY AFTER ENGINE TEMPERATURES HAD COOLED BUT WOULD PROVIDE FALSE INDICATIONS WITH ENGINE AT OPERATING T EMPERATURE. FEEL THIS IS A SERIOUS PROBLEM BECAUSE THIS SYSTEM IS STC APPROVED AS A PRIMARY INSTRUMENT AND ITS MALFUNCT ION COULD CAUSE UNNECESSARY AND DANGEROUS OFF AIRPORT LANDINGS. 1 L 7 1 3O 3 O RT A782 E5CE 2007101600073 20071016 00073 NM 2007 10 16 2007FA0000877 1 20070807 G 2420 LC41550FG ALTERNATOR COLUMB LC41 LC41550FG400 5150011 NM CONT O550 TSIO550A 41516 SO ENGINE FAILED F O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 NM 09 376PD 350 41018 A FLIGHT TEST WAS BEING CONDUCTED ON 07/30/07 ON A REWORKED THERMAL SYSTEMS (KATS) EVADE SYSTEM, WHEN THE SYSTEM WENT UN STABLE CAUSING THE ALTERNATOR TO GO OFF LINE. THE TECHNICIAN MONITORING THE SYSTEM ON A DIAGNOSTIC LAPTOP COMPUTER ANNO UNCED TO THE PILOT THAT THE SYSTEM WAS FAILED BUT THE PILOT DID NOT HAVE A "FAILED" ANNUNCIATION ON THE INSTRUMENT PANEL . KATS CONFIRMED THAT THERE WAS A PROBLEM WITH THE FAULT DETECTION SOFTWARE THAT WOULD ALLOW THIS UNDER VERY SPECIFIC C ONDITIONS. KATS STATED THAT THEY DO NOT BELIEVE THIS TO BE A SERIOUS SITUATION SINCE THE SYSTEM IS CERTIFIED INADVERTEN T ICING ONLY. 1 L 7 1 3O 3 O NT A00003SE E5SO 2007102300067 20071023 00067 2007 10 23 2007FA0000878 4 20070629 G 3455 TDR906221270001 TRANSPONDER GARRTT TFE731 TFE731* 01518 WP TAILCONE FAILED B BSYR O OTHER O OTHER NR NOT REPORTED 1 GL 07 56EM 144 ON 6/27/2007 WHILE ENROUTE, THE PRIMARY TRANSPONDER FAILED WHILE THE AIRCRAFT WAS OPERATING IN AIRSPACE. THE CREW WAS A BLE TO SWITCH TO THE SECONDARY TRANSPONDER AND CONTINUE THEIR FLIGHT TO LOCK WITHOUT FURTHER INCIDENT. UPON ARRIVAL, TH E PRIMARY TRANSPONDER WAS CONFIRMED FAILED AND WAS REPLACED WITH A SERVICEABLE TRANSPONDER. THE SYSTEM WAS TESTED IAW F AR PART 43, APPENDIX F AND APPENDIX E, SUB PARA C, AND ICA NR 30A05002, REVISION C. THE SYSTEM WAS FOUND TO BE OPERATIN G NORMALLY AND THE AIRCRAFT WAS RETURNED TO SERVICE. (K) 4 F E6WE 2007102300068 20071023 00068 CE 2007 10 23 2007FA0000879 1 20070909 G 2823 12161001 SELECTOR VALVE CESSNA 207 T207A 2073614 CE CONT O520 TSIO520M 17040 SO MCAULY D3A34 D3A34C401 GL FUEL SYSTEM MISMANUFACTURED D O OTHER O OTHER NR NOT REPORTED 1 WP 07 803AN 161 20700570 248811R 765815 WHEN THE FUEL SELECTOR VALVE IS SELECTED TO THE RT TANK, FUEL IS BEING DELIVERED FROM THE LT TANK, VISE VERSA. THIS WAS DISCOVERED DURING A SHORT FLIGHT IN WHICH THE PILOT NOTICED THE RT TANK FUEL GAUGE WAS DROPPING WHEN THE LT TANK WAS SE LECTED. THIS WAS LATER CONFIRMED DURING AN INSPECTION IN WHICH FUEL WAS DRAINED FROM BOTH TANKS. IN FACT THE SELECTOR VALVE IS PUT TOGETHER INTERNALLY BACKWARDS. (K) 1 H 7 1 3O 3 O A16CE E8CE 5 C P47GL 2007102300069 20071023 00069 CE 2007 10 23 2007FA0000880 1 20070917 G 2420 DOFF10300JR ALTERNATOR CESSNA 172 172M 2072418 CE LYC O320 O320* 41508 EA INOPERATIVE D UT2R O OTHER O OTHER NR NOT REPORTED 1 WP 23 9531H 46 17266205 THIS ALTERNATOR WAS OVERHAULED, OPERATED LESS THAN 50 HOURS, FAILED. THE STUD THAT HOLDS THE DIODE PLATE IN THE ALTERNA TOR WAS BROKEN, AND THE SECOND STUD WAS LOOSE. THIS HAS BEEN AN ONGOING PROBLEM WITH OVERHAULS. WE ARE A SMALL SHOP, Y ET WE HAVE HAD MANY FAILURE WITH THIS PRODUCT IN THE PAST 2 YEARS. APPROXIMATELY 70 PERCENT OF THE OVERHAULS WE HAVE IN STALLED HAVE GONE BACK FOR WARRANTY. PROBLEMS INCLUDE LOOSE DRIVE PULLEYS, LOOSE HARDWARE, SHORT CIRCUITS, DEAD FIELD W INDINGS, DEFECTIVE BRUSHES. MY SUPPLIERS STATE THAT THEY HAVE HAD MANY COMPLAINTS ABOUT THIS REPAIR. 1 H 7 1 3O 3 O NT 3A12 E274 2007102300070 20071023 00070 2007 10 23 2007FA0000881 4 20070918 G 8300 23066678 PINION GEAR ALLSN ALLSN 250C 250C47B GL GEARBOX FRACTURED B YKER O OTHER O OTHER NR NOT REPORTED 1 EA 17 CAG47225 CAE847225 RECEIVED THE ENGINE FOR REPAIR DUE TO VIBRATIONS, AND METAL IN OIL. UPON DISASSEMBLY OF THE GEARBOX FOUND THE ROLLER RE TAINER OF THE NR 3 BEARING FRACTURED IN (4) PLACES. ALSO FOUND THAT THE NR 1 TURBINE WHEEL BLADE TIPS HAD BEEN RUBBING THE BLADE TRACK WHICH CAUSED THE VIBRATION. TECH SUSPECTS THE FRACTURED RETAINER MAY HAVE BEEN A RESULT OF THE VIBRATIO N. (K) 3 U E1GL 2007102300071 20071023 00071 GL 2007 10 23 2007FA0000882 1 20070831 G 7820 20559002 MUFFLER CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 07 824ZB 559 1674 CHECK MUFFLER IAW MFG SB, SB2X-78-07, ISSUED JUNE, 2007. FOUND SPOT WELDS ON EXTERNAL BAFFLE CRACKED. REPLACED MUFFLER . THIS SB APPLIES ONLY TO SR20`S SN 1005 THRU 1797. (K) 1 L 7 1 3O 3 O NT A00009CH E1CE 2007102300072 20071023 00072 SO 2007 10 23 2007FA0000883 1 20070807 G 3213 7873804 AXLE PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA HARTZL HCC2Y HCC2YK1 GL LT MLG BROKEN D O OTHER O OTHER NR NOT REPORTED 1 AL 03 8905N 10353 3240690 L2683048E CH35831B ON TAXI TO TAKEOFF, AC TURNED AROUND AFTER BACK TAXI. PIVOTING ON LT M/G. SIDE LOAD BROKE AXLE AT END OF DRILLED OUT C ENTER. EVIDENCE OF PREVIOUS CRACKING FROM INSIDE OB. (K) 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 2007102300074 20071023 00074 CE 2007 10 23 2007FA0000884 1 20070717 G 3240 07516800 PLATE CESSNA 208 208 2073702 CE PWA PT6 PT6A6 52043 EA CRACKED C FE4R O OTHER O OTHER NR NOT REPORTED 1 AL 03 9602F 15966 20800103 FOUND TORQUE PLATE CRACKED DURING ROUTINE INSPECTION. (K) 1 H 7 1 3T 3 T NT A37CE E4EA 2007102300075 20071023 00075 EU 2007 10 23 2007FA0000885 1 20070910 G 5753 257WF101A VANE BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE731* 01518 WP TE FLAP CORRODED B JGVR O OTHER O OTHER NR NOT REPORTED 1 CE 09 150SB 5758 258197 LT IB FLAP VANE, UPPER SKIN CORRODED BEYOND LIMITS. POSSIBLE CAUSE: DISSIMILAR METAL CORROSION AS TRAILING EDGE IS MAGN ESIUM AND SKIN IS ALUMINUM OR ENVIRONMENT IN WHICH THE VANE OPERATES. IT IS LOCATED BEHIND THE MLG. ASSURE THE SKIN IS PROPERLY TREATED IAW CORROSION PREVENTION PROCEDURES AND PAINTED WITH EPOXY PRIMER BEFORE INSTALLATION. (K) 2 L 7 2 4F 4 F RT A3EU E6WE 2007102300078 20071023 00078 EA 2007 10 23 2007FA0000886 2 20070817 G 8500 ENGINE BEECH 60 A60 1153604 CE LYC O541 TIO541E1C4 41536 EA MAKING METAL D O OTHER O OTHER NR NOT REPORTED 1 NM 01 98KA P212 RL79259 DURING ROUTINE OIL CHANGE, METAL SHAVINGS WERE FOUND IN OIL FILTER AND SCREEN. SHAVINGS WERE MAGNETIC. THESE ENGINES D O HAVE WEAR ISSUES ON CAM AND LIFTERS. AFTER REMOVING OIL PAN, FOUND CAM BAD AND LIFTER WEAR. OIL ANALYSIS DIDN`T PICK UP LARGER MICRON IN OIL. RECOMMEND INSPECTION OF CAM AND LIFTER BEFORE 1000 HOUR. REMOVED OIL PAN ON RT ENGINES AND F OUND BEAD WEAR AS WELL. NO METAL IN FILTER. (K) 1 L 7 2 3O 3 O A12CE E10EA 2007102300080 20071023 00080 GL 2007 10 23 2007FA0000887 2 20070803 G 7250 TURBINE WHEEL CESSNA STC STC206C 1182107 CE ALLSN 250C 250C30P 03013 GL ENGINE FAILED C K NONE O OTHER IN INSP/MAINT 1 NM 05 5746N 1654 13 45461 890629 AFTER 13 HOURS OF OPERATION SINCE OVERHAUL, DURING A POWER CHECK, THE TURBINE ASSY FAILED CAUSING THE FORCED LANDING OF THE HELICOPTER. FORCED LANDING CAUSED SUBSTANTIAL DAMAGE TO THE AIRCRAFT. (K) 1 H 7 1 3O 3 U NT A4CE E1GL 2007102300083 20071023 00083 CE 2007 10 23 2007FA0000888 1 20070830 G 3246 C163003102 WHEEL CESSNA 172 172M 2072418 CE LYC O360 O360A4M 41514 EA SNSNCH 76E 76EM8 EA LT MLG FAILED D O OTHER O OTHER NR NOT REPORTED 1 NM 01 9898Q 17265842 L3551036A 31674R WHEEL IS A 3 PIECE CONSTRUCTION, OUTER RIM AND THE INNER SPACER. BROKE APART ON TAXIING OF AIRCRAFT. JACKED AIRCRAFT AN D INSTALLED SERVICEABLE UNIT, THREADS STRIPPED OUT OF CENTER SECTION. (K) 1 H 7 1 3O 3 O NT 3A12 E286 5 N P4EA 2007102300086 20071023 00086 SO 2007 10 23 2007FA0000889 2 20070911 G 8530 ROCKER CUBCFT CC11 CC11100 060002H CE CONT O200 O200A 17020 SO NR 4 CYLINDER MISINSTALLED D O OTHER O OTHER NR NOT REPORTED 1 NM 01 787AK 118 CC1100006 256113 FOUND THE ROCKER ARMS REVERSED, INTAKE EXHAUST ROCKERS IN CYLINDER NR 4 LEADING TO POSSIBLE EXHAUST GUIDE AND VALVE DAMA GE DO TO THE EXHAUST ROCKER ARM HAS AN OILING PORT FOR THE EXHAUST VALVE AND THE INTAKE ROCKER ARM DOES NOT HAVE THE OI LING PORT. THE ROCKER ARMS WERE REMOVED AND INSTALLED CORRECTLY. DAMAGE TO VALVE AND GUIDE UNKNOWN AT THIS TIME, WILL HAVE TO CONTACT MFG. (K) 1 H 7 1 3O 3 O NC E252 2007102300088 20071023 00088 SO 2007 10 23 2007FA0000890 2 20070911 G 8530 MS5196364 SETSCREW CUBCFT CC11 CC11100 060002H CE CONT O200 O200A 17020 SO CYL ROCKER BOSS DAMAGED C O OTHER O OTHER NR NOT REPORTED 1 NM 01 787AK 118 CC1100006 256113 IN THE NEW STYLE CYLINDER ASSY PN 655482 FOR THE ENGINE, THE ROCKER ARM PIN PN 654375 IS RETAINED BY A SET SCREW PN MS51 966364 IN THE CENTER ROCKER BOSS SUPPORT. FOUND IN THIS ENGINE (2) SET SCREWS LOOSE AND A THIRD FOUND RATTLING AROUND A ND LODGED UNDER THE INTAKE ROCKER ARM BETWEEN THE CYLINDER HEAD. THE ROCKER SHAFTS ARE MOVING OFF CENTER AND ROTATING A ND WITH A MACHINED SHARP CUT IN THE END OF THE ROCKER SHAFT TO INDICATE WERE SET SCREW IS TO LINE UP WITH THE ROCKER SHA FT, IT IS CUTTING THROUGH THE VALVE COVERS AND WILL LEAD TO LOSS OF ENGINE OIL AND OPERATION OF THE ENGINE AND POSSIBLE LOSS OF PERSONAL LIFE. (K) 1 H 7 1 3O 3 O NC E252 2007102300091 20071023 00091 SO 2007 10 23 2007FA0000891 2 20070914 G 8530 O200D SETSCREW AMCNLG AL3 AL3 060002K CE CONT O200 O200* 17020 SO ROCKER ARM BOSS MISMANUFACTURED D O OTHER O OTHER NR NOT REPORTED 1 SO 05 65LC 42 AL1083 CHECKING ROCKER ARM SHAFT SET SCREWS AND TO ASSURE INTAKE AND EXHAUST ROCKER ARMS NOT SWITCHED IAW INFORMATION TO OWNERS FORM INTERNET OWNERS AIRCRAFT FORUM. CYLINDER NR 1, SN AC06HB070, SET SCREW AND ROCKER ARMS, OK. CYLINDER NR 2, SN AC0 6FA543, SET SCREW LOOSE ENOUGH TO ALLOW SHAFT TO MOVE, ROCKER ARMS, OK. CYLINDER NR 3, SN AC06HA911, SET SCREW OK, INTA KE AND EXHAUST ROCKER ARMS SWITCHED. CYLINDER NR 4, SN AC06HA935, SET SCREW AND ROCKER ARMS, OK. (K) 1 H 7 1 3 O 3O EXPA1H71 E252 2007102300087 20071023 00087 CE 2007 10 23 2007FA0000892 1 20071010 G 2750 1434425 FLEX DRIVE CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C GL RT TE FLAPS BROKEN B K NONE O OTHER IN INSP/MAINT 1 WP 23 22NG 7500204 THE RT FLAP FLEX DRIVE HOUSING FAILED AT THE SWAGED END OF THE HOUSING AT THE IB END. ON SEPTEMBER 11, 2007 THIS AIRCRA FT HAD A SIMILAR EVENT WITH THE LT OB FLAP DRIVE WHICH ALLOWED THE FLEX DRIVE TO DISENGAGE FROM THE OB FLAP DRIVE CAUSIN G THE FLAPS TOP REMAIN AT 3 DEGREES POSITION AND PREVENTING FURTHER EXTENSION OR RETRACTION. WE OPERATE 2 AIRCRAFT AND THIS IS THE 4TH FAILURE OF THE FLEX DRIVE BETWEEN THE 2 AIRCRAFT. 2 L 7 2 4J 4 F RT T00007WI TE6CH 2007102300127 20071023 00127 WP 2007 10 23 2007FA0000893 2 20070914 G 7230 307516034 TURBINE WHEEL RAYTHN DH125 HAWKER800XP 7150012 CE GARRTT TFE731 TFE7315BR WP LP COMPRESSOR FAILED E E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 NM 04 800WY 3172 258556 107656 CLIMBING THROUGH FL270, A LOUD BANG IN REAR OF ACFT. LT ENGINE COMPUTER LIGHT ILLUMINATED. PF BROUGHT LT ENGINE TO IDL E, PNF PULLED CHECKLIST. AFTER SURVEY OF ENGINE PARAMETERS, PF TURNED LT ENGINE COMPUTER BACK ON TO CONTROL PARAMETERS. ENGINE COMPUTER DID STAY ON & DID APPEAR TO CONTROLL ENGINE. POWER ADVANCED SLOWLY ON LT ENGINE. AT APPROXIMATELY 70 % N1 ANOTHER LOUD BANG IN REAR & LT ENGINE COMPUTER LIGHT ILLUMINATED AGAIN. ENGINE PARAMETERS MOVED TO RED LINE. PF SHUT DOWN LT ENGINE. PNF CONTACTED ATC, DECLARED AN EMERGENCY & REQUESTED & RECEIVED DIRECT CLOSEST AIRPORT. SINGLE ENGINE APPROACH CHECKLIST & PROGRAMMED FMS FOR AN APPROACH. ACFT CLEARED FOR VISUAL APPROACH. AFTER A NON-EVENTFUL LANDING. 2 L 7 2 4F 4 F RT A3EU E6WE 2007102300109 20071023 00109 CE 2007 10 23 2007FA0000895 1 20071001 G 3150 UNKNOWN BEECH MU300 400A 1155402 CE UNKNOWN E O OTHER J WARNING INDICATION CR CRUISE 1 SO 11 418GJ RK418 AC EXPERIENCED A FLAP ASYMMETRIC LIGHT IN FLIGHT. THE CREW DID NOT TRY TO PUT THE FLAPS DOWN AND DIVERTED FOR A NO FLAP LANDING. CRITICAL CARE MAINTENANCE DROVE DOWN TO REPAIR THE AIRCRAFT. MAINTENANCE COULD NOT DUPLICATE THE PROBLEM AFT ER SEVERAL ATTEMPTS. MAINTENANCE INSPECTED AND CLEANED ALL CONNECTORS, INSPECTED HYDRAULIC SYSTEMS, AND FLAP RIGGING AN D CABLES. MAINTENANCE C/W ALL OPERATIONAL CHECK IAW THE MM. THE PROBLEM WAS NEVER DUPLICATED. 2 H 7 2 4F RT A16SW 2007102300003 20071023 00003 CE 2007 10 23 2007FA0000897 1 20071012 G 2730 CONTROL CABLE CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ELEVATORS WORN D K NONE O OTHER IN INSP/MAINT 1 WP 23 379TA 1560 172S9379 L3083351A CONTROL CABLE, (P/N 0510105-308), FOUND WORN TO REPLACE LIMITS PER AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7. IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS CONSTANT CONTACT. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMIT S. 1 H 7 1 3O 3 O NT 3A12 1E10 2007102300135 20071023 00135 CE 2007 10 23 2007FA0000898 1 20071012 G 5712 051179616 BULKHEAD CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ZONE 100 MISALIGNED D K NONE O OTHER IN INSP/MAINT 1 WP 23 373ES 3780 17280052 L2701351A CONTROL CABLE, (P/N 0510105-339), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7. IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS CONSTANT CONTACT. CESSNA MAINTENANCE MANUAL DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAK AGE AND CORROSION LIMITS. 1 H 7 1 3O 3 O NT 3A12 1E10 2007102300140 20071023 00140 CE 2007 10 23 2007FA0000900 1 20071012 G 2730 CONTROL CABLE CESSNA 182 182S 2072701 CE LYC O540 IO540AB1A5 EA ZONE 100 WORN D K NONE O OTHER IN INSP/MAINT 1 WP 23 7262Y 1400 18280812 L1241261E CONTROL CABLE, (P/N 0510105-189), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH MICARDA GUARD PLATE OVER FUEL LINES AT FUEL SELECTOR AREA JUST FORWARD OF FRONT SEATS. THE CABLES ARE IN CONSTANT CONTACT WITH PLATES EVEN WITH CABLE TENSION CORRECT. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR CO MMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS. 1 H 7 1 3O 3 O NT 3A13 1E4 2007102300134 20071023 00134 CE 2007 10 23 2007FA0000904 1 20071012 G 5712 051179616 BULKHEAD CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ZONE 100 MISALIGNED D K NONE O OTHER IN INSP/MAINT 1 WP 23 625SP 1560 172S8616 L2922551A CONTROL CABLE, (P/N 0510105-339), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7. IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS CONSTANT CONTACT. MM DOES NOT CONTAIN ANY "CABLE WEAR" LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMIT S. 1 H 7 1 3O 3 O NT 3A12 1E10 2007102300137 20071023 00137 CE 2007 10 23 2007FA0000906 1 20071012 G 5712 051179616 BULKHEAD CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ZONE 100 MISALIGNED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 23 658SP 4200 172S8063 L2796451A CONTROL CABLE, (P/N 0510105-308), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7. IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS CONSTANT CONTACT. MM DOES NOT CONTAIN ANY "CABLE WEAR" LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMIT S. 1 H 7 1 3O 3 O NT 3A12 1E10 2007102300138 20071023 00138 CE 2007 10 23 2007FA0000907 1 20071012 G 5712 051179616 BULKHEAD CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ZONE 100 MISALIGNED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 23 2630U 1628 17280568 L2761951A CONTROL CABLE, (P/N 0510105-308), FOUND WORN TO REPLACE LIMITS IAW AC43.13-1A, CABLE INSPECTION. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH LANDING GEAR BULKHEAD FAIRLEAD P/N S338-7. IT IS BELIEVED THAT THE HOLE MISALIGNMENT CAUSED THIS CONSTANT CONTACT. MM DOES NOT CONTAIN ANY "CABLE WEAR" LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMIT S. 1 H 7 1 3O 3 O NT 3A12 1E10 2007102300004 20071023 00004 CE 2007 10 23 2007FA0000908 1 20070919 G 3230 JE1 STOP CESSNA 310 310Q 2074242 CE CONT O470 IO470* 17026 SO MLG GEARBOX BROKEN B OF1R O OTHER O OTHER NR NOT REPORTED 1 EA 17 20SS 3235 310Q0521 PILOT HAD NO LT GEAR DOWN INDICATION. HE CYCLED GEAR WITH NO SUBSEQUENT GEAR DOWN INDICATION. HE ATTEMPTED MANUAL EXTE NSION, CRANKED TO THE MECHANICAL STOP IN THE GEARBOX AND BROKE THE STOP. BELLCRANK CONTINUED PAST DOWN AND THEN WENT PA RTIALLY (UP). GEAR COLLAPSED ON LANDING. (K) 1 L 7 2 3O 3 O 3A10 E1CE 2007102300165 20071023 00165 CE 2007 10 23 2007FA0000909 1 20070911 G 5280 45A3161521 DOOR BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE NLG CRACKED B ZKFR K NONE O OTHER IN INSP/MAINT 1 EA 61 262PA RK203 FOUND DURING INSPECTION. NOSE GEAR FOLLOW UP DOOR PN 45A31615-21 ON BRACKETS, PN 45A31613-9 AND 45A31613-7 AT ATTACHING RIVET HAS CRACKS GOING FORWARD TO AFT THROUGH THE FIRST RIVET ALONG THE RIVET ROW. RELATIVE WIND PUSHING AFT ON THE DO OR WHILE GEAR IS EXTENDED FOR TAKEOFF AND LANDING AND VIBRATION. USING THICKER MATERIAL DURING MFG AND OR ADDING A DOUB LER. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007102300166 20071023 00166 CE 2007 10 23 2007FA0000910 1 20070920 G 5280 45A3161521 DOOR BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE NLG CRACKED B ZKFR K NONE O OTHER IN INSP/MAINT 1 EA 61 268PA RK323 FOUND DURING INSPECTION. NOSE GEAR FOLLOW UP DOOR, P/N 45A31615-21 ON BRACKETS PN 45A31613-9, 45A31613-7 AND 45A31616-3 AT ATTACHING RIVET HAS CRACKS GOING FORWARD TO AFT THOUGH THE FIRST RIVET ALONG THE RIVET ROW. RELATIVE WIND PUSHING AF T ON THE DOOR WHILE GEAR IS EXTENDED FOR TAKEOFF AND LANDING AND VIBRATION. USING THICKER MATERIAL DURING MFG AND OR AD DING A DOUBLER. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007110100172 20071101 00172 CE 2007 11 1 2007FA0000911 1 20070917 G 5280 STRUCTURE BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE NLG DOOR CRACKED B ZKFR K NONE O OTHER IN INSP/MAINT 1 EA 61 26PA RK256 FOUND DURING INSPECTION. NOSE GEAR FOLLOW UP DOOR PN 45A31615-21 ON BRACKETS PN 45A31613-9 AND 45A31613-7 AT ATTACHING RIVET HAS CRACKS GOING FORWARD TO AFT THROUGH THE FIRST RIVET ALONG THE RIVET ROW. RELATIVE WIND PUSHING AFT ON THE DOO R WHILE GEAR IS EXTENDED FOR TAKEOFF AND LANDING AND VIBRATION. USING THICKER MATERIAL DURING MFG AND OR ADDING A DOUBL ER. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007110100173 20071101 00173 CE 2007 11 1 2007FA0000912 1 20071001 G 5610 45AS3101012 WINDOW BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE COCKPIT CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 03 480M RK6 WHILE PERFORMING A SCHEDULED A-D INSPECTION FOUND NR 2 (COPILOT) SIDE WINDOW CRACKED USING THE PRISM INSPECTION METHOD. THE D-INSPECTION REQUIRES THAT BOTH WINDSHIELD RETAINERS OR USING OPTICAL PRISM INSPECTION METHOD. THE IS NO STATEMENT IN THE AIRCRAFT MM OR IN THE A-D INSPECTION CHECKLIST THAT REQUIRES YOU TO INSPECT THE COCKPIT SIDE WINDOWS IN THE SAME MANNER AS THE WINDSHIELDS. ALL OF THE WINDOWS IN THE COCKPIT AREA ARE INSTALLED OR FASTENED IN THE SAME MANNER AS THE WINDSHIELDS. IT IS SUSPECTED THAT THE COPILOT WINDOW CRACKED FROM FATIGUE, OR TT INSTALLED. WOULD RECOMMEND THAT INSPEC TIONS OF ALL COCKPIT WINDOWS WITH A PRISM AT SCHEDULED INTERVALS BE COMPLETED. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007102300011 20071023 00011 CE 2007 10 23 2007FA0000914 1 20071003 G 5510 FITTING BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE HORIZONTAL STAB LOOSE C K NONE O OTHER IN INSP/MAINT 1 GL 03 480M RK6 WHILE PERFORMING AN A-D INSPECTION FOUND 8 LOOSE RIVETS IN THE FORWARD RIVET LINE OF THE ATTACHMENT PIVOT FITTING PN 45A 21183-11 ON THE BOTTOM OF THE HORIZONTAL STABILIZER. IT IS SUSPECTED THAT THE LOOSE RIVETS WERE CAUSED BY FATIGUE AND A GE. RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION. RECOMMEND CONTACTING MFG FOR REPAIR OPTIONS. THIS IS THE 3RD AIRCRAFT IN A ROW THAT THESE SAME RIVETS HAVE BEEN LOOSE OR MISSING. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007102300007 20071023 00007 CE 2007 10 23 2007FA0000915 1 20071001 G 5520 HINGE BRACKET CESSNA 500 S550 2076607 CE PWA JT15 JT15D4 52112 NE LT ELEVATOR CORRODED B SI6R K NONE O OTHER IN INSP/MAINT 1 SW 17 52FT S5500056 LT OB HINGE BRACKET BROKE OFF DURING AILERON REMOVAL. APPEARS TO HAVE FAILED DUE TO CORROSION. (K) 1 L 7 2 4F 4 F RT A22CE E1NE 2007102300010 20071023 00010 CE 2007 10 23 2007FA0000916 1 20070928 G 7830 STRUCTURE LEAR 35 35A 5170602 CE GARRTT TFE731 TFE7312 01518 WP THRUST REVERSER DAMAGED C O OTHER O OTHER NR NOT REPORTED 1 EA 17 10UF 0011 166 P74521C DURING THE PILOT PREFLIGHT, THE PILOT HAD NOTICED THAT THERE WAS A TEAR IN THE SHEET METAL OF THE LT ENGINE THRUST REVER SER INNER SKIN. WE COULD NOT IDENTIFY WHAT HAS CAUSED THIS TEAR. THE UNIT WILL BE REPAIRED BY THE MFG AND WILL INFORM YOU WITH ANY INFO THEY GIVE TO US ABOUT THIS INCIDENT. (K) 2 L 7 2 4F 4 F A10CE E6WE 2007102300017 20071023 00017 EA 2007 10 23 2007FA0000917 2 20070820 G 7322 3013460 ROD EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA FUEL CONTROL BROKEN C O OTHER O OTHER NR NOT REPORTED 1 EA 65 621KC 110335 DURING A 150 HR INSPECTION THE LOWER FUEL CONTROL ROD WAS FOUND BROKEN ON THREADED SHAFT WHERE IT SCREWS INTO COUPLING. IT LOOKS LIKE IT MAY HAVE BEEN BENT AND A MORE DETAILED INSPECTION OF THIS COMPONENT SHOULD OCCUR. (K) 1 L 7 2 4T 4 T A21SO E4EA 2007110100175 20071101 00175 CE 2007 11 1 2007FA0000918 1 20070927 G 2435 23085001 STARTER GEN BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE LEFT FAILED B E81R O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION NR NOT REPORTED 1 GL 03 350TT 4822 FL413 PILOT REPORTED LT GENERATOR GOING OFF-LINE ON APPROACH. FOUND STARTER/GENERATOR INOPERATIVE. UPON REMOVAL NOTICED EVID ENCE OF COOLING FAN TIPS RUBBING ON HOUSING, BEARINGS WORN (ARMATURE ASSY LOOSE).(K) 2 L 7 2 4T 4 T A24CE E4EA 2007110100176 20071101 00176 GL 2007 11 1 2007FA0000919 1 20070913 G 7160 CONTROL ARM DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA CARB HEAT BROKEN D O OTHER O OTHER NR NOT REPORTED 1 NM 07 423FP 452 40FC023 CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA KE. (K) 1 L 7 1 3O 3 O NT A47CE E286 2007110100177 20071101 00177 CE 2007 11 1 2007FA0000920 1 20071002 G 2420 DOFF10300JR ALTERNATOR CESSNA 172 172M 2072418 CE LYC O320 O320* 41508 EA ENGINE INOPERATIVE D O OTHER O OTHER NR NOT REPORTED 1 NM 07 9531H 40 17266205 ALTERNATOR, DEFECT UNKNOWN, FAILED INTERNALLY, GROUND POST LOOSE INTERNALY EXCESSIVE ARMATURE END PLAY. RETURNED FOR WA RRANTY. (K) 1 H 7 1 3O 3 O NT 3A12 E274 2007110100178 20071101 00178 CE 2007 11 1 2007FA0000921 1 20071002 G 2420 DOFF10300JR ALTERNATOR CESSNA 172 172M 2072418 CE LYC O320 O320* 41508 EA ENGINE INOPERATIVE D O OTHER O OTHER NR NOT REPORTED 1 NM 07 9531H 40 17266205 ALTERNATOR, DEFECT UNKNOWN, FAILED INTERNALLY. RETURNED FOR WARRANTY. (K) 1 H 7 1 3O 3 O NT 3A12 E274 2007102300015 20071023 00015 CE 2007 10 23 2007FA0000922 1 20071002 G 8011 MHJ4003S MOTOR CESSNA 340 340A 2076405 CE CONT O520 TSIO520* 17040 SO STARTER NOISY D O OTHER O OTHER NR NOT REPORTED 1 NM 07 340RF 46 340A0212 STARTER STARTED MAKING A LOUD SQUEALING NOISE WHEN OPERATING STARTER, AND SLOW ROTATION OF ENGINE. REMOVED AND RETURNED FOR WARRANTY. (K) 1 L 7 2 3O 3 O 3A25 E8CE 2007102600086 20071026 00086 CE 2007 10 26 2007FA0000923 1 20071005 G 2797 CONNECTOR CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C GL MISINSTALLED B CNQR O OTHER O OTHER NR NOT REPORTED 1 CE 07 964QS 7500164 PRIMARY STAB TRIM FAILED CLIMBING THROUGH FL280 AT 300 KTS. NO CAS MESSAGE WAS PRESENT. CLACKER WAS STUCK ON. STAB WAS NOT MOVING WHEN CLACKER WAS GOING OFF. AUTO PILOT DISENGAGED ON ITS OWN DUE TO HEAVY NOSE CONFIG. AFTER TROUBLESHOOTI NG SHOULD THE ECM TO BE BAD. REMOVED AND REPLACED (ECM NR 421400216J1) WITH NEW PART 4214-0021-11 (LATEST DASH NR) COM PLETED PRIMARY CHANNEL A/B TRAVEL VERIFICATION CHECKS IAW 750 MM, TASK 27-40-00-721, NO FAULTS NOTED. FOUND THE PRIMARY AND SECONDARY CONNECTORS SWAPPED. WHICH HAD NO EFFECT IN THIS FAILURE. (K) 2 L 7 2 4J 4 F RT T00007WI TE6CH 2007102300012 20071023 00012 CE 2007 10 23 2007FA0000924 1 20070616 G 5712 051179616 BULKHEAD CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA FUSELAGE MISLOCATED C K NONE O OTHER IN INSP/MAINT 1 WP 23 2630U 1628 17280568 L2761951A CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE. IT IS BELIEVED THAT A HOLE MISLOCATIO N CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CA BLE WIRE BREAKAGE AND CORROSION LIMITS. 1 H 7 1 3O 3 O NT 3A12 1E10 2007102300001 20071023 00001 CE 2007 10 23 2007FA0000925 1 20071018 G 7603 632558A1 LINK ROD CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO THROTTLE WORN D K NONE O OTHER IN INSP/MAINT 1 NM 07 4640E 877 18503824 832429R THROTTLE BUTTERFLY (P/N: 625601G) AND THROTTLE BODY (P/N: 639437)ARE WORN, ALLOWING BUTTERFLY SHAFT TO SLIDE SIDE TO SID E CAUSING THE LINK ROD ASSEMBLY (P/N: 632558A1)TO WEAR CHAFING THE WAVE WASHER AND COTTER PIN. THE COTTER PIN AND WAVE W ASHER AT THE THROTTLE BODY WERE MISSING AT THE TIME OF INSPECTION. IF THE LINK ROD FROM THE THROTTLE BODY ARM AND THE ME TERING BLOCK ARM DETACHES, PROPER FUEL METERING CEASES. 1 H 7 1 3O 3 O 3A24 E5CE 2007102300052 20071023 00052 CE 2007 10 23 2007FA0000926 1 20070812 G 5712 051179616 BULKHEAD CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ZONE 100 WORN C K NONE O OTHER IN INSP/MAINT 1 WP 23 379TA 1560 172S9379 L3083351A CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE. IT IS BELIEVED THAT A HOLE MISLOCATIO N CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CAB LE WIRE BREAKAGE AND CORROSION LIMITS. 1 H 7 1 3O 3 O NT 3A12 1E10 2007102300160 20071023 00160 CE 2007 10 23 2007FA0000929 1 20070712 G 5712 051179616 BULKHEAD CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ZONE 100 MISALIGNED C K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 23 373ES 3780 17280052 L2701351A CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE. IT IS BELIEVED THAT A HOLE MISLOCATIO N CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CAB LE WIRE BREAKAGE AND CORROSION LIMITS. 1 H 7 1 3O 3 O NT 3A12 1E10 2007110100187 20071101 00187 CE 2007 11 1 2007FA0000930 1 20071018 G 7603 632558A1 LINK ROD CONT CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO THROTTLE WORN D K NONE O OTHER IN INSP/MAINT 1 NM 07 4640E 877 18503824 832429R THROTTLE BUTTERFLY (P/N: 625601G) AND THROTTLE BODY (P/N: 639437) ARE WORN, ALLOWING BUTTERFLY SHAFT TO SLIDE SIDE TO SI DE CAUSING THE LINK ROD ASSEMBLY (P/N: 632558A1)TO WEAR CHAFING THE WAVE WASHER AND COTTER PIN. THE COTTER PIN AND WAVE WASHER AT THE THROTTLE BODY WERE MISSING AT THE TIME OF INSPECTION. IF THE LINK ROD FROM THE THROTTLE BODY ARM AND THE METERING BLOCK ARM DETACHES, PROPER FUEL METERING CEASES. 1 H 7 1 3O 3 O 3A24 E5CE 2007102300161 20071023 00161 CE 2007 10 23 2007FA0000931 1 20070912 G 5712 051179616 BULKHEAD CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ZONE 100 MISALIGNED C K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 23 658SP 4200 172S8063 L3083351A CONTROL CABLE, ( P/N 0510105-308), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDELINES IN AC43.13-1A. THE CABLE CONSTANTLY RUBS THE S338-7 FAIRLEAD IN THE LANDING GEAR BULKHEAD HOLE. IT IS BELIEVED THAT A HOLE MISLOCATIO N CAUSES THE MISALIGNMENT WHICH ALLOWS THE CABLE RUB. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CAB LE WIRE BREAKAGE AND CORROSION LIMITS. 1 H 7 1 3O 3 O NT 3A12 1E10 2007110100186 20071101 00186 EA 2007 11 1 2007FA0000932 2 20071018 G 8520 AS18840 CAMSHAFT BEECH 23 A2324 1151226 CE LYC O360 IO360A1A 41514 EA ENGINE SPALLED B K NONE O OTHER IN INSP/MAINT 1 EA 23 6956Q 556 556 MA304 RL707851A 556 HOURS SINCE MAJOR OVERHAUL, CAMSHAFT AND LIFTERS SPALLED AND CORROSION IS EVIDENT. ENGINE HAS BEEN OPERATED ON PHIL LIPS XC 20W50 OIL. 1 L 7 1 3O 3 O A1CE 1E10 2007110100193 20071101 00193 SO 2007 11 1 2007FA0000933 1 20071019 G 2432 MS915861 SHUNT PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540* 41532 EA MASTER BATTERY BLOWN D O OTHER O OTHER NR NOT REPORTED 1 NE 03 788JG 440 3257369 COMPLETE ELECTRICAL FAILURE. WHEN BATTERY MASTER SWITCH WAS TURNED ON, NO POWER REACHED MAIN BUSS. FOUND BATTERY AMMETE R SHUNT BURNED THROUGH. BATTERY AMMETER SHUNT INSTALLED WAS 30 AMP VALUE. (P/N MS91586-1) BATTERY AMMETER SHUNT SHOULD BE 100 AMP VALUE. NO RECORD OF BATTERY AMMETER SHUNT BEING REPLACED SINCE AIRCRAFT WAS MANUFACTURED. INSTALLED CORREC T AMP VALUE SHUNT AND ELECTRICAL SYSTEM OPS CHECKED GOOD. PIPER P/N 486-684 (MS91586-6) RECOMMEND THAT ALL SHUNTS BE CH ECKED FOR ALL THIS MODEL AIRCRAFT. (ALTERNATOR AMMETER SHUNT IS SAME P/N) 1 L 7 1 3O 3 O A3SO E14EA 2007110100182 20071101 00182 EA 2007 11 1 2007FA0000935 2 20071018 G 7414 PIN PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA MAGNETO GROOVED D K NONE O OTHER IN INSP/MAINT 1 GL 09 2916W 633 G03EA044 447995300 L45577T STOP PINS GROOVED BEYOND LIMITS. 1 L 7 2 3O 3 O A19S0 E286 2007102300162 20071023 00162 CE 2007 10 23 2007FA0000937 1 20070912 G 2730 CONTROL CABLE CESSNA 182 182S 2072701 CE LYC IO360 IO360L2A EA ZONE 100 WORN C K NONE O OTHER IN INSP/MAINT 1 WP 23 7262Y 1400 18280812 L3083351A LT AND RT ELEVATOR CONTROL CABLES, ( P/N 0510105-189), FOUND WORN TO REPLACEMENT LIMITS IAW CABLE WEAR INSPECTION GUIDEL INES IN AC43.13-1A. CABLE WAS WORN DUE TO CONSTANT CONTACT WITH THE MICARDA PLATES OVER THE FUEL LINES AT FUEL SELECTOR AREA JUST FORWARD OF THE FRONT SEATS. THE CABLE TENSIONS ARE CORRECT BUT THE CABLES ARE IN CONSTANT CONTACT WITH PLATE S. MM DOES NOT CONTAIN ANY (CABLE WEAR) LIMITS OR COMMENTS, ONLY CABLE WIRE BREAKAGE AND CORROSION LIMITS. 1 H 7 1 3O 3 O NT 3A13 1E10 2007102600095 20071026 00095 SO 2007 10 26 2007FA0000938 1 20071022 G 3297 AN551 BOLT PIPER PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA DRAG LINK SHEARED B O OTHER O OTHER LD LANDING 1 WP 07 574ER 3743 NA 4496150 FORWARD DRAG LINK BOLT ON NOSE GEAR FAILED DURING TOUCH AND GO PRACTICE. A/C RETURNED TO DEPARTURE AND LANDED WITH THE NOSE GEAR STUCK IN THE NOSEWHEEL WELL. 1 L 7 2 3O 3 O A19S0 E286 2007102600097 20071026 00097 CE 2007 10 26 2007FA0000939 1 20071021 G 3260 LAMP BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE MLG INDICATOR INOPERATIVE D O OTHER P NO WARNING INDICATION DE DESCENT 1 SO 11 442GJ RK442 PILOT HAD NO GREEN DOWN AND LOCKED INDICATION FOR THE RT GEAR WHEN LANDING. PILOT CONFIRMED WITH THE TOWER THE GEAR WAS DOWN, ALSO THE PILOT CONFIRMED THAT THE LIGHT WOULD NOT ILLUMINATE WHEN TESTED. AFTER LANDING MAINTENANCE CHECKED OUT AI RCRAFT AND REPLACED LAMP IN GEAR INDICATION. SYSTEM OPERATIONAL CHECK GOOD. 2 H 7 2 4F 4 F RT A16SW E25EA 2007120400004 20071204 00004 SW 2007 12 4 2007FA0000941 1 20071009 G 2700 KS178 ROLL SERVO MOONEY M20 M20K 5870220 SW CONT O360 TSIO360* 17025 SO INSIDE CASE LOOSE D O OTHER O OTHER NR NOT REPORTED 1 EA 13 697SP 160 5644 252002 MOTOR ASSY COMING LOOSE ON SERVO MOUNT. LOOSE HARDWARE, LOOSE MOTOR. RECOMMEND SERVO TO BE INSPECTED FOR PROPER SERVO A SSY (THAT MOTOR AND HARDWARE ARE NOT LOOSE). (K) 1 L 7 1 3O 3 O 2A3 E9CE 2007102600109 20071026 00109 SO 2007 10 26 2007FA0000942 1 20070921 G 3220 LANDING GEAR PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO NOSE COLLAPSED C AG3R O OTHER O OTHER NR NOT REPORTED 1 WP 15 84643 348233033 AIRCRAFT TAXIED TO RUNWAY AFTER LOADING CARGO. AFTER NORMAL RUNUP, THE PILOT TAXIED ONTO THE RUNWAY AND STOPPED. THE P ILOT ADVANCED THROTTLES AND RELEASED BRAKES, AFTER RELEASING BRAKE, THE NOSE GEAR COLLAPSED. AIRCRAFT WAS RECOVERED AND TOWED OFF RUNWAY TO A SAFE TIE DOWN SPOT. NO CAUSE IS YET KNOWN AS TO WHY THE NOSE GEAR COLLAPSED. (K) 1 L 7 2 3O 3 O A7SO E9CE 2007102600110 20071026 00110 CE 2007 10 26 2007FA0000944 1 20071012 G 8011 6462751 STARTER CESSNA 421 421C 2076016 CE CONT O520 GTSIO520N 17032 SO RT ENGINE SHORTED C O OTHER O OTHER NR NOT REPORTED 1 EA 25 421KD 29 421C1006 808319R OVERHAULED STARTER FAILED AFTER 30 HOURS. (K) 1 L 7 2 3O 3 O A7CE E7CE 2007102600111 20071026 00111 CE 2007 10 26 2007FA0000945 1 20071012 G 2913 PUMP RAYTHN 390 390 7150030 CE WILINT FJ44 FJ442A GL HYD SYSTEM DAMAGED D JAS2 O OTHER O OTHER NR NOT REPORTED 1 WP 09 408J RB193 HYDRAULIC PUMP ASSY, PN 390-389022-0003, INSPECTED AND FOUND NOT DEFECTIVE. FOUND DEFECTIVE/ DAMAGED PART PN MS28778-6, PACKING. FLIGHT CREW COMPLETED ABNORMAL CHECKLIST. UPON INSPECTION FOUND THAT PACKING AT HYDRAULIC PUMP PRESSURE OUTL ET FITTING HAD FAILED. THIS COMPONENT WAS WORKED ON IAW MFG SAFETY COMMUNIQUE , CONTROL NR JAS-SDR-001. (K) 1 L 7 2 3F 4 F RT A00010WI E3GL 2007102600113 20071026 00113 NM 2007 10 26 2007FA0000946 1 20071016 G 5313 STRINGER BOEING 727 727200 138407E NM PWA JT8 JT8D217C 52053 NE BS940-945 CRACKED B FY4Y K NONE O OTHER IN INSP/MAINT 1 WP 03 705AA 22462 THE AIRCRAFT INPUT FOR 4C CHECK AND CPCP ON SEPT 3, 2007. DURING CPCP, THE INSPECTOR PERFORMED VISUAL INSPECTION AND FO UND 5 INCH CRACK BOTH ON LT AND RT FUSELAGE STRINGER S18A BETWEEN BS940 AND BS945 ON SEPT 21, 2007. A PROPOSAL WAS INIT IALLY SUBMITTED ON SEPT 22. AFTER REPAIR TO THE STRINGERS, FORM 337 WILL BE SUBMITTED TO FAA FOR FINAL RESULT OF CORREC TIVE ACTIONS DETAIL. (K) 2 L 7 3 4F 4 F RT A3WE E9NE 2007110200002 20071102 00002 EU 2007 11 2 2007FA0000947 1 20071003 G 3233 X110061 ACTUATOR DIAMON DA42 DA42 2990004 EU MLG INOPERATIVE D O OTHER O OTHER NR NOT REPORTED 1 NM 07 240TS 681 42072 PILOTS WERE UNABLE TO EXTEND RT MLG WITH THE EMERGENCY EXTENSION HANDLE IN FLIGHT. EMERGENCY SYSTEM OPERATED WITHIN LIM ITS ON THE GROUND. UPON REMOVAL, THE ACTUATOR WAS FOUND TO BE VERY DIFFICULT TO MOVE. ( K) 1 L 7 2 3I RT A57CE 2007102600112 20071026 00112 SO 2007 10 26 2007FA0000948 1 20071024 G 3220 CENTERING MECH PIPER PIPER PA46 PA46310P 7104605 SO CONT O520 TSIO520* 17040 SO NLG FAILED G O OTHER O OTHER LD LANDING 1 SO 11 383SA 4608033 UPON TOUCHDOWN AIRCRAFT VEERED LT ABRUPTLY AND DEPARTED RUNWAY SURFACE. GEAR EXTENSION AND INDICATION WERE NORMAL. INVES TIGATION REVEALED THAT UPON TOUCHDOWN THE NOSE LANDING GEAR HAD FAILED TO CENTER CORRECTLY DURING EXTENSION. 1 L 7 1 3O 3 O RT A25SO E8CE 2007102600106 20071026 00106 NM 2007 10 26 2007FA0000949 1 20071017 G 5610 58935578 WINDSCREEN BOEING 737 7377H4 1384404 NM GE CFM56 CFM567B24 NE COCKPIT CRACKED D H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 WP 01 66ZB 2985 29233 IN CRUISE, 41,000FT (8.5PSID), -60C, ARCING AND SMOLDERING OBSERVED FROM MID BOTTOM OF WINDOW PROPAGATING UP TO TOP FWD EDGE OF RT NR 2 SLIDING WINDOW. WINDOW HEAT, RT, SIDE SWITCH SELECTED OFF. WHILE QRH CONSULTED, AS WINDOW COOLED, CRACK ING OBSERVED ON OUTER PANE ONLY THROUGHOUT THE WINDOW AREA. QRH STATES NO FURTHER ACTION REQUIRED DUE OUTER PANE NOT PR IMARY STRUCTURAL SUPPORT. FLIGHT CONTINUED AT 41,000 FT FOR NEXT 20 MINS TO TOP OF DESCENT. LANDING CARRIED OUT NORMAL LY. WINDOW ASSY REPLACED.. 2 L 7 2 4F 4 F RT A16WE E00055EN 2007102600107 20071026 00107 NM 2007 10 26 2007FA0000950 1 20071017 G 5610 58935578 WINDSCREEN BOEING 737 7377H4 1384404 NM GE CFM56 CFM567B24 NE COCKPIT CRACKED D H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 WP 01 2985 29233 IN CRUISE, 41,000FT (8.5PSID), -60C, ARCING AND SMOULDERING OBSERVED FROM MID BOTTOM OF WINDOW PROPAGATING UP TO TOP FWD EDGE OF RT NR 2 SLIDING WINDOW. WINDOW HEAT, RT, SIDE SWITCH SELECTED OFF. WHILE QRH CONSULTED, AS WINDOW COOLED, CRAC KING OBSERVED ON OUTER PANE ONLY THROUGHOUT THE WINDOW AREA. QRH STATES NO FURTHER ACTION REQUIRED DUE OUTER PANE NOT P IMARY STRUCTURAL SUPPORT. FLIGHT CONTINUED AT 41,000 FT FOR NEXT 20 MINS TO TOP OF DESCENT. LANDING CARRIED OUT NORMAL LY. WINDOW ASSY REPLACED. 2 L 7 2 4F 4 F RT A16WE E00055EN 2007113000142 20071130 00142 EA 2007 11 30 2007FA0000951 2 20070713 G 7261 56G23399 BAFFLE FOUND FBA FBA2C1 3640103 EA LYC O540 TIO540* 41532 EA OIL SUMP BROKEN B O OTHER O OTHER NR NOT REPORTED 1 AL 03 796 599 50 OIL BAFFLE IN SUMP RUBBING ON BOTTOM OF SUMP. 4 OUT OF 6 HOLES CRACKED OUT AROUND MOUNTING AREA. 2 HOLES COMPLETELY WO RN THROUGH AND STILL HAD PARTS OF BAFFLE UNDER WASHER AND MOUNTING SCREW. (K) 1 H 7 1 3O 3 O NC A7EA E14EA 2007110500008 20071105 00008 EA 2007 11 5 2007FA0000952 2 20071010 G 8530 AEL85099 CYLINDER PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA NR 4 FAILED D O OTHER O OTHER NR NOT REPORTED 1 SO 15 602FT 733 2841196 CYLINDER HAD FAILURE, SEPARATION FROM BARREL AT 733 HRS, NOT INCORPORATED IN AD2006-12-7. (K) 1 L 7 1 3O 3 O 2A13 E274 2007110500009 20071105 00009 2007 11 5 2007FA0000953 4 20071011 G 2562 BATTERY AMERIKING PIPER PA28 PA28151 7102805 SO LYC O320 O320* 41508 EA ELT DAMAGED D O OTHER O OTHER NR NOT REPORTED 1 NM 02 32276 287515109 FOUND ELT BATTERY CASE BULGED ON BOTTOM. FOUND ALL CONTACTS WITHIN BATTERY COMPARTMENT LOOSE DUE TO HIGH TEMPERATURE (C OULD SEE WHERE PLASTIC HAD MELTED) COULD NOT DETERMINE WHAT CAUSED THE SHORT. REPLACED ELT. (K) 1 L 7 1 3O 3 O 2A13 E274 2007110500012 20071105 00012 2007 11 5 2007FA0000954 4 20071011 G 2562 BATTERY AMERIKING CESSNA 210 210C 2073412 CE CONT O470 IO470* 17026 SO ELT DAMAGED D K NONE O OTHER IN INSP/MAINT 1 NM 02 22GP 58202 DURING ANNUAL INSPECTION FOUND DRIED ALKILINE BATTERY SUBSTANCE ON EXTERIOR OF CASE. OPEND CASE AND FOUND THAT THE BATT ERIES, ALKALINE BATTERIES WERE COMING APART AT THE SEAMS AND LEAKING. CLEANED BATTERY COMPARTMENT AND INSTALLED FRESH S ET OF BATTERIES. FUNCTION TESTED OK. THIS IS THE THIRD SUCH OCCURENCE THIS YEAR. OF ACID LEAK INTO THE TRANSMITTER. U NIT HAD TO BE REPLACED. (K) 1 H 7 1 3O 3 O 3A21 E1CE 2007110500014 20071105 00014 SO 2007 11 5 2007FA0000955 2 20070921 G 8530 CYLINDER HEAD BEECH 33 F33A 1151425 CE CONT O520 IO520* 17032 SO NR 2 SEPARATED D O OTHER O OTHER NR NOT REPORTED 1 EA 09 711JA CE478 IN-FLIGHT NR 2 CYLINDER HEAD SEPARATED FROM CYLINDER BASE AT TOP OF SLEEVE. PUSHRODS AND TUBES BENT. EXHAUST MANIFOLD B ENT. NOZZLE ASSEMBLY DAMAGED. (K) 1 L 7 1 3O 3 O 3A15 E5CE 2007113000143 20071130 00143 CE 2007 11 30 2007FA0000956 1 20070919 G 5740 50270025 BRACKET CESSNA 310 310R 2074245 CE CONT O520 IO520* 17032 SO RT MLG WW INOPERATIVE E O OTHER O OTHER NR NOT REPORTED 1 GL 13 5338C 310R1544 THE RT MAIN LANDING GEAR WOULD NOT RETRACT INTO WHEEL WELL. PILOT REPORTED LOUD BANG HEARD AFTER RETRACTING OF GEAR. W HEN EXTENDING THE GEAR FOR LANDING, THE RT GEAR WOULD NOT INDICATE GREEN BUT WAS VISUALLY CONFIRMED DOWN. PILOT LANDED WITHOUT INCIDENT AND GREEN LIGHT ILLUMINATED UPON TOUCHDOWN. INSPECTION OF THE RT GEAR FOUND THE TORQUE TUBE SUPPORT BR ACKET ASSY, PN 50270025, BEARING PULLED LATERALLY FROM BRACKET AND ROD END FOR THE UPLOCK PUSH-PULL TUBE BROKEN OFF AT T HE TORQUE TUBE ATTACH POINT PN HM4, AND FORWARD TORQUE TUBE ATTACH BOLT, PN NAS146-40, BENT SLIGHTLY. FAILURE OF THE SU PPORT BRACKET PN 5027002-5 POSSIBLY DUE TO FATIGUE. (K) 1 L 7 2 3O 3 O 3A10 E5CE 2007113000145 20071130 00145 SO 2007 11 30 2007FA0000957 2 20071004 G 7414 10500556101 MAGNETO CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO ENGINE MISOVERHAULED B YD5R O OTHER W INADEQUATE Q C NR NOT REPORTED 1 GL 15 434SR 20 2557 690898 AIRCRAFT ENGINE RUNNING ROUGH AND BACKFIRING ON FLIGHT TEST. PILOT RETURNED AND GROUNDED AIRCRAFT FOR MAINTENANCE. MAI NTENANCE PERSONNEL PERFORMED INTERNAL INSPECTION OF CONVERTED MAGNETOS TO PRESSURIZATION. MAGNETO CONVERTED TO PRESSURI ZED, INSPECTION REVEALED CARBON BRUSHES MISSING ON BOTH MAGNETOS, INTERNAL TIMING WAS WRONG ON ONE OF THE MAGNETOS, WIRE S WERE CHAFED, EXCESS GREASE WAS FOUND ON ROTOR BRUSH ASSEMBLY. FURTHER INVESTIGATION OF AIRCRAFT WITH MAGNETO PN 10-55 0556-101 MODIFIED, INSTALLED ON AIRCRAFT FOR TURBO NORMALIZING. 6 ADDITIONAL MAGNETOS EXHIBITED THE SAME CONDITIONS LIST ED ABOVE. RECOMMENDATIONS FOR CORRECTION ARE TO CONVERT MAGNETOS IAW PUBLISHED SPECS AND PROCEDURES. (K) 1 L 7 1 3O 3 O NT A00009CH E3SO 2007110500013 20071105 00013 EU 2007 11 5 2007FA0000958 2 20070913 G 7310 CASC216 REGULATOR GULSTM G1159 G1159A 3970109 SO RROYCE SPEY SPEY5118 54523 EU FUEL FLOW FAILED D O OTHER J WARNING INDICATION NR NOT REPORTED 1 EA 07 776MA 891 447 11298 PILOTS REPORT FELT HEAVY VIBRATION FOR 3 TO 4 SECONDS, THEN HEARD A LOUD BANG FOLLOWED BY LT ENGINE SPOOLING DOWN. AIRC RAFT SAFELY LANDED AT AIRPORT. CONTACTED MFG, WHO DISPATCHED A RESPONSE CREW TO AIRPORT. FOUND THAT THE FUEL FLOW REGU LATOR HAD FAILED IN FLIGHT. (K) 2 L 7 2 4F 4 F A12EA E2EU 2007113000146 20071130 00146 WP 2007 11 30 2007FA0000959 2 20071002 G 7314 30708507 PUMP LEAR 35 35LEAR 5170600 CE GARRTT TFE731 TFE73122B 01518 WP RT ENGINE FUEL FAILED B X5ER K NONE O OTHER IN INSP/MAINT 1 SW 05 354PM 4254 015 P74271 RT ENGINE FAILED ON TAKEOFF ROLL JUST BEFORE 80 KNTS IAS. AIRCRAFT WAS STILL ON GROUND. FUEL PUMP, FAILED TO PUMP FUEL . (K) 2 L 7 2 4F 4 F A10CE E6WE 2007113000147 20071130 00147 SO 2007 11 30 2007FA0000960 1 20070906 G 3240 BRAKE MAULE MX7 MX7180A 5460186 SO LYC O360 O360* 41514 EA PARK SYS INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 SO 03 30822 22003C PARK BRAKE CABLE HANGING ON 90 DEGREE CABIN FITTING COMING THROUGH FIREWALL. AIRCRAFT BRAKES LOCKED ON WHEN LANDING. D ISCONNECTED PARK BRAKE CABLE AND SAFETY WIRED BRAKE LOCK LEVERS ON MASTER CYLINDER IN NEUTRAL/OFF POSITION PLACARD PANEL MADE LOG BOOK ENTRY. (K) 1 H 7 1 3O 3 O NC 3A23 E286 2007110500015 20071105 00015 SO 2007 11 5 2007FA0000961 1 20070718 G 2140 1386725 HEATER PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A60A 52043 NE COCKPIT LEAKING B O OTHER K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 GL 25 650RS 1 31T8020071 DURING OPERATION OF COMBUSTION HEATER, THE PILOT NOTED JET FUEL ODOR AND SMOKE IN CABIN. HEATER OPERATION WAS TERMINATE D, CABIN WAS VENTED. EMERGENCY WAS DECLARED AND AIRCRAFT LANDED AT NEAREST AIRPORT WITHOUT INCIDENT. UPON REMOVAL, A F UEL LEAK WAS NOTED AT COMBUSTION HEAD AND FUEL SOLENOID AREA. HEATER WAS REPLACED WITH A SERVICEABLE UNIT. (K) 1 L 7 2 3T 4 T A8EA E4EA 2007113000155 20071130 00155 SO 2007 11 30 2007FA0000962 1 20071018 G 3250 3526202 BUNGEE PIPER PA28 PA28140 7102802 SO LYC O320 O320* 41508 EA NLG STEERING FAILED D O OTHER O OTHER NR NOT REPORTED 1 GL 09 56978 287425077 SHORTLY AFTER TAKEOFF, AIRCRAFT WENT INTO SHARP RT TURN. THE PILOT, BY USING FULL OPPOSITE RUDDER AND AVAILABLE RUDDER TRIM, WAS ABLE TO LAND AIRCRAFT SUCCESSFULLY. INSPECTION DETERMINED THAT THE RT NOSE GEAR STEERING BUNGEE SPRING RETAIN ER HAD DEPARTED AND THE SPRING WAS EXTENDED FROM THE BARREL ASSY. THE TURN WAS ALSO EXAGGERATED BY THE LARGE FIN USED O N THE NOSE WHEEL FAIRING. AS IT IS DIFFICULT TO EXAMINE THE RETAINER DUE TO THE LOCATION OF THE BUNGEE ASSY UNDER THE E XHAUST SYSTEM, IT CAN NOT BE DETERMINED IF THE BACK SIDE OF THE RETAINER IS BEING WORN OR CORRODED. THIS PART IS ONLY H ELD IN PLACE BY A FEW TWISTS OF SAFETY WIRE. IT IS SUGGESTED THAT THE MFG LOOK AT THIS AS A MAJOR SAFETY ISSUE AND EITH 1 L 7 1 3O 3 O 2A13 E274 2007113000157 20071130 00157 CE 2007 11 30 2007FA0000963 1 20071018 G 3222 07436062 FITTING CESSNA 182 182T 2072703 CE LYC O540 IO540AB1A5 EA NLG STRUT CHAFED D K NONE O OTHER IN INSP/MAINT 1 SO 03 6025D 18281830 LOWER STRUT SUPPORT FITTING CLAMPING RING CENTER BORE IS NOT CENTERED. THIS CAUSES THE STEERING COLLAR AND LOWER STRUT SUPPORT TO CHAFE AND FOR METAL TO METAL CONTACT TO OCCUR. HAVE TRIED TWO OTHER NEW LOWER STRUT SUPPORT FITTING RESULTIN G WITH METAL TO METAL CHAFING. INITIALLY CONTACTED MFG AND REPORTED THE PROBLEM REVEALING NUMEROUS IDENTICAL PARTS HAVE THE SAME DEFECT. RECOMMEND THAT CONTACT BE MADE WITH MFG AND TO MEASURE FOR PROPER THICKNESS OF THE RING ON THE LOWER STRUT SUPPORT FITTING. (K) 1 H 7 1 3O 3 O NT 3A13 1E4 2007120400005 20071204 00005 SO 2007 12 4 2007FA0000964 1 20071017 G 2822 35328803 PUMP PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA FUEL BOOST MALFUNCTIONED D O OTHER Y ENGINE STOPPAGE CR CRUISE 1 NM 02 515MS 2750 2842157 REPORTED ENGINE QUITTING DURING NORMAL CRUISE, PROBLEM ASSOCIATED WITH FUEL SYSTEM, ONCE ELECTRIC FUEL PUMP TURNED ON EN GINE WOULD RUN NORMAL, FUEL PRESS READINGS CONFIRMED FUEL STARVATION PROBLEM, INITIAL INSPECTIONS FAILED TO FIND A PROBL EM & COULD NOT BE DUPLICATED, REPLACED EDP WITH NEW & FLEW ACFT, PROBLEM REOCCURRED & APPEARED TO BE ISOLATED TO THE RT SIDE FUEL TANK SELECTION, REMOVED FUEL LINE AT CARB & PUMPED FUEL USING BOOST PUMP, MONITORED FLOW RATE FOR BOTH RT AND LT TANKS, INSTALLED VACUUM GAUGE IN SYSTEM AT GASCOLATOR AND MONITORED AMOUNT OF SUCTION CREATED FOR BOTH THE LT & RT, P ROBLEM FINALLY DUPLICATED WHILE MONITORING & PUMPING FUEL, FOUND PROBLEM WAS NOT ISOLATED TO ONE SIDE BUT WOULD OCCUR ON 1 L 7 1 3O 3 O 2A13 E274 2007113000181 20071130 00181 EA 2007 11 30 2007FA0000966 2 20070810 G 8530 LW15322 VALVE LYC O360 O360E1A6 41514 EA CYLINDER WRONG PART D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 RL15377T DURING ASSEMBLY OF THE ENGINE AFTER MAJOR OVERHAUL, ONE OF THE FACTORY NEW CYLINDERS (PN LW15322) HAD A DIFFERENT INTAKE VALVE INSTALLED (PN 73938), AND THE CORRECT VALVE PN LW15314 WAS INSTALLED BY THE CYLINDER SHOP. THIS CYLINDER WAS FACT ORY NEW. (K) 3 O E286 2007110500002 20071105 00002 GL 2007 11 5 2007FA0000967 1 20071031 G 3150 M835366022M RELAY BOMBDR BD700 BD7001A10 1390006 GL MASTER CAUTION FAILED D K NONE N FALSE WARNING IN INSP/MAINT 1 NM 09 1690 9114 MASTER CAUTION RELAY (WIRING DIAGRAM 31-52-00 SHEET 1 - K28, LOCATED ON CIRCUIT CARD DB5 OF JUNCTION BOX 4 FAILED CAUSIN G BOTH MASTER CAUTION WARNING ANNUNCIATORS TO STAY ILLUMINATED - NO RESET AVAILABLE. THIS IS A SINGLE POINT OF FAILURE F OR THE WARNING/CAUTION CONTROL SYSTEM. (3) INTEGRATED AVIONICS COMPUTERS FEED THIS MASTER CAUTION RELAY - SAME WITH THE MASTER WARNING. AFTER DOING A LIMITED INDEPENDENT SURVEY, I DETERMINED THAT THIS HAS OCCURRED ON SEVERAL OTHER AIRCRAFT . 2 L 7 2 4F RT T00003NY 2007120400050 20071204 00050 SO 2007 12 4 2007FA0000968 1 20071102 G 2510 110744701 INERTIA REEL PIPER PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA SEAT HARNESS SEVERED D K NONE O OTHER IN INSP/MAINT 1 SW 99 8440M 8718 288216002 L1042639A A61404 PILOTS SHOULDER HARNESS INERTIA REEL LOCKED UP, UPON EXAMINATION THE METAL GUIDE WHICH SURROUNDS THE FABRIC AND GUIDES I T ONTO THE REEL, HAD RUBBED AGAINST THE CENTER SHAFT OF THE REEL ITSELF. THIS OVER TIME REDUCED THE DIAMETER OF THE SHA FT UNTIL IT FAILED. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2007120400061 20071204 00061 2007 12 4 2007FA0000969 1 20071029 G 6510 538715 SHAFT TAIL ROTOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 WP 23 FINE TRANSVERSE CRACK(S) LOCATED NEAR THE CENTER PORTION OF PART. 2007120400063 20071204 00063 2007 12 4 2007FA0000970 1 20071029 G 6510 538715 SHAFT TAIL ROTOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 WP 23 FINE TRANSVERSE CRACK(S) LOCATED NEAR THE CENTER PORTION OF PART. 2007120400048 20071204 00048 CE 2007 12 4 2007FA0000971 1 20071031 G 3260 41EN16 SQUAT SWITCH BEECH MU300 400BEECH CE PWA JT15 JT15D4 52112 NE LEFT FAILED E A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SO 11 8HQ RJ50 PILOTS REPORTED THAT THE THRUST REVERSER ARM LIGHTS WERE ILLUMINATED IN FLIGHT. PILOTS LANDED AT LZU MAINTENANCE FOUND A FAULTY LT GROUND SAFE SWITCH. MAINTENANCE REPLACED SWITCH WITH NEW UNIT AIRCRAFT CHECKED GOOD. 2 H 7 2 4F 4 F RT A16SW E1NE 2007113000152 20071130 00152 EA 2007 11 30 2007FA0000974 2 20071031 G 7414 K3975 COIL SLICK CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA RT MAGNETO OPEN D D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 NM 07 2378X 1168 98060921 T20608023 L1003761A PILOT REPORTED RT MAGNETO FAILED WHEN CHECKED DURING RUN UP. FOUND COIL HAD OPEN CIRCUIT WHEN CHECK IAW TABLE SEVEN IN U NISON'S 4300/6300 SERIES MM P/N L-1363C. 1 H 7 1 3O 3 O RT A4CE E14EA 2007113000184 20071130 00184 GL 2007 11 30 2007FA0000975 1 20071031 G 3150 M835366022M RELAY BOMBDR BD700 BD7001A10 1390006 GL FAILED C K NONE J WARNING INDICATION IN INSP/MAINT 1 NM 09 999YY 1690 9114 MASTER CAUTION RELAY (WIRING DIAGRAM 31-52-00 SHEET 1 - K28), LOCATED ON CIRCUIT CARD DB5 OF JUNCTION BOX 4 FAILED CAUSI NG BOTH MASTER CAUTION WARNING ENUNCIATORS TO STAY ILLUMINATED - NO RESET AVAILABLE. THIS IS A SINGLE POINT OF FAILURE F OR THE WARNING/CAUTION CONTROL SYSTEM. THREE INTEGRATED AVIONICS COMPUTERS FEED THIS MASTER CAUTION RELAY - SAME WITH TH E MASTER WARNING. AFTER DOING A LIMITED INDEPENDENT SURVEY, I DETERMINED THAT THIS HAS OCCURRED ON SEVERAL OTHER AIRCRA FT. 2 L 7 2 4F RT T00003NY 2007113000125 20071130 00125 WP 2007 11 30 2007FA0000976 2 20071029 G 7250 30606266 ROTOR ISRAEL 1125 ASTRASPX 4500205 EU ALIDSG TFE731 TFE7313AR WP LPT3 SEPARATED B A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 WP 07 400CP 131 113211 IAW SERVICE BULLETIN TFE731-72-5175. BLADE SEPARATION ON ONE LPT3 BLADE AS LISTED IN TABLE 1 OF S/B 72-5175. 2 L 7 2 4F 4 F RT A16NM E6WE 2007120400136 20071204 00136 EA 2007 12 4 2007FA0000979 2 20071018 G 7322 CONTROL ARM DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA CARB HEAT BROKEN D O OTHER O OTHER NR NOT REPORTED 1 SW 99 423FP 40FC023 CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA KE. (K) 1 L 7 1 3O 3 O NT A47CE E286 2007120400137 20071204 00137 SO 2007 12 4 2007FA0000980 1 20071019 G 7820 E362000 MUFFLER PIPER PA18 PA18150 7101828 SO LYC O320 O320B2B 41508 EA ENGINE BROKEN D O OTHER O OTHER NR NOT REPORTED 1 GL 13 98SA 996 187609088 L1333839A THE TAILPIPE CRACKED AWAY FROM THE SHELL. THERE ARE NO STRAPS WELDED FROM THE PIPE TO THE SHELL LIKE SOME OTHER MUFFLER S. THE METAL FAILED, NOT THE WELD. 1 H 7 1 3O 3 O 1A2 E274 2007120400139 20071204 00139 CE 2007 12 4 2007FA0000981 1 20071103 G 3710 RV05268 RELIEF VALVE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE PNEUMATIC SYS SEPARATED D K NONE O OTHER IN INSP/MAINT 1 AL 03 1232Y 3 208B0566 RELIEF VALVE FOR BLEED AIR PNEUMATIC SYSTEM END WASHER AND CAP SEPARATED FROM VALVE AND LAYING IN BOTTOM OF COWLING. SU SPECT RIVET HOLDING PARTS ON IS TOO SOFT. THIS IS THE THIRD VALVE TO FAIL LIKE THIS ON DIFFERENT AIRCRAFT IN THE LAST M ONTH. AND ALL WERE NEW WITH LESS THAN 70 HOURS TIME IN SERVICE. (K) 1 H 7 1 3T 3 T A37CE E4EA 2007120400142 20071204 00142 SO 2007 12 4 2007FA0000982 1 20071028 G 3233 HM6 BEARING PIPER PA24 PA24250 7102404 SO LYC O540 O540* 41532 EA RT MLG ACTUATOR BROKEN D O OTHER O OTHER NR NOT REPORTED 1 GL 13 108SG 2160 24149 RT OB HEIM BEARING BROKE AT THREADS NEXT TO JAM NUT ON ACTUATOR ROD DURING TAKEOFF ROLL W/RESULTANT GEAR COLLAPSE. INCRE ASE SIZE AND STRENGTH OF PART. (K) 1 L 7 1 3O 3 O 1A15 E295 2007120400143 20071204 00143 CE 2007 12 4 2007FA0000983 1 20071022 G 3010 80713 CONTROLLER LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE STAB DEICE INOPERATIVE C K NONE O OTHER IN INSP/MAINT 1 NM 07 415NP 024 REPLACED HORIZONTAL STAB HEAT CONTROLLER. AFTER CHANGING CONTROLLER AIRCRAFT STILL HAD FAULT IN SYSTEM. T/S FURTHER DET ERMINED REPAIRED CONTROLLER WAS NO GOOD. CONTROLLER SHOWED A FAULT IN T8. INSTALLED ANOTHER CONTROLLER SYSTEM CHECKED GOOD. (K) 2 L 7 2 4F 4 F RT A10CE E35NE 2007120400164 20071204 00164 CE 2007 12 4 2007FA0000986 1 20071008 G 2910 165580001135 LINE BEECH 23 C24R 1151254 CE LYC O360 IO360A1A 41514 EA HYD SYSTEM CHAFED D K NONE O OTHER IN INSP/MAINT 1 SO 09 5246M 6712 MC564 PILOT REPORTED HAVING TO SERVICE BRAKE HYDRAULIC RESERVOIR AND/OR RT SIDE OF THE BRAKES VERY SOFT. DURING INSPECTION, F OUND HYDRAULIC FLUID ON WIRE BUNDLE FORWARD OF COPILOTS RT RUDDER PEDAL. CLEANED LINE AND LT LINE SIT FOR A COUPLE DAYS , WHILE DOING AN INSPECTION ON THE REST OF THE AIRCRAFT. FOUND HYDRAULIC FLUID ON LINE. REMOVAL OF THE LINE REVEALED A WORN/CHAFED SPOT APPROX 12 INCHES TO THE LT OF THE B-NUT WHERE IT ATTACHES TO THE BULKHEAD FITTING FROM THE RESERVOIR. DID NOT SEE THE CAUSE OF THE CHAFED AREA ON THE TUBE. SUSPECT AIRFRAME VIBRATION CAUSED THE LINE TO VIBRATE. RECOMMEN D THAT ALL LINES ARE CHECKED FOR CLEARANCE FROM AIRFRAME STRUCTURE OR OTHER LINES. (K) 1 L 7 1 3O 3 O A1CE 1E10 2007120400165 20071204 00165 CE 2007 12 4 2007FA0000987 1 20071101 G 5312 45A3490111 BULKHEAD BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE BS 329 CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 19 940VA RK197 WHILE PERFORMING AN A-C INSPECTION FOUND RT AFT FUSELAGE BLEED AIR LINE ATTACH BRACKET PULLED FROM FUSELAGE BULKHEAD RES ULTING IN A CRACK IN THE BULKHEAD AT FRAME STATION 329.92. RECOMMEND CONTACTING MFG FOR REPAIR OPTIONS CRACK HAS BEEN FOUND ON BOTH SIDES OF THE AIRCRAFT.(K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007120400166 20071204 00166 CE 2007 12 4 2007FA0000988 1 20071031 G 5551 45A2100291 PIVOT BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE HORIZONTAL STAB LOOSE D K NONE O OTHER IN INSP/MAINT 1 GL 19 940VA RK197 WHILE PERFORMING AN A-C INSPECTION FOUND 8 LOOSE RIVETS IN THE FORWARD RIVET LINE OF THE ATTACHMENT PIVOT FITTING PN 45A 2118311 ON THE BOTTOM OF THE HORIZONTAL STABILIZER. IT IS SUSPECTED THAT THE LOOSE RIVETS WERE CAUSED BY FATIGUE AND AG E. 2 H 7 2 4F 4 F RT A16SW E25EA 2007120400103 20071204 00103 SO 2007 12 4 2007FA0000989 1 20071106 G 3211 LANDING GEAR PIPER PA30 PA30 7103002 SO LYC O320 IO320* 41508 EA MAINS WORN G O OTHER O OTHER LD LANDING 1 CE 07 22HW 5124 893 30791 PART (A) OF AD 77-13-21 REQUIRES INSPECTION OF LANDING GEAR EVERY 1000 HRS IAW SL 782. AIRCRAFT EXPERIENCED A COLLAPSED RT MLG FOLLOWING A SCENARIO THAT IS IDENTIFIED IN SL 782. THIS SCENARIO INCLUDES A POPPED LANDING GEAR MOTOR CIRCUIT B REAKER RESULTING IN A FAILED MLG EXTENSION, FOLLOWED BY A MANUAL GEAR EXTENSION. INVESTIGATION FOUND MANY OF THE PARTS IDENTIFIED IN SL 782 WERE WORN AND REQUIRED REPLACEMENT. PART (A) OF THE AD 77-13-21 HAD BEEN COMPLETED 893 HRS AND 12 YEARS AGO. OWNERS AND OPERATORS SHOULD CONSIDER COMPLYING WITH AD 77-13-21 PART (A) MORE OFTEN THAN THE 1000 HRS AS REQ UIRED. AD 77-13-21 DOES NOT CONTAIN A CALENDAR REQUIREMENT. 1 L 7 2 3O 3 O A1EA 1E12 2007120400130 20071204 00130 SO 2007 12 4 2007FA0000990 1 20070130 G 3230 452729 BEARING PIPER PA32 PA32R300 7103213 SO LYC O540 IO540* 41532 EA ROD END BROKEN D O OTHER O OTHER NR NOT REPORTED 1 CE 01 406RB 6700 32R7880009 NOSE GEAR EXTENDED SUDDENLY AND UNCOMMANDED IN FLIGHT, EXAMINED AND FOUND CYLINDER ROD END TO NOSE GEAR RETRACT ASSY WA S BROKEN. 1 L 7 1 3O 3 O A3SO 1E4 2007120400167 20071204 00167 CE 2007 12 4 2007FA0000995 1 20071107 G 2420 6041H190 RELAY BEECH 200 A200 1152921 CE RT STARTER GEN MELTED D K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 SW 99 BC27 RT STARTER GENERATOR RELAY P/N: 6041H190 MELTED AT BUSS BAR CONNECTION. 1 L 7 2 4T A24CE 2007120400110 20071204 00110 CE 2007 12 4 2007FA0000996 1 20071107 G 5753 086210057 TUBE CESSNA 414 414A 2075907 CE TE FLAPS BROKEN D O OTHER O OTHER LD LANDING 1 GL 27 7707 DURING FLAP EXTENSION THE RT SIDE FLAPS RETRACTED SUDDENLY LEAVING THE LT FLAPS DOWN. FOUND THE PUSHROD TUBE CONNECTING THE IB AND MIDDLE FLAP BELLCRANK TO HAVE FAILED AT THE OB END OF THE TUBE. THE TUBE APPEARS TO HAVE BEEN ABOUT 60 PERC ENT CRACKED THROUGH THE DIAMETER FOR SOME TIME, POSSIBLY SINCE NEW. THIS FAILURE OCCURRED JUST BELOW THE LOCK NUT WHICH SECURES THE ROD END TO THE TUBE, AND THE FAILED AREA IS IN THE THREADED PORTION OF THE TUBE MAKING IT DIFFICULT OR IMPO SSIBLE TO SEE A DEVELOPING CRACK. 1 L 7 2 3O A7CE 2007120400070 20071204 00070 SO 2007 12 4 2007FA0000997 1 20071105 G 3220 452729 BEARING PIPER PA32 PA32R301 7103218 SO LYC O540 IO540* 41532 EA NLG ROD END FAILED C O OTHER O OTHER CR CRUISE 1 CE 01 83213 6282 32R8113035 WHILE IN FLIGHT THE NOSE GEAR RETRACT CYLINDER PISTON ROD END FAILED, CAUSING IMMEDIATE EXTENSION OF THE NOSE GEAR. 1 L 7 1 3O 3 O A3SO 1E4 2007120400174 20071204 00174 GL 2007 12 4 2007FA0000999 1 20071108 G 2421 BRUSHES CESSNA CIRRUS SR SR20 05628AJ GL LYC IO360 IO360L2A EA ALTERNATOR WORN D K NONE O OTHER IN INSP/MAINT 1 GL 09 1180 494 A180062 1576 L3328651E DURING FLIGHT, PILOT REPORTED LOW VOLTAGE INDICATION. RESET ATTEMPTS WERE UNSUCESSFUL. PILOT RETURNED TO STATION. ALTE RNATOR BRUSHES FOUND TO BE WORN BEYOND USE. 1 L 7 1 3O 3 O NT A00009CH 1E10 2007120400173 20071204 00173 EU 2007 12 4 2007FA0001000 1 20071108 G 3320 6178A POWER SUPPLY HAWKER BAE125 BAE125700B 7450007 EU GARRTT TFE731 TFE731* 01518 WP CABIN LIGHTING BURNED B O OTHER O OTHER NR NOT REPORTED 1 GL 15 107LT 257146 DISCREPANCY WAS CABIN INDIRECT LIGHTING IS INTERMITTENT. FOUND SHORTED WIRING AT AFT LT SIDE VALANCE, 2 BURNED POWER SUP PLIES AND SEVERAL CRACKED LAMP FIXTURES. CUSTOMER STATED THIS IS THE 3RD TIME THE POWER SUPPLIES WERE FOUND BURNED. 2 L 7 2 4F 4 F RT A3EU E6WE 2007110900245 20071109 00245 CE 2007 11 9 2007FA0001001 1 20071109 G 2750 040010740 CONTROL CABLE CESSNA 150 150E 2071812 CE TE FLAP FRAYED B O OTHER O OTHER AP APPROACH 1 WP 07 31ER 6487 98 15061072 ASSYMETRIC DEPLOYMENT OF FLAPS ON FINAL APPROACH. LOUD SNAP HEARD NOVING FLAPS FROM 30 TO 40 DEGREES. MAINTENANCE FOUND THE LEFT FLAP EXTEND CABLE BROKEN AT THE OUTBOARD PULLEY. 1 H 7 1 3O 3A19 2007121300243 20071213 00243 SW 2007 12 13 2007FA0001002 1 20071106 G 5520 TORQUE TUBE SWRNGN SA227 SA227* SW LT ELEVATOR SHEARED H K NONE O OTHER IN INSP/MAINT 1 SW 17 6734 858 DURING A ROUTINE PHASE INSPECTION OF THE AIRCRAFT, IT WAS DISCOVERED THAT THE LT ELEVATOR PIVOT PIN ON THE TORQUE TUBE A SSEMBLY PN 27-44026-007 WAS SHEARED. INITIAL INSPECTION REVEALED CORROSION/RUST AND EXTENSIVE PITTING IN THE PIN. THIS P IN IS (1) OF (3) IN A LINEAR LINE ATTACHING THE ELEVATOR TO THE AIRCRAFT STABILIZER. THIS AIRCRAFT IS NORMALLY LOCATED O UTSIDE EXPOSED TO THE WEATHER ELEMENTS NEAR SALT AIR/RAIN. THIS PART ALSO REVEALED A CORRODED VTA BEARING PN VTA04270. A VISUAL GVI IN THE SUSPECT AREA CAN EASILY INDICATE A PROBLEM FOR CORROSION. RECOMMENDATION: (1) GVI OF TORQUE TUBE AS SEMBLY IF THE AIRCRAFT IS STORED EXPOSED TO SALT AIR OR RAIN ON A ROUTINE BASIS. (2) GVI OF THE VTA BEARING. IPC 27-30 2 L 7 2 4T RT A5SW 2007120500018 20071205 00018 EA 2007 12 5 2007FA0001007 1 20071031 G 3246 269A3245919 SKID SCWZER 269 269D 8059501 EA ALLSN 250C 250C30 03013 GL LT MLG DAMAGED D O OTHER O OTHER LD LANDING 1 EA 63 411HU 122 0040 UPON LANDING THE HELICOPTER IN A SLIGHT FWD AND LT MOTION IN FLAT GRASS AREA HEARD SLIGHT CLICK OR CLUNK, PIC DIDN`T SEE ANY DAMAGE, PICKED UP AIRCRAFT TO A HOVER AND GROUND CREW SAW FWD END OF LT SKID TUBE HANGING BELOW THE AIRCRAFT. (K) 1 G 7 1 3U 3 U 0 4H12 E1GL 2007120500019 20071205 00019 CE 2007 12 5 2007FA0001008 1 20071029 G 2612 991203611 FIRE LOOP CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE NR 1 ENGINE FAILED D F ACTIVATE FIRE EXT. N FALSE WARNING CR CRUISE 1 GL 09 189WW 5605069 NR 1 ENGINE FIRE LOOP FAILED, CAUSING THE NR 1 ENGINE FIRE INDICATOR IN COCKPIT TO ERRONEOUSLY INDICATE A FIRE. CREW FI RED BOTH FIRE EXTINGUISHERS FOR THE ENGINE WHICH DID NOT EXTINGUISH THE FIRE INDICATOR. THE CREW THEN DECLARED AN IN-FL IGHT EMERGENCY. (K) 2 L 7 2 4F 4 F RT A22CE E00059EN 2007120500020 20071205 00020 SO 2007 12 5 2007FA0001009 1 20071003 G 3230 757496 PIN WIEBEL PIPER PA31 PA31350 7103110 SO LYC O540 TIO540* 41532 EA LOWER CLEVIS BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 05 31NW 5912 318152139 EMERGENCY GEAR EXTENSION PUMP LOWER CLEVIS PIN BROKEN, FAILURE FOUND ON 2 SIMILAR AIRCRAFT. (K) 1 L 7 2 3O 3 O A20SO E14EA 2007120500021 20071205 00021 SO 2007 12 5 2007FA0001010 1 20071101 G 7810 PA18ESA PIPE PIPER PA18 PA18150 7101828 SO LYC O360 O360A1A 41514 EA MCAULY 1A200 1A200FA GL EXHAUST FAILED G K NONE O OTHER IN INSP/MAINT 1 GL 15 7066B 185140 L76336 LEADING EDGE EXHAUST SYSTEM INSTALLED BY STC SA02200AK FAILED AT THE SAIL PIPE TO MUFFLER WELD. SYSTEM HAS 36 HOURS SIN CE NEW. (K) 1 H 7 1 3O 3 O 1A2 E286 5 N P874 2007120500022 20071205 00022 SO 2007 12 5 2007FA0001011 2 20071025 G 8550 SA56250 DRAIN BBAVIA 7 7EC 2110120 SW CONT O200 O200* 17020 SO ENGINE OIL LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 13 274AC 101407 INSTALLED QUICK DRAIN VALVE (OIL) ON NEW AIRCRAFT/ ENGINE. AIRCRAFT FLEW APPROX 1 HR , INITIAL FLIGHT TEST. VERY MINUT E OIL LEAK WAS NOTED FROM OIL QUICK DRAIN VALVE. REMOVED VALVE TO FIND VALVE SNAP RING IN OIL DRAINED FROM ENGINE, ALSO FOUND O-RING SPLIT. NOTE: NO DAMAGE TO ENGINE OCCURRED. (K) 1 H 7 1 3O 3 O A759 E252 2007120500024 20071205 00024 CE 2007 12 5 2007FA0001012 1 20071030 G 2140 HYLZ50336001 TRANSISTOR BARBERCOL BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A60A 52043 NE TEMP CONTROL FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 200CJ 377OK BB143 PC BOARD IN ASSY PN HYLZ50336-001 HAD FAILURE, BURNED/ OVERHEATED TRANSISTOR. NOTE: FAN IN ASSY WAS WORKING. PC BOARD PN HYLZ 105-001. (K) 1 L 7 2 4T 4 T A24CE E4EA 2007120500026 20071205 00026 CE 2007 12 5 2007FA0001013 1 20071105 G 2612 991203611 FIRE LOOP CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE NR 1 ENGINE FAILED D F ACTIVATE FIRE EXT. N FALSE WARNING CR CRUISE 1 EA 09 189WW 5605069 NR 1 ENGINE FIRE LOOP FAILED CAUSING THE NR 1 ENGINE FIRE INDICATOR IN COCKPIT TO ERRONEOUSLY INDICATE A FIRE. CREW FIR ED BOTH FIRE EXTINGUISHERS FOR THE ENGINE WHICH DID NOT EXTINGUISH THE FIRE INDICATOR. THE CREW THEN DECLARED AN IN-FLI GHT EMERGENCY. (K) 2 L 7 2 4F 4 F RT A22CE E00059EN 2007120500027 20071205 00027 SO 2007 12 5 2007FA0001015 1 20071105 G 2797 061E1P1E1 CONNECTOR GULSTM GV GULFSTREAMGV 3980116 SO RROYCE BR700 BR700710A110 NE RT FLAP RESOLVER CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 11 507QS 625 BACK SHELL IS BROKEN/CRACKED AND SEPARATED FROM CONNECTOR PLUG ASSY. POSSIBLE CAUSE IS WIRE BUNDLE TO CONNECTOR PLUG ST RESSES AND PULLING ON BACK SHELL. BACK SHELL IS MADE ON PLASTIC NOT METAL. IF BACK SHELL WAS MADE OF METAL IT WOULD HOL D UP AS A STRAIN RELIEF FOR THE ATTACHING WIRE BUNDLE. IF A PLASTIC BACK SHELL IS CONTINUED TO BE USED, WIRE BUNDLE SHO ULD ALLOW SLACK ENOUGH NOT TO STRAIN THE STRAIN RELIEF. A METAL BACKSHELL IS THE MORE POSITIVE FIX FOR THIS PROBLEM. ( K) 2 L 7 2 4F 4 F RT A12EA E00057EN 2007120500028 20071205 00028 EU 2007 12 5 2007FA0001016 1 20071106 G 5330 SKIN AEROSP AS355 AS355F2 8680812 EU ALLSN 250C 250C20 03013 GL FUSELAGE WORN B UOHR K NONE O OTHER IN INSP/MAINT 1 GL 13 942MS 6444 5498 RT AND LT FUSELAGE SKIN AT TAILBOOM ATTACH BULKHEAD. FOUND WORKING RIVETS ON BOTH SIDES. (40) FOUND SKIN UNDER WORKING RIVETS WORN .018. ASB 05-00-42 AS FACTOR. FUSELAGE SENT TO A REPAIR FACILITY FOR SKIN REPLACEMENT. (K) 1 G 7 2 3U 3 U H11EU E4CE 2007120500029 20071205 00029 SW 2007 12 5 2007FA0001017 1 20070830 G 8120 635630 TURBOCHARGER MOONEY M20 M20K 5870220 SW CONT O520 TSIO520NB 17040 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 231GZ 959 250253 8223022R FOUND APPROX 1.25 INCH CRACK IN TURBO CHARGER HOUSING BELOW EXHAUST INLET AT WELD. (K) 1 L 7 1 3O 3 O 2A3 E8CE 2007120500030 20071205 00030 EU 2007 12 5 2007FA0001018 1 20071024 G 2820 CONTROL UNIT AMD FALC90 FALCON900EX 2730009 EU GARRTT TFE731 TFE731* 01518 WP CROSSFEED LEAKING C K NONE K FLUID LOSS IN INSP/MAINT 1 EA 25 47EG 903 B72992 154 FUEL LEAKING FROM CENTRAL LB CROSSFEED UNIT AND DRAIN TUBE CAP BROKEN. REF MFG SERVICE ADVISORY FSA900EX-EASY-28-10-03-R 1. (K) 2 L 7 3 4F 4 F RT A46EU E6WE 2007120500034 20071205 00034 SO 2007 12 5 2007FA0001019 2 20071113 G 8530 TISN712ACA CYLINDER HEAD BEECH 55 D55 1152730 CE CONT O520 TSIO520EB 17040 SO ENGINE CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 05 69RP 937 TE766 282253R CRACKED CYL HEAD BEHIND INJECTOR BETWEEN FIN NR 12, NR 3. DEFECTIVE MFG PROCESS. (K) 1 L 7 2 3O 3 O 3A16 E8CE 2007120500035 20071205 00035 SO 2007 12 5 2007FA0001020 2 20071113 G 8530 TISN712ACA CYLINDER HEAD BEECH 55 D55 1152730 CE CONT O520 TSIO520EB 17040 SO NR 3 CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 05 69RP 937 TE766 282253R CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3. DEFECTIVE MFG PROCESS. (K) 1 L 7 2 3O 3 O 3A16 E8CE 2007120500036 20071205 00036 SO 2007 12 5 2007FA0001021 2 20071113 G 8530 TISN712ACA CYLINDER HEAD BEECH 55 D55 1152730 CE CONT O520 TSIO520EB 17040 SO ENGINE CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 05 69RP 937 TE766 282253R CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3. DEFECTIVE MFG PROCESS. (K) 1 L 7 2 3O 3 O 3A16 E8CE 2007120500037 20071205 00037 SO 2007 12 5 2007FA0001022 2 20071113 G 8530 TISN712ACA CYLINDER HEAD BEECH 55 D55 1152730 CE CONT O520 TSIO520EB 17040 SO ENGINE CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 03 69RP 937 TE766 2822253R CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3. DEFECTIVE MFG PROCESS. (K) 1 L 7 2 3O 3 O 3A16 E8CE 2007120500038 20071205 00038 SO 2007 12 5 2007FA0001023 2 20071113 G 8530 TISN712ACA CYLINDER HEAD BEECH 55 D55 1152730 CE CONT O520 TSIO520EB 17040 SO ENGINE CRACKED C O OTHER O OTHER NR NOT REPORTED 1 SW 05 69RP 937 TE766 282253R CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3. DEFECTIVE MFG PROCESS. (K) 1 L 7 2 3O 3 O 3A16 E8CE 2007120500039 20071205 00039 SO 2007 12 5 2007FA0001024 2 20071108 G 8530 TISN712BCA CYLINDER HEAD CESSNA 402 402B 207590P CE CONT O520 TSIO520EB 17040 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 4165G 677 402B1212 510771 CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR1, NR3. DEFECT IN MFG PROCESS. (K) 1 L 7 2 3O 3 O A7CE E8CE 2007120500040 20071205 00040 SO 2007 12 5 2007FA0001025 2 20071108 G 8530 TISN712BCA CYLINDER HEAD CESSNA 402 402B 207590P CE CONT O520 TSIO520EB 17040 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 4165G 677 402B1212 510771 CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3. DEFECT IN MFG PROCESS. (K) 1 L 7 2 3O 3 O A7CE E8CE 2007120500041 20071205 00041 SO 2007 12 5 2007FA0001026 2 20071108 G 8530 TISN712BCA CYLINDER HEAD CESSNA 402 402B 207590P CE CONT O520 TSIO520EB 17040 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 4165G 677 402B1212 510771 CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3. DEFECT IN MFG PROCESS. (K) 1 L 7 2 3O 3 O A7CE E8CE 2007120500042 20071205 00042 SO 2007 12 5 2007FA0001027 2 20071108 G 8530 TISN712BCA CYLINDER HEAD CESSNA 402 402B 207590P CE CONT O520 TSIO520EB 17040 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 4165G 677 402B1212 510771 CRACKED CYL HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3. (K) 1 L 7 2 3O 3 O A7CE E8CE 2007120500043 20071205 00043 SO 2007 12 5 2007FA0001028 2 20071107 G 8530 TISN712BCA CYLINDER HEAD CESSNA 402 402B 207590P CE CONT O520 TSIO520EB 17040 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 4165G 677 402B1212 510771 CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR1, NR3. DEFECT IN MFG PROCESS. (K) 1 L 7 2 3O 3 O A7CE E8CE 2007120500044 20071205 00044 SO 2007 12 5 2007FA0001029 2 20071113 G 8530 TISN712ACA CYLINDER HEAD BEECH 55 D55 1152730 CE CONT O520 TSIO520EB 17040 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 69RP 937 TE766 282253R CRACKED CYLINDER HEAD BEHIND INJECTOR BETWEEN FIN NR 1, NR 3. DEFECTIVE MFG PROCESS. (K) 1 L 7 2 3O 3 O 3A16 E8CE 2007120500046 20071205 00046 CE 2007 12 5 2007FA0001030 1 20071106 G 5740 5012007716 SUPPORT BRACKET BEECH 90 C90 1152913 CE PWA PT6 PT6* 52043 EA MLGWW CRACKED B HSRR K NONE O OTHER IN INSP/MAINT 1 NM 05 28KP 6171 LJ845 DRAG LEG SUPPORT BRACKETS FOUND CRACKED ON BOTH LT AND RT SIDES DURING A ROUTINE INSPECTION. MOST LIKELY FATIGUE CRACKS OR A ROUGH LANDING. (K) 1 L 7 2 3T 3 T 3A20 E2NE 2007120500047 20071205 00047 CE 2007 12 5 2007FA0001031 1 20071106 G 5740 5012007717 SUPPORT BRACKET BEECH 90 C90 1152913 CE PWA PT6 PT6* 52043 EA MLG WW CRACKED B HSRR K NONE O OTHER IN INSP/MAINT 1 NM 05 28KP 6171 LJ845 DRAG LEG SUPPORT BRACKETS FOUND CRACKED ON BOTH LT AND RT SIDES DURING A ROUTINE INSPECTION. MOST LIKELY FATIGUE CRACKS OR A ROUGH LANDING. (K) 1 L 7 2 3T 3 T 3A20 E2NE 2007120500049 20071205 00049 CE 2007 12 5 2007FA0001032 1 20071022 G 2120 354021 DUCT RKWELL NA265 NA26560 7630106 CE PWA JT12 JT12A8 52042 NE CABIN PRESSURE DEFORMED D K NONE O OTHER IN INSP/MAINT 1 GL 15 59K 30682 P672922NB ATTACHING SLEEVE SLID OFF OF DUCT CAUSING LOSS OF PRESSURIZATION. EMERGENCY PRESSURIZATION FUNCTIONED NORMALLY. CLAMPS TIGHTENED TOO TIGHT AND DEFORMED FIBERGLASS DUCT. RECOMMEND METAL SLEEVE BE INSTALLED TO ALLEVIATE DEFORMATION. (K) 2 L 7 2 4J 4 J RT A2WE 1E9 2007120500050 20071205 00050 SO 2007 12 5 2007FA0001033 1 20071106 G 5312 49099 BULKHEAD LUSCOM 8 8F 8190114 SO LYC O320 O320* 41508 EA FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 15 9937B 2115 S41 DURING AN ANNUAL INSPECTION, FOUND AFT FUSELAGE BULKHEAD CRACKED AT TOP OF CUTOUT FOR ELEVATOR HORN. 50 PERCENT. THIS IS WHERE THE VERTICAL AND HORIZONTAL STABILIZERS ATTACH. THIS AREA IS HIDDEN BEHIND THE WEB OF THE VERTICAL STAB AFT SP AR AND WAS FOUND WHEN COMPONENTS WERE REMOVED TO REPAIR FWD SPAR (FOUND CRACKED) OF THE HORIZONTAL STAB. THE VERTICAL S TAB IS NOT OF THE ROUNDED TIP TYPE, HAS AN ALUMINUM FWD ATTACHMENT AND STEEL AFT ATTACHMENT. (K) 1 H 7 1 3O 3 O A694 E274 2007120500051 20071205 00051 CE 2007 12 5 2007FA0001034 1 20070913 G 5230 1211673323 DOOR CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA RT AFT CARGO MISRIGGED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 07 168JS 154 T20608735 MM (52-30-00 PG 201), (THE AFT DOOR IS HINGED AT FUSELAGE STA 112 AND IS A STRUCTURAL, LOAD CARRYING MEMBER WHEN CLOSED AND LOCKED). REMOVED AFT CARGO DOOR ROYALITE AND TRIM TO GAIN ACCESS TO LWR AFT CABIN LOWER HOOK ADJUSTMENT ROD. THIS WAS DUE TO A CLUB MEMBER IMPROPERLY CLOSING THE DOOR AND BENDING THE ROD. THE PERSON FAILED TO PULL-DOWN RED HANDLE WH EN CLOSING DOOR AND JAMMED THE LOWER HOOK. HOWEVER, FOUND THE ADJUSTMENT RODS LOOSE(UPPER AND LOWER) AND WOULD EASILY T URN, INCLUDING THE TURNBUCKLES, UPPER AND LWR. THIS WAS DUE TO THE JAM NUTS FOR THE TURNBUCKLES LOOSE AND/OR BACKED OFF TO WHERE THERE WERE BOTTOM OF THREADS ON THE ADJUSTMENT RODS FOR THE HOOKS. IF LEFT UNADDRESSED COULD CAUSE PREVENTING 1 H 7 1 3O 3 O RT A4CE E14EA 2007120500053 20071205 00053 CE 2007 12 5 2007FA0001035 1 20071114 G 2820 0500106326 LINE CESSNA 180 180J 2072622 CE CONT O470 O470* 17026 SO FUEL SYS MISROUTED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 19 6WH 2365 18052492 (2) AILERON CABLES, (1) FLAP CABLE AND THE FUEL LINE ARE ALL ROUTED THROUGH THE LT LOWER AFT DOOR POST AREA. THE FUEL L INE IS PROTECTED BY A PLASTIC SLEEVE BUT THE CABLE WORE THROUGH THE SLEEVE AND WAS WEARING INTO THE FUEL LINE. THE LINE IS APPROX 20 INCHES LONG WITH (4) BENDS. SUGGEST A (1) TIME INSPECTION IN CASE OTHER AC MIGHT HAVE THIS PROBLEM. (K) 1 H 7 1 3O 3 O 5A6 E273 2007120500054 20071205 00054 CE 2007 12 5 2007FA0001036 1 20071108 G 5610 WINDSHIELD CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C GL COCKPIT FAILED D O OTHER O OTHER CR CRUISE 1 CE 03 93TX 7500099 AC IN FLIGHT AND AT CRUISE ALTITUDE THE LT WINDSHIELD HEAT FAILED, A VISABLE SHORT OR ARCING AREA WAS SEEN, CONDITION OF UNIT MATCHED WITH SWITCH (OFF) 30 SEC LATER WINDSHIELD CRACKED IN A SPIDER WEB FASHION. AC LANDED IN STL. WINDSHIELD REPLACED BY SERVICE CENTER WITH A NEW STYLE WINDSHIELD PN 139731-1 (9914380-13). 2 L 7 2 4J 4 F RT T00007WI TE6CH 2007120500055 20071205 00055 2007 12 5 2007FA0001037 1 20071101 G 3246 BEARING NLG WHEEL WRONG PART B SCSZ K NONE O OTHER IN INSP/MAINT 1 EA 33 1170 ON OCT 10, INFORMED BY TECH THAT THEY HAD AN INSTALLED NOSEWHEEL (PN 277A6000-851, SN 1170) ON AIRCRAFT, WITH A WRONG BE ARING INSTALLED. IAW STS, THE ERROR WAS ONLY DISCOVERED AFTER THE WHEEL HAD BEEN INSTALLED, BUT BEFORE THE AC WAS RELEA SED TO SERVICE. REPORTED ERROR WAS THAT THE INNER BEARING DIAMETER WAS 11MM TOO WIDE. ONCE WHEEL WAS RETURNED TO SHOP, INVESTIGATION SHOWED THAT A WRONG BEARING HAD BEEN INSTALLED. INSTEAD OF THE CORRECT BEARING, A MD80 BEARING HAD BEEN INSTALLED. INVESTIGATION OF THE ASSY PROCESS REVEALED NO DISCREPANCIES IN THE PROCESS ITSELF. IT HAS THEREFORE BEEN JU DGED AS A HUMAN ERROR. IN ORDER TO RAISE AWARENESS AMONG THE TECHNICIANS AND ENSURE PREVENTIVE MEASURES, THE PRODUCTION 2007120500056 20071205 00056 SO 2007 12 5 2007FA0001038 1 20070828 G 7810 76048 GASKET PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA EXHAUST WRONG PART D K NONE O OTHER IN INSP/MAINT 1 CE 07 7325L 31P7400206 VISUALLY INSPECTED RT ENG AFTER RECOVERING THE A/C FROM A FIELD. FOUND MELTED WIRING AT NR 6 CYLINDER AND BEHIND IT. T HE P-LEAD FOR THE RT MAG WAS MELTED AND WHEN TESTED FOUND TO BE SHORTED OUT. THIS SHUT-OFF RT MAG. THE NR 6 BOTTOM PLU G WIRE WAS HANGING LOOSE AND THE NUT ATTACHING LEAD TO THE PLUG WAS MELTED OFF. SEVERAL OTHER PLUG WIRES WERE BURNED AS WELL. CAUSE OF THIS DAMAGE WAS A BLOWN OUT EXHAUST GASKET ON NR 6 CYLINDER. WHEN THE GASKET BLEW OUT, HOT EXHAUST WAS AL LOWED TO BURN UP THE PLUG WIRES AND MAG P-LEAD. P-LEAD THEN SHUT OFF THE RT MAG PROTECTIVE COATING WAS BURNED OFF. SO NOW AT BEST, HAVE 1 MAG WORKING AND ONLY FIRING ON 5 CYLINDERS, AND A LARGE EXHAUST LEAK WHICH WILL LOWER MANIFOLD PRESS 1 L 7 2 3O 3 O A8EA E19EA 2007120400343 20071204 00343 SO 2007 12 4 2007FA0001039 1 20071118 G 2721 62829003 SHAFT PIPER PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA RUDDER TRIM SHEARED C D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 EA 15 149LH 1697 2842192 THE RUDDER TRIM SHAFT ASSEMBLY'S SPRING RETAINING PIN SHEARED AT WELD, CAUSING HIGH LT RUDDER STIFFNESS AND PREVENTING T HE NOSE WHEEL FROM BEING TURNED WITH TOW BAR. 1 L 7 1 3O 3 O 2A13 E274 2007120500016 20071205 00016 EU 2007 12 5 2007FA0001040 2 20071108 G 7320 057610E000201 FADEC DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE1250299 EU MALFUNCTIONED D A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SO 15 490TS 6 42AC090 020201763 DURING FLIGHT TRAINING MANEUVERS, SIMULATED SINGLE ENGINE OPERATIONS AT 5000 FT ASL, THE LT ENGINE WAS THROTTLED BACK TO FLIGHT IDLE (5 PERCENT POWER, THROTTLE RETARDED). UPON RETURN TO NORMAL POWER OPERATIONS THE LT ENGINE BEGAN TO SURGE F ROM 20-100 PERCENT POWER, REGARDLESS OF THROTTLE POSITION, ENGINE WAS UNCONTROLLABLE. THE LT ENGINE FADEC WAS SELECTED FROM ECU A TO ECU B AND CONTROL OF LT ENGINE WAS REGAINED. THE AIRCRAFT RETURNED TO DEPARTURE AND LANDED WITHOUT FURTHER INCIDENT. DISCREPANCY COULD NOT BE DUPLICATED DURING GROUND TESTS. LT ENGINE OPERATED NORMALLY ON BOTH ECU A AND ECU B OF THE LT FADEC. LT FADEC REPLACED AND AIRCRAFT RELEASED FOR TEST FLIGHT. NO FURTHER ENGINE SURGING NOTED. 1 L 7 2 3I 3 B RT A57CE E00069EN 2007120400327 20071204 00327 NE 2007 12 4 2007FA0001042 2 20071115 G 7320 RSA10AD1 FUEL CONTROL RHNFLU EXT300 EA300L 70218DG EU LYC O540 AEIO540L1B5 41532 NE ENGINE MALFUNCTIONED G O OTHER Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 WP 05 51E 1759 015 L2570748A THE AIRCRAFT EXPERIENCED AN INFLIGHT ENGINE SHUTDOWN RESULTING IN A FORCED LANDING ON THE BEACH. THE CAUSE OF THE INFLIG HT ENGINE SHUTDOWN WAS THE INTERNAL FAILURE OF THE FUEL SERVO. THE FUEL SERVO WAS EVALUATED . THE FAILED UNIT WAS SENT TO THE MANUFACTURER FOR FURTHER EVALUATION. AFTER FURTHER INVESTIGATION THEY DETERMINED THE CAUSE OF THE INTERNAL FAILUR E WAS DUE TO FOD ENTERING THE FUEL SERVO AND WORE AWAY AT THE REGULATOR ASSEMBLY. THE DIFINITIVE CAUSE IS STILL UNDER IN VESTIGATION AT MFG. 1 M 7 1 3O 3 O NC EA67U 1E4 2007121300260 20071213 00260 CE 2007 12 13 2007FA0001043 1 20071024 G 3222 3908204080001 STOP RAYTHN 390 390 7150030 CE NLG STRUT DISTORTED B E81R O OTHER J WARNING INDICATION CL CLIMB 1 GL 03 112CM RB123 PILOT REPORTED LANDING GEAR UNLOCKED INDICATION AFTER GEAR RETRACTION AFTER TAKEOFF. FOUND NLG STOPPER ASSY DAMAGED AND PREVENTING NLG ASSY FROM CENTERING AND ENGAGING UPLOCK ASSY. REPLACED STOPPER ASSY AFTER NLG DISASSEMBLY AND INSPECTIO N, LANDING GEAR OPERATIONS NORMAL. REPORTED THAT AIRCRAFT WAS PREVIOUSLY TOWED WITH NLG TORQUE LINKS CONNECTED. FLIGHT CREW, GROUND OPERATIONS, PERSONNEL AND TECHS SHOULD BE AWARE OF CORRECT PREMIER TOWING PROCEDURES AS SPECIFIED IN THE 3 90 MM, SEC 9-10-01-201. (K) 1 L 7 2 3F RT A00010WI 2007121300261 20071213 00261 CE 2007 12 13 2007FA0001044 1 20071114 G 3210 12116013 CASTING CESSNA 206 T206H 2073303 CE LT MLG CRACKED B RDDR O OTHER O OTHER NR NOT REPORTED 1 NM 11 1250 T20608075 AIRCRAFT OPERATED ON MOSTLY UNIMPROVED AIRSTRIPS. PART IS SAME AS 206F AND G MODELS. PART IN QUESTION WAS INSTALLED AT TIME OF MFG OF AIRPLANE. CASTING IS CRACKED IN (3) DIFFERENT LOCATIONS. WE OPERATE NUMEROUS OF THESE AC AND HAVE A LO NG HISTORY WITH 206 AIRCRAFT. WE HAVE SEEN CRACKS OF THIS NATURE BEFORE, BUT RARELY WITH SO LITTLE TIME IN SERVICE. (K ) 1 H 7 1 3O RT A4CE 2007121300280 20071213 00280 CE 2007 12 13 2007FA0001045 1 20071113 G 2420 E3FF10300AA ALTERNATOR CESSNA 210 P210N 2073454 CE CONT O520 TSIO520P 17040 SO FAILED D O OTHER O OTHER AP APPROACH 1 WP 27 4814K 10 P21000332 513626 DURING NIGHT IMC APPROACH, LOW VOLTAGE LIGHT ILLUMINATED AND BUS VOLTAGE DROPPED BELOW 24 VOLTS. PILOT RECYCLED ALTERNA TOR SWITCH BUT WAS UNABLE TO KEEP ALTERNATOR ON LINE. PILOT REDUCED LOADS AND SUCCESSFULLY EXECUTED APPROACH AND LANDED WITHOUT INCIDENT. CHARGING SYSTEM TROUBLESHOOT BY MECHANIC. FOUND LATERNATOR OUTPUT TO BE 26 VOLTS UNLOADED, AND WITH 50 PERCENT LOAD ON BUSS, LATERNATOR VOLTAGE WOULD DROP BELOW 24 VOLTS. NOTE: SECOND ALTERNATOR FAILURE IN 50 HOURS. ( K) 1 H 7 1 3O 3 O 3A21 E8CE 2007121300281 20071213 00281 CE 2007 12 13 2007FA0001046 1 20071110 G 2420 E3FF10300AA ALTERNATOR CESSNA 210 P210N 2073454 CE CONT O520 TSIO520P 17040 SO FAILED D O OTHER O OTHER CR CRUISE 1 WP 27 4814K 50 P21000332 513626 DURING DAY VMC FLIGHT, LOW VOLTAGE LIGHT ILLUMINATED AND BUS VOLTAGE DROPPED BELOW 24 VOLTS. PILOT MINIMIZED LOADS, DID A MANUAL GEAR EXTENSION, AND LANDED WITHOUT INCIDENT. CHARGING SYSTEM TROUBLESHOOT BY MECHANIC. FOUND ALTERNATOR OUTP UT TO BE 26 VOLTS UNLOADED, AND WITH 50 PERCENT LOAD ON BUS, ALTERNATOR VOLTAGE WOULD DROP BELOW 24 VOLTS. NOTE: ALTERN ATOR OVERHAULED. (K) 1 H 7 1 3O 3 O 3A21 E8CE 2007121300282 20071213 00282 CE 2007 12 13 2007FA0001047 1 20071107 G 2910 632701617 LINE CESSNA 525 525A 2076615 CE WILINT FJ44 FJ442A GL HYDRAULIC SYS SEPARATED B RO3R K NONE K FLUID LOSS IN INSP/MAINT 1 CE 03 361JR 525A0361 FOUND FLAP RETRACT LINE SEPARATED FROM BACK OF B-NUT. SYSTEM FLUID WAS LOST. SUSPECT DEFECT WAS AT TIME OF MANUFACTURE . (K) 1 L 7 1 4F 4 F RT A1WI E3GL 2007121300283 20071213 00283 CE 2007 12 13 2007FA0001048 1 20070911 G 3210 12116013 CASTING CESSNA 206 T206H 2073303 CE MLG CRACKED B RDDR O OTHER O OTHER NR NOT REPORTED 1 NM 11 1776 T20608105 AIRCRAFT OPERATED ON MOSTLY UNIMPROVED AIRSTRIPS. PART IS SAME AS 206F AND G MODELS. PART IN QUESTION WAS INSTALLED AT TIME OF MFG OF AIRPLANE. CASTING CRACKED AND FAILED UPON LANDING. AFT BOLT ALSO WAS CRACKED AND SHEARED. LANDING WAS A NORMAL APPROACH AND LANDING. GEAR LEG BROKE LOOSE FROM OB CASTING AND PUSHED BACKWARDS, PINCHING BRAKE LINE AND LOCK ING UP LT BRAKE. (K) 1 H 7 1 3O RT A4CE 2007121300273 20071213 00273 NE 2007 12 13 2007FA0001050 2 20071127 G 7261 ENGINE BEECH MU300 400BEECH CE PWA JT15 JT15D5 52112 NE NR 1 LEAKING E E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION DE DESCENT 1 SO 11 8HQ RJ50 100151 ON THE DECENT, THE CREW HAD AN OIL PRESSURE LOW LIGHT AT THAT TIME THE CREW OBSERVED THE OIL PRESSURE GAUGE WAS INDICATI NG LOW PRESSURE. THE CREW SHUTDOWN THE NR 1 ENGINE DECLARED AN EMERGENCY AND LANDED UNEVENTFULLY. UPON INSPECTION BY MAI NTENANCE IT WAS FOUND THAT THE OIL FILL CAP WAS NOT PROPERLY LATCHED DOWN AND THAT OIL HAD LEAKED OUT OVER THE COURSE OF THE FLIGHT. DO TO THE AMOUNT OF OIL MISSING FROM THE OIL TANK THE ENGINE IS BEING REMOVED FOR FURTHER INSPECTION. 2 H 7 2 4F 4 F RT A16SW E25EA 2007121300315 20071213 00315 SO 2007 12 13 2007FA0001051 1 20071130 G 3220 SPRING LUSCOM 8 8A 8190104 SO CONT A65 A65* 17003 SO TAIL WHEEL BROKEN G D RETURN TO BLOCK D INFLIGHT SEPARATION TO TAKEOFF 1 SO 09 2099K 2826 4826 6153488 ON TAKEOFF ROLL AND BEFORE ROTATION, THE TAILSKID SPRING ASSEMBLY BROKE AND THE TAIL WHEEL, CONNECTED TO THE FUSELAGE BY THE CONNECTOR SPRINGS, CAME TO REST ON TOP OF THE ELEVATOR AND WEDGED ITSELF AGAINST THE RUDDER, EFFECTIVELY JAMMING IT IN PLACE, CAUSING THE AIRCRAFT TO YAW 30 TO 40 DEGREES AND CREATED AN EXTREME SIDE SLIP NOT ALLOWING THE AIRCRAFT TO CL IMB. 1 H 7 1 3O 3 O A694 E205 2007121300320 20071213 00320 EU 2007 12 13 2007FA0001052 1 20071115 G 3250 STEERING SYS AMTR EVKTOR SPORTSTAR 0600012 EU ROTAX 912 ROTAX912ULS 55172 EU NLG SENSITIVITY D O OTHER O OTHER LD LANDING 1 NM 03 617EV 20071001 AFTER A NORMAL LANDING, CFI (WITH 80 HOURS IN TYPE) AND STUDENT (WITH 1.2 HOURS IN TYPE) LOST CONTROL OF THE AIRCRAFT, E XITED THE RUNWAY, AND CAME TO REST IN A DRAINAGE DITCH. THEY STATED THAT THE EXTREME SENSITIVITY OF THE NOSEWHEEL STEER ING LED TO PILOT INDUCED OSCILLATIONS THAT GREW PROGRESSIVELY WORSE UNTIL THE AIRPLANE WAS COMPLETELY UNCONTROLLABLE. T HE SENSITIVITY OF THE NOSEWHEEL STEERING IS A COMMON COMPLAINT, AND HAS BEEN CITED IN SEVERAL OTHER INCIDENTS. 1 L 7 1 3O 3 O NT EXPA1L71 EXPE3O 2007121300317 20071213 00317 SO 2007 12 13 2007FA0001053 2 20071130 G 8510 641909 LOCK PLATE CESSNA 421 421B 2076014 CE CONT O520 GTSIO520* 17032 SO CRANKSHAFT MISSING D H DEACTIVATE SYST/CIRCUITS J F WARNING INDICATION FLT CONT AFFECTED CR CRUISE 1 SO 15 707DT 65 65 HO13474 421B0468 218370R THIS ENGINE WAS REMOVED ON AUGUST 31, 2007, HOBBS TIME 1523.9 DUE TO CRACKED ENGINE CASE. THE ENGINE WAS SENT TO RAM AIR CRAFT FOR REPAIR. RAM REPAIRED THE ENGINE ON SEPT 20, 2007. THIS ENGINE WAS REINSTALLED BACK ON THE AIRCRAFT. DURING A N IGHT FLIGHT ON NOVEMBER 20, 2007 THE PILOT HAD AN ALTERNATOR FAILURE. HE REPORTED THE PROBLEM THE NEXT DAY. UPON INSPECT ION OF THE ALTERNATOR, IT WAS FOUND IN PIECES, WITH THE MOUNT HOUSING STILL ATTACHED TO THE ENGINE. THE INSIDE OF THE AL TERNATOR INSTALLATION HOLE WAS INSPECTED.THE INSPECTION REVEALED THAT THE ATTACH BOLTS ON THE ALTERNATOR FACE GEAR HAD N O TAB LOCK PLATES INSTALLED. THE ATTACH BOLTS CAME LOOSE AND DAMAGED THE ENGINE AND ALTERNATOR. RAM AIRCRAFT WAS NOTIFIE 1 L 7 2 3O 3 O A7CE E7CE 2007121300341 20071213 00341 SO 2007 12 13 2007FA0001054 2 20071121 G 8530 TISN712ACA CYLINDER HEAD BEECH 36 36BEECH 1151602 CE CONT O520 IO520BA 17032 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 1194A 785 E159 807201R CRACKED BEHIND INJECTOR BETWEEN FIRST AND THIRD FIN. SAME AS ALL THE OTHERS. THE (NEW) E-SERIES CYLINDER HEAD IS DEFEC TIVE. (K) 1 L 7 1 3O 3 O 3A15 E5CE 2007121300342 20071213 00342 SO 2007 12 13 2007FA0001055 2 20071121 G 8530 TISN712ACA CYLINDER HEAD BEECH 36 36BEECH 1151602 CE CONT O520 IO520BA 17032 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 1194A 901 E159 807201R CYLINDER HEAD CRACKED BEHIND INJECTOR BETWEEN FIN NR 1 AND 3. DEFECTIVE MFG PROCESS. (K) 1 L 7 1 3O 3 O 3A15 E5CE 2007121300343 20071213 00343 CE 2007 12 13 2007FA0001056 1 20071113 G 2450 CIRCUIT BREAKER CESSNA 172 172R 2072401 CE LYC O360 IO360A1A 41514 EA INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 NM 02 24442 251 17280862 PILOT SQUAWKED ON INTERMITTENT SWITCH. THE SWITCH WAS DISASSEMBLED AND INSPECTED. THE BONDED INTERNAL CONDUCTOR HAD SE PARATED FROM CONTACTOR. A TOTAL OF 20 SWITCHES IN OUR FLEET, HAVE ALREADY BEEN REPLACED. UPON INSPECTION, NUMEROUS SWI TCHES HAD SIMILAR PROBLEMS INTERNALLY. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2007121300346 20071213 00346 EA 2007 12 13 2007FA0001057 2 20071127 G 7414 06058002 BOOSTER PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA MAGNETO SHORTED D O OTHER O OTHER NR NOT REPORTED 1 WP 25 1473T 28R7235300 RL1904551A PILOT REPORTED ROUGH ENGINE; IGNITION SYSTEM TROUBLESHOOT FOUND START MAGNETO STARTER BOOSTER INTERNALLY SHORTED, GROUND ING MAGNETO P-LEAD CAUSING MAGNETO FAILURE. REMEDIED BY REMOVING START FROM AIRCRAFT AND MAGNETO OPERATING NORMALLY. ( K) 1 L 7 1 3O 3 O 2A13 1E10 2007121300364 20071213 00364 CE 2007 12 13 2007FA0001058 1 20071204 G 2497 CONNECTOR BEECH 100 A100 1152915 CE PWA PT6 PT6A60A 52043 NE ELECTRICAL ARCED B A UNSCHED LANDING B H SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC CL CLIMB 1 GL 07 23404 10027 B234 PARTIAL ELECTRICAL POWER LOSS TO COMPONENTS FROM RT NR 1 AND NR 2 SUBPANEL CIRCUIT BREAKERS. FOUND RT CIRCUIT PANEL CON NECTOR SOCKET MODULE AND SOCKET RT 1B BURNED. REPLACED MODULE (NR 8 WIRE-4 SOCKET) AND 4 SOCKETS. REPLACED PINS (4). FUNCTION CHECK SATISFACTORY. SUGGEST THESE HEAVY WIRE CONNECTIONS BE CHECKED MORE CLOSELY ON THE OLDER AIRCRAFT. THIS P ARTICULAR AIRCRAFT IS 30 YEARS OLD. 1 L 7 2 3T 4 T A14CE E4EA 2007121300327 20071213 00327 NM 2007 12 13 2007FA0001060 1 20071203 G 3060 SMR6201 STRAP COLUMB LC41 LC41550FG400 5150011 NM CONT O550 TSIO550C SO HARTZL HCC3Y HCC3YF1 GL PROPELLER DEICE DEBONDED D K NONE G MULTIPLE FAILURE IN INSP/MAINT 1 SW 07 969GM 266 41616 LX163B PROPELLER DEICE BOOT RETAINER STRAP DEBONDED OVER HALF OF THE BLADE CIRCUMFERENCE. OTHER (2) BLADES DEBONDED ABOUT .3. THIS STRAP HOLDS THE IB END OF THE DEICE BOOT AND TRIES TO KEEP THE LONG DEICE LEADS FROM PULLING UP THE BOOT. THE PRO P DEICE BOOT BEGINS TO COME LOOSE AFTER THE STRAP DEBONDS. THE RETAINER STRAPS NEED TY-RAPS TO HOLD THE LEADS, AS IS CO MMON PRACTICE ON OTHER PROPELLERS. 1 L 7 1 3O 3 O NT A00003SE E5SO 5 C P25EA 2007121400290 20071214 00290 EU 2007 12 14 2007FA0001061 1 20071203 G 2435 COMMUTATOR BFGOODRICH PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE STARTER GEN FAILED B B A EMER. DESCENT UNSCHED LANDING H E ELECT. POWER LOSS-50 PC VIBRATION/BUFFET CR CRUISE 1 CE 07 462PC 97102 462 PCEPR0336 DURING CRUISE FLIGHT, LOUD NOISE FROM ENGINE COMPARTMENT FOLLOWED BY VIBRATION AND LOSS OF PRIMARY ELECTRICAL POWER. UP ON INSPECTION, ONE SEGMENT FROM COMMUTATOR WAS MISSING AND AFT END OF GENERATOR AND BRUSHES HAD SUSTAINED HEAVY DAMAGE. AFTER REPLACEMENT WITH OVERHAULED UNIT, NO ABNORMALITIES WERE NOTED. 1 L 7 1 3T 4 T RT A78EU E26NE 2007121400335 20071214 00335 CE 2007 12 14 2007FA0001066 1 20071119 G 2751 100TA1966N4 TRANSMITTER BEECH MU300 400A 1155402 CE TE FLAPS INOPERATIVE B E81R K NONE N FALSE WARNING IN INSP/MAINT 1 GL 03 420CT RK517 TROUBLESHOT IN-FLIGHT (FLAP ASSYMETRY) ANNUNCIATOR INDICATION. FOUND RT FLAP POSITION TRANSMITTER RESISTANCE TO GO ABOV E SERVICE LIMITS WHEN COLD SOAKED. REPLACED RT FLAP POSITION TRANSMITTER AND ADJUSTED LT , RT FLAP FOLLOW-UP SWITCHES A ND POSITION TRANSMITTER RIGGING AS REQUIRED. VERIFIED FLAP SYSTEM RIGGING CABLE TENSIONS WITHIN SERVICE LIMITS. FLAP S YS FUNCTIONAL TESTS OK. SUGGEST MFG INVESTIGATE CURRENT PRODUCTION TRANSMITTER ASSY FOR QC OR MOISTURE INGRESS FAULTS. HBC PN 45AS86805-031, MFG DATE 8/07/2006. (K) 2 H 7 2 4F RT A16SW 2007121400337 20071214 00337 CE 2007 12 14 2007FA0001067 1 20071119 G 7830 64760 CONTROL VALVE BEECH MU300 400A 1155402 CE THRUST REVERSER MALFUNCTIONED B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 420CT RK517 TROUBLESHOT INOPERATIVE THRUST REVERSER DEPLOYMENT. FOUND LT, RT REVERSERS MECHANICALLY STIFF AND DIFFICULT TO OPERATE. THRUST REVERSER LINKS AND PIVOTS FOUND DRY, INITIAL 400 HR LUBRICATION NOT DUE FOR 55 HRS. LUBED REVERSERS IAW MM. 1 2-20-00, VERIFIED OPERATIONS OK. FOUND LT REVERSER NOT DEPLOYING UNTIL AFTER RT DEPLOYED. REPLACED LT CONTROL VALVE, O PERATIONAL CHECKS NORMAL. SUGGEST ALL THRUST REVERSER LUBES BE COMPLIED WITH AT 200 HR INITIAL INSPECTION. SUGGEST MFG INVESTIGATE CNTRL VALVE FOR POSSIBLE QUALITY CONTROL OR SYSTEM CONTAMINATION ISSUES. (K) 2 H 7 2 4F RT A16SW 2007121400339 20071214 00339 CE 2007 12 14 2007FA0001068 1 20071111 G 2730 MS250836BB5 BONDING JUMPER BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE ELEVATOR FRAYED B E81R O OTHER O OTHER IN INSP/MAINT 1 GL 03 400MV 1596 RK286 TROUBLESHOT REPORT OF HORIZONTAL STABILIZER ANTI-ICE SYSTEM FAIL INDICATION. NOTED ELEVATOR HORN HEAT SYSTEM RESISTANCE READINGS ERRATIC WHEN ELEVATORS MOVED. FOUND ELEVATOR BONDING JUMPERS FRAYED AND CORRODED. REPLACED ELEVATOR BONDING JUMPERS, ELEVATOR HORN HEATER RESISTANCE READINGS NOW WITHIN SERVICE LIMITS. HORIZONTAL STABILIZER ANTI-ICE SYSTEM TEST S IAW MM 30-12-00 NORMAL, NO FAULTS INDICATED. RECOMMEND TECH/INSP NOTE CONDITION OF ELEVATOR BONDING JUMPERS CLOSELY D URING SCHEDULED INSPECTIONS AND REPLACE JUMPERS WHEN DETERIORATION EVIDENT. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007121400341 20071214 00341 NE 2007 12 14 2007FA0001069 2 20071111 G 7230 PIPE BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE GAS GENERATOR CRACKED B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 400MV A000*LNX RK286 PERFORMED HOT SECTION INSPECTION PRIOR TO SCHEDULED 1800 HR INTERVAL TO INVESTIGATE COMPLAINT OF SLOW STARTING. UPON DI SASSEMBLY, FOUND DIFFUSER PIPES OF GAS GENERATOR CASE CRACKED AND PORTIONS MISSING AT APPROXIMATE 10:30, 11:00 POSITION. SUSPECT CAUSED BY STREAKING FUEL NOZZLES WITH COKED-UP TIPS FROM LOW IDLE OPERATION WITH EFC OFF. PILOTS AND TECH SHO ULD BE AWARE OF MONITORING ENGINE RPM DURING TAXING OPERATIONS WITH EFC TURNED-OFF. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2007121400349 20071214 00349 CE 2007 12 14 2007FA0001070 1 20071201 G 2420 AC2101 CONTROL UNIT CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL ALTERNATOR FAILED C K NONE O OTHER IN INSP/MAINT 1 WP 25 2472J 215 172S10072 L3240751E ZK23029 THE AIRCRAFT FACTORY INSTALLED ACU BEGAN FAILING AT 200 HOURS (INTERMITTENT ALTERNATOR DROPPING (OFF LINE) FOR A FEW SEC ONDS) (ON ONE OCCASION, THE FIELD CB DISENGAGED) A NEW ACU WAS INSTALLED AT 215.9. AT 246.1 THE SAME PROBLEM SURFACED, AND THE THIRD ACU WAS INSTALLED. THE SERVICE CENTER HAS HAD THE SAME PROBLEM WITH OTHER AC. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2008010800347 20080108 00347 CE 2008 1 8 2007FA0001072 1 20071208 G 2751 WARNING SYSTEM CESSNA 310 310K 2074228 CE T/E FLAP MALFUNCTIONED E A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 SO 11 418GJ 310K0067 AC EXPERIENCED FLAP ASYMMETRIC LIGHT IN CRUISE FLIGHT CREW DIVERTED TO ATL LIGHT WENT OUT AND FLAPS WORKED PROPERLY FOR AN UNEVENTFUL LANDING. PROBLEM COULD NOT BE DUPLICATED SO BOTH FLAP FOLLOW UPS WERE REPLACED IAW THE MM. AIRCRAFT OPS CH ECK GOOD. 1 L 7 2 3O 3A10 2008010800350 20080108 00350 SO 2008 1 8 2007FA0001073 1 20071211 G 3211 67042013 TRUNNION PIPER PA44 PA44180 7104402 SO RT MLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 WP 07 570ER 4145 4496146 RT AFT MAIN TRUNNION CASTING, P/N 67042-013, FOUND TO BE CRACKED DURING INSPECTION. THIS IS A NEARLY IDENTICAL CRACK TO ONE FOUND AUGUST 2006 ON A SISTER SHIP. 1 L 7 2 3O A19S0 2007121400344 20071214 00344 SO 2007 12 14 2007FA0001074 1 20071130 G 2720 CONTROL SYSTEM PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360* 17025 SO RUDDER SEIZED C K NONE O OTHER IN INSP/MAINT 1 SO 11 557C 3449247 WITH FULL RT RUDDER TRIM, RT RUDDER FOR HARD CLIMBING RT TURN, RUDDER FROZE WITH FULL RT DEFLECTION. RUDDER CABLE TURNB UCKLE IN TAIL SECTION WAS (CAUGHT) UNDER BULKHEAD TOP EDGE CAUSING RUDDER TO FREEZE IN FULL RT DEFLECTION - DESPITE SIGN IFICANT LT RUDDER PRESSURE. 1 L 7 2 3O 3 O A7SO E9CE 2008010800356 20080108 00356 CE 2008 1 8 2007FA0001075 1 20071212 G 2730 053200135 ADAPTER CESSNA 172 172E 2072412 CE CONT O300 O300* 17022 SO LT ELEVATOR WORN G K NONE O OTHER IN INSP/MAINT 1 NM 07 3901S 6491 17251101 LT ELEVATOR TORQUE TUBE ARM ADAPTER RIVET HOLES WERE WORN POSSIBLY DUE TO UNSECURED CONTROLS IN GUSTY WINDS. 1 H 7 1 3O 3 O NT 3A12 E253 2008010800371 20080108 00371 2008 1 8 2007FA0001076 2 20071215 G 7414 10357586 DISTRIBUTOR GEAR CONT MAGNETO LOOSE D K NONE O OTHER IN INSP/MAINT 1 SO 15 500 500 500-HOUR INSPECTION PERFORMED ON BOTH MAGNETOS REMOVED FROM. FOUND AXLE CRIMPED WASHER LOOSE ON SHAFT AND WORN TO THE PO INT OF FALLING OFF GEAR. THIS IS THE SECOND TIME THIS CONDITION HAS BEEN FOUND ON MAGNETOS USING THIS GEAR. TTS NEW 500 AND 580. 2008010800372 20080108 00372 2008 1 8 2007FA0001077 2 20071215 G 7414 10357586 DISTRIBUTOR GEAR CONT MAGNETO LOOSE D K NONE O OTHER IN INSP/MAINT 1 SO 15 500 500 500-HOUR INSPECTION PERFORMED ON BOTH MAGNETOS REMOVED. FOUND AXLE CRIMPED WASHER LOOSE ON SHAFT AND WORN TO THE POINT O F FALLING OFF GEAR. THIS IS THE SECOND TIME THIS CONDITION HAS BEEN FOUND ON MAGNETOS USING THIS GEAR. TTSNEW 500 AND 58 0. 2008010800367 20080108 00367 EU 2008 1 8 2007FA0001078 1 20071214 G 3230 PNDIN47108VE RETAINING CLIP DIAMON DIAMON DA42 DA42 2990004 EU LT MLG MISSING B K NONE O OTHER IN INSP/MAINT 1 SO 15 904ER 100 2 42281 DURING PREFLIGHT THE PILOT NOTICED THAT THE LMG DOWNLOCK PIN (P/N-D60-3237-11-34) HAD NO RETAINING CLIP(P/N-DIN471-08-VE RZ) AND HAD SHIFTED AFT. THE FORWARD DOWNLOCK HOOK WAS COVERING ONE HALF OF THE HOLE SINCE THERE WAS NO PIN TO STOP ITS MOVEMENT. THE REMAINING CLIP BROKE IN HALF WHEN IT WAS REMOVED. IT APPEARED TO BE BRITTLE. A NEW PIN WAS INSTALLED WITH NEW CLIPS. THOSE CLIPS HAD MORE SPRING TO THEM. ALSO, THE GROOVES IN THE PIN ARE VERY SHALLOW. 1 L 7 2 3I RT A57CE 2008010800368 20080108 00368 EU 2008 1 8 2007FA0001079 1 20071214 G 3230 PNDIN47108VE RETAINING CLIP DIAMON DIAMON DA42 DA42 2990004 EU LT MLG MISSING B K NONE O OTHER IN INSP/MAINT 1 SO 15 904ER 100 2 42281 DURING PREFLIGHT THE PILOT NOTICED THAT THE LMG DOWNLOCK PIN (P/N-D60-3237-11-34) HAD NO RETAINING CLIP(P/N-DIN471-08-VE RZ) AND HAD SHIFTED AFT. THE FORWARD DOWNLOCK HOOK WAS COVERING ONE HALF OF THE HOLE SINCE THERE WAS NO PIN TO STOP ITS MOVEMENT. THE REMAINING CLIP BROKE IN HALF WHEN IT WAS REMOVED. IT APPEARED TO BE BRITTLE. A NEW PIN WAS INSTALLED WITH NEW CLIPS. THOSE CLIPS HAD MORE SPRING TO THEM. ALSO, THE GROOVES IN THE PIN ARE VERY SHALLOW. 1 L 7 2 3I RT A57CE 2008010800385 20080108 00385 SO 2008 1 8 2007FA0001080 1 20071115 G 3213 653319004 CYLINDER PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA RT MLG FAILED D K NONE O OTHER TX TAXI/GRND HDL 1 SW 17 8218Z 11743 288090320 RT M/G CYLINDER FAILED AT THE UPPER TORQUE LINK ATTACH LUGS WHILE TAXIING FROM THE ACTIVE RUNWAY: THE AIRCRAFT (SINCE N EW) IS USED FOR FLIGHT TRAINING IN A 141 FLIGHT SCHOOL. THE PREMATURE FAILURE OF THE CYLINDER WAS PROBABLY CAUSED BY A HARD LANDING. (K) 1 L 7 1 3O 3 O 2A13 E286 2008010800387 20080108 00387 WP 2008 1 8 2007FA0001081 1 20070926 G 7921 20006A OIL COOLER ROBSIN R22 R22ALPHA 7640104 WP LYC O320 O320B2C 41508 EA CRACKED D A UNSCHED LANDING K FLUID LOSS NR NOT REPORTED 1 EA 11 97CP 0421 L1414339A AT A 100 HR INSPECTION ON HELICOPTER, INSTALLED A NEW OIL COOLER REPLACING THE ORIGINAL OIL COOLER. (NOVEMBER 5, 2007, HOUR METER 1042) WHILE FLYING, NOTICED THE OIL TEMPERATURE RISING AND THE OIL PRESSURE DROPPING. MADE AN UNSCHECULED LA NDING AND DISCOVERED THE TAILBOOM COVER WITH ENGINE OIL. TRACED THE OIL BACK TO THE OIL COOLER, REMOVED OIL COOLER AND PRESSURE TESTED IT AND FOUND A .7500 INCH CRACK IN THE COOLER CORE. (TT 16.8 HOURS) (K) 1 G 7 1 3O 3 O H10WE E274 2008010800388 20080108 00388 CE 2008 1 8 2007FA0001082 1 20070926 G 5320 BRACKET CESSNA 441 441 2076020 CE GARRTT TPE331 TPE331* 01514 WP CRACKED D OF1R K NONE O OTHER IN INSP/MAINT 1 EA 17 731BH 4410360 FOUND BROKEN T-BRACKET DURING ROUTINE 2, 3, D INSPECTION. (K) 1 L 7 2 3T 3 T RT A28CE E2WE 2008010800389 20080108 00389 CE 2008 1 8 2007FA0001083 1 20070927 G 5350 581201412 TAIL CONE CESSNA 441 441 2076020 CE GARRTT TPE331 TPE331* 01514 WP CRACKED D OF1R K NONE O OTHER IN INSP/MAINT 1 EA 17 731BH 7779 4410360 FOUND CRACK DURING ROUTINE 2,3,D PHASE INSPECTION. (K) 1 L 7 2 3T 3 T RT A28CE E2WE 2008010800393 20080108 00393 CE 2008 1 8 2007FA0001084 1 20071109 G 5753 3516505084 NOSE RIB BEECH 95 B95 1153404 CE LYC O360 O360A1A 41514 EA T/E FLAP CRACKED B OF1R K NONE O OTHER CR CRUISE 1 EA 17 9349Y 4288 TD445 L421536 IN-FLIGHT, PILOT LOWERED FLAPS AND AIRCRAFT STARTED TO ROLL TO THE RT. PILOT NOTICED RT FLAP WAS RETRACTED, HE THEN RET RACTED FLAP HANDLE. AIRCRAFT LANDED SAFELY, WITHOUT INCIDENT. UPON INSPECTION, FOUND RT FLAP ROD ATTACH BRACKET BROKEN AND FLAP NOSE RIB NUTPLATE FLANGE TORN. INSPECTED LT SIDE AND FOUND NOSE RIB FLANGE AND WEB CRACKED. (K) 1 L 7 2 3O 3 O 3A16 E286 2008010900387 20080109 00387 CE 2008 1 9 2007FA0001085 1 20071109 G 5753 3516505084 NOSE RIB BEECH 55 D55 1152730 CE CONT O520 IO520C 17032 SO T/E FLAP CRACKED B OF1R K NONE O OTHER IN INSP/MAINT 1 EA 17 810WA 4552 TE486 267930R AT ANNUAL INSPECTION, FOUND CRACKED FLAP ROD ATTACH POINT RIB. RT FLAP ONLY. (K) 1 L 7 2 3O 3 O 3A16 E5CE 2008010900388 20080109 00388 CE 2008 1 9 2007FA0001086 1 20071109 G 5753 3516505084 NOSE RIB BEECH 36 A36 1151604 CE CONT O550 IO550B SO T/E FLAP CRACKED B OF1R K NONE O OTHER IN INSP/MAINT 1 EA 17 20TC 3144 E873 281740R AT ANNUAL INSPECTION FOUND BOTH LT AND RT FLAP ATTACH POINT RIBS CRACKED. (K) 1 L 7 1 3O 3 O 3A15 E3SO 2008010900389 20080109 00389 CE 2008 1 9 2007FA0001087 1 20071109 G 5753 3516505084 RIB BEECH BEECH 35 V35B 1151548 CE CONT O520 IO520BA 17032 SO T/E FLAP CRACKED B OF1R K NONE O OTHER IN INSP/MAINT 1 EA 17 4475S 4248 D9775 280904R AT ANNUAL INSPECTION FOUND RT FLAP ROD ATTACH POINT RIB CRACKED. (K) 1 L 7 1 3O 3 O 3A15 E5CE 2008010900390 20080109 00390 CE 2008 1 9 2007FA0001088 1 20071109 G 5753 3516505084 RIB BEECH BEECH 95 95B55 1152729 CE CONT O520 IO520E 17032 SO T/E FLAP CRACKED B OF1R K NONE O OTHER IN INSP/MAINT 1 EA 17 127RW 4421 TC1958 215825R AT ANNUAL INSPECTION FOUND CRACK ON FLAP RIB. (FLAP ROD ATTACH POINT) BOTH LT AND RT FLAPS. (K) 1 L 7 2 3O 3 O RT 3A16 E5CE 2008010900391 20080109 00391 CE 2008 1 9 2007FA0001089 1 20071109 G 5753 3516505084 RIB BEECH BEECH 33 F33A 1151425 CE CONT O550 IO550B SO T/E FLAP CRACKED B OF1R K NONE O OTHER IN INSP/MAINT 1 EA 17 89AU 5255 CE1129 675607 AT ANNUAL INSPECTION, FOUND RT FLAP ROD ATTACH POINT RIB CRACKED. (K) 1 L 7 1 3O 3 O 3A15 E3SO 2008011000024 20080110 00024 GL 2008 1 10 2007FA0001090 1 20071126 G 7160 CONTROL ARM DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA AIRBOX BROKEN C GO3S K NONE O OTHER IN INSP/MAINT 1 NM 07 423FP 28 40FC023 CARBURETOR HEAT CONTROL ARM BROKEN OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INT AKE. RECOMMEND INSTALLED THICKER MATERIAL ON CARB HEAT CONTROL ARM LEVER. DIFFERENT WELDING PROCESS, OR DIFFERENT ATTA CHMENT PROVISION ALTOGETHER. (K) 1 L 7 1 3O 3 O NT A47CE E286 2008011000131 20080110 00131 NM 2008 1 10 2007FA0001091 1 20070525 G 2761 252T13021 MANIFOLD BOEING 767 767* NM SPOILERS FRACTURED D K NONE O OTHER IN INSP/MAINT 1 WP 01 MANIFOLD CRACKED IN THE FILTER BOWL AS DESCRIBED IN BETWEEN WHAT IS DESCRIBED IN THE SERVICE LETTER AND THIS UNIT FRACTU RED COMPLETELY. VISUAL INSPECTION APPEARS TO SHOW THAT THE CRACK ORIGINATED IN THE THREAD ROOT AT THE THINNEST AREA OF THE HOUSING. THE CRACK PROPAGATED UNTIL THERE WAS DUCTILE OVERLOAD FAILURE OF THE HOUSING. (K) 2 L 7 2 4F RT A1NM 2008011100005 20080111 00005 SO 2008 1 11 2007FA0001092 1 20071130 G 2530 243185502 OVEN GULSTM GVSP GVSPG550 3980203 SO RROYCE BR700 BR700710A110 NE GALLEY FAILED B K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 EA 11 607PM 105 5146 FLIGHT CREW REPORTED THE ODOR OF ELECTRICAL SMOKE IN THE GALLEY. THE ODOR WAS COMING FROM THE OVEN, THEN THE OVEN CB OP ENED (POP). THE OVEN WAS REMOVED AND REPLACED WITH A NEW UNIT. (K) 2 L 7 2 4F 4 F RT A12EA E00057EN 2008011100008 20080111 00008 EA 2008 1 11 2007FA0001094 1 20071211 G 2520 SEAT BACK DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA SEAT BROKEN B SCIR K NONE O OTHER IN INSP/MAINT 1 NM 07 252SA 1691 614 PCE50502 BOTH LOWER SEAT BACK BRACES BROKE JUST ABOVE THE WELDS, ABOVE WHERE THE FLANGE BOLTS ON TO THE SEAT BOTTOM. (K) 1 H 7 2 3T 4 T RT A9EA E4EA 2008010900393 20080109 00393 2008 1 9 2007FA0001095 4 20071218 G 3160 70000006003 DISPLAY PIPER PA46 PA46500TP 7104622 SO GARRTT TPE331 TPE33111U 01514 WP COCKPIT MISREPAIRED B K NONE O OTHER IN INSP/MAINT 1 CE 03 3110T 318 4697221 WE SENT IN BOTH AIRCRAFT PFD'S FOR REPAIR AND SB COMPLIANCE. BOTH UNITS WERE REPAIRED AND REINSTALLED. WE TRIED TO CAL IBRATE THE ADHRS AND THE PILOT PFD CONTINUED TO GIVE AN ERROR. WE SPOKE WITH ANOTHER SHOP AND WERE TOLD THEY HAVE HAD T HE SAME PROBLEM. IN FACT, WE WERE TOLD THEY NORMALLY HAVE PROBLEMS WITH REPAIRED UNITS (ABOUT 50 PERCENT OF THE TIME). 1 L 7 1 3O 4 T RT A25SO E4WE 2008011100010 20080111 00010 EU 2008 1 11 2007FA0001096 1 20071121 G 7120 80446101403 MOUNT PIAGIO P180 P180 6960204 EU PWA PT6 PT6* 52043 EA ENGINE CHAFED D O OTHER O OTHER NR NOT REPORTED 1 GL 23 180AV 6059 1018 OIL COOLER RETURN LINE CHAFED AGAINST ENGINE MOUNT. DID NOT SHOW SIGNS OF CHAFING STATICALLY DURING ROUTINE INSPECTIONS, WAS CHAFING DURING FLIGHT. INSTALLED REDESIGNED OIL LINE THAT CANNOT COME IN CONTACT WITH MOUNT. MFG DID NOT INFORM OP ERATORS ABOUT REDESIGNED OIL LINE, P/N MS8000M300JF, SAID USE AS SPARE IN ILLUSTRATED PARTS CATALOG. ALSO INSTALLED NEW ENGINE MOUNT. 1 H 7 2 3O 3 T RT A59EU E2NE 2008011100056 20080111 00056 CE 2008 1 11 2007FA0001097 1 20071212 G 5720 509800913 BUMPER BLOCK BEECH 90 C90A 1152911 CE PWA PT6 PT6* 52043 EA RT MLG UNBONDED B EHHR K NONE O OTHER IN INSP/MAINT 1 EA 17 266RD 1628 LJ1633 COMMUNIQUE NR 2000-04 ANNOUNCED THAT STARTING LJ-1088 AND AFTER THAT LANDING GEAR BUMPER BLOCK WILL BE BONDED TO THE MAI N SPAR WHERE IT CROSSES INSIDE THE LANDING GEAR WHEEL WELLS. THIS AC FOUND THE RT LANDING GEAR BUMPER BLOCK ON THE FLOO R OF HIS HANGER. NOT KNOWING WHAT THIS PART WAS THE OWNER ALMOST THREW IT IN THE TRASH. LUCKILY HE KEPT IT FOR AT OUR NEXT PHASE INSPECTION, WE FOUND THAT IT WAS MISSING AND TOLD THE OWNER, WHO REMEMBER STORING THIS UNKNOWN PART IN A LOCK ER AT THIS HANGER. CLEANED THE AREA AND ATTACHED THE BUMPER BY APPLYING THE EC2216 EPOXY IAW THE COMMUNIQUE. THIS BLOC K ON EARLIER AC WERE BOLTED ONTO THE SPAR. THIS METHOD WAS MOST LIKELY DISCONTINUED BECAUSE ELIMINATION OF APPLYING EXT 1 L 7 2 3T 3 T RT 3A20 E2NE 2008011100015 20080111 00015 SW 2008 1 11 2007FA0001098 1 20071219 G 6710 ATTACH FITTING BELL 412 412 1182202 SW PWA PT6 PT6* 52043 EA CYCLIC STICK GOUGED B K NONE O OTHER IN INSP/MAINT 1 SO 19 107X 19997 33113 DURING INSPECTION FOR BHT ASB-412-07-127 (CYCLIC STICK BEARING INSPECTION) IT WAS FOUND THAT THE LATERAL CONTROL TUBE PN 412-001-307-101 FIXED (OB) CLEVIS PN 212-001-059-001 OR -103 HAD GOUGED THE CYCLIC LEVER ASSEMBLY BEYOND REPAIRABLE LIM ITS AND THE BEARING GREASE SEAL RETAINER WAS DISLODGED. THIS DAMAGE WAS CAUSED BY ANGULAR MISSALIGNMENT OF THE FIXED CL EVIS WITH RELATION TO THE ADJUSTABLE (IB) CLEVIS. IT WAS ALSO NOTED THAT BOTH CLEVIS'S WERE A DIFFERENT DESIGN THAN THE OTHER CLEVIS'S INSTALLED ON THE CYCLIC OF THIS AND OTHER 412 AIRCRAFT AVAILIABLE FOR INSPECTION. THIS DESIGN WAS A STR AIGHT (TUNNING FORK) DESIGN AS APPOSED TO THE OTHER CLEVIS DESIGN WITH AN ELONGATED (C) SHAPE WHICH ALLOWED FOR MORE CLE 1 G 7 2 4U 3 T H4SW E2NE 2008011100052 20080111 00052 SO 2008 1 11 2007FA0001103 1 20071220 G 5200 99271000 BRACKET PIPER PA32 PA32R301 7103218 SO ACCONDENSOR DOOR CORRODED D O OTHER O OTHER CR CRUISE 1 SO 19 9087V 3700 32R8613005 AIR CONDITIONING CONDENSOR DOOR P/N 99271-000 FAILED IN FLIGHT WHILE DEPLOYED. THE SMALL EXTRUDED ANGLE BRACKET ON THE R T SIDE OF DOOR WHERE THE BEARING ASSY P/N 99561-000 CONNECTS TO THE DOOR CORRODED WHERE THE TWO MEET. THIS CONDITION IS IMPOSSIBLE TO INSPECT UNLESS THE MECHANIC DROPS THE CONDENSOR DOOR DOWN. THE LT SIDE WAS IN PERFECT CONDITION. THE MAIN CAUSE OF THE CORROSION IS THE FACT THAT THAT THE ENGINE EXHAUST TRAVELS DOWN THE RT SIDE OF THE BOTTOM OF THE AIRCRAFT. THIS PORTION OF THESE LOW WING PIPERS ALWAYS SHOW MORE SURFACE CORROSION ON THE RT SIDE OF THE BELLY. 1 L 7 1 3O A3SO 2008011100012 20080111 00012 NM 2008 1 11 2007FA0001104 1 20071219 G 5330 SKIN UNIVAR 415 415C 0420302 NM FUSELAGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 03 31140 3143 IAW AD2002-26-02,- CORROSION FROM WATER, DIRT AND ACID FROM BATTERY ATE THROUGH BOTTOM SKINS 415-13058-1,415-13047L AND R, RIBS 415-13016L AND R AND BOTTOMS OF SERVICE ASSEMBLY NR 5. AIRCRAFT HAD SAT SINCE 1977. 1 L 7 1 3O A718 2008011100101 20080111 00101 GL 2008 1 11 2007FA0001106 1 20071222 G 2497 WIRE HARNESS CIRRUS SR SR22 2130001 GL CONT O550 IO550* SO ALTERNATOR DAMAGED D A UNSCHED LANDING P NO WARNING INDICATION CR CRUISE 1 SO 15 1501C 1 0528 ALTERNATOR FAILED ON FIRST FLIGHT AFTER INSTALLATION FROM OVERHAUL. FOUND FIELD WIRE RIPPED OUT OF FIELD BRUSH AND BARE WIRE DEBRIS INSIDE ALTERNATOR CASE. SUSPECT WIRE EPOXY HOLD DOWN VIBRATED LOOSE ALLOWING ROTOR ASSEMBLY TO SNAG WIRE. 1 L 7 1 3O 3 O NT A00009CH E3SO 2008011100145 20080111 00145 NE 2008 1 11 2007FA0001107 2 20071129 G 7250 TURBINE BLADES RROYCE RB211 RB211TRENT89 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 EA 35 61160 DURING INSPECTION, A CRACKED FIRTREE POST HAS BEEN HIGHLIGHTED. THE DISC HAS BEEN SCRAPPED OFF AND THIS ISSUE HAS BEEN FORWARDED TO MFG. THE DISC HAS BEEN SENT TO LAB FOR ANALYSIS. REF NR: MEM5 D070133. (K) 4 F E00050EN 2008011100146 20080111 00146 NE 2008 1 11 2007FA0001108 2 20071029 G 7200 BEARING RROYCE RB211 RB211535E4 54555 NE ENGINE DAMAGED W DR5Y K NONE O OTHER IN INSP/MAINT 1 EA 35 31141 DAMAGE FOUND ON STRIP. HP AND IP SHAFTS SEIZED, HP/IP BEARING DAMAGED, ALSO LP VISIBLE COUPLINGS AND SEAL ARM. DESIGN ORGANIZATION AND UK CAA HAVE BEE NOTIFIED. THE ENGINE WAS BEING OPERATED BY AA AT TIME OF IN-FLIGHT SHUTDOWN. THE ENGI NE WAS RECEIVED IN OCTOBER, 2007 FOR REPAIR. (MEMS D070108) (K) 4 F E12EU 2008011100153 20080111 00153 NM 2008 1 11 2007FA0001109 1 20071224 G 5320 SB727570112 BRACKET BOEING 727 727233 138408A NM BS 760 CRACKED B EB1R K NONE O OTHER IN INSP/MAINT 1 SO 11 CGXFA 20938 RT PREVENTATIVE MODIFICATION FWD IB ANGLE CRACKED AT BS 760.95. REPAIRED CRACK AT RT BL 70.5, BS 760.95, UPPER AND LOW ER MOST FORWARD HOLES. OVERSIZED CRACKED HOLE IAW 57-112. NDT PERFORMED TO CONFIRM CRACK TERMINATION. COMPLIED WITH TE RMINATION REPAIR IAW SB 727-57-0112. REMOVED RT PREVENTATIVE MODIFICATION FWD IB ANGLE BRACKET. (K) 2 L 7 3 4F RT A3WE 2008011100143 20080111 00143 EA 2008 1 11 2007FA0001110 1 20071227 G 5522 16920 SKIN FRCHLD FH227 FH227D 3373050 EA ELEVATOR CRACKED M K NONE O OTHER IN INSP/MAINT 1 SW 17 A SMALL CRACK WAS FOUND UNDERNEATH ELEVATOR STATIC WICK BASES APPROX. BL 84.0 ON BOTH LTAND RT ELEVATOR CONTROL SURFACES . A SECOND AIRCRAFT IN THE FLEET REVEALED A SIMILIAR CRACK UNDERNEATH THE STATIC BASE ON THE RT ELEVATOR ONLY. SUSPECT THE CRACK WAS CAUSED BY VIBRATION ON STATIC WICK IN THE SLIPSTREAM OF THE ENGINES. REPAIRED IAW SRM 51-90-04 REPAIR SCHE ME NR 6. 2 H 7 2 4T 7A1 2008011100201 20080111 00201 SO 2008 1 11 2007FA0001111 2 20071217 G 8520 SA6419311075 THRU BOLT CONT O520 IO520C 17032 SO CRANKCASE BROKEN B VI4R K NONE O OTHER IN INSP/MAINT 1 SO 15 17256H INSTALLING ALL NEW SA641931-10.75 LOT NR K070059179, REV E THRU BOLTS IN ENGINE. AFTER TORQUE, WITHIN A FEW HOURS THE T HRU BOLT SNAPPED, AT THE OIL RING GROOVE. THIS IS THE THIRD THRU BOLT THAT HAS SNAPPED AFTER TORQUE, AND SETTING. PROB ABLE CAUSE, IS IMPROPER HEAT TREATING DURING OR AFTER PLATING. (K) 3 O E5CE 2008011100202 20080111 00202 CE 2008 1 11 2007FA0001112 1 20071130 G 2400 727755 CIRCUIT BREAKER CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FAILED B D0FR K NONE O OTHER IN INSP/MAINT 1 SW 05 18728 1489 172S9929 CIRCUIT BREAKER WILL RESET AFTER BEING TRIPPED BY ROTATING THE KNOB. THIS RESULTS IN A BREAKER THAT IS RESET WHILE BEIN G IN THE TRIPPED POSITION. THIS BREAKER WILL PRODUCE THIS RESULT EVERY TIME THAT THIS PROCEDURE IS TRIED. THIS PARTICUL AR BREAKER WAS INSTALLED IN THE AUTOPILOT SYSTEM. THE CIRCUIT BREAKER IN QUESTION IS ATTACHED. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2008011100203 20080111 00203 SO 2008 1 11 2007FA0001113 1 20071214 G 1400 EWD0420839 BOLT EMB 145 EMB145LR 3260212 SO ALLSN AE300 AE3007A GL BEARING CAP BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 21 673AE 145797 NEW BOLT BROKEN DURING TORQUE. TORQUE VALUE NEVER OBTAINED BEFORE THE BOLT BROKE. THIS BOLT HOLDS THE BEARING CAP IN P LACE THAT HOLDS THE MAIN LANDING GEAR ON THE AIRCRAFT. (K) 2 L 7 2 4T 4 F RT T00011AT TE6CH 2007032600145 20070326 00145 CE 2007 3 26 2007FA0313001 1 20070313 G 5210 55123515 HINGE CESSNA CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE PAX DOOR CRACKED B O OTHER O OTHER TX TAXI/GRND HDL 1 SW 13 6763L 6986 5500673 DESCRIPTION AMENDED TO SAY THAT THE LOWER LUG WAS CRACKED INSTEAD OF THE UPPER LUG. 1 L 7 2 4F 4 F A22CE E1NE 2007032200066 20070322 00066 2007 3 22 2007FA032201 4 20070308 G 2200 6226717104 SERVO BEECH MU300 400A 1155402 CE ELEVATOR CONTROL MALFUNCTIONED E O OTHER F FLT CONT AFFECTED DE DESCENT 1 WP 05 188JF 351 RK446 DIFFICULTY OCCURRED UPON DESCENT. PILOT DISENGAGED AUTO-PILOT AND FELT RESISTANCE IN THE ELEVATOR CONTROL SYSTEM. ON I NSPECTION OF THE SYSTEM THE AUTO-PILOT ACTUATOR WAS FOUND PARTIALLY ENGAGED. UNIT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THIS AIRCRAFT WAS LAST INSPECTED ON 11/28/2006 AT 218HR. 2 H 7 2 4F RT A16SW 2007041100001 20070411 00001 SO 2007 4 11 2007FA041101 1 20070407 G 7160 AIR BOX PIPER PA18 PA18105SPEC 7101808 SO LYC O360 O360* 41514 EA CARBURETOR FAILED P O OTHER O OTHER NR NOT REPORTED 1 SO 11 8326 96 7 182341 CARBURATOR AIR BOX AIR FILTER RETAINING SHAFT SHEARED ADJACENT TO FISH MOUNTH WELD AT FORWARD EDGE OF HORIZONTAL PLATE ( APPROXIMATELY 1/3 SHAFT LENGTH FROM BASE). AIR FILTER DOME, SHAFT AND RETAINING NUT APPEARANTLY DEPARTED AIRPLANE IN FL IGHT. AIR FILTER WAS FOUND LOOSE IN COWL AIR SCOOP AFTER LANDING. NO OPERATIONAL INDICATIONS AND NO DAMAGE TO PROPELLER , COWL, FUSELAGE OR LANDING GEAR. AIRPLANE COMPLETELY REBUILT 2004. NEW K & N AIR FILTER INSTALLED AT ANNUAL INSPECTION NOVEMBER 2006. PHOTOS AVAILABLE. 1 H 7 1 3O 3 O 1A2 E286 2007032300001 20070323 00001 SW 2007 3 23 2007FA0703221 1 20070322 G 3234 5059 HANDLE MOONEY M20 M20A 5870204 SW LYC O360 O360* 41514 EA MLG BROKEN G O OTHER O OTHER AP APPROACH 1 SW 17 1068B 1295 GEAR HANDLE (MECHANICAL RETRACTION HANDLE) BROKE OFF IN THE PILOT'S HAND DURING GEAR EXTENSION ON LANDING APPROACH. THE LANDING GEAR DISENGAGED BUT IT DID NOT EXTEND FULLY. THE BREAK WAS JUST BELOW THE WELD. 1 L 7 1 3O 3 O 2A3 E286 2007102300153 20071023 00153 CE 2007 10 23 2007FA1015001 1 20071015 G 2435 MHB6016 STARTER GEN CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA ENGINE MAKING METAL D K NONE O OTHER IN INSP/MAINT 1 NM 03 52298 376 17274489 L1342739A STARTER BENDIX DRIVE HAS NOT BEEN FULLY RETRACTING AFTER ENGINE START AND HAS BEEN SCRAPING THE ENGINE STARTER RING GEAR , CAUSING WEAR ON STARTER RING GEAR AND BENDIX ENGAGEMENT GEAR. WHEN THE BENDIX DRIVE DOES NOT DISENGAGE FROM STARTER R ING GEAR COMPLETELY, THE BENDIX DRIVE DISENTIGRATES ALSO DAMAGING THE ENGINE STARTER RING GEAR. THIS IS A REOCCURING PROBLEM. WITH SILVER BENDIX DRIVES, P/N EBB-75A. 1 H 7 1 3O 3 O NT 3A12 E274 2007030900061 20070309 00061 CE 2007 3 9 2007H0002 1 20070305 G 2730 556545092 ACTUATOR CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ELEVATOR MISOVERHAULED B R3R2 K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 01 2663Y 550602 ACTUATOR RODS PROVIDED WITH UNIT WERE TOO SHORT TO MOVE ELEVATOR TABS THE REQUIRED AMOUNT. 1 L 7 2 4F 4 F A22CE E1NE 2008011100229 20080111 00229 2008 1 11 2008FA0000005 4 20071220 G 2565 CABLE ESCAPE SLIDE WRONG PART B K NONE O OTHER IN INSP/MAINT 1 EA 35 INCORRECT PULL HANDLE CABLE (FIRING CABLE) DEPLOYMENT CABLE WAS SECURED WITH TAPE WHICH HINDERED DEPLOYMENT OF SLIDE. I NCORRECT HANDLE AND CABLE ASSEMBLY FITTED. CABLE NOT THREADED TROUGH GROMMET DUE TO INCORRECT FIRING CABLE ASSEMBLY. C MM 25-61-10, STEPS 26 PAGE 50 WAS NOT FOLLOWED. 8130-3 TRACKING NR SBP-5473, SO NR 287413, PO NR R9246, DATED 10/23/2007 , MO 0598171. 2008011400027 20080114 00027 NE 2008 1 14 2008FA0000020 2 20071015 G 7200 ENGINE UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE MAKING METAL D O OTHER O OTHER NR NOT REPORTED 1 WP 07 179CB 26 1412 34435 ON GROUND RUN, ENGINE CHIP DETECTOR ILLUMINATED. BOTH DETECTORS HAD METAL SLIVERS. SAMPLES TAKEN, AND MFG CONDEMNED ENGI NE. ENGINE REMOVED FROM SERVICE, AND RETURNED TO MFG FOR REPAIR. 1 G 7 2 3U 3 U NC R0001RD E34NE 2008011400026 20080114 00026 NE 2008 1 14 2008FA0000022 2 20071221 G 7261 OIL JET UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIUS2F 60010 NE ENGINE LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 183CB 618 18 1421 34428 ENGINE EXPERIENCING INTERNAL OIL LEAKAGE. MFG CONDEMNED ENGINE. ENGINE REMOVED SERVICE, AND RETURNED TO MFG FOR REPAIR. 1 G 7 2 3U 3 U NC R0001RD E34NE 2008011400025 20080114 00025 NE 2008 1 14 2008FA0000024 2 20071019 G 7200 ENGINE UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIUS2F 60010 NE MAKING METAL D A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 07 197CB 249 49 1448 34506 ENGINE CHIP DETECTOR ILLUMINATED. BOTH CHIP DETECTORS HAD METAL CONTAMINATION. SAMPLES TAKEN, AND MFG CONDEMNED ENGINE. ENGINE REMOVED FROM SERVICE, AND RETURNED TO MFG FOR REPAIR. 1 G 7 2 3U 3 U NC R0001RD E34NE 2008012200105 20080122 00105 2008 1 22 2008FA0000026 2 20071227 G 7322 10603511 CARBURETOR ENGINE FAILED B FCPR K NONE O OTHER IN INSP/MAINT 1 NM 09 CARBURETOR FAILED THE STUMBLE TEST, FOUND TO BE ACCELERATOR CIRCUIT. PART RETURNED TO PRECISION FOR FURTHER EVALUATION. (K) 2008012200107 20080122 00107 CE 2008 1 22 2008FA0000027 1 20071212 G 5320 109033 BRACKET CESSNA 185 185A 2072804 CE CONT O470 IO470F 17026 SO ALTERNATOR CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SO 13 10044 45 1850419 INSTALLED PLANE POWER ALTERNATOR CONVERSION KIT, STC SA 10682SC ON AC. DURING OIL CHANGE FOUND ALTERNATOR BRACKET CRACK ED TOTOALLY IN HALF. ALTERNATOR HAD ONLY BEEN IN USE 3 WEEKS AND APPROX 45 HRS. (K) 1 H 7 1 3O 3 O 3A24 3E1 2008012200112 20080122 00112 SO 2008 1 22 2008FA0000028 1 20071226 G 7312 MS21919DG3 CLAMP PIPER PA22 PA22150 7102210 SO LYC O320 O320* 41508 EA HEAT BOX LOOSE D O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 AL 01 7637D 225346 ENGINE DID NOT RESPOND WHEN POWER APPLIED ON A LOW FLY BY AND CAUSED THE PLANE TO LAND NEXT TO RUNWAY IN SNOW, DAMAGING ACFT. FOLLOWING PROBLEMS WERE FOUND ON POST INCIDENT INSPECTION OF ENGINE AND EITHER ONE CAN CONTRIBUTE TO LOSS OF LIT TLE ALONE BOTH TOGETHER. FOUND CARBURETOR HEAT CABLE CLAMP LOOSE ON CABLE HOUSING. WRONG CLAMP INSTALLED ON CARBURET OR HEAT CABLE HSG AT REAR OF AIR BOX. AND MUFFLER END WITH THE CARB HEAT SHROUD HAS A SUBSTANTIAL EXHAUST LEAK INTO THE CARB HEAT SHROUD. THE INSIDE OF THE CARB HEAT SHROUD, SCAT HOSE AND AIR BOX ARE VERY SOOTY FROM EXHAUST GASSES. THE EX HAUST MUFFLER CLAMP LEAKING. THIS WILL CAUSE A POWER LOSS DUE TO THE HOT INDUCTION AIR, (K) 1 H 7 1 3O 3 O 1A6 E274 2008012200050 20080122 00050 NE 2008 1 22 2008FA0000029 2 20071230 G 7261 WARNING LIGHT UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE CHIP DETECTOR FALSE ACTIVATION D O OTHER N FALSE WARNING CR CRUISE 1 GL 21 372HS 1460 34517 ENGINE CHIP LIGHT IN CRUISE FLIGHT. INSPECTED BOTH MAGNETIC PLUGS FOR FOREIGN MATERIAL, NONE WAS NOTED. INSPECTED AND TESTED MAGNETIC PLUG HEADS IAW 79-38-00-750-801, INSPECTION AND OPS CHECKS WERE GOOD. REMOVED AND REPLACED ENGINE OIL A ND RETURN FILTER IAW 79-24-05-901-801-A01. OPS AND LEAK CHECKS GOOD. (K) 1 G 7 2 3U 3 U NC R0001RD E34NE 2008012200128 20080122 00128 NE 2008 1 22 2008FA0000030 3 20071211 G 6111 6607132886 BLADE ROTOL ROTOL R389 R389* NE PROPELLER CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 34226 BLADE RECEIVED FROM CUSTOMER WITH A CRACKED ROOT END OUTERSLEEVE. NO REPAIR AVAILABLE. PART HAS BEEN REMOVED FROM FURT HER SERVICE. (K) 6 C P30NE 2008012200148 20080122 00148 SW 2008 1 22 2008FA0000031 1 20071205 G 6710 2040012741 LINER BELL 204 UH1B 1181410 SW COLLECTIVE WORN D H50L K NONE O OTHER IN INSP/MAINT 1 NM 05 46969 638548 PILOT EXPERIENCED COLLECTIVE BOUNCE ON TAKEOFF. INSPECTION OF COLLECTIVE LINERS SHOWED A SUFFICIENT AMOUNT OF LINER REM AINING IN THE WEAR AREA. WITH FURTHER INSPECTION, THE MINIMUM COLLECTIVE FRICTION WAS TOO LOW. INSPECTION ON NR 3 AND NR 6 PHASE IAW TM 55-1520-219-PMS, PAGE 6, ITEM NR 2.14 REQUIRES TO INSPECT COLLECTIVE FRICTION LINERS FOR WEAR. ADJUST MENT OF MINIMUM COLLECTIVE FRICTION SHOULD ALSO BE INCLUDED IN THE PHASE INSPECTION CHECKLIST ALONG WITH VISUAL INSPECTI ON OF THE LINERS. (K) 1 G 7 1 4U EXPA1G71 2008012200149 20080122 00149 SO 2008 1 22 2008FA0000032 1 20071212 G 8011 MHB4016 STARTER PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA ENGINE INOPERATIVE B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 326 OPERATOR COMPLAINED THAT THE ENGINE STARTER WOULD NOT ENGAGE. AFTER INSPECTION, FOUND THAT THE STARTER FIELD CASE HAD S EPARATED FROM GEAR HOUSING. A DETAILED INSPECTION OF THE FIELD CASE SCREW HOLES REVEALED THAT MOST OF THE THREADS WERE STRIPPED OUT AND HOLES WERE ELONGATED. WOULD RECOMMEND THAT AT EACH 100 HR/ANNUAL INSPECTION, PERFORM TORQUE CHECK OF G EAR HOUSING TO CASE ATTACH SCREWS AND REPAIR AS REQUIRED. (K) 1 L 7 1 3O 3 O 2A13 E286 2008012200066 20080122 00066 EA 2008 1 22 2008FA0000033 1 20071015 G 2740 21207008 ACTUATOR CNDAIR CL600 CL6002B16 1900305 EA PITCH TRIM FAILED B UO2R O OTHER O OTHER NR NOT REPORTED 1 GL 19 BMAI 6552 5049 PITCH TRIM ACTUATOR, PN 21207-008, SN 344: CONNECTOR P5CD- PINS A, B AND D ARE SHORTED TO PIN E. THE SHORT IS LESS THA N 1. PIN C HAS A 25 SHORT TO PIN E. FLEXING THE CONNECTOR CAUSES THE SHORT TO COME AND GO. (K) 2 L 7 2 4F RT A21EA 2008012200051 20080122 00051 SO 2008 1 22 2008FA0000034 1 20071012 G 5540 63451000 SUPPORT PIPER PA28 PA28181 7102807 SO LYC O360 O360* 41514 EA RUDDER BAR CRACKED B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 4146R 5820 2843160 FOUND CRACKED AFT ZEE ASSY PN 62664-000. THE ZEE ASSY IS RIVETED TO THE TOP FWD END OF TUNNEL PLATE PN 62601-003 AND AS AN ATTACHMENT POINT FOR THE RUDDER BAR SUPPORT ASSY PN 63451-000 USING 4 STANDARD AN3-4A BOLTS, WHICH ARE SECURED THROU GH NUTPLATES THAT ARE RIVETED ON BOTH FORE AND AFT ZEE ASSEMBLIES. CRACKING POSSIBLY CAUSED BY LOOSENESS IN TOE BRAKE S UPPORT BRACKETS PN 63468-000 ON BOTH PILOT AND CO-PILOTS SIDE. THE STANDARD AN3-13A BOLTS USED TO ATTACH THESE TOE BRAK E SUPPORT BRACKETS LOOSEN OVER TIME AND CAUSE LOSS OF SUPPORT TO THE RUDDER PEDAL BAR ASSY PN 63420-000. EXCESS MOVEMEN T IN RUDDER BAR SUPPORT ASSY. THIS FLEXING TRANSFERS DOWN TO THE ZEE ASSEMBLIES CAUSING METAL FATIGUE AND SUBSEQUENT CR 1 L 7 1 3O 3 O 2A13 E286 2008012200043 20080122 00043 GL 2008 1 22 2008FA0000035 1 20071218 G 7312 CONTROL ARM DIAMON DA40 DA40 2990002 GL LYC O360 O360* 41514 EA CARB HEAT BROKEN D O OTHER O OTHER NR NOT REPORTED 1 NM 07 418FP 40FC018 CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA KE. RECOMMEND INSTALLED THINKER MATERIAL ON CARB HEAT CONTROL ARM LEVER, DIFFERENT WELDING PROCESS, OR DIFFERENT ATTACH MENT PROVISION ALTOGETHER. (K) 1 L 7 1 3O 3 O NT A47CE E286 2008012200126 20080122 00126 NE 2008 1 22 2008FA0000042 2 20071212 G 8530 CYLINDER HEAD DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE ENGINE CRACKED E O OTHER O OTHER CL CLIMB 1 AL 05 777DH 1434 47 42222299 CYLINDER CRACKED IN THE AREA OF EXHAUST VALVE. 1 H 7 1 3R 3 R A806 5E1 2008021200238 20080212 00238 NE 2008 2 12 2008FA0000045 3 20070823 G 6111 6607132886 BLADE ROTOL ROTOL R389 R389* NE NR 1 CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 39882 4932 DR6828288 DR6828288 PROP REMOVED DUE TO NR 1 BLADE LOOSE IN HUB. NR 1 BLADE SN 689 WAS FOUND TO HAVE A CRACKED OUTER SLEEVE ON BLADE ROOT E ND. BLADE WAS REJECTED AND REMOVED FROM FURTHER SERVICE. (K) 6 C P30NE 2008013100304 20080131 00304 CE 2008 1 31 2008FA0000064 1 20071119 G 2435 23085001 STARTER GEN BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE FAILED D O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 SO 03 80BZ FA117 PCE95242 THE NR 1 BEARING FAILED RESULTING IN A CATASTROPHIC FAILURE AND AN IN FLIGHT SHUTDOWN. THE ENGINE WAS REMOVED AND SENT FOR REPAIR. DURING THE FAILURE INVESTIGATION, ELECTRICAL ARCING WAS FOUND ON THE NR 1 BEARING, INPUT SHAFT, AND STARTER /GENERATOR DRIVE GEAR. SD ADVISORY NR AV-2007-05 ISSUED THAT STATES ACCUMULATION OF BRUSH DUST CAN CAUSE STARTER GENERA TOR ARMATURE LEAKAGE. OUR RESEARCH DOES NOT SHOW ANY PREVENTATIVE MAINTENANCE ACTIONS THAT MAY BE PERFORMED TO THE STAR TER GENERATOR TO CHECK FOR ELECTRICAL DISCHARGE. (K) 2 L 7 2 4T 4 T A24CE E4EA 2008012900294 20080129 00294 CE 2008 1 29 2008FA0000065 1 20070824 G 3246 WHEEL HALF CESSNA 310 310L 2074230 CE LANDING GEAR CRACKED C K NONE O OTHER IN INSP/MAINT 1 SO 01 63EL 2200 310L0088 UPON CHANGING A TIRE ON A CLEVELAND WHEEL ASSEMBLY ON ABOVE AIRCRAFT IT WAS DISCOVERED THAT THE PORTION OF THE WHEEL HAL F THAT HOLDS THE BEARING RACE WAS CRACKING. IT HAD CRACKED OVER 180 DEGREES AROUND THE AXLE OPENING, WHICH COULD HAVE EV ENTUALLY HAD A SERIOUS ACCIDENT. 1 L 7 2 3O 3A10 2008020400105 20080204 00105 SO 2008 2 4 2008FA0000067 2 20071219 G 7414 GEAR DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO RT MAGNETO MAKING METAL B XGKR K NONE O OTHER IN INSP/MAINT 1 WP 25 293DC C0193 806439 PRIOR TO PERFORMING SB 03-7 INSPECTION, 2 NEW GEARS WERE ORDERED FROM MFG IN EVENT WOULD NEED THEM DURING INSPECTION. A T 372.9 TACH TIME, THE RT MAGNETO GEAR BROKE A TOOTH DURING START AND WAS IDENTIFIED DURING PRE-TAKEOFF RUNUP. THE ENG INE WAS INSPECTED AND FOUND TO HAVE METAL PARTICLES DISTRIBUTED THROUGHOUT THE ENGINE. (K) 1 L 7 1 3O 3 O NT TA4CH E7SO 2008022000062 20080220 00062 GL 2008 2 20 2008FA0000076 1 20071221 G 3233 ACTUATOR AMTR QUTAIR QUESTAIRVENT 0561898 GL CONT O550 IO550N 17042 SO MCAULY 2A34C B2A34C205 GL MLG MALFUNCTIONED H O OTHER O OTHER LD LANDING 1 SO 19 203V 35 22 NOSE GEAR LINEAR ACTUATOR TRIPPED CIRCUIT BREAKER INFLIGHT AND WAS NOT DETECTED PRIOR TO LANDING. THE AIRCRAFT WAS INAD VERTENTLY LANDED WITH THE NOSE GEAR NOT EXTENDED. WHEN THE AIRCRAFT WAS RECOVERED, THE AIRCRAFT WAS LIFTED SO THE GEAR COULD BE EXTENDED. WHEN POWER WAS APPLIED TO THE AIRCRAFT AND THE CIRCUIT BREAKER WAS RESET THE NOSE GEAR EXTENDED NORM ALLY AND LOCKED IN THE DOWN POSITION, THE CIRCUIT BREAKER DID NOT TRIP. OTHER AIRCRAFT IN THE FLEET HAVE HAD PROBLEMS W ITH THE GEAR ACTUATOR BREAKERS BEING TO LOW OF A RATING BUT THIS AIRCRAFT HAS THE HIGHER RATED BREAKER INSTALLED. 1 L 7 1 3O 3 O RT EXPA1L71 E3SO 5 C P3EA 2008031000331 20080310 00331 CE 2008 3 10 2008FA0000090 1 20071112 G 2797 C352B20 WIRE BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE PITCH TRIM CHAFED B AKGR O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 CE 05 213BK 3287 RK216 PITCH TRIM INOPERATIVE REMOVED RT FWD GALLEY AND RT FWD PARTITION. FOUND WIRE BUNDLE CHAFED BEHIND PARTITION. REPAIRED (3) WIRES THAT WERE CHAFED THROUGH TO THE CONDUCTORS. PROVIDED CLEARANCE BETWEEN WIRE BUNDLE AND PARTITION. INSTALLED ANTI-CHAFE MATERIAL ON PARTITION. AT THE TIME OF THE REPAIR NO OTHER COMPONENTS HAD MALFUNCTIONED FRO THE OTHER (2) CH AFED WIRES. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 2008031000342 20080310 00342 SO 2008 3 10 2008FA0000097 2 20071226 G 8520 649900 CRANKSHAFT PIPER PA46 PA46310P 7104605 SO CONT O550 TSIO550C SO ENGINE BROKEN D O OTHER O OTHER NR NOT REPORTED 1 NM 03 47BC 4608129 814584 CRANKSHAFT BROKE JUST AFT OF PROPELLER MOUNTNG FLANGE. (K) 1 L 7 1 3O 3 O RT A25SO E5SO 2008031000345 20080310 00345 SO 2008 3 10 2008FA0000098 1 20071226 G 3221 1303400 MOUNT PIPER PA22 PA22150 7102210 SO LYC O320 O320* 41508 EA NLG CRACKED D K NONE O OTHER LD LANDING 1 AL 01 7637D 225346 FOUND NOSE GEAR MOUNT CORRODED THIN IN SPOTS ON THE LOWER TUBES FROM THE INSIDE. ORIGINAL THICKNESS .049 INCH AND IN TH E THIN SPOTS THE THICKNESS WAS LESS THAN .020 INCH. THE MOUNT HAD BEEN REPAIRED BY WELDING AND ONE WELD WAS A COLD WELD THAT CRACKED AND ALLOWED MOISTURE INTO THE INSIDE OF THE TUBING. ANNUAL INSP 35 HOURS BEFORE FAILURE. THE MOUNT FAILE D ON A SOFT FIELD LANDING AND CAUSED SUBSTANTIAL DAMAGE AFTER AN ENGINE FAILURE. IN MY OPINION THE THIN WALL FROM THE C ORROSION IS WHY THE MOUNT FAILED. RECOMMENDATIONS TO PREVENT SUCH RECURRENCES ARE TO INSPECT ALL WELDS FOR CRACKS, ESPE CIALLY FIELD REPAIRS. THESE FIELD REPAIR WELDS NEED TO BE EXAMINED FOR THE QUALITY OF THE WELD, CRACKS AND PIN HOLES EA 1 H 7 1 3O 3 O 1A6 E274 2008031900366 20080319 00366 EA 2008 3 19 2008FA0000103 2 20071030 G 7414 6393 MAGNETO LYC O540 IO540E1B5 41532 EA ENGINE WORN B O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 GL 15 51RF 58 ENGINE WAS GETTING HARD TO START, CHECKED MAG TIMING AND FOUND LT MAG TIMING, OUT OF LIMITS. DISASSEMBLED MAG AND FOUND THE CAM WORN OUT . 58.7 HRS SINCE NEW. 3 O 1E4 2008032400435 20080324 00435 SO 2008 3 24 2008FA0000105 1 20071204 G 3213 31661STCSA4618NM FITTING PIPER PA18 PA18 7101802 SO LYC O360 O360A1A 41514 EA RT MLG BROKEN G K NONE O OTHER LD LANDING 1 AL 03 723C 181150 PILOT STATED THAT HE PERFORMED AN OFF AIRPORT LANDING ALONG A BEACH WHILE HUNTING. UPON LANDING, THE UPPER RT MLG CABAN E FITTING BROKE. THE LANDING GEAR SAFETY CABLES PREVENTED A TOTAL GEAR COLLAPSE. (K) 1 H 7 1 3O 3 O 1A2 E286 2008033100046 20080331 00046 SO 2008 3 31 2008FA0000109 1 20071221 G 3210 6569100 TORQUE LINK PIPER PA28 PA28140 7102802 SO LYC O320 O320* 41508 EA MLG SEPARATED D O OTHER O OTHER LD LANDING 1 EA 23 9855W 6910 2823369 TORQUE LINK SEPARATED ON ABORTED LANDING ALLOWING WHEEL AND AXLE ASSY TO SEPARATED FROM AC. SAFE LANDING ON UPPER CASTI NG ASSY WAS MADE WITH DAMAGE TO CASTING AND FLAP. AD 72-08-06 OR THIS LINK CALLED FOR 500 HR INSP. INTERVAL PAR 203.8 HR PRIOR. WOULD SUGGEST THAT AD SHOULD BE CHARGED TO RETIRE THESE PARTS AT 5000 HR. (K) 1 L 7 1 3O 3 O 2A13 E274 2008033100144 20080331 00144 GL 2008 3 31 2008FA0000134 1 20070727 G 2822 51000020 PUMP DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA FUEL SYS INOPERATIVE C GO3S K NONE O OTHER IN INSP/MAINT 1 NM 07 423FP 156 40FC023 AFTER A PREVIOUS FLIGHT AND BEFORE THE NEXT STUDENTS FLIGHT, THE ELECTRIC FUEL PUMP WAS FOUND TO BE INOPERATIVE. INADEQ UATE COOLING IS WHAT WE BELIEVE TO BE THE SOURCE OF THE MALFUNCTIONS. PROVIDE RAM AIR PROPER COOLING OF THE FUEL PUMP A ND MOTOR. (K) 1 L 7 1 3O 3 O NT A47CE E286 2008033100145 20080331 00145 GL 2008 3 31 2008FA0000136 1 20070221 G 2822 51000020 PUMP DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA FUEL SYSTEM INOPERATIVE D GO3S K NONE O OTHER IN INSP/MAINT 1 NM 07 424FP 232 40FC024 AFTER A PREVIOUS FLIGHT, AND BEFORE THE NEXT STUDENTS FLIGHT, THE ELECTRIC FUEL PUMP WAS FOUND TO BE INOPERATIVE. INADE QUATE COOLING IS WHAT WE BELIEVE TO BE THE SOURCE OF THE MALFUNCTIONS. PROVIDE RAM AIR FOR PROPER COOLING OF FUEL PUMP AND MOTOR. (K) 1 L 7 1 3O 3 O NT A47CE E286 2008033100174 20080331 00174 EU 2008 3 31 2008FA0000147 1 20070615 G 6710 COVER SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL1D1 60053 NE COLLECTIVE STICK LOOSE D O OTHER O OTHER NR NOT REPORTED 1 EA 11 4048L 2732 3020 9245 COLLECTIVE MOUNTED HOIST EMERGENCY RELEASE (JETT) SWITCH COVER SECURITY. IF THE BASE OF THE COVER IS LOOSE AND TURNED 1 80 DEGREES, AS WAS THE CASE HERE, THE COVER OPENS FORWARD AND EXTENDS OFF OF THE END OF THE COLLECTIVE. IN THIS CONDITI ON WHEN THE COLLECTIVE IS FULLY LOWERED, THE PUSHBUTTON COVER JAMS AGAINST THE GENEVA MODIFIED CENTER CONSOLE UNTIL THE PILOT PUSHES THE COLLECTIVE THROUGH THE BINDING, AND THE HINGED COVER POPS UP AND OUT OF THE WAY. IN THIS CONDITION, WI TH THE COLLECTIVE JETT SWITCH OPEN COVER WEDGED AGAINST THE CENTER CONSOLE, A PILOT MAY FEEL THAT THE COLLECTIVE IS FULL Y DOWN WHEN IT IS NOT. 1 G 7 1 3U 3 U H9EU E19EU 2008041000261 20080410 00261 CE 2008 4 10 2008FA0000222 1 20071116 G 3260 513771 DOWNLOCK SWITCH CESSNA 210 210L 2073448 CE MLG BROKEN G K NONE O OTHER IN INSP/MAINT 1 WP 01 987M 3344 21061093 EXAMINATION OF THE LANDING GEAR SYSTEM REVEALED THAT THE LT LDG DOWN LIMIT SWITCH PLUNGER WAS DAMAGED AND STUCK IN THE D EPRESSED POSITION WITH APPROX .012 INCH AIRGAP BETWEEN PLUNGER TIP AND STRIKER PLATE. WITH SIMULATED AIR LOADS APPLIED TO THE LT MAIN GEAR THE LANDING GEAR PUMP WOULD SHUT OFF PRIOR TO THE LT MAIN GEAR LOCKING IN THE DOWN LOCK. THE GEAR P OSITION INDICATOR IN THE COCKPIT INDICATED GREEN AND THE UNSAFE HORN DID NOT SOUND WHEN THE THROTTLE WAS RETARDED. (K) 1 H 7 1 3O 3A21 2008041000233 20080410 00233 EA 2008 4 10 2008FA0000228 2 20071016 G 8530 INTAKE VALVE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CYLINDER WORN D K NONE O OTHER IN INSP/MAINT 1 WP 15 49811 23C064444 15281332 FOLLOWING ACCIDENT THAT RESULTED IN ENGINE FAILURE, INVESTIGATION FOUND NO COMPRESSION ON THE NR 1 CYL AND REPORTED VALV E CLEARANCE WAS 0.002 INCH. THE CYL WAS NOT REMOVED AND THE AC WAS RELEASED INTO CUSTODY. REMOVED THE NR 1 CYLINDER AND VALVES. BOTH VALVES HAD ACCELERATED WEAR TO THE VALVE SEATS WITH EVIDENCE OF LEAKAGE. LAST VALVE GUIDE CHECK WAS PERF ORMED 46 HOURS EARLIER WITHIN LIMITS. (K) 1 H 7 1 3O 3 O NT 3A19 E223 2008042500111 20080425 00111 SO 2008 4 25 2008FA0000251 1 20071114 G 5343 95555000 FITTING PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360* 17025 SO NLG MOUNT SEPARATED C K NONE O OTHER IN INSP/MAINT 1 SO 15 467TC 347870006 SB 1123B TABLE 1, ITEM 14 STATES TO INSPECT TUNNEL BRACKET 95554-000 AND FITTING 95555-000 FOR CONDITION AND ATTACHMENT. ACCORDING TO FIGURE 1A, THE CONDITION INDICATED NO PROBLEMS, HOWEVER FITTING 95555-000 WAS SEPARATED FROM BRACKET 9555 4-000. ALL 4 AN426 RIVETS HAD SHEARED, ALLOWING FITTING TO SHIFT POSITIONS, ALLOWING NOSE GEAR OVERCENTER GEOMETRY TO C HANGE, RESULTING IN GEAR COLLAPSE. ITEM 14 DESCRIBES INSPECTION THROUGH AND ACCESS OPENING IN BOTTOM SKIN AT BL 0.0 JUS T AFT OF STATION 49.5. IT IS UNCLEAR WHETHER THIS ACCESS OPENING IS TO BE CUT IN THE SKIN AND A DOUBLER AND INSPECTION PLATE INSTALLED OR IF THIS HOLE IS ALREADY PRESENT. NO PA-34 AC IN OUR FLEET HAS THIS OPENING. THIS DEFECT WAS NOTED 1 L 7 2 3O 3 O A7SO E9CE 2008042800299 20080428 00299 NM 2008 4 28 2008FA0000255 1 20071202 G 2497 CIRCUIT BREAKER AMD FALC50 FALCON2000 2730170 NM PWC PW308 PW308C 52182 NE MISINSTALLED W BO5Y K NONE W B INADEQUATE Q C SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 EA 33 4QG 028 MAU 1B AND AGM 2 FAIL IN FLIGHT AND RECOVERED AFTER 3 SECONDS. SHUNT (IPC 24-05-10, ITEM 210) INSECURED ON BREAKER, ELE CTRIC ARC. ONE SCREW ON BREAKER L501X, TOO THREAD LENGTH OVERSIZED. RESULTS: EXCHANGE SHUNT AND BREAKERS. (K) 2 L 7 2 4F 4 F RT A50NM E00065EN 20080603 CE 2008 6 3 2008FA0000319 1 20071225 G 5100 UNKNOWN CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA UNKNOWN D O OTHER G MULTIPLE FAILURE CR CRUISE 1 WP 05 6079C R18200371 RL1970540A INFLIGHT FAILURE OF PART OR PARTS UNKNOWN WITH NO SYMPTOMS FROM WITHIN COCKPIT, IE: OIL PRESSURE, OIL TEMPERATURE, AND C YLINDER HEAD TEMPERATURES WERE ALL INDICATING WITHIN NORMAL RANGES. OUTWARD MANIFESTATIONS WERE EXCESSIVE BLOW-BY OIL O N BELLY OF THE AIRPLANE. OTHER MANIFESTATIONS WERE: AN INTERRUPTION IN THE SMOOTH MOVEMENT OF THE PROP (WHEN ROTATING B Y HAND) AT THE SAME LOCATION IN THE ROTATION ON EVERY OTHER COMPLETE ENGINE ROTATION, IE: RELATED TO THE CAMSHAFT (720 D EGREES OF ROTATION). A CRACK IN THE LT SIDE OF THE ENGINE CASE OVER THE BASE OF THE NR 5 CYLINDER WHERE THE ENGINE CASE FARES INTO THE INTAKE VALVE PUSHROD TUBE. A CRACK IN THE RT SIDE OF THE ENGINE CASE OVER THE BASE OF THE NR 6 CYLINDER 1 H 7 1 3O 3 O RT 3A13 E295 20080715 GL 2008 7 15 2008FA0000342 1 20070910 G 5210 DA4522100002 DOOR DIAMON DA40 DA40 2990002 GL LYC O360 IO360LYC* 41514 EA HARTZL HCC2Y HCC2YR1 GL PAX DOOR DEPARTED G O OTHER D INFLIGHT SEPARATION TO TAKEOFF 1 WP 07 686US 615 40640 L3262751A CH39554B ON TAKEOFF ROLL AT VR, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1 L 7 1 3O 3 O NT A47CE 1E10 5 C P920 20080715 GL 2008 7 15 2008FA0000344 1 20071106 G 5210 DA4522100002 DOOR DIAMON DA40 DA40 2990002 GL LYC O360 IO360LYC* 41514 EA HARTZL HCC2Y HCC2YR1 GL PAX DOOR DEPARTED G O OTHER D INFLIGHT SEPARATION TO TAKEOFF 1 WP 07 605US 225 40675 L3276151A CH399768 WHILE TAXIING INTO TAKEOFF POSITION ON RUNWAY, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1 L 7 1 3O 3 O NT A47CE 1E10 5 C P920 20080715 EA 2008 7 15 2008FA0000375 2 20071226 G 7322 MS21919DG3 CLAMP PIPER PIPER PA22 PA22150 7102210 SO LYC O320 O320* 41508 EA CARB HEAT WORN D O OTHER O OTHER NR NOT REPORTED 1 AL 01 7637D 225346 ENGINE DID NOT RESPOND WHEN POWER WAS APPLIED ON A LOW FLY BY OF THE RUNWAY AND CAUSED THE PLANE TO LAND NEXT TO THE RUN WAY IN THE SNOW DAMAGING THE AIRCRAFT. THE FOLLOWING TWO PROBLEMS WERE FOUND ON POST INCIDENT INSPECTION OF THE ENGINE A ND EITHER ONE CAN CONTRIBUTE TO LOSS. THE FIRST PROBLEM FOUND WAS THE CARBURETOR HEAT CABLE CLAMP WAS LOOSE ON THE CABL E HOUSING. THIS WOULD ALLOW THE HOUSING TO SLIP IN THE CLAMP AND SOMETIME NOT MAKE STOP TO STOP TRAVEL. THE WRONG CLAMP WAS INSTALLED ON THE CARBURETOR HEAT CABLE HOUSING AT REAR OF AIR BOX. THE CLAMP INSTALLED WAS PN MS21919GD3 (3/16) INC H DIAMETER ADEL CLAMP. THE ADEL CLAMP USED HAS AN CHLOROPRENE RUBBER CUSHION WITH A MAXIMUM TEMP OF 212 DEGREES (F). THE 1 H 7 1 3O 3 O 1A6 E274 20080715 SO 2008 7 15 2008FA0000376 1 20071226 G 7810 1423500 CLAMP PIPER PA22 PA22150 7102210 SO LYC O320 O320* 41508 EA EXHAUST PIPE LOOSE D O OTHER O OTHER NR NOT REPORTED 1 AL 01 7637 225346 ENGINE DID NOT RESPOND WHEN POWER WAS APPLIED ON A LOW FLY BY OF THE RUNWAY AND CAUSED THE PLANE TO LAND NEXT TO THE RUN WAY IN THE SNOW DAMAGING THE AIRCRAFT. THE FOLLOWING PROBLEM WAS FOUND ON POST INCIDENT INSPECTION OF ENGINE AND EITHER ONE CAN CONTRIBUTE TO LOSS. THE PROBLEM FOUND WAS THE MUFFLER END WITH THE CARB HEAT SHROUD HAS A SUBSTANTIAL EXHAUST L EAK INTO THE CARB HEAT SHROUD. THE INSIDE OF THE CARB HEAT SHROUD, SCAT HOSE AND AIR BOX ARE VERY SOOTY FROM EXHAUST GAS SES. THE EXHAUST MUFFLER PN 10308-03 END THAT EXHAUST PIPE PN 12043-23 END SLIDES INTO AND HAS PN 14235-00 EXHAUST CLAM P AROUND IT IS LEAKING. THE PIPE END THAT SLIPS INTO THE MUFFLER IS VERY LOOSE, NOT A TIGHT SEAL LIKE NORMAL. THE CLAMP 1 H 7 1 3O 3 O 1A6 E274 20080715 EU 2008 7 15 2008FA0000386 1 20071101 G 3250 STEERING SYS PIAGIO P180 P180 6960204 EU NLG CONTAMINATED D O OTHER O OTHER NR NOT REPORTED 1 SW 07 STEERING SYSTEM DISENGAGEMENT DURING TAXI. STEERING DRIFT DURING ENGAGEMENT. STEERING HART TO TURN (NO INPUT). STEERING RELIABILITY VERY LOW. STEERING CONTAMINATION DURING MFG BENCH TESTING. AIRCRAFT RUNWAY EXCURRSION DURING LANDING AND TAXI DUE TO STEERING CONTROL LOSS. AIRCRAFT DAMAGED FROM STEERING DRIFT DURING LANDING. (K) 1 H 7 2 3O RT A59EU 20080715 EA 2008 7 15 2008FA0000417 2 20071221 G 8500 IGSO480 ENGINE BEECH 65 A65 1152803 CE LYC O480 GSO480* 41529 EA LEFT SEIZED G E ENGINE SHUTDOWN O OTHER NR NOT REPORTED 1 CE 07 8108R LC329 L119933C AIRCRAFT LANDED WITH LT ENGINE SHUTDOWN (IN-FLIGHT SHUTDOWN). INITIAL INVESTIGATION REVEALED THAT THE ENGINE WAS SEIZED. OIL SCREEN WAS REMOVED AND FOUND HEAVILY CONTAMINATED WITH METAL PARTICLES. ENGINE OIL SUMP DRAIN PLUG WAS REMOVED. L ARGE METAL PARTICLES, SOME APPROXIMATELY .25 IN DIAMETER WERE REMOVED FROM IMMEDIATELY INSIDE THE SUMP DRAIN HOLE. OTHE R PARTICLES APEAR TO BE GEAR TEETH, AS SHEARED FROM THE GEAR. ENGINE WAS REMOVED FROM THE AIRCRAFT(12-18-2007) AND SENT TO CUSTOMER DESIGNATED REPAIR FACILITY. (K) 1 L 7 2 3O 3 O 3A20 E284 20080715 GL 2008 7 15 2008FA0000423 1 20071106 G 5210 DA4522100002 DOOR DIAMON DA40 DA40 2990002 GL REAR PASSENGER DEPARTED G D RETURN TO BLOCK D INFLIGHT SEPARATION TX TAXI/GRND HDL 1 WP 28 605US 40675 WHILE TAXIING INTO TAKEOFF POSITION ON RUNWAY, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1 L 7 1 3O NT A47CE 20080715 GL 2008 7 15 2008FA0000425 1 20070910 G 5210 DA4522100002 DOOR DIAMON DA40 DA40 2990002 GL REAR PAX DOOR DEPARTED G O OTHER S AFFECT SYSTEMS TO TAKEOFF 1 WP 28 686US 40640 ON TAKEOFF ROLL AT VR, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1 L 7 1 3O NT A47CE 2007032200048 20070322 00048 CE 2007 3 22 20582007TJ001 1 20070313 G 5344 551123515 HINGE CESSNA CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE PAX DOOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 13 6763L 6986 5500673 DURING A DAILY INSPECTION OF THE AIRCRAFT A CRACK WAS FOUND ON THE UPPER LUG OF THE DOOR HINGE. DURING REPLACEMENT OF TH E HINGE THE LUG COMPLETELY BROKE IN (2) PEICES. 1 L 7 2 4F 4 F A22CE E1NE 2007121400292 20071214 00292 NM 2007 12 14 220757 1 20071205 G 2913 65446747 HOUSING BOEING BOEING 737 737 UTILSYS NM MODULE CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 0728 HOUSING WAS FOUND CRACKED DURING TEARDOWN IN SHOP. 2 L 7 2 4F RT A16WE 2007120500045 20071205 00045 2007 12 5 243DR1 4 20071121 G 2216 1C7921888 SERVO CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520* 17040 SO ELEVATOR TRIM MISINSTALLED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 17 243DR 4056 U20604747 WHILE UNDERGOING A SCHEDULED INSPECTION, MECHANIC FOUND ELEVATOR TRIM SYS WAS MISRIGGED. TRAVEL LIMITS WERE NOT CORRECT AND WERE ACTUALLY RIGGED OPPOSITE WITH REGARDS TO MAX TRAVEL UP/DOWN. TRAVEL LIMITS IN MM NR D2070-3-13 FIGURE 1-1 WERE MISINTERPRETED, MFG SHOULD REVISE THIS MANUAL SECTION TO BE MORE SPECIFIC SINCE WE HAVE SEEN THIS BEFORE. ADDITIONALLY I T WAS FOUND THAT ELEVATOR TRIM SYS COULD NOT BE RIGGED BECAUSE CENTURY 2000 AUTOPILOT ELEVATOR TRIM SERVO WAS NOT INSTAL LED CORRECTLY WHEN SYS WAS INSTALLED ON 10/9/2001 UNDER STC SA3479SW-D. FOUND SERVO MISMOUNTED, IT DID NOT MATCH CENTUR Y DRAWING 69D1754. REINSTALLED THE TRIM SERVO IAW THE STC DRAWINGS. 1 H 7 1 3O 3 O A4CE E8CE 2007051500183 20070515 00183 GL 2007 5 15 26519A 3 20070502 G 6111 A4564 BUSHING MCAULY CESSNA 208 208B 2073701 CE PWA PT6 PT6* 52043 EA MCAULY 3AF34C 3GFR34C703 GL BLADE LINK CRACKED B WIWA K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 WP 07 122JB 1850 208B1025 020657 VIBRATION REPORTED BY PILOT. OPERATOR WAS UNABLE TO DYNAMIC BALANCE. OPERATOR NOTICED ONE BLADE HAS ROTATIONAL PLAY. UPON DISASSEMBLY NR 2 BLADE LINK BUSHING P/N A4564 WAS FOUND CRACKED WITH PIECES MISSING. THE LINK P/N B4743 AND BLADE ACTUATING PIN P/N B5072-1 WERE DAMAGED FROM METAL TO METAL CONTACT. 1 H 7 1 3T 3 T A37CE E2NE 5 C P60GL 2007051100151 20070511 00151 SW 2007 5 11 31038042507 1 20070425 G 5610 3G5630F00111A2 WINDOW AGUSTA AB139 AB139 0260110 SW PWA PT6 PT6* 52043 EA CREW DOOR DEPARTED B O OTHER D INFLIGHT SEPARATION CR CRUISE 1 EA 17 139BK 31038 DURING CRUISE FLIGHT AT AN ALTITUDE OF 2000FT, IAS 152KTS,THE CO-PILOT DOOR WINDOW SEPARATED FROM AIRCRAFT. 2 G 7 2 6U 3 T R00002RD E2NE 2007040200151 20070402 00151 CE 2007 4 2 40675 1 20070320 G 2741 45AS610023139 ACTUATOR BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE PITCH TRIM INOPERATIVE C R71A O OTHER F FLT CONT AFFECTED DE DESCENT 1 WP 05 790SS 1550 RK363 DIFFICULTY OCCURED UPON DESCENT. PILOT RECIEVED A WARNING PITCH TRIM WAS NOT SYNCRONIZED WITH AUTOPILOT SYSTEM AND TO PREPARE FOR RESISTANCE WHEN AUTOPILOT IS DISCONNECTED. PITCH TRIM ACTUATOR WAS FOUND INOPERATIVE IN THE EMERGENCY MODE/A UTOPILOT MODE. REPLACED PITCH TRIM UNIT AND RETURNED AIRCRAFT TO SERVICE. THIS AIRCRAFT WAS LAST INSPECTED ON 11-9-06 A T 1408.6 TT. 2 H 7 2 4F 4 F RT A16SW E25EA 2007120400107 20071204 00107 CE 2007 12 4 470884 1 20071105 G 4940 CH3459 IGNITER HONEYWELL RE100 LEAR 45 45LEAR 5170805 CE APU BROKEN B K NONE O OTHER IN INSP/MAINT 1 GL 09 762EL 549 P205 107 TIP OF IGNITER BROKE OFF AND WAS FOUND DURING COMPLIANCE WITH SB45-28-12. 2 L 7 2 4F RT T00008WI 2007100300005 20071003 00005 SO 2007 10 3 4757 2 20070925 G 8530 AEC631397 CYLINDER CONT CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO RT ENGINE CRACKED B FCPR O OTHER O OTHER CR CRUISE 1 NM 09 919FA 1120 276632R 414A0628 276632R PILOT WAS INFORMED BY LINE PERSONNEL DURING TAXI TO TIE DOWN, THAT ENGINE WAS MAKING A LOUD (AIR PULSING) SOUND. PILOT C OULD ONLY HEAR THE SOUND AFTER REMOVING NOISE CANCELLING HEAD SET. PILOT THEN SHUTDOWN ENGINE. INSPECTION REVEALED THE N R 4 CYLINDER TO BE CRACKED AT THE PARTING SURFACE. EXHAUST WAS ESCAPING FROM THE CRACK CAUSING THE (AIR PULSING) SOUND. 1 L 7 2 3O 3 O A7CE E8CE 2007121400346 20071214 00346 CE 2007 12 14 68DA 1 20070213 G 5512 SKIN BEECH 100 B100 1152919 CE GARRTT TPE331 TPE331* 01514 WP HORIZONTAL STAB WRINKLED B ODAR O OTHER O OTHER NR NOT REPORTED 1 EA 21 68DA BE14 DURING ROUTINE MAINTENANCE, MECHANIC DISCOVERED THAT THE HORIZONTAL STABILIZER SKIN WAS WRINKLED AT THE AFT RT ATTACH PI VOT POINT. 1 L 7 2 4T 3 T A14CE E2WE 2007062500008 20070625 00008 GL 2007 6 25 A101913 2 20070612 G 7260 23038229 GEAR ALLSN T63A720 ALLSN 250C T63A720 03002 GL GEARBOX ASSY FRACTURED B K NONE O OTHER IN INSP/MAINT 1 EA 25 NA AE405995 ENGINE WAS SENT FOR REPAIR DUE TO GENERATING METAL. UPON DISASSEMBLY FOUND THAT THE SHAFT ON THE FORWARD SIDE OF THE CE NTRIFUGAL BREATHER GEAR WAS FRACTURED IN THE AREA OF THE RADIUS WHERE THE SHAFT JOINS THE GEAR. THE RELATIVE MOTION BET WEEN THE SHAFT AND THE GEAR WAS THE CAUSE OF METAL GENERATION. 3 U E4CE 2007062500009 20070625 00009 GL 2007 6 25 A1019131 2 20070612 G 7260 23038229 GEAR SHAFT ALLSN T63A720 ALLSN 250C T63A720 03002 GL GEARBOX ASSY FRACTURED B K NONE O OTHER IN INSP/MAINT 1 EA 25 NA AE405995 ENGINE WAS SENT FOR REPAIR DUE TO GENERATING METAL. UPON DISASSEMBLY FOUND THAT THE SHAFT ON THE FORWARD SIDE OF THE CE NTRIFUGAL BREATHER GEAR WAS FRACTURED IN THE AREA OF THE RADIUS WHERE THE SHAFT JOINS THE GEAR. THE RELATIVE MOTION BET WEEN THE SHAFT AND THE GEAR WAS THE CAUSE OF METAL GENERATION. 3 U E4CE 2007120400293 20071204 00293 CE 2007 12 4 AFASVRA3181 1 20071114 G 2432 G25 BATTERY CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MASTER OVERHEATED D K NONE M J OVER TEMP WARNING INDICATION CR CRUISE 1 NM 03 9582V 556 17264384 L4623627A AIRCRAFT 12 VOLT BATTERY OVERHEATED CAUSING: ELECTROLYTE BOILING OVER, CORRODING OF ALUMINUM BATTERY BOX, LANDING LIGHT PLASTIC SWITCH MELTING, LANDING LIGHT PLASTIC CONNECTOR IN COWLING MELTING, LANDING LIGHT INOP AND ALTERNATOR FAILURE WI THOUT THE LANDING LIGHT CB TRIPPING. PILOTS COMPLYING WITH FAA RECOMMENDATIONS OF LEAVING LANDING LIGHTS ON WITHIN 5 NM OF AIRPORT ARE THE CAUSE OF THIS PROBLEM DURING TRAINING SORTIES OF 1 TO 2 HOURS WITH THE LANDING LIGHTS ON FOR THE DU RATION OF FLIGHT. THESE AIRCRAFT ARE FLOWN IN A PILOT TRAINING OPERATION WHERE SORTIES ARE 1 TO 2 HOURS ENDURANCE AND 8 TO 10 TAKEOFFS AND LANDINGS WITH THE LANDING LIGHT/LIGHTS ON FOR THE DURATION OF THE FLIGHT. 1 H 7 1 3O 3 O NT 3A12 E274 2007040900033 20070409 00033 SO 2007 4 9 AMCR200700001 1 20070329 G 2822 B12520 PRESSURE SWITCH GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU BOOST PUMP FAILED B AMCR O OTHER J WARNING INDICATION DE DESCENT 1 GL 09 706VA 1267 1528 DURING DESCENT, THE RT MAIN FUEL PUMP FAILED. MAINTENANCE FOUND THAT THE FUEL PRESSURE SWITCH ON THE RT MAIN FUEL PUMP H AD FAILED. THIS IS THE SECOND FAILURE OF A PUMP PRESSURE SWITCH WE KNOW OF WITHIN THE LAST 4 MONTHS. 2 L 7 2 4F 4 F RT A12EA E25NE 2007062500012 20070625 00012 NE 2007 6 25 AMCR200700002 1 20070612 G 2612 61423473205 FIRE DETECTOR SKRSKY S76 S76B 8143007 NE NR 1 ENGINE FAULTY B AMCR O OTHER N FALSE WARNING TX TAXI/GRND HDL 1 GL 09 520AC 2282 760380 UPON STARTER ENGAGEMENT FOR FIRST ENGINE START (EITHER ENGINE), THE NR 1 ENGINE FIRE ANNUNCIATOR WOULD ILLUMINATE ALONG WITH A FIRE TONE, BUT NO T-HANDLE ILLUMINATION. ILLUMINATION AND TONE WOULD CEASE AROUND 35-45% RPM. ALL FIRE DETECTION TESTS WOULD CHECK OK. REPLACEMENT OF NR 1 BOTTOM FLAME DETECTOR FIXED PROBLEM. 1 G 7 2 4U H1NE 2007071800220 20070718 00220 NE 2007 7 18 AMCR200700003 1 20070709 G 3240 C20497000 BRAKE ASSY SKRSKY S92 S92A NE MLG BINDING B AMCR K NONE O OTHER IN INSP/MAINT 1 GL 09 252DV 572 920009 DURING WHEEL CHANGE (LT OB) COULD NOT REMOVE THE WHEEL OFF OF AXLE. FOUND ONE OF THE CENTER STATORS (A35579) OF THE BRAK E ASSY TO BE PROTRUDING OUT OF THE PACK. THE STATOR CUT INTO THE WHEEL PREVENTING THE REMOVAL. WE DID NOT TEARDOWN THE B RAKE BUT SUSPECT EITHER THE STATOR IS OUT OF ROUND OR HAS ID DAMAGE, OR THE TORQUE TUBE IS DAMAGED ALLOWING STATOR TO SH IFT BEYOND THE PACK CIRCUMFERENCE. P/N 78286/92250-00801-102. 2 G 7 2 4U R00024BO 2007121400351 20071214 00351 CE 2007 12 14 AMCR200700004 1 20071207 G 5753 NAS509L6 JAM-NUT CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL TE FLAPS WRONG PART B AMCR K NONE O OTHER IN INSP/MAINT 1 GL 09 279DV 536 0070 DURING COMPLIANCE WITH SL525B-27-01 WHICH IS CHECKING FLAP PUSH ROD FOR IMPROPER SAFETY WIRING, FOUND THAT THE AFT JAM N UT (NAS509L6) WAS UP AGAINST THE CENTER STUD (6365028-10) RATHER THAN TIGHT AGAINST THE ROD END TUBE (6365028-9). EVERYT HING WAS SAFETIED IN THIS POSITION. 1 L 7 2 4F 4 F RT A1WI E3GL 2007031300018 20070313 00018 GL 2007 3 13 AMTR02022007 1 20070202 G 5314 KEELBEAM AMTR AIRCAR SPENCERAIRCR GL FUSLEAGE CORRODED G K NONE O OTHER IN INSP/MAINT 1 CE 01 41RH 2437 DURING AN ACCIDENT INVESTIGATION OF A S12D, THE AIRFRAME REAR KEEL SUPPORT WAS FOUND TO HAVE EXCESSIVE CORROSION AND THE WOODEN STRUCTURE ATTACHED TO THE KEEL WAS DRY ROTTED. ALTHOUGH THE CORROSION IS EVIDENT, WE BELIEVE IT WAS NOT A CAUSE OF THE ACCIDENT. THE AIRCRAFT WAS BUILT IN 1975 AND WAS OPERATED IN A SALT WATER ENVIRONMENT. THE AIRCRAFT HAD JUST RECE IVED A CONDITION INSPECTION. THERE WAS NO ACCESS TO INSPECT THE KEEL SUPPORT WHICH IS LOCATED AFT OF THE PASSENGER COMPA RTMENT. IT IS RECOMMENDED THAT AN ACCESS PANEL BE MADE TO INSPECT THE KEEL ASSEMBLY AND THAT IT BE INSPECTED AT LEAST EV ERY CONDITION INSPECTION. 1 H 7 1 3O EXPA1H71 2007082400242 20070824 00242 SW 2007 8 24 AOC0701 1 20070816 G 6210 BEARING BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE PITCH LINK DAMAGED B R29R K NONE O OTHER IN INSP/MAINT 1 SW 19 31893 33110 DURING A PREFLIGHT INSPECTION OF THE SUBJECT AIRCRAFT, A PITCH CHANGE LINK BEARING (ATTACHED TO THE DRIVER END) APPEARED TO BE WORN. THE PILOT ATTEMPTED TO MOVE THE DRIVER TO CHECK FOR WEAR BUT THE BEARING, BOLT AND DRIVER WERE TIGHT. THE P ILOT THEN OBSERVED THE BEARING WHILE THE OTHER PILOT PULLED SLIGHTLY UP ON THE COLLECTIVE CONTROL. AS THIS OCCURRED, THE PILOT FOUND THAT THE BOLT AND BEARING WERE MOVING APPROXIMATELY .1875 INCH. FURTHER INSPECTION REVEALED THAT THE STEEL BUSHING ON THE DRIVER, TRAILING (NUT) SIDE, WAS WORN DOWN CONSIDERABLY (.0001 - .0002 INCH OF STEEL REMAINING). HAD THIS BEEN ALLOWED TO CONTINUE, THE BOLT WOULD HAVE STARTED TO WEAR INTO THE SOFTER METAL OF THE DRIVER, EVENTUALLY CAUSING L 1 G 7 2 4U 4 U H4SW E22EA 2007071100139 20070711 00139 EU 2007 7 11 AS350B3 1 20070628 G 6320 350A32031002 GEARBOX SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B1 60056 NE WARNING LIGHT B A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 EA 17 808CP 161 4151 23335 MGB CHIP LIGHT CAME ON IN FLIGHT. REMOVED CHIP PLUGS FROM THE MGB AND THE MAST FOUND PARTICLES ON THE MGB PLUG LESS THAN LIMITS CALLED OUT IN AEC AS350B3 SPM 20.08.01.601 NOTHING ON THE MAST PLUG. PERFORMED 10 MIN. HOVER AND RECHECKED CHIP PLUGS IAW AEC AS350B3 MWC 05.53.00.608 NO MORE PARTICLES FOUND AND NO RE-OCCURRENCE OF THE CHIP LIGHT. 1 G 7 1 3U 3 U H9EU E00054EN 2007121300285 20071213 00285 CE 2007 12 13 ATL07LA057 1 20070319 G 2810 FUEL CELL BEECH 95 95B55 1152729 CE CONT O470 IO470* 17026 SO RT WING LEAKING G E7TA E D ENGINE SHUTDOWN RETURN TO BLOCK K A FLUID LOSS FLAME/FIRE TX TAXI/GRND HDL 1 SO 11 500JP 2396 DURING START OF RT ENGINE, PILOT REPORTED HEARING A LOUD THUMP, NOTED FIRE COMING FROM THE BOTTOM OF THE RT COWLING. SH UTDOWN ENGINES, EVACUATED AIRCRAFT, AND NOTED APPARENT EXPLOSION HAD OCCURRED IN RT WING. VISUAL INSPECTION DID NOT R EVEAL CAUSE OF EVENT. WING STILL HELD APPROXIMATELY 40 GALLONS OF FUEL AND WAS NOT LEAKING ALTHOUGH BOX CELL LINER HAD BEEN CRACKED OPEN FROM FORCE OF EXPLOSION. FUEL TRUCK WAS DISPATCHED AND WING WAS FULLY TOPPED OFF TO INSPECT FOR LEAKS ; NONE WERE NOTED. AIR IN RT FUEL SYSTEM WAS DISPLACED AND AFTER APPROXIMATELY 10 MINUTES A LEAK WAS DETECTED IN THE R T WHEEL WELL. FURTHER INVESTIGATION REVEALED THIS LEAK WAS ORIGINATING FROM A B-NUT ON THE OUTPUT SIDE OF THE AUXILIARY 1 L 7 2 3O 3 O RT 3A16 E1CE 2007061500220 20070615 00220 CE 2007 6 15 B3OR2007131 1 20070511 G 2731 556545092 ACTUATOR CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ZONE 300 BINDING B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 26621 5500593 A NEWLY OVERHAULED ELEVATOR TRIM TAB ACTUATOR WAS BINDING AND WOULD NOT PROVIDE ADEQUATE DEFLECTION AT THE TRIM TAB ONCE INSTALLED. FURTHER INVESTIGATION REVEALED THAT THIS ACTUATOR HAD EXCESSIVE PLAY AT THE END BEARINGS AND THAT THE PRIMA RY SPROCKET PN WAS INCORRECT RELATIVE TO THE ASSEMBLY PN. THIS ASSEMBLY WAS OVERHAULED UNDER WORK ORDER NR 15356 ON 4/2/ 2002. THE ITEM WAS RETURNED TO THE OVERHAULING AGENCY FOR WARRANTY REPAIR. 1 L 7 2 4F 4 F A22CE E1NE 2007061500219 20070615 00219 CE 2007 6 15 B3OR2007138 1 20070518 G 2731 556545098 ACTUATOR CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ELEVATOR TRIM BINDING B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 26621 5500593 FOLLOWING INSTALLATION OF A NEWLY OVERHAULED ELEVATOR TRIM TAB ACTUATOR, PARTIAL BINDING OF THE ACTUATOR OCCURRED. FURT HER INVESTIGATION REVEALED THAT THIS ACTUATOR HAD EXCESSIVELY WORN END BEARINGS ALLOWING LATERAL PLAY IN INTERNAL JACKSC REWS SUFFICIENT TO CAUSE BINDING ONCE INSTALLED. ALSO DISCOVERED THAT THE LUBRICANT IN THIS ASSEMBLY WAS GREY IN COLOR, WHICH IS CONTRARY TO THE LOW MOISTURE CONTENT GREASE (PINK OR WHITE IN COLOR) STRICTLY SPECIFIED IN THE COMPONENT MM. T HIS ASSEMBLY WAS RECENTLY OVERHAULED UNDER WO NR 1059 ON 3/20/2007. 1 L 7 2 4F 4 F A22CE E1NE 2007080800028 20070808 00028 NM 2007 8 8 BAI71007 1 20070710 G 6300 A1902 BELT ROBSIN R22 R22BETAII 7640110 NM LYC O360 O360A1D 41514 EA M/R DRIVE BROKEN B B EMER. DESCENT R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SO 15 7109C 1085 2952 MAIN ROTOR DRIVE BELTS SEPARATED IN FLIGHT CAUSING THE CLUTCH ACTUATOR TO RUN EXCESSIVELY. THE OVER-TRAVEL LIMIT-SWITCH LANYARD WAS SEVERED BY A PORTION OF THE BROKEN BELTS AND DID NOT PERFORM IT'S INTENDED FUNCTION. THE PIC HAD TO DISABLED THE CLUTCH ACTUATOR SYSTEM BY PULLING THE CLUTCH CIRCUIT BREAKER AND THEN AUTO ROTATED TO THE GROUND. THERE WAS NO ADDI TIONAL DAMAGE TO THE AIRCRAFT OR INJURY TO OCCUPANTS AS A RESULT OF THE AUTOROTATION. 1 G 7 1 3O 3 O H10WE E286 2007012900195 20070129 00195 EA 2007 1 29 CA070103011 2 20070104 G 7250 TURBINE BLADES DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE FRACTURED W O OTHER R X PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT CR CRUISE 1 CA 41266 (CAN) ENGINE OIL PRESSURE AND TORQUE WERE SEEN TO FLUCTUATE IN FLIGHT FOLLOWED BY A LOUD NOISE AND AN ENGINE FLAMEOUT. SUBSEQUENT INSPECTION REVEALED METAL IN THE ENGINE OIL AND FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR THE INVESTI GATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103011) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007012900201 20070129 00201 GL 2007 1 29 CA070105004 2 20070105 G 7240 6899237 COMBUSTION CASE ALLSN 250C28B BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA CAE860657 CAE860657 (CAN) DURING A 200 HR INSPECTION A CRACK WAS FOUND IN THE ARM PIT AREA OF THE OUTER COMBUSTION CASE. CASE REPLACED. (TC NR 20070105004) 1 G 7 1 3U 3 U H2SW E1GL 2007050700240 20070507 00240 SW 2007 5 7 CA070105005 1 20070105 G 7921 206061432031 IMPELLER BELL BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL OIL COOLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA VN7184 (CAN) 300 HR NDT FOUND CRACKS IN THE WEB AREA. PART REPLACED. (TC NR 20070105005) 1 G 7 1 3U 3 U H2SW E1GL 2007050700241 20070507 00241 CE 2007 5 7 CA070105006 1 20070104 G 5610 10138402523 WINDSHIELD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL COCKPIT CRACKED W O OTHER O OTHER DE DESCENT 1 CA (CAN) DURING PRESSURIZED FLIGHT THE LT WINDSHIELD CRACKED IN SEVERAL PLACES ALL ALONG THE IB SECTION OF THE WINDOW. THE WINDOW WAS ORIGINALLY A REPAIRED WINDOW AND WAS INSTALLED FOR 1512.9HRS/1450CYCLES BEFORE FAILING. (TC NR 20070105006) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007012900202 20070129 00202 CE 2007 1 29 CA070105007 1 20070103 G 2435 66082019 SHAFT LEAR 35 35A 5170602 CE GARRTT TFE731 TFE73122B 01518 WP GENERATOR SHEARED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 616 (CAN) LT GENERATOR CAME OFF LINE .5 HR BEFORE LANDING . THE INDICATOR SHOWED 0 AMPS, A RESET WAS ATTEMPED BUT DID NOT CO ME ONLINE. WHEN MAINTENANCE REMOVED THE GENERATOR FOR INSPECTION, THE GENERATOR SHAFT WAS FOUND SHEARED. THE GENERATOR W AS INSPECTED FURTHER AND ROTATED FREELY. CAUSE OF SHEARED SHAFT IS UNKNOWN. (TC NR 20070105007) 2 L 7 2 4F 4 F A10CE E6WE 2007050800190 20070508 00190 CE 2007 5 8 CA070108001 1 20070103 G 3220 LANDING GEAR BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL NOSE INOPERATIVE W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA (CAN) AIRCRAFT EXPERIENCED NO NOSE GEAR. (TC NR 20070108001) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007050800191 20070508 00191 CE 2007 5 8 CA070108002 1 20070103 G 3260 404EN16 DOWNLOCK SWITCH BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL MLG MALFUNCTIONED W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA CVBCBNM7CXZZ (CAN) THE AIRCRAFT ORIGINALLY EXPERIENCED A GEAR WARNING SYSTEM FAILURE ON APPROACH. SUBSEQUENTLY, THE DOWNLOCK SWITCHE S WERE CLEANED AND LUBRICATED AND THE SYSTEM TESTED SERVICEABLE. THE NEXT FLIGHT HAD A LT MAIN GEAR INDICATION FAILURE, EMERGENCY PROCEDURES WERE FOLLOWED AND THE LT GEAR INDICATION WORKED PRIOR TO TOUCH DOWN. THE AIRCRAFT WAS RETURNED TO M AINTENANCE AND THE LANDING GEAR SYSTEM WAS TROUBLESHOT EXTENSIVELY AND TEST FLOWN EACH TIME WORK WAS CARRIED OUT UNSUCC ESSFULLY. THE SNAG ONLY OCCURRED AT HIGHER ALTITUDES OR COLDER TEMPERATURES. THE LT MAIN GEAR SWITCH WAS REPLACED DUE T O SUSPECT WATER PROPAGATION AND FREEZING. THE AIRCRAFT WAS TEST FLOWN AT THE SAME ALTITUDES AND WAS SUCCESSFUL. THE AIRC 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007012900204 20070129 00204 EA 2007 1 29 CA070108003 1 20070108 G 2910 TA3050052403 FAIRLEAD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE HYDRAULIC SYS WORN W K NONE O OTHER IN INSP/MAINT 1 CA 14717 14717 (CAN) DURING MAINTENANCE INSPECTION, FOUND FAIRLEAD (CLAMP) ON NR 1 HYDRAULIC SYSTEM LINES FAIRLEAD IN AFT FUSELAGE (APU COMPARTMENT) WORN. [IPC 29-11-00 FIG 15 (H) ITEM 395. BLOCK HAS 3 HOLES FOR CLAMPING HYDRAULIC LINES AND CENTER HOLE (P RESSURE LINE) MATERIAL WORN THROUGH TO CASE DRAIN LINE HOLE, ALLOWING PRESSURE LINE AND CASE DRAIN LINE TO START CHAFFIN G. SEVERAL SIMILAR CLAMPS IN THIS AREA ALSO EXHIBITING SIMILAR SIGNS OF WEAR. FAIRLEAD (CLAMP BLOCK) ASSEMBLY REPLACED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070108003) 2 L 7 2 4F 4 F RT A21EA E15NE 2007012900213 20070129 00213 WP 2007 1 29 CA070108009 2 20070105 G 7200 TPE33111U6 ENGINE FRCHLD SA227 SA227CC 3377522 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE LEFT DAMAGED W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION AP APPROACH 1 CA 366 (CAN) UPON SHORT FINAL A "POP" WAS HEARD SIMILAR TO THE SOUND OF A DOOR SEAL. THE AIRCRAFT YAWED A BIT YET NOT ENOEGH T O ALERT THE FLIGHT CREW THAT IT WAS ANYTHING MORE THAN TURBULENCE. OIL PRESSURE WAS NOTED TO BE DROPPING. AN ENGINE FAI LURE OCCURED ON THE LH SIDE. ENGINE WAS SHUT DOWN ON THE RUNWAY AND NOT IN THE AIR. UPON MAINTENANCE INITIAL REVIEW MO ST OF THE DAMAGE WAS AT THE BACK OF THE ENGINE. THERE WAS NO NOTED DAMAGE AT THE FRONT, GEARBOX, OF THE ENGINE. FURTHE R INVESTIGATION WIL BE CARRIED WHEN ENGINE ARRIVES AT THE OEM. MORE DETAILS THEN. (TC# 20070108009) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2007050900063 20070509 00063 CE 2007 5 9 CA070108010 1 20070105 G 5700 817861018 BOLT BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1437 (CAN) SCHEDULED WING BOLT INSPECTION, NOTED RT UPPER AFT WING BOLT CRACKED ON BOLT HEAD TO SHANK RADIUS. BOLT REPLACED WITH NEW. (TC NR 20070108010) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007012900219 20070129 00219 NM 2007 1 29 CA070109002 1 20070108 G 3040 INSULATION SIERRACIN 80260007 DHAV DHC8 DHC8* NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU WINDSHIELD HEAT OUT OF POSITION W H DEACTIVATE SYST/CIRCUITS W B INADEQUATE Q C SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 30 729 (CAN) INVESTIGATING SMELL OF SMOKE IN COCKPIT AFTER CREW TURNED ON WINDSHIELD HEAT. FOUND THE LUG ON 3041-TB1 POSITION L2 HAD INSULATION BETWEEN THE SCREW HEAD AND THE LUG. REMOVED THE INSULATION FROM UNDER THE HEAD OF THE SCREW. (TC NR 2 0070109002) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007012900222 20070129 00222 SO 2007 1 29 CA070109006 2 20070109 G 8530 AEC648005PL PISTON RING CESSNA 206 206CESSNA 2073302 CE CONT O520 IO520F 17032 SO ENGINE SEPARATED W O OTHER O OTHER NR NOT REPORTED 1 CA 1344 1344 (CAN) MATERIAL FROM THE FACE OF THE TOP COMPRESSION RING HAD FLAKED AWAY ON PISTONS NR1, NR2, NR4, AND NR6 (TC NR 200701 09006). 1 H 7 1 3O 3 O A4CE E5CE 2007012900224 20070129 00224 EA 2007 1 29 CA070110001 2 20070110 G 7200 ENGINE PWA PT6 PT6A34 52043 EA FAILED W O OTHER O OTHER CR CRUISE 1 CA 31612 7695 (CAN) (IFSD WITH MAJOR INTERNAL DAMAGE). THE ENGINE SUFFERED SEVERE DISTRESS WITH COMPLETE LOSS OF ALL TURBINE BLADES AN D ASSOCIATED STATIC COMPONENTS. THE GG CASE AND EXHAUST DUCT WERE SUBJECTED TO SEVERE TORQUE LOADS AND WERE FOUND DISTOR TED. ENGINE WAS CONVERTED STC SE96-02. DURING FLIGHT AND FOLLOWING A LOUD BANG FROM THE ENGINE, AN ENGINE SHUTDOWN WAS CARRIED OUT. CSN: 48301, CSO 10087 TSHSI: 64, CSHSI 25. THIS ENGINE CONVERTED VIA STC SE96-02 (TC NR 20070110001). 4 T E4EA 2007031200048 20070312 00048 NM 2007 3 12 CA070110004 1 20070109 G 3240 BRAKE DISC BFGOODRICH DHAV DHC5 DHC5A 2803018 NM NR 1 BRAKES DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 2492 411 (CAN) DURING B4 CHECK ON THE AIRCRAFT, THE NR 1 TIRE WAS REMOVED TO SERVICE THE WHEEL BEARINGS, AT THIS TIME, A PIECE OF THE BRAKE DISC FELL FROM THE BRAKE UNIT. THE BRAKE UNIT WAS REMOVED AND A SERVICEABLE ONE WAS INSTALLED. UPON INVESTIGA TION OF THE UNIT IT HAS BEEN DETERMINED THAT A BRAKE ADJUSTER HAD SEIZED RESULTING IN THE BRAKE DISC SITTING AT AN ANGLE INSTEAD OF AT 90 DEGREES TO THE AXLE LINE, THIS RESULTING FORCE CAUSED STRESS TO BE PLACED ON THE DISC RESULTING IN ITS FRACTURE, THIS ALSO CAUSED THE BRAKE PUCKS TO SCORE AND DAMAGE DISC FACE. IAW THE INSPECTION SCHEDULE, THE MAIN WHEELS ARE REMOVED EVERY 200 HOURS (B CHECK) TO INSPECT THE BRAKES AND WHEEL BEARINGS. THERE WAS NO FAULTS NOTED ON THE LAST B3 2 H 7 2 4T RT 2007012900229 20070129 00229 EA 2007 1 29 CA070111003 1 20070109 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE WING JAMMED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA (CAN) FLAPS FAILED ON APPROACH WHEN SELECTED TO 8 DEGREES, FLAPS DID NOT MOVE AND FLAP FAIL EICAS MESSAGE, OAT WAS -30 D EGREES ON APPROACH, DURING CRUISE -58 DEGREES C, FAULTS CODES BEING RETRIEVED AND AIRCRAFT BEING PREPARED FOR FERRY FOR FOLLOW UP. (801573 1/9/2007 19:04) RESET FLAP SYSTEM AND SELECT FLAPS TO 8 DEGREES FOR FERRY FLIGHT, REFERENCE RJ-SL-27- 077 (801573 1/9/2007 20:14). FLAPS RESET. AIRCRAFT FERRIED (803789 1/10/2007 07:29) (TC NR 20070111003). 2 L 7 2 4F 4 F RT A21EA E15NE 2007012900230 20070129 00230 EA 2007 1 29 CA070111004 1 20070110 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE WING JAMMED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA (CAN) CREW REPORTED ON SHORT FINAL, WHEN SELECTING FLAPS TO 8 DEGREE THE FLAP FAIL MESSAGE APPEARED AND THE FLAPS DID NO T MOVE OUT OF 0 DEGREE. MAINTENANCE UNABLE TO GET CODES. A/C FERRIED FOR FURTHER INVESTIGATION AND TROUBLESHOOTING. (TC NR 20070111004) 2 L 7 2 4F 4 F RT A21EA E15NE 2007012900231 20070129 00231 EA 2007 1 29 CA070111005 1 20070110 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE WING JAMMED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA (CAN) FLAPS SELECTED TO 8 DEGREES, NO ISSUES, THEN SELECTED TO 20 DEGREES, NO ISSUES, FLAPS 30 SELECTED NO ISSUES, UPON SELECTION TO 45 DEGREES, FLAP FAIL AND THE FLAPS LOCKED AT 30 DEGREES, OAT -30 IN FLIGHT, - 15 DEGREES OPN APPROACH, TEM P WAS -15. HAS OBTAINED FAULT CODES AND THEY HAVE BEEN FORWARDED TO TECH OPS (803789 1/10/2007 17:14). A/C GROUNDED FOR FURTHER INVESTIGATION AND TROUBLESHOOTING. (TC NR 20070111005) 2 L 7 2 4F 4 F RT A21EA E15NE 2007012900232 20070129 00232 EA 2007 1 29 CA070111006 1 20070110 G 2750 FLAP CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE WING FROZEN W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 CA (CAN) FLAP FAIL AT 20. ON APPROACH, ON FLAP EXTENSION, THEY FROZE AT 20 DEGREES. OAT WAS ABOUT -25 DEGREES C AT THE TI ME, ALTHOUGH THEY WERE ABOUT 1 HOUR AND 10 MINUTES IN FLIGHT AT ABOUT -50 DEGREES FOR MOST OF THE FLIGHT. AIRSPEED WAS 1 70 KNOTS AT THE TIME OF THE FAILURE. (TC NR 20070111006) 2 L 7 2 4F 4 F RT A21EA E15NE 2007012900233 20070129 00233 GL 2007 1 29 CA070111010 3 20070108 G 6110 HCB4MP3A PROPELLER HARTZL HCB4M HCB4MP3 GL DAMAGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 16787 32 (CAN) PROPELLER WAS RECEIVED FOR COMPLIANCE WITH AD 2006-24-07. PROPELLER PREVIOUSLY OVERHAULED ON SEPTEMBER 20, 2000. T HE PROPELLER WAS DISSASSEMBLED AND THE FOLLOWING FINDINGS WERE CORRECTED. (4) LOW STOP RODS WERE CORRODED BEYOND REPAIR . (4) BLADE CLAMP ASSEMBLIES WERE REPLACED DUE TO CORROSION AND LACK OF PLATING. PISTON HAD A CORROSION PIT IN FELT RING GROOVE. HUB WAS REPLACED DUE TO CORROSION/RUST IN PILOT TUBES. NR 4 BLADE HAD WATER IN BLADE BORE BEHIND GREASE BUT NO EVIDENCE OF CORROSION. COUNTERWEIGHT BOLTS WERE ALL RUSTED AND WATER WAS FOUND IN BLADE CLAMP COUNTERWEIGHT BOLT HOLES. (TC NR 20070111010) 6 C P56GL 2007012900234 20070129 00234 EA 2007 1 29 CA070111011 1 20070110 G 2750 FLAP CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE WING OBSTRUCTED W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 CA (CAN) FLAPS FAILED ON RETRACTION AFTER LANDING L 5 DEG, R 6 DEG. AFTER LANDING, FOUND SNOW COMPACTED, ALL SNOW REMOVED, FLAPS CYCLED. (TC NR 20070111011) 2 L 7 2 4F 4 F RT A21EA E15NE 2007012900235 20070129 00235 EU 2007 1 29 CA070111012 1 20070111 G 5610 WINDOW BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU COCKPIT CRACKED W A UNSCHED LANDING M OVER TEMP CL CLIMB 1 CA (CAN) DURING CLIMB THE FIRST OFFICERS MAIN WINDOW CRACKED. THE AIRCRAFT RETURNED TO POINT OF DEPARATURE WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE WINDOW AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070111012) 2 L 7 2 3T 4 T A24EU A196 6 C P899 2007012900236 20070129 00236 EA 2007 1 29 CA070111013 2 20070108 G 7310 FUEL LINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA ENGINE CHAFED W K NONE K FLUID LOSS NR NOT REPORTED 1 CA (CAN) THE FLIGHT CREW REPORTED FUEL LEAKAGE FROM THE RT ENGINE AREA AFTER SHUTDOWN. THE ENGINE COWLING WAS REMOVED AND I NVESTIGATION HAD SHOWN THAT THE ENGINE DRIVEN FUEL PUMP TO FCU LINE HAD CHAFED AN THE BACK EDGE OF THE FCU. THE LINE IS ON CONDITION AND NOT A TIMED UNIT. A FLEET CAMPAIGN AND TECHNICAL INFORMATION BULLETIN WAS RELEASED TO ENSURE CORRECT ROUTING OF THE LINE AND ADEQUATE PROTECTION. ANY SUSPECT LINES REPLACED. (TC NR 20070111013) 2 L 7 2 4T 4 T RT A24CE E4EA 2007012900238 20070129 00238 NE 2007 1 29 CA070111015 2 20070111 G 7310 3035987 FUEL LINE DHAV DHC8 DHC8202 2809007 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE ENGINE CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) FUEL LEAK AT ENGINE FIREWALL PRESSURE LINE. THE LINE WAS DAMAGED BY CHAFFING ON COLLAR (P/N 3043536-01A) AND RETAI NING PLATE (P/N 3043535-01). POST SB21460. 2 OTHER LINES COVERED BY THE SAME SB (INCORPORATED IN DEC.2001) SHOWED SAME DAMAGE AND NEEDS REPLACEMENT. (TC NR 20070111015) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007012900239 20070129 00239 2007 1 29 CA070111017 4 20070104 G 2360 STRUCTURE BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33112UHR WP ROTOL R333 R333482F12 GL FUSELAGE UNBONDED W O OTHER G MULTIPLE FAILURE CR CRUISE 1 CA (CAN) CREW REPORTED THAT WHEN THE AIRCRAFT ENTERED INTO A CLOUD, THE RADIOS BECAME UNREADABLE. ALL RADIO NAVIGATION EQUI PMENT BECAME UNRELIABLE AS WELL AS THE GPS SYSTEM. AIRCRAFT ARRIVED AT MTC. BASE AND AVIONICS STATIC SPECIALIST CONTRACT ED. P-STATIC TEST CARRIED OUT AND FOUND BONDING ISSUES ON MULTIPLE AIRFRAME COMPONENTS. REPAIRS CARRIED OUT AND P-STATIC TEST CARRIED OUT AGAIN. NO FURTHER FAULTS. (TC NR 20070111017) 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C P61GL 2007050900064 20070509 00064 CE 2007 5 9 CA070111018 1 20070109 G 3233 5082021811 SHAFT BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL NLG CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) THE NOSE GEAR ACTUATOR WAS REMOVED TO PERFORM AN END PLAY CHECK. THE NOSE GEAR RETRACT DRIVE SPROCKET AND SHAFT ( PN 50-820218-11) ASSEMBLY WAS REMOVED FOR CLEANING. INSPECTION OF THE DRIVE SPROCKET AND SHAFT FOUND THAT A CRACK HAD FO RMED ON THE END DIAMETER (.745) THAT ENGAGES THE SUPPORT BEARING. THE CRACK STARTS AT THE END OF THE SHAFT, EXTENDS AXIA LLY FOR .350 AND THEN EXTENDS RADIALLY FOR ANOTHER .400. THE CRACK HAS THE APPEARANCE OF STRESS CORROSION. THE TOTAL TIM E AND TOTAL CYCLES OF THIS PART IS UNKNOWN. (TC NR 20070111018) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007050900066 20070509 00066 EU 2007 5 9 CA070112002 1 20070106 G 5540 9408328506 BEARING PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL RUDDER WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION OF TAIL TOP ATTACH BOLT FOUND TO HAVE EXCESSIVE WEAR. RUDDER REMOVED AND NEW BOLT P/N 932.35.71. 