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 2008032500257 20080325 00257 CE 2008 3 25 0000H2484 1 20080318 G 2820 LINE BEECH 35 V35 1151538 CE CONT O550 IO550B SO FUEL SYSTEM CHAFED B WS9R K NONE O OTHER IN INSP/MAINT 1 NM 07 363BC 3 D9763 297203R FUEL LINE MOUNTED ON FIREWALL FABRICATED PER STC SA8676SW WAS CHAFING THE ENGINE TAILPIPE. 1 L 7 1 3O 3 O 3A15 E3SO 2008040300090 20080403 00090 CE 2008 4 3 01030413 1 20080103 G 3242 314901 BRAKE ASSY BFGOODRICH CESSNA 500 560CESSNA 2076750 CE MLG LOCKED B PAZR O OTHER E VIBRATION/BUFFET LD LANDING 1 CE 03 561JS 2290 5600413 UPON LANDING THE AIRCRAFT YAWED TO THE RIGHT AND IN OVERCOMPENSATING THE AIRCRAFT THEN STARTED A SIDEWAYS DRIFT ENOUGH T HAT THE LEFT MAIN TIRE FAILED. IT WAS FOUND THAT ONE RIGHT HAND BRAKE STATOR WAS LOCKED AND HAD GROUND THE WHEEL FLAT AN D THE LEFT MAIN FAILED AS A RESULT OF TIRE SIDEWALL FAILURE. DAMAGE INCLUDES BOTH TIRES AND WHEELS. LEFT LANDING LIGHT. LEFT HAND INBOARD FLAP AND RIGHT HAND BRAKE AND BRAKE LINES. 2 L 7 2 4F RT A22CE 2008041000260 20080410 00260 EU 2008 4 10 03252008 1 20080325 G 3233 D52177 HOLDER MESSIER AMD FALC20 FALCON200 2730150 EU ACTUATOR BROKEN B O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 SW 05 DRI76878 THE PACKING HOLDER P/N D52177 BROKE IN (2) PIECES CAUSING HYDRAULIC FLUID LOSS. THIS PART HAD BEEN MODIFIED IAW SB F200 -110 TO PREVENT FUTURE FAILURES. THIS IS THE SECOND PACKING HOLDER FOUND TO BE BROKEN AFTER MODIFICATION. BOTH PARTS WE RE MODIFIED AND IDENTIFIED SRD IAW THE S/B. 2 L 7 2 4F RT A7EU 2008031300042 20080313 00042 SO 2008 3 13 115301 1 20080218 G 4910 1159AC30551103 DUCT GULSTM G1159 GIV 3980115 SO APU INLET CRACKED E CLWA K NONE O OTHER IN INSP/MAINT 1 SW 05 589HM 6464 1153 A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM). 2 L 7 2 4F RT A12EA 2008031300044 20080313 00044 SO 2008 3 13 115302 1 20080218 G 4910 1159AC30551103 DUCT GULSTM G1159 GIV 3980115 SO APU INLET CRACKED E CLWA K NONE O OTHER IN INSP/MAINT 1 SW 05 589HM 6464 1153 A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM). 2 L 7 2 4F RT A12EA 2008021900067 20080219 00067 CE 2008 2 19 20080101 1 20080118 G 2752 505212234 ACTUATOR BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA T/E FLAP CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 LJ833 RT OB FLAP ACTUATOR ASSY, PISTON TUBE CRACKED 100 PERCENT IN DEPTH, 100 PERCENT ENTIRE LENGTH OF TUBE. CRACK RUNS PARAL LEL TO TUBE . 1 L 7 2 3T 4 T 3A20 E4EA 2008050800116 20080508 00116 SO 2008 5 8 20080420001 1 20080420 G 7810 BRACKET MAULE MX7 MX7180A 5460186 SO LYC O360 O360* 41514 EA ENGINE EXHAUST CRACKED C C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 SO 16 ON TAKE-OFF, 50 FEET, PARTIAL POWER LOSS (2,500+ RPM TO 1,100 RPM) AND ENGINE ROUGHNESS. ABORTED TAKE-OFF. WHEN CARBUR ATOR TAKEN OFF PLANE, FOUND 1 INCH X .5 INCH PIECE OF METAL LOOSE IN AIR/FUEL MIXING CHAMBER UPSTREAM OF VENTURI. PIECE WAS TOO BIG TO GO THROUGH VENTURI, BUT BIG ENOUGH TO DISRUPT FLOW THROUGH VENTURI. FOUND SOURCE OF METAL TO BE A PIECE OF THE BRACKET FROM LEFT MUFFLER. BRACKET USED TO CONNECT SHROUD TO MUFFLER TO CAPTURE HEAT FOR USE IN DIRECTING CARB HE AT. ENTIRE BRACKET WAS ABOUT 12 INCHES LONG. THE 1 INCH LONG PIECE OF THE BRACKET BROKE OFF AND MADE ITS WAY DOWN CARB H EAT DUCTING INTO MIXING CHAMBER OF MUFFLER, UPSTREAM OF VENTURI. BASED ON ENGINE OPERATIONS, BELIEVE PIECE HAD BROKEN F 1 H 7 1 3O 3 O NC 3A23 E286 20080519 CE 2008 5 19 20080506FA001 1 20080506 G 3246 10320400AN53 BOLT PARKERHANFIN RAYTHN 36 G36 7150061 CE RT MLG WHEEL SHEARED B K NONE O OTHER IN INSP/MAINT 1 CE 07 222GL 479 479 E3763 THE PILOT REPORTED A "POP" AS HE WAS GROUND HANDLING THE AIRCRAFT ON THE RAMP (IN A STRAIGHT DIRECTION USING AN AIRTUG). FURTHER INVESTIGATION REVEALED 1 NUT/BOLT COMBINATION HAD SHEARED ON THE INBOARD WHEEL HALF OF THE RIGHT HAND MAIN LAN DING GEAR ASSEMBLY. THE BOLT HAD SUBSEQUENTLY BACK OUT APPROXIMATELY 1/4INCH. THIS AIRCRAFT HAS BEEN THROUGH 1 ANNUAL INSPECTION AND HAS NEVER HAD THE WHEEL HALVES DISASSEMBLED. UPON DISCOVERY OF THE SHEARED BOLT, THE LEFT AND RIGHT WHEE LS WERE DISASSEMBLED, CLEANED, INSPECTED AND REASSEMBLED WITH NEW BOLTS AND NUTS. DURING DISASSEMBLY OF THE WHEEL HALF RETAINING BOLTS IT WAS NOTED THAT VERY LITTLE FORCE WAS REQUIRED TO BREAK THE NUTS LOOSE. THE NOSE WHEEL WAS THEN CHECKE 1 L 7 1 3O RT 3A15 20080701 EA 2008 7 1 2008F00016 2 20080415 G 8500 ENGINE GIPPLD GA8 GA8 3900102 EU LYC O540 IO540K1A5 41532 EA FAILED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SO 23 7508M GA805094 L3095348A AIRCRAFT EXPERIENCED AN ENGINE FAILURE. ATTEMPTS TO RESTART ENGINE FAILED AND A SAFE LANDING WAS ACCOMPLISHED. CAUSE OF FAILURE REMAINS UNKNOWN AT THIS TIME. (K) 1 H 7 1 3O 3 O NT 1E4 20080811 CE 2008 8 11 2008F00019 1 20080715 G 3260 A46270 SWITCH CESSNA 500 550 2076604 CE MLG OUT OF ADJUST D A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 EA 68 187JN 5500335 ON DEPARTING AIRPORT, UPON GEAR RETRACTION, THE DOOR UNLOCK LIGHT ACTIVATED. THE PILOT OPTED TO BURN FUEL AND LAND WHEN LANDING WEIGHT WAS ACHIEVED. THE LANDING WAS WITHOUT INCIDENT. MAINT WAS THEN CALLED. THE SWITCH WAS DETERMINED TO B E OUT OF ADJUSTMENT. THE SWITCH WAS THEN ADJUSTED IAW MM AND RETURNED TO SERVICE. (K) 1 L 7 2 4F A22CE 20080811 GL 2008 8 11 2008F00020 1 20080711 G 6100 ROD CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO PITCH CHANGE MISINSTALLED W O OTHER W INADEQUATE Q C NR NOT REPORTED 1 SW 99 554PG 2009 360674 ON INSTALLATION OF PROP TO ENG MOUNTING FLANGE IAW MM 61-00-45, THE PLASTIC PROTECTIVE CAP FITTED TO THE END OF THE PITC H CHANGE ROD WAS NOT REMOVED. ON FLIGHT TEST OF THE AC, ENGINE OVERSPEED WAS NOTED AT TAKEOFF TO 2850 RPM, NO SIGNIFICA NT LOSS OF OIL PRESSURE WAS NOTED. THE PILOT THROTTLED BACK TO REDUCE PROPELLER SPEED TO LESS THAN 2700 RPM ( WITHIN PE RMITTED LIMITATIONS) ENGINE POWER WAS REDUCED TO 48 PERCENT AT THIS POINT AND THE ENGINE SUBSEQUENTLY STOPPED. THE PILO T RESTARTED THE ENGINE, SLIGHTLY EXCEEDING 2700 RPM FOR A SHORT PERIOD. THE PILOT RETURNED THE AIRCRAFT TO BASE, LANDIN G SAFELY AND REPORTED THE INCIDENT TO THE MAINT MGR. ON INVESTIGATION THE PROP WAS REMOVED AND THE PROTECTIVE CAP WAS I 1 L 7 1 3O 3 O NT A00009CH E1CE 20081110 EA 2008 11 10 2008F00024 2 20081001 G 7414 4371 MAGNETO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE DAMAGED B K NONE O OTHER IN INSP/MAINT 1 CE 07 227BH 172S10662 L33887L2A EXCESSIVE MAGNETO DROP DURING RUNUP AND MAGNETO CHECK. 100 RPM DIFFERENTIAL BETWEEN LT AND RT MAGNETO, ALSO RT MAGNETO R UNNING ROUGH. CHECKED FOUND RT MAGNETO TIMING OFF. FOUND RT MAGNETO AT 20 DEGREES BEFORE TOP DEAD CENTER, SUPPOSE TO BE 25 DEGREES BTDC. DRIVE GEAR FOR THE DISTRIBUTOR WAS FOUND UNEVEN, CAUSING IT TO WOBBLE WHEN ROTATING. THIS CAUSED UNUSU AL WEAR ON BOTH DRIVE GEAR AND DISTRIBUTOR GEAR. DRIVE GEAR MATERIAL NOT REMOVED DURING CLEANUP PROCESS FROM INJECTION M OLDING. PIECES WERE COMING OFF INSIDE MAGNETO. EXCESSIVE CAM WEAR FOR 379.9 HRS. CONTACT POINTS FOUND MISALIGNED, BREAK ER POINT ARM HAS FALLEN DOWN & IS RIDING ON THE RIDGE ON CAM. RIDGE CREATED BY EXCESSIVE CAM WEAR. CONDITION MAY CAUSE R 1 H 7 1 3O 3 O NT 3A12 1E10 20081210 NE 2008 12 10 2008F00025 1 20081113 G 2612 PROBE SKRSKY S76 S76C 8143008 NE FIRE WARNING MALFUNCTIONED G K NONE N FALSE WARNING CR CRUISE 1 EA 63 85PS 760489 NUMBER 2 ENGINE HAD A FIRE CAUTION WARNING LIGHT ILLUMINATE WITH HORN FOR TWO SECONDS. THIS OCCURRED TWICE DURING THE FL IGHT. WHEN THE MECHANICS TRIED TO TROUBLESHOOT THE PROBLEM, COULD NOT DUPLICATE IT. TO FURTHER TROUBLESHOOT, THE AFT N R 1 & 2 FIRE PROBES P/N 76306-07902-104 WERE SWAPPED TO SEE IF THE PROBLEM RE-OCCURRED AND FOLLOWED THE PROBE. 1 G 7 2 3U NC H1NE 20090105 EU 2009 1 5 2008F00026 1 20081216 G 5311 117223121151 FRAME BOLKMS 117 BK117B1 5626012 EU ZONE 200 CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 19 330SL 7216 DURING INSP FOUND SPIDER CRACKS AROUND 1 RIVET ON THE DECK UNDER THE TANDEM HYD PACK. FURTHER INSP FOUND 2 FRAMES CRACKE D UNDER THE HYD DECK. 1 G 7 2 3U H13EU 20090106 EU 2009 1 6 2008F00027 1 20081215 G 7797 MS3126F1415S CONNECTOR BRAERO DH125 HS125700A 4230170 EU N1 INDICATOR DEFECTIVE H O OTHER O OTHER NR NOT REPORTED 1 SO 19 411P 11744 1070 549E ON NOVEMBER 23, 2008, THE NR 2 ENGINE N1 GAUGE DIGITAL PORTION FAILED. THE MALFUNCTION WAS TRACED TO A DEFECTIVE CONNECT OR AT THE GAUGE. 2 L 7 2 4F A3EU 2008011100261 20080111 00261 SO 2008 1 11 2008FA0000003 1 20080102 G 3213 39489003 STRUT PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE MCAULY 3AF32C 3AF32C512 GL RT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 01 69BP 2091 2091 3449085 321475 981180 DURING ANNUAL INSPECTION IT WAS NOTED THAT A CRACK WAS FOUND ON THE RT MAIN GEAR LOWER FORK ASSY PN 39489-003. THE CRAC K IS LOCATED IN THE MILLED SECTION OF THE CASTING AT THE 11 O'CLOCK AND 1 O'CLOCK POSITIONS. THIS MILLED SECTION IS USED TO BOLT THE TORQUE PLATE PN 451-786 TO THE MLG ASSY. CONTACTED MFG THRU THERE DAS SYSTEM AND WAS TOLD THEY NEVER HEARD OF ANY PROBLEMS. REQUESTED FROM MFG TO BLEND CRACK AREA OUT AND REQUEST WAS DENIED. PROCEEDED TO CONTACT A DER FOR APPRO VAL ON BLENDING CRACKED AREA OUT AND AGAIN REQUEST DENIED. FOUND ANOTHER LOWER STRUT IN A SALVAGE YARD WHICH WE PURCHASE D ONLY TO FIND THIS STRUT ALSO WAS CRACKED IN THE EXACT SAME SPOT. ALSO I NOTED THAT THE CASTING VARY IN THICKNESS UPTO 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 2008011000012 20080110 00012 SO 2008 1 10 2008FA0000004 1 20080102 G 3213 39489003 STRUT PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE MCAULY 3AF32C 3AF32C512 GL RT MAIN GEAR CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 01 69BP 2091 2091 3449085 321475 981180 DURING ANNUAL INSPECTION, IT WAS NOTED THAT A CRACK WAS FOUND ON THE RT MAIN GEAR LOWER FORK ASSEMBLY PN 39489-003. THE CRACK IS LOCATED IN THE MILLED SECTION OF THE CASTING AT THE 11 O'CLOCK AND 1 O'CLOCK POSITIONS. THIS MILLED SECTION IS USED TO BOLT THE TORQUE PLATE PN 451-786 TO THE MAIN LANDING GEAR ASSY. CONTACTED MFG THRU THERE DAS SYSTEM AND WAS TOL D THEY NEVER HEARD OF ANY PROBLEMS. REQUESTED FROM MFG TO BLEND CRACK AREA OUT AND REQUEST WAS DENIED. PROCEEDED TO CONT ACT A DER FOR APPROVAL ON BLENDING CRACKED AREA OUT AND AGAIN REQUEST DENIED. FOUND ANOTHER LOWER STRUT IN A SALVAGE YAR D WHICH WE PURCHASED ONLY TO FIND THIS STRUT ALSO WAS CRACKED IN THE EXACT SAME SPOT. THIS STRUT CAME OFF A MODEL PA34-2 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 2008011400075 20080114 00075 CE 2008 1 14 2008FA0000010 1 20080104 G 3213 390810001 STRUT RAYTHN 390 390 7150030 CE WILINT FJ44 FJ442A GL LT MLG LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 CE 09 701KB 30 RB211 PILOT REPORTED LT AND RT MAIN LANDING GEAR STRUTS LEAKING HYDRAULIC FLUID. DISASSEMBLY LOWER LT MAIN LANDING GEAR STRUT, FOUND PAINT CHIPS CONTAMINATING SEALS. DISASSEMBLED RT LOWER MAIN LANDING GEAR STRUT, FOUND PAINT CHIPS CONTAMINATING S EALS AND METAL FILLINGS IN INNER BARREL OF STRUT. 1 L 7 2 3F 4 F RT A00010WI E3GL 2008011400074 20080114 00074 CE 2008 1 14 2008FA0000011 1 20080104 G 3213 390810001 STRUT RAYTHN 390 390 7150030 CE WILINT FJ44 FJ442A GL RT MLG LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 CE 09 701KB 30 RB211 PILOT REPORTED LT AND RT MAIN LANDING GEAR STRUTS LEAKING HYDRAULIC FLUID. DISASSEMBLY LOWER LT MAIN LANDING GEAR STRUT, FOUND PAINT CHIPS CONTAMINATING SEALS. DISASSEMBLED RT LOWER MAIN LANDING GEAR STRUT, FOUND PAINT CHIPS CONTAMINATING S EALS AND METAL FILLINGS IN INNER BARREL OF STRUT. 1 L 7 2 3F 4 F RT A00010WI E3GL 2008011100297 20080111 00297 EA 2008 1 11 2008FA0000013 2 20080102 G 7414 6393 MAGNETO GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCC3Y HCC3YR GL ENGINE WORN C D RETURN TO BLOCK L NO TEST TX TAXI/GRND HDL 1 SO 14 51RF 50 50 CAM LOBE INSIDE MAG THAT OPENS AND CLOSES POINTS WORN OUT. 1 H 7 2 3O 3 O 6A1 1E4 5 C P25EA 2008011400030 20080114 00030 CE 2008 1 14 2008FA0000018 1 20080108 G 2701 YOKE CESSNA 177 177B 2073708 CE LYC O360 O360* 41514 EA MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 09 30673 17701397 WHILE DOING AN ANNUAL, FOUND LOOSENESS IN THE YOKE FOR AND AFT MOVEMENT. AFTER MUCH CHECKING, FOUND THE LOOSENESS TO BE BETWEEN THE YOKE LEVER ASSY 1767033-7 AND 1767037-2 WHICH IS THE SHAFT. ALSO THERE WAS LOOSENESS BETWEEN THE SHAFT 1767 037-2 AND THE QUADRANT 1767024-1. FURTHER INVESTIGATION FOUND STANDARD AN4 BOLTS INSTEAD OF THE NAS464P4-17 CALLED FOR IN THE PARTS MANUAL CONNECTING THESE PARTS. THE DIFFERENCE IN DIAMETER OF THE BOLTS CAUSED THE LOOSENESS. PARTS MANUAL, FIGURE 63. 1 H 7 1 3O 3 O A13CE E286 2008012200046 20080122 00046 EU 2008 1 22 2008FA0000036 1 20080114 G 3210 DIN47108VERZ RETAINING CLIP DIAMON DA42 DA42 2990004 EU DOWNLOCK PIN MISSING B K NONE O OTHER IN INSP/MAINT 1 SO 15 966WW 13 13 42AC106 DURING PREFLIGHT THE PILOT NOTICED THAT THE MLG DOWNLOCK PIN (PN-D60-3237-11-34) HAD NO RETAINING CLIPS(PN-DIN471-08-VER Z). THE GROOVES IN THE PIN ARE VERY SHALLOW AND ALLOW THE CLIPS TO MIGRATE OFF. 1 L 7 2 3I RT A57CE 2008012200194 20080122 00194 SO 2008 1 22 2008FA0000041 1 20080109 G 7120 MOUNT PIPER PA28 PA28R201 7102816 SO LYC O360 IO360A1A 41514 EA LT ENGINE CRACKED B B2ER K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 EA 23 25EL 28R7837087 ENGINE MOUNT FOUND CRACKED AT BOTTOM LT WHERE SHOCK MOUNT ATTACHES. (K) 1 L 7 1 3O 3 O 2A13 1E10 2008021200236 20080212 00236 EA 2008 2 12 2008FA0000043 2 20080111 G 8520 600050507 PUSHROD PIPER PA60 PA60602P 7106015 NM LYC O540 IO540* 41532 EA ENGINE CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 25 700LG 608265043 THE AREA IN WHICH THE CORRODED SECTION OF THE PUSHROD ASSY IS LOCATED IS PRONE TO EXHAUST CONTAMINATION SINCE IT IS DIRE CTLY BEHIND THE ENGINE EXHAUST PIPE OUTLETS. AREA NEEDS TO BE KEPT CLEAN OF EXHAUST RESIDUE AND CORROSION PREVENTATIVE APPLIED. OLDER TUBES WERE ALODINED ALUMINUM. NEWER TUBES ARE ZINC CHROMATED ALUMINUM BUT ARE STILL SUSCEPTIBLE TO CORR OSION. INSPECTION OF THIS AREA IS ACCESSIBLE THROUGH THE WING FLAP ACTUATOR ACCESS PANEL. SB 600-122 ADDRESSES THIS S UBJECT. (K) 1 M 7 2 3O 3 O RT A17WE 1E4 2008021200237 20080212 00237 EA 2008 2 12 2008FA0000044 2 20080111 G 8520 600050507 PUSHROD PIPER PA60 PA60601P 7106012 NM LYC O540 IO540* 41532 EA ENGINE CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 25 25RH 2446 61P066979633 THE AREA IN WHICH THE CORRODED SECTION OF THE PUSHROD ASSY IS LOCATED IS PRONE TO EXHAUST CONTAMINATION SINCE IT IS DIRE CTLY BEHIND THE ENGINE EXHAUST PIPE OUTLETS. THIS AREA NEEDS TO BE KEPT CLEAN OF EXHAUST RESIDUE AND CORROSION PREVENTA TIVE APPLIED. OLDER TUBES WERE ALODINED ALUMINUM. NEWER TUBES ARE ZINC CHROMATED ALUMINUM BUT ARE STILL SUSCEPTIBLE TO CORROSION. SB 600-122 ADDRESS THIS SUBJECT. INSPECTION IS DONE THROUGH FLAP ACTUATOR ACCESS PANEL. (K) 1 M 7 2 3O 3 O RT A17WE 1E4 2008021200239 20080212 00239 SO 2008 2 12 2008FA0000046 1 20080104 G 3297 153615 WIRE PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540* 41532 EA MLG FAILED D SNSR O OTHER O OTHER NR NOT REPORTED 1 GL 13 878BT 446 3257402 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT. SILIC ONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT. NEEDS BETTER WIRE AND ROUTING. (K) 1 L 7 1 3O 3 O A3SO E14EA 2008021200240 20080212 00240 SO 2008 2 12 2008FA0000047 1 20080109 G 3297 153615 WIRE PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540* 41532 EA MLG FAILED D SNSR K NONE O OTHER IN INSP/MAINT 1 GL 13 5354V 528 3257298 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT. SILIC ONE TYPE WIRE COATING TENDS TO HOLE WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT. NEEDS BETTER WIRE AND ROUTING. (K) 1 L 7 1 3O 3 O A3SO E14EA 2008013100288 20080131 00288 SO 2008 1 31 2008FA0000048 1 20080104 G 3297 153615 WIRE PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540* 41532 EA DOWNLOCK SWITCH FAILED D SNSR K NONE O OTHER IN INSP/MAINT 1 GL 13 5354V 3257298 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT. SILIC ONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT. NEEDS BETTER WIRE AND ROUTING. (K) 1 L 7 1 3O 3 O A3SO E14EA 2008021200241 20080212 00241 SO 2008 2 12 2008FA0000049 1 20080111 G 3297 153615 WIRE PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540* 41532 EA MLG FAILED D SNSR O OTHER O OTHER NR NOT REPORTED 1 GL 13 999TC 3257356 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT. SILIC ONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT. NEEDS BETTER WIRE AND ROUTING. (K) 1 L 7 1 3O 3 O A3SO E14EA 2008021200242 20080212 00242 SO 2008 2 12 2008FA0000050 1 20080104 G 3297 153615 WIRE PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540* 41532 EA MLG FAILED D SNSR K NONE O OTHER IN INSP/MAINT 1 GL 13 999TC 249 3257356 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT. SILIC ONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT. NEEDS BETER WIRE AND ROUTING. (K) 1 L 7 1 3O 3 O A3SO E14EA 2008021200245 20080212 00245 CE 2008 2 12 2008FA0000051 1 20080107 G 2752 991434446 FLEX DRIVE CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C GL T/E FLAP WORN B CNQR A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CE 07 953QS 7500153 AIRCRAFT EXPERIENCED A FLAP FAIL MESSAGE AFTER TAKEOFF, DIVERTED FOR REPAIR AND THE PILOT ELECTED TO DECLARE AN EMERGENC Y BEFORE LANDING. THE AIRCRAFT LANDED WITHOUT INCIDENT. AFTER TROUBLESHOOTING, THE FLAP SYSTEM THE RT AND LT NR 5 FLAP FLEX DRIVES WERE FOUND TO BE WORN CAUSING A FLAP FAULT. DRIVES HAVE BEEN REPLACED AND SYSTEM MECHANICAL AND ELECTRICAL OPERATIONAL CHECK ACCOMPLISHED. NO FURTHER DEFECTS WERE FOUND. (K) 2 L 7 2 4J 4 F RT T00007WI TE6CH 2008013100296 20080131 00296 CE 2008 1 31 2008FA0000052 1 20080116 G 3060 BOOT BEECH 60 A60 1153604 CE LYC O541 TIO541* 41536 EA PROPELLER SEPARATED B PZ4R K NONE D INFLIGHT SEPARATION IN INSP/MAINT 1 GL 11 4445W P245 A PROPELLER CAME IN FOR REPAIRS WHICH NECESSITATED THE INSTALLATION OF NEW DEICE BOOTS ON ALL 3 BLADES. THE PROP WAS LA TER INSTALLED BY THE OWNER’S MECHANIC. 1 OF THE 3 BOOTS CAME OFF RESULTING IN A DENT ON THE AIRCRAFT FUSELAGE, REPORTED AFTER ABOUT 7 HOURS OF FLYING. QUESTIONING OF OUR TECH THAT INSTALLED THE BOOTS REVEALED NO DEVIATIONS IN PROCEDURES O CCURRED DURING THE INSTALLATION. IT WAS DETERMINED THAT THE GLUE USED FOR THE INSTALLATION WAS RECEIVED BY OUR FACILITY ON 8/23/07 WITH AN EXPIRATION DATE OF 9/30/08. MM 202A LISTS THE SHELF LIFE OF 1300L ADHESIVE AS 15 MONTHS. AS A PREC AUTION, THE ADHESIVE WAS REMOVED FROM USE EVEN THOUGH NO DISCREPANT CONDITION COULD BE FOUND. FACILITY VISITED LOCATION 1 L 7 2 3O 3 O A12CE E10EA 2008013100292 20080131 00292 CE 2008 1 31 2008FA0000053 1 20080117 G 2134 1303687 PRESSURE SENSOR LEAR 35 35A 5170602 CE GARRTT TFE731 TFE731* 01518 WP AFT BAGGAGE MALFUNCTIONED E B EMER. DESCENT J WARNING INDICATION CL CLIMB 1 SO 11 55FN 11587 202 LOSS OF CABIN PRESSURE AT 25K FT. PRESSURE SENSOR MALFUNCTIONED 2 L 7 2 4F 4 F A10CE E6WE 2008013100294 20080131 00294 CE 2008 1 31 2008FA0000056 1 20080123 G 5514 ATTACH BOLT CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15* 52060 NE HORIZONTAL STAB UNDERTORQUED B HSRR K NONE O OTHER IN INSP/MAINT 1 NM 05 570EJ 5600164 DURING A ROUTINE PHASE INSPECTION WE FOUND 50 PERCENT OF THE HORIZONTAL STABILIZER AFT ATTACH BOLTS TO BE UNDERTORQUED, AND CAUSING SOME MOVEMENT AND A POPPING NOISE WHEN THE STABILIZER WAS PUSHED UP AND DOWN AT THE OB TIP. WE RE-TORQUED A LL BOLTS AND THE NOISE AND MOVEMENT WENT AWAY. SOME OF THE BOLTS REQUIRED 180 DEGREE ROTATION TO OBTAIN PROPER TORQUE. PERFORMED HIDDEN DAMAGE INSPECTION, NO DEFECTS WERE NOTED. 2 L 7 2 4F 4 T RT A22CE E1NE 2008012900004 20080129 00004 SO 2008 1 29 2008FA0000057 1 20080118 G 7603 455322 THROTTLE CABLE PIPER PA28 PA28R201 7102816 SO LYC O360 IO360A1A 41514 EA INFLT SEPARATION B A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SO 15 701ER 4192 82 2844053 DURING FLIGHT, THE CREW EXPERIENCED A SEPARATION OF THE THROTTLE CABLE. THE POWER SETTING ALLOWED THEM TO MAINTAIN ALTIT UDE PLUS A SLIGHT CLIMB. THE CREW POSITIONED THE AIRCRAFT FOR A LANDING ON A RUNWAY THAT HAD AMPLE LENGTH. AN UNEVENTFUL LANDING WAS MADE. THE THROTTLE CABLE WAS REMOVED AND INSPECTED AND FOUND TO BE BROKEN A FEW INCHES INSIDE THE OUTER HOU SING JUST AFT OF THE FUEL SERVO. THERE IS NO TIME/LIFE LIMIT ON THESE CABLES, HOWEVER THE OPERATOR WILL NOW CHANGE THE C ABLES DURING EACH ENGINE CHANGE. 1 L 7 1 3O 3 O 2A13 1E10 2008013100295 20080131 00295 NE 2008 1 31 2008FA0000058 2 20080123 G 7200 0319008000 ENGINE UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIUS2F 60010 NE MAKING METAL B A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 SW 01 146CB 173 169 1407 34481 ON 10, OCT. 2007 THE PILOT REPORTED THE ENGINE CHIP WARNING LAMP ILLUMINATED. THE AIRCRAFT WAS LANDED WITHOUT INCIDENT. THIS WAS THE FOURTH OCCURRENCE IN 10.9 HOURS. THE ENGINE WAS REMOVED AND RETURNED TO MFG FOR EVALUATION AND REPAIR. 1 G 7 2 3U 3 U NC R0001RD E34NE 2008013100303 20080131 00303 EA 2008 1 31 2008FA0000062 2 20080102 G 7314 2B664 PUMP PIPER PA31 PA31350 7103110 SO LYC O540 TIO540* 41532 EA FUEL SYSTEM INOPERATIVE D A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 SO 05 202TC 2098 318152037 ON 1/2/2008 THE PILOT WAS DEPARTING WHEN HE REPORTED THAT HE LOST SUBSTANTIAL POWER TO THE LT ENGINE JUST AFTER TAKEOFF AND THE LT LOW PRESSURE FUEL BOOST PUMP LIGHT ON THE AC ANNUNCIATOR PANEL ILLUMINATED. PILOT LANDED AT AIRPORT AND CALL ED AC TECH. AIRCRAFT TECH ON LOCATION COULD NOT FIND ANY PROBLEMS WITH THE ENGINE DURING RUN UP OTHER THAN THE ELECTRIC LOW PRESSURE FUEL BOOST PUMP NOT SUPPLYING RATED PRESSURE. THE ELECTRIC IN-LINE LOW PRESSURE BOOST PUMP IS INTENDED FO R FLIGHT ABOVE 15,000 FT MSL AND CAN BE DEFERRED IAW PART 91 MEL. AC WENT TO DEPART AIRPORT AND THE LT ENGINE LOST POWE R AGAIN DURING THE TAKEOFF ROLL AT ABOUT 40 KNOTS OF AIRSPEED. TROUBLESHOOTING OF ENGINE FUEL PUMP, FUEL NOZZLES REVEAL 1 L 7 2 3O 3 O A20SO E14EA 2008021200259 20080212 00259 CE 2008 2 12 2008FA0000063 1 20080116 G 3060 4E11883 BOOT BEECH 60 A60 1153604 CE LYC O541 TIO541* 41536 EA HARTZL HCF3Y HCF3YR2 GL PROPELLER DEBONDED B PZ4R O OTHER O OTHER NR NOT REPORTED 1 GL 11 4445W 4 P245 DA684 PROP WAS SENT FOR REPAIRS CONSISTING OF FLUSH AND RESEAL OF PROP, PAINTING OF BLADES AND INSTALLATION OF NEW DEICE BOOTS . AC HAS FLOWN 3.5 HRS AND THREW A DEICE BOOT, DENTED THE RT NOSE SECTION OF THE AC. SPEAKING WITH SERVICE REP, HE STA TED THAT THE GLUE USED TO ADHERE THE BOOT HAD FAILED AFTER REVIEWING PHOTOS SENT TO HIM. IF THIS IS THE CASE, A RECOMME NDATION OF FINDING OUT LOT NUMBER OF ADHESIVE, AND RECALLING ANY WORK DONE USING THIS LOT NUMBER. (K) 1 L 7 2 3O 3 O A12CE E10EA 5 C P31EA 2008013100289 20080131 00289 CE 2008 1 31 2008FA0000066 1 20080122 G 3411 FITTING CESSNA 206 T206H 2073303 CE LYC O360 O360E1A6D 42305 EA STATIC SYS FAILED D K NONE O OTHER NR NOT REPORTED 1 NE 01 2095S T20608442 PRIOR TO COMPLIANCE WITH FAR 91.411, A STATIC SYSTEM CHECK WAS CONDUCTED. UNDER TEST SYSTEM SHOWED APPROXIMATELY 100 FPM DESCENT RATE. INSPECTION REVEALED THE 90 DEGREE PLASTIC FITTINGS (ONE ON EACH SIDE OF THE FORWARD FUSELAGE) FOR STATIC SYSTEM PLUMBING WERE MADE OF MOLDED PLASTIC AND INCLUDED A TINY RIDGE (MOLD LINE) ALONG THE THREADED AREA. ADDITIONALLY MFG INSTALLED THE PART WITHOUT THE USE OF PIPE SEALING COMPOUND MAKING AT LEAST PARTIAL FAILURE INEVITABLE. 1 H 7 1 3O 3 O RT A4CE E286 2008020400106 20080204 00106 2008 2 4 2008FA0000068 1 20080130 G 6500 538715 SHAFT TAIL ROTOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 WP 23 ONE PIECE TRANSVERSE CRACK AROUND THE AREA OF PART THAT HAD LONGITUDINAL INDICATIONS (ORIGIN UNKNOWN BUT POSSIBLY RELATE D TO STRESS, FATIGUE OR WEAR), OTHER 4 PIECES ONLY WITH THE SAME LONGITUDINAL INDICATIONS. 2008020400108 20080204 00108 EU 2008 2 4 2008FA0000069 1 20080123 G 5510 T700A5510065000 HINGE SOCATA TBM TBM700 8682000 EU STABILIZER CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 13 800GS 857 100 149 HINGE FOUND CRACKED IN AREA OF CONCERN IDENTIFIED IN AD 99-07-11, PREVIOUS INSPECTION 100 HOURS EARLIER SHOWED NO SIGN O F CRACKING. 1 L 7 1 3T RT A60EU 2008020400102 20080204 00102 EU 2008 2 4 2008FA0000070 1 20080131 G 5280 D605287300 HINGE DIAMON DA42 DA42 2990004 EU MLG DOOR BROKEN B N3XR O OTHER E VIBRATION/BUFFET LD LANDING 1 SO 15 902ER 195 95 42278 DURING FLIGHT WHEN THE LANDING GEAR WAS OPERATED, THERE WAS A NOISE HEARD BY THE CREW. UPON LANDING THE LT MAIN LANDING GEAR DOOR WAS ATTACHED ONLY BY THE LOWER DOOR CONTROL LINK. THE REAR GEAR DOOR HINGE, AFT BRACKET HAD BROKEN AT THE WELD OF THE PIECE BOLTED TO THE WING STRUCTURE. THE DOOR HAD FALLEN LOW ENOUGH TO WHERE THE FORWARD CORNER WAS WORN AWAY BY CONTACT WITH THE GROUND. THIS OPERATOR OPERATES A FLEET OF 9 DA42 AIRCRAFT. ON INITIAL INSPECTION MANY OF THE OTHER AIRC RAFT HAD CRACKS DEVELOPING AT THE POINT OF FRACTURE OF THE DAMAGED AIRCRAFT. ALL OF THE HINGE POINTS ON ALL OF THE AIRCR AFT WILL BE CHANGED. 1 L 7 2 3I RT A57CE 2008021200038 20080212 00038 NM 2008 2 12 2008FA0000071 1 20080204 G 5220 LANYARD AMD FALC50 FALCON2000 2730170 NM CFE CFE73811B NE EMERGENCY WINDOW MISSING B CWQD K NONE O OTHER IN INSP/MAINT 1 GL 05 275QS 75 ACCESS COVER FOR THE EMERGENCY WINDOW HANDLE DOES NOT HAVE A LANYARD WHEN IT IS REMOVED. THE COVER HANGS BY THE WIRING THAT ILLUMINATES IT PUTTING STRESS ON THE SOLDERED CONNECTIONS TO BREAK CAUSING EITHER AN INOPERATIVE EMERGENCY LIGHT OR A SHORT CAUSING MORE THAN ONE EMERGENCY LIGHT TO NOT ILLUMINATE. THIS COVER IS REMOVED ROUTINELY FOR SECURITY PINNING OF THE EXIT HANDLE AND FOR EMERGENCY WINDOW HANDLE INSPECTION. THERE SHOULD BE A LANYARD TO PROVIDE STRESS RELIEF FOR T HE ASSOCIATED WIRING MOUNTED ON THE COVER AND IN THE WINDOW ASSY. (K) 2 L 7 2 4F 4 F RT A50NM E44NE 2008021200037 20080212 00037 NE 2008 2 12 2008FA0000072 2 20080111 G 7250 1808M15G03 SUPPORT CFMINT AIRBUS 320 A320* EU CFMINT CFM56 CFM565B42P 13013 NE HPT NOZZLE ERODED B QEMY K NONE O OTHER IN INSP/MAINT 1 EA 35 51X79408 779408 DURING DISASSEMBLY OF THE CORE MAJOR MODULE, REMOVED FROM ESN 779408, REMOVAL OF THE COMBUSTION LINER MODULE EXPOSED THE FWD INNER NOZZLE MODULE EXPOSED THE FORWARD INNER NOZZLE SUPPORT (FINS). IT WAS NOTED THAT THE FINS HAD 1-OFF AREA OF LOCALIZED EROSION WHICH HAD RESULTED IN PENETRATION OF THE COMPONENT. THE EROSION WAS LOCATED ON THE SUPPORT BODY SECTI ON OF THE COMPONENT, JUST AFT OF THE FWD FLANGE AND ADJACENT TO THE NR 22 AND 23 BOLT HOLES (CLOCKWISE FROM TDC, ALF) TH E CAUSE OF THE EROSION IS UNKNOWN. CIRCUMFERENTIAL EROSION TO THE SUPPORT BODY OF THE FINS IS COMMON BUT LOCALIZED EROS ION, AS SEEN IN THIS INSTANCE HAS NOT BEEN SEEN PREVIOUSLY. ALL AFFECTED PARTS ARE SCHEDULED FOR RETURN TO MFG FOR FAIL 2 L 7 2 4F 4 F RT A46NM 2008021200035 20080212 00035 SO 2008 2 12 2008FA0000073 1 20080114 G 5341 62448003 ATTACH FITTING PIPER PA28 PA28151 7102805 SO LYC O320 O320* 41508 EA FUSELAGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 EA 01 44542 287415662 THIS FUSELAGE REAR WING ATTACH FITTING WAS BEING REPLACED DUE TO CORROSION PITTS ON FRONT SURFACE. UPON REMOVAL SOME SE VERE PITTING WAS NOTED JUST IB OF THE .3125 INCH WING ATTACH BOLT HOLE ON THE REAR SIDE OF THE FITTING. THIS AREA IS EX POSED TO OUTSIDE AIR AND MOISTURE AND IS LOCATED IN A DIFFICULT AREA TO INSPECT. THIS ARA IS ALSO MORE CRITICAL IN RELA TION EVENTUAL PART FAILURE THAN THE FRONT SURFACE THAT IS VISIBLE FROM INSIDE THE FUSELAGE. RECOMMEND CLEANING DIRT OUT OF AREA AND INSPECTING WITH A GOOD LIGHT. (K) 1 L 7 1 3O 3 O 2A13 E274 2008021200032 20080212 00032 SO 2008 2 12 2008FA0000074 2 20080115 G 8530 AEC642068 CYLINDER CESSNA 182 182H 2072718 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL NR 1 DAMAGED B MS2R K NONE O OTHER IN INSP/MAINT 1 CE 09 1928X 247 18256028 288449R 822386 WHILE PERFORMING A COMPRESSION CHECK TO FIND AN OIL LEAK, FOUND NR 1 CYLINDER WITH O COMPRESSION. PULLED CYLINDER OFF A ND FOUND THE PLATING ON THE CYLINDER LOOSE AND FLAKING OFF. (K) 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2008022000026 20080220 00026 SO 2008 2 20 2008FA0000077 2 20080207 G 7414 6310 CAM BEECH 58 58 1152740 CE CONT O550 IO550C SO MAGNETO WORN B D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 WP 27 878JM 444 444 TH2065 690181AND6 100 RPM MAGNETO DROP ON PRE-FLIGHT RUN-UP. INSPECTED ALL (4) MAGNETOS ON BOTH ENGINES. FOUND ALL MAGNETO CAMS WORN. N O LUBRICATION WAS FOUND ON THE CAMS. THESE MAGNETOS HAD 444.0 HRS TIME SINCE NEW, AND HAD COME INSTALLED ON NEW ENGINES. THEY HAD NOT HAD THEIR FIRST 500 HR INSPECTION, SO HAD NEVER BEEN INSPECTED/OPENED SINCE NEW. MAGNETOS, SN'S: 06121306 , 06121346, 06120367, AND 06121304. 1 L 7 2 3O 3 O 3A16 E3SO 2008031700256 20080317 00256 EU 2008 3 17 2008FA0000078 1 20080125 G 2910 GCH1004 HYDRAULIC SYSTEM UROCOP EC120 EC120B 8680987 EU CONTAMINATED D K NONE J WARNING INDICATION IN INSP/MAINT 1 WP 28 179CB 555 55 1412 HYD POWER PACK PRE-CLOGGING INDICATOR IS DISPLAYED BEFORE FLIGHT. 1 G 7 2 3U NC R0001RD 2008031900262 20080319 00262 CE 2008 3 19 2008FA0000082 1 20080218 G 3397 CAPACITOR BEECH 90 E90 1152914 CE PWA PT6 PT6* 52043 EA MCAULY 4HFR34 4HFR34C762 NE CABIN LIGHTS BURNED E B EMER. DESCENT B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 SO 14 662JS LW176 AT CRUISE FL 150, CREW NOTICED SMOKE AND ELECTRICAL ODOR COMING FROM SIDEWALL UNDERNEATH EMERGENCY EXIT. PIC DECLARED E MERGENCY AND LANDED AC WITHOUT FURTHER INCIDENT. UPON INSP OF SIDEWALL UNDER EMERGENCY EXIT, IT WAS NOTICED THAT A SMA LL HOLE WHICH APPEARED TO LOOK LIKE A CIGARETTE BURN AT FIRST HAD PENETRATED THROUGH HONEYCOMB MATERIAL AND THE ULTRA SU EDE LINER THAT COVERS THE SIDEWALL. UPON CLOSER INSP BEHIND SIDEWALL, NO ELECTRICAL COMPONENTS OR WIRING ARE LOCATED BE HIND THE AREA WHERE THE HOLE IS LOCATED. AFTER REMOVING THE VALANCE PANEL ON THE EMERGENCY EXIT WINDOW, IT WAS NOTICED THAT THE CAPACITOR AND THE DIODE FOR THE INDIRECT LIGHTING POWER SUPPLY WAS BURNED. 1 L 7 2 3T 3 T 3A20 E2NE 6 C 3PNE 2008040300040 20080403 00040 CE 2008 4 3 2008FA0000084 1 20080221 G 2910 1285094 LINE CESSNA 210 T210M 2073451 CE CONT O520 TSIO520* 17040 SO HYDRAULIC SYS CHAFED D K NONE O OTHER IN INSP/MAINT 1 SW 15 761AV 4400 21062110 REPLACED HYDRAULIC TUBE 128509-4 DUE TO CHAFING FROM LONG SCREW IN WRONG LOCATION OF INSPECTION COVER PLATE. THIS WAS F OUND BY INSPECTION AS DESCRIBED IN MFG SEB07-03 AND WHICH HAVE A SUPERSEDED PN AVAILABLE TO NULLIFY THE POTENTIAL PROBLE M. THIS SERIES AND OTHER MODELS SHOULD BE ADDED TO SERVICE BULLETIN APPLICABILITY. 1 H 7 1 3O 3 O 3A21 E8CE 2008022500004 20080225 00004 CE 2008 2 25 2008FA0000085 1 20080221 G 2910 1285094 LINE CESSNA 210 T210M 2073451 CE HYDRAULIC SYS CHAFED D O OTHER O OTHER NR NOT REPORTED 1 SW 15 761AV 4400 21062110 REPLACED HYDRAULIC TUBE (PN 128509-4) DUE TO CHAFFING FROM LONG SCREW IN WRONG LOCATION OF INSPECTION COVER PLATE. THIS WAS FOUND BY INSPECTION AS DESCRIBED IN SEB07-03 FOR 182 SERIES, AND WHICH 182'S HAVE A SUPERSEDED PN AVAILABLE TO NULL IFY THE POTENTIAL PROBLEM. THIS SERIES AND OTHER MODELS SHOULD BE ADDED TO SB APPLICABILITY. 1 H 7 1 3O 3A21 2008022500005 20080225 00005 CE 2008 2 25 2008FA0000086 1 20080215 G 5711 0411129 SPAR CESSNA 150 150G 2071816 CE CONT O200 O200* 17020 SO WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 WP 07 3895 15065116 WINGS WERE PREVIOUSLY REMOVED TO FACILITATE TRANSPORTATION. INSP OF THE LT AND RT FWD SPAR BEARING BLOCKS IN THE FUSELAG E (P/N 0411129) FOUND SEVERE CORROSION DAMAGE. IT APPEARS TO BE DISSIMILAR METAL CORROSION BETWEEN THE SPAR BLOCKS AND T HE AN3-21A ATTACHMENT BOLTS. THIS AREA WOULD BE VERY DIFFICULT TO INSPECT WITH THE WINGS ATTACHED. THE SAME P/N AND WING ATTACHMENT SYS IS USED ON MOST OF THE AC SERIES HIGH WING AIRCRAFT. 1 H 7 1 3O 3 O 3A19 E252 2008040300022 20080403 00022 CE 2008 4 3 2008FA0000087 1 20080215 G 5311 0411129 SPAR CESSNA 150 150G 2071816 CE CONT O200 O200* 17020 SO WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 WP 07 3816J 3895 15065116 WINGS WERE PREVIOUSLY REMOVED TO FACILITATE TRANSPORTATION. INSPECTION OF THE LT AND RT FWD SPAR BEARING BLOCKS IN THE F USELAGE (P/N 0411129) FOUND SEVERE CORROSION DAMAGE. IT APPEARS TO BE DISSIMILAR METAL CORROSION BETWEEN THE SPAR BLOCKS AND THE AN3-21A ATTACHMENT BOLTS. THIS AREA WOULD BE VERY DIFFICULT TO INSPECT WITH THE WINGS ATTACHED. 1 H 7 1 3O 3 O 3A19 E252 2008040200041 20080402 00041 SO 2008 4 2 2008FA0000088 2 20080207 G 7414 6310 CAM BEECH 58 58 1152740 CE CONT O550 IO550C SO MAGNETO WORN B D RETURN TO BLOCK R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 WP 27 878JM 444 444 TH2065 690181AND6 100 RPM MAGNETO DROP ON PRE-FLIGHT RUN-UP. INSPECTED ALL FOUR MAGNETOS ON BOTH ENGINES.FOUND ALL MAGNETO CAMS WORN. NO LUBRICATION WAS FOUND ON THE CAMS. THESE MAGNETOS HAD 444.0 HRS TIME SINCE NEW, AND HAD COME INSTALLED ON NEW ENGINES. THEY HAD NOT HAD THEIR FIRST 500 HR INSPECTION, SO HAD NEVER BEEN INSPECTED/OPENED SINCE NEW. SLICK 6310 MAGNETOS, SN'S : 06121306, 06121346, 06120367, AND 06121304. 1 L 7 2 3O 3 O 3A16 E3SO 2008031000330 20080310 00330 CE 2008 3 10 2008FA0000089 1 20080129 G 2915 7629001004001 PRESSURE SWITCH LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE731* 01518 WP HYDRAULIC SYS FAILED B WMYR A UNSCHED LANDING O OTHER NR NOT REPORTED 1 SO 09 444MW 2127 131 LT HYDRAULIC PRESSURE SWITCH (S9) FAILED IN FLIGHT, RESULTING IN LOSS OF HYDRAULIC FLUID AND FAILURE OF BOTH LT AND RT H YDRAULIC PUMPS. NECESSITATED A FLIGHT DIVERSION TO AN ALTERNATE AIRPORT WITH AN EMERGENCY DECLARATION. (K) 2 L 7 2 4F 4 F RT T00008WI E6WE 2008031000332 20080310 00332 CE 2008 3 10 2008FA0000091 1 20080122 G 3245 TUBE CESSNA 172 172R 2072401 CE LYC O360 IO360A1A 41514 EA LANDING GEAR FAILED B AW4R O OTHER O OTHER NR NOT REPORTED 1 WP 11 784WW 17280816 FROM SEPT 7 TO PRESENT, AC HAS EXPERIENCED (3) LANDING GEAR TIRE TUBE FAILURES. FAILURES ALL OCCURRED IN THE SIDEWALL O F THE TUBES. THERE WAS NO EVIDENCE OF THE TUBES BEING PINCHED OR OTHERWISE DAMAGED DURING INSTALLATION. DAMAGE RANGED FROM SMALL (.1250 INCH) SPLITS TO A LARGE (.5 INCH) SPLIT. EXAMINATION OF THE TUBE SIDEWALLS EVIDENCED WHAT APPEAR TO B E SOME FORM OF (WEATHER CHECKING) THAT NORMALLY APPEARS ON OLD RUBBER COMPONENTS. ALL TUBES WERE OF RECENT MANUFACTURE. ONE FAILURE OCCURRED ON A G15/6.00/6 TUBE (PN 302-246-401) WITH TT OF 123 HOURS. (2) FAILURES OCCURRED ON 5.00 X 5 TU BES (PN 302-013-400 AT 125 HOURS AND 112 HOUR RESPECTIVELY. TUBES WERE FORWARDED TO MFG FOR EVALUATION. EVALUATION IS 1 H 7 1 3O 3 O NT 3A12 1E10 2008031000333 20080310 00333 2008 3 10 2008FA0000092 4 20080111 G 2564 100102303 LIFE RAFT CABIN UNWANTED DEPLOY D JAVR K NONE O OTHER IN INSP/MAINT 1 EA 61 LIFE RAFT STARTED TO INFLATE WHILE PLACING ON AIRCRAFT WITH NORMAL HANDLING. LIFE RAFT WAS IMMEDIATELY REMOVED AND HELD FOR VENDOR PICK-UP. NOTE: LIFE RAFT WAS A LOANER , OVERHAULED ON 7/26/07. LIFE RAFT WAS RECEIVED AND INSPECTED ON 1/ 11/2008 WITH NO DAMAGE NOTED. (K) 2008033100041 20080331 00041 GL 2008 3 31 2008FA0000093 3 20080204 G 6114 HUB CESSNA 188 A188B 2073005 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C98 GL PROPELLER CRACKED B LU4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 731VX 18803200T 775315 PROPELLER HUB CRACKED. (K) 1 L 7 1 3O 3 O A9CE E5CE 5 C P3EA 2008031000334 20080310 00334 GL 2008 3 10 2008FA0000094 3 20080204 G 6114 HUB MCAULY CESSNA 337 M337B 2075708 CE CONT O360 IO360D 17025 SO MCAULY 2AF34C D2AF34C61 GL PROPELLER CRACKED D LU4R K NONE O OTHER IN INSP/MAINT 1 SO 19 373AZ 661450 337M0079 RELEVENT INDICATION (CRACKED). (K) 1 H 7 2 3O 3 O RT A6CE E1CE 5 C P5EA 2008031000335 20080310 00335 GL 2008 3 10 2008FA0000095 3 20080204 G 6114 HUB MCAULY CESSNA 402 402B 207590P CE CONT O520 TSIO520* 17040 SO MCAULY 3AF32C 3AF32C87 GL PROPELLER CRACKED D LU4R K NONE O OTHER IN INSP/MAINT 1 SO 19 95RG 779643 402B0538 RELEVENT INDICATION (CRACKED 2 PLACES). (K) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2008031000336 20080310 00336 SO 2008 3 10 2008FA0000096 1 20080128 G 5343 86282010 SPAR PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA NLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 856ND 4495001 THE SPAR ASSY WAS CRACKED AT THE LT SIDE NOSE GEAR SUPPORT FITTING. THE CRACK RADIATED OUT FROM THE AFT LOWER BOLT ATTA CHMENT ( AS VIEWED FROM BELOW THE NOSE STRUCTURE FLOORING) ONCE THE A-FRAME SUPPORT WAS REMOVED, THERE WAS A (2 INCH) C RACK IN THE SPAR WEB (NOT VISIBLE UNTIL THE SUPPORT WAS REMOVED). THE LOWER EXTRUSION HAS BEEN REPLACED WITH NEW AT SOM E POINT IN THE AIRPLANES HISTORY (NOT AT THIS SHOP). THE EXTRUSION CRACKING WAS THE REASON FOR DISASSEMBLY AT THIS TIME . THIS IS ADDRESSED IN AD 81-10-01 BUT THE AD IS NOT APPLICABLE TO THIS SERIAL NUMBER AIRCRAFT. SB NR 1143 COVERS THE LATER SN AC. (K) 1 L 7 2 3O 3 O A19S0 E286 2008031000346 20080310 00346 GL 2008 3 10 2008FA0000099 2 20080131 G 7230 23074076 SCROLL BELL 407 407 1182206 SW ALLSN 250C 250C47B GL COMPRESSOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 05 31PB 1082 53569 CAC45245 COMPRESSOR (PN 23065593 SN CAC45245) WAS RECEIVED INTO THE SHOP FOR REMOVAL AND REPLACEMENT OF THE SCROLL (PN 23074076(B ) SN 40353) FOR A VISIBLE OPEN HOLE OR BROKEN OFF HEX EXTERNAL BOSS LOCATING PIN AT THE TURNING VANE LOCATION ON THE SCR OLL. THE OPERATOR CONDUCTS PATROLLING OR POLICE ACTIVITY USING THE AC AND FOUND THE DEFECT WHILE PERFORMING A 100 HR MA INT TASK. THE AFFECTED COMPRESSOR SCROLL WAS COATED WITH SERVETEL WHICH IS AN OEM APPROVED COATING FOR PROTECTION AGAIN ST CORROSION AND AS INDIDCATED IN THE LOG BOOKS, THIS IS THE 2ND SCROLL TO HAVE BEEN REPLACED. (K) 1 G 7 1 3U 3 U O H2SW E1GL 2008032400430 20080324 00430 CE 2008 3 24 2008FA0000100 1 20080205 G 2915 7629001004001 PRESSURE SWITCH LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP HYDRAULIC SYSTEM FAILED D A UNSCHED LANDING J K WARNING INDICATION FLUID LOSS CR CRUISE 1 SO 09 444MW 131 APPROXIMATELY 40 MIN IN TO PLANNED FLIGHT, WHILE AT FL410, IN FINAL CRUISE CONDITION, A WHITE ADVISORY CAS MESSAGE APPEA RED INDICATING (MAIN HYD QTY LOW). FLIGHT CREW OPENED THE APPROPRIATE CREW CHECKLIST AND FLIGHT MANUAL AND REFERENCED T HE CHECKLIST WHICH SAID (MAIN HYDRAULIC QUANTITY IS LOW), WITH NO ACTION REQUIRED. THE PF DIRECTED THE PNF TO REFER TO ANY ABNORMAL PROCEDURES OR ANY EMERGENCY CHECKLIST PAGE PROCEDURES AS A PRECAUTION FOR LOSS OF HYDRAULIC QUANTITY OR PRE SSURE. THE CREW REVIEWED THESE PROCEDURES AND CONTINUED IN CRUISE. APPROX 15 MIN LATER, DURING DESCENT, A WHITE (L HYD PUMP LO) CAS MESSAGE BEGAN TO APPEAR INTERMITTENTLY, AND HYD PRESSURE FLUCTUATIONS WERE NOTED ON THE PRESSURE INDICATIO 2 L 7 2 4F 4 F RT T00008WI E6WE 2008031900295 20080319 00295 2008 3 19 2008FA0000101 4 20080108 G 2210 238006679 YAW DAMPER LEAR 24 24 5170302 CE FAULTY B A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 01 989TL 160 THIS PART FAILED TO OPERATE DURING FIRST FLIGHT, AFTER INSTALLATION, AT CRUISE. 2 L 7 2 4J A10CE 2008040300055 20080403 00055 2008 4 3 2008FA0000104 4 20080224 G 3197 WIRE HARNESS CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA INSTRUMENT PANEL BURNED B K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CE 07 227BH 6 172S10662 WIRING HARNESS BEHIND AUDIO PANEL WAS CHAFING ON BRACKET THAT HELPS SUPPORT STANDBY BATTERY ON THE PFD SIDE AND CAUSED W IRING TO ARC AND BURN (NOTE: HARNESS IS FOR LIGHT DIMMING OF G-1000). FOUND HARNESS PULLED HARD AGAINST BRACKET. THIS C AUSED THE WIRE TO CHAFE THROUGH THE INSTALLATION AND SHORT OUT. HOWEVER, CIRCUIT BREAKERS AND TRANSISTORS FOR THE LIGHT DIMMING CIRCUIT DID AT NO TIME POP OR FAIL AND WOULD EXPECT TO HAPPEN WHEN THEIR IS A HARD SHORT SINCE THE WIRES ARE ASS OCIATED WITH THE LIGHT DIMMING CIRCUIT. THE HARNESS WAS PULLED HARD AGAINST THE STRUCTURE AS TO CHAFE THROUGH THE INSULA TION AND ARC/SCORCHED THE STRUCTURE. THE WIRE BURNED THROUGH AND ALSO, DAMAGED OTHER WIRES IN THE HARNESS. HARNESS WAS A 1 H 7 1 3O 3 O NT 3A12 1E10 2008033100043 20080331 00043 CE 2008 3 31 2008FA0000106 1 20080211 G 5340 BRACKET CESSNA 500 550 2076604 CE VOLT REGULATOR CORRODED B K NONE O OTHER IN INSP/MAINT 1 WP 21 554MB 5500040 LT GENERATOR VOLTAGE REGULATOR MOUNT BRACKET FOUND TO HAVE CORROSION AT MOUNT SURFACE. ELECTRICAL GROUND PATH AFFECTED. CORROSION REMOVED ALLOWING GOOD GROUND AND ABLE TO ADJUST VOLTAGE REGULATOR, TO SPEC. 1 L 7 2 4F A22CE 2008033100044 20080331 00044 CE 2008 3 31 2008FA0000107 1 20080209 G 2910 98811241 POWERPACK CESSNA 210 T210N 2073456 CE CONT O520 TSIO520* 17040 SO HYD SYSTEM WORN C O OTHER B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 SW 17 127TC 3309 21063381 SMOKE IN COCKPIT, GEAR NOT FULLY RETRACTED, EXTENDED OK. FOUND HYDRAULIC POWERPACK MOTOR (ORIGINAL) WORNOUT. REMOVED A ND REPLACED WITH O/H UNIT. OPS, OK. 1 H 7 1 3O 3 O 3A21 E8CE 2008033100045 20080331 00045 SW 2008 3 31 2008FA0000108 1 20080227 G 2841 5643860 GAUGE MOONEY M20 M20D 5870210 SW LYC O360 O360A1D 41514 EA HARTZL HCC2Y HCC2YK1 GL FUEL SYSTEM INACCURATE D K NONE N FALSE WARNING IN INSP/MAINT 1 GL 15 6608U 5103 103 L533036 CH26709E FUEL GAUGE INDICATION IS APPROX 2.5 TO 3 GAL HIGHER THAN WHAT IS IN THE TANK. (K) 1 L 7 1 3O 3 O 2A3 E286 5 C P920 2008033100048 20080331 00048 2008 3 31 2008FA0000110 4 20080215 G 2312 ANTENNA ISRAEL 1125 ASTRASPX 4500205 EU VHF SYSTEM GOUGED B K NONE O OTHER IN INSP/MAINT 1 WP 09 411MM 080 FOLLOWING REMOVAL OF SATCOM ANTENNA FROM UPPER FUSELAGE FOR INSPECTION, NOTICED FOOTPRINT OF PREVIOUSLY REMOVED NR 1 VHF ANTENNA. UPON INSPECTION OF VHF ANTENNA FOOTPRINT, FOUND NUMEROUS APPARENT MECHANIC INDUCED GOUGES ON FUSELAGE OUTER S KIN. DAMAGE WAS APPARENTLY CAUSED BY IMPROPER REMOVAL OF PREVIOUSLY INSTALLED VHF ANTENNA. REPAIR WAS TO BLEND OUT GOU GES IAW DER EVALUATION. (K) 2 L 7 2 4F RT A16NM 2008032500033 20080325 00033 GL 2008 3 25 2008FA0000111 1 20080304 G 6420 ECD00213 BEARING ENSTRM F28 280FX 3300506 GL LYC O360 HIO360F1AD 41514 EA TAIL ROTOR SEIZED D O OTHER F FLT CONT AFFECTED CR CRUISE 1 NM 03 285SH 1 2120 THE THRUST BEARINGS IN THE TAIL ROTOR BLADE GRIPS ARE OF MATCHED SETS. THESE SETS HAVE A SPECIFIC INSTALLATION ORIENTATI ON. ORIENTATION OF THESE BEARINGS ARE MARKED WITH A (V). THE (V) IS TO BE ORIENTED TOWARD THE CENTER OF THE TAIL ROTOR S PINDLE HUB. ON THESE SPECIFIC BEARINGS THE (V) WAS MARKED POINTING THE WRONG DIRECTION LEADING TO A REVERSED INSTALLATIO N CAUSING A SEIZURE OF THE BEARINGS. ALL BEARINGS WERE INSTALLED IN ACCORDANCE WITH ENSTROM SERVICE LETTER 133 DATED JUN E 8, 1987 , SERVICE LETTER 153 DATED FEBRUARY 15, 2002 AND ENSTROM F SERIES MAINTENANCE MANUALS REVISION 1 DATED 4-3-86 AND REVISION 2 DATED 11-18-88. 1 G 7 1 3O 3 O H1CE 1E10 2008031700264 20080317 00264 EU 2008 3 17 2008FA0000114 1 20080129 G 2435 160SG140Q1XL STARTER GEN UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIUS2F 60010 NE ENGINE FAILED D K NONE O OTHER NR NOT REPORTED 1 WP 28 179CB 558 58 1412 STARTER/GENERATOR FAILED TO ENERGIZE. 1 G 7 2 3U 3 U NC R0001RD E34NE 2008033100052 20080331 00052 2008 3 31 2008FA0000115 4 20080118 G 6113 C2365 BULKHEAD SNSNCH MAULE MX7 MXT7160 5470204 SO LYC O320 O320* 41508 EA SNSNCH 74D 74DM EA PROP SPINNER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 11 57HS 3600 17005C RL1318639A A57306 THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT MOLT HOLES. THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K) 1 H 7 1 3O 3 O 3A23 E274 5 N P88614 2008033100053 20080331 00053 2008 3 31 2008FA0000116 4 20080118 G 6113 C2367 BULKHEAD SNSNCH MAULE MX7 MXT7180A 5460187 SO LYC O360 O360C4F 42290 EA SNSNCH 76E 76EM8 EA PROP SPINNER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 11 114HS 300 21092C L4051336A 37618K THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES. THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K) 1 H 7 1 3O 3 O NC 3A23 E286 5 N P4EA 2008033100054 20080331 00054 2008 3 31 2008FA0000117 4 20080118 G 6113 C2367 BULKHEAD SNSNCH MAULE MX7 MXT7180A 5460187 SO LYC O360 O360C4F 42290 EA SNSNCH 76E 76EM8 EA PROP SPINNER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 11 171HS 200 21096C L4089636A THE FWD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES. THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K) 1 H 7 1 3O 3 O NC 3A23 E286 5 N P4EA 2008033100056 20080331 00056 2008 3 31 2008FA0000118 4 20080118 G 6113 C2367 BULKHEAD MAULE MX7 MXT7180A 5460187 SO LYC O360 O360C4F 42290 EA SNSNCH 76E 76EM8S5 EA FWD SPINNER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 11 125HS 200 21093C L4056636A 37939K THE FWD BULKHEAD CRACKED THROUGHT THE MOUNT BOLT HOLES. THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K) 1 H 7 1 3O 3 O NC 3A23 E286 5 N P4EA 2008033100057 20080331 00057 2008 3 31 2008FA0000119 4 20080118 G 6113 C2367 BULKHEAD SNSNCH MAULE MX7 MXT7180A 5460187 SO LYC O360 O360C4F 42290 EA SNSNCH 76E 76EM8 EA PROP SPINNER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 11 152HS 200 21095C L4081336E 38281K THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES. THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K) 1 H 7 1 3O 3 O NC 3A23 E286 5 N P4EA 2008033100059 20080331 00059 GL 2008 3 31 2008FA0000120 1 20080206 G 3020 CONTROL ARM DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA CARB HEAT BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 07 423FP 13 40FC023 CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA KE. RECOMMEND INSTALLIING THICKER MATERIAL ON CARB HEAT CONTROL ARM LEVER, DIFFERENT WELDING/HEAT TREATING PROCESS, OR DIFFERENT ATTACHMENT PROVISION ALTOGETHER. (K) 1 L 7 1 3O 3 O NT A47CE E286 2008033100061 20080331 00061 GL 2008 3 31 2008FA0000121 1 20080206 G 3020 D4F732612001 CONTROL ARM DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA CARB HEAT BROKEN D GO3S K NONE O OTHER IN INSP/MAINT 1 NM 07 418FP 31 40FC018 CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA KE. RECOMMEND INSTALLING THICKER MATERIAL ON CARB HEAT CONTROL ARM LEVER, DIFFERENT WELDING/HEAT TREATING PROCESS, OR D IFFERENT ATTACHMENT PROVISION ALTOGETHER. (K) 1 L 7 1 3O 3 O NT A47CE E286 2008033100062 20080331 00062 CE 2008 3 31 2008FA0000122 1 20080206 G 2197 WIRE HARNESS BEECH 90 C90A 1152911 CE A/C START CONT MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 01 4764A LJ1161 AIR CONDITIONER NOT COOLING. FOUND WIRING FOR AC START CONTROL PANEL AS WELL AS COMPRESSOR CLUTCH NOT IN PROPER CONFIGU RATION IAW WIRING PRINT. AFTER PROPER INSTALLATION OF WIRING AND SUBSEQUENT OPS CHECK, THE MOTOR AND SYS, THE AIR CONDI TIONER WOULD CYCLE IN AND OUT OF ITS SOFT START CYCLE. THIS IN TURN CREATED EXCESSIVE HEAT IN THE LOAD RESISTOR CIRCUIT . THIS CYCLING CONTINUED UNTIL AT SOME POINT THE SOFT START CIRCUIT FAILED, WHICH CAUSED THE LOAD RESISTOR TO OVERHEAT AND MELT THE PHENOLIC BLOCK SHIELDS WHICH CAUGHT FIRE AND DAMAGED THE IMMEDIATE SURROUNDING STRUCTURE OF THE NOSE COMPA RTMENT. PROBABLE CAUSE WOULD INDICATE FAILURE OF THE AC START CONTROL PANEL CIRCUITRY THAT SUBSEQUENTLY LEAD TO A NOSE 1 L 7 2 3T RT 3A20 2008033100063 20080331 00063 2008 3 31 2008FA0000123 4 20080114 G 6113 05502366 BULKHEAD CESSNA 172 172H 2072424 CE CONT O300 O300* 17022 SO PROP SPINNER CRACKED D HE8S K NONE O OTHER IN INSP/MAINT 1 CE 09 4987R 92 17256341 PROP SPINNER FWD, BULKHEAD CRACKED NEAR MOUNT BOLTS. PART PROBABLY NOT STURDY. RECOMMEND PART BE MADE OF THICKER METAL DOUBLER INSTALLED. ALSO, IT APPEARED THAT MOUNT BOLT HOLES MAY BE TOO LARGE. (K) 1 H 7 1 3O 3 O NT 3A12 E253 2008032500068 20080325 00068 SW 2008 3 25 2008FA0000124 1 20080114 G 6220 NAS5161A GREASE FITTING BELDEN BELL 212 212 1181420 SW M/R HUB BLOCKED W DB5Y K NONE O OTHER IN INSP/MAINT 1 EA 33 DURING LUBRICATION OF A MAIN ROTOR HUB, WE DISCOVERED THAT THE SPRING IN THE GREASE FITTING (NAS516-1A) WAS PRESSED OUT FROM THE FITTING AND BLOCKED THE GREASE PASSAGE. THIS HAPPENED (3) TIMES. WE FOUND THE SPRINGS AFTER EVERY ATTEMPT. T HIS COULD RESULT IN A LOOSE SPRING IN A ROTATING BEARING. (K) 1 G 7 1 4U H4SW 2008032500105 20080325 00105 WP 2008 3 25 2008FA0000125 2 20080212 G 7210 8937396 GEAR CASA C212 C212CC 2410204 EU GARRTT TPE331 TPE33110R 0517 WP GEAR BOX BROKEN W X1NY K NONE O OTHER IN INSP/MAINT 1 WP 03 961BW 2170 P5372 248 ENGINE RECEIVED WITH BROKEN FEATHER VALVE, NOSE CONE NUTS LOOSE, ROTATION OF ENGINE ROTATING COMPONENTS FOUND CLUNKY AND SEIZED. MAGNETIC PLUG CONTAMINATED WITH FINE METAL PARTICLES. NOSE CONE AND DIAPHRAGM REMOVED TO INVESTIGATE CAUSE OF FAILURE. WHEN DIAPHRAGM ASSY WAS REMOVED BIG CHUNKS OF METAL NOTICED AT THE GEARBOX CAVITY IDENTIFIED AS BULL GEAR PIE CES. HIGH SPEED PINION GEAR HELICAL TEETH BROKEN OFF AND CRUNCHED. SEVERAL BULL GEAR TEETH BROKEN OFF. BIG PIECE (2- 3 INCH) OF GEAR RIM MISSING AND FOUND TRAPPED BETWEEN DIAPHRAGM HOUSING AND SCAVENGE PUMP CAUSING A RUPTURE OF THE PUMP HOUSING. THE PRELIMINARY REASON FOR THE GEAR BOX FAILURE IS BELIEVED TO BE CAUSE BY BULL GEAR FAILURE. THE SEPARATION 2 H 7 2 4T 4 T A43EU E4WE 2008032500106 20080325 00106 NE 2008 3 25 2008FA0000126 2 20080111 G 7250 1808M15G03 SUPPORT CFMINT AIRBUS 320 A320* EU CFMINT CFM56 CFM565B4P NE HPT NOZZLE UNSERVICEABLE W QEMY K NONE O OTHER IN INSP/MAINT 1 EA 35 51X79408 799408 DURING DISASSY OF THE CORE MAJOR MODULE, REMOVED FROM ESN 779408, REMOVAL OF THE COMBUSTION LINER MODULE EXPOSED THE FWD INNER NOZZLE SUPPORT (FINS). IT WAS NOTED THAT THE FINS HAD 1-OFF AREA OF LOCALIZED EROSION WHICH HAD RESULTED IN PENE TRATION OF THE COMPONENT. THE EROSION WAS LOCATED ON THE SUPPORT BODY SECTION OF THE COMPONENT, JUST AFT OF THE FWD (CL OCKWISE). THE CAUSE OF THE EROSION IS UNKNOWN. CIRCUMFERENTIAL EROSION TO THE SUPPORT BODY OF THE FINS IS COMMON BUT L OCALIZED EROSION, AS SEEN IN THIS INSTANCE HAS NOT BEEN SEEN, PREVIOUSLY. ALL AFFECTED PARTS ARE SCHEDULED FOR RETURN T O MFG FOR FAILURE ANALYSIS. (K) 2 L 7 2 4F 4 F RT A46NM E38NE 2008033100138 20080331 00138 EU 2008 3 31 2008FA0000127 1 20080206 G 2497 WIRE AMD FALC50 FALCON900 2730160 EU GARRTT TFE731 TFE731* 01518 WP ELECTRICAL DAMAGED B K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 NM 09 900VL 60 WHILE TROUBLESHOOTING AC ELECTRICAL OUTLETS FOR BEING INOPERATIVE. REMOVED FLOOR PANEL TO ACCESS AC INVERTER AND DETECT ED BURNING PLASTIC. FOUND SYSTEM HAD SELF RESETTING CIRCUIT BREAKERS INSTALLED THAT HAD BEEN AND WERE CONTINUING TO RES ET AND ALLOWING THE KAPTON WIRE INSULATION AND SPIRAL WRAP TO BURN. ONE OF THE AREAS THAT BURNED WAS ONLY 3 INCHES BELO W A CARBON FLIGHT CONTROL ROD. THIS HAPPENED ON A VERY LONG FLIGHT, THE OUTCOME COULD HAVE BEEN VERY TRAGIC. REPLACING THES C/B`S WITH NON SELF RESETTING CB WOULD PREVENT THE DAMAGE FROM PROGRESSING TO THE POINT IN WHICH IT DID IN THIS IN STANCE. (K) 2 L 7 3 4F 4 F RT A46EU E6WE 2008033100139 20080331 00139 GL 2008 3 31 2008FA0000128 1 20080215 G 2822 51000020 PUMP DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA FUEL SYS INOPERATIVE D GO3S K NONE O OTHER IN INSP/MAINT 1 NM 07 417FP 102 40FC017 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 2008033100142 20080331 00142 GL 2008 3 31 2008FA0000131 1 20080307 G 2822 51000020 PUMP DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA FUEL SYS INOPERATIVE D GO3S K NONE O OTHER IN INSP/MAINT 1 NM 07 418FP 40FC018 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 2008033100143 20080331 00143 GL 2008 3 31 2008FA0000132 1 20080227 G 2822 51000020 PUMP DIAMON DA40 DA40 2990002 GL LYC O360 O360A4M 41514 EA FUEL SYS INOPERATIVE D GO3S K NONE O OTHER IN INSP/MAINT 1 NM 07 419FP 265 40FC019 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 FOR PROPER COOLING OF FUEL PUMP A ND MOTOR. (K) 1 L 7 1 3O 3 O NT A47CE E286 2008040200040 20080402 00040 CE 2008 4 2 2008FA0000137 1 20080123 G 3250 358250549 ARM BEECH B300 B300B350C CE PWA PT6 PT6* 52043 EA STEERING WORN B K NONE O OTHER IN INSP/MAINT 1 EA 13 57SC 6028 FL34 NOSE GEAR STEERING ARM WORN EXCESSIVELY AT ROD END ATTACHMENT POINT FOR STEERING PUSH PULL TUBE. LOSS OF NOSE GEAR STEER ING WOULD OCCUR IF ARM WERE TO BREAK. THE ORIGINAL .2500 INCH BOLT HOLE WAS ELONGATED TO A .5 INCH SLOT. THE ARM IS ATTA CHED TO THE PILOT'S RUDDER PEDAL TORQUE SHAFT AND IS LOCATED IN A SMALL UNPRESSURIZED PANEL AREA BELOW THE PILOT SIDE FL OORBOARDS. INSPECTIONS ARE OVERLOOKED BECAUSE THIS SEALED PANEL IS NOT OPENED TYPICALLY DURING ROUTINE INSPECTIONS. 2 L 7 2 4T 3 T RT A24CE E2NE 2008040200013 20080402 00013 CE 2008 4 2 2008FA0000146 1 20080129 G 3220 07436051 TORQUE LINK CESSNA 182 182G 2072716 CE CONT O470 O470* 17026 SO ZONE 700 CRACKED C K NONE O OTHER IN INSP/MAINT 1 WP 05 82BG 2855 18255427 ON INSPECTION, A CRACK WAS IDENTIFIED IN THE FORGING FOR THE UPPER TORQUE LINK FOR THE NOSE LANDING GEAR. THE CRACK WAS ON BOTH SIDES OF THE BEAM SECTION ADJACENT TO THE EXTENSION STOP FOR THE GEAR.(AFT SIDE) 1 H 7 1 3O 3 O NT 3A13 E273 2008033100175 20080331 00175 EU 2008 3 31 2008FA0000148 1 20080327 G 6320 C632A2103101 HOUSING UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE GEARBOX WORN D K NONE O OTHER IN INSP/MAINT 1 SW 19 179CB 622 M569 1412 34224 INPUT BOX HOUSING BEARING WORN. (SHOULDER) 1 G 7 2 3U 3 U NC R0001RD E34NE 2008040100109 20080401 00109 EU 2008 4 1 2008FA0000149 1 20080227 G 2497 CONNECTOR DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE1250299 EU FUEL RAIL ARCED D O OTHER O OTHER NR NOT REPORTED 1 WP 28 4129M 480 42AC068 020201611 CONNECTOR IS NOT MAKING GOOD CONTACT AND CAUSING ARCING. PROBABLE CAUSE IS AUTOMOTIVE QUALITY AND NOT OF THE THREADED T YPE. TO PREVENT OCCURRENCE RECOMMEND USING AVIATION THREADED TYPE PLUG. (K) 1 L 7 2 3I 3 B RT A57CE E00069EN 2008040100111 20080401 00111 CE 2008 4 1 2008FA0000150 1 20080307 G 2497 S26062 WIRE HARNESS CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA MCAULY 1C235 1C235LFA GL FLAP MOTOR DETERIORATED D O OTHER O OTHER NR NOT REPORTED 1 CE 05 467CM 17280859 L2651551A TJ040 UPON INSPECTION OF A PHASE II INSPECTION, IT WAS DISCOVERED THAT THE WIRE BUNDLE MOUNT PN S26062 THAT HOLDS THE FLAP MOT OR WIRE HARNESS HAD DETACHED FROM THE RIB IN THE RT WING AND HAD ALLOWED THE WIRE BUNDLE TO CHAF INTO THE INSPECTION PAN EL SUPPORT ON THE WING. THE WIRE BUNDLE HAD (2) WIRES CHAFED THROUGH THE INSULATION AND WAS IN CONTACT WITH THE BARE WI RE. RECOMMEND INSPECTION OF THESE MOUNTS AND REPLACE AS NEEDED, OR ON CONDITION. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P12EA 2008040100121 20080401 00121 EA 2008 4 1 2008FA0000151 2 20080305 G 8520 13B2713485 CRANKSHAFT LYC O360 O360A4A 41514 EA ENGINE CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 17 CRANKSHAFT HAS VERY LARGE RADIAL CRACKS AT THE BASE OF THE FORWARD THRUST FACE, EXTENDING APPROX. 