166 AND BEARING REPLACED. MFG AIRCRAFT NOTIFIED OF DEFECT. (TC NR 20070112002) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007082000032 20070820 00032 SW 2007 8 20 CA070112003 1 20070111 G 5610 2719442003 WINDSHIELD SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3016 (CAN) UPON LANDING THE FLIGHT CREW WITNESSED THE LT HEATED WINDSHIELD CRACK FROM THE LOWER RT CORNER TO THE UPPER CENTER PORTION OF THE WINDOW. THE LANDING WAS REPORTED AS NORMAL AND NO ABNORMAL INDICATIONS WERE NOTICED PRIOR TO FAILURE OF THE WINDOW. UPON INSPECTION BY MAINTENANCE, THE WINDOW WAS FOUND CORRECTLY INSTALLED AND TRIMMED TO FIT CORRECTLY. THE ATTACHING SCREWS WERE TORQUE CHECKED AND A FEW WERE FOUND SLIGHTLY UNDERTORQUED. IT IS UNLIKELY THIS CAUSED THE FAILURE AS THIS OPERATOR HAS HAD SEVERAL IN FLIGHT HEATED WINDSHIELD FAILURES WITHIN THE LAST 24 MONTHS. ANOTHER OPERATOR OPERAT ING SIMILAR AIRCRAFT IN THE PNR HAS REPORTED INCREASED FAILURES AS WELL OF THESE HEATED WINDSHIELDS. THE WINDSHIELD IS B 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 2007012900242 20070129 00242 NE 2007 1 29 CA070112004 3 20070110 G 6112 RELAY DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PROPELLER DE-ICE FAULTY W O OTHER M OVER TEMP TX TAXI/GRND HDL 1 CA (CAN) WHEN AIRCRAFT POWER APPLIED, BLADES NR 2 AND NR 4 ON LT PROP HEATED AND BURNED OUT THE HEATER ELEMENTS. FOR PRECA UTION RELAYS P/N KC-D4N AND E-387-C1 WERE REPLACED AND AIRCRAFT WAS TESTED WITH NO FAULTS FOUND. AIRFRAME HOURS=44789:11 . CYCLES=48426. (TC NR 20070112004) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007082000033 20070820 00033 EU 2007 8 20 CA070113001 1 20070102 G 5344 5531412027 HINGE PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL PAX DOOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 7953 7953 (CAN) AFTER A HEADS UP CONDITION FROM ANOTHER RCMP AIR SECTION. AN INSPECTION OF CONDITION WAS CARRIED OUT ON MPI. THE PART INSPECTED WAS FOUND SEVERELY CORRODED AND IF LT UNCHECKED COULD AFFECT THE INTEGRITY OF THE CABIN DOOR FRAME. THE HINGE PLATE MOUNTED AT THE BASE OF THE AIRSTAIR DOOR OPENING AND IS RIVETED TO THE DOOR SILL ASSY. APPROXIMATELY 50 PER CENT OF THE HINGE WAS AFFECTED BY CORROSION. THE CAUSE IS THOUGHT TO BE FROM SALT ON PASSENGER BOOTS IN WINTER OPERATIO NS. THE HINGE IS DIFFICULT TO INSPECT UNTIL DERIVATE FROM THE DOOR SILL ASSY.THE MFG HAD SEALED BETWEEN THE HINGE ASSY AND THE DOOR SILL WITH PRC AND THIS PREVENTED DOOR SILL DAMAGE. (TC NR 20070113001) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007012900245 20070129 00245 SO 2007 1 29 CA070114001 2 20070109 G 8530 EXHAUST VALVE CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL ENGINE LEAKING W K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CA 327 (CAN) DURING ENGINE PERFORMANCE GROUND RUN AFTER INSPECTION, ENGINE WAS RUNNING ROUGH. ENGINE COMPRESSION CHECK CARRIED OUT AND CYLINDER NR 3 FAILED COMPRESSION CHECK AND AIR WAS LEAKING FROM THE EXHAUST. ROUGH RUNNING DURING TAKEOFF WAS A LSO REPORTED BY PILOT PREVIOUSLY WHICH COULD NOT BE CONFIRMED DURING GROUND-RUN AT THAT TIME AND AIRCRAFT WAS TEST FLOWN SATISFACTORY. (TC NR 20070114001) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2007012900246 20070129 00246 EU 2007 1 29 CA070114002 2 20070112 G 7230 GEJ818P060A BOLT CFMINT CFM563 CFMINT CFM56 CFM563B2 13802 EU FAN DISK CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 722356 (CAN) ENGINE WAS INDUCTED INTO SHOP FOR SCHEDULED MAINTENANCE. DURING THE SHOP VISIT THE FAN DISK WAS REMOVED FROM THE F AN ASSEMBLY AND ROUTED FOR OVERHAUL. THE DISK ATTACH BOLTS (QTY 30) WERE ROUTED FOR NDT INSPECTION. FPI DETECTED ONE FA N DISK ATTACH BOLT WAS CRACKED FROM THE HEAD AND EXTENDING AXIALLY INTO THE SHANK. FURTHER INSPECTION WITH A 10X MAGNIF YING GLASS REVEALED THAT THE CRACK HAD PROPAGATED FROM A FAINT AXIAL LINE ON THE SIDE OF THE HEAD THAT INITIALLY APPEARS TO BE A MFG DEFECT. A SECOND BOLT (NOT CRACKED) WAS FOUND WITH THE IDENTICAL AXIAL LINE (SAME DIMENSION AND ANGLE) IN THE BOLT HEAD. REMAINING 28 BOLTS HAD NO DEFECTS NOTED. ALL BOLTS INITIALLY APPEARED IN GOOD CONDITION WITH NO EVIDENCE 4 F E21EU 2007050900067 20070509 00067 2007 5 9 CA070114003 4 20070104 G 3442 066311400 INDICATOR BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL WEATHER RADAR MALFUNCTIONED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA BB1343 (CAN) CREW REPORTS THAT IN CRUISE NOTED THE WEATHER RADAR FAILED AND IMMEDIATELY BOTH MAIN GENERATOR BUSES FAILED. CREWS RESET GENERATORS AND MONITORED BUS VOLTAGES AND LOADS, NORMAL. CREW THEN NOTED THE 28VDC CIRCUIT BREAKER POPPED ON THE AVIONICS BUS FOR THE WEATHER RADAR. BREAKER RESET BUT INDICATOR UNSERVICEABLE. AFTER AIRCRAFT RETURNED TO MTC BASE, MAIN TENANCE CREW INSPECTED ELECTRICAL SYSTEM WITH NO FAULTS FOUND. RADAR INDICTOR REPLACED AND F/C NORMAL. UNSERVICEABLE WEA THER RADAR SENT TO REPAIR FACILITY WITH DETAILS OF INCIDENT AND REQUEST FOR WORK / STRIP REPORT. (TC 20070114003) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007082000034 20070820 00034 EU 2007 8 20 CA070115001 1 20070109 G 2500 INSULATION PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL FUSELAGE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 CA 7963 7962 (CAN) DURING AN INTERIOR REFURBISHMENT IT WAS NOTED THE FUSELAGE INSULATION FROM THE CABIN FLOOR AND UP HAD BADLY DEGRAD ED INSULATION BAGS. THE THERMAL ACOUSTIC FOAM IS SURROUNDED BY BAGS WITH A VAPOR FOIL ON THE INNER SURFACE AND SEALED T O A THIN LATEX TYPE BARRIER ON THE OB SURFACE. THE OUTER SURFACE HAD RUPTURED AND DEGRADED ON ALL OUTER SURFACES OF TH E INSULATION BAGS. ALL CABIN INSULATION HAD TO BE REMOVED AND REPAIRED WITH THE APPROVED TAPE. IF LEFT UNCHECKED THIS COULD ADD A CORROSION PROBLEM WITHIN THE FUSELAGE AS MOISTURE HAD WICKED INTO THE INSULATION IN SOME AREAS. IF THE A/C WAS NOT HANGARED EACH NIGHT FOR DRYING IT COULD POSE A WEIGHT PROBLEM THAT WOULD BE UNKNOWN TO FLIGHT AND MAINTENANCE C 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007050900069 20070509 00069 SO 2007 5 9 CA070115002 1 20070109 G 2140 D405065D793 HEATER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL CABIN FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 649 (CAN) PILOT REPORTED EXHAUST ODOR WHEN FRONT COMBUSTION HEATER WAS OPERATING. SOOT COLLECTED ON THE PILOT AND CO-PILOT W INDSHIELDS ABOVE THE DEFROST VENTS. COMPLETED A HEATER DECAY TEST WHICH CONFIRMED THE BURNER CAN WAS DEFECTIVE. REMOVED THE HEATER FROM THE AIRCRAFT AND DISCOVERED 2 HOLES IN THE BURNER CAN APPROXIMATELY .5 INCH WIDE AND OPEN ABOUT .2500 I NCH. HEATER WAS REPLACED WITH OVERHAULED UNIT AND AIRCRAFT RETURNED TO SERVICES. (TC NR 20070115002) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007012900255 20070129 00255 EA 2007 1 29 CA070115003 1 20070113 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE WING JAMMED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) FLAPS FAILED UPON SELECTION TO 8 DEGREES, THEY DID NOT MOVE FROM 0 DEGREES, OAT -46 AT ALTITUDE, - 15 DEGREES ON A PPROACH. AIRCRAFT LANDED FLAPS ZERO. (TC NR 20070115003) 2 L 7 2 4F 4 F RT A21EA E15NE 2007050900070 20070509 00070 NE 2007 5 9 CA070115004 2 20070115 G 7200 ENGINE AIRBUS 320 A320214 3930316 EU CFMINT CFM56 CFM565B4P NE NR 1 FAILED W C ABORTED TAKEOFF Y J ENGINE STOPPAGE WARNING INDICATION TO TAKEOFF 1 CA 757267 (CAN) AFTER POWER SET FOR TAKEOFF, AND TAKEOFF ROLL COMMENCED, ENG NR 1 FAILED. AIRCRAFT TAXIED BACK TO THE GATE. (TC N R 20070115004) 2 L 7 2 4F 4 F RT A28NM E38NE 2007012900257 20070129 00257 2007 1 29 CA070115005 4 20070115 G 2562 E01G1 ELT CABIN FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) OVER THE LAST YEAR, HAVE HAD SEVERAL ACK ELTS E-01 WITH FAULTY (G) SWITCHES. FAULTS INCLUDE: INTERMITTENT ACTIVAT ION, LIGHT ACTIVATION, NO ACTIVATION ACK HAS NO PUBLISHED DATA ON ACTIVATION BUT USES SIMILAR (G) SWITCH TO THE ELT WHIC H HAS A PUBLISHED ACTIVATION OF 2 (GS). HAVE ALSO SEEN SIMILAR FAULTS WITH ELTS. (TC NR 20070115005) 2007012900261 20070129 00261 EA 2007 1 29 CA070115007 2 20070112 G 8530 CYLINDER LYC LTIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE SEPARATED W B A EMER. DESCENT UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 2175 L787161A (CAN) ON THE CLIMB OUT A LOSS OF POWER OCCURED ON THE RT ENGINE. THE MANIFOLD PRESSURE DROPPED FROM TAKEOFF POWER TO 30 INCHES. (TC NR 20070115007) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007050900076 20070509 00076 SW 2007 5 9 CA070115014 1 20070102 G 5730 204382 SKIN AIRTRC AT802 AT802 0390305 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MA3 GL WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 452 (CAN) DURING ANNUAL INSPECTION SEVERAL CRACKS WERE DETECTED AT THE RIVET HOLES WHERE THE FLAP BAY SKIN (PN 20438-2) ATTA CH TO THE RIB FLANGES. CRACKS WERE STOP DRILLED AND PLATE INSTALLED OVER THE RIB FLANGE AREA IAW AIR TRACTOR INSTRUCTIO NS (ATTACHED). THIS PROBLEM HAS BEEN FOUND ON EARLY SN AIRCRAFT (802-001 - 802A-0014), SUBSEQUENT S/N HAD EXTRA RIVETS INSTALLED BY MFG. THIS AIRCRAFT S/N IS 802-0121. (TC NR 20070115014) 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2007082000037 20070820 00037 CE 2007 8 20 CA070115015 1 20070112 G 5340 50110131 MOUNT CESSNA 401 401 207590C CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C* GL MLG GEARBOX LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED LANDING GEAR ROUTINE INSPECTION, LANDING GEAR ACTUATOR GEARBOX MOUNTING BOLTS (3) FOUND MISSING A ND REMAINING (1) BOLT FOUND SHEARED. EMERGENCY GEAR OPERATION ATTEMPTED TO RELOCATE GEAR. EMERGENCY OPERATION INHIBITED DUE TO IMPROPER GEARBOX ALIGNMENT. GEAR REPOSITIONED AND GEARBOX AND LANDING GEAR SYSTEM INSPECTED FOR CONDITION. NEW MOUNTING BOLTS INSTALLED AND GEAR SYSTEM NORMAL AND EMERGENCY TESTED SERVICEABLE. (TC NR 20070115015) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2007012900304 20070129 00304 EA 2007 1 29 CA070115016 1 20070112 G 2731 C6CF14053 CONTROL CABLE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL ELEVATOR TRIM BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TRIM CABLE WAS FOUND BROKEN AND WAS REPLACED. THE BROKEN CABLE IS BEING ANALYZED AT THEIR LOCAL AIRWORTHINESS AUTH ORITY AND WE AWAIT THE RESULTS. (TC NR 20070115016) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2008030600281 20080306 00281 CE 2008 3 6 CA070115017 1 20070112 G 5312 97440019101 STIFFENER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL BULKHEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 16398 BB84 (CAN) SPECIAL INSP NR53 WAS COMPLETED IAW MM 5-20-05, WHICH INVOLVES THE FOLLOWING: AFT FUSELAGE AREA AND REAR PRESSUR E BULKHEAD. INSPECT THE ENTIRE FWD AND AFT SIDE OF THE REAR PRESSURE BULKHEAD FOR CRACKS AND LOOSE OR MISSING RIVETS. C HECKED OXYGEN BOTTLE MOUNTING BRACKETS FOR CRACKS AND LOOSE OR MISSING RIVETS. CHECKED OUTFLOW AND SAFETY VALVE BOX FOR CRACKS AND LOOSE OR MISSING RIVETS. THE INSP INTERVAL IS INITIALLY 10,000 CYCLES AND AT 500 CYCLES THERE AFTER. DURING THIS INSP OF THE REAR PRESSURE BULKHEAD (F.S. 347.75) THE AFT ZEE STIFFENER (P/N:97-440019-101) WAS FOUND CRACKED. THE C RACK WAS LOCATED AT THE LOWER ATTACH POINT OF THE OXYGEN BOTTLE SUPPORT (P/N: 50-560019-13) WHICH ATTACHES TO THE ZEE ST 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007050900077 20070509 00077 SW 2007 5 9 CA070117003 1 20070115 G 5610 2719442004 WINDSHIELD SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE COCKPIT DELAMINATED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 2751 (CAN) DURING FLIGHT THE FLIGHT CREW HEARD A LOUD CRACK FROM THE RT HEATED WINDSHIELD. THEY IMMEDIATELY NOTICED THE WINDO W PANES BEGIN TO DELAMINATE. NO OBJECT WAS WITNESSED HITTING THE AIRCRAFT OR WINDSHIELD. THE AIRCRAFT LANDED SAFELY AND THEN RETURNED TO BASE ON A FLIGHT PERMIT FOR REPAIRS. NO CRACKING IN THE WINDOW WAS EVIDENT. THE WINDOW WAS REPLACED BY MAINTENANCE. (TC NR 20070117003) 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 2007012900307 20070129 00307 EA 2007 1 29 CA070117005 2 20070117 G 7320 C6CF14043 CABLE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA DAMAGED W O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) NEW CABLE, THE BALL END OF THE TRIM CABLE IS OUT OF ROUND AND WILL NOT FIT INTO THE TRIM JACK ASSEMBLY. WHERE THE CABLE MEETS THE BALL END IT HAS BEEN BRAZED AND THE CABLE HAS NOW FRAYED AFTER ATTEMPTING TO INSTALL IT INTO HTE TRIM JA CK ASSEMBLY. (TC NR 20070117005) 1 H 7 2 3T 4 T RT A9EA E4EA 2007050900078 20070509 00078 WP 2007 5 9 CA070117006 1 20070117 G 6310 C1883 SPRAG CLUTCH ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 933 (CAN) DURING AN AES 1000HR INSPECTION, A CRACK WAS FOUND ON THE CAGE IN THE MIDDLE OF (1) CROSSBAR. (TC NR 20070117006) 1 G 7 1 3O 3 O H11NM 1E4 2007050900186 20070509 00186 EA 2007 5 9 CA070117007 1 20070115 G 5610 601R3303311 WINDOW CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 9980 (CAN) PILOT SIDE WINDOW INNER LAYER CRACKED. SIDE WINDOW ACC AMM 56-12-01 REPLACED. OPERATIONAL TEST OF WINDOW TEMP CON TR. DO A LEAK TEST OF LT SIDE WINDOW AFTER REPLACEMENT ACC AMM 56-12-400-801 A01 PERFORMED SATISFIED (TC NR 20070117007 ) 2 L 7 2 4F 4 F RT A21EA EOOO63EN 2007050900187 20070509 00187 EA 2007 5 9 CA070117008 1 20070115 G 3213 7339FT160T SEAL BFGOODRICH CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C1 NE NLG STRUT LEAKING W O OTHER O OTHER AP APPROACH 1 CA SPP510096 (CAN) FLIGHT 5663 DEPARTED WITH 65 PASSENGERS ON BOARD WITH NO ISSUES NOTED. ON APPROACH, AFTER GEAR DOWN SELECTION CRE W NOTED A NWS INOP CAUTION MESSAGE. TO GIVE THEMSELVES TIME TO GO THROUGH THE NWS INOP MESSAGE, THEY CARRIED OUT A GO A ROUND. AS THEY FLEW BY THE RUNWAY, THE TOWER INFORMED THEM THAT THE NOSEWHEELS APPEARED TO BE TURNED 90 DEGREES. AN AC FLYING NEARBY OFFERED TO FLY BY THE AIRCRAFT AND INSPECT THE NOSE GEAR. THE PILOT REPORTED THAT THE NOSE GEAR WHEELS W ERE OFF CENTER BY 20 DEGREES. AT THE GATE MAINTENANCE INSPECTED THE NOSE GEAR AND FOUND THAT THE STRUT WAS FLAT. MAINT ENANCE SERVICED THE STRUT AND NOTED THAT THE STRUT WAS LEAKING. STL MAINTENANCE IS DISPATCHING MAINTENANCE AND SEALS TO 2 L 7 2 4F 4 F RT A21EA EOOO63EN 2007050900188 20070509 00188 CE 2007 5 9 CA070118001 1 20070115 G 5542 04330106 SKIN CESSNA CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL RUDDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE DOING 100 HR INSPECTION ON AIRCRAFT, MECHANIC NOTICED THAT THERE WAS A CRACK BY THE LIGHTING HOLE BELOW THE TOP HINGE ATTACH BRACKET. NEW SKIN ORDERED AND WHEN RECEIVED NOTICED THAT MFG HAS REMOVED THIS LIGHTING HOLE. REST OF A IRCRAFT OF THIS TYPE IN FLEET WILL BE INSPECTED FOR THIS SAME DAMAGE. (TC NR 20070118001) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2007050900189 20070509 00189 EA 2007 5 9 CA070118002 1 20070117 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE TE FLAPS MALFUNCTIONED W O OTHER O OTHER AP APPROACH 1 CA (CAN) THE CREW REPORTED A FLAP FAIL MESSAGE ON APPROACH. THE CREW SELECTED FLAP 8 AND FLAP FAIL MESSAGE CAME ON IMMEDIAT ELY AND THE FLAPS FROZE AT 0 DEGREES INDICATED. ON THE GROUND A CB RESET WAS CARRIED OUT AND THE CODES WERE OBTAINED . T HE AIRCRAFT WAS FERRIED WHERE AN INVESTIGATION IS STILL ONGOING BY LINE MAINTENANCE (TC NR 20070118002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007012900308 20070129 00308 SO 2007 1 29 CA070118003 2 20070110 G 7314 6467582 PUMP PIPER PA28 PA28R201T 7102813 SO CONT O360 TSIO360F 17025 SO HARTZL HCC2Y BHCC2YF1 GL ENGINE FAULTY W O OTHER J WARNING INDICATION NR NOT REPORTED 1 CA 1056 (CAN) ENGINE DRIVEN FUEL PUMP OUTPUT IS LOW AT RATED RPM 2600. (TC NR 20070118003) 1 L 7 1 3O 3 O 2A13 E9CE 5 C P920 2007012900309 20070129 00309 GL 2007 1 29 CA070118004 3 20070112 G 6110 B2222 PLATE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE2Y HCE2YR2 GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3850 2009 (CAN) PROPELLER RECEIVED FROM CUSTOMER FOR ROUTINE OVERHAUL. PROPELLER DISMANTLED, PARTS NDT INSPECTED AND CRACK FOUND. NO AD`S OR BULLETIN`S ON THAT PART. (TC NR 20070118004) 1 L 7 2 3O 3 O A20SO E14EA 5 C P9EA 2007012900310 20070129 00310 EA 2007 1 29 CA070118005 2 20070103 G 7320 3027791 SENSE LINE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE BROKEN W O OTHER J WARNING INDICATION CL CLIMB 1 CA 5597 PCE85142 (CAN) P3 TUBE SUDDENLY BROKEN WHILE AIRCRAFT WAS IN CLIMB. ENGINE FAIL TO IDLE, ENGINE WAS SHUTDOWN BY THE CREW. AIRCRA FT RETURN TO DEPARTURE AIRPORT WITHOUT OTHER DIFFICULTY. (TC NR 20070118005) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007050900190 20070509 00190 WP 2007 5 9 CA070118006 1 20070117 G 6210 369D21100516A BLADE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2813 (CAN) THE UPPER BLADE SURFACE IS CRACKED CHORDWISE FROM LEADING EDGE TO TRAILING EDGE BETWEEN BLADE STATION 120 AND 124. THE LOWER BLADE SURFACE IS ALSO CRACKED IN THE MID CORD AREA BETWEEN STATION 120 AND 124 BUT DOES NOT EXTENT TO THE LEA DING EDGE OR TRAILING EDGE. (TC NR 20070118006) 1 G 7 1 3U 3 U H3WE E4CE 2007051100005 20070511 00005 EA 2007 5 11 CA070118008 1 20070117 G 2752 852D10019 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE TE FLAPS CONTAMINATED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 6959 6959 (CAN) ON APPROACH CREW REPORTED A FLAPS FAIL MESSAGE AFTER SELECTION TO 8 DEGREES. FLIGHT COMPLETED A FLAPLESS LANDING W ITHOUT INCIDENT. AIRCRAFT THEN COMPLETED A FERRY FLIGHT. TROUBLESHOOTING OF FAULT CODES AND REPAIRS CURRENTLY ONGOING BY MAINTENANCE. THE RT IB FLAP ACTUATOR WAS REPLACED DUE TO NOT ACCEPTING GREASE. SUSPECT MOISTURE INGRESS HAD FROZEN INSI DE ACTUATOR. AS PART OF REPAIRS MOD IS601R227530052 REV B: FLAP DRIVE SYSTEM-ALTERNATE METALLIC SEAL FOR FLEXIBLE DRIVE SHAFT WAS INCORPORATED. (TC NR 20070118008) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100006 20070511 00006 EA 2007 5 11 CA070118009 1 20070116 G 2910 AE7090072 LINE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE NR 2 EDP LOOSE W O OTHER E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION CR CRUISE 1 CA MX598642 (CAN) ENROUTE CREW ADVISED THAT THEY HAD LOST NR 2 HYDRAULIC SYSTEM AND WERE DIVERTING. CREW DECLARED AN EMERGENCY AN D ADVISED PASSENGERS OF REASON. WHEN THE INCIDENT HAPPENED THE CREW HAD A HYD 2 LOW PRESSURE MESSAGE, WHEN THEY TURNED O N NR 2 PUMP (HYD PUMP 2A) MESSAGE WAS CONTINUOUSLY ON. A FEW MINUTES LATER ALL NR 2 HYD QUANTITY WAS LOST. MAINTENANCE INSPECTION REVEALED THAT THE QUICK DISCONNECT FITTING ON THE CASE DRAIN LINE TO THE NR 2 PUMP WAS LEAKING AROUND THE BAS E OF THE COUPLER. ONCE ALL THE FLUID LEAKED OUT IT STARVED THE PUMP CAUSING IT TO MAKE METAL CAUSING ENGINE VIBRATION A ND EVENTUALLY SEIZE. THE CASE DRAIN LINE, NR2 EDP, PRESS AND CASE DRAIN FILTERS WERE REPLACED AND AIRCRAFT WAS FUNCTION 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100007 20070511 00007 EU 2007 5 11 CA070118010 1 20070118 G 5302 350A13111620 BOLT SNIAS 350 AS350B1 8680811 EU TMECA ARRIEL ARRIEL1D NE TAILBOOM DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) THIS IS (1) OF (2) BOLTS USED TO RETAIN THE HORIZONTAL STAB. TO THE TAIL BOOM OF THE HELICOPTER. THE THREADED SEC TION OF THE BOLT AND THE NUT WERE FOUND MISSING. IT APPEARS THAT THE THREADED SECTION OF THE BOLT HAD BEEN CRACKED FOR SOME TIME BEFORE DEPARTING. (TC NR 20070118010) 1 G 7 1 3U 3 U H9EU E19EU 2007051100008 20070511 00008 EU 2007 5 11 CA070118011 1 20070104 G 6730 AC67244 SERVO SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ROTOR UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 1263 (CAN) DURING HYDRAULIC PRE-FLIGHT CHECK CAUSED CYCLIC TO MOVE 4-5 INCHES TOWARDS 8 O’CLOCK POSITION. SERVO REMOVED SERV ICEABLE UNIT INSTALLED. SERVO SENT OUT FOR REPAIR AWAITING TEARDOWN REPORT. (TC NR 20070118011) 1 G 7 1 3U 3 U H9EU E19EU 2007051100009 20070511 00009 EA 2007 5 11 CA070119001 1 20070117 G 5610 NP1393229 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6269 (CAN) SEVERAL CRACKS IN LT SIDEWINDOW INNER AND CENTER. A/C AOG LT SIDEWINDOW CHANGED ACC AMM. ALL TESTS SATISFIED (TC N R 20070119001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007012900311 20070129 00311 EU 2007 1 29 CA070119003 1 20070109 G 2930 AIR45428 INDICATOR BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU HYDRAULIC SYS LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ENROUTE, THE CREW OBSERVED BOTH HYD SYSTEMS INDICATING APPROXIMATELY 1200 PSI WITH LOW FLOW LIGHTS ON. THE CREW CO NTINUED WHERE ON APPROACH THE HYDRAULIC PRESSURE RECOVERED AND THE FLOW LIGHTS EXTINGUISHED. THE AIRCRAFT LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE FOUND THE HYDRAULIC FLOW INDICATION VALVE LEAKING WHICH WAS REPLACED PRIOR TO THE AIRCRAFT RETURNING TO SERVICE. (TC NR 20070119003) 2 L 7 2 3T 4 T A24EU A196 6 C P899 2007012900312 20070129 00312 EA 2007 1 29 CA070119004 1 20070118 G 5343 FASTENER DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE NLG TRUNNION LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NLG TRUNNION FITTING FASTENERS FOUND LOOSE. REFERENCE IPC 53-20-00; FIGURE 25; ITEM 190. BOTH SIDES (LT AND RT) AF T ROW OF BOLTS. RE-TORQUED NUTS IAW SB8-53-49. (TC NR 20070119004) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007051100011 20070511 00011 EU 2007 5 11 CA070119005 1 20070118 G 3097 2840A SWITCH BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ANTI ICE SHORTED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 851 (CAN) AIRCRAFT IS IN CRUISE FLIGHT WHEN PILOT SELECTED NR 1 AND NR 2 ANTI-ICE (ON) DUE TO THE OAT AND VISIBLE MOISTURE. ON SHORT FINAL TO THE BASE THE PILOT SELECTED BOTH ANTI-ICE SWITCHES TO THE (OFF) POSITION. IMMEDIATELY UPON ACTIVATING NR 1 SWITCH TO (OFF) THE PILOT HEARD AN AUDIBLE (CLICK). LOOKING DOWN HE NOTICED THAT THE NR1 ANTI-ICE 3AMP BREAKER HA D POPPED. ONE UNSUCCESSFUL ATTEMPT WAS MADE TO RESET THE BREAKER. AFTER THE AIRCRAFT HAD SHUTDOWN THE MAINTENANCE STAF F TROUBLESHOT THE SYSTEM AND FOUND THAT THERE WAS A (DEAD SHORT) IN THE ANTI ICE SWITCH P/N 2840A. THE SWITCH WAS REPLA CED AND AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070119005) 1 G 7 2 3U 3 U H3EU E4CE 2007051100016 20070511 00016 CE 2007 5 11 CA070119009 1 20070116 G 5711 122210614 SPAR CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO MCAULY D3A34 D3A34C402 GL RT WING FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) EDGE DISTANCE OF RIVETS ON LOWER FLANGE LESS THAN MINIMUM ALLOWED. REPLACEMENT OF PART REQUIRED TO REPAIR PROBLEM . (TC NR 20070119009) 1 H 7 1 3O 3 O A4CE E8CE 5 C P47GL 2007080800125 20070808 00125 CE 2007 8 8 CA070119010 1 20070116 G 5711 12220052 SPAR CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO MCAULY D3A34 D3A34C402 GL RT WING FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING REPLACEMENT OF LOWER OB SKIN, EDGE DISTANCE OF RIVETS THROUGH LOWER FLANGE LESS THAN MINIMUM ALLOWED IN 32 PLACES FROM STAT. 100.0 TO STAT. 154.00 REPLACEMENT OF PARTS REQUIRED TO REPAIR PROBLEM. (TC NR 20070119010) 1 H 7 1 3O 3 O A4CE E8CE 5 C P47GL 2007051100018 20070511 00018 NM 2007 5 11 CA070119011 1 20070116 G 5343 69634801 BOLT BOEING 727 727227 1384078 NM PWA JT8 JT8D9A 52048 NE TRUNION SHEARED W O OTHER O OTHER NR NOT REPORTED 1 CA 63218 (CAN) DURING A ROUTINE (C) CHECK INSPECTION, IT WAS NOTICED THAT THE LT MAIN LANDING GEAR TRUNION BOLT P/N 69-63480-1 AP PEARED TO BE SHEARED. UPON REMOVAL OF THE GEAR, IT WAS CONFIRME4D THAT THE BOLT WAS SHEARED AND ALSO THE BEARING P/N 10- 61849-10 WAS CRACKED. THE ABOVE PN ARE WITH REFERENCE TO MFG IPC 32-10-00-01 P.4 ITEM 317. (TC NR 20070119011) 2 L 7 3 4F 4 F A3WE E2EA 2007051100019 20070511 00019 SO 2007 5 11 CA070119012 1 20070113 G 8120 4091709001 TURBOCHARGER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE LEAKING W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA 1362 L430261A (CAN) EXCESSIVE SMOKE FROM THE LT ENGINE WAS REPORTED BY PASSENGER AND GROUND CONTROL DURING APPROACH TO AIRPORT. FLIGHT CREW DECLARED AN EMERGENCY AND AIRCRAFT LANDED AND PASSENGERS IMMEDIATELY DISEMBARKED. AIRPORT EMERGENCY RESPONSE VEHIC LES ATTENDED. NO VISIBLE FLAMES OR FIRE WAS EVIDENT PRIOR TO OR AFTER LANDING. AIRCRAFT WAS TOWED FROM THE RUNWAY TO MAI NTENANCE FACILITY. MAINTENANCE INVESTIGATION REVEALED EXCESSIVE OIL IN THE TURBOCHARGER EXHAUST. TURBOCHARGER REPLACED W ITH O`HAULED UNIT AND AIRCRAFT/ENGINE OPERATION CHECKED NORMAL. (TC NR 20070119012) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007051100021 20070511 00021 SO 2007 5 11 CA070120001 1 20070118 G 8120 BEARING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL TURBOCHARGER FAILED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 13433 121 L206368A (CAN) RT ENGINE OIL CONSUMPTION HAD INCREASED, OIL RESIDUE FOUND ON EXHAUST STACK. INSPECTION FOUND THAT THE EXHAUST SI DE OF THE RT TURBOCHARGER WAS COVER IN OIL. FOUND THAT THE INNNER SUPPORT BEARING AND SEAL HAD FAILED ALLOWING OIL TO BE INTRODUCED TO THE HOT SIDE OF THE TURBO. REPLACED TURBOCHARGER, CHANGED ENGINE OIL, INSPECTED RT ENGINE OIL FILTER FOR METAL, NO FAULT FOUND. (TC NR 20070120001) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007051100023 20070511 00023 EA 2007 5 11 CA070122001 1 20070119 G 3213 C6UM117227 RETAINING NUT DHAV DHC6 DHC6 2802606 EA AXLE MISMANUFACTURED W O OTHER W INADEQUATE Q C NR NOT REPORTED 1 CA (CAN) NEW AXLE NUTS FOR THE SERIES AIRCRAFT NOT FULLY ASSEMBLED. THE HOLES FOR THE (2) PINS HAVE BEEN DRILLED BUT NO PIN S HAVE BEEN INSTALLED, INCOMPLETE PARTS. MARKING ON NUT WO-04403/1, DEC 07 2006 C6UM1172-27. (TC NR 20070122001) 1 H 7 2 3T RT A9EA 2007051100025 20070511 00025 WP 2007 5 11 CA070122002 1 20070122 G 7800 D3171 HEAT SHIELD ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 152 (CAN) DURING A ROUTINE 100 HR ENGINE/AIRFRAME INSPECTION, IT WAS NOTED THAT THE SUBJECT HEAT SHIELD, THAT IS INSTALLED O N THE ENGINE EXHAUST TAILPIPE, WAS FOUND CRACKED. THE CRACK ORIGINATED IN THE DOUBLER AREA WHERE THE FORWARD CLAMP IS AT TACHED. THE CRACK LOOKS LIKE IT HAS ORIGINATED FROM A RIVET THAT ATTACHES THE DOUBLER AND BRACKET, WHICH PROVIDES A MEAN S TO ATTACH THE CLAMP TO THE EXHAUST TAILPIPE. THE PART IN QUESTION HAS 151.3 HOURS SINCE NEW ON IT. THE AIRCRAFT IN QUE STION HAS 495.0 HOURS SINCE NEW. THE PART WILL BE SUBMITTED TO MFG FOR WARRANTY. THIS IS THE 3RD HEAT SHIELD TO BE REPLA CED ON THIS AIRCRAFT SINCE IT WAS NEW. THE PRIOR HEAT SHIELDS WHERE REPLACED AT 343.5 AIRCRAFT HOURS, AND 203.2 AIRCRAFT 1 G 7 1 3O 3 O H11NM 1E4 2007051100026 20070511 00026 WP 2007 5 11 CA070122003 1 20070122 G 5310 D3807 SHROUD ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE BAY CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 202 (CAN) DURING A ROUTINE 100 HR ENGINE/AIRFRAME INSP, IT WAS NOTED THAT THE SUBJECT SHROUD WAS CRACKED JUST AFT OF THE UPP ER/AFT MOUNTING SCREW LOCATION. THE SHROUD IS PART OF A SERIES OF SHROUD COVERS THAT SURROUND THE ENGINE FOR COOLING PUR POSES. THE SHROUD HAS 201.8 HOURS SINCE NEW ON IT. THE AIRCRAFT HAS ACCUMULATED 495.0 HOURS SINCE NEW. THIS IS THE SECON D TIME THAT THIS PARTICULAR SHROUD HAS BEEN REPLACED. THE ORIGINAL SHROUD THAT CAME NEW WITH THE AIRCRAFT WAS FOUND CRAC KED IN THE SAME LOCATION, AND REPLACED AT 293.2 AIRCRAFT HOURS. THIS SEEMS TO BE A WEAK AREA THAT IS SUBJECTED TO ENGINE VIBRATION. HAVE TAKEN NOTE OF THIS WEAK AREA AND HAVE STEPPED UP OUR VISUAL INSPECTIONS TO SPOT CRACKS IN THEIR EARLY D 1 G 7 1 3O 3 O H11NM 1E4 2007051100028 20070511 00028 WP 2007 5 11 CA070122004 1 20070122 G 5311 C2617C2618 RIB ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 495 (CAN) DURING A ROUTINE 100 HOUR ENGINE/AIRFRAME INSPECTION, IT WAS NOTED THAT THE SUBJECT PARTS WHERE CRACKED. THE CRACK S WHERE FOUND AT THE FORWARD ANCHOR NUT LOCTIONS. THE RIBS ARE PART OF THE STRUCTURE THAT ENCLOSES THAT MAST AREA. THE R IBS WHERE REPLACED WITH NEW ASSEMBLIES. THE AIRCRAFT IN QUESTION HAS 495.0 HRS SINCE NEW. (TC NR 20070122004) 1 G 7 1 3O 3 O H11NM 1E4 2007051100029 20070511 00029 EA 2007 5 11 CA070122005 1 20070119 G 5551 600210713 BUSHING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE HORIZONTAL STAB LACK OF LUBE W K NONE O OTHER IN INSP/MAINT 1 CA 5433 (CAN) CREAKING NOISE HEARD WHEN HORIZONTAL STABLIZER WAS CYCLED THROUGH FULL RANGE. HORIZONTAL STAB HINGE BUSHINGS.THEY WERE FOUND DRY. IPC REF:27-43-01-01, ITEM NR 60. PARTS HAND LUBED AND RE-ASSEMBLED IAW MM TASK NR 000-13-320-121. CURR ENT INTERVAL FOR THIS TASK IS 10,000 FLT.HRS (TC NR 20070122005) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100042 20070511 00042 EA 2007 5 11 CA070122006 1 20070121 G 5551 600210713 BUSHING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE HORZONTAL STAB LACK OF LUBE W K NONE O OTHER IN INSP/MAINT 1 CA 5406 (CAN) CREAKING NOISE HEARD WHEN THE HORIZONTAL STABILIZER WAS CYCLED THROUGH FULL RANGE. AFT FITTING ON THE HORIZONTAL STABILIZER DISASSEMBLED. BUSHING WAS FOUND DRY ( NO LUBRICATION ). PARTS CLEANED, INSPECTED, HAND LUBED AND RE-ASSEMBL ED IAW MM TASK NR 000-12-320-121. CURRENT INTERVAL FOR THIS TASK IN THE MANUAL IS 10,000 FLIGHT HOURS. (TC NR 200701220 06) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100043 20070511 00043 NM 2007 5 11 CA070122007 1 20070105 G 2910 82970009235 LINE DHAV DHC8 DHC8101 2809002 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE RT MLG RUPTURED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 27198 (CAN) DURING TAKEOFF, AFTER SELECTING LANDING GEAR UP, NR 2 ENGINE HYD PUMP FAILED AND AFTER SEVERAL MIN, A/C LOST ALL O F THE NR 2 HYD QUANTITY. SYSTEM NR 2 PRESSURE LOW AND QUANTITY DEPLETED, ALTERNATE LANDING GEAR EXTENSION. AFTER INVEST IGATION HYD TUBE, P/N 82970009-235 AT RT HYD SYSTEM (L/G BAY), WAS FOUND RUPTURED (IN THE FLARED AREA). TUBE WAS REPLACE D; BLEEDING AND LEAK CHECK C/OUT OF RT HYD SYSTEM AND NO LEAKS OBSERVED. (TC NR 20070122007) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007051100065 20070511 00065 CE 2007 5 11 CA070122008 1 20070120 G 3230 508103385 DRAG LINK BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL RT MLG FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFTER SCHEDULED MAINTENANCE THE AIRCRAFT WAS REMOVED FROM THE HANGER AND WAS TOWED TO THE FUEL PUMPS TO BE LEAK CH ECKED. AFTER TOWING THE AIRCRAFT ABOUT 500 FEET THE RT MLG COLLAPSED CAUSING DAMAGE TO THE RT MAIN LANDING GEAR AND DOOR S, WING TIP, CARGO POD AND ONE BLADE OF THE RT PROP. THE AIRCRAFT WAS THEN LIFTED AND JACKED TO ALLOW INSPECTION OF THE LANDING GEAR AREA AND ALLOWED FOR A TEMPORARY DOWNLOCK TO BE MADE AND THE AIRCRAFT WAS RETURNED TO THE HANGER. THE AIRCR AFT IS STILL BEING INSPECTED FOR OTHER UNSEEN DAMAGE. THE PRELIMINARY FINDINGS SHOW THAT THE PRIMARY FAILURE WAS OF THE DRAG LINK LOCK. THIS IS ONLY A PRELIMINARY REPORT A MORE CONCLUSIVE REPORT WILL BE ADDED TO THIS SDR WHEN THE FINDINGS A 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007051100044 20070511 00044 SO 2007 5 11 CA070122009 2 20070117 G 8530 EC649358CN CYLINDER CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO HARTZL HCC3Y HCC3YF1 GL NR 4 FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 755 (CAN) NR 4 CYILINDER FAILED, BURNING VARIOUS ENGINE COMPARTMENT WIRING AND DUCTING. (TC NR 20070122009) 1 H 7 1 3O 3 O A4CE E5CE 5 C P25EA 2007051100045 20070511 00045 CE 2007 5 11 CA070122010 1 20070106 G 2497 1003641621 CONTROL PANEL BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCD4N3 HCD4N3A GL COCKPIT LIGHTS SHORTED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) CREW REPORTED COCKPIT OVERHEAD PANEL LIGHTS CIRCUIT BREAKER POPPED AND ABOUT THE SAME TIME REPORTED SMELLING SMOKE . PCB PANEL REMOVED AND FOUND TO OF SHORTED OUT CAUSING SMALL BURN HOLE THROUGH PANEL SCORCHING METAL BEHIND PANEL. CAUS E OF SHORT BELIVED TO BE MOISTURE FROM EXCESSIVE CONDENSATION. (TC NR 20070122010) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007051100046 20070511 00046 SW 2007 5 11 CA070122011 1 20070122 G 6710 2040011841 COLLECTIVE STICK BELL 204 204B 1181404 SW LYC T53 T5311B 41549 NE MAIN ROTOR RATCHETING W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) PILOT COMPLAINED OF RATCHETING FEEL TO COLLECTIVE CONTROL STICK. AIRCRAFT RETURNED TO BASE. INSPECTION REVEALED THAT THE COLLECTIVE FRICTION SURFACE ROLL PIN WAS WORKING INTERNALLY AND CAUSING THE RATCHETING FEEL. ELBOW WAS REPLACE D. (TC NR 20070122011) 1 G 7 1 4U 4 U H1SW E1EA 2007051100047 20070511 00047 CE 2007 5 11 CA070123001 1 20070119 G 7603 9938000521 CONTROL CABLE BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCB4T HCB4TN3 GL LT ENGINE SEPARATED W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 CA (CAN) THE LT ENGINE COULD NOT BE SHUTDOWN ON THE GROUND USING THE CONDITION LEVER, THE PILOT HAD TO USE THE FIREWALL SHU T-OFF IN ORDER TO SHUT THE ENGINE DOWN. INVESTIGATION BY MAINTENANCE FOUND THAT THE LT IDLE CONTROL CABLE ASSY FAILED AT THE MALE TERMINAL END AT THE ENGINE. THE MALE THREADED END PORTION SLIPPED OFF THE CABLE SLIDE AT THE POINT WHERE IT IS SWAGED/PRESSED ON. (TC NR 20070123001) 1 L 7 2 3T 4 T A14CE E4EA 6 C P40EA 2007051100049 20070511 00049 EA 2007 5 11 CA070123002 1 20070122 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE TE FLAPS JAMMED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) AIRCRAFT HAD A FLAPLESS LANDING, AFTER FLAP SELECTION 8, LT FLAP INDICATED ZERO, RT UNKNOWN, CREW THEN SELECTED TO 20 AND FLAPS TRAVELED TO APROX 5 DEGREES INDICATION WAS GREEN TRAVELED TO 5 DEGREES AND THEN TURNED WHITE. CREW THEN RE TRACTED FLAPS BACK TO FLAP ZERO AND LANDED FLAPLESS, FLAP FAIL CAUTION WAS NOT ILLUMINATED. FERRY FLIGHT FOR TROUBLESHO OTING. T/S C/O AND ALL DCU`S ARE DISPLAYING THE SAME INFO, APPEARS TO BE POTENTIOMETER FAIL. WAITING FOR PART TO BE IN STALLED. (TC NR 20070123002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007080800126 20070808 00126 CE 2007 8 8 CA070123004 1 20070121 G 3040 99180021 FAN CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE WINDSHIELD ODOR W G H O2 MASK DEPLOYED DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA 6004 (CAN) ON APPROACH WHEN THE CREW SMELLED SOMETHING BURNING IN THE CABIN. THE CABIN FILLED UP WITH SMOKE AND THE CREW PUT ON THEIR MASKS AND DROPPED THE PASSENGERS MASKS. THEY LANDED WITHOUT DECLARING AN EMERGENCY. AN AME WAS SENT TO AND D ETERMINED THAT THE DEFOG FAN WAS AT FAULT. THE FAN WAS DEFERRED AND WILL BE REPLACED ON ITS RETURN. (TC NR 20070123004) 1 L 7 2 4F 4 F A22CE E1NE 2007051100050 20070511 00050 EA 2007 5 11 CA070123005 1 20070118 G 2752 852D10019 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE TE FLAPS WORN W L ABORTED APPROACH F FLT CONT AFFECTED AP APPROACH 1 CA 5457 5321 (CAN) ON FINAL APPROACH CREW SELECTED FLAPS 20 DEGREES. FLAPS STUCK AT 8 DEGREES AND CREW RECEIVED A FLAP FAIL MESSAGE. CREW BROKE OFF APPROACH AND CONTACTED DISPATCH. AIRCRAFT SUBSEQUENTLY LANDED WITHOUT INCIDENT WITH FLAPS AT 8 DEGREES. M AINTENANCE TROUBLESHOOTING FOUND EXCESSIVE LINEAR PLAY IN THE LT AND RT IB FLAP ACTUATORS. ACTUATORS REPLACED (RT IB ACT UATOR PN CL600-2B19, S/N 5051. TSN 5321:44 HOURS, TSO 5321:44, CYCLES 4332) MOD SUM IS601R27530052 REV B: FLAP DRIVE SYS TEM, ALTERNATE METALLIC SEAL FOR FLEXIBLE DRIVE SHAFT COMPLETED. SYSTEM RE-GREASED. FLAP SYSTEM RIGGED IAW AMM 27-51-10. SUCCESSFUL TEST FLIGHT COMPLETED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070123005) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100051 20070511 00051 EA 2007 5 11 CA070123006 1 20070122 G 3230 574205A VALVE DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE MLG MALFUNCTIONED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 36649 9188 (CAN) DURING APPROACH WHEN LANDING GEAR SELECTED DOWN, NO GEAR MOVEMENT. CIRCUIT BREAKERS, HYDRAULIC PX AND QUANTITY AND DOORS ALL NORMAL. AFTER APPROXIMATELY 10 MINUETS, LANDING GEAR DEPLOYED NORMALLY TO EXTENDED POSITION. AIRCRAFT FERRIED GEAR DOWN TO MAINTENANCE BASE. LANDING GEAR SELECTOR VALVE REPLACED, GEAR SWINGS CARRIED OUT. SERVICEABLE. AIRCRAFT RET URNED TO SERVICE. (TC NR 20070123006) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007051100066 20070511 00066 NE 2007 5 11 CA070123007 1 20070106 G 6420 9235806343101 CONE SKRSKY SKRSKY S92 S92A NE TAILROTOR G/B SPLIT W K NONE O OTHER IN INSP/MAINT 1 CA 596 A13200020 (CAN) ON 06 JAN 07, THE TAIL ROTOR HEAD WAS IN PROCESS OF BEING REPLACED WHEN IT WAS NOTICED THAT THE IB SET OF SPLIT CO NES WHICH CENTER AND SUPPORT THE TAIL ROTOR HUB LOADS WERE MISSING. FURTHER INVESTIGATION FOUND THAT WHEN THIS TAIL GEAR BOX WAS INSTALLED 596 HOURS PREVIOUS ON 18 JUNE 06 THE MFG MM DID NOT HAVE ANY REFERENCE TO THE INNER SPLIT CONES. NO M ENTION OF THEM IN THE REMOVAL/INSTALLATION INSTRUCTION, OR THE REQUIRED PARTS LISTING OR ON ANY ILLUSTRATION.( NOTE: MFG MM HAVE SINCE BEEN UPDATED AS OF SEPT 06 TO INCLUDE THE IB SPLIT CONES) FIELDS FOR P/N NOT LONG ENOUGH TGB P/N 92358- 06100-043 (TC NR 20070123007) 2 G 7 2 4U R00024BO 2007051100052 20070511 00052 EA 2007 5 11 CA070123008 1 20070123 G 5415 TA305002403 FAIRLEAD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE HYD LINE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 10220 8646 (CAN) DURING MAINTENANCE INSPECTION , FOUND AFT FUSELAGE EQUIPMENT BAY HYDRAULIC LINE CLAMPS (FAIRLEAD), WITH CENTER (PR ESSURE LINE) HOLES WORN THROUGH RUBBER/SILICON COMPOUND AND ALLOWING TUBING TO CHAFE ON METAL PORTION OF BLOCK. BLOCK P N TA3050024-03 CONSISTS OF (2) HALVES (INK STAMP P/N B0305103-002 OR 601R75126-3). CLAMP HALVES REPLACED. (TC NR 2007012 3008) 2 L 7 2 4F 4 F RT A21EA E15NE 20080520 CE 2008 5 20 CA070123009 1 20070123 G 5320 51220465 BRACKET CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL CORRODED W O OTHER O OTHER DE DESCENT 1 CA (CAN) WHEN FLAPS LOWERED AC SEEMED TO ROTATE SLIGHTLY. PILOT RETURNED TO BASE. FLAP SYS INSPECTED AND FAULT FOUND WITH L T FLAP BELLCRANK LOWER MOUNTING BRACKET. BELLCRANK MOUNTING HOLE WAS SEVERELY CORRODED ALLOWING LARGE BOLT MOVEMENT WHEN FLAPS OPERATED. BRACKET REMOVED AND NEW PART ON ORDER. (TC NR 20070123009) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2007051100068 20070511 00068 NE 2007 5 11 CA070123010 2 20070123 G 7261 311145101 SEAL BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE NR 2 ENGINE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 15852 4083 (CAN) CREW LANDED AND REPORTED ENGINE NR 2 LEAKING OIL. MAINTENANCE INSPECTED AND FOUND THE OIL LEVEL DOWN CONSIDERABLY, THEY INSPECTED THE FWD CHIP DETECTOR, OIL FILTER, FUEL OIL HEATER AND FOUND NO DEFECTS. THE ENGINE WAS GROUND RUN WITH A LITTLE OIL LEAKAGE FOUND. THE OIL BREATHER LINE WAS REMOVED AND THE A/C SENT ON A TEST FLIGHT. WHEN IT RETURNED THE BA G WAS FULL (.5 LTR) WITH SOME SPILLAGE FROM THE BAG .THE A/C WAS GROUNDED AND WITH THE AID OF A MFG ENGINEER, THE REDUCT ION GEAR BOX ASSY WAS REMOVED FROM THE ENGINE. CLOSE INSPECTION FOUND THE INTERNAL CARBON SEAL ASSY WITH SLIGHT DAMAGE A ND STUCK IN THE OPEN POSITION. AS SOON AS THE SEAL WAS TOUCHED THE SPRING IN THE ASSY CLOSED THE OPENING IN THE SEAL ASS 2 L 7 2 4T 4 T RT A24CE E26NE 2007080800127 20070808 00127 NM 2007 8 8 CA070123012 1 20070119 G 3520 RVA7101 CONTROL UNIT AMD FALC50 FALCON2000 2730170 NM OXYGEN SYSTEM FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA 1564 (CAN) UPON A NON-ROUTINE DEPLOYMENT OF THE OXYGEN MASKS ON THE GROUND BY MAINTENANCE. OXYGEN CONTROL UNIT (10WJ) WAS PL ACED INTO (OVERRIDE) TO MANUALLY DEPLOY THE PAX OXYGEN MASKS. THEY DID NOT DEPLOY ON COMMAND. MULTIPLE ATTEMPTS WERE M ADE TO MANUALLY DEPLOY THE PAX OXYGEN MASKS IN (OVERRIDE). THEY STILL DID NOT DEPLOY. OXYGEN CONTROL UNIT (10WJ) WAS R EPLACED IAW MP35-203, OPS TESTED SERVICEABLE. PN OFF: RVA71-01 SN OFF: 0640 ATSO: 1563.8 ACSO: 711. FAULTY OXYGEN CON TROL UNIT FORWARDED TO MFG FOR EXCHANGE. (TC NR 20070123012) 2 K 7 2 4F RT A50NM 2007051100055 20070511 00055 EA 2007 5 11 CA070123013 1 20070117 G 2910 AE2460260G0074 HOSE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE HYD SYSTEM LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 CA (CAN) ON FINAL APPROACH WITH GEAR DOWN AND AT 2000FT THE MESSAGE HYD NR3 LOW PRESS CAME ON EICAS WITH THE HYDRAULIC NR3 RESERVOIR LEVEL AT 0 PERCENT. CREW COMPLIED WITH QRH. THE AIRCRAFT LANDED NORMALLY AND DEPLOYED THE THRUST REVERSER , THE GROUND SPOILERS DEPLOYED AND OPERATED BRAKES . THE AIRCRAFT AT A SPEED AROUND 70 KTS SUDDENLY DIVERTED ON THE RT E ND SIDE . THE AIRCRAFT LEFT THE SIDE OF THE RUNWAY BY 13 METER AND ENDED UP ON THE GRASS AFTER THE A/C COVERED 50/55 MET ERS (TC NR 20070123013) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100056 20070511 00056 EA 2007 5 11 CA070123014 1 20070121 G 5610 NP13932114 WINDSHIELD CNDAIR CL600 CL6002D24 1390016 EA GE CF34 CF348C1 NE COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA 565 (CAN) RT WINDSHIELD CRACKED, FL240.IAS250 DIFF PRESS 7.4 RT WINDSHIELD REPLACED ACC AMM 56-11-01-400. CURE TIME OF SEAL ANT TIL 21-01-2007, 20:00 LOC TIME. PLS PERFORM ADJUSTMENT OF WIPER ARM TENSION ACC AMM 30-42-09-400-801-A01 AND OPS TES T OF WIPER AND PERFORM A LEAK TEST OF WINDSHIELD ACC AMM 56-11-01-400-801-A01 (E). CONDITION OF SEALANT CHECKED OK. AD JUSTMENT OF WIPER ARM IAW.AMM. CHECKED OK. OPS TEST OF WIPER OK. CABIN PRESSURE TEST UP TO DELTA P 6.0 PERFORMED FOUND SATISFIED. (TC NR 20070123014) 2 L 7 2 4F 4 F RT A21EA EOOO63EN 2007051100058 20070511 00058 EA 2007 5 11 CA070123015 1 20070118 G 5610 NP13932113 WINDSHIELD CNDAIR CL600 CL6002D24 1390016 EA GE CF34 CF348C1 NE COCKPIT CRACKED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 564 (CAN) LT WINDSHIELD CRACKED. LT WINDSHIELD REPLACED IAW AMM 56-11-01-000-801 (TC NR 20070123015) 2 L 7 2 4F 4 F RT A21EA EOOO63EN 2007051100126 20070511 00126 EA 2007 5 11 CA070124001 1 20070122 G 2840 73664310 COMPUTER CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE FUEL QUANTITY MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 10220 10220 (CAN) JUST PRIOR TO TOP OF CLIMB, LEFT FUEL QUANTITY AND TOTAL FUEL QUANTITY STARTED TO REDUCE, FOLLOWED BY FUEL IMBALAN CE MESSAGE. CREW ELECTED TO RETURN TO DEPARTURE AIRPORT. ON FINAL APPROACH FUEL INDICATIONS RETURNED TO NORMAL. FUEL SYS TEM INSPECTED, WITH NO LEAKAGE FOUND. AIRCRAFT DISPATCHED UNDER MEL. ON NEXT MAINTENANCE VISIT FUEL COMPUTER REPLACED. ( TC# 20070124001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007080800128 20070808 00128 CE 2007 8 8 CA070124002 1 20070122 G 3020 991240216 SOLENOID VALVE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ANTI-ICE SYS FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) STILL IN CRUISE CONFIG PILOTS DECIDED TO SELECT ANTI-ICE IN PREPARATION FOR DECENT TO AIRPORT. AT THIS TIME, A LT ANTI-ICE FAIL LIGHT ILLUMINATED. TROUBLESHOOTING LATER CONFIRMED THAT THE LT ENGINE ANTI-ICE VALVE HAD FAILED. THE VAL VE IS POWERED 28VDC CLOSED UNTIL THE PILOT SELECTS ANTI-ICE ON, THEN POWER IS REMOVED AND THE VALVE IS OPENED BY ENGINE BLEED AIR PRESSURE. THE SYSTEM IS INTENDED TO BE A FAILSAFE SYSTEM, WHERE A NO POWER SITUATION WILL ALWAYS ALLOW BLEED A IR TO THE ENGINE INTAKE. THIS PARTICULAR VALVE FAILED TO PROVIDE THE FAILSAFE CONDITION. NO ENGINE BLEED AIR WAS AVAILA BLE TO THE ENGINE INLET ALLOWING AN EXCESSIVE BUILD UP OF ICE. THIS CONDITION COULD HAVE LED TO ICE INGESTION CAUSING EN 1 L 7 2 4F 4 F A22CE E1NE 2007051100069 20070511 00069 CE 2007 5 11 CA070124003 1 20070119 G 5753 99160011 ROLLER BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL TE FLAPS WORN W A UNSCHED LANDING F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) PILOT REPORTED INTERFERENCE WITH AILERON CONTROL UPON APPROACH WHEN FLAPS WERE APPROXIMATELY 30 PERCENT. AIRCRAFT LANDED WITHOUT INCIDENT. INVESTIGATION REVEALED RT OB FLAP IB HINGE ATTACH BRACKET, PN 35-165050-31, FAILED AT THE AFT ROLLER ASSY ATTACH AREA. THIS IN TURN CAUSED THE OPPOSITE ATTACH BRACKET TO FAIL. THIS CAUSED THE IB AFT AREA OF THE FLAP TO MOVE FREELY AND CHANGE THE NORMAL ATTITUDE OF THE FLAP CAUSING INTERFERENCE WITH THE IB RT AILERON SKIN. THE HI NGE ATTACH BRACKET FAILED FROM THE AFT ROLLER ASSY, P/N 99-160011, WEARING INTO THE HINGE ATTACH BRACKET. INSPECTED ALL OTHER HINGE ATTACH AREAS AND FOUND SIMILAR WEAR IN OTHER AFT ROLLER ATTACH LOCATIONS. THE ROLLER ASSEMBLY, PN 99-16001 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007051100059 20070511 00059 EA 2007 5 11 CA070125001 1 20070125 G 3233 6008500185 ACTUATOR CNDAIR CL601 CL6012A12 1900303 EA GE CF34 CF343A 30015 NE MLG INOPERATIVE W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA 25189 6776 (CAN) RT MAIN LANDING GEAR UNLOCK INDICATION APPROX. 15 - 20 MIN. AFTER ARRIVAL, NO PUMP, NO GEAR COMMAND, LOCK PARTIALL Y MOVED TO UNLOCK POSITION. RETRACTING ACTUATOR REPLACED AND AC RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21AE E15NE 2007080800129 20070808 00129 CE 2007 8 8 CA070125002 1 20070124 G 3231 08411131 SCREW CESSNA 401 401B 207590E CE CONT O520 TSIO520EB 17040 SO MCAULY 3AF32C 3AF32C505 GL RT MLG ADJ BROKEN W O OTHER O OTHER LD LANDING 1 CA (CAN) UPON LANDING RT MLG INADVETENTLY RETRACTED. AIRCRAFT VEERED OFF RUNWAY. AIRCRAFT INSPECTED AND CAUSE DEEMED FAILUR E OF RT MLG ADJUSTING SCREW CAUSING SIDE BRACE ASSY TO UNLOCK. (TC NR 20070125002) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2007051100127 20070511 00127 NM 2007 5 11 CA070125003 1 20070123 G 2612 3023143 SMOKE DETECTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE CARGO BAY FALSE INDICATION W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 28530 28530 (CAN) ON DEPARTURE THROUGH 4000 FT, FLT CREW RECEIVED A MASTER WARNING BAGGAGE SMOKE INDICATION. FLIGHT CREW DECLARED AN EMERGENCY AND ELECTED TO RETURN TO DEPARTURE AIRPORT. THERE WAS A COMPANY LINE CHECK CAPTAIN ON BOARD WHO WITH THE FLIG HT ATTENDANT WENT TO CHECK THE CARGO HOLD. THERE WAS NO INDICATION OF SMOKE. FLIGHT LANDED SAFELY WITHOUT FURTHER INCIDE NT. MAINTENANCE REPLACED THE NR 1 BAGGAGE SMOKE DETECTOR , THE LAMPS IN THE NR 2 DETECTOR (P/N 376), CLEANED THE CONNECT ORS OF BOTH DETECTORS AND GROUND TESTED THEM SERVICEABLE. ENGINE RUNS WERE CARRIED OUT WITH NO DUPLICATION OF THE ORIGIN AL DEFECT. TIME SINCE LAST REPAIR OF THE NR 1 DETECTOR WAS 1883:46 HOURS. (TC 20070125003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007051100070 20070511 00070 EU 2007 5 11 CA070125004 1 20070123 G 6220 601741 BEARING BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL PENDULUM ABSORB FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON LANDING AT THE MAINTENANCE BASE AND FOLLOWING HELICOPTER BEING SHUTDOWN, THE PILOT WAS EXITING AND LEAVING TH E AIRCRAFT HE NOTICED THAT THE M/R PENDULUM ABSORBER ON THE YELLOW MAIN ROTOR BLADE WAS IN THE HORIZONTAL POSITION. CLOS ER INSPECTION REVEALED THAT WHEN AN ATTEMPT TO ROTATE THE PENDULUM ABSORBER IT WAS EXTREMELY ROUGH AND DIFFICULT TO ROTA TE. PENDULUM ABSORBER WAS REMOVED AND DISASSEMBLED, WHERE IT WAS FOUND THAT ONE OF THE BEARINGS HAD A FRACTURED OUTER C ASE. THE BEARING APPEARED TO BE DRY, AS NO EVIDENCE OF LUBRICATION WAS FOUND. NEW BEARINGS, SEALS, AND O-RINGS WERE IN STALLED. PENDULUM ABSORBER WAS RE-INSTALLED AND AIRCRAFT NOW RETURNED TO SERVICE. (TC NR 20070125004) 1 G 7 2 3U 3 U H3EU E4CE 2007051100071 20070511 00071 EA 2007 5 11 CA070125005 2 20070125 G 7250 312111101 BLADE PWA PT6 PT6A65B 52043 EA TURBINE SECTION FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE ENGINE PT6A-65B S/N: PCE-32399 WAS RECEIVED FOR OVERHAUL. DURING THE ENGINE DISASSEMBLING IT WAS FOUND THAT T HE COMPRESSOR TURBINE BLADES WERE SEVERELY RUBBED AND ONE BLADE FAILED AT FIRTREE. ALSO THE INSPECTION REVEALED THAT TH E COMPRESSOR TURBINE VANE TRAILING EDGE, SHROUD SEGMENTS AND SHROUD HOUSING ARE DAMAGED. THE POWER TURBINE COMPONENTS: 1 ST AND 2ND STAGES BLADES AND VANES FOUND IMPACT DAMAGED. THE BLADE WHICH FAILED AT THE FIRTREE SHOWED EVIDENCE OF FAT IGUE WITH AN ANOMALY AT THE ORIGIN. NOTE: CODES DETERMINED FROM PILOT REPORT. (TC NR 20070125005) 4 T E4EA 2007051100060 20070511 00060 NE 2007 5 11 CA070125006 2 20070123 G 7261 ENGINE BOEING 727 727243 138408D NM PWA JT8 JT8D9A 52048 NE NR 3 LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 67467 8505 666071 (CAN) ENROUTE, NR 3 ENGINE OIL LOSS, AIRCRAFT DIVERTED. INSPECTED AND FERRIED AIRCRAFT. ENGINE REPLACED (TC NR 2007012 5006) 2 L 7 3 4F 4 F RT A3WE E2EA 2007051100061 20070511 00061 GL 2007 5 11 CA070126001 2 20070121 G 7200 ENGINE EMB 135 EMB135LR 3260305 SO ALLSN AE300 AE3007A GL MALFUNCTIONED W E B A ENGINE SHUTDOWN EMER. DESCENT UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA 9808 CAE312136 (CAN) DURING CLIMB (280 KNOTS) AT FL350 , CREW HEARD A LOUD POP FOLLOWED BY MULTIPLE UNSPECIFIED EICAS MESSAGES AND ITT WAS IN THE AMBER RANGE. ENGINE SHUTDOWN UNCOMMANDED. F/A REPORTED WHITE SMOKE IN THE CABIN. CREW CONSIDERED ATTEMPTIN G A RE-START BUT OIL QUANTITY WAS ONLY 3 QUARTS. CREW DIVERTED AND A CMC DOWNLOAD REVEALED THAT AN OIL DEBRIS MESSAGE HA D BEEN SET ON JANUARY 19. ENGINE ENROUTE TO MFG FOR INVESTIGATION, FURTHER REPORT WILL BE SUBMITTED ON ENGINE TEARDOWN. (TC NR 20070126001) 2 L 7 2 4F 4 F RT T00011AT TE6CH 2007080800130 20070808 00130 CE 2007 8 8 CA070126002 1 20070125 G 3260 426EN98 SQUAT SWITCH LEAR 35 35LEAR 5170600 CE GARRTT TFE731 TFE73122B 01518 WP LT MAIN GEAR SHORTED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) PRELIMINARY REPORT, SUSPECT THAT THE SHUTTLE VALVE THAT DIRECTS HYDRAULICS TO THE UP- OR DOWN-SIDE OF THE LANDING GEAR WAS STUCK OR BROKEN IN THE UP DIRECTION. WHEN THE L/G WAS SELECTED DOWN ON THE ARRIVAL, NOTHING HAPPENED EXCEPT TH E L/G DOORS OPENED THE FIRST TIME, NOTHING AT ALL ON THE SECOND ATTEMPT. THE CREW WENT AROUND AND PUT THE L/G DOWN WITH EMERGENCY SYSTEM. IT WORKED AND THEY HAD THREE GREEN, BUT THE EMERGENCY GEAR EXTENSION LEVER DID NOT LOCK AS IT SHOULD , AND THE L/G RETRACTED ON ITS OWN SHORTLY THEREAFTER! THE EMERGENCY SYSTEM WAS RE-ACTIVATED, THE L/G WENT DOWN AS IT S HOULD AND THE LEVER WAS HELD IN THE DOWN POSITION. THREE GREEN, NORMAL LANDING, AND THE A/C TURNED ONTO A TAXIWAY AND W 2 L 7 2 4F 4 F A10CE E6WE 2007051100128 20070511 00128 NM 2007 5 11 CA070126005 1 20070126 G 5343 85310340015 FITTING DHAV DHC8 DHC8106 2809020 NM NLG WHEEL WELL LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING "C-CHECK", WE FOUND THE NLG ACTUATOR FUSELAGE FITTING WITH A FASTENER BROKEN AND ALL THE OTHER ONE LOOSE. W E EMBODIED THE SB 8-53-50. THIS SB WAS NOT ATTACH TO ANY AD. (TC# 20070126005) 2 H 7 2 4T RT A13NM 2007051100075 20070511 00075 SW 2007 5 11 CA070126006 1 20070121 G 5302 206020113207 TAIL BOOM BELL 206 206L4 1182110 SW ALLSN 250C 250C30P 03013 GL VERTICAL FIN DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 3368 52054 (CAN) UPON CHANGING FORMER P/N 206-020-113-093 ON VERTICAL FIN, DAMAGE/GOUGING DETECTED ON THE IB FIN SKIN WITHIN CLOSE PROXIMITY TO VERTICAL FIN MOUNTING HOLE. IT IS SUSPECTED THAT WHEN ORIGINALLY FITTING THE COWLS THAT THE FORMER WAS TRIM MED AND THAT AT THIS TIME THE DAMAGE OCCURRED. MFG WAS CONTACTED AND AN APPROVED REPAIR WAS PROVIDED AND CARRIED OUT. (TC NR 20070126006) 1 G 7 1 3U 3 U NC H2SW E1GL 2007051100129 20070511 00129 SW 2007 5 11 CA070126007 1 20070121 G 5302 205030767005 FITTING BELL 205 205A1 1181414 SW TAIL BOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AIRFRAME INSPECTION, A CRACK WAS FOUND ON LONGERON P/N 205-030-207-005 UNDER FITTING P/N 205-030-767-005. F ITTING REMOVED, INSPECTED FOUND TO BE CRACKED AT AFT SIDE OF BOLT LOCATION. CRACKS IN FITTING P/N 205-030-767-005 NOT FO UND UNTIL REMOVAL OF PART. THIS FITTING IS KNOWN TO CRACK AT THE RIVET HOLE LOCATIONS, BUT IN THIS INSTANCE, IT WAS CRAC KED ON THE AFT SIDE OF THE BOLT HOLE LOCATION. LONGERON AND FITTING WERE REPLACED WITH NEW PARTS. (TC# 20070126007) 1 G 7 1 4U H1SW 2007053000006 20070530 00006 NM 2007 5 30 CA070126008 1 20070117 G 2611 SMOKE DETECTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LAVATORY MALFUNCTIONED W D RETURN TO BLOCK N FALSE WARNING TX TAXI/GRND HDL 1 CA (CAN) ON GOING REPORTS OF LAVATORY SMOKE DETECTOR ACTIVATION. PROBLEM APPEARS TO HAVE BEGUN ON JANUARY 17, 2007 WITH A P ILOT REPORT OF THE NR 2 ENGINE WILL NOT START AFTER (3) ATTEMPTS AND THEN AN OIL LEAK. MAINTENANCE REPLACED THE ENGINE I GNITERS AND CLEANED THE RESIDUAL OIL. ENGINE WAS THEN STARTED SUCCESSFULLY AND RUN TO TROUBLESHOOT THE OIL LEAK. NO OIL LEAK COULD BE FOUND AND IT WAS SUSPECTED TO BE AS A RESULT OF THE NO START CONDITION. ON JANUARY 18, 2007 LAVATORY SMOKE DETECTOR ACTIVATED ON FINAL APPROACH. FLIGHT ATTENDANT DETECTED ODOR ON GROUND. MAINTENANCE REPLACED DETECTOR (P/N 46-0 083-4) AND SYSTEM CHECKED SERVICEABLE. ON NEXT FLIGHT, DETECTOR ACTIVATED AGAIN WITH NO SMOKE OR ODOR. LOW BATTERY (TC N 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007051100174 20070511 00174 SO 2007 5 11 CA070126009 1 20070118 G 3246 402377 BOLT PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2A GL LT MLG BROKEN W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) WHILE TAXIING, THE UPPER TORQUE LINK BOLT BROKE WHICH ALLOWED THE LT MAIN WHEEL TO TURN SIDEWAYS. (TC NR 200701260 09) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007051100175 20070511 00175 CE 2007 5 11 CA070126010 1 20070123 G 2110 206SZZC BEARING BEECH 115555024 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL COMPRESSOR DISINTEGRATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BEARING WITHIN RT ENGINE AIR CONDITIONING COMPRESSOR DRIVE PULLEY DISINTEGRATED WHICH GREATLY CAUSED FURTHER HARM TO ITS ASSOCIATED PARTS. THE QUILL SHAFT, COMPRESSOR DRIVE PULLEY, COMPRESSOR MOUNT ASSEMBLY, DRIVE SUPPORT, BEARING SH IMS AND SPACER, AND DUAL BELT (COMPRESSOR DRIVE BELT) HAVE HAD IRREVOCABLE DAMAGE. QUILL SHAFT DID NOT SHEAR. (TC NR 200 70126010) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007080800131 20070808 00131 CE 2007 8 8 CA070126011 1 20070118 G 3213 50411148 TORQUE LINK CESSNA 401 401 207590C CE RT MLG FAILED W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) AIRCRAFT WAS DOING TOUCH AND GO`S ON THE 2ND LANDING PILOT REPORTED ABNORMAL LANDING AND NO GEAR UP INDICATION. G EAR CYCLED AND ONLY 2 OUT OF 3 INDICATOR LIGHTS ILUMINATED. RT MAIN, NO INDICATION. GEAR CYCLED AGAIN NO UP INDICATION A ND NO RT GREEN DOWN INDICATION. AIRCRAFT COMPLETED FLY BY CONTROL TOWER WHEN PILOT WAS INFORMED OF HIS RT MAIN WHEEL AT A 45 DEGREE ANGLE. AIRCRAFT CARRIED OUT A FLY OVER OF MORGAN AIR`S FACILITY WHERE WITH BINOCULARS, I COULD SEE THE RT MA IN GEAR OVER CENTER DOWN AND LOCK WAS OVER CENTERED. PILOT CARRIED OUT SUCCESSFUL LANDING AND AIRCRAFT WAS REMOVED FROM RUNWAY WITHIN 10 MINUTES. (TC NR 20070126011) 1 L 7 2 3O A7CE 2007051100178 20070511 00178 2007 5 11 CA070126012 4 20070124 G 2300 FEEDER CABLE BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33112UHR WP ROTOL R333 R333482F12 GL RADIO LOOSE W O OTHER H ELECT. POWER LOSS-50 PC AP APPROACH 1 CA (CAN) TOTAL LOSS OF CAPT`S RADIO COMMUNICATIONS. TROUBLESHOOTING FOUND MAIN POWER FEED CONNECTION NOT TIGHTEN ON TERMINA L BLOCK T5GA CAUSING CONNECTOR TERMINAL RING TO FLOAT AND REMOVE POWER SUPPLY TO CAPT`S AUDIO STATION BOX (TC NR 2007012 6012) 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C P61GL 2007051100179 20070511 00179 NE 2007 5 11 CA070126013 2 20070126 G 7220 FAN CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE ENGINE DISLODGED W B A EMER. DESCENT UNSCHED LANDING D T Y INFLIGHT SEPARATION ENGINE CASE PENETRATION ENGINE STOPPAGE CL CLIMB 1 CA (CAN) THE NR 1 ENGINE FAN DISLODGED ITSELF FROM THE ENGINE AND TORE OFF THE INLET AND FAN CASING. IT ALSO DID EXTENSIVE DAMAGE TO THE PYLON AND THE FUSELAGE. NTSB IS ON SITE FOR THE INVESTIGATION. MORE INFORMATIOON TO FOLLOW ONCE AVAILABLE . (TC NR 20070126013) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100180 20070511 00180 SO 2007 5 11 CA070127002 1 20070123 G 6120 454254 CONTROL CABLE PIPER PA31 PA31325 7103105 SO LYC O540 TIO540F2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL PROPELLER FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 317512033 (CAN) LT PROPELLER CONTROL CABLE FAILURE. THE PILOT NOTED THAT THE LT PROPELLER CONTROL WAS STIFF ON APPROACH. THE LT EN GINE AND PROPELLER CONTROLS WERE INSPECTED, MAINTENANCE DETERMINED THE LT PROPELLER CONTROL CABLE IN THE CABIN PEDESTAL HAD FAILED. THE PROPELLER CONTROL CABLE WIRES HAD TWISTED AND SEVERED APPROXIMATELY .2500 FROM THE SWAGED PORTION OF THE ROD END. THE LT PROPELLER CONTROL CABLE PN: 454-254 (ALT P/N: 24894-08) WAS REPLACED. THE AIRCRAFT RETURNED TO SERVICE . (TC NR 20070127002) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007051600133 20070516 00133 NE 2007 5 16 CA070128001 2 20070125 G 7250 BEARING SEAL CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE NR 2 ENGINE LEAKING W A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA 11811 11811 872974 (CAN) REPORTS OF LAV SMOKE CAUTION MSG COMING ON. PROBLEM APPEARS TO HAVE BEGUN ON DEC 5,2006 FLT. 8620, ON CLIMB-OUT, C REW RECEIVED A LAV SMOKE DETECT CAUTION LIGHT, FA CHECKED LAV NO SMOKE WAS EVIDENT, FLIGHT RETURNED TO DEPARTURE. A/C WA S DE-ICED PRIOR TO DEPARTURE AND DE-ICE FLUID WAS THE SUSPECTED CAUSE. BOTH COALESER BAGS WERE REPLACED AND GROUND RUNS WERE CARRIED OUT. A 2ND EVENT OCCURRED ON THE GROUND , DEC 5,2006, LAV SMOKE MSG CAME ON FOR 30 SEC’S THEN DID NOT COM E ON AGAIN, C/B’S WERE RESET AND A/C WAS POWERED DOWN AND RESET, FUNCTION CHECKED SERVICEABLE. 3RD EVENT, JANUARY 17, 2 007, FLT. 7690, SHORTLY AFTER ROTATION, FLIGHT CREW RECEIVED A SMOKE IN THE LAV INDICATION AND FA CONFIRMED LAV SMOKE D 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100183 20070511 00183 EA 2007 5 11 CA070128002 1 20070126 G 4900 APU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE CONTAMINATED W O OTHER B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA (CAN) SHORTLY AFTER DEPARTURE, THE CREW NOTICED A LAV SMOKE WARNING AND SMOKE WAS VISIBLE IN THE CABIN FOR 3-4 MINUTES THEN IT DISSIPATED. SMOKE WAS BLUISH IN COLOR AND OILY SMELLING. (2) MAINTENANCE PERSONNEL WERE ON BOARD, INITIALLY THEY THOUGHT SINCE THE AIRCRAFT HAD JUST BEEN DE-ICED WITH ENGINES AND APU RUNNING THAT DE-ICE FLUID WAS THE CAUSE SO A DECI SION WAS MADE TO CONTINUE. THE COALESER BAGS WERE INSPECTED AND REPLACED. AFTER ENGINE RUNS AND FURTHER TROUBLESHOOTING IT WAS NOTICED THAT NR 2 PRSOV IS RUNNING AT 38 TO 41 PSI AND MAY HAVE CAUSED DAMAGE TO NR 2 ACM. FURTHER TROUBLESHOOTI NG ON GOING. (TC NR 20070128002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100184 20070511 00184 EU 2007 5 11 CA070129001 1 20070127 G 3800 LINE EMB ERJ190 ERJ190100IGW 3260408 EU WATER LEAKING W O OTHER K FLUID LOSS CR CRUISE 1 CA 2865 (CAN) REPORTED STIFF AILERONS IN FLIGHT AND IT APPEARS THE ROOT CAUSE WAS A WATER LEAK RESULTING IN WATER POOLING IN THE BILGE AND BINDING THE AILERON CABLES. AN INVESTIGATION IS STILL TAKING PLACE. (TC NR 20070129001) 2 L 7 2 4F RT A57NM 2007051100185 20070511 00185 EU 2007 5 11 CA070129002 1 20070125 G 3244 TIRE EMB ERJ190 ERJ190100IGW 3260408 EU MLG FAILED W O OTHER O OTHER LD LANDING 1 CA (CAN) ON LANDING, RT OB MAIN WHEEL TIRE FAILED, DUE TO BRAKE SEIZING. INVESTIGATION STILL UNDERWAY ON CAUSE. (TC NR 2007 0129002) 2 L 7 2 4F RT A57NM 2007053000007 20070530 00007 GL 2007 5 30 CA070129003 1 20070122 G 3810 4E32612 VALVE BFGOODRICH BOMBDR BD700 BD7001A10 1390006 GL WATER SYSTEM OPEN W H DEACTIVATE SYST/CIRCUITS K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) OVER AN HOUR INTO THE FLIGHT, A SPOILER MOMENTARY DEPLOYMENT WITH WING ROLL AFTER SPOILER FAULT CAS OCCURRED. FLI GHT SPOILER FAIL CAS POSTED SHORTLY AFTERWARDS. SEVERAL CABIN SYSTEM MALFUNCTIONS OCCURRING NEXT FOLLOWED BY HAVING NO WATER FROM ANY FAUCET AVAILABLE. A/C LANDED AT FINAL DESTINATION AND SPOILER/STAB IN BIT CAS POSTED. WATER NOTED TO BE D RAINING FROM FORWARD FUSELAGE BELLY SKIN DRAINS WITH WATER TANK QUANTITY SHOWING EMPTY. GALLEY CARPET FOUND WET WITH GA LLEY UNDER SINK AREA WET AS WELL. VISUAL INSPECTION OF AVIONICS BAY CARRIED OUT WITH FCU RESET PROCEDURE CARRIED OUT. SP OILER FAIL CAS CLEARED WITH SPOILER/STAB IN BIT ONLY THAT WAS MMEL`D . WATER SYSTEM LEFT EMPTY AND TURNED OFF FOR UNEVEN 2 L 7 2 4F RT T00003NY 2007051100186 20070511 00186 EA 2007 5 11 CA070129004 1 20070115 G 2560 11011200 BUCKLE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL CREW SEATBELT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SPECIAL INSPECTION OF CREW SEAT BELT ROTORY LATCH SYSTEM PERFORMED. BOTH LT AND RT CREW SEATBELT BUCKLE ASSEMBLIES WERE CAPABLE OF BEING UNLATCHED WHEN CONTACTED BY THE CONTROL YOKE WHEN ROTATED LT OR RT WITH THE YOKE FULL AFT AND THE SEAT IN THE MOST FORWARD POSITION. THIS SPECIAL INSPECTION WAS MANDATED BY A COMPANY CAMPAIGN NOTICE TO INSPECT AIRCRAF T IAW FAA SPECIAL AIRWORTHINESS INFORMATION BULLETIN (NM-06-39)TO DATE, NO RECTIFICATION FOR THIS PROBLEM HAS BEEN PUBLI SHED. (TC NR20070129004) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007051100188 20070511 00188 NM 2007 5 11 CA070129005 1 20070128 G 3230 83221002003 LOCK DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NLG DAMAGED W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF THE NOSE LANDING GEAR FAILED TO RETRACT. FLIGHT CONTINUED AND LANDED TO THE DESTINATION AIRPORT WIT HOUT FURTHER INCIDENT. MAINTENANCE INSPECTED THE AIRCRAFT AFTER ARRIVAL AND FOUND THE NOSE GEAR GROUND LOCK OUT, AND IN LOCK POSITION. (TC NR 20070129005) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007051100191 20070511 00191 SW 2007 5 11 CA070129007 1 20070125 G 6510 DRIVE SHAFT BELL 407 407 1182206 SW TAIL ROTOR BROKEN W O OTHER O OTHER LD LANDING 1 CA (CAN) THE A/C WAS BEING LANDED TO DROP OFF SKIERS AND REPORTEDLY HAD A T/R DRIVE SHAFT BREAK BETWEEN THE ENGINE AND THE OIL COOLER. THE A/C WAS LANDED WITHOUT DAMAGE. THERE WAS NO INDICATION OF A T/R STRIKE. (TC NR 20070129007) 1 G 7 1 3U O H2SW 2007051500188 20070515 00188 NM 2007 5 15 CA070129008 1 20070126 G 3230 483023 VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU LT NACELLE FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 215 (CAN) CREW REPORTED THAT THE GEAR WENT UP BUT THE LT MAIN LANDING GEAR DOORS REMAINED OPEN. JACKED AIRCRAFT AND PERFORM ED A GEAR SWING. GEAR WENT UP BUT THE LT DOORS REMAINED OPEN AFTER SYSTEM WENT TO BYPASS MODE. ON SELECTION OF GEAR DOW N THE LT MAIN GEAR DOORS CLOSED AND THE GEAR CAME DOWN WITH THE LT UPLOCK RELEASING. RETRACTED THE GEAR AND TURNED OFF THE HYDRAULICS. PERFORMED AN ALTERNATE GEAR EXTENSION TO GET THE GEAR DOWN. (TC NR 20070129008) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007051100194 20070511 00194 EA 2007 5 11 CA070130001 1 20070129 G 2820 LINE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL FUEL VACUUM LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLIGHT CREWS REPORTED THAT FUEL FLOW FLUCTUATES WHEN BOOST PUMPS ARE SELECTED OFF. SEVERAL VACUUM LEAKS WHERE FOUN D IN THE FUEL LINES IN THE NACELLE AREA. SYSTEM SEALED AS REQUIRED, ENGINE GROUND RUNS CARRIED OUT AND NO FLUCTUATIONS N OTED AT TAKEOFF POWER WITH BOOST PUMPS OFF. (TC NR 20070130001) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007051600134 20070516 00134 2007 5 16 CA070130002 4 20070123 G 3414 INDICATOR BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU AIRSPEED INOPERATIVE W C ABORTED TAKEOFF P NO WARNING INDICATION TO TAKEOFF 1 CA (CAN) ON TAKEOFF ROLL THE CREW REJECTED THE TAKEOFF AT 85 KTS WITH NO INDICATION ON FIRST OFFICERS SIDE. MAINTENANCE CON DUCTED A PURGE OF THE SYSTEM AND CARRIED OUT A PITOT/STATIC SYSTEM TEST.THE SYSTEM WAS VERIFIED SERVICEABLE AND THE AIRC RAFT RETURNED TO SERVICE. (TC NR 20070130002) 2 L 7 2 3T 4 T A24EU A196 6 C P899 2007051100195 20070511 00195 CE 2007 5 11 CA070130003 1 20070129 G 7600 5052456849 CONDITION LEVER BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL CONTROL PEDESTAL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PILOTS REPORTED LT FUEL CONDITION LEVER CRACKED HALF WAY DOWN LEVER. AIRCRAFT REMOVED FROM SERVICE. RT CONDITION LEVER INSPECTED AND SHOWED SIGNS OF WEAR. LT AND RT CONDITION LEVERS ON ORDER. (TC NR 20070130003) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007051100196 20070511 00196 NM 2007 5 11 CA070130004 1 20070126 G 2820 O-RING BOEING 767 767306 1385148 NM GE CF6 CF680C2B6F 30025 NE FUEL SYSTEM LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 CA (CAN) AC LANDED WITH LOW HYD FLUID IN CENTER SYS FOUND ACMP NR 2 CENTER FILTER MODULE PRESSURE DELTA P POP-UP LEAKING DU E TO A FAILED O-RING. O-RING REPLACED AND HYD SYSTEM SERVICED (37 QTS). (TC NR 20070130004) 2 L 7 2 4F 4 F RT A1NM E13NE 2007051100198 20070511 00198 EA 2007 5 11 CA070131001 2 20070129 G 7397 CONNECTOR BENDIX DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL NR 1 TRANSMITTER SEPARATED W O OTHER N FALSE WARNING NR NOT REPORTED 1 CA 4801 812141 (CAN) AIRCREW REPORTED THAT THE NR 1 FUEL FLOW WAS FLUCTUATING WITH NO OTHER ENGINE PARAMETERS BEING AFFECTED. MAINTENAN CE TROUBLESHOT THE SYSTEM, SWAPPED GAUGES FROM SIDE TO SIDE, PERFORMED ENGINE RUNS AND COULD NOT FAULT THE SYSTEM. AIRC RAFT WAS RELEASED FOR FLIGHT. WHEN AIRCRAFT RETURNED TO BASE THE AIRCREW REPORTED THAT THE SNAG WAS STILL PRESENT. MAINT ENANCE BEGAN INVESTIGATING DEEPER INTO SYSTEM. WHEN THE NR 1 FUEL FLOW TRANSMITTER WAS LOOKED AT, IT WAS FOUND THAT THE CONNECTOR PLUG BOSS HAD SEPARATED FROM THE MAIN BODY, THIS ALLOWED THE WIRES TO STRIKE THE HOUSING SIDES DURING FLIGHT D UE TO NORMAL VIBRATIONS, SHORTING OUT THE TRANSMITTER. THIS COMPONENT HAS BEEN INSTALLED ON THE AIRCRAFT SINCE WE TOOK P 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007080800132 20070808 00132 EA 2007 8 8 CA070131002 1 20070131 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE TE FLAPS MALFUNCTIONED W O OTHER J WARNING INDICATION LD LANDING 1 CA (CAN) THE CREW REPORTED THAT ON APPROACH THAT THEY RECEIVED AN INITIAL FLAP HALFSPEED MESSAGE FOLLOWED BY A (FLAP FAIL) MESSAGE WHEN FLAPS SELECTED ON APPROACH. ZERO FLAP LANDING WAS COMPLETED. THE AIRCRAFT IS CURRENTLY WITH LINE MAINTENAN CE TROUBELSHOOTING THE INCIDENT. (TC NR 20070131002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100200 20070511 00200 EA 2007 5 11 CA070131003 1 20070130 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) THE CREW REPORTED THAT UPON APPROACH FLAPS 8 DEGREES WERE SELECTED OKAY. UPON FLAP 20 DEGREE SELECTION, THE FLAPS DID NOT MOVE AND THE FLAP FAIL CAUTION LIGHT ILLUMINATED. THE FLAPS LOCKED AT 8 DEGREES. THE AIRCRAFT IS CURRENTLY IN LI NE, MAINTENANCE IS TROUBLESHOOTING.(TC NR 20070131003) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100202 20070511 00202 SW 2007 5 11 CA070131004 1 20070122 G 6210 206010200133 BLADES BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR OUT OF BALANCE W K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 CA (CAN) COULD NOT ACHEIVE DYNAMIC BALANCE OF A/C. (TC NR 20070131004) 1 G 7 1 3U 3 U H2SW E4CE 2007080800133 20070808 00133 EA 2007 8 8 CA070131005 1 20070124 G 3230 LANDING GEAR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE MAINS INOPERATIVE W O OTHER O OTHER LD LANDING 1 CA (CAN) THE AIRCRAFT LANDED WITH ALL LANDING GEAR UP. BA FSR ON SITE. FSR REPORTED THAT THE ADG WAS DEPLOYED, AND FLAPS RE TRACTED. AIRPORT AUTHORITIES ARE PRESENTLY IN THE PROCESS OF LIFTING THE A/C IAW THE AIRCRAFT RECOVERY MANUAL USING CRAN ES. AIRCRAFT CONDITION APPEARS TO BE GOOD. CONFIRMATION OF A WHEELS UP LANDING HAS BEEN RECEIVED. BA AIR SAFETY IS IN CONTACT WITH THE TSBC TO ESTABLISH WHAT ACTUALLY OCCURRED. IT IS NOT KNOWN IF THERE WERE ANY INJURIES. AN UPDATE WILL BE ISSUED SHORTLY. THE TSBC HAS CONTACTED THE CIAIC (SAFETY BOARD) OF SPAIN. THE BA RESPONSE WILL BE BASED ON THE NEXT UPD ATE FROM BARCELONA. THE FOLLOWING COULD BE OBSERVED IN THE COCKPIT (VERY LIMITED TIME ALLOWED): LANDING GEAR CONTROL H 2 L 7 2 4F 4 F RT A21EA E15NE 2007051100203 20070511 00203 EU 2007 5 11 CA070131007 1 20070128 G 5610 1379628C401 WINDSHIELD BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33110UG 01514 WP MCAULY 4HFR34 4HFR34C652 NE COCKPIT DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING MAINTENANCE INSPECTION, WINDOW WAS FOUND TO BE DELAMINATING AT THE CENTER OF THE BOTTOM EDGE. WINDOW WAS RE PLACED. (TC NR 20070131007) 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C 3PNE 2007051100204 20070511 00204 EU 2007 5 11 CA070131008 1 20070131 G 2910 373Q2277 LINE BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU HYDRAULIC SYS LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) IN CRUISE FLIGHT (30 MINUTES AFTER DEPARTURE THE FLIGHT CREW OBSERVED NR 1 AND NR 2 LOW HYDRAULIC PRESSURE LIGHTS ILLUMINATED. THE FLIGHT CREW RETURNED TO DEPARTURE, USED ALTERNATE MEANS FOR EXTENDING THE LANDING GEAR AND LANDED UNEVE NTFUL. MAINTENANCE FOUND INSUFFICENT FLUID IN THE HYDRAULIC SYSTEM. A LEAK IN HYDRAULIC LINE P/N 373Q2277, CAUSED BY CH AFING WAS FOUND IN THE LT MAIN LANDING GEAR WHEEL WELL. THE LINE WAS REPLACED, SYSTEM BLEED AND FUNCTION CHECKED OK. (TC NR 20070131008) 2 L 7 2 3T 4 T A24EU A196 6 C P899 2007051400004 20070514 00004 NM 2007 5 14 CA070201003 1 20070201 G 3246 31573 WHEEL BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NR 3 FAILED W O OTHER O OTHER LD LANDING 1 CA (CAN) AN AIRCRAFT EXPERIENCED NR 3 WHEEL AND TIRE SEPARATION UPON LANDING DUE TO WHEEL BEARING FAILURE. DETERIORATION OF THE MAIN LANDING GEAR WHEEL BEARINGS, RESULTING IN DAMAGE TO THE WHEEL, AXLE, AND BRAKE UNITS. (TC NR 20070201003) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007051400005 20070514 00005 EA 2007 5 14 CA070201004 1 20070201 G 2797 WIRE CNDAIR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE FLAP SYSTEM BROKEN W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA (CAN) APPROX 1 MILE OUTSIDE THE OUTER MARKER AT 3000 AGL, THE AMBER FLAP CAUTION LIGHT ILLUMINATED. THE CREW SELECTED F LAP 20 AND THE FLAPS WENT TO 20. WHEN THE LIGHT ILLUMINATED THE CREW WENT THROUGH THEIR EMERGENCY CHECKLIST AND CARRIED OUT AN UNEVENTFUL LANDING. THE AIRCRAFT WAS THEN FERRIED FOR MAINTENANCE. ALL FLAP ACTUATORS WERE PURGED AND SERVICED WITH FRESH GREASE IAW MM TASK 12-20-29-640-805. BOTH BPSU’S WERE REPLACED IAW MM TASK 27-51-10-000-80. FLAP OPERATIONA L TESTS AND A TEST FLIGHT WERE CARRIED OUT WITH NO FAULTS FOUND. JANUARY 29/2007 IN HOUSE TASK RJ2-275002 FLAP MOISTURE PREVENTION PROGRAM WAS CARRIED OUT. JANUARY 30/2007 THE AIRCRAFT FLEW FOUR LEGS AND ON THE FORTH LEG, THE FLAPS FAILED 2 L 7 2 4F 4 F RT A21EA E15NE 2007051400006 20070514 00006 EU 2007 5 14 CA070201005 1 20070130 G 2710 S27010022120100 WASHER AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE AILERON SPLIT W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) THE CREW OBSERVED BINDING IN THE AILERON SYSTEM WHILE EXECUTING A RT TURN DURING DEPARTURE. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. POST FLIGHT INSPECTION DETECTED A LOCATION IN THE SYSTEM WHICH EXHIBITED AN INCREASED RESISTANCE TO TRAVEL WHEN CYCLING THE SYSTEM BUT THERE WAS NO RESTRICTION TO FULL MOVEMENT. MAINTENANCE FOU ND A SPLIT TEFLON WASHER FOULING THE BEARING AT THE SWING LINK BETWEEN RIBS 8 AND 9. THE WASHER WAS REPLACED AND THE AIR CRAFT WAS RETURNED TO SERVICE WITHOUT FURTHER PROBLEM. (TC NR 20070201005) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008032000001 20080320 00001 CE 2008 3 20 CA070201007 1 20070123 G 3244 0283353 TIRE BEECH 200 B200 1152922 CE SIDEWALL SCORED W K NONE O OTHER IN INSP/MAINT 1 CA 18 (CAN) DURING MAINT WALK AROUND INSP, IT WAS NOTED THAT ALL (4) MLG LOCATIONS RECEIVED SIDE WALL DAMAGE ON FIRST 20 HRS O F FLIGHT ON A FACTORY NEW AC DUE TO INTERFERENCE FIT. AC HAS (2) STC’S INCLUDED IN THE MLG. THEY ARE AS FOLLOWS: AC EQ UIPPED WITH (P/N:028-335-3) (WILDERNESS TIRES): STC SA00184LA. AC ALSO EQUIPPED WITH WHEEL AND BRAKE CONVERSION KIT: STC SA757GL BY STC HOLDER - MFG WAS CONTACTED AND STATED THAT THEY WERE AWARE OF THE PROBLEM SOME SIX MONTHS AGO. I’M TOLD THE PROBLEM HAS ARISEN WITH THE (19.5X6.75-8/10/190 P/N:028335-3) WHEN MFG OUTSOURCED ITS MANUFACTURE TO FROM THE E XISTING USA FACILITY. THE OUT OF COUNTRY MFG TIRES ARE BUILT TO A WIDER TOLERANCE FOR SOME REASON. NOTE: ALL AFFECTED TI 1 L 7 2 4T A24CE 2007051400007 20070514 00007 GL 2007 5 14 CA070201008 2 20070127 G 7321 23034702 FCU HUGHES 369 369HS 4470728 WP ALLSN 250C 250C20 03013 GL THROTTLE LEVER FAILED W E ENGINE SHUTDOWN K FLUID LOSS NR NOT REPORTED 1 CA 2719 CAE820727 (CAN) AFTER THE AIRCRAFT WAS STARTED, THE PILOT DECIDED TO DO A WALK AROUND THE AIRCRAFT. FUEL WAS NOTICED FLOWING FROM THE ENGINE BAY TO THE GROUND. FURTHER INVESTIGATION REVEALED A MASSIVE FUEL LEAK AT THE FUEL CONTROL THROTTLE LEVER SHAF T SEAL. FUEL WAS FLOWING FROM THE FUEL CONTROL AND SATURATING THE STARTER GENERATOR WITH FUEL. THE ENGINE WAS SHUTDOWN A ND THE AIRCRAFT EVACUATED. FCU REPLACED WITH SERVICABLE UNIT, STARTER VISUALLY INSPECTED AIRCRAFT GROUND RUN, LEAK CHECK ED AND TEST FLOWN. AIRCRAFT RELEASED. THIS COULD HAVE BEEN A DIFFERENT STORY. NORMALLY THE PILOT WOULD HAVE JUST TAKEN OFF AFTER STARTING THE AIRCRAFT. HIS DECISION TO PERFORM A WALK AROUND MAY HAVE SAVED LIVES AS THE AMOUNT OF FUEL LEAKIN 1 G 7 1 3U 3 U H3WE E4CE 2007051400011 20070514 00011 SW 2007 5 14 CA070201009 1 20070201 G 2410 BRACKET LYC LW11147 GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCC3Y HCC3YR2 NE ALTERNATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE ALTERNATOR ADJUSTING BRACKET BOLT HOLE THAT ATTACHES THE BRACKET TO THE ENGINE WAS FOUND CRACKED ALL THE WAY T HROUGH. THE BRACKET WAS ONLY BEING HELD IN PLACE BY THE TENSION OF THE BELT. THERE IS SEVERAL OTHER REPORTS OF CRACKS IN THE BOLT HOLE OF THIS BRACKET ON OUR ENGINES. (TC NR 20070201009) 1 H 7 2 3O 3 O 6A1 1E4 5 C P25EA 2007080800135 20070808 00135 EU 2007 8 8 CA070202001 1 20070130 G 7110 5711012091 COWLING PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL DAMAGED W A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 CA 14281 (CAN) AFTER TAKEOFF THE PILOTS NOTICED THAT THE TOP FRONT COWLING WAS LIFTING OFF AT THE REAR. THEY RETURNED TO THE FIEL D AND DURING THE FLARE THE COWLING DEPARTED THE AIRCRAFT, STRIKING AND DAMAGING THE PROP REQUIRING ITS DISASSEMBLY AND R T WING DAMAGING THE OB DEICE BOOT. THE POWER SECTION WAS REMOVED FOR A PROP STRIKE INSPECTION. MAINTENANCE HAD BEEN ACCO MPLISHED THE PREVIOUS EVENING WHERE THAT COWLING HAD BEEN REMOVED AND REINSTALLED. THE (4) LATCHES APPEARED SECURE TO TH E AME AND THE PILOTS ON THEIR WALK AROUND. THERE IS NO VISUAL AID ON THIS COWLING DESIGN OTHER THEN THE LATCH BEING (FLU SH) TO INDICATE TO THE PILOT OR TECHNICIAN THAT THE LATCH IS SECURED. PREVIOUS EXPERIENCE HAS SHOWN THAT THE DIFFERENCE 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007051400013 20070514 00013 EA 2007 5 14 CA070202002 1 20070126 G 4930 38834491 LINE HONEYWELL 38004883 CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE APU FUEL CHAFED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA P160 (CAN) JANUARY 296/2007 DEFECT 591259, THERE WAS A FUEL SMELL COMING FROM THE APU BLEED. THE APU WAS DEFERRED AND INHIBI TED IAW MEL 49-10-01-1. JANUARY 29/2007 MAINTENANCE REPLACED THE ECU FOR TROUBLESHOOTING, BUT THERE WAS NO FIX. FEBRUAR Y 01/2007 FURTHER TROUBLESHOOTING CARRIED OUT BY MAINTENANCE AND APU FUEL LINE FOUND TO BE LEAKING ABOVE THE EXCITER BOX . THE ADEL CLAMP HAD CHAFED THROUGH THE LINE. FUEL LINE PN 3883449-1 WAS REPLACED, NEW CLAMPS INSTALLED AND APU LEAK AND FUNCTION CHECKED SERVICEABLE. APU HOUR SINCE OVERHAUL ARE 3254 AND CYCLES 2660. (TC NR 20070202002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051400015 20070514 00015 NM 2007 5 14 CA070202003 1 20070116 G 5210 SEAL BOEING 727 727225 1384077 NM PWA JT8 JT8D15A 52051 NE FAILED W G O2 MASK DEPLOYED O OTHER CR CRUISE 1 CA (CAN) DURING CRUISE AT FL320, CABIN RATE STARTED TO CLIMB AT 1500 FPM. CREW (CARGO FIT) DONED O2 MASKS. PRESSURIZATION C ONTROLLER SELECTED TO (MANUAL) AND (STBY), NO CHANGE. CARGO HEAT OUTFLOW VALVE CLOSED, RECOVERED PRESSURE. O2 REMOVED, F LIGHT CONTINUED WITHOUT FURTHER INCIDENT. MAINTENANCE CLEANED DOOR SEALS OF DEBRIS AND CARRIED OUT PRESSURIZATION CONTR OL TEST IAW MM 21-31-00 AND FOUND SERVICEABLE. (TC NR 20070202003) 2 L 7 3 4F 4 F A3WE E2EA 2007051400016 20070514 00016 NM 2007 5 14 CA070202004 1 20070117 G 2697 W27260718 WIRE BOEING 727 727225 1384077 NM PWA JT8 JT8D15A 52051 NE FIRE DETECTION SHORTED W F ACTIVATE FIRE EXT. N FALSE WARNING CL CLIMB 1 CA (CAN) DURING CLIMB AT FL120, APU FIRE LIGHT AND BELL ILLUMINATED. APU FIRE DRILL CARRIED OUT, REMAINED (ON). DECLARED EM ERGENCY, RETURNED TO AIRPORT WITHOUT INCIDENT. UPON INSPECTION NO FIRE DETECTED. MAINTENANCE FOUND (FIRE WARNING) WIRE NR W272-607-18 SHORTED TO GROUND. WIRE REPLACED, FUNCTIONED CHECKED SERVICEABLE IAW MM 26-15-01. (TC NR 20070202004) 2 L 7 3 4F 4 F A3WE E2EA 2007051400017 20070514 00017 NM 2007 5 14 CA070202005 1 20070130 G 7110 DUCT BOEING 727 727225 1384077 NM PWA JT8 JT8D15A 52051 NE ENGINE COWLING MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON ARRIVAL, MAINTENANCE NOTICED AN APPROXIMATELY 6 INCH HOLE IN NR 1 ENGINE COWL. FURTHER INVESTIGATION DETERMIN ED THE CAP ON THE 6TH STAGE SADDLE DUCT MISSING, LOCATED IN COWL. CAP INSTALLED AND SECURED IAW MM AND COWL REPAIRED. (T C NR 20070202005) 2 L 7 3 4F 4 F A3WE E2EA 2007051400018 20070514 00018 SW 2007 5 14 CA070202006 1 20070124 G 2432 301265AA DIODE BELL BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL BATTERY RELAY FAILED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA 81640 (CAN) SINCE THE DIODE FAILED, A DIRECT SHORT TO GROUND OCCURED. CAUSING THE BATTERY CIRCUIT WIRING TO BURN OFF ITS SHIE LDING AND THE DIODE PIG TAIL FROM X1 TO X2 ON THE RELAY HEATED UP TO THE POINT OF BREAKING, FLAME WAS PRESENT. THE BATT ERY SWITCH WAS NOT DAMAGED, NOR WAS THE RELAY. (TC NR 20070202006) 1 G 7 1 3U 3 U H2SW E1GL 2007051600135 20070516 00135 NM 2007 5 16 CA070202007 1 20070201 G 7500 311269001 ADAPTER DHAV DHC8 DHC8202 2809007 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE P3 BLEED AIR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9051 9051 PCE123291 (CAN) DURING ENGINE OIL SERVICING, TECHNICIAN NOTICED HEAT BLANKET WAS DAMAGED ON HP DUCT, BLANKET WAS REMOVED AND CRACK WAS FOUND ON DUCT. (TC NR 20070202007) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007080800136 20070808 00136 EU 2007 8 8 CA070202008 1 20070130 G 3251 NB046547R COLLAR BNORM BN2 BN2A26 1520226 EU LYC O540 O540E4C5 41532 EA HARTZL HCC2Y HCC2YK2 GL NLG STEERING BROKEN W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) NOSE LANDING GEAR STEERING COLLAR, BROKE IN TWO PIECES DURING GROUND HANDLING. COLLAR CRACKED AFT GREASE FITTING H OLE ANF FWD RT RELEASE DOG SLOT. (TC NR 20070202008) 1 H 7 2 3O 3 O A17EU E295 5 C P920 2007051400079 20070514 00079 NE 2007 5 14 CA070202009 2 20070114 G 7313 311992001 FUEL NOZZLE BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ROUTINE FUEL NOZZLE CLEANING AND FLOW TEST IT WAS NOTICED THAT ONE FUEL NOZZLE SHEATH WAS CRACKED FROM THE AIR BLEED SLOT AT A 45 DEGREE ANGLE TOWARDS THE NOZZLE HOLE. THE SHEATH HAD 400 HOURS TIME IN SERVICE SINCE LAST INSPECT ION. (TC NR 20070202009) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007080800137 20070808 00137 CE 2007 8 8 CA070202010 1 20070202 G 5540 12310231920 HINGE BRACKET CESSNA CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO HARTZL HCJ3Y PHCJ3YF1 GL RUDDER WORN W K NONE O OTHER IN INSP/MAINT 1 CA * (CAN) DURING A 200 HR INSPECTION THE RUDDER WAS REMOVED FROM THE AIRCRAFT TO REPLACE THE RUDDER HINGE BEARINGS. INSPECTI ON OF THE RUDDER HINGE PIONT BRACKETS FOUND THE UPPER BRACKET P/N 1231023-19 OF THE LOWER HINGE POINT WORN COMPLETLY THR OUGH BY THE BEARING, AND UPPER BRACKET P/N 1231023-20 HAD GROVES WORN INTO IT BY THE BEARING. THE BRACKETS WERE REPLACED WITH NEW PARTS AND THE RUDDER WAS REINSTALLED ON THE AIRCRAFT. (TC NR 20070202010) 1 H 7 1 3O 3 O A4CE E5CE 5 C P36EA 2007080800138 20070808 00138 EU 2007 8 8 CA070202011 1 20070201 G 3222 5322012165 BARREL NUT PILATS 532201203 PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 5232 IL192 (CAN) PILOT REPORTED THAT ON OCCASION DURING EXTENSION OF LANDING GEAR THAT A LOUD CLUNK WAS HEARD IN NOSE GEAR AREA.DUR ING A TEARDOWN OF NOSE LANDING GEAR TO REPLACE INTERNAL SEALS ,IT WAS NOTED THAT ON THE INNER GROOVE OF BARREL NUT ,THAT SUPPORTS A PHENOLIC GUIDE RING THAT CORROSION WAS OCCURING IN THE ALUMINIUM BARRLE NUT.THIS CORROSION PUT SO MUCH PRESS URE ON BACKSIDE OF GUIDE RING THAT THE RING WAS CLAMPING TO OLEO STRUT NOT ALLOWING THE STRUT TO FULLY EXTEND PRIOR TO R ETRACTION OF GEAR. WHEN GEAR WAS LOWERED IN COLD FLIGHT CONDITIONS THE NOSE FORK WOULD CONTACT GEAR RETRACT MECHANISM ON EXITING GEAR WELL CAUSING CLUNK. REMOVAL AND TREATMENT OF CORROSION, CLEANING OF GUIDE RING ALLOWED FREE MOVEMENT OF O 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007061300154 20070613 00154 NM 2007 6 13 CA070202012 1 20070131 G 2410 BEARING LUCAS DHAV DHC5 DHC5A 2803018 NM DC GENERATOR FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 1850 102 1093 (CAN) AIRCRAFT WAS RETURNING TO BASE WHEN THE NR 1 GENERATOR FAILED. FLIGHT WAS CONTINUED WITHOUT FURTHER PROBLEMS. WHEN MAINTENANCE REMOVED THE GENERATOR FOR REPLACEMENT THE QUILL SHAFT WAS FOUND SHEARED AND THE FORWARD BEARING ON THE GENE RATOR SUFFERED A CATASTROPHIC FAILURE AND WAS COMPLETELY DESTROYED. THE GENERATOR HAD JUST BEEN INSTALLED 102 HOURS PREV IOUSLY FRESH FROM OVERHAUL FACILITY. ANOTHER GENERATOR WAS INSTALLED AND CHECKED SERVICEABLE. (TC 20070202012) 2 H 7 2 4T RT 2007051400081 20070514 00081 EA 2007 5 14 CA070202013 1 20070202 G 2913 65WE01042 PUMP CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE HYDRAULIC SYS WORN W K NONE O OTHER IN INSP/MAINT 1 CA 763 (CAN) PUMP INSIDES COUPLING SPLINES BADLY WORN, OUT OF LIMITS. (TC NR 20070202013) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2007051400082 20070514 00082 NM 2007 5 14 CA070202014 1 20070118 G 5610 NP15790114 WINDSHIELD DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE COCKPIT CRACKED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 11448 (CAN) DURING FLIGHT, SMOKE AND FLAMES STARTING COMING FROM THE TOP OF FO`S WINDSCREEN. SECONDS LATER WINDSCREEN SHOWED SEVERAL CRACKS. FOUND TERMINAL END L2 BURNED, REMOVED AND REPLACED TERMINAL END AND F/O`S WINDSHIELD. (TC NR 200702020 14) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007051400083 20070514 00083 CE 2007 5 14 CA070202015 1 20070202 G 2612 473275 FIRE DETECTOR BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA HARTZL HCE4N HCE4N3 NE RT NACELLE MALFUNCTIONED W E F A ENGINE SHUTDOWN ACTIVATE FIRE EXT. UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA 289 (CAN) DURING A ROUTINE MISSION, THE RT FIRE WARNING ANNUNCIATOR LIGHTS ILLUMINATED. THERE WAS NO VISUAL INDICATION OF FI RE. THE PILOT`S SECURED THE ENGINE IAW PUBLISHED PROCEDURES, ACTIVATED THE FIRE SUPPRESSION SYSTEM AND RETURNED TO THE B ASE. MAINTENANCE WAS ABLE TO FAULT THE FIRE DETECTION SYSTEM FWD OF THE RT ENGINE FIREWALL, BUT WERE UNABLE TO PINPOINT THE EXACT CAUSE TO EITHER OF THE UPPER FIRE DETECTORS OR THE CONNECTING HARNESS. BOTH DETECTORS AND THE HARNESS WERE REP LACED. THE ENGINE WAS INSPECTED FOR DAMAGE FROM THE RELEASE OF FIRE SUPPRESSION AGENT. NO DAMAGE WAS EVIDENT. THE FIRE BOTTLE AND SQUIB WERE REPLACED. AIRCRAFT WAS RELEASED INTO SERVICE. (TC NR 20070202015) 1 L 7 2 3T 4 T RT 3A20 E4EA 5 C P10NE 2007051400084 20070514 00084 CE 2007 5 14 CA070202016 1 20070202 G 2810 509215873 GASKET BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA HARTZL HCE4N HCE4N3 NE RT ENGINE DAMAGED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 166 (CAN) PILOTS NOTICED FUEL (STREAMING) FROM THE RT NACELLE TOP COVER SHORTLY AFTER TAKEOFF. THE AIRCRAFT RETURNED TO BASE WITHOUT INCIDENT. THIS HAPPENED (3) TIMES BEFORE THE PROBLEM WAS CORRECTED. 1ST NOTICE, AFT 86.9 HRS. MAINTENANCE ATTRI BUTED THE EXCESS FUEL FOUND UNDER THE NACELLE COVER TO A PROBABLE FAULTY FUEL VENT CHECK VALVE ATTACHED TO THE FUEL FILL ER NECK IN THIS AREA. THIS AREA OF THE AIRCRAFT WAS REINSPECTED DURING SCHEDULED MAINTENANCE AND MINIMAL FUEL WAS NOTICE D. 2ND NOTICE - AFT 157.6 HRS. MAINTENANCE CHECKED THE AREA, PLUGGED THE VENT LINES AND FILLED THE FUEL CELL COMPLETELY . NO FAULTS WERE NOTED, SO ANOTHER CHECK VALVE WAS INSTALLED. 3RD NOTICE -- AFT 165.9 HRS. MAINTENANCE REMOVED THE RT NA 1 L 7 2 3T 4 T RT 3A20 E4EA 5 C P10NE 2007051400086 20070514 00086 CE 2007 5 14 CA070202017 1 20070201 G 2497 CONNECTOR CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA MCAULY 1C235 1C235LFA GL POWER JUNCTION CORRODED W O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 CA 3758 (CAN) DURING A PREFLIGHT INSPECTION WHEN THE FLAPS WERE SELECTED TO LOWER A COMPLETE POWER FAILURE RESULTED. UPON INSPEC TION BY THE AMO THE POWER JUNCTION BOX PLUG WAS FOUND CORRODED RESULTING IN PINS BREAKING WHEN PLUG WAS PULLED APART FOR INSPECTION. THIS PLUG FAILURE RESULTED IN A POOR CONTINUITY FROM THE MASTER SOLENOID AND THE MASTER SWITCH RESULTING IN A 12+ VOLTAGE LOSS AND THE HOMINOID FAILING TO ENGAGE. (TC NR 20070202017) 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P12EA 2007051400088 20070514 00088 EA 2007 5 14 CA070202018 1 20070201 G 3246 50105711 WHEEL CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE MLG DAMAGED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA 6836 (CAN) DURING ROTATION THE A/C PULLED TO THE LT ON CLIMB OUT , ASSOCIATED WITH SEVERE VIBRATION. THE FLIGHT CREW DECIDED TO DIVERT THE A/C. UPON LANDING THE ROB TIRE DEFLATED. UPON INVESTIGATION, THE FOLLOWING WAS FOUND . THE INNER RT MAIN WHEEL CORD WAS DAMAGED AND DEFLATED. ( FROM ORIGINAL REPORT ON T/O. BOTH MAIN WHEEL`S WERE REPLACED . THE OUTER RT MAIN WHEEL WAS DAMAGED ON LANDING. THE RT INNER FLAP WAS DAMAGED BY THE TIRE SEPARATION NR REPLACED . THE AFT FUSELAGE BODY FAIRING WAS SLIGHTLY DAMAGED AND REPAIRED UNDER REO 601R-53-82-267( 500 FT/HRS ) (TC NR 20070202018) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051400090 20070514 00090 EA 2007 5 14 CA070202019 1 20070131 G 5610 601R3303031 WINDOW CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C1 NE COCKPIT CRACKED W O OTHER O OTHER DE DESCENT 1 CA 8520 (CAN) CREW NOTED ON DESCENT, CAPT SIDE WINDOW CRACKED HOWEVER  CABIN PRESS REMAINED NORMAL AND A.C LANDED SAFELY. C/A-- -REMOVED AND REPLACED CAPT SIDE WINDOW IAW CRJ AMM 56-10-05 AND OPS CK GOOD MX REPORT CAPT SIDE WINDOW SHATTERED (TC N R 20070202019) 2 L 7 2 4F 4 F RT A21EA EOOO63EN 2007051400100 20070514 00100 EU 2007 5 14 CA070204001 1 20070201 G 5320 CHANNEL SNIAS 350 AS350D 8680803 EU LYC LTS101 LTS101600A2 41560 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN UNSCHEDULED MAINTENANCE PROCEDURE OF THE VIBRATION DAMPER ASSEMBLIES UNDER THE CABIN FLOOR, IT WAS FOUND THROUGH THE USE OF A BOROSCOPE THAT THE IB CHANNELS OF THE LATERAL SUPPORT STRUCTURE WERE CRACKED AT THE UPPER ENDS. S UBSEQUENT INSPECTION OF ALL OUR AIRCRAFT REVEALED SIMILAR DISCREPANCIES. (TC NR 20070204001) 1 G 7 1 3U 3 U H9EU E5NE 2007051400101 20070514 00101 EU 2007 5 14 CA070205001 1 20070202 G 6220 704A33341003 SPRING SNIAS 350 AS350* EU TMECA ARRIEL ARRIEL1B 6OO30 NE ANTI VIBRATION BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 11359 1460 (CAN) WE ARE DOING A 12 YEAR INSPECTION ON AIRCRAFT, AS WELL AS SEND IT OUT FOR PAINT. THE MAIN ROTOR ANTI-VIBRATOR WAS REMOVED FOR CHECK AND MODIFICATION. WHEN SPRINGS WERE REMOVED, ONE WAS FOUND TO BE BROKEN 40 MM FROM OB END. THIS AREA I S HIDDEN BEHIND SIDE COVERS. (TC NR 20070205001) 1 G 7 1 3U 3 U H9EU E19EU 2007051400103 20070514 00103 2007 5 14 CA070205002 4 20070203 G 3418 0861HB VANE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE AOA FAILED W O OTHER J WARNING INDICATION CL CLIMB 1 CA 1428 1428 (CAN) DURING CLIMB OUT STALL FAIL CAUTION MESSAGE ILLUMINATED. CREW UNABLE TO RESET DURING FLIGHT. CREW ELECTED TO LAND AT ENROUTE MAINTENANCE BASE. MAINTENANCE REPLACED RT AOA VANE, FUNCTION CHECKED AND AIRCRAFT RETURNED TO SERVICE (TC NR 20070205002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051400105 20070514 00105 EA 2007 5 14 CA070205003 1 20070203 G 2752 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE TE FLAP FAILED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH, CREW SELECTED FLAP 8 AND RECEIVED A (FLAP FAIL) MESSAGE. FLAP FAILED AT 0. CREW ADVISED ATC AND DECLA RED EMERGENCY. LANDING WAS UNEVENTFUL. (TC NR 20070205003) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051600136 20070516 00136 NM 2007 5 16 CA070205004 1 20070121 G 3231 83232013003 BELLCRANK DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE NLG DOOR BROKEN W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 3000 (CAN) AN OPERATOR MADE AIR TURN BACK DUE TO NOSE GEAR DOOR MALFUNCTION. THE NLG DOORS WON’T CLOSE WHEN SELECTED. THE AMB ER NOSE GEAR DOOR LIGHT SHOWED ON LANDING GEAR CONTROL PANEL. MAINTENANCE FOUND THE NOSE GEAR BELLCRANK BROKEN AT ONE OF THE LUGS. (TC NR 20070205004) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007051400107 20070514 00107 CE 2007 5 14 CA070205005 1 20070205 G 2560 497900312 BUCKLE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ROTARY SEAT BELT FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) REF FAA SPECIAL AIRWORTHINESS INFORMATION BULLETIN NM-06-29 AND MFG CAMPAIGN NOTICE 010-25-10-011 REV 1 FIXED WING AIRCRAFT EQUIPPED WITH ROTARY CREW SEAT BELT BUCKLES. WHEN THE CONTROL COLUMN IS PULLED FULLY AFT THE SEAT BELT BUCKLE CAN BE RELEASED BY ROTATING THE CONTROL WHEEL IN BOTH THE PILOT AND CO-PILOT POSITIONS. (TC NR 20070205005) 1 L 7 2 4F 4 F A22CE E1NE 2007051400110 20070514 00110 NM 2007 5 14 CA070205007 1 20070130 G 2741 651948218 GEARBOX BOEING 727 727227 1384078 NM PWA JT8 JT8D9A 52048 NE HORIZONTAL STAB FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) AFTER DEPARTURE, CREW EXPERIENCED STAB TRIM FAILURE. A/C RETURNED TO AIRPORT WITHOUT INCIDENT. MAINTENANCE CREWS FOUND THE STAB TRIM GEARBOX TO BE QUITE STIFF TO OPERATE AND REPLACED IT. A/C RETURNED TO SERVICE. THE STAB TRIM GEAR BOX AND JACKSCREW WERE INSPECTED AND LUBED ON A 2A CHECK NOV 19/2006. (TC NR 20070205007) 2 L 7 3 4F 4 F A3WE E2EA 2007051400112 20070514 00112 CE 2007 5 14 CA070206002 1 20070205 G 3260 LANDING GEAR BEECH 100 B100 1152919 CE GARRTT TPE331 TPE3316252B 01514 WP HARTZL HCB4T HCB4TN5 GL MAINS UNKNOWN W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) LANDING GEAR (IN TRANSIT) LIGHT STAYED ON AFTER GEAR UP SELECTION AFTER TAKEOFF. GEAR DOWN SELECTED AND GEAR WENT DOWN AND LOCKED NORMALLY (3 GREEN LIGHTS) FOR LANDING BACK TO DEPARTURE AIRPORT. AIRCRAFT JACKED, RETRACTIONS DONE, LAN DING GEARS INSPECTED, CLEANED AND LUBED, NO DEFAULT FOUND, SYSTEM FOUND SERVICEABLE. (TC NR 20070206002) 1 L 7 2 4T 4 T A14CE E2WE 6 C P40EA 2007051400115 20070514 00115 2007 5 14 CA070206003 4 20070204 G 8300 COVER CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE AGB DISLODGED W E ENGINE SHUTDOWN J WARNING INDICATION AP APPROACH 1 CA (CAN) APPROX 10 MINS INTO THEIR DESCENT, THE NR 1 OIL PRESSURE WARNING LIGHT ILLUMINATED. THE NR 1 OIL PRESSURE READ 0. THE CREW REFERENCED THEIR CHECKLIST AND SHUTDOWN THE ENGINE. THE CREW ANNOUNCED TO THE PAX THAT DUE TO LOW OIL PRESSURE THEY WERE GOING TO SHUT DOWN AN ENGINE. MAINTENANCE CHECKED AND CLEANED TRANSDUCER CONNECTOR PLUGS, OIL TANK AND ASSOCI ATED PLUMBING. THE ONLY ANOMALY NOTED WAS THE PLUG ON THE ACCESSORY GEAR BOX WAS NOT PROPERLY SECURED. THE CIRCLIP WAS O FF AND THE PLUG DISLODGED SOMEWHAT. THERE WAS NO EVIDENCE OF MASSIVE OIL LOSS, BUT SUSPECT WITH CAP OFF ENGINE WAS PROBA BLY SUCKING AIR, AND NOT PRESSURIZING ACCESSORY GEAR BOX PROPERLY. CIRCLIP SECURED. IDLE AND HIGH POWER RUNS COMPLETED S 2 L 7 2 4F 4 F RT A21EA E15NE 2007051400117 20070514 00117 CE 2007 5 14 CA070207001 1 20070203 G 3230 MC815A51 RELAY BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL MLG INOPERATIVE W O OTHER O OTHER NR NOT REPORTED 1 CA 484 (CAN) LANDING GEAR IN TRANSIT LIGHT STAYED ON AFTER GEAR WAS SELECTED UP AND AN ALTERNATE GEAR EXTENSION WAS DONE AND TH E A/C RETURNED TO BASE. THE LANDING GEAR CONTROL RELAY BOX WAS REPLACED AND LANDING GEAR SYSTEM FUNCTION CHECKED SERVICE ABLE. (TC NR 20070207001) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007051400119 20070514 00119 EA 2007 5 14 CA070207002 1 20070131 G 5210 600315351001 STRIKER CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE DOOR SEAL DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) DURING A TYPE III REPAIR (MFG REO 601R-53-22-033) DUE TO A CRACK FOUND ON THE OUTER FLANGE OF THE PASSENGER DOOR F WD SEAL STRIKER, THE FORWARD SEAL STRIKER FLANGE WAS FOUND CRACKED IN THE RADIUS (OVER 3INCHES IN LENGTH) UNDER AN EXIS TING REPAIR (REPAIR TYPE I, REO 601R-53-22-033). AFTER A VISUAL CHECK, THE AFT PASSENGER DOOR SEAL STRIKER (ALSO PREVIOU SLY REPAIRED TYPE I) WAS FOUND CRACKED IN THE RADIUS. (TC NR 20070207002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051400121 20070514 00121 CE 2007 5 14 CA070207003 1 20070206 G 2560 1101983 BUCKLE BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA HARTZL HCB3T HCB3TN3 GL CREW SEATBELTS DAMAGED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) CAMPAIGN NOTICE 010-25-10-011 / FAA SAIB NM-06-29. CREW SEAT BELT ROTARY LATCH IS CONTACED BY THE CONTROL YOKE AN D THE POSSIBLITY EXISTS TO RELEASE THE BELT WITH ROTATION OF THE CONTROL YOKE WHEN FUNCTIONAL TEST WAS CARRIED OUT IAW S AIB. (TC NR 20070207003) 1 L 7 2 3T 4 T RT 3A20 E4EA 6 C P15EA 2007051400131 20070514 00131 CE 2007 5 14 CA070207007 1 20070206 G 3310 LIGHT BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCD4N3 HCD4N3A GL CABIN INOPERATIVE W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA 8862 8862 (CAN) WHILE ON FINAL APPROACH, SMOKE WAS OBSERVED IN COCKPIT COMING FROM THE LOWER LT C/B PANEL. SIDE LIGHT C/B POPPED A ND SMOKE STOPPED. LANDING COMPLETED WITHOUT FURTHER INCIDENT. MAINTENANCE WAS CONTACTED AND IN CONVERSATION WITH FLIGHT CREW SMOKE PROBLEM WAS ISOLATED TO EDGE OF PANEL LIGHTING, C/B WAS PULLED AND POWER FUNCTION TEST REVEALED NO FURTHER S MOKE ISSUES. RETURN FLIGHT WITH ESSENTIAL CREW WAS CARRIED OUT. MAINTENANCE STAFF CONFIRMED PROBLEM AND SHORTED PANEL WA S REPAIRED. (TC NR 20070207007) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007051400133 20070514 00133 WP 2007 5 14 CA070207008 1 20070202 G 6710 A9182 BUNGEE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FLT CONTROLS DISCONNECTED W K NONE O OTHER IN INSP/MAINT 1 CA 87 (CAN) UPON INSPECTION, BUNGEE FOUND HANGING DOWN AND DISCONNECTED FROM THE FLIGHT CONTROL. THERE WERE NO FLIGHT PERFORMA NCE ISSUES REPORTED. MINOR SCRAPES FOUND IN CONTROL TUBE PAINT. CORDS WERE CHECKED FOR DAMAGE AND RECONNECTED. (TC NR 20 070207008) 1 G 7 1 3O 3 O H11NM 1E4 2007051400136 20070514 00136 EA 2007 5 14 CA070208001 1 20070207 G 2750 7805013 CONTROL LEVER CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE TE FLAP CONTROL DAMAGED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION LD LANDING 1 CA (CAN) AFTER LANDING WITH FLAPS SELECTED TO 45 DEGREES, THE CREW SELECTED FLAPS FROM 45 TO 20 DEGREES AND THE FLAPS DID N OT MOVE. CAPTAIN PUT THE FLAPS BACK TO 45 DEGREES. FECU (FLAPS ELECTRONIC CONTROL UNIT) CODES RETRIEVED BY MAINTENANCE P OINTED OUT TO THE FLAP CONTROL LEVER WHICH WAS REPLACED. (TC NR 20070208001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051400139 20070514 00139 CE 2007 5 14 CA070208002 1 20070128 G 5610 50420066137 WINDOW BEECH 100 B100 1152919 CE GARRTT TPE331 TPE3316252B 01514 WP HARTZL HCB4T HCB4TN5 GL COCKPIT DEPARTED W B EMER. DESCENT D INFLIGHT SEPARATION CL CLIMB 1 CA 10639 (CAN) AFTER TAKEOFF AND CLIMB TO APPROXIMATELY 10,000 FEET, THE LT. (TC NR 20070208002) 1 L 7 2 4T 4 T A14CE E2WE 6 C P40EA 2007051400157 20070514 00157 SO 2007 5 14 CA070208003 1 20070117 G 7603 30205002 THROTTLE CABLE PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YR2 GL FAILED W E ENGINE SHUTDOWN R F PARTIAL RPM/PWR LOSS FLT CONT AFFECTED DE DESCENT 1 CA (CAN) DURING DESCENT THE RT THROTTLE DID NOT RESPOND. THE ENGINE WAS SHUTDOWN AND PROPELLER FEATHERED. UPON RETURN TO TH E HANGAR, CABLE 30205-002 WAS REPLACED AND DUAL INSPECTION CARRIED OUT. (TC NR 20070208003) 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2007051400160 20070514 00160 CE 2007 5 14 CA070208004 1 20070207 G 2497 S21351 WIRE CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL CONNECTOR BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE INSPECTION IT WAS DISCOVERED THAT ONE WIRE GOING TO THE OVER VOLTAGE WARNING LIGHT WAS FOUND BURN ED. CAUSE OF THE BURNED WIRE WAS DUE TO FAILURE OF A BUTT SPLICE IN THE WIRE WHICH HAD EXPOSED THE BARE WIRE CAUSING IT TO SHORT OUT. THE BURNED SECTION OF WIRE WAS REPLACED. THE AIRCRAFT WAS GROUND CHECKED SERVICEABLE AND RETURNED TO SERV ICE. (TC NR 20070208004) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007051400164 20070514 00164 SW 2007 5 14 CA070208005 1 20070205 G 5610 2719442004 WINDSHIELD SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE COCKPIT CRACKED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 2415 (CAN) DURING TAXI WITH THE WINDSHEILD HEAT SELECTED ON THE RT COCKPIT HEATED WINDSHEILD CRACKED. THE FLIGHTCREW RETURNED TO THE TERMINAL AND THE AIRCRAFT WINDOW HAS BEEN REPALCED BY MAINTENANCE. NO CAUSE OF THE CRACKED GLASS COULD BE DETERM INED. THIS IS THE THIRD FAILURE OF A HEATED WINDSHEID THIS COMPANY HAS INCURRED SINCE JAN 1, 2007. 12 WERE REPORTED IN 2 006. OTHER AIRCRAFT OPERATORS OF THIS TYPE OF AIRCRAFT HAVE BEEN CONTACTED AND ARE INCURRING SIMILAR FAILURE RATES. (TC NR 20070208005) 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 2007051400161 20070514 00161 CE 2007 5 14 CA070209001 1 20070207 G 2560 110198301 BUCKLE BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA HARTZL HCB3T HCB3TN3 GL SEAT BELT ASSY DAMAGED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) WITH A COCKPIT CREW MEMBER STRAPPED INTO THEIR SEAT WITH THE SEAT FULLY FORWARD, INTERFERENCE BETWEEN THE CONTROL COLUMN YOKE AND THE ROTARY SEAT BELT BUCKLE FINS OCCURS WHEN THE CONTROL YOKE IS PULLED FULLY AFT AND ROTATED. THE POSSI BILITY EXISTS THAT THE SEAT BELT ROTARY BUCKLE COULD BE INADVERTENTLY RELEASED DURING EXTREME FLIGHT CONTROL MOVEMENTS. THIS CONDITION WAS VERIFIED WHILE PERFORMING THE PROCEDURE AS DESCIBED IN FAA SAIB NM-06-29. A GUARDED BUCKLE WOULD NEGA TE THE POSSIBILITY OF ACCIDENTAL RELEASE (TC NR 20070209001) 1 L 7 2 3T 4 T RT 3A20 E4EA 6 C P15EA 2007051400158 20070514 00158 CE 2007 5 14 CA070209002 1 20070207 G 2560 110193201 BUCKLE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE SEAT BELT MALFUNCTIONED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) WITH A COCKPIT CREW MEMBER STRAPPED INTO THEIR SEAT WITH THE SEAT FULLY FORWARD, INTERFERENCE BETWEEN THE CONTROL COLUMN YOKE AND THE ROTARY SEAT BELT BUCKLE FINS OCCURS WHEN THE CONTROL YOKE IS PULLED FULLY AFT AND ROTATED. THE POSSI BILITY EXISTS THAT THE SEAT BELT ROTARY BUCKLE COULD BE INADVERTENTLY RELEASED DURING EXTREME FLIGHT CONTROL MOVEMENTS. THIS CONDITION WAS VERIFIED WHILE PERFORMING THE PROCEDURE AS DESCIBED IN FAA SAIB NM-06-29. A GUARDED BUCKLE WOULD NEGA TE THE POSSIBILITY OF ACCIDENTAL RELEASE (TC NR 20070209002) 1 L 7 2 4F 4 F A22CE E1NE 2007051400159 20070514 00159 CE 2007 5 14 CA070209003 1 20070207 G 2560 110193201 BUCKLE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE CREW SEATS INTERFERENCE W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) WITH A COCKPIT CREW MEMBER STRAPPED INTO THEIR SEAT WITH THE SEAT FULLY FORWARD, INTERFERENCE BETWEEN THE CONTROL COLUMN YOKE AND THE ROTARY SEAT BELT BUCKLE FINS OCCURS WHEN THE CONTROL YOKE IS PULLED FULLY AFT AND ROTATED. THE POSSI BILITY EXISTS THAT THE SEAT BELT ROTARY BUCKLE COULD BE INADVERTENTLY RELEASED DURING EXTREME FLIGHT CONTROL MOVEMENTS. THIS CONDITION WAS VERIFIED WHILE PERFORMING THE PROCEDURE AS DESCIBED IN FAA SAIB NM-06-29. A GUARDED BUCKLE WOULD NEGA TE THE POSSIBILITY OF ACCIDENTAL RELEASE. (TC NR 20070209003) 1 L 7 2 4F 4 F A22CE E1NE 2007051400162 20070514 00162 GL 2007 5 14 CA070209004 3 20070203 G 6110 HCE4A3D PROPELLER PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL LEAKING W O OTHER K FLUID LOSS NR NOT REPORTED 1 CA 3188 3188 HJ1517 (CAN) DURING FLIGHT OIL WAS NOTICED ON THE WINDSCREEN WHILE ON ROUTE. UPON INSPECTION AFTER LANDING, MAINTENANCE FOUND E XCESSIVE OIL ON ENGINE COWLING. PROP WAS REMOVED AND SENT FOR REPAIRS. REPAIR SHOP CHANGED ALL THE INTERNAL SEALS AND RE TURNED THE PROP. REPAIRED PROP WAS RE-INSTALLED. AFTER 6 HRS IN OPERATION FLUID WAS NOTICED LEAKING FROM PROP AGAIN ALTH OUGH NOT TO THE DEGREE THAT OCCURRED ON THE FIRST OCCASION. AFTER CLEANING AND GROUND RUNS IT WAS DETERMINED THAT THE PR OP WAS LEAKING OIL AGAIN. PROP WAS REMOVED AND SENT FOR REPAIR AGAIN. REPAIR SHOP FINDINGS HAVE YET TO BE DETERMINED. ( TC NR 20070209004) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007051400163 20070514 00163 GL 2007 5 14 CA070209005 1 20070209 G 2720 C2TR445 BELLCRANK DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE RUDDER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 23428 (CAN) ON REMOVAL OF RUDDER FOR BEARING REPLACEMENT CORROSION WAS PRESENT ON THE OB ATTACH POINTS OF THE RUDDER BELLCRANK NR C2TR445 (PICTURE ATTACHED) CORROSION WAS NOT EVIDENT BEFORE THE REMOVAL OF THE RUDDER AS THE DAMAGED AREA WAS COVERE D BY THE RUDDER CONNECTING RODS NR C2UT233. THE AIRCRAFT NOTED ABOVE HAS BEEN OPERATED EXTENSIVELY FROM SALT WATER. (TC NR 20070209005) 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2007051400173 20070514 00173 NE 2007 5 14 CA070209008 2 20070111 G 7200 ENGINE BELL 427 427 1182207 SW PWC PW207 PW207D NE OVERSPEED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA BF0116 (CAN) THE ENGINE WENT TO AN OVERSPEED CONDITION ON TAKE-OFF AND THE TAKE-OFF WAS ABORTED. MFG WILL INVESTIGATE THE INCI DENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070209008) 1 G 7 1 3U 3 U R00001RC E42NE 2007051500189 20070515 00189 NE 2007 5 15 CA070209009 2 20070112 G 7532 31J285704 MOTOR CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE BLEED VALVE UNSERVICEABLE W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA (CAN) ON APPROACH, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY VIBRATION, AN EEC REVERSION AND A LACK OF THROTTLE RES PONSE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A UNSERVICEABLE BLEED VALVE TORQUE MOTOR. (TC NR 20070209009) 2 L 7 2 4F 4 F RT A22CE E00059EN 2007051500190 20070515 00190 EA 2007 5 15 CA070209010 2 20070103 G 7321 3027791 TUBE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL FCU P3 FRACTURED W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 5581 (CAN) ON CLIMB, ENGINE POWER REDUCED TO IDLE UNCOMMANDED. THE ENGINE WAS SHUTDOWN IN FLIGHT. INSPECTION REVEALED A FRAC TURED FCU P3 DELIVERY TUBE. (TC NR 20070209010) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007051500191 20070515 00191 NE 2007 5 15 CA070209011 2 20070118 G 7310 3026779 LINE BEECH 200 B200 1152922 CE PWA PT6 PT642A NE FUEL SYSTEM FRACTURED W K NONE K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) ON INSPECTION FOLLOWING A REPORT OF FUEL ODOR IN THE CABIN, THE ENGINE HIGH PRESSURE FUEL DELIVERY TUBE WAS FOUND CRACKED. (TC NR 20070209011) 1 L 7 2 4T 4 T A24CE E4EA 2007051500192 20070515 00192 NE 2007 5 15 CA070209012 2 20070116 G 7260 DRIVE GEAR FOKKER F27 F27MK50 EU PWA PW120 PW127 NE GEARBOX DAMAGED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION DE DESCENT 1 CA (CAN) THE ENGINE FLAMED OUT ON DESCENT. SUBSQUENT INSPECTION REVEALED DAMAGE TO THE ANGLE DRIVE GEARBOX GEARING. (TC NR 20070209012) 2 H 7 2 4T 4 T RT A817 E20NE 2007051500193 20070515 00193 NE 2007 5 15 CA070209013 2 20070118 G 7260 GEAR AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE GEARBOX DAMAGED W O OTHER X ENGINE FLAMEOUT CR CRUISE 1 CA (CAN) THE ENGINE FLAMED OUT IN CRUISE. SUBSEQUENT INVESTIGATION REVEALED DAMAGED TOWERSHAFT DRIVE BEVEL GEARS. (TC NR 2 0070209013) 2 H 7 2 4T 4 T RT E20NE 2007051500194 20070515 00194 NE 2007 5 15 CA070209014 2 20070119 G 7321 8237007 HMU CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE ENGINE UNSERVICEABLE W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION NR NOT REPORTED 1 CA F51037 (CAN) THE ENGINE FLAMED OUT IN FLIGHT. SUBSEQUENT INSPECTION REVEALED AN UNSERVICEABLE HYDROMECHANICAL FCU. (TC NR 2007 0209014) 2 L 7 2 4F 4 F RT A22CE E00059EN 2007051500195 20070515 00195 NE 2007 5 15 CA070209015 2 20070121 G 7261 TUBE EMB 120 EMB120 3260201 SO PWA 118 PW118 NE ENGINE OIL FRACTURED W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) IN CRUISE ENGINE OIL PRESSURE REDUCED AND THE PILOT SHUT THE ENGINE DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALE D A FRACTURED NR 6 AND 7 BEARING OIL TRANSFER TUBE. (TC NR 20070209015) 2 L 7 2 4T 4 T RT A31SO E20NE 2007051500196 20070515 00196 NE 2007 5 15 CA070209016 2 20070123 G 7200 ENGINE DORNER DO32 DO328100 2996000 NM PWA 119 PW119B NE FAILED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA 116011 (CAN) DURING CRUISE THE ENGINE CHIP DETECTOR AND LOW OIL PRESSURE WARNINGS ACTIVATED AND THE ENGINE FLAMED OUT IN FLIGHT . SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAU SE ONCE DETERMINED. (TC NR 20070209016) 2 H 7 2 4T 4 T RT A45NM E20NE 2007051500198 20070515 00198 CE 2007 5 15 CA070209019 1 20070131 G 5711 5016000355 SPAR BEECH 100 100BEECH 1152916 CE RT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 17018 (CAN) RT IB FLAP P/N 50-160003-97 REMOVED FOR HINGE BRACKET REPLACEMENT. UPON TEARDOWN OF FLAP FOR HINGE BRACKET REMOVA L, AN 8 INCH CRACK WAS NOTED ON THE SPAR UPPER RADIUS. THE CRACK EXTENDED 4 INCHES EITHER SIDE OF THE FLAP ACTUATOR BRA CKET ATTACH AREA. PROBABLY CRACKED DUE TO CYCLING OF THE FLAP OVER TIME AND THE LOCALIZED STRESSES IN THAT AREA OF THE F LAP, AROUND THE ACTUATOR BRACKET. CRACK IN SPAR CANNOT BE SEEN WITHOUT DISASSEMBLY OF FLAP. (TC NR 20070209019) 1 L 7 2 3T A14CE 2007051500199 20070515 00199 SO 2007 5 15 CA070209020 1 20070207 G 2424 B002861 VOLT REGULATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL LT ALTERNATOR FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) IN CRUISE FLIGHT, THE LT ALTERNATOR FAIL LIGHT CAME ON, AIRCRAFT RETURNED TO BASE FOR REPAIRS. VOLTAGE REGULATORS REPLACED WITH NEW, RT ALTERNATOR P/N ALU8521 REPLACED WITH OVERHAULED UNIT. GROUND RUNS CARRIED OUT TO CHECK FUNCTION, C HECKED OK. TEST FLIGHT CARRIED OUT AND SYSTEM CHECKED NORMAL. (TC NR 20070209020) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007051500200 20070515 00200 NE 2007 5 15 CA070209021 2 20070207 G 7250 BLADE SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE TURBINE DISK SEPARATED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 12458 12458 785590 (CAN) AFTER REACHING CRUISING ALTITUDE OF 23000 FT THE LT ENGINE SURGED AND THE LOW OIL PRESSURE LIGHT ILLUMINATED. THE ENGINE WAS SHUTDOWN AND THE FLIGHT CONTINUED TO WHERE AN UNEVENTFULL LANDING WAS MADE. THE ENGINE STRIP SHOWED THAT THE COMPRESSOR STAGE ONE TURBINE DISK HAD LOST A BLADE. THE REMAINING BLADES HAD SUFFERED EXTENSIVE DAMAGE, AS TOO HAD THE S TATOR ASSY. THE ENGINE AND COMPONENTS HAVE BEEN RETURNED TO GE (ENGINE OEM) FOR INVESTIGATION. (TC NR 20070209021) 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2007051500201 20070515 00201 EU 2007 5 15 CA070209022 1 20070209 G 2750 FLAP SYSTEM GROB 120 G120A 1660208 EU LYC O540 AEIO540D4D5 EA FROZEN W O OTHER O OTHER NR NOT REPORTED 1 CA 261 (CAN) THE COLD WEATHER HAS AFFECTED SEVERAL AIRCRAFT IN THE FLEET OF 9. IN -25 C OR COLDER TEMPERATURES, THE CIRCUIT BRE AKERS POP AFTER LANDING WHEN THE FLAPS ARE SELECTED (TC NR 20070209022) 1 L 7 1 3O 3 O RT A49CE 1E4 2007051600137 20070516 00137 EA 2007 5 16 CA070209023 1 20070207 G 5610 6003303026 WINDSHIELD CNDAIR CL601 CL6013A 8070802 EA COCKPIT CRACKED W A UNSCHED LANDING Z SIGNIFICANT FAILURE REPORT CR CRUISE 1 CA 1167 (CAN) RT WINDSHIELD OUTER LAYER CRACKED DURING FLIGHT, A SINGLE CRACK LOCATED IN THE CENTER OF THE WINDSHIELD AND IS VER TICAL FROM TOP TO BOTTOM. AIRCRAFT PRESSURIZATION WAS NOT AFFECTED AND AIRCRAFT RETURNED TO BASE. (TC NR 20070209023) 2 L 7 2 4F RT A21EA 2007051600138 20070516 00138 EU 2007 5 16 CA070212001 1 20070201 G 2711 978731813 ACTUATOR PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL AILERON TRIM TAB INTERMITTENT W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) AILERON TRIM INTERMITTENT. TRIM TAB ACTUATOR REPLACED AND AIRCRAFT RETURNED TO SERVICE (TC NR 20070212001) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007051600139 20070516 00139 EU 2007 5 16 CA070212002 1 20070208 G 7600 941941141 CONDITION LEVER PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL COCKPIT STIFF W K NONE O OTHER IN INSP/MAINT 1 CA 6263 (CAN) DURING INSPECTION, IT WAS FOUND THAT THE CONDITION LEVER WAS EXTREMELY HARD TO MOVE. THE CONDITION LEVER CABLE WA S REPLACED. (TC NR 20070212002) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007051600140 20070516 00140 EU 2007 5 16 CA070212003 1 20070207 G 3250 STEERING SYS BAG JETSTM JETSTM3212 1500217 EU NLG UNSERVICEABLE W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA 4808 (CAN) INTERNAL STEERING MECHANISM SLOPPY. A/C HARD TO CONTROL DURING TAXI. NOSE LANDING GEAR REMOVED AND REPLACED WITH O VERHAULED UNIT, GROUND TEST CARRIED OUT AND FOUND SERVICEABLE. DEFECTIVE LANDING GEAR HAS NOT BEEN SHIPPED FOR OVERHAUL AT THIS TIME. (TC NR 20070212003) 2 L 7 2 4T RT BA15CAA 2007051600141 20070516 00141 GL 2007 5 16 CA070212004 1 20070208 G 5340 C2FS5487A FITTING DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HARTZL HCB3R HCB3R304 GL FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AT SCHEDULED INSPECTION THE PORK CHOP FITTINGS WERE FOUND CORRODED. THESE C2FS5487A LT AND RT WERE BOTH REPLACED. DEPTH OF CORROSION WAS APPROX 20 PERCENT OF OVERALL PART THICKNESS. THE MANUFACTURE WAS CONTACTED AND REPORTED SEVERAL S ERVICE DIFFICULTY REPORTS HAVE BEEN FILED BY OEM. (TC NR 20070212004) 1 H 7 1 3R 3 R RC A806 5E1 5 C P28EA 2007051600142 20070516 00142 WP 2007 5 16 CA070212005 2 20070207 G 7200 TPE33110UG ENGINE BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33110UG 01514 WP UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 17244 4760 (CAN) DURING PRE FLIGHT INSPECTION FLIGHT CREW HEARD ABNORMAL NOISE COMING FROM ENGINE WHILE THEY TURNED THE PROPELLER. MAINTENANCE WAS NOTIFIED AND ENGINE WAS INSPECTED, SUSPECT REAR BEARING FAILURE, OIL SYSTEM INSPECTED AND FOUND TO HAVE NO METAL CONTAMINATION. ENGINE REMOVED AND HAS NOT YET BEEN SENT FOR REPAIR. (TC NR 20070212005) 2 L 7 2 4T 4 T RT BA15CAA E4WE 2007051600143 20070516 00143 EU 2007 5 16 CA070212006 1 20070211 G 5210 MECHANISM EMB ERJ190 ERJ190100IGW 3260408 EU L2 DOOR FROZEN W K NONE O OTHER IN INSP/MAINT 1 CA 1243 (CAN) F/A ADVISED L2 DOOR FROZEN UNABLE TO OPEN VENT FLAP. L2 DOOR THAWED OUT IN HANGAR, GVI CARRIED OUT ON DOOR, CHECK ED SERVICEABLE. NOTE: SINCE NOV 1 2006, HAVE FOUND 8 OTHER SNAGS RELATED TO E190 FROZEN DOORS. COULD BE A CONCERN IN T HE EVENT OF AN EMERGENCY SITUATION. (TC NR 20070212006) 2 L 7 2 4F RT A57NM 2007051600144 20070516 00144 CE 2007 5 16 CA070212007 1 20070129 G 2730 1155240465 TORQUE TUBE BEECH 99 B99 1154004 CE PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE TAIL CONE WAS REMOVED FOR OTHER SCHEDULED MAINTENANCE. IT WAS NOTICED THAT THE ELEVATOR BELLCRANK TORQUE TUBE WAS CRACKED. THE CRACK STARTED AT THE HORN ATTACH TAPER PIN AND SPIRALED AROUND THE TORQUE TUBE APPROX 270 DEGREES. THE ASSEMBLY WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE (TC 20070212007) 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2007051600145 20070516 00145 EU 2007 5 16 CA070212008 1 20070127 G 3800 LINE EMB ERJ190 ERJ190100IGW 3260408 EU GE CF34 CF34* NE WATER SYS RUPTURED W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) WHILE ENROUTE TO DESTINATION CREW REPORTED TO MAINTENANCE THAT AILERON CONTROL COLUMN FREEZES AND TAKES EXCESSIVE FORCE TO FREE UP, UPON INSPECTION AT DESTINATION MAINTENANCE FOUND AILERON CONTROLS COVERED IN ICE CAUSED BY A BROKEN WA TER LINE. A MAINTENANCE INVESTIGATION FOUND THAT A CLAMP HAD COME OFF FROM THE FORWARD WATER SYSTEM DRAIN PLUMBING. (T C NR 20070212008) 2 L 7 2 4F 4 F RT A57NM E15NE 2007051600146 20070516 00146 CE 2007 5 16 CA070212010 1 20070201 G 3246 BEARING BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3A NE MAIN WHEEL DESTROYED W K NONE O OTHER TX TAXI/GRND HDL 1 CA (CAN) WHEN THE AIRCRAFT LANDED ALL OF PASSENGERS WERE UNLOADED FOR REFUELING. THE CAPTAIN OF THE AIRCRAFT WALKED AROUND THE RT SIDE OF THE AIRCRAFT TO TALK TO THE FUELER AND NOTICED THAT THE RT MAIN GEAR ONLY HAD ONE MAIN WHEEL ASSEMBLY AT TACHED. HE IMMEDIATELY CONTACTED MAINTENANCE AND GROUNDED THE AIRCRAFT. UPON INSPECTION OF THE AXLE STUB IT WAS FOUND T HAT THE INNER RACES OF THE BEARINGS, NUT AND SAFETY HARDWARE WAS STILL ATTACHED. THE OTHER 3 WHEEL ASSEMBLIES WERE REMO VED AND INSPECTED FOR CONDITION AND SECURITY. ONE OF THE 3 HAD BEEN CHANGED BY US ALREADY AND WAS FINE. THE LAST TWO W ERE FOUND TO HAVE GREASE COATED ON THE OUTSIDE OF THE BEARINGS BUT NOT (PACKED) INSIDE. NOTE: THE AIRCRAFT IS NEW TO 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2007051600147 20070516 00147 EA 2007 5 16 CA070213001 1 20070212 G 2750 FCU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE TE FLAPS MALFUNCTIONED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) FLAP FAIL MESSAGE RECEIVED IN-FLIGHT. AIRCRAFT LANDED UNEVENTFUL WITH FLAPS ZERO (FLAPS WOULD NOT MOVE). (TC NR 20 070213001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051600148 20070516 00148 CE 2007 5 16 CA070213002 1 20070131 G 2910 991242339 VALVE CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL HYD SYSTEM FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1409 (CAN) POST INSPECTION RUN REVEALED HYDRAULIC PRESSURE ON ANNUNCIATOR LIGHT DID NOT EXTINGUISH WHEN SYSTEM SHOULD HAVE BE EN AT REST. HYDAULIC LOADING VALVE FOUND FAILED. BLEED ORIFICE RECOVERED FROM HYDRAULIC MANIFOLD UNDER RELIEF VALVE (3R D FROM LOADING VALVE). LOADING VALVE MAY HAVE FALLEN APART DURING EMERGENCY GEAR EXTENSION TEST. LOADING VALVE REPLACED . ALL TESTS NORMAL. FAILED VALVE SENT TO MFG FOR ANALYSIS. (TC NR 20070213002) 1 L 7 2 4F 4 F RT A1WI E3GL 2007051600149 20070516 00149 NM 2007 5 16 CA070213003 1 20070206 G 2497 50086003 CONTACT BOEING 727 727223 1384074 NM PWA JT8 JT8D15 52051 NE GENERATOR BURNED W O OTHER O OTHER CL CLIMB 1 CA (CAN) DURING CLIMB OUT ALL 4 CB`S POPPED FOR TANK 2 FUEL BOOST PUMPS, AIRCRAFT RETURNED TO AIRPORT. DETERMINED NR 3 GENE RATOR VOLTAGE FLUCTUATING, (THE PUMP FAULT WAS ATTRIBUTED TO THE POWER FLUCTUATION WHICH WAS POWERING THE (ESSENTIAL POW ER) AND THE (SYNC BUSS POWERING THESE PUMPS). INSPECTION OF NR 3 GENERATOR CB FOUND BURNED CONTACTS. CB REPLACED, CONTA CTS CLEANED NO FURTHER REPORTS. (TC NR 20070213003) 2 L 7 3 4F 4 F A3WE E2EA 2007051600150 20070516 00150 CE 2007 5 16 CA070213005 1 20070213 G 3510 510010951 LINE CESSNA 425 425 2076018 CE PWA PT6 PT6A112 52043 NE MCAULY 4HFR34 4HFR34C762 NE CREW O2 SYS CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) FOUND LT SIDE CABIN OXYGEN LINE P/N 5100109-51 CORRODED WHERE IT CROSSES THE OVERHEAD CABIN AIR DUCT P/N CM3212-2 (WL 103.10) AT FS 160.0. (TC NR 20070213005) 1 L 7 2 3T 3 T RT A7CE E4EA 6 C 3PNE 2007051600151 20070516 00151 2007 5 16 CA070213006 4 20070206 G 3444 401020101 PROXIMITY SENSOR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU RT MLG WOW 1 MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 369 (CAN) ON TAKEOFF CREW GOT (WT ON WHEELS) CAUTION LIGHT MOMENTARILY. LIGHT CAME ON AGAIN IN FLIGHT, QRH ACTIONED AND RET URN TO BASE. PSEU SHOWED THAT RT MLG WOW 1 SENSOR PROXIMITY SHOWED (UNREASONABLY NEAR). COULD ADJUST OUT SO THAT MILLI HENERYS WERE IN SPEC BUT THE GAP WAS OUT. REPLACED SENSOR PROXIMITY. (TC NR 20070213006) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007061300155 20070613 00155 NM 2007 6 13 CA070213007 1 20070206 G 3230 483023 SEQUENCE VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA NLG FAILED W A UNSCHED LANDING D J INFLIGHT SEPARATION WARNING INDICATION CL CLIMB 1 CA 654 (CAN) NOSE LANDING GEAR DOORS WOULD NOT CLOSE ON GEAR RETRACTION. GEAR WOULD NOT EXTEND NORMALLY SO CREW DID AN ALTERNAT E GEAR EXTENSION. REPLACED VALVE,SOLENOID SEQUENCE AS WE HAD DEALT WITH THIS ISSUE A WEEK EARLIER ON ANOTHER AIRCRAFT ( TC# 20070213007). 2 H 7 2 4T 4 T RT A13NM E00062EN 2007051600152 20070516 00152 WP 2007 5 16 CA070213008 1 20070204 G 6730 D2121 SERVO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAIN ROTOR LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) RT LATERAL SERVO FOUND LEAKING BY ENGINEER DURING DI. SERVO REMOVED FOR REPAIR AND SERVICABLE UNIT INSTALLED. (TC NR 20070213008) 1 G 7 1 3O 3 O H11NM 1E4 2007051600153 20070516 00153 EU 2007 5 16 CA070213009 1 20070113 G 6730 704A44831142 SERVO SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B NE TAIL ROTOR LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 6258 2996 (CAN) SERVO FOUND LEAKING BY ENGINEER ON POST FLIGHT INSP. SERVO REPLACED WITH SERVICABLE UNIT. SERVO WAS SENT OUT FOR REPAIR. THE SERVO WAS OVERHAULED AND IS BEING SHIPPED BACK TO US FOR INSTALLATION. (TC NR 20070213009) 1 G 7 1 3U 3 U H9EU E00054EN 2007051600154 20070516 00154 EA 2007 5 16 CA070214001 1 20070214 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE TE FLAPS JAMMED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH, WHEN THE CREW SELECTED FLAP 8, THE FLAPS DID NOT MOVE AND THEY STAYED AT 0. CREW LANDED FLAPLESS WITH OUT INCIDENT. NO MORE DETAILS. INFORMATION WILL BE UPDATED AS SOON AS IS AVAILABLE. (TC NR 20070214001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051600155 20070516 00155 EU 2007 5 16 CA070214002 1 20070207 G 7603 55CF8891 CABLE UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE THROTTLE FAILED W E ENGINE SHUTDOWN F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 4461 4461 (CAN) THROTTLE FROZEN IN THE FULL OPEN POSITION. FUEL FIRE WALL SHUT OFF USED TO CONTAIN ENGINE. (TC NR 20070214002) 1 G 7 2 3U 3 U NC R0001RD E34NE 2007051600156 20070516 00156 SO 2007 5 16 CA070214004 2 20070203 G 8530 5A10204 EXHAUST VALVE CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL CYLINDER HEAD BROKEN W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA 1541 (CAN) DURING TAKEOFF, AN ENGINE VIBRATION WAS FELT. A PRIORITY LANDING WAS REQUESTED. CYLINDER EXHAUST VALVE NR 3 FOUND BROKEN AT THE VALVE HEAD. CYLINDER SA10200, S/N AM1376 INSTALLED. OTHER VALVES INSPECTED AND REPLACED VALVES SA10204 ON CYLINDER NR 4 AND NR 2. (TC NR 20070214004) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2007051600157 20070516 00157 EA 2007 5 16 CA070214005 1 20070212 G 3610 3035279 LINE DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL PNEUMATIC SYS BROKEN W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) AFTER LANDING THE NR 1 PROP RPM WAS LOWER THAN NORMAL. MAINTENANCE FOUND THAT THE P3 LINE FROM THE P3 FILTER BOWL TO THE ENGINE WAS BROKEN PN 3035279. THE LINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070214005) 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2007080800140 20070808 00140 CE 2007 8 8 CA070215001 1 20070213 G 3340 CM358910 SWITCH CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL LANDING LIGHT SMOKE W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 2364 (CAN) LANDING LIGHT SWITCH GAVE OFF ODOR OF SMOKE, WHEN PILOT WENT TO TURN OFF, THE SWITCH WAS HOT AND THE SHUTOFF THE S WITCH WAS REPLACED WITH A NEW UNIT (TC NR 20070215001) 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2007051600158 20070516 00158 WP 2007 5 16 CA070215002 2 20070213 G 7260 HOUSING ALIDSG BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33110UG 01514 WP MCAULY 4HFR34 4HFR34C652 NE ACCESSORY DRIVE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA P63269C (CAN) ACCESSORY DRIVE HOUSING BOTTOM CASE DRAIN THREADED MOUNTING BOSS DISCOVERED BROKEN. ENGINE REMOVED AND LOANER ENGI NE INSTALLED. (TC NR 20070215002) 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C 3PNE 2007051600159 20070516 00159 CE 2007 5 16 CA070215003 1 20070215 G 2435 SPLINE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL STARTER GEN WORN W O OTHER O OTHER NR NOT REPORTED 1 CA 624 19360 (CAN) START ATTEMPTED ON ENGINE. STARTER/GENERATOR ROTATED BUT ENGINE DID NOT. S/G REMOVED AND INSPECTED. S/G SHAFT SPLI NE NOTED AS EXTREMELY WORN. ENGINE ACCESSORY HOUSING INTERNAL SPLINE CHECKED FOR WEAR WITH WEAR CHECK TOOL. DIMENSIONS W ITHIN ACCEPTABLE LIMITS. S/G REPLACED WITH NEW UNIT. (TC NR 20070215003) 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2007080800141 20070808 00141 CE 2007 8 8 CA070215004 1 20070210 G 2434 10300B ALTERNATOR CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL ENGINE MALFUNCTIONED W O OTHER O OTHER CL CLIMB 1 CA (CAN) ON CLIMB OUT A LOW VOLTAGE LIGHT INDICATION. PILOT RECYCLED ALTERNATOR, LOW VOLTAGE INDICATION WAS NOT CORRECTED A ND PILOT RETURNED FOR LANDING (TC NR 20070215004) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007080800142 20070808 00142 CE 2007 8 8 CA070215007 1 20070214 G 3221 NAS464P4A10 BOLT CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE NLG BROKEN W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA 7092 (CAN) AFTER GEAR WERE RETRACTED A VIBRATION IN THE NOSE OF THE AIRCRAFT WAS NOTICED. THE AIRCRAFT RETURNED TO BASE WITH NO INCIDENT. AN INSPECTION WAS CONDUCTED AND THE NOSE GEAR DOOR TORQUE TUBE ATTACH BOLT WAS FOUND BROKEN. THIS BOLT AT TACHES THE TORQUE TUBE TO THE WHEEL WELL STRUCTURE AND THE TORQUE TUBE ROTATES AROUND THIS BOLT. THE TORQUE TUBE WAS INS PECTED AND REINSTALLED. (TC NR 20070215007) 2 L 7 2 4F 4 F RT A22CE E25EA 2007051600160 20070516 00160 SW 2007 5 16 CA070216001 1 20070214 G 2820 206040525101 HOUSING BELL 206 206L4 1182110 SW FUEL SYS DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BYPASS INDICATOR BORE MISSING ONE 0.062 INCH DIA OIL PASSAGE AT BOTTOM OF BORE BREAKING THROUGH THE SMALLEST RECES SED BORE DIAMETER OF .375 INCH. PICTURE OF PART WITH THE MISSING HOLE ATTACHED. (TC NR 20070216001) 1 G 7 1 3U NC H2SW 2007051600168 20070516 00168 CE 2007 5 16 CA070216002 1 20070214 G 2750 100984040 MOTOR BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL TE FLAP FAILED W L ABORTED APPROACH F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) ON FINAL APPROACH, THE PILOT SELECTED FLAPS DOWN, WHEN THE FLAPS REACHED 5 DEGREES, THE ASSOCIATED CIRCUIT BREAKER POPPED. THE PILOT OVERSHOT TO EVALUATE THE SITUATION AND THEN CARRIED OUT AN UNEVENTFUL LANDING WITH 5 DEGREE OF FLAP. UPON INVESTIGATION BY MAINTENANCE, IT WAS FOUND THAT THE BEARING IN THE FLAP MOTOR HAD FAILED. THE MOTOR WAS REPLACED AN D THE AIRCRAFT RETURNED TO SERVICE. AS THE FLAP MOTOR IS NOT CONTROLLED FOR HARD TIME, THE OPERATORS HAVE INDUCED A MAND ATORY OVERHAUL OF THE MOTOR AND GEARBOX EVERY 5000 CYCLES. (TC NR 20070216002) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007051600169 20070516 00169 SO 2007 5 16 CA070216003 1 20070216 G 2730 AN17422A BOLT PIPER PA31 PA31325 7103105 SO LYC O540 TIO540J2BD 41532 EA ELEVATOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AT INSPECTION FOUND BOLTS (AN174-22A (6EA)) IN ELEVATOR TORQUE TUBE ASSEMBLY (40070-05) CORRODED. (TC NR 200702160 03) 1 L 7 2 3O 3 O A20SO E14EA 2008031900133 20080319 00133 CE 2008 3 19 CA070216004 1 20070209 G 7120 829 SPACER CESSNA 172 172E 2072412 CE LYC O360 IO360A1A 41514 EA HARTZL HCC2Y HCC2YR1 GL ENGINE MOUNT SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA 1000 15182 (CAN) A RATTLE NOISE WAS HEARD AT ENGINE START. CLOSE INSP OF THE ENGINE MOUNT ASSY REVEALED ALL 4 MOUNT SPACERS, P/N 82 9, HAD SHEARED THEIR ATTACHMENT RIVET HEADS. THIS AC WAS MODIFIED IN THE PAST WITH 180HP CONVERSION. DISASSEMBLY REVEALE D THE USE OF VERY SOFT ALUMINUM ALLOY RIVETS TO ATTACH THE ALUMINUM SPACERS TO THE STEEL TUBE MOUNT STRUCTURE, PN 17201- 1, WEAR DAMAGE PREVENTED POSITIVE VISUAL ID OF THE RIVET TYPE. IT IS UNKNOWN IF THESE RIVETS ARE A FACTORY OR A FIELD I NSTALLATION. FAILURE OF THESE RIVETS ALLOW SPACER TO OSCILLATE LATERALLY ON THEIR MOUNTING PADS. SUBMITTER RECOMMENDS TO EXAMINE THIS ENGINE MOUNT SPACER CLOSELY FOR SMOKING OR LOOSE RIVET HEADS AT INSP. (TC NR 20070216004) 1 H 7 1 3O 3 O NT 3A12 1E10 5 C P920 2007051600170 20070516 00170 GL 2007 5 16 CA070216005 2 20070210 G 7261 OIL SYSTEM ALLSN LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL HAMSTD 54H 54H60117 NE NR 2 ENGINE LOW PRESSURE W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 9453 (CAN) IN CRUISE FLIGHT, THE CREW OBSERVED THAT THE OIL QUANTITY WAS DROPPING ON NR 2 ENGINE. AFTER VISUAL CONFIRMATION T HAT OIL WAS EXITING THE OVERBOARD DRAIN, THE ENGINE WAS SHUTDOWN. THE AIRCRAFT LANDED WITHOUT FURTHER PROBLEM. MAINTENA NCE REPLACED THE ENGINE SCAVENGE SYSTEM FILTER, THE ENGINE OIL COOLER, CHECKED THE ENGINE MAGNETIC DRAIN PLUGS AND REFIL LED THE ENGINE WITH FRESH OIL. NO CONTAMINATION WAS OBSERVED OTHER THAN SOME CARBON IN THE SCAVENGE FILTER. THE AIRCRAFT WAS GROUND RUN AND THE RETURNED TO SERVICE. (TC NR 20070216005) 2 H 7 4 4T 4 T A1SO E282 6 C P906 2007051600171 20070516 00171 SW 2007 5 16 CA070216006 1 20070207 G 6320 GEARBOX BELL BELL 427 427 1182207 SW MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1623 A37 (CAN) FOUND A CRACK IN MAIN ROTOR TRANSMISSION, ON THE LT SIDE INPUT SHAFT. OIL STARTED TO SIP OUT OF THE TRANSMISSION. (TC NR 20070216006) 1 G 7 1 3U R00001RC 2007053000010 20070530 00010 NE 2007 5 30 CA070216008 2 20070216 G 7230 5009T34P01 BLADE GE GE CT58 CT581401 30011 NE COMPRESSOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3971 258 (CAN) ON INSPECTION, A STAGE 4 BLADE WAS FOUND TO HAVE A 0.080 INCH CRACK THROUGH THE DOVE TAIL AREA ON THE TRAILING EDG E SIDE. OUR FILE NR SQID 07-00588 (TC NR 20070216008) 4 U 1E3 2007051600173 20070516 00173 NE 2007 5 16 CA070219001 2 20070216 G 7230 FAN BLADE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE NR 2 ENGINE BENT W A UNSCHED LANDING C F.O.D. CL CLIMB 1 CA 25204 25204 807217 (CAN) FEB 16/07, AIR TURN BACK. THE CREW REPORTED THAT AFTER TAKEOFF A LOUD RUMBLING NOISE WAS HEARD. CREW BELIEVED THA T ICE MAY HAVE BEEN INGESTED INTO THE RT ENGINE DURING LANDING ON THE PREVIOUS LEG INBOUND TO DESTINATION. MAINTENANCE C ONFIRMED SEVERAL FAN BLADES WERE DAMAGED AT OUTER TIPS. THE FAN BLADES WERE REMOVED AND REPLACED AND A COMPRESSOR INSPE CTION WAS CARRIED OUT WITH NFF. ENGINE RUNS WERE CARRIED OUT AND ALL PARAMETERS FOUND WITHIN LIMITS AND AIRCRAFT WAS RE TURNED TO SERVICE. (TC NR 20070219001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051600174 20070516 00174 EA 2007 5 16 CA070219003 1 20070218 G 2750 FLAP SYSTEM CNDAIR CL600 CL600* EA TE FLAPS JAMMED W L ABORTED APPROACH O OTHER AP APPROACH 1 CA (CAN) ON APPROACH, CREW RECEIVED SLATS FAIL MESSAGE, ALSO, FLAPS STOPPED AT 8 DEGREES. FLIGHT LANDED WITHOUT INCIDENT. INFORMATION WILL BE UPDATED AS SOON AS IS AVAILABLE. (TC NR 20070219003) 2 L 7 2 4F RT A21EA 2007051600175 20070516 00175 SW 2007 5 16 CA070219004 1 20070204 G 5610 2719442003 WINDSHIELD SWRNGN SA227 SA227AC 8780603 SW COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA 3829 (CAN) WHILE IN CRUISE FLIGHT ENROUTE, THE CAPTAIN’S WINDSCREEN CRACKED IN THE OUTER PANE. THE AIRCRAFT CONTINUED ON AND LANDED WITHOUT INCIDENT. THE WINDSHIELD WAS REPLACED WITH AN OVERHAULED ASSEMBLY AND THE AIRCRAFT RELEASED. (TC 200702 19004) 2 L 7 2 4T RT A8SW 2007051600176 20070516 00176 SW 2007 5 16 CA070219005 1 20070218 G 7120 276211497 MOUNT SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8945 (CAN) DURING INSPECTION A CRACK WAS DISCOVERED IN THE UPPER AFT OUTBOARD WELD ASSEMBLY ON THE ENGINE MOUNT TRUSS REQUIRI NG REPLACEMENT OF THE MOUNT ASSEMBLY. (TC NR 20070219005) 2 L 7 2 4T 4 T RT A8SW E4WE 2007051600177 20070516 00177 EA 2007 5 16 CA070219006 2 20070208 G 7321 34475523 FCU BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL ENGINE FAULTY W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) DURING GROUND RUN, RT POWER LEVER FOUND NOT CONTOLLING FCU. INSPECTED THROTLE LEVER LINKAGES AND CABLE TO FCU AND NO FAULTS FOUND. AFTER TROUBLESHOOTING WITH MFG TECH SUPPORT, SUSPECTED FAULTY FUEL CONTROL UNIT. FCU HAS BEEN REPLACED AND FAULT ELIMINATED. (TC NR 20070219006) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007051700116 20070517 00116 EA 2007 5 17 CA070219008 1 20070218 G 5551 C6TPM102228 BRACKET DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL HORIZONTAL STAB LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE FLIGHT CREW WHERE CONDUCTING A GROUND RUN, MAINTENANCE ON THE GROUND NOTED THE RT ELEVATOR WAS MOVING UP AND DOWN EXCESSIVELY. UPON INVESTIGATION, MAINTENANCE FOUND BRACKET P/N C6TPM1022-28 WITH RIVETS WORKING AND SEVERAL WHERE ACTUALLY MISSING. THIS BRACKET IS THE PART OF THE ELEVATOR HINGE THAT IS RIVETED TO THE HORIZONTAL STABILIZER. ALL MISSI NG, LOOSE OR DAMAGED FASTNERS WHERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE COMPANY HAS ISSUED A FLEET INSPEC TION OF ALL OTHER TWIN OTTERS. (TC NR 20070219008) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007053000011 20070530 00011 EA 2007 5 30 CA070219009 1 20070216 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 17589 13354 (CAN) DURING APPROACH WHEN FLAP SELECTED TO 8 DEG, CREW RECEIVED (FLAP FAIL) CAUTION MESSAGE ON EICAS, CONTROL POSITION DISPLAY SHOWED 2DEG ON LT FLAP AND 0 DEG ON RT FLAP. ZERO DEG FLAP LANDING CARRIED OUT. AFTER LANDING CREW PERFORMED VI SUAL INSPECTION OF THE FLAPS AND NOTED THAT LT FLAPS APPEARED TO BE AT 2 DEG AND RT FLAP LOOKED LIKE 2 DEG ON THE IB AND 0 DEG ON THE OB. FLAP CIRCUIT BREAKER RESET PROCEDURE CARRIED OUT. FLAPS FUNCTION CHECKED NORMAL. AIRCRAFT POSITIONED T O MAINTENANCE BASE. MAINTENANCE FOUND NO OBVIOUS FAULTS. ALL FLAP ACTUATORS REPLACED WITH REPLACEMENT UNITS, ALL FLAP DR IVE CABLES REMOVED AND INSPECTED AND RE-LUBRICATED. BOTH BPSU`S (FLAP BRAKE AND POSITION SENSOR UNITS) REPLACED. MAINTEN 2 L 7 2 4F 4 F RT A21EA E15NE 2007051700117 20070517 00117 EU 2007 5 17 CA070219010 1 20070219 G 5497 WIRE BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33112UHR WP ROTOL R333 R333482F12 GL NR 2 NACELLE DAMAGED W A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CL CLIMB 1 CA (CAN) CREW REPORTED THAT THE AIRCRAFT NR 2 ENGINE STARTED TO SURGE AND THE TORQUE INDICATION FLUCTUATED BETWEEN 0-120 PE RCENT. TTL AND SRL COMPUTERS TURNED OFF AND ENGINE SURGE STABILIZED AND CONTINUED TO RUN NORMALLY. INDICATION CONTINUED TO FLUCTUATE. TROUBLESHOOTING INDICATED DAMAGED WIRING IN THE NR 2 ENGINE COMPARTMENT. WIRING REPAIRED. INDICATION CALIB RATED AND NO FURTHER FAULTS FOUND. (TC NR 20070219010) 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C P61GL 2007051700118 20070517 00118 2007 5 17 CA070219011 4 20070217 G 2397 M2430823F CONNECTOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE P1RU CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA 5121 5121 (CAN) CREW REPORTED PASSENGER ADDRESS CIRCUIT BREAKER 1Q5 POPPED , NON PA/CHIMES/CALL FUNCTION. MAINTENANCE INSPECTION F OUND STOWED CONNECTOR P1RU CORRODED AND SHORTING , CONNECTOR IS FOR AFT CABIN PA HANDSET ( NOT INSTALLED ON THIS TAIL) , CONNECTOR HAD BEEN BAGGED AND STOWED ABOVE CEILING PANEL. MAINTENANCE REMOVED CONNECTOR AND HEAT SHRUNK AND STOWED WIRI NG IAW AMM 20-17-10 . (TC NR 20070219011) 2 L 7 2 4F 4 F RT A21EA E15NE 2008031900134 20080319 00134 SW 2008 3 19 CA070220001 1 20070215 G 2913 297037 SPLINE VICKERS SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE HYD PUMP STRIPPED W O OTHER J WARNING INDICATION LD LANDING 1 CA MX433286C (CAN) LT HYD LIGHT ILLUMINATED BEFORE LANDING. THE DRIVE SPLINE ON THE PUMP WAS FOUND TO BE STRIPPED. IT IS MADE OF SOFT ER MATERIAL AND MADE TO WEAR INSTEAD OF THE ENGINE. PUMP ASSY WAS REPLACED AND AC RETURNED TO SERVICE. THIS IS THE 3RD S PLINE REPLACED. ONE IN OCT- 06, ONE IN DC-06 AND NOW THIS ONE FEB-07. (TC NR 20070220001) 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 2007051700119 20070517 00119 EA 2007 5 17 CA070220002 2 20070212 G 7200 ENGINE BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL RIGHT MAKING METAL W O OTHER J WARNING INDICATION LD LANDING 1 CA 285 40812100 (CAN) CREW CALLED IN ON LANDING TO INFORM MAINTENANCE THAT THE RT CHIP LIGHT HAD ILLUMINATED. MAINTENANCE FOUND ENGINE HAD METAL IN OIL. ENGINE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. THIS ENGINE WILL REQUIRE FURTHER INVESTIGATION AS TO THE CAUSE OF THE MIO. IT IS A LOW TIME POWER SECTION THAT IS ON IT`S SECOND MIO. THE FIRST TIME WAS 183 HOURS A ND 341 CYCLES (TC NR 20070220002) 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2007051700120 20070517 00120 WP 2007 5 17 CA070220003 1 20070218 G 6510 C04111 BEARING ROBSIN ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA DRIVESHAFT DEFECTIVE W K NONE O OTHER IN INSP/MAINT 1 CA 85 1062 (CAN) DAMPER HANGAR BEARING INNER RACE ROTATED ON DRIVESHAFT ASSY. BEARING REPLACED ON DRIVE SHAFT ASSY WITH SERVICABLE UNIT. (TC NR 20070220003) 1 G 7 1 3O 3 O H11NM E295 2007051700121 20070517 00121 NE 2007 5 17 CA070220004 2 20070213 G 7200 ENGINE AIRBUS A319 A319112 3930323 EU CFMINT CFM56 CFM565A1 NE UNKNOWN W A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CA 731587 (CAN) EARLY INVESTIGATIONS POINT TO A NR 4 BEARING FAILURE, AT THIS TIME THE ENGINE HAS NOT BEEN DISSASSEMBLED FOR CONFI RMATION OF FAILURE, PRESENTLY ENROUTE TO SHOP. (TC NR 20070220004) 2 L 7 2 4F 4 F RT A28NM E29NE 2007051700122 20070517 00122 NM 2007 5 17 CA070220005 1 20070216 G 3230 483023 SEQUENCE VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NLG MALFUNCTIONED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 8173 (CAN) ON GEAR EXTENSION GOT 3 GREEN AND DOOR AMBER. TROUBLESHOOTING POINTED TO THE NOSE VALVE SOLENOID SEQUENCE. VALVE REPLACED. (TC NR 20070220005) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008031900135 20080319 00135 NE 2008 3 19 CA070220006 2 20070216 G 7230 31B525501 ACTUATOR GULSTM 200 200 4500308 NM PWC PW306 PW306A 52165 NE IGV LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 525 PCECC02423 (CAN) AC PERFORMED NORMALLY FOR THE TAKEOFF AND INITIAL CLIMB TO 5000 FEET. APPROX (2) MINUTES INTO THE FLIGHT AFTER CLE ARANCE TO 17000 FT WITH CLIMB PWR REAPPLIED TO COMMENCE THE CLIMB, THE RT ENG EXPERIENCED A COMPRESSOR STALL. AFTER (2) OR (3) SURGES THE ENGINE ROLLED BACK TO AROUND 50 PERCENT, N1 WITH FLUCTUATING RPM AND ITT. ROLLBACK WAS FOLLOWED BY A F ADEC MAJOR FAIL FAULT LIGHT. THE PILOT REDUCED POWER ON THE RT ENGINE AND THE N1 STABILIZED AT FLIGHT IDLE. CHECKLIST WA S CALLED FOR AND THE RT ENG WAS SHUTDOWN IAW MFG CHECKLIST. FUEL DUMP WAS COMPLETED WITH CLEARANCE FROM THE DEPARTURE CO NTROLLER AND THE AC WAS REDUCED TO LANDING WEIGHT AND RETURNED FOR LANDING AT AIRPORT WITH NO FURTHER INCIDENT. THE AC 2 L 7 2 4F 4 F RT A53NM E35NE 2007051700123 20070517 00123 CE 2007 5 17 CA070220007 1 20070219 G 3233 SHAFT BEECH 76 76 1153005 CE LYC O360 LO360A1G6 41514 EA HARTZL HCM2Y HCM2YR GL MLG ACTUATOR FRACTURED W A UNSCHED LANDING J WARNING INDICATION DE DESCENT 1 CA 1329 1329 (CAN) MAIN LANDING GEAR ACTUATOR SHAFT FRACTURED AT LAST THREAD FARTHEST FROM ROD END BEARING JAM NUT. SHAFT BENT SLIGHT LY THROUGHOUT ITS FULL LENGTH WITH AN APPROXIMATELY 40 DEGREE BEND AT FRACTURE POINT. (TC NR 20070220007) 1 L 7 2 3O 3 O A29CE 1E10 5 C P43GL 2007051700124 20070517 00124 EA 2007 5 17 CA070221001 1 20070219 G 2720 600902461 BUSHING CNDAIR CL601 CL6012A12 1900303 EA GE CF34 CF348E5A1 30015 NE RUDDER FAILED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA 7326 7326 (CAN) DURING FLIGHT THE CO-PILOTS RUDDER PEDAL ADJUSTMENT MECHANISM FAILED ALLOWING THE RUDDER PEDALS TO FALL FORWARD TO THE LIMIT OF THEIR TRAVEL. INSPECTION REVEALED THAT THE THREADED BUSHING IN THE ADJUSTMENT MECHANISM HAD FAILED ALLOWIN G THE SYSTEM TO DICONNECT. NOTE: RUDDER CONTROL WAS STILL AVAILIBLE THOUGH RUDDER PEDAL POSITION ADJUSTMENT WAS NOT. (TC NR 20070221001) 2 L 7 2 4F 4 F RT A21AE E00063EN 2007051700125 20070517 00125 EA 2007 5 17 CA070221002 1 20070218 G 2782 7663854 ACTUATOR CNDAIR CL600 CL600* EA SLATS FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) SLAT FAIL MESSAGE, UNABLE TO MOVE SLATS AND FLAPS ONLY MOVED TO 8 DEGREES. MDC CODE B1-007772 INDICATES JAMMED SLA T ACTUATOR AND AIRCRAFT REMOVED FROM SERVICE FOR INVESTIGATION. BOTH LEFT HAND OUTBOARD ACTUATORS NR 5 AND NR 6 REPLACED AND TEST COMPLETED SUCCESSFULLY. WILL ASK FOR STRIP REPORTS FROM MANUFACTURER. INFORMATION WILL BE UPDATED AS SOON AS I S AVAILABLE. (TC NR 20070221002) 2 L 7 2 4F RT A21EA 2007051700126 20070517 00126 CE 2007 5 17 CA070221003 1 20070205 G 2560 1101983 BUCKLE PACIFICSCIEN BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA HARTZL HCB3T HCB3TN3 GL SEAT BELT MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) COMPLIED WITH COMPANY CAMPAIGN NOTICE 010-25-10-011 NM-06-29. THE CREW SEATBELT ROTARY LATCH CAN BE CONTACTED WIT H THE CONTROL YOKE WITH THE SEAT FULL FORWARD AND THE YOKE FULL AFT. IT IS POSSIBLE TO UNLATCH THE SEATBELT BY ROTATING THE YOKE AND MAKING CONTACT WITH THE BUCKLE. THE FUNCTION TEST WAS CARRIED OUT IAW THE INSTRUCTIONS GIVEN IN NM-06-29. (TC NR 20070221003) 1 L 7 2 3T 4 T RT 3A20 E4EA 6 C P15EA 2007051700127 20070517 00127 CE 2007 5 17 CA070221004 1 20070210 G 2560 1101983 BUCKLE PACIFICSCIEN BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA HARTZL HCB3T HCB3TN3 GL SEAT BELT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) COMPLIED WITH COMPANY CAMPAIGN NOTICE 010-25-10-011, NM-06-29. THE CREW SEATBELT ROTARY LATCH CAN BE CONTACTED WI TH THE CONTROL YOKE WITH THE SEAT FULL FORWARD AND THE YOKE FULL AFT. IT IS POSSIBLE TO UNLATCH THE SEATBELT BY ROTATING THE YOKE AND MAKING CONTACT WITH THE BUCKLE. THE FUNCTION TEST WAS CARRIED OUT IAW THE INSTRUCTIONS GIVEN IN NM-06-29. (TC NR 20070221004) 1 L 7 2 3T 4 T RT 3A20 E4EA 6 C P15EA 2007080800143 20070808 00143 CE 2007 8 8 CA070221005 1 20070206 G 2560 BUCKLE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE SEATBELT MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) COMPLIED WITH COMPANY CAMPAIGN NOTICE 010-25-10-011/SAIB NM-06-29. THE CREW SEATBELT ROTARY LATCH CAN BE CONTACTE D WITH THE CONTROL YOKE LET DOWN HOLDER WITH THE SEAT FULL FORWARD AND THE YOKE FULL AFT. IT IS POSSIBLE TO UNLATCH THE SEATBELT BY ROTATING THE YOKE AND MAKING CONTACT WITH THE BUCKLE. THE FUNCTION TEST WAS CARRIED OUT IAW THE INSTRUCTIONS GIVEN IN SAIB NM-06-29. (TC NR 20070221005) 1 L 7 2 4F 4 F A22CE E1NE 2007051700128 20070517 00128 NE 2007 5 17 CA070221006 1 20070213 G 3230 4546A MOTOR SKRSKY S61 S61N 8142104 NE GE CT58 CT581402 30011 NE LANDING GEAR INOPERATIVE W O OTHER J WARNING INDICATION DE DESCENT 1 CA 10618 1192 A019 (CAN) ON PRELANDING CHECK, MAIN LANGDNG GEAR FAILED TO EXTEND. EMERGENCY BLOW DOWN PROCEDURE WAS FOLLOWED AND AIRCRAFT L ANDED WITHOUT FURTHER INCIDENT. INVESTIGATION DETERMINED THAT THE ELECTRIC MOTOR THAT DRIVES THE MLG HYDRAULIC PUMP HAD FAILED AND TRIPPED THE CIRCUIT BREAKER. (TC NR 20070221006) 2 G 7 2 4U 4 U 1H15 1E3 2007051700129 20070517 00129 NM 2007 5 17 CA070221007 1 20070220 G 2133 14C3308 COUPLER HYDROFLOW BOEING 737 737* NM FS 967 S23R LEAKING W A UNSCHED LANDING K G FLUID LOSS MULTIPLE FAILURE CR CRUISE 1 CA (CAN) ALMOST AN HOUR INTO THE FIRST FLIGHT OF THE DAY, AIRCRAFT EXPERIENCED AUTOMATIC PRESSURIZATION FAULT WITH (AUTO-FA IL) LIGHT ON (WITH BOTH CPC`S FAIL). CREW RESORT TO MANUAL PRESSURIZATION CONTROL. AIRCRAFT ADVISED TO DIVERT TO MAIN BA SE FOR RECTIFICATION. UPON INVESTIGATION THE AFT OUT FLOW VALVE FOUND BLOCKED WITH ICE AND WATER SYSTEM QUANTITY LOW. THIS WAS THE SECOND SIMILAR INCIDENT ON THIS AIRCRAFT. FURTHER INVESTIGATION REVEALED WATER LEAKING FROM THE COUPLING ( SIMILAR TO COUPLING) AT THE FITTING RT ABOVE THE AFT OUTFLOW VALVE. (SIMILAR TO PREVIOUS FINDING). FITTING/LINES RE-ALI GNED TO RELIEVE POSSIBLE STRESS ON COUPLING. COUPLING TIGHTENED AND RESECURED WITH NEW PACKING. NO FURTHER LEAKS AND AIR 2 L 7 2 4F RT A16WE 2007051700131 20070517 00131 EA 2007 5 17 CA070222001 1 20070212 G 7897 22858222801 WIRE HARNESS CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE NR 1 ENGINE CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 22696 22696 (CAN) DURING ROUTINE MAINTENANCE INSPECTION , FOUND WIRING HARNESS ON NR1 ENGINE FOR THRUST REVERSER STOW SWITCH WIRING CHAFING ON EDGE OF LIGHTENING HOLE OF MOUNTING BRACKET. DAMAGED WIRING CUT OFF AND END RE-TERMINATED. MFG ILLUSTRATED PA RTS CATALOG (CSP A-006) 78-37-01 FIG 1A PG 0 , ITEM 40 (BRACKET ASSY, STOW SWITCH MOUNTING). LIGHTNING HOLE ON THIS BRAC KET CHAFED ON HARNESS FOR STOW SWITCH (TC NR 20070222001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007051700132 20070517 00132 EA 2007 5 17 CA070222002 1 20070212 G 5730 6001201687S SKIN CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE LT WING DENTED W K NONE O OTHER IN INSP/MAINT 1 CA 25955 25955 (CAN) CREW REPORTED BIRDSTRIKE ON APPROACH, MAINTENANCE INSPECTION FOUND DENT IN LT WING LEADING EDGE APPROX 6 FT OB FRO M FUSELAGE. DENT ALLOWABLE IAW SRM LIMITS. (TC NR 20070222002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007080800144 20070808 00144 CE 2007 8 8 CA070222003 1 20070222 G 5514 07321014 BRACKET CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2383 (CAN) HORIZONTAL STABILIZERS REMOVED FOR REPAIR. AFT ATTACHMENT POINT REINFORCEMENT BRACKETS PN 0732101-4 REPLACED WITH NEW. ADJACENT RIVETS REPLACED. TAIL RE-ASSEMBLED. DUAL INSPECTED. (TC NR 20070222003) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2007051700133 20070517 00133 NE 2007 5 17 CA070222004 2 20070219 G 7200 70BM031090 MODULE SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) POSSIBLE T1 OR T2 MO3 TURBINE RUB. REMOVED MO3 AND SEND TO MFG FOR INVESTIGATION. THE TURBINE RUB WAS NOTICED AFTE R SHUTDOWN OF THE ENGINE. (TC NR 20070222004) 1 G 7 1 3U 3 U NC H9EU E19EU 2007080800145 20070808 00145 CE 2007 8 8 CA070223001 1 20070220 G 2130 6621000000037 CHECK VALVE LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE731* 01518 WP CABIN PRESSURE BROKEN W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 2491 (CAN) SHORTLY AFTER TAKEOFF, DURING INITIAL CLIMBOUT, THE CREW NOTICED THAT THE CABIN ALTITUDE RATE OF CLIMB INDICATOR S HOWED 600FT/MIN CLIMB. USUALLY, THE CONTROLLER IS SET TO 400FT/MIN. THEY CONTINUED TO CLIMB AND TO MONITOR THE PRESSUR IZATION SYSTEM. A FEW MOMENTS LATER, THE INDICATOR SHOWED A 1500-2000FT/MIN CLIMB. THE CABIN ALTITUDE FOLLOWED THE AIRP LANE ALTITUDE. THE AIRPLANE WAS NOT PRESSURIZING THE CABIN. THE CREW CARRIED OUT THE APPROPRIATE CHECKLIST AND DECIDED TO DIVERT TO THEIR ALTERNATE AIRPORT. MEANWHILE, NO WARNING OR CAUTION INDICATIONS/MESSAGES APPEARED ON EICAS AND THE C REW COULD NOW SMELL KIND OF ODOR OF A OVERHEATED DUCT. THEY NOTICED ALSO THAT NO HEATED/CONDITIONED AIR WAS COMING FROM 2 L 7 2 4F 4 F RT T00008WI E6WE 2007053000012 20070530 00012 CE 2007 5 30 CA070223002 1 20070220 G 7797 8975294 WIRE HARNESS BEECH 100 100BEECH 1152916 CE GARRTT TPE331 TPE3316252B 01514 WP HARTZL HCB4T HCB4TN5 GL ENGINE ITT FAILED W E ENGINE SHUTDOWN N FALSE WARNING TX TAXI/GRND HDL 1 CA 495 P27035 (CAN) FLIGHT CREW DID ATTEMPTED AN ENGINE START NR 2 ENGINE WITH NO SUCCESS. AFTER MAINTENANCE HAD CORRECTED THE PROBLEM ASSOCIATED WITH THE FAILED START, THE CREW PROCEEDED TO CARRY OUT ANOTHER ENGINE START. ONCE THE ENGINE LIT OFF THE CRE W NOTED THAT THE ITT WAS CLIMBING RAPIDLY TOWARDS THE RED BUT THEN WOULD DROP AND RISE AGAIN. THEY DECIDED TO CONTINUE W ITH THE START. ONCE THE ENGINE HAD SETTLED AT IDLE, THE ITT BEGAN TO FLUCTUATE AND SLOWLY CLIMB TO THE REDLINE. THE CREW DECIDED AT THIS TIME TO SHUTDOWN THE ENGINE. MAINTENANCE TROUBLESHOT THE SYSTEM AND FOUND THAT THE ITT HARNESS WAS U/S . DUE TO THE FACT THAT THEY COULD NOT SPECIFICALLY STATE THAT THE PROBLEM WAS THE HARNESS AND NOT THAT THE HARNESS AND T 1 L 7 2 3T 4 T A14CE E2WE 6 C P40EA 2007053000013 20070530 00013 EA 2007 5 30 CA070223003 2 20070221 G 8520 UNK SEAL PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA MCAULY 3DF36C B3DF36C526 GL CRANKSHAFT LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 7000 1365 L327861A (CAN) DURING A NORMAL WALK AROUND, OIL WAS OBSERVED ON THE COWLING. AN INVESTIGATION INTO THE OIL LEAK REVEALED THE CRAN KSHAFT SEAL WAS BLOWN OUT. THE OIL SUMPS WERE DRAINED AND OIL FILTER CHECKED AND FOUND TO CONTAIN LARGE QUANTITIES OF ME TAL FILINGS. THE ENGINE WAS REMOVED FOR TEARDOWN REPORT AND OVERHAULED ENGINE INSTALLED. (TC NR 20070223003) 1 L 7 2 3O 3 O A20SO E14EA 5 C 2007051700160 20070517 00160 EA 2007 5 17 CA070223004 1 20070222 G 5330 SKIN DHAV DHC6 DHC6100 2802610 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 35713 (CAN) AIRCRAFT IS IN THE PROCESS OF GOING THROUGH ITS (5) YEAR CORROSION INSPECTION. DURING INSPECTION, SEVERAL AREAS OF CORROSION WERE NOTED IN AREAS WHERE CORROSION IS USUALLY NOT FOUND. THE HORIZONTAL STAB LOWER SKIN (CENTER) WAS CORRODE D AROUND SOME ANCHOR NUTS (FOR THE FAIRINGS), THE SUPPORT BRACKET FOR THE LOWER RUDDER ATTACH POINT, AND AROUND ALL THE PASSENGER WINDOW FRAMES (WHERE SPOT WELDS ARE). THE SUPPORT BRACKET IS BEING REPLACED AND WE ARE WAITING FOR RD`S FROM V IKING FOR THE OTHER AREAS. (TC NR741 20070223004) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007051700161 20070517 00161 SW 2007 5 17 CA070223005 1 20070220 G 6510 204040608001 SPRING BELL BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA TAIL ROTOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA A512 (CAN) ENGINEER CARRYING OUT REQUIREMENTS OF CAMP CODE NR 650121 (INSPECT/LUBE T/R DRIVESHAFT FLEX COUPLING). WHEN DISAS SEMBLING THE T/R QUILL OUTPUT COUPLING IN SITU ON THE M/R TRANSMISSION. UPON REMOVAL OF RETAINER AND PLATE, A SMALL SEC TION OF SPRING PN 204-040-608-001 FELL INTO THE HAND OF THE ENGINEER. REMAINDER OF SPRING WAS IN CORRECT POSITION. FUR THER DISASSEMBLY OF COUPLING REVEALED DAMAGE TO COUPLING P/N 204-040-603-009. NEW SPRING P/N 204-040-608-001 AND SERVIC EABLE COUPLING P/N 204-040-603-009 S/N A12-42482 INSTALLED. COMPLETE COUPLING ASSEMBLY LUBED AND REASSEMBLED IAW CHAPTE R 65 OF MM, AND REASSEMBLED ONTO THE M/R TRANSMISSION. (TC NR 20070223005) 1 G 7 1 4U 4 U H4SW E22EA 2007051700162 20070517 00162 SW 2007 5 17 CA070223007 1 20070222 G 6210 206010200133 BLADE BELL 206 206B 1181511 SW MAIN ROTOR DENTED W O OTHER O OTHER NR NOT REPORTED 1 CA 3224 (CAN) WHILE IN HANGAR, METAL PIECE OUT OF HANGAR OVERHEAD HEATER FELL ON M/R BLADE AND DENTED THE BLADE. BLADE WAS REMOV ED AND SENT FOR INSPECTION. HANGAR STAFF AND MANAGER WERE NOTIFIED AND REQUESTED TO INSPECT ALL OVERHEAD ACCESSORIES INC LUDING HEATERS FOR LOOSE OBJECTS. (TC NR 20070223007) 1 G 7 1 3U H2SW 2007080800146 20070808 00146 CE 2007 8 8 CA070223008 1 20070214 G 3245 0923150 TUBE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA MAIN TIRE FAILED W O OTHER O OTHER LD LANDING 1 CA 1000 (CAN) THE PILOT REPORTED A FLAT TIRE ON THE RUNWAY. MAINTENANCE REMOVED THE AIRCRAFT FROM THE RUNWAY. FOUND NO DAMAGE T O THE TIRE, THE TUBE WAS FOUND SPLIT IN TWO PLACES AROUND THE OUTER CIRCUMFERENCE. PART HAD BEEN INSTALLED APPROX 1000 HOURS AND APPROX 15 MONTHS. REPLACED THE TUBE AND TIRE AND RETURNED TO SERVICE. (TC NR 20070223008) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P9045 2007053000017 20070530 00017 EA 2007 5 30 CA070225001 1 20070212 G 5610 1393215 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE COCKPIT BROKEN W O OTHER O OTHER CR CRUISE 1 CA 10130 (CAN) INNER CORE OF CAPTAINS WINDSHIELD SHATTERED AT FL 330. MX REPLACED CAPTAINS WINSHIELD IAW 56-11-01. (TC NR 2007022 5001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007053000020 20070530 00020 2007 5 30 CA070226001 4 20070221 G 3497 CONNECTOR HONEYWELL BOEING 757 757236 1384971 NM RROYCE RB211 RB211535E437 54555 NE DRIVE UNIT BURNED W K NONE O OTHER IN INSP/MAINT 1 CA 4531 (CAN) CREW REPORTED EICAS STATUS MESSAGE, WXR SYSTEM. ON REPLACEMENT OF WXR DRIVE UNIT, FOUND BURNED ELECTRICAL CONNECTO RS. (TC NR 20070226001) 2 L 7 2 4F 4 F RT A2NM E12EU 2007053000021 20070530 00021 NM 2007 5 30 CA070226002 1 20070223 G 5610 5717623133 WINDSCREEN BOEING 737 737522 138449F NM CFMINT CFM56 CFM563C 13802 EU COCKPIT BROKEN W O OTHER O OTHER CR CRUISE 1 CA (CAN) CAPTAIN`S NR 2 WINDOW OUTER LAYER SHATTERED IN FLIGHT. WINDOW WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. REPOR TED AS AN SDR DUE TO A SUSPECTED RELIABILITY ISSUE WITH SUBJECT WINDOWS. (TC NR 20070226002) 2 L 7 2 4F 4 F RT A16WE E21EU 2007053000024 20070530 00024 CE 2007 5 30 CA070226005 1 20070208 G 5210 1014300327 PLATE BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL DOOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1328 1328 (CAN) DISCOVERED DOOR MAKING NOISE WHEN RAISING OR LOWERING DOOR. INVESTIGATED FOR LOOSE HARDWARE INSIDE DOOR AND DETERM INED PIN AND ROLLER ASSY MIGRATED OUT OF LOWER AFT LATCH ASSY. THE DEFECTIVE PART IN QUESTION IS THE PLATE P/N 101-43003 2-7. THE PLATE IS THE FIXTURE FOR A PIN P/N 101-430032-9 AND ROLLER P/N 50-430037-7. THESE PARTS (PIN/ROLLER)ARE CONTAIN ED IN THE PLATE BY MEANS OF STAKING WAS NOT PROPERLY SET WHEN MFG CAUSING THE PIN MIGRATING OUT OF THE PLATE. ALL OTHER PLATES WERE INSPECTED TO ENSURE EACH PLATE`S SECURITY. THESE PLATES/LATCHES ARE CRUCIAL TO THE STRUCTURAL INTEGRITY OF T HE DOOR AND FUSELAGE FRAME UNDER PRESSURIZATION LOADS. IPI REFERENCE 52-10-00 PG.16 ITEM 280, 285, 290 ILLUSTRATION SHEE 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007053000025 20070530 00025 SO 2007 5 30 CA070226006 2 20070219 G 8520 626608 CAMSHAFT CESSNA 150 150H 2071818 CE CONT O200 O200A 17020 SO MCAULY 1A101 1A101DCM GL ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 1294 (CAN) EXCESSIVE WEAR ON NR 1 AND NR 2 INTAKE LOBE. CAUSED EXCESSIVE PITTING ON ALL LIFTER BODY ASSEMBLIES. (TC NR 20070 226006) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2007053000027 20070530 00027 EA 2007 5 30 CA070226008 1 20070226 G 5711 2151003268 SPAR CAP CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43D 43D50 NE RT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4124 (CAN) WHILE PERFORMING AD CF92-26R1, A CRACK WAS DETECTED ON THE RT REAR LOWER SPAR CAP JUST OB OF RBL 51.00. WORK COMM ENCED ON REPAIR IAW THE MFG SPEC. UPON REMOVAL OF REINFORCING STRIP (P/N 215-10032-76) AN ADDITIONAL CRACK WAS FOUND ON THE LOWER SPAR CAP AT RBL 49.50. FOLLOWING REMOVAL OF THE DAMAGED SPAR CAP AN ADDITIONAL CRACK WAS NOTICED ON THE WING S PAR WEB (P/N 215-10032-242) AT RBL 50.00 THAT EXTENDED FROM THE SECOND LOWER, WING TO FUSELAGE PICK UP ANGLE FASTENER HO LE THROUGH TO THE LOWER FASTENER HOLE AND OUT THE EDGE OF THE WEB. THESE CRACKS ARE BOTH LOCATED OUTSIDE OF THE DESIGNAT ED INSPECTION AREA. (TC NR 20070226008) 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P8879 2007053000028 20070530 00028 EU 2007 5 30 CA070226009 1 20070131 G 5310 350A3821003 CROSSBEAM SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 373 (CAN) IAW THE AD 96-156-071 (B) R1 VISUAL INSPECTION EVERY 30 HOURS OR 150 LANDINGS. THE CRACKS WERE FOUND ON THE VISUAL . (TC NR 20070226009) 1 G 7 1 3U 3 U H9EU E19EU 2007053000029 20070530 00029 CE 2007 5 30 CA070226010 1 20070225 G 3297 CONNECTOR BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL MLG LOOSE W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) CREW REPORTED THAT THE GEAR INDICATION WOULD NOT INDICATE DOWN AND LOCKED ON APPROACH. MAINTENANCE PERSONNEL LAT ER CARRIED OUT AIRCRAFT LANDING GEAR SWINGS AND FOUND RT SQUAT SWITCH CONNECTOR PLUG LOOSE ON BULKHEAD. CLEANED, SECURED AND GEAR SWINGS FUNCTION CHECKS CARRIED OUT. NO FAULTS FOUND (TC NR 20070226010) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007053000030 20070530 00030 WP 2007 5 30 CA070226011 1 20070224 G 6310 C1664 RETAINER ROBSIN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE CLUTCH CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 895 2043 (CAN) CRACKS AT OUTER RING BOLT HOLES. CLUTCH ASSY REMOVED AND IS BEING SENT TO MFG FOR WARRANTY. (TC NR 20070226011) 1 G 7 1 3O 3 O H11NM 1E4 2008021900141 20080219 00141 SW 2008 2 19 CA070227001 1 20070222 G 6220 204011121121 GRIP BELL 212 212 1181420 SW MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) M/R GRIP TANG FOUND CRACK. COMPONENT ACCUMULATE 111 HRS SINCE LAST 150HRS NDT INSPECTION. (TC NR 20070227001) 1 G 7 1 4U H4SW 2007053000031 20070530 00031 2007 5 30 CA070227002 4 20070225 G 3442 20414440406 DRIVE UNIT BOEING 757 757236 1384971 NM RROYCE RB211 RB211535E4 54555 NE WX RADAR ANTENNA BURNED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) WXR RADAR DRIVE UNIT FOUND WITH TERMINAL 15 AND 16 BURNED (TC NR 20070227002) 2 L 7 2 4F 4 F RT A2NM E12EU 2007053000032 20070530 00032 NE 2007 5 30 CA070227003 2 20070215 G 7210 GEARBOX PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL REDUCTION MAKING METAL W A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 CA PCEPR0089 (CAN) SHORTLY AFTER TAKEOFF THE ENGINE CHIP LIGHT ILLUMINATED. THE PILOT RETURNED TO BASE. THE REDUCTION GEARBOX CHIP DE TECTOR WAS INSPECTED AND A FERROUS METAL FLAKE WAS FOUND ON THE DETECTOR, NO CONTAMINATION WAS FOUND IN ANY SCREENS OR T HE MAIN OIL FILTER. THE ENGINE WAS RETURNED TO SERVICE AFTER COMPLETING THE MAINTENANCE REQUIREMENTS SPECIFIED IN MM CH. 79-20-02. AFTER 10 HRS OF OPERATION THE OIL FILTER WAS PULLED AND NO CONTAMINATION WAS FOUND. THE ENGINE HAS ACCUMULATE D 101 HRS SINCE THE INCIDENT WITH NO FURTHER PROBLEMS. THE POWER SECTION NOW HAS 8788.3 TSN AND 652.9 TSO. (TC NR 200702 27003) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007053000033 20070530 00033 EA 2007 5 30 CA070227004 2 20070221 G 8550 TRANSFER TUBE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL OIL SYSTEM LOOSE W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) CRANKSHAFT FWD CAVITY OIL TRANSFER TUBE LOOSE LATERALLY AND ROTATIONALLY. CRANKSHAFT WAS REPAIRED APPROX 500 HOURS AGO. (TC NR 20070227004) 1 H 7 1 3O 3 O A21CE E286 5 N P874 2007080800147 20070808 00147 EU 2007 8 8 CA070227006 1 20070222 G 3234 GH115TAREVE HANDLE GROB 120 G120A 1660208 EU LYC O540 AEIO540D4D5 EA HARTZL HCC3Y HCC3Y* GL LANDING GEAR FAILED W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA 97 (CAN) LANDING GEAR HANDLE FAILED TO GIVE GEAR POSITION LIGHT AND IN-TRANSIT LIGHT INDICATIONS DURING A TRAINING MISSION. THE PILOT ELECTED TO FLY BY THE TOWER FOR ALL GEAR IN EXTENDED POSITION CONFIRMATION BEFORE AN UNEVENTFUL LANDING. AFT ER SHUTDOWN, THE LANDING GEAR POSITION LIGHTS BEGAN TO FUNCTION NORMALLY. MAINTENANCE PERSONNEL PLACED THE AIRCRAFT ON J ACK AND TRIED UNSUCCESSFULLY TO DUPLICATE THE SNAG. THE WIRING AND TERMINALS WERE INSPECTED FOR FAULTS. NUMEROUS GEAR SW INGS WERE PERFORMED. THE AIRCRAFT WAS RELEASED SERVICEABLE. HISTORICALLY, THE LANDING GEAR HANDLE UNIT POSITION LIGHTS H AVE FAILED ON GROUND CHECKS AND THE UNITS (A FLEET OF 9 NEW (2006) AIRCRAFT) WERE SYSTEMATICALLY UPGRADED TO REVISION (E 1 L 7 1 3O 3 O RT A49CE 1E4 5 C P25EA 2007053000035 20070530 00035 GL 2007 5 30 CA070227008 3 20070223 G 6111 BLADE HARTZL HCE4A3D PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL PROPELLER LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 2234 KX130 (CAN) EXCESSIVE GREASE WAS NOTED LEAKING FROM PROPELLER BLADE ROOT ON ALL (4) BLADES. PROPELLER REMOVED AND SENT FOR REP AIR. (TC NR 20070227008) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007080800148 20070808 00148 2007 8 8 CA070227010 4 20070223 G 3160 0710143931 CONTROL PANEL PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL EFIS FAILED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) MOVING THE HEADING KNOB ON THE CONTROL PANEL WOULD CAUSE A FAILURE INDICATION (RED X) THROUGH THE HEADING BUG, AND A TD WARNING ON THE BOTTOM RT CORNER OF THE EFIS SCREEN. THE CONTROL PANEL WAS REPLACED. (TC NR 20070227010) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007080800149 20070808 00149 2007 8 8 CA070227012 4 20070223 G 3455 066107214 RECEIVER PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ADF ERRATIC W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) THE VOLUME ON THE ADF WAS VERY HARD TO ADJUST AND ERRATIC. ADF RECEIVER REPLACED (TC NR 20070227012) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007053000038 20070530 00038 2007 5 30 CA070227013 4 20070223 G 3100 973321920 LIGHT PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL CAUTION LIGHT STUCK W O OTHER N FALSE WARNING CR CRUISE 1 CA (CAN) WHEN RESETING THE CAUTION LIGHT, IT WOULD OCCASIONALY STICK ON. THE CAUTION LIGHT ASSY WAS REPLACED WITH NEW. (TC NR 20070227013) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007053000039 20070530 00039 NE 2007 5 30 CA070227015 2 20070126 G 7210 PT6T3B GEARBOX BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE REDUCTION GB MAKING METAL W O OTHER J WARNING INDICATION CR CRUISE 1 CA 16983 1182 (CAN) ENGINE NR 1 CHIP DETECTOR CAUTION LIGHT ILLUMINATED WHILE IN CRUISE FLIGHT AND PILOT RETURNED TO BASE. REDUCTION G EARBOX NR 1 SIDE CHIP DETECTOR FOUND WITH SMALL AMOUNT OF METAL. CHIP DETECTOR WAS CLEANED AND AIRCRAFT FLEW ANOTHER 2 H OURS BEFORE SECOND CHIP LIGHT AND RETURNED TO BASE. SLIGHTLY MORE METAL FOUND ON PLUG. OIL WAS CHANGED AND AIRCRAFT WAS GROUND RUN 1 MINUTE BEFORE CHIP LIGHT ILLUMINATED. CHIP DETECTOR AND OIL FILTER CONTAINED MASSIVE AMOUNT OF METAL. REDU CTION GEARBOX WAS REPLACED AND SENT TO MFG FOR INVESTIGATION. NO REPORT HAS BEEN ISSUED AS YET. (TC NR 20070227015) 1 G 7 1 4U 4 U H4SW E22EA 2007053000040 20070530 00040 2007 5 30 CA070228002 4 20070221 G 6122 89741016 ARM WOODWARD MTSBSI MU2 MU2B60 5780460 CE GARRTT TPE331 TPE33110 01514 WP HARTZL HCB4T HCB4TN5 GL GOVENOR STIFF W O OTHER F FLT CONT AFFECTED LD LANDING 1 CA 875 875 2131212 (CAN) WHEN AIRCRAFT LANDED IT WOULD PULL TO THE LT. MAINTENANCE FOUND THAT THE PROP GOVERNOR ARM WAS STIFF AND WOULD N OT RETURN TO THE STOP. NOTE THIS GOVERNOR HAS SB TPE331-72-0567 RETURN SPRING INCORPORATED ON IT. GOVERNOR WAS REPLACED AND CHECKED SERVICEABLE. (TC NR 20070228002) 1 H 7 2 3T 4 T RT A10SW E4WE 6 C P40EA 2007053000041 20070530 00041 2007 5 30 CA070228003 4 20070228 G 6122 AT210937 CONTROL ARM CESSNA 206 U206 2073306 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL GOVERNOR DEFECTIVE W A UNSCHED LANDING F R J FLT CONT AFFECTED PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) THE SUBJECT AIRCRAFT WAS CLIMBING OUT AFTER TAKEOFF AND EXPERIENCED A SIGNIFICANT LOSS OF CLIMB POWER RELATED TO A DROP IN ENGINE RPM FROM 2700 RPM TO 1600 RPM. THE PILOT EXECUTED ALL APPROPRIATE EMERGENCY PROCEDURES/ACTIONS WITH NO IMPROVEMENT. THE PILOT DECLARED AN EMERGENCY AND WAS ABLE TO MANEUVER THE AIRCRAFT BACK TO THE AIRPORT, LANDED WITHOUT FURTHER INCIDENT. UPON EXAMINATION, IT WAS DETERMINED THAT THE INTENTION OF THE DESIGN OF THE PROP GOVERNOR ARM ATTACHME NT WAS TO HAVE THE BOLT THAT COMPRESSES THE ARM ON TO THE SPLINED SHAFT WAS TO PASS THROUGH THE GROVE IN THE SHAFT THUS PREVENTING THE ARM FROM SEPARATING EVEN IF THE BOLT DOES NOT HAVE SUFFICIENT TORQUE. IN THIS CASE THE ARM IS MANUFACTURE 1 H 7 1 3O 3 O A4CE E5CE 5 C P3EA 2007053000044 20070530 00044 CE 2007 5 30 CA070228006 1 20070228 G 7120 1299100471 MOUNT BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL ENGINE CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ROUTINE MAINTENANCE A BLEED AIR LINE WAS FOUND CHAFING AN ENGINE TRUSS MOUNT TUBE. BLEED AIR LINE PN: 118-9 10033-93 TRUSS MOUNT PN: 129-910047-17. THE DAMAGE WAS FOUND TO BE WITHIN REPAIRABLE LIMITS IAW THE AIRCRAFT SRM. THE MO UNT WAS REPAIRED BY A QUALIFIED WELDER AND THE AIRCRAFT WAS RELEASED BACK INTO SERVICE. A FLEET CAMPAIGN WAS CONDUCTED A ND ONE OTHER AIRCRAFT WAS FOUND WITH THE SAME PROBLEM WITH BOTH INCIDENTS ON THE LT ENGINE TRUSS MOUNT. (TC NR 20070228 006) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007053000045 20070530 00045 2007 5 30 CA070228007 4 20070215 G 3452 KT76A TRANSPONDER CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL INTERMITTENT W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) DURING CIRCUIT FLYING, TOWER REPORTED TO PILOT THAT HIS TRANSPONDER WAS INTERMITTENT. PILOT CANCELLED REMAINDER O F FLIGHT AND RETURNED TO AIRPORT. DEFECT WAS NOT DUPLICATED ON THE GROUND. DEFECT OCCURED THE NEXT DAY WHILE AIRCRAFT WA S AGAIN IN THE CIRCUIT, PILOT CANCELLED AND RETURNED TO AIRPORT. MAINTENANCE REMOVED TRANSPONDER, CLEANED CONTACTS AND R E-RACKED TRANSPONDER. AIRCRAFT RETURNED TO SERVICE AND HAS NOT HAD ANOTHER OCCURANCE IN OVER 50 HOURS. (TC NR 2007022800 7) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2007053000046 20070530 00046 CE 2007 5 30 CA070228008 1 20070208 G 5630 51116052 WINDOW CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO MCAULY 3AF34C 3AF34C92 GL EMERGENCY EXIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING MAJOR INSPECTION OF AIRCRAFT, REMOVED PLASTIC UPHOLSTERY COVER ON THE EMREGENCY EXIT HATCH. WINDOW FOUND CR ACKED AT ALL LOWER ATTACH SCREW HOLES, ONLY THE SEALANT KEEPING THE WINDOW IN PLACE. (TC NR 20070228008) 1 L 7 2 3O 3 O A7CE E7CE 5 C P22EA 2007053000047 20070530 00047 2007 5 30 CA070228009 4 20070227 G 3400 SWITCH CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA AVIONICS FAILED W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 CA (CAN) DURING TRAINING FLIGHT, PILOT EXPERIENCED COMPLETE AVIONICS FAILURE WHEN DEPRESSING THE PTT SWITCH. AIRCRAFT RETUR NED TO BASE, MAINTENANCE DUPLICATED THE SNAG, DISCOVERED THE AVIONICS SWITCH DEFECTIVE AND REPLACED IT WITH NEW ONE, NO FURTHER FAULTS FOUND. (TC NR 20070228009) 1 H 7 1 3O 3 O NT 3A12 E274 2007053000048 20070530 00048 EA 2007 5 30 CA070301001 2 20070301 G 8530 LW11901 INTAKE VALVE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE CRACKED W A UNSCHED LANDING R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CL CLIMB 1 CA 29 (CAN) INVESTIGATING LOW COMPRESSION REVEALED SMALL CHUNK (ONE QUARTER INCH SQUARE) OF INTAKE VALVE MISSING ON EDGE, AND A CRACK IN ANOTHER AREA. (TC NR 20070301001) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2007053000049 20070530 00049 EA 2007 5 30 CA070301002 1 20070228 G 5343 FITTING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE LANDING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BOTH MAIN LANDING GEAR FITTING FOUND CRACKED ON NDT INSPECTION IAW ADCF-1999-32R3. MAIN LANDING GEAR WILL BE REPLA CED. LT P/N 5321103 S/N PO-422V5Q, RT P/N 3521104 S/N PO-BBBB10. (TC NR 20070301002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007052400194 20070524 00194 NM 2007 5 24 CA070301003 1 20070223 G 2761 A44700009 ACTUATOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE SPOILER CRACKED W K NONE K FLUID LOSS NR NOT REPORTED 1 CA (CAN) WHILE DOING A PRE-FLIGHT WALK AROUND THE PILOT NOTICED HYDRAULIC FLUID DRIPPING FROM THE RT FLAP TRACK NR 3 FAIRIN G. THE LEAK WAS FOUND TO BE COMING FROM THE OB ROLL SPOILER ACTUATOR. UPON REMOVAL OF THE ACTUATOR IT WAS FOUND THAT THE HOUSING HAD CRACKED IN THE AREA SUROUNDING ONE OF THE PLUGS CAUSING THE PLUG TO DISLODGE. THE CRACK EXTENDED AROUND THE ENTIRE CIRCUMFERENCE OF THE THREADED PORTION OF THE ACTUATOR BODY WHERE THE PLUG IS THREADED IN. THE ACTUATOR WAS REPLA CED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070301003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007052400208 20070524 00208 EA 2007 5 24 CA070301004 1 20070301 G 2760 6009260273 ROD CNDAIR CL601 CL6012A12 1900303 EA SPOILER CORRODED W O OTHER J WARNING INDICATION IN INSP/MAINT 1 CA 10927 (CAN) DURING THE PILOT PRE-FLIGHT CHECKS THE LT FLIGHT SPOILER INDICATED DEPLOYED WHEN STOW WAS SELECTED. THE FLIGHT SPO ILER STOW/DEPLOY HANDLE WAS STIFF AT THE STOW EXTREMELY. VISUAL CONFIRMATION REVEALED THAT THE FLIGHT SPOILER WAS NOT FU LLY STOWED BUT THE RT SPOILER WAS. INVESTIGATION REVEALED THAT THE ROD ENDS OF THE 15 DEGREE CONTROL ROD WERE CORRODED W ITH RED RUST AND WERE NOT ABLE TO MOVE RESTRICTING THE FEEDBACK OF THE FLIGHT SPOILER CONTROL UNITS ON THE LT SIDE. OPER ATIONS USING TYPE 4 ANTI-ICING FLUIDS HAVE SHOWN TO CAUSE RED RUST CORROSION ON UNPROTECTED STEEL. THERE CURRENTLY IS NO REQUIREMENT TO TREAT THE SURFACES WITH A CORROSION INHIBITOR. THE USE OF TYPE 4 ANTI-ICING FLUIDS CONTRIBUTING TO CORRO 2 L 7 2 4F RT A21AE 2007053000050 20070530 00050 EA 2007 5 30 CA070302001 1 20070228 G 2497 WIRE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE DAMAGED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) AFTER A NORMAL LANDING AND WHILE TAXING TO THE GATE, THE FLT CREW REPORTED INTERMITTENT ARCING AND SMOKE COMING FR OM BEHIND THE CAPTAINS SIDE CB PANEL. AIRCRAFT DEPLANED NORMALLY. ELECTRICAL POWER WAS SHUT DOWN AND FIRE CREW WERE CA LLED TO CHECK OF FIRE. NO FURTHER REPORTS OF SMOKE/FIRE AFTER POWER WAS REMOVED FROM THE AIRCRAFT. UPON FURTHER INVES TIGATION, MAINTENANCE NOTED THAT (2) BUS FEEDER WIRES BECAME UNSECURED AND ARCED ON THE BULKHEAD WHICH RUNS PARALLEL TO B SCREEN TRAILING EDGE ON CAPTAINS SIDE AND APPROX FS280. DAMAGE WAS NOTED TO WIRE TERMINAL ENDS AND WIRE INSULATION AN D WELL AS BURN MARKS ON BULKHEAD/STRINGER AND 2 RIVETS. NO DAMAGE TO EXTERNAL FUSELAGE SKIN. BURN ON BULKHEAD IS 1 INC 2 L 7 2 4F 4 F RT A21EA E15NE 2007053000051 20070530 00051 EA 2007 5 30 CA070302002 1 20070225 G 5410 COWLING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE LT NACELLE DEPARTED W O OTHER D INFLIGHT SEPARATION CL CLIMB 1 CA (CAN) FLIGHT 3808, REPORTED A LOUD NOISE SHORTLY AFTER DEPARTURE, ON LANDING DISCOVERED COWLING MISSING AND UNKNOWN DAMA GE TO HORIZONTAL STABILIZER, NO REPORTED INJURIES, SN 7849 (REG N456ZW). WHAT COLLATERAL DAMAGE TO HZ STAB AND OTHER A REAS? HZ STAB LEADING EDGE AND HZ STAB CENTER BULLET CAP SIGNIFICANT IMPACT DAMAGE ASSUMED FROM LT UPPER FAN COWL DEPART ING THE AIRCRAFT. WHAT POINT IN DEPARTURE WAS (LOAD NOISE) HEARD? (LOUD NOISE) ASSUMED TO BE (CARGO SHIFT) NOW SUSPECT ED AS COWL DEPARTURE AT 2800 FEET ON INITIAL CLIMB OUT, ENROUTE. BECAUSE PILOTS ASSESSED NOISE TO BE (CARGO SHIFT) THEY ELECTED TO CONTINUE. LT UPPER FAN COWL WAS RECOVERED BY AND CURRENTLY RETAINED BY US COAST GUARD FROM LOCATION OUTSIDE 2 L 7 2 4F 4 F RT A21EA E15NE 2007053000052 20070530 00052 SW 2007 5 30 CA070302004 1 20070228 G 6230 206010003001 CONE SET BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MAIN ROTOR TORQUE CHECK WAS PERFORMED ON M/R MAST NUT BETWEEN 3 TO 8 FLIGHT HOURS IAW THE MM CHAPTER 5, AND MM, SE CTION 62-7, PARAGRAPH 5. INITIAL TORQUE CHECK OF MAST NUT TORQUE WAS FOUND BELOW MINIMUM SPECIFIED TORQUE OF 250 FT/L BS, IAW MM. A SUBSEQUENT TORQUE CHECK WAS PERFORMED AFTER SECOND FLIGHT OF 3 HOURS WITH THE SAME RESULTS, MAST NUT TORQ UE FALLING BELOW MINIMUM TORQUE VALUE OF 250FT/LBS. UPON VISUAL INSPECTION IN THE AREA OF THE CONE SET TO TRUNNION, IT WAS FOUND THAT ONE OF THE SPLIT CONES HALVES HAD MOVED. THEREFORE DID NOT PROVIDE A TRUE SEAT FOR THE SPLIT CONES T O THE M/R TRUNNION AS CONE SET AND WAS PARTIALLY COCKED. IT IS SUSPECTED THAT EACH OF THE 2 TORQUE CHECK ADJUSTMENTS 1 G 7 1 3U 3 U H2SW E4CE 2007053000053 20070530 00053 NM 2007 5 30 CA070305001 1 20070303 G 2752 NAS1611130 O-RING BOEING BOEING 727 727247 138408F NM DIRVE MOTOR FAILED W O OTHER K J FLUID LOSS WARNING INDICATION IN INSP/MAINT 1 CA 69942 84630D (CAN) AIRCRAFT EXPERIENCED LOW PRESSURE WARNING LIGHT FROM THE (A) HYD SYSTEM. DUE TO WEATHER THE CREW DECIDED THAT A RETURN TO DEPARTURE POINT WOULD BE THE BEST OPTION. THE CREW DECLARED AN EMERGENCY AND RETURNED WHERE THEY HAD A SAFE LA NDING AND THE AIRCRAFT WAS TOWED OFF THE RUNWAY TO THE RAMP. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THAT THE OB F LAP DRIVE HYD MOTOR WAS LEAKING HYD FLUID FROM THE CASE DRAIN TUBE. DUE TO WEATHER THE OB FLAP DRIVE HYD MOTOR WAS REPLA CED THE NEXT DAY. SYSTEM WAS SERVICED AND THE SYSTEM WAS LEAK AND FUNCTION TESTED SERVICEABLE. THE AIRCRAFT DEPARTED ON MAR.3, 2007 WITH NO FURTHER FAULTS. (TC NR 20070305001) 2 L 7 3 4F A3WE 2007053000054 20070530 00054 EA 2007 5 30 CA070305002 1 20070305 G 3233 MS2125004012 BOLT DHAV DHC8 DHC8311 1386006 EA ACTUATOR FITTING SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE ACCOMPLISHMENT OF C-CHECK, THE NOSE ACTUATOR FUSELAGE FITTING WAS FOUND WITH (2) BOLTS SHEARED. SB 8-53 -50 FOR THIS FAILURE. THE CUT IN S/N WAS 403 AND OUR A/C WAS S/N:410. THE MODIFICATION 8/2140 WAS TRULY ACCOMPLISHED. TH E FITTING WAS INSTALLED WITH BIGGER BOLTS BUT (2) OF THOSE BOLTS WERE SHEARED. (TC NR 20070305002) 2 H 7 2 4T RT A13NM 2007053000055 20070530 00055 NM 2007 5 30 CA070305003 1 20070305 G 2497 CL12068161 RELAY DHAV DHC8 DHC8102 2809003 NM ECU BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE ACCOMPLISHMENT OF THE INSPECTION TASK 7320/02, BOTH RELAY (RELAYS 7611-K3 AND K4) BASES WERE FOUND BROK EN AND BARELY MAKING CONTACT. SHOULD BOTH OF THEM HAVE FALLEN OFF AND DISCONNECTED IN FLIGHT, BOTH ECU`S WOULD HAVE HAD A COMPLETE POWER FAILURE. ECU SYSTEMS ARE DESIGNED TO HAVE POWER FED FROM NR 1 AND NR 2 ESSENTIAL BUSES. BOTH POWER SOUR CES GO THROUGH THEIR RESPECTIVE RELAYS K3 AND K4, A BROKEN BASE WOULD COMPROMISE THE 2 POWER SOURCES SIMULTANEOUSLY, RES ULTING IN EACH ECU REVERTING TO MANUAL MODE. THIS RELAY BASE PROBLEM WAS REPORTED BY ME FEW TIME FOR DIFFERENT SYSTEM ON DIFFERENT A/C AND DIFFERENT OPERATOR. (TC NR 20070305003) 2 H 7 2 4T RT A13NM 2007053000056 20070530 00056 CE 2007 5 30 CA070305004 1 20070228 G 5610 11438402522 WINDSHIELD BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE COCKPIT FAILED W B EMER. DESCENT O OTHER CR CRUISE 1 CA 21017 (CAN) CO-PILOTS WINDSHIELD SHATTERED IN CRUISE. AIRCRAFT DESCENDED IAW ABNORMAL OCCURRENCE CHECKLIST AND BROUGHT CABIN DIFF DOWN TO BELOW 2PSI. AIRCRAFT DESCENDED TO 11000 FT LOWERED CABIN ALTITUDE AT 500 FPM TO 11000FT. PUT CABIN INTO D UMP MODE AND CONTINUED FLIGHT WITHOUT INCIDENT. WINDSHIELD WAS REPLACED WITH IMPROVED PART. (TC NR 20070305004) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2007053000057 20070530 00057 WP 2007 5 30 CA070306001 1 20070223 G 2916 RESERVOIR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING INSPECTION HYDRAULIC FLUID FOUND VERY LOW, DETERMINED FLUID WAS LEAKING OUT OF THE VENT CAP ON HYDRAULIC RE SERVOIR. FLUID TOPPED UP TO CENTER OF SIGHT GLASS. AIRCRAFT GROUND RAN, DETERMINED FLUID WAS RISING IN RESERVOIR AND VEN TING OUT OF VENT CAP. RESERVOIR SENT TO MFG. REINSTALLED AFTER REPAIR, GROUND RAN AND FOUND HYDRAULIC LEVEL TO STAY AT C ENTER OF SIGHT GLASS. (TC NR 20070306001) 1 G 7 1 3O 3 O H11NM 1E4 2007053000058 20070530 00058 SW 2007 5 30 CA070306002 1 20070226 G 6310 206040118001 COUPLING BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL GEARBOX LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) C-GELT`S MAIN DRIVESHAFT P/N 206-040-015-103, S/N A-1331, 600 HR INSPECTION AND REPACK C/W FEB 22/07 AT 13635.5 HR S. TEST FLOWN 0.3 HRS, FLEW 7.1 HRS FEB 24 AND 25, ENGINEER FOUND TRANS. SIDE LEAKING GREASE AND COUPLING OVERHEATED. DR IVE SHAFT S/N A-2441 REMOVED FROM AC WITH FRESH 600 HR INSP. AND REPACK INSTALLED ON C-GELT. WHICH FAILED IN 11.7 HRS. W ITH THE SAME PROBLEM. DRIVE SHAFT S/N A1331 OVERHAULED WITH NEW INNER GEAR, NEW OUTER COUPLING, NEW O-RINGS, AND GREASE (PN 204-040-755-5 EXP. NOV 2/08) INSTALLED ON YHY, FAILED IN 23 MINUTES FLYING TIME, SAME PROBLEM (TRANSMISSION SIDE) TH E SAME TUBE OF GREASE WAS USED FOR ALL THE REPACKS. (TC NR 20070306002) 1 G 7 1 3U 3 U H2SW E4CE 2007053000059 20070530 00059 NM 2007 5 30 CA070306003 1 20070308 G 2150 20405010 ACM BOEING 737 737210C 1384459 NM PWA JT8 JT8D9A 52048 NE LEFT ODOR W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) SHORTLY AFTER DERPARTING, A SMOKE SMELL/HAZE WAS NOTICED IN THE CABIN AREA. THE AIRCRAFT RETURNED TO POINT OF DEPA RTURE AND LANDED WITHOUT FURTHER PROBLEM. THE CREW ADVISED MAINTENANCE THEY SUSPECTED THE LT PACK. THE SMOKE SMELL SOURC E WAS VERIFIED AS THE THE LT AIR CYCLE MACHINE. THE AIRCRAFT WAS RELEASED UNDER THE MEL. THE AIR CYCLE MACHINE WAS REPLA CED THE FOLLOWING DAY. (TC NR 20070306003) 2 L 7 2 4F 4 F A16WE E2EA 2007053000060 20070530 00060 EU 2007 5 30 CA070306004 1 20070308 G 5610 WINDSHIELD AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE COCKPIT FAILED W O OTHER O OTHER DE DESCENT 1 CA (CAN) ON DESCENT THE LT WINDSHIELD OUTER PANE FAILED. THE AIRCRAFT LANDED AT DESTINATION WITHOUT FURTHER PROBLEM. MAINTE NANCE INSPECTED THE AIRCRAFT PRIOR TO RETURN UNDER MEL, WHERE THE WINDSHIELD WAS REPLACED. (TC NR 20070306004) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2007053000061 20070530 00061 NE 2007 5 30 CA070306005 2 20070305 G 7510 82110588003 DUCT DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE BLEED AIR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 38233 38233 (CAN) DURING MAINTENANCE, TROUBLESHOOTING FOR LOW FLOW FROM CABIN GASPERS, MAINTENANCE, WHILE INSIDE THE AFT CARGO COMPA RTMENT FELT THE REAR PRESSURE BULKHEAD AS BEING WARM/HOT. INVESTIGATION IN THE AFT EQUIPMENT BAY, FOUND THE ENGINE BLEED AIR / APU / AIR-CONDITIONING PACKS JUNCTION DUCT CRACKED, CRACK EXTENDED AT LEAST 50 PERCENT OF CIRCUMFERENCE AND WAS O PEN BY APPROX .2500 INCH. DUCT ASSEMBLY REPLACED, FUNCTION CHECKS CARRIED OUT. AIRCRAFT RETURNED TO SERVICE. (TC NR 20 070306005) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007053000062 20070530 00062 EA 2007 5 30 CA070306006 1 20070304 G 3220 498003 DAMPER CNDAIR CL600 CL6002C10 1390015 EA NLG MALFUNCTIONED W O OTHER E VIBRATION/BUFFET LD LANDING 1 CA 3750 (CAN) ON LANDING CREW REPORTED AN AIRFRAME VIBRATION. CREW INDICATED THAT THE VIBRATION DEMINISHED AS THE AIRCRAFT SPEE D REDUCED. AIRCRAFT TAXIIED TO GATE WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTION REVEALED LOOSE APEX NUT ON LT SHI MMY DAMPER. NEW SHIMMY DAMPER AND ASSOCIATED PARTS ARE BEING REPLACED. (TC NR 20070306006) 2 L 7 2 4F RT A21EA 2007053000063 20070530 00063 EU 2007 5 30 CA070307001 1 20070302 G 3240 90002340PR BRAKE ASSY EMB ERJ190 ERJ190100IGW 3260408 EU GE CF34 CF3410E6 30015 NE MLG ICED W O OTHER E VIBRATION/BUFFET LD LANDING 1 CA (CAN) ON LANDING, AT 90 KNOTS THE LT OB TIRE BLEW, DAMAGING PART OF THE GEAR DOOR ASSEMBLY. ACFT DEPARTED WHERE A SEVERE SNOW STORM WAS TAKING PLACE, IT WAS NOTED THAT WATER WAS RUNNING FROM THE BRAKE ASSEMBLY AND DRIPPING FOR HOURS, SUSPEC T BRAKE BECAME PACKED WITH SNOW AND ICE. (TC NR 20070307001) 2 L 7 2 4F 4 F RT A57NM E00070EN 2007053000064 20070530 00064 EA 2007 5 30 CA070307002 1 20070305 G 2560 110124007 BUCKLE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL SEAT BELT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN COMPLYING WITH COMPANY CAMPAIGN NOTICE 010-25-10-011 AN INSPECTION FOR INTERFERENCE BETWEEN THE YOKE AND SEAT BELT BUCKLE WAS CARRIED OUT IAW NM-06-29.THE RESTRAINT RELEASE MECHANISM ON PILOT AND COPILOTS SEAT BELTS CAN BE OPERATE D UNINTENTIONALLY BY EXTREME NOSE UP AND ROLL COMMANDS OF THE CONTROL COLUMN. (TC NR 20070307002) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007053000065 20070530 00065 EA 2007 5 30 CA070307003 1 20070305 G 5730 C6W1017 SKIN PANEL DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL LT WING DEBONDED W K NONE O OTHER IN INSP/MAINT 1 CA 17756 (CAN) DEBONDING OF UPPER WING SKIN, OB OF NACELLE. DEBONDING DETECTED DURING ULTRA SONIC INSPECTION IAW SB 6/543. REPAIR CARRIED OUT IAW REO6-57-30-V013 REV A. (TC NR 20070307003) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007053000066 20070530 00066 EA 2007 5 30 CA070307004 1 20070305 G 5730 C6W1017 SKIN PANEL DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL RWS 72-97 DEBONDED W K NONE O OTHER IN INSP/MAINT 1 CA 17756 (CAN) DEBONDING OF UPPER WING SKIN, IB OF NACELLE. DEBONDING DETECTED DURING ULTRA SONIC INSPECTION IAW SB 6/543. REPAIR CARRIED OUT IAW REO6-57-30-V012 REV A. (TC NR 20070307004) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007053000067 20070530 00067 2007 5 30 CA070307005 4 20070306 G 3160 0660312525 DISPLAY PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL EFIS INOPERATIVE W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) DURING CRUISE, A (DU) WARNING APPEARED ON THE CO-PILOTS EADI DISPLAY INDICATING INSUFFICENT COOLING. THE DISPLAY U NIT WAS REPLACED. (TC NR 20070307005) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007053000068 20070530 00068 EA 2007 5 30 CA070307006 1 20070305 G 5730 SKIN DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 17756 (CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM T HE EXHAUST STACKS. REPAIRS CARRIED OUT IAW REO6-57-30-V017 (YW 85-91.25) AND REO6-57-30-V018 (YW 127-146). (TC NR 200703 07006) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007053000069 20070530 00069 EA 2007 5 30 CA070307007 1 20070305 G 5730 MS20470AD SKIN DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 17756 (CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM T HE EXHAUST STACKS. REPAIRS CARRIED OUT IAW REO6-57-30-V019 (YW 85-91.25) AND REO6-57-30-V020 (YW 122-135). (TC NR 200703 07007) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007053000070 20070530 00070 EA 2007 5 30 CA070307008 1 20070305 G 5730 C6W101427 SKIN PANEL DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL LT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 17756 (CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM T HE EXHAUST STACKS. REPAIRS TO CORRODED RIVETS WAS INITIATED AND REVEALED CORROSION UNDER THE RIVET HEADS EXISTED TO A DE PTH OF 0.011. REPAIRS CARRIED OUT I.A.W. VIKING REO6-57-30-V025 (YW 85-97.25). I.C.A.`S PENDING D.T.A. BY VIKING. (TC NR 20070307008) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007053000071 20070530 00071 SW 2007 5 30 CA070307009 1 20070305 G 2910 66D44 REGULATOR FRCHLD SA227 SA227CC 3377522 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE HYD SYSTEM MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AC DEPARTED BASE AND UPON GEAR RETRACTION BOTH LT AND RT HYD PRESSURE LIGHTS ILLUMINATED FOR 3-4 SECONDS THEN WENT OUT. AIRCRAFT RETURNED TO BASE AND UPON INVESTIGATION IT WAS FOUND THAT NO RESIDUAL HYD PRESSURE WAS PRESENT AFTER ENG INE SHUTDOWN. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THE 31 PSI REGULATOR WAS CONTAMINATED WITH HYD FLUID. THE REGULATOR CHECK VALVE HAD BEEN INSTALLED INCORRECTLY. THE CHECK VALVE WAS REPOSITIONED AND THE REGULATOR WAS REPLAC ED. GEAR WINGS WERE CARRIED OUT SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070307009) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2007053000072 20070530 00072 NE 2007 5 30 CA070307010 2 20070307 G 7497 WIRE WIRE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 286 E051A254 (CAN) GOVERNOR WAS LAZY AND SNAGGED BY PILOT. UPON FURTHER INVESTIGATION, THE MAGNETO WAS REMOVED AND PRIMARY COIL WIRE WAS TOUCHING AND CHAFING ON TACH POINT CONNECTOR. THIS MAY BE THE POSSIBLE CAUSE FOR LAZY GOVERNOR. NEW MAGNETO INSTAL LED PROBLEM RECTIFIED. MAGNETO SENT BACK FOR WARRANTY. (TC NR 20070307010) 1 G 7 1 3O 3 O H11NM 1E4 2008032400412 20080324 00412 EU 2008 3 24 CA070307011 1 20070307 G 6710 CYCLIC CONTROL UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE MAIN ROTOR MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) CYCLIC CONTROLS JAMMED IN NEUTRAL POSITION, CYCLIC WAS ABLE TO MOVE AFT, FWD, AND LT BUT WAS UNABLE TO MOVE CYCLIC TO THE RT DURING LEVEL CRUISE AT 2500 FT AGL. REDUCED AIRSPEED TO 65 KNOTS AND CONTROLS BROKE FREE AND OPERATED NORMALL Y. THEN FLEW BACK TO THE HANGER AT AN AIRSPEED OF 65 KNOTS AND CONTROLS FELT NORMAL UNTIL AT ABOUT 200 FT AGL AND AIRSP EED AT ABOUT 40 KNOTS WITH 300 FT IAW MINUTE DESCENT RATE THE CYCLIC JAMMED ON THE RT SIDE AGAIN. THE AC SLOWLY STARTED A BANK AND AN OVERSHOOT AND PROCEEDED TO THE RUNWAY. DURING THE OVERSHOOT, BROUGHT AIRSPEED BACK UP TO AROUND 65 KNOTS A ND JOINED A RT DOWNWIND FOR RUNWAY 13. ON A BASE LEG, SHUTOFF HYD AND PERFORMED A NORMAL HYD FAILURE APPROACH. CONTROLS 1 G 7 2 3U 3 U NC R0001RD E34NE 2007053000073 20070530 00073 SO 2007 5 30 CA070308001 1 20070302 G 2842 68101002 FLOAT PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA HARTZL HCC3Y HCC3YF1 GL FUEL CELL WORN W K NONE O OTHER IN INSP/MAINT 1 CA 7968 (CAN) HOLE IN FLOAT WAS EXTREMELY WORN AND FLOAT FELL OFF. (TC NR 20070308001) 1 L 7 1 3O 3 O 2A13 1E10 5 C P25EA 2007053000074 20070530 00074 2007 5 30 CA070308002 4 20070306 G 2397 J176037 WIRE COLLINS BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE NR 2 COMM HEAD SHORTED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 16604 14617 (CAN) FLIGHT CARRIED OUT MAR. 5, 2007, NR 2 COMM DISPLAY WENT BLANK. CONTROL HEAD REPLACED WITH LOANER UNIT, GROUND TES TED OK. NEXT FLIGHT AIRCRAFT TOOK OFF AND UPON ROTATION THE CREW SMELLED SOMETHING BURNING AND SAW SMOKE COMING FROM THE NR 2 COMM CONTROL HEAD. AIRCRAFT RETURNED TO BASE. CONTROL HEAD REMOVED FOR REPAIR AND INVESTIGATION. FOUND WIRE P/N J176037 IN NOSE AVIONICS BAY GOING FROM RELAY J304 TO TRANSCEIVER TRAY WITH CONTINUITY TO GROUND. WIRE REPAIRED AND ORI GINAL CONTROL HEAD INSTALLED AFTER REPAIR, COMM OPERATED FOR 2 HOURS ON THE GROUND WITHOUT FAULT. NO PROBLEMS REPORTED T HE SUBSEQUENT FLIGHT. (TC NR 20070308002) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2007053000075 20070530 00075 EA 2007 5 30 CA070308003 1 20070307 G 7603 2100140007 GEARBOX CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B1 NE THROTTLE FAILED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 1740 (CAN) DURING CLIMB, THE RT ENGINE WAS NOT ABLE TO ACHIEVE CLIMB POWER. THE AIRCRAFT DIVERTED TO ANOTHER AIRPORT AND LAND ED UNEVENTFULLY. INVESTIGATION REVEALED THAT THE THROTTLE GEARBOX HAS AN AREA WHERE MOVEMENT OF THE THROTTLE HAS NO EFFE CT ON THE MFC. THIS CONDITION WOULD NOT ALLOW THE MFC TO REACH THE MAX POWER STOP. MFG SB 604-76-004 HAD NOT BEEN COMPLI ED WITH AT THIS TIME NOR WAS IT REQUIRED AT THIS TIME BUT WAS PLANNED TO BE COMPLETED. THERE ARE (2) AD`S FOR THROTTLE G EARBOX WEAR ON THE RJ FLEET. REF: AD 2005-06-04, AD 2004-05-12. AFTER REPAIR AND RETURN OF THE AIRCRAFT TO THE MAIN BA SE AND EXAMINATION OF THE FAILED PART THEN MORE INFORMATION WILL BE PROVIDED. (TC NR 20070308003) 2 L 7 2 4F 4 F RT A21EA E15NE 2007053000076 20070530 00076 WP 2007 5 30 CA070308004 1 20070306 G 2430 CONTROL SWITCH CVAC 340 340CVAC 242270A WP ALLSN 501D 501D22 03005 GL HAMSTD 54H 54H60 NE SHORTED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) WHILE CARRYING OUT FLIGHT TRAINING THE LT GENERATOR WAS TURNED OFF. WHEN SELECTED BACK ON, IT WAS NOTED THAT SMOKE WAS COMING FROM THE VOLTAGE REGULATOR. THE GANG BAR WAS SELECTED TO SHUTOFF DC POWER. DURING TROUBLESHOOTING THE MAINTE NANCE CREW DISCOVERED AN AN960-10L WASHER HAD SHORTED OUT THE WIRE ATTACHMENT LUGS ON THE BACK OF THE GENERATOR CONTROL SWITCH. A REPLACEMENT VOLTAGE REGULATOR WAS INSTALLED AND THE WIRING SYSTEM WAS INSPECTED. NO FURTHER DAMAGE WAS NOTED. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070308004) 2 L 7 2 4R 4 T 6A6 E282 6 C P906 2007053000077 20070530 00077 EU 2007 5 30 CA070309001 1 20070303 G 2820 110BR02 VALVE BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R408 CR4086123F17 EU FUEL CROSSFEED MALFUNCTIONED W A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) AC WAS IN CRUISE FLIGHT, WHEN THE FLIGHT CREW OPENED THE FUEL CROSSFEED VALVE TO BALANCE THE FUEL LOAD. WHEN THE F LIGHT CREW SELECTED THE LT BOOST PUMPS TO OFF, THE NR 1 ENGINE FLAMED OUT. THE FLIGHT CREW FEATHERED ENGINE NR 1. THE PI LOT THEN CLOSED THE FUEL CROSSFEED VALVE, SWITCHED THE LT FUEL BOOST PUMPS TO ON AND SUCCESSFULLY RELIT ENGINE NR 1. THE AIRCRAFT CONTINUED WITH OUT FURTHER DIFFICULTY. UPON ARRIVAL, MAINTENANCE BLED THE FUEL SYSTEM, CHECKED FOR FUEL CONTA MINATION AND EXTENSIVELY GROUND RAN ENGINE NR 1. NO FAULTS WERE FOUND. FURTHER INVESTIGATION HAS DETERMINED HS SB 28/27 WHICH PREVENTS ACCUMULATION OF AIR IN THE CROSSFEED LINE HAS NOT BEEN ACCOMPLISHED ON THIS AIRCRAFT. IT IS BELIEVED AIR 2 L 7 2 3T 4 T A24EU A196 6 C P17BO 2008021900147 20080219 00147 EU 2008 2 19 CA070309002 1 20070308 G 6210 C621A1006103 BLADE UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 995 995 (CAN) BLADE CRACKED BY TRAILING EDGE OF TRIM TAB, IB SIDE. (TC NR 20070309002) 1 G 7 2 3U 3 U NC R0001RD E34NE 2007053000078 20070530 00078 WP 2007 5 30 CA070309003 1 20070302 G 6210 500P2100101 BLADE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20 03013 GL MAIN ROTOR CRACKED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 CA 2597 (CAN) PILOT FELT A VIBRATION AND UPON LANDING CHECKED MAIN ROTOR BLADES. A CRACK APPROXIMATELY 18 INCHES FROM THE ROOT, RUNNING PERPENDICULAR TO THE TRAILING EDGE WAS DISCOVERED. IT APPEARS AS IF THE BLADE DEBONDED AT A RIB, AS THE CRACK FO LLOWS STRAIGHT FROM THE RIB TOWARD THE C-CHANNEL BEFORE IT TRAILS OFF TO THE SIDE. MDHI )OEM) HAS SUGGESTED THAT THE CA USE WAS TOO MUCH TENSION ON THE BLADES AT TIE-DOWN, OIL-CANNING BETWEEN THE RIBS PUTTING PRESSURE ON THE BOND. (TC NR 20 070309003) 1 G 7 1 3U 3 U H3WE E4CE 2007053000079 20070530 00079 EU 2007 5 30 CA070310001 1 20070302 G 2752 9787320309 ACTUATOR PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TE FLAPS FROZEN W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 2242 2242 (CAN) FLAPS WOULD WORK AS NORMAL, EVEN AFTER 4 HOUR FLIGHT AT -45. AFTER LANDING & SELECTING FLAPS UP, (FLAPS) CAUTION WOULD COME ON NR FLAPS WOULD NOT MOVE. NORMAL GROUND RESET WOULD NOT WORK. FLAP CONTROL 1 AMP C/B APPEARED TO BE (BLOWN) BUT NOT POPPED. AFTER RESETTING C/B, NORMAL FLAP RESET WOULD WORK. TRYING TO MOVE FLAPS AGAIN WOULD CAUSE THE SAME PROB LEM. NOTE THIS DEFECT WOULD ONLY OCCUR IF THE GROUND TEMP WAS -5 TO -12. AFTER WARMING THE AIRCRAFT IN A HANGAR FLAPS WO ULD RESET NR WORK. UPON INSPECTION OF THE ACTUATORS IT WAS DISCOVERED THAT 3 OF THE 4 ACTUATORS WERE HEATING UP. +40 TO +50 C. ACTUATORS WERE REMOVED FROM SERVICE. ALSO NOTED WAS FLAP CONTROL WARNING UNIT FAILURE CODES INCLUDED TOO HIGH CUR 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007053000080 20070530 00080 EU 2007 5 30 CA070310002 1 20070302 G 2752 97897320309 ACTUATOR PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TE FLAPS FROZEN W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 2242 2242 (CAN) FLAPS WOULD WORK AS NORMAL, EVEN AFTER 4 HOUR FLIGHT AT -45. AFTER LANDING AND SHUTDOWN (FLAPS) CAUTION WOULD COME ON AND FLAPS WOULD NOT MOVE. NORMAL GROUND RESET WOULD NOT WORK. FLAP CONTROL 1 AMP C/B APPEARED TO BE (BLOWN) BUT NOT POPPED. AFTER RESETTING C/B, NORMAL FLAP RESET WOULD WORK. TRYING TO MOVE FLAPS AGAIN WOULD CAUSE THE SAME PROBLEM. NOTE THIS DEFECT WOULD ONLY OCCUR IF THE GROUND TEMP WAS -5 TO -12. AFTER WARMING THE AIRCRAFT IN A HANGAR FLAPS WOULD RESET AND WORK. UPON INSPECTION OF THE ACTUATORS IT WAS DISCOVERED THAT 3 OF THE 4 ACTUATORS WERE HEATING UP. +40 - +50 C. AC TUATORS WERE REMOVED FROM SERVICE. ALSO NOTED WAS FLAP CONTROL WARNING UNIT FAILURE CODES INCLUDED TOO HIGH CURRENT DRAW 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007053000081 20070530 00081 EU 2007 5 30 CA070310003 1 20070302 G 2752 9787320309 ACTUATOR PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TE FLAPS FROZEN W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 2242 2242 (CAN) FLAPS WOULD WORK AS NORMAL, EVEN AFTER 4 HOUR FLIGHT AT -45. AFTER LANDING AND SHUTDOWN (FLAPS) CAUTION WOULD COME ON AND FLAPS WOULD NOT MOVE. NORMAL GROUND RESET WOULD NOT WORK. FLAP CONTROL 1 AMP C/B APPEARED TO BE (BLOWN) BUT NOT POPPED. AFTER RESETTING C/B, NORMAL FLAP RESET WOULD WORK. TRYING TO MOVE FLAPS AGAIN WOULD CAUSE THE SAME PROBLEM. NOTE THIS DEFECT WOULD ONLY OCCUR IF THE GROUND TEMP WAS -5 TO -12. AFTER WARMING THE AIRCRAFT IN A HANGAR, FLAPS WOULD RESE T AND WORK. UPON INSPECTION OF THE ACTUATORS IT WAS DISCOVERED THAT 3 OF THE 4 ACTUATORS WERE HEATING UP. +40 - +50 C. A CTUATORS WERE REMOVED FROM SERVICE. ALSO NOTED WAS FLAP CONTROL WARNING UNIT FAILURE CODES INCLUDED TOO HIGH CURRENT DRA 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007053000082 20070530 00082 NM 2007 5 30 CA070312001 1 20070220 G 2913 SHAFT DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE HYD PUMP SHEARED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA 20954 8792 MX422697 (CAN) AFTER START OF THE NR 1 ENGINE, THE HYDRAULIC PUMP CAUTION LIGHT REMAINED ON WITH ZERO PRESSURE INDICATED ON THE A SSOCIATED HYDRAULIC SYSTEM PRESSURE GAUGE. AIRCRAFT ENGINES WERE SUBSEQUENTLY SHUTDOWN AND ENGINEERING CONTACTED TO COND UCT DEFECT RECTIFICATION PRIOR TO RETURNING THE AIRCRAFT TO SERVICE. ENGINEERING DEFECT INVESTIGATION REVEALED THAT THE NR 1 ENGINE DRIVEN HYDRAULIC PUMP DRIVE SHAFT WAS SHEARED. THE HYDRAULIC PUMP WAS REPLACED WITH A SERVICEABLE ASSY IAW A MM 29-10-11 AND THE AIRCRAFT SUBSEQUENTLY RETURNED TO SERVICE. (TC NR 20070312001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007053000083 20070530 00083 NE 2007 5 30 CA070312002 2 20070306 G 7230 BLADES AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE COMPRESSOR DAMAGED W A UNSCHED LANDING R A PARTIAL RPM/PWR LOSS FLAME/FIRE CL CLIMB 1 CA 40214 18251 731775 (CAN) ON TAKEOFF AT 500 AGL, 3 TO 4 STALLS ON NR 2 ENGINE, LOUD POPPING NOISE, ATC SAW FLAMES COMING OUT. AIRCRAFT RETUR NED TO DEPARTURE, ENGINE BOROSCOPE FOUND DAMAGED COMPRESSOR BLADES FROM STAGE 6 TO STAGE 9. ENGINE REMOVED FROM AIRCRAFT AND SENT TO SHOP FOR INVESTIGATION. (L-4298804) (TC NR 20070312002) 2 L 7 2 4F 4 F RT A28NM E29NE 2007053000084 20070530 00084 NM 2007 5 30 CA070312003 1 20070312 G 4940 360581217 STARTER BOEING 737 73735B 13844BM NM GE CFM56 CFM563B1 13802 NE APU FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) APU SHUTDOWN ON ITS OWN AND WOULD NOT RE-START. NEW STARTER INSTALLED. NEW STARTER BLEW APART ON FIRST START ATTEM PT. SECOND STARTER INSTALLED AND OPERATED SERVICEABLE. (TC NR 20070312003) 2 L 7 2 4F 4 F RT A16WE E2GL 2007053000085 20070530 00085 NM 2007 5 30 CA070312004 1 20070307 G 3810 LINE BOEING 767 767306 1385148 NM GE CF6 CF680C2B6F 30025 NE POTABLE WATER FAILED W O OTHER K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) DURING NORMAL WALK AROUND FOUND WATER LEAKING OUT OF THE BELLY OF THE AIRCRAFT, FORWARD AREA. SUBSEQUENT INVESTIGA TION FOUND CLAMSHELL (CLAMP) P/N CA62505-56BL HOLDING POTABLE WATER LINE THAT RUNS OVER FWD. E&E COMPARTMENT TOWARD THE FWD. LAVATORY FAILED RESULTING IN THE TWO EICAS COMPUTERS BEING SOAKED WITH WATER. BOTH COMPUTERS CHANGED, CLAMP REPLAC ED WITH APPROVED P/N 14C33-08, METAL NOT THE ORIGINAL PLASTIC. (TC NR 20070312004) 2 L 7 2 4F 4 F RT A1NM E13NE 2007053000086 20070530 00086 EA 2007 5 30 CA070312005 1 20070225 G 5220 1196411 HOUSING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE ECAPE HATCH CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 11157 (CAN) CREW ESCAPE HATCH HANDLE HOUSING FOUND CRACKED AND OUTER HANDLE WAS CORRODED. THE PART OF THE HOUSING THAT FITS IN SIDE OF THE INNER HANDLE WAS CRACKED COMPLETELY OFF. (TC NR 20070312005) 2 L 7 2 4F 4 F RT A21EA E15NE 2008021900156 20080219 00156 CE 2008 2 19 CA070312006 1 20070222 G 3230 1225P363 PRESSURE SWITCH ADI7999001 BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL LANDING GEAR MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING LANDING GEAR SWINGS IT WAS NOTICED THAT THE LANDING GEAR PUMP WAS HESITATING. PROBLEM WAS TRACED BACK TO TH E PRESSURE SWITCH. SWITCH WAS REPLACED AND GEAR SWUNG, FAULT FEE. (TC NR 20070312006) 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2008021900171 20080219 00171 SO 2008 2 19 CA070312007 1 20070303 G 3246 16102100 WHEEL HALF PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL LANDING GEAR DESTROYED W K NONE O OTHER NR NOT REPORTED 1 CA 2203 (CAN) SUSPECT HARD LANDING WITH SIDE MOVEMENT STRESSED WHEEL HALF CASTING. THE BACK STOP PORTION OF HUB CASTING HAS A NE W CLEAN BREAK. WITH RACE BROKEN, BEARING CONE FAILED. WHEEL ASSEMBLY TIPPED IN MOUNTING FORK AND RODE ON BRAKE CALIBER T ORQUE PLATE. BRAKE DISK WORE ON INSIDE OF MOUNTING FORK. (TC NR 20070312007) 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 2007053000087 20070530 00087 NM 2007 5 30 CA070312008 1 20070222 G 3230 10134501 TORQUE LINK DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE LT MLG BROKEN W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA 5304 (CAN) DURING TAKEOFF A SEVERE VIBRATION WAS NOTICED ON THE ENTIRE AC, THE CREW ABORTED THE TAKEOFF SUCCESSFULLY. MAINTEN ANCE FOUND THE LT MLG TORQUE LINK BROKE INTO 2 PARTS ALONG WITH DAMAGE TO LT IB AND LT OB TIRES, BRAKE UNITS NR 1 AND 2, WIRING AND BRAKE LINES, AND STRUCTURE DAMAGE TO THE NACELLE. MFG TO CARRY OUT INVESTIGATION AS TO THE CAUSE OF TORQUE L INK FAILURE. (TC NR 20070312008) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008021900187 20080219 00187 SO 2008 2 19 CA070312009 1 20070220 G 2420 587857 ALTERNATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL LEFT FAILED W O OTHER H P ELECT. POWER LOSS-50 PC NO WARNING INDICATION CR CRUISE 1 CA (CAN) LT ALTERNATOR FAILED AT CRUISE, FAULT-FIELD POWER FUSE BLOWER. RT ALTERNATOR FAILED/NOT ON LINE, FAULT, BAD ALTER NATOR MASTER SWITCH OR NOT ON. RT INOP ALTERNATOR SWITCH/RELAY FAILED SO NO COCKPIT INOP LIGHT. AC CONTINUED FLIGHT ON BATTERY POWER TO DESTINATION. FLIGHT AT NIGHT -30C AND IFR CONDITIONS. CONCLUSIONS/RECTIFICATIONS: LT FIELD FUSE REP LACED. RT ALTERNATOR INOP SWITCH REPLACED. ALTERNATOR MASTER SWITCH CLEANED/TESTED. BATTERY CHARGED AND TESTED. AC AND ALTERNATOR SYS OPS CHECKED AND AC RETURNED TO SERVICE. (TC NR 20070312009) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007053000088 20070530 00088 EA 2007 5 30 CA070312010 2 20070307 G 7320 COTTER PIN HONEYWELL BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL FUEL CONTROL MISINSTALLED W E ENGINE SHUTDOWN W INADEQUATE Q C DE DESCENT 1 CA 2504 A63002 (CAN) ON DESCENT FROM 21000 FEET, THE RT POWER LEVER WAS PULLED BACK BUT THE ENGINE DID NOT RESPOND TO THE COMMAND. ENGI NE WAS THEN SHUTDOWN TO PREVENT OVERTORQUING. ON INSPECTION OF FCU LINKAGES, MECHANICS FOUND THE COTTER PIN GOING THRO UGH INPUT SHAFT AFT OF MAX STOP ARM HAD ONLY ONE LEG BENT OVER. OTHER LEG, IN CERTAIN POSITIONS WOULD HANG UP ON MIN ST OP SCREW, PREVENTING FCU ARM FROM RETURNING TO IDLE. COTTER PIN WAS PROPERLY SECURED AND AIRCRAFT WAS TEST FLOWN WITH N O FURTHER INCIDENTS. (TC NR 20070312010) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007053000089 20070530 00089 EA 2007 5 30 CA070313001 2 20070312 G 8530 LW16812 LIFTER CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL INTAKE UNLOCKED W K NONE O OTHER IN INSP/MAINT 1 CA 1778 1778 RL326476T (CAN) DURING THE REAMING OF A STICKY EXHAUST VALVE GUIDE IN CYLINDER NR 4, IT WAS FOUND THAT THE NR 4 CYLINDER INTAKE HY DRAULIC LIFTER HAD LOST ITS SNAP RING. THE WEAR PATTERN SHOWED THAT THE SNAP RING HAD MIGRATED ALONG BETWEEN THE PUSHRO D AND THE SHROUD TUBE (THE SNAP RING SHOWED WEAR ON ITS INSIDE DIAMETER WERE IT HAD MOVED ALONG THE PUSHROD, AND WEAR ON ITS OUTSIDE DIAMETER, WHERE IT HAD WORN ALONG THE INSIDE OF THE PUSHROD SHROUD TUBE). THE SNAP RING WAS FOUND INTACT (S AME SHAPE), IN THE NR 4 CYLINDER ROCKER BOX. ONE EXPLANATION IS THAT WHEN THE CYLINDER WAS CHANGED 525.0 HRS PREVIOUS, THE SNAP RING WAS NOT PROPERLY INSTALLED IN THE HYDRAULIC LIFTER WHEN IT WAS BLED DOWN BEFORE INSTALLATION, AND IT POPPE 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007053000090 20070530 00090 2007 5 30 CA070313002 4 20070312 G 6113 05503214 BULKHEAD CESSNA CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL SPINNER CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 373 (CAN) THIS AIRCRAFT HAS HAD ALL THE AFT BULKHEAD AND HEAVIER SPINNER UPGRADES AND HAS HAD IT ALL ASSEMBLED IAW THE LATES T SB. CRACKS WERE FOUND FORMING PARALLEL FROM THE PROP BOLT HEAD CONTACT SURFACE ON (3) OF THE (6) HOLES. YOU HAVE TO LO OK VERY CAREFULLY AS THE CRACKS RADIATING FROM THE PROP BOLT HOLES ARE VERY FINE AND HIDE UNDER THE FACTORY PRIMER. THE TORQUE OF THE PROP BOLTS IS SHEAR STRESSING THE BULKHEAD. A COVER PLATE IS NEEDED TO OFFSET THE BOLTS FROM THE THIN ALU MINUM SHEET METAL BULKHEAD. THIS PROBLEM IS RE-OCCURRING WITH THIS SPINNER ASSY ON SEVERAL OF OUR AC THAT WE MAINTAIN. ( TC NR 20070313002) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007060100117 20070601 00117 EU 2007 6 1 CA070313003 1 20070312 G 3320 8ES00375200 POWER SUPPLY AIRBUS 310 A310300 3930305 EU GE CF6 CF680C2* GL CABIN LIGHTS OVERHEATED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) DURING CRUISE, FLIGHT CREW OBSERVED WHAT APPEARED TO BE WHITE SMOKE EMANATING FROM READING LIGHT (PSU) PANEL ASSEM BLY ABOVE SEAT 30 AB. CREW SWITCHED OFF READING LIGHTS AND SMOKE STOPPED. ON ARRIVAL TO THE STATION, MAINTENANCE FOUND O NE TRANSFORMER PRINTED CIRCUIT BORD SEVERELY OVERHEATED. POWER SUPPLY REPLACED AND SYSTEM TESTED SERVICEABLE. (TC NR 2 0070313003) 2 L 7 2 4F 4 F RT A35EU E23EA 2007060100118 20070601 00118 NM 2007 6 1 CA070313004 1 20070313 G 3230 LANDING GEAR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NOSE INOPERATIVE W O OTHER O OTHER AP APPROACH 1 CA (CAN) DURING APPROACH TO BASE, THE NLG DOORS DID NOT OPEN AND THE NLG DID NOT EXTEND. APPROACH CANCELLED, AIRCRAFT ENTE RED HOLDING PATTERN. GEAR CYCLED WITHOUT SUCCESS NLG EXTENSION. MLG OPERATED NORMALLY. ALTERNATE EXTENSION PROCEDURE CON DUCTED. NLG REMAINED RETRACTED AND NLG DOORS REMAINED CLOSED. AIRCRAFT PERFORMED A TOUCH AND GO TO SHOCK THE NLG DOWN, W ITHOUT SUCCESS. AIRCRAFT CONDUCTED A 60-DEGREE BANK TO APPLY POSITIVE G IN AN EFFORT TO EXTEND THE NLG WITHOUT SUCCESS. AIRCRAFT LANDED WITH NLG RETRACTED. TO COMPLETE FULL INVESTIGATION. AOM NR 210 ISSUED. (TC NR 20070313004) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007060100119 20070601 00119 CE 2007 6 1 CA070313005 1 20070312 G 5340 05521335 SUPPORT CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL LANDING LIGHT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2647 (CAN) THE SUPPORT WAS CRACKING AT THE MOUNTING FLANGE BEND RADII AT THE (4) AND (8) O`CLOCK POSITIONS. THE CRACKS HAD PR EVIOUSLY BEEN STOPDRILLED BUT HAD CONTINUED PAST THE STOPDRILLING. SUSPECT THAT CRACKING STARTS AT SHARP/ROUGH ALUMINUM EDGES AND IS AGGRAVATED BY THE PROPELLER’S PROXIMITY CAUSING PULSATION AGAINST THE LIGHT. (TC NR 20070313005) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007060100120 20070601 00120 EA 2007 6 1 CA070313006 2 20070308 G 8520 13F1773585 CRANKSHAFT RKWELL 700 700 7630520 SW LYC O540 TIO540R2AD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE BROKEN W E ENGINE SHUTDOWN E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA 1289 RL352361A (CAN) APPROXIMATELY 45 MILES OUT, THE CREW NOTED A VIBRATION FROM THE LT ENGINE. THE CREW SECURED THE ENGINE AND FEATHER ED THE PROP IAW THE CHECK LIST. THE FLIGHT CONTINUED TO DESTINATION WITHOUT INCIDENT. WITH COWLING’S REMOVED, NOTED THE CASE HAD BEEN BREACHED AND THE CAMSHAFT HAD BROKEN. WITH NR 5 CYL. REMOVED WE COULD SEE THAT THE CRANKSHAFT WAS BRO KEN AFT OF THE MAIN BEARING BETWEEN CYLINDER BANKS 2-4 AND 5-6. THIS PERMITTED THE CRANK SEGMENT WITH CONNECTING RODS F OR CYL`S 5 AND 6 TO FLAIL AROUND, BREAKING THE CRANKCASE AND CAMSHAFT. THE ENGINE WILL BE SENT OUT FOR FURTHER TEARDOW N. PARTS AVAILABLE FOR INSPECTION. (TC NR 20070313006) 1 L 7 2 3O 3 O A12SW E14EA 5 C P33EA 2007060100121 20070601 00121 NE 2007 6 1 CA070313008 2 20070313 G 7530 3024606 FITTING AIRTRC AT802 AT802 0390305 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MA3 GL ENGINE CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 1761 PCE107017 (CAN) UPON INSPECTION OF THE P3 AIR LINES, IT WAS DISCOVERED THAT THERE WAS NO CLEARANCE BETWEEN THE P3 FILTER HOUSING N IPPLE FITTING (P/N 3024606) AND THE ENGINE REAR FIRE SEAL PLATES (P/N 3031003 AND 3031004). UPON REPOSITIONING OF THE F IRE SEAL PLATES, IT WAS DISCOVERED THAT THE PLATES HAD CHAFED INTO THE NIPPLE FITTING APPROXIMATELY 0.020 INCH. THE FITT ING WAS REMOVED AND REPLACED. THE OTHER AIRCRAFT IN OUR FLEET WERE INSPECTED WITH NO OTHER DEFECTS NOTED. (TC NR 200703 13008) 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2008021900194 20080219 00194 SW 2008 2 19 CA070313009 1 20070313 G 5411 804501 FRAME AIRTRC AT802 AT802A 0390308 SW PWA PT6 PT6A65AG 52043 NE HARTZL HCB5M HCB5MA3 GL FIREGATE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 568 (CAN) DURING ANNUAL INSPECTION, THE LOWER LONGITUDINAL FRAME OF THE STAINLESS STEEL FIREGATE P/N 80450-1 WAS NOTED TO BE CRACKED AT THE FWD END AND BULGED AT THE AFT END. (2) OTHER AC HAVE SIMILAR DAMAGE. WATER WAS FOUND IN THE TUBE AND TH E DAMAGE APPEARS TO BE CAUSED BY WATER FREEZING. (TC NR 20070313009) 1 L 7 1 3T 4 T NC A19SW E4EA 6 C P44GL 2008012900013 20080129 00013 SO 2008 1 29 CA070314001 1 20070314 G 3233 WTC21151 ACTUATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL MLG BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ACTUATOR BROKEN, FOUND DURING REPAIRS TO AIRCRAFT. (TC NR 20070314001) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007060100122 20070601 00122 EA 2007 6 1 CA070314002 2 20070117 G 7200 ENGINE BEECH 1900 1900D 1154162 CE PWA PT6 PT6* 52043 EA MAKING METAL W E ENGINE SHUTDOWN A FLAME/FIRE CL CLIMB 1 CA 114390 (CAN) ON CLIMB FOLLOWING TAKE-OFF, FLAMES WERE SEEN EXITING THE ENGINE EXHAUST ACCOMPANIED BY A LOUD NOISE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL AND ROTOR SEIZURE. MFG WILL INVE STIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314002) 2 L 7 2 4T 3 T RT A24CE E2NE 2007060100123 20070601 00123 NE 2007 6 1 CA070314004 2 20070125 G 7321 311717804 FUEL CONTROL AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE UNSERVICEABLE W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION AP APPROACH 1 CA 9077 (CAN) ON APPROACH, ENGINE TORQUE FELL TO ZERO WHEN POWER LEVER WAS RETARDED. SUBSQUENT THROTTLE INPUT RESULTED IN TORQUE FLUCTUATION AND THE ENGINE WAS SUBSEQUENTLY SHUTDOWN IN FLIGHT. TROUBLESHOOTING LED TO REPLACEMENT OF THE ENGINE FUEL CONTROL UNIT. (TC NR 20070314004) 2 H 7 2 4T 4 T RT E20NE 2007060100124 20070601 00124 WP 2007 6 1 CA070314005 2 20070217 G 7200 FE73121C ENGINE AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE7312 01518 WP NR 1 VIBRATION W E ENGINE SHUTDOWN E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA P73114 (CAN) NR1 ENGINE FAILED, TEMPERATURE SPIKE ABOVE 1000 DEGREES C. AS VIBRATION INCREASED, THEN INDICATIONS (ITT, FIFY N2 ) DECREASED. N1 TURNED, SECURITY, PULLED FIRE HANDLE. ON ARRIVAL, COULD NOT TURN N1, FOUND OIL AND METAL PIECES IN EXHA UST, ENGINE REMOVED FROM AIRCRAFT. PRIOR OIL ANALYSIS WERE NORMAL (16 DEC.2006 AND 21 SEPT, 2005). NO METAL ON MAG PLU G. A FEW SLIVERS IN FILTER. (TC NR 20070314005) 2 L 7 2 4F 4 F A33EU E6WE 2008013100014 20080131 00014 SO 2008 1 31 CA070314006 1 20070307 G 5720 STRUCTURE PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA SNSNCH 74D 74DM EA RT WING ROOT CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 8000 (CAN) RT FORWARD WING WALK ASSEMBLY, P/N 62061-002. RT ROOT WAS CRACKED. (TC NR 20070314006) 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2007061300123 20070613 00123 EU 2007 6 13 CA070314007 1 20070130 G 7930 310595801 RELIEF VALVE AEROSP ATR42 ATR42500 8680948 EU PWA PW120 PW127 NE ENGINE OIL UNSERVICEABLE W E ENGINE SHUTDOWN J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSP ECTION LED TO REPLACEMENT OF THE ENGINE COLD-OIL PRESSURE RELIEF VALVE. (TC NR 20070314007) 2 H 7 2 4T 4 T RT A53EU E20NE 2007060100125 20070601 00125 EU 2007 6 1 CA070314008 1 20070313 G 2752 9787320309 ACTUATOR PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TE FLAPS FROZEN W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 2259 2259 (CAN) FLAP ACTUATOR WOULD TEMPORARILY FREEZE/SEIZE AT THE END OF A FLIGHT WHILE WAITING ON THE GROUND AT OAT-5-12C. AFTE R WARMING A/C, FLAPS WOULD RESET AND FUNCTION NORMALLY. ACTUATOR REMOVED FROM SERVICE. FLAP WARNING UNIT FAILURE CODES INDICATED HIGH CURRENT DRAW. FLAPS SYSTEM TESTED WITHIN CURRENT DRAW LIMITS AFTER REPLACEMENT OF ACTUATOR. MFG TECH REP HAS REQUESTED TEARDOWN REPORTS. (TC NR 20070314008) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007061300124 20070613 00124 EA 2007 6 13 CA070314009 2 20070129 G 7200 ENGINE PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A6 52043 EA FLAMED OUT W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA 103238 (CAN) DURING ATTITUDE RECOVERY TRAINING, THE ENGINE FLAMED OUT. THE ENGINE WAS SUCCESSFULLY RE-STARTED IN FLIGHT BUT SU FFERED AN OVER TEMPERATURE DURING THE RE-LIGHT. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHE D. (TC NR 20070314009) 1 L 7 1 3T 3 T RT A78EU E4EA 2007060100126 20070601 00126 EU 2007 6 1 CA070314010 1 20070313 G 2752 ROD END PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ACTUATOR LOOSE W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 17 (CAN) ROD END WAS FOUND LOOSE/WORN OUT ON OVERHAULED ACTUATOR. TEMPORARILY INSTALLED IN AIRCRAFT WHILE AWAITING REPLACEM ENT. REMOVED WITH 16.8 HRS TSO BEFORE RETURNING TO SUPPLIER. (TC NR 20070314010) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007061300125 20070613 00125 NE 2007 6 13 CA070314011 2 20070208 G 7260 SHAFT DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE ACCESSORY DRIVE DAMAGED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 12383 (CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CRUISE AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED ACCESSORY DRIVE TOWER SHAFT DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070314011) 2 H 7 2 4T 4 T RT A13NM E20NE 2007061500188 20070615 00188 NE 2007 6 15 CA070314012 2 20070213 G 7261 PW545B ENGINE CESSNA 500 560CESSNA 2076750 CE PWC 545 PW545B NE OIL CONSUMPTION W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA DD0351 (CAN) THE ENGINE LOW-OIL-PRESSURE WARNING ACTIVATED IN FLIGHT. SUBSEQUENT INVESTIGATION REVEALED HIGH OIL CONSUMPTION. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314012) 2 L 7 2 4F 4 F RT A22CE E00059EN 2007061300126 20070613 00126 NE 2007 6 13 CA070314013 2 20070213 G 7250 BLADES AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE POWER TURBINE DAMAGED W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 121276 (CAN) DURING CLIMB, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER. THE ENGINE WAS SH UTDOWN IN FLIGHT. GROUND INSPECTION REVEALED A SEIZED PROPELLER AND DAMAGED POWER TURBINE BLADES. MFG WILL INVESTIGAT E THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC 20070314013) 2 H 7 2 4T 4 T RT A53EU E20NE 2007061300127 20070613 00127 NE 2007 6 13 CA070314014 2 20070202 G 7230 COMPRESSOR BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE ENGINE SEIZED W E ENGINE SHUTDOWN A FLAME/FIRE CR CRUISE 1 CA 114109 (CAN) FLAMES WERE SEEN EXITING THE ENGINE EXHAUST AND THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALE D COMPRESSOR SEIZURE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314014) 2 L 7 2 4T 4 T RT A24CE E26NE 2007061300128 20070613 00128 NE 2007 6 13 CA070314015 2 20070210 G 7250 TURBINE BLADES AEROSP ATR72 ATR72 EU PWA PW120 PW124B NE ENGINE DAMAGED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CL CLIMB 1 CA 124662 (CAN) THE ENGINE FLAMED OUT OUT FOLLOWING TAKEOFF. SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES AND META L DEBRIS IN THE ENGINE OIL SYSTEM. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20 070314015) 2 H 7 2 4T 4 T RT E2ONE 2007061300129 20070613 00129 NE 2007 6 13 CA070314016 2 20070215 G 7200 ENGINE BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE VIBRATION W E ENGINE SHUTDOWN E VIBRATION/BUFFET CR CRUISE 1 CA 100180 (CAN) ENGINE EXHIBITED HEAVY VIBRATION DURING CRUISE AND WAS SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE EVENT AND ADV ISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070314016) 2 H 7 2 4F 4 F RT A16SW E25EA 2007060100127 20070601 00127 NM 2007 6 1 CA070314017 1 20070312 G 4900 4503067A APU BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU APU BAY MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) CREW MADE A NORMAL APU START REQUEST, A FEW SECONDS LATER HEARD A LOUD BANG AND GOT THE APU FAIL ADVISORY LIGHT. A PU ENCLOSURE SUFFERED STRUCTURAL DAMAGE AFTER FUEL VAPOR IGNITED. NO FIRE LIGHT OR FIRE NOTED. EXAMINATION OF APU COMPA RTMENT AREA REVEALED THAT APU ACCESS DOORS DEPARTED THE TAILCONE. TAIL CONE TO BE REPLACED. (TC NR 20070314017) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007061300130 20070613 00130 NE 2007 6 13 CA070314018 2 20070216 G 7230 ACTUATOR GULSTM 200 200 4500308 NM PWC PW306 PW306A 52165 NE INLET GUIDE VANE FAILED W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) ON APPLICATION OF POWER IN CLIMB, THE ENGINE EXPERIENCED A COMPRESSOR STALL ACCOMPANIED BY AN UNCOMMANDED POWER RE DUCTION, PARAMETER FLUCTUATIONS AND A FADEC FAULT INDICATION. SUBSEQUENT INVESTIGATION LED TO REPLACEMENT OF THE ENGINE INLET GUIDE VANE ACTUATOR. (TC NR 20070314018) 2 L 7 2 4F 4 F RT A53NM E35NE 2007061300131 20070613 00131 NE 2007 6 13 CA070314019 2 20070216 G 7310 3033981 LINE PIPER PA46 PA46500TP 7104622 SO PWA PT6 PT6A42 52043 NE FCU FRACTURED W O OTHER R X J PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN FLIGHT AND FLAMED OUT ON LANDING ROLL-OUT. SUBSEQUENT I NSPECTION REVEALED A FRACTURED FUEL DELIVERY TUBE. (TC NR 20070314019) 1 L 7 1 3O 4 T RT A25SO E4EA 2007061300132 20070613 00132 EA 2007 6 13 CA070314020 2 20070122 G 7250 TURBINE BLADES AGUSTA A109 A119 0261102 EU PWA PT6T PT6T3 52045 EA ENGINE FRACTURED W E ENGINE SHUTDOWN O OTHER LD LANDING 1 CA TH0727 (CAN) ON LANDING FOLLOWING A TRAINING FLIGHT, THE ENGINE EMITTED A LOUD NOISE. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314020) 1 G 7 2 3U 4 U H7EU E22EA 2007061300133 20070613 00133 NE 2007 6 13 CA070314021 2 20070223 G 7200 ENGINE RAYTHN 36 G36 7150061 CE PWA PT6 PT6A68 NE MAKING METAL W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING A TRAINING MISSION, THE ENGINE EXPERIENCED AN UNCOMMANDED REDUCTION IN POWER ACCOMPANIED BY A NOISE AND A C HIP DETECTOR INDICATION. SUBSEQUENT INSPECTION REVEALED METALLIC DEBRIS IN THE ENGINE OIL SYSTEM. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314021) 1 L 7 1 3O 4 T RT 3A15 E26NE 2007061300134 20070613 00134 NE 2007 6 13 CA070314022 2 20070222 G 7200 ENGINE AYRES S2 S2RHGT65 0970110 SO PWA PT6 PT6A65AG 52043 NE FLAMED OUT W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) THE ENGINE WAS REPORTED TO HAVE FLAMED OUT IN FLIGHT. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONC E DETERMINED. (TC NR 20070314022) 1 L 7 1 3T 4 T NC E4EA 2007060100128 20070601 00128 EU 2007 6 1 CA070315001 1 20070306 G 3000 HEATER AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE CCAS PROBE FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DEPARTING, THE CREW OBSERVED A STICK PUSHER/ STICK SHAKER FAULT. AFTER A FAILED, RESET THE AIRCRAFT, RETURNED TO P OINT OF DEPARTURE WITH OUT FURTHER PROBLEM. MAINTENANCE VERIFIED THE NR 1 CCAS ALPHA PROBE HEAT FUNCTION HAD FAILED. THE PROBE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE (TC NR 20070315001) 2 H 7 2 4T 4 T RT A53EU E20NE 2007060100129 20070601 00129 EA 2007 6 1 CA070315002 1 20070313 G 3320 BB100200258 SOCKET CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE CABIN LIGHTS BURNED W H K DEACTIVATE SYST/CIRCUITS NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) REF LOG PAGE NR 593976. F/A REPORTS ELECTRICAL SMELL IN FORWARD CABIN, AROUND ROW 2 AND 3. 4FD SIDEWALL LIGHT HOLD ER FOUND AT FAULT, CBP2 C/B S5 OPENED AND SECURED. SIDEWALL LIGHT INOP, DEFERRED IAW MEL 33-21-01 CAT (C). SOCKET ASSY P/N BB1-0020-02-58 (TC NR 20070315002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007060400003 20070604 00003 EU 2007 6 4 CA070315003 1 20070310 G 3297 CONNECTOR AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE MLG UNSECURE W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) DEPARTING, THE CREW OBSERVED A FAIL TO RETRACT INDICATION ON THE RT MAIN LANDING GEAR. THE AIRCRAFT RETURNED TO PO INT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE FOUND A CONNECTOR IN THE INDICATION SIGNAL HARNESS WIT H A CONNECTOR NOT FULLY LOCKED. THE CONNECTOR WAS SECURED SYSTEM INTEGRITY VERIFIED AND THE AIRCRAFT RETURNED TO SERVICE . (TC NR 20070315003) 2 H 7 2 4T 4 T RT A53EU E20NE 2007060400004 20070604 00004 2007 6 4 CA070315004 4 20070312 G 3410 7004544713 HSI AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE NR 1 MALFUNCTIONED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) DEPARTING THE CREW OBSERVED A CIRCUIT BREAKER TRIP ON THE NR 1 EADI, RESET SUCCESSFUL. THIS WAS FOLLOWED BY A CIRC UIT BREAKER TRIP ON THE NR 1 EHSI. THE RESET ATTEMPT FAILED AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURT HER PROBLEM. MAINTENANCE REPLACED THE NR 1 SYMBOL GENERATOR UNIT. THE SYSTEM FUNCTION CHECKED SATISFACTORY AND THE AIRC RAFT WAS RETURNED TO SERVICE. (TC NR 20070315004) 2 H 7 2 4T 4 T RT A53EU E20NE 2007060400005 20070604 00005 NM 2007 6 4 CA070315005 1 20070215 G 3246 29685 BEARING BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NR 4 MAIN WHEEL DAMAGED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) AFTER LANDING, A PIECE OF NR4 BRAKE DISK WAS FOUND AT THE SPOT WHERE THE A/C WAS PARKED. A/C WAS INSPECTED AND THE FOLLOWING ARE REPORTED. FOUND DAMAGE AT INNER BEARING AFTER THE INSPECTION WITH NR 4 WHEEL ASSEMBLY WAS REMOVED. WHEEL BRAKE AND AXLE ASSYS REPLACED. (TC NR 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008013100015 20080131 00015 EU 2008 1 31 CA070316001 1 20070315 G 6340 MS2771923 SWITCH SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE LOW ROTOR INTERMITTENT W K NONE N FALSE WARNING IN INSP/MAINT 1 CA 8171 (CAN) LOW ROTOR HORN NOT WORKING BUT LIGHT ON 4ALPHA PANEL WOULD COME ON. SYSTEM TROUBLESHOT AND FOUND SWITCH TO BE INT ERMITENT. A/C GROUNDED TILL NEW SWITCH HAD BEEN REPLACED. THE POTENTIAL FOR GIVING A FALSE READ TO THE PILOT DURING FLI GHT MAY HAVE OCCURED. AIRCRAFT WAS GROUNDED. SWITCH HAS BEEN REPACED AND A/C RETURN TO SERVICE. (TC NR 20070316001) 1 G 7 1 3U 3 U H9EU E19EU 2008013100016 20080131 00016 SW 2008 1 31 CA070316002 1 20070316 G 3610 LINE AIRTRC AT802 AT802 0390305 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MA3 GL BLEED AIR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 1437 (CAN) DURING ANNUAL INSPECTION, THE BLEED AIR LINE FOR THE CABIN HEATER WAS FOUND UNSECURED UNDER THE COCKPIT FLOOR. FUR THER INVESTIGATION FOUND THE MUFFLER FOR THE LINE BROKEN IN (2) PIECES AT THE FWD END. THE PARTS WERE REPLACED. THE REMA INING AIRCRAFT IN THE FLEET WERE INSPECTED. ONE ADDITIONAL AIRCRAFT WAS FOUND WITH THE SAME DEFECT. THE PARTS WERE REPLA CED WITH SERVICEABLE UNITS. (TC# 20070316002) 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2008020100099 20080201 00099 CE 2008 2 1 CA070316003 1 20070313 G 7714 MS250384 TACH GENERATOR BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) N1 TACH GENERATOR FAILED IN FLIGHT. (TC NR 20070316003) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007061300136 20070613 00136 EA 2007 6 13 CA070316004 2 20070212 G 7322 CARBURETOR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE OUT OF ADJUST W O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA 455 (CAN) ENGINE WAS RUNNING ROUGH, UNABLE TO ADJUST IDLE ON CARBURETOR. ENGINE WANTED TO SHUTDOWN ON APPROACH WHEN THROTTL E WAS RETARDED. (TC NR 20070316004) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2007060400006 20070604 00006 EU 2007 6 4 CA070319001 1 20070312 G 2140 BAS30198 PRESSURE SWITCH BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R408 CR4086123F17 EU HEATER MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING DEPARTURE THE AIRCRAFT`S HEATER FAILED AND THE CREW WAS UNABLE TO RESTART THE HEATER. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE HEATER PRESSURE SWITCH AND THE AIRCR AFT RETURNED TO SERVICE AFTER SATIFACTORY GROUND CHECK. (TC NR 20070319001) 2 L 7 2 3T 4 T A24EU A196 6 C P17BO 2007060400007 20070604 00007 NE 2007 6 4 CA070319004 2 20070316 G 7310 263451 DUMP VALVE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE FLOW DIVIDER LEAKING W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 4065 1179 (CAN) AFTER TAKEOFF DURING CLIMB, NR1 ENGINE LOST POWER AND TRQ ROLL BACK, CREW ELECTED TO SHUT ENGINE DOWN AND RETURN T O DEPARTURE AIRPORT. MAINTENANCE INSPECTION FOUND FUEL SUPPLY LINE TO FLOW DIVIDER/DUMP VALVE (B-NUT) NOT LOCKWIRED AND BACKED OFF, ALLOWING HIGH PRESSURE FUEL LEAK. O-RINGS REPLACED, FUEL LINE (B-NUT) TIGHTENED AND LOCKWIRED. ENGINE RUNS C ARRIED OUT, AIRCRAFT RETURNED TO SERVICE. (TC NR 20070319004) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007060400008 20070604 00008 WP 2007 6 4 CA070319005 2 20070316 G 7230 8934825 IMPELLER FRCHLD SA227 SA227CC 3377522 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE ENGINE FRACTURED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 20650 20650 P44721C (CAN) ENGINE WAS REMOVED DUE TO NOT MAKING TARGET TAKEOFF TORQUE. UPON DISASSEMBLY THE 2ND STAGE COMPRESSOR IMPELLER FA ILED AND HAS EXPERIENCED A FATIGUE TYPE FAILURE. THE PRESENT TIME ON THE IMPELLER IS 20,650.2 HOURS AND 28,175 CYCLES. A LARGE PIECE OF THE LEADING EDGE BROKE OFF AND WAS DISCOVERED FURTHER DOWN IN THE ENGINE. IT HAS BEEN RETAINED. IT HA S EXTENSIVE DAMAGE DUE TO SECONDARY IMPACT DAMAGE. NO RUB DAMAGE, AS WOULD TYPICALLY CAUSE A PROBLEM, FOR THE IMPELLER WAS FOUND SUGGESTING THAT THE COMPRESSOR WAS BUILT PROPERLY. THE DAMAGE NOTED IN PHOTOGRAPH IS BELIEVED TO BE SECONDARY RUB DAMAGE DUE TO THE CRACKED PIECE GETTING LODGED BETWEEN THE SHROUD AND THE IMPELLER. ALL DIMENSIONS FOR ENGINE SHIMM 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2007060400009 20070604 00009 EA 2007 6 4 CA070319006 2 20070314 G 8530 77672 TAPPET BEECH 60 B60 1153605 CE LYC O541 TIO541E1C4 41536 EA HARTZL HCF3Y HCF3YR2 GL ENGINE SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 443 (CAN) ENGINE MODIFIED IAW FIREWALL FORWARD CENTRILUBE STC. PREVIOUS EXPERIENCE WITH THIS ENGINE SERIES PROMPTS REGULAR T APPET INSPECTIONS. TAPPETS INSPECTED AND SPALLING WAS FOUND, EVEN ON THIS STC`D ENGINE. TAPPETS SENT TO FIREWALL FORWAR D FOR EXAMINATION, AND ONLY 3 OF THE 12 TAPPETS WERE JUDGED REUSABLE. THIS TAPPET-BODY MANUFACTURING PROCESS HAS BEEN H IGHLY SUSPECT FOR MANY YEARS BY THIS SUBMITTER. (TC NR 20070319006) 1 L 7 2 3O 3 O A12CE E10EA 5 C P31EA 2007060400010 20070604 00010 EA 2007 6 4 CA070319008 2 20070315 G 8520 CAMSHAFT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 136 L521861A (CAN) THIS ENGINE WAS JUST PUT ON WING TO REPLACE AN ENGINE THAT HAD CAMSHAFT WEAR. DURING A ROUTINE INSPECTION THE OIL WAS DRAINED AND A SUBSTANTIAL AMOUNT OF FERROUS METAL WAS DISCOVERED IN THE FILTER. AN OIL SAMPLE WAS SENT IMMEDIATELY T O PROGRESSIVE FOR ANALYSIS. THEY REPORTED BACK THAT IT WAS THE CAMSHAFT FAILING. WE ARE SENDING THE ENGINE TO THEM FOR T EARDOWN AND WILL NOT KNOW UNTIL THEN WHETHER IT IS AN OPERATIONAL PROBLEM OR A COMPONENT PROBLEM. (TC NR 20070319008) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007060400011 20070604 00011 NM 2007 6 4 CA070319009 1 20070209 G 3297 WIRE HARNESS BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NLG WOW DAMAGED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) AFTER TAKE OFF, ALL THREE GEAR FAILED TO RETRACT. (3) RED AND (3) GREEN LIGHTS REMAINED ILLUMINATED. RAN CHECKLIS T, NO HELP. HANDLE DID ILLUMINATE AMBER. FLIGHT WAS DIVERTED BACK TO BASE. MAINTENANCE REMOVED AND REPLACED NLG WOW 2 CENTERING WIRING HARNESS. (TC NR 20070319009) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007060400012 20070604 00012 NM 2007 6 4 CA070320001 1 20070207 G 5610 80260006 WINDSHIELD BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 12216 (CAN) RT WINDSHIELD SPIDER WEBBED AT 24,000 FT CRUISE. WINDSHIELD HEAT ON. NO CAUTION LIGHTS. FLIGHT WAS DIVERTED BACK T O BASE. MAINTENANCE REPLACED RT WINDSHIELD IAW AMM 56-10-01. (TC NR 20070320001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007060400013 20070604 00013 NE 2007 6 4 CA070320002 2 20070317 G 7313 3038589 STUD CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL FUEL NOZZLE LOOSE W O OTHER O OTHER NR NOT REPORTED 1 CA 349 349 PCEPC0700 (CAN) DURING FIRST FUEL NOZZLE INSPECTION FROM OVERHAUL -9 OF 28 FUEL NOZZLE STUDS WERE REMOVED WITH NUTS ON STUDS P/N 3 038589. HAVE A CODE H19 STAMPED ON THE END -DURING A PHONE CONVERSATION WITH AN EMPLOYEE AT MFG, THEY INDICATED THAT OV ERSIZED STUDS WERE PROBABLY NOT USED AT THE OVERHAUL. MFG ACKNOWLEDGED THE PROBLEM, AND ARE INTERNALLY LOOKING INTO IT, AND PROVIDING THE PROPER HARDWARE TO BE INSTALLED. (TC NR 20070320002) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2007060400014 20070604 00014 EA 2007 6 4 CA070320003 1 20070317 G 2120 X8905 MANIFOLD CNDAIR CL600 CL6002B19 1900309 EA CABIN AIR SPLIT W O OTHER S AFFECT SYSTEMS CR CRUISE 1 CA (CAN) A/C IS UNDERGOING MODIFICATION TO FREIGHTER CONFIGURATION,AND WAS BEING TEST FLOWN FOR COLLECTING CABIN VENTILATI ON SYSTEM PRESSURES, UNDER VARIOUS OPERATIONAL CONDITIONS.THE A/C WAS CONFIGURED FOR THE TEST; SPECIFICALLY (2) TEST POR TS WERE FITTED TO THE A/C VENTILATION SYSTEM DUCTING TO MEASURE DUCT PRESSURE IN FLIGHT. THE DUCT PRESSURES WERE MEASURE D SUCCESSFULLY UNDER SEVERAL OPERATING CONDITIONS, BUT IT WAS NOTED THAT THE DISTRIBUTION MAIN FEED MANIFOLD WOULD NOT W ITHSTAND THE PRESSURE FROM THE PACK FLOW, WITH MAX CLIMB POWER APPLIED. THE FLIGHT WAS CONCLUDED AND THE A/C RETURNED UN EVENTFULLY. UPON INSPECTION OF THE SYSTEM,THE THE MAINFEED MANIFOLD WAS FOUND TO HAVE A SPLIT AT ONE OF THE JOINTS. (TC 2 L 7 2 4F RT A21EA 2007060400016 20070604 00016 EA 2007 6 4 CA070320005 1 20070319 G 7830 THRUST REVERSER CNDAIR CL600 CL600* 1900302 EA GE CF34 CF348C1 NE UNKNOWN W O OTHER J WARNING INDICATION TO TAKEOFF 1 CA (CAN) AFTER TAKEOFF AND CLIMBING THROUGH 25000 FEET, CREW RECEIVED RED THRUSTER REVERSER ICON IN THEIR N1 GAUGE. SHORTLY THEREAFTER CREW RECEIVED REVERSER STATUS MESSAGE. AFTER DISCUSSION WITH MTC, ELECTED TO RETURN TO DEPARTURE TO LOCK OUT THRUST REVERSER. THRUST REVERSER DEFERRED IAW MEL 78-30-01 WILL PROVIDE MORE INFORMATION WHEN IT BECOMES AVAILABLE. WI TH THE SUPPORT OF MFG WE HAVE CONCLUDED THAT THE CAUSE OF THE INDICATION PROBLEMS IS RELATED TO A PYLON CONNECTOR THAT I S BEING CONTAMINATED WITH MOISTURE. THE IMMEDIATE SHORT TERM FIX IS TO APPLY A WATER RESISTANCE FILLER TO THE BACK OF TH E CONNECTOR TO PREVENT WATER INGRESS. THE LONG TERM FIX IS TO REPLACE THE CONNECTOR WITH A NEW WATER TIGHT CONNECTOR. MF 2 L 7 2 4F 4 F RT A21EA EOOO63EN 2007060400017 20070604 00017 SW 2007 6 4 CA070320006 1 20070226 G 2750 19023 CONTROL CABLE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL LT WING TE DLAP FRAYED W O OTHER O OTHER NR NOT REPORTED 1 CA 535 (CAN) FLAP CABLE FOUND FRAYED AT ALLUMINUM PULLEY IN LT WING GAP AREA. (TC NR 20070320006) 1 H 7 1 3O 3 O A21CE E286 5 N P874 2007060400018 20070604 00018 CE 2007 6 4 CA070320007 1 20070316 G 3245 7008006 TUBE CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO HARTZL HCC3Y HCC3YF1 GL TIRE CRACKED W O OTHER O OTHER LD LANDING 1 CA 374 (CAN) MAINTENANCE WAS DISPATCHED AND THE WHEEL ASSEMBLY WAS REPLACED UPON INSPECTION, VALVE STEM FOUND CRACKED DUE TO EX TREME COLD. (TC NR 20070320007) 1 H 7 1 3O 3 O A16CE E5CE 5 C P25EA 2007060400019 20070604 00019 SW 2007 6 4 CA070320008 1 20070226 G 2750 19023 CONTROL CABLE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL RT WING TE FLAP FRAYED W O OTHER O OTHER NR NOT REPORTED 1 CA 535 (CAN) FLAP CABLE FOUND FRAYED AT ALLUMINUM PULLEY IN RT WING GAP AREA. (TC NR 20070320008) 1 H 7 1 3O 3 O A21CE E286 5 N P874 2007060400020 20070604 00020 2007 6 4 CA070320009 4 20070320 G 8300 9408308902 BEARING PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ACCESSORY DRIVE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 CA 477 (CAN) TRYING TO DIAGNOSE A NR 2 GENERATOR HOUSING DRAIN LINE OIL LEAK ,THE NR 2 GEN HOUSING ASSY WAS REMOVED TO REPLACE THE ENGINE ACCESSORY DRIVE SEAL WHICH WAS SUSPECT LEAKING. UPON REASSEMBLY OF NR 2 GEN HOUSING PLAY WAS NOTED ON PULLEY END OF DRIVE SHAFT. DISASSEMBLY REVEALED THAT THE OUTER BEARING P/N:940.83.08.902 OR P202PP/FS5000 HAD BEGUN TO DISINTE GRATE. THERE WERE 3 BALLS MISSING AND THE REMAINING BALLS STILL WERE CARRYING LOAD. THERE WAS ENOUGH SIDE PLAY IN THE SH AFT WHICH WOULD CAUSE THE SHAFT NOT TO RUN TRUE WHICH IN TURN CAUSED THE ENGINE ACCESSORY SEAL TO FAIL. ALL AFFECTED PAR TS REPLACED WITH NEW AND OIL LEAK IS GONE. (TC NR 20070320009) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007060400021 20070604 00021 EA 2007 6 4 CA070320010 1 20070314 G 5350 CL6002D15 RADOME CNDAIR CL600 CL600* 1900302 EA GE CF34 CF34* NE FUSELAGE BURNED W O OTHER O OTHER CR CRUISE 1 CA 4522 4522 (CAN) DURING CRUISE AIRCRAFT STRUCK BY LIGHTENING. MAINTENANCE INSPECTION FOUND SCORCH MARKS ON RADOME, ALONG CENTER EDG ES OF NLG DOORS, AND ALONG FORWARD FUSELAGE UP TO WING ROOT FAIRINGS. ALSO MINOR BURN MARK ON RT WINGLET TIP. NO DAMAGE TO ANY STATIC DISCHARGE WICKS. ADF WILL NOT POINT, ADF LOOP ANTENNA REPLACED. FUSELAGE BURN MARKS REPAIRED IAW MFG INSTR UCTIONS. WINGLET DAMAGE ALLOWABLE AS IAW MFG REO. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070320010) 2 L 7 2 4F 4 F RT A21EA E15NE 2007060400022 20070604 00022 CE 2007 6 4 CA070321001 1 20070307 G 3230 115811020651 GEARBOX BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA MLG FAILED W O OTHER O OTHER CL CLIMB 1 CA 9220 2576 (CAN) GEAR WOULD NOT COME UP WHEN SELECTED, LANDING GEAR GEARBOX REPLACED. OVERHAUL FACILITY REPORTED THAT A INTERNAL GE AR MAY HAVE BEEN SHIMMED IMPROPERLY THAT CAUSED PREMATURE WEAR (TC# 20070321001) 1 L 7 2 3T 4 T A14CE E4EA 2007060400023 20070604 00023 SO 2007 6 4 CA070321002 1 20070320 G 8120 BEARING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL TURBOCHARGER FAILED W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 2110 L147768A (CAN) RT ENGINE LOST BOOST AT ALTITUDE. PILOT ELECTED TO DESCEND TO LOWER ALTITUDE. AT LOWER ALTITUDE, RT ENGINE HAD NO RMAL POWER. APPROXIMATELY 20 MINUTES LATER, RT OIL PRESSURE WAS OBSERVED LOWER THAN NORMAL. ENGINE WAS SECURED AND SHU TDOWN. UNEVENTFUL SINGLE-ENGINE LANDING WAS CARRIED OUT. (TC NR 20070321002) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007060400024 20070604 00024 NE 2007 6 4 CA070321003 3 20070320 G 6114 S8462 BARREL HAMSTD 2D 2D30 NE PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 855 112779 (CAN) LOWER BARREL HALF FOUND WITH 5.5 INCH CRACK AT FLANGE AREA. (TC NR 20070321003) 5 C P206 2007060400025 20070604 00025 EA 2007 6 4 CA070321004 2 20070316 G 8510 CRANKCASE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1033 L11868AA (CAN) THE AIRCRAFT WAS BROUGHT INTO THE HANGAR DURING AN INTERMEDIATE STOP TO WORK ON SOME SNAGS. THE ENGINEER NOTICED A QUANTITY OF OIL ON THE OUTSIDE OF THE IB NACELLE OF THE RT ENGINE. AFTER CLEANING THE ENGINE AND RUNNING IT AGAIN A C RACK WAS NOTICED EMANATING FROM THE LOWER FORWARD STUD OF THE NR 2 CYLINDER. IT RAN FORWARD TO THE THREADED HOLE FOR TH E PROP GOVERNOR BRACE. THE CRACK WAS NDT`D AND FOUND TO ALSO BE RUNNING BACKWARDS ALONG THE CASE UNDER THE STARTER AREA . IT ALSO RAN HALFWAY UP THE EDGE OF THE CYLINDER BOSS. THE ENGINE HAS GONE FOR REPLACEMENT OF THE CASE. (TC NR 200703 21004) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007060400026 20070604 00026 EA 2007 6 4 CA070321005 1 20070228 G 2497 PA204D8 WIRE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE COCKPIT BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 26799 26799 (CAN) AFTER LANDING ELECTRICAL SHORT/ARCING BEHIND CAPTAINS SEAT IN CIRCUIT BREAKER PANEL. SOME SMOKE OBSERVED. AC TAXIE D CLEAR OF ACTIVE RUNWAY. SMOKE AND SPARKS STOPPED, AIRCRAFT TAXIED TO RAMP, PRIOR TO ARRIVAL AT GATE SPARKS RE-OCCURRED . AIRCRAFT STOPPED AND DEPLANED. MAINTENANCE INSPECTION FOUND BUSS FEEDER JUMPER WIRE DISCONNECTED AND HAD MADE CONTACT WITH BULKHEAD BEHIND CB PANEL. ARCING DAMAGE BURNED THROUGH STRINGER AND BULKHEAD SKIN. BULKHEAD BURN THROUGH APPROX 1 I NCH BY .5 INCH . (2) FEEDER WIRES BURNED INSULATION. FEEDER WIRES PA204D8 AND PA204E8 REPLACED. WIRE PA204C8 CONNECTION FOUND LOOSE AT CB 1-H2, ALL SCREWS ON BUS BAR H FROM H2 TO H13 FOUND NOT TIGHT. SB601R-34-096 (PROVISIONAL GPS INSTALLAT 2 L 7 2 4F 4 F RT A21EA E15NE 2007060400027 20070604 00027 CE 2007 6 4 CA070321006 1 20070320 G 5410 S32471 LATCH CESSNA 208 208 2073702 CE PWA PT6 PT6A114 52043 NE MCAULY 3AF34C 3GFR34C703 GL LT NACELLE LOOSE W O OTHER O OTHER CR CRUISE 1 CA 14254 (CAN) LT ENGINE UPPER COWL OPENED IN FLIGHT. AIRCRAFT LANDED WITHOUT INCIDENT. AIRCRAFT WAS FLYING THROUGH TURBULENCE WH EN THE COWL OPENED. DURING THE INSPECTION OF THE COWL, IT WAS FOUND THAT ALL 3 LATCHES WERE LOOSE. THE LATCHES WERE RE-A DJUSTED. (TC NR 20070321006) 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2007060400028 20070604 00028 NM 2007 6 4 CA070321007 1 20070320 G 3260 PSEU DHAV DHC8 DHC8103 1386005 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE MLG MALFUNCTIONED W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) DURING APPROACH TO AIRPORT, THE PILOTS SELECTED GEAR DOWN AND HAD A GEAR (UNSAFE) LIGHT BUT NO GEAR EXTENSION. ALT ERNATE EXTENSION WAS PERFORMED IAW CHECK LIST WITHOUT FURTHER REMARKS. PSEU (PROXIMITY SWITCHING ELECTRONIC UNIT) REPL ACED AS PRECAUTION. FURTHER INVESTIGATION FOUND OUT THE MAIN CAUSE OF THE EVENT WAS LOOSE WIRING/TERMINAL ON THE MLG I NHIBIT SWITCH. MFG ISSUED DASH 8 Q100/200/300 AOM 828 TO PROVIDE DETAILS OF THIS EVENT. (TC NR 20070321007) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007060400029 20070604 00029 SW 2007 6 4 CA070321008 1 20070321 G 5310 205030163395 BEAM BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE FUSELAGE CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 1231 (CAN) WEB P/N 205-030-163-395 FOUND CRACKED AT INDUCTION BAFFLE SUPPORT WL 80.13. THE CRACK WAS APPROX 1 INCH IN LENGTH AND .5 INCH DOWN . REPAIR SCHEME IN PROGRESS THROUGH MFG. (TC NR 20070321008) 1 G 7 1 4U 4 U H1SW E17EA 2007060400030 20070604 00030 EU 2007 6 4 CA070321009 3 20070305 G 6197 697070212 BUSS BAR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU PROP HUB SHORTED W E ENGINE SHUTDOWN F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) NR 2 ENGINE SHUTDOWN MANUALLY IN FLT DUE PEC FAIL CAUTION AND PROP SPEED AT 1060 RPM. FAULT CODES RT CH A/B 160 AN D 162. MAINT DISPATCHED TO T/S. FOUND BUSBAR FOR PROPELLER DEICE CHAFFING ON MPU BRACKET, CAUSING MPU TO PICKUP SENS FRO M BUSBAR. MPU ADJUSTED AND NEW BUSBAR INSTALLED. ENGINE GROUND RUNS C/O NORMAL. (TC NR 20070321009) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007061300137 20070613 00137 NE 2007 6 13 CA070321010 2 20070316 G 7321 430109817 FCU SNIAS 350 AS350D 8680803 EU LYC LTS101 LTS101600A2 41560 NE ENGINE FAILED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION DE DESCENT 1 CA 1082 (CAN) THE ENGINE FLAMED OUT WHILE THE THROTTLE WAS BEING RETARDED DURING A PRACTICE AUTOROTATION. THE POSITION OF THE TH ROTTLE AT THE TIME OF THE FLAME OUT WAS NO WHERE NEAR THE POSITION IT NORMALLY CUTS OFF THE FUEL DURING NORMAL SHUTDOWN. AFTER CONDUCTING A NORMAL AUTOROTATION, THE PILOTS RESTARTED THE ENGINE AND PERFORMED A TEST HOVER AND FLIGHT. THEY PER FORMED (3) MORE PRACTICE AUTOROTATIONS WITHOUT ANY MORE INCIDENT OR SYMPTOMS. NO FUEL LEAKS OR VISIBLE MECHANICAL ISSUE S WERE FOUND. THE FCU WAS REPLACED AS A PRECAUTION AND IS BEING SENT TO AN APPROVED FACILITY FOR BENCH TESTING. (TC NR 20070321010) 1 G 7 1 3U 3 U H9EU E5NE 2007060400031 20070604 00031 SW 2007 6 4 CA070321011 1 20070321 G 6230 206010332121 MAST BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 2213 (CAN) DURING ANNUAL INPECTION OF INTERIOR OF MAST, CORROSION AND PITTING WERE DISCOVERED. MAST WAS REMOVED AND SENT TO AN OVERHAUL FACILITY FOR REPAIR. (TC NR 20070321011) 1 G 7 1 3U 3 U H2SW E4CE 2007060400032 20070604 00032 EA 2007 6 4 CA070321012 1 20070321 G 5330 SKIN CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE FS 388 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3765 (CAN) DURING A REGULAR SCHEDULED MAINTENANCE B-CHECK, THE MAINTENANCE GUIDE CHECKLIST CALLED FOR A VISUAL INSPECTION IN ZONE 330/340 FUSELAGE TO WING AREA, BS 388-434. A SMALL 1 INCH CRACK WAS FOUND STEMMING FROM UNDERNEATH THE SHEAR PLATE AT BS 388. AFTER REMOVAL OF THE PRC, PAINT STRIPPING, AND COMPLETING A LIQUID DYE PENETRANT INSPECTION, (2) CRACKS AT S TA 388 BETWEEN WL216 AND WL210 WERE IDENTIFIED. ONE CRACK WAS APPROXIMATELY 3.5 INCH AND THE OTHER APPROXIMATELY 0.5 INC H. PICTURES AND INFORMATION SENT TO THE MFG FOR DIRECTION TO COMPLETE THIS REPAIR. (TC NR 20070321012) 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 2007060400033 20070604 00033 EA 2007 6 4 CA070321013 1 20070319 G 4930 21188002 ECU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE APU MALFUNCTIONED W O OTHER A FLAME/FIRE NR NOT REPORTED 1 CA 5330 5330 (CAN) GROUND CREW REPORTED FLAMES FROM APU EXHAUST DURING PUSHBACK. COCKPIT HAD NO FIRE INDICATIONS. CREW SHUTDOWN AND P ASSENGERS DEPLANED. MAINTENANCE INSPECTED AND APU MEL`D. LATER MAINTENANCE TROUBLESHOOTING FOUND APU ECU WITH FAULT/ERRO R CODES. APU ECU REPLACED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070321013) 2 L 7 2 4F 4 F RT A21EA E15NE 2007060400034 20070604 00034 CE 2007 6 4 CA070322001 1 20070321 G 5414 1019800013 PANEL BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL NACELLE CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 1375 1375 (CAN) PANEL IS INSTALLED ON RT IB SIDE OF NACELLE. IT COVERS THE FUEL FIREWALL SHUTOFF VALVE. THE PANEL IS MANUFACTURED WITH A BULGE TO ACCOMMODATE THE VALVE. IN THIS INSTALLATION THE VALVE CONNECTOR PLUG CHAFFED AGAINST THE PANEL CAUSING A STRESS RISER RESULTING IN A 1.5 CRACK VISIBLE FROM THE OUTSIDE OF THE PANEL. PANEL WAS REPAIRED IAW THE SRM 54-00-01. A NEW PANEL P/N 101-980001-41 WAS ORDERED. THIS ALTERNATE PANEL HAS A LARGER/DEEPER DEPRESSION TO BETTER ACCOMMODATE THE VALVE. (TC NR 20070322001) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007060400037 20070604 00037 EA 2007 6 4 CA070322004 1 20070321 G 7897 CONNECTOR CNDAIR CL600 CL600* 1900302 EA GE CF34 CF348C1 NE THRUST REVERSER DAMAGED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) ENROUTE, CREW RECEIVED RED THRUST REVERSER ICON IN THEIR N1 GAUGE. AFTER DISCUSSIONS WITH MAINTENANCE AND DISPATCH , ELECTED TO DIVERT FOR MAINTENANCE TO LOCK OUT THE THRUST REVERSER. LANDED WITHOUT INCIDENT AND MAINTENANCE CARRIED OUT THE PROCEDURE. RT THRUST REVERSER LOCKED OUT. MEL 78-30-01 APPLIED WILL PROVIDE MORE INFORMATION WHEN IT BECOMES AVAILA BLE CORRECTIVE ACTION, DATED 29 MARCH 2007: WITH THE SUPPORT OF MFG WE HAVE CONCLUDED THAT THE CAUSE OF THE INDICATION PROBLEMS IS RELATED TO A PYLON CONNECTOR THAT IS BEING CONTAMINATED WITH MOISTURE. THE IMMEDIATE SHORT TERM FIX IS TO AP PLY A WATER RESISTANCE FILLER TO THE BACK OF THE CONNECTOR TO PREVENT WATER INGRESS. THE LONG TERM FIX IS TO REPLACE THE 2 L 7 2 4F 4 F RT A21EA EOOO63EN 2007060400038 20070604 00038 2007 6 4 CA070322005 4 20070313 G 6122 8210410 GOVERNOR BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE PROPELLER MALFUNCTIONED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) AIRCRAFT DEPARTED FOR DESTINATION, WHEN THE CREW ATTEMPTED TO SET CLIMB POWER, THE RT PROP DROPPED TO 1200 RPM AND THE TORQUE WENT TO 2200 LBS. THE CREW DECLARED AN EMERGENCY AND LANDED UNEVENTLY . MAINTENANCE WENT TO SITE THE FOLL OWING DAY AND CHANGED THE RT PROPELLER, RIGGED IT AND PERFORMED GROUND RUNS .THE AIRCRAFT WAS RETURNED TO SERVICE WITH N O FURTHER PROBLEMS. (TC NR 20070322005) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2007060400039 20070604 00039 SO 2007 6 4 CA070322006 2 20070128 G 7314 64936849A1 PUMP DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA FUEL SYSTEM OUT OF ADJUST W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 69 806498 (CAN) PILOT REPORTED ENGINE STOPPED DURING POWER OFF STALL. RECORDS INDICATED (2) SID97-3C FUEL SET UP ADJUSTMENTS CARR IED OUT IN THE PREVIOUS FIVE DAYS OR 13.1 HRS PRIOR TO THE INCIDENT. SID CHECK REVEALED UNMETERED PRESSURE OUT OF LIMITS BY -1.1 PSI, LIMIT IS +/- 0.2 PSI. MECHANICAL FUEL PUMP REPLACED, PUMP OFF S/N B06LA110, NEW PUMP S/N B06LA111 INSTALL ED, FUEL INJECTORS, INLINE FILTER AND ALL FUEL LINE REMOVED CLEANED INSPECTED AND RE-INSTALLED. AIRCRAFT RELEASED CONDIT IONAL TO SATISFACTORY TEST FLIGHT AND TEST FLOWN UNSATISFACTORY. EITHER PUMP WAS UNABLE TO BE ADJUSTED TO OBTAIN LEANING SCHEDULE LIMITS OR UNABLE TO RE-ADJUST TO MEET SID SPEC AFTER TEST FLIGHT. MECHANICAL FUEL PUMP REPLACED ONCE AGAIN W 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 20081107 GL 2008 11 7 CA070322007 1 20070108 G 3245 TIRE DIAMON DA20 DA20C1 2990001 GL MLG MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) AFTER 2 FLAT TIRES WITHIN APPROX. 30 HRS. ASSOCIATED WITH A SMALL MANUFACTURE LABEL ADHERED TO THE INSIDE OF THE TIRE DURING THE MANUFACTURING PROCESS. THE GLUE OR LABEL MATERIAL WAS REACTING WITH THE TUBE AND CAUSING SMALL CRACKS A ND EVENTUALLY ALLOWING AIR TO ESCAPE. FAILURES DID NOT SEEM TO BE RELATED TO ANY PARTICULAR FLIGHT SEGMENT AS SOME WERE GOING FLAT OVERNIGHT, OTHERS WERE GOING FLAT WHILE TAXIING AND SOME SHORTLY AFTER LANDING ON ROLL OUT. SINCE THE TIRE R EPLACEMENTS TO DATE WE HAVE HAD NO RECURRENT ISSUES DUE TO THE LABEL. APPROX. 35 TIRES AND TUBES HAVE BEEN REPLACED, SOM E WERE REPLACED AS A PRECAUTION NOT NECESSARILY A FAILURE. 1 L 7 1 3O NT TA4CH 20081113 GL 2008 11 13 CA070322008 1 20070309 G 3245 500X56PLY TIRE CLEVELANDPNU 4078E DIAMON DA20 DA20C1 2990001 GL LANDING GEAR SPLIT W O OTHER O OTHER IN INSP/MAINT 1 CA (CAN) SINCE OUR PLAGUED REPORTED UNDER SDR 20070322007, WE HAVE ENCOUNTERED MORE FLAT TIRES. THIS TIME WE ARE FINDING SP LITS IN THE TUBE OUTER EDGE CENTRE LINE. NOT THE SAME PROBLEM WE WERE HAVING WITH THE MCCREARY TIRES. THE COMMONALITY IN THESE FAILURES SEEMS TO BE RELATED TO MICHELIN TUBES. WE HAVE SINCE RETURNED 5 TUBES TO MICHELIN FOR THEIR INSPECTION. A CONVERSATION WITH AN AVIALL REPRESENTATIVE WHO HAS BEEN IN CONTACT WITH MICHELIN TODAY CONFIRMS THEY HAVE RECEIVED THE TUBE AND HAVE BEGUN PRELIMINARY INSPECTION. THEY HAVE INDICATED THAT THEY ARE ALSO DEALING WITH ANOTHER CUSTOMER WITH S IMILAR PROBLEMS AND WILL GET BACK TO US WITH THE DETAILS OF THE ANALYSIS. WE HAVE SINCE PURCHASED TUBES FROM A DIFFERENT 1 L 7 1 3O NT TA4CH 2007060400040 20070604 00040 EA 2007 6 4 CA070322009 3 20070314 G 6111 TAPE SNSNCH W69EK W69EK63 EA PROPELLER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 71 AG7471 (CAN) DURING VISUAL INSPECTION, IT WAS FOUND THAT THE TAPE USED ON THE LEADING EDGE OF THIS PROP WHICH WAS INSTALLED BY THE MFG, UNDER SPEC SP-127, WAS STARTING TO BLISTER AND SEPARATE FROM THE LEADING EDGE, WORSE AT THE TIPS. TAPE WAS REMO VED AND LOG ENTRIES CARRIED OUT. NO WEIGHT AND BALANCE CHANGES AND THOUGH DISCUSSIONS WITH BOTH MFGS. THERE IS NO ILL E FFECT ON BALANCE AS LONG AS BOTH BLADE TAPES ON BOTH BLADES ARE REMOVED. COULD NOT SEEM TO ENTER THAT THIS IS A W69EK-6 3 MODEL PROP. (TC NR 20070322009) 5 N TA4CH 20081104 EA 2008 11 4 CA070322010 3 20070314 G 6110 TAPE SNSNCH W69EK W69EK63 EA PROPELLER BLISTERED W K NONE O OTHER IN INSP/MAINT 1 CA 48 (CAN) DURING VISUAL INSP, IT WAS FOUND THAT THE TAPE USED ON THE L/E OF THIS PROP WHICH WAS INSTALLED BY THE MFG UNDER S PECIFICATION SP-127 WAS STARTING TO BLISTER AND SEPERATE FROM THE L/E, WORSE AT THE TIPS. TAPE WAS REMOVED AND LOG ENTRI ES CARRIED OUT. NO WEIGHT AND BALANCE CHANGES AND THOUGH DISCUSSIONS WITH BOTH PROP MFG AND ACFT MFG, THEIR IS NO ILL EF FECT ON BALANCE AS LONG AS BOTH BLADE TAPES ON BOTH BLADES ARE REMOVED.. (TC NR 20070322010) 5 N TA4CH 2007060400041 20070604 00041 CE 2007 6 4 CA070322011 1 20070322 G 5610 35410291652 WINDOW BEECH 95 E95 1153410 CE LYC O360 IO360B1B 41514 EA HARTZL HCC2Y HCC2YK2 GL COCKPIT BROKEN W O OTHER D INFLIGHT SEPARATION CR CRUISE 1 CA (CAN) IN CRUISE FLIGHT, AT 6000 FT, THE MAJORITY OF THE LT SIDE COCKPIT WINDOW DEPARTED THE AC. THE AC BEING CLOSE TO IT S INTENDED DESTINATION CONTINUED ON AND LANDED WITHOUT INCIDENT. A FLIGHT PERMIT WAS ISSUED AND THE AIRCRAFT FLOWN TO MA IN BASE FOR EVALUATION AND REPAIR. SPEAKING WITH THE PILOT THE WINDOW DID NOT APPEAR DAMAGED OR CRACKED PRIOR TO THE EVE NT. THE SAME PILOT WHO FLEW THE SAME AIRCRAFT DAYS EARLIER MENTIONED HIS HEAD HIT THE WINDOW DURING AN ENCOUNTER WITH TU RBULENT AIR BUT DID NOT FEEL IT WAS SEVERE ENOUGH TO CAUSE DAMAGE TO THE WINDOW. THE ONLY SUBSEQUENT DAMAGE TO THE AIRCR AFT WAS A SMALL CUT IN THE LT HORIZONTAL STABILIZER DE-ICE BOOT. THE AIRCRAFT IS AN UNPRESSURIZED AIRCRAFT. (TC NR 20070 1 L 7 2 3O 3 O 3A16 1E10 5 C P920 2007060400042 20070604 00042 EU 2007 6 4 CA070323001 2 20070301 G 7240 RK47289 COMBUST CHAMBER RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU ENGINE FAILED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 2479 (CAN) PILOTS NOTICED THE LT ENGINE OPERATING APPROX. 100 POUNDS OF TORQUE LOW. UPON LANDING MAINTENANCE WAS NOTIFIED. IT WAS FOUND THAT THE NR 2 COMBUSTION CAN ASSEMBLY HAD LOST A SECTION OF ITS OUTSIDE AIR CASING. A GENERAL INSPECTION OF THE AREA GAVE NO CLUES AS TO WHY THIS HAPPENED. IAW THE MM ALL APPLICABLE INSPECTIONS WERE COMPLETED TO ENSURE THE ENGI NE WOULD BE SAFE TO CONTINUE IN SERVICE. FURTHERMORE, DUE TO A HOT SECTION INSPECTION COMING DUE ALL OTHER COMBUSTION C ANS WERE REPLACED. THE AIRCRAFT WAS RETURNED TO SERVICE WITH NO ISSUES SINCE. (TC NR 20070323001) 4 T A196 6 C P899 20081104 NM 2008 11 4 CA070323002 1 20070321 G 5280 8233101003 PUSHROD DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MLG DOOR BROKEN W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) NR 1 MLG, AFT DOOR OPEN IN FLIGHT. FOUND BOTH GEAR DOOR PUSH ROD, P/N: 8323101-003 AND SPRING, P/N: 83231020-003, BROKEN. PUSH ROD AND SPRING REPLACED. (TC NR 20070323002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007060400043 20070604 00043 NE 2007 6 4 CA070323003 2 20070321 G 7261 4115T43PO3 CARBON SEAL CNDAIR CL600 CL600* 1900302 EA GE CF34 CF34* NE NR 1 ENGINE MISSING W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 5302 (CAN) AFTER DEPARTURE AND CLIMBING THOUGH 16,000 FT, CREW RECEIVED (OIL LEVEL LOW) MESSAGE FOR NR 1 ENGINE. QUANTITY WAS 50 PERCENT AND DROPPING. AFTER DISCUSSION WITH MAINTENANCE ELECTED TO RETURN TO BASE. ANNOUNCED TO PASSENGERS THAT THE Y WERE RETURNING DUE TO OIL QUANTITY INDICATION. JUST PAST THE OUTER MARKER CREW RECEIVED RED OIL LEVEL WARNING AND SHUT DOWN NR 1 ENGINE. NO EMERGENCY WAS DECLARED AS THEY WERE SO CLOSE TO LANDING AT THIS POINT. DID A FLAP 20 LANDING WITHO UT INCIDENT AND ADVISED PASSENGERS THAT THEY DID HAVE TO SHUTDOWN ENGINE DUE OIL LEVEL. NO ADVERSE PASSENGER REACTION. FDR READOUT WAS TAKEN AND NO HEAVY LANDING INSPECTION WAS REQUIRED. EARLIER THAT DAY THE NR 1 EDP HYDRAULIC PUMP HAD BE 2 L 7 2 4F 4 F RT A21EA E15NE 2007060400044 20070604 00044 NM 2007 6 4 CA070323004 1 20070322 G 3260 387 BULB BOEING 727 727247 138408F NM MLG INDICATOR FAILED W O OTHER P NO WARNING INDICATION AP APPROACH 1 CA (CAN) AIRCRAFT ON MARCH 22, 2007 WAS ON APPROACH WHEN THE CREW EXTENDED THE LANDING GEAR FOR LANDING. WHEN THE GEAR WAS DOWN, THE CREW NOTICED THAT THE LT MAIN GEAR GREEN LOCKED LIGHT WAS NOT ILLUMINATED. THE CREW REJECTED THE LANDING AND C ONTACTED ATC FOR A NEW APPROACH LINE-UP. THE SECOND APPROACH REVEALED THE SAME RESULTS. THE CREW REMOVED AND REPLACED A FAULTY BULB AND THE AIRCRAFT LANDED WITH NO FURTHER INCIDENTS. MAINTENANCE CHECKED THE SYSTEM AND CHECKED THAT THE CORRE CT BULB WAS USED. NO FURTHER PROBLEMS. (TC NR 20070323004) 2 L 7 3 4F A3WE 2007061300138 20070613 00138 EA 2007 6 13 CA070323005 2 20070322 G 7300 CONTROLLER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA FUEL SYSTEM LEAKING W A UNSCHED LANDING K E R FLUID LOSS VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 1069 L91568A (CAN) DURING A TRAINING FLIGHT WHEN POWER WAS APPLIED, THE RT ENGINE ACCELERATED NORMALLY TO 40 INCHES AND THEN STARTED TO SURGE BETWEEN 20 AND FORTY INCHES. THE PILOT WAS ABLE TO STABILIZE THE ENGINE AT ABOUT 25 INCHES OF MANIFOLD PRESSUR E. ALL GAUGES WERE NORMAL ALTHOUGH THEY COULD NOT GAIN ANY MORE THAN 30 INCHES OF MANIFOLD PRESSURE. A LOT OF BLACK S MOKE WAS OBSERVED UNDER THE WING OF THE AIRCRAFT. AS THE AIRCRAFT LANDED, THE RIGHT ENGINE QUIT. A QUANTITY OF FUEL WAS POURING OUT THE `SNIFFLE` VALVE OF THE ENGINE. MAINTENANCE REMOVED THE DENSITY AND DIFFERENTIAL CONTROLLERS. THE DEN SITY CONTROLLER APPEARED TO HAVE AN INTERNAL LEAKAGE WHICH HAD CONTAMINATED BOTH THE DIFFERENTIAL CONTROLLER AND THE FCU 1 L 7 2 3O 3 O A20SO E14EA 2007060400045 20070604 00045 NM 2007 6 4 CA070326001 1 20070322 G 2497 WIRE HARNESS DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE CHAFED W O OTHER O OTHER NR NOT REPORTED 1 CA 13589 (CAN) AN OPERATOR HAS REPORTED FINDING SOME WIRE LOOMS THAT WE HAVE DAMAGED DUE TO CHAFING. THIS CHAFING IS OCCURRING WI TH THE CABIN FLOOR WIRE TROUGH ON AN A/C THAT IS POST MOD 8/2705, S/B 8-53-66. THE BULK OF THE CHAFING HAS BEEN OBSERVED IN THE REAR OF THE FUSELAGE WHERE THE LOOM TIE MOUNTS ARE GREATLY REDUCED. MFG IS REVIEWING WIRING INSTALLATION. (TC N R 20070326001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007060400046 20070604 00046 EU 2007 6 4 CA070326002 1 20070322 G 2741 RELAY PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TRIM SYS MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) A/C WAS CLIMBING OUT. THE PILOT MADE A MANUAL TRIM UP SELECTION WHEN A HZ STAB TRIM RUNAWAY OCCURRED. THE PILOT SE LECTED THE TRIM INTERRUPT SWITCH TO STOP THE RUNAWAY AND RETURNED. THE TRIM RELAY K 022 WAS REPLACED AND SYSTEM WAS GROU ND CHECKED SERVICEABLE AND THE A/C RETURNED TO SERVICE. NO FURTHER PROBLEMS HAVE BEEN REPORTED. (TC NR 20070326002) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007060400047 20070604 00047 CE 2007 6 4 CA070326003 1 20070214 G 5311 11543008435 FRAME BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL FUSELAGE CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) FRAME SEGMENT P/N 115-43008-35 CRACKED AT OB ENDS. AIRCRAFT IS AN EMS MACHINE. DEFECT APPEARS TO BE RELATED TO HIG H FLOOR LOADING. (TC NR 20070326003) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007060400048 20070604 00048 CE 2007 6 4 CA070327001 1 20070326 G 3010 BOOT BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL DE ICE SYSTEM ARCED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) PILOTS REPORTED THAT THE IB LEADING EDGE DEICE BOOT WAS NOT FUNCTIONING. THE DEICE SYSTEM WAS TESTED AND THE SNAG WAS CONFIRMED. WHEN THE LEADING EDGE WAS REMOVED TO CHECK THE BOOT SYSTEM EVIDENCE OF SEVERE ARCING WAS FOUND IN THE VICINITY OF THE START RELAYS. IT IS SUSPECTED THAT THE DEICE HOSE WAS ROUTED IMPROPERLY TO THE LEADING EDGE. OVER TIME THE HOSE CHAFED ON THE WIRING FROM THE RELAYS. MAINTENANCE REPLACED THE LEADING EDGE AS WELL AS ANY CONNECTORS THAT WERE DAMAGED. (TC NR 20070327001) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007060400049 20070604 00049 NM 2007 6 4 CA070327002 1 20070322 G 3810 6BS10011 DRAIN VALVE AMD FALC50 FALCON2000 2730170 NM HNYWL AS907 AS90711A 33908 WP POTABLE WATER DAMAGED W O OTHER W INADEQUATE Q C NR NOT REPORTED 1 CA 3626 3626 (CAN) THE AIRCRAFT POTABLE WATER SYSTEM WAS DAMAGED DUE TO HAVING THE WATER SYSTEM FULL OF WATER. THEN HAVING THE AIRCRA FT LEFT ON THE RAMP FOR 8 HOURS AT -14C WITH NO ADDITIONAL HEAT TO KEEP THE WATER SYSTEM FROM FREEZING. UPON ARRIVAL THE PILOTS REPORTED (WATER APPEARS TO BE LEAKING FROM THE BELLY). THE MAINTENANCE PERSONNEL INVESIGATED THE SNAG AND FOUND THE WATER SYSTEM DRAIN VALVE WAS DAMAGED DUE TO THE SEVERE FREEZING. A REMINDER TO ALL CORPORATE PILOTS TO MONITOR THE P OTABLE WATER SYSTEM AND THE OAT IN WINTER. (TC NR 20070327002) 2 K 7 2 4F 4 F RT A50NM E00010LA 2007060400050 20070604 00050 SW 2007 6 4 CA070327003 1 20070319 G 2435 230321910 FRICTION CUP BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL STARTER GEN CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 660 10481 (CAN) DURING INSPECTON STARTER-GENERATOR FRICTION CUP PLATE WAS FOUND TO BE CRACKED. NEW PART ORDERED AND INSTALLED WHEM IT ARRIVED. (TC NR 20070327003) 1 G 7 1 3U 3 U H2SW E4CE 2007060400052 20070604 00052 SO 2007 6 4 CA070327005 1 20070322 G 3260 487862 PROXIMITY SWITCH PIPER PA31 PA31325 7103105 SO LYC O540 TIO540F2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL MLG FAILED W K NONE N FALSE WARNING IN INSP/MAINT 1 CA (CAN) MAINTENANCE COULD NOT DUPLICATE FAULT ON GROUND WITH AIRCRAFT ON JACKS. CYCLED GEAR 20 TIMES FAULT FREE. WIRING C HECKED,OK, RIGGING CHECKED OK, HYDRAULIC POWER PACK CHECKED, OK. CORRECTIVE ACTION TO REPLACE ALL 6 LANDING GEAR PROXIMI TY SWITCHES. (TC NR 20070327005) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081104 EA 2008 11 4 CA070327006 2 20070323 G 7414 10391584 DISTRIBUTOR BLK BENDIX PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA HARTZL HCC3Y HCC3YR GL MAGNETO UNSERVICEABLE W D RETURN TO BLOCK R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 1130 (CAN) DISTURBER BLOCK CENTER BUSHING WAS LOOSE IN THE PLASTIC MOLDING. (TC NR 20070327006) 1 L 7 1 3O 3 O 2A13 1E10 5 C P25EA 2007060400054 20070604 00054 EA 2007 6 4 CA070327008 2 20070312 G 8500 ENGINE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL FAILED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 2145 (CAN) ENGINE FAILURE, PROP STOPPED IN FLIGHT. NO EXTERNAL DAMAGE TO ENGINE. SUSPECT CRANKSHAFT FAILURE. (TC NR 20070327 008) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007060400055 20070604 00055 SW 2007 6 4 CA070327009 1 20070313 G 6520 206040402003 GEARBOX BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 5118 (CAN) OIL LEAK. SHIPPED TO AUTHORIZED SERVICE CENTER FOR REPAIR AND RE-INSTALLATION. (TC NR 20070327009) 1 G 7 1 3U 3 U H2SW E4CE 2007060400056 20070604 00056 CE 2007 6 4 CA070327010 1 20070208 G 2730 1260505406 CONTROL CABLE CESSNA 206 U206F 2073333 CE CONT O550 IO550F 17042 SO MCAULY 3A32C D3A32C* GL ELEVATOR CUT W K NONE O OTHER IN INSP/MAINT 1 CA 2664 (CAN) A SCREW FROM THE AVIONIC EQUIPMENT LOOSENED, FELL AND LODGED BETWEEN THE PULLEY AND CABLE FOR THE ELEVATOR FLIGHT CONTROL. WITH TIME, THE CABLE WAS DAMAGED AS IT ROLLED OVER THE SCREW. (TC NR 20070327010) 1 H 7 1 3O 3 O A4CE E3SO 5 C P21EA 2007060400057 20070604 00057 EU 2007 6 4 CA070327011 1 20070327 G 3500 D2475 COUPLING SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE BLEED AIR SYS DAMAGED W E ENGINE SHUTDOWN N FALSE WARNING CR CRUISE 1 CA (CAN) IN CRUISE A BLEED AIR LEAK INDICATION WAS OBSERVED FOR THE RT ENGINE. THE ENGINE WAS SHUTDOWN AS A PRECAUTIONARY M EASURE. AN UNEVENTFUL LANDING WAS MADE. MAINTENANCE INSPECTION FOUND NO EVIDENCE OF A BLEED AIR LEAK. FURTHER INVESTIGAT ION SHOWED THAT A FIRE WIRE COUPLING WAS LOOSE IN THE RT WING. WHEN THE COUPLING WAS REMOVED IT WAS FOUND THAT A CRUSH W ASHER WAS MISSING FROM THE ASSEMBLY. THE COUPLING WAS CLEANED, INSPECTED AND REASSEMBLED CORRECTLY WITH (2) CRUSH WASHER S. AFTER INSTALLATION THE FIRE WIRE ELECTRICALLY TESTED SATISFACTORY. THE AIRCRAFT WAS SUBJECT TO FULL ENGINE RUNS AND N O BLEED AIR LEAK WAS EVIDENT. ALL COCKPIT INDICATIONS WERE NORMAL. (TC NR 20070327011) 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2007060400058 20070604 00058 2007 6 4 CA070328001 4 20070325 G 3418 350A230083 COMPUTER AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF5 NE STALL WARNING MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) FOLLOWING DEPARTURE, THE CREW OBSERVED A STICK PUSHER/ STICK SHAKER FAULT. THE AIRCRAFT RETURNED TO POINT OF DEPAR TURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE CREW ALERTING COMPUTER, SYSTEM GROUND CHECKED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070328001) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2007060400059 20070604 00059 CE 2007 6 4 CA070328002 1 20070312 G 2120 651510314 DUCT CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE CABIN AIR SYS DEBONDED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) COMPANY CAMPAIGN NOTICE 851-21-20-034 WAS CARRIED OUT. INSPECTION FOUND THE CLAMP PORTION OF THE BLEED AIR WELD AS SEMBLY LOOSE. THE WELD ASSEMBLY WAS REPAIRED BY COLD BONDING IAW INSTRUCTIONS RECEIVED FROM MFG CUSTOMER SUPPORT. UNIT R ETURNED TO SERVICE. (TC NR 20070328002) 1 L 7 2 4F 4 F A22CE E1NE 2007060400060 20070604 00060 EA 2007 6 4 CA070328003 1 20070323 G 2910 600752406 LINE CNDAIR CL601 CL6012A12 1900303 EA GE CF34 CF348E5A1 30015 NE HYD SYSTEM FAILED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 15054 15054 (CAN) DURING ROUTINE SERVICING AFTER A/C ARRIVAL, HYD FLUID WAS NOTICED LEAKING OUT OF THE BOTTOM OF THE RUDDER AND RUNN ING DOWN THE TAILCONE AND TO THE GROUND. PANELS WERE REMOVED TO LOCATE THE LEAK, FIGURING THAT THERE WAS A BAD RUDDER PC U LEAKING. WHAT WAS FOUND IT WAS THE NR 3 HYDRAULIC RETURN SYSTEM LINE P/N 600-75240-6 CHAFED THREW AT THE BOTTOM OF THE HORIZONTAL STAB REAR SPAR. 3 MONTH PREVIOUS A 15,000 HOUR INSP WAS C/O AND THE CENTER BOTTOM HINGE BEARING WAS FOUND WO RN OUT, SO THE HOLE BRACKET ASSY WAS REPLACED. TO REPLACED THIS BRACKET THE HYD LINE OF THE NR 3 RETURN SYSTEM HAD TO BE DISASSEMBLE TO GAIN ACCESS TO THE BRACKET. WHEN THE RUDDER WAS REMOVED TO DO THE REPAIR, AS THIS LINE IS ON THE REAR SP 2 L 7 2 4F 4 F RT A21AE E00063EN 20081104 CE 2008 11 4 CA070328004 1 20070327 G 7921 10656D OIL COOLER BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL LT ENGINE LEAKING W O OTHER K FLUID LOSS NR NOT REPORTED 1 CA (CAN) EXCESSIVE OIL NOTED ON LT ENGINE NACELLE. OIL LEAK TRACED TO LT ENGINE OIL COOLER. NEW OIL COOLER INSTALLED. 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 20081104 NM 2008 11 4 CA070328005 1 20070317 G 2520 VL200307A ACTUATOR BOEING BOEING 767 767333 1385301 NM PWA 4060 PW4060 52119 NE LEG REST FAILED W O OTHER O OTHER CR CRUISE 1 CA (CAN) SEAT LOCATION ON THE ACFT WAS 7F, AND FAILED IN FLIGHT. LEG REST ACTUATOR KEPT DRIVING THE FOOTREST BACKWARD, AND PUNCTURED THE REAR SPAR OF THE SEAT. THERE IS A CONCERN THAT ECU SOFTWARE 2.8 MAY BE TO BLAME, BUT INVESTIGATION IS ON G OING. THERE HAS BEEN A PREVIOUS CASE OF A BENT SPAR, PRIOR TO THIS LEVEL OF SOFTWARE, SO IT IS POSSIBLE THAT THERE IS ST ILL AN UNKNOWN FAILURE MODE THAT CAUSES THE FEEDBACK FROM THE FOOTREST POSITION TO BE LOST, AND DRIVE THE FOOTREST UNTIL FAILURE. 2 L 7 2 4F 4 F RT A1NM E24NE 2007050300001 20070503 00001 EU 2007 5 3 CA070329001 1 20070326 G 6310 350A35105901 COUPLING SNIAS SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 NE M/R DRIVESHAFT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK IN DISC LAMINATE FOUND DURING POST FLIGHT (DAILY) INSPECTION. (TC NR 20070329001) 1 G 7 1 3U 3 U H9EU E19EU 2007051100001 20070511 00001 EA 2007 5 11 CA070329002 1 20070323 G 5340 CN6272017203 BRACKET CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C1 NE HYD LINE BROKEN W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 5723 (CAN) AC EXPERIENCED A COMMANDED IFSD DUE TO OIL PRESSURE LOSS DURING CRUISE. DURING FLIGHT, PILOT NOTICED OIL PRESSURE DECREASING STEADILY DURING CRUISE. AT 36 PSI OIL PRESSURE, PILOT INITIATED A COMMANDED SHUTDOWN OF THE NR 2 ENGINE AND D IVERTED INTO BILLINGS FOR AN UNEVENTFUL SINGLE ENGINE LANDING. UPON INSPECTION OF ENGINE, MECHANICS NOTICED A STATIC OI L LEAK FROM THE BOTTOM OF GEARBOX. AFTER FURTHER INSPECTION, IT WAS NOTICED THAT THE BRACKET HOLDING THE HYD LINE TO GEA RBOX AT 6:30 ON THE AFT AGB FLANGE HAD BROKEN OFF, AND CONTACTED THE BOTTOM OF THE GEARBOX JUST ABOVE THE BRACKET LOCATI ON, HAD WORN A HOLE IN THE AGB HOUSING, RESULTING IN THE OIL LOSS. ENGINE IS BEING REMOVED AND REPLACED, ANOTHER ENGINE 2 L 7 2 4F 4 F RT A21EA EOOO63EN 2007050300002 20070503 00002 CE 2007 5 3 CA070329005 1 20070329 G 2560 110195203 BUCKLE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE SEATBELT INTERFERENCE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CONTROL YOKE INTERFERENCE WITH ROTORY SEAT BUCKLES INSPECTED IAW INTERNAL CAMPAIGN NOTICE 010-25-10-011. OPERATION OF EITHER PILOTS AND CO-PILOTS YOKES WITH SEATS FULL FORWARD CONFIRMS THAT INTERFERENCE CAN CAUSE UNLATCHING OF THE SEA TBELT ROTARY BUCKLES. (TC NR 20070329005) 1 L 7 2 4F 4 F A22CE E1NE 2007050300003 20070503 00003 SO 2007 5 3 CA070329006 2 20070313 G 8530 CYLINDER CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL NR 4 DETACHED W A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 1587 (CAN) ENGINE VIBRATION AND POWER LOSS IN FLIGHT, ENGINE CAME TO TOTAL STOP ON TAXIWAY. CYLINDER NR 4 FOUND DETACHED. ENG INE (2587.4 HOURS). ENGINE REMOVED FOR OVERHAULED. (TC NR 20070329006) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2007061300139 20070613 00139 2007 6 13 CA070329007 4 20070314 G 6122 8210004 GOVERNOR DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL PROPELLER UNSERVICEABLE W E ENGINE SHUTDOWN S AFFECT SYSTEMS TX TAXI/GRND HDL 1 CA 2862 PCE40320 (CAN) A GROUND INCIDENT OCCURRED WHERE ONE AC TAXIED INTO ANOTHER. BOTH AIRCRAFT WERE ON STRAIGHT SKIS. AFTER START-UP THE AC MOVED FORWARD FROM ITS PARKING SPOT, THEN WHEN THE PILOT MOVED THE POWER LEVER INTO REVERSE THE NR 2 PROP WENT I NTO REVERSE MOMENTARILY BUT THEN WENT INTO FORWARD PITCH WITH THE POWER LEVER STILL IN REVERSE. AS A CONSEQUENCE THE RT WING MOVED FORWARD CAUSING THE AIRCRAFT TO SWING TO THE LT AND THE AIRCRAFT ENDED UP WITH IT’S LT WING UNDER THE RT WIN G OF THE PARKED AC, IT’S LT SPINNER INTO THE RT WINDSHIELD OF THE PARKED AC, AND THE NR 1 PROP DAMAGED THE NOSE OF THE P ARKED AIRCRAFT. AFTER TEMPORARY REPAIRS WERE COMPLETED AND THE NR 1 PROP AND ENGINE WERE CHANGED ON THE AIRCRAFT THAT HA 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007050400083 20070504 00083 CE 2007 5 4 CA070329008 1 20070327 G 3250 1018100327 TORQUE KNEE BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCD4N3 HCD4N3A GL MLG WORN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 7020 7020 (CAN) WHILE TAXING BACK TO THE RAMP, THE PILOT NOTICED THAT THE STEERING WAS MORE DIFFICULT AND INEFFECTIVE. HE SHUTDOWN BOTH ENGINES AND ON INVESTIGATION FOUND THE LT LANDING GEAR TORQUE KNEE BOLT DISCONNECTED. THE CAUSE OF THE DISCONNECTI ON WAS A WORN OUT RETAINING WASHER. MAINTENANCE REPLACED THE WASHER AND RETURNED THE AIRCRAFT TO SERVICE. THIS AREA WAS RECENTLY INSPECTED. THE MM DOES NOT SPECIFY DISASSEMBLING THIS AREA TO INSPECT. THE ONLY WAY THIS COULD HAVE BEEN DETECT ED WAS BY DISASSEMBLY. OUR MAINTENANCE PROGRAM TRACKING SHEETS HAVE BEEN AMENDED TO INCLUDE DISASSEMBLY OF THE TORQUE K NEES EACH 800 HOURS. (TC NR 20070329008) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007050300004 20070503 00004 CE 2007 5 3 CA070329009 1 20070329 G 2897 WIRE BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL SHUTOFF VALVE CHAFED W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CR CRUISE 1 CA 434 (CAN) 5 AMP ANNUNCIATOR INDICATION (CB4) POPPED IN FLIGHT AND THE CREW LOST THE GREEN AND WHITE ANNUNCIATOR LIGHTS. THE CREW ATTEMPTED TO RESET THE 5 AMP CIRCUIT BREAKER, BUT COULD NOT BE RESET. PROBLEM WAS IN FOUND ON WIRE PIN D WIRE NR Q 62A20 ON THE RT FUEL SHUTOFF VALVE HAD CHAFED TO GROUND ON ONE OF THE SCREWS THAT HOLDS ON THE INSPECTION PANEL ON. DID A REPAIR ON WIRE NR Q62A20 AND THE SYSTEM WAS FUNCTION TESTED NORMAL. (TC NR 20070329009) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007050400086 20070504 00086 NE 2007 5 4 CA070330002 3 20070216 G 6114 58462 BARREL HAMSTD DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 855 112779 (CAN) PROPELLER HISTORY - AUG 28 06 TTSOH 712.8 PROPELLER REPAIRED. - JAN 19 07 TTSOH 839.6 PROPELLER FLY WEIGHT ROLLER STIFF, ROLLER LUBRICATED AND RETURNED TO SERVICE. - FEB 16 07 TTSOH 854.9 PROPELLER REMOVED FROM SERVICE AND RETURNED T O O/H SHOP FOR REPAIR, SLOW TO CHANGE PITCH. - MAR 13 07 TTSOH 854.9 PROPELLER REPAIRED BY O/H SHOP, NEW CYLINDER AND CO UNTER WEIGHT ROLLER KITS INSTALLED. - MAR 15 07 TTSOH 854.9 PROPELLER INSPECTED BEFORE INSTALLATION ON AIRCRAFT AND THE REAR PORTION OF THE PROPELLER BARREL (HUB) WAS FOUND TO BE CRACKED FROM THE BOLT BOSS 90` TO THE REAR OF THE BARREL ALON G THE OUTSIDE RADIUS. CONTINUED OPERATION OF THE UNIT IN THIS CONDITION WOULD HAVE LED TO A CATASTROPHIC FAILURE. THIS 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2007050400092 20070504 00092 WP 2007 5 4 CA070330003 1 20070329 G 2780 N547E RELAY CVAC 340 340CVAC 242270A WP ALLSN 501D 501D13D 03004 GL ALLSN A6441 A6441FN606 GL TE FLAP FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION, THE FLAPS WERE SELECTED DOWN. THEY STOPPED MOVING APPROXIMATELY HALF WAY DOWN. THE FLAP SOLENO ID CIRCUIT BREAKER WAS OBSERVED TO BE OPEN. UPON INVESTIGATION THE FLAP RELAY LOCATED IN THE GENERAL RELAY PANEL WAS FO UND TO HAVE FAILED. THE RELAY WILL BE REPLACED WITH A SERVICEABLE UNIT. (TC NR 20070330003) 2 L 7 2 4R 4 T 6A6 E282 6 C P898 2007050400094 20070504 00094 NM 2007 5 4 CA070330004 1 20070329 G 3230 LANDING GEAR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MALFUNCTIONED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 48007 48007 (CAN) DURING CRUISE CREW RECEIVED INTERMITTENT LANDING GEAR INOP CAUTION LIGHT. CREW ELECTED TO RETURN TO ORIGINATING AI RPORT. ALTERNATE GEAR EXTENSION USED TO LOWER LANDING GEAR. NORMAL LANDING. MAINTENANCE INSPECTION FOUND NO FAULTS. AI RCRAFT WILL BE RETURNED TO SERVICE SUBJECT TO A SATISFACTORY TEST FLIGHT. (TC NR 20070330004) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007050300005 20070503 00005 NE 2007 5 3 CA070330005 2 20070326 G 7261 ENGINE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE RIGHT MAKING METAL W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA 14491 6131 PS0149 (CAN) PILOTS LOADED PAX DEPARTED THE GATE. AFTER RECEIVING TAXI CLEARANCE THE PILOT NOTICED THE RIGHT LOW OIL PRESSURE W ARNING LIGHT,THE AIRCRAFT WAS TURNED AROUND AND THE ENGINE SHUTDOWN. THE AIRCRAFT RETURNED TO THE GATE AND THE PASSENGER S UNLOADED. THE AIRCRAFT WAS TOWED BACK TO THE MAINTENANCE HANGER AND INSPECTED. WHEN THE OIL FILTER WAS REMOVED THERE W AS A LARGE AMOUNT OF SILVER COLORED MAGNETIC PARTICLES IN THE FILTER. THE ENGINE HAS BEEN REMOVED AND WILL BE SENT BACK TO MFG FOR INSPECTION/OVERHAUL, (TC NR 20070330005) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2007050300008 20070503 00008 NM 2007 5 3 CA070402001 1 20070329 G 6120 666000459 CONTROL UNIT BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NR 2 PROPELLER MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) DURING LEVEL FLIGHT FL. 250, ENGINE NR 2 PROPELLER SPEED WENT TO 1051 RPM, FOLLOWED BY POWERPLANT ON ED. THIS CASE WAS TREATED AS AN OVERSPEED AND QRH CONSULTED, ENDING UP WITH ENGINE SHUTDOWN, ON NR 2 ENGINE. EMERGENCY DECLEARED AND A NORMAL DESCENT TOWARDS BASE WAS INITIATED. LANDING PERFORMED AND TAXI TO REMOTE GATE WAS DONE. MAINTENANCE ARRIVED AN D FOUND FAULT CODE 160 CH A AND B. FIM TASK 61-20-04-810-813 PERFORMED. NO CONTACT WITH MPU AND BUSS BARS. REMOVE AND RE PLACED MPU. (TC NR 20070402001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007050300010 20070503 00010 EU 2007 5 3 CA070402002 1 20070402 G 2910 7229160003 LINE SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE HYD SYSTEM CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) HYDRAULIC FLUID WAS NOTICED ROUND ACCESS PANEL 151CB RT. INVESTIGATION REVEALED A WEAR MARK AND PIN HOLE IN A HYDR AULIC LINE UNDER THE PANEL. FURTHER INVESTIGATION INDICATED THAT AN AJACENT PANEL BONDING STRAP HAD LOOPED WHEN THE PANE L WAS CLOSED AND HAD BEEN RUBBING ON THE HYDRAULIC LINE. THAT THE STRAP WOULD CHAFE ON THE HYDRAULIC LINE WAS NOT OBVIOU S WHEN THE PANEL WAS CLOSED. (TC NR 20070402002) 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2007050300019 20070503 00019 EU 2007 5 3 CA070402003 1 20070322 G 2917 973811430 PRESSURE SWITCH PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL HYD SYSTEM LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 165 (CAN) DURING INSPECTION IT WAS NOTED THAT THIS HYDRAULIC PRESSURE SWITCH WAS LEAKING FLUID AT THE SWAGED SEEM OF THE SWI TCH. THE SWITCH WAS REPLACED WITH NEW. (TC NR 20070402003) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007050300023 20070503 00023 EU 2007 5 3 CA070402004 1 20070330 G 7700 304544902 CHIP DETECTOR PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 6574 (CAN) WHEN THE CONNECTOR WAS REMOVED FROM THE CHIP DETECTOR AT INSPECTION, IT WAS NOTED THAT ONE OF THE PINS OF THE CHIP DETECTOR HAD BROKE, AND STAYED IN THE CONNECTOR. THE CHIP DETECTOR WAS REPLACED. (TC NR 20070402004) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007050300026 20070503 00026 SW 2007 5 3 CA070402006 1 20070315 G 5610 36004314SS WINDSHIELD GULSTM 690TP 690D 3970405 SW GARRTT TPE331 TPE3315 01514 WP ROTOL R306 R306382F7 GL COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 6350 (CAN) DURING A ROUTINE MEDIVAC FLIGHT AT AN ALTITUDE OF 12,000 FEET, THE FLIGHT CREW VISUALLY NOTED THAT THE RT WINDSHIE LD WAS CRACKED ACROSS THE UPPER OB CORNER. AIRCRAFT RETURNED TO BASE. INSPECTION OF THE WINDSHIELD FOUND THE OUTER WIND OW PANE CRACKED APPROXIMATELY 2.5 INCHES LENGTH ACROSS THE CORNER. NEW WINDSHIELD INSTALLED AND AIRCRAFT RETURNED TO SE RVICE. (TC NR 20070402006) 1 H 7 2 3T 4 T 2A4 E4WE 6 C P8EU 2007050300030 20070503 00030 CE 2007 5 3 CA070403001 1 20070328 G 5740 SPS8178510 BOLT BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL WING ATTACH CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 7540 (CAN) DURING A SCHEDULED NDT INSPECTION OF THE WING ATTACHMENT BOLTS THE FWD UPPER BOLT ON THE RT SIDE WAS REJECTED AFTE R THE LIQUID PENETRANT INSPECTION REVEALED A CRACK AT THE HEAD OF THE BOLT. THE BOLT HAD 7540.5 TSN. THIS INSPECTION IS DUE EVERY 1000 HRS. (TC NR 20070403001) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007050300031 20070503 00031 SW 2007 5 3 CA070403002 1 20070401 G 5610 2719442004 WINDSHIELD SWRNGN SA226 SA226AT 8780405 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCB3T HCB3TN5 GL COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA 5049 (CAN) THE FLIGHT CREW OBSERVED THE LT HEATED WINDSHEILD DELAMINATE AND CRACK DURING FLIGHT. THEY CARRIED OUT THEIR EMERG ENCY PROCEDURES AND LANDED AT THEIR POINT OF DESTINATION. MAINTENANCE REPLACED THE WINDSHEILD. NO REASON FOR THE FAILURE (IE IMPACT) COULD BE DETERMINED. THIS IS ONE OF MANY FAILURES OF THIS WINDSHEILD PN INCURRED BY THIS OPERATOR. MULTIPLE ATTEMPTS TO CONTACT THE MFG HAS RESULTED IN NO RESPONSE. (TC NR 20070403002) 2 L 7 2 4T 4 T RT A5SW E4WE 6 C P15EA 2007050300033 20070503 00033 2007 5 3 CA070403003 4 20070321 G 6122 3020094 DRIVE GEAR WOODWARD GARRTT TPE331 TPE331* 01514 WP PROPELLER GOV MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA 1754695 (CAN) CONSTANT SPEED, SINGLE ACTING PROPELLER GOVERNOR P/N 895490-10 WAS RECEIVED AT MFG WITH REPORTED PROBLEM CUSTOMER RETURNED ON IN TRANSIT B69894 AND IRR NR 5170 STATING PROP GOVERNOR HAS NO RESET PRESSURE AND SHAFT STICKS AND WILL NOT RETURN TO MINIMUM STOP. THE FAULT WAS NOT CONFIRMED BY AN EXTERNAL VISUAL INSPECTION. A (RUN AS RECEIVED) WAS PERFORMED AND THE FOLLOWING WAS NOTED: ( PUMP CAPACITY WAS 7.8 QPM, SHOULD HAVE BEEN 9.0 QPM ) RELIEF VALVE PRESSURE WAS 440 PSI, SHOULD HAVE BEEN 465 +/- 20 PSI MAGNETIC PICKUP WAS 3.2 VOLTS AT 3700 RPM, SHOULD HAVE BEE 4.5 +/- 0.2 VOLTS THE UNIT W AS SYSTEMATICALLY DISASSEMBLED IAW COMPONENT MM (CMM 33091C, 1986), AND SIGNIFICANT DAMAGE WAS FOUND TO SEVERAL INTERNAL 3 T E2WE 2007050300034 20070503 00034 SO 2007 5 3 CA070403004 1 20070331 G 3250 AN3H7A ATTACH BOLT PIPER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL STEERING ARM SHEARED W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 CA (CAN) DURING T/O ROLL DEPARTING CREW ABORTED T/O DUE A VIBRATION AND PULLING TO THE RIGHT. A/C TAXIED OFF RUNWAY, SHUTDO WN AND CREW VISUALLY INSPECTED A/C, NO DEFECTS NOTED. TAXIED BACK TO HANGER, MTCE WAS NOTIFIED. MAINTENANCE INSPECTION REVEALED (2) STEERING ARM ATTACH BOLTS SHEARED. NLG INSPECTED FOR OVER STEERAGE FROM GROUND HANDLING, NO OBSERVED DEFECT S NOTED. STEERING BOLTS REPLACED WITH NEW AND SYSTEM/TRAVEL/LANDING GEAR FUNCTION TESTS C/W . (TC NR 20070403004) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007050300035 20070503 00035 EA 2007 5 3 CA070403005 1 20070331 G 3820 060150C1 WATER HEATER CNDAIR CL601 CL6013A 8070802 EA GE CF34 CF343A 30015 NE LAVATORY ODOR W B A EMER. DESCENT UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 5057 (CAN) WHILE EN ROUTE, A BURNING ODOR WAS NOTICED BY THE CREW AND PASSENGERS. NO SMOKE WAS APPARENT IN THE CABIN OR COCK PIT. THEN SEARCHED THE LAVATORY AND BAGGAGE COMPARTMENT. A TRACE OF SMOKE WAS FOUND IN THE BAGGAGE COMPARTMENT. A QUI CK VISUAL INSPECTION OF THE LUGGAGE WAS CARRIED OUT TO SEE IF THIS WAS THE SOURCE OF THE SMOKE. IT WAS NOT. UPON EXITI NG THE LUGGAGE COMPARTMENT THE SMOKE WAS SEEN SLOWLY ADVANCING TO THE PASSENGER CABIN. CLOSED THE DOOR TO THE BAGGAGE A REA AS WELL AS TO THE LAVATORY. BRIEFED THE PASSENGERS TO NOT OPEN THE DOORS AND MOVED THEM TO THE MOST FORWARD SEATING POSITIONS. DECLARED AN EMERGENCY AND REQUESTED TO LAND. A RAPID DESCENT WAS INITIATED AND THE QRH PROCEDURE FOR SMOKE 2 L 7 2 4F 4 F RT A21EA E15NE 2007050300036 20070503 00036 CE 2007 5 3 CA070404001 1 20070325 G 5610 10138402521 WINDSHIELD BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) DURING CRUISE FLIGHT THE L/H OUTER WINDSHIELD PANE CRACKED IN SEVERAL PLACES. THE CREW CARRIED OUT THE APPLICABLE PROCEDURES AND LANDED AT THE NEAREST AIRPORT. THE WINDSHIELD WAS INSPECTED BY MAINTENANCE AND THE AIRCRAFT WAS FERRIED T O A MAINTENANCE FACILITY WHERE THE WINDSHIELD WAS REPLACED. THE AIRCRAFT WAS THEN RETURNED TO SERVICE. (TC NR 2007040400 1) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2007050300037 20070503 00037 GL 2007 5 3 CA070404002 1 20070402 G 5511 C2TP39ND RIB DHAV DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HARTZL HCB3R HCB3R304 GL HORIZONTAL STAB CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 112 (CAN) DURING MAIN SPAR REPLACEMENT AFTER COMPLETION OF SB 2/47, A SINGLE NOSE RIB WAS FOUND TO BE HEAVILY CORRODED. AIR CRAFT TT 22235.0. THE AIRCRAFT OPERATES ON FLOATS IN A CORROSIVE ENVIRONMENT. PREVIOUS CORROSION TREATMENT WAS NOT IN E VIDENCE (TC NR 20070404002) 1 H 7 1 3R 3 R RC A806 5E1 5 C P28EA 2007050300038 20070503 00038 EA 2007 5 3 CA070404003 1 20070403 G 2797 UK WIRE HARNESS CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE RUDDER POSITION DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 30222 (CAN) DURING AN INSPECTION, THE RUDDER POSITION TRANSMITTER HARNESS WAS FOUND TO BE DAMAGED. THE CAUSE OF THE DAMAGE WAS FOUND TO BE IMPROPER ROUTING BY COMPARING WITH ANOTHER A/C S/N 7163. THE ACTUAL ROUTING DRAWING WHERE REQUESTED FROM BO MBARDIER AND THE HARNESS WILL BE REPAIRED AND REROUTED PROPERLY. (TC NR 20070404003) 2 L 7 2 4F 4 F RT A21EA E15NE 2007050300040 20070503 00040 EU 2007 5 3 CA070404004 1 20070404 G 2910 AE2463774G0164 HOSE AIRBUS 310 A310304 3930339 EU GE CF6 CF680C2A5 NE HYD SYSTEM PUNCTURED W O OTHER K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) GREEN HYDRAULIC ECAM MESSAGE LOW LEVER WARNING CAME ON AFTER TAKE OFF. ON ARRIVAL, MAINTENANCE FOUND THE RT MAIN L ANDING GEAR DOWN LOCK ACTUATOR FLEX LINE HOSE LEAKING. FOUND HOLE IN FLEX LINE. FLEX LINE WAS REPLACED WITH BOTH HYDRAUL IC PUMPS, CASE DRAIN FILTERS AND GREEN SERVO CONTROL MANIFOLD FILTERS. (TC NR 20070404004) 2 L 7 2 4F 4 F RT A35EU E13NE 2007050400107 20070504 00107 NM 2007 5 4 CA070404006 1 20070329 G 2781 H1010262 SWITCH BOEING 727 727243 138408D NM PWA JT8 JT8D9A 52048 NE NR 3 KRUGER MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) ON FLAP RETRACTION THE CREW NOTICED THE NR 3 KRUGER FLAP INDICATED (IN TRANSIT). CREW RETURNED TO BASE. NR 3 KRUG ER FLAP RETRACT SWITCH WAS REPLACED AND A/C RETURNED TO SERVICE. (TC NR 20070404006) 2 L 7 3 4F 4 F RT A3WE E2EA 2007050400109 20070504 00109 SW 2007 5 4 CA070404007 1 20070404 G 2810 2060636321 FUEL CELL BELL 206 206L1 1182107 SW ALLSN 250C 250C28 03013 GL LEFT LEAKING W O OTHER K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) RETURNING FROM A FLIGHT IT WAS NOTED THERE WAS A FUEL ODOR IN THE REAR CABIN. INVESTIGATING DETERMED THE LT FWD FU EL CELL HAD A SMALL LEAK. FUEL CELL WAS CHANGED OUT. (TC NR 20070404007) 1 G 7 1 3U 3 U H2SW E1GL 2007050400112 20070504 00112 CE 2007 5 4 CA070404008 1 20070329 G 5710 97430000150 CROSS TIE BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL BS 187 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10546 (CAN) THE STRUCTURAL PIECE CALLED A CROSSTIE P/N 97-430000-150 WAS FOUND CRACKED DURING INSPECTION. IPC / REF: 53-10-20 FIG. 20 ITEM NR 26. THE CRACK IS LOCATED LT SIDE OF AIRCRAFT AT FS 187.383 AND WL 119 ( LOWER LONGERON ). REPLACED WITH NEW. (TC NR 20070404008) 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 2007050700076 20070507 00076 EA 2007 5 7 CA070404009 1 20070401 G 2740 706010 CONTROL UNIT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE HORIZONTAL STAB MALFUNCTIONED W B A EMER. DESCENT UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF, FLIGHT EXPERIENCED A HSTA RUNAWAY. ACFT HAD JUST DEPARTED RUNWAY AND FLAPS WERE RETRACTED TO 0 DEGREES. AUTOPILOT DISENGAGED. TRIM SELECTION INPUT MADE. STABILIZER TRIM CONTINUED TO RUN & ASSOCIATED AURAL ALER T SOUNDED. IMMEDIATE ACTION CHECKLIST WAS COMPLETED, AS WAS QRH PROCEDURE. MODERATE CONTROL PULL FORCES WERE REQUIRED TO FLY ACFT AT 10,000 & 250 KNOTS. CREW USED ACARS SYSTEM TO CALCULATE A WEIGHT & BALANCE, & REDISTRIBUTED CABIN LOAD T O ALLEVIATE CONTROL FORCES. ICE ENCOUNTERED AT 10,000 FT & REQUIRED DESCENT TO 8,000 FT. EMERGENCY DECLARED. ACFT RET URNED. FLAPS SELECTED TO 20 DEGREES WHILE BETWEEN 8000 & 6000 FT. CONTROL FORCES WERE SIGNIFICANTLY LIGHTER ONCE FL 2 L 7 2 4F 4 F RT A21EA E15NE 2007050400114 20070504 00114 EA 2007 5 4 CA070404010 1 20070328 G 5610 NP13932113 WINDSHIELD CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C1 NE COCKPIT FAILED W B EMER. DESCENT O OTHER CL CLIMB 1 CA (CAN) ON CLIMB OUT THROUGH 11000` PILOTS WINDSHIELD SHATTERED. REMARKS FROM PILOT (TOOK OFF CLIMBING THROUGH 11000 OR 1 2000) THE LT FRONT PILOT WINDSHIELD SPIDERWEBBED AND SHATTERED. IT SPIDERWEBBED ALL AT ONCE VERY QUICKLY. WE DECLARED AN EMERGENCY, DESCENDED TO 8000 FT AND SLOWED THE AIRCRAFT DOWN TO 190 KNOTS. COMPLETED THE QRH FOR LT WINDSHIELD HEAT. TRANSFERRED THE CONTROLS TO THE FIRST OFFICER AND PREPARED FOR AN EMERGENCY LANDING. BRIEFED THE FLIGHT ATTENDANTS AN D SENT A MESSAGE TO DISPATCH VIA ACARS. NEXT WE ADVISED OPS WE WERE RETURNING AND WERE ASSIGNED GATE. FIRST OFFICER AN D BRIEFED AN OVERWEIGHT LANDING AND COMPLETED IN RANGE AND BEFORE LANDING CHECKLIST. CONDITIONS WERE GUSTY WINDS GUSTIN 2 L 7 2 4F 4 F RT A21EA EOOO63EN 2007050400118 20070504 00118 EA 2007 5 4 CA070404011 1 20070330 G 4900 38004883 APU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE FAILED W F ACTIVATE FIRE EXT. B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 4510 (CAN) TECHNICIAN WAS TROUBLESHOOTING THE APU FOR APU AUTO SHUTDOWN, LOSS OF APU DOOR POSITION ON STATUS PAGE. ECU CODE: 109,224,91 MAINTENANCE FOUND THE ELECTRICAL CONNECTOR FOR OIL TEMP SENSOR PARTIALLY INSTALLED ( CODE 91). RESECURED TH E CONNECTOR AND PROCEEDED TO START THE APU. AT THAT TIME NO FUEL LEAK / OIL LEAK WERE NOTED IN THE APU ENCLOSURE. START THE APU WITH NO PROBLEM AND WITH BOTH A/C PACKS RUNNING, A STRONG SMELL OF FUEL IN THE COCKPIT AND GALLEY AREA WAS NOTE D. SOME FUEL ON THE GROUND AT THE DRAIN AREA WAS NOTED. SHUTDOWN THE APU, CLIMBED IN THE AFT EQUIPMENT BAY, START TO OP EN THE OIL SERVICING PANEL ONCE A FEW FASTENERS WERE LOOSE THEN A FIRE FLARED UP. ASKED THE CREW TO DISCHARGE THE ONBOAR 2 L 7 2 4F 4 F RT A21EA E15NE 2007061300141 20070613 00141 CE 2007 6 13 CA070405001 1 20070404 G 7830 LA7139A BEARING CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE THRUST REVERSER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 7285 2537 (CAN) WATER INFILTRATED BETWEEN SLEEVE P/N LA7140 AND BEARING P/N LA7139A CAUSING PIN HOLE CORROSION IN THE BEARING JAC KET, ALLOWING WATER TO COME IN CONTACT WITH THE DRIVER LINK P/N 202-0007-3 PIVOT POINT CORRODING IT BEYOND REPAIR. (TC N R 20070405001) 1 L 7 2 4F 4 F A22CE E1NE 2007080800150 20070808 00150 CE 2007 8 8 CA070405003 1 20070215 G 2720 04310031 BELLCRANK CESSNA 150 150 2071802 CE CONT O200 O200A 17020 SO SNSNCH 69CK M69CK EA RUDDER CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 10000 (CAN) FOLLOWING ITEMS FOUND INSTALLED: TRIANGLE DOUBLERS IAW SL 150-27; ANGLE STIFFENER NOT INSTALLED IAW SL 65-10. ANGL E STIFFENER MIGHT BE INSTALLED IAW PERSONAL PLANE SERVICE LTD (OTTAWA). DRAWING NR PPS.161. HAVE NOT BEEN ABLE TO FIND A COPY OF PPS 161, AT THIS TIME (MARCH 29, 2007). IF CRACKED PART IS A NON CONFORMING PART, NO FURTHER ACTION IS NEEDED. MY CONCERNS IS THIS: IF PART IS IAW PPS 161, AND NO FURTHER ACTION IS REQUIRED AFTER INSTALLATION (A VERY LONG TIME AGO) AND THEY ARE CRACKING IN SERVICE IT COULD BE QUITE SERIOUS, IN MY OPINION TO LOSE RUDDER CONTROL. THE AREA IN QUESTION IS ALSO VERY DIRTY AND HARD TO LOOK AT DUE TO OIL ACCUMULATION AND DIRT. (TC NR 20070405003) 1 H 7 1 3O 3 O NT 3A19 E252 5 N P9045 2007050400120 20070504 00120 EA 2007 5 4 CA070405005 1 20070405 G 2120 C6VF11531 FLAPPER VALVE DHAV DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA RAM AIR DUCT OBSTRUCTED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 14 (CAN) THE RAM AIR FLAPPER VALVE, P/N C6VF1153-1, BECAME JAMMED IN IT`S DUCT. ATTEMPTS BY THE PILOT TO RECTIFY THE PROBLE M BY MOVING THE CONTROL LEVER BACK AND FORTH RESULTED IN THE CONTROL CABLE, P/N 130-032A22.75B29.0, BECOMING KINKED AND UNSERVICEABLE. DIS-ASSEMBLY OF THE SYSTEM REVEALED THAT THE RUBBER-LIKE MATERIAL USED TO SEAL THE PERIMETER OF THE FLAP PER VALVE HAD BECOME DISTORTED AND ENLARGED, POSSIBLY DUE TO EXPOSURE TO HEAT. THIS CAUSED THE SEAL TO CONTACT THE INNER WALLS OF THE DUCT BEFORE THE FLAPPER WAS AT A 90-DEGREE ANGLE TO THE DUCT, IE: BEFORE THE FLAPPER WAS IN THE CLOSED POS ITION. REMOVAL AND REPLACEMENT OF THE DAMAGED CABLE AND FLAPPER VALVE REQUIRED REMOVAL AND REPLACEMENT OF MUCH OF THE A 1 H 7 2 3T 4 T RT A9EA E4EA 2007050400122 20070504 00122 EA 2007 5 4 CA070405006 1 20070405 G 3250 7116111 COLLAR DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL STEERING SYS CRACKED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) STEERING COLLAR CRACKED AT RADIUSED AREA OF ATTACH STUD TO STEERING ACTUATOR. FOUND AT ROUTINE MAINTENANCE INSPECT ION (TC NR 20070405006) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2008022100003 20080221 00003 CE 2008 2 21 CA070405007 1 20070321 G 7603 565549012 THROTTLE CONTROL CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A105 1A105* GL BROKEN W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA 4475 (CAN) PILOT REPORTED STRANGE, SPRINGY FEELING TO THROTTLE CONTROL. IT WAS DISCOVERED THAT THE OUTER PART OF THE CONTROL HAD SEPARATED WHERE IT WAS SWAGED TO THE FLEXIBLE, SPIRAL ROUND PART OF THE CONTROL. (TC NR 20070405007) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P918 2007050400123 20070504 00123 EA 2007 5 4 CA070405008 1 20070405 G 3220 713381 TORQUE LINK DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LOWER TORQUE LINK CRACKED AT ATTACHMENT LUG TO UPPER TORQUE LINK. CRACK FOUND ON ROUTINE MAINTENANCE INSPECTION (T C NR 20070405008) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007051100002 20070511 00002 EA 2007 5 11 CA070405009 1 20070403 G 2450 VS643 RELAY CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE JUNCTION BOX NR6 BURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) DURING CRUISE IB, FLIGHT CREW NOTICED AN AC ESSENTIAL BUS MESSAGE FOLLOWED BY A POPPING SOUND AND A BURNED ODOR ON THE FLT DECK. LOOKED AT AC ELECTRICAL SYNOPTIC PAGE AND EVERYTHINGS WAS NORMAL BUT THE F/A NOTICED THAT THE EMERGENCY L IGHTS WERE ON. FLIGHT CREW APPLIED QRH AND CARRIED ON FLIGHT. ON ARRIVAL AT THE GATE, BURNED ODOR WAS STRONGER AND THEY SHUTDOWN EVERYTHING INCLUDING THE APU. AFTER INVESTIGATION, MAINTENANCE FOUND AC ESSENTIAL RELAY K1XD BURNED IN JB6 AN D CARBON TRACES WERE FOUND ON THE RELAY SOCKET AND JB6 BRACKET/CASING. REF LOG NR 565535 AC ESSENTIAL SENSE RELAY K1XD P/N VS 643 AND RELAY SOCKET PN S0-1021-7127 WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070405009) 2 L 7 2 4F 4 F RT A21EA E15NE 2007050400124 20070504 00124 SO 2007 5 4 CA070405010 1 20070405 G 3220 203601042 AXLE CURTIS CURTIS C46 C46DAIRLIFT SO PWA R2800 R280051 52026 NE HAMSTD 23E 23E50 NE TAIL GEAR FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING TAXI TO RUNWAY POSITION, TAIL WHEEL AXEL FRACTURED RESULTING IN TAIL WHEEL DEPARTING TAIL GEAR ASSEMBLY. T AXI WAS AT SLOW SPEED BUT TAIL FORK DAMAGED DURING AXEL FAILURE. TAIL WHEEL FORK AND AXEL ASSEMBLY, WERE REPLACED AND A IRCRAFT RETURNED TO SERVICE. (TC NR 20070405010) 2 L 7 2 4R 4 R 3A2 5E8 6 C P603 20080520 CE 2008 5 20 CA070405011 1 20070403 G 7110 05521335 SUPPORT CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL ENGINE COWL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 48 (CAN) THE ORIGINAL PART WAS FOUND CRACKED AND WAS REPLACED LESS THAN 50 HOURS AGO. THE CRACKS ORIGINATE AT THE 4 O’CLOCK AND 8 O’CLOCK POSITIONS, AT THE END OF THE FLANGED SECTION OF THE SUPPORT. SUBMITTER SUSPECTS THAT THE PULSATING AIRFLO W FROM THE PROPELLER, WHICH IS IMMEDIATELY IN FRONT OF THIS ASSEMBLY, IS RESPONSIBLE FOR THE FATIGUE CRACKING. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007050400125 20070504 00125 NM 2007 5 4 CA070407001 1 20070404 G 5280 DOOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NLG DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 44803 44803 (CAN) MAINTENANCE CARRIED OUT A LIGHTENING STRIKE INSPECTION IAW AMM 05-50-31 AND DAMAGE WAS NOTED ON THE RT FWD NOSE GE AR DOOR, BURN AND PITTING MARKS ON BELLY FUSELAGE AND LT ELEVATOR STATIC WICK WAS BURNED OFF. NDT WAS CARRIED OUT AND T HE BELLY SKIN WAS REPAIRED IAW MFG RD8-53-9556 ISSUE 1, TEMP REPAIR FOR 1000 HRS. THE ELEVATOR TIP FAIRING FASTENERS WE RE REPLACED IAW SRM AND THE STATIC WICK WAS REPLACED AND BONDING CHECKS WERE CARRIED OUT. RT NOSE GEAR DOOR A SCREW WAS REPLACED. ALL SYSTEMS AND FLIGHT CONTROLS FUNCTION CHECKED SERVICEABLE AND THE A/C WAS RETURNED TO SERVICE. (TC NR 200 70407001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007051100101 20070511 00101 NE 2007 5 11 CA070409001 2 20070330 G 7200 ENGINE CNDAIR CL600 CL6002D24 1390016 EA GE CF34 CF348E5 30015 NE NR 1 MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 194243 (CAN) ON TAKEOFF ROLL, 1ST OFFICER NOTICE A MOMENTARY FLUCTUATION OF ABOUT 2% ON NR 1 N1 GAGE JUST AFTER THE 80 KNOTS CA LL. N1 THEN STABILIZED UNTIL REACHING JUST OVER 100 KNOTS, FLUCTUATED AGAIN. DID NOT HEAR OR FEEL ANY CHANGES IN ENGIN E. THERE WERE NO EICAS MSG AND ALL OTHER ENGINE READOUTS WERE STABLE AND NORMAL. THIS WAS POSSIBLY A ERRONEOUS N1 READ OUT, ELECTED TO CONTINUE TAKEOFF. EVERYTHING NORMAL ON CLIMB UNTIL SHORTLY AFTER ACCELERATION ALTITUDE WHEN NR 1 N1 BEG AN TO FLUCTUATE MORE SIGNIFICANTLY. COULD NOW HEAR AND FEEL NR 1 ENGINE SURGING. WITHIN SECONDS, ENGINE WENT INTO AN O VERSPEED CONDITION ACCOMPANIED BY A FADEC FAULT 1 STATUS MSG. BROUGHT THRUST LEVER TO IDLE, NO EFFECT. DECLARED AN EMER 2 L 7 2 4F 4 F RT A21EA E00063EN 2007050700176 20070507 00176 EA 2007 5 7 CA070409002 1 20070404 G 2913 R1309P216 PLUG CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE RT EDP MISSING W B EMER. DESCENT K J Y FLUID LOSS WARNING INDICATION ENGINE STOPPAGE CR CRUISE 1 CA 8717 (CAN) AFTER TAKEOFF FROM SOUTH BEND (SBN), THE AIRCRAFT CLIMBED TO FL 290. SHORTLY AFTER REACHING CRUISE ALTITUDE, THE RT ENGINE OIL PRESS WARNING ILLUMINATED FOLLOWED BY A DROP IN THE OIL PRESSURE ON THE RT OIL PRESSURE GAUGE. THE FLIGHT CREW PERFORMED THE QRH PROCEDURES AND REDUCED POWER ON THE RT ENGINE. SEEING THAT THE OIL PRESSURE CONTINUED TO DROP, TH E CAPTAIN ELECTED TO SHUTDOWN THE ENGINE. AN EMERGENCY WAS DECLARED AND AN UNEVENTFUL APPROACH AND LANDING WAS MADE AT M SP. UPON LANDING, MAINTENANCE FOUND THAT THE AIRCRAFT HAD A MEL OPENED FOR NR 2 ENGINE DRIVEN HYDRAULIC PUMP. FURTHER I NVESTIGATION REVEALED THE RT EDP HAD NOT BEEN PROPERLY MEL`D AND THAT THE OIL LOSS WAS THE RESULT OF A MISSING SPLINE PL 2 L 7 2 4F 4 F RT A21EA E15NE 2007050400126 20070504 00126 CE 2007 5 4 CA070409003 1 20070404 G 2910 25800 SELECTOR VALVE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL HYD SYSTEM LEAKING W O OTHER K FLUID LOSS DE DESCENT 1 CA 2 (CAN) VALVE WAS OVERHAULED BY VENDOR. AFTER OVERHAUL IT WAS INSTALLED IN THE AIRCRAFT. AFTER 2 HOURS OF OPERATION A LEAK DEVELOPED. THE VALVE WAS REMOVED AND DISTRIBUTION MANIFOLD DISASSEMBLED. WHEN CHECKING THE IPC IT WAS NOTED THAT AT OVE RHAUL, THE OVERHAUL FACILITY FAILED TO INSTALL 2 O-RINGS. THE O-RINGS WERE INSTALLED AND RE-ASSEMBLED, THE AIRCRAFT GEAR SWING CARRIED OUT SATISFACTORY (TC NR 20070409003) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007080800151 20070808 00151 CE 2007 8 8 CA070409004 1 20070402 G 5610 551127517 WINDOW CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE COCKPIT DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PILOT`S STORM WINDOW DELAMINATED AT UPPER EDGE, RESULTING IN A CRACK FROM ATTACH HOLE RADIUS TO AFT EDGE. (TC NR 2 0070409004) 1 L 7 2 4F 4 F A22CE E1NE 2007050400221 20070504 00221 SO 2007 5 4 CA070409005 1 20070406 G 2823 SELECTOR PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YR2 GL FUEL FAILED W D RETURN TO BLOCK Y ENGINE STOPPAGE TX TAXI/GRND HDL 1 CA (CAN) DURING FUNCTIONAL TEST PRIOR TO TAKEOFF, WHEN MOVING FUEL SELECTOR FROM OB TO IB TANKS THE ROLL PIN CONNECTING THE FUEL SELECTOR HANDLE TO THE LINKAGE FAILED. THIS FAILURE LEFT THE RT ENGINE FUEL SELECTOR IN THE OFF POSITION, STARVI NG THE ENGINE FOR FUEL. THE AIRCRAFT RETURNED TO THE RAMP FOR REPAIRS. (TC NR 20070409005) 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2008021900367 20080219 00367 CE 2008 2 19 CA070409006 1 20070405 G 3230 508103385 DRAG BRACE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL LT MLG FAILED W O OTHER Z SIGNIFICANT FAILURE REPORT TX TAXI/GRND HDL 1 CA (CAN) AC WAS DISCOVERD OUTSIDE HANGER WITH THE LT MLG COLLAPSED. THE FAULT OF THE PROBLEM WAS THE LT MLG DRAG BRACE. IT WAS REPLACED RECENTLY WHEN A SIMILIAR INCIDENT OCCURED TO THE RT MLG DRAG BRACE CAUSING THE LT MLG TO COLLAPSE WHILE BE ING TOWED. DAMAGE CAUSED FROM THIS INCIDENT WAS AS FOLLOWS, DAMAGE TO LT WING TIP, LT MLG DOORS, LT MLG ACTUATOR, VHF AN TENNA. THE AIRCRAFT WAS LIFTED AND JACKED AND A LOCALLY MFG DOWNLOCK WAS INSTALLED. THE AIRCRAFT IS IN THE PROCESS OF BE ING INSPECTED FOR OTHER DAMAGE. THIS IS ONLY A PRELIMINARY REPORT, A MORE CONCLUSIVE REPORT WILL BE ADDED WHEN FINDINGS ARE COMPLETE. (TC NR 20070409006) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007050700077 20070507 00077 WP 2007 5 7 CA070409007 2 20070228 G 7314 GEAR GARRTT TPE331 TPE33110UG 01514 WP ROTOL R333 R333482F12 GL FUEL PUMP UNKNOWN W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA P63259 (CAN) GEARS DRIVING THE FUEL PUMP FAILED CAUSING THE ENGINE TO SHUTDOWN IN FLIGHT. (TC NR 20070409007) 4 T E4WE 6 C P61GL 2007050700078 20070507 00078 NE 2007 5 7 CA070410001 2 20070408 G 7260 CASE DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE ACC GEARBOX CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 30198 10612 PW123150 (CAN) ON MARCH 28TH/07 IT WAS REPORTED AN OIL LEAK ON NR 2 ENGINE. THE OIL LEVEL WHEN DOWN 2L IN 5.55 HOURS OF FLIGHT TI ME. THE PROPELLER ASSY AND THE LT SIDE OF THE ENGINE WAS REPORTED TO HAVE BEING WASHED WITH OIL AND BOTH THEY WERE INSPE CTED FOR LEAKAGE. NO SIGNS OF DETERIORATION FOUND AT THE TIME AND IT WAS DECIDED TO DO A POWER RUN CHECK. AGAIN NO SIGNS OF LEAKAGE FOUND. ON MARCH 29TH/07 WAS REPORTED ANOTHER OIL LEAKAGE FROM NR 2 ENGINE. PERSONNEL INVESTIGATED THE PROPEL LER AND THE ENGINE AND IT WAS FOUND AN APPROXIMATE 2. (TC NR 20070410001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007050700079 20070507 00079 EU 2007 5 7 CA070410002 1 20070408 G 2750 1700637 DRIVE SHAFT EMB ERJ170 ERJ170100 EU GE CF34 CF348E5A1 30015 NE FLAP DRIVE DAMAGED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) DURING APPROACH, THERE WAS A FLAP FAIL MSG. ACFT LANDED WITH FLAPS LOCKED OUT. TROUBLESHOOTING REVEALED THAT GEAR BOX SPLINED SHAFT AND DRIVE SHAFT WERE NOT LOCKED INTO PLACE BY LOCK SCREW. SIMILAR SCENARIO OCCURRED ON RHS, WHERE THE IB MOST FLAP ACTUATOR DISCONNECTED WITH THE SPLINE IN THE SAME WAY. THE LOCKBOLT WAS IN PLACE AND SAFETIED, BUT WAS NO T INSTALLED THROUGH THE HOLE IN THE SPLINED SHAFT. ANGLED GEARBOX PN IS AS ABOVE, BUT FLAP ACTUATOR PN IS C154814-2. (TC NR 20070410002) 2 L 7 2 4F 4 F RT A56NM E00063EN 2007080800152 20070808 00152 CE 2007 8 8 CA070410003 1 20070327 G 3233 NAS464P4A29 BOLT CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO HARTZL HCJ3Y PHCJ3YF1 GL LT MLG ACTUATOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON SCHEDULED INSPECTION APPRENTICE FOUND ONE ATTACH BOLT BACKED OUT OF HOLE. ON REMOVING THE BOLT FULLY HE FOUND T HE BOLT TO BE BROKEN. THE AIRCRAFT WAS JACKED UP AND THE ACTUATOR WAS REMOVED. THE OTHER 2 ATTACH BOLTS WERE INSPECTED A ND FOUND WORN. THE ACTUATOR WAS INSPECTED FOR CRACKS. NONE FOUND. THE ATTACH BULKHEAD WAS INSPECTED ALSO. NO FAULTS WERE FOUND. THE ACTUATOR WAS REINSTALLED WITH NEW BOLTS. GEAR WAS SWUNG AND AIRCRAFT RETURNED TO SERVICE. SUSPECT THAT AS TH ERE ARE NO LOCKING DEVICES OTHER THAN TORQUE, BOLTS LOOSENED OVER TIME AND BOLT BROKE DUE TO GEAR TRANSIT FORCES. (TC NR 20070410003) 1 H 7 1 3O 3 O 3A21 E5CE 5 C P36EA 2007050700178 20070507 00178 EU 2007 5 7 CA070410004 1 20070406 G 5753 BELLCRANK PZLWAR WILGA PZL104W35A 7360104 EU LYC O540 IO540K1B5 41532 EA HARTZL HCE3Y HCE3YR1 GL TE FLAPS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 276 (CAN) LOWER LT FLAP ACTUATOR BELLCRANK SUPPORT BRACKET CRACKED AT UPPER END. WHEN FLAP IS SUBJECTED TO A SIMULATED AIR L OAD, THE SUPPORT BRACKET FLEXES AND THE CRACK VISIBLY OPENS. THIS BRACKET HAS EVIDENCE OF PREVIOUS REPAIR (A DOUBLER IS PRESENT AT THE LOWER END). NONE OF THE OTHER (3) SUPPORT BRACKETS HAVE ANY DOUBLERS OR SHOW ANY EVIDENCE OF CRACKS. (TC NR 20070410004) 1 H 7 1 3R 3 O NC EXPA1H71 1E4 5 C P33EA 2007050700180 20070507 00180 SW 2007 5 7 CA070411001 1 20070409 G 6310 209340265103 SEAL BELL 407 407 1182206 SW FREEWHEEL UNIT LEAKING W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 395 (CAN) TRANSMISSION OIL PRESSURE DROP (2) BARS BELOW THE GREEN. ON ROUTE BACK TO BASE THE TRANSMISSION OIL LOW PRESSURE LIGHT CAME ON UPON LANDING. THE ENGINE DECK IS COVERED WITH OIL. THE FREEWHEEL AFT SEAL HAD POPPED OUT OF ITS BORE, RES ULTING IN A LOSS OF OIL. (TC NR 20070411001) 1 G 7 1 3U O H2SW 2007050700080 20070507 00080 EU 2007 5 7 CA070411002 1 20070405 G 3230 A2757040500200 SWITCH AIRBUS 310 A310304 3930339 EU GE CF6 CF680C2A5 NE MLG STICKING W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) DURING CLIMB THE AIRCRAFT HAD A (KRUGER) FAULT ECAM WARNING.QAH CARRIED OUT BUT WARNING REMAINED ON. AIRCRAFT RETU RNED TO THE STATION. DURING TROUBLESHOOTING THE BITE TEST ON THE SFCC 1 AND 2 FAULTED THE RT RETRACT SWITCH. THE SWITCH WAS FOUND DIRTY AND STICKING AND TARGET WAS FOUND WORN. SWITCH WAS CLEANED AND TARGET ADJUSTED IAW MM. SYSTEM WAS TESTED SERVICEABLE. (TC NR 20070411002) 2 L 7 2 4F 4 F RT A35EU E13NE 2008022000007 20080220 00007 SW 2008 2 20 CA070411003 1 20070317 G 6320 DRIVE GEAR KAMAN K974002103 KAMAN K1200 K1200 05625F6 SW LYC T53 T5317A1LYC 41615 NE TRANSMISSION DAMAGED W E ENGINE SHUTDOWN J Z WARNING INDICATION SIGNIFICANT FAILURE REPORT IN INSP/MAINT 1 CA 7556 2748 AA1825 (CAN) DURING THE INITIAL START UP OF THE DAY, AT APPROX 10 PERCENT ROTOR RPM, AN ABNORMAL NOISE WAS HEARD COMING FROM TH E POWER TRAIN AND A TRANSMISSION CHIP WARNING LIGHT INDICATION. THE START WAS THEN ABORTED. THE ATTENDING AME INSPECTED THE TRANSMISSION SYS CHIP PLUGS AND FOUND AN ABUNDANCE OF PARTICLES OF ON THE LT SUMP CHIP PLUG. PRODUCT SUPPORT WAS CO NTACTED AND WANTED US TO REMOVE THE OIL PUMP AND THE OIL PUMP DRIVE ASSY AND INSPECT THE OIL PUMP DRIVE GEAR FOR DAMAGE. THIS INSPECTION REVEALED THE DRIVE GEAR HAD SUSTAINED SIGNIFICANT DAMAGE. THIS GEAR IS INSIDE THE TRANSMISSION MAIN HOU SING AND IS NOT FIELD REPAIRABLE ITEM. THE TRANSMISSION WAS SUBSEQUENTLY REPLACED ON LOCATION WITH TSO 0.0 UNIT INSTALLE 1 G 7 1 4F 4 U NT TR7BO E17EA 20081104 WP 2008 11 4 CA070411004 1 20070408 G 6310 V31001 SWITCH ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE CLUTCH ASSY UNSERVICEABLE W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA 507 (CAN) DURING GROUND RUN AND PRE-TAKEOFF CHECKS, THE CLUTCH FAILED TO ENGAGE. SWITCH V3-1001 IS SPRING LOADED AND BREAKS AND THE CLUTCH WILL NOT ENGAGE. THESE SWITCHES ARE A WEAK PART OF THE SYSTEM. (TC NR 20070411004) 1 G 7 1 3O 3 O H11NM 1E4 2007050700081 20070507 00081 EA 2007 5 7 CA070411005 1 20070410 G 5310 C3FS249 STRUT DHAV DHC3 DHC3 2800202 EA PWA R1340 R1340* 52016 NE HAMSTD 23D 23D40 NE WINDSCREEN CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING REPLACEMENT OF THE LT WINDSCREEN, CORROSION WAS FOUND ON THE STRUT PN C3FS2-49. AFTER REMOVAL OF SEALANT I T WAS NOTED THE STRUT WAS CORRODED COMPLETELY THROUGH ONE OF THE WALLS OF THE STRUT. RT STRUT INSPECTED AND NO FAULT F OUND (TC NR 20070411005) 1 H 7 1 3R 3 R A815 5E2 6 C P719 2007050700082 20070507 00082 2007 5 7 CA070411006 4 20070411 G 2300 52611 CONTROL PANEL DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE AUDIO CONTROL BURNED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 32513 4328 (CAN) ENROUTE CREW NOTICED SMOKE COMING FROM AUDIO CNTRL PANEL, PULLED CIRCUIT BREAKER, SMOKE STOPPED. CREW DONNED O2 MA SKS AND ELECTED TO RETURN TO ORIGINATING AIRPORT FOR NORMAL LANDING. MAINTENANCE REPLACED LT AUDIO CNTRL PANEL AND AIRCR AFT RETURNED TO SERVICE (TC NR 20070411006) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007050700083 20070507 00083 SW 2007 5 7 CA070412001 1 20070320 G 7120 206062102001 MOUNT BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON A ROUTINE ENGINE REPLACEMENT, IT WAS FOUND THAT THE LT LOWER ENGINE MOUNT WAS CRACKED AT THE ATTACH POINT. AFTE R CLOSER INSPECTION THE MOUNT WAS COMPLETELY SEPARATED FROM THE AIRFRAME. THERE WAS NO INITIAL INDICATION OF A PROBLEM. IT WAS FOUND THAT THERE WAS EXCESSIVE TORQUE ON THE ATTACH BOLT TO THE AIRFRAME. THE ATTACH POINT WAS ALSO CUPPED TO IND ICATE THAT THE PROPER PROCEDURE WAS NOT USED TO REMOVE THE ENGINE IE; LOOSENING THE ENGINE MOUNTS FIRST. (TC NR 20070412 001) 1 G 7 1 3U 3 U H2SW E4CE 20081104 EA 2008 11 4 CA070412002 1 20070411 G 3246 50105844 WHEEL CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6421 1492 (CAN) DURING ROUTINE NDT HFEC INSP OF MAIN WHEELS, ACCORDING TO ABSC NDT MANUAL PART 1, CH. 32-42-03, CRACKS WERE FOUND IN THE LOCKING RING GROOVE. THE DEPTH OF 3 CRACKS IS GREATER THAN .040 INCH AND THE LENGTH OF THE CRACKS ARE 30MM, 20MM AND 5MM. ONE CRACK HAS A DEPTH OF .020 INCH AND A LENGTH OF 20MM. COMPONENT COULD BE SENT FOR MACHINING, BUT THE DEFECT DEPTH IS ALREADY GREATER THAN THE MACHINING LIMITS. 2 L 7 2 4F 4 F RT A21EA E15NE 20081104 EA 2008 11 4 CA070412003 1 20070411 G 3246 50105844 WHEEL CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6421 1492 (CAN) DURING ROUTINE NDT HFEC INSP OF RJ MAIN WHEELS, ACCORDING TO NDT MANUAL PART 1, CH. 32-42-03, CRACKS WERE FOUND IN THE LOCKING RING GROOVE. THE DEPTH OF 3 CRACKS IS GREATER THAN .040 INCH AND THE LENGTH OF THE CRACKS ARE 30MM, 20MM AN D 5MM. ONE CRACK HAS A DEPTH OF .020 INCH AND A LENGTH OF 20MM. COMPONENT COULD BE SENT FOR MACHINING, BUT THE DEFECT DE PTH IS ALREADY GREATER THAT THE MACHINING LIMITS. 2 L 7 2 4F 4 F RT A21EA E15NE 2007050700084 20070507 00084 NE 2007 5 7 CA070412004 2 20070330 G 7323 116085023 GOVERNOR BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 2920 1160 LE07576 (CAN) DURING THE DAILY INSPECTION PERFORMED BY THE ENGINEER, THE SCREW HOLDING THE GOV SERVO LEVER PLATE IN PLACE WAS EN TIRELY BACKED OUT OF THE HOLE. THIS PART HAD BEEN REPLACED, TESTED AND ADJUSTED AT TSN 2346.3 FOR LOOSE SCREWS. THE SC REWS ARE STAKED IN PLACE AND YET WERE STILL ABLE TO BACK OUT. THE GOVENOR WAS SENT FOR REPAIR. THE SCREW MAY POISE A RIS K IN JAMMING THE SERVO LEVER. (TC NR 20070412004) 1 G 7 1 4U 4 U H1SW E17EA 2007050700085 20070507 00085 NM 2007 5 7 CA070412005 1 20070407 G 3110 B030302104C94 HOSE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU INSTRUMENT PANEL CUT W O OTHER J WARNING INDICATION CR CRUISE 1 CA 908 (CAN) CREW REPORTED THAT THE INTEGRATED STANDBY ELECTRONIC INSTRUMENT WAS NOT READING THE SAME AS THE PRIMARY FLYING DIS PLAYS. INVESTIGATION REVEALED THAT THE LINES TO THE INSTRUMENT HAVE TO BE REMOVED TO PERFORM AD CF2005-15 PART B. ON R EASSEMBLY IF THE LINES ARE NOT ORIENTED PROPERLY THAT WILL CHAFE ON STRUCTURE. (TC NR 20070412005) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007050700097 20070507 00097 EA 2007 5 7 CA070413001 1 20070407 G 7830 COWLING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE THRUST REVERSER DEPARTED W B A EMER. DESCENT UNSCHED LANDING D E INFLIGHT SEPARATION VIBRATION/BUFFET CR CRUISE 1 CA (CAN) A/C EXPERIENCED A THRUST REVERSER UNLOCK IN FLIGHT AT A CRUISE FLIGHT LEVEL OF 16000 FEET WITH AN APPROXIMATE SPEE D OF 280 KNOTS. A SMALL VIBRATION IN THE AIRFRAME WAS FELT BY THE CREW PRIOR TO RECEIVING THE (REVERSER UNLOCK) MSG, FO LLOWED BY A LOUD BANG, WITH THE AIRCRAFT PITCHING UP AND ROLLING LT.  THE CREW STOWED THE REVERSER AND VIBRATIONS SUBSEQ UENTLY STOPPED. UPON LANDING INTO ORD UNDER A DECLARED EMERGENCY, IT WAS NOTE THAT T/R TRANSLATING COWLS WERE MISSING, ALONG WITH THE STRUCTURAL DAMAGE TO THE VERTICAL AND HORIZONTAL STAB. LIST OF AFFECTED COMPONENT TO FOLLOW. (TC NR 2007 0413001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007050700098 20070507 00098 NM 2007 5 7 CA070413002 1 20070409 G 3230 69141061 CYLINDER BOEING 727 727233 138408A NM PWA JT8 JT8D15 52051 NE NLG FAILED W O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA (CAN) THE CREW OBSERVED AN A SYSTEM DEPLETION CONDITION AFTER EXTENDING THE LANDING GEAR. THE AIRCRAFT LANDED WITHOUT FU RTHER PROBLEM. MAINTENANCE FOUND THE NOSE LANDING GEAR SYSTEM TRANSFER CYLINDER HAD FAILED. THE CYLINDER HAD FAILED AT T HE LAST END CAP THREAD. THE UNIT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070413002) 2 L 7 3 4F 4 F RT A3WE E2EA 2008021900368 20080219 00368 EA 2008 2 19 CA070413003 1 20070411 G 3240 B121 PEDAL FOUND FBA FBA2C1 3640103 EA COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 147 (CAN) DURING CLEAN UP AFTER THE REPLACEMENT OF THE FUEL GAUGE ON AC 52 MECHANIC NOTICED THAT THE CO-PILOTS BRAKE-PEDAL A SSY WAS CRACKED. AFTER DISCUSSION WITH CHIEF ENGINEER HE NOTED THAT THIS WAS THE SECOND TIME, IT HAD HAPPENED PREVIOUSLY TO AC 53. FOUND MFG HAS INITIATED A MATERIAL REVIEW BOARD, A SB WILL BE MAILED OUT. THE SB WILL REQUIRE AN IMMEDIATE VI SUAL INSPECTION TO THE BRAKE PEDAL AND A VISUAL INSPECTION EVERY 100 HOURS AFTERWARDS. IF A CRACK IS FOUND OR TO TERMINA TE THE SB, A DOUBLER WILL BE INSTALLED. A TEST FIXTURE WILL BE FABRICATED TO TEST THE CRACKED BRAKE PEDAL TO FIND THE RE SIDUAL LOAD. THE FIXTURE WILL ALSO BE USED TO TEST A REPAIRED PEDAL AND A NEW DESIGN OF BRAKE PEDAL. (TC NR 20070413003) 1 H 7 1 3O NC A7EA 2007050700099 20070507 00099 EA 2007 5 7 CA070413004 1 20070410 G 6120 C6NF1117 CONTROL BOX DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL BETA SYSTEM FAILED W C ABORTED TAKEOFF F J FLT CONT AFFECTED WARNING INDICATION TO TAKEOFF 1 CA (CAN) THE AIRCRAFT WAS BEING USED FOR CREW TRAINING WHEN, ON TAKEOFF, THE RT PROPELLER RPM DROPPED TO 30 PERCENT. THE PI LOTS ABORTED THE TAKEOFF AND RETURNED TO THE RAMP. THE PILOTS NOTED THAT NP WAS STILL AT 30 PERCENT WITH THE POWER LEVER AT IDLE. THE PROPELLER WAS FEATHERED WITH THE PROP LEVER AND IT DID SO. WHEN THE PROP LEVER WAS SELECTED FULLY FWD THE PROPELLER WOULD NOT UNFEATHER. TROUBLESHOOTING REVEALED THAT THERE WAS POWER TO THE BETA BACKUP SOLENOID VALVE. FURTHER TROUBLESHOOTING LED BACK TO THE BETA BACKUP CONTROL BOX P/N C6NF1117. THIS WAS REPLACED AND THE AIRCRAFT CHECKED SERVICE ABLE. IT IS SUSPECTED THAT RELAY K4 MAY HAVE MALFUNCTIONED. THE CONTROL BOX IS BEING RETURNED TO THE OEM FOR EXAMINATIO 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081104 CE 2008 11 4 CA070416001 1 20070413 G 8011 PM2401 HOUSING LAMAR CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL STARTER CRACKED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 965 (CAN) PILOT ATTEMPTED TO START THE ACFT. ALL THAT COULD BE HEARD WAS A CLICKING NOISE. FURTHER INVESTIGATION REVEALED TH E FWD HSG WAS CRACKED CAUSING THE INCORRECT ENGAGEMENT OF THE STARTER BENDIX. STARTER WAS REPLACED AND ACFT RETURNED TO SERVICE. (TC NR 20070416001) 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2007050700101 20070507 00101 CE 2007 5 7 CA070416002 1 20070413 G 7720 3034389 PROBE BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL ENGINE T5 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 7 OUT OF 8 T5 INDICATION PROBES WERE FOUND WITH LOOSE OR BROKEN TERMINALS AND MISSING CERAMIC INSULATION. THE PRO BES APPEAR TO QUITE FRAGILE IN COMPARISON TO THE OEM PART. THE PARTS IN QUESTION ARE PMA PARTS, THEIR PN 26584. PROBES REPLACED AND AIRCRAFT RETURNED TO SERVICE (TC NR 20070416002) 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2007050700102 20070507 00102 NM 2007 5 7 CA070416003 1 20070415 G 3297 471515 WIRE HARNESS BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NLG DAMAGED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER T/O LANDING GEAR WOULD NOT RETRACT WHEN SELECTED. A/C RETURNED TO BASE FOR MAINTENANCE INSPECTION. HARNESS WOW NR 2 REPLACED IAW AMM. A/C RTS (TC NR 20070416003) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007050700105 20070507 00105 NM 2007 5 7 CA070416004 1 20070413 G 6120 699018002 CONTROL UNIT BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NR 2 PROP FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 CA (CAN) CREW COMPLETED A NR 2 ENGINE SHUTDOWN MANUALLY (IFSD) DUE POWERPLANT MESSAGE AND PEC CAUTION. MAINT ARRIVED AND FC 161 CH A AND B. FIM TASK PERFORMED. NO CONTACT WITH MPU AND BUSS BARS. REMOVED & REPLACED PEC. (TC NR 20070416004) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007050700106 20070507 00106 EA 2007 5 7 CA070416005 1 20070413 G 3297 CONNECTOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE SELECTOR VALVE CONTAMINATED W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA 14977 8924 1999 (CAN) ON APPROACH NOSE LANDING GEAR DID NOT EXTEND. CREW CARRIED OUT A GO-AROUND AND COMPLETED A MANUAL EXTENSION. THE GEAR LOWERED AND LOCKED-CREW RECEIVED 3 GREENS IN THE COCKPIT. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE WAS DISPATCHED TO TROUBLESHOOT. PSEU CODES READ AND FORWARDED TO TECH OPS. AFTER CONSULTATION WITH TECH OPS, SUSPECT THE N LG SELECTOR VALVE AT FAULT. AFTER FURTHER INSPECTION IT WAS NOTED THAT THE NLG SELECTOR VALVE HAD A SLIGHT LEAK NR THE SOLENOID CONNECTOR PLUG WAS CONTAMINATED WITH HYD FLUID. THE SELECTOR VALVE WAS REPLACED AND GEAR SWINGS WERE CARRIED O UT WITH NFF AND A/C WAS RETURNED TO SERVICE WITHOUT ANY FURTHER INCIDENTS. (TC NR 20070416005) 2 L 7 2 4F 4 F RT A21EA E15NE 2007050700107 20070507 00107 NM 2007 5 7 CA070416006 1 20070315 G 2750 C1486742003 CONTROL UNIT BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU TE FLAPS MALFUNCTIONED W A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CR CRUISE 1 CA 1613 (CAN) ENROUTE BASE, THE FLAP POWER CAUTION LIGHT ILLUMINATED. RESET WAS CARRIED OUT IAW QRH 10.11 HOWEVER ONE MINUTE LAT ER THE CAUTION LIGHT RE-ILLUMINATED. IAW THE QRH FLAPS RENDERED UNAVAILABLE FOR LANDING. FLAPLESS LANDING WAS CARRIED O UT WITHOUT INCIDENT. ENGINEERING INVESTIGATION REVEALED FAILURE OF THE FLAP CONTROL UNIT. UNIT REPLACED AND TESTED IAW M AINTENANCE MANUAL REQUIREMENTS. AIRCRAFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. AS DEFECT CONFIRMED WITH REPLACEM ENT OF THE FCU. (TC NR 20070416006) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007050700108 20070507 00108 SO 2007 5 7 CA070416007 1 20070416 G 2910 OAS229307 POWERPACK PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL HYD SYSTEM FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1091 317552010 (CAN) DURING A MAINTENANCE RUN AFTER WORK ON AN ENGINE THE MECHANICS DID A HYDRAULIC PUMP CHECK BY SELECTING HANDLE TO G EAR DOWN POSITION. THE HANDLE WOULD NOT RETURN TO THE NEUTRAL POSITION AS IS NORMAL. WHEN GEAR SWINGS WERE CARRIED OUT IN THE HANGAR THE OB GEAR DOORS WOULD ONLY PROCEED HALFWAY AND THEN SIT AND SHUDDER. A LOUD BANG WAS HEARD FROM THE PO WERPAK AND THEN THE DOORS WOULD CLOSE OR OPEN AS SELECTED. THERE WAS NO PRIOR INDICATION OF PROBLEMS WITH THE POWERPACK . (TC NR 20070416007) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007050700109 20070507 00109 2007 5 7 CA070416008 4 20070324 G 3460 101741111 COMPUTER DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE FMS MALFUNCTIONED W A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 CA 534 (CAN) CREW REPORTED FMS FAILED THEN FLIGHT DECK EXPERIENCED SMOKE AND FUMES. CREW ELECTED TO RETURN THE AIRCRAFT TO BASE WHERE A LANDING WAS CARRIED OUT WITHOUT INCIDENT. ENGINEERING REPLACED THE FMS UNIT. INITIAL INVESTIGATION OF THE REMO VED UNIT INDICATES AN ELECTRICAL FAILURE OF AN INTERNAL CIRCUIT BOARD. UNIT HAS BEEN RETURNED TO THE MFG FOR REPAIR AND WITH A REQUEST TO PROVIDE A STRIP REPORT. (TC NR 20070416008) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007050700110 20070507 00110 NM 2007 5 7 CA070416009 1 20070327 G 2421 31708001A GENERATOR DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE NR 2 AC SYSTEM MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) ON INITIAL CLIMB AFTER TAKEOFF THE AC GENERATOR `HOT` CAUTION LIGHT ILLUMINATED. CREW ELECTED TO RETURN THE AIRCRA FT TO BASE WHERE AN APPROACH AND LANDING WAS CARRIED OUT WITHOUT INCIDENT. ENGINEERING REPLACED THE AC GENERATOR AND RET URNED THE AIRCRAFT TO SERVICE. (TC NR 20070416009) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007061500189 20070615 00189 SW 2007 6 15 CA070417001 1 20070412 G 3242 A032 VALVE PARAMOUNT SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP MASTER CYLINDER STUCK W O OTHER S AFFECT SYSTEMS LD LANDING 1 CA 5282 13026 (CAN) THE AC RT MLG TIRES WERE BLOWN UPON LANDING. DURING INSPECTION IT WAS FOUND THAT THE RT BRAKE ASSY WERE DRAGGING A ND OVERHEATED CAUSING THE WHEELS NOT TO TURN FREELY UPON TOUCHDOWN. TIRES, BRAKES AND AFFECTED BRAKE MASTER CYLINDERS W ERE REPLACED. AN INITIAL TEARDOWN OF THE MASTER CYLINDERS INDICATED THAT THE CAPTAIN`S RT CYLINDER WAS AT FAULT DUE TO M ALFUNCTIONS OF INTERNAL COMPONENTS. AD 2002-08-01 DEALS WITH A SPECIFIC FAILURE MODE OF THESE MASTER CYLINDERS AND HAVE A OVERHAUL LIMIT OF 15000 HRS TIS. THESE MASTER CYLINDERS HAD 5282.00 HRS TT SINCE OVERHAUL. FURTHER INVESTIGATION REVE ALED THAT THE COTTER PIN (AN380-2C2) WHICH HOLDS THE VALVE IN THE MASTER CYLINDER TO THE ACTUATING ARM WAS BENT NOT ALLO 2 L 7 2 4T 4 T RT A8SW E4WE 2007051100003 20070511 00003 EA 2007 5 11 CA070417002 1 20070417 G 5751 2151500080680 RIB CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE AILERON DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DAMAGE FOUND TO BOTH AILERONS ON THE (2) FIRST CENTER HINGE RIBS ASSEMBLY, ADJACENT TO THE FIXED STOPS. A/C HOURS ; 4658.7, CYCLES; 2973 (TC NR 20070417002) 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 20081104 EU 2008 11 4 CA070417003 1 20070409 G 3240 RFS1010 DISK BAG JETSTM JETSTM3101 1500215 EU MLG BRAKE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DISC WAS FOUND BROKEN IN HALF. NEW BRAKE UNIT INSTALLED. 2 L 7 2 4T RT A21EU 2007050700125 20070507 00125 GL 2007 5 7 CA070418001 1 20070416 G 3810 4E32612 POTABLE WATER BOMBDR BD700 BD7001A10 1390006 GL RROYCE BR700 BR700710A220 09500 NE GALLEY LEAKING W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 422 (CAN) FOLLOWING THE ADVISORY WIRE FROM MFG, THE WATER SYSTEM VENT VALVES (6) WHERE REPLACED IN MFG. ON THE NEXT CUSTOMER FLIGHT, ONE VENT VALVE FROM THE GALLEY HAS STARTED TO LEAK. END RESULT, AVIONICS BAY FLOODED, BLACK BOXES FULL OF WATER . INVESTIGATION SHOWED THAT THE 2 VALVES ARE ACTING REVERSE. AS A TEMPORARY MEASURE, MFG DRAWING NR BAS67038670 INCORPOR ATED. (REMOVED VENT VALVES AND INSTALLED PLUGS) (TC NR 20070418001) 2 L 7 2 4F 4 F RT T00003NY E00061EN 20081104 EA 2008 11 4 CA070418002 1 20070227 G 3240 0860162001 ACCUMULATOR DHAV DHC8 DHC8311 1386006 EA PARKING BRAKE CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 33458 21048 (CAN) WHILE PERFORMING AN LPI ON THE LANDING GEAR (PARKING BRAKE ACCUMULATOR), (3) AXIAL CRACKS WERE FOUND IN THE BOTTOM PORTION OF THE INSPECTION AREA. THIS INSPECTION WAS IN SUPPORT OF SB A8-32-162. THE CRACKS EXTEND OUTSIDE THE TAPERED S ECTION AND ARE .75, .50, AND .25 IN LENGTH. RETURNED TO STORES FOR REPAIR. 2 H 7 2 4T RT A13NM 20081104 SW 2008 11 4 CA070418003 1 20070321 G 7120 205060105001 MOUNT BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 91 (CAN) ENGINE MOUNT WAS INSTALLED NEW IAW STC SH99-11. POWER PLANT WAS ALIGNED IAW MM SUPPLEMENT. THE MM SUPPLEMENT INCL UDES AN INSP EVERY 100 HRS OR ANNUALLY. NOTE TO INSPECT ENGINE MOUNTS FOR CRACKS, DAMAGE, CORROSION AND SECURITY. THE CR ACK STARTED BELOW THE MOUNT BETWEEN THE WELDS AND MOVES INWARD. ACFT WAS CHECKED FOR VIBRATION AND ALIGNMENT NO DEFECTS NOTED. 1 G 7 1 4U 4 U H1SW E17EA 20081104 EA 2008 11 4 CA070418004 1 20070301 G 3240 0860162001 ACCUMULATOR DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE PARKING BRAKE CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA 34933 5783 (CAN) WHILE PERFORMING AN LPI INSPECTION ON THE LANDING GEAR (PARK BRAKE ACCUMULATOR) IAW SB A8-32-162 A .015 CORROSION PIT WAS FOUND IN THE RADIUS OF THE TOP CAP,BETWEEN THE TAPERED SECTION AND THE SHAFT OF THE CAP. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007050700129 20070507 00129 2007 5 7 CA070418005 4 20070416 G 3497 M227591622 WIRE DOUG DC3 DC3C 3021457 WP PWA PT6 PT6A67R 52043 NE HAMSTD 23E 23E50 NE AIRSPEED WARNING ARCED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) THE AIRSPEED AURAL WARNING CIRCUIT BREAKER WAS FOUND TO BE (POPPED). WHEN THE UPPER PANEL WAS LOWERED EVIDENCE OF ARCING WAS FOUND ON AIRFRAME STRUCTURE. THE WIRE WAS REPAIRED THROUGH PARTIAL REPLACEMENT, CHAFE PROTECTOR WAS ADDED T O THE AIRFRAME STRUCTURE AND THE WIRE BUNDLE AND THE WIRE BUNDLE WAS RE-POSITIONED. (TC NR 20070418005) 2 L 7 2 4R 4 T A669 E26NE 6 C P603 2007050700130 20070507 00130 NE 2007 5 7 CA070418006 2 20070322 G 8530 CH90ER CYLINDER HEAD PWA R985 R985AN14B 52008 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 586 (CAN) ON 100 HR INSPECTION DURING A DIFFERENTIAL CHECK CYLINDER WAS READING LOW. USING A SOAP SOLUTION IT WAS DETERMINED THAT THERE WAS A LEAK ACROSS THE HEAD DUE TO A CRACK BETWEEN THE COOLING FINS. (TC NR 20070418006) 3 R 5E1 2007050700133 20070507 00133 GL 2007 5 7 CA070418007 1 20070417 G 5341 VALTB12091 FITTING DHAV DHC1 DHC1 2801702 GL PWA R985 R985AN14B 52008 NE HARTZL HCB3R HCB3R304 GL WING TO BODY CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA 6052 (CAN) A CURSORY INSPECTION REVEALED CORROSION ON THE LT PORK CHOP FITTING. BOTH LT AND RT FITTINGS WERE REPLACED WITH NE W UNITS. DEPTH OF CORROSION WAS APPROX 25 PERCENT OF PART OVERALL THICKNESS. THE MANUFACTURE WAS CONTACTED. THE PART IN QUESTION IS APPROX 11 YEARS OLD. (TC NR 20070418007) 1 L 7 1 3O 3 R EXPA1L71 5E1 5 C P28EA 2007080800153 20070808 00153 2007 8 8 CA070419001 4 20070418 G 3197 WIRE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE NR 1 FEEDER CHAFED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA (CAN) DURING AN ATTEMPT TO RUN THE AIRCRAFT TO FUNCTION CHECK THE WINDSHIELD ANTI-ICE BLEED AIR (SNAG-NO BLEED AIR TO TH E WINDSHIELD FOR ANTI-ICE UNTIL WINDSHIELD ANTI-ICE CB IS PULLED). WHEN THE BATTERY SWITCH WAS TURNED ON THE LT CB PANEL 35 AMP CIRCUIT BREAKER (LOCATED ON THE RT HAND CB PANEL) POPPED. IT WAS DISCOVERED THAT THE NR 1 FEEDER WIRE (P10A6) F OR THE LT BUSS, THE INSULATION HAD ABRADED THROUGH AND MADE CONTACT WITH A SCREW ON THE BACK OF THE DE-ICE PANEL ASSY. THIS WAS THE DIRECT CAUSE OF THE ABOVE MENTIONED 35AMP CIRCUIT BREAKER POPPING. WHEN THIS DE-ICE SIDE CONSOLE PANEL ASS Y IS INSTALLED. (3) 6 GAUGE WIRES (ALL LT BUS FEED WIRES P10A6, P11A6 AND P12A6) ARE ROUTED IN BEHIND THIS PANEL. THE F 1 L 7 2 4F 4 F A22CE E1NE 2007050700136 20070507 00136 EA 2007 5 7 CA070419002 2 20070413 G 7230 BLADES PWC BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL COMPRESSOR DEPARTED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA 4538 PCE51225 (CAN) LT ENGINE EXPERIENCED A SUDDEN POWER LOSS ON CLIMB OUT. THE ENGINE WAS SHUTDOWN AND THE A/C RETURNED TO BASE WITHO UT ANY FURTHER INCIDENT. THE POWER SECTION WAS REMOVED FOR INVESTIGATION. THE INVESTIGATION REVEALED THAT PIECES WERE MISSING FROM SEVERAL CT IGV`S, MULITPLE CT BLADES BEING DAMAGED (IE. MISSING PIECES) AS WELL AS DAMAGE TO SEVERAL PT BLA DES AND GUIDE VANES. THE ENGINE HAS 4538.3 HRS AND 4622 CYCLES SINCE O/H AND IS ON CONDITION FOR HOT SECTION INSPECTIONS . THE LAST HSI WAS COMPLETED 2068.6 HRS AND 2695 CYCLES AGO WHEN 0.0 TSO CT BLADES P/N 3039901 WERE RE-INSTALLED. THE E NGINE HAS BEEN SENT FOR O/H AND FURTHER INFO WILL BE AVAILABLE AFTER WHEN A TEARDOWN REPORT BECOMES AVAILABLE (TC# 20070 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007050700137 20070507 00137 CE 2007 5 7 CA070419003 1 20070418 G 5540 1145240253 TORQUE SHAFT BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE RUDDER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 15917 (CAN) DURING A PHASE INSPECTION IT WAS DISCOVERED THAT THE RUDDER TORQUE SHAFT WAS CORRODED. IT IS BELIEVED THAT THE COR ROSION OCCURRED DUE TO WATER MIGRATION FROM THE VERTICAL STABILIZER. THE TORQUE SHAFT WAS REPLACED. (TC NR 20070419003) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2007050700138 20070507 00138 SW 2007 5 7 CA070419004 1 20070419 G 6520 476206297 BEARING BELL 47 47G2 1181008 SW LYC O435 VO435A1D 41516 EA TAIL ROTOR GB MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA 3111 685 (CAN) DURING ROUTINE 100 HR INSPECTION THE OIL WAS FOUND TO BE DARKER IN COLOR THAN NORMAL, AFTER CLOSER INSPECTION AND CHECKING FOR STEEL WITH A MAGNET THE DARKNESS IN COLOR WAS ATTRIBUTED TO METAL CONTAMINATION IN THE OIL SO FINE THAT IT LOOKED LIKE METALLIC PAINT. THE GEARBOX IS IN FOR TEARDOWN AND WILL ADVISE THE FINDINGS AFTER INSPECTION. (TC NR 200704 19004) 1 G 7 1 3O 3 O H1 E279 2007080800154 20070808 00154 CE 2007 8 8 CA070419005 1 20070412 G 5540 05310181 BRACKET CESSNA 172 172D 2072410 CE LYC O360 O360A1A 41514 EA HARTZL HCC2Y HCC2YK1 GL RUDDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3717 (CAN) DURING THE ANNUAL INSPECTION, BOTH RUDDER HINGE BRACKETS WERE FOUND TO BE CRACKED. RUDDER WAS REMOVED AND REINSTA LLED AFTER REPAIRS. PN 0531018-1 AND 0531018-2 WERE REPLACED WITH NEW IAW THE MM. (TC NR 20070419005) 1 H 7 1 3O 3 O NT 3A12 E286 5 C P920 2007050700140 20070507 00140 NE 2007 5 7 CA070420001 2 20070419 G 8530 153084 CYLINDER DOUG DC4 DC4 3021502 WP PWA R2000 R20007M2 52023 NE NR 4 ENGINE CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) REPLACED NR 14 CYLINDER ON NR 4 ENGINE, DUE TO CRACK. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070420001) 2 L 7 4 4R 4 R A762 5E5 2007050700142 20070507 00142 EA 2007 5 7 CA070420002 2 20070417 G 8520 SL12596 BOLT LYC O540 LTIO540J2BD 41533 EA CONNECTING ROD FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA 671 (CAN) BOLT FAILED CAUSING CONNECTING ROD TO BECAME DETACHED FROM CRANKSHAFT CAUSING MAJOR DAMAGE TO LOWER END OF ENGINE. (TC NR 20070420002) 3 O E14EA 2007050700143 20070507 00143 EA 2007 5 7 CA070420003 1 20070418 G 5220 DOOR DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE EMERGENCY EXIT STIFF W K NONE O OTHER IN INSP/MAINT 1 CA 34704 34704 (CAN) ON GROUND, WHEN FLIGHT ATTENDANTS UNDERGOING RECURRENT TRAINING ATTEMPTED TO OPEN FWD RT EMERG EXIT DOOR, WERE UNA BLE TO GET DOOR OPEN. MAINTENANCE CALLED TO ASSIST AND REQUIRED TWO ENGINEERS (ONE ON INSIDE HANDLE AND ONE ON OUTSIDE H ANDLE) TO GET DOOR OPEN . MAINTENANCE INSPECTED AND LUBRICATED INTERNAL DOOR MECHANISM, DOOR RE-INSTALLED AND FUNCTIONED WITH NORMAL OPENING FORCE. (TC NR 20070420003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007050700193 20070507 00193 EU 2007 5 7 CA070423001 1 20070420 G 6220 601741 BEARING BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL MAIN ROTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING PERFORMANCE OF A 100/300 HOUR INSPECTION OF THE AIRCRAFT AND IN PARTICULAR THE MAIN ROTOR BLADES. THE ENGI NEER FOUND THAT THE PENDULUM ABSORBER OF THE RED MAIN ROTOR BLADE WAS EXTREMELY ROUGH. UPON DISASSEMBLY OF THE PENDU LUM ABSORBER IT WAS FOUND THAT THE BEARINGS WERE DRY, WITH NO TRACE OF OIL PRESENT. ONE BEARING CAGE HAD FAILED, AND TH E BALL BEARINGS HAD WORN TO WELL BEYOND ANY CIRCULAR SHAPE. JUST A NOTE TO SAY THAT THERE HAD BEEN NO TRACE OF OIL ON T HE HEAD IN PREVIOUS INSPECTIONS TO INDICATE A LEAK. ONE BEARING AND SEAL WERE REPLACE, THE ASSEMBLY REASSEMBLED AND INSTALLED ONTO THE ROTOR BLADE. AIRCRAFT RETURNED TO SERVICE UPON COMPLETION OF THE INSPECTION. (TC NR 20070423001) 1 G 7 2 3U 3 U H3EU E4CE 2007050700194 20070507 00194 EA 2007 5 7 CA070423002 2 20070423 G 8530 LW12427 CYLINDER BEECH 23 C23 1151242 CE LYC O360 O360A4K 41514 EA SNSNCH 76E 76EM8S5 EA ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1397 (CAN) CRACK FOUND IN CYLINDER. (TC NR 20070423002) 1 L 7 1 3O 3 O A1CE E286 5 N P4EA 2007071100290 20070711 00290 NE 2007 7 11 CA070423004 2 20070421 G 7297 6015091017 WIRE HARNESS CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE RT ENGINE CHAFED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CL CLIMB 1 CA (CAN) SHORTLY AFTER T/O, THE RT ENGINE VIBRATION INDICATOR FLUCTUATED ERRATICALLY THE WENT TO DASHES MOMENTARILY THEN RE TURNED TO NORMAL OPERATION. FLIGHT RETURNED FOR MAINTENANCE TROUBLESHOOTING. AFTER CHANGING THE ENGINE ACCELEROMETER A ND SIGNAL CONDITIONER WITH NO FIX, THE ENGINE VIBRATION HARNESS SHIELDED WIRE WAS FOUND CHAFFING AGAINST ENGINE CLOSE TO THE ENGINE DISCONNECT PLUG. THE VIBRATION HARNESS WAS REPLACED AND THE AIRCRAFT WAS FUNCTION CHECKED SERVICEABLE. (TC NR 20070423004) 2 L 7 2 4F 4 F RT A21EA E15NE 2007050800197 20070508 00197 EA 2007 5 8 CA070423005 2 20070419 G 8530 LW12966 CYLINDER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1702 RL145668A (CAN) OIL WAS NOTICED LEAKING FROM THE PUSHROD AREA. THE PUSHROD WAS REMOVED TO REPLACE THE SEALS. THE CRACK IN THE CY LINDER HEAD WAS FOUND THEN. THE CRACK RAN FROM THE BOTTOM OF THE CYLINDER HEAD SEAM TO ABOUT 4-5 INCHES ALONG THE HOLLO W WHERE THE PUSHROD TUBE RESIDES. THE CYLINDERS WERE MANUFACTURED NEW STEEL AT OVERHAUL. (TC NR 20070423005) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007080800155 20070808 00155 CE 2007 8 8 CA070423006 1 20070419 G 2510 05142043 SEAT CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4224 (CAN) WHILE PERFORMING AD CF87-15R2 A CRACK WAS NOTED IN THE RADIUS OF THE MACHINED FORK AT THE LT FRONT LOCATION. THE F ORK IS MADE OF RATHER THIN RECTANGULAR ALUMINUM TUBING AND IS SUBJECT TO SOME FLEXING AS OCCUPANTS ENTER OR EXIT THE AIR CRAFT. (TC NR 20070423006) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007050800199 20070508 00199 CE 2007 5 8 CA070423007 1 20070418 G 2430 290143 PROBE BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL TEMP MONITOR INTERMITTENT W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) BATTERY TEMP MONITOR WAS INDICATING HIGHER THAN NORMAL ON APPROACH. AIRCRAFT LANDED WITHOUT INCIDENT. BATTERY WA S LUKEWARM TO THE TOUCH. MONITOR WAS UNRESPONSIVE. BATTERY AND PROBE WERE REPLACED ALONG WITH WIRING INSPECTED AND AIRC RAFT RETURNED TO SERVICE. NO FAULTS WERE FOUND DURING DEEP CYCLE OF BATTERY AT BATTERY SHOP. PROBE REPLACED DUE TO POS SIBLE INTERMITTENT OPERATION. (TC NR 20070423007) 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2007071100289 20070711 00289 WP 2007 7 11 CA070423008 2 20070416 G 7321 8978015 FUEL CONTROL SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE ENGINE LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 CA 3600 (CAN) NOTED LARGE FUEL LEAK UNDER THE AIRCRAFT IN THE HANGER. DETERMINED THE FUEL WAS COMING FROM AN ENGINE DRAIN. GRO UND RAN THE ENGINE, FOUND THE FUEL CONTROL DRAIN LEAKING. REMOVED AND REPLACED THE FUEL CONTROL WITH AN OVERHAULED UNIT , NO FURTHER DEFECTS NOTED. (TC NR 20070423008) 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 2007050800201 20070508 00201 CE 2007 5 8 CA070423009 1 20070422 G 5322 9743000015 CROSS TIE BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 7390 (CAN) THE INTERIOR WAS REMOVED FOR REFURBISHMENT. MAINTENANCE DISCOVERED A CRACK IN THE CROSS TIE, A STRUCTURAL MEMBER AROUND THE EMERGENCY EXIT ON THE LT SIDE OF THE AIRCRAFT. CONTACTED MFG FOR A REPAIR. (TC NR 20070423009) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007061500190 20070615 00190 EU 2007 6 15 CA070424001 1 20070420 G 2910 571191 PTU AIRBUS 310 A310304 3930339 EU GE CF6 CF680C2* GL HYD SYSTEM LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING FLIGHT, CREW NOTICED LOSS OF GREEN SYSTEM HYDRAULIC FLUID. FLIGHT DIVERTED TO MAIN MAINTENANCE BASE FOR INV ESTIGATION. DURING INVESTIGATION, THE GREEN/YELLOW SYSTEM PTU WAS FOUND LEAKING AT THE CHECK VALVE DUE TO A DAMAGED O RI NG. PTU UNIT WAS REPLACED AND SYSTEM TESTS SERVICEABLE. (TC NR 20070424001) 2 L 7 2 4F 4 F RT A35EU E23EA 2007061500191 20070615 00191 EU 2007 6 15 CA070424002 1 20070421 G 2121 X76451 FAN AIRBUS 310 A310304 3930339 EU GE CF6 CF680C2* GL CABIN ODOR W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) DURING FLIGHT CABIN CREW REPORTED ELECTRICAL BURN ODOR FROM THE AFT CABIN. FAULT ISOLATED TO THE AFT RT FAN HEATE R FIN NR 28HC. CB’S WERE PULLED AND ODOR DISAPPEARED. SYSTEM WAS PLACED ON MEL DUE PART IS NIL STOCK. (TC NR 200704240 02) 2 L 7 2 4F 4 F RT A35EU E23EA 2007061800114 20070618 00114 EU 2007 6 18 CA070424003 1 20070412 G 2800 UNKNOWN AIRBUS 310 A310304 3930339 EU GE CF6 CF680C2* GL FUEL SYSTEM UNKNOWN W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, CREW NOTICES A FUEL DISCREPANCY OF ONE TON BETWEEN FUEL ON BOARD AND FUEL USED. AFTER RECALCULATION SHORTLY THEREAFTER THE FUEL DISCREPANCY HAD GROWN TO 1.4 TONS. CREW PROCEEDED WITH QRH PROCEDURES AND SPOTTED FUEL SPAY ING FROM THE RIGHT WING TIP VENT BOX. SHORTLY THEREAFTER THE FUEL VENTING CEASED. THE FLIGHT WAS DIVERTED TO THE MAIN ST ATION. DURING INVESTIGATION MAINTENANCE ATTEMPTED TO DUPLICATE THE PROBLEM WITH NO SUCCESS. AIRBUS WAS CONTACTED FOR THE IR RECOMMENDATION. THE FOLLOWING UNITS WERE REPLACED AND ROUTE TO THE VENDOR FOR SHOP CHECK AND STRIP REPORT: (A) RT INN ER TANK VENT FLOAT VALVE (B) 2 RT OB BOOST PUMP CHECK VALVES (C) RT WING REFUEL/DEFUEL VALVE (D) FUEL TRANSFER VALVE A 2 L 7 2 4F 4 F RT A35EU E23EA 2008021900369 20080219 00369 CE 2008 2 19 CA070424004 1 20070419 G 2913 10138800517 POWERPACK BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCD4N3 HCD4N3A GL HYDRAULIC SYSTEM FAILED W O OTHER J WARNING INDICATION TO TAKEOFF 1 CA 9010 9010 BB1281 (CAN) DURING A ROUTINE MEDEVAC AND TEN MINUTES AFTER DEPARTURE THE RED LIGHT IN THE IN THE LANDING GEAR HANDLE ILLUMINA TED.VISUAL CONFIRMATION OUT CAPT SIDE WINDOW OF LANDING GEAR PARTIALLY DOWN. A MANUAL GEAR EXTENSION WAS INITIATED AND A UNEVENTFUL LANDING WAS COMPLETED. TELCOM WITH MTCE. AND FLIGHT CREW CONFIRMED, LANDING GEAR MOTOR WAS NON FUNCTIONING. VISUAL INSP WAS C/O BY CREW FOR DAMAGE OR EXCESSIVE FLUID LOSS, WITH NONE OBSERVED. AC WAS RETURNED WITH LANDING GEAR IN THE DOWN/ LOCKED POSITION, ESSENTIAL CREW ONLY ON BOARD. MAINT INSPECTION REVEALED,THE L/G HYD POWERPACK HAD INTERNA LLY FAILED TO MAINTAIN SYS PRESSURE,CAUSING THE PUMP TO RUN AND EXCEEDED OPERATIONAL TOLERANCE WHICH POPPED THE C/B. REP 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007050900062 20070509 00062 EA 2007 5 9 CA070424005 2 20070424 G 7230 COMPRESSOR WHEEL PWA PT6 PT6A27 52043 EA ENGINE MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) OPERATOR REPORTED THAT WHEN THE ENGINE WAS STARTED, THE PROPELLER DID NOT ROTATE. AFTER SHUTDOWN, THE ENGINE AND P ROP COULD BE ROTATED BY HAND. HOWEVER, SEVERAL SMALL PIECES OF METALLIC DEBRIS WAS REMOVED FROM THE EXHAUST AREA. DISAS SEMBLY OF THE ENGINE REVEALED SEVERE IMPACT DAMAGE ON THE FWD FACE OF THE CT DISC ASSY AND 4 MISSING CT VANE RETAINING B OLTS. FURTHER INVESTIGATION REVEALED IMPACT DAMAGE ON THE CT VANE LOCK PLATE, CT VANE, CT BLADES AND PT BLADES. (TC NR 2 0070424005) 4 T E4EA 2007061800115 20070618 00115 EA 2007 6 18 CA070424006 1 20070420 G 2497 C030722 DIODE DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE LT DC ESS BUSS MISWIRED W K NONE O OTHER IN INSP/MAINT 1 CA 35404 35404 (CAN) DURING GRD RUN LEAK CHECKS, AFTER ROUTINE MAINTENANCE, NOTED NO DISCHARGE SHOWING ON THE BATTERY MONITOR FOR THE AUX BATTERY. INVESTIGATION FOUND WIRING BACKWARDS AT DIODE 2431-CR5; THIS IS THE POWER SUPPLY TO THE BUS FROM THE AUX BA TTERY. IN THIS CONDITION NO POWER IS AVAILABLE FROM THE AUX BATTERY UNDER ANY CONDITIONS. THE ONLY INDICATION OF THIS M ISCONNECTION WAS BATTERY MONITOR SHOWING NO DISCHARGE FROM THE AUX BATTERY, WHEN BOTH MAIN AND AUX BATTERIES WERE SELECT ED ON. (NORMAL OPERATING PROCEDURE IS TO HAVE BOTH BATTERIES SELECTED ON) ALL OTHER ELECTRICAL SYSTEM INDICATIONS WERE NORMAL. WIRING CORRECTED SYSTEM FUNCTION CHECKED NORMAL. (TC NR 20070424006) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007061800116 20070618 00116 NE 2007 6 18 CA070424007 2 20070423 G 7230 JT8D15QM BLADE PWA BOEING 727 727247 138408F NM PWA JT8 JT8D15 52051 NE COMPRESSOR FAILED W C ABORTED TAKEOFF R Y PARTIAL RPM/PWR LOSS ENGINE STOPPAGE TO TAKEOFF 1 CA 57339 3677 696622 (CAN) DURING TAKEOFF ROLL AT 80KTS, THE TOWER ADVISED THE CREW THAT FLAMES WERE VISIBLE OUT OF ONE OF THE ENGINES. THE C REW REJECTED THE TAKEOFF AND ENGINES WERE SHUTDOWN. THE AIRCRAFT WAS TOWED BACK TO THE RAMP. MAINTENANCE INSPECTED THE ENGINES AND FOUND NR 2 ENGINE TO HAVE TURBINE DAMAGE. SOME INTERNAL ENGINE PARTS HAD EXITED THE ENGINE AND WERE FOUND O N THE RUNWAY. (16 IN YYC). AT THIS TIME IT LOOKS AS THOUGH THE FAILURE STARTED WITHIN THE COMPRESSOR SECTION. THE ENGIN E IS CURRENTLY BEING REMOVED FROM THE AIRCRAFT AND A FOLLOW-UP TO THIS SDR SHALL BE ACCOMPLISHED ONCE THE ENGINE HAS BEE N DISASSEMBLED FOR INSPECTION. (TC NR 20070424007) 2 L 7 3 4F 4 F A3WE E2EA 2008021900370 20080219 00370 CE 2008 2 19 CA070424008 1 20070422 G 2910 124F0016CR0164 HYDRAULIC LINE BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL HYDRAULIC SYSTEM RUPTURED W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 CA (CAN) DURING APPROACH TO LAND THE CREW EXTENDED THE LANDING GEAR AND NOTICED THE NOSE GEAR WAS NOT DOWN AND LOCKED. THE EMERGENCY GEAR EXTENSION WAS ACTIVATED AND THE NOSE GEAR WAS LOCKED IN THE DOWN POSITION. THE AC LANDED WITHOUT INCEDENT . UPON INSP BY MAINT IT WAS DETERMINED THE HYDR SYS ACCUMULATOR LINE HAD RUPTURED PURGING THE HYDRAULIC FLUID FROM THE S YS OVERBOARD. NO DEFINITIVE CAUSE FOR THE RUPTURE OF THE LINE COULD BE DETERMINED. THE AGE OF THE LINE IS UNKNOWN. IT IS SUSPECTED CYCLIC FATIGUE IS THE CAUSE OF THE RUPTURE. NO LIFE LIMIT OR REPLACEMENT INTERVAL IS MANDATED BY THE AC MFG. (TC NR 20070424008) 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 20081104 CE 2008 11 4 CA070424010 1 20070418 G 3297 973106A12SL64 CONNECTOR RAYTHN 623372 BEECH 1900 1900C 1154161 CE SELECTOR VALVE CORRODED W L ABORTED APPROACH O OTHER AP APPROACH 1 CA (CAN) ON (GEAR DOWN) SELECTION, CIRCUIT BREAKER FOR THE GEAR CONTROL POPPED AND THE GEAR REMAINED RETRACTED. AFTER A MIS SED APPROACH THE NORMAL SOP`S WERE CARRIED OUT AND THE GEAR MANUALLY EXTENDED. AN UNEVENTFUL LANDING WAS THEN CARRIED OU T. ON INVESTIGATION THE CONNECTOR TO THE GEAR SELECTOR VALVE ON THE HYDRAULIC POWER PACK WAS FOUND TO BE CORRODED AND HA D A BROKEN WIRE. THE CONNECTOR WAS REPLACED AND THE WIRE REPAIRED. THE GEAR SWINGS WERE NORMAL AND THE ACFT HAS SINCE FL OWN WITH NO REOCCURRENCE OF THE DEFECT. 2 L 7 2 4T RT A24CE 2007050800203 20070508 00203 SW 2007 5 8 CA070424011 1 20070418 G 7712 IDLER GEAR SWRNGN SA226 SA226* SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE TORQUE SENSOR LOOSE W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 3115 3115 P8640C (CAN) FOUND ON TAKEOFF ROLL, THE RT CHIP LIGHT CAME ON THROUGH 70 KTS. THE TAKEOFF WAS ABORTED AND THE AC TAXIED BACK TO THE RAMP WITHOUT ANY FURTHER INCIDENT. AT THIS TIME MAINT HAD DONE A SOAP SAMPLE AND FOUND METAL IN THE OIL FILTER. W HEN THE ENGINE WAS TAKEN APART THE TORQUE SENSOR IDLER GEAR WAS NOTICED TO BE LOOSE DUE TO THE BEARING HAD FAILED ON THE IDLER GEAR THAT IS ATTACHED TO THE TORQUE SENSOR. (TC NR 20070424011) 2 L 7 2 4T 4 T RT A56W E4WE 5 C P10NE 2007080800156 20070808 00156 CE 2007 8 8 CA070425001 1 20070423 G 3233 55275042 ACTUATOR CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE MLG MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION DE DESCENT 1 CA 7518 (CAN) AIRCRAFT EXPERIENCED UNSAFE GEAR EXTENSION WHILE DOING CIRCUITS. GEAR SELECTION WAS MADE WHILE IN DOWNWIND TURN A ND RT MAIN GEAR DOWN AND LOCKED LIGHT DID NOT ILLUMINATE, (GEAR UNLOCKED) AND (HYD PRESS ON) LIGHTS REMAINED ON. GEAR WA S RECYCLED IN LEVEL FLIGHT AND NORMAL INDICATION RESULTED. AIRCRAFT WAS FLOWN UNDER FERRY FLIGHT PERMIT WITH GEAR VERIF IED DOWN AND LOCKED. MAINTENANCE CONDUCTED SEVERAL GEAR SWINGS TO ENSURE PROPER OPERATION AND DOWNLOCK SWITCH CONTINUITY , WHICH REVEALED NO FAULTS. WHEN A LOWER THAN NORMAL HYDRAULIC PRESSURE WAS APPLIED AND GEAR DOWN SELECTION MADE, THE N OSE AND LT GEAR RELEASED BUT THE RT MAIN REMAINED IN THE UPLOCK. PRESSURE WAS THEN INCREASED TO NORMAL WITH NO EFFECT O 1 L 7 2 4F 4 F A22CE E1NE 2007062000002 20070620 00002 NM 2007 6 20 CA070425002 1 20070421 G 3213 83210301001 STRUT DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE LT MLG SEPARATED W O OTHER W Z INADEQUATE Q C SIGNIFICANT FAILURE REPORT LD LANDING 1 CA (CAN) LT MLG SEPARATED FROM AIRCRAFT DURING LANDING. THE LOWER OLEO STRUT WITH THE WHEELS AND AXLE DEPARTED THE AIRCRAFT ; AIRCRAFT LANDED ON DRAG STRUT WHICH THEN COLLAPSED AND SHEARED OFF. SUBSTANTIAL DAMAGE WAS DONE TO THE LOWER FUSE, LT NACELLE, ENGINE AND PROP, AND LT WING TIP. PILOT REPORTED THAT THERE WAS NOT A HARD LANDING. MFGS ARE INVESTIGATING THE EVENT. (TC NR 20070425002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007061800117 20070618 00117 NM 2007 6 18 CA070425003 1 20070419 G 2421 11522184 GENERATOR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NR 1 LACK OF LUBE W E ENGINE SHUTDOWN G J MULTIPLE FAILURE WARNING INDICATION AP APPROACH 1 CA 3760 1620 (CAN) DURING APPROACH TO BASE AT 1000 FEET, THE NR 1 AC GENERATOR CAUTION LIGHT ILLUMINATED. PILOT CYCLED THE NR 1 AC GE NERATOR AND THEN THE AC GENERATOR HOT CAUTION LIGHT ILLUMINATED AS WELL AS THE AC GENERATOR CAUTION LIGHT. AFTER TOUCHD OWN WHEN PLA RETARDED TO DISC THE NR 1 OIL PRESS WARNING LIGHT ILLUMINATED AND THE ENGINE WAS SHUTDOWN. GROUND INSPECTI ON REVEALED: AC GEN OVERHEATED, AC GEN QUILL SHAFT SEPARATED, NO OIL ON THE SIGHT GAGE, NO EXTERNAL LEAK, METAL TRAPPED ON THE AC GEN MCD 41 SEC, LOW OIL PRESS EXCEEDED, RECORDED IN EMU. NR 1 ENGINE REPLACED DUE TO THE EXCEEDING. (TC NR 20 070425003) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008022000008 20080220 00008 SO 2008 2 20 CA070425004 1 20070405 G 3221 67054803 TRUNNION PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6D 42305 EA HARTZL HCC3Y HCC3YR2 NE NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10636 (CAN) DURING A PREFLIGHT INSP THE PILOT NOTICED THE NOSE GEAR TRUNNION CRACKED. THE CRACK STARTS FROM THE UPPER PART OF THE CASTING AND GOES DOWN HALFWAY AT WHICH POINT IT SPREADS INTO 3 OTHER CRACKS. THE IDENTICAL CRACK CAN BE FOUND ON THE REAR SIDE OF THE CASTING .THE CRACK IS 5 INCHES LONG. SUSPECT A HARD LANDING, A HARD LANDING INPS WAS CARRIED OUT AND NO FURTHER DAMAGE WAS FOUND. THE NOSE TIRE SHOWED EVIDENCE OF A HARD LANDING. THE PART IS BEING KEPT, CAN SEND A PICTURE OR MAKE THE PART AVAILABLE FOR INSP. (TC NR 20070425004) 1 L 7 2 3O 3 O A19S0 E286 5 C P25EA 2008022000009 20080220 00009 EU 2008 2 20 CA070425005 1 20070425 G 2913 593733 BEARING 350A35109223 SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE HYDRAULIC PUMP WORN W K NONE O OTHER IN INSP/MAINT 1 CA 1188 4KMVA (CAN) DURING DI, HYDRAULIC PUMP PULLEY WAS NOTICED TO BE LOOSE LATERALLY WHEN MOVED SIDE TO SIDE. WHEN MAIN ROTOR WAS RO TATED HYDRAULIC PUMP PULLEY WAS FOUND NOT SPINNING SQUARE AND THE HYDRAULIC BELT WAS OFF SET FROM CENTER. HYDRAULIC PUMP PULLEY WAS REMOVED AND BEARING INNER RACE WAS FOUND SPINNING ON SHAFT AND WORE A SUBSTANTIAL GROOVE IN PULLEY SHAFT. ( TC NR 20070425005) 1 G 7 1 3U 3 U H9EU E00054EN 2007050800204 20070508 00204 NE 2007 5 8 CA070426002 2 20070424 G 7314 6078T39P04 PUMP CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE FUEL SYSTEM LEAKING W E D ENGINE SHUTDOWN RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 24818 683 872485 (CAN) DURING ENGINE START UP, GROUND CREW OBSERVED A LEAK COMING FROM BELOW THE ENGINE NR 2. LINE MAINTENACE FOUND A FU EL LEAK FROM A MICROSCOPIC PIN HOLE CLOSE TO A PLUGGED FITTING ADAPTOR ON ENGINE NR 2 FUEL PUMP AFT CASING. THE EXACT PI N HOLE LOCATION WAS NOT FOUND DUE TO THE HIGH FUEL PRESSURE MIST. FUEL PUMP SN CGWT0202. (TC NR 20070426002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007050800212 20070508 00212 EA 2007 5 8 CA070426003 2 20070426 G 8530 72242 ROCKER COVER RKWELL 700 700 7630520 SW LYC O540 TIO540R2AD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE SEPARATED W A UNSCHED LANDING R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CR CRUISE 1 CA 24 L633761A (CAN) SHORTLY AFTER TAKEOFF, THE PILOTS EXPERIENCED A POWER LOSS IN THE LT ENGINE, HOWEVER THE ENGINE REMAINED RUNNING. THEY RETURNED TO THE NEARBY AIRPORT WITHOUT INCIDENT. MAINTENANCE INSPECTED THE ENGINE AND FOUND THAT NR 6 CYLINDER R OCKER COVER HAD BEEN DAMAGED. THE COVER WAS REMOVED AND FOUND THAT THE RETAINING CLIP THAT HOLDS THE ROCKER SHAFTS IN PL ACE FOR THE INTAKE AND EXHAUST VALVES HAD FALLEN OFF. THE ROCKER SHAFT FOR THE INTAKE VALVE HAD FALLEN OUT ALLOWING TH E ROCKER TO BECOME DISLODGED THEREBY DISABLING THAT CYLINDER. THE VALVE ASSEMBLY WAS INSPECTED AND REINSTALLED WITH A RE PLACEMENT VALVE COVER AND GASKET. GROUND RUNS COMPLETED AND ALL CHECKS FOUND SERVICEABLE. AS NOTED ABOVE, THE ENGINE 1 L 7 2 3O 3 O A12SW E14EA 5 C P33EA 2007061800118 20070618 00118 NM 2007 6 18 CA070426005 1 20070420 G 5753 RD8457049 SEAL BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU RT OB FLAP MISSING W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) AFTER 30 MINS INTO FLIGHT, CREW REPORT AILERON MISMATCH, AP DISCONNECTED AND AILERON STUCK. PILOT USED FORCE TO R ELEASE AILERONS. REST OF FLT SYSTEM, OPS NORMAL. THIS WAS THE FIRST FLT OF THE DAY AND THE TEMP AT FL250 WAS -45 DEG C . FOUND RT FLAP SEAL LOOSE, PART MISSING AND LT FLAP SEAL LOOSE. LT AND RT FLAP SEALS REPLACED. (TC NR 20070426005) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007080800157 20070808 00157 CE 2007 8 8 CA070426007 1 20070420 G 2910 S217840114 CONNECTOR CESSNA 177 177RG 2073709 CE NLG LEAKING W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) AIRCRAFT PLANNING ON LANDING WHEN UNDERCARRIAGE LIGHT FAILED TO INDICATED GEAR DOWN AND LOCKED. DECLARED AN EMERGE NCY. AFTER SEVERAL ATTEMPTS AT TRYING TO PUMP GEAR DOWN BY HAND THE PILOT GOT A GEAR DOWN AND LOCKED LIGHT. AIRCRAFT LAN DED WITH NO EVENT TAKING PLACE. MAINTENANCE LATER FOUND THE NOSE GEAR ACTUATOR HOSE HAD SLID PARTIALLY FROM ITS SWAGED E ND CONNECTOR AND WAS LEAKING BADLY. HOSE REPLACED. (TC NR 20070426007) 1 H 7 1 3O A20CE 2007061800119 20070618 00119 EU 2007 6 18 CA070426008 1 20070419 G 3080 45150560 PROBE AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE AOA MALFUNCTIONED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) WHILE TAXIING TO POSITION FOR DEPARTURE THE CREW OBSERVED AN ICE DETECTOR FAULT. THE AIRCRAFT RETURNED TO THE RAMP FOR TROUBLESHOOTING. MAINTENANCE REPLACED THE CAPTAINS ALPHA PROBE AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 200 70426008) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2007061800120 20070618 00120 GL 2007 6 18 CA070426009 1 20070420 G 5521 C2TE83ND RIB DHAV DHC2 DHC2MKI 2801830 GL PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ELEVATOR CRACKED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 89 (CAN) THIS ELEVATOR LEADING EDGE RIB WAS FOUND CRACKED WHILE CARRYING OUT ANNUAL INSPECTION. IT WAS DETERMINED THAT THE CRACK WAS THE RESULT OF TOO SHARP OF A BEND RADIUS IN THE AREA WHERE THE PART GETS RIVETED TO THE ELEVATOR LEADING EDG E SKIN. THIS DEFECT WAS COMMUNICATED AND THE TOOLING HAS BEEN REPAIRED ALLOWING FOR A MOVE UNIFORM RADIUS ON THE PART I N QUESTION. (TC NR 20070426009) 1 H 7 1 3R 4 T RC A806 E4EA 6 C P15EA 2008032000002 20080320 00002 EU 2008 3 20 CA070427001 1 20070416 G 5210 332A2213010006 DOOR SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU MAIN PAX SEPARATED W A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 CA (CAN) AFTER TAKING OFF FROM AN OFFSHORE RIG AT 300 FT, 70 KNOTS, CREW HEARD A STRONG NOISE AND ONE OF THE PASSENGERS ADV ISED THAT DOOR WAS MISSING. P/C NOTICED NO CAUTION LIGHTS. AC RETURNED TO THE RIG AND LANDED WITHOUT FURTHER INCIDENT. A C SUBSEQUENTLY RETURNED TO CHC`S OPS MAIN BASE WITHOUT PASSENGERS AND IS PRESENTLY QUARANTINED AWAITING INVESTIGATION TE AM. CAPTAIN`S STATEMENT: FIRST FLIGHT OF THE DAY. BEFORE TAKEOFF DOOR CAUTION LIGHT FLICKERING. P/C CHECKED MEL AND ALL DOORS LOCKED. ENGINEER ON DUTY INFORMED, HE INSPECTED DOORS LOCKERS. SECOND FLIGHT. BEFORE TAKEOFF FROM (OFFSHORE RIG), DOORS WERE CONFIRMED LOCKED AND NO CAUTION LIGHTS. PASSING 00 FT AFTER TAKEOFF STRONG NOISE, PAX ADVISE DOOR MISSING, P 2 G 7 2 4U 4 U H4EU E12NE 2007061800121 20070618 00121 EA 2007 6 18 CA070427003 1 20070425 G 7897 B080201500398S CONNECTOR CNDAIR CL600 CL600* 1900302 EA GE CF34 CF34* NE THRUST REVERSER SHORTED W K NONE J WARNING INDICATION TX TAXI/GRND HDL 1 CA 6005 6005 (CAN) ON GROUND, EICAS SHOWED (PROX SYS FAULT 2). MAINTENANCE INSPECTION FOUND PYLON CONNECTOR WITH INTERNAL SHORT, IND ICATING FAILURE OF THRUST REV PROX SENSOR. CONNECTOR P/N B0802015-003-98SA (REF: WIRING MANUAL 71-50-01 J508) REPLACED, SYSTEM FUNCTION TEST NORMAL, AIRCRAFT RETURNED TO SERVICE (TC NR 20070427003) 2 L 7 2 4F 4 F RT A21EA E15NE 2007061800194 20070618 00194 CE 2007 6 18 CA070427004 1 20070423 G 2435 99121252 STARTER GEN CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL ENGINE FAILED W O OTHER J WARNING INDICATION NR NOT REPORTED 1 CA 756 (CAN) GENERATOR OUTPUT FAILURE, NO OUTPUT. (TC NR 20070427004) 1 L 7 2 4F 4 F RT A1WI E3GL 2007061800190 20070618 00190 SW 2007 6 18 CA070427005 1 20070416 G 6220 407310104103 SPRING BELL 407 407 1182206 SW ALLSN 250C 250C47B GL MAIN ROTOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON SCHEDULED INSPECTION IT WAS NOTICED THAT ONE OF THE EIGHT SPRINGS IN THE MAIN ROTOR FRAME ASSEMBLY WAS BROKEN . (TC NR 20070427005) 1 G 7 1 3U 3 U O H2SW E1GL 2007061300142 20070613 00142 NM 2007 6 13 CA070427006 1 20070410 G 5754 ATTACH BRACKET BOEING 727 727225 1384077 NM PWA JT8 JT8D15 52051 NE NR 7 SLAT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A AND B5 INSPECTION NR 7 SLAT ATTACH BRACKET UPPER MOUNT ON FRONT SPAR CRACKED. P/N TO BE DETERMINED FROM MFG ENGINEERING DRAWINGS. RDA ISSUED BY DECA ENGINEERING TO REPAIR. (TC NR 20070427006) 2 L 7 3 4F 4 F A3WE E2EA 2007061800196 20070618 00196 SO 2007 6 18 CA070427007 1 20070425 G 3220 16667000 LINK PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YK2 GL NOSE GEAR BROKEN W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) DURING GEAR RETRACTION THE PILOTS DID NOT GET A GEAR UP AND SAFE LIGHT, UPON VISUALLY INSPECTING THE GEAR WITH THE MIRRORS THE NOSE GEAR WAS SEEN TO BE DANGLING AT AN APPROXIMATE 60 DEGREE ANGLE. GEAR WAS SELECTED DOWN, DOWN AND LOCK ED INDICATION WAS PROVIDED AND THE AIRCRAFT LANDED UNEVENTFULLY. DURING INSPECTION OF THE GEAR SYSTEM THE NOSE GEAR DOW N LOCK LINK ASSEMBLIES WERE FOUND TO BE BROKEN IN HALF. THEY ARE MADE OF STEEL. THE LINK ASSEMBLIES WERE REPLACED NEW AND THE GEAR SWUNG NUMEROUS TIMES SATISFACTORILY. (TC NR 20070427007) 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2007061800197 20070618 00197 EA 2007 6 18 CA070427008 1 20070425 G 2710 82740220101 GUARD DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE WORN W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA 34757 34757 (CAN) FLIGHT CREW REPORTED ROLL CONTROL INPUTS SEEMED STIFF, ESPECIALLY LT TO RT IN-FLIGHT. ON GROUND NO INDICATION OF S TIFFNESS AND NOTHING ADVERSE WITH ROLL DISCONNECT. MAINTENANCE INSPECTION FOUND LT OB AILERON CABLE ROUTED AROUND WRONG SIDE OF CABLE GUARD. CABLE ROUTING WAS RECTIFIED, CABLE GUARD REPLACED, CABLE INSPECTED WITH NO SIGNS OF DETERIORATION. AILERON CABLES RE-TENSIONED AND INDEPENDENT INSPECTION COMPLETED. AIRCRAFT RETURNED TO SERVICE. REF: DHC-83 IPC 27-12-00 FIG 10 ITEM 350 P/N 82740220-101 CABLE GUARD , REF: DHC-83 IPC 27-12-00 FIG. 25 ITEM 470 P/N 82700563-S001 CABLE, REF: DHC SERIES 300 MAINT. TASK CARD 2710/02 PG 3 OF 6 VIEW H, PG 6 OF 6 FIGURE 4 CABLE ROUTING. (TC NR 20070427008) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007061800207 20070618 00207 EA 2007 6 18 CA070502001 1 20070502 G 2810 K215T6400212 FUEL TANK CNDAIR CL215 CL2156B11215 EA LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) TESTED BEFORE INSTALLATION, THE NEW TANK HAS BEEN FOUND LEAKING BY ONE OF PROBE ATTACHMENT. THE PROBE ATTACHMENT NUT HAS BEEN REPLACED, RETIGHTENED AND TANK INSTALLED IN A/C. (TC NR 20070502001) 2 H 7 2 4T RT A14EA 2007061800198 20070618 00198 SW 2007 6 18 CA070502002 1 20070426 G 6510 222044003107 HANGER ASSY BELL 230 230 1182149 SW TAIL ROTOR DRIVE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) T/R HANGAR BEARING ASSY FAILURE WAS DISCOVERED AFTER THE PILOT WAS ALERTED BY AN UNUSUAL NOISE UPON ENGINE START. (TC NR 20070502002) 1 G 7 2 3U NC H9SW 2007061800206 20070618 00206 EA 2007 6 18 CA070502003 1 20070502 G 2810 K215T6400212 FUEL TANK CNDAIR CL215 CL2156B11215 EA LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) TESTED BEFORE INSTALLATION, THE NEW TANK HAS BEEN FOUND LEAKING BY ONE OF THE PROBE ATTACHMENT PATCH INSTALLATION. THE NEW TANK HAS BEEN REJECTED. (TC NR 20070502003) 2 H 7 2 4T RT A14EA 2007080800158 20070808 00158 CE 2007 8 8 CA070502005 1 20070410 G 5312 24120111 BULKHEAD CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA BS 108 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8484 (CAN) PARTS WERE CRACKED AT ATTACH POINTS OF WHEEL WELL COVER SKIN 2412011-1 AND BULKHEADS STATION 108 AND 124 AND CRACK ON WHEEL WELL COVER AT RT FRONT CORNER WHERE IT ATTACHES TO BULKHEAD STATION 108. TIEDOWN RINGS ALSO ATTACH IN THIS AR EA. (TC NR 20070502005) 1 H 7 1 3O 3 O 3A17 E286 2008022000010 20080220 00010 SW 2008 2 20 CA070502006 1 20070426 G 6320 CASE BELL 427040006107 BELL 427 427 1182207 SW TRANSMISSION CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 450 56024 (CAN) ON INVESTIGATING AN OIL LEAKAGE, A CRACK WAS FOUND ON THE TRANSMISSION LOWER CASE (SIMILAR LOCATION AS SDR 2007021 6006) (TC NR 20070502006) 1 G 7 1 3U R00001RC 20081104 EA 2008 11 4 CA070502007 2 20070501 G 7414 4371 MAGNETO CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA LEFT MALFUNCTIONED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION TX TAXI/GRND HDL 1 CA 2458 475 (CAN) UPON RUN-UP, THE LT MAGNETO WAS SELECTED CAUSING THE ENGINE TO STOP. THE MAGNETO WAS REPLACED, AND AFTER SATISFACT ORY GROUND RUNNING, THE A/C WAS RELEASED FOR RETURN TO SERVICE. (TCNR 20070502007) 1 H 7 1 3O 3 O NT 3A12 E274 2008022000046 20080220 00046 SO 2008 2 20 CA070502008 1 20070427 G 7602 455361 CONTROL CABLE PIPER PA28 PA28R201T 7102813 SO CONT O360 TSIO360F 17025 SO HARTZL HCC2Y BHCC2YF1 GL MIXTURE CONTROL DAMAGED W O OTHER F FLT CONT AFFECTED IN INSP/MAINT 1 CA (CAN) MIXTURE CONTROL WAS FOUND TO BE STIFF BY MAINT ON AN ENGINE START FOR TAXI TO HANGER. CABLE WAS REMOVED. THE CABLE ROUTING POSITIONS THE CABLE LESS THAN (6) INCHES FROM THE TURBOCHARGER. AN ASBESTOS COVER HAD PREVIOUSLY BEEN PLACED OV ER THE CABLE AND STITCHED TOGETHER WITH LOCK WIRE TO PROTECT THE CABLE. ( NOT DONE AT OUR SHOP). ONCE THE COVER WAS REPL ACED WE DISCOVERED THE ENTIRE OUTER CABLE SHIELD DETERIORATED AND MISSING A TWO INCH SECTION. (TC NR 20070502008) 1 L 7 1 3O 3 O 2A13 E9CE 5 C P920 2007061800122 20070618 00122 EA 2007 6 18 CA070502009 2 20070410 G 8500 ENGINE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL NR 2 FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) NR 2 ENGINE FAILED SEVEN MINUTES PRIOR TO LANDING AT AIRPORT. NR 2 CYLINDER DROPPED DOWN INSIDE THE COWLING AND AP PROXIMATELY 2 QUARTS OF OIL WAS LOST. THE ENGINE WAS SECURED WITHIN A FEW SECONDS AND A LANDING WAS SAFELY EXECUTED AT A IRPORT. THE ENGINES WERE BOTH SET AT 31 INCHES HG, 2200 RPM AND APPROXIMATELY 1500F EGT, PRIOR TO THE NR 2 ENGINE FAILU RE. THE FAILURE OCCURRED ON THE 30 MARCH 2007. (TC NR 20070502009) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007080800159 20070808 00159 CE 2007 8 8 CA070502010 1 20070418 G 2710 0510105365 CONTROL CABLE CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL AILERONS FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 2392 (CAN) DURING INSPECTION RT WING AILERON CONTROL CABLES FOUND TO BE FRAYED WITH BROKEN STRANDS AT WING STATION 100 WHERE CABLES TRAVEL ON TOP OF FAIRLEAD PN 0522647-10 CABLES WERE REPLACED WITH NEW UNITS FROM MFG. (TC NR 20070502010) 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2007061800191 20070618 00191 NE 2007 6 18 CA070502011 2 20070420 G 7250 TURBINE WHEEL BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE NR 1 DAMAGED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 3238 469 (CAN) IN FLIGHT SHUTDOWN OF NR 1 ENGINE. POWER TURBINE WHEEL SHED BLADES. DAMAGE FOUND ON MAIN ROTOR BLADES AND TAIL ROT OR BLADES. LARGE AMOUNTS OF METAL ON CHIP DETECTOR. (TC NR 20070502011) 1 G 7 1 4U 4 U H4SW E22EA 2007061800195 20070618 00195 2007 6 18 CA070502012 1 20070424 G 3246 9546 WHEEL LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK2 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AXLE PLUG 9546 WHICH IS USED TO SECURE AXLE IN NOSE WHEEL SEPARATED ALLOWING AXLE BOLT TO COME HALF WAY OUT OF AXL E WHICH THE PILOT NOTICED ON WALK AROUND. ON INSPECTION IT WAS NOTICED THAT WHEEL HALF RETAINING BOLTS/NUTS HAD LOOSENED CAUSING WHEEL HALVES TO SEPARATE, PUTTING ADDED FORCE ON PLUG 9546 WHICH IN TURN SHEARED PLUG CAUSING BOLT TO EXIT AXLE PART WAY. (TC NR 20070502012) 3 O 1E4 5 C P6EA 2007080800161 20070808 00161 NM 2007 8 8 CA070502014 1 20070424 G 2497 FEEDER CABLE DORNER DO32 DO328300 NM PWA 306 PW306B NE ALTERNATOR CHAFED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) DURING TROUBLESHOOTING OF INTERMITTENT AC ALTERNATOR FOUND FEEDER WIRE CHAFED AND ARCED TO COWL STRUCTURE. STRUCT URE AFFECTED IS RETAINER FOR COWL SUPPORT ARM. (TC NR 20070502014) 2 H 7 2 4T 4 F RT A55NM E35NE 2007061800205 20070618 00205 EU 2007 6 18 CA070502015 1 20070430 G 7810 1379049H401 EXHAUST PIPE BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33112UHR WP ROTOL R333 R333482F12 GL ENGINE BROKEN W F A ACTIVATE FIRE EXT. UNSCHED LANDING R B J PARTIAL RPM/PWR LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA P66042C (CAN) ON CLIMB PILOTS EXPERIENCED TORQUE FLUCTUATIONS ON RT ENGINE. THEY RETURNED TO THE AIRPORT WITH NO FURTHER PROBLEM S. ON TAXI THEY BLEW THE FIRE BOTTLES ON THE RT ENGINE. WHEN MAINTENANCE REMOVED THE COWLS THEY DISCOVERED HEAT DAMAGE TO SOME WIRING. ON FURTHER INVESTIGATION THEY DISCOVERED THAT THE EXHAUST PIPE STUB HAD BROKEN AND FOLDED OVER PARTIALLY BLOCKING THE EXHAUST GAS FLOW. FURTHER INVESTIGATION IS REQUIRED. (TC NR 20070502015) 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C P61GL 2007061800201 20070618 00201 EU 2007 6 18 CA070502016 1 20070426 G 3240 18942 CLEVIS SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE RT BRAKE PEDAL BROKEN W D RETURN TO BLOCK S AFFECT SYSTEMS TX TAXI/GRND HDL 1 CA (CAN) ON RUN UP THE RT BRAKE PEDAL CLEVIS FORKEND AT THE BRAZE JOINT BROKE. ON TROUBLESHOOTING THIS SNAG, IT WAS FOUND T HAT SB 340-32-078 HAD NOT BEEN COMPLETED ON THIS A/C, THE NEW SOLID FORKEND P/N 250704 WAS INSTALLED IAW SB. (TC NR 2007 0502016) 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2007061300140 20070613 00140 EA 2007 6 13 CA070503001 1 20070207 G 2742 83963 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE HORIZONTAL STAB UNSERVICEABLE W O OTHER F FLT CONT AFFECTED CL CLIMB 1 CA 6392 1114 (CAN) SHORTLY AFTER DEPARTURE, RUNWAY 27L, AT APPROXIMATELY 3000 FEET, THE AC ROLLED TO 45 DEGREES, AND PITCHED UP > 18 DEGREES. THE CREW RECOVERED THE AIRCRAFT AT AN ALTITUDE OF 4500 FEET. POST INCIDENT INVESTIGATION FOUND NO ANOMALIES W ITH THE AILERON CONTROL SYSTEM, AILERON TRIM SYSTEM, ELEVATOR CONTROL SYSTEM, AND THE HSTA SYSTEM. SUBSEQUENT PRE-FLIGHT PREPARATION DETECTED A MALFUNCTION WITHIN THE HSTA. THE HSTA WAS REPLACED. AIR SAFETY IS IN CONTACT WITH THE TSBC WHO IN TURN ARE IN CONTACT WITH THE GERMAN BFU. CRJ 7901 APPEARS TO HAVE OPERATED WITHOUT FURTHER INCIDENT SINCE REPLACEMEN T OF THE HSTA. CRJ 7901 WAS EQUIPPED WITH A –9 HSTCU DURING THE INCIDENT FLIGHT, THIS UNIT WAS NOT SUSPECTED AND WAS NOT 2 L 7 2 4F 4 F RT A21EA E15NE 2007061800204 20070618 00204 NE 2007 6 18 CA070503002 3 20070430 G 6111 8173861 SLEEVE DHAV DHC8 DHC8106 2809020 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE MR 3 BLADE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 7571 (CAN) DURING ACTUATOR CHANGE FOUND THAT THE BLADE PIN BEARING ON THE NR 3 BLADE HAD EXCESSIVE MOVEMENT. UPON FURTHER INV ESTIGATION, FOUND THAT THE BEARING SLEEVE WAS WORN THRU TO THE BEARING AND THAT THE BLADE PIN WAS WORN AS WELL. MFG SB 1 4SF-61-134 ADDRESSES THE PROBLEM ENCOUNTERED AND WAS NOT BEEN INCORPORATED ON THIS BLADE. (TC NR 20070503002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007061800208 20070618 00208 EA 2007 6 18 CA070503003 2 20070503 G 8530 LW19332S CONNECTING ROD RKWELL 700 700 7630520 SW LYC O540 TIO540R2AD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE BROKEN W E A ENGINE SHUTDOWN UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 670 L528761A (CAN) IT WAS REPORTED TO MAINTENANCE THAT THE RT ENGINE HAD EXPERIENCED SOME TROUBLE. THE ENGINE WAS SHUTDOWN (DURING F LIGHT) AND PROP WAS FEATHERED. THE AIRCRAFT COMPLETED THE FLIGHT TO THE NEAREST AIRPORT AND LANDED WITHOUT INCIDENT. TH E PRELIMINARY INSPECTION INDICATES THAT THE NR 4 CYLINDER CONNECTING ROD BROKE THROUGH THE PISTON PIN HOLE. THIS PERMIT TED THE PISTON TO BECOME DISLODGED AND THE CYLINDER ASSEMBLY WAS SUBSEQUENTLY FORCED FREE OF THE ENGINE BREAKING ALL THE CYLINDER BASE HOLD DOWN STUDS. THE ENGINE WILL REQUIRE MAJOR REPAIRS. (TC NR 20070503003) 1 L 7 2 3O 3 O A12SW E14EA 5 C P33EA 2007061800200 20070618 00200 WP 2007 6 18 CA070503004 2 20070426 G 7321 89777026 FUEL CONTROL MTSBSI MU2 MU2B36 5780412 CE GARRTT TPE331 TPE33110 01514 WP HARTZL HCB3T HCB3TN5 GL ENGINE WORN W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 4283 4283 P106684 (CAN) ENGINE WAS SHUTDOWN DUE TO ABNORMAL INDICATIONS. ENGINE REMOVED AND SENT TO OVERHAUL FACILITY, FCU AND FUEL PUMP R EMOVED, DAMAGE FOUND TO THE FUEL CONTROL QUILL SHAFT AND THE STUB SHAFT INTERNAL SPLINES. FCU AND FUEL PUMP REPLACED. N OTE: FCU HAD 780.4 HOURS SINCE LAST SPLINE INSPECTION. NOTE: FUEL PUMP P/N 897400-5 WAS REPLACED AT THIS TIME DUE TO SP LINE CHECK OUT OF LIMITS. (TC NR 20070503004) 1 H 7 2 3T 4 T RT A10SW E4WE 6 C P15EA 2007061800189 20070618 00189 EA 2007 6 18 CA070503005 2 20070413 G 8520 76786 DRIVE GEAR PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2A GL CRANKSHAFT FAILED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 2340 RL118861 (CAN) LT ENGINE FAILED IN CRUISE FLIGHT. AIRCRAFT RETURNED TO BASE. ENGINE REMOVED AND REPLACED. THE ACCESSORY CASE WAS REMOVED AND FOUND THAT THE CRANKSHAFT DRIVE GEAR HAD FAILED (TEETH STRIPPED OFF DRIVE GEAR). (TC NR 20070503005) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007061800202 20070618 00202 EA 2007 6 18 CA070503006 2 20070426 G 8520 C3317228 SEAL PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL CRANKSHAFT LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA L521861A (CAN) RECEIVED ENGINE, AFTER A REPAIR FOR PREMATURE CAMSHAFT FAILURE (REF: SDR 20070319008). AFTER INSTALLATION AND RUN -UPS, AN OIL LEAK WAS DISCOVERED AT THE CRANKSHAFT SEAL. WHEN THE SEAL WAS REMOVED IT WAS NOTED THAT IT WAS A (SPLIT) TY PE SEAL NOT THE ONE-PIECE AS CALLED FOR IN THE IPC. AFTER SPEAKING WITH REPAIR STATION, THEY AGREED TO COVER THE LABOR AND NEW SEAL COSTS. A NEW SEAL WAS INSTALLED AND THERE HAVE BEEN NO LEAKS SINCE. WE RETURNED THE DEFECTIVE SEAL, AS THEY REQUESTED IT FOR QUALITY PURPOSES. (TC NR 20070503006) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007062500002 20070625 00002 NM 2007 6 25 CA070503007 1 20070428 G 3240 530425 LOCK BFGOODRICH DHAV DHC5 DHC5A 2803018 NM BRAKE MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 24 347 (CAN) DURING A ROUTINE DAILY INSPECTION, IT WAS NOTED ON ONE OF THE BRAKE UNITS WEAR INDICATOR PINS WAS NO LONGER PROTRU DING FROM THE BRAKE. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THE LOCKING CLIP FOR THE END OF THE PIN WAS MISSI NG ALLOWING THE PIN TO SLIDE IN AND OUT OF THE UNIT. THE BRAKE UNIT HAD JUST BEEN RETURNED FROM REPAIR BY CONDOR AVIATIO N AND INSTALLED ON THE AIRCRAFT 24.3 HOURS BEFORE. THE DEFECTIVE UNIT WAS REMOVED AND REPLACED WITH A SERVICEABLE ONE. ( TC# 20070503007) 2 H 7 2 4T RT 2007061800203 20070618 00203 NE 2007 6 18 CA070503008 2 20070429 G 8530 LW13622 VALVE STEM ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE BENT W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 466 (CAN) AIRCRAFT WAS FLYING DURING A SEISMIC JOB. ENGINE LOST POWER AND ENGINE WAS RUNNING ROUGH. EMERGENCY LANDING TOOK PLACE. MAINTENANCE INVESTIGATED AND FOUND NR 1 CYLINDER DEFECTIVE. UPON FURTHER INVESTIGATION INTAKE VALVE STUCK OPEN AND CONTACTED PISTON. CYLINDER AND PISTON WERE REPLACED AND AIRCRAFT WAS PUT BACK IN SERVICE. (TC NR 20070503008) 1 G 7 1 3O 3 O H11NM 1E4 2007061800192 20070618 00192 EU 2007 6 18 CA070503009 1 20070422 G 2742 9787314203 ACTUATOR PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL PITCH TRIM INOPERATIVE W O OTHER J WARNING INDICATION NR NOT REPORTED 1 CA 7794 5773 (CAN) THE SECONDARY ELECTRIC MOTOR, WHICH ACTUATES THE PITCH TRIM ACTUATOR IN RESPONSE TO AUTO PILOT COMMANDS WAS NOT OP ERATIVE. THIS RENDERED THE AUTOPILOT SYSTEM U/S. THE ACTUATOR WAS REPLACED AND THE SYSTEM WAS CHECKED AIRWORTHY. THE O/H INTERVAL ON THESE ACTUATORS IS 6000 HRS. OR 5 YEARS INSTALLED TIME. (TC NR 20070503009) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007061800193 20070618 00193 SW 2007 6 18 CA070503010 1 20070423 G 7603 C8102413 CONTROL CABLE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCB3T HCB3TN5 GL POWER LEVER FAILED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) CONTROL CABLE FAILED WHERE IT MAKES A BEND COMING OUT OF THE CENTER PEDESTAL. COMMON FAILURE POINT. REPLACED WIT H NEW PART, REPLACED OTHER SIDE AS A PRECAUTION AS WELL. (TC NR 20070503010) 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 2007061900127 20070619 00127 NM 2007 6 19 CA070503011 1 20070428 G 2910 3811374102 CABLE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE INDICATOR SEPARATED W O OTHER J WARNING INDICATION NR NOT REPORTED 1 CA 127 0193 (CAN) THE ORIGINAL RESERVOIR WAS REPLACED DUE TO FAULTY DIAPHRAGM INTERNALLY. NEW O/H UNIT WAS INSTALLED. APPROXIMATELY 127 HOURS LATER AS THE AIRCRAFT WAS PREPARING FOR DEPARTURE THE HYD. LOW PRESS. LIGHTS ILLUMINATED. THE AIRCRAFT RETURN ED TO THE DEPARTURE RAMP AND SHUTDOWN. DURING THE INVESTIGATION OF THE FAULT THE HYD LEVEL WAS CHECKED USING THE GAUGES WHICH BOTH SHOWED FULL. THE PUMP WAS REMOVED TO SEE IF THE SHAFT HAD SHEARED BUT IT DID NOT. UPON FURTHER TROUBLESHOOTIN G IT WAS DISCOVERED THAT THE HYDRAULIC SYSTEM WAS EMPTY. IT WAS THEN NOTICED UPON CLOSER INVESTIGATION OF THE INDICATOR CABLE ASSY. THAT THERE WAS A KINK IN THE CABLE NEXT TO THE NUT WHICH SECURES IT TO THE TOP OF RESERVOIR PREVENTING FREE 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007061900128 20070619 00128 NM 2007 6 19 CA070504001 1 20070501 G 5400 312N570138 LINE BOEING 757 757236 1384971 NM RROYCE RB211 RB211535E437 54555 NE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) FORWARD PYLON PRESSURE LINE FOUND CHAFED THROUGH CAUSING LEAK. DAMAGE CAUSED BY A DEFECTIVE HOSE CLAMP. (TC NR 20 070504001) 2 L 7 2 4F 4 F RT A2NM E12EU 2008012900014 20080129 00014 SW 2008 1 29 CA070504002 1 20070503 G 6220 471401241 TUBE BELL BELL 47 47G2 1181008 SW LYC O435 VO435A1D 41516 EA STABILIZER BAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 14126 1108 54C (CAN) ON NORMAL WALK AROUND PILOT NOTICED STABILIZER BAR TUBE CRACKED AT SLEEVE AT IB END OF TUBE. STAB BAR ASSEMBLY WAS REPLACED AND MACHINE RETURNED TO SERVICE. AD 74-08-02 COVERS THIS ISSUE ON SOME OF THE LATER MODEL STAB BARS BUT NOT TH E EARLIER MODELS OF STAB BARS. ALTHOUGH WE CHECK THIS AS PART OF OUR NORMAL PREFLIGHT CHECK AND THIS IS HOW IT WAS FOUND . (TC NR 20070504002) 1 G 7 1 3O 3 O H1 E279 2008031900136 20080319 00136 EA 2008 3 19 CA070504003 2 20070502 G 7250 3024711 TURBINE WHEEL BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 14878 PCE85202 (CAN) DURING A HOT SECTION INSPECTION, A CRACK WAS DISCOVERED ON THE CT HUB FROM ONE UNUSED BALANCE HOLE, AROUND THE FLA NGE AND BACK TO THE SAME BALANCE HOLE.THE CRACK WAS ADJACENT TO (1) OF THE (3) PROTRUDING LOCK LUGS. (TC NR 20070504003) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007061900129 20070619 00129 NM 2007 6 19 CA070504004 1 20070430 G 5330 SKIN BOEING 737 7372L9 1384497 NM PWA JT8 JT8D17 52049 NE BS 727 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING WASHING PROCEDURE MAINTENANCE DETECTED A SKIN CRACK AT BS727, WL215, APPROXIMATELY 1.5 INCHES LONG. THIS IS KNOWN AREA ADDRESSED BY SB 737-53-1065. THE AREA WAS REPAIRED IAW THE MANUFACTURERS SRM AND RETURNED TO SERVICE (TC NR 20070504004) 2 L 7 2 4F 4 F RT A16WE E2EA 2007061900130 20070619 00130 SO 2007 6 19 CA070504006 1 20070501 G 5343 36058711 FITTING LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL HAMSTD 54H 54H60117 NE TRUNNION SUPPORT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION, A CRACKED LT NLG TRUNNION SUPPORT WAS DETECTED AND THE AIRCRAFT IS CURRENTLY UNDERGOING REPLACE MENT OF THE FITTING. (TC NR 20070504006) 2 H 7 4 4T 4 T A1SO E282 6 C P906 2007080800162 20070808 00162 CE 2007 8 8 CA070504007 1 20070507 G 3245 7008006 TUBE CESSNA 207 207 2073602 CE CONT O520 IO520D 17032 SO HARTZL HCC3Y HCC3YF1 GL TIRE LEAKING W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 185 185 (CAN) AIRCRAFT LANDED, DURING TAXI RT MAIN WHEEL WENT FLAT AIRCRAFT WAS REMOVED FROM RUNWAY WHEEL ASSY REMOVED, TUBE FOU ND TO HAVE A PIN HOLE, TUBE REPLACED, AIRCRAFT RETURNED TO SERVICE (TC NR 20070504007) 1 H 7 1 3O 3 O A16CE E5CE 5 C P25EA 2008013100018 20080131 00018 CE 2008 1 31 CA070504008 1 20070503 G 2822 1013640867 PUMP BEECH BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL FUEL TRANSFER MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA PC112 (CAN) RT FUEL PUMP RUNNING EVEN AFTER MASTER SWITCH OFF. (TC NR 20070504008) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007061900131 20070619 00131 2007 6 19 CA070504009 4 20070503 G 2210 COMPUTER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL FLT DIRECTOR MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) FLIGHT DIRECTOR CB TRIPPED AND WILL NOT RESET. (TC NR 20070504009) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007061900132 20070619 00132 NM 2007 6 19 CA070504010 1 20070502 G 3234 MS253831 SWITCH BOEING 737 737201 1384454 NM PWA JT8 JT8D17 52049 NE MLG HANDLE INTERMITTENT W L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 CA (CAN) ON FINAL APPROACH, THE FLIGHT CREW SELECTED LANDING GEAR DOWN. THE LAND GEAR INDICATORS ILLUMINATED 3 GREEN AND 3 RED. THIS INDICATED A DISAGREEMENT BETWEEN LANDING GEAR HANDLE POSITION AND LANDING GEAR POSITION. THE FLIGHT CREW SELEC TED GEAR UP AND ABORTED THE LANDING. ON THE DOWNWIND LEG THE FLIGHT CREW SELECTED LANDING GEAR DOWN AND ALL ILLUMINATION WAS NORMAL (3 GREEN AND NO RED ILLUMINATION). THE FLIGHT CREW LANDED UNEVENTFUL. MAINTENANCE INSERTED THE LANDING GEAR PINS AND SELECTED GEAR UP AND DOWN NUMEROUS TIMES AND WAS NOT ABLE TO DUPLICATE THE PROBLEM. THE AIRCRAFT WAS RELEASED AND CONTINUES TO FLY WITHOUT REOCCURRENCE OF THE PROBLEM. OPERATOR HAS ORDERED AN NEW LANDING GEAR HANDLE SWITCH AND WIL 2 L 7 2 4F 4 F A16WE E2EA 2007062200051 20070622 00051 EA 2007 6 22 CA070505001 1 20070501 G 5610 NP1393225 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE COCKPIT CRACKED W B G EMER. DESCENT O2 MASK DEPLOYED O OTHER CR CRUISE 1 CA (CAN) THE CAPTAIN`S SIDE WINDSCREEN OUTER PANE CRACKED. THE FLIGHT WAS AT 34000FT, WHEN THE INCIDENT OCCURRED, THEN THEY DESCENDED AND DAWNED THEIR OXYGEN MASKS AS A PRECAUTION. THERE WAS NO PRESSURE LOSS AND NO EMERGENCY DECLARED. MAINTENA NCE INSPECTED THE AIRCRAFT AFTER LANDING AND REPLACED THE CRACKED WINDOW. (TC NR 20070505001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007061900133 20070619 00133 SW 2007 6 19 CA070506001 1 20070423 G 6510 204010765001 NUT BELL 204 204B 1181404 SW LYC T53 T5313B 41549 NE TAIL ROTOR DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) ON APRIL 23, 2007 DURING A TEST FLIGHT FOR MAINTENANCE THAT WAS PERFORMED, THE PILOT EXPERIENCED AN UNCONTROLLED Y AW TO THE RIGHT WHILE IN A 4 FOOT HOVER. THE HELICOPTER WAS IMMEDIATELY SET DOWN ON THE TARMAC. THERE APPEARED TO BE A STEP WORN IN THE INTERNAL WORM GEAR SPLINE OF NUT ASSEMBLY P/N 204-010-765-001 THAT MAY HAVE AFFECTED THE RIGGING PROCE DURE THAT WAS ACCOMPLISHED THE NIGHT BEFORE. NO DAMAGE TO HELICOPTER, CARS 625 APPENDIX G WAS PERFORMED AT THE SCENE WI TH NO REPORTED DEFECT. ENTIRE QUILL ASSEMBLY WAS REPLACED; AIRCRAFT RECEIVED FURTHER INSPECTION AND RE-RIGGED TAIL ROTO R ASSEMBLY AND TEST FLOWN WITH NO DEFECT. TSB WAS NOTIFIED AND HAVE NOT FINISHED THEIR INVESTIGATION. PRODUCT SUPPORT 1 G 7 1 4U 4 U H1SW E17EA 2007061900134 20070619 00134 EA 2007 6 19 CA070506002 1 20070505 G 7110 22850020113 NOSE COWL CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE RT ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A SCHEDULED MAINTENANCE CHECK, AFTER FAN COWL RT REMOVAL, STRUCTURAL DAMAGE WAS OBSERVED ON THE INLET COWL BY THE CAPPED 14TH STAGE BLEED AIR DUCT. DAMAGE WAS OBSERVED ON THE REMOVED FAN COWL, SAME AREA, AS WELL. MAINTENANCE P ROCEED TO REPLACE THE FAN COWL AND THE INLET COWL. AIRFRAME HOURS=26110:41. CYCLES= 21307. (TC NR 20070506002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007061900135 20070619 00135 NM 2007 6 19 CA070507005 1 20070507 G 2760 82742339001 PULLEY DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE SPOILER CABLE MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 8935 (CAN) AN OPERATOR HAS REPORTED THE FOLLOWING FINDINGS DURING THE C2 INSPECTION BEING PERFORMED ON AN AIRCRAFT. DURING IN SPECTION OF THE SPOILER CABLE DISCONNECT SENSING SYSTEM ASSY, THE FAIRLEAD ROLLER AND SPRING ATTACHMENT HAVE BEEN FOUND INSTALLED INCORRECTLY. THE OPERATOR STATE THAT THEY HAD NO REASON TO BELIEVE THAT THIS COULD HAVE BEEN CARRIED OUT IN SE RVICE, AND THE ERROR WOULD HAVE OCCURRED DURING AIRCRAFT PRODUCTION. THE OPERATOR IS CURRENTLY CONDUCTING A FLEET-WIDE INSPECTION AND WILL ADVISE US ON THEIR FINDINGS. (TC NR 20070507005) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007061900136 20070619 00136 CE 2007 6 19 CA070507007 1 20070504 G 8011 642085A4 ADAPTER CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL NR 1 STARTER FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA 10 (CAN) UNABLE TO ROTATE ENGINE DURING WALKAROUND INSPECTION PRIOR TO ENGINE START. FAULT ISOLATED TO STARTER ADAPTER ASSY . STARTER ADAPTER FAILED ONLY 9.6 HRS IN SERVICE AFTER OVERHAUL. OVERHAUL FACILITY CONTACTED. UNIT TO BE SHIPPED TO FACI LITY FOR TEARDOWN INSPECTION. STARTER ADAPTER REPLACED. (TC NR 20070507007) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2007061900137 20070619 00137 SW 2007 6 19 CA070507008 1 20070506 G 7120 276211495 TRUSS FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE RT ENGINE MOUNT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A PHASE 6 INSPECTION, A GAPING CRACK WAS FOUND ON THE RT ENGINE TRUSS MOUNT AT THE UPPER IB WELD JOINT OF T HE FIREWALL ATTACH FITTING. (TC NR 20070507008) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2007061900138 20070619 00138 CE 2007 6 19 CA070507009 1 20070503 G 7931 3020958 RELIEF VALVE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL ENGINE OIL MALFUNCTIONED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 7508 125 PCE19412 (CAN) IN CRUISE FLIGHT, OIL PRESSURE BEGAN TO FLUCTUATE FROM BOTTOM TO MIDDLE OF GREEN RANGE, 80 TO 90 PSI. FAULT CONFI RMED ON GROUND RUN, NOT RELATED TO INDICATION. CONSULTATION WITH ENGINE OVERHAULER, OIL PRV VALVE TO BE CHECKED. PARTS A T TOOLS DISPATCHED, THIS REPORT OPEN. (TC NR 20070507009) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20081104 EA 2008 11 4 CA070507010 1 20070502 G 3246 50105844 WHEEL CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 14976 (CAN) DURING ROUTINE NDT HFEC INSP ON RJ MAIN WHEEL, ACCORDING TO ABSC NDT MANUAL PART 1, 32-42-03, CRACKS WERE FOUND IN THE LOCKING RING GROOVE. THE CRACKS HAVE A DEPTH OF .040 INCH, .020 INCH AND .010.INCH. COMPONENT COULD BE SENT FOR MA CHINING, BUT THE DEFECT DEPTH IS ALREADY GREATER THAN THE MACHINING LIMITS. 2 L 7 2 4F 4 F RT A21EA E15NE 2007062200001 20070622 00001 EU 2007 6 22 CA070507011 1 20070504 G 3297 WIRE HARNESS BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU LT MLG WW DAMAGED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) DEPARTING THE LANDING GEAR SELECT LEVER WOULD NOT MOVE TO THE GEAR UP POSITION. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE DETERMINED THE SOURCE OF THE PROBLEM WAS IN THE LT GEAR HARNES S WHEELWELL CONNECTOR. THE WIRING WAS REPAIRED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070507011) 2 L 7 2 3T 4 T A24EU A196 6 C P899 2007062200002 20070622 00002 EU 2007 6 22 CA070507012 1 20070503 G 3610 SHUTOFF VALVE AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF5 NE BLEED AIR SYS MALFUNCTIONED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) DEPARTING THE CREW OBSERVED THAT THE ARCRAFT WAS FAILING TO PRESSURIZE NORMALLY. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER DIFFICULTY. MAINTENANCE REPLACED THE NR 1 BLEED AIR SHUTOFF VALVE AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070507012) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2007061900076 20070619 00076 EA 2007 6 19 CA070507013 2 20070412 G 7414 ROTOR BENDIX S4LN20 CESSNA 172 172K 2072430 CE LYC O320 O320E2D 41508 EA MCAULY 1A175 1A175* GL MAGNETO FAILED W D RETURN TO BLOCK R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 1995 (CAN) PILOT OF AC ON FLOATS DETECTED A DEAD MAGNETO ON HIS PRE-TAKEOFF INSPECTION, AND RETURNED TO THE DOCK. (TC NR 2007 0507013) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P857 20081104 CE 2008 11 4 CA070508001 1 20070507 G 8011 MHB4016R STARTER CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL ENGINE MALFUNCTIONED W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 440 (CAN) PILOT DID RUN-UP, ALL ENGINE INDICATIONS WERE NORMAL SO HE COMMENCED HIS TAKE-OFF. JUST AFTER HE STARTED TO CLIMB HE NOTICED THAT THE ACFT DID NOT WANT TO CLIMB AS IT SHOULD. ALL ENGINE INSTRUMENTS WERE WHERE THEY WERE SUPPOSED TO BE. HE ABORTED HIS TAKE-OFF WITHOUT INCIDENT. ACFT WAS RUN UP BY MAINT, ALL ENGINE INDICATIONS WERE CORRECT. COWLINGS WERE REMOVED AND ENGINE WAS INSPECTED, NOTHING WAS NOTED AS BEING WRONG. COMPRESSION CHECK WAS COMPLETED ON ENGINE AND WHILE DOING THE TEST. THE STARTER BENDIX ENGAGED BY ITS SELF (NO POWER WAS ON). TALKED TO ENGINE SHOP AND CONCLUDED THAT THE S TARTER MUST HAVE ENGAGED ITS SELF ON TAKE-OFF AND THIS CAUSED LOSS OF POWER. SERVICABLE STARTER INSTALLED AND ACFT WAS F 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2007061900078 20070619 00078 SW 2007 6 19 CA070508002 1 20070507 G 7120 206064106001 LEG ASSY BELL 206064106 BELL 206 206L1 1182107 SW ALLSN 250C 250C30 03013 GL ENGINE MOUNT BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 11747 (CAN) ON STARTING A 200HR SCHEDULED INSPECTON FOUND LT ENGINE MOUNT LEG BROKEN IN (2) PIECES AND UPON REMOVAL FOUND SEVE RE INTERNAL CORROSION THAT CAUSED THE WALL THICKNESS TO DEGRADE TO THE POINT OF COLLAPSE AND FAILURE. (TC NR 20070508002 ) 1 G 7 1 3U 3 U H2SW E1GL 2007061900079 20070619 00079 WP 2007 6 19 CA070508003 1 20070508 G 6220 369X10045 PIN HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL MAIN ROTOR BENT W K NONE O OTHER IN INSP/MAINT 1 CA 1333 (CAN) DURING AN INSPECTION THE ENGINEER NOTICED THE THE M/R BLADE FOLDING PIN LOOKED BENT. UPON TAKING THE UNIT APART HE NOTICED THAT THE THREADS OF THE PIN WERE NOT ON THE PIN STRAIGHT, KIND OF LOPSIDED. (TC NR 20070508003) 1 G 7 1 3U 3 U H3WE E4CE 2007080800163 20070808 00163 CE 2007 8 8 CA070508004 1 20070411 G 2750 S19061 CONTROL SWITCH CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL TE FLAPS FAULTY W A UNSCHED LANDING F FLT CONT AFFECTED NR NOT REPORTED 1 CA (CAN) DURING CIRCUITS, PILOTS SELECTED FLAPS UP AND THEY REMAINED IN THE FULL DOWN POSITION. FOUND UP CONTROL SWITCH AT FLAP SELECTOR IN COCKPIT FAULTY, REPLACED SWITCH, OPS CHECKED OK WITH NO FURTHER OCCURANCES. (TC NR 20070508004) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2007061900082 20070619 00082 SO 2007 6 19 CA070508005 1 20070504 G 2913 268028 HOUSING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL HYD PUMP CRACKED W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) 2ND MAINTENANCE GROUND RUN WAS COMPLETED ON AIRCRAFT AND ENGINES SHUTDOWN. HAD LUNCH AND RETURNED TO A/C AND OBSER VED POOL OF HYDRAULIC FLUID BENEATH THE RT ENGINE. POST INSPECTION OF HYD PUMP REVEALED A CRACKED HOUSING. REPLACED THE HYDRAULIC PUMP. (TC NR 20070508005) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007061900083 20070619 00083 NM 2007 6 19 CA070509001 1 20070507 G 5610 80260008 WINDSHIELD BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 69 (CAN) IN CRUISE FLIGHT AT 25,000, THE FO`S WINDSHIELD CRACKED. REMOVED AND REPLACED FO`S WINDSHIELD I/A/W Q 400 TASK 56- 10-01-000-801 AND TASK 56-10-01-400-801, REMOVED AND REPLACED FO`S WINDSHIELD ANTI-ICE CONTROLLER I/A/W Q 400 TASK 30-41 -01-00-801 AND TASK 30-41-01-400-801 OP`S TEST GOOD. (TC NR 20070509001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008022000047 20080220 00047 CE 2008 2 20 CA070509002 1 20070509 G 2133 10138001313 CONTROL VALVE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL CABIN PRESSURE INOPERATIVE W O OTHER O OTHER IN INSP/MAINT 1 CA (CAN) WORK WAS DONE TO THE AC THAT OPENED THE PRESSURE VESSEL. WHEN THIS WORK WAS STARTED THE AC WOULD HOLD MAX DIFF. TH E WORK DONE LED TO A PRESSURIZATION PROBLEM, WHICH, WHILE TROUBLESHOOTING, LED TO THE DISCOVERY OF FLOW CONTROL VALVE TH AT WAS WORKING INCORRECTLY. THE CABIN LEAK CAUSED BY THE WORK DONE WAS CORRECTED AND AN O/H FLOW PACK INSTALLED. THE AC STILL WOULD NOT HOLD MAX DIFF, MORE CABIN LEAKS WERE DISCOVERED AND REPAIRED. OUTFLOW AND SAFETY VALVES WERE CHANGED. P ROBLEM STILL REMAINED. A SERVICEABLE CONTROL VALVE FROM AN IN SERVICE AC WAS INSTALLED FOR TROUBLESHOOTING, AND THE AIRC RAFT WOULD PRESSURIZE TO MAX DIFF. A SECOND O/H FLOW CONTROL VALVE WAS INSTALLED ON THE LT SIDE AS WELL AS AN O/H UNIT 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007080800164 20070808 00164 EU 2007 8 8 CA070509003 1 20070504 G 2841 360930001 SIGNAL COND UNIT AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE73121C NE FUEL INDICATOR MALFUNCTIONED W O OTHER N FALSE WARNING CR CRUISE 1 CA 7 (CAN) IN FLIGHT, ON THE WAY BACK TO BASE THE CREW NOTICED THE RT FUEL GAUGE WAS INTERMITTENT AND NOT WORKING MOST OF THE TIME. THE DEFECTIVE PART WAS JUST REPLACED 7 HOURS PRIOR WITH THE SAME ISSUE. ANOTHER SIGNAL CONDITIONER HAS BEEN INS TALLED AND CALIBRATED. THERE HAS BEEN NO FAULTS SINCE THE REPLACEMENT. (TC NR 20070509003) 2 L 7 2 4F 4 F A33EU E6WE 2007062200003 20070622 00003 EA 2007 6 22 CA070509004 1 20070503 G 7110 2285008114 COWLING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE NR 1 ENGINE SEPARATED W K NONE D E INFLIGHT SEPARATION VIBRATION/BUFFET DE DESCENT 1 CA 5855 (CAN) ON DESCENT, THROUGH FL280, CREW FELT SLIGHT VIBRATION TO THE AIRCRAFT. FIRST OFFICER (FO) FELT A SLIGHT SHUDDER I N THE CABIN. ON ARRIVAL, IT WAS FOUND NR 1 LOWER ENGINE COWL HAD SEPARATED FROM THE AIRCRAFT. UPON MAINTENANCE INITIA L INSPECTION, IT WAS NOTED THAT 75 PERCENT OF THE CAMLOC FASTENERS THAT HOLD THE COWL WERE STILL INSTALLED IN THE COWL R ETAINERS. THE COWL SEPARATION CAUSED DAMAGE TO THE UPPER ACCESS NOSE COWL, NOSE COWL, LOWER TORQUE BOX, LOWER OB T/R CAS CADE, AND SOME T/R PDU LINES. (2) RETAINERS WERE REPLACED, THE LOWER CASCADE VANE WAS REPLACED, P2 SENSE LINE WAS REPLA CED AND THE UPPER AND LOWER COWLS WERE REPLACED. THE A/C WAS THEN FERRIED FOR FULL INSPECTION AND REPAIR. AFTER FURTH 2 L 7 2 4F 4 F RT A21EA E15NE 2007061900085 20070619 00085 NM 2007 6 19 CA070510001 1 20070506 G 2920 DSC1896 CHECK VALVE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE NR 2 HYD SYS CRACKED W O OTHER K FLUID LOSS AP APPROACH 1 CA (CAN) AN OPERATOR EXPERIENCED A LOSS OF NR 2 HYD FLUID SYSTEM DUE TO A FRACTURED CHECK VALVE WHEN THE LANDING GEAR WAS S ELECTED DOWN DURING APPROACH. THE CAUSE OF THE EVENT IS A CIRCUMFERENTIAL CRACK AROUND NR 2 HYD SYSTEM MANIFOLD CHECK VA LVE. (TC NR 20070510001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007082000038 20070820 00038 CE 2007 8 20 CA070510002 1 20070117 G 5512 SKIN CESSNA 441 441 2076020 CE STABILATOR DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA 9440 (CAN) FOUND DELAMINATION (OF 8 INCH X 16 INCH) ON TOP OF LT SIDE IB HORIZONTAL STABILIZATOR. DELAMINATION FOUND WHEN DO ING PHASE 2 AND 3 INSPECTION. HORIZONTAL STABILIZATOR REPLACED, NO REPAIR IS ALLOWED ON HORIZONTAL STABILIZATOR IAW SRM . (TC NR 20070510002) 1 L 7 2 3T RT A28CE 2008022000048 20080220 00048 CE 2008 2 20 CA070510003 1 20070428 G 3260 SQUAT SWITCH BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE RT MLG FAILED W O OTHER G MULTIPLE FAILURE DE DESCENT 1 CA (CAN) OUR 1900D WAS ON APPROACH, PILOT SELECTED THE LANDING GEAR DOWN. NOTHING HAPPENED, AC RETURNED TO IT’S MAIN BASE. WHEN MAINT RECEIVED THE AC THE FAULT COULDN’T BE DUPLICATED. DURING TROUBLESHOOTING ON THE GROUND THE MAINT WAS ABLE TO FIND A CONSTANT FAULT ON THE GROUND, IT WAS FOUND THAT THERE WAS A CONSTANT 28 VOLTS APPLIED TO THE (UP) SOLENOID OF THE HYDR POWERPACK, PREVENTING THE (DOWN) SOLENOID FROM MOVING THE SELECTOR VALVE TO THE DOWN POSITION WHEN THE LANDING GEA R HANDLE IS PLACED IN THE (DOWN) SELECTION. THE VOLTAGE SOURCE ORIGINATED FROM THE PROP GOVERNOR TEST CIRCUIT THROUGH TH E RT MLG SQUAT SWITCH. THE SQUAT SWITCH WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070510003) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2008031900137 20080319 00137 SO 2008 3 19 CA070510004 2 20070420 G 8530 TISN73OCA221 CYLINDER CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO NR 2 BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 103 150045H (CAN) WHEN DOING 100 HRS INSP, FOUND DAMAGE ON COVER VALVE ROCKER CYLINDER NR 4, COVER (PN : 631834) REMOVED AND FOUND R ETAINER ROCKER SHAFT (PN: 646032) BROKEN. NEW CYLINDER WAS INSTALLED IN POSITION NR 4. ALSO FOUND CYLINDER NR 2 WITH LOW COMPRESSION (50 PSID), THE CYLINDER WAS REPLACED BY NEW ONE. (TC NR 20070510004) 1 L 7 2 3O 3 O A7CE E7CE 2007061900086 20070619 00086 WP 2007 6 19 CA070510005 2 20070507 G 7250 TURBINE BLADES LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 607 P116662C (CAN) DURING POST/PREFLIGHT INSPECTION, MAINTENANCE PERSONNEL NOTICED NICKS ON 2 OF THE 3RD STAGE TURBINE BLADES. NO FOD DAMAGE WAS NOTICED ON THE COMPRESSOR END OF THE ENGINE, SUSPECT FIRST STAGE BLADE RETAINER COMING LOOSE FROM TURBINE DI SC AS ON SDR NR 20061110007 AND SDR NR 20060618001. WILL NOTIFY WHEN HAVE CONFIRMATION. ENGINE HAS BEEN REMOVED AND S ENT TO AN HEAVY MAINTENANCE FACILITY FOR INVESTIGATION AND REPAIR. A RENTAL ENGINE HAS BEEN INSTALLED AND THE AIRCRAFT R ETURNED TO SERVICE. (TC NR 20070510005) 2 L 7 2 4F 4 F RT T00008WI E6WE 2007061900087 20070619 00087 EU 2007 6 19 CA070510006 1 20070510 G 6520 350A33100021 GEAR SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE T/R GEARBOX WORN W A UNSCHED LANDING J WARNING INDICATION AP APPROACH 1 CA 691 691 MA1110 (CAN) GEAR SET, PINION GEAR AND BEVEL GEAR WEAR AND PRODUCED METAL. GEAR SET SCRAPPED DUE TO SPALLING. GEAR SET INSTALL ED AT LAST OVERHAUL OF THE GEARBOX. TGB TSN 4632.8 / TSO 691.2 GEAR SET TSN 691.2 (TC NR 20070510006) 1 G 7 1 3U 3 U H9EU E19EU 2007061900088 20070619 00088 NM 2007 6 19 CA070510007 1 20070504 G 3233 85311176009 ACTUATOR DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE NLG CRACKED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH, THE NOSE LANDING GEAR WOULD NOT EXTEND TO THE DOWN AND LOCKED POSITION. CREW DID A FLY-BY PASS THE AT C CONTROL TOWER, WHO CONFIRMED THAT THE GEAR WAS EXTENDED, BUT DID NOT APPEAR TO BE LOCKED. GEAR WAS CYCLED AND ALL (3) GEARS WERE CONFIRMED DOWN AND LOCKED. AIRCRAFT THEN LANDED WITHOUT FURTHER INCIDENT. AIRCRAFT WAS THEN FERRIED WITH GEA R PINNED DOWN TO A MAINTENANCE BASE FOR FURTHER INSPECTION AND REPAIR. THE FOLLOWING DAMAGE WAS FOUND. THE NLG UPLOCK AC TUATOR FITTING ASSY P/N 85311176-009 WAS FOUND CRACKED AT THE ACTUATOR ATTACH POINT. DISCOLORATION OF PART OF THE CRACK INDICATES PROPAGATION OCCURRED OVER A PERIOD OF TIME. RECOMMEND A MORE FOCUSED SPECIFIC VISUAL OR NDT INSPECTION OF THIS 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081104 WP 2008 11 4 CA070511001 1 20070508 G 8010 C0531 SWITCH ROBSIN C0512 ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE CLUTCH ACTUATOR DEFECTIVE W O OTHER S AFFECT SYSTEMS TX TAXI/GRND HDL 1 CA 487 (CAN) ACFT SHUTDOWN AT LEASE SITE. PILOT ATTEMPTED TO START THE ACFT TO CARRY OUT DAY AND ACFT FAILED TO START. FURTHER INVESTIGATION CONDUCTED BY AN AME FOUND ENGAGING SWITCH HAD FAILED. THE ACTUATOR ASSY WAS VERY DUSTY AND DIRTY FROM BELT DEBRIS. THE ACFT WAS FERRIED BACK TO A MAINT BASE AND THERE CLUTCH ASSY WAS REPLACED AND ACFT RETURNED TO THE FLIGHT LI NE. (TC NR 20070511001) 1 G 7 1 3O 3 O H11NM 1E4 2007080800165 20070808 00165 CE 2007 8 8 CA070511002 1 20070510 G 3210 504501025 TORQUE TUBE CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C* GL MLG BROKEN W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) AFTER TAKE-OFF PILOT RETACTED GEAR ALL 3 GREEN LIGHTS WENT OUT AND UNLOCKED LIGHT WAS OUT. RADIO CALL FROM TOWER INFORMED PILOT THAT LT MAIN GEAR WAS NOT RETRACTED. PILOT PUT GEAR DOWN AND GOT ALL 3 GREEN LIGHTS. SHUT DOWN LT ENGINE IN CASE GEAR COLLAPSED ON LANDING AND MADE UNEVENTFUL LANDING. AIRCRAFT INSPECTED AND IT WAS NOTED THAT THE LT MAIN RET RACT TORQUE TUBE WAS BROKEN. NEW PART ON ORDER. (TC NR 20070511002) 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2007061800123 20070618 00123 EA 2007 6 18 CA070511003 2 20070410 G 8520 BUSHING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE WORN W E A ENGINE SHUTDOWN UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 1208 L739061A (CAN) DURING CRUISE PORTION OF THE FLIGHT, THE PILOT NOTICED A VIBRATION FOLLOWED BY A NOISE AND LOSS OF OIL. THE PILOT SHUTDOWN THE ENGINE AND DIVERTED TO A NEARBY AIRPORT AND LANDED SAFELY. THE ENGINE WAS REMOVED AND SENT TO AN ENGINE SHO P FOR A TEARDOWN. IT WAS DETERMINED THAT THE COUNTERWEIGHT BUSHING WAS WORN THUS CAUSING EXCESSIVE PLAY. THIS EXCESSIV E PLAY CAUSED THE COUNTERWEIGHT CHEEK TO BREAK AND THE COUNTERWEIGHT COMING LOOSE INSIDE THE ENGINE WHICH CAUSED SUBSTAN TIAL DAMAGE. THE POSSIBLE REASON FOR THE FAILURE COULD BE DUE TO ENGINE OVERSPEED AT SOMETIME OR ANOTHER. (TC NR 200705 11003) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007061800124 20070618 00124 EU 2007 6 18 CA070511004 1 20070405 G 3230 9740926112 RELAY PILATS PC12 PC1245 7090551 EU MLG MALFUNCTIONED W O OTHER O OTHER LD LANDING 1 CA (CAN) ON A RETURN FLIGHT, GEAR DOWN WAS SELECTED BY PILOT. AFTER GEAR DOWN AND LOCKED, THE HYDRAULIC PUMP REMAINED OPER ATING. PILOT LANDED AIRCRAFT AND MAINTENANCE WAS NOTIFIED. DURING TROUBLESHOOTING MAINTENANCE DISCOVERED WHEN POWER APP LIED TO AIRCRAFT, THE HYDRAULIC PUMP REMAINED OPERATIONAL. PULLING THE HYDRAULIC CONTROL 5 AMP CIRCUIT BREAKER HAD NO EF FECT. THIS LED MAINTENANCE TO THE K601 RELAY WHERE IT WAS FOUND THAT THE CONTACTS WERE STUCK. CONSEQUENTLY THE ONLY WAY TO SHUT THE PUMP OFF WAS WITH THE BATTERY MASTER SWITCH. AFTER REPLACEMENT OF THE RELAY, SYSTEM OPERATED NORMALLY. (TC N R 20070511004) 1 L 7 1 3T RT A78EU 2007062000003 20070620 00003 GL 2007 6 20 CA070511005 2 20070502 G 7323 23007505 GOVERNOR BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE FAILED W D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 1054 (CAN) GOVERNOR DROOPED TO 95 PERCENT WOULD NOT RETURN TO 100 PERCENT. RETURNED TO BASE, TO CHANGE AIRCRAFT. DRIVE FROM GOVERNOR WAS BINDING INTERMITTENTLY. WHEN THE GOVERNOR WAS MOVED IT SOUNDED LIKE THERE WAS SOME PARTS LOOSE INTERNALLY. GOVERNOR REPLACED, PROBLEM RECTIFIED. (TC NR 20070511005) 1 G 7 1 3U 3 U H2SW E4CE 2007062000004 20070620 00004 SW 2007 6 20 CA070511006 1 20070430 G 6410 406016100119 BLADE BELL 407 407 1182206 SW ALLSN 250C 250C47B GL TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1596 (CAN) TAIL ROTOR BLADE WAS FOUND CRACKED AT THE TIP BLOCK. (TC NR 20070511006) 1 G 7 1 3U 3 U O H2SW E1GL 2007062000005 20070620 00005 SW 2007 6 20 CA070511007 1 20070430 G 6220 407310104105 SPRING BELL 407010150105 BELL 407 407 1182206 SW ALLSN 250C 250C47B GL FRAHM ASSY BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 2 SPRINGS WERE FOUND BROKEN. (TC NR 20070511007) 1 G 7 1 3U 3 U O H2SW E1GL 2007062000006 20070620 00006 SO 2007 6 20 CA070511008 2 20070502 G 8520 CRANKCASE CONT TSIO520AE3B CESSNA 303 T303 2073820 CE CONT O520 TSIO520AE 17040 SO MCAULY 3AF32C 3AF32C506 GL ENGINE CRACKED W K NONE J WARNING INDICATION CR CRUISE 1 CA 1941 246135 (CAN) SUDDEN DROP OF OIL PRESSURE DURING FLIGHT TO THE BOTTOM OF THE GREEN ON OIL PRESSURE GAUGE. CONTINUED FLIGHT WITH SAFE LANDING. CRACK NOT FOUND BY NDT. BOTTOM END REBEARINGED, BUT ENGINE OIL PRESSURE WOULD DROP ONCE WARMED UP (POST R EPAIR). FURTHER NDT BY RTD QUALITY SERVICES FOUND POSITIVE CRACK INDICATION AT ROOF OF OIL PICKUP PASSAGE WHERE THE OIL PICKUP TUBE CONNECTS TO THE SOCKET MACHINED INTO THE CRANKCASE. NDT TECHNICIAN MENTIONED A CASTING FLAW SEEMED TO BE TH E CAUSE. RTD MDT REPORT SUBMITTED AS SUPPORTING DOCUMENTATION TO THIS SDR. (TC NR 20070511008) 1 L 7 2 3O 3 O A34CE E8CE 5 C P57GL 2007062000007 20070620 00007 NM 2007 6 20 CA070511009 1 20070511 G 3246 2601483 TIE BOLT MESSIER C20509000 BOEING 767 767328 1385290 NM GE CF6 CF680C2B6F 30025 NE MLG WHEEL SHEARED W K NONE O OTHER TX TAXI/GRND HDL 1 CA 04207 (CAN) DURING ROUTINE WALKAROUND CHECK AFTER LANDING, A TIE BOLT FOR NR 2 MLG WHEEL WAS FOUND BROKEN. BROKEN PARTS FOUND JAMMED IN THE BRAKE ASSY CAUSING DAMAGES TO BOTH WHEEL ASSY AND BRAKE ASSY. FURTHER INVESTIGATION ON GOING AS TO THE CA USE OF BOLT FAILURE. (TC NR 20070511009) 2 L 7 2 4F 4 F RT A1NM E13NE 20081104 NE 2008 11 4 CA070511010 2 20070510 G 7414 SB9RU3 GEAR BOSCH DHAV DHC1 DHC1 2801702 GL PWA R985 R985AN14B 52008 NE HARTZL HCB3R HCB3R304 GL MAGNETO STRIPPED W O OTHER Y ENGINE STOPPAGE NR NOT REPORTED 1 CA (CAN) ON RUNUP BEFORE FLIGHT MAG CHECK CARRIED OUT. ENGINE WOULD NOT RUN WHEN SELECTED TO RT MAG. REMOVED RT MAG, FOUND 50 PERCENT OF TEETH ON MAIN TIMING GEAR TO BE STRIPPED OFF. RT MAG REPLACED WITH SERVICEABLE MAG. (TC NR 20070511010) 1 L 7 1 3O 3 R EXPA1L71 5E1 5 C P28EA 2007062000008 20070620 00008 EA 2007 6 20 CA070511011 1 20070502 G 5210 601R317621 HANDLE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE PAX DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5941 5941 (CAN) DURING ROUTINE MAIN CABIN DOOR INSPECTION FOUND MAIN CABIN PHASE IV DOOR HANDLE WITH (2) CRACKS. DOOR HANDLE REPLA CED. AIRCRAFT RETURNED TO SERVICE (TC NR 20070511011) 2 L 7 2 4F 4 F RT A21EA E15NE 2007062000009 20070620 00009 NM 2007 6 20 CA070512001 1 20070510 G 5610 NP15790213 WINDOW DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE COCKPIT CRACKED W K NONE O OTHER TX TAXI/GRND HDL 1 CA (CAN) UPON ARRIVAL AT THE GATE THE PILOT SET THE PARK BRAKE AND AND THE PILOT`S SIDE WINDOW OUTER LAYER SHATTERED. THE WINDOW WAS REPLACED BY MAINTENANCE AND FUNCTION CHECKED SERVICEABLE. (TC NR 20070512001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007062000010 20070620 00010 SO 2007 6 20 CA070514001 1 20070511 G 2550 UNKNOWN LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL HAMSTD 54H 54H60117 NE CARGO BAY CRACKED W O OTHER O OTHER CR CRUISE 1 CA 38990 (CAN) AT FL220 APPROXIMATELY 20 MINUTES FROM DESTINATION THE AIRCRAFT EXPERIENCED A LOSS OF PRESSURIZATION. THE CREW DES CENDED TO 10,000 AND THE AIRCRAFT CONTINUED AND LANDED WITHOUT FURTHER PROBLEM. INVESTIGATION DETERMINED THE SOURCE OF T HE PRESSURIZATION TO BE A CRACK MIDWAY IN THE RT EDGE OF THE UPPER CARGO. (TC NR 20070514001) 2 H 7 4 4T 4 T A1SO E282 6 C P906 2007071100288 20070711 00288 CE 2007 7 11 CA070514002 1 20070509 G 6120 A1464 LINK HARTZL C23035L MTSBSI MU2 MU2B60 5780460 CE GARRTT TPE331 TPE33110 01514 WP HARTZL HCB4T HCB4TN5 GL PISTON UNIT TIGHT W K NONE O OTHER IN INSP/MAINT 1 CA 291 291 M7489 (CAN) AT THE AIRCRAFT 100 HOUR INSPECTION AND DURING THE REMOVAL OF THE PROP PITCH LINKS, IT WAS FOUND THAT THE PIVOT PI N WAS DIFFICULT TO REMOVE. AFTER REMOVAL, THE PISTON UNIT (THAT WAS REPLACED RECENTLY) WAS FOUND TO HAVE PAINT INSIDE THE PIVOT PIN HOLE CAUSING THE TIGHT FIT. PAINT WAS REMOVED PIVOT PIN REPLACED AND CHECKED SERVICEABLE. (TC NR 20070514 002) 1 H 7 2 3T 4 T RT A10SW E4WE 6 C P40EA 2007061800125 20070618 00125 NE 2007 6 18 CA070514003 2 20070301 G 7261 SEAL CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE ENGINE OIL SYS LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE IN CLIMB AND DURING CRUISE THE LOW OIL PRESSURE WARNING ACTIVATED. THE E NGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A LEAKING ACCESSORY GEARBOX LIP SEAL. (TC NR 20070514003) 2 L 7 2 4F 4 F RT A22CE E00059EN 2007062000011 20070620 00011 NE 2007 6 20 CA070514004 2 20070502 G 7210 COVER FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE RGB LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA (CAN) THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED ON APPROACH AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPE CTION REVEALED LEAKING AT THE REDUCTION GEARBOX ACCESSORY COVER RELATED TO COATING LOSS. (TC NR 20070514004) 2 H 7 2 4T 4 T RT A817 E20NE 2007061800126 20070618 00126 CE 2007 6 18 CA070514005 1 20070228 G 2120 UNKNOWN CESSNA 500 500CESSNA 2076602 CE PWA JD15 JT15D1A NE CABIN SMOKE W G A O2 MASK DEPLOYED UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 77216 (CAN) SMOKE WAS OBSERVED IN THE CABIN AIR FOLLOWING TAKE-OFF. OXYGEN MASKS WERE DEPLOYED AND AN EMERGENCY DECLARED. T HE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. ( TC NR 20070514005) 1 L 7 2 4F 4 F A22CE E25EA 2007062200004 20070622 00004 EA 2007 6 22 CA070514006 2 20070303 G 7320 304867607 FMU AGUSTA AB139 AB139 0260110 SW PWA PT6 PT6* 52043 EA UNSERVICEABLE W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA (CAN) ENGINE POWER REDUCED UNCOMMANDED IN CRUISE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. THE FUEL MANAGEMENT MODULE (FMM ) WAS SUBSEQUENTLY REPLACED. (TC NR 20070514006) 2 G 7 2 4U 3 T R00002RD E2NE 2007061800127 20070618 00127 NE 2007 6 18 CA070514007 2 20070306 G 7532 BLEED VALVE AEROSP ATR72 ATR72212 8680945 EU PWA PW120 PW127 NE ENGINE MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) TAKEOFF WAS ABORTED DUE TO HIGH TURBINE TEMPERATURE INDICATION. THE INTERCOMPRESSOR BLEED VALVE WAS SUBSEQUENTLY REPLACED. (TC NR 20070514007) 2 H 7 2 4T 4 T RT A53EU E20NE 2007061800128 20070618 00128 NE 2007 6 18 CA070514008 2 20070307 G 7322 32448716 FUEL CONTROL AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE ENGINE MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) TAKEOFF WAS ABORTED DUE TO HIGH TURBINE TEMPERATURE INDICATIONS. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. (TC NR 20070514008) 2 H 7 2 4T 4 T RT E20NE 2007062000012 20070620 00012 CE 2007 6 20 CA070514009 1 20070426 G 8011 GEAR CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA STARTER IMPROPER PART W O OTHER O OTHER NR NOT REPORTED 1 CA 400 L601976 (CAN) THE GEARS ON THE STARTER DID NOT MESH WITH THE RING GEAR FROM THE ENGINE CAUSING THE TEETH TO RIDE UP AND HIT THE TOP OF THE OPPOSITE GEAR. THIS CAUSED THE ENGINE AND STARTER TO LOCK UP. (TC NR 20070514009) 1 H 7 1 3O 3 O NT 3A12 E274 2007061800129 20070618 00129 NE 2007 6 18 CA070514010 2 20070223 G 7200 ENGINE RAYTHN 36 G36 7150061 CE PWA PT6 PT6A68 NE MAKING METAL W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA RA0363 (CAN) ON A TRAINING MISSION, THE ENGINE EXPERIENCED A LOSS OF THRUST (DURING TRAFFIC PATTERN STALLS) ACCOMPANIED BY A NO ISE AND A CHIP DETECTOR INDICATION. THE PILOT DECLARED AN EMERGENCY AND ABORTED THE MISSION. SUBSEQUENT INSPECTION RE VEALED METAL PARTICLES IN THE ENGINE OIL. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514010) 1 L 7 1 3O 4 T RT 3A15 E26NE 2007061800130 20070618 00130 NE 2007 6 18 CA070514011 2 20070308 G 7313 ST3367009 PACKING AEROSP ATR72 ATR72202 8680940 EU PWA PW120 PW124B NE FUEL NOZZLES LEAKING W E ENGINE SHUTDOWN K R J FLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CLIMB AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FUEL LEAK RESULTING FROM DAMAGED FUEL NOZZLE PACKINGS. (TC NR 20070514011) 2 H 7 2 4T 4 T RT A53EU E2ONE 2007061800131 20070618 00131 EA 2007 6 18 CA070514012 2 20070305 G 7532 DIAPHRAGM SZD 48 SZD48 8821648 EU PWA PT6 PT6A65B 52043 EA BLEED VALVE PUNCTURED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CLIMB. SUBSEQUENT INSPECTION REVEALED PUNCTURED COMPRESS OR BLEED VALVE DIAPHRAGM. (TC NR 20070514012) 1 K 0 0 4 T EXP1K00 E4EA 2007061800132 20070618 00132 CE 2007 6 18 CA070514013 1 20070309 G 7931 ENGINE CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE LOW PRESSURE W O OTHER J WARNING INDICATION CR CRUISE 1 CA DB0676 (CAN) THE ENGINE EXPERIENCED AN LOSS OF OIL PRESSURE DURING CRUISE AND WAS REMOVED FROM SERVICE FOR FURTHER INVESTIGATIO N. MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514013) 2 L 7 2 4F 4 F RT A22CE E00059EN 2007061800133 20070618 00133 EA 2007 6 18 CA070514014 2 20070312 G 7314 SPLINE BELL 412 412EP 1182205 SW PWA PT6T PT6T3 52045 EA FUEL PUMP WORN W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION NR NOT REPORTED 1 CA (CAN) THE ENGINE SUFFERED AN IN-FLIGHT SHUTDOWN DUE TO FUEL STARVATION AS A RESULT OF WORN FUEL PUMP DRIVE SHAFT SPLINES . (TC NR 20070514014) 1 G 7 2 4U 4 U H4SW E22EA 2007061800134 20070618 00134 EU 2007 6 18 CA070514015 1 20070303 G 6123 AUTOFEATHER SYS AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE UNSERVICEABLE W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS AP APPROACH 1 CA MM1347 (CAN) ON APPROACH, THE ENGINE EXPERIENCED UNCOMMANDED TORQUE REDUCTIONS ACCOMPANIED BY FEATHERING OF THE PROPELLER. THE ENGINE WAS SHUTDOWN IN FLIGHT. THE ENGINE AUTO-FEATHER UNIT WAS SUBSEQUENTLY REPLACED. (TC NR 20070514015) 2 H 7 2 4T 4 T RT E20NE 2007061800135 20070618 00135 NE 2007 6 18 CA070514016 2 20070314 G 7321 8197354 FUEL CONTROL CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE ENGINE FAULTY W E ENGINE SHUTDOWN F FLT CONT AFFECTED DE DESCENT 1 CA 2599 (CAN) DURING DESCENT, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT, ACCOMPANIED BY A FUEL BOOST PRESSURE WARNIN G INDICTATION. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FAULTY MECHANICAL FUEL CONTROL UNIT . (TC NR 20070514016) 2 L 7 2 4F 4 F RT A22CE E00053EN 2007061800136 20070618 00136 EA 2007 6 18 CA070514017 2 20070316 G 7230 STATOR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA COMPRESSOR DAMAGED W C ABORTED TAKEOFF X J ENGINE FLAMEOUT WARNING INDICATION TO TAKEOFF 1 CA (CAN) THE ENGINE EXPERIENCED COMPRESSOR STALLS ON TAKEOFF ROLL AND THE TAKEOFF WAS ABORTED. SUBSEQUENT INSPECTION REVEA LED A DAMAGED SECOND STAGE COMPRESSOR STATOR. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514017) 2 H 7 2 4T 4 T RT A13NM E00062EN 2007061800137 20070618 00137 NE 2007 6 18 CA070514018 2 20070309 G 7210 GEARBOX CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE ENGINE MAKING METAL W O OTHER J R WARNING INDICATION PARTIAL RPM/PWR LOSS CR CRUISE 1 CA PC0634 (CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY A NOISE AND SMOKE IN THE CABIN AIR. SUBSEQUENT INSPECTION REVEALED OIL AT THE ENGINE INLET AND METALLIC DEBRIS ON THE REDUCTION GEARBOX CHIP DETECTOR . MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070514018) 1 H 7 1 3T 3 T A37CE E4EA 2007061800138 20070618 00138 EU 2007 6 18 CA070514019 1 20070319 G 7931 ENGINE AGUSTA A109 A119 0261102 EU PWA PT6 PT6* 52043 EA LOW PRESSURE W E ENGINE SHUTDOWN N FALSE WARNING NR NOT REPORTED 1 CA UC0035 (CAN) ENGINE OIL PRESSURE WAS SEEN TO INCREASE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE EVENT AN D ADVISE OF ROOT CAUE ONCE ESTABLISHED. (TC NR 20070514019) 1 G 7 2 3U 3 T H7EU E2NE 2007061800139 20070618 00139 NE 2007 6 18 CA070514020 2 20070202 G 7200 BEARING BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE NR 2 DAMAGED W O OTHER A FLAME/FIRE NR NOT REPORTED 1 CA (CAN) THE ENGINE EXHIBITED FLAMES FROM THE EXHAUST IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A DAMAGED (NR 2) BEARING. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514020) 2 L 7 2 4T 4 T RT A24CE E26NE 2007061800140 20070618 00140 CE 2007 6 18 CA070514021 1 20070318 G 7931 ENGINE CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION NR NOT REPORTED 1 CA DD0343 (CAN) THE ENGINE EXPERIENCED AN INCREASE IN OIL PRESSURE AND TEMPERATURE AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTI ON REVEALED METALLIC DEBRIS IN THE ENGINE OIL. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABL ISHED. (TC NR 20070514021) 2 L 7 2 4F 4 F RT A22CE E00059EN 2007061800141 20070618 00141 EA 2007 6 18 CA070514022 2 20070222 G 7310 TUBE AYRES S2 S2RHGT65 0970110 SO PWA PT6 PT6A41 52043 EA ENGINE FRACTURED W O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA (CAN) DURING SPRAYING OPERATIONS, THE ENGINE LOST POWER RESULTING IN A FORCED LANDING. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL P3 DELIVERY LINE. (TC NR 20070514022) 1 L 7 1 3T 4 T NC E4EA 2007061800142 20070618 00142 NE 2007 6 18 CA070514023 2 20070320 G 7310 ST3367009 PACKING AEROSP ATR72 ATR72212 8680945 EU PWA PW120 PW127 NE FUEL MANIFOLD LEAKING W E ENGINE SHUTDOWN K R FLUID LOSS PARTIAL RPM/PWR LOSS CR CRUISE 1 CA (CAN) THE ENGINE EXHIBITED AN UNCOMMANDED POWER REDUCTION IN CRUISE AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION R EVEALED LEAKING FUEL MANIFOLD PACKINGS. (TC NR 20070514023) 2 H 7 2 4T 4 T RT A53EU E20NE 2007062200005 20070622 00005 SO 2007 6 22 CA070514024 2 20070514 G 8530 637781 EXHAUST VALVE CONT 639056 CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO ENGINE FAILED W A UNSCHED LANDING R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CR CRUISE 1 CA 847 (CAN) EXHAUST VALVE HEAD SEPARATED, STRIKING THE INTAKE VALVE AND CAUSING THE INTAKE VALVE TO FAIL. THE HEAD OF THE EXHA UST VALVE LODGED INTO THE EXHAUST PORT. THE INTAKE VALVE HAD (2) PIECES SEPARATE AND ONE LODGED ITSELF INTO THE TOP OF T HE NR 1 CYLINDER HEAD, THE OTHER PORTION MIGRATED TO AN ADJACENT CYLINDER. ALL CYLINDERS WILL BE REMOVED AS COMPRESSION IS LOW ON ALL. (TC NR 20070514024) 1 L 7 2 3O 3 O A7CE E7CE 2007061800143 20070618 00143 NE 2007 6 18 CA070514026 2 20070227 G 7310 ST3367009 PACKING AEROSP ATR72 ATR72 EU PWA PW120 PW124B NE FUEL MANIFOLD LEAKING W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION AP APPROACH 1 CA (CAN) THE ENGINE FLAMED OUT ON APPROACH. SUBSEQUENT INSPECTION REVEALED LEAKING FUEL NOZZLE MANIFOLD PACKINGS. (TC NR 2 0070514026) 2 H 7 2 4T 4 T RT E2ONE 2007062200006 20070622 00006 NE 2007 6 22 CA070514027 2 20070416 G 7532 0301037140 BLEED VALVE TMECA ARRIEL1D1 SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE ENGINE BROKEN W K NONE L NO TEST IN INSP/MAINT 1 CA 9219 (CAN) PIPE FAILED/BROKEN AROUND COMPLETE CIRCUMFERENCE OF FLARE. FOUND WHEN BLEED VALVE WOULD NOT PASS TEST FOR CORRECT OPERATION. (TC NR 20070514027) 1 G 7 1 3U 3 U H9EU E19EU 2007061800144 20070618 00144 NE 2007 6 18 CA070514028 2 20070322 G 7250 TURBINE BLADES CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE ENGINE DAMAGED W O OTHER A FLAME/FIRE TX TAXI/GRND HDL 1 CA PC0463 (CAN) ON ENGINE SHUTDOWN FLAMES WERE SEEN EXITING THE EXHAUST. SUBSEQUENT INSPECTION REVEALED DAMAGED COMPRESSOR TURBIN E BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514028) 1 H 7 1 3T 3 T A37CE E4EA 2007062200007 20070622 00007 EU 2007 6 22 CA070514029 1 20070422 G 5330 SKIN SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FOUND CRACK IN SKIN OF MAIN TRANSMISSION DECK DURING SCHEDULED 500 HOUR INSPECTION. DECK REPAIRED IAW MFG REPAIR I NSTRUCTIONS FOR CRACKS DISCOVERED IN THIS AREA. (TC NR 20070514029) 1 G 7 1 3U 3 U H9EU E19EU 2007061800145 20070618 00145 NE 2007 6 18 CA070514030 2 20070322 G 7310 33026779 LINE BEECH 200 B200 1152922 CE PWA PT6 PT642A NE FUEL CONTROL FRACTURED W O OTHER K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) A FUEL LEAK WAS NOTED DURING GROUND OPERATIONS. SUBSEQUENT INSPECTION REVEALED A FRACTURE FUEL LINE AT THE FUEL C ONTROL. (TC NR 20070514030) 1 L 7 2 4T 4 T A24CE E4EA 2007061900089 20070619 00089 NM 2007 6 19 CA070514031 1 20070512 G 2420 TRANSFORMER 736664A BOEING 767 767233 1385113 NM PWA JT9 JT9D7R4D 52054 NE IDG OPEN W O OTHER J WARNING INDICATION CR CRUISE 1 CA 42599 D0161 (CAN) DURING CRUISE, THE LT AC BUS FAILED WITH THE LOSS OF ASSOCIATED SYSTEMS. THE CONCERN WAS BEING ABLE TO START THE APU. FLIGHT DECLARED A PAN-PAN WITH ATC AND BEGAN DIVERSION. AT FL 350, 2 APU START ATTEMPTS, BUT START WAS ACHIEVED O NLY AT FL150. IAW CHECKLIST, LT BUS TIE SWITCH WAS RESET, AND LT BUS RESTORED. HOWEVER, APU GEN AND GEN FAILED LIGHTS WERE ON. ACFT LANDED APPROX 3 TONS OVERWEIGHT. MTC CARRIED OUT WIRING CHECKS IAW FIM 24-20-00-101, AND FOUND THE LT ID G CURRENT TRANSFORMER OPEN. THEY REPLACED THE LT IDG AND LT GCU IAW AMM 24-11-01-401 AND 24-22-02. NOTE: GCU WAS CHAN GED ALONG WITH THE IDG. THE REMOVED GCU INFO IS: P/N 734284D, S/N 1696, 73326 HOURS TOTAL TIME (TC NR 20070514031) 2 L 7 2 4F 4 F RT A1NM E3NE 2007061800146 20070618 00146 NE 2007 6 18 CA070514032 2 20070323 G 7250 TURBINE BLADES AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE ENGINE DAMAGED W E ENGINE SHUTDOWN R A PARTIAL RPM/PWR LOSS FLAME/FIRE CL CLIMB 1 CA 127007 (CAN) THE ENGINE EXPEREINCED AN UNCOMMANDED POWER REDUCTION IN CLIMB, ACCOMPANIED BY NOISE AND FLAMES EXITING THE EXHAUS T. THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED FRACTURED HIGH POWER TURBINE BLADES. MFG WILL I NVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514032) 2 H 7 2 4T 4 T RT E20NE 2007061900090 20070619 00090 SO 2007 6 19 CA070514033 1 20070429 G 2410 LW18129 BELT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ALTERNATOR LOOSE W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 25 (CAN) PILOT NOTICED ALTERNATOR INOPERATIVE LIGHTS ILLUMINATE A FEW TIMES THEN STAYED ON, SO HE ELECTED TO LAND AT NEARES T AIRPORT. MAINTENANCE FOUND BOTH ALTERNATOR BELTS LOOSE, CAUSE WAS DETERMINED TO BE BELT STRETCH AND WEAR-IN DUE TO BOT H BELTS BEING REPLACED 25 HOURS PREVIOUSLY. (TC NR 20070514033) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007061800147 20070618 00147 NE 2007 6 18 CA070514034 2 20070326 G 7321 32448094 FCU PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A135 52043 NE ENGINE FAULTY W E ENGINE SHUTDOWN F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) DURING CLIMB, ENGINE POWER INCREASED UNCOMMANDED, RESULTING IN A TORQUE EXCEEDANCE. THE ENGINE WAS SHUTDOWN IN FL IGHT. SUBSEQUENT INSPECTION REVEALED A FAULTY FUEL CONTROL UNIT. (TC NR 20070514034) 1 L 7 2 3T 4 T A8EA E4EA 2007061800148 20070618 00148 EA 2007 6 18 CA070514035 2 20070326 G 7310 3011849 LINE EMB 110 EMB110* SO PWA PT6 PT6A34 52043 EA FCU FRACTURED W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) A FUEL LEAK WAS DISCOVERED DURING GROUND HANDLING OPERATIONS. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL TUBE . (TC NR 20070514035) 1 L 7 2 4T 4 T RT A21SO E4EA 2007061800149 20070618 00149 NE 2007 6 18 CA070514036 2 20070328 G 7200 ENGINE GULSTM 200 200 4500308 NM PWC PW306 PW306A 52165 NE NOISY W E ENGINE SHUTDOWN E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA CC0071 (CAN) IN CRUISE THE ENGINE EMITTED A NOISE ACCOMPANIED BY VIBRATION, A FADEC FAULT INDICATION AND FIRE WARNING INDICATIO N. THE ENGINE WAS SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514036) 2 L 7 2 4F 4 F RT A53NM E35NE 2007061900091 20070619 00091 NE 2007 6 19 CA070514037 2 20070321 G 7200 ENGINE PWA PT6 PT6A65AR 52043 NE HARTZL HCB5M HCB5MP3 GL NOISY W C ABORTED TAKEOFF E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 CA 97047 (CAN) THE ENGINE EMITTED A NOISE ON TAKEOFF ROLL ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER. TAKEOFF WAS ABORTED. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514037) 4 T E4EA 6 C P44GL 2007061800150 20070618 00150 EA 2007 6 18 CA070514038 2 20070328 G 7261 PACKING BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA OIL PUMP LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ENGINE OIL PRESSURE FLUCTURATED DURING FLIGHT AND OIL WAS SEEN EXITING THE ENGINE COWLINGS. SUBSEQUENT INSPECTION REVEALED A DAMAGED OIL PUMP O-RING PACKING. (TC NR 20070514038) 2 H 7 2 4T 4 T RT A13NM E00062EN 2007061800151 20070618 00151 NE 2007 6 18 CA070514039 2 20070330 G 7313 ST3367009 PACKING AEROSP ATR72 ATR72212 8680945 EU PWA PW120 PW127 NE FUEL MANIFOLD LEAKING W O OTHER K X J FLUID LOSS ENGINE FLAMEOUT WARNING INDICATION AP APPROACH 1 CA (CAN) THE ENGINE FLAMED OUT ON APPROACH. SUBSEQUENT INSPECTION REVEALED DAMAGED FUEL NOZZLE MANIFOLD O-RING PACKINGS. ( TC NR 20070514039) 2 H 7 2 4T 4 T RT A53EU E20NE 2007061800152 20070618 00152 NE 2007 6 18 CA070514040 2 20070331 G 7230 FAN BLADE LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE ENGINE FRACTURED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, THE ENGINE EMITTED A LOUD NOISE AND HIGH VIBRATIONS AND SHUTDOWN. SUBSEQUENT INSPECTION REVEALED A FRACTURED LOW PRESSURE COMPRESSOR FAN BLADE, DAMAGE TO THE ENGINE NACELLE INLET, MISSING ENGINES COWLS AND ASSOCIATED A IRFRAME IMPACT DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514040) 2 L 7 2 4F 4 F RT A10CE E35NE 2007061800153 20070618 00153 NE 2007 6 18 CA070514041 2 20070327 G 7321 DRIVE SHAFT 9682011739 PILATS PC7 PC7 7090401 EU PWA PT6 PT6A25 52043 NE FCU SHEARED W E ENGINE SHUTDOWN F FLT CONT AFFECTED AP APPROACH 1 CA 4352 98034 (CAN) THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT AND SUBSEQUENTLY ACCELERATED UNCOMMANDED. THE ENGINE WAS SH UTDOWN ON APPROACH. SUBSEQUENT INSPECTION REVEALED A SHEARED FUEL CONTROL UNIT DRIVE SHAFT. (TC NR 20070514041) 1 L 7 1 3T 3 T RT A50EU E4EA 2007061800154 20070618 00154 NE 2007 6 18 CA070514042 2 20070403 G 7200 ENGINE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE MALFUNCTIONED W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 114033 (CAN) ENGINE TORQUE FLUCTUATED IN FLIGHT ACCOMPANIED BY HIGH INTER-TURBINE TEMPERATURE AND LOW OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION FOUND THE POWER SECTION SEIZED AND THE EXHAUST DUCTS DENTED. MFG WILL M ONITOR THE INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514042) 2 L 7 2 4T 4 T RT A24CE E26NE 2007061800155 20070618 00155 NE 2007 6 18 CA070514043 2 20070404 G 7313 ST3367009 PACKING AEROSP ATR72 ATR72212 8680945 EU PWA PW120 PW127 NE FUEL NOZZLE LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) DURING BOARDING, FUEL WAS DISCOVERED LEAKING FROM THE ENGINE. SUBSEQUENT INSPECTION REVEALED DAMAGED FUEL NOZZLE TRANSFER TUBE PACKINGS. (TC NR 20070514043) 2 H 7 2 4T 4 T RT A53EU E20NE 2007061800156 20070618 00156 NE 2007 6 18 CA070514044 2 20070403 G 7320 31B474707 FADEC LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE ENGINE FAULTY W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION DE DESCENT 1 CA (CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION DURING DESCENT AND WOULD NOT RESPOND TO THROTTLE INPUT. THE ENGINE WAS SHUTDOWN IN FLIGHT. THE ELECTRONIC ENGINE CONTROL (FADEC) WAS SUBSEQUENTLY REPLACED. (TC NR 20070514044) 2 L 7 2 4F 4 F RT A10CE E35NE 2007061800157 20070618 00157 NE 2007 6 18 CA070514045 2 20070409 G 7250 TURBINE BLADES AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE ENGINE FRACTURED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF THE ENGINE EXHIBITED TORQUE FLUCTUATIONS AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. S UBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. (TC NR 20070514045) 2 H 7 2 4T 4 T RT E20NE 2007061900093 20070619 00093 NE 2007 6 19 CA070514046 2 20070411 G 7230 ROTOR DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE ENGINE SEIZED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION CL CLIMB 1 CA AW0015 (CAN) DURING CLIMB THE ENGINE EXHIBITED VIBRATION AND SHUTDOWN, UNCOMMANDED. SUBSEQUENT INSPECTION REVEALED HIGH PRESSU RE ROTOR SEIZURE AND METAL CONTAMINATION IN THE TURBO MACHINE OIL SYSTEM. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514046) 2 H 7 2 4T 4 T RT A13NM E20NE 2007061900094 20070619 00094 NE 2007 6 19 CA070514047 2 20070411 G 7250 TURBINE BLADES PIAGIO P180 P180 6960204 EU PWA PT6 PT6A66 52043 NE TURBINE SECTION FRACTURED W E ENGINE SHUTDOWN J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB, THE ENGINE EMITTED A NOISE AND ENGINE PARAMETERS WERE SEEN TO FLUCTUATE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. (TC NR 20070514047) 1 H 7 2 3O 4 T RT A59EU E26NE 2007061900095 20070619 00095 NE 2007 6 19 CA070514048 2 20070413 G 7313 ST3367009 PACKING DHAV DHC8 DHC8201 2809001 NM PWA PW120 PW123 NE FUEL NOZZLE LEAKING W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) DURING STARTING, FUEL WAS FOUND LEAKING FROM THE ENGINE. SUBSEQUENT INSPECTION REVEALED DAMAGED FUEL NOZZLE TRANSF ER TUBE O-RING PACKINGS. (TC NR 20070514048) 2 H 7 2 4T 4 T RT A13NM E20NE 2007062200052 20070622 00052 2007 6 22 CA070514049 4 20070507 G 6122 6506715 GOVERNOR ALLSN 501D 501D13D 03004 GL ALLSN A6441 A6441FN606 GL RT PROPELLER MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) WHILE ON CLIMB OUT, AFTER THE CREW MADE A ROUTINE SELECTION OF PROP SYNC, THE RT PROP/ ENGINE BEGAN TO CYCLE UNCON TROLLABLY. THE CREW SHUT IT DOWN AND RETURNED TO STATION. MAINTENANCE REPLACED THE RT PROP GOVERNOR AND THE A/C RETURNED TO SERVICE. (TC NR 20070514049) 4 T E282 6 C P898 2007062200053 20070622 00053 NE 2007 6 22 CA070514050 2 20070418 G 7200 PT6A11AG ENGINE FLTCHR 24 FU24AIRPTS 3530202 WP PWA PT6 PT6A11AG 52043 NE MALFUNCTIONED W E ENGINE SHUTDOWN F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) ENGINE POWER INCREASED UNCOMMANDED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE EVENT AND ADVI SE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070514050) 1 L 7 1 3O 3 T 4A12 E4EA 2007062200054 20070622 00054 NE 2007 6 22 CA070514051 2 20070418 G 7200 PT6A67A ENGINE AIRTRC AT802 AT802 0390305 SW PWA PT6 PT6A67A 52043 NE FLAMED OUT W O OTHER X ENGINE FLAMEOUT CR CRUISE 1 CA RD0014 (CAN) THE ENGINE FLAMED OUT IN FLIGHT. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514051) 1 L 7 1 3T 4 T NC A19SW E26NE 2007062200055 20070622 00055 EA 2007 6 22 CA070514052 2 20070413 G 7200 PT6A28 ENGINE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA SURGES W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 51225 (CAN) THE ENGINE SURGED DURING CLIMB ACCOMPANIED BY AN INCREASE IN INTERTURBINE TEMPERATURE. MFG WILL INVESTIGATE THE E VENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514052) 1 L 7 2 3T 4 T A14CE E4EA 2007062200056 20070622 00056 NE 2007 6 22 CA070514053 2 20070418 G 7250 TURBINE BLADES BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE ENGINE FRACTURED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA (CAN) ON ADVANCING POWER FOR TAKEOFF, THE ENGINE EMITTED A NOISE AND LOST POWER. SUBSEQUENT INSPECTION REVEALED FRACTUR ED POWER TURBINE BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070514053) 2 L 7 2 4T 4 T RT A24CE E26NE 2007062200057 20070622 00057 2007 6 22 CA070514054 1 20070420 G 6123 AUTOFEATHER SYS PWA PW120 PW123 NE ENGINE MALFUNCTIONED W O OTHER F FLT CONT AFFECTED IN INSP/MAINT 1 CA (CAN) DURING WATER SCOOPING, THE ENGINE PROPELLER AUTO-FEATHERED. THE ENGINE TORQUE SENSOR AND ELECTRICAL HARNESS WERE SUBSEQUENTLY REMOVED FOR INVESTIGATION. MFG WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070514054) 4 T E20NE 2007062200058 20070622 00058 NE 2007 6 22 CA070514055 2 20070422 G 7200 PW120 ENGINE DHAV DHC8 DHC8* NM PWA 120 PW120 NE FLAMED OUT W O OTHER X ENGINE FLAMEOUT CR CRUISE 1 CA (CAN) THE ENGINE FLAMED OUT IN CRUISE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514055) 2 H 7 2 4T 4 T RT A13NM E20NE 2007061900097 20070619 00097 NE 2007 6 19 CA070514056 2 20070420 G 7200 PW121 ENGINE AEROSP ATR42 ATR42300 8680920 EU PWA PW121 PW121 52124 NE FLAMED OUT W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA 121328 (CAN) THE ENGINE FLAMED OUT IN CRUISE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514056) 2 H 7 2 4T 4 T RT A53EU E20NE 2007061800158 20070618 00158 NE 2007 6 18 CA070514057 2 20070113 G 7230 BLADE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE COMPRESSOR DAMAGED W O OTHER J WARNING INDICATION DE DESCENT 1 CA (CAN) DURING DESCENT ENGINE OIL PRESSURE REDUCED ACCOMPANIED BY AN INCREASE IN INTER-TURBINE TEMPERATURE. ENGINE POWER WAS REDUCED AND A LANDING ACCOMPLISHED AT LOW POWER. SUBSEQUENT INSPECTION REVEALED COMPRESSOR TURBINE BLADE DAMAGE. M FG WILL MONITOR INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514057) 1 H 7 1 3T 3 T A37CE E4EA 2007061800159 20070618 00159 EA 2007 6 18 CA070514058 2 20070227 G 7230 COMPRESSOR EMB 110 EMB110* SO PWA PT6 PT6A34 52043 EA ENGINE DAMAGED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 56418 (CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A REDUCTION IN ALL PARAMERTERS TO ZERO. SUBSEQUENT I NSPECTION REVEALED COMPRESSOR AND POWER TURBINE DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ES TABLISHED. (TC NR 20070514058) 1 L 7 2 4T 4 T RT A21SO E4EA 2007061900098 20070619 00098 NE 2007 6 19 CA070514059 2 20070423 G 7313 PACKING FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE FUEL NOZZLE DAMAGED W O OTHER R X J PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE ENGINE POWER REDUCED UNCOMMANDED AND THE ENGINE SUBSEQUENTLY FLAMED OUT. INSPECTION REVEALED A DAMA GED FUEL NOZZLE TRANSFER TUBE O-RING PACKING. (TC NR 20070514059) 2 H 7 2 4T 4 T RT A817 E20NE 2007061900099 20070619 00099 NE 2007 6 19 CA070514061 2 20070423 G 7250 ENGINE AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE MALFUNCTIONED W E ENGINE SHUTDOWN F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) AT TOP OF CLIMB, ENGINE TORQUE REDUCED UNCOMMANDED ACCOMPANIED BY A POWER TURBINE OVER-SPEED CONDITION. THE ENGIN E WAS SHUTDOWN IN FLIGHT. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070514061) 2 H 7 2 4T 4 T RT E20NE 2007061900101 20070619 00101 NE 2007 6 19 CA070514062 2 20070426 G 7250 TURBINE BLADES BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE ENGINE FRACTURED W O OTHER O OTHER NR NOT REPORTED 1 CA TB0071 (CAN) THE ENGINE CHIP DETECTOR WARNING ACTIVATED IN FLIGHT AND THE ENGINE SHUTDOWN UNCOMMANDED. SUBSEQUENT INSPECTION R EVEALED FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE DETERMINED (TC NR 20070514062) 1 G 7 1 4U 4 U H4SW E22EA 2007080900035 20070809 00035 CE 2007 8 9 CA070515001 1 20070514 G 2822 MS2774317 RELAY 2C68 CESSNA 208 208 2073702 CE PWA PT6 PT6A114 52043 NE MCAULY 3AF34C 3GFR34C703 GL FUEL PUMP INOPERATIVE W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) A/C ABORTED TAKEOFF AUX PUMP LIGHT ON AT HIGH POWER. RELAY REPLACED, A/C GROUND RUN AT HIGH POWER NO FAULT FOUND (TC NR 20070515001) 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2007061900102 20070619 00102 EA 2007 6 19 CA070515002 1 20070514 G 3250 711619 COLLAR DHAV 7110029 DHAV DHC6 DHC6200 2802620 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL STEERING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 226 (CAN) DURING MAINTENACE TO REPAIR THE NOSE GEAR ASSEMBLY IT WAS NOTED THAT THE STEERING COLLAR WAS CRACKED. THE NOSE GEA R WAS THEN FULLY DISASSEMBLED TO REMOVE THE CRACKED STEERING COLLAR. THE NLG WAS THEN VISUALLY INSPECTED AND SOME OF THE ITEMS SENT FOR NDT. STEERING COLLAR CRACK CONFIRMED BY NDT. STEERING LIMITS OF ACTUATOR CHECKED FOR CORRECT TRAVEL AND VERIFIED WITHIN LIMITS. THIS COLLAR HAS BEEN IN SERVICE FOR SOME TIME. (TC NR 20070515002) 1 H 7 2 3T 3 T RT A9EA E4EA 6 C P15EA 2007061900103 20070619 00103 NM 2007 6 19 CA070515003 1 20070507 G 2910 65178444441 TUBE BOEING 727 727225 1384077 NM PWA JT8 JT8D15 52051 NE HYD SYSTEM CHAFED W L ABORTED APPROACH K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA (CAN) IB, HYDRAULIC A SYS PRESSURE WAS NORMAL ON APPROACH AND QUANTITY REPORTED APPROXIMATELY ZERO. UPON SELECTION OF FL APS, QUANTITY READ ZERO AND LOW PRESSURE LIGHTS ILLUMINATED. FLIGHT CREW DECLARED AN EMERGENCY AND THE HYDRAULIC FAILURE CHECKLIST WAS CARRIED OUT AFTER MISSED APPROACH PROCEDURE. THE AIRCRAFT LANDED NORMALLY WITH NO FURTHER INCIDENT. A HY D LEAK WAS FOUND INSIDE THE AFT AIRSTAIR AREA ON THE LT SIDE. THE HYDRAULIC A SYSTEM PRESSURE LINE FROM THE NR 1 ENGINE TO THE HYDRAULIC A SYSTEM MODULE WAS FOUND CHAFED WHERE THE LINE COMES INTO THE AFT AIRSTAIR AREA FROM THE NR 1 ENGINE P YLON. THE CHAFED LINE WAS CAUSED BY EXCESSIVE PLAY OF THE HYDRAULIC TUBING FIRE SEAL BETWEEN THE PYLON AND THE AFT AIRST 2 L 7 3 4F 4 F A3WE E2EA 2007061900111 20070619 00111 EA 2007 6 19 CA070515004 2 20070502 G 8530 A4871 RETAINER ROBSIN R22 R22BETA 7640110 NM LYC O320 O320B2C 41508 EA CYLINDER BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING 25 HOUR INSPECTION, FOUND (NR 2), (A) CYLINDERS IB LOWER BAFFLE RETAINER HEAD BROKEN AND ITS SPRING MISSING , THUS AFT BAFFLE IN CONTACT WITH NR 2 CYLINDER OIL RETURN LINE CAUSED DEEP WEAR ON OIL LINE. NO LEAK FOUND AT THAT TIME . RETAINER, SPRING AND OIL RETURN LINE REPLACED. (TC NR 20070515004) 1 G 7 1 3O 3 O H10WE E274 2007061900112 20070619 00112 GL 2007 6 19 CA070515005 3 20070503 G 6114 D2A34C580 HUB CESSNA 185 A185F 2072821 CE CONT O520 IO520* 17032 SO MCAULY 2A34C D2A34C58 GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3545 1052 (CAN) EDDY CURRENT DETECTED INDICATION BEYOND ALLOWABLE LIMITS ON HUB SOCKET NR 1, 2 TO 3 THREADS DOWN. (TC NR 200705150 05) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2007061900113 20070619 00113 SW 2007 6 19 CA070515006 1 20070501 G 2434 LW10382 BRACKET HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA ALTERNATOR BROKEN W O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA L3515336A (CAN) ALTERNATOR BRACKET BROKEN. REPLACED BRACKET WITH NEW PART PN LW10382. (TC NR 20070515006) 1 G 7 1 3O 3 O O 4H12 E286 2007061900114 20070619 00114 EA 2007 6 19 CA070515007 2 20070513 G 7261 OIL SYSTEM DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 26205 4436 PCE41553 (CAN) DURING CRUISE FLIGHT, THE FLIGHT CREW NOTICED A MOMENTARY FLUCTUATION AND THEN DECREASING OIL PRESSURE, THEN EVERY THING RETURNED TO NORMAL. MOMENTS LATER, THE ENGINE FAILED AND THE CREW CARRIED OUT THE SHUTDOWN. THE AIRCRAFT LANDED WITHOUT INCIDENT, ONCE ON THE GROUND, THE FLIGHT CREW ATTEMPTED TO TURN THE PROPELLER AND FOUND IT WAS SEIZED. MAINTENAN CE ARRIVED AND CONFIRMED A CATASTROPHIC FAILURE OF THE POWER SECTION GEAR BOX. (TC NR 20070515007) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081104 2008 11 4 CA070515008 4 20070515 G 6122 8210410 GOVERNOR BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE PROPELLER OUT OF RIG W O OTHER F FLT CONT AFFECTED LD LANDING 1 CA 6508 (CAN) ON NUMEROUS LANDINGS THE AC YAWED HARD TO THE LT. AFTER RIGGING THE SNAG WOULD GO AWAY FOR NUMEROUS LANDINGS THEN YAW AGAIN TO THE LT. MAINT REPLACED THE LT PROP GOVERNOR AND RETURNED THE ACFT TO SERVICE. TO DATE THE SNAG HAS NOT RE-O CCURED. (TC NR 20070515008) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2008022000049 20080220 00049 SW 2008 2 20 CA070516001 1 20070515 G 5310 712551 TUBE BBAVIA 7 7ECA 21101NN SW LYC O235 O235K2C 41505 EA SNSNCH 72C 72CK EA FUSELAGE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 3787 (CAN) WHILE PREFLIGHTING THE AC, THE PILOT NOTED WRINKLED FABRIC AT THE LOWER AFT END OF THE FUSELAGE. OPENING THE FABRI C REVEALED THAT THE VERTICAL TUBE THAT FORMS THE FIN SPAR AND IS THE ATTACH POINT FOR THE RUDDER HINGES AND TAILWHEEL SP RING AFT ATTACH WAS BROKEN THROUGH ABOUT AN INCH AND A HALF UP FROM ITS LOWER END, JUST ABOVE THE WELDED SKID ATTACHMENT . THERE IS NO EVIDENCE THAT THIS WAS CAUSED BY ANY FLIGHT LOADS OR HARD LANDINGS. SUSPECT THAT TAILWHEEL SHIMMY FLEX ED THE SKID PLATE ATTACHMENT IN A TORSIONAL MANNER AND CAUSED A FATIGUING OF THE TUBE AT THIS POINT, EVENTUALLY RESULTIN G IN ITS FAILURE. (TC NR 20070516001) 1 H 7 1 3O 3 O A759 E223 5 N P9045 2007080900036 20070809 00036 CE 2007 8 9 CA070516002 1 20070507 G 7810 2654008205 EXHAUST DUCT CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 837 (CAN) SECONDARY EXHAUST DUCT CRACKED ALONG THE SEAM ON THE OUTER SIDE FROM ABOUT .2500 THE LENGTH DOWN TO .7500 THE LENG TH, CAUSING SEVERAL SMALLER CRACKS TO FORM ALONG INITIAL CRACK 90 DEGREES FROM THE ORIGINAL BOTH ON THE UPPER AND LOWER SIDES. OTHER OPERATORS REPORTED THAT IT IS NOT UNCOMMON TO HAVE SOME CRACKING. (TC NR 20070516002) 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2007062200076 20070622 00076 EU 2007 6 22 CA070516003 1 20070514 G 6123 SOLENOID PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL FEATHERING SYS STUCK W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA 570 (CAN) PILOT INITIATED START FOLLOWING TURNAROUND AND NOTICED PROP RPM FOLLOWING START WAS ONLY AT 500 RPM AND NOT AT THE NORMAL, ABOVE 1000 RPM AT ENGINE IDLE. ALSO HAD EIS FLASHING AMBER AND RED ON EIS AS PROP WAS OPERATING BELOW 950 RPM. PROP WAS NOT COMING OUT OF FEATHER POSITION. PILOT SHUTDOWN ENGINE. INVESTIGATION REVEALED A STUCK OPEN PROP FEATHERING SOLENOID WHICH DID NOT ALLOW UNFEATHERING OF PROP. ONCE SOLENOID COOLED DOWN SOLENOID FUNCTIONED NORMALLY. REPLACED OVER SPEED GOVERNOR WITH REPAIRED AND TESTED UNIT. (TC# 20070516003) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008022000050 20080220 00050 SO 2008 2 20 CA070516004 1 20070505 G 2810 BLADDER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL FUEL TANK INCORRECT W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 7400 (CAN) AC IN FOR MAINTENANCE AND FUEL DRAINED FROM AC. DID NOT GET ANY FUEL FROM THIS QUICK DRAIN SO ADDED FUEL TO TANK A ND OBSERVED A FUEL LEAK AROUND THE COVER PLATE IN BOTTOM OF WING UNDER THE TANK AND LOCATION OF QUICK-DRAIN. MAINT REMOV ED COVER AND FOUND THE QUICK DRAIN NOT CONNECTED TO FUEL BLADDER. FOUND THAT SOMEONE HAD THREADED A BOLT INTO THE BLADDE R AND HAD REDUCED THE LENGTH OF CONNECTOR TO THE QUICK DRAIN SO THE COVER PLATE WOULD FIT BACK IN PLACE. NO SNAG ON AIRC RAFT ADDRESSING THIS AND NO WAY FUEL COULD HAVE BEEN SUMPED FROM THIS TANK. FUEL BLADDER TANK WAS REMOVED AND SERVICEABL E BLADDER INSTALLED. (TC NR 20070516004) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007061900115 20070619 00115 CE 2007 6 19 CA070517001 1 20070515 G 7920 77853 ADAPTER CESSNA 172 172N 2072434 CE LYC O360 O360A4A 41514 EA SNSNCH 76E 76EM8 EA ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA L1859236A (CAN) DURING GROUND RUN AFTER OVERHAUL, AN OIL LEAK WAS NOTICED ORIGINATING FROM THE LOWER RT ATTACH POINT OF THE OIL FI LTER ADAPTER. UPON CLOSE VISUAL INSPECTION A CRACK WAS FOUND IN THE RADIUS OF THE LOWER RT FLANGE. UNIT WAS REPLACED A ND LEAK CHECKED. (TC NR 20070517001) 1 H 7 1 3O 3 O NT 3A12 E286 5 N P4EA 2007062200077 20070622 00077 EA 2007 6 22 CA070517002 2 20070418 G 7200 O320D2J ENGINE CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 2280 L1088539A (CAN) INTERMITTENT VIBRATION AFTER UNUSUAL FLIGHT ATTITUDES DURING TRAINING. (TC NR 20070517002) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007062200078 20070622 00078 SW 2007 6 22 CA070517007 1 20070508 G 5730 9000351 WINGLET GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCC3Y HCC3YR2 NE WING SEPARATED W K NONE D INFLIGHT SEPARATION IN INSP/MAINT 1 CA (CAN) IT WAS FOUND THAT THE SHEET METAL SCREWS HOLDING THE TIP ON THE WING HAD ALL COME LOOSE. THE WING TIP THEN VIBRATE D FOR A PERIOD OF TIME ,ELONGATING THE SCREW HOLES IN THE WING UNTIL ALL OF THE SCREWS FELL OUT AND THE WING TIP DEPARTE D THE WING IN FLIGHT. THE PILOT DID NOT NOTICE ANYTHING ABNORMAL AND ONLY NOTICED IT WAS MISSING ON WALK AROUND. (TC NR 20070517007) 1 H 7 2 3O 3 O 6A1 1E4 5 C P25EA 2007061900116 20070619 00116 EU 2007 6 19 CA070518001 1 20070514 G 7603 355A57217007 LEVER AEROSP AS355 AS355F2 8680812 EU ALLSN 25OC 250C20R GL RT THROTTLE BROKEN W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 4995 (CAN) PART BROKE IN (2) PIECES JUST ABOVE ATTACHMENT POINT DURING ENGINE PRE-START CHECK PROCEDURES. (TC NR 20070518001) 1 G 7 2 3U 3 U H11EU E4CE 2007061900117 20070619 00117 NE 2007 6 19 CA070518002 2 20070516 G 8530 LW13622 INTAKE VALVE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE FRACTURED W C ABORTED TAKEOFF E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 567 (CAN) PILOT LANDED TO CONDUCT TASK AT WELL SITE. DURING ATTEMPTED START UP, THE AIRCRAFT WOULD NOT START. AFTER A SHORT TIME, THE PILOT ATTEMPTED AGAIN AND THE AIRCRAFT STARTED. IT RAN VERY ROUGH AND EXCESSIVE VIBRATIONS. PILOT TOOK THE ENGINE POWER UP TO CHECK IF THE ISSUE WAS MAGNETO`S. HE THEN SHUT IT DOWN. MAINTENANCE CONDUCTED FURTHER INVESTIGATION S AND FOUND CYLINDER NR 3 INTAKE VALVE HAD SNAPPED OR FRACTURED IN 3 PIECES. PORTION OF THE VALVE WAS FOUND IN THE INTAK E INDUCTION BOX. WILL NOTIFY WHEN FURTHER DETAILS ARE AVAILABLE. (TC NR 20070518002) 1 G 7 1 3O 3 O H11NM 1E4 20081104 2008 11 4 CA070518003 2 20070515 G 7322 206061716003 LEVER FCU MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSP, ENGINEER ATTEMPTED TO REPLACE FCU LEVER ON FCU NOT YET INSTALLED ON ACFT. INSTALLING BOLT P/N AN173-5 COULD NOT BE INSERTED THROUGH HOLE BORE OF LEVER. BORE FOUND UNDERSIZE AND REMOVED FROM SERVICE. (TC NR 20070518003) 2007061800162 20070618 00162 NE 2007 6 18 CA070518004 2 20070325 G 8520 48564 CASE DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 22D 22D30 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA JP207649 (CAN) ENGINE WAS OVERHAULED OCT 02,2005, ENGINE WAS REMOVED FROM STEEL SHIPPING CONTAINER FOR INSTALLATION MARCH 25, 200 7. CRACKS WERE FOUND ON THE REAR CASE AT THE IB HOLES FOR MAGNETO MOUNTING. THE ENGINE WAS SENT TO APPROVED AMO AND REPA IRED. FOLLOWING REPAIR ENGINE WAS INSTALLED IN AIRCRAFT . GROUND RUN FOR 30 SECONDS AND ENGINE SHUTDOWN DUE TO OIL LEAK FROM REAR CASE. VISUAL INSPECTION DISCOVERED THAT THE REAR CASE HAD (3) DISTINCT PIN HOLES THROUGH THE CASE IN THE AREA OF THE OIL SCREEN HOUSING. THE HOLES LOOKED LIKE CAUSED BY CORROSION. THE ENGINE WAS REMOVED AND IS TO BE SENT TO APPRO VED AMO FOR FURTHER REPAIR OR REPLACEMENT OF REAR CASE/BLOWER ASSY. (TC NR 20070518004) 1 H 7 1 3R 3 R RC A806 5E1 5 C P736 2007061900118 20070619 00118 NM 2007 6 19 CA070518005 1 20070516 G 7500 69474753 DUCT BOEING 727 727260 138408K NM PWA JT8 JT8D17 52049 NE BLEED AIR RUPTURED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE PERFORMING THE DAILY INSPECTION, MAINTENANCE PERSONNEL HEARD A LOUD BANG, WHICH WAS FOLLOWED BY A DROP IN AP U DUCT PRESSURE TO 0 PSI. UPON INSPECTION, 2 BLEED AIR DUCTS WERE FOUND RUPTURED, FORWARD OF THE APU LOAD CONTROL VALVE THAT CONNECT TO THE BLEED AIR BY-PASS VALVE. NO ADDITIONAL DAMAGE PROBLEMS WERE NOTED. NOTE: INFORMATION LISTED ABOVE I N AREA 9, BLOCK(B) PN. THE PN LISTED ARE FOR THE TWO DUCT ASSEMBLIES THAT WERE FOUND DAMAGED. DUCT P/N 69-47475-3 AND 69-47474-3 (TC NR 20070518005) 2 L 7 3 4F 4 F RT A3WE E2EA 2007062000013 20070620 00013 EA 2007 6 20 CA070518006 1 20070516 G 3260 864808 PSEU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE LANDING GEAR MALFUNCTIONED W O OTHER N FALSE WARNING CR CRUISE 1 CA 2864 (CAN) IN CRUISE FLIGHT CREW RECEIVED PROX SYS CHAN FAULT CAUTION MESSAGE AS WELL AS (3) RED GEAR INDICATIONS, IAW AFM HA D TO PERFORM ALTERNATE EXTENSION, FLIGHT LANDED WITHOUT INCIDENT. AFTER MAINTENANCE TROUBLESHOOTING THE MDC IS POINTED TOWARDS THE PSEU ITSELF. THE PSEU WAS REPLACED AND FUNCTION TESTS WERE CARRIED OUT AND GEAR SWINGS AND THE AIRCRAFT WAS RETURNED TO SERVICE. PRESENT AC HRS:24426:01 AND CYCLES: 20077 (TC NR 20070518006) 2 L 7 2 4F 4 F RT A21EA E15NE 2007062000014 20070620 00014 SW 2007 6 20 CA070518007 1 20070517 G 6510 MS150011 GREASE FITTING 407040303135 BELL 407 407 1182206 SW HANGAR BRGS LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 200 (CAN) WHILE THE SHAFT WAS REMOVED THE MECHANIC WENT TO WIPE THE HANGER BEARING GREASE FITTING AND THE FITTING CAME OFF I N HIS HAND. ALL OTHER HANGER BEARING GREASE FITTINGS WERE THEN CHECKED AND 4 OUT OF THE 6 WERE FOUND TO BE VERY LOOSE. THE ONES WE FOUND LOOSE WERE AS FOLLOWS: BOTH FWD AND AFT OIL COOLER BLOWER HANGER BEARINGS AND THE 4TH AND 6TH HANGER B EARINGS. (TC NR 20070518007) 1 G 7 1 3U O H2SW 2007062000015 20070620 00015 SW 2007 6 20 CA070518008 1 20070517 G 2810 457370 FUEL CAP FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE LT WING LEAKING W A UNSCHED LANDING K FLUID LOSS CL CLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF, THE CREW NOTICED THAT FUEL WAS LEAKING FROM THE LT WING FUEL CAP. THE CREW RETURNED TO BASE WITHOUT INCIDENT. THE AIRCRAFT WAS INSPECTED AND IT WAS DISCOVERED THAT THE FUEL CAP WAS DEFECTIVE. THE LARGE PLASTIC NUT AT THE BASE OF THE CAP ASSEMBLY IS HELD AT THE CORRECT TORQUE WITH THE USE OF A PIN THAT PASSES THROUGH THE NUT INT O THE BASES OF THE ASSEMBLY. THIS PIN WAS MISSING, WHICH ALLOWED THE NUT TO TURN WHEN THE FUEL CAP WAS OPENED AND CLOSE D. THE TORQUE ON THIS NUT SETS THE PROPER SEATING OF THE FUEL CAP. BECAUSE THE NUT BACKED OFF, THE FUEL CAP BECAME LOS E AND ALLOWED FUEL TO LEAK PAST THE FUEL CAP. THE FUEL CAP WAS REPLACED WITH AN IMPROVED CAP THAT IS DESIGNED TO PREVENT 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2007062000016 20070620 00016 NM 2007 6 20 CA070518009 1 20070516 G 2915 9752753 RELIEF VALVE BOMBDR CL600 CL6002D15 NM GE CF34 CF34* NE HYDRAULIC SYS MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 3105 1230 (CAN) ON PUSHBACK FROM GATE CREW RECEIVED NOSE STEERING INOP MESSAGE. AIRCRAFT STEERING MEL`D. AFTER TAKEOFF GEAR FAILED TO RETRACT. AIRCRAFT RETURNED TO ORIGINATING AIRPORT FOR NORMAL LANDING. MAINTENANCE TROUBLESHOOTING REPLACED HYD BALAN CE RELIEF VALVE, NR 3 HYD SYSTEM BLED, GEAR SWINGS COMPLETED, AIRCRAFT RETURNED TO SERVICE. (NOTE: PART AT LAST REPAIR H AD BEEN RETURNED TO VENDOR AS CAUSING NOSE STEERING INOP (1875HR/853CY TSN) (TC NR 20070518009) 2 L 7 2 4F 4 F RT A21EA E15NE 2007062000017 20070620 00017 EA 2007 6 20 CA070520001 1 20070520 G 3230 LANDING GEAR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE COLLAPSED W O OTHER O OTHER LD LANDING 1 CA (CAN) UPON ARRIVAL CREW HAD A SUSPECTED HARD LANDING, STAB TRIM AURAL WARNING CLACKER SOUNDED AND BOTH MAIN GEAR COLLAPS ED. THERE WAS MAJOR STRUCTURAL DAMAGE AND PRELIMINARY REVIEW OF PICTURES SHOWS EXCESSIVE ENGINE BLADE DAMAGE DUE TO DEBI S INGESTION, FURTHER UPDATE TO FOLLOW. TSB HAS PULLED THE FDR AND CVR. PRESENTLY INVESTIGATION IS UNDERWAY AND WILL UP DATE FURTHER WHEN COMPLETE. (TC NR 20070520001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007062000018 20070620 00018 EA 2007 6 20 CA070521001 1 20070520 G 3230 LANDING GEAR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE COLLAPSED W O OTHER O OTHER LD LANDING 1 CA (CAN) UPON ARRIVAL, CREW HAD A SUSPECTED HARD LANDING. STAB TRIM AURAL WARNING CLACKER SOUNDED AND BOTH MAIN GEAR COLLAP SED. THERE WAS MAJOR STRUCTURAL DAMAGE AND A PRELIMINARY REVIEW OF THE PICTURES SHOWS EXCESSIVE ENGINE BLADE DAMAGE DUE TO DEBRIS INGESTION. THE FDR AND CVR HAVE BEEN PULLED BY TSB AND AN INVESTIGATION IS UNDERWAY. NO PICTURES AVAILABLE TO THE FSR AS OF YET. (TC NR 20070521001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007062000019 20070620 00019 EA 2007 6 20 CA070521002 1 20070514 G 2740 70609 CONTROL UNIT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE HORIZ STAB MALFUNCTIONED W B H A EMER. DESCENT DEACTIVATE SYST/CIRCUITS UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 CA (CAN) THERE WAS A STAB TRIM RUNAWAY EVENT THAT OCCURRED. AN EMERGENCY WAS DECLARED AND A RETURN TO BASE. FURTHER AC DAMA GE AFTER SUCCESSFUL LANDING. BASED ON THE ATTACHED CREW REPORT, IT WAS A STAB TRIM RUNAWAY NOSE DOWN EVENT. PLEASE NOTE THAT A DFDR DOWNLOAD WAS CARRIED OUT ON THIS AC AND A COPY OF THIS DOWNLOAD WILL BE SENT TO THE APPROPRIATE PEOPLE WITH IN MFG AS SOON AS IT BECOMES AVAILABLE TO ME. THE NTSB ADVISED THAT THE FAA HAS REPORTED THIS AIRCRAFT DECLARED AN EMER GENCY DUE TO A STABILIZER TRIM PROBLEM. THE AIRCRAFT WAS ON A SCHEDULED FLIGHT WHEN THE STAB TRIM RUNAWAY FAULT OCCURRE D. THE NTSB ALSO REPORTED THAT THE CREW FOLLOWED THE QRH PROCEDURES AND AIRCRAFT REACHED A NOSE-DOWN ATTITUDE BY THE TI 2 L 7 2 4F 4 F RT A21EA E15NE 2007062000020 20070620 00020 EU 2007 6 20 CA070522001 1 20070518 G 7110 V40GT3911AA SPRING 10562648 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENGINE COWLING BROKEN W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) COMING OUT OF A MAJOR INSPECTION WHERE THE EJECTION SPRING ON ALL THE COWLS (P/N 105-62648, 105-62664, 105-62643 A ND 105-62663) WERE REPLACED, SEVERAL EJECTION SPRING P/N V40GT39-1-1AA WERE BREAKING IN TWO PIECES. THIS PROBLEM HAPPEN ED STATICALLY AND IN FLIGHT. THESE EJECTION SPRINGS WERE ORDERED NEW FROM MFG AND RECEIVED ON DEC 22/06. BATCH NR S2006 02192. (TC NR 20070522001) 1 G 7 2 3U 3 U H3EU E4CE 2007062000021 20070620 00021 WP 2007 6 20 CA070522002 1 20070519 G 3213 369H60022 STRUT HUGHES 369H600132 HUGHES 369 369E 4470707 WP ALLSN 250C 250C20B 03013 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN ANNUAL INSPECTION OF THE AIRCRAFT IT WAS NOTICED THAT THE LANDING GEAR HAD SOME PLAY IN IT. UPON FURTHE R INSPECTION THE ENGINEER FOUND THAT THE BRACE TO STRUT BOLT HAD SOME SLOP IN IT. THE ENGINEER REMOVED THE BRACE BOLT A ND FOUND 3 CRACKS EMMITTING FROM THE BLACE BOLT HOLE ON THE AFT RT LANDING GEAR STRUT. ONE CRACK ON THE TOP OF THE STRU T AND 2 CRACKS ON THE BOTTOM OF THE STRUT. (TC NR 20070522002) 1 G 7 1 3U 3 U H3WE E4CE 2007062000022 20070620 00022 SO 2007 6 20 CA070522003 2 20070507 G 8520 653058 CAMSHAFT CONT IO520 CESSNA 180 180K 2072624 CE CONT O520 O520* SO MCAULY D3A34 D3A34C403 GL ENGINE SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 1087 821995R (CAN) IN REMOVING NR 1 CYLINDER TO BE CHANGED OUT THE LIFTERS WERE REMOVED TO BE BLEED DOWN, LIFTERS WERE SPAWLED. THE A ME INSPECTED THE CAM AND THE EXHAUST LOBE WAS ALSO SPALLED. THE ENGINE WAS REMOVED AND PREPARED FOR SHIPMENT TO A REPAIR SHOP. UNDER FURTHER INVESTIGATION WE FOUND OTHER LOBES AND LIFTERS WITH SPALLING. OUR HYPOTHESIS IS LACK OF ENGINE USE CAUSING INTERNAL CORROSION/RUST WICH LEAD TO FAILURE (TC NRIN 20070522003) 1 H 7 1 3O 3 O 5A6 E5CE 5 C P47GL 2008022000051 20080220 00051 SW 2008 2 20 CA070522004 1 20070522 G 6220 407310101101 BEARING BELL 407010100 BELL 407 407 1182206 SW ALLSN 250C 250C47B GL MAIN ROTOR SEPARATED W K NONE O OTHER IN INSP/MAINT 1 CA 1493 LK37 (CAN) COMPLETE FAILURE/SEPARATION OF SHEAR BEARING ELASTOMERIC LAMINATIONS (4 OF 4). FOUND AT INSPECTION. SHEAR BEARING P/N 407-310-100-115. S/N 8345, 8325, 8109, 8113. (TC NR 20070522004) 1 G 7 1 3U 3 U O H2SW E1GL 2007062000023 20070620 00023 EA 2007 6 20 CA070522005 2 20070521 G 7250 TURBINE WHEEL PWC PT6A65B BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL ENGINE UNKNOWN W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 4137 (CAN) ECTM TREND INDICATED ENGINE ITT WAS INCREASING WITH TIME. ENGINE SPLIT. CT WHEEL NOTED AS CONTACTING THE GUIDE VAN E ASSY. ENGINE TO BE SENT TO MFG TO INVESTIGATE. (TC NR 20070522005) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2008022000052 20080220 00052 CE 2008 2 20 CA070522006 1 20070520 G 2731 10552002221 CONTROL CABLE BEECH 76 76 1153005 CE LYC O360 O360A1G6D EA HARTZL HCM2Y HCM2YR GL ELEVATOR TRIM FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AIRCRAFT WAS IN THE HANGER FOR INSPECTION. AN INSPECTION WAS BEING STARTED IN THE AFT TAIL AREA. THE AME APPRENTIC E NOTICED THE ELEVATOR TRIM CABLE SEVERELY FRAYED WHERE IT WRAPPED AROUND THE TRIM SERVO. THE CABLE WAS REMOVED AND REPL ACED WITH A NEW PART (TC NR 20070522006) 1 L 7 2 3O 3 O A29CE E286 5 C P43GL 2008022000053 20080220 00053 CE 2008 2 20 CA070523001 1 20070522 G 7920 3391000015 LINE BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO MCAULY 3A32C 3A32C406 GL OIL SYSTEM FRACTURED W A UNSCHED LANDING K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 8334 (CAN) OIL PRESSURE LINE FRACTURED AT FIREWALL CAUSING AN OIL LEAK ON THE INSIDE OF THE FIREWALL. LINE APPEARS TO BE HA RD FROM AGE. AIRCRAFT LANDED WITHOUT ANY FURTHER PROBLEMS. (TC NR 20070523001) 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 2008022000054 20080220 00054 CE 2008 2 20 CA070523002 1 20070518 G 2120 EM6303 BLOWER BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE CABIN SEIZED W G O2 MASK DEPLOYED B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) WHILE ENROUTE, THE AC CABIN AND COCKPIT FILLED UP WITH SMOKE FROM WHAT SMELLED ELECTRICAL IN NATURE. OXYGEN WAS US ED AND THE AC FINISHED ITS TRIP AND LANDED (DESTINATION WAS CLOSER THAN TO TURN AROUND). MAINT WAS CALLED AND AN AC WAS DISPATCHED TO CONTINUE THE DAY. SYSTEMS WERE CHECKED, NO FAULTS WERE FOUND. THE AC WAS RETURNED TO BASE WITH NO PASSENGE RS ON BOARD. UPON FURTHER INSP AT THE BASE, IT WAS FOUND THAT ONE OF THE CABIN VENT BLOWERS WAS SEIZED AND THE (2) SPEED ADJUSTING RESISTORS INSTALLED ON THE BLOWER WERE WARPED AND MELTED FROM HEAT. THE VENT BLOWER WAS REPLACED AND THE AC W AS RETURNED TO SERVICE. (TC NR 20070523002) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2007062000024 20070620 00024 EA 2007 6 20 CA070523003 1 20070523 G 2810 UNKNOWN 21564075 CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE FUEL SYSTEM CRACKED W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 1850 546 (CAN) LEAK AT (3) LOWER CORNERS NEAR INTERCONNECTS. DROPS 9180 (TC NR 20070523003) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2008031900139 20080319 00139 NM 2008 3 19 CA070523004 1 20070410 G 4930 69254518 SHUTOFF VALVE AMD FALC50 FALCON2000 2730170 NM PWC PW308 PW308C 52182 NE APU OPEN W O OTHER A B FLAME/FIRE SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 118 118 P439 (CAN) WHILE PREPARING FOR A DEPARTURE. APU FAILED TO START. APU NEVER ACCEL`D PAST 13 PERCENT ON FIRST ATTEMPT AND LARGE AMOUNT OF FUEL VAPOR EMITTED FROM EXHAUST. NEAR THE END OF START ATTEMPT, BRIEF FLAME AND SMOKE EVIDENT AT EXHAUST PIPE EXIT. AFTER ALLOWING TIME FOR TRAPPED FUEL TO DRAIN, 2ND START ATTEMPTED. THIS TIME NO ACCEL PAST APPROX 10 PERCENT AND FIRE AND SMOKE EMITTING FROM TAILPIPE AND TAILCONE UPPER AIRSCOOPS. FIRE SELF EXTINGUISHED PRIOR TO DISCHARGE OF FIRE B OTTLES. INITIAL INDICATIONS FALSELY LED US TO TROUBLESHOOT POSSIBLE A/C ELECTRICAL PROBLEM DUE TO ABNORMALLY HIGH START AMPERAGES AND VOLTAGE INDICATIONS. BOTH AIRFRAME AND APU MFG TECH REPS INVOLVED IN THE (4) DAY TROUBLESHOOTING PROCESS. 2 L 7 2 4F 4 F RT A50NM E00065EN 2007062000025 20070620 00025 EA 2007 6 20 CA070523005 1 20070523 G 2810 215640022 FLUID 215640022 CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE FULE SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1849 540 (CAN) LEAK AT LOWER CORNERS NEAR INTERCONNECTS. (TC NR 20070523005) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 20081104 CE 2008 11 4 CA070523006 1 20070430 G 3246 08A01156027 GUSSET CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL FLOAT ASSY MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 15 (CAN) AS THE RESULT OF BUMPING A DOCK, THE FWD BULKHEAD HAD TO BE REPLACED ON THE LT FLOAT ASSY ON THE ACFT. AFTER GAIN ING ACCESS, IT WAS FOUND THAT THE AREA WHICH IS NOT NORMALLY ACCESSED HAD SEVERAL PARTS RIVETED AS PART OF THE STRUCTURE HAD NO PROPER EDGE DISTANCE ON THE RIVETS. FURTHER INVESTIGATION FOUND THE OTBD GUSSET WAS PAINTED OVER WITH PRC HIDING THE FACT THAT THE HOLES WERE DRILLED ONLY HALF ON THE GUSSET. QC HAS BEEN ADVISED OF THE PROBLEM AND SUPPLIED REPLACEM ENT PARTS, AND IS IN REVIEW OF QUALITY INSP PROCEDURES TO VERIFY WHY THIS HAPPEND SO IT WILL NOT HAPPEN AGAIN. ADVISED OF A POSSIBLE ENGINEERING CHANGE ON THE PART TO INCREASE IT`S SIZE SLIGHTLY TO GET THE REQUIRED EDGE DISTANCE. THERE WER 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2008012900017 20080129 00017 WP 2008 1 29 CA070523007 1 20070521 G 6210 PIN HUGHES HUGHES 369 369A 4470503 WP ALLSN 250C 250C20B 03013 GL M/R BLADE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 3885 0098848293 (CAN) PIN FOUND BROKEN AT FIRST THREAD / SHANK. NUT WAS CAPTURED IN THE HANDLE CLIP. 1 G 7 1 3U 3 U H3WE E4CE 2007062200079 20070622 00079 GL 2007 6 22 CA070523008 1 20070504 G 2720 C2CF1777A ARM DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE RUDDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK FOUND IN WELD RADIUS ON OB SIDE OF CABLE ATTACH ARM. (TC NR 20070523008) 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2007062000026 20070620 00026 NE 2007 6 20 CA070524001 2 20070517 G 7314 PUMP TA7 BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE FUEL SYSTEM FAILED W A UNSCHED LANDING J WARNING INDICATION DE DESCENT 1 CA 1743 662AL3381 (CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPERATIONS, UPON DESCENT WITH AN EXTERNAL LOAD: THE MASTER CAUTION WARNING I NDICATION WAS ILLUMINATED. THE LOAD WAS SET AND RELEASED. THE CAUTION PANEL OBSERVED TO REVEAL THAT THE ENGINE DRIVEN F UEL PUMP WARNING LIGHT WAS ON. THE P/C IMMEDIATELY ABORTED ANY FURTHER OPERATIONS AND RETURNED TO THE SERVICE LANDING WH ICH WAS APPROXIMATELY ONE KILOMETER AWAY AND THE NEAREST SUITABLE LANDING SIGHT. A NORMAL LANDING AND ENGINE SHUTDOWN WA S CARRIED OUT. TROUBLESHOOTING BY THE AME AT SERVICE FOUND THAT IT WAS A POSITIVE INDICATION THAT ONE OF THE TWO PUMP EL EMENTS HAD FAILED TO DELIVER FUEL PRESSURE. AD 2006-11-16, 1250 HOUR MAIN AND SECONDARY DRIVE SHAFT AND PUMP GEAR SPLIN 1 G 7 1 4U 4 U H1SW E17EA 2007062000027 20070620 00027 EU 2007 6 20 CA070524002 1 20070522 G 2424 243211 GCU AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE NR 1 FAILED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 157 (CAN) DURING DEPARTURE THE NR 1 AC WILD SYSTEM WENT OFF LINE. WHEN THE CREW ATTEMPTED A RESET THE (BLUE) HYDRAULIC SYSTE M WENT OFF LINE. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND CARRIED OUT A NORMAL LANDING. MAINTENANCE REPLACED THE NR 1 AC WILD GCU. AFTER WHICH THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070524002) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2007062000028 20070620 00028 EA 2007 6 20 CA070524003 1 20070524 G 3246 C3UF1085 STRUT DHAV 557170 DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL FLOAT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ANNUAL INSPECTION A (4 TO 5) CRACK WAS FOUND. THE CRACK PROPAGATED COMPLETELY THROUGH THE BOTTOM CENTER OF THE STRUT LEG BETWEEN THE LOWER ATTACH POINTS. THE STRUT LEG WAS REMOVED AND REPLACED. PICTURES ON FILE AT REPAIR STATIO N. (TC NR 20070524003) 1 H 7 1 3R 4 T A815 E4EA 6 C P15EA 2007062000029 20070620 00029 EA 2007 6 20 CA070524004 1 20070523 G 3240 10100199 SENSOR CNDAIR CL600 CL600* 1900302 EA GE CF34 CF34* NE NR 1 BRAKE CORRODED W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA 5781 5781 (CAN) DURING CRUISE CREW RECEIVED BRAKE OVERHEAT WARNING , LT OUTER BTMS SHOWING INCREASING BRAKE TEMP UP TO 20 UNITS, T HEN STARTED TO DECREASE. AIRCRAFT DESCENDED TO LOWER ALTITUDE AND SPEED SLOWED. BRAKE TEMP STARTED TO RISE TO 18 UNITS. GEAR EXTENDED, BRAKE TEMPS RETURNED TO NORMAL GREEN INDICATION. RETURNED TO ORIGINATING AIRPORT, NORMAL LANDING. MAINTEN ANCE FOUND NR 1 BRAKE TEMP SENSOR HAD CORRODED PINS. BRAKE TEMP SENSOR REPLACED. AIRCRAFT RETURNED TO SERVICE. (NOTE: PA RT IS AN EXPENDABLE AND SYSTEM DOES NOT TRACK COMPONENT TIME. TIMES PROVIDED ARE AIRCRAFT TOTAL TIME.) (TC NR 2007052400 4) 2 L 7 2 4F 4 F RT A21EA E15NE 2007062000030 20070620 00030 2007 6 20 CA070524005 1 20070519 G 2710 82740162001 LINK ASSY PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU RT AILERON BROKEN W O OTHER F FLT CONT AFFECTED IN INSP/MAINT 1 CA 795 (CAN) WHEN DOING WP8 INSPECTION TASK 000-057-640-500 GVI OF THE (RT) AILERON ASSY. MAINTENANCE FOUND LINK ASSY P/N 82740 162-001 FROM THE RT AILERON LVDT BROKEN. (TC NR 20070524005) 4 T E00062EN 6 C P17BO 2007062200080 20070622 00080 NE 2007 6 22 CA070524006 2 20070517 G 7200 CT581402 ENGINE SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE NR 1 FAILED W B EMER. DESCENT X ENGINE FLAMEOUT CR CRUISE 1 CA 22313 102 295130C (CAN) REPORT NR 07-02204 (ON MAY 11, 2007) THE AC UNDERWENT AN ENGINE CHANGE ON NR 1 ENGINE AND REQUIRED A MAINTENANCE T EST FLIGHT. AFTER (2) GROUND RUNS INCLUDING LEAK CHECKS, DEPARTED TO THE TRAINING AREA TO PERFORM REQUIRED ENGINE TOPPIN G CHECK. VERIFIED WEATHER CONDITIONS AT 2000 FT, PA AND DESCENDED TO 1000 FT PA TO BEGIN CHECK. WITH NR 2 ENGINE SSL PU LLED BACK TO 94 PERCENT NF AND NR 1 ENGINE AT FULL THROTTLE WE NOTED ENGINE VALUES CLIMBING THROUGH 2000 PA. LEVELED AIR CRAFT OFF TO CHECK EMERGENCY FUEL LEVER RIGGING AND THE CO-PILOT INCREASED EMERGENCY FUEL LEVER TO MAXIMUM AFTER DECREAS ING NR1 ENGINE SSL TO ABOVE GOVERNING RANGE. TOPPING VALUES WERE ON TARGET FOR NR 1 ENGINE AND THE CO-PILOT SLIGHTLY RE 2 G 7 2 4U 4 U 1H15 1E3 2007062000031 20070620 00031 EA 2007 6 20 CA070524007 1 20070520 G 2752 735619C COUPLING DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE T/E FLAP TORN W K NONE J WARNING INDICATION LD LANDING 1 CA (CAN) CREW REPORTED (FLAP DRIVE) CAUTION LIGHT ILLUMINATED DURING FLAP EXTENSION , FLAPS CONTINUED TO MOVE. NORMAL LANDI NG. MAINTENANCE INSPECTION FOUND FLAP SECONDARY CENTER DRIVE COUPLING TORN FROM MOUNTING BRACKET AND LYING IN RT ARMPIT. FLAP SECONDARY CENTER DRIVE SECTION (CORE AND HOUSING) REPLACED, FLAP SECONDARY DRIVE CENTER COUPLING REPLACED. MOUNTIN G BRACKET REPLACED. FLAP SECONDARY DRIVES CLEANED AND LUBRICATED. AIRCRAFT RETURNED TO SERVICE. NOTE: FLAP SECONDARY DR IVE INSPECTION AND LUBRICATION TASKS (1500HR INTERVAL) LAST COMPLETED 791HR / 949CY PREVIOUS. (TC NR 20070524007) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081104 WP 2008 11 4 CA070524008 1 20070523 G 6310 V31001 SWITCH ROBSIN C0511 ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA CLUTCH ACTUATOR FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA 349 (CAN) DURING AN INSP, CLUTCH ACTUATOR FAILED TEST AND CLUTCH WOULD NOT ENGAGE DUE TO MICROSWITCH FAILURE. CLUTCH REPLACE D AND CHECKED SERVICEABLE. (TC NR 20070524008) 1 G 7 1 3O 3 O H11NM E295 2007062000032 20070620 00032 EA 2007 6 20 CA070525001 1 20070525 G 3233 2158500116 ACTUATOR 2158500116 CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE LANDING GEAR FAILED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA H213 (CAN) THE NEWLY OVERHAULED ACTUATOR FAIL THE FUNCTIONAL CHECK AFTER INSTALLATION, IT DOESN’T STAY LOCKED WITH HYDRAULIC PRESSURE REMOVED. (TC NR 20070525001) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2007062000033 20070620 00033 NE 2007 6 20 CA070525002 2 20070511 G 7210 MS949034 BOLT PWC 311276701 PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE ENGINE FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 946 946 83D248 (CAN) ENGINE WAS REMOVED AFTER THE PILOT REPORTED THAT A LOUD BANG AND SHUDDER WAS EXPERIENCED BY THE AIRCRAFT DURING CL IMB IN AUTOPILOT NEAR TAKEOFF POWER APPROXIMATELY 5 MINUTES AFTER TAKEOFF AT 6000 FT. THE REDUCTION GEARBOX CHIP DETECT OR WAS ILLUMINATED AND THE AIRCRAFT RETURNED BACK TO BASE AT LOW POWER WITH NO OTHER ABNORMALITIES OBSERVED. ALL GROUND OPERATIONS WERE NORMAL. THE DATE OF THE INCIDENT WAS MAY 11, 2007. DURING INVESTIGATION DISMANTLE OF THE POWER SECTIO N AND FIRST-STAGE REDUCTION CARRIER ASSEMBLY, OF (6) MACHINE HEX BOLTS (IPC P/N 3038338, CH. 72-11-00, FIGURE 4, ITEM 20 0, P/N MS9490-34) WAS FOUND WITHOUT THE BOLT HEAD ATTACHED. NOTE THAT THE CARRIER HEX BOLTS SECURE THE FIRST-STAGE CARR 1 L 7 1 3T 4 T RT A78EU E26NE 2007062200081 20070622 00081 EU 2007 6 22 CA070525003 1 20070524 G 3230 A1029E BOLT BAG JETSTM JETSTM3101 1500215 EU GARRTT TPE331 TPE33110U 01514 WP MCAULY 4HFR34 4HFR34C652 NE NLG SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NLG RETRACTION JACK MOUNT UPPER IB MOUNTING BOLT SHEARED. DISCOVERED DURING SCHEDULED NLG RETRACTION, JACK ATTACH BOLT INTEGRITY INSPECTION. ALL MOUNTING BOLTS REPLACED WITH NEW. (TC NR 20070525003) 2 L 7 2 4T 4 T RT A21EU E4WE 6 C 3PNE 2007062200082 20070622 00082 NE 2007 6 22 CA070528001 2 20070521 G 7250 TURBINE CFMINT 71200011 AIRBUS A319 A319112 3930323 EU CFMINT CFM56 CFM565A3 NE ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN E VIBRATION/BUFFET CL CLIMB 1 CA 733107 (CAN) WAITING FOR SHOP TEAR DOWN, SUSPECTED FAILURE CAUSES BUT NOT CONFRIMED ARE NR 4 BEARING OR HPT BLADE. ENG TT 2646 2, CYC 12034, TSI 13977, CSI 6250. (TC NR 20070528001) 2 L 7 2 4F 4 F RT A28NM E29NE 2007080900038 20070809 00038 EU 2007 8 9 CA070528002 1 20070511 G 3230 9740926112 RELAY PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL MLG FAULTY W O OTHER O OTHER NR NOT REPORTED 1 CA 3047 (CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN. THE NOSE LANDING GEAR IN TRANSIT LIGHT WAS SLOW TO EXTINGUISH. UP ON MAINTENANCE TROUBLESHOOTING THE HYDRAULIC PUMP WAS FOUND TO BE INTERMIITTENTLY CUTTING OUT. THE LANDING GEAR RELAY W AS REPLACED AND NO FURTHER ADNORMALITIES WERE REPORTED. (TC NR 20070528002) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007062200083 20070622 00083 GL 2007 6 22 CA070528003 3 20070319 G 6114 4716 HUB MCAULY D2A34C58 CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3399 647 740488 (CAN) PROPELLER RECEIVED FOR OVERHAUL AT 10 YEARS CALENDAR TIME, FOUND HUB THREADS CRACKED, FOUND ONE BLADE THREAD CRACK ED, FOUND ONE BLADE RETENTION NUT CRACKED. FAA AD 91-15-04 APPLIED TO THIS PROPELLER FOR INITIAL INSPECTION AND MODIFIC ATION WHICH HAD BEEN ACCOMPLISHED (TC NR 20070528003) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2007061800163 20070618 00163 NM 2007 6 18 CA070528004 1 20070307 G 3244 TIRE AIRBUS A319 A319114 3930350 NM CFMINT CFM56 CFM565A3 NE NLG DEFLATED W O OTHER O OTHER AP APPROACH 1 CA (CAN) ON APPROACH AT 5000 FT CREW HEARD LOUD BANG, AIRCRAFT LANDED WITHOUT INCIDENT, FLIGHT CREW SUSPECTED A BIRD STRIKE . AT ARRIVAL GATE MAINTENANCE FOUND LT NOSE WHEEL TIRE DEFLATED AND OFF THE RIM. BOTH NOSE WHEEL ASSEMBLIES REPLACED, SH OP FOUND THAT THE LT NOSE WHEEL ASSEMBLY OVER INFLATION VALVE HAD BLOWN. NO EVIDENCE OF A BIRD STRIKE WAS FOUND. (TC NR 20070528004) 2 L 7 2 4F 4 F RT A28NM E29NE 2007062200084 20070622 00084 GL 2007 6 22 CA070528005 3 20070319 G 6114 4716 HUB MCAULY D2A34C58 CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1563 690816 (CAN) PROPELLER RECEIVED FOR OVERHAUL AT 10 YEARS CALENDAR TIME, AT THAT TIME THE PROPELLER HAD BEEN INSPECTED IAW AIRWO RTHINESS MANUAL PART VI APPENDIX C (4). THE LAST OVERHAUL COMPLETED WAS JUNE 1987. THE PROPELLER HAD EXCEEDED THE MFG HARD TIME OF 1,500 HOURS BETWEEN OVERHAULS. FOUND HUB THREADS CRACKED. FAA AD 91-15-04 APPLIED TO THIS PROPELLER FOR IN ITIAL INSPECTION AND MODIFICATION WHICH HAD BEEN ACCOMPLISHED. (TC NR 20070528005) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2007062200085 20070622 00085 GL 2007 6 22 CA070528006 3 20070301 G 6111 S90AT4 BLADE MCAULY D2A34C58 CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 890 890 736835 (CAN) PROPELLER RECEIVED FOR OVERHAUL AT 10 YEARS CALENDAR TIME, AT THAT TIME THE PROPELLER HAD BEEN INSPECTED PER AIRWO RTHINESS MANUAL PART VI APPENDIX C (4). THE LAST OVERHAUL COMPLETED WAS OCTOBER 1991. FOUND BOTH BLADE THREADS CRACKED. FAA AD 91-15-04 APPLIED TO THIS PROPELLER FOR INITIAL INSPECTION AND MODIFICATION WHICH HAD BEEN ACCOMPLISHED. (TC NR 20070528006) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2007062200120 20070622 00120 EA 2007 6 22 CA070528007 1 20070526 G 3234 750006000 SELECTOR VALVE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE NLG WW UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) CLIMBING THROUGHT 13000 FT AT 290 KIAS, THE NLG DOOR WARNING/UNSAFE MESSAGE WAS DISPLAYED AND CREW COULD HEAR A CL UNKING NOISE FROM THE NLG AREA. ELECTED TO RETURN. MLG EXTENDED NORMALLY WITH (3) GREEN LIGHTS AND NO CAUTION/ADVISORY MESSAGES DISPLAYED. AIRCRAFT LANDED AND TAXIED TO THE GATE WITHOUT FURTHER PROBLEM. TROUBLESHOOTING WAS IN PROGRESS AND FOUND THE LANDING GEAR SELECTOR VALVE WAS UNSERVICEABLE. PART WAS REPLACED, FUNCTION CHECK FOUND NO FURTHER DEFECT. AIR CRAFT RETURNED FOR SERVICE (TC NR 20070528007) 2 L 7 2 4F 4 F RT A21EA E15NE 2007062200121 20070622 00121 EU 2007 6 22 CA070528008 1 20070413 G 7933 RP22100 SENSOR CFMINT CFM565C4 AIRBUS A340 A340313 EU CFMINT CFM56 CFM565C4 13802 NE OIL SYSTEM INOPERATIVE W E ENGINE SHUTDOWN M OVER TEMP AP APPROACH 1 CA 27909 15670 741603 741603 (CAN) NR 2 ENGINE OIL TEMPERATURE HIGH, 30 MILES FROM AIRPORT, ENGINE SHUTDOWN IAW QRH PROCEDURES, AIRCRAFT LANDED WITHO UT INCIDENT. ENGINE OIL TEMP SENSOR AND FUEL RETURN VALVE REPLACED, NO SUBSEQUENT FAULTS AFTER PARTS CHANGED. (TC NR 200 70528008) 2 L 7 4 4F 4 F RT A197 E37NE 2008013100034 20080131 00034 EA 2008 1 31 CA070528009 2 20070527 G 7310 3032791 LINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL LT ENG FUEL CHAFED W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA (CAN) FUEL FLOW TRANSMITTER LINE P/N 3032791 FOUND CHAFED. NEW PART ON ORDER. (TC NR 20070528009) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007062200122 20070622 00122 NM 2007 6 22 CA070528010 1 20070526 G 2530 UNKNOWN BOEING 767 767333 1385301 NM GE CF6 CF680C2B6F 30025 NE GALLEY MALFUNCTIONED W H DEACTIVATE SYST/CIRCUITS O OTHER CR CRUISE 1 CA (CAN) A FLIGHT ATTENDANT RECEIVED AN ELECTRIC SHOCK FROM THE WATER DISPENSER IN THE REAR GALLEY. COFFEE MAKERS REMOVED, GALLEY WIRING INSPECTED AND CONTINUITY CHECK CARRIED OUT (L-4355954). MORE IT TROUBLESHOOTING STEPS HAVE BEEN PROVIDED BUT NOT COMPLETED YET. (TC NR 20070528010) 2 L 7 2 4F 4 F RT A1NM E13NE 2008013100035 20080131 00035 CE 2008 1 31 CA070528011 1 20070528 G 5610 PPG10138402522 WINDSHIELD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL LT COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) CO-PILOTS WINDSCREEN CRACKED UNDER PRESSURIZED CONDITION. AIRCRAFT RETURNED TO BASE FOR WINSHEILD REPLACEMENT. UNA BLE TO INDICATE CORRECT MFG. (NOT IN LIST) (TC NR 20070528011) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2008031900140 20080319 00140 CE 2008 3 19 CA070528012 1 20070524 G 2435 300SGC12902 STARTER GEN CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE RIGHT UNSERVICEABLE W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CL CLIMB 1 CA 771 DC0074 (CAN) RT ENGINE GENERATOR FAILED WHICH ILLUMINATED THE GENERATOR FAIL LIGHT. AC RETURNED TO BASE. (TC NR 20070528012) 2 L 7 2 4F 4 F RT A22CE E00053EN 2007080900039 20070809 00039 EU 2007 8 9 CA070528013 1 20070522 G 3251 1855A000003 MODULE EMB ERJ190 ERJ190100IGW 3260408 EU GE CF34 CF3410E6 30015 NE NLG STEERING MALFUNCTIONED W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA 2829 (CAN) STEERING FAIL MESSAGE ON FINAL APPROACH, FLIGHT DID 2 MISSED APPROACHES FOR GEAR RECYCLING, LANDED ON THIRD CYCLIN G OF GEAR. FLIGHT HISTORY DATA BASE DOWNLOADED, MFG REP FOUND STEERING CONTROL MODULE AT FAULT. ACFT THR 3643, TCY 1663 (TC NR 20070528013) 2 L 7 2 4F 4 F RT A57NM E00070EN 2008031900141 20080319 00141 EU 2008 3 19 CA070528014 1 20070527 G 7120 7254120511 MOUNT SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A 30030 NE ROTOL R389 R3894123F25 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE AFT ENGINE MOUNT BRACKET WAS DISCOVERED TO BE CRACKED DURING A SCHEDULED ENGINE CHANGE. THE AFFECTED BRACKET W AS REPLACED WITH A SERVICEABLE UNIT. NO FURTHER ACTION NOTED. (TC NR 20070528014) 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P30NE 2007062200123 20070622 00123 WP 2007 6 22 CA070529001 2 20070529 G 7250 30606901 TURBINE BLADES GARRTT TFE73120R1B LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP RT ENGINE MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 2232 2232 P111221C (CAN) DURING A DAILY INSPECTION, IT WAS NOTICED BY THE TECHNICIAN THAT A PIECE OF A BLADE FROM THE RT ENGINE TURBINE WAS MISSING. NO DIFFICULTIES HAD BEEN REPORTED BY THE FLIGHT CREW AND NO OTHER DAMAGE HAS BEEN NOTED ON THE ENGINE. THE ENG INE WILL BE REMOVED AND SENT FOR REPAIR TO AN OUTSIDE ENGINE SHOP. (TC NR 20070529001) 2 L 7 2 4F 4 F RT T00008WI E6WE 2008020400157 20080204 00157 EU 2008 2 4 CA070529002 1 20070528 G 6220 704A3363320851 SPHERICAL STOP SNIAS AS350B2 SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE M/R HEAD MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 CA 13 2785 (CAN) ALL SPHERICAL STOPS WHERE REPLACED DURING A 500 HRS INSPECTION. PILOT REPORTED UNCONTROLLED STICK MOVEMENT DURING HYDRAULIC OFF TEST. WITH HYDRAULIC ON, NO PROBLEM WAS REPORTED. DURING TROBLESHOOTING THIS PROBLEM IT WAS FOUND THAT ONE OF THE SPHERICAL STOP BEARINGS PREVIOUSLY INSTALLED HAD A MFG DESIGN PROBLEM. THE PRESET ANGLE ATTACH BOLT WHICH ATTAC H TO THE STARFLEX WAS FOUND NOT IAW SPEC WHICH INDUCED AN UNCONTROLLED STICK MOUVEMENT DURING HYDRAULIC OFF TEST. THIS PART WAS RETURNED TO MFG FOR EXCHANGE UNDER WARRANTY (TC NR 20070529002) 1 G 7 1 3U 3 U H9EU E19EU 2007062200124 20070622 00124 NE 2007 6 22 CA070529003 2 20070527 G 8500 ENGINE DOUG DC4 C54EDC 3021528 WP PWA R2000 R20007M2 52023 NE HAMSTD 23E 23E50 NE MAKING METAL W E ENGINE SHUTDOWN O OTHER CL CLIMB 1 CA (CAN) ENGINE REMOVED DUE TO METAL IN OIL SCREEN, TBO 750 HOURS. ENGINE BEING SENT OUT FOR OVERHAUL. (TC NR 20070529003) 2 L 7 4 4R 4 R A762 5E5 6 C P603 2007080900040 20070809 00040 NM 2007 8 9 CA070529004 1 20070507 G 3010 29S7D524007 BOOT DORNER DO32 DO328100 2996000 NM DE-ICE SYSTEM LOOSE W O OTHER O OTHER NR NOT REPORTED 1 CA 55 (CAN) PILOTS REPORTED LT HORIZONTAL STAB DE-ICE BOOT APPEARS LOOSE. MAINTENANCE INSPECTED THE BOOT AND FOUND THE DE-ICER BOOT HAD COME LOOSE FROM THE AIRCRAFT AT THE AFT EDGES. THE ADHESIVE (3M 1300L) DID NOT SECURE THE DEICER BOOT TO STAB. THE DEICER BOOT WAS RECENTLY REPLACED UNDER WORK ORDER 15249. TIME ON PART 54.6 HOURS AND 73 LANDINGS. DEICER BOOT REP LACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070529004) 2 H 7 2 4T RT A45NM 2007080900041 20070809 00041 CE 2007 8 9 CA070529005 1 20070511 G 5531 07310292 SPAR CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO HARTZL HCC3Y PHCC3YF1 GL VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4534 (CAN) DURING AN ANNUAL/100 HOUR INSPECTION FIN AFT SPAR WAS FOUND CRACKED. MFG SINGLE ENGINE CUSTOMER CARE SERVICE INFOR MTION LETTER SE 80-85 ADDRESSES THIS PROBLEM. SERVICE KIT SK 185-25A INSTALLED THIS DATE. (TC NR 20070529005) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P25EA 2007062200125 20070622 00125 SO 2007 6 22 CA070529006 2 20070507 G 8520 646778 CONNECTING ROD CONT IO520D CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL ENGINE DESTROYED W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 174942R (CAN) DURING FLIGHT, THE ENGINE BEGAN TO RUN ROUGH. THE AIRCRAFT MADE AN UNSHEDULED LANDING FOR INSPECTION. THE CRANKCAS E WAS FOUND CRACKED AT THE NR 2 CYLINDER. THE ENGINE WAS REMOVED FROM THE AIRCRAFT. (TC NR 20070529006) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2007080900042 20070809 00042 CE 2007 8 9 CA070529007 1 20070529 G 2701 4527102070001 WASHER LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP CONTROL COLLUMN FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 2158 (CAN) DURING A SCHEDULE INSPECTION THE PILOT CONTROL WHEEL WAS FOUND TO HAVE MORE FREE PLAY THAN THE CO-PILOT. UPON FURT HER INVESTIGATION IT WAS FOUND THAT THE TAB WASHER P/N 4527102070-001 WHICH IS SECURING THE NUT P/N NAS1423-20. HAD ONLY ONE TAB BENT, TO ADD TO THE PROBLEM THE TAB WAS IMPROPERLY BENT. AFTER A WHILE THE TAB PERMITTED THE NUT TO BACK OFF ON E FLAT GIVING THE FREE PLAY TO THE CONTROL WHEEL. IT WAS FOUND IN THE MM, CHAPTER 27-10-01 PAGE 202 SECTION B) 9. BEND THE WASHER TABS TO THE NUT FLATS. ONLY ONE TAB WAS BENT, PERMITTING THE NUT TO BACK OFF, THE CO-PILOT CONTROL WHEEL WAS INSPECTED FOR PROPER INSTALLATION AND FOUND TO BE DONE CORRECTLY. THE TAB WASHER WILL BE REPLACED PRIOR TO RETURNING TH 2 L 7 2 4F 4 F RT T00008WI E6WE 2008022000055 20080220 00055 EU 2008 2 20 CA070529008 1 20070528 G 2932 MA12401 PRESSURE SWITCH SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE HYDRAULIC SYSTEM DEFECTIVE W D RETURN TO BLOCK P NO WARNING INDICATION IN INSP/MAINT 1 CA (CAN) SWITCH REMAINED OPEN AND WOULD NOT ACTIVATE THE HYDRAULIC PRESSURE WARNING HORN. (TC NR 20070529008) 1 G 7 1 3U 3 U H9EU E19EU 2007080900043 20070809 00043 2007 8 9 CA070530001 4 20070529 G 3422 25863333 GYRO CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE DIRECTIONAL DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE COMPLETION OF AN UNASSOCIATED SB IT WAS NOTICED THAT THE C-12 GYRO HAD FREED ITSELF OF ITS MOUNTING. UN TIL NOW NO COMPARATOR ANNUNCIATIONS OR COMPASS RELATED SNAGS HAD BEEN REPORTED OR DETECTED. (TC NR 20070530001) 1 L 7 2 4F 4 F A22CE E1NE 20081104 2008 11 4 CA070530002 4 20070530 G 2562 CIR112 ELT BEECH 100 100BEECH 1152916 CE GARRTT TPE331 TPE3316252B 01514 WP HARTZL HCB4T HCB4TN5 GL CABIN FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN TESTING ELT FOR THE REQUIREMENT OF CAR 571 APPENDIX G FOUND G SWITCH WOULD NOT ACTIVATE. (TC NR 20070530002) 1 L 7 2 3T 4 T A14CE E2WE 6 C P40EA 2007061800166 20070618 00166 EA 2007 6 18 CA070530003 2 20070320 G 8520 CRANKSHAFT CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA (CAN) ON THE WAY BACK TO THE AIRPORT THE ENGINE DEVELOPED ABNORMAL VIBRATIONS AND THE PILOT DECIDED TO CLIMB TO 2,400 FT , THEN THE ENGINE SUDDENLY STOPPED. THE PILOT DECIDED TO FORCE LAND ON THE AUTO ROUTE IN A WESTERLY DIRECTION. AFTER INS PECTION, IT WAS DETERMINED THAT THERE WAS NO LOSS OF OIL AND THAT THE PROP WAS UNABLE TO TURN. THE ENGINE CRANKSHAFT WAS THE CAUSE OF FAILURE. (TC NR 20070530003) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2007062200126 20070622 00126 NE 2007 6 22 CA070530004 2 20070528 G 7261 36022375 SEAL PWA PW121 AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE NR 1 ENGINE LEAKING W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA PCE120714 PCE120714 (CAN) WHILE CONDUCTING AN ACCEPTANCE CHECK FLIGHT, THE CREW OBSERVED A LOW OIL PRESSURE CONDITION ON THE NR 1 ENGINE. TH E CREW CONDUCTED A PRECAUTIONARY SHUTDOWN OF THE ENGINE AND RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PR OBLEM. MAINTENANCE DETERMINED THE NR 1 STARTER GENERATOR DRIVE SEAL WAS LEAKING. THE SEAL WAS REPLACED AND THE AIRCRAF T RETURNED TO SERVICE AFTER SATISFACTORY GROUND RUN. (TC NR 20070530004) 2 H 7 2 4T 4 T RT A53EU E20NE 2007081000094 20070810 00094 CE 2007 8 10 CA070530005 1 20070520 G 3010 SMR517515 BOOT CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE HARTZL HCB3T HCB3TN3 GL DE-ICE SYSTEM WORN W O OTHER O OTHER NR NOT REPORTED 1 CA 252 (CAN) DE-ICE BOOT, FOUND WORN RUBBER THAT WAS MELTED FROM EXHAUST GASES. MINOR BLISTERING FOUND ON TOP RT OF BOOT. (TC N R 20070530005) 1 H 7 1 3T 3 T A37CE E4EA 6 C P15EA 2007062200127 20070622 00127 NM 2007 6 22 CA070530006 1 20070530 G 2134 WARNING SYSTEM BOEING 727 727225 1384077 NM CABIN PRESSURE ACTIVATED W J A DUMP FUEL UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER DEPARTURE, WHEN AT 13,000 FEET ALT WARNING HORN SOUNDED AND COULD NOT BE SILENCED WITH THE HORN CUTOUT. CREW TRIED SWITCHING TO STBY WITH NO RESULTS. HORN CONTINUED ON APPROACH. AT TIME OF INITIAL HORN, CABIN PRESSURE WAS 5000 F T AND 5PSI DIF. THE AIRCRAFT DUMPED FUEL FOR THE LANDING AND LANDED SUCCESSFULLY AND RETURNED TO THE RAMP. THE MAINTENAN CE PERSON CARRIED OUT MM SYSTEM TESTS WITH NO FAULTS. AIRCRAFT WAS GROUND PRESSURIZED AND AGAIN NO FAULTS. THE CREW ATTE MPTED A SECOND DEPARTURE AND HAD THE WARNING COME ON AT 9000 FT. AIRCRAFT RETURNED TO DEPARTURE POINT AND IS AOG WHILE T ROUBLESHOOTING IS IN PROGRESS. OPERATOR WILL ADVISE SDR REPORTING OF RECTIFICATION WHEN IT IS ESTABLISHED. (TC NR 200705 2 L 7 3 4F A3WE 20081104 2008 11 4 CA070530007 4 20070530 G 2562 AK450 ELT AMTR F1156 F1156C 5910310 GL LYC O540 IO540* 41532 EA MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN TESTING ELT FOR THE REQUIREMENT OF CAR 571 APPENDIX G FOUND LITTLE OR NO AUDIO MODULATION. UNIT WAS TRANSMITT ING RF CARRIER ONLY. (TC NR 20070530007) 1 H 7 1 3O 3 O NC EXPA1H71 1E4 2007062000034 20070620 00034 EA 2007 6 20 CA070531001 1 20070527 G 5610 NP13932111 WINDSHIELD CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C1 NE COCKPIT CRACKED W B A EMER. DESCENT UNSCHED LANDING O OTHER CR CRUISE 1 CA 9395 (CAN) CREW NOTED THAT LT W/S CRACKED IN CRUISE FLT (40,000FT) AND DIVERTED FOR MTX NO OTHER PROBLEMS NOTED. C/A REMOVED AND REPLACED LT WINDSHIELD IAW MM 56-11-01. REF LGPG 2330059 ITEM 1, 2, AND 3 FOR OK TO INSTALL, FUNCTIONAL CHECK AND O PS CHECK. END (TC NR 20070531001) 2 L 7 2 4F 4 F RT A21EA EOOO63EN 2007062000035 20070620 00035 NE 2007 6 20 CA070531002 2 20070524 G 7200 CF343A1 ENGINE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE RIGHT VIBRATION W E A ENGINE SHUTDOWN UNSCHED LANDING E D F VIBRATION/BUFFET INFLIGHT SEPARATION FLT CONT AFFECTED CR CRUISE 1 CA 5800 (CAN) AIRCRAFT (FLT 4344) WAS ENROUTE WHEN CREW EXPERIENCED AN UNCONTROLLABLE VIBRATION FROM THE RT ENGINE. THE ENGINE W AS SHUTDOWN IN FLIGHT. THE AIRCRAFT WAS DIVERTED AND LANDED AT TRI. IT WAS REPORTED BY THE CREW (TO MAINT CONTROL) THA T THE RT THROTTLE WAS BINDING NEAR FLIGHT IDLE BUT THEY WERE ABLE TO PERFORM A SHUTDOWN. IN ADDITION, IT WAS REPORTED T HAT PARTS OF THE COWL/NACELLE HAVE DEPARTED THE AIRCRAFT. (TC NR 20070531002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007062000036 20070620 00036 NM 2007 6 20 CA070531003 1 20070530 G 3411 PITOT SYSTEM BOEING 727 727260 138408K NM PWA JT8 JT8D17 52049 NE PITOT/STATIC SYS OBSTRUCTED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA (CAN) THE AIRCRAFT BEGAN THE TAKEOFF ROLL WHEN THE FLIGHT CREW NOTICED A LAG IN THE FIRST OFFICERS AIR SPEED INDICATION. THE TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE GATE WITH NO ADDITIONAL PROBLEMS. UPON INSPECTION OF THE FIRST OFFICERS PITOT INSTALLATION AN OBSTRUCTION WAS FOUND (BUG/INSECT) AND WAS REMOVED. THE PITOT STATIC SYSTEM WAS TESTED I AW THE AIRPLANE MM WITH NO FURTHER FAULTS. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070531003) 2 L 7 3 4F 4 F RT A3WE E2EA 2007062200128 20070622 00128 EU 2007 6 22 CA070531004 1 20070530 G 2120 UNKNOWN AIRBUS 330 A330243 3930330 EU RROYCE RB211 RB211* 54555 NE CABIN ODOR W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) DURING FLIGHT, A PAPER BURNING SMELL AT SEAT 26DE WAS REPORTED TO THE CABIN CREW. THE AUDIO SYSTEM WAS SHUTOFF IAW PRECAUTION AND SMELL DISAPPEARED AFTER 20 MINUTES. THE AUDIO SYSTEM WAS TESTED ON ARRIVAL AND THE AREA INSPECTED FOR BU RNING MARKS. AUDIO SYSTEM AND AREA WAS FOUND NORMAL WITH NO DEFECT. AIRCRAFT WAS RETURN TO SERVICE WITH NO REPEAT. (TC NR 20070531004) 2 L 7 2 4F 4 F RT A46NM A12EU 2007062200129 20070622 00129 NE 2007 6 22 CA070531005 2 20070425 G 7313 3186100 VALVE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE ENGINE MALFUNCTIONED W O OTHER X ENGINE FLAMEOUT IN INSP/MAINT 1 CA (CAN) ASSEMBLY IS ON CONDITION. AFTER CARRYING OUT A 100 HR AND 300 HR INSPECTION A FUNCTIONAL CHECK WITH THE INJECTOR ELECTRO VALVE (IEV) WAS ACCOMPLISHED. FOLLOWING A RUN-UP TO 100 PERCENT, THE ENGINE RPM WAS REDUCED AND STABILIZED AT JU ST OVER FLIGHT IDLE FOR 30 SECONDS IAW COOL DOWN REQUIREMENTS. DEPRESSION OF THE STARTER BUTTON AT THIS POINT SHOULD NOT HAVE CAUSED ANY PROBLEM BUT IN THIS FUNCTIONAL CHECK A FLAME OUT OCCURRED. FOLLOWING THE FLAME OUT A BENCH TEST WAS CAR RIED OUT AND IT WAS DETERMINED THAT IT`S OPERATION AT A PRE DETERMINED P2 PRESSURE WAS INTERMITTENT. SENT UNIT TO MFG FO R REPAIR OR OVERHAUL AND THE UNIT WAS SCRAPPED. (TC NR 20070531005) 1 G 7 1 3U 3 U H9EU E19EU 2008022000319 20080220 00319 WP 2008 2 20 CA070531006 1 20070529 G 6310 C0183 CLUTCH ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE TRANSMISSION SEIZED W D RETURN TO BLOCK O OTHER AP APPROACH 1 CA 948 948 (CAN) LOUD BANG DURING POWER CHANGE ON APPROACH. INSPECTED AC AND FOUND CLUTCH ASSY ROUGH. TURNED IT A FEW TIMES BY HA ND AND SEIZED. NEW CLUTCH ASSY INSTALLED, DEFECT RECTIFIED. CLUTCH BEING SENT TO OUR IN HOUSE COMPONENT SHOP FOR INVESTI GATION. WILL FWD THE PICTURES AND INFORMATION WHEN RECEIVED FROM THE COMPONENT SHOP. PICTURES ATTACHED AND CLUTCH ASSY BEING SENT TO MFG FOR WARRANTY AND INVESTIGATION. (TC NR 20070531006) 1 G 7 1 3O 3 O H11NM 1E4 2007062200130 20070622 00130 NE 2007 6 22 CA070531007 2 20070425 G 7313 3186100 VALVE SNIAS 350 AS350B1 8680811 EU TMECA ARRIEL ARRIEL1D 60048 NE ENGINE MALFUNCTIONED W O OTHER X ENGINE FLAMEOUT IN INSP/MAINT 1 CA (CAN) ASSEMBLY ON CONDITION. THIS UNIT WAS REMOVED SERVICEABLE FOR ANOTHER AIRCRAFT. A FUNCTIONAL CHECK WAS CARRIED OUT. FOLLOWING A RUN UP TO 100 PERCENT THE ENGINE RPM WAS REDUCED AND STABILIZED AT JUST OVER FLIGHT IDLE FOR 30 SECONDS IAW COOL DOWN REQUIREMENTS. DEPRESSION OF THE STARTER BUTTON AT THIS POINT SHOULD NOT HAVE CAUSED ANY PROBLEM BUT IN THIS FUNCTIONAL CHECK A FLAME OUT OCCURED. A BENCH WAS CARRIED OUT WITH CONSISTENT FAILURES OCCURRED AT PRESCRIBED P2 PRESSUR E. (TC NR 20070531007) 1 G 7 1 3U 3 U H9EU E19EU 2007062200131 20070622 00131 SO 2007 6 22 CA070601001 1 20070528 G 5330 SKIN LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL HAMSTD 54H 54H60117 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING PRE-FLIGHT CHECK PRIOR TO DEPARTING, CRACKING WAS OBSERVED IN THE AFT FUSELAGE SKIN IN THE AREA OF STATION 946. THE AIRCRAFT HAS BEEN FERRIED FOR REPAIR. (TC NR 20070601001) 2 H 7 4 4T 4 T A1SO E282 6 C P906 2007071100287 20070711 00287 EA 2007 7 11 CA070601002 1 20070531 G 2420 820465 ADG CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE DEPLOYED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 6118 6118 (CAN) ADG DEPLOYED AS THE LANDING GEAR WAS SELECTED UP. THE FLIGHT RETURNED WITHOUT INCIDENT. MAINTENANCE TROUBLESHOOT ING WAS CARRIED OUT AND THE ADG AUTO DEPLOY CONTROLLER WAS REPLACED AND TESTED SERVICEABLE. THE ADG WAS INSPECTED VISUAL LY IAW MFG AND IS TO HAVE FLUORESCENT PENETRANT CARRIED OUT WITHIN 3 CALENDAR DAYS. (TC NR 20070601002) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022000320 20080220 00320 SW 2008 2 20 CA070601003 1 20070528 G 2810 2060636321 FUEL CELL BELL 206 206L1 1182107 SW ALLSN 250C 250C28 03013 GL LEAKING W O OTHER K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) FUEL SMELL NOTED. INSPECTION FOUND SMALL FUEL LEAK. FUEL CELL REMOVED SENT OUT FOR REPAIR, REINSTALLED. (TC NR 200 70601003) 1 G 7 1 3U 3 U H2SW E1GL 2007071100286 20070711 00286 EA 2007 7 11 CA070601004 1 20070529 G 2797 WIRE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE TE FLAPS BURNED W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) FLAP FAIL MESSAGE COME ON DURING CRUISE AT ALT FL330 WITH NO FLAP SELECTION MADE. AIRCRAFT RETURN TO ORIGINATING STATION, MAINTENANCE REPLACED THE BPSU AND FECU BUT NO FIX. FURTHER INVESTIGATION REVEALED SOME BURNED WIRES AT LT BPSU CONNECTOR. TEMPORARY REPAIRS CARRIED OUT AND AIRCRAFT FERRIED. AIRCRAFT IS NOW UNDERGOING A HEAVY CHECK AND THE SNAG IS STILL BEING WORKED ON. MORE SPECIFICS OF THE DEFECT RECTIFICATION TO FOLLOW. (TC NR 20070601004) 2 L 7 2 4F 4 F RT A21EA E15NE 2007062200132 20070622 00132 SW 2007 6 22 CA070604001 1 20070603 G 6320 23063393 GEARBOX ALLSN 250C47B BELL 407 407 1182206 SW ALLSN 250C 250C47B GL MAIN ROTOR SEIZED W R AUTOROTATION J Y WARNING INDICATION ENGINE STOPPAGE CR CRUISE 1 CA 6077 CAE847124 CAE847124 (CAN) ENGINE CHIP ILLUMINATED, APPROX 3-4 SECONDS LATER ENGINE FAILED. (TC NR 20070604001) 1 G 7 1 3U 3 U O H2SW E1GL 2007071100284 20070711 00284 GL 2007 7 11 CA070604002 2 20070518 G 7320 FADEC BELL 407 407 1182206 SW ALLSN 250C 250C47B GL MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A FLIGHT ON MAY 18 AT 6755.9 TAT, THE PILOT EXPERIENCED A CONTROLLED ENGINE OVERSPEED CONDITION. THE PILOT WAS NOT GIVEN AT INDICATION IAW MFG FM CRITERIA. LATER THE PILOT REPORTED THE CONDITION TO THE AME. THE AME DOWN LOADE D THE FADEC INFORMATION AND THE FOLLOWING WERE NOTED. 38060 NP AND 53.3 PERCENT Q. WHICH IS ACTUALLY 80 RPM BELOW THE POINT WHERE THE PILOT WOULD GET A LIGHT BUT OVER THE LIMITS IN MM 72-00-00 AND 77-50-00. THE AIRCRAFT WAS REMOVED FROM SERVICE AND RETURNED TO THE MAIN MAINTENANCE BASE UNDER A TC FLIGHT PERMIT. THE ENGINE HAS BEEN REMOVED AND SENT TO MFG FOR INSPECTION. (TC NR 20070604002) 1 G 7 1 3U 3 U O H2SW E1GL 2008022000321 20080220 00321 WP 2008 2 20 CA070604003 1 20070526 G 2435 32991 LINK ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE STARTER GEN CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING 100HR INSPECTION FOUND CRACKED STARTER GENERATOR LINK. (TC NR 20070604003) 1 G 7 1 3O 3 O H11NM 1E4 2007071100282 20070711 00282 NE 2007 7 11 CA070605001 2 20070603 G 7321 FCU AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE NR 2 ENGINE INOPERATIVE W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB AFTER DEPARTURE, THE CREW OBSERVED A SLOW DECREASE IN TORQUE ON THE NR 2 ENGINE AND WITH REDUCED FUEL FLOW. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE NR 2 FUEL CONTROL UNIT (FCU) AND RETURNED THE AIRCRAFT TO SERVICE AFTER SATISFACTORY GROUND RUN. (TC NR 20070605001) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2007071100281 20070711 00281 NE 2007 7 11 CA070605002 2 20070512 G 7320 3035381A LINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HMU-P3 CRACKED W O OTHER R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) THE NR 2 ENGINE WAS SNAGGED AS NOT PRODUCING FULL POWER ON TAKEOFF AND IN FLIGHT. MAINTENANCE FOUND THAT THE P3 SE NSE LINE WAS CRACKED AT THE HYDRO MECHANICAL UNIT. UPON REMOVAL, THE LINE BROKE. THE SENSE LINE WAS REPLACED AND THE AI RCRAFT RETURNED TO SERVICE. (TC NR 20070605002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007071200127 20070712 00127 EA 2007 7 12 CA070605003 2 20070601 G 8520 LW15328 MAIN BEARING LYC O360E1A6D PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC2Y HCC2YR2 GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 3690 RL38277T (CAN) MAIN BEARING FAILED DUE TO EXCESSIVE TSO. CRANKCASE DAMAGED BEYOND REPAIR. VERY CLOSE TO HAVING A COMPLETE ENGINE FAILURE. (TC NR 20070605003) 1 L 7 2 3O 3 O A19S0 E286 5 C P920 20081229 CE 2008 12 29 CA070605004 1 20070605 G 2730 05341221 BELLCRANK CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA ELEVATOR MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 CA 8805 (CAN) ELEVATOR UP TRAVEL FOUND TOO LOW. INVESTIGATION REVEALED UP CABLE ATTACH BOLT INSTALLED WRONG WAY. THIS RESULTED I N CONTACT WITH VERT STAB ATTACH BRACKET (WHERE CABLE PASSES THROUGH LIGHTENING HOLE)THUS LIMITING TRAVEL BY APPROX 3 DEG LESS THAN REQUIREMENT. BOLT INSTALLED PROPERLY AND SYSTEM RETURNED TO SERVICE. 1 H 7 1 3O 3 O NT 3A12 E274 2007081000095 20070810 00095 SO 2007 8 10 CA070605005 1 20070605 G 5340 4178902 ATTACH BOLT PIPER PA42 PA42720 7104212 SO PWA PT6 PT6A61 52043 EA HARTZL HCB3T HCB3TN3 GL MLG ACTUATOR BENT W K NONE O OTHER IN INSP/MAINT 1 CA 202 (CAN) CONTINUOUS PROBLEM OF PREMATURE WEAR AND INDICATIONS OF STRESS ON MAIN LANDING GEAR ACTUATOR ATTACH HARDWARE. LOW ER FORK BOLT PN 41789-02 AND UPPER ACTUATOR ATTACH BOLT 401-195 (AN5-17A) (BOTH LIFE LIMITED BY MFG INSPECTION PROGRAM) SHOW SIGNS OF BENDING AND/OR WEAR VIRTUALLY EACH DETAILED GEAR INSPECTION (TYPICALLY 200 AIRCRAFT HOURS). THESE PARTS AR E REMOVED AND CLOSELY INSPECTED EACH GEAR INSPECTION AND TYPICALLY REPLACED AT FAR LOWER INTERVALS THAN THE PUBLISHED LI FE LIMITS. (TC NR 20070605005) 1 L 7 2 4T 4 T A23SO E4EA 6 C P15EA 2007081000096 20070810 00096 SW 2007 8 10 CA070606002 1 20070602 G 2910 2781032261 LINE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE HYD SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) HYD LEAK IN RT WHEEL WELL. FOUND LINE CHAFED, LINE REPLACED AND AIRCRAFT RETURNED TO SERVICE AFTER SUCCESSFUL GEA R SWINGS CARRIED OUT. (TC NR 20070606002) 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 2007071200128 20070712 00128 WP 2007 7 12 CA070606003 2 20070605 G 7250 TURBINE BLADES GARRTT TPE33112UHR FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE ENGINE FAILED W E ENGINE SHUTDOWN E VIBRATION/BUFFET CR CRUISE 1 CA 5510 5510 P70224 (CAN) THE AIRCRAFT WAS ON A SHORT REPOSITIONING FLIGHT. AFTER AN UNEVENTFUL TAKEOFF AND CLIMB, THE CREW LEVELED AT 9,00 0 FT AND REDUCED POWER TO 30 PERCENT. FIVE MINUTES LATER, THE RT ENGINE HAD A VIOLENT AND SUDDEN VIBRATION. THE CREW S HUTDOWN THE ENGINE IMMEDIATELY AND DECLARED AN EMERGENCY. THE AIRCRAFT MADE AN UNEVENTFUL LANDING. MAINTENANCE INSPECTE D THE ENGINE AND FOUND THAT THE NR 3 TURBINE WHEEL HAD (4) BLADES MISSING LARGE SECTIONS. THE OIL FEED LINE WAS SEVERED AND IMPACT DAMAGE WAS FOUND ON THE EXHAUST CONE AND TAIL PIPE. THE LAST MAJOR INSPECTION ON THIS ENGINE WAS A HSI/GBI AT 3499.2 HOURS. (TC NR 20070606003) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081104 EA 2008 11 4 CA070606004 1 20070605 G 3233 HF6G ROD END DHAV DHC3 DHC3 2800202 EA WALTER M601 M601E11 EU ACTUATOR BROKEN W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) PILOT COULD NOT GET GEAR DOWN INDICATION, BUT COULD GET GEAR UP AND LOCKED INDICATION. WATER LANDING CARRIED OUT. MAINT FOUND LT NOSE GEAR WOULD NOT EXTEND. ROD END FOUND BROKEN ON NOSE GEAR ACTUATOR, REPLACED AND ACFT RETURNED TO SER VICE. (TC NR 20070606004) 1 H 7 1 3R 3 T A815 E00048EN 2007071200129 20070712 00129 EA 2007 7 12 CA070606006 2 20070601 G 8530 LW12966 CYLINDER LYC TIO540A2C PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 1636 (CAN) LT ENGINE, NR 5 CYLINDER WAS FOUND TO HAVE LOW COMPRESSION DURING THE INSPECTION PROCESS. EXCESSIVE AIR WAS PASS ING THE RINGS. CYLINDER WAS FOUND TO BE GLAZED. CYLINDER WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. WILL UPDATE WITH CYLINDER HOURS. (TC NR 20070606006) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007081000097 20070810 00097 CE 2007 8 10 CA070607001 1 20070530 G 3230 BEARING CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE UPLOCK ROLLER WORN W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA 7559 40 (CAN) AC WAS UNABLE TO LOWER THE RT MAIN LANDING GEAR. THE EMERGENCY EXTENSION PROCEDURE DID NOT INITIALLY RELEASE THE L ANDING GEAR UPLOCK. SUBSEQUENT MANIPULATION OF THE SYSTEM RELEASED THE GEAR TO A DOWN AND LOCKED CONDITION AND THE AIRCR AFT MADE A SAFE LANDING. MAINTENANCE INVESTIGATION REVEALED (2) CONDITIONS WHICH CONTRIBUTED TO THIS SITUATION. IT WAS N OTED DURING INSPECTION OF THE SYSTEM THAT THE EMERGENCY EXTENSION CABLE WAS CONTACTING THE BRAKE ASSY IN SUCH A WAY THAT THE CABLE WAS BEING DEFLECTED APPROXIMATELY .2500 INCH AND COULD PREMATURELY PULL THE HOOK OFF THE ROLLER. THE CONCERN IS THAT THE CABLE MAY FRAY AND BREAK PREVENTING MANUAL EXTENSION OF THE GEAR. THIS WAS NOT A FACTOR IN THIS CASE. INV 1 L 7 2 4F 4 F A22CE E1NE 2008031900142 20080319 00142 CE 2008 3 19 CA070607002 1 20070606 G 2410 359553S8 RETAINING NUT MOTORCRAFT CESSNA 210 210R 2073458 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL ALTERNATOR SHAFT MISSING W O OTHER B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 CA 1 97043226 (CAN) PILOT HAD CALLED AND REPORTED THAT THE ALTERNATOR THAT WE HAD REPLACED THE NIGHT BEFORE HAD GONE OFFLINE .7 HRS AN D A SLIGHT ODOR OF BURNING RUBBER NOTED INTO HIS FIRST LEG OF FLIGHT. UPON LANDING INVESTIGATION HAD REVEALED THAT THE A LTERNATOR SHAFT FAN RETAINING NUT HAD COME LOOSE AND EXITED THE AC. FAN HAD ROTATED ON SHAFT AND DRIVE BELT HAD COME OF F. NO DAMAGE TO ANYTHING IN ENG COMPARTMENT EXCEPT TO ALTERNATOR COMPONENTS. THIS ALTERNATOR HAD BEEN REPAIRED AND TESTE D BY A COMPANY, WHICH I WILL NOT NAME THAT THIS HAS HAPPENED BEFORE. THE FAN HAD ALSO COME OFF THE SHAFT, POSSIBLY DUE T O INSUFFICENT TORQUE ON RETAINING NUT OR SELF LOCKING ABILITY OF NUT WAS NOT SUFFICENT. SERVICEABLE ALTERNATOR INSTALLED 1 H 7 1 3O 3 O RT 3A21 E5CE 5 C P47GL 2007071100155 20070711 00155 EA 2007 7 11 CA070607003 2 20070511 G 8530 05K21108 CYLINDER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1279 L896061A (CAN) DURING A VISUAL INSPECTION OF THE ENGINE, A CRACK WAS FOUND UNDERNEATH THE PUSHROD TUBE. THE CRACK WAS RUNNING FR OM THE BASE OF THE CYLINDER HEAD ALONG THE BOTTOM OF THE COOLING FINS TOWARDS THE HEAD. THE CRACK IS SIMILAR TO THAT FRO M SDR 20070423005. (TC NR 20070607003) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007071100156 20070711 00156 EA 2007 7 11 CA070607004 2 20070515 G 8530 05K21108 CYLINDER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1744 RL145668A (CAN) WHILE INSPECTING THE ENGINE, A CRACK WAS FOUND IN THE PUSHROD TUBE AREA OF THE NR 2 CYLINDER. IT WAS AT THE BASE OF THE COOLING FINS AND RAN FROM THE BOTTOM OF THE CYLINDER HEAD TOWARDS THE TOP OF THE CYLINDER. THE CRACK STARTS WHER E THE CYLINDER HEAD IS ATTACHED TO THE BARREL. THIS IS SIMILAR TO THE EVENTS IN SDR`S 20070607003 AND 20070423005. (T C NR 20070607004) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007071100158 20070711 00158 GL 2007 7 11 CA070607005 1 20070528 G 8011 AN33711 RELAY DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985* 52008 NE HARTZL HCB3R HCB3R304 GL STARTER FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) JUST AFTER TAKEOFF, PILOT NOTICED FAINT SMOKE ODOR BUT UNSURE OF SOURCE, CONTINUED. DURING CLIMB WHITE SMOKE CAME IN AROUND RUDDER PEDALS SO PILOT SHUTDOWN ELECTRICS AND PROCEEDED TO LAND AIRCRAFT. AFTER LANDING PILOT NOTICED SMOKE COMING FROM THE ACCESSORY SECTION BUT IT DIMINISHED RAPIDLY AND THERE WERE NO SIGNS OF FIRE. UPON FURTHER INSPECTION BY MAINTENANCE STAFF, THE STARTER (PN 756-21C) SHOWED SIGNS OF OVERHEATING AND WAS REPLACED. THE STARTER RELAY (PN AN3371- 1) WAS ALSO REPLACED. UPON EVALUATION OF THE RELAY THE FOLLOWING WAS NOTED: CLOSE AT 5 VDC OPEN AT 0 VDC TESTED COIL RE SISTANCE 9.1 OHMS OILY UNDER COVER, SCREWS AND GASKETS CONTACT A1 SHOWS SIGNS OF RECENT STICKING CONTACT SHOWS ARCING AR 1 H 7 1 3R 3 R RC A806 5E1 5 C P28EA 2007081000098 20070810 00098 CE 2007 8 10 CA070607006 1 20070606 G 5100 AE366372460330 HOSE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL UNKNOWN LEAKING W O OTHER K FLUID LOSS NR NOT REPORTED 1 CA 1 1 (CAN) HOSE PN-AE366372460330 REPLACED DUE TO SHEDULED MAINTENANCE AND LEAK CHECKED SERVICEABLE, AFTER 1.4 HRS AND 4 CYCL ES FOUND LEAKING DURING GROUND HANDLING. HOSE REPLACED AND LEAK CHECKED SERVICEABLE (TC NR 20070607006) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2007081000099 20070810 00099 CE 2007 8 10 CA070607008 1 20070607 G 3230 MS2124010C40 UPLOCK ROLLER CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE MLG WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CAMPAIGN NOTICE 851-32-40-040 AND 851-32-40-040R1 CARRIED OUT. ACTION WAS REQUIRED TO THE RT MAIN GEAR BEARING P/N MS21240-10C40. THE INSIDE BEARING MATERIAL WHEN INSPECTED WAS FOUND TO HAVE PIECES MISSING AND FURTHER INSPECTION REVEA LED THE REMAINDER OF THE LINER WAS EASY TO REMOVE BY HAND. THERE WAS NO DAMAGE FOUND ON THE INNER SLEEVE OR ON THE BOLT. PRIOR TO DISASSEMBLY THE ROLLERS WERE INSPECTED IN SITU AND FOUND TO TURN WITH VERY LITTLE EFFORT REQUIRED. NEW BEARING WAS INSTALLED (TC NR 20070607008) 1 L 7 2 4F 4 F A22CE E1NE 2007071100159 20070711 00159 NE 2007 7 11 CA070607009 3 20070604 G 6111 E10950PK BLADE HARTZL BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8796 HJ448 (CAN) DURING ROUTINE MAINTENANCE, THE LT PROPELLER BLADE NR 1 WAS FOUND CRACKED. THE CRACK RAN CHORD WISE APPROXIMATELY 2.3750 INCH FROM THE BLADE ROOT WITH A LENGTH OF APPROXIMATELY 1 INCH. THE PROPELLER HAS BEEN REPLACED AND WILL BE SENT FOR REPAIR AS WELL AS A STRIP REPORT. (TC NR20070607009) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2007071100161 20070711 00161 NM 2007 7 11 CA070607010 1 20070607 G 2910 012152130010 LINE BOEING 777 777* UTILUSE NM HYD SYSTEM LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ON TRAINING FLIGHT RT HYDRAULIC QUANTITY REDUCED. HYDRAULIC LEAK FOUND IN RIGHT ENGINE PYLON AREA. HYDRAULIC SUPPL Y PIPE FOUND LEAKING AT FLEXIBLE AREA, THIS FLEXIBLE AREA IS COVERED BY A RUBBER SHEATH. PEN INDICATES AREA FLUID WAS L EAKING FROM (TC NR 20070607010) 2 L 7 2 4F RT T00001SE 2007081000100 20070810 00100 EA 2007 8 10 CA070607011 1 20070606 G 2750 601R930507 FCU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE TE FLAPS MALFUNCTIONED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) (FLAPS FAIL) MESSAGE DISPLAYED ON APPROACH. FLAPS FAILED WHEN SELECTING FROM FLAP 20 DEGREES TO FLAPS 30 DEGREES. FLAPS REMAINED AT 20 DEGREES AT A SPEED OF 170 KIAS. MAINTENANCE REPLACED FECU (FLAPS ELECTRONIC CONTROL UNIT) DUE TO UNABLE TO TEST AND THE LT BPSU (BRAKE POWER SENSOR UNIT) P/N 8550100-9, S/N 372. AIRFRAME HOURS: 24818:12 CYCLES: 20440 . (TC NR 20070607011) 2 L 7 2 4F 4 F RT A21EA E15NE 2007081000101 20070810 00101 CE 2007 8 10 CA070607012 1 20070517 G 2730 4527301000U1 DISCONNECT UNIT LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP ELEVATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 2400 2400 (CAN) WHEN AIRCRAFT WAS DOWN FOR A 2400 HR INSPECTION, IT WAS DISCOVERED THAT THERE WAS PLAY BETWEEN THE LT AND RT ELEVA TOR (INSPECTION IRN D2730007). AN ELEVATOR FREE-PLAY CHECK WAS C/W AND ELEVATORS WERE FOUND TO BE OUT OF LIMITS. ELEVA TOR CONTROL SYSTEM T/S AND FREE PLAY FOUND IN THE AFT ELEVATOR DISCONNECT. PART REPLACED, FREE-PLAY RE-CHECKED AND FOUN D TO BE WITHIN LIMITS. (TC NR 20070607012) 2 L 7 2 4F 4 F RT T00008WI E6WE 2008030600044 20080306 00044 CE 2008 3 6 CA070608001 1 20070606 G 5510 115620010101 STRUCTURE BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 11730 (CAN) CRACK FOUND IN STRUCTURE OF HORIZONTAL STAB. CRACK LOCATED AT TRAILING EDGE UPPER SURFACE AT CENTER OF HORIZONTAL STAB. CRACK LENGTH 0.600, CRACK REPAIRED IAW REPAIR DWG SUPPLIED BY MFG AND AIRCRAFT RETURNED TO SERVICE. (TC NR 2007060 8001) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007081000102 20070810 00102 CE 2007 8 10 CA070608002 1 20070524 G 2720 4555401134011 TORQUE TUBE LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP RUDDER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 2400 2400 (CAN) DURING 2400 HR INSPECTION, SB 45-27-24/ DVI IAW 5-19-00-N2720030, CORROSION WAS FOUND INSIDE OF RUDDER TORQUE TUBE . TORQUE TUBE WAS TO BE REPLACED IAW SB45-27-25. WHEN TORQUE TUBE KIT ARRIVED, IT WAS DISCOVERED THAT THE REPLACEMENT TORQUE TUBE WAS MANUFACTURED INCORRECTLY. A SECOND KIT WAS ORDERED AND IT TOO WAS INCORRECT. ORIGINAL TORQUE TUBE CORR OSION CLEANED AND REINSTALLED. (TC NR 20070608002) 2 L 7 2 4F 4 F RT T00008WI E6WE 2007081000103 20070810 00103 CE 2007 8 10 CA070608003 1 20070524 G 5741 ATTACH FITTING LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP WING TO BODY WORN W K NONE O OTHER IN INSP/MAINT 1 CA 2400 2400 (CAN) DURING 2400 HR INSPECTION, IT WAS DISCOVERED THAT A NR OF THE WING TO FUSELAGE LINKS HAD WORN PAINT OFF THE ATTACH FITTINGS. ALL AFFECTED FITTINGS AND LINKS INSPECTED. NO DAMAGE FOUND. MFG ADVISED OF FINDINGS. MFG FOLLOWED UP WITH A LETTER OF APPROVAL TO INSTALL PHENOLIC SPACERS BETWEEN ALL LINKS AND FITTINGS. (TC NR 20070608003) 2 L 7 2 4F 4 F RT T00008WI E6WE 2007071100163 20070711 00163 CE 2007 7 11 CA070608004 1 20070524 G 6100 UNKNOWN MCAULY 1A103 CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8656 2793 SR774449 (CAN) PROPELLER RECEIVED FOR INSPECTION IAW AD 2003-12-05. INSPECTION FOUND CRACK INDICATIONS IN PREVIOUSLY REPAIRED ARE AS. PROPELLER HAS BEEN REMOVED FROM SERVICE IAW THIS AD AND ASB 221C. (TC NR 20070608004) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 20081104 2008 11 4 CA070608005 4 20070608 G 2562 E01 ELT CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL INOPERATIVE W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) WHEN TESTING ELT FOR THE REQUIREMENT OF CAR 571 APPENDIX G FOUND G SWITCH INOPERATIVE. UNIT BEING RETURNED TO MFG FOR REPAIR. (TC NR 20070608005) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007081000104 20070810 00104 EU 2007 8 10 CA070608006 1 20070606 G 6220 350A31190700 STARFLEX SNIAS SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE MAIN ROTOR HEAD DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA 2139 M1199 (CAN) WHILE WAITING FOR HIS CREW TO RETURN, THE PILOT NOTICED SOME BLACK SOOT AROUND ONE OF THE STARFLEX ARMS. FURTHER E XAMINATION REVEALED THAT THE STAINLESS STEEL BUSHING BONDED ON THE END OF THE STARFLEX ARM HAD COME LOOSE AND WAS FLOATI NG INSIDE THE SPHERICAL BEARING IN THE FREQUENCY ADAPTER. THE BUSHING WAS IN GOOD CONDITION THAT MORNING BEFORE THE FLIG HT AND NO UNUSUAL NOISES OR VIBRATIONS WERE DETECTED PRIOR TO DISCOVERING THE DAMAGED STARFLEX. THE PILOT AND CREW HAD T O BE FLOWN OUT OF THE BUSH WITH ANOTHER HELICOPTER. A NEW STARFLEX WAS INSTALLED ON SITE THE NEXT DAY WITH NO FURTHER IS SUES. (TC NR 20070608006) 1 G 7 1 3U 3 U H9EU E19EU 2007071100167 20070711 00167 NM 2007 7 11 CA070608007 1 20070604 G 2900 10607102 BYPASS VALVE BOEING 727 727233 138408A NM PWA JT8 JT8D15 52051 NE HYD SYSTEM FAILED W A UNSCHED LANDING F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) ON ARRIVAL, THE IB FLAPS FAILED TO EXTEND WHEN LANDING, CONFIGURATION SELECTED. THE CREW ELECTED TO DIVERT. THE AI RCRAFT COMPLETED A NORMAL LANDING. MAINTENANCE WAS UNABLE TO DUPLICATE THE PROBLEM AND INSPECTED THE SYSTEM FOR LEAKS AN D ANOMALIES. THE FLAP POSITION INDICATOR WAS REPLACED AS PRECAUTION AND THE AIRCRAFT WAS RETURNED TO SERVICE. THE AIRCRA FT SUBSEQUENTLY REPOSITIONED WITHOUT FURTHER PROBLEM. HOWEVER DURING DEPARTURE THE CREW OBSERVED LOW HYDRAULIC QUANTITY ON THE A SYSTEM AFTER SELECTING GEAR AND FLAPS UP. THE AIRCRAFT DIVERTED AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED A FAILED IB FLAP BYPASS VALVE. BOTH A SYSTEM PUMPS AND THE RESPECTIVE CASE DRAIN FILTERS WERE REPLACED NO CON 2 L 7 3 4F 4 F RT A3WE E2EA 2007071100169 20070711 00169 EU 2007 7 11 CA070608008 1 20070606 G 2730 CONTROL CABLE FOKKER F28 F28MK0100 4990807 EU RROYCE TAY TAYMK65015 EU ELEVATOR BROKEN W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA (CAN) FLIGHT CREW REPORTED DURING HEAD START CHECKS THAT THE FLIGHT CONTROL LOCK WOULD NOT LOCK THE ELEVATOR CONTROLS A ND WAS VERY STIFF WHEN MOVING CONTROL LOCK TO FREE POSITION. RECERTIFICATION, FOUND THE FLIGHT CONTROL LOCK CABLE FCL1 SNAPPED AT AILERON FLIGHT CONTROL LOCK PULLEY. CABLE REPLACED AND ADJUSTMENT COMPLETED. OPERATIONAL TEST OF FLIGHT CON TROL LOCK SYSTEM COMPLETED. FOLLOW UP ACTION THE CABLE BROKE AT AN IDLER PULLEY AND APPEARED TO HAVE BEEN POSSIBLE FRAY ED. ENTIRE ELEVATOR CONTROL LOCK CABLE RUN INSPECTED AND FOUND SERVICEABLE. IN FOLLOW UP A SPECIAL INSPECTION WILL BE I SSUED FOR AIRCRAFT TO INSPECT THE SAME AREA. (TC NR 20070608008) 2 L 7 2 4F 4 F RT 2007071100170 20070711 00170 NE 2007 7 11 CA070608009 2 20070607 G 7310 D22AA1022 VALVE AIRBUS A319 A319114 3930350 NM CFMINT CFM56 CFM565A1 NE FUEL RETURN FAILED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION DE DESCENT 1 CA 30078 11851 731901 (CAN) DUE TO A LT ENGINE STALL MESSAGE ON ECAM, THE FLIGHT CREW SHUTDOWN THE NR 1 ENGINE AS A PRECAUTION. MAINTENANCE FOUND FUEL RETURN VALVE AT FAULT DURING AN ENGINE MOTORING TEST, UNIT REPLACED IAW AMM 73-11-50. (TC NR 20070608009) 2 L 7 2 4F 4 F RT A28NM E29NE 20081104 2008 11 4 CA070608010 1 20070608 G 6320 RG36343 SHAFT GEARBOX PUMP DAMAGED W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA 1556 (CAN) S 76 MAIN GEARBOX REMOVED FOR GENERATING METAL. TSN 1556.5 THE METAL HAS BEEN SENT OUT FOR ANALYSIS TO ENSURE THA T IT IS THE TYPE CONSISTANT WITH THE DAMAGED PARTS. WE WILL ATTACH THE REPORT WHEN RECEIVED. (TC NR 20070608010) 2007081000105 20070810 00105 EU 2007 8 10 CA070611001 1 20070608 G 2822 9638411403 PUMP PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL FUEL BOOST MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 697 (CAN) WHILE PERFORMING A DEFUEL OF AIRCRAFT TO PERFORM SCHEDULED MAINTENANCE, RT WING FUEL BOOST PUMP POPPED CIRCUIT BRE AKER AFTER 3 MINUTES OF OPERATION DEFUELING AIRCRAFT. PUMP WAS ALLOWED TO SIT FOR 10 MINUTES AND C/B RESET AND PUMP WOU LD AGAIN WORK FOR 3 MINUTES. THIS HAPPENED 3 TIMES UNTIL DEFUEL WAS COMPLETE. PUMP WAS REPLACED WITH O/H UNIT. TESTED SATISFACTORY (TC NR 20070611001) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007071100174 20070711 00174 NM 2007 7 11 CA070611002 1 20070610 G 3244 DR0231T TIRE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NR 4 FAILED W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 CA (CAN) DURING A NORMAL AND SMOOTH TAKEOFF ROLL, CREW NOTICE A VIBRATION (120KNTS,V1=134KNTS). AT VR ROTATED INTO SMOOTH CLIMB AND REQUESTED GEAR UP WITH POSITIVE CLIMB. SHORTLY AFTERWARDS CABIN CREW CALLED TO SAY PASSENGERS REPORTED A WHEE L CAME OFF DURING TAKEOFF. AIRCRAFT COMPLETED AN UNEVENTFUL LANDING. NR 4 MAINWHEEL TIRE WAS FOUND SHREDDED WITH MAINW HEEL ASSY STILL IN PLACE. (TC NR 20070611002) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007081000106 20070810 00106 EU 2007 8 10 CA070612001 1 20070529 G 3233 SWITCH PILATS PC12 PC1245 7090551 EU GARRTT TPE331 TPE33112UHR WP ROTOL R333 R333482F12 GL MLG ACTUATOR MALFUNCTIONED W O OTHER J WARNING INDICATION LD LANDING 1 CA 0623E (CAN) CREW REPORTED THE LT MAIN LANDING GEAR DOWN AND LOCK INDICATION WAS SHOWING (IN TRANSIT) WHEN SELECTED DOWN. THE SYSTEM WAS TROUBLESHOT TO THE DOWNLOCK INDICATOR SWITCH IN THE GEAR ACTUATOR. ACTUATOR REPLACED AND AIRCRAFT RETURNED T O SERVICE. (TC NR 20070612001) 1 L 7 1 3T 4 T RT A78EU E4WE 6 C P61GL 2007071100175 20070711 00175 NM 2007 7 11 CA070612002 1 20070611 G 3232 82970014009 ACTUATOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE RT MLG DOOR BYPASSING W O OTHER J WARNING INDICATION AP APPROACH 1 CA 44480 44480 (CAN) ON LANDING, GEAR DOWN SELECTION HEARD LOUD CLUNK, AND RT MAIN GEAR UNSAFE WARNING. CYCLED GEAR WITH SAME RESULT. ALTERNATE GEAR EXTENSION ACTIVATED, ALL GEAR INDICATED DOWN, NORMAL LANDING. MAINTENANCE INSPECTION FOUND RT AFT GEAR D OOR ACTUATOR SLOW TO OPEN DOORS DUE TO INTERNAL PRESSURE BYPASSING. RT AFT GEAR DOOR ACTUATOR REPLACED, LEAK AND FUNCTI ON CHECKS COMPLETED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070612002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007071100176 20070711 00176 NM 2007 7 11 CA070612003 1 20070601 G 2421 BRUSHES ROBSIN R22 R22BETA 7640110 NM LYC O360 O360J2A 41514 EA ALTERNATOR LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 215 (CAN) ON BACK OF ALTERNATOR, POWER-OUT STUD FOUND LOOSE AND NYLON BUSHING FOUND MELTED. WIRE TERMINAL WAS FOUND MELTED A ND BROKEN. PROBLEM HAS SINCE BEEN DETECTED ON TWO OTHER AIRCRAFT. (TC NR 20070612003) 1 G 7 1 3O 3 O H10WE E286 2007081000107 20070810 00107 SW 2007 8 10 CA070612004 1 20070612 G 6310 269A5512 DRIVE BELT HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA MAIN ROTOR SPLIT W K NONE O OTHER IN INSP/MAINT 1 CA 59 (CAN) DRIVE BELT AXIAL SPLIT OVER 50 PERCENT OF BELT CIRCUMFERENCE; SPLIT OCCURS UNDER OUTER LAYER OF BELT. NOTE: PLE ASE ADVISE IF PHYSICAL VERIFICATION IS REQUIRED AS MUST RETURN BELTS TO MFR FOR WARRANTY CONSIDERATION. (TC NR 200706120 04) 1 G 7 1 3O 3 O O 4H12 E286 2007071200130 20070712 00130 GL 2007 7 12 CA070612005 2 20070610 G 7250 23034787 BEARING BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA 534 534 (CAN) FOUND METAL ON BOTH CHIP PLUGS AND THEN FOUND THAT THE 2.5 BEARING HAD STARTED TO FAIL. REPLACED BEARING AND INNE R RACE OF SPUR ADAPTER. NO FURTHER PROBLEMS. (TC NR 20070612005) 1 G 7 1 3U 3 U H2SW E4CE 2007071200131 20070712 00131 EU 2007 7 12 CA070613001 2 20070612 G 7270 JR21756A DUCT RROYCE SPEY SPEY55515P 54521 EU ENGINE BYPASS MISREPAIRED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 14716 2950 (CAN) ENGINE FRONT BYPASS DUCT FOUND AT INSPECTION WITH NON STANDARD REPAIR OUTSIDE OEM LIMITATION. PATCH REPAIR ON OUTS IDE WALL 8 INCH LONG BY 2.5 INCH WIDE OUTSIDE SCOPE OF XRS3025. PART REJECTED AND REMOVED FROM ENGINE. (TC NR 200706130 01) 4 F E2EU 2007071100177 20070711 00177 EA 2007 7 11 CA070613002 1 20070613 G 2810 21564002 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE RT WING LEAKING W O OTHER K FLUID LOSS NR NOT REPORTED 1 CA 1803 (CAN) FUEL LEAK SUSPECTED ON RT WING. RT FUEL CELL NR 6 HAS BEEN FOUND LEAKING AFTER INVESTIGATION AND REPLACED. DROPS 9050 (TC NR 20070613002) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 20081104 CE 2008 11 4 CA070613003 1 20070612 G 8011 MMU4001R STARTER CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA SHORTED W K NONE O OTHER IN INSP/MAINT 1 CA 421 (CAN) STUDENT TRIED TO START ENGINE THE STARTER WOULD NOT ENGAGE. AIRCRAFT BROUGHT INTO HANGAR AND COWLS REMOVED. AME TR IED TO ENGAGE STARTER IN THE SHOP BUT IT WOULD NOT ENGAGE. WHEN HE CHECKED THE STARTER IT WAS VERY HOT AND THERE WAS SOM E SMOKE COMING OUT OF IT. STARTER REMOVED AND SENT BACK FOR WARRANTY REPLACMENT. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P9045 20081104 GL 2008 11 4 CA070613004 1 20070611 G 2497 AN316010 CIRCUIT BREAKER DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN3 52008 NE HARTZL HCB3R HCB3R304 GL FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) WHILE TROUBLESHOOTING A U/S TAIL NAV LIGHT AND REPLACING A CORRODED KNIFE CONNECTOR AT THE TAILCONE, POWER WIRE TO THE LIGHT ASSEMBLY OVERHEATED AND MELTED, FILLING THE CABIN WITH SMOKE. PWR WAS DISCONNECTED AND SMOKE DISSIPATED. FURT HER INVESTIGATION REVEALED THAT NAV LIGHT SOCKET HAD CORROSION BUILDUP ON THE WIRING TERMINALS THAT HAD SHORTED THE SOCK ET TO GROUND. PWR LIRE MELTED FROM THE SOCKET BACK TO CIRCUIT BREAKER, AND FROM THERE TO MAIN BUS. INVESTIGATION WAS THE N CENTERED ON THE CIRCUIT BREAKER WHICH HAD NOT TRIPPED. BREAKER WAS FOUND TO BE A 10 AMP BREAKER AND NOT THE 5 AMP UNIT LISTED IN THE ACFT MANUAL. A FUNCTION CHECK OF THE BREAKER REVEALED THAT IT WOULD NOT TRIP AT ALL. AN APPROPRIATELY RA 1 H 7 1 3R 3 R RC A806 5E1 5 C P28EA 2007081000108 20070810 00108 SW 2007 8 10 CA070614001 1 20070608 G 6310 269A5512 DRIVE BELT HUGHES 269 269C1 8059504 SW LYC O360 HIO360* 41514 EA MAIN ROTOR SPLIT W K NONE O OTHER IN INSP/MAINT 1 CA 177 (CAN) DRIVE BELT AXIAL SPLIT OVER 50 PERCENT OF BELT CIRCUMFERENCE; SPLIT OCCURS UNDER OUTER LAYER OF BELT. DEFECT HAS B EEN FOUND ON (2) OTHER AIRCRAFT OF THE SAME TYPE. NOTE: PLEASE ADVISE IF PHYSICAL INSPECTION IS REQUIRED AS MUST RETUR N BELTS TO MANUFACTURER FOR WARRANTY CONSIDERATION. (TC NR 20070614001) 1 G 7 1 3O 3 O O 4H12 1E10 2008031900143 20080319 00143 SO 2008 3 19 CA070614002 1 20070604 G 7810 LW15849 EXHAUST STACK PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL RT ENGINE SEPARATED W D RETURN TO BLOCK R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA L258765A (CAN) PRIOR TO DEPARTURE, ENGINE RUN-UP PILOT REPORTED THAT RT ENGINE RUNNING ROUGH. ENGINE ONLY PRODUCING 30" MP AND MA X 2250 RPM, AT GPH FF. RT MAG DROP WAS EXCESSIVE. MAINT INVESTIGATION FOUND ENGINE RT EXHAUST SEGMENT P/N LW-15849 SEPAR ATED FROM NR 5 EXHAUST STACK PIPE PN LW-10161 AT THE SLIP JOINT. NEW EXHAUST SEGMENTS INSTALLED AND ENGINE OPERATION CHE CKED SERVICEABLE. NO VISIBLE HEAT DAMAGE NOTED TO AREA WIRING OR COMPONENTS. SLIGHT DISTORTION NOTED TO SOME AREA HOSE S UPPORT WRAPPING. NOTE: THIS ENG WAS RECENTLY INSTALLED AND HAD ACCUMULATED 2.2 HRS SINCE INSTALLATION. THE ORIGINAL EXHA UST SEGMENTS FROM THE REMOVED ENGINE WERE INSTALLED. NO DEFINITIVE CAUSE FOR THE SEPARATION HAS BEEN DETERMINED. SUSPECT 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007071100178 20070711 00178 SW 2007 7 11 CA070614003 1 20070613 G 2910 2781032682 LINE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE HYD SYSTEM CRACKED W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 CA (CAN) CREW NOTICED A LARGE PUDDLE OF HYDRAULIC FLUID COMING FROM THE NOSE WHEEL WELL AREA. DETERMINED TO BE A CRACKED L INE ON A BEND RADIUS, WHICH WAS THE SUPPLY LINE TO THE NWS SYSTEM. THE SYSTEM WAS DISABLED AND PLACED ON AN MEL DEFERRA L, CLEANED AND LEAK TESTED, SERVICEABLE. AWAITING PARTS FOR REPAIR. (TC NR 20070614003) 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 2007071700011 20070717 00011 NM 2007 7 17 CA070614004 1 20070511 G 2497 CONNECTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE AC POWER MONITOR BURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 552 (CAN) UPON GETTING IN A/C DISCOVERED AC POWER C/B`S POPPED UPON EXTERNAL PLUGGED INTO A/C ASSUME POPPED WHEN GSE PLUGGE D IN PILOT ENTERED COCKPIT AND PUSHED ALL BREAKERS IN ON WALK AROUND EXITING A/C AND DOING WALKAROUND WENT BACK TO COCK PIT AND DISCOVERED SMOKE REMOVED POWER FROM A/C AND CALL MAINTENANCE UPON REMOVAL OF AC POWER MONITOR DISCOVERED BURNED CONNECTOR ON INDICATOR AND CONNECTOR, CONNECTOR AND INDICATOR /MONITOR REPLACED WITH NO FURTHER ISSUES. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007071100179 20070711 00179 NE 2007 7 11 CA070614005 2 20070307 G 7250 MS955608 BOLT CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE GAS GENERATOR LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 4400 (CAN) DURING SCHEDULED MAINTENANCE ACTIVITIES, 3 OF THE MS9556-08 BOLTS LOCATED AT THE ENGINE GAS GENERATOR TO INTERMEDI ATE CASE FLANGE WERE DETERMINED TO BE LOOSE. AN ADDITIONAL BOLT WAS FOUND TO BE COMPLETELY MISSING. MFG WILL INVESTIGAT E AND ADVISE ON ROOT CAUSE AND REMEDIAL MAINTENANCE ACTIONS. (TC NR 20070614005) 2 L 7 2 4F 4 F RT A22CE E00059EN 2007071100279 20070711 00279 NM 2007 7 11 CA070615001 1 20070612 G 2435 23088008 GENERATOR DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE NR 1 INTERMITTENT W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 2594 (CAN) AFTER SEVERAL SECTORS WITH INTERMITTENT NR 1 DC GEN PROBLEMS, CREW REPORTED ILLUMINATION OF DC BUS CAUTION LIGHT P LUS SEVERAL OTHER CAUTIONS: AUX INV, NR 1 DC GEN, RUD FULL PRESS, NR 2 RUD HYD, EPWS. THE QRH WAS ACTIONED BUT THEY WER E NOT ABLE TO RESTORE THE LOST BUSES. THE NR 1 DC GENERATOR WAS REPLACED AND THE SYSTEM TESTED NORMALLY. ON REMOVAL FROM THE A/C, THE DC GENERATOR WAS NOTED TO HAVE SIGNIFICANT DAMAGE WITH SEVERAL LARGE METALLIC (CHUNKS) DROPPING OUT. (TC N R 20070615001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007081000109 20070810 00109 NM 2007 8 10 CA070615002 1 20070606 G 6310 A1902 DRIVE BELT ROBSIN R22 R22BETA 7640110 NM LYC O360 O360J2A 41514 EA MAIN ROTOR SEPARATED W O OTHER O OTHER LD LANDING 1 CA 38 (CAN) BELTS WERE REPLACED AT 2200HR OVERHAUL AND AFTER 38 HRS IN SERVICE WERE FOUND SEPARATED IN A SECTION ABOUT 2 INCHE S LONG. (TC NR 20070615002) 1 G 7 1 3O 3 O H10WE E286 2007071100278 20070711 00278 2007 7 11 CA070615003 1 20070613 G 3230 622800200 SWITCH BAG GARRTT TPE331 TPE33110UG 01514 WP MCAULY 4HFR34 4HFR34C652 NE MLG FAILED W O OTHER L NO TEST AP APPROACH 1 CA (CAN) DURING APPROACH, THE CREW EXPERIENCED A LANDING GEAR FAILURE AND OBSERVED THE CIRCUIT BREAKER HAD POPPED. THEY PRO CEEDED WITH AN EMERGENCY LANDING GEAR EXTENSION AND LANDED WITHOUT INCIDENT. THE FAULT WAS TRACED TO THE LT UPLOCK MICRO SWITCH. WHEN THE MICROSWITCH WAS ACTIVATED THE FAULT DISAPPEARED AND WAS UNABLE TO BE RE-CREATED. THE SWITCH WAS REPLACE D. (TC NR 20070615003) 4 T E4WE 6 C 3PNE 2007071100276 20070711 00276 EU 2007 7 11 CA070615004 1 20070613 G 3220 A1026EAND9E BOLT BAG JETSTM JETSTM3101 1500215 EU GARRTT TPE331 TPE33110UG 01514 WP ROTOL R333 R333482F12 GL NLG FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SCHEDULE INSPECTION AD UK 024-05-87 / SB53A-JA870510R1, WE NOTICE THE 2 UPPER BOLT OF THE NLG JACK MOUNTING BRACKE T WERE SHEARED AND THE 2 LOWER ONES WERE LOOSE. ACCOMPLISHED PART A OF THE SB C/OUT(ALL 4 BOLTS AND NUTS REPLACED), PAR TS INSPECTED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070615004) 2 L 7 2 4T 4 T RT A21EU E4WE 6 C P61GL 2007081000110 20070810 00110 2007 8 10 CA070615005 4 20070613 G 2350 M1035CHKFJLJ2 AUDIO CONTROL SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE3311 01514 WP MCAULY 4HFR34 4HFR34C652 NE STICKING W O OTHER O OTHER CR CRUISE 1 CA (CAN) BUTTONS HAVE TO BE PRESSED NUMEROUS TIMES BEFORE THEY ENGAGE, REPLACED UNIT. (TC NR 20070615005) 2 L 7 2 4T 3 T RT A8SW E3WE 6 C 3PNE 2008031900146 20080319 00146 2008 3 19 CA070615006 4 20070613 G 2300 M1035CHKFJLJ2 AUDIO CONTROL SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE331* 01514 WP MCAULY 4HFR34 4HFR34C652 NE COCKPIT STICKING W O OTHER O OTHER CR CRUISE 1 CA (CAN) BUTTONS HAVE TO BE PRESSED NUMEROUS TIMES BEFORE THEY ENGAGE, REPLACED UNIT (TC NR 20070615006) 2 L 7 2 4T 3 T RT A8SW E2WE 6 C 3PNE 2007071100180 20070711 00180 WP 2007 7 11 CA070616001 2 20070527 G 7200 ENGINE RAYTHN DH125 HAWKER800XP 7150012 CE GARRTT TFE731 TFE7315BR WP LEFT MAKING METAL W A UNSCHED LANDING B E SMOKE/FUMES/ODORS/SPARKS VIBRATION/BUFFET CR CRUISE 1 CA P107188 (CAN) DURING CRUISE, CREW NOTED ODOR IN CABIN AND VIBRATION, AND EXECUTED PRECAUTIONARY LANDING. LT ENGINE HAD HIGH VIB RATION ON LOW POWER GROUND RUN, ENGINE OIL FILTER WAS HEAVILY CONTAMINATED WITH BOTH FERROUS AND NON-FERROUS MATERIAL, E NGINE WAS REMOVED FOR REPAIR, SUSPECT BEARING AND/OR CARBON SEAL FAILURE, TEARDOWN REPORT PENDING. (TC NR 20070616001) 2 L 7 2 4F 4 F RT A3EU E6WE 2007081000111 20070810 00111 CE 2007 8 10 CA070618001 1 20070617 G 3210 MS2124010C40 BEARING CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE MLG WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS SDR IS BEING SUBMITTED TO SATISFY THE REQUIREMENT OF AIRCRAFT SERVICES DIRECTORATE CAMPAIGN NOTICE CN-1 851-3 2-40-040R1 THE INTERNAL TEFLON MATERIAL OF THE BEARING HAD DETERIORATED CAUSING THE BEARING TO BE DIFFICULT TO ROTATE. ( TC NR 20070618001) 1 L 7 2 4F 4 F A22CE E1NE 2007071100181 20070711 00181 EA 2007 7 11 CA070618002 2 20070606 G 8520 CRANKSHAFT PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA SNSNCH 74D 74DM EA ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 2746 2746 (CAN) ENGINE CONVERTED TO 160 HP IAW STC SE367CH. ENGINE NOW SIMILAR TO O-320-D2A. CRANKSHAFT INSPECTED IAW AD 98-02-0 8. PITTED FOUND, NO CRACKS. (TC NR 20070618002) 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2007081000112 20070810 00112 SW 2007 8 10 CA070618003 1 20070616 G 2752 20619502 ACTUATOR AIRTRC AT802 AT802A 0390308 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MA3 GL TE FLAP FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 616 (CAN) DURING APPROACH FOR A SCOOPING OPERATION, THE FLAPS WOULD NOT EXTEND WITH AN AIR LOAD. THE AIRCRAFT RETURNED TO B ASE. UPON INVESTIGATION BY MAINTENANCE STAFF, FLAPS WOULD EXTEND THE FIRST 10 DEGREES WITH NO AIR LOAD AND THE ACTUATO R MADE A GRINDING NOISE. THE FLAP ACTUATOR WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC 20070618003) 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2007081000113 20070810 00113 EA 2007 8 10 CA070618004 1 20070613 G 2897 MS312183P CONNECTOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE AUX TANK MISINSTALLED W O OTHER W INADEQUATE Q C NR NOT REPORTED 1 CA (CAN) ON PATS RT AUXILARY TANK FOUND THE PRESSURE DIFFERENTIAL SWITCH, THE SOCKET OF THE SWITCH AND THE ELECTRICAL HARNE SS CONNECTOR HAVING BOTH PINS, THE CONNECTOR SHOULD BE A FEMALE TYPE. THE DIFFERENTIAL SWITCH IS WORKING ONLY ON GROUND DURING FUELING. FOUND ALSO THAT THE SYSTEM IS WORKING BECAUSE THAT THE PINS ARE CONTACTING EACH OTHER. PATS THE STC HOLD ER ADVISED AND A SB IS ALREADY OUT (TC NR 20070618004) 2 L 7 2 4F 4 F RT A21EA E15NE 2007081000114 20070810 00114 CE 2007 8 10 CA070618005 1 20070504 G 7603 509440767 POWER LEVER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL LT ENGINE WORN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) FLIGHT SNAG REPORTED - (LT ENGINE REMAINS AT HIGH IDLE AT LOW IDLE SETTINGS). MAINTENANCE FOUND THE AIRFRAME POWE R LEVER ARM AT THE REVERSING CAM GROUND PIN HEAD JUMPED THE SPLINE, CAUSING THE SHOULDERED PIN TO HOLD THE FCU INTERCONN ECT ARM FROM RESETTING TO GROUND IDLE.THE ARM WAS RE-ADJUSTED AND IS ASSUMED WORN OUT INTERNALLY. AS A PRECAUTION ALL TH ROTTLE ARMS WERE REPLACED. (TC NR 20070618005) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007071100182 20070711 00182 EA 2007 7 11 CA070618007 2 20070618 G 7297 311792401 WIRE HARNESS PWA PT6 PT6A27 52043 EA ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ACCESSORIES SERVICES PLANT 2. DURING BENCH CHECKING ACTIVITIES THE PART WAS EXHIBITING AN UNKNOWN CONFIGURATION. UNABLE TO DETERMINE THE MANUFACTURING SOURCE. THE PART WAS REPLACED WITH GENUINE PART. THIS PART WILL BE KEPT FOR 1 MON TH FOR EXAMINATION. (TC NR 20070618007) 4 T E4EA 2007081000115 20070810 00115 EA 2007 8 10 CA070618008 1 20070617 G 3213 492009 AXLE CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF34* NE LT MLG BROKEN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 4513 (CAN) REPORTED A FRACTURED LT IB MLG AXLE (NR 2) ON A/C, LT SHOCK STRUT ASSY HAS P/N 49200-9 WITH SPP0049 WITH CURRENTLY . EFFECTED SUBASSY PISTON/AXLE HAS P/N 49263-1 WITH S/N BA0066 AND IS ORIGINALLY INSTALLED ON A/C SINCE DELIVERY. RT SHO CK STRUT ASSY HAS P/N 49200-10 WITH S/N SPP0097 AND SUBASSY PISTON AXLE ASSY WITH P/N 49263-1 AND S/N BA0111 AND BOTH HA VE TAC=7763 (ORIGINALLY INSTALLED SINCE DELIVERY). (TC NR 20070618008) 2 L 7 2 4F 4 F RT A21EA E15NE 2007081000116 20070810 00116 EA 2007 8 10 CA070618009 1 20070615 G 2820 O-RING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE FUEL SYSTEM LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING FLIGHT, ENROUTE, THE CREW OBSERVED A RT FUEL LOW PRESS MESSAGE ON EICAS FOLLOWED BY FUEL IMBALANCE. AT 10 00 LB FUEL DIFFERENTIAL BETWEEN TANKS, THE QRH PROCEDURE FOR FUEL IMBALANCE WAS INITIATED. AS A RESULT, THE RT ENGINE WA S SHUTDOWN. THE AIRCRAFT DIVERTED. AN EMERGENCY WAS DECLARED AND GROUND EMER EQUIP WAS ON STANDBY. THE AIRCRAFT LANDE D WITHOUT FURTHER EVENT. MAINT FOUND A CLAMP FOR THE FUEL FEED LINE FROM THE RT COLLECTOR TANK WAS NOT PROPERLY ATTACHE D. THE CLAMP HAD SHIFTED SUFFICIENT TO ALLOW A MISALIGNMENT OF THE FUEL LINES RESULTING IN THE ESCAPE OF FUEL AT THAT L OCATION. THE ROOT CAUSE FOR THIS IS NOT FULLY ESTABLISHED. MAINT REPLACED THE COUPLING O-RINGS AND RECONNECTED THE WIG 2 L 7 2 4F 4 F RT A21EA E15NE 2007082000039 20070820 00039 EA 2007 8 20 CA070618010 1 20070613 G 3213 492033 AXLE CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF34* NE MLG SHEARED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 956 (CAN) WHILE LOADING, THE PASSENGER AT SLC THE FLIGHT CREW FELT A CERTAIN JOLT . INVESTIGATING THE SOURCE , THE CREW FOUN D MLG NR 4 AXLE COMPLETELY SHEARED OFF. MLG NR 4 MLG AXLE COMPLETELY SHEARED OFF. (TC NR 20070618010) 2 L 7 2 4F 4 F RT A21EA E15NE 20081104 CE 2008 11 4 CA070619001 1 20070617 G 2731 26616151 ACTUATOR CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL ELEVATOR TRIM BINDING W O OTHER J WARNING INDICATION CR CRUISE 1 CA 3730 551 (CAN) EXCESSIVE RESISTANCE IN ELEVATOR TRIM REPORTED. RT ELEVATOR TRIM ACTUATOR FOUND TO BE BINDING AND REPLACED WITH OV ERHAULED UNIT. ACFT HAS FLOWN WITH NO REOCCURENCE OF THE DEFECT. THE SUBJECT ACTUATOR WAS OVERHAULED AND FITTED IAW THE MAINT SCHEDULE IN JULY 2006. (TC NR 20070619001) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2007082000040 20070820 00040 CE 2007 8 20 CA070619002 1 20070618 G 5210 504300401 STEP BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL PAX DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN INSP IT WAS NOTICED THAT THE STEP ON THE AIRSTAIR DOOR WAS CRACKED AT THE PIVOT STUD. THE STEP WAS REMO VED AND A SERVICEABLE STEP WAS INSTALLED. (TC NR 20070619002) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007082000041 20070820 00041 CE 2007 8 20 CA070619006 1 20070618 G 3297 WIRE CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO HARTZL HCC3Y PHCC3YF2 GL MLG CUT W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 2738 (CAN) LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF DUE TO A FAULTY WIRE TERMINAL CONNECTION BETWEEN THE (GEAR-UP LIMIT S WITCH) AND THE (GEAR MOTOR RELAY). (TC NR 20070619006) 1 L 7 2 3O 3 O 3A25 E8CE 5 C P25EA 2007082000042 20070820 00042 NE 2007 8 20 CA070619007 2 20070611 G 7321 BOLT SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE FCU CONNECTION LOOSE W A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION AP APPROACH 1 CA (CAN) OCCURRENCE WHERE THE ENGINE SPEED CONTROL DISENGAGED FROM THE FUEL CONTROL UNIT, RESULTING IN AN IN-FLIGHT SHUTDOW N OF THE ENGINE. SUSPECTED CAUSE WAS A LOOSE SELF LOCKING BOLT, P/N NK4-4A, AND OR A WORN NON METALLIC LOCKING INSERT ON THE NK4-4A BOLT. IN ORDER TO PREVENT THIS FROM HAPPENING AGAIN, THE MAINTENANCE CREW HAVE BEEN REMINDED TO TAKE CARE WH EN INSTALLING THE SPEED CONTROL WHEN RE-USING THE NK4-4A BOLT TO ENSURE THAT THERE IS THREAD INTERFERENCE. MM, SA 4045- 80, SECTION 20-00, PAGE 5, PARAGRAPH 9 (REUSE OF SELF LOCKING NUTS), SUB-PARAGRAPH C. STATES THAT ALL NUTS MUST BE CHECK ED BEFORE RE-USE. THERE MUST BE THREAD INTERFERENCE, SUCH INTERFERENCE INDICATES THAT THE SELF LOCKING FEATURE IS WORKIN 2 G 7 2 4U 4 U 1H15 1E3 2007082000043 20070820 00043 2007 8 20 CA070620002 4 20070322 G 6122 321524 SOLENOID HAMSTD 4U1827 CNDAIR CL215 CL2151A10 1900320 EA PWA R2800 CA3 52026 NE HAMSTD 43E 43E60 NE PROP GOVERNOR INOPERATIVE W E ENGINE SHUTDOWN F FLT CONT AFFECTED CR CRUISE 1 CA CSP0059 (CAN) DURING A TEST FLIGHT, THE NR 1 PROP WAS FEATHERED TO VERIFY CORRECT FUNCTION OF THE SYSTEM. THE FLIGHT CREW WAS UN ABLE TO UNFEATHER THE PROPELLER AND RETURNED TO THE AIRPORT. MAINTENANCE CREWS FUNCTION TESTED THE SYSTEM ON THE GROUND AND THE SYSTEM FUNCTIONED CORRECTLY. THE PROP FEATHERING SOLENOID WAS SUSPECT AND WAS REPLACED. AIRCRAFT WAS RETURNED T O SERVICE. (TC NR 20070620002) 2 H 7 2 4R 4 R RT A14EA E231 6 C P871 2007071100183 20070711 00183 NM 2007 7 11 CA070620003 1 20070607 G 3150 UNKNOWN BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU UNKNOWN W H DEACTIVATE SYST/CIRCUITS N FALSE WARNING TX TAXI/GRND HDL 1 CA 946 (CAN) WHEN REFUELING AIRCRAFT GROUND CREW NOTICED THAT WHEN THE REFUEL PANEL DOOR WAS OPEN THAT THEY HAD LIGHTS ON THE P ANEL THAT SHOULD NOT HAVE BEEN ON. (TC NR 20070620003) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007082000044 20070820 00044 EU 2007 8 20 CA070621001 1 20070621 G 6220 BUSHING UROCOP UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE SCISSOR LINK FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 98 (CAN) FACTORY NON- FIELD REPLACEABLE BUSHING BOND FAILED IN THE SCISSOR LINK, BROKE FREE AND WORE INTO THE SISSOR LINK. EXCESSIVE PLAY AND "SMOKE" WAS EVIDENT. (TC NR 20070621001) 1 G 7 2 3U 3 U NC R0001RD E34NE 2007082000045 20070820 00045 CE 2007 8 20 CA070621002 1 20070616 G 2910 MOTOR BEECH 76 76 1153005 CE LYC O360 O360A1G6D EA HARTZL HCM2Y HCM2YR GL HYD SYSTEM CONTAMINATED W O OTHER O OTHER AP APPROACH 1 CA (CAN) DURING APPROACH, PILOTS SELECTED LANDING GEAR DOWN, GEAR MOTOR CIRCUIT BREAKER POPPED AND GEAR WOULD NOT EXTEND. A N EMERGENCY EXTENSION WAS CARRIED OUT SATISFACTORILY. AFTER RETURN TO BASE MECHANICS FOUND THAT THE HYDRAULIC MOTOR WAS CONTAMINATED WITH HYDRAULIC FLUID WHICH LED TO AN ELECTRICAL SHORT. FURTHER INSPECTION FOUND THAT THE O-RING WHICH SEP ARATES THE RESERVOIR AND THE MOTOR WAS DETERIORATED. MECHANICS FOUND THAT SPARE POWER PACKS IN STORES HAD SIMILAR CONTAM INATION DUE TO FAULTY O-RINGS. THESE SPARE POWER PACKS ARE LAID ON THEIR SIDES WHICH WOULD ALLOW FLUID TO PASS TO THE MO TOR. A FLEET WIDE INSPECTION OF POWER PACKS IN SERVICE IS BEING CARRIED OUT BY THE AMO TO PREVENT FURTHER OCCURRENCES. A 1 L 7 2 3O 3 O A29CE E286 5 C P43GL 2007082000046 20070820 00046 CE 2007 8 20 CA070621003 1 20070620 G 5711 1058100237 FRAME BEECH 76 76 1153005 CE LYC O360 O360A1G6D EA HARTZL HCM2Y HCM2YR GL RT WING SEPARATED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) DURING TAXI PILOTS FELT THE RT WING DROP SUDDENLY AND HEARD A TIRE SKIDDING SOUND. THEY IMMEDIATELY STOPPED THE AI RCRAFT. MECHANICS FOUND THE LANDING GEAR A-FRAME HAD BROKEN FREE FROM THE MAIN LANDING GEAR TRUNNION. THE LANDING GEAR DID NOT COLLAPSE BUT ROTATED OB AND CONTACTED THE WING WHEEL WELL SKIN CUTOUT, AFTER THE A-FRAME BECAME DISCONNECTED. TH E A-FRAME THAT FAILED HAD BEEN REPLACED WITH AN IMPROVED DESIGN AS REQUIRED BY AD 97-06-10. A FLEET WIDE INSPECTION OF A -FRAMES IN SERVICE ON COMPANY OPERATED AIRCRAFT IS BEING CONDUCTED BY THE AMO TO DETECT EVIDENCE OF CRACKS AT THE WELD B ETWEEN THE UPPER ATTACH FITTING (SQUARE SHAPE) AND THE ROUND TUBULAR STRUCTURE. (TC NR 20070621003) 1 L 7 2 3O 3 O A29CE E286 5 C P43GL 2007082000047 20070820 00047 SO 2007 8 20 CA070621004 1 20070611 G 2731 4173478 CABLE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ELEVATOR TRIM SEPARATED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA 14256 (CAN) PILOT REPORTED ELEVATOR TRIM VERY STIFF WHILE IN FLIGHT, THEN FREE AFTER SEVERAL ATTEMPTS. MAINT INVESTIGATION REV EALED TRIM CABLE P/N 41734-78 SEPARATED AT THE TRIM SERVO P/N 1C469-6-498. CABLE WAS REPLACED AND SYSTEM RIGGED IAW MM 5 -32. CABLE INSPECTION DID NOT REVEAL ANY UNUSUAL WEAR OR FRAYING AT THE SEPARATED ENDS. CABLE WAS SHREDDED AND APPEARED TO BE TORN APART. FURTHER INVESTIGATION BY AVIONICS REPAIR STATION REVEALED THAT THE ELEVATOR ELECTRIC/AP TRIM SERVO CLU TCH RELEASE MECHANISM WAS INTERMITTENT. SERVO WAS REPAIRED AND OPERATION CHECKED SERVICEABLE. (TC NR 20070621004) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007082000048 20070820 00048 EA 2007 8 20 CA070622002 2 20070620 G 8550 O320H2AD ENGINE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL LEFT LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 6383 2085 RL567576T (CAN) OIL LEAKING FROM FRONT LT AREA OF ENGINE. (TC NR 20070622002) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007082000049 20070820 00049 WP 2007 8 20 CA070622003 1 20070619 G 6310 SHAFT ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE CLUTCH WORN W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 563 (CAN) LOUD (BANG) HEARD DURING FLIGHT. CLUTCH SUSPECTED. REMOVED TO INSPECT. CLUTCH WAS TORN DOWN IN THE COMPONENT SHOP AND SHAFT WAS FOUND WORN BEYOND LIMITS. SPRAG WAS MOST LIKELY DRAGGING ON THE SHAFT. CLUTCH AND SHAFT ASSY BEING SENT B ACK FOR WARRANTY. (TC NR 20070622003) 1 G 7 1 3O 3 O H11NM 1E4 2007082000050 20070820 00050 EU 2007 8 20 CA070622004 1 20070619 G 2121 9599022154 BLOWER PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL RIGHT INOPERATIVE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 6594 (CAN) RT VENTILATION BLOWER WOULD NOT OPERATE WHEN SWITCHED ON. REPLACED WITH NEW. (TC NR 20070622004) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007082000051 20070820 00051 SW 2007 8 20 CA070622005 1 20070621 G 2841 EA4703587 INDICATOR BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL FUEL QTY DEFECTIVE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FUEL QUANTITY INDICATOR WAS REMOVED DUE TO INDICATION PROBLEMS. WHEN REMOVED IT WAS FOUND THAT THE FLOAT WAS FULL OF FUEL AND ONE OF THE DECALS FROM PHP WAS GONE AND WAS IN THE FUEL SYSTEM. DECAL WAS LOCATED AND SENDER IS BEING REPL ACED WITH A NEW UNIT. (TC NR 20070622005) 1 G 7 1 3U 3 U H2SW E4CE 2007071100184 20070711 00184 CE 2007 7 11 CA070622006 1 20070619 G 2822 025323150 PUMP CESSNA 425 425 2076018 CE PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL FUEL SYSTEM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1453 (CAN) DURING AN INSPECTION THE INLET FILTER WAS REMOVED. THE FILTER COVER (CAP) WAS FOUND CRACKED UNDER THE O-RING LOCAT ION ALL THE WAY AROUND. IT APPEARS TO HAVE BEEN OVER TORQUED. IT WAS NOT LEAKING AT THIS TIME. THE INLET FILTER ASSEM BLY WAS REPLACED. (TC NR 20070622006) 1 L 7 2 3T 3 T RT A7CE E4EA 5 C P60GL 2007082000052 20070820 00052 EU 2007 8 20 CA070622007 1 20070619 G 6220 C623A2005103 SCISSOR LINK UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE MAIN ROTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 98 (CAN) (1) OF (4) BONDED BUSHINGS FAILED, RESULTING EXCESSIVE PLAY/SMOKING. BUSHING CONTINUED TO WEAR INTO SCISSOR LINK U NTIL CAUGHT AT FIRST 100 HOUR INSPECTION (SINCE NEW). (TC NR 20070622007) 1 G 7 2 3U 3 U NC R0001RD E34NE 2007082000053 20070820 00053 CE 2007 8 20 CA070622008 1 20070612 G 2730 1016100190014 TORQUE TUBE BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE HARTZL HCD4N3 HCD4N3A GL ELEVATOR CONTROL MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) DURING RIGGING CHECK, DUE TO REPLACEMENT OF THE ELEVATOR TORQUE TUBE, DISCOVERED THE ARM LOCATION WAS INCORRECT IN RELATION TO THE MOUNTING PLATE. THIS RESULTED IN NOT BEING ABLE TO ACHIEVE FULL TRAVEL OF THE ELEVATOR. THIS WAS CONF IRMED WHEN COMPARED TO THE REMOVED TORQUE TUBE AND THE SECOND REPLACEMENT. THE CONCLUSION IS INCORRECT ASSEMBLY AT MFG. (TC NR 20070622008) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007071100185 20070711 00185 EA 2007 7 11 CA070625001 2 20070606 G 8530 O320H2AD CYLINDER CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL ENGINE CRACKED W A UNSCHED LANDING R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CL CLIMB 1 CA 1400 L518276T (CAN) INSTRUCTOR RETURNED FROM A FLIGHT WHERE HE EXPERIENCED A ROUGH ENGINE AND LOSS OF POWER FOR A FEW MOMENTS, AFTER W HICH THE ENGINE RAN NORMALLY AGAIN. WHEN MAINTENANCE REMOVED THE COWLING TO CHECK OVER THE ENGINE, A LOT OF OIL WAS NOT ICED IN THE COWL, FURTHER INSPECTION AND CLEANING FOUND A 2 INCH LONG CRACK IN THE CRANKCASE FROM CYLINDER NR 2 MOUNTING PAD AND FORWARD. (TC NR 20070625001) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007082000054 20070820 00054 NE 2007 8 20 CA070625004 2 20070624 G 8560 SUPERCHARGER DOUG DC6 DC6B 3021712 WP PWA R1340 BWASP 52016 NE HAMSTD 43E 43E60 NE ENGINE FAILED W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 1906 (CAN) AT TOP OF CLIMB ENGINE POWER DECREASED TO 20 INCH MANIFOLD PRESSURE AND 80 BMEP. ENGINE WAS SHUTDOWN AND AIRCRAFT RETURNED TO AIRPORT. SUSPECT ENGINE SUPERCHARGER BLOWER FAILED. (TC NR 20070625004) 2 L 7 4 4R 3 R 6A4 ATC14 6 C P871 2007082000055 20070820 00055 EU 2007 8 20 CA070625005 1 20070613 G 6720 21863753 PUSH-PULL ROD SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE T/R GEARBOX CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 1000 (CAN) HEAT SHRINK WHICH PROTECTS THE TAIL ROTOR PUSH PULL TUBE AS IT GOES THRU BEARING P/N 359A27-1191-20 IS CHAFING PRE MATURLY AT THE AFT MOST BEARING LOCATION ON THE TAILBOOM. IPC 67.20.10.00006.00 FIG. 3 (TC# NR 20070625005) 1 G 7 1 3U 3 U H9EU E19EU 2007082000056 20070820 00056 SW 2007 8 20 CA070626001 1 20070622 G 2820 206063607101 HOSE BELL 206 206L4 1182110 SW FUEL SYSTEM DEBONDED W K NONE K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) FUEL HOSE ASSY DEBONDED CAUSING FUEL LEAK FROM FWD TANKS. THE RUBBER BELLOW PART OF THE TUBE ASSEMBLY DEBONDED FRO M THE ALUMINUM TUBING. THIS HOSE ASSEMBLY IS LOCATED ON THE LT SIDE FWD FUEL TANK. REFER TO HELICOPTER IPB FIGURE 28-3 I TEM NR 57. (TC NR 20070626001) 1 G 7 1 3U NC H2SW 2007082000057 20070820 00057 CE 2007 8 20 CA070627001 1 20070622 G 3260 1013646281 DOWNLOCK SWITCH BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL LT MLG UNSERVICEABLE W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA (CAN) THE AIRCRAFT WAS ON A RETURN LEG, WHEN THE CREW LOWERED THE LANDING GEAR THEY NOTICE AN UNSAFE INDICATION ON THE L T MAIN. THEY ABORTED THE LANDING AND INITIATED A (GO-AROUND) PROCEDURE. THE LANDING GEAR WAS CYCLED TWICE MORE AND ON TH E SECOND TRY A SAFE INDICATION WAS OBSERVED. THE AIRCRAFT LANDED WITHOUT INCIDENT. THE LT MAIN LANDING GEAR DOWNLOCK SWI TCH ASSY (P/N 101-364628-1) WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070627001) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007082000058 20070820 00058 NE 2007 8 20 CA070627002 2 20070624 G 7261 4138T09P03 CARBON SEAL CF343B1 CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE NR 2 ENGINE DAMAGED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 872403 (CAN) ON CLIMB OUT, CREW REPORTED NR 2 OIL PRESSURE WAS LOW AND FLUCTUATING BETWEEN 30-41 PSI. INTERMITTENTLY TRIGGERIN G THE LOW OIL WARNING. THE AIRCRAFT WAS DIVERTED AND LANDED NORMALLY. AT LOCATION, CONTRACT MAINTENANCE ADDED (4) QUARTS OF OIL AND A/C WAS CHECKED SERVICEABLE. THE A/C THEN RETURNED TO ORIGINATING BASE WHERE FURTHER TROUBLESHOOTING WAS TO BE CARRIED OUT. MAINTENANCE FOUND NR 2 ENGINE IDG CARBON SEAL DAMAGED. THE CARBON SEAL WAS REPLACED AND LEAK CHECKS A ND RUNS CARRIED OUT AND CHECKED SERVICEABLE. A/C HRS.:17552:25, CYCLES:13370 (TC NR 20070627002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007082000059 20070820 00059 CE 2007 8 20 CA070627003 1 20070626 G 2621 3090385659 SQUIB PACIFICSCIEN LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP FIRE BOTTLE INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA 2172 39925B1 (CAN) WHILE PERFORMING ANOTHER MAINTENANCE TASK IT WAS DISCOVERED THAT THE LOWER (FWD) FIRE BOTTLE SQUIBS WERE NOT INSTA LLED IN THE CORRECT POSITION. BOTH FIRE BOTTLES CONTAIN A SQUIB FOR THE LT AND RT ENGINES, THE LOWER NR 1 BOTTLE IS FOR THE FIRST SHOT AND THE UPPER NR 2 BOTTLE IS FOR THE SECOND SHOT. THE LT AND RT SQUIBS ON EACH BOTTLE HAVE A DIFFERENT PN WITH A DIFFERENT CONNECTOR PLUG RECEPTACLE IN ORDER NOT TO ACCIDENTALLY SWAP LT AND RT ENGINES EXTINGUISHING CAPABILI TIES. HOWEVER, SINCE THE SQUIBS WERE INSTALLED INCORRECTLY THE FIRST EXTINGUISHING SHOT WOULD HAVE BEEN DIRECTED TO THE WRONG ENGINE. UPON INVESTIGATION IT WAS DISCOVERED THAT THE SQUIBS MAY HAVE BEEN INSTALLED INCORRECTLY AT THE LAST 10- 2 L 7 2 4F 4 F RT T00008WI E6WE 2007071100187 20070711 00187 NE 2007 7 11 CA070628001 3 20070625 G 6114 7826691 BOLT DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE PROPELLER HUB SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA 19004 8360 (CAN) DURING REINSTALLATION OF PROPELLER ASSEMBLY AFTER NR 2 ENGINE CHANGE, ONE OF THE MOUNTING BOLTS (P/N 782669-1) SHE ARED. A DIFFERENT PROPELLER ASSEMBLY WAS INSTALLED. AFFECTED SHEARED BOLT TO BE REMOVED AND REPLACED IAW CMM P/N 802325- 1, CH 61-13-06, HUB REPAIR 7-5, PAGES 601-602. TIMES AND CYCLES ARE FOR HUB ASSEMBLY. (TC NR 20070628001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007082000060 20070820 00060 NE 2007 8 20 CA070628003 2 20070516 G 7260 MS949034 BOLT MRCHTI S205 S20522R 8120412 EU PWA PT6 PT6A65AR 52043 NE FIRST STAGE FAILED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 175 PCE97543 (CAN) ENGINE S/N PCE 97543 WAS REMOVED SUBSEQUENT TO IN-FLIGHT SHUTDOWN AFTER THE ENGINE OIL PRESSURE DROPPED TO (0) IN FLIGHT. METAL WAS FOUND IN THE OIL FILTER AND RGB DURING GROUND CHECKS PRIOR TO ENGINE REMOVAL. DURING INVESTIGATION D ISMANTLE OF THE POWER SECTION, (2) OF (6) FIRST-STAGE REDUCTION CARRIER ASSEMBLY MACHINE HEX BOLTS (IPC P/N 3032844, CH. 72-11-00, FIGURE 4, ITEM 200, P/N MS9490-34) WERE FOUND WITHOUT THE BOLT HEADS ATTACHED (REFERENCE FIGURE 1). NOTE THA T THE CARRIER HEX BOLTS SECURE THE FIRST-STAGE CARRIER AND THE FIRST-STAGE REDUCTION SPLINED ADAPTER. THERE ARE A QUANT ITY OF SIX HEX BOLTS INSTALLED WITH KEYWASHERS AND ARE TORQUED 75 TO 85 IN.LB. ENGINE OVERHAUL RECORDS INDICATED THAT Q 1 L 7 1 3O 4 T A9EU E4EA 2007082000061 20070820 00061 WP 2007 8 20 CA070629001 2 20070625 G 7210 8941241 SHAFT GARRTT TPE331 TPE33110 01514 WP SPLINES WORN W O OTHER O OTHER LD LANDING 1 CA 2321 (CAN) AIRCRAFT EXPERIENCED A NTS EVENT DURING LANDING PHASE, WITH POWER LEVER REDUCED TO FLIGHT IDLE, AC CONFIGURED FOR LANDING, WITH NORMAL ATTITUDE FOR LANDING. AIRCRAFT LANDED AND TAXIED WITH NO OTHER PROBLEMS REPORTED. AIRCRAFT INSPECTE D, FLIGHT IDLE BLADE ANGLES ADJUSTED AND RETURNED TO SERVICE. DUE TO SOAP RESULTS AND NTS GROUND CHECK RESULTS, THE ENG INE WAS SUBSEQUENTLY REMOVED FROM SERVICE. NTS ACTION IS POTENTIALLY DUE TO (SUSPECTED) COMBINATION OF WEAR OF THE QUILL SHAFT AND BALL LOCK WHICH WOULD HAVE IN EFFECT, CAUSED A REDUCTION IN THE PRELOAD OF THE NTS SYSTEM, THEREBY ALLOWING T HE NTS TO ACTIVATE AT A LOWER THRESHOLD THAN SET CALIBRATION. CODE (TC NR20070629001) 4 T E4WE 20081105 2008 11 5 CA070629002 1 20070629 G 2910 PACKING HYD ACTUATOR DEFECTIVE W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) WHILE REPLACING O-RINGS AND BACK-UP SEALS IN SOME HYDRAULIC ACTUATORS, FOUND SOME OF NEW BACK-UP SEALS DEFECTIVE. THE CHAMFERED EDGE OF THE SEAL IS TO SHORT WHICH IN TURN CAUSED THE EDGE TO DAMAGE THE O-RING. IT SEEMS TO ACT AS A KNIF E EDGE. ALL SEALS IN A BATCH WERE NOT FOUND LIKE THIS, ONLY A FEW. THAT IS WHY SOME OF OUR ACTUATORS HAVE BEEN LEAKING DUE TO THE BACK-UP SEAL CUTTING THE O-RING. WILL BE SENDING A REPORT AND PICTURES TO THE VENDOR. 