85% OF THE WAY AROUND THE SHAFT. APPEARS TO HAVE BEEN A FRONTAL IMPACT ON THE CRANKSHAFT DRIVING IT REWARD IN THE ENGINE AND IMPACTING THE CRA NKCASE. 3 O E286 2008040400001 20080404 00001 2008 4 4 2008FA0000152 1 20080304 G 4990 38809981 PUMP APU OIL FAILED B O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 99 13599 1468 2 APUS WERE REPORTED LOP AUTO SHUTDOWN. HAVE RECEIVED APU P-195 AND P-141 FROM FOR THE SAME REASON OF REMOVAL. DISASSEMB LY OF THE ENGINES REVEALED LP ROLLER BEARING FAILURE. ONE OF THE ENGINE'S BEARING DID NOT HAVE LUBRICATION AT ALL. THE OIL PUMPS P/N 3880998-1 WERE ROUTED TO BENCH TEST AND LOW PERFORMANCE WAS NOTED. DISASSEMBLY OF THE OIL PUMP REVEALED PO RT PLATE P/N 3603681-1 HAD SIGNIFICANTLY WORN. IT ALLOWED THE PORT PLATE MOVE TO RESTRICT THE OIL INLET PORT AND OUTLET PORT AND CAUSED LOW PUMP PERFORMANCE. THE BEARING FAILURE WAS A CONSEQUENCE OF INSUFFICIENT OIL PRESSURE. 2008040200043 20080402 00043 CE 2008 4 2 2008FA0000153 1 20080212 G 2810 CHAIN CESSNA 172 172S 2072439 CE CONT C85 C8512F 17008 SO FUEL CAP LOOSE D O OTHER O OTHER TX TAXI/GRND HDL 1 GL 15 5055Q 4413 8972 LT FUEL GAUGE INDICATED 10 GAL. IN TANK AT ALL FUEL LEVELS. THE TANK WAS DRAINED AND ACCESS COVER REMOVED. THE FUEL CAP RETAINING CHAIN WAS FOUND TO HAVE COME LOOSE ON THE TANK END (S) HOOK AND WRAPPED AROUND THE ARM ON THE FUEL LEVEL SENDI NG UNIT LOCKING IT AT A 10 GAL. INDICATION. 1 H 7 1 3O 3 O NT 3A12 E233 2008040300025 20080403 00025 CE 2008 4 3 2008FA0000154 1 20080215 G 5511 45A2111XXXX RIB BEECH MU300 400A 1155402 CE HORIZONTAL STAB CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 13 907JE 5335 RK107 FOUND SEVERAL CRACKS (25) IN RIB TO LOWER SKIN ATTACH FLANGES, AT RIVET HOLES , IN 3 LT, AND 4 RT HORIZONTAL STABILIZER INNER SPAR RIBS. RIBS NR 234 ON LT SIDE, AND NR 2345 ON RT SIDE. AFFECTED. 2 H 7 2 4F RT A16SW 2008040300026 20080403 00026 CE 2008 4 3 2008FA0000155 1 20080215 G 5511 45A2111XXXX RIB BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE HORIZONTAL STAB CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 13 907JE 5335 RK107 FOUND SEVERAL CRACKS (25) IN RIB TO LOWER SKIN ATTACH FLANGES, AT RIVET HOLES , IN 3 LT , AND 4 RT HORIZONTAL STABILIZE R INNER SPAR RIBS. RIBS NR 234 ON LT SIDE, AND NR 2345 ON RT SIDE AFFECTED. 2 H 7 2 4F 4 F RT A16SW E25EA 2008040300046 20080403 00046 2008 4 3 2008FA0000156 4 20080222 G 2564 5A320410312 LIFE RAFT AMD FALC50 FALCON50MYST 2730106 EU GARRTT TFE731 TFE731* 01518 WP CABIN INOPERATIVE B K NONE O OTHER IN INSP/MAINT 1 NM 01 900KE 1 052 RECEIVED SUBJECT LIFE RAFT FOR ANNUAL INSPECTION FROM REGISTERED OWNER. THE LIFE RAFT WAS RECEIVED BY THIS REPAIR STATIO N IN A PACKED CONDITION AND IN ITS "AS-REMOVED" CONDITION FROM THE AIRCRAFT. DURING DISASSEMBLY AND PRELIMINARY INSPECT ION OF SUBJECT LIFE RAFT, FOUND A STEEL SAFETY PIN INSTALLED IN THE LIFE RAFT INFLATION BOTTLE. THE LIFE RAFT WOULD NOT HAVE BEEN OPERABLE WITH THIS SAFETY PIN INSTALLED HAD THIS LIFE RAFT BEEN CALLED UPON TO FUNCTION IN AN ACTUAL EMERGENCY . 2 L 7 3 4F 4 F A46EU E6WE 2008040300048 20080403 00048 2008 4 3 2008FA0000157 4 20080108 G 2210 238006679 YAW DAMPER LEAR 24 24 5170302 CE ZONE 300 FAULTY B A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 01 989TL 160 THIS PART FAILED TO OPERATE DURING FIRST FLIGHT AFTER INSTALLATION AT CRUISE. 2 L 7 2 4J A10CE 2008040300049 20080403 00049 SO 2008 4 3 2008FA0000160 1 20080225 G 3245 0923150 TUBE PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA LT TIRE CUT B O OTHER E VIBRATION/BUFFET LD LANDING 1 GL 21 359ND 118 2842187 UPON LANDING, LT MAIN TIRE DEFLATED UPON DISASSEMBLY TUBE WAS FOUND TO HAVE A SMALL SLIT IN THE OUTSIDE OF THE CIRCUMFER ENCE OF THE TUBE. THIS SLIT HAS BEEN FOUND ON NUMEROUS TUBE FAILURES FOUND BY THIS REPAIR STATION. DISCUSSION WITH TUBE MFG HAVE BEEN FRUITLESS AS THEY FEEL IT IS A FOLD INDUCED DURING INFLATION BUT THEIR INSTALLATION PROCEDURES HAVE BEEN F OLLOWED TO THE LETTER AND PROBLEM STILL EXIST DURING EXTREME TEMP CHANGES EXPERIENCED IN OUR CLIMATE (NORTH DAKOTA). 1 L 7 1 3O 3 O 2A13 E274 2008040300051 20080403 00051 SO 2008 4 3 2008FA0000161 1 20080225 G 3245 0923150 TUBE PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA LT TIRE CUT B O OTHER E VIBRATION/BUFFET LD LANDING 1 GL 21 359ND 118 2842187 UPON LANDING, LT MAIN TIRE DEFLATED. UPON DISASSEMBLY, TUBE WAS FOUND TO HAVE A SMALL SLIT IN THE OUTSIDE OF THE CIRCU MFERENCE OF THE TUBE. THIS SLIT HAS BEEN FOUND ON NUMEROUS TUBE FAILURES FOUND BY THIS REPAIR STATION. DISCUSSION WITH TUBE MFG HAVE BEEN FRUITLESS AS THEY FEEL IT IS A FOLD INDUCED DURING INFLATION BUT THEIR INSTALLATION PROCEDURES HAVE B EEN FOLLOWED TO THE LETTER AND PROBLEM STILL EXIST DURING EXTREME TEMP CHANGES EXPERIENCED IN OUR CLIMATE (NORTH DAKOTA) . 1 L 7 1 3O 3 O 2A13 E274 2008040300052 20080403 00052 EA 2008 4 3 2008FA0000164 2 20080110 G 7414 6393 MAGNETO GULSTM 500 500S 0141107 SW 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 100 3298 ENGINE WAS GETTING HARD TO START, CHECKED MAG TIMING AND FOUND LT MAG TIMING OUT OF LIMITS, DISASSEMBLED MAG AND FOUND T HE CAM WORN OUT . 100.3 HRS SINCE NEW 1 H 7 2 3O 3 O 6A1 1E4 2008040300054 20080403 00054 EA 2008 4 3 2008FA0000167 2 20080226 G 7414 6393 MAGNETO GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA ENGINE WORN B O OTHER R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 GL 15 51RF 81 3298 ENGINE WAS GETTING HARD TO START, CHECKED MAG TIMING AND FOUND LT MAG TIMING OUT OF LIMITS, DISASSEMBLED MAG AND FOUND T HE CAM WORN OUT . 81.1 HRS SINCE NEW. 1 H 7 2 3O 3 O 6A1 1E4 2008040300056 20080403 00056 SO 2008 4 3 2008FA0000168 1 20080226 G 3245 0923080 TUBE PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA TIRE FAILED B O OTHER O OTHER TX TAXI/GRND HDL 1 GL 21 437ND 28 2842214 NOSE TIRE FOUND FLAT IN HANGER. DISASSEMBLE FOUND SMALL SLIT IN OUTSIDE CIRCUMFERENCE OF TUBE TYPICAL OF OTHER FLAT TIRE S FROM SAME MFG. SAMPLE FAILED TUBES HAVE BEEN RETURNED TO MFG FOR EVALUATION. 1 L 7 1 3O 3 O 2A13 E274 2008040300061 20080403 00061 CE 2008 4 3 2008FA0000169 1 20080220 G 2820 057313K001301 LINE CESSNA 172 172S 2072439 CE THIELT TAE125 TAE1250299 EU FUEL SYSTEM CRACKED C B A EMER. DESCENT UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 SO 19 1735L 3 172S10647 020201880 PILOT WAS FLYING AT 5,500 FEET WHEN THE ENGINE STARTED RUNNING ROUGH. WITHIN MOMENTS THE FADEC (A) LIGHT CAME ON THEN FA DEC (B) ILLUMINATED. THE PILOT TRIED TO ACTIVATE THE MANUAL OVERRIDE BUT WAS UNABLE TO PUT OUT THE WARNING LIGHTS. THE R PMS DROPPED UNTIL ENGINE STOPPED, THEN THE PROP STOPPED. THE PILOT DID A GREAT JOB AND FOUND A SAFE ROAD TO LAND ON, AND COMMUNICATED WITH ATC THAT HE PLANNED TO MAKE AN EMERGENCY LANDING. WHEN THE PILOT LANDED HE ADVISED ATC THAT HE WAS SA FE AND DID NOT REQUIRE ANY SERVICES (FIRE, PARAMEDICS). ATC NOTIFIED THE LOCAL SHERIFF’S DEPARTMENT AND A DEPUTY WAS SEN T OUT TO CONFIRM. THE PILOT MOVED THE AC FROM THE ROADWAY TO AVOID DAMAGE OR ANY INCIDENT WITH TRAFFIC. UPON REACHING TH 1 H 7 1 3O 3 B NT 3A12 E00069EN 2008040300062 20080403 00062 SO 2008 4 3 2008FA0000173 1 20080228 G 3245 0923080 TUBE PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA TIRE FLAT B O OTHER O OTHER LD LANDING 1 GL 21 350ND 70 2842179 ON LANDING, RT MAIN LANDING GEAR TIRE FLAT. UPON DISASSEMBLY FOUND A SMALL SLIT IN THE OUTSIDE CIRCUMFERENCE OF THE TUB E. HAVE FOUND MANY SIMILAR SLITS IN OTHER FAILED TUBES FROM MFG. 1 L 7 1 3O 3 O 2A13 E274 2008040300064 20080403 00064 2008 4 3 2008FA0000177 1 20080229 G 6100 5038004811 RELAY PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL BURNED B K NONE O OTHER IN INSP/MAINT 1 GL 15 964LB UPON LANDING A POWER/ TORQUE SURGE OF THE LT ENGINE WAS ENCOUNTERED. THE INCREASED THRUST FROM THE LT SIDE AND ICE COVE RED RUNWAY CONDITIONS CAUSED AN OFF RUNWAY INCURSION. INVESTIGATION OF THE GROUND FINE SOLENOID SYSTEM RESULTED IN A BU RNED K4 RELAY ON THE AFFECTED PC CARD CONTROLLING THE GROUND FINE SYSTEM ON THE LT SIDE. 4 T E4EA 6 C P56GL 2008040300065 20080403 00065 NM 2008 4 3 2008FA0000179 1 20080229 G 5712 RIB UNIVAR 415 415E 0420308 NM CONT C85 C85* 17008 SO RT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 05 87346 519 COMPLIANCE WITH AD 2002-26-02 DETECT AND CORRECT CORROSION IN WING CENTER SECTION. FOUND 5 RIVETS CORRODED OFF THE LOWE R CENTER RIB ON THE RT WING WALKWAY BOX. 1 L 7 1 3O 3 O A787 E233 2008040300089 20080403 00089 CE 2008 4 3 2008FA0000180 1 20080229 G 3232 65412045 STUD CESSNA 501 501 2076603 CE LT MLG ACTUATOR BROKEN D K NONE O OTHER UK UNKNOWN 1 SO 09 793AA 5010106 LT MLG ACTUATOR TO GEAR STUD BROKEN OFF AT BASE OF THE NUT ON THE TAPER SIDE, NUT AND WASHER SET MISSING AND STUD WAS NO T TIGHT IN THE GEAR. 1 L 7 2 4F A27CE 2008040300091 20080403 00091 SO 2008 4 3 2008FA0000181 2 20080304 G 8530 AEC633099 PISTON BEECH 35 B35 1151506 CE CONT E225 E2258 17015 SO ENGINE FAILED G A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 CE 07 D3633 03593D58 NR 6 PISTON DISINTEGRATED. CAUSE UNKNOWN. PISTON P/N AEC633099 WAS ORIGINALLY MANUFACTURED BY AIRMOTIVE ENGINEERING, I NC.(AEC). ENGINE COMPONENTS, INC. (ECI) HAS SINCE BOUGHT OUT AEC. ECI HAS NOT PRODUCED THIS P/N. 1 L 7 1 3O 3 O A777 E267 2008040300096 20080403 00096 NE 2008 4 3 2008FA0000183 2 20080304 G 7250 304997801 TURBINE BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE ENGINE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 19 185XP 4837 1771 BB952 93220 DURING PERFORMANCE OF A SCHEDULED 1800 HOUR HOT SECTION INSPECTION OF THE RT ENGINE, AT 1771 HOURS AND 7 YEARS TIME IN S ERVICE SINCE OVERHAUL, INITIAL VISUAL INSPECTION OF THE CT BLADES TIP CLEARANCE REVEALED CLEARANCES IN EXCESS OF ALLOWAB LE FOR RETURN TO SERVICE. IT WAS NOTED THAT THERE WAS SOME METAL BUILD-UP ON THE SHROUD SEGMENTS IN THE 4 O'CLOCK THRU 6 O'CLOCK POSITIONS. NO IMPACT DAMAGE WAS NOTED TO ANY OF THE CT BLADES OR THE CT NOZZLE. SEVERAL CRACKS WERE ALSO NOT ED IN THE OUTER SECTION OF THE COMBUSTION LINER. AFFECTED COMPONENTS WILL BE SENT TO A P&WC APPROVED REPAIR FACILITY FO R REPAIRS OR REPLACEMENT AS NECESSARY. 1 L 7 2 4T 4 T A24CE E4EA 2008041400002 20080414 00002 NE 2008 4 14 2008FA0000184 2 20080304 G 7230 304997801 COMPRESSOR BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE RT ENGINE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 19 185XP 4837 1771 BB952 93220 DURING PERFORMANCE OF A SCHEDULED 1800 HOUR HOT SECTION INSPECTION OF THE RT ENGINE, AT 1771 HOURS AND 7 YEARS TIS SINCE OVERHAUL, INITIAL VISUAL INSPECTION OF THE CT BLADES TIP CLEARANCE REVEALED CLEARANCES IN EXCESS OF ALLOWABLE FOR RETUR N TO SERVICE. IT WAS NOTED THAT THERE WAS SOME METAL BUILD-UP ON THE SHROUD SEGMENTS IN THE 4 O'CLOCK THRU 6 O'CLOCK PO SITIONS. NO IMPACT DAMAGE WAS NOTED TO ANY OF THE CT BLADES OR THE CT NOZZLE. SEVERAL CRACKS WERE ALSO NOTED IN THE OU TER SECTION OF THE COMBUSTION LINER. AFFECTED COMPONENTS WILL BE SENT TO A MFG APPROVED REPAIR FACILITY FOR REPAIRS OR REPLACEMENT AS NECESSARY. 1 L 7 2 4T 4 T A24CE E4EA 2008040300098 20080403 00098 CE 2008 4 3 2008FA0000186 1 20080306 G 7120 051351119 MOUNT BRACKET CESSNA 172 R172K 2072431 CE LT ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 15 758PX R1723262 FOUND UPPER LT ENGINE MOUNT BRACKET CRACKED WHILE INSPECTING FOR CESSNA SEB07-2 REV 2. THIS SERVICE BULLETIN DOES NOT A PPLY TO THIS SERIAL NUMBER, ALTHOUGH A CRACK WAS FOUND. RECOMMEND INCREASING THE SERIAL NUMBER RANGE OF AFFECTED AIRCRA FT. THIS SHOP HAS ALSO NOTED SEAPLANES HAVE A DIFFERENT LOWER MOUNT BRACKET THAN THAT WHICH IS CALLED OUT IN THE SERVIC E BULLETIN. RECOMMEND INCLUDING THE PROPER SEAPLANE MOUNT BRACKET NUMBERS FOR AIRCRAFT SO EQUIPPED. 1 H 7 1 3O 3A17 2008041000203 20080410 00203 SO 2008 4 10 2008FA0000187 1 20080402 G 8097 767391 SOLENOID PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA STARTER SHORTED B K NONE O OTHER IN INSP/MAINT 1 GL 21 350ND 2842179 DURING PRE-FLIGHT WHEN MASTER SWITCH WAS TURNED ON, THE PROP BEGAN TO ROTATE UNCOMMANDED. TROUBLESHOT TO FUSED STARTER S OLENOID. THIS IS THE SECOND SOLENOID FAILURE OF THIS TYPE IN ONE WEEK TIME, SAME MODEL AIRCRAFT. REPLACED WITH NEW PART, OPS CHECKED GOOD. 1 L 7 1 3O 3 O 2A13 E274 2008040400006 20080404 00006 CE 2008 4 4 2008FA0000188 1 20080310 G 3233 2000300003 ACTUATOR LEAR 45 45LEAR 5170805 CE PWA JT12 JT12A8 52042 NE LT MLG BYPASSING D O OTHER S AFFECT SYSTEMS CL CLIMB 1 CE 09 828CA 3137 159 LT MLG ACTUATOR BYPASSING ON RETRACTION CAUSING INTERFERENCE WITH IB DOOR ROLLERS. NO EXTERNAL FAILURE INDICATION. UPON TEARDOWN, IT WAS DISCOVERED THAT THE CYLINDER WAS SCRATCHED AND THE PISTON SEAL WAS DAMAGED. 2 L 7 2 4F 4 J RT T00008WI 1E9 2008041000231 20080410 00231 EA 2008 4 10 2008FA0000190 2 20080313 G 7322 NUT PREAIR PIPER PA28 PA28R201 7102816 SO LYC O360 IO360A1A 41514 EA FUEL SERVO LOOSE C K NONE O OTHER IN INSP/MAINT 1 WP 13 283PA 263 62760 2844059 AD 2008-06-51 IS NOT APPLICABLE DUE TO THE ENGINE AND FUEL SERVO WERE OVERHAULED BY MFG ON MARCH 03, 2006 (OUTSIDE THE D ATE RANGE OF THIS AD). HOWEVER, WE DECIDED TO CHECK ALL OF OUR AIRCRAFT AND DURING THIS INSPECTION FOUND THE HEX NUT WA S LOOSE ON THIS PARTICULAR SERVO. 1 L 7 1 3O 3 O 2A13 1E10 2008041000235 20080410 00235 EA 2008 4 10 2008FA0000191 2 20080331 G 7322 30802 FLOAT PREAIR MA45 MAULE M7235 M7235C 5460110 SO LYC O540 O540B4B5 41532 EA CARBURETOR BENT D K NONE O OTHER IN INSP/MAINT 1 NM 01 249RD 439 75103715 25069C L2571940A CARBURETOR FLOAT PN 30-802 PLASTIC FLOAT, THE CARBURETOR HAD A HIGH FLOAT LEVEL TWICE AFTER SETTING THE FLOAT TO SPEC IA W MM. THE FLOAT WAS REMOVED DUE TO THE FLOAT LEVER TANG WAS BENDING UNDER NORMAL USE CONTACTING THE NEEDLE VALVE AND RES ULTING IN A HIGH FLOAT LEVEL AND ROUGH RUNNING ENGINE. IT WAS NOTICED THAT THE FLOAT LEVER TANG ON THE PLASTIC FLOAT PN 30-802 MADE OF STAINLESS STEEL IS ABOUT .5 THE THICKNESS THAT OF THE BRASS FLOAT PN 30-764 WHICH HAS HAD NO PROBLEMS WIT H THE LEVER TANG BENDING IN NORMAL USE. A PN 30-764 FLOAT WAS INSTALLED AND ENGINE WAS NORMAL, NO ROUGHNESS NOTED. PLEA SE LOOK IN TO THIS PROBLEM SO AS NO ONE HAS A ROUGH AND RICH RUNNING ENGINE DUE TO THIS PROBLEM AND POSSIBLE EARLIER THA 1 H 7 1 3O 3 O NC 3A23 E295 2008041000241 20080410 00241 SO 2008 4 10 2008FA0000192 1 20080218 G 3230 9582900 LINK ASSY PIPER PA34 PA34200 7103405 SO LYC O360 IO360A1A 41514 EA NLG SHEARED G O OTHER O OTHER LD LANDING 1 EA 17 1031U 347250012 ACFT EXPERIENCED A NLG COLLAPSE UPON LANDING. INSPECTION OF ACFT, NLG DOWNLOCK LINK ASSY FOUND SHEARED NEAR ATTACHMENT TO DOWNLOCK ASSY BODY. IT IS NOT KNOW WHAT CAUSED THIS LINK ASSY TO SHEAR. DETERMINED THAT NOT ALL THE REQUIREMENTS OF AD 2005-13-16 WERE ACCOMPLISHED DURING THE LAST ANNUAL, AND IT IS POSSIBLE THIS COULD HAVE BEEN A CONTRIBUTING FACTOR. NUMEROUS COMPONENTS OF THE NLG REQUIRE MX ACTIONS & REPETITIVE INSPECTIONS. FRACTURE MODE OF SHEARED ASSY COULDN`T DET ERMINE IF PART FAILED INSTANTANTLY OR PROGRESSIVELY, SIGNATURE SUGGESTS A FATIGUE FRACTURE MAY HAVE BEEN PRESENT. AD2005 -13-16 ADDRESSES CONCERNS THAT HAVE RESULTED FROM SDR`S RELATED TO THE COLLAPSE OR INVOLUNTARY RETRACTION OF THE NLG ON 1 L 7 2 3O 3 O A7SO 1E10 2008041000244 20080410 00244 SO 2008 4 10 2008FA0000193 1 20080321 G 5720 902010XXX SUPPORT BRACKET GRUMAV AMRGEN AA5 AA5A 3960106 SO ZONE 600 CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 15 2850 100 SERIES WHILE COMPLYING WITH AD 79-22-04 ON AILERON CONTROL SYS INSP AND SB 165A, 100 HOUR REPETITIVE INSP, FOUND LT OB AILERON HINGE SUPPORT BRACKET, 902010-501 CRACKED. CRACKED VISUALLY SEEN WITH OUT DISASSEMBLY USING A STRONG LIGHT AND SYSTEM LO ADING. HOWEVER, WHEN REMOVED FOR REPLACEMENT WITH NEW SUPPORT, THERE WERE 3 ADDITIONAL CRACKS GIVING A TOTAL OF (4) ON THIS COMPONENT, PAINT AND LOCATION OF CRACKS PRACTICALLY IMPOSSIBLE TO DISTINGUISH WITH COMPONENT INSTALLED. 1 L 7 1 3O A16EA 2008040400010 20080404 00010 NM 2008 4 4 2008FA0000194 1 20080319 G 8120 PIPE COLUMB LC40 LC40550FG300 5150010 NM CONT O550 TSIO550C SO TURBOCHARGER CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 21 1024Z 438 1CF730011 41097 802744 RT TURBO TRANSITION PIPE CRACKED. THIS IS THE THIRD ONE INTO OUR SHOP. 1 L 7 1 3O 3 O NT A00003SE E5SO 2008040400004 20080404 00004 EA 2008 4 4 2008FA0000195 2 20080229 G 7320 25244509 FUEL CONTROL PIPER PA28 PA28R201 7102816 SO LYC O360 IO360C1C6 41514 EA ENGINE LOOSE C D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 GL 11 540PU 2900 695 2844096 L3103051A RAN ENGINE AFTER INSPECTION AND FOUND FUEL FLOW AT TO POWER SETTING TO BE QUITE LOW. INVESTIGATED AND FOUND PLUG LOOSE ON SIDE OF INJECTION SERVO. CONTACTED ENGINE SHOP FOR FIX. 1 L 7 1 3O 3 O 2A13 1E10 2008041400012 20080414 00012 EA 2008 4 14 2008FA0000197 2 20080321 G 8530 CYLINDER PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YR2 GL NR 3 SEPARATED C E ENGINE SHUTDOWN O OTHER NR NOT REPORTED 1 EA 21 126 277554157 RL77048 HCE2YR2KBS NR 3 CYLINDER SEPARATED FROM ENGINE CASE. 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2008041400008 20080414 00008 SO 2008 4 14 2008FA0000198 2 20080318 G 8530 SA530348P15 PISTON CESSNA 150 150D 2071810 CE CONT O200 O200A 17020 SO NR 3 CYLINDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 01 6029T 885 15060729 REMOVAL OF NR 3 CYLINDER FOR REPLACEMENT REVEALED A 1.5 INCH CRACK IN THE UPPER PISTON SKIRT STARTING FROM THE BOTTOM OF THE PISTON. 885 HOURS SINCE NEW. 1 H 7 1 3O 3 O 3A19 E252 2008041400006 20080414 00006 SO 2008 4 14 2008FA0000199 2 20080318 G 8500 CASE CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO RT ENGINE CRACKED B E ENGINE SHUTDOWN E VIBRATION/BUFFET NR NOT REPORTED 1 WP 09 12RJ 1748 937 421C0306 292115R REMOVED THIS ENGINE FROM THE RT POSITION FOR SHIPMENT BACK TO RAM AC DUE TO A DAMAGED CASE. DAMAGE APPEARS TO BE CAUSED BY A FAILED CONNECTING ROD THAT BROKE APART AND PUNCTURED (2) LARGE HOLES IN THE CRANKCASE. BRIEF ENGINE HISTORY: 347 HOURS PRIOR TO THE FAILURE THE ENGINE DEVELOPED AN OIL LEAK FROM A HAIRLINE CRACK IN THE RT CASE. THE ENGINE WAS SHIPPED TO RAM WHERE IT WAS DISASSEMBLED, CLEANED AND INSPECTED BEFORE GETTING REASSEMBLED USING A SERVICEABLE CRANKCASE, NEW C AMSHAFT, LIFTERS, MAIN AND ROD BEARINGS. 1 L 7 2 3O 3 O A7CE E7CE 2008041400009 20080414 00009 SO 2008 4 14 2008FA0000200 2 20080318 G 8530 CYLINDER CESSNA 150 150D 2071810 CE CONT O200 O200A 17020 SO NR 1 CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 01 6029T 885 15060729 MUFFLER PRESSURE TEST REVEALED CRACKS IN NR 1 CYLINDER EXHAUST PORT, FWD SIDE. UNKNOWN CYLINDER TIME, WAS BORED .015 INC H OVERSIZE. 1 H 7 1 3O 3 O 3A19 E252 2008041400007 20080414 00007 CE 2008 4 14 2008FA0000201 1 20080318 G 7820 FLAME TUBE CESSNA CESSNA 150 150D 2071810 CE CONT O200 O200A 17020 SO MUFFLER RUPTURED D K NONE O OTHER IN INSP/MAINT 1 CE 01 6029T 3900 15060729 RT MUFFLER P/N 0450400-26 WAS REMOVED FOR CYLINDER REPLACEMENT, INSP REVEALED DETERIORATED FLAME TUBES IN OUTLET PIPE AN D NR1 INLET PIPE. OUTLET PIPE FLAME TUBE IS NOT READILY VISIBLE LOOKING UP TAIL PIPE. NO ENTRIES IN LOGBOOK INDICATING R EPLACEMENT OF EITHER MUFFLER. 1 H 7 1 3O 3 O 3A19 E252 2008041400018 20080414 00018 CE 2008 4 14 2008FA0000202 1 20080328 G 7120 MOUNT CESSNA 172 172D 2072410 CE ENGINE WRONG PART C K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 21 AN UNKNOWN AMOUNT OF AC FIREWALL ATTACH ASSEMBLIES (ENGINE MOUNTS) THAT WERE NOT FAA-PMA APPROVED. THE MIDO ATTEMPTED TO CONTACT THE OWNER OF MFG CONCERNING THIS MATTER, HOWEVER, ALL PHONE CALLS WERE NOT RETURNED, AND CERTIFIED LETTERS NOT ACCEPTED. AS OF THIS TIME, THE COMPANY HAS CLOSED DOORS, HOWEVER, A FIREWALL ASSEMBLY WAS FOUND ON AC. THE OWNER OF THE AIRCRAFT WAS ADVISED THAT THE PART WAS NOT APPROVED AND IT HAD TO BE REMOVED. THE MIDO WAS INFORMED OF THE UNAPPROVED MO UNT. THE MOUNT DOES NOT HAVE A PART NUMBER. THE MIDO WILL CONTACT THE FAA SUP OFFICE TO PUT OUT A NOTICE. RECOMMEND THAT INFORMATION BE DISSEMINATED TO THE AC MFG COMMUNITY TO ADVISE OWNERS, PILOTS, AND MECHANICS IF THEY HAVE ANY OF THESE M 1 H 7 1 3O NT 3A12 2008040800001 20080408 00001 SW 2008 4 8 2008FA0000203 1 20080320 G 8011 14912LS STARTER MOONEY M20 M20F 5870214 SW LYC O360 IO360A1A 41514 EA HARTZL HCC2Y HCC2YK1 GL ENGINE FAILED D O OTHER O OTHER NR NOT REPORTED 1 SW 05 9615M 62 670192 L189451 CH388859B THIS STARTER WAS PURCHASED NEW FROM A LOCAL VENDOR. THE STARTER FAILED TO OPERATE AFTER LESS THAN A YEAR AND LESS THAN 100 HOURS OF SERVICE. THE OWNER\OPERATOR WANTED TO HAVE THE OLDER, HEAVIER STARTER INSTALLED HOWEVER NONE WERE AVAILABLE , AFTER CONTACTING SEVERAL PARTS VENDORS. THE OPERATOR OPTED TO HAVE THE STARTER REPAIRED BY THE MFG. THE REPAIRED START ER WAS INSTALLED BUT FAILED AGAIN SEVEN MONTHS AND 62.3 OPERATING HOURS LATER. A SERVICABLE STARTER WAS LOCATED AND INST ALLED IAW ENGINE SERVICE INSTRUCTION 1154L DATED JANARY 27, 2006. OUR SHOP RECOMMENDED THIS CHANGE DUE TO A TREND WE AR E SEEING IN THE LIGHT WEIGHT STARTERS. WE HAVE SEEN AT LEAST 6 FAILURES OR THE STARTER DRIVE GEAR EITHER FAILING TO ENGA 1 L 7 1 3O 3 O 2A3 1E10 5 C P920 2008041400010 20080414 00010 NM 2008 4 14 2008FA0000206 1 20080319 G 8120 654327E TURBOCHARGER COLUMB LC40 LC40550FG300 5150010 NM CONT O550 TSIO550C SO RIGHT CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 21 438 41097 802744 RT TURBO TRANSITION PIPE CRACKED. THIS IS THE THIRD ONE INTO OUR SHOP. 1 L 7 1 3O 3 O NT A00003SE E5SO 2008041400019 20080414 00019 SO 2008 4 14 2008FA0000208 1 20080328 G 2910 1159SCH2393 SHUTOFF VALVE GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6108 NE HYD SYSTEM SEIZED C O OTHER J WARNING INDICATION CR CRUISE 1 GL 23 312EL 7509 1105 WHILE AT CRUISE ALTITUDE, THE COMBINE HYDRAULIC SHUTOFF VALVE FAILED TOWARD CLOSED POSITION WHICH IS INDICATED IN THE CO CKPIT ON THE EICAS WITH DASHED LINES (VALVE IN TRANSITION) THUS TAKING AWAY YOUR HYDRAULIC PRESSURE INDICATION. WHEN TH E VALVE IS FULLY CLOSED THE INDICATION ON THE EICAS IS DIAGONAL SOLID LINES. THE ONLY WAY TO GET THIS VALVE TO MOVE CLO SED IS WITH THE FIRE L HANDLE. 2 L 7 2 4F 4 F RT A12EA E25NE 2008041400036 20080414 00036 EA 2008 4 14 2008FA0000209 2 20080401 G 7414 M11522 BREAKER POINTS SLICK 6393 PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA MAGNETO WORN E K NONE O OTHER TX TAXI/GRND HDL 1 EA 17 62BA 87 0700226 274859 L1947848A ENGINE BECAME INCREASINGLY DIFFICULT TO START, CHECKED IGNITION TIMING AND FOUND LT MAGNETO OUT OF TOLERANCE. INSPECTED LT MAGNETO, POINTS FAILED TO OPEN DUE TO EXCESSIVLY WORN BREAKER POINT CAM. 87 HOURS SINCE NEW 1 L 7 2 3O 3 O 1A10 1E4 2008041400013 20080414 00013 SO 2008 4 14 2008FA0000210 1 20080325 G 8011 701122223 SOLENOID PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA STARTER STICKS B H DEACTIVATE SYST/CIRCUITS O OTHER TX TAXI/GRND HDL 1 GL 21 245ND 2842086 WHEN BATTERY MASTER TURNED ON PROP BEGAN ROTATING UNCOMMANDED. TROUBLESHOT TO FUSED STATER SOLENOID. REPLACED SOLENOID W ITH NEW OEM PART PROBLEM PERSISTED. NEW SOLENOID WAS STRUCK WITH A SIDE BLOW AND CONTACTS FREED. REPLACED WITH ANOTHER NEW OEM PART, PROBLEM CORRECTED. 1 L 7 1 3O 3 O 2A13 E274 2008041400004 20080414 00004 SO 2008 4 14 2008FA0000211 2 20080312 G 8500 654327E DUCT LANCAR LC41 LC41550FG 5150001 NM CONT O550 TSIO550A 41516 SO ENGINE CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 21 154 41722 914564 RT TURBO TRANSITION DUCT CRACKED. (NOTE: THIS IS THE SECOND TIME WE HAVE SEEN THIS) 1 L 7 1 3O 3 O NT A00003SE E5SO 2008041400011 20080414 00011 EA 2008 4 14 2008FA0000212 2 20080319 G 7322 383493 GASKET PREAIR CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA FUEL SERVO UNKNOWN D K NONE P NO WARNING INDICATION IN INSP/MAINT 1 NM 01 2446X 70A59005 20608097 RL3065348A INSPECTED FUEL SERVO PLUG IAW SBPRS-107, REVISION 1, DATED MARCH 6, 2008. NO DAMAGE FOUND ON THE THREADS OF THE PLUG OF THE SERVO UNIT. INSTALLED PLUG AND SAFETIED IAW INSTRUCTIONS. 1 H 7 1 3O 3 O RT A4CE 1E4 2008041400005 20080414 00005 CE 2008 4 14 2008FA0000214 1 20080207 G 3040 FED2000 DEFOG SYSTEM LEAR 35 35A 5170602 CE GARRTT TFE731 TFE731* 01518 WP COCKPIT BURNED G A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 NM 01 60WL 382 RIGHT AFTER TAKEOFF, AUX DE-FOG UNIT ON CO-PILOT SIDE BURNED AND SMOKE FROM BLOWER FAILURE. NO WIRE PROBLEMS OR CIRCUIT BREAKER ISSUES FOUND. UNIT FAILURE CAUSED SMOKE IN COCKPIT, CREW DECLARED EMERGENCY AND RETURNED TO AIRPORT WITHOUT FURT HER INCIDENT. 2 L 7 2 4F 4 F A10CE E6WE 2008041000186 20080410 00186 CE 2008 4 10 2008FA0000215 1 20080204 G 2800 NUT CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA FUEL SERVO LOOSE B Z08R A UNSCHED LANDING O OTHER IN INSP/MAINT 1 CE 07 168JS 302 T20608735 WHILE PERFORMING SB PRS-107, FOUND PN 383493 HEX NUT ACCESS PLUG FINGER LOOSE. ALSO, FOUND RED DYE INSIDE FUEL SERVO AI R CHAMBER. THIS AC HAS HAD AN ISSUE WITH LEAN IDLE MIXTURE IN THE PAST. NOTE: HEX NUT WILL BE LOOSER IF ENGINE IS WARM ED UP. SUSPECT UNDERTORQUED FROM FACTORY AND RED DYE NOT FLUSHED FROM CHAMBER. SENT TO OVERHAUL FACILITY TO HAVE CORRE CTED AND PERFORMED THE REQUIREMENTS OF PRS-107 SB. (K) 1 H 7 1 3O 3 O RT A4CE E14EA 2008041000170 20080410 00170 EA 2008 4 10 2008FA0000216 2 20080204 G 7200 NUT CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE LOOSE B Z08R K NONE O OTHER IN INSP/MAINT 1 CE 07 227BH 172S10662 WHILE PERFORMING SB PRS-107, FOUND PN 383493 HEX NUT PLUG FINGER LOOSE. OTE: HEX NUT WILL BECOME LOOSE IF ENGINE IS WAR MED UP. SUSPECT UNDERTORQUED FROM THE FACTORY. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2008041000184 20080410 00184 EA 2008 4 10 2008FA0000217 2 20080204 G 7320 SERVO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FUEL SYSTEM UNDERTORQUED C Z08R K NONE O OTHER IN INSP/MAINT 1 CE 07 719JW 172S10527 WHILE PERFORMING SB PRS-107, FOUND PN 383493, HEX NUT PLUG FINGER LOOSE. NOTE: HEX NUT WILL BE LOOSER IF ENGINE IS WARM ED UP. SUSPECT UNDERTORQUED FROM FACTORY 1 H 7 1 3O 3 O NT 3A12 1E10 2008041000193 20080410 00193 EA 2008 4 10 2008FA0000218 2 20080204 G 7300 SERVO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENG FUEL LOOSE B Z08R K NONE J WARNING INDICATION IN INSP/MAINT 1 CE 07 452SM 172S10528 WHILE PERFORMING SB PRS-107 FOUND PN 383493 HEX NUT PLUG FINGER LOOSE. NOTE: HEX NUT WILL BE LOOSER IF ENGINE IS WARMED UP. SUSPECT UNDERTORQUED FROM THE FACTORY. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 2008041400043 20080414 00043 SW 2008 4 14 2008FA0000219 1 20080205 G 2820 SELECTOR VALVE MOONEY M20 M20C 5870208 SW LYC O360 O360* 41514 EA FUEL SYSTEM SEIZED D K NONE O OTHER IN INSP/MAINT 1 SW 09 6529U 2312 FUEL SELECTOR VALVE SEIZED IN THE (OFF) POSITION DURING A ROUTINE FUEL TANK SWITCHOVER. FAILURE CAUSED BY CORROSION ON SELECTOR VALVE SHAFT WHERE IT PASSES THROUGH THE UPPER VALVE HOUSING. POOR DESIGN. NO PROVISION MADE TO PREVENT SPILLE D LIQUIDS OR MOISTURE FROM CARPET FROM ENTERING UPPER HOUSING VALVE SHAFT BORE. (K) 1 L 7 1 3O 3 O 2A3 E286 2008041400044 20080414 00044 CE 2008 4 14 2008FA0000220 1 20080222 G 2701 05131682 CONTROL WHEEL CESSNA 172 172A 2072404 CE CONT O300 O300* 17022 SO BROKEN D O OTHER O OTHER TX TAXI/GRND HDL 1 NM 08 34264 625 ON TAXI FROM REFUELING PILOT WAS MAKING A LT TURN IN FRONT OF HANGER. PULLED CONTROL WHEEL FULL AFT (TO TAKE WEIGHT OFF OF FRONT WHEEL) CONTROL WHEEL BROKE OFF IN HIS HAND. (OUTSIDE TEM APPROX 20 DEGREES) BREAK WAS FROM LWR LT (7 OCLOCK) TO UPPER RT (2 OCLOCK). (K) 1 H 7 1 3O 3 O 3A12 E253 2008041000246 20080410 00246 EA 2008 4 10 2008FA0000221 1 20080220 G 7921 269D45031 SCROLL SCWZER 269 269D 8059501 EA ALLSN 250C 250C20 03013 GL OIL COOLER FAN CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 03 411HU 0040 UPON INSPECTION OF OIL COOLER FAN ASSY, FOUND MANY CRACKS AROUND THE TOP MOUNT OF SCROLL ASSY. (K) 1 G 7 1 3U 3 U 0 4H12 E4CE 2008041000205 20080410 00205 CE 2008 4 10 2008FA0000223 1 20080308 G 5753 052390133 SKIN CESSNA 182 182M 2072728 CE CONT O470 O470* 17026 SO TE FLAP CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 71784 5800 1200 18259755 ON INSPECTION BOTH FLAPS RT AND LT TOP AND BOTTOM FLAP SKINS WERE CRACKED 6 TO 8 INCHES ALONG THE T/E, ON THE RIVET LINE . ALSO SHEERED RIVETS ON (3) OF THE (4) FLAP TRACK LOWER TRACK TO RIBS. RESKINNED FLAPS AND INSTALLED MS21042 STEEL SC REWS IN REPLACEMENT OF THE SHEERED RIVETS. PROBABLE CAUSE BY FLAP OVERSPEED WITH HIGH G, LOADS. THIS AIRCRAFT TOWS GLI DERS ALL THE TIME. (K) 1 H 7 1 3O 3 O NT 3A13 E273 2008041000194 20080410 00194 SO 2008 4 10 2008FA0000224 1 20080321 G 2910 1159SCH5197 SIGHT GLASS GULSTM GVSP GVSPG550 3980203 SO RROYCE BR700 BR700710A110 NE HYD TANK CRACKED C K NONE O OTHER IN INSP/MAINT 1 GL 15 57UH 5163 SIGHT GLASS CRACKED IN SEVERAL LOCATIONS AND LEAKS HYDRAULIC FLUID. THIS TANK IS ONE OF SEVERAL RETURNED FOR THE SAME D EFECT. (K) 2 L 7 2 4F 4 F RT A12EA E00057EN 2008041000234 20080410 00234 NM 2008 4 10 2008FA0000225 1 20080401 G 8120 654327 TRANSITION DUCT LANCAR LC41 LC41550FG 5150001 NM CONT O550 TSIO550C SO TURBOCHARGER CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 19 431PC 41050 DURING ANNUAL INSP FOUND TURBO TRANSITION PART OF EXHAUST CRACKED ALL THE WAY THRU FRONT RADIUS OF THE PIPE. (K) 1 L 7 1 3O 3 O NT A00003SE E5SO 2008042800298 20080428 00298 SO 2008 4 28 2008FA0000226 1 20080321 G 2910 1159SCH5197 SIGHT GLASS GULSTM GIVX GIVXG450 3980205 SO RROYCE TAY TAY6118 EU HYD SYSTEM CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 25 612AF 224 4069 SIGHT GLASS CRACKED IN SEVERAL LOCATIONS AND LEAKS HYDRAULIC FLUID, THIS TANK IS ONE OF SEVERAL RETURNED FOR THE SAME DE FECT. (K) 2 L 7 2 4F 4 F RT A12EA E25NE 2008041000219 20080410 00219 SO 2008 4 10 2008FA0000227 1 20080225 G 3210 86262003 TUBE PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA MLG WORN D UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 5341Z 2193 4496107 NOSE GEAR DOOR TUBE PN 86262003 FOUND WITH GROOVE WORN INTO TUBE AT APPROX 65 PERCENT OF TUBE THICKNESS IN THE AREA OF T HE LT AND RT SUPPORTS PN 86262-005 AND 86262-012 RESPECTIVELY. THIS TUBE CONNECTS TO THE LT AND RT NOSE GEAR DOOR RODS AND PIVOTS AS THE GEAR IS RAISED AND LOWERED AND IT IS AT THE PIVOT POINT OF THE TUBE WHERE THIS WEAR IS OCCURRING. CUR RENTLY THERE IS A NYLON BUSHING PN 452647 THAT IS INSERTED AT THIS PIVOT POINT TO PROVIDE FOR SOME PROTECTION OF THE TUB E. THERE IS HOWEVER, NO WEAR TO THIS NYLON BUSHING. IT CAN BE ASSUMED THAT THIS NYLON BUSHING IS THE CAUSE OF THE WEAR AND PROVIDES NO GUARD AGAINST PROTECTING THE INTEGRITY OF THE TUBE. CURRENTLY THERE IS NO REQUIREMENT FOR LUBRICATION 1 L 7 2 3O 3 O A19S0 E286 2008041400053 20080414 00053 SO 2008 4 14 2008FA0000229 1 20080408 G 8011 701122223 SOLENOID PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA STARTER STICKS B H DEACTIVATE SYST/CIRCUITS S AFFECT SYSTEMS TX TAXI/GRND HDL 1 GL 21 436ND 3478 2842213 AFTER START, STARTER ANNUNCIATOR DID NOT EXTINGUISH. ENGINE SHUTDOWN WITH MIXTURE BUT CONTINUED TO CRANK OVER WITH MASTE R TURNED ON. TROUBLESHOOTING REVEALED STARTER CONTACTOR STUCK CLOSED. WHEN STRUCK CONTACTS WOULD OPEN BUT WHEN POWER APP LIED WOULD STICK CLOSED UNTIL STRUCK. 1 L 7 1 3O 3 O 2A13 E274 2008041400058 20080414 00058 SW 2008 4 14 2008FA0000230 1 20080331 G 2731 CONTROL TUBE ECLIPS EA500 ECLIPSEEA500 3350000 SW PITCH TRIM OUT OF ADJUST B CJ6R C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 GL 03 875NA 000018 AC EXPERIENCED A PITCH TRIM MALFUNCTION ON TAKEOFF ACCOMPANIED BY A WARNING MESSAGE. AN EMERGENCY WAS DECLARED AND THE AC WAS RETURNED TO BASE. PROBLEM WAS DUPLICATED ON THE GROUND. AFTER TROUBLESHOOTING, IT WAS DETERMINED THAT A REPLACE MENT ACTUATOR SHOULD BE INSTALLED. AFTER INSTALLING NEW PART, DEFECT STILL EXISTED. FURTHER TROUBLESHOOTING REVEALED T HAT THE CONTROL TUBES CONNECTED THE ACTUATOR TO THE CONTROL SURFACE WERE NOT SIMILARLY ADJUSTED. THIS CONDITION CAUSED A BINDING OF THE SYS MECHANICS AND THE SUBSEQUENT FAILURE. WHEN THE CONTROL TUBES WERE SIMILARLY ADJUSTED, THE SYSTEM O PERATED CORRECTLY ON GROUND AND IN SUBSEQUENT OPERATIONAL CHECK FLIGHT. (K) 1 L 7 2 4J RT A00002AC 2008041400060 20080414 00060 CE 2008 4 14 2008FA0000231 1 20080331 G 2820 LINE CESSNA 182 182P 2075816 CE CONT O470 O470* 17026 SO GAS COLATOR LEAKING C K NONE K J FLUID LOSS WARNING INDICATION IN INSP/MAINT 1 SO 03 20935 18261306 FUEL LEAKING FROM GAS COLATOR BOWL, TIGHTENED AT FACTORY DURING ACCEPTANCE FLIGHT (5.0 HOURS). FUEL LEAKING FROM GAS CO LATOR INLET LINE (10 HOURS SINCE NEW) RESULTED IN OFF-AIRPORT LANDING DUE TO FUEL QUANTITY. (K) 1 H 7 1 3O 3 O NT TA13 E273 2008041400061 20080414 00061 WP 2008 4 14 2008FA0000232 1 20080331 G 2621 130835 CARTRIDGE DOUG DC3 DC3CR183090C 3021466 WP PWA PT6 PT6* 52043 EA FIRE BOTTLE FAILED G VWBR K NONE O OTHER IN INSP/MAINT 1 GL 13 300BF 03692C1 26744 THE FIRE BOTTLE WAS BEING DISCHARGED FOR AN OVERHAUL. THE CARTRIDGE FIRED BUT DID NOT DISCHARGE THE BOTTLE. SUSPECT IM PROPER SETUP OF CARTRIDGE IN BOTTLE. (K) 2 L 7 2 4R 3 T A669 E2NE 2008041400062 20080414 00062 EA 2008 4 14 2008FA0000233 2 20080318 G 8530 IO360AV CYLINDER MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA HARTZL HCC2Y HCC2YR1 GL ENGINE WORN D K NONE O OTHER IN INSP/MAINT 1 WP 07 79337 547 CH42539B PILOT REPORTED PARTIAL POWER LOSS ON TAKEOFF. ENG INSP REVEALED THE FOLLOWING DISCREPANCIES AND CORRECTIONS AS NOTE: CY L NR 1 HAD BAD INTAKE VALVE SEAT WITH EXCESSIVE WEAR, AND FUEL INJECTOR AIR SCREEN CONTAMINATED. THIS POSSIBLY CAUSED C YL TO BURN LEAN AND CAUSED EXCESSIVE WEARING ON VALVE SEAT. THIS IN TURN WOULDN’T ALLOW THE INTAKE VALVE TO CLOSE PROPE RLY, CRATING ROUGH ENG RUNNING AND OCCASIONAL BACK-FIRING. COMPLETE STUD ASSY WAS REPLACED WITH REBUILT ASSY SN 162, UN DER WO 032608AA. CYL NR 4 HAD EXCESSIVE ROCKER ARM SIDE CLEARANCE. ROCKER ARM SIDE CLEARANCE WAS RESHIMMED AS SERVICE INSTRUCTIONS IN SB NR 225B BY ADDING ADDITIONAL SHIMS TO BRING ROCKER ARM SIDE. 1 L 7 1 3O 3 O 2A3 1E10 5 C P920 2008041400064 20080414 00064 SO 2008 4 14 2008FA0000234 1 20080307 G 7160 VALVE MAULE M4 M4210C 5460112 SO CONT IO360 IO360* 17025 CE ALT AIR VALVE BROKEN G O OTHER J WARNING INDICATION CR CRUISE 1 WP 11 51430 1097C THE ENG AUTOMATIC ALTERNATE INDUCTION AIR VALVE THAT IS PARTIALLY LOCATED INSIDE THE CYLINDRICAL PAPER INDUCTION AIR FIL TER CAME APART AND SOME OF ITS PART (2 INCH LONG, .2500 INCH DIAMETER BOLT. 2 INCH LONG SPIRAL SPRING WASHER, AND COTTE R PIN) WERE INGESTED INTO THE ENGINE INTAKE MANIFOLD, ENG CYL VALVES AND THE ENG CYL. THIS CAUSED A MAJOR LOSS OF POWER AFTER TAKEOFF, THE PILOT WAS ABLE TO GET BACK TO THE RUNWAY, BUT HE GROUND LOOPED THE AIRPLANE CAUSING AN ACCIDENT DUE TO SUBSTANTIAL DAMAGES TO THE AIRPLANE. POST ACCIDENT INVESTIGATION FOUND THAT AT AN EARLIER DATE THE PREVIOUS OWNER HA D DISASSEMBLED THE ALTERNATE AIR VALVE TO PAINT IT AND HE MAY HAVE IMPROPERLY REINSTALLED THE COTTER PIN INTO THE CASTEL 1 H 7 1 3O 3 O 3A23 E1CE 2008041400065 20080414 00065 CE 2008 4 14 2008FA0000235 1 20080301 G 2510 MS27039116 SCREW CESSNA 182 R182 2072734 CE LYC O540 O540* 41532 EA UNDER REAR SEAT IMPROPER PART D LN7R K NONE O OTHER IN INSP/MAINT 1 EA 13 757XU R18201273 MFG SB NR SEB07-3 TO CHECK THE LENGTH OF THE SCREWS IN ACCESS PLATE UNDER REAR SEAT. THE PLATE MAY HAVE HAD TOO LONG A SCREW INSTALLED WHICH COULD CAUSE A FAILURE OF THE LANDING GEAR TO OPERATE DOWN. THE SB LISTED THE PROPER SCREWS TO USE IN EACH HOLE IN THE PLATE. THE SCREWS LISTED ARE THE ONES IN THE PARTS CATALOG. THOSE ARE THE SCREWS THAT ARE TOO LON G. IF ANYBODY PUT IN THE PROPER LENGTH SCREW, (MS27039-1-12), THEN THE AC WOULD BE LESS SAFE AFTER COMPLYING WITH THE S B. THE PLATE NEEDS 17 EA MS27039-1-12, AND 1 MS27039-1-09. (K) 1 H 7 1 3O 3 O RT 3A13 E295 2008041400066 20080414 00066 EU 2008 4 14 2008FA0000236 1 20080227 G 3222 5322012039 PIN PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE NLG STRUT MISMANUFACTURED B Z4MR K NONE O OTHER IN INSP/MAINT 1 WP 27 672SD 666 DURING NOSE STRUT RESEALING, TORQUE LINKS WERE REMOVED. BEFORE REASSEMBLY THE PINS WERE CHECKED TO VERIFY GREASE WOULD PASS THROUGH. GREASE WOULD PASS THROUGH THE LOWER BUT NOT THE UPPER (UPPER AND LOWER PINS THAT CONNECT THE TORQUE LINKS TO THE GEAR ARE THE SAME PN). AFTER CLEANING, FOUND THAT THE UPPER PIN COUNTER BORE ONLY WENT PART WAY THROUGH THE PIN . (K) 1 L 7 1 3T 4 T RT A78EU E26NE 2008041400067 20080414 00067 NE 2008 4 14 2008FA0000237 1 20080221 G 6410 7610105017045 SPAR SKRSKY S76 S76B 8143007 NE PWA PT6 PT6* 52043 EA T/R BLADE CRACKED C CW1R K NONE O OTHER IN INSP/MAINT 1 EA 11 780P 2905 760359 DURING A ROUTINE INSP A SLIGHT, OCCASIONAL CLICK WAS HEARD WHILE FLEXING TAIL ROTOR BLADE. BLADE ASSY PN 761005501042, SN A245-00153 WAS REMOVED FOR PRECAUTIONARY MEASURES SENT FOR INSPECTION/ EVALUATION. UPON DISASSEMBLY AND INSPECTION SP AR WAS FOUND TO HAVE CRACKS COMING FROM ELLIPTICAL PLUG AREA. SPAR WAS SUBSEQUENTLY CHANGED, BLADE INSPECTED AND RETURN ED TO SERVICEABLE CONDITION. SCRAPED SPAR. 1 G 7 2 4U 3 T H1NE E2NE 2008041400076 20080414 00076 GL 2008 4 14 2008FA0000238 1 20080227 G 3411 51815001 BUSHING CIRRUS SR SR20 05628AJ GL CONT IO360 IO360* 17025 CE REDUCER INCORRECT C LN7R K NONE O OTHER IN INSP/MAINT 1 EA 13 362HE 1263 STATIC SYSTEM FAILED LEAK CHECK DURING 2 YEAR STATIC SYS IFR CERTIFICATION, LEAKS WERE CAUSED BY REDUCED BUSHING FAILING TO SEAL STATIC LINE SUMP. (ON BOTH SIDES, PILOT AND COPILOT). TO REPAIR THE LEAKAGE, PIPE THREAD TAPE (TEFLON TAPE) W AS USED ON THE REDUCER BUSHING BEFORE MATING IT WITH THE STATIC LINE SUMP. THE TYPE OF THREAD ON THESE ITEMS SHOULD NOT REQUIRE TEFFLON TAPE TO SEAL. SB 2X-34-22R1 (REVISED 10 OCT 2006) STEP L (FOR KIT 701164-001) STATES (APPLY THREAD SEA LANT TO ALL MALE PIPE THREAD FITTINGS PRIOR TO STATIC LINE SUMP ARE NOT PIPE THREAD, AND THEREFOR WERE NOT (TAPED). REC OMMEND CHANGING PROCEDURE TO STATE (APPLY THREAD SEALANT TO ALL MALE FITTINGS PRIOR TO ASSY). (K) 1 L 7 1 3O 3 O NT A00009CH E1CE 2008041400093 20080414 00093 WP 2008 4 14 2008FA0000239 1 20080115 G 6410 MHS54896 NUT HUGHES 369 369E 4470707 WP TAIL ROTOR BLADE SPLIT D K NONE O OTHER IN INSP/MAINT 1 NM 11 9460T 0238E ON FINAL TORQUE OF TAIL ROTOR BLADES RETENTION BOLT, NEW NUT SPLIT PRIOR TO ACHIEVING TORQUE. NEW NUT, IS THINNER AND L IGHTER STRENGTH THAN PREVIOUSLY MFG OLDER PN. NEW BOLTS ALSO REQURIE A NEW HIGHT TORQUE VALUE. (K) 1 G 7 1 3U H3WE 2008041400094 20080414 00094 EA 2008 4 14 2008FA0000240 2 20080307 G 8520 BOLT BEECH 80 65B80 1152812 CE LYC O540 IGO540B1A 41532 EA CONNECTING ROD FAILED G KZ5R A UNSCHED LANDING R Y J PARTIAL RPM/PWR LOSS ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 GL 15 103BA LD435 NR 1 ENGINE SHUTDOWN IN FLIGHT. SUSPECTED NR 7 CONNECTING ROD BOLT FAILURE. CAUSING CYL SEPARATION FROM CASE AND CRANK CASE CRACK. AC LANDED SAFELY WITHOUT OTHER DAMAGE. (K) 1 L 7 2 3O 3 O 3A20 1E11 2008041400063 20080414 00063 EU 2008 4 14 2008FA0000241 2 20080409 G 8500 ENGINE DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE1250299 EU LEFT POWER LOSS D O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 SO 15 49OTS 42AC090 020201763 AFTER TAKEOFF AND PULLING LANDING GEAR UP, LT ENGINE POWER REDUCTION TO 75 PERCENT FOR ABOUT ONE MINUTE AND POWER WAS RE STORED. THIS SAME ISSUE HAS BEEN INDUCTED TWICE IN LESS THAN 24 HRS. THERE IS NO FEDAC WARNINGS SHOWN ON SYS. A REPORT H AS BEEN SENT TO MFG. 1 L 7 2 3I 3 B RT A57CE E00069EN 2008041400098 20080414 00098 SO 2008 4 14 2008FA0000243 1 20080410 G 8120 TURBOCHARGER PIPER PA28 PA28R201T 7102813 SO CONT O360 TSIO360FB 17025 SO ENGINE FOD D K NONE C F.O.D. IN INSP/MAINT 1 SO 05 47550 28R7703397 232784B TURBOCHARGER COMPRESSOR DAMAGED BY FOD INGESTED THROUGH THE ALTERNATE AIR DOOR. THIS DOOR IS ON TOP OF THE AIR FILTER BO X ALLOWING ANY OBJECT THROWN UP BY THE NOSE WHEEL TO ENTER THE INDUCTION SYSTEM WHEN THE DOOR IS ACTIVATED DURING PREFLI GHT CHECKS. 1 L 7 1 3O 3 O 2A13 E9CE 2008041400059 20080414 00059 CE 2008 4 14 2008FA0000245 1 20080409 G 2731 TRIM SYSTEM BEECH 90 C90A 1152911 CE PWA PT6 PT6* 52043 EA ELEVATOR ICED P O OTHER F FLT CONT AFFECTED CL CLIMB 1 EA 21 200TR 400 LJ1067 WHEN THE AIRPLANE HAS SET ON THE RAMP IN THE RAIN, THEN TAKES OFF WITH A QUICK CLIMB TO COLDER TEMPERATURES AT ALTITUDE, THE ELEVATOR TRIM FREEZES. THE AUTOPILOT KICKS OFF BECAUSE IT IS UNABLE TO RESPOND. THE PILOT THEN HANDFLYS WITH THE EL EVATOR FORCE LOADED UP AND UNABLE TO TRIM. WITH LITTLE NUDGES BACK AND FORTH ON THE TRIM WHEEL FOR ABOUT 10 MINUTES, TH E SYSTEM BECOMES FREE. EACH TIME I REPORT THIS TO MECHANICS, THEY INSPECT AND LUBRICATE THE SYSTEM AND REPORT EVERYTHIN G IS SATISFACTORY. THIS WAS MY EXPERIENCE FROM 1984 TO 2005. THE PLANE WAS NORMALLY KEPT IN A HANGAR SO OCCURRENCES WER E INFREQUENT. 1 L 7 2 3T 3 T RT 3A20 E2NE 2008041400104 20080414 00104 EA 2008 4 14 2008FA0000246 2 20080411 G 8530 CYLINDER PIPER PA31 PA31325 7103105 SO LYC O540 TIO540* 41532 EA NR 5 DAMAGED D O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 GL 21 476EB 1400 1400 317612059 L167768A NR 5 CYL EXHAUST VALVE BROKEN, SENDING THE HEAD OF THE VALVE THROUGH THE EXHAUST AND LODGING ITSELF INTO THE TURBOCHARGE R, EXTENSIVE DAMAGE TO THE CYLINDER, PISTON, AND TURBO. 1 L 7 2 3O 3 O A20SO E14EA 2008042500057 20080425 00057 CE 2008 4 25 2008FA0000247 1 20080131 G 3245 22X8007008 TUBE CLEVELAND CESSNA 208 208B 2073701 CE PWA PT6 PT6* 52043 EA NOSE WHEEL TORN G K NONE O OTHER IN INSP/MAINT 1 AL 03 694MA 69 208B0694 PILOT REPORTED NOSE TIRE FLAT. UPON DISASSEMBLY OF NOSE TIRE, FOUND MIDDLE SEAM ON OUTSIDE OF TUBE, TORN/SPLIT, APPROX 1 INCH IN LENGTH. (K) 1 H 7 1 3T 3 T A37CE E2NE 2008041700024 20080417 00024 CE 2008 4 17 2008FA0000248 1 20080204 G 3260 THROTTLE SWITCH CESSNA 210 210J 2073439 CE CONT O520 IO520* 17032 SO COCKPIT INTERMITTENT D O OTHER O OTHER LD LANDING 1 EA 23 1333T T21059108 GEAR WARNING HORN WAS INOPERATIVE. AC LANDED WITH LANDING GEAR UP. SUBSEQUENT INVESTIGATION DETERMINED THROTTLE MICROS WITCH WAS MAKING INTERMITTENT CONTACT WHEN ENGAGED AND GROUND CONNECTION WAS INSUFFICIENT. CORRECTED BY REPLACING SWITC H AND REPAIRING GROUND CONNECTION. HORN OPERATION SHOULD BE CHECKED VIA TEST FEATURE DURING PREFLIGHT. (K) 1 H 7 1 3O 3 O 3A21 E5CE 2008042500069 20080425 00069 CE 2008 4 25 2008FA0000249 1 20080207 G 3233 MS28775112 SEAL CESSNA 172 172RG 2072438 CE LYC O360 O360* 41514 EA NLG ACTUATOR LEAKING D K NONE O OTHER IN INSP/MAINT 1 SO 11 6562V 172RG0775 AFTER REPEATED TOUCH AND GO PROCEDURES, THE AC FAILED TO RETRACT THE LANDING GEAR DUE TO A LACK OF HYDRAULIC FLUID. THIS RESULTED IN A GEAR UP LANDING. DURING THE ACCIDENT INVESTIGATION IT WAS DETERMINED THAT THE HYDRAULIC FLUID RESERVOIR WAS DEPLETED OF FLUID BY CYCLING THE LANDING GEAR. THE NLG ACTUATOR WAS LEAKING STEADILY WHILE THE HYDRAULIC PUMP WAS C YCLING. DAMAGE TO THE AC WAS LIMITED DUE TO THE PROPER EXECUTION OF EMERGENCY LANDING PROCEDURES. THERE WERE NO INJURI ES. (K) 1 H 7 1 3O 3 O 3A17 E286 2008042500106 20080425 00106 WP 2008 4 25 2008FA0000250 2 20080305 G 7200 ENGINE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33110UG 01514 WP ROTOL R321 R321482F8 GL OVERHEATED W LY0F E ENGINE SHUTDOWN M J OVER TEMP WARNING INDICATION CR CRUISE 1 SO 23 139LC 24465 AC732 P44344 DRG856029 IN CRUISE TO 8000 FT, INDICATION OF RED LIGHT OF OIL PRESSURE WITH 870 DEGREE TEMPERATURE. LIGHT TURNS OFF. AFTER 15 S ECONDS, THE LIGHT TURNS ON AGAIN WITH 870 DEGREE TEMPERATURE, BUT THE PRESSURE DOWN NEAR ZERO. THE CREW MADE THE SHUTD OWN ENGINE PROCEDURE. LANDING WITHOUT NOVELTY. AT THE MOMENT THE ENGINE IS WAITING TECH INSPECTOR. (K) 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P61GL 2008042500112 20080425 00112 CE 2008 4 25 2008FA0000252 1 20080305 G 8011 MOUNT CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA STARTER FAILED C K NONE O OTHER IN INSP/MAINT 1 SW 15 214CE 1 T20608592 ORIGINAL STARTER (TT 433.4) WAS REMOVED BECAUSE IT FAILED (SMELLED BURNED). A REPLACEMENT WAS ORDERED FROM MFG AND INST ALLED. CHANGED THE SPARK PLUGS AND CHECKED ENGINE TIMING, WHICH WAS FOUND GOOD. AFTER INSTALLATION OF STARTER STARTED THE AC (5) TIMES AND OPS CHECKED GOOD. 2/29/2008 THE PILOT TRIED TO START THE ACFT AND HEARD A GROWLING SOUND. OPENED THE COWLINGS AND FOUND THE STARTER MOUNT CRACKED THROUGH THE BELL HOUSING. NOTIFIED MFG AND THEY ASSURED ME THIS WAS N ORMAL WHEN AN AC HAS A KICKBACK. THE PILOT STATED HE DID NOT HAVE A KICKBACK. SENT THE STARTER FOR REPAIR AND WHEN RET URNED, INSTALL AND AGAIN CHECKED THE IGNITION SYS WITH NO ABNORMITIES FOUND. STARTED THE AC (5) TIMES AND HAD THE OWNER 1 H 7 1 3O 3 O RT A4CE E14EA 2008042500127 20080425 00127 CE 2008 4 25 2008FA0000254 2 20080305 G 7310 SERVO DIAMON DA40 DA40 2990002 GL CONT IO360 IO360* 17025 CE HARTZL HCC2Y HCC2YR1 GL FUEL INJECTION DAMAGED D U1VS K NONE O OTHER IN INSP/MAINT 1 NM 07 103UV 687 40683 L3284951A CH40160B WHILE PERFORMING A 100 HR INSP, THE TECH DISCOVERED FINE METAL PARTICLES COVERING THE THROAT AND VALVE OF THE FUEL INJEC TION SERVO (2576568-1, SN 70B10709). THE SERVO WAS SENT TO A REPAIR FACILITY TO DETERMINE WHETHER OR NOT ANY OF THE MET AL PARTICLES ENTERED THE SERVOS BLAST TUBES. IT HAS BEEN DETERMINED THAT THE METAL ORIGINATED FROM THE CHAFING OF THE L OOSE FITTING INLET RING (ITEM 220) WITHIN THE FLANGE (ITEM 20). THE LOOSE FIT IS DUE TO MFG. MFG HAS NOT COME UP WITH A FIX AS OF THIS DATE. FOR NOW WE ARE CEMENTING THE INLET RING TO THE FLANGE WHILE AWAITING A PERMANENT FIX. 1 L 7 1 3O 3 O NT A47CE E1CE 5 C P920 2008042800300 20080428 00300 CE 2008 4 28 2008FA0000256 1 20080321 G 2520 17001277 PANEL CESSNA 182 182Q 2072732 CE CONT O470 O470* 17026 SO CABIN CORRODED G K NONE O OTHER IN INSP/MAINT 1 SO 09 97660 15328 18267161 DURING AN AGING AC INSP OF FLEET AC, VEERING SEVERITY OF SURFACE CORROSION HAS BEEN FOUND IN AC CONTAINING SOUNDPROOFING PANELS SHOWN IN MFG IPC FIG 90. THE HEAVIEST AND MOST SEVERE CORROSION WAS FOUND UNDER SOUNDPROOFING PANELS PN 0700076 2-23 ITEM 7, PN 1700127-7 AND -10, ITEMS 10 AND 13, PN 1200217-8, ITEM 14 AND 1200193-11, ITEM 15. REMOVAL OF SURFACE C ORROSION, CLEANING, BRIGHTING, AND ALODINING THE EFFECTED AREAS TO REMOVING OF COMPLETE SKIN PANELS TO RESTORE STRUCTURA L INTEGRITY OF THE AC. PROBABLE CAUSE IS THE MFG TO PROVIDE A SUITABLE CORROSION BARRIER TO PROTECT THE AC STRUCTURAL I NTEGRITY AND THE SKIN PANELS BEING EXPOSED TO CHEMICAL ACTION OF THE ADHESIVES USED TO ATTACH THE SOUNDPROOFING PANELS T 1 H 7 1 3O 3 O NT 3A13 E273 2008042800304 20080428 00304 NE 2008 4 28 2008FA0000257 2 20080311 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MALFUNCTIONED E A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CE 03 957FE 208B0070 17431 AS PILOT OF FLT 7575, LEVELED OFF AT 9000 FT, HEARD A LOUD POP NOISE COME FROM THE ENGINE AND NOTICED TRQ DROPPED BELOW 600 LBS AND ITT STARTED RISING. PILOT NEVER LOST POWER BUT DUE TO TEMP RISING HE DECLARED AN EMERGENCY AND LANDED SAFEL Y. AFTER TALKING TO PILOT AND CHECKING POWER ANALYZER AND RECORDER (PAR) THE ITT TEMP REACHED 926 DEGREES. ACCORDING T O MM, ANYTHING OVER 900 DEGREES IN CRUISE FLT REQUIRES TO BE PULLED AND SENT TO OVERHAUL SHOP FOR INSPECTION. WE HAVE B OROSCOPED THE ENGINE AND SEE NO EVIDENCE OF ANY FOD ACCORDING TO OUR CONTRACT MAINT. THERE IS SIGNS OF AN OVERTEMP. FI GURED THAT WITH WHAT THE PAR SHOWS. NOT SURE WHAT CAUSE THE LOUD POP AND THE OVER TEMP. MAYBE THE COMPRESSOR BLEED VAL 1 H 7 1 3T 3 T A37CE E4EA 2008042800307 20080428 00307 CE 2008 4 28 2008FA0000258 1 20080228 G 5730 TAPE CESSNA 140 140 2071602 CE CONT C90 C90* 17009 SO WING LOOSE D K NONE O OTHER IN INSP/MAINT 1 GL 03 3527V 14796 DURING FLIGHT, THE FABRIC PATCH CAME OFF. THE AC WAS LANDED WITH SOME DIFFICULTY BUT WITHOUT INCIDENT. IT IS SPECULATE D THE AIR STREAM GOT UNDER A LOOSE TAPE AND LIFTED THE ENTIRE PATCH FROM THE WING INCLUDING RIPPING THE FABRIC CLIPS OUT OF THE RIBS. IT IS FURTHER SPECULATED THE PILOTS PREFLIGHT HAD FAILED TO IDENTIFY A POTENTIAL PROBLEM ARISING FROM A L OOSE TAPE. NEW SYS VI DIFFERS FROM THE OLDER PROCESS IN THE TYPE OF BASE PRIMER AND FINISHING PAINT. CURRENT SYS CALLS FOR BRUSHING A COAT OF THINNED U500 ADHESIVE WHERE THE TAPE WILL BE LAID. THIS IS ALLOWED TO DRY. TAPE IS THEN LAID D OWN AND BRUSHED WITH CEMENT, WORKING THE CEMENT UP INTO THE WEAVE OF THE TAPE AND PAYING SPECIAL ATTENTION TO WORKING TH 1 H 7 1 3O 3 O NC A768 E252 2008042800308 20080428 00308 GL 2008 4 28 2008FA0000259 1 20080314 G 2780 SLAT SYSTEM BOMBDR BD700 BD7001A10 1390006 GL RROYCE BR700 BR700710A110 NE MALFUNCTIONED D O OTHER J WARNING INDICATION TO TAKEOFF 1 SW 05 917GL 9117 FLIGHT CREW REPORTED THAT SHORTLY AFTER ROTATION (AFTER T/O) THEY HAD A (FLICKERING) SLAT HALF SPD AND SLAT/FLAP HALF SP D EICAS MESSAGE. SHORTLY THEREAFTER THEY HAD AN AMBER SLAT FAIL, STALL WARN ADVANCE EICAS MESSAGE, C/B TRIP (E-2 SLAT/F LAP PWR 2) AND FLIGHT SPOILER FAULT EICAS MESSAGE. THEY WERE ABLE TO LAND AT HOME BASE WITH SLATS OUT/FLAPS 0, WITHOUT INCIDENT (SLATS WERE AVAILABLE, FLAPS WERE NOT AVAILABLE. THE CAS MESSAGES WERE STILL PRESENT WHEN THEY PARKED THE AC A ND THE FOLLOWING FDE MESSAGES: RT MFS NR 3 ACTUATOR/WRG 27656232SX; FLT CONT 2B FAULT (FCU 2 27654282SX; FLAP FAIL LATCH ED FAULT NR1 2751000STD. TROUBLESHOOTING BY MAINT AND DEBRIEF FROM THE FLT CREW REVEALED A BOTTLE OF DRINKING WATER HAD 2 L 7 2 4F 4 F RT T00003NY E00057EN 2008042800309 20080428 00309 SO 2008 4 28 2008FA0000260 2 20080227 G 8530 712BCA CYLINDER CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 5421M 544 402B0021 CRACKED BETWEEN FIN NR1-3, BEHIND INJECTOR. DEFECTIVE PRODUCT. (K) 1 L 7 2 3O 3 O A7CE E8CE 2008042800395 20080428 00395 SO 2008 4 28 2008FA0000261 2 20080317 G 8520 639193 BUSHING CONT O520 TSIO520WB 17040 SO COUNTER WEIGHT BROKEN B VA1R K NONE O OTHER IN INSP/MAINT 1 SW 19 32 518853 RECEIVED ENGINE IN AFTER 32.2 HOURS SINCE MAJOR OVERHAUL. ENGINE WAS DAMAGED BY COUNTERWEIGHT FAILURE ON CRANKSHAFT. D AMAGED TO THE CRANKCASE, CYLINDERS AND ROD WAS FROM WHAT APPEARED TO BE A BROKEN COUNTERWEIGHT PIN OR FAILURE OF THE COU NTERWEIGHT BUSHING. THE BUSHING WAS FOUND IN SEVERAL PIECES. (K) 3 O E8CE 2008042800396 20080428 00396 CE 2008 4 28 2008FA0000262 1 20080401 G 5410 HINGE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA ENG COWLING BROKEN D K NONE O OTHER IN INSP/MAINT 1 WP 09 XCBCN BB435 PCE80952 ENGINE ICE VANE HINGE ASSY, BROKEN. HINGE ASSY BREAKS AND FRAGMENTS INTO SMALL PIECES THAT TEND TO BE INGESTED INTO ENG INE, CAUSING FOD. (K) 1 L 7 2 4T 4 T A24CE E4EA 2008042800386 20080428 00386 EA 2008 4 28 2008FA0000263 2 20080403 G 8530 LW12993 CYLINDER PIPER PA32 PA32301 7103207 SO LYC O540 IO540K1G5 41532 EA NR 2 CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 05 8200M 1311 328006048 L1642048AC NR 2 CYL CRACKED FROM UPPER SPARK PLUG HOLE TO THE EXHAUST VALVE SEAT. CRACK IN HEAD LED TO FAILURE OF EXHAUST PUSHROD HOUSING, AND DEFORMATION OF THE EXHAUST PUSHROD. AC LANDED WITHOUT INCIDENT. (K) 1 L 7 1 3O 3 O A3SO 1E4 2008042800387 20080428 00387 CE 2008 4 28 2008FA0000264 1 20080402 G 3710 RA442CW12 PUMP BEECH 58 58 1152740 CE CONT O550 IO550* SO VACUUM SYSTEM FAILED B PZ4R K NONE O OTHER IN INSP/MAINT 1 GL 11 8050U TH1657 VACUUM PUMP FAILED TO DEVELOP ANY AIR OUTPUT UPON INSTALLATION. REMOVED PUMP AND INSPECTED, SUSPECT VANES ARE NOT SLIDI NG OUT AGAINST CYLINDER WALL THUS NOT ALLOWING ANY AIR TO BE DEVELOPED. (K) 1 L 7 2 3O 3 O 3A16 E3SO 2008042800388 20080428 00388 WP 2008 4 28 2008FA0000265 2 20080322 G 7230 307241616 COMPRESSOR RAYTHN 900 HAWKER900XP 4220011 CE GARRTT TFE731 TFE731* 01518 WP ENGINE SEPARATED B ZN3R O OTHER E VIBRATION/BUFFET CL CLIMB 1 WP 07 897QS 135 HA0014 P122133 ON CLIMB THROUGH FL140 CREW HEARD BANG FROM RT ENGINE WITH VIBRATION. RT ITT INCREASED 150C BUT NO OVER TEMP. REDUCED POWER, THEN BROUGHT POWER BACK UP, WITH SAME RESULT. CREW LANDED WITHOUT INCIDENT AND ENGINE REMOVED AND SENT FOR REPAI R AND OVERHAUL. (K) 1 L 7 2 4F 4 F RT A3EU E6WE 2008042800389 20080428 00389 CE 2008 4 28 2008FA0000266 1 20080409 G 2820 1200406245 FUEL LINE CESSNA 172 172M 2072418 CE LYC O320 O320* 41508 EA FUEL SYSTEM DEFORMED B HP6R K NONE O OTHER IN INSP/MAINT 1 NM 01 22479 732 17264066 DURING ANNUAL INSPECTION OF THE MAIN FUEL LINE, BELOW FLOOR, JUST AFT OF FIREWALL, WAS FOUND DEFORMED (TWISTED). PILOT DID NOT REPORT LOW POWER. (K) 1 H 7 1 3O 3 O NT 3A12 E274 2008042800390 20080428 00390 SW 2008 4 28 2008FA0000267 1 20080407 G 5751 RIB BBAVIA 7 7GCAA 21101N8 SW LYC O320 O320B2B 41508 EA SNSNCH 74D 74DM EA RT AILERON BOWED C V36R K NONE O OTHER IN INSP/MAINT 1 SO 13 872JM 42299 L1907339A AA57931 REMOVED THE RT AILERON DUE TO REPORTS OF BINDING BETWEEN THE AILERON AND WING DURING AEROBATIC MANEUVERS. ON THE GROUND THE IB AILERON TO AILERON BAY RIB CLEARANCE WAS APPROX .0625 INCH. IAW TECH SUPPORT THE CLEARANCE SHOULD BE .2500 INCH . THE WING IB AILERON BAY RIB APPEARED TO HAVE BOWED DUE TO FABRIC SHRINKAGE OVER TIME, CAUSING THE INTERFERENCE. THE IB AILERON RIB FABRIC WAS OPENED, THE RIB WAS RELOCATED OB .1875 INCH, AND THE FABRIC WAS REPAIRED UTILIZING NEW TAPES A ND THE SUPERFLITE PROCESS. THE REPAIR WAS PAINTED WITH FLEX AGENT ADDED. IAW TECH SUPPORT, AILERON BALANCING WAS NOT R EQUIRED. REINSTALLED AILERON. AILERON CLEARANCE AND OPERATION SATISFACTORY. (K) 1 H 7 1 3O 3 O A759 E274 5 N P88614 2008050800007 20080508 00007 CE 2008 5 8 2008FA0000268 1 20080304 G 3800 DRAIN CESSNA 208 208B 2073701 CE PWA PT6 PT6A114 52043 NE FUSELAGE PLUGGED B MT9R O OTHER S AFFECT SYSTEMS DE DESCENT 1 SW 05 9546B 208B0126 DURING FLT IN MODERATE TURBULENCE THE AP STARTED TO DISCONNECT, TWICE. THIRD ATTEMPT TO ENGAGE THE AP, THE AC MADE AN U NCOMMANDED 1500 FPM DESCENT. ATTEMPT TO CORRECT THE ATTITUDE WITH THE CWS FUNCTION WAS MADE BUT THE AP WOULD NOT DISENG AGE. THE AP DISCONNECT BUTTON WOULD NOT LET GO EITHER. HAD TO OVERPOWER THE AP CLUTCHES TO REGAIN CONTROL AND ATTEMPTE D TO DISCONNECT THE SYS WITH THE C/B, THE AP REMAINED ON AND LIT AFTER PULLED. RECYCLED THE C/B AND WAS SUCCESSFUL. TH IS HAPPENED ON DESCENT, THE SYS HAD BEEN FUNCTIONING NORMALLY PRIOR TO THE INCIDENT. MX FOUND WATER ACCUMULATED BEHIND THE REAR CURTAIN. THIS IS THE AREA THAT THE PITCH SERVO IS LOCATED. THEY FOUND THAT THE SERVO HAD A SOLENOID STUCK CLO 1 H 7 1 3T 3 T A37CE E4EA 2008042800394 20080428 00394 NM 2008 4 28 2008FA0000269 1 20080401 G 8120 654327 TRANSITION DUCT LANCAR LC41 LC41550FG 5150001 NM CONT O550 TSIO550C SO TURBOCHARGER CRACKED B L9OR K NONE O OTHER IN INSP/MAINT 1 WP 19 139DC 714 41056 914313 DURING ANNUAL INSPECTION FOUND TURBO TRANSITION PART OF EXHAUST CRACKED ALL THE WAY THRU FRONT RADIUS OF THE PIPE. (K) 1 L 7 1 3O 3 O NT A00003SE E5SO 2008050800009 20080508 00009 CE 2008 5 8 2008FA0000270 1 20080403 G 3222 07436062 ATTACH FITTING CESSNA 182 182T 2072703 CE LYC O540 IO540AB1A5 EA NLG CRACKED B 7TFR K NONE O OTHER IN INSP/MAINT 1 WP 07 783WB 1044 18281512 L3000248 DISCOVERED CRACK DURING ANNUAL INSPECTION. (2) LONG CRACKS APPROXIMATELY (1) INCH ON (1) SIDE OF THE FITTING ONLY, (1) AT THE LT LOWER ATTACHMENT AND THE OTHER JUST AFT AND LT OF THE AREA WHERE THE STRUT BARREL IS SECURED. SUSPECT HARD L ANDING BUT NO OTHER DAMAGE NOTED. (K) 1 H 7 1 3O 3 O NT 3A13 1E4 2008050800010 20080508 00010 WP 2008 5 8 2008FA0000271 1 20080403 G 2820 LINE HUGHES 269 269C 4470504 WP FUEL SYSTEM LEAKING D K NONE O OTHER IN INSP/MAINT 1 SW 17 111AB 5 5 S1911 FUEL LEAKING FROM GASCOLATOR INLET LINE, APPROX 5.0 HRS SINCE NEW. (K) 1 G 7 1 3O 4H12 2008050800011 20080508 00011 CE 2008 5 8 2008FA0000272 1 20080112 G 5280 3901104580007 DOOR RAYTHN 390 390 7150030 CE WILINT FJ44 FJ442A GL LT MLG DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 15 7088S 264 RB188 AFTER ROUTINE FLIGHT, THE PILOT WAS PERFORMING HIS PREFLIGHT WALKAROUND INSP IN PREPARATION FOR THE NEXT LEG OF THE FLIG HT. HE NOTICED THAT BOTH MLG OUTER DOORS WERE DAMAGED. MECHANIC/MAINT WENT TO EVALUATE THE DAMAGE TO THE DOORS. RECOM MENDED THAT THE AIRPLANE BE FLOWN BACK UNDER SPECIAL FLIGHT PERMITS. THE DOORS WERE EVALUATED BY MAINT AND QUALITY DEPT , AS WELL AS TECH REP, DETERMINED UNREPAIRABLE. NEW DOORS WERE ORDERED, RECEIVED, INSTALLED, RIGGED AND TESTED SATISFAC TORILY. AC HAS SINCE BEEN RETURNED TO SERVICE WITH NO FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM. (K) 1 L 7 2 3F 4 F RT A00010WI E3GL 2008050800012 20080508 00012 CE 2008 5 8 2008FA0000273 1 20080112 G 5280 390110458008 DOOR RAYTHN 390 390 7150030 CE WILINT FJ44 FJ442A GL RT MLG DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 15 7088S 264 RB188 AFTER ROUTINE FLIGHT, THE PILOT WAS PERFORMING HIS PREFLIGHT WALKAROUND INSP IN PREPARATION FOR THE NEXT LEG OF THE FLIG HT. HE NOTICED THAT BOTH MLG OUTER DOORS WERE DAMAGED. MECH/ MAINT WENT TO EVALUATE THE DAMAGE TO THE DOORS. RECOMMEN DED THAT THE AIRPLANE BE FLOWN BACK UNDER SPECIAL FLIGHT PERMITS. THE DOORS WERE EVALUATED BY MAINT AND QUALITY DEPT, A S WELL AS TECH REP, DETERMINED UNREPAIRABLE. NEW DOORS WERE ORDERED, RECEIVED, INSTALLED, RIGGED AND TESTED SATISFACTOR ILY. AC HAS SINCE BEEN RETURNED TO SERVICE WITH NO FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM. (K) 1 L 7 2 3F 4 F RT A00010WI E3GL 2008050800014 20080508 00014 CE 2008 5 8 2008FA0000274 1 20080128 G 5280 3901104500017 DOOR RAYTHN 390 390 7150030 CE LT MLG DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 15 34GN 1121 RB58 THE PILOT WAS INFORMED BY THE FUEL TRUCK DRIVER THAT THE LT MLG IB DOOR WAS NOT PROPERLY LOCKED IN THE UP POSITION, AND THE OB PORTION OF THE DOOR HAD MADE CONTACT WITH THE RUNWAY DURING LANDING. ENGINEERING DEPT RECOMMENDED THAT THE AIRPL ANE BE FLOWN BACK UNDER THE AUSPICES OF FAR PART 21.197, SPECIAL FLIGHT PERMITS. THE DOOR WAS EVALUATED BY MAINT AND QU ALITY DEPT, AS WELL AS BY THE LOCAL TECH REP, AND DETERMINED UNREPAIRABLE. AC HAS SINCE BEEN RETURNED TO SERVICE WITH N O FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM. (K) 1 L 7 2 3F RT A00010WI 2008050800015 20080508 00015 CE 2008 5 8 2008FA0000275 1 20080128 G 3297 WIRE RAYTHN 390 390 7150030 CE LT MLG BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 15 34GN RB58 AFTER LANDING, THE PILOT WAS INFORMED BY FUEL TRUCK DRIVER THAT LT MLG IB DOOR WAS NOT PROPERLY LOCKED IN THE UP POSITIO N, AND THE OB PORTION OF THE DOOR HAD MADE CONTACT WITH THE RUNWAY DURING LANDING. ENGINEERING DEPT RECOMMENDED THAT TH E AC BE FLOWN BACK UNDER AUSPICES OF FAR PART 21.197, SPECIAL FLIGHTS PERMITS. THE DOOR WAS EVALUATED BY MAINT, QUALITY DEPT, AND BY TECH REP, AND DETERMINED UNREPAIRABLE. ADDITIONAL TROUBLESHOOTING REVEALED THAT WIRING FOR THE UPLOCK MIC ROSWITCH WAS BROKEN, AND IT WAS THIS BROKEN WIRING THAT CAUSED THE MICROSWITCH TO FAIL TO ALLOW THE UPLOCK TO PROPERLY E NGAGE THE LOCKING LUG ON THE DOOR. MICROSWITCH AND A NEW LT MLG IB DOOR WERE ORDERED RECEIVED, INSTALLED, RIGGED AND T 1 L 7 2 3F RT A00010WI 2008042800324 20080428 00324 GL 2008 4 28 2008FA0000278 1 20080415 G 2100 VALVE DIAMON DA40 DA40 2990002 GL CONT IO360 IO360* 17025 CE LOOSE D K NONE O OTHER IN INSP/MAINT 1 NM 11 105UV 40685 L3277551A THE ALTERNATE AIR VALVE IS VIBRATING AND CAUSING FRETTING BETWEEN THE INLET RING, PN D41-7166-20-31 AND FLANGE, PN D41-7 166-20-33. THE "DUST" IS BEING INGESTED INTO THE FUEL CONTROL SERVO AND ENGINE. THERE NEEDS TO BE A TIGHTER FIT BETWEEN THESE PARTS. 