2007082000062 20070820 00062 WP 2007 8 20 CA070629003 1 20070525 G 2916 D2112 RESERVOIR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE HYD SYSTEM LEAKING W K NONE K J FLUID LOSS WARNING INDICATION IN INSP/MAINT 1 CA 196 (CAN) DURING POST INSPECTION RUN UPS, IT WAS WITNESSED THE HYDRAULIC RESERVIOR WAS VENTING HYDRAULIC FLUID OUT OF THE VE NT. NO DETERMINING FACTOR COULD BE FOUND, SO THE RESERVIOR WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 2007062 9003) 1 G 7 1 3O 3 O H11NM 1E4 2008022000322 20080220 00322 SO 2008 2 20 CA070703001 1 20070628 G 3211 4032700 TRUNNION PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL LT MLG CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 19470 317405228 (CAN) DURING A SCHEDULED LAYOVER, ON POST FLIGHT WALK AROUND THE PILOTS NOTICED THAT THE LT GEAR STRUT WAS DEFLATED. EXA MINATION BY MAINT SHOWED THAT THE TRUNNION HAD CRACKED ALONG THE WELD THAT HOLDS THE (2) HALVES OF THE TRUNNION TOGETHER . IT HAD CRACKED UP PAST THE ORINGS INTO THE SEALED AREA OF THE STRUT. IT IS UNKNOWN IF THIS STRUT IS THE ORIGINAL AIRC RAFT ONE. (TC NR 20070703001) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081104 EA 2008 11 4 CA070703002 2 20070509 G 7414 M3548 ROTOR SHAFT SLICK 4370 ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA MAGNETO SHEARED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA 1272 (CAN) A STUDENT PILOT NOTICED THAT THE ENGINE WOULD NOT RUN WHEN THE RT MAGNETO WAS SELECTED. MAINT WAS CALLED AND THE R T MAGNETO WAS REMOVED FROM THE ENGINE AND DISSASSEMBLED. THE ROTOR WAS FOUND SHEARED AT THE CAM ROTOR SLOT. (TC NR 2007 0703002) 1 L 7 1 3O 3 O 0 A76EU 1E10 2008013100071 20080131 00071 SW 2008 1 31 CA070703003 1 20070701 G 2822 1C27 CARTRIDGE AIRBORNE BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL BOOST PUMP UNSERVICEABLE W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) CAUTION LIGHT ILLUMINATED DURING FLIGHT INDICATING A BOOST PUMP FAILURE. FUEL SYSTEM INSPECTED FWD BOOST FOUND TO BE NOT OPERATING. CARTRIDGE CHANGED OUT WITH AN OVERHAULED UNIT.FUEL SYSTEM SERVICABLE. (TC NR 20070703003) 1 G 7 1 3U 3 U H2SW E4CE 2007082000063 20070820 00063 SO 2007 8 20 CA070703004 2 20070613 G 8530 AEC631397 CYLINDER CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO HARTZL HCC3Y HCC3YF1 GL NR 2 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 484 454 547388 (CAN) CYLINDER CRACKED FROM FUEL INJECTOR TO SPARK PLUG HOLE, CRACK FOUND DURING 100 HR INSPECTION (TC NR 20070703004) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P25EA 2007082000064 20070820 00064 SO 2007 8 20 CA070703005 2 20070608 G 7414 662 MAGNETO CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C401 GL ENGINE UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 300 (CAN) SHEARED MOUNTING FLANGE HOUSING. (TC NR 20070703005) 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2007082000065 20070820 00065 NM 2007 8 20 CA070703006 1 20070702 G 2612 4739551 CONTROL PANEL BOEING 737 737* NM GE CFM56 CFM567B24 NE FIRE CONTROL DAMAGED W K NONE N FALSE WARNING IN INSP/MAINT 1 CA 10460 10460 (CAN) ON JULY 2/07 IN PREPARATION FOR THE DAYS FLYING THE CREW REPORTED THE CARGO FIRE BELL SOUNDING. THE FORWARD CARGO FIRE C/BS WERE FOUND POPPED AND SMOKE WAS COMING FROM THE FLIGHT DECK CARGO FIRE DETECTOR PANEL. THIS RESULTED IN THE FWD CARGO PIT EXTINGUISHER DISCHARGING ITSELF. THE FIRE PANEL MODULE AND THE DEPLETED FIRE BOTTLE WERE REPLACED. THE OE M TO WHICH THE DAMAGED PANEL WAS SENT HAS BEEN REQUESTED TO INVESTIGATE, PROVIDE A DETAIL STRIP REPORT AND PHOTOS. FURT HER INFORMATION WILL BE SUBMITTED AT THE CONCLUSION OF THIS INVESTIGATION. (TC NR 20070703006) 2 L 7 2 4F 4 F RT A16WE E00055EN 2007082000066 20070820 00066 2007 8 20 CA070704001 1 20070703 G 7810 31015827 EXHAUST DUCT GARRTT TPE331 TPE33110UA 01514 WP ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON ROUTINE INSPECTION, THE MAINTENENCE CREW FOUND THE EXHAUST DUCT CRACKED. THE ENGINE WAS REMOVED AND THE EXHAU ST DUCT WAS REPLACED WITH A OVERHAULED ONE. NO OTHER PROBLEMS WERE DETECTED AT THIS INSPECTION. (TC NR 20070704001) 4 T E4WE 2007082000067 20070820 00067 EA 2007 8 20 CA070704002 1 20070703 G 2750 C6CF14681 ROD DHAV DHC6 DHC6300 2802606 EA TE FLAPS MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) DURING INSPECTION OF THE FLAP RODS IAW S/B 6/502 AND 6/388 IT WAS NOTICED THAT THE SWAGED END OF THE FLAP ROD WAS NOT COMPRESSED. UPON INSPECTION OF THE ROD IT WAS NOTED THAT THE COLLAR WAS NOT IN THE CORRECT POSITION AND HAD NOT BEE N COMPRESSED ENOUGH. THE SWAGED END MEASURES 0.9880OF AN INCH AND THE END IN QUESTION MEASURES 1.0055 OF AN INCH. THERE IS NORMALLY A BUMP IN THE SWAGED END, BUT THE END IN QUESTION DOES NOT HAVE ANY BUMP ON IT. (TC NR 20070704002) 1 H 7 2 3T RT A9EA 2007082000068 20070820 00068 NM 2007 8 20 CA070704003 1 20070704 G 5210 85210276101 BOLT DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HANDRAIL SUPPORT LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CREW REPORTED THAT MAIN CABIN DOOR WOULD STOP OPENING SOMETIMES. FLIGHT ATTENDANT HAD TO PUSH THE HANDRAIL TO GET THE DOOR FULLY OPEN. LINE MAINTENANCE FOUND REAR HANDRAIL SUPPORT STRUT BOLT (REF IPC 52-10-00-35-50) UNSCREWED AND CONT ACTING WITH HANDRAIL LOWER NEWEL STRUT (REF IPC 52-10-00-40-90). THE BOLT HAS NO LOCKING FEATURE. THE BOLT WAS TIGHTENED , SYSTEM CHECKED SERVICEABLE AND THE AIRCRAFT RELEASED INTO SERVICE (TC NR 20070704003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081104 CE 2008 11 4 CA070704004 1 20070703 G 2435 BRUSHES CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL STARTER GEN WORN W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA 1005 (CAN) PILOT ATTEMPTED TO START AIRCRAFT. AIRCRAFT FAILED TO START. FURTHER INVESTIGATION REVEALED A STARTER BRUSH HAD FR ACTURED AND SEPARATED INTO A FEW PIECES. DAMAGE TO THE COMMUNTATOR WAS FOUND. IT WAS APPROXIMATELY 240 HRS SINCE THE LAS T BRUSH INSPECTION AND NO ISSUE WERE NOTED. (TC NR 20070704004) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2007082000069 20070820 00069 NM 2007 8 20 CA070704005 1 20070627 G 5210 R2210151 DOOR FRAME ROBSIN R22 R22BETA 7640110 NM LYC O320 O320B2C 41508 EA PAX DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING VISUAL INSPECTION TO COMPLY WITH AWD 2005-16-05 LT DOOR ASSY WAS FOUND CRACKED. FUTHER INSPECTION OF THE T ECH-TOOL DOOR AND FRAME REVEALED ADDITIONAL CRACKS. DOOR FOUND TO BE U/S AND REMOVED FROM A/C. (TC NR 20070704005) 1 G 7 1 3O 3 O H10WE E274 2008013100037 20080131 00037 NM 2008 1 31 CA070704006 1 20070627 G 5210 R2210152 FRAME ROBSIN R22 R22BETA 7640110 NM LYC O320 O320B2C 41508 EA RT DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING VISUAL INPECTION TO COMPLY WITH AWD 2005-16-05 RT DOOR ASSY WAS FOUND CRACKED. FUTHER INPECTION OF THE TECH -TOOL DOOR AND FRAME ASSY REVEALED ADDITIONAL CRACKS. DOOR FOUND TO BE UNSERVICEABLE AND REMOVED FROM A/C. (TC NR 200707 04006) 1 G 7 1 3O 3 O H10WE E274 2007082000070 20070820 00070 2007 8 20 CA070704007 4 20070704 G 6113 05503214 BULKHEAD CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 652 (CAN) BULKHEAD IS CRACKED AROUND SEVERAL OF THE PROP THROUGH BOLT HOLES. (TC NR 20070704007) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007082000071 20070820 00071 2007 8 20 CA070704008 4 20070517 G 6113 05503214 BULKHEAD CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA SPINNER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 320 (CAN) CRACKED AROUND SEVERAL OF THE PROP BOLT THROUGH HOLES. (TC NR 20070704008) 1 H 7 1 3O 3 O NT 3A12 E274 2007082000072 20070820 00072 NE 2007 8 20 CA070704009 2 20070509 G 7313 ST3367009 PACKING AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE FUEL MANIFOLD DEFECTIVE W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) SHORTLY AFTER TAKE-OFF PASSENGERS REPORTED FLUID ESCAPING FROM THE ENGINE. THE PILOT REDUCED ENGINE POWER AND DIV ERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED LEAKING FUEL NOZZLE MANIFOLD PACKINGS. MFG HAS DETERMINED THE PACKINGS TO BE ASSOCIATED WITH A MANUFACTURER`S QUALITY ESCAPE (REFERENCE: MFG SERVICE BULETIN SB21740) (TC NR 20070 704009) 2 H 7 2 4T 4 T RT E20NE 2007082000073 20070820 00073 EA 2007 8 20 CA070704010 2 20070505 G 7532 BLEED VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA COMPRESSOR FAULTED W E ENGINE SHUTDOWN J WARNING INDICATION AP APPROACH 1 CA 4107 (CAN) ON APPROACH, AN ENGINE FADEC CAUTION LIGHT ILLUMINATED AND THE PILOT ELECTED TO SHUTDOWN THE ENGINE (PRECAUTIONARY ). SUBSEQUENT INSPECTION REVEALED A FAULTY INTERCOMPRESSOR BLEED VALVE. (TC NR 20070704010) 2 H 7 2 4T 4 T RT A13NM E00062EN 2007082000074 20070820 00074 NE 2007 8 20 CA070704011 2 20070514 G 7261 OIL SYSTEM PIAGIO P180 P180 6960204 EU PWA PT6 PT6A66 52043 NE ENGINE OVERTEMP W E ENGINE SHUTDOWN M J OVER TEMP WARNING INDICATION CR CRUISE 1 CA 104058 (CAN) IN FLIGHT, THE ENGINE OIL TEMPERATURE WAS SEEN TO INCREASE AND THE ENGINE WAS SHUTDOWN. POST-FLIGHT INSPECTION RE VEALED OIL LEAKAGE AT THE ENGINE (C) FLANGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070704011) 1 H 7 2 3O 4 T RT A59EU E26NE 2007082000075 20070820 00075 EU 2007 8 20 CA070704012 1 20070511 G 2913 3022375 SEAL REIMS 406 F406 7535723 EU PWA PT6 PT6A112 52043 NE HYDRAULIC PUMP FRACTURED W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) IN CRUISE, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE AND SUBESQUENTLY DECREASE. OIL WAS SEEN ESCAPING FROM THE EN GINE NACELLE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INVESTIGATION REVEALED A FRACTURED HYDRAULIC PUMP PAD OIL SEAL. (TC NR 20070704012) 1 L 7 2 3T 3 T RT A54EU E4EA 2007082000076 20070820 00076 NE 2007 8 20 CA070704014 2 20070519 G 7310 ST3367009 PACKING AEROSP ATR72 ATR72212 8680945 EU PWA PW120 PW127 NE FUEL MANIFOLD FRACTURED W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) FUEL WAS FOUND LEAKING FROM THE FUEL MANIFOLD DRAIN DURING TAXI. SUBSEQUENT INSPECTION REVEALED LEAKING FUEL MANI FOLD PACKINGS. MFG HAS DETERMINED THE PACKINGS TO BE ASSOCIATED WITH A MANUFACTURER`S QUALITY ISSUE (REFERENCE MFG SB21 740). (TC NR 20070704014) 2 H 7 2 4T 4 T RT A53EU E20NE 2007082000077 20070820 00077 NE 2007 8 20 CA070704015 2 20070511 G 7261 ENGINE PWA PT6 PT6A65AR 52043 NE HARTZL HCB5M HCB5MP3 GL SEIZED W E A ENGINE SHUTDOWN UNSCHED LANDING B R SMOKE/FUMES/ODORS/SPARKS PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 97048 (CAN) IN CRUISE, SMOKE WAS OBSERVED IN THE CABIN AND ENGINE POWER REDUCED UNCOMMANDED. THE ENGINE WAS SHUTDOWN IN FLIGH T AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED SEIZURE OF THE ENGINE AND OIL LEAKAGE . MFG WILL MONITOR THE INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070704015) 4 T E4EA 6 C P44GL 2007082000078 20070820 00078 EA 2007 8 20 CA070704016 2 20070513 G 7210 GEARBOX DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE DISTRESSED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA 41553 (CAN) PRIOR TO START OF DESCENT, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE. DURING THE DESCENT THE ENGINE FLAMED OUT. S UBSEQUENT INSPECTION REVEALED REDUCTION GEARBOX DISTRESS. MFG WILL INVESTIGATE THE EVENT AND ADVICE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070704016) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007082000079 20070820 00079 NE 2007 8 20 CA070704017 2 20070523 G 7200 ENGINE BEECH 200 B200 1152922 CE PWA PT6 PT642A NE OVERTEMP W E A ENGINE SHUTDOWN UNSCHED LANDING A J FLAME/FIRE WARNING INDICATION CR CRUISE 1 CA PJ0243 (CAN) IN CRUISE, THE ENGINE INTER-TURBINE TEMPERATURE WAS SEEN TO INCREASE AND FLAMES AND SPARKS WERE SEEN EXITING THE E XHAUST. THE ENGINE WAS SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISH ED. (TC NR 20070704017) 1 L 7 2 4T 4 T A24CE E4EA 20081104 2008 11 4 CA070704018 1 20070702 G 3240 95214071 LINER LORAL 95409761 BRAKE ASSY SEPARATED W D RETURN TO BLOCK O OTHER LD LANDING 1 CA 2 (CAN) DURING THE ROLLOUT AFTER LANDING, THE FLIGHT CREW NOTICED THE LT BRAKE PEDAL TRAVEL WAS MORE THAN NORMAL. UPON INS P IT WAS NOTED THAT THE FIXED LININGS P/N 9521407-1 (2 OF THE 3) HAD SEPARATED FROM THE BRAKE ASSY. THE LININGS WERE LAT ER LOCATED ON THE RUNWAY THAT THE ACFT HAD LANDED ON. THERE WAS NO VISIBLE EVIDENCE AS TO WHY THE LININGS SEPARATED. ONE THEORY IS THAT A FOREIGN OBJECT SUCH AS A ROCK WAS THROWN INTO THE BRAKE ASSY AT THE TIME OF LANDING. THE ACFT WAS INSP ECTED, THE BRAKE ASSY WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE. (TC NR 20070704018) 2007082000080 20070820 00080 2007 8 20 CA070705001 2 20070528 G 7320 FADEC CESSNA 680 680CE 2076811 CE MALFUNCTIONED W O OTHER R F PARTIAL RPM/PWR LOSS FLT CONT AFFECTED LD LANDING 1 CA (CAN) THE ENGINES FAILED TO RESPOND TO THROTTLE INPUT FOLLOWING TOUCHDOWN. PRELIMINARY INVESTIGATION REVEALED THE ISSUE RELATED TO THE FADEC`S RESPONSE TO ARMING THE THRUST REVERSERS ON APPROACH (NOT AN AFM PROCEDURE), COUPLED WITH A BOUNCE FOLLOWING INITIAL TOUCHDOWN. P&WC WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20070705001) 2 L 7 2 4F RC T00012WI 2007082000081 20070820 00081 CE 2007 8 20 CA070705002 1 20070530 G 2435 SEAL BEECH 200 B200 1152922 CE PWA PT6 PT642A NE STARTER GEN LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ENGINE OIL PRESSURE WAS SEEN TO REDUCE AND FLUCTUATE IN CRUISE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FAULTY LIP SEAL (RECENTLY REPLACED) ON THE STARTER GENERATOR DRIVE SHAFT. (TC NR 20070705002) 1 L 7 2 4T 4 T A24CE E4EA 2007082000082 20070820 00082 EU 2007 8 20 CA070705003 1 20070528 G 2435 3022383 SEAL AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF5 NE STARTER GEN LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ON A MAINTENANCE FLIGHT, THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUB SEQUENT INSPECTION REVEALED A LEAKING STARTER GENERATOR GARLOCK LIP SEAL. (TC NR 20070705003) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2007082000083 20070820 00083 NE 2007 8 20 CA070705004 2 20070519 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE POWER LOSS W A UNSCHED LANDING E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA PC0810 (CAN) IN CRUISE FLIGHT, THE ENGINE EMITTED A LOUD NOISE AND LOST POWER, RESULTING IN A FORCED LANDING. MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND REPORT ROOT CAUSE ONCE DETERMINED. (TC NR 20070705004) 1 H 7 1 3T 3 T A37CE E4EA 2007082000084 20070820 00084 NE 2007 8 20 CA070705005 2 20070303 G 7321 3244768 FCU BEECH 1900 1900C 1154161 CE PWA PT6 PT642A NE ENGINE DEFECTIVE W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) IN FLIGHT THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION RESULTING IN AN OVER-TORQUE CONDITION. SUBSEQUENT IN SPECTION REVEALED A FAULTY FCU. (TC NR 20070705005) 2 L 7 2 4T 4 T RT A24CE E4EA 2007082000085 20070820 00085 EA 2007 8 20 CA070705006 1 20070618 G 5330 215300174 SKIN CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE BS 584.5 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1308 (CAN) A 3 INCH CRACK WAS DISCOVERED IN THE SKIN. CAUSE AT HIS TIME IS UNKKOWN AIND IS UNDER FURTHER INVESTIGATRION (TC NR 20070705006) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2007082000086 20070820 00086 EA 2007 8 20 CA070705007 1 20070618 G 5330 215300174 SKIN CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE BS 584.5 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1308 (CAN) A (5) INCH CRACK WAS DISCOVERED IN THE SKIN AT APPROX F/S 584.50 AND W/L100. CAUSE AT THE TIME IS NOT KNOWN AND IS UNDER FURTHER INVESTIGATION. (TC NR 20070705007) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 20081104 2008 11 4 CA070705008 2 20070705 G 7414 10160858 HOUSING MAGNETO CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 499 (CAN) MAG SENT IN FOR 500 HR INSP. FOUND MOUNTING EAR CRACKED WHERE HOLD-DOWN NUT AND WASHER CONTACT EAR. THIS IS A NEW STYLE OF CASTING FROM MFG WITH THE NAME "EMPIRE" CAST INTO THE INTERIOR OF THE HSG AND JUST THE LETTERS "TCM" CAST ON TH E OUSIDE OF THE HSG. THE OLD STYLE OF HSG HAD EITHER "TCM" OR "BENDIX" AND THE MAGNETO INFORMATION BLOCK CAST INTO THE O UTSIDE OF THE HSG. THE OLD STYLE OF HSG WOULD CRACK IF OVERTORQUED OR IF THE WRONG GASKET WAS USED IN APPROXIMATELY 1 OU T OF 30 MAGS RECEIVED FOR INSP. IN THIS CASE 4 OF 6 MAGS WITH THE NEW CASTING HAVE CRACKS IN THIS LOCATION. SEPERATE SDR `S WILL BE FILED FOR EACH MAGNETO. (TC NR 20070705008) 20081105 2008 11 5 CA070705011 2 20070705 G 7414 10160858 HOUSING BENDIX MAGNETO CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 2000 (CAN) MAGNETO SENT IN AS A CORE, BUT HAS SAME CRACK AS 3 OTHER MAGNETOS RECEIVED FOR REPAIR. THIS CRACK IS IN A NEW STYL E OF CASTING PUT INTO PRODUCTION BY MFG. 2007082000087 20070820 00087 SW 2007 8 20 CA070705012 1 20070705 G 2434 ALU8521LS ALTERNATOR HUGHES 269 269C1 8059504 SW LYC O360 HIO360* 41514 EA FAILED W E ENGINE SHUTDOWN H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA 400 (CAN) ALTERNATOR FAILED ON STARTUP. FOUND ROTOR JAMMING AND PULLEY HAD OVERHEATED. LOOSE PARTS HEARD INSIDE ALTERNATOR . NO PREVIOUS INDICATIONS OF IMPENDING FAILURE. (TC NR 20070705012) 1 G 7 1 3O 3 O O 4H12 1E10 20081104 SW 2008 11 4 CA070705013 1 20070702 G 7810 GASKET HUGHES 269 269C1 8059504 SW LYC O360 HIO360G1A 41898 EA EXHAUST CRACKED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 210 (CAN) DURING ROUTINE INSP, IT WAS NOTICED THAT NEARLY ALL OF THE GASKET BETWEEN THE FWD FLANGE AND THE EXHAUST MUFF HAD CRACKED AND FALLEN AWAY, LEAVING THE POSSIBILITY OF A CABIN EXHAUST LEAK. (TC NR 20070705013) 1 G 7 1 3O 3 O O 4H12 1E10 2008022000323 20080220 00323 CE 2008 2 20 CA070706001 1 20070706 G 3230 AN33701 RELAY BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA HARTZL HCB3T HCB3TN3 GL LANDING GEAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ANNUAL INSPECTION OF THE HYD LANDING GEAR INSTALLATION THE LANDING GEAR RELAY EXHIBITED SIGNS OF HEAVY PITT ING AND METAL TRANSFER. THE LANDING GEAR RELAY WAS REPLACED. (TC NR 20070706001) 1 L 7 2 3T 4 T 3A20 E4EA 6 C P15EA 2007082000088 20070820 00088 GL 2007 8 20 CA070706002 2 20070705 G 7230 23056109 SCROLL RROYCE BELL 206 206L1 1182107 SW ALLSN 250C 250C28 03013 GL COMPRESSOR WARPED W K NONE O OTHER IN INSP/MAINT 1 CA 7120 CAC70614 (CAN) DURING A GROUND RUN AN AIR LEAK WAS FOUND AT THE SCROLL DIFFUSER SPLIT LINE. COMPRESSOR ASSY WAS CHANGED OUT. (TC NR 20070706002) 1 G 7 1 3U 3 U H2SW E1GL 2007082000089 20070820 00089 EU 2007 8 20 CA070706003 1 20070703 G 3240 BRAKE ASSY EMB ERJ190 ERJ190100IGW 3260408 EU GE CF34 CF34* NE MLG OVERHEATED W O OTHER M J OVER TEMP WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) HOT BRAKE INDICATION ON TAXI IN OF 460 CELSIUS. BRAKE OVERTEMP INSPECTION CARRIED OUT WITH NO FAULTS. CMC MESSAG E BRAKE TEMP SENSOR OVERHEAT. IAW FIM, REPLACE TEMP SENSOR. PLACED ON MEL DUE NO STOCK. FOLLOWING DAY, RT IB/OB BRAKE TEMPERATURES CREPT UP TO 110/ 195 CELSIUS. THERE IS A HISTORY OF HYDRAULIC CONTROL PROBLEMS, POSSIBLE CAUSE IN THIS CASE MAY BE THE BRAKE CONTROL VALVE. (TC NR 20070706003) 2 L 7 2 4F 4 F RT A57NM E15NE 2007082000090 20070820 00090 GL 2007 8 20 CA070706004 2 20070705 G 7320 23065144 FUEL CONTROL BELL 206 206L1 1182107 SW ALLSN 250C 250C28 03013 GL ENGINE UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 14467 1070 (CAN) FUEL CONTROL WAS INTERMITTENT ON ENGINE LIGHT-OFF DURING A START. FUEL CONTROL CHANGED OUT. (TC NR 20070706004) 1 G 7 1 3U 3 U H2SW E1GL 2008022000324 20080220 00324 NM 2008 2 20 CA070706005 1 20070703 G 5280 450530501 SHEAR PIN PIPER PA60 PA60600 7106001 NM LYC O540 IO540K1J5 41532 EA HARTZL HCC3Y HCC3YR2 NE LG DOOR SHEARED W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF THE PILOT SELECTED GEAR UP, THE GEAR UP LIGHT FAILED TO ILLUMINATE. THE LANDING GEAR WAS EXTENDED AN D THE AIRCRAFT LANDED AT AIRPORT. UPON INVESTIGATION THE LANDING GEAR DOOR SHEAR PIN WAS FOUND SHEARED. THE PIN WAS REPL ACED, THE AIRCRAFT WAS PLACED ON JACKS AND A FUNCTION CHECK OF THE LANDING GEAR AND INDICATING SYSTEM WAS COMPLETED WITH NO FAULTS. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070706005) 1 M 7 2 3O 3 O RT A17WE 1E4 5 C P25EA 2007082000091 20070820 00091 EA 2007 8 20 CA070707001 1 20070706 G 2910 0860163002 ACCUMULATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE HYD SYSTEM SEPARATED W D RETURN TO BLOCK R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 25942 (CAN) DURING TAXI-OUT, HYD 1 LO PRESS MESSAGE CAME ON. THE CREW REPORTED LOUD BANG FROM AFT PART OF CABIN. CREW EXECUT ED RELEVANT ABNORMAL CHECKLISTS AND RETURNED TO RAMP. AFTER VERIFICATION BY THE MTCE CREW, THEY FOUND OUT THAT THE NR 2 HYDRAULIC ACCUMULATOR SEPARATED. (TC NR 20070707001) 2 L 7 2 4F 4 F RT A21EA E15NE 20081104 2008 11 4 CA070708001 4 20070421 G 2562 ELT10 ELT CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA CABIN MALFUNCTIONED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) ELT FOUND DEFECTIVE DURING ROUTINE INSP. ELT WAS FOUND MAKING SQUELCHING SOUND THROUGH RADIO, ON FURTHER INVESTIGA TION IT WAS FOUND THAT ELT WAS ACTIVATED WHICH COULD NOT BE SWITCHED-OFF EVEN AFTER DISCONNECTING THE CONNECTOR/POWER. E LT WAS REMOVED FROM ACFT AND BATTERY WAS DISCONNECTED TO DEACTIVATE THE ELT. ELT WAS SENT FOR REPAIR. (TC NR2007070800 1) 1 H 7 1 3O 3 O NT 3A12 E274 2007082000092 20070820 00092 WP 2007 8 20 CA070709001 1 20070706 G 2700 24031404021 SHAFT CVAC 30 30 2423202 WP ALLSN 501D 501D13H 03004 GL ALLSN A6441 A6441FN606 GL ROLL FORCE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE ROLL FORCE MODIFICATION WAS BEING INSTALLED IN THE AIRCRAFT IAW STC SA05-49. UPON TORQUING THE PILOT`S YOKE ASSEMBLY SHAFT IAW THE INSTRUCTIONS CONTAINED IN DOCUMENT K130-102-001-012, THE FLANGE ON THE SHAFT P/N 240-3140402-1 CR ACKED. THE REMAINING AIRCRAFT IN THE FLEET WERE INSPECTED FOR SIGNS OF PLAY WITH NO DEFECTS NOTED. THE AIRCRAFT ARE ALS O BEING INSPECTED FOR EXCESSIVE BREAK AWAY TORQUE OF CONTROL YOKE SHAFT NUT. ANY ADDITIONAL FINDINGS WILL BE FORWARDED U PON COMPLETION OF THE INSPECTIONS. (TC NR 20070709001) 2 L 7 4 4J 4 T 4A30 E282 6 C P898 2007082000093 20070820 00093 NM 2007 8 20 CA070709002 1 20070707 G 2420 HCAIN022 GENERATOR DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE NR 2 INOPERATIVE W O OTHER H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA (CAN) AT THE END OF EXTENSIVE POST BLOCK CHECK GROUND RUNS; THE NR 2 ENG GEN FELL OFF LINE AND NR 1 TRU AND AC BUS FELL OFF LINE; TRIED TO POWER BACK AND RESET IT WAS NOTICED THAT THE AC GEN CAUTION LIGHT WAS NOT SHOWING. SO THE AIRCRAFT WA S SHUTDOWN AND AFTER SOME INVESTIGATION IT WAS FOUND THAT THE AC GEN CONTACTOR HC-AIN-022 HAD FAILED INTERNALLY MELTING THE RELAY AND ASSOCIATED WIRING. (TC NR 20070709002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008031900147 20080319 00147 NE 2008 3 19 CA070709003 2 20070705 G 7320 5018T64G02 MANIFOLD SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE LT FUEL FRACTURED W F E ACTIVATE FIRE EXT. ENGINE SHUTDOWN B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 CA 10521 209 280140MA (CAN) THE PILOTS NOTICED A WARM SEMI SMOKE SMELL, AND OBSERVED A T5 RISE IN NR 1 ENGINE. THE FIRE LIGHT ACTIVATED ON NR 1 ENGINE. THE ENGINE WAS SHUT DOWN AS WELL AS A THE FIRE BOTTLES WERE ACTIVATED. THE AC LANDED WITH ONE ENGINE WITH NO I NCIDENT. THE ENGINE WAS REPLACED. ENGINE TSN 23764.8, TSO 2373.5, (TC NR 20070709003) 2 G 7 2 4U 4 U 1H15 1E3 2007082000094 20070820 00094 NM 2007 8 20 CA070709004 1 20070706 G 3244 DR7622T TIRE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) LT INNER TIRE BLOWN AFTER TAKEOFF. UNSCHEDULED LANDING CARRIED OUT. A/C TOWED TO HANGER. INSPECTION AND NR 1 AND NR 2 MAINWHEELS REPLACED. TIRE WAS A RETREAD R2. (TC NR 20070709004) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081104 CE 2008 11 4 CA070710001 1 20070705 G 2434 DOFF10300JR ALTERNATOR CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA ENGINE INOPERATIVE W O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 CA 351 (CAN) ALTERNATOR NOT CHARGING . (TC NR 20070710001) 1 H 7 1 3O 3 O NT 3A12 E274 2007082000095 20070820 00095 NM 2007 8 20 CA070710002 1 20070615 G 3510 17426008 OXYGEN MASK BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU COCKPIT INOPERATIVE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) F/O`S OXYGEN MASK WHEN DONED, WEARER COULD NOT EXHALE WHEN BREATHING. ENGINEERING INVESTIGATION INDICATES THAT THE MASK EXHALE VALVE IS DEFECTIVE. MASK REPLACED. AIRCRAFT RETURNED TO SERVICE SATISFACTORY. MASK HAS BEEN RETURNED TO THE MANUFACTURER FOR REPAIR AND WITH A REQUEST FOR A STRIP REPORT. (TC NR 20070710002) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007082000096 20070820 00096 NM 2007 8 20 CA070710003 1 20070531 G 3150 301450301 PSEU BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU PROXIMITY SENSOR INOPERATIVE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) ON DEPARTURE CLIMBING THROUGH 9000 FT, THE ENGINE DISPLAY POWERPLANT ADVISORY ILLUMINATED. FOLLOWING DISCUSSIONS W ITH BASE ENGINEERING THE CREW DECIDED TO RETURN THE AIRCRAFT TO BASE WHERE AN APPROACH AND LANDING WAS CARRIED OUT WITHO UT INCIDENT. THE POWERPLANT ADVISORY FAULT CODE 338 IS THE 3RD OCCURRANCE ON THIS AIRCRAFT. FOLLOWING ADVICE FROM THE MF G AND DETAILED TROUBLESHOOTING THE AIRCRAFT`S PSEU WAS REPLACED. AIRCRAFT WAS RELEASED BACK TO SERVICE WHERE IT HAS OPER ATED SINCE WITHOUT INCIDENT. (TC NR 20070710003) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007082000097 20070820 00097 EA 2007 8 20 CA070710004 2 20070426 G 7230 3034051 GUIDE VANE DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL ENGINE FAILED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 73 86123 (CAN) DURING FLIGHT, THE TURBINE TEMPERATURE ROSE SUDDENLY FROM 738 TO 785 DEGREES CELSIUS. A BORESCOPE INSPECTION REVEA LED DAMAGE TO THE CT GUIDE VANE. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE HOT SECTION WAS REMOV ED FROM THE ENGINE AND FURTHER INSPECTED. ONE OF THE CT GUIDE VANE’S AIRFOIL-COOLING DUCT SURFACE HAD BEEN PREVIOUSLY RE PAIRED. THE VANE CRACKED/FAILED AROUND THE WELDS ALLOWING THE COOLING DUCT TO OPEN UP AND BREAK AWAY. WITHOUT THE PROPE R COOLING THE VANE BURNED THROUGH. THE HOLE IN THE VANE CHANGED THE AIRFLOW ALLOWING DIRECT FLOW TO THE CT BLADES IN TUR N CAUSING THEM TO OVERHEAT. GUIDE VANE CSO 48. THIS IS THE SECOND FAILURE OF THIS NATURE AS THE OTHER FAILURE OCCURRED 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2007082000098 20070820 00098 CE 2007 8 20 CA070711001 1 20070605 G 7120 TUBE CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO HARTZL HCC3Y HCC3YF1 GL RT NACELLE CRACKED W K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 CA 2590 (CAN) ONE TUBE CRACKED NEAR RT REAR ENGINE LOAD MOUNT. NEW MOUNT INSTALLED. (TC NR 20070711001) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P25EA 2008022000325 20080220 00325 CE 2008 2 20 CA070711002 1 20070708 G 3020 1013800019 BOOT BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL HORIZ STAB DAMAGED W A UNSCHED LANDING F E FLT CONT AFFECTED VIBRATION/BUFFET CL CLIMB 1 CA (CAN) THE AIRCRAFT DEPARTED AND BEGAN TO CLIMB TO CLEARED ALTITUDE. AS THE AIRCRAFT PASSED 5500 FEET THERE WAS A VIBRATI ON OR BUFFETING FELT THROUGH THE CONTROL COLUMN. THE AIRCRAFT RETURNED TO BASE WITHOUT INCIDENT. A THROUGH INSPECTION WA S CARRIED OUT WHICH REVEALED A DAMAGED LT HORIZONTAL DE-ICE BOOT. SEVERAL HOLES WERE FOUND AND REPAIRED IAW APPROVED PRO CEDURES. THE AIRCRAFT WAS RETURNED TO SERVICE AND OPERATED WITHOUT ANY FURTHER PROBLEMS. (TC NR 20070711002) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007082000099 20070820 00099 EA 2007 8 20 CA070711003 1 20070711 G 2810 215640024 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 1924 (CAN) FUEL CELL NR 7 RT, LEAKING BY THE LOWER INTERCONNECT CORNER. A/C HOURS: 1924 CYCLES: 1236 DROPS: 9808 (TC NR 20 070711003) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2007082000100 20070820 00100 EA 2007 8 20 CA070711004 1 20070711 G 2810 K215T6400212 FUEL CELL CNDAIR CL215 CL2156B11215 EA LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) TESTED BEFORE INSTALLATION, THE CELL HAS BEEN FOUND WITH LOOSE LOWER PROBED ADAPTOR AND LEAKING BY THE TOP CORNER REPAIR PATCH . THE CELL HAS BEEN REJECTED. (TC NR 20070711004) 2 H 7 2 4T RT A14EA 2007082000101 20070820 00101 CE 2007 8 20 CA070711005 1 20070711 G 2510 05142031 SEAT CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DEFECT REPORTED IN THE JOURNEY LOG BOOK THAT RT SEAT WOULD NOT ADJUST. REMOVED SEAT, INSPECTED, AND FOUND THE SEA T BOTTOM FRAME CRACKED COMPLETELY IN (2) PIECES. AREA IS DIFFICULT TO INSPECT BECAUSE OF UPHOLSTERY INSTALLATION. LOWE ST TIME IN THE FLEET. (TC NR 20070711005) 1 H 7 1 3O 3 O NT 3A12 E274 2007082000102 20070820 00102 EA 2007 8 20 CA070711006 1 20070711 G 2810 K215T6400212 FUEL CELL CNDAIR CL215 CL2156B11215 EA LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) TESTED BEFORE INSTALLATION, THE CELL HAS BEEN FOUND LEAKING BY A PIN HOLE NEAR UPPER PROBE ADAPTOR AND REJECTED. ( TC NR 20070711006) 2 H 7 2 4T RT A14EA 2007082000103 20070820 00103 GL 2007 8 20 CA070711007 1 20070710 G 2823 TC17300 SELECTOR DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE FUEL STIFF W K NONE O OTHER TX TAXI/GRND HDL 1 CA (CAN) REMOVED CABLE DRUM FROM FUEL SELECTOR, LUBRICATED SELECTOR WITH YIELD AND REINSTALLED CABLE DRUM. (TC NR 200707110 07) 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2007082000104 20070820 00104 NM 2007 8 20 CA070712001 1 20070709 G 6120 699018002 CONTROLLER BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NR1 ENGINE MALFUNCTIONED W A UNSCHED LANDING F Y J FLT CONT AFFECTED ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 3109 (CAN) DURING CRUISE AT 25,000 FT, THE NR 1 POWERPLANT AND NR 1 PEC (PROP ELECTRONIC CONTROLLER) CAUTION LIGHTS ILLUMINAT ED. THE NR 1 ENGINE WENT INTO THE AMBER. PILOTS CARRIED OUT AN IN-FLIGHT SHUTDOWN, DECLARED AN EMERGENCY AND RETURNED T O BASE. FAULT CODES 161 AND 157 WERE LOGGED IN THE CDS. PROPELLER ELECTRONIC CONTROL UNIT REPLACED, OVERSPEED GOVERNOR (OSG) FAULTS HAVE BEEN SINCE BEEN CLEARED AND FUNCTIONAL CHECKS HAVE BEEN COMPLETED. (TC NR 20070712001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007082000105 20070820 00105 EU 2007 8 20 CA070712002 1 20070710 G 2910 TC2500065500 LINE BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU HYDRAULIC SYS PERFORATED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER DEPARTING, THE CREW OBSERVED BOTH THE LT AND RT HYDRAULIC PRESSURE LOSS INDICATION LIGHTS WERE ILLUMINATED. THE AIRCRAFT DIVERTED AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE FOUND THE NR 2 HYDRAULIC PRESSURE RETURN LINE TO THE HP FILTER IN THE WHEEL WELL PERFORATED DUE TO CONTACT WITH A BROKEN CLAMP WHICH SUPPORTS THE GENERATOR COOLING BLEED AIR LINE. BOTH ITEMS WERE REPLACED AFTER WHICH THE AIRCRAFT WAS SATISFACTORILY GROUNDED AND RETURNED TO SERVICE. FIRST AIR CONDUCTED A CHECK OF THE REMAINING SAME TYPE AIRCRAFT OPERATED AND FOUND NO SIMILAR CONDITION PRESENT. (TC NR 200707 12002) 2 L 7 2 3T 4 T A24EU A196 6 C P899 20081104 2008 11 4 CA070712003 4 20070712 G 2562 ELT97A256 ELT ACTIVATED W D RETURN TO BLOCK N FALSE WARNING NR NOT REPORTED 1 CA (CAN) ELT ACTIVATED ON FIRST ENGINE START. DIDN`T LEAVE THE GROUND. (TC NR 20070712003) 2007082000106 20070820 00106 EA 2007 8 20 CA070713001 1 20070710 G 3010 14463108 PICCOLO TUBE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE RUPTURED W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CR CRUISE 1 CA (CAN) THE FLIGHT CREW RECEIVED AN ANTI-ICE DUCT WARNING MESSAGE DURING FLIGHT. THE APPLICABLE SYNOPTIC PAGE SHOWED THE R T WING LEADING EDGE BEING AT FAULT. WING ANTI-ICE SWITCH WAS SELECTED FROM NORMAL TO STAND-BY WITHOUT SUCCESS. DURING TR OUBLESHOOTING, MAINTENANCE DISCOVERED THE RT WING OB ANTI-ICE DUCT (PICCOLO TUBE) REF IPC 30-11-00-10-240C END CAP MISSI NG. THE WELDED PICCOLO TUBE END CAP HAS RUPTURED FROM THE ASSY. THE ANTI-ICE DUCT ASSY WAS REPLACED IAW AMM 30-11-41 AND THE AIRCRAFT RELEASED INTO SERVICE. (TC NR 20070713001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022000326 20080220 00326 EU 2008 2 20 CA070713002 1 20070712 G 6510 350A34021006 DRIVE SHAFT SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE TAIL ROTOR OUT OF ROUND W K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 CA 2473 (CAN) UNABLE TO BALANCE SHORT SHAFT, RUNOUT CHECK OF FWD END OF SHAFT WAS .017 INCH. PREVIOUS T-CHECK REVEALED A RUNOUT OF .009 INCH WITH TROUBLES OF SAME NATURE AND SHORT SHAFT WAS INSPECTED AND FOUND TO BE BENT, AND REPLACED WITH BALANCE OBTAINED. (TC NR 20070713002) 1 G 7 1 3U 3 U H9EU E19EU 2007082000107 20070820 00107 EA 2007 8 20 CA070713003 2 20070706 G 7313 252416314 SERVO PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL FUEL INJECTOR LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 1225 L653661A (CAN) FUEL INJECTOR SERVO ON LT ENGINE FOUND TO HAVE AN INTERNAL LEAK AND WOULD NOT SHUTDOWN PROPERLY. SERVO WAS REMOVE D AN OVERHAULED UNIT INSTALLED ENGINE GROUND RUN. (TC NR 20070713003) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007082000108 20070820 00108 GL 2007 8 20 CA070715001 2 20070714 G 7261 FITTING LKHEED 188 188C 5262604 SO ALLSN 501D 501D13 03004 GL ALLSN A6441 A6441FN606 GL OIL SYSTEM LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) THE CREW NOTICED A LOSS OF OIL QUANTITY ON THE NR 3 ENGINE. THIS LOSS WAS FOLLOWED BY A FLUCTUATION IN THE REDUCTI ON GEARBOX PRESSURE. THE ENGINE WAS SHUTDOWN PRIOR TO LANDING. IT WAS DETERMININED THAT A FITTING ON THE TURBINE SECTION WAS LEAKING. THERE WAS 3-4 GALLONS OF OIL REMAINING IN THE RESEVOIR, THE AIRCRAFT WAS FERRIED FOR AN ENGINE CHANGE. (TC NR 20070715001) 2 L 7 4 4T 4 T 4A22 E282 6 C P898 2007082000109 20070820 00109 EA 2007 8 20 CA070716001 1 20070714 G 5343 215340711 MOUNT CNDAIR CL215 CL2151A10 1900320 EA PWA R2800 R2800CA3 52026 NE HAMSTD 43E 43E60 NE LANDING GEAR DAMAGED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, THE LANDING GEAR WAS RETRACTED AND THE RT/MAIN GEAR DID NOT INDICATE UP AND LOCKED. THE GEAR WAS SE LECTED DOWN AND ALL (3) GEAR INDICTED DOWN AND LOCKED. MAINTENANCE HAS FOUND THE RT MAIN GEAR ACTUATOR MOUNTING DAMAGED. PARTS 215-34071-1,215-34071,215-34014-3,215-34014-2 ON ORDER. (TC NR 20070716001) 2 H 7 2 4R 4 R RT A14EA 5E8 6 C P871 2007082000110 20070820 00110 EU 2007 8 20 CA070716002 1 20070713 G 3150 WARNING MESSAGE AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE STAB TRIM ACTIVATED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 51519 37472 (CAN) AFTER DEPARTURE, AN ECAM MSG INDICATED STAB TRIM FAILURE. NEITHER OF THE AUTOPILOTS COULD BE RE-ENGAGED. AN EMER GENCY WAS DECLARED WITH ATC AND THE FLIGHT LANDED APPROX 7.5 TONS OVERWEIGHT. (TC NR 20070716002) 2 L 7 2 4F 4 F RT A28NM E29NE 2007082000112 20070820 00112 NM 2007 8 20 CA070717001 1 20070626 G 2497 WIRE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU EDU DAMAGED W O OTHER H ELECT. POWER LOSS-50 PC AP APPROACH 1 CA (CAN) LATE IN THE AIRCRAFT`S LANDING SEQUENCE, THE FLIGHT DECK ENGINE DISPLAY SUFFERED A FAILURE CAUSING THE DISPLAY TO GO BLANK. THE LANDING WAS COMPLETED WITHOUT INCIDENT. ONCE SHUTDOWN ON THE RAMP, THE CREW IDENTIFIED THAT ONE OF THE ESI D CIRCUIT BREAKERS WAS (POPPED). FOLLOWING ADVICE FROM ENGINEERING, ATTEMPTS TO RESET THE CIRCUIT BREAKER WERE UNSUCCES SFUL. ON SITE ENGINEERING INVESTIGATION IDENTIFIED THAT BOTH POWER WIRES TO THE EDU WERE DAMAGED DUE CHAFING RESULTING I N A SHORT CIRCUIT TO GROUND. DAMAGED WIRES WERE REPAIRED IAW MM PROCEDURES. IT WAS ESTABLISHED THAT THE WIRE CHAFING WAS DUE TO INCORRECT FACTORY INSTALLATION OF THE WIRING LOOM EDU CONNECTOR BACKSHELL WHICH IN TURN ALLOWS THE LOOM WIRES TO 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007082000113 20070820 00113 NE 2007 8 20 CA070717002 2 20070704 G 7321 4120T01P02 FMU CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF34* NE NR 1 ENGINE UNSERVICEABLE W C ABORTED TAKEOFF X J ENGINE FLAMEOUT WARNING INDICATION TO TAKEOFF 1 CA (CAN) STARTING T/O, NR 1 ENGINE DID NOT RESPOND TO THROTTLE IN TOGA POSTION. ENGINE REMAINED AT IDLE. AFTER 10 SECONDS L ENGINE FLAMEOUT CAUTION MSG. T/O ABORTED AT 40 KNOTS. MDC (MAINTENANCE DIAGNOSTICS COMPUTER) INTERROGATED BY MAINTENA NCE. FAULT CODE 353 BIT 29 SET, FMU CMD/POS DISAGREE (WF METERING VALVE ACTUAL POSITION DOES NOT MATCH EXPECTED POSITION BASED ON COMMAND). SUSPECT WF METERING VALVE TORQUE MOTOR. SUSPECT FAULTY COMPONENT: FMU 4120T01P02). FMU P/N4120T01 P02 S/N12391265 REMOVED AND CHANGED IAW AMM 73-21-02-400-801-A01. ENGINE LEAK CHECKED AND FUNCTIONED SATISFIED. AIRCRAF T RETURNED TO SERVICE. (TC NR 20070717002) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022000327 20080220 00327 SW 2008 2 20 CA070717003 1 20070629 G 5210 2050314352 BRACKET BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA PAX DOOR BROKEN W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) ON APPROACH TO THE LANDING AREA, THE (DOOR LOCK) LIGHT ON CAUTION PANEL ILLUMINATED. AIRCRAFT LANDED SAFELY WITHOU T ANY FURTHER INCIDENT. UPON LANDING THE ENGINEER EXITED THE AIRCRAFT AND PHYSICALY CHECKED ALL DOORS AND PANELS TO ENSU RE THAT THEY WERE CORRECTLY SECURED. NO DOORS OR PANELS WERE FOUND OPEN. UPON INVESTIGATION OF THE RT PASSENGER/CARGO D OOR, IT WAS FOUND TO BE LOOSE IN THE DOOR TRACK. FURTHER INVESTIGATION REVEALED THAT THE UPPER FWD ROLLER BRACKET HAD FA ILED. THIS ALLOWING THE MICRO-SWITCH TO BE DEACTIVATED, AND THE LIGHT COMING ON. THE BRACKET WAS REPLACED AND NO FURTH ER PROBLEMS EXISTED. (TC NR 20070717003) 1 G 7 1 4U 4 U H4SW E22EA 2007082000114 20070820 00114 EA 2007 8 20 CA070717004 1 20070628 G 5210 85210240055 ROD DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE PAX DOOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PASSENGER DOOR AFT SUPPORT STRUT BROKE MAKING IT DIFFICULT TO OPEN THE MAIN CABIN DOOR. EXPLANATION CODES: 7(A) S PECIAL OPS- AIRCRAFT HAD ALREADY LANDED AND PASSENGERS WERE ABOUT TO DISEMBARK. 7(B) DOOR WAS DIFFICULT TO OPEN. 7(C) D OOR WAS OPENED BY (2) CREW MEMBERS. (TC NR 20070717004) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007082000115 20070820 00115 NE 2007 8 20 CA070717005 2 20070619 G 7310 021578201 FILTER CESSNA 425 425 2076018 CE PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL FUEL PUMP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN INSPECTION THE INLET FILTER WAS REMOVED. THE FILTER COVER (CAP) WAS FOUND CRACKED UNDER THE O-RING LOCAT ION ALL THE WAY AROUND. IT APPEARS TO HAVE BEEN OVER TORQUED. IT WAS NOT LEAKING AT THIS TIME. THE INLET FILTER ASSEMBLY WAS REPLACED. (TC NR 20070717005) 1 L 7 2 3T 3 T RT A7CE E4EA 5 C P60GL 2008030600046 20080306 00046 2008 3 6 CA070717006 4 20070705 G 3197 WIRE HARNESS UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE BURNED W O OTHER N FALSE WARNING CR CRUISE 1 CA (CAN) DURING CRUISE FLIGHT, PILOT NOTED THE V/A INDICATION ON THE VEMD WAS OSCILLATING INTERMITTENTLY BETWEEN PARAMETERS , AS WELL, THE LOW ROTOR AURAL WARNING WAS INTERMITTENTLY SOUNDING AND AT TIMES WAS ON STEADY. AT NO TIME WERE ANY ANOMO LIES NOTICED IN THE COCKPIT ENGINE INDICATIONS OR ENGINE PERFORMANCE. UPON LANDING, THE PILOT NOTED THE VEMD CIRCUIT BRE AKER ON THE COCKPIT PANEL WAS TRIPPED. AFTER SUBSEQUENT TROUBLESHOOTING, IT WAS FOUND THAT THE WIRE HARNESS LEADING UP T O THE VEMD WAS PINCHED BETWEEN THE TOP AFT LT CORNER OF THE VEMD (VIEWED LOOKING FORWARD WITH VEMD INSTALLED AND GLARESH IELD REMOVED) AND THE GLARESHIELD ITSELF. SEVERAL WIRES WERE FOUND CHAFED THROUGH AND/OR BURNED THROUGH ALTOGETHER. UPON 1 G 7 2 3U 3 U NC R0001RD E34NE 2007082000116 20070820 00116 CE 2007 8 20 CA070717007 1 20070623 G 3230 NAS464P6A16 BOLT CESSNA 177 177RG 2073709 CE MLG SHEARED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 3940 (CAN) MAIN GEAR JAMMED ON RETRACTION FROM TAKEOFF. LANDED WITH MAIN GEAR PARTIALLY EXTENDED. (TC NR 20070717007) 1 H 7 1 3O A20CE 2007082000117 20070820 00117 2007 8 20 CA070717009 4 20070512 G 6113 BRACKET CESSNA 120 120 2071402 CE CONT C85 C8512F 17008 SO MCAULY 1B90 1B90CM GL SPINNER BROKEN W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA (CAN) V-BRACKET OF SPINNER BROKE ON ONE SIDE, THAT CAUSED OFFSET OF SPINNER WHICH CAUSED VIBRATION AND DECIDED TO CONDUC T A PRECAUTIONARY LANDING ON A FARMERS FIELD. NO FURTHER DAMAGE. (TC NR 20070717009) 1 H 7 1 3O 3 O A768 E233 5 N P842 2007082000118 20070820 00118 NM 2007 8 20 CA070717010 1 20070703 G 2797 BACC63BV22F55PN CONNECTOR BOEING 737 737800* NM CFMINT CFM56 CFM567B26US NE TE FLAPS CORRODED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 19956 (CAN) AFTER FLAP 25 TAKEOFF, WHEN FLAP RETRACTION INITIATED, FLAP ASYMMETRY INDICATED AND TE FLAP SKEW SENSOR CB POPPED. AIRCRAFT RETURNED TO JTR. SFCC BITE TEST CARRIED OUT, MSG 27-51407 INTERMITTENT. FIM TASK 27-51-00-810-848 CARRIED OUT WITH NO FINDINGS. VISUAL CHECK OF SLAT/FLAP SYSTEM CARRIED OUT WITH NO FINDINGS. OVERWEIGHT LANDING INSP CARRIED OUT WIT H NO FINDINGS. AC DEPARTED TO DUB. ON APPROACH TO DUB, MACH TRIM LIGHT CAME ON MOMENTARY, FOLLOWED BY NO PITCH COMMANDS ON CAPTAIN`S FD, NO AP A AND MAGENTA IAS INDICATION ON CAPTAIN`S DU. WHEN FLAP SELECTED TO 1, FLAP ASYMMETRY INDICATION OBSERVED AND TE FLAP SKEW SENSOR CB WAS FOUND POPPED. AFTER EXTENSIVE TROUBLESHOOTING A SHORT WAS FOUND IN THE LT TE FLA 2 L 7 2 4F 4 F RT A16WE E00055EN 2007082000119 20070820 00119 CE 2007 8 20 CA070717011 1 20070621 G 3213 21A05000016 ARM CESSNA 172 172N 2072434 CE LYC O360 O360A1F6 41514 EA MCAULY 1A200 1A200FA GL FLOATS BENT W E ENGINE SHUTDOWN O OTHER LD LANDING 1 CA 244 23076 (CAN) ON ROLL OUT AFTER LANDING THE RT MAIN LANDING GEAR COLLAPSED. INVESTIGATION FOUND THAT THE ACTUATING CYLINDER BENT (P/N D68194-A-4). FURTHER INVESTIGATION FOUND THE RETRACT ARM P/N 21A05000-016 HAD WORN ELONGATED BOLT HOLES NOT ALLOWI NG A DOWN LOCK OVER CENTRE POSITION. (TC NR 20070717011) 1 H 7 1 3O 3 O NT 3A12 E286 5 N P874 2007082000120 20070820 00120 NE 2007 8 20 CA070717012 2 20070611 G 8510 288935 THRUST BEARING DHAV DHC3 DHC3 2800202 EA PWA R1340 R134059 52016 NE HAMSTD 23D 23D40 NE PROPELLER BROKEN W O OTHER E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 851 (CAN) WHILE TAXIING FROM DOCK, THE AIRCRAFT ENGINE STARTED SHAKING AND THE PILOT SHUT THE ENGINE DOWN. AIRCRAFT TOWED BA CK TO DOCK. AFTER RE-STARTING, STRANGE NOISES FROM NOSE CASE, AND PROPELLER LOOKED (OUT OF TRACK). PROPELLER REMOVED FR OM COVER ON NOSE CASE REMOVED. BEARING SEPARATOR HAD STARTED TO BREAK UP. (TC NR 20070717012) 1 H 7 1 3R 3 R A815 5E2 6 C P719 2007082000121 20070820 00121 EA 2007 8 20 CA070717014 2 20070711 G 7261 061040M0240180 LINE DHAV DHC6 DHC6100 2802610 EA PWA PT6 PT6* 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE OIL FAILED W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) THE CREW OF FLOATPLANE EXPERIENCED A 10 LB LOSS OF TORQUE IN CRUISE ALONG WITH LOWERED OIL PRESSURE AND AN INCREAS E IN OIL TEMP. THE PILOT CONTINUED THE FLIGHT TO A MAINTENANCE BASE USING REDUCED POWER ON THE AFFECTED ENGINE. AN UNE VENTFUL LANDING AND DOCKING WAS MADE. MAINTENANCE INVESTIGATION REVEALED THAT THE MAJORITY OF THE ENGINE OIL SUPPLY HAD BEEN EJECTED THROUGH THE ENGINE BREATHER SYSTEM. INSPECTION OF THE ENGINE OVERBOARD BREATHER LINE INTERNALLY REVEALED THAT IT HAD BROKEN DOWN AND PARTIALLY PLUGGED THE ACCESSORY CASE VENTING SYSTEM. THIS CAUSED THE ACCESSORY CASE TO PRES SURIZE AND THE ENGINE OIL TO VENT OVERBOARD. THE BREAKDOWN OF THE LINE RESULTED FROM THE LINE BEING POORLY ROUTED DURIN 1 H 7 2 3T 3 T RT A9EA E2NE 6 C P15EA 2007082000122 20070820 00122 NE 2007 8 20 CA070717015 2 20070711 G 7321 806304101A FUEL CONTROL PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ENGINE MALFUNCTIONED W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA 590 63 (CAN) ON TAKEOFF, THE FULL ENGINE POWER (43 PSI) WAS NOT ACHIEVABLE, 35 PSI WAS ALL THE ENGINE WOULD PRODUCE. THE PILOT REPORTED ENGINE WAS NOT CONTROLABLE WITH POWER LEVER WHEN PULLED TO IDLE (ENGINE AT 35 PSI TORQUE). ADVISED NOT TO TRY A ND START THE ENGINE AND TO REPLACE THE FCU. FCU WAS REPLACED AND ALL ENGINE RUNS CHECKED SERVICEABLE. (TC NR 20070717015 ) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007082000123 20070820 00123 2007 8 20 CA070717016 4 20070705 G 2562 C5895120103 ELT CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA CABIN INTERMITTENT W O OTHER N FALSE WARNING LD LANDING 1 CA 91 (CAN) EARLY ACTIVATION. SELF-ACTIVATION REPORTED TWICE. (TC NR 20070717016) 1 H 7 1 3O 3 O NT 3A12 E274 2007082000124 20070820 00124 NM 2007 8 20 CA070717017 1 20070703 G 5753 NAS679A3W NUT BOEING 727 727225 1384077 NM PWA JT8 JT8D15 52051 NE TE FLAPS LOOSE W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH, CREW SELECTED FLAPS FROM 2 TO 5 AND HAD AN AMBER LIGHT INDICATION FOR THE NR 1 KRUGER FLAP INDICATING STILL RETRACTED. FELT MODERATE VIBRATION AND DECLARED AN EMERGENCY. UNEVENTFUL LANDING. MAINTENANCE CYCLED SYSTEM AND COULD NOT FAULT. FURTHER INSPECTION FOUND THE NR 1 KRUGER FLAP SWITCH LINK BOLT/NUT LOOSE. (TC NR 20070717017) 2 L 7 3 4F 4 F A3WE E2EA 2007082000125 20070820 00125 GL 2007 8 20 CA070717019 1 20070717 G 5270 SAL2D864 PLUNGER DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE DOOR SWITCH SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA 1090 (CAN) AT INSPECTION OBSERVED THE FRONT DOOR HANDLE IN OPEN POSITION BUT STILL ABLE TO START ENGINE. UPON INSPECTION, F OUND WITH DOOR OPEN MANUALLY OPERATING PLUNGER ON FORWARD DOOR LOCK OUT SWITCH ON LOWER DOOR SILL, FOUND SWITCH PLUNGER SEIZED IN CLOSED POSITION. THIS CAN ALLOW AIRCRAFT TO BE STARTED WITH FORWARD DOOR NOT LATCHED PROPERLY. RECTIFICATION I S TO REPLACE SEIZED SWITCH PLUNGER AND LUBRICATE SWITCHES ON A REGULAR BASIS. (TC NR 20070717019) 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2007082000126 20070820 00126 NM 2007 8 20 CA070718001 1 20070708 G 7931 310573501A REGULATOR DHAV DHC8 DHC8101 2809002 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ENGINE OIL FLUCTUATES W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA 8278 121242 (CAN) DURING FLIGHT, THE OIL PRESS INDICATOR NR 1 ENGINE, DROPPED TO 50 PSI. QRH DRILL COMPLETED, UNSCHEDULED LANDING CO MPLETED. OIL PRESSURE REGULATOR ASSEMBLY REPLACED IAW AMM 71-01-50, SYSTEM TESTED SERVICEABLE AND AIRCRAFT RETURNED TO S ERVICE. (TC NR 20070718001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007082000127 20070820 00127 CE 2007 8 20 CA070718002 1 20070717 G 3230 2317100016 ACTUATOR LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE NLG FAULTY W O OTHER J WARNING INDICATION LD LANDING 1 CA 4538 4538 (CAN) DURING ARRIVAL, NOSE LANDING GEAR WOULD NOT INDICATE DOWN AND LOCK. ALTERNATE GEAR EXTENSION WAS PERFORMED. AIRC RAFT WAS FERRIED, FUNCTIONAL CHECK OF THE EMERGENCY GEAR EXTENSION WAS CHECKED, NOSE GEAR STAYED IN WHEEL WELL. FREE FA LL PRESSURE TESTED AND FOUND TO BE BETWEEN 85 TO 90 LBS (MAX LIMIT 20 LBS). GEAR DOOR AND GEAR ACTUATOR WAS DISCONNECTE D AND GEAR FREE FALL WAS CHECKED AND FOUND TO BE WITHIN LIMITS. SUSPECT FAULTY INTERNAL GEAR ACTUATOR LOCKING SLEEVE. NOSE GEAR ACTUATOR REPLACED. FUNCTIONAL CHECK CARRIED OUT-SERVICEABLE. (TC NR 20070718002) 2 L 7 2 4F 4 F RT A10CE E35NE 2007082000128 20070820 00128 2007 8 20 CA070718003 4 20070717 G 3418 906100004 COMPUTER DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE STALL WARNING FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 8277 (CAN) DURING CRUISE, THE NR 2 STALL SYSTEM FAIL AND PUSHER SYSTEM FAIL CAUTION LIGHTS ILLUMINATED. QRH CHECKLIST WAS PE RFORMED. UNSCHEDULED LANDING COMPLETED. DUAL STALL WARNING COMPUTER DETERMINED TO BE THE CAUSE OF THE REPORTED DEFECT. DUAL STALL WARNING COMPUTER REPLACED IAW AIRCRAFT MM CHAPTER 27-33-00 AND SYSTEM TESTED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070718003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007082000129 20070820 00129 CE 2007 8 20 CA070718004 1 20070714 G 6120 022A431113 LEVER MTSBSI MU2 MU2B36 5780412 CE GARRTT TPE331 TPE33110 01514 WP HARTZL HCB3T HCB3TN5 GL PROP PITCH LOOSE W E ENGINE SHUTDOWN F FLT CONT AFFECTED DE DESCENT 1 CA 4539 4539 (CAN) THE PPC LEVER WAS FOUND SEPARATED FROM THE PPC INPUT SHAFT. THE BOLT WAS OF THE CORRECT P/N, YET WAS THREAD BOUND WITHOUT PRODUCING ENOUGH TENSION TO HOLD THE PPC ARM ONTO THE PPC SHAFT. THE PPC ARM WAS REINSTALLED AND A WASHER WAS PLACED UNDER THE HEAD OF THE BOLT TO PROVIDE A BETTER GRIP ON THE SPLINED SHAFT. THE PPC INPUT SHAFT HAS A THREADED B ORE WHICH WOULD ALLOW THE USE OF AN ADDITIONAL BOLT AND WASHER AS A BACKUP RETAINER FOR THE PPC ARM IN THE EVENT THAT TH E ARM WERE TO LOOSEN OFF. THE AIRFRAME IPC DOES NOT SHOW A BOLT FOR THIS PURPOSE. (TC NR 20070718004) 1 H 7 2 3T 4 T RT A10SW E4WE 6 C P15EA 2007082000130 20070820 00130 GL 2007 8 20 CA070718005 2 20070715 G 7240 6899081 COMBUSTION LINER BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1008 (CAN) COMBUSTION LINER REMOVED AND INSPECTED DURING UN-RELATED ENGINE MAINTENANCE. FOUND CRACKED AND WARPED BEYOND LIMIT S. (TC NR 20070718005) 1 G 7 1 3U 3 U H2SW E1GL 2007082000131 20070820 00131 CE 2007 8 20 CA070718006 1 20070627 G 5312 05120151 BULKHEAD CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2884 (CAN) DURING THE 200 HOUR INSPECTION, A ONE-INCH CRACK WAS NOTED RUNNING HORIZONTALLY ACROSS THE FLANGE BEND RADIUS AT T HE LOWER LT CORNER OF THE BULKHEAD. A SMALL DENT WAS NOTED AT THIS POINT, PROBABLY EXISTING SINCE MFG, STRESSING THE AL UMINUM AND TIGHTENING THE BEND RADIUS SOMEWHAT. THIS AREA CAN BE FELT TO FLEX SLIGHTLY WHEN THE TAIL IS MANUALLY MOVED SIDEWAYS. (TC NR 20070718006) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2008030600047 20080306 00047 SW 2008 3 6 CA070719001 1 20070716 G 7603 212060722001 MOUNT BELL 412 412EP 1182205 SW THROTTLE INTERFERENCE W K NONE O OTHER IN INSP/MAINT 1 CA 284 (CAN) DURING A SCHEDULED INSPECTION, AN AREA OF INTERFERENCE BETWEEN THE A THROTTLE JACKSHAFT MOUNT ASSY AND THE LT AIR INLET DUCT WAS IDENTIFIED. 1 G 7 2 4U H4SW 20081104 2008 11 4 CA070719007 4 20070718 G 2330 178661101 ELECTRICAL BOX BOEING 777 777* UTILUSE NM SEAT BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) THE VIDEO ENTERTAINMENT SYS ON 3 SEATS WAS NOT WORKING. WHEN THE SEAT ELECTRONICS BOX WAS ACCESSED AND REPLACED DA MAGE WAS NOTED ON THE REMOVED UNIT. SOOT ASSOCIATED WITH WHAT APPEARED TO BE BURNED CIRCUIT CARD IN THE SEU WAS OBSERVED . AN ELECTRICAL BURNING TYPE ODOR WAS PRESENT IN THE AREA. (TC NR 20070719007) 2 L 7 2 4F RT T00001SE 2008030600048 20080306 00048 SW 2008 3 6 CA070719008 1 20070719 G 6320 206040581001 TUBE BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL XMSN OIL CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) OIL LINE CRACKED IN BEND JUST FWD TO FLARED FITTING. SUSPECT FATIGUE FROM IMPROPER TIGHTENING AT SOME POINT THROUG HOUT THE LIFE OF THE LINE. SUSPECT THIS TUBE WAS ORIGINAL EQUIPMENT. UNABLE TO DETECT LEAK ON GROUNG RUN LEAK CHECK AS T HE MAINROTOR TRANSMISSION WOULDN`T BE WARM ENOUGH TO BE SENDING OIL TO THE OIL COOLER. (TC NR 20070719008) 1 G 7 1 3U 3 U H2SW E1GL 2007082000132 20070820 00132 NM 2007 8 20 CA070719009 1 20070628 G 2750 745583A FLEX DRIVE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE TE FLAPS SEIZED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) FLIGHT CREW REPORTED (FLAP DRIVE) CAUTION LIGHT ILLUMINATED FROM 2-3 SECONDS WHEN FLAPS SELECTED. MAINTENANCE INSP ECTION FOUND FLAP SECONDARY DRIVE, IN WING CENTER SECTION, CORE HAD UNWOUND AND SEIZED CAUSING THE CASING TO ROTATE AND DAMAGED SUPPORT BRACKET AND TORQUE SENSOR. FLAP CORE APPEARED TO LACK LUBRICATION AND RUST WAS EVIDENT. FLAP SECONDARY FLEX SHAFT REPLACED. ALL OTHER FLAP SECONDARY DRIVES LUBRICATED. BRACKET AND TORQUE SENSOR DAMAGE REPAIRED. AIRCRAFT RE TURNED TO SERVICE. FLAP SECONDARY DRIVE IS CLASSIFIED AS AN EXPENDABLE PART AND TIME ON PART NOT TRACKED. (TC NR 2007071 9009) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007082000133 20070820 00133 NM 2007 8 20 CA070720003 1 20070717 G 2910 AE7128852 HOSE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NLG ACTUATOR RUPTURED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING SELECTING GEAR UP, THE CAUTION WARNING AND NOSE GEAR INDICATED NOT UP, MAIN GEAR UP. SUBSEQUENTLY NOTED (N R 2 HYDRAULIC SYSTEM ZERO QUANTITY. FLUID LOSS DUE TO DAMAGED HYDRAULIC PIPE IN NLG WELL. REPAIRS COMPLETED, AC RTS. (T C NR 20070720003) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007082000134 20070820 00134 CE 2007 8 20 CA070720004 1 20070718 G 2730 EM21542 CURRENT LIMITER LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP ELEVATOR FAILED W K NONE N FALSE WARNING IN INSP/MAINT 1 CA 2312 (CAN) WHEN COMPLETING POST FLIGHT INSPECTION (DI), AN AMBER CAS MESSAGE, ELEVATOR DISCONNECT WAS NOTICED ON THE EICAS DI SPLAY. ELEVATOR DISCONNECT WAS NOT ACTUATED AT THIS TIME (THIS INDICATES THE ELEVATORS ARE DISCONNECTED ON THE GROUND). ELEVATOR DISCONNECT FUNCTION CHECKED AND IT WAS DISCOVERED THAT THE ELEVATORS WOULD NOT DISCONNECT. SYSTEM TROUBLESHO T AND FOUND THAT CURRENT LIMITER HAD FAILED. A NEW LIMITER WAS ORDERED AND INSTALLED. ELEVATOR DISCONNECT SYSTEM FUNCT ION CHECKED SERVICEABLE. MFG NOTIFIED OF FAILURE. (TC NR 20070720004) 2 L 7 2 4F 4 F RT T00008WI E6WE 2007082000135 20070820 00135 SW 2007 8 20 CA070720005 1 20070719 G 2742 ACTUATOR SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE PITCH TRIM MALFUNCTIONED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA 898 (CAN) AFTER FLAP RETRACTION, FLIGHT CREW DISCOVERED THAT THEY HAD NO CONTROL OF PITCH TRIM USING PRIMARY OR SECONDARY CI RCUITS. AFTER DISCUSSION WITH MAINTENANCE, FLIGHT CONTINUED TO MAINTENANCE BASE WHERE MAINTENANCE REPLACED TRIM ACTUATOR . (TC NR 20070720005) 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 2007082000136 20070820 00136 EU 2007 8 20 CA070720006 1 20070707 G 3240 03024400 BRAKE ASSY PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL MLG FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 825 (CAN) WHILE AIRCRAFT WAS BEING PUSHED BACK USING A TOWING DEVICE PART OF THE BRAKE ROTORS CAME LOOSE ON THE RT MLG AND P UNCTURED THE RIM ASSEMBLY. CAUSED THE TIRE TO GO FLAT. BRAKE DISC AND WHEEL. REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. WAS INFORMED BY THE LOCAL DEALER THAT THE ROTORS USED IN THIS BRAKE DISC WERE SUPPOSED TO BE NEW AND IMPROVED JUST FOR THIS SITUATION. (TC NR 20070720006) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008030600049 20080306 00049 SW 2008 3 6 CA070720007 1 20070710 G 6230 212040136001 BEARING BELL BELL 205 205A1 1181414 SW LYC T53 T5317BLYC 41616 NE MAST SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 2210 A1212568 (CAN) THIS PN BEARING IS A (ON CONDITION) PART. THE MAST WAS LAST OVERHAULED 2210.4 HOURS AGO. THE ENGINEER FOUND FERROU S METAL IN THE TRANSMISSION INTERNAL AND EXTERNAL FILTERS. A POWDER OR PASTE WAS FOUND ON THE TRANSMISSION CHIP DETECTOR , NOT ENOUGH TO ACTIVATE A CHIP LIGHT. (TC NR 20070720007) 1 G 7 1 4U 4 U H1SW E17EA 2007082000137 20070820 00137 GL 2007 8 20 CA070720008 2 20070718 G 7230 COMPRESSOR LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL HAMSTD 54H 54H60117 NE ENGINE ERODED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 6233 550195 (CAN) DEPARTING DESTINATION, THE CREW NOTED A COMPRESSOR STALL CONDITION ASSOCIATED WITH HIGH TGT ON NR 1 ENGINE. THE CR EW CARRIED OUT A PRECAUTIONARY SHUTDOWN, RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANC E FOUND SIGNIFICANT EROSION IN THE COMPRESSOR 5TH AND 10TH STAGE BY VISUAL INSPECTION AND ELECTED TO REPLACE THE ENGINE. (TC NR 20070720008) 2 H 7 4 4T 4 T A1SO E282 6 C P906 2007082000139 20070820 00139 EU 2007 8 20 CA070720010 1 20070718 G 2150 15310000 A/C PACK BAG JETSTM JETSTM3212 1500217 EU RIGHT SEIZED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 328 (CAN) PILOT REPORTED OVER TEMP LIGHT, AND CONTINUED FLIGHT IAW J-31 MEL. UPON TROUBLESHOOTING IT WAS FOUND THAT THE RT CAU WAS SEIZED. CAU WAS REPLACED WITH OVERHAULED UNIT AND AIRCRAFT RETURNED TO SERVICE. THIS UNIT HAS A 6000 HOUR LIFE BETWEEN OVERHAULS, AND FAILED AFTER 327.5 HOURS IN SERVICE. SEIZED UNIT WILL BE SENT FOR WARANTY OVERHAUL. (TC# 2007072 0010) 2 L 7 2 4T RT BA15CAA 2008030600050 20080306 00050 SW 2008 3 6 CA070720011 1 20070710 G 6220 206011260103 BOLT BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1141 1141 (CAN) MAIN ROTOR PARTS SENT TO NDT FOR INSPECTION AND ON MAGNAFLUX INSPECTIION FOUND STRAP BOLT CRACKED ON SHANK ABOUT O NE QUARTER WAY AROUND. PART SENT TO BELL HELICOPTER LAB FOR FURTHER INVESTIGATION. BOLT WAS PURCHASED NEW ON MARCH 14,20 05 (TC NR 20070720011) 1 G 7 1 3U 3 U H2SW E4CE 2007082000140 20070820 00140 EA 2007 8 20 CA070721001 1 20070718 G 3297 WIRE HARNESS CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE MLG FAILED W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) THE A/C ARRIVED AND WAS TAXIING TO THE GATE WHEN IT WAS NOTED THAT NR 3 BTMS WAS ON THE RISE AND SUSPECTED DRAGGIN G BRAKES. THE FLIGHT CREW NOTICED THAT THE BRAKE TEMP MONITOR DROPPED TO ZERO. THE CAPTAIN GOT OUT OF THE A/C TO CHECK THE RT GEAR WHEN HE SAW THAT IT WAS ON FIRE, AT THIS TIME THE RAMP CREW EXTINGUISHED THE FIRE WITH A FIRE EXTINGUISHER. MAINTENANCE ON THE SCENE REPLACED NR3 MAIN WHEEL AND FOUND THAT THE DISCONNECT ON NR3 BRAKE LINE WAS LOOSE AND ONLY TO OK TWO TURNS TO REMOVE. IT IS SUSPECTED THAT THE QUICK DISCONNECT CONNECTOR MAY HAVE BACKED OFF CAUSING THE DRAGGING BRA KE CONDITION LEADING TO OVERHEAT AND FLUID LOSS CAUSING THE FIRE. NR 3 AND NR 4 BRAKES WERE REPLACED THE NIGHT BEFORE F 2 L 7 2 4F 4 F RT A21EA E15NE 2008032000003 20080320 00003 CE 2008 3 20 CA070723001 1 20070719 G 3250 50820035 ROD BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA MCAULY 4HFR34 4HFR34C762 NE NLG STEERING CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA 20586 (CAN) DURING THE REPLACEMENT OF RODEND P/N F4-19 ON THE NOSE LANDING GEAR STEERING BARREL ASSY. P/N 50820042-601 WAS DIS ASSEMBLED TO FACILITATE THE REMOVAL OF THE RODEND FROM THE ROD ASSY P/N 50-820035 (ITEM 21). AFTER DISASSY IT WAS NOTICE D THAT THE ROD ASSY WAS HEAVILY CORRODED. THE CORROSION SEEMED TO START FROM INSIDE THE ROD ASSEMBLY AND WORKED ITS WAY OUT, CAUSING THE HARD CHROME TO FLAKE OFF IN 4 SPOTS ALL NEAR THE CARTER OF THE HOLLOW TUBE REVEALING A HOLES IN THE PAR ENT METAL COMPLETELY THROUGH THE WALL OF THE TUBE. THE ROD ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THERE IS NO CURRENT REQUIREMENT TO DISASSEMBLE THIS PART FOR INSPECTION AND THE CORRODED AREA IS NOT VISIBLE WITH THE PA 1 L 7 2 3T 4 T A14CE E4EA 6 C 3PNE 2007091700075 20070917 00075 SW 2007 9 17 CA070724001 1 20070718 G 3233 O-RING GULSTM 690TP 690 0141720 SW GARRTT TPE331 TPE3315251K NM HARTZL HCB3T HCB3TN5 GL GEAR ACTUATOR LEAKING W K NONE J WARNING INDICATION CR CRUISE 1 CA (CAN) INCIDENT/HAZARD DESCRIPTION: UNSAFE GEAR WARNING LIGHT ILLUMINATED. HYDRAULIC PRESSURE WAS DOWN TO 500 PSI. ONCE ON GROUND, FOUND HYDRAULIC FLUID HAD LEAKED OUT IN THE RT WHEEL WELL, DETERMINED THE RT GEAR ACTUATOR FOR BRINGING GEAR UP HAD A O-RING FAIL (SPLIT) AIRCRAFT SLOWED TO BELOW 200KTS, GEAR SELECTED DOWN AND (3) GEAR CONFIRMED AND GEAR VISUAL LY DOWN AND LOCKED. ONCE GEAR WAS DOWN HYDRAULIC PRESSURE WAS BACK UP TO 1000 PSI, AND LANDING MADE . BRAKES WORKED FINE , AIRCRAFT REPAIRED FOR ALERTS ON THE 19TH OF JULY. TEST FLIGHT COMPLETED (TC NR 20070724001) 1 H 7 2 3T 4 T 2A4 E2WE 6 C P15EA 2007082000141 20070820 00141 EA 2007 8 20 CA070724002 1 20070711 G 2731 C3CF3487 CABLE DHAV DHC3 DHC3 2800202 EA GARRTT TPE331 TPE33110R 0517 WP HARTZL HCB4T HCB4TN5 GL ELEV TRIM FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100/150 HOURS INSPECTION, THE ELEVATOR, LOWER TRIM CABLE (P/N: C3CF348-7) WAS FOUND FRAYED IN (2) LOCATIO NS. THE FIRST LOCATION WAS IN THE PEDESTAL AREA WHERE THE TRIM CABLE ATTACHES TO THE ELEVATOR TRIM DRUM ASSEMBLY (P/N: C 3CF222-3). IT APPEARS THAT THE CABLE WAS WEARING ON THE FWD AND REAR GUARDS P/N: C3CF310-3 AND C3CF309-3. THE SECOND ARE A FOUND FRAYING WAS LOCATED IN THE UPPER CABIN AREA WHERE THE TRIM CABLE PASSES THROUGH FAIRLEAD BETWEEN FS 171.8 TO FS 194.8. CABLE REPLACED, AIRCRAFT RETURNED TO SERVICE. (TC NR 20070724002) 1 H 7 1 3R 4 T A815 E4WE 6 C P40EA 20081104 2008 11 4 CA070724003 4 20070724 G 2562 AK450 ELT CESSNA 180 180K 2072624 CE CONT O470 O470U 17026 SO MCAULY 2A34C C2A34C204 GL CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BATTERY CONNECTIONS HAD EXCESSIVE CORROSION AND EVEN THOUGH THE INDICATOR LAMP INDICATED THAT UNIT WAS WORKING THE UNIT HAD NO SWEEP OUTPUT (TC NR 20070724003) 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2007082000142 20070820 00142 EA 2007 8 20 CA070724004 1 20070721 G 2797 CF61A22WHT WIRE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE TE FLAPS DAMAGED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) IN CRUISE GEAR/FLAPS/BTMS INDICATIONS APPEARED WITH FLAP INDICATION SHOWING BOTH SIDES. FLAPLESS LANDING WAS SAFEL Y PERFORMED. MAINTENANCE FOUND WIRE CF61A22WHT AT CONNECTOR P2CF OF RT FLAP POSITION TRANSDUCER WITH DAMAGED INSULATION AND TOUCHING THE SHIELD OF THE HARNESS. WIRE REPAIRED (REO601R-20-12-001 AND REO601R-20-12-048); CONNECTOR P2CF (P/N D38 999-26WB355N) AND HARNESS (P/N HET-A-02B) REPLACED. (TC NR 20070724004) 2 L 7 2 4F 4 F RT A21EA E15NE 2007082000143 20070820 00143 NE 2007 8 20 CA070724005 2 20070723 G 7323 204060765007 CONTROL LEVER BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE ENGINE BROKEN W A UNSCHED LANDING R F J PARTIAL RPM/PWR LOSS FLT CONT AFFECTED WARNING INDICATION DE DESCENT 1 CA (CAN) THIS IS THE INITIAL REPORT. INFORMATION NOT HERE YET. THE PILOT COULD ONLY GET 92 PERCENT NR RP, LANDED THE AIRCRA FT NO INCIDENT, AFTER SHUTDOWN THE ENGINEER OPENED THE GOVERNOR SIDE ENGINE COWLING AND FOUND THE THE GOVERNOR LEVER BRO KEN BOTH ENDS OF THE LEVER OR ARM WERE SECURE AND SAFETY. WE ARE STILL INVESTIGATING. (TC NR 20070724005) 1 G 7 1 4U 4 U H1SW E17EA 2007082000144 20070820 00144 GL 2007 8 20 CA070724006 2 20070723 G 7200 ENGINE BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL OVERHEATED W E ENGINE SHUTDOWN M OVER TEMP TX TAXI/GRND HDL 1 CA 821948 (CAN) THE PILOT HAD JUST TAKEN HIS FINGER OFF THE THE STARTER ON STARTUP AND WAS REVIEWING HIS COMPANY PILOT MINI LOG WH EN HE NOTED A DIFFERENT ENGINE SOUND AS THOUGH IT HAD INCREASED. WHILE CHECKING THE THROTTLE AND SCANNING THE GAUGES THE PILOT NOTICED THAT THE TOT WAS AT 1000 DEGREES. THE ENGINE ASSEMBLY WAS REPLACED. (TC NR 20070724006) 1 G 7 1 3U 3 U H2SW E4CE 2007121300197 20071213 00197 SW 2007 12 13 CA070724007 1 20070721 G 7931 ENGINE KAMOV KA32 KA32A1 SW KLIMOV TB3117 TB3117BMA EU MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 638 346 (CAN) THE LT ENG OIL PRESSURE CAUTION LIGHT WAS FLICKERING WHILE SLINGING A LOAD. THE OIL PRESSURE GAUGE WAS CROSSCHECKE D AND INDICATED 2.5 KG/CM2 (THE CAUTION RANGE) AND THE OIL TEMPERATURE WAS NORMAL. THE LOAD WAS DROPPED OFF. AFTER THE L OAD WAS DELIVERED AIRCRAFT BACK IN LEVEL FLIGHT, THE CREW REVIEWED THE CHECKLIST AND FLIGHT MANUAL. AS A PRECAUTIONARY M EASURE THE ENGINE WAS BROUGHT BACK TO IDLE. AT IDLE THE LT ENGINE WAS STILL BEING MONITORED, A FEW MILES FROM SERVICE TH E FLIGHT CREW ADVANCED THE THROTTLE TOWARDS AUTO TO CHECK THE OIL PRESSURE. THE LT OIL PRESSURE LIGHT ILLUMINATED STEADI LY AND THE OIL PRESSURE REMAINED AT IDLE OIL PRESSURE (2 KG/CM2 MINIMUM ALLOWABLE AT IDLE) THE AIRCRAFT WAS AT A WEIGHT 1 G 7 2 4U 4 U NC EXPE4U 2007082000145 20070820 00145 WP 2007 8 20 CA070724008 1 20070724 G 7410 AH720 RELAY CVAC 340 34030 2422702 WP ALLSN 501D 501D13D 03004 GL HAMSTD 54H 54H60 NE IGNITION POWER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NR 1 ENGINE FAILED TO START DUE TO NO IGNITION. FOUND IGNITION RELAY P/N AH720 S/N CN-90127 FOUND CONNECTOR SEPAR ATED FROM BODY OF RELAY. RELAY REPLACED AND ENGINE GROUND RUN SERVICEABLE. (TC NR 20070724008) 2 L 7 2 4R 4 T 6A6 E282 6 C P906 2007091200057 20070912 00057 CE 2007 9 12 CA070725001 1 20070712 G 2752 995240257 ACTUATOR BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL TE FLAP NOISY W D RETURN TO BLOCK F FLT CONT AFFECTED LD LANDING 1 CA 2963 (CAN) UPON LANDING AN ATTEMPT TO RETRACT THE FLAPS FROM APPROACH TO ZERO RESULTED IN THE MOVEMENT OF THE RT IB FLAP ONLY . THE REMAINING (3) FLAPS DID NOT MOVE. A FLIGHT PERMIT WAS GRANTED AND THE A/C WAS FLOWN WITH THE FLAPS LOCKED IN THE Z ERO POSITION. THE GEARBOX OPERATION WAS NOISY AND WAS REPLACED. THE SYSTEM WAS RIGGED AND OPERATIONALLY CHECKED IAW MFG INSTRUCTIONS. NO OTHER PROBLEMS WERE NOTED. (TC NR 20070725001) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007082000146 20070820 00146 NM 2007 8 20 CA070725002 1 20070322 G 3810 6BS10011 DRAIN VALVE AMD FALC50 FALCON2000 2730170 NM CFE CFE73811B NE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 3626 3626 (CAN) THE AIRCRAFT POTABLE WATER SYSTEM WAS DAMAGED DUE TO HAVING THE WATER SYSTEM FULL OF WATER. THEN PARKING THE AIRCR AFT ON THE RAMP FOR 8 HRS AT -14 DEGREES C. WITH NO ADDITIONAL HEAT TO KEEP THE WATER SYSTEM FROM FREEZING. UPON ARRIVI NG, THE PILOTS REPORTED (WATER APPEARS TO LEAKING FROM THE BELLY) THE MAINTENANCE PERSONAL INVESTIGATED THE PROBLEM AND FOUND THE WATER SYSTEM DRAIN VALVE WAS DAMAGED DUE TO THE SEVERE FREEZING OF THE WATER SYSTEM. THE DRAIN VALVE WAS REPLA CED AND THE AIRCRAFT RETURNED TO SERVICE. A REMINDER TO ALL PILOTS TO MONITOR THE POTABLE WATER SYSTEM AND THE OAT IN T HE WINTER. (TC NR 20070725002) 2 K 7 2 4F 4 F RT A50NM E44NE 2008030600051 20080306 00051 CE 2008 3 6 CA070725003 1 20070717 G 2750 3X5K8563A44172 FLEX DRIVE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL TE FLAP CONTROL DAMAGED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) AN ATTEMPT TO LOWER THE FLAPS TO APPROACH SETTING FROM ZERO DEGREES RESULTED IN THE RT IB FLAP NOT MOVING AND THE (3) OTHERS MOVING TO FULL DOWN. THE PILOT LANDED WITHOUT INCIDENT AND A FERRY PERMIT WAS GRANTED FOR A FLIGHT WITH THE F LAPS UP AND LOCKED. UPON DISASSEMBLY OF THE SYSTEM IT WAS FOUND THAT THE RT FLAP FLEX DRIVE WAS DAMAGED AND BINDING UP O PERATION OF THE ACTUATOR. (TC NR 20070725003) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007082000147 20070820 00147 NM 2007 8 20 CA070725004 1 20070504 G 3010 29S7D524007 BOOT DORNER DO32 DO328100 2996000 NM PWA 119 PW119C NE HARTZL HDE6C HDE6C3B NE HORIZONTAL STAB LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 55 (CAN) PILOTS REPORTED LT HORIZONTAL STAB. DE-ICER BOOT APPEARS LOOSE. MAINTENANCE INSPECTED THE DE-ICER BOOT AND FOUND THE BOOT HAD COME LOOSE FROM THE AIRCRAFT AT THE AFT EDGES. THE ADHESIVE (3M 1300L) DID NOT SECURE THE DE-ICER BOOT TO T HE STAB. THE BOOT WAS RECENTLY REPLACED BY AC SERVICES, UNDER WO 15249. TIME ON PART WAS 54.6 HOURS AND 73 LANDINGS THE DE-ICER BOOT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC 20070725004) 2 H 7 2 4T 4 T RT A45NM E20NE 6 C P34NE 2008031900149 20080319 00149 EA 2008 3 19 CA070725005 2 20070711 G 7230 3027301 BLADE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL COMPRESSOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE COMPRESSOR TURBINE BLADE (STRETCH) INSP, ONE CT BLADE WAS FOUND CRACKED DURING THE NDT PROCESS. T HE CRACK WAS ACROSS THE BLADE FACE AND BACK. THIS TYPE OF CRACK SCRAPS THE BLADE AND THE SET IT WAS INSTALLED WITH. THIS SET OF BLADES HAD A TSN OF 9299.1 HOURS. THE BLADES WERE REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20070725005) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007082000148 20070820 00148 EA 2007 8 20 CA070725006 2 20070725 G 8520 0360A3A CRANKCASE LYC O360 O360A3A 41514 EA ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 1800 (CAN) OVERHAULED CYLINDER ASSY`S WERE INSTALLED APPROX 500 HRS AGO ONTO A FRETTED CRANKCASE. THE CENTER MAIN BEARING TH EN SPUN IN THE BEARING SADDLE. METAL WAS DETECTED IN THE OIL SCREEN AND THE ENGINE WAS SUBSEQUENTLY TORN DOWN FOR OVERH AUL. THE CRANKCASE IS UNSERVICEABLE. (TC NR 20070725006) 3 O E286 2007110200003 20071102 00003 GL 2007 11 2 CA070726003 2 20070709 G 7321 2542102 SLEEVE HONEYWELL BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL FUEL CONTROL CRACKED W O OTHER B K SMOKE/FUMES/ODORS/SPARKS FLUID LOSS TX TAXI/GRND HDL 1 CA 30 333104 (CAN) PILOT STARTING A/C, THROTTLE OPENED, NO ENGINE LIGHT OFF OCCURED. OPENED ENGINE COWL TO INVESTIGATE, NOTICED FUEL DRIPPING FROM AROUND START DE-RICHMENT ADJUSTMENT OF FCU, ONTO THE STARTER GENERATOR. CONTACTED MAINTENANCE PERSONNEL TO INVESTIGATE. FUEL CONTROL UNIT WAS REMOVED, AND O/H`D UNIT INSTALLED - NO FURTHER DEFECT NOTED ON START-UP. OVERHAUL SH OP WORK ORDER DETAILS REVEALED A CRACKED SLEEVE ASSY P/N 2542102, AND CRACKED SCREWS P/N 334S606 (TC NR 20070726003) 1 G 7 1 3U 3 U H2SW E4CE 2007082000149 20070820 00149 NE 2007 8 20 CA070726004 2 20070726 G 7230 4017T37P02 SEAL GE CT58 CT581402 30011 NE COMPRESSOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 280122KL (CAN) MULTIPLE CRACKS THROUGH KNIFE EDGE SEALS. THIS REPORT WILL ALSO BE SUBMITTED TO MFG IAW SEI-183 SECTION 72-32-7 PA GE 302. (TC NR 20070726004) 4 U 1E3 2007082000150 20070820 00150 NE 2007 8 20 CA070727001 2 20070727 G 7310 AN81510 FITTING DHAV DHC8 DHC8202 2809007 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE FUEL MANIFOLD BROKEN W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ENGINE DRIVEN PUMP NR 1, INLET PRESSURE MANIFOLD FITTING AN 815-10 BROKEN IN FLIGHT. FITTING HAS BEEN REPLACED AN D A/C RETURNED TO SERVICE. (TC NR 20070727001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007082000151 20070820 00151 SO 2007 8 20 CA070727002 2 20070725 G 8530 65354A10 CYLINDER HEAD CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CYLINDER ASSY FOUND CRACKED DURING INSPECTION. LEAK COULD BE HEARD FROM CRACK DURING DIFF COMPRESSION TEST. CYLIND ER REMOVED AND LARGE CRACK OBSERVED IN HEAD CASTING (INTERIOR VIEW). THE S/N OF CYLINDER REMOVED IS E41375-4 (TC NR 2007 0727002) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2008030600132 20080306 00132 SW 2008 3 6 CA070727003 1 20070725 G 2911 MS28775212 O-RING BELL BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE ACCUMULATOR FAILED W B EMER. DESCENT F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) LOST OF HYDRAULIC IN FLIGHT, EMERGENCY LANDING, FAULT FOUND IN THE ACCUMULATOR, O-RING P/N MS28775-212 REPLACED A/ C GROUND RUN AND LEAK CHECK COMPLETED AND RELEASED TO SERVICE. (TC NR 20070727003) 1 G 7 1 4U 4 U H1SW E17EA 2007082000152 20070820 00152 NM 2007 8 20 CA070727004 1 20070725 G 7920 FITTING BOEING 727 727243 138408D NM PWA JT8 JT8D9A 52048 NE GEARBOX OIL DAMAGED W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION DE DESCENT 1 CA (CAN) TOP OF DESCENT, THE NR 1 LOW OIL PRESSURE LIGHT ILLUMINATED, QTY AT ZERO. PRECAUTIONARY ENGINE SHUTDOWN CARRIED O UT. GEARBOX FITTING (OIL PRESSURE DIFFERENTIAL SWITCH) THREAD REPAIRED AND FITTING REPLACED. ENGINE INSPECTEED IAW MM AND RETURNED TO SERVICE. (TC NR 20070727004) 2 L 7 3 4F 4 F RT A3WE E2EA 2007082000153 20070820 00153 NE 2007 8 20 CA070727005 2 20070726 G 8550 SEAL DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE IMPELLER FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA 255 (CAN) ENGINE REMOVED DUE TO EXCESSIVE OIL CONSUMPTION. UPON REMOVING NR 7 CYLINDER INTAKE TUBE, OIL WAS NOTED. THIS IND ICATES POSSIBLE IMPELLER SEAL FAILURE. ENGINE WAS REMOVED FROM SERVICE. (TC NR 20070727005) 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2007082000154 20070820 00154 CE 2007 8 20 CA070727006 1 20070723 G 7120 WEB CESSNA 172 172K 2072430 CE LYC O320 O320E2D 41508 EA MCAULY 1A175 1A175ATM GL ENGINE MOUNT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 536 (CAN) CRACK FOUND AT LOWER WELD WEB LT SIDE. (TC NR 20070727006) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P857 2007082000155 20070820 00155 SW 2007 8 20 CA070727008 1 20070717 G 3243 VI151000 MASTER CYLINDER SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE BRAKES FAULTED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 7753 (CAN) AIRCRAFT ABORTED TAKEOFF DUE TO A DRAGGING BRAKE. UPON MAINTENANCE INSPECTION THE RT BRAKE MASTER CYLINDERS WERE F OUND AT FAULT. BRAKE PRESSURE COULD NOT BE RELEASED BY THE AFFECTED MASTER CYLINDERS. BOTH NR 2 AND NR 4 BRAKE MASTER CYLINDERS WERE REPLACED. NR 2 CYLINDER P/N V-1000 S/N 3187 TSO - 4382.9, NR 4 CYLINDER P/N VI-15-1000 S/N 13008 TSO- 7753.3. (TC NR 20070727008) 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 2007082000156 20070820 00156 WP 2007 8 20 CA070727009 1 20070723 G 3234 340315061627 LEVER CVAC 440 440 2422902 WP ALLSN 501D 501D22 03005 GL HAMSTD 54H 54H60 NE LANDING GEAR DISTORTED W O OTHER O OTHER DE DESCENT 1 CA 10869 10869 (CAN) UPON SELECTION OF (GEAR DOWN), THE LOCKING ARM OF THE LANDING GEAR SELECTOR HANDLE STUCK IN THE EXTENDED POSITION, PREVENTING ASSOCIATED FUNCTION OF DEPRESSING THE GEAR WARNING LIGHT SWITCH. THE RESULT WAS NO GEAR DOWN INDICATING LIG HTS ON THE ANNUNCIATOR PANEL. EMERGENCY PROCEDURES FOLLOWED AND AC LANDED WITHOUT INCIDENT. MAINTENANCE FOUND LANDING GEAR ACTUATING LEVER LOCKPIN JAMMED AND CONTROL HANDLE BEYOND THE 90 DEGREE POSITION. LEVER DISASSEMBLED, DAMAGE FOUND W AS A DISTORTED (CUPPED) INTERNAL ALUMINUM 960D10L WASHER. CUPPED WASHER REMOVED. NEW WASHER AND ONE EXTRA WASHER INSTALL ED FOR SUPPORT DURING RE-RIG OF HANDLE WITHOUT COMPROMISING TRAVELS PER CONVAIR MAINTENANCE MANUAL LANDING GEAR MECHANIC 2 L 7 2 4R 4 T 6A6 E282 6 C P906 2007091200058 20070912 00058 GL 2007 9 12 CA070729001 1 20070717 G 3220 203220080 FORK DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA NOSE GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3109 (CAN) DURING ROUTING INSPECTION, A CRACK SIMILAR TO THE ONE IN THE ATTACHMENT WAS FOUND. FORK WAS REPLACED. FLEET INSP ECTION REVEALED (3) OTHER AIRCRAFT WITH VARYING CRACK PROGRESSION ALL FORKS WERE REPLACED. (TC NR 20070729001) 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2007082000157 20070820 00157 NE 2007 8 20 CA070729002 2 20070712 G 8520 39892 COUNTERWEIGHT BEECH 18 D18S 1151004 CE PWA R985 R985AN14B 52008 NE HAMSTD 22D 22D30 NE ENGINE SEPARATED W A UNSCHED LANDING E Y VIBRATION/BUFFET ENGINE STOPPAGE CR CRUISE 1 CA 251 42121964 (CAN) AIRCRAFT WAS IN CRUISE, ALL SYSTEMS NORMAL WHEN A VIOLENT VIBRATION HAPPENED IN THE LT ENGINE. ENGINE SEIZED DURI NG SHUTDOWN/FEATHER PROCESS AND FEATHERING WAS UNAVAILABLE. A SAFE LANDING WAS MADE ON A LAKE. INVESTIGATION REVEALED NR 1 CYLINDER COMPLETELY REMOVED FROM THE ENGINE AND NR 9 PARTIALLY REMOVED. FORWARD COUNTERWEIGHT HAD SEPARATED COMPLETE LY FROM ITS ARM AND WAS FOUND LODGED IN THE TOP PART OF THE ENGINE AFTER BLOWING OUT A SECTION OF THE NOSE SIDE OF THE C RANKCASE COVER. AN ENGINE CHANGE WAS CONDUCTED ON SITE AND AIRCRAFT RETURNED TO RED LAKE WITH A LOANER PROP INSTALLED. (TC NR 20070729002) 1 L 7 2 3R 3 R A765 5E1 5 C P736 2007082000158 20070820 00158 EA 2007 8 20 CA070729003 1 20070728 G 5210 601R319119 STRUT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE PAX DOOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON ARRIVAL IT WAS DISCOVERED THAT THE PAX AIRSTAIR HAD BEEN DAMAGED WHEN CLOSED. MAINTENANCE FOUND A SMALL PUNCTU RE IN THE MAIN CABIN DOOR INNER SKIN BESIDE UPPER STEP. MAINTENANCE DISCOVERED THE GAS STRUT ON THE MCD FAILED CAUSING THE SKIN PUCTURE BY CABLE ATTACHMENT ON THE DOOR BRACKET NOT RETRACTING. NDT C/O NO CRACKS FOUND, STRUT AND COUNTER BAL ANCE REPLACED AND REO 601R-52-11-1295 C/O WITH A RE-INSPECT OF THE SPEED TAPE EVERY 50 HRS. PRESENT A/C HOURS 25062:54 AND CYCLES 20668. (TC NR 20070729003) 2 L 7 2 4F 4 F RT A21EA E15NE 20081104 2008 11 4 CA070730001 4 20070730 G 2562 G SWITCH ELT MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) DURING ANNUAL INSP IT WAS FOUND THAT THE G-SWITCH OPERATION WAS OVERSENSITIVE. UNIT REJECTED AND RETURNED TO MFG F OR REPAIR (TC NR 20070730001) 2007082000159 20070820 00159 EU 2007 8 20 CA070730002 1 20070723 G 3240 30244 BRAKE DISC PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL MLG BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 1848 (CAN) AT THE TIME OF TAKEOFF THE WHEEL OF BLOCKED LT A AND A CAUSED THE EXIT OF TRACK OF THE APPARATUS. APPARATUS A DOES NOT SUFFER ANY DAMAGE AND AT SUMMER MOVED TO THE AIR OF PARKING. A TEAM OF MAINTENANCE OF THE COMPANY EAST GONE ON THE SPOT AND A FOUND THAT A DISC OF THE LT BRAKE WAS BROKEN. REPLACED BRAKE. (TC NR 20070730002) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081104 EU 2008 11 4 CA070730003 1 20070716 G 5610 WINDSCREEN BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33110 01514 WP ROTOL R333 R333482F12 GL COCKPIT CRACKED W B EMER. DESCENT O OTHER CR CRUISE 1 CA (CAN) AFTER LEVELLING OFF AT 20000 FT, THE RT PILOTS WINDSCREEN CRACKED. A/C BEGAN A DESCENT TO 5500 FT AND RETURNED TO BASE UNPRESSURIZED WITH NO FURTHER INCIDENT. WINDSHIELD HEAT WAS IN USE WITH NO OVERHEAT CAPTIONS.A NEW WINDSCREEN WAS INSTALLED WITH NO ABNORMALITIES IN ITS REMOVED AND REPLACED. (TC NR 20070730003) 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C P61GL 20081104 2008 11 4 CA070730004 1 20070102 G 2421 6431041 ROTOR HONEYWELL GENERATOR FAILED W O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 CA (CAN) RECENT DASH 8 400 AC GENERTOR (P/N1152218-3,-4,-5) FAILURE INVESTIGATIONS AT MFG HAVE IDENTIFIED THE MAIN ROTOR BA NDS AS THE INITIAL FAILURE LOCATIONS FOR FIVE GENERATORS INVESTIGATED (S/N 062C-0420, 062C-0421, 1152218-00026, 1152218- 00062, 1152218-00064). FIELDED AC GENERATORS MAY HAVE A WELD JOINT NONCONFORMANCE ASSOCIATED WITH INTERNAL ROTOR BANDS ( QTY 2 IAW GENERATOR). THE NONCONFORMANCE IDENTIFIED IS AN INCOMPLETE FUSION OF THE WELD JOINT. THIS CONDITION WAS INITIA LLY IDENTIFIED IN EARLY JAN 2007 ON GENERATOR S/N 1152218-00064 ORIGINALLY SHIPPED ON FEB 20, 2006. (TC NR 20070730004) 2007082000160 20070820 00160 SO 2007 8 20 CA070730005 1 20070728 G 5753 STRUCTURE LKHEED 188 188C 5262604 SO ALLSN 501D 501D13 03004 GL ALLSN A6441 A6441FN606 GL TE FLAPS SEPARATED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) FIRE SUPPRESSION OPERATIONS IN RUGGED MOUNTAINOUS TERRAIN. FINISHED LAST OF 4 DROPS. APPLIED MAX POWER AND FLAPS T O 78 PERCENT AND PROCEEDED WITH CLEAN UP CHECKLIST. NOTICED ABNORMAL OF CONTROL COLUMN ( MORE AILERON). ADJUSTED TRIMS AND POWER SETTINGS. PNF WENT TO THE BACK NOTICED DAMAGE TO RT OB PORTION OF FLAP. PILOT SLOWED AIRCRAFT. ADVISED FS S OF PROBLEM. PILOT RAN FLAPLESS CHECKLIST AND REQUESTED EMERGENCY VEHICLES. PILOT SLOWED AIRCRAFT TO DETERMINE CONTROLL ABILITY. REVIEWED BRAKE FIRE PROCEDURES PRIOR TO LANDING AND THEN FLEW APPROACH AT MARKED BUG TO RUNWAY AND LANDED WITHO UT INCIDENT. MAINTENANCE FOUND 5 FT OF THE RT FLAP PANEL SEPARATED FROM THE ASSEMBLY AND TRAILING ON THE FLAP RAIL. MAI 2 L 7 4 4T 4 T 4A22 E282 6 C P898 20081104 CE 2008 11 4 CA070730006 1 20070730 G 2497 1013841069 METER BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL ELECTRICAL LOAD DISCONNECTED W K NONE O OTHER IN INSP/MAINT 1 CA 100 (CAN) DURING START UP FOR SERVICE CHECK THE VOLTAGE WAS CHECKED BUT THERE WAS NO INDICATION ON THE METER. METER WAS REM OVED AND THE PUSH TO TEST SWITCH WAS FOUND DISCONNECTED FROM THE BODY OF THE METER. THE METER WAS REPLACED WITH REPAIRED UNIT. THIS METER WAS JUST INSTALLED AFTER A REPAIR. UNIT HAD ABOUT 100 HOURS ON IT, NUT THAT HOLDS SWITCH IN PLACE HAS STRIPPED OR BACKED OFF. UNIT SENT BACK FOR REPAIR. (TC NR 20070730006) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007082000161 20070820 00161 NE 2007 8 20 CA070731001 2 20070727 G 7320 SEAL AIRBUS 310 A310300 3930305 EU GE CF6 CF680C2A5 NE HMU LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 2538 (CAN) DURING TAXI-IN AT THE GATE, A LARGE FUEL LEAKAGE WAS OBSERVED COMING FROM THE HMU FUEL DRAIN BELOW NR 2 ENGINE. EN GINE WAS SHUTDOWN, BUT LEAKAGE CONTINUED. NR 2 ENGINE FIRE HANDLE WAS PULLED AND LEAKAGE STOPPED. FOUND LEAKAGE WAS F OM THE MEC SHAFT SEAL. MEC WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070731001) 2 L 7 2 4F 4 F RT A35EU E13NE 2007091200059 20070912 00059 SO 2007 9 12 CA070731002 1 20070727 G 2750 486597 FLEX COUPLING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL FLAP MOTOR SEIZED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA 6059 (CAN) ON CLIMB OUT PILOT FOUND HIS FLAP CIRCUIT BREAKER HAD POPPED AND HIS FLAPS WOULD NOT RETRACT. HE MADE AN UNEVENTF UL LANDING. UPON TROUBLE SHOOTING, IT WAS FOUND THAT THE R/H FLAP FLEX SHAFT (MOTOR TO TRANSMISSION) WAS SEIZED. AS A RESULT OF THE SEIZED SHAFT, THE MOTOR WAS ALSO DAMAGED. THE MOTOR AND SHAFT HAVE BOTH BEEN REPLACED AND THE AIRCRAFT RE LEASED FOR SERVICE. (TC NR 20070731002) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008032400416 20080324 00416 CE 2008 3 24 CA070801001 1 20070727 G 2810 369200157 FUEL CELL BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO HARTZL HCC3Y PHCC3YF2 GL RT WING DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE RT WING LEADING EDGE FUEL CELL WAS REMOVED BECAUSE OF A FUEL LEAK. A REPLACEMENT FUEL CELL WAS ORDERED. PRIOR TO INSTALLATION OF THE NEW (OVERHAULED) CELL, IT WAS INSPECTED AND FOUND TO CONTAIN A LARGE QUANTITY OF SAWDUST-LIKE PAR TICLES. ON FURTHER INSPECTION, THE FUEL CELL STILL HAD THE FOAM FILLED FUEL RESERVOIR INSIDE. THIS FOAM WAS BREAKING DOW N. AFTER DISCUSSIONS WITH MFG TECH SUPPORT IT WAS CONCLUDED THAT AD68-26-06 HAD BEEN COMPLIED WITH AT SOME POINT OF TIME WHICH REQUIRED THE INSTALLATION OF FUEL RESERVOIRS TO PREVENT ENGINE POWER LOSS DURING STEEP TURNS ON TAKEOFF. THESE RE SERVOIRS HAD A FOAM INSERT WHICH WAS COMPATIBLE WITH 100/130 FUEL. THE USE OF 100LL HOWEVER CAUSES THE FOAM TO BREAK DOW 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P25EA 2007082100081 20070821 00081 2007 8 21 CA070801002 4 20070731 G 2330 3088510101 ENTERTAIN SYS BOEING 737 737* NM CFMINT CFM567 CFM567B22 13802 NE CABIN SMOKE W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) WHILE LOADING THE AFT BAGGAGE PIT, A BURNING ELECTRICAL ODOR AND SMOKE WERE NOTICED AND TRACED TO THE LIVE-TV ELEC TRICAL RACK COMPONENT WIRELESS AIRCRAFT UNIT. POWER WAS REMOVED FROM THE AIRCRAFT AND THE WIRELESS AIRCRAFT UNIT WAS RE MOVED. THIS COMPONENT WILL BE RETURNED TO THE MFG AND A COMPLETE TEARDOWN REPORT WILL BE REQUESTED. THIS SDR WILL BE UP DATED ONCE THAT INFORMATION IS AVAILABLE. (TC NR 20070801002) 2 L 7 2 4F 4 F RT A16WE E00055EN 2007082100083 20070821 00083 SO 2007 8 21 CA070801003 2 20070725 G 8550 635616 PAN CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C401 GL ENGINE OIL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) OIL PAN FOUND CRACKED DURING INSPECTION. (TC NR 20070801003) 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2007082100084 20070821 00084 SO 2007 8 21 CA070801004 2 20070720 G 8530 AEC65385 CYLINDER CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO HARTZL HCC3Y HCC3YF1 GL NR 6 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION FOUND 6 CYLINDER CRACKED AT SPARK PLUG HOLE. (TC NR 20070801004) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P25EA 2007082100085 20070821 00085 SO 2007 8 21 CA070801005 2 20070720 G 8530 AEC65385 CYLINDER CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO HARTZL HCC3Y HCC3YF1 GL NR 5 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION FOUND NR 5 CYLINDER CRACKED AT SPARK PLUG HOLE. (TC NR 20070801005) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P25EA 2007082100086 20070821 00086 EU 2007 8 21 CA070801006 1 20070729 G 3320 BR6303121 LIGHT SAAB SF340 340B 7860101 EU GE CT7TP CT75A2 30030 NE ROTOL R389 R3894123F25 NE CABIN OVERHEATED W A UNSCHED LANDING M B OVER TEMP SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) CABIN OVERHEAD FLOURESCENT LIGHTING FIXTURE OVERHEATED. BURNED OUT BULB FOUND AND CONTACTS IN FIXTURE THAT CONDUC T ELECTRICITY TO BULB FOUND LOOSE AND OVERHEATED, CAUSING PLASTIC PART OF ASSY TO OVERHEAT. PARTS REPLACED AND A/C RELEA SED TO SERVICE WITHOUT ANY FURTHER INCIDENT. (TC NR 20070801006) 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P30NE 2007091200060 20070912 00060 SW 2007 9 12 CA070801007 1 20070731 G 6510 476205561 BEARING BELL 47 47G2 1181008 SW LYC O435 VO435A1E 41516 EA DRIVE ASSY FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 889 (CAN) ON WALK AROUND TAIL ROTOR OUTPUT SHAFT AT TRANSMISSION WAS NOTED TO HAVE LOTS OF PLAY, FWD DRIVESHAFT WAS REMOVED TO CHECK FOR COUPLING SPLINE WEAR WHICH WAS GOOD SO THE DRIVE ASSY WAS REMOVED FOR FURTHER INVESTIGATION. IT WAS DETERMI NED THAT ONE OF THE DUPLEX BEARINGS WAS ROUGH AND THE ROLLER BEARING P/N 47-620-929-1 WAS WORN AND THE DRIVE GEAR WAS SH OWING SIGNS OF UNEVEN WEAR CAUSED BY THE DUPLEX BEARING STARTING TO FAIL WHICH IN TURN MADE THE SHAFT MOVE IN AN UNEVEN PATTERN DAMAGING THE GEAR AND ROLLER BEARING. THE ROUGH FEELING DUPLEX BEARING WAS TAKEN APART AND FOUND THAT THE INNER RACE WAS STARTING TO SPALL ABOUT A THIRD OF THE WAY AROUND, NO METAL OR FLAKES HAD BEEN FOUND AND THE SCREEN WAS PULLED 1 G 7 1 3O 3 O H1 E279 2007082100087 20070821 00087 NE 2007 8 21 CA070801008 2 20070720 G 8530 327626 CYLINDER HEAD CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE ENGINE CRACKED W E ENGINE SHUTDOWN R B PARTIAL RPM/PWR LOSS SMOKE/FUMES/ODORS/SPARKS FF FIRE FIGHTING 1 CA 76 P35411 (CAN) DURING A NORMAL WATER PICKUP FOR FIRE FIGHTING OPERATIONS, THERE WAS A NOTICEABLE LOSS OF MANIFOLD PRESSURE(MP) AN D BMEP INDICATIONS. ON NR 1 POWER REDUCTION THERE WAS A SMALL BACKFIRE AND FURTHER LOSS OF MP AND BMEP. WATERLOAD WAS J ETTISONED AND FLIGHTCREW REDUCED POWER TO CLIMB. THEY CLIMBED TO CRUISE ALTITUDE AND NOTICED A SMALL OIL LEAK AND SMOKE TRAIL. ALL OTHER INDICATIONS WERE NORMAL EXCEPT FOR A COLD CYLINDER HEAD TEMP. AFTER APPROX.: 45 WITH A SMOKE TRAIL AND OIL LEAK APPARENTLY GETTING WORSE, THE FLIGHTCREW SHUT DOWN AND SECURED THE RT ENGINE. AME FOUND CRACKED NR 2 CYCLINDER AND BROKEN PUSHROD AND HOUSING. CYLINDER WAS REPLACED, SCREEN CHECKED OK. ENGINE GROUND RUN AND FOUND SERVICEABLE. (TC 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 2007082100088 20070821 00088 EA 2007 8 21 CA070801009 1 20070722 G 2612 41493 ELBOW CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE FIRE DETECTION CRACKED W E ENGINE SHUTDOWN N FALSE WARNING CR CRUISE 1 CA 4816 4816 1003 (CAN) DURING BOMBING OPERATIONS, FLIGHTCREW HAD AN INTERMITTENT RT, ZONE 1 FIRE INDICATION. THEY LEFT THE FIRE CIRCUIT, CLIMBED TO ALTITUDE, AND SECURED RT ENGINE IAW CHECKLIST. SHORTLY AFTERWARD (APPROX 5 MINUTES)THE LT GENERATOR FAILED. UPON ENTERING THE ZONE, ELECTRICAL POWER LOST TO RADIOS, MADE A LANDING WITHOUT INCIDENT. AMES FOUND CRACKED CERAMIC ELBOW ON FIRE DETECTION SYSTEM THE FOLLOWING DAY AFTER ANOTHER FALSE INDICATION. ELECTRICAL POWER CHARGING SYSTEM LOST WHEN LT ENGINE GENERATOR FAILED ON OPERATING ENGINE DURING SINGLE ENGINE OPERATIONS. GENERATOR REPLACED. SYSTEM CHECKED, FOUND SERVICEABLE. (TC NR 20070801009) 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 2007091200061 20070912 00061 CE 2007 9 12 CA070802001 1 20070214 G 5311 11543008435 FRAME BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 19854 (CAN) ON INSPECTION WE NOTICED THE FRAME WAS CRACKED ON THE LT AND THE RT SIDE. A NEW FRAME WAS INSTALLED. (TC NR 20070 802001) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007091200062 20070912 00062 CE 2007 9 12 CA070802002 1 20070213 G 5210 504300431397 CABLE BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL DOOR STEP FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON INSPECTION IT WAS NOTICED THAT THE UPPER AND THE LOWER CABLES WERE FRAYED. THEY WERE REPLACED AND ADJUSTED. (TC NR 20070802002) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007091200063 20070912 00063 CE 2007 9 12 CA070802003 1 20070312 G 5344 HINGE BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL LT DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON INSPECTION THE LT DOOR WAS FOUND CRACKED ALONG THE FRONT HINGE. (TC NR 20070802003) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007091200064 20070912 00064 CE 2007 9 12 CA070802004 1 20070723 G 2810 1019200931 FUEL TANK BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL PURGE TANK CRACKED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA (CAN) IT WAS NOTICED THAT ON SHUTDOWN THE LT ENGINE SMOKED. NOTICE THAT THE COLLECTOR TANK WAS CRACKED ALONG THE WELD. (TC NR 20070802004) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007082100093 20070821 00093 2007 8 21 CA070802005 4 20070726 G 6113 05503214 BULKHEAD CESSNA 172 172N 2072434 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL SPINNER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 380 (CAN) THIS AIRCRAFT HAS HAD ALL THE AFT BULKHEAD AND HEAVIER SPINNER UPGRADES AND HAS HAD IT ALL ASSEMBLED IAW THE LATES T SB. CRACKS WERE FOUND FORMING PARALLEL FROM THE PROP BOLT HEAD CONTACT SURFACE ON (3) OF THE (6) HOLES. HAVE TO LOOK V ERY CAREFULLY AS THE CRACKS RADIATING FROM THE PROP BOLT HOLES ARE VERY FINE AND HIDE UNDER THE FACTORY PRIMER. THE TORQ UE OF THE PROP BOLTS IS SHEAR STRESSING THE BULKHEAD. A COVER PLATE IS NEEDED TO OFFSET THE BOLTS FROM THE THIN ALUMINUM SHEET METAL BULKHEAD. THIS PROBLEM IS CONSTANTLY RE-OCCURRING WITH THIS SPINNER ASSY. (TC NR 20070802005) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007082100095 20070821 00095 EA 2007 8 21 CA070802006 2 20070724 G 8530 LW12416 CYLINDER CESSNA 172 172N 2072434 CE LYC O320 O320D2J 41508 EA ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2019 (CAN) (2) CRACKS FOUND DURING ENGINE ON-CONDITION INSPECTION. CRACKS START FROM BOTTOM SPARK PLUG HOLE AND EACH CRACK GO ES TO A VALVE SEAT. THESE CRACKS WERE NOT DETECTED DURING DIFFERENTIAL PRESSURE INSPECTION OR LEAK TEST. INTERNAL BORESC OPE INSP WAS DETECTION METHOD IAW LATEST B041. (TC NR 20070802006) 1 H 7 1 3O 3 O NT 3A12 E274 2007091200002 20070912 00002 SO 2007 9 12 CA070802007 1 20070722 G 7810 65442003 CLAMP PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA SNSNCH 74D 74DM EA EXHAUST PIPE WORN W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) PIN THAT PROTRUDES THROUGH THE MUFFLER AND EXHAUST PIPE WAS WORE ALLOWING THE THEM TO SEPARATE. OTHER AIRCRAFT IN THE FLEET WERE CHECKED AND FOUND OK. (TC NR 20070802007) 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2007082100097 20070821 00097 GL 2007 8 21 CA070802008 3 20070727 G 6197 MS3126E1419S CONNECTOR DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL WIRE HARNESS UNSERVICEABLE W E A ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) ON CLIMB OUT SHORTLY AFTER TAKEOFF, THE BETA WARNING LIGHTS (BOTH) CAME ON AND THE NR 2 PROPELLER STARTED TO FEATH ER. THE PILOT PULLED THE BETA SYSTEM CIRCUIT BREAKER BUT THE LIGHTS DID NOT GO OFF, BUT THE PROPELLER STOPPED GOING TO FEATHER. THE PILOT LANDED AND CONTACTED MAINTENANCE. WHEN MAINTENANCE DID A GROUND RUN THE NR 2 PROPELLER WOULD NOT CO ME OUT OF FEATHER. TROUBLESHOOTING THE SYSTEM FOUND THAT THE CONNECTOR ON THE BETA SYSTEM CONTROL BOX WAS SHORTED OUT I NTERNALLY, WHICH CAUSED FAULTS IN THE BETA CONTROL AND CAUTION LIGHT DIMMING CIRCUITS. THE BETA SYSTEM WAS CAUSED TO (T HINK) THE NR 2 PROPELLER WAS GOING INTO BETA, WHEN ACTUALLY IT WAS NOT, AND THEREFORE STARTED TO FEATHER THE PROPELLER. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007082100099 20070821 00099 NM 2007 8 21 CA070802009 1 20070702 G 6123 30005000056 TSCU DHAV DHC8 DHC8201 2809001 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE NR 2 MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) AUTOFEATHER ARM LIGHT FAILED TO ILLUMINATE DURING TAKEOFF ROLL (AUTO FEATHER SYSTEM INOP). REPLACED THE NR 2 TSCU IAW P/W MM 72-01-10, PAGE 420-424, PARAGRAPH 7. GROUND RUNS COMPLIED WITH. OPERATIONAL CHECK GOOD. AIRCRAFT RETURNED T O SERVICE. (TC NR 20070802009) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007082100101 20070821 00101 EA 2007 8 21 CA070802010 1 20070801 G 5270 SAL2D864 PLUNGER DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL CARGO DOOR SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION, FOWARD CARGO DOOR SWITCH PLUNGER WAS FOUND SEIZED. (TC NR 20070802010) 1 H 7 1 3T 4 T A806 E4EA 6 C P15EA 2007091200004 20070912 00004 CE 2007 9 12 CA070803001 1 20070420 G 5753 052323113 FLAP TRACK CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL LT TE FLAP SEPARATED W A UNSCHED LANDING E F VIBRATION/BUFFET FLT CONT AFFECTED DE DESCENT 1 CA (CAN) DURING HARD MANEUVERING WITH FLAPS DOWN, A LOUD BANG WAS HEARD BY THE PILOTS WHO NOTICED THE LT FLAP BEING PUSHED BACK AT A STRANGE ANGLE. THE FLAPS WERE LEFT IN THE DOWN POSITION AND THE AIRCRAFT WAS RETURNED WITHOUT INCIDENT. UPON INVESTIGATION THE LT IB FLAP TRACK WAS FOUND SEPARATED AND CRACKED FROM THE AIRFRAME AT THE LOWER FLANGE. THE CAUSE AP PEARS TO BE THE CHERRYMAX RIVETS ATTACHING THE LOWER FLANGE OF THE WING RIB FRETTING, BECOMING WORN, AND WEARING THE RIV ET HOLES IN THE WING SPAR UNTIL THE HIGHER STRESSES OF MANEUVERING TORE THEM FREE. THE FLAPS AND TRACKS WERE REMOVED, SPAR INSPECTED WITH NO DAMAGE NOTED. THE FLAP TRACK RIB ASSY`S WERE REPLACED, USING STRUCTURAL SCREWS AND NUTS TO ATTAC 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007082100102 20070821 00102 EA 2007 8 21 CA070803002 1 20070802 G 6123 3014403 TSCU DHAV DHC6 DHC6300 2802606 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE RIGHT INOPERATIVE W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 667 (CAN) AUTOFEATHER DID NOT ARM DURING THE TAKEOFF ROLL. TAKEOFF WAS ABORTED AND AN AUTOFEATHER TEST PERFORMED ON THE TAXI WAY WHICH ALSO DID NOT ARM THE AUTOFEATHER. RETURNED TO BLOCK WHERE MAINTENANCE PERFORMED TROUBLESHOOTING AND REPLACED T HE RT TSCU. (TC NR 20070803002) 1 H 7 2 3T 4 T RT A9EA E20NE 6 C P7NE 2007082100104 20070821 00104 EU 2007 8 21 CA070803003 1 20070601 G 6123 3004800001 AUTOFEATHER SYS AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE PROP CONTROL DEFECTIVE W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA (CAN) THE ENGINE WAS REPORTED TO HAVE EXPERIENCED AN INFLIGHT SHUTDOWN. AUTOFEATHER CONTROL UNIT WAS SUBSEQUENTLY REPLA CED. (TC NR 20070803003) 2 H 7 2 4T 4 T RT E20NE 2007082100107 20070821 00107 EA 2007 8 21 CA070803004 2 20070601 G 7261 OIL SYSTEM SKRSKY S76 S76B 8143007 NE PWA PT6 PT6B36 52043 EA ENGINE LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA PT0001 (CAN) ENGINE OIL TEMPERATURE WAS OBSERVED TO INCREASE IN FLIGHT AND THE PILOT ELECTED TO SHUT THE ENGINE DOWN. OIL WAS SUBSEQUENTLY SEEN LEAKING FROM THE ENGINE EXHAUST. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMI NED. (TC NR 20070803004) 1 G 7 2 4U 4 U H1NE E4EA 2007082100110 20070821 00110 NE 2007 8 21 CA070803005 2 20070530 G 7250 TURBINE BLADES AIRTRC AT802 AT802A 0390308 SW PWA PT6 PT6A67A 52043 NE ENGINE FRACTURED W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA RD0007 (CAN) THE ENGINE LOST POWER ON TAKEOFF ROLL AND THE TAKEOFF WAS ABORTED. SUBSEQUENT INSPECTION REVEALED FRACTUED POWER TURBINE BLADES AND A DISCONNECTION BETWEEN THE POWER TURBINE AND PROP. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROO T CAUSE ONCE ESTABLISHED. (TC NR 20070803005) 1 L 7 1 3T 4 T NC A19SW E26NE 2007091200005 20070912 00005 CE 2007 9 12 CA070803006 1 20070803 G 3244 0213500 TIRE RAYTHN C90 C90GT 7150062 CE PWA PT6 PT6A135 52043 NE HARTZL HCE4N HCE4N3 NE MLG DELAMINATED W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 CA 223 (CAN) VIBRATION REPORTED ON TAKEOFF AND LANDING STARTING/ENDING AT 60-70 KNOTS, VIBRATION INCREASED AT HIGH SPEEDS ON GR OUND AND DISAPPEARED AFTER LANDING GEAR WAS RETRACTED. LT AND RT MAIN WHEEL TIRE BALANCE PATCHES WERE FOUND DELAMINATED AND FLOATING INSIDE WHEEL ASSEMBLIES. RT TIRE P/N 021-350-0 S/N 6121W00482 REPLACED WITH TIRE P/N 850T06-3, LT TIRE P/ N 021-350-0 S/N 6200W00106 ALSO REPLACED WITH NEW TIRE P/N 850T06-3 2) HIGH SPEED TAXI CHECKS COMPLETED WITH PILOTS UP TO 100 KNOTS, NO VIBRATIONS NOTED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070803006) 1 L 7 2 3T 4 T RT 3A20 E4EA 5 C P10NE 2007091200006 20070912 00006 NE 2007 9 12 CA070803007 2 20070617 G 7200 PT6A67R ENGINE STBROS SD3 SD360 8100606 EU PWA PT6 PT6A67R 52043 NE DAMAGED W O OTHER B R J SMOKE/FUMES/ODORS/SPARKS PARTIAL RPM/PWR LOSS WARNING INDICATION AP APPROACH 1 CA (CAN) ON SHORT FINAL, THE ENGINE LOST POWER AND SMOKE WAS SEEN EXITING THE ENGINE EXHAUST. POST-FLIGHT INSPECTION REVEA LED INTERNAL ENGINE DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE COMPLETED. (TC NR 20070803007) 2 H 7 2 4T 4 T A41EU E26NE 2007091200007 20070912 00007 NE 2007 9 12 CA070803008 2 20070618 G 7210 TOWERSHAFT DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE REDUCTION GB SEIZED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA (CAN) THE ENGINE WAS REPORTED TO HAVE EXPERIENCED AN INFLIGHT SHUTDOWN. SUBSEQUENT INSPECTION REVEALED A SEIZED TOWER S HAFT AND DEBRIS IN THE ENGINE OIL. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 200 70803008) 2 H 7 2 4T 4 T RT A13NM E20NE 2007091200008 20070912 00008 CE 2007 9 12 CA070803009 1 20070803 G 3244 0763670 TIRE RAYTHN C90 C90GT 7150062 CE PWA PT6 PT6A135 52043 NE HARTZL HCE4N HCE4N3 NE NLG OUT OF ROUND W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 CA 187 (CAN) NOSE WHEEL SHIMMY TIRE PN 076-367-0 SN 4190W00091 FOUND OUT OF ROUND .5 INCH. TIRE REPLACED AND REBALANCED. NOSE WHEEL STEERING DAMAGE CAUSED BY SHIMMY REPAIRED AS REQUIRED ALL WORN BOLTS, BUSHINGS, BEARINGS AND NOSE STEERING IDLER A SSY. REPLACED NEW. (TC NR 20070803009) 1 L 7 2 3T 4 T RT 3A20 E4EA 5 C P10NE 2007091200009 20070912 00009 GL 2007 9 12 CA070803010 1 20070227 G 7931 2279300004 TRANSMITTER DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA ENGINE OIL PRESS DEFECTIVE W O OTHER N FALSE WARNING DE DESCENT 1 CA (CAN) OIL PRESSURE REPORTED LOW WHEN ENGINE BROUGHT BACK TO IDLE FOR LANDING. INSTALLED NEW OIL PRESSURE SENDER AND AIRF RAME GAUGE CALIBRATION CHECK COMPLETED. LOGBOOK NOT AT CURRENTLY CLOSE AT HAND, FOR TOTAL TIME ON OIL SENDER, OPERATOR HAS REPLACED THEM IN THE PAST DUE TO SIMILAR TROUBLE. (TC NR 20070803010) 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2007091200010 20070912 00010 NE 2007 9 12 CA070803011 2 20070615 G 7210 MS949034 BOLT STBROS SD3 SD360 8100606 EU PWA PT6 PT6A67R 52043 NE REDUCTION GEAR SHEARED W E ENGINE SHUTDOWN J WARNING INDICATION CL CLIMB 1 CA (CAN) ON CLIMB, ENGINE OIL PRESSURE WAS SEEN TO FALL TO ZERO AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INVESTIG ATION REVEALED A SHEARED 1ST STAGE REDUCTION GEAR CARRIER BOLT. (TC NR 20070803011) 2 H 7 2 4T 4 T A41EU E26NE 2007091200011 20070912 00011 SO 2007 9 12 CA070803012 1 20070728 G 2720 63420006 TORQUE TUBE PIPER PA34 PA34200 7103405 SO LYC O360 LIO360C1E6 41515 EA HARTZL HCC2Y HCC2YK2 GL LT RUDDER BROKEN W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA 11513 (CAN) THE LT RUDDER CABLE TORQUE TUBE CONNECTION BROKE OFF FROM THE TUBE. RUDDER CONTROL WAS LIMITED TO THE TRIM. (TC N R 20070803012) 1 L 7 2 3O 3 O A7SO 1E10 5 C P920 2007091200012 20070912 00012 NE 2007 9 12 CA070803013 2 20070625 G 7250 TURBINE BLADES UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206B 0 NE ENGINE DAMAGED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA BB0113 (CAN) THE ENGINE WAS REPORTED TO HAVE SHUTDOWN IN CRUISE. SUBSEQUENT INSPECTION REVEALED POWER TURBINE BLADE DAMAGE. M FG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070803013) 1 G 7 2 3U 3 U O H88EU E42NE 2007091200013 20070912 00013 NE 2007 9 12 CA070803014 2 20070627 G 7200 ENGINE FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE POWER LOSS W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 124152 (CAN) THE ENGINE LOST POWER IN FLIGHT AND WAS SHUTDOWN BY THE CREW. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROO T CAUSE ONCE ESTABLISHED. (TC NR 20070803014) 2 H 7 2 4T 4 T RT A817 E20NE 2007091200014 20070912 00014 GL 2007 9 12 CA070803015 1 20070730 G 7931 2279300004 TRANSMITTER DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA ENGINE OIL PRESS DEFECTIVE W O OTHER N FALSE WARNING DE DESCENT 1 CA 194 (CAN) PILOT REPORTED LOW OIL PRESSURE DURING DESCENT WITH ENGINE RPM REDUCED TO IDLE. COMPLEATED OIL PRESSURE GUAUGE CA LIBRATION CHART USING CABIBRATED GAUGE. INDICATED 30PSI -> ACTUAL 38PSI, INDICATED 20 -> ACTUAL 27PSI, INDICATED 15PSI - > ACTUAL 20PSI, INDICATED TOP OF RED LINE 12PSI -> ACTUAL 18PSI, MIDDLE OR REDLINE 10PSI -> ACTUAL 16PSI. (TC NR 200708 03015) 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2007091200015 20070912 00015 NE 2007 9 12 CA070803016 2 20070626 G 7230 COMPRESSOR BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE ENGINE SEIZED W E ENGINE SHUTDOWN Y J ENGINE STOPPAGE WARNING INDICATION AP APPROACH 1 CA 114113 (CAN) ON APPROACH, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A LOSS OF OIL PRESSURE AND AN INCREASE IN INTER-TURBIN E TEMPERATURE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED COMPRESSOR SEIZURE AND INTERNAL OIL L EAKAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070803016) 2 L 7 2 4T 4 T RT A24CE E26NE 2007091200017 20070912 00017 CE 2007 9 12 CA070804001 1 20070801 G 2840 AG112 SIGHT GLASS BOEING 75 A75N1 1380134 CE CONT R670 R670* 17016 SO FUEL TANK CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 351 (CAN) AD CF61-7 CALLS FOR AN ANNUAL REPLACEMENT OF THIS TUBE, HOWEVER THIS OPERATOR HAS OBTAINED AN AMOC TO ALLOW OPERAT ING UNTIL FAILURE. IT HAS BEEN FOUND THAT THIS TUBE WILL FAIL AT ANY TIME, REGARDLESS OF REPLACEMENT OR TIME IN SERVICE . IT WILL FAIL AT THE BASE WHERE IT IS INSERTED INTO THE TANK FITTING, AND WILL MANIFEST ITSELF AS A MINOR (WEEP). THE DANGER OF COURSE IS IF IT BREAKS OFF ENTIRELY. THEREFORE, CONTINUED VIGILENCE IS PARAMOUNT. (TC NR 20070804001) 1 Q 7 1 3R 3 R A743 E162 2007091700041 20070917 00041 SO 2007 9 17 CA070805001 1 20070803 G 3240 17766110 HOSE PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL RT MLG BRAKE FAILED W E ENGINE SHUTDOWN B A SMOKE/FUMES/ODORS/SPARKS FLAME/FIRE TX TAXI/GRND HDL 1 CA 2564 (CAN) WHILE THE PILOTS WHERE TAXIING THE AIRCRAFT, IT WAS NOTED THAT THE RT BRAKES WHERE U/S. AS THEY WHERE TAXIING BAC K TO THE FBO ANOTHER AIRCRAFT REPORTED SMOKE COMING FROM THE RT BRAKE AREA. THE FIRE WAS PUT OUT BY THE AIRPORT FIRE DE PARTMENT QUICKLY. AFTER THE INITIAL INSPECTION WAS CARRIED OUT, IT WAS FOUND THAT THE RT LOWER FLEXIBLE BRAKE LINE WAS U/S THAT ATTACHES TO THE CALIPER. THE RT TIRE WAS U/S DUE TO THE FIRE. THE WHEEL ASSY WAS REPLACED AND THE AIRCRAFT WA S TOWED TO THE FBO`S HANGER WHERE IT WAS JACKED AND A DETAILED INSPECTION WAS CARRIED OUT. AFTER THE INSPECTION WAS CAR RIED OUT, THERE WAS NO DAMAGE TO THE RT MLG, SURROUNDING PARTS AND STRUCTURE OTHER THAN THE FLEXIBLE BRAKE LINE, CALIPER 1 L 7 2 3T 4 T A8EA E4EA 6 C P15EA 2007091200018 20070912 00018 NM 2007 9 12 CA070807001 1 20070727 G 3230 651781914 LOCK ACTUATOR BOEING 737 73735B 13844BM NM GE CFM56 CFM563B1 13802 NE NLG FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) DURING APPROACH, THE NOSE LANDING GEAR DID NOT RECEIVE A DOWNLOCK INDICATION IN THE COCKPIT. IT WAS BELIEVED BY TH E CREW THAT THE GEAR FAILED TO EXTEND. A SECOND ATTEMPT WAS MADE AND THE NOSE GEAR EXTENDED AND LOCKED AS NORMAL. NOTE: THE EMERGENCY EXTENSION WAS NOT USED. WITH THE LANDING GEAR EXTENDED, THE AIRCRAFT WAS REMOVED FROM SERVICE AND FERRIE D TO DESTINATION. MAINTENANCE INSPECTED THE SYSTEM AND CONDUCTED TROUBLESHOOTING IAW THE AMM. AFTER CONSULTATION WITH M FG, THEY REPLACED THE LOCK ACTUATOR AS IT IS RESPONSIBLE FOR LOCKING THE LANDING GEAR IN THE UP AND DOWN POSITIONS. ITS REPLACEMENT WAS RECOMMENDED BY MFG. AS A PRECAUTION, THE NOSE GEAR ACTUATOR WAS ALSO REPLACED. THE LANDING GEAR UNDERWEN 2 L 7 2 4F 4 F RT A16WE E2GL 2007091200019 20070912 00019 NM 2007 9 12 CA070807002 1 20070803 G 2611 CGAB140000 SMOKE DETECTOR BOEING 737 737522 138449F NM CFMINT CFM56 CFM563C1 13802 EU FWD CARGO BAY MALFUNCTIONED W F A ACTIVATE FIRE EXT. UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA (CAN) ENROUTE, IT WAS LESS THEN AN HOUR INTO THE FLIGHT WHEN AN ORANGE DETECT LIGHT FOR THE FORWARD CARGO SMOKE DETECTIO N SYSTEM CAME ON. THE EXTINGUISHER SYSTEM WAS ACTIVATED AND THE FLIGHT DIVERTED TO CLOSEST AIRPORT AND LANDED SAFELY. A N INSPECTION OF THE FORWARD CARGO COMPARTMENT FOUND NO EVIDENCE OF FIRE OR SMOKE. AN OVERWEIGHT LANDING INSPECTION WAS C ARRIED OUT. THE AIRCRAFT WAS FERRIED BACK TO BASE WHERE THE SYSTEM WAS EXAMINED. NO SYSTEM FAULTS WERE FOUND, BOTH FOR WARD SMOKE DETECTORS WERE REPLACED AS A PRECAUTION AND THE DIVERTER VALVE AND METERING VALVE WERE REPLACED DUE TO THE SY STEM BEING ACTIVATED. THE CARGO SMOKE AND FIRE EXTINGUISHER SYSTEM INSTALLED ON THIS AIRCRAFT IS AN AAE STC ST01674AT. 2 L 7 2 4F 4 F RT A16WE E21EU 2007091200020 20070912 00020 EU 2007 9 12 CA070807003 3 20070804 G 6111 697071003 BLADE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU PROPELLER DAMAGED W O OTHER O OTHER AP APPROACH 1 CA 3425 360 (CAN) DURING APPROACH, AN AIRCRAFT EXPERIENCED IMPACT STRUCTURE DAMAGE DUE TO LOSS OF THE PROPELLER BLADE EROSION STRIP. THE PROPELLER COMPONENT CAME OFF AND STRUCK THE FUSELAGE ICE SHIELD AND DAMAGED THE FUSELAGE. INSPECTION FOUND THAT T HE COMPLETE EROSION STRIP (LEADING EDGE GUARD) WAS MISSING, FROM THE NR 5 BLADE ON LT PROPELLER. THIS BLADE HAD 308 FLIG HT HOURS AND 36O CYCLES SINCE IT WAS REPAIRED DUE TO A BLADE TIP CRACK. (TC NR 20070807003) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007091200021 20070912 00021 SO 2007 9 12 CA070807004 1 20070801 G 3240 17700200 PIN PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL PARKING BRAKE SHEARED W O OTHER O OTHER LD LANDING 1 CA (CAN) PARKING BRAKE VALVE STOP PIN IN THE OFF POSITION WAS SHEARED OFF CAUSING THE BRAKE LEVER TO GO PAST THE STOP POSIT ION. THIS CAUSE THE BRAKE TO BE IN A ON POSITION. ON LANDING THE PILOT TESTED HIS BRAKES BY PUMPING THE BRAKES AND BECAU SE THE LEVER WAS PAST THE STOP POSITION IT CAUSE THE BRAKES TO LOCK ON. WHEN THE PILOT LANDED, THE BRAKES WHERE BOTH LO CKED ON CAUSING THE TIRES TO BURST INTO FLAMES. (TC NR 20070807004) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007091200022 20070912 00022 2007 9 12 CA070807005 4 20070717 G 2397 MS3126E1419P CONNECTOR BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE NR 2 VHF RADIO BURNED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA (CAN) TRAINING FLIGHT, NOTICED SMOKE COMING UP FROM CENTER CONSOLE BEHIND VHF NR 2 RADIO. PUT DOWN, A/C ON GROUND. CO-P ILOT JUMPED OUT TO CHECK IN BATT COMPARTMENT. NO ANOMALIES FOUND. FORCE TRIM CB POPPED. CARGO RELEASE LIGHT CAME ON AND STAYED ON. VHF RADIO INOPERATIVE TO TRANSMIT AND RECEIVE, BUT WAS ALWAYS LIVE. CONNECTOR AT BASE OF PILOT CYCLIC STICK, FOUND BURNED/SHORTING OUT, AFFECTING ALL 3 CIRCUITS. (TC NR 20070807005) 1 G 7 1 4U 4 U H1SW E17EA 2007091200023 20070912 00023 EU 2007 9 12 CA070807006 1 20070714 G 6320 332A38101521 PIN SNIAS AS332 AS332C 8680808 EU TMECA MAKILA MAKILA1A 60040 EU M/R GEARBOX WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON MAIN ROTOR GEARBOX REMOVAL SMALL PIN P/N 332A38-1015-21 FOUND INSTALLED IN LIEU OF LARGE PIN P/N 332A38-1019-21 IN LOWER POSITION OF FORWARD SUSPENSION BAR. RESULTANT, RADIAL PLAY 6 MM APPROXIMATELY. MFG CONTACTED TO DETERMINE FU RTHER ACTION. RECORDS INDICATE PIN INSTALLED FOR 40 FLIGHT HOURS. (TC NR 20070807006) 2 G 7 2 4U 4 U H4EU E12NE 2007091200024 20070912 00024 EA 2007 9 12 CA070807007 2 20070715 G 7322 CONTROL CABLE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA CARBURETOR WORN W B A EMER. DESCENT UNSCHED LANDING R F PARTIAL RPM/PWR LOSS FLT CONT AFFECTED CL CLIMB 1 CA (CAN) ONCE AIRCRAFT REACHED 5000 FT THE PILOT COMMENCED CRUISE CHECKLIST, LEANED THE MIXTURE OF THE ENGINE WHEN THE POWE R REDUCED TO IDLE. PILOT COULD NOT REGAIN ENGINE POWER AND MADE THE DECISION TO LAND IN A FIELD APPROX 3 MILES NE OF AIR PORT. UPON LANDING THERE WAS NO APPARENT DAMAGE TO THE AIRCRAFT OR THE PEOPLE ON BOARD. UPON INSPECTION, THE AIRCRAFT W AS NOT DAMAGED AND IT WAS FOUND THAT THE HARDWARE ATTACHING THE MIXTURE CABLE TO THE CARBURETOR WAS WORN, ALLOWING THE C ABLE TO SLIDE IN THE CARBURETOR MIXTURE ARM. (TC NR 20070807007) 1 H 7 1 3O 3 O NT 3A12 E274 2007091200025 20070912 00025 SW 2007 9 12 CA070807008 1 20070805 G 2913 DRIVE SHAFT ROMEC BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL HYD PUMP SHEARED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 2074 2074 00010494 (CAN) APPROX 1 HR INTO FLIGHT, COCKPIT NR WARNING HORN CAME ON INTERMITTENTLY. NR GAUGE BEGAN GIVING ERRATIC INDICATION S, BEFORE PROGRESSIVELY DECAYING DOWN TO A STABILIZED READING OF 30 PERCENT. AFTER LANDING, A VISUAL INSP REVEALED A LA RGE AMOUNT OF HYDRAULIC FLUID ON THE XMSN DECK, AND A SHEARED OFF INTERNALLY WRENCHING SOCKET HEAD FROM THE UPPER LT COR NER OF MOUNTING PLATE OF THE NR TACH DRIVE ASSY TO THE HYDRAULIC PUMP. PILOT OPENED UP HYDRAULIC RESERVOIR AND FOUND AP PROX 20 PERCENT OF FLUID REMAINING. ENGINEER WAS CALLED AND REMOVED THE NR TACH GENERATOR, REVEALING A SHEARED SHAFT AT THE DRIVE ADAPTER FOR THE TACH GENERATOR. HYDRAULIC PUMP AND RESERVOIR ASSEMBLY WAS REPLACED, AND AIRCRAFT DEPARTED FO 1 G 7 1 3U 3 U H2SW E4CE 2007091200026 20070912 00026 WP 2007 9 12 CA070808001 1 20070807 G 7820 C16932 MUFFLER ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE TAILPIPE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 609 (CAN) DURING SCHEDULED INSPECTION. AD CF90-03R2 BEING ACCOMPLISHED, A LARGE CRACK WAS FOUND AT THE TAILPIPE ATTACHMENT POINT, IN THE MUFFLER SUB-ASSY. IT WAS DIFFICULT TO DETERMINE ROOT CAUSE OF CRACK ORIGINATION, BUT POSSIBLE CAUSE WAS I MPACT WITH FOREIGN OBJECT WHEN AIRCRAFT LANDED IN AN UNPREPARED LANDING AREA. MUFFLER SUB-ASSEMBLY P/N C169-32 REPLACED WITH NEW ASSY, SAME P/N, A/C RELEASED FOR CONTINUED OPERATION (TC# 20070808001) 1 G 7 1 3O 3 O H11NM 1E4 20081104 CE 2008 11 4 CA070808002 1 20070807 G 3244 10X3504 TIRE CESSNA 185 A185F 2072821 CE CONT O550 IO550D 17042 SO MCAULY D3A34 D3A34C401 GL MLG BULGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TIRE CORDS DELAMINATING FROM THE INSIDE ALL AROUND THE TIRE. NO EXTERNAL FAULTS COULD BE DETECTED VISUALLY UNTIL TIRE BEGAN TO BULDGE. (TC NR 20070808002) 1 H 7 1 3O 3 O 3A24 E3SO 5 C P47GL 2007091700042 20070917 00042 CE 2007 9 17 CA070808003 1 20070807 G 5610 10138402523 WINDSCREEN BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) ON CLIMBOUT, PILOTS WINDSCREEN SHATTERED/CRACKED. DEVIATED TO ANOTHER AND DEPLANED PASSENGERS. THE PILOTS INSPEC TED THE WINDSCREENS AND DECIDED, BASED ON INFORMATION PROVIDED BY MAINTENANCE, OUT OF MM CHAPTER 5, THAT IT WOULD BE ACC EPTABLE TO FERRY FOR WINDSCREEN REPLACEMENT. MAINTENANCE PERSONNEL DETERMINED THAT THE COPILOTS WINDSCREEN WAS DELAMINA TED AND HAD SMALL CRACKS IN THE LOWER INSIDE CORNER. IT HAS BEEN CONCLUDED THAT AT SOME POINT IN TIME THE WINDSCREEN HE AT HAD BEEN LT ON AND HAD DELAMINATED THE RT WINDSCREEN, IT WAS UNDETERMINED WHAT HAD OCCURRED TO THE LT WINDSCREEN TO CAUSE IT TO SHATTER. (TC NR 20070808003) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 20081112 2008 11 12 CA070808004 2 20070808 G 7414 10400576 CAPACITOR MAGNETO MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) WHEN REMOVED FROM PACKAGE (NEW) THE FLAG TERMINAL THAT CONNECTS TO THE POINTS IN THE MAGNETO DID NOT HAVE ANY WIRE VISIBLE OUTSIDE THE CRIMP AREA OF THE TERMINAL. ACCORDING TO MFG, THE WIRE MUST BE FLUSH OR EXTENDED SLIGHTLY BEYOND TH E CRIMP AREA. ALL 54 CAPACITORS IN STOCK WERE CHECKED AND FOUND TO HAVE THE SAME DEFECT. THESE CAPACITORS WILL BE SENT B ACK TO TCM FOR WARRANTY EVALUATION. 2007091700043 20070917 00043 2007 9 17 CA070809001 4 20070806 G 3442 CDU BOEING 737 737210C 1384459 NM PWA JT8 JT8D9A 52048 NE WX RADAR FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) IN CRUISE AFTER DEPARTURE, THE CREW OBSERVED A FAILURE WITH THE WEATHER RADAR. DUE TO FORECAST CONDITIONS THE CRE W ELECTED TO RETURN TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE DISPLAY UNIT AND THE SYSTEM TESTED SERVICEABLE. TH E AIRCRAFT WAS RETURNED TO SERVICE WITH NO FURTHER PROBLEM REPORTED. (TC NR 20070809001) 2 L 7 2 4F 4 F A16WE E2EA 20081105 CE 2008 11 5 CA070809002 1 20070809 G 3233 ADI79990021A ACTUATOR BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL MLG DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NOSE GEAR ACTUATOR SENT IN TO HAVE SEALS REPLACE DO TO UNIT BECAUSE IT WAS SITTING ON SHELF FOR 6 YEARS. ACTUATOR WAS OVERHAULED AND HAD NEVER BEEN USED. UNIT WAS DISASSEMBLED TO REPLACE SEALS AND INTERIOR OF CYLINDER WAS SCORED AND A SPRING BROKEN. ACTUATOR HAS BEEN SENT BACK FOR OVERHAUL. 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2007091700044 20070917 00044 NM 2007 9 17 CA070809003 1 20070805 G 2622 898052 EXTINGUISHER BOEING 737 737* NM CFMINT CFM567 CFM567B22 13802 NE COCKPIT LEAKING W G O2 MASK DEPLOYED K FLUID LOSS CR CRUISE 1 CA 12530 (CAN) FLIGHT DECK FIRE EXTINGUISHER LEAKED IN CRUISE. CAPTAIN AND F/O HEARD A HISSING SOUND COMING FROM THE FIRE EXTING UISHER BEHIND AND LEFT OF THE F/O. CAPTAIN AND F/O DONNED O2 AND ASSESSED THE SITUATION IE; FEELING THE LEAK NEAR THE EX TINGUISHER`S NECK. CAPTAIN THEN RELEASED FIRE EXTINGUISHER FROM IT’S HOLDER AND STOWED THE UNIT IN THE FORWARD LAVATORY FOR THE REMAINDER OF THE FLIGHT. CAPTAIN OPENED VENTS AND PUT PACKS ON HIGH AND ENQUIRED AS TO HOW THE FO WAS FEELING. FO SEEMED FINE AND LATER COMMENTED THAT HE MAY HAVE BEEN A BIT DIZZY. A DETAILED REPORT HAS BEEN REQUESTED FROM THE RE PAIR FACILITY AND DETAILS WILL BE UPDATED TO THIS REPORT AS THEY ARE OBTAINED. (TC NR 20070809003) 2 L 7 2 4F 4 F RT A16WE E00055EN 20081104 NM 2008 11 4 CA070809004 1 20070610 G 2622 898052 EXTINGUISHER BOEING 737 737* NM CFMINT CFM567 CFM567B22 13802 NE COCKPIT FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA 10279 (CAN) FOUND A FLIGHT DECK FIRE EXTINGUISHER THAT WAS REMOVED FROM THE AIRPLANE FOR LOSS OF PRESSURE. BOTTLE WAS FOUND CO MPLETELY EMPTY AND THE TOP WAS LOOSE. YOU COULD SPIN THE TOP RIGHT OFF. STRIP REPORT REQUESTED FROM REPAIR FACILITY FOR INFORMATION. THIS REPORT WILL BE UPDATED AS INFORMATION BECOMES AVAILABLE. (TC NR 20070809004) 2 L 7 2 4F 4 F RT A16WE E00055EN 20081105 EA 2008 11 5 CA070810001 1 20070809 G 3212 6A05158019 COVER DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL MLG FLOATS DAMAGED W A UNSCHED LANDING J WARNING INDICATION LD LANDING 1 CA 220 (CAN) THIS TURBO OPERATING AMPH FLOATS WAS ON DESCENT TO LAND AT ITS HOME AIRPORT WHEN THERE WAS NO GEAR DOWN INDICATION ON RT MAIN WHEEL. PILOT ASKED PASSENGER IN THE RT SEAT TO LOOK AT THE TOP OF FLOATS TO CHECK TIE-DOWN ROPES, AND IT WAS NOTICED THAT THE END OF THE FLOAT ROPE WAS IN INSP HOLE ABOVE MAIN GEAR LOCKING MECHANISM. PILOT RETRACTED THE LANDING GEAR TO UP POSTION AND WHEN THERE WAS ALL 4 GEAR UP INDICATION, HE LANDED SAFELY IN THE WATER. ACFT WAS THAN TRANSPORTED TO ITS MAINT BASE WHERE PROBLEM WAS IDENTIFIED AS A DAMAGED UP LOCK CARRAIGE COVER, IT WAS THAN REPLACED WITH A NEW UNI T. THE SYSTEM WAS FUNCTION TESTED SERVICEABLE AND ACFT WAS RETURNED TO SERVICE. NOTE: THE PILOT IN COMMAND WILL BE MORE 1 H 7 1 3T 4 T A806 E4EA 6 C P15EA 2007091200027 20070912 00027 EA 2007 9 12 CA070812001 1 20070809 G 3230 4622 PRIORITY VALVE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE NLG FAULTY W O OTHER O OTHER AP APPROACH 1 CA 12320 3214 (CAN) ON APPROACH, GEAR WAS SELECTED DOWN AND THE NOSE GEAR DID NOT COME DOWN. THE CREW THEN CYCLED THE GEAR, BUT THE N OSE GEAR STILL DID NOT COME DOWN. THE CREW SWITCHED 3B HYDRAULIC PUMP FROM AUTO TO ON AND 30 SECONDS LATER THE NOSE GEA R CAME DOWN. THE LANDING GEAR WAS DEFERRED FOR THE A/C TO RETURN FOR REPAIR. MAINTENANCE T/S DISCOVERED NLG PRIORITY V ALVE TO BE AT FAULT. PRIORITY VALVE WAS REPLACED AND GEAR SWINGS C/O AND A/C WAS CHECKED SERVICEABLE. (TC NR 2007081200 1) 2 L 7 2 4F 4 F RT A21EA E15NE 2007091200028 20070912 00028 NE 2007 9 12 CA070813001 2 20070727 G 8520 27056CA1 PISTON DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE ENGINE CRACKED W O OTHER K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA (CAN) THE PILOT MADE A PRECAUTIONARY LANDING WHEN HE NOTICED OIL DROPS ON THE WINDSHIELD AND SAW SOME SMOKE COMING OUT F ROM THE REAR OF THE COWLING. THE ENGINE WAS INSPECTED TO DETERMINE THE CAUSE OF THE OIL LEAK. A DIFFERENTIAL COMPRESSION SHOWED THAT THE NR 2 CYLINDER WAS FLAT. THE CYLINDER ASSEMBLY WAS REMOVED AND REVEALED THAT THE PISTON WAS CRACKED FROM HALFWAY ACROSS THE TOP, DOWN TO THE PISTON PIN HOLE AND THAT THERE WAS ALSO A .3750 INCH RAGGED HOLE THROUGH THE PISTON ON THE TOP EDGE OF IT ALLOWING THE PRESSURIZATION OF THE CRANKCASE AND PUSHING OIL OUT THE FRONT CASE AROUND THE PROPEL LER SHAFT. A COMPLETE CYLINDER AND PISTON ASSEMBLY WERE INSTALLED. THE PART IS AVAILABLE IF REQUESTED. (TC NR 200708130 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2007091200029 20070912 00029 NM 2007 9 12 CA070813002 1 20070730 G 3411 PITOT TUBE BOEING 727 727223 1384074 NM PWA JT8 JT8D15A 52051 NE BLOCKED W C ABORTED TAKEOFF P NO WARNING INDICATION TO TAKEOFF 1 CA (CAN) THE AIRCRAFT BEGAN TO DEPART ON THE TAKE-OFF ROLL WHEN THE FLIGHT CREW OBSERVED THAT THE CAPTAINS AIRSPEED INDICAT ION HAD FAILED. THE TAKE-OFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE GATE WITH NO ADDITIONAL PROBLEMS. UPON INSPECT ION OF THE CAPTAINS PITOT-TUBE A PARTIAL BLOCKAGE WAS NOTICED. AN INSECT AND SOME DEBRIS WAS REMOVED FROM THE PITOT-TUBE AND A LEAK TEST WAS CARRIED OUT ON THE CAPTAINS PITOT-STATIC SYSTEM, IAW THE AIRPLANE MM, AND NO FAULTS WERE FOUND. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070813002) 2 L 7 3 4F 4 F A3WE E2EA 2007091200030 20070912 00030 SO 2007 9 12 CA070813003 2 20070719 G 8520 0200 PISTON CESSNA 150 150H 2071818 CE CONT O200 O200A 17020 SO NR 2 CYLINDER WORN W K NONE O OTHER IN INSP/MAINT 1 CA 1314 (CAN) TOP RING BROKEN. ALL CYLINDERS REPLACED WITH NEW CYLINDER, PISTONS RINGS VALVES. COMPRESSION TEST AT INSPECTION ON MIN - 60 OVER 80. (TC NR 20070813003) 1 H 7 1 3O 3 O 3A19 E252 2007091200031 20070912 00031 CE 2007 9 12 CA070813004 1 20070615 G 3110 6227876011 DISPLAY BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL COCKPIT LOOSE W O OTHER O OTHER TO TAKEOFF 1 CA (CAN) DURING TAKEOFF ROTATION THE MFD SLID OUT OF ITS RACK. THE DISPLAY WAS LIMITED IN MOVEMENT AFT BY THE F/O. THE UNIT WAS PUSHED BACK INTO PLACE AND THE FLIGHT CONTINUED WITHOUT FURTHER INCIDENT. THE MFD HAD RECENTLY BEEN REPLACED. UPON INVESTIGATION THE LOCKING CLIPS THAT RETAIN THE MFD WERE FOUND IN THE LATCHED POSITION, HOWEVER, THEY HAD FAILED TO ENGA GE THE RACK. THE MFD IS FLUSH ROUTED. THAT IS TO SAY ONCE INSTALLED THERE IS LITTLE TO NO EDGE UPON WHICH TO PULL THE UN IT IN ORDER TO CHECK ITS SECURITY. NORMAL OPERATION OF THE LOCKING FEATURE IS FOR THE LOCKING TAB TO ROTATE DUE TO THREA D FRICTION IN A CLOCKWISE MOTION AS THE LOCKING SCREW IS TURNED. WHEN THIS LOCK FAILS, IT IS NORMALLY DUE TO MISALIGNMEN 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 20081104 2008 11 4 CA070813005 4 20070803 G 3420 LUN1241E8G8R INDICATOR GROB 120 G120A 1660208 EU LYC O540 AEIO540D4D5 EA HARTZL HCC3Y HCC3YR GL ATTITUDE UNRELIABLE W O OTHER N FALSE WARNING CR CRUISE 1 CA 225 120 (CAN) MFG INSTALLED MICROTECHNA ELECTRIC ATTITUDE INDICATORS IN A FLEET OF 9 AIRCRAFT USED FOR FLIGHT TRAINING. AFTER 18 MONTHS, ONE ORIGINAL ATTITUDE INDICATOR IS STILL FUNCTIONING AFTER 500 HOURS (9) INSTRUMENTS AVERAGED 225 HOURS BEFORE FAILING THE FIRST TIME. (6) HAVE FAILED WITH AN AVERAGE OF 120 HOURS TSO. (3) AIRCRAFT HAVE BEEN GROUNDED WAITING FOR RE PLACEMENT INTSTRUMENTS. 1 L 7 1 3O 3 O RT A49CE 1E4 5 C P25EA 2007091200032 20070912 00032 SW 2007 9 12 CA070814002 1 20070710 G 6210 206015001107 BLADE BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL MAIN ROTOR DAMAGED W E ENGINE SHUTDOWN C F.O.D. LD LANDING 1 CA 3143 (CAN) UPON LANDING IN A BRUSH AREA, THE PILOT LOWERED THE COLLECTIVE, WHICH IN TURN RAISED (2) TREES THAT WERE SITUATED ON THE LEFT AND THEN HIT THE ROTOR DISK. THE PILOT THEN DISPLACED THE AIRCRAFT TO THE RT. AN ENGINE SHUTDOWN WAS PERFOR MED AND VISUAL INSPECTION CARRIED OUT. THE ROTOR RPM DID NOT DECREASE UPON IMPACT WITH THE TREES, ONLY A COLLISION SOUN D WAS NOTED. PRIOR TO ENGINE SHUTDOWN, ALL ENGINE PARAMETERS WERE NORMAL. THE VISUAL INSPECTION REVEALED THAT THE BLADE WEIGHTS WERE MISSING AT THE BLADE TIPS (3.5 - 4 INCHES). (TC NR 20070814002) 1 G 7 1 3U 3 U H2SW E4CE 2007091200033 20070912 00033 SO 2007 9 12 CA070814003 1 20070707 G 3230 487312 SPRING PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YR2 GL DOWNLOCK HOOK BROKEN W E L ENGINE SHUTDOWN ABORTED APPROACH O OTHER AP APPROACH 1 CA (CAN) RT LANDING GEAR DOWN LOCK SPRING (P/N 487-312) BROKE AND LODGED ITSELF BETWEEN THE HOOK AND THE LOCK OF THE UPLOCK BOX. THE GEAR COULD NOT MOVE AND THEN THE GEAR LIGHT DID NOT COME ON. (TC NR 20070814003) 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2007091200034 20070912 00034 SO 2007 9 12 CA070814004 1 20070718 G 2910 460635 BOWL PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL HYD FILTER LEAKING W O OTHER K FLUID LOSS CR CRUISE 1 CA (CAN) THE RT POWERPACK FILTER BOWL HAD A HYDRAULIC LEAK IN FLIGHT, THE POWERPACK WAS PARTIALLY EMPTY. THE LANDING GEAR W AS MANUALLY DESCENDED AND THE PILOT DECLARED AN EMERGENCY. MECHANIC REPLACED FILTER ASSY (460635) WITH O-RING (MS 2877 8-16) THE POWER PACK WAS SERVICED, GEAR SWING CARRIED OUT, LEAK CHECKED SERVICEABLE. (TC NR 20070814004) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007091200035 20070912 00035 2007 9 12 CA070814005 1 20070812 G 7810 89P11985 CLAMP WRIGHT R1820 982C9HE2 67020 EA HAMSTD 43D 43D51 NE EXHAUST PIPE BROKEN W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA PC10184C (CAN) AIRCRAFT WAS ENROUTE TO A FIRE, DURING CRUISE, THE NR 2 ENGINE FIRE WARNING SYSTEM ACTIVATED. THE ENGINE POWER WAS REDUCED AND THE FIRE WARNING WENT OUT. WHEN POWER WAS RE-APPLIED THE FIRE WARNING CAME ON AGAIN. THE RETARDANT LOAD WAS JETTISONED AND THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION BY MAINTENANCE CREW, AN EXHAUST CLAMP HAD BROKEN, ALLO WING THE EXHAUST STACK TO SEPARATE FROM THE CYLINDER CAUSING A FALSE FIRE WARNING INDICATION. A SECOND EXHAUST CLAMP WAS FOUND BROKEN ON THE NR 1 ENGINE WHICH HAD ALSO CAUSED A FIRE WARNING. ALL REMAINING AIRCRAFT IN THE FLEET WILL BE INSPE CTED FOR EXHAUST CLAMP CONDITION. (TC NR 20070814005) 4 R E259 6 C P8879 2007091200036 20070912 00036 GL 2007 9 12 CA070814006 1 20070810 G 5511 C2TP160A BRACKET DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HARTZL HCB3R HCB3R304 GL HORIZONTAL STAB CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION ON FRONT TAILPLANE PICKUP BRACKET, FOUND AT INSPECTION WHILE DOING CF-1991-42R1. (TC NR 20070814006) 1 H 7 1 3R 3 R RC A806 5E1 5 C P28EA 2007091200037 20070912 00037 CE 2007 9 12 CA070814007 1 20070813 G 7810 3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 390 (CAN) DURING ROUTINE MAINTENANCE ON THE ENGINE, AN INSPECTION OF THE POWER TURBINE BLADES INDICATED LARGE CRACKS AND MIS SING SECTIONS OF THE EXHAUST DUCT. THIS ENGINE WAS INSTALLED ON APRIL 02, 2007 AFTER OVERHAUL. THE CAUSE OF THE CRACKS A RE UNDER INVESTIGATION. (TC NR 20070814007) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007091200038 20070912 00038 GL 2007 9 12 CA070814008 1 20070809 G 3250 C2UT473 POST DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE TILLER SHEARED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) TILLER POST FOUND SHEARED AT TOP, UNDER CABLE ATTACH FLANGE. (TC NR 20070814008) 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2007091200039 20070912 00039 CE 2007 9 12 CA070814009 1 20070813 G 2560 SEAT BELT CESSNA 172 172K 2072430 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL COCKPIT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SEAT BELT LOOPS THAT SECURE THE FRONT SEAT LAP BELTS TO THE SEAT FAILED. THIS ALLOWED THE SEAT BELT, WHILE BEING SECURED, TO LOOP OVER THE SEAT BACK ADJUSTMENT LEVER. WHEN THE PILOT ADJUSTED HIS SEAT PRIOR TO TAXI, THE SEAT BACK ADJ UST LEVER WAS ACTIVATED AND THE SEAT BACK RECLINED TO ITS FULL BACK POSITION. (TC NR 20070814009) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007091200040 20070912 00040 NE 2007 9 12 CA070814010 2 20070807 G 7200 ENGINE SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE MALFUNCTIONED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION HO HOVERING 1 CA 295178 (CAN) ROTORCRAFT WAS LOGGING AT THE TIME OF THE ENGINE SHUTDOWN. THE AIRCRAFT WAS HOVERING ABOVE A LOG GETTING READY TO PULL THE LOG FROM THE SETTING. NR 1 ENGINE INDICATIONS DROPPED OFF (IE OIL PRESSURE, FUEL PRESSURE, NG). THE AIRCRAFT RELEASED ITS LONGLINE AND BEGAN AN UNSCHEDULED LANDING. THE AIRCRAFT LANDED WITHOUT INCIDENT AND THE ENGINE WAS REMOVED FOR INSPECTION. (TC NR 20070814010) 2 G 7 2 4U 4 U 1H15 1E3 2007110200004 20071102 00004 SO 2007 11 2 CA070815001 1 20070813 G 3230 487495 SPRING PIPER 7872322 PIPER PA44 PA44180 7104402 SO LYC O360 O360A1H 41514 EA HARTZL HCC2Y HCC2YR2 GL DOWNLOCK SPRING BROKEN W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA (CAN) ON A LANDING APPROACH, THE PILOT NOTICED THAT THE LT (GREEN) GEAR DOWN AND LOCKED LIGHT WAS NOT ILLUMINATED. AS TH E AIRCRAFT WAS SLOWED DOWN ON FINAL THE (GEAR) UNSAFE LIGHT CAME ON. THE PILOTS ELECTED TO GO AROUND AND INFORMED FLIGHT SERVICES ABOUT THEIR CIRCUMSTANCES AND THE LOCAL FIRE DEPARTMENT WAS INFORMED ALSO. MAINTENANCE WAS NOTIFIED AND SPOKE DIRECTLY TO THE PILOTS. IT WAS LEARNED THAT AN EMERGENCY EXTENSION WAS CARRIED OUT AND THE RESULT WAS THE SAME. IT WAS A LSO ESTABLISHED THAT THE LT MAIN GEAR WAS GOING FULL TRAVEL AND JUST NOT LOCKING DOWN. IT WAS DECIDED TO HAVE THE EMERGE NCY EXTENSION KNOB PUSHED BACK INTO ITS NORMAL POSITION AND THE GEAR RETRACTED AND EXTENDED HYDRAULICALLY. IT WAS AT THI 1 L 7 2 3O 3 O A19S0 E286 5 C P920 2007091200041 20070912 00041 GL 2007 9 12 CA070815002 3 20070813 G 6110 B1843 SEAL HARTZL HCB3TN3 HARTZL HCB3T HCB3TN3 GL PROPELLER MISSING W K NONE O OTHER IN INSP/MAINT 1 CA BUA24432 (CAN) PROPELLER WAS RECEIVED BY SHOP BECAUSE OF GREASE LEAKAGE AROUND BLADE CLAMPS. UPON DISASSEMBLY TO PERFORM REPAIRS IT WAS NOTICED THAT THE DUST SEAL WAS MISSING FROM THE PROPELLER PISTON ASSEMBLY. SINCE THIS ITEM CAN`T PHYSICALLY FALL OUT IT IS ASSUMED THAT IT WAS INADVERTENTLY LEFT OUT AT A PREVIOUS REPAIR. (TC NR 20070815002) 6 C P15EA 2007091700045 20070917 00045 EA 2007 9 17 CA070815003 2 20070809 G 7200 ENGINE BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL DAMAGED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION NR NOT REPORTED 1 CA 12676 3595 PCE51741 (CAN) DURING TAKEOFF ROLL, (JUST PRIOR TO VR) A LOUD POP WAS HEARD. THE AC CONTINUED WITH THE TAKEOFF AND ONCE AIRBORNE THE CREW DIVERTED BACK TO DEPARTURE AIRPORT FOR LANDING. AS THEY WERE COMING AROUND, THE PROP RPM, TORQUE, AND FUEL FLOW ON THE RT ENGINE BEGAN TO FLUCTUATE BUT REMAINED WITHIN LIMITS. POWER WAS REDUCED AND AN UNEVENTFUL LANDING CARRIED OUT . FLIGHT CREW CONTACTED MAINTENANCE AND WERE INSTRUCTED TO CARRY OUT A GROUND RUN. THE ENGINES WERE RUN UP AND ALL PARAM ETERS WERE WITHIN LIMITS, WHEN POWER WAS ADVANCED BEYOND 85 PERCENT NG ON THE RT ENGINE, TORQUE AND FUEL FLOW BEGAN TO F LUCTUATE. AS THIS SEEMED TO INDICATE IT WAS A FUEL SCHEDULING PROBLEM, IT WAS DECIDED, IN CONSULTATION BETWEEN THE FLIGH 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2007091200042 20070912 00042 2007 9 12 CA070816001 3 20070810 G 6110 CONNECTOR CVAC 440 440 2422902 WP ALLSN 501D 501D13D 03004 GL ALLSN STC STCA6441 OIL PROP FILLER UNSECURE W A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 CA (CAN) ENGINE NR 1 RPM UNSTABLE, REDUCED RPM TO 13,600. AIRCRAFT DIVERTED TO NEAREST AIRPORT. ENGINE WAS SHUTDOWN IN FIN AL APPROACH, DUE TO RPM REDUCTION TO 13500 RPM. MAINTENANCE WAS SENT ON SITE AND FOUND THAT OIL PROPELLER FILLER PLUG W AS NOT SECURED PROPERLY AND ONE GALLON OF OIL HAD LEAKED OUT. PROPELLER REFILLED AND ENGINE RUN C/O (SERVICEABLE). AIR CRAFT RETURN TO SERVICE. (TC NR 20070816001) 2 L 7 2 4R 4 T 6A6 E282 6 C P898 2007091200043 20070912 00043 EA 2007 9 12 CA070816002 1 20070816 G 2730 215T9250446 CONTROL CABLE CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE ELEVATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A VISUAL INSPECTION ( 50 HRS), A TECH FOUND AN ELEVATOR CABLE BADLY WORN, ALMOST CUT AT FUS STN 726 ZONE 3 10 FRONT OF THE PULLEY (TC NR 20070816002) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2007091200044 20070912 00044 EA 2007 9 12 CA070816003 1 20070815 G 2721 6018610017 POTENTIOMETER CNDAIR CL604 CL604 1900301 EA RUDDER TAB CONTR INOPERATIVE W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA 7 (CAN) ON TAKEOFF ROLL, AS THE AC WAS ACCELERATING AND PRIOR TO 80 KTS. FULL RUDDER INPUT WAS APPLIED TO MAINTAIN CENTERL INE. CENTERLINE WAS UNABLE TO BE MAINTAINED AND THE TAKEOFF WAS ABORTED. THE AIRCRAFT TAXIED WITHOUT INCIDENT BACK TO BA SE. AIRCRAFT IS OPERATED BY MFG. MARKING N605JP (TC NR 20070816003) 2 L 7 2 4F RT A21EA 2008012900019 20080129 00019 2008 1 29 CA070817001 4 20070718 G 3197 E321A CONNECTOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL CONTROL PANEL BURNED W H D DEACTIVATE SYST/CIRCUITS RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 15304 317952033 (CAN) SMOKE WAS REPORTED FROM THE OVERHEAD SWITCH PANEL WHEN TAXIING FOR TAKEOFF. THE CONNECTOR BEHIND THE PANEL WAS FOU ND IN A BURNED CONDITION. THE CONNECTOR WAS REPLACED BY REMOVING THE BURNED WIRING AND SPLICING IN A NEW CONNECTOR. (TC NR 20070817001) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007091700047 20070917 00047 NM 2007 9 17 CA070817002 1 20070813 G 5753 85780009011 FLAP TRACK DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE RT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 40546 (CAN) EXCESSIVE CORROSION FOUND ON FLAP TRACKS NR 4 AND NR 5 ON BOTH LT AND RT WINGS DURING 60K REPLACEMENT OF FLAP TRAC KS. SUPPORT BRACKETS REMOVED FOR TRANSFER TO NEW BEAMS, CORROSION FOUND IN RECESSES OF TRACKS BEHIND BRACKETS. LT NR 4 T RACK FOUND FULL OF WATER, BOTH SIDES OF BRACKET APPEARS TO BE NEWER BRACKET. RUST STARTING TO FORM BELOW PAINT. NR 4 LT : P/N 85780009-011; NR 4 RT: P/N 85780009-112; NR 5 LT: P/N 85780010-007; NR 5 RT: P/N 85780010-008. RECTIFICATION: F LAP TRACKS REPLACED AS PART OF THE 60K WORK PACKAGE REQUIREMENT. FURTHER INSPECTION OF CORROSION AND CAUSE SHOULD BE CAR RIED OUT. (TC NR 20070817002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008032400418 20080324 00418 GL 2008 3 24 CA070817003 1 20070816 G 3246 8834040 PIN NAMER T6 HARVARDMK4 1922828 GL PWA R1340 R1340* 52016 NE HAMSTD 12D 12D40 NE TAIL WHEEL SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA 4917 (CAN) DURING 50 HOUR INSP, EXCESSIVE ROTATIONAL MOVEMENT WAS NOTED ON THE TAIL WHEEL KNUCKLE (FORK), WITH THE TAIL WHEEL CONTROL LOCK ON. TAIL WHEEL MAST WAS DISMANTLED AND PIN HOLDING THE UPPER AND LOWER EXTENSION PIECES TOGETHER WAS FOUND SHEARED. THIS COULD HAVE RESULTED IN THE LOSS OF THE ENTIRE TAIL WHEEL, OR POTENTIALLY IN THE LOSS OF CONTROL ON THE GR OUND. UNIT WAS REPAIRED AND RETURNED TO SERVICE. THIS PIN COULD HAVE BEEN DAMAGED BY IMPROPER GROUND HANDLING OF THE AIR CRAFT IE: PUSHING AC IN REVERSE WITH THE CONTROL LOCKS OFF. (TC NR 20070817003) 1 L 7 1 3R 3 R EXPA1L71 5E2 5 C P257 2007091200045 20070912 00045 WP 2007 9 12 CA070817005 1 20070816 G 3246 CON1194515 WHEEL GRUMAN TS2 TS2ACALFORST 3951102 WP WRIGHT R1820 982C9HE2 67020 EA HAMSTD 43D 43D51 NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN (A) INSPECTION, A 6 INCH LONG CRACK WAS NOTED ON THE MAIN WHEEL OUTER HALF. THE CRACK WAS RUNNING AROUND THE CIRCUMFERENCE OF THE WHEEL. THE WHEEL ASSEMBLY WAS REMOVED AND A SERVICEABLE WHEEL ASSEMBLY WAS INSTALLED. THE AIRC RAFT WAS RETURNED TO SERVICE. (TC NR 20070817005) 2 H 7 2 4R 4 R A25WE E259 6 C P8879 2007091200046 20070912 00046 WP 2007 9 12 CA070817006 1 20070814 G 2620 MANIFOLD CVAC 340 340CVAC 242270A WP ALLSN 501D 501D13D 03004 GL ALLSN A6441 A6441FN606 GL EXTINGUISHER MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, AT APPROXIMATELY 7000 FEET AND THE RETARDANT SYSTEM DE-ARMED, THE RETARDANT TANK CONTENTS EXITED TH E TANK. THE CREW RETURNED TO BASE. MAINTENANCE TROUBLESHOT THE SYSTEM AND THE HYDRAULIC MANIFOLD FOR THE RETARDANT TANK WAS REPLACED. THE TANK DOOR OVER CENTERS WERE CHECKED. THE RETARDANT TANK SYSTEM WAS FUNCTION CHECKED, THE AIRCRAFT WAS TEST FLOWN AND RETURNED TO SERVICE. (TC NR 20070817006) 2 L 7 2 4R 4 T 6A6 E282 6 C P898 2007091200047 20070912 00047 EA 2007 9 12 CA070817007 1 20070814 G 5280 DOOR CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF34* NE LT MLG MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE LT MAIN GEAR DOOR WAS MISSING AND HAD CAUSED DAMAGE TO THE LT IB FLAP WHEN IT EXITED THE AIRCRAFT. (TC NR 2007 0817007) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022100013 20080221 00013 2008 2 21 CA070819001 4 20070817 G 3421 6224565001 VERTICAL GYRO BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCE4N HCE4N3 NE EFIS FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) PILOT`S EFIS DISPLAYED ATT AND FD FLAGS, CO-PILOT FINISHED FLIGHT. REPLACED GYRO, PROBLEM SOLVED. (TC NR 200708190 01) 1 L 7 2 4T 4 T A24CE E4EA 5 C P10NE 2007091200048 20070912 00048 NM 2007 9 12 CA070820001 1 20070801 G 3231 483023 SEQUENCE VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU RT MLG DOOR INOPERATIVE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, RT GEAR DOOR LIGHT REMAINED ON. LOWERED GEAR, RT MAIN GEAR DID NOT EXTEND. ACCOMPLISHED ALTERNATE GEAR EXTENSION. MAINTENANCE REPLACED RT MLG DOOR SOLENOID SEQUENCING VALVE AND SECONDARY MLG SELECTOR VALVE FITTING. BL EED NR 2 HYD SYSTEM. A/C RETURNED TO SERVICE. (TC NR 20070820001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007091200049 20070912 00049 CE 2007 9 12 CA070821001 1 20070820 G 3233 12810016 HOUSING CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5458 (CAN) 500 HOUR LIQUID PENETRANT INSPECTION IAW MFG SEB 01-2 REVEALED, CRACK AT INDICATED AREA (TC NR 20070821001) 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2007091200050 20070912 00050 NM 2007 9 12 CA070821002 1 20070815 G 2710 82740162101 LINK ASSY BOMBDR DHC8 DHC8402 1390042 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU LT AILERON FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1753 (CAN) WHILE MAINTENANCE WAS DOING A OVERNIGHT CHECK TO THE AIRCRAFT, THEY OBSERVED THE LINK-ASSY AILERON LVDT WAS HANGIN G DOWN. THE ROD LINK HAD BROKEN AT THE AILERON END. (TC NR 20070821002) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007091200051 20070912 00051 EA 2007 9 12 CA070821003 3 20070608 G 6111 76EM8S5060 BLADE SNSNCH 76EM8S5060 PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA SNSNCH 76E 76EM8S5 EA PROPELLER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 16514K (CAN) WELDED PROPELLER, AIRCRAFT IMPORTED, NO LOG FOR FIXED-PITCH PROP. PROP REMOVED FOR 5 YR CORROSION INSPECTION AS A PRECAUTIONARY MEASURE - SINCE PROP WAS ONLY ALODINED, PROP WAS ANODIZED DURING INSPECTION AT HOPE AERO, TIP FOUND STAIN ED AFTER ANODIZING. CONFIRMED WELDING OF PROP BY EDDY CURRENT. (TC NR 20070821003) 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA 2007091200052 20070912 00052 EA 2007 9 12 CA070821004 1 20070821 G 3246 215850026 WHEEL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE NLG DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 140 (CAN) THE (6) DOWEL PINS ON NOSE WHEEL HAS BEEN FOUND PROTRUDED FROM HUB AND THE RETAINING WASHER DEFORMED OR BENDED. (TC NR 20070821004) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2008031900152 20080319 00152 SW 2008 3 19 CA070821005 1 20070820 G 7500 B-NUT BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL BLEED AIR LOOSE W R AUTOROTATION R PARTIAL RPM/PWR LOSS DE DESCENT 1 CA (CAN) THE ROTORCRAFT DEPARTED AT LANDING AREA AT APPROX 4500 FT WITH ALL NORMAL PARAMETERS. AT APPROX 4300 FT THE PILOT NOTICED A DIFFERENCE IN ENGINE NOISE LEVELS. THE DIFFERENCE IN NOISE LEVELS WERE ACCOMPANIED BY ACTIVATION OF THE ENGINE AUTO RE-LIGHT SYS AND A DROP IN NG TO GROUND IDLE. THE PILOT ELECTED TO ENTER INTO AUTOROTATION AND LANDED WITH NO DAMA GE TO THE AC. THE CAUSE WAS DETERMINED TO BE AN AIR LEAK TO THE GOVERNOR FROM A LOOSE B-NUT. (TC NR 20070821005) 1 G 7 1 3U 3 U H2SW E4CE 2008030600133 20080306 00133 CE 2008 3 6 CA070821006 1 20070820 G 7110 101910016651 INTAKE BEECH BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL COWL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) COWL ASSY LOWER FWD P/N 101-910024-1 WAS ONCE MODIFIED. (TC NR 20070821006) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007091200053 20070912 00053 EA 2007 9 12 CA070822001 1 20070822 G 2810 215640026 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE NR 5 LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FUEL LEAK ON CELL, RT, NR 5. DROPS 9963 (TC NR 20070822001) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2007091200054 20070912 00054 EA 2007 9 12 CA070822002 1 20070822 G 2810 215640011 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 834 (CAN) FUEL LEAKING FROM PATCH ON BOTTOM SURFACE OF CELL. A/C HOURS 1889 CYCLES 1142 DROPS 9727 (TC NR 20070822002) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2007110200005 20071102 00005 NM 2007 11 2 CA070822003 1 20070805 G 2910 AS11510K0324 HOSE BOEING 767 767306 1385148 NM HYDRAULIC SYS DAMAGED W A UNSCHED LANDING J F J WARNING INDICATION FLT CONT AFFECTED WARNING INDICATION CR CRUISE 1 CA (CAN) AIRCRAFT WAS ONE HOUR OUT OF DEPARTURE PLACE AND ON ROUTE TO ENGLAND WHEN EICAS ILLUMINATED WITH THE FOLLOWING MES SAGES: C HYD SYS FLUID LOSS - C HYD SYS PRESS AIRCRAFT DIVERTED TO NEAREST AIRPORT WHERE IT WAS FOUND THAT THE LT MAIN L ANDING GEAR TRUCK TILT ACTUATOR RETURN FLEX HOSE WAS DAMAGED. THE FOLLOWING MAINTENANCE ACTIONS WERE PERFORMED: - DAMAGE D HYDRAULIC HOSE REPLACED (TC NR 20070822003) 2 L 7 2 4F RT A1NM 2007091200055 20070912 00055 NE 2007 9 12 CA070822004 2 20070822 G 7210 311294501 CASE PWA PT6 PT6A67D NE RGB CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS PART WAS DECLARED UNSERVICEABLE DURING A TENTATIVE REPAIR AT MFG, HOWEVER, IT WAS REINSTALLED INTO THE ENGIN E BY MISTAKE AND DELIVERED TO THE CUSTOMER. THE PART WAS CORRODED ON THE EXTERNAL WALL AND FURTHER PROGRESSION OF THIS DAMAGE COULD HAVE RESULTED IN A SUBSTANTIAL OIL LEAK FROM THE REDUCTION GEARBOX. MFG DISCOVERED ITS MISTAKE PRIOR ENGIN E USE AND THE ENGINE WAS IMMEDIATELY RECALLED FOR PART REPLACEMENT. MFG IS CURRENTLY EXAMINING THE MAINTENANCE RECORDS OF SPECIFIC ENGINES TO MAKE SURE THAT A SIMILAR MISTAKE DID NOT HAPPEN ELSEWHERE. (TC NR 20070822004) 4 T E26NE 2007110200006 20071102 00006 CE 2007 11 2 CA070822005 1 20070816 G 5797 65280042 WIRE HARNESS CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE WING CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 9022 (CAN) WHILE DOING SKIN REPAIRS ON RT WING WE FOUND WIRES CHAFED IN THE FLAP BAY AREA WHERE THE BUNDLE WAS TY WRAPPED TO A NYLON ANCHOR. THE TY WRAP WAS ONLY PUT THROUGH ON LEG OF THE ANCHOR NOT BOTH. THE CONDITION WAS FOUND AT 4 ANCHORS. TH E LT WING WAS INSPECTED. THE WIRE BUNDLE THERE WAS TY WRAPPED THROUGH BOTH LEGS OF THE ANCHOR AND NO DEFECT WAS FOUND. T HE P/N OF THE ANCHOR IS S1471-4. THE TY WRAPS ANCHORING THE WIRE BUNDLES SHOULD BE REMOVED TO REALLY INSPECT FOR DAMAGE AS THE AREA IS DIFFICULT TO INSPECT AND THE DAMAGE IS AT THE BOTTOM OF THE WIRE BUNDLE. (TC NR 20070822005) 2 L 7 2 4F 4 F RT A22CE E25EA 2008030600134 20080306 00134 SW 2008 3 6 CA070822006 1 20070820 G 6320 206040004 TRANSMISSION BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL MAIN ROTOR MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 6670 2778 (CAN) SHORTLY AFTER TAKEOFF THE PILOT RECEIVED A CHIP LIGHT ON THE TRANSMISSION. LANDED THE AIRCRAFT. METAL WAS DISCOV ERED ON THE SENSOR. THE AIRCRAFT WAS REMOVED FROM SERVICE AND THE TRANSMISSION WAS REPLACED WITH A SERVICEABLE UNIT. AIR CRAFT RETURNED TO SERVICE (TC NR 20070822006) 1 G 7 1 3U 3 U H2SW E1GL 2007110200007 20071102 00007 CE 2007 11 2 CA070822007 1 20070816 G 8011 87818 RELAY CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA STARTER BURNED W H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) STARTER RELAY STUCK CLOSED AFTER ENGINE START. SUBSEQUENT DAMAGE WAS NOTED ON STARTER AS WELL. (TC NR 20070822007) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P9045 2008030600136 20080306 00136 SO 2008 3 6 CA070822008 1 20070821 G 2912 AN62341 FILTER HOUSING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL HYD SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) ON THE 21ST OF AUGUST 2007, MAINTENANCE RECEIVED A CALL THAT AN AC HAD A HYDR FLUID LEAK. A RESCUE MISSION WAS DIS PATCHED TO THE AC. UPON INVESTIGATION ONCE MAINT ARRIVED AT LOCATION IT WAS FOUND THAT THE NR 1 ENG HYDR FILTER HSG WAS LEAKING. AFTER DISASSEMBLY, IT WAS NOTED THAT THERE WAS A CRACK IN THE TREADS RUNNING .5 AROUND THE DIAMETER. THE HYDR F ILTER WAS ISOLATED FROM THE SYS, THE SYS TOPPED UP WITH FLUID, AND A LEAK RUN PERFORMED BEFORE RETURNING TO DEPARTURE WI THOUT PASSENGERS. IT HAS BEEN DETERMINED THROUGH AN INVESTIGATION THAT THE FAILURE WAS A DIRECT RESULT OF THE USAGE OF T HE WRONG PN O-RING. THE O-RING THAT WAS FOUND INSTALLED ON THE FILTER HOUSING IS OF THE SAME OUTER DIAMETER AS THE PROPE 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007091200056 20070912 00056 EU 2007 9 12 CA070823001 1 20070816 G 2750 59128437 SENSOR EMB ERJ190 ERJ190100IGW 3260408 EU GE CF34 CF3410E6 30015 NE TE FLAP DEFECTIVE W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH, FLIGHT EXPERIENCED A FLAP FAIL MESSAGE. SLAT WENT TO 3 GREEN, FLAP INDICATION BECAME YELLOW, AND SHO WED BELOW THE 2 MARKER. FLIGHT DID GO AROUND, AND DECLARED EMERGENCY WITH TOWER. CFR WAS AVAILABLE, AND FLIGHT LANDED AT HIGHER THAN NORMAL SPEED. INFLIGHT PERFORMED ABNORMAL LANDING PROCEDURE AFTER THEY WERE BRIEFED BY FLIGHT CREW THAT THEY WERE GOING TO LAND AT HIGHER THAN NORMAL SPEED. PRIOR TO TAXI, CFR INSPECTED AIRCRAFT. ON INVESTIGATION, FOUND RT OB FLAP SKEW SENSOR AT FAULT, SENSOR REPLACED IAW AMM 27-53-06-400. MOC REQUESTED THAT NR 4 AND NR 3 RT FLAP ACTUATORS BE REPLACED AS WELL. (TC NR 20070823001) 2 L 7 2 4F 4 F RT A57NM E00070EN 2008030600137 20080306 00137 2008 3 6 CA070823002 4 20070821 G 2564 JETTISON SYSTEM SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL2S2 60036 NE LIFE RAFT FAILED W C ABORTED TAKEOFF O OTHER TX TAXI/GRND HDL 1 CA (CAN) EXTERNAL LIFERAFT JETTISON SYS FAILED TO OPERATE. WHEN LEVER ACTUATED, CABLE BROKE AND PULLEY BRACKET ON LT SIDE O F CENTER PEDESTAL DETACHED. (2) BRACKETS UNDER FLOOR FOUND TO BE LOCATED INCORRECTLY. INSTALLATION WAS CARRIED OUT IAW ASI-500-100 REV.G. (TC NR 20070823002) 1 G 7 2 3U 4 U NC H1NE E00054EN 2007110200008 20071102 00008 CE 2007 11 2 CA070823003 1 20070821 G 2510 SPL19251 LOCK CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA MCAULY 3D36C B3D36C432 GL SEAT BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 366 (CAN) RT SEAT LOCKING PIN SHEATH FOUND BROKEN AT THE SEAT LEG ATTACH POINT. THE LOCKING PIN WOULD RETRACT BUT NOT ENGAGE ON THAT SIDE. THE SEAT LOCK MECHANISM COMPRISES OF A SPRING LOADED HANDLE , WITH TWO CABLES ATTACHED AND TWO SHEATHS SE CURED TO THE SEAT LEG WHICH SURROUND THE LOCKING PINS. PART REPLACED. (TC NR 20070823003) 1 H 7 1 3O 3 O RT A4CE E14EA 5 C P58GL 2007091700049 20070917 00049 SW 2007 9 17 CA070823004 1 20070821 G 6310 M2742630150 RETAINER BELL 407 407 1182206 SW FREEWHEEL UNIT MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 CA A6724 (CAN) UPON QUALIFYING A FREEWHEELING UNIT, IT WAS DISCOVERED THAT THE WRONG RETAINING RINGS WERE USED IN (2) PLACES. SU SPECT RETAINING RINGS M27642/3-0152C WERE INSTALLED IN ASSEMBLIES INSTEAD OF M27426/3-0150C RETAINING RINGS. THIS OCCUR RED DURING APRIL 07. (TC NR 20070823004) 1 G 7 1 3U O H2SW 2007091700050 20070917 00050 NE 2007 9 17 CA070823005 2 20070819 G 7261 IMPELLER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ENGINE LEAKING W E ENGINE SHUTDOWN K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TX TAXI/GRND HDL 1 CA 10758 10758 TM120329 (CAN) ON TAXI, THE F/O NOTICED SMOKE IN THE FLIGHT DECK AND F/A CONFIRMED HAZE IN CABIN. BLEEDS WERE TURNED OFF. AS AIRC RAFT TURNED ONTO GATE LAV SMOKE DETECTOR WENT OFF. CREW STOPPED 10 FEET SHORT OF THE GATE SHUT DOWN AIRCRAFT AND DEPLANE D PASSENGERS. IT WAS NOT A RAPID DEPLANEMENT AS THERE WAS NO PANIC AMONG PASSENGERS BUT CONCERN AS THEY COULD SEE SMOK E. FIRE FIGHTERS BOARDED AIRCRAFT AFTER PASSENGERS DEPLANED AND REPORTED NO VISIBLE SMOKE OR OIL SMELL. A LITTLE LATER M AINTENANCE WENT ON BOARD AND NO SMOKE ODOR WAS EVIDENT. A VERY SLIGHT OIL/HYDRAULIC ODOR WAS NOTICED AROUND THE CENTER C ABIN AREA. MAINTENANCE TROUBLE SHOOTING CONSISTED OF A SERIES OF ENGINE RUNS WHICH ISOLATED PROBLEM TO NR 2 ENGINE. REPL 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007091700051 20070917 00051 GL 2007 9 17 CA070823006 1 20070713 G 5100 2224121400 BRACKET DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA ALTERNATOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 95 (CAN) ALTERNATOR BRACKET IS BREAKING ON THESE AIRCRAFT AROUND 100 HOURS T/S. THE FACTORY HAS RUN OUT OF STOCK AND IS RO BBING THE PART FROM NEW PRODUCTION AIRCRAFT. SUGGEST RE ENGINEERING AND POSSIBLE AD. (TC NR 20070823006) 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2007110200009 20071102 00009 CE 2007 11 2 CA070823007 1 20070821 G 2822 A10055B PUMP CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA MCAULY 3D36C B3D36C432 GL FUEL BOOST LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 366 (CAN) FUEL DYE RESIDUE NOTED ON ELECTRIC FUEL BOOST PUMP HOUSING, FOUND TO BE FROM AN AUX PORT PLUG. PLUG RESEALED, FURT HER CHECK FOR SEEPING SATISFACTORY. (TC NR 20070823007) 1 H 7 1 3O 3 O RT A4CE E14EA 5 C P58GL 2008030600138 20080306 00138 SW 2008 3 6 CA070823008 1 20070818 G 2810 EA4703587 TANK BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL FUEL SYSTEM FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TANK UNIT WAS INSTALLED FOR AN INACCURATE FUEL INDICATION. AFTER INSTALLATION OF THE REPAIRED TANK UNIT WE APPLIED GROUND POWER FOR THE FUEL CALIBRATION AND FOUND THE GAUGE TO BE INOPERATIVE. AFTER TROUBLESHOOTING IT WAS DETERMINED TH AT THE TANK UNIT WAS FAULTY. THE TANK UNIT WAS REMOVED AND A RESISTANCE CHECK WAS PERFORMED IAW THE MM, THE TANK UNIT F AILED THE TEST. (TC NR 20070823008) 1 G 7 1 3U 3 U H2SW E4CE 2007091700052 20070917 00052 CE 2007 9 17 CA070823009 1 20070724 G 7931 IO360G ENGINE CESSNA 337 337G 2075730 CE CONT O360 IO360G 17025 SO MCAULY 2AF34C D2AF34C306 GL FAILED W A E UNSCHED LANDING ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 1990 (CAN) REAR ENGINE EXPERIENCED A LOSS OF OIL PRESSURE DURING FLIGHT. ENGINE WAS SHUT DOWN AND AIRCRAFT RETURNED TO BASE. ENGINE WAS REPLACED. UNABLE TO DETERMINE OIL PRESSURE PROBLEM WITH FAILED OIL PRESSURE ON ENGINE. ENGINE WAS SHIPPED TO ENGINE SHOP. (TC NR 20070823009) 1 H 7 2 3O 3 O A6CE E1CE 5 C P5EA 2007110200010 20071102 00010 CE 2007 11 2 CA070823010 1 20070725 G 5520 07341102 TORQUE TUBE CESSNA CESSNA 182 182G 2072716 CE CONT O470 O470R 17026 SO MCAULY 2A36C 2A36C29 GL ELEVATOR LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 3830 (CAN) MINOR PLAY (UP AND DOWN) ON THE RT ELEVATOR CAUSE BY LOOSE RIVETS ON THE TORQUE TUBE (TC NR 20070823010) 1 H 7 1 3O 3 O NT 3A13 E273 5 C P880 2007091700053 20070917 00053 NM 2007 9 17 CA070823011 1 20070822 G 5610 001A561A0000218 WINDOW DORNER DO32 DO328100 2996000 NM COCKPIT CRACKED W B EMER. DESCENT O OTHER CR CRUISE 1 CA 6521 6088 (CAN) ENROUTE AT FLIGHT LEVEL 27,000 THE PILOTS LT SIDE WINDOW CRACKED WITH A LOUD POP. INITIATED DESCENT TO 8,000 FEET AND MANUALLY RAISED CABIN PRESSURE TO ZERO DIFFERENTIAL PRESSURE AND CONTINUED. ADVISED COMPANY OF THE FAILURE PRIOR T O ARRIVAL. AN ENGINEER INSPECTED THE WINDOW AND FOUND IT WITHIN LIMITS FOR A FERRY FLIGHT. AUGUST 23,2007 FOR REPLACEM ENT OF THE WINDOW. (TC NR 20070823011) 2 H 7 2 4T RT A45NM 2007110200011 20071102 00011 EA 2007 11 2 CA070823012 1 20070821 G 2612 14034012 SWITCH CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE RT FIRE DETECT FAILED W O OTHER N FALSE WARNING TX TAXI/GRND HDL 1 CA 9156 9156 (CAN) DURING LANDING ROLLOUT CREW RECEIVED MOMENTARY ILLUMINATION OF (BOTTLE ARMED PUSH TO DISCH) FOR RT ENG. CREW WAS C HECKING FOR TRAFFIC AS HAD BEEN CLEARED ACROSS ANOTHER RUNWAY. WHEN ACROSS THIS RUNWAY NOTICED RED (R ENG OIL PX) AND RT ENG N1 AND N2 (ZERO). CREW CARRIED OUT RT ENG SHUTDOWN PROCEDURE. MAINTENANCE INSPECTION FOUND RT ENG FIRE PUSH SWITCH FAULTY. SWITCH REPLACED, FUNCTION CHECKS CARRIED OUT, AIRCRAFT RETURNED TO SERVICE. NOTE: ACTIVATION OF ENG FIRE PUSH SW ITCH WILL SHUT OFF FUEL/HYD CAUSING ENGINE TO SHUT DOWN. (TC NR 20070823012) 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600139 20080306 00139 SO 2008 3 6 CA070823013 1 20070810 G 3297 CONNECTOR PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6D 42305 EA HARTZL HCC2Y HCC2YR2 GL DOWNLOCK BROKEN W O OTHER N FALSE WARNING DE DESCENT 1 CA (CAN) WIRE FOUND BROKEN ON DOWNLIMIT SWITCH CONNECTOR. (TC NR 20070823013) 1 L 7 2 3O 3 O A19S0 E286 5 C P920 2007110200012 20071102 00012 EU 2007 11 2 CA070824001 1 20070803 G 2752 1703911 ACTUATOR EMB ERJ190 ERJ190100IGW 3260408 EU GE CF34 CF34* NE TE FLAPS MALFUNCTIONED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH, SLAT FAIL AND COUNTLESS MESSAGES ON EICAS ON INITIAL SELECTION. SLAT 0, FLAP 1. FOUND LT NR 4 ACTUATO R RT NR 4 ACTUATOR AND RT NR 7 ACTUATOR TRIPPED. ACTUATORS CHANGED IAW AMM 27-81-01. OPERATION CHK C/O, FOUND SYS SERVI CEABLE. OTHER P/NS AFFECTED: 1703909, S/N 216 1703911, S/N 229 (TC NR 20070824001) 2 L 7 2 4F 4 F RT A57NM E15NE 2007091700054 20070917 00054 EA 2007 9 17 CA070824002 1 20070819 G 3246 6A07116002 CYLINDER DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL FLOAT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A WHEELS DOWN LANDING OF AN AMPHIBIOUS EQUIPPED AIRCRAFT, THE LANDING GEAR COLLAPSED. UPON INSPECTION, CO RROSION WAS NOTED UNDER THE (ZAP STRAPS), WHICH WERE INSTALLED BY THE MANUFACTURER, ON BOTH LT AND RT NOSE GEAR ACTUATIN G CYLINDERS. ON THE LT CYLINDER, THE CORROSION WAS EXTENSIVE ENOUGH THAT HYDRAULIC FLUID WAS LEAKING THROUGH A PIN HOLE THAT HAD FORMED. (TC NR 20070824002) 1 H 7 1 3R 4 T A815 E4EA 6 C P15EA 2007110200013 20071102 00013 EA 2007 11 2 CA070824003 1 20070824 G 2810 215640751 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LEAK FROM BOTTOM SURFACE ON FUEL CELL NR 8 RT. A/C HOURS 3381 CYCLES 2237. DROPS 15187 MFG. (TC NR 200708240 03) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2008030600141 20080306 00141 CE 2008 3 6 CA070824004 1 20070810 G 5520 115610010325 TORQUE TUBE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL ELEVATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 16 (CAN) ON INSPECTION, THE ELEVATOR WAS FOUND TO HAVE .75 INCH PLAY AT T/E. THE ELEVATOR WAS REMOVED AN THE TORQUE TUBE WA S INSPECTED. ALL 4 TAPER PINS WERE FOUND LOOSE, AND FOUND INSTALLED TO MAXIMUM ALLOWED PENETRATION. UPON DISASSEMBLY THE HOLES WERE FOUND OVERSIZED AND FILLED WITH PAINT FROM MFG. NEW TORQUE TUBE WAS INSTALLED AND AIRCRAFT RETURNED TO SERVI CE. (TC NR 20070824004) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007091700055 20070917 00055 EU 2007 9 17 CA070824005 1 20070730 G 2910 373Q2277 LINE BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU HYDRAULIC SYS LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) WHILE FLYING BOTH HYDRAULIC PUMP LIGHTS CAME ON. THE AIRCRAFT LANDED USING ITS BACKUP SYSTEM. IT WAS FOUND THAT THE HYDRAULIC LINE THAT RUNS BETWEEN THE PUMP AND FILTER ON THE LT NACELLE. THE LINE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. THE LEAK CAME FROM A SPOT WHERE THE LINE WAS CLAMPED. (TC NR 20070824005) 2 L 7 2 3T 4 T A24EU A196 6 C P899 2007091700056 20070917 00056 NE 2007 9 17 CA070824006 3 20070813 G 6110 8173881 SEAL 14SF23 DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE PROPELLER TORN W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 85 20060114 20060114 (CAN) CREW NOTICED A LARGE AMOUNT OF OIL ON THE LT NACELLE WHICH APPEARED TO ORIGINATE FROM THE PROPELLER. THE ENGINE WA S SHUTDOWN DUE TO THE EXCESSIVE LEAKAGE AND THE AIRCRAFT RETURNED TO BASE. THE PROPELLER NR 1 BLADE SEAL WAS REPLACED A ND GROUND LEAK CHECKS CARRIED OUT. THE SEAL (WHICH WAS FURTHER DAMAGED DURING REMOVAL) APPEARS TO HAVE HAD A TEAR ON TH E SURFACE WHICH FACES OB AND IS EXPOSED WHEN INSTALLED. (TC NR 20070824006) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007091700057 20070917 00057 WP 2007 9 17 CA070824007 1 20070725 G 7921 315341 DOOR CVAC 440 440 2422902 WP ALLSN 501D 501D22 03005 GL HAMSTD 54H 54H60 NE OIL COOLER INOPERATIVE W E ENGINE SHUTDOWN J WARNING INDICATION CL CLIMB 1 CA 26 (CAN) AIRCRAFT WAS DISPATCHED FOR FIRE ACTION. AFTER DEPARTURE, THE RT OIL TEMPERATURE GAUGE WAS OBSERVED TO BE AT THE B OTTOM OF THE RED ARC, APPROXIMATELY 100 DEGREES C. THE FLIGHT CREW IMMEDIATELY SHUTDOWN THE RT ENGINE AS A PRECAUTION AN D RETURNED TO BASE. DURING INSPECTION BY MAINTENANCE, THE RT OIL COOLER DOOR WAS OBSERVED TO BE NOT FUNCTIONING AND POSI TIONED FULLY CLOSED. THE RT OIL COOLER DOOR ACTUATOR WAS REMOVED AND INSPECTED. DURING DISASSEMBLY, SEVERAL WIRES AND A TERMINAL BLOCK WERE FOUND TO BE BROKEN IN THE ELECTRICAL BOX. THE OIL COOLER DOOR ACTUATOR WAS REPLACED AND RIGGED IAW M M. AFTER GROUND CHECKED SERVICEABLE, THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070824007) 2 L 7 2 4R 4 T 6A6 E282 6 C P906 2008012900020 20080129 00020 CE 2008 1 29 CA070826000 1 20070825 G 3245 TUBE MICHEL BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCE4N HCE4N3 NE TIRE DETACHED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA 6196W00409 (CAN) ON TAKEOFF THE CREW NOTICED A STRONG VIBRATION. THEY DECIDED TO CANCEL THE FLIGHT AND LAND BACK AT AIRPORT. FOUND THE NOSE TIRE BALANCE PATCH (FACTORY INSTALLED) HAD COME DISCONNECTED AND WAS TUMBLING LOOSE INSIDE THE TIRE. (TC NR 20 070826000) 1 L 7 2 4T 4 T A24CE E4EA 5 C P10NE 2007091700060 20070917 00060 NE 2007 9 17 CA070827001 2 20070823 G 7250 311666801 GASKET CESSNA 500 S550 2076607 CE PWA JT15 JT15D4 52112 NE NR 4 BRG HSG LEAKING W E ENGINE SHUTDOWN J K WARNING INDICATION FLUID LOSS AP APPROACH 1 CA 1840 (CAN) NR 4 BEARING GASKET LEAKED CAUSING COKING AND BLOCKAGE OF THE OIL SCAVENGE TUBE. (TC NR 20070827001) 1 L 7 2 4F 4 F RT A22CE E1NE 2007110200014 20071102 00014 NM 2007 11 2 CA070827002 1 20070725 G 2761 A44700009 HOUSING DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ACTUATOR CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 001677 (CAN) WHILE DOING A LAYOVER INSPECTION A HYDRAULIC LEAK WAS FOUND IN THE LT FLAP AREA. THE LEAK WAS FOUND TO BE COMING F ROM THE LT OB ROLL SPOILER ACTUATOR. UPON REMOVAL OF THE ACTUATOR IT WAS FOUND THAT THE HOUSING HAD CRACKED IN THE AREA SUROUNDING ONE OF THE PLUGS CAUSING THE PLUG TO DISLODGE. THE CRACK EXTENDED AROUND THE ENTIRE CIRCUMFERENCE OF THE ACT UATOR BODY WHERE THE PLUG IS THREADED IN. THE ACTUATOR WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE (TC NR 20070827 002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007091700061 20070917 00061 EU 2007 9 17 CA070827003 1 20070808 G 5200 SP915C16 SEAL BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE7315R 01518 WP BUTTON DETERIORATED W O OTHER O OTHER CL CLIMB 1 CA 6436 (CAN) UPON CLIMB OUT WITH CABIN DIFFERENTIAL PRESSURE APPROACHING APPROXIMATELY 6 PSI, A DISTINCT AUDIABLE DISCERNING NO ISE WAS HEARD FROM THE CENTER AREA OF THE CABIN. DURING DESCENT WHERE CABIN DIFFERENTIAL PRESSURIZATION FELL BELOW 6 PSI , NOISE WOULD SUBSIDE AND GO AWAY. NUMEROUS MAINTENANCE ACTIONS WERE CONDUCTED IN ORDER TO ISOLATE CAUSE INCLUDING PRESS URIZATION CHECKS AND CABIN LEAK RATES. NOISE COULD NOT BE REPRODUCED ON THE GROUND WHICH LED TO THE CONCLUSION THAT AIRS PEED WAS ALSO A FACTOR. FINALLY THE RUBBER RING SEAL WHICH IS HOUSED IN THE EXTERNAL RELEASE BUTTON MECHANISM OF THE EM ERGENCY ESCAPE HATCH WAS REPLACED AND THE MECHANISM LUBRICATED. NOISE DISSAPEARED. CONCLUSION WAS THAT THE BUTTON WAS V 2 L 7 2 4F 4 F RT A3EU E6WE 2007110200015 20071102 00015 EA 2007 11 2 CA070827004 1 20070824 G 3320 BR95005 BALLAST CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE CABIN LIGHT BURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) CREW REPORTED WHEN THEY APPLIED EXT AC POWER TO THE AIRCRAFT AND TURNED ON THE SWITCH IN THE COCKPIT, THEY COULD S MELL SOMETHING BURNING AND SAW A BLUE HAZE IN THE AIR. THEY IMMEDIATELY TURNED POWER OFF AND CALLED MAINTENANCE CONTROL. MAINTENANCE INSPECTION REVEALED THAT LIGHT BALLAST AT 7DF WAS FOUND TO BE THE SOURCE OF THE SMOKE/SMELL. THE BALLAST W AS REMOVED AND THE LIGHT WAS DIFFERED SO THE A/C COULD RETURN TO DEPARTURE FOR REPAIRS. ONCE IN THE AREA WHERE BALLAST W AS INSTALLED WAS INSPECTED AND BURNED INSULATION WAS FOUND. AN INSULATED TAPE REPAIR WAS CARRIED OUT AND THE BALLAST AT 7DF WAS REPLACED. THE APU WAS RUN FOR HALF HOUR WITH PACKS ON TO VERIFY NO OIL SMELL. THE A/C WAS THEN DEODORIZED AND 2 L 7 2 4F 4 F RT A21EA E15NE 2008013100038 20080131 00038 CE 2008 1 31 CA070827006 1 20070727 G 2497 MS33491 CONNECTOR SAFT BEECH 100 B100 1152919 CE GARRTT TPE331 TPE3316252B 01514 WP HARTZL HCB4T HCB4TN5 GL BATTERY MELTED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 111597 (CAN) WHILE IN FORMATION FLIGHT, THE LT (BATTERY CHARGE) LIGHT CAME ON AND STAYED ON FOR 15 MINUTES AND THEN EXTINGUISHE D. AFTER LANDING AND ENGINES SHUTDOWN, THERE WAS NO MORE POWER COMING FROM THE BATTERIES. AN INSPECTION WAS CARRIED OUT AND THE LT BATTERY WAS DISCOVERED (TOASTED) INCLUDING THE BATTERY COMPARTMENT. THE CAUSE WAS DETERMINED TO BE A BAD CON TACT ON THE NEGATIVE POLE. (TC NR 20070827006) 1 L 7 2 4T 4 T A14CE E2WE 6 C P40EA 2007110200016 20071102 00016 SW 2007 11 2 CA070827008 1 20070823 G 7697 WIRE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE CONNECTOR DAMAGED W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) AFTER AIRCRAFT LANDED AND WAS TAXING THE SPEED LEVERS WERE PULLED BACK INTO LOW IDLE THE RT ENGINE OIL LIGHT CAME ON AT WHICH POINT THE CREW REALIZED THE RT ENGINE HAD SHUT ITSELF DOWN. CREW CONTACTED MAINTENANCE. MAINTENANCE INVESTIG ATED AND REPAIRED WIRING ON CONNECTOR PLUG AND RAN AIRCRAFT WHICH THEY WERE NOT ABLE TO DUPLICATE ENGINE SHUT DOWN. TES T FLIGHT WAS COMPLETED AND UPON LANDING ENGINE SHUTDOWN AGAIN WHEN SPEED LEVERS WERE BROUGHT BACK INTO LOW IDLE. FUEL SH UT OFF WAS REPLACED AT THIS TIME AND ENGINE SHUTDOWN COULD NOT BE DUPLICATED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070 827008) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2007110200017 20071102 00017 EA 2007 11 2 CA070827009 1 20070808 G 2711 2776016105 ACTUATOR FRCHLD 22 22C7A 3370104 EA GARRTT TPE331 TPE331* 01514 WP MCAULY 4HFR34 4HFR34C652 NE LT AILERONS STIFF W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) PILOT COMPLAINED ABOUT AILERON STIFF TO MOVE AND WOULD OCCASIONALLY STICK IN THE FULL RT POSITION. UPON MAINTENAN CE TROUBLESHOOTING IT WAS NOTICED THAT THE LT AILERON TRIM ACTUATOR THAT WAS RECENTLY REPLACED, APPROXIMATLY 80 HOURS PR EVIOUS, WAS AGAIN STIFF TO OPERATE. IT WOULD ALSO STICK IN THE FULL EXTENDED POSITION. TRIM ACTUATOR WAS REPLACED AND AI RCRAFT RETURNED TO SERVICE. TRIM ACTUATOR WAS PASSED INTO QA WHO SENT TRIM ACTUATOR FOR FURTHER INVESTIGATION. 1 H 7 1 3I 3 T ATC438 E2WE 6 C 3PNE 2007091700062 20070917 00062 NE 2007 9 17 CA070827011 2 20070731 G 7300 25766304 SERVO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYSTEM MALFUNCTIONED W O OTHER R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA 1765 (CAN) DURING START UP, THE AIRCRAFT COULD DEVELOP AND POWER ABOVE 80 TO 85 PERCENT POWER INPUTS. THE SERVO WAS INSTALLED AND REMOVED WITH A TOTAL OF 3.7 HRS IN OPERATION ON THIS AIRCRAFT. SERVO WAS SENT FOR REPAIR AND CONTAMINATION WAS REPO RTED TO BE THE CAUSE OF LACK OF POWER. NO ISSUE WERE NOTED IN AIRCRAFT FUEL SYSTEM AND REPLACEMENT OF SERVO FIXED THE PR OBLEM. (TC NR 20070827011) 1 G 7 1 3O 3 O H11NM 1E4 2007110200018 20071102 00018 NE 2007 11 2 CA070827012 2 20070729 G 7414 MAGNETO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE BL600646201 FAILED W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA 168 (CAN) DURING START UP THE AIRCRAFT THE RT MAGNETO FAILED. MAGNETO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20070827012) 1 G 7 1 3O 3 O H11NM 1E4 2007110200019 20071102 00019 EA 2007 11 2 CA070827013 2 20070827 G 8530 AEL11800 VALVE SPRING CESSNA 172 172M 2072418 CE LYC O360 O360A4M 41514 EA MCAULY 1A200 1A200DFA GL INTAKE BROKEN W O OTHER O OTHER NR NOT REPORTED 1 CA 313 (CAN) ALUMINUM PARTICLES WERE FOUND IN THE OIL FILTER. UPON TEARDOWN OF THE ENGINE, A BROKEN INTAKE VALVE SPRING (OUTER) HAS DAMAGED THE ALUMINUM CYLINDER HEAD. (TC NR 20070827013) 1 H 7 1 3O 3 O NT 3A12 E286 5 N P874 2007110200020 20071102 00020 WP 2007 11 2 CA070827014 1 20070626 G 2842 A5501 TRANSMITTER ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE AUX FUEL CELL ERRATIC W K NONE N FALSE WARNING IN INSP/MAINT 1 CA 813 (CAN) DURING A 50 HR INSPECTION IT WAS NOTED THAT THE AUX FUEL TANK INDICATION SYSTEM HAD ERRATIC MOVEMENT. THE SENDER W AS REPLACED, FUEL SYSTEM CALIBRATION WAS CARRIED AND NO FURTHER ISSUES WERE NOTED. 1 G 7 1 3O 3 O H11NM 1E4 2007110200021 20071102 00021 WP 2007 11 2 CA070827015 1 20070810 G 2410 ALX8521 ALTERNATOR ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ENGINE MALFUNCTIONED W O OTHER J WARNING INDICATION LD LANDING 1 CA 1760 (CAN) DURING LANDING THE ALTERNATOR LIGHT FAILED TO EXTINGUISH. CHARGING SYSTEM WAS CHECKED AND THE ALTERNATOR WAS THE D EFECTIVE PART. THE ALTERNATOR WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20070827015) 1 G 7 1 3O 3 O H11NM E295 2007110200022 20071102 00022 WP 2007 11 2 CA070827016 1 20070626 G 6730 D2121 SERVO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FLT CONTROL LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1042 (CAN) DURING A 50/300 HR INSPECTION, IT WAS NOTED THAT THE AFT SERVO WAS LEAKING. SERVO WAS REPLACED AND NO FURTHER DEF ECTS WERE NOTED. (TC NR 20070827016) 1 G 7 1 3O 3 O H11NM 1E4 2007110200023 20071102 00023 WP 2007 11 2 CA070827017 1 20070626 G 2822 D7431 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYS DEFECTIVE W K NONE O OTHER IN INSP/MAINT 1 CA 1042 (CAN) DURING A MAINTENANCE INSPECTION A FUNCTION CHECK WAS CARRIED OUT ON THE AUX FUEL PUMP AND SOUNDS BEGAN TO COME FRO M THE PUMP WHICH IS NOT PART OF IT`S NORMAL OPERATION. PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 200708 27017) 1 G 7 1 3O 3 O H11NM 1E4 2007110200024 20071102 00024 EA 2007 11 2 CA070828002 1 20070824 G 2910 601R75239463 LINE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE HYD SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 27240 (CAN) DURING C-CHECK INSPECTION, CHAFING DAMAGE WAS NOTED ON THE HYDRAULIC PUMP 3B SUCTION LINE P/N 601R75239-463. THIS HYDRAULIC TUBE LINE WAS RUBBING AGAINST THE UPLOCK NR 3 HYDRAULIC TUBE LINE (P/N 601R75239-273) THAT FEEDS INTO THE EXTE ND LINE FOR THE RHS MAIN LANDING GEAR RETRACTION ACTUATOR. THE HYDRAULIC LINE HAS BEEN ORDERED AND WILL BE REPLACED BEFO RE THE AIRCRAFT LEAVES THE HEAVY CHECK. (TC NR 20070828002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007110200025 20071102 00025 EA 2007 11 2 CA070828003 1 20070824 G 2910 601R75239463 LINE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE HYD SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 27240 (CAN) DURING A C-CHECK INSPECTION IN THE RT MAIN LANDING GEAR WHEEL WELL, THE HDRAULIC SUCTION TUBE ASSY(P/N 601R75239-4 63) OF HYDRAULIC PUMP 3B WAS FOUND WITH CHAFING DAMAGE. THIS TUBE WAS RUBBING AGAINST THE HYDRAULIC LINE(P/N 601R75239-2 73),WHICH IS THE UPLOCK NR 3 LINE FEEDING INTO THE RT MAIN LANDING GEAR RETRACTION ACTUATOR.THE HYDRAULIC LINE HAS BEEN ORDERED AND WILL BE REPLACED BEFORE THE AIRCRAFT LEAVES THE HEAVY MAINTENANCE CHECK. (TC NR 20070828003) 2 L 7 2 4F 4 F RT A21EA E15NE 2007110200026 20071102 00026 SW 2007 11 2 CA070828004 1 20070821 G 6420 204011761001 BEARING BELL 204 204B 1181404 SW LYC T53 T5313B 41549 NE TAIL ROTOR HEAD WORN W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) PILOT WAS FLYING HELICOPTER AND FELT TWO SLIGHT YAWS TO THE RT APPROXIMATELY 30 TO 40 SECONDS APART. AT FIRST THE PILOT SUSPECTED IT MIGHT HAVE BEEN A GUST OF WIND, BUT THE SECOND YAW ALERTED THE PILOT TO A PROBLEM WITH THE TAIL ROTOR AS IT WAS ACCOMPANIED BY A NOTICEABLE RELUCTANCE OF THE AIRCRAFT TO RECOVER TO THE NOSE POINTED IN THE DIRECTION OF FLI GHT. THE PILOT MADE A SUCCESSFUL UNSCHEDULED LANDING WITH NO DAMAGE TO THE AIRCRAFT. UPON A MAINTENANCE INSPECTION OF T HE T/R CROSSHEAD, IT WAS DETERMINED THAT THE DUPLEX BEARING INSIDE THE CROSSHEAD, BEARING P/N 204-011-761-001, HAD SEIZE D. NEW PARTS WERE SUBSEQUENTLY ORDERED AND INSTALLED. PARTS HAVE BEEN SHIPPED TO MAIN BASE FOR FURTHER INVESTIGATION. ( 1 G 7 1 4U 4 U H1SW E17EA 2008013100039 20080131 00039 SW 2008 1 31 CA070828005 1 20070726 G 5753 240014901 BLOCK MOONEY M20 M20C 5870208 SW LYC O360 O360A1D 41514 EA HARTZL HCC3Y HCC3YR GL FLAP HINGE BLOCK CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT WING CENTER FLAP HINGE BLOCK HAD SERIOUS INTER-GRANULAR CORROSION. CORROSION APPEARS TO HAVE STARTED IN THE POR TION OF THE BLOCK THAT IS USED AS A STOP. THE STOP IS NOT EMPLOYED IN THE LOCATION THIS HINGE BLOCK WAS INSTALLED, (AFFE CTED HINGE BLOCK, CENTER HINGE LOCATION). (TC NR 20070828005) 1 L 7 1 3O 3 O 2A3 E286 5 C P25EA 2007110200027 20071102 00027 NE 2007 11 2 CA070828006 2 20070827 G 7250 BLADES CNDAIR CL600 CL6002D24 1390016 EA GE CF34 CF34* NE NR 1 ENGINE DAMAGED W O OTHER C F.O.D. TX TAXI/GRND HDL 1 CA 6692 194299 (CAN) ON WALK AROUND ON THE RAMP, IT WAS DISCOVERED THAT NR 1 ENGINE HAD BLADE AND STATOR DAMAGE CAUSED BY UNKNOWN FOD. THE A/C WAS TAXIED TO THE HANGER FOR INSPECTION AND BOROSCOPE. THE INSPECTION REVEALED THAT NR 14 BLADE HAD A SMALL DENT , FURTHER INVESTIGATION REVEALED DAMAGE AT THE 1ST STAGE STATOR AT THE 5 O-CLOCK POSITION AND A PUNCTURE TO THE ENGINE L INER. (APPROX 1.4X1.0 HOLE JUST AFT THE NR1 FAN AND JUST FORWARD OF STATOR AT APPROX 4 O’CLOCK POSITION LOOKING AFT.) DU E TO THE SKIN CONTAINMENT DAMAGE 1 INCH X .40 , MM DOES NOT ALLOW FOR ANY DAMAGE IN THIS AREA. ENGINE CHANGE HAS BEEN C/ O. PRESENT A/C HOURS:6692:52 AND CYCLES:3126. 2 L 7 2 4F 4 F RT A21EA E15NE 2007110200028 20071102 00028 SO 2007 11 2 CA070828007 2 20070827 G 8530 637781 EXHAUST VALVE CESSNA 185 185A 2072804 CE CONT O520 IO520* 17032 SO MCAULY 2A34C D2A34C58 GL NR 2 CYLINDER BURNED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION, FOUND THE NR 2 CYLINDER LOW COMPRESSION, RESULT WAS THE EXHAUST VALVE EDGE WAS BURNE D. (TC NR 20070828007) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2008013100041 20080131 00041 WP 2008 1 31 CA070829001 1 20070819 G 2435 BC3151004 STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INTERMITTENT W K NONE O OTHER IN INSP/MAINT 1 CA 1038 (CAN) DURING AN ATTEMPTED START THE STARTER FUNCTION WAS INTERMITTENT. STARTER WAS REPLACED AND NO FURTHER ISSUES WERE N OTED. (TC NR 20070829001) 1 G 7 1 3O 3 O H11NM 1E4 2008013100044 20080131 00044 EA 2008 1 31 CA070829002 2 20070714 G 7323 D2781 GOVERNOR ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ENGINE INTERMITTENT W O OTHER J WARNING INDICATION CR CRUISE 1 CA 1144 (CAN) DURING CRUISE, THE GOVERNOR CONTROL SETTING BECAME HIGHER. MAINTENANCE INVESTIGATED AND NO ISSUES COULD BE FOUND. GOVERNOR WAS REPLACED AND NO ISSUES WERE NOTED. (TC NR 20070829002) 1 G 7 1 3O 3 O H11NM E295 2007110200029 20071102 00029 EA 2007 11 2 CA070829004 1 20070827 G 7160 75420022101 INTAKE DUCT DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL NACELLE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 33785 (CAN) LEVEL 3 CORROSION WAS FOUND BETWEEN THE LOWER INTAKE FORWARD LIP AND THE NACELLE STRUCTURE. (TC NR 20070829004) 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2008022100014 20080221 00014 SW 2008 2 21 CA070830001 1 20070827 G 5320 NAS50134A BOLT AIRTRC AT802 AT802A 0390308 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MA3 GL DISPERSAL GATE BROKEN W D RETURN TO BLOCK K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) RETARDANT WAS DISCOVERED LEAKING FROM AROUND THE TANK DOORS. UPON INVESTIGATION, IT WAS NOTED THAT THE BOLT SECURI NG THE ANGLE INSIDE THE RT DISPERSAL GATE ASSY WAS BROKEN. THE BOLT WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVIC E. (TC NR 20070830001) 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2007110200030 20071102 00030 GL 2007 11 2 CA070830002 3 20070719 G 6114 2339 HUB CESSNA 180 180E 2072612 CE CONT O470 O470R 17026 SO MCAULY 2A36C 2A36C29 GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1251 441 61822 (CAN) HUB THREADS FOUND CRACKED DURING OVERHAUL PROCESS (TC NR 20070830002) 1 H 7 1 3O 3 O 5A6 E273 5 C P880 2007110200031 20071102 00031 EA 2007 11 2 CA070830003 1 20070819 G 2810 215640024 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE RT WING LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1407 (CAN) FUEL LEAK, RT WING FUEL CELL, NR 2 REPLACED DUE TO LEAKS IN FUEL CELL (TC NR 20070830003) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2007110200032 20071102 00032 EA 2007 11 2 CA070830004 1 20070819 G 2810 2156400212 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE RT WING LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) FUEL LEAK RT WING, FUEL CELL NR 3 REPLACED DUE TO HOLE IN THE CELL. (TC NR 20070830004) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2007110200033 20071102 00033 EA 2007 11 2 CA070830005 1 20070819 G 2810 2156400212 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE RT WING LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1407 (CAN) FUEL LEAK RT WING FUEL CELL NR 7 REPLACED DUE TO HOLES IN THE FUEL CELL. (TC NR 20070830005) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2007110200034 20071102 00034 EA 2007 11 2 CA070830006 1 20070823 G 2760 72740251001 ROD DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL SPOILER IND BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING TROUBLESHOOTING, A PFCS INDICATOR PROBLEM, IT WAS NOTICED THAT THE ROD FOR THE RT IB ROLL SPOILER TRANSMITT ER HAD SHEARED INSIDE OF THE ROD END AT THE SPOILER END. THERE WAS NO INDICATIONS OF THE ROD CONTACTING ANY OTHER SURFAC E TO CAUSE IT TO BREAK, THE BREAK MAY HAVE DEVELOPED FROM A CRACK. THE ROD WAS REPLACED AND THE AIRCRAFT RETURNED TO SE RVICE. (TC NR 20070830006) 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2008022100015 20080221 00015 EU 2008 2 21 CA070831001 1 20070726 G 6220 RING SNIAS 350 AS350D 8680803 EU TMECA ARRIEL ARRIEL1D 60048 NE M/R HEAD LOOSE W O OTHER O OTHER LD LANDING 1 CA (CAN) DURING ENGINE SHUTDOWN THE MAIN ROTOR BLADE DROOP STOP RING FELL DOWN THE MAST ASSY. THE HARDWARE HOLDING THE RING BRACKET ALL CAME OFF ALLOWING THE RING TO FALL DOWN THE MAST TO THE SWASHPLATE DRIVE LINK. SINCE THIS WAS REPORTED, I T HAS BEEN DETERMINED THAT THIS IS NOT THE FIRST TIME THE HARDWARE FOR THE DROOP RING HAS COME LOOSE AFTER INSTALLATION. THE MAINTENANCE REVIEW BOARD HAS NOTIFIED TO SEE IF ANY ADDTION MAINTENANCE REQUIREMENTS ARE NECESSARY. (TC NR 20070831 001) 1 G 7 1 3U 3 U H9EU E19EU 2008030600143 20080306 00143 CE 2008 3 6 CA070831002 1 20070830 G 2752 503801535 DRIVE ASSY BEECH BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCE4N HCE4N3 NE FLAP ACTUATOR MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 240 (CAN) ON LANDING, WHEN FLAPS SELECTED FROM 40 PERCENT TO 100 PERCENT, FLAPS STOPPED AT APPROXIMATELY 60 PERCENT, LT OB F LAP WAS SPLIT APPROXIMATELY 10 PERCENT. FLAP WOULD NOT EXTEND OR RETRACT. LT OB FLAP ACTUATOR FOUND TO HAVE COME APART AT THE 90 DEGREE DRIVE ASSY ATTACH POINT. CLOSER VISUAL EXAMINATION REVEALED THAT IT HAD NOT BEEN PROPERLY ASSEMBLED DUR ING AC AND/OR PART MFG. RETAINING KEYWAY HAD DAMAGED THE SLOTTED COLLAR BY NOT BEING FULLY ENGAGED WHEN RETAINING NUT W AS TIGHTENED. THIS SHOULD HAVE BEEN EVIDENT WHEN PART WAS ASSEMBLED AS THE RETAINING NUT WOULD NOT HAVE BEEN IN SAFETY A FTER BEING TIGHTENED. ALSO THE RETAINING KEYWAY WOULD NOT HAVE BEEN RECESSED (APPROX .1250 INCH ON PROPERLY ASSEMBLED PA 1 L 7 2 4T 4 T A24CE E4EA 5 C P10NE 2007110200035 20071102 00035 NE 2007 11 2 CA070831005 2 20070829 G 8520 39785A PIN PWA BEECH 18 D18S 1151004 CE PWA R985 R985AN14B 52008 NE HAMSTD 22D 22D30 NE MASTER ROD LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 575 (CAN) CREW ATTEMPTED TO CHECK FOR HYDRAULIC LOCK PRIOR TO START, AND WAS UNABLE TO TURN THE ENGINE MORE THAN 180 DEGREES . THROUGH DIAGNOSIS AND DISCUSSION WITH ENGINE OVERHAUL FACILITY, IT WAS ELECTED TO REMOVE A CYLINDER AND CONFIRM THE IN TEGRITY OF THE MASTER ROD ASSEMBLY. ONE OF THE LINK PINS SECURING THE LINK RODS TO THE MASTER ROD WAS FOUND BACKED OUT O F ITS HOLE AND WAS STRIKING THE INSIDE OF THE CRANKCASE, PREVENTING THE FULL ROTATION OF THE CRANKSHAFT. FAILURE OF THIS LINK PIN WOULD HAVE BEEN CATASTROPHIC FOR THIS ENGINE. (TC NR 20070831005) 1 L 7 2 3R 3 R A765 5E1 5 C P736 2007110200036 20071102 00036 EA 2007 11 2 CA070902001 1 20070813 G 2100 GG670950093 ACM CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C1 NE RIGHT FAILED W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 7563 (CAN) RT PACK GOES FULL HOT AND FAILS WITH BURNING ODOR. (TC NR 20070902001) 2 L 7 2 4F 4 F RT A21EA EOOO63EN 2007113000087 20071130 00087 EA 2007 11 30 CA070902002 1 20070812 G 2730 BA6709260213 CONTROL ROD CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF34* 30015 NE VERTICAL STAB UNKNOWN W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA (CAN) AFTER ENGINE START FOR DEPARTURE FLIGHT AF 7836 ,THE ELEVATOR WAS FOUND JAMMING DURING CHECK LIST . AIRCRAFT RETU RNED TO THE GATE. THE EFFORTS ARE NORMAL ON CONTROL COLUMN UNTIL HALF WAY THE BECOMES HARD. EICAS INDICATION FOR THE ELE VATOR SHOWS FULL DEFLECTION WHEN THE CONTROL COLUMN REACHES HALF WAY . IN REFERENCE TO N16/07 THE ACFT WAS IN CHECK AN D COMPLETED ALL GROUND AND FLT TESTS SATISFACTORY . THE ACFT WAS REPOSITIONED. THE SB 670BA-27-022 WAS DONE AND INSPECT ED BUT A BUSHING REPLACEMENT WAS PENDING TO FULLY COMPLETE THE SB . DURING THIS BUSHING REPLACEMENT AN INVERSION OF THE ACTUATING RODS WAS DONE BETWEEN UPPER AND LOWER POSITION ON THE LEVER. THE RODS WERE REPOSITIONED IN NORMAL CONFIGURATI 2 L 7 2 4F 4 F RT A21EA 2007110200037 20071102 00037 EA 2007 11 2 CA070902003 1 20070824 G 5610 NP1393219 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE LEFT CRACKED W B EMER. DESCENT O OTHER CR CRUISE 1 CA (CAN) FL 330 LT, WINDSHIELD CRACKED. AIRCRAFT CONTINUED TO DESTINATION. NO FURTHER REPORTED DETAILS. (TC NR 20070902003) 2 L 7 2 4F 4 F RT A21EA E15NE 2007110200038 20071102 00038 NM 2007 11 2 CA070903001 1 20070902 G 3233 8400105 ACTUATOR DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE MLG MALFUNCTIONED W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) ON DEPARTURE THE LANDING GEAR RETRACTED NORMALLY. APPROXIMATELY 20 SECONDS LATER, THE NOSE GEAR CYCLED UNSAFE AND THEN RETRACTED. APPROXIMATIVE 10 SEC. LATER IT OCCURRED AGAIN BUT THIS TIME DID NOT RETRACT. FLIGHT CREW CYCLED GEAR DOW N MANUALLY IAW QRH BOOK, RECEIVED 3 GREEN LIGHTS (DOORS CLOSED) AND WHEN SELECTED GEAR UP, THE GEAR RETRACTED NORMALLY A ND LOCKED. ON LANDING AT DESTINATION, LANDING GEAR EXTENDED NORMALLY AND AIRCRAFT LANDED NORMALLY. MAINTENANCE REPLACED THE NLG DRAG STRUT ACTUATOR. (TC NR 20070903001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007110200039 20071102 00039 EA 2007 11 2 CA070904001 2 20070902 G 8530 LW19001 EXHAUST VALVE ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA NR 1 CYLINDER WORN W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA 1836 (CAN) AN INTERMITENT SLIGHT POWER LOSS WAS INITIALY MISDIAGNOSED AS A FAULTY GOVERNOR CONTROL BOX. WHEN THE PROBLEM PERS ISTED, IT WAS DETERMINED THAT THE EXHAUST VALVE IN THE NR 1 CYLINDER WAS WORN AND HAD A SMALL PIECE MISSING. THE CYLINDE R ASSEMBLY IS CURRENTLY BEING REPLACED. (TC NR 20070904001) 1 G 7 1 3O 3 O H11NM E295 2007110200040 20071102 00040 NM 2007 11 2 CA070904002 1 20070902 G 2760 85770068003 LEVER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE GROUND SPOILER BROKEN W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) THE FLIGHT CREW SNAGGED THAT THE GROUND SPOILER LIGHT ILLUMINATED IN FLIGHT. UPON INVESTIGATION MAINTENANCE FOUND THE LT OB GROUND SPOILER LEVER BROKEN AT THE SPOILER ACTUATOR ATTACH POINT. THE LEVER WAS REPLACED AND THE AIRCRAFT RETU RNED TO SERVICE. (TC NR 20070904002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007102600114 20071026 00114 SO 2007 10 26 CA070904003 1 20070829 G 5343 TRUNNION LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL HAMSTD 54H 54H60117 NE NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 39503 (CAN) DURING THE A-CHECK INSPECTION, MAINTENANCE DETECTED A CRACKED RT NOSE LANDING GEAR TRUNNION FITTING. THE AIRCRAFT WAS RE- POSITIONED FOR PART REPLACEMENT. (TC NR 20070904003) 2 H 7 4 4T 4 T A1SO E282 6 C P906 2007102600115 20071026 00115 GL 2007 10 26 CA070905001 2 20070811 G 7250 TBA BEARING SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL NR 5 DISINTEGRATED W B A EMER. DESCENT UNSCHED LANDING X E J ENGINE FLAMEOUT VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA 3576 758 (CAN) FLIGHT CREW ENCOUNTERED A NR 2 ENGINE CHIP WARNING LIGHT FOLLOWED BY COMPLETE ENGINE FAILURE WITHIN 1 MIN EMERGENC Y LANDING EXECUTED. NR 2 ENGINE AND OIL COOLER REPLACED, A/C RETURNED TO SERVICE. SUBSEQUENT INVESTIGATION CARRIED OUT AT AMO REVEALED FAILURE OF THE NR 5 BEARING. THE BEARING FAILURE CAUSED POWER TURBINE ROTOR VIBRATION AND OSCILLATION R ESULTING IN SUBSEQUENT DAMAGE AND DECOUPLING OF TURBINE TO COMPRESSOR (N1) COUPLING. THE GAS GENERATOR TURBINE ENTERED O VER-SPEED OF UNKNOWN VALUE. THE GP TURBINE OVER SPEED CAUSED NR 2 TURBINE BLADES TO PROGRESSIVELY SEPARATE FROM THE DISK . THE NR 5 BEARING HAD BEEN OVERHAUL INSPECTED BY THIS AMO APPROXIMATELY 757.9 HRS PRIOR TO FAILURE AND RE-INSTALLED AS 1 G 7 2 3U 3 U H1NE E1GL 2007110200041 20071102 00041 EU 2007 11 2 CA070905002 1 20070828 G 2421 ALTERNATOR BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU NR 2 INOPERATIVE W A D UNSCHED LANDING RETURN TO BLOCK J WARNING INDICATION CR CRUISE 1 CA (CAN) AFTER DEPARTING AND ENROUTE, THE CREW OBSERVED NR 2 ALTERNATOR HAD TRIPPED OFFLINE AND DID NOT RESET. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE NR 2 ALTERNATOR. THE AIRCRA FT COMPLETED A SATISFACTORY GROUND RUN AND WAS RETURNED TO SERVICE. (TC NR 20070905002) 2 L 7 2 3T 4 T A24EU A196 6 C P899 2007102600116 20071026 00116 EA 2007 10 26 CA070905003 1 20070904 G 2750 601R9310511 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE TE FLAPS INOPERATIVE W O OTHER J WARNING INDICATION LD LANDING 1 CA (CAN) WING FLAPS FAILED TO FULLY EXTEND FOR LANDING. AFTER SELECTING FLAPS 8 THE CREW RECEIVED A FLAP FAULT CAUTION MESS AGE AND THE FLAPS WOULD NOT MOVE ANY FURTHER. THE CREW LANDED WITH FLAPS AT 8 DEGREES UNEVENTFULLY. FECU SHOWS LT BPSU A T FAULT. BPSU REPLACED, RIGGED AND FUNCTIONAL TEST COMPLETED SUCCESFULLY. AIRCRAFT RETURNED TO SERVICE. (TC NR 20070905 003) 2 L 7 2 4F 4 F RT A21EA E15NE 2007102600117 20071026 00117 EU 2007 10 26 CA070905004 1 20070828 G 7930 810710000 TRANSMITTER AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE OIL PRESSURE INOPERATIVE W E ENGINE SHUTDOWN N FALSE WARNING DE DESCENT 1 CA (CAN) WHILE INBOUND, THE CREW OBSERVED LOW OIL PRESSURE ON THE NR 1 ENGINE WITH A LOCAL ALERT LIGHT INDICATION THE CREW SHUT THE ENGINE DOWN AND LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE VERIFIED THAT THERE WAS NO OIL LOSS AND REPLACED T HE NR 1 OIL PRESSURE TRANSMITTER. THE AIRCRAFT WAS GROUND RUN SATISFACTORILY AND RETURNED TO SERVICE. FULL P/N IS 8107-1 00-00-10 (TC NR 20070905004) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2007102600118 20071026 00118 EU 2007 10 26 CA070905005 1 20070830 G 3240 30Z10322 LEVER BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU PARK BRAKE FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) AFTER ARRIVING AT AIRPORT, THE AIRCRAFT ROLLED FORWARD AFTER THE PARK BRAKE WAS APPLIED WITH ENGINES STILL RUNNING AND THEN CONTACTED GROUND EQUIPMENT. MAINTENANCE DETERMINED THAT THERE WAS A FAULT WITH THE PARK BRAKE SYSTEM AND THE HANDLE ASSEMBLY WAS REPLACED. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070905005) 2 L 7 2 3T 4 T A24EU A196 6 C P899 2007102600119 20071026 00119 CE 2007 10 26 CA070905006 1 20070810 G 5312 051218712 CHANNEL CESSNA CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL BULKHEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2923 17263199 (CAN) SEB 97-1 ADDRESSES THE POSSIBILITY OF CRACKING OF THE AFT DOORPOST CHANNELS AT THE LOWER END, IN THE SMALL CUTOUT RADIUS BETWEEN THE VERTICAL AND HORIZONTAL FLANGE BENDS. THE CRACK IS VERY DIFFICULT TO SEE. BOTH DOORPOSTS WILL CRACK, AND IT IS THE SUBMITTERS OPINION THAT THIS CRACKING IS CAUSED CHIEFLY BY TAXIING OVER ROUGHER GROUND SO THAT THE FUSELA GE BULKHEAD THAT INCORPORATES THE AFT DOORPOSTS FLEXES MORE THAN IN MOST OTHER OPERATIONS. THIS IS THE THIRD AC WE HAVE FOUND WITH THIS DEFECT WITHIN THE LAST 7 YEARS. (TC NR 20070905006) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007102600120 20071026 00120 2007 10 26 CA070905007 4 20070831 G 3170 6229820009 DCU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE NR 3 INOPERATIVE W E ENGINE SHUTDOWN N FALSE WARNING CL CLIMB 1 CA (CAN) DURING CLIMB OUT, CREW REPORTED A (L ENG MISCOMP) MESSAGE FOLLOWED BY A HIGH ITT. THE CREW ELECTED TO SHUTDOWN THE ENGINE. AFTER SHUTDOWN THE ITT REMAINED AT 998 DEGREES CELSIUS. AT TIME OF THE INCIDENT, THE AIRCRAFT WAS OPERATING UND ER MEL31-41-01 DUE TO AN INOPERATIVE DCU NR 3. DURING TROUBLESHOOTING, IT WAS DISCOVERED THAT SEVERAL SNAGS OCCURRED F OLLOWING THE REPLACEMENT OF ONE DCU WITH A P/N 622-9820-009. ALL OTHERS DCU WERE P/N 622-9820-008. ACCORDING TO SL RJ-SL -31-011 BOTH P/N ARE INTERCHANGEABLE AND INTERMIXABLE. DCU NR 1 AND NR 3 WERE REPLACED AND THE AIRCRAFT WAS RELEASED I NTO SERVICE. NO SIMILAR INCIDENT TO DATE HAS BEEN NOTED. (TC NR 20070905007) 2 L 7 2 4F 4 F RT A21EA E15NE 2007110200042 20071102 00042 EU 2007 11 2 CA070905009 1 20070904 G 2121 FAN AIRBUS 330 A330300 EU RROYCE RB211 RB211* 54555 NE MELTED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) AFTER T/O, SMOKE AND UNUSUAL SOUND COMING FROM L2 AREA. HAZE REPORTED IN THE CABIN. FLT RETURNED TO AIRPORT. ELECT RICAL ODOR WAS COMING FROM THE L2/R2 AREA WITH HAZE VISIBLE AT 5 DIFFERENT TIMES. IT WOULD APPEAR AND THEN DISAPPEAR. A REA INSPECTED AND FOUND MID-GALLEY CHILLER DUCT CLAMP ADRIFT, CAUSING UNUSUAL SOUND (S513) AND THE PROJECTOR 7DG (B-CLAS S) OVERTEMP LIGHT ON. FOUND COOLING FAN MELTED. CONNECTOR PLUG REMOVED. NEW CHILLER CLAMP INSTALLED. PROJECTOR REPLACED. (TC NR 20070905009) 2 L 7 2 4F 4 F RT A12EU 2007102600121 20071026 00121 NM 2007 10 26 CA070905010 1 20070903 G 2910 15E0803003 PIPE EMB ERJ170 ERJ170100SU 3260403 NM GE CF34 CF348E5A1 30015 NE HYD SYSTEM CUT W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING ROUTINE A CHECK INSPECTION A CUT APPROXIMATELY 1 CM LONG WAS NOTICED ON THE ENGINE HYDRAULIC PUMP SUPPLY PI PE. THIS CUT WAS APPROXIMATELY .050 DEEP AND WAS THE RESULT OF CHAFFING WHEN THE COWLS WERE CLOSED. (TC NR 20070905010) 2 L 7 2 4F 4 F RT A56NM E00063EN 2007102600122 20071026 00122 EA 2007 10 26 CA070905011 1 20070903 G 7500 16673301 DUCT DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE BLEED AIR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CABIN PACK REPORTED AS UNCONTROLLABLE AT LOW POWER SETTINGS. MAINTENANCE GROUND RUNS NOTED NON SUPPLY OF BLEED AIR AT FLIGHT IDLE SETTINGS, ALSO NOTED BLEED AIR LEAK FROM CEILING OF ACM COMPARTMENT. ACCESS GAINED TO INTERNAL OF DORSAL FIN AND FOUND BLEED AIR DUCT P/N 16673-301 CONNECTS TO FUSELAGE DUCT, CRACKED AND SPLIT OPEN APPROX HALF OF ITS DIAMETE R. DUCT REPLACED, GROUND RUNS COMPLETED AND AIRCRAFT RETURNED TO SERVICE. PART IS CONSIDERED AS AN EXPENDABLE AND TIMES NOT TRACKED. AIRFRAME TIMES 36419HR/51123CY (TC NR 20070905011) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007102600123 20071026 00123 SO 2007 10 26 CA070905012 2 20070831 G 8530 TSIN712ACA CYLINDER HEAD CESSNA 206 U206E 2073350 CE CONT O520 IO520F 17032 SO HARTZL HCC3Y PHCC3YF1 GL ENGINE CRACKED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 1343 282939R (CAN) CRACKED FROM SPARK PLUG HOLE TO EXHAUST VALVE (TC NR 20070905012) 1 H 7 1 3O 3 O A4CE E5CE 5 C P25EA 2007102600124 20071026 00124 EU 2007 10 26 CA070906001 1 20070827 G 5531 SPAR SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 7617 (CAN) CRACKS DISCOVERED ON BOTH SIDES OF STABILIZER THROUGH LOWER DOUBLER AT SPAR. FOUR RIVETS FOUND MISSING FROM FORWAR D SPAR ATTACHMENT OF LOWER STABILIZER FRAME. (VISISBLE UPON REMOVAL ONLY) SUSPECT INCORRECT SHIMMING AT THIS TIME. (TC N R 20070906001) 1 G 7 1 3U 3 U NC H9EU E19EU 2008030600144 20080306 00144 CE 2008 3 6 CA070906002 1 20070905 G 5520 115610010325 TORQUE TUBE BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA MCAULY 4HFR34 4HFR34C762 NE ELEVATOR LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 209 (CAN) DURING A ROUTINE INSPECTION THE LT ELEVATOR TORQUE TUBE WAS FOUND TO HAVE AN EXCESSIVE AMOUNT OF PLAY AT THE TAPER PINS ON BOTH COLLARS. THE TORQUE TUBE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THIS TORQUE TUBE ONLY HAD 209. 2 HOUR SINCE NEW AND IT IS ONLY REQUIRED TO BE INSPECTED EVERY 1000 HOUR. (TC NR 20070906002) 1 L 7 2 3T 4 T A14CE E4EA 6 C 3PNE 2007110200043 20071102 00043 NM 2007 11 2 CA070906003 1 20070902 G 5340 85311176009 ATTACH FITTING DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NLG ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED NOSE LANDING GEAR CHANGE, IT WAS DISCOVERED THAT THE NLG UPLOCK ACTUATOR FITTING ASSEMBLY P/N 853 11176-009 WAS CRACKED. FITTING REPLACED AND FITTING FASTENERS INSTALLED IAW RD8-53-3805. AFTT: 42865 HRS. TOTAL CYCLES: 50005. (TC NR 20070906003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007110200044 20071102 00044 NM 2007 11 2 CA070906004 1 20070904 G 3231 483023 SEQUENCE VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU LEFT NACELLE FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 1411 (CAN) ON DEPARTURE FROM AIRPORT, THE LEFT MAIN LANDING GEAR DOORS REMAINED OPEN. VISUALY CONFIRMED BY THE PURSER THAT TH E LT GEAR DOORS WERE LEFT OPEN. CREW SELECTED GEAR DOWN AND LEFT GEAR DOORS CLOSED WHILE THE OTHER GEAR DOORS OPENED. CR EW PERFORMED ALTERNATE EXTENSION OF THE MAIN LANDING GEAR AND RETURNED TO CYUL. MAINTENANCE INVESTIGATION REVEALED THAT WHEN THE LEFT GEAR DOOR CLOSED THE MAIN LANDING GEAR CAME DOWN DAMAGING THE LEFT MAIN OUTBOARD GEAR DOOR. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007110200045 20071102 00045 GL 2007 11 2 CA070906006 2 20070903 G 7210 GEARBOX CVAC 340 340CVAC 242270A WP ALLSN 501D 501D13D 03004 GL HAMSTD 54H 54H60 NE NR 2 UNKNOWN W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 192 (CAN) NR 2 ENGINE OIL PRESSURE AND QUANTITY INDICATION BOTH SHOWED A DECREASE UPON REACHING CRUISE ALT. NR 2 ENGINE SHU TDOWN AND RETURNED TO DEPARTURE. NR 2 REDUCTION GEARBOX BEING REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 2007090 6006) 2 L 7 2 4R 4 T 6A6 E282 6 C P906 2008030600145 20080306 00145 CE 2008 3 6 CA070906007 1 20070904 G 2750 1005240741 GEARBOX BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE TE FLAPS WORN W O OTHER O OTHER LD LANDING 1 CA (CAN) FLAPS WOULD NOT RETRACT AFTER LANDING. GEARBOX FOUND EXCESSIVELY WORN. (TC NR 20070906007) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2007102600125 20071026 00125 EA 2007 10 26 CA070906008 1 20070903 G 5610 NP1393225 WINDOW CNDAIR CL600 CL6002C10 1390015 EA COCKPIT CRACKED W O OTHER O OTHER AP APPROACH 1 CA 11434 (CAN) CREW REPORTED THAT ON SHORT FINAL, CAPTAIN LT SIDE WINDOW CRACKED. REPLACED SIDE WINDOW IAW AMM (TC NR 2007090600 8) 2 L 7 2 4F RT A21EA 2007102600126 20071026 00126 NE 2007 10 26 CA070906009 2 20070813 G 7250 BLADES CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE NR 2 ENGINE DAMAGED W E A ENGINE SHUTDOWN UNSCHED LANDING E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 25122 (CAN) A/C DIVERTED DUE TO NR 2 ENG. VIBRATION AND LOUD NOISE. NR 2 ENGINE WAS SHUTDOWN IN FLIGHT. PILOT DECLARED AN EMER GENCY. CONTRACT MAINTENANCE FOUND THE EXHAUST TURBINE BLADES DAMAGED. PRELIMINARY INSPECTION THAT THE LAST STAGE TURBI NE WITH TOTAL DAMAGE TO ALL BLADES. APPEARS THAT SOMETHING IN BETWEEN THE FIRST STAGE HPT AND LAST STAGE LPT CAME LOOSE AND DEPARTED THROUGH THE TURBINE. ENG WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. ENG IS IN ENG SHOP AND IS BEING PR EPPED FOR SHIPPING. (TC NR 20070906009) 2 L 7 2 4F 4 F RT A21EA E15NE 2007102600127 20071026 00127 NM 2007 10 26 CA070907001 1 20070906 G 3297 471515 WIRE HARNESS BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NLG DAMAGED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, GEAR WOULD NOT RETRACT RESULTING IN AN AIR TURNBACK. DURING GROUND INSPECTION FOUND NOSE GEAR HARNE SS TO BE INTERMITTENT DURING TESTING. DETAILED INSPECTION OF HARNESS FOUND IN SHARP BEND OF CONDUIT BOTH WOW SENSOR HARN ESS AND NOSE WHEEL CENTERING HARNESS CRACKED AND SHIELDING EXPOSED. NLG WOW 2/CENTERING HARNESS HARNESS REPLACED. (TC NR 20070907001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007110200046 20071102 00046 SO 2007 11 2 CA070907002 1 20070906 G 3411 LPMILH55934 HOSE GULSTM GV GULFSTREAMGV 3980116 SO GARRTT TFE731 TFE73140 29001 NE STATIC SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 985 (CAN) DURING PITOT STATIC CHECKS IT WAS FOUND THE SYSTEM WAS SLIGHTLY LEAKING. FURTHER VISUAL INSPECTION FOUND THE STATI C HOSE GOING TO THE ADC WAS WEATHER CRACKED AND LEAKING NEAR THE FITTING. THE HOSE WAS MFG THE FIRST QUARTER OF 2001.(1Q 01).(25W752005-063H) PREVIOUSLY G100 C-FHRL SN NR 150 HAD 3 HOSES REPLACED FOR THE SAME REASON AND BY ERROR AN SDR WAS N OT SUBMITTED. ALSO 1 OF THE SAME BASE NR HOSES WAS REPLACED ON C-FHNS G100 SN NR 156. ASTRA SPX (G100) NR 087 C-FRJZ WER E LOOKED AT AND THE HOSES WERE FINE. THIS SEAMS SOMEWHAT PREMATURE AGING FOR THESE HOSES. THE HOSES ARE LOCATED IN THE N OSE COMPARTMENT AREA AND THERE ARE 2 IAW ADC HAVING THE SAME BASE NR AND DIFFERENT DASH NRS. (TC NR 20070907002) 2 L 7 2 4F 4 F RT A12EA E1NM 2008030600146 20080306 00146 SW 2008 3 6 CA070907003 1 20070906 G 5740 31692 ATTACH FITTING BBAVIA 7 7ECA 21101NN SW LYC O235 O235K2C 41505 EA SNSNCH 72C 72CK EA WING FAULTY W K NONE O OTHER IN INSP/MAINT 1 CA 1000 (CAN) AD 96-18-02 AND THE AIRWORTHINESS LIMITATIONS FOR THIS AC REQUIRE THAT THE WING SPAR/STRUT ATTACH FITTINGS BE REMO VED AND NDI WITH FLUORESCENT DYE PENETRANT EVERY 1000 HOURS. NDI DISCLOSED A FLAW WITHIN THE METAL, APPARENTLY EXISTING WITHIN THE RAW STOCK WHEN MFG, AND THE AMOUNT OF DYE THAT BLED OUT INDICATES THAT THE FLAW EXTENDS DEEPLY INTO THE META L. IT IS NEAR THE TOP BOLT HOLE WHERE THE STRESSES ARE MINIMAL, AND NO CRACKING WAS NOTED BETWEEN THE FLAW AND THE HOLE. (TC NR 20070907003) 1 H 7 1 3O 3 O A759 E223 5 N P9045 2008012900026 20080129 00026 EA 2008 1 29 CA070907004 2 20070906 G 7310 3040637 FUEL LINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL ENGINE BAY CHAFED W O OTHER K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA PCE32232 (CAN) FUEL LINE ASSY WAS FOUND TO HAVE BEEN CHAFED BY THE STARTER GENERATOR VENT HOSE, CAUSING A VERY SMALL PIN HOLE IN THE RIGID STAINLESS FUEL LINE, RESULTING IN A FUEL LEAK. (TC NR 20070907004) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007110200047 20071102 00047 NM 2007 11 2 CA070907005 1 20070907 G 5751 85740337105106 HINGE FITTING DHAV DHC8 DHC8301 1386003 NM AILERON MIGRATED W K NONE O OTHER IN INSP/MAINT 1 CA 22128 (CAN) THE BEARINGS ON THE AILERON HINGE FITTINGS LOCATED AT YW515.19 WERE FOUND TO BE MIGRATED. IT WAS FOUND THAT THE HI NGE FITTING P/N`S 85740337-105/-106 WERE MANUFACTURED INCORRECTLY SINCE THE DISTANCE BETWEEN THE TWO LUG FACES (0.850 IN CH NOMINAL) MEASURES 0.970 INCH. (TC NR 20070907005) 2 H 7 2 4T RT A13NM 2008013100045 20080131 00045 SW 2008 1 31 CA070909001 1 20070908 G 2421 LW10382 BRACKET HUGHES 269 269C1 8059504 SW LYC O360 HIO360* 41514 EA ALTERNATOR BROKEN W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) ALTERNATOR BRACKET FOUND WITH BROKEN ATTACHMENT LUG. ALTERNATOR BELT TENSION LOSS AND SUBSEQUENT SYSTEM UNSERVICEA BILITY. CAUSE OF FAILURE UNDER INVESTIGATION. (TC NR 20070909001) 1 G 7 1 3O 3 O O 4H12 1E10 2007102600128 20071026 00128 EA 2007 10 26 CA070909002 2 20070904 G 7314 RG908054AM PUMP PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE FAULTY W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA 7 (CAN) DURING START UP THE ENGINE WOULD NOT MAINTAIN FUEL PRESSURE AT 700 RPM. ENGINE WOULD NOT SUSTAIN POWER AT 2000 RPM AND PRESURE DROPS AND ENGINE QUITS. ENGINE DRIVEN FUEL PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. ENGINE WAS P REVIOUS OVERHAULED ALONG WITH FUEL PUMP. (TC NR 20070909002) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007102600129 20071026 00129 GL 2007 10 26 CA070910001 3 20070907 G 6110 1A101 PROPELLER CESSNA 150 150H 2071818 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100* GL CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1343 (CAN) WHILE PERFORMING A 5 YEAR CORROSION INSPECTION ON SUBJECT PROPELLER IAW CAR 625 APPENDIX C, PARA.5, CORROSION WAS NOTED IN THE MOUNTING HOLE BORE. IN CONSULTATION WITH THE PROPELLER OVERHAUL AMO, IT WAS DECIDED TO SEND IT TO THEM FOR FURTHER EVALUATION. CURRENTLY AWAITING THEIR REPORT AS TO IT`S STATUS. (TC NR 20070910001) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2008022500080 20080225 00080 NE 2008 2 25 CA070910002 2 20070905 G 7314 D7431 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE AUX FUEL SYS UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AUX FUEL PUMP FOUND UNSERVICEABLE DURING DI REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20070910002) 1 G 7 1 3O 3 O H11NM 1E4 2007110200048 20071102 00048 EU 2007 11 2 CA070910003 1 20070906 G 2910 T2C5000605500 LINE BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU HYDRAULIC SYS RUPTURED W O OTHER K J FLUID LOSS WARNING INDICATION DE DESCENT 1 CA (CAN) 10 MINUTES PRIOR TO LANDING, THE PORT AND STARBOARD HYDRAULIC PUMP LIGHTS ILLUMINATED WITH MAIN PRESSURE DEPLETING AND STOPPING AT ACCUMULATOR PRESSURE. THE CREW CARRIED OUT THE APPROPRIATE PROCEDURES AND LANDED WITH NO FURTHER INCIDE NT. MAINTENANCE FOUND A HYDRAULIC FLEX LINE, IN THE RT WHEEL BAY, WHICH GOES TO THE HIGH-PRESSURE HYDRAULIC FILTER RUPTU RED. THE FLEX LINE, ALONG WITH BOTH HYDRAULIC PUMPS, WAS REPLACED AND THE SYSTEM FUNCTION CHECKED SERVICEABLE. (TC NR 20 070910003) 2 L 7 2 3T 4 T A24EU A196 2007102600130 20071026 00130 CE 2007 10 26 CA070910004 1 20070909 G 2510 110195203 BUCKLE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE SEATBELT DISCONNECTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE COMPLYING WITH COMPANY CAMPAIGN NOTICE 010-25-10-011 CREW SEAT BELT BUCKLE INSPECTION, (REFER TO FAA SAIB NM -06-29)INTERFERENCE BETWEEN THE COCKPIT SEATBELT BUCKLES AND THE CONTROL COLUMN WOULD UNLATCH THE SEATBELT BUCKLE WHEN T HE YOKE WAS MOVED THROUGH FULL TRAVEL LT AND RT. THERE ARE NO CURRENTLY APPROVED SEAT BELT REPLACEMENTS AVAILABLE TO E LIMINATE THIS HAZARDOUS SITUATION. (TC NR 20070910004) 1 L 7 2 4F 4 F A22CE E1NE 2008022500081 20080225 00081 CE 2008 2 25 CA070910005 1 20070822 G 5720 6147514435 WASHER BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL WING DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE DOING CF-1981-25R6 LOWER FWD WING ATTACH FITTINGS YOU MUST REPLACE THE LOWER FWD. WING BOLT WASHER ASSY UPON RE-INSTALL OF BOLTS. NEW WASHER KITS WERE INSTALLED, BUT WERE UNABLE TO TORQUE IAW THE MFG SIRM., THE TORQUE WAS TOO GR EAT TO GET THE REQUIRED READING OF THE SPRING SCALE, THE THREADS ON THE NUTS WERE DAMAGED AND SO WERE THE THREADS ON THE BOLTS. THE BOLTS AND NUTS WERE REPLACED WITH NEW, AND THE WASHER KITS WERE ALSO REPLACED, AND NORMAL TORQUE WAS ATTAINE D. (TC NR 20070910005) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007110200049 20071102 00049 SO 2007 11 2 CA070910006 2 20070901 G 8530 641917 CYLINDER CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO MCAULY 1A101 1A101HCM GL EXHAUST VALVE STUCK W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA 21468372A (CAN) ON CLIMB OUT AFTER TAKEOFF, THE PILOT NOTICED MILD TO MODERATE ENGINE VIBRATION WITH A PARTIAL LOSS OF POWER. A RE TURN TO THE AIRSTRIP WAS CARRIED OUT WITH A SUCCESSFUL LANDING. ON INVESTIGATION BY AN AME, THE PROBLEM WAS NOTICED AS A N EXHAUST VALVE STUCK OPEN ON THE NR 3 CYLINDER. THE CYLINDER WAS REMOVED AND WAS SENT TO AN ENGINE OVERHAUL SHOP FOR RE PAIRS. THE CYLINDER IS STILL BEING REPAIRED AND WILL BE REINSTALLED UPON RETURN FROM THE SHOP. (TC NR 20070910006) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2007102600131 20071026 00131 GL 2007 10 26 CA070910007 2 20070910 G 7321 23070606 FUEL CONTROL BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE UNSERVICEABLE W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA 147 (CAN) OVERSPEED OCCURED DURING FLIGHT, FUEL CONTROL REPLACED WITH SERVICEABLE UNIT. WHEN REMOVED, IT WAS NOTED THAT THE FCU INPUT SHAFT BEARING WAS DAMAGED. FCU SENT OUT FOR INSP/REPAIR. (TC NR 20070910007) 1 G 7 1 3U 3 U H2SW E4CE 2007110200050 20071102 00050 WP 2007 11 2 CA070910008 2 20070827 G 7322 8978012 FCU FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE RT ENGINE MALFUNCTIONED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION TX TAXI/GRND HDL 1 CA 2302 (CAN) AFTER AIRCRAFT LANDED AND SPEED LEVERS WERE PULLED BACK INTO LOW IDLE THE RT ENGINE LIGHT CAME ON AT WHICH POINT T HE CREW REALIZED THAT THE ENGINE HAD SHUTDOWN. THE FCU AND FUEL PUMP WERE REPLACED. AIRCRAFT CHECKED OUT SERVICIBLE AND NO FURTHER REPORTED INCIDENCES. (TC NR 20070910008) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2007110200051 20071102 00051 WP 2007 11 2 CA070910009 1 20070907 G 3240 147515 BRAKE GRUMAN TS2 TS2ACALFORST 3951102 WP WRIGHT R1820 982C9HE2 67020 EA HAMSTD 43D 43D51 NE MLG FAILED W O OTHER O OTHER LD LANDING 1 CA 177 (CAN) ON LANDING RT BRAKE FAILED. RT BRAKE FOUND TO BE LEAKING A LARGE QUANTITY OF HYDRAULIC FLUID. BRAKE WAS REPLACED. (TC NR 20070910009) 2 H 7 2 4R 4 R A25WE E259 6 C P8879 2007110200052 20071102 00052 EU 2007 11 2 CA070911001 1 20070906 G 2435 8260123 STARTER GEN AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE NR 2 MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) AFTER DEPARTING, THE CREW OBSERVED A NR 2 GENERATOR FAULT AND THE CREW ELECTED TO RETURN TO POINT OF DEPARTURE. MA INTENANCE REPLACED THE NR 2 GENERATOR CONTROL UNIT (GCU) AN THE AIRCRAFT WAS CHECKED SERVICEABLE AN RETURNED TO SERVICE. THE PROBLEM REOCCURRED APPROXIMATELY ONE HOUR AFTER THE AIRCRAFT HAD MADE A SECOND DEPARTURE. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE NR 2 STARTER GENERATOR AND THE AIRCRAFT RETURNED TO SERVICE WITHOUT FURTHER PROBLEM REPORTED. (TC NR 20070911001) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008022500082 20080225 00082 EU 2008 2 25 CA070911002 1 20070906 G 3240 BRAKE ASSY AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE MLG LOCKED W O OTHER O OTHER LD LANDING 1 CA (CAN) DURING TOUCH DOWN THE RT MLG IB TIRE WENT FLAT. THE FAILURE WAS ATTRIBUTED TO BRAKE LOCKUP. THE AC WAS TOWED FROM THE RUNWAY. MAINT CHECKED THE NR 3 AND NR 4 POSITION BRAKE AND ANTISKID SYSTEMS WITH NO FAULT FOUND. THE NR 3 AND NR 4 W HEEL TIRE ASSEMBLIES WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070911002) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2007102600132 20071026 00132 NM 2007 10 26 CA070911003 1 20070907 G 7312 32015 VALVE BOEING 737 737217 1384464 NM PWA JT8 JT8D17 52049 NE FUEL HEAT MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) APPROXIMATELY 25 MINUTES AFTER DEPARTING, THE CREW OBSERVED THE NR 1 ENGINE OIL TEMPERATURE CLIMBING THROUGH THE Y ELLOW BAND. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE NR 1 FUEL HEAT VALVE AND CONDUCTED THE APPROPRIATE OVERWEIGHT LANDING INSPECTION BEFORE THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070911003) 2 L 7 2 4F 4 F A16WE E2EA 2007110200053 20071102 00053 NE 2007 11 2 CA070911004 2 20070827 G 7250 FW35594 TURBINE BLADES BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE HP1 FAILED W C ABORTED TAKEOFF M J OVER TEMP WARNING INDICATION TO TAKEOFF 1 CA 2693 13318 (CAN) DURING ENGINE THROTTLE FOR TAKEOFF, ISSUED (TGT-OVRTP, MAX=1146 LIMIT=900) AND ENGINE SURGE. THE PILOT THROTTLED D OWN, THE AIRCRAFT WAS RETURNED TO THE GATE AND PASSENGERS WERE UNLOADED. METAL (TURBINE BLADE PARTICLES) WERE FOUND IN THE TAILPIPE UPON VISUAL INSPECTION. ENGINE JUST BEING INDUCTED AT MFG FOR INVESTIGATION. FURTHER DETAILS WILL BE SUBMIT TED AFTER ENGINE DISSASSEMBLY. (TC NR 20070911004) 2 L 7 2 4F 4 F TR A6WE E00061EN 2007110200054 20071102 00054 NM 2007 11 2 CA070911005 1 20070906 G 2421 31708500 ADAPTER LUCAS DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE GENERATOR PULLED W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 11421 1454 874 (CAN) WHILE ENROUTE FLIGHT CREW RECEIVED A NR 1 ENGINE OIL PRESSURE LOW INDICATION AND ALSO HAD A VISUAL INDICATION OF D ECLINING OIL PRESSURE. CREW SHUTDOWN NR 1 ENGINE AND DIVERTED TO AN ALTERNATE AIRPORT. CREW DID NOT DECLARE AN EMERGENCY AND LANDED SAFELY WITHOUT FURTHER INCIDENT. MAINTENANCE TROUBLESHOOTING FOUND THAT THE AC GENERATOR ATTACH STUDS HAD PU LLED THROUGH THE ADAPTOR MOUNTING PLATE CAUSING THE AC GENERATOR TO BECOME LOOSE AND LEAK OIL. MOUNTING PLATE AND AC GEN ERATOR WERE REPLACED. ENGINE WAS SERVICED WITH OIL, FUNCTION AND LEAK CHECKS COMPLETED WITH NO FURTHER FAULTS FOUND. (TC NR 20070911005) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007102600133 20071026 00133 EU 2007 10 26 CA070911007 1 20070907 G 3240 10903000 PAD PARKER PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL BRAKE ASSY WORN W K NONE O OTHER IN INSP/MAINT 1 CA 552 1172 (CAN) PILOT REPORTED SPONGY FEELING WHEN RT BRAKE PEDAL ACTUATED. UPON FURTHER INSPECTION FOUND BRAKE WEAR PADS PREMATUR ELY WORN IN A CUPPING SHAPE BEYOND LIMITS. BRAKE ASSEMBLY REPLACED AND RETURNED TO STORES. (TC NR 20070911007) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008030600147 20080306 00147 CE 2008 3 6 CA070911008 1 20070907 G 3233 99810057652 ACTUATOR BEECH 99 99 1154002 CE PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL MLG STRIPPED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF GEAR SELECTED UP RT GEAR DID NOT COME UP. GEAR SELECTED DOWN, (3) GREEN INDICATIONS OBSERVED AC L ANDED. AC BROUGHT INTO HANGER AND PUT ON JACKS RT MLG ACTUATOR REMOVED. FOUND THAT NUT, ACTUATOR P/N 115-810029-24 HAD NO TREADS IN IT. PART SENT OUT FOR TEARDOWN REPORT (TC NR 20070911008) 1 L 7 2 3T 3 T A14CE E4EA 6 C P15EA 2007110200055 20071102 00055 CE 2007 11 2 CA070911009 1 20070830 G 5730 652230553 SKIN CESSNA 500 550 2076604 CE PWA 530 PW530A NE WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 3401 (CAN) DE-ICE BOOT REPLACEMENT AT MFG. AFTER REMOVAL OF DE-ICE BOOT NOTED AREA OF FUEL STAINING, CORROSION NOTED. DISCONT INUED BOOT REPLACEMENT, OBTAINED FERRY PERMIT AND RELOCATED AIRCRAFT. FURTHER INVESTIGATION SHOWS: SEVERAL LOCATIONS OF CORROSION DAMAGE WERE NOTED ON THE IB, LT WING, LEADING EDGE SKIN (P/N 6522305-53) BETWEEN WS 86.20 AND WS 91.00. THE D AMAGE WAS SUCH THAT THE SKIN PANEL WAS REQUIRED TO BE REPLACED. CORROSION DAMAGE WAS ALSO NOTED ON THE OB, LT WING, LEAD ING EDGE SKIN (P/N 5522300-45) BETWEEN WS 91.00 AND WS 91.50. SEE PAGE 2.1 ATTACHED FOR DAMAGE LOCATION. MFG HAS INDICAT ED OTHER SAME TYPE AIRCRAFT HAVE NEEDED SKIN REPAIRS DUE TO THE SAME TYPE CORROSION PROBLEM. THIS SEVERE CORROSION OCCUR 1 L 7 2 4F 4 F A22CE E00053EN 2007110200056 20071102 00056 WP 2007 11 2 CA070911010 2 20070829 G 7321 307080022 FUEL CONTROL BRAERO DH125 HS125700A 4230170 EU GARRTT TFE731 TFE7313R1H 29001 WP ENGINE FAULTY W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 663 P84414 (CAN) - MANUAL MODE SELECTION PROVIDES IDLE ONLY FUEL. NO SPOOL UP WITH POWER LEVER INCREASE. ENGINE FUNCTIONS NORMALL Y IN AUTO - COMPUTER (ON) MODE. (TC NR 20070911010) 2 L 7 2 4F 4 F A3EU E6WE 2007110200057 20071102 00057 NE 2007 11 2 CA070911011 2 20070910 G 7414 UNKNOWN CURTIS C46 C46DAIRLIFT SO PWA R2800 R280051M1 52026 NE HAMSTD 23E 23E50 NE ENGINE UNKNOWN W E ENGINE SHUTDOWN E VIBRATION/BUFFET CR CRUISE 1 CA (CAN) PRECAUTIONARY SHUTDOWN DUE TO ROUGH RUNNING, ENGINE RUNUP ON GROUND BY MAINTENANCE AND SUSPECT BAD MAGNETO. THE EN GINE WILL BE INSPECTED AND TIMED ACCORDINGLY. (TC NR 20070911011) 2 L 7 2 4R 4 R 3A2 5E8 6 C P603 2007110200058 20071102 00058 NE 2007 11 2 CA070911012 2 20070905 G 7260 547344P3 STUD BOEING 727 727260 138408K NM PWA JT8 JT8D17 52049 NE GEARBOX DISLODGED W E A ENGINE SHUTDOWN UNSCHED LANDING K FLUID LOSS CR CRUISE 1 CA (CAN) DURING CRUISE, THE NR 2 OIL QUANTITY SLOWLY DECREASED TO ZERO. WHEN THE OIL QUANTITY WENT BELOW THE GREEN ARC THE FLIGHT CREW SHUTDOWN THE ENGINE USING THE APPROPRIATE CHECKLIST AND AN EMERGENCY WAS DECLARED INTO AIRFIELD. THE AIRCRAF T LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE INVESTIGATED AND A STUD WAS FOUND ADRIFT FROM THE ACCESSORY DRIVE GEARBO X, FORWARD LOWER SPLIT LINE. THE THREADS WERE INSPECTED AND FOUND TO BE SERVICEABLE. THE STUD WAS REINSTALLED AND TORQUE D. THE ENGINE OIL FILTER WAS REMOVED AND INSPECTED. NO CONTAMINATION WAS FOUND AND THE OIL FILTER WAS REPLACED WITH A NE W UNIT. ENGINE GROUND RUN AND LEAK CHECK WAS CARRIED OUT AND WAS CHECKED SERVICEABLE WITH NO LEAKS. THE AIRCRAFT DEPART 2 L 7 3 4F 4 F RT A3WE E2EA 2007110200059 20071102 00059 EA 2007 11 2 CA070911013 1 20070908 G 2750 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE FAULTED W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) THE CREW RECEIVED A FLAP FAIL MESSAGE AFTER SELECTING THE FLAP TO 0 DEGREE AFTER LANDING. THE FECU TO LT BPSU WIRI NG WAS INSPECTED AND NO FAULT WAS FOUND. FECU WAS REPLACED, FUNCTIONAL TEST COMPLETED AND THE AIRCRAFT RELEASED INTO SER VICE, FOUR FLIGHTS LATER THE CREW EXPERIENCED A FLAP FAIL MESSAGE WHEN FLAP WERE SELECTED FROM 0 TO 8 DEGREES IN PREPA RATION FOR TAKE OFF. THE FECU FAULT CODE WAS AGAIN INDICATING PROBLEM WITH WIRING BETWEEN THE LT BPSU AND FECU. WIRING W AS INSPECTED AND NO FAULT WAS NOTICED. FURTHER INVESTIGATION REVEALED THAT THE RT BPSU WAS AT FAULT. R/H BPSU WAS REPLAC ED, FUNCTIONAL TEST COMPLETED AND THE AIRCRAFT RELEASED INTO SERVICE. (TC NR 20070911013) 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600149 20080306 00149 GL 2008 3 6 CA070911014 1 20070816 G 2720 2027220100 RUDDER PEDAL DIAMON DA20 DA20A1 2990000 GL ROTAX 912 ROTAX912F3 EU HOFMAN HOV352 HOV352F NE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 4050 (CAN) THE LT PILOT SIDE RUDDER CABLE PASSES THROUGH A TUBE ON THE PILOT RUDDER PEDAL. THIS TUBE WEARS AWAY DUE TO CHAFIN G AND IS UNDETECTABLE UNTIL THE CABLE HAS TOTALLY WORN THROUGH RESULTING IN BOTH PEDAL ASSY AND CABLE DAMAGE. (TC NR 200 70911014) 1 L 7 1 3O 3 O NT TA4CH E00051EN 5 C TP5BO 2007110200060 20071102 00060 EA 2007 11 2 CA070911015 2 20070907 G 8530 72877 TAPPET CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA ENGINE BROKEN W O OTHER R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CA (CAN) THE ENGINE HAS BEEN DOWN ON POWER FOR QUITE SOMETIME. UPON OVERHAUL TEARDOWN, IT WAS DISCOVERED THAT THE NR 1 AND NR 2 EXHAUST AND INTAKE TAPPET BODIES HAD BROKE. THE PIECES WERE TOO BIG TO BE DISCOVERED IN THE OIL SCREEN. (TC NR 2007 0911015) 1 H 7 1 3O 3 O NT 3A12 E274 2007110200061 20071102 00061 SO 2007 11 2 CA070912001 2 20070827 G 8520 536421 GEAR CONT O520 IO520F 17032 SO CRANKSHAFT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE TROUBLESHOOTING A STARTER PROBLEM. THE CRANKSHAFT GEAR WAS FOUND TO BE MISSING 2 TEETH. ENGINE WAS DISASSEMB LED, INSPECTED AND REPAIRED AS NECESSARY. PART OF THE MAGNETO IMPULSE CAM BROKE OFF, FELL DOWN INTO THE CRANK AND CAMSHA FT GEARS. THE GEARS JAMMED AND BROKE THE TEETH OFF. (TC NR 20070912001) 3 O E5CE 2007110200062 20071102 00062 EA 2007 11 2 CA070912002 2 20070824 G 8530 EXHAUST VALVE LYC O360 AEIO360A1E 41514 EA HARTZL HCC2Y HCC2YK4 GL ENGINE BROKEN W A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 1170 (CAN) EXHAUST VALVE BROKE AT HEAD. BROKEN PART EJECTED THROUGH EXHAUST PORT. CYLINDER/VALVES/PISTON REPLACED. NEW VALV ES ON ORDER FOR REMAINING CYLINDER. ENGINE HAS SPENT MOST OF ITS TOTAL TIME AT HIGH POWER AEROBATIC USE. (NEGLECTABLE W EAR ON PISTON CYLINDER). (TC NR 20070912002) 3 O 1E10 5 C P920 2007110200063 20071102 00063 SO 2007 11 2 CA070912003 2 20070830 G 8520 536421 GEAR CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO CRANKSHAFT DAMAGED W K NONE L NO TEST IN INSP/MAINT 1 CA 940 826612R (CAN) PILOT/OPERATOR CONVEYED A STARTING ABNORMALITY. TROUBLESHOOTING FOUND THAT TWO TEETH WERE MISSING FROM CRANKSHAFT GEAR. ENGINE REMOVED AND SENT FOR FURTHER EVALUATION AT ATC AMO NR 59-96. SEE SDR NR 20070912001 FROM AMO 59-96 FOR FUR THRER FOLLOW UP. (TC NR 20070912003) 1 H 7 1 3O 3 O A4CE E5CE 2007110200064 20071102 00064 CE 2007 11 2 CA070912005 1 20070823 G 5711 1217029 SPAR CESSNA 210 210J 2073439 CE CONT O520 IO520J 17032 SO MCAULY 3A32C D3A32C* GL WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 3225 (CAN) DURING A MAINTENANCE FUNCTION SEVERE CORROSION WAS DISCOVERED ON THE BOTTOM OF THE WING SPAR ENTRE SECTION. THIS S ECTION OF THE SPAR HAS HIGH DENSITY FOAM GLUED TO THE SPAR WHICH PREVENTS ADEQUATE INSPECTION. THE CORROSION WAS SUCH TH AT THE WING SPAR CENTRE SECTION REQUIRED REPLACEMENT. (TC NR 20070912005) 1 H 7 1 3O 3 O 3A21 E5CE 5 C P21EA 2008030600150 20080306 00150 CE 2008 3 6 CA070912007 1 20070908 G 2750 1013800002 FLEX DRIVE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE TE FLAP SEIZED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) ABOUT 2 MINUTES INTO A FLIGHT THE CREW DETECTED AN ELECTRICAL ODOR. THE PILOTS TURNED OFF THE VENT BLOWER SYS WHIC H HELPED FOR A BIT BUT NOT LONG. NO SMOKE WAS NOTICED, JUST THE ODOR. ALL OTHER NON-ESSENTIAL ELECTRICS WERE TURNED OFF. THE SMELL STAYED SO AN EMERGENCY WAS DECLARED AND THE AC PREPARED TO LAND AT ITS INTENDED AIRPORT. WHEN THE AC WAS PRE PARING TO LAND 17 DEGREES OF FLAP WAS SELECTED, THE AC INDICATOR SHOWED THAT THEY ONLY MADE IT TO 12 DEGREES. THE FLAPS WERE TRIED AGAIN AND DEEMED FAILED. THE GEAR WAS SELECTED DOWN AND THE LANDING WAS COMPLETED WITHOUT FURTHER INCIDENT. A FTER MAINT ARRIVED AND ASSESSED THE SITUATION IT WAS FOUND THAT THE LT INNER FLAP DRIVE CABLE HAD SLOWLY BOUND UP AND SE 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2007110200065 20071102 00065 GL 2007 11 2 CA070912008 2 20070910 G 7314 6899253 PUMP AEROSP AS355 AS355F2 8680812 EU ALLSN 250C 250C20F 03013 GL FUEL SYSTEM DEFECTIVE W B EMER. DESCENT R Y J PARTIAL RPM/PWR LOSS ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 3338 (CAN) ENGINE AUTO-REIGNITION ACTIVATED IN FLIGHT. REPORTS OF SOFT (BANG) PRECEEDING DECEL. INVESTIGATION REVEALED AIR IN FUEL SYSTEM, SUBSEQUENT TROUBLESHOOTING FOUND ENGINE DRIVEN FUEL PUMP DEFECTIVE. (TC NR 20070912008) 1 G 7 2 3U 3 U H11EU E4CE 2007110200066 20071102 00066 2007 11 2 CA070912009 4 20070910 G 3460 7013270936 RMU DORNER DO32 DO328100 2996000 NM FAILED W O OTHER J B WARNING INDICATION SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 7960 (CAN) ENROUTE RMU NR1 FAIL CAS MESSAGE, QRH PROCEDURES COMPLETED, THE ODOR OF ELECTRICAL FIRE/SMOKE WAS DETECTED IN THE COCKPIT. DECLARED AN EMERGENCY AND INITIATED ODOR OF SMOKE IN COCKPIT DRILL. PROCEEDED WITHOUT FURTHER INCIDENT.PAX DE PLANED AT GATE ,NORMALLY,FIRE DEPARTMENT INVESTIGATED FOR FURTHER DAMAGE. MAINTENANCE DETERMINED THAT THE RMU HAD SHORT ED INTERNALLY AND CAUSED A SMOKE ODOR IN THE COCKPIT. THE NR 1 RMU WAS DISCONNECTED AND THE CIRCUIT BREAKER PULLED AND C OLLERED.THE A/C WAS FERRY FLOWN, THE FOLLOWING DAY, A REPLACEMENT RMU IS IN TRANSIT. (TC NR 20070912009) 2 H 7 2 4T RT A45NM 2007110200067 20071102 00067 CE 2007 11 2 CA070912010 1 20070910 G 8011 MMU4001 STARTER CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA STICKING W K NONE O OTHER IN INSP/MAINT 1 CA 179 (CAN) STARTER FOUND STICKING. (TC NR 20070912010) 1 H 7 1 3O 3 O NT 3A19 E223 2007110200068 20071102 00068 EA 2007 11 2 CA070913001 1 20070910 G 2421 820465 ADG CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B1 NE LEFT UNWANTED DEPLOY W O OTHER O OTHER TO TAKEOFF 1 CA 1 (CAN) DURING TAKEOFF, AS SOON AS A/C LEFT GROUND ADG DEPLOYED. CREW DECIDED TO CONTINUE FLIGHT USING ADG DEPLOY FLIGHT P ROCEDURES. A/C LANDED WITHOUT INCIDENT. ADG AUTODEPLOY UNIT WAS FOUND TO HAVE BEEN REPLACED A FEW HOURS BACK DUE TO FAI LURE OF UNIT`S SELF TEST. THE INSTALLED SERVICEABLE REPAIRED UNIT WAS FOUND TO BE AT FAULT. UNIT WILL BE REPLACED AND A/ C RETURNED TO SERVICE. (TC NR 20070913001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600151 20080306 00151 CE 2008 3 6 CA070913002 1 20070913 G 2421 ES4118 BRUSHES CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL ALTERNATOR CONTAMINATED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 220 G104183 (CAN) EXCESSIVE GREASE WAS APPLIED TO THE REAR ROTOR BEARING DURING OVERHAUL. SOME OF IT ESCAPED AND WAS FLUNG ONTO THE BRUSHES AND SLIP RINGS, FOULING THEM AND CAUSING A BUILDUP OF GREASE AND CARBON ON THE SLIP RINGS AND BRUSH FACES. THE E LECTRICAL RESISTANCE INCREASED AND THE FIELD CURRENT WAS REDUCED TO THE POINT THAT THE ALTERNATOR WAS UNABLE TO KEEP UP WITH THE AIRCRAFT`S REQUIREMENTS. (TC NR 20070913002) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007110200069 20071102 00069 WP 2007 11 2 CA070913004 1 20070820 G 3246 NAS14651 TIE BOLT LORAL 9540512 CVAC 340 340CVAC 242270A WP ALLSN 501D 501D13D 03004 GL HAMSTD 54H 54H60 NE MAIN WHEEL MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 358 285955 (CAN) DURING DAILY INSPECTION OF AIRCRAFT, THE NR3 MAIN WHEEL ASSEMBLY WAS FOUND TO HAVE 4 MISSING TIE BOLTS. THE WHEEL ASSEMBLY WAS REPLACED WITH A SERVICEABLE UNIT, AN AXLE INSPECTION WAS CARRIED OUT AND THE AIRCRAFT WAS RETURNED TO SERVI CE. AFTER INVESTIGATION, THE OVERHAUL PROCEDURE HAS BEEN REVISED TO DISCARD TIE BOLTS AND NUTS DURING WHEEL OVERHAUL/REP AIR. THE WHEEL OVERHAUL TASK CARD HAS ALSO BEEN REVISED TO INCLUDE THIS INFORMATION. (TC NR 20070913004) 2 L 7 2 4R 4 T 6A6 E282 6 C P906 2008030600152 20080306 00152 SO 2008 3 6 CA070913005 1 20070705 G 5741 6244802 FITTING PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 4998 (CAN) ON A SCHEDULED 100 HOUR INSPECTION, BOTH THE LT AND RT LOWER COCKPIT FITTINGS THAT THE REAR WING SPARS ATTACH TO W ERE FOUND TO BE HEAVILY CORRODED. THE PARTS WERE REMOVED, THE AREA DECORRODED AS REQUIRED AND NEW FITTINGS INSTALLED. LT P/N 62448-02 AND RT P/N 62448-03. (TC NR 20070913005) 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2007110200070 20071102 00070 NM 2007 11 2 CA070913007 1 20070911 G 3234 574205A SELECTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LANDING GEAR MALFUNCTIONED W O OTHER O OTHER DE DESCENT 1 CA (CAN) IN DESCENT, THE PILOT SELECTED GEAR DOWN. THE GEAR FAILED TO EXTEND AND THE PILOT CYCLED THE GEAR 4 TIMES WITH NO RESULT, ON THE 5 CYCLE, THE GEAR EXTENDED. MAINTENANCE PLACED THE AIRCRAFT ON JACKS AND NOTED THAT WHEN GEAR EXTENSION W AS SELECTED, IT TOOK ABOUT 10 SECONDS BEFORE THE GEAR INITIATED THE COMMAND. THE LANDING GEAR SELECTOR WAS FOUND TO BE C AUSING THE DELAY, THE SELECTOR WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070913007) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008031900154 20080319 00154 EA 2008 3 19 CA070913008 2 20070911 G 7200 ENGINE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL OVERHEATED W E ENGINE SHUTDOWN M B J OVER TEMP SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION LD LANDING 1 CA 13899 459 PCE81089 (CAN) SHORTLY AFTER LANDING, THE PILOT NOTICED AN UNUSUALLY HIGH ITT INDICATION FOLLOWED BY SPARKS EXITING THE RT ENGINE . THE PILOT SHUTDOWN THE ENGINE AND CONTINUED TAXING WITHOUT FURTHER INCIDENT. FURTHER REPORT TO FOLLOW PENDING TEARDOWN REPORT. (TC NR 20070913008) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2007110200071 20071102 00071 EU 2007 11 2 CA070913009 1 20070913 G 7120 MOUNT EMB ERJ190 ERJ190100IGW 3260408 EU GE CF34 CF34* NE ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT ENGINE MOUNT. THE REVERSER THERMAL BLANKETS CONTACT THE MOUNT AND WITH ENGINE VIBRATION, CAUSE THE DAMAGE. THE MOUNT INSTALLED ON THE SPARE ENGINE SHOWED THE SAME TYPE OF DAMAGE. THE WEAR DAMAGE WAS APPROXIMATELY .080 IN TO .210 IN IN WIDTH X.600 IN LONG WITH A DEPTH OF .008 IN. THE DAMAGE WAS BEYOND LIMIT IAW THE CF34-10E ENGINE MANUAL. AT THE PR ESENT TIME NO DAMAGE LIMIT IS ALLOWED. GE IS PRESENTLY REVISING THE SITUATION. THE ROOT CAUSE HAS BEEN DETERMINED THAT THE THERMAL BLANKETS HAD NO CLEARANCE WHEN THE ENGINE COWL IS CLOSED. MFG DIDN’T DETERMINE A SOLUTION YET. (TC NR 20070 913009) 2 L 7 2 4F 4 F RT A57NM E15NE 2007110200072 20071102 00072 2007 11 2 CA070914001 4 20070912 G 3416 066030620010 ALTIMETER PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL MALFUNCTIONED W K NONE J WARNING INDICATION AP APPROACH 1 CA (CAN) DURING APPROACH THE PILOTS ENCODING ALTIMETER WAS STICKING AND THE FLAG DISPLAYED. THE ALTIMETER WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE (TC NR 20070914001) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007110500016 20071105 00016 NE 2007 11 5 CA070914002 2 20070713 G 7250 TURBINE BLADES PIAGIO P180 P180 6960204 EU PWA PT6 PT6A66 52043 NE ENGINE FRACTURED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION AP APPROACH 1 CA 104012 (CAN) THE ENGINE SHUTDOWN IN FLIGHT ON APPROACH. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070914002) 1 H 7 2 3O 4 T RT A59EU E26NE 2007110500017 20071105 00017 NE 2007 11 5 CA070914003 2 20070718 G 7320 3035466 TUBE BAG ATP ATP EU PWA PW120 PW126A NE FUEL P3 AIR FRACTURED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA (CAN) THE ENGINE SHUTDOWN UNCOMMANDED IN CRUISE. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL P3 AIR SUPPLY T UBE. (TC NR 20070914003) 2 L 7 2 4T 4 T RT A27NM E2ONE 2007110500018 20071105 00018 NE 2007 11 5 CA070914004 2 20070702 G 7200 ENGINE AYRES S2 S2RT15RESTD SO PWA PT6 PT6A15AG 52043 NE POWER LOSS W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA (CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION DURING SPRAYING OPERATIONS RESULTING IN A FORCED LANDING AND SUBSTANTIAL AIRFRAME DAMAGE. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070914004) 1 L 7 1 3T 4 T A4SW E4EA 2007110500019 20071105 00019 NE 2007 11 5 CA070914005 2 20070710 G 7323 3032490B SEAL AEROSP ATR42 ATR42* 8680900 EU PWA PW121 PW121 52124 NE O/SPEED GOVERNOR LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) THE LOW ENGINE OIL PRESSURE WARNING ACTIVATED IN CRUISE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTI ON REVEALED A LEAKING OVERSPEED GOVERNOR HIGH PRESSURE PUMP SEAL. (TC NR 20070914005) 2 H 7 2 4T 4 T RT A53EU E20NE 2007110500020 20071105 00020 NE 2007 11 5 CA070914006 2 20070709 G 7321 324485516 HMU AEROSP ATR72 ATR72201 8680943 EU PWA PW120 PW124B NE MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CLIMB FOLLOWING TAKE-OFF. SUBSEQUENT INVESTIGATION IDENT IFIED A FAULTY HYDROMECHANICAL FUEL CONTROL UNIT. (TC NR 20070914006) 2 H 7 2 4T 4 T RT A53EU E2ONE 2007110500021 20071105 00021 EA 2007 11 5 CA070914007 2 20070622 G 7250 TURBINE BLADES BELL 412 412 1182202 SW PWA PT6T PT6T3 52045 EA ENGINE FRACTURED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION NR NOT REPORTED 1 CA TH0729 (CAN) THE ENGINE COULD NOT BE RELIGHT IN FLIGHT FOLLOWING A SIMULATED ENGINE-OUT TRAINING EXERCISE. SUBSEQUENT INSPECTIO N REVEALED FRACTURED TURBINE BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 G 7 2 4U 4 U H4SW E22EA 2007110500022 20071105 00022 NE 2007 11 5 CA070914008 2 20070708 G 7321 32448716 FCU AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE ENGINE FAULTY W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION AP APPROACH 1 CA 10416 5095 (CAN) THE ENGINE LOST POWER ON APPROACH AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FAULTY MECHANICAL F UEL CONTROL UNIT. (TC NR 20070914008) 2 H 7 2 4T 4 T RT E20NE 2007110500023 20071105 00023 EA 2007 11 5 CA070914009 2 20070713 G 7200 ENGINE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION NR NOT REPORTED 1 CA FA0067 (CAN) ENGINE OIL PRESSURE REDUCED IN FLIGHT FOLLOWED BY A CHIP DETECTOR WARNING INDICATION. THE ENGINE WAS SHUTDOWN IN F LIGHT. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE TURBOMACHINE OIL SYSTEM. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070914009) 2 H 7 2 4T 4 T RT A13NM E00062EN 2007110500024 20071105 00024 NE 2007 11 5 CA070914010 2 20070717 G 7321 10078001 FCU CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE ENGINE FAULTY W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA 60 (CAN) ON TAKEOFF ROLL, THE ENGINE CONTROL FAULT LIGHT ILLUMINATED AND ENGINE POWER WOULD NOT INCREASE TO THROTTLE INPUT. THE TAKEOFF WAS ABORTED. SUBSEQUENT INSPECTION REVEALED A FAULTY FUEL CONTROL UNIT. (TC NR 20070914010) 2 L 7 2 4F 4 F RT A22CE E00053EN 2007110500025 20071105 00025 NE 2007 11 5 CA070914011 2 20070703 G 7261 ENGINE BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 118318 (CAN) ON CLIMB, THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTI ON REVEALED INTERNAL ENGINE OIL LEAKAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20070914011) 2 H 7 2 4F 4 F RT A16SW E25EA 2007110500026 20071105 00026 NE 2007 11 5 CA070914012 2 20070723 G 7200 ENGINE FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE MAKING METAL W E A ENGINE SHUTDOWN UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NR NOT REPORTED 1 CA 125236 (CAN) THE CREW OBSERVED SMOKE IN THE CABIN AND ENGINE OIL PRESSURE FLUCTUATIONS IN FLIGHT. THE ENGINE WAS SHUTDOWN IN FL IGHT. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE TURBOMACHINERY OIL SYSTEM. MFG WILL INVESTIGATE THE EVENT AND A DVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070914012) 2 H 7 2 4T 4 T RT A817 E20NE 2007110500027 20071105 00027 NE 2007 11 5 CA070914013 2 20070723 G 7320 LINE UROCOP EC135 EC135P1 8680990 EU PWC PW206C PW206C NE FUEL SYS P3 AIR CONTAMINATED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) ON TAKEOFF ENGINE POWER REDUCED UNCOMMANDED. SUBSEQUENT INSPECTION REVEALED CONTAMINATION / BLOCKAGE OF THE FUEL C ONTOL P3 AIR PRESSURE FITTING AT THE NR 8 BEARING CARBON SEAL LOCATION. (TC NR 20070914013) 1 G 7 2 3U 3 U O H88EU E42NE 2007110500028 20071105 00028 NE 2007 11 5 CA070914014 2 20070721 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE UNKNOWN W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 19278 (CAN) FOLLOWING TAKEOFF A LOUD NOISE WAS HEARD ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN ENGINE POWER. A FORCED LANDING WAS CARRIED OUT RESULTING IN AIRFRAME DAMAGE. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLIS HED. (TC NR 20070914014) 1 H 7 1 3T 3 T A37CE E4EA 2007110500029 20071105 00029 NE 2007 11 5 CA070914015 2 20070714 G 7314 PUMP AEROSP ATR42 ATR42500 8680948 EU PWA PW120 PW127 NE FUEL SYSTEM FAULTY W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA (CAN) ON TAKEOFF ROLL, THE ENGINE WAS FOUND NOT TO PRODUCE COMMANDED POWER AND THE TAKEOFF WAS ABORTED. THE ENGINE FUEL PUMP AND MFCU WERE SUBSEQUENTLY REPLACED. (TC NR 20070914015) 2 H 7 2 4T 4 T RT A53EU E20NE 2007110500030 20071105 00030 EA 2007 11 5 CA070914016 1 20070727 G 7712 311555701 TORQUE SENSOR CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE ENGINE FAULTY W E ENGINE SHUTDOWN N FALSE WARNING NR NOT REPORTED 1 CA 2231 (CAN) IN LEVEL FLIGHT, THE ENGINE LOST POWER ACCOMPANIED BY A LOUD NOISE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FAULTY TORQUE SENSOR. (TC NR 20070914016) 2 H 7 2 4T 4 T RT A14EA E20NE 2007110500031 20071105 00031 NM 2007 11 5 CA070914017 1 20070730 G 6120 CONTROL UNIT BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA PROPELLER MALFUNCTIONED W E ENGINE SHUTDOWN J WARNING INDICATION DE DESCENT 1 CA (CAN) ON LEVELING OFF FROM DESCENT, THE PROPELLER WENT TO AN OVERSPEED CONDITION AND THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT. THE ENGINE WAS SHUTDOWN IN FLIGHT. THE MFG PROPELLER ELECTRIC CONTROL, SPEED SENSOR AND ASSOCIATED E NGINE HARNESS WERE SUBSEQUENTLY REPLACED. MFG WILL MONITOR INVESTIGATION OF THESE COMPONENTS AND ADVISE OF ROOT CAUSE ON CE ESTABLISHED. (TC NR 20070914017) 2 H 7 2 4T 4 T RT A13NM E00062EN 2007110500032 20071105 00032 EU 2007 11 5 CA070914018 1 20070907 G 2997 WIRE HARNESS AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE HYD PUMP SHORTED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) DEFECT - BLUE HYDRALULIC PUMP U/S. RECTIFICATION, AC WILD BLUE PUMP WIRING SHORTED AND BURNED IN HYDRAULIC BAY DUR ING TROUBLESHOOTING OF UNSERVICEABLE BLUE HYDRAULIC PUMP. (TCNR 20070914018) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008012900032 20080129 00032 NE 2008 1 29 CA070914019 1 20070911 G 6210 6117020201 BLADE SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE MAIN ROTOR LEAKING W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 5456 (CAN) BIM WARNING LIGHT ILLUMINATED IN FLIGHT. SPAR PRESSURE WAS FOUND TO BE .25 LBS BELOW MINIMUM CHECKING PRESSURE. SP AR PRESSURE WAS SERVICED APPROXIMATELY 80 DAYS PREVIOUS. (TC NR 20070914019) 2 G 7 2 4U 4 U 1H15 1E3 2008013100047 20080131 00047 SW 2008 1 31 CA070917001 1 20070914 G 6730 30000556001 PIN BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL CYCLIC SERVO BRINELLED W K NONE O OTHER IN INSP/MAINT 1 CA 4523 2276 344 (CAN) DURING ROUTINE MAINTENANCE, FLIGHT CONTROL CHECKS REVEALED A RATCHET SENSATION DURING MOVEMENT OF SHOULDER PIN ON LT LATERAL SERVO. PIN REMOVED AND INSPECTED REVEALING INDICATIONS OF BRINELLING AND THE POSSIBILITY OF PLATING WHICH HAS BEEN ADDRESSED BY AD CF95-11 R2 ( ASB 206-95-84).SERVO AND PIN WILL BE FORWARDED FOR FURTHER INSPECTION. (TC NR 2007091 7001) 1 G 7 1 3U 3 U H2SW E4CE 2007110500033 20071105 00033 CE 2007 11 5 CA070917002 1 20070915 G 3245 302039402 TUBE GOODYEAR 650C063 CESSNA 425 425 2076018 CE PWA PT6 PT6A112 52043 NE MCAULY 4HFR34 4HFR34C762 NE TIRE DESTROYED W A UNSCHED LANDING E VIBRATION/BUFFET LD LANDING 1 CA 120 62710247 (CAN) UPON LANDING EITHER THE TIRE WAS ALREADY FLAT OR IT BLEW OUT. THE PILOT CONTROLLED THE AIRCRAFT TO A STOP WITH OUT ANY HARM TO THE AIRCRAFT. THE LT MAIN TIRE, TUBE WERE DESTROYED DURING THE ROLLOUT. NO DEFINITE CAUSE HAS BEEN DETERMIN ED TO THIS POINT, BUT THIS IS ONE OF MANY ISSUES WE HAVE HAD SINCE CHANGING AND NOW WILL BE REPLACING ALL PRODUCTS ON OU R FLEET OF AIRCRAFT. (TC NR 20070917002) 1 L 7 2 3T 3 T RT A7CE E4EA 6 C 3PNE 2007110500038 20071105 00038 CE 2007 11 5 CA070917003 1 20070827 G 3245 G156006 TUBE GOODYEAR CESSNA 425 425 2076018 CE PWA PT6 PT6A112 52043 NE MCAULY 4HFR34 4HFR34C762 NE TIRE SPLIT W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 123 42520008 (CAN) DURING GROUND HANDLING AFTER LANDING THE NOSE TIRE WAS NOTED TO BE LOW IN PRESSURE AND HISSING COULD BE HEARD FROM THE TIRE. T IRE / INNERUBE WAS DISASSEMBLED AND INNER TUBE WAS FOUND TO HAVE SMALL SPILT / CUTS AND PIN PUNCTURES IN SI DE WALLS. TORE WAS INSPECTED FOR ANOMALIES AND NONE WERE FOUND. NEW ASSEMBLIES WERE INSTALLED. (TC NR 20070917003) 1 L 7 2 3T 3 T RT A7CE E4EA 6 C 3PNE 2007110500040 20071105 00040 CE 2007 11 5 CA070917004 1 20070913 G 3244 229K482 TIRE CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE MLG OUT OF BALANCE W A UNSCHED LANDING E VIBRATION/BUFFET LD LANDING 1 CA 231 (CAN) PILOTS REPORTED VIBRATION DURING LANDING IN MAIN WHEELS. INSPECTION AND DISASSEMBLY SHOWS LT MAIN WHEEL TIRE BALAN CE PATCH IS FALLING OFF CAUSING THE MAIN TIRE TO BE IN AN UNBALANCE CONDITION. ASSEMBLY REPLACED AND NO FURTHER VIBRATIO NS NOTED. (TC NR 20070917004) 2 L 7 2 4F 4 F RT A22CE E00053EN 2007110500041 20071105 00041 EA 2007 11 5 CA070917005 1 20070913 G 2700 UNKNOWN CNDAIR CL601 CL6013A 8070802 EA MULTIPLE FAIL W O OTHER A FLAME/FIRE TX TAXI/GRND HDL 1 CA (CAN) AIRCRAFT EXPERIENCED FLAP FAILURE ON PREPARATION FOR LANDING, THEN FLEW APPROXIMATELY A FURTHER 10 MINUTES ATTEMPT ING,UNSUCCESSFULLY, TO DEPLOY THE FLAPS. ON TOUCHDOWN THE THRUST REVERSERS (TR) DID NOT DEPLOY WHEREUPON THE CREW RECYCL ED THE TR ARM SWITCH AFTER WHICH THE TRS DEPLOYED. AFTER LANDING THE AIRCRAFT WAS TAXIED TO THE RAMP AND PARKED. THE BRA KE FIRE WAS OBSERVED POST CREW AND PASSENGER DEPLANE TO ATTEND CUSTOMS. NR 2 BRAKE CAUGHT FIRE, NRS 3 AND 4 BRAKE FUSES BLEW WHILE NR 1 TIRE HELD PRESSURE. (TC NR 20070917005) 2 L 7 2 4F RT A21EA 2007110500042 20071105 00042 SO 2007 11 5 CA070917006 1 20070912 G 7603 12694002 THROTTLE CABLE PIPER PA12 PA12 7101202 SO LYC O320 O320A2B 41508 EA SNSNCH 74DM M74DM EA ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AIRCRAFT ON FLOATS. PILOT DEPARTED RIVER AND WHEN THE PILOT PULLED THE ENGINE BACK THE RPM WOULD NOT RETARD. PILOT TURNED ONE MAG OFF AND HELD THE AIRCRAFT NOSE UP TO PREVENT ENGINE OVER-SPEED AND RETURNED TO STARTING POINT. PILOT PUL LED MIXTURE WHEN HE KNEW HE COULD MAKE THE LANDING SUCCESSFULLY. THROTTLE CABLE REPLACED WITH NEW PART. (TC NR 200709170 06) 1 H 7 1 3O 3 O A780 E274 5 N P88614 2007110500043 20071105 00043 EA 2007 11 5 CA070917007 1 20070913 G 2750 1104SD100201 FLEX DRIVE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE TE FLAPS WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CREW REPORTED THAT THE FLAPS OPERATED NORMALLY ON APPROACH, WHEN SELECTED TO FLAPS 45. AFTER LANDING AND DURING TA XI, WHEN THE CREW SELECTED FLAPS 0, THEY RECEIVED A FLAP FAIL AND THE FLAPS REMAINED AT 45. CONTRACT MAINTENANCE RETRIEV ED THE CODES FROM THE FECU AND THE IDENTIFIED A POSSIBLE MISRIG OF THE BPSU. THE FLAPS WERE THEN CYCLED THREE TIMES WITH NO FAULTS FOUND, A/C WAS RETURNED TO SERVICE. BPSU RIGGING WAS CHECKED SERVICEABLE. THE A/C WAS FLOWN FOR A BEAM REPAIR AND IT WAS DECIDED THAT TASK RJ2-275002 (FLAP LUBE AND INSPECTION WOULD BE COMPLETED.) IT WAS DISCOVERED THAT LT AND RT NR 2 FLAP FLEX DRIVES WERE UNSERVICEABLE, ONE WAS WORN, THE OTHER HAD A SLIGHT KINK AND REQUIRED REPLACEMENT. BOTH WERE 2 L 7 2 4F 4 F RT A21EA E15NE 2007110500044 20071105 00044 NE 2007 11 5 CA070917008 2 20070829 G 7414 BL60064620 MAGNETO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE RIGHT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 171 (CAN) DURING START UP THE AIRCRAFT THE RT MAGNETO FAILED. MAGNETO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20070917008) 1 G 7 1 3O 3 O H11NM 1E4 2008013100048 20080131 00048 EU 2008 1 31 CA070917009 1 20070901 G 6730 SC5083 SERVO CONTROL SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE MAIN ROTOR LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 2003 (CAN) M/R SERVO REMOVED FROM RT POSITION DUE TO LEAKAGE. (TC NR 20070917009) 1 G 7 1 3U 3 U H9EU E00054EN 2007110500045 20071105 00045 EU 2007 11 5 CA070917011 1 20070417 G 2820 ST3367009 PACKING AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE FUEL MANIFOLD LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) ST3367-009 PACKINGS SUPPLIED, FOUND LEAKING AT FUEL MANIFOLD. SUSPECTED UNAPPROVED PARTS - PACKINGS MANUFACTUED / SUPPLIED WITHOUT PMA AUTHORIZATION FROM MFG. ST3367 IS A MFG PROPRIETARY SPECIFICATION. (TC NR 20070917011) 2 H 7 2 4T 4 T RT E20NE 2008022500131 20080225 00131 EA 2008 2 25 CA070917013 2 20070914 G 7322 SEAL AVIAT A1 A1B 2210406 GL LYC O360 O360A1P 42259 EA HARTZL HCC2Y HCC2YK1 GL INDUCTION SYS DISLODGED W O OTHER R PARTIAL RPM/PWR LOSS LD LANDING 1 CA 310 (CAN) ON FINAL APPROACH THE ENGINE SUDDENLY EXPERIENCED A SEVERE LOSS OF POWER WHEN CARB HEAT WAS SELECTED. DURING INSPE CTION, AFTER LANDING, A (3) INCH PIECE OF FOAM SEAL WAS FOUND LODGED IN THE CARB VENTURI. ON FURTHER INSPECTION, A CORRE SPONDING GAP WAS FOUND IN THE SEAL BETWEEN THE COWL INTAKE SCOOP AND THE INDUCTION AIR FILTER. THE REMAINING PIECES OF FOAM SEAL WERE REMOVED AND A SATISFACTORY GROUND RUN WAS CARRIED OUT. THE AC WAS RETURNED TO SERVICE. INSP OF A SECOND A C OF THE SAME MODEL DISCOVERED SIMILAR PIECES MISSING FROM THE SEAL BETWEEN THE COWL AND THE INDUCTION AIR FILTER. (TC N R 20070917013) 1 H 7 1 3O 3 O NC A22NM E286 5 C P920 2008022500133 20080225 00133 EA 2008 2 25 CA070918001 2 20070914 G 7397 476284 CIRCUIT BOARD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL FUEL COLLECTOR SHORTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) A SHORT ON THE NR 2 ENGINE FUEL COLLECTOR DRAIN PUMP CIRCUIT (TC NR 20070918001) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2007110500046 20071105 00046 WP 2007 11 5 CA070918002 1 20070916 G 5730 8398011 PANEL LKHEED 188 188A 5262602 WP ALLSN 501D 501D13 03004 GL ALLSN A6441 A6441FN606 GL LT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFTER A (WATER - FIRE SUPPRESSION) BOMBING MISSION, FUEL WAS FOUND LEAKING FROM A CRACK THAT WAS COMING FROM AN OL D REPAIR. THE A/C WAS DOWN LOADED WITH WEIGHT AND THE A/C WAS FERRIED TO THE COMPANY MAINTENANCE STATION. (TC NR 2007091 8002) 2 L 7 4 4T 4 T RT 4A22 E282 6 C P898 2007110500047 20071105 00047 NE 2007 11 5 CA070918003 3 20070917 G 6111 8173881 SEAL DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE PROP BLADE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 104 20060115 (CAN) AFTER FLIGHT, OIL LEAK NOTED FROM NR 2 PROP LEAK TRACED TO NR 2 BLADE SEAL. NR 2 SEAL REPLACED. ABRASION MARKS NOT ED ON SEALING SURFACE. (TC NR 20070918003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008030600153 20080306 00153 CE 2008 3 6 CA070918004 1 20070914 G 5340 1018200363 BRACKET BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL NLG WW BROKEN W O OTHER O OTHER AP APPROACH 1 CA 11317 (CAN) THE AC WAS ON A RETURN LEG . UPON SELECTING THE LANDING GEAR TO THE DOWN POSITION, THERE WAS NO INDICATION OF A DO WN AND LOCKED NOSE AS WELL AS THE (IN TRANSIT LIGHT) REMAINED ON IN THE GEAR HANDLE. THE CREW CARRIED OUT AN EMERGENCY L OWERING AND STILL NO DOWN AND LOCKED INDICATION FOR THE NOSE. AT THIS TIME A (FLY BY) THE TOWER CONFIRMED THE NOSE GEAR HAD EXTENDED. AN EMERGENCY LANDING WAS CARRIED OUT WITHOUT INCIDENT. MAINTENANCE DISCOVERED THAT THE BRACKET P/N 101-820 036-3, WHICH HOLDS THE NOSE LANDING GEAR DOWN, MICROSWITCH HAD BROKEN AND CAUSED THE PROBLEM. THE BRACKET WAS REPLACED W ITH A SERVICEABLE UNIT AND THE MICROSWITCH ADJUSTED. SEVERAL GEAR SWINGS WERE CARRIED OUT THE SYSTEM CHECKED SERVICEABLE 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 2008031900158 20080319 00158 EA 2008 3 19 CA070918005 2 20070907 G 8530 ST203 PISTON RING PIPER PA23 PA23250 7102308 SO LYC O540 TIO540C1A 41532 EA HARTZL HCE2Y HCE2YR2 GL CYLINDER ASSY DAMAGED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 296 104573 (CAN) THE PROBLEM STARTED WITH HIGH OIL TEMP ON LT ENG, NEAR THE RED LINE IN TURBOBOOST AND WITH SMALL SPLIT OF MANIFOLD PRESS BETWEEN BOTH ENGINES. WE TROUBLESHOOT ALL SYS REGARDING HIGH OIL TEMP AND MANIFOLD PRESS UNTIL REPLACEMENT OF TUR BO BY ITSELF BUT WITH NO CHANGE. ONLY WHAT WE FOUND WAS (2) CYLINDER WITH 65,67 OVER 80 PSID. MAKE THE DECISION TO REMOV ED THOSE (2) CYLINDER ASSY. FOUND THE COMPRESSOR RING UNPLATING AT DIFFERENT LOCATIONS. THE ENG TSO IS 864.5 AND ALL THE CYLINDERS WAS OVERHAUL AT 568.5 FOR THE SAME SITUATION, RING UNPLATING. SO WE TOOK THE DECISION TO REMOVED THE OTHER 4 CYLINDER LT ON THE ENGINE AND WE FOUND RING UNPLATING ALSO. WE REINSTALLED 6 O/H CYL ASSY ON LT ENGINE AND EVERY THING R 1 L 7 2 3O 3 O 1A10 E14EA 5 C P9EA 2008030600154 20080306 00154 SO 2008 3 6 CA070918006 1 20070822 G 2731 41234028 CONTROL CABLE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ELEVATOR TRIM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2440 317952033 (CAN) DURING AN INSPECTION OF THE ELEVATOR TRIM SYSTEM, A CRACK WAS FOUND IN THE SWAGED END OF THE TRIM CABLE. THE SWAGE D BARREL WAS CRACKED ALL THE WAY THROUGH TO THE CABLE ON ONE SIDE AND SHOWED INDICATIONS OF A CRACK ON THE OPPOSITE SIDE . THE CRACK IS APPROXIMATELY 3 INCHES LONG AND PRETTY WELL RUNS THE LENGTH OF THE SWAGE. (TC NR 20070918006) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008030600155 20080306 00155 SW 2008 3 6 CA070918007 1 20070917 G 5412 26009121 BULKHEAD AEROCD GULSTM 690TP 695A 7630519 SW GARRTT TPE331 TPE33110 01514 WP ROTOL R306 R306382F7 GL NACELLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6654 6654 (CAN) DURING WINTER MAINTENANCE, REAR NACELLE BULKHEAD FOUND CRACKED IN THE RADIUS. BULKHEAD TO BE REPLACED. (TC NR 200 70918007) 1 H 7 2 4T 4 T 2A4 E4WE 6 C P8EU 2007110500048 20071105 00048 SO 2007 11 5 CA070919001 1 20070917 G 2820 641098 TUBE PIPER PA28 PA28R201T 7102813 SO CONT O360 TSIO360F 17025 SO HARTZL HCC2Y BHCC2YF1 GL FUEL DISCHARGE BROKEN W A UNSCHED LANDING K R J FLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 650 305114 (CAN) FUEL DISCHARGE TUBE BROKE, ENGINE LOST POWER. SUSPECT MID-TUBE CLIP P/N: 626477-2 MAY HAVE FAILED FIRST. (TC NR 20 070919001) 1 L 7 1 3O 3 O 2A13 E9CE 5 C P920 2007110500049 20071105 00049 EA 2007 11 5 CA070919003 1 20070916 G 7714 311090801 PROBE DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE NR 2 TORQUE FAULTED W E ENGINE SHUTDOWN N FALSE WARNING TX TAXI/GRND HDL 1 CA (CAN) ON FIRST START OF THE DAY, THE NR 1 ENGINE OVERTORQUED TO AN UNDETERMINED VALUE. TORQUE WAS SEEN TO BE DECREASING THROUGH 70 PERCENT. IT WENT BACK TO 30 PERCENT AND THEN STARTED TO ACCELERATE AGAIN. ENGINE WAS SHUTDOWN AT 50 PERCENT T ORQUE. FDR DOWNLOADED AND READ MAX TQ EXPERIENCED ON FDR READING IS 69 PERCENTS. TROUBLESHOOTING FOUND THE NR 2 TORQUE P ROBE TO BE AT FAULT. TORQUE PROBE REPLACED ON NR1 ENGINE. GROUND RUNS COMPLETED, CHECKED SERVICEABLE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007110500050 20071105 00050 GL 2007 11 5 CA070919004 2 20070919 G 7250 23062462 RING CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C GL VANES MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 6979 CAE330181 (CAN) DURING ENGINE DISASSEMBLY IT WAS FOUND THAT 1 OFF LOCATING PLUG WAS INTERCHANGE WITH THE BOROSCOPE PLUG. THE LPT2 VANE RING IS HELD IN PLACE BY 3 LOCATING PLUGS, 2 PLUGS ONLY WERE FOUND CORRECTLY INSTALLED. LPT2 VANE RING WAS FOUND HE AVILY RUBBED ON THE TRAILING EDGE AT THE OUTER SHROUD LOCATION OVER AN ARC OF 75 DEG. APPROX.. THE INNER SHROUD LOCATION WAS ALSO FOUND HEAVILY RUBBED AT THE INNER PLATFORM LOCATION OVER THE SAME ARC DISTANCE. THE LPT2 BLADES (L/E SIDE), WA S FOUND HEAVILY RUBBED AT THE INNER AND OUTER SHROUD LOCATIONS, MATCHING THE LPT2 VANE RING RUB. THE LOCATING PLUG THAT WAS FOUND INSTALLED AT THE WRONG LOCATION WAS WORN. PREVIOUS SIMILAR EVENT HAD CAUSED A MAJOR ENGINE FAILURE AND ABORTED 2 L 7 2 4J 4 F RT T00007WI TE6CH 2008030600156 20080306 00156 2008 3 6 CA070919006 4 20070917 G 2562 200610 ANTENNA POINTER ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ELT MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 409016 (CAN) DURING A POST FLIGHT CHECK THE ELT ANTENNA CONNECTOR WAS FOUND BROKEN OFF THE ELT CASE. UPON FURTHER INVESTIGATION IT WAS ALSO NOTED THAT THE PORTABLE ANTENNA WAS MISSING. A THOROUGH SEARCH WAS CARRIED OUT FOR THE MISSING PARTS WITHIN THE AREA. NO PARTS WERE FOUND, THE ELT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070919006) 1 G 7 1 3O 3 O H11NM E295 2007110500051 20071105 00051 EU 2007 11 5 CA070919007 1 20070917 G 3213 1847L ROD BAG JETSTM JETSTM3101 1500215 EU LT MLG LEAKING W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA 1951 (CAN) ON A WALKAROUND OF THE AIRCRAFT, THE LT MLG RADIUS ROD WAS FOUND TO BE LEAKING A SIGNIFICANT AMOUNT OF MIL-5606 HY DRAULIC FLUID FROM THE PISTON SEAL AREA. THE OVERHAUL INTERVAL FOR THIS PART IS 10000 CYCLES OR 6 YEARS, AND THIS ROD WA S INSTALLED FOR ONLY 1421 CYCLES AND APPROXIMATELY 21 MONTHS. THIS RADIUS ROD WAS PURCHASED ON PO NR 1609. THIS ROD WAS REMOVED FROM SERVICE 09/18/2007 AND REPLACED WITH AN OVERHAULED UNIT. (TC 20070919007) 2 L 7 2 4T RT A21EU 2007110500052 20071105 00052 GL 2007 11 5 CA070919008 2 20070914 G 7323 SHAFT HONEYWELL BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL GOVERNOR SEIZED W E C ENGINE SHUTDOWN ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 183 19671 (CAN) WHILE THE PILOT WAS DOING HIS PREFLIGHT SYSTEM CHECKS, HE NOTICED THAT HIS GOVERNOR RANGE HAD SHIFTED DOWN FROM TH E NORMAL RANGE OF 100 PERCENT DOWN TO 97 NR ROTOR RPM. THE GOVERNOR WAS INSPECTED BY THE ENGINEER AND HE FOUND THAT THE GOVERNOR LEVER SHAFT WAS SEIZED. HE CONTINUED INSPECTING THE GOVERNOR CONTROL LINKAGE AND NOTICED THAT THE DROOP COMPENS ATION TORQUE SHAFT WAS TWISTED DO TO THE GOVERNOR SHAFT BEING SEIZED. THE GOVERNOR AND THE DROP COMPENSATION LEVER ASSEM BLY WERE REPLACED, GOVERNOR RIGGED AND BEEP RANGE SET. THE HELICOPTER WAS TEST FLOWN AND FOUND SATISFACTORY. (TC NR 2007 0919008) 1 G 7 1 3U 3 U H2SW E4CE 2007110500053 20071105 00053 EU 2007 11 5 CA070919009 1 20070918 G 3211 B00A703066A LANDING GEAR BAG JETSTM JETSTM3212 1500217 EU RIGHT MISOVERHAULED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 18944 138 (CAN) (AD)2006-0087 WAS REVIEWED AS PART OF THE NEW AIRCRAFTS BRIDGING INSPECTION. DURING REVIEW OF THIS AD IT WAS FOUN D THAT THE RT MAIN LANDING GEAR HAD BEEN REASSEMBLED AT OVERHAUL WITH THE WRONG PART NUMBER UPPER AND LOWER TOGGLES INST ALLED. THE INSTALLED UPPER TOGGLE P/N 184514 IS OF THE WRONG EFFECTIVITY FOR THIS GEAR LEG AND SHOULD BE P/N 100A703090. THE INSTALLED LOWER TOGGLE P/N 184513 IS ALSO OF THE WRONG EFFECTIVITY FOR THIS GEAR AND SHOULD BE P/N 100A703093 OR 10 1A703093. THE AIRCRAFT WILL NOT ENTER SERVICE UNTIL THIS ISSUE HAS BEEN RECTIFIED. MLG LEG S/N BADL 479 WAS OVERHAULED O N THE SECOND OF AUGUST 2006. IT WAS THEN INSTALLED ON SEPTEMBER 1 2006. THE AIRCRAFT WAS OPERATED WITH THIS GEAR FROM D 2 L 7 2 4T RT BA15CAA 2007110500054 20071105 00054 NM 2007 11 5 CA070921001 1 20070917 G 3230 483023 SEQUENCE VALVE BOMBDR DHC8 DHC8400 NM NLG FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 2763 (CAN) DURING LANDING GEAR `UP` SELECTION FOLLOWING TAKEOFF, THE NLG `RED` GEAR UNSAFE LIGHT REMAINED `ON`. CREW LOWERED THE LANDING GEAR BY ALTERNATE EXTENSION, WITH ALL LANDING GEARS INDICATING THREE GREENS GEAR SAFE, THE AIRCRAFT WAS RETU RNED TO BASE WHERE A NORMAL APPROACH AND LANDING WAS CARRIED OUT WITHOUT INCIDENT. LINE MAINTENANCE INVESTIGATION IDENT IFIED FAILURE OF THE NLG SOLENOID SEQUENCE VALVE. AFFECTED VALVE WAS REPLACED AND FOLLOWING APPROPRIATE CHECKS IAW THE A IRCRAFT`S MM THE AIRCRAFT WAS RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. (TC NR 20070921001) 2 H 7 2 4T RT A13NM 2008030600157 20080306 00157 CE 2008 3 6 CA070921002 1 20070919 G 5531 10164000033 RIB BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK FOUND IN VERTICAL STABILIZER AT RIB CSS 11.500. CRACK REPAIRED IAW SRM 51-70-17-001. CRACKED RIB REPAIR (NO N-PRESSURIZED AREA). (TC NR 20070921002) 2 L 7 2 4T 4 T RT A24CE E4EA 2007110500055 20071105 00055 NE 2007 11 5 CA070921003 2 20070921 G 8530 CYLINDER PWC DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 413 4217366 (CAN) AIRCRAFT CAME IN FOR 100 HOUR INSPECTION WITH ENGINE OIL LEAK UPPER LT SIDE. ON GROUND RUN ENGINE VIBRATION WAS E VIDENT, MAG CHECKS WERE NORMAL, ONCE COWLINGS WERE REMOVED IT WAS DISCOVERED THAT THE CYLINDER HEAD OF NR 1 CYLINDER WAS LOOSE ON THE BARREL. FURTHER INVESTIGATION REVEALED THAT THE CYLINDER HEAD HAD COMPLETELY SEPARATED FROM THE CYLINDER B ARREL. ASSY WAS REMOVED AND REPLACED WITH SERVICEABLE CYLINDER ASSY. (TC NR 20070921003) 1 H 7 1 3R 3 R RC A806 5E1 2008012900033 20080129 00033 GL 2008 1 29 CA070921004 1 20070921 G 7160 SEAL AVIAT A1 A1B 2210406 GL LYC O360 O360A1P 42259 EA HARTZL HCC2Y HCC2YK1 GL INDUCTION SYS LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) REFERENCED TO SDR NR 20070917013 AFTER FINDING COWLING SEAL LODGED IN THE CARB VENTURI. THE PILOT/OWNER OF THIS AI RCRAFT WAS REQUESTED TO CHECK THE CONDITION OF THE COWLING SEAL, IT WAS FOUND TO BE LOOSE AND DETERIORATED AS WELL. ALL OF THE SEAL WAS REMOVED FROM THE COWLING. (TC NR 20070921004) 1 H 7 1 3O 3 O NC A22NM E286 5 C P920 2007110500056 20071105 00056 NM 2007 11 5 CA070921005 1 20070919 G 3251 SJ5049172 SWIVEL MENASCO BOMBDR DHC8 DHC8402 1390042 NM MANIFOLD LOOSE W O OTHER K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 2007 MAL0178 (CAN) FLIGHT CREW NOTICED A PUDDLE OF FLUID AROUND THE NLG WHILE DOING A WALK AROUND. MAINTENANCE REPORTED THAT THE JAMB NUT FOUND ON THE STEERING MANIFOLD PRESSURE AND RETURN LINE WERE LOOSE. TIGHTEN JAMB NUTS. (TC NR 20070921005) 2 H 7 2 4T RT A13NM 2007110500057 20071105 00057 EA 2007 11 5 CA070924001 2 20070924 G 7314 RG9080JAM PUMP PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL FUEL SYSTEM WEAK W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA (CAN) RT ENGINE DRIVEN PUMP WEAK. (TC NR 20070924001) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008013100049 20080131 00049 WP 2008 1 31 CA070924002 1 20070911 G 6320 369D2512311 DRIVE GEAR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20 03013 GL M/R TRANSMISSION BROKEN W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA 594 (CAN) MAIN ROTOR TRANSMISSION REMOVED DUE TO CHIP LIGHT ILLUMINATION. TRANSMISSION RETURNED TO HELICOPTERS COMPONENT OVE RHAUL SHOP FOR REPAIR. UPON DISMANTLE IT WAS DISCOVERED THAT THE I/P GEAR HAD FAILED AND EXHIBITED ONE COMPLETE TOOTH BR OKEN OFF FROM THE GEAR. (TC NR 20070924002) 1 G 7 1 3U 3 U H3WE E4CE 2007110500058 20071105 00058 NM 2007 11 5 CA070924004 1 20070915 G 5610 8SC0043013 WINDSHIELD DHAV DHC8 DHC8* NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE COCKPIT BROKEN W O OTHER O OTHER CR CRUISE 1 CA 25492 (CAN) AN AIRCRAFT WAS CRUISING AT 23,000 FT WHEN THE LHS WINDSCREEN SHATTERED. THE OPERATOR BELIEVES THE HEATING ELEMENT FUSED, CREATING A HOT SPOT AND SHATTERING THE OUTER GLASS PAIN OF THE WINDSCREEN. LHS WINDSHIELD REPLACED AND THE AIRCR AFT RETURNED WAS TO SERVICE. (TC NR 20070924004) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007110500059 20071105 00059 EA 2007 11 5 CA070924005 1 20070924 G 2710 FITTING BOMBDR DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL CONTROL CABLE MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) NEW AILERON CABLE P/N JNL-C6CF1125-3 FROM JNL (W.O. 091) THE CSP FITTING ON IT MEASURES .4405. THE CSP FITTING WIL L NOT ENGAUGE INTO THE RECEPTICAL ON THE QUADRANT. THE CABLE REMOVED MEASURES .4310. (TC NR 20070924005) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2007110500065 20071105 00065 EU 2007 11 5 CA070924006 1 20070923 G 2910 O-RING AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE PTU MANIFOLD FAILED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) FOLLOWING A YELLOW HYDRAULIC SYSTEM FAILURE, THE AIRCRAFT SUBSEQUENTLY EXPERIENCED A GREEN HYDRAULIC SYSTEM FAILUR E, AND DIVERTED BACK TO DEPARTURE POINT. THE FLIGHT DECLARED AN EMERGENCY, AND LANDED 4000 KG OVERWEIGHT. AFTER LANDING, A NR 1 AND 3 BRAKE FIRE WAS ENCOUNTERED, WHICH WAS EXTINGUISHED BY CFR. THE AIRCRAFT WAS TOWED TO THE HANGAR. THE YELLO W SYSTEM WAS WORKED ON THE 18TH, AND A CHECK VALVE PACKING WAS REPLACED FOLLOWING AN INFLIGHT PRESSURE LOSS. (TC NR 200 70924006) 2 L 7 2 4F 4 F RT A28NM E29NE 2007110500066 20071105 00066 EA 2007 11 5 CA070924007 1 20070924 G 2710 FITTING DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL CONTROL CABLE DAMAGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) NEW AILERON CABLE P/N JNL-C6CF1153-3 FROM JNL (W/O 022. THE CSP FITTING MEASURES .4405. THE CSP FITTING WILL NOT E NGAUGE INTO THE AILERON QUARDRANT. ORIGINAL CABLE CSP FITTING MEASURES .4320 (TC NR 20070924007) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2008030600158 20080306 00158 GL 2008 3 6 CA070925001 1 20070922 G 3246 138892629 CONE BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP NLG BEARING CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 315 315 (CAN) TO COMPLY WITH SB 100-32-10 (NLG REPLACEMENT OF THE LOCKING SEGMENT WITH A LOCKING COLLAR) BOTH NOSE WHEEL ASSY. W ERE REMOVED TO GAIN ACCESS, CORROSION WAS FOUND ON ALL BRG CONES AND ON ALL BEARING CUPS. THE AXLE WAS ALSO FOUND TO HAV E CORROSION AND WAS REMOVED AND REPLACED. (2) SERVICEABLE NOSE WHEEL WERE ALSO INSTALLED. SINCE NO CAUSE WAS FOUND TO BE THE ROOT OF THE PROBLEM, THE OTHER CHALLENGER 300 SN 20107 303.3 TTSN FROM OUR FLEET WAS ALSO INSPECTED FOR CORROSION. THE LT NOSE WHEEL ASSY. WAS FOUND TO HAVE HEAVY BRG CONE AND CUP CORROSION. THE BRG CONE HAD TO BE DESTROYED TO REMOVE I T FROM THE AXLE. THE AXLE WAS INSPECTED AND FOUND SERVICEABLE. NO NOSE WHEEL ASSY HAD BEEN REPLACED SINCE BOTH AC HAD BE 2 L 7 2 4F 4 F RT T00005NY E00010LA 2007110500067 20071105 00067 NE 2007 11 5 CA070925002 2 20070925 G 8550 ENGINE DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) ENGINE LEAKING EXCESSIVE OIL OUT OF GENERATOR DRIVE. ENGINE CASE FILLING WITH OIL. (TC NR 20070925002) 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2007110500068 20071105 00068 EA 2007 11 5 CA070925003 1 20070923 G 3230 46193 PRIORITY VALVE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE MLG FAILED W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF THE FOLLOWING MESSAGES WERE DISPLAYED IN THE COCKPIT: STEERING INOP, GEAR DISAGREE, W.O.W. SENSOR FA ILURE AND W.O.W. STATUS. NOSE GEAR REMAINED IN DOWN POSITION WITH MAIN GEAR RETRACTED. AIRCRAFT TURNED-BACK AND LANDED U NEVENTFULLY. MAINTENANCE REPLACED THE MLG PRIORITY VALVE AND THE ELECTRIC MOTOR DRIVEN PUMP HYDRAULIC SYSTEM 3B (P/N 848 847), FOLLOWED BY SUCCESSFUL GEAR SWINGS. 2 L 7 2 4F 4 F RT A21EA E15NE 2007110500069 20071105 00069 CE 2007 11 5 CA070926001 1 20070924 G 7712 3012347 VALVE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL TORQUE METER WORN W O OTHER S AFFECT SYSTEMS TX TAXI/GRND HDL 1 CA PCE32270 (CAN) FOUND WORN TORQUE METER VALVE IN POWER SECTION OF ENGINE GIVING ERRATIC ENGINE TORQUE INDICATION AT COCKPIT INDICA TOR. VALVE REPLACED. NO OTHER PROBLEMS NOTED. (TC NR 20070926001) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2008030600159 20080306 00159 SW 2008 3 6 CA070926002 1 20070726 G 7930 206075187003 INDICATOR BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL ENG OIL PRESS FLUCTUATES W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) THE AC WAS DEPARTING FROM BASE WHEN IT WAS NOTICED THAT THE ENGINE OIL PRESSURE INDICATOR WAS FLUCTUATING. THE PIL OT RADIO A PAN TO ATC AND DID A PRECAUTIONARY LANDING. NO INCIDENT ON LANDING. THE ENGINEER WAS DISPATCHED TO THE LANDIN G SITE AND IT WAS DETERMINED THAT THE INDICATOR WAS AT FAULT. REPLACED INDICATOR (TC NR 20070926002) 1 G 7 1 3U 3 U H2SW E1GL 20080520 CE 2008 5 20 CA070927001 1 20070831 G 3246 4040A WHEEL CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO HARTZL HCC3Y PHCC3YF2 GL RT MLG BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING MAINT THE RT MAIN WAS FOUND WITH PART OF THE BEAD MISSING, PILOT SAID THE WHEEL WAS OK PRIOR TO DEPARTURE A ND LANDING NORMAL. TOWER ADVISED AND CREW SENT OUT FOR INSP, NO PIECES FOUND. (TC NR 20070927001) 1 L 7 2 3O 3 O 3A10 E5CE 5 C P25EA 2007110500076 20071105 00076 EU 2007 11 5 CA070927002 1 20070924 G 2434 GCU AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE NR 2 GENERATOR FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 813133 (CAN) AFTER DEPARTURE, THE CREW OBSERVED A NR 2 DC GENERATOR TRIP. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDE D WITHOUT FURTHER DIFFICULTY. MAINTENANCE REPLACED THE NR 2 GENERATOR CONTROL UNIT AND THE AIRCRAFT WAS RETURNED TO SERV ICE AFTER SATISFACTORY GROUND RUN. (TC NR 20070927002) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2007110500077 20071105 00077 EU 2007 11 5 CA070927003 1 20070925 G 3220 A1029E BOLT BAG JETSTM JETSTM3101 1500215 EU GARRTT TPE331 TPE33110UG 01514 WP MCAULY 4HFR34 4HFR34C652 NE NLG SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION IAW AD 024-05-87 BAE SB 53-A-JA870510R1 PART B, IT WAS NOTED THAT THE TWO UPPER BOLTS WERE SHEAR ED. THE AIRCRAFT WAS REMOVED FROM SERVICE AT THIS TIME. THE LOWER 2 BOLTS HAVE NOT YET BEEN REMOVED FOR INSPECTION. DU E TO THIS FINDING AND THE POSSIBLE SAFETY RISK, HAVE ELECTED TO CARRY OUT A DVI OF THE NLG RETRACT JACK ATTACH FITTINGS FOR THE REMAINING J-3112`S IN OUR FLEET. NO OTHER DEFECTS WERE FOUND. EVALUATING WHAT CHANGES TO THE INSPECTION FREQUENC Y AND POSSIBLE BOLT LIFE LIMITS MAY BE REQUIRED. REMAINING BOLTS AND SURROUNDING STRUCTURE WILL BE INSPECTED TODAY, A R EPORT WILL FOLLOW. (TC NR 20070927003) 2 L 7 2 4T 4 T RT A21EU E4WE 6 C 3PNE 2008011400202 20080114 00202 WP 2008 1 14 CA070927004 2 20070926 G 7261 307481812 LINE RAYTHN 850 HAWKER850XP 7150016 CE GARRTT TFE731 TFE7315BR WP ENGINE CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 307 307 (CAN) DURING SCHEDULE INSPECTION FOUND 2 OIL LINES CHAFING. THE SAME PROBLEM WAS ON BOTH ENGINES.THE PROBLEM COMES FROM THE FACTORY SINCE THE AIRCRAFT IS NEW AND LOW TIME. THE AIRCRAFT HISTORY DOES NOT SHOW ANY MAINTENANCE ACTION BEING PERF ORMED IN THAT AREA SINCE THE AIRCRAFT WAS DELIVERED NEW AND IS STILL UNDER WARRANTY. LINE PN 3074818-1 AND PN 3072083-2 (BOTH ENGINES ARE TFE731-5BR SERIES) (TC NR 20070927004) 1 L 7 2 4F 4 F RT A3EU E6WE 2007110500078 20071105 00078 SO 2007 11 5 CA070927005 2 20070926 G 7414 36066 GEAR DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA MAGNETO LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 155 07032007 (CAN) FOLLOWING A 50HR OIL CHANGE, IT WAS NOTED THE AC WAS VERY DIFFICULT TO START TO CARRY OUT THE REQUIRED LEAK CHECK. TROUBLESHOOTING REVEALED A DEFECTIVE MAGNETO. WHEN THE MAG WAS REMOVED IT WAS NOTED THAT THE DRIVE GEAR P/N 36066 WAS L OOSE ON THE DRIVE GEAR SUPPORT CASTING (P/N N/A). UPON REMOVAL OF THE NUT P/N M3019 IT WAS NOTED THAT A AN960-616L WASHE R WAS NEXT TO THE GEAR, AND BEHIND THE LARGE P/N M3172 WASHER. THIS INSTALLATION SEQUENCE WOULD NOT ALLOW FOR SUFFICIENT CLAMP UP OF THE P/N M3172 WASHER NEXT TO THE P/N 36066 DRIVE GEAR, AND OVER TIME WOULD LEAD TO THE LOOSENESS ENCOUNTERE D. THE MAGNETO WAS REPLACED AND THE WASHER INSTALLATION REVERSED, WITH THE AN 960-616L WASHER PLACED NEXT TO THE NUT. TH 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2007110500079 20071105 00079 SO 2007 11 5 CA070927006 2 20070926 G 7414 36066 GEAR DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA MAGNETO LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 132 07032004 (CAN) THE AIRCRAFT WAS HARD TO START WITH NO APPARENT REASON. AFTER TROUBLESHOOTING, A HARD STARTING PROBLEM ON ONE OTHE R A/C IN THE FLEET AND FINDING A LOOSE DRIVE GEAR ON THE LT MAG IT WAS DECIDED TO CHECK THIS A/C FOR A SIMILAR PROBLEM. THE LT MAG WAS REMOVED AND IT WAS NOTED THAT THE MAG DRIVE GEAR WAS LOOSE AS WAS THE CASE WITH THE OTHER A/C. (REFER: SD R 9/27/07 C-FNTJ) THE GEAR P/N 36066 AND WASHER P/N M3172 WERE REMOVED AND INSPECTED. AS WITH THE OTHER A/C IT WAS NOTED THAT A AN960-616L WASHER HAD BEEN PLACED ON THE BACKSIDE OF THE M3172 WASHER AND NEXT TO THE 36066 GEAR, RESULTING IN I NSUFFICIENT CLAMP UP OF THE GEAR. THE GEAR WAS REASSEMBLED TO THE MAG WITH THE WASHER POSITIONS REVERSED AND THE NUT RET 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2007110500080 20071105 00080 GL 2007 11 5 CA070927007 2 20070905 G 7230 STATOR VANE ALLSN HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL COMPRESSOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 389 CAC30263F (CAN) NR 6 STATOR VANE FAILURE (1 VANE ONLY). NO EROSION TO NEIGHBORING VANES OR PLASTIC COATING. FOUND BY HELICOPTER OP ERATOR. (TC NR 20070927007) 1 G 7 1 3U 3 U H3WE E4CE 2007110500081 20071105 00081 GL 2007 11 5 CA070928001 2 20070831 G 7230 23057142 STATOR VANE ALLSN HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL COMPRESSOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 389 CAC30263F (CAN) PILOT REPORTS UNUSUAL NOISE COMING FROM AIRCRAFT DURING GROUND RUN. AIRCRAFT IS GROUNDED UNTIL ENGINEER INVESTIGA TES THE UNUSUAL NOISE. NOISE IS DESCRIBED AS A (KNOCKING NOISE COMING FROM THE ENGINE) AND TOT HOTTER THAN USUAL. DURING THE GROUND RUN THE EXACT SYMPTOMS WERE DUPLICATED. THE ENGINEER DISASSEMBLED THE ENGINE TO FIND THE 6TH AXIAL ROW OF ST ATORS IN THE COMPRESSOR HAD A MISSING BLADE. BOTH COMPRESSOR AND TURBINE WERE SENT INTO THE ENGINE SHOP FOR REPAIR. ENGI NE REPAIR SHOP ALSO FILED SDR REPORT. (TC NR 20070928001) 1 G 7 1 3U 3 U H3WE E4CE 2007110500082 20071105 00082 NE 2007 11 5 CA070928002 2 20070927 G 7261 6087T04P05 SCAVENGE PUMP CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE NR 1 ENGINE OIL FLUCTUATES W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 25148 25148 (CAN) SHORTLY AFTER TAKEOFF THE NR ONE ENGINE OIL HIGH TEMPERATURE/LOW PRESSURE CAUTION LIGHT CAME ON. FLIGHT RETURNED T O DEPARTURE AIRPORT. FLIGHT LANDED APPROX 1000 POUNDS OVERWEIGHT. NO EMERGENCY DECLARED BUT EMERGENCY VEHICLES ON STANDB Y. MAINTENANCE TROUBLESHOOTING DRAINED 1 LITER OF OIL FROM OIL TANK, INSPECTED OIL PRESSURE AND TEMPERATURE WIRE HARNESS ES AND COMPLETED GROUND ENGINE RUNS. OIL PRESSURE SLOW TO RISE ON START. OIL TEMP ROSE 1 EVERY 2 SECONDS. TEMPERATURE RO SE TO 156 WITH YELLOW CAUTION. FUEL FLOW ALSO FLUCTUATING. AFTER GROUND RUN FOUND OIL OVER SERVICED AGAIN. AGB FOUND WIT H 5 LITERS OF OIL, SHOULD HAVE ONLY .75 LITERS. NR 1 LUBE/SCAVENGE OIL PUMP REPLACED AND OIL SYSTEM ADJUSTED TO CORRECT 2 L 7 2 4F 4 F RT A21EA E15NE 2007110500083 20071105 00083 SO 2007 11 5 CA070928003 1 20070921 G 8120 LW16840 CONTROLLER PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL ENGINE LEAKING W A UNSCHED LANDING K R FLUID LOSS PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 6890550 (CAN) DURING TAKEOFF A VIBRATION AND LOW EGT WAS FELT ON THE LT ENGINE. TAKEOFF POWER WAS STILL ACHIEVED FOR THE FLIGHT. THE AIRCRAFT RETURNED TO LAND. BOTH THE DENSITY AND DIFFERENTIAL CONTROLLERS WERE FOUND TO HAVE OIL LEAKS. THE OIL WOUL D CONTAMINATE THE AIR PASSAGES IN THE FCU AND CAUSE THE LOSS OF POWER AND VIBRATION. THE CONTROLLERS WERE REPLACED AND R UNUPS COMPLETED WITH NO FURTHER PROBLEMS. (TC NR 20070928003) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008030600160 20080306 00160 GL 2008 3 6 CA070928004 2 20070925 G 7311 369D25623 BELT HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL OIL COOLER WORN W E A ENGINE SHUTDOWN UNSCHED LANDING E VIBRATION/BUFFET AP APPROACH 1 CA 800 HL8615 (CAN) ON LANDING, THE PILOT FELT A STRANGE VIBRATION. AFTER LANDING, THE AC WAS GROUNDED PENDING MAINTENANCE TROUBLESHOO TING. A CLOSE INSP WAS COMPLETED AND DETERMINED TO BE A LOOSE COOLER BELT CAUSING EXCESSIVE VIBRATION AT 100 PERCENT. THE BELT WAS REPLACED SHIMED PROPERLY AND GROUND RUN AND FLIGHT TEST COMPLETED. (TC NR 20070928004) 1 G 7 1 3U 3 U H3WE E4CE 2007110500091 20071105 00091 NE 2007 11 5 CA071001001 2 20070909 G 7250 FW35594 TURBINE BLADES BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE ENGINE FAILED W C ABORTED TAKEOFF M J OVER TEMP WARNING INDICATION TX TAXI/GRND HDL 1 CA 3091 13218 (CAN) DURING ENGINE THROTTLE FOR TAXI OVERTEMP SIGNAL, AIRCRAFT ABORTED TAKEOFF. VISUAL INSPECTION REPORTED METAL IN TAI L PIPE, SUSPECT HP 1 TURBINE BLADE FAILURE. FURTHER INFORMATION WILL BE SUBMITTED AFTER ENGINE TEAR DOWN. ENGINE BEING I NDUCTED AT RRC. (TC NR 20071001001) 2 L 7 2 4F 4 F TR A6WE E00061EN 2008030600161 20080306 00161 SW 2008 3 6 CA071001002 1 20070712 G 2820 206063607101 TUBE BELL 206 206L4 1182110 SW FUEL SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) HELICOPTER DEVELOPED FUEL LEAK SITTING IN HANGER. BONDING MATERIAL BETWEEN ALUMINUM FLANGE AND RUBBER TUBE IS ALMO ST NON-EXISTENT. THE RUBBER ALSO SEEMS TO HAVE SWELLED. (TC NR 20071001002) 1 G 7 1 3U NC H2SW 2007110500092 20071105 00092 EA 2007 11 5 CA071001003 1 20070929 G 3310 18271 POWER SUPPLY DHAV DHC6 DHC6300 2802606 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE COCKPIT LIGHTS DAMAGED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 7521 (CAN) DURING CRUISE, THE INTERNAL COCKPIT LIGHTING WAS SWITCHED ON, OVERHEAD PANEL LIGHTS DID NOT ILLUMINATE. OVERHEAD P ANEL LIGHT CIRCUIT BREAKER WAS OBSERVED AS TRIPPED. CIRCUIT BREAKER WAS RESET. A FEW MINUTES LATER A SUSPECTED ELECTRICA L BURNING SMELL WAS OBSERVED. F/A 1 WAS CONTACTED AND ASKED TO COME TO THE FLIGHTDECK. F/A 1 CONFIRMED THE SMELL AND ST ATED IT WAS STRONGER NEAR THE WARDROBE. QRH ACTIONS FOR FIRE/SMOKE UNKNOWN SOURCE WERE CARRIED OUT. A UNSCHEDULED LANDIN G COMPLETED. ENGINEERING INVESTIGATION REVEALED THAT THE NR 2 DC POWER SUPPLY EXHIBITED SIGNS OF OVERHEATING, AND DAMAGE DUE TO POSSIBLE EXCESSIVE CURRENT DRAW. UNIT ALSO HAD STRONG BURNED SMELL. THE NR 2 DC POWER SUPPLY WAS REPLACED IAW TH 1 H 7 2 3T 4 T RT A9EA E20NE 6 C P7NE 2007110500093 20071105 00093 NM 2007 11 5 CA071001004 1 20070930 G 2612 285T03855 WARNING SYSTEM BOEING 767 767328 1385290 NM GE CF6 CF680C2B6F 30025 NE FIRE/OVERHEAT NO TEST W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) DURING DAILY CHECK AN OPERATIONAL CHECK OF AUTOMATIC FIRE/OVERHEAT LOGIC TEST SYSTEM WAS CARRIED OUT AND WAS DISCO VERED THAT AURAL WARNING IS INOPERATIVE. SYSTEM BELL AND CHIME MODULE REPLACED AND SYSTEM FUNCTION CHECKED SERVICEABLE. (TC NR 20071001004) 2 L 7 2 4F 4 F RT A1NM E13NE 2007113000091 20071130 00091 EU 2007 11 30 CA071001005 2 20070928 G 7230 RK49612 IMPELLER BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU ENGINE DAMAGED W E F A ENGINE SHUTDOWN ACTIVATE FIRE EXT. UNSCHED LANDING A X T FLAME/FIRE ENGINE FLAMEOUT ENGINE CASE PENETRATION CL CLIMB 1 CA 4842 4842 14796 (CAN) WHILE ON CLIMB AFTER DEPARTING, THE WAS A BANG FROM THE RT ENGINE, TOTAL LOSS OF POWER AND FIRE WARNING. THE FWD P ART OF THE ENGINE WAS SEEN TO BE ON FIRE, WHICH WAS EXTINGUISHED BY (2) SHOTS OF THE EXTINGUISHER SYSTEM. THE AIRCRAFT R ETURNED TO DEPARTURE AND MADE AN EMERGENCY LANDING WITH NO FURTHER INCIDENT. INSPECTION REVEALED THAT THE LP IMPELLER CA SING WAS PUNCTURED IN SEVERAL PLACES AROUND ITS EDGE. THE COWLINGS WERE ALSO SEVERELY DAMAGED BY THE FIRE. THIS ENGINE W ILL BE RETURNED TO MFG FOR INVESTIGATION. 2 L 7 2 3T 4 T A24EU A196 6 C P899 2007110500094 20071105 00094 GL 2007 11 5 CA071001006 2 20070621 G 7250 23037413 SHAFT BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE CRACKED W O OTHER K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 232 CAT40248 (CAN) POWER TURBINE ACTION DISMANTLED TO DETERMINE CAUSE OF OIL CONSUMPTION AND SMOKING. UPON TEARDOWN AND DETAIL INSPEC TION IT WAS NOTED THAT THE PT OUTER SHAFT HAD A LARGE CRACK ORIGINATING AT ROOT OF 1 CURVIC COUPLINGS AND SPLITTING INTO 2 FURTHER DOWN SHAFT. CRACKING AND MATERIAL DAMAGE TO CURVIC RESULTED IN LOSS OF 1 OF CURVICS WHICH WAS NOT RECOVERED. FRETTING DAMAGE IS ALSO OBSERVED ON MATING CURVICS OF 3RD AND 4TH STAGE WHEELS. REPORTED OIL CONSUMPTION AND SMOKING ASS OCIATED WITH THIS TURBINE LIKELY RESULT OF OIL AND OIL MIST MOVING THROUGH TIGHT FIT OF PT INNER AND OUTER SHAFT. NORMAL TIGHT FIT BETWEEN THESE COMPONENTS WOULD HAVE BEEN AFFECTED BY CRACKING OF OUTER SHAFT RESULTING IN OIL FLOW ACROSS THI 1 G 7 1 3U 3 U H2SW E4CE 2007110500095 20071105 00095 EA 2007 11 5 CA071001007 1 20070928 G 5200 33130131 PISTON CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 AWASP 52016 NE HAMSTD 43E 43E60 NE WATER DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE DOING A C CHECK OUR NDT CONTRACTOR ADVISED US THAT HE HAS BEEN FINDING CRACKS IN THIS AREA WHILE WORKING FOR OTHER CUSTOMERS. WE ARE CHECKING THE REST OF OUR FLEET AS THIS FAILURE WOULD RESULT IN A UNCOMMANDED BOMB DOOR OPENING. 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 2008031900160 20080319 00160 2008 3 19 CA071001008 4 20070919 G 3457 GPS430WX2 GPS FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE COCKPIT FAILED W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA 2 (CAN) ON APPROACH, THE GPS430W UNITS INDICATED A DISTANCE OF 30 MILES WHICH THEN, SUDDENLY CHANGED TO AN INDICATED DISTA NCE OF (2) TO (3) MILES CAUSING A LOSS OF CREW SITUATION AWARENESS. THE APPROACH WAS ABORTED. MFG WAS CONTACTED AND INFO RMED OF THE PROBLEM. MFG REPLIED, STATING THE ERROR WAS CAUSED BY THE SOFTWARE VERSION IN USE WHICH WOULD BE CORRECTED A SAP. A COPY OF THE PILOT`S REPORT IS ENCLOSED. (TC NR 20071001008) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2008030600162 20080306 00162 SO 2008 3 6 CA071001009 1 20070907 G 3210 4028400 BRACE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL MLG BROKEN W O OTHER O OTHER LD LANDING 1 CA 12435 (CAN) ON LANDING THE LT MLG COLLAPSED. UPON INSPECTION IT WAS DETERMINED THAT THE MLG LOWER SIDE BRACE LINK ASSY HAD FA ILED AT THE AFT HOLE CONTAINING MLG LOCK PIN. THE LOCK PIN WAS GONE AND UNABLE TO LOCATE. MLG SIDE BRACE PN 40284-00 ML G P/N 40376-00 (TC NR 20071001009) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008030600163 20080306 00163 SW 2008 3 6 CA071001010 1 20070922 G 6410 206310105101 BEARING RACE BELL BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL T/R BLADE CRACKED W A UNSCHED LANDING O OTHER HO HOVERING 1 CA 1737 764 CS12475 (CAN) PILOT REPORTED AN INCREASE OF FORCE REQUIRED TO PUSH THE T/R PEDALS AT 100 PERCENT RPM WHICH EXCEEDED THE OPERATIO NAL LIMITS. HOWEVER, AT ZERO RPM THE FORCE WAS NORMAL. IT WAS DETERMINED THAT THE CAUSE WAS ASSOCIATED WITH THE T/R FEA THERING BEARINGS. INSPECTION SHOWED THAT THE BEARINGS ALTHOUGH SOMEWHAT WORN DID NOT HAVE EXCESSIVE WEAR. FURTHER INSP ECTION FOUND THAT ONE OF THE IB BEARINGS HAD A CRACKED INNER RACE RUNNING FULL LENGTH PARALLEL TO IT`S AXIS. THE BEARIN G IS THE ORIGINAL BEARING INSTALLED BY THE MFG. INSTALLATION OF NEW T/R BLADES RECTIFIED THE EXCESSIVE T/R FORCE AT 100 PERCENT RPM DEFECT. (TC NR 20071001010) 1 G 7 1 3U 3 U H2SW E1GL 2007110500105 20071105 00105 EA 2007 11 5 CA071001011 2 20070715 G 7240 310926302 DUCT PWC PT6A34 DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 4180 RB0196 (CAN) WHILE PERFORMING A BOROSCOPE INSPECTION DURING A REGULARLY SCHEDULED FUEL NOZZLE CHANGE, DAMAGE WAS FOUND ON THE L ARGE EXIT DUCT (LED). THE LED WAS CHANGED AND UPON CLOSER INSPECTION IT WAS FOUND THAT A LARGE HOLE HAD BEEN BURNED THRO UGH ONE LAYER OF THE DUCT. A CRACK THAT TRAVELED APPROXIMATELY .2500 OF THE CIRCUMFERENCE OF THE OUTER PORTION OF THE LE D WAS ALSO NOTICED. (TC NR 20071001011) 1 H 7 1 3R 4 T A815 E4EA 6 C P15EA 2007110500107 20071105 00107 GL 2007 11 5 CA071001012 2 20070928 G 7200 ENGINE EMB 135 EMB135ER 3260203 SO ALLSN AE300 AE3007A GL NR 1 MAKING METAL W B EMER. DESCENT Y J ENGINE STOPPAGE WARNING INDICATION AP APPROACH 1 CA 16065 CAE311496 (CAN) N13992/145284 ENGINE NR 1 (A1P, CAE311496) EXPERIENCED AN UNCOMMANDED INFLIGHT SHUTDOWN ON APPROACH TO EWR FROM ME M, FLIGHT 2144, ON 27 SEP. THE CREW OBSERVED AN ENG 1 OUT MESSAGE ON THE EICAS DURING FINAL APPROACHED AND ATTEMPTED AN UNSUCCESSFUL RESTART. UPON SAFE LANDING, MAJOR AMOUNTS OF METAL CHIPS AND FLAKES WERE FOUND ON BOTH OIL TANK MCDS WITH L IGHT AMOUNTS OF DEBRIS ON REMAINING MCDS. ENGINE ALLOCATED TO ROLLS-ROYCE CANADA FOR INVESTIGATION, FURTHER DETAIL WILL BE SUBMITTED FOLLOWING ENGINE TEARDOWN (TC NR 20071001012) 2 L 7 2 4F 4 F RT T00011AT TE6CH 2007110500108 20071105 00108 NM 2007 11 5 CA071002002 1 20071002 G 2910 DSC1896 CHECK VALVE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE NR 2 HYD SYS CRACKED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) AN AIRCRAFT EXPERIENCED A LOSS OF HYDRAULIC SYSTEM NR 2 DURING TAKEOFF. FLIGHT ABORTED. ALTERNATE LDG EXTENSION US ED. MAINTENANCE FOUND SPU NR 2 CHECK VALVE WITH A CIRCUMFERENTIAL CRACK ON ITS BODY. (TC NR 20071002002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008030600164 20080306 00164 CE 2008 3 6 CA071002003 1 20070925 G 3397 WIRE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL LANDING LIGHT FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) DURING TAKEOFF, ODOR NOTICED IN COCKPIT. FLIGHT CONTINUED. SMOKE AND SPARKS NOTICED FROM BEHIND AREA WHERE LANDING LIGHT SWITCH IS LOCATED. MASTER TUNRED OFF AND AC RETURNED TO FIELD. DURING THIS TIME, A FIRE HAD STARTED RIGHT BEHIND THE LANDING LIGHT SWITCH AND WAS EXTINGUISHED USING THE ONBOARD FIRE EXTINGUISHER. AC LANDED WITHOUT FURTHER INCIDENT. UPON INVESTIGATION, FOUND WIRES FROM BEHIND LANDING LIGHT HAD FALLEN OFF DUE TO LANDING LIGHT SWITCH OVER HEATING AND TE RMINALS FROM THE SWITCH FALLING OFF. THIS ALLOWED THE SUPPLY WIRE FOR THE LANDING LIGHT SWITCH TO CONTACT GROUND AND STA RT ARCING WHICH STARTED THE FIRE. THE CIRCUIT BREAKER WAS FOUND IN THE CLOSED POSITION INDICATING IT DID NOT OPEN DURING 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2008031900161 20080319 00161 EA 2008 3 19 CA071002004 2 20070930 G 8530 16A23033 CYLINDER CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL NR 3 CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ENG COMPRESSION CHECK WAS COMPLETED DUE TO REPORTED ROUGH RUNNING ENG. CYL NR 3 FOUND TO HAVE NO COMPRESSION AND W AS BOROSCOPED. DURING BOROSCOPE, A PIECE OF WIRE WAS FOUND TO BE HUNG UP BETWEEN THE INTAKE VALVE AND THE EXHAUST VALVE. CYLINDER WAS REMOVED. BOTH VALVES WERE REMOVED FROM THE CYL AND THE WIRE THAT WAS NOTICED DURING BOROSCOPING FELL OUT. UPON INVESTIGATION OF THE WIRE, IT WAS DETERMINED THAT THIS WIRE WAS FROM A SCAT HOSE WHICH WAS ATTACHED TO THE CARBURAT OR AIR BOX. THE WIRE WAS APPROX 3 INCHES LONG AND WAS SUCKED UP THROUGH THE AIR BOX, CARBURATOR, INDUCTION SYS AND RT IN TO THE CYL. DURING CLOSE INSP OF THE WIRE, CHAF MARKS WERE NOTICED ON THE WIRE WHERE IT HAD BEEN RUBBING ON THE EDGE OF 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2007110500109 20071105 00109 SO 2007 11 5 CA071002005 2 20070928 G 8530 PISTON BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO HARTZL HCA3V PHCA3VF2 GL ENGINE DAMAGED W E A ENGINE SHUTDOWN UNSCHED LANDING E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 1414 98 297694R (CAN) DURING CRUISE FLT, RT ENGINE BEGAN TO LOOSE OIL PRESSURE. OIL TEMP & CHT INCREASED. PILOT ELECTED TO SHUTDOWN ENGI NE AS A VIBRATION BECAME APPARENT & OIL PRESSURE DECREASED TO NEAR ZERO. AN EMERGENCY DECLARED & AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. UPON INSPECTION, NR 5 CYLINDER & PISTON FOUND DAMAGED. PISTON FOUND WITH A HOLE IN SIDE JUST BELOW CO MPRESSION RINGS. HOLE DOES NOT APPEAR TO BE CAUSED BY OPERATIONAL DAMAGE & ONLY 98 HRS TSO IS UNLIKELY. LOOKS LIKE A MAN UFACTURING DEFECT OR SOME TYPE OF MECHANICAL DAMAGE. HOLE CAUSED CRANKCASE TO PRESSURIZE & THERFORE CAUSE ENGINE TO VENT IT`S OIL OVERBOARD THROUGH BREATHER TUBE. SAME AIRCRAFT & ENGINE EXPERIENCED SAME PROBLEM A WEEK PRIOR TO THIS EVENT B 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P6EA 2007110500110 20071105 00110 NM 2007 11 5 CA071002006 1 20070930 G 2912 20011610 FILTER ADAPTER BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU HYD SYSTEM CLOGGED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, CREW HAD TROUBLES WITH LANDING GEAR, MAIN GEARS WOULD NOT RETRACT. NOSE RETRACTED NORMALLY. ALTERNA TE LANDING GEAR EXTENSION ACC. CHECKLIST DONE. UNEVENTFUL LANDING. AIRCRAFT HANDED OVER TO MAINTENANCE. NO FAULTS CODES . FOUND BYPASS VALVE FILTER COLLAPSED, FILTER REPLACED, A/C RTS. (TC NR 20071002006) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007110500111 20071105 00111 EA 2007 11 5 CA071003001 1 20071002 G 3230 750005000 SELECTOR VALVE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE MLG INOPERATIVE W A UNSCHED LANDING J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH (GEAR DISAGREE) WARNING MESSAGE AT LDG SELECTION. MLG`S WOULD NOT COME DOWN, NLG OK. CYCLED LDG SAME. ALTERNATE EXTENSION USED, OK. AIRCRAFT LANDED. SNAG CAN BE REPRODUCED ON JACKS. MLG SELECTOR VALVE FOUND INOPERATIVE. RE PLACED VALVE. A/C RTS. (TC NR 20071003001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007110500112 20071105 00112 EA 2007 11 5 CA071003002 1 20071002 G 2497 BUSS BAR CNDAIR CL600 CL6002D24 1390016 EA GE CF34 CF34* NE COCKPIT OVERHEATED W L A ABORTED APPROACH UNSCHED LANDING H ELECT. POWER LOSS-50 PC AP APPROACH 1 CA (CAN) ON APPROACH CREW RECEIVED WING ANTI ICE FAULT STS MSG FOLLOWED BY DC BUS 1 CAUTION MESSAGE. AIR TURN BACK MAINTENA NCE FOUND CB`S D6, D7 AND THEIR BUS BAR OVERHEATED. REPLACED C/B`S AND BUS BAR. PARTS REPLACED: BUS BAR CIRCUIT BREAKE R D6 (80A) CIRCUIT BREAKER: D7 (3A) BUS BAR: S6938-1 CIRCUIT BREAKER D6 (80A): MS25361-80 CIRCUIT BREAKER D7 (3A): MS22 073-3 (TC NR 20071003002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007110500113 20071105 00113 EA 2007 11 5 CA071003003 1 20071001 G 2752 852D10019 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE TE FLAP MALFUNCTIONED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 11009 (CAN) FLAPS FAIL CAUTION MSG AND 40 DEG. RAN QRH PROCEDURES AS REQUIRED AND COMPLIED WITH INSTRUCTIONS. A/C DISPATCHED U NDER PROVISIONS OF FAA AD 2006-12-21 (DEFERRAL FOR 72 HRS). AT OVERNIGHT MAINTENANCE, FOUND RT WING FLAP DRIVE SYSTEM T ORQUE VALUE AT 25 IN/LBS. FOUND RT IB ( NR 1 ACTUATOR) WITH HIGH TORQUE. REPLACED RT NR 1 FLAP ACTUATOR IAW CRJ AMM 27-5 3-01. (TC NR 20071003003) 2 L 7 2 4F 4 F RT A21EA E15NE 2007110500114 20071105 00114 EA 2007 11 5 CA071003004 1 20071003 G 3213 21587525 PLATE CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 AWASP 52016 NE HAMSTD 43E 43E60 NE MLG MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ADJUSTING PLATE P/N 215-87525 MISSING ON A NEWLY OVERHAULED LOWER MEMBER P/N 160-600-35 S/N H126. A/C HOURS 4658. 7 CYCLES 2973 DROPS16691 (TC NR 20071003004) 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 2008030600165 20080306 00165 SO 2008 3 6 CA071003005 1 20070920 G 3230 74087002 ROD END PIPER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL MAIN GEAR DOOR STIFF W O OTHER J WARNING INDICATION LD LANDING 1 CA (CAN) ON SEPT 12, THE DOWNLOCK HOOK ON THE RT GEAR DID NOT COMPLETELY LOCK TO ACTIVATE THE DOWNLOCK SWITCH. THE RETRACTI ON SYS WAS TROUBLESHOT AND FOUND THE ROD END ON THE DOWNLOCK CABLE ASSY WAS STIFF AND THE SWITCH WAS STICKING. THE GEAR WAS CLEANED AND LUBRICATED. RETRACTION TESTS CARRIED OUT AND AC RETURNED TO SERVICE. ON THE SEPT 20, THE SAME SNAG HAPP ENED. THE ROD END HAD STIFFENED UP AGAIN. THE ROD END WAS CHANGED AND NO MORE PROBLEM. THE ROD END AT FAULT WAS LUBRICAT ED AND FOUND TO MOVE FREELY BUT AFTER BEING LEFT ON THE BENCH FOR A FEW DAYS SEIZED UP AGAIN. (TC NR 20071003005) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007110500115 20071105 00115 NM 2007 11 5 CA071003006 1 20071002 G 5544 72760059101 MOUNT DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 44877 44877 (CAN) DURING RIGGING OF LOWER RUDDER ACTUATOR SPRING STRUT, NOTICED ACTUATOR ADAPTOR FLEXING. ADAPTOR FOUND TO BE CRACKE D FROM OUTER FLANGE HORIZONTALLY ACROSS RADIUS TO INNER FLANGE. ADAPTOR REPLACED. (TC NR 20071003006) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007110500121 20071105 00121 EA 2007 11 5 CA071003007 2 20070810 G 8550 LW13383 BAFFLE FOUND FBA FBA2C2 3640104 EA LYC O540 IO540L1A5 41532 EA HARTZL HCC3Y HCC3YR GL OIL SUMP FAILED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 10 (CAN) ENGINE OIL SUMP BAFFLE CONTACTING BOTTOM OF OIL SUMP. REPLACED OIL SUMP WITH A NEW ONE FROM MFG. INSPECTION ACCOMP LISHED BECAUSE OF REQUEST FROM CUSTOMER WHO SUBMITTED FAA SDR NR 2007FA0000760 AND 1. (TC NR 20071003007) 1 H 7 1 3O 3 O NC A7EA 1E4 5 C P25EA 2008030600166 20080306 00166 CE 2008 3 6 CA071003008 1 20070914 G 5540 0510128 BRACKET CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL RUDDER WORN W K NONE O OTHER IN INSP/MAINT 1 CA 16797 (CAN) ON A 100 HOUR INSPECTION, MAINT DISCOVERED THE RUDDER PEDAL TORQUE TUBE SPRING ATTACHMENT BRACKET HOLE WAS WORN MO RE THAN HALF THRU. THIS IS A HARD TO INSPECT AREA AT THE FWD TUNNEL CENTER SECTION UNDER THE DASH. THE BRACKET WAS REPLA CED AND RUDDER RE-RIGGED AS REQUIRED. (TC NR 20071003008) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2007110500122 20071105 00122 NE 2007 11 5 CA071003009 2 20070802 G 7261 3034677 TUBE AEROSP ATR72 ATR72202 8680940 EU PWA PW120 PW124B NE ENGINE OIL LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB, ENGINE OIL PRESSURE WAS SEEN TO DECREASE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTIO N REVEALED A LEAKING OIL PRESSURE TUBE AT THE REAR INLET CASE. (TC NR 20071003009) 2 H 7 2 4T 4 T RT A53EU E2ONE 2007110500123 20071105 00123 NE 2007 11 5 CA071003010 2 20070803 G 7200 ENGINE FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE MAKING METAL W O OTHER B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA (CAN) DURING DESCENT OIL ODOR AND SMOKE WERE EVIDENT IN THE CABIN. ENGINE BLEED WAS SELECTED OFF. SUBSEQUENT INSPECTION REVEALED METAL PARTICLES IN THE ENGINE OIL. 2 H 7 2 4T 4 T RT A817 E20NE 2007110500124 20071105 00124 EU 2007 11 5 CA071003011 1 20070805 G 7712 SENSOR AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE AUTOFEATHER SYS MISINSTALLED W O OTHER R W J PARTIAL RPM/PWR LOSS INADEQUATE Q C WARNING INDICATION DE DESCENT 1 CA (CAN) ON DESCENT THE ENGINE EXPERIENCED AN UNCOMMANDED REDUCTION IN POWER ACCOMPANIED BY FEATHERING OF THE PROPELLER. PR ELIMINARY INSPECTION REVEALED IMPROPERLY TORQUED TORQUE SENSOR AND POOR CONTINUITY BETWEEN THE AFU AND FUEL CONTROL. 2 H 7 2 4T 4 T RT E20NE 2007110500125 20071105 00125 NE 2007 11 5 CA071003012 2 20070808 G 7200 ENGINE DHAV DHC8 DHC8106 2809020 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE SMOKE W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 120696 (CAN) FOLLOWING TAKEOFF OIL ODOR AND SMOKE WERE EVIDENT IN THE CABIN. THE ENGINE WAS SHUTDOWN IN FLIGHT. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007110500126 20071105 00126 NE 2007 11 5 CA071003013 2 20070805 G 7200 ENGINE AGUSTA A109 A109E 0260119 EU PWC PW206C PW206C NE POWER LOSS W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA BC0541BC0542 (CAN) DURING TAKEOFF, THE PILOT REPORTED A POWER LOSS ACCOMPANIED BY AN LOW TORQUE WARNING INDICATION. THE AIRCRAFT WAS DAMAGED IN THE RESULTING FORCED LANDING. 1 G 7 2 3U 3 U RT H7EU E42NE 2007110500127 20071105 00127 NE 2007 11 5 CA071003014 2 20070808 G 7321 8273002 FCU CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE ENGINE UNRESPONSIVE W O OTHER R F PARTIAL RPM/PWR LOSS FLT CONT AFFECTED DE DESCENT 1 CA (CAN) ON DESCENT, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT. THE FUEL CONTROL UNIT WAS REPLACED. 2 L 7 2 4F 4 F RT A22CE E00059EN 2007110500102 20071105 00102 NE 2007 11 5 CA071003015 2 20070807 G 7200 ENGINE AEROSP ATR72 ATR72 EU PWA PW120 PW124B NE MAKING METAL W A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA 124623 (CAN) THE ENGINE FLAMED OUT IN CRUISE. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE OIL SYSTEM. 2 H 7 2 4T 4 T RT E2ONE 2007102600134 20071026 00134 EA 2007 10 26 CA071003016 2 20070630 G 7230 FRACTURE BLADES AIRTRC AT500 AT502A 0390306 SW PWA PT6 PT6A65B 52043 EA COMPRESSOR FRACTURED W C ABORTED TAKEOFF R A PARTIAL RPM/PWR LOSS FLAME/FIRE TO TAKEOFF 1 CA (CAN) ON TAKEOFF, THE ENGINE EXPERIENCED A POWER LOSS ACCOMPANIED BY FLAMES EXITING THE EXHAUST. THE AIRCRAFT WAS DAMAGE D, RESULTING IN A FORCED LANDING. SUBSEQUENT INSPECTION REVEALED FRACTURED COMPRESSOR BLADES. MFG WILL MONITOR THE INVES TIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003016) 1 L 7 1 3T 4 T NC A17SW E4EA 2007102600135 20071026 00135 NE 2007 10 26 CA071003017 2 20070810 G 7200 ENGINE UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206B 0 NE POWER LOSS W O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA (CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN FLIGHT. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF R OOT CAUSE ONCE ESTABLISHED. (TC NR 20071003017) 1 G 7 2 3U 3 U O H88EU E42NE 2007102600136 20071026 00136 NE 2007 10 26 CA071003018 2 20070813 G 7200 ENGINE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE SMOKE W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 70176 (CAN) IN CRUISE SMOKE BECAME EVIDENT IN THE AIRCRAFT CABIN REQUIRING THE ENGINE AIR BLEED TO BE SELECTED OFF. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003018) 1 L 7 2 4F 4 F A22CE E1NE 2007102600137 20071026 00137 NE 2007 10 26 CA071003019 2 20070813 G 7321 32448716 FUEL CONTROL AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE ENGINE FAULTY W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA (CAN) IN FLIGHT, ENGINE POWER REDUCED UNCOMMANDED AND THE ENGINE WAS SHUTDOWN. AN IN-FLIGHT RELIGHT ATTEMPT WAS UNSUCCES SFUL. SUBEQUENT INSPECTION REVEALED A FAULTY FUEL CONTROL UNIT. (TC NR 20071003019) 2 H 7 2 4T 4 T RT E20NE 2007110500001 20071105 00001 NM 2007 11 5 CA071003020 1 20070930 G 2622 SEAL BOEING 737 737800* NM CFMINT CFM56 CFM567B26US NE EXTINGUISHER FAILED W O OTHER K FLUID LOSS CR CRUISE 1 CA 9918 W856080 (CAN) ON SEPTEMBER 30, 2007 THE FLIGHT CREW REPORTED THAT THE PORTABLE FLIGHT DECK FIRE EXTINGUISHER PARTIALLY DISCHARGE D DURING CRUISE ON A/C 803. THE FIRE EXTINGUISHER WAS REPLACED WITH NO FURTHER ACTION REQUIRED. 2 L 7 2 4F 4 F RT A16WE E00055EN 2007113000093 20071130 00093 NE 2007 11 30 CA071003021 2 20070807 G 7230 ENGINE CESSNA 510 510 2076617 CE PWC PW615 PW615FA 52282 NE MALFUNCTIONED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA LB0013 (CAN) IN CRUISE IN LIGHT ICING CONDITIONS, ENGINE N1 SPEED REDUCED UNCOMMANDED. THE N1 RETURNED TO NORMAL SETTINGS IN DE SCENT. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 L 7 2 4F 4 F RT A00014WI E00073EN 2007102600138 20071026 00138 NE 2007 10 26 CA071003022 2 20070819 G 7250 TURBINE BLADES BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE ENGINE DAMAGED W A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CL CLIMB 1 CA JA0236 (CAN) THE ENGINE FLAMED OUT IN FLIGHT AND AN ATTEMPTED RELIGHT WAS UNSUCCESSFUL. SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003022) 2 H 7 2 4F 4 F RT A16SW E25EA 2007102600139 20071026 00139 NE 2007 10 26 CA071003023 2 20070812 G 7230 30B285501 FAN BLADE LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE COMPRESSOR FRACTURED W E A ENGINE SHUTDOWN UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA (CAN) IN CRUISE, THE ENGINE EMITTED A LOUD NOISE AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED TWO FRACTURE D FAN BLADES. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003023) 2 L 7 2 4F 4 F RT A10CE E35NE 2007102600140 20071026 00140 CE 2007 10 26 CA071003024 1 20070824 G 7931 OIL SYSTEM BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE ENGINE FLUCTUATES W E ENGINE SHUTDOWN J WARNING INDICATION AP APPROACH 1 CA 114070 (CAN) ON APPROACH, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. MFG WILL MONITOR IN VESTIGATION OF THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003024) 2 L 7 2 4T 4 T RT A24CE E26NE 2007102600141 20071026 00141 EU 2007 10 26 CA071003025 3 20070825 G 6197 WIRE HARNESS BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU ENGINE UNKNOWN W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA FA0249 (CAN) IN CRUISE, THE PROPELLER ELECTRONIC CONTROL (PEC) AND POWER PLANT WARNINGS ACTIVATED. THE ENGINE WAS SHUTDOWN IN F LIGHT. THE PEC, SENSOR AND RELATED HARNESS WERE SUBSEQUENTLY REPLACED. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROO T CAUSE ONCE ESTABLISHED. (TC NR 20071003025) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2007102600142 20071026 00142 CE 2007 10 26 CA071003026 1 20070826 G 7603 COUPLING BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE THROTTLE FRACTURED W E ENGINE SHUTDOWN F J FLT CONT AFFECTED WARNING INDICATION DE DESCENT 1 CA (CAN) ON INITIATING DESCENT, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT. THE ENGINE WAS SHUTDOWN IN FLIGHT. S UBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL (PLASTIC) DRIVE COUPLING. (TC NR 20071003026) 1 L 7 2 4T 4 T A24CE E4EA 2007102600143 20071026 00143 EA 2007 10 26 CA071003027 2 20070829 G 7200 ENGINE BELL 412 412EP 1182205 SW PWA PT6T PT6T3 52045 EA MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION TX TAXI/GRND HDL 1 CA TH0736 (CAN) AN ENGINE CHIP DETECTOR WARNING ACTIVED AND THE POWER SECTION WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEAL ED METAL DEBRIS IN THE ENGINE OIL SYSTEM. MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 200710 03027) 1 G 7 2 4U 4 U H4SW E22EA 2007102600144 20071026 00144 NE 2007 10 26 CA071003028 2 20070823 G 7261 STRAINER CESSNA 500 S550 2076607 CE PWA JT15 JT15D4 52112 NE NR 4 BEARING BLOCKED W E ENGINE SHUTDOWN J WARNING INDICATION DE DESCENT 1 CA (CAN) IN DESCENT, ENGINE OIL PRESSURE REDUCED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED OIL COKING AND BLOCKAGE OF THE NR 4 BEARING SCAVENGE OIL STRAINER. (TC NR 20071003028) 1 L 7 2 4F 4 F RT A22CE E1NE 2007102600145 20071026 00145 EU 2007 10 26 CA071003029 1 20070829 G 7720 THERMOCOUPLE FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE ENGINE UNSERVICEABLE W E ENGINE SHUTDOWN N FALSE WARNING NR NOT REPORTED 1 CA (CAN) THE ENGINE OVER-TEMPERATURE WARNING ACTIVATED IN FLIGHT AND THE ENGINE WAS SHUTDOWN. SUBSEQUENT INSPECTION REVEALE D TWO UNSERVICEABLE T6 THERMOCOUPLES. (TC NR 20071003029) 2 H 7 2 4T 4 T RT A817 E20NE 2007102600146 20071026 00146 WP 2007 10 26 CA071004001 1 20071003 G 8011 14924HTH STARTER ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE INOPERATIVE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) ZERO TIMED STARTER INSTALLED ON AIRCRAFT. WOULD NOT TURN OVER DURING FUNCTIONAL CHECK. (TC NR 20071004001) 1 G 7 1 3O 3 O H11NM 1E4 2007110500010 20071105 00010 NM 2007 11 5 CA071004002 1 20070928 G 2497 WIRE HARNESS DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 17156 (CAN) WIRE BUNDLE AT STATION FS 510 (BELOW FLOOR BOARD) CROSSING OVER FROM STARBOARD TO PORT SIDE. WIRE BUNDLE CURVES UP WARD RUNNING BENEATH SEAT RAIL STRUCTURE THEN GOES FORWARD ONTRAY. WIRE BUNDLE FOUND NOT PROTECTED AS IT CURVES UP BENE ATH SEAT RAIL STRUCTURE (PORT SIDE). FOUR WIRES WERE CHAFING AGAINST THIS STRUCTURE OF WHICH 3 OF THEM HAD WORN THROUGH THE INSULATOR. WIRES WERE REPAIRED AND WIRE BUNDLE PROTECTED. (TC NR 20071004002) 2 H 7 2 4T 4 T RT A13NM E20NE 2008030600167 20080306 00167 CE 2008 3 6 CA071004003 1 20071001 G 5210 231127416 ARM LEAR 35 35LEAR 5170600 CE GARRTT TFE731 TFE73122B 01518 WP PAX DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 19829 1010 (CAN) DURING ROUTINE DAILY INSP, FOUND LOWER DOOR AFT LATCH ARM CRACKED ALL THE WAY THROUGH DUE TO CORROSION FATIGUE. (T C NR 20071004003) 2 L 7 2 4F 4 F A10CE E6WE 2008012900036 20080129 00036 WP 2008 1 29 CA071004005 1 20070918 G 6730 D2121 SERVO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE HYDRAULIC SYS LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1123 1123 (CAN) DURING 50/100 HOUR INSPECTION HYDRAULIC SERVO FOUND LEAKING FROM PILOT VALVE. 1 G 7 1 3O 3 O H11NM 1E4 2008012900038 20080129 00038 CE 2008 1 29 CA071004006 1 20071001 G 7602 991027114 CABLE CESSNA 414 414 2075908 CE CONT O520 TSIO520N 17040 SO MCAULY 3AF32C 3AF32C505 GL MIXTURE CONTROL BROKEN W D RETURN TO BLOCK R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 10177 (CAN) DURING THE ENGINE RUN-UP, THE RT ENGINE DID NOT RESPOND TO MIXTURE CONTROL. THE MIXTURE CONTROL CABLE WAS FOUND BR OKEN UNDER THE ENGINE CONTROL PEDISTAL. THE BRAKE WAS INSIDE THE CONTROL CABLE HOUSING AND COULD NOT BE SEEN WITH ANY IN SPECTION. (TC NR 20071004006) 1 L 7 2 3O 3 O RT A7CE E8CE 5 C P22EA 2007110500034 20071105 00034 WP 2007 11 5 CA071004007 1 20070918 G 8011 14924HTH STARTER ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN O OTHER TX TAXI/GRND HDL 1 CA 227 227 (CAN) STARTER WOULD NOT DISENGAGE AFTER START. AFTER SHUTDOWN GEAR HAD TO BE PRYED BACK TO DISENGAGE. (TC NR 20071004007 ) 1 G 7 1 3O 3 O H11NM 1E4 2008030600168 20080306 00168 EA 2008 3 6 CA071004008 2 20071001 G 8550 LW15628 SEAL LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL CRANKCASE UNSECURE W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) OIL FOUND IN COWLING ON LT ENGINE NEAR FRONT, FWD CRANKCASE OIL SEAL FOUND TO HAVE POPPED OUT OVERHAUL INFORMED TH IS COMPANY THAT THEY WERE HAVING PROBLEMS WITH THE ADHESIVE THAT THEY USE TO SECURE THIS SEAL (TC NR 20071004008) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007110500035 20071105 00035 EA 2007 11 5 CA071005001 1 20071004 G 5320 CA447 SHROUD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE BS 559 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A HEAVY CHECK THE FUEL SHROUD ASSY AND FUEL LINES AT FRAME 559 WERE REMOVED TO FACILITATE A SHEET METAL REP AIR. IT WAS DISCOVERED THAT BOTH SHROUD AND FUEL LINES HAVE CHAFING BEYOND LIMITS. THIS SAME REPAIR IS BEING C/O ON A/C C-FZSI(126) AND SIMILAR DAMAGE WAS FOUND IN THE SAME LOCATION. THE FUEL LINES AND SHROUD ASSY. HAVE BEEN ORDERED FOR BOT H A/C AND WILL BE REPLACED BEFORE THE A/C LEAVES THE HEAVY CHECK. (TC NR 20071005001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600169 20080306 00169 EU 2008 3 6 CA071005002 1 20071003 G 6730 7050A4673006 SERVO CONTROL UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE ROTOR UNLOCKED W K NONE O OTHER IN INSP/MAINT 1 CA 1533 (CAN) PILOT REPORTED, WHEN PREFLIGHT HYDRAULIC TEST ACTIVATED, CYCLIC MOTORED RT. CYCLIC SHOULD STAY CENTERED DURING HYD TEST. SERVO REPLACED WITH O/H UNIT. GROUND TESTED, SERVICEABLE. AFTER REMOVAL OF SERVO, NOTICED THAT INPUT LEVER WAS S LIGHTLY LOOSE. AFTER MOVING THE INPUT LEVER A FEW TIMES, LEVER APPEARED TO LOCK, AS REQUIRED. SUSPECT STICKY INTERNAL LO CK PIN. (TC NR 20071005002) 1 G 7 2 3U 3 U NC R0001RD E34NE 2008030600170 20080306 00170 EU 2008 3 6 CA071005003 1 20070928 G 3222 5321012193 RING PILATS PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL SHOCK ABSORBER SWOLLEN W K NONE O OTHER IN INSP/MAINT 1 CA IL512 (CAN) DURING ANNUAL INSPECTION IT WAS FOUND THAT STRUTS WERE STIFF, NOT EXTENDING ALL THE WAY. FOUND MICARTA GUIDE RINGS TOO TIGHT. SANDED MICARTA GUIDE RINGS SAME WAY AS MOD TO NOSE OLEO. SERVICED STRUTS WITH FLUID AND NITROGEN. RETURNED T O SERVICE. (TC NR 20071005003) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2007110500036 20071105 00036 SW 2007 11 5 CA071005004 1 20071002 G 3210 AN17722 BOLT FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE RT MLG MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PILOT CALLED AND REPORTED THAT THE BOLT WAS MISSING FROM THE RT MLG TORQUE KNEE. MAINTENANCE INSPECTED TORQUE KNE E ASSEMBLY AND NO SECONDARY DAMAGE WAS NOTED. NEW BOLT WAS INSTALLED AND SECURED AND AIRCRAFT RETURNED OUT OF SERVICE. (TC NR 20071005004) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2007110500037 20071105 00037 EA 2007 11 5 CA071009001 1 20071005 G 2752 852D10021 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE TE FLAPS FROZEN W O OTHER F J FLT CONT AFFECTED WARNING INDICATION DE DESCENT 1 CA (CAN) ON DESCENT CREW RECEIVED FLAP FAIL MESSAGE UPON SELECTION OF FLAPS DOWN. FLAPS FAILED AT ZERO DEGREES. FLIGHT LAND ED WITHOUT INCIDENT. UPON INVESTIGATION IT WAS FOUND THAT THE ACTUATORS WERE FROZEN. ALL IB AND OB ACTUATORS REPLACED (8 ), FLAP RIGGING CARRIED OUT AND SYSTEM OPERATIONAL CHECK CARRIED OUT WITH NO FAULTS FOUND. AIRCRAFT RETURNED TO SERVICE. (TC NR 20071009001) 2 L 7 2 4F 4 F RT A21EA E15NE 2007110500039 20071105 00039 EA 2007 11 5 CA071009002 1 20071007 G 5712 601R120474 RIB CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE RT WING DENTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) REMNANTS OF A BIRD WAS FOUND ON ARRIVAL. INSP REVEALED A DENT IN THE RT WING LEADING EDGE AT WING. THE DENT WAS AP PROXIMATELY 4 INCHES BY 2 INCHES AND .25 INCHES DEEP. MAINTENANCE REMOVED THE DENT AND REPLACED RIB AT WING STATION 167. 00 AND THE L/E WAS RE-INSTALLED AND WING ANTI ICE WAS FUNCTION CHECKED SERVICEABLE. (TC NR 20071009002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007110500060 20071105 00060 NM 2007 11 5 CA071010001 1 20071005 G 2824 1321536250 CONTROL VALVE DHAV DHC8 DHC8315 2809010 NM PWA PW120 PW123 NE FUEL SYSTEM OBSTRUCTED W K NONE C F.O.D. IN INSP/MAINT 1 CA 21 (CAN) DURING TEST FLIGHT, RT AUX TO MAIN FUEL TRANSFER SYSTEM STOPPED TRANSFERRING. BOLT FOUND IN LEVEL CONTROL VALVE CA USING VALVE TO STOP TRANSFER SYSTEM. BOLT REMOVED, SYSTEM FUNCTIONED NORMALLY. SAME SNAG REPORTED DURING CUSTOMER ACCEPT ANCE FLIGHTS AT MFG. THIS F.O.D. HELD THE VALVE CLOSED INTERMITTENTLY. (TC NR 20071010001) 2 H 7 2 4T 4 T RT A13NM E20NE 2008030600171 20080306 00171 CE 2008 3 6 CA071010002 1 20071008 G 7500 12991003315 HOSE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE BLEED AIR CRACKED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) BLEED AIR FAIL LIGHT CAME ON DURING THE TAKEOFF PROCESS. THE AC CAME AROUND AND LANDED. MAINTENANCE WAS CALLED. IT WAS DISCOVERED THAT A BLEED AIR LINE WAS CRACKED AT THE FLANGE. LINE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20071010002) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2008031900162 20080319 00162 GL 2008 3 19 CA071010003 2 20071009 G 7240 6870992 COMBUSTION CASE BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE CRACKED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA CAE821328 (CAN) PILOT RETURNING TO BASE REPORTED HIGHER THAN NORMAL ENGINE TEMP. INSP OF THE ENG INDICATION SYS FOUND SERVICEABLE. INSP OF THE ENGINE FOUND A CRACK IN THE COMBUSTION CASE. COMBUSTION CASE REPLACED. AC GROUND RUN AND FOUND SERVICEABLE AND RETURNED TO SERVICE. (TC NR 20071010003) 1 G 7 1 3U 3 U H2SW E4CE 2008030600172 20080306 00172 CE 2008 3 6 CA071010004 1 20070926 G 2421 BRUSHES LEAR 35 31 5170530 CE MOTOR BURNED W O OTHER O OTHER NR NOT REPORTED 1 CA 1080S (CAN) BRUSH ASSEMBLIES BURNED. (TC NR 20071010004) 2 L 7 2 4F RT A10CE 2008030600173 20080306 00173 SW 2008 3 6 CA071010005 1 20070828 G 6210 204011250001 BLADE BELL 204 204B 1181404 SW LYC T53 T5311B 41549 NE MAIN ROTOR CRACKED W O OTHER E VIBRATION/BUFFET AP APPROACH 1 CA 1851 (CAN) ON TUESDAY THE 28TH OF AUGUST 2007, AT APPROX 19:00, LANDED AT THE STAGING AREA. THE PILOT COMMENTED THAT THERE WA S A VIOLENT LATERAL VIBRATION. AT THIS TIME THE TRANSMISSION WAS OBSERVED SHAKING EXCESSIVELY AND IT WAS DECIDED TO SHUT THE AIRCRAFT DOWN WHERE IT SAT. AS THE MAIN ROTOR BLADES SPOOLED DOWN THE PILOT OBSERVED A LARGE CRACK IN ONE OF THE BL ADES. FURTHER INSPECTION REVEALED A CRACK THROUGH THE ENTIRE THICKNESS OF THE BLADE. BOTH THE TOP AND BOTTOM SKIN ARE BR OKEN. THE CRACK/BREAK IS LOCATED 98 INCHES FROM THE ROOT OF THE BLADE AND RUNS FROM THE T/E TO 6 INCHES FROM THE L/E (AS CENDING, THE LEADING EDGE SPAR). AT THE START OF THE CRACK (THE TRAILING EDGE) THE SKIN HAS SPREAD APPROXIMATELY .1250 I 1 G 7 1 4U 4 U H1SW E1EA 2007110500061 20071105 00061 NE 2007 11 5 CA071010006 2 20070927 G 7250 500310401 TURBINE WHEEL BOEING 727 727225 1384077 NM PWA JT8 JT8D15 52051 NE ENGINE FAILED W C ABORTED TAKEOFF X J ENGINE FLAMEOUT WARNING INDICATION TO TAKEOFF 1 CA 20974 700585 (CAN) AT THE RUNWAY THRESHOLD THE FLIGHT CREW ADVANCED THE THROTTLES TO 1.2 EPR, STABLE ENGINES WERE CALLED. ADVANCED TH RUST LEVERS AND APPROACHING TAKEOFF THRUST, BEFORE REACHING APPROXIMATELY 20 KTS, A LOUD BANG AND VIBRATION OCCURRED. TH E FLIGHT CREW REJECTED THE TAKEOFF AND CLEARED THE RUNWAY. THE NR1 ENGINE WAS SHUT DOWN AFTER OBSERVING N2 SPOOL DOWN AN D INCREASING EGT INDICATION. THE AIRCRAFT RETURNED TO THE GATE. MAINTENANCE FOUND THAT THE ENGINE TURBINE HAD FAILED. T HE ENGINE WAS REMOVED AND REPLACED WITH A SERVICEABLE ASSEMBLY. (TC NR 20071010006) 2 L 7 3 4F 4 F A3WE E2EA 2008030600174 20080306 00174 SO 2008 3 6 CA071010007 1 20070906 G 3260 2124800 RHEOSTAT PIPER PA24 PA24250 7102404 SO LYC O540 O540A1C5 41532 EA MCAULY 3D32C B3D32C417 GL MLG INDICATOR MALFUNCTIONED W B EMER. DESCENT H P ELECT. POWER LOSS-50 PC NO WARNING INDICATION LD LANDING 1 CA (CAN) PILOT SELECTED GEAR DOWN AND DID NOT SEE THE GREEN LIGHT, FOR THE GEAR DOWN POSITION. PILOT THEN STARTED EMERGENCY GEAR DOWN PROCEDURES. IT JAMMED WITH THE GREAR IN NEUTRAL POSITION, BECAUSE THE ELECTRIC SWITCH WAS NOT IN NEUTRAL. THE PILOT LANDED WITH THE GEAR UP. AFTER THE AIRPLANE WAS PUT ON THE JACKS AND THE GEAR WAS LOCKED. THE RHEOSTAT WAS TURNED TO THE DAYLIGHT RUNNING POSITION AND THE GREEN LIGHT, FOR THE GEAR DOWN LOCK POSITION CAME ON. (TC NR 20071010007) 1 L 7 1 3O 3 O 1A15 E295 5 C P58GL 2008012900041 20080129 00041 CE 2008 1 29 CA071010008 1 20071003 G 2711 1295210325 ACTUATOR BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE LT AILERON TRIM SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA 99948 (CAN) DURING A 50 HOUR ROUTINE INSPECTION MAINTENANCE PERSONEL DISCOVERED THAT THE AILERON TRIM WAS NOT MOVING. UPON INS PECTION OF THE SYSTEM IT WAS DISCOVERED THAT THE AILERON TRIM ACTUATOR WAS SEIZED. THE ACTUATOR WAS REMOVED AND DISSASSE MBLED. THERE WAS INTERNAL RUST IN THE TRIM ACTUATOR HOUSING AND ONE BEARING WAS SEIZED. (TC NR 20071010008) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2008012900043 20080129 00043 SW 2008 1 29 CA071010009 1 20071005 G 2911 223002 ACCUMULATOR FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE HYD SYSTEM CRACKED W O OTHER J WARNING INDICATION DE DESCENT 1 CA 18203 (CAN) AIRCRAFT WAS INBOUND WHEN CREW REPORTED THE AIRCRAFT HAD LOST ALL HYDRAULIC PRESSURE. EMERGENCY GEAR EXTENSION WAS USED AND AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE DISCOVERED A 6 CENTIMETER CRACK LOCATED ON THE TOP SHOULDER AREA OF THE HYDRAULIC ACCUMULATOR CAP. (TC NR 20071010009) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2008012900044 20080129 00044 SW 2008 1 29 CA071010011 1 20071005 G 3230 750069501 SHAFT GULSTM 690TP 690 0141720 SW GARRTT TPE331 TPE3315251K NM HARTZL HCB3T HCB3TN5 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3600 (CAN) DURING ANNUAL INSPECTION, THE SHAFT THAT PIVOTS THE NOSE GEAR UPPER LINK ASSY P/N ES10107 WAS FOUND CRACKED. THE C RACK IS LOCATED ON THE IB END OF THE SHAFT IN THE NOSE WHEEL WELL, WHERE IT IS FLUSH WITH THE EDGE OF THE HOLE IN THE UP PER LINK ASSEMBLY. THE CRACK IS APPROXIMATELY .5 INCH IN LENGTH AND PROGRESSES TO THE THRU BOLT HOLE. THE PIECE WILL BE REPLACED WITH A SERVICEABLE PART. (TC NR 20071010011) 1 H 7 2 3T 4 T 2A4 E2WE 6 C P15EA 2008012900046 20080129 00046 CE 2008 1 29 CA071011001 1 20070914 G 3230 1153800025 MOTOR BEECH 100 B100 1152919 CE GARRTT TPE331 TPE3316252B 01514 WP HARTZL HCB4T HCB4TN5 GL LANDING GEAR UNSERVICEABLE W E ENGINE SHUTDOWN J WARNING INDICATION AP APPROACH 1 CA (CAN) IN DESCENT FOR LANDING, THERE WERE ONLY 2 GREEN GEAR DOWN INDICATION LIGHTS INSTEAD OF THREE. AFTER RECYCLING THE GEAR, THE PROBLEM PERSISTED. THE EMERGENCY LANDING GEAR SYSTEM WAS DEPLOYED AND THE 3 GREEN LIGHTS WERE ON AS REQUIRED. AIRCRAFT LANDED WITHOUT INCIDENT. FURTHER INSPECTION REVEALED THE LANDING GEAR MOTOR WAS UNSERVICEABLE. (TC NR 2007101 1001) 1 L 7 2 4T 4 T A14CE E2WE 6 C P40EA 2008012900048 20080129 00048 CE 2008 1 29 CA071011002 1 20071003 G 7820 MUFFLER CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL ENGINE CRACKED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) MUFFLER CRACKED AROUND PIPE AFTER BACKFIRE. (TC NR 20071011002) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2008030600175 20080306 00175 2008 3 6 CA071011006 2 20071009 G 7320 6047T74P13 FCU CNDAIR CL600 CL600* 1900302 EA ENGINE MALFUNCTIONED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) WHILE ENROUTE AND AT FL 400, THE NR 1 ENGINE FLAMED OUT. AC DESCENDED TO FL200 AND RESTARTED IAW AFM. AC ARRIVED SAFELY. MFG REP IS ON SITE AND RECOMMENDED THAT THE FUEL CONTROL UNIT BE REPLACED. (TC NR 20071011006) 2 L 7 2 4F RT A21EA 2007110500062 20071105 00062 EU 2007 11 5 CA071011007 1 20070914 G 5343 25FN1609 ATTACH FITTING HWKSLY DH125 HS125600A 4230158 EU GARRTT TFE731 TFE7313R 01518 WP NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFTER REPAINT OF A/C INSPECTION REVEALED A CRACK ON SIDE OF ATTACH POINT. LDG WAS PULLED TO REPLACE ATTACH POINT B RACKET AND ATTACH POINT BRACKET BOLTS. THESE BOLTS WERE SHOWING WEAR MARKS ON THE SHANK, SUGGESTING THE NUTS WERE THREAD BOUND, INDICATING NOT ENOUGH WASHERS WERE USED. THE LDG SIDEWALL WAS ALSO SHOWING WEAR DUE TO THE BRACKET VIBRATING. WI TH ALL THESE FINDING IT WAS DECIDED TO CHECK BOLT HOLE CLEARANCE ON THE LDG SIDEWALL, ALL BOLT HOLES WERE ELONGATED. DUE TO INSUFFICIENT WASHER BUILD UP THE TORQUES WERE INACCURATE CAUSING THE BRACKET TO SHIFT WITH EACH LDG CYCLE. THE CRACK S FOUND ON BRACKET COULD BE AN INDICATION OF EXCESSIVE SIDE LOAD POSSIBLY DURING CROSSWIND LANDING, INCORRECT TAXI PROCE 2 L 7 2 4J 4 F A3EU E6WE 2008030600176 20080306 00176 SO 2008 3 6 CA071011008 1 20071005 G 3000 50363007 INLET SCREEN PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE EVENT INSPECTION, A SMALL 1.5 INCH CRACK WAS NOTED IN THE INLET ICE SCREEN. DURING THE NEXT EVENT INSPECTION IT WAS NOTED THAT THE CRACK HAD SPREAD SIGNIFICANTLY AND CAUSED SEPARATION FROM THE ASSEMBLY. THE STAINLESS STEEL AIR INLET WAS ALSO CRACKED AND NEEDED REPAIRS. THE SCREEN WAS REPLACED WITH A NEW UNIT. (TC NR 20071011008) 1 L 7 2 3T 4 T A8EA E4EA 6 C P15EA 2007110500063 20071105 00063 SO 2007 11 5 CA071011009 2 20071011 G 8530 652984 ROCKER SHAFT CESSNA 180 180A 2072604 CE CONT O470 O470K 17026 SO MCAULY 2A34C 2A34C203 GL NR 4 CYLINDER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 400 (CAN) POOR DIFF ON INSPECTION, EXH VALVE ROCKER SHAFT FOUND DAMAGED DUE TO LACK OF OIL, CAUSING OVERHEATING AND FAILURE OF ROCKER BUSHING. VALVE DAMAGED DUE TO LACK OF COOLING OIL ALSO. CAUSE OF OIL LOSS TO ROCKER UNKNOWN, MAY POSSIBLY HAV E BEEN A BLOCKED GALLERY AT SOME POINT. (TC NR 20071011009) 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2008012900049 20080129 00049 CE 2008 1 29 CA071011010 1 20070514 G 3233 11013880141 ACTUATOR BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL MLG BYPASSING W O OTHER J WARNING INDICATION LD LANDING 1 CA 473 (CAN) WHILE CONDUCTING A LANDING, THE PILOTS NOTED THAT WHILE SELECTING THE GEAR DOWN THE GEAR MOTOR RAN LONGER THAN NOR MAL. THEY THEN NOTED THAT THE RT GEAR INDICATION LIGHT HAD FAILED TO SHOW A DOWN AND LOCKED POSITION. THEY TRIED AN EMER GENCY GEAR EXTENSION WITH NO LUCK. THEY FLEW THE AC TO A BIGGER CENTER WHERE EMERGENCY SERVICES WHERE AVAILABLE. CONDUCT ED A FLYBY AND THE GEAR WAS VERIFIED TO BE IN THE DOWN AND LOCKED POSITION. THE AIRCRAFT LANDED WITH NO INCIDENT. MAINTE NANCE CREW FLEW NORTH TO INVESTIGATE. DURING THIS TIME IT WAS NOTED BY THE ENGINEERS THAT THE GEAR ACTUATOR WAS BY-PASSI NG INTERNALLY, FAILING TO BUILD SUFFICIENT PRESSURE TO COMPLETELY LOCK THE GEAR SYSTEM. THE AIRCRAFT WAS FLOWN BACK SOUT 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2007110500070 20071105 00070 EU 2007 11 5 CA071012001 1 20071010 G 5280 137414B100 BRACKET BAG JETSTM JETSTM3212 1500217 EU RT MLG DOOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT MAIN LANDING GEAR DOOR AFT HINGE BRACKET FOUND BROKEN (ONE LUG OF TWO) DURING INSPECTION. NEW BRACKET INSTALLED , GEAR SWINGS CARRIED OUT. (TC NR 20071012001) 2 L 7 2 4T RT BA15CAA 2007110500071 20071105 00071 NE 2007 11 5 CA071012002 3 20071012 G 6111 6903A10 BLADE HAMSTD 43E60583 CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 405 N196694 (CAN) DURING COMPLIENCE WITH AD 81-13-06R2 AND S/B 664 A CRACK WAS FOUND EMINATING FROM ONE OF THE BUSHING RETENTION SCR EW HOLES. CRACK HAS BECOME LARGER DURING REWORK PROCEDURES RENDERING THE BLADE U/S. (TC NR 20071012002) 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 2008031900164 20080319 00164 2008 3 19 CA071012003 2 20071009 G 7320 442324 HMU HONEYWELL BOMBDR BD100 BD1001A10 1390044 GL ENGINE MALFUNCTIONED W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA 118130 (CAN) PILOT REPORTED, THEY LINED UP FOR TAKEOFF WITH PASSENGERS ON BOARD. WHEN HE ADVANCED THE THROTTLES FOR TAKEOFF, TH E RT ENGINE DID NOT COME OUT OF IDLE. NO CAS MESSAGES. NO CURRENT FAULTS. NO CURRENT SERVICE MESSAGES. ONCE BACK AT TH E FBO PASSENGERS DEPLANED. THE PILOT STILL HAD THE RT ENG RUNNING. HE ADVANCED THE RT THROTTLE. AGAIN, NOTHING HAPPENED. SYS PARAMETERS SHOWED THE CORRECT TQA TLA. HE HIT THE EVENT BUTTON. REMOVED RT ENGINE HMU AND INSTALLED A REPLACEMENT. OPS CHECK GOOD (TC NR 20071012003) 2 L 7 2 4F RT T00005NY 2008012900050 20080129 00050 SO 2008 1 29 CA071015001 1 20070928 G 2560 010816811 SEAT BELT PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL COCKPIT BROKEN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 317552130 (CAN) AFTER STARTUP THE CAPTAIN WENT TO ATTACH AND TENSION HIS LAPBELT. AT THAT POINT THE LAP BELT DISCONNECTED FROM THE SEAT. CLOSER INSPECTION SHOWED CORROSION IN THE AREA OF THE BOLT HOLE OF THE FEMALE SIDE. THE SEATS ARE PROVIDED WITH A COVER OVER THIS AREA FOR COSMETIC REASONS. IT MAKES THE AREA DIFFICULT TO INSPECT UNLESS THE BOLT IS REMOVED AND THE CO VER ALSO REMOVED. DURING FOLLOWUP INSPECTIONS WITH OTHER SEATS IN THIS AC, MORE CORROSION WAS FOUND ON THE ATTACHMENT B RACKETS OF THE SEAT BELTS. IN ALL 3 SETS OF SEAT BELTS WERE REPLACED ON THE AIRCRAFT. A FLEETWIDE INSPECTION OF SEAT BE LTS IN THIS AREA IS BEING CARRIED OUT. AS WELL ALL COSMETIC COVERS THAT MAY INTERFERE WITH A PROPER INSPECTION HAVE BEEN 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2007110500072 20071105 00072 EA 2007 11 5 CA071015002 1 20071011 G 2750 855D10011 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE FLAP SYSTEM FAULTED W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) EVENT OCCURRED AT GATE PUSHBACK, PREFLIGHT FLAP SELECTION. FLAP FAIL CAUTION ILLUMINATED WHEN SELECTED TO 20 DEGRE ES. LT FLAPS SHOWING 2 DEGREES/RT SIDE SHOWING ZERO. BOTH FLAPS WERE PHYSICALLY AT 2 DEGREES. FAULT CODES SHOWED BPSU AT FAULT. DURING REPLACEMENT WAS ALSO FOUND THE FLAP DRIVE SHEARED. BOTH PARTS REPLACED AND RIGGED. FLAP SYSTEM TEST COMPL ETED WITH NO FURTHER FAULT NOTED. SYSTEMS CHECKS SERVICEABLE. (TC NR 20071015002) 2 L 7 2 4F 4 F RT A21EA E15NE 2007110500073 20071105 00073 NM 2007 11 5 CA071015003 1 20071015 G 5720 BRACKET DHAV DHC8 DHC8102 2809003 NM SPOILER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE ACCOMPLISHEMENT OF A PRE CHECK, A SPACE WAS OBSERVED BETWEEN THE SPOILER ACTUATOR AND THE SPOILER ACTUA TOR BRACKET. FURTHER INVESTIGATION FOUND THAT THE BRACKET WAS CRACKED. (TC NR 20071015003) 2 H 7 2 4T RT A13NM 2007110500074 20071105 00074 GL 2007 11 5 CA071015004 2 20071012 G 7323 SPLINE RROYCE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20 03013 GL GOVERNOR FAILED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA 1844 22451 (CAN) PILOT COMPLAINED OF EXCESSIVE (ROTOR) DROOPING. CHECKED AIRCRAFT RIGGING AND LOOSE ENGINE AIR LINES. REMOVED GOVER NOR FOR BLEED CLEANING AND THE DRIVE ASSY ON THE GOVERNOR WAS COMPLETELY DISCONNECTED FROM THE PT GOVERNOR. COMPONENT WA S SHIPPED FOR FURTHER ANALYSIS. (TC NR 20071015004) 1 G 7 1 3U 3 U H3WE E4CE 2008012900051 20080129 00051 NE 2008 1 29 CA071015005 2 20071012 G 7420 CH5339906 IGNITION LEAD BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE CARRYING OUT A FUEL NOZZLE REPLACEMENT, FOUND A DAMAGED INSULATOR ON THE IGNITER END OF THE IGNITION LEAD. R EPLACED IGNITION LEAD AND TESTED SERVICEABLE. (TC NR 20071015005) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2008012900052 20080129 00052 GL 2008 1 29 CA071015006 2 20070920 G 7321 23065104 FCU BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE OUT OF ADJUST W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA CAE832736 (CAN) FCU SN 304536 REMOVED FOR OVERHAUL(RUNNING NORMAL)FCU SN 308210 TSO 0 INSTALLED (FROM SAE)AND REQUIRED MAXIMUM ADJ USTMENTS,START DERICH AND START ACCEL.TO GET ENGINE TO START. AFTER 7.3HRS, OUR AME DEEMED IT NECESSARY TO CHANGE IT FO R A BETTER ONE. A LOANER FCU WAS RECEIVED AND SN 308210 WAS REMOVED AND SN 87041003 WAS INSTALLED AGAIN FROM SAE. THIS U NIT WOULD NOT EVEN START THE AC EVEN AFTER ALL ADJUSTMENTS. ANOTHER FCU WAS RECEIVED FROM ESSENTIAL TURBINES SN BR54951 AND IT WAS INSTALLED WHICH STARTED NORMALLY WITH LITTLE ADJUSTMENT. NEEDS TO CHECK ITS FLOW BENCH FOR CALIBRATION. (TC NR 20071015006) 1 G 7 1 3U 3 U H2SW E4CE 2007110500075 20071105 00075 NE 2007 11 5 CA071016001 2 20070831 G 7250 TURBINE BLADES DHAV DHC8 DHC8103 1386005 NM PWA PW121 PW121 52124 NE ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) FOLLOWING TAKEOFF, THE ENGINE EMITTED A LOUD NOISE AND WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED FRA CTURED POWER TURBINE BLADES. ASSOCIATED FRACTURE OF THE EXHAUST DUCT CLAMP RESULTED IN EXHAUST IMPINGING ON THE LANDING GEAR STRUT IN THE AIRCRAFT WHEELWELL, TRIGGERING A FIRE WARNING INDICATION. MFG WILL INVESTIGATE THE EVENT AND ADVISE O F ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016001) 2 H 7 2 4T 4 T RT A13NM E20NE 2007110500084 20071105 00084 NE 2007 11 5 CA071016002 2 20070902 G 7200 ENGINE AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE DAMAGED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 120891 (CAN) ENGINE TORQUE AND OIL PRESSURE WERE SEEN TO FLUCTUATE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED INTERNAL ENGINE DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071 016002) 2 H 7 2 4T 4 T RT A53EU E20NE 2007110500085 20071105 00085 NE 2007 11 5 CA071016003 2 20070905 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE POWER LOSS W A UNSCHED LANDING R E J PARTIAL RPM/PWR LOSS VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA (CAN) IN CRUISE, THE ENGINE EMITTED A NOISE ACCOMPANIED BY VIBRATION AND A COMPLETE LOSS OF POWER. THE AIRCRAFT CRASHED DURING FORCED LANDING. WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016003) 1 H 7 1 3T 3 T A37CE E4EA 2007110500086 20071105 00086 NE 2007 11 5 CA071016004 2 20070620 G 7200 ENGINE AYRES S2 S2RT15RESTD SO PWA PT6 PT6A34AG 52053 NE POWER LOSS W O OTHER R PARTIAL RPM/PWR LOSS AG AGRICULTURE 1 CA 56068 (CAN) DURING SPRAYING OPERATIONS, THE ENGINE LOST POWER AND THE AIRCRAFT SUBSEQUENTLY CRASHED. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016004) 1 L 7 1 3T 4 T A4SW E4EA 2007110500087 20071105 00087 2007 11 5 CA071016005 4 20070906 G 8300 GEARBOX BELL 412 412EP 1182205 SW PWA PT6T PT6T3 52045 EA MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) THE POWER SECTION CHIP DETECTOR ACTIVATED AND THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED M ETAL DEBRIS IN THE ACCESSORY GEARBOX. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016005) 1 G 7 2 4U 4 U H4SW E22EA 2007110500088 20071105 00088 NE 2007 11 5 CA071016006 2 20070802 G 7250 TURBINE BLADES BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE ENGINE DAMAGED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) ON TAKEOFF ROLL THE ENGINE EMITTED A LOUD NOISE AND THE TAKEOFF WAS ABORTED. SUBSEQUENT INSPECTION REVEALED DAMAGE D POWER TURBINE BLADES. (TC NR 20071016006) 2 L 7 2 4T 4 T RT A24CE E26NE 2008012900053 20080129 00053 NE 2008 1 29 CA071016007 2 20070908 G 7250 311608001 BEARING DOUG MD900 MD900 3027375 NM PWA PW206 PW206A NE ENGINE FAILED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) THE ENGINE CHIP DETECTOR ACTIVATED, ACCOMPANIED BY VIBRATION AND A TEMPERATURE INCREASE, AND THE ENGINE WAS SHUTDO WN IN FLIGHT. SUBSEQUENT INVESTIGATION REVEALED A DAMAGED NR3 BEARING AND RESULTANT TURBOMACHINERY DAMAGE. (TC NR 200710 16007) 1 G 7 2 3U 3 U NC H19NM E42NE 2007110500089 20071105 00089 NM 2007 11 5 CA071016008 1 20070906 G 2421 ADAPTER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE GEARBOX LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF ENGINE OIL PRESSURE WAS LOST AND THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A LEAKING GENERATOR MOUNTING PAD ADAPTER. (TC NR 20071016008) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2007110500090 20071105 00090 EU 2007 11 5 CA071016009 1 20070828 G 6123 AUTOFEATHER SYS AEROSP ATR42 ATR42500 8680948 EU PWA PW120 PW127 NE FAULTY W O OTHER F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) DURING CLIMB THE PROPELLER FEATHERED UNCOMMANDED AND RECOVERED. SUBSEQUENT INSPECTION REVEALED A FAULTY AUTOFEATHE R UNIT. 2 H 7 2 4T 4 T RT A53EU E20NE 2007110500096 20071105 00096 NE 2007 11 5 CA071016010 2 20070911 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE POWER LOSS W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA PC0605 (CAN) FOLLOWING TAKEOFF THE ENGINE LOST POWER. THE AIRCRAFT WAS DAMAGED IN THE RESULTING FORCED LANDING. 1 H 7 1 3T 3 T A37CE E4EA 2007110500097 20071105 00097 NE 2007 11 5 CA071016011 2 20070831 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE POWER LOSS W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA PC0643 (CAN) THE ENGINE LOST POWER FOLLOWING TAKEOFF AND THE AIRCRAFT WAS DAMAGED IN THE RESULTING FORCED LANDING. 1 H 7 1 3T 3 T A37CE E4EA 2007110500098 20071105 00098 NE 2007 11 5 CA071016012 2 20070915 G 7200 ENGINE AEROSP ATR72 ATR72202 8680940 EU PWA PW120 PW124B NE MAKING METAL W A UNSCHED LANDING X B J ENGINE FLAMEOUT SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA 124371 (CAN) DURING CLIMB THE ENGINE FLAMED OUT AND OIL SMELL WAS EVIDENT IN THE CABIN. SUBSEQUENT INSPECTION REVEALED METAL DE BRIS IN THE ENGINE OIL. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016012) 2 H 7 2 4T 4 T RT A53EU E2ONE 2007110500099 20071105 00099 NE 2007 11 5 CA071016013 2 20070914 G 7200 ENGINE AIRTRC AT602 AT602 0390309 SW PWA PT6 PT6A65AG 52043 NE POWER LOSS W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA PN0060 (CAN) THE ENGINE LOST POWER IN FLIGHT AND THE AIRCRAFT WAS DAMAGED IN THE RESULTING FORCED LANDING. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016013) 1 L 7 1 3T 4 T NC A19SW E4EA 2007110500100 20071105 00100 EU 2007 11 5 CA071016014 1 20070831 G 7931 310573401 REGULATOR VALVE AEROSP ATR42 ATR42300 8680920 EU PWA PW121 PW121 52124 NE ENGINE OIL PRESS FAULTY W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALE D A FAULTY OIL PRESSURE REGULATING VALVE. (TC NR 20071016014) 2 H 7 2 4T 4 T RT A53EU E20NE 2007110500101 20071105 00101 NE 2007 11 5 CA071016015 2 20070917 G 7200 ENGINE AIRTRC AT802 AT802A 0390308 SW PWA PT6 PT6A65AG 52043 NE POWER LOSS W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS FF FIRE FIGHTING 1 CA (CAN) THE ENGINE LOST POWER DURING FIREFIGHTING OPERATIONS RESULTING IN A FORCED LANDING. 1 L 7 1 3T 4 T NC A19SW E4EA 2007110500106 20071105 00106 EA 2007 11 5 CA071016016 2 20070820 G 7200 ENGINE AIRTRC AT400 AT401 0390204 SW PWA PT6 PT6A34 52043 EA POWER LOSS W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION AG AGRICULTURE 1 CA (CAN) DURING SPRAYING OPERATIONS THE ENGINE EMITTED A LOUD NOISE AND LOST POWER, RESULTING IN A FORCED LANDING. 1 L 7 1 3R 4 T A17SW E4EA 2007110500116 20071105 00116 NE 2007 11 5 CA071016017 2 20070925 G 7240 LINER CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE COMBUST CHAMBER DAMAGED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) THE ENGINE WAS REPORTED TO HAVE REPEATEDLY FLAMED OUT DURING TAXI OPERATIONS. INSPECTION REVEALED A DAMAGED/WORN C OMBUSTION CHAMBER LINER. (TC NR 20071016017) 2 L 7 2 4F 4 F RT A22CE E25EA 2007110500117 20071105 00117 EA 2007 11 5 CA071016018 2 20070927 G 7250 TURBINE BLADES PILATS PC6 PC6 7090102 EU PWA PT6 PT6A27 52043 EA ENGINE FRACTURED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) DURING AIRCRAFT STALL RECOVERY TRAINING, THE ENGINE FLAMED OUT. SUBSEQUENT RE-LIGHT ATTEMPTS WERE UNSUCCESSFUL. IN SPECTION REVEALED FRACTURED COMPRESSOR TURBINE BLADES. (TC NR 20071016018) 1 H 7 1 3O 4 T 7A15 E4EA 2008012900055 20080129 00055 NE 2008 1 29 CA071016020 1 20071014 G 2820 7630700701041 HOSE SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL FUEL DIST COLLAPSED W C ABORTED TAKEOFF X J ENGINE FLAMEOUT WARNING INDICATION TO TAKEOFF 1 CA (CAN) FUEL HOSE INTERNAL COLLAPSE (TC NR 20071016020) 1 G 7 2 3U 3 U H1NE E1GL 2008012900067 20080129 00067 EU 2008 1 29 CA071016021 1 20071016 G 2810 257PV6589A FLOAT VALVE BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE7315R 01518 WP VENTRAL TANK STUCK W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 6452 DHB97 (CAN) DURING REFUELLING USING SINGLE-POINT SYS & FILLING BOTH MAIN (WINGS) & VENTRAL TANK. AS VENTRAL TANK REACHED 1.5 T O 3 QUARTERS CAPACITY FUEL WOULD FLOW THROUGH VENT SYS INTO LT SURGE TANK & SHUTDOWN BY CLOSING MAIN VALVE. COMPLETION O F REFUELLING COULD ONLY RESUME ONCE SURGE TANK EMPTIED & VENTRAL TANK FUELED VIA FUELING CAP. ON REMOVAL OF VENTRAL TANK , DISCOVERED RT VENT FLOAT INADVERTENTLY GLUED TO VALVE BODY & NEEDLE HARD TO OPERATE. BOTH CONDITIONS LEFT RT VENT VALV E OPEN DURING ALL CONDITIONS CAUSING FUEL TO ENTER VENT PIPING THOUGH NONE EXISTED. FLOAT REMOVED & NEW NEEDLE INSTALLE D, OPS OF VALVE CHECKED FOR SMOOTHNESS & PROPER SEALING OF NEEDLE TO SEAT. MODIFICATION (25G137A) EMBODIED TO INCORPORAT 2 L 7 2 4F 4 F RT A3EU E6WE 2007110500118 20071105 00118 GL 2007 11 5 CA071017001 1 20071016 G 2434 A3579101 GENERATOR BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP RIGHT FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 330 (CAN) IN CRUISE FLIGHT RT GENERATOR FAILED. AFTER FOLLOWING PROCEDURES A/C LANDED WITHOUT ANY MORE INCIDENT. TROUBLESHOO TING WITH MDC REPORTED PCB6 AT FAULT FROM GCU P/N R608-003. FURTHER TROUBLESHOOTING REVEALED RT GENERATOR WAS AT FAULT N OT THE GCU. GENERATOR WAS REMOVED AND REPLACED AND A/C RETURNED TO SERVICE. NORMAL TBO FOR GENERATOR IS 3000 HRS GENERAT OR HAD ONLY 329.7 HRS. MANUFACTURER OF GENERATOR IS AUXILEC (F0296) TAKEN ON DATA PLATE. (TC NR20071017001) 2 L 7 2 4F 4 F RT T00005NY E00010LA 2008030600177 20080306 00177 EA 2008 3 6 CA071017002 1 20071017 G 2810 21564002 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1893 (CAN) FUEL LEAK ON BOTTOM OF FUEL CELL NR 5 LT. (TC NR 20071017002) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2008030600178 20080306 00178 EA 2008 3 6 CA071017003 2 20071012 G 7414 104001667 IMPULSE COUPLING CONT LYC O320 O320H2AD 41508 EA MAGNETO CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 671 G05KA029R (CAN) IMPULSE CAM ASSEMBLY FOUND CRACKED AT KEY WAY AREA. REPLACED WITH NEW ASSY. (TC NR 20071017003) 3 O E274 2007110500119 20071105 00119 SO 2007 11 5 CA071018001 2 20071016 G 8500 IO240B ENGINE DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA STALLED W O OTHER R Y PARTIAL RPM/PWR LOSS ENGINE STOPPAGE NR NOT REPORTED 1 CA 979 C0416 (CAN) DURING POWER ON STALL THE PROPELLER CAME TO A FULL STOP, THROTTLE WAS AT 1700 RPM AND THE NOSE POINTED UP FOR A ST ALL CONFIGURATION AND ON POWER APPLICATION THE ENGINE CAME TO A FULL STOP. THE AIRCRAFT WAS THEN POINTED NOSE DOWN, THE PROPELLER STARTED WIND MILLING AND ON THROTTLE APPLICATION THE ENGINE RE-STARTED. A/C RETURNED TO BASE WITH NO PROBLEM. THIS WAS A NEW RETROFIT EQUIPPED A/C WITH A COMPLETE -54 ENGINE CONFIGURATION. MFG WERE INFORMED AND THE COMPONENTS ARE SCHEDULED TO BE TESTED AND REMOVED BY MFG AT THE END OF THIS WEEK. (TC NR 20071018001) 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2008013100051 20080131 00051 SW 2008 1 31 CA071018003 1 20071017 G 2911 223003 ACCUMULATOR SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE331* 01514 WP MCAULY 4HFR34 4HFR34C652 NE HYD SYSTEM INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ACCUMULATOR WAS REMOVED FOR TROUBLESHOOTING HYDRAULIC LEAKS IN SYSTEM. IT WAS SUSPECTED THAT THE ACCUMULATOR WAS N OT DOING ITS JOB OF ABSORBING THE HYDRAULIC SHOCKS. UPON REMOVAL IT WAS NOTED THAT THE INTERNAL PISTON WAS INSTALLED BAC KWARDS. THE -3 ACCUMULATOR DOES NOT SHOW UP IN THE PRESENT IPC. THE ACCUMULATOR WAS INSTALLED IN 2002 AND CAME INTO INVE NTORY IN 1999 AND WAS CERTIFIED IN 1997. (TC NR 20071018003) 2 L 7 2 4T 3 T RT A8SW E2WE 6 C 3PNE 2008012900068 20080129 00068 EA 2008 1 29 CA071018004 1 20071015 G 5510 C6FSM181421 ADAPTER DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 57RF 18455 688 (CAN) WHILE REMOVING ATTACHMENT ADAPTER P/N C6FSM1814-21, IT WAS NOTED THAT THE RIVETS INSTALLED IN THE VERTICAL WEBS TO ADAPTER WERE THE INCORRECT TYPE. THE RIVETS REMOVED FROM THIS ADAPTER PLATE WERE A.D. RIVETS. THE CORRECT RIVET WOULD HAVE BEEN D.D. ADAPTER SHOWS SIGNS OF FRETTING CORROSION CAUSED BY SLIGHT MOVEMENT. 1 H 7 2 3T 4 T RT A9EA E4EA 2008012900069 20080129 00069 WP 2008 1 29 CA071019001 1 20071017 G 6520 B5631 SIGHT GLASS ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE TAIL ROTOR LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 818 (CAN) DURING INSPECTION, IT WAS NOTED THAT THERE WAS FLUID LEAKING AROUND THE TAIL ROTOR GEARBOX SIGHT GLASS. THE PART W AS REMOVED AND REPLACED WITH A NEW PART. IT WAS FURTHER EXAMINED AND NOTED THE GLASS COULD ROTATE IN THE HOUSING, NO LON GER SECURE ALLOWING FLUID TO BYPASS AND LEAKING. THERE IS NO ISSUE OF THE GLASS DEPARTING THE AIRCRAFT AND POSSIBLY STRI KING THE T/R BLADES. (TC NR 20071019001) 1 G 7 1 3O 3 O H11NM 1E4 2008012900070 20080129 00070 CE 2008 1 29 CA071019002 1 20071019 G 5740 NAS680A08 NUT PLATE CESSNA 172 172K 2072430 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL FUEL TANK BAYS MISREPAIRED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON INSPECTING THE FUEL TANKS, FOUND SEVERAL NUTPLATES PREVIOUSLY DAMAGED. UPON FURTHER INSPECTION FOUND THAT AT A PREVIOUS TIME, SOME SCREWS BROKE OFF IN THE NUTPLATES AND RATHER REPAIR/REPLACE THE NUTPLATES, IT APPEARS THE DAMAGED NUTPLATES WERE DRILLED AND SHEET METAL SCREWS WERE INSTALLED WHERE STRUCTURAL SCREWS SHOULD HAVE BEEN. THE REPAIR WAS SI MPLE, DRILL OUT THE OLD NUTPLATES AND NEW NUTPLATES INSTALLED. AS THE FUEL TANK COVERS ARE A STRUCTURAL PART OF THE WING I RECOMEND KEEPING THIS AREA IN GOOD REPAIR. (TC# 20071019002) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2008030600179 20080306 00179 NE 2008 3 6 CA071019003 2 20071013 G 7314 C8187B PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE AUX FUEL FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1122 (CAN) DURING AN ATTEMPTED START UP THE AIRCRAFT FAILED TO START. IT WAS FOUND THAT THE AUXILIARY FUEL PUMP HAD FAILED. P UMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20071019003) 1 G 7 1 3O 3 O H11NM 1E4 2008030600180 20080306 00180 NE 2008 3 6 CA071019004 2 20070712 G 7250 TURBINE BLADES EMB 120 EMB120 3260201 SO PWA 118 PW118 NE ENGINE FRACTURED W A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CL CLIMB 1 CA (CAN) ENGINE FLAMEOUT OUT IN CLIMB. RELIGHT ATTEMPT WAS UNSUCCESSFUL. SUBSEQUENT INSPECTION REVEALED FRACTURED TOWERSHAF T AND DAMAGED POWER TURBINE BLADES. (TC NR 20071019004) 2 L 7 2 4T 4 T RT A31SO E20NE 2008030600181 20080306 00181 NE 2008 3 6 CA071022001 2 20071019 G 7320 22852402115 TUBE CNDAIR CL601 CL6013A 8070802 EA GE CF34 CF343A2 30067 NE FUEL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5991 (CAN) DURING POWER PLANT BUILD UP, FOUND LINE P/N 228-52402-115 FOR PYLON STATIC PRESSURE TO FCU CRACKED AT MIDDLE. THE CRACK WAS HIDDEN BY A LINE IDENTIFICATION DECAL. LINE WAS REMOVED AND REPLACED AIRCRAFT WILL BE RETURNED TO SERVICE. (TC NR 20071022001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600182 20080306 00182 EA 2008 3 6 CA071022002 2 20071009 G 8520 LW10292 IDLER GEAR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL GEAR SHAFT WORN W K NONE O OTHER IN INSP/MAINT 1 CA 6311 1154 L41868A (CAN) DURING A SCHEDULED INSP OF THE ENGINE, THE OIL FILTER WAS REMOVED AND DISASSEMBLED. IT WAS NOTED THAT THE FILTER M EDIA CONTAINED AN ABNORMAL AMOUNT OF METAL. THE AIRCRAFT WAS FLOWN AN ADDITIONAL 10 HRS AND THE FILTER WAS AGAIN INSPECT ED. UPON INSPECTION THE FILTER CONTAINED AN ABNORMAL AMOUNT OF METAL AND AS A RESULT THE ENGINE WAS REMOVED AND SENT TO AN OVERHAUL FACILITY. THE OVERHAUL FACILITY FOUND THE CRANKSHAFT IDLER GEAR HAD EXCESSIVE PLAY AND WAS CAUSING WEAR ON T HE IDLER GEAR BUSHING. THE BUSHING GEAR WAS REPLACED AND ENGINE REASSEMBLED. (TC NR 20071022002) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008030600183 20080306 00183 WP 2008 3 6 CA071022003 1 20070930 G 8011 14924HTH STARTER ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 202 202 (CAN) REMOVED DUE TO CRACKED BASE. (TC NR 20071022003) 1 G 7 1 3O 3 O H11NM 1E4 2008012900071 20080129 00071 NE 2008 1 29 CA071022004 2 20071018 G 7320 SWITCH SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE HMU MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA CGSGH 1275 1275 (CAN) DURING GROUND RUN THE FORCED IDLE FUNCTION OF THE TWIST GRIP WAS BEING TESTED WHEN IT WAS OBSERVED TO NOT ACCELERA TE BACK TO FLIGHT IDLE WHEN RETURNED TO THE (VOL) POSITION. THIS FUNCTION IS USED TO SIMULATE ENGINE FAILURE DURING PRAC TICE AUTOROTATION. SUCCESSIVE ATTEMPTS OF ROLLING THE THROTTLE FROM (VOL) TO (MIN) TO (VOL) PRODUCED ERRATIC RESULTS, TH E ENGINE EITHER STAGNATED AT IDLE NG OR WAS SLOW TO RESPOND BACK TO FLIGHT IDLE, (NO ERROR CODES WERE RECORDED ON THE VE MD). THE FORCED IDLE MICRO SWITCH WAS TESTED IAW MFG ALERT SB NR 05.00.49, NO ANOMALIES WERE FOUND. THE SWITCH IN QUESTI ON PN DHS772-400.30 WAS REPLACED AS A TROUBLESHOOTING MEASURE. MFG MANDATORY SB A292 73 2814, INSPECTION AND LUBRICATION 1 G 7 1 3U 3 U H9EU E00054EN 2008012900072 20080129 00072 SW 2008 1 29 CA071022005 1 20071018 G 3220 7500761 BOLT GULSTM 690TP 695A 7630519 SW GARRTT TPE331 TPE33110 01514 WP ROTOL R306 R306382F7 GL DRAG BRACE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6654 6654 (CAN) DURING DISASSEMBLY OF NOSE LANDING GEAR FOR ITS 5 YEAR INSPECTION/OVERHAUL, BOLT P/N 750076-1 OF THE NOSE LANDING GEAR DRAG BRACE-NOSE LANDING GEAR STRUT WAS FOUND BENT WITH VISIBLE CRACK. CRACK WAS CONFIRMED BY NDT(LPI AND MPI). THIS WAS THE AIRCRAFT’S FIRST OVERHAUL OF ITS LANDING GEAR SINCE COMPANY PURCHASED AIRCRAFT 2 YEARS AGO. RECORDS CHECK INDIC ATED MINIMAL PARTS REPLACEMENT DURING PREVIOUS 5 YEAR OVERHAULS (TC NR 20071022005) 1 H 7 2 4T 4 T 2A4 E4WE 6 C P8EU 2008012900073 20080129 00073 EU 2008 1 29 CA071022006 1 20071003 G 6320 6894171 GEARBOX BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL NR1 ENGINE MAKING METAL W O OTHER J WARNING INDICATION CR CRUISE 1 CA 6479 3017 (CAN) APPROXIMATELY 5 MILES FROM AIRPORT, MAGI NR1 LIGHT ILLUMINATED. PULSED OFF AND 2 MINUTES LATER LIGHT ILLUMINATED A GAIN. AN EMERGENCY LANDING WAS CARRIED OUT. BOTH NR1 AND NR2 MAGNETIC PLUGS CHECKED AND FOUND CONTAMINATED WITH METAL. T HE GEARBOX WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TIC NR 20071022006) 1 G 7 2 3U 3 U H3EU E4CE 2008013100052 20080131 00052 WP 2008 1 31 CA071022007 1 20070909 G 6310 C0183 CLUTCH ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAIN ROTOR SLIPPED W A UNSCHED LANDING L NO TEST CL CLIMB 1 CA 1864 1864 (CAN) CLUTCH REMOVED DUE TO PROBLEMS AT HIGH POWER SETTINGS. POSSIBLE CLUTCH SLIPPAGE. (TC NR 20071022007) 1 G 7 1 3O 3 O H11NM 1E4 2008013100053 20080131 00053 NE 2008 1 31 CA071022008 2 20071009 G 7322 25766304 ARM ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL CONTROL BINDING W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 1470 1470 (CAN) INTERMITTENT ROTOR DROOP. FOUND BINDING ARM ON FUEL CONTROL CAUSING ERRATIC GOVERNOR OPERATION. (TC NR 20071022008 ) 1 G 7 1 3O 3 O H11NM 1E4 2008013100055 20080131 00055 WP 2008 1 31 CA071022009 1 20070912 G 2913 LINE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE HYD PUMP LEAKING W E ENGINE SHUTDOWN K FLUID LOSS TX TAXI/GRND HDL 1 CA 301 301 0814 (CAN) PUMP REPLACED DURING TROUBLESHOOTING SMALL LEAK AT SPLIT LINE ON PUMP. (TC NR 20071022009) 1 G 7 1 3O 3 O H11NM 1E4 2008013100057 20080131 00057 WP 2008 1 31 CA071022010 1 20070912 G 2916 D2112 RESERVOIR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE HYD SYSTEM VENTING W E ENGINE SHUTDOWN K FLUID LOSS TX TAXI/GRND HDL 1 CA 362 362 (CAN) HYDRAULIC RESERVOIR VENTING. (TC NR 20071022010) 1 G 7 1 3O 3 O H11NM 1E4 2008013100059 20080131 00059 EA 2008 1 31 CA071022011 2 20071019 G 7200 ENGINE BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL RIGHT MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION DE DESCENT 1 CA 1765 PCE51107 (CAN) RT ENGINE CHIP DETECTOR LIGHT CAME ON IN FLIGHT SO WE SHUTDOWN THE RT ENGINE. ENGINE BEING REMOVED AND SENT TO EN GINE O/H FACILITY FOR REPAIR. LOANER ENGINE TO BE INSTALLED. (TC NR 20071022011) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2007110500120 20071105 00120 GL 2007 11 5 CA071022012 1 20071022 G 5511 C2TP57 SPAR DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 22D 22D30 NE STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4200 (CAN) STAB SPAR FOUND CRACKED IAW AWD CF-1991-42R1 S.B 2/47. INSPECTED IAW PEN REQUIREMENTS, SPAR CRACKED ABOVE BOTH FWD ATTACH BRACKETS. ALL SPAR MODS C/W 4200HRS AGO ALONG WITH A NEW VIKING SPAR. (1992). CRACKS ABOUT .7500 INCH LENGTH RUN NING HORIZONTALLY .2500 ABOVE TOP ATTACH BOLTS, NOT IN RADIUS OF SPAR. VIKING NOTIFIED OF CRACKS IAW SB. (TC NR 20071022 012) 1 H 7 1 3R 3 R RC A806 5E1 5 C P736 2008030600199 20080306 00199 SW 2008 3 6 CA071023001 1 20071022 G 7931 OIL SYSTEM BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE LOW PRESSURE W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA CAE821945F (CAN) LOSS OF ENGINE OIL PRESSURE IN FLIGHT. ENGINE WILL BE REMOVED AND SENT FOR INVESTIGATION. (TC NR 20071023001) 1 G 7 1 3U 3 U H2SW E4CE 2008012900074 20080129 00074 SW 2008 1 29 CA071023002 1 20071022 G 6230 206040078103 NUT BELL BELL 206 206L4 1182110 SW ALLSN 250C 250C30P 03013 GL MAST ASSY LOOSE W O OTHER O OTHER NR NOT REPORTED 1 CA 620 (CAN) WHILE INVESTIGATING MAST BEARING PLAY. UNABLE TO REMOVE NUT (BEARING TORQUED). MAST ASSY SENT TO MFG FOR INVESTIGA TION. NEW MAST ASSY PROVIDED BY MFG (TC NR 20071023002). 1 G 7 1 3U 3 U NC H2SW E1GL 2008012900075 20080129 00075 CE 2008 1 29 CA071023003 1 20071015 G 2750 1013800005 CABLE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE LT FLAP DRIVE SHEARED W O OTHER O OTHER NR NOT REPORTED 1 CA 6577 (CAN) ON APPROACH , PILOTS SELECTED APPROACH FLAP. FLAPS STOPPED MOVING JUST PRIOR TO 17 DEGREES APPROACH FLAP POSITION. THE FLAP ASYMMETRY SWITCH WAS ACTIVATED. UPON INSPECTION THE LT OB FLAP DRIVE CABLE WAS CEASED. THE FLAP DRIVE CABLE WA S REMOVED AND REPLACED WITH A SERVICEABLE UNIT. FURTHER INSPECTION OF THE CABLE REVEALED IT WAS SHEARED AT APPROXIMATELY 85 INCHES OB OF FLAP MOTOR AND TRANSMISSION ASSEMBLY. EVIDENCE OF CORROSION AND MOISTURE WERE FOUND IN THE FLAP DRIVE S HEATHING AND CABLE WHICH LIKELY CONTRIBUTED TO THE CABLE FAILURE. (TC NR 20071023003) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2008012900076 20080129 00076 SW 2008 1 29 CA071023004 1 20071022 G 6230 206040078103 NUT BELL BELL 206 206L4 1182110 SW ALLSN 250C 250C30P 03013 GL MAST BEARING FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 620 52351 (CAN) WHILE INVESTIGATION MAST BEARING PLAY, UNABLE TO REMOVE NUT (BEARING TORQUE). MAST ASSEMBLY SENT TO MFG FOR INVEST IGATION. NEW MAST ASSEMBLY PROVIDED BY MFG. (TC NR 20071023004) 1 G 7 1 3U 3 U NC H2SW E1GL 2008012900077 20080129 00077 SW 2008 1 29 CA071023005 1 20071022 G 7931 OIL SYSTEM BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE LOW PRESSURE W O OTHER J WARNING INDICATION CR CRUISE 1 CA CAE821945F (CAN) LOSS OF ENGINE OIL PRESSURE IN FLIGHT. ENGINE WILL BE REMOVED AND SENT FOR INVESTIGATION. (TC NR 20071023005) 1 G 7 1 3U 3 U H2SW E4CE 2008012900078 20080129 00078 EU 2008 1 29 CA071023006 1 20071003 G 6320 6894171 GEARBOX BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL NR 1 ENGINE MAKING METAL W O OTHER J WARNING INDICATION CR CRUISE 1 CA 6473 3017 (CAN) APPROXIMATELY 5 MILES FROM DESTINATION, MAG NR1 LIGHT ILLUMINATED. PULSED OFF AND 2 MINUTES LATER LIGHT BACK ON. N R1 THROTTLE ROTATED TO IDLE, CONTINUED APPROACH TO DESTINATION, CRASH TRUCK ADVISED. ON FINAL, NR1 THROTTLE ADVANCED AN D NORMAL LANDING CARRIED OUT. ENGINE SHUTDOWN AND MAINTENANCE ADVISED. UPON INSPECTION OF UPPER MAG PLUG, 7 SLIVERS OF M ETAL WERE FOUND AND THE LOWER PLUG WAS COVERED WITH MANY PARTICLES AND FUZZ. THE ESCAPED OIL WAS CAPTURED AND METAL PART ICLES WERE VISIBLE IN THE OIL. OIL TANK DRAINED, N1 CAP FILTER REPLACED, GEARBOX OIL FILTER INSPECTED AND SCAVEMGE LINE FLUSHED. GEARBOX REPLACE WITH OVERHAULED UNIT (TC NR 20071023006) 1 G 7 2 3U 3 U H3EU E4CE 2008030600200 20080306 00200 SO 2008 3 6 CA071023007 1 20071022 G 3710 441CC7 PUMP PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL VACUUM SYS INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA 473 (CAN) WHILE PERFORMING AN COMPRESSION TEST, THE ENGINEER HEARD A SQUEAKING AS THE PROP WAS BEING ROTATED. THE SOURCE WAS INDENTIFED COMING FROM THE VACUUM PUMP. PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20071023007) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008030600201 20080306 00201 SW 2008 3 6 CA071023008 1 20071022 G 6420 206010743013 MECHANISM BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL PITCH CHANGE WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE TAIL ROTOR PITCH CHANGE MECHANISM PORTION OF THE 100 HOUR INSP, THE PITCH CONTROL TUBE BUSHING AND/OR B EARING WERE FOUND WORN BEYOND LIMITS ON THE CONTROL TUBE ASSY. AN EXHAUSTIVE CHECK OF PAPER WORK WAS CARRIED OUT FOR TH E TSN AND TSO, THESE COULD NOT BE CONFIRMED. THE PITCH CHANGE MECHANISM HAS PASSED INSPECTION ON THE LAST (2) 600 HOUR I NSPECTIONS. (TC NR 20071023008) 1 G 7 1 3U 3 U H2SW E4CE 2008030600202 20080306 00202 EA 2008 3 6 CA071024001 1 20071021 G 2750 855D10011 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS INOPERATIVE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) THE AC SUFFERED FROM (2) SIMILAR FLAP PROBLEMS IN A SHORT PERIOD OF TIME. THE 1ST OCCURRENCE HAPPENED ON OCTOBER 20TH 2007. THE CREW REPORTED A FLAP FAIL CAUTION MESSAGE AFTER TAKEOFF WHEN FLAPS WERE SELECTED UP. THE AC TURNED BACK A ND LANDED SAFELY. THE CREW COMPLETED A VISUAL INSP OF THE FLAPS, THE SYS WAS RESET AND SEVERAL CYCLES COMPLETED. UPON DE STINATION, THE FAULT CODES WERE DOWNLOADED AND THE SYS CHECKED SERVICEABLE BY MAINT. ON OCTOBER 21ST, CREW REPORTED A F LAP FAIL CAUTION MESSAGE AFTER TAKEOFF. THE EICAS SECONDARY DISPLAY FLIGHT CONTROLS PAGE WAS INDICATING LT FLAP POSITION AT 6 DEGREES AND RT AT 8 DEGREES. THE FLIGHT CREW ELECTED TO CONTINUE THE FLIGHT AND LANDED WITHOUT INCIDENT AT DESTINA 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600203 20080306 00203 SW 2008 3 6 CA071024002 1 20071019 G 6310 CL422501 CLUTCH BELL BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL FREEWHEEL UNIT CRACKED W O OTHER O OTHER LD LANDING 1 CA 1045 BLA20067 (CAN) THE A/C HAD A FREEWHEEL CHIP LIGHT AND LANDED AT MAIN BASE, AFTER DOING THE 2 MINUTE COOLDOWN THE ENGINE WAS SHUTD OWN. WHILE SPOOLING DOWN A NOISE WAS NOTICED THAT WAS NOT NORMAL. THE FREEWHEEL WAS REMOVED AND DISASSEMBLED. THE CLUTCH CAGE WAS FOUND CRACKED ON ONE SIDE AND THE INNER SHAFT HAD BRINNELLING MARKS. THESE ITEMS HAVE BEEN SCRAPPED. (TC NR 20 071024002) 1 G 7 1 3U 3 U H2SW E4CE 2008012900079 20080129 00079 NE 2008 1 29 CA071024003 2 20071023 G 7314 DIAPHRAGM LYC ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL PUMP TORN W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1215 1215 3803 (CAN) FUEL PUMP CHANGED DUE TO EXTERNAL OIL LEAKAGE. THIS USER HAS HAD 14 OF THESE FUEL PUMPS FAIL OVER THE LAST 8 MONTH S. THIS WAS THE FIRST PUMP DIASSEMBLED. IT WAS QUITE EVIDENT THAT THE UPPER DIAPHRAM HAD RUPTURED. THE SIDE OF UPPER DIA PHRAM MATERIAL EXPOSED TO THE ENGINE OIL SHOWED A DEFINITE INDICATION OF DETERIORATION AND THE RUBBER MATERIAL BREAKING DOWN. WHEREAS THE MATERIAL ON THE FUEL SIDE SHOWS NO DETERIORATION, EXCEPT WHERE THE DIAPHRAM HAD TORN. THIS LEADS US TO WONDER IF THE FUEL COMPATIBLE DIAPHRAM MATERIAL IS NOT COMPATIBLE WITH THE W80 ENGINE OIL USED. (TC NR 20071024003) 1 G 7 1 3O 3 O H11NM 1E4 2008012900080 20080129 00080 NM 2008 1 29 CA071024004 1 20071023 G 2910 82920010265 LINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE SELECTOR VALVE SEVERED W O OTHER K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) THE NR 2 HYDRAULIC ISOLATION VALVE CAUTION LIGHT ILLUMINATED APPROXIMATELY 27 NAUTICAL MILES AFTER TAKEOFF. SHORLT Y FOLLOWING THIS, THE NR2 SYSTEM HYDRAULIC FLUID DEPLETED. THE CREW CARRIED OUT THE APPLICABLE QRH PROCEDURES AND RETURN ED TO BASE. MAINTENANCE FOUND A SEVERED HYDRAULIC TUBE AT THE LANDING GEAR SELECTOR VALVE. THE HYDRAULIC TUBE WAS REPLAC ED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20071024004) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008012900081 20080129 00081 SW 2008 1 29 CA071024005 1 20071023 G 6730 41103750017 SERVO BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL HYDRAULIC SYS WORN W K NONE O OTHER IN INSP/MAINT 1 CA 1695 (CAN) PLAY NOTED IN CYCLIC CONTROL. ONCE INVESTIGATED THE PILOT VALVE LINKAGE ON RT CYCLIC SERVO FOUND WORN BEYOND LIMIT S. (TC NR 20071024005) 1 G 7 1 3U 3 U H2SW E4CE 2008012900082 20080129 00082 GL 2008 1 29 CA071024006 1 20071004 G 2823 PV332010 SHUTOFF VALVE DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE FUEL SYSTEM LEAKING W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 10229 (CAN) STRONG FUEL ODOR IN COCKPIT. INVESTIGATED AND FOUND FUEL SHUTOFF VALVE WAS LEAKING. OVERHAULED PN PV3320-10 INSTAL LED AND SYSTEM CHECKED FOR LEAKS. AIRCRAFT SERVICEABLE. (TC NR 20071024006) 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2008012900083 20080129 00083 NE 2008 1 29 CA071024007 1 20071022 G 3340 50316 BEACON SKRSKY S92 S92A NE GE CT7TS CT78A 30136 NE FAILED W O OTHER O OTHER CR CRUISE 1 CA (CAN) DURING FERRY FLIGHT (CRASH POSITION INDICATOR) DEPARTED AIRCRAFT FOR NO APPARENT REASON. UNIT DID NOT TRANSMIT. T HE DEPLOYABLE BEACON WAS INSTALLED IAW MFG DWG NR 92604-40331. (TC NR 20071024007) 2 G 7 2 4U 4 U R00024BO E8NE 2008012900084 20080129 00084 NE 2008 1 29 CA071024008 2 20071004 G 7200 ENGINE BEECH 200 B200 1152922 CE PWA PT6 PT642A NE FAILED W E ENGINE SHUTDOWN B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 CA 93447 (CAN) AT FL260, ITT INCREASED TO NEAR MAXIMUM. POWER WAS REDUCED TO FLIGHT IDLE HOWEVER ITT REMAINED HIGH. HEAVY SMOKE W AS OBSERVED COMING FROM EXHAUST. CREW ELECTED TO SHUTDOWN ENGINE AND PERFORM SINGLE ENGINE LANDING. POST FLIGHT INSPECTI ON REVEALED OIL DRIPPING FROM EXHAUST AND SEIZED PROPELLER SHAFT. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CA USE ONCE ESTABLISHED. 1 L 7 2 4T 4 T A24CE E4EA 2008012900085 20080129 00085 EU 2008 1 29 CA071024009 1 20071013 G 3246 MS2125006038 TIE BOLT AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE MLG WHEEL BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 398 CAA10 (CAN) MAINTENANCE CREWS NOTED A BROKEN MAIN WHEEL TIE BOLT. THE MAIN WHEEL ASSEMBLY AND BRAKE ASSEMBLY WERE REPLACED. (T C NR 20071024009) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008012900086 20080129 00086 CE 2008 1 29 CA071024010 1 20071021 G 3210 50810323 TORQUE KNEE BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA MCAULY 4HFR34 4HFR34C762 NE LANDING GEAR CRACKED W O OTHER E VIBRATION/BUFFET LD LANDING 1 CA (CAN) AFTER LANDING, UPON DECELERATING THROUGH 60 KIAS THE AIRCRAFT BEGAN TO VIOLENTLY SHAKE, SHUDDER AND APPEAR TO SKIP WHILE VEERING TOWARD THE LT SIDE OF THE RUNWAY. CONTROL WAS MAINTAINED AND THE AIRCRAFT WAS BROUGHT TO A SLOW TAXI AT W HICH TIME THE CONDITIONS CEASED. UPON EXAMINATION OF THE AIRCRAFT, IT WAS DISCOVERED THAT THE LT MAIN GEAR LOWER TORQUE KNEE HAD FAILED. THE TORQUE KNEE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THIS PART,4 YEARS SINCE INSPECTION, DUE EVERY 8000 LANDING OR 6 YEARS. (TC NR 20071024010) 1 L 7 2 3T 4 T A14CE E4EA 6 C 3PNE 2008012900087 20080129 00087 NM 2008 1 29 CA071024011 1 20070921 G 7931 OIL SYSTEM DHAV DHC8 DHC8202 2809007 NM PWA 120 PW123D 52152 NE ENGINE LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION CL CLIMB 1 CA AG0054 (CAN) DURING CLIMB, LOW OIL PRESSURE WARNING ANNUNCIATED. PILOT INITIATED SHUTDOWN PROCEDURES AND SINGLE ENGINE LANDING. ENGINE WAS REMOVED FOR INVESTIGATION. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071024011) 2 H 7 2 4T 4 T RT A13NM E20NE 2008012900090 20080129 00090 EU 2008 1 29 CA071025001 1 20071023 G 6200 V40G3911AA SPRING BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL EJECTOR MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 CA 20 (CAN) POOR METAL COMPOSITION IN PART CAUSES CRACKING. THESE PARTS WILL CRACK WITHOUT BEING SUBJECT TO FLIGHT. ONE BATCH HAS BEEN DISPOSED OF AND THE NEXT BATCH HAS THE SAME ISSUE. THE MFG HAS BEEN NOTIFIED. REF MBB-BO-105 IPC 60-00-00 FIG 8 ITEM NR 440. (TC NR 20071025001) 1 G 7 2 3U 3 U H3EU E4CE 2008012900091 20080129 00091 EA 2008 1 29 CA071025002 1 20071020 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 12986 12986 (CAN) DURING APPROACH, AIRCRAFT RECEIVED A FLAPS FAIL MESSAGE WITH FLAPS AT 30 DEGREES. FLAPS WERE NOT RESELECTED. RECT IFICATION: RT BRAKE POSITION SENSOR UNIT (BPSU) FOUND TO BE AT FAULT. BPSU REPLACED AND RIGGED IAW AMM. (TC NR 200710250 02) 2 L 7 2 4F 4 F RT A21EA E15NE 2008012900094 20080129 00094 NE 2008 1 29 CA071025003 2 20071004 G 7261 PT08001A01 OIL CAP DHAV DHC8 DHC8* NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE OIL FILLER MISINSTALLED W E A ENGINE SHUTDOWN UNSCHED LANDING W K J INADEQUATE Q C FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 120848 (CAN) DURING CLIMB, THE LOW OIL PRESSURE WARNING ILLUMINATED. THE CREW ELECTED TO PERFORM AN INFLIGHT SHUTDOWN OF THE EN GINE AND RETURN TO POINT OF DEPARTURE. GROUND INSPECTION REVEALED THAT THE OIL FILLER CAP HAD BEEN IMPROPERLY INSTALLED , AND THAT THE SEALING FUNCTION OF THE POST-SB 21150 FILLER NECK CHECK VALVE HAD BEEN RENDERED INEFFECTIVE THROUGH FLATT ENING OF THE O-RING AND MECHANICAL DAMAGE. (TC NR 20071025003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008012900097 20080129 00097 EU 2008 1 29 CA071025004 1 20071015 G 2820 HOSE EMB ERJ190 ERJ190100IGW 3260408 EU GE CF34 CF3410E5A1 30022 NE FUEL SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 4425 (CAN) APU FUEL FEED LINE LEAK WITHIN THE HYDRAULIC SERVICE COMPARTMENT. FUEL LEAKS FROM HOSE CORE AND SOAKS FABRIC BRAID . LEAK IS IN THE AREA OF SECOND AND THIRD SUPPORTING CLAMPS. SUGGEST THAT THIS MAY BE A MATERIAL SPECIFICATION PROBLEM. SUPPORT CLAMPS ARE INTACT AND DO NOT APPEAR TO BE CHAFFING LINE. (TC NR 20071025004) 2 L 7 2 4F 4 F RT A57NM E00070EN 2008012900100 20080129 00100 EA 2008 1 29 CA071025005 1 20071006 G 7931 O-RING DHAV DHC6 DHC6300 2802606 EA PWA PW120 PW123 NE OIL PRESSURE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 123357 (CAN) PILOT OBSERVED A SUDDEN DROP IN OIL PRESSURE AND ELECTED TO PERFORM AN IN FLIGHT SHUTDOWN. FLIGHT WAS DIVERTED. G ROUND INSPECTION REVEALED A DEFECTIVE O-RING ASSOCIATED WITH THE PCU (PROPELLOR CONTROL UNIT) ASSEMBLY. (TC NR 200710250 05) 1 H 7 2 3T 4 T RT A9EA E20NE 2008012900107 20080129 00107 NE 2008 1 29 CA071025006 2 20071011 G 7200 ENGINE BEECH 200 B200 1152922 CE PWA PT6 PT642A NE MAKING METAL W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 93724 (CAN) 15 MINUTES INTO FLIGHT, THE ENGINE CEASED OPERATION AND SIMUTANEOUSLY ILLUMINATED THE CHIP DETECTOR INDICATOR. THE CHIP DETECTOR CIRCUIT BREAKER WAS THEN REPORTED TO HAVE `POPPED`. AIRCRAFT RETURNED TO POINT OF DEPARTURE. POST FLIGHT INSPECTION REVEALED SUBSTANTIAL INTERNAL ENGINE DISTRESS. THE CHIP DETECTOR HAD `POPPED` ON THE PREVIOUS FLIGHT AND HAD BEEN RESET. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 L 7 2 4T 4 T A24CE E4EA 2008012900108 20080129 00108 CE 2008 1 29 CA071025007 1 20071024 G 5753 ROLLER BEECH BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCE4N HCE4N3 NE RT TE FLAP SEIZED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) ON APPROACH WHEN FLAPS WERE SELECTED DOWN, THE RT WING BECAME HEAVY. AILERON CONTROL WAS REDUCED AND FELT DIFFEREN T THAN NORMAL. THE PILOT LANDED WITHOUT FURTHER INCIDENT AND SELECTED FLAPS UP. THE FLAPS DID NOT MOVE WHEN SELECTED UP, SPLIT-FLAP SAFETY MECHANISM WAS ACTUATED. THE RT OB FLAP, IB AFT ROLLER APPEARS TO HAVE SEIZED AND TORE OUT OF THE FLA P BRACKET. WHEN THE AMO DRILLED APART THE FLAP FOR REPAIR, THEY NOTED THAT THE BRACKET WAS WORN THIN FROM THE ROLLER. TH IS, WOULD ONLY BE VISIBLE ONCE THE ROLLER WAS REMOVED. THE MM DOES NOT SPECIFICALLY REQUIRE REMOVAL OF FLAPS OR ROLLERS FOR INSPECTION OR LUBRICATION. A REGULAR REMOVAL OF ALL FLAPS TO INSPECT CONDITION OF ROLLERS AND FLAP BRACKETS WOULD L 1 L 7 2 4T 4 T A24CE E4EA 5 C P10NE 2008012900109 20080129 00109 NM 2008 1 29 CA071025008 1 20071022 G 7931 OIL SYSTEM DHAV DHC8 DHC8* NM PWC 150 PW150A EA ENGINE LOW PRESSURE W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA FA0060 (CAN) DURING CRUISE, THE LOW OIL PRESSURE WARNING WAS ACTIVATED FOLLOWED BY SURGING AND UNCOMMANDED SHUTDOWN. THE FLIGHT WAS DIVERTED. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071025008) 2 H 7 2 4T 4 T RT A13NM E00062EN 2008012900110 20080129 00110 NE 2008 1 29 CA071025009 2 20071020 G 7250 ACCESSORY UNIT DHAV DHC8 DHC8201 2809001 NM PWA PW120 PW123 NE ENGINE DAMAGED W E ENGINE SHUTDOWN J WARNING INDICATION NR NOT REPORTED 1 CA 123012 (CAN) THE ENGINE WAS REPORTED TO HAVE HAD AN IFSD. GROUND INSPECTION REVEALED THE POWER TURBINES DID NOT TURN FREELY AND THE ACCESSORY DRIVE WAS DAMAGED. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071 025009) 2 H 7 2 4T 4 T RT A13NM E20NE 2008012900111 20080129 00111 NM 2008 1 29 CA071025010 1 20071015 G 3242 CABLE EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE PARKING BRAKE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 4928 (CAN) AFTER PUSHBACK, PARKING BRAKE CABLE BROKE. EMERGENCY PARKING BRAKE CABLE ASSY REPLACED IAW AMM 32-44-03 (TC NR 200 71025010) 2 L 7 2 4F 4 F RT A56NM E00063EN 2008012900112 20080129 00112 EA 2008 1 29 CA071025011 1 20071017 G 5410 22850080 COWLING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE THRUST REVERSER LOOSE W O OTHER D INFLIGHT SEPARATION LD LANDING 1 CA 12626 (CAN) ACTUALLY WE HAVE A AOG A/C AT PRG. DURING THRUST REVERSER OPERATING AFTER TOUCHDOWN AT PRG WE’RE LOSING THE UPPER AND LOWER RT ENGINE COWLINGS. ONE OF THE COWLINGS HIT THE A/C AT FS 700 IN BETWEEN STR 5 TO 7 AND DAMAGED THE FUSELAGE A ND ALSO THE FRAME FS STN 700. (TC NR 20071025011) 2 L 7 2 4F 4 F RT A21EA E15NE 2008012900113 20080129 00113 SW 2008 1 29 CA071026001 1 20071012 G 2435 150SG117Q STARTER GEN BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL DEFECTIVE W K NONE O OTHER IN INSP/MAINT 1 CA 4132 251 (CAN) DURING SHUTDOWN, IT WAS NOTED THAT A NOISE WAS COMING FROM THE ENGINE BAY AREA. FURTHER INVESTIGATION NOTED THE ST ARTER GEN REQUIRED TO BE REPLACED. STARTER GEN WAS REPLACED FOR NO FURTHER DEFECTS. (TC NR 20071026001) 1 G 7 1 3U 3 U H2SW E4CE 2008012900114 20080129 00114 EA 2008 1 29 CA071026002 1 20071024 G 5711 215003268 SPAR CAP CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE WS 50.0 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4279 (CAN) WHILE PERFORMING AD 92-26R1 IAW SB 215-A454 REV 3, NO DEFECTS WERE FOUND IAW OUTLINED ULTRASONIC INSPECTION PROCED URES. THE NDI TECH NOTED THAT HE WAS PICKING UP WHAT HE THOUGHT WAS A SUSPECTED CRACK OUTSIDE THE AREA OUTLINED IN THE S B AND PROCEEDED TO ENQUIRE ABOUT THE SURROUNDING STRUCTURE WITH A COMPANY AME. FS 434.8 REAR SPAR WS 50.0 THE SUSPECTED CRACK ON THE ULTRASOUND WAS SHOWN TO THE AME AND A LINEAR MEASUREMENT WAS MADE AS TO THE SCALE ON THE INSTRUMENT. IT WAS BELIEVED THAT THE CRACK WOULD BE AT APPROXIMATELY LT WING WS 50.0 IN LINE WITH THE REAR OUTER VERTICAL PICK-UP ANGLE TO REAR SPAR CAP ATTACHMENT VIA LOCK FASTENER. NR 2 FUEL CELL AND FUEL BAY LINERS WERE REMOVED AND A CRACK IN THE PAINT PR 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 2008012900116 20080129 00116 SW 2008 1 29 CA071026003 1 20071025 G 6710 204001363015 CYCLIC STICK BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 24962 (CAN) PILOTS CYCLIC STICK DISASSEMBLED FOR PAINT AND REFURBISH. STEEL RING PN 204-001-369-001 IS RIVETED ON THE CYCLIC S TICK. THE STEEL RING IS USED FOR APPLICATION OF FRICTION. THE STEEL RING WAS REMOVED AND EXTREME CORROSION PITTING WAS F OUND IN THE CYCLIC STICK. IF THE CORROSION DEPTH COULD BE MEASURED ACCURATELY IT WOULD BE 40-50 PERCENT OF THE TUBE THIC KNESS. PULLED A USED CYCLIC STICK ASSY OUT OF OUR STOCK INVENTORY DISASSEMBLED IT ONLY TO FIND IT CORRODED AS WELL NOT Q UITE AS BAD BUT BEYOND SERVICEABLE. FINDING 2 HAS PROMPTED US TO CONSIDER THIS TO BE MORE THAN A ONE OF ISSUE CORROSION ISSUE. (TC NR 20071026003) 1 G 7 1 4U 4 U H4SW E22EA 2008012900118 20080129 00118 WP 2008 1 29 CA071026004 1 20071023 G 3251 ACTUATOR CVAC 440 440 2422902 WP ALLSN 501D 501D13D 03004 GL ALLSN A6441 A6441FN606 GL NLG STEERING MALFUNCTIONED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 2882 (CAN) DURING APPROACH WHEN LANDING GEARS SELECTED DOWN, THE LANDING GEARS UNLOCK LIGHT CAME ON, HOWEVER, NO NOSE WHEEL D OWN LIGHT CAME ON. THE CREW CONFIRMED VISUALLY GEAR NOT DOWN. AFTER A FEW CYCLES GEAR UP AND GEAR DOWN AND EMERGENCY UPL ATCH RELEASE TO NO AVAIL. AFTER TURNING NOSE GEAR STEERING THE NOSE GEAR CAME DOWN AND LOCKED NORMALLY. THE NOSE GEAR ST EERING ACTUATOR FOUND TO BE CREEPING TO THE RT ON ITS OWN INTERMITTENTLY. SUBSEQUENT INSPECTION FOUND THAT THE UPPER PIV OT POINT WAS WORN. STEERING ASSY REMOVED AND SENT TO OVERHAUL SHOP FOR INVESTIGATION AND OVERHAUL. 2 L 7 2 4R 4 T 6A6 E282 6 C P898 2008012900119 20080129 00119 EU 2008 1 29 CA071026005 1 20071016 G 2722 793500501 ACTUATOR ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE73131G 29003 NE RUDDER TRIM FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE PERFORMING AN A-CHECK, THE RUDDER TRIM ACTUATOR (PN: 793500-501) FAILED THE FREE PLAY CHECK IAW MM 5-20-06 P ARA: 1.F.(4) AND MM 27-20-00 PAGE 503 PARA: 4.A. A NEW RUDDER TRIM LOWER ACTUATOR (PN: 793500-501) (ALTERNATE PN:1092AS1 00-3) WAS ORDERED. WHEN RECEIVED, THE NEW ACTUATOR 8130-3 RELEASE FORM STATED THAT THE UNIT WAS OVERHAULED. THE PART HAD 3 DISCREPANCIES, BOTH ROD ENDS WERE WORN, CORRODED, SCORED, ALSO THE ELECTRICAL LEAD, CONNECTOR PLUG WAS CORRODED. THE UNIT WAS RETURNED TO VENDOR. (TC NR 20071026005) 2 M 7 2 4F 4 F A2SW E6WE 2008013100060 20080131 00060 SW 2008 1 31 CA071026006 1 20071024 G 6210 4711012050 BLADE BELL 47 47G2 1181008 SW LYC O435 VO435A1D 41516 EA MAIN ROTOR BROKEN W R A AUTOROTATION UNSCHED LANDING D E INFLIGHT SEPARATION VIBRATION/BUFFET AP APPROACH 1 CA 1664 (CAN) DURING NORMAL TRAINING FLIGHT, VIBRATION WAS FELT AND AUTOROTATION LANDING CARRIED OUT. UPON SHUTDOWN AND INSPECTI ON OF BLADES, A FIVE (5) FOOT SECTION OF BLADE COVERING WAS DISCOVERED MISSING FROM THE UNDERSIDE OF THE BLADE FROM THE TIP EXPOSING THE WOOD BLADE CORE CAUSING THE ABNORMAL VIBRATION. BLADES WERE REMOVED AND AIRCRAFT TRANSPORTED BACK TO TH E MAINTENANCE FACILITY. NTSB WERE ON SITE SHORTLY AFTER AND REQUESTED THAT THE BLADES BE SHIPPED OFF FOR A DETAILED EXAM INATION. (TC NR 20071026006) 1 G 7 1 3O 3 O H1 E279 2008013100061 20080131 00061 EU 2008 1 31 CA071026007 1 20071018 G 3240 50028053 BRAKE ASSY ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE73131G 29003 NE RT MLG FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 3 (CAN) A-CHECK INSPECTION COMPLETED AT AIRCRAFT. FOLLOWING INSPECTION A TEST FLIGHT WAS COMPLETED, ON RETURN TO BASE, IT WAS NOTED THAT THE RT BRAKE WAS DRAGGING. MAINTENANCE FOUND TOP AFT GRIP AND TUBE OUT OF ADJUSTMENT. REMOVED AND RESET A SSEMBLY TO NEUTRAL POSITION, OPS CHECK BRAKE SERVICEABLE. AC DEPARTED, UPON LANDING THE PILOT NOTED THAT THE BRAKE WAS D RAGGING, AND FOUND THE RT BRAKE WAS NOT FULLY RELEASING. MAINTENANCE WAS CALLED IN, REMOVED RT BRAKE ASSEMBLY (PN: 50028 05-3 S/N: S-MAR88-2), AND INSTALLED OVERHAULED BRAKE ASSEMBLY (PN: 5002805-3 S/N: OCT 85-522) PER MM 32-43-01. AIRCRAFT RETURNED TO SERVICE. UNSERVICEABLE BRAKE ASSEMBLY RETURNED TO VENDOR (TSO: 2.7 HRS, 2 LANDINGS).REQUESTING VENDER TO SUP 2 M 7 2 4F 4 F A2SW E6WE 2008020400156 20080204 00156 EU 2008 2 4 CA071026008 1 20071023 G 2910 137311D1233 LINE BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33110UG 01514 WP MCAULY 4HFR34 4HFR34C652 NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE 200 HOUR AIRFRAME INSP, HYD FLUID WAS FOUND TO BE LEAKING FROM ABOVE THE BAGGAGE POD ON THE BELLY OF THE AC. THE AIRCRAFT`S IMPENDING DEPARTURE WAS CANCELLED, AND THE POD REMOVED TO INVESTIGATE. IT WAS FOUND THAT TH ERE WAS A CLAMP MISSING ON THE MAIN HYD RETURN LINE, WHICH ALLOWED THE BACKSIDE OF AN ADELL CLAMP ON A HYD PRESS LINE TO CHAFF ON THE MAIN RETURN LINE. THIS CHAFFING ACTION WAS FOUND TO HAVE BREACHED THE RETURN LINE, P/N 137311D1233. THE RE TURN LINE WAS REMOVED AND REPLACED WITH A SERVICEABLE LINE, ALL CLAMPS AND LINES IN THE AREA WERE INSPECTED FOR PROPER A SSEMBLY AND CHAFFING AND NO OTHER DEFECTS WERE NOTED. THE AIRCRAFT HYDRAULIC SYSTEM WAS SERVICED AND BLED AND THE AIRCRA 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C 3PNE 2008013100063 20080131 00063 NM 2008 1 31 CA071026009 1 20071026 G 5315 147A55067 FLOORBEAM BOEING 737 737790 13844CN NM BS 986.5 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CABIN BS 986.5 BEAM UPPER CAP CORRODED AT LBL24, LBL18, RBL10, RBL, RBL32, RBL28, RBL22, RBL17 REPAIRED IAW CU STOMER EA. (TC NR 20071026009) 2 L 7 2 4F RT A16WE 2008013100064 20080131 00064 GL 2008 1 31 CA071026010 1 20071026 G 3246 C2US1285A LINK ASSY DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 22D 22D30 NE AT SKI ATTACH CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 10 (CAN) SKIS OLD SURPLUS PARTS, 0 HRS, PUT INTO SERVICE 1 YR AGO. SKIS INSPECTED TO REATTACH TO AIRCRAFT, DISASSEMBLED FOR MAINTENANCE. UPON REMOVAL OF LINK ASSY FROM SKI PIVOT ATTACHMENT, BASE OF LINK FOUND CORRODED OUT AND U/S. CORROSION WO ULD HAVE ONLY BEEN APPARENT DURING FULL DISASSEMBLE OF SKI, NOT A NORMAL PRACTICE. SKIS APPEAR TO HAVE BEEN OILED IAW EN GINEERING DWG, BUT 1 PLUG SCREW IS MISSING AND ANOTHER LOSE, LIKELY CAUSE OF WATER TO ENTER LINK ASSY. (TC NR 2007102601 0) 1 H 7 1 3R 3 R RC A806 5E1 5 C P736 2008013100066 20080131 00066 NM 2008 1 31 CA071026011 1 20071026 G 5320 453A26113 STRIP BOEING 737 737790 13844CN NM BS 847-947 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION ON CAP STRIP BETWEEN BS 847 AND BS 947 RT SIDE AFT CARGO REPAIRED IAW CUSTOMER EA. (TC NR 20071026011) 2 L 7 2 4F RT A16WE 2008013100067 20080131 00067 NM 2008 1 31 CA071029002 1 20070815 G 2701 MS21919WDG9 CLAMP EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE COLUMN ROD LOOSE W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA (CAN) PRIOR TO PUSHBACK, WHEN TOE BRAKES WERE PRESSED TO RELEASE PARK BRAKE, THE CONTROL COLUMN YOKE MOVED AFT APPROX 1 INCH. REF: LOAD CELL INSTALLATION. THE CLAMP IS INSTALLED ON THE CONTROL COLUMN ROD ASSY ON THE TAPERED SECTION OF THE R OD. THE CLAMP CANNOT BE PROPERLY TIGHTENED DUE TO THE ANGLE IN THE ROD AND EVENTUALLY BECOMES LOOSE. WHEN THE CLAMP IS F REE TO MOVE ALONG THE ROD, IN CERTAIN CONDITIONS, THE CLAMP CAN INTERFERE WITH CONTROL COLUMN MOVEMENT. MFG HAS CORRECT ED THE PROBLEM ON OTHER AC, NOT ON THIS AC, THUS A MODIFICATION IS REQUIRED. (TC NR 20071029002) 2 L 7 2 4F 4 F RT A56NM E00063EN 2008013100068 20080131 00068 NE 2008 1 31 CA071029003 2 20071019 G 8530 399357 CYLINDER AYRES S2 S2RHGT65 0970110 SO PWA R1340 R1340AN1 52016 NE HAMSTD 23D 23D40 NE NR 7 CRACKED W O OTHER J WARNING INDICATION NR NOT REPORTED 1 CA 910 910 (CAN) PILOT REPORTED FAILURE OF ENGINE TO MAINTAIN FULL POWER AT THE TAKEOFF SETTING. AIRCRAFT RETURNED TO THE RAMP. COM PRESSION TEST REVEALED CYLINDER NR 7, WAS LOW ON COMPRESSION AND LEAKING VIA A CRACK IN THE EXHAUST PORT AREA OF THE CYL INDER. THE OFFENDING CYLINDER WAS REMOVED AND AN OVERHAULED CYLINDER WAS INSTALLED. AIRCRAFT RETURNED TO FLIGHT STATUS. (TC NR 20071029003) 1 L 7 1 3T 3 R NC 5E2 6 C P719 2008013100069 20080131 00069 SW 2008 1 31 CA071029004 1 20070809 G 6320 HOUSING BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL M/R TRANSMISSION CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA BMC00040 (CAN) OIL FOUND ON TRANSMISSION DECK AFTER BRIEF DAILY INSPECTION, OIL LEAK FOUND FROM THE BOTTOM OF THE TRANSMISSION. UPON FURTHER INVESTIGATION TRANSMISSION REMOVED AND BOTTOM CASING FOUND TO BE CRACKED AT LOWER MAST SUPPORT BRG. (TC NR 20071029004) 1 G 7 1 3U 3 U H2SW E4CE 2008013100070 20080131 00070 CE 2008 1 31 CA071029005 1 20071027 G 3240 10310300 BOLT CLEVELAND BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCE4N HCE4N3 NE TORQUE PLATE MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 337 (CAN) DURING MAINTENANCE ON AIRCRAFT, NR 4 MAIN TIRE WORN TO LIMITS. DURING NR 4 MAIN WHEEL AND TIRE CHANGE, FOUND 3 OU T OF 6 BRAKE TORQUE PLATE ATTACH BOLTS MISSING AND REMAINING ATTACH BOLTS LOOSE. A LOOSE BOLT WAS FOUND LODGED IN WHEEL BETWEEN A WHEEL HALF TIE BOLT HEAD AND THE BRAKE DISC. 3 NEW BOLTS WERE INSTALLED AND ALL 6 BOLTS WERE INSTALLED AND TO RQUED TO MFG SPECS. OTHER 3 BRAKE INSTALLATIONS AND 4 BRAKE INSTALLATIONS VISUALLY VERIFIED NO BOLTS MISSING. HAVE CONT ACTED MFG TO PURSUE THE USE OF DRILLED AND LOCKWIRED BOLTS. (TC NR 20071029005) 1 L 7 2 4T 4 T A24CE E4EA 5 C P10NE 2008012900120 20080129 00120 2008 1 29 CA071029006 4 20071025 G 3197 MS2524475 CIRCUIT BREAKER BELL 205 205B SW LYC T53 T5317BLYC 41616 NE ODOR W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) SMOKE AND ODOR IN CABIN. LANDED BACK AT PAD. (TC NR 20071029006) 1 G 7 1 4U 4 U H1SW E17EA 2008012900121 20080129 00121 EA 2008 1 29 CA071029007 1 20071029 G 5544 DAT4864A BEARING CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE RUDDER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 421 (CAN) RUDDER BEARING FOUND DAMAGED ON C-CHECK. THE BEARING WAS INCORPORATED BY SB ON WINTER WORK 2005-2006 AND CUMULATE 421 HOURS SINCE INSTALLATION. A/C HOURS 2141 CYCLES 1316 DROPS 11678 (TC NR 20071029007) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2008012900122 20080129 00122 EU 2008 1 29 CA071029008 1 20071026 G 5320 120A6050 FRAME GROB 120 G120A 1660208 EU LYC O540 AEIO540D4D5 EA HARTZL HCC3Y HCC3YR GL OIL COOLER DAMAGED W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CR CRUISE 1 CA 659 (CAN) FLIGHT DEPARTED AT 1344 FOR AT TRAINING FLIGHT TO THE WEST PRACTICE AREA. APPROXIMATELY 5 MINUTES OUT WHILE CRUISI NG AT 4000 FT AND 120 KTS THE INSTRUCTOR OBSERVED (ALT OFF) ANNUNCIATION. A SCAN OF INTEGRATED ENGINE DISPLAY REVEALED ( AMPS) TO BE READING -24A AND VOLTAGE READING 24.7V. THE INSTRUCTOR THEN OBSERVED (VOLT) ANNUNCIATION. THE INSTRUCTOR FOL LOWED EMERGENCY CHECKLIST AND SELECTED (ALTERNATOR) SWITCH OFF AND REMOVED NON-ESSENTIAL ELECTRICAL LOADS. THIS RESULTED IN A REDUCED NEGATIVE LOAD OF -9A. INSTRUCTOR THEN BRIEFLY CONFIRMED FAULT BY RETRYING (ALTERNATOR) SWITCH ON - LOAD WE NT BACK TO -24A , (ALTERNATOR) SWITCH WAS IMMEDIATELY SELECTED OFF AGAIN. THE INSTRUCTOR MADE (PAN) CALL AND RETURNED . 1 L 7 1 3O 3 O RT A49CE 1E4 5 C P25EA 2008012900123 20080129 00123 NM 2008 1 29 CA071029009 1 20071027 G 3220 273A45141 SHAFT BOEING 737 737* NM CFMINT CFM567 CFM567B22 13802 NE NLG CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 6885 (CAN) THE FLIGHT CREW REPORTED THAT AFTER TAKEOFF, (THE NOSE GEAR INDICATES DOWN IN THE UP POSITION. WHEN GEAR HANDLE PU T IN THE OFF POSITION, THE NOSE GEAR CAME DOWN.) THE FLIGHT RETURNED TO BASE AND MADE AN UNEVENTFUL LANDING. MANUAL EXT ENSION ARM FOUND IN THE EXTEND POSITION AND WOULD NOT RELEASE. PAINT FOUND ON THE P/N 273A4514-1 SHAFT. PAINT REMOVED, M ICARTA BUSHINGS CLEANED AND SHAFT REINSTALLED IAW OHM 32-35-05 AND SOPM 20-50-01. NOSE GEAR RETRACT TEST C/W IAW AMM 32- 33-00 WITH NO FAULT FOUND. HAVE ADVISED MFG OF THE EVENT AND THE REPORT OF PAINT FOUND ON THE SHAFT ASSEMBLY. (TC NR 20 071029009) 2 L 7 2 4F 4 F RT A16WE E00055EN 2008012900124 20080129 00124 EA 2008 1 29 CA071029010 1 20071028 G 2821 63E951 HOUSING GRIMES CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE FUEL FILTER DAMAGED W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA GWD16759 (CAN) JUST BEFORE PUSHBACK, THE RAMP CREW OBSERVED A FUEL LEAK COMING FROM THE APU AREA. CAPTAIN PERFORMED RAPID PASSENG ER DEPLANEMENT WITH EMERGENCY CREWS ON STAND-BY. MAINTENANCE FOUND THE FUEL LEAK COMING FROM THE NR 2 ENGINE- FUEL FILT ER HOUSING, BY THE FUEL FILTER IMPENDING BYPASS PLUG. IN THIS AREA, THE FUEL FILTER HOUSING AND THE SQUARE PLUG WERE FOU ND GROOVED AND THE SQUARE PLUG SEAL WAS FOUND DAMAGED AS WELL. MAINTENANCE REPLACED THE ALL FUEL FILTER ASSY. (TC NR 200 71029010) 2 L 7 2 4F 4 F RT A21EA E15NE 2008012900125 20080129 00125 CE 2008 1 29 CA071029011 1 20071027 G 2710 CONTROL CABLE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL AILERONS CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) GRINDING NOISE UNDER PILOT FLOOR WHEN AILERONS ARE MOVED. CONTROL CABLE FOUND CHAFING ON STEEL BRAIDED NITROGEN LI NE. APPROX 3 INCH DEFLECTION OF CONTROL CABLE CAUSED, DUE TO INCORRECT ROUTING OF NITROGEN LINE. NITROGEN PRESSURE LINE REROUTED. AILERON CABLE HAS 1 BROKEN STRAND WITHIN ACCEPTABLE LIMITS IAW AMM CH20-04-00-201 (TC NR 20071029011). 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2008012900127 20080129 00127 SW 2008 1 29 CA071030001 1 20071024 G 2915 204076437003 CHECK VALVE BELL 412 412EP 1182205 SW HYD SYSTEM OBSTRUCTED W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 CA 4 (CAN) DURING GROUND RUN, FIRST START OF THE DAY, BOTH HYDRAULIC SYSTEMS NR 1 AND NR 2 INDICATED GOOD PRESSURE AND BOTH H YDRAULIC CAUTIONS WERE EXTINGUISHED. THE FORCE TO DISPLACE PEDALS WAS NOTED TO BE ABNORMALLY HIGH. TO CONFIRM SYSTEM NR 1 WAS FUNCTIONING CORRECTLY, SYSTEM NR 2 WAS SELECTED OFF. A TOTAL LOSS OF HYDRAULICS WAS ENCOUNTERED TO BOTH CYCLIC AND COLLECTIVE. THE AIRCRAFT WAS IMMEDIATELY SHUTDOWN. DURING INVESTIGATION, FOD WAS FOUND OBSTRUCTING THE CHECK VALVE, O RIGIN OF FOD IS UNKNOWN AND UNDER INVESTIGATION. (TC NR 20071030001) 1 G 7 2 4U H4SW 2008012900128 20080129 00128 CE 2008 1 29 CA071030002 1 20071025 G 5753 501600183 FLAP TRACK BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL TE FLAPS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 26566 (CAN) ON MAINTENANCE WALKAROUND THE RT OB FLAP HAD MORE PLAY THAN USUAL. FLAP WAS REMOVE AND THE OB FLAP TRACK WAS FOUND TO BE CRACKED ON THE REAR TIP. TRACK REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20071030002) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2008012900130 20080129 00130 GL 2008 1 29 CA071030004 2 20071029 G 7261 6898607 CARBON SEAL ALLSN BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL NR 1 DAMAGED W K NONE K J FLUID LOSS WARNING INDICATION IN INSP/MAINT 1 CA 36 CAC39586 (CAN) DURING AN OIL LEAK WAS DISCOVERED BY THE BLEED VALVE. NR 1 BEARING CARBON SEAL FOUND DAMAGED, THE BEARING WAS REM OVED AND UPON INSPECTION FOUND UNSERVICEABLE. THE BEARING WHEN TURNED HAD A ROUGH, COURSE FEELING TO IT. (TC NR 20071030 004) 1 G 7 1 3U 3 U H2SW E4CE 2008012900131 20080129 00131 2008 1 29 CA071030005 4 20071016 G 3418 CONNECTOR LEAR 35 35A 5170602 CE GARRTT TFE731 TFE73122B 01518 WP STALL WARNING TRANSPOSED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) DURING A 300HR INSPECTION THE STALL WARNING ACCELEROMETER CHECK WAS DUE ( IAW AD 82-01-05). WHEN CHECK WAS CARRIED OUT, THE STALL WARNING SYSTEM FAILED. WHEN SYSTEM WAS TROUBLESHOT, IT WAS DISCOVERED THAT CONNECTORS BNC 3 AND BNC 4 (F ORM PIN D AND PIN F RESPECTIVELY) WERE FOUND REVERSED. CONNECTORS SWITCHED BACK AND STALL WARNING SYSTEM FUNCTIONED CHEC KED SERVICEABLE. SYSTEM LAST CHECKED AT A MFG SERVICE CENTER. (TC NR 20071030005) 2 L 7 2 4F 4 F A10CE E6WE 2008012900132 20080129 00132 NM 2008 1 29 CA071030006 1 20071030 G 5730 112A41029 SKIN PANEL BOEING 737 737790 13844CN NM LWS 260 & 240 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT WING LWR SKIN PANEL CHAFFING DAMAGE FROM CONTACT WITH NACELLE STRUT AFT FAIRING BLADE SEAL APPROX WSTA 260, 240 REPAIRED IAW EA 5720-01337. (TC NR 20071030006) 2 L 7 2 4F RT A16WE 2008012900134 20080129 00134 NM 2008 1 29 CA071030007 1 20071030 G 5730 112A410210 SKIN PANEL BOEING 737 737790 13844CN NM RWS 240,260 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT WING LWR WING SKIN PANEL CHAFFING DAMAGE FROM CONTACT WITH NACELLE STRUT AFT FAIRING BLADE SEAL APPROX WSTA 240 ,262 REPAIRED IAW EA 5720-01338. (TC 20071030007) 2 L 7 2 4F RT A16WE 2008012900135 20080129 00135 SO 2008 1 29 CA071030008 1 20071025 G 7720 41506 INDICATOR PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL OIL TEMP ERRATIC W O OTHER H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA (CAN) DURING RUN-UP, OIL TEMP INDICATOR DROPPED OFF SCALE. THEN WENT BACK TO NORMAL INDICATION. THE ERATIC OPERATION COU LD BE INDUCED BY ENERGIZING DIFFERENT ELECTRICAL EQUIPMENT. HOURS IN USE, NONE AT THIS TIME. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008012900136 20080129 00136 NE 2008 1 29 CA071030009 2 20071029 G 7314 LW15473 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYS LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1460 (CAN) DURING AN INSPECTION, THE ENGINEER NOTED THAT THE ENGINE DRIVEN FUEL PUMP HAD EVIDENCE OF OIL LEAKAGE AROUND THE S EAL AREA (BODY). PUMP WAS REMOVED, REPLACED AND NO FURTHER ISSUES WERE NOTED. THERE HAS BEEN MANY OF THE THESE PUMPS LAT ELY WITH VARIOUS HRS OF FAILURE. (TC NR 20071030009) 1 G 7 1 3O 3 O H11NM 1E4 2008012900138 20080129 00138 SW 2008 1 29 CA071030010 1 20071030 G 7920 6899246 HOUSING BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL OIL FILTER MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA CAG34008 (CAN) DUE TO A INTERNAL CASTING DEFECT INSIDE THE OIL FILTER HOUSING, THE PRESSURE REGULATING POPPET CANNOT FULLY BOTTOM OUT WHEN INSTALLED. THIS THEN GIVES A FALSE INDICATION OF PROPER POSITION OF THE POPPET WHEN (BACKED OUT) 5.5 TURNS FOR INITIAL ADJUSTMENT FOLLOWING OVERHAUL. THE MFG WAS ADVISED AND RECOMMENDS THAT AN APPROVED FACILITY MACHINE THE INTERNA L SURFACE OF THE HOUSING TO REMOVE THE DEFECT. (TC NR 20071030010) 1 G 7 1 3U 3 U H2SW E4CE 2008012900139 20080129 00139 NE 2008 1 29 CA071030011 2 20071008 G 7314 DIAPHRAGM LYC ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL PUMP LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 797 4105 (CAN) DURING INSPECTION, ENGINEER DISCOVERED OIL LEAKAGE FROM VENT. SUSPECT DAMAGED DIAPHRAGM. (TC NR 20071030011) 1 G 7 1 3O 3 O H11NM 1E4 2008012400333 20080124 00333 GL 2008 1 24 CA071031002 1 20070417 G 7160 6552241 INTAKE PIPE CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO HARTZL HCJ2Y BHCJ2YF1 GL ENGINE DETERIORATED W K NONE E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 394 (CAN) INTAKE PIPE FLANGE DETERIORATED AND AIR LEAK OCCURRED. ENGINE IDLE INCREASED AND ENGINE RUNS SLIGHTLY ROUGH. INSTA LLED NEW INTAKE PIPE P/N 655224-1 AND GASKET 554227 (NR 3 CYLINDER) (TC NR 20071031002) 1 L 7 1 3O 3 O NT A00009CH E1CE 5 C P37EA 2008013100092 20080131 00092 SO 2008 1 31 CA071031004 2 20070621 G 8530 6552241 TUBE CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO HARTZL HCJ2Y BHCJ2YF1 GL CYLINDER INTAKE DETERIORATED W O OTHER E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 470 (CAN) INTAKE TUBE AT FLANGE TO CYLINDER DETERIORATED. NEW INTAKE PIPE 655224-1 AND GASKET 554227 INSTALLED (NR 3 CYLINDE R). (TC NR 20071031004) 1 L 7 1 3O 3 O NT A00009CH E1CE 5 C P37EA 2008013100095 20080131 00095 SO 2008 1 31 CA071031005 2 20071023 G 8530 50339001 TUBE CIRRUS SR SR20 05628AJ GL CONT O360 IO360E 17025 SO HARTZL HCJ2Y BHCJ2YF1 GL CYLINDER INTAKE DAMAGED W K NONE E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 623 360074 (CAN) INTAKE PIPE ON NR 1 CYLINDER FLANGE DAMAGED. (TC NR 20071031005) 1 L 7 1 3O 3 O NT A00009CH E1CE 5 C P37EA 2008013100098 20080131 00098 EA 2008 1 31 CA071031006 1 20071030 G 5350 600330061 RADOME CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE FUSELAGE DAMAGED W O OTHER O OTHER CL CLIMB 1 CA (CAN) FLIGHT ON CLIMB OUT THE CREW HEARD A LOUD BANG IN THE NOSE AND SAW A BIRD TRAVEL PAST THE COCKPIT WINDOW. ALL FLIG HT SYSTEMS WERE NORMAL AND FLIGHT CONTINUED. UPON ARRIVAL MAINTENANCE MET THE AIRCRAFT AND FOUND A HOLE IN THE RADOME AS WELL AS A DAMAGE TO THE LT FUSELAGE AFT OF PITOT HEAD. DAMAGE ASSESSMENT IS UNDER WAY AND IT WILL BE UPDATED AS SOON AS MORE INFOMATION IS AVAILABLE. (TC NR 20071031006) 2 L 7 2 4F 4 F RT A21EA E15NE 2008013100101 20080131 00101 NE 2008 1 31 CA071031007 2 20071029 G 8530 CYLINDER HEAD DOUG DC4 C54EDC 3021528 WP PWA R2000 R20007M2 52023 NE HAMSTD 23E 23E50 NE FUSELAGE CRACKED W E A ENGINE SHUTDOWN UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA (CAN) CRACK DISCOVERED AT SPARK PLUG HOLE, RETURNED TO BASE AND REPLACED CYLINDER AND A/C RETURNED TO SERVICE. (TC NR 20 071031007) 2 L 7 4 4R 4 R A762 5E5 6 C P603 2008013100112 20080131 00112 CE 2008 1 31 CA071031008 1 20071030 G 3246 950476 BEARING BEECH BEECH 99 B99 1154004 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL MAIN WHEEL FAILED W A UNSCHED LANDING D INFLIGHT SEPARATION TO TAKEOFF 1 CA (CAN) ON TAKEOFF THE CREW NOTED THAT THEY FELT A SLIGHT VIBRATION, BUT FELT THAT IT WAS LIKELY THE RAISED RUNWAY LIGHTS. AFTER TAKEOFF THEY WERE ADVISED THAT THEY HAD LOST A TIRE. THE AIRCRAFT WAS LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THAT ONE OR BOTH WHEEL BEARINGS HAD FAILED. THIS ALLOWED THE WHEEL TO DEPART FROM THE AXLE. INSPECTION SHOWED NO DAMAGE TO ANY OTHER PART OF THE AIRCRAFT, INCLUDING AXLE AND BRAKE. THE WHEEL ASSY. INCLUDING BEARINGS WERE REPLACED AND THE AI RCRAFT WAS RELEASED TO SERVICE. (TC NR 20071031008) 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2008013100115 20080131 00115 2008 1 31 CA071031009 4 20071021 G 2397 EH19565 WIRE HARNESS AIRBUS A319 A319114 3930350 NM CFMINT CFM56 CFM565A1 NE CABIN BROKEN W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA (CAN) AN APPARENT NOTICEABLE ELECTRICAL ODOR WAS DETECTED IN VICINITY OF SEATS 19 DEF BY IN FLIGHT CREW AND PASSENGER. O DOR PERSISTED FOR APPROX 5 MIN AND STOPPED AT THE TIME WHEN INFLT VIDEO SYSTEM WAS SHUTDOWN. FOUND BROKEN WIRE IN THE H ARNESS THAT RUNS FROM UNDER SEATS 18 DEF TO UNDER THE FLOOR. BROKEN WIRE CAPPED AND STOWED INSIDE HARNESS CONNECTOR. TH IS APPEARS TO BE AN INSTALLATION ERROR. THE WHITE WIRE APPEARS TO HAVE BEEN INSTALLED UNDER TOO MUCH TENSION, AND WAS P ULLED FROM THE BACK OF THE CONNECTOR. (TC NR 20071031009) 2 L 7 2 4F 4 F RT A28NM E29NE 2008020400155 20080204 00155 CE 2008 2 4 CA071101001 1 20071019 G 3260 MS21090348 SQUAT SWITCH CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE MLG LOOSE W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) ON FINAL APPROACH APPROXIMATELY 3 MILES FROM TOUCH DOWN, THE LT THRUST REVERSER (T/R) ARM AND UNLOCK LIGHTS ILLUMI NATED BRIEFLY. AT APPROXIMATELY 1.5 FROM TOUCH DOWN THE LT T/R ARM, UNLOCK AND DEPLOY LIGHTS ILLUMINATED AND THE LT POWE R LEVER AUTOMATICALLY MOVED TO IDLE. ALL (3) LIGHTS EXTINGUISHED BEFORE EITHER OF THE PILOTS COULD TAKE ACTION TO EMERGE NCY STOW THE T/R. THE FACT THAT THE MECHANICAL T/R POWER LEVER INTERCONNECT CAUSED THE POWER LEVER TO RETARD TO IDLE IND ICATES THAT THE T/R DID ACTUALLY DEPLOY AND THAT THIS WAS NOT AN ERRONEOUS ANUNNCIATOR. THE LANDING GEAR SQUAT SWITCHES SHOULD HAVE PREVENTED INADVERTENT T/R DEPLOYMENT, WITH ONLY THE T/R ARM LIGHT ILLUMINATING EVEN IN THE EVENT OF A COMMAN 1 L 7 2 4F 4 F A22CE E1NE 2008013100118 20080131 00118 EA 2008 1 31 CA071101002 2 20071031 G 7200 ENGINE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU POWER LOSS W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA FA0268 (CAN) DURING FLIGHT, A LOUD NOISE WAS HEARD FOLLOWED BY A LOSS OF POWER RESULTING IN AN INFLIGHT SHUTDOWN OF THE ENGINE. POST FLIGHT EXAMINATION REVEALED SEVERE INTERNAL DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071101002) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008031900165 20080319 00165 EU 2008 3 19 CA071101003 1 20071029 G 3246 BEARING EMB ERJ190 ERJ190100IGW 3260408 EU GE CF34 CF3410E5A1 30022 NE NR 4 WHEEL SEIZED W D RETURN TO BLOCK M J OVER TEMP WARNING INDICATION TX TAXI/GRND HDL 1 CA 786 (CAN) THE A/C LANDED NORMALLY, TAXIED TO THE GATE AND STOPPED SHORT OF ITS FINAL POSITION. THE CREW REPORTED 60 PERCENT N1 REQUIRED (SINGLE ENG TAXI) TO MOVE THE AC FROM A HOLD SHORT OF THE GATE. THE GROUND CREW ARRIVING THE AC HEARD A LOT OF NOISE FROM THE RT GEAR AS IT MOVED TO THE GATE. NO OTHER FAULT INDICATIONS IN THE COCKPIT. UPON INSP OF THE RT LAN DING GEAR IT WAS IDENTIFIED THAT THE (NR 4 WHEEL WAS DRAGGING AND INTERFERING WITH BRAKE CARRIER). FURTHER INSP FOUND T HE WHEEL BRG SEIZED ON THE GEAR AXLE, WITH NR 4 TIRE AND THE BRAKE DAMAGED. DECOLONIZATION OF THE AXLE WAS NOTED DUE T O EXCESSIVE HEAT BUILD UP. THE RT LANDING GEAR ASSY, BRAKE AND TIRE WAS REPLACED IAW AMM. INVESTIGATION CONTINUES TO I 2 L 7 2 4F 4 F RT A57NM E00070EN 2008013100120 20080131 00120 GL 2008 1 31 CA071101005 2 20071029 G 7210 78023061 MAGNETIC SEAL CESSNA 206 U206G 2073356 CE ALLSN 250C 250C20 03013 GL HARTZL HCC3Y HCC3YN GL PROP RGB LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 CA 22 22 074 (CAN) ONE OF THE PILOTS NOTICED A SMALL ENGINE OIL LEAK ON BOTTOM OF ENGINE COWLING. REMOVED THE ENGINE COWLING AND FOUN D LEAK ON PROP REDUCTION GEARBOX INPUT SEAL AREA. REMOVED PROP REDUCTION GEARBOX, INPUT QUILL ASSY AND REPLACED MAGNETIC SEAL. UNDER 10X MAGNIFYING GLASS, A SCRATCH AT 90 DEGREE ACROSS THE CARBON SEALING SURFACE WAS FOUND. AIRCRAFT GROUND R UN, NO LEAKS, RETURN TO SERVICE. DEFECTIVE MAGNETIC SEAL RETURN TO MFG. (TC NR 20071101005) 1 H 7 1 3O 3 U A4CE E4CE 5 C P25EA 2008013100122 20080131 00122 EA 2008 1 31 CA071102001 1 20071029 G 2752 852D10019 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS FAILED W O OTHER J F WARNING INDICATION FLT CONT AFFECTED AP APPROACH 1 CA 7986 7986 (CAN) DURING APPROACH, THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE WHEN THE FLAPS WERE SELECTED FROM 0 TO 8 DEGREES. T HE EICAS FLIGHT CONTROL PAGE WAS INDICATING 0 DEGREE ON BOTH SIDES. THE CREW CONTINUED THE APPROACH AND COMPLETED A FLAP LESS LANDING WITHOUT INCIDENT. NO EMERGENCY WAS DECLARED. THE SYSTEM WAS RESET, THE FLAPS SET TO 8 DEGREES AND THE AC W AS FERRIED FOR MAINTENANCE. ALL FLAP ACTUATORS WERE REMOVED AND SENT TO THE SHOP. THE LT NR1 FLAP ACTUATOR FAILED THE - 60 DEGREES TORQUE CHECK. DECISION WAS MADE TO REPLACE ALL FLAP ACTUATORS. FLAP ACTUATORS WERE REPLACED, ADJUSTED, TESTED AND THE AIRCRAFT WAS RELEASED. A SUCCESSFUL TEST FLIGHT WAS CONDUCTED AND THE AIRCRAFT RETURNED INTO SERVICE. (TC NR 20 2 L 7 2 4F 4 F RT A21EA E15NE 2008013100123 20080131 00123 CE 2008 1 31 CA071102002 1 20071031 G 2497 CM358930 SWITCH CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL AVIONICS 2 OVERHEATED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 4804 (CAN) SHORTLY AFTER DEPARTURE THE PILOT BECAME AWARE OF A BURNING ODOR. HE NOTICED THAT THE AVIONICS 2 SWITCH WAS HOT TO TOUCH. THE PILOT RETURNED TO BASE. INVESTIGATION FOUND THAT THE AVIONICS 2 SWITCH HAD OVERHEATED TO THE POINT OF FAILUR E. A NEW SWITCH P/N 7270-5-30 WAS INSTALLED. ( REF CAB97-8 ) (TC NR 20071102002) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2008013100124 20080131 00124 SW 2008 1 31 CA071102003 1 20071029 G 6510 206040272101 BOOT BELL BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL DRIVE SHAFT DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 CA 21 A2000807 (CAN) DRIVE SHAFT WAS RECENTLY INSPECTED, GREASED AS REQUIRED AT MFG. OLD BOOTS WERE SERVICEABLE, BUT AGE WAS NOT KNOW N SO REPLACEMENT WAS ELECTED AS A SAFETY PRECAUTION. NEW BOOTS INSTALLED AND DRIVE SHAFT SERVICED. 21.1 HOURS AFTER R EPACK GREASE LEAK WAS DETECTED BY PILOT AND DRIVE SHAFT REMOVED. AS A SERVICEABLE DRIVE SHAFT WAS AVAILABLE THE LEAKIN G ONE IN QUESTION WAS (RED TAGGED). UNSERVICEABLE DRIVE SHAFT DISASSEMBLED AND BOOT FOUND DETERIORATED, ALMOST TO A DIS SOLVED STATE, RUBBER SEEMS MORE LIKE A PLASMA THEN RUBBER STATE. BOOT INFO SKF BO201 SKF BCO-BO-7206 MFG 1/19/07. (TC N R 20071102003) 1 G 7 1 3U 3 U H2SW E4CE 2008013100125 20080131 00125 GL 2008 1 31 CA071102004 1 20071031 G 3245 30200530001110 TUBE DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO MLG TIRE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 3 (CAN) DURING A SPECIAL INSPECT TO THE MAIN AND NOSE WHEEL ASSEMBLIES, DEFECTS WERE NOTED IN THE TIRE-TUBES INSTALLED INT O BOTH MAIN AND THE NOSE WHEELS. REPORTS HAVE BEEN MADE OF TIRE-TUBES FAILING WITH VERY LOW TIME. AFTER RECEIVING THESE REPORTS AN INSPECTION WAS PERFORMED ON ALL 3 WHEEL ASSEMBLIES ON 2 AIRCRAFT ALL TIRE-TUBES INSPECTED WERE DEFECTIVE, SHO WING THE SAME DEFECTS AS REPORTED. PHOTOGRAPHS OF THE REPORTED TIRE-TUBES FAILURES ARE ATTACHED TO THIS SDR. THE TUBES I NSPECTED ARE IDENTICAL IN APPEARANCE. SEVERAL TUBES P/N 5.00-5 TR 67 AND 30200530001110 HAVE BEEN FOUND WITH SIMILAR DIS CREPANCIES (TC NR 20071102004) 1 L 7 1 3O 3 O NT TA4CH E7SO 2008013100126 20080131 00126 EA 2008 1 31 CA071102005 2 20071026 G 8530 LW167035C ROCKER BOSS CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL CYLINDER HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 145 L2371415 (CAN) ON CYLINDER NR 3 THE ROCKER SHAFT RT BOSS HAS BEEN FOUND BROKEN (SPLIT) IN THE MIDDLE SECTION. THE BROKEN PART/ALL AND REST JUST BESIDE THE EXHAUST VALVE. (TC NR 20071102005) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2008013100127 20080131 00127 CE 2008 1 31 CA071102006 1 20071031 G 3260 1CH25 DOWNLOCK SWITCH BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL MLG INOPERATIVE W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) UNABLE TO GET NLG (GREEN LIGHT) ON APPROACH. RECYCLED 3 TIMES AND GREEN LIGHT OBTAINED. NLG DRAG LINK DOWN AND LO CK SWITCH REPLACED. GEAR SWINGS COMPLETED. NO FURTHER FAULTS AT THIS TIME. (TC NR 20071102006) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2008013100129 20080131 00129 SO 2008 1 31 CA071102008 1 20071031 G 5210 DOOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL DEPARTED W O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 CA (CAN) UPPER DOOR ASSEMBLY DEPARTED THE AIRCRAFT WHILE IN FLIGHT, UPPER DOOR REPLACED AND DAMAGED STRUCTURE REPAIRED. THI NK THE PROBLEM AROSE WITH THE FACTORY PIPER SLIDING LOCK. WE SUSPECT THAT IT WAS WORN THOUGH THERE WAS NO PRIOR INDICATI ON. (TC NR 20071102008) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008013100130 20080131 00130 EA 2008 1 31 CA071102009 1 20071030 G 2761 601R107022 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE SPOILERON FRACTURED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA SBRJ75 (CAN) DURING SHORT FINAL, THE FLAPS WERE SELECTED TO 45 DEGREES AND THE AIRCRAFT ROLLED TO THE RT. FULL AILERON TRIM AN D A LITTLE BIT OF AILERON WAS REQUIRED TO KEEP THE AIRCRAFT LEVEL. THE EICAS FLIGHT CONTROL PAGE WAS REVIEWED AND THE RT SPOILERON WAS SHOWING UP. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE DISCOVERED THAT THE RT SPOILERON OB ACTUAT OR ATTACHMENT HAS FRACTURED. THE RT SPOILERON ASSY AND BOTH ACTUATORS WERE REPLACED, ADJUSTED AND THE SYSTEM TESTED SERV ICEABLE. THE AIRCRAFT WAS RELEASED AND RETURNED INTO SERVICE. (TC NR 20071102009) 2 L 7 2 4F 4 F RT A21EA E15NE 2008013100131 20080131 00131 NM 2008 1 31 CA071102010 1 20071017 G 5230 SENSOR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU CARGO DOOR FALSE INDICATION W B EMER. DESCENT N FALSE WARNING CR CRUISE 1 CA (CAN) AIRCRAFT WAS ALREADY UNDER MEL 52-10-05 DUE FORWARD BAGGAGE DOOR GIVES A FALSE (OPEN) INDICATION IN THE COCKPIT. AIRCRAFT COULD FLY PRESSURIZED BUT PRESSURIZATION SYSTEM MUST BE CONTROL IN MANUAL MODE. AIRCRAFT SUFFERED A DEPRESSURI ZATION AT 20,000 FT. ALL SYSTEM CHECK AND NO FAULT WAS FOUND IN MANUAL AND AFTER DOOR SENSOR WAS REPAIR SYSTEM WORK ALS O IN AUTO MODE. STILL UNDER INVESTIGATION. (TC NR 20071102010) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008013100132 20080131 00132 EA 2008 1 31 CA071102011 2 20071031 G 7200 ENGINE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU LEFT NOISY W E A ENGINE SHUTDOWN UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA 2047 PCEFA0268 (CAN) AROUND 20000 FT, AFTER HEARING A STRANGE SOUND THAT SEEM TO COME FROM THE LT ENGINE, PILOT NOTICED THAT THE LT ENG INE SUDDENLY STOPPED BY ITSELF. PILOT WAS ABLE TO FEATHER THE PROP. EMERGENCY WAS DECLARED. A/C LANDED WITHOUT OTHER PRO BLEM. NO ONE INJURED. UNDER INVESTIGATION (TC 20071102011) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008013100133 20080131 00133 CE 2008 1 31 CA071102012 1 20071102 G 3211 05412024 BUSHING CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL MLG SEPARATED W K NONE O OTHER IN INSP/MAINT 1 CA 4792 4792 (CAN) THE MAIN GEAR LEG BUSHINGS ARE A STEEL OUTER TUBE, WITH A THICK INNER URETHANE CENTER. DURING PROGRESSIVE CARE OPE RATION NR 4, INSPECTION OF THE LT MAIN GEAR LEG REVEALED THAT THAT THE URETHANE INNER BUSHING MATERIAL HAD DEPARTED FRO M THE OUTER STEEL BUSHING (P/N 0541202-4). IT HAD MOVED LOOSELY ALONG THE TUBULAR GEAR LEG TOWARDS THE CENTER OF THE AIR CRAFT. THIS ALLOWED THE TUBULAR GEAR LEG TO RATTLE ON THE INSIDE OF THE STEEL OUTER BUSHING. THE STEEL OUTER BUSHING IS HELD IN PLACE WITH 2 (C) CLIPS, HOWEVER THE URETHANE INNER PART OF THE BUSHING LOOKS TO BE ONLY A PRESS FIT. (TC NR 2007 1102012) 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2008013100137 20080131 00137 SW 2008 1 31 CA071102013 1 20071101 G 6320 476206283 BEARING CAGE BELL BELL 47 47G2 1181008 SW LYC O435 VO435A1E 41516 EA M/R TRANSMISSION MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA 100 B125159 (CAN) DURING ROUTINE INSPECTION, SMALL AMOUNT OF BRASS WAS FOUND IN OIL SCREEN, THE TRANSMISSION WAS DISASSEMBLED TO LOC ATE THE FAILED ITEM AND IT WAS FOUND TO BE ONE OF THE BEARING CAGES IN THE DUPLEX BEARING THAT THE UPPER SUN GEAR GOES T HROUGH, THIS IS THE NEW AND IMPROVED BEARING INSTALLED IAW TB 47-75-4 (TC NR 20071102013) 1 G 7 1 3O 3 O H1 E279 2008013100143 20080131 00143 EA 2008 1 31 CA071103001 1 20071101 G 4970 21188002 ECU HONEYWELL CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE APU FAULTY W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 18983 6143 (CAN) FLIGHT RETURNED DUE TO APU OIL PRESSURE MESSAGE CAUSING THE APU TO FAIL. AIRCRAFT WAS ALREADY OPERATING WITH 1 IDG GENERATOR UNSERVICEABLE. MAINTENANCE CHECKED THE SYSTEM AND FOUND AN ECU FAULT MESSAGE. THE APU ECU WAS REPLACED AND TH E A/C WAS CHECKED SERVICEABLE. NR 1 IDG WAS ALSO REPLACED AT THIS TIME AND CHECKED SERVICEABLE CLEARING THE MEL. CYCLES SINCE OVERHAUL:4860 (TC NR 20071103001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008013100144 20080131 00144 NE 2008 1 31 CA071105001 2 20071101 G 7200 ENGINE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE MALFUNCTIONED W E ENGINE SHUTDOWN B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 CA 114284 (CAN) CREW OBSERVED LOW OIL PRESSURE WARNING, FOLLOWED BY SMOKE IN THE CABIN. ELECTION WAS MADE TO PERFORM AN INFLIGHT E NGINE SHUTDOWN. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. FULL ENGINE SN GAS GENERATO R MODULE: 114283 POWER SECTION MODULE: 114135 (TC NR 20071105001) 2 L 7 2 4T 4 T RT A24CE E26NE 2008013100146 20080131 00146 EU 2008 1 31 CA071105002 1 20071102 G 2910 9433772104 HOSE PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL LT MAIN GEAR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN TRYING TO INSTALL THE NEW LINE IT WOULD BIND UP HALF WAY ON, HAD 2 NEW HOSES AND WHEN WE TRIED THE OTHER HO SE IT WENT ON WITH NO PROBLEMS, SUSPECT THREADS ON B-NUT FITTING ON NEW HOSE. (TC NR 20071105002) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008013100149 20080131 00149 NE 2008 1 31 CA071105003 2 20071024 G 7200 TRANSDUCER FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE ECU DEFECTIVE W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA 125146 (CAN) TAKEOFF WAS ABORTED DUE TO UNCOMMANDED POWER CHANGES OBSERVED ON GAUGES IN CONCERT WITH AIRCRAFT YAWING MOTION. T ROUBLESHOOTING DETERMINED THAT THE PT TRANSDUCER IN THE ELECTRONIC CONTROL WAS DEFECTIVE. PN AND SN TO BE SUPPLIED IN DU E COURSE. (TC NR 20071105003) 2 H 7 2 4T 4 T RT A817 E20NE 2008013100152 20080131 00152 EA 2008 1 31 CA071105004 1 20071030 G 5610 601R3303312 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT BROKEN W B A EMER. DESCENT UNSCHED LANDING O OTHER CR CRUISE 1 CA 12170 (CAN) OUTBOUND THE FO’S SIDE WINDOW BROKE GOING THROUGH 20,000 FT. MX REPLACED SIDE WINDOW (TC NR 20071105004) 2 L 7 2 4F 4 F RT A21EA E15NE 2008013100157 20080131 00157 NE 2008 1 31 CA071105005 2 20071026 G 7200 601R6000267 ENGINE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE NR 1 FAILED W O OTHER C E F.O.D. VIBRATION/BUFFET CL CLIMB 1 CA 4404 872911 (CAN) AFTER TAKEOFF, THE CREW SENT ACARS INDICATING THAT THE LT ENGINE HAD A HIGH VIB. AFTER FOLLOWING THE QRH. THEY RE DUCED POWER TO ACCOMMODATE THE VIB IN THE GREEN. IN SEPARATE ACARS, THEY HAD ANTI SKID MESSAGE. THEY CONTINUED AND ONCE ON THE GROUND DISCOVERED THAT THE NR 2 MAIN TIRE HAD SHREDDED AND PART OF THE DEBRI WENT INTO THE NR 1 ENGINE. 2 FAN BLA DES WERE BENT AND 2 STATORS WERE CRACKED. THE NOSE COWL HAS A DENT THAT IS OUT OF LIMITS. THE REMAINING MAIN WHEEL TIRE PRESSURES WERE ALL ABOVE 200 PSI. PARTS REPLACED: STATOR SPACER PN 5128T05G01 NSN, FAN BLADE C-25 PN 6018T30P06 SN KL AJ6586 FAN BLADE L-11 PN 6018T30P06 SN KGAR3406 FAN BLADE C-22 PN 6018T30P14 SN KGACR870 FAN BLADE L-8 PN 6018T30P14 SN 2 L 7 2 4F 4 F RT A21EA E15NE 2008013100160 20080131 00160 NM 2008 1 31 CA071106001 1 20071017 G 5610 NP17820110 WINDSHIELD GULSTM 200 200 4500308 NM COCKPIT BROKEN W O OTHER O OTHER CR CRUISE 1 CA 830 (CAN) PILOT REPORTED RT WINDSHIELD CRACKED ON RETURN. C/O INSPECTION ON RT WINDSHIELD AND COULD NOT FAULT THE WINDSHIELD . THE AIRCRAFT WAS RELEASE FOR RETURN TO SERVICE. THE AIRCRAFT MADE (3) OTHER TRIPS. THE PILOTS REPORTED THE SAME CRACK ON THE RT WINDSHIELD. AGAIN C/O THE INSPECTION ON THE RT WINDSHIELD AND COULD NOT FAULT. PILOTS REPORTED THEY COULD ONLY SEE THE CRACK WHEN THE AIRCRAFT IS AT ALTITUDE. SPOKE TO MFG AND DECIDED TO REPLACE THE WINDSHIELD. THE UNIT REMOVED WI LL BE SENT BACK TO MFG AND THEY WILL REPORT ON THE FAILURE OF THE WINDSHIELD. THE NEW RT WINDSHIELD WAS INSTALLED AND TH E AIRCRAFT HAD SEVERAL FLIGHTS WITH NO FURTHER REPORTS. (TC NR 20071106001) 2 L 7 2 4F RT A53NM 2008013100161 20080131 00161 CE 2008 1 31 CA071106002 1 20071105 G 3244 226K084 TIRE LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP MLG DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA 412 (CAN) DURING AN INSPECTION, A BULGE WAS NOTICED ON THE NR 2 TIRE. THIS BULGE WAS NOTICED IN 3 SPOTS ON THE TIRE, EACH EX TENDING FOR ABOUT 3 INCHES. THE BULGE STARTED AT THE CORNER OF THE TREAD AND EXTENDED TO THE SIDEWALL AND. THE TIRE WAS REPLACED. (TC NR 20071106002) 2 L 7 2 4F 4 F RT T00008WI E6WE 2008013100164 20080131 00164 NM 2008 1 31 CA071106003 1 20071106 G 5330 146A323110 SKIN BOEING 737 737990 NM BS 777-830 RBL26 SCRATCHED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SCRATCHES ON FUSELAGE SKIN BELOW AFT CARGO PIT LOWER SILL BS 777 TO BS 830, RBL 26 REPAIRED IAW CUSTOMER EA. (TC N R 20071106003) 2 L 7 4 4F RT A16WE 2008013100167 20080131 00167 NM 2008 1 31 CA071106004 1 20071106 G 5730 112A4102209 SKIN BOEING 737 737990 NM LWS 240 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT WING LOWER SKIN PANEL CHAFFING AT WSTA 240, IB OF BLADE SEAL. REPAIRED IAW CUSTOMER EA (TC NR 20071106004) 2 L 7 4 4F RT A16WE 2008013100170 20080131 00170 NM 2008 1 31 CA071106005 1 20071106 G 5730 112A4102209 SKIN BOEING 737 737990 NM LWS 260 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT WING LOWER SKIN PANEL CHAFFING DAMAGE AT WSTA 260, OB OF BLADE SEAL FAIRING. REPAIRED IAW CUSTOMER EA (TC NR 20 071106005) 2 L 7 4 4F RT A16WE 2008013100172 20080131 00172 NM 2008 1 31 CA071106006 1 20071106 G 5730 112A4102210 SKIN BOEING 737 737990 NM RWS 240 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT WING LOWER SKIN CHAFING DAMAGE AT WSTA 240, IB OF FAIRING SEAL REPAIRED IAW CUSTOMER EA (TC NR 20071106006) 2 L 7 4 4F RT A16WE 2008013100176 20080131 00176 CE 2008 1 31 CA071106007 1 20071106 G 2931 9536830 INDICATOR BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL HYD SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) WE HAD A PRESSURE GAUGE THAT HAD A SMALL LEAK SO WE PURCHASED A NEW GAUGE FROM MFG AND INSTALLED IT ON THE AIRCRAF T. WHEN SYSTEM WAS BROUGHT UP TO THE PROPER PRESSURE THE NEW GAUGE LEAKED WORSE THAN THE ORIGINAL GAUGE. THE GAUGE WAS S ENT BACK TO BEECH AND WE ARE WAITING FOR A REPLACEMENT. THIS IS A QUALITY CONTROL ISSUE. (TC NR 20071106007) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2008013100179 20080131 00179 NE 2008 1 31 CA071106008 3 20071025 G 6110 31025731 RETAINER FRCHLD SA227 SA227CC 3377522 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE PROP SHAFT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA P44738 (CAN) WHILE ENGINE WAS BEING REPLACED MAINTENANCE NOTICED FATIQUE CRACKS EMINATING FROM THE (PROP SHAFT) RETAINING BOLT AREA. (TC NR 20071106008) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2008013100182 20080131 00182 SW 2008 1 31 CA071106009 1 20071026 G 3220 2752530001 ARM SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE NLG CENTER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ROLLER BEARING OUTER CASE FOUND CRACKED COMPLETLY THROUGH. REPLACED AND RETURNED TO SERVICE (TC NR 20071106009) 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 2008013100186 20080131 00186 WP 2008 1 31 CA071106010 2 20071030 G 7313 31032359 FUEL NOZZLE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE3311 01514 WP MCAULY 4HFR34 4HFR34C652 NE ENGINE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) FUEL NOTICED IN ENGINE COWL DURING INSPECTION. NOZZLE IN NR 3 POSITION FOUND CRACKED WHERE PRIMARY/SECONDARY LINES HOOK UP TO NOZZLE. CRACK WAS 95 PERCENT THROUGH CIRCUMFERENCE. (TC NR 20071106010) 2 L 7 2 4T 3 T RT A8SW E3WE 6 C 3PNE 2008013100187 20080131 00187 EU 2008 1 31 CA071106011 1 20071025 G 2820 30733341 TUBE BRAERO DH125 HS125700A 4230170 EU GARRTT TFE731 TFE7313R1H 29001 WP FUEL SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON A PREFLIGHT INSPECTION, MAINTENANCE DISCOVERED THE FIRE DETECTOR (P/N 3001-31-900-400-17) AGAINST THE FUEL TUBE ASSEMBLY (P/N P-84417). UPON REPOSITIONING THE FIRE DETECTOR INTO POSITION, A CHAFED MARK ON THE NR 1 ENGINE FUEL TUBE ASSEMBLY WAS DISCOVERED. THE FUEL TUBE ASSEMBLY WAS ORDERED AND REPLACED. AN ENGINE RUN WAS CARRIED OUT FOR A LEAK CHECK INSPECTION. (TC NR 20071106011) 2 L 7 2 4F 4 F A3EU E6WE 2008013100188 20080131 00188 2008 1 31 CA071106012 4 20071104 G 2210 BACC18AE35 CIRCUIT BREAKER BOEING 737 737* NM PWA JT8 JT8D17A 52049 NE FAILED W A UNSCHED LANDING S AFFECT SYSTEMS CR CRUISE 1 CA (CAN) ENROUTE AT FL300, THE CREW EXPERIENCED AN AUTO PILOT DISENGAGEMENT AS WELL AS THE LOSS OF THE FOLLOWING, YAW DAMPE R, MACH TRIM, CAPTS. PITOT STATIC, NR 1 ENG ANTI ICE, RADAR ALTIMETER, NO 2 EGT AND SEVERAL OTHERS. THE CREW ATTEMPTED A RESET OF THE NR 1 NORMAL TRANSFER BUS CIRCUIT BREAKER, WHICH FAILED. THE AIRCRAFT WAS DIVERTED AND LANDED WITHOUT FUR THER INCIDENT. MAINTENANCE REPLACED THE CIRCUIT BREAKER AND THE AIRCRAFT HAS RETURNED TO SERVICE WITHOUT FURTHER PROBLEM . (TC NR 20071106012) 2 L 7 2 4F 4 F RT A16WE E2EA 2008013100190 20080131 00190 EA 2008 1 31 CA071107001 2 20071103 G 7200 ENGINE DHAV DHC6 DHC6100 2802610 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL RIGHT FAILED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA PCE50661 (CAN) PILOTS HAD TO SHUTDOWN RT ENGINE. MAINTENANCE INSPECTION FOUND PROP WOULDN`T TURN, EXPECT POWER SECTION FAILURE. ( TC NR 20071107001) 1 H 7 2 3T 3 T RT A9EA E4EA 6 C P15EA 2008013100193 20080131 00193 EA 2008 1 31 CA071107002 2 20071105 G 7230 BLADES BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL COMPRESSOR FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 CA PCE85202 (CAN) PILOTS OBSERVED SPARKS COMING OUT RT ENGINE EXHAUST ON LANDING. MAINTENANCE INSPECTION FOUND COMPRESSOR BLADES LAY ING IN THE ENGINE BAY. (TC NR 20071107002) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2008013100197 20080131 00197 CE 2008 1 31 CA071107003 1 20071107 G 2731 55657544 LEVER CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE TRIM INDICATOR WORN W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 CA 6834 (CAN) PILOT ABORTED TAKEOFF DUE TO NO RESPONSE TO CONTROL COLUMN INPUT. UPON INSPECTION FOUND ELEVATOR TRIM TAB WAS ALMO ST ON FULL NOSE DOWN POSITION AND TRIM INDICATION IN COCKPIT WAS AT TAKEOFF. FOUND INDICATOR LEVER AND CONTROL WHEEL WOR N, INDICATOR LEVER HAD JUMPED ON CONTROL WHEEL TO GIVE WRONG INDICATION. TRIM CONTROL WHEEL AND INDICATOR LEVER REPLACED AND INDICATION SYSTEM RIGGED IAW AMM AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20071107003) 1 L 7 2 4F 4 F A22CE E1NE 2008013100200 20080131 00200 EU 2008 1 31 CA071107004 1 20071107 G 5320 MS24693C273 SCREW EMB ERJ190 ERJ190100IGW 3260408 EU GE CF34 CF3410E5A1 30022 NE P-ACE RACK WRONG PART W K NONE O OTHER IN INSP/MAINT 1 CA 4104 (CAN) RETAINING SCREW FOR THE P-ACE (PRIMARY- ACTUATOR CONTROL ELECTRONICS) LT AND RT RACKS WERE THE WRONG SIZE (DIAMETE R AND LENGTH TOO SMALL). THE RT P-ACE AND RACK WERE FREE FLOATING IN THE SLOT. THE LT P-ACE AND RACK WERE SECURED WITH T HE WRONG HARDWARE. THE CORRECT P/N OF THE RETAINING SCREW IS MS24693C273. (TC NR 20071107004) 2 L 7 2 4F 4 F RT A57NM E00070EN 2008013100202 20080131 00202 EA 2008 1 31 CA071107005 1 20071012 G 2730 TBC6CF11461 CABLE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL ELEVATORS CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 1532 (CAN) WHILE INSPECTING THE CONTROL CABLES IAW TRANSPORT, ALERT (SDA) AL-2007-03, THE ELEVATOR CABLE WAS FOUND CHAFED AT THE PULLEYS AT STA 262.0. THE LOCATION OF THE WEAR ON THE CABLE, IS DIRECTLY OVER THE PULLEYS WHEN THE CONTROL LOCKS A RE IN. (TC NR 20071107005) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2008013100209 20080131 00209 SW 2008 1 31 CA071108001 1 20071105 G 2400 ELECTRICAL SYS SWRNGN SA227 SA227AC 8780603 SW FAILED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA AC739B (CAN) A/C ENROUTE AT 6000 FT, EXPERIENCED TURBULENCE AND ST.ELMO`S FIRE. AFTER SOME TIME, LIGHTNING APPEARED AS A BLUE L IGHT (AS REPORTED BY PASSENGER. IMMEDIATELY AFTER, ALL ELECTRICAL POWER (BOTH BATTERIES AND GENERATORS) WAS LOST. AIRCRE W RESET THE BATTERIES AFTER ESTABLISHING A SAFE FLIGHT ATTITUDE WITH THEIR PERSONAL FLASH LIGHTS. POWER WAS RESTORED AS SOON AS BATTERY RESET WAS ATTEMPTED. FLIGHT CONTINUED. MAINTENANCE WAS CONTACTED. AS THERE WAS NO OBVIOUS DAMAGE, ENTRIE S WERE MADE IN THE JOURNEY LOG AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20071108001) 2 L 7 2 4T RT A8SW 2008013100212 20080131 00212 GL 2008 1 31 CA071108003 1 20071102 G 5740 ATTACH FITTING DHAV DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HARTZL HCB3R HCB3R304 GL LIFT STRUTS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9690 0140 (CAN) WHILE ACCOMPLISHING THE REQUIREMENTS OF SB 2/55, CRACKS WERE DETECTED ON THE LOWER LUGS OF BOTH WING LIFT STRUTS. IN BOTH CASES THE CRACKS WERE LOCATED ON THE IB FACE OF THE LUG AND WERE .7500 INCH LONG LT STRUT P/N C2W1103A, S/N 0140 WAS CRACKED ON THE AFT FACE OF THE FWD LUG RT STRUT P/N C2W1104A S/N 0113 WAS CRACKED ON THE FWD FACE OF THE AFT LUG. S . B. 2/41 WAS COMPLETED 1 YEAR AGO WITH NO FAULTS FOUND AT THAT TIME. THE AC OPERATES EXCLUSIVELY ON FLOATS IN A CORROSI VE ENVIRONMENT. BOTH STRUTS WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. TAT 18060.1 (TC NR 20071108003) 1 H 7 1 3R 3 R RC A806 5E1 5 C P28EA 2008013100216 20080131 00216 NE 2008 1 31 CA071108004 2 20071025 G 7320 8228224004 EEC CESSNA 680 680CE 2076811 CE PWC PW306 PW306C 52169 NE ENGINE DEFECTIVE W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA CG0214 (CAN) DURING FLIGHT, THE CREW RECIEVED A YELLOW, HIGH TEMPERATURE, (WARNING LIGHT). THE POWER WAS REDUCED AND THE FLIGHT WAS DIVERTED. TROUBLESHOOTING REVEALED A DEFECTIVE ELECTRONIC ENGINE CONTROL. (TC NR 20071108004) 2 L 7 2 4F 4 F RC T00012WI E35NE 2008013100218 20080131 00218 NM 2008 1 31 CA071108005 1 20071105 G 2820 LJ35801 LINE BOEING 757 75728A 1384976 NM RROYCE RB211 RB211535E437 54555 NE NR 1 ENGINE CHAFED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB, THE CREW NOTICED THAT NR1 ENGINE PARAMETERS WERE NOT AS SCHEDULED. AIRCRAFT RETURNED TO THE AIRPORT. WITH DECREASING ALTITUDE THE NR1 ENGINE PARAMETERS IMPROVED AND A NORMAL LANDING WAS PERFORMED. FOUND P1 LINE CHAFED TH ROUGH. LINE REPLACED. TEST FLIGHT CONDUCTED. ALL PARAMETERS NORMAL. AIRCRAFT RETURNED TO SERVICE. (TC NR 20071108005) 2 L 7 2 4F 4 F RT A2NM E12EU 2008020400154 20080204 00154 NM 2008 2 4 CA071108006 1 20071107 G 3233 2630000004 ACTUATOR GULSTM 200 200 4500308 NM MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 855 (CAN) AFTER TAKEOFF THE CREW REPORTED THAT THE GEAR WAS SELECTED UP AND THE NOSE AND RT MAIN GEAR RETRACTED WITH NO FAUL T, THE LT GEAR DID NOT RETRACT. THE CREW REPORTED THEY CYCLED THE GEAR DOWN AND THE (3) GREEN LIGHTS WAS ON EICAS INDIC ATING DOWN AND LOCK. ANOTHER ATTEMPT WAS MADE TO CYCLE THE GEAR UP, AGAIN ONLY THE NOSE AND THE RT MAIN RETRACTED. THE LT UNSAFE INDICATION WAS INDICATED ON EICAS. THE CREW ELECTED TO CYCLE THE GEAR DOWN AGAIN AND WAS COMPLETED SUCCESSFUL LY, (3) GREENS ON EICAS.THE AIRCRAFT WAS RETURNED TO POINT OF DEPARTURE AND LANDED NO PROBLEMS. MAINTENANCE WAS CALLED A ND THE AIRCRAFT WAS PLACED ON JACKS C/O GEAR SWINGS. TROUBLESHOOTING REVEALED THAT THE LT GEAR ACTUATOR INTERNAL LOCKING 2 L 7 2 4F RT A53NM 2008013100222 20080131 00222 EU 2008 1 31 CA071108007 1 20071107 G 3210 200915254 LINK BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE MLG UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 32356 8282 (CAN) IT HAS BEEN DISCOVERED DURING INSPECTION OF THE ABOVE MENTIONED PART THAT IT IS IN AN UNSERVICEABLE CONDITION. WHI LE ON JACKS THE COMPONENT WAS INSPECTED AND MOVEMENT COULD BE FELT BETWEEN THE ROD ASSY AND EYE END. THE EYE END IS THRE ADED INTO THE ROD FOLLOWED BY A JAMB NUT AND SAFETY ASSY. NO MOVEMENT IS PERMITTED. THERE IS EVIDENCE OF CORROSION DEPOS ITS LEACHING THROUGH THE SEALANT. THIS IS THE SUSPECTED CAUSE. (TC NR 20071108007) 2 H 7 4 4F 4 F RT A49EU E6NE 2008013100223 20080131 00223 NM 2008 1 31 CA071109001 1 20071105 G 2432 4011769 BATTERY BOMBDR DHC8 DHC8402 1390042 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MASTER FAILED W E ENGINE SHUTDOWN J WARNING INDICATION NR NOT REPORTED 1 CA 16205 176 (CAN) DURING ENGINE NR 2 START UP, THE NR STALLED AT 20 NR AND THE ITT INDICATOR REACHED 800 DEGREES CELSIUS. THE ENGINE START WAS ABORTED FOLLOWING BY A LOUD BANG FROM THE NOSE COMPARTMENT. MAINTENANCE WAS CALLED IN AND THEY FOUND THE MAI N BATTERY TOP COVER POPPED OUT. NO STRUCTURAL DAMAGE WAS OBSERVED. THE MAIN AND AUXILIARY BATTERIES WERE REPLACED. THE A IRCRAFT WAS RELEASE AND RETURNED INTO SERVICE. (TC NR 20071109001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008013100224 20080131 00224 CE 2008 1 31 CA071109002 1 20071107 G 2731 55657544 LEVER CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE TRIM WHEEL INOPERATIVE W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 CA 6834 (CAN) PILOT ABORTED TAKEOFF. UPON INSPECTION FOUND ELEVATOR TRIM TAB WAS ALMOST ON FULL NOSE DOWN TRIM POSITION. TRIM IN DICATION IN THE COCKPIT WAS AT TAKEOFF. FOUND THAT THE INDICATOR LEVER HAD JUMPED ON THE CONTROL WHEEL TO GIVE THE WRONG INDICATION. TRIM CONTROL WHEEL AND INDICATOR LEVER REPLACED AND INDICATION SYSTEM RIGGED IAW AMM. (TC NR 20071109002) 1 L 7 2 4F 4 F A22CE E1NE 2008013100225 20080131 00225 EU 2008 1 31 CA071109003 1 20071109 G 7820 L24266710000 BAFFLE ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA MUHBR MTV MTV9* EU EXHAUST SILENCER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION, ONE INTERNAL BAFFLE OF THE PRIMARY EXHAUST SILENCER WAS FOUND TO BE CRACKED 25 PERCE NT OF THE ATTACHING WELD. SILENCER WAS SUBSEQUENTLY REPLACED. (TC NR 20071109003) 1 L 7 1 3O 3 O 0 A76EU 1E10 5 C P24NE 2008013100226 20080131 00226 NE 2008 1 31 CA071109004 2 20071005 G 8520 16475 CRANKCASE DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HARTZL HCB3R HCB3R304 GL ENGINE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1141 21739 (CAN) DURING RUNUP AFTER INSPECTION, INVESTIGATION OF A MINOR OIL LEAK REVEALED THAT THE ENGINE CRANKCASE WAS CRACKED NE AR AN ENGINE THROUGHBOLT AT THE BASE OF NR 2 CYLINDER, BETWEEN CYLS NR 2 AND NR 3. THE ENGINE WAS REPLACED. (TC NR 20071 109004) 1 H 7 1 3R 3 R RC A806 5E1 5 C P28EA 2008020400153 20080204 00153 NE 2008 2 4 CA071109005 2 20071108 G 7321 7898435010 ECU AEROSP ATR42 ATR42300 8680920 EU PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF5 NE NR 2 ENGINE FAILED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION DE DESCENT 1 CA PCE120178 (CAN) AC EXPERIENCED AN IN FLIGHT ENGINE SHUTDOWN OF THE NR 2 ENG ON DESCENT ABOUT 20 MILES FROM DESTINATION. CREW REPOR TED NO DISCREPANCIES PRIOR TO THE INCIDENT. THE CREW DID NOT ATTEMPT A RESTART BUT DECIDED TO LAND AS CONFIGURED. THE EC U FAULT LIGHT DID NOT ILLUMINATE AFTER ENGINE SHUTDOWN. THE RT UP-TRIM LIGHT ILLUMINATED AFTER THE ENGINE QUIT IN FLIGHT AS REPORTED BY THE PILOTS. MAINT VISUALLY INSPECTED THE ENGINE FOR OBVIOUS DEFECTS, NONE NOTED. THE ENGINE DRIVEN FUEL PUMP AND HMU WERE REMOVED TO CHECK FOR FUEL PUMP CONDITION. NO FAULTS NOTED. FUEL FILTERS AND ENGINE OIL FILTERS WERE IN SPECTED OK. NO BYPASS OR FUEL CLOG ANNUNCIATIONS NOTED. THE ENGINE WAS DRY MOTORED TO LISTEN FOR UNUSUAL NOISES (TOWER S 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008013100244 20080131 00244 SW 2008 1 31 CA071109006 1 20071108 G 7720 850568503 INDICATOR GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE3315 01514 WP HARTZL HCB3T HCB3TN5 GL ITT UNSERVICEABLE W E ENGINE SHUTDOWN N FALSE WARNING CR CRUISE 1 CA 11192 (CAN) DURING CRUISE THE NR2 ENGINE ITT INDICATION BECAME ERRATIC, THEN CLIMBED THROUGH THE RED LINE. THE FLIGHT CREW SHU TDOWN THE ENGINE AND FEATHERED THE PROP. THE AIRCRAFT RETURNED TO AIRPORT. MAINTENANCE TESTED THE ITT SYSTEM AND FOUND T HE INDICATOR TO BE AT FAULT. THE ITT INDICATOR WILL BE REPLACED WITH A SERVICEABLE UNIT AND THE AIRCRAFT WILL BE RETURNE D TO SERVICE. (TC NR 20071109006) 1 H 7 2 3T 4 T 2A4 E4WE 6 C P15EA 2008013100246 20080131 00246 CE 2008 1 31 CA071109007 1 20071013 G 2750 C1450046 GEAR CESSNA CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE HARTZL HCB3T HCB3TN3 GL TRANSMISSION BROKEN W O OTHER F FLT CONT AFFECTED DE DESCENT 1 CA 2880 (CAN) THE PILOT WAS ON DECENT AND WENT TO SELECT FLAPS AND THE CIRCUIT BREAKER POPPED AFTER THE FLAPS WERE AT ABOUT 10 D EGREES. HE THEN LANDED THE AIRCRAFT NORMALLY. MAINTENANCE FOUND THE FLAP TRANSMISSION TO BE MAKING NOISE OUT OF THE NORM . THE INTERNAL GEAR THAT DRIVES THE TRANSMISSION JACK SCREW WAS FOUND TO HAVE CHIPS OUT OF A FEW TEETH. THE TRANSMISSION WAS REPLACED AND SYSTEM FUNCTIONED NORMAL. (TC NR 20071109007) 1 H 7 1 3T 3 T A37CE E4EA 6 C P15EA 2008013100248 20080131 00248 NE 2008 1 31 CA071109008 2 20071103 G 7314 LW15473 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYSTEM WEAK W K NONE O OTHER IN INSP/MAINT 1 CA 1859 407 (CAN) ENGINE DRIVEN PUMP FOUND TO BE WEAK WILL NOT SUSTAIN ENGINE IDLE ON IT`S OWN. (TC NR 20071109008) 1 G 7 1 3O 3 O H11NM 1E4 2008013100250 20080131 00250 WP 2008 1 31 CA071109009 1 20071103 G 2822 D7431 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYSTEM WEAK W K NONE O OTHER IN INSP/MAINT 1 CA 902 902 (CAN) ELECTRIC AUX FUEL PUMP WEAK, MOTOR SOUNDED LIKE IT WAS OVERWORKING. (TC NR 20071109009) 1 G 7 1 3O 3 O H11NM 1E4 2008013100252 20080131 00252 NE 2008 1 31 CA071109010 2 20071103 G 7322 25766304 FUEL CONTROL ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA 1859 1859 (CAN) DURING MAINTENANCE GROUND RUN, THE ENGINE WAS HESITATING AT 70 PERCENT AND THEN DROOPS TO 65 PERCENT OR LESS. FUEL CONTROL NOT RESPONDING TO THROTTLE INPUT CORRECTLY. (TC NR 20071109010) 1 G 7 1 3O 3 O H11NM 1E4 2008013100254 20080131 00254 EA 2008 1 31 CA071109011 2 20071108 G 8530 LW13870 CYLINDER ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ENGINE INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA 438 (CAN) DURING A 50 HOUR INSPECTION, BOTTOM SPARK PLUG ON CYLINDER NR 5 REVEALED UNUSUAL AMOUNT OF OIL. A COMPRESSION TEST WAS CARRIED OUT AND CYLINDER NR 5 WAS NOTED TO HAVE 18 OVER 80 PSI COMPRESSION. TSO WILL HAVE TO BE VERIFIED. (TC NR 2 0071109011) 1 G 7 1 3O 3 O H11NM E295 2008013100255 20080131 00255 NM 2008 1 31 CA071112001 1 20071111 G 3297 473901 WIRE HARNESS BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NLG FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, NOSE GEAR UNSAFE ILLUMINATED. CREW PERFORMED NORMAL EXTENSION AND THE NLG DOORS DID NOT OPEN. ALSO, NLG NOT SHOWING DOWN AND LOCKED. SECOND ATTEMPT FOR EXTENSION, NOSE DOOR AMBER LIGHT ILLUMINATED. CREW PERFORMED ALTERN ATE EXTENSION AND LANDED WITHOUT FURTHER INCIDENTS. MAINTENENCE DISCOVERED PSEU REPORTED FAULT, NLG LOCK PROX 1. NOSE LOCK SENSOR REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20071112001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008013100256 20080131 00256 WP 2008 1 31 CA071112002 1 20071026 G 2720 369A75058 BRACKET HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL RUDDER PEDELS BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 15663 (CAN) RUDDER PEDALS WERE FOUND TO BE LOOSE IN MOUNTS ON FURTHER INVESTIGATION IT WAS FOUND THE BRACKET THAT THE RUDDER P EDALS MOUNT IN WAS BROKEN ON (3) OF THE (4) MOUNTING BOLT EARS. (TC NR 20071112002) 1 G 7 1 3U 3 U H3WE E4CE 2008013100258 20080131 00258 EU 2008 1 31 CA071112003 1 20071109 G 2612 FIRE LOOP BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU NR 1 NACELLE FAULTY W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) AFTER TAKEOFF, ENGINE NR 1 FIRE-WARNING ALARM WENT OFF. THE FLIGHT CREW INFORMED TOWER AND RETURNED TO AIRPORT. A HOLE WAS FOUND IN THE FLEXIBLE DUCT AT THE SUPERCHARGER OUTLET. ALSO, (2) FIRE DETECTION LOOPS WERE REPLACED BECAUSE T HEY FAILED THE RESISTANCE CHECK LIMITS FOUND IN THE HS 748 MM. (TC NR 20071112003) 2 L 7 2 3T 4 T A24EU A196 6 C P899 2008013100259 20080131 00259 NM 2008 1 31 CA071113001 1 20071110 G 6120 699018002 CONTROLLER BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU PROPELLER MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 CA (CAN) DURING FLIGHT, CREW REPORTED A NR 2 PEC CAUTION LIGHT ILLUMINATED FOLLOWED BY THE NR 2 ENGINE NP SURGE. THE QRH CO NSULTED AND THE NR 2 ENGINE WAS SHUTDOWN. EMU DOWNLOAD C/O, FAULT ISOLATION C/O FOR CODES 236 AND 260 IAW TASK 61-20-05 -810-822, 61-20-06-810-818. SERVO VALVE CONNECTORS RT J26 AND J27 CLEANED AND TREATED WITH STABILANT. PEC CONNECTORS 20 AND 21 CLEANED AND TREATED WITH STABILANT. AUTO FEATHER AND UP TRIM CHECKED SERVICEABLE FOR RETURN TO SERVICE IAW TASK 6 1-20-00-710-801. FURTHER FAULT CODE 131 DISPLAYED IN CDS. RT PEC REPLACED IAW AMM 61-20-36 AND C/O IAW AMM 71-00-00, NI L FAULTS EVIDENT. (TC NR 20071113001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008013100260 20080131 00260 NE 2008 1 31 CA071113003 2 20071106 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE POWER LOSS W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA PC1078 (CAN) SHORTLY AFTER TAKEOFF WHILE PERFORMING A LOW LEVEL TURN, THE ENGINE REPORTEDLY LOST POWER. EMERGENCY POWER LEVER W AS ACTIVATED WITH NO RESPONSE. AIRCRAFT LANDED ON A STREET, NO FATALITIES. INITIAL INVESTIGATION REVEALED NO EVIDENCE OF PRE-IMPACT ANOMALIES. FUEL SYSTEM COMPONENTS WILL BE INVESTIGATED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVIS E OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071113003) 1 H 7 1 3T 3 T A37CE E4EA 2008013100261 20080131 00261 NE 2008 1 31 CA071113005 2 20071106 G 7321 32448809 FUEL CONTROL CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE ENGINE FAILED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION AP APPROACH 1 CA JC0359 (CAN) DURING APPROACH, ENGINE SPEED DESCENDED TO SUBNORMAL VALUE. NO/SLOW RESPONSE FROM THRUST LEVER. CONDITION WAS REPE ATABLE ON GROUND FOLLOWING THE INCIDENT. FUEL CONTROL CHANGED AS PART OF TROUBLESHOOTING. (TC NR 20071113005) 2 L 7 2 4F 4 F RT A22CE E25EA 2008020400152 20080204 00152 EA 2008 2 4 CA071113006 1 20071112 G 3340 BJ10021003 CAMLOCK BRUCE BJ10021003 CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE LIGHT WORN W K NONE O OTHER IN INSP/MAINT 1 CA 0075 (CAN) DURING AN OVERNIGHT MAINTENANCE INSPECTION IT WAS DISCOVERED THAT THE LT WING INSPECTION LIGHT LENS WAS MISSING TO GETHER WITH THE BULB HOLDER LEAVING THE WIRES EXPOSED. WHEN THE FAIRING WAS REMOVED TO REPLACE THE ASSEMBLY IT WAS NOTIC ED THAT A CAMLOC NUT HAD BEEN STRETCHED CAUSING THE FASTENER TO BE LOOSE. FORTUNATELY THE MISSING PARTS DID NOT DAMAGE T HE AIRCRAFT OR THE ENGINE. (TC NR20071113006) 2 L 7 2 4F 4 F RT A21EA E15NE 2008020400151 20080204 00151 EU 2008 2 4 CA071113007 1 20071108 G 2510 5PC41301001 DOUBLER ISRAEL PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL SEAT PAN CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2763 386 (CAN) DOUBLER INSTALLED ON CRACKED SEAT PAN WEB IAW SB 5PC41000-MOD1, FOUND CRACKED. NEW DOUBLER PN 5PC41301-001 INSTALL ED. (TC NR 20071113007) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008020400150 20080204 00150 EA 2008 2 4 CA071113008 1 20071106 G 5610 NP13932111 WINDOW CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C1 30049 NE COCKPIT BROKEN W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 11455 (CAN) CREW REPORT THAT AT 360 THE CAPTS FWD WINDOW SHATTERED AND THEY DIVERTED WINDOW REPLACED (TC NR 20071113008) 2 L 7 2 4F 4 F RT A21EA E00063EN 2008020400149 20080204 00149 NE 2008 2 4 CA071113009 2 20071108 G 7261 CARBON SEAL CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE ACTUATOR DEFECTIVE W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 17457 (CAN) AFTER TAKEOFF, CREW GOT A (SMOKE TOILET CAUTION MESSAGE). CABIN WAS FILLED WITH SMOKE. AFTER QRH WAS COMPLETED RET URNED TO FIELD AND MESSAGE WAS GONE A SHORT WHILE AFTER. MX FOUND OIL LEAKING FROM ENGINE VARIABLE GUIDE VANE (VG) ACT UATOR STRUTS AND LEAKING INTO THE BLEEDS. SUSPECT NR 3 CARBON SEAL. SLC REPLACED THE RT ENGINE. (TC NR 20071113009) 2 L 7 2 4F 4 F RT A21EA E15NE 2008020400148 20080204 00148 NE 2008 2 4 CA071113010 2 20071105 G 7261 CARBON SEAL CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE NR 3 LEAKING W A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA (CAN) JUST AFTER TAKEOFF, THE CABIN STARTED TO FILL WITH SMOKE AND THE LAV SMOKE DETECTOR WENT OFF. THEY DECLARED EMERGE NCY AND RETURNED TO THE FIELD. NO EVACUATION, SMOKE CLEARED ON LANDING. MX FOUND THE RT ENGINE NR3 CARBON SEAL TO BE FAU LTY. MX REPLACED RT ENGINE (TC NR 20071113010) 2 L 7 2 4F 4 F RT A21EA E15NE 2008020400147 20080204 00147 SO 2008 2 4 CA071114001 1 20071022 G 2435 HOUSING PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2A GL STARTER GEN FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 112 FN2407123 (CAN) MOTOR ATTACH BOLT PULLING OUT OF HOUSING. NOT AN INFLIGHT SAFETY CONCERN. (TC NR 20071114001) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008020400146 20080204 00146 SO 2008 2 4 CA071114002 1 20071109 G 2435 CASE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL STARTER GEN FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 50 FNR510603 (CAN) MOTOR ATTACH BOLT PULLING OUT OF HOUSING. (TC NR 20071114002) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008020400145 20080204 00145 CE 2008 2 4 CA071114003 1 20070924 G 3246 31607 WHEEL CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 2114 (CAN) RIM WAS EDDY CURRENT INSPECTED FOR CRACKS IAW MM AND CORROSION PITS WERE FOUND ON RIMS (IB AND OB) WHERE TIRE MAKE S AIR SEAL. THE CORROSION PITS WERE MORE THAN 0.010 INCH ALLOWED AND WHEEL WAS SCRAPPED. (TC NR 20071114003) 2 L 7 2 4F 4 F RT A22CE E00053EN 2008020400144 20080204 00144 WP 2008 2 4 CA071114004 1 20071005 G 2140 C16932 SHROUD ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE HEATER CRACKED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 1288 (CAN) THE PILOT SMELLED EXHAUST FUMES IN THE CABIN WHILE IN CRUISE FLIGHT. THE PILOT THEN CLOSED THE HEATER CONTROL AND OPENED THE VENTS FOR FRESH AIR. THE PILOT THEN FLEW BACK TO THE BASE FOR THE ENGINEER TO INSPECT. THE ENGINEER FOUND A CRACK IN THE EXHAUST SYSTEM INSIDE THE HEAT SHROUD AT THE ELBOW WHERE THE EXHAUST EXITS THE MUFFLER. THE EXHAUST SYSTEM WAS THEN REPLACED WITH A NEW PART. (TC NR 20071114004) 1 G 7 1 3O 3 O H11NM 1E4 2008020400143 20080204 00143 2008 2 4 CA071114005 4 20071109 G 3418 TRANSMITTER PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL AOA INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA 1873 0321 (CAN) DURING ROUTINE 150 HR INSP , LT AOA VANE HEAT WAS FOUND INOPERATIVE. PROBE AND PLATE HEAT WERE FUNCTIONING NORMAL. COMPLETE ASSY REPLACED. (TC NR 20071114005) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008020400142 20080204 00142 CE 2008 2 4 CA071114006 1 20070928 G 2435 300SGL129Q2 STARTER GEN CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE FAILED W O OTHER O OTHER CR CRUISE 1 CA 671 (CAN) AC INFLIGHT HAD RT GENERATOR OUTPUT FLUCTUATING. CHECKED ON GENERATOR IAW MM WAS FOUND OK. BUT INFLIGHT FLUCTUATIN G, REPLACED GENERATOR AND PROBLEM WENT AWAY. (TC NR 20071114006) 2 L 7 2 4F 4 F RT A22CE E00053EN 2008020400141 20080204 00141 EU 2008 2 4 CA071114007 1 20071012 G 6320 BM1021 CHIP DETECTOR UROCOP UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE M/R GEARBOX SHORTED W O OTHER O OTHER NR NOT REPORTED 1 CA 33 M672 (CAN) MAIN GEARBOX MAGNETIC CHIP PLUG SHORTED INTERNALLY. (TC NR 20071114007) 1 G 7 2 3U 3 U NC R0001RD E34NE 2008020400140 20080204 00140 CE 2008 2 4 CA071114008 1 20071102 G 3297 WIRE HARNESS CESSNA 525 525 2076601 CE BRAKES SHORTED W O OTHER O OTHER LD LANDING 1 CA (CAN) THE EMERGENCY BRAKE HAD TO BE USED UPON LANDING AS IT WAS DISCOVERED THAT THE ANTI-SKID WIRING HARNESS HAD A SMALL AMOUNT OF SLACK BETWEEN THE TRAILING LINK AND THE TRUNNION. THIS ALLOWED IT TO RUB AGAINST THE TIRE, WEARING OFF THE CO ATING AND UPON LANDING ON A WET SURFACE CAUSED SHORTING. (TC NR 20071114008) 1 L 7 2 4F RT A1WI 2008020400139 20080204 00139 CE 2008 2 4 CA071114009 1 20070913 G 3211 998100287 BRACE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCB4T HCB4TN3 GL MLG TORQUE LINK CRACKED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 6269 (CAN) FLIGHT CREW CONDUCTED A CROSSWIND LANDING, SHUTDOWN, AND PASSENGERS DEPLANED ON REMOTE RAMP LOCATION. UPON TAXIING TO THE TERMINAL FOR THE NEXT FLIGHT, CREW NOTICED THE AIRCRAFT FELT DIFFERENT. MAINTENANCE WAS CALLED, AND A VISUAL INS PECTION FOUND THAT THE LT MLG TRUNNION BOSS ASSY HAD BROKEN AWAY. FURTHER INVESTIGATION REVEALED THE RT MLG WAS CRACKED IN THE SAME AREA. A HARD-LANDING INSPECTION WAS COMPLETED IAW CARS 625 APP G, AND AMM 5-50-00 AS A PRECAUTIONARY MEASUR E. MAIN LANDING GEAR ASSEMBLIES WERE REPLACED, SERVICED, AND GEAR SWINGS CONDUCTED IAW AMM. (TC NR 20071114009) 1 L 7 2 3T 4 T A14CE E4EA 6 C P40EA 2008020400138 20080204 00138 CE 2008 2 4 CA071114010 1 20071114 G 5751 0523809 RIB CESSNA 150 A150M 2071831 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL LT AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9500 9500 (CAN) AILERON CENTER RIB P/N 0523809 FOUND CRACKED MULTIPLE LOCATIONS ON FWD VERTICAL ANGLE COMMON TO CONTROL ROD ATTACH BRACKET. IN ADDITION THE CONTROL ROD ATTACH BRACKET P/N 0760011-2 WAS ALSO CRACKED IN 2 LOCATIONS COMMON TO AILERON SP AR. (TC NR 20071114010) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2008020400137 20080204 00137 EU 2008 2 4 CA071115001 1 20071110 G 5343 S53578400000 FITTING AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF5 NE MLG ACTUATOR FAILED W O OTHER O OTHER LD LANDING 1 CA 29987 (CAN) DURING THE APPROACH, THE CREW HEARD A LOUD BANG WHEN THE LANDING GEAR WAS SELECTED DOWN. THE CREW DID NOT OBSERVE ANY OTHER WARNING INDICATIONS AND A NORMAL LANDING WAS COMPLETED. THE CREW CONDUCTED A POST LANDING CHECK AND FOUND THE LT MLG EXTENTION/RETRACTION ACTUATOR SEPARATED FROM THE AIRCRAFT. THE FUSELAGE MOUNTING FITTING HAD FAILED. THE AIRCRAFT MOVED FOR MAINTENANCE ACTION. THE COMPANY HAS INITIATED A FLEET CAMPAIGN TO INSPECT ALL ACTUATOR FITTINGS. (TC NR 20071 115001) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008020400136 20080204 00136 EA 2008 2 4 CA071115002 1 20071024 G 3246 L814749 BEARING DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL WHEEL ASSY FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFTER LANDING THE LT OB MAIN WHEEL HUBCAP WAS DISCOVERED MISSING. FURTHER INVESTIGATION FOUND THE INNER BEARING WA S BLOWN APART, THE WHEEL AND BRAKE ASSY HAD EXTENSIVE DAMAGE FROM THE WHEEL RUBBING ON THE BRAKE ASSY. THE AXLE WAS INSP ECTED, NO DAMAGE WAS FOUND. DUE TO ALL THE RAIN IN THE AREA, THIS AIRCRAFT IS OPERATING IN A EXTREMELY MUDDY ENVIRONMENT , WE SUSPECT THAT MUD AND WATER MAY HAVE ENTERED THE BEARING AREA CAUSING PREMATURE FAILURE OF BEARING. THIS BEARING HAD 144 LANDINGS SINCE NEW. CURRENTLY, THE BEARINGS ARE INSPECTED AND RE-LUBRICATED AT THE (A) CHECK (150 HOURS). THIS INS PECTION ALONG WITH THE LUBRICATION OF THE LANDING GEAR WILL BE REDUCED TO 50 HOURS FOR THE DURATION OF THE OPERATION IN 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2008020400135 20080204 00135 GL 2008 2 4 CA071115003 2 20071115 G 7230 6871259 BOLT ALLSN ALLSN 250C 250C20J 03013 GL COMPRESSOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3486 CAC43118 (CAN) COMPRESSOR TIEBOLT S/N KU506716 FOUND CRACKED AXIALLY UPON REWORK AT MPI AFTER REMOVAL OF SILVER PLATING ON EXTERI OR OF PART. PART SCRAPPED. CRACK WAS NOT DISCOVERED UPON INITIAL MPI, MOST LIKELY BECAUSE OF THE SILVER PLATE BRIDGING THE CRACK SURFACE. SEM EVALUATION OF CRACK INDICATED A DEPTH OF APPROXIMATELY 600 MICRO METERS RADIALLY . EDS EVALUATI ON OF THE CRACK INDICATED THAT THE CRACK WAS FULL TO EXTREMITIES WITH IRON OXIDE. THIS APPEARS TO BE A MANUFACTURING DEF ECT. NO ASSOCIATED DAMAGE OR SERVICE ISSUES NOTED ON REMAINDER OF COMPRESSOR ASSEMBLY. HARDNESS OF MATERIAL WAS WITHIN S PECIFICATIONS. FAILURE OF BOLT WOULD BE CATASTROPHIC. (TC NR 20071115003) 3 U E4CE 2008020400134 20080204 00134 EA 2008 2 4 CA071115004 1 20071115 G 7120 CSP28229 BOLT DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE MOUNT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 1739 (CAN) ENGINE MOUNT BOLTS THAT DAMAGED THE THREADS UPON REMOVAL. BOLTS WHERE INSTALLED ON 12/22/2005. (2) OF THE (4) TOP MOUNT BOLTS HAVE DAMAGED THREADS AND ARE NOT RE-USABLE. THREADS IN ENGINE CASE REQUIRE CLEAN-UP. (TC 20071115004) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2008020400133 20080204 00133 EU 2008 2 4 CA071115005 1 20071115 G 6400 355A12004008 TAIL ROTOR SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE OUT OF BALANCE W K NONE E F VIBRATION/BUFFET FLT CONT AFFECTED IN INSP/MAINT 1 CA (CAN) UNABLE TO BALANCE T/R WITH OUT LARGE AMOUNTS OF BALANCE WEIGHT. T/R WOULD GO OUT OF BALANCE EVERY 3 TO 4 DAYS. SEN DING T/R TO MFG FOR EVALUATION. (TC NR 20071115005) 1 G 7 1 3U 3 U H9EU E19EU 2008020400132 20080204 00132 EA 2008 2 4 CA071115006 1 20071115 G 2497 BUSS BAR CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE DAMAGED SPARKS W K NONE O OTHER IN INSP/MAINT 1 CA 1968 (CAN) CPB1 CENTER BUS BAR LINK W57PD SPARKING UNDER LOOSED SCREW. BUS BAR W57PD AND W440PD REPLACED. 10029 DROPS (TC N R 20071115006) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2008020400131 20080204 00131 NE 2008 2 4 CA071115007 1 20071114 G 6320 SB2151107 BEARING SKRSKY S76 S76C 8143008 NE M/R GEARBOX SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 2969 A23100240 (CAN) MGB REMOVED DUE TO MAKING METAL, THE ABOVE BEARING WAS FOUND TO BE SPALLED (TC NR 20071115007) 1 G 7 2 3U NC H1NE 2008013100262 20080131 00262 GL 2008 1 31 CA071115008 1 20071031 G 7602 HF3M BEARING DIAMON DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA ROD END SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA 244 (CAN) PILOT REPORTED MIXTURE STICKING DIFFICULT TO MOVE. INSPECTION REVEALED MIXTURE CONTROL ROD END AT MECHANICAL FUEL PUMP SEIZED. ROD END WAS REPLACED WITH NEW UNIT. THIS ROD END IS OF THE SAME PN WHICH SEIZED ON ANOTHER AIRCRAFT`S THROT TLE CONTROL WHICH RESULTED IN AN OFF AIRPORT LANDING AND DAMAGE TO THE AIRCRAFT BACK IN FEB. 2005. HOPING TO HAVE THE BE ARING ANALYZED BY A LAB. (TC NR 20071115008) 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2008013100263 20080131 00263 EU 2008 1 31 CA071115009 1 20071115 G 6410 355A12004008 TAIL ROTOR SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE UNBALANCED W K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 CA 1067 (CAN) EXCESSIVE AMOUNT OF TIP BALANCE WEIGHT TO BALANCE TAIL ROTOR. (TC NR 20071115009) 1 G 7 1 3U 3 U H9EU E19EU 2008013100264 20080131 00264 EA 2008 1 31 CA071115010 1 20071112 G 5312 C6W11509 RIB DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 29229 (CAN) RIB FLANGE FOUND CRACKED ON IB SIDE WHERE IT IS RIVETED TO THE TOP SKIN CORRUGATIONS. CRACKING FOUND WHEN INSPECTI NG RIBS 8-22 IAW MFG STRUCTURAL LIFE LIMITS. (TC NR 20071115010) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2008013100265 20080131 00265 EA 2008 1 31 CA071115011 1 20071114 G 5532 C6TFM102527 PLATE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 31743 (CAN) CRACK INDICATION FOUND IN A CORROSION PIT IN THE AFT ATTACH PLATE WHEN INSPECTING IT IAW SB 454. (TC NR 2007111501 1) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2008013100266 20080131 00266 SW 2008 1 31 CA071116001 1 20071114 G 3040 SENSOR SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE WINDSHIELD TEMP OVERHEATED W O OTHER M B OVER TEMP SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA 4805 87H0829830 (CAN) THE FOLLOWING WAS REPORTED BY THE FLIGHT CREW FOLLOWING THE CO-PILOTS HEATED WINDSHIELD FAILURE: (WHILE ON THE ILS FO MENTIONED A BURNING SMELL, AND NOTICED IT AS WELL.) TOOK MY FLASHLIGHT OUT BUT COULD NOT NOTICE ANY DETECTABLE SMOKE IN THE CABIN OR COCKPIT. CONTINUED THE APPROACH WITH BLEED HEAT OFF AND FRESH AIR FAN RUNNING. BY THE TIME WE LANDED, T HE SMELL WAS STRONGER BUT COULD NOT SEE ANY SMOKE. ON THE GROUND WE SHUTDOWN THE ELECTRONICS AS SOON AS POSSIBLE AND THE N SHUT DOWN THE AIRCRAFT. PASSENGERS NOTICED THE SMELL IN THE BACK AS WELL. IT WAS OBVIOUS THAT IT WAS AN ELECTRICAL SME LL, AND THERE WAS SMOKE EVIDENT WHEN WE TOOK OUT OUR FLASHLIGHTS AGAIN ON THE GROUND. UPON INSPECTION BY MAINTENANCE IT 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 2008013100267 20080131 00267 CE 2008 1 31 CA071116002 1 20071115 G 3610 1013800273 REGULATOR VALVE BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL PNEUMATIC PRESS INOPERATIVE W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 210 (CAN) WHILE IN CRUISE FLIGHT AT FL230 THE FLIGHT CREW OBSERVED THE PNEUMATIC PRESSURE GUAGE RAPIDLY FLUCTUATING BETWEEN 18 AND 23 PSI. THERE WAS AN ASSOCIATED CHATTERING HEARD IN THE AIRFRAME, IN CONJUNCTION WITH THE FLUCTUATING INDICATOR. FLIGHT CREW DECIDED TO RETURN TO BASE AND PNEUMATIC INDICATIONS RETURNED TO NORMAL DESCENDING THROUGH 15,000 FEET AND RE MAINED THAT WAY TO LANDING. MAINTENANCE REPLACED PNEUMATIC PRESSURE VALVE/REGULATOR PN 101-380027-3 (PN 1H75-12). (TC NR 20071116002) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2008013100269 20080131 00269 EA 2008 1 31 CA071118001 1 20071115 G 2730 510009 ROD END MENASCO 510009 CNDAIR CL600 CL6002D24 1390016 EA GE CF34 CF348C5 30050 NE PCU BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA MAL2449 (CAN) REPORT FROM AIR ONE: REF /A/ - AIPC 27-33-01, FIG 1 WHILE PERFORMING TASK CARD 000-27-220-010 - OPERATIONAL TEST OF THE ELEVATOR PCUS, AIR ONE FOUND THAT WITH HYD 1 ONLY, THE ELEVATOR WOULD NOT MOVE. AFTER INSPECTION, THEY FOUND TH AT PCU 1 ROD END (ON THE ELEVATOR ATTACHING LUG) WAS BROKEN IN (2) PIECES AT THE PCU PISTON THREADS. PRIOR REMOVING ANY THING, IT WAS NOTICED THAT THE ROD END SEEMED JAMMED (UNABLE TO TURN THE ROD END AROUND THE BOLT) ON ITS ATTACHING BOLT (REF /A/ ITEM 275) WHILE ATTEMPTING TO REMOVE THE BROKEN ROD END, THE ATTACHING NUT (REF /A/, ITEM 295) WAS EASILY REMO VABLE. HOWEVER, IT WAS NOT POSSIBLE TO TURN OR REMOVE THE BOLT (REF /A/, ITEM 275) FROM THE ELEVATOR PCU FITTING (REF SR 2 L 7 2 4F 4 F RT A21EA E00063EN 2008013100270 20080131 00270 EA 2008 1 31 CA071118002 1 20071108 G 5610 NP13932113 WINDSHIELD CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C5B1 30052 NE COCKPIT CRACKED W B EMER. DESCENT O OTHER CR CRUISE 1 CA (CAN) IN FLIGHT LT WINDSHIELD CRACKED, AIRCRAFT CONTINUED TO DESTINATION. NO FURTHER REPORTED DETAILS. (TC NR 2007111800 2) 2 L 7 2 4F 4 F RT A21EA E00063EN 2008013100271 20080131 00271 2008 1 31 CA071119001 4 20071106 G 2210 065008617 CONTROL MODULE PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL EADI INOPERATIVE W O OTHER O OTHER CR CRUISE 1 CA (CAN) (ALT) LAMP DID NOT ILLUMINATE ON MODE CONTROL. ALTITUDE CAPTURE WAS NORMAL WITH ALT CAPTIONS (ON) AS DISPLAYED ON BOTH EADI SCREENS. (TC NR20071119001) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008013100272 20080131 00272 2008 1 31 CA071119002 4 20071115 G 3497 CONNECTOR PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL OAT INDICATOR DAMAGED W O OTHER N FALSE WARNING CR CRUISE 1 CA 7326 (CAN) OAT INDICATION ON EIS ERRACTIC. ONE OF THE PINS IN OAT CONNECTOR FOUND LOOSE. NEW CONNECTOR INSTALLED WITH 2 NEW P INS. SYSTEM NORMAL. (TC NR 20071119002) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008013100273 20080131 00273 EU 2008 1 31 CA071119003 1 20071115 G 3110 0660312525 DISPLAY PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL EADI INTERMITTENT W O OTHER O OTHER CR CRUISE 1 CA (CAN) PILOT`S EADI DISPLAY REPORTED TO GO (FUZZY) AND INTERMITTENTLY GOING BLANK. ED462 REPLACED WITH SERVICEABLE UNIT. (TC NR 20071119003) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008022100004 20080221 00004 NM 2008 2 21 CA071120001 1 20071115 G 2910 82970010149 LINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYD SYSTEM CHAFED W O OTHER J WARNING INDICATION DE DESCENT 1 CA 20516 (CAN) AIRCRAFT WAS RETURNING TO BASE WHEN THE HYDRAULIC LOW PRESSURE LIGHT ILLUMINATED. UPON SELECTION OF GEAR DOWN A LO UD (BANGING) NOISE WAS HEARD. GEAR EXTENDED NORMALLY, ALTHOUGH THE LOW PRESSURE LIGHTS WERE FLICKERING IN CONJUNCTION WI TH THE (BANGING) NOISE. AC WAS PLACED IN HANGER AND HYDRAULIC SYSTEM INSPECTED. THE RESERVOIR WAS FOUND TO BE LOW. RESER VOIR WAS REFILLED AND HYDRAULIC SYSTEM BLED, IT WAS AT THIS TIME THAT FLUID WAS OBSERVED TO BE LEAKING FROM ABOVE THE NR 2 ENGINE EXHAUST PIPE. UPON FURTHER INSPECTION THE PRESSURE LINE (82970010-149, PRE-MOD 8/670) WAS FOUND TO BE SEVEREL Y CHAFED. IT APPEARS TO HAVE BEEN CHAFED BY SPIRAL WRAP APPLIED TO THE SUCTION LINE, THE LINE WAS ALSO CLAMPED, BUT IMPR 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008022100005 20080221 00005 NE 2008 2 21 CA071120002 2 20071115 G 7230 COMPRESSOR SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE ENGINE STALLED W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 25972 4926 GEE785555 (CAN) TAKEOFF ROLL HAD NO PROBLEMS, BUT WHEN CHANGING THROTTLE SETTING FROM CLIMB POWER TO CRUISE POWER THE LT ENGINE EX PERIENCED A COMPRESSOR STALL. THEN THE A/C YAWED, THEN ANOTHER COMPRESSOR STALL OCCURRED AND THE (ENGINE) OVER TEMP`D. LITE FOR THE ITT CAME ON, THE PILOTS THEN SHUT THE LT ENGINE DOWN AND RETURNED TO AIRPORT ON THE RT ENGINE. (TC NR 2007 1120002) 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2008022100006 20080221 00006 SW 2008 2 21 CA071120004 1 20071116 G 6420 476411731 SHIM BELL BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL T/R HUB INOPERATIVE W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 CA A3402 (CAN) T/R VIBRATION DISCOVERED AND SUBSEQUENT STROBING WAS NOT EFFECTIVE AT REMOVING THE VIBRATION. DURING INSPECTION OF THE T/R HUB ASSEMBLY WAS FOUND TO HAVE BOTH PRE AND POST (TB: 206-91-139) METHODS OF TRUNNION CENTERING PERFORMED. SHIM 120-006C15-0 AND THRUST PLUG 47-641-173-1 USED ON ONE SIDE AND SHIM 206-011-861-101 AND THRUST PLUG 206-011-862-101 USE D ON THE OTHER. TAIL ROTOR HUB ASSEMBLY WAS REPAIRED. (TC NR 20071120004) 1 G 7 1 3U 3 U H2SW E4CE 2008020400130 20080204 00130 2008 2 4 CA071120005 4 20071119 G 3160 066031252500 DISPLAY PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL COCKPIT INOPERATIVE W O OTHER O OTHER CR CRUISE 1 CA (CAN) PILOT REPORTED LT EHSI WENT BLANK AND BACK ON TWICE DURING FLIGHT. DEFECT WAS CONFIRMED IN THE HANGAR AS THE DISPL AY WENT BLANK APPROX. 3 MINUTES AFTER POWER UP. (TC NR 20071120005) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008020400129 20080204 00129 EU 2008 2 4 CA071120006 1 20071106 G 2140 704A34402034 HOSE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE HEATER BURST W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) HEATER LINE FROM ENGINE FOUND BURST AND NOT SUPPLYING ALL THE HEAT TO THE CABIN. (TC NR 20071120006) 1 G 7 1 3U 3 U H9EU E19EU 2008022100007 20080221 00007 EU 2008 2 21 CA071120007 1 20071110 G 7921 350A5310520351 BLOWER MOTOR SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE OIL COOLER UNSERVICEABLE W O OTHER O OTHER LD LANDING 1 CA (CAN) HEARD NOISE AFTER LANDING AND SHUT THE AIRCRAFT DOWN. UPON INSPECTION FOUND THE BLOWER ROTOR COMPLETELY GONE. REPL ACED THE ROTOR, DUCT AND MOTOR TO GET THE AIRCRAFT SERVICEABLE. (TC NR 20071120007) 1 G 7 1 3U 3 U H9EU E19EU 2008022100008 20080221 00008 GL 2008 2 21 CA071121001 3 20071118 G 6111 BUSHING CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL PROP HUB WORN W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA 3729 962459 (CAN) THE PILOTS FELT A VIBRATION ON CLIMB. THEY REDUCED THE POWER BUT THE VIBRATION REMAINED. THEY RETURNED TO THE AIRP ORT WHERE THE AME INSPECTED THE ENGINE AND PROPELLER. NO DISCREPANCIES WERE NOTED ON THE ENGINE. ONE BLADE OF THE PROP W AS ABLE TO BE TWISTED BY HAND APPOX 3-5 DEGS. WE SUSPECT A FAILURE OF A BUSHING IN THE HUB AND HAVE SENT A REPLACEMENT P ROP BEFORE FURTHER FLIGHT. (TC NR20071121001) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2008022100009 20080221 00009 SW 2008 2 21 CA071121003 1 20071115 G 2497 AN3230 SWITCH SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE331* 01514 WP MCAULY 4HFR34 4HFR34C652 NE BUSS TIE BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) PILOT REPORTED STRANGE SMELL COMING FROM LT BLEED IN COCKPIT. AFTER TROUBLESHOOTING BY MAINTENANCE IT WAS FOUND TH AT LT ESSENTIAL BUS TIE SWITCH WAS CRACKED AND THE WIRE CONNECTORS GOING TO THE LT CB PANEL HAD BECOME OVERHEATED AND ME LTED THE HEAT SHRINK AND THE RUBBER PROTECTIVE BOOT AT THE TERMINALS. BUS TIE SWITCH REPLACED AND BOTH CONNECTORS REPAIR ED. (TC NR 20071121003) 2 L 7 2 4T 3 T RT A8SW E2WE 6 C 3PNE 2008022100010 20080221 00010 NM 2008 2 21 CA071121004 1 20071120 G 2150 TURBINE DORNER DO32 DO328100 2996000 NM PWA 119 PW119C NE HARTZL HDE6C HDE6C3B NE A/C PACK SEIZED W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 350 (CAN) AIRCRAFT DEVELOPED WHITE SMOKE IN CABIN WHILE TAXING FOR TAKEOFF. PILOTS NOTICED A CAS LT PACK FAIL LIGHT AND AN A FT LAV SMOKE DETECT CAS MESSAGE. AIRCRAFT RETURNED TO BLOCKS AND PASSENGERS DEBOARDED. CAUSE OF SMOKE WAS TURBINE SEIZED CAUSING A LT PACK OVERHEAT. ENVIROMENTAL CONTROL UNIT (ECU) REPLACED. (TC NR 20071121004) 2 H 7 2 4T 4 T RT A45NM E20NE 6 C P34NE 2008022100011 20080221 00011 EU 2008 2 21 CA071122001 1 20071116 G 3234 F10A793 CONTROL HANDLE AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE7312 01518 WP MLG EMER EXTEND INOPERATIVE W O OTHER J WARNING INDICATION CL CLIMB 1 CA 5874 (CAN) DURING THE CLIMB, THE LT MAIN LANDING GEAR INTRANSIT STAYED ON DURING GEAR RETRACTION. THE CREW FLEW BACK TO DEPAR TURE WITH THE GEAR DOWN. AFTER THEY LANDED AT DEPARTURE AIRPORT. WE INSPECTED THE GEAR IAW THE MM AND CAR 605.88. IT WAS FOUND THAT THE MANUAL EMERGENCY HANDLE WAS OFF SET SLIGHTLY CAUSING THE GEAR NOT TO FULLY LOCK IN THE UP POSITION. THE EMERGENCY CONTROL SYS WAS RESET IAW THE MM. SATISFACTORY GEAR SWINGS WERE CARRIED OUT. CALLED FOR A TEST FLIGHT, THE TE ST FLIGHT WAS CARRIED OUT WITH NO FAULTS. (TC NR 20071122001) 2 L 7 2 4F 4 F A33EU E6WE 2008022100012 20080221 00012 CE 2008 2 21 CA071122002 1 20071121 G 3210 508103237 TORQUE LINK BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA MCAULY 4HFR34 4HFR34C762 NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A SPECIAL LPI INSP (SELF IMPOSED INSPECTION DUE TO BROKEN LINK SEE SDR NR 2007024010) OF THE UPPER AND LOWE R TORQUE LINKS ON (2) OF OUR AC, (3) TORQUE LINKS WERE FOUND CRACKED IN THE RADIUS AREA. ONE LINK HAS 2 CRACKS SIDE BY SIDE THE OTHER HAD ONE SMALLER CRACK. THE CRACK IN THE THIRD LINK WAS VERY SMALL AND DID NOT SHOW IN THE PHOTOS. (TC NR 20071122002) 1 L 7 2 3T 4 T A14CE E4EA 6 C 3PNE 2008022100016 20080221 00016 NM 2008 2 21 CA071122003 1 20071122 G 3246 296852629 BEARING BOMBDR DHC8 DHC8400 NM NR 4 WHEEL FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1584 70 (CAN) WHILE SERVICING THE MAINT OBSERVED SWARF AND GREASE AROUND THE HUBCAP OF NR 4 MAIN WHEEL ASSY. IB BEARING HAD FAIL ED. (TC NR 20071122003) 2 H 7 2 4T RT A13NM 2008022100017 20080221 00017 SW 2008 2 21 CA071122004 1 20071123 G 2810 71494R TANK BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL FUEL SYS CRACKED W K NONE K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 3206 (CAN) AIRCRAFT WAS IN FOR A 50 HR INSPECTION. AFTER ENGINE RUN UP, MECHANIC DETECTED GAS FUMES AND LOOKED ON THE RT SIDE ON THE AC WINGS NEAR TRAILING EDGE NOTICE FUEL STAINING. RT OB TANK WAS REMOVED AND 1 INCH CRACK WAS FOUND ON THE RADIU S OF THE LATERAL RE-ENFORCEMENT INDENT OF TANK. (TC NR 20071122004) 1 H 7 1 3O 3 O A21CE E286 5 N P874 2008022100018 20080221 00018 NM 2008 2 21 CA071122006 1 20071109 G 3230 656021132 ACCESSORY UNIT BOEING 727 727223 1384074 NM PWA JT8 JT8D15 52051 NE MLG INOPERATIVE W O OTHER O OTHER CL CLIMB 1 CA (CAN) THE CREW DISCOVERED THAT THE LANDING GEAR HANDLE WOULD NOT MOVE PAST THE (OFF) POSITION WITHOUT THE USE OF THE OVE RRIDE TRIGGER. AT THE TERMINATING STATION, MAINTENANCE REPLACED THE LANDING GEAR ACCY UNIT AND RETURNED THE AIRCRAFT TO SERVICE. (TC NR 20071122006) 2 L 7 3 4F 4 F A3WE E2EA 2008022100019 20080221 00019 NE 2008 2 21 CA071122007 2 20071121 G 7414 BL600646201 MAGNETO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 1242 1242 (CAN) ENGINE START ATTEMPTED, RT MAGNETO FAILED TO OPERATE. (TC NR 20071122007) 1 G 7 1 3O 3 O H11NM 1E4 2008022100020 20080221 00020 SO 2008 2 21 CA071123001 1 20071120 G 8120 BEARING GARRTT PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL TURBOCHARGER FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 357 357 JJR00638 (CAN) DURING A RT ENGINE INSPECTION AN EXHAUST STAIN WAS WAS NOTICED IN THE AREA OF THE TURBOCHARGER. UPON CLOSER INVES TIGATION, IT WAS DISCOVERED THAT THE TURBOCHAGERS EXHAUST BEARING SEAL BETWEEN THE COMPRESSOR AND TURBINE HAD FAILED. TH E TURBO WAS REPLACED AND AC RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. (TC NR 20071123001) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008022100021 20080221 00021 EU 2008 2 21 CA071123002 1 20071123 G 7700 ENGINE ARRIEL2B SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE MALFUNCTIONED W R AUTOROTATION J WARNING INDICATION CR CRUISE 1 CA 22360 (CAN) PILOT IN CRUISE FLIGHT, APPROX 2000 FEET, EXPERIENCED ENGINE PROBLEMS WITH ANNUNCIATOR INDICATIONS . PROCEEDED WIT H SUCCESSFUL AUTOROTATION LANDING IN FIELD. REST IS UNDER INVESTIGATION (TC NR 20071123002) 1 G 7 1 3U 3 U H9EU E00054EN 2008022100022 20080221 00022 CE 2008 2 21 CA071123003 1 20071122 G 7120 595104814 MOUNT CESSNA 425 425 2076018 CE PWA PT6 PT6A112 52043 NE MCAULY 4HFR34 4HFR34C762 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6126 (CAN) WHILE PERFORMING MFG 100 HR ENGINE INSPECTION ON THE RT ENGINE, THE OB ENGINE MOUNT WAS FOUND CRACKED. THE MOUNT W AS REPLACED WITH A NEW UNIT. (TC NR 20071123003) 1 L 7 2 3T 3 T RT A7CE E4EA 6 C 3PNE 2008022100023 20080221 00023 EA 2008 2 21 CA071123004 1 20071116 G 5610 NP1393226 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) RT SIDE WINDOW CRACKED ON FLIGHT. AC RETURNED. NO FURTHER INFORMATION REPORTED BY CREW. RT SIDE WINDOW CHANGED A ND AC RETURNED TO SERVICE. (TC NR 20071123004) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022100024 20080221 00024 WP 2008 2 21 CA071123005 2 20071122 G 7210 REDUCTION GB BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33110 01514 WP ROTOL R333 R333482F12 GL LT ENGINE FAILED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 18925 4525 P63283 (CAN) WHILE IN CRUISE AT 16000 FT, A THUMP WAS FELT AND HEARD FROM THE LT ENGINE. A LARGE POWER DROP WAS NOTICED THEN A SECOND THUMP FROM THE LT ENGINE WHICH WAS FOLLOWED BY THE OIL CAP ANNUNCIATION ILLUMINATION. IMMEDIATELY TURNED BACK AND SHUT THE ENG DOWN. ATC, COMPANY, AND PASSENGERS WERE ADVISED AND REQUESTED THE EMERGENCY VEHICLES BE ON STANDBY, THE REMAINDER OF THE FLIGHT AND LANDING WERE UNEVENTFUL. MAINT INSP OF LT ENGINE REVEALED LIMITED ENGINE ROTATION WHEN TUR NING THE PROP, INDICATING RGB INTERNAL COMPONENT/S FAILURE. LT ENGINE CHIP DETECTOR AND OIL FILTER WERE REMOVED AND META L CONTAMINATION WAS OBSERVED IN BOTH AREAS. THE ENGINE WAS REMOVED FOR SHIPMENT TO A REPAIR FACILITY FOR TEAR DOWN DAMAG 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C P61GL 2008022100025 20080221 00025 NE 2008 2 21 CA071126001 2 20071123 G 7310 87620102007015 CONTROL ROD DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE FUEL SYS SEPARATED W C ABORTED TAKEOFF X J ENGINE FLAMEOUT WARNING INDICATION TO TAKEOFF 1 CA (CAN) ON TAKEOFF ROLL, THE NR 1 ENG PROPELLER RPM ONLY REACHED 900 RPM (NORMAL 1200RPM) AND THE TORQUE INDICATION REACHE D 115 PERCENT FOR APPROX 2 SECONDS. POWER LEVERS WERE RETARDED TO FLIGHT IDLE AND THE TAKEOFF ABORTED, AC RETURNED TO T HE GATE. THE PROPELLER WOULD NOT FEATHER NORMALLY SO MANUAL FEATHER WAS SELECTED TO FEATHER AND WHEN THE FUEL CONDITION WAS SET TO SHUTOFF, THE ENGINE DID NOT SHUTDOWN AND THE FIRE T-HANDLE HAD TO BE PULLED TO SHUTDOWN. MAINT INVESTIGATED AND IT WAS FOUND THAT THE FUEL CONDITION CONTROL ROD HAD SEPARATED, THEREFORE THERE WAS NO FUEL SHUTOFF CONTROL. THE FU EL CONDITION CONTROL ROD WAS REPLACED (PN 87620134-003 INSTALLED, 72-20-00-05-150) AND THE AC RETURNED TO SERVICE. (TC N 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008022100026 20080221 00026 GL 2008 2 21 CA071126002 3 20071110 G 6110 1192 DIAPHRAGM NAVION STC STCNAVION CONT E225 E2254 17015 SO HARTZL HC12X HC12X207 GL PROPELLER SPLIT W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION DE DESCENT 1 CA NAV4779 (CAN) RUBBER ON DIAPHRAM WAS FOUND SPLIT AT INNER SECTION. UNCERTAIN AS TO WHY THE RUBBER APPEARED STIFFER THAN THE PREV IOUS DIAPHRAM. THE DIAPHRAM IS BEING RETURNED TO MFG FOR INSP. WILL UPDATE WHEN RECEIVE THE INFORMATION BACK FROM THE M FG. (TC NR 20071126002) 1 L 7 1 3O 3 O A782 E267 5 C P845 2008022100027 20080221 00027 EA 2008 2 21 CA071126003 1 20071123 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAP UNSERVICEABLE W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA 2 2 (CAN) FLAP FAIL CAUTION MESSAGE ILLUMINATED WHILE IN CRUISE AND FLAPS WERE AT 0 DEG. FLAPLESS LANDING C/O AND A/C LANDED SAFELY. MAINT RANG OUT WIRES AND COULD NOT FIND ANY FAULTS. THE FECU AND THE RT BPSU WERE REPLACED. A TEST FLIGHT WAS C /O TO COLD SOAK TEMPERATURES FOR (2) HOURS AND THE A/C TESTED SERVICEABLE. THERE HAS NOT BEEN A REOCCURRENCE AT THIS TIM E. (TC NR 20071126003) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022100028 20080221 00028 CE 2008 2 21 CA071126006 1 20071106 G 8011 35016R GEAR CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO MCAULY 1A101 1A101HCM GL STARTER BROKEN W O OTHER O OTHER NR NOT REPORTED 1 CA 360 814153R (CAN) STARTER DRIVE ENGAGES ON TEETH ON GEAR. STARTER WAS SLIPPING, TOOK APART TO EXAMINE AND FOUND 3 BROKEN TEETH. STAR TER IS LIGHT WEIGHT. REPLACE STARTER SOLENOID 19 HOURS EARLIER AND BELIEVE FAULTY SOLENOID CAUSE OF PROBLEM. (TC NR 2007 1126006) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2008022100029 20080221 00029 WP 2008 2 21 CA071126007 2 20071108 G 7200 21190108000 COMPUTER BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE7315R 01518 WP DEEC INOPERATIVE W O OTHER J WARNING INDICATION CR CRUISE 1 CA 7 (CAN) ENGINES FRESH, NEW INSTALLATION OF DEECS ON AC. DEEC PROBLEMS OCCURRED. THE PROBLEM ENCOUNTERED WITH DIGITAL ENGI NE COMPUTERS (DEEC). (TC NR 20071126007) 2 L 7 2 4F 4 F RT A3EU E6WE 2008022100030 20080221 00030 EA 2008 2 21 CA071126008 1 20071122 G 2420 766283C GCU CNDAIR CL600 CL6002D24 1390016 EA GE CF34 CF348C5 30050 NE NR 2 FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) ACCORDING TO THE CREW WRITE UP: NR1- HYD 3A FAILED ( HYP PUMP 3A CAUTION MSG POSTED) ELECTRICALLY POWERED BY AC BU S NR2 - (GEN2 FAILED) WE DID NOT GET A AMBER GEN FAIL INDICATION OR WARNING. AC BUS 2 FAILED AGAIN, NO WARNING. TRU 2 AN D ESS TRU FAILED, NO WARNING. GEN AND IDG PINK ON SYNOPTIC PAGE AND PURPLE DASH LINES FOR KVA, V, HZ.   GEN1 DID NOT PIC K UP AC BUS 2. MAINTENANCE RAN THE ENGINES, CYCLED THE IDG SW (AUTO/OFF/RESET), COULD NOT DUPLICATE. PLACED A GCU ON O RDER. BASED ON THE MDC INFORMATION. GCU NR 2 REPLACED. (TC NR 20071126008) 2 L 7 2 4F 4 F RT A21EA E00063EN 2008022100031 20080221 00031 EA 2008 2 21 CA071126009 1 20071123 G 7110 2285000808 COWLING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE NACELLE BROKEN W K NONE D INFLIGHT SEPARATION IN INSP/MAINT 1 CA (CAN) UPON LANDING, DURING THE OPERATION OF NR1 THRUST REVERSER THE NR 1 ENGINE UPPER FAN COWL DEPARTED THE AC. THE PIL OTS DID NOT NOTICE THAT THE COWLING WAS MISSING UNTIL THEY DID THEIR POST FLIGHT WALK-AROUND. THE COWLING WAS LATER FOUN D BY AIRPORT OPERATIONS ON THE AIRFIELD OFF THE SIDE OF THE RUNWAY. THE COWLING WAS FOUND TO BE BROKEN IN HALF WHEN IT W AS RECOVERED. THE FAA STILL HAS POSSESSION OF THE COWING AT THIS TIME. (WILL ADD COWL SN WHEN THEY ARE MADE AVAILABLE) ( TC NR 20071126009) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022100032 20080221 00032 NE 2008 2 21 CA071126010 1 20071122 G 6320 S613566300 GEARBOX SKRSKY S61 S61N 8142104 NE GE CT58 CT581402 30011 NE MAIN ROTOR MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 30833 961 (CAN) INTERMEDIATE GEAR BOX CHIP LIGHT ILLUMINATED IN FLIGHT. AFTER LANDING CHIP PLUG INSPECTION CONFIRMED METAL CONTAMI NATION, AS WELL AS PAINT DISCOLORATION WAS NOTED IN THE INPUT BRG AREA. ASSY WILL BE SENT TO OH SHOP FOR INVESTIGATION. (TC NR 20071126010) 2 G 7 2 4U 4 U 1H15 1E3 2008022100033 20080221 00033 SW 2008 2 21 CA071126011 1 20071113 G 6320 212030154101 FITTING BELL BELL 205 205A1 1181414 SW LYC T53 T5317BLYC 41616 NE LIFT BEAM BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE INSPECTION OF THE LIFT LINK AREA, A CRACK WAS NOTED ON THE LIFT LINK FITTING. UPON FURTHER INVESTIGATIO N THE AFT EAR WAS COMPLETLY BROKEN FROM THE FITTING. THE BOLT SECURING THE LIFT LINK TO THE FITTING WAS INCORRECT FOR TH AT PN OF FITTING. THE BOLT DID FIT THE AFT EAR HOWEVER THERE WAS A .030 INCH GAP BETWEEN THE BOLT AND BUSHING IN THE FWD EAR ALLOWING THE BOLT TO ROCK UP AND DOWN IN THE FITTING. THIS ROCKING MOTION OCCURRED EVERY TIME IT WAS UNDER LOAD, AN D STRESSED THE AFT EAR SUBSEQUENTLY CAUSING IT TO CRACK. THE TRANSMISSION WAS INSTALLED IN 2001. ALL ENGINEERS MUST BE C ERTAIN WHEN INSTALLING FASTERNERS OR COMPONENTS THAT CORRECT PARTS ARE BEING USED ESPECIALLY WHEN DISASSEMBLY WHEN OFTEN 1 G 7 1 4U 4 U H1SW E17EA 2008022100034 20080221 00034 SW 2008 2 21 CA071126012 1 20071121 G 5302 206030446001 BULKHEAD BELL BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA BCJN07214 (CAN) LT AFT MOUNTING HOLE FOR T/R GEARBOX FOUND CRACKED. (TC NR 20071126012) 1 G 7 1 3U 3 U H2SW E4CE 2008022100035 20080221 00035 EU 2008 2 21 CA071127001 1 20071120 G 2913 3508806 PUMP AIRBUS 310 A310304 3930339 EU GE CF6 CF680C2A5 NE HYD SYSTEM CRACKED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 180 (CAN) DURING CRUISE, THE YELLOW HYD SYS OVERHEAT ECAM MESSAGE CAME ON. LATER THE HYD RESERVOIR (LO LEVEL) WARNING CAME O N THE ECAM. NORMAL QRH PROCEDURE WAS PERFORMED. DURING INVESTIGATION, MAINT FOUND YELLOW HYD PUMP LEAKING. HYD PUMP CASI NG WAS CRACKED. PUMP AND FILTERS WERE REPLACED AND AC RETURN TO SERVICE. UNSERVICEABLE PUMP WAS ROUTED TO REPAIR SHOP FO R INVESTIGATION. (TC NR 20071127001) 2 L 7 2 4F 4 F RT A35EU E13NE 2008022100036 20080221 00036 EU 2008 2 21 CA071127002 1 20071121 G 2530 HE62190 COFFEEMAKER AIRBUS 310 A310300 3930305 EU GE CF6 CF680C2A5 NE GALLEY SPARKS W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 20783 1782 (CAN) DURING FLIGHT, THE F/A REPORTED THE FWD COFFEE MAKER/WATER BOILER OVERHEATING AND NOTICED SOME SPARK COMING FROM T HE UNIT. THE UNIT WAS DEACTIVATED. THE UNIT WAS REPLACED BY MAINTENANCE AND ROUTED TO THE REPAIR SHOP FOR INVESTIGATION. (TC NR 20071127002) 2 L 7 2 4F 4 F RT A35EU E13NE 2008022100037 20080221 00037 WP 2008 2 21 CA071127003 1 20071126 G 6210 C1591 BEARING ROBSIN ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA M/R BLADE SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 652 5470A (CAN) WHILE CONDUCTING A DI, THE M/R BLADE BOOT WAS FOUND DISTORTED. THE BOOT WAS REPLACED AND A CHECK OF THE SPINDLE BE ARINGS WERE FOUND TO BE ROUGH. FURTHER INVESTIGATION REVEALED THE NR 6 BEARING INNER RACE WAS FOUND SPALLING. BEARING RE PLACED AND ASSY REINSTALLED. (TC NR 20071127003) 1 G 7 1 3O 3 O H11NM E295 2008022100038 20080221 00038 WP 2008 2 21 CA071127004 1 20071120 G 6730 D2121 SERVO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1848 (CAN) WHILE CARRYING OUT A 100 HOUR INSPECTION THE FWD LT SERVO WAS FOUND LEAKING. THE SERVO WAS CHANGED, GROUND RUN AND LEAK CHECK CARRIED OUT WITH OUT FURTHER INCIDENT. (TC NR 20071127004) 1 G 7 1 3O 3 O H11NM 1E4 2008022100039 20080221 00039 NE 2008 2 21 CA071127005 2 20071125 G 7314 LW15473 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYS FAILED W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA 355 (CAN) WHEN PILOT TRIED TO PULL THE AC UP IN A HOVER, THE ENGINE DECELERATED (BOGGED DOWN) UNTIL THE COLLECTIVE WAS LOWER ED. THIS WAS TRIED SEVERAL TIMES WITH NO SUCCESS. ALL INDICATIONS WERE NORMAL, TEMPS, PRESSURES, MAG DROPS, ETC. WHILE WAITING FOR THE ENGINEER TO ARRIVE ON SITE, THE PILOT GROUND RAN THE AC FOR 40 MIN TO WARM IT UP AND TRIED TO PULL POWER AGAIN. THIS TIME THE AC LIFTED UP NORMALLY WITH NO SYMPTOMS WHATSOEVER. WHEN THE ENGINEER ARRIVED THE AC WAS INSPECTED AND NO DEFECTS WERE FOUND. A 5 MIN TEST FLIGHT WAS COMPLETED WITH NO ABNORMAL SYMPTOMS. THE AC WAS SHUTDOWN AND REFUELED TO BE REPOSITIONED TO ANOTHER LOCATION. AFTER RE-STARTING AND WHILE TRANSITIONING FROM A HOVER TO FWD FLIGHT, THE ENGI 1 G 7 1 3O 3 O H11NM 1E4 2008022100040 20080221 00040 SW 2008 2 21 CA071127006 1 20071122 G 5302 BULKHEAD BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL TAILBOOM CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) AFT BULKHEAD P/N 206-030-446-001F CRACKED AT RT GEARBOX MOUNTING HOLE. (TC NR 20071127006) 1 G 7 1 3U 3 U H2SW E4CE 2008022100041 20080221 00041 SO 2008 2 21 CA071127007 1 20071122 G 8120 LW12778 BUTTERFLY VALVE LYC LTIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE WARPED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 1487 RL145668A (CAN) THE AC WOULD NOT GET FULL POWER ON THE RT ENGINE. AFTER A RUNUP ALL PARAMETERS WERE NORMAL AND THE TAKEOFF RESUMED . MAINT INSPECTED THE ENGINE AND FOUND THE BUTTERFLY VALVE TUBE THAT GOES OVER THE SHAFT WAS WARPED AND SPLIT. THIS WAS PROBABLY CAUSING AN INTERMITTENT STICKINESS IN THE BUTTERFLY. THE WASTEGATE WAS REPLACED WITH NO FURTHER ISSUES. (TC NR 20071127007) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008022100042 20080221 00042 EA 2008 2 21 CA071127008 1 20071121 G 5610 NP13932114 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) F/O WINDSHIELD SHATTERED OUTSIDE LAYERS AT FL340. (TC NR 20071127008) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022100043 20080221 00043 EA 2008 2 21 CA071127009 1 20071120 G 5610 13932113 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) CLIMBING THROUGH 32,400 ON OUR WAY TO 34,000 WE HEARD A POP AND SAW THE PILOTS WINDSHIELD CRACK/ SPLINTER. FOLLOWE D QRH AND CONTINUED TO DESTINATION. (TC NR 20071127009) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022100044 20080221 00044 NM 2008 2 21 CA071127010 1 20071123 G 3297 CONNECTOR GULSTM 200 200 4500308 NM NLG STEERING SYS CONTAMINATED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA 878 (CAN) AIRCRAFT LANDED, PILOT REPORTED NO NOSE WHEEL STEERING. PARKED AIRCRAFT AT FBO. LATER A/C WAS TAKEN TO MFG. THE NO SE WHEELING SYSTEM WAS INSPECTED AND MOISTURE WAS FOUND IN THE FEEDBACK POTENTIOMETER CONNECTOR PLUG. CLEANED AND RECONN ECTED CONNECTOR PLUG, APPLY SEALANT TO THE CONNECTOR PLUG AND THE COVER FOR THE FEEDBACK POTENTIOMETER. C/O FUNCTION CH ECKS ON SYSTEM OK. AIRCRAFT RELEASE FOR RETURN TO SERVICE. (TC NR 20071127010) 2 L 7 2 4F RT A53NM 2008022100045 20080221 00045 SW 2008 2 21 CA071127011 1 20071105 G 6320 2120400545 FITTING BELL BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE M/R GEARBOX CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 785 ABT301 (CAN) ON ROUTINE INSPECTION, A CRACK WAS NOTED IN THE LIFT LINK FITTING. TRANSMISSION WAS REMOVED AND SENT FOR REPAIR. T HE TSO FOR THE COMPLETE TRANSMISSION WAS AT 785.1 AND TT 19803.1. NO AVAILABLE INFORMATION FOR TT ON THE SUMP ASSY CASE. (TC NR 20071127011) 1 G 7 1 4U 4 U H1SW E17EA 2008022100046 20080221 00046 EU 2008 2 21 CA071128001 1 20071106 G 6130 PROP BRAKE AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE PROPELLER DAMAGED W E ENGINE SHUTDOWN J WARNING INDICATION TX TAXI/GRND HDL 1 CA 127023 (CAN) SHORTLY AFTER ENGINE START, CREW OBSERVED A PROP BRAKE WARNING LIGHT FOLLOWED BY A FIRE WARNING. ENGINE WAS SECURE D AND THE AIRCRAFT EVACUATED. INITIAL INVESTIGATION REVEALED A SEVERELY DAMAGED PROPELLER BRAKE ASSY. MFG WILL CONTINU E INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071128001) 2 H 7 2 4T 4 T RT E20NE 2008022100047 20080221 00047 NE 2008 2 21 CA071128002 2 20071108 G 7532 31J285704 TORQUE MOTOR CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE BLEED VALVE DEFECTIVE W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION DE DESCENT 1 CA DD0396 (CAN) DURING DESCENT, CREW NOTED ENGINE NOISE, FOLLOWED BY A REVERSION OF THE EEC TO MANUAL. ENGINE POWER LEVEL REMAINED AT FLIGHT IDLE. INVESTIGATION REVEALED A DEFECTIVE BLEED VALVE TORQUE MOTOR. (TC NR 20071128002) 2 L 7 2 4F 4 F RT A22CE E00059EN 2008022100048 20080221 00048 NE 2008 2 21 CA071128003 2 20071108 G 7200 HMU AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE ENGINE MALFUNCTIONED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CL CLIMB 1 CA 120178 (CAN) OPERATOR REPORTED UNCOMMANDED ENGINE SHUTDOWN AND EEC REVERSION DURING CLIMB. EEC WAS LATER REPLACED ON GROUND AND OPERATION WAS NORMAL. HMU WAS ALSO REPLACED AS A PRECAUTION. BOTH UNITS WILL BE RETURNED TO MFG FOR INVESTIGATION AND F OLLOW UP. (TC NR 20071128003) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008022100049 20080221 00049 NE 2008 2 21 CA071128004 2 20071112 G 7200 ENGINE BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE SEIZED W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 93211 (CAN) CREW REPORT FLASH OF LIGHT FOLLOWED BY SPARKS FROM ENGINE, AND ELECTED TO PERFORM AN INFLIGHT SHUTDOWN. AFTER LAND ING AND DURING INITIAL INVESTIGATION, THE PROPELLER COULD NOT BE ROTATED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR20071128004) 1 L 7 2 4T 4 T A24CE E4EA 2008030600204 20080306 00204 NM 2008 3 6 CA071128005 1 20071020 G 4920 TURBINE BLADES PWC BOEING 747 747400 13848AT NM APU ENGINE SEPARATED W K NONE O OTHER IN INSP/MAINT 1 CA 900663 (CAN) DURING AC B-CHECK, AIRFRAME APU COMPARTMENT IMPACT DAMAGE WAS OBSERVED CAUSED BY APPARENT TURBINE BLADE LIBERATION AND CASE FLANGE SEPARATION. THE APU HAD BEEN DECLARED INOPERATIVE BY THE OPERATOR SINCE OCTOBER 20 2007. MFG WILL CON TINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071128005) 2 L 7 4 4F RT A20WE 2008022100050 20080221 00050 EA 2008 2 21 CA071128006 2 20071103 G 7200 ENGINE DHAV DHC6 DHC6100 2802610 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL SURGES W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 40865 (CAN) DURING CRUISE, THE CREW OBSERVED ENGINE (SURGES) AND PERFORMED AN INFLIGHT SHUTDOWN. POST FLIGHT INSPECTION REVEAL ED A SEIZED PROPELLER SHAFT AND POWER TURBINE BLADE DISTRESS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF R OOT CAUSE ONCE ESTABLISHED (TC NR 20071128006) 1 H 7 2 3T 3 T RT A9EA E4EA 6 C P15EA 2008022100051 20080221 00051 WP 2008 2 21 CA071128007 1 20071024 G 5311 C04621 FRAME ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUSELAGE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 1314 (CAN) THE HELICOPTER WAS IN FOR A SCHEDULED 100 HOUR INSPECTION AND THE BROKEN FRAME WAS DISCOVERED BY THE AME. THE AIRC RAFT WAS GROUNDED AND A NEW PART WAS ORDERED AND INSTALLED. (TC NR 20071128007) 1 G 7 1 3O 3 O H11NM 1E4 2008022100052 20080221 00052 CE 2008 2 21 CA071128008 1 20071128 G 2435 BRUSHES BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL STARTER GEN FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 670 12527 (CAN) WHILE ON FINAL THE PILOT NOTICED THAT THE LT GENERATOR HAD FAILED. UPON LANDING, AN INSPECTION WAS CARRIED OUT ON THE GENERATOR. IT WAS NOTICED THAT THE BRUSHES WERE ALL BROKEN WHICH WOULD INDICATE AN INTERNAL FAILURE. (TC NR 20071128 008) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2008022100053 20080221 00053 NE 2008 2 21 CA071128009 2 20071116 G 7261 AS3209014 O-RING BRAERO 1000 BAE1251000A 1500104 EU PWA 305 PW305B 52128 NE NR 4 BEARING LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 305025 (CAN) CREW REPORTED OIL PRESSURE FLUCTUATIONS AND ILLUMINATION OF THE LOW OIL PRESSURE WARNING INDICATOR. THE ENGINE WAS SHUTDOWN AND THE FLIGHT DIVERTED. INVESTIGATION REVEALED DEFECTIVE O-RINGS ON THE NR4 BEARING TRANSFER TUBES (TC NR 2 0071128009) 2 L 7 2 4F 4 F RT A3EU E35NE 2008022100054 20080221 00054 CE 2008 2 21 CA071128010 1 20071116 G 5344 051218712 BULKHEAD CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL DOOR FRAME CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4714 (CAN) WHILE CARRYING OUT THE SEB 97-1 AFT DOORPOST INSPECTION, CRACKS WERE NOTED AT THE SUBJECT AREAS ON BOTH DOORPOSTS (IPC "CHANNEL-BULKHEAD"). SUBMITTER SUSPECTS THAT TAXIING OVER ROUGH SURFACES, OR POSSIBLY HARD OR CRABBED LANDINGS, CON TRIBUTES TO THE FLEXING OF THE BULKHEAD THAT RESULTS IN THE CRACKING. CRACKS ARE FOUND BY LOOKING WITH LIGHT AND MIRROR FORWARD NEAR THE AILERON CABLE PULLEY AT THE BOTTOM OF THE AFT DOORPOSTS. THE CRACK RADIATES FROM THE RELIEF CUTOUT WHE RE THE INSIDE FLANGE OF THE BULKHEAD CHANGES FROM VERTICAL TO HORIZONTAL. (TC NR 20071128010) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2008022100055 20080221 00055 NE 2008 2 21 CA071128011 2 20071031 G 7321 FUEL CONTROL BEECH MU300 400BEECH CE PWA JT15 JT15D5 52112 NE ENGINE INOPERATIVE W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA JG0033 (CAN) DURING CRUISE, ENGINE POWER GRADUALLY REDUCED FROM 102 PERCENT N1 INDICATION TO 74 PERCENT. NO RESPONSE TO THROTTL E LEVER MOVEMENT. FLIGHT WAS DIVERTED AND AIRCRAFT LANDED WITH BOTH ENGINES RUNNING. THE ENGINE FUEL CONTROL WAS REPLAC ED AND AIRCRAFT RETURNED TO SERVICE. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHE D. (TC NR 20071128011) 2 H 7 2 4F 4 F RT A16SW E25EA 2008032000004 20080320 00004 GL 2008 3 20 CA071128012 1 20071123 G 2432 GE50C BATTERY NAMER T6 HARVARDMK4 1922828 GL PWA R1340 R1340* 52016 NE HAMSTD 12D 12D40 NE MASTER SHORTED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CL CLIMB 1 CA 253 (CAN) AC SUFFERED ALMOST AN ENTIRE ELECTRICAL FAILURE DURING CLIMBOUT. AFTER SUBSEQUENT UNSCHEDULED LANDING, IT WAS DETE RMINED THAT THE BATTERY HAD ACQUIRED AN INTERNAL SHORT, WHICH DEPLETED THE GENERATOR OUTPUT AND CAUSED THE AVIONICS TO M ALFUNCTION. BATTERY REPLACED WITH A SERVICEABLE SPARE, AND AC ELECTRICAL SYS CONFIRMED OPERATIONAL. (TC NR 20071128012) 1 L 7 1 3R 3 R EXPA1L71 5E2 5 C P257 2008022100056 20080221 00056 NE 2008 2 21 CA071128013 2 20071109 G 7321 FUEL CONTROL CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE ENGINE FAILED W O OTHER R Y PARTIAL RPM/PWR LOSS ENGINE STOPPAGE NR NOT REPORTED 1 CA PC0509 (CAN) ENGINE POWER LOSS AND SUBSEQUENT INFLIGHT SHUTDOWN REPORTED. MFG IS ATTEMPTING TO RECOVER THE FUEL CONTROL UNIT F OR INVESTIGATION AND WILL ADVISE. (TC NR 20071128013) 1 H 7 1 3T 3 T A37CE E4EA 2008022100057 20080221 00057 NE 2008 2 21 CA071128014 2 20071123 G 7261 FILTER DHAV DHC8 DHC8103 1386005 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ENGINE OIL FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 120189 (CAN) DURING CLIMB, THE CREW OBSERVED ERRATIC OIL PRESSURE INDICATIONS AND ELECTED TO RETURN TO POINT OF DEPARTURE. THE ENGINE OIL PRESSURE CONTINUED TO REDUCE AND THE CREW PERFORMED AN INFLIGHT SHUTDOWN. INVESTIGATION REVEALED A FAULTY MAI N OIL PRESSURE FILTER WITH A REPORTED COLLAPSED INTERNAL ELEMENT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071128014) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008022100058 20080221 00058 NM 2008 2 21 CA071128015 1 20071126 G 3240 ZMV811A VALVE GULSTM 200 200 4500308 NM PWC PW306 PW306A 52165 NE PARKING BRAKE MALFUNCTIONED W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA 878 (CAN) PILOT REPORTED PARK BRAKE SET AND INDICATED ON EICAS. STARTED RT ENGINE WITH THE CHOCKS REMOVED, READY FOR DEPARTU RE. THE AIRCRAFT ROLL FWD AFTER THE ENGINE WAS STARTED. PILOT CHECKED THE INDICATION ON EICAS AND THE INDICATION WAS STI LL ON EICAS PARK BRAKE ON. PILOT HAD TO USE NORMAL BRAKE TO STOP AIRCRAFT. MAINT WAS CALLED AND TROUBLESHOOTING REVEAL ED THAT THE PARK BRAKE VALVE FAILED IN THE CLOSED POSITION. REPLACED PARK BRAKE VALVE AND C/O F/C ON PARK BRAKE SYS AND AC BRAKING SYS ALL FUNCTIONS OK. AC RELEASED FOR RETURN FOR SERVICE. (TC 20071128015) 2 L 7 2 4F 4 F RT A53NM E35NE 2008022100059 20080221 00059 WP 2008 2 21 CA071128017 1 20071126 G 6730 D2121 SERVO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 857 (CAN) WHILE CARRYING OUT A 100 HOUR INSP THE FWD LT HYDR SERVO WAS DISCOVERED LEAKING. SERVO WAS REPLACED, GROUND RUN AN D LEAK CHECK CARRIED OUT SERVICEABLE (TC NR 20071128017) 1 G 7 1 3O 3 O H11NM 1E4 2008022100060 20080221 00060 CE 2008 2 21 CA071128018 1 20071128 G 2510 505590401 CABLE AMSAFE 505590401 CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA SEAT BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 2 (CAN) COMPLIED WITH SB07-5 PILOT SECONDARY SEAT STOP INSTALLATION. THE AIRCRAFT LEFT OUR SHOP SERVICABLE AND IN COMPLIAN CE WITH THE SB. BROUGHT IT IN THE NEXT DAY TO DO UNSCHEDULED MAINT. LOOKING OVER THE JOB FOR A SECOND TIME FOUND THE T HREADED PLASTIC END OF THE CABLE BROKEN IN HALF AND THE PRODUCT NO LONGER FUNCTIONING CORRECTLY. BELIEVE A POSSIBILITY O F THE PART BRAKING TO BE COOL WEATHER AND THE FACT THAT THE PART IS PLASTIC. (TC NR 20071128018) 1 H 7 1 3O 3 O NT 3A12 E274 2008022100061 20080221 00061 WP 2008 2 21 CA071128019 1 20071006 G 7810 C16932 TAILPIPE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) PILOT REPORTED ODOR OF EXHAUST IN CABIN. INSPECTION OF EXHAUST COMPLIED WITH AND FOUND BURNED OUT AREA AT TAILPIPE JUNCTION. CF90-03R2 COMPLIED WITH 72.8 HRS PREVIOUS WITH NO DEFECTS FOUND AT THAT TIME. EXHAUST REPLACED. (TC NR 200711 28019) 1 G 7 1 3O 3 O H11NM 1E4 2008022100062 20080221 00062 2008 2 21 CA071129001 2 20071122 G 7261 AS121670 CLEVIS PIN PN3004073 DHAV DHC6 DHC6300 2802606 EA HARTZL HCB3T HCB3TN3 GL OIL TANK DRAIN MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 22 (CAN) THIS RT ENGINE S/NPCE-50013, WAS IDENTIFIED TO HAVE THE OIL TANK DRAIN PLUG P/N 3004073, MISSING THE LOCKING PIN P /N AS121670. THIS COULD HAD LEAD TO THE COMPLETE LOSS OF ENGINE OIL, RESULTING OF ENGINE SHUTDOWN, IF THE PLUG HAD LOOSE N AND FALLEN AWAY FROM THE ENGINE. (TC NR 20071129001) 1 H 7 2 3T RT A9EA 6 C P15EA 2008022100063 20080221 00063 CE 2008 2 21 CA071129002 1 20071122 G 5753 3516505030 BRACKET BEECH BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCE4N HCE4N3 NE FLAP BRACKET WORN W K NONE O OTHER IN INSP/MAINT 1 CA 7336 BB1610 (CAN) DURING PHASE 1 INSPECTION, LT FLAPS WERE REMOVED TO INSPECT SUPECTED AREA AS RT OB FLAP HAD FAILED IN THE SAME ARE A A FEW HOURS PRIOR AND WAS REPORTED UNDER A SEPARATE SDR. WHEN RT OB FLAP BRACKET FAILED, THE FLIGHT CONTROLS WERE AFFE CTED. THE CAUSE OF THE WEAR ON THE BRACKET IS FROM BEARING PN BC56985 WEARING OUT CHAFING INTO BRACKET. (TC NR 200711290 02) 1 L 7 2 4T 4 T A24CE E4EA 5 C P10NE 2008022100064 20080221 00064 NM 2008 2 21 CA071130001 1 20071110 G 3350 32145410 POWER SUPPLY AIRBUS A319 A319114 3930350 NM CFMINT CFM56 CFM565A3 NE EMERGENCY LIGHTS FAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) IN PROCESS OF DOING AB EMERGENCY LIGHTING TEST, AFTER THE COMPLETION OF THE IN-FLIGHT ENTERTAINMENT MAKEOVER, IT W AS DISCOVERED THAT THE AFT EMERGENCY LIGHTING WAS NOT TESTING. A STRONG BURNING SMELL WAS DETECTED AFTER OPENING A PANEL TO ACCESS THE AFT EMERGENCY POWER SUPPLY UNIT. ONE CORNER OF THE BATTERY UNIT WAS MELTED THROUGH THE CASE AND THE POSIT IVE TERMINAL CONNECTION AND CIRCUIT BOARD ON THE ESPU HAD SIGNS OF SEVERE OVERHEATING. THE ESPU AND BATTERY WERE SENT TO THE SHOP FOR EVALUATION. THE SUSPECTED CAUSE WAS LIQUID INGESTION BUT COULD NOT BE SUBSTANTIATED. (TC NR 20071130001) 2 L 7 2 4F 4 F RT A28NM E29NE 2008022100065 20080221 00065 GL 2008 2 21 CA071130002 1 20071129 G 2422 GC53100043 INVERTER BOMBDR BD100 BD1001A10 1390044 GL RROYCE BR700 BR700710A220 09500 NE OVERHEATED W K NONE O OTHER IN INSP/MAINT 1 CA 257 (CAN) DURING MAINT AND AFTER THE AC HAD BEEN POWERED WITH EXTERNAL GROUND POWER FOR APPROX 4 HOURS, THE CREW NOTICED A B URNING SMELL AROUND THE AC. NO ABNORMAL INDICATIONS WERE DISPLAYED ON THE CREW ALERTING SYS (CAS) MESSAGE AND THE ELECTR ICAL MGMT SYS CONTROL AND DISPLAY UNITS (EMSCDU). THE POWER WAS REMOVED FROM THE AC. THE INVESTIGATION INDICATES THAT T HE INTEGRAL LIGHTING INVERTER A179 SHOWN SIGN OF INTERNAL OVERHEATING. THIS RESULTED IN DEPOSITING SOOT TO THE ADJACENT INTEGRAL LIGHTING POWER SUPPLY A176 AND WIRES. BOTH UNITS WERE REMOVED, REPLACE AND SENT TO THE VENDOR TO IDENTIFY THE R OOT CAUSE OF THE FAILURE. THE AC IS BACK IN SERVICE. (TC NR 20071130002) 2 L 7 2 4F 4 F RT T00005NY E00061EN 2008022100066 20080221 00066 CE 2008 2 21 CA071130003 1 20071128 G 5610 10138402522 WINDSHIELD BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA (CAN) COPILOTS WINDSHIELD INNER PANE SHATTERED DURING NORMAL CRUISE FLIGHT. WINDSHIELD REPLACED UPON RETURN TO MAINTENAN CE BASE. (TC NR 20071130003) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2008022100067 20080221 00067 EU 2008 2 21 CA071130004 1 20071128 G 2497 WIRE HARNESS AEROSP ATR42 ATR42300 8680920 EU PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF5 NE CONTROL PANEL SHORTED W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) STANDBY HORIZON CB POPPED. MODERATED ELECTRICAL SMELL/SMOKE. WIRE BUNDLE UNDER COPILOTS SIDE PANEL ASSY (PNS25110 49800300) FOUND CHAFED AND SHORTING TO PANEL. (PANEL IS BELIEVED TO BE MADE OF CARBON FIBER WHICH WILL CONDUCT ELECTRICI TY). PANEL ASSY INSPECTED WITH BURNED SPOTS AT WIRE BUNDLE LOCATION AS WELL AS AFT EDGE WHICH WAS CHAFING ON (2) SCREWS. DAMAGED WIRING BUNDLE REPAIRED. PANEL REPAIRED AND REINSTALLED. (TC NR 20071130004) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008022100068 20080221 00068 WP 2008 2 21 CA071130006 1 20071123 G 2435 14924HTH STARTER ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 155 (CAN) A PILOT ATTEMPTING A START THE AC AND FAILED TO TURN OVER. FURTHER INVESTIAGTION REVEALED STARTER WAS DEFECTIVE. S TARTER WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20071130006) 1 G 7 1 3O 3 O H11NM 1E4 2008022100069 20080221 00069 NM 2008 2 21 CA071130007 1 20071130 G 5315 146A75031 FLOORBEAM BOEING 737 737790 13844CN NM CARGO BAY CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR SUPPORT RAIL AT BS 767+6 LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA, LEVEL 2 CORROSION. (TC N R 20071130007) 2 L 7 2 4F RT A16WE 2008013100275 20080131 00275 NM 2008 1 31 CA071130008 1 20071130 G 5315 146A75035 FLOORBEAM BOEING 737 737790 13844CN NM AFT CARGO PIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOORBEAM RAIL CORRODED AT BS 767+6 LBL 8 AND REPAIRED IAW CUSTOMER EA LEVEL 2 CORROSION (TC NR 2007 1130008) 2 L 7 2 4F RT A16WE 2008013100276 20080131 00276 NM 2008 1 31 CA071130009 1 20071130 G 5315 147A55047 FLOORBEAM BOEING 737 737790 13844CN NM BS 947 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CABIN FLOOR SUPPORT BEAM AT BS 947 LBL 53 CORRODED AND REPAIRED IAW CUSTOMER EA LEVEL 2 CORROSION (TC NR 2007 1130009) 2 L 7 2 4F RT A16WE 2008013100277 20080131 00277 NM 2008 1 31 CA071130010 1 20071130 G 5730 112A410210 SKIN BOEING 737 737790 13844CN NM RWS 240 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT WING LWR SKIN AT AFT EDGE CHAFFING DAMAGE FROM CONTACT WITH NACELLE STRUT AFT FAIRING INBD BLADE SEAL AT APPROX . WS 240 REPAIRED IAW CUSTOMER EA (TC NR 20071130010) 2 L 7 2 4F RT A16WE 2008013100278 20080131 00278 NM 2008 1 31 CA071130011 1 20071130 G 5730 112A41029 SKIN BOEING 737 737790 13844CN NM LWS 260 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT WING LWR SKIN CHAFFING DAMAGE FOUND FROM CONTACT WITH NACELLE STRUT AFT FAIRING OB BLADE SEAL AT APPROX WS 260 REPAIRED IAW CUSTOMER EA (TC NR 20071130011) 2 L 7 2 4F RT A16WE 2008013100279 20080131 00279 EU 2008 1 31 CA071130012 1 20071130 G 6321 C762C1004103 BRAKE UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE ROTOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 1730 (CAN) MECHANICAL DAMAGE TO ROTOR BRAKE GRID ASSEMBLY, DUE TO IMPROPER OPERATION. TRIGGER WAS NOT DEPRESSED PRIOR TO ENG AGING ROTOR BRAKE HANDLE CAUSING MECHANICAL DAMAGE TO GRID ASSEMBLY. NEW GRID ASSEMBLY INSTALLED (TC NR 20071130012) 1 G 7 2 3U 3 U NC R0001RD E34NE 2008013100280 20080131 00280 NM 2008 1 31 CA071130013 1 20071130 G 5730 112A410210 SKIN BOEING 737 737790 13844CN NM RWS 260 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT WING LWR SKIN CHAFFING DAMAGE FROM CONTACT WITH NACELLE STRUT AFT FAIRING OB BLADE SEAL AT APPROX WS 260 REPAIR ED IAW EA.(TC NR 20071130013) 2 L 7 2 4F RT A16WE 2008020400128 20080204 00128 2008 2 4 CA071130014 1 20071126 G 3411 3001T60P03 SEAL GE CT58 CT581401 30011 NE DEBONDED W K NONE O OTHER IN INSP/MAINT 1 CA 295291 (CAN) STATIC DISCHARGE SEAL DEBONDED WHILE ENGINE (SN 295-291) WAS BEING RUN. OUR INTERNAL SQID REPORT NR 07-06724 REFER S. (TC NR 20071130014) 4 U 1E3 2008020400127 20080204 00127 2008 2 4 CA071130015 4 20071130 G 3197 WIRE BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL BURNED W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 393 (CAN) AFTER STARTING ENGINE FOR GROUND RUN, AVIONICS SWITCH WAS SELECTED ON. IMMEDIATELY SMOKE STARTED COMING FROM RT CB PANEL. ENGINES WERE IMMEDIATELY SHUTDOWN AND POWER WAS REMOVED FROM A/C. INVESTIGATION REVEALED THAT A FACE PLATE MOUNT ING SCREW HAD SHORTED TO AN AVIONICS FEEDER WIRE P72A10 DUE TO POOR ROUTING OF THE WIRE AT MFG. (2) 10GAUGE WIRES ARE A TTACHED TO ONE TERMINAL OF CB120 (TCAS), ONE COMING FROM CB92 (AVIONICS POWER LT GEN BUS) WHICH IS A 30AMP BREAKER. ONE OF THE WIRES WAS MOUNTED ALONG THE BACK OF THE PANEL AND HAD BEEN IN HARD CONTACT WITH THE AFT MIDDLE FACE PLATE MOUNTIN G SCREW. WIRE REPLACED IAW AC43.13-1B PARA 11-98, ROUTED TO AVIOD CONTACT WITH MOUNTING HARDWARE. (TC NR 20071130015) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2008020400126 20080204 00126 CE 2008 2 4 CA071202001 1 20071201 G 5312 BULKHEAD CESSNA 206 U206G 2073356 CE CONT O550 IO550F 17042 SO HARTZL HCJ3Y PHCJ3YF1 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING COMPLIANCE WITH SEB 93-5 INSP OF LOWER DOOR POST, THE BULKHEAD WAS FOUND CRACKED ON THE LT SIDE, UPPER PART OF LOWER BULKHEAD, JUST IB OF THE WING STRUT ATTACHMENT FITTING. RT SIDE WAS TO BE FREE OF CRACKS AT THIS TIME. MFG SER VICE KIT SK260-42C WAS INCORPORATED TO THE LT LOWER DOOR POST. AC RETURNED TO SERVICE. THIS INSP IS ALSO CALLED UP IN T HE CONTINUED AIRWORTHINESS PROGRAM INSP NR 53-40-01 INITIAL INSPECTION TO BE DONE AT 12000 HOURS AND REPEAT INSPECTIONS EACH 3000 HOURS THERE AFTER. SEB 95-3R1 CALL FOR THIS INSPECTION AT 4000 HOURS TT AND REPEAT INSPECTIONS EACH 1000 HOUR S THERE AFTER. NOT ALL OPERATORS OF THESE AC ARE IN COMPLIANCE WITH THE C.A.P MANUALS. (TC NR 20071202001) 1 H 7 1 3O 3 O A4CE E3SO 5 C P36EA 2008013100281 20080131 00281 NM 2008 1 31 CA071202002 1 20071201 G 5730 112A4101209 SKIN BOEING 737 737990 NM RWS 260 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 19198 (CAN) A/C UNDERGOING C-CHECK,HEAVY MAINTENANCE. RT WING, LOWER SKIN PANEL CHAFING DAMAGE FOUND FROM CONTACT WITH NACELLE STRUT AFT FAIRING OB BLADE SEAL AT APPROX WS 260. REPAIRED IAW EA 5720-01345. (TC NR 20071202002) 2 L 7 4 4F RT A16WE 2008013100282 20080131 00282 NM 2008 1 31 CA071202003 1 20071201 G 5730 112A4101209 SKIN BOEING 737 737990 NM LWS 240 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 19198 (CAN) A/C UNDERGOING C-CHECK HEAVY MAINTENANCE. LT WING LOWER SKIN PANEL CHAFING DAMAGE FOUND DUE TO CONTACT WITH NACELL E STRUT AFT FAIRING IB BLADE SEAL AT APPROX WS 240. REPAIRED IAW EA 5720-01345. (TC NR 20071202003) 2 L 7 4 4F RT A16WE 2008022100070 20080221 00070 NM 2008 2 21 CA071202004 1 20071201 G 5730 112A4101209 SKIN PANEL BOEING 737 737990 NM WS 260 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 19198 (CAN) A/C UNDERGOING C-CHECK HEAVY MAINT. LT WING LOWER SKIN PANEL CHAFING DAMAGE FOUND DUE TO CONTACT WITH NACELLE STRU T AFT FAIRING OB BLADE SEAL AT APPROX WS 260. REPAIRED IAW EA 5720-01346. (TC NR 20071202004) 2 L 7 4 4F RT A16WE 2008022100071 20080221 00071 SO 2008 2 21 CA071203001 1 20071202 G 3710 VANE RAPCO 441CC7 PIPER PA31 PA31310 7103103 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL AIR PUMP BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 771 125777 (CAN) DURING A PRE-MAINTENANCE GROUND RUN, IT WAS NOTED THAT THE RT AIR PUMP WAS INDICATING INOPERATIVE DURING INSPECTIO N. THE DRIVESHAFT WAS FOUND TO BE SHEARED DUE TO THE CARBON VANES BREAKING AND JAMMING THE PUMP. (TC NR 20071203001) 1 L 7 1 3O 3 O RT A20SO E14EA 5 C P33EA 2008022500010 20080225 00010 SO 2008 2 25 CA071203002 1 20071202 G 5340 STRUCTURE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL NLG WW CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 17329 17329 (CAN) DURING AN EVENT 1 INSP ON THE AC, ENGINEER NOTICED WHAT HE THOUGHT THERE WAS A CRACK ON THE EXTRUSION (LOCATED ABO VE THE NLG WHEEL WELL, JUST AFT OF HYD POWERPACK), TO WHICH THE NOSE LANDING GEAR RETRACTION ACTUATOR ATTACHES TO. AFTER PERFORMING A LIQUID PENETRANT INSP, THE PRESENCE OF A CRACK WAS CONFIRMED. THE EXTRUSION WAS REMOVED FROM THE AIRCRAFT, AT THIS TIME IT WAS ALSO NOTED THAT THE ATTACH POINT (BOLT HOLE) WAS ALSO CRACKED. A NEW EXTRUSION IS BEING INSTALLED. THIS EXTRUSION HAS BEEN INSTALLED SINCE THE AIRFRAME WAS MFG (17328.9 TSN). (TC NR 20071203002) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008022500011 20080225 00011 NE 2008 2 25 CA071203003 2 20071203 G 7314 D7341 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYSTEM FAILED W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA (CAN) THE AUXILIARY FUEL PUMP LIGHT CAME, AND WOULD NOT EXTINQUISH. TROUBLESHOOTING REVEALED THAT THE PUMP WAS NO LONGER PUMPING FUEL. THE PUMP WAS CHANGED, LEAK, AND FUNCTION CHECKED SERVICEABLE. (TC 20071203003) 1 G 7 1 3O 3 O H11NM 1E4 2008022500012 20080225 00012 SW 2008 2 25 CA071203004 1 20071101 G 5514 400928 SPRING AIRTRC AT802 AT802A 0390308 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MA3 GL TAIL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 858 (CAN) CRACK FOUND ON TAIL SPRING BEGINNING FROM FWD ATTACH HOLE EXTENDING ALONG SIDE OF SPRING. CRACK THEN EXTENDS TO TO P OF SPRING. LENGTH OF CRACK TOTALS APPROX 6 INCHES. (TC NR 20071203004) 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2008022500013 20080225 00013 EU 2008 2 25 CA071203005 1 20071203 G 6720 11731822A PITCH LINK BOLKMS 117 BK117B2 5626013 EU LYC LTS101 LTS101750B1 41560 NE TAIL ROTOR MISMARKED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) TAIL ROTOR PITCH LINKS P/N 117.31822A. REPLACED ON 31 OCT/2007, DUE TO BEARING WEAR. ON DEC 3/2007 THE LINKS WERE INSPECTED PRIOR TO BEARING REPLACEMENT AND WERE FOUND TO HAVE AN INCORRECT P/N STAMPED ON THEM. THE NR WAS MISSING THE NR 1. THE STAMP INDICATED P/N 117.3822A. THIS NUMBER IS NOT IN THE IPC MANUAL. THE LINKS ARE THEREFORE SUSPECT. (TC NR 2 0071203005) 1 G 7 2 3U 3 U NC H13EU E5NE10 2008022500014 20080225 00014 SW 2008 2 25 CA071203006 1 20071203 G 7120 205060105001 MOUNT BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 7609 (CAN) LT ENGINE TRIPOD AFT TUBING MOUNT FOUND CRACKED DURING 100 HRS INSPECTION JUST BELOW ENGINE MOUNTING PLATE AFT TUB E JUNCTION. NOTE: THIS MOUNT WAS MODIFIED IAW STC SH99-11, DART ADJUSTABLE MOUNT. (TC NR 20071203006) 1 G 7 1 4U 4 U H1SW E17EA 2008031900166 20080319 00166 NE 2008 3 19 CA071203007 2 20071201 G 7321 01645487201 FCU SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE ENGINE LEAKING W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA (CAN) THE PILOT WAS DESCENDING WHEN ALL OF A SUDDEN THE CABIN AREA FILLED UP WITH A MIST ORIGINATING FROM THE THE DEFROS T VENTS. THE MIST WAS SO STRONG THAT THE PILOT HELD HIS BREATH AND OPENED THE FUSELAGE DOOR SO THE MIST COULD EXIT THE A C. AFTER A FEW SECONDS THE MIST DISSIPATED SO THE PILOT COULD BREATH NORMALLY. THE PILOT LANDED AT STAGING SITE AND THE AC WAS GROUNDED. THE ENGINEER WAS CALLED TO TROUBLESHOOT THE PROBLEM. WE BELIEVE IT IS THE FUEL CONTROL THAT CAUSED TH IS FUEL MIST IN THE CABIN. THE FUEL CONTROL HAS ABOUT 1400 HOURS SINCE LAST OVERHAUL THE TECH. (3000 HOUR O/H BY MFG) (T C NR 20071203007) 1 G 7 1 3U 3 U H9EU E19EU 2008022500015 20080225 00015 SW 2008 2 25 CA071203008 1 20071126 G 3210 BUTTON FRCHLD SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE MLG SHORT W K NONE O OTHER IN INSP/MAINT 1 CA AC714 (CAN) UPON DISASSEMBLY OF A MLG FOR OVERHAUL AND SERVICING IT WAS NOTICED THE CYLINDER PISTON TEFLON BUTTONS WERE UNDER FLUSH WITH THE PISTON. THE TEFLON BUTTONS AND PINS ALLOW THE PISTON TO SLIDE INSIDE THE CYLINDER WITHOUT SCORING AND WIT HOUT ALLOWING FLUID BLOWBY. UPON INSPECTION OF THE PISTON IT WAS NOTICED THE HOLES WERE TOO DEEP FOR THE TEFLON BUTTONS AND PINS AND ALLOWED FOR SCORING OF THE CYLINDER WALLS. WHEN COMPARED TO A KNOWN CERTIFIED PART, IT DID NOT MEET THE SAM E MEASUREMENTS. ACTUAL ENGINEERING DRAWINGS WITH SPECIFIC MEASURMENTS WERE NOT AVAILABLE TO CONFIRM PISTON MEASURMENTS. LIKELY THIS PART IS SUBSTANDARD BUT THE POSSIBILITY OF BEING AN UNAPPROVED PART EXISTS. TOTAL TIME ON THE PISTON IS UNKN 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 2008022500016 20080225 00016 GL 2008 2 25 CA071204001 2 20071129 G 7323 23076061 GOVERNOR BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE INOPERATIVE W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 456 (CAN) WHILE CARRYING OUT A START, THE ENGINE WAS SLOW TO REACH IDLE, WITH THE N2 INDICATOR STICKING ON START. ONCE DESNA GGED IT WAS DISCOVERED THE GOVENOR WAS THE CAUSE. 1 G 7 1 3U 3 U H2SW E4CE 2008022500017 20080225 00017 SW 2008 2 25 CA071204002 1 20071101 G 2450 PDLM120 CIRCUIT BREAKER AIRTRC AT802 AT802A 0390308 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MA3 GL CB BODY CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5676 5676 (CAN) CB CRACKED. (TC NR 20071204002) 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2008022500018 20080225 00018 SW 2008 2 25 CA071204003 1 20071101 G 5320 NUT EISRVAC AIRTRC AT802 AT802A 0390308 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MA3 GL VACUUM SWITCH BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 5676 5676 (CAN) THE VACUUM SWITCH WAS SUPPLIED BY MFG. PLASTIC ADJUSTING NUT SPLIT, PREVENTING THE VACUUM SWITCH FROM INDICATING A LOW FUEL PRESSURE WARNING. (TC NR 20071204003) 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2008022500019 20080225 00019 NM 2008 2 25 CA071204004 1 20071204 G 3230 656021132 ACCESSORY UNIT BOEING 727 727247 138408F NM PWA JT8 JT8D15 52051 NE LANDING GEAR UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 9451 7879 (CAN) SHORTLY AFTER TAKEOFF WHEN GEAR WAS BEING RETRACTED, CREW NOTICED THAT THE RT MAIN GEAR RED LIGHT WAS STILL ILLUMI NATED. CREW CYCLED THE LANDING GEAR (3) TIMES WITH THE SAME RESULTS. THE CREW ADVISED THAT AIR NOISE COULD BE HEARD. GEA R WAS SELECTED DOWN WITH (3) GREEN AND RETURNED TO THE RAMP. EXTENSIVE TROUBLESHOOTING AND GEAR SWINGS REVEALED LANDING GEAR ASSY UNIT IS AT FAULT. SERVICEABLE UNIT INSTALLED AND GEAR FUNCTION TESTED SERVICEABLE. THE AC HAS FLOWN 4 LEGS SIN CE THE REPAIR WITH NO FURTHER PROBLEMS. 2 L 7 3 4F 4 F A3WE E2EA 2008022500020 20080225 00020 NE 2008 2 25 CA071204006 2 20071202 G 7314 LW15473 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYSTEM FAILED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA 1013 (CAN) THE AIRCRAFT WAS FLOWN FOR AN HOUR AND THEN SHUTDOWN TO WAIT FOR CUSTOMERS. THE AC WAS RE-STARTED A HALF HOUR LATE R AND THE PILOT TRIED TO LIFT OFF, WHEN THE ENGINE LOST PARTIAL POWER AND THE MANIFOLD PRESSURE ROSE ABNORMALLY. THE PO WER SETTINGS CAME BACK TO NORMAL WHEN THE COLLECTIVE WAS LOWERED BUT WOULD DETERIORATE EVERY TIME THE COLLECTIVE WAS RAI SED. AFTER SHUTTING DOWN THE ENGINE, FUEL WAS SEEN FLOWING OUT OF THE ENGINE DRIVEN FUEL PUMP DRAIN. THE OAT WAS -30 CEL CIUS AND THE ENGINE WAS PRE-HEATED. (TC NR 20071204006) 1 G 7 1 3O 3 O H11NM 1E4 2008022500021 20080225 00021 SW 2008 2 25 CA071204007 1 20071204 G 6410 212010710001 BALANCE WEIGHT BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA T/R BLADE INCORRECT W K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 CA (CAN) INCORRECT WEIGHT FOR PN CAUSED IMBALANCE IN TAIL ROTOR WHICH COULD NOT BE CORRECTED WITHIN BALANCE LIMITS. (TC NR 20071204007) 1 G 7 1 4U 4 U H4SW E22EA 2008022500022 20080225 00022 NE 2008 2 25 CA071204008 1 20071129 G 6520 BEARING S613566300 SKRSKY S61 S61N 8142104 NE GE CT58 CT581402 30011 NE GEARBOX OVERHEATED W C ABORTED TAKEOFF B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 14 A151024 (CAN) ON FIRST FLIGHT OF THE DAY, AIRCRAFT WAS GROUND TAXIING TO TAKE OFF AREA WHEN GROUND CREW NOTICED SMOKE FROM TAIL ROTOR DRIVE INTERMEDIATE GEAR BOX AREA. AIRCRAFT WAS SHUT DOWN, AND INSPECTION REVEALED OVERHEATING IN THE INPUT BEARING AREA. SIKORSKY AND OVERHAUL SHOPS ADVISED, AND ARE INVESTIGATING CAUSE. THIS IS A REOCCURANCE OF PREVIOUS FAILURE. IN B OTH CASES GEAR BOX OIL LEVEL WAS FOUND TO BE SATISFACTORY. (TC# 20071204008) 2 G 7 2 4U 4 U 1H15 1E3 2008022500023 20080225 00023 GL 2008 2 25 CA071204009 1 20071130 G 5551 C2TP160A BRACKET DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HARTZL HCB3R HCB3R304 GL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE COMPLETING THE REQUIREMENTS OF CF 91-42R1 IAW SB 2/47 REV (E), THE RT FWD STABILIZER ATTACH BRACKET WAS FOUN D TO BE CRACKED. THE CRACK EXTENDED FROM THE TOP OF THE IB EAR OF THE BRACKET, THROUGH THE LOCKWIRE HOLE AND CONTINUED A PPROX 75 PERCENT OF THE WAY DOWN THE BRACKET. THIS AIRCRAFT OPERATES EXCLUSIVELY ON FLOATS IN A CORROSIVE ENVIRONMENT. 1 H 7 1 3R 3 R RC A806 5E1 5 C P28EA 2008022500024 20080225 00024 NE 2008 2 25 CA071204010 2 20071123 G 7261 1111065 OIL FILTER DHAV DHC8 DHC8103 1386005 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ENGINE RESTRICTED W E ENGINE SHUTDOWN F FLT CONT AFFECTED CR CRUISE 1 CA 600 (CAN) INFLIGHT SHUTDOWN AS A PRECAUTION, OIL PRESSURE INDICATION FLUCTUATING IN FLIGHT. OIL FILTER APPEARED CLEAN BUT W AS RESTRICTING FLOW AS TO WHERE IT WAS CAUSING OIL BYPASS IN THE FILTER HOUSING, WHICH CAUSED THE ERRONEOUS INDICATIONS. (TC NR 20071204010) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008022500025 20080225 00025 GL 2008 2 25 CA071204011 1 20071123 G 5343 ATTACH FITTING TCRAFT BC BC12D 8850316 GL CONT A65 A658 17003 SO UNIVAC 72 72A GL MLG BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE INSTALLING NEW STRUTS IAW APPLICABLE STC, THE LT REAR ATTACH FITTING SEPERATED (BROKE IN HALF) AS VERY SLIGH T DOWNWARD PRESSURE WAS APPLIED TO THE LIFT STRUT. INSPECTION OF THE FAILED PART SHOWED A PRE EXISTING CRACK UNDER THE LOCKNUT. (TC NR 20071204011) 1 H 7 1 3O 3 O A696 E205 5 N 802 2008022500026 20080225 00026 EA 2008 2 25 CA071205001 1 20071205 G 2820 215T640836 FITTING CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE TANK DRAIN BROKEN W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) MAJOR FUEL LEAK BY THE BROKEN NR 3 COLLECTOR TANK DRAIN FITTING, SOLENOID SIDE. PIPE DRAIN 215T64083-6 REPLACED. (TC NR 20071205001) 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2008022500027 20080225 00027 EU 2008 2 25 CA071205002 1 20071203 G 5610 3501262334 WINDSHIELD SNIAS 350 AS350* EU TMECA ARRIEL ARRIEL1B 6OO30 NE COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2295 (CAN) DURING PREFILGHT INSP, CRACKS WERE DISCOVERED ON LT WINDSHIELD TECH TOOLS PLASTICS P/N 350126231 AND RT WINDSHIELD TECH TOOLS PLASTICS P/N 3501-2623-1. BOTH LT AND RT WINDSHIELDS WERE CRACKED 4.5 TO 5 INCHES LONG ON BOTTOM EDGE. THE A IRCRAFT HAND FLOWN THE PREVIOUS DAY IN TEMPERATURES OF -30 DEGREES C AND HAD BEEN HANGERED OVERNIGHT. (TC NR 20071205002 ) 1 G 7 1 3U 3 U H9EU E19EU 2008022500028 20080225 00028 EA 2008 2 25 CA071205003 2 20071205 G 7322 62226 STOP PIN AMTR ELITE ELITE532 13027GG GL LYC O360 O360A2F 41514 EA SNSNCH 76E 76EM8S5 EA AIR METERING MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 105 (CAN) AN INTERMITTENT, MINOR ROUGHNESS IN THE ENGINE WAS OBSERVED TO TAKE PLACE JUST BEFORE LANDING. NOTHING OUT OF THE ORDINARY WAS OBSERVED DURING LANDING, TAXI AND SHUTDOWN (I.E. NO ABNORMAL CHT, EGT OR RPM). INSP OF ENGINE REVEALED NOTH ING, EXTERNALLY. CARB WAS REMOVED FROM ENGINE AND SENT IN TO INSTALL AN OPTIONAL ENRICHMENT KIT TO CONVERT THE P/N 10- 3878 CARB TO A P/N 10-3878M FOR IMPROVED PERFORMANCE AND BETTER COLD WEATHER OPS. WHEN DISASSEMBLED, IT WAS DISCOVERED T HAT THE CARB AIR METERING STOP PIN HAD VIBRATED LOOSE AND HAD FALLEN OUT. ALLOWING SPRING LOADED AIRBLEED NEEDLE TO POP OUT AND FALL INSIDE CARB, JAMMING THE THROTTLE. PILOT DID NOT DETECT ANY JAMMING OF THROTTLE OR MALFUNCTION OF MECHANICA 1 G 7 1 3I 3 O NT EXPA1G71 E286 5 N P4EA 2008022500031 20080225 00031 NE 2008 2 25 CA071205004 2 20071128 G 7300 UNKNOWN CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE UNKNOWN W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB, THE EEC REVERTED TO MANUAL WITH LOSS OF THRUST LEVER, RESPONSE NOTED. THRUST DECREASED INITIALLY TO 54 PERCENT AND LATER TO 25 PERCENT. FLIGHT WAS DIVERTED AND AN UNSCHEDULED LANDING PERFORMED. AFTER TROUBLESHOOTING, AC WAS CLEARED TO RETURN TO BASE. ADDITIONAL TROUBLESHOOTING FOCUSED ON FUEL SYS COMPONENTS. AC HAS RETURNED TO SERVICE AF TER REPLACEMENT OF SUSPECT COMPONENTS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLIS HED (TC NR 20071205004) 2 L 7 2 4F 4 F RT A22CE E00059EN 2008022500035 20080225 00035 EU 2008 2 25 CA071205005 1 20071202 G 7110 COWLING UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206B 0 NE ENGINE BURNED W E ENGINE SHUTDOWN A FLAME/FIRE TX TAXI/GRND HDL 1 CA (CAN) DURING START, AN ENGINE COMPARTMENT FIRE WAS NOTED. DAMAGE IS EVIDENT TO COWLING, ENGINE AND ENGINE COMPARTMENT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071205005) 1 G 7 2 3U 3 U O H88EU E42NE 2008022500037 20080225 00037 NE 2008 2 25 CA071205006 2 20071130 G 7261 ENGINE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE OIL CONSUMPTION W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA AE0084 (CAN) OIL MIST WAS NOTED IN THE CABIN AFTER LANDING. INITIAL TROUBLESHOOTING REVEALED THAT 2 LITRES OF OIL WERE CONSUMED DURING THE PREVIOUS FLIGHT. ENGINE WAS REMOVED FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071205006) 2 H 7 2 4T 4 T RT A13NM E20NE 2008022500039 20080225 00039 EA 2008 2 25 CA071205007 2 20071130 G 7200 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T6 52045 EA MAKING METAL W E A ENGINE SHUTDOWN UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA 72459 (CAN) CREW HEARD A METALLIC BANG FROM THE ENGINE AREA, FOLLOWED BY CAUTION LIGHTS. ENGINE WAS SHUTDOWN AND AIRCRAFT LAND ED. SUBSEQUENT INITIAL INSPECTION REVEALED DEBRIS ON THE OIL FILTER. ENGINE IS BEING REMOVED FOR INVESTIGATION. P&WC WIL L CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071205007) 1 G 7 2 4U 4 U H4SW E22EA 2008022500041 20080225 00041 NE 2008 2 25 CA071205008 2 20071128 G 7314 PUMP AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE FUEL SYSTEM MALFUNCTIONED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, THE CREW REPORTED THAT ENGINE TORQUE WAS (UNSTABLE). POST FLIGHT INVESTIGATION REVEALED THAT ENGI NE POWER WAS LIMITED TO 86 PERCENT VS. 90 PERCENT TARGET. FUEL PUMP AND FUEL CONTROL WERE REPLACED. FUEL PUMP IS SUSPECT AND WILL BE SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHE D (TC NR 20071205008) 2 H 7 2 4T 4 T RT E20NE 2008022500068 20080225 00068 EA 2008 2 25 CA071205009 2 20071130 G 7200 ENGINE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA FOD W O OTHER R X J PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA FA0279 (CAN) ENGINE (FLAMED OUT) AND AUTO RECOVERED WITHIN TEN SECONDS TIME FRAME WITH NO CREW INTERVENTION. FADEC DATA INDICA TES POSSIBLE WATER/ICE INGESTION. (TC NR 20071205009) 2 H 7 2 4T 4 T RT A13NM E00062EN 2008022500069 20080225 00069 EU 2008 2 25 CA071205010 1 20071126 G 2160 342B030000AMDTA THERMOSTAT AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE TEMP CONTROL FAILED W B A EMER. DESCENT UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 5970 (CAN) WHILE IN CRUISE AT FL 390, THE CREW HAD A BLEED AIR SUPPLY NR 2 FAILURE, AND DURING A DESCENT WHILE REFERING TO TH E QRH, ALSO HAD NR 1 BLEED FAIL. CREW LOST BOTH PACKS, AND INITIATED EMERGENCY DESCENT TO 10,000 FT. FLT DIVERTED TO NEA RBY AIRPORT. TEMP CONTROL THERMOSTAT (TCT) AND FAN AIR VALVE WERE CHANGED. IT IS TO BE NOTED THAT THE TCT IS POST MOD T O ENABLE IT TO OPERATE UNDER SINGLE BLEED CONDITIONS. (TC NR 20071205010) 2 L 7 2 4F 4 F RT A28NM E29NE 2008022500071 20080225 00071 CE 2008 2 25 CA071206001 1 20071205 G 3230 508103237 TORQUE LINK BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA MCAULY 4HFR34 4HFR34C762 NE MLG CRACKED W L ABORTED APPROACH O OTHER IN INSP/MAINT 1 CA (CAN) DURING A SPECIAL LPI INSPECTION OF THE MLG TORQUE LINKS DUE TO THE FAILURE OF A LINK ON ANOTHER AIRCRAFT (SDR 2007 1024010 AND 20071122002), 3 OF THE 4 LINKS WERE FOUND CRACKED. THE LINKS FROM 3 ADDITIONAL AIRCRAFT WERE REPLACED IN OR DER TO COMPLETE THE LPI OFF AIRCRAFT, THE LPI WAS COMPLETED AND 4 OF THE 12 LINKS WERE FOUND TO HAVE VERY SMALL CRACKS, ALL THE CRACKS ARE IN THE SAME RADIUS AREA, (TC# 20071206001) 1 L 7 2 3T 4 T A14CE E4EA 6 C 3PNE 2008022500073 20080225 00073 CE 2008 2 25 CA071206003 1 20071203 G 3510 1183840093 CONTROL CABLE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE OXYGEN MASK STIFF W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 10075 (CAN) WHILE PERFORMING AN INTERIOR PREFLIGHT CHECK THE F/O PULLED THE CONTROL KNOB FOR THE OXYGEN SYS. THE KNOB WAS DIFF ICULT TO PULL BUT THE PILOT CONFIRMED THAT THERE WAS FLOW AT THE MASKS. DURING THE FLIGHT THE PILOT AND CO-PILOT DONNED THE OXYGEN MASKS AND FOUND THERE WAS NO OXYGEN FLOW. UPON RETURN TO BASE MAINT CHECKED THE SYS AND FOUND IT SERVICEABLE . DURING THE NEXT FLIGHT THE PILOTS FOUND THE SAME PROBLEM WITH THE CONTROL KNOB. DURING TROUBLESHOOTING THE AC WAS COLD -SOAKED AND THE KNOB FOUND DIFFICULT TO PULL. THE CONTROL CABLE ASSY WAS REMOVED AND REPLACED. (TC NR 20071206003) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2008022500075 20080225 00075 CE 2008 2 25 CA071206004 1 20071205 G 3260 MS25237327 BULB CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE MLG ANNUNCIATOR BURNED OUT W L ABORTED APPROACH P NO WARNING INDICATION AP APPROACH 1 CA (CAN) PILOTS REPORT, ON FINAL TO LANDING RUNWAY, SELECTED THE GEAR DOWN HOWEVER THE RT MAIN GEAR GREEN LIGHT FAILED TO I LLUMINATE. THE RED (GEAR UNLOCKED) LIGHT WAS EXTINGUISHED. ADVISED TOWER AND CONDUCTED A MISSED APPROACH WITH REQUEST FO R VECTORS TO REMAIN IN AREA. WE COULD VISUALLY SEE THE WHEEL DOWN, AND THE GEAR HORN WOULD NOT SOUND WITH FULL FLAPS HOW EVER EXECUTED THE MANUAL EXTENSION PROCEDURE REGARDLESS, ASKED FOR THE EMERGENCY VEHICLES TO BE STANDING BY ON LANDING A S A PRECAUTION. BRIEFED OURONLY PASSENGERS AND LANDED WITH OUT FURTHER INCIDENT. CLEARED THE RUNWAY, ASKED FOR EMERGENCY CREWS TO VIEW OUR RT WHEEL FOR ANY OBVIOUS DAMAGED. THEY REPORT NOTHING APPARENT TO THEM AND SINCE THE AC LANDED, ROLLE 1 L 7 2 4F 4 F A22CE E1NE 2008022500078 20080225 00078 CE 2008 2 25 CA071206005 1 20071203 G 2120 UNKNOWN BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE COCKPIT ODOR W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA UE63 (CAN) UPON REACHING LEVEL FLIGHT BOTH THE CAPT AND F/O SMELLED SMOKE IN THE COCKPIT, WHICH SHORTLY AFTER COULD ALSO BE S EEN IN THE COCKPIT. AFTER LESS THAN A MINUTE THE SMOKE DISSIPATED AND THE CAPTAIN MADE THE DECISION TO RETURN TO THE DEP ARTURE POINT. AFTER CONTACT WITH ATC THE SMOKE AND SMELL HAD COMPLETELY DISAPPEARED. MAINT PERFORMED GROUND RUNS AND COU LD NOT DUPLICATE THE DEFECT. SYS TESTED AND INSPECTED, FWD NOSE AVIONICS, INSTRUMENT PANEL WIRING, COOLING FANS, CABIN A ND COCKPIT LIGHTING, CIRCUIT BREAKERS, PC BOARDS, INVERTER AND DC BUS CHECKS, ENVIRONMENTAL SYSTEM, ACM, LT AND RT ENGIN ES, AND WINDSHIELD HEAT ALL CHECKED SERVICEABLE WITH NO FAULT FOUND. (TC NR 20071206005) 1 L 7 2 4T 4 T A24CE E26NE 5 C P10NE 2008022500079 20080225 00079 NM 2008 2 25 CA071206006 1 20071126 G 2710 82700518001 CONTROL CABLE DHAV DHC8 DHC8106 2809020 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE AILERON WORN W O OTHER F FLT CONT AFFECTED DE DESCENT 1 CA (CAN) PILOTS REPORTED THAT THE AILERON CONTROLS WERE STIFF (OAT -20C). INSPECTION OF THE AIRCRAFT WAS CARRIED OUT AND TH E AILERON CABLE WAS FOUND TO BE WORN WHERE IT CROSSED A ROLLER FAIRLEAD AT APPROX STN YW189.00. THE ROLLER FAIRLEAD WAS NEARLY SEIZED. THE OB AILERON QUADRANT BEARINGS WERE ALSO FOUND TO BE STIFF WHEN COLD. THE CABLES IN BOTH WINGS WERE REP LACED AS WELL AS THE ROLLER FAIRLEAD. THE BEARINGS WERE REPLACED IN THE AILERON QUADRANTS AND THE AIRCRAFT WAS RETURNED TO SERVICE WITH NO FURTHER DEFECTS. (TC NR 20071206006) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008022500083 20080225 00083 NM 2008 2 25 CA071206007 1 20071203 G 2797 WIRE HARNESS LUCAS DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE AILERON ACTUATOR WORN W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA 18550 18550 0084 (CAN) AFTER ROTATION, HEAVY LT AILERON INPUT NEEDED IN FLIGHT. AILERON TRIM WAS CENTERED BUT HAD NO EFFECT. FLIGHT RETUR NED TO DEPARTURE AIRPORT SAFELY WITH NO NEED TO DECLARE AN EMERGENCY. MAINT TROUBLESHOOTING, FOUND WIRE HARNESS ON AILER ON TRIM ACTUATOR WORN WHERE WIRES ENTER BODY OF ACTUATOR CAUSING CIRCUIT BREAKER TO POP WHEN TRIM IMPUT WAS SELECTED. AI LERON TRIM ACTUATOR REPLACED AND SYSTEM TESTED SERVICEABLE. (TC NR 20071206007) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008031900167 20080319 00167 NE 2008 3 19 CA071206008 2 20071129 G 7320 70BM032010 MODULE SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE ENGINE FUEL DAMAGED W A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA 2975 (CAN) IN A CRUISE FLIGHT OR CLIMB POWER, THE AC ENGINE WOULD SURGE. THE AC WAS REMOVED FROM SERVICE FOR INSP. A CLOSE I NSPECTION OF THE COVER THAT IS LOCATED OVER THE COMPRESSOR IMPELLOR, REVEALED A HOLE APPX. 4-5MM IN DIAMETER. THE MODULE 3 WAS REMOVED AND REPLACED WITH A DIFFERENT MODULE AND THE AIRCRAFT WAS RE CERTIFIED. 1 G 7 1 3U 3 U H9EU E00054EN 2008022500085 20080225 00085 SO 2008 2 25 CA071207002 1 20071120 G 3231 40327000 TRUNNION PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL MLG DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 317552130 (CAN) DURING INSPECTION, A CRACK WAS FOUND IN THE RT UPPER TRUNNION, MOVING FROM THE BOTTOM OF THE TRUNNION UPWARDS TOWA RD THE ATTACHMENT POINT, THE GEAR DOOR ROD. THIS IS THE SECOND ONE THIS YEAR. (TC NR 20071207002) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2008022500086 20080225 00086 NM 2008 2 25 CA071207003 1 20071104 G 3230 483023 SOLENOID VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU RT MLG INOPERATIVE W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) UPON TAKEOFF AND GEAR RETRACTION RT MLG DOOR REMAINED OPEN WITH RT GEAR DOOR UNSAFE INDICATION. MAINT REPLACED RT MLG SOLENOID SEQUENCE VALVE. (TC NR 20071207003) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008031900168 20080319 00168 EA 2008 3 19 CA071207004 2 20071130 G 8500 ENGINE GULSTM 500 500B 0141106 SW LYC O540 IO540B1A5 41532 EA HARTZL HCC3Y HCC3YR2 NE POWER LOSS W B EMER. DESCENT R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) AFTER 45 MINUTE FLIGHT BOTH ENGINES BEGAN LOSING PWR WITH NO FUEL FLOW INDICATIONS OR FUEL PRESSURE INDICATIONS. E NGINES WOULD ONLY DEVELOP IDLE PWR. PILOT MADE A FORCED LANDING WITH MINOR INJURIES. FOLLOW UP INVESTIGATION TO FOLLOW. FOLLOW UP REPORT ON FINDING TO FOLLOW. (TC NR 20071207004) 1 H 7 2 3O 3 O 6A1 1E4 5 C P25EA 2008031900169 20080319 00169 NE 2008 3 19 CA071208001 2 20071205 G 7320 01644448430 FCU SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE SURGES W K NONE X ENGINE FLAMEOUT IN INSP/MAINT 1 CA (CAN) FCU WAS SURGING DURING A GROUND RUN LEAK CHECK, BLEED VALVE TACH BOX HAD BEEN CHANGED FOR TROUBLESHOOTING, SURGING CONTINUED. FCU CHANGED OUT AND SURGING PROBLEM WAS RESOLVED. AC RETURN TO SERVICE. (TC NR 20071208001) 1 G 7 1 3U 3 U NC H9EU E19EU 2008022500087 20080225 00087 NM 2008 2 25 CA071210001 1 20071206 G 2133 20224806 ACTUATOR BOEING 767 7673Y0 NM GE CF6 CF680C2B6F 30025 NE OUTFLOW VALVE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) ON DEPARTURE FLIGHT, LOST BOTH AUTO PRESSURIZATION SYS. FLIGHT CLIMBED TO FL190, AND RETURNED TO AIRPORT. CABIN PR ESS WAS APPROX 2000 FT. THE STATUS MESSAGES RECEIVED: CABIN ALT AUTO 1 AND CABIN ALT AUTO 2. QRH CARRIED OUT, AND FLIGHT RETURNED TO DEPARTURE. NO FAULT FOUND, SYSTEM RESET, BUT THE VALVE ACTUATOR IS SUSPECTED, (TC NR 20071210001) 2 L 7 2 4F 4 F RT A1NM E13NE 2008032400421 20080324 00421 EU 2008 3 24 CA071210003 1 20071206 G 3250 AIR860020 SELECTOR VALVE BAG JETSTM JETSTM3212 1500217 EU NLG STEERING UNSERVICEABLE W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA BADL48 (CAN) ON TAXI, PILOT FOUND THAT HE HAD REDUCED STEERING CONTROL OF THE AC USING THE NOSE WHEEL STEERING SYS. PILOT RETUR NED TO BLOCKS, UNABLE TO CONTINUE HIS FLIGHT. UPON TROUBLESHOOTING, IT WAS FOUND THAT THE STEERING SELECTOR WAS NOT OPER ATING PROPERLY, CAUSING A STEERING SYS FAILURE. THE STEERING SELECTOR WAS INSTALLED 03/10/2007 AND HAS ACCUMULATED 513 C YCLES SINCE O/H AND 38.2 WEEKS IN SERVICE. THE O/H INTERVAL FOR THIS PART IS 10 000 CYCLES OR 72 MONTHS. THE STEERING SE LECTOR WAS REMOVED AND AN O/H UNIT WAS INSTALLED AND THE NOSE WHEEL STEERING SYS FUNCTION CHECKED WITH NO FAULTS FOUND. AC RETURNED TO SERVICE. THIS STEERING SELECTOR WAS PURCHASED THROUGH TURBINE ENGINE CONSULTANTS INCORPORATED AFTER HAVIN 2 L 7 2 4T RT BA15CAA 2008022500089 20080225 00089 CE 2008 2 25 CA071210004 1 20071209 G 5753 351650503031 HINGE BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCE4N HCE4N3 NE TE FLAP WORN W K NONE O OTHER IN INSP/MAINT 1 CA 9534 (CAN) LT AND RT OB FLAPS IB HINGES WORN DUE TO ROLLER DIGGING INTO OB BRACKETS P/N 35-165050-30 AND 35-165050-31. THE AF T BEARINGS/ROLLERS HAVE TO BE REMOVED TO GET A GOOD INSPECTION OF THIS AREA. IT SHOULD NOT BE DONE (IN-SITU). THIS IS TH E 3RD AIRCRAFT IN THIS COMPANY FLEET THAT HAS HAD WEAR IN THIS AREA. IF LET GO TOO FAR, A FLIGHT CONTROL ISSUE MAY BE EN COUNTERED. (TC NR 20071210004) 1 L 7 2 4T 4 T A24CE E4EA 5 C P10NE 2008022500090 20080225 00090 WP 2008 2 25 CA071210005 1 20071204 G 6310 369A53515 HOUSING DOUG HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL CLUTCH CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 1758 (CAN) CLUTCH HOUSING RECEIVED FOR OVERHAUL AFTER PAINT STRIPPING HOUSING SENT OUT FOR NDT INSPECTION AND CAME BACK FOUND CRACKED ON ENGINE SIDE OF HOUSING. (TC NR 20071210005) 1 G 7 1 3U 3 U H3WE E4CE 2008022500091 20080225 00091 EU 2008 2 25 CA071210006 1 20071207 G 2917 RPR2B CONTROLLER SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE HYD ACCUMULATOR MALFUNCTIONED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 8813 (CAN) DURING FIRST GROUND RUN FOLLOWING A MAJOR 12 YEAR INSP, THERE WAS SIGNIFICANT HYDR FLUID LOSS IN THE AREA OF THE M AIN ROTOR ACCUMULATORS. THE HELICOPTER HAD BEEN AT 70 PERCENT GROUND IDLE FOR APPROX 3-4 MINUTES. THE HELICOPTER WAS SHU TDOWN IMMEDIATELY AND INSPECTED. ALL (3) ACCUMULATORS UNDERWENT VARYING DEGREES OF DEFORMATION (EXPANSION) DUE EXCESSIVE HYDR PRESSURE. HYDR FLUID LOSS WAS ISOLATED TO THE AREA OF THE COLLECTOR ASSEMBLIES MOUNTED ON THE SIDES OF THE SERVOS, SPECIFICALLY AT THE ACCUMULATOR AND ELECTRO VALVE JOINTS. IT IS SUSPECTED THE PRESSURE REGULATING VALVE OF THE HYDR MAN IFOLD STUCK, PREVENTING FLUID FROM RETURNING TO TANK. THIS ALLOWED PRESSURE TO BUILD BEYOND REGULATED PRESSURE. FURTHER 1 G 7 1 3U 3 U H9EU E19EU 2008022500092 20080225 00092 NM 2008 2 25 CA071211001 1 20071108 G 2731 82760174005 JACKSCREW DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE ELEVATOR TRIM CONTAMINATED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA 7816 (CAN) ADVISORY MESSAGE DISPLAY INDICATED (MISTRIM NOSE DN) WITH AUTOPILOT ENGAGED. DISENGAGED AUTOPILOT - FWD CONTROL CO LUMN FORCE REQUIRED TO MAINTAIN LEVEL FLIGHT, ATTEMPTED TO TRIM FWD BUT TRIM WHEEL WAS JAMMED WITH TRIM INDICATOR AT FWD OF THE TAKEOFF RANGE. TRIM MOVED REARWARDS OF THAT POSITION BUT NOT FWD OF IT. PAN DECLARED AND SERVICES REQUESTED, NOR MAL APPROACH AND LANDING COMPLETED. FUNCTIONAL CHECK OF THE ELEVATOR TRIM SYS CARRIED OUT ON THE GROUND. UNABLE TO REPL ICATE REPORTED CONDITION. BOTH THE LT AND RT HAND SCREW JACK ASSEMBLIES, ELEVATOR TRIM WERE INSPECTED AND FOUND TO HAVE SUFFICIENT GREASE LUBRICATION, BUT THE GREASE WAS DETERMINED TO BE WATER CONTAMINATED DUE TO THE DISCOLORATION OF THE GR 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008022500093 20080225 00093 EU 2008 2 25 CA071211002 1 20071210 G 2750 Z4243130000 CONTROL CABLE ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA MUHBR MTV MTV9* EU TE FLAPS FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 404 (CAN) THE FLAP CENTER CABLE WAS FOUND FRAYED DURING REGULARLY SCHEDULED MAINTENANCE. (TC NR 20071211002) 1 L 7 1 3O 3 O 0 A76EU 1E10 5 C P24NE 2008022500094 20080225 00094 2008 2 25 CA071211003 4 20071208 G 3417 8220372497 ADC CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF348C5 30050 NE MALFUNCTIONED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 CA 616 616 (CAN) THE FO REPORTED AN AIRSPEED OVER-SPEED TAPE ILLUMINATED AND COVERED THE ENTIRE SPEED TAPE ON THE AIRSPEED INDICATO R. AN AMBER (STALL FAIL) EICAS MESSAGE AND STICK SHAKER ENSUED. THE STALL PTCT SWITCH WAS SELECTED OFF HOWEVER THE STICK SHAKER CONTINUED. QRH PROCEDURE C/O, REVERTED TO NR1 ADC AND SHAKER STOPPED, ALTHOUGH STALL FAIL, SPOILER FAIL AND MANY OTHER EICAS MESSAGES DISPLAYED. OPERATED SINGLE ADC AND ELECTED TO TURN BACK TO DEPARTURE. MDC FAULT HISTORY DISPLAYED ADC 2 NR OUT PUT MESSAGE B1-005863, STALL FAIL B1-008073 AND LABEL 350 BIT 27 SET INCONSISTENT ADC DATA. NR2 ADC AND NR2 AOA SENSOR AT FAULT. NR2 ADC AND NR2 AOA SENSOR REPLACED AND FUNCTION TEST OF ADC-OVERSPEED WARNING AND ALTIMETER SCALE 2 L 7 2 4F 4 F RT A21EA E00063EN 2008022500095 20080225 00095 EA 2008 2 25 CA071211004 1 20071205 G 2750 865D1007 PDU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 7610 7610 (CAN) AFTER LANDING WITH FLAPS AT 45 DEGREES, FLAPS SELECTED TO 0 DEGREES. CREW RECEIVED A FLAP FAIL AMBER MESSAGE AT FL APS 41 DEGREES. MAINTENANCE TROUBLESHOOTING REVEILED FECU FAULT CODES FOR ASYMMETRY, BINDNG AND FLAPS NOT IN POSITION LE ADING TO REPLACEMENT OF THE FLAP POWER DRIVE UNIT IAW AMM 27-52-01-400. WILL UPDATE WHEN TEAR DOWN RESULTS BECOME AVAIL ABLE. (TC NR 20071211004) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500096 20080225 00096 EA 2008 2 25 CA071211005 1 20071205 G 2750 1104SD10020 FLEX DRIVE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS TWISTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFTER LANDING WITH FLAPS AT 45 DEGREES, FLAPS SELECTED TO 0 DEGREES. CREW RECEIVED A FLAP FAIL AMBER MESSAGE AT FL APS 41 DEGREES. DURING MAINTENANCE TROUBLESHOOTING OF FLAPS THE NR 2 RT FLEX DRIVE SHAFT ASSY WAS FOUND TWISTED. UPON RE MOVAL PART LENGHTH WAS DISCOVERED TO BE 40 INCHES INSTEAD OF 39 INCHES IAW MFG SPECIFICATIONS. NO RECORD OF PREVIOUS REP LACEMENT SINCE AC NEW. IPC 27-53-00 FIG 1, ITEM 10B. (TC NR 20071211005) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500097 20080225 00097 NE 2008 2 25 CA071211006 2 20071130 G 7314 LW15473 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENG FUEL LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 746 (CAN) DURING A 50 HOUR INSPECTION THE ENGINE DRIVE FUEL PUMP WAS FOUND LEAKING FROM SEAL. (INNER DIAPHRAM) (TC NR 20071 211006) 1 G 7 1 3O 3 O H11NM 1E4 2008022500098 20080225 00098 NE 2008 2 25 CA071211007 2 20071211 G 7314 LW15473 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENG FUEL LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 822 (CAN) DURING GROUND RUN, PUMP WAS FOUND LEAKING FROM DRAIN. PUMP REPLACED, NO FURTHER DEFECT. (TC NR 20071211007) 1 G 7 1 3O 3 O H11NM 1E4 2008022500099 20080225 00099 EU 2008 2 25 CA071211008 1 20071210 G 2820 WYE PIPE SNIAS 350 AS350BA 8680817 EU LYC LTS101 LTS101600A2 41560 NE FUEL SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) THE AC WAS BEING REFUELED OUT SIDE WHEN FUEL STARTED POURING ON THE GROUND FROM SOMEWHERE IN THE FUEL TANK AREA. F URTHER INVESTIGATION REVEALED THE (Y) CONNECTION OF THE FUEL SUPPLY LINE FROM THE 2 BOOST PUMPS HAD SIMPLY FALLEN OUT OF THE FUEL LINE GOING UP TO THE FUEL FILTER ON THE TRANSMISSION DECK. THE 2 GEAR CLAMPS THAT SECURE THE HOSE TO THE (Y) F ITTING WERE SECURED TIGHT ENOUGH THAT THE CLAMPS FELT TIGHT AND COULD NOT BE ROTATED ON THE HOSE BUT WHEN CHECKED WITH A SCREWDRIVER, THEY COULD BE TIGHTENED BY A FEW TURNS. DUE THE NATURE OF THE ROUTING AND CLAMPING OF THE HOSE, THERE WAS A NATURAL TENDENCY FOR THE Y FITTING TO PULL DOWN ON THE UPPER HOSE. THE HOSE WAS REPOSITIONED AND CLAMPED PROPERLY TO 1 G 7 1 3U 3 U NC H9EU E5NE 2008022500101 20080225 00101 CE 2008 2 25 CA071212002 1 20070921 G 5711 95B55 SPAR BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO HARTZL HCC2Y BHCC2YF2 GL WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9896 (CAN) DURING ANNUAL INSPECTION, VISUAL INSPECTION OF AREA REVEALED A SUSPECTED CRACK. NOT OF DYE PENETRANT AND EDDY CURR ENT CONFIRMED. MFG SERVICE KIT TO INSTALLED. PART LAST NDT INSPECTED 22.1 HRS PREVIOUS AND NO INDICATIONS. (TC NR 200712 12002) 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P920 2008022500102 20080225 00102 2008 2 25 CA071212003 4 20070510 G 3416 152734 RING ISRAEL 1125 1125 NM GARRTT TFE731 TFE7313A 01518 WP STBY ALTMETER INCORRECT W O OTHER O OTHER NR NOT REPORTED 1 CA 8091 (CAN) MODIFICATION OF LOCKING PIN SLOT OF ITEM (PN 152734). RING SUPPORT FOUND ON THIS STBY ALTIMETER (TC NR 20071212003 ). 2 L 7 2 4F 4 F RT A16NM E6WE 2008022500103 20080225 00103 GL 2008 2 25 CA071212004 3 20071110 G 6114 B1192 DIAPHRAGM NAVION STC STCNAVION CONT E185 E1853 17014 SO HARTZL HC12V HC12V20* GL PROP HUB CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 34 (CAN) OIL LEAK AROUND PROP HUB AND SPRAYED ONTO WINDSHIELD. PROP REMOVED. JACK PLATE ASSY REMOVED. DIAPHRAGM REMOVED. I NNER SURFACE AROUND CENTER ATTACH RING ALMOST TOTALLY SPLIT AROUND CIRCUMFERENCE. THE DIAPHRAGM WAS INSTALLED JUNE 15, 2 007 AND FAILED IMMEDIATELY. (TC NR 20071212004) 1 L 7 1 3O 3 O A782 E246 5 C P46GL 2008022500105 20080225 00105 CE 2008 2 25 CA071212005 1 20071127 G 5344 051701912 HINGE PIN CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL DOOR HINGE CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) DOOR HINGE PINS APPEAR TO BE WELDING RODS OR STEEL PINS CUT LONG AND BENT OVER TO SERVE FROM FALLING OUT. REPLACED WITH PROPER PARTS. CAUSED DISSIMILAR METAL CORROSION TO HINGE MATERIAL AS BOGUS PINS RUSTED. THE ENTIRE FLEET HAS THES E SAME BOGUS PINS (10 AIRCRAFT IN TOTAL). INSTALLED BY PREVIOUS MAINTAINER, AMO 73-03. (TC NR 20071212005) 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2008022500106 20080225 00106 EA 2008 2 25 CA071212006 3 20071127 G 6111 BLADE SNSNCH DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 265 AG1827 AG1827 (CAN) LONGITUDINAL CRACK AT BLADE TIP NR 1 BLADE. CRACK APPROX 1.5 INCH LONG AT APPROX .75 CHORD. FOUND DURING INSPECT ION (ROUTINE). APPEARS TO BE CAUSED BY IMPACT DAMAGE FROM FOD. (TC NR 20071212006) 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2008022500108 20080225 00108 EA 2008 2 25 CA071212007 3 20071127 G 6111 BLADE DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA PROPELLER CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 330 AG3920 AG3920 (CAN) LONGITUDINAL CRACK AT BLADE TIP, NR 1 BLADE. CRACK APPROX 0.75 INCH LONG AT .25 CHORD. FOUND DURING INSPECTION ( ROUTINE). NO APPARENT CAUSE, NO IMPACT DAMAGE FROM FOD. (TC NR 20071212007) 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2008022500110 20080225 00110 NE 2008 2 25 CA071212009 2 20071114 G 7200 ENGINE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE CONTAMINATED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 123216 (CAN) CREW RECEIVED A LOW OIL PRESSURE WARNING AND ELECTED TO SHUTDOWN THE ENGINE. INITIAL POST FLIGHT INVESTIGATION REV EALS CONTAMINATION OF THE CHIP DETECTORS AND OIL FILTERS. THE ENGINE WILL BE SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071212009) 2 H 7 2 4T 4 T RT A13NM E20NE 2008022500111 20080225 00111 NE 2008 2 25 CA071212010 2 20070613 G 7250 TURBINE AEROSP ATR72 ATR72201 8680943 EU PWA PW120 PW124B NE ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 124515 (CAN) REPORTED TO MFG ON DEC 07 2007. ENGINE REPORTED TO HAVE SUFFERED AN INFLIGHT SHUTDOWN DURING TAKEOFF/CLIMB. NO OT HER DETAILS PROVIDED. POST FLIGHT INSPECTION INDICATES SEVERE DAMAGE TO THE TURBINE SECTION. MFG WILL CONTINUE INVESTI GATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071212010) 2 H 7 2 4T 4 T RT A53EU E2ONE 2008022500113 20080225 00113 NE 2008 2 25 CA071212011 2 20071021 G 7261 TUBE AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE ENGINE OIL FRACTURED W F E A ACTIVATE FIRE EXT. ENGINE SHUTDOWN UNSCHED LANDING K A J FLUID LOSS FLAME/FIRE WARNING INDICATION CR CRUISE 1 CA 120746 (CAN) FIRE WARNING DURING CRUISE. CREW ACTIVATED THE FIRE SUPPRESSION SYSTEM AND SECURED THE ENGINE. POST FLIGHT INITIAL INSPECTION REVEALED A FRACTURED NR 6 AND NR 7 BEARING OIL TRANSFER TUBE. SOME FIRE DAMAGE WAS OBSERVED ON THE AFT PORTI ON OF THE ENGINE. THE ENGINE HAS BEEN REMOVED AND FORWARDED FOR FUTHER INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071212011) 2 H 7 2 4T 4 T RT A53EU E20NE 2008022500114 20080225 00114 CE 2008 2 25 CA071212012 1 20071211 G 2720 MS35206228 SCREW CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE RUDDER PEDAL MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SL 550-27-14 FOUND 2 SCREWS, P/N MS350206-228, MISSING FROM PILOTS LT RUDDER SUPPORT BRACKET AND 2 LOOSE SCREWS P/ N MS 350206-228 ON THE CO-PILOTS RT RUDDER SUPPORT BRACKET.CARRY OUT ACCOMPLISHMENT INSTRUCTIONS PARAGRAPH 1THRU 4. (TC NR 20071212012) 1 L 7 2 4F 4 F A22CE E1NE 2008022500115 20080225 00115 EU 2008 2 25 CA071212014 1 20071211 G 2922 704A34629013 STRAINER SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE HYD SYSTEM CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) STRAINER WAS INSPECTED AND FOUND CONTAMINATED WITH PARTICLES FOREIGN MATTER AND SLIVERS OF MATERIAL FROM THE O-RIN G, P/N MS28775-016, WHICH WAS HARD AND BRITTLE. THE MFG MM REQUIRES INSPECTION AND CLEANING OF THE STRAINER ONLY WHEN T HE MANIFOLD IS REPLACED DURING A HYDRAULIC PUMP REPLACEMENT, THERE IS NO SCHEDULED INTERVAL FOR CLEANING. ALL AC IN THE COMPANY FLEET WILL BE INSPECTED ON OR BEFORE THE NEXT 100 HOUR INSPECTION AND THIS TASK WILL BE ADDED TO 500 HOUR T-INS PECTION. THE MFG TECH REP HAS BEEN INFORMED OF THE FINDINGS OF THIS INSPECTION. (TC NR 20071212014) 1 G 7 1 3U 3 U NC H9EU E19EU 2008022500118 20080225 00118 EA 2008 2 25 CA071212024 1 20071026 G 7810 3009090 EXHAUST DUCT DHAV DHC6 DHC6100 2802610 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5861 (CAN) WHILE INSPECTING THE POWER SECTION FOR REASSEMBLY AFTER HSI, CIRCUMFERENTIAL CRACKS WERE DISCOVERED ALONG THE WELD S OF THE EXHAUST DUCT JUST FWD OF THE PT VANE MOUNTING FLANGE. (4) CRACKS RANGED IN LENGTH FROM .75 INCH TO 4.75 INCH. T HE POWER SECTION WAS REPLACED. (TC NR 20071212024) 1 H 7 2 3T 3 T RT A9EA E4EA 6 C P15EA 2008022500119 20080225 00119 GL 2008 2 25 CA071212025 3 20071212 G 6114 87292 HUB MCAULY CESSNA 180 180J 2072622 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL PROPELLER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1481 022853 022853 (CAN) AT OVERHAUL PROPELLER HUB WAS STRIPPED OF PAINT FINISH. ENTIRE OUTER SURFACE OF HUB AND BLADE O-RING GROOVES WERE CORRODED BEYOND LIMITS. HUB WAS RETURNED TO MFG FOR EVALUATION. (TC NR 20071212025) 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2008022500122 20080225 00122 GL 2008 2 25 CA071212026 3 20071211 G 6110 FLANGE MCAULY CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1516 SR773463 SR773463 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION IAW AD 2003-12-05. A SMALL CRACK WAS LOCATED RADIALLY AT THE EDGE OF O NE MOUNTING BOLT HOLE. TIME SINCE LAST INSPECTED FOR AD 2003-12-05 WAS 409.2 HOURS. (TC NR 20071212026) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2008022500123 20080225 00123 CE 2008 2 25 CA071212027 1 20071207 G 3244 TU29110010 TIRE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL MLG FLAT W O OTHER O OTHER LD LANDING 1 CA (CAN) TIRE WENT FLAT. (TC NR 20071212027) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2008022500124 20080225 00124 CE 2008 2 25 CA071212028 1 20071128 G 3244 TU29110010 TIRE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL MLG FLAT W O OTHER O OTHER LD LANDING 1 CA 920 (CAN) TIRE WENT FLAT. (TC NR 20071212028) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2008022500126 20080225 00126 NE 2008 2 25 CA071213001 2 20071212 G 7261 6087T04P09 SCAVENGE PUMP GE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE ENGINE FAILED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 29540 367 807240 807240 (CAN) DURING CRUISE FLIGHT, THE CREW RECEIVED RED NR 2 ENG LOW OIL PRESS MESSAGE AND GAUGE INDICATION FOR NR 2 ENGINE SH OWED (0) PSI, CREW ELECTED TO SHUTDOWN ENGINE AND RETURN TO DEPARTURE AIRPORT, NORMAL LANDING. MAINTENANCE FOUND NR 2 EN GINE, OIL LUBE/SCAVENGE PUMP ROTATES FREELY WITH NO PRESSURE OUTPUT. PUMP TO BE SENT OUT TO VENDOR FOR INVESTIGATION. OIL PUMP INFORMATION: MFG CO P/N 99207SOCN6087T04P09, CODE IDENT 86329, REF 4406-9 S/N NMAAD498 TSN 29540HR / 24208CY , TSO 367HR / 309CY.(TC NR 20071213001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500127 20080225 00127 CE 2008 2 25 CA071213002 1 20071212 G 2121 BRUSHES BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA HARTZL HCB3T HCB3TN3 GL BLOWER MOTOR BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 1357 (CAN) CREW DECLARED EMERGENCY DUE TO SMOKE IN COCKPIT AND LANDED SAFELY. REPAIR PARTY LT FROM ANOTHER BASE. FOUND CAUSE WAS CABIN VENT BLOWER. DISABLED SYSTEM. AIRCRAFT FERRIED TO AIRPORT. MAINTENANCE WILL REPLACE VENT BLOWER. (TC NR 20071 213002) 1 L 7 2 3T 4 T RT 3A20 E4EA 6 C P15EA 2008022500128 20080225 00128 NM 2008 2 25 CA071213003 1 20071213 G 5321 CMKD8400FP540 FLOOR PANEL BOMBDR DHC8 DHC8400 NM CABIN DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA 2595 (CAN) FORWARD CABIN FLOOR PANEL WHERE PURSER STANDS TO GIVE PRE-FLIGHT BRIEFING STARTING TO DELAMINATE. MATERIAL IS COMP 28 WHICH IS BUILT TO STAND STRESS OF 75 LB/FT SQUARED. (TC NR 20071213003) 2 H 7 2 4T RT A13NM 20080520 CE 2008 5 20 CA071213004 1 20070725 G 2720 07600323 SHAFT CESSNA 180 180J 2072622 CE CONT O470 O470S 17026 SO MCAULY 2A34C 2A34C203 GL RUDDER PEDALS CRACKED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 14983 (CAN) RUDDER BAR ASSY CRACKED AT SPIGOT ATTACH POINT WHERE RUDDER PEDAL STUB SHAFT (PN 0411307) CONNECTS TO RUDDER BAR A SSY. PILOTS REPORTED A SOFT PEDAL ON WATER OPERATIONS, INVESTIGATION REVEALED A SPHERICAL CRACK ON THE RUDDER PEDAL TOR QUE TUBE. (TC NR 20071213004) 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2008022500129 20080225 00129 CE 2008 2 25 CA071214001 1 20071204 G 5220 HANDLE BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCE4N HCE4N3 NE EMERGENCY EXIT JAMMED W K NONE O OTHER IN INSP/MAINT 1 CA 200 (CAN) DURING THE INITIAL PHASE ONE INSPECTION THE EMERGENCY EXIT COULD NOT BE OPENED FROM THE OUTSIDE AND THE EXIT COULD NOT BE LOCKED FROM THE INSIDE. (TC NR 20071214001) 1 L 7 2 4T 4 T A24CE E4EA 5 C P10NE 2008022500130 20080225 00130 GL 2008 2 25 CA071214002 1 20071214 G 5751 C2WA126A HINGE BRACKET DHAV DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985* 52008 NE AILERON BROKEN W O OTHER O OTHER AP APPROACH 1 CA SA721 (CAN) FAILURE NOTICED DURING WALK AROUND BY MECHANIC. THE SPIGOT (INTEGRAL PART OF THE HINGE BRACKET) HAD FAILED COMPLET ELY, JUST BELOW THE UPPER EDGE OF THE BALANCE WEIGHT ARM. JUDGING BY THE SURFACES THE SPIGOT HAD BEEN BROKEN FOR SOME TI ME. EXTREMELY DANGEROUS SITUATION. NO LOG BOOKS OR RECORDS AVAILABLE. (TC NR 20071214002) 1 H 7 1 3R 3 R RC A806 5E1 2008013100283 20080131 00283 EA 2008 1 31 CA071214003 1 20071214 G 2823 C2CE523A CABLE DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985* 52008 NE FUEL SELECTOR CORRODED W O OTHER O OTHER AP APPROACH 1 CA (CAN) FUEL SELECTOR CABLE VERY BADLY CORRODED, CABLE FAILED WHEN REMOVED. NO LOG BOOKS OR RECORDS AVAILABLE. (TC NR 200 71214003) 1 H 7 1 3R 3 R A806 5E1 2008013100284 20080131 00284 EA 2008 1 31 CA071214004 1 20071213 G 2752 852D10019 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS UNSERVICEABLE W O OTHER J WARNING INDICATION DE DESCENT 1 CA (CAN) FLAP FAIL ON DESCENT, WHEN FLAP SELECTED FROM 0 DEG TO 8 DEG. FLAPLESS LANDING CARRIED OUT WITHOUT FURTHER INCIDEN T. TROUBLESHOOTING IN PROGRESS. WILL UPDATE WHEN MORE INFORMATION IS AVAILABLE (TC NR 20071214004) 2 L 7 2 4F 4 F RT A21EA E15NE 2008013100285 20080131 00285 GL 2008 1 31 CA071214005 1 20071004 G 5344 C2FS1253A HINGE BRACKET DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE CARGO DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 11888 (CAN) TOP HINGE BRACKET CRACKED ON FWD FACE OF HINGE. (TC NR 20071214005) 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2008013100287 20080131 00287 2008 1 31 CA071214006 4 20071212 G 6122 3011847 LINE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL ENGINE CRACKED W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA PCE51194 (CAN) AFTER DEPARTURE DURING CLIMB, THE PILOT NOTICED SLIGHT POWER LOSS ON THE LT ENGINE WHICH SLOWLY DECAYED UNTIL TORQ UE WAS AT 100LBS AT WHICH TIME THE PROP WAS FEATHERED. THE CREW ELECTED TO LEAVE THE ENGINE RUNNING AS ALL OTHER INDICAT IONS WERE GREEN AND THEY WANTED THE GENERATOR RUNNING AS ICING CONDITIONS WERE FORECAST. UPON INSPECTION BY MAINTENANCE , IT WAS DISCOVERED THE PY LINE FROM THE PROP GOVERNOR TO THE FCU WAS CRACKED. THE LINE WAS REPLACED GROUND RUNS CARRIED OUT AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20071214006) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2008020400125 20080204 00125 EU 2008 2 4 CA071214007 1 20071210 G 3411 257SF2099 PITOT TUBE BRAERO DH125 HS125700A 4230170 EU GARRTT TFE731 TFE7313R1H 29001 WP CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 6664 (CAN) FOLLOWING A FAILED PITOT STATIC TEST, AN INSPECTION OF THE PITOT STATIC TUBING WAS CARRIED OUT AND MAINT FOUND THA T ONE OF THE TUBES (P/N 25-7SF209-9) HAD A PIN HOLE, WHICH APPEARS TO HAVE BEEN CAUSED BY INTERGRANULAR CORROSION. THE L INE WAS REPAIRED AND THE PITOT STATIC SYSTEM TESTED SERVICEABLE. REFERENCE: PARTS CATALOG 34-10-00-22 ITEM 24 (P/N 25- 7SF209-9), PIPE ASSY-STATIC 5 FEED, TEE-PIECE TO TEE-PIECE, 3/8 INS O/D, L56, 22 SWG (MOD252870) (TC NR 20071214007) 2 L 7 2 4F 4 F A3EU E6WE 20080520 CE 2008 5 20 CA071214008 1 20071213 G 3230 CAC99126259 VALVE CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE MLG FAILED W O OTHER O OTHER AP APPROACH 1 CA 585 (CAN) AT LANDING GEAR SELECTION, THE LANDING GEAR DID NOT COME DOWN AND NONE OF THE FOLLOWING INDICATIONS WERE OBSERVED: HYD PUMP OPERATION GEAR MOVEMENT / NOISE GEAR DOWN LIGHTS INDICATION ON THE CONTROLLER, NOTE: ALL OTHER HYD CONSUMERS WERE OPERATIONAL THE GEAR WAS RECYCLED WITH NO SUCCESS. A GO-AROUND WAS INITIATED THEN THE ABNORMAL/EMERGENCY CHECKLIST WAS REVIEWED AND CARRIED OUT, GEAR CAME DOWN AND LOCKED . VALVE REPLACED GEAR SYS, OK (TC NR 20071214008) 2 L 7 2 4F 4 F RT A22CE E00059EN 2008020400124 20080204 00124 SW 2008 2 4 CA071214009 1 20071210 G 7120 205060106001 MOUNT BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE RT ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9047 (CAN) RT ENGINE BIPOD INSPECTED FOR SUSPICIOUS CRACK IN FRONT TUBING DURING 100 HRS INSPECTION. NDT REVEALED CRACK MOUNT AT WELDED JOINT. NOTE: THIS MOUNT WAS MODIFIED IAW STC SH99-11, DART ADJUSTABLE MOUNT. (TC NR 20071214009) 1 G 7 1 4U 4 U H1SW E17EA 2008020400123 20080204 00123 WP 2008 2 4 CA071214010 1 20071214 G 7603 A9333 ROD END ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE THROTTLE CONTROL SEPARATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ENGINE HAD HIGH IDLE, TRYED TO ADJUST AND WAS UNABLE TO BRING IDLE BELOW 64 PERCENT ENG RPM. INSPECTED THROTTLE LI NKAGE AND FOUND ROD END BRG OUTER HOUSING SEPARATED FROM STAKED IN SPHERICAL BEARING. POSSIBLE LOST OF ENGINE CONTROL UN DER QUICK POWER CHANGES. REPLACED ROD END AND RECTIFIED DEFECT. (TC NR 20071214010) 1 G 7 1 3O 3 O H11NM 1E4 2008020400122 20080204 00122 CE 2008 2 4 CA071214011 1 20071214 G 5280 16911003421 BOLT BEECH BEECH 76 76 1153005 CE LYC O360 O360A1G6D EA HARTZL HCM2Y HCM2YR GL MLG DOOR MISSING W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) PILOT NOTICED ON PRE-FLIGHT, ABNORMAL ANGLE OF GEAR DOOR. IT WAS DISCOVERED THAT THE BOLT SECURING THE DOOR WAS MI SSING. THIS STRESSED THE AFT BRACKET TO THE POINT OF CRACKING WHICH ALSO CAUSED THE DOOR TO CRACK ALONG THE BOLT HOLES. (TC NR 20071214011) 1 L 7 2 3O 3 O A29CE E286 5 C P43GL 2008020400121 20080204 00121 NE 2008 2 4 CA071217001 2 20071205 G 7230 FAN BLADE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE RT ENGINE DAMAGED W A UNSCHED LANDING C E F.O.D. VIBRATION/BUFFET CR CRUISE 1 CA 807658 (CAN) CREW REPORTED N2 VIB ICON (RT ENG) POSTED DURING CRUISE AT FL320. CREW FOLLOWED QRH AND COULD NOT CONTROL VIB IFSD AND DIVERTED. MAINTENANCE OBSERVED FOD DAMAGE TO FAN BLADES. ENGINE REMOVED AND REPLACED (TC NR 20071217001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008020400120 20080204 00120 NM 2008 2 4 CA071217003 1 20071205 G 2910 DSC252B40124 FLEX LINE DHAV DHC8 DHC8202 2809007 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE HYD SYSTEM LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION DE DESCENT 1 CA (CAN) TOTAL FAILURE OF NR 2 HYD SYS OCCURRED AFTER GEAR EXTENSION (NORMAL). LOSS OF PRESSURE WITH ASSOCIATED CAUTION LIG HTS QUICKLY FOLLOWED BY TOTAL LOSS OF ALL NR 2 HYD QUANTITY (FLUID). UPGRADED CALL TO PAN WITH REQUEST FOR LOCAL SERVICE S ON STANDBY. AFTER ALTERNATE GEAR EXTENSION, THE NR 2 HYD PRESSURE ROSE TO NORMAL AT 3000 PSI. AFTER LANDING WITH NORMA L HYD PRESSURE, AC TAXIED CLEAR OF RUNWAY. ENGINEERING INVESTIGATION REVEALED A FAILURE OF THE NLG DRAG BRACE ACTUATOR (DOWN) FLEXIBLE HOSE. HOSE REPLACED AND FOLLOWING APPROPRIATE CHECKS IAW THE MM. THE AIRCRAFT WAS RELEASED BACK TO SER VICE WITHOUT FURTHER INCIDENT. THIS IS A KNOWN ISSUE PREVIOUS SDR 20031030005. (TC NR 20071217003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008022500136 20080225 00136 EA 2008 2 25 CA071217004 1 20071212 G 7600 3052970 CONTROL CABLE DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL CONDITION LEVER DISCONNECTED W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 CA (CAN) AFTER FLIGHT, THE NR 2 CONDITION LEVER WOULD NOT MOVE TO FEATHER OR CUTOFF, THE ENGINE HAD TO BE SHUTDOWN USING TH E T-HANDLE. FURTHER INVESTIGATION REVEALED THAT THE NR 2 TELEFLEX CABLE HAD BECOME UNSCREWED NEAR THE BEARING. WE WERE UNAWARE THAT THE CABLE COULD BE UNSCREWED AT THIS LOCATION, WHEN THE CABLE IS ASSEMBLED THERE IS NO VISUAL INDICATION T HAT THE CABLE CAN BE DISASSEMBLED. THERE ARE NO PROVISIONS FOR THE CABLE TO BE LOCK WIRED AT THIS LOCATION. TIME SINCE N EW UNKNOWN. FURTHER INVESTIGATION FOUND ONE OTHER UNSCREWED CABLE ON THE AIRCRAFT. WE WILL BE INSPECTING OUR FLEET TO A SSURE NO OTHER CABLES ARE LOOSE. (TC NR 20071217004) 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2008022500137 20080225 00137 EA 2008 2 25 CA071217005 1 20071214 G 2752 852D100 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS FROZEN W O OTHER F J FLT CONT AFFECTED WARNING INDICATION DE DESCENT 1 CA (CAN) FLAP FAIL DURING DESCENT. FLAPS WOULD NOT EXTEND WHEN SELECTED, FLAP 0 APPROACH AND LANDING CONDUCTED. AIRCRAFT LA NDED WITHOUT FURTHER INCIDENT. FAULT CODES SENT TO TECH OPS, AIRCRAFT WILL BE FERRIED WHEN CREW AVAILABLE. FAULT CODES ARE AS FOLLOWS: EVENT 1 FLIGHT LEG 4555 JAM/ LT BPSU/ PDU DIFFERENTIAL/ 5 1B/ 5 2B/ 9 1A/ 9 2A/ 17 1A/ 17 2A/ 25 BC. EV ENT 2 FLIGHT LEG 4555 JAM/ ADC SIGNALS/ LH BPSU FAIL/ 5 2B. FAULT INDICATION IS POINTING A FREEZE EVENT. MORE INFORMATIO N WILL BE ADDED AS SOON AS BECOME AVAILABLE. (TC NR 20071217005) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500138 20080225 00138 WP 2008 2 25 CA071217006 2 20071214 G 7321 NAS1351C3LL6 BOLT WOODWARD BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33110UG 01514 WP ROTOL R333 R333482F12 GL FUEL CONTROL BACKED OUT W A UNSCHED LANDING R F PARTIAL RPM/PWR LOSS FLT CONT AFFECTED CL CLIMB 1 CA 2137501 (CAN) ON CLIMB OUT, THE PILOT REPORTS NR 1 ENG RPM DROPPED TO 97 PERCENT AND HE WAS NOT ABLE TO RESTORE THE ENG TO 100 P ERCENT RPM. PROCEEDED TO MAKE AN UNSCHEDULED LANDING AT DEPARTURE AIRFIELD. UPON INVESTIGATION IT WAS FOUND THAT THE BO LT ATTACHING THE SPEED LEVER TELEFLEX CABLE TO SPEED INPUT SHAFT OF THE FCU HAD BACKED OUT COMPLETELY AND THE CABLE HAD SEPARATED FROM THE INPUT ROD. THE BOLT IN QUESTION WAS RE-USED ON AN ENGINE CHANGE THAT TOOK PLACE 33.6 HOURS PRIOR TO T HIS EVENT, ON 11/28/2007. AT THAT TIME THE BOLT MET THE RUN-DOWN TORQUE REQUIREMENTS FOR SELF LOCKING HARDWARE IAW MM ST ANDARD PRACTICES. THE BOLT WAS REPLACED, THE ENGINE RE-RIGGED WITH NO FAULTS FOUND AND THE AC RETURNED TO SERVICE. (TC N 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C P61GL 2008022500140 20080225 00140 NE 2008 2 25 CA071217007 2 20071217 G 7314 D7431 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE AUX FUEL FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1564 (CAN) PILOT ATTEMPTED TO START AIRCRAFT, BUT FAILED. FURTHER INVESTIGATION REVEALED THE AUX FUEL PUMP DID NOT SUPPLY FUE L TO START AIRCRAFT. PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. (TC NR 20071217007) 1 G 7 1 3O 3 O H11NM 1E4 2008022500141 20080225 00141 EA 2008 2 25 CA071217008 1 20071212 G 2750 5275200 DRIVE ASSY CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAULTY W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 9151 9145 (CAN) FLAPS FAILED AT 30 DEG WHEN 45 DEG SELECTED. FLAP ACTUATORS, PDU AND FECU REPLACED TEST FLIGHT CARRIED OUT CHECKE D SUSPECT POWER FLAP DRIVE AT FAULT DUE TO HISTORY. (TC NR 20071217008) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500142 20080225 00142 EA 2008 2 25 CA071217009 1 20071214 G 2752 854D10019 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAP MALFUNCTIONED W L ABORTED APPROACH J F WARNING INDICATION FLT CONT AFFECTED AP APPROACH 1 CA 7255 (CAN) ON APPROACH THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE AFTER SELECTING THE FLAP LEVER TO 8 DEGREES. THE EICAS F LIGHT CONTROL PAGE WAS SHOWING THE FLAP POSITION AT 2 DEGREES. THE CREW REQUESTED EMERGENCY SERVICES AND LANDED WITHOUT FURTHER INCIDENT. AC WAS INSPECTED AND FERRIED. ADCF 2007-10 AND SB601R-27-150 WERE COMPLETED. THE LT NR4 AND RT NR3 F LAP ACTUATORS FAILED THE -60 DEGREES CELSIUS TORQUE CHECK AT A VALUE OF 35 AND 30 INCHES/POUND RESPECTIVELY. LT NR4, P /N 854D100-19, S/N 2312, TSN 7255:58, CSN 5839, TSR 1971:52 RT NR3, P/N 853D100-20, S/N 3377, TSN 8268:20, CSN 6104, TSR 1971:52 BOTH ACTUATORS WERE REPLACED. THE LT NR3, RT NR1 AND NR4 FLAP ACTUATORS WERE FOUND NEAR SERVICE LIMIT AND WERE 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500143 20080225 00143 EA 2008 2 25 CA071217010 1 20071213 G 2750 FCU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAULTED W L ABORTED APPROACH F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) FLAP FAIL ON APPROACH WHEN FLAPS SELECTED TO 20 FROM 8. SYS RESET AND CHECKED SERVICEABLE, MAINT EMPLOYEE ON SITE GOT FAULT CODES FROM FECU. SKEW BITE RESET AND FLAP CONTROL AND POWER DRIVE UNIT RESETS CARRIED OUT. FLAP FAULT CLEAR ED. FLAPS CYCLED SEVERAL TIMES NO FAULTS NOTED. SYSTEM FUNCTION CHECKED SERVICEABLE FOR FLIGHT. (TC NR 20071217010) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500145 20080225 00145 EU 2008 2 25 CA071218001 2 20071208 G 7261 FC3401B01B01B029 HOSE DIAMON DA20 DA20A1 2990000 GL ROTAX 912 ROTAX912 55555 EU HOFMAN HOV352 HOV352F NE ENGINE OIL LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 2000 (CAN) PILOT LANDED NORMALLY AND SHUTDOWN AFTER NOTICING FALLING OIL PRESSURE INDICATION. THIS WAS ON INITIAL TEST FLIGHT OF A NEW ENGINE INSTALLATION, ON INSPECTION THE OIL PRESSURE HOSE FITTING AT THE OIL PUMP WAS FOUND TO BE LEAKING, THIS WAS TIGHTENED AND AN INSPECTOR OF THE ENGINE COMPLETED. A SEPARATE MECHANIC VERIFIED THE OIL LINE FITTING AND FOUND IT TO BE LOOSENED OFF AGAIN. A TWIST IN THE HOSE AND A WEAK THREAD ENGAGEMENT WERE SUSPECTED. A NEW HOSE WAS INSTALLED AND THE ENGINE TEST RUN AND CHECKED WITH NO PROBLEMS NOTED, A TEST FLIGHT WAS COMPLETED AND ANOTHER INSPECTION OF THE ENGINE REVEALED NO PROBLEMS. THE AC WAS RETURNED TO SERVICE. (TC NR 20071218001) 1 L 7 1 3O 3 I NT TA4CH EXPE3I 5 C TP5BO 2008022500147 20080225 00147 CE 2008 2 25 CA071218002 1 20071214 G 7110 10191011947 VANE BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL RT INTAKE DUCT DEBONDED W K NONE O OTHER IN INSP/MAINT 1 CA 744 (CAN) ON THE RT ENGINE COWLING INTAKE DUCT THERE IS A VANE ASSY TO REDIRECT INTAKE AIRFOW. THE VANE ASSY WAS FOUND TO HA VE DEBONDED ITSELF FROM THE ATTACH BRACKETS. THE VANE WAS ALSO CRACKED COMPLETELY ALONG THE TRAILING EDGE AND A 4 INCH C RACK LOCATED ON THE LT SIDE LEADING EDGE OF THE VANE. IT LOOKS LIKE POOR WELDING AND BONDING WERE THE CAUSE OF FAILURE. (TC NR 20071218002) 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 2008022500149 20080225 00149 NE 2008 2 25 CA071218003 2 20071217 G 7320 78639110 HMU DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ENGINE UNSERVICEABLE W E ENGINE SHUTDOWN F FLT CONT AFFECTED AP APPROACH 1 CA 26832 120644 (CAN) NR2 ENGINE EXPERIENCED AN IN FLIGHT SHUTDOWN, SHORT FINAL (500FT AGL) AND WAS IN ECU MODE. CREW DID NOT HAVE THE T IME TO TRY MANUAL MODE. AS THEY WERE FEATHERING THE ENGINE (PROPELLER), THEY NOTICED THE TORQUE INCREASING, AS IT HIT AR OUND 90 PERCENT AND THE CREW SHUT THE ENGINE DOWN. FDR WAS REMOVED AND YYC AVIONICS SHOP HAS BEEN RESERVED TO READ THE FDR. ANALYSIS OF THE FDR INDICATES THAT THERE IS AN UNCOMMANDED INPUT OF FUEL TO NR2 ENGINE. THERE IS NO INDICATION THA T THE PROPELLER IS OVER TORQUED AND IS THEREFORE SERVICEABLE FOR FURTHER USE. THE FOLLOWING MAINTENANCE ACTIONS WERE CAR RIED OUT: NR2 HMU CHANGED. NR2 ENGINE RIGGING CHECK CARRIED OUT FROM THE COCKPIT OUT TO THE ENGINE. NR 2 SPRING STRUT I 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008022500151 20080225 00151 CE 2008 2 25 CA071218004 1 20071217 G 3246 WHEEL CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE MLG DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON PILOTS WALK AROUND THEY FOUND METAL AROUND NOSE WHEEL TIRE. AIRCRAFT WAS TOWED INTO A HEATED HANGER AND PILOT P HONED MAINTENANCE . ENGINEER JACKED NOSE WHEEL AND INSPECTED NOSE WHEEL SPIN-UP KIT AND FOUND LT TURBINE AND LT SPIN-UP COVER WERE DAMAGED. REMOVED NOSE WHEEL SPIN-UP KIT AND INSTALLED ANOTHER TIRE/WHEEL ASSY AND RETURNED AIRCRAFT TO SERVIC E (TC NR 20071218004) 1 L 7 2 4F 4 F A22CE E1NE 2008022500152 20080225 00152 NE 2008 2 25 CA071218005 2 20071216 G 7261 SEAL AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF5 NE NR 1 ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA PCE120670 (CAN) AFTER DEPARTURE AND ENROUTE TO DESTINATION, THE CREW OBSERVED A LOW OIL PRESSURE WARNING LIGHT AND NOTED FLUCTUATI NG OIL PRESSURE ON THE NR 1 ENGINE. THE ENGINE WAS SHUTDOWN AND RESTARTED IAW THE OPERATING PROCEDURES MANUAL, THE OIL P RESSURE WAS NOTED TO BE NEAR ZERO. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT INCIDENT. NO EMERGENCY WAS DECLARED. MAINTENANCE DETERMINED THAT THE NR 1 GENERATOR SEAL FAILED RESULTING IN THE LOSS OF OIL FROM THE NR 1 ENG INE. (TC NR 20071218005) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008022500153 20080225 00153 SW 2008 2 25 CA071218006 1 20071214 G 5610 2719442004 WINDSHIELD SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE COCKPIT CRACKED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 4884 (CAN) UPON ENGINE START AND TAXI THE F/O HEATED WINDSCREEN CRACKED. THE GLASS CRACKED FROM THE BOTTOM UP. THE CREW TURNE D AROUND AND SHUTDOWN. MAINT REMOVED AND REPLACED THE WINDOW. OUR COMPANY CONTINUES TO HAVE PROBLEMS WITH THESE HEATED W INDSHIELDS AND IN SPEAKING WITH OTHER OPERATORS IN THE RECENT PAST THEY HAVE HAD SIMILAR FAILURES OF THESE WINDSHIELDS. MOST OF THE FAILURES ARE IN FLIGHT FAILURES. THE TOTAL TIME ON THE WINDSHIELD WAS DETERMINED TO BE 4884.1 BUT MAY BE SLI GHTLY HIGHER AS THIS WINDSHEILD WAS INSTALLED ON THE AC PRIOR TO PURCHASE. REGARDLESS OF TOTAL TIME THE FAILURE MODE OF THESE WINDOWS IS A SAFFTY CONCERN. (TC NR 20071218006) 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 2008022500155 20080225 00155 EA 2008 2 25 CA071218007 1 20071214 G 5320 CA447 SHROUD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE BS 559 CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 29474 (CAN) DURING HEAVY CHECK INSP, THE FUEL DISTRIBUTION PRESSURE BOX ASSY, P/N 601R62676-5 WAS FOUND CRACKED AND BOTH THE F UEL SHROUD AND FUEL LINES HAVE CHAFFING DAMAGE BEYOND LIMITS. THESE COMPONENTS ARE LOCATED AT FUSELAGE STATION FS559. P ARTS ARE ON ORDER AND DAMAGED FUEL SHROUD AND THE FUEL BOX WILL BE REPLACED BEFORE AIRCRAFT IS RELEASED FROM HEAVY CHECK . NOTE:- PLEASE REFER TO PREVIOUS SDR NR 20071005001 (TC NR20071218007) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500156 20080225 00156 EU 2008 2 25 CA071218008 1 20071213 G 2560 22719TK060052X PIN SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE SEAT BELT LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE PROCESS OF AN ICC FOLLOWING HEAVY MAINT, THE ENGINEER NOTICED THAT THE RETAINING PIN P/N 22719TK060052X FOR THE PILOT`S SEAT BELT OB FITTING WAS LOOSE OR ABOUT TO FALL OUT OF THE FLOOR SUPPORT. UPON INVESTIGATION IT WAS FOU ND THAT THE RIVET THAT NORMALLY HOLDS THE SEAT BELT PIN IN PLACE HAD BEEN REPLACED, POSSIBLE DURING A VERTICAL REFERRENC E WINDOW INSTALLATION. THE RIVET WAS REPLACED WAS BUCKED TO THE NORMAL SIZE IAW STANDARD PRACTICES AND DID NOT PROTRUDE LONG ENOUGH TO HOLD THE PIN IN PLACE. UPON NOTICING THIS OCCURANCE WE CHECKED (4) OTHER AIRCRAFT ON SITE AND FOUND 2 MOR E WITH THE SAME PROBLEM. IN THE IPC 53.10.20.000 (04-06) PAGE 02.00 FIGURE 1 SHOWS THE PIN AS DRILLED AT THE END MAYBE 1 G 7 1 3U 3 U H9EU E19EU 2008022500157 20080225 00157 NM 2008 2 25 CA071219001 1 20071216 G 3234 6131001001 SELECTOR VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, LANDING GEAR SELECTOR LEVER SELECTED UP, BOTH LT AND RT MAIN GEAR DOOR CAUTION LIGHTS ILLUMINATED, BOTH MAIN GEARS FAILED TO RETRACT BUT NOSE GEAR HAD RETRACTED. AC RETURNED TO BASE FOR FURTHER INVESTIGATION. FLIGHT SN AG COULD BE DUPLICATED ON GROUND. DURING TROUBLESHOOTING AND REMOVAL OF THE MLG SELECTOR VALVE, IT WAS NOTICED THAT FILT ER HAD SEPARATED IN VALVE CAUSING BLOCKAGE. (TC NR 20071219001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008022500159 20080225 00159 NE 2008 2 25 CA071219002 2 20071218 G 7230 BRH20419 BLADE RROYCE BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE HP COMPRESSOR FAILED W O OTHER R PARTIAL RPM/PWR LOSS AP APPROACH 1 CA 1744 M33121 (CAN) ENGINE SURGE ON LANDING. ENGINE RETURNED TO SHOP FOR SUSPECTED HPC STG 1 BLADES DAMAGE. DURING ENGINE DISSASEMBLY HPC ROTOR WAS FOUND WITH HEAVY DAMAGE, SUSPECT DAMAGE CAUSED BY A BLADE FAILURE AT PLATFORM. ALL FAILED PARTS WILL BE RE TURNED TO THE OEM FOR INVESTIGATION. (TC NR 20071219002) 2 L 7 2 4F 4 F TR A6WE E00061EN 2008022500160 20080225 00160 NE 2008 2 25 CA071219003 2 20071219 G 7250 FW35594 TURBINE BLADES BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE ENGINE FAILED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 8994 (CAN) ENGINE WILL BE INDUCTED IN JANUARY, 2008 FOR INVESTIGATION FOR HPT STG 1 BLADE FAILURE. BLADES WERE FITTED NEW AT LAST SHOP VISIT AT 14773 CYCLES. SUSPECT FAILURE SIMILAR TO PREVIOUS SDR SUBMITTED 20070911004, 20071001001. FURTHER DE TAILS WILL BE SUBMITTED AT ENGINE DISASSEMBLY. (TC NR 20071219003) 2 L 7 2 4F 4 F TR A6WE E00061EN 2008022500161 20080225 00161 NE 2008 2 25 CA071219004 2 20071219 G 7250 FW35544 TURBINE BLADES BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE ENGINE FAILED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 7723 (CAN) ENGINE CURRENTLY IN SHOP FOR REPAIR DUE TO HP 1 TURBINE BLADE FAILURE, ENGINE DISASSEMBLY REVEALED FAILURE OF BLAD E AT PLATFORM. FAILED PART WILL RETURNED TO THE OEM FOR INVESTIGATION. PREVIOUS SDR RAISED FOR SAME EVENT 2007091104, 20 071001001,20071219003. ENGINES SHOP VISITS DOCUMENTATIONS HAS BEEN REQUESTED BY THE OEM FOR ALL SIMILAR EVENT FOR THE IN VESTIGATION (TC NR 20071219004) 2 L 7 2 4F 4 F TR A6WE E00061EN 2008022500162 20080225 00162 NE 2008 2 25 CA071219005 2 20070905 G 8530 127599 SCREW DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE INTAKE ROCKER SEVERED W K NONE O OTHER IN INSP/MAINT 1 CA 869 (CAN) DURING AN UNRELATED INSPECTION, THE INTAKE VALVE ROCKER ARM ADJUSTMENT SCREW (127599) WAS FOUND SEVERED INSIDE THE LOCKING JAM NUT. POSSIBLE METAL FATIGUE. (TC NR 20071219005) 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2008022500164 20080225 00164 EA 2008 2 25 CA071219006 1 20071217 G 5414 SKIN CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE NACELLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 29474 (CAN) BOTH THE LT AND RT REPAIR DOUBLERS THAT ARE IDENTIFIED AS ITEM -1 ON THE ATTACHED REO601R-53-61-358, REVISION A, W ERE FOUND CRACKED DURING AN INSPECTION OF THE ENGINE SUPPORT BEAMS AT A HEAVY CHECK VISIT. THIS AC CAME INTO OUR AIRLIN E OPERATION AT APPROX 20859 CYCLES. WE ARE UNABLE TO CONFIRM THE EXACT TIME THIS REPAIR WOULD HAVE BEEN INCORPORATED ON THIS AC. WE HAVE CONTACTED THE MFG TECHNICAL HELP DESK WITH OUR FINDING AND ARE AWAITING FURTHER REPAIR INSTRUCTIONS FR OM THEM. (TC NR 20071219006) 2 L 7 2 4F 4 F RT A21EA E15NE 20080520 CE 2008 5 20 CA071219008 1 20071213 G 2497 AAPA4CHAFED WIRE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL NR 2 BUS BAR CHAFED W O OTHER O OTHER CR CRUISE 1 CA (CAN) DURING CRUISE FLIGHT ALL (3) BUS, NR 2 CIRCUIT BREAKERS POPPED AND THE STANDBY POWER CIRCUIT BREAKER ON BUS, NR 2 POPPED. THE AC LANDED WITHOUT FURTHER INCIDENT. UPON ARRIVAL MAINT PERSONNEL INSPECTED THE WIRING ON THE DISTRIBUTION PA NEL AND FOUND WIRE AAPA4 CHAFED TO THE NR 2 BUS BAR. THE CHAFED WIRE WAS REPAIRED IAW STANDARD PRACTICES AND THE AC WAS GROUND RUN AND CHECKED SERVICEABLE. (TC NR 20071219008) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2008022500167 20080225 00167 NM 2008 2 25 CA071219009 1 20071218 G 3230 535201 SEQUENCE VALVE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MLG MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 28240 925 (CAN) THE GEAR WAS SELECTED UP, IT RETRACTED NORMALLY. THROUGH 2000 FT THUMPING NOISE IN NOSE WAS HEARD FOLLOWED BY AN A MBER LIGHT IN THE SELECTOR KNOB FLASHING ON. OCCASIONALLY A RED NOSE GEAR LIGHT CAME ON. MAINT REPLACED NLG DOOR WARN P ROX SWITCH AND SWAPPED THE NOSE GEAR SEQ VALVE RELAY WITH THE RT MLG DOOR SEQ VALVE. AFTER FURTHER T/S IT WAS SUSPECTED THAT MLG SELECTOR HANDLE WAS AT FAULT. AT THIS TIME THE MLG SELECTOR HANDLE WAS REPLACED FOR T/S AND WILL UPDATE FURTHER WHEN AVAILABLE. GEAR SWINGS WERE C/O WITH THE NEW SELECTOR HANDLE AND THE A/C WAS CHECKED SERVICEABLE. (TC NR 20071219 009) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008022500169 20080225 00169 WP 2008 2 25 CA071219010 2 20071214 G 7261 31081331 TUBE BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33110UG 01514 WP MCAULY 4HFR34 4HFR34C652 NE ENGINE OIL CHAFED W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA P63333 (CAN) DURING A SCHEDULED FLIGHT BETWEEN, A WARNING INDICATION OF OIL PRESSURE LOSS ON THE NR 1 ENGINE APPEARED ON THE AN NUNCIATOR PANEL. THE CREW VERIFIED THE WARNING BY OBSERVING THE OIL PRESSURE GAUGE. THE ENGINE WAS SHUTDOWN AND AN EMERG ENCY WAS DECLARED. THE CREW LANDED THE AC WITHOUT INCIDENT. UPON INSPECTION IT WAS FOUND THAT THE STEEL TUBE BETWEEN THE PROPELLER GOVERNOR AND A T-FITTING WAS LEAKING FROM THE FLARED END WHERE IT ATTACHED TO THE T-FITTING. THE TUBE WAS REP LACED WITH A NEW ONE AND HIGH POWER GROUND RUNS WERE PERFORMED. NO LEAKS WERE PRESENT. THE OIL WAS CLEANED FROM THE ENGI NE COMPARTMENT AND THE AC RETURNED TO BASE. DURING REPLACEMENT OF THE TUBE IT WAS NOTED THAT IT HAD BEEN CHAFFING ON AN 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C 3PNE 2008022500170 20080225 00170 NM 2008 2 25 CA071220001 1 20071219 G 3297 GROUND STUD DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE MLG LOOSE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 39432 39432 (CAN) AFTER SELECTING GEAR UP, LT AND RT MAIN GEAR DOOR AMBER WARNING AND NLG RED WARNING. GEAR SELECTED DOWN AND NORMAL EXTENSION, AFTER GEAR DOWN (AMBER) NLG LIGHT REMAINED ILLUMINATED. MAINT INSPECTION/ TROUBLE SHOOTING REPLACED LANDING GEAR SELECTOR VALVE AND NLG DOOR SEQUENCE VALVE, DURING GEAR SWINGS GEAR FAILED TO RETRACT AFTER SECOND CYCLING . FURTHE R INVESTIGATION FOUND NLG DOOR SEQUENCE VALVE GROUND STUD (WIRE DIAGRAM 32-30-00 SHEET 4 OF 4 PAGE 1 WIRE IDENTIFIER 93A 22N , STUD IDENTIFIER 3251-GS-1) LOOSE. STUD LOCATED ON BULKHEAD FWD OF FWD PRESSURE BULKHEAD. STUD TIGHTENED, GEAR SWIN GS COMPLETED SUCCESSFULLY. AC RETURNED TO SERVICE. (TC NR 20071220001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008031900170 20080319 00170 EU 2008 3 19 CA071220002 2 20071108 G 7320 057610E000201 ECU THIELT DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE12502114 EU FADEC MALFUNCTIONED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA 608 3544 (CAN) DURING FLIGHT TRAINING MANEUVERS, SIMULATED SINGLE ENG OPS AT 5000 FT ASL, THE LT ENGINE WAS THROTTLED BACK TO FLI GHT IDLE (5 PERCENT PWR, THROTTLE RETARDED). UPON RETURN TO NORMAL PWR OPS THE LT ENG BEGAN TO SURGE FROM 20-100 PERCEN T PWR, REGARDLESS OF THROTTLE POSITION, ENG WAS UNCONTROLLABLE. THE LT ENGINE FADEC WAS SELECTED FROM ECU A TO ECU B AN D CONTROL OF LT ENGINE WAS REGAINED. THE AC RETURNED TO DEPARTURE AND LANDED WITHOUT FURTHER INCIDENT. MAINT ACTIONS: DISCREPANCY COULD NOT BE DUPLICATED DURING GROUND TESTS. LT ENGINE OPERATED NORMALLY ON BOTH ECU A AND ECU B OF THE LT F ADEC. LT HAD FADEC REPLACED AND AC RELEASED FOR TEST FLIGHT. NO FURTHER ENG SURGING NOTED. (TC NR 20071220002) 1 L 7 2 3I 3 B RT A57CE E00069EN 20080520 CE 2008 5 20 CA071220004 1 20071215 G 2910 AE2463531G0460 HOSE CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE HYDRAULIC PUMP CRACKED W O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA (CAN) ALL GEARS DOWN AND LOCK WITH (3) GREEN LIGHTS. WHEN PILOT SELECTED FLAPS DOWN, LT HYD FLOW LIGHT COMES ON AND FOL LOW THE RT SIDE. FINALLY, HYD FLUID LEVEL LIGHT COMES ON. AC LANDED SAFELY WITH NO HYD SYS AVAILABLE. FOUND LT ENG HYD PRESSURE HOSE CRACKED. BOTH HYD PRESSURE HOSE REPLACED WITH AE2463531G0460 ON LT SIDE AND AE2463531G0226 ON RT AND BOTH ENG DRIVEN HYD PUMP REPLACED WITH 9912062-4. HYD FILTER INSPECTED AND REPLACED WITH NEW FILTER KIT CPDPHF-1. FUNCTIONAL CHECK C/O AND AC RETURN TO SERVICE. (TC NR 20071220004) 2 L 7 2 4F 4 F RT A22CE E25EA 2008022500172 20080225 00172 EU 2008 2 25 CA071221001 1 20071219 G 2997 WIRE SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE HYD CONTROL INCORRECT W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 2076 (CAN) DURING AN AC CONVERSION IAW SB 01.00.50 THE HYD CONTROL WIRE WAS FOUND NOT CRIMPED PROPERLY IN SPLICE CONNECTOR. WIRE DH5E PULLED OUT OF SPLICE DURING HANDLING. WIRE CONNECTOR SHOW NO SIGN OF PROPER CRIMP. THE INSTALLATION OF THIS SPLICE IS MANDATED BY EASA AD F-2004-089 (ASB 29.00.07). WIRE CONNECTION FAILURE RENDERS THE PILOT UNABLE TO PERFORM EM ERGENCY PROCEDURES LISTED IN THE FLIGHT MANUAL SECTION 3.3 (HYD FAILURE) AND SECTION 3.1 PARA 5 (TAIL ROTOR CONTROL FAI LURE) THE LACK OF PROPER CRIMPING WAS ALSO FOUND ON AC. (TC NR 20071221001) 1 G 7 1 3U 3 U NC H9EU E19EU 2008022500174 20080225 00174 NE 2008 2 25 CA071221002 2 20071209 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE SEIZED W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CL CLIMB 1 CA 17384 (CAN) SHORTLY AFTER TAKEOFF, CREW FELT VIBRATION FOLLOWED BY AN INDICATION OF LOW OIL PRESSURE. AC LANDED IN A FIELD AW AY FROM THE DEPARTURE POINT AND CREW SHUTDOWN ENGINE. POST FLIGHT INSP REVEALED THAT NEITHER ENGINE ROTOR COULD BE TURN ED AND THE OIL FILTER AND CHIP DETECTORS WERE CONTAMINATED BY DEBRIS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADV ISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071221002) 1 H 7 1 3T 3 T A37CE E4EA 2008022500175 20080225 00175 NE 2008 2 25 CA071221003 2 20071212 G 7532 31J285704 MOTOR CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE BLEED VALVE DEFECTIVE W E ENGINE SHUTDOWN E F J VIBRATION/BUFFET FLT CONT AFFECTED WARNING INDICATION DE DESCENT 1 CA DD0323 (CAN) VIBRATION, (RUMBLE) AND EEC REVERSION WAS EXPERIENCED DURING DESCENT. THE CREW ELECTED TO PERFORM AN INFLIGHT SHUT DOWN OF THE ENGINE AND CONTINUE TO DESTINATION. TROUBLESHOOTING REVEALED A DEFECTIVE BLEED VALVE TORQUE MOTOR CAUSING TH E COMPRESSOR SURGES/STALLS. THE UNIT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC 20071221003) 2 L 7 2 4F 4 F RT A22CE E00059EN 2008022500176 20080225 00176 EU 2008 2 25 CA071221004 1 20071212 G 7930 OIL SYSTEM AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE ENGINE LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 127176 (CAN) DURING CRUISE, THE CREW OBSERVED FLUCTUATIONS IN THE OIL PRESSURE, FOLLOWED BY A DROP TO ZERO. THE ENGINE WAS SHUT DOWN ACCORDINGLY. TROUBLESHOOTING IS ONGOING, MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE E STABLISHED (TC NR 20071221004) 2 H 7 2 4T 4 T RT E20NE 2008022500177 20080225 00177 NE 2008 2 25 CA071221005 2 20071214 G 7200 ENGINE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION AP APPROACH 1 CA 1140211142 (CAN) DURING FINAL APPROACH, THE LOW OIL PRESSURE WARNING ACTIVATED. THE CREW SHUTDOWN THE ENGINE. POST FLIGHT INVESTIGA TION REVEALED THAT THE ENGINE ROTORS WERE DIFFICULT TO TURN AND THAT METAL SHAVINGS WERE DEPOSITED ON THE OIL FILTER. TH E ENGINE IS BEING SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTA BLISHED (TC NR 20071221005) 2 L 7 2 4T 4 T RT A24CE E26NE 2008022500181 20080225 00181 NE 2008 2 25 CA071221006 2 20071217 G 7200 ENGINE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE SEIZED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 123019 (CAN) OPERATOR REPORTED THAT THERE WAS AN INFLIGHT SHUTDOWN OF THE ENGINE AND THAT POST FLIGHT INSPECTION REVEALED THAT THE POWER TURBINE ASSY COULD NOT BE ROTATED. NO OTHER DETAILS PROVIDED AT THIS TIME. MFG WILL CONTINUE INVESTIGATING TH E EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071221006) 2 H 7 2 4T 4 T RT A13NM E20NE 2008022500182 20080225 00182 NE 2008 2 25 CA071221007 2 20071202 G 7250 TURBINE BLADES CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE ENGINE DISTRESSED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA PC503 (CAN) OPERATOR REPORTED (TECHNICAL PROBLEMS) WHICH RESULTED IN A FORCED LANDING ON A PUBLIC MOTORWAY. INITIAL INVESTIGAT ION REVEALED COMPRESSOR TURBINE BLADE DISTRESS. THE ENGINE IN BEING RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE P ROVIDED WHEN AVAILABLE. (TC NR 20071221007) 1 H 7 1 3T 3 T A37CE E4EA 2008022500183 20080225 00183 NE 2008 2 25 CA071221008 2 20071216 G 7261 ENGINE AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF5 NE LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 120670 (CAN) DURING CLIMB, THE OIL PRESSURE STARTED TO FLUCTUATE AND THE LOW OIL PRESSURE WARNING WAS ACTIVATED. THE CREW SHUT THE ENGINE DOWN AND RETURNED TO THE POINT OF ORIGIN. 5 MIN PRIOR TO LANDING, THE ENGINE WAS RE-STARTED AND ALL PARAMETER S WERE NORMAL EXCEPT THAT THERE WAS NO OIL PRESSURE INDICATION AND THE LOW OIL PRESSURE WARNING. THEY KEPT THE ENGINE R UNNING TILL LANDING. POST FLIGHT INSP REVEALED THAT THE OIL TANK WAS EMPTY AND A SIGNIFICANT OIL LEAK WAS OBSERVED AT TH E STARTER GENERATOR PAD. THE ENGINE WILL BE REMOVED AND SENT FOR REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT A ND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071221008) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008022500184 20080225 00184 EA 2008 2 25 CA071221009 2 20071129 G 7261 FITTING DHAV DHC8 DHC8* NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU ENGINE OIL LOOSE W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA FA0302 (CAN) DURING CRUISE, THE OIL PRESSURE WAS OBSERVED TO DECREASE AND AND A WARNING SOUNDED. THE ENGINE WAS SHUTDOWN AND TH E AC RETURNED TO BASE. INITIAL INVESTIGATION REVEALED AN AIRFRAME SUPPLIED OIL COOLER HOSE FITTING HAD PULLED FREE OF TH E ENGINE AND CAUSED A MASSIVE LEAKAGE. THE ENGINE HAS BEEN REMOVED AND WILL BE SENT FOR INVESTIGATION. MFG WILL CONTINU E INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20071221009) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008022500185 20080225 00185 NE 2008 2 25 CA071221010 2 20071129 G 7250 TURBINE BLADES BEECH 99 C99 1154006 CE PWA PT6 PT6A36 52043 NE ENGINE DAMAGED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 38152 (CAN) DURING CRUISE A LOUD BANG WAS HEARD AND ENGINE OPERATION CEASED WITHOUT CREW INVOLVEMENT. POST FLIGHT INPECTION D ISPLAYED COMPRESSOR AND POWER TURBINE BLADE DAMAGE. THE COMPRESSOR ROTOR IS SEIZED THE ENGINE WILL BE REMOVED AND FORWAR DED TO MFG FOR INVESTIGATION. UPDATES WILL BE PROVIDED WHEN AVAILABLE. (TC NR 20071221010) 1 L 7 2 3T 4 T A14CE E4EA 2008022500186 20080225 00186 NM 2008 2 25 CA071221011 1 20071215 G 7712 SIGNAL COND UNIT DHAV DHC8 DHC8* NM PWA 120 PW123D 52152 NE ENGINE TORQUE MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA AG0044 (CAN) TAKEOFF WAS ABORTED DUE TO NOISES SIMILAR TO ENGINE SURGE OR PROPELLER MALFUNCTION. INSPECTION REVEALED THAT THE E NGINE HAD REACHED 136 PERCENT TORQUE FOR A PERIOD LESS THAN 20 SECONDS. THE PROPELLER, TORQUE PROBE AND TORQUE SIGNAL CO NDITIONER WERE REPLACED. ROOT CAUSE HAS NOT BEEN ESTABLISHED. UPDATES WILL BE PROVIDED WHEN AVAILABLE. (TC NR 2007122101 1) 2 H 7 2 4T 4 T RT A13NM E20NE 2008022500187 20080225 00187 NE 2008 2 25 CA071221012 2 20070820 G 7250 TURBINE BLADES PWA PW120 PW127 NE ENGINE CLOGGED W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA (CAN) THIS SDR IS BEING RAISED TO ADVISE OF A QUALITY ESCAPE REPORTED. DUE TO THE USE IMPROPER MATERIALS AND PROCEDURES, THE COOLING PASSAGES OF SOME HP TURBINE BLADES WERE INADVERTANTLY BLOCKED BY BLASTING MEDIA DURING THE CLEANING PROCESS AT SHOP VISIT. THESE BLADES WERE THEN INSTALLED ON A NR OF ENGINES AND RELEASED TO THE FIELD FOR SERVICE. THERE HAVE B EEN (2) CASES OF THESE BLADES SUBSEQUENTLY FRACTURING IN SERVICE DUE TO OVERHEATING, ENGINES AV0063 AND 120308. HAVE A CKNOWLEGED THE QUALITY ESCAPE AND TAKING REMEDIAL ACTION TO ADDRESS OTHER AFFECTED ENGINES. WILL BE ADVISED OF FURTHER OCCURANCES IN THE FIELD. (TC NR 20071221012) 4 T E20NE 2008022500188 20080225 00188 NM 2008 2 25 CA071222001 1 20071222 G 5315 146A75032 FLOORBEAM BOEING 737 737790 13844CN NM BS 767 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR SUPPORT RAIL AT BS 767+5 RBL 3 FOUND CORRODED DURING CPCP INSPECTION. LEVEL 2 CORROSION. REPAI RED IAW CUSTOMER E.A. (TC NR 20071222001) 2 L 7 2 4F RT A16WE 2008022500189 20080225 00189 NM 2008 2 25 CA071222002 1 20071222 G 5315 146A75031 FLOORBEAM BOEING 737 737790 13844CN NM BS767 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR SUPPORT RAIL AT BS 767+14, LBL 3 FOUND CORRODED DURING CPCP INSPECTION. LEVEL 2 CORROSION. REP AIRED IAW CUSTOMER EA. (TC NR 20071222002) 2 L 7 2 4F RT A16WE 2008022500190 20080225 00190 NM 2008 2 25 CA071222003 1 20071222 G 5320 146A75035 FLOOR SUPPORT BOEING 737 737790 13844CN NM BS767 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR SUPPORT RAIL AT BS 767+5, LBL8 FOUND CORRODED DURING CPCP INSPECTION. LEVEL 2 CORROSION. REPAI RED IAW CUSTOMER EA. (TC NR 20071222003) 2 L 7 2 4F RT A16WE 2008022500191 20080225 00191 NM 2008 2 25 CA071222004 1 20071222 G 5315 141A550519 FLOORBEAM BOEING 737 737790 13844CN NM BS 344 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PASSENGER CABIN FLOORBEAM AT BS 344, RBL4 TO LBL56 FOUND CORRODED DURING CPCP INSPECTION. LEVEL 2 CORROSION. REPAI RED IAW CUSTOMER EA. (TC NR 20071222004) 2 L 7 2 4F RT A16WE 2008022500193 20080225 00193 NM 2008 2 25 CA071222005 1 20071222 G 5315 147A55048 FLOORBEAM BOEING 737 737790 13844CN NM BS 947 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CABIN FLOORBEAM AT BS 947, LBL53 FOUND CORRODED DURING CPCP INSPECTION. LEVEL 2 CORROSION FOUND. REPAIRED IAW CUSTOMER EA. (TC NR 20071222005) 2 L 7 2 4F RT A16WE 2008022500194 20080225 00194 WP 2008 2 25 CA071224001 1 20071223 G 2897 WIRE1544 WIRE HARNESS ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE AUX FUEL PUMP CHAFED W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA (CAN) AC HAD AN INTERMITTENT PROBLEM WITH ITS FUEL PUMP WARNING LIGHT. INTERMITTENTLY THE AUX FUEL PUMP WARNING LIGHT WO ULD FLICKER ON AND OFF AT APPROX. 60 PERCENT BRIGHTNESS DURING A LONG FLIGHT. AN ENGINEER CHANGED THE AUX FUEL PUMP AND THE FUEL PRESSURE SWITCH. THE PROBLEM DID NOT REOCCUR DURING TESTING. HOWEVER, THE AC WAS BROUGHT BACK TO BASE TO ENSURE THERE WAS NO OTHER PROBLEM. UPON FURTHER INSPECTION, FOUND ONE OF THE WIRES FOR THE FUEL PUMP WAS CHAFING ON A VENT TUB E NEAR THE FIREWALL. REPLACED A SECTION OF WIRE AND COVERED IT IN SPIRAL WRAP, TO PREVENT CHAFING IN THE FUTURE. (TC NR 20071224001) 1 G 7 1 3O 3 O H11NM 1E4 2008022500195 20080225 00195 EU 2008 2 25 CA071224002 1 20071213 G 2710 AILERON BRAERO DH125 HS125700A 4230170 EU GARRTT TFE731 TFE7313R1H 29001 WP ICED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 9523 (CAN) PILOT’S REPORTED ON APPROACH INTO AIRPORT, COULD NOT GET ANY ROLL ON AC CONTROLS. IT APPEARED THAT AILERONS WERE F ROZEN. SHORTLY BEFORE TOUCHDOWN THEY WERE ABLE TO GAIN CONTROL OF THE AILERON MOVEMENT. THE AC LANDED WITHOUT INCIDENT. MAINT WAS CALLED AND ON INSPECTION OF THE AC FOUND ICE BUILD UP ON LT AND RT AILERON HORNS, LT AND RT WINGS AND WING TIP S. SOME AREAS OF THE LEADING EDGE HAD SOME ICE BUILD UP. CHECKED AC CONTROLS AND VERIFIED CORRECT MOVEMENT. AILERON CONT ROLS OPERATED WITHOUT ANY BINDING. CONTACTED MFG AND REPORTED INCIDENT. FURTHER TROUBLESHOOTING WILL BE CARRIED OUT ON T HE AC AILERONS TO AS CERTAIN THE CAUSE OF THE AILERON FREEZING UP. (TC NR 20071224002) 2 L 7 2 4F 4 F A3EU E6WE 2008022500225 20080225 00225 NE 2008 2 25 CA071224003 2 20071220 G 7314 D74311 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE AUX FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 828 (CAN) WHILE ATTEMPTING TO START THE AIRCRAFT, THE AUX FUEL PUMP FAILED TO RUN. FURTHER INVESTIGATION REVEALED THE PUMP A ND AUX FUEL PUMP PRESSURE SWITCH (P/N B426-6) HAD FAILED. PUMP AND SWITCH WERE REPLACED AND NO FURTHER DEFECTS WERE NOTE D. (TC NR 20071224003) 1 G 7 1 3O 3 O H11NM 1E4 2008022500226 20080225 00226 NM 2008 2 25 CA071224004 1 20071219 G 7920 305726501 ADAPTER BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA LP COMPRESSOR LOOSE W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 2628 (CAN) WHILE INVESTIGATING AN OIL LEAK, DISCOVERED THAT WHEN REMOVING THE OIL COOLER LINE FROM THE LP COMPRESSOR CASE, AF TER CUTTING THE LOCKWIRE FROM 1 OF THE 3 BOLTS, THE REMAINING 2 BOLTS CAME OUT WITH THE LOCKWIRE STILL ATTACHED. BOLTS S ECURE THE OIL COOLER LINE AND ADAPTOR OIL TUBE TO THE LP COMPRESSOR. (TC NR 20071224004) 2 H 7 2 4T 4 T RT A13NM E00062EN 2008022500227 20080225 00227 EA 2008 2 25 CA071226001 1 20071222 G 3020 300013000003 ANTI-ICE VALVE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE LT NACELLE UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 7709 7709 (CAN) WHILE ENROUTE, AC DEVELOPED A COWL ANTI ICE SNAG. THE AC RETURNED TO FOR REPAIRS. MAINTENANCE FOUND THE COWL ANTI ICE VALVE TO BE AT FAULT ONCE REPLACED OPERATIONAL CHECKS WERE C/O SERVICEABLE. A/C WAS RETURNED TO SERVICE. (TC NR 200 71226001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500228 20080225 00228 EA 2008 2 25 CA071227001 1 20071224 G 2752 854D1001921 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS UNSERVICEABLE W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA (CAN) AFTER LANDING, CREW WERE UNABLE TO RETRACT FLAPS, STUCK AT 41 DEGREES. FLT CANCELLED AS A RESULT. EXPECT TO FERRY AC. CODES RETRIEVED: 1)FECU/BPSU 2)ETHER BPSU 3)WIRING, AC RETRIEVED CODES, FORWARDED TO TECH. CARRIED OUT ACTION PLAN 168 AND ALL WIRING RANG OUT OK. FLAPS WERE CYCLED 5 TIMES IN HANGAR WITH NO FAULTS NOTED. PERFORMED A LOW TEMP TORQUE C HECK OF THE ACTUATORS AND REPORT FAILED UNITS. TAIL 168 FLAP ACTUATOR FREEZE TORQUE CHECK COMPLETED AND RESULTS AS FOLLO WS: LT IB FLAP, IB ACT FAILED, C NR 5275305 LT IB FLAP, OB ACT PASSED LT OB FLAP, IB ACT FAILED, C NR 5275306 LT OB FL AP, OB ACT FAILED, C NR 5275308 RT IB FLAP, IB ACT PASSED RT IB FLAP, OB ACT FAILED, C NR 5275305 RT OB FLAP, IB ACT FA 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500229 20080225 00229 NE 2008 2 25 CA071227002 2 20071223 G 7230 355924400 SENSING ELEMENT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE 14TH STAGE DUCT CHAFED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) RT 14TH STAGE DUCT MESSAGE DURING CLIMBOUT. FLIGHT RETURNED TO AIRFIELD. MAINTENANCE INSPECTION DISCOVERED 14TH S TAGE COWL DUCT INSULATION BROKEN AND CHAFING ON SENSING LOOP. BOTH SENSING LOOP AND DUCT WERE REPLACED AND ENGINE RUN’S WERE C/O AND THE AC WAS CHECKED SERVICEABLE. (TC NR 20071227002) 2 L 7 2 4F 4 F RT A21EA E15NE 20080520 CE 2008 5 20 CA071227003 1 20071015 G 3220 NAS464P5A42 BOLT CESSNA 210 2105 2073404 CE CONT O470 IO470S 17026 SO MCAULY D3A36 D3A36C410 GL NLG DRAG STRUT BROKEN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 8203 (CAN) WHILE TAXING ON BUSH STRIP, NOSE GEAR AFT DRAG STRUT BOLT BROKE AND WORKED OUT CAUSING NOSE GEAR TO FOLD FWD. (TC NR 20071227003) 1 H 7 1 3O 3 O 3A21 3E1 5 C P47GL 20080520 CE 2008 5 20 CA071227004 1 20070909 G 5312 12128582 BULKHEAD CESSNA 206 TU206A 2073318 CE CONT O520 TSIO520C 17040 SO HARTZL HCC3Y PHCC3YF1 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5803 (CAN) CRACK IN REAR BULKHEAD PIN DURING MANDATORY NDT INSPECTION OF THE ARGA. (TC NR 20071227004) 1 H 7 1 3O 3 O A4CE E8CE 5 C P25EA 2008022500230 20080225 00230 EA 2008 2 25 CA071227006 1 20071213 G 2421 M2750010SP3U00 WIRE HARNESS CNDAIR CL600 CL600* 1900302 EA GE CF34 CF348E5A1 30062 NE RAT CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 15541 (CAN) DURING INCORPORATION OF SB601-0591 (SPECIAL CHECK/MODIFICATION AIR-DRIVEN GENERATOR SYS REPLACEMENT OF CHAFING AD G POWER FEED WIRE) FOUND THE WIRING CHAFED BARE AND CLAMPS BURNED AFT OF THE FWD PRESSURE BULKHEAD AT THE FIRST STANDOFF AFT OF THE FEED THROUGH AT APPROX FS 210. WIRES HAVE BEEN REPLACED IAW SB601-0591 INSTRUCTIONS. (TC NR 20071227006) 2 L 7 2 4F 4 F RT A21EA E00063EN 2008022500232 20080225 00232 GL 2008 2 25 CA071227007 2 20071218 G 7261 6793065 CAP ALLSN 23035102 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL OIL PUMP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA SER26317 (CAN) DURING ROUTINE INSPECTION AND FILTER CHANGE, A CRACK AROUND THE EAR OF THE CAP WAS NOTED. THE STUD WAS ALSO STRIPP ED. MFG COVERED THIS TOPIC IN THEIR CSL-1251. TORQUEING IS THE POSSIBLE CAUSE FOR THIS DEFECT, THE LETTER RECOMMENDS 30- 40 LBS-IN. IT IS IMPORTANT TO FOLLOW MFG PROCEDURES IN ASSEMBLY AND REPAIR. (TC NR 20071227007) 1 G 7 1 3U 3 U H3WE E4CE 2008022500233 20080225 00233 EA 2008 2 25 CA071227008 1 20071220 G 3260 895304 PSEU CNDAIR CL600 CL600* 1900302 EA GE CF34 CF348C5 30050 NE MLG FAILED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 2275 (CAN) A/C EXPERIENCED A PROX SYS FAULT DURING CLIMB OUT MESSAGE BECAME INTERMITTENT AFTER 8-10 MINUTES. FLIGHT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. MAINT REPLACED THE PSEU AND CHECKED THE SYS THROUGH THE MFG SERVICEABLE. GEAR SWING S C/O, NFF. A/C RETURNED TO SERVICE. (TC NR 20071227008) 2 L 7 2 4F 4 F RT A21EA E00063EN 2008022500235 20080225 00235 EU 2008 2 25 CA071228001 1 20071224 G 7603 7898435010 ECU AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE POWER LEVER FAILED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) POWER LEVER SPLIT AT HIGH POWER SETTINGS. FAULT ISOLATED TO FAULTY LT ENGINE ECU. ECU REPLACED. TESTED SERVICEABLE . (TC NR 20071228001) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008022500237 20080225 00237 EA 2008 2 25 CA071228002 1 20071227 G 2421 720845E IDG CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE NR 2 DAMAGED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION NR NOT REPORTED 1 CA 3922 3922 4258 (CAN) AT ALTITUDE CREW RECEIVED AN IDG CAUTION MESSAGE. THE NR 2 IDG WAS DEFERRED UNTIL MAINT COULD BE ACCOMPLISHED. AC WAS BROUGHT TO THE HANGER TO HAVE REPAIRS C/O, REMOVAL OF THE IDG REVEALED THAT THE INTERNAL SHAFT OF THE IDG PUNCHED TH ROUGH THE OUTER CASING AND METAL SHAVINGS COLLECTED AT BOTTOM OF IDG/AGB MATING FLANGE PLUGGING DRAIN HOLE. ALL METAL DE BRIS WAS CLEANED FROM THE FLANGE AND DRAIN AND NEW CARBON SEAL AND IDG INSTALLED AND CHECKED SERVICEABLE. (TC NR 2007122 8002) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500238 20080225 00238 2008 2 25 CA071228003 4 20071227 G 8300 3008779 COLLAR DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL ACCESSORY G/B DISLODGED W K NONE O OTHER IN INSP/MAINT 1 CA PCE40510 (CAN) DURING AN ENGINE NR 2 SCHEDULE OIL CHANGE WHILE REMOVING OIL AT THE ACCESSORY GB DRAIN PLUG PORT HOLE, A METALLIC COLLAR HALF (P/N 3008779) FELL OUT. SUSPECTED THAT THIS COLLAR HALF HAD FALLEN OFF THE SCAVENGE OIL PUMP DRIVESHAFT. EN GINE REMOVED FROM AIRCRAFT AND SENT TO MFG FOR INVESTIGATION. (TC NR 20071228003) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2008022500239 20080225 00239 EA 2008 2 25 CA071231001 1 20071228 G 2750 855D10011 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS UNSERVICEABLE W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA (CAN) FLAP FAIL ON APPROACH. FLAP ZERO APPROACH AND LANDING CARRIED OUT. FLIGHT LANDED WITHOUT FURTHER INCIDENT. RT FLAP BRAKE SENSOR UNIT, SKEW DETECTION UNIT AND RT OB FLEX DRIVE SHAFT REPLACED. FLAP SYS FUNCTION CHECKED SERVICEABLE. (TC NR 20071231001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500240 20080225 00240 SO 2008 2 25 CA071231002 1 20071228 G 3397 2067081 CONNECTOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA CONTROL PANEL BURNED W O OTHER O OTHER CR CRUISE 1 CA (CAN) STROBE CB POPPED AND WILL NOT RESET. FAULT T/S TO DAMAGED WIRE IN RT WING. WIRE (L161FF) REPLACED IAW AC43-13-1B A ND SECURED. WIRES FOR AILERON TRIM, STALL WARNING, POSITION LIGHTS AND FUEL QUANTITY SENDERS DISTURBED. ALL CONNECTIONS OF THESE SYSTEMS WERE RETERMINATED AND OPERATION CHECKED OK. DURING T/S CONNECTOR E312(TAXI AND LANDING LIGHTS) IN THE O VERHEAD PANEL WAS NOTED DAMAGE. (SEVERAL BURNED PINS) INSULATION TEST OF THE SYS CARRIED OUT AND ADDITIONAL DAMAGE FOUND AT CONNECTOR E302. BOTH CONNECTORS REPLACED AS REQUIRED. TAXI AND LANDING LIGHT LINES MEGGERED OUT WITH NO FURTHER FAUL TS INDICATED. SYSTEM OPN TESTED SERVICEABLE. (TC NR 20071231002) 1 L 7 2 3O 3 O A20SO E14EA 2008022500253 20080225 00253 NM 2008 2 25 CA080102004 1 20071227 G 3310 LAMP DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE COCKPIT LIGHTS BURNED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) SIDEWALL LAMP HOLDER AT SEAT AREA 3DF FOUND BURNED WHILE TROUBLESHOOTING SAME POSITION. DEFECT FOUND DURING LAND S ERVICE CHECK. LAMP HOLDER/BALLAST ASSY REPLACED. (TC NR 20080102004) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008022500254 20080225 00254 CE 2008 2 25 CA080102005 1 20071231 G 5420 10191001641 COVER BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCD4N3 HCD4N3A GL NACELLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FOUND EXHAUST SOOT IN COWLS. CLOSER INSPECTION FOUND THE BUTTERFIELD STC COVER PLATE LEAKING AND THE HEATED INLET CRACKED IN MULTIPLE LOCATIONS ON BOTH COWLS. (TC NR 20080102005) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2008022500257 20080225 00257 EA 2008 2 25 CA080102007 1 20071230 G 2150 A/C PACK CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE RIGHT SMOKE W A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA (CAN) (AC RETURNED TO THE FIELD DUE TO SMOKE TOILET WARNING. THERE WAS A HAZE IN THE CABIN. THEY DECLARED AN EMERGENCY) FOUND THAT THE RT PACK WAS SMOKING UP THE CABIN. DEFERRED THE RT PACK. ADDITIONAL INFORMATION REQUESTED TO THE FSR, A C STILL UNDER MMEL (TC NR 20080102007) 2 L 7 2 4F 4 F RT A21EA E15NE 20080522 SW 2008 5 22 CA080102008 1 20071227 G 2612 3219027001 MODULE FRCHLD 2782797001 FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE FIRE EXTINGUISH DAMAGED W E A ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 5472 (CAN) DURING CLIMB-OUT THE PILOTS NOTICED THE ENGINE FIRE DETECTION INDICATION LIGHT CAME ON. THE ENGINE WAS SHUTDOWN AN D THE ENGINE FIRE EXTINGUISHING BOTTLE WAS ACTIVATED. THE PILOTS DECLARED AN EMERGENCY, LANDED SAFELY AT THE AIRPORT OF ORIGIN AND EVACUATED THE AIRCRAFT. NO ENGINE FIRE WAS OBSERVED. MAINTENANCE INSPECTED THE FIRE EXTINGUISHING SYSTEM AND FOUND THAT THE FIRE LOGIC CONTROL BOX HAD HEAT DAMAGE AT AN ELECTRICAL CONNNECTOR. (TC NR 20080102008) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2008022500258 20080225 00258 NE 2008 2 25 CA080103001 2 20071224 G 7414 E06KA245 MAGNETO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INOPERATIVE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 224 (CAN) AFTER ROUTINE START ENGINE RPM AND OR GOVENOR BEGAN TO HUNT. PROBLEM PERSISTED EVEN AFTER ENGINE WARMED UP. ENGINE SHUTDOWN AND RT MAGNETO REPLACED. GROUND RUN CARRIED AND NO DEFECTS FOUND WITH NEW MAGNETO. (TC NR 20080103001) 1 G 7 1 3O 3 O H11NM 1E4 2008022500259 20080225 00259 WP 2008 2 25 CA080103004 1 20071223 G 2910 D2121 SERVO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE HYD SYSTEM LEAKING W K NONE K J FLUID LOSS WARNING INDICATION IN INSP/MAINT 1 CA 1213 (CAN) DURING A POST FLIGHT INSPECTION THE HYDRUALIC SERVO WAS FOUND LEAKING AT THE PILOT VALVE. SERVO CHANGED AND LEAK C ARRIED OUT SERVICEABLE. (TC NR 20080103004) 1 G 7 1 3O 3 O H11NM 1E4 2008022500261 20080225 00261 CE 2008 2 25 CA080103005 1 20071228 G 7797 8975294 WIRE HARNESS GARRTT TPE3316252 BEECH 100 100BEECH 1152916 CE GARRTT TPE331 TPE3316252B 01514 WP HARTZL HCB4T HCB4TN5 GL ENGINE FAILED W E ENGINE SHUTDOWN N FALSE WARNING TX TAXI/GRND HDL 1 CA 1000 P27038 P27038 (CAN) AFTER A STOPOVER THE AIRCREW WENT TO START THE NR 2 ENGINE, AT THIS TIME IT WAS NOTED THAT THE ITT GAUGE WAS NOT W ORKING. MAINTENANCE PERSONNEL FLEW TO THE AIRCRAFT LOCATION AND THROUGH TROUBLESHOOTING DETERMINED THAT THE ITT HARNESS HAD FAILED. A FERRY PERMIT WAS USED TO RETURN THE AIRCRAFT BACK TO THE MAIN BASE. ENGINE WAS REMOVED AND A NEW HARNESS I NSTALLED. (TC NR 20080103005) 1 L 7 2 3T 4 T A14CE E2WE 6 C P40EA 2008022500262 20080225 00262 EA 2008 2 25 CA080103006 2 20071227 G 7414 BL6006163 MAGNETO ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ENGINE UNSERVICEABLE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 961 (CAN) ENGINE WOULD NOT START. LT MAGNETO FOUND UNSERVICEABLE. MAGNETO CHANGED, GROUND RUN AND FUNCTIONAL CHECKS CARRIE D OUT SERVICEABLE. (TC NR 20080103006) 1 G 7 1 3O 3 O H11NM E295 2008022500264 20080225 00264 WP 2008 2 25 CA080103008 1 20071222 G 8011 COVER ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE STARTER LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 173 (CAN) DURING A 50/100 HOUR INSPECTION, THE STARTER COOLING COVER WAS FOUND LOOSE. THE 3 SCREWS HOLDING IT IN PLACE HAD L OOSENED OFF. THE STARTER WAS REPLACED, GROUND RUN CHECKED SERVICEABLE. (TC NR 20080103008) 1 G 7 1 3O 3 O H11NM 1E4 20080520 CE 2008 5 20 CA080104002 1 20071229 G 7603 SL60112SL6011 KNOB CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL POWER LEVER SEPARATED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 6101 6101 (CAN) (2) KNOBS ON EITHER SIDE OF THE POWER LEVER ARE USED TO RAISE A GATE TO ALLOW REVERSE THRUST. THE KNOBS ARE SCREWE D TOGETHER. DURING FLIGHT THE KNOBS SEPARATED (UNSCREWED) AND FELL OFF. THIS ALLOWED THE GATE TO PIVOT IF THE POWER LEVE R WAS RETARDED ALLOWING THE ENGINE/PROP TO ENTER THE REVERSE MODE OF OPERATION. (TC NR 20080104002) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2008022500266 20080225 00266 EU 2008 2 25 CA080104003 1 20071231 G 6410 355A12003114 TRIM TAB SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE TAIL ROTOR UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 3104 (CAN) WHILE PERFORMING A BRIDGING INSPECTION ON AN A/C PREVIOUSLY LEASED TO A DIFFERENT COMPANY, AD 2007-0138-E WAS BEIN G C/O. SECTION OF MISSING PAINT NOTED ON AREA REQUIRING INSPECTION IAW ASB 05-00.40( IB ATTACHMENT POINT OF T/E TAB). A CRACK WAS NOTED THROUGH VISUAL INSP, AND THE T/R ASSY REMOVED FROM A/C FOR FURTHER EVALUATION. AD HAD BEEN SIGNED OUT BY PIC PRIOR TO PERFORMING FERRY FLIGHT TO OUR BASE. T/R ASSY WAS INSTALLED ON THIS AIRCRAFT 19.7 HRS PRIOR TO DISCOVERY O F DEFECT. BLADE ASSY SENT TO MFG FOR FURTHER EVALUATION (TC NR 20080104003) 1 G 7 1 3U 3 U H9EU E19EU 2008031900172 20080319 00172 EA 2008 3 19 CA080105001 1 20071224 G 2497 VS643 RELAY CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE ELECTRICAL PWR FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) UPON ARRIVAL, GROUND PWR APPLIED TO AC BUT SHUTOFF IMMEDIATELY. GROUND PWR RESTARTED AND AFTER ABOUT A MINUTE CREW NOTED NUMEROUS CIRCUIT BREAKERS POPPED, HEARD A LOUD BANG FROM THE NOSE SECTION AND A LIGHT SMELL OF SMOKE IN THE COCKP IT. CIRCUIT BREAKERS POPPED INCLUDED CENT TRU 1, NAV LIGHTS, TRU 1, TRU2, STCU, TRU SERVICE, SENSOR TOILET, CEILING LIGH TS, SIDEWALL LIGHTS AND STAB CHAN HSTCU. MAINT TROUBLESHOOTING, TRACED FAULT TO AN AC SERVICE BUS FAULT. PWR SENSE RELAY K5XD ( P/N VS-643) IN JB6 REPLACED (SHORTED WIRING ALSO REPAIRED). NUMEROUS OTHER PARTS REPLACED DUE TO DOWN LINE FAILU RES. ( HSTCU P/N 7060-10, S/N 213.) LT AND RT WINDSHIELD HEAT CONTROLLERS P/N 601R59006-5, S/N’S 5131 & 3475(SOME BURNE 2 L 7 2 4F 4 F RT A21EA E15NE 2008031900174 20080319 00174 2008 3 19 CA080106002 4 20071228 G 3418 501177003 ACTUATOR CNDAIR CL600 CL6002D24 1390016 EA GE CF34 CF348C5B1 30052 NE STICK PUSHER FOD W O OTHER F FLT CONT AFFECTED LD LANDING 1 CA (CAN) THE CABLE RUNS HAVE BEEN INSPECTED IN THE FWD ELECTRONICS BAY AND THE FWD QUADRANTS HAVE BEEN INSPECTED AND NO DEF ECTS NOTED. THE FWD PULLEYS AND CABLES WERE LUBED AND AC SENT FOR A TEST FLIGHT. IN ALL OTHER MODES OF FLIGHT THE AC OPE RATES NORMALLY. ONLY ON LANDING WHEN THE PILOTS HAVE FLARED THE NOSE UP AND THE MLG HITS THE GROUND DOES IT SEEM TO LOCK UP PREVENTING THE PILOTS FROM PRESSING THE NOSE DOWN TO LAND. WITH THE AC ON THE GROUND AND THE PITCH DISCONNEC TED YOU CAN FEEL WHAT IS DESCRIBED AS A ROUGH SPOT IN THE FO’S YOKE AS YOU MOVE HALF WAY FROM FULLY AFT TO CTR AND HALF WAY FROM CENTER POSITION TO FULLY FWD POSITION. PROBLEM WAS SOLVED BY REPLACING THE STICK PUSHER ASSY. STICK PUSHER WAS 2 L 7 2 4F 4 F RT A21EA E00063EN 2008032000005 20080320 00005 NE 2008 3 20 CA080108001 2 20071218 G 7261 SUMP CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE NR 1 ENGINE LEAKING W C ABORTED TAKEOFF B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TO TAKEOFF 1 CA (CAN) SMOKE CARGO MESSAGE SHORTLY AFTER T/O AND ODOR OF SMOKE ON FLIGHT DECK. LANDED, & TAXI TO PARKING AND DEBARKING O F PAX, CABIN INSPECTED BY FIRE BRIGADE. CABIN CREW REPORTED NO SMOKE IN CABIN AND TOILET DURING FLT AND TAXI BACK. DURIN G TROUBLESHOOTING, FOUND A-SUMP OIL LEAK ON ENGINE NR 1. A-SUMP CARBON SEAL NR 1 AND NR 3 ON ENGINE NR 1 ON WING ACC. SE I 756 SPECIAL PROCEDURE 41 REPLACED. INSP AND ENGINE RUNS SATISFACTORY. NO MORE SMOKE OBSERVED. REF OS WO 5524048. AIRCR AFT RELEASED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 20080520 CE 2008 5 20 CA080108008 1 20071217 G 3230 55275042 VALVE SEAT CESSNA 55275042 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE UPLOCK ACTUATOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 6025 (CAN) WHEN PRESSURE IS APPLIED TO THE UPLOCK ACTUATOR THE ACTUATOR MUST TRAVEL FULL STROKE BEFORE ALLOWING FLUID TO THE GEAR ACTUATOR. IN THIS ACTUATOR THE DAMAGED SEAT ALLOWED FLUID TO THE GEAR ACTUATOR BEFORE THE UPLOCK HAD RELEASED THE G EAR. WE HAVE HAD A COUPLE INCIDENTS WHERE THE GEAR WOULD NOT EXTEND WHEN THE GEAR ACTUATOR APPLIED DOWN FORCE TO THE GE AR BEFORE THE UPLOCK COULD RELEASE AND THE UPLOCK COULD NOT OVERCOME THE FORCE. UPLOCK ACTUATOR WAS REPLACED. (TC NR 200 80108008) 1 L 7 2 4F 4 F A22CE E1NE 20080520 NE 2008 5 20 CA080109007 2 20071227 G 7261 MS955610 BOLT EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE PUMP LOOSE W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) AC WAS ON MONITOR FOR LOW OIL QTY SNAGS SINCE THE 21ST OF DEC. TODAY (27TH) ALL OF THE EDP MIDDLE CASING BOLTS WER E FOUND LOOSE. CMM 29-12-10, ITEM 300: BOLT P/N MS9556-10 AND ITEM 305: WASHER NAS620C10L. (TC NR 20080109007) 2 L 7 2 4F 4 F RT A57NM E00070EN 2008022500274 20080225 00274 NM 2008 2 25 CA080110004 1 20070831 G 2913 6617303 PUMP BOMBDR DHC8 DHC8400 NM HYD SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1497 (CAN) MFG HAD ISSUED SB 84-29-15A/ SB 66173-29-349 DUE TO LEAKING OF THE ENGINE DRIVEN HYD PUMP. THE SB WAS CARRIED OUT ON THE ABOVE MENTIONED COMPONENT AT TSN: 834.0 AND CSN OF 874. COMPONENT REMOVED DUE TO LEAKAGE IN THE FLANGE AREA THAT HAD BEEN RETORQUED IAW THE SB. HAVE ADDED THE RETORQUING OF THIS COMPONENT IAW THE ABOVE MENTIONED SB INTO THE AC MAINT PROGRAM. (TC NR 20080110004) 2 H 7 2 4T RT A13NM 2008022500275 20080225 00275 CE 2008 2 25 CA080110005 1 20070108 G 7110 10191001651 COWLING BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE MCAULY 3G34C7 3GFR34C701 GL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BACK WALL OF HEATED LIP ASSY FOUND CRACKED. DEFECT INTRODUCES HOT EXHAUST GASES INTO COWL ASSY, CONTAMINATING ENG INE INTAKE, CABIN PRESSURIZATION, ENGINE CONTROL, AIR. DEFECT CAUSES INCREASED CORROSION OF COWL ASSY. DEFECT IS DIFFI CULT TO SEE UPON INSP DUE TO LOCATION. (TC NR 20080110005) 1 L 7 2 4T 4 T A24CE E4EA 5 C P60GL 2008032000008 20080320 00008 EU 2008 3 20 CA080114004 1 20071212 G 2497 WIRE GROB 120 G120A 1660208 EU ALTERNATOR CHAFED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 632 (CAN) ALTERNATOR CB POPPED IN FLIGHT WITH MINOR SMELL OF SMOKE. AC RETURNED TO BASE WITHOUT FURTHER INCIDENT. MAINT FOU ND THE ALTERNATOR PWR WIRE HAD CHAFED THROUGH THE OIL COOLER HSG AND GROUNDING CONTACT WAS MADE THROUGH CARBON FIBER LOW ER COWLING AND HARDWARE ATTACH POINTS SEVERING THE GROUND CABLE FROM THE ALTERNATOR. THIS WAS THE THIRD INCIDENT (FOR FL EET) INVOLVING THE ALTERNATOR WIRES MAKING CONTACT WITH THE OIL COOLER SHROUD. MFG ADDRESSED THE PROBLEM BY ISSUING SB 1 121-093, WHERE THE ALTERNATOR WIRES WERE SHORTENED AND SECURED AWAY FROM THE OIL COOLER SHROUD. (TC NR 20080114004) 1 L 7 1 3O RT A49CE 2008030600220 20080306 00220 EA 2008 3 6 CA080115011 1 20071217 G 2910 AE4186G0210000 LINE CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF343A1 30068 NE HYDRAULIC SYS RUPTURED W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 CA 4495 (CAN) PRESSURE LINE ON NR 3A PUMP RUPTURED AND SYS FLUID WAS LOST. GEAR WAS ALTERNATELY EXTENDED AND LANDED WITHOUT INCI DENT. THE HOSE WAS REPLACED AND THE AC WAS FERRIED. THE GEAR WAS SWUNG AND THE HYDRAULICS BLED, TESTED SERVICEABLE. THER E ARE CURRENTLY NO LIFE LIMIT ON THESE LINES. (TC NR 20080115011) 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600222 20080306 00222 NE 2008 3 6 CA080116004 2 20071220 G 7200 ENGINE AEROSP ATR42 ATR42500 8680948 EU PWA PW120 PW127 NE MAKING METAL W E A ENGINE SHUTDOWN UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CL CLIMB 1 CA AM0076 (CAN) VIBRATION WAS FELT ACCOMPANIED BY 3 LOUD NOISES AND FIRE WARNING. ENGINE WAS SHUTDOWN AND AC RETURNED TO POINT OF DEPARTURE. POST FLIGHT INSPECTION REVEALED NO EVIDENCE OF FIRE, HOWEVER PROPELLER COULD NOT BE ROTATED AND THE TURBOMACH INE CHIP DETECTOR WAS FOUND TO BE HEAVILY CONTAMINATED WITH METALIC DEBRIS. MFG WILL CONTINUE INVESTIGATING THE EVENT AN D ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080116004) 2 H 7 2 4T 4 T RT A53EU E20NE 2008030600223 20080306 00223 NE 2008 3 6 CA080116005 2 20071212 G 7200 ENGINE AEROSP ATR42 ATR42500 8680948 EU PWA PW120 PW127 NE SHUTDOWN W E ENGINE SHUTDOWN J WARNING INDICATION NR NOT REPORTED 1 CA AM0110 (CAN) CREW ELECTED TO SHUTDOWN ENGINE DURING FLIGHT DUE TO LOW/NO OIL PRESSURE INDICATION. ENGINE WAS SUBMITTED TO REPA IR SHOP FOR INVESTIGATION AND REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISH ED (TC NR 20080116005) 2 H 7 2 4T 4 T RT A53EU E20NE 2008030600225 20080306 00225 NE 2008 3 6 CA080116008 2 20071220 G 7200 FITTING AGUSTA A109 A109E 0260119 EU PWC PW206C PW206C NE P3 CONTAMINATED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA BC0503 (CAN) DURING CRUISE, THE ENGINE POWER DECREASED UNCOMMANDED TO IDLE SETTING, FOLLOWED BY LOSS OF OIL PRESSURE. THE CREW ELECTED TO SHUTDOWN THE ENGINE AND RETURN TO BASE. INVESTIGATION FOUND THE P3 FITTING TO BE CONTAMINATED WITH FOREIGN DE BRIS. FITTING AND SYS WAS CLEANED AND THE AC RETURNED TO SERVICE. (TC NR 20080116008) 1 G 7 2 3U 3 U RT H7EU E42NE 2008030600227 20080306 00227 NE 2008 3 6 CA080116010 2 20071221 G 7200 ENGINE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE MALFUNCTIONED W E ENGINE SHUTDOWN J B WARNING INDICATION SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 114478114162 (CAN) DURING CRUISE, THE MASTER CAUTION ILLUMINATED AND ENGINE SURGES WERE NOTED FOLLOWED BY LOSS OF POWER AND OIL HAZE IN THE CABIN. THE CREW ELECTED TO SHUT THE ENGINE DOWN. THE ENGINE IS TO BE RETURNED TO MFG FOR INVESTIGATION, UPDATES T O FOLLOW. (TC NR 20080116010) 2 L 7 2 4T 4 T RT A24CE E26NE 2008030600228 20080306 00228 NE 2008 3 6 CA080116011 2 20071226 G 7320 FUEL CONTROL CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE ENGINE INOPERATIVE W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION AP APPROACH 1 CA JC0550 (CAN) DURING APPROACH, THE ENGINE DID NOT RESPOND TO THRUST LEVER INPUTS AND REMAINED AT IDLE. AFTER LANDING GROUND TEST S INDICATED THAT THE ENGINE WOULD NOT ACCELERATE ABOVE 46 PERCENT, N2. THE FUEL CONTROL WAS REPLACED AND AIRCRAFT RETURN ED TO SERVICE. (TC NR 20080116011) 2 L 7 2 4F 4 F RT A22CE E25EA 2008030600229 20080306 00229 NE 2008 3 6 CA080116012 2 20071231 G 7320 FUEL CONTROL CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE ENGINE MALFUNCTIONED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION AP APPROACH 1 CA DB0324 (CAN) DURING APPROACH AT 3000 FEET, THE LOW FUEL FLOW WARNING CAME ON, FOLLOWED BY ENGINE SHUTDOWN. THE FUEL CONTROL HAS BEEN REMOVED AND SUBMITTED FOR INVESTIGATION. UPDATES WILL BE PROVIDED WHEN AVAILABLE. (TC NR 20080116012) 2 L 7 2 4F 4 F RT A22CE E00059EN 2008030600230 20080306 00230 EU 2008 3 6 CA080116013 1 20071230 G 7931 OIL SYSTEM AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE ENGINE LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA EB0078 (CAN) DURING CRUISE, THE ENGINE OIL PRESSURE FLUCTUATED INTERMITTENTLY, THEN DROPPED DURING DESCENT. THE CREW ELECTED TO SHUTDOWN THE ENGINE. ENGINE IS TO BE INVESTIGATED BY MFG, UPDATES TO FOLLOW. (TC NR 20080116013) 2 H 7 2 4T 4 T RT E20NE 2008030600233 20080306 00233 EA 2008 3 6 CA080116016 2 20071126 G 7250 TURBINE BLADES DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA ENGINE FRACTURED W C E D ABORTED TAKEOFF ENGINE SHUTDOWN RETURN TO BLOCK R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA PG0179 (CAN) DURING TAKEOFF ROLL, THE ENGINE LOST POWER. TAKEOFF WAS ABORTED AND AC RETURNED TO THE RAMP. INVESTIGATION BY MFG REVEALED FRACTURED COMPRESSOR TURBINE BLADES AND A FRACTURED FUEL BYPASS LINE. (TC NR 20080116016) 1 H 7 2 3T 4 T RT A9EA E4EA 2008030600235 20080306 00235 NM 2008 3 6 CA080116018 1 20071225 G 4920 STARTER PWC BOEING 747 747400 13848AT NM APU ACC G/B FAILED W F ACTIVATE FIRE EXT. B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TX TAXI/GRND HDL 1 CA 900077 (CAN) WHILE DEPLANING PASSENGERS, AN OIL SMELL WAS NOTED IN THE CABIN ACCOMPANIED BY A FIRE WARNING. THE FIRE BOTTLES WE RE DISCHARGED. THE ENGINE WAS REMOVED AND SENT FOR INVESTIGATION. INITIAL INSP INDICATES A MALFUNCTION OF THE STARTER MO TOR LEADING TO ACCESSORY GEARBOX DISTRESS. UPDATES WILL BE PROVIDED AS AVAILABLE. (TC NR 20080116018) 2 L 7 4 4F RT A20WE 2008032400427 20080324 00427 GL 2008 3 24 CA080116019 2 20071230 G 7230 23064613 IMPELLER ALLSN BELL 407 407 1182206 SW ALLSN 250C 250C47B GL COMPRESSOR SATURATED W O OTHER K FLUID LOSS LD LANDING 1 CA 5708 CAC44047 (CAN) AFTER UNEVENTFUL AND NORMAL SHUTDOWN, PILOT NOTICED A POOL OF OIL UNDER THE AC AND OIL ALL OVER THE ENGINE COWLS A S WELL AS SOAKING THE IB .2500 OF THE MAIN ROTOR BLADES. THERE WERE NO OIL TEMP OR PRESSURE CAUTION WARNINGS OR ENGINE C HIP LIGHT INDICATIONS. TO THE PILOT SHUTDOWN WAS NORMAL AND PLANNED, EXCEPT FOR A NOTICEABLE ODOR IN THE COCKPIT. SUBSE QUENT INSP SHOWED OIL EMANATING FROM COMPRESSOR FRONT SUPPORT AREA WITH OIL DISCHARGING FROM BLEED VALVE (VENTED INTO EX HAUST COLLECTOR) AND COMPRESSOR VENT. INITIALLY SUSPECTED NR1 BEARING OIL SEAL FAILURE OR CRACK IN THE COMPRESSOR FRONT SUPPORT OIL PRESSURE/RETURN STRUT. ENGINE SERVICE TECH WAS CALLED IN TO DISASSEMBLE AND REPLACE THE FRONT SUPPORT OR SEA 1 G 7 1 3U 3 U O H2SW E1GL 20081104 CE 2008 11 4 CA080121006 1 20071218 G 3222 0543011 CAP CESSNA 172 172D 2072410 CE CONT O300 O300D 17022 SO NLG STRUT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3346 (CAN) DURING ANNUAL INSP OF THE NOSE GEAR ASSY AND OLEO, THE OLEO CAP WAS FOUND TO BE CRACKED. THE CRACK WAS LOCATED .18 75 IN FROM THE RADIUS OF THE END FLANGE. THE CAP WAS FOUND TO BE BROKEN THROUGH AND WAS REMOVED IN 2 PIECES. REVIEW OF T HE TECHNICAL RECORDS INDICATED THAT THE ACFT HAD BEEN SUBJECT TO SIGNIFICANT DAMAGE LATE IN 1979 AT 2479.9 HRS TTAF. (TC NR 20080121006) 1 H 7 1 3O 3 O NT 3A12 E253 20081105 2008 11 5 CA080122006 1 20071107 G 7810 PN2031 COLLECTOR NAVION STC STCNAVION CONT E185 E1853 17014 SO HARTZL HC12V HC12V20* GL EXHAUST DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FOUND WHEN CF90-03R2 WAS DONE. THERE WERE NO VISIBLE SIGNS OF EXHAUST LEAKS. WHEN PRESSURE TESTED WITH AIR AND SOA PY WATER, 4 LEAKS WERE EVIDENT. IT HAS BEEN STANDARD PRACTICE IN THIS AMO TO DO SOAPY WATER TESTS ONLY. OVER THE LAST 8 TO 10 YEARS WE HAVE FOUND 4 OR 5 EXHAUST UNITS THAT SHOW NO VISIBLE SIGNS OF LEAKS, BUT FAIL THE SOAPY WATER TEST. ALL W ERE LEAKS AROUND EXISTING WELDS. ONE CRACK THAT STARTED MY POLICY OF SOAPY WATER ONLY TESTING, WAS ALONG THE EDGE OF A W ELDED PIPE. THAT CRACK WAS ABOUT .6250 INCH LONG. THERE WERE NO SIGNS OF LEAKS. IT WAS THE RATHER SURPRISED RESPONSE FRO M MY TC. THAT PROMPTED THIS REPORT. THE QUESTION IS, HOW MANY OTHERS ARE OUT THERE THAT PASS THE VISUAL TEST, BUT FAIL T 1 L 7 1 3O 3 O A782 E246 5 C P46GL 2008022000037 20080220 00037 CE 2008 2 20 CA080122011 1 20071225 G 2497 WIRE BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL DC GENERATOR CHAFED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) MAINT HAD TROUBLESHOT A GENERATOR PROBLEM. THE GENERATOR WOULD GO OFF LINE OCCASIONALLY. REPLACED PC CARD, REPLAC ED THE GENERATOR. THE PROBLEM WAS GONE FOR 3 WEEKS. IT RETURNED, MAINT REPLACED THE PC CARD, WITH A HARD FAULT. TESTED S ERVICEABLE. NEXT MORNING ON TAXI THE GENERATOR FAILED AGAIN. DISCOVERED A WIRE FROM THE PC CARD TO THE GENERATOR BUS TIE RELAY CHAFED IN THE NACELLE. THE BUNDLE WAS PROPERLY SECURED AND PROTECTED, HOWEVER, THE ONE WIRE WAS ON THE EDGE OF TH E BUNDLE AND CHAFED ON A RIVET HEAD. REROUTED THE BUNDLE, SPLICED THE WIRE AND RETURNED THE AC TO SERVICE. (TC NR 200801 22011) 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 2008022000038 20080220 00038 CE 2008 2 20 CA080122012 1 20071128 G 3610 13182E40600 TUBE BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL BLEED AIR LEAKING W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) CREW REPORTED A BLEED AIR FAIL ANNUCIATOR IN FLIGHT. TROUBLESHOOT AND FOUND A PIN HOLE IN THE BLEED AIR WARNING LI NE. HOLE WAS NOT CAUSED BY A BLEED AIR LEAK, NOR BY MECHANICAL DAMAGE. LINE WAS ADEQUATELY SUPPORTED AND NO CHAFING WAS EVIDENT. SPLICED IN REPAIR SECTION IAW MFG SIRM AND TESTED SERVICEABLE. SECOND AC TO HAVE A FALSE FAILURE RECENTLY. (TC NR 20080122012) 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 2008022000041 20080220 00041 EU 2008 2 20 CA080123004 1 20071009 G 6220 704A33633208 SPHERICAL STOP SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE MAIN ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5209 (CAN) PROTRUDING RUBBER FOUND COMING OUT, IN THE MIDDLE OF STOP. (TC NR 20080123004) 1 G 7 1 3U 3 U H9EU E00054EN 2008022000042 20080220 00042 EU 2008 2 20 CA080123005 1 20071009 G 6220 350431182703 FREQ ADAPTER SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE MAIN ROTOR HEAD BLISTERED W K NONE O OTHER IN INSP/MAINT 1 CA 5208 (CAN) ON INSP OF MAIN ROTOR HEAD AT THE END OF THE DAY ENGINEER FOUND BLISTERS ON THE SIDE OF ONE FREQUENCY ADAPTER. BLI STERS WHERE FOUND TO BE BEYOND LIMITS: REPLACED ALL (3) ADAPTERS. (TC NR 20080123005) 1 G 7 1 3U 3 U H9EU E00054EN 2008022000076 20080220 00076 SO 2008 2 20 CA080128003 1 20070527 G 2912 460635 FILTER PIPER PA42 PA42720 7104212 SO PWA PT6 PT6A61 52043 EA HARTZL HCB3T HCB3TN3 GL HYD SYSTEM CRACKED W O OTHER K FLUID LOSS LD LANDING 1 CA 10144 (CAN) DURING APPROACH TO LANDING, FLIGHT CREW EXPERIENCED DIFFICULTY EXTENDING THE LANDING GEAR VIA NORMAL MEANS AND SUB SEQUENTLY MANUALLY LOWERED THE GEAR. INVESTIGATION SHOWED SUBSTANTIAL HYD FLUID LOSS THROUGH CRACKED THREADS OF THE LT E NG HYDR FILTER BOWL. MAINT TO REPLACE THE DAMAGED BOWL WITH NEW, AND TO OVERHAUL THE HYDR PUMPS AND FLUSH THE HYD SYS PR IOR TO FURTHER FLIGHT. (TC NR 20080128003) 1 L 7 2 4T 4 T A23SO E4EA 6 C P15EA 2008022000077 20080220 00077 SW 2008 2 20 CA080128006 1 20071215 G 6320 214040118001 BEARING BELL 205040001101 BELL 205 205A1 1181414 SW LYC T53 T5317BLYC 41616 NE TRANSMISSION MAKING METAL W O OTHER J WARNING INDICATION CR CRUISE 1 CA ABT00760 (CAN) TSO OF THE TRANSMISSION ASSY 1186.6 HOURS. THE AC HAD TAKEN OFF AND WAS IN CRUISE WHEN A TRANSMISSION METAL DETEC TOR LIGHT ILLUMINATED. THE PILOT LANDED AC BACK AT CAMP FOR THE ENGINEER TO INVESTIGATE THE DEFECT. THE BEARING IS AN O N CONDITION BEARING. THE MAST ASSY AND TRANSMISSION ASSY WERE REMOVED. THE COMPONENT SHOP FOUND THAT THE TRANSMISSION INPUT TRIPLEX BEARING, P/N 214-040-118-001, WAS THE FERROUS METAL MAKER. THE MAST BEARING WAS ALSO INSPECTED AND NO DEF ECT WAS FOUND. (TC NR 20080128006) 1 G 7 1 4U 4 U H1SW E17EA 2008031900183 20080319 00183 SW 2008 3 19 CA080204006 1 20070614 G 2497 WIRE BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE COCKPIT SHORTED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) PILOT REPORTED SPARKS AND A SMALL AMOUNT OF SMOKE FROM THE OVERHEAD CONSOL. UPON INVESTIGATION IT WAS FOUND THAT T HE LT OVERHEAD CONSOL PANEL HAD CHAFED THROUGH SEVERAL WIRES COMING UP THE CENTER POST OF THE WINDSHIELD CAUSING THE WIR ES TO SHORT TO GROUND. AFFECTED WIRES REPLACED AND THE WIRING BUNDLE REPOSITIONED. (TC NR 20080204006) 1 G 7 1 4U 4 U H1SW E17EA 2008031900192 20080319 00192 EU 2008 3 19 CA080206007 1 20071217 G 6123 PROPELLER CASA C212 C212CC 2410204 EU PWA PW120 PW127 NE MALFUNCTIONED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS AP APPROACH 1 CA AX0043 (CAN) DURING APPROACH, CREW REPORTED TORQUE AND PROP SPEED REDUCTION. THE PROPELLER FEATHERED AND AC LANDED. TROUBLESHOO TING IS FOCUSING ON AUTOFEATHER UNIT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISH ED. INSTALLATION IS CASA 295M. FLEET PRESENTLY GROUNDED AND TROUBLESHOOTING ON HOLD DUE TO CRASH OF SISTER AC. (TC NR 2 0080206007) 2 H 7 2 4T 4 T A43EU E20NE 20081222 CE 2008 12 22 CA080207001 1 20071214 G 2160 IE502 ACTUATOR VALVE CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE HEAT EXCHANGER STICKING W C ABORTED TAKEOFF M J OVER TEMP WARNING INDICATION TO TAKEOFF 1 CA 88 88 (CAN) RT BLEED AIR OVERTEMP WARNING LITE CAME ON DURING T/O. TWICE IN 42 T/O. THE HEAT EXCHANGER VALVE WAS STICKING IN C LOSED POSITION - VALVE ACTUATOR PIN IE50-2 WAS REPLACED. 2 L 7 2 4F 4 F RT A22CE E00059EN 20081222 CE 2008 12 22 CA080207002 1 20071214 G 7830 64ND782047 ACTUATOR CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE THRUST REVERSER LEAKING W D RETURN TO BLOCK K FLUID LOSS TX TAXI/GRND HDL 1 CA 88 88 (CAN) LT THRUST REVERSER INBD ACTUATOR. WEEPING HYDRAULIC FLUID. NOTE: THIS ACTUATOR WEEPED FLUID FROM DAY ONE ON 560 S/ N 0648 HAD 2 ACTUATORS I/B LT REPLACED FOR HYDRAULIC FLUID LEAKS OVER APPROX 1800 HRS. 2 L 7 2 4F 4 F RT A22CE E00059EN 20081222 CE 2008 12 22 CA080207003 1 20070920 G 2433 RR18 CONVERTER CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL INOPERATIVE W O OTHER O OTHER NR NOT REPORTED 1 CA 69 69 (CAN) MFD FAIL TO COME ON WHEN ACFT MASTER SWITCH TURNED ON. DC-DC CONVERTER REPLACED - SAME PROBLEM OCCURED AT 102.6 AI RFRAME HRS. - 66 AIRFRAME CYLES, AND DC-DC CONVERTER REPLACED AGAIN (33 HRS + 19 CYCLES) MFG IS AWARE OF THE POOR QUALIT Y OF THE RR18 DC-DC CONVERTERS. 1 L 7 2 4F 4 F RT A1WI E3GL 20081222 CE 2008 12 22 CA080207004 1 20071005 G 3246 49290 PLUG CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE RT WHEEL LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 30 30 (CAN) TIRE/WHEEL ASSY LOOSING AIR PRESSURE. SL560XL32-19 PROVIDES IMPROVED THERMAC PLUG. PIN 542-7 WHICH WAS TO BE INSTA LLED IN THIS SERIAL NR ACFT AND WHEEL S/N- THE OLD PIN 49-290 PLUG IS MAGNETIC. THE NEW PIN 542-7 IS NO MAGNETIC. CHECKI NG OF NEW SPARE WHEEL AND BOTH ACFT MAIN WHEELS FOUND OLD PIN PLUGS INSTALLED. 2 L 7 2 4F 4 F RT A22CE E00059EN 2008031900210 20080319 00210 NM 2008 3 19 CA080208006 1 20071230 G 7160 658536912 NOSE BULLET BOEING 737 737275 1384485 NM PWA JT8 JT8D17 52049 NE ENGINE SEPARATED W A UNSCHED LANDING D R INFLIGHT SEPARATION PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) FOLLOWING DEPARTURE, THE CREW REPORTED COMPRESSOR STALLING OF THE NR 1 ENG AT CLIMB PWR. THE ENGINE PWR WAS REDUCE D AND COMPRESSOR STALLS STOPPED. THE AC RETURNED TO DEPARTURE WITH NO FURTHER INCIDENT. INSP OF THE ENGINE IDENTIFIED TH AT THE NR 1 ENGINE NOSE DOME HAD SEPARATED FROM THE ENGINE DURING FLIGHT AND MINOR DAMAGE TO THE INTAKE ACOUSTIC LINER A ND FIRST STAGE COMPRESSOR BLADES. A BOROSCOPE INSP SHOWED NO INTERNAL ENGINE DAMAGE. THE FIRST STAGE COMPRESSOR BLADES W ERE BLENDED, ENGINE INTAKE WAS REPLACED ALONG WITH THE NOSE DOME AND THE A/C WAS RETURNED TO SERVICE. (TC NR 20080208006 ) 2 L 7 2 4F 4 F A16WE E2EA 2008031900216 20080319 00216 NM 2008 3 19 CA080211016 1 20070224 G 3260 H10101534 DOWNLOCK SWITCH BOEING 727 727243 138408D NM PWA JT8 JT8D9A 52048 NE MLG FAILED W O OTHER N FALSE WARNING DE DESCENT 1 CA (CAN) DURING APPROACH INTO AIRPORT, THE LANDING GEAR WAS EXTENDED AT WHICH TIME THE NOSE GEAR UNSAFE LIGHT REMAINED ILLU MINATED AND THE DOWN AND LOCKED LIGHT REMAINED EXTINGUISHED. THE GEAR WAS RECYCLED WITH THE SAME RESULT AND SOON AFTERWA RD, THE UNSAFE LIGHT EXTINGUISHED AND THE DOWN AND LOCKED LIGHT ILLUMINATED AND THE AC LANDED WITHOUT FURTHER INCIDENT. THE GEAR UNSAFE AND DOWN AND LOCKED SWITCHES WERE REPLACED AND THE AC WAS RETURNED TO SERVICE. (TC NR 20080211016) 2 L 7 3 4F 4 F RT A3WE E2EA 20080520 SO 2008 5 20 CA080213009 1 20071101 G 2752 B5195 WORM DRIVE EMB D22466 EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL FLAP ACTUATOR STRIPPED W A UNSCHED LANDING F FLT CONT AFFECTED LD LANDING 1 CA 1872 (CAN) AFTER LANDING, THE WING FLAPS OF AN AC COULD NOT BE RETRACTED. THE ASYMMETRY WARNING SYSTEM HAD BEEN TRIPPED. THE LT AND RT FLAP ACTUATORS WERE REPLACED WITH OVERHAULED UNITS AND THE AC WAS DISPATCHED. UPON DISASSEMBLY OF THE ACTUATOR AT THE OVERHAUL SHOP THE BRASS WORM WHEEL THAT DRIVES THE SCREW JACK WAS FOUND STRIPPED. AWD 82-07-04R3 PART 2 HAD BEE N COMPLETED FEBRUARY 19, 2007. THE PART HAD ONLY 2202 CYCLES AND 1871.8 HOURS SINCE OVERHAUL AND THE ACCOMPLISHMENT OF T HE AWD. (TC NR 20080213009) 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 20080521 EA 2008 5 21 CA080213011 1 20070919 G 3250 712761 STUD DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL NLG STEERING SHEARED W O OTHER O OTHER LD LANDING 1 CA (CAN) DURING TAXI, A SNAP WAS HEARD BY THE FLIGHT CREW AND HYDRAULIC STEERING CONTROL WAS LOST. THE AC WAS TAXIED TO THE RAMP USING DIFFERENTIAL PWR AND BRAKING. THE STUD SECURING THE HYD STEERING ACTUATOR WAS FOUND SHEARED. THE NOSE GEAR ASSY WAS REPLACED AND AC WAS RETURNED TO SERVICE. THE CAUSE OF THE BROKEN STUD COULD NOT BE DETERMINED. (TC NR 200802130 11) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20080521 GL 2008 5 21 CA080214006 2 20071219 G 7250 6847100 SHAFT CVAC 440 440 2422902 WP ALLSN 501D 501D13D 03004 GL ALLSN A6441 A6441FN606 GL ENGINE DAMAGED W E F ENGINE SHUTDOWN ACTIVATE FIRE EXT. R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 445 (CAN) IN CRUISE AT 22,000 FEET, THE CREW OBSERVED A DROP IN RPM FOLLOWED BY A FIRE WARNING IN ENGINE NR1. THE FLIGHT CRE W PULLED THE (E) HANDLE AND DISCHARGED THE (2) FIRE EXTINGUISHER BOTTLES. THE FLIGHT CREW THEN PROCEEDED, AFTER DECLARIN G AN EMERGENCY. THE AC LANDED SAFELY AND NO OTHER INCIDENT REPORTED. THE COMPRESSOR AND TURBINE INTERCONNECT SHAFT AND C OUPLING FOUND DAMAGED CAUSING FREE TURBINE ROTATION. THE QEC WAS REMOVED, SPLIT, INSPECTED AND ALL THE PARTS SENT TO THE ENGINE SHOP FOR INVESTIGATION. (TC NR 20080214006) 2 L 7 2 4R 4 T 6A6 E282 6 C P898 20081230 CE 2008 12 30 CA080219003 1 20070914 G 5551 04320049 ATTACH BRACKET CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 12749 (CAN) DURING INSP OF FIN ATTACH BRACKET NUT PLATES IAW AD 80-11-04 CRACKS WERE DISCOVERED RUNNING ALONG THE BEND RADIUS OF THE WELDED BRACKET. THE AD ALLOWS FOR REMOVING REPETATIVE INSP REQUIREMENTS IF THE NUT PLATES ARE DRILLED OFF AND REP LACED WITH FIBERLOCKING NUTS. ALTHOUGH THE AD MAY NO LONGER MAY BE APPLIABLE IN SOME ACFT THE ENTIRE WELDED BRACKET SHOU LD BE INSPECTED CLOSELY EVERY 100-HRS. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 20081104 WP 2008 11 4 CA080221006 1 20071214 G 6330 369H5105 BOLT HUGHES 369 369A 4470503 WP ALLSN 250C 250C20B 03013 GL M/R TRANSMISSION CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MAIN ROTOR TRANSMISSION RECEIVED FOR OVERHAUL AFTER NDT INSPECTION 31 OF THE 32 RING GEAR BOLTS P/N 369H5105 WERE FOUND CRACKED UNDER THE BOLT HEADS. (TC NR 20080221006) 1 G 7 1 3U 3 U H3WE E4CE 200805141 20080514 1 EA 2008 5 14 CA080304008 2 20070322 G 8530 LW13622 INTAKE VALVE LYC 05K21108 PIPER PA31 PA31325 7103105 SO LYC O540 TIO540F2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE FAILED W B A EMER. DESCENT UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 136 (CAN) WHILE IN CRUISE, THE PILOT HEARD A BANG AND EXPERIENCED A LOSS IN POWER ON THE LT ENGINE. AS THE ENGINE REMAINED R UNNING AND THERE WAS NO IMMEDIATE CONCERN FOR SAFETY THE PILOT CHOSE TO LEAVE THE ENGINE RUNNING AND SET DOWN AT THE NEA REST AIRPORT. UPON EXAMINATION OF THE ENGINE IT WAS DISCOVERED THAT THE NR1 CYLINDER INTAKE VALVE HAD FAILED AT THE TIP KEEPER LOCATION. THE DECISION WAS MADE TO REMOVE THE ENTIRE ENGINE ASSY AND RETURN IT TO THE OVERHAUL SHOP DUE TO THE LO W TIME SINCE OVERHAUL (TSO). I WOULD LIKE TO MAKE NOTE THAT THE ENGINE PARTS MANUAL IS NOT CLEAR AS TO THE STYLE OF KE EPER REQUIRED FOR THE INTAKE VALVE POSITION AND, THOUGH IT WAS NOT A CONCERN IN THIS CASE, IT COULD BECOME AN ISSUE FOR 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20090102 CE 2009 1 2 CA080305006 1 20071130 G 2197 OR551 RESISTOR CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C505 GL HEATER BLOWER OVERHEATED W B EMER. DESCENT B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) RESISTOR LOCATED UNDER CO-PILOT SEAT(CONTROLS HIGH LOW OPERATION OF HEATER BLOWER MOTOR. THERE ARE 3 RESISTORS OF THE SAME TYPE IN THIS LOCATION, IN THIS CASE HEATER RESISTOR-OR55-1 OVERHEATED CAUSING THE TY-RAP LOCATED ON THE UPPER PORTION OF RESISTOR TO MELT AND CATCH FIRE, THERE IS A SMALL SHIELD OF FLAME RESISTANCE MATERIAL ON THIS TERMIAL WHICH T HE TY-RAP KEEPS IN PLACE. RECOMMEND THIS AREA BE CHECK TO THE HEAT BUILD UP OF THIS RESISTOR AS THIS WILL INDIACATE THE NEED TO BE CHANGED. RESISTOR WAS CHANGED AND THE NEW RESISTOR HL55-08-Z-1-OHM WAS FOUND AFTER A 30 MINUTE RUN THE TEMP WAS 123 FDEGREES AND THE OLD RESISTOR WAS 187F DEGRESS IN FREE AIR WITH THE SAME LOAD FACTOR,IN THE ENCLOSED SPACE I ASS 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 20080602 NE 2008 6 2 CA080305014 2 20071220 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE STOPPED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA DURING FLIGHT AT 12000 FEET ENGINE POWER WAS LOST. THE AIRCRAFT WAS FORCED TO DITCH 25 MILES OFF COAST. CREW WAS RESCU ED. INVESTIGATION REVEALED THAT THE ENGINE WAS MAKING NO POWER AT TIME OF IMPACT. THE FUEL PUMP DRIVE SHAFT REVEALED W ORN AND FRACTURED DRIVE SPLINES. INVESTIGATION IS ONGOING, UPDATES WILL BE PROVIDED. 1 H 7 1 3T 3 T A37CE E4EA 20080521 NE 2008 5 21 CA080305015 2 20071027 G 7200 ENGINE BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE FAILED W A UNSCHED LANDING E T VIBRATION/BUFFET ENGINE CASE PENETRATION AP APPROACH 1 CA (CAN) DURING APPROACH, VIBRATION WAS NOTED BY THE CREW THROUGH THE FLIGHT CONTROLS. LANDING WAS ABORTED AND AC RETURNED TO BASE. NEARING BASE, VIBRATION LEVEL INCREASED ABD CREW DECLARED AN EMERGENCY. DURING LANDING FLARE, (2) LOUD NOISES W ERE HEARD. POST FLIGHT INSP REVEALED NON-CONTAINMENT OF ENGINE POWER TURBINE SECTION HARDWARE WHICH HAD PENETRATED THE A IRFRAME DECK, COWLING AND BELLY. MFG WAS NOTIFIED OF THIS BY THE OVERHAUL AGENCY CONDUCTING THE INVESTIGATION. THE DAMA GED HARDWARE WILL BE RETURNED TO MFG FOR FURTHER ANALYSIS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080305015) 1 G 7 1 4U 4 U H4SW E22EA 20081104 EU 2008 11 4 CA080305018 1 20071017 G 2822 P94B12209 PUMP SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE FUEL BOOST FAILED W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA 162 (CAN) PILOT HAD INDICATION OF A FUEL BOOST PUMP FAILURE. ACFT PERFORMED A NORMAL PLANNED LANDING AND THE PUMP WAS SUBSEQ UENTLY REPLACED, NO FURTHER INCIDENT. (TC NR 20080305018) 1 G 7 1 3U 3 U H9EU E19EU 20080521 NE 2008 5 21 CA080305019 2 20071010 G 7310 419110003 MANIFOLD SNIAS 350 AS350B2 8680813 EU LYC LTS101 LTS101* NE FUEL SYSTEM UNSERVICEABLE W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING POST MAINT INSP GROUND RUN, A FUEL LEAK WAS DISCOVERED AT THE FUEL MANIFOLD, IT WAS DETERMINED THE MANIFOLD WAS THE CAUSE, THE PART WAS REPLACED WITHOUT FURTHER INCIDENT. (TC NR 20080305019) 1 G 7 1 3U 3 U H9EU E5NE 20081105 EU 2008 11 5 CA080318005 1 20071120 G 2916 RESERVOIR UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 3193 (CAN) THE RESERVOIR SECTION OF THE HYDRAULIC PUMP ASSEMBLY BEGAN TO LEAK HYDRAULIC FLUID. THE LEAK WAS NOTED ON A PREFLI GHT INSPECTION WHERE THERE WAS A PUDDLE OF HYDRAULIC FLUID ON THE TRANSMISSION DECK OF THE HELICOPTER. THE FLIGHT WAS CA NCELLED. THE LEAK WAS TRACED TO A LARGE PLUG WHICH IS SWAGED OR STAKED INTO THE BOTTOM OF THE RESERVOIR. THE HYDRAULIC P UMP ASSEMBLY WAS REMOVED AND IT WAS FOUND THAT THE PLUG WAS LOOSE IN THE BOSS, AND COULD ROTATE FREELY. THERE IS NO REPL ACEABLE SEAL OR METHOD TO RESEAL THE PLUG. THE HYDRAULIC PUMP ASSEMBLY WAS RETURNED TO THE MANUFACTURER. 1 G 7 2 3U 3 U NC R0001RD E34NE 20081229 2008 12 29 CA080404003 4 20070807 G 8300 2140402141 LINER BELL BELL 214 214B1 1182105 SW LYC T55 T5508D 41555 NE RGB BEARING SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA 9203 1345 (CAN) DURING THE COURSE OF A 100 HR INSP, AME FOUND A LARGE AMOUNT OF NON-FERROUS METAL PARTICLES IN THE REDUCTION GEARB OX OIL FILTER AND THE OIL DRAINED FROM THE GEARBOX. CHIP PLUG WAS INSPECTED AND FOUND CLEAN. REDUCTION GEARBOX WAS REMOV ED AND REPLACED WITH A SERVICEABLE GEARBOX. LATER TEARDOWN OF THE GEARBOX FOUND THE INPUT BEARING LINER P/N 214-040-214- 1 HAD SHEARED ITS 3 RETAINING PINS AND SPUN WITHIN THE MAGNESIUM CASE P/N 214-040-211-005. 2 G 7 1 4U 4 U H6SW E4NE 20081107 NE 2008 11 7 CA080714002 2 20070806 G 7250 304915201 TURBINE BLADES DHAV DHC8 DHC8106 2809020 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE TURBINE SECTION FRACTURED W A UNSCHED LANDING E Y VIBRATION/BUFFET ENGINE STOPPAGE CR CRUISE 1 CA 7628 (CAN) ON AUGUST 6/2007 SHORTLY AFTER TAKEOFF, MX HAD A REPORT FROM THE CREW OF A SMELL OF OIL IN THE CABIN. THIS WAS FOL LOWED BY A NR 2 ENGINE FIRE WARNING AND THE CREW PROCEEDED TO CARRY OUT THEIR SOP`S AND THE ENGINE WAS SHUT DOWN. THE AC FT PROCEEDED BACK TO YYT WHERE IT LANDED WITHOUT INCIDENT. THE ENGINE WAS REMOVED AND SENT FOR EVALUATION. IT WAS DETER MINED THAT 1 OF THE LOW PRESSURE TURBINE BLADES HAD FRACTURED AT THE BLADE ROOT. THE BLADES WERE SENT TO P&W FOR EVALUAT ION. IT WAS DETERMINED THAT 1 FRACTURED LPT BLADE AT .050 INCH FROM THE BLADE PLATFORM OCCURRED AS A RESULT OF FATIGUE O RIGINATING FROM THE TRAILING EDGE. DAMAGE TO THE REMAINING LPT BLADE AIRFOILS WAS CAUSED BY SUBSEQUENT MECHANICAL IMPACT 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081112 EU 2008 11 12 CA080729005 1 20070620 G 2913 1259A MOTOR DORNER DO228 DO228202 2992030 EU GARRTT TPE331 TPE3315251K NM HARTZL HCB4T HCB4TN5 GL HYD SYSTEM INTERMITTENT W O OTHER S AFFECT SYSTEMS NR NOT REPORTED 1 CA 1153 (CAN) UPON SELECTED GEAR DOWN NOTHING HAPPENED. PILOT THEN CYCLED THE GEAR DOWN AGAIN ALL FUNCTION NORMALLY, 3 GREEN DOW N AND LOCKED. ACFT WAS THEN INSPECTED, NO FAULTS FOUND, MAINT CREWS AND EQUIPMENT WERE FLOWN IN AND PUT A/C ON JACKS GEA R SWUNG NO FAULTS ACFT WAS THEN FLOWN BACK, FOR FURTHER TROUBLESHOOTING. AFTER SEVERAL GEAR SWING HYDR MOTOR WAS FOUND T O OPERATE INTERMITTENTLY. IT IS ALSO BELIEVED THAT COLD WEATHER POSSIBLY COULD OF HAD A INFLUENCE, BELIEVED TO BE -40. 2 H 7 2 4T 4 T RT A16EU E2WE 6 C P40EA 20081119 EA 2008 11 19 CA080805004 1 20070901 G 3070 11020140T HEAT TAPE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE WATER HEATER BURNED W K NONE M OVER TEMP IN INSP/MAINT 1 CA (CAN) THE AFT WATER SUPPLY HEATER TAPE OVERHEATED AND BURNED. INVESTIGATION REVEALED WATER HEATER WAS RUNNING WITHOUT TE MP REGULATION. HEATER WAS REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 20081112 NM 2008 11 12 CA080815008 1 20071224 G 3240 BRAKE EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE MLG STICKING W O OTHER S AFFECT SYSTEMS TX TAXI/GRND HDL 1 CA (CAN) AS REPORTED BY FLIGHT CREW: ON LANDING IAH BRAKES WORKED WELL. DURING TAXI OFF RUNWAY FELT BRAKES GRABBING. WALKAR OUND NORMAL, BRAKE TEMP NORMAL. HAD REPORT OF SMOKE FROM RT SIDE. NO EVIDENCE OF DAMAGE. ON TAXI OUT RT OTBD FAILED. BRA KE WAS REMOVED AND CONFIRMED CARBON FAILURE 2 L 7 2 4F 4 F RT A56NM E00063EN 20081230 2008 12 30 CA081118009 4 20071101 G 2300 TRANSPONDER BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP NAV/COMM MALFUNCTIONED W O OTHER N FALSE WARNING CR CRUISE 1 CA (CAN) LOSS OF COMM/NAV/ TRANSPONDER OCCURRED BACK IN NOV 2007. NOT REPORTED UNTIL 9/11/08 AFTER CUSTOMER HAD HEARD OF A SIMILAR OCCURRENCE ON ANOTHER CHALLENGER 300 (20016) THROUGH ADV COMMITTEE CONFERENCE CALL. IN FLIGHT CREW NOTED THAT TR ANSPONDER CODE CHANGING FREQ. LT AND RT RADIOS INDICATED YELLOW ON C/P MFD. ALSO ON C/P MFD, HAD AMBER BOXED DCP FLASHI NG ON AND OFF. IAW RECOMMENDATION FROM REP, THE C/P DCP CHANGED OUT. TECHS UNABLE TO DUPLICATE PROBLEM. 2 L 7 2 4F 4 F RT T00005NY E00010LA 20081230 GL 2008 12 30 CA081121008 1 20071109 G 2910 1005354220N50192 LINE BOMBDR BD100 BD1001A10 1390044 GL HYDRAULIC SYS CHAFED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 4000 (CAN) CREW REPORTED DURING CRUISE FLIGHT THEY LOST ALL RT SIDE HYD FLUID. NUMEROUS CAS MESSAGES. RT SYS SHOWS 2 PERCENT QUANTITY AND 0 PSI. TEMP 36 C. ACFT DIVERTED IN FLIGHT. AFTER LANDING CREW NOTED HYD FLUID RUNNING OUT OF THE LR FUSELA GE BY THE MAIN WHEEL WELL AREA. FOUND NR 2 ENGINE HYD SUPPLY LINE WITH CLAMP THAT HAD CHAFED INTO THE TUBE ASSY AND WORN A HOLE. 2 L 7 2 4F RT T00005NY 2008010800361 20080108 00361 EA 2008 1 8 CHI08CA035 2 20071101 G 8520 NUT LYC MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA HARTZL HCC2Y HCC2YK1 GL CONNECTING ROD BACKED OUT G B A H EMER. DESCENT UNSCHED LANDING DEACTIVATE SYST/CIRCUITS R Y T PARTIAL RPM/PWR LOSS ENGINE STOPPAGE ENGINE CASE PENETRATION CR CRUISE 1 GL 11 5912Q 1800 818 821 L227651A CA385 NR 3 PISTON CONNECTING ROD SEPARATED FROM THE CRANKSHAFT. PISTON SHEARED MOUNTING STUDS OF CYLINDER HOUSING AT ENGINE CA SING. CYLINDER HOUSING SEPARATED FROM ENGINE CASING. ENGINE SHUTDOWN. 1 L 7 1 3O 3 O 2A3 1E10 5 C P920 2007050400131 20070504 00131 CE 2007 5 4 CM2R747K 1 20070501 G 2730 53608014 BELLCRANK CESSNA 340 340A 2076405 CE ALLSN 250C 250C28B 03013 GL ELEVATOR BROKEN B CM2R O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 SW 15 397R 6383 127 0009 BEARING AND BOLT FAILED IN THE ELEVATOR BELLCRANK P/N 5360801-4. CENTER BEARING THAT SUPPORTS THIS BELLCRANK FAILED. B EARING IS P/N MS27640-4. BOLT P/N AN4-14 WAS SEVERELY WORN AND BROKEN IN TWO. IF EITHER END OF THE BOLT SLIPPED OUT O F THIS BELLCRANK, THE A/C WOULD HAVE LOST PRIMARY ELEVATOR CONTROL. THE ELEVATOR TRIM SYSTEM WOULD STILL FUNCTION. 1 L 7 2 3O 3 U 3A25 E1GL 2007080800065 20070808 00065 CE 2007 8 8 CNQ2918C 1 20070726 G 3010 M1200180244 THERMAL SWITCH CESSNA 680 680CE 2076811 CE ANTI ICE SYSTEM WARNING MESSAGE B A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 GL 25 350QS 1725 6800036 IN-FLIGHT AT FL 300, LT IB WING ANTI-ICE MSG ILLUMINATED, FOLLOWED BY ILLUMINATION OF THE LT WING ANTI-ICE COLD CAS MSG AND THE LT WING BLEED LEAK CAS MSG. FLIGHT CREW FOLLOWED CHECKLIST PROCEDURES; COULD NOT EXTINGUISH ANY AMBER CAS MSGS. FLIGHT CREW DIVERTED AIRCRAFT FOR MAINTENANCE. TECHNICIANS FOUND THE (2) ELECTRICAL LEAD WIRES BROKEN AT SL006 SWITCH, SOLDER CONNECTIONS. REPAIRED WIRES AND PERFORMED OPERATIONAL CHECKS; ALL OPERATIONAL CHECKS WERE SATISFACTORY. AIRCRA FT RETURNED TO SERVICE 07/19/07. 2 L 7 2 4F RC T00012WI 2007082400310 20070824 00310 NM 2007 8 24 CO1Y200700001 1 20070818 G 5313 A6A71211 LONGERON DOUG MD11 MD11 3023602 NM ZONE 100 CRACKED B CO1Y K NONE O OTHER IN INSP/MAINT 1 EA 33 702BC 48504 CAC COMPARTMENT AT STA 6-100 ON LONGHERON NR 37LT SIDE FOUND CRACK 1 INCH. 2 L 7 3 4F RT A22WE 2007082400311 20070824 00311 NM 2007 8 24 CO1Y200700002 1 20070818 G 5330 AEA75732 DOUBLER DOUG MD11 MD11 3023602 NM BS 1321-1341 CORRODED B CO1Y K NONE O OTHER IN INSP/MAINT 1 EA 33 702BC 48504 MAIN CABIN FROM STA 1321 TO STA 1341 FROM L NR 13 TO L NR 14 RT SIDE ON DOUBLER FOUND CORROSION. 2 L 7 3 4F RT A22WE 2007091700002 20070917 00002 NM 2007 9 17 CO1Y200700003 1 20070901 G 5730 SKIN DOUG MD11 MD11 3023602 NM LT WING CORRODED B CO1Y K NONE O OTHER IN INSP/MAINT 1 EA 33 702BC 48504 LT WING UPPER SURFACE ON SKIN FROM XORS 130 TO XORS 738 FOUND EXFOLIATION CORROSION. 2 L 7 3 4F RT A22WE 2007091700001 20070917 00001 NM 2007 9 17 CO1Y200700004 1 20070901 G 5730 SKIN DOUG MD11 MD11 3023602 NM RT WING CORRODED B CO1Y K NONE O OTHER IN INSP/MAINT 1 EA 33 702BC 48504 RT WING UPPER SURFACE FROM XORS 345 TO XORS 828 FOUND 15EA EXFOLIATION CORROSION POINTS. 2 L 7 3 4F RT A22WE 2007120400104 20071204 00104 NM 2007 12 4 CO1Y200700009 1 20071105 G 5330 ACA3108503 SKIN DOUG MD11 MD11 3023602 NM BS 535 CRACKED B CO1Y K NONE O OTHER IN INSP/MAINT 1 EA 33 702BC 48504 AT RT AIR CONDITIONING COMPARTMENT AFT DOOR JAMB FOUND 0.25 INCH CRACK ON EXTERNAL SKIN STA 535 L NR32RH. 2 L 7 3 4F RT A22WE 2007020200015 20070202 00015 SO 2007 2 2 CWQD200702 1 20070130 G 3251 1159LM305489 SCISSORS GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU MLG STEERING CRACKED B DXTA K NONE O OTHER IN INSP/MAINT 1 GL 05 411QS 9576 1311 DURING CHECKLIST FOUND UPPER TORQUE LINK CRACKED P/N 1159LM30548-9 AT CONNECTING LOWER TORQUE LINK P/N 1159LM30553-3. 2 L 7 2 4F 4 F RT A12EA E25NE 2007013100140 20070131 00140 CE 2007 1 31 CWQR200701 1 20070122 G 2730 55653426 PUSHROD CESSNA 500 550 2076604 CE ELEVATOR MISMANUFACTURED B DXTA K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 05 DURING THE REPAIR STATION PRELIMINARY INCOMING PARTS INSPECTION, IT WAS OBSERVED THAT ONE OF THE NEW ELEVATOR PUSHROD CL EVIS ENDS WERE ATTACHED WITH ALUMINUM RIVETS. ANOTHER NEW UNIT AND THE OLD PUSHRODS USED MONEL RIVETS. A CALL TO MFG CON FIRMED THAT MONEL RIVETS SHOULD BE INSTALLED. THE PART WAS REJECTED, TAGGED AND RETURNED TO MFG. ASKED MFG TO CHECK THE IR STOCK FOR THIS CONDITION. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 271980. 1 L 7 2 4F A22CE 2007041700134 20070417 00134 CE 2007 4 17 CWQR200702 1 20070416 G 5410 65526022 FLANGE CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE NACELLE CRACKED B DXTA K NONE O OTHER IN INSP/MAINT 1 GL 05 820QS 2627 5600650 DURING A PHASE 1-4 INSPECTION A 2.5 INCH CRACK WAS FOUND ON THE ENGINE INLET FLANGE, THIS CRACK PASSES THROUGH (2) FASTE NERS THAT ATTACH THE INLET TO THE FLANGE. AND ARE AT THE 3 O'CLOCK POSITION ON BOTH THE LT AND RT ENGINES. 2 L 7 2 4F 4 F RT A22CE E00053EN 2007071200134 20070712 00134 CE 2007 7 12 CWQR200703 1 20070706 G 5340 556560821 ATTACH BRACKET CESSNA 500 560CESSNA 2076750 CE MASTER CYLINDER CRACKED B DXTA K NONE O OTHER IN INSP/MAINT 1 GL 05 347QS 7855 5600357 DURING A PHASE 1-4 INSPECTION, FOUND THE MASTER CYLINDER ATTACH BRACKET MOUNT HOLES GOUGED DURING INSTALLATION AT THE FA CTORY, UPON FURTHER INSPECTION FOUND A .7500 INCH CRACK IN THE FLANGE ATTACH LEG RADIUS. REPLACED WITH NEW BRACKET ASSY. SUBMITTED SCR TO MFR UNDER SCR NR 301844. 2 L 7 2 4F RT A22CE 2007080800045 20070808 00045 CE 2007 8 8 CWQR200704 1 20070716 G 5712 66211511 CLOSEOUT PANEL CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE LEFT WHEEL WELL CRACKED B DXTA K NONE O OTHER IN INSP/MAINT 1 GL 05 694QS 5605194 DURING A PHASE 5 INSPECTION, FOUND LT WHEEL WELL AFT SPAR CLOSE OUT PANEL CRACKED. (3) CRACKS WERE FOUND BEGINNING FROM THE LOWER SKIN ATTACH FLANGE AND GOES STRAIGHT UP THE PANEL. AN SDR HAS BEEN SUBMITTED TO AIRCRAFT UNDER NR 303303. 2 L 7 2 4F 4 F RT A22CE E00059EN 2007080800046 20070808 00046 CE 2007 8 8 CWQR200705 1 20070716 G 5712 66211511 CLOSEOUT PANEL CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE LEFT WHEEL WELL CRACKED B DXTA K NONE O OTHER IN INSP/MAINT 1 GL 05 694QS 5605194 DURING A PHASE 5 INSPECTION, FOUND LT WHEEL WELL AFT SPAR CLOSE OUT PANEL CRACKED. (3) CRACKS WERE FOUND BEGINING FROM THE LOWER SKIN ATTACH FLANGE AND GOES STRAIGHT UP THE PANEL. AN SCR HAS BEEN SUBMITTED TO MFG AIRCRAFT UNDER NR 303303. 2 L 7 2 4F 4 F RT A22CE E00059EN 2007080800101 20070808 00101 CE 2007 8 8 CWQR200706 1 20070725 G 5540 663322513 PLATE CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE RUDDER RUSTED B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 801QS 5600601 DURING A PHASE 1-4 INSPECTION, NOTICED A RUST STAIN COMING FROM THE LOWER RUDDER BEARING PLATE ASSY (LOWEST HINGE POINT) . UPON DISASSEMBLE, FOUND THE DRAIN HOLE FROM THE RUDDER TORQUE TUBE WAS DRAINING INTO THE LOWER BEARING PLATE ASSY. THI S IS DUE TO A NEW DESIGN OF THE PLATE ASSY, THE NEW ONE IS BEEFED UP AND HAS A BUILT UP AREA AROUND THE BEARING, THAT DI RECTS WATER TO THE BEARING, UNLIKE THE PREVIOUS DESIGN THAT WAS A FLAT PLATE AND ALLOWED WATER TO DRAIN AWAY FROM THE BE ARING. SERVICE CONDITION REPORT HAS BEEN FILED WITH MFG UNDER NR 305034. 2 L 7 2 4F 4 F RT A22CE E00053EN 2007082400304 20070824 00304 CE 2007 8 24 CWQR200707 1 20070821 G 5540 66331508 BALANCE WEIGHT CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE RUDDER MISINSTALLED B DXTA K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 05 698QS 5605653 DURING A PHASE 1-4 INSPECTION, FOUND THE RUDDER BALANCE WEIGHT WAS TRIMMED DOWN AND ATTACHED WITH ONLY (2) BOLTS.THE IPC SHOWS (4) BOLTS TO ATTACH THIS WEIGHT. CONTACTED MFG ENGINEERING, THEY STATED THE WEIGHT REQUIRES (4) BOLTS TO MEET THE 100 (G) STANDARD. APPEARS THE RUDDER BALANCE WEIGHT WAS TRIMMED DOWN AND INSTALLED AT THE FACTORY. REPLACED RUDDER BALA NCE WEIGHT IAW SRM 51-60-03, RUDDER BALANCING. SUBMITTED SERVICE CONDITION REPORT TO MFG UNDER NR 310349. 2 L 7 2 4F 4 F RT A22CE E00059EN 2007082400312 20070824 00312 CE 2007 8 24 CWQR200708 1 20070731 G 3110 556560914 SUPPORT CHANNEL CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE INST PANEL CRACKED B DXTA K NONE O OTHER IN INSP/MAINT 1 GL 05 371QS 5600471 DURING MAINTENANCE FOUND THE RUDDER UPPER SUPPORT CHANNEL CRACKED WHERE IT ATTACHES TO THE INSTRUMENT PANEL. THIS AIRCR AFT HAD SL560-27-13 COMPLIED WITH 826.6 HOURS PRIOR TO FINDING THE CRACKED CHANNEL. THIS SL UPGRADED THE ATTACHING HARDW ARE BUT DOES NOT CHANGE THE BRACKET. REPLACED BRACKET AND HARDWARE WITH NEW. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 306488. 2 L 7 2 4F 4 F RT A22CE E25EA 2007082400313 20070824 00313 CE 2007 8 24 CWQR200709 1 20070808 G 5415 65526022 MOUNT CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE NACELLE CRACKED B DXTA K NONE O OTHER IN INSP/MAINT 1 GL 05 810QS 5600625 DURING AN INSPECTION FOUND THE ENGINE NACELLE ATTACH FLANGE EARS CRACKED IN (2) LOCATIONS. SENT TO MFG FOR EVALUATION AN D REPAIR. SUBMITTED SCR TO MFG UNDER NR 308174. 2 L 7 2 4F 4 F RT A22CE E00053EN 2007082400315 20070824 00315 CE 2007 8 24 CWQR200710 1 20070808 G 3220 55423002 FORK CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE NLG LOOSE B DXTA K NONE O OTHER IN INSP/MAINT 1 GL 05 804QS 5600610 DURING A MAINTENANCE TAXI CHECK NOTICED SHIMMY FROM NOSE GEAR. UPON DISASSEMBLY FOUND FORK LOOSE ON NOSE GEAR PISTON, TH IS SHOULD BE A PRESS FIT FROM THE FACTORY. SENT UNIT RELIABILITY GROUP FOR EVALUATION. A SCR HAS BEEN SUBMITTED TO MF G UNDER NR 308107. 2 L 7 2 4F 4 F RT A22CE E00053EN 2007082400316 20070824 00316 CE 2007 8 24 CWQR200711 1 20070813 G 7160 65526057 INTAKE DUCT CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE LT ENGINE CRACKED B DXTA K NONE O OTHER IN INSP/MAINT 1 GL 05 804QS 5600610 DURING A PHASE INSPECTION FOUND LT ENGINE INLET DUCT ASSY CRACKED. CRACKS WERE FOUND ON THE AFT PORTION OF THE INLET DUC T ASSY THROAT. THIS UNIT HAD TO BE RETURNED TO THE MFG FOR REPAIR. AN SCR WAS SUBMITTED TO MFG UNDER NR 308858. 2 L 7 2 4F 4 F RT A22CE E00053EN 2007082400317 20070824 00317 CE 2007 8 24 CWQR200712 1 20070813 G 7160 65526057 INTAKE DUCT CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE RT ENGINE CRACKED B DXTA K NONE O OTHER IN INSP/MAINT 1 GL 05 804QS 5600610 DURING A PHASE INSPECTION FOUND RT ENGINE INLET DUCT ASSY CRACKED. CRACKS WERE FOUND ON THE AFT PORTION OF THE INLET DUC T ASSY THROAT. THIS UNIT HAD TO BE RETURNED TO THE MFG FOR REPAIR. AN SCR WAS SUBMITTED TO MFG UNDER NR 308873. 2 L 7 2 4F 4 F RT A22CE E00053EN 2007020900101 20070209 00101 CE 2007 2 9 DEBD624B0207 1 20070202 G 3246 GYS186C21 BOLT GOODYEARAERO BEECH MU300 400A 1155402 CE MLG WHEEL BROKEN B DEBD K NONE O OTHER IN INSP/MAINT 1 GL 19 624B 1169 NOV991386 RK369 A WHEEL THRU BOLT BROKE WHILE BEING TORQUED DURING WHEEL REASSEMBLY AFTER A TIRE CHANGE. 2 H 7 2 4F RT A16SW 2007012500140 20070125 00140 CE 2007 1 25 DELR200700001 1 20070104 G 7120 2652002 BOLT LEAR 55 55LEAR 5170702 CE ALIDSG TFE731 TFE7313AR WP ZONE 400 SHEARED B DELR K NONE O OTHER IN INSP/MAINT 1 CE 03 345RJ 7248 6267 078 P85197 AFTER REMOVAL OF SAFTY WIRE TO REMOVE BOLT, THE MOUNT BOLT WAS FOUND SHEARED AT THE NECK OF THE BOLT. THREADED SECTION O F BOLT WAS REMOVED WITH AN EASYOUT IAW CHAPTER 5 THIS ITEM IS LIFE LIMITED AT 20,000.00 HOURS. 2 L 7 2 4F 4 F A10CE E6WE 2007050400150 20070504 00150 GL 2007 5 4 DJS041707 1 20070417 G 7700 35C155103 SENSOR AMTR 500 ECLIPSE500 05614K5 GL ENGINE FAULTY C E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 EA 27 110DJ 42 000007 INFLIGHT SHUTDOWN IAW AFM DUE TO LOSS OF OIL TEMPERATURE. TROUBLESHOT TO A FAULTY MOT/MOP SENSOR. 1 L 7 2 3F RT EXPA1L72 2007042500248 20070425 00248 GL 2007 4 25 DJS110DJ 1 20070416 G 3244 40440A TIRE AMTR 500 ECLIPSE500 05614K5 GL LT MLG BLOWN C O OTHER O OTHER TX TAXI/GRND HDL 1 EA 27 110DJ 41 000007 LT MAIN WHEEL AND TIRE ASSEMBLY BLEW OUT DURING TAXI. 1 L 7 2 3F RT EXPA1L72 2007030200035 20070302 00035 NM 2007 3 2 DU4R2007060 1 20070227 G 5710 VENT DOUG MD80 MD83 3023681 NM LT WING CORRODED B BWIA K NONE O OTHER IN INSP/MAINT 1 SO 15 789BV 49789 S/O 244001 N/R 22938 N/R 22839 CORROSION ON I/B END OF EXISTING REPAIR ON AFT L/H WING VENT BOX REPAIRED BY REMOVING EXI STING DOUBLER, FLAP PEENED CORROSION IAW BWIA DWG BW-D9-57-A/5120 AND MD-80 MM 20-10-10. FABRICATED AND INSTALLED DOUBLE R 41.9 X 3.5, FILLER 1.5 X .9 FROM 2024-T3 0.100 IAW BWIA DWG BW-D9-57-A/5120 AND MD-80 SRM 51-30-2 AND 51-30-1. 2 L 7 2 4F RT 2007110100192 20071101 00192 CE 2007 11 1 EA25070193 1 20071019 G 3220 3400 LANDING GEAR CESSNA 182 182P 2075816 CE CONT O470 O470S 17026 SO FWD RT DEPARTED G O OTHER D INFLIGHT SEPARATION CL CLIMB 1 EA 25 6506M 30 18263735 AIRCRAFT ALTERED IAW STC SA02031NY INSTALLATION OF 3400 AMPHIBIOUS FLOATS APPROXIMATELY 36 HOURS PRIOR TO OCCURRENCE. ON TAKEOFF FROM HARD SURFACE RUNWAY, RT FORWARD WHEEL AND SUPPORT ASSY DEPARTED LANDING GEAR STRUT. WHEEL AND SUPPORT ASSY LT GEAR STRUT CLEANLY AND ONLY DAMAGE APPEARED TO BE FROM GROUND IMPACT. AIRCRAFT MADE SUBSEQUENT WATER LANDING WITHOU T INCIDENT. INSPECTION OF AIRCRAFT SHOWS THAT WHEEL AND SUPPORT ARE ATTACHED TO GEAR STRUT THROUGH USE OF A SPRING AND P AWL MECHANISM. IMPOSSIBLE TO TELL IF SPRING OR PAWL FAILED WITHOUT FURTHER DISASSEMBLY. POSSIBLE THAT ASSEMBLY WAS OVER -GREASED OR GREASED TOO QUICKLY, AS PLACARD NEAR GREASE FITTING WARNS TO (APPLY GREASE SLOWLY). WILL FORWARD THIS INFOR 1 H 7 1 3O 3 O NT TA13 E273 2008011000130 20080110 00130 SO 2008 1 10 EA25200802753 1 20071218 G 5340 62522000 FITTING PIPER PA34 PA34200 7103405 SO LYC O360 IO360A1A 41514 EA FUSELAGE CORRODED G K NONE O OTHER IN INSP/MAINT 1 EA 25 1031U 9840 347250012 DURING WINDSHIELD REPLACEMENT, NOTED STEEL FITTINGS AND ATTACHING HARDWARE WERE SUBSTANTIALLY CORRODED. FUNCTION OF FITT INGS IS ATTACHMENT OF FUSELAGE OVERHEAD (A) PILLAR TO FUSELAGE STRUCTURE PROPER. OTHER THAN SOME RIVETS THROUGH THE SKIN S, THESE FITTINGS ARE THE MAJOR STRUCTURAL ATTACHMENTS OF THE CABIN OVERHEAD TO THE FUSELAGE STRUCTURE. CAUSE OF CORROSI ON APPEARS TO BE FOAM INSULATION, HELD IN CONSTANT CONTACT WITH THE FITTINGS, BECOMING AND REMAINING WET THROUGH LEAKING WINDSHIELDS. COMPANY MECHANIC RECOMMENDS REMOVING PORTION OF INSULATION IN CONTACT WITH FITTINGS AND INSPECTING THIS AR EA AT EACH 100 HOUR/ANNUAL INSPECTION. ACCESS IS GAINED THROUGH SIMPLE REMOVAL OF INTERIOR WINDSHIELD PILLAR TRIM PANELS 1 L 7 2 3O 3 O A7SO 1E10 2008012200011 20080122 00011 SO 2008 1 22 EA25200803022 1 20071218 G 5340 68257000 FITTING PIPER PA34 PA34200 7103405 SO LYC O360 IO360A1A 41514 EA CORRODED G K NONE O OTHER IN INSP/MAINT 1 EA 25 1031U 9840 347250012 DURING WINDSHIELD REPLACEMENT, MECHANIC NOTED STEEL FITTINGS AND ATTACHING HARDWARE WERE SUBSTANTIALLY CORRODED. FUNCTIO N OF FITTINGS IS ATTACHMENT OF FUSELAGE OVERHEAD A PILLAR TO FUSELAGE STRUCTURE PROPER. OTHER THAN SOME RIVETS THROUGH T HE SKINS, THESE FITTINGS ARE THE MAJOR STRUCTURAL ATTACHMENTS OF THE CABIN OVERHEAD TO THE FUSELAGE STRUCTURE. CAUSE OF CORROSION APPEARS TO BE FOAM INSULATION, HELD IN CONSTANT CONTACT WITH THE FITTINGS, BECOMING AND REMAINING WET THROUGH LEAKING WINDSHIELDS. MECHANIC RECOMMENDS REMOVING PORTION OF INSULATION IN CONTACT WITH FITTINGS AND INSPECTING THIS ARE A AT EACH 100 HOUR/ANNUAL INSPECTION. ACCESS IS GAINED THROUGH SIMPLE REMOVAL OF INTERIOR WINDSHIELD PILLAR TRIM PANELS. 1 L 7 2 3O 3 O A7SO 1E10 2007062500004 20070625 00004 EU 2007 6 25 EBVR200700000 1 20070609 G 2742 12342 MOTOR AMD AMD FALC10 FALCON10 2730101 EU BRAKE UNIT FAILED B K NONE O OTHER IN INSP/MAINT 1 GL 09 55DG 863 103 207 FAILED NORMAL MOTOR TRAVEL TIME CHECKS. SUSPECT NORMAL MOTOR BRAKE WAS PREVIOUSLY ASSEMBLED INCORRECTLY CAUSING DAMAGE T O MOTOR. 2 L 7 2 4F A33EU 2007071200126 20070712 00126 NE 2007 7 12 EWCR070700002 2 20070703 G 7200 ENGINE CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE LEFT UNKNOWN B EWCA E A ENGINE SHUTDOWN UNSCHED LANDING X Y T ENGINE FLAMEOUT ENGINE STOPPAGE ENGINE CASE PENETRATION CL CLIMB 1 EA 39 757CK 5600028 108055 FOLLOW UP REPORT AFTER PILOT REPORT TO FSDO OF (LARGE) BIRD STRIKE TO INLET AND INGESTION INTO LT ENGINE. 2 L 7 2 4F 4 F RT A22CE E25EA 2007082100281 20070821 00281 2007 8 21 EY2R0097613 3 20070718 G 6110 7826761 BEARING EMB 120 EMB120 3260201 SO BLADE CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 PROPELLER BLADE BEARING CORRODED. 2 L 7 2 4T RT A31SO 2007113000111 20071130 00111 SO 2007 11 30 FA20071025001 2 20071025 G 7414 655845 GEAR SLICK 4309 DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA MAGNETO BROKEN D A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 25 629DC 1134 490 99052002 C0129 806243 AE4420 IN CRUISE, NOTICED DROP IN OIL PRESSURE BELOW YELLOW ARC NOT INDICATED DURING RUN UP & TAKEOFF. MADE PRECAUTIONARY RET URN TO HOME BASE & LANDED APPROX 7-8 MINUTES AFTER NOTICING DROP IN OIL PRESSURE. OIL PRESSURE INDICATED ZERO PSI DURIN G TAXI BACK TO HANGER. PRELIMINARY INSP &MAINT PERFORMED. REMOVED OIL FILTER, CUT OPEN AND INSPECTION SATISFACTORY, N O METAL PRESENT. REPLACED OIL PRESSURE TRANSDUCER WITH NEW AND RAN ENGINE. LOW OIL PRESSURE STILL INDICATED. CHECKED OIL PRESSURE WITH CALIBRATED SHOP GAGE. LOW OIL PRESSURE INDICATED. REMOVED AND CHECKED OIL PRESSURE RELIEF VALVE, FOU ND FERROUS METAL CHUNK APPROX SIZE .060 DIA AT VALVE SEAT. RAN ENGINE & OIL PRESSURE IN INDICATED IN THE GREEN ARC. IN 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2008011100232 20080111 00232 GL 2008 1 11 FAA010208001 1 20071130 G 2497 UNKNOWN CIRRUS SR SR22 2130001 GL CONT O550 IO550* SO PFD MALFUNCTIONED D O OTHER O OTHER NR NOT REPORTED 1 SW 99 123DV 1313 PFD AND GPS/NAV1 BOTH REBOOTED AT THE SAME TIME. RESTARTED WITHOUT GOING THROUGH EITHER ITS STANDARD INITIALIZATION OR ITS FAST START ROUTINE. THE AUTOPILOT SEEMED TO BE STILL ENGAGED BUT THE VS SELECTION, QNH, ALTITUDE PRE-SELECT AND HEA DING WERE RESET AND THESE RESET VALUES APPEARED TO BE PASSED TO THE AUTOPILOT. THIS OCCURRED AT LOW LEVEL, IN THE CLIMB , IN IMC WITH HEADING AND ALTITUDE ACQUIRE SET ON THE AUTOPILOT. THERE WAS SOME ELECTRICAL ACTIVITY WITHIN 10 MILES. THE AIRCRAFT WAS FLOWN SAFELY BACK TO THE DEPARTURE FIELD USING BACKUP INSTRUMENTS. ENGINEERS SUSPECT EITHER A SPIKE FR OM ALTERNATOR 2 OR MFG BELIEVES THIS COULD BE A BONDING ISSUE AND WAS CAUSED BY STATIC. MFG INCIDENT REF: 871500HQ. EN 1 L 7 1 3O 3 O NT A00009CH E3SO 2008011100233 20080111 00233 CE 2008 1 11 FAA010208002 1 20071102 G 3233 MS28775218 O-RING CESSNA 425 425 2076018 CE PWA PT6 PT6A60A 52043 NE NLG ACTUATOR DISINTEGRATED B YN8R A UNSCHED LANDING J WARNING INDICATION LD LANDING 1 CE 07 1262K 4250234 AN EMERGENCY LANDING MADE, DID NOT GET A GREEN DOWN AND LOCK INDICATION FOR MLG. MADE SAFE LANDING. FOUND RT MLG NOT D OWN AND FULLY LOCKED. DISCOVERED BLOW DOWN BOTTLE FULLY DISCHARGED, DISCOVERED HYDRAULIC RESERVOIR EMPTY. JACKED ACFT & ATTEMPTED TO MANUAL EXTEND RT MLG BY HAND. DISCOVERED THAT RT MLG WAS HYDRO-LOCKED. BLED OFF HYDRAULIC PRESSURE FRO M ACTUATOR, ABLE TO ENGAGE DOWNLOCK. , JACKED ACFT AND TRIED TO CYCLE GEAR SYSTEM. GEAR WOULD NOT CYCLE UP OR DOWN. T ROUBLESHOT AND DISCOVERED NLG ACTUATOR, PISTON O-RINGS HAD COME APART AND WENT THRU THE ENTIRE MLG AND PLUGGED SYSTEM. PRIOR TO FLIGHT, FWD SEALS ON ACTUATOR HAD BEEN REPLACED DUE TO EVIDENCE OF HYD LEAK. AFTER SEALS HAD BEEN REPLACED, PE 1 L 7 2 3T 4 T RT A7CE E4EA 2008011100235 20080111 00235 SO 2008 1 11 FAA010208003 2 20071219 G 8550 SAS6250 VALVE BBAVIA 7 7EC 2110120 SW CONT O200 O200A 17020 SO OIL TANK DAMAGED G K NONE O OTHER IN INSP/MAINT 1 GL 13 274AC 1 10142007 256377 INSTALLED OIL QUICK DRAIN VALVE PN SG250 ON NEW AIRCRAFT/ ENGINE. AIRCRAFT FLEW APPROX 1 HOUR. OIL LEAK NOTICED FROM D RAIN VALVE. REMOVED VALVE TO FIND VALVE SNAP RING IN OIL DRAINED FROM ENGINE AND VALVE O-RING DAMAGED. ONE CUT THROUGH AND THE OTHER NICKED. INVESTIGATION REVEALED OIL DRAIN VALVE CONTACTED THE EDGE OF THE OIL PICK-UP TUBE CAUSEING DAMAG E. SUBJECT VALVE IS NOT COMPATABLE WITH THE O200A66B ENGINE. (K) 1 H 7 1 3O 3 O A759 E252 2007070300048 20070703 00048 EU 2007 7 3 FAA070628001 1 20070628 G 6320 350A32031002 GEARBOX SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B1 60056 NE MAIN ROTOR MAKING METAL B A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 EA 17 808CP 161 4151 23335 MGB CHIP LIGHT CAME ON IN FLIGHT. REMOVED CHIP PLUGS FROM THE MGB AND THE MAST FOUND PARTICALS ON THE MGB PLUG LESS THAN LIMITS CALLED OUT IN AEC AS350B3 SPM 20.08.01.601 NOTHING ON THE MAST PLUG.PERFORMED 10 MIN. HOVER AND RECHECKED CHIP P LUGS AS PER AEC AS350B3 MWC 05.53.00.608 NO MORE PARTICALS FOUND AND NO RE-ACCURANCE OF THE CHIP LIGHT. 1 G 7 1 3U 3 U H9EU E00054EN 2008011100144 20080111 00144 EA 2008 1 11 FAA122707001 2 20071111 G 8530 AEL65102SN041 CYLINDER HEAD CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA ENGINE CRACKED D B EMER. DESCENT Y J ENGINE STOPPAGE WARNING INDICATION CL CLIMB 1 SO 19 62281 1083 17275242 L1236139A HEAD CAME OFF BARRELL OF CYLINDER P/N AEL65102 SN0.41 S/N 20255-13 1083.3 HOURS ON CYLINDER SINCE INSTRUCTION OF 10/5/04 (HEAD, BARRELL SEPARATED). 1 H 7 1 3O 3 O NT 3A12 E274 2008011100222 20080111 00222 CE 2008 1 11 FAA122808001 1 20071228 G 3220 AN7520 BOLT BEECH 18 H18 1151012 CE PWA R985 R985* 52008 NE NLG SHEARED G O OTHER O OTHER LD LANDING 1 SO 19 117ME BA638 DURING THE INVESTIGATION. IT WAS DISCOVERED THAT THE REMAINDER OF THE BOLT FOR NOSE GEAR RETRACT PUSH PULL TUBE TO CANT ILEVER ARM FOR DRAG BRACE HAD SHEARED ON (2) DIFFERENT OCCASIONS FOR REASONS UNDETERMINED. THE OPERATOR ALSO OPERATES ( 2) OTHER VOLPAR TRICYCLE GEARED AC, A BOLT FROM ONE OF THOSE AC WAS REMOVED TO FIND SCORE MARKS IN THE SHANK OF THE BOLT IN THE SAME VICINITY OF THE SHEAR POINTS OF THE INCIDENT AIRCRAFT BOTH AIRCRAFT HAVE SIMILAR AIRFRAME TT. IT WAS DISCU SSED WITH THE OPERATOR ON TECHNIQUES AND MISTAKES MADE DURING LANDING AND IT WAS DISCOVERED THAT IF THE AIRCRAFT IS EMPT Y/LIGHT AND THE PILOT ALLOWS THE NOSE TO SETTLE TOO SOON IF COULD INDUCE A PORPOSING EFFECT THAT COULD PUT LARGE SHEAR L 1 L 7 2 3R 3 R A765 5E1 2007070300006 20070703 00006 GL 2007 7 3 FAA20070618001 3 20070618 G 6114 HUB PIPER PA34 PA34200 7103405 SO HARTZL HCC2Y HCC2Y* GL PROPELLER FAILED D A UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 SO 15 15156 347350028 ON JUNE 6,2007 PIPER SENECA N15156 WHILE IN CRUSE ON A TRAINING FLIGHT HAD A CATROSTRIFIC FAILRUE OF THE PROPELLER HUB C AUSING THE LOSS INFLIGHT OF ONE OF THE PROPELLER BLADES. THE FAILURE OF THE HUB WAS OF THE SAME KIND ADDRESSED IN AD2006 -18-15 EXCEPT THE FAILURE IN THIS CASE PROPAGATED FROM THE AFT HALF OF THE HUB WHICH IS NOT PART OF THE AD'S REQUIRED IN SPECTION. EDDY CURRENT INSPECTION IN ACCORDANCE WITH THE AD HAD BEEN PREFORMED 17 HOURS PRIOR TO THE FAILURE. INSPECTOR FOR HARTZELL PROPS CONFIRMED THIS INFORMATION AFTER INSPECTING THE HUB ALONG WITH FAA AND NTSB INVESTIGATORS ON JUNE 9TH , 2007. 1 L 7 2 3O A7SO 5 C P920 2008010400239 20080104 00239 SO 2008 1 4 FAA2007121001 1 20071210 G 2130 SYLC518361 ACTUATOR EMB 135 EMB135BJ 3260306 SO ALLSN AE300 AE3007A GL RAM AIR SHORTED B A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SO 11 124LS 14500948 WHILE IN FLIGHT THE AIRCRAFT EXPERIENCED AND NR1 PAC OVLD INDICATION WITH SUBSEQUENT NR1 PAC AUTO SHUTDOWN AS A RESULT T HE FLIGHT CREW MADE AN IN-FLIGHT DIVERSION AND UNSCHEDULED LANDING. PERFORMED DOWNLOAD OF THE CENTRAL MAINTENANCE COMPU TER WHICH REVEALED 1 OCCURRENCE OF NR1 PAC OVERTEMP AND 63 OCCURRENCES OF NR2 PAC OVERTEMP. TROUBLESHOOTING REVEALED TH AT THE LT AND RT PAC OVERTEMP SWITCHES FAILED BENCH CHECK. BOTH SWITCHES WERE REPLACED WITH NEW SWITCHES. DURING THE P ERFORMANCE OF THE PAC SYSTEM OPERATIONAL TEST IT WAS DISCOVERED THAT THE RT RAM AIR ACTUATOR HAD AN ELECTRICAL SHORT CAU SING THE CIRCUIT BREAKER TO (POP). REPLACED THE RT RAM AIR ACTUATOR AND PERFORMED PAC SYSTEM OPERATIONAL TESTS. DURING 2 L 7 2 4F 4 F RT TE6CH 2007012500254 20070125 00254 2007 1 25 FCPR20070001 4 20070105 G 3416 5934PA1 ALTIMETER COCKPIT BROKEN B FCPR K NONE O OTHER IN INSP/MAINT 1 NM 09 BAROMETRIC SCALE DOES NOT MOVE WITH DIAL INDICATION RESULTING IN INACCURATE READINGS THROUGH OUT THE ENTIRE RANGE. ALLO WS GEARS TO DISENGAGE INTERNALLY. PART IS REMOVED FROM AIRCRAFT AT DISCOVERY. 2007021400143 20070214 00143 SO 2007 2 14 FCPR20070003 2 20070131 G 8520 655516 GEAR BEECH 36 A36 1151604 CE CONT O550 IO550B SO CAMSHAFT BROKEN B FCPR A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 NM 09 18391 200 E1113 685492 ENGINE FAILED IN FLIGHT. FOUND 13 TEETH MISSING FROM CAMSHAFT GEAR P/N 655516. 1 L 7 1 3O 3 O 3A15 E3SO 2008011000057 20080110 00057 2008 1 10 FCPR200700118 2 20071227 G 7322 10603511 CARBURETOR ENGINE NO TEST B FCPR O OTHER O OTHER NR NOT REPORTED 1 NM 09 CARBURETOR FAILED THE STUMBLE TEST, FOUND TO BE ACCELERATOR CIRCUIT. PART RETURNED TO MFG FOR FURTHER EVALUATION. (K) 2008011400085 20080114 00085 2008 1 14 FCPR200700125 2 20071227 G 7322 10603511 CARBURETOR ENGINE NO TEST B FCPR K NONE L NO TEST IN INSP/MAINT 1 NM 09 CARBURETOR FAILED THE STUMBLE TEST, FOUND TO BE ACCELERATOR CIRCUIT. PART RETURNED TO MFG FOR FURTHER EVALUATION. (K) 2008010800351 20080108 00351 EA 2008 1 8 FCPR20070110 2 20071208 G 7314 RB15985 DIAPHRAGM ROMEC RG179801M PIPER PA23 PA23250 7102308 SO LYC O540 TIO540C1A 41532 EA FUEL PUMP FAILED B FCPR K NONE O OTHER UK UNKNOWN 1 NM 09 294 C5518 277754126 L853261A PUMP VALVE REGULATOR DIAPHRAGM FAILED AT GUIDE PIN, PUMP WOULD NOT FUNCTION. 1 L 7 2 3O 3 O 1A10 E14EA 2007041200006 20070412 00006 CE 2007 4 12 FMOR20070001 1 20070409 G 3230 57412025 UPLOCK HOOK CESSNA 414 414A 2075907 CE CONT O520 TSIO520* 17040 SO ZONE 700 CRACKED B O OTHER S AFFECT SYSTEMS CR CRUISE 1 SO 15 6161Z 7024 414A0019 PILOT REPORTED THAT THE LANDING GEAR CAME UNHOOKED FROM THE UP POSITION IN FLIGHT. THE GEAR WAS EXTENDED AND THE AIRCRA FT LANDED. THE AIRCRAFT WAS JACKED AND THE GEAR CYCLED TO THE UP POSITION. WHEN ALL (3) UPLOCK SWITCHES WERE MADE THE RT MAIN GEAR FELL FROM THE WHEEL WELL. A DISTORTED AND CRACKED UPLOCK HOOK WAS FOUND. THE CRACK WAS FROM THE CENTER OF THE HOOK TO THE HOLE FOR THE UPLOCK SWITCH. 1 L 7 2 3O 3 O A7CE E8CE 2007041300111 20070413 00111 CE 2007 4 13 FMOR20070002 1 20070410 G 2731 NAS302665170 CONTROL CABLE BEECH 90 C90A 1152911 CE PWA PT6 PT6* 52043 EA FS 216 FRAYED B O OTHER S AFFECT SYSTEMS CR CRUISE 1 SO 15 120TT 5072 LJ1073 THE ELEVATOR TRIM CABLE BEGAN UNRAVELING JUST FORWARD OF THE CABIN DOOR. FROM THERE THE CABLE BEGAN BINDING IN A PULLEY UNDERNEATH THE PILOT'S SIDE FORWARD FACING PASSENGER CHAIR CAUSING STIFFNESS OF OPERATION BY HAND AND THE MALFUNCTION O F THE ELECTRIC TRIM SYSTEM LEADING TO THE EVENTUAL INOPERATION OF THE ELEVATOR TRIM. THE ISSUE MOST LIKELY AROSE DUE TO AGE. WHILE UNDER THE SCHEDULED INSPECTION PROGRAM OUTLINED BY MFG THE INSPECTION OF THESE AREAS OCCURS ONCE EVERY (2) YEARS OR 800 HOURS. 1 L 7 2 3T 3 T RT 3A20 E2NE 2007090600082 20070906 00082 CE 2007 9 6 FMOR20070003 1 20070828 G 2731 NAS302665170 CONTROL CABLE BEECH 90 C90 1152913 CE PWA PT6 PT6A60A 52043 NE FS 216 FRAYED B FMOR K NONE O OTHER IN INSP/MAINT 1 SO 15 725AR 6415 310 LJ879 THE ELEVATOR TRIM CABLE WAS FOUND TO HAVE SEVERAL BROKEN STRANDS AND BEGINNING TO UNRAVEL WHERE IT GOES AROUND THE ELEVA TOR TRIM ACTUATOR CAPSTAND. THIS CONDITION WAS MOST LIKELY CAUSED BY AGE. 1 L 7 2 3T 4 T 3A20 E4EA 2007042500260 20070425 00260 CE 2007 4 25 FMOR477K 1 20070409 G 3230 57412025 UPLOCK HOOK CESSNA 414 414A 2075907 CE CONT O520 TSIO520* 17040 SO MLG DISTORTED B O OTHER O OTHER CR CRUISE 1 SO 15 6161Z 7024 414A0019 PILOT REPORTED THAT THE LANDING GEAR CAME UNHOOKED FROM THE UP POSITION IN FLIGHT. THE GEAR WAS EXTENDED AND THE AIRCRA FT LANDED. THE AIRCRAFT WAS JACKED AND THE GEAR CYCLED TO THE UP POSITION. WHEN ALL (3) UPLOCK SWITCHES WERE MADE THE RT MAIN GEAR FELL FROM THE WHEEL WELL. A DISTORTED AND CRACKED UPLOCK HOOK WAS FOUND. THE CRACK WAS FROM THE CENTER OF THE HOOK TO THE HOLE FOR THE UPLOCK SWITCH. 1 L 7 2 3O 3 O A7CE E8CE 2008011100134 20080111 00134 2008 1 11 FPFC20070113 2 20071226 G 7322 10603511 CARBURETOR NO TEST B FCPR K NONE L NO TEST IN INSP/MAINT 1 NM 09 CARBURETOR FAILED THE STUMBLE TEST, FOUND DEFECTIVE ACCELERATOR CIRCUIT. PART RETURNED TO PRECISION FOR FURTHER EVALUATI ON. 2007082400324 20070824 00324 CE 2007 8 24 GC4N200700001 1 20070824 G 3233 ACTUATOR RAYTHN 390 390 7150030 CE WILINT FJ44 FJ442A GL NLG FAULTED D O OTHER J WARNING INDICATION LD LANDING 1 GL 07 7088S RB188 AFTER COMPLAINT FROM THE PILOT OF NOT GETTING A NOSE LANDING GEAR DOWN LIGHT STRAIT AWAY, PLACED THE AIRCRAFT ON JACKS A ND CARRIED OUT 4 RETRACTIONS WHICH RESULTED IN 100 PERCENT FAILURE OF THE NOSE LANDING GEAR FULLY EXTENDING, AFTER FAULT FINDING WE BELIEVE THE NOSE LANDING GEAR ACTUATOR TO BE FAULTY, A PART IS ON ORDER FROM MFG. 1 L 7 2 3F 4 F RT A00010WI E3GL 2008011100284 20080111 00284 SO 2008 1 11 GW4R200700001 1 20071210 G 2130 SYLC518361 ACTUATOR EMB 135 EMB135BJ 3260306 SO ALLSN AE300 AE3007A GL RAM AIR FAILED B CWQA A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SO 11 124LS 14500948 DURING FLIGHT, AIRCRAFT EXPERIENCED AND NR 1 PACK OVLD INDICATION WITH SUBSEQUENT NR 1 PACK AUTO SHUTDOWN AS A RESULT MA DE AN IN-FLIGHT DIVERSION AND UNSCHEDULED LANDING. PERFORMED DOWNLOAD OF THE CENTRAL MAINTENANCE COMPUTER WHICH REVEALE D 1 OCCURRENCE OF NR 1 PACK OVERTEMP AND 63 OCCURRENCES OF NR 2 PACK OVERTEMP. TROUBLESHOOTING REVEALED THE LT AND RT P ACK OVERTEMP SWITCHES FAILED BENCH CHECK. BOTH SWITCHES WERE REPLACED. DURING PERFORMANCE OF PACK SYSTEM OPS TEST, IT WAS DISCOVERED THAT THE RT RAM AIR ACTUATOR HAD AN ELECTRICAL SHORT CAUSING THE CIRCUIT BREAKER TO TRIP. REPLACED THE R T RAM AIR ACTUATOR AND PERFORMED PAC SYSTEM OPS TESTS. DURING THE ABOVE CENTRAL MAINTENANCE COMPUTER DOWNLOAD, 17 OCCUR 2 L 7 2 4F 4 F RT TE6CH 2008010800326 20080108 00326 SO 2008 1 8 GW4R237272 1 20071129 G 2130 SYLC518361 ACTUATOR EMB 135 EMB135BJ 3260306 SO ALLSN AE300 AE3007A GL RT RAM AIR SHORTED B A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SO 11 124LS 14500948 WHILE IN FLIGHT THE AC EXPERIENCED AND NR1 PAC OVLD INDICATION WITH SUBSEQUENT NR1 PAC AUTO SHUTDOWN AS A RESULT THE FLI GHT CREW MADE AN IN-FLIGHT DIVERSION AND UNSCHEDULED LANDING. DOWNLOAD OF THE COMPUTER REVEALED 1 OCCUR OF NR1 PAC OVER TEMP AND 63 OF NR2 PAC OVERTEMP. LT AND RT PAC OVERTEMP SWITCHES FAILED BENCH CHECK. BOTH SWITCHES WERE REPLACED. DUR ING THE PAC SYSTEM OPS TEST, THE RT RAM AIR ACTUATOR HAD AN ELECTRICAL SHORT CAUSING THE CIRCUIT BREAKER TO POP. REPLAC ED THE RT RAM AIR ACTUATOR AND PERFORMED PAC SYSTEM OPERATIONAL TESTS. DURING THE COMPUTER DOWNLOAD, 17 OCCURRENCES OF A NR1 PRECOOLER TEMP CONTROL SYSTEM FAIL MESSAGE WAS NOTED. ACCESSED FAN AIR TEMPERATURE THERMOSTATS FOR TROUBLESHOOTIN 2 L 7 2 4F 4 F RT TE6CH 2008010800333 20080108 00333 SO 2008 1 8 GW4R237272NR1 1 20071129 G 2150 SYLC518361 SWITCH EMB 135 EMB135BJ 3260306 SO ALLSN AE300 AE3007A GL A/C PACK FAILED B A UNSCHED LANDING J WARNING INDICATION UK UNKNOWN 1 SO 11 124LS 14500948 IN FLIGHT AC EXPERIENCED AND NR1 PAC OVLD IND WITH NR1 PAC AUTO SHUTDOWN. FLT CREW MADE AN IN-FLIGHT DIVERSION AND UNSC HEDULED LANDING. DOWNLOAD OF THE COMPUTER REVEALED 1 OCCUR OF NR1 PAC OVERTEMP AND 63 NR2 PAC OVERTEMP. LT AND RT PAC OVERTEMP SWITCHES FAILED BENCHCHECK. BOTH SWITCHES WERE REPLACED. DURING THE PAC SYSTEM OPS TEST DISCOVERED THE RT RAM AIR ACTUATOR HAD AN ELEC SHORT CAUSING THE CB TO POP. REPLACED THE RT RAM AIR ACTUATOR AND PAC SYSTEM OPS TESTS. DURI NG THE COMPUTER DOWNLOAD, 17 OCCURRENCES OF A NR1 PRECOOLER TEMP CONTROL SYSTEM FAIL MESSAGE WAS NOTED. ACCESSED FAN AI R TEMPERATURE THERMOSTATS FOR TROUBLESHOOTING AND UPON REMOVAL IT WAS NOTED THAT THE AMBIENT AIR TEMPERATURE PORTS ON EA 2 L 7 2 4F 4 F RT TE6CH 2007022700054 20070227 00054 CE 2007 2 27 HAG07001 1 20070223 G 5753 2322330177 SUPPORT BRACKET GARKENYON 26044 LEAR 60 60LEAR 5170707 CE PWA 305 PW305 NE FLAP ACTUATOR FAILED B H51R O OTHER F FLT CONT AFFECTED AP APPROACH 1 NM 03 252FX 5936 0295 196 DURING FLAP OPERATION, FLAP ACTUATOR SUPPORT BRACKETS FAILED CAUSING FLAP ACTUATOR TO DAMAGE LT WING RIB SEGMENT. 2 L 7 2 4F 4 F RT A10CE E35NE 2007030900001 20070309 00001 CE 2007 3 9 HAG07002 1 20070222 G 5532 4555030001804 PANEL LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312B WP VERTICAL STAB CRACKED B H51R K NONE O OTHER IN INSP/MAINT 1 NM 03 451WM 5571 091 DURING INSPECTION, FOUND RT SIDE VERTICAL STABILIZER CENTER BULLET FAIRING PANEL CRACKED IN 5 LOCATIONS. 2 L 7 2 4F 4 F RT T00008WI E6WE 2007031200058 20070312 00058 CE 2007 3 12 HAG2007001 1 20070223 G 5740 2322330177 SUPPORT BRACKET GARKENYON 26044 LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE ZONE 500 FAILED B H51R O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 NM 03 252FX 5936 0295 196 DURING FLAP OPERATION, FLAP ACTUATOR SUPPORT BRACKETS FAILED CAUSING FLAP ACTUATOR TO DAMAGE LT WING RIB SEGMENT. 2 L 7 2 4F 4 F RT A10CE E35NE 2007022600164 20070226 00164 CE 2007 2 26 HAGGAN07001 1 20070223 G 5740 2322330177 SUPPORT BRACKET GARKENYON 26044 LEAR 60 60LEAR 5170707 CE ZONE 500 FAILED B H51R O OTHER F FLT CONT AFFECTED AP APPROACH 1 NM 03 252FX 5936 0295 196 DURING FLAP OPERATION, FLAP ACTUATOR SUPPORT BRACKETS FAILED CAUSING FLAP ACTUATOR TO DAMAGE LT WING RIB SEGMENT. 2 L 7 2 4F RT A10CE 2007061300171 20070613 00171 NE 2007 6 13 IG0R200743437 2 20070508 G 7322 2526385 BELLOWS ALIDSG DPF2 PWA PT6 PT6A135 52043 NE FUEL CONTROL FAILED B O OTHER R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 NM 03 92 A59386 PCE92578 THE FUEL CONTROL (FCU) P/N 3244777-4-3-2, S/N A59386 DIRECTED THE ENGINE TO MIN FLOW SHORTLY AFTER LANDING WITHOUT ANY F URTHER POWER LEVER RESPONSE. THE CONTROL TSO IS 92.8. THIS CONTROL WAS LAST SERVICED BY INTERNATIONAL GOVERNOR SERVICE S (IGS) IN NOV 2006. THE AS RECEIVED TEST REVEALED FUEL FLOWS HAD DROPPED BELOW SCHEDULE AT ALL TEST POINTS EXCLUDING MI N FLOW AND MAX FLOW (THESE ARE BOTH PHYSICAL HARD STOPS). FURTHER INVESTIGATION REVEALED THAT THE EVACUATED SECTION OF THE BELLOWS (HONEYWELL P/N 2526385) WAS BREACHED (LOST THE VACUUM). THE INSPECTION CRITERIA FOR THE EVACUATED SECTION OF THE BELLOWS INVOLVES MEASURING THE BELLOWS HEIGHT AND COMPARING THE READING WITH THAT RECORDED DURING ORIGINAL MANUFACT 4 T E4EA 2007061300203 20070613 00203 EA 2007 6 13 IG0R200743667 2 20070509 G 7321 2523973 BEARING ALIDSG DPF2 PWA PT6 PT6* 52043 EA FCU FAILED B K NONE O OTHER NR NOT REPORTED 1 NM 03 C75067 PCEPH0218 ALLIED SIGNAL AEROSPACE (HONEYWELL) FUEL CONTROL UNIT (FCU)P/N 4138008-3, S/N C75067 RECEIVED FOR OVERHAUL AT INTERNATIO NAL GOVERNOR SERVICES (IGS) CRS IG0R976N EXPERIENCED A SPOOL BEARING (P/N 2523973) FAILURE. THE FCU WAS REMOVED FROM PT 6A ENGINE S/N PCE-PH0218. CONTROL APPEARS TO BE FIRST RUN OVERHAUL, HOWEVER, WE ARE UNABLE TO OBTAIN TIME SINCE NEW. IG S WILL FORWARD THE BEARING TO HONEYWELL FOR REVIEW. NOTE: THIS IS THE 5TH OR 6TH BEARING WE HAVE SEEN FAIL IN THE PAST 6 MONTHS OR SO. 3 T E2NE 2007061500172 20070615 00172 EA 2007 6 15 IG0R200746139 2 20070518 G 7322 2523629 HOUSING HONEYWELL DPF2 PWA PT6 PT6* 52043 EA FUEL CONTROL CORRODED B K NONE O OTHER IN INSP/MAINT 1 NM 03 2452 309482 CORROSION ON FLOW BODY METERING VALVE OPERATING LEVER COVER, EXCEEDS LIMITS. 3 T E2NE 2008011000133 20080110 00133 EA 2008 1 10 IG0R200751070 2 20071219 G 7321 2523631 BELLOWS HNYWL DPF2 BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA FCU DAMAGED B E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 NM 03 54 A33630 ENGINE WENT TO IDLE IN FLIGHT. FAILED BELLOWS BENCH TEST. BELLOWS BREACHED. UPON FURTHER INSPECTION THERE WAS NO PHYSICA L DAMAGE TO THE BELLOWS HOWEVER THERE WAS CORROSION ON THE TOP OF THE BELLOWS AND AT THE FIRST CONVOLUTION. REPLACED BEL LOWS AND RECALIBRATED FUEL CONTROL UNIT. 1 L 7 2 3T 4 T 3A20 E4EA 2007120500061 20071205 00061 CE 2007 12 5 IWP2720085003 1 20071123 G 3230 608100961 SPRING BEECH BEECH 60 B60 1153605 CE MLG DOWNLOCK MISINSTALLED G O OTHER G MULTIPLE FAILURE LD LANDING 1 WP 27 408FA P434 THIS AIRCRAFT EXPERIENCED A BENT /DAMAGED RT MAIN GEAR RETRACT ROD ASSEMBLY P/N 60-810057-617. A CURRENT OVERLOAD OF THE LANDING GEAR MOTOR CIRCUIT. THE RT MAIN GEAR FAILED TO EXTEND. THE EMERGENCY GEAR FAILED TO ALSO EXTEND THE RETRACTED M AIN. AC WAS FORCED TO LAND GEAR UP. INVESTIGATION REVEALED AN IMPROPERLY INSTALLED TORSION SPRING (IN QUESTIONABLE COND ITION) ON THE RT MAIN DOWN-LOCK CABLE (JURY STRUT). INVESTIGATION REVEALED THAT THE IMPROPER INSTALLATION OF THIS SPRING RESULTED IN THE RT DOWN LOCK CABLE MOVING INTO AND ENTANGLING WITH THE DRAG BRACE KNEE JOINT AND UPLOCK DOWNLOCK PIVOT POINT DURING RETRACTION. HOWEVER- IT HAS NOT BEEN PROVEN BY FAA INSPECTORS, THAT THE IMPROPER INSTALLATION OF THIS SPRIN 1 L 7 2 3O A12CE 2007031200022 20070312 00022 CE 2007 3 12 J0UR200700001 1 20070218 G 2121 EM6039 MOTOR BEECH 90 C90A 1152911 CE PWA PT6 PT6* 52043 EA BLOWER FAILED B J0UR A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 SO 09 1103G LJ1475 AIR CONDITIONING / VENT BLOWER MOTOR ASSEMBLY FAILED CAUSING SMOKE IN COCKPIT. PILOT DECLARED EMERGENCY AND LANDED AT CL OSEST AIRPORT WITHOUT FURTHER INCIDENT. 1 L 7 2 3T 3 T RT 3A20 E2NE 2007022600126 20070226 00126 2007 2 26 JZBR710K21907 2 20070219 G 7322 9867500500 NUT SKRSKY S76 S76C 8143008 NE FILTER CAP ASSY MISSING B K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 25 165ML 121B 760471 20026 DURING COMPLIANCE WITH MANDATORY SB 292-73-2824, (REPLACEMENT OF FUEL FILTER DRAIN SCREW ON HMU FILTER BOWL COVER ASSEMB LY), UPON COVER REMOVAL IT WAS DISCOVERED THAT THE NUT (P/N 9867500500) AND STOP WASHER (P/N 0319910870) WERE NOT INSTAL LED, MISSING FROM DRAIN SCREW THREADS ON THE INSIDE OF THE COVER ASSEMBLY. FILTER WAS REMOVED FOR FURTHER INSPECTION OF FILTER BOWL LOWER RECESSES WITH NO EVIDENCE OF MISSING PARTS INSIDE. 1 G 7 2 3U NC H1NE 2008010800325 20080108 00325 EU 2008 1 8 LJER12102007 2 20071206 G 7414 106825515 CONTACTOR PIPER PA44 PA44180 7104402 SO ROTAX ROTAX* EU MAGNETO DEBONDED B LJER A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 NM 09 2163 1 CONTACT POINT MATERIAL DEBONDED, POINTS WILL NOT CLOSE. 1 L 7 2 3O 3 I A19S0 EXPE3I 2007091800110 20070918 00110 EA 2007 9 18 LX5R200700006 2 20070913 G 7200 ENGINE SKRSKY S76 S76B 8143007 NE PWA PT6 PT6B36 52043 EA RIGHT MAKING METAL B LX5R A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 GL 19 761LL 3685 760379 PS36144 DURING CRUISE, SHORTLY AFTER T/O NR 2 ENG CHIP LIGHT ILLUMINATED. APPROPRIATE CB WAS PULLED TO TRY AND (BURN) OFF FUSS, BUT LIGHT REMAINED ILLUMINATED. IAW FLIGHT MANUAL, CREW LANDED WITHOUT INCIDENT AT NEAREST AIRPORT TO INVESTIGATE CHIP LIGHT. FLIGHT CONDITIONS WERE DAY VFR, NO CLOUDS, UN-RESTRICTED VISABILITY, WIND CALM, 65 DEGREE F, AND CRUISE SPEED WAS 145KTS. AFTER LANDING CREW CALLED HOME MAINT BASE. A MECHANIC TALKED TO OUR HOME BASE AND INSPECTED AFFECTED CHIP DET ECTOR. IT WAS DETERMINED, THE SMALL SLIVERS OF METAL WERE ACCEPTABLE IAW MM. ENG WAS CLOSED UP AND THE CREW PERFORMED A GROUND RUN AND CHIP LIGHT DID NOT COME BACK ON. FLGT CONTINUED TO DESTINATION, WITHOUT OTHER INDICATIONS. (K) 1 G 7 2 4U 4 U H1NE E4EA 2007022600031 20070226 00031 SO 2007 2 26 M1144 2 20070208 G 8530 EXHAUST VALVE CESSNA 421 421C 2076016 CE CONT O520 GTSIO520* 17032 SO NR 5 CYLINDER BROKEN B B EMER. DESCENT R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CE 03 540CA 1776 612 421C0144 PILOT REPORTED THAT RT ENGINE WAS RUNNING ROUGH IN FLIGHT. HE DID NOT SHUTDOWN ENGINE. FOUND NO COMPRESSION IN NR 5 CYLI NDER ON RT ENGINE. REMOVED CYLINDER AND FOUND EXHAUST VALVE WAS BROKEN. INSTALLED OVERHAULED CYLINDER ASSEMBLY. 1 L 7 2 3O 3 O A7CE E7CE 2007040200135 20070402 00135 CE 2007 4 2 M40675 1 20070320 G 2740 45AS610023139 ACTUATOR BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE PITCH TRIM INOPERATIVE C R71A O OTHER F FLT CONT AFFECTED DE DESCENT 1 WP 05 790SS 1550 RK363 DIFFICULTY OCCURRED UPON DESCENT. PILOT RECEIVED A WARNING PITCH TRIM WAS NOT SYNCHRONIZED WITH AUTOPILOT SYSTEM AND TO PREPARE FOR RESISTANCE WHEN AUTOPILOT IS DISCONNECTED. PITCH TRIM ACTUATOR WAS FOUND INOPERATIVE IN THE EMERGENCY MODE/A UTOPILOT MODE. REPLACED PITCH TRIM UNIT AND RETURNED AIRCRAFT TO SERVICE. THIS AIRCRAFT WAS LAST INSPECTED ON 11-9-06 AT 1408.6 TT. 2 H 7 2 4F 4 F RT A16SW E25EA 2007050400151 20070504 00151 GL 2007 5 4 MDR041607 1 20070416 G 3244 TIRE AMTR 500 ECLIPSE500 05614K5 GL LT MLG FAILED C O OTHER O OTHER TX TAXI/GRND HDL 1 EA 27 110DJ 41 000007 LT MAIN LANDING GEAR WHEEL AND TIRE ASSEMBLY BLEW OUT DURING TAXI. WHEEL HAS BEEN QUARANTINED AND WILL BE FORWARDED TO A N INDEPENDENT INSPECTION LAB FOR FURTHER REVIEW. 1 L 7 2 3F RT EXPA1L72 2007100200029 20071002 00029 SO 2007 10 2 MINR2007918A 1 20070918 G 7810 40B19974 EXHAUST PIPE PIPER PA46 PA46350P 7104602 SO LYC O540 TIO540AE2 EA ENGINE BULGED B K NONE O OTHER IN INSP/MAINT 1 NM 05 498MM 1349 4636149 THE EXHAUST CROSSOVER EXHAUST PIPE WAS FOUND SEVERELY BULGED IN THE AREA COVERED BY THE HEAT SHROUD. THE DAMAGE WAS TO T HE POINT, ISSUES WERE FORMING THAT WOULD HAVE LED TO RUPTURE. IF AN EXHAUST LEAK OCCURS IN THIS AREA, THE HEAT WILL AFFE CT THE MAGNETO, FUEL AND OIL LINES. IT IS HIGHLY RECOMMENDED BY MAINTENANCE PERSONNEL THAT THE HEAT SHROUD BE REMOVED AT EACH 100 HOUR INSPECTION FOR AIRCRAFT WITH MORE THAT 500 HOURS. NR 3 CYLINDER EXHAUST RISER PN 40B19827 WAS ALSO FOUND SEVERELY BULGED. THIS CAN BE SEEN WITH THE ENGINE COWLING REMOVED WITHOUT FURTHER DISASSEMBLY. THE LT EXHAUST TRANSITI ON PN 47C19848 WAS FOUND BULGED AND CRACKED. THIS CAN BE SEEN WITH A MIRROR AND FLASHLIGHT. IF ANY DAMAGE IS FOUND ON T 1 L 7 1 3O 3 O RT A25SO E14EA 2007102300092 20071023 00092 CE 2007 10 23 N843E12007 1 20070801 G 2432 9036102331 HED BEECH 1900 1900D 1154162 CE PWA PT6 PT6A6 52043 EA BATTERY FAULTED C A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 NE 03 843E 7178 UE339 CREW LEFT STATION. TWENTY MINUTES IN FLIGHT "BATT TIE OPEN" ANNUNCIATOR ILLUMINATED. CREW RETURNED TO STATION WITHOUT ISSUE. REMOVED AND REPLACED BATTERY HED. OPS CHECK GOOD. 2 L 7 2 4T 3 T RT A24CE E4EA 2008011400058 20080114 00058 CE 2008 1 14 ODAA121907001 1 20071219 G 5510 ACCESS PANEL RAYTHN DH125 HAWKER800XP 7150012 CE GARRTT TFE731 TFE731* 01518 WP OUT OF ADJUST E ODAA O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 EA 21 2G 258354 PILOT REPORTED RUDDER PEDALS BINDING FOUND DURING PREFLIGHT, WITH RT PEDAL FORWARD AND LT PEDAL AFT. AFTER APPLYING PRE SSURE TO PEDALS WITH FEET, PEDALS BECAME UNBOUND WITH POPPING NOISE HEARD. INSPECTED RUDDER SYSTEM. FOUND RUDDER BINDI NG AT PANEL SCREW FOR LOWER CONTROL COLUMN ACCESS, FORWARD, DUE TO BEND IN PANEL. REMOVED SCREWS AND ADJUSTED PANEL FOR BETTER CLEARANCE. REPLACED SCREWS WITH SHORTER VERSION OF SAME. RUDDER SYSTEM OPERATED NORMALLY. REFERENCE MM, CHAPT ER 27. 2 L 7 2 4F 4 F RT A3EU E6WE 2007121400348 20071214 00348 GL 2007 12 14 ODAR15DR1 1 20070411 G 2421 BC4101 ALTERNATOR CIRRUS SR SR22 2130001 GL CONT O550 IO550* SO NR 2 DESTROYED B ODAR O OTHER J WARNING INDICATION NR NOT REPORTED 1 EA 21 15DR 0394 OWNER REPORTED NR2 ALTERNATOR LIGHT ILLUMINATED. REMOVED TOP COWLING TO INSPECT NR2 ALTERNATOR. FOUND NR2 ALTERNATOR B ROKEN OFF AT MOUNTING PLATE BY (3) STUDS. ONE STUD STILL ATTACHED WITH NUT, BUT LOOSE. REMOVED P/N BC410-1, S/N 092140 3. 1 L 7 1 3O 3 O NT A00009CH E3SO 2007041700030 20070417 00030 GL 2007 4 17 ODAR3 1 20070411 G 2421 BC4101 ALTERNATOR CIRRUS SR SR22 2130001 GL CONT O550 IO550* SO NR 2 DESTROYED B ODAR K NONE J WARNING INDICATION IN INSP/MAINT 1 EA 21 15DR 0394 OWNER REPORTED NR 2 ALTERNATOR LIGHT ILLUMINATED. REMOVED TOP COWLING TO INSPECT NR 2 ALTERNATOR. FOUND NR 2 ALTERNATO R BROKEN OFF AT MOUNTING PLATE BY (3) STUDS. ONE STUD STILL ATTACHED WITH NUT, BUT LOOSE. REMOVED P/N BC410-1, S/N 092 1403. PICTURES AVAILABLE AT THIS FACILITY. 1 L 7 1 3O 3 O NT A00009CH E3SO 2007050100085 20070501 00085 CE 2007 5 1 OMKR20071 1 20070331 G 3230 08420003 DRAG LINK CESSNA 310 310C 2074210 CE CONT O470 IO470* 17026 SO NLG BROKEN B OMKR O OTHER O OTHER LD LANDING 1 NM 03 4411 39024 UPON LANDING, THE NOSE LANDING GEAR DRAG LINK ASSEMBLY P/N 0842000-3 BROKE AT THE STRUT ATTACH POINT, ALLOWING THE NOSE GEAR TO COLLAPSE REARWARD, CAUSING THE AIRCRAFT TO SLIDE ON ITS NOSE UNTIL IT STOPPED. THE DRAG LINK ASSEMBLY APPEARS T O HAVE BROKEN THROUGH THE FORWARD ATTACH HOLE. TOTAL TIME OF THE PART AND TOTAL TIME OF THE AIRCRAFT ARE UNKNOWN AT THIS TIME DUE TO ABSENCE OF LOG BOOKS. CURRENT HOBBS TIME IS 118.4. 1 L 7 2 3O 3 O 3A10 E1CE 2007120500057 20071205 00057 CE 2007 12 5 OMKR200711211 1 20071121 G 2500 443030401 ADJUSTER CESSNA 206 U206G 2073356 CE CONT O520 IO520* 17032 SO HARNESS ADJUSTER IMPROPER PART B OMKR K NONE O OTHER IN INSP/MAINT 1 NM 03 9957R U20606999 AD 2004-19-01C CALLS FOR A SPRING TO BE REMOVED FROM SHOULDER HARNESS ADJUSTER P/N443030-401, THAT WAS INADVERTENTLY INS TALLED ON A CERTAIN BATCH OF ACCESSORY KITS SHIPPED FROM MFG 1984 THROUGH 1986. THIS RESULTED IN AD 86-26-04 BEING ISSU ED. CURRENTLY HAVE (2) AIRCRAFT IN THE HANGAR WITH THIS PN ADJUSTER WITH SPRINGS INSTALLED. THEY DO NOT FALL INTO THE AFFECTIVITY RANGE OF THE AD OR SB. CONTACTED THE ENGINEER ON THE BACK OF THE AD, AND HE INSISTS I DO NOT HAVE AN AFFECT ED ADJUSTER. HE HAD A MFG REP. WHO WAS FAMILIAR WITH THE AD CONTACT ME AND I FOUND OUT THE AD RESULTS FROM (INCORRECTLY ) INSTALLED SPRINGS. I SUBMIT THE AD REQUIRES CLARITY AS TO THE DIFFERENCE BETWEEN (INADVERTENTLY INSTALLED) AND (INCOR 1 H 7 1 3O 3 O A4CE E5CE 2007013100171 20070131 00171 SO 2007 1 31 PAI52007S4448 2 20070130 G 8520 STUD CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO NR 4 CYLINDER BROKEN B PAI5 K NONE O OTHER IN INSP/MAINT 1 SO 05 414CJ 1403 414A0432 519053 DURING ANNUAL INSPECTION FOUND 5 BROKEN HOLD DOWN STUDS ON NR 4 CYLINDER. ENGINE WAS MODIFIED IAW RAM STC SE3630SW AND SE3631SW AT PREVIOUS OVERHAUL. 1 L 7 2 3O 3 O A7CE E8CE 2007032600098 20070326 00098 CE 2007 3 26 PAI52007S4508 1 20070322 G 7600 10052417717 CONDITION LEVER BEECH B300 B300 1159232 CE PWA PT6 PT6A6 52043 EA COCKPIT LOOSE B PAI5 K NONE O OTHER IN INSP/MAINT 1 SO 05 507EB 4957 FL81 PILOT NOTED RT ENGINE CONDITION LEVER CONTROL FELT LOOSE AND IDLE N1 SPEED LOW. UPON INSPECTION, MAINTENANCE FOUND ALL SCREWS ATTACHING CONDITION LEVER TO QUADRANT LOOSE TO THE POINT OF ALMOST FALLING OUT. 2 L 7 2 4T 3 T RT A24CE E4EA 2007061400142 20070614 00142 CE 2007 6 14 PAI52007S4573 1 20070515 G 5730 00011013333 SKIN BEECH B300 B300 1159232 CE WING CRACKED B PAI5 K NONE O OTHER IN INSP/MAINT 1 SO 05 507EB 5010 196 FL81 WHILE PERFORMING PHASE 2 INSPECTION NOTED AN 8 INCH LONG SPANWISE CRACK ON LOWER SURFACE OF WING LEADING EDGE SKIN P/N 0 00-110133-33. ALSO FOUND CHANNEL P/N 101-910119-147 INSIDE THE ABOVE MENTIONED SKIN BROKEN IN TWO. REPLACED BOTH PARTS WITH NEW PARTS FROM BEECH. 2 L 7 2 4T RT A24CE 2007100300016 20071003 00016 EU 2007 10 3 PAI52007S4724 1 20070926 G 3010 80232118401 DUCT PIAGIO P180 P180 6960204 EU PWA PT6 PT6* 52043 EA WING LE CRACKED B PAI5 K NONE O OTHER IN INSP/MAINT 1 SO 05 145SL 2994 1093 DURING 3000 HOUR D-CHECK FOUND 3 OF 4 WING OB LEADING EDGE PANELS WITH CRACKED HEATING DUCTS. 1 H 7 2 3O 3 T RT A59EU E2NE 2007110500004 20071105 00004 SW 2007 11 5 PAI52007S4751 1 20071024 G 2910 T610488109 LINE GULSTM 690TP 690B 7630516 SW HYD SYSTEM RUPTURED B PAI5 A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 SO 05 91CT 11428 HYDRAULIC PRESSURE FLEX LINE AT RT ENGINE DRIVEN HYDRAULIC PUMP RUPTURED IN FLIGHT CAUSING LOSS OF HYDRAULIC FLUID. 1 H 7 2 3T 2A4 2007050100117 20070501 00117 CE 2007 5 1 PAZR200700001 1 20070416 G 5551 663110215 ATTACH FITTING CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE ZONE 300 CRACKED B PAZR K NONE O OTHER IN INSP/MAINT 1 CE 03 186XL 2179 5605186 DURING A SCHEDULED INSPECTION, A 1.5 INCH CRACK WAS FOUND IN THE LOWER RADIUS OF THE HORIZONTAL STABILIZER AFT ATTACH FI TTING. 2 L 7 2 4F 4 F RT A22CE E00059EN 2007020600050 20070206 00050 2007 2 6 QKPR07001 1 20070202 G 4930 38828406 FCU HONEYWELL GTCP36150RR APU LEAKING B QKPR O OTHER L NO TEST NR NOT REPORTED 1 SO 05 THERE IS A PIN HOLE IN THE FCU HOUSING. IN THIS CASE THERE WAS 4 STREAMS OF FUEL AND HEAVY MISTING. 2007041000068 20070410 00068 NM 2007 4 10 QXEANM09402 1 20070315 G 4920 164161100 DRAIN VALVE SUNDSTRANDEM BOMBDR DHC8 DHC8402 1390042 NM PWC 150 PW150A EA APU MISINSTALLED G K NONE O OTHER IN INSP/MAINT 1 NM 09 402QX 4032 BALL ON WRONG SIDE OF SPRING, WHICH ALLOWS IT TO REST IN CLOSED POSITION, NOT ALLOWING PROPER DRAINAGE. 2 H 7 2 4T 4 T RT A13NM E00062EN 2007040900125 20070409 00125 NM 2007 4 9 QXEANM09417 1 20070314 G 4920 164161100 DRAIN VALVE BOMBDR DHC8 DHC8402 1390042 NM PWC 150 PW150A EA APU PLUGGED G QXEA O OTHER O OTHER NR NOT REPORTED 1 NM 09 417QX 4086 BALL ON WRONG SIDE OF SPRING ALLOWING IMPROPER DRAINAGE. 2 H 7 2 4T 4 T RT A13NM E00062EN 2007013100185 20070131 00185 NE 2007 1 31 R021692 3 20070117 G 6111 D7745 BEARING BEECH 1900 1900D 1154162 CE PWA PT6 PT6* 52043 EA HARTZL HCE4A HCE4A3A NE PROPELLER BLADE BROKEN B SJ3R O OTHER E VIBRATION/BUFFET IN INSP/MAINT 1 GL 05 SJ3R 3115 HJ1819 ON 12/14/06 REPORTED AIRCRAFT VIBRATIONS FROM STBD ENGINE. INSPECTION OF PROPELLER ON GROUND REVEALED EXCESSIVE RADIAL P LAY OUT OF LIMIT OF NR 3 BLADE. PROPELLER REMOVED FROM AIRCRAFT FOR FURTHER INVESTIGATION. SERVICE CENTER NOTES: BLADE NR 3 CAM FOLLOWER BROKEN, PRELOAD PLATE GOUGED, BLADE SIDE D-7745 BEARING CRACKED RADIALLY AND PIECE MISSING. RETAINING WASHER ATTACHED TO PC KNOB. BLADE NR 3 FORK SLOT WORN 0.028, OTHER 3 SLOTS WORN 0.015-0.021, CIRCUMFERENTIAL WEAR IN FOR K SEAT. BLADE NR 3 RETENTION SHOULDER HEIGHT MEASURED 0.914 - 0.974, UNABLE TO PERFORM OPTICAL COMPARATOR INSPECTION OF RADIUS DUE TO SHOULDER HEIGHT DIMENSION BELOW 0.972. SEE S/B 287. 2 L 7 2 4T 3 T RT A24CE E2NE 5 C P10NE 2007032200091 20070322 00091 GL 2007 3 22 R022366 3 20070316 G 6110 A20742 SEAL RING CIRRUS SR SR22 2130001 GL CONT O550 IO550F 17042 SO HARTZL HCJ3Y PHCJ3YF1 GL PROPELLER BLADE DEBONDED B SJ3R K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 GL 05 81 FP5296B TEFLON (BLADE SEAL) DEBONDED FROM THE SHANK OF BLADE SN A0336 CAUSING GREASE LEAK. 1 L 7 1 3O 3 O NT A00009CH E3SO 5 C P36EA 2007082100233 20070821 00233 GL 2007 8 21 R0240301 3 20070814 G 6110 B3493 BRACKET MTSBSI MU2 MU2B60 5780460 CE HARTZL HCB4T HCB4TN5 GL PROPELLER CRACKED B SJ3R K NONE O OTHER IN INSP/MAINT 1 GL 05 FIVE B-3493 START LOCK BRACKETS WERE FOUND DURING PENETRANT INSPECTION TO BE CRACKED AT THE SAME LOCATION. CRACKS ARE LO CATED ON THE EXTERIOR START PIN BORE NEXT TO THE SPINNER MOUNTING BOLT RELIEF CUT-OUT. THIS BRACKET IS PART OF THE 830-3 4L START LOCK UNIT INSTALLED ON 4-BLADED MU-2S. 1 H 7 2 3T RT A10SW 6 C P40EA 2007100200024 20071002 00024 CE 2007 10 2 RDA092407 1 20070924 G 2842 05235571 TRANSMITTER CESSNA 175 175 2072502 CE CONT O300 GO300* 17022 SO FUEL QTY CRACKED G K NONE O OTHER IN INSP/MAINT 1 GL 23 9456B 2440 55256 WHILE CALIBRATING THE FUEL QUANTITY SYSTEM THE LT FUEL GAUGE WOULD SHOW AN INCREASE IN QUANTITY THEN START DECREASING. WHILE TROUBLESHOOTING THE LT TANK FUEL QUANTITY SENDER, FOUND 2 CRACKS APPROXIMATELY 1 INCH LONG IN THE BRASS FLOAT. 1 H 7 1 3O 3 O NT 3A17 E298 2007062700005 20070627 00005 CE 2007 6 27 RUAGACC61007 1 20070610 G 3210 16410077 SPRING CESSNA 188 T188C 2073012 CE CONT O520 TSIO520* 17040 SO LT MLG FAILED G RUAG O OTHER O OTHER CL CLIMB 1 NM 05 2535J 7163 181 T18803471T AIRCRAFT ACCIDENT. LT MLG (SPRING) FAILED DURING TAKEOFF ATTEMPT, APPROXIMATELY 6 INCHES ABOVE AXLE. NO EVIDENCE OF PR EVIOUS FRACTURE (CRACK) COULD BE DETECTED. LT WING BUCKLED AND AIRCRAFT NOSED OVER. SUBSTANTIAL DAMAGE, NO INJURIES. 1 L 7 1 3O 3 O A9CE E8CE 2007121300378 20071213 00378 EU 2007 12 13 S0700432 1 20071203 G 2435 COMMUTATOR BFGOODRICH PILATS PC12 PC1245 7090551 EU STARTER GEN FAILED B B A EMER. DESCENT UNSCHED LANDING H E ELECT. POWER LOSS-50 PC VIBRATION/BUFFET CR CRUISE 1 CE 07 462PC 97102 462 DURING CRUISE FLIGHT, LOUD NOISE FROM ENGINE COMPARTMENT FOLLOWED BY VIBRATION AND LOSS OF PRIMARY ELECTRICAL POWER. UP ON INSPECTION, ONE SEGMENT FROM COMMUTATOR WAS MISSING AND AFT END OF GENERATOR AND BRUSHES HAD SUSTAINED HEAVY DAMAGE. AFTER REPLACEMENT WITH OVERHAULED UNIT, NO ABNORMALITIES WERE NOTED. 1 L 7 1 3T RT A78EU 2007022700071 20070227 00071 SO 2007 2 27 SDR0701 1 20070123 G 5312 1159B2156227 ANGLE GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6108 NE BS 793 CRACKED W K NONE O OTHER IN INSP/MAINT 1 EA 29 254GA 11823 1032 DURING SCHEDULED 5000 LANDING FS793 BULKHEAD CAP ANGLE NDT INSPECTION, DETECTED A 1.25 INCH LONG CRACK IN RT BULKHEAD CA P ANGLE. MANUFACTURER HAS RECOMMENDED REPLACEMENT OF LT AND RT FS793 BULKHEAD CAP ANGLES. 2 L 7 2 4F 4 F RT A12EA E25NE 2007021300080 20070213 00080 CE 2007 2 13 SO19200712477 1 20070126 G 3297 WIRE CESSNA 177 177RG 2073709 CE LYC O360 IO360A1B6 41514 EA WARNING HORN BROKEN C O OTHER P NO WARNING INDICATION LD LANDING 1 SO 19 177RR 177RG0937 DURING THIRD NIGHT CURRENCY LANDING PILOT FAILED TO EXTEND GEAR AND DIDN'T HEAR THE GEAR UP WARNING HORN. SHOWING A BRO KEN WIRE AT THE GEAR WARNING HORN SWITCH. 1 H 7 1 3O 3 O A20CE 1E10 2007012500157 20070125 00157 NM 2007 1 25 SROM200700001 1 20070105 G 2120 65544709 DUCT BOEING 737 737201 1384454 NM PWA JT8 JT8D15 52051 NE A/C PACK RUPTURED I SROM H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AL 03 245US 22751 UPON TAKEOFF A POP WAS WAS HEARD FOLLOWED BY PERCEIVED SMOKE (DUST) IN THE CABIN. PACS WERE SELECTED TO OFF AND A IMMED IATE LANDING MADE AT THE DEPARTURE AIRPORT. ALL COCKPIT INDICATIONS NORMAL. FOUND LT AIR CONDITIONING PAC MIXING CHAMB ER AND HOT AIR SUPPLY DUCT SEPARATED/ DAMAGED ALLOWING HOT CONDITIONED AIR TO ENTER CABIN THROUGH RETURN GRILLS, THUS CR EATING DUST. APPEARS TO HAVE EXPERIENCED INTERNAL DAMAGE RESULTING IN BACK PRESSURE WHICH CAUSED THE DUCT/FLANGE FAILUR E. NO OTHER DAMAGE NOTED. REPLACED MIXING AND HOT AIR DUCTS. 2 L 7 2 4F 4 F A16WE E2EA 2007061400143 20070614 00143 NM 2007 6 14 SROM200700002 1 20070516 G 5280 DOOR BOEING 737 737205 1384456 NM NLG BINDING C SROM A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 AL 03 736BP 23465 LOUD VIBRATION AFTER TAKEOFF. VIBRATION INCREASED WITH SPEED AND DECREASED AT LOWER SPEEDS. RETURNED TO DEPARTURE AIRP ORT. PERFORMED VIBRATION CONDITIONAL INSPECTION. FOUND NLG DOORS ON GRAVEL SKI EQUIPPED AIRCRAFT TO BE BINDING ON EACH OTHER. ADJUSTED PER AMM 32-22-12. AIRCRAFT RELEASED AN OPERATIONAL CHECK FLIGHT NORMAL. NO REPORT OF VIBRATION ON SU BSEQUENT FLIGHTS. 2 L 7 2 4F RT A16WE 2007061300244 20070613 00244 NM 2007 6 13 SROM200700003 1 20070522 G 5753 BEARING BOEING 737 737205 1384456 NM ROD END LOOSE C SROM A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 AL 03 736BP 23465 AIRFRAME BUFFET NOTED AFTER GEAR UP ON TAKEOFF & BEFORE FLAP RETRACTION & POWER REDUCTION DURING CLIMB. THIS IS THE 2ND WRITE UP OF THIS CONDITION. PERFORMED AIRFRAME CONDITIONAL INSPECTION. REPLACED NLG GRAVEL SKI DEFLECTOR ACTUATOR DUE TO LOOSE ROD END AND REPLACED BEARING IN LEFT INBOARD GROUND SPOILER OUTBOARD ACTUATOR LINKAGE DUE TO LOOSENESS. AIRCR AFT RELEASED FOR OPERATION CHECK FLIGHT WITH NO REPORTS OF VIBRATION ON TWO TAKEOFFS DURING CHECK FLIGHT. 2 L 7 2 4F RT A16WE 2007061400179 20070614 00179 NM 2007 6 14 SROM200700004 1 20070531 G 2120 28410 VALVE BOEING 737 737205 1384456 NM FLOW CONTROL FLUTTER C SROM A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 AL 03 736BP 7463 23465 AFTER TAKEOFF AT AROUND 1000 FEET VIBRATION STARTED IN FWD PART OF AIRCRAFT AND TRAVELED TO REAR OF AIRCRAFT. AFTER SHU TTING OFF ALL PACKS AND BLEEDS IT SLOWLY WENT AWAY. AIRCRAFT RETURNED TO DEPARTURE AIRPORT. AIRCRAFT INSPECTED WITH NO FAULTS FOUND AND RELEASED FOR FLIGHT TO MAINTENANCE BASE WITH SLIGHT VIBRATION NOTED IN FLOOR. FURTHER INSPECTION FOUN D CRACKED E&E BAY COOLING DUCT AND CHATTERING E&E BAY FLOW CONTROL VALVE. REPLACED DUCTS AND VALVE. NO REPORTS OF VIBR ATION ON SUBSEQUENT FLIGHT. 2 L 7 2 4F RT A16WE 2007082400323 20070824 00323 NM 2007 8 24 SROM200700006 1 20070801 G 5311 FRAME BOEING 737 737205 1384456 NM PWA JT8 JT8D17 52049 NE BS 616 CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR63-CRACK ON BODY FRAME INNER CHORD BS616 RT SIDE AT STUB BEAM LOWER CHORD ATTACH (ABOVE WING BOX BL64R). DAMAGE OF BOD Y FRAME INNER CHORD STA 616 RT SIDE AT STUB BEAM LOWER CHORD ATTACH REMOVED IAW MFG SB 737-53-1182R1. REPAIR ANGLE INSTA LLED IAW MFG SB 737-53-1182R1 AND MFG MSG NR: 1-508321689-2. 2 L 7 2 4F 4 F RT A16WE E2EA 2007090600068 20070906 00068 NM 2007 9 6 SROM200700007 1 20070807 G 5315 FLOORBEAM BOEING 737 737205 1384456 NM PWA JT8 JT8D17A 52049 NE BS 660 CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR228-CRACK IN FLOORBEAM AND WEB STA 660 BL0. CRACKED FLOORBEAM AND WEB AT STA 660 BL0 REPAIRED IAW MFG SB 737-57-1210, REV 1, DATED AUG 27/07. 2 L 7 2 4F 4 F RT A16WE E2EA 2007091700005 20070917 00005 NM 2007 9 17 SROM200700008 1 20070808 G 5330 SKIN BOEING 737 737205 1384456 NM PWA JT8 JT8D17 52049 NE BS 900 S17-18L DENTED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR247- DENT FOUND STA 900 LT BETWEEN STRINGERS 17 AND 18. REPAIRED IAW MFG SRM 53-30-3, PAGES 253-320 AND 51-30-3, PAGE 7 AND 51-30-02. 2 L 7 2 4F 4 F RT A16WE E2EA 2007091300062 20070913 00062 NM 2007 9 13 SROM200700009 1 20070808 G 3211 SUPPORT FITTING BOEING 737 737205 1384456 NM RT MLG DAMAGED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR269 - WEAR DAMAGE RIGHT MAIN LANDING GEAR FUSE TO TRUNNION SUPPORT BEAM ATTACH FITTING. REPAIRED IN ACCORDANCE WITH B OEING APPROVED FAA FORM 8100-9 MESSAGE 1-515849678-6, DATED AUGUST 23, 2007. 2 L 7 2 4F RT A16WE 2007091300146 20070913 00146 NM 2007 9 13 SROM200700010 1 20070808 G 5743 65C313326 SUPPORT BEAM BOEING 737 737205 1384456 NM RT MLG CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR270 - PITTING RIGHT MAIN LANDING GEAR TRUNNION SUPPORT BEAM UPPER SURFACE. REPLACED RIGHT MLG SUPPORT BEAM IN ACCORDA NCE WITH BOEING 737 AMM 57-15-0. 2 L 7 2 4F RT A16WE 2007091300147 20070913 00147 NM 2007 9 13 SROM200700011 1 20070808 G 5743 658276415 SUPPORT BEAM BOEING 737 737205 1384456 NM LT MLG CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR279 - PITTING LEFT MAIN LANDING GEAR TRUNNION SUPPORT BEAM UPPER SURFACE (LIGHT). REPLACED LEFT MLG SUPPORT BEAM IN A CCORDANCE WITH BOEING 737 AMM 57-15-0. 2 L 7 2 4F RT A16WE 2007091700021 20070917 00021 NM 2007 9 17 SROM200700012 1 20070808 G 5343 TRUNNION BOEING 737 737205 1384456 NM PWA JT8 JT8D17 52049 NE LT MLG WORN C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 WEAR DAMAGE, LT MLG FUSELAGE TO TRUNNION SUPPORT BEAM ATTACH FITTING. BLEND REPAIRED IAW MFG, FORM 8100-9, MESSAGE NR 1- 515849678-6, DATED AUGUST 23, 2007. 2 L 7 2 4F 4 F RT A16WE E2EA 2007091300063 20070913 00063 NM 2007 9 13 SROM200700013 1 20070808 G 5315 FLOORBEAM BOEING 737 737205 1384456 NM FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR291 - CORROSION ON FLOORBEAM UPPER FLANGE STA 344 LBL 48-60. REPAIRED IN ACCORDANCE WITH BOEING SRM 53-10-9, FIGURE 1 . 2 L 7 2 4F RT A16WE 2007090600085 20070906 00085 NM 2007 9 6 SROM200700014 1 20070810 G 5315 FLOORBEAM BOEING 737 737205 1384456 NM PWA JT8 JT8D17A 52049 NE ZONE 100 CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR296-CORROSION ON FLOORBEAM UPPER FLANGE AT STA 294 AND RBL 43 TO 53. FLOORBEAM UPPER FLANGE FROM RBL 6 (EXISTING SPLIC E) TO RBL 60, STA 294 REMOVED AND REPLACED IAW WITH MFG SRM 53-10-9, FIG 5, SHEET 1-5. 2 L 7 2 4F 4 F RT A16WE E2EA 2007091400101 20070914 00101 NM 2007 9 14 SROM200700015 1 20070810 G 5512 SKIN BOEING 737 737205 1384456 NM HORIZONTAL STAB GOUGED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR378 - RT STABILIZER LOWER SURFACE FOUND WITH A GOUGE IN THE SKIN ON THE RIB ATTACH LOCATION AT 138.7 DEPT IS 0.037 WHI CH IS OVER 50 PERCENT. DAMAGED SECTION OF SKIN ON RT STABILIZER LOWER SURFACE LOCATION 138.7 REMOVED. REPAIR DOUBLER F ABRICATED AND INSTALLED IN ACCORDANCE WITH DER APPROVED DRAWING NR 73R55116228. 2 L 7 2 4F RT A16WE 2007091300148 20070913 00148 NM 2007 9 13 SROM200700016 1 20070810 G 5330 SKIN BOEING 737 737205 1384456 NM FUSELAGE CRACKED C SROM K NONE Z SIGNIFICANT FAILURE REPORT IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR393 - FUSELAGE SKIN CRACKED AT AIRSTAIR CONTROL HANDLE CUTOUT AT BS 378 BETWEEN STRINGERS 21-L AND 22-L. REPAIR DOUBL ER FABRICATED AND INSTALLED IN ACCORDANCE WITH BOEING SB 737-53-1093. 2 L 7 2 4F RT A16WE 2007091300149 20070913 00149 NM 2007 9 13 SROM200700017 1 20070810 G 5343 SUPPORT BEAM BOEING 737 737205 1384456 NM NLG CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR419 - CRACK ON NLG ACTUATOR SUPPORT BEAM AT BS 227-0 UPPER RIGHT SIDE. REPLACED NLG ACTUATOR UPPER RIGHT SIDE SUPPORT BEAM IN ACCORDANCE WITH BOEING 737 SRM 51-10-1, 53-10-2 AND 51-30-2. 2 L 7 2 4F RT A16WE 2007090600075 20070906 00075 NM 2007 9 6 SROM200700018 1 20070818 G 5330 SKIN BOEING 737 737205 1384456 NM PWA JT8 JT8D17A 52049 NE BS 907 NICKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NICK STA 907 STR 22 LT. NICK AT STA 907, STR 22L REPAIRED IAW SRM 53-30-3, FIG 48. NICK BEYOND LIMITS AND DAMAGE REMOVED . HFEC IAW NDT PART 6, 53-30-00, FIG 4 OF REPAIR AT FUSELAGE SKIN STA 907 STR 22L. NO CRACKS EVIDENT. 2 L 7 2 4F 4 F RT A16WE E2EA 2007090600001 20070906 00001 NM 2007 9 6 SROM200700019 1 20070818 G 5330 SKIN BOEING 737 737205 1384456 NM PWA JT8 JT8D17A 52049 NE ZONE 100 NICKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NICK STA 887 STR 24L-25L LT. DAMAGED AREA OF SKIN REMOVED AND REPAIR PLATES FABRICATED IAW SRM 53-30-3, FIG 48. INSTALL ED REPAIR IAW 51-30-2. 2 L 7 2 4F 4 F RT A16WE E2EA 2007090600071 20070906 00071 NM 2007 9 6 SROM200700020 1 20070818 G 5330 SKIN BOEING 737 737205 1384456 NM PWA JT8 JT8D17A 52049 NE ZONE 100 NICKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NICK STA 847 STR 21 LT. NICK AT STA 847 STR 21L FOUND TO BE BEYOND LIMITS. NICK REMOVED AND AREA AT STA 847 STR 21L REP AIRED IAW SRM 53-30-3, FIG 48. 2 L 7 2 4F 4 F RT A16WE E2EA 2007090600079 20070906 00079 NM 2007 9 6 SROM200700021 1 20070810 G 5315 FLOORBEAM BOEING 737 737205 1384456 NM PWA PT6 PT6A114A 52043 NE BS 328 CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR392-CORROSION ON UPPER CHORD OF FLOORBEAM STA 328 RBL 52. FLOORBEAM REPAIRED IAW SRM 53-10-9, FIG 5, PAGE 21. 2 L 7 2 4F 3 T RT A16WE E4EA 2007090600066 20070906 00066 NM 2007 9 6 SROM200700022 1 20070803 G 5311 FRAME BOEING 737 737205 1384456 NM PWA JT8 JT8D17A 52049 NE BS 783 S25R CORRODED I SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR145-LIGHT CORROSION ON FRAME AT STA 783 STR 25R. REPAIRED FRAME IAW MFG MESSAGE NR 1-518342007-2, DATED AUG 1, 2007 AN D PRODUCTION DRAWINGS FOR PN 65-47959-47 STRAP AND PN 65C31240-1 FRAME DOUBLER. 2 L 7 2 4F 4 F RT A16WE E2EA 2007091700046 20070917 00046 NM 2007 9 17 SROM200700023 1 20070807 G 5524 NUT PLATE BOEING BOEING 737 737205 1384456 NM PWA JT8 JT8D17 52049 NE ELEVATOR STRIPPED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 982 457 23465 NR122-LT ELEVATOR TRIM TAB IB HINGE FITTING MISSING BOLT. NEW ELEVATOR INSTALLED 12/06/06, 982 TT, 717 TC. (2) OUT OF (4) HINGE ATTACH FITTING NUTPLATES STRIPPED FROM THE FACTORY. REPLACED NUTPLATES IAW SRM 51-30-2, FIGURES 3 AND 7. 2 L 7 2 4F 4 F RT A16WE E2EA 2007091300064 20070913 00064 NM 2007 9 13 SROM200700024 1 20070815 G 4910 INTAKE DUCT BOEING 737 737205 1384456 NM APU CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 38551 23465 NR481 - CORROSION AROUND AIR INLET DUCT FLANGE APU TORQUE BOX WEB BS 1064 RIGHT HAND SIDE. REPLACED AIR INLET DUCT FLAN GE IN ACCORDANCE WITH BOEING SRM 51-10-1, PAGE 8, 51-30-2, FIGURES 11, 12, 13, AND 51-30-6, FIGURE 3. 2 L 7 2 4F RT A16WE 2007101600051 20071016 00051 NM 2007 10 16 SROM200725 1 20071005 G 8097 WIRE BOEING 737 737205 1384456 NM PWA JT8 JT8D17A 52049 NE START SWITCH BURNED C SROM A H UNSCHED LANDING DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AL 03 736BP 38641 NSN 23465 DURING CLIMB SPARKS AND SMOKE EMITTED FROM THE AREA OF THE NR 1 START SWITCH. LOW IGNITION CB POPPED AT WHICH TIME THE S PARKS AND SMOKE CEASED. FLIGHT CREW RETURNED TO THE DEPARTURE AIRPORT FOR AN UNEVENTFUL LANDING. REPLACED SWITCH DUE TO ARCING ON CASE AND REPAIRED WIRING. INSPECTED OTHER AIRCRAFT IN FLEET NO OTHER CHAFED WIRES FOUND IN VICINITY OF THE STA RT SWITCHES. 2 L 7 2 4F 4 F RT A16WE E2EA 2007091800096 20070918 00096 2007 9 18 STS001 4 20070914 G 2564 1116FAUL33011 LIFE RAFT ACTIVE B K NONE L NO TEST NR NOT REPORTED 1 SO 15 WL7R LIFE RAFT (APPLIANCE, CAT II) SERVICED 10/19/2005 (SMER451X) THE 406 MHZ ELT NOT TIED TO BOARDING LADDER IAW MANUAL. EL T WOULD NOT HAVE SELF-DEPLOYED TO ALERT SAR, AS REQUIRED BY CMM 25-60-101, REVISION E 200805141 20080514 1 NE 2008 5 14 SWDG20080016 2 20070318 G 7250 310718501 GAS GENERATOR AIRTRC AT802 AT802A 0390308 SW PWC PT6 PT6A67AG 52211 NE HARTZL HCB5M HCB5MA3 GL ENGINE ERODED D SWDG K NONE O OTHER IN INSP/MAINT 1 SW 11 803DG 4731 550 802A0077 PCERD0016 BROKEN 'T' HEAD BOLT SHANK FOUND IN COWLING. MANUFACTURER REP VISITED AND TOOK PICTURES OF ERODED GAP IN THE 'C' FLANGE AT THE SCAVENGE TUBE COUPLING LOCATION WHERE THE BOLT HAD BEEN SEVERED. THE DAMAGE TO THE BOLT, FLANGE MATING SURFACES AND COUPLING ARE CLEARLY NOT THE RESULT OF CORROSION BECAUSE THE SURFACES IN THE AREAS OF DAMAGE ARE CLEAN AND HAVE AN ALMOST POLISHED APPEARANCE. SIMILAR ENGINES HAVE A SEALING RING INCORPORATED INTO THE FLANGE APPARENTLY FOR THIS VERY R EASON. THE MANUFACTURER REPS HAVE STATED THAT THIS EROSION IS UNEXPLAINED AND THEREFORE IS NOT A SAFETY OF FLIGHT ISSUE . THE MACHINING OF THE FLANGES AND INSTALLATION OF SEALING RING WOULD BE A START FOR REPAIRS, AND THE SOLUTION WOULD BE 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 200805141 20080514 1 NE 2008 5 14 SWDG20080024 2 20070319 G 7250 310718501 GAS GENERATOR AIRTRC AT802 AT802A 0390308 SW PWC PT6 PT6A67AG 52211 NE HARTZL HCB5M HCB5MA3 GL ENGINE ERODED D SWDG K NONE O OTHER IN INSP/MAINT 1 SW 11 804DG 3129 3129 802A0089 PCERD0024 ENGINE REMOVED FOR OVERHAUL EVALUATION. DUE TO THE FINDING OF SEVERE EROSION DAMAGE TO THE 'C' FLANGE AND NUMEROUS BROKE N 'T' BOLTS ON 3 OTHER ENGINES, THE DISSASSEMBLED EXHAUST DUCT AND GAS GENERATOR CASE FLANGES HAVE BEEN PHOTOGRAPHED AND FOUND THAT THIS 4TH ENGINE SUFFERS FROM SIMILAR DAMAGE. IT SHOULD BE NOTED THAT THE MANUFACTURER HAS BEEN NOTIFIED AND THAT THEIR REP HAS TAKEN PICTURES OF THE DAMAGED ENGINES AND HAS TOLD US THAT THE BROKEN BOLTS, 'C' FLANGE DAMAGE, AND P3 AIR LEAKAGE ONTO THE OIL TUBES ARE NOT SAFETY OF FLIGHT ISSUES. IT IS SUGGESTED THAT THE MANUFACTURER IMPLEMENT WARR ANTY PROVISIONS FOR THE INCORORATION OF A SEALING RING ON THE -67AG JUST LIKE SIMILAR ENGINES IN THE FAMILY. 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 200805141 20080514 1 NE 2008 5 14 SWDG20080077 2 20070319 G 7250 310718501 GAS GENERATOR AIRTRC AT802 AT802A 0390308 SW PWC PT6 PT6A67AG 52211 NE HARTZL HCB5M HCB5MA3 GL ENGINE ERODED D SWDG K NONE O OTHER IN INSP/MAINT 1 SW 11 803DG 1800 1800 802A0077 PCERD0077 AS THE 'T' HEAD BOLTS WERE BEING REMOVED FOR HSI, ONE NUT DETACHED FROM THE BOLT SHANK WITH THE THREAD INSIDE THE NUT. CLOSE INSPECTION OF THE ADJACENT BOLT REVEALED SEVERE EROSION (NOT CORROSION OR STRETCH DAMAGE) TO THE BOLT SHANK. IT W AS FURTHER NOTED AND PHOTOGRAPHED BY THE MANUFACTURER REP THAT THE EXHAUST DUCT FLANGE AND GAS GENERATOR FLANGE IN THE B ROKEN BOLT AREA HAD MATERIAL LOSS THAT WAS ALLOWING P3 AIR LOSS THAT MAY BE ATTRIBUTED TO THE HIGHER THAN NORMAL OIL TEM P INDICATION ON THE GROUND. THE AIR LEAK IS VENTING ONTO THE SCAVENGE OIL TUBE COUPLING. MANUFACTURER REPS SAY THAT TH IS IS AN ISOLATED CASE AND IS NOT A SAFETY OF FLIGHT ISSUE AS THAT THERE ARE MANY MORE BOLTS THAT HOLD 'C' FLANGE TOGETH 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 200805141 20080514 1 NE 2008 5 14 SWDG20080113 2 20070319 G 7250 310718501 GAS GENERATOR AIRTRC AT802 AT802A 0390308 SW PWC PT6 PT6A67AG 52211 NE HARTZL HCB5M HCB5MA3 GL ENGINE ERODED D SWDG K NONE O OTHER IN INSP/MAINT 1 SW 11 804DG 346 346 802A0089 PCERD0113 ENGINE PARAMETERS ABNORMAL AND SUBSIQUENT INSPECTION FOUND T5 HARNESS DAMAGED AT ASSEMBLY. IT WAS FURTHER NOTED THAT SU BSTANTIAL MATERIAL LOSS IN THE CENTER BOLT HOLE @ THE SCAVENGE TUBE COUPLING WAS ALLOWING COMPRESSOR AIR TO ERODE THE 'T ' BOLT SHANK. MANUFACTURER REP TOOK PICTURES OF DAMAGE AS NOTED ON NOVEMBER 22, 2006 AND HAS YET TO OFFER SUGGESTED CAU SE OR REPAIR SCHEME. THE "WITNESS" MARK OF SURFACE CONTACT OF THE 'C' FLANGES INDICATE NON-UNIFORM ALIGNMENT AXIALY OF THE FLANGE WELDED TO THE CASE. THE MANUFACTURER REPS HAVE FURTHER COMMENTED THAT P3 AIR LEAKAGE IS NOT A SAFETY OF FLIG HT ISSUE AND THAT FLANGE DAMAGE AND BOLT DAMAGE OR LOSS IS NOT A SAFETY OF FLIGHT ISSUE. 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2008011400042 20080114 00042 CE 2008 1 14 T4OR4765001 1 20071221 G 5210 5043004315 LEVER BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE CABIN DOOR TWISTED B T4OR K NONE O OTHER IN INSP/MAINT 1 EA 63 240CT 7199 BB1063 WHILE TRYING TO RIG THE CABIN DOOR UPPER LATCH HOOKS FOR PROPER OVERCENTER, IT WAS FOUND PROPER OVERCENTER COULD NOT BE OBTAINED WITHOUT THE ADJUSTING ROD END WITNESS HOLES BEING EXPOSED. CLOSER EXAMINATIONS SHOWED THE FWD AND AFT DOOR ACT UATION LEVER ASSEMBLIES, PN 50-430043-15 (FWD) AND 50-430043-17 (AFT) WERE TWISTED, CHANGING THE RELATIVE ANGLE BETWEEN THE LATCH HOOK AND ROD END ATTACH POINT. NORMALLY THE ANGLES BETWEEN THE LATCH HOOK AND LATCH ROD ATTACH POINT IS ABOUT 90 DEGREES. THE PARTS IN THIS DOOR WERE SOMEWHAT LESS THAT 90 DEGREES, CLOSER TO 75 DEGREES DUE TO THE TWIST. WITH TH IS CONDITION, THE PUSHROD FOR THE UPPER HOOK OVERCENTER ADJUSTMENT WOULD NEED TO BE EXTENDED FARTHER THAN DESIGNED, EXPO 1 L 7 2 4T 4 T A24CE E4EA 2007120400234 20071204 00234 EU 2007 12 4 T9NR200700001 1 20071106 G 3246 315182 WHEEL AEROSP ATR42 ATR42* 8680900 EU MLG CRACKED B TL9R K NONE O OTHER IN INSP/MAINT 1 SO 19 OUR SHOP REPORTS THE PRESENCE OF AN UNUSUAL CRACK ON THIS WHEEL. IT LIES BETWEEN THE WHEEL'S LIGHTING HOLES (WEB), AND I S COMPLETELY CRACKED BETWEEN ADJACENT LIGHTING HOLES. THE WHEEL ASSEMBLY PN IS NOTED BELOW, BUT THE CRACK EXHIBITED ITSE LF ON THE WHEEL HALF PN 300-824/10-1606 2 H 7 2 4T RT A53EU 2007120400235 20071204 00235 EU 2007 12 4 T9NR200700002 1 20071106 G 3246 315182 WHEEL AEROSP ATR42 ATR42* 8680900 EU ZONE 700 CRACKED B T9NR K NONE O OTHER IN INSP/MAINT 1 SO 19 OUR SHOP REPORTS THE PRESENCE OF AN UNUSUAL CRACK ON THIS WHEEL. IT LIES BETWEEN THE WHEEL'S LIGHTING HOLES (WEB), AND I S COMPLETELY CRACKED BETWEEN ADJACENT LIGHTING HOLES. THE WHEEL ASSEMBLY PN IS NOTED BELOW, BUT THE CRACK EXHIBITED ITSE LF ON THE WHEEL HALF PN 300-824/10-1606 2 H 7 2 4T RT A53EU 2008011100158 20080111 00158 CE 2008 1 11 TAS07003 1 20071116 G 3233 1FA100433 CAP BEECH 1900 1900 1154160 CE MLG ACTUATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 05 11943 1209B MLG ACTUATOR WAS RECEIVED DUE TO INDICATIONS FOUND IN THE END CAP DURING ULTRASONIC TESTING. ACTUATOR WENT THROUGH A PR ELIMINARY INSPECTION AND A COMPLETE FUNCTIONAL TEST WITH NO EXTERNAL EVIDENCE OF LEAKING OR CRACKING. AFTER DISASSEMBLY , A CRACK IN THE INTERNAL RADIUS OF THE END CAP WAS CONFIRMED BY A FLUORESCENT PENETRANT INSPECTION. 2 L 7 2 4T RT A24CE 2007041200024 20070412 00024 EU 2007 4 12 THMN4346176 1 20070410 G 5340 ATTACH BRACKET AMD FALC10 FALCON10 2730101 EU RT NLG DOOR CRACKED B T0DR K NONE O OTHER IN INSP/MAINT 1 CE 03 101HS 82 RT NOSE LANDING GEAR DOOR ATTACH POINT IN THE RT NOSE COMPARTMENT HAS 2 EA CRACKS AT FRAME C. MADE AIRWORTHY REPAIR IAW SRM 51-20-02-0, 51-40-11, AND 51-40-13. 2 L 7 2 4F A33EU 2007041200025 20070412 00025 EU 2007 4 12 THMN4346177 1 20070410 G 5340 ATTACH BRACKET AMD FALC10 FALCON10 2730101 EU LT NLG DOOR CRACKED B T0DR K NONE O OTHER IN INSP/MAINT 1 CE 03 101HS 82 LT NOSE LANDING GEAR DOOR ATTACH POINT IN THE LT NOSE COMPARTMENT HAS 2 EA CRACKS AT FRAME C. MADE AIRWORTHY REPAIR IAW SRM 51-20-02-0, 51-40-11, AND 51-40-13. 2 L 7 2 4F A33EU 2007041200026 20070412 00026 EU 2007 4 12 THMN4346179 1 20070410 G 5320 SPLICE PLATE AMD FALC10 FALCON10 2730101 EU FUSELAGE CRACKED B T0DR K NONE O OTHER IN INSP/MAINT 1 CE 03 101HS 82 SPLICE PLATE ON RT SIDE OF CABIN AT FRAME 13 JUST BELOW WINDOW LINE CRACKED. MADE AIRWORTHY REPAIR IAW SRM 51-00-01 FIG . 201 AND 51-40-11. 2 L 7 2 4F A33EU 2007061400144 20070614 00144 CE 2007 6 14 TIMR20070003 1 20070521 G 3233 998201233 ACTUATOR BEECH 99 B99 1154004 CE NLG DOOR SEPARATED E TIMA A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 NM 07 950AA 388 U159 DURING CRUISE, PILOT HEARD A CLUNK AND THE -GEAR IN TRANSIT- LIGHT CAME ON. RETURNED TO AIRPORT, PERFORMED FLY-BY WHICH CONFIRMED NOSE GEAR HANGING OUT BUT NOT FULLY EXTENDED. NOSE GEAR COLLAPSED ON LANDING. INVESTIGATION REVEALED THAT T HE ACTUATOR SHAFT HAD SHEARED JUST ABOVE THE CLEVIS BOLT CONNECTING TO THE DRAG BRACE. 1 L 7 2 3T A14CE 2007113000179 20071130 00179 CE 2007 11 30 TIMR20070008 1 20071031 G 3230 SWITCH BEECH 99 99A 1154003 CE PWA PT6 PT6* 52043 EA POWER LEVER INOPERATIVE B TIMA A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 NM 07 899CA U104 GEAR-IN-TRANSIT LIGHT DID NOT EXTINGUISH AFTER TAKE-OFF AND GEAR UP. PILOT CYCLED GEAR AGAIN WITH SAME RESULT. PILOT RE TURNED TO DEPARTURE AND LANDED. MECHANIC FOUND THAT THE LT POWER LEVER SWITCH HAD FAILED. REPLACING THE SWITCH RESOLVE D THE PROBLEM. 1 L 7 2 3T 3 T A14CE E2NE 2007120400297 20071204 00297 CE 2007 12 4 TIMR20070009 1 20070928 G 3233 993880011 ACTUATOR BEECH 99 99 1154002 CE PWA PT6 PT6* 52043 EA MLG CRACKED B TIMA A UNSCHED LANDING J WARNING INDICATION AP APPROACH 1 NM 07 4381Y 961 U71 AFTER SELECTING GEAR DOWN ON APPROACH, THE PILOT NOTICED THAT HE DID NOT HAVE A GREEN (SAFE) INDICATION FOR THE NOSE GEA R. HE FOLLOWED THE EMERGENCY PROCEDURE TO PUMP THE GEAR DOWN BUT WAS UNABLE TO BUILD UP PRESSURE OR GET A GREEN LIGHT. PILOT THEN LANDED AND THE NOSE GEAR COLLAPSED. INVESTIGATION FOUND THAT THE LT MAIN GEAR ACTUATOR END CAP HAD CRACKED A ND ALLOWED THE EMERGENCY SYSTEM FLUID TO VENT OVERBOARD, PREVENTING THE NOSE ACTUATOR FROM EXTENDING FULLY. 1 L 7 2 3T 3 T A14CE E2NE 2007050700190 20070507 00190 EU 2007 5 7 TL9R200700001 1 20070501 G 3240 C200601004 BRAKE AIRBUS 330 A300* EU MLG MAKING METAL B TL9R K NONE O OTHER IN INSP/MAINT 1 GL 13 BRAKE ROTORS DE-LINED (STARTED TO FALL APART) IN OPERATION. 2 L 7 2 4F RT A26NM 2007071200133 20070712 00133 NE 2007 7 12 UE5R02 2 20070705 G 7210 310825401 GEARBOX AIRTRC AT602 AT602 0390309 SW PWA PT6 PT6A60 52043 NE CORRODED B UE5R K NONE O OTHER IN INSP/MAINT 1 EA 61 PSRG0056 PT6A-60AG REDUCTION GEAR REAR HOUSING P/N 3106854-01 HAS SEVERE CORROSION ON OUTER SURFACE OF HOUSING. DEEP PITTING, SOM E AREAS UP TO .125 INCH DEEP. CORRODED AREAS EXTEND THE ENTIRE CIRCUMFERENCE OF HOUSING, PRIMARILY NEXT TO MATING FLANGE FOR FWD HOUSING. 1 L 7 1 3T 4 T NC A19SW E4EA 2007091700071 20070917 00071 EA 2007 9 17 UE5R04 2 20070911 G 7250 T102401100 BLADES BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA TURBINE SECTION CRACKED B UE5R O OTHER O OTHER NR NOT REPORTED 1 EA 61 DURING STRETCH CHECK OF TURBINE BLADES P/N T102401-100, FLUORESCENT PENETRANT INSPECTION WAS PERFORMED. THIS INSPECT RE VEALED SEVERAL BLADES WITH CRACKS ALONG TRAILING EDGE. THESE CRACKS IN THE DIRECTION OF THE CHORD OF THE BLADE. 1 L 7 2 3T 4 T A14CE E4EA 2007041600052 20070416 00052 NE 2007 4 16 UE5R1 2 20070402 G 7230 3023401 BLADE PWC BEECH 100 100BEECH 1152916 CE PWC PT6 PT6A67AG 52211 NE COMPRESSOR DISC CRACKED B UE5R K NONE O OTHER IN INSP/MAINT 1 EA 61 7P070 COMPRESSOR TURBINE DISC BLADE FAILURE. SINGLE BLADE IN COMPRESSOR TURBINE DISC CRACKED IN FUR TREE AREA OF BLADE. CAUSED MISALIGNMENT OF CT BLADE AND SUBSEQUENT RUB ON SHROUD SEGMENTS. THE CRACK IN FIR TREE WAS NOT VISIBLE WITH ENGINE SPLIT IF PERFORMING A ROUTINE INSPECTION, HOWEVER BLADE MISALIGNMENT AND RUB WERE VISIBLE. THE BLADE CRACK BECAME VISIBLE WHE N CT DISC ASSY WAS REMOVED FROM ENGINE. 1 L 7 2 3T 4 T A14CE E26NE 2007081700096 20070817 00096 SW 2007 8 17 WGEA200700001 1 20070803 G 2752 EM41165 ACTUATOR ECLIPS EA500 ECLIPSEEA500 3350000 SW T/E FLAPS MALFUNCTIONED C WGEA K NONE F FLT CONT AFFECTED DE DESCENT 1 EA 27 109DJ 205 205 000006 FLAP FAIL CAS MESSAGE IN FLIGHT. REMOVED AND REPLACED LT AND RT INBOARD FLAP ACTUATORS PER EA 500 AM CH 27-51-11. RIGG ED FLAP`S AND COMPLIED WITH SATISFACTORY FUNCTIONAL/OPERATIONAL CHECKS. 1 L 7 2 4J RT A00002AC 2008011100136 20080111 00136 CE 2008 1 11 WSA12262007 1 20071226 G 1400 998100611 BOLT BEECH 200 200BEECH 1152920 CE MLG MISMANUFACTURED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 17 1558 BC20 HAVE ORDERED FROM MFG THE LANDING GEAR DRAG LEG BOLTS TWICE AND HAVE RECEIVED (2) DEFECTIVE BOLTS EACH TIME. THE COTTER PIN HOLE WAS MISDRILLED AND WOULD COULD NOT GET THE HOLES TO LINE UP WITH THE NUT CASTELLATION. (2) OF THE BAD BOLTS WER E DATE TAGGED 12/2/2006. THE ACTUAL BOLT MANUFACTURER IS UNKNOWN ALTHOUGH THEY WERE SOURCED FROM AC MFG. IT IS BELIEVED THAT AC MFG HAS PULLED THESE FROM THEIR INVENTORY AFTER OUR PROBLEM. 1 L 7 2 4T A24CE 2007080800063 20070808 00063 EU 2007 8 8 WTU0701 1 20070719 G 2435 150SG122Q STARTER GEN SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE ENGINE SEIZED B R8RR A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 WP 07 5204Y 10 10 3101 9782 WHILE CONDUCTING A SEARCH OVER MOUNTAINOUS TERRIAN AT NIGHT UTILIZING AN SX-5 SEARCHLIGHT, TEN MINUTES INTO THE SEARCH L IGHT QUIT WORKING. APPROXIMATELY 30 SECONDS LATER THE GENERATOR FAIL LIGHT ILLUMINATED AND THE CREW SMELLED SMOKE IN TH E COCKPIT. APPROXIMATELY 30 SECONDS LATER THE FIRE LIGHT ILLUMINATED. THE PILOT IMMEDIATELY EXCEUTED EMERGENCY PROCEDU RES BY TURNING OFF THE GENERATOR AND LAND AS SOON AS PRACTICAL. AFTER THE PILOT LANDED AND SHUTDOWN THE AIRCRAFT THEY E XITED AND SAW SMOKE COMING OUT OF THE STARTER GENERATOR COOLING DUCT TUBE. THE CREW OPENED THE ENGINE COWLING AND THERE WAS NO FIRE BUT EVIDENCE THAT THERE MAY HAVE BEEN ONE INSIDE THE S/G. UPON REMOVAL THE S/G HAD A SHEARED SHAFT IT WAS 1 G 7 1 3U 3 U H9EU E19EU 2007090600020 20070906 00020 EU 2007 9 6 WTU0702 1 20070828 G 2435 150SG122Q STARTER GEN SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE ENGINE INOPERATIVE B R8RR A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 WP 07 455AE 15 15 3509 9576 WHILE CONDUCTING A ROUTINE PATROL AT NIGHT THE GENERATOR FAILED AND WOULD NOT RESET. ALL NON ESSENTIAL EQUIPMENT WAS SH UTOFF AND THE PILOT RETURNED TO BASE UTILIZING BATTERY BUSS POWER WITHOUT FURTHER INCIDENT. 1 G 7 1 3U 3 U H9EU E19EU 2007061200149 20070612 00149 NE 2007 6 12 Y4MR200700521 2 20070521 G 7200 PT6A135 ENGINE BEECH 90 F90 1152909 CE PWA PT6 PT6A135 52043 NE RIGHT MAKING METAL B W1MA E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 SO 09 89CA 6546 3399 LA152 PCE92418 DURING CRUISE, RT ENGINE CHIP DETECTOR ILLUMINATED. OTHER RT ENGINE INDICATIONS WERE MONITORED CLOSELY FOR ANY SIGN OF MECHANICAL PROBLEM. NO OTHER INDICATIONS THAT WOULD SUGGEST MECHANICAL PROBLEMS WERE NOTED AT THAT TIME. THE CHIP LIGH T WENT OUT WITHIN A FEW MINUTES AND PILOT CONTINUED TO CLOSELY MONITOR RT ENGINE INDICATIONS. PRIOR TO START OF DESCENT (FROM 15000) FOR DESTINATION AIRPORT (BHM) PILOT NOTED SMALL FLUCTUATION IN RT ENGINE OIL PRESSURE FOLLOWED BY TORQUE F LUCTUATION (APPROXIMATELY 200 LBS); ITT INDICATION WAS STABLE. DECLARED AN EMERGENCY, SECURED ENGINE AS PRECAUTIONARY M EASURE, AND LANDED AT THE NEAREST AIRPORT WITHOUT INCIDENT. MAINTENANCE WAS DISPATCHED TO INVESTIGATE AND UPON INSPECTI 1 L 7 2 4T 4 T A31CE E4EA 2007101600075 20071016 00075 NM 2007 10 16 Y5CR200700001 1 20071005 G 6320 369D2512311 BEVEL GEAR DOUG MD500 MD500E 3027372 NM M/R GEARBOX BROKEN B Y5CR K NONE O OTHER IN INSP/MAINT 1 WP 05 687 PART OF TOOTH ON INPUT BEVEL GEAR BROKEN OFF. 1 G 7 2 3U NC 2007120500058 20071205 00058 NM 2007 12 5 Y5CR200700002 1 20071120 G 6510 JOURNAL DOUG MD500 MD500E 3027372 NM TAIL ROTOR BROKEN B Y5CR K NONE O OTHER IN INSP/MAINT 1 WP 05 3149 BEARING JOURNAL BROKEN OFF ON OUTPUT PINION. 1 G 7 2 3U NC 2007061400221 20070614 00221 EU 2007 6 14 YNTA20070001 1 20070516 G 2750 FLAP SYSTEM HAWKER BAE125 BAE125700B 7450007 EU TE FLAPS INOPERATIVE E L ABORTED APPROACH O OTHER AP APPROACH 1 SW 05 281B 281 ON APPROACH, THE FLAPS BECAME STUCK AT 15 DEGREES. AFTER TRYING THE FLAPS 25 DEGREE SETTING NOTICED THE FLAPS DID NOT MO VE FROM THE 15 DEGREE POSITION. RESET THE FLAPS TO THE 15 DEGREE POSITION AND UP TO 0 DEGREE, NO MOVEMENT WAS NOTED. RES ELECTED THE FLAPS TO 15 DEGREE EXECUTED A GO-AROUND WITH TOWER. REFERRED TO THE CHECK LIST FOR NO FLAP LANDINGS, NOTED T HAT THERE IS NO LANDING DISTANCE DATA. DECLARED AN EMERGENCY DUE TO ABNORMAL LANDING CONFIGURATION. THE SIC BRIEFED THE PASSENGERS ON THE SITUATION. AFTER LANDING, TAXIED OFF THE RUNWAY INTO A RUN-UP AREA SHUT THE AIRCRAFT DOWN. MET WITH F IRE DEPARTMENT LOOKED AT THE TIRES AND BRAKES , NOTICED NO SMOKE OR FIRE. AIRPORT OFFICIAL SAID THEY SAW NO SMOKE ON LAN 2 L 7 2 4F RT A3EU 2007020500045 20070205 00045 2007 2 5 ZB0R20070001 4 20070131 G 3197 WIRE CESSNA 172 172S 2072439 CE INSTRUMENT PANEL CHAFED B ZB0R C ABORTED TAKEOFF B SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 SO 05 6026S 172S10206 PILOT REPORTED SMOKE ODOR AND STANDBY INSTRUMENT LIGHTS FLICKERED ON RUN-UP PRIOR TO TAKEOFF. INVESTIGATION REVEALED WIR E BUNDLE WHICH CONTAINS THE POWER WIRE FOR THE STANDBY INSTRUMENT LIGHTS WAS CHAFING ON THE LOWER LEFT CORNER OF THE AUD IO PANEL RACK. MAINT REPLACED A SECTION OF THE AFFECTED WIRE. OPS CK GOOD. 1 H 7 1 3O NT 3A12 2007102300168 20071023 00168 EA 2007 10 23 ZB0R20070002 2 20071015 G 7322 105220 CARBURETOR CESSNA 150 152 2071835 CE LYC O235 O235* 41505 EA ENGINE LEAKING B ZB0R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 39 95300 1413 15285871 L2379515 DURING PROGRESSIVE INSP, FOUND CARBURETOR BOWL LEAKING AT GASKET. BOLTS WOULD NOT TIGHTEN - STRIPED THREADS. REPLACED C ARBURETOR TO CORRECT DISCREPANCY. 1 H 7 1 3O 3 O NT 3A19 E223 2007102300022 20071023 00022 SO 2007 10 23 ZB0R20070003 1 20071015 G 3233 9686002 ACTUATOR PIPER PA34 PA34200 7103405 SO LYC O360 IO360A1A 41514 EA NLG LEAKING B ZB0R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 39 15412 347350060 DURING GEAR MAINTENANCE, FOUND NLG ACTUATOR LEAKING. INSPECTION REVEALED WORN SEALS. REPLACED SEALS BUT STILL LEAKED. FU RTHER INSPECTION WITH BORESCOPE IN BODY OF ACTUATOR REVEALED LONGITUDINAL SCORING ON INSIDE WALL OF ACTUATOR BODY. REPLA CED ACTUATOR TO CORRECT DISCREPANCY. 1 L 7 2 3O 3 O A7SO 1E10 2007102300174 20071023 00174 EA 2007 10 23 ZB0R20070004 2 20070915 G 8520 LW18840 CAM PIPER PA28 PA28R200 7102811 SO LYC O360 IO360A1A 41514 EA ENGINE WORN B ZB0R A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 EA 39 41331 1216 28R7435169 L1561051A ON CLIMB-OUT, PILOT NOTICED LOW POWER. RETURNED TO AIRPORT. MAINTENANCE INSPECTION REVEALED BELOW MINIMUM VALVE TRAVELS FOR ALL INTAKE VALVES. REMOVED NR 1 CYLINDER. FOUND CAM LOBES SEVERELY WORN AND TAPPETS CORRODED AND WORN IN A CONCAVE MANNER. ENGINE REPAIRED BY SERVICE CENTER. REINSTALLED ON ACFT. ALL SYSTEMS OPS CK NORMAL. 1 L 7 1 3O 3 O 2A13 1E10 2007102300177 20071023 00177 EA 2007 10 23 ZB0R20070005 2 20071001 G 8530 CYLINDER CESSNA 150 152 2071835 CE LYC O235 O235* 41505 EA NR 2 LEAKING B ZB0R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 39 95300 15285871 L2379515 DURING PROGRESSIVE INSP, FOUND NR 2 CYLINDER UPPER TOP THROUGH BOLT LEAKING SEVERELY. REMOVED ENGINE FOR REPAIR. REINS TALLED AFTER REPAIR BY SERVICE CENTER. (CASE WAS FOUND FRETTING AND BEARING WEAR WAS EVIDENT AT BOLT LOCATION). 1 H 7 1 3O 3 O NT 3A19 E223 2007120400072 20071204 00072 SO 2007 12 4 ZB0R20070006 1 20071102 G 5730 62061002 SKIN PIPER PA28 PA28R200 7102811 SO LYC O360 IO360A1A 41514 EA RT WING CRACKED B ZB0R K NONE O OTHER IN INSP/MAINT 1 SO 05 15143 4617 28R7335027 DURING PROGRESSIVE INSPECTION, DISCOVERED WING WALK ON RT WING SPONGY. INSPECTION REVEALED SUBSTRATE REINFORCEMENT CRACK ED IN SEVERAL LOCATIONS. REPLACED WING WALK. 1 L 7 1 3O 3 O 2A13 1E10 2007120400081 20071204 00081 CE 2007 12 4 ZB0R20070008 1 20071102 G 2560 DETECTOR CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA CARBON MONOXIDE INOPERATIVE B ZB0R O OTHER J WARNING INDICATION CR CRUISE 1 SO 05 60457 85 85 172S10212 CARBON MONOXIDE DETECTOR FAILED. SECOND FAILURE WITHIN 6 MONTHS 1 H 7 1 3O 3 O NT 3A12 1E10 2008010800375 20080108 00375 SO 2008 1 8 ZB0R20070009 1 20071214 G 7603 89307000 ROD END PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA FUEL CONTROL SEPARATED B ZB0R E ENGINE SHUTDOWN O OTHER CR CRUISE 1 EA 39 15412 376 39 347350060 IN CRUISE, PILOT ATTEMPTED TO REDUCE POWER FOR MANEUVERS PRACTICE. LT ENGINE WAS UNRESPONSIVE. INSTRUCTOR IDENTIFIED LT ENGINE THROTTLE PROBLEM, ENGINE RPM WAS STABLE AT NEAR FULL POWER. RETURNED TO HOME BASE. PILOT FEATHERED AND SHUTDOWN L T ENGINE ON APPROACH. MAINTENANCE DISCOVERED LT ENGINE THROTTLE CONTROL ROD END AT FUEL CONTROL HAD SEPARATED. 1 L 7 2 3O 3 O A7SO 1E10