1 L 7 1 3O 3 O NT A47CE E1CE 2008042800327 20080428 00327 EA 2008 4 28 2008FA0000280 2 20080112 G 8550 16991000327 HOSE BEECH 23 C23 1151242 CE LYC O360 O360A4G 41514 EA OIL COOLER LEAKING G H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 EA 17 2102W 26 M1429 L1673536A THE AC EXPERIENCED AN EMERGENCY LANDING AFTER THE PILOT REPORTED SMOKE IN THE COCKPIT. INSP AND INVESTIGATION REVEALED AN OIL COOLER LINE HAD BEEN MAKING CONTACT WITH THE NR4 EXHAUST STACK (RISER), EVENTUALLY CAUSED THE FIRE SHEATHING AND OIL LINE TO DETERIORATE, CAUSING THE OIL TO LEAK INTO THE HEAT EXCHANGER, WHICH CAUSED SMOKE IN THE COCKPIT OBSERVED BY THE PILOT. UPON INSP, ALL BUT 16 OZ OF OIL LEAKED OUT OF ENGINE, WELL BELOW THE MINIMUM SAFE QUANTITY FOR THE MODEL INS TALLED ON THIS AC. PILOT IN THIS CASE WAS ABLE TO KEEP OIL PRESSURE UPON LANDING, THUS AVOIDING A POTENTIALLY SERIOUS S ITUATION. AS A RESULT OF THIS OCCURRENCE, ENGINE HAD TO BE DISASSEMBLED, CLEANED, INSPECTED, REPAIRED AS NECESSARY, AND 1 L 7 1 3O 3 O A1CE E286 2008042800328 20080428 00328 CE 2008 4 28 2008FA0000281 1 20080416 G 7120 051313211 MOUNT CESSNA 175 175 2072502 CE CONT O300 GO300* 17022 SO LT ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 11 6620E 1927 723 56120 INSP FOUND UPPER LT BRACKET (0513132-11) WITH A SMALL CRACK ORIGINATING FROM THE LOWER EDGE OF THE ENGINE MOUNT BOLT WAS HER. ONLY A SMALL BEND LINE WAS VISIBLE FROM THE COCKPIT SIDE OF THE BRACKET VIA BOROSCOPE. AFTER REMOVAL OF THIS BRAC KET A CRACK WAS CLEARLY VISIBLE ON THE ENGINE SIDE OF BRACKET. FOUND UPPER RT BRACKET WITH (3) CRACKS SEPARATING THE BRA CKET INTO 4 PIECES. THE THRESHOLD FOR THIS INSP SHOULD BE REDUCED FROM 2500 HRS. A MORE FREQUENT BOROSCOPE INSP WITHOU T REMOVAL OF THE ENGINE TRUSS MOUNT BOLTS WOULD PROVIDE AN EQUAL LEVEL OF SAFETY AS LONG AS A LARGER AREA WASHER HAS NOT BEEN INSTALLED. INSTALLATION OF A LARGER AREA WASHER MAY REDUCE THE STRESS POINT AND IMPROVE THE LIFE OF THE BRACKET. 1 H 7 1 3O 3 O NT 3A17 E298 2008050800051 20080508 00051 EA 2008 5 8 2008FA0000285 1 20080402 G 2822 1D217 PUMP DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA FUEL SYSTEM FAILED B SCIR K NONE O OTHER IN INSP/MAINT 1 NM 07 359AR 359 BOOST PUMP FAILS AT 11,000 TO 12,000 FT OF ALTITUDE. WORKS FINE ON GROUND. (K) 1 H 7 2 3T 4 T RT A9EA E4EA 2008050800052 20080508 00052 EA 2008 5 8 2008FA0000286 2 20080414 G 8530 AEL61247 COVER CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 09 98874 632 17276370 L1379939A EF023 FOUND ROCKER BOX COVER WITH MULTIPLE CRACKS DURING AC FLEET INSPECTION, FOLLOWING DISCOVERY OF ANOTHER CRACKED COVER ON A DIFFERENT AC. CRACKS CAUSED, DUE TO IMPROPER CLEARANCE BETWEEN COVER AND ROCKER ARMS ALLOWING ROCKER ARMS TO CONTACT COVER. THERE IS A NOTABLE CLEARANCE DIFFERENCE BETWEEN ORIGINAL MFG COVER AND THE OTHER MFG COVER AT THE LOWER PORTION OF THE COVER. RECOMMEND REPLACEMENT OF ALL SS COVERS PN AEL61247 WITH ORIGINAL MFG OR SUITABLE SUBSTITUTE. (K) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2008050800054 20080508 00054 EA 2008 5 8 2008FA0000287 2 20080414 G 8530 AEL61247 COVER CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 09 63450 191 17275434 L1420839A TK039 FOUND ROCKER BOX COVER CRACKED DURING 100 HOUR INSPECTION. CRACKS CAUSED DUE TO IMPROPER CLEARANCE BETWEEN COVER AND RO CKER ARMS ALLOWING ROCKER ARMS TO CONTACT COVER. THERE IS A NOTABLE CLEARANCE DIFFERENCE BETWEEN AN ORIGINAL MFG COVER AND THE OTHER MFG COVER AT THE LOWER PORTION OF THE COVER. (K) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2008050800064 20080508 00064 CE 2008 5 8 2008FA0000288 1 20080401 G 5712 12210628 BULKHEAD CESSNA 177 177B 2073708 CE LYC O360 O360* 41514 EA RT WING CRACKED B H5GR K NONE O OTHER IN INSP/MAINT 1 EA 07 99NA 6339 17702697 DURING ROUTINE INSPECTION, FOUND PART CRACKED. CHECKED (2) OTHER CARDINALS THAT HAPPENED TO BE IN OUR SHOP AND FOUND (1 ) OF THEM TO HAVE A SIMILAR CRACK. THIS SECTION OF THE BULKHEAD IS THE ATTACH STRUCTURE FOR THE LOWER ATTACH ANGLE FOR THE IB FLAP DRIVE BELLCRANK. IT IS CURIOUS THAT THE FACTORY INSTALLED SOME EXTRA REINFORCEMENT STRUCTURE (A BRACKET) IN THIS POSITION IN THE LT WING. THERE ARE EVEN SOME (PILOT DRILL) (PD) HOLES DRILLED AT THE FACTORY IN THE RIB AND HEAVY ATTACH ANGLE ON THE AFFECTED RT SIDE. IT WOULD APPEAR THAT BOTH LT AND RT BELLCRANKS WOULD EXPERIENCE THE SAME FORE-AF T FORCES BY AIR LOADS ON THE FLAPS. SO WHY REINFORCE ONLY ONE SIDE? IS IT POSSIBLE THAT THE FACTORY ASSY LINE NEGLECTED 1 H 7 1 3O 3 O A13CE E286 2008050800065 20080508 00065 CE 2008 5 8 2008FA0000289 1 20080401 G 5712 12210628 BULKHEAD CESSNA 177 177RG 2073709 CE LYC O360 IO360A1B6 41514 EA RT WING CRACKED B H5GR K NONE O OTHER IN INSP/MAINT 1 EA 07 52543 4336 177RG1206 DURING ROUTINE INSP, FOUND PART CRACKED. CHECKED (2) OTHER CARDINALS THAT HAPPENED TO BE IN OUR SHOP AND FOUND (1) OF T HEM TO HAVE A SIMILAR CRACK. THIS SECTION OF THE BULKHEAD IS THE ATTACH STRUCTURE FOR THE LOWER ATTACH ANGLE FOR THE IB FLAP DRIVE BELLCRANK. IT IS CURIOUS THAT THE FACTORY INSTALLED SOME EXTRA REINFORCEMENT STRUCTURE (A BRACKET) IN THIS POSITION IN THE LT WING. THERE ARE EVEN SOME (PILOT DRILL) (PD) HOLES DRILLED AT THE FACTORY IN THE RIB AND HEAVY ATTAC H ANGLE ON THE AFFECTED RT SIDE. IT WOULD APPEAR THAT BOTH LT AND RT BELLCRANKS WOULD EXPERIENCE THE SAME FOR-AFT FORCE S BY AIR LOADS ON THE FLAPS. SO WHY REINFORCE ONLY ONE SIDE? IS IT POSSIBLE THAT THE FACTORY ASSY LINE NEGLECTED TO IN 1 H 7 1 3O 3 O A20CE 1E10 2008050800059 20080508 00059 EU 2008 5 8 2008FA0000290 1 20080423 G 3210 DIN47108VERZ FASTENER DIAMON DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE1250299 EU MLG MISSING B NX4S K NONE O OTHER IN INSP/MAINT 1 SO 15 966WW 179 79 42106 DURING PREFLIGHT, THE CREW NOTICED THAT THE SMALL CIRCLIP (PN DIN471-08-VERZ) THAT SECURES THE MLG DOWNLOCK HOOK PIN IN POSITION WAS MISSING. MAINT JACKED THE AC AND INSTALLED A NEW CLIP. WHEN THIS CLIP IS NOT IN PLACE, THE PIN MIGRATES AFT AND IN SOME CASES DAMAGES THE AFT LIP OF THE WHEEL WELL MATERIAL. THIS OPERATOR HAS 9 OF THESE AIRPLANES AND THERE HAVE BEEN OTHER INSTANCES OF THIS DISCREPANCY. 1 L 7 2 3I 3 B RT A57CE E00069EN 2008050800089 20080508 00089 2008 5 8 2008FA0000291 4 20080424 G 3425 011N097200 UNKNOWN CESSNA 182 T182T 2072738 CE LYC O540 TIO540* 41532 EA COCKPIT MALFUNCTIONED B O OTHER O OTHER NR NOT REPORTED 1 WP 05 488PJ 75 T18208333 WHEN TURNING THE (CRS) COURSE KNOB, THE INNER KNOB (BARO) BAROMETRIC PRESSURE KNOB WOULD TURN ALSO. CHANGING THE ALTITU DE INDICATED. 1 H 7 1 3O 3 O NT 3A13 E14EA 2008050800067 20080508 00067 EA 2008 5 8 2008FA0000292 2 20080423 G 7414 CAM SLICK PIPER PA46 PA46350P 7104602 SO LYC O540 TIO540AE2A 41532 EA MAGNETO WORN C UXCR K NONE O OTHER TX TAXI/GRND HDL 1 SW 05 855P 49 07100592 4692014 L1291661A BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW. TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICUL T TO START. 1 L 7 1 3O 3 O RT A25SO E14EA 20080707 EA 2008 7 7 2008FA0000293 2 20080423 G 7414 CAM SLICK PIPER PA46 PA46R350T 7104610 SO LYC O540 TIO540AE2A 41532 EA MAGNETO WORN C UXCR K NONE O OTHER TX TAXI/GRND HDL 1 SW 05 855P 49 07100592 4692014 L1291661A BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW. TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICUL T TO START. 1 L 7 1 3O 3 O RT A25SO E14EA 20080707 EA 2008 7 7 2008FA0000294 2 20080423 G 7414 CAM SLICK PIPER PA46 PA46R350T 7104610 SO LYC O540 TIO540AE2A 41532 EA MAGNETO WORN C UXCR K NONE O OTHER TX TAXI/GRND HDL 1 SW 05 855P 49 07100592 4692014 L1291661A BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW. TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICUL T TO START. 1 L 7 1 3O 3 O RT A25SO E14EA 20080707 EA 2008 7 7 2008FA0000295 2 20080423 G 7414 CAM SLICK PIPER PA46 PA46R350T 7104610 SO LYC O540 TIO540AE2A 41532 EA MAGNETO WORN C UXCR K NONE O OTHER TX TAXI/GRND HDL 1 SW 05 855P 49 07100592 4692014 L1291661A BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW. TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICUL T TO START. 1 L 7 1 3O 3 O RT A25SO E14EA 2008050800109 20080508 00109 2008 5 8 2008FA0000296 4 20080425 G 3425 011N097200 UNKNOWN CESSNA 182 T182 2072736 CE LYC O540 TIO540* 41532 EA COCKPIT MALFUNCTIONED B O OTHER O OTHER NR NOT REPORTED 1 WP 05 488PJ 75 T18208333 WHEN TURNING THE INNER "CRS" COARSE KNOB THE OUTER "BARO" BAROMETRIC PRESSURE KNOB WOULD TURN ALSO. CHANGING THE ALTITUD E. 1 L 7 1 3O 3 O 3A13 E14EA 2008050800117 20080508 00117 2008 5 8 2008FA0000297 2 20080426 G 8550 ADAPTER OIL SYSTEM MISMANUFACTURED C K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 15 ORDERED SPIN ON OIL FILTER ADAPTER MODEL NR (TAFL). MACHINED PART WAS NOT COMPLETELY FINISHED. AN IMPORTANT HOLE IN TH E OIL PASSAGE DID NOT CONNECT WITH THE OIL DELIVERY LINE BECAUSE IT WASN'T DRILLED DEEP ENOUGH. MFG HAS BEEN COOPERATIV E AND AGREES TO REPLACE, HOWEVER IF ANY OF THESE DEFECTIVE PARTS HAVE BEEN INSTALLED IN THIS CONDITION, ENGINE FAILURE C OULD RESULT. (SN 28653L) 200805141 20080514 1 CE 2008 5 14 2008FA0000300 1 20080422 G 5312 45A3490111 BULKHEAD BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE FUSELAGE CRACKED B KX5R K NONE O OTHER IN INSP/MAINT 1 GL 15 400SF RK221 WHILE PERFORMING AN (A-B) INSPECTION FOUND RT AFT FUSELAGE BLEED AIR LINE ATTACH BRACKETS PULLED FROM AFT FUSELAGE BULKH EAD RESULTING IN CRACKS IN THE BULKHEADS AT FRAME STA 329.92. RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION. RECOMMEND CONTACTING MFG FOR REPAIR OPTIONS. THIS IS THE 5TH AIRCRAFT IN A ROW THAT THE BULKHEAD HAS BEEN CRACKED. TH E CRACK HAS BEEN FOUND ON BOTH SIDES OF THE AC. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 200805141 20080514 1 SO 2008 5 14 2008FA0000301 1 20080418 G 7160 U086126 MUFF LUSCOM 8 8E 8190112 SO CONT C85 C8512F 17008 SO RT CARB FAILED D K NONE O OTHER IN INSP/MAINT 1 NM 01 2004 561 5937 2244612C AFTER A FLIGHT, IT WAS NOTED THAT A PORTION OF SCAT HOSE WAS HANGING FROM THE BOTTOM OF COWLING OPENING. UPON INSPECTIO N IT WAS FOUND THAT THE CARBURETOR HEAT FLANGE HAD SEPARATED WITH THE SCAT HOSE ATTACHED WITH CLAMP FRO THE IB HALF OF T HE RT CARB HEAT MUFF. THE CARB HEAT MUFF HALVES WERE REMOVED AND INSPECTED. EXAMINATION OF THE FAILED ROUND DUCT FLANG E FOUND THE ENTIRE TUBE BROKE OFF AT THE CIRCUMFERENCE ALONG THE EDGE OF THE WELD. SECONDLY, THERE WERE ABOUT (6) SPIDE R LIKE CRACKS AROUND THE BROKEN HOLE WHICH PROPAGATED OUTWARD. A TOTAL OF APPROX 16 CRACKS, BROKEN TABS INCLUDING A PRE VIOUS (PATCH) REPAIR WERE NOTED ON BOTH IB AND OB MUFF HALVES. AN INNER MUFF RIB WHICH WAS TACK WELDED IN (3) PLACES HA 1 H 7 1 3O 3 O A694 E233 20080520 CE 2008 5 20 2008FA0000302 1 20080419 G 7921 649964 GASKET CESSNA 210 210L 2073448 CE CONT O520 IO520* 17032 SO OIL COOLER FAILED D O OTHER K FLUID LOSS CR CRUISE 1 SW 09 132WB 140 21060114 295375R THE OIL COOLER ADAPTER GASKET TAILED IN FLIGHT CAUSING (2) QUARTS OF OIL IN ONE HOUR TO BE PUMPED INTO THE ENGINE COWLIN G. THIS ENGINE IS A FACTORY REMANUFACTURED ENGINE WITH 140 HOURS SINCE REMAIN. ON INSPECTION AND DISASSEMBLY THE OIL C OOLER ADAPTER BOLTS DID NOT APPEAR TO BE TORQUED ENOUGH BUT THE GASKET ITSELF WAS BRITTLE AND LEAKING. THE ENGINE AND A DAPTER SURFACE WERE FLAT AND CLEAN. THE REPLACEMENT GASKET APPEARS TO BE A BETTER QUALITY. (K) 1 H 7 1 3O 3 O 3A21 E5CE 20080520 SO 2008 5 20 2008FA0000303 1 20080421 G 3222 86280003 DRAG LINK PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA NOSE GEAR CRACKED B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 5328L 4496108 NOSE GEAR DRAG LINK (PN 86280-003) CRACK LOCATED IN PIVOT BOLT HOUSING ON DRAG LINK WHERE A STANDARD (AN175-22A) BOLT AT TACHES NOSE GEAR DOWN LOCK (PN 86275-004). PROBABLE FATIGUE CRACK FROM NORMAL CYCLE TIME ON GEAR. RECOMMEND VISUAL INS P OF AREA AT A SPECIFIC PERIOD OF TIME TO BE DETERMINED BY THE MFG. (K) 1 L 7 2 3O 3 O A19S0 E286 20080520 2008 5 20 2008FA0000304 4 20080125 G 2300 G6860113 CONTROL HEAD AMD FALC50 FALCON50MYST 2730106 EU GARRTT TFE731 TFE731* 01518 WP COCKPIT BURNED D G O2 MASK DEPLOYED O OTHER DE DESCENT 1 SO 15 970S 238 DURING NORMAL DESCENT, AT JUST PRIOR TO 18000 FT, CREW NOTICED DISTINCT BURNING ELECTRICAL ODOR, OXY MASK PULLED AND THE SMOKE CHECKLIST WAS RUN. EMERGENCY PRIORITY REQUESTED UPON ARRIVAL, POSSIBLE LIGHT SMOKE IN COCKPIT ONLY WITH NONE IN THE CABIN. IN LESS THAN (1) MINUTE THE ODOR WAS NOT INCREASING AND SUBSEQUENTLY BEGAN TO CLEAR. THROUGH 10000 FT IT WA S NOTED THAT THE NR 2 NAV CONTROL HEAD WAS BLANK AND SUSPECTED AS THE PROBABLE CAUSE AS IT WAS CLOSE TO THE STRONGEST SM ELL. NO CIRCUIT BREAKERS POPPED. REMOVAL OF UNIT NAV/COM CONTROL HEAD (PN G6860113 SN298) NOTED ELECTRICAL BURNED SME LL WITH UNIT. PART HAS 9 HOURS SINCE REPAIR/MODIFICATION. UNIT TO BE SENT BACK FOR REPAIR. (K) 2 L 7 3 4F 4 F A46EU E6WE 200805141 20080514 1 CE 2008 5 14 2008FA0000305 1 20080429 G 3246 FN22A524 NUT RAYTHN DH125 HAWKER800XP 7150012 CE GARRTT TFE731 TFE731* 01518 WP WHEEL MISMANUFACTURED C K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 01 733A 258687 WHEEL LOCK NUT (P/N FN22A-524) WAS BEING INSTALLED TO COMPLY WITH SB 32-1374 AND WAS FOUND TO HAVE ZERO RUN ON TORQUE. T HIS IS A NEW PART AND HAS NEVER BEEN INSTALLED. ONLY ONE OF 24 BOUGHT FROM MFG THAT WAS BAD. THIS BOLT/NUT COMBINATION I S WHAT HOLDS THE (2) HALVES OF THE WHEEL TOGETHER. 2 L 7 2 4F 4 F RT A3EU E6WE 20080520 EU 2008 5 20 2008FA0000306 1 20080501 G 3520 17408031 OXYGEN MASK ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE731* 01518 WP CABIN COLLAPSED H K NONE O OTHER IN INSP/MAINT 1 GL 15 DURING AN OPS INSPECTION OF THE PASSENGER OXYGEN DROP DOWN MASKS, THERE WAS ONE THAT WOULD NOT LET OXYGEN FLOW THRU THE CONNECTION BETWEEN THE LARGER LINE ATTACHED TO THE BARBED FITTING ON THE OXYGEN DROP DOWN BOX AND THE SMALLER LINE THAT GOES TO THE MASK. IN THIS CASE THE SMALLER LINE WAS SQUEEZED SHUT AND WOULD NOT ALLOW OXYGEN TO FLOW TO THE MASK. THE PN IN QUESTION IS A 174080-31 REV "K". 2 M 7 2 4F 4 F A2SW E6WE 20080520 GL 2008 5 20 2008FA0000307 1 20080225 G 7921 646880 OIL COOLER CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO WORN C K NONE O OTHER IN INSP/MAINT 1 SO 15 476DA 300 THE OIL COOLER SUPPORT SHOE RUBBER COATING IS FAILING AND EATING INTO THE OIL COOLER .020 TO .040 OF AN INCH. IAW MM IT IS INSTALLED AT ENGINE ASSY AND ADJUSTED AFTER INITIAL TEST RUN. THERE IS NO PUBLISHED IN SERVICE INSTRUCTION FOR IT. I F THIS CONDITION IS NOT ADDRESSED BY REPLACEMENT OF SHOE AND OIL COOLER THE POSSIBILITY OF LOSS OF ENGINE OIL IS HIGH. T HE 5 AIRCRAFT THAT WE HAVE FOUND, ON THOSE AC THE OIL COOLER HAD TO BE REPLACED. IN ADDITION TO THAT WE HAVE TO REPLACE 18 OIL COOLER SHOE'S PN 632983. THE FAILURE TIME FROM NEW TO HAVING WORN INTO THE ENGINE OIL COOLER IS LESS THEN 600HRS TTAF. THIS IS DUE TO THE RUBBER PORTION OF SHOE FAILING AND ALLOWING THE STEEL PART TO CUT INTO THE OIL COOLER. 1 L 7 1 3O 3 O NT A00009CH E1CE 20080520 EU 2008 5 20 2008FA0000308 1 20080501 G 3520 17408031 OXYGEN MASK ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE731* 01518 WP CABIN COLLAPSED H K NONE O OTHER IN INSP/MAINT 1 GL 15 DURING AN OPS INSPECTION OF THE PASSENGER OXYGEN DROP DOWN MASKS, THERE WAS ONE THAT WOULD NOT LET OXYGEN FLOW THRU THE CONNECTION BETWEEN THE LARGER LINE ATTACHED TO THE BARBED FITTING ON THE OXYGEN DROP DOWN BOX AND THE SMALLER LINE THAT GOES TO THE MASK. IN THIS CASE THE SMALLER LINE WAS SQUEEZED SHUT AND WOULD NOT ALLOW OXYGEN TO FLOW TO THE MASK. THE PN IN QUESTION IS A 174080-31 REV "K". 2 M 7 2 4F 4 F A2SW E6WE 2008050800001 20080508 00001 SO 2008 5 8 2008FA0000309 1 20080507 G 2720 2223900 TORQUE TUBE PIPER PA24 PA24260 7102406 SO RUDDER CONTROL BROKEN B D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 NM 05 9506P 3404 245023 DURING MAINTENANCE RUNUP AND TAXI CHECK AFTER MAINTENANCE THE LEFT RUDDER TORQUE TUBE BROKE OFF. IT APPEARED TO HAVE BEE N CRACKED FOR SOME TIME PRIOR TO FAILING DURING TAXI. IT IS SUGGESTED THAT THE AREA BE CLEANED AND INSPECTED WITH A 10X MAGNIFYING GLASS. A BORESCOPE WITH A SIDE VIEW END COULD ALSO BE INSERTED IN THE TUBE TO INSPECT IT FROM THE INSIDE. IF THIS HAD HAPPENED DURING LANDING AND HAD BROKEN AT INITIAL BRAKE APPLICATION, THE AIRCRAFT WOULD PROBABLY HAVE DEPARTED THE RUNWAY. 1 L 7 1 3O 1A15 20080522 NE 2008 5 22 2008FA0000310 2 20080506 G 7200 0319008000 ENGINE UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIUS2F 60010 NE MAKING METAL D A UNSCHED LANDING J WARNING INDICATION DE DESCENT 1 SO 07 197CB 278 84 1448 34546 ENGINE CHIP DETECTOR LIGHT ILLUMINATED. INSPECTED CHIP DETECTORS, AND FOUND METAL SLIVERS ON MODULE NR 1 CHIP DETECTOR. ENGINE REMOVED FROM SERVICE. 1 G 7 2 3U 3 U NC R0001RD E34NE 20080522 NE 2008 5 22 2008FA0000311 2 20080502 G 7261 LINE AEROSP SA365 SA365N1 8680668 EU TMECA ARRIEL ARRIEL2C 60054 NE P2 OIL LOOSE C E A ENGINE SHUTDOWN UNSCHED LANDING K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NR NOT REPORTED 1 EA 07 95MD 2551 50 6320 24072 ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNIN G LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED. 1 G 7 2 3U 4 U H10EU E00054EN 20080522 NE 2008 5 22 2008FA0000312 2 20080502 G 7261 LINE AEROSP SA365 SA365N1 8680668 EU TMECA ARRIEL ARRIEL2C 60054 NE P2 OIL LOOSE C E A ENGINE SHUTDOWN UNSCHED LANDING K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NR NOT REPORTED 1 EA 07 95MD 2551 50 6320 24072 ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNIN G LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED. 1 G 7 2 3U 4 U H10EU E00054EN 20080522 NE 2008 5 22 2008FA0000313 2 20080502 G 7261 LINE AEROSP SA365 SA365N1 8680668 EU TMECA ARRIEL ARRIEL2C 60054 NE P2 OIL BACKED OUT C E A ENGINE SHUTDOWN UNSCHED LANDING K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NR NOT REPORTED 1 EA 07 95MD 2551 50 6320 24072 ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNIN G LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED. 1 G 7 2 3U 4 U H10EU E00054EN 20080522 NE 2008 5 22 2008FA0000314 2 20080502 G 7261 LINE AEROSP SA365 SA365N1 8680668 EU TMECA ARRIEL ARRIEL2C 60054 NE P2 OIL BACKED OUT C E A ENGINE SHUTDOWN UNSCHED LANDING K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NR NOT REPORTED 1 EA 07 95MD 2551 50 NA 6320 24072 ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNIN G LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED. 1 G 7 2 3U 4 U H10EU E00054EN 20080602 CE 2008 6 2 2008FA0000317 1 20080506 G 3246 10320400AN53 BOLT PARKERHANFIN RAYTHN 36 G36 7150061 CE ZONE 700 SHEARED B K NONE O OTHER IN INSP/MAINT 1 CE 07 222GL 479 479 E3763 THE PILOT REPORTED A "POP" AS HE WAS GROUND HANDLING THE AIRCRAFT ON THE RAMP (IN A STRAIGHT DIRECTION USING AN AIRTUG). FURTHER INVESTIGATION REVEALED 1 NUT/BOLT COMBINATION HAD SHEARED ON THE INBOARD WHEEL HALF OF THE RIGHT MAIN LANDING GEAR ASSEMBLY. THE BOLT HAD SUBSEQUENTLY BACK OUT APPROXIMATELY 1/4 INCH. THIS AIRCRAFT HAS BEEN THROUGH 1 ANNUAL INSP ECTION AND HAS NEVER HAD THE WHEEL HALVES DISASSEMBLED. UPON DISCOVERY OF THE SHEARED BOLT, THE LEFT AND RIGHT WHEELS W ERE DISASSEMBLED, CLEANED, INSPECTED AND REASSEMBLED WITH NEW BOLTS AND NUTS. DURING DISASSEMBLY OF THE WHEEL HALF RETA INING BOLTS IT WAS NOTED THAT VERY LITTLE FORCE WAS REQUIRED TO BREAK THE NUTS LOOSE. THE NOSE WHEEL WAS THEN CHECKED F 1 L 7 1 3O RT 3A15 20080603 EA 2008 6 3 2008FA0000318 2 20080422 G 8520 13B27134 CRANKSHAFT PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA ENGINE CRACKED B UC2R A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 GL 19 4149T 2843192 AC WAS FLYING AT 5000 FT, WHEN ENGINE STARTED TO LOSE POWER AND FAILED. AC LANDED SAFELY IN A FIELD. ENGINE WAS FOUND TO BE LOCKED UP. ENGINE WAS DISASSEMBLED AND COMPONENTS INSPECTED. CRANKSHAFT WAS FOUND TO HAVE CRACK, CAUSING ENGINE TO LOCK UP. PROBABLE CAUSE: UNDERTERMINED AT THIS TIME. (K) 1 L 7 1 3O 3 O 2A13 E286 20080603 CE 2008 6 3 2008FA0000320 1 20080425 G 5100 S34691 BEARING CESSNA 177 177RG 2073709 CE LYC O360 IO360A1B6 41514 EA MCAULY 2D34C B2D34C207 GL ACTUATOR FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 09 52156 4247 1533 177RG1180 L1699351A 771391 WHERE THE ROD END BEARING ATTACHES TO THE LATERAL BOLT, FWD. THIS BEARING (S34691 FAILED AT THE BEARING END. THIS BEAR ING IS UNDER EXTREEM TENSION LOAD AND WAS ORIGINAL. AGE WAS A FACTOR IN FAILING. REPLACING THIS BEARING AT 1000 HR INT ERVALS IS NECESSARY. DATE OF THE ACTUATOR WAS 10/77. (K) 1 H 7 1 3O 3 O A20CE 1E10 5 C P7EA 2008051500001 20080515 00001 CE 2008 5 15 2008FA0000321 1 20080425 G 5711 00011001316 SPAR CAP BEECH BEECH 90 E90 1152914 CE RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 05 692M 8812 400 LW228 THE CRACK EMANATES FROM THE 5TH RIVET OUTBOARD OF THE LOWER FORWARD WING BOLT FITTING, (4TH RIVET FROM END OF SPAR CAP)I N THE REAR ROW OF RIVETS, & EXTENDS TO THE TRAILING EDGE OF CAP. THE A/C PASSED 2-400 HR WING SIRM INSPECTIONS. THE CRAC K WAS DETECTED AT THE CURRENT 400 HR INTERVAL WING SIRM INSPECTION. NOTE:BEECH HAS REDUCED INTERVAL FOR EDDY CURRENT INS PECTION ITEM OF SPAR CAP TO 200 HRS DUE TO RECURRENCE OF THIS PROBLEM. REF 8110-4 FOR N776DC FOR SIMILAR DETAILS. A/C IS ON USFS CONTRACT. 1 L 7 2 3T 3A20 20080602 SO 2008 6 2 2008FA0000322 1 20080505 G 8010 701122223 SOLENOID PIPER PA28 PA28161 7102803 SO STARTER SHORTED B H DEACTIVATE SYST/CIRCUITS S AFFECT SYSTEMS TX TAXI/GRND HDL 1 GL 21 238ND 817 2842101 WHEN MASTER SWITCH TURNED ON PROP BEGAN TO ROTATE UNCOMMANDED. TROUBLESHOT TO STUCK STARTER SOLENOID. SOLENOID REPLACE D, OPS CHECK GOOD. 1 L 7 1 3O 2A13 20080602 SW 2008 6 2 2008FA0000323 1 20080504 G 2720 183M SLEEVE BBAVIA 7 7GCBC 1220601 SW LYC O320 O320A2D 41508 EA RUDDER CABLE CRIMPED D A UNSCHED LANDING O OTHER TX TAXI/GRND HDL 1 SO 03 53718 86775 RIGHT RUDDER CABLE SEPARATED AT RUDDER BELLCRANK DURING RECOVERY OF INTENTIONAL LEFT SPIN. CABLE APPARENTLY PULLED OUT OF NICOPRESS SLEEVE. AIRPLANE WAS LANDED AT KCHA, WITHOUT INCIDENT, AFTER DECLARING AN EMERGENCY. 1 H 7 1 3O 3 O NC A759 E274 20080602 SW 2008 6 2 2008FA0000324 1 20080507 G 3110 011097203 DISPLAY BBAVIA 7 7DC 2110116 SW INSTRUMENT PANEL DEFECTIVE D O OTHER O OTHER NR NOT REPORTED 1 NM 03 555Y 93 7DC2078 PRIMARY FLIGHT DISPLAY PANEL HAS A MALFUNCTION IN THE COARSE/BAROMETRIC PRESSURE ADJUSTMENT KNOB. THE DESIGN INCORPORAT ES A DUAL FUNCTION TYPE CONTROL KNOB. THE CENTER KNOB ADJUSTS THE DESIRED NAVIGATIONAL COARSE DISPLAYED ON THE HSI NAV DISPLAY. THE OUTER KNOB ADJUSTS THE PRIMARY ALTIMETER BAROMETRIC PRESSURE SETTING. AT TIMES DURING FLIGHT ADJUSTMENT O F THE INNER COARSE KNOB RESULTS IN AN INADVERTENT CHANGE IN THE BAROMETRIC PRESSURE. THIS MALFUNCTION CAN BE QUITE DANG EROUS, ESPECIALLY WHEN SHOOTING AN INSTRUMENT APPROACH, PILOT CHANGES COARSE HEADING DURING AN APPROACH AND MAY, WITHOUT KNOWING, CHANGE THE BAROMETRIC PRESSURE THUS CAUSING THE ALTITUDE DISPLAY TO BE INACCURATE. 1 H 7 1 3O A759 20080602 CE 2008 6 2 2008FA0000326 1 20080425 G 5711 00011001316 SPAR CAP BEECH 90 E90 1152914 CE WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 05 776DC 8204 181 LW235 THE CRACK EMANATES FROM THE 5TH RIVET OUTBOARD OF THE LOWER FORWARD WING BOLT FITTING, 4TH RIVET FROM END OF SPAR CAP, I N THE FRONT ROW OF RIVETS, AND EXTENDS TO THE LEADING EDGE OF CAP. THE A/C PASSED 2-400 HOUR WING SIRM INSPECTIONS. 18 1 HRS INTO NEXT INTERVAL WAS WHEN CRACK WAS DETECTED DURING ROUTINE MAINTENANCE. BEECH HAS REDUCED INTERVAL FOR EDDY CU RRENT INSP OF SPAR CAP TO 200 HRS DUE TO RECURRENCE OF THIS PROBLEM REF 8110-4 FOR N692M FOR SIMILAR DETAILS. A/C IS ON USFS CONTRACT. 1 L 7 2 3T 3A20 20080603 EU 2008 6 3 2008FA0000330 1 20080502 G 3242 244755 BRAKE DISC BFGOODRICH PILATS PC12 PC12 7090550 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL BROKEN B K NONE O OTHER IN INSP/MAINT 1 NE 05 708AF 1656 0563 708 PR0583 KX309 WHILE REMOVING RIGHT MAIN WHEEL ASSEMBLY DISCOVERED THE OUTBOARD BRAKE DISC OF THE RIGHT BRAKE BROKEN INTO TWO PIECES. REPLACED RIGHT BRAKE ASSEMBLY. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20080603 EU 2008 6 3 2008FA0000331 1 20080506 G 3242 244755 BRAKE DISC BFGOODRICH PILATS PC12 PC12 7090550 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL BROKEN B K NONE O OTHER IN INSP/MAINT 1 NE 05 776AF 1103 0715 776 PR0657 KX423 FLIGHT CREW REPORTS RIGHT BRAKE GRABBING. REMOVED RIGHT MAIN TIRE ASSEMBLY AND DISCOVERED THE OUTBOARD BRAKE DISC WAS B ROKEN INTO TWO PIECES. REPLACED THE RIGHT BRAKE ASSEMBLY. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20080603 EU 2008 6 3 2008FA0000332 1 20080506 G 3242 244755 BRAKE DISC BFGOODRICH PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL BRAKE ASSY BROKEN B K NONE O OTHER IN INSP/MAINT 1 NE 05 591AF 875 875 0213 591 PR0454 KX164 FLIGHT CREW REPORTS LEFT BRAKE GRABBING. REMOVED LEFT MAIN TIRE ASSEMBLY TO INVESTIGATE DISCREPANCY AND DISCOVERED THE OUTBOARD BRAKE DISC BROKEN INTO THREE PIECES. REPLACED THE LEFT BRAKE ASSEMBLY. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20080603 EU 2008 6 3 2008FA0000333 1 20080425 G 3520 INDICATOR ISRAEL 1124 1124 4500102 EU OXYGEN MASK INOPERATIVE C K NONE L NO TEST IN INSP/MAINT 1 AL 05 500KE 379 360 PASSENGER OXYGEN MASK FLOW INDICATOR INOPERATIVE. THIS UNIT CAME FROM LOT LC 0521 K OR LOT LC 0526K 2 M 7 2 4F A2SW 20080701 CE 2008 7 1 2008FA0000335 1 20080418 G 2140 88D7015EL TUBE BEECH 58 58 1152740 CE CONT O550 IO550C SO MCAULY 3AF32C 3AF32C512 GL HEATER CRACKED B YWBR O OTHER O OTHER NR NOT REPORTED 1 WP 17 873AN 453 A04010003 TH1680 WHILE PERFORMING A PRESSURE DECAY TEST IAW AD2004-21-05, THE COMBUSTION TUBE WOULD NOT AINTAIN PRESSURE AND AIR LEAKING WAS NOTED. INVESTIGATION FOUND A .75 INCH LONG CRACK IN THE AFT END OF THE COMBUSTION TUBE NEAR THE RADIUS. CRACK MAY HA VE BEEN CAUSED BY STRESS INDUCED WHILE FORMING THE END CAP ALONG WITH NORMAL HEATING AND COOLING OF THE HEATER. HEATER HAD 98 HOURS SINCE LANST PRESSURE TEST. A FACTORY REBUILT UNIT WAS INSTALLED AND AIRCRFAT RETURNED TO SERVICE. 1 L 7 2 3O 3 O 3A16 E3SO 5 C P22EA 20080701 EU 2008 7 1 2008FA0000336 1 20080527 G 7920 307194912 PUMP AMD FALC50 FALCON50MYST 2730106 EU GARRTT TFE731 TFE7313 01518 WP ENGINE OIL FAILED D O OTHER O OTHER NR NOT REPORTED 1 SO 15 970S 70 238 IAW MFG RECOMMENDATION, WE REMOVED THE ENGINE OIL PUMP, PN 3071949-11, AND INSTALLED PN 3071949-12 PUMP BECAUSE OF AN I SSUE (ENGINE HIDING OIL) NOT ABLE TO GET A PROPER OIL QUANITITY READING AFTER SHUTDOWN. MFG SAID THE PN 3071949-12 PUMP SHOULD CORRECT THAT, WHICH IT DID. THE PUMP WE INSTALLED PN 3071949-12, SN 7018, TSO 20 HOURS WITH A ZERO TIME SINCE REP AIRED 8130 FROM MFG TRACKING NR 41056, WO NR 877515-001, DATED 2-4-2008 WITH NO FAULT FOUND. AFTER APPROXIMATELY 10 HOUR S, WE HAD WRITE UP OF OIL PRESSURE FLUCTUATING. GROUND RUN AND COULD NOT DUPLICATE, SO WE SWAPPED OIL PRESSURE TRANSMITT ERS AND GAUGE WITH OTHER ENGINES FOR TROUBLESHOOTING. THEN THE AIRCRAFT FLEW APPROXIMATELY 38 HOURS WITH EVERYTHING NORM 2 L 7 3 4F 4 F A46EU E6WE 20080701 SW 2008 7 1 2008FA0000337 1 20080701 G 6400 206011725011 ROD BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL TAIL ROTOR CHAFED B ULXR O OTHER O OTHER NR NOT REPORTED 1 WP 01 83WP 51359 DURING AN INSPECTION THE THE TAIL ROTOR PITCH CONTROL TUBE SLEEVES, WE DISCOVERED THAT BELLCRANK PN 206-001-763-001 HAD BEEN CHAFED INTO BY THE RIVET SECURING THE ROD END OF ROD ASSEMBLY PN 206-011-725-001. THIS WEAR OCCURS WHEN LEVER ASSEM BLY PN 206-011-722-105 PIVOT DURING CONTROL MOVEMENTS, CHANGING THE PLANE OF THE ROD. THE MM DOES NOT TELL YOU WHICH WAY TO INSTALL THE ROD, HOWEVER, ALL OF THE ILLUSTRATIONS SHOW THE RIVETED END OF THE ROD TO BE CONNECTED TO THE BELLCRANK. PLEASE SEE BHT-206L-SERIES-IPB, FIG 64-1 AND FIG 67-12 AND BHT-206L-MM, PARA 67-63, FIG 67-17 DETAIL D, PARA 64-20 AND FIG 64-14. THIS CAN BE CURED BY INSTALLING THE ROD WITH THE ADJUSTABLE END CONNECTING TO THE LEVER. 1 G 7 1 3U 3 U H2SW E1GL 20080701 SW 2008 7 1 2008FA0000338 1 20080530 G 6200 407310104103 SPRING BELL BELL 407 407 1182206 SW ALLSN 250C 250C47B GL FRAHM ASSY DAMAGED B O OTHER O OTHER NR NOT REPORTED 1 WP 01 701WP 53542 ONE OF EIGHT SPRINGS BROKEN CAUSING DAMAGE TO LOWER HOUSING. LOWER HOUSING, SPRINGS 2 EA. AND PLUGS WERE REPLACED. UNKNO WN WHI SPRING BROKE, SPRING WAS FOUND BROKEN ON SCHEDULED 300 HOUR INSPECTION. (K) 1 G 7 1 3U 3 U O H2SW E1GL 20080701 CE 2008 7 1 2008FA0000339 1 20080512 G 5610 10138402521 WINDSHIELD BEECH 90 C90 1152913 CE COCKPIT CRACKED D O OTHER O OTHER NR NOT REPORTED 1 EA 25 585R 4772 LJ1169 PILOT WAS ON TAKEOFF AND HAD JUST LEVELED OUT FOR FLIGHT AND WINDSHIELD CRACKED ON THE INNER PANE. PILOT RETURNED TO BAS E AND THE WINDSHIELD WAS REPLACED. WINDSHIELD WAS SENT TO INSURANCE CO. LAB FOR EVALUATION. (K) 1 L 7 2 3T 3A20 20080701 EU 2008 7 1 2008FA0000340 1 20080512 G 3233 C239251103 ACTUATOR AMD FALC50 FALCON50MYST 2730106 EU MALF MALFUNCTIONED B JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 900KE 9497 052 WHILE PERFORMING THE LANDING GEAR GRAVITY EXTENSION CHECK (MP32-470) DURING THE (B) INSPECTION IT WAS DISCOVERED BOTH MA IN LANDING GEAR ACTUATORS WOULD EXTEND PARTIALLY (APPROXIMATELY 30 PERCENT OF NORMAL TRAVEL) AND STOP. FURTHER TROUBLESH OOTING REVEALED IT TOOK EXTREME PRESSURE TO MOVE THE ACTUATORS TO THE DOWN AND LOCKED POSITION. THE ACTUATORS NORMALLY F REE-FALL TO THE EXTENDED POSITION AND NEED TO BE PULLED INTO THE DOWN AND LOCKED POSITION. BOTH ACTUATOR WERE REPLACED W ITH OVERHAULED ACTUATORS. THE FAULTY ACTUATORS WERE SENT TO THE MFG REPAIR FACILITY FOR TEARDOWN AND EVALUATION. THE ACT UATOR PART AND SERIAL NUMBER ARE AS FOLLOWS: LT ACTUATOR/ PN C23925-1103, SN U22, RT ACTUATOR/ PN C23926-1103. 2 L 7 3 4F A46EU 20080701 EU 2008 7 1 2008FA0000341 1 20080512 G 3233 C239261103 ACTUATOR AMD FALC50 FALCON50MYST 2730106 EU MLG MALFUNCTIONED B JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 900KE 052 WHILE PERFORMING THE LANDING GEAR GRAVITY EXTENSION CHECK (MP32-470) DURING THE (B) INSPECTION IT WAS DISCOVERED BOTH MA IN LANDING GEAR ACTUATORS WOULD EXTEND PARTIALLY (APPROXIMATELY 30 PERCENT OF NORMAL TRAVEL) AND STOP. FURTHER TROUBLESH OOTING REVEALED IT TOOK EXTREME PRESSURE TO MOVE THE ACTUATORS TO THE DOWN AND LOCKED POSITION. THESE ACTUATORS NORMALLY FREE-FALL TO THE EXTENDED POSITION AND NEED TO BE PULLED INTO THE DOWN AND LOCKED POSITION. BOTH ACTUATORS WERE REPLACE D WITH OVERHAULED ACTUATORS. THE FAULTY ACTUATORS WERE SENT TO THE MANUFACTURER`S REPAIR FACILITY FOR TEARDOWN AND EVALU ATION. LT ACTUATOR, PN C239251103, SN U22 / RT ACTUATOR PN C239261103, SN U22. (K) 2 L 7 3 4F A46EU 20080715 GL 2008 7 15 2008FA0000343 1 20080618 G 5210 HINGE DIAMON DA40 DA40 2990002 GL LYC O360 IO360LYC* 41514 EA HARTZL HCC2Y HCC2YR1 GL DOOR CRACKED G O OTHER O OTHER NR NOT REPORTED 1 WP 07 686US 40640 L3262751A CH39554B FOUND CRACKS IN AFT DOOR HINGE. (K) 1 L 7 1 3O 3 O NT A47CE 1E10 5 C P920 20080715 GL 2008 7 15 2008FA0000345 1 20080616 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 CL CLIMB 1 WP 07 605US 536 40675 L3276151A CH399768 ON TAKEOFF CLIMB OUT, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1 L 7 1 3O 3 O NT A47CE 1E10 5 C P920 20080715 GL 2008 7 15 2008FA0000346 1 20080625 G 5210 D4152210000 HINGE DIAMON DA40 DA40 2990002 GL REAR CABIN DOOR CRACKED D O OTHER O OTHER NR NOT REPORTED 1 WP 07 4189U 991 40768 REAR HINGE DEVELOPING CRACKS IN FIBERS. NORMAL OPERATING CONDITION. PROBABLE CAUSE IS REAR HOLD OPEN CYLINDER CAUSING STRESS ON HINGE POINT. (K) 1 L 7 1 3O NT A47CE 20080715 GL 2008 7 15 2008FA0000347 1 20080625 G 5210 D4152210000 HINGE DIAMON DA40 DA40 2990002 GL REAR CABIN DOOR CRACKED D O OTHER O OTHER NR NOT REPORTED 1 WP 07 4191M 40769 REAR HINGE DEVELOPING CRACKS IN FIBERS. NORMAL OPERATING CONDITION. PROBABLE CAUSE IS REAR HOLD OPEN CYLINDER CAUSING ST RESS ON HINGE POINT. (K) 1 L 7 1 3O NT A47CE 20080715 CE 2008 7 15 2008FA0000348 1 20080318 G 2711 EM408810 ACTUATOR RAYTHN 390 390 7150030 CE ROLL TRIM MALFUNCTIONED B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 837JM 758 RB169 IN CONJUNCTION WITH REPAIRS FOR UNCOMMANDED ROLL, TRIM ACTUATION AT KMDW REPLACED RT ROLL TRIM ACTUATOR (HBC PN 390-3810 090010) WITH RAPID SUPPLIED REPAIRED UNIT. ATTEMPTED TO PERFORM ROLL TRIM FUNCTIONAL CHECKS IAW THE 390 MM 27-10-00-501 AFTER ACTUATOR REPLACEMENT BUT FOUND ROLL TRIM CIRCUIT BREAKER TRIPPING UPON POWER APPLICATION. (K) 1 L 7 2 3F RT A00010WI 20080715 CE 2008 7 15 2008FA0000349 1 20080502 G 3220 12434262 TORQUE LINK CESSNA 210 210M 2073450 CE NLG CRACKED B ONFR K NONE O OTHER IN INSP/MAINT 1 EA 05 70HG 4609 21062120 OUR REPAIR STATION HAS REPLACED SEVERAL OF THESE SAME UPPER TORQUE LINKS DUE TO FINDING THEM BENT AT INSPECTION (APPROX 5 TOTAL) THIS IS THE FIRST ONE FOUND CRACKED. PROBABLE CASUE IS WHAT I BELIEVE IS LANDING IMPACT WITH MORE THAN RECOMME NDED STRUT ESTENSION (5.00 INCH MAX) IAW SRM FIGURE 5-15 WHICH IS ADJUSTABLE BY ADDING SHIMS (ITEM 15) MAXIMUM OF THREE, PN 12436182 IAW THE NOTE OF FIGURE 5-18 OF THE SRM. (K) 1 H 7 1 3O 3A21 20080715 CE 2008 7 15 2008FA0000350 1 20080429 G 3520 38101550360 HOSE CESSNA 500 560CESSNA 2076750 CE LAV OXYGEN LEAKING B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 501CW 5600050 DURING SCHEDULED PHASE INSPECTION NOTED HOSE ASSY. SUPPLYING OXYGEN TO LAVATORY OXYGEN MASK COMPARTMENT FROM MAIN UPPER CABIN OXYGEN LINE ASSY LEAKING. FURTHER INVESTIGATION SHOWED MULTIPLE HOLES IN OXYGEN HOSE ASSY FLEXIBLE HOSE SECTION. SUSPECT HOSE ASSY DETERIORATED FROM AGE AND POSSIBLY HEAT FROM AIRCRAFT BEING PARKED OUTDOORS FOR EXTENDED PERIODS. RECO MMEND TECH CLOSELY INSPECT CABIN OXYGEN SYSTEM COMPONENTS DURING SCHEDULED INSPECTIONS ON OLDER AND HIGH-TIME SERIES AC FOR AGE RELATED DEFECTS. (K) 2 L 7 2 4F RT A22CE 20080715 CE 2008 7 15 2008FA0000351 1 20080429 G 5230 991434317 LATCH CESSNA 500 560CESSNA 2076750 CE CARGO DOOR BROKEN B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 501CW 5600050 DURING SCHEDULED PHASE INSPECTION, FOUND AFT BAGGAGE COMPARTMENT DOOR AFT LATCH ASSY, NOT LOCKING. FURTHER INVESTIGATION FOUND AFT DOOR LATCH ASSY, BROKEN. REPLACED LATCH ASSY W/ SERVICEABLE LATCH ASSY, OPERATIONS NORMAL. RECOMMEND FURTHER INVESTIGATION BY MFG TO DETERMINE IF MFGED LATCHES PRONE TO EARLY FATIGUE FAILURE AND ISSUE SB TO REPLACE IF HIGH FAILU RE RATES NOTED. TECHS SHOULD INSPECT THESE LATCHES CLOSELY DURING SCHEDULED PHASE CHECKS TO PREVENT POSSIBLE DOOR OPENI NG IN FLIGHT. (K) 2 L 7 2 4F RT A22CE 20080715 NM 2008 7 15 2008FA0000352 1 20080514 G 5712 41513017 RIB UNIVAR 415 415D 0420306 NM LT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 09 94052 3674 1375 SUBJECT PART WAS FOUND TO BE CORRODED WHILE PERFORMING INSPECTION IAW AD 2002-26-02 (D) (3 YEAR REQUIREMENT). LEFT REAR CENTER SECTION RIB, CORRODED AROUND LARGE HOLE THROUGH WHICH PITOT AND STATIC LINES, AND NAV LITE WIRE PASS TO OUTER WIN G PANEL. REMOVED DEFECTIVE PART AND INSTALLED NEW PART (415-13017) SUPPLIED BY MFG. CAUSE OF CORROSION UNKNOWN, AS SURR OUNDING STRUCTURE WAS NOT AFFECTED. CORRODED PART IS UNTREATED (NOT CORROSION PROOF IN ANY WAY). SUGGEST WING CENTER SEC TION OF THESE AIRCRAFT BE CORROSION PROOFED WITH ACF-50 OR WITH CORROSION X OR EQUIVALENT COMPOUND TO PREVENT FURTHER PR OBLEMS OF THIS NATURE. (K) 1 L 7 1 3O A787 20080715 CE 2008 7 15 2008FA0000353 1 20080516 G 3233 SHAFT BEECH 80 65A80 1152808 CE LYC O540 IGSO540B1A 41532 EA NLG ACTUATOR LACK OF LUBE D O OTHER O OTHER AP APPROACH 1 SW 13 6AQ 4434 LD214 NOSE LANDING GEAR WOULD NOT DEPLOY ON APPROACH TO LANDING. AFTER NLG REMOVAL, IT WAS DISCOVERED THAT THE NLG ACTUATOR DR IVE SHAFT PN 50820218 INTERNAL SPLINE WAS WORN AND SHEARED. LUBE POINTS ON DRIVE SHAFT TO LUBE SPLINES TO REDUCE WEAR. (K) 1 L 7 2 3O 3 O 3A20 1E7 20080715 NE 2008 7 15 2008FA0000354 3 20080603 G 6110 7826691 BOLT DHAV DHC8 DHC8202 2809007 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE PROPELLER SHEARED B S88R K NONE O OTHER IN INSP/MAINT 1 SO 19 802MR 1613 20050318 612 PCEAG0125 20050318 WHILE DOING A RGB CHANGE ON THE NR 1 ENGINE OF DASH-8, N802MR, DURING REINSTALLATION OF THE PROPELLER WHILE DOING THE TO RQUE SEQUENCE, WE BROKE ONE PROP MOUNTING BOLT. WE SENT THE HUB OUT FOR REPAIR AND SENT THE TORQUE WRENCH TO THE CAL PLA CE TO BE VERIFIED. THEY REPLACED 3 MOUNTING BOLTS. WHEN THE HUB CAME BACK FROM REPAIR WE PROCEEDED TO INSTALL THE BLADE USING A DIFFERENT TORQUE WRENCH. AS WE WERE DOING THE CRISSCROSS PATTERN, I NOTICED THAT THE BOLTS THAT WERE NOT REPLACE D WOULD NOT GRAB TORQUE THE TORQUE WRENCH WOULD CLICK ONCE BUT ON THE SECOND CLICK IT WOULD MOVE OVER .2500 OF A TURN, THE 3 NEW SCREWS CLICK FINE CLICK CLICK. WE FIGURED THAT THE BOLTS HAD JUST BEEN REMOVED AND REINSTALLED AND THEY WERE 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080715 2008 7 15 2008FA0000355 4 20080513 G 2215 L109BBM ACTUATOR SKRSKY S76 S76B 8143007 NE AUTOPILOT SYS MALFUNCTIONED G O OTHER F P FLT CONT AFFECTED NO WARNING INDICATION CR CRUISE 1 EA 63 150US 760312 PILOT HSI SPINS WILDLY TO THE RIGHT AND DISPLAYS A HEADING FLAG. PILOT`S FLIGHT DIRECTOR MAINTAINS HEADING AND ALTITUDE FOR APPROXIMATELY 30 SECONDS THEN LOSES ALL INPUT. THE AIRCRAFT THEN TURNS AND DESCENDS AT WILL. WHILE THIS HAPPENS THE LEFT ANTI-TORQUE PEDAL DRIVES FORWARD PLACING THE HELICOPTER OUT OF TRIM. THE PILOT SIDE HEADING COMMAND BARS JUMP WILD LY AND TURN TO THE LEFT WHILE THE AIRCRAFT IS IN STRAIGHT AND LEVEL FLIGHT. ONCE THE FLIGHT DIRECTOR LOSES INPUT THE CYC LIC TRIM WILL NOT RESPOND IN THE PITCH OR ROLL CHANNEL. TRIED TO DISENGAGE AND RE-ENGAGE THE SYSTEM BUT THE SAME PROBLEM RETURNS. THE AIRCRAFT REQUIRES MANUAL PEDAL INPUT TO REMAIN IN TRIM. NO EMERGENCY ACTIONS WERE TAKEN OR NEEDED DURING T 1 G 7 2 4U H1NE 20080715 GL 2008 7 15 2008FA0000357 1 20080501 G 3222 11907005 STRUT CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO NLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 241CP 516 201713 360239 AFTER INSPECTION OF AIRCRAFT AFTER A REPORT OF NOSE WHEEL PANT DAMAGE ON LANDING. I FOUND THE UPPER LEFT ARM ON THE NOSE STRUT WAS SERIOUSLY CRACKED. THE CRACK RAN FROM THE TOP OF THE ARM ON THE NOSE STRUT WAS SERIOUSLY CRACKED. THE CRACK R AN FROM THE TOP OF THE ARM. JUST FORWARD OF THE STRUT DATA PLATE, THROUGH THE ENTIRE ARM AND STOPPED AT THE BOTTOM WHE RE A GUSSET WAS WELDED. THE CRACK CONTINUED TO RUN PARALLEL TO GUSSET FOR ABOUT .5 OF AN INCH. A SMALLER CRACK WAS ALSO FOUND ON THE RIGHT ARM STARTING AT THE SAME POINT AS THE LEFT ARM BUT ONLY MEASURED ABOUT .5 OF AN INCH. ALSO FOUND NOS E WHEEL STOP AND NOSE FORK WAS DAMAGED. POSSIBLE CAUSE COULD BE REPEATED UNREPORTED HARD LANDINGS. WOULD RECOMMENDED ALL 1 L 7 1 3O 3 O NT A00009CH E1CE 20080715 EA 2008 7 15 2008FA0000358 1 20080519 G 2750 60093000123 CONTROL BOX CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF343A 30066 NE T/E FLAPS FAILED C O OTHER J WARNING INDICATION AP APPROACH 1 SO 03 779AZ 12 5176 CREW REPORTED FLAP FAILURE DURING APPROACH APPROXIMATELY 8 HOURS AFTER INSTALLATION. RESET SYSTEM AND FLAPS WORKED FINE. FLEW AIRCRAFT HOME AND NO DISCREPANCIES. UNABLE TO DUPLICATE PROBLEM UNTIL SEVERAL WEEKS LATER DURING MAINTENANCE RUN. FLAPS WOULD IMMEDIATELY FAIL, INTERMITTENTLY. PLACED ELECTRICAL RECORDER ON SYSTEM WITH BREAKOUT BOX AND FOUND INTERMIT TENT SIGNAL LOSS ON SIGNAL 2 WHEN INSTALLED ON LEFT WING. SWAPPED UNIT TO RIGHT WING AND FLAPS WOULD CONSISTANTLY FAIL I NTERMITTENTLY. THIS TIME FOUND SIGNAL LOSS ON RIGHT WING, SIGNAL 1. INSTALLED REPAIRED UNIT, SYSTEM WORKING OK RIGHT NOW . THIS UNIT HAD LESS THAN 13 HOURS TT SINC REPAIR ON IT. (K) 2 L 7 2 4F 4 F RT A21EA E15NE 20080715 EA 2008 7 15 2008FA0000359 1 20080521 G 2750 600930035 CONTROL HANDLE CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF343A1 30068 NE COCKPIT DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SO 03 779AZ 3502 5176 807241 AIRCRAFT HAD BEEN EXPERIENCING MULTIPLE INFLIGHT FLAP FAILURES WHICH WERE NOT DUPLICATED ON THE GROUND. DURING TROUBLESH OOTING OF THE FLAP SYSTEM, FLAPS WOULD NOT MOVE FROM 45 DEGREES TO 30 DEGREES WHEN SELECTED. NO FAILURE WAS DISPLAYED BY THE AIRCRAFT. FLAP HANDLE WAS JOGGLED AND FLAP MOVEMENT WOULD BEGIN. REPLACED FLAP CONTROL HANDLE. (K) 2 L 7 2 4F 4 F RT A21EA E15NE 20080715 CE 2008 7 15 2008FA0000360 1 20080515 G 5720 662121126 STIFFENER CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE LT MLG WW MISINSTALLED B X07R K NONE O OTHER IN INSP/MAINT 1 CE 07 698QS 5605653 FOUND RT STIFFENER (PN 662121126) INADVERTENTLY INSTALLED IN LT POSITION. WITH LANDING GEAR IN THE STOWED POSITION, THE ACTUATOR CONTACTED THE STIFFENER AND CAUSED MINOR CHAFFING. NEITHER THE ACTUATOR NOR THE STIFFENER WERE DEFORMED/ DAMAGE D. (K) 2 L 7 2 4F 4 F RT A22CE E00059EN 20080715 EA 2008 7 15 2008FA0000361 1 20080521 G 2750 60093000117 FCU CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF343A1 30068 NE T/E FLAPS FAILED D O OTHER J WARNING INDICATION AP APPROACH 1 SO 03 779AZ 5176 807245 AC HAS BEEN EXPERIENCING INTERMITTENT FLAP SYSTEM FAILURES IN DIFFERENT MODES OF FLIGHT, PRIMARILY DURING APPROACH. TROU BLESHOOTING IAW MM RECOMMENDED REPLACEMENT OF FLAP CONTROL UNIT DUE TO IMMEDIATE ( INTERMITTENT) FAILURES AFTER FLAP MOV EMENT SELECTION. AFTER INSTALLATION OF THIS UNIT IN AIRPLANE, FLAPS FAILED TAKEOFF CONFIGURATION WARNING SYSTEM CHECK WH EN UTILIZING LEFT POWER LEVER (THROTTLE LEVER). UNIT NOT RETURNED TO SERVICE. NO FLIGHT TIME PLACED ON UNIT. THIS PART HAD A FRESH INSPECTION TAG FROM VENDOR. (K) 2 L 7 2 4F 4 F RT A21EA E15NE 20080715 CE 2008 7 15 2008FA0000362 1 20080507 G 2910 620701098 HYDRAULIC LINE CESSNA 650 650 2076802 CE HYDRAULIC SYSTEM LEAKING D K NONE O OTHER IN INSP/MAINT 1 SO 15 126MT 3822 6500044 NOTED HYDR FLUID LEAKING FROM RT WING IN THE MLG AREA. TROUBLESHOOTING REVEALED A GROUND SPOILER HYD LINE. LOCATED ON TH E REAR FACE OR THE AFT SPAR AT WS 84 (APPROX). HAD BEEN CHAFED THROUGH BY THE AILERON CABLES. DUE TO THE CLOSE PROXIMITY OF THE LINE AND CABLES, THIS AREA SHOULD BE CLOSELY INSPECTED TO DETECT ANY CHAFING PROBLEM. (K) 2 L 7 2 4F A9NM 20080715 EU 2008 7 15 2008FA0000363 1 20080406 G 6320 350A32030004 GEARBOX SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1A2 60030 NE MAIN ROTOR DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 13 111AK 4093 2110 3092 4571 HAD A MAIN GEARBOX CHIP EVENT. PERFORMED CHECKS IAW MM TO INCLUDE OIL DAIN, STRAIN AND FLUSH. HAD FIVE SCALE TYPE CHIPS THE LARGEST BEING 1.5MM AND SENT IN FOR ANALYSIS. RETURNED AIRCRAFT TO SERVICE. AT RECEIPT OF ANALYSIS DATA PERFORMED A BORESCOPE OF PINION AND BEVEL WHEEL. FOUND FROSTING DAMAGE ON PINION GEAR AND REMOVED AIRCRAFT FROM SERVICE. (K) 1 G 7 1 3U 3 U NC H9EU E19EU 20080715 CE 2008 7 15 2008FA0000364 1 20080509 G 2731 TRIM SWITCH CESSNA 206 P206B 2073309 CE CONT O520 IO520F 17032 SO PILOTS YOKE INOPERATIVE D O OTHER O OTHER NR NOT REPORTED 1 NM 01 4711F P2060311 248025R PILOT REPORTED IN FLIGHT WHEN AUTOPILOT/ELECTRIC TRIM ENABLE, TRIM SERVO "RAN ON", WHEN ELECTRIC TRIM TURNED OFF MANUAL TRIM WHEEL OPERABLE AND NO MALFUNCTION OF SYSTEM NOTED, UPON INSPECTION NOTICED SOLDERED CONNECTION ON BASE OF SWITCH BE NT AND JUMPED BETWEEN WIRE POSTS ON BASE OF SWITCH. RESOLDERED CONNECTION, SEAL WITH HEAT SHRINK AND OPERATED SYSTEM OK. (K) 1 H 7 1 3O 3 O A4CE E5CE 20080715 EA 2008 7 15 2008FA0000365 2 20080522 G 8530 SLC36005 CYLINDER CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA ENGINE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 NM 01 21295 681 17263925 ENGINE WAS OVERHAULED NOV 2001 USING NEW CILINDER ASSEMBLES. BREAK-IN OPERATION PERFORMED WITH MFG SERVICE INSTRUCTION 1 427B AND MINERAL OIL. ENGINE OPERATED NEAR DAILY FLIGHTS AVERAGEING .5 HOUR EACH. REGULAR OIL CHANGES USING 15W50 OIL AN D ADDITIVE, POST BREAK-IN TIME OF 25 HOURS. OIL SAMPLE RESULTS INDICATED PREMATURE WEAR OF RINGS AND WALLS STARTING WITH FIRST SAMPLE AT 111.0 HOURS AND EVERY 30-50 HOURS THERE AFTER. REMOVED CYLINDERS FOR INSPECTION AFTER DISCOVERING VISIB LE METAL IN SCREEN AT 681 HOURS SINCE OVERHAUL. CYLINDER WALLS ON ALL FOUR ENGINE CYLINDERS WORN/DETERIORATED TO DEGREE THAT THE PISTON PIN PLUGS WERE SCRAPING ON RIDGES FROM PISTON RINGS. NOTABLE ALUMINUM FROM PISTON PIN PLUGS WAS FOUND I 1 H 7 1 3O 3 O NT 3A12 E274 20080715 CE 2008 7 15 2008FA0000366 1 20080524 G 7603 ARM CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA THROTTLE CABLE BROKEN B O6WR K NONE O OTHER IN INSP/MAINT 1 GL 05 75528 17267783 L153076T BOLT CONNECTING CARBURETOR THROTTLE ARM TO THROTTLE CABLE FAILED RESULTING IN THROTTLE STICKING OPEN. PILOT PLACED MIXTU RE CONTROL IN IDLE CUTOFF POSITION AND ATTEMPTED TO GLIDE TO RUNWAY AT AIRPORT. AIRCRAFT IMPACTED POWER LINES SHORT OF R UNWAY. BOLT WAS NOT RECOVERED. (K) 1 H 7 1 3O 3 O NT 3A12 E274 20080715 CE 2008 7 15 2008FA0000367 1 20080522 G 2750 99105863 MOTOR CESSNA 208 208B 2073701 CE TE FLAPS BURNED D B EMER. DESCENT B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 NM 04 110WY 295 208B1020 ON 5/7/08 DEPARTED AT APPROXIMATELY 8:30 LOCAL TIME. FLAPS SET TO 10 DEGREES FOR TAKEOFF. TAKEOFF & CLIMB NORMAL. AFTER 10 TO 15 MINUTES INTO FLT WITH AUTOPILOT ENGAGED, NOTICED A BURNING ODOR & SAW A SMALL AMOUNT OF SMOKE THAT LASTED FOR A SECOND OR TWO. DISENGAGED AUTOPILOT & LOOKED AT CIRCUIT BREAKERS & NOTICED STALL WARNING CIRCUIT BREAKER HAD POPPED. AF TER RETURNING TO AIRPORT, FOUND SEVERAL CIRCUIT BREAKERS HAD POPPED & FLAPS WERE INOPERATIVE & STUCK AT 10 DEGREES. AVIO NICS SHOP REPORTED THE FOLLOWING: HIDDEN DAMAGE INSPECTION PERFORMED. BURNED WIRES FOUND IN WIRE BUNDLE RUNNING FROM MAI N FLAP MOTOR TO CIRCUIT BREAKER PANEL & FROM MAIN FLAP MOTOR TO GROUND BLOCK J66. INSULATION OF ADJACENT WIRES ALONG SAM 1 H 7 1 3T A37CE 20080715 CE 2008 7 15 2008FA0000368 1 20080509 G 2430 DOFFO10300J ALTERNATOR CESSNA 206 206CESSNA 2073302 CE CONT O520 IO520F 17032 SO ENGINE SEPARATED D K NONE O OTHER IN INSP/MAINT 1 NM 01 4711F P2060311 248025R BODY THRU SCREWS BACKING OUT CAUSING ALTERNATOR HALVES TO START TO SEPARATE, THOUGH NO IMMEDIATE ISSUES WITH AICAFTS CHA RGING SYSTEM, NOTICED DISCREPANCY UPON VISUAL INSPECTION AFTER LANDING. (K) 1 H 7 1 3O 3 O A4CE E5CE 20080715 SO 2008 7 15 2008FA0000369 2 20080322 G 7414 GEAR CONT O550 IO550N 17042 SO MAGNETO STRIPPED G A UNSCHED LANDING E VIBRATION/BUFFET TO TAKEOFF 1 EA 61 2354B 0077 685811 A PRE-TAKEOFF ENGINE RUNUP WAS SATISFACTORY. SHORTLY AFTER LIFTOFF THE AIRCRAFT BEGAN VIBRATING SUBSTANTIALLY. AFTER REA CHING PATTERN ALITUDE, REDUCED POWER AND SWITCHED TO LT MAGNETO OPERATION AND THE ENGINE RAN SMOOTHLY. SWITCHED TO RT MA GNETO OPERATION THE ENGINE ESSENTIALLY DIED AND UPON RETURNING TO "LT" THE ENGINE EXPERIENCED AN AFTER FIRE (AKA BACKFIR E) THEN RAN SMOOTHLY ONCE AGAIN. RETURNED TO THE DEPARTURE AIRPORT AND REMOVED THE ENGINE COWLING. REMOVED THE TIMING PL UG ON THE RT MAG AND FOUND THE DISTRIBUTOR GEAR WOULD TURN FREELY. REMOVED THE MAGNETO. PARTIAL DISASSEMBLY REVEALED THE DISTRIBUTOR GEAR WAS STRIPPED OF NEARLY HALF ITS TEETH. BOTH MAGNETOS HAVE SINCE BEEN REPLACED. EACH MAGNETO HAS A THRE 3 O E3SO 20080715 CE 2008 7 15 2008FA0000370 1 20080507 G 3220 LEG ASSY CESSNA 170 170A 2072304 CE ROTAX 912 ROTAX912UL EU NLG BROKEN D O OTHER O OTHER NR NOT REPORTED 1 CE 01 5455C 19489 5645575 NOSE LANDING GEAR LEG BROKEN AT FORWARD WELD ON SHOCK ABSORBER ATTACHMENT BRACKET. EXISTING INTERNAL CRACK. PROBABLE CAU SE, BAD WELD. (K) 1 H 7 1 3O 3 O A799 EXPE3I 20080718 SO 2008 7 18 2008FA0000371 2 20080510 G 8500 ENGINE CESSNA 172 172G 2072420 CE CONT O300 O300D 17022 SO VAPOR LOCK D O OTHER O OTHER NR NOT REPORTED 1 SW 19 172BX 17254216 24635D1D AC WAS BEING FLOWN ON RT FUEL TANK. AFTER RUNNING TANK DRY, PILOT SELECTED RT FUEL TANK AND MOMENTS LATER THE ENG STOPPE D PRODUCING POWER AND MADE AN EMERGENCY LANDING. AC FUEL SYS WAS INSPECTED FOR CONTAMINATES AND FAILURES, NONE WERE FOU ND. POSSIBLE CAUSE IS VAPOR LOCK IN FUEL SYS FROM RUNNING FUEL TANK TRY. TO PREVENT THIS FROM RECURRING, WOULD BE TO SEL ECT ANOTHER FUEL TANK PRIOR TO RUNNING THE SELECT FUEL TANK DRY. (K) 1 H 7 1 3O 3 O NT 3A12 E253 20080715 WP 2008 7 15 2008FA0000372 1 20080514 G 6330 23688 RETAINER HILLER UH12 UH12E 4360122 WP LYC O540 VO540* 41532 EA M/R TRANSMISSION MISMANUFACTURED B ZYEG K NONE O OTHER IN INSP/MAINT 1 EA 25 1523T 1740 RETAINER SUSPECTED LOCALLY MADE INSTALLATION WORD "UP" IS NOT STAMPED ON PART BUT ETCHED ON BY HAND. THICKNESS OF RETAIN ER IS .045, ACTUAL PART THICKNESS OF NEW RETAINER IS .051. FOUND SHAFTS THAT ARE SHIMMED WITH BAD RETAINERS TO BE SHIMM ED IMPROPERLY DUE TO RETAINER THICKNESS AS REQURIED BY MFG O/H MANUAL. SHAFTS WERE OUT OF TOLERANCE BY .014 TO .020. (K) 1 G 7 1 3O 3 O 4H11 E304 20080715 SO 2008 7 15 2008FA0000373 1 20080515 G 3010 488699 TIMER PIPER PA31T PA31T1 7103126 SO WING DE-ICE SYS MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 10 93CN 31T8004029 THESE UNITS WERE BOUGHT NEW FROM MANUFACTURER AND WHEN THEY WERE INSTALLED IN THE AIRCRAFT IT WAS NOTED THAT THE SURFACE DEICE BOOTS WERE INFLATED ALL OF THE TIME WHEN THE AIRCRAFT POWER WAS TURNED ON. A SECOND TIMER UNIT WAS PURCHASED AND THE SAME PROBLEM EXISTED WHEN IT WAS INSTALLED. UPON TROUBLESHOOTING THE SYSTEM AND VERIFYING CORRECT INSTALLATION AND W IRING, IT WAS FOUND THAT TWO OF THE WIRES COMING OUT OF THE UNIT WERE SWITCHED DURING MFG AND THE BOXES WERE OPERATING O PPOSITE AS IS INTENDED. THERE ARE FOUR WIRES. RED, BLACK, WHITE AND BLUE. THE WHITE AND BLUE WIRES ARE REVERSED. (K) 1 L 7 2 3T A8EA 20080715 SO 2008 7 15 2008FA0000374 1 20080515 G 3010 488699 TIMER PIPER PA31T PA31T1 7103126 SO WING DE-ICE MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 10 93CN 31T8004029 THESE UNITS WERE BOUGHT NEW FROM MANUFACTURER AND WHEN THEY WERE INSTALLED IN THE AIRCRAFT IT WAS NOTED THAT THE SURFACE DEICE BOOTS WERE INFLATED ALL OF THE TIME WHEN THE AIRCRAFT POWER WAS TURNED ON. A SECONDTIMER UNIT WAS PURCHASED AND THE SAME PORBLEM EXISTED WHEN IT WAS INSTALLED. UPON TROUBLESHOOTING THE SYSTEM AND VERIFYING CORRECT INSTALLATION AND WIRING, IT WAS FOUDN THAT TWO OF THE WIRES COMING OUT OF THE UNIT WERE SWITCHED DURING MFG AND THE BOXES WERE OPERATING OPPOSITE AS INTENDED. THERE ARE FOUR WIRES, RED, BLACK, WHITE AND BLUE, THE WHITE AND BLUE WIRES ARE REVERSED. (K) 1 L 7 2 3T A8EA 20080715 CE 2008 7 15 2008FA0000377 1 20080701 G 5730 501102715 SKIN BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 19 7232R 8914 BL69 DURING A PREFLIGHT INSPECTION, MAINTENANCE TECH NOTED A 3.75 INCH LONG CRACK IN THE RT WING LOWER WING SKIN JUST FWD OF THE IB SECTION OF THE OB FLAP. ADDITIONALLY A SUPPORT/ ANCHOR TAB THAT ATTACHES THE LOWER WING SKIN TO THE IB MOST FLAP WELL RIB OF THE OB WING, WITHIN THE FLAP WELL, WAS FOUND CRACKED THROUGH/FAILED. WE BELIEVE THIS TAB FAILURE ALLOWED THE SKIN TO VIBRATE GENERATING THE RAPID CRACK GROWTH. THIS CRACK IS DIRECTLY AFT OF THE LOWER AFT WING BOLT. THIS CRACK HA S JUST APPEARED WITHIN THEPAST (2) HOURS OF FLIGHT TIME. CAN PINPOINT THIS TIME FRAME SINCE THE 5 YEAR WING BOLTS REMOV AL AND INSPECTION PROCESS WAS COMPLETED JUST 2 FLIGHT HOURS AGO AND NO WING SKIN CRACKS WERE NOTED/ DOCUMENTED AT THAT T 1 L 7 2 4T 4 T A24CE E4EA 20080718 GL 2008 7 18 2008FA0000378 1 20080415 G 7931 TRANSMITTER CIRRUS SR SR22 2130001 GL CONT O550 IO550* SO OIL PRESSURE MALFUNCTIONED D O OTHER O OTHER NR NOT REPORTED 1 SO 13 748CD 0086 FOLLOWING ACTIONS WERE TAKEN AS A RESULT OF A PRECAUTIONARY LANDING, WHERE PILOT REPORTED A LOSS OF OIL PRESSURE. AT CR UISE, AT 8000 FT, OIL PRESSURE ANNUNCIATOR LIGHT ILLUMINATED, OIL PRESSURE GAUGE INDICATED NO OIL PRESSURE. AFTER LAND ING, OIL PRESSURE RETURNED TO NORMAL. TECH SUPPORT WAS CONTACTED, RECOMMENDED CHECKING OIL PRESSURE SWITCH CONNECTORS. T HEY FEED BOTH ANNUNCIATOR AND GAUGE. CONNECTORS WERE CLEANED, CHECKED FOR INTEGRITY AND RECONNECTED. NO PROBLEMS WERE FO UND. OIL LEVEL WAS FOUND AT APPROX (6) QTS. (1) QUART 20X50 WAS ADDED. ENGINE STARTUP AND OIL PRESSURE WAS NORMAL, WITH READING AT TOP OF THE GREEN, COLD, DECREASING TO 50 PSI, HOT. ALL OTHER ENG PARAMETERS APPEAR NORMAL. SUSPECT A CO 1 L 7 1 3O 3 O NT A00009CH E3SO 20080715 EA 2008 7 15 2008FA0000379 1 20080530 G 5541 SPAR SCWZER G164 G164B 3952802 EA PWA R1340 R1340* 52016 NE RUDDER CORRODED D K NONE O OTHER IN INSP/MAINT 1 WP 25 3628D 735B FOUND EXTERNAL CORROSION ON RUDDER MAIN TUBULAR SPAR APPROXIMATELY (2) INCHES ABOVE RUDDER CONTROL HORN. POST WAS SEVERE LY CORRODED WITH HOLES THRU TUBE. AD 78-08-09 ADDRESSES THIS PROBLEM BUT NOT FOR THIS MODEL AIRCRAFT. (K) 1 Q 7 1 3R 3 R 1A16 5E2 20080715 SO 2008 7 15 2008FA0000380 2 20080303 G 8520 ENGINE CONT O520 IO520CB 17032 SO MALFUNCTIONED D O OTHER O OTHER NR NOT REPORTED 1 SW 99 2400 502 OH ENGINE AND RETURNED TO SERVICE APROX (2) YEARS AGO, 600 HOURS OPERATION. ENGINE FAILED WHEN POWER WAS REDUCED ON LAN DING. THE COUNTERWEIGHT MANAGED TO HOOK ON THE CYLINDER DECK STUD AND DRAG IT INTO THE CASE, GETTING INVOLVED WITH THE R OTATING COMPONENTS. MASSIVE DAMAGE TO THE ENTIRE ROTATING MASS. IT WAS NOTED ON TEARDOWN THAT AT THE CYLINDER DECK STU DS (NECK STUDS) DO EXTEND THRU THEIR HOLES IN THE CYLINDER PAD APPROX .1875 TO .3125 BELOW THE BOTTOM OF THE HOLE IN THE CASTING. THE LATER CASTINGS HAVE .2500 TO .3125 THICKER MATERIAL CAUSING THE STUDS TO BE EVEN WITH THE BOTTOM OF THE H OLES, AND TO HAVE SEVERAL MORE THREADS IN THE CASTING. AFTER EXAMINING THE CASE, NOTED, BASED ON THE DESIGN OF THE STUD 3 O E5CE 20080718 CE 2008 7 18 2008FA0000381 1 20080401 G 5312 12210628 BULKHEAD CESSNA 177 177RG 2073709 CE FUSELAGE CRACKED B H5GR K NONE O OTHER IN INSP/MAINT 1 EA 07 7582V 2340 177RG0873 DURING ROUTINE INSP, FOUND PART CRACKED. CHECKED (2) OTHER AC THAT HAPPENED TO BE IN SHOP, FOUND (1) OF THEM TO HAVE A S IMILAR CRACK. THIS SECTION OF BULKHEAD IS ATTACH STRUCTURE FOR LWR ATTACH ANGLE FOR IB FLAP DRIVE BELLCRANK. IT IS CUR IOUS THAT THE FACTORY INSTALLED SOME EXTRA REINFORCEMENT STRUCTURE (A BRACKET) IN THIS POSITION IN LT WING. THERE ARE E VEN SOME "PILOT DRILL" (PD) HOLES DRILLED AT FACTORY IN RIB AND HEAVY ATTACH ANGLE ON THE AFFECTED RT SIDE. IT WOULD APP EAR THAT BOTH LT AND RT BELLCRANKS WOULD EXPERIENCE SAME FORE-AFT FORCES BY AIR LOADS ON FLAPS. SO WHY REINFORCE ONLY O NE SIDE? IT IS POSSIBLE THAT FACTORY ASSY LINE NEGLECTED TO INSTALL AN INTENDED SIMILAR REINFORCEMENT ON THE RT SIDE? ( 1 H 7 1 3O A20CE 20080715 EU 2008 7 15 2008FA0000382 1 20080424 G 7922 1586108 REGULATOR BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE7315R 01518 WP OIL SYSTEM DAMAGED D K NONE O OTHER IN INSP/MAINT 1 NM 07 626CG 258041 P91187 RECEIVED O/H OIL TEMP REGULATOR FROM MFG UNDER THEIR WO 815978-001, DATED 04/22/2008. WHILE PERFORMING INCOMING PARTS I NSPECTION ON 04/24/2008, FOUND FUEL INLET PORT SMASHED. THERE WAS NO DAMAGE TO THE SHIPPING CONTAINER. PROBABLE CAUSE OF DAMAGE WAS MOST LIKELY PRIOR TO PACKING OF UNIT FOR SHIPMENT. (K) 2 L 7 2 4F 4 F RT A3EU E6WE 20080715 WP 2008 7 15 2008FA0000383 2 20080523 G 7210 31020474 HOUSING MTSBSI MU2 MU2B25 5780409 CE GARRTT TPE331 TPE33110 01514 WP GEARBOX CRACKED B A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 SW 15 856JT 306 PILOT REPORTED LOW AND FLUCTUATING OIL PRESSURE FROM LEFT ENGINE IN FLIGHT AND ELECTED TO SHUT THE ENGINE DOWN. AN UNEVE NTFUL SINGLE ENGINE LANDING WAS MADE. THE ENGINE OIL BYPASS VALVE WAS FOUND TO BE IN THE "POPPED" CONDITION, THE OIL FI LTER WAS THEN REMOVED AND FOUND TO BE BLACK IN COLOR WITH THE FORWARD SEALING SURFACE BROKEN IN SEVERAL SMALL PIECES. T HE REDUCTION GEAR BOX WAS DISASSEMBLED AND THE OIL PRESSURE PUMP REMOVED. THE FORWARD HOUSING WAS CRACKED APPROXIMATELY (3 INCH) RADIALLY AT FWD DETAIL. (K) 1 H 7 2 3T 4 T A2PC E4WE 20080718 GL 2008 7 18 2008FA0000384 2 20080519 G 7261 23063413 GEAR BELL 206 OH58B 1181503 SW ALLSN 250C T63A720 03002 GL AIR/OIL SEPARATR BROKEN D A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SO 05 600 AE405555 PILOT REPORTED ENGINE CHIP LIGHTS ON TAKEOFF. ABORTED MISSION AND RETURNED TO HELIPAD. ENG WAS REMOVED AND SENT FOR INV ESTIGATION. ENG RECEIVED FOR REPAIR DUE TO ENG CHIP LIGHTS AND METAL IN OIL. DISASSEMBLY REVEALED AIR OIL SEPARATOR GE AR SHAFT HAD BROKEN WHERE STEM MEETS THE BASE. THIS IS THIRD OCCURRENCE ON THIS PARTICULAR ENG ASSY OF SIMILAR GEAR FAI LURES. HAVE SEEN AT LEAST 8 OF THESE FAILURES IN T63 ENGINES SINCE THEY HAVE BEEN RELEASED TO PUBLIC. (K) 1 G 7 1 3U 3 U H2SW E4CE 20080715 CE 2008 7 15 2008FA0000385 1 20080605 G 3221 66426119 TRUNNION CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE NLG CORRODED B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 640QS 6122 5605240 (REF CWQR200806) WHILE WORKING AN UNSCHEDULED NOSE GEAR VIBRATION, POPPING, DISCREPANCY. FOUND BEARING PN MS2464268G TO BE ROUGH WHEN TURNING. UPON FURTHER INSPECTION FOUND CORROSION AND PITTING BETWEEN STEEL BEARINGS AND ALUM NLG TRUNNIO N ASSY. NLG TRUNNION SHOULD BE TREATED TO PREVENT DISSIMILAR METAL CORROSION. FILED SLR NR 363322. (K) 2 L 7 2 4F 4 F RT A22CE E00059EN 20080715 NM 2008 7 15 2008FA0000387 1 20080610 G 5340 ATTACH ANGLE BOEING 737 737448 13844BU NM FUSELAGE CORRODED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 742VA (REF DU4R2008212) DURING SCHEDULED INSPECTION, FOUND CORROSION IN AFT LOWER CARGO COMPARTMENT AT STA 727A ATTACH ANGLE G BGETWEEN S-27R AND S-26R. (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000388 1 20080610 G 5310 DOOR FRAME BOEING 737 737448 13844BU NM FUSELAGE CRACKED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 742VA 24773 (REF DU4R2008213) DURING SCHEDULED INSPECTION, FOUND 1 INCH LONG CRACK ON FWD CARGO DOOR CUT-OUT AFT FRAME INNER CHORD R ADIUS. (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000389 1 20080610 G 5330 SKIN BOEING 737 737448 13844BU NM BS 887 S19R DENTED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 742VA 24773 (REF DU4R2008214) DURING SCHEDULED INSPECTION, FOUND DENT ON LWR RT LOWER AFT FUSELAGE BS 887 S-19R. (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000390 1 20080610 G 5347 CARGO TRACK BOEING 737 737448 13844BU NM CARGO BAY CORRODED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 742VA 24773 DURING SCHEDULED INSPECTION, FOUND CORROSION IN THE AFT CARGO COMPARTMENT LT TIE DOWN TRACK LBL 17.20 FROM STA 727B - ST A 727E. PARTICULARLY IN FASTENER HOLE UPPER AND LOWER SURFACE. (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000391 1 20080620 G 5320 141A5505 FLOOR SUPPORT BOEING 737 73783N 13844HI NM FUSELAGE CORRODED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 318TZ 28247 (REF DU4R2008219) DURING SCHEDULED INSPECTION, FOUND CORROSION ON FLOOR SUPPORT CABIN STA 344, BL-0 TO BL-12L. (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000392 1 20080613 G 5320 FLOOR SUPPORT BOEING 737 737448 13844BU NM FUSELAGE CORRODED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 742VA 24773 (REF DU4R2008216) DURING SCHEDULED INSPECTION, FOUND CORROSION ON UPPER SURFACE OF FLOOR SUPPORT BEAM BS 328, RBL-16 TO RBL-60. S/O NR 312001, OPS NR 24738. (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000393 1 20080613 G 5311 FRAME BOEING 737 737448 13844BU NM FUSELAGE DAMAGED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 742VA 24773 (REF DU4R2008217) DURING SCHEDULED INSPECTION, FOUND DOUBLE-DRILLED HOLE ON MAIN FRAME UPPER CAP AT BS 986.5 AT FLOOR LE VEL RT. (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000394 1 20080620 G 5320 141A5410 FLOOR SUPPORT BOEING 737 73783N 13844HI NM FUSELAGE CORRODED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 318TZ 28247 (REF DU4R2008220) DURING SCHEDULED INSPECTION, FOUND CORROSION ON FLOOR SUPPORT CABIN. STA 340, LBL 11. (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000395 1 20080623 G 5230 SKIN BOEING 737 73783N 13844HI NM AFT CARGO DOOR DENTED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 304TZ 30675 (DU4R2008221) DURING SCHEDULED INSPECTION, FOUND AFT CARGO DOOR EXT SKIN HAS DENT 11 INCHES AFT FROM FWD EDGE 5 INCHS UP FROM BOTTOM EDGE WIDTH OF DENT 1.25 INCHES OF DENT .070 INCH W/Y=17 DENT MEASURES WITH DEPTH GUAGE A-1979. S/O NR 2450 10, OPS NR 26681. (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000396 1 20080623 G 5230 SKIN BOEING 737 73783N 13844HI NM FWD CARGO DOOR DENTED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 304TZ 30675 (REDF DU4R2008222) DURING SCHEDULED INSPECTION FOUND DENT IN EXT SKIN OF C-1 DOOR 25 INCH DOWN FROM TOP EDGE OF DOOR AND 22 INCHES AFT FROM FWD EDGE OF DOOR. (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000397 1 20080624 G 5230 SKIN BOEING 737 73783N 13844HI NM AFT CARGO DOOR DENTED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 304TZ 30675 (DU4R2008223) DURING SCHEDULED INSPECTION, FOUND DENT IN AFT CARGO DOOR (C-2) EXT. SKIN. S/O NR 245010, N/R 26678. (K) 2 L 7 2 4F RT A16WE 20080718 NM 2008 7 18 2008FA0000398 1 20080630 G 5340 NUT CLIP BOEING 737 73783N 13844HI NM BS 967 CHAFED B DU4R O OTHER O OTHER NR NOT REPORTED 1 EA 39 304TZ 30675 (DU4R2008225) DURING SCHEDULED INSP, FOUND AFT CABIN BS 967, RBL 24, TO LBL 49 FLOORBOARD ATTACH POINTS, CLIP NUTS HAVE WORN GROOVES/CHAFE MARKS. S/O NR 245010, N/R NR27070 (K) 2 L 7 2 4F RT A16WE 20080718 NM 2008 7 18 2008FA0000399 1 20080630 G 5315 FLOORBEAM BOEING 737 73783N 13844HI NM BS986 CORRODED B DU4R O OTHER O OTHER NR NOT REPORTED 1 EA 39 304TZ 30675 (DU4R2008226) DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN WET AREA ON FLOORBEAM FASTENERS AND FASTENER HOLES AT BS 986 FORM RBL45 TO LBL 45. S/O 245010 , N/R 27072 (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000400 1 20080630 G 5512 SKIN BOEING 737 73783N 13844HI NM LT HORIZ STAB DENTED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 308TZ 28244 (REF DU4R2008227) DURING SCHEDULED INSPECTION, FOUND OUT OF LIMITS DENT IN LT HORIZ STAB L/E STA 280. S/O 245008, N/R 2 1578 (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000401 1 20080630 G 5512 SKIN BOEING 737 73783N 13844HI NM HORIZ STAB DENTED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 308TZ 28244 DURING SCHEDULED INSPECTION, FOUND DENT IN LT L/E OF HORIZ STAB STA 105. S/O 245008, N/R 21591. S/O 245008, N/R 21591 . (K) 2 L 7 2 4F RT A16WE 20080715 NM 2008 7 15 2008FA0000402 1 20080630 G 5315 FLOORBEAM BOEING 737 73783N 13844HI NM FUSELAGE CORRODED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 318TZ 28247 DURING SCHEDULED INSPECTION, FOUND CORROSION ON AFT CABIN FLOORBEAM, BS947, RBL 5 TO LBL5. S/O 245009, N/R 26378 (K) 2 L 7 2 4F RT A16WE 20080715 EA 2008 7 15 2008FA0000403 2 20080616 G 7414 4371 MAGNETO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE OUT OF POSITION B Z08R K NONE O OTHER IN INSP/MAINT 1 CE 07 987AP 172S10710 CHECKED THE MAGNETO TIMING AND FOUND THAT BOTH MAGNETOS WERE OFF APPROX 5 DEGREES. CURRENTLY SET AT APPROX 30 DEGREES B EFORE TOP DEAD CENTER. MFG SPEC IS 25 DEGREES BTDC. THE AIRCRAFT ENGINE TO MAGNETO TIMING WAS CHECKED WHEN NEW, SHORTLY AFTER DELIVERY 4/14/2008- 3.5 HRS TIS AND FOUND OK. IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICALLY TO THE ADVANCED P OSITION. ORANGE FACTORY PUTTY NOTED ON MAGNETO HOLDOWN NUTS. IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICALLY TO THE A DVANCED POSITION IN 80 HRS TIS. THE MAGNETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOING ISSUE WITH MFG. SB SB2-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS, AS IN THIS CASE. 1 H 7 1 3O 3 O NT 3A12 1E10 20080715 EA 2008 7 15 2008FA0000404 2 20080617 G 7414 M3820 DISTRIBUTOR BLK SLICK CESSNA 182 182T 2072703 CE LYC O540 IO540AB1A5 EA MAGNETO MISREPAIRED B Z08R K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 07 658PW 08011866 18282098 DURING INTERNAL MAGNETO INSPECTION, FOUND DISTRIBUTOR BLOCK SPOT FACED AREA FOR POLES. APPEARS TO BE INCORRECTLY SPOT F ACED. MATERIAL THAT WAS LEFT BEHIND HAS THE SAME LOFT AS BEARING BOSS AREA ON DISTRIBUTOR BLOCK. THIS CAUSES THE FINGE R ON THE DISTRIBUTOR GEAR TO RUB ON THE DISTRIBUTOR BLOCK. (K) 1 H 7 1 3O 3 O NT 3A13 1E4 20080715 EA 2008 7 15 2008FA0000405 2 20080616 G 7414 MAGNETO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE OUT OF POSITION B Z08R K NONE O OTHER IN INSP/MAINT 1 CE 07 227BH 172S10662 DURING A PHASE 2 (100 HR) CHECK THE MAGNETO TIMING AND FOUND THE RT MAGNETO ADVANCED TO APPROXIMATELY 27 DEGREES. MFG S PECS CALL FOR 25 DEGREES. LAST CHECK AT 90 HOURS PRIOR, FOUND TO BE OK. SUSPECT MAGNETO DRIFTING IS OCCURING. THE MAG NETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOING ISSUE WITH ENGINE AND MAGNETOS. SB SB2 -08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS, AS IN THIS CASE. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 20080715 EA 2008 7 15 2008FA0000406 2 20080611 G 7414 4371 MAGNETO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA POWERPLANT OUT OF POSITION B Z08R K NONE O OTHER IN INSP/MAINT 1 CE 07 712DS 98 172S10711 L3404451 DURING THE AC FIRST PHASE 2 INSPECTION (100 HR) FOUND THAT BOTH MAGNETOS WERE OFF APPROXIMATELY 5 DEGREES. CURRENTLY SE T 30 DEGREES BEFORE TOP DEAD CENTER PLUS (MFG SUM SAYS 25 DEGREES BTDC) THE AIRCRAFT MAGNETO TO ENGINE TIMING WAS CHECKE D WHEN NEW, SHORTLY AFTER DELIVERY 4/25/2008, 4.3 HRS TIS. IT APPEARS THE MAGNETOS HAVE DRIFTED TO THE ADVANCED POSITIO N. ORANGE PUTTY ON THE MAGNETO HOLD-DOWN STUDS WAS NOTED. IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICANTLY TO THE AD VANCED POSITION IN 93 HOURS TIS. THE MAGNETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOIN G ISSUE WITH MFG OF ENGINE AND MFG OF MAGNETO SB2-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS AS IN THIS C 1 H 7 1 3O 3 O NT 3A12 1E10 20080715 EA 2008 7 15 2008FA0000407 2 20080611 G 7414 4371 MAGNETO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA OUT OF POSITION B Z08R K NONE O OTHER IN INSP/MAINT 1 CE 07 712DS 172S10711 L3404451E DURING THE AC FIRST PHASE 2 INSP (100 HR) FOUND THAT BOTH MAGNETOS WERE OFF APPROX 5 DEGREES. CURRENTLY SET 30 DEGREES B EFORE TOP DEAD CENTER PLUS MFG SRM SAYS 25 DEGREES BTDC). THE AIRCRAFT MAGNETO TO ENGINE TIMING WAS CHECKED WHEN NEW, S HORTLY AFTER DELIVERY 4/25/2008. 4.3 HOURS TIS. IT APPEARS THE MAGNETOS HAVE DRIFTED TO THE ADVANCED POSITION. ORANGE PUTTY ON THE MAGNETO HOLD-DOWN STUDS WAS NOTED. IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICANTLY TO THE ADVANCED POSI TION IN 93 HRS TIS. THE MAGNETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOING ISSUE WITH ENGINE MFG AND MAGNETO MFG, SB2-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS AS IN THIS CASE. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 20080715 SO 2008 7 15 2008FA0000408 1 20080528 G 3246 3080D WHEEL PIPER PA23 PA23250 7102308 SO LYC O540 IO540* 41532 EA LT MLG CORRODED C K NONE O OTHER IN INSP/MAINT 1 SO 27 959C 278154029 DURING A ROUTINE INSPECTION THE AMT ENCOUNTERED DIFFICULTY WHILE REMOVING THE LT MAIN GEAR WHEEL ASSEMBLY AXLE RETAINING NUT. HE STOPPED AND DEFLATED THE TIRE. THE WHEEL WAS THEN REMOVED EASILY. FOLLOWING REMOVAL THE WHEEL WAS FOUND TO BE SEVERELY CORRODED AND ALL BUT ONE WHEEL-HALF RETAINING BOLT HAD FAILED. THE LOG BOOK ENTRY INDICATED THAT THE WHEEL HA D LSAST BEEN DISASSEMBLED 217 HOURS AGO. (K) 1 L 7 2 3O 3 O 1A10 1E4 20080715 SO 2008 7 15 2008FA0000409 1 20080607 G 2434 32C22491 ALTERNATOR PIPER PA32 PA32R301 7103218 SO LYC O540 IO540K1G5 41532 EA DAMAGED D O OTHER S AFFECT SYSTEMS NR NOT REPORTED 1 EA 13 30969 3246230 L3047448A 4 SCREWS THAT HOLD THE RECTIFIER PLATE INTO THE BACK CASE OF ALTERNATOR CAME LOOSE AND CONTACTED THE ROTOR, DESTROYED AL TERNATOR. (K) 1 L 7 1 3O 3 O A3SO 1E4 20080715 EA 2008 7 15 2008FA0000410 2 20080527 G 7250 3013411 TURBINE AYRES S2 S2RT34NORMAL 0970106 SO PWA PT6 PT6A34 52043 EA ENGINE DAMAGED G O OTHER O OTHER NR NOT REPORTED 1 SW 11 3105E 1026 T34177 PCE56299 06/20/2008 REPORT: ON 5/27/08 AC UNDER LOAD IN TURN EXPERIENCED ENGINE FAILURE RESULTING IN ACCIDENT. LOUD BANG! ENGINE QUIT. CT TURBINE TEETH MISSING, NR 2 BEARING DESTROOYED. 1026.1 HOURS ON PMA BLADES PQ0812NE. (K)(NTSB: DFW08CA155) 1 L 7 1 3T 4 T A3SW E4EA 20080715 CE 2008 7 15 2008FA0000411 1 20080612 G 3230 ROD END CESSNA 310 T310Q 2074244 CE LYC O360 IO360A1A 41514 EA LANDING GEAR BROKEN G O OTHER O OTHER CL CLIMB 1 EA 39 7044Q T310Q0204 AFTER TAKEOFF, WHEN RETRACTING GEAR, PILOT HEARD LOUD CRACK. NOSE GEAR WOULD NOT RETRACT. AIRCRAFT LANDED WITH NOSE GE AR TRAILING AFT. NOSE GEAR COLLAPLSED ON LANDING. INSPECTION REVEALED ROD END UNDER PILOT`S FLOOR THAT CONNECTS NOSE G EAR RETRACT ROD TO BELLCRANK SEPARATED CAUSING NOSE GEAR TO BECOME DISCONNECTED FROM LANDING GEAR TRANSMISSION. 1 L 7 2 3O 3 O 3A10 1E10 20080717 NE 2008 7 17 2008FA0000412 2 20080528 G 7510 101910026191 CONTROL ARM BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE LT NACELLE WORN B CWNR O OTHER O OTHER NR NOT REPORTED 1 WP 09 6604L 100 BB1121 LT ENGINE NACELLE ICE-VANE CONTROL ARM HAD WORN OUT OR DESTROYED BUSHINGS AT ALL 3 ACTUATING CONTROL ARM DRIVE POINTS AN D LINKS, CAUSING POTENTIAL FOR F.O.D. TO ENGINE. WHEN ICE VANE IS IN THE RETRACTED POSITION THERE ARE NO HARD STOPS TO KEEP IT FROM VIBRATING. (K) 1 L 7 2 4T 4 T A24CE E4EA 20080715 GL 2008 7 15 2008FA0000413 3 20080423 G 6114 05522311 BULKHEAD CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA MCAULY 1A170 1A170E GL PROPELLER CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 23 897LP 570 172S8897 REPEATED FINDINGS OF CRACKS AT EDGE OF WASHER FOOT PRINT. ALLOY CHANGE, OR HARDWARE CHANGE MAY HELP. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 20080715 EA 2008 7 15 2008FA0000414 2 20080701 G 7310 RSA5AD1 INJECTOR CESSNA 182 182T 2072703 CE LYC O540 TIO540AK1A EA FUEL SERVO CLOGGED G O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 EA 23 101LP 569 T18208265 L1165861A PLANE LOST ENGINE POWER, BECAME VERY LEAN, COULD NOT GET FUEL FLOW> 9 GPH. TURNED OUT TO BE ALUMINUM SHAVING FROM ORIGIN AL MFG OF FUEL SERVO. CLOGGED MIXTURE HOLE INSIDE FUEL SERVO. THIS WAS A DEFECT FROM TIME OF MANUFACTURE OF FUEL SERVO . EMERGENCY LANDING. (K) 1 H 7 1 3O 3 O NT 3A13 20080718 2008 7 18 2008FA0000415 2 20080505 G 7414 S6LSC204T MAGNETO BEECH 58 58 1152740 CE ENGINE FAILED B NW4R O OTHER O OTHER NR NOT REPORTED 1 SO 15 142DR 4 TH1458 SMOKE WAS REPORTED IN COCKPIT. UPON INVESTIGATION, FOUND PIN HOLE CORRODED IN METAL LINE CLOSE TO AIR CONDITIONER BLOWE R MOTOR. ALCOHOL SOAKED INSULATION NEAR FRONT BULKHEAD. BURNED SOME INSULATION AND AIR CONDITION FILTER HAD HOLE BURNED IT ALSO. WAS UNABLE TO FIND LEAK WITHOUT LINE REMOVAL AND PRESSURE TEST. CONTACT POINT PN 10-382585 WAS FOUND IN MAGN ETO. POINT CONTACT SURFACE WAS DEBONDED FROM BASE. RESULT WAS FAILED MAGNETO. FOR INFO ONLY - TO SEE IF MORE BREAKER POINTS SHOW SAME TYPE OF FAILURE MAY BE MFG PROCESS. (K) 1 L 7 2 3O 3A16 20080715 SO 2008 7 15 2008FA0000416 1 20080609 G 5720 494718 TAPE PIPER PA28 PA28161 7102803 SO WING PEELING D O OTHER O OTHER NR NOT REPORTED 1 NE 02 8369A 288116198 STUDENT PILOT DECLARED AN EMERGENCY AS HE THOUGHT NOISE HE WAS HEARING WAS HIS ENGINE COMING APART. AFTER SAFELY LANDIN G IT WAS FOUND THAT THE NOISE WAS THE ANTI-SLIP WINGWALK MATERIAL SLAPPING THE WING, IN THE SLIP STREAM. WIND GOT UNDER THE MATERIAL AND LIFTED UP A SECTION OF IT, PEELING IT BACK ENOUGH TO MAKE THE "SLAPPING- BANGING" NOISE HE HEARD. REM OVED THE OLD WING WALK MATERIAL AND INSTALLED NEW PIECE. (K) 1 L 7 1 3O 2A13 20080715 SO 2008 7 15 2008FA0000418 1 20080628 G 3246 WHEEL PIPER PA23 PA23250 7102308 SO LYC O540 IO540* 41532 EA RT MLG BROKEN D PP4R O OTHER O OTHER NR NOT REPORTED 1 EA 39 959C 217 278154029 DIFFICULTY WAS ENCOUNTERED WHILE AN AMT WAS REMOVING THE RETAINING NUT FROM THE AXLE ON THE RT MAIN GEAR OF AC. HE STOP PED AND DEFLATED THE TIRE. THE WHEEL ASSEMBLY WAS THEN REMOVED WITHOUT RESISTANCE. AFTER REMOVAL ALL BUT ONE OF THE AS SEMBLY RETAINING BOLTS WERE FOUND BROKEN AND THE WHEEL HALVES WERE ALSO BROKEN. CORROSION CAUSED THE PROBLEM. THE WHEE L HAD ACCUMULATED 217 HOURS SINCE IT WAS LAST DISASSEMBLED AND INSPECTED. TT ON THE WHEEL IS UNKNOWN. THE ENTIRE WHEEL ASSEMBLY WAS REPLACED. (K) 1 L 7 2 3O 3 O 1A10 1E4 20080715 GL 2008 7 15 2008FA0000419 1 20080618 G 5210 DA4522100002 DOOR DIAMON DA40 DA40 2990002 GL REAR PAX DOOR DEPARTED G A UNSCHED LANDING D INFLIGHT SEPARATION TO TAKEOFF 1 WP 28 686US 615 40640 ON TAKE-OFF ROLL AT VR, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1 L 7 1 3O NT A47CE 20080715 GL 2008 7 15 2008FA0000420 1 20080618 G 5344 HINGE DIAMON DA40 DA40 2990002 GL DOOR CRACKED G K NONE O OTHER IN INSP/MAINT 1 WP 28 686US 40640 FOUND CRACKS IN AFT DOOR HINGE. (K) 1 L 7 1 3O NT A47CE 20080715 GL 2008 7 15 2008FA0000421 1 20080618 G 5210 DA4522100002 DOOR DIAMON DA40 DA40 2990002 GL REAR PAX DOOR DEPARTED G O OTHER D INFLIGHT SEPARATION TX TAXI/GRND HDL 1 WP 28 605US 225 40675 WHILE TAXIING INOT TAKEOFF POSITION ON RUNWAY, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1 L 7 1 3O NT A47CE 20080715 GL 2008 7 15 2008FA0000422 1 20080616 G 5210 DA4522100002 DOOR DIAMON DA40 DA40 2990002 GL AFT PAX DOOR DEPARTED G O OTHER D INFLIGHT SEPARATION CL CLIMB 1 WP 28 605US 536 40675 ON TAKEOFF CLIMBOUT, AFT PASSENGER DOOR DEPARTED AIRFRAME. 1 L 7 1 3O NT A47CE 20080715 GL 2008 7 15 2008FA0000424 1 20080616 G 5210 DA4522100002 DOOR DIAMON DA40 DA40 2990002 GL REAR PASSENGER DEPARTED G O OTHER D INFLIGHT SEPARATION CL CLIMB 1 WP 28 605US 40675 ON TAKEOFF CLIMBOUT, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1 L 7 1 3O NT A47CE 20080715 GL 2008 7 15 2008FA0000426 1 20080618 G 5344 HINGE DIAMON DA40 DA40 2990002 GL DOOR CRACKED G O OTHER O OTHER NR NOT REPORTED 1 WP 28 686US 40640 FOUND CRACKS IN AFT DOOR HINGE. (K) 1 L 7 1 3O NT A47CE 20080717 NM 2008 7 17 2008FA0000427 1 20080601 G 2751 18195816 TRANSMITTER BOEING 767 767241 1385115 NM GE CF6 CF680C2* GL FLAP POSITION FAULTY W TAMF A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 SO 23 770QT 23802 LT FLAP DID NOT MOVE FROM 1 TO UP POSITION. FLIGHT RETURNED TO DEPARTURE. REMOVED AND REPLACED PROXIMITY SENSORS S282 A ND S283 IAW SWPM 20-30-12 AND AMM 27-88-01, BITE TEST PSEU WAS PERFORMED AND IT WAS FOUND NORMAL IAW FIM 32-09-03, FIG 1 03. FLAP POSITION TRANSMITTER NR 5 WAS REMOVED AND REPLACED IAW MM 27-51-45, PG 201-222, OPS CHECK NORMAL, OVERWEIGHT LA NDING INSPECTION WAS ACCOMPLISHED IAW MM 05-51-35 PHASE I, OPTION A, PG 201-203, NO DAMAGES WERE FOUND. (K) 2 L 7 2 4F 4 F RT A1NM E23EA 20080718 2008 7 18 2008FA0000428 4 20080610 G 3420 LIGHT BOEING 767 767241 1385115 NM GE CF6 CF680C2* GL ALTITUDE INDICAT ILLUMINATED W TAMF O OTHER J WARNING INDICATION NR NOT REPORTED 1 SO 23 770QT 23802 CABIN ALT AND CABIN ALTITUDE LIGHTS ILLUM, EICAS MSG CABIN ALTITUDE WAS DISPLAYED. UNABLE TO RESTORE CABIN PRESS USING MANUAL MODE. AIRPLANE RETURNED TO DEPARTURE. IAW FIM 21-31-00, FIG 103 BLOCKS 1,2,22,23,23A, 24, 44, PLN U3 IN CONNECTOR D2712A WAS REPAIRED. REF WDM 21-31-11/21-31-21. TEST WITH AIRCRAFT PRESSURIZED ON GROUND IS SATISFACTORY. (K) 2 L 7 2 4F 4 F RT A1NM E23EA 20080717 CE 2008 7 17 2008FA0000429 1 20080605 G 3222 66420003 PISTON CESSNA 500 560CESSNA 2076750 CE NLG LOOSE B CWQR O OTHER O OTHER NR NOT REPORTED 1 GL 05 351QS 1556 5600451 ( REF CWQR200801) DURING A1-5 PHASE INSPECTION, FOUND EXCESSIVE PLAY INT HE NOSE GEAR FWD AND AFT PLAY CHECK. AFTER FU RTHER INSPECTION , FOUND THE NOSE GEAR FORK LOOSE ON THE PISTON. THEN THE SAFETY BOLT WAS REMOVED THE FORK FELL FROM THE PISTON. THIS SHOULD BE AN INTERFERENCE FIT. THIS IS A LOW TIME AC AND APPEARS TO BE A MFG PROBLEM. FILED SCR NR 3632 22 WITH MFG. (K) 2 L 7 2 4F RT A22CE 20080717 EA 2008 7 17 2008FA0000430 1 20080625 G 3230 7455025 CONTROL PANEL CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF34* 30015 NE MLG MALFUNCTIONED B RO3R O OTHER O OTHER NR NOT REPORTED 1 CE 03 614BA 1176 5614 LANDING GEAR HANDLE DIFFICULT TO ACTUATE TO UP POSITION. REQUIRED MULTIPLE ATTEMPTS TO ACTUATE GEAR HANDLE. FOUND LIGH TED COVER PANEL LOOSE ON GEAR HANDLE ASSEMBLY. REMOVED LIGHT PANEL TO INVESTIGATE. FOUND ONE SCREW FROM BACKSIDE OF PA NEL HAD FALLEN OUT AND WAS INTERFERING WITH GEAR UP RELEASE MECHANISM. REINSTALLED SCREW AND TIGHTENED ALL OTHERS . RE INSTALLED LIGHT PANEL. PREFORMED MULTIPLE GEAR SWINGS, NO FAULTS NOTED. (K) 2 L 7 2 4F 4 F RT A21EA 20080718 NM 2008 7 18 2008FA0000431 1 20080630 G 5320 715K9004507 ANGLE BOEING 717 717200 1383700 NM BS 26 CRACKED A MWEA O OTHER O OTHER NR NOT REPORTED 1 GL 13 970ME 65171 RT UPPER BUCKET, FWD OB Z-FRAME IS CRACKED AT STA 26 APPROXIMATELY 1 INCH LONG. FABRICATED AND INSTALLED ANGLE. (K) 2 L 7 2 4F TR A6WE 20080717 CE 2008 7 17 2008FA0000432 1 20080602 G 3260 602EN166B DOWNLOCK SWITCH CESSNA 501 551 2076605 CE PWA JT15 JT15D4 52112 NE RT MAIN GEAR INOPERATIVE B UPWR O OTHER P NO WARNING INDICATION LD LANDING 1 GL 03 502CL 5510002 RT MAIN GEAR GREEN INDICATOR DID NOT ILLUMINATE WHEN GEAR EXTENDED GOING INTO LAND. CYCLED GEAR AND GREEN INDICATOR LIG HT REMAINED OUT. AC LANDED WITHOUT INCIDENT. RT MAIN GEAR DOWNLOCK SWITCH FOUND TO BE FAULTY. (K) 1 L 7 2 4F 4 F A27CE E1NE 20080717 EA 2008 7 17 2008FA0000433 1 20080521 G 2751 60093000123 ASYMMETRY SWITCH CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF343A1 30068 NE TE FLAPS FAILED D O OTHER J WARNING INDICATION NR NOT REPORTED 1 CE 21 779AZ 5176 FLAPS FAIL FOUR DEGREES AFTER SELECTION. USING BREAKOUT BOX, SELECTED THIS BDU AND FLAPS WOULD CONSISTENTLY FAIL. SELEC TED OTHER SIDE BDU AND FLAPS WOULD OPERATE NORMALLY. UNIT ALSO RATTLES ON BENCH WHEN CHECKING DRAG TORQUE (UNLOCKED). (K) 2 L 7 2 4F 4 F RT A21EA E15NE 20080717 2008 7 17 2008FA0000434 1 20080605 G 2560 RELEASE MECH SEAT BELT FAILED D O OTHER O OTHER NR NOT REPORTED 1 WP 25 SEAT BELT WILL RELEASE WITHOUT PULLING ON THE RELEASE BUCKLE. DURING FLIGHT THE SEAT BELT CAME UNDONE WITHOUT ANYONE PH YSICALLY UNLATCHING THE BELT. CAUSE WAS DUE TO DEFECTIVE LATCH MECHANISM. ALL BELTS WITH CERTAIN BATCH NUMBERS ARE DEF ECTIVE. (1-954/784-3178 MFG) (K) 20080717 NM 2008 7 17 2008FA0000435 1 20080627 G 3213 656174010 CYLINDER BOEING BOEING 737 7373B7 1384580 NM MLG CRACKED B O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 WP 07 514AU XC92439 23700 AFTER AIRCRAFT TOW, FLUID WAS OBSERVED LEAKING FROM .5 INCH CRACK (APPROXIMATE) IN THE OUTER CYLINDER OF THE LT MLG SHOC K STRUT. THE CRACK IS LOCATED APPROXIMATELY 26 INCHES BELOW THE SHOCK STRUT AIR VALVE. (K) 2 L 7 2 4F RT A16WE 20080717 SO 2008 7 17 2008FA0000436 2 20080506 G 8530 SA52006A1 CYLINDER BEECH 35 V35 1151538 CE CONT O520 IO520BA 17032 SO NR 4 CRACKED B BJFR O OTHER O OTHER NR NOT REPORTED 1 EA 23 2024W D8078 241723R CRACK VISIBLE AT NR 4 CYLINDER. CRACK APPEARS TO START AT CASTING ANOMALY, CONTINUES TO EDGE OF FINS, AND IS VISIBLE AT THE FIRST FOUR COOLING FINS. ALSO VERIFIED, THROUGH USE OF EDDY CURRENT, THAT THE CRACK CONTINUES TO THE SPARK PLUG HOLE . ALL OTHER CYLINDERS HAVE SIMILAR CASTING ANOMALIES WITH INDICATIONS OF DISCONTINUITIES FOUND WITH EDDY CURRENT EQUIPME NT. THIS FACILITIES OPINION IS THAT POOR CASTING TECHNIQUES BY THE MFG LEFT STRESS POINTS FOR THE FORMATION AND CONTINUA TION OF CRACKS, AND MORE THAN LIKELY, ANY CYLINDER NOT YET CRACKED, PROBABLY WILL. (K) 1 L 7 1 3O 3 O 3A15 E5CE 20080717 2008 7 17 2008FA0000437 4 20080618 G 2211 31B641 TRIM SWITCH BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA CONTROL WHEEL FAILED B QPID O OTHER O OTHER NR NOT REPORTED 1 SO 19 362MC 3188E LJ760 AFTER INSTALLATION OF NEW MFG AUTOPILOT SYS, AUTOPILOT COMPUTER TRIM CIRCUITRY FAILED ON INITIAL CHECK OUT. COMPUTER WAS RETURNED TO MFG AND REINSTALLED AFTER REPAIR. TRIM CIRCUITRY FAILED AGAIN AND RETURNED TO MFG. MFG TECH SUPPORT ADVISE D REPLACEMENT OF SUSPECTED BAD TRIM SWITCH ASSY AT THIS TIME AS CAUSE OF REPEATED FAILURE. SWITCHES IN ASSY FAILED ALLOW ING BOTH UP & DOWN COMMANDS AT THE SAME TIME. TRIM SWITCH ASSY PROVIDED BY MFG, WAS REPLACED & COMPUTER REPAIRED & REINS TALLED. TRIM CIRCUITRY FAILED AGAIN AFTER 3 HOURS OF FLT. COMPUTER REPAIRED & REINSTALLED. TRIM CIRCUITRY FAILED ON IN ITIAL CHECKOUT. COMPUTER REMOVED FOR REPAIR & TRIM SWITCH CONFIRMED TO BE CAUSING FAILURE AGAIN. TRIM UP SWITCH STUCK I 1 L 7 2 3T 4 T 3A20 E4EA 20080717 CE 2008 7 17 2008FA0000438 1 20080630 G 2910 605700311 HOSE LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE HYD SYSTEM FAILED E JBGA O OTHER O OTHER NR NOT REPORTED 1 SW 11 260AN 5025 124 PCECA0083 PILOT REPORTED A LOSS OF HYDRAULICS DURING FLIGHT AT CRUISE FL400. INSPECTION REVEALED THAT THE RT ENGINE DRIVEN HYDRAU LIC PUMP, PRESSUE SIDE HYDRAULIC LINE WAS LEAKING, AND ALLOWED THE AIRCRAFT`S HYDRAULIC SYSTEM FLUID TO BE DEPLETED. FU RTHER INSPECTION REVEALED THAT THE LINE HAD FAILED INTERNALLY AND WHEN PRESSURE WAS APPLIED THE HOSE WOULD SWELL AND BEG IN TO LEAK. THE PROBABLE CAUSE OF THE FAIURE IS AGE AND POSSIBLE EMBRITTLEMENT OF THE HOSE. TO POSSIBLY PREVENT RECURR ENCE OF SUCH FAILURES AT TIME INTERVAL FOR REPLACEMENT OF AGEING TEFLON HOSES MAY BE NEEDED. (K) 2 L 7 2 4F 4 F RT A10CE E35NE 20080717 GL 2008 7 17 2008FA0000439 1 20080701 G 2430 BEARING CAP CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO HARTZL HCJ3Y PHCJ3YF1 GL ALTERNATOR CASE CRACKED B YD5R O OTHER O OTHER NR NOT REPORTED 1 GL 15 391CP 1042440 3072 691753 FP6720B PILOT REPORTE TO HAVE AN ALTERNATOR NR 1 FAILURE DURING GROUND PRE-FLIGHT RUN-UP. AC WAS BROUGHT IN FOR MAINTENANCE TO TROUBLESHOOT ALTERNATOR ISSUE. ALTERNATOR BEARING END CAP WHICH IS PART OF THE ALTERNATOR CASE COMPLETED CRACKED OFF AND WAS LYING ON THE ENGINE BAFFLING. AC WAS FURTHER INSPECTED WITH NO OTHER DISCREPANCIES FOUND. ALTERNATOR WAS REPLACED WITH NEW. GROUND AND FLIGHT TESTS CHECK GOOD. (K) 1 L 7 1 3O 3 O NT A00009CH E3SO 5 C P36EA 20080717 SW 2008 7 17 2008FA0000440 1 20080610 G 6720 206011725001 ROD BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL T/R PITCH CHAFED B ULXR O OTHER O OTHER NR NOT REPORTED 1 WP 01 600W 51250 DURING AN INSPECTION OF THE TAIL ROTOR PITCH CONTROL TUBE SLEEVES, WE DISCOVERED THAT BELLCRANK PN 206001763001 HAD BEEN CHAFED INTO BY THE RIVET SECURING THE ROD END OF ROD ASSEMBLY PN 206011725001. THIS WEAR OCCURS WHEN LEVER ASSEMBLY PN 206011722105 PIVOT DURING CONTROL MOVEMENTS, CHANGING THE PLANE OF THE ROD. THE MM DOES NOT TELL YOU WHICH WAY TO INSTA LL THE ROD, HOWEVER ALL OF THE ILLUSTRATIONS SHOW THE RIVETED END OF THE ROD TO BE CONNECTED TO THE BELLCRANK. PLEASE S EE BHT 206L SERIES IPB, FIG 64-1 AND FIG 67-12 AND BHT 206L MM, PARA 67-63, FIG 67-17 DETAIL D. PARA 64-20 AND FIG 64-14 . THIS CAN BE CURED BY INSTALLING THE ROD WITH THE ADJUSTABLE END CONNECTING TO THE BELLCRANK AND THE RIVETED END CONNE 1 G 7 1 3U 3 U H2SW E1GL 20080717 GL 2008 7 17 2008FA0000441 2 20080604 G 7230 23009670 BEARING BELL 407 407 1182206 SW ALLSN 250C 250C47B GL COMPRESSOR FAILED B O OTHER J WARNING INDICATION NR NOT REPORTED 1 SO 05 3WV CAC45603 53713 CAE847787 PILOT REPORTED ENGINE CHIP LIGHT PRECAUTIONARY LANDING MADE TO INVESTIGATE. A CONSIDERABLE AMOUNT OF FERROUS MATERIAL WA S ON THE TOP AND BOTTOM CHIP DETECTORS. NO PENALTY RUNS WERE PERFORMED. AIRCRAFT WAS PLACED ONTO A TRAILER AND MOVED BA CK TO BASE WHERE THE ENGINE WAS REMOVED AND FORWARDED TO THE ENGINE SHOP FOR INVESTIGATION. THE DISMANTLE AND INVESTIGA TION REVEALED THE NR 2 BEARING THAT SUPPORTS THE REAR OF THE IMPELLER HAD FAILED. THE BALL BEARING KEEPER HAD FRACTURED COMPLETELY ACROSS THE SURFACE. AT LEAST ONE OF THE BALLS HAD SPALLED AND ALSO THE OUTER RACE HAD SEVERAL AREAS OF SPALLI NG. THE FAILED BEARING WAS REPLACED, THE REMAINDER OF THE ENGINE OIL SYSTEM WAS FLUSHED WITH NO DISCREPANCIES NOTED. E 1 G 7 1 3U 3 U O H2SW E1GL 20080717 2008 7 17 2008FA0000442 1 20080701 G 3610 AS18954175 COUPLING CFMINT CFM56 CFM567B26US NE ENGINE DUCT MISSING G O OTHER O OTHER NR NOT REPORTED 1 EA 33 894464 DURING GROUND RUN AFTER INSTALLATION, HOT AIR ESCAPED FROM THE NOSE COWL ANTI-ICE DUCT AT THE 12 O`CLOCK POSITION CAUSIN G THERMAL DAMAGE TO THE C-DUCT THERMAL BLANKETS AND TRUST LINK TEFLON WASHERS. INVESTIGATION FOUND DUCT COUPLING PN AS1 895-4-175 MISSING. ENGINE WAS RELEASED FOLLOWING MAINTENANCE TO RECTIFY HIGH OIL PRESSURE INDICATIONS IN FEB 2008. (K) 4 F E00055EN 20080717 EA 2008 7 17 2008FA0000443 2 20080617 G 8530 GUIDE CESSNA 210 T210N 2073456 CE CONT O550 IO550P 17216 EA EXHAUST VALVE OUT OF TOLERANCE C B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 6621A 21063559 AFTER NUMEROUS ATTEMPTS TO TROUBLESHOOT FREQUENT ENGINE MISFIRES OCCURRING PRIMARILY IN THE INITIAL CLIMB STAGES OF FLIG HT, THE ENGINE VALVE TRAIN WAS INSPECTED FOR STICKING VALVES. DIMENSIONAL INSPECTIONS OF THE EXHAUST VALVE GUIDES IN AL L 6 CYLINDERS REVEALED THAT THE EXHAUST VALVE GUIDES WERE BELOW THE MINIMUM ACCEPTABLE DIAMETERS AS PUBLISHED IN THE APP LICABLE O/H MANUAL. IT IS BELIEVED THAT THE EXCESS MATERIAL EXISTS BECAUSE THE GUIDES WERE NOT MEASURED OR REAMED DURIN G THEMFG ASSY PROCESS. CORRECTIVE ACTION NOT AVAILABLE AT THIS TIME. (K) 1 H 7 1 3O 3 O 3A21 E3SO 20080717 2008 7 17 2008FA0000444 4 20080609 G 6113 BULKHEAD CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA PROP SPINNER CRACKED B OMKR K NONE O OTHER IN INSP/MAINT 1 NM 03 537SP 172S8393 DURING A 100 HR INSPECTION, PROPELLER SPINNER FWD BULKHEAD WAS FOUND TO BE CRACKED FROM A PROP BOLT HOLE OUT TOWARD THE OUTER EDGE OF THE BULKHEAD, APPROX 1.5 INCH LONG. THE PROP BOLTS AND THE BULKHEAD WERE REMOVED FRO THE AIRCRAFT. CLOSER INSPECTION SHOWED THE CRACK ORIGINATED FROM THE OUTER APEX OF THE WASHER MARK, NOT THE BOLT HOLE ITSELF. ALSO, ALL BOL T HOLES WERE FOUND TO BE CRACKED IN THE SAME LOCATION (OUTER APEX OF WASHER IMPRESSION), RANGING FROM .2500 TO 1.0 IN LE NGTH. THE MM HAS A NOTE THAT SAYS, "THE MOUNTING BOLT HOLES IN THE FORWARD BULKHEAD MAY BE UNDERSIZED DUE TO THE ORIGIN AL TORQUING OF THE MOUNTING BOLTS". IT IS PLAIN TO SEE THIS CRUSHES THE ALUMINUM, CASUING STRESS CONCENTRATIONS AROUND 1 H 7 1 3O 3 O NT 3A12 1E10 20080717 CE 2008 7 17 2008FA0000445 1 20080611 G 5210 1014300329 PIN BEECH B300 B300 1159232 CE PWA PT6 PT6* 52043 EA PAX DOOR MISSING B XA14 O OTHER O OTHER NR NOT REPORTED 1 SW 17 10TX 3132 FL1 UPPER AFT ENTRANCE DOOR BAYONET SHIFTED OB .7500 INCH CAUSING AC TO DEPRESSURIZE. THIS WAS CAUSED BY A PIN (PN 101-4300 32-9) FALLING OUT OF PLATE (101-4300323) CAUSING ROLLER (PN 50-430037-7) TO FALL OUT. THIS CAUSED ROD (PN 50-430016-11) WITH BOLT (PN 50-430177-5), (ASSY CALLED A DOOR BAYONET), TO SHIFT OUTBOARD .7500 INCH THROUGH AFT DOOR FRAME (PN 50-43 0032-3 INSTALLED 180 DEGREE OUT. THE PINS THAT HOLD THE ROLLERS IN PLACE ARE STAKED. IT LOOKS AS THOUGH OVER TIME THAT THE PIN WORE THE STAKES SMOOTH AND THUS ALLOWING PIN AND ROLLER TO FALL OUT.. STAKED PINS SHOULD BE CHANGED TO COTTER KEYED TYPE PINS TO KEEP THIS FROM HAPPENING ON OTHER AC. CHECK MFG AND THESE HAVE THE COTTER PIN TYPE PINS. (K) 2 L 7 2 4T 3 T RT A24CE E2NE 20080717 2008 7 17 2008FA0000446 1 20080109 G 3500 80130700 CYLINDER OUT OF TOLERANCE B AY54 O OTHER O OTHER NR NOT REPORTED 1 EA 35 GEZJO OXYGEN CYLINDER (PN 801307-00, SN ST26121) ARRIVED AT WORKSHOP ON 9TH JAN, 2008, REMOVED OFF OF G-EZJO FOR HAVING LOW CO NTENTS PRESSURE. ON CLOSE INSPECTION, IT WAS DISCOVERED THAT THE CYLINDER NECK HAD BEEN MARKED WITH HIGH STRESS STAMPS. CYLINDER LAST OVERHAULED BY AVOX. IN THE RIN STAMP, THE NUMBER 1 CLEARLY SHOWS THAT THE INCORRECT STAMPS HAVE BEEN US ED. (K) 20080717 GL 2008 7 17 2008FA0000447 2 20080529 G 7250 23073853 TURBINE WHEEL ALLSN 250C 250C20B 03013 GL ENGINE FAILED B K NONE O OTHER IN INSP/MAINT 1 SO 05 1036 CAT34953 TURBINE ASSY RECEIVED FOR REPAIR DUE TO METAL IN OIL. UPON DISASSEMBLY, IT WAS NOTED THAT THE 1ST STAGE TURBINE WHEEL B LADES WERE MISSING PIECES OF BLADE MATERIAL. THE APPARENT IMBALANCE OF THE GP ROTOR ASSY PRODUCED BY THE MISSING BLADE PIECES CAUSED THE GP STATOR SEAL TO FRACTURE. ONE PORTION OF THE STATOR SEAL BEGAN TO ROTATE WITH THE NR 8 BEARING OUTE R RACE. THE DOWNSTREAM PORTION OF THE STATOR SEAL BELOW THE FRACTURE REMAINED STATIONARY AND THE GRINDING BETWEEN THE S TATIONERY PORTION OF THE SEAL AND THE ROTATING PORTION APPEARS TO BE THE SOURCE OF THE METAL. THE TURBINE WHEEL BLADE T IPS APPEAR TO HAVE FAILED DUE TO HOT - CORROSION SULFIDATION AS DEFINED IN MFG CSL-1210. SOME DOWNSTREAM PORTIONS OF TH 3 U E4CE 20080717 NE 2008 7 17 2008FA0000448 2 20080618 G 7250 1975M56G03 NOZZLE BOEING 777 777224 1385225 NM GE GE90 GE9092B 30036 NE ENGINE FAILED B QEMY O OTHER O OTHER NR NOT REPORTED 1 EA 35 78008 39277 17271 29478 900240 ENGINE SUFFERED AN OVERTEMP AND HPC/HPT ROTOR VIBRATION EXCCEEDANCE. THE CUSTOMER REPORTED METAL PARTICLES IN THE EXHAU ST. DURING ENGINE MODULE DISASSEMBLY AT MFG, IT WAS NOTED THAT THE HPT STAGE 2 NOZZLE ASSY EXHIBITED SIGNIFICANT HARDWA RE DAMAGE TO THE NOZZLE SEGMENTS, STAGE 1 AND STAGE 2 SHROUDS. (K) 2 L 7 2 4F 4 F RT T00001SE E00049EN 20080718 SO 2008 7 18 2008FA0000449 1 20080701 G 5340 7955300 FITTING PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA FUSELG TO WNDSHD CORRODED D O OTHER O OTHER NR NOT REPORTED 1 SO 15 602FT 2841196 STEEL FITTINGS (PN 79553-00) LT AND (PN 79553-01(RT) WERE FOUND WITH SEVERE CORROSION DURING LT AND RT WINDSHIELD REMOVA L, THOSE FITTINGS CARRY STRUCTURAL LOADS AND LEFT UNCORRECTED COULD JEOPARDIZE THE INTEGRITY OF THE UPPER FUSELAGE SECTI ON, PROBABLE CAUSE COULD BE DISSIMILAR METAL CORROSION BETWEEN STEEL AND ALUMINUM AND A FOAM INSTALLED AT FACTORY WHICH KEEP MOISTURE IN, FOUND SAME PROBLEM IN OTHER AC. (K) 1 L 7 1 3O 3 O 2A13 E274 20080717 SO 2008 7 17 2008FA0000450 1 20080701 G 5340 7955301 FITTING PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA FUSLG TO WNDSHLD CORRODED D O OTHER O OTHER NR NOT REPORTED 1 SO 15 602FT 2841196 STEEL FITTING FOUND WITH SEVERE CORROSION DURING LT AND RT WINDSHIELD REMOVAL, THOSE FITTING CARRY STRUCTURAL LOADS AND LEFT UNCORRECTED COULD JEOPARDIZE THE INTEGRITY OF THE UPPER FUSELAGE SECTION, PROBABLE CAUSE COULD BE DISSIMILAR METAL CORROSION BETWEEN STEEL AND ALUMINUM AND A FOAM INSTALLED AT FACTORY WHICH KEEP MOISTURE IN, I HAVE FOUND THE SAME PROBL EM IN OTHER AC. (K) 1 L 7 1 3O 3 O 2A13 E274 20080718 GL 2008 7 18 2008FA0000451 1 20080609 G 7810 ELBOW CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO RT EXHAUST MISINSTALLED G K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 04 266SR 2626 WHILE ACCOMPLISHING SERVICE ADVISORY 08-03 IT WAS DISCOVERED THAT RT SIDE EXHAUST ELBOW WHICH IS INSERTED BETWEEN WASTEG ATE OUTLET FITTING AND TAILPIPE WAS ORIGINALLY INSTALLED BACKWARDS A THE FACTORY. THIS INCORRECT INSTALLATION RESULTED I N ELBOW HAVING ONLY A .1875 INCH ENGAGEMENT WITH WASTEGATE FITTING AND A 2.2500 INCH ENGAGEMENT IN TAILPIPE. THE .3750 INCH ENGAGEMENT COULD HAVE RESULTED IN SEPARATION OF JOINT. THE 2.2500 INCH ENGAGEMENT CAUSED A 1 INCH OBSTRUCTION IN E XHAUST GAS PATH. (K) 1 L 7 1 3O 3 O NT A00009CH E3SO 20080717 EU 2008 7 17 2008FA0000452 1 20080610 G 3411 PITOT TUBE AEROSP ATR72 ATR72212 8680945 EU PWA PW120 PW127 NE OBSTRUCTED D C ABORTED TAKEOFF P NO WARNING INDICATION TO TAKEOFF 1 EA 21 820FX 248 ON TAKEOFF ROLL THE F/O AIRSPEED INDICATOR REMAINED AT ZERO. THE TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE G ATE. MAINTENANCE FOUND FOD (SPIDER) IN THE PITOT TUBE. THE TUBE WAS CLEARED AND THE SYSTEM CHECKED GOOD. THE AIRCRAFT WAS RETURNED TO SERVICE. (K) 2 H 7 2 4T 4 T RT A53EU E20NE 20080717 SO 2008 7 17 2008FA0000453 1 20080510 G 3220 BUNGEE PIPER PA28 PA28R201T 7102813 SO LT NOSE WHEEL BROKEN G O OTHER O OTHER NR NOT REPORTED 1 WP 11 9581C 28R7803267 THE PILOT SLOWED FOR LANDING AND DEPLOYED THE GEAR. A SAFE CONDITION WAS INDICATED FOR THE MAINS, BUT NOT FOR THE NOSE. THE GEAR WAS CYCLED; HOWEVER AGAIN, NO SAFE NOSE INDICATION. AN EMERGENCY GEAR DEPLOYMENT WAS ATTEMPTED BUT STILL, NO G REEN NOSE LIGHT. THE PILOT ASSUMED THAT DUE TO PREVIOUS PROBLEMS WITH THE LANDING GEAR INDICATOR LIGHTS THAT THE NOSE G EAR HAD PROBABLY DEPLOYED AND CONTINUED THE LANDING. IMMEDIATELY AFTER TOUCHDOWN, THE NOSE LANDING GEAR COLLAPSED. POS INCIDENT INVESTIGATION REVEALED THE LT NOSE WHEEL BUNGEE ASSY; PN 76425-03 HAD BROKEN AND WEDGE IN THE NOSE LANDING GEAR PREVENTING EXTENSION. THE FAILURE APPEARS TO HAVE OCCURRED WHEN THE GEAR WAS IN THE RETRACTED POSITION. (K) 1 L 7 1 3O 2A13 20080718 CE 2008 7 18 2008FA0000454 1 20080630 G 5510 45A21085003 BRACKET BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE HORIZONTAL STAB CRACKED B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 184AR 4512 RK34 HORIZ STAB IB RIBS LT AND RT ROLLER BRACKETS FOUND CRACKED. REPLACED PN 45A21085-003 LT FWD BRACKET. PN 45A21086-003 LT AFT BRACKET, PN 45A21085-004 RT FWD. BRACKET PN 45A21086-004 RT AFT BRACKET WITH IMPROVED PN 128-620021-0001 (LT) AND PN 128-620021-0002 (RT) BRACKETS IAW MFG COMMUNIQUÉ NR 83. REPLACED PN 45A21146-005 RIB (LT) AND PN 45A21146-006 RIB (RT) WITH IMPROVED PN 128-620022-0001 (LT) AND PN 128-620022-0002 (RT) RIBS IAW MFG COMMUNIQUÉ NR 83. INSPECTION NEWLY I NCORPORATED INTO MM 5-20-02 INSP GUIDE AND SECTION 55-30-00. (K) 2 H 7 2 4F 4 F RT A16SW E25EA 20080718 CE 2008 7 18 2008FA0000455 1 20080626 G 2435 M835366026L RELAY RAYTHN 390 390 7150030 CE STARTER GEN STUCK B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 404JM 444 RB167 INVESTIGATED PILOT REPORT OF RT ENG STARTER/GEN NOT DISENGAGING FROM START FUNCTION AFTER ENG START. FOUND 80K5 RT ENG S TART LATCH RELAY STUCK IN START FUNCTION. RT STARTER/GEN TERMINAL COVER AND COOLING AIR INLET DUCT SHOW SIGNS OF OVERHE ATING. INSPECTED STARTER/GEN, REPLACED 80K5 RELAY, STARTER/GEN FUNCTIONS NORMAL. HAVE REPLACED NUMEROUS 80K3 AND 80K5 ST ART LATCH RELAYS IN 390 SERIES AC THAT HAVE FAILED WITH SHORT TIS. RECOMMEND MFG INVESTIGATE WHETHER THIS IS A RELAY QC OR DESIGN/INSTALLATION ISSUE. (K) 1 L 7 2 3F RT A00010WI 20080718 CE 2008 7 18 2008FA0000456 1 20080626 G 3020 5188001 VALVE RAYTHN 390 390 7150030 CE ANTI ICE SYSTEM STUCK B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 404JM RB167 REPLACED FAILED RT ENGINE ANTI-ICE VALVE WITH 0 TSOH VALVE ASSY SUPPLIED BY HBC/RAPID; O/H BY MFG, WO R73432, DATED 5/22 /2008. VALVE ASSY FAILED IN STUCK IN OPEN POSITION, WHEN INITIALLY TESTED FOLLOWING INSTALLATION. REPLACED VALVE WITH ANOTHER RAPID-SUPPLIED VALVE ASSY, OPERATIONS NORMAL. RECOMMEND MFG INVESTIGATE WHETHER THIS IS A QC ISSUE OR IF VALVE A SSY SUBJECTED TO HIDDEN INTERNAL DAMAGE DUE TO ROUGH HANDLING DURING SHIPPING. (K) 1 L 7 2 3F RT A00010WI 20080718 SO 2008 7 18 2008FA0000457 2 20080710 G 7414 07010003 MAGNETO CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO LEFT BURNED D GICR K NONE O OTHER IN INSP/MAINT 1 NM 01 662AJ 1632 DURING ROUTINE MAINT, THE LT MAGNETO WAS DISCOVERED OUT OF TIME TO ENGINE. WAS UNABLE TO RE-TIME MAG WITHOUT RE-STABBIN G. WHEN REMOVED, OPENED COVER AND FOUND INTERNAL PLASTIC COMPONENTS BURNED WITH SIGNIFICANT AMOUNT OF LOOSE (BURNED) PL ASTIC PARTS LOOSE WITHIN MAGNETO. THIS MAGNETO WAS SUPPLIED WITH NEW ENGINE 261.3 HOURS AGO, OTHER THAN MAG TO ENGINE T IMING BEING OFF, THERE WAS NO INDICATION (OPERATIONALLY) OF A PROBLEM. THIS IS FIRST TIME HAVE SEEN THIS KIND OF DAMAGE TO MAGNETO AND HAVE IT STILL OPERATE. PERFORM 500 HR INTERNAL INSP OF MAGS AND BEING HALF WAY THERE, IT THEORETICALLY WOULD NOT HAVE BEEN DISCOVERED UNTIL 500 HOUR MARK OR TOTAL FAILURE OF MAGNETO. (K) 1 L 7 1 3O 3 O NT A00009CH E1CE 20080718 CE 2008 7 18 2008FA0000458 1 20080702 G 3230 50452112 FORK CESSNA 340 340A 2076405 CE CONT O520 TSIO520* 17040 SO MLG FRACTURED G K NONE O OTHER IN INSP/MAINT 1 GL 17 60PP 340A0073 LANDING GEAR DOWN ACTUATION ON 7/2/2008 PRODUCED AN INDICATED UNSAFE NOSE LANDING GEAR LIGHT. AN ATTEMPT TO ACTUATE MAN UAL EXTENSION OF THE LANDING GEAR PROVED UNSUCCESSFUL SINCE THE NOSE LANDING GEAR DID NOT EXTEND TO A DOWN AND LOCKED PO SITION. SUBSEQUENT DAMAGE RESULTED TO THE AIRCRAFT WHEN THE NOSE LANDING GAR COLLAPSED UPON LANDING. AN INSPECTION OF THE AC REVEALED THAT NLG LINKAGE "ADJUSTING FORK" FRACTURED THEREBY DISABLING THE EXTENSION OF THE NLG FROM EXTENDING TO A DOWN AND LOCKED POSITION. EVIDENCE SUGGESTS THAT THE FRACTURE WAS PROGRESSIVE IN NATURE DUE TO INDICATIONS THAT A DE GRADATION TO THE STRUCTURE OF THIS COMPONENT EXISTED PRIOR TO FAILURE OF THIS COMPONENT. (K) 1 L 7 2 3O 3 O 3A25 E8CE 20080718 SW 2008 7 18 2008FA0000459 1 20080701 G 2400 102149 METER BELL 206 206B 1181511 SW ALLSN 250C 250C20J 03013 GL MALFUNCTIONED C DDZR O OTHER O OTHER NR NOT REPORTED 1 CE 03 6BU 7003 4034 CAE270422 AC MAINT HOBBS METER FOUND RUNNING SLOW. THIS PROBLEM CAUSES THE ACTUAL TT OF THE AC TO BE INCORRECT. THIS PROBLEM CAU SED THE AC TO OVER RUN INSPECTIONS, AND TIME LIFE ITEM. PROBABLE CAUSE OF THIS PROBLEM, HOBBS METERS GETTING OLD AND WO RN OUT. RECOMMENDATION TO PREVENT THIS PROBLEM: MAINT HOBBS METER, TO BE CHECKED BY PILOTS CLOCK WEEKLY TO MAKE SURE ME TER IS RUNNING PROPERLY. (K) 1 G 7 1 3U 3 U H2SW E4CE 20080718 SW 2008 7 18 2008FA0000460 1 20080701 G 2400 102149 METER BELL 206 206L4 1182110 SW ALLSN 250C 250C30P 03013 GL MALFUNCTIONED B DDZR O OTHER O OTHER NR NOT REPORTED 1 CE 03 75TV 7845 52095 CAE895710 AC MAINT HOBBS METER FOUND RUNNING SLOW. THIS PROBLEM CAUSES THE ACTUAL TT OF THE AC TO BE INCORRECT. THIS PROBLEM CA USED THE AC TO OVER RUN INSPECTIONS, AND TIME LIFE ITEM. PROBABLE CAUSE OF THIS PROBLEM, HOBBS METERS GETTING OLD AND W ORN OUT. RECOMMENDATION TO PREVENT THIS PROBLEM; MAINT, HOBBS METER TO BE CHECKED BY PILOTS CLOCK WEEKLY TO MAKE SURE M ETER IS RUNNING PROPERLY. 1 G 7 1 3U 3 U NC H2SW E1GL 20080718 NM 2008 7 18 2008FA0000461 1 20080703 G 5315 FLOORBEAM BOEING 737 73783N 13844HI NM GE CFM56 CFM56* 13802 NE BS294 CORRODED B DU4R O OTHER O OTHER NR NOT REPORTED 1 EA 39 304TZ 30675 DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AROUND FASTENERS AT BS 294 FROM RBL-2 TO R BL 43. SO NR 245010 NR 27077. (K) 2 L 7 2 4F 4 F RT A16WE E2GL 20080718 NM 2008 7 18 2008FA0000462 1 20080704 G 5315 FLOORBEAM BOEING 737 73783N 13844HI NM GE CFM56 CFM56* 13802 NE BS 328, RBL26 CORRODED B DU4R O OTHER O OTHER NR NOT REPORTED 1 EA 39 304TZ 30675 DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AT BS 328, RBL 26 AFT SIDE OF BEAM FOUND T O BE BEYOND LIMITS. (K) 2 L 7 2 4F 4 F RT A16WE E2GL 20080718 NM 2008 7 18 2008FA0000463 1 20080703 G 5315 FLOORBEAM BOEING 737 73783N 13844HI NM GE CFM56 CFM56* 13802 NE BS328 CORRODED B DU4R O OTHER O OTHER NR NOT REPORTED 1 EA 39 304TZ 30675 DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AT BS 328 FROM RBL 13 TO RBL 50. (K) 2 L 7 2 4F 4 F RT A16WE E2GL 20080718 NM 2008 7 18 2008FA0000464 1 20080707 G 5315 FLOORBEAM BOEING 737 73783N 13844HI NM GE CFM56 CFM56* 13802 NE BS 344 CHAFED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 304TZ 30675 DURING SCHEDULED INSP, FOUND CLIP NUTS CHAFING FLOORBEAM IN FWD CABIN BS 344, LBL 0 TO LBL 55. (K) 2 L 7 2 4F 4 F RT A16WE E2GL 20080718 NM 2008 7 18 2008FA0000465 1 20080707 G 5315 FLOORBEAM BOEING 737 73783N 13844HI NM GE CFM56 CFM56* 13802 NE BS344, LBL10 CORRODED B DU4R O OTHER O OTHER NR NOT REPORTED 1 EA 39 304TZ 30675 DURING SCHEDULED INS, FUND FWD CABIN BS 344, LBL10, FLOORBEAM CORRODED. (K) SO 245010, NR27110 2 L 7 2 4F 4 F RT A16WE E2GL 20080718 2008 7 18 2008FA0000466 4 20080711 G 3460 4052500927 COMPUTER BOEING 767 767* NM FMC FAILED W ANCF O OTHER O OTHER NR NOT REPORTED 1 SO 23 421AV 25421 AIR TURNBACK DUE PILOT REPORT 4273256-1; EICAS MSG L FMC FAIL DISPLAYED. FIM 34-61-00 FOLLOWED L FMC PWR RESET ALL INDI CATIONS NORMAL. PLS MONITOR FURTHER. AS A PREVENTIVE ACTION DURING OVERNIGHT; IAW AMM 34-61-01/401 WAS REMOVED AND REPL ACED THE FLIGHT MANAGEMENT COMPUTER. (K) 2 L 7 2 4F RT A1NM 20080718 GL 2008 7 18 2008FA0000467 1 20080512 G 6100 SNAP RING NAMER T6 AT6F 6400420 GL HAMSTD 23D 23D40 NE PROP GOVERNOR MISSING D O OTHER O OTHER NR NOT REPORTED 1 SW 15 767WB 12142537 PROPELLER WAS INSTALLED IMPROPERLY. SNAP RING THAT HOLDS ON PROP NUT AND CRANKSHAFT EXTENSION WAS NOT INSTALLED. THIS ALLOWED CRANKSHAFT EXT TO UNSCREW AND LET PROP GOVERNOR PRESSURE OF 180 LBS TO BE PUT ON ENGINE AND PROPELLER. THIS CAU SED PROPELLER AND ENG TO LEAK OIL. (K) 1 L 7 1 3R A2575 6 C P719 20080718 CE 2008 7 18 2008FA0000468 1 20080701 G 5344 NAS405 HINGE BEECH 80 65B80 1152812 CE LYC O720 IO720A1B 41546 EA CABIN DOOR CRACKED C O OTHER O OTHER NR NOT REPORTED 1 WP 13 44MA LD412 L15595YA (2) OF THE HINGE LINKS HAD CRACKED OFF ON ONE END. UPON DISASSEMBLY IT WAS DETERMINED THAT A CRACK HAD FORMED LENGTHWIS E BETWEEN THE FASTENERS AND THE HINGE LINKS. POSSIBLE CAUSE MAY HAVE BEEN FATIGUE. (K) 1 L 7 2 3O 3 O 3A20 1E15 20080721 GL 2008 7 21 2008FA0000469 1 20080616 G 5340 MOUNT CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO ALTERNATOR CRACKED C O OTHER O OTHER NR NOT REPORTED 1 SW 15 710CD 849 100575 0013 685689 STANDBY ALTERNATOR MOUNTING FLANGE CRACKED IN (2) PLACES. OIL GALLING AT MOUNT FLANGE WHERE CRACKS WERE NOTED. (K) 1 L 7 1 3O 3 O NT A00009CH E3SO 20080721 SW 2008 7 21 2008FA0000470 1 20080701 G 5343 ED12758 CLEVIS GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE33112UHR WP RT MLG ACTUATOR BROKEN B BOER K NONE O OTHER IN INSP/MAINT 1 GL 19 122AV 11235 WHEN FLYING IN TO LAND, LANDING GEAR WAS SELECTED DOWN, RT MLG CAME DOWN ABOUT A FOOT AND STOPPED ON (2) ATTEMPTS, UPON (3RD) ATTEMPT GEAR CAME DOWN AND INDICATED LOCKED. AC WAS BROUGHT INTO OUR SHOP AND WHEN THE RT MLG WAS INSPECTED, IT W AS FOUND THAT CLEVIS ASSY FROM UPPER STRUT HSG TO MAIN ACTUATOR HAD BROKEN IN (2) PIECES, (1) PART STILL ATTACHED TO ACT UATOR AND THE OTHER WAS STILL IN THE UPPER STRUT ASSY. AN OEM SL REQUIRING THAT THE CLEVIS BE REMOVED EA 500 HR AND INSP ECTED BY A LEVEL II INSPECTOR. THIS CLEVIS HAD 274 HR ON IT SINCE THAT INSPECTION, WHERE IT WAS FOUND AIRWORTHY. ON TH ESE AC THERE IS A MAIN ACTUATOR AND AN AUXILLIARY ONE WITH ITS OWN CLEVIS MOUNTING ALSO. LANDING GEAR CAME DOWN AND LOC 1 H 7 2 3T 4 T 2A4 E4WE 20080721 NM 2008 7 21 2008FA0000471 1 20080601 G 7700 PT25 SENSOR BOEING 777 7772Q8 1385238 NM GE GE90 GE9094B 30045 NE RT ENGINE FAILED W ASMF O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SW 23 745AM 10004 32718 900475 AC RETURNED TO DEPARTURE DUT TO RT ENGINE STALLED. MAINT PERFORMED FIM 75-21 TASK 822 AND STALL INSPECTION IN 1ST, 5TH AND 9TH HPC STAGES. NO DAMAGES WERE DETECTED IAW MM 71-00-00. RT PT25 SENSOR WAS REPLACED IAW MM 73-21-63, TESTED CORR ECT. THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO AIRCRAFT LANDED WITH 211, 400 KGS AND MAXIMUM LANDING WEIGHT IS 213 KGS. (K) 2 L 7 2 4F 4 F RT T00001SE E00049EN 20080721 NE 2008 7 21 2008FA0000472 2 20080606 G 7200 ENGINE BOEING 777 7772Q8 1385238 NM GE GE90 GE9094B 30045 NE RIGHT FAILED W ASMF K NONE O OTHER IN INSP/MAINT 1 SW 23 745AM 10838 32718 DURING TRANSIT CHECK, THE RT ENGINE WAS DETECTED WITH DAMAGES. MAINT PERFORMED BOROSCOPIC INSPECTION, DETECTING DAMAGES OUT OF LIMITS, SO RT ENGINE WAS REPLACED AND TESTED IAW MM 71-00-02 AND 71-00-00, ALL CORRECT. (K) 2 L 7 2 4F 4 F RT T00001SE E00049EN 20080721 NE 2008 7 21 2008FA0000473 2 20080619 G 7200 ENGINE DOUG DC9 DC987 3022087 WP PWA JT8 JT8D219 52053 NE RIGHT VIBRATION W ASMF O OTHER E J VIBRATION/BUFFET WARNING INDICATION NR NOT REPORTED 1 SW 23 205AM 49405 CAPTAIN REPORTED STRONG VIBRATION IN RT ENGINE WITH EPR`S BETWEEN 1.7 AND 1.75. TECHS VERIFIED THE RT ENGINE CONDITION AND PERFORMED OPERATIONAL TEST IAW AMM 71-00-01 FOUND ALL CORRECT. VIBRATION WAS WITHIN LIMITS (0.4 UNITS INDICATED). ( K) 2 L 7 2 4F 4 F RT A6WE E9NE 20080725 NM 2008 7 25 2008FA0000474 1 20080709 G 5230 SKIN BOEING 737 737448 13844BU NM CFMINT CFM56 CFM563C 13802 EU CARGO DOOR DENTED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 742VA 24773 DURING SCHEDULED INSPECTION, FOUND NUMEROUS DENT ON AFT CARGO EXT DOOR SKIN. S/O 312001, OPS 24422. (K) 2 L 7 2 4F 4 F RT A16WE E21EU 20080728 NM 2008 7 28 2008FA0000475 1 20080627 G 5315 FLOORBEAM BOEING 737 737448 13844BU NM CFMINT CFM56 CFM563C 13802 EU BS 986 CORRODED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 742VA 24773 DURING SCHEDULED INSPECTION, FOUND CORROSION ON UNDERSIDE OF "T" CAP REPLACEMENT 986.5 AROUND ATTACH HOLES BL 29R TO BL 29L, NUMEROUS HOLES. (K) 2 L 7 2 4F 4 F RT A16WE E21EU 20080725 WP 2008 7 25 2008FA0000476 1 20080617 G 3245 95502677 WHEEL DOUG DC9 DC983 3022083 WP PWA JT8 JT8D* NE NLG LOOSE W ANCF C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 SO 23 160BS 1211 53463 REJECTED TAKEOFF, DURING T/O ROLL, THERE WAS AND ABNORMAL AND ABRUPT VIBRATION IN THE NOSE SECTION. IAW AMM 32-21-04, P AGE 201/210 WAS CHECKED TORQUE LINKS ASSY BY LOOSE AND ADJUSTMENT ALSO WERE CHECK BOTH NOSE WHEELS, IAW AMM 32-40-02 PAG E 201, PRESS IN BOTH WHEELS 150 PSI IAW AMM 12-16-01 AND IAW AMM 32-22-01, PAGE 201 WERE CHECK BOTH DOORS AND LINKAGE. (K) 2 L 7 2 4F 4 F RT A6WE E2EA 20080725 NM 2008 7 25 2008FA0000477 1 20080602 G 2130 1305027 SELECTOR BOEING 767 767284 1385184 NM CABIN PRESSURE INOPERATIVE W ANCF O OTHER J WARNING INDICATION CR CRUISE 1 SO 23 988AN 24742 AIR TURN BACK, CABIN ALT, CABIN ALTITUDE LIGHT EICAS MSG DISPLAYED OPERATIONAL AND MANUAL MODE RESTORED CABIN PRESS CABI N AUTO INOP 1 AND 2. IAW AMM 21-31-01/401. CABIN PRESSURE SELECTOR WAS REPLACED AND WAS ACCOMPLISHED CABIN PRESSURE CO NTROL SYS, OPS TEST IAW TASK 21-31-00-705-001. TEST SATISFACTORY. (K) 2 L 7 2 4F RT A1NM 20080725 NM 2008 7 25 2008FA0000478 1 20080618 G 5610 WINDOW BOEING 767 767259 1385136 NM COCKPIT LEAKING W ANCF C ABORTED TAKEOFF W INADEQUATE Q C TO TAKEOFF 1 SO 23 985AN 24618 REJECTED TAKEOFF, VERY STRONG NOISE AT 2R WINDOW DURING ROLL. IT WAS APPLY SEALANT IN THE FINISH AROUND THE WINDOW EDGE IAW AMM 56-11-00 PAGE 801, DID THE WINDOW TEST IAW AMM 56-11-02, PAGE 601, TEST OK. (K) 2 L 7 2 4F RT A1NM 20080725 NM 2008 7 25 2008FA0000479 1 20080617 G 2750 FLAP SYSTEM BOEING 767 767283ER 1385149 NM TE FLAPS MALFUNCTIONED W ANCF O OTHER J WARNING INDICATION LD LANDING 1 SO 23 728CG 24728 EMERGENCY LANDING, EICAS MSG TE FLAP DISAGREE DISPLAYED, TRAILING EDGE LIGHT ILLUMINATED WHEN ANY TE FLAP POSITION SELEC TED. FLAP FAIL TO MOVE SELECTED POSITION. IAW FIM 27-51-00, FIG 105, BLOCKS 1,21,22,23,43 WAS ACCOMPLISHED AND IAW FIM 27-51-00, FIG 104 BLOCK 1 TO 4 IT IS OK, FSEU BITE WAS ACCOMPLISHED. (K) 2 L 7 2 4F RT A1NM 20080725 CE 2008 7 25 2008FA0000480 1 20080415 G 3233 2317100016 ACTUATOR LEAR 60 60LEAR 5170707 CE NLG FAILED G K NONE O OTHER IN INSP/MAINT 1 SO 14 50038 THE NLG ACTUATOR HAD IMPACT MARKS FROM THE LOCKING BALLS IN THE LOCKING CHANNEL. THESE IMPACT MARKS ALSO PUSHED PISTON M ATERIAL OUT OF THE CHANNEL CAUSING INTERFERENCE WITH THE LOCKING SLEEVE. THIS INTERFERENCE CREATED METAL SHAVINGS THAT INTERFEERED WITH THE DOWN LOCK MECHANISM. (K) 2 L 7 2 4F RT A10CE 20080725 EU 2008 7 25 2008FA0000481 1 20080702 G 2697 0292697390 CONNECTOR SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE FIRE DETECTION CONTAMINATED B QMLR A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 NM 03 902CF 3746 3630 22351 DURING CRUISE FLIGHT, THE ENGINE FIRE LIGHT ILLUMINATED. DURING THE DESCENT FOR A PRECAUTIONARY LANDING, THERE WAS NO S MOKE TRAILING THE AC AND THE ENGINE FIRE LIGHT EXTINGUISHED AND ILLUMINATED SEVERAL TIMES. AFTER SECURING THE AC UPON L ANDING, THE PILOT INSPECTED THE ENGINE AREA AND NO FIRE DAMAGE WAS NOTED. THE MAINTENANCE STAFF CAME OUT AND FOUND MOIST URE IN THE CONNECTOR PLUG ON THE FIRE DETECTION SYSTEM. AFTER CLEANING AND INSPECTING THE SYSTEM, THE PILOT PERFORMED A CHECK FLIGHT AND THE AC WAS RETURNED TO SERVICE. (K) 1 G 7 1 3U 3 U H9EU E00054EN 20080725 EU 2008 7 25 2008FA0000482 1 20080706 G 2150 060018 BELT SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE AIR CONDITIONER BROKEN B QMLR A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 NM 03 152AC 3574 IMMEDIATELY AFTER TAKEOFF AND LEVELING FOR CRUISE, THE AIR CONDITIONER WAS TURNED ON. WITHIN A SHORT TIME A STRONG ACRI D SMELL WAS PRESENT IN THE AIRCRAFT. THE SOURCE OF THE SMELL WAS UNKNOWN IN FLIGHT. THE AIRCRAFT WAS IMMEDIATELY LANDED NEXT TO A HARD-SURFACE ROAD JUST SOUTH OF THE HOSPITAL IN A SOY BEAN FIELD. THE SKIDS WERE DIRECTLY BETWEEN THE ROWS A ND NO DAMAGE WAS DONE TO THE FIELD BY THE AIRCRAFT. AN AMBULANCE WAS IMMEDIATELY DISPATCHED TO THE SCENE AND THE PATIEN T TRANSFERRED TO THE AMBULANCE FOR TRANSPORT. THE DUTY MECHANIC WAS IMMEDIATELY CALLED. THE MECHANIC INSPECTED THE AIR CRAFT, DETERMINED THE CAUSE OF THE ACRID SMELL AS THE AIR CONDITIONER BELT. THE MECHANIC THEN INSPECTED THE AIR CONDITIO 1 G 7 1 3U 3 U H9EU E19EU 20080725 EU 2008 7 25 2008FA0000483 1 20080704 G 2150 060018 BELT SNIAS 350 AS350B3 8680954 EU TMECA ARRIUS ARRIUS2B1 NE AIR CONDITIONER BROKEN B QMLR A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 NM 03 105LN 3249 GROUND CREW NOTICED THE SMELL OF FUEL AND VAPOR COMING FROM AIRCRAFT AFTER LIFTING FROM SCENE. PIC NOTIFIED OF THE CIRC UMSTANCES. PIC MADE A PRECAUTIONARY LANDING WITH PATIENT ON BOARD. PIC DETERMINED THAT THE VAPOR WAS COMING FROM THE AI R CONDITIONER, AND NO FUEL LEAK. (K) 1 G 7 1 3U 3 U H9EU E34NE 20080725 CE 2008 7 25 2008FA0000484 1 20080516 G 2497 WIRE CESSNA 208 208B 2073701 CE STARTER GEN SHORTED D K NONE O OTHER IN INSP/MAINT 1 WP 21 208B0989 ON (2) RECENT OCCASIONS (2) AIRCRAFT HAVE HAD IDENTICAL DISCREPANCIES WITH THE STARTER ENERGIZED (SE) CIRCUIT. DURING A NORMAL START THE SE ANNUNCIATOR DID NOT EXTINGUISH NORMALLY/AUTOMATICALLY AS THE ENGINE NG INCREASES. THE ANNUNCIATOR S TAYS ON UNTIL THE PILOT MOVES THE STAT SWITCH TO "OFF" AT WHICH TIME THE LIGHT GOES OUT AND THE GENERATOR COMES ON-LINE. TROUBLESHOOTING IN BOTH OF THESE CASES REVEALED HIGH RESISTANCE IN THE SPEED SENSOR CIRCUIT. FURTHER INSPECTION REVEA LED THAT THIS WAS DUE TO POOR WORKMANSHIP (CRIMPED AND POORLY SOLDERED) ON THE WIRE CONNECTIONS INSIDE THE STARTER/GEN ( S/G CONNECTOR. WIRE WAS PINCHED BETWEEN CONNECTOR AND CASE. IN BOTH CASES THE S/G HAD BEEN RECENTLY OVERHAULED. (K) 1 H 7 1 3T A37CE 20080725 NE 2008 7 25 2008FA0000485 2 20080709 G 7320 256072 FLOW DIVIDER CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE NR 1 ENGINE FUEL FAILED B B3OR A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SW 03 6001L 5500169 71709 DURING CLIMB OUT AFTER TAKEOFF, NR 1 ENGINE COULD ONLY PRODUCE 85 PERCENT N1. WHILE RETURNING TO BASE , ENGINE SHUT ITS ELF DOWN ON 2 MILE FINAL. TROUBLESHOOTING FOUND THAT FUEL FLOW DIVIDER HAD MALFUNCTIONED. FUEL FLOW DIVIDER WAS REMOVE D FROM SERVICE, AND REPLACED WITH AN OVERHAULED UNIT. AIRCRAFT WAS RETURNED TO SERVICE. (K) 1 L 7 2 4F 4 F A22CE E1NE 20080725 2008 7 25 2008FA0000486 4 20080618 G 2200 TRIM SWITCH BEECH 90 C90 1152913 CE AUTO PILOT FAILED B QPIR K NONE O OTHER IN INSP/MAINT 1 SO 19 362MC 3188E LJ760 AFTER INSTALLATION OF NEW AUTOPILOT SYSTEM, AUTOPILOT COMPUTER TRIM CIRCUITRY FAILED ON INITIAL CHECK OUT, 10/02/2007. COMPUTER WAS RETURNED TO MFG AND REINSTALLED AFTER REPAIR. TRIM CIRCUITRY FAILED AGAIN AND WAS RETURNED TO MFG ON 1/18/ 2008. TECH SUPPORT ADVISED REPLACEMENT OF SUSPECTED BAD TRIM SWITCH ASSY AT THIS TIME AS CAUSE OF REPEATED FAILURE. MI CRO SWITCHES IN ASSY FAILED ALLOWING BOTH UP AND DOWN COMMANDS AT THE SAME TIME. TRIM SWITCH ASSY PROVIDED WAS REPLACED AND COMPUTER REPAIRED AND REINSTALLED. TRIM CIRCUITRY FAILED AGAIN AFTER (3) HOURS OF FLIGHT. COMPUTER WAS REPAIRED A ND REINSTALLED ON 2/17/2008. TRIM CIRCUITRY FAILED ON INITIAL CHECKOUT. COMPUTER WAS REMOVED FOR REPAIR AND THE TRIM S 1 L 7 2 3T 3A20 20080725 2008 7 25 2008FA0000487 3 20080717 G 6110 D5258 BULKHEAD BEECH 33 F33A 1151425 CE CONT O520 IO520* 17032 SO PROP MOUNT CRACKED B CNZ2 K NONE O OTHER IN INSP/MAINT 1 WP 01 500JL 1279 CE1603 PROPELLER SPINNER BULKHEAD CRACKING BETWEEN ATTACH BOLT HOLES IN (2) PLACES. CRACK COULD BE INDUCED FROM VIBRATION. INS PECT VISUALLY EVERY PRE-FLIGHT. A BETTER HEAT TREATING PROCESS MAY STRENGTHEN THE BULKHEAD AND REDUCE THE CRACKING FROM VIBRATION. (K) 1 L 7 1 3O 3 O 3A15 E5CE 20080725 EA 2008 7 25 2008FA0000488 2 20080423 G 7210 3028266 HOUSING PWA PT6 PT6A27 52043 EA RGB BROKEN B UTUR K NONE O OTHER IN INSP/MAINT 1 SO 19 PCE41761 ABOUT 12 INCHES OF THE RGB FRONT HOUSING SPLINES WERE FOUND BROKEN OFF DUE TO FATIGUE CRACK. (K) 4 T E4EA 20080725 CE 2008 7 25 2008FA0000489 1 20080620 G 5410 109910029165 INLET BEECH 90 C90A 1152911 CE LWR AFT COWLINGS CRACKED B O OTHER O OTHER NR NOT REPORTED 1 GL 05 5115H 901 LJ1705 LT AND RT WELD ASSY CRACKED ALONG A WELDED SEAM. THE CRACKS ARE APPROXIMATELY 12 INCHES LONG. THESE WELD ASSY ARE A PO RTION OF THE ENGINE INLET. A PORTION OF THE INLET AIR IS USED FOR THE OIL COOLER AND SOME AIR IS BYPASSED AND EXITS FRO M THE LOWER PORTION OF THE COWLING. THE CRACK IN THE WELD ASSY HAPPENED AT THE UPPER WELDED SEAMS IN THE BYPASS PORTION OF THE DUCT. THE CRACKS POSED NO POTENTIAL PROBLEM OF BEING INGESTED INTO THE ENGINE. WE HAVE COMMUNICATED THIS ISSUE WITH THE MFG OF THE AC. WE DO NOT KNOW OR WANT TO SPECULATE AT THIS TIME WHAT CAUSED THE PROBLEM OR ARE THERE ANY RECOM MENDATIONS TO PREVENT IT FROM HAPPENING AGAIN. OUR ONLY RECOMMENDATION IS TO INSPECT THIS AREA IN BOTH LT AND RT COWLING 1 L 7 2 3T RT 3A20 20080728 NE 2008 7 28 2008FA0000490 2 20080622 G 7200 ACOUSTIC LINER DOUG DC9 DC987 3022087 WP PWA JT8 JT8D219 52053 NE LEFT DAMAGED W ASMF O OTHER O OTHER NR NOT REPORTED 1 SW 23 216AM 45271 7361 49586 AC RETURNED TO PLATFORM, DURING ENGINE ACCELERATION UP TO 1.4 EPR, STRONG NOISE IN THE RT ENG WAS HEARD. MAINT PERFORME D AN INSPECTION AND DETECTED ACOUSTIC LINER DELAMINATION OF THE DIFFUSER OUTER FAN DUCT, BUT WITHIN LIMITS TO OPERATE TE N HOURS IAW MM 72-00-00. AC, DURING OVERNIGHT CHECK, THE RT ENG WAS REPLACED AND TESTED IAW MM 71-00-02 AND MPCM 71-00- 01, ALL CORRECT. (K) 2 L 7 2 4F 4 F RT A6WE E9NE 20080728 GL 2008 7 28 2008FA0000491 2 20080709 G 7230 66032 BLADE CESSNA 525 525 2076601 CE WILINT FJ44 FJ441A GL IP ROTOR BLADE DEPARTED B FCPR K NONE O OTHER IN INSP/MAINT 1 NM 09 678RF 1040 5250537 2091 DURING ROUTINE INSP, FOUND DAMAGE TO THE 1ST STAGE STATOR ASSY, UPON FURTHER INSPECTION, FOUND 1 BLADE HAD FAILED AND DE PART THE LP ROTOR ASSY CAUSING DAMAGE TO THE REST OF THE ENGINE DOWN STREAM. (K) 1 L 7 2 4F 4 F RT A1WI E3GL 20080725 GL 2008 7 25 2008FA0000492 1 20080630 G 2421 FAN CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO HARTZL HCJ3Y PHCJ3YF1 GL ALTERNATOR CRACKED B O OTHER O OTHER NR NOT REPORTED 1 SW 99 PROMZ 3041 691724 FP6763 ALTERNATOR NR 2 (BELT DRIVEN ALTERNATOR) COOLING FAN DEVELOPED CRACK AT FAN BLADE RADIUS. CRACK ELONGATED UNTIL FAN SEP ARATED FROM ALTERNATOR. (K) 1 L 7 1 3O 3 O NT A00009CH E3SO 5 C P36EA 20080728 GL 2008 7 28 2008FA0000493 1 20080623 G 5397 WIRE CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO ALT AIR DOOR FATIGUED C O OTHER O OTHER NR NOT REPORTED 1 WP 05 683SR 2766 691392 WIRES THAT CONNECT TO THE ALTERNATE AIR DOOR (WHICH ARE SOLDERED TO THE SWITCH) FOR THE TORNADO ALLEY TURBO SYSTEM ARE B ECOMING FATIGUED AND SOLDER IS BREAKING AT SWITCH. IF THE ALTERNATE AIR WAS TO OPEN AND THESE WIRES WERE BROKEN, IT WOU LD NOT GIVE THE PILOT AN INDICATION THAT THE ALTERNATE AIR DOOR WAS OPEN. (K) 1 L 7 1 3O 3 O NT A00009CH E3SO 20080725 SO 2008 7 25 2008FA0000494 1 20080715 G 2170 234018623 WATER SEPARATOR GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU DAMAGED D O OTHER O OTHER NR NOT REPORTED 1 WP 21 595PE 141 1373 BOTH UNITS O/H AT MFG. WHEN CHANGING SOCK, FOUND RUST STAINS ON SOCK. REMOVED AND FOUND RETAINING CHAIN PN 834639 RUST ED. CHAIN WAS WRONG MATERIAL (METAL) AND INCORRECT LENGTH (9.5 INCHES). REPLACEMENT UNIT WAS SS WITH A TOTAL LENGTH OF (6 INCHES). ALSO ON UNIT 67-272 (1) OF (8) INTERNAL RETAINING SCREWS WAS FOUND NOT SEATED AND IN CONTACT WITH PART GAS KET. ALSO FOUND INSIDE SAME UNIT WAS A PIECE OF MASKING TAPE (2 INCHES X 6 INCHES) WITH SN OF UNIT WRITTEN WITH A RED M ARKER STILL AFFIXED TO INNER COATING OF AFT SECTION. WO NR TTT91055 (SN 49-945) DATED SEPT 28, 2006. AND CLJ14812 (SN 6 7-272) DATED SEPT 24, 2007. (K) 2 L 7 2 4F 4 F RT A12EA E25NE 20080728 EU 2008 7 28 2008FA0000495 1 20080525 G 2800 FUEL SYS RHNFLU EXT300 EA300L 70218DG EU LYC O540 AEIO540* EA MALFUNCTIONED D A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION NR NOT REPORTED 1 NE 05 22MW 131 APPROX 9 GALLONS OF FUEL IN CENTER TANK BECAME INACCESSIBLE DURING FLT, PRECAUTIONARY LANDING. AFTER DEPARTING USING CENTER TANK FUEL FOR A 120 MILE FERRY FLIGHT, SWITCHED TO THE WING TANKS FOR THE PREPONDERANCE OF THE TRIP. NEARING THE DESTINATION WITH THE WING TANKS ALMOST DRY, SELECTED THE FUSELAGE TANK FOR THE REMAINDER OF THE FLIGHT. THE FUEL FLOW METER INDICATED THAT AIR, RATHER THAN FUEL , WAS BEING DRAWN INTO THE SERVO. THE ENGINE STOPPED. RESELECTED THE WING TANKS; THE ENGINE RESTARTED. ATTEMPTED 4 MORE TIMES TO SOURCE FUEL FROM THE FUSELAGE; EACH TIME, THE ENGINE STOPPED. MA DE A PRECAUTIONARY LANDING. MECH DECOWLED ACFT AND CONFIRMED THAT FUEL COULD BE SOURCED INTO THE SERVO FROM EITHER THE W 1 M 7 1 3O 3 O NC EA67U 1E4 20080725 2008 7 25 2008FA0000496 4 20080618 G 2200 30B641 TRIM SWITCH CENTURY AMTR SUKHOI SU26MX 1152913 GL PWA PT6 PT6A21 52043 EA CONTROL COLLUMN INOPERATIVE B QPID O OTHER O OTHER NR NOT REPORTED 1 SO 19 362MC 3188E LJ760 AFTER INSTALLATION OF NEW AUTOPILOT SYSTEM, AUTOPILOT COMPUTER TRIM CIRCUITRY FAILED ON INITIAL CHECK OUT, OCT 02, 2007. COMPUTER WAS RETURNED TO MFG AND REINSTALLED AFTER REPAIR. TRIM CIRCUITRY FAILED AGAIN AND WAS RETURNED TO MFG ON JAN 18, 2008. MFG TECH SUPPORT ADVISED REPLACEMENT OF SUSPECTED BAD TRIM SWITCH ASSY AT THIS TIME AS CAUSE OF REPEATED FAI LURE. MICRO SWITCHES IN ASSY FAILED ALLOWING BOTH UP AND DOWN COMMANDS AT THE SAME TIME. TRIM SWITCH ASSY PROVIDED BY M FG WAS REPLACED AND COMPUTER REPAIRED AND REINSTALLED ON FEB 17, 2008. TRIM CIRCUITRY FAILED ON INITIAL CHECKOUT. COMP UTER WAS REMOVED FOR REPAIR AND THE TRIM SWITCH WAS CONFIRMED TO BE CAUSING THE FAILURE AGAIN. THE TRIM UP MICRO SWITCH 1 M 7 1 3R 4 T NC EXPA1M71 E4EA 20080728 NM 2008 7 28 2008FA0000497 1 20080620 G 2701 BOOT ADAMAC A500 A500 05614IQ NM CONT O550 TSIO550E 17043 SO CONTROL COLLUMN MISINSTALLED D O OTHER W INADEQUATE Q C NR NOT REPORTED 1 WP 27 896MH 0008 AT LOCATION WHERE CONTROL "STICK" PASSES THROUGH L/R SIDE ARM REST, THE BOOT SURROUNDING BASE OF STICK LIES OPEN TO CONT ROL MECHANISMS. WHERE THE STICK ENTERS THE COCKPIT, THE LEATHER BOOT THAT IS DESIGNED TO COVER THE AREA BENEATH THE STIC K, IS PARTIALLY OPEN. THIS ALLOWS FOREIGN OBJECTS, PLACED ALONG THIS AREA, TO FALL DOWN INTO WHERE CONTROLS COULD BECOM E JAMMED. THIS HAS ALREADY OCCURRED, RESULTING IN LOSS OF VERTICAL CONTROL. MFG NEEDS TO ISSUE AN IMMEDIATE AD AND ISSU E REMEDY FOR THIS SAFETY OF FLIGHT ISSUE. (K) 1 L 7 2 3O 3 O RT A00009DE E5SO 20080725 CE 2008 7 25 2008FA0000498 1 20080711 G 5510 04320049 BRACKET CESSNA 150 152 2071835 CE LYC O235 O235* 41505 EA HORIZONTAL STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 27 66970 15281696 WHILE CONDUCTING A 100 HOUR INSPECTION ON THE AIRCRAFT, COMPLYING WITH AD80-11-04 (NUTPLATE INSPECTION). UPON INSPECTIO N, IT WAS FOUND THAT NOT ONLY WAS THERE A CRACKED NUTPLATE, BUT THERE IS ALSO A (1 INCH) CRACK IN THE WELDED BRACKET- TH E PART THAT THE NUTPLATES MOUNT TO. IT CAN BE SEEN IN MFG ILLUSTRATED PARTS CATALOG, FIGURE 18, ITEM NR 10. UPON REMOV ING THE BRACKET FROM THE AIRCRAFT, ALSO DISCOVERED THAT A LARGE PORTION OF THE STEEL BRACKET HAD BEEN RUSTED; PARTICULAR LY IN THE WELDED AREAS. BECAUSE MFG NO LONGER MAKES THIS PART, ACQUIRED A SERVICEABLE PART, INSPECTED THE WELDS, TREATE D THE CORROSION, AND INSTALLED IT ON THE AIRCRAFT. (K) 1 H 7 1 3O 3 O NT 3A19 E223 20080725 CE 2008 7 25 2008FA0000499 1 20080716 G 2750 98600581 CONTROL CABLE CESSNA 210 T210L 2073449 CE CONT O520 TSIO520* 17040 SO FLAPS DEFECTIVE D O OTHER O OTHER NR NOT REPORTED 1 SW 15 2423S 21061275 ORDERED NEW MFG FLAP FOLLOW UP CABLE; TO REPLACE ORIGINAL CABLE WHICH HAD BECOME DEFECTIVE DUE TO NORMAL USAGE AND AGE. THIS CABLE IS SIMILAR TO A THROTTLE CABLE WITH AN INSIDE CABLE WHICH SLIDES IN AN OUTSIDE HOUSING. UPON INSTALLATION, O F NEW MFG FLAP FOLLOW UP CABLE, OPERATION WAS VERY ROUGH AND INTERMITTENT. SMOOTH OPERATION IS CRITICAL TO MEET MM SPE CS AND AIRCRAFTS FLIGHT MANUAL REQUIREMENTS FOR CERTAIN SPECIFIED FLIGHT CONFIGURATIONS. CONTACTED MFG SERVICE CENTER AND THEN MFG TECH SUPPORT DIRECT. MFG ASSURED, VERBALLY THE CABLE HAS BEEN MFG TO ORIGINAL SPECIFICATIONS. FROM FIRST GLANCE, CABLE IS OBVIOUSLY CONSTRUCTED IN A DIFFERENT MANNER AND OF DIFFERENT MATERIAL OF ORIGINAL PART ON THIS AND OTHE 1 H 7 1 3O 3 O 3A21 E8CE 20080725 CE 2008 7 25 2008FA0000500 1 20080713 G 7897 WIRE CESSNA 500 550 2076604 CE PWA JT15 JT15D5 52112 NE THRUST REVERSER CHAFED D A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 EA 23 67SF 6216 5500243 ON CLIMB OUT, AFTER DEPARTURE, THE LT THRUST REVERSER DEPLOY LIGHT ILLUMINATED. NO ABNORMAL FLIGHT CHARACTERISTICS WERE FELT IN THE AC. AFM PROCEDURES WERE FOLLOWED AND A SAFE LANDING BACK AT DEPARTURE AIRPORT WAS MADE. AFTER LANDING, TH E PILOT CYCLED THE LT THRUST REVERSER AND THE LIGHT EXTINGUISHED. THE TRIP WAS CANCELLED UNTIL THE AIRCRAFT COULD BE IN SPECTED. INVESTIGATION REVEALED A WIRE FOR THE DEPLOY SWITCH HAD CHAFED TO GROUND AT THE STRUCTURE OF THE LT THRUST REV ERSER OB STANG. THE DAMAGED WIRE WAS REPAIRED AND THE WIRE BUNDLE IN THAT AREA WAS REPOSITIONED TO PREVENT ANY FURTHER CHAFING. OPS CHECK OF THE THRUST REVERSER SYSTEM AFTER REPAIR WAS NORMAL. (K) 1 L 7 2 4F 4 F A22CE E25EA 20080728 CE 2008 7 28 2008FA0000501 1 20080715 G 5730 SKIN BEECH 300 300BEECH 1152930 CE WING DAMAGED B KX5R K NONE O OTHER IN INSP/MAINT 1 GL 15 613BA FL396 AIRCRAFT WAS BROUGHT IN FOR INSPECTION OF DOUBLE ROW OF RIVETS AT WING STA 209.016. RIVETS WERE FOUND SMOKING AND PAINT WAS POPPED ON THE RIVET HEADS. USED BOROSCOPE TO INSPECT RIVET BUCKTAILS. FOUND ALL OF THE RIVETS IN THE DOUBLE ROW O F THE SKIN LAP AT WS 209.016 WERE UNDER DRIVEN. THESE RIVETS WERE INSTALLED NEW AT THE FACTORY. AIRCRAFT HAS A TT OF 1 659.1. RECOMMEND INSPECTING THESE RIVET FOR POPPED PAINT AND SMOKING CONDITION AND INSTALLING NEW RIVETS IAW AC 43.13-1 B. (K) 2 L 7 2 4T A24CE 20080728 2008 7 28 2008FA0000502 4 20080718 G 2200 6222263016 AMPLIFIER ISRAEL 1124 1124A 4500103 EU GARRTT TFE731 TFE731* 01518 WP AUTOPILOT INOPERATIVE D O OTHER O OTHER NR NOT REPORTED 1 SO 19 818JH 341 AFTER (1) HOUR DISENGAGES AUTOPILOT. PRELIMINARY INSPECTION RESULTS, NO DEFECTS NOTED AFTER BENCH CHECK. (K) 2 M 7 2 4F 4 F A2SW E6WE 20080728 CE 2008 7 28 2008FA0000503 1 20080715 G 5730 SKIN BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE RT WING DAMAGED B KX5R K NONE O OTHER IN INSP/MAINT 1 GL 15 291B FL559 AIRCRAFT WAS BROUGHT IN FOR PHASE INSPECTION. DURING INSPECTION A DOUBLER ROW OF RIVETS AT WING STATION 209.016 WERE FO UND WITH PAINT POPPING OFF OF THE RIVET HEADS. USED BOROSCOPE TO INSPECT RIVET BUCKTAILS. FOUND ALL OF THE RIVETS IN T HE DOUBLE ROW OF THE SKIN LAP AT WS 209.016 WERE UNDER DRIVEN. THESE RIVETS WERE INSTALLED NEW AT THE FACTORY. AIRCRAF T HAS A TT OF 201.8. RECOMMEND INSPECTING THESE RIVETS FOR POPPED PAINT AND SMOKING CONDITION AND INSTALLING NEW RIVETS IAW AC 43.13-1B. (K) 2 L 7 2 4T 4 T A24CE E4EA 20080728 GL 2008 7 28 2008FA0000505 3 20080722 G 6197 1219310 CONNECTOR WOODWARD DIAMON DA40 DA40 2990002 GL CONT IO360 IO360* 17025 CE HARTZL HCC2Y HCC2YR1 GL PROP GOVERNOR DAMAGED B WOGR A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 GL 03 412PJ 300 00272 40495 L3186051A CH38785B ON JUNE 28TH, 2008, DURING CLIMB OUT, PASSING THROUGH 4000 FEET THE ENGINE SUDDENLY WENT INTO AN OVER SPEED CONDITION OF OVER 3100 RPM. THE AIRCRAFT REMAINED UNDER CONTROL AND WAS LANDED SAFELY AT AIRPORT AFTER AN EMERGENCY WAS DECLARED. U PON DISASSEMBLY OF THE GOVERNOR, IT WAS DISCOVERED THAT THE 1219-310 PLUG HAD BECOME DISLODGED FROM THE GOVERNOR BODY. THIS SEPARATION AND THE RESULTANT LOSS OF PROPELLER SERVO PRESSURE ALLOWED THE PROP TO RETRACT TO ITS LOW PITCH POSITION AND OVERSPEED THE ENGINE. A PROBABLE CAUSE WAS LACK OF PROPER TORQUE DURING ASSEMBLY. APPLICATION OF LOCK-TIGHT TO TH E PLUG AND INDEPENDENT SECOND PARTY VERIFICATION OF TORQUE DURING ASSEMBLY IS SUGGESTED. (K) 1 L 7 1 3O 3 O NT A47CE E1CE 5 C P920 20080728 SO 2008 7 28 2008FA0000506 1 20080702 G 7714 ACA500 TRANSMITTER GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU LT ENGINE MALFUNCTIONED G O OTHER O OTHER NR NOT REPORTED 1 SO 19 61WH 1075 TRANSMITTER CAUSED LT ENGINE TO SPOOL BACK TO IDLE, AC RETURNED TO AIRPORT AND LANDED WITH NO INCIDENT. (K) 2 L 7 2 4F 4 F RT A12EA E25NE 20080728 CE 2008 7 28 2008FA0000507 1 20080715 G 5730 SKIN BEECH 300 300BEECH 1152930 CE WING DAMAGED B KX5R O OTHER O OTHER NR NOT REPORTED 1 GL 15 613BA FL396 AIRCRAFT WAS BROUGHT IN FOR INSPECTION OF DOUBLER ROW OF RIVETS AT WING STA 209.016. RIVETS WERE FOUND SMOKING AND PAIN T WAS POPPED ON THE RIVET HEADS. USED BOROSCOPE TO INSPECT RIVET BUCKTAILS. FOUND ALL OF THE RIVETS IN THE DOUBLER ROW OF THE SKIN LAP AT WS 209.016 WERE UNDER DRIVEN. THESE RIVETS WERE INSTALLED NEW AT THE FACTORY. AC HAS A TT OF 1659. 1. RECOMMEND INSPECTING THESE RIVETS FOR POPPED PAINT AND SMOKING CONDITION AND INSTALLING NEW RIVETS IAW AC 43..13-1B. (K) 2 L 7 2 4T A24CE 20080728 CE 2008 7 28 2008FA0000508 1 20080716 G 5210 5043006221 BRACKET BEECH 200 B200 1152922 CE PAX DOOR LATCH MISINSTALLED D O OTHER W INADEQUATE Q C NR NOT REPORTED 1 EA 05 786DD 661 BB1171 BB1171 PILOT REPORTED DOOR CAME OPEN IN FLIGHT. UPON LANDING, IT WAS FOUND THE MAIN CABIN DOOR HAD DEPARTED AIRCRAFT. DOOR WA S RECOVERED. DURING INSPECTION AND DISASSEMBLY OF THE DOOR, SEVERAL ISSUES WERE FOUND. 1) UPPER FORWARD LATCH HOOK WAS FOUND WITHOUT RIGGING HOLES INSTALLED AND WAS INCORRECTLY RIGGED. 2) DOOR BELLCRANK, PN 50-430031-29 WAS FOUND BENT AN D TWISTED. 3) MAIN CABIN DOOR LATCH BRAZE ASSEMBLY WAS CATCHING ON HOOK. DID NOT ALLOW FOR A SMOOTH TRANSITION TO A L OCKED POSITION. (K) 1 L 7 2 4T A24CE 20080805 SO 2008 8 5 2008FA0000509 1 20080722 G 3250 9539500 ARM PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360* 17025 SO NLG STEERING WORN B BIER O OTHER O OTHER NR NOT REPORTED 1 EA 21 2190K 4792 347970096 NLG MOUNT ASSY ATTACHMENT POINT FOR STEERING ARM ASSY HAS EXCESSIVE WEAR AT LWR MOUNT HOLE, SRM DOES NOT SPECIFY AT FIX OR ALLOWABLE LIMIT FOR PN 95551-23. DISCREPANCY FOUND DURING INSP IAW SB 1123A & B AND ANNUAL INSPECTION IAW SRM INSPEC TION GUIDE. SB 1123B GIVES THE SERVICE LIMITS TO THE STEERING ARM CENTER PIVOT BUSHINGS AND CENTER PIVOT SLEEVE. HOWEV ER THE MORE CRITICAL COMPONENT, THE NLG MOUNT ASSY IS NOT ADDRESSED FOR THE SERVICE LIMIT OF THE STEERING ARM MOUNTING T ABS. MFG SHOULD INCORPORATE SERVICE LIMIT DATA THAT COVERS THE NLG MOUNT ASSY AND REPAIR DATA. (K) 1 L 7 2 3O 3 O A7SO E9CE 20080811 EU 2008 8 11 2008FA0000511 1 20080719 G 2435 105SG1220 STARTER GEN SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE ENGINE FAILED B HDNR O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 SW 03 350BH 2813 9345 WHILE ACFT WAS CIRCLING AT A SCENE CALL, THE CREW WAS STARTING TO DETECT WHAT SEEMED TO BE BURNING PLASTIC FOLLOWED BY A GENERATOR CAUTION LIGHT. AC LANDED BACK AT HOSPITAL PAD WITHOUT INCIDENT. MAINT WAS DISPATCHED. IT WAS FOUND THAT THE STARTER GENERATOR HAD FAILED AND THE PLASTIC FAN BLADES WERE DEFORMED RESULTING IN THE PLASTIC BURNING ODOR. THE STARTE R GENERATOR WAS REPLACED AND AN OPERATIONAL CHECK OF THE SYSTEM WAS SATISFACTORY. (K) 1 G 7 1 3U 3 U H9EU E19EU 20080811 CE 2008 8 11 2008FA0000512 1 20080702 G 2760 12SX1T SWITCH RAYTHN 390 390 7150030 CE SPOILERS FAILED B E81R O OTHER J WARNING INDICATION CR CRUISE 1 GL 03 972PF 1146 RB38 PILOT REPORTED SPOILER FAIL INDICATION IN CRUISE FLIGHT. ALL SPOILER PANELS DEPLOYED UPON LANDING. SCU FAULT CODE 44R4 RV3V INDICATED. ADJUSTED LT & RT SPOILER FINAL POSITION LVDT`S AS REQUIRED IAW MM 27-60-00-501. REPLACED LT THROTTLE S WITCH S1, SPOILER SYS FUNCTIONAL CHECKS NORMAL, NO FAULTS INDICATED SUSPECT LT THROTTLE S1 SWITCH TO HAVE PREMATURE INTE RNAL FAULT. RECOMMEND MFG INVESTIGATE IF FLEET IS EXPERIENCING PREMATURE FAILURES OF THROTTLE SWITCHES AND REDESIGN SWI TCH IF REQUIRED. (K) 1 L 7 2 3F RT A00010WI 20080811 NM 2008 8 11 2008FA0000513 1 20080730 G 5753 SPAR BOEING 737 737448 13844BU NM CFMINT CFM56 CFM563C 13802 EU LT TE FLAP CORRODED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 742VA 24773 DURING SCHEDULED INSPECTION, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD. (K) 2 L 7 2 4F 4 F RT A16WE E21EU 20080811 NM 2008 8 11 2008FA0000514 1 20080730 G 5753 SPAR BOEING 737 737448 13844BU NM CFMINT CFM56 CFM563C 13802 EU LT WING TE FLAP CORRODED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 742VA 24773 DURING SCHEDULED INSP, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD. (K) 2 L 7 2 4F 4 F RT A16WE E21EU 20080811 WP 2008 8 11 2008FA0000515 1 20080729 G 5530 INLET DOUG DC9 DC982 3022082 WP PWA JT8 JT8D* NE HEAT EXCHANGER CRACKED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 886GA 49931 DURING SCHEDULED INSP, FOUND VERTICAL STABILIZER L/E AT HEAT EXCHANGER INLET IS CRACKED APPROX 6.5 INCHES LONG ON LT SID E. FOUND TO BE OUT OF LIMITS IAW SRM 55-05 FIG 3. (K) 2 L 7 2 4F 4 F A6WE E2EA 20080811 EA 2008 8 11 2008FA0000516 2 20080721 G 8550 CH481101 OIL FILTER CESSNA 150 152 2071835 CE LYC O235 O235* 41505 EA ENGINE CONTAMINATED D K NONE O OTHER IN INSP/MAINT 1 NE 01 4900H 1 15284009 FILTER INSTALLED AND OIL CHANGE RUN-UP NORMAL. FIRST FLIGHT AFTER OIL CHANGE, PILOT NOTICED OIL PRESSURE DROPPING AND H IGH OIL TEMP, UNABLE TO CORRECT, PILOT RETURNED TO ORIGIN AND REPORTED FINDINGS. INVESTIGATION FOUND FILTER ELEMENT DEB RIS UNDER PRESSURE RELIEF VALVE CAUSING LOW OIL PRESSURE, UPON FURTHER INVESTIGATION A SECOND FILTER OF SAME DATE CODE W AS FOUND TO HAVE LOOSE DEBRIS IN THE FILTERED SIDE OF THE FILTER ELEMENT AND THE ELEMENT WAS BONDED ON ONE END ONLY. TH E ENGINE GULLIES WERE FLUSHED WITH AIR AND SEVERAL PIECES OF DEBRIS WERE FOUND, A NOW FILTER OF DIFFERENT DATE CODE WAS INSTALLED, SEVERAL GROUND RUNS WERE MADE, NO SIGNIFICANT DEBRIS WAS FOUND. A NEW FILTER OF A DIFFERENT MFG WAS INSTALLE 1 H 7 1 3O 3 O NT 3A19 E223 20080811 EU 2008 8 11 2008FA0000517 1 20080801 G 3210 DIN4718ZP FITTING DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE12501 59300 EU MLG LOOSE D O OTHER O OTHER NR NOT REPORTED 1 EA 17 119BJ 42AC045 CIRCLIP THAT SECURES DOWNLOCK PIN IN MLG LEGS HAS BEEN TWISTING OFF RENDERING THIS DOWNLOCK PIN LOOSE ENOUGH TO FALL OUT WHEN GEAR IS RETRACTED, THIS PARTICULAR AC HAD THE AFT SECTION OF THE WHEELWELL DAMAGED DUE TO THE PIN HANGING HALF WAY OUT AND CONTACT THROUGH THE LAMINATE. THIS PIN SHOULD BE SECURED WITH SOMETHING THAT IS PERMANENT LIKE A COTTER PIN OR SAFETY WIRE. THIS PROBLEM WAS DISCOVERED ON A PILOTS PRE-FLIGHT. (K) 1 L 7 2 3I 3 B RT A57CE E00069EN 20080811 SO 2008 8 11 2008FA0000518 2 20080717 G 8520 654837 CAMSHAFT CONT O550 IO550B SO ENGINE WORN B Y2GR O OTHER O OTHER NR NOT REPORTED 1 EA 23 2079 296655 CAMSHAFT LOBES WORN EXCESSIVELY FORM CORROSION PITS. (K) 3 O E3SO 20080811 EA 2008 8 11 2008FA0000519 2 20080717 G 8520 LW19173 CAMSHAFT LYC O540 IO540* 41532 EA ENGINE WORN B Y2GR O OTHER O OTHER NR NOT REPORTED 1 EA 23 1329 L100268A CAMSHAFT LOBES WORN FROM CORROSION PITS. (K) 3 O 1E4 20080811 EA 2008 8 11 2008FA0000520 1 20080624 G 2730 C6CTM102827 JACKSCREW DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6* 52043 EA LT ELEVATOR DAMAGED D O OTHER O OTHER NR NOT REPORTED 1 WP 09 300DZ 644 FOUND SCREW-DRIVE INTERNAL THREADS STRIPPED AND SAFETY SPLIT, PIN MISSING. PILOT HAD DIFFICULTY CONTROLLING ELEVATOR. PART HAD 196.2 IN SERVICE, SINCE REPAIR. RECOMMENDED TO INSPECT LT ELEVATOR TRIM TAB FOR EXCESSIVE PLAY IAW MM AS PART OF PREFLIGHT AND EVERY SCHEDULED INSP. (K) 1 H 7 2 3T 3 T RT A9EA E2NE 20080811 CE 2008 8 11 2008FA0000521 1 20080723 G 7120 10191012253 MOUNT BEECH 300 300BEECH 1152930 CE PWA PT6 PT6* 52043 EA LT ENGINE CRACKED B GSPR K NONE O OTHER IN INSP/MAINT 1 WP 05 73WC 6814 FL135 DURING A PHASE 2, 200 HR INSP, A CRACK WAS FOUND ON THE LT ENGINE MOUNT UPPER IB COWLING BRACKET. THE CRACK EXTENDED FR OM THE TOP OF THE WELD AND WAS APPROXIMATELY 1 INCH IN LENGTH. THE ADJACENT AREAS DID NOT APPEAR DAMAGED.. TECH SUPPOR T WAS CONTACTED AND THE MOUNT SENT TO A QUALIFIED WELDER FOR REPAIR. CAUSE OF CRACK IS UNKNOWN. (K) 2 L 7 2 4T 3 T A24CE E2NE 20080811 SO 2008 8 11 2008FA0000522 1 20080731 G 2530 50231L0V5280 PAN GULSTM G1159 GIV 3980115 SO PWC PW615 PW615FA 52282 NE OVEN MISINSTALLED D O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SO 13 416QS 1316 CABIN SMOKE DUE TO DRIP PAN IN OVEN BEING IMPROPERLY INSTALLED CAUSING DRIPPINGS FROM FOOD TO CONTACT OVEN LOWER BURNER ELEMENTS. (K) 2 L 7 2 4F 4 F RT A12EA E00073EN 20080811 SO 2008 8 11 2008FA0000523 1 20080707 G 8120 LW18302 MOUNT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA TURBOCHARGER BROKEN D O OTHER O OTHER NR NOT REPORTED 1 EA 23 3580X 318052085 L628661A FOUND MOUNT FOR TURBOCHARGER TO BE BROKEN COMPLETELY THROUGH ON IB LOWER TUBE ON RT ENGINE. CRACK WAS APPROXIMATELY 4 T O 5 INCHES FROM FWD LOWER ATTACH POINT. NO REPORTED VIBRATION ISSUES OF OPERATIONAL ISSUES. (K) 1 L 7 2 3O 3 O A20SO E14EA 20080811 2008 8 11 2008FA0000524 4 20080802 G 2300 G888012 CONTROL HEAD AMD FALC50 FALCON50MYST 2730106 EU GARRTT TPE331 TPE3313 01514 WP NR 1 NAV/COMM FAILED D O OTHER B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION DE DESCENT 1 SO 14 980S 249 P75665 AS CREW REPORTED DURING DESCENT THREW 16000 FT 1.40 HR INTO FLIGHT EXPERIENCED A SUDDEN ELECTRICAL BURNING ODOR THAT WAS ACCOMPANIED BY SMALL PLUME OF SMOKE. COMPLETED ALL MEMORY ITEMS ON THE CHECKLIST AND DECLARED EMERGENCY FOR PRIORITY L ANDING. SHORTLY THEREAFTER WHILE DESCENDING TO 6000 FT THE SMOKE AND ELECTRICAL ODOR CLEARED AND NOTED NR 1 NAV/COM CON TROL NO LONGER WORKING AND PULLED CIRCUIT BREAKER. AT THAT TIME EMERGENCY WAS OVER AND REQUESTED NORMAL HANDLING TO THE AIRPORT. UPON FURTHER INSPECTION BY TECH, THE NR 1 NAV/COM CONTROL HEAD HAD FAILED CAUSING THE PROBLEM. REPLACEMENT P ART INSTALLED. REMOVED UNIT PN G8060-12, SN 273 SENT FOR EVALUATION AND REPAIR. (K) 2 L 7 3 4F 4 T A46EU E4WE 20080811 EA 2008 8 11 2008FA0000525 2 20080722 G 7414 AB382584 CONTACTOR BENDIX BLANCA 17 1731ATC 1220437 GL LYC O540 TIO540* 41532 EA MAGNETO BROKEN G K NONE O OTHER IN INSP/MAINT 1 SW 13 222SN 31004 A BROKEN CONTACT BREAKER WAS FOUND DURING TROUBLESHOOTING AN IGNITION PROBLEM. THE CONTACTOR RIVET WAS BROKEN ON THE MA GNETO. THE CONTACTOR RIVET MAY BE INSUFFICIENT TO PROPERLY HOLD THE CONTACTOR IN PLACE. (K) 1 L 7 1 3O 3 O A18CE E14EA 20080811 SO 2008 8 11 2008FA0000526 2 20080619 G 7414 K3823 DISTRIBUTOR CESSNA 182 182Q 2072732 CE CONT O470 O470* 17026 SO MAGNETO WORN B AKGR O OTHER O OTHER NR NOT REPORTED 1 CE 05 16MS 182 18267267 REMOVED NEW MAGNETOS PN 6310, SN 07061208 & 07061310.. ACCOMPLISHED SB 3-08 PREMATURE CARBON BRUSH WEAR. BOTH CARBON B RUSHES HAD PREMATURE WEAR AS DEPICTED IN THE CENTER ILLUSTRATION FIG 1, PAGE 3 OF 5. (K) 1 H 7 1 3O 3 O NT 3A13 E273 20080811 SO 2008 8 11 2008FA0000527 2 20080619 G 7414 M1827 CAM CESSNA 182 182Q 2072732 CE CONT O470 O470* 17026 SO MAGNETO WORN B AKGR O OTHER O OTHER NR NOT REPORTED 1 CE 05 16MS 182 07061208 18267267 REMOVED NEW MAGNETOS PN 6310, SN 07061308 & 07061310. ACCOMPLISHED SB 2-08, MAGNETO CONTACT POINT CAMP PREMATURE WEAR. INSTALLED 2 NEW CONTACT POINT ASSEMBLIES PN M3081; SET "E" GAP AND TIMED TO THE ENGINE. (K) 1 H 7 1 3O 3 O NT 3A13 E273 20080811 CE 2008 8 11 2008FA0000528 1 20080729 G 3222 STRUT CESSNA 172 172RG 2072438 CE LYC O360 O360* 41514 EA NLG DAMAGED B QFBR O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 NM 01 6448V 172RG0709 PILOT REPORTED A CLUNKING NOISE COMING FROM THE NLG. UPON INSPECTION, IT WAS NOTED THAT .2500 INCH UP AND DOWN PLAY AT THE LOWER TRUNNION ASSY. THE AC`S NLG ASSY WAS REMOVED AND DURING FATHER INSPECTION THE BARREL WAS FOUND TO BE THE CULP RIT. THE BOLT THAT HOLDS THE HEAD AND TUBE ASSY SHOCK STRUT PN 2443005-1 AND COLLAR ASSY TO THE BARREL HAD SHIFTED AT . 2500 INCH TO THE BARREL BOLT HOLE ELONGATED AND DISPLACING METAL ABOVE THE BOLT HOLE. THE AC IS USED FOR FLIGHT TRAININ G, WAS IS SUSPECT PLAYS SOME ROLE BUT BELIEVE THE PROBLEMS HAD BEEN DETECTED BEFORE AND ONLY THE BOLT WAS REPLACED. (K) 1 H 7 1 3O 3 O 3A17 E286 20080811 EA 2008 8 11 2008FA0000529 2 20080730 G 8530 74230 GUIDE CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA CYLINDER HEAD SEIZED D A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 WP 07 543ER 889 172S10522 L3342451E DURING FLIGHT, THE ENGINE STARTED RUNNING ROUGH AND LOST POWER. EMERGENCY LANDING COMPLETED WITHOUT DAMAGE OR INJURY. MAINT FOUND THE NR 3 EXHAUST VALVE SEIZED IN THE VALVE GUIDE. FURTHER INVESTIGATION FOUND THE GUIDE BROKEN IN THE CYLIN DER HEAD. OPERATOR HAS AIRCRAFT WITH THE NEW ROLLER TAPPET ENGINES. HAVE BEEN PERFORMING A SB388C INSPECTION ON THE RE ST OF THE FLEET AND HAVE FOUND THE MAJORITY OF THE EXHAUST VALVES FOR ALL CYLINDERS TO BE TIGHT IN THE GUIDES. MFG RECO MMENDS A 1000 HOUR INTERVAL FOR THESE ENGINES FOR SB388C INSPECTION. WILL BE INITIATING A 600 HOUR INTERVAL FOR THE SB3 88C FOR OUR FLEET. HAVE REVISED LEANING PROCEDURES. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 20080811 SO 2008 8 11 2008FA0000530 1 20080714 G 2420 365662R STATOR PIPER PA32 PA32R300 7103213 SO LYC 0540 IO540K1G5D 41532 SO HARTZL HCC3Y HCC3YR GL ALTERNATOR SHORTED C A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION NR NOT REPORTED 1 SW 11 2125V 32R7780431 L1664445A DY4143A THE AC SUFFERED LOSS OF ELECTRICAL POWER WHILE IN CONTACT WITH ATC WHEN LOST RADIO CONTACT. CONTACTED BKP VIA CELL PHO NE AND STATED HIS PROBLEM AND REQUESTED RUNWAY LIGHT AND WHEN THEY WERE TURNED ON HE WAS WITHIN SIGHT OF THE RUNWAY AND USED EMERGENCY RELEASE OF THE LANDING GEAR AT 120 KNOTS. AS AC TOUCHED DOWN THE NOSE GEAR COLLAPSED CAUSING THE AC TO S KID OFF RUNWAY. DAMAGE WAS CONFINED TO THE PROP, MLG DOORS AND RT WING L/E, WING TIP. NO FLIGHT PLAN HAD BEEN FILED AN D VFR CONDITIONS PREVAILED. NO INJURIES. TESTED ALTERNATOR FOUND STATOR HAD SHORTED OUT, IN TURN HAD SHORTED OUT RECTI FIER. (K) 1 L 7 1 3O 3 O A3SO 1E4 5 C P25EA 20080811 EA 2008 8 11 2008FA0000531 2 20080728 G 7314 SEAL PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2B 41979 EA NR 2 ENG LEAKING D O OTHER K FLUID LOSS NR NOT REPORTED 1 SO 05 3589X E2048 318052138 L244768A FUEL PUMP DRIVE SHAFT SEAL FAILED RESULTING IN LARGE FUEL LEAK AT DRAIN. (K) 1 L 7 2 3O 3 O A20SO E14EA 20080811 GL 2008 8 11 2008FA0000532 1 20080801 G 2450 BUSS BAR CIRRUS SR SR22 2130001 GL CONT O550 IO550N 17042 SO CB PANEL LOOSE B YEBR K NONE O OTHER IN INSP/MAINT 1 CE 05 839CT 2938 PILOT REPORTED THE NR 2 ALTERNATOR WAS INTERMITTENT. WHILE TROUBLESHOOTING THE NR 2 ALTERNATOR, FOUND 13 SCREWS LOOSE A ND 1 SCREW MISSING ON THE COPPER CIRCUIT BREAKER BUSS BAR. THE 1 SCREW MISSING WAS ON THE NR 2 ALTERNATOR CIRCUIT BREAK ER BUSS FEED. PROBABLE CAUSE FOR THIS WOULD BE THAT THEY WERE NOT TIGHT FROM FACTORY. RECOMMEND CHECKING TORQUE OF ALL CIRCUIT BREAKER SCREWS AT NEXT MAINTENANCE ACTION. (K) 1 L 7 1 3O 3 O NT A00009CH E3SO 20080811 CE 2008 8 11 2008FA0000533 1 20080714 G 7160 45A35042003 SKIN BEECH MU300 400A 1155402 CE RT ENGINE INLET CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SO 19 470LX 1491 RK478 REPORTED RT ENG INLET CRACKED AT 9:00 POSITION. THE INLET WAS REMOVED AND REPAIRED AND REINSTALLED ON THE AC. (K) 2 H 7 2 4F RT A16SW 20080808 SO 2008 8 8 2008FA0000534 1 20080712 G 2820 1500106151 LINE PIPER PA46 PA46500TP 7104622 SO PWA PT6 PT6* 52043 EA FUEL SYSTEM CHAFED D O OTHER K FLUID LOSS NR NOT REPORTED 1 SO 07 5339G 4697095 FOUND FUEL LINE, PN 1500106-151, CHAFED AGAINST THROTTLE CABLES , PROP CONTROL CABLES BELOW THROTTLE. THIS LINE PROVIDE S FUEL PRESSURE TO THE 2 MANUAL ENGINE PRIMER PUMPS AT THE BASE OF THE QUADRANT. HAD THIS LINE CHAFED THROUGH, FUEL UND ER PRESSURE WOULD HAVE FLOWED INTO THE AIRPLANE CABIN. THE ONLY WAY TO SHUT OFF FUEL FLOW TO THIS LINE WOULD BE TO CLOS E THE FRONT ENGINE FUEL SELECTOR VALVE, AND SHUT DOWN THE FRONT ENGINE. THIS IS A POTENTIAL HAZARDOUS CONDITION AND COU LD CAUSE AN INFLIGHT CABIN FIRE WITH RESULTANT LOSS OF LIFE AND AIRCRAFT IF NOT FOUND AND CORRECTED. (K) 1 L 7 1 3O 3 T RT A25SO E2NE 20080811 SW 2008 8 11 2008FA0000535 1 20080730 G 3234 5040560006 DOWNLOCK MOONEY M20 M20B 5870206 SW LYC O360 O360A1A 41514 EA MCAULY 2A36C D2A36C* GL CONTROL LEVER WORN C O OTHER O OTHER NR NOT REPORTED 1 SW 19 74542 3371 1853 L402336 58618 LANDING GEAR LEVER BECAME DISENGAGED FROM THE DOWN LOCK LATCHING ASSY ON THE PILOT`S LOWER CENTER INSTRUMENT PANEL. AC W AS ON THE GROUND DURING LANDING ROLLOUT. THIS ALLOWED GEAR TO COLLAPSE. SB M20-88B, 5/10/94. (K) 1 L 7 1 3O 3 O 2A3 E286 5 C P880 20080811 EA 2008 8 11 2008FA0000537 1 20080724 G 5730 SKIN CNDAIR CL600 CL6001A11 1900308 EA WING CORRODED B ZLJR O OTHER O OTHER NR NOT REPORTED 1 EA 17 100QR 1043 SURFACE CORROSION (PITTING) DISCOVERED ON BOTH WINGS LOWER SURFACES ADJACENT TO AND OB OF WHEEL WELLS, CORROSION DEEMED UNUSUALLY SEVERE. (K) 2 L 7 2 4F RT A21EA 20080811 NM 2008 8 11 2008FA0000538 1 20080730 G 5753 SPAR BOEING 737 737448 13844BU NM CFMINT CFM56 CFM563C 13802 EU LT WING TE FLAP CORRODED B DU4R K NONE O OTHER IN INSP/MAINT 1 EA 39 742VA 24773 DURING SCHEDULED INSP, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD. (K) 2 L 7 2 4F 4 F RT A16WE E21EU 20080811 CE 2008 8 11 2008FA0000539 1 20080502 G 3244 15117300 WHEEL BEECH 200 B200 1152922 CE MLG CRACKED B E5WR K NONE O OTHER IN INSP/MAINT 1 GL 21 200ND 2738 BB1612 CRACK INDICATIONS LOCATED IN BEED AREA OF WHEELS REAVEALED BY FLUORESCENT PENETRANT. (K) 1 L 7 2 4T A24CE 20080903 CE 2008 9 3 2008FA0000540 1 20080502 G 3246 4088 WHEEL BEECH 200 B200 1152922 CE PWA PT6 PT6* 52043 EA MLG CRACKED B HJ2R K NONE O OTHER IN INSP/MAINT 1 GL 21 200ND BB1612 CRACK INDICATIONS LOCATED IN BEAD AREA OF WHEELS, REVEALED BY FLUORESCENT PENETRANT. (K) 1 L 7 2 4T 3 T A24CE E2NE 20080903 WP 2008 9 3 2008FA0000541 2 20080801 G 7250 30753507 MODULE RAYTHN DH125 HAWKER800XP 7150012 CE GARRTT TFE731 TFE7315BR WP LPT FAILED B O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 GL 03 225PB 3495 258558 107662 AIRCRAFT EXPERIENCED A VIBRATION IN FLIGHT. CREW SHUTDOWN NR 1 ENGINE AND LANDED. MAINT CREWS DETERMINED THE THIRD STA GE LOW PRESSURE TURBINE (LPT) MODULE HAD EXPERIENCED A BLADE FAILURE. ONE BLADE WAS MISSING A PIECE ABOUT ONE INCH LONG. MAINT ALSO DISCOVERED A CRACK IN THE THIRD STAGE STATOR WHICH EXTENDED BETWEEN ONE THIRD TO ONE HALF THE CIRCUMFERENCE OF THE HOUSING. NO OTHER ANOMALIES WERE NOTED DURING THE DISASSEMBLY OF THE ENGINE. PARTS WERE SENT TO MFG FOR INVESTIGA TION AND REPAIR. (K) 2 L 7 2 4F 4 F RT A3EU E6WE 20080903 SW 2008 9 3 2008FA0000542 1 20080728 G 6220 471201281 BEAM BELL 47 47G 1181002 SW MAIN ROTOR CRACKED B E5WR K NONE O OTHER IN INSP/MAINT 1 GL 21 BEAM CRACK INDICATION AT EAR END (FPT). HUB - CRACK INDICATIONS AT RADIUS ON STUB ENDS (FMT). (K) 1 G 7 1 3O H1 20080903 SW 2008 9 3 2008FA0000543 1 20080728 G 6220 471201171 HUB BELL 47 47G 1181002 SW MAIN ROTOR CRACKED B E5WR O OTHER O OTHER NR NOT REPORTED 1 GL 21 BEAM - CRACK INDICATION AT EAR END (FPT). HUB - CRACK INDICATIONS AT RADIUS ON STUB ENDS. (K) 1 G 7 1 3O H1 20080903 EU 2008 9 3 2008FA0000544 1 20080730 G 2421 ALU8521 ALTERNATOR SOCATA TB9 TB9 8680694 EU LYC O320 O320D2A 41508 EA ENGINE FAILED B NI1R O OTHER O OTHER NR NOT REPORTED 1 CE 03 1 ALTERNATOR WILL FAIL ABOVE 2500 RPM, LOW VOLTAGE LIGHT COMES ON AND THE VOLTMETER INDICATES BATTERY VOLTAGE. OPS CHECK D URING GROUND RUNS ARE NORMAL MAX RPM DURING GROUND RUN 2400 RPM. ALTERNATOR APPEARS TO BE RPM SENSITIVE. POSSIBLE CAUSE : BRUSHES NOT RIDING TRUE ON SLIP RING. OVERHAUL PROCESS MAY CONTRIBUTE TO PROBLEM. AN ADDITIONAN (2) ALU8521 ALTERNATOR S FROM INVENTORY PRODUCE THE SAME SYMPTOMS, SN E113128 AND F043304. BOTH ALTERNATORS FAILED WITHIN 2 HOURS OF OPERATION. BOTH WERE O/H UNITS. (K) 1 L 7 1 3O 3 O NT AS1EU E274 20080903 CE 2008 9 3 2008FA0000545 1 20080712 G 3610 65550384 BELLOWS CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE RUPTURED B QFYR K NONE O OTHER IN INSP/MAINT 1 EA 63 17PL 5600412 PCEJC0312 THE BELLOWS INSIDE THE BRADED CONNECTION CRACKED OUT LEAVING A HOLE ABOUT .75 IN IN DIA AT THE UP STREAM SIDE OF THE FLE XIBLE CONNECTOR. THE PROBLEM WAS DISCOVERED ON A MAINT RUN UP AT WHICH TIME THE FIRE DETECTION SYS WAS ACTIVATED FROM A N OVERHEAT SITUATION. RECOMMEND REMOVING THE ELBOWS AND CHECKING THE BELLOWS FOR CRACKS WITH A BORESCOPE. (K) 2 L 7 2 4F 4 F RT A22CE E25EA 20080903 CE 2008 9 3 2008FA0000546 1 20080717 G 2750 98600581 CONTROL CABLE CESSNA 210 T210L 2073449 CE CONT O520 TSIO520* 17040 SO TE FLAPS DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 SW 15 2423S 21061275 ORDERED NEW FLAP FOLLOW UP CABLE; TO REPLACED ORIGINAL CABLE WHICH HAD BECOME DEFECTIVE DUE TO NORMAL USAGE AND AGE. 1 H 7 1 3O 3 O 3A21 E8CE 20080903 SW 2008 9 3 2008FA0000547 1 20080628 G 3260 560006 DOWNLOCK MOONEY M20 M20B 5870206 SW LYC O360 O360A1A 41514 EA MLG WORN C O OTHER O OTHER TX TAXI/GRND HDL 1 SW 19 74542 3371 1853 L402336 LANDING GEAR LEVER BECAME DISENGAGED FROM THE DOWNLOCK LATCHING ASSY ON THE PILOT`S LOWER CENTER INSTRUMENT PANEL. AC WA S ON THE GROUND DURING LANDING ROLLOUT. THIS ALLOWED GEAR TO COLLAPSE, SB M20-88B, 5-10-94. (K) 1 L 7 1 3O 3 O 2A3 E286 20080903 SO 2008 9 3 2008FA0000548 1 20080804 G 5330 69904000 SKIN PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540* 41532 EA FUSELAGE CRACKED B L6QR K NONE O OTHER IN INSP/MAINT 1 EA 05 121TF 1520 3257351 UPPER COMM/NAV ANTENNA DOUBLER AND SKIN CRACKED FROM FWD SEAM ALONG BOTH ANTENNA MOUNT NUTPLATE LINES. CRACKS ARE APPROX 6 INCHES LONG WITH ADDITIONAL CRACKING RADIATING OUT FROM FWD NUTPLATES TO FWD DOUBLER MOUNTING RIVETS. ANTENNA DOUBLER IS CRACKED COMPLETELY THROUGH ON LT SIDE AND 90 PERCENT THROUGH ON RT SIDE. DAMAGE PICTURE AVAILABLE UPON REQUEST. DAM AGE APPEARS TO HAVE BEEN CAUSED BY PROLONGED OIL CANNING OF THE UPPER SKIN PANEL FROM AERODYNAMIC LOADS AGAINST THE ANTE NNA DURING FLIGHT. TO PREVENT REOCCURRENCE REPAIR WITH FLUSH PATCH IAW 43.13-1B, SEC 4, HOWEVER BEND .5 INCH LIP ON LT, RT AND AFT EDGES OF BACKING PATCH TO INCREASE STIFFNESS AND REDUCE OIL CANNING EFFECT. JOG FRONT EDGE OF BACKING PATCH 1 L 7 1 3O 3 O A3SO E14EA 20080903 SO 2008 9 3 2008FA0000549 1 20080804 G 5330 99813004 DOUBLER PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540* 41532 EA FUSELAGE CRACKED B L6QR K NONE O OTHER IN INSP/MAINT 1 EA 05 121TF 1520 3257351 UPPER COMM/NAV ANTENNA DOUBLER AND SKIN CRACKED FROM FWD SEAM ALONG BOTH ANTENNA MOUNT NUTPLATE LINES. CRACKS ARE APPROX 6 INCHES LONG WITH ADDITIONAL CRACKING RADIATING OUT FROM FWD NUTPLATES TO FWD DOUBLER MOUNTING RIVETS. ANTENNA DOUBLER IS CRACKED COMPLETELY THROUGH ON LT SIDE AND 90 PERCENT THROUGH ON RT SIDE. DAMAGE PICTURE AVAILABLE UPON REQUEST. DAM AGE APPEARS TO HAVE BEEN CAUSED BY PROLONGED OIL CANNING OF THE UPPER SKIN PANEL FROM AERODYNAMIC LOADS AGAINST THE ANTE NNA DURING FLIGHT. TO PREVENT REOCCURRENCE REPAIR WITH FLUSH PATCH IAW 43.13-1B, SEC 4, HOWEVER BEND .5 INCH LIP ON LT, RT AND AFT EDGES OF BACKING PATCH TO INCREASE STIFFNESS AND REDUCE OIL CANNING EFFECT. JOG FRONT EDGE OF BACKING PATCH 1 L 7 1 3O 3 O A3SO E14EA 20080903 EA 2008 9 3 2008FA0000550 1 20080729 G 6300 269D53085 DRIVE SHAFT SCWZER 269 269D 8059501 EA ALLSN 250C 250C20 03013 GL MAIN ROTOR UNSERVICEABLE D K NONE O OTHER IN INSP/MAINT 1 SW 17 277DT 674 0028 CAE845057 DURING PREFLIGHT, THE M/R DROOP STOP NUT WAS FOUND TO BE LOOSE. UPON FURTHER INSP IT WAS DETERMINED THAT M/R HUB SHOULD BE REMOVED TO LOOK FOR SIGNS OF WEAR. ONCE HUB WAS REMOVED AND INSPECTED, MODERATE WEAR (FRETTING) WAS FOUND ON DROOP ST OP RETAINER PLATE (PN 269A1320), DROOP STOP RETAINER RING (PN 269D1329), DROOP STOP RETAINER (PN 269A1332) AND UPPER SCI SSORS SUPPORT (PN 269A1328-901) TO THRUST BEARING TUBE SPACER ASSY (PN 269A13183). ONCE THESE PARTS WERE REMOVED, THE DR IVE SHAFT WAS REMOVED FOR INSP. ONCE DRIVE SHAFT WAS REMOVED THE DRIVE SHAFT THRUST BRG WAS REMOVED FOR INSP AND CORROSI ON WAS FOUND ON DRIVE SHAFT THRUST BRG JOURNAL. CORROSION WAS REMOVED AND FURTHER VISUAL EXAMINATION REVEALED A POSSIBLE 1 G 7 1 3U 3 U 0 4H12 E4CE 20080903 2008 9 3 2008FA0000551 2 20080806 G 7261 BEARING DOUG MD90 MD9030 3023690 NM OIL PUMP SEIZED B HZ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 PUMP SEIZED, OIL PUMP BEARING BRACKET SHOWED SIGNS OF RUBBING WITH THE OIL PUMP GEAR. PENDING ENGINEERING EVALUATION. (K) 2 L 7 2 4F RT A6WE 20080903 CE 2008 9 3 2008FA0000552 1 20080521 G 2910 SA7670024001 LINE RAYTHN DH125 HAWKER800XP 7150012 CE HYD SYSTEM RUPTURED D A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 GL 23 484JC 258644 HYDR FLEXABLE LINE TO RT MLG DOOR ACTUATOR RUPTURED DURING FLIGHT. LOSS OF FLUID CAVITATED RT AND LT ENGINE DRIVE HYDR PUMPS. LINE RUPTURED IN SIDEWALL NEAR SWAGED END FITTING FOR CONNECTOR. PRESSURE IS 3000 PSI CONSTANT. NO LANDING GEA R ACTUATION WAS IN PROCESS. SUSPECT MFG DEFECT. AC MFG NOTIFIED. THIS IS FIRST INSTANCE OF THIS FOR THS AC. LT MLG DOO R HYDR LINE RUPTURED 2 MONTHS BEFORE IN THE SAME EXACT WAY AND CAUSED THE SAME DAMAGE. MFG NOTIFIED AGAIN. 2 L 7 2 4F RT A3EU 20080903 CE 2008 9 3 2008FA0000553 1 20080808 G 2910 SA7670024001 LINE RAYTHN DH125 HAWKER800XP 7150012 CE HYD SYSTEM RUPTURED D A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 GL 23 484JC 2369 258644 HYDR FLEXIBLE LINE TO THE LT LANDING GEAR DOOR ACTUATOR RUPTURED DURING FLIGHT. LOSS OF FLUID CAVITATED LT AND RT ENG D RIVEN HYDR PUMPS. LINE RUPTURED IN SIDEWALL NEAR SWAGED END FITTING FOR CONNECTOR. PRESSURE IS 3000 PSI CONSTANT. NO LANDING GEAR ACTUATION WAS IN PROCESS. SUSPECT MFG DEFECT. AC MFG NOTIFIED. THIS IS SECOND OCCURRANCE FOR THIS AC. S AME LINE RUPTURED 2 MONTH PREVIOUSLY ON RT SIDE ACTURATOR CAUSING SAME DAMAGE. MFG AGAIN NOTIFIED. (K) 2 L 7 2 4F RT A3EU 20080902 CE 2008 9 2 2008FA0000554 1 20080813 G 7160 125083029 INTAKE DUCT CESSNA 206 TU206G 2073357 CE INDUCTION BOX CRACKED C K NONE O OTHER IN INSP/MAINT 1 SW 17 602MB 10 U20604052 MANUFACTURER SUPPLIED ENG INTAKE DUCT BEFORE THE AIR FILTER IS SUBJECT TO CRACKING IN MULTIPLE LOCATIONS. THIS PARTICUL AR ACFT AND ANOTHER IDENTICAL MODEL ACFT THIS FACILITY MAINTAINS HAVE BEEN CONVERTED TO AN IO-550-F ENG. AFTER THE STC CONVERSION, THE CRACKING PROBLEM HAS INCREASED SIGNIFICANTLY. CONTACTED THE STC HOLDER AND HAVE RESPONDED WITH A SCHEME TO REINFORCE THIS DUCT. THIS REPAIR STATION IS LOOKING INTO THIS ALTERATION TO THIS DUCT WHICH MAY REQUIRE PER SUPPORT . AT PRESENT, THE DUCTS ARE REQUIRING REPAIRS OR REPLACEMENT EVERY 50 HOURS. A PMA REPLACEMENT DUCT MADE FROM COMPOSIT E MATERIAL IS NO LONGER AVAILABLE. (S) 1 H 7 1 3O A4CE 20080825 EA 2008 8 25 2008FA0000555 1 20080804 G 3260 INDICATION SYS CNDAIR CL600 CL6002B16 1900305 EA MLG MALFUNCTIONED C O OTHER P NO WARNING INDICATION LD LANDING 1 SW 99 190MP 5161 ON APPROACH TO KSSI, WHEN LANDING GEAR DEPLOYED, ONLY RECEIVED NOSE DOWN INDICATION, NO MAIN GEAR DOWN INDICATION. CYCL ED SEVERAL TIMES. CREW DIVERTED TO KAGS AND USED EMERGENCY PROCEDURE TO LOWER GEAR. ALL GEAR DOWN AND LOCKED FOR LANDI NG. MAINTENANCE WAS UNABLE TO DUPLICATE. CHECKED ADJUSTMENTS OF MAIN LANDING GEAR PROXIMITY SWITCHES, VISUALLY INSPECT ED DOWNLOCK WIRING HARNESSES AND ACCOMPLISHED MAIN LANDING GEAR RETRACTION AND EXTENSION SEVERAL TIMES AND PERFORMED AN EMERGENCY EXTENSION. NO DEFECTS NOTED. REPLACED 4 NEW DOWNLOCK INDICATOR BULBS (PRECAUTIONARY). A MAINTENANCE CHECK F LIGHT WAS ACCOMPLISHED AFTER MAINTENANCE WITH ALL OPERATIONS NORMAL. THERE IS NO HISTORY OF THIS DISCREPANCY ON THIS AC 2 L 7 2 4F RT A21EA 20080902 CE 2008 9 2 2008FA0000556 1 20080702 G 2931 1240583000 TRANSDUCER LEAR 60 60LEAR 5170707 CE HYD PRESSURE MALFUNCTIONED C O OTHER J WARNING INDICATION LD LANDING 1 SW 99 262FX 633 323 HYDRAULIC PRESSURE GAUGE READ ZERO ON LANDING CHECK. FLAPS AND LANDING GEAR EXTENDED NORMALLY. GAUGE WAS SEEN TO FLUCT UATE BETWEEN NORMAL TO 1000 PSI TO ZERO PSI ON APPROACH. BRAKES AND THRUST REVERSERS OPERATED NORMALLY. GAUGE READS ZE RO DURING TAXI. CREW DECLARED AN IFE AS A PRECAUTION. MAINTENANCE REPLACED THE HYDRAULIC PRESSURE TRANSDUCER. OPS CHE CK AND LEAK CHECK PERFORMED SATISFACTORILY. (S) 2 L 7 2 4F RT A10CE 20080826 NM 2008 8 26 2008FA0000557 1 20080801 G 2742 900C2010375103 CONTROL ROD DOUG MD900 MD900 3027375 NM VERTICAL STAB BROKEN C A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 WP 25 902RN 90000121 EXPERIENCED EXCESSIVE LT PEDAL (2-3 INCHES) DURING CRUISE FLIGHT AT 70 TO 80 PERCENT TRANSMISSION TORQUE. DURING POST F LIGHT FOUND THAT THE LT VERTICAL STABILIZER MOVED FREELY. FURTHER INSPECTION REVEALED THAT THE LT VERTICAL STABILIZER C ONTROL SYSTEM (VSCS) ACTUATOR CONTROL ROD WAS BROKEN AT THE THREADED PORTION. (S) 1 G 7 2 3U NC H19NM 20080903 CE 2008 9 3 2008FA0000558 1 20080801 G 5753 0425118 FITTING CESSNA 140 140 2071602 CE LT TE FLAP CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 03 76671 11111 THE PART WAS BEGINNING TO RUST THROUGH IN LOCATION RESPONSIBLE FOR ATTACHING THE LT FLAP TO THE FLAP CONTROL. THE DEFECT WAS FOUND DURING AN ANNUAL INSPECTION. PROBABLE CAUSE WAS RUSTING DUE TO AGE. A MORE THOROUGH INSPECTION OF THE AREA DU RING PREFLIGHT SHOULD HELP DETECT THE PROBLEM SO THAT CORRECTIVE ACTION CAN BE TAKEN. 1 H 7 1 3O NC A768 20080903 EA 2008 9 3 2008FA0000559 2 20080810 G 7414 DRIVE SHAFT PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA MAGNETO BROKEN D K NONE O OTHER IN INSP/MAINT 1 CE 01 2952R 03092108 28R35344 DISTRIBUTOR (POINT CAM SHAFT BROKE FLUSH WITH UPPER MAG GEAR INNER RACE CAUSING TOTAL MAG FAILURE. PART WAS RETURNED TO OWNER. (K) 1 L 7 1 3O 3 O 2A13 1E10 20080903 CE 2008 9 3 2008FA0000560 1 20080808 G 3222 S18271 VALVE CESSNA 172 R172K 2072431 CE NOSE STRUT DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SW 09 9927V R1722354 A NEW VALVE WAS ORDERED AND INSTALLED TO CURE A SUSPECTED LEAK IN THE VALVE CORE. THE NEW VALVE ARRIVED WITH A BRIGHT A PPEARANCE, EITHER CHROME OR NICKEL PLATED. WITH THE NEW VALVE INSTALLED, THE STRUT LEAK WORSENED. AN EXTERNAL INSP REV EALED THAT THE COSMETIC PLATING WAS FLAKING FROM THE HEX FLATS. THE VALVE WAS REMOVED AND IT WAS FOUND THAT THE PLATING WAS ALSO FLAKING IN THE THREAD-AREA, AND THIS RESULTED IN A LEAK AROUND THE VALVE. THIS VALVE EMPLOYS A NPT THREAD (1/ 4 INCH PIPE THREAD) AND THE THREADS FORM THE SEAL WHEN INSTALLED. THE REMAINING PLATING WAS EASILY SCRAPED FROM THE THR EADS WITH A PICK AND THE VALVE WAS REINSTALLED WITHOUT FURTHER DIFFICULTY. SUBMITTER ADMITS THAT THE PLATING RESULTS IN 1 H 7 1 3O 3A17 20080903 SO 2008 9 3 2008FA0000561 1 20080513 G 2497 WIRE PIPER PA44 PA44180 7104402 SO LYC O320 O320* 41508 EA ALTERNATOR BROKEN D O OTHER O OTHER NR NOT REPORTED 1 SO 15 2163F H092370 447995167 INTERNAL FAILURE DUE TO BROKEN WIRES INTERNALLY, HEAVY SPARKING INSIDE ENGINE COMPARTMENT. (K) 1 L 7 2 3O 3 O A19S0 E274 20080903 CE 2008 9 3 2008FA0000562 1 20080627 G 5311 12943003723 FRAME BEECH 1900 1900D 1154162 CE PWA PT6 PT6* 52043 EA FS 363.25 CRACKED B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 534M 10817 UE333 DURING STRUCTURAL INSP, FOUND LOWER FRAME WEB CRACKED AT FLANGE CORNER. TEE ATTACHED TO FRAME CRACKED THRU LOWER RIVET HOLE. DOUBLER ATTACHED TO LOWER AFT SIDE OF WEB WAS ALSO CRACKED. THE AFT CLIP, ATHAT ATTACHES THE LOWER FRAME TO THE SIDEWALL SEAT TRACK STRINGER, WAS LEFT OUT AT BUILD. THE STRESSES NOT BEING TRANSFERRED TO SUPPORTING STRUCTURE, BECAUS E OF THE MISSING CLIP, MAY HAVE ADDED TO THE FRAME FAILURE. THE DAMAGE WAS REPAIRED IAW SRM AND DER REPORT. (K) 2 L 7 2 4T 3 T RT A24CE E2NE 20080903 CE 2008 9 3 2008FA0000563 1 20080808 G 2810 5038903417 FUEL CELL BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE LT WING PLUGGED B E81R O OTHER O OTHER NR NOT REPORTED 1 GL 03 350RV 60 FL585 PILOT REPORTED FUEL IMBALANCE OF 200 LBS AFTER TOPPING OFF TANKS. FUEL QUANTITY INDICATING AND FUEL VENT SYSTEM WERE CH ECKED AND CONFIRMED GOOD. DURING DEFUEL, NOTED THAT LT WING TRANSFER TO LT NACELLE TANK WAS TOO SLOW TO ALLOW FULL SERV ICING OF LT WING FUEL SYSTEM . ACCESSED FUEL TRANSFER TUBE FROM INSIDE OF LT IB AFT FUEL CELL, TO NACELLE FUEL TANK, AN D FOUND IT PLUGGED WITH A RAG. REMOVED RAG, CLEANED WING FUEL STRAINER, AND SECURED FUEL SYSTEM. LT FUEL SYSTEM CAN NO W BE SERVICED TO FULL. (K) 2 L 7 2 4T 4 T RT A24CE E4EA 20080903 CE 2008 9 3 2008FA0000565 1 20080813 G 7160 125083029 INTAKE DUCT CESSNA 206 TU206G 2073357 CE CONT O550 IO550* SO ENGINE CRACKED B RC0R O OTHER O OTHER NR NOT REPORTED 1 SW 17 602MB 10 U20604052 MFG SUPPLIED ENGINE INTAKE DUCT BEFORE THE AIR FILTER IS SUBJECT TO CRACKING IN MULTIPLE LOCATIONS. THIS PARTICULAR AC AND ANOTHER IDENTICAL MODEL AC THIS FACILITY MAINTAINS, HAVE BEEN CONVERTED TO ANOTHER ENGINE AFTER THE STC CONVERSION. CRACKING PROBLEM HAS INCREASED SIGNIFICANTLY. HAVE CONTACTED STC HOLDER, THEY HAVE RESPONDED WITH A SCHEME TO REINFORC E THIS DUCT. THIS REPAIR STATION IS LOOKING INTO THIS ALTERATION TO THIS DUCT WHEICH MAY REQUIRE DER SUPPORT. AT PRESE NT, THE DUCTS ARE REQUIRING REPAIRS OF REPLACEMENT EVERY 50 HOURS. A PMA REPLACEMENT DUCT MADE FROM COMPOSITE MATERIAL IS NO LONGER AVAILABLE. (K) 1 H 7 1 3O 3 O A4CE E3SO 20080827 NM 2008 8 27 2008FA0000566 1 20080218 G 7830 315A2502102 PANEL BOEING 737 737 UTILSYS NM THRUST REVERSER DELAMINATED B Z6WR O OTHER O OTHER NR NOT REPORTED 1 CE 07 33297 THE TRANSLATING SLEEVE OF THE NR2 OTBD THRUST REVERSER HALF, INNER BOND PANEL ASSY (ACOUSTIC) HAS AN AREA APPROXIMATELY 30 INCHES X 85 INCHES WHERE THE PANEL HAS DELAMINATED/SEPARATED FROM THE CORE. THIS AREA STARTED AS 12 SMALL AREAS OF D ELAMINATION AND CONTINUES TO GROW. THE PANEL IS BEING SCRAPPED AS A RESULT. THE BONDING SURFACE OF THE PERFORATED PAN EL APPEARS TO HAVE BEEN INADEQUATELY PREPPED PRIOR TO BONDING IN THE ORIGINAL BUILD. THIS CONDITION WAS DISCOVERED AT S PIRIT AEROSYSTEMS REPAIR STATION Z6WR3367 WHERE IT WAS SENT FOR REPAIR FROM CONTINENTAL AIRLINES. (S) 2 L 7 2 4F RT A16WE 20080828 NM 2008 8 28 2008FA0000567 1 20080822 G 5313 LONGERON DOUG MD80 MD83 3023681 NM BS 154 L23L DAMAGED B DU4R K NONE O OTHER IN INSP/MAINT 1 SO 15 874GA 49643 DURING SCHEDULED REPAIR, FOUND DOUBLE DRILLED ON LONGERON 23L AT FS 154.5. (S) 2 L 7 2 4F RT 20080828 NM 2008 8 28 2008FA0000568 1 20080822 G 5313 LONGERON DOUG MD80 MD83 3023681 NM BS 150 L23L DAMAGED B DU4R K NONE O OTHER IN INSP/MAINT 1 SO 15 874GA 49643 DURING SCHEDULED REPAIR, MISDRILLED 3 EACH HOLES AT FS 150 AND 3 INCHES BELOW LONGERON 23L. (S) 2 L 7 2 4F RT 20080903 EU 2008 9 3 2008FA0000570 1 20080729 G 6220 704A33651158 BEARING SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE M/R SWASHPLATE WORN B P49R K NONE O OTHER IN INSP/MAINT 1 EA 65 277HC 688 M1687 2052 COMPLIED WITH 2 YEAR / 500 HR INSP. TASK 62.30.00.601 M/R SHAFT INSP. WHILE PERFORMING INSP OF SWASHPLATE GUIDE UNIBAL L FOUND WHILE ROTATING SWASHPLATE. UPPER SEAL FOR BRG WAS NOT ROTATING BECAUSE IT WAS NOT FIRMLY ATTACHED TO OUTER RACE OF BRG WITH THE SEAL BEING LOOSE & UNSECURED IT WORE INTO SWASHPLATE BRG OUTER STOP RING. REPLACED SWASHPLATE BRG, OUT ER STOP RING WITH NEW. RECOMMENDATION WOULD BE WHILE GREASING SWASHPLATE BRG DURING 100 HOUR INSP, LIFT SWASHPLATE BOOT TO INSPECT BRG SEAL FOR MOVEMENT DURING ROTATION. (L) 1 G 7 1 3U 3 U NC H9EU E19EU 20080903 CE 2008 9 3 2008FA0000571 1 20080722 G 2730 CONTROL CABLE MTSBSI MU2 MU2B36A 5780413 CE ELEVATOR BROKEN B IZ2R K NONE O OTHER IN INSP/MAINT 1 SW 15 868MA 9216 708SA PILOT COMPLAINED OF POOR ELEVATOR TRIM OPS. UPON INSP, FOUND ELEVATOR TRIM CABLE 311AS-14-7245 BROKEN (RT CABLE). 311A S-14-7362 (LT CABLE), 010A-61179-81 (RT AFT) CABLES FRAYED. IDLER PULLEY SHAFT ON PITCH TRIM SERVO SHEARED. REPLACED C ABLES & SERVO, OPS CHECKED. RIGGED AS NEEDED. 1 H 7 2 3T A10SW 20080903 SO 2008 9 3 2008FA0000572 1 20080818 G 3233 35380000000 ACTUATOR GULSTM G159 G159 3952202 SO GARRTT TFE731 TFE7314R 01518 WP RT MLG LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 5950C 774 213 RT MLG SIDE BRACE ACTUATOR LEAKING FROM SWITCH ASSY. SIDE BRACE ACTUATOR REMOVED, REPLACED WITH REPAIRED ACTUATOR ASSY. 2 L 7 2 4T 4 F 1A17 E6WE 20080903 CE 2008 9 3 2008FA0000573 1 20080821 G 2842 1183810025 FLOAT VALVE RAYTHN 390 390 7150030 CE FUEL TANK SEPARATED D K NONE N FALSE WARNING IN INSP/MAINT 1 WP 01 3725L 1219 RB155 DURING 1200 HR INSP WHICH REQUIRES OPENING ALL WING AND FUSELAGE FUEL TANK ACCESS PANELS FOR INTERNAL INSPECTION IN BOTH LT & RT CTR FUSELAGE TANKS, FWD FLOAT VENT VALVES FLOAT SECTION OF VALVE ASSY WAS FOUND SEPARATED AND LAYING LOOSE INSI DE FUEL TANK AREA. RECOMMEND INSP OF LT & RT FWD VENT VALVE FLOAT ASSEMBLIES AT NEXT EARLIEST TIME OR INSP. REPLACE AL L SUSPECTED OR FAULTY FLOAT VALVES. 1 L 7 2 3F RT A00010WI 20080903 SO 2008 9 3 2008FA0000574 2 20080815 G 7414 IMPULSE COUPLING CESSNA 182 182N 2072730 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL MAGNETO FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 07 92551 1736 18260256 275543R 891141 PILOT PERFORMED PRE-FLIGHT INSP DISCOVERED OIL ON FWD PORTION OF COWLING, SLIGHT OIL RESIDUE ON WINDSHIELD. MECHANIC RE MOVED TOP COWLING TO INVESTIGATE, DISCOVERED MAGNETO HOUSING SHATTERED AT AREA IMMEDIATELY ADJACENT TO IMPULSE COUPLING. APPARENTLY IMPULSE COUPLING ENGAGING MECHANISM SOMEHOW CONTACTED ACTUATING PIN WHILE OPERATING (OR ENGINE BACKFIRED, W E DON`T HAVE FURTHER INFORMATION TO ASCERTAIN THIS CONDITION) SHATTERED MAGNETO BODY HSG. MAGNETO WAS STILL FIRING, FIX ED TO ENGINE (NOT LOOSE) ENGINE OPS WAS REPORTED NORMAL UPON ARRIVAL OF LAST FLIGHT, WHICH SEEMS TO INDICATE THAT MAGNET O HAD OPERATED IN THIS CONDITION FOR WHAT APPEARS TO BE AT LEAST AN HOUR OR MORE. NO MISFIRE OR MAGNETO DROP DETECTED. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 20080904 NM 2008 9 4 2008FA0000575 1 20080821 G 2421 SHAFT DOUG MD90 MD9030 3023690 NM AC GENERATOR SEIZED C HZ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 17572 436 GENERATOR UNIT SEIZED. THE GENERATOR FAILURE ROOT CAUSE WAS DETERMINED TO BE A ROTOR BAND SHAFT WHICH RESULTED IN AN OUT OF BALANCE CONDITION. THE OUT OF BALANCE ROOT CAUSED AN EARLY FAILURE OF THE ADE BEARING. ALL OTHER DAMAGE RESULTED FRO M THE BEARING FAILURE. PENDING ENGINEERING EVALUATION. (K) 2 L 7 2 4F RT A6WE 20081001 EA 2008 10 1 2008FA0000577 2 20080612 G 8530 AEL12688P020 VALVE SEAT LYC O360 IO360A1A 41514 EA CYLINDER HEAD DAMAGED B Y2GR O OTHER O OTHER NR NOT REPORTED 1 EA 23 INTAKE VALVE SEAT CAME LOOSE FROM THE SEAT BORE IN THE CYLINDER HEAD. THE LOOSE SEAT DAMAGE TO THE CYLINDER HEAD, VALVE , AND VALVE SEAT. INTERFERENCE FIT BETWEEN THE VALVE SEAT AND THE CYLINDER HEAD WAS NOT CORRECT. THIS WAS AN OVERHAULE D CYLINDER. (K) 3 O 1E10 20081001 EA 2008 10 1 2008FA0000578 2 20080716 G 8530 AEL12688P020 VALVE SEAT LYC O360 IO360C1E6 41514 EA CYLINDER HEAD DAMAGED B Y2GR K NONE O OTHER IN INSP/MAINT 1 EA 23 INTAKE VALVE SEAT CAME LOOSE FROM THE SEAT BORE IN THE CYLINDER HEAD. THE LOOSE SEAT DAMAGE TO CYLINDER HEAD, VALVE, AN D VALVE SEAT. INTERFERENCE FIT BETWEEN THE VALVE SEAT AND THE CYLINDER HEAD WAS NOT CORRECT. THIS WAS AN OVERHAULED CY LINDER. (K) 3 O 1E10 20080909 SO 2008 9 9 2008FA0000579 1 20080610 G 2916 RESERVOIR PIPER PA31 PA31325 7103105 SO LYC O540 LTIO540F2BD 41533 EA HYD SYSTEM LOW G O OTHER J WARNING INDICATION AP APPROACH 1 CE 01 727HB 318112006 L266868A ON FINAL APPROACH THE LANDING GEAR HANDLE WAS PLACED IN THE DOWN POSITION. THE GEAR WAS VIEWED IN THE MIRROR AT 45 DEGR EE ANGLE. THERE WERE NO GREEN LIGHTS INDICATING GEAR DOWN AND LOCKED. THE PILOT TRIED TO RAISE AND LOWER THE GEAR AGAIN WITH NO MOVEMENT EITHER DIRECTION. THE PILOT THEN PROCEEDED TO MANUALLY PUMP THE GEAR DOWN. AFTER THREE GREEN LIGHTS WERE ON, THE AIRCRAFT WAS FLOWN BACK, WITH THE GEAR DOWN. MAINT NOTE: HYDR RESERVOIR WAS FOUND TO BE IMPROPERLY SERVICE D. TRAINING WAS CONDUCTED FOR ALL MAINT ON PROPERLY SERVICING THE POWERPACK. THIS CAN BE TRICKY AS IT IS DIFFICULT TO S EE THE FLUID LEVEL. (K) 1 L 7 2 3O 3 O A20SO E14EA 20080909 CE 2008 9 9 2008FA0000580 1 20080827 G 2435 BEARING CESSNA 500 S550 2076607 CE PWA JT15 JT15D4 52112 NE STARTER GEN FAILED B OW5R O OTHER O OTHER NR NOT REPORTED 1 GL 27 802Q 95264 S5500157 PCE102330 FRONT BEARING FAILURE IN FLIGHT. (K) 1 L 7 2 4F 4 F RT A22CE E1NE 20081001 SO 2008 10 1 2008FA0000581 1 20080812 G 5100 SL53E19600 VERNATHERM PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL FAILED D O OTHER O OTHER TX TAXI/GRND HDL 1 AL 03 27663 392 317852094 L152068A DJ10231A THIS VERNATHERM HAD A SHAFT AND NUT ASSY THAT WAS SECURED WITH A ROLL PIN. THE SHAFT FAILED AT ROLLPIN. THE NUT, SHAFT PIECE AT ROLLPIN TRAVELED THRU THE OIL GALLY AND LODGED AT A FITTING. HIGH OIL TEMP ALERTED US TO THIS FAILURE, OIL PR ESSURE WAS NORMAL.(K) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081006 EA 2008 10 6 2008FA0000583 2 20080708 G 8530 CYLINDER HEAD CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C16 GL ENGINE SEPARATED G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 WP 19 5268U 172RG0314 RL2898936A 04136 ON JULY 8, 2008, MADE AN EMERGENCY LANDING IN DESSERT TERRAIN AFTER THE ENGINE BEGAN TO EXHIBIT SEVERE VIBRATIONS, LOSS OF POWER AND SMOKE. THE NR 2 CYLINDER WAS FOUND TO HAVE SEPARATED FROM THE CASE, SEVEN OF THE EIGHT HOLD STUDS WERE FO UND TO HAVE SHEARED. ONLY ONE HOLD DOWN STUD WAS LT INTACT. THERE WAS NO HISTORY IN THE AC LOGS TO INDICATE IF THE HOL D DOWN STUDS HAD BEEN REPLACED. (K) 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 20080909 CE 2008 9 9 2008FA0000584 1 20080731 G 2510 551900921 SEAT FRAME CESSNA 500 550 2076604 CE COCKPIT SEAT CRACKED D O OTHER O OTHER NR NOT REPORTED 1 CE 05 64TF 5500064 UPPER CHAIR BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAI R WAS REPAIRED IAW STO-1042WI STRUCTURAL SEAT REPAIR. (K) 1 L 7 2 4F A22CE 20081006 2008 10 6 2008FA0000585 1 20080818 G 2421 11522185 GENERATOR FAILED B HZ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 1572 FAILS SATURATION CURVE CHECK-ZERO VOLTS ANY PHASE. BROKEN LOWER CROSSOVER ON ROTOR. PENDING ENGINEERING EVALUATION. (K) 20081003 EA 2008 10 3 2008FA0000586 2 20080915 G 8520 TT73806 PUSHROD LYC O235 O235L2C 41505 EA ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 11 L1972215 (3) PUSHRODS (TT73806) WERE INSTALLED IN THIS ENGINE AND ALL 3 HAD APPROXIMATELY A .3750 INCH VERTICAL CRACK ON BOTH END S. CAUSE UNKNOWN - NO RECOMMENDATIONS. (K) 3 O E223 20081006 2008 10 6 2008FA0000587 4 20080819 G 6113 D57691P DOME MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA HARTZL HCC2Y HCC2YR1 GL SPINNER CRACKED B NT3R O OTHER O OTHER CR CRUISE 1 WP 25 9485V 22 700043 CH42078B THE SPINNER ASSY FAILED IN FLIGHT ON A 2.2 HR FLIGHT LEG. APPROXIMATELY 1.5 HRS INTO THE FLIGHT A SMALL SHUDDER WAS FELT AND ALL INDICATION CHECKED NORMAL. THE AC COMPLETED THE FLIGHT AND IT WAS NOTED THAT 4" X 4" SECTION OF THE SPINNER BRO KE OFF. THE COWLING HAD TWO SCRAP MARKS AND NO OTHER DAMAGE WAS NOTED. MFG SL-61-286 WAS ACCOMPLISHED 7.31 HRS PRIOR TO FAILURE. OWNER REPORTS SPINNER WAS CHECKED ON PREFLIGHT APPROXIMATELY 1.5 HRS PRIOR TO FAILURE. SPINNER TT 21.64 HRS. P ROBABLE CAUSE: SPINNER DOME IS TOO LARGE FOR A SPINNER WITHOUT A FORWARD BULKHEAD FOR SUPPORT. (K) 1 L 7 1 3O 3 O 2A3 1E10 5 C P920 20081003 SO 2008 10 3 2008FA0000588 1 20080826 G 3220 502341 BOLT PIPER PA44 PA44180 7104402 SO NG LOCKING PAW SHEARED D MOVV K NONE O OTHER IN INSP/MAINT 1 WP 21 239AT 4496038 DURING FAA CHECK RIDE, THE NOSE LANDING GEAR DID NOT PROVIDE A GREEN LIGHT AND THE GEAR UNSAFE WARNING LIGHT AND HORN OP ERATED. AFTER AN UNEVENTFUL LANDING. THE ACFT WAS BROUGHT INTO MAINT FOR TROUBLESHOOTING AND REPAIRS. THE PIVOT BOLT FOR THE NOSE GEAR LOCKING PAW HAD SHEERED IN TWO. THE FAIL POINT IS LOCATED 1.25 INCHES FROM THE BOTTOM OF THE BOLT HEAD. T HIS PREVENTED THE PAW FROM ACTUATING PROPERLY AND CLOSING THE DOWN LIMIT SWITCH. UPON REPLACEMENT WITH A NEW BOLT, THE P AW ACTUATED PROPERLY AND THE GEAR RETRACTION AND EMERGENCY EXTENSION WERE NORMAL WITH PROPER INDICATIONS. (K) 1 L 7 2 3O A19S0 20081006 GL 2008 10 6 2008FA0000589 1 20080826 G 2110 220045510 DRIVE SHAFT CIRRUS SR SR22 2130001 GL CONT O550 IO550* SO COMPRESSOR SHEARED B 5CSR K NONE O OTHER IN INSP/MAINT 1 SW 05 433CF 0710 THIS AC HAS HAD 5 FAILURES OF THE AIR CONDITIONING COMPRESSOR DRIVE SHEAR SHAFT. THE AVERAGE TIME BETWEEN FAILURES IS 35 .8 HOURS. THE SAME SHAFT BUILT BY ANOTHER MFG, HAS HAD ZERO FAILURES. WE HAVE HAD SEVERAL FAILURES IN DIFFERENT AC WITH THIS PART. THE DESIGN OF THE OTHER SYSTEM SHAFT IS SLIGHTLY DIFFERENT. MFG WILL NO LONGER COVER THIS PART UNDER WARRANT Y. WE HAVE TRIED SEVERAL RECOMMENDATION FROM MFG TO SOLVE THIS PROBLEM TO NO AVAIL. (K) 1 L 7 1 3O 3 O NT A00009CH E3SO 20081006 CE 2008 10 6 2008FA0000590 1 20080813 G 3222 998201005 STRUT BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE NLG MALFUNCTIONED C E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 1250 FA88 POSITION OF THIS TORQUE LINK MOUNT RELATIVE TO THE SHIMMY DAMPNER ARMS HOLE ARE SUCH THAT THE TWO PARTS INTERFERE WITH E ACH OTHER AND DON’T ALLOW THE STRUT TO COMPRESS CLOSER THAN 2 INCHES FROM FULLY COLLAPSED. (K) 2 L 7 2 4T 4 T A24CE E4EA 20081003 EA 2008 10 3 2008FA0000591 2 20080805 G 8520 ST203P010 PISTON RING CESSNA 177 177RG 2073709 CE LYC O360 IO360A1B6 41514 EA ENGINE MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 03 2170Q 25 177RG0570 L1256851A ENGINE WAS OVERHAULED USING MFG PISTON RINGS ST203P010. AFTER 25.4 HRS, RINGS STILL NOT SEATED AND EXCESSIVE BLOW-BY WAS FOULING PLUGS. REPLACED WITH ANOTHER SET OF ST203P010 AFTER HAVING CYLINDERS REWORKED. AFTER 4.2 HRS, ENGINE WAS OPERAT ING SO POORLY, DUE TO BLOW-BY, THAT IT WAS CONSIDERED UNSAFE AND GROUNDED. INDEPENDENT HARDNESS TESTING BY QUALITY TEST ING SVCS, INC, COMFIRMED THE RINGS WERE SOFT. COMPARATIVE TESTS WERE PERFORMED AGAINST PISTON RINGS. AFTER SWITCHING TO OTHER, THERE HAVE BEEN NO PROBLEMS.(K) 1 H 7 1 3O 3 O A20CE 1E10 20081006 CE 2008 10 6 2008FA0000592 1 20080821 G 3230 12801111 SWIVEL FITTING CESSNA 182 R182 2072734 CE LT GEAR LEG FAILED H O OTHER O OTHER TX TAXI/GRND HDL 1 GL 03 4652T R18201725 BRAKE SWIVEL JOINT FAILED LEADING TO FAILURE OF LT BRAKE WHEN EXITING RUNWAY. (K) 1 H 7 1 3O RT 3A13 20081006 EU 2008 10 6 2008FA0000593 1 20080811 G 3520 MC1014101 OXYGEN MASK BRAERO DH125 BAE125800A 1500285 EU CABIN FAILED D G13R K NONE O OTHER IN INSP/MAINT 1 GL 13 862CW 258062 THREE OXYGEN MASKS WERE FOUND TO HAVE THE SAME FAULT. WHEN THE EMERGENCY/PRESS TO TEST CONTROL WAS TURNED TO EMERGENCY T HERE WAS NOT A POSITIVE INCREASE IN PRESSURE. REF MFG MM 35-20-52, PAGE 502 TEST (13). PROBABLE CAUSE: UNKNOWN, RECOMMEN DATION: INCREASE HOW OFTEN CREW OXYGEN MASKS ARE TESTED AND INSURE THAT THEY ARE BEING TESTED PROPERLY.(K) 2 L 7 2 4F RT A3EU 20081006 EU 2008 10 6 2008FA0000594 1 20080811 G 3520 MC1014101 OXYGEN MASK BRAERO DH125 BAE125800A 1500285 EU CABIN DAMAGED D G13R K NONE O OTHER IN INSP/MAINT 1 GL 13 897CW 258077 THREE OXYGEN MASKS WERE FOUND TO HAVE THE SAME FAULT. WHEN THE EMERGENCY/PRESS TO TEST CONTROL WAS TURNED TO EMERGENCY T HERE WAS NOT A POSITIVE INCREASE IN PRESSURE. REF MFG MM 35-20-52, PAGE 502 TEST (13). PROBABLE CAUSE: UNKNOWN, RECOMMEN DATION: INCREASE HOW OFTEN CREW OXYGEN MASKS ARE TESTED AND INSURE THAT THEY ARE BEING TESTED PROPERLY. (K) 2 L 7 2 4F RT A3EU 20081007 EA 2008 10 7 2008FA0000595 1 20080821 G 3241 60025663 PCB CNDAIR CL600 CL600* 1900302 EA MLG UNSERVICEABLE D K NONE O OTHER IN INSP/MAINT 1 NM 01 604SJ JAN82118 1042 UPON LANDING, THE LT OB TIRE BLEW. UPON INSP, TIRE SHOWED SIGNS OF A SEVERE SKID. TESTED THE ANTISKID SYS & TESTED NORMA L. TESTED ALL 4 WHEEL SPEED SENSORS AND FOUND THAT WITH THE BRAKES SET & FULL HYD PRESSURE ON, BOTH OB MAIN WHEELS WOULD NOT RELEASE WHEN SPINNING STOPPED ON WHEEL SPEED SENSORS. BOTH IB WHEELS RELEASED NORMALLY WHEN TESTED. CONTACTED MFG T ECH SUPPORT & INFORMED THE COMPUTER HAD 2 IDENTICAL PCB CARDS THAT COULD BE SWAPPED FOR TROUBLESHOOTING PURPOSES. ONE CA RD IS FOR THE IB MAIN WHEELS AND 1 CARD IS FOR THE OB MAIN WHEELS. SWAPPED CARDS AND THE PROBLEM FOLLOWED TO THE IB MAIN WHEELS. NOW THE OB MAINS WOULD RELEASE NORMALLY DURING A SIMULATED SKID CONDITION BUT THE IB MAINS WOULD NOT RELEASE. R 2 L 7 2 4F RT A21EA 20081007 CE 2008 10 7 2008FA0000596 1 20080821 G 7820 83004 MUFFLER CESSNA 150 150H 2071818 CE CONT O200 O200A 17020 SO ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 05 22355 339 15068233 682287A END CAP SEPARATED (CLEAR BREAK) FROM MUFFLER CAR. FAILURE OCCURED IN THE BEND RADIAS OF END CAP. NOT IN THE END CAP TO MUFFLER CAP, WELD. (K) 1 H 7 1 3O 3 O 3A19 E252 20081003 NE 2008 10 3 2008FA0000597 2 20080826 G 7250 305086010 SUPPORT AMD FALC50 FALCON2000 2730170 NM CFE CFE73811B NE NR 4 BEARING CRACKED B ZN3R K NONE O OTHER IN INSP/MAINT 1 WP 07 48CG 3031 041 P105194 THE NR 4 BEARING SUPPORT, PN 305086010, CRACKED CAUSING THE ENGINE TO SEIZE. AT OPERATING TEMPERATURES, THE NR 4 BEARING SUPPORT AND INVESTMENTCAST MANIFOLD MAY HAVE BECAME LOOSE, PERMITTING RELATIVE MOVEMENT BETWEEN THE PARTS. SB CEF738-7 2-8060 REPLACES THE NR 4 BEARING SUPPORT WITH SUPPORT ASSY PN 305086012, WHICH HAS BEEN DESIGNED WITH AN INCREASED INTER FERENCE FIT TO ELIMINATE MOVEMENT. (K) 2 L 7 2 4F 4 F RT A50NM E44NE 20081007 GL 2008 10 7 2008FA0000598 1 20080814 G 5344 DA4522100002 HINGE DIAMON DA40 DA40 2990002 GL AFT PAX DOOR BROKEN D L10R K NONE O OTHER IN INSP/MAINT 1 GL 11 681DS 523 40611 THE REAR CABIN DOOR AFT HINGE HAS BROKE AS DECRIBED IN AC 43-16A ALERT 360. PROBABLE CAUSE IS REAR HOLD-OPEN CYLINDER. 1 L 7 1 3O NT A47CE 20081006 GL 2008 10 6 2008FA0000599 1 20080814 G 5210 DA4522100002 HINGE DIAMON DA40 DA40 2990002 GL AFT CABIN DOOR CRACKED D L10R K NONE O OTHER IN INSP/MAINT 1 GL 11 504DS 40204 THE REAR CABIN DOOR AFT HINGE HAS A CRACK IN THE SAME AREA AS DESCRIBED IN AC 43-16A ALERT 360. PROBABLE CAUSE IS REAR H OLD-OPEN CYLINDER. (K) 1 L 7 1 3O NT A47CE 20081006 CE 2008 10 6 2008FA0000600 1 20080702 G 3240 BRAKE ASSY CESSNA 525 525B 2076616 CE WILINT FJ44 FJ44 66000 GL MLG MALFUNCTIONED D O OTHER O OTHER TX TAXI/GRND HDL 1 GL 03 92MA 525B0048 NORMAL LANDING UNTIL BRAKE APPLICATION, AT BRAKE APPLICATION AC YAWED AGRESSIVELY TO THE LT. AC WAS CONTROLLED WITH RT B RAKE AND NOSE WHEEL STEERING. RT BRAKE APPEARED WEAK, AS SPEED DECREASED DIRECTION CONTROL WAS HARDER TO MAINTAIN. AC DE CELERATED SLOWER THAN NORMAL APPROACHING END OF RUNWAY. EMERGENCY BRAKE WAS APPLIED. LT BRAKE GRABBED FORCING THE ACFT O FF THE RUNWAY INVESTIGATION IN TO SOURCE OF THE PROBLEM IS ON GOING. PN AND PART NAME WILL FOLLOW AFTER MFG TEST COMPON ENTS. (K) 1 L 7 2 4F 4 F RT A1WI E3GL 20081003 CE 2008 10 3 2008FA0000601 1 20080901 G 8011 149NL STARTER CESSNA 172 172S 2072439 CE ENGINE FAILED B NO1Y K NONE O OTHER IN INSP/MAINT 1 EA 35 GMEGS 55 10723 STARTER MOTOR FAILURE, AFTER PRE-FLIGHT CHECK, THE STARTER MOTOR WAS UNABLE TO TURN THE ENGINE OVER. (K) 1 H 7 1 3O NT 3A12 20081003 CE 2008 10 3 2008FA0000602 1 20080814 G 7921 99103434 OIL COOLER CESSNA 208 208 2073702 CE PWA PT6 PT6A114 52043 NE CRACKED B MT9R K NONE O OTHER IN INSP/MAINT 1 SW 05 9762F 20800181 PCE17397 UPPER MOUNTING FLANGE HAS A 1.25 INCH CRACK AGAINST OIL COOLER BODY. (K) 1 H 7 1 3T 3 T NT A37CE E4EA 20081003 CE 2008 10 3 2008FA0000603 1 20080723 G 2820 RING RAYTHN 390 390 7150030 CE WILINT FJ44 FJ442A GL REFUELING SYS DISLODGED W NUUY K NONE K FLUID LOSS IN INSP/MAINT 1 EA 35 390EV RB PRESSURE REFUELING CONNECTION CAP FOUND WITH SEALING RING DISLODGED AND HOLDING THE CHECK VALVE OPEN WHEN THE CAP IS INS TALLED. FUEL LEAK FROM CAP CAUSING FUEL TO FLOW FROM IT UP THE SIDE OF THE AC. THE FUEL FLOWING UP THE OUTSIDE OF THE AC FT HAS BEEN DRAWN INTO THE REAR MAINT BAY BY DIFFERENTIAL PRESSURE AT THE GROUND POWER SOCKET AND SPRAYED OVER FLYING CO NTROL CABLES AND ELECTRICAL EQUIPMENT IN THE MAINT BAY AND TAIL CONE, THE DE-ICE CONTROL UNIT, STROBE POWER SUPPLY, PITC H TRIM COMPUTER, COCKPIT VOICE RECORDER AND MAIN POWER DISTRIBUTION AND RELAY BOX ARE ALL CONTAMINATED. (K) 1 L 7 2 3F 4 F RT A00010WI E3GL 20081003 GL 2008 10 3 2008FA0000604 1 20080814 G 5610 CANOPY AMTR ZODIAC CH601XL 05615PW GL COCKPIT DAMAGED G K NONE O OTHER IN INSP/MAINT 1 SW 05 451BB 601051S CANOPY OPENED IN FLIGHT RESULTING IN THE ACFT ENTERING INTO A NOSE DIVE ATTITUDE AND IMPACTING THE GROUND SERIOUSLY INJU RING ONE PILOT AND MINOR INJURIES TO THE OTHER PILOT. THE CANOPY’S LOCKING MECHANISMS AND OVERALL STRUCTURE DO NOT SEEM RELIABLE. THE LT AND RT LATCHING POINTS BOLTS DO NOT APPEAR TO BE LONG ENOUGH AND/OR PROVIDE ENOUGH MATERIAL FOR THE CAN OPY LOCKS TO LATCH DOWN ON. THE CANOPY PLEXIGLASS IS VERY THIN AND COVERS A LARGE CANOPY AIRFRAME AREA WHICH MAKES THE C ANOPY LOOSE AND WOBBLY. THE TWO GASEOUS RETRACT/ EXTEND SHOCKS ON EACH SIDE OF THE FWD CANOPY ALSO APPEAR TO BE TOO STRO NG (40 PSI EACH) WHICH MAY CAUSE THE CANOPY TO HAVE A TENDENCY TO EXTEND IN THE OPEN POSITION IN FLIGHT. IN GENERAL, THE 1 L 7 1 EXPA1L71 20081003 CE 2008 10 3 2008FA0000605 1 20080807 G 3246 D30260 WHEEL CESSNA 172 172M 2072418 CE LYC O320 O320* 41508 EA LT MLG FAILED G K NONE O OTHER IN INSP/MAINT 1 CE 17 9925V 4450 17264559 AFTER LANDING, WHILE TAXIING, HEARD A LOUD BANG. THEN ANOTHER BANG AND THE ACFT DROPPED LEFT. STOPPED, CONTACTED GROUND AND ASKED FOR ASSISTANCE. FOUND THE LT MAIN TIRE FLAT AND OUTER RIM FROM THE LT MAIN WHEEL WAS LYING 6 FT BEHIND ACFT, THE ATTACH BOLTS WERE SCATTERED ACROSS THE TAXIWAY. COULD ONLY FIND FOUR OF THE SIX BOLTS. ASI EXAMINATION OF THE WHEEL, THERE WAS A SPLIT IN THE INNER TUBE AND THE FOUR OUTER RIM ATTACH BOLTS THAT WERE FOUND HAD METAL FROM THE CENTER WHEEL HUB EMBEDDED IN THE BOLT THREADS WHERE THEY HAD PULLED OUT OF THE HUB. TWO BOLTS WERE NOT LOCATED. INSPECTED THE BOLT ATTACH AREAS OF THE HUB WITH A MAGNIFYING GLASS, FOUND SOME CORROSION BUT NO APPARENT CRACKS NOTED. IT APPEARS THAT E 1 H 7 1 3O 3 O NT 3A12 E274 20081006 CE 2008 10 6 2008FA0000606 1 20080815 G 3222 63420003 FORK CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL NLG BROKEN B K NONE O OTHER IN INSP/MAINT 1 GL 25 300BV 1928 5250418 DURING ROUTINE TAXI TO PERFORM MAINT CHECKS AFTER AC HAD BEEN PAINTED, NOSE GEAR AXLE BROKE LOOSE FROM NOSE GEAR STRUT. INVESTIGATION SHOWED BOTH WHEEL BEARING HAD HEAVY RUST AND DID NOT TURN FREELY ON THE AXLE. VERY LITTLE GREASE WAS FOUND IN EIGHER OF THE NOSE WHEEL BEARINGS. IT APPEARS THAT DURING THE TAXI, THE BEARINGS SEIZED ON THE AXLE AND THE RESULTAN T STRESS AND HEAT CAUSED ONE SIDE OF THE NOSE STRUT ASSY TO BREAK WHICH IN TURN ALLOWED THE NOSE WHEEL AND AXLE TO COCK AND BEND THE OTHER SIDE OF THE NOSE STRUT. IMPROPER LUBRICATION OF THE NOSE WHEEL BEARINGS IS SUSPECTED AS A PROBABLE CA USE. (K) 1 L 7 2 4F 4 F RT A1WI E3GL 20081007 NE 2008 10 7 2008FA0000607 2 20080906 G 7250 BRR19985 TURBINE BLADES GULSTM GV GULFSTREAMGV 3980116 SO RROYCE BR700 BR700710A110 NE HP TURBINE CRACKED C K NONE O OTHER IN INSP/MAINT 1 WP 01 551GA 3516 606 11325 DURING A RECENT MID LIFE INSPECTION OF THIS ENGINE BY THE MFG, 58 OF 74 FIRST STATE TURBINE BLADES WERE FOUND CRACKED B EYOND SERVICEABLE LIMITS. THIS WAS A HIGH FAILURE RATE CONSIDERING THE LOW TOTAL ENGINE HOURS. A REPORT FROM THE MFG INT ENDING TO PROVIDE AN UNDERSTANDING FOR THE HIGH RATE OF FAILURE STATED THAT SAND WAS INGESTED AND WAS BLOCKING SOME COOL ING HOLES LEADING TO THERMAL STRESSES WHICH CAUSED THE CRACKS. OF INTEREST IS THAT WHILE BOTH ENGINES ON THIS PARTICULA R AIRFRAME WERE NEVER SEPARATED SINCE NEW AND ALWAYS OPERATED IDENTICALLY BY THE SAME CREWS, AND BOTH INSPECTED AT THIS TIME, ONLY ONE ENGINE EXHIBITED THIS ALARMINGLY HIGH RATE OF FAILURE TO THE STAGE 1 BLADES. THE SISTER ENGINE EXHIBITED 2 L 7 2 4F 4 F RT A12EA E00057EN 20081007 GL 2008 10 7 2008FA0000608 2 20080904 G 7200 2544198 BEARING HONEYWELL BELL 206 206L1 1182107 SW ALLSN 250C 250C30 03013 GL PT GOVERNOR FAILED B HEFR O OTHER O OTHER NR NOT REPORTED 1 WP 01 396RL 1648 BR44409 45396 890360 SPOOL BEARING ASSY (PN 2544198) FAILED INTERNALLY. BEARING ASSY NO LONGER ROTATES AND CAUSED DRIVE SHAFT (PN 2539033) GU IDE POST AND FORK ON GOVERNOR LEVER ASSY. (PN 2523293) TO BEND. ONE FLYWEIGHT (PN 2544200) WAS DAMAGED FROM THE SPOOL BE ARING CHAFING. (K) 1 G 7 1 3U 3 U H2SW E1GL 20081003 GL 2008 10 3 2008FA0000609 2 20080905 G 7230 BLADE BELL 206 206B3 1181506 SW ALLSN 250C 250C20J 03013 GL COMPRESSOR FAILED B HEFR O OTHER O OTHER NR NOT REPORTED 1 WP 01 43MA 6228 2904 KR66644 4156 THIRD STAGE COMPRESSOR BLADE, ONE OF THE BLADES WAS "THROWN" FROM THE PART. NOTE: THIS COMPRESSOR WHEEL IS A ONE-PIECE BLADE DISK. (K) 1 G 7 1 3U 3 U H2SW E4CE 20081003 GL 2008 10 3 2008FA0000610 2 20080908 G 7200 2544198 BEARING BELL 206 206L4 1182110 SW ALLSN 250C 250C30 03013 GL SPOOL FAILED B HEFR O OTHER O OTHER NR NOT REPORTED 1 WP 01 520RL 2932 942 52052 CAE895008 SPOOL BEARING ASSY FAILED INTERNALLY. BEARING ASSY NO LONGER ROTATES AND CAUSED DRIVE SHAFT GUIDE POST AND FORK IN GOVER NOR LEVER ASSY TO BEND. THE UPPER BEARING LOWER SHIELD AND RETAINER HAS COME OFF. THE LOWER BEARING IS INTACT BUT NO L ONGER ROTATES. (K) 1 G 7 1 3U 3 U NC H2SW E1GL 20081007 SO 2008 10 7 2008FA0000611 1 20080814 G 3200 4049B TUBE MAULE MX7 MXT7160 5470204 SO LYC O320 O320* 41508 EA AT FORK OLEO SHEARED B TODR O OTHER O OTHER NR NOT REPORTED 1 CE 07 31865 572 17003C OLEO TUBE (PN 4049B) SHEARED OFF AT FORK ASSY (PN 4086E) UPON LANDING DAMAGE DONE TO PROP, ENGINE, ENGINE MOUNT, NOSE GE AR MOUNT, FIREWALL M ATTACH POINTS, LOWER COWL, AIR INTAKE PLUS ANY HIDDEN DAMAGE FOUND ON INSPECTION. PN FOUND ON MFG DRAWING NR 4050X, DATED 6/7/1988. OLEO TUBE ITEN NR 17, FORK ASSY, ITEM NR 5. (K) 1 H 7 1 3O 3 O 3A23 E274 20081003 2008 10 3 2008FA0000612 2 20080903 G 7414 BEARING CESSNA 182 182T 2072703 CE MAGNETO BURNED B L9OR K NONE O OTHER IN INSP/MAINT 1 WP 19 53610 503 02111750 18281223 REMOVED MAGNETO TO S/B3-08 AND MFG 500 HOUR INSPECTION. REMOVED HARNESS CAP FOUND A LIGHT SMOKE COLORED FILM COVERING CA P AND DISTRIBUTOR BLOCK. REMOVED MAGNETO FROM ENGINE FOUND BEARING BAR BURNED THROUGH ON LEFT SIDE WHEN VIEWED FROM DRIV E END. (K) 1 H 7 1 3O NT 3A13 20081007 GL 2008 10 7 2008FA0000613 3 20080903 G 6111 C13019S CLAMP BEECH 90 F90 1152909 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4T HCB4TN3 GL BLADE FAILED B ZY2R K NONE O OTHER IN INSP/MAINT 1 WP 23 90BD 5569 LA134 EAA1457 PROPELLER UNIT WAS OVERHAULED ON JULY 28, 2008, WO 79785. THE PROPELLER WAS INSTALLED ON ACFT AUG 27, 2008. UPON RUN UP OF ACFT, THE MECHANIC NOTED A GREASE LEAK FROM THE PROPELLER BLADE. A CRACK WAS FOUND. O/H FACILITY WAS NOTIFIED OF THE FINDINGS. THE PROPELLER WAS REMOVED FROM THE ACFT AND RETURNED TO THE FACILITY FOR INSPECTION . O/H FACILITY VERIFIED T HE SAME FINDINGS. BLADE CLAMP WAS REMOVED AND REPLACED WITH AN OHC CLAMP ASSY. ALL WORK WAS PERFORMED IAW SRM 118F, 202A , AND 133C. (K) 1 L 7 2 4T 4 T A31CE E4EA 6 C P40EA 20081007 GL 2008 10 7 2008FA0000614 3 20080909 G 6110 B3476A2 ROD DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL PROPELLER BROKEN B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 19 V2LFC BUA26256 BUA26256 BETA ROD CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALF UNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081007 GL 2008 10 7 2008FA0000615 3 20080909 G 6110 B30012 RING HARTZL DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL PROPELLER BROKEN B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 19 V2LFC 29388 BUA26256 BETA RING CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALF UNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081007 2008 10 7 2008FA0000616 4 20080815 G 2562 DCELL BATTERY PIPER PA28 PA28161 7102803 SO ELT LEAKING B KABR K NONE K FLUID LOSS IN INSP/MAINT 1 GL 13 44FT 297 043551 287716219 BATTERYS LEAK ACID ON TO SPRINGS AND CORRODED THEM. (K) 1 L 7 1 3O 2A13 20081007 CE 2008 10 7 2008FA0000617 1 20080822 G 2121 903840311 BLOWER BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA HARTZL HCD4N3 HCD4N3A GL VENT FAILED B BNGR A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 GL 19 904RB 764 LJ1088 PCE25175 FY2838 PILOT DETECTED SMOKE IN CABIN, LANDED. TROUBLESHOT ODOR, CHECK IN ENGINE BAYS, NO DEFECT NOTED. FOUND CABIN VENT BLOWE R NOT WORKING, CHECKED BLOWER SYSTEM WIRING, NO DEFECTS NOTED, CHECKED VENT BLOWER UNDER PILOT FLOOR AND FOUND BLOWER MO TOR LOCKED UP. REMOVED ASSY FOUND MOTOR HAD BURNED, ELEC ODOR. REMOVED AND REPLACED VENT BLOWER WITH OVERHAULED UNIT. OP ERATION CHECKED NORMAL. THIS MOTOR RUNS ON LOW SPEED ANYTIME AUTO COOL OR AUTO HEAT SWITCH IS ON OR WITH BLOWER SWITCH I N LOW OR HIGH AND ENGINES ARE RUNNING. DURING INSPECTION WITH THIS LOCATION OPEN, CHECK BLOWER FOR PROPER OPERATION AND SPEED. (K) 1 L 7 2 3T 4 T RT 3A20 E4EA 5 C STC 20081007 SO 2008 10 7 2008FA0000618 1 20080819 G 2810 3848808 TANK PIPER PA32 PA32R301 7103218 SO LYC O540 IO540* 41532 EA FUEL LEAKING B SVTR K NONE K FLUID LOSS IN INSP/MAINT 1 GL 03 53646 607 3246214 THE ACFT OPERATOR DROPPED THE ACFT OFF WITH A COMPLAINT OF A FUEL LEAK IN THE LT WING. THERE WAS EXTERNAL STAINING AT TH E IB AFT EDGE OF THE TANK ASSY WHERE IT ATTACHES TO THE WING SKIN. THE TANK WAS REMOVED FROM THE AIRCRAFT TO LOOK FOR TH E LEAK. IT APPEARS THAT THE SEALANT HAD DISSOLVED OR WASHED OUT OF THE TANK. THE TANK WAS SENT FOR INSPECTION AND REPAI R. THEY VERIFIED THAT THE SEAM WAS LEAKING AND REPAIRED IT. THERE WAS NO VISIBLE PHYSICAL DAMAGE TO THE TANK OR MOUNTIN G STRUCTURE. AT THE AGE OF THIS AIRCRAFT, WOULD NOT EXPECT TO SEE A TANK LEAK LIKE THIS UNLESS THE SEALANT WAS IMPROPER LY MIXED AT THE FACTORY OR ASSY OR SOME COMPONENT IN THE FUEL WAS DISSOLVING THE SEALANT. (K) 1 L 7 1 3O 3 O A3SO 1E4 20081007 CE 2008 10 7 2008FA0000619 1 20080915 G 2400 CONTACT BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE RELAY ERODED B CROR O OTHER O OTHER NR NOT REPORTED 1 EA 03 300TN 415 FA168 HAD 3 FAILURES OF THE SAME RELAY, FIRST RELAY LASTED 457 HOURS, SECOND RELAY LASTED 187 HOURS, AND THE THIRD RELAY LASTE D 415 HOURS. MOST OF THE TIME THE FAILURE STARTS WITH THE 2 MICRO SWITCHES IN THE COVER GOING BAD. FOR HAVING RELATIVELY LOW TIME, THE MAIN CONTACTS WERE ERODED FAIRLY WELL. (K) 2 L 7 2 4T 4 T A24CE E4EA 20081007 2008 10 7 2008FA0000620 4 20080915 G 2397 M3902957357 SOCKET SKRSKY S76 S76B 8143007 NE CONNECTOR MISINSTALLED B AMCR O OTHER W INADEQUATE Q C NR NOT REPORTED 1 GL 09 520AC 2422 760380 CREW COULD NOT TRANSMIT ON AN FM FREQUENCY THROUGH NR 1 AUDIO CONTROL BOX. MAINT FOUND CONNECTOR PIN SOCKET INSTALLED BA CKWARD. THE PART FOR THE WIRE WAS INSTALLED TOWARD THE PIN SIDE, AND THE PIN SIDE HAD THE WIRE CRIMPED INTO IT. THE SOCK ET IS SYMMETRICAL. UNIT HAS BEEN LIKE THIS FOR MANY YEARS. (K) 1 G 7 2 4U H1NE 20081003 NE 2008 10 3 2008FA0000621 2 20080826 G 7230 307241613 COMPRESSOR WHEEL AMD FALC90 FALCON900EX 2730009 EU GARRTT TFE731 TFE73160 NE ENGINE SEPARATED B ZN3R O OTHER O OTHER NR NOT REPORTED 1 WP 07 58CG 47 112349 THE CREW REPORTED VIBRATION AND ITT RISE. POWER WAS PULLED BACK TO IDLE AND THE AC LANDED WITHOUT INCIDENCE. DISASSEMBLY FINDINGS REVEALED THE LPC2 ROTOR ASSY (PN 307241613). DISC PN 30603731, SN 990316003093, EXHIBITED MATERIAL LOSS IN TH E FORM OF A DISC POST SEPARATION. (K) 2 L 7 3 4F 4 F RT A46EU E1NM 20081003 CE 2008 10 3 2008FA0000622 1 20080904 G 7810 265202231 COWLING CESSNA 208 208B 2073701 CE PWA PT6 PT6A114 52043 NE EXHAUST CRACKED B MT9R O OTHER O OTHER NR NOT REPORTED 1 SW 05 9634B 208B0141 THE SECONDARY EXHAUST COWLING WAS FOUND TO HAVE A 5.5 INCH LONG CRACK NEXT TO THE CENTER EXHAUST HANGER ROD END BRACKET. IT WAS NOTICED THAT ANOTHER CARAVAN IN THE HANGER FOR INSPECTION HAD THE SAME CRACK (LENGTH AND LOCATION) THAT HAD BEEN PREVIOUSLY REPAIRED BY INSTALLING A DOUBLER PATCH. (K) 1 H 7 1 3T 3 T A37CE E4EA 20081003 CE 2008 10 3 2008FA0000623 1 20080905 G 5730 SKIN CESSNA 310 310Q 2074242 CE LT WING CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 13 100EL 310Q0688 FOUND CRACK IN UPPER WING SKIN AS DESCRIBED IN SB MEB08-3. CRACK EXTENDS 4 INCHES FORE AND AFT PARALLEL TO LT WING MAIN LANDING GEAR ASIDE BRACE WING RIB NR 502210451 OB FLANGE. CRACK IS APPROXIMATELY CENTERED IN MLG WHEEL WELL OPENING. CR ACK WAS FOUND VISUALLY DURING COMPLIANCE WITH MEB76-2 MAIN LANDING GEAR RIB SIDE BRACE CRACKS, DURING INSTALLATION OF SK 414-8E. (K) 1 L 7 2 3O 3A10 20081003 SO 2008 10 3 2008FA0000624 2 20080905 G 8520 BUSHING CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO PISTON PIN CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 13 414NC 414A0484 DURING CYLINDER NR 2 REMOVAL TO CORRECT CRACKED CYLINDER, FOUND CONNECTING ROD PISTON P/N BUSHING CRACKED WITH LARGE PIE CE MISSING FROM EDGE. FAILURE IS AS NOTED IN MFG SB071. REMOVED ALL 6 CYLINDERS FROM ENGINE AND FOUND 4 MORE BUSHINGS C RACKED IN SAME LOCATION. MFG HAS CHANGED BUSHING SLIP LOCATION TO POSITION IAW FIGURE 3 OF SB B807. (K) 1 L 7 2 3O 3 O A7CE E8CE 20081007 SO 2008 10 7 2008FA0000625 2 20080905 G 8520 BUSHING CESSNA 421 421C 2076016 CE CONT O520 GTSIO520N 17032 SO PISTON PIN CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 13 410AJ 421C1093 823531R DURING CYLINDER NR 5 REMOVAL TO CORRECT HIGH OIL CONSUMPTION , FOUND CONNECTING ROD PISTON PIN BUSHING CRACKED WITH LARG E PIECE MISSING FROM EDGE. FAILURE IS AS NOTED IN MFG SB SB07-1. REMOVED ALL 6 CYLINDERS FROM ENGINE AND FOUND 4 MORE B USHINGS CRACKED IN SAME LOCATION. MFG HAS CHANGED BUSHING SLIP LOCATION TO POSITION IAW FIGURE 3 OF SB SB071. (K) 1 L 7 2 3O 3 O A7CE E7CE 20081003 CE 2008 10 3 2008FA0000627 1 20080723 G 5753 710516000015 HINGE BRACKET BEECH 76 76 1153005 CE LYC O360 O360* 41514 EA LT WING TE FLAP CORRODED G BEJS O OTHER O OTHER NR NOT REPORTED 1 SO 15 6708A 7712 ME302 LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFOR M VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN. (K) 1 L 7 2 3O 3 O A29CE E286 20081007 CE 2008 10 7 2008FA0000628 1 20080722 G 5753 10516000015 HINGE BRACKET BEECH 76 76 1153005 CE LYC O360 O360* 41514 EA LT WING TE FLAP CORRODED G BEJS O OTHER O OTHER NR NOT REPORTED 1 SO 15 6638D 9976 ME268 LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORT RIBS, WHERE HINGE BRACKET PIN FLAP. UNABLE TO PERFORM VI SUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED INSIDE OF SKIN. (K) 1 L 7 2 3O 3 O A29CE E286 20081003 CE 2008 10 3 2008FA0000629 1 20080722 G 5753 10516000015 HINGE BRACKET BEECH BEECH 76 76 1153005 CE LYC O360 O360* 41514 EA LT WING TE FLAP CORRODED G BEJS K NONE O OTHER IN INSP/MAINT 1 SO 15 110SU 11007 ME81 LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFOR M VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN. (K) 1 L 7 2 3O 3 O A29CE E286 20081003 CE 2008 10 3 2008FA0000630 1 20080723 G 5753 10516000015 HINGE BRACKET BEECH BEECH 76 76 1153005 CE LYC O360 O360* 41514 EA LT WING TE FLAP CORRODED G BEJS K NONE O OTHER IN INSP/MAINT 1 SO 15 278D 16533 ME23 LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFOR M VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN. (K) 1 L 7 2 3O 3 O A29CE E286 20081006 2008 10 6 2008FA0000631 4 20080911 G 6122 210044 ROD WOODWARD BEECH 58 58 1152740 CE GOVERNOR BROKEN B LU4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 6681L 1098981 TH1088 LIFT ROD WAS DISCOVERED BROKEN AT DISASSEMBLY. (K) 1 L 7 2 3O 3A16 20081007 2008 10 7 2008FA0000632 4 20080911 G 6122 B20429 DRIVE SYSTEM MCAULY CONT O520 IO520* 17032 SO BROKEN B LU4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 CGFLM 790221 SPRING-DRIVE DISCOVERED BROKEN AT DISASSEMBLY. (K) 3 O E5CE 20081007 SW 2008 10 7 2008FA0000633 1 20080826 G 6711 206076031107 SERVO BELL 206 206B3 1181506 SW RT CYCLIC MALFUNCTIONED C O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 SW 99 6NJ 4534 DURING START, PILOT NOTICED CYCLIC STICK COULD NOT BE MOVED WHEN THE HYD OFF PROTAKE OFF CHECK WAS INITIATED. WITH HYD POWER ON, FLT CONTROL OP NORM. THE HELICOPTER RETURNED FROM FLT, THE HYDRAULIC FIELD AND SERVO WERE HOT, IT WAS A VERY HOT DAY, TEMP ABOUT 96 DEGREES. PILOT NOTICED THE CYCLIC STICK COULD NOT BE MOVED DURING HIS HYD CHECK. IT WAS SHUT DO WN AND BROUGHT INTO THE HANGAR MX. A HYD MULE WAS HOOKED UP AND OPS NORMAL. BELL HELICOPTER TECH REP WAS NOTIFIED AND ASKED TO COME TO THE FACILITY. THE TECHS DID A GROUND RUN FOR APPROX 15 MIN W/O INCIDENT. AFTER HOVERING FOR 5 MINUTES , THE PROBLEM RETURNED. THE PROB APPEARED TO BE THE RT HYD SERVO (S/N 8528). LT SERVO WAS NEAR OVERHAUL, WE REPLACED I 1 G 7 1 3U H2SW 20081007 SO 2008 10 7 2008FA0000635 2 20080824 G 8500 ENGINE CESSNA 172 172F 2072414 CE CONT O300 O300D 17022 SO POWER LOSS B IGBR O OTHER O OTHER NR NOT REPORTED 1 WP 01 8546U 17252446 29446D4D AC WAS NOT OPERATING UNDER PART 135, IT WAS UNDER PART 91 FLIGHT WHEN INCIDENT OCCURRED. PILOT STATEMENT "ENROUTE, AS WE CRESTED THEMOUNTAINS, THE ENGINE STARTED SPUTTERING, AND RPMS WERE DROPPING. APPLIED CARB HEAT, TRIED SWITCHING BETWEE N FUEL TANKS, MAGNETOS, AND THE RPMS KEPT DROPPING. WE THEN WENT THROUGH THE FORMAL CHECK LIST TO NO AVAIL. THE DECISIO N WAS MADE TO LAND AT RADAR FACILITY. BY THIS TIME THE ENGINE HAD STOPPED. WE MADE THE EMERGENCY LANDING AT THE FACILIT Y AND CAME TO A FULL STOP. DURING THE DESCENT, TRIED STARTING THE ENGINE MULTIPLE TIME, BUT IT DIDN’T START. NO ONE WAS INJURED AND THE PLANE WAS NOT DAMAGED. 1 H 7 1 3O 3 O NT 3A12 E253 20081007 CE 2008 10 7 2008FA0000636 1 20080910 G 3233 20410202 PIVOT ASSY CESSNA 177 177RG 2073709 CE MLG ACTUATOR SHEARED B H5GR O OTHER O OTHER NR NOT REPORTED 1 EA 07 7503V 4800 177RG0802 PILOT COULDN’T OBTAIN GEAR DOWN INDICATION AFTER EXTENDING GEAR. JACKED AC AND FOUND MAIN GEAR WOULDN’T COMPLETELY ENTER DOWN-AND-LOCKED POSITION. FOUND MAIN GEAR RETRACT ACTUATOR REAR MOUNTING/ PIVOT PIN HAD ONE SIDE COMPLETELY SHEARED. TH IS ALLOWED/CAUSED THE TUBULAR MOUNT STRUCTURE TO FLEX FROM SIDE TO SIDE AND CRACK MOST OF THE WAY THROUGH. (K) 1 H 7 1 3O A20CE 20081007 SO 2008 10 7 2008FA0000637 1 20080902 G 5510 510229615 ANGLE AMRGEN AA5 AA5B 3960105 SO HORIZONTAL STAB CRACKED B H5GR O OTHER O OTHER NR NOT REPORTED 1 EA 07 28665 4640 AA5B0739 MAINT NOTICED A CLICKING NOISE AND EXCESSIVE MOVEMENT WHEN APPLYING UP AND DOWN PRESSURE TO HORIZONTAL STABILIZER TIPS. FOUND DELAMINATION, CRACKS AND WRINKLES IN HORIZONTAL STAB FWD SPAR CARRY-THROUGH ATTACH ANGLES INSIDE EMPENNAGE. WE BEL IEVE THE SINGLE MOST CAUSE TO BE PILOTS AND MAINT PUSHING DOWN ON THE FWD SSPAR AREA TO RAISE THE NOSEWHEEL OFF THE GROU ND. (K) 1 L 7 1 3O A16EA 20081007 SO 2008 10 7 2008FA0000638 1 20080902 G 5510 510229616 ANGLE AMRGEN AA5 AA5B 3960105 SO HORIZONTAL STAB CRACKED B H5GR O OTHER O OTHER NR NOT REPORTED 1 EA 07 28665 4640 AA5B0739 MAINT NOTICED A CLICKING NOISE AND EXCESSIVE MOVEMENT WHEN APPLYING UP AND DOWN PRESSURE TO HORIZONTAL STABILIZER TIPS. FOUND DELAMINATION, CRACKS, AND WRINKLES IN HORIZONTAL STAB FORWARD SPAR CARRY-THROUGH ATTACH ANGLES INSIDE EMPENNAGE. WE BELIEVE THE SINGLE-MOST CAUSE TO BE PILOTS AND MAINTENANCE PUSHING DOWN ON THE FWD SPAR AREA TO RAISE THE NOSEWHEEL OFF THE GROUND. (K) 1 L 7 1 3O A16EA 20080930 GL 2008 9 30 2008FA0000639 1 20080902 G 5753 13431003 HINGE CIRRUS SR SR22 2130001 GL CONT O550 IO550* SO TE FLAPS CORRODED B ACOR O OTHER O OTHER NR NOT REPORTED 1 EA 39 121HC 724 0277 FLAP HINGES IN ALL POSITIONS BOTH LT AND RT HAVE INTERGRANDULAR CORROSION NEAR THE POINT OF FAILURE. PN 13431-003, PN 1 3431-004, 13432-002, QTY 2, 13433-006, 13433-005. CONDITION WAS FOUND AT ANNUAL INSPECTION. (K) 1 L 7 1 3O 3 O NT A00009CH E3SO 20081007 SO 2008 10 7 2008FA0000640 2 20080801 G 7414 M3215 BRUSHES COLUMB LC41 LC41550FG400 5150011 NM CONT O550 TSIO550C SO MAGENTO WORN B BIER O OTHER O OTHER NR NOT REPORTED 1 EA 21 623TS 243 41668 914471 DETECTED NUMEROUS MAGNETOS WITH CARBON BLOCKS AND COILS TABS THAT ARE PREMATURELY WEARING OUT IN MAGNETO PN 6320. HAVE H AD CUSTOMERS WITH MAGNETO FAILURES AS EARLY AS 5.5 HOURS ON THEIR NEW MAGNETOS. EVEN THOUGH MFG HAS IDENTIFIED THIS ISSU E AND PUT OUT GUIDANCE TO INSPECT MAGNETOS WITHIN THE NEXT 50 HOURS OF OPERATION AS OF MAY 2, 2008, THIS ISSUE IS A MAJO R CONCERN TO ALL CUSTOMERS DUE TO THE PERFORMANCE ISSUES THEY HAVE EXPERIENCED WITH THESE MAGNETOS AND THE ADDITIONAL DO WN-TIME OF THE AC DUE TO THE FREQUENT INSP REQUIRED (EVERY 100 HRS). MFG NEEDS TO RESOLVE THEIR PRODUCT DEFICIENCY IMMED IATELY AND THE ANSWER SHOULDN’T BE THE CUSTOMERS BEAR THE COST OF REPLACEMENT OR THE ADDED COST OF FREQUENT INSPECTIONS. 1 L 7 1 3O 3 O NT A00003SE E5SO 20081007 EU 2008 10 7 2008FA0000641 1 20080917 G 3230 A223801 SWITCH AMD FALC20 FALCON20C5 2730107 EU GARRTT TFE731 TFE7315BR WP MLG INOPERATIVE B DJSR A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 GL 23 531FL 2389 113 P95155C LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K) 2 L 7 2 4F 4 F RT A7EU E6WE 20081007 EU 2008 10 7 2008FA0000642 1 20080919 G 3230 123371 CONTROL SWITCH AMD FALC20 FALCON20C5 2730107 EU GARRTT TFE731 TFE7315BR WP MLG INOPERATIVE B DJSR A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 GL 23 531FL 2389 113 P95155C LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K) 2 L 7 2 4F 4 F RT A7EU E6WE 20081003 NM 2008 10 3 2008FA0000643 1 20080918 G 8011 6420871A7 ADAPTER COLUMB LC42 LC42550FG350 5150012 NM CONT O550 IO550N 17042 SO STARTER FAILED B BIER O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 21 964SG 42518 689029 OWNER/OPERATOR COMPLAINS THAT HIS ENGINE USES EXCESSIVE OIL OVER SHORT AND LONG FLIGHTS, SOME TIME AS MUCH AS (2) QUARTS IN LESS THAN A 2 HOUR FLIGHT. REPLACED STARTER ADAPTER ASSY WITH NEW PART FROM MFG AND PROBLEM STILL OCCURS WITH OIL BEING PUMPED TO THE OIL SEPERATOR DURING THE GROUND ENGINE RUN. A COPY OF FAA FORM 8130-3 AND SHIPPING DOCUMENTS ARE ATT ACHED TO THIS SDR WITH ADDITIONAL INFORMATION. (K) 1 L 7 1 3O 3 O NT A00003SE E3SO 20081003 GL 2008 10 3 2008FA0000644 3 20080918 G 6111 A66315A CLAMP HARTZL HCA2 HCA2MVK2 GL PROPELLER BLADE BROKEN B ME4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 C6BH4 1873 H138 BLADE CLAMP FOUND TO BE CRACKED DURING MAGNETIC PARTICLE INSPECTION. CRACK IS LOCATED IN REAR HALF EXTENDING FROM THE A- 321 OUTER BOLT HOLE TO THE INSIDE OF THE CLAMP. DURING TEARDOWN INSPECTION, A-321 BOLT REMOVED FROM THIS CLAMP WAS BROKE N IN HALF. (K) 5 C P24EA 20081003 GL 2008 10 3 2008FA0000645 3 20080918 G 6111 A321 BOLT HARTZL HCA2 HCA2MVK2 GL BLADE CLAMP BROKEN B ME4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 H138 A-321 CLAMP BOLT WAS FOUND TO BE BROKEN DURING TEARDOWN INSPECTION. BOLT IS CRACKED IN (2) PIECES APPROXIMATELY .5 THE L ENGTH DOWN THE TREADED AREA. CLAMP THAT IT WAS ATTACHED TO WAS LATER FOUND TO BE CRACKED DURING MAG PARTICLE INSPECTION. (K) 5 C P24EA 20081008 SW 2008 10 8 2008FA0000646 1 20080901 G 6210 407015001111 BLADE BELL 407 407 1182206 SW MAIN ROTOR CRACKED B UOHR O OTHER O OTHER NR NOT REPORTED 1 GL 13 407LG 53143 M/R BLADE HAS 2706.0 HRS TT WHEN CLEANING BLADE FOR REINSTALLATION, MANY SHALLOW CRACKS WERE FOUND ON THE TOP SURFACE OF BLADE 24 INCH IB OF TRIM TAB. THE CRACKS RUN 45 DEGREES TO BLADE SPAN. CONTACTED MFG PRODUCT SUPPORT AND WAS INFORMED T HAT THIS CONDITION IS CALLED "TRACER STRANDS" AND IS A CONDITION NEEDING REPAIR. PRODUCT SUPPORT ALSO INFORMED US THAT T HIS WOULD BE REFERENCED INT THE MANUALS IN THE NEAR FUTURE AND THAT NEWER BLADES HAVE BEEN CORRECTED FOR THIS PROBLEM. ( K) 1 G 7 1 3U O H2SW 20081008 EA 2008 10 8 2008FA0000647 1 20080912 G 5347 SH670RPA0045 SEAT TRACK CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF34* 30015 NE FS 424-513 CORRODED B O OTHER O OTHER NR NOT REPORTED 1 GL 03 636BR 7307 LT FLOOR SEAT TRACK AT FS 424.0-513.0 FOUND TO BE CORRODED BEYOND LIMITS. REMOVED AND REPLACED SEAT TRACK IAW SRM 51-41 -00. (K) 2 L 7 2 4F 4 F RT A21EA 20081008 EA 2008 10 8 2008FA0000648 1 20080912 G 5347 SH670RPA0045 SEAT TRACK CNDAIR CL600 CL6002B19 1900309 EA FS 409 CORRODED B O OTHER O OTHER NR NOT REPORTED 1 GL 03 636BR 7307 LT FLOOR SEAT TRACK AT FS 409.00+16-409.00+128 FOUND TO BE CORRODED BEYOND LIMITS. REMOVED AND REPLACED SEAT TRACK IAW S RM 51-41-00. (K) 2 L 7 2 4F RT A21EA 20081008 EA 2008 10 8 2008FA0000649 2 20080922 G 7414 7710398 MAGNETO CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA LEFT SEIZED D A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SO 13 712TT 643 17275235 L1173239A DURING FLIGHT, A SHUDDER AND SLIGHT LOSS OF POWER WAS REPORTED BY THE PILOT. PRIOR TO THE NEXT FLT DURING THE MAGNETO CH ECK IT WAS DISCOVERED THAT THE LT MAGNETO WAS INOPERATIVE. FURTHER INVESTIGATION FOUND THE LT MAGNETO CONDENSER WAS OUT OF THE MAGNETO CASE AND THE MOUNT FLANGE WAS BROKEN. THE MAGNETO HAD SEIZED, CAUSING THE CASE TO BREAK FREE OF THE ENGIN E. THE INTERNAL PARTS MELTED AND DESTROYED. INSP OF THE INSIDE OF THE ENGINE DRIVE GEARS AND CASE DID NOT REVEAL ANY DA MAGE. OIL WAS DRAINED AND INLET SCREEN CHECKED WITH NO METAL FOUND. THE MAGNETO WAS REPLACED. ACCORDING TO THE LOGBOOKS, THE REMOVED MAGNETO HAD BEEN OVERHAULED AND INSTALLED AT ENGINE OVERHAUL ON 6/30/08 WITH NO INDICATION OF FURTHER MAINT 1 H 7 1 3O 3 O NT 3A12 E274 20081008 CE 2008 10 8 2008FA0000650 1 20080905 G 5320 45A336065 BRACKET BEECH MU300 400A 1155402 CE FUSELAGE CRACKED B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 95GK 8304 RK27 DURING SCHEDULED AIRFRAME INSPECTION FOUND PN 45A33606-5 AND PN 45A33606-6 CABIN UNDER FLOOR REINFORCING BRACKETS AT CAB IN DOOR ENTRANCEWAY CRACKED. SEE SRM 53-10-50-001, FIG 1, SHEET 2 OR 3, ITEMS 29 AND 30. SUSPECT CRACKED FROM FATIGUE, ALSO POSSIBLY FROM PREVIOUS ROUGH CABIN DOOR STEP ASSY HANDLING. AC TECHNICIANS/ INSPECTORS SHOULD INSPECT THIS AREA CAR EFULLY DURING SCHEDULED INSPECTIONS ON HIGHER TIME AIRCRAFT, AND/OR AIRCRAFT WITH PREVIOUS HISTORY OPERATED BY CHARTER/A IR TAXI/ FRACTIONAL OPERATORS. (K) 2 H 7 2 4F RT A16SW 20081008 SO 2008 10 8 2008FA0000651 1 20080828 G 5343 67054803 TRUNNION PIPER PA28 PA28R201 7102816 SO LYC O360 IO360A1A 41514 EA NLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 13 27GS 28R7737160 AIRCRAFT CAME IN FOR HARD STARTING. WHILE REMOVING LOWER COWL, TO ACCESS LOWER SPARK PLUGS, TECH NOTICED THE NOSE LANDIN G GEAR TRUNNION CRACKED WHERE DRAG BRACE ATTACHES TO IT. (K) 1 L 7 1 3O 3 O 2A13 1E10 20081008 NE 2008 10 8 2008FA0000652 2 20080822 G 8500 ENGINE AIRTRC AT300 AT301 0390103 SW PWA R1340 R1340* 52016 NE STOPPED D O OTHER Y ENGINE STOPPAGE NR NOT REPORTED 1 SW 03 2391Z 3010452 12403 ENGINE QUIT IN MID-AIR. ENGINE HAD 1195.0 HOURS SINCE MAJOR OVERHAUL. (K) 1 L 7 1 3R 3 R A9SW 5E2 20081008 EA 2008 10 8 2008FA0000653 1 20080816 G 5347 SEAT TRACK CNDAIR CL600 CL6002B19 1900309 EA BS 409-559 CORRODED D O OTHER O OTHER NR NOT REPORTED 1 GL 03 636BR 7307 (3) SEAT TRACK SECTIONS WERE FOUND TO BE CORRODED BEYOND LIMITS DURING AN INSPECTION AT WL 79.50 - FS 409.0+12 TO FS559. 0 RT SIDE, WL 72.50 - FS 409.0+12 TO 559.0 RT SIDE, WL 79.50 - FS409.0+12 TO FS559.0 LT SIDE. (K) 2 L 7 2 4F RT A21EA 20081008 EA 2008 10 8 2008FA0000654 2 20080723 G 8530 HIO360F1AD CYLINDER HEAD ENSTRM F28 F28F 3300412 GL LYC O360 HIO360* 41514 EA ENGINE DAMAGED G K NONE O OTHER IN INSP/MAINT 1 GL 13 8626E 744 DURING CYLINDER OVERHAUL A DAMAGE SEAT POCKET CUTTER USE USED. THIS RESULTED IN A VALVE SEAT POCKET THAT MEASURED WITHIN LIMITS BUT LACKED THE PROPER SURFACE CONTACT. AFTER APPROXIMATELY 3 HOURS OF ENGINE OPERATION, THE VALVE SEAT CAME OUT CAUSING THE INTAKE VALVE TO BREAK. THIS CAUSED A LOSS OF ENGINE POWER AND THE HELICOPTER MADE A HARD LANDING. HELICOPTE R WAS DESTROYED BY FIRE. (K) 1 G 7 1 3O 3 O H1CE 1E10 20081006 WP 2008 10 6 2008FA0000655 1 20080921 G 7810 C1691 MUFFLER ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540* 41532 EA ENGINE CRACKED D O OTHER O OTHER NR NOT REPORTED 1 GL 03 3203D 200 11598 MUFFLER WAS HEAT BLISTERED AND CRACKED AT TAIL PIPE TRANSITION. COLLECTOR WAS BURNED THRU UNDER CLAMP AT NR 1 CYLINDER, ALSO HEAT BLISTERED. (K) 1 G 7 1 3O 3 O H11NM 1E4 20081008 WP 2008 10 8 2008FA0000656 1 20080921 G 7820 C1691 MUFFLER ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540* 41532 EA EXHAUST BULGED D O OTHER O OTHER NR NOT REPORTED 1 GL 03 510KJ 799 10338 MUFFLER FOUND - BULGED - BLISTERED AND HEAT CRACKED AT TAILPIPE TRANSITION. (K) 1 G 7 1 3O 3 O H11NM 1E4 20081006 CE 2008 10 6 2008FA0000657 1 20080919 G 7810 265202231 COWLING CESSNA 208 208 2073702 CE PWA PT6 PT6A114 52043 NE EXHAUST CRACKED B MT9R O OTHER O OTHER NR NOT REPORTED 1 SW 05 9653F 20800114 PCE17260 THE SECONDARY EXHAUST COWLING WAS FOUND TO HAVE A 5.5 INCH LONG CRACK NEXT TO THE CENTER EXHAUST HANGER ROD END BRACKET. (K) 1 H 7 1 3T 3 T NT A37CE E4EA 20081008 SO 2008 10 8 2008FA0000658 1 20080901 G 5711 6707002 SPAR PIPER PA28 PA28R200 7102811 SO LT WING CRACKED D O OTHER O OTHER NR NOT REPORTED 1 EA 13 LT WING SPAR CRACKED IN THE AREA OF WHERE THE PIVOT BLOCK IS INSTALLED. (K) 1 L 7 1 3O 2A13 20081008 CE 2008 10 8 2008FA0000659 1 20080916 G 2520 71500 SEAT BBAVIA 8 8KCAB 2110612 CE CABIN FAILED D O OTHER O OTHER NR NOT REPORTED 1 GL 13 7698S 26276 REAR SEAT PN 7-1500 FAILED AT THE LT HINGE POINT. THE AN3 SERIES BOLT PULLED THRU THE HINGE LUGS WHICH ARE WELDED TO THE SEAT FRAME BOTTOM. THE RT HINGE HOLES SHOW ELONGATION, BUT REMAINED INTACT. THE AC WAS DOING SPIN TRAINING AT THE TIME OF THE INCIDENT. RECOMMEND THAT THE SEAT FRAME BE MODIFIED TO CURRENT STANDARDS INSTALLED ON NEWER AC. (K) 1 H 7 1 3O A21CE 20081008 SO 2008 10 8 2008FA0000660 2 20080917 G 7414 10357174 CONTACT BEECH 35 G35 1151516 CE CONT E225 E2258 17015 SO RT MAGNETO FAILED D O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 NM 01 4998B 34 F159517DR D4516 33951 RT MAGNETO FAILED COMPLETELY IN FLIGHT DUE TO THE TIP OF THE CONTACT POINTS HAVING SEPARATED FROM HE ASSY. THIS LEFT TH E CONTACTS AND THEREFORE PRIMARY ELECTRICAL CIRCUIT IN A CONTINUALLY OPEN POSITION. RENDERING THE MAGNETO INOPERATIVE. IN A PHONE CONVERSATION WITH THE MFG REP, MFG IS AWARE OF THE POTENTIAL CONDITION AND HAD ISSUED A DISTRIBUTOR INFORMATI ON BULLETIN D1B2008-3. RECALLING CONTACT ASSY AT THE DISTRIBUTOR LEVEL MFG WITH DATE CODES OF 0716-0816 OR THE (16) WEEK OF 2007 TO THE (16) WEEK OF 2008. THE CONTACTS THAT WERE INSTALLED IN THIS MAGNETO IN MAY OF2008 DURING A ROUTINE 500 HR INSP, HAD APPARENTLY MADE THEIR WAY INTO THE RETAIL INVENTORY SYS. (K) 1 L 7 1 3O 3 O A777 E267 20081008 GL 2008 10 8 2008FA0000661 1 20080917 G 8011 CASTING DIAMON DA40 DA40 2990002 GL CONT IO360 IO360* 17025 CE STARTER BROKEN B MZER O OTHER O OTHER TX TAXI/GRND HDL 1 GL 15 273DS F4L08012 40954 L3417151E CUSTOMER ATTEMPTED TO START ENGINE. WHILE CRANKING ENGINE, CUSTOMER REPORTED A LOUD "CLUNK" AND THE PROPELLER STOPPED RO TATING. INVESTIGATED PROBLEM AND FOUND THE STARTER DRIVE CASTING BROKE FROM STARTER MOTOR. THE CASTING INCLUDED A BEARIN G FOR THE STARTER DRIVE SHAFT. SHAFT AND BENDIX GEAR WAS STILL ATTACHED TO THE STARTER MOTOR. (K) 1 L 7 1 3O 3 O NT A47CE E1CE 20081008 CE 2008 10 8 2008FA0000662 1 20080922 G 2810 SEAL RAYTHN 390 390 7150030 CE WILINT FJ44 FJ442A GL FUEL CAP DISLODGED W K NONE K FLUID LOSS TX TAXI/GRND HDL 1 EA 35 390EU RB242 PRESSURE REFUELING CONNECTION CAP FOUND WITH SEALING RING DISLODGED AND HOLDING THE CHECK VALVE OPEN WHEN THE CAP IS INS TALLED. FUEL LEAKING FROM CAP CAUSING FUEL TO FLOW FROM IT UP THE SIDE OF THE AIRCRAFT. THE FUEL FLOWING UP THE OUTSIDE OF THE AIRCRAFT HAS BEEN DRAWN INTO THE REAR MAINTENANCE BAY BY DIFFERENTIAL PRESSURE AT THE GROUND POWER SOCKET AND SPR AYED OVER FLYING CONTROL CABLES AND ELECTRICAL EQUIPMENT IN THE MAINT BAY AND TAILCONE, THE DE-ICE CONTROL UNIT, STROBE POWER SUPPLY, PITCH TRIM COMPUTER, COCKPIT VOICE RECORDER AND MAIN POWER DISTRIBUTION AND RELAY BOX ARE ALL CONTAMINATED . 1 L 7 2 3F 4 F RT A00010WI E3GL 20081006 NE 2008 10 6 2008FA0000663 2 20080826 G 7314 50466 PUMP RKWELL NA265 NA26560 7630106 CE PWA JT12 JT12A8 52042 NE LT ENGINE FUEL WORN C UVVR A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CE 03 XCCAM 6367 632 306145 P689751 AFTER TAKEOFF THE PILOT COULD NOT ADJUST THE LT ENGINE POWER OUTPUT. ENGINE REMAINED AT TAKEOFF POWER WHILE POWER LEVER WAS RETARDED TO IDLE. PILOT RETURNED TO AIRPORT AND SUCCESSFULLY SHUTDOWN THE LT ENGINE BY PLACING POWER LEVER TO CUT-O FF POSITION AND MADE AN UNEVENTFUL LANDING. FUEL CONTROL, PN 706633, SN 55832 WAS REMOVED FROM THE ENGINE DRIVEN FUEL PU MP AND WAS FOUND THAT THE FUEL CONTROL DRIVE SHAFT REMAINED ENGAGED IN FUEL CONTROL DRIVE SPLINE ON THE FUEL PUMP. FURT HER INSPECTION OF FUEL CONTROL UNIT REVEALED THAT THE FUEL CONTROL DRIVE SHAFT RETAINER PLATE HAD WORN COMPLETELY THROUG H AND ALLOWED DISENGAGEMENT OF FUEL CONTROL DRIVE SHAFT FROM FUEL CONTROL UNIT. FUEL PUMP, PN 50466, SN 3ACF34 WAS INSPE 2 L 7 2 4J 4 J RT A2WE 1E9 20081015 SO 2008 10 15 2008FA0000665 1 20081006 G 2460 454668 CIRCUIT BREAKER PIPER PA28 PA28161 7102803 SO COCKPIT FAILED B K NONE H G ELECT. POWER LOSS-50 PC MULTIPLE FAILURE NR NOT REPORTED 1 CE 05 8325T 6923 288116134 FIVE CIRCUIT BREAKERS FAILED INTERMITTENTLY. THE FAILED CIRCUIT BREAKERS WERE ALL RATED AT 5 AMPS, PIPER P/N 454668, DA TE CODE 7903. THE FIVE CIRCUITS AFFECTED WERE; ENGINE GAUGES, TURN COORDINATOR, INSTRUMENT PANEL LIGHTS, OVERHEAD LIGHT S AND RADIO LIGHTS. 1 L 7 1 3O 2A13 20081015 CE 2008 10 15 2008FA0000666 1 20080910 G 5542 5533000095 SKIN CESSNA 500 560CESSNA 2076750 CE RUDDER CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 905LC 7599 5600334 THE LOWER FORWARD RUDDER SKIN IS CRACKED 2.5 INCHES, THIS WAS FOUND DURING ROUTINE PHASE INSPECTIONS. THE RUDDER SKIN P ART NUMBER IS 5533000-95. THIS IS THE THIRD CRACK FOUND IN THE SAME LOCATION ON THE SAME MODEL AIRPLANE THIS CALENDER Y EAR. 2 L 7 2 4F RT A22CE 20081015 CE 2008 10 15 2008FA0000667 1 20081007 G 5610 6656100000009 WINDSHIELD LEAR 45 45LEAR 5170805 CE COCKPIT CRACKED E A UNSCHED LANDING O OTHER CL CLIMB 1 GL 13 241LJ 1778 241 AIRCRAFT DEPARTED LAX PASSING THROUGH 18000 FT CREW HEARD A POP AND PILOT'S WINDSHIELD OUTER PLY CRACKED. CREW DECLARED EMERGENCY AND RETURNED TO LAX. LANDING WAS UNEVENTFUL. INSPECTION OF WINDSHIELD BY STANDARD AERO - LAX FOUND OUTER PL Y WINDSHIELD HAD FAILED. STANDARD AERO - LAX CURRENTLY REPLACING WINDSHIELD WITH NEW. 2 L 7 2 4F RT T00008WI 20081015 NE 2008 10 15 2008FA0000668 2 20081003 G 8530 66713 GUIDE LYC ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE UNDERSIZE D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 99 4126A 464 12096 L3247448E MOMENTARY SEVERE VIBRATION, POWER LOSS AND ENGINE RPM DROP OCCURRED IN-FLIGHT THEN RETURNED TO NORMAL. COMPRESSION CHEC K (COLD) REVEALED STUCK INTAKE VALVE ON NR 6 CYL. INTAKE VALVE GUIDE ID MEASURED .4035" (UNDERSIZED). LIMITS .4040 / . 4050. NO BUILDUP FOUND ON VALVE GUIDE OR STEM. VALVE GUIDE REAMED TO PROPER SIZE PER LYC. TABLE OF LIMITS SSP1776. N O REOCCURRENCE REPORTED. 1 G 7 1 3O 3 O H11NM 1E4 20081017 CE 2008 10 17 2008FA0000669 1 20081002 G 2752 232507911 ATTACH BRACKET LEAR 35 35A 5170602 CE T/E FLAP CRACKED B AJCA K NONE O OTHER IN INSP/MAINT 1 SW 15 308BW 9341 600 438 DURING 600 HOUR INSPECTION FOUND TWO SHEARED ALUMINUM RIVETS, ALONG WITH A 0NE INCH CRACK IN LT FLAP ACTUATOR ATTACHMENT BRACKET, P/N 2325079-11. INSTALLED NEW BRACKET ASSEMBLY, P/N 2325079-17. THIS BRACKET HAS TWO STEEL RIVETS IN PLACE O F THE ORIGINAL ALUM RIVETS. 2 L 7 2 4F A10CE 20081016 CE 2008 10 16 2008FA0000671 1 20080924 G 2797 CC75LA61 WIRE HARNESS CESSNA 208 208B 2073701 CE FLAP SYSTEM CHAFED B MT9R O OTHER O OTHER NR NOT REPORTED 1 SW 05 9738B 11206 208B0097 TIE WRAP WAS MISSING FROM THE CLAMP AT FS 201.50, WHICH ALLOWED THE WIRING BUNDLE CONTAINING THE WIRES FOR THE FLAP SYS PRIMARY MOTOR TO SAG AND CHAFE THROUGH WIRE NR CC75 TO THE FLAP SYSTEM AND PARTIALLY THROUGH LA61 TO THE CARGO AREA LIGH TS ON THE BULKHEAD. THIS CAUSED THE FLAPS TO ONLY RECEIVE POWER TO THE PRIMARY MOTOR IN ONE DIRECTION. SINCE WIRE LA61 WASN`T CHAFFED COMPLETELY THROUGH THE CARGO AREA LIGHTS WERE STILL WORKING. (K) 1 H 7 1 3T A37CE 20081016 CE 2008 10 16 2008FA0000672 1 20080926 G 5340 65651285 CHANNEL CESSNA 500 560CESSNA 2076750 CE CABLE PULLEY MISLOCATED B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 809QS 5600698 DURING PHASE 5 INSP, FOUND ELEVATOR TRIM CABLE CONTACTING ELEVATOR SELECTOR DRIVE CHAIN. FOUND THE TRIM CABLE PULLEY CH ANNEL BRACKET MIS-LOCATED. ORDERED NEW CHANNEL BRACKET AND RELOCATED PULLEY TO CLEAR SECTOR DRIVE CHAIN. (K) 2 L 7 2 4F RT A22CE 20081015 CE 2008 10 15 2008FA0000673 1 20080924 G 5350 671261713 FRAME CESSNA 750 750 2076810 CE TAIL CONE CRACKED B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 960QS 7500160 DURING ROUTINE INSP, FOUND FWD FRAME PN 6712617-13 CRACKED IN (2) LOCATIONS, ON THE TOP LT AND RT SIDES. ALSO FOUND FRA ME AFT OF THIS ONE CRACKED. PN 6712617-14 ON THE TOP RT SIDE. (K) 2 L 7 2 4J RT T00007WI 20081015 CE 2008 10 15 2008FA0000674 1 20080924 G 5350 671261713 FRAME CESSNA 750 750 2076810 CE TAIL CONE CRACKED E CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 978QS 7500187 DURING ROUTINE INSP FOUND FWD FRAME PN 6712617-13 CRACKED. THE CRACKED FRAME WAS LOCATED IN THE UPPER LT SIDE UNDER THE RUDDER TO STINGER FAIRING. (K) 2 L 7 2 4J RT T00007WI 20081016 CE 2008 10 16 2008FA0000675 1 20080908 G 2731 666000134 CONTROL CABLE CESSNA 560 560XL 2076702 CE ELEVATOR TRIM BROKEN B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 641QS 5605295 DURING ROUTINE INSP, FOUND BROKEN STRANDS ON ELEVATOR TRIM CABLE ASSY PN 666000134. DAMAGE FOUND WHERE CABLE PASSES THR OUGH A SERIES OF "S" PULLEYS. (K) 2 L 7 2 4F RT A22CE 20081016 CE 2008 10 16 2008FA0000676 1 20080908 G 2731 666000134 CONTROL CABLE CESSNA 560 560XL 2076702 CE TAIL BROKEN B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 627QS 5605227 DURING ROUTINE INSP, FOUND CABLE STRANDS BROKEN AND FRAMED. THE DAMAGED AREA OF THE CABLE IS WHERE IT GOES OVER A SERIE S OF "S" PULLEYS MOUNTED IN THE HORIZ STAB. SHOULD MAKE THIS A TIME CHANGE ITEM. (K) 2 L 7 2 4F RT A22CE 20081016 2008 10 16 2008FA0000677 4 20080930 G 2562 AK451 ELT PIPER PA34 PA34200T 7103406 SO CABIN FAILED B BIER K NONE O OTHER IN INSP/MAINT 1 EA 21 2190K 347970096 ELT EMERGENCY LOCATOR TRANSMITTER WILL NOT TEST PROPERLY ON A CONSISTENT BASIS BY DISPLAYING CORRECT 3-DIGIT COUNTRY COD E OR 15 DIGIT HEX ID CODE. THIS ELT HAS BEEN TESTED WITH (2) DIFFERENT 406 MHZ TESTERS DISTRIBUTED BY PN 453-1000 AND P N 453-0131 (MEASURE MODEL MEZ 1000 AND PSION ORGANIZER II MODEL LZ64) AND THE PERFORMANCE OF THE 451 ELT HAS BEEN UNSATI SFACTORY. INCONSISTENT RESULTS INCLUDED A DIFFERENT COUNTRY CODE DISPLAYED (305) RATHER THAN CODE 369 OR 366 FOR THE US A AND DIFFERENT 15 DIGIT HEX ID CODE OF 26273300A5FF7FE RATHER THAN THE ACTUAL CODE FOR THE UNIT BEING TESTED (2E285980E 4FFBFF). RAN ADDITIONAL TESTS DUE TO THE INCONSISTENT RESULTS AND THE UNIT FAILED TO OPERATE PROPERLY. UNIT WAS REPLACE 1 L 7 2 3O A7SO 20081015 2008 10 15 2008FA0000678 4 20080930 G 2562 AK451 ELT PIPER PA34 PA34200T 7103406 SO CABIN NO TEST B BIER K NONE L NO TEST IN INSP/MAINT 1 EA 21 2190K 347970096 ELT EMERGENCY LOCATOR TRANSMITTER WILL NOT TEST PROPERLY ON A CONSISTENT BASIS BY DISPLAYING CORRECT 3-DIGIT COUNTRY COD E OR 15 DIGIT HEX ID CODE. THIS ELT HAS BEEN TESTED WITH (2) DIFFERENT 406 MHZ TESTERS. DISTRIBUTED, PN 453-1000 AND 4 53-0131 AND THE PERFORMANCE OF THE 451 ELT HAS BEEN UNSATISFACTORY. INCONSISTENT RESULTS INCLUDED A DIFFERENT COUNTRY C ODE DISPLAYED (305) RATHER THAN CODE 369 OR 366 FOR THE USA AND DIFFERENT 15 DIGITS HEX ID CODE OF 26273300A5FF7FE RATHE R THAN THE ACTUAL CODE FOR THE UNIT BEING TESTED (2E28598052FFBFF). RAN ADDITIONAL TESTS DUE TO THE INCONSISTENT RESULTS AND THE UNIT FAILED TO OPERATE PROPERLY. UNIT WAS REPLACED BY ANOTHER ELT. THE INCONSISTENT RESULTS WERE THE SAME. (K 1 L 7 2 3O A7SO 20081016 NM 2008 10 16 2008FA0000679 1 20080829 G 2910 25W711008293 LINE ISRAEL 1125 1125 NM HYD RESERVOIR CHAFED B JGVR O OTHER K FLUID LOSS NR NOT REPORTED 1 CE 09 111EL 055 TROUBLESHOT HYDRAULIC SYS AND FOUND THE AUXILIARY HYDRAULIC SYS RETURN LINE THAT CONNECTS THE RETURN HYDRAULIC FILTER TO T THE AUXILIARY HYDRAULIC TANK CHAFED, WHICH CAUSED A SLOW LEAK IN THE HYDRA SYS. ACCOMPLISHMENT OF SB 1125-29-254 "HYD RAULIC TUBE CLEARANCE" PROVIDES INSTRUCTIONS FOR A ONE TIME INSP OF THE CLEARANCE BETWEEN THE PRESSURE TUBE AND THE RETU RN TUBE IN THE AREA OF THE HYDR AUXILIARY RESERVOIR. PROCEDURES ARE GIVEN TO ADJUST OR REPLACE THE AFFECTED TUBE ASSEMB LIES DEPENDENT UPON THE INSPECTION FINDINGS. ACFT WAS REPAIRED BY REPLACEMENT OF AUXILIARY HYDRA RETURN TUBE PN 25W7110 08-293 AND ENSURING CLEARANCES WERE MET IAW THE ACCOMPLISHMENT INSTRUCTIONS OF SB 1125-29-254. (K) 2 L 7 2 4F RT A16NM 20081016 GL 2008 10 16 2008FA0000680 3 20080929 G 6110 A3204 SCREW PIPER PA32 PA32300 7103212 SO HARTZL HCC2Y HCC2YK1 GL PROP BLADE WORN B K NONE O OTHER IN INSP/MAINT 1 NM 11 200 CH43680B CUSTOMER COMPLAINED OF AN EXCESSIVELY LOOSE BLADE PRELOAD ON (1) BLADE 4 MONTHS AFTER OVERHAUL. INSP REVEALED EXCESSIVE WEAR ON END OF BLADE PRELOAD SCREWS CAUSING LOOSENESS OF BLADE. OPPOSITE SCREW WAS WORN ALSO BUT NOT TO EXTENT TO BE NOT ICEABLE. SECOND OCCURRENCE OF THIS TYPE NOTICED. INSPECTION OF NEW SCREWS IN STOCK REVEALED IRREGULAR END, IE NOT FLAT BUT ANGULAR. REPLACED BOTH SCREWS AND RETURNED TO SERVICE. (K) 1 L 7 1 3O A3SO 5 C P920 20081028 SO 2008 10 28 2008FA0000681 2 20081014 G 8530 AEC631397 CYLINDER BEECH 36 A36 1151604 CE CONT O550 IO550* SO NR 1 CRACKED D C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 SW 99 6036 355 E1422 296794R AIRCRAFT OWNER REPORTED SEVERE VIBRATION. AFTER INSPECTION IT WAS FOUND THAT SPINNER BULKHEAD WAS SEVERELY CRACKED. AFTE R FURTHER INSPECTION NR 1 CYLINDER WAS FOUND TO BE CRACKED ALL AROUND THE CIRCUMFERENCE OF THE CYLINDER DIAMETER. THE C RACK WAS RIGHT AT THE 9TH AND 10TH COOLING FINS. THIS CYLINDER HAD A TOTAL TIME OF 355 HOURS SINCE NEW. THIS CYLINDER, DUE TO IT'S IDENTIFICATION MARKINGS DID NOT APPLY TO AD 2004-8-10, HOWEVER IT DID APPLY TO ECI'S MSB 06-2 WHICH IDENTIF IES THIS CYLINDER FOR INSPECTION FOR CRACKS. THE AD 2004-8-10 SHOULD PROBABLY INCLUDE ALL CYLINDERS IN ECI'S MSB 06-2. THE CONDITION WAS REPORTED IMMEDIATELY AFTER TAKEOFF AND THE PILOT RETURNED IMMEDIATELY TO THE AIRPORT AND LANDED UNEVE 1 L 7 1 3O 3 O 3A15 E3SO 20081016 CE 2008 10 16 2008FA0000682 1 20080621 G 2720 05701051 CONTROL CABLE CESSNA 170 170A 2072304 CE RUDDER BROKEN C K NONE O OTHER IN INSP/MAINT 1 GL 21 9739A 6459 19200 CABLE BROKE AFT OF REAR PULLEY AND BULKHEAD. NO INSPECTION HOLES IN THIS AREA. (K) 1 H 7 1 3O A799 20081020 EU 2008 10 20 2008FA0000683 1 20080919 G 3210 LANDING GEAR AMD FALC20 FALCON20C5 2730107 EU GARRTT TFE731 TFE7315BR WP FAILED B DJSR A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 GL 23 531FL 113 P95155C LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K) 2 L 7 2 4F 4 F RT A7EU E6WE 20081020 EU 2008 10 20 2008FA0000684 1 20080917 G 3260 A223801 POSITION SWITCH AMD FALC20 FALCON20C5 2730107 EU MLG INOPERATIVE B DJSR A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 GL 23 531FL 113 LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K) 2 L 7 2 4F RT A7EU 20081020 CE 2008 10 20 2008FA0000685 1 20080926 G 2697 WIRE LEAR 45 45LEAR 5170805 CE FIRE DETECTION CHAFED B HMGR O OTHER O OTHER NR NOT REPORTED 1 SW 15 45NM 1158 253 APU FIRE DETECT CIRCUIT BREAKER POPPED ON RT COCKPIT CIRCUIT BREAKER PANEL DURING POWER UP OF AIRCRAFT. TROUBLESHOT SYS TEM FOUND WIRING CHAFED AT FUSELAGE STATION 614.210 AFT EQUIPMENT BAY UPPER AVIONICS SHELF SUPPORT ANGLE PN 4525708307. THE ANGLE DOES NOT HAVE ANY PROTECTION TO PREVENT CHAFING OF WIRING FROM THE FACTORY AND IT APPEARS THAT CLEARANCE IS NO T GREAT ENOUGH TO KEEP THE WIRING FROM CHAFING. HAVE NOTIFIED MFG TECH SUPPORT. (K) 2 L 7 2 4F RT T00008WI 20081020 CE 2008 10 20 2008FA0000686 1 20080929 G 2910 6317003136 LINE CESSNA 525 525 2076601 CE HYD SYSTEM RUPTURED B EWCR O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 39 44CK 2416 5250401 RUPTURE OF TUBE AT SIDE WHERE BENDING DIES LT MARKING BOTH ABOVE AND BELOW OPENING. AFTER TAKEOFF, LOW FLUID AND PRESSU RE WARNING LIGHTS CAME ON AND ACFT RETURNED TO AIRPORT. ACFT WAS TURNED OVER TO SERVICE CENTER. LEAK WAS LOCATED AND TH E LINE REPLACED ALONG WITH BOTH HYDRAULIC PUMPS. (K) 1 L 7 2 4F RT A1WI 20081020 EA 2008 10 20 2008FA0000688 2 20081001 G 7314 154739704 PUMP CESSNA 182 182S 2072701 CE LYC O540 IO540AB1A5 EA FUEL SYSTEM CRACKED D O OTHER K FLUID LOSS NR NOT REPORTED 1 FS 60 66419 18280132 L2616748A PUMP HOUSING CRACKED ALONG SEAM. POSSIBLE WEAK SPOT UPON MANUFACTURING. (K) 1 H 7 1 3O 3 O NT 3A13 1E4 20081028 CE 2008 10 28 2008FA0000689 1 20081003 G 2731 6660161156660161 PUSHROD CESSNA 560 560XL 2076702 CE ELEVATOR TAB WORN C K NONE E VIBRATION/BUFFET CR CRUISE 1 NM 07 669TT 694 5605684 ON RETURN FLIGHT TO HOME STATION, CREW COMPLAINED OF SLIGHT VIBRATION IN FLIGHT. CREW FELT THE VIBRATION WAS ISOLATED T O THE ELEVATOR CONTROL SYSTEM. UPON PRELIMINARY INSPECTION OF THE ELEVATOR SYSTEM, FOUND BOTH ELEVATOR TRIM TABS PLAYS BEYOND THE TOLERANCE DEFINED IN 560XL AMM TASK 27-31-00 220. REMOVED AND REPLACED PUSH RODS (P/N 6660161-15 AND 6660161 -17) ON BOTH ELEVATOR TRIM TABS IAW 560XL AMM 27-32-03 PARAGRAPH 4D(3)(A). AIRCRAFT RETURNED TO SERVICE. SUBSEQUENT FL IGHT REVEALED NO FURTHER ISSUE. 2 L 7 2 4F RT A22CE 20081028 SO 2008 10 28 2008FA0000690 2 20081017 G 8530 AEC631397 CYLINDER CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C505 GL ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 05 414AN 654 414A0819 813675R UPON INSPECTION FOUND THAT NR 1 AND NR 5 CYLINDERS WERE CRACKED AND LEAKING FUEL ORIGINATING JUST INBOARD OF THE FUEL NO ZZLE BETWEEN THE 16TH AND 18TH COOLING FINS. CYLINDERS WERE NEW WHEN INSTALLED AT ENGINE OVERHAUL. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 20081023 2008 10 23 2008FA0000693 4 20080911 G 6122 210044 ROD BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO GOVERNOR BROKEN B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 19 6681L TH1088 LIFT ROD WAS DISCOVERED BROKEN AT DISASSEMBLY. (K) 1 L 7 2 3O 3 O 3A16 E5CE 20081023 2008 10 23 2008FA0000694 4 20080911 G 6122 B20429 SPRING DRIVE MCAULY CONT O520 IO520* 17032 SO GOVERNOR BROKEN B LU4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 CGFLM 790221 SPRING DRIVE DISCOVERED BROKEN AT DISASSEMBLY. (K) 3 O E5CE 20081023 EA 2008 10 23 2008FA0000695 1 20080909 G 6120 B3476A2 ROD HARTZL DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL BETA SYSTEM BROKEN B LU4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 V2LFC BUA26256 BETA ROD CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALF UNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081023 EA 2008 10 23 2008FA0000696 1 20080909 G 6120 B30012 BETA RING DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL PROPELLER BROKEN B LU4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 V2LFC BUA26256 BETA RING CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MAL FUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR. (K) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081023 SO 2008 10 23 2008FA0000697 2 20080930 G 7414 SPRING CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO IMPULSE COUPLING BROKEN D O OTHER O OTHER TX TAXI/GRND HDL 1 GL 21 622CP 4 D08BA175 1932 360623 DURING MAGNETO CHECK ON GROUND RUN-UP 30 SEPT 2008, THE PILOT REPORTED THAT WHEN THE LT MAG WAS SELECTED THE ENGINE WOUL D NOT STAY RUNNING. ACFT WAS BROUGHT IN FOR MAINT AND IT WAS DISCOVERED THAT THE MAGNETO IMPULSE COUPLING SPRING WAS BRO KEN IN THE LEFT MAGNETO. THE LT MAGNETO WAS REMOVED AND REPLACED, GROUND RUN CHECK WAS GOOD, AND ACFT WAS RETURNED TO SE RVICE. (K) 1 L 7 1 3O 3 O NT A00009CH E1CE 20081030 NM 2008 10 30 2008FA0000698 1 20081019 G 3510 VALVE BOEING 767 7673CB 1385187 NM OXYGEN BOTTLE OUT OF ADJUST B O OTHER W INADEQUATE Q C IN INSP/MAINT 1 NM 01 592HA 33468 AIR NEW ZEALAND FAA REPAIR STATION ANZY 188C AKL - FLT NZ707 - DURING PRE-FLIGHT, TECH CREW NOTED THAT CREW OXY PRESSUR E ON EICAS DROPPED FROM 1600 PSI TO APPROX 300 PSI WHILE DEPRESSING THE TEST BUTTONS ON THE CREW OXY MODULES. ENGINEER CALLED ON HEADSET TO INVESTIGATE. ENGINEER CHECKED CREW BOTTLE AND FOUND THAT THE VALVE WAS APPROX ONLY 1/3 OPEN AND NO T SAFETY WIRED. BOTTLE VALVE SUBSEQUENTLY FULLY OPENED AND COPPER WIRED IN POSITION AS REQUIRED. CREW OXYGEN CHECKS NO W NORMAL WITH NO NOTICEABLE DROP IN PRESSURE ON EICAS. AIR NEW ZEALAND MAINTENANCE QUALITY RISK AND SAFETY (MQRS) SAFET Y INVESTIGATION GROUP HAS RAISED THE FOLLOWING AIR NEW ZEALAND INVESTIGATION (08/SI/135). 2 L 7 2 4F RT A1NM 20081027 CE 2008 10 27 2008FA0000699 1 20081010 G 5313 50440012319 STRINGER BEECH 90 C90 1152913 CE PWA PT6 PT6* 52043 EA FS 298 CRACKED D O OTHER O OTHER NR NOT REPORTED 1 CE 01 902XP 5781 LJ1136 REAR PRESSURE BULKHEAD, FS 298.00, ON RT SIDE. STRINGER NR 9 WAS FOUND CRACKED ON THE AFT SIDE OF THE REAR PRESSURE BULK HEAD AT THE POINT WHERE THE ZEE STIFFENER IS ATTACHED TO THE STRINGER WITH (6) RIVETS. (K) 1 L 7 2 3T 3 T 3A20 E2NE 20081027 NE 2008 10 27 2008FA0000700 3 20080718 G 6111 6607132886 BLADE ROTOL R389 R3894123F25 NE PROPELLER CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 37586 DR6176385 PROP RECEIVED FOR ROUTINE O/H. AFTER PROP WAS DISASSEMBLED IT WAS NOTED THAT BLADE NR 2, SN 1141 HAD A CRACKED ROOT END OUTER SLEEVE. BLADE IS REJECTED FROM FURTHER SERVICE. SB SF 340.60.A106 ADDRESSES THIS. (K) 6 C P30NE 20081027 2008 10 27 2008FA0000701 4 20081006 G 2210 4006719910 SERVO MTSBSI MU2 MU2B60 5780460 CE GARRTT TPE331 TPE331* 01514 WP YAW DAMPENER CONTAMINATED D K NONE O OTHER IN INSP/MAINT 1 NM 07 544CB 46 1536SA 8/11/08 INSTALLED YAW DAMPENER. 10/06/08 - CUSTOMER COMPLAINT OF INDUCED YAW WHEN ENGAGING AUTO PILOT. REMOVED YAW DAMP ENER AND FOUND UNIT CONTAMINATED WITH WATER. UNIT IS MOUNTED WITH DRIVE SHAFT UP AND WITH NO DRAIN, THIS PROVIDES FOR WA TER TO BE TRAPPED IN THE SERVO. RECOMMEND SEALING THE UNIT BETTER OR PROVIDING DRAINS FOR UNIT. (K) 1 H 7 2 3T 3 T RT A10SW E2WE 20081027 SO 2008 10 27 2008FA0000702 1 20081016 G 3210 6569100 TORQUE LINK PIPER J3 J3C65 7100510 SO MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 23 70127 5440 17106 CRACK FOUND DURING 100 HR INSPECTION. LAST INSPECTION FOR AD 72-08-06. DONE AT 5214.07 HR, PRESENT TIME 5440.53 (225.76 HR). SUGGEST PART BE LIFE LIMITED. THIS IS 2ND SET CRACK. THIS FLEET WITH OVER 5000 HR. TIME IN SERVICE. (K) 1 H 7 1 3O A691 20081027 CE 2008 10 27 2008FA0000703 1 20081002 G 2730 NAS428420 BOLT BEECH 200 200BEECH 1152920 CE ELEVATOR CONTROL OUT OF ADJUST B ML2R K NONE O OTHER IN INSP/MAINT 1 GL 11 124EK BB1993 DURING A PHASE 1-4 INSPECTION ON AC. BOLT FOR ELEVATOR CONTROL SYS. WAS FOUND TO BE ADJUSTED ALL THE WAY DOWN AND WAS NO T PROVIDING A STOP FOR THE BALLAST. IN THIS CONDITION, THE POSSIBILITY EXISTS FOR THE INTERCONNECT LINK BETWEEN THE BAL LAST WEIGHT BELLCRANK AND THE CONTROL COLUMN BRACKET TO TRAVEL PAST AN OVERCENTER CONFIGURATION AND MAY PREVENT PROPER C ONTROL OF THE ELEVATOR SYSTEM IF THE ELEVATOR PRIMARY OR SECONDARY STOPS FAIL OR ARE ADJUSTED INCORRECTLY. THE PHASE IN SPECTION BEING CONDUCTED IS THE INITIAL INSPECTION ON THE AC, AND LOG RESEARCH DID NOT REVEAL ANY PRIOR MAINTENANCE ON T HE ELEVATOR CONTROL SYSTEM RIGGING. (K) 1 L 7 2 4T A24CE 20081030 NM 2008 10 30 2008FA0000704 1 20081024 G 5711 9252502 SPAR CAP LKHEED P3A P3A 5260103 NM RT WING FRACTURED B K NONE K FLUID LOSS IN INSP/MAINT 1 WP 00 921AU 16842 1465 151385 DURING INSPECTION TO DETERMINE THE SOURCE OF A FUEL LEAK A FRACTURE WAS FOUND IN THE LOWER FORWARD RIGHT SPAR CAP AT WIN G STA 75 EMANATING FROM NUT PLATE FASTENER HOLE ON FORWARD FLANGE TO THE EDGE OF FLANGE MEMBER WITH SLIGHT ENCROACHMENT AFT FROM SAME HOLE, APPROX .125 INCH. SECOND FRACTURE SHOWS AT WS 72.2 FROM FORWARD FLANGE NUT PLATE HOLE INTO THE VERT ICAL FLANGE SEVERING THE FLANGE. A THIRD FRACTURE WAS APPRECIATED AT WS 71R IN THE SPAR WEB. THE CRACK APPEARS TO STAR T AT A HI-LOK PIN HOLE AT THE LOWER CAP AND PROPAGATES APPROXIMATELY THREE INCHES VERTICAL WITH SOME INBOARD TRACK. 2 L 7 4 4T RT A32NM 20081027 CE 2008 10 27 2008FA0000705 1 20080929 G 2910 6317003136 LINE CESSNA 525 525 2076601 CE HYDRAULIC SYS RUPTURED B EWCR O OTHER O OTHER NR NOT REPORTED 1 EA 39 44CK 5250401 RUPTURE OF TUBE AT SIDE WHERE BENDING DIES LEFT MARKING, BOTH ABOVE AND BELOW OPENING. AFTER TAKEOFF, LOW FLUID AND PRES SURE WARNING LIGHTS CAME ON AND ACFT RETURNED TO DEPARTURE. ACFT WAS TURNED OVER TO REPAIR STATION. LEAK WAS LOCATED AN D LINE REPLACED ALONG WITH BOTH HYDRAULIC PUMPS. (K) 1 L 7 2 4F RT A1WI 20081027 SO 2008 10 27 2008FA0000706 1 20081014 G 3246 16109302 WHEEL PIPER PA32 PA32R300 7103213 SO MLG CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 15 1228H 32R7780146 WHEEL FOUND CRACKED, INNER HALF APPROX 2 INCH LONG. (K) 1 L 7 1 3O A3SO 20081031 SO 2008 10 31 2008FA0000707 1 20081026 G 5712 9560401 SPAR CAP PIPER PA34 PA34200 7103405 SO RT WING CORRODED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 05 14258 4695 347350180 DURING ANNUAL INSPECTION, SEVERE INNER GRANULAR CORROSION WAS FOUND IN THE RIGHT WING, MAIN UPPER SPAR CAP AT THE AFT PO RTION OF THE T-CAP, IN THE VICINITY OF THE WHEEL WELL IN PARTICULAR THE LOCATION OF WHEEL SPIN OFF. DURING TIME, CAUSED DAMAGE TO THE POINT OF SPAR REPLACEMENT. 1 L 7 2 3O A7SO 20081028 CE 2008 10 28 2008FA0000708 1 20080924 G 3010 LINE CESSNA 208 208B 2073701 CE DE-ICE SYSTEM FROZEN D K NONE N L FALSE WARNING NO TEST IN INSP/MAINT 1 SO 03 DURING MX OPERATION OF DE-ICE BOOTS MINUTES AFTER ACFT RETURNED FROM FLT, OPERATION OF THE DEICE BOOTS PRODUCED NORMAL C OCKPIT INDICATION (GREEN PRESSURE LIGHT). NOTICED, THOUGH, THAT THE RT WING DEICE BOOTS DID NOT INFLATE DESPITE THE INFL ATION INDICATION IN THE COCKPIT. FROZEN WATER WAS FOUND AT A BEND IN THE DEICE AIR SUPPLY DUCTING IN THE RT WING ROOT. T HIS ALLOWED PRESSURE TO BUILD UP AND ACTIVATE THE PRESSURE SWITCH, PRODUCING A NORMAL INDICATION IN THE COCKPIT DESPITE THE BOOTS NOT ACTUALLY INFLATING. IF THIS WERE TO OCCUR IN THE TAIL, IT WOULD BE EVEN MORE UNDETECTABLE. RECOMMEND A CAL IBRATED LEAK IN PNEUMATIC SUPPLY DUCTING IN THE FUSELAGE/ WING TO PREVENT THE ACCUMULATION OF WATER. (K) 1 H 7 1 3T A37CE 20081028 SO 2008 10 28 2008FA0000709 1 20081014 G 3246 16109302 WHEEL PIPER PA32 PA32R300 7103213 SO LYC O540 TIO540* 41532 EA MLG CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 15 1228H 32R7780146 CLEVELAND WHEEL, HOLE FOUND CRACKED, INNER HALF APPROX 2 INCHES LONG. (K) 1 L 7 1 3O 3 O A3SO E14EA 20081104 CE 2008 11 4 2008FA0000710 1 20081027 G 6120 TUBE BEECH 95 95B55 1152729 CE NACELLE CHAFED D K NONE O OTHER IN INSP/MAINT 1 CE 03 527T 4985 TC576 ALUMINUM TUBING TO PROP GOVERNOR FOUND CHAFED DUE TO TIE RAP RUBBING TUBE. FABRICATED NEW TUBE, INSTALLED AND LEAK CHEC KED. 1 L 7 2 3O RT 3A16 20081104 GL 2008 11 4 2008FA0000721 2 20081027 G 7260 KHU17D31 RELAY CESSNA 206 U206G 2073356 CE ALLSN 250C 250C20 03013 GL HARTZL HCC3Y HCC3YN GL ENGINE BAY INTERMITTENT B C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 GL 19 891LL 4565 U20606937 CAE290031 GC91A THE PILOT REPORTED THAT AFTER TURNING ON TO THE RUNWAY FOR TAKEOFF AND APPLYING POWER THE ENGINE CHIP LIGHT CAME ON AND STAYED ON. POWER WAS REDUCED, AND TOWER APPROVED A RETURN BACK TO THE RAMP. THE AIRCRAFT NEVER APPROACED TAKEOFF SPEED . THE AIRCRAFT WAS BROUGHT IN AND INSPECTED, UPON APPLYING ELEC POWER TO AIRCRAFT THE CHIP LIGHT WAS NO LONGER ON. ALL THREE CHIP LIGHTS WERE INSPECTED AND FOUND NO DISCREPANCIES. SUSPECTED WIRING PROBLEM OR RELAY PROBLEM. REPLACED RELA Y FOR THE CHIP DETECTORS. 1 H 7 1 3O 3 U A4CE E4CE 5 C P25EA 20081104 EA 2008 11 4 2008FA0000722 2 20081029 G 7322 105217 CARBURETOR CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL ENGINE DAMAGED D O OTHER E VIBRATION/BUFFET TO TAKEOFF 1 NM 03 1401E 247 247 17270986 L291176T WA44044 PILOT WAS MAKING 3RD TOUCH AND GO, ON CLIMBOUT ENGINE STARTED VIBRATING EXCESSIVELY, POWER WAS REDUCED AT PATTERN ALTITU DE, MIXTURE ADJUSTED, SWITCHED MAGNETO'S FROM R TO L WITH NO CHANGE IN THE VIBRATION. AIRCRAFT LANDED AND SUBSEQUENT OP ERATION WHILE TAXIING TO PARKING NO VIBRATION WAS ENCOUNTERED. A RUN UP WAS ACCOMPLISHED AND AT ENGINE OPERATION ABOVE 1800 RPM THE VIBRATION REOCCURRED. MAINTENANCE DISCOVERED THE PROBLEM TO BE THE CARBURETOR ACCELERATION DISCHARGE TUBE WAS MISSING AND HAD BEEN INGESTED BY THE ENGINE. THE ENGINE AND CARBURETOR HAD 246.9 HOURS SINCE OVERHAUL BY TEXTRON LYC OMING. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20081104 NM 2008 11 4 2008FA0000723 1 20081029 G 5711 9252511 SPAR CAP LKHEED P3A P3A 5260103 NM RT WING CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 921A 16842 1465 151385 DURING FURTHER EVALUATION FOLLOWING PREVIOUSLY REPORTED DAMAGE A SECOND CRACK WAS FOUND ON THE FORWARD LOWER CAP AT BUTT LINE 56R. THE CRACK WAS VISUALLY IDENTIFIED AND CONFIRMED WITH EDDY-CURRENT SURFACE SCAN. 2 L 7 4 4T RT A32NM 20081104 NM 2008 11 4 2008FA0000724 1 20081029 G 5711 9252502 SPAR CAP LKHEED P3A P3A 5260103 NM RT WING CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 921A 16842 1465 151385 DURING FURTHER EVALUATION FOLLOWING PREVIOUSLY REPORTED DAMAGE A TERTIARY FRACTURE WAS FOUND ON THE FORWARD SPAR CAP, HO RIZONTAL FLANGE, WING STA 143.5. THE FRACTURE WAS VISUALLY IDENTIFIED AND CONFIRMED WITH EDDY CURRENT. AN INTERNAL VIS UAL EXAMINATION IDENTIFIED THE AFT HORIZONTAL FLANGE AND VERTICAL FLANGE HAD ALSO BEEN FRACTURED. THE AFT FLANGE IS FRA CTURED APPROXIMATELY .750 INCHES, PROPAGATING AFT TOWARD THE FLANGE END. THE VERTICAL FLANGE FRACTURE PROPAGATED THROUG H THE FILLET RADIUS UP TO THE FIRST HORIZONTAL ROW OF HI-LOK PINS. THE FRACTURE LENGTH IS APPROXIMATELY ONE INCH. FRAC TURES WERE CONFIRMED WITH EDDY-CURRENT SURFACE SCAN. 2 L 7 4 4T RT A32NM 20081104 SO 2008 11 4 2008FA0000725 1 20081029 G 5753 6232800162328000 RIB PIPER PA28 PA28180 7102808 SO TE FLAP CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 99 DURING ANNUAL INSPECTION FOUND ALL FLAPS, LEADING EDGE RIBS WERE SEVERELY CORRODED. DETECTION METHOD WAS TO TAKE THE FO REFINGER AND THUMB AND SQUEEZE LEADING EDGE AT THE RIB, GOT A CRUNCHING FEEL AND SOUND. 1 L 7 1 3O 2A13 20081104 CE 2008 11 4 2008FA0000726 1 20081016 G 2120 66151007 TUBE CESSNA 560 560XL 2076702 CE AC BAY CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 27 2331 5333 ENVIRONMENTAL CONTROL UNIT ASPIRATOR AIR LINE THAT RUNS FROM SECONDARY HEAT EXCHANGER TO ASPIRATOR FOUND BROKEN IN TWO J UST DOWNSTREAM OF SECONDARY HEAT EXCHANGER ELBOW FITTING. CESSNA P/N 6615100-7 2 L 7 2 4F RT A22CE 20081104 2008 11 4 2008FA0000727 4 20081029 G 2210 AUTOPILOT SYS ECLIPS EA500 ECLIPSEEA500 3350000 SW COCKPIT UNKNOWN C A UNSCHED LANDING G MULTIPLE FAILURE CR CRUISE 1 SW 99 678P 191 FLIGHT FROM SDL TO TUL, DIVERT TO ABQ. AUTOPILOT DISENGAGED VIOLENTLY AT 410 AND YD OFF. REFER TO QRH RESET CB. AUTOP ILOT BACK ON AT 390. 40 SECONDS LATER, AUTOPILOT AND YD DISENGAGED. UNABLE TO RESET CB. FL 370 AUTOPILOT BACK ON AND 3 0 SECONDS LATER DISENGAGED AGAIN. REMAINED OFF THE REST OF THE FLIGHT. YD RECOVERED AT 280. AIRSPEED DISAGREE AT 370. REFERRED TO QRH. ADC SOURCE USED AND STILL GIVING AIRSPEED DISAGREE. DISAPPEARED AT FL250 AND 265 KNOTS. PILOT ELEC TED TO DIVERT TO ABQ. AIRCRAFT IS BEING WORKED ON AT FACTORY SERVICE CENTER. UNKNOWN CAUSE AT THIS TIME. 1 L 7 2 4J RT A00002AC 20081031 EU 2008 10 31 2008FA0000729 1 20080930 G 2120 UNKNOWN SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE CABIN ODOR B QMLR A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 NM 03 106LN 3251 SHORTLY AFTER TAKEOFF, PERSONNEL ONBOARD REPORTED A BURNING ODOR TO THE PILOT. ABORTED FLT AND RETURNED TO HELIPAD TO IN VESTIGATE. MECH PERFORMED AN INSPECTION OF THE AIRFRAME, ENGINE, WIRING, HOSES AND THE BELTS OF ALL COMPONENTS. NO DEFE CTS OR THE SOURCE OF A BURNING ODOR WAS FOUND. SUBSEQUENT CHECK FLIGHT WAS PERFORMED BY THE PILOT & MECHANIC TO INVESTIG ATE FOR BURNING ODOR, NONE FOUND. THE ACFT WAS RETURNED TO SERVICE. (K) 1 G 7 1 3U 3 U H9EU E00054EN 20081031 NE 2008 10 31 2008FA0000730 2 20080903 G 7321 2523631 BELLOWS PWA PT6 PT6A34AG 52053 NE FCU DAMAGED B IG0R K NONE L NO TEST IN INSP/MAINT 1 NM 03 B32178 PCEPH0028 FCU (PN 32447866-6, SN B32178) BENCH TESTED AND FOUND TO BE UNSERVICEABLE DUE TO BREACHED BELLOWS, (PN 2523631, SN 8011) . (K) 4 T E4EA 20081104 CE 2008 11 4 2008FA0000731 1 20081030 G 3210 244110010 PIVOT ASSY CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL LT MLG SHEARED B A UNSCHED LANDING J WARNING INDICATION LD LANDING 1 GL 00 5319V 2532 172RG0505 L3678636E 799482 THE LEFT MAIN LANDING GEAR PIVOT ASSY SHEARED IN TWO NEAR THE ACTUATOR END. THE SPLICED SECTION WHERE THE DRIVE GEAR IS INSTALLED SEPARATED. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 20081104 CE 2008 11 4 2008FA0000732 1 20081016 G 2120 66151007 TUBE CESSNA 560 560XL 2076702 CE AC BAY CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 27 3 2242 5341 ENVIRONMENTAL CONTROL UNIT ASPIRATOR AIR LINE THAT RUNS FROM SECONDARY HEAT EXCHANGER TO ASPIRATOR FOUND BROKEN IN TWO, JUST DOWNSTREAM OF SECONDARY HEAT EXCHANGER ELBOW FITTING. CESSNA P/N 6615100-7 2 L 7 2 4F RT A22CE 20081104 SW 2008 11 4 2008FA0000733 1 20081030 G 3233 B10006 COUPLING DUKES MOONEY M20 M20E 5870212 SW LANDING GEAR FAILED G O OTHER O OTHER LD LANDING 1 WP 09 204WF 3483 210021 DURING APPROACH FOR LANDING, THE PILOT WAS UNABLE TO GET THE LANDING GEAR TO EXTEND, EITHER NORMALLY OR USING THE EMERGE NCY GEAR EXTENSION SYSTEM. A GEAR-UP LANDING WAS ACCOMPLISHED WITH ONLY MINOR DAMAGE AND NO INJURIES. SUBSEQUENT INVES TIGATION DETERMINED THAT THE COUPLING (P/N B100-06) BETWEEN THE LANDING GEAR MOTOR TRANSMISSION AND THE DRIVE ACTUATOR H AD BROKEN. THE COUPLING HAS NO REPLACEMENT REQUIREMENTS, BUT IS RECOGNIZED IN MOONEY SERVICE INSTRUCTION M20-89 AS A PA RT THAT COULD FAIL DUE TO AGE HARDENING AND DETERIORATION. THE AIRCRAFT OWNER WAS NOT AWARE OF THIS CONDITION. 1 L 7 1 3O 2A3 20081104 EA 2008 11 4 2008FA0000735 2 20080925 G 7414 M3828 GEAR SLICK CESSNA 182 182T 2072703 CE LYC O540 IO540AB1A5 EA MAGNETO DAMAGED B Z08R K NONE O OTHER IN INSP/MAINT 1 CE 07 658PW 08080703 18282098 L03291348E WHILE PERFORMING SB03-08, FOUND THE DISTRIBUTOR GEAR DRIVE GEAR WEARING PREMATURELY AND CAUSING GEAR DUST INSIDE MAGNETO . GEAR MATERIAL WAS COMING OFF CAUSING IT TO COLLECT INSIDE DISTRIBUTOR CAP. ALSO, FOUND EXCESSIVE AMOUNT OF OIL INSIDE MAGNETO. REPLACED MAGNETO. (K) 1 H 7 1 3O 3 O NT 3A13 1E4 20081104 2008 11 4 2008FA0000737 2 20080905 G 7200 ENGINE AMD FALC20 FALCON200 2730150 EU FOD B UO2R A UNSCHED LANDING C J F.O.D. WARNING INDICATION CL CLIMB 1 GL 19 69EC 498 AFTER TAKEOFF, OVERSPEED WARNING LIGHT ILLUMINATED. RPM REDUCTION USING PROP GOVERNOR CONTROL NOT SUCCESSFUL, USED THROT TLE CONTROL TO REDUCE ENGINE RPM. LANDED WITHOUT INCIDENT. REPAIR STATION INSPECTED AND DUPLICATED PROBLEM ON ENGINE GRO UND RUN. ALL VISUAL INSP REVEALED NO DISCREPANCIES EXCEPT AN EXTRUSION OF SMALL AREA TO THE TOP OF CRANKCASE ABOVE NR 2 CYLINDER (NO OIL LEAK NOTICED). BECAUSE OF THIS ABNORMALITY, WE REMOVED THE OIL FILTER AND SUCTION SCREEN SHOWED SUBSTAN TIAL METAL SHAVING AND SMALL PIECES OF METAL AND (2) SMALL SILVER COLOR BALLS (SUSPECT BALL BEARING OF SOME SORT). THE E NGINE WAS REMOVED FOR TEAR DOWN INSP AND REPAIR. ENGINE TEAR DOWN REVEALED DESTRUCTION OF BOTH INTAKE AND EXHAUST LIFTER 2 L 7 2 4F RT A7EU 20081104 2008 11 4 2008FA0000738 2 20080913 G 8500 ENGINE AMD FALC20 FALCON200 2730150 EU MAKING METAL B UO2R A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 GL 19 69EC 498 AFTER TAKEOFF, OVERSPEED WARNING LIGHT ILLUMINATED. RPM REDUCTION USING PROP GOVERNOR CONTROL NOT SUCCESSFUL & USED THRO TTLE CONTROL TO REDUCE ENGINE RPM. LANDED WITHOUT INCIDENT. REPAIR STATION INSPECTED & DUPLICATED PROBLEM ON GROUND RUN. NO DISCREPANCIES EXCEPT AN EXTRUSION OF SMALL AREA TO THE TOP OF CRANKCASE ABOVE NR 2 CYLINDER (NO OIL LEAK NOTICED). B ECAUSE OF THIS ABNORMALITY, REMOVED OIL FILTER & SUCTION SCREEN SHOWED SUBSTANTIAL METAL SHAVING & SMALL PIECES OF METAL AND 2 SMALL SILVER COLORED BALLS (SUSPECT BALL BEARING OF SOME SORT). ENGINE REMOVED FOR TEAR DOWN INSP & REPAIR. ENGIN E TEAR DOWN REVEALED DESTRUCTION OF BOTH INTAKE & EXHAUST LIFTER BODIES OF NR 1 CYLINDER & EXTENSIVE DAMAGE OF ENGINE. A 2 L 7 2 4F RT A7EU 20081113 CE 2008 11 13 2008FA0000739 1 20081103 G 3710 ADAPTER CESSNA 172 172M 2072418 CE VACUUM SYS DAMAGED B K NONE O OTHER CR CRUISE 1 SW 99 30830 5902 17264138 AIRCRAFT HAD A FRESHLY OVERHAULED ENGINE INSTALLED AND WAS MAKING ITS FIRST FLIGHT. DURING CRUISE, IN VFR CONDITIONS, T HE PILOT NOTED A OVERHEATING TYPE OF ODOR AND THEN NOTED A MOMENTARY SMALL REDUCTION IN POWER AFTER WHICH POWER RETURNED TO NORMAL. THE PILOT THEN NOTICED THAT BOTH GYROS BEGAN PROCESSING AND THE VACUUM GAUGE READ ZERO. AIRCRAFT RETURNED WITHOUT FURTHER INCIDENT. INVESTIGATION BY MAINTENANCE FOUND THAT THE VACUUM PUMP ADAPTER WAS DISCOLORED. REMOVAL OF V ACUUM PUMP FOUND THAT THE SPLINED SHAFT HAD MELTED AWAY AND ITS PARTICLES WERE CAUGHT BETWEEN PUMP AND ADAPTER. MAINTEN ANCE NOTED THAT THE OIL DISTRIBUTION HOLES BETWEEN THE ADAPTER AND THE ENGINE WERE ALIGNED PROPERLY. NO IMMEDIATE CAUSE 1 H 7 1 3O NT 3A12 20081106 EA 2008 11 6 2008FA0000740 2 20081001 G 7414 AB382585 CONTACT ROBSIN R22 R22BETA 7640110 NM LYC O360 O360J2A 41514 EA MAGNETO DAMAGED D O OTHER O OTHER NR NOT REPORTED 1 NM 09 7087J 2873 CONTACT ASSY, AS A NEW ASSY OPENS BEYOND THE MAXIMUM .024 INCH. THIS IS A REOCCURRING PROBLEM WITH BOTH THE LT AND THE R T CONTACT ASSEMBLIES. CIRCUMSTANCES ARE WHEN THE POINTS ARE REPLACED. (K) 1 G 7 1 3O 3 O H10WE E286 20081106 EU 2008 11 6 2008FA0000741 1 20081026 G 6322 MS210436 NUT HUGHES 369 369FF 4470709 EU ALLSN 250C 250C30 03013 GL BLOWER BACKED OUT D K NONE O OTHER IN INSP/MAINT 1 WP 19 5185G 0009F OIL COOLER BLOWER DRIVEN PULLEY RETAINING NUT IS BACKING OFF OF SHAFT DURING NORMAL US. NUT IS A STAINLESS STEEL, SILVER PLATED, ALL METAL SELF LOCKING TYPE NUT. THIS WAS THE THIRD OCCURRENCE OF THIS TYPE FOR OUR UNIT AND WE ARE ALSO CAUSE S THE SHAFT BEARING TO GO BAD WHICH DESTROYS THE OIL COOLER BELT. THIS LEADS TO EXTREME ENGINE OIL AND MAIN TRANSMISSIO N OIL TEMPERATURES. AFTER INVESTIGATING PNS WE FOUND THAT MFG HAS BEEN USING THIS TYPE OF NUT FOR A LONG TIME AND WE ARE UNSURE IF THE NUTS CURRENTLY BEING PRODUCED ARE SUBSTANDARD. 1 G 7 1 3U 3 U H3WE E1GL 20081106 EA 2008 11 6 2008FA0000742 2 20080925 G 7414 4371 MAGNETO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE CONTAMINATED B Z08R K NONE O OTHER IN INSP/MAINT 1 CE 07 452SM 5 172S10528 L3343151E DURING INSPECTION FOR SB 03-08 THE FIRST 5 HOUR INSPECTION FOUND OIL ON THE COIL TAB ON BOTH MAGNETOS AND CAM WEARING ON BOTH MAGNETOS FOR THE AMOUNT HOURS ON MAGNETOS. ALSO, FOUND EXCESSIVE AMOUNT OF OIL INSIDE DISTRIBUTOR FOR THE AMOUNT O F HOURS ON MAGNETOS. THIS IS CAUSING THE CARBON DUST TO COLLECT AND BUILDUP INSIDE MAGNETOS. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 20081107 SW 2008 11 7 2008FA0000743 1 20080929 G 5541 442283 SPAR GULSTM 112 114 7630314 SW RUDDER CRACKED D O OTHER O OTHER NR NOT REPORTED 1 EA 65 4945W 603 14267 SPAR IS CRACKED AND BROKEN OUT AT UPPER HINGE ATTACH POINT. THIS SPAR WAS REPLACED WITH NEW 1-1-99 FOR SAME CONDITION. THIS CONDITION WAS FOUND BY CLOSE EXAMINATION OF AREA DURING ANNUAL INSPECTION. WE ARE IN RECEIPT OF INFORMATION OF SAM E FAILED CONDITION ON SN 14408. RECOMMEND THAT DOUBLER BE INSTALLED TO STRENGTHEN SPAR IN THIS AREA. (K) 1 L 7 1 3O A12SO 20081110 CE 2008 11 10 2008FA0000745 1 20080922 G 2820 AN8156D CONNECTOR RAYTHN B300 B300RAYTHEON 7150007 CE RT AUX TANK DISCONNECTED C O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 SO 15 102FL FL263 UPON ENGINE RUN-UP, OBSERVED FUEL DUMPING BUT RT HEATED FUEL VENT PROBE. UPON INVESTIGATION FOUND FUEL LINE DISCONNECTED INSIDE RT AUX TANK. FUEL LINE, PN 101-920000-9 FROM MOTIVE FLOW VALVE TO JET PUMP DISCONNECTED FROM UNION PN AN815-6D. FUEL LINE PN 101-920000-19, FOUND LOOSE ON UNION PN AN815-6D. FUEL LINES FROM JET PUMP TO NACELLE TANK PN 101-920000-57 AND 101-920000-43 FOUND LOOSE ON UNION PN AN815-8D. RECONNECTED AND TIGHTENED ALL LINES AND FITTINGS INSIDE RT FUEL AUX TANK. INSPECTION OF LT FUEL AUX TANK FOUND ALL LINES AND FITTINGS OK. (K) 2 L 7 2 4T RT A24CE 20081107 NE 2008 11 7 2008FA0000746 2 20081015 G 7314 PUMP BOEING 727 727200 138407E NM PWA JT8 JT8D217C 52053 NE FUEL SYS MALFUNCTIONED A I5PA A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 WP 13 705AA 22462 726206U CRUISE NR 1 ENG STARTED TO SPOOL DOWN OTHER PARAMETERS ARE NORMAL, PERFORMED IN-FLIGHT START CHECKLIST SEVERAL TIMES INC LUDING RESETTING SWITCHES, NO LIGHT OFF. ACFT DIVERTED AND THE CREW PERFORMED ENG INSPECTION AND START ON NR 1 ENG HIGH IGNITION SYS, ENGINE STARTED OK IN GROUND. START IGNITION NR 1 FROM HIGH-ENERGY FAIL IN FLIGHT POSITION. DEFERRED NR 1 E NG IGNITION IAW MEL 74-1 AND 705 CONTINUED SERVICE. MAINT REMOVED AND REPLACED NR 1 ENG FUEL PUMP IAW MM 73-11-1, PURGE FUEL SYSTEM, PS4, PT7, AND P AND D VALVE CHECK FOR MOISTURE. PERFORMED FULL POWER ENGINE RUN AND LEAK CHECK SYSTEM OPER ATIONAL CHECK, OK. (K) 2 L 7 3 4F 4 F RT A3WE E9NE 20081121 CE 2008 11 21 2008FA0000747 1 20081106 G 3520 C3512000205 OXYGEN MASK CESSNA 500 550 2076604 CE CABIN TORN B K NONE O OTHER IN INSP/MAINT 1 SW 99 43SA 2500 5500086 THREE OF THE DROP DOWN PASSENGER OXYGEN MASKS P/N C351-2000-205 OR CESSNA P/N 17504-61 WERE FOUND WITH TEARS IN THE FACE CUSHION NEXT TO THE INNER MASK HOUSING IN THE SAME AREA DESCRIBED IN AD 99-08-21. HOWEVER THE ELASTOMERIC CURE DATES O N THESE MASKS ARE THE 3RD QUARTER OF 1999, THE AD ONLY ADDRESSES MASKS WITH A CURE DATE FROM 3RD QUARTER 1993 TO 1ST QUA RTER 1997. THESE TEARS COULD LEAD TO LEAKAGE AND POSSIBLE INSUFFICIENT OXYGEN DELIVERY AS DESCRIBED IN THE ORIGINAL A/D . 1 L 7 2 4F A22CE 20081110 2008 11 10 2008FA0000748 1 20081101 G 2810 CB959 FUEL TANK DAMAGED B RYHR O OTHER O OTHER NR NOT REPORTED 1 NM 03 FUEL TANKS WERE FOUND TO HAVE SIGNIFICANT LEAKS IN AN AREA NOT CLOSE TO ANY SEAMS, WELDS, OR BOSSES. THERE WERE NO VISIB LE DENTS, DINGS, SCRATCHES, GOUGES OR OTHER DAMAGE IN THE AREAS OF THE LEAKS. THE LEAK HOLES WERE MUCH SMALLER THAN THE DIAMETER OF A PIN AND WERE NOT VISUALLY DETECTABLE. TANKS WERE TAGGED UNAIRWORTHY. FUEL TANKS WERE ALSO TAGGED UNAIRWOR THY PENDING FURTHER TESTINGS AS A PRECAUTION. (K) 20081128 GL 2008 11 28 2008FA0000750 2 20081106 G 7200 44904 STIFFENER WILINT WILINT FJ44 FJ443A 66006 GL LP TURBINE SEPARATED B K NONE O OTHER IN INSP/MAINT 1 GL 23 1858 AU00307 141224 WHILE UNDERGOING A CHECK 3 MAINT INSP DURING EARLY NOVEMBER 2008, THE STIFFENING RING ON THE 1ST LOW PRESSURE TURBINE NO ZZLE ON ENGINE WAS FOUND SEPARATED AND TRAPPED BETWEEN THE 1ST LP TURBINE NOZZLE AND THE HIGH PRESSURE TURBINE NOZZLE. NO SECONDARY DAMAGE WAS NOTED. PROBABLE CAUSE IS A SUSPECT MANUFACTURING OPERATION. 4 F E3GL 20081126 EA 2008 11 26 2008FA0000751 2 20081024 G 7414 SS1001 BOOSTER SLICK HUGHES 269 269C1 8059504 SW LYC O360 HIO360G1A 41898 EA ZONE 100 EXPLODED D E H ENGINE SHUTDOWN DEACTIVATE SYST/CIRCUITS B A SMOKE/FUMES/ODORS/SPARKS FLAME/FIRE TO TAKEOFF 1 SW 41 2014T 701 50 0313 L3373151A START MAGNETO, START BOOSTER BOX PN SS1001 BLEW THE TOP PORTION APART. IT CAUGHT ON FIRE AND SMOKE WENT EVERYWHERE. INSP ECTED HELICOPTER WHEN SMOKE CLEARED AND COULD NOT FIND THE PROBLEM. TURNED OFF THE FUEL AND BUMPED THE STARTER AND FOUND THE PROBLEM TO BE THE START BOX. WITHIN JUST BUMPING THE STARTER , HELICOPTER WAS COVERED IN SMOKE. I REMOVED AND REPLA CED THE BOX AND INSPECTED ALL THE WIRING AND ALL IS WORKING JUST FINE NOW. BIGGEST PROBLEM I SEE IS THAT THE SLICK START BOX SETS TO CLOSE TO THE FUEL MAIN LINE, WITCH COULD OF LED TO A COMPLETE LOSS OF AIRCRAFT. 1 G 7 1 3O 3 O O 4H12 1E10 20081125 CE 2008 11 25 2008FA0000752 1 20081103 G 3320 CLE23602 LIGHT CESSNA 560 560XL 2076702 CE CABIN BURNED OUT C K NONE O OTHER IN INSP/MAINT 1 SO 13 669TT 714 5684 DURING POSTFLIGHT FOUND CABIN (LT) UPWASH, AND (RT) DOWNWASH LED LIGHT ELEMENTS INOP. INTIALLY TROUBLESHOOTING FOUND CIR CUIT BREAKER 140 IN THE INTERIOR DC "J" BOX OPEN. ATTEMPTED TO RESET, BREAKER WOULD OPEN IMMEDIATLY WHEN THE CABIN LIGHT SWITCH WAS ACTIVATED ON. FURTHER TROUBLESHOOTING FOUND THAT THE LT AFT CABIN UPWASH LIGHT ELEMENT SHOWED EVIDENCE OF EX CESSIVE HEAT APPROX IN THE MIDDLE OF ELEMENT. REMOVED LIGHT ELEMENT AND INSTALLED SERVICEABLE O/H ELEMENT. OPS CHECK OF SYS PERFORMED, SYS CHECKS GOOD. TECH SUPPORT SUGGESTS MOISTURE INGRESS AS THE CAUSE OF THE LIGHT ELEMENT FAILURE. DEFE CTIVE PART WAS RETURNED TO MFG CPD. 2 L 7 2 4F RT A22CE 20081125 SO 2008 11 25 2008FA0000753 2 20081107 G 7414 IMPULSE COUPLING CONT O550 IO550N 17042 SO MAGNETO INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 GL 15 502BZ 1021 D05KA054 917755 WHILE REMOVING MAGNETO FOR EXCHANGE FOUND IMPULSE COUPLING INOPERABLE. THIS IS THE SECOND LOW TIME MAGNETO OF THIS MODE L FOUND WITH A BAD IMPULSE COUPLING. 3 O E3SO 20081125 EA 2008 11 25 2008FA0000754 2 20081111 G 7414 4371 MAGNETO PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA ENGINE OUT OF POSITION D K NONE O OTHER IN INSP/MAINT 1 GL 03 9360C 90 287890401 L2454636A EXCESSIVE TIMING DRIFT. BOTH MAGS SET 25 DEGREES BTDC ON NR1 CYLINDER. NEXT FIRING ORDER (NR 3 CYLINDER) IS OFF 6 DEGR EES BETWEEN LT/RT MAG. NEXT FIRING ORDER (NR2 CYLINDER) IS NORMAL. LAST FIRING ORDER (NR4 CYLINDER) IS OFF 6 DEGREES B ETWEEN LT/RT MAGS. INITIAL SUSPECT IS CAM LOBE. CARBON BRUSH INSPECTED IAW SB3-08. BRUSH SHOWS POSSIBLE INDICATION OF (EARLY STAGE) UNDERCUT. SLIGHT BRUSH RESIDUE EVIDENCED ON BEARING BAR. 1 L 7 1 3O 3 O 2A13 E286 20081112 EU 2008 11 12 2008FA0000755 1 20080930 G 7603 JOINT PIAGIO P180 P180 6960204 EU CONTROL CABLE DAMAGED C K NONE O OTHER IN INSP/MAINT 1 SW 99 23RF 1080 RT ENGINE POWER CONTROL CABLES FREEZING AT ALTITUDE. INSPECTED CABLE AND FOUND THE STAINLESS STEEL SLEEVE DISCONNECTED A T JOINT TO FLEX SLEEVE. IT APPEARS TO BE A SILVER SOLDERED JOINT, AND SOLDER FAILED ALLOWING MOISTURE TO ENTER THE INTER NAL OF CABLE AND FREEZE WHICH COULD CAUSE LOSS OF MOTION OF THE CONTROL CABLES AND CAUSE FUEL CONTROL CABLES NOT TO ACHI EVE FULL TRAVEL, RESTRICTING ENGINE POWER. 1 H 7 2 3O RT A59EU 20081125 CE 2008 11 25 2008FA0000756 1 20081112 G 7120 051313211 MOUNT CESSNA 175 175 2072502 CE ZONE 100 CRACKED G K NONE O OTHER IN INSP/MAINT 1 GL 23 175UK 55829 DURING INSP, MECHANIC FOUND THE LT UPPER ENGINE MOUNT BRACKET, PN 0513132-11, CRACKED ALL THE WAY THROUGH. CRACK WAS AT THE OUTER RADIUS OF THE WASHER. 1 H 7 1 3O NT 3A17 20081112 SW 2008 11 12 2008FA0000757 1 20080718 G 5610 WINDOW ECLIPS EA500 ECLIPSEEA500 3350000 SW COCKPIT FAILED C O OTHER O OTHER NR NOT REPORTED 1 EA 61 136EA 000136 THERE WAS A POPPING NOISE COMING FRAOM THE VICINITY OF THE PILOTS WINDOW, WINDOW WAS REPLACED. 1 L 7 2 4J RT A00002AC 20081112 SW 2008 11 12 2008FA0000758 1 20080818 G 2621 FX002002 EXTINGUISHER ECLIPS EA500 ECLIPSEEA500 3350000 SW RT NACELLE LEAKING C O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 61 575CC 000075 RT ENGINE FIRE EXTINGUISHER CARTRIDGE LEAKED THROUGH DISCHARGE NOZZLE AND EXPOSED THE ENGINE AND COMPONENTS TO HIGHLY CO RROSIVE CHEMICAL. ENGINE REMOVED FOR CLEAN UP AND REPAIR BY MANUFACTURER. 1 L 7 2 4J RT A00002AC 20081112 SW 2008 11 12 2008FA0000759 1 20080911 G 5340 RETAINER ECLIPS EA500 ECLIPSEEA500 3350000 SW COCKPIT WINDOW UNKNOWN C K NONE O OTHER IN INSP/MAINT 1 EA 61 568EA 000168 A POPPING NOISE COMING FROM THE VICINITY OF THE CO PILOTS WINDOW. SIDE WINDOW RETAINERS WERE REPLACED. 1 L 7 2 4J RT A00002AC 20081125 SO 2008 11 25 2008FA0000760 2 20081112 G 8530 AEC631397 CYLINDER CESSNA 188 188B 2073007 CE CONT O550 IO550D 17042 SO MCAULY D3A34 D3A34C401 GL ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 07 78417 18801952T 1580856D 001465 FOUND ALL 6 CYLINDERS WERE CRACKED. CYLINDER NR1 S/N 50422-12, CRACKED BETWEEN COOLING FIN 16 AND 17 (COUNTED DOWN FROM TOP) FROM THE INTAKE PORT ALL THE WAY AROUND THE CYLINDER, OVER THE TOP SPARK PLUG HOLE, TO THE EXHAUST PORT. 2 CRACKS ON THE INSIDE FROM THE TOP SPARK PLUG HOLE TO THE INTAKE SEAT AND THE INTAKE SEAT TO THE EXHAUST SEAT. AN APPROX .1250 X .2500 HOLE BY THE EXHAUST SEAT ALL THE WAY THROUGH THE HEAD. THE OTHER 5 CYLINDERS (S/N 50741-13, 50974-19, 50960-01 , 50422-06, AND 50991-25) ARE CRACKED UNDER FIN 16 OR 17 ANYWHERE FROM 1INCH TO 6 INCH LONG ON THE OUTSIDE OF THE INTAKE PORT, APPROX MIDDLE SECTION OF THE HEAD (CRACKS RUN PARALLEL WITH COOLING FINS). 1 L 7 1 3O 3 O A9CE E3SO 5 C P47GL 20081126 SO 2008 11 26 2008FA0000761 1 20081113 G 5347 7745405 SEAT TRACK PIPER PA38 PA38112 7103812 SO ZONE 100 CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 09 2472D 3879A0327 PASSENGER SEAT WAS REMOVED FOR ANNUAL INSPECTION. UPON VISUAL INSPECTION OF SEAT RAILS, A CRACK WAS DISCOVERED GOING TH ROUGH THE ENTIRE RAIL. THE SEAT RAIL MUST BE REPLACED IN ORDER TO FACILITATE SAFE FLIGHT. 1 L 7 1 3O A18SO 20081118 CE 2008 11 18 2008FA0000762 1 20081020 G 2721 S22952593 CHAIN CESSNA CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA RUDDER TRIM BROKEN B BGSR K NONE O OTHER IN INSP/MAINT 1 EA 21 169EC 288 172RG0515 L2843836A DURING A NON RELATED MAINTENANCE ACTION, THE MECHANIC NOTICED THE RUDDER TRIM WHEEL WAS MOVING WITH NO RESISTANCE. THE M ECHANIC INSPECTED FURTHER AND FOUND THE CHAIN HAD SEPARATED AT ONE OF THE LINKS. AFTER CLOSER EXAMINATION IT HAS BEEN F OUND THAT SEVERAL OF THE LINK PINS ARE EITHER TOO SHORT OR WAS NOT PRESSED ENOUGH TO HOLD THE LINKS TOGETHER. THE PART WAS ORDERED FROM MFG. (K) 1 H 7 1 3O 3 O 3A17 E286 20081118 CE 2008 11 18 2008FA0000763 1 20081008 G 2720 717 SOLENOID VALVE BEECH 90 C90 1152913 CE RUDDER STUCK B E81R O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 GL 03 261GB 5351 LJ1119 INVESTIGATED PILOT REPORT OF RUDDER BOOST CONSTANTLY KICKING TO LEFT. FOUND PN 717 LT SOLENOID VALVE STUCK IN OPEN POSI TION. ALSO FOUND (3) PN AN9181D RUDDER BOOST CONTROL SYSTEM CROSS FITTING CRACKED AND WATER IN SYSTEM. PURGED WATER FR OM SYSTEM AND REPLACED LT SOLENOID VALVE, CRACKED FITTINGS AND SYSTEM FILTER; OPERATIONS NORMAL. SUSPTECT CONDENSATION OR OTHER SOURCE OF WATER INGESTION INTO SYSTEM THAT CAUSED FREEZING DAMAGE TO COMPONENTS. (K) 1 L 7 2 3T 3A20 20081118 CE 2008 11 18 2008FA0000764 1 20081021 G 2760 21EN96 SWITCH BEECH MU300 400A 1155402 CE SPEED BRAKE SYS CORRODED B E81R O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 GL 03 48SE RK48 INVESTIGATED PILOT REPORT OF UNCOMMANDED "SPEEDBRAKE EXTENDED" ANNUNCIATOR LIGHT ILLUMINATION IN FLIGHT. FOUND HIGH RES ISTANCE IN SPOILER MIXER ASSY. SPEEDBRAKE RETRACT SWITCH ASSY, REPLACED S156 SWITCH WITH SUPERSEDING PN 21EN42-6 SWITCH ASSY. SPEEDBRAKE SYSTEM OPERATIONS NORMAL, NO FAULTS INDICATED. SUSPECT S156 SWITCH CONTACTS CORRODED OR PITTED FRO W EAR AND/OR LONGTERM WATER/DIRT CONTAMINATION. RECOMMEND SIMILAR SWITCHES ON BE 400 SERIES AIRCRAFT BE REPLACED WITH IMP ROVED SWITCHES WITH BETTER SEALING CAPABILITIES BY RECOMMENDED SERVICE BULLETIN OR SIMILAR. (K) 2 H 7 2 4F RT A16SW 20081118 2008 11 18 2008FA0000765 4 20081020 G 3457 13824120211 GPS SNIAS 350 AS350BA 8680817 EU COCKPIT OVERHEATED B H0CR A H UNSCHED LANDING DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 WP 01 29FX 2085 DURING FLIGHT, THE TRIMBLE GPS OVERHEATED AND EMITTED SMOKE. THE PILOT MADE A PRECAUTIONARY LANDING AND SECURED POWER T O THE GPS BY REMOVING THE FUSE. THE UNIT HAD BEEN INSTALLED SINCE 1996. (K) 1 G 7 1 3U NC H9EU 20081124 GL 2008 11 24 2008FA0000766 1 20080808 G 2752 EM41165 ACTUATOR AMTR LANCAR LANCAIR320 056300A GL TE FLAP FAILED C TOWR O OTHER O OTHER NR NOT REPORTED 1 GL 09 320LA 269 MULTIPLE FLAP ACTUATION FAILURES. (K) 1 L 7 1 3O RT EXPA1L71 20081124 CE 2008 11 24 2008FA0000769 1 20081010 G 2710 1260505315 CONTROL CABLE CESSNA 210 210N 2073453 CE CONT O520 IO520* 17032 SO TR AILERON WORN B TF2R K NONE O OTHER IN INSP/MAINT 1 CE 05 6523N 3369 21063081 DURING ANNUAL INSP, THE RT AILERON RETURN CABLE WAS FOUND WORN BEYOND LIMITS BY THE WHITE PLASTIC PULLEY NEAR THE LEADIN G EDGE AT THE WING ROOT. (K) 1 H 7 1 3O 3 O 3A21 E5CE 20081120 CE 2008 11 20 2008FA0000770 1 20081026 G 2720 441921933 RUDDER PEDAL CESSNA 680 680CE 2076811 CE PWC PW306 PW306C 52169 NE COCKPIT JAMMED B CNQR K NONE O OTHER DE DESCENT 1 CE 01 370QS 6800099 ON ACFT DEPARTURE, THE RUDDER PEDALS JAMMED ON THE COCKPIT SIDE PANELS ON THE TAKEOFF. AN EMERGENCY WAS DECLARED AND TH E ACFT LANDED UNEVENTFULLY. DURING THE PREVIOUS MAINT VISIT, THE RUDDER WAS REPLACED WITH A RENTAL UNIT, THE RUDDER WAS PROPERLY INSTALLED AND DOCUMENTED AND RIG AND TRAVEL CHECKS WERE GOOD. THE ACFT FLEW AN OPERATIONAL CHECK FLIGHT AFTER MAINT WITH NO REPORTED ISSUES. THE SIDE PANELS HAVE BEEN PROPERLY SECURED AND CLEARANCE IS SATISFACTORY. A SCR (SERVIC E CONDITION REPORT) HAS BEEN SUBMITTED TO ENGINEERING FOR REVIEW TO CHANGE SECURING METHOD FROM VELCRO TO A FASTENER TYP E INSTALLATION. (K) 2 L 7 2 4F 4 F RC T00012WI E35NE 20081120 CE 2008 11 20 2008FA0000771 1 20081026 G 2720 RUDDER PEDAL CESSNA 680 680CE 2076811 CE PWC PW306 PW306C 52169 NE COCKPIT JAMMED B CNQR O OTHER O OTHER DE DESCENT 1 CE 07 370QS 6800099 ON ACFT DEPARTURE, THE RUDDER PEDALS JAMMED ON THE COCKPIT SIDE PANELS ON THE TAKEOFF. AN EMERGENCY WAS DECLARED AND TH E ACFT LANDED UNEVENTFULLY. DURING THE PREVIOUS MAINT VISIT, THE RUDDER WAS REPLACED WITH A RENTAL UNIT, THE RUDDER WAS PROPERLY INSTALLED AND DOCUMENTED AND RIG AND TRAVEL CHECKS WERE GOOD. THE ACFT FLEW AN OPERATIONAL CHECK FLIGHT AFTER MAINT WITH NO REPORTED ISSUES. THE SIDE PANELS HAVE BEEN PROPERLY SECURED AND CLEARANCE IS SATISFACTORY. A SCR (SERVIC E CONDITION REPORT) HAS BEEN SUBMITTED TO ENGINEERING FOR REVIEW TO CHANGE SECURING METHOD FROM VELCRO TO A FASTENER TYP E INSTALLATION. (K) 2 L 7 2 4F 4 F RC T00012WI E35NE 20081120 CE 2008 11 20 2008FA0000772 1 20081002 G 2750 67183281 CONTROLLER CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C 03047 GL TE FLAP FAILED B CNQR O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 CE 07 78SL 7500238 FLAPS HARD FAILED DURING FLIGHT. FOUND THAT THE FLAP CONTROLLER HARD FAILED DURING COLD SOAKING. REPLACED FLAP CONTROL LER AND ACCOMPLISHED SATISFACTORY FLAP FUNCTIONAL CHECK WITH NO DEFECTS NOTED. RETURNED ACFT TO SERVICE. (K) 2 L 7 2 4J 4 F RT T00007WI TE6CH 20081120 SO 2008 11 20 2008FA0000773 2 20080929 G 8530 65315 CYLINDER CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO ENGINE CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SO 15 5307Q 1081 15073207 21411272A NR 4 CYLINDER FOUND CRACK AT BARREL BETWEEN COOLING FINS. CRACK WAS APPROX 300 DEGREES AROUND CYLINDER CIRCUMFERENCE. SYMPTOMS INCLUDED ROUGH RUNNING, LARGE OIL LEAK AND SMOKE. CATASTROPHIC FAILURE WAS EMANATE AND WOULD HAVE CAUSED COMPL ETE LOSS OF ENGINE POWER. (K) 1 H 7 1 3O 3 O 3A19 E252 20081120 EU 2008 11 20 2008FA0000774 1 20081031 G 5210 709010401101 TRIM TAB AGUSTA A109 A119 0261102 EU PWA PT6 PT6B37A 52179 NE MAIN ROTOR BLADE DELAMINATED D K NONE O OTHER IN INSP/MAINT 1 EA 17 315PD 14035 PU0041 UPON POST FLIGHT IT WAS NOTICED THE MAIN ROTOR BLADE TRIM TAB WAS SERIOUSLY DELAMINATED AND SEPARATED IN FLIGHT. THIS PR OBLEM HAS OCCURRED NUMEROUS TIMES IN THE PAST. SOME OCCASIONS REQUIRED THE BLADE TO BE REMOVED AND SENT BACK TO THE MFG FOR REPAIR. AS IN THIS CASE, OTHER TIMES THE BLADE WAS ABLE TO BE REPAIRED AT OUR FACILITY IAW MM. MFG IS AWARE OF TH IS PROBLEM AND STILL HAS NOT CORRECTED IT. PROBABLE CAUSE IS THE BONDING MATERIAL AND/OR THE BONDING PROCEDURE. (K) 1 G 7 1 3U 4 U H7EU E4EA 20081120 EA 2008 11 20 2008FA0000775 2 20081027 G 7322 383493 SERVO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 SO 11 5339M 2362 172S9359 L3084051A PN 383943 PLUG FOUND HANGING BY SAFETY WIRE WHEN TROUBLESHOOTING LACK OF POWER FROM ENGINE. THREADS IN COVER MISSING. THIS SERVO WAS NOT INCLUDED IN AD2008-08-14 DUE TO MFG DATE OF UNIT. THE SERVO WAS ORIGINAL EQUIPMENT ON A 2003, 172S, WITH A TT OF 2462.0 HOURS AND HAD NOT BEEN REPAIRED OR O/H. PLUG GASKET WAS MISSING. (K) 1 H 7 1 3O 3 O NT 3A12 1E10 20081125 EA 2008 11 25 2008FA0000776 2 20081024 G 8530 AEL75838 GUIDE BELL 47 47G4A 1181031 SW LYC O540 VO540B1B3 41532 EA NR 1 CYLINDER WORN G PFIG K NONE O OTHER IN INSP/MAINT 1 GL 13 24HM 7688 L245043 DURING INVESTIGATION OF AN ACCIDENT IN WHICH ACFT LOST POWER AND WAS FORCED TO LAND THE FOLLOWING WAS DISCOVERED: COMPRE SSION CHECK REVEALED THE NR 1 CYL WAS LEAKING PAST THE EXHAUST VALVE. (COMPRESSION 45/80). EXAMINATION OF THE CYLINDER REVEALED THE EXHAUST GUIDE WAS EXTREMELY WORN AND CRACKED IN 4 PLACES. VALVE OD .496 INCH GUIDE ID .540 INCH, .044 INCH CLEARANCE. IT WAS FURTHER DISCOVERED THAT THE VALVE WAS PN SL-16740 NIMONIC VALVE GUIDE. THIS VALVE REQUIRES THE USE O F A HIGH CHROME CONTENT NI-RESIST VALVE GUIDE. ECI VALVE GUIDE AEL 75838 WAS FOUND INSTALLED. THIS IS A NI-RESIST VALV E GUIDE. ECI VALVE GUIDE AEL 75838 WAS FOUND INSTALLED. THIS IS A NI-RESIST GUIDE. HOWEVER IT DOES NOT HAVE THE CHROM 1 G 7 1 3O 3 O 2H3 E304 20081120 CE 2008 11 20 2008FA0000777 1 20081024 G 2820 FUEL LINE CESSNA 340 340A 2076405 CE CONT O520 TSIO520* 17040 SO FUEL SYSTEM CORRODED D O OTHER K FLUID LOSS NR NOT REPORTED 1 GL 07 340SU 3808 340A0979 THE FUEL CROSSFEED LINE LT TANK TO RT ENGINE, HAD CORRODED TO THE POINT OF LEAKAGE. THE CORRODED AREA WAS UNDER THE CAB IN FLOOR BEHIND THE CO-PILOT SEAT. THE DUCTWORK FOR THE CABIN VENTILATION SYSTEM LAYS ON THE LINE THIS LOCATION. THE C ORROSION WAS LIMITED TO THE AREA OF CONTACT. PIN HOLES HAD DEVELOPED ALLOWING A SMALL QUANTITY OF FUEL TO LEAK, NOT ENO UGH TO DRIP, BUT ENOUGH TO SATURATE THE DUCT WORK AND PRODUCE A STRONG ODOR IN THE CABIN. THE VENTILATION DUCT MUST BE MOVED FOR VISUAL INSPECTION. IN ADDITION, WHEN THE LINE WAS REMOVED, THERE IS EVIDENCE OF ABRASION FROM CONTROL CABLES AT THE OTBD PORTION OF THE LINE. THIS NEEDS TO BE INSPECTED AT THE NEXT OPPORTUNITY. (K) 1 L 7 2 3O 3 O 3A25 E8CE 20081120 CE 2008 11 20 2008FA0000778 1 20081029 G 5511 65320104 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000779 1 20081029 G 5511 65320125 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000780 1 20081029 G 5511 65320124 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000781 1 20081029 G 5511 65320134 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000782 1 20081029 G 5511 65320144 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000783 1 20081029 G 5511 65320104 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000784 1 20081029 G 5511 65320114 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000785 1 20081029 G 5511 65320124 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000786 1 20081029 G 5511 65320135 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000787 1 20081029 G 5511 65320134 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000788 1 20081029 G 5511 65320145 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000789 1 20081029 G 5511 65320144 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000790 1 20081029 G 5511 65320154 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 371QS 5600471 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE RE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTE R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATEDIN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000791 1 20081029 G 5511 65320104 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000792 1 20081029 G 5511 65320114 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HLES BUT MOST OF THE CRACKS CONTINUED P AST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY I NSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000793 1 20081029 G 5511 65320125 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000794 1 20081029 G 5511 65320124 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000795 1 20081029 G 5511 65320135 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000796 1 20081029 G 5511 65320134 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000797 1 20081029 G 5511 65320145 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATEDIN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000798 1 20081029 G 5511 65320154 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000799 1 20081029 G 5511 65320104 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000800 1 20081029 G 5511 65320114 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000801 1 20081029 G 5511 65320125 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000802 1 20081029 G 5511 65320124 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000803 1 20081029 G 5511 65320123 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000804 1 20081029 G 5511 65320135 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000805 1 20081029 G 5511 65320134 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000806 1 20081029 G 5511 65320133 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000807 1 20081029 G 5511 65320145 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000808 1 20081029 G 5511 65320144 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000809 1 20081029 G 5511 65320143 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000810 1 20081029 G 5511 65320163 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000811 1 20081029 G 5511 65320174 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 330QS 5600329 WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS. AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W ERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFT ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000812 1 20081029 G 5511 65320104 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000813 1 20081029 G 5511 65320125 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000814 1 20081029 G 5511 65320124 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000815 1 20081029 G 5511 65320135 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000816 1 20081029 G 5511 65320134 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000817 1 20081029 G 5511 65320145 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000818 1 20081029 G 5511 65320144 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000819 1 20081029 G 5511 65320154 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000820 1 20081029 G 5511 65320164 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000821 1 20081029 G 5511 65320193 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000822 1 20081029 G 5511 65320144 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000823 1 20081029 G 5511 65320114 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000824 1 20081029 G 5511 65320124 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000825 1 20081029 G 5511 65320124 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000826 1 20081029 G 5511 65320135 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000827 1 20081029 G 5511 65320134 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000828 1 20081029 G 5511 65320145 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000829 1 20081029 G 5511 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000830 1 20081029 G 5511 65320154 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000831 1 20081029 G 5511 65320164 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081120 CE 2008 11 20 2008FA0000832 1 20081029 G 5511 65320174 RIB CESSNA 500 560CESSNA 2076750 CE HORIZ STAB CRACKED B JQ0R K NONE O OTHER IN INSP/MAINT 1 CE 09 363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AF TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND. ALL OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIBS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES. THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE RY LIMITED. (K) 2 L 7 2 4F RT A22CE 20081124 EA 2008 11 24 2008FA0000833 2 20081101 G 7414 M3008 DISTRIBUTOR GEAR SLICK CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MAGNETO DESTROYED D DF2S K NONE O OTHER IN INSP/MAINT 1 SW 15 4260Q 1186 04070369 17260160 CONTACT PIN ON THE DISTRIBUTOR GEAR COMES LOOSE AND IS UNUSEABLE. PLASTIC HOLDING IT ON IS CRACKED. (K) 1 H 7 1 3O 3 O NT 3A12 E274 20081126 GL 2008 11 26 2008FA0000834 2 20081106 G 7250 72165 TURBINE NOZZLE WILINT FJ44 FJ44 66000 GL ENGINE SEPARATED D K NONE O OTHER IN INSP/MAINT 1 GL 09 1858 141224 WHILE UNDER GOING A CHECK 3 MAINTENANCE INSPECTION, THE STIFFENING RING ON THE 1ST LOW PRESSURE TURBINE NOZZLE ON THIS ENGINE WAS FOUND SEPARATED AND TRAPPED BETWEEN THE 1ST LP TURBINE NOZZLE AND THE HIGH PRESSURE TURBINE NOZZLE. NO PROBA BLE CAUSE IS A SUSPECT MFG OPERATION. HELD FOR INVESTIGATION. (K) 4 F E3GL 20081125 GL 2008 11 25 2008FA0000835 2 20080930 G 7313 23031938 DIAPHRAGM ALLSN 250C 250C20B 03013 GL NOZZLE CRACKED C HEFR K NONE O OTHER IN INSP/MAINT 1 WP 01 1568 CAT34079 FLOURESCENT PENTRANT INSPECTION PRODUCED INDICATIONS AT 2 LOCATIONS ALONG BRAZING WHERE DIAPHRAGM AND OUTER RING ARE JOI NED. INDICATIONS ARE APPROXIMATELY 1.60 AND 2.50 INCHES LONG, APPROX 180 DEGREES APART. VOIDS IN BRAZING ARE ALSO PRES ENT AT 2 LOCATIONS. (K) 3 U E4CE 20081125 CE 2008 11 25 2008FA0000836 1 20081120 G 2750 FLAP SYSTEM CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL ZONE 600 FAILED C A UNSCHED LANDING J WARNING INDICATION AP APPROACH 1 SW 99 17259899 L3814327A ON FINAL APPROACH THE PILOT DECIDED TO EXECUTE A GO AROUND AND AS HE BROUGHT UP THE FLAPS TO THE 20 DEGREE SETTING THE R T FLAP INBD ROLLER SUPPORT JAMMED IN THE FLAP TRACK ASSY AND THE FLAP RETRACTED CROOKED AND JAMMED AGAINST THE RT AILERO N LEAVING THE RT AILERON STUCK IN THE UP POSITION AND CAUSING AN ASYMMETRICAL FLAP CONDITION WHICH CAUSED THE AIRPLANE T O PULL TO THE RT. WITH FULL LT PRESSURE ON THE YOKE AND WITH RUDDER THE PILOT WAS ABLE TO CONTROL THE AIRPLANE. THE PIL OT WAS ABLE TO TURN LT AND WITHOUT FURTHER INCIDENT FLY THE PATTERN AND LAND THE AIRPLANE SAFELY. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20081201 NM 2008 12 1 2008FA0000838 1 20081121 G 3610 7732873 PRECOOLER BOEING 767 767222 1385122 NM ZONE 400 FRACTURED B K NONE O OTHER IN INSP/MAINT 1 EA 39 767VA 77387 77387 21870 NR1 PYLON PRECOOLER CRACKED IN SEVERAL PLACES. REMOVED AND REPLACED NR1 ENG PRECOOLER IAW MM 36-11-15. WORK PERFORMED O N NR 35501 S/O 599197. 2 L 7 2 4F RT A1NM 20081201 EU 2008 12 1 2008FA0000839 1 20081122 G 7700 NE00000133101 SENSOR DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE1250299 EU CRANKSHAFT DIRTY D O OTHER R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 SW 99 490TS 244 42AC090 020201763 FADEC CONTROLLED POWERPLANT/ HAD UNCOMMANDED POWER REDUCTION TO 75 PERCENT (3 SEPARATE WRITE-UPS) ACCOMPANIED BY MINOR E NGINE SURGING AT VARIOUS TIMES DURING NORMAL CRUISE FLIGHT. MFG FIX WAS RE-DESIGNED FADEC SOFTWARE, THAT DID NOT ALLEVIA TE THE PROBLEM. WHILE PERFORMING A CLUTCH PLATE INSPECTION THE AREA WAS CLEANED AS WELL AS THE CRANKSHAFT POSITION SENSO RS, WHICH IS ONE OF THE FADEC’S SENSORY INPUTS. THIS ACTION SEEMED TO RESOLVE THE AFOREMENTIONED PROBLEMS. TO DATE THERE IS APPROX 23 HOURS OF ENGINE OPERATION TIME WITH NO REPEAT OF THE ISSUE. OTHER OPERATORS HAVE DESCRIBED HAVING THE SAME TYPE OF PROBLEM. 1 L 7 2 3I 3 B RT A57CE E00069EN 20081202 SW 2008 12 2 2008FA0000840 1 20081124 G 2400 MS902982 GROUND STUD MOONEY M20 M20K 5870220 SW CONT O360 TSIO360* 17025 SO AIRFRAME MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 13 305P 2847 250524 AIRFRAME GROUND PLUG IN HAS NEVER BEEN CONNECTED TO AIRFRAME GROUND. BASE OF RECEPTACLE WAS INSULATED FROM AIRFRAME GROU ND BY PRIMER ON METAL ANGLE. WE FOUND COMPLETE ISOLATION FROM GROUND POINT TO FUEL FILLER OPENING, NO GROUND ON OUR FUEL ING OPERATIONS FOR PAST 3 YEARS. MFG SHOULD CHECK CONTINUITY ON AIRFRAME GROUND PORT AT MFG SINCE NO OTHER TIME IN LIFE OF ACFT IS IT REQUIRED TO CHECK. 1 L 7 1 3O 3 O 2A3 E9CE 20081202 GL 2008 12 2 2008FA0000841 1 20081124 G 5210 LATCH DIAMON DA40 DA40 2990002 GL CONT IO360 IO360* 17025 CE HARTZL HCC2Y HCC2YR1 GL PAX DOOR DISENGAGED P B A EMER. DESCENT UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SW 99 661DS 1050 40600 L3241251A CH39369B AT 10500 FT IN CRUISE FLIGHT, GOT AN AUDIBLE "DING" ON THE G1000 WARNING AND THEN A LIGHT SAYING THAT A DOOR WAS OPEN. B ACK DOOR HAD COME OPEN IN FLIGHT. THE DOOR HAD BEEN SHUT AND THERE HAD BEEN NO WARNING DURING PRE-FLIGHT CHECK AND RUN- UP. WAS IN THE RT SEAT AND COULD NOT REACH THE DOOR UNTIL I UNDONE MY SEATBELT. TRIED TO SHUT THE DOOR, BUT DUE THE DE SIGN OF THE HANDLE, THERE IS NO WAY TO SHUT THE DOOR. THE SAFETY LATCH WAS ABOUT TO LET GO AND I HELD ONTO THE HANDLE A S LONG AS I COULD. IT FINALLY GOT INTO THE AIR SCREAM AND WAS JERKED OUT OF MY HAND AND THEN THE DOOR DEPARTED THE AIRC RAFT. DECLARED AN EMERGENCY AND LANDED. 1 L 7 1 3O 3 O NT A47CE E1CE 5 C P920 20081202 SW 2008 12 2 2008FA0000842 1 20081124 G 2897 GROUND WIRE BELL 206 206B3 1181506 SW BOOST PUMP MISSING D K NONE O OTHER IN INSP/MAINT 1 WP 28 304PD 6486 4525 MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH . GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681 -101. OPS NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP. 1 G 7 1 3U H2SW 20081202 SO 2008 12 2 2008FA0000843 1 20081110 G 5414 COWLING PIPER PA32 PA32300 7103212 SO LYC O540 IO540* 41532 EA ZONE 400 BROKEN G A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 SO 19 2772P 6938 6905 3240456 AFTER LIFTOFF, AT APPROX 250 TO 300 FEET AGL THE RT SIDE OF THE UPPER ENGINE COWLING CAME LOOSE AND BROKE OFF AT APPROX THE MIDDLE LT PORTION OF THE COWLING, FALLING TO THE GROUND. THE ACFT HAD UNDERGONE A 100 HOUR INSP ON THE ENGINE AT 6 905.8 HRS. OWNER STATED NO ADDITIONAL MAINT SINCE THAT TIME. 1 L 7 1 3O 3 O A3SO 1E4 20081202 SW 2008 12 2 2008FA0000844 1 20081124 G 2897 GROUND WIRE BELL 206 206B3 1181506 SW BOOST PUMP MISSING D K NONE O OTHER IN INSP/MAINT 1 WP 07 305PD 2853 4586 MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH . GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681 -101. OPERATION NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP. 1 G 7 1 3U H2SW 20081202 SW 2008 12 2 2008FA0000845 1 20081124 G 2897 GROUND WIRE BELL 206 206B3 1181506 SW BOOST PUMP MISSING D K NONE O OTHER IN INSP/MAINT 1 WP 07 306PD 4588 MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH . GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681 -101. OPERATION NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP. 1 G 7 1 3U H2SW 20081201 SW 2008 12 1 2008FA0000846 1 20081124 G 2897 GROUND WIRE BELL 206 206B3 1181506 SW ALLSN 250C 250C20J 03013 GL BOOST PUMP MISSING D K NONE J WARNING INDICATION IN INSP/MAINT 1 WP 07 306PD 1990 4588 MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH . GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681 -101. OPS NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP. 1 G 7 1 3U 3 U H2SW E4CE 20081202 CE 2008 12 2 2008FA0000847 1 20081125 G 8011 S539800M015 SPRING BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO STARTER ADAPTER BROKEN G K NONE O OTHER IN INSP/MAINT 1 SW 13 5716V 14 14 CAS2234 TC990 272745R STARTER ADAPTER P/N 635050-A4, STARTER SPRING FAILED. STARTER ADAPTER OVERHAULED, RETURNED TO SERVICE AFTER OVERHAUL. P ART SOLD, STARTER ADAPTER INSPECTED AND RETAGGED AND SOLD TO MFG. MAINT INSTALLED STARTER ADAPTER AND SPRING FAILED 14 H OURS LATER. 1 L 7 2 3O 3 O RT 3A16 3E1 20081202 EA 2008 12 2 2008FA0000848 2 20081119 G 7310 STD2048ORLW18733 HOSE CESSNA 182 182 2072702 CE LYC O540 TIO540AK1A EA FUEL SYSTEM DETERIORATED D O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 NM 09 72758 554 T18208004 L1088361A ENGINE LOST RPM AND PARTIAL POWER ON GO-AROUND FROM REJECTED LANDING. ACFT THEN FLEW NORMAL PATTERN AND LANDED WITHOUT INCIDENT. GROUND RUN-UP SHOWED NO ABNORMALITIES. MAINT REMOVED INJECTOR NOZZLES. NR 2 CYL NOZZLE WAS PLUGGED AND CONT AMINANTS FOUND IN SEVERAL OTHER INJECTORS. THE CONTAMINANTS APPEARED TO BE FLAKES FROM THE INSIDE OF AIR BLEED HOSES TO THE INJECTOR NOZZLES. THE HOSES ARE HARDENED BY HEAT AND SHOW CRACKING; THEY ARE CHIPPED WHERE THEY SLIDE ONTO THE NOZ ZLE TUBES. WE INSTALLED NEW HOSES. PERHAPS HOSE P/N LW-18737 SHOULD BE REPLACED AT 500 HOUR INTERVALS. 1 H 7 1 3O 3 O NT 3A13 20081201 SW 2008 12 1 2008FA0000849 1 20081101 G 2435 30B4521A STARTER GEN NAMER T28C T28C 6402509 SW ENGINE FAILED B XB2R K NONE O OTHER IN INSP/MAINT 1 WP 01 39FS 624480 STARTER GEN PREVIOUSLY HAD A FIELD FAILURE-COMPLETE MELT DOWN AFTER APPROX 12 FLIGHTS AFTER OVERHAUL. IT WAS REPAIRED U NDER WARRANTY AND REINSTALLED. AFTER APPROX 4 FLIGHTS IT WOULD NOT CONSISTENTLY CARRY THE LOAD. ACFT REGULATION/CHARGI NG SYST CHECKED AND FOUND CORRECT. THE INSP COVER ON THE GENERATOR WAS REMOVED AND DAMAGE TO THE COMMUTATOR WAS FOUND P ROBABLY DUE TO THE PREVIOUS FAILURE. INSP OF 1 SET OF BRUSHES REVEALED GROOVED FACES AND THE LACK OF PROPER BRUSH RUN A T OVERHAUL. AS STATED THIS IS 2ND FAILURE OF THIS ITEM IN A VERY SHORT TIME, THESE FAILURES ARE OBVIOUSLY DUE TO THE LA CK OF PROPER PROCEDURES/ WORKMANSHIP BEING FOLLOWED. (K) 1 L 7 1 4R RT EXPA1L71 20081201 2008 12 1 2008FA0000850 4 20081024 G 2565 PIN BOEING 767 767238 1385114 NM PWA JT9 JT9D7R4D 52054 NE EVAC SLIDE INSTALLED B M4QR K NONE L NO TEST IN INSP/MAINT 1 SW 19 673BF 43 23402 A SLIDE DEPLOYMENT OF THE RT AFT ENTRY DOOR OF THE ACFT WAS ATTEMPTED IN CONJUNCTION WITH A DITCHING DEMONSTRATION IN SU PPORT OF OUR FAR PART 125 CONFORMITY ASSESSMENT BY FSDO - 25. THE SLIDE DID NOT EXTRACT FROM THE DOOR BUSTLE AS THE DOO R WAS OPENED. UPON INVESTIGATION OF THE CAUSE OF THE FAILURE, IT WAS FOUND THAT THE GIRT BAR WAS NOT PROPERLY INSERTED INTO THE GIRT BAR CARRIER OF THE SLIDE AS CALLED OUT IN AMM 25-66-01, PAGE 405, STEP (15). THIS CONDITION WAS CORRECTED AND THE DOOR WAS CLOSED TO ATTEMPT SLIDE DEPLOYMENT AGAIN. ON THE SECOND ATTEMPT, THE SLIDE PACK DID RELEASE FROM THE D OOR AND DROPPED PROPERLY, HOWEVER IT DID NOT INFLATE. THE IN-CABIN FA OPERATING THE DOOR ATTEMPTED TO MANUALLY INFLATE 2 L 7 2 4F 4 F RT A1NM E3NE 20081210 CE 2008 12 10 2008FA0000851 1 20081023 G 3260 12707332 WARNING SYSTEM CESSNA 210 210N 2073453 CE LANDING GEAR MALFUNCTIONED B H DEACTIVATE SYST/CIRCUITS N FALSE WARNING CR CRUISE 1 SW 99 6621A 78 21063559 821099R WHILE FLYING THROUGH RAIN IN IFR CONDITIONS, THE LANDING GEAR NOT DOWN/LOCKED WARNING HORN SOUNDED FALSELY EVEN THOUGH T HROTTLE WAS NOT RETARDED TO DESCENT CONFIGURATION. AIRCREW PULLED WARNING HORN CIRCUIT BREAKER TO TEMPORARILY CANCEL TH E HORN WHICH ALSO DEACTIVATES THE NORMAL FUNCTION OF THE STALL/GEAR WARNING SYSTEM. THE HORN IS VERY LOUD INTERFERING W ITH ATC COMMUNICATIONS DURING A CRITICAL PHASE OF FLIGHT. TROUBLESHOOTING REVEALED THE THROTTLE SWITCH INPUT ON THE DUA L WARNING UNIT IS HYPERSENSITIVE TO A HIGH RESISTANCE GROUND, I.E. MOISTURE ACCUMULATION AT THE THROTTLE SWITCH TERMINA L. 1 H 7 1 3O 3A21 20081210 SO 2008 12 10 2008FA0000852 2 20081129 G 8550 ES48109 OIL FILTER CESSNA 172 172A 2072404 CE CONT O300 O300D 17022 SO ENGINE RUPTURED P E ENGINE SHUTDOWN K FLUID LOSS TX TAXI/GRND HDL 1 SW 99 7830T 2 2 47430 ON 11/26/2008, APPROXIMATELY 1 MINUTE AFTER START-UP THE OIL FILTER RUPTURED RESULTING IN MASSIVE LOSS OF ENGINE OIL. T HE OIL FILTER WAS THE LAST OF FOUR THAT WERE PURCHASED ON 10/05/2006. THE ENGINE WAS SHUT DOWN UPON NOTICE OF LOW OIL P RESSURE AND HAS BEEN DETERMINED TO BE UNHARMED BY THE LOCAL AP MECHANIC. 1 H 7 1 3O 3 O 3A12 E253 20081210 CE 2008 12 10 2008FA0000853 1 20081130 G 2421 ASG120001 ALTERNATOR CESSNA 303 T303 2073820 CE ENGINE SHORTED D H D DEACTIVATE SYST/CIRCUITS RETURN TO BLOCK B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TX TAXI/GRND HDL 1 SW 99 303ET 149 T30300036 246242 840184 HAVE HAD MULTIPLE FAILURES, BOTH IN FLIGHT AND DURING MAINTENANCE GROUND OPERATIONS. HOURS ON FAILED ALTERNATORS RANGE FROM AS LOW AS 30 TO A MAXIMUM OF 220 HOURS TIME IN SERVICE. THE ONE COMMON FACTOR IN ALL FAILURES HAS BEEN THE DISCOVE RY OF LOOSE HEX HEAD CASE BOLTS INSTALLED AND SAFETY WIRED BY MANUFACTURER. THIS PROBLEM IS NOT RESTRICTED TO ONE SIDE ONLY, BOTH ENGINES DRIVE THE SAME ALTERNATOR WITH SAME PART NUMBER. 1 L 7 2 3O A34CE 20081219 GL 2008 12 19 2008FA0000854 2 20081201 G 7200 23038229 SPUR GEAR BELL 206 OH58A 1181579 SW ALLSN 250C 250C20C 03013 GL ENGINE BROKEN B K NONE O OTHER IN INSP/MAINT 1 SW 99 306HP 7120794 AE405466 GAS PRODUCER TRAIN IDLER SPUR GEARSHAFT PN: 23038229. SHEARED IN HALF, PRODUCING METAL IN OIL. WHEN TECHNICIAN DISASSE MBLED GEARBOX FOUND THAT GEARSHAFT WAS THE SOURCE OF THE METAL 1 G 7 1 3U 3 U H2SW E4CE 20081219 2008 12 19 2008FA0000855 2 20081201 G 7210 23038229 SPUR GEAR BELL 206 OH58A 1181579 SW GEARBOX SHEARED B K NONE O OTHER IN INSP/MAINT 1 SW 99 306HP 1954 162 7120794 GAS PRODUCER TRAIN IDLER SPUR GEARSHAFT PN: 23038229. SHEARED IN HALF, PRODUCING METAL IN OIL. WHEN TECHNICIAN DISASSEM BLED GEARBOX FOUND THAT GEARSHAFT WAS THE SOURCE OF THE METAL 1 G 7 1 3U H2SW 20081202 CE 2008 12 2 2008FA0000856 1 20081124 G 3230 SM50D7 RELAY BEECH 33 F33A 1151425 CE LANDING GEAR INTERMITTENT B VJ3R O OTHER O OTHER NR NOT REPORTED 1 WP 07 8252T 184 CE1545 PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE UP POSITION. THE GEAR FAILED TO RETRACT, 3-4 MINUTES LATER THE PI LOT REPORTED THE GEAR CAME UP ON ITS OWN. PILOT THEN PUT THE GEAR IN THE DOWN POSITION AND RETURNED TO BASE. PROBABLE CAUSE AT THIS TIME UNKNOWN. INSTALLED NEW AND IMPROVED RELAY IAW DATE CODE. (K) 1 L 7 1 3O 3A15 20081203 EA 2008 12 3 2008FA0000857 2 20080314 G 7414 SHAFT PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA MAGNETO BROKEN B ZF7R O OTHER O OTHER NR NOT REPORTED 1 WP 07 9126M 110 07071657 2816104 RL1306439A ROTATING MAGNET SHAFT BROKE IN HALF. BROKE DIRECTLY BELOW WHERE THE ROTOR CAM GOES. (K) 1 L 7 1 3O 3 O 2A13 E274 20081202 GL 2008 12 2 2008FA0000858 2 20081118 G 7412 106149504 EXCITER BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL POWERPLANT INTERMITTENT B BJFR O OTHER O OTHER TX TAXI/GRND HDL 1 EA 23 739NM 51124 ENGINE HAD AN INTERMITTENT DELAYED LIGHTOFF CAUSING HOT STARTS. REPLACING THE IGNITION EXCITER CORRECTED THE PROBLEM. T HE DEFECTIVE EXCITER WAS FOUND TO HAVE A LOOSE STUD WHERE THE INPUT VOLTAGE IS APPLIED. SUSPECT THIS WAS CAUSING A LOW OUTPUT VOLTAGE. IT APPEARS THE NUT ON THE STUD WAS OVERTORQUED DURING INSTALLATION, CAUSING THE STUD TO LOOSEN. (K) 1 G 7 1 3U 3 U H2SW E1GL 20081202 CE 2008 12 2 2008FA0000859 1 20081113 G 3211 SUPPORT CESSNA 414 414A 2075907 CE TRUNNION CRACKED B E5WR K NONE O OTHER IN INSP/MAINT 1 GL 21 901BA 6946 414A0232 ON THE FWD TRUNNION SUPPORT, A CRACK WAS LOCATED ON THE LT AND RT SIDES. EDDY CURRENT INSP USED. (K) 1 L 7 2 3O A7CE 20081203 SO 2008 12 3 2008FA0000860 1 20081118 G 3240 16405700 BRAKE DISC PIPER PA23 PA23250 7102308 SO RT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 09 63954 238 277854085 THE DISC WAS FOUND DURING ROUTINE MAINTENANCE TO HAVE A RADIAL CRACK EXTENDING FROM APPROX .5 INCH FROM THE OUTER CIRCUM FERENCE TO OUTER EDGE AND ABOUT HALF WAY THROUGH THE THICKNESS OF THE DISK. (K) 1 L 7 2 3O 1A10 20081203 GL 2008 12 3 2008FA0000861 1 20081117 G 8011 14924LS STARTER DIAMON DA40 DA40 2990002 GL LYC O360 IO360M1A NE ENGINE BROKEN D O OTHER O OTHER NR NOT REPORTED 1 SW 03 203US 40903 L3393551E STARTER HOUSING BROKE AT FRONT CASTING BREAKING OFF FRONT MOTOR SHAFT SUPPORT BEARING WHICH ALLOWED STARTER SHAFT TO DRO P DOWN PREVENTING POSITIVE ENGAGEMENT OF STARTER TO FLY WHEEL. CONVERSATION WITH AIRCRAFT MFG NOTED THIS IS NOT AN ISOL ATED INCIDENT AND THERE ARE DEFECTS IN THE FRONT CASTINGS. (K) 1 L 7 1 3O 3 O NT A47CE 1E10 20081202 CE 2008 12 2 2008FA0000862 1 20081114 G 5743 10112002584 BRACKET BEECH 200 200BEECH 1152920 CE PWA PT6 PT6* 52043 EA RT MLG SUPPORT CRACKED C K NONE O OTHER IN INSP/MAINT 1 EA 27 40R BC07 A 1.4 INCH LONG CRACK WAS FOUND IN THE RT MLG DRAG BRACE SUPPORT BRACKET DURING INSPECTION. DURING THE REMOVAL OF THE P ART (2) ADDITIONAL CRACKS 1.4 INCH LONG WERE FOUND AROUND 4 FASTENERS WHERE THE BRACKET ATTACHES TO THE MAIN SPAR WEB. WHEN INSTALLED, THE AREA AROUND THESE 4 FASTENERS IS OBSCURED BY THE MLG DRAG BRACE FWD ATTACH FITTING (PN 50-120201-5). THE PART WAS REPLACED WITH A NEW BRACKET. NO CRACKS WERE FOUND N THE SPAR WEB. SUSPECT CRACKS CAUSED BY FATIGUE AND OR HARD LANDINGS. (K) 1 L 7 2 4T 3 T A24CE E2NE 20081203 EA 2008 12 3 2008FA0000863 1 20081110 G 6320 269A510351 PINION GEAR SCWZER 269 269D 8059501 EA ALLSN 250C 250C20W NE TRANSMISSION WORN D BS2R O OTHER O OTHER NR NOT REPORTED 1 SW 17 297BJ S0005 0029 CAE845042 DURING SHUT-DOWN, PILOTS REPORTED CLUNKING NOISE. UPON FURTHER INSPECTION, NOISE WAS LOCATED AT UPPER PULLEY SPRAG CLUT CH AREA. REMOVED UPPER PULLEY AND FOUND M/R TRANSMISSION INPUT PINION (PN:269A5103-51) WORN EXCESSIVELY DUE TO LOOSE AF T PINION NUT. PROBABLE CAUSE OF AFT PINION NUT LOOSENING IS SB DB-019 (CORROSION PROTECTION OF INPUT PINION SPLINES). POSSIBLE EXCESSIVE APPLICATION OF ZINC-CHROMATE PRIMER TO INPUT PINION CAUSED IMPROPER CLAMP-UP DURING TORQUING PROCEDUR E. (K) 1 G 7 1 3U 3 U 0 4H12 E4CE 20081203 CE 2008 12 3 2008FA0000864 1 20081108 G 3233 15232003 ACTUATOR CESSNA 500 560CESSNA 2076750 CE NLG LEAKING B FZPR K NONE O OTHER IN INSP/MAINT 1 NM 11 45KB 5600191 ON NOV 6, THE ACFT EXPERIENCED FOR THE THIRD TIME, LANDING GEAR RETRACTION PROBLEMS. IT WAS FLOWN TO REPAIR STATION FOR LANDING GEAR MAINTENANCE. THE ACFT WAS JACKED, AND A GEAR RETRACT CHECK WAS ABLE TO DUPLICATE THE INFLIGHT PROBLEM. T ROUBLESHOOTING REVEALED THAT THE NOSE GEAR ACTUATOR WAS LEAKING INTERNALLY, FILLING THE NITROGEN EMERGENCY EXTENSION SYS TEM WITH HYD FLUID. THIS RESULTED IN A HYDRAULIC LOCK DURING THE NORMAL LANDING GEAR RETRACTION CYCLE, THUS PREVENTING ONE OR MORE MAIN LANDING GEAR FROM ACHIEVING AN UP AND LOCKED POSITION. APPROX 1.5 PINTS OF HYD FLUID WERE DRAINED FROM THE EMERGENCY EXTENSION LINES AND COMPONENTS. ADDITIONALLY, THE EMERGENCY EXTENSION BREATHER CHECK VALVE PN P48-389 HAD 2 L 7 2 4F RT A22CE 20081203 CE 2008 12 3 2008FA0000865 1 20080920 G 6220 368200119 ROD BEECH 33 F33A 1151425 CE NOSE GEAR BENT D K NONE O OTHER IN INSP/MAINT 1 EA 05 6431X 2333 CE1005 ON LANDING, PILOT OBSERVED THREE GREEN LIGHTS. ON TOUCHDOWN AND ROLL OUT NOSE GEAR COLLAPSED INTO NOSE GEAR WHEEL WELL. UPON INVESTIGATION GEAR TRANSMISSION WAS DOWN AND LOCKED. NOSE GEAR ROD END BENT FWD SIDE OF AFT RETRACT ROD. NOSE G EAR ROD END CAN BE ACCESSED IN WHEEL WELL AFT RT SIDE ATTACHED TO KEEL UNDER SHIELD. THIS IS A GOOD PLACE TO LOOK AT HA RD LANDINGS AND DURING ANNUAL INSPECTIONS. PILOT INTERVIEWED AND SAID HE DID NOT HAVE HARD LANDING OR PORPOISE ACFT. P N OF ROD IS 36-820011-9, PN FOR ROD END IS ANDE5-323. (K) 1 L 7 1 3O 3A15 20081203 CE 2008 12 3 2008FA0000866 1 20081117 G 7120 26510088 MOUNT CESSNA 208 208B 2073701 CE PWA PT6 PT6A114 52043 NE ENGINE CRACKED B MT9R O OTHER O OTHER NR NOT REPORTED 1 SW 05 9750B 12988 208B0100 PCE17240 THE CENTER ENGINE MOUNT BRACKET WAS FOUND TO HAVE CRACKS INSIDE THE ASSY AT THE TERMINATION END OF BOTH WELDS. (K) 1 H 7 1 3T 3 T A37CE E4EA 20081202 CE 2008 12 2 2008FA0000867 1 20081117 G 7120 26510127 MOUNT CESSNA 208 208B 2073701 CE PWA PT6 PT6A114 52043 NE LT ENGINE CRACKED B MT9R O OTHER O OTHER NR NOT REPORTED 1 SW 05 9750B 208B0100 THE LT ENGINE MOUNT BRACKET WAS FOUND TO HAVE CRACKS INSIDE THE ASSY AT THE TERMINATION END OF BOTH WELDS. (K) 1 H 7 1 3T 3 T A37CE E4EA 20081202 SO 2008 12 2 2008FA0000868 1 20081121 G 5340 67271800 BRACKET PIPER PA28 PA28R201 7102816 SO NLG ACTUATOR CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 99 4142N 16129 2837012 NOSE GEAR ACTUATOR AFT ATTACH POINT CRACKED. PROBABLE CAUSE IS TIME IN SERVICE. CHANGE AT A REASONABLE TIME. (K) 1 L 7 1 3O 2A13 20081202 SO 2008 12 2 2008FA0000869 1 20081029 G 5340 67271800 BRACKET PIPER PA28 PA28R201 7102816 SO LYC O360 IO360A1A 41514 EA NLG ACTUATOR CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 99 4155G 2837017 NOSE GEAR ACTUATOR AFT ATTACH POINT CRACKED. PROBABLE CAUSE IS TIME IN SERVICE. CHANGE AT A REASONABLE TIME. (K) 1 L 7 1 3O 3 O 2A13 1E10 20081203 2008 12 3 2008FA0000870 1 20081028 G 8011 774960A4 STARTER ENGINE MISMANUFACTURED D SI3R O OTHER W INADEQUATE Q C NR NOT REPORTED 1 EA 63 425 FOUND BAFFLES INSTALLED INCORRECTLY, INCORRECT HOUSING INSTALLED AND VARIOUS INTERNAL PARTS. (K) 20081203 CE 2008 12 3 2008FA0000871 1 20081101 G 5100 SPAR BEECH 18 H18 1151012 CE PWA R985 R985* 52008 NE UNKNOWN CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SW 07 6GJ BA633 HAVE JUST HAD THE SPAR X-RAY ACCOMPLISHED IAW AD75-27-09 R2. UPON REVIEW OF THE X-RAYS IT WAS DETERMINED THAT THERE WAS A CRACK. IT SEEMS THIS CRACK OF A VERY SIMILAR ONE WAS PREVIOUSLY REPAIRED AND THAT REPAIR IS IN QUESTION AS WELL. (K ) 1 L 7 2 3R 3 R A765 5E1 20081202 EA 2008 12 2 2008FA0000874 2 20081118 G 7414 M3820 DISTRIBUTOR PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA MAGNETO DAMAGED B O OTHER O OTHER NR NOT REPORTED 1 SW 99 63954 881 277854085 SUBJECT PART APPEARS TO HAVE NOT RETAINED ITS LOWER BEARING THAT SUPPORTS THE DISTRIBUTOR GEAR. THE PART WAS FOUND TO B E BURNED AND THE BEARING HOLE MISSING THE BEARING AND ROUNDED OUT WHICH CAUSED THE MAGNETO TO FAIL AND PREVENTED ENGINE STARTUP. JUST PRIOR TO THIS, ENGINE STARTUP HAD BEEN DIFFICULT, HOWEVER, MAG DROP AND PERFORMANCE WERE NORMAL. (K) 1 L 7 2 3O 3 O 1A10 1E4 20081203 SO 2008 12 3 2008FA0000875 1 20081118 G 3240 16405700 BRAKE DISC PIPER PA23 PA23250 7102308 SO MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 63954 277 277854085 THE DISC WAS FOUND DURING ROUTINE MAINTENANCE TO HAVE A RADIAL CRACK EXTENDING FROM APPROX .75 INCH FROM THE OUTER CIRCU MFERENCE TO OUTER EDGE AND ABOUT HALF WAY THROUGH THE THICKNESS OF THE DISC. (K) 1 L 7 2 3O 1A10 20081202 CE 2008 12 2 2008FA0000876 1 20081117 G 3240 6364106 BRAKE CABLE CESSNA 525 525B 2076616 CE LT BRAKE FAILED B JVGR K NONE O OTHER IN INSP/MAINT 1 CE 09 92MA 525B0048 LET ACFT SIT OVER NIGHT WITH PARKING BRAKE APPLIED AND FOUND BRAKE SYS TO STILL HAVE 700 PSI IN BRAKE SYS. RELEASED PAR KING BRAKE AND FOUND THAT THE LT BRAKE STILL HAD 160 PSI RESIDUAL PRESSURE AND RT SIDE HAD ZERO RESIDUAL PRESSURE. VERI FIED RT WHEEL ASSY WOULD ROTATE, CHECK LT SIDE AND LT WHEEL ASSY WOULD NOT ROTATE. INSPECTED INSIDE PORTION OF BRAKE ME TERING VALVE IN CABIN AND NOTICED THAT THE LT ACTUATION CABLE CLEVIS END COULD GET HOOKED ON EDGE OF CABLE BALL END. WH EN THAT HAPPENS 160 PSI REMAINS ON LT BRAKE. WHEN CABLE IS POSITIONED PROPERLY LT BRAKE HAS NO RESIDUAL PRESSURE ON GAU GE AND LT WHEEL ROTATES. OBTAINED NEW AFT BRAKE CABLES FROM MFG AND MODIFIED IAW ENGINEERING CO NR 525-1495. REMOVED O 1 L 7 2 4F RT A1WI 20081203 2008 12 3 2008FA0000877 4 20081120 G 2360 GROUND STUD CESSNA 510 510 2076617 CE PWC PW615 PW615FA 52282 NE RT WING LOOSE B JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 551WH 5100055 ADJACENT TO RT WING ACCESS PANEL 623DB THERE IS A GROUNDING POINT TO GROUND THE ACFT DURING FUELING OR WHILE PERFORMING MAINTENANCE. IN AN ATTEMPT TO GROUND TO ACFT IN ORDER TO PERFORM MAINT, WE FOUND THE GROUNDING JACK MISSING. PANEL 632 DB WAS REMOVED AND UPON FURTHER INSP THE PARTS WERE FOUND FLOATING AROUND INSIDE THIS AY WHICH ALSO HOUSES THE AILERON C ONTROL SECTOR. SOME TYPE OF SAFETY SHOULD BE INCLUDED ON GROUNDING JACK TO PREVENT IT FROM COMING APART AND POTENTIALLY JAMMING THE AILERON. (K) 1 L 7 2 4F 4 F RT A00014WI E00073EN 20081217 SW 2008 12 17 2008FA0000878 1 20081127 G 3220 TUBE MOONEY M20 M20F 5870214 SW NLG BROKEN G A UNSCHED LANDING O OTHER CL CLIMB 1 SO 11 6829V 3000 220012 PILOT STATED THAT HE HEARD A LOUD SOUND DURING THE TAKE OFF ROLL OFF OF A GRASS STRIP AND THE ACFT BEGAN TO "HANDLE DIF FERENTLY". HE CONTINUED TO ACCELERATE BRIEFLY AND THEN DECIDED TO ABORT THE TAKE-OFF. INCIDENT INVESTIGATION FOUND ACF T ON ITS NOSE WITH THE NOSE LANDING GEAR FOLDED BACK UNDERNEATH THE ACFT. INSPECTION REVEALED THAT THE TUBING OF THE NL G LEG ASSEMBLY WAS BROKEN. THERE WERE POSSIBLE STRESS FRACTURES AT THE WELS POINTS ON BOTH SIDES OF THE STRUCTURE. 1 L 7 1 3O 2A3 20090107 SW 2009 1 7 2008FA0000879 1 20081127 G 3220 540004501 LEG ASSY MOONEY M20 M20F 5870214 SW NLG BROKEN D C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 SO 11 V6829 3000 220012 PILOT STATED THAT HE HEARD A LOUD NOISE DURING TAKE-OFF AND THAT THE AIRCRAFT BEGAN TO "HANDLE DIFFERENTLY." HE CONTINUE D TO ACCELERATE BRIEFLY, LIFTED OFF AND THEN DECIDED TO ABORT THE TAKEOFF. THE ACFT CAME TO REST ON ITS NOSE WITH THE N OSE L/G FOLDED BACK BENEATH THE ACFT. INSP OF THE NOSE GEAR REVEALED THAT THE NLG LEG TUBING HAD BROKEN AT THE WELD POIN TS ON THE UPPER ENDS OF THE TUBING. CLOSER INVESTIGATION SHOWED POSSIBLE FATIGUE CRACKS AT THE FWD PORTION OF THE WELDED JOINTS. 1 L 7 1 3O 2A3 20090106 GL 2009 1 6 2008FA0000880 1 20081122 G 7931 12635002 SENSOR CIRRUS SR SR20 05628AJ GL CONT IO360 IO360* 17025 CE OIL SYSTEM DEFECTIVE G O OTHER N FALSE WARNING AP APPROACH 1 SO 19 212LV 678 678 1547 360009 SENSOR PRODUCED A FALSE HIGH OIL PRESSURE INDICATION DURING ACFT APPROACH TO AIRPORT. PROBABLE CAUSE WAS INTERNAL FAILUR E, RECOMMENDATIONS TO PREVENT RECURRENCE ARE UNAVAILABLE, AS THE FREQUENCY OF THIS TYPE OF OCCURRENCE HAS BEEN VERY LOW. 1 L 7 1 3O 3 O NT A00009CH E1CE 20090106 SO 2009 1 6 2008FA0000881 2 20081209 G 7414 4310 MAGNETO DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO LEFT FAILED B K NONE O OTHER IN INSP/MAINT 1 WP 23 293DC 22 22 C0193 824561R MAGNETO, PN 4310, SN 08063188. DELIVERED NEW WITH APPLICABLE SB, SB3-08A. AFTER 21.6 HOURS COMPLIANCE WITH SB3-08A FOUND PART FAILED. 1 L 7 1 3O 3 O NT TA4CH E7SO 20090107 SW 2009 1 7 2008FA0000882 1 20081209 G 2710 473501 BELLCRANK GULSTM 112 112A 7630302 SW ZONE 500 MISREPAIRED D K NONE O OTHER IN INSP/MAINT 1 WP 19 1420J 1560 1560 420 EXCESSIVE AILERONS T/E FREE PLAY. SUSPECTED AIL SYS CUMULATIVE WEAR. UPON FURTHER CLOSE VISUAL INSP, FOUND AILERONS BELL CRANK ASSY, PIVOT BRG HSG SECURED TO BELLCRANK PLATE WITH (3 EACH) BLIND FASTENERS. PROTRUDING HEAD FASTENERS WERE FOUND LOOSE AND EXHIBITING BLACK POWDERY RESIDUE AT FASTENER'S PROTRUDING HEAD PERIMETER, SUGGESTING BRINELLING IS OCCURRING ABOUT UPSET FASTENER HOLLOW SHANK OD AND BELLCRANK PLATE FASTENER HOLE SURFACE. ALL SUBJECT FASTENER'S DRIVE STEEL PINS WERE FOUND NOT TO HAVE LIBERATED FROM FASTENER HOLLOW SHANK ID. REPLACED PIVOT BEARING HOUSING ASSY P/N MS20218-1 DUE W ORN AND REINSTALLED/SECURED SAME WITH SOLID AD RIVETS. COMMANDER IPC PAGE 2-195 ITEMS 25, 27 BELLCRANK ASSY PIVOT BEARIN 1 L 7 1 3O A12SO 20090107 EA 2009 1 7 2008FA0000884 2 20081210 G 7322 229164 DISCHARGE TUBE CESSNA 172 172P 2072436 CE LYC O320 O320* 41508 EA FUEL PUMP LOOSE D K NONE O OTHER IN INSP/MAINT 1 SW 99 64204 669 669 75534 DURING 100 HR INSP, FOUND THE PUMP DISCHARGE TUBE ON A MA-4SPA LOOSE. THIS IS THE THIRD SUCH FIND. OTHER ACFT HAVE HAD T HE PUMP DISCHARGE TUBE MISSING AND FOUND AT THE BOTTOM OF THE CARB AIRBOX. 1 H 7 1 3O 3 O NT 3A12 E274 20090107 CE 2009 1 7 2008FA0000885 1 20081211 G 3250 66426438 JAM-NUT CESSNA 560 560XL 2076702 CE STEERING BUNGEE LOOSE D K NONE O OTHER CR CRUISE 1 SO 13 669TT 740 560XL5684 DURING ALL FLIGHT REGIMES (CLIMB/CRUISE/DESCENT) CREW FELT RESISTANCE WHEN LT RUDDER PEDAL WAS DEPRESSED. NO CHANGE IN F EEL WITH LANDING GEAR POSITION (UP OR DOWN). ON GROUND RESISTANCE COULD NOT BE FELT, HOWEVER ACFT WOULD PULL LT WHILE TA XIING. INITIAL FINDINGS REVEALED THE JAM NUT ON THE NOSE STEERING BUNGEE ASSY HAD BACKED OFF AND THE CLEVIS END OF THE B UNGEE HAD TURNED INTERNALLY CAUSING THE OVERALL LENGTH TO INCREASE. NOT KNOWING WHAT IF ANY INTERNAL DAMAGE WAS DONE TO THE SPRING, THE DECISION WAS MADE TO REPLACE THE NOSE STEERING BUNGEE WITH A NEW UNIT. THE BUNGEE WAS INSTALLED AND THE AND THE STEERING SYS WAS RIGGED IAW AMM. ACFT WAS RELEASED FOR TEST FLIGHT, NO RESISTANCE WAS FELT IN THE RUDDER, AND DU 2 L 7 2 4F RT A22CE 20090106 NE 2009 1 6 2008FA0000886 2 20081111 G 8530 CYLINDER PIPER PA31 PA31310 7103103 SO LYC O540 TIO540J2B NE HARTZL HCC2Y HCC2Y* GL ENGINE SEPARATED D K NONE R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CR CRUISE 1 EA 09 801JK 787 318012014 L528061A FH998 PILOT NOTED REDUCTION OF PWR, THEN VIBRATION IN CRUISE FLIGHT. VISUAL INSP REVEALED NR1 CYL INTAKE TUBE SEPARATED FROM S UMP INLET AND WEDGED APPROX 1 INCH AFT OF INLET. FUEL INJECTOR LINE BROKE AT INJECTOR. BOTTOM (2) CYL HOLD DOWN STUDS B ROKE AND (1) BOTTOM, (1) TOP HOLD DOWN NUTS BACKED OFF. SUSPECT CYL HEAD SEPARATION. 1 L 7 1 3O 3 O RT A20SO E14EA 5 C P920 20081217 2008 12 17 2008FA0000887 4 20081028 G 2211 GFC700 AUTOPILOT SYS CESSNA 510 510 2076617 CE MALFUNCTIONED P H DEACTIVATE SYST/CIRCUITS O OTHER AP APPROACH 1 SW 99 510AZ 20 510124 WHEN A DISCREPENCY BETWEEN THE NAVDATA DATABASE & ACTUAL IMPLEMENTATION OF A LOCALIZER NAVAID, GFC700 WILL NOT INTERCEPT & TRACK LOCALIZER SIGNAL CORRECTLY. IT EITHER FLIES THROUGH COURSE OR WILL ACTIVATE LOC MODE & IMMEDIATELY TURN OFF CO URSE. AFCS APPEARS TO REFERENCE LOCALIZER COURSE FROM DATABASE RATHER THAN SELECTED COURSE ON HSI. FIRST DISCOVERED ON ASE LOC DME A APPROACH LAST APRIL. NAVDATA HAD INCORRECT COURSE OF 120 FOR I-PKN LOCALIZER. I-PKN TUNED, HSI WOULD AU TO-SET COURSE TO 120. THE PILOT CAN TURN THE NEEDLE TO THE CORRECT COURSE OF 300, AND THE HSI WILL PROVIDE CORRECT SENS ING. AUTOPILOT WILL NOT CAPTURE THAT COURSE & WILL FLY RIGHT THROUGH LOCALIZER TOWARD TERRAIN. MANUFACTURERS AND FAA/N 1 L 7 2 4F RT A00014WI 20081219 CE 2008 12 19 2008FA0000888 1 20081215 G 2751 DT2RA7 SWITCH BEECH 90 C90 1152913 CE TE FLAPS BENT B O OTHER O OTHER TX TAXI/GRND HDL 1 SW 99 964G 7692 LJ1007 THE UP TRAVEL SWITCH ON THE RT FLAP FAILED TO TRIP UPON FLAP RETRACTION. THIS CAUSED THE FLAP MOTOR TO CONTINUE TO RUN ALTHOUGH THE FLAP WAS ALREADY FULLY RETRACTED. THE MOTOR OVERHEATED AND STARTED GENERATING SMOKE. THE ACFT WAS ON THE GROUND, TAXIING FOR TAKEOFF WHEN THIS WAS DISCOVERED. THE ACFT RETURNED TO THE RAMP. UPON INSPECTION BY MX STAFF IT WA S DISCOVERED THAT THE ARM ON THE FLAP UP TRAVEL SWITCH WAS BENT (CAUSE UNKNOWN.) THIS PREVENTED THE SWITCH FROM CLOSING . A CAREFUL EXAMINATION OF THE AREA COULD NOT REVEAL WHAT CAUSED THE ARM TO BEND. SPECULATION IS THAT PERHAPS IT WAS R ELATED TO ICE OR FOD DEBRIS. 1 L 7 2 3T 3A20 20081230 EU 2008 12 30 2008FA0000889 1 20081119 G 6520 4639306038 PINION GEAR BOLKMS 105 BO105LSA3 5626020 EU TAIL ROTOR DRIVE DEFORMED W ZF6Y K NONE O OTHER IN INSP/MAINT 1 EA 33 315LS 2033 THE MAIN TRANSMISSION WAS DELIVERED FOR OVERHAUL. THERE WAS NO NOTICE ABOUT AN INCIDENT OR A CHIP WARNING. CHIP DETECT OR AND OIL FILTER WERE CLEAN. AT THE BEGINNING OF THE DISASSEMBLY, MECHANIC NOTED THAT THE TAILROTOR DRIVE DIDN’T MOVE WHEN THE INPUT FLANGE WAS TURNED. AFTER REMOVING THE UPPER HOUSING, A SEVERE DAMAGE OF THE TAIL ROTOR DRIVE PINION AND THE ASSOCIATED ROLLER BEARINGS WAS DETECTED. THE BEARING WAS CRACKED AND THE TEETH OF THE PINION WERE SEVERELY DEFORMED . THERE WERE MANY METAL CHIPS INSIDE THE GEARBOX. (K) 1 G 7 2 3U H3AU 20081222 EU 2008 12 22 2008FA0000890 1 20081119 G 6500 4639306006 BEARING BOLKMS 105 BO105LSA3 5626020 EU TAIL ROTOR DRIVE CRACKED W ZF6Y K NONE O OTHER IN INSP/MAINT 1 EA 33 315LS 603 2033 MAIN TRANSMISSION WAS DELIVERED FOR O/H. THERE WAS NO NOTICE ABOUT AN INCIDENT OR A CHIP WARNING. CHIP DETECTOR AND OIL FILTER WERE CLEAN. AT THE BEGINNING OF THE DISASSEMBLY, THE MECHANIC NOTED THAT THE TAILROTOR DRIVE DID NOT MOVE WHEN THE INPUT FLANGE WAS TURNED. AFTER REMOVING THE UPPER HOUSING, A SEVERE DAMAGE OF THE TAIL ROTOR DRIVE PINION AND THE A SSOCIATED ROLLER BEARINGS WERE DETECTED. THE BEARING WAS CRACKED, AND THE TEETH OF THE PINION WERE SEVERELY DEFORMED. THERE WERE MANY METAL CHIPS INSIDE THE GEARBOX. (K) 1 G 7 2 3U H3AU 20081229 EU 2008 12 29 2008FA0000891 1 20081111 G 6310 COUPLING AEROSP AS355 AS355N 8680818 EU TMECA ARRIUS ARRIUS1A NE MAINTRANSMISSION MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 05 766AM 5601 21252126 ENGINE TO MAIN TRANS COUPLINGS FOUND TO BE INCORRECTLY ASSEMBLED. THS WAS FOUND DURING A PRE-FLIGHT INSP. THE COUPLING S HAVE NOW BEEN ASSEMBLED CORRECTLY. (K) 1 G 7 2 3U 3 U RT H11GU E34NE 20081230 CE 2008 12 30 2008FA0000892 1 20081001 G 2510 CLEVIS PIN CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA PILOT SEAT MISSING D K NONE O OTHER IN INSP/MAINT 1 SW 99 75743 17267920 CLEVIS PIN THAT SUPPORTS BACK OF PILOTS SEAT WORN OVER .2500 THRU. THIS PIN SLIDES IN A CURVED PORTION OF THE LOWER FRA ME OF THE SEAT. PROBLEM PARTS ARE CLEVIS PINS THAT SUPPORT THE SEAT BACK ON NR (2), (BELLCRANK). THE BELLCRANK IS WELL WORN IN THE CURVED SECTION AND FILING INTO THE CLEVIS PIN. IF THIS PIN FAILS, THE BACK-REST OF THE SEAT WILL PARTIALLY DROP OFF OR POSSIBLY COMPLETELY DROP OFF WITH OBVIOUS RESULTS. MY SOLUTION WILL BE TO ROUND-OFF THE CURVE IN THE BACK OF THE BELLCRANK, SMOOTH IT WELL AND MAKE A STEEL ROLLER TO FIT INTO THE AREA OF THE CLEVIS PIN WHERE THE BELLCRANK WEAR S ON IT. JUST PERIODICALLY REPLACING THE CLEVIS PIN SHOULD SUFFICE UNLESS THE COARSE WEARING IN THE BELLCRANK IS OBSER 1 H 7 1 3O 3 O NT 3A12 E274 20090107 NE 2009 1 7 2008FA0000893 2 20081217 G 7314 2PR600CWT PUMP DOUG DC3 C47 3021461 WP PWA R1830 R183092 52020 NE LT ENGINE FUEL LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 CE 19 982Z 163 163 12947 438796 LT ENG FUEL PUMP DEVELOPED LEAK THROUGH THE BLEED HOLE IN A PLUG INSTALLED ON THE PRESSURE ADJUSTMENT PORTION OF THE PUM P. SYS WAS PRESSURIZED BY THE ELECTRIC FUEL PRESSURE BOOST PUMP AND A LEAK WAS DETERMINED TO BE APPROX (1) DROP PER SEC OND AT A PRESSURE OF 18 PSI. 2 L 7 2 4R 4 R A669 5E4 20090106 SO 2009 1 6 2008FA0000894 2 20081215 G 7314 6467683A1 PUMP CESSNA 210 T210N 2073456 CE CONT O520 TSIO520* 17040 SO ENGINE SHEARED E WNHA C ABORTED TAKEOFF Y ENGINE STOPPAGE TO TAKEOFF 1 WP 25 5340Y 2 2 21064173 289648 ON SECOND TEST FLIGHT AFTER FACTORY REBUILT ENG INSTALLATION, ENG QUIT DURING TAKEOFF, JUST AFTER LIFTOFF, ALTITUDE LESS THAN 5 FT AGL. PILOT LANDED ACFT AND ROLLED OUT WITHOUT FURTHER INCIDENT. DURING THIS EVENT, PILOT REPORTED THAT AT TAK EOFF INITIATION, POWER SETTINGS WERE " NORMAL, SMOOTH, AND HEALTHY." AT ACFT ROTATION (65-70 KNOTS), PILOT REPORTED MANI FOLD PRESSURE AND FUEL FLOW DECREASED STEADILY AS ENGINE FALTERED, THEN QUIT COMPLETELY. TOWED ACFT TO MAINT AREA. ENG PROMPTLY RESTARTED BUT QUICKLY FALTERED. WITH PROMPT USE OF AUXILIARY FUEL PUMP ENGINE WAS ABLE TO KEEP RUNNING. INSPECT ED ENG AND FOUND ENG DRIVEN FUEL PUMP DRIVE SHAFT SHEARED. CURRENTLY IN CONTACT WITH MFG ABOUT THE INCIDENT. 1 H 7 1 3O 3 O 3A21 E8CE 20090107 NM 2009 1 7 2008FA0000895 1 20081212 G 6310 A1902 BELT ROBSIN ROBSIN R22 R22BETA 7640110 NM LYC O360 O360J2A 41514 EA CLUTCH ASSY DEFECTIVE E A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 23 558LA 1968 3153 L3771936A THE PILOT REPORTED A CLUTCH LIGHT COMING ON FOR MORE THAN 5 SECONDS, FOLLOWED THE PROCEDURES IN THE POH AND MADE A PRECA UTIONARY LANDING. UPON VISUAL INSP IT WAS DEFECTED THAT ONE OF THE DRIVE BELTS IN THE CLUTCH SYS HAD FAILED AND CAUSED T HE CLUTCH ACTUATOR TO ENGAGE CAUSING THE CLUTCH LIGHT TO ILLUMINATE. THERE WERE NO DAMAGES TO THE ROTORCRAFT OR ANY INJ URIES TO THE PILOTS. DRIVE BELTS WHERE REPLACED AND THE ROTORCRAFT WAS RETURNED TO SERVICED. 1 G 7 1 3O 3 O H10WE E286 20090106 CE 2009 1 6 2008FA0000896 1 20081201 G 3010 671440211 TUBE CESSNA 750 750 2076810 CE ANTI-ICE SYSTEM MISMANUFACTURED C NOZR O OTHER W INADEQUATE Q C NR NOT REPORTED 1 WP 23 9NG 4141 7500213 LT WING INBD HEATED LEADING EDGE AIR DISTRIBUTION TUBE PN 6714402-11 HAS AN INCOMPLETE WELD ON THE PERIPHERY OF THE FITT ING. HAD ANIT-ICE TUBE PN 671440211 WELDED IAW DWG 6714402 DWG 001. REINSTALLED L/E AND SEALED SEAMS. (K) 2 L 7 2 4J RT T00007WI 20090107 SW 2009 1 7 2008FA0000897 1 20081214 G 6210 206011135005 BOLT BELL BELL 206 206L3 1182108 SW MAIN ROTOR DEBONDED D K NONE O OTHER LD LANDING 1 EA 23 739NM 12938 A298 51124 MAIN ROTOR BLADE BOLT LWR PLUG, PN 206-011-137-001, FELL OUT ON ENG SHUTDOWN WHEN ROTOR RPM DROPPED BELOW 40 PERCENT. TH IS ALLOWED LEAD BALANCE WEIGHTS TO ALSO FALL OUT OF BOLT. THIS PLUG IS BONDED INTO THE BOLT AT MFG AND APPEARS TO NOT HA VE HAD ADEQUATE ADHESIVE APPLIED. 1 G 7 1 3U H2SW 20090105 CE 2009 1 5 2008FA0000898 1 20081222 G 5311 FRAME LEAR 35 35A 5170602 CE GARRTT TFE731 TFE731* 01518 WP FUSELAGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 19 244LJ 4361 35A244 WHILE INSPECTING THE LT AFT FUEL TANK STRUCTURE, DUE TO LIGHTENING DAMAGE EVENT, FOUND THE FOAM INSULATION WATER SOAKED , AND CAUSING SERIOUS CORROSION IN OUTER FLANGE OF AFT PRESSURE BULKHEAD AND SURROUNDING STRUCTURE. THE HOLE IN THE LT OUTER PRESSURE BULKHEAD FLANGE, WHERE HOT AIR PIPE PENETRATES FLANGE HAD SEVERE INTERGRANULAR CORROSION OCCURRING , AN D AREA WAS VERY WET. 2 L 7 2 4F 4 F A10CE E6WE 20090106 EA 2009 1 6 2008FA0000899 2 20081016 G 8520 13B21431 CRANKSHAFT CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA ENGINE BROKEN B YYBR K NONE O OTHER IN INSP/MAINT 1 GL 03 6478P 15285025 THE ENGINE WAS REMOVED DUE TO ABNORMAL NOISE AND ROUGHNESS, UPON TEARDOWN INSP, FOUND THE CRANKSHAFT BROKEN IN TWO AT TH E CENTER MAIN BEARING AREA. THE CTR MAIN BRG SHOWED DISTRESS, BUT DID NOT INDICATE ANY LACK OF LUBRICATION. THE CRANKC ASE HAD SLIGHT DAMAGE IN THE BEARING RETAINING AREA. THIS ENGINE HAD BEEN FACTORY OVERHAULED ON 7/14/06, AND PRESENTLY HAS 961.3 HOURS SINCE OVERHAUL. THE LOG BOOK DID NOT INDICATE ANY PROP STRIKE OR PROPELLER CHANGE. (K) 1 H 7 1 3O 3 O NT 3A19 E223 20090105 CE 2009 1 5 2008FA0000900 1 20081009 G 3233 99121204 ACTUATOR CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE NOSE GEAR BYPASSING B BGSR K NONE O OTHER IN INSP/MAINT 1 EA 21 3FA 5600023 HYD LOW LEVEL LIGHT CAME ON AFTER TAKEOFF AND REMAINED ON UNTIL FLAPS AND GEAR WERE SELECTED UP AND LOCKED. REPLACED NO SE GEAR ACTUATOR DUE TO INTERNALLY BYPASSING INTO THE EMERGENCY SIDE FOR GEAR EXTENSION. SENT NOSE GEAR ACTUATOR OUT FO R OVERHAUL AND INSTALLED AN OVERHAULED ACTUATOR. (K) 2 L 7 2 4F 4 F RT A22CE E25EA 20090106 CE 2009 1 6 2008FA0000901 1 20081202 G 3230 390814101007 DAMPER RAYTHN 390 390 7150030 CE BUMPER MISSING WRONG PART B E81R K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 100WE RB45 INVESTIGATED PILOT REPORT OF MLG DOORS NOT CLOSING INDICATION FOLLOWING GEAR RETRACTION. FOUND RUBBER BUMPER MISSING FR OM LT MAIN GEAR UPLOCK DAMPER ASSY, LT MAIN GEAR UPLOCK DAMPER ASSY CAUSING LT MN GEAR UPLOCK HOOK NOT TO RESET AND ENG AGE ROLLER FOLLOWING GEAR RETRACTION DUE TO EXCESSIVE UP-TRAVEL OF LT MAIN GEAR. REPLACED LT MAIN GEAR UPLOCK DAMPER WI TH SERVICEABLE, SUPERSEDING PN 3908141010013 DAMPER ASSY. LANDING GEAR RETRACTION/ EXTENSION OPERATIONS NORMAL. 1 L 7 2 3F RT A00010WI 20090102 WP 2009 1 2 2008FA0000902 1 20081208 G 7500 369H8407 TUBE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL BLEED AIR UNSERVICEABLE B BS2R K NONE O OTHER IN INSP/MAINT 1 SW 17 8617F 272 570128D CAE830481 THIS DEFECT WAS DETECTED DURING TROUBLESHOOTING FOR AN ENGINE PWR PROBLEM. THIS FLEX TYPE TUBE ASSY WAS INSTALLED IN CO NJUCTION WITH AN STC FROM ENG PWR PROBLEM. THIS FLEX TYPE TUBE ASSY WAS INSTALLED IN CONJUNCTION WITH AN STC, PC SAFETY VALVE KIT SE5511NM. AFTER THE DEFECT WAS DETECTED, THE KIT FOR SAFETY VALVES WAS REMOVED AND THE ORIGINAL HARD LINE WA S RE-INSTALLED. THE STC KIT WILL NOT FIT IN THE ENGINE COMPARTMENT WITHOUT THE USE OF THE FLEX BLEED AIR TUBE. THESE T UBE ASSY ARE VERY SENSITIVE TO BREAKAGE AFTER THEY HAVE TAKEN A SET. (K) 1 G 7 1 3U 3 U H3WE E4CE 20090105 CE 2009 1 5 2008FA0000903 1 20081208 G 3244 850108PR TUBE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL TIRE LEAKING C MT9R K NONE O OTHER IN INSP/MAINT 1 SW 05 1120N 208B0386 PCE19211 980220 THE PILOT REPORTED A FLAT TIRE. MAINT FOUND AN INNER-TUBE LEAKING WITH NO APPARENT DAMAGE TO THE TIRE. THE TUBE WAS RE PLACED WITH A NEW TUBE. SIX DAYS LATER THE SAME PILOT IN CHARGE OF THE SAME ACFT REPORTED THE SAME TIRE FLAT. MX AGAIN FOUND THE INNER TUBE FLAT WITH NO APPARENT SIGNS OF DAMAGE TO THE TIRE. A THROUGH INSP OF THE INNER-TUBE SHOWED PIECES OF WHAT APPEAR TO BE PAPER TOWEL EMBEDDED INTO THE RUBBER. THE FIRST TUBE WAS THEN INSPECTED WHICH SHOWED THE SAME MAT ERIAL EMBEDDED INTO IT. AN INSPECTION OF NEW STOCK SPARE INNER TUBES OF THIS TYPE THAT HAD NEVER BEEN ISSUED OUT, FOUND THE SAME MATERIAL EMBEDDED IN THEM ALONG WITH, IN SOME CASES, PIECES OF HARD MATERIAL. (K) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20090106 NE 2009 1 6 2008FA0000904 2 20081209 G 7250 30606266 TURBINE BLADES AMD FALC50 FALCON50MYST 2730106 EU GARRTT TFE731 TFE73140 29001 NE NR 2 ENGINE DAMAGED B JGVR O OTHER O OTHER NR NOT REPORTED 1 CE 09 373RS 0259 THE THIRD STAGE LP TURBINE DISK ON NR 2 ENG HAD A BLADE (PN 30606901) BREAK IN FLIGHT DAMAGING THE EXHAUST NOZZLE AND TH E AFTER BODY OF THE ENG. THE BLADES OF THE TURBINE DISK HAD A 2500 HOUR MPI REQUIRED EDDY CURRENT INSP COMPLETED AT 245 8.6 TSN AND 1979 CSN. THE NEXT INSP APPEARS TO BE DUE IN 216.5 HRS. (K) 2 L 7 3 4F 4 F A46EU E1NM 20090106 SO 2009 1 6 2008FA0000905 2 20081201 G 8530 ECC712CN CYLINDER BEECH 58 58 1152740 CE CONT O550 IO550C SO ENGINE SEPARATED D K NONE O OTHER IN INSP/MAINT 1 EA 25 333ZX TH1739 NR 1 CYL FAILED, HEAD SEPARATED FROM BARREL. ALL CYL, WERE OVERHAULED, 5/12/2004, 817.5 HRS AGO. (K) 1 L 7 2 3O 3 O 3A16 E3SO 20090106 EU 2009 1 6 2008FA0000906 1 20081122 G 8120 SEAL GARRTT SOCATA TB20 TB21 8680697 EU LYC O540 TIO540AB1A 41533 EA TURBOCHARGER FAILED D K NONE O OTHER IN INSP/MAINT 1 CE 09 2802W SCR0175 1137 L921061A PILOT REPORTED THAT ENGINE LOST OIL PRESSURE AT AN ALTITUDE OF 8000 FT ABOUT 14 MILES WEST OF MUNICIPAL AIRPORT. HE WAS ABLE TO MAKE AIRPORT AND SHUTDOWN THE ENGINE AFTER COMING TO A STOP ON THE RUNWAY. REPORTED THAT WHEN THE ACFT LEFT, T HE OIL WAS CHECKED AND WAS INDICATING 10 QTS. ON THE DIPSTICK. THE ENGINE WAS EXAMINED WITH A REP FROM FAA PRESENT. IT WAS DETERMINED AFTER EXAMINING THE TURBOCHARGER AREA THAT THE INTERNAL SEALS TO TURBO MUST HAVE FAILED, CAUSING OIL TO ENTER BOTH INTAKE SYS AND HOT SIDE OF TURBO. SCAVENGE PORT OF TURBO WAS INSPECTED AND FOUND TO BE UNOBSTRUCTED. OIL WA S DRAINED FROM SUMP, YIELD WAS 1.5 QTS. (K) 1 L 7 1 3O 3 O RT A51EU E14EA 20090106 SO 2009 1 6 2008FA0000907 2 20081208 G 8530 539491 CYLINDER BEECH 33 35C33 1151408 CE CONT O470 IO470K 17026 SO MCAULY 2A36C 2A36C23 GL ENGINE CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 653P 295 CD991 818526R 652989 ANNUAL INSP REVEALED A LARGE QUANITY OF VERY BLACK OIL RUNNING DOWN THE ENGINE MOUNT LEG AND AIRFRAME STRUCTURE. FURTHE R INVESTIGATION FOUND THE LEAK TO ORIGINATE AT THE HEAD TO BARREL CONNECTIONS OF CYLINDERS NR 1, AND NR 3. COMPRESSION CHECK USING AN INPUT PRESSURE OF 80 PSI AND LEAK DETECTING SOLUTION SHOWED AIR TO BE LEAKING FROM THE CYLINDER HEAD TO B ARREL CONNECTION. CYLINDERS WERE REMOVED AND INSPECTED BUT IT COULD NOT BE CONFIRMED IF CRACK EXISTED OR IF LEAK WAS TH ROUGH THE THREADS. THE LOW TIME ON NEW MFG CYLINDERS INDICATES THAT THE PROBLEM COULD BE IN THE MFG PROCESS. NOTE: ENG INE WAS REBUILT / ZERO TIMED USING NEW CYLINCERS ON 5/20/2001. (K) 1 L 7 1 3O 3 O 3A15 3E1 5 C P880 20090107 SO 2009 1 7 2008FA0000908 2 20080810 G 8520 510384 CONNECTING ROD PIPER J3 J3C65 7100510 SO CONT C90 C908F 17009 SO ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 15 42080 14307 4077788 NR 1 CONNECTING ROD FAILED IN FLT, OFF-AIRPORT LANDING AND SUBSTANTIAL DAMAGE. CONNECTING ROD FAILED SLIGHTLY ABOVE CR ANKSHAFT; ROD CAP STILL BOLTED & SAFETIED TO DAMAGED & SEPARATED LOWER PORTION OF CONNECTING ROD. DAMAGE TO CRANKCASE, CRANKSHAFT, & ADDITIONAL INTERNAL ENGINE COMPONENTS SUGGEST A FAILED/ SPUN NR 1 ROD BEARING, RESULTING IN A LOSS OF LUBR ICATION TO NR 1 CONNECTING ROD. EXCESSIVE HEAT BUILDUP, AND SUBSEQUENT SEIZURE TO THE CRANKSHAFT JOURNAL AND ROD FAILURE . THE OIL SCREEN MINIMAL CONTAMINATION, INDICATING A SHORT OPERATING TIME BETWEEN PART FAILURE AND ENGINE SHUTDOWN. E NG EXHAUST WAS CLEAN AND THERE WAS NO EVIDENCE OF EXTERNAL OIL LEAKAGE ON THE ENG; REGARDLESS, OIL QUANTITY IN THE ACFT 1 H 7 1 3O 3 O A691 E252 20090106 GL 2009 1 6 2008FA0000909 2 20080825 G 7261 23038229 SEPARATOR ALLSN 250C T63A720 03002 GL AIR/OIL BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 AE405466 CUSTOMER HAD CHIP LIGHT INDICATING METAL GENERATION IN ENG. INVESTIGATION/ DISASSEMBLY REVEALED THE AIR OIL SEPARATOR G EAR WAS BROKEN AT GEARFACE TO SHAFT LOCATION (WHERE THE 16 DRILLED HOLES CONVERGE AT GEAR CTR). THIS IS THE 4TH OR 5TH AIR OIL SEPARATOR GEAR I`VE SEEN BROKEN LIKE THIS IN 7-8 YEARS. WHEN THE GEAR BREAKS, IT GENERATES METAL BUT DOESN`T FA IL IN OPERATION, BUT THEN THE GEARBOX IS OPENED THE GEAR COMES OUT IN TWO PIECES. (THE GEAR IS SUPPORTED BY A BEARING ON EITHER END AND IN OPERATION THE BROKEN GEAR IS HELD TOGETHER BY THE SANDWICH FIT CREATED BY THE GEARBOX IT OPERATES IN) . THE PROBABLE CAUSE FOR THE REPEATED FAILURES IS POSSIBLY THE DESIGN. THE GEAR HAS 16 HOLES DRILLED INTO IT AND THEY 3 U E4CE 20090107 CE 2009 1 7 2008FA0000910 1 20081226 G 7120 AN721 BOLT CESSNA 500 550 2076604 CE ENGINE MOUNT INCORRECT D K NONE O OTHER IN INSP/MAINT 1 SW 05 649WM 500 42030 DURING UNSCHEDULED MAINT THE ENG WAS REMOVED FROM THE MOUNTS, (1) ENG MOUNT HAD THE HELICOIL PULL OUT OF THE CASTING NEC ESSITATING REPLACEMENT OF THE MOUNT. IT WAS ALSO DISCOVERED THAT ALL OF THE ENGINE MOUNT BOLTS WERE OF THE INCORRECT PN. ALL OF THE BOLTS INSTALLED (AN7-21) WERE DRILLED FOR COTTER PINS RATHER THAN THE BOLTS (AN7-21A) NOT DRILLED FOR A COT TER PIN THAT ARE CALLED OUT IN THE PARTS BOOK. THERE WERE NO LOG ENTRIES FOUND INDICATING THAT THE ENG HAD BEEN REMOVED SINCE INSTALLATION AT THE FACTORY. 1 L 7 2 4F A22CE 20090106 CE 2009 1 6 2008FA0000911 1 20081201 G 3230 HMX5FG ROD END CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO LT MLG CRACKED C K NONE J WARNING INDICATION IN INSP/MAINT 1 GL 17 77RG 12579 310R0636 PILOT REPORTED NO LT GEAR DOWN LIGHT AND ALSO HEARD A LOUD BANG WHEN GEAR WAS RETRACTED. PILOT DID SEVERAL FLYBYS FOR M ECHANICS ON GROUND, GEAR APPEARED TO BE DOWN. PILOT LANDED WITHOUT INCIDENT AND STOPPED ON RUNWAY. GEAR WAS NOT COMPLET ELY LOCKED. GEAR WAS SECURED AND ACFT WAS TAXIED TO MAINT. WHEN PLACED ON JACKS, THE ROD END (HEIM END) ON THE IB LT M AIN GEAR PUSH PULL TUBE WAS FOUND TO HAVE THE BALL PULLED OUT OF THE ROD END. ROD END APPEARED TO HAVE A SMALL CRACKED WHERE IT FAILED. NOTE: ACFT HAD BEEN LANDED GEAR UP JAN O2. (K) 1 L 7 2 3O 3 O 3A10 E5CE 20090106 CE 2009 1 6 2008FA0000912 1 20081201 G 7400 IGNITION SYS CESSNA 182 182C 2072708 CE CONT O470 O470L 17026 SO EGNINE DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 GL 15 8595T 52495 6944670LR ENG RUNS ROUGH. ENG MISFIRES. HISTORY: 2/25/2004; TACH 487.1 - REPLACED LT AND RT MAGNETOS. ACFT RUN UP CHECKED OUT OK. 4/26/2004 TACH 508 - CHECKED TIMING. 05/11/2005 (NO TACH) - TROUBLESHOOTING ROUGH ENGINE. REMOVED INTAKE MANIFOLD AN D FLAT SAND FLANGES AND REMOVE DENTS. REPLACE ALL INTAKE FLANGE GASKETS AND HOSES. PRESSURE TEST INTAKE MANIFOLD. REM OVE AND REPAIR MA4-5 CARB. RUNUP OK. 8/16/2007 TACH 542.7 - CHECK MAG TO ENG TIMING. RUN-UP AND LEAK CHECK OK. SOLUT ION; TACH 573.8 USED DAIL INDICATOR AND FOUND THAT UTILIZING TIMING MARKS RESULTS IN 20+ DEGREE RETARDED IGNITION. USED DIAL INDICATOR TO SET PROPER TIMING AND ENGINES PERFORMS AS IT SHOULD. (K) 1 H 7 1 3O 3 O NT 3A13 E273 20090102 EU 2009 1 2 2008FA0000917 1 20081217 G 2435 BEARING UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE STARTER GEN UNSERVICEABLE D K NONE O OTHER IN INSP/MAINT 1 EA 07 451F 1781 1124 PILOT COMPLAINED OF A SEVERE ENGINE VIBRATION AND HOWLING NOISE EMANATING FROM THE ENGINE AREA, DURING ALL PHASES OF ENG INE OPERATION. THE STARTER WAS REPLACED AND THE VIBRATION CEASED. (K) 1 G 7 2 3U 3 U NC R0001RD E34NE 20090106 NE 2009 1 6 2008FA0000918 2 20081215 G 7414 103827991 MAGNETO MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6D 41828 NE ENGINE MALFUNCTIONED B C41R O OTHER O OTHER TX TAXI/GRND HDL 1 SO 13 201TC 240173 L1710951AC STARTED THE ACFT NORMALLY, TAXIED FROM HANGAR TO THE SELF-SERVE FUEL PUMP AND SHUTDOWN. FUELED ACFT. ATTEMPTED TO STAR T THE ACFT AFTER FUELING. THE ENG TURNED OVER NORMALLY, BUT DID NOT FIRE. TROUBLESHOOTING REVEALED NO SPARK OUTPUT FRO M THE MAGNETO. SENT MAGNETO OUT FOR REPAIR MAGNETO SHOP DETERMINED THE MAGNET HAD SLIPPED ON THE SHAFT. A NEW MAGNETO WAS INSTALLED IN THE ACFT. ENGINE TT: 5345.1; TSO 132.6. THIS MAGNETO WAS INSTALLED AT THE ENGINE OVERHAUL AS AN OVERH AULED EXCHANGE UNIT. PROBABLE CAUSE/ RECOMMENDATIONS TO PREVENT RECURRENCE; NO ADDITIONAL INSP REQUIREMENTS ARE RECOMME NDED. A FAILURE SO SOON AFTER OVERHAUL SUGGESTS A DEFECT IN THE PARTS OR A FAILURE IN THE OVERHAUL PROCESS. THE LARGEST 1 L 7 1 3O 3 O 2A3 1E10 20090107 CE 2009 1 7 2008FA0000919 1 20081210 G 5711 52221003 SPAR CESSNA 402 402B 207590P CE CONT O520 TSIO520EB 17040 SO MCAULY 3AF32C 3AF32C87 GL LT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 13 141MC 10940 402B0547 DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR. THE MAIN GEAR IS ATTACHED AT THE OTBD END. THE CRAC KS WERE AT THE 11, 2, 5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LE NGTH WITH THE 2 LOWER HOLES CONTINUING INTO THE ACCESS HOLE. CRACKS WERE ALSO AT THE 7 AND 5 O, CLOCK POSITIONS OF THE LARGE ACCESS HOLE TO WHICH A COVER PLATE IS ATTACHED WITH A RIGN AND NUT PLATES ON THE OPPOSITE SIDE. THESE CRACKS WEN T THROUGH THE SCREW HOLES AND EXTENDED UP T 2+ INCHES. THE CRACKS WERE OBSERVED 2671 HOURS AFTER THE MAIN SPAR CAP MODI FICATION. SIMILAR CRACKS OF VARYING DEGREE HAVE BEEN OBSERVED IN 5 OF 8 ACFT. ALL HAVE THE MOD. IT IS NOT KNOWN IF TH 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 20090106 CE 2009 1 6 2008FA0000920 1 20081216 G 3233 12810016 ACTUATOR CESSNA 172 172RG 2072438 CE RT MLG CRACKED D JU8S O OTHER O OTHER NR NOT REPORTED 1 GL 25 9423D 1940 172RG0285 ON 7/08/2008, RT MLG NOT FULLY RETRACTED REPORTED BY ATC. THE PILOTS NOTICED THE RT MLG WAS NOT FULLY RETRACTED. THE L ANDING GEAR WAS THEN EXTENDED, A DOWN AND LOCKED IND FOR GEAR WAS REPORTED. THE RT MLG ACTUATOR BODY (DATE STAMP OF AUG 21, 2001.) WAS FOUND CRACKED AT THE FWD BOLT HOLE ATTACH POINT. THE CRACK ALLOWED THE ACTUATOR SECTOR GEAR AND PISTON TO BECOME MISALIGNED. ACTUATOR SECTOR GEAR PN 988200202 AND PISTON ASSY PN 98820041 WERE FOUND TO BE DAMAGED. THIS ACT UATOR BODY WAS REPLACED WITH A NEW PART IAW SEB 01-2 R1 ON 10-11-2001 AT AN TT OF 5180.2. IT WOULD BE POSSIBLE FOR THIS DAMAGE TO PREVENT THE GEAR FROM TRAVELING TO THE FULL DOWN AND LOCKED POSITION RESULTING IN LOSS OF ACFT CONTROL DURING 1 H 7 1 3O 3A17 20090106 CE 2009 1 6 2008FA0000921 1 20081210 G 5711 522210003 SPAR CESSNA 402 402B 207590P CE CONT O520 TSIO520EB 17040 SO MCAULY 3AF32C 3AF32C87 GL LT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 13 402CA 12660 402B0842 DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR. THE MAIN GEAR IS ATTACHED AT THE OTBD END. THE CRAC KS WERE AT THE 11, 2, 5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LE NGTH. CRACKS WERE ALSO AT THE 7 AND 5 O`CLOCK POSITIONS OF THE LARGE ACCESS HOLE TO WHICH A COVER PLATE IS ATTACHED WIT H A RING AND NUT PLATES OF THE OPPOSITE SIDE. THESE CRACKS WENT THROUGH THE SCREW HOLES AND EXTENDED UP TO 1.5 INCH. T HE CRACKS WERE OBSERVED 1600 HOURS AFTER THE MAIN SPAR CAP MODIFICATIONS. SIMILAR CRACKS OF VARYING DEGREE HAVE BEEN OB SERVED IN 5 OF 8 ACFT. ALL HAVE THE MOD. IT IS NOT KNOWN IF THERE IS ANY CORROLATION. (K) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 20090106 CE 2009 1 6 2008FA0000922 1 20081210 G 5711 52221003 SPAR CESSNA 402 402B 207590P CE CONT O520 TSIO520NB 17040 SO LT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 13 106GP 16296 402B1235 DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR. THE MAIN GEAR IS ATTACHED AT THE OTBD END. THE CRAC KS WERE AT THE 11,2,5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LENG TH. CRACKS WERE ALSO AT THE 7 O`CLOCK POSITIONS OF THE LARGE ACCESS HOLE TO WHICH A COVER PLATE IS ATTACHED WITH A RING AND NUT PLATES ON THE OPPOSITE SIDE. THIS CRACK WENT THROUGH THE SCREW HOLE AND EXTENDED 1 INCH. THE CRACKS WERE OBSER VED 930 HOURS AFTER THE MAIN SPAR CAP MODIFICATION. SIMILAR CRACKS OF VARYING DEGREE HAVE BEEN OBSERVED IN 5 OF 8 ACFT. ALL HAVE THE MOD. IT IS NOT KNOW IF THERE IS ANY CORROLATION. (K) 1 L 7 2 3O 3 O A7CE E8CE 20090106 EU 2009 1 6 2008FA0000923 1 20081212 G 3222 25UN561 AXLE BRAERO DH125 HS125700A 4230170 EU NLG WORN B X42R K NONE O OTHER IN INSP/MAINT 1 GL 03 483FG 521 257094 CONTINUOUS NOSE GEAR VIBRATIONS UPON LANDING. TEARDOWN AND INSPECTION OF NOSE GEAR AXLE BARREL ASSY REVEALED THE NOSE A XLE TO BE WORN BEYOND LIMITATIONS. (2) .005" GROOVES WORN INTO AXLE. (1) ON EACH SIDE WHERE THE AXLE BARREL COVER PLAT E SEALS ARE LOCATED. NO WEAR IS PERMITTED AS PER THE OVERHAUL MANUAL. (K) 2 L 7 2 4F A3EU 20090102 CE 2009 1 2 2008FA0000924 1 20081201 G 2710 500000066 CONTROL CABLE CESSNA 421 421B 2076014 CE LT AILERON CABLE FRAYED D O OTHER O OTHER NR NOT REPORTED 1 GL 13 68494 TT ON CABLES UNKNOWN SUSPECT ORIGINAL. FOUND LT AFT AILERON CABLE FRAYED AT WING STATION 58.94 THE PULLEY WAS FROZEN. INSPECTED REST OF SYSTEM NO DEFECTS FOUND. ON REPLACEMENT OF CABLE FOUND WAS ALSO FRAYED AT WING STA 87.29. THE PULLEY S AT THIS STATION WERE TURNING FREELY. WHEN INSTALLING NEW CABLE NOTICED THE FWD AILERON CABLE WITH BROKEN STRANDS ALSO AT WING STATION 87.29, ALSO REQUIRING CABLE REPLACEMENT. SUGGEST THAT EVERYONE BE REMINDED OF THIS LOCATION AND OF WIN G STATION 106.79 AS THESE ACCESS PANELS ARE IN WHEEL WELL WITH THE PULLEYS OFF TO THE SIDE AND DOWN THEY ARE A HARD AREA TO INSPECT, AND THE AILEREONS HAD TO BE MOVED TO THE TRAVEL LIMITS TO BE COMPLETELY INSPECTED, AS THE CABLES WERE BROKE 1 L 7 2 3O A7CE 20090107 CE 2009 1 7 2008FA0000925 1 20081215 G 2820 6017001079 VENT LINE BEECH 58 58 1152740 CE RT WING LEAKING B EHHR K NONE K FLUID LOSS IN INSP/MAINT 1 EA 17 584RF 1933 TH2012 FOUND RT WING FUEL VENT CONSTANTLY LEAKING FUEL. OPENED RT WING TIP FILLER CAP AND BLEW AIR THROUGH THE VENT SYSTEM AND BUBBLES WERE SEEN IN THE LOWER END OF THE FUEL TANK WHERE THE VENT TUBE PASSES THROUGH THE FUEL TANK BULKHEAD. USED AC FT MM TO FABRICATE A HOLE IN FUEL CELL TO GAIN ACCESS TO THE LEAKING TUBE AND APPLIED PRO SEAL TO SEAL THE TUBE TO THE B USHING WHERE THE LEAK WAS OBSERVED. (K) 1 L 7 2 3O 3A16 20090102 CE 2009 1 2 2008FA0000926 1 20081201 G 2710 500000067 CONTROL CABLE CESSNA 421 421B 2076014 CE LT AILERON FRAYED D O OTHER O OTHER NR NOT REPORTED 1 GL 13 68494 TT ON CABLES UNKNOWN SUSPECT ORIGINAL. FOUND LT AFT AILERON CABLE FRAYED AT WING STA 59 THE PULLEY WAS FROZEN. INSPECTE D REST OF SYSTEM NO DEFECTS FOUND. ON REPLACEMENT OF CABLE FOUND WAS ALSO FRAYED AT WING STA 87.29. THE PULLEYS AT THIS STATION WERE TURNING FREELY. WHEN INSTALLING NEW CABLE NOTICED THE FWD AILERON CABLE WITH BROKEN STRANDS ALSOAT WING ST ATION 87.29, ALSO REQUIRING CABLE REPLACEMENT. SUGGEST THAT EVERYONE BE REMINDED OF THIS LOCATION AND OF WING STA 106.7 9 AS THESE ACCESS PANELS ARE IN WHEEL WELL WITH THE PULLEYS OFF TO THE SIDE AND DOWN THEY ARE A HARD AREA TO INSPECT, AN D THE AILERONS HAD TO BE MOVED TO THE TRAVEL LIMITS TO BE COMPLETELY INSPECTED, AS THE CABLES WERE BROKEN IN SMALL LOCAL 1 L 7 2 3O A7CE 20090120 SO 2009 1 20 2008FA0000927 2 20081201 G 8500 S1053E16T HOSE CESSNA 150 A150K 2071824 CE CONT O200 O200* 17020 SO AIR INTAKE CONTAMINATED D A UNSCHED LANDING R Y PARTIAL RPM/PWR LOSS ENGINE STOPPAGE CL CLIMB 1 AL 05 8450M A15000150 BEGAN NORMAL LANDING CHECK LIST INCLUDING CHECKING CARB HEAT. AFTER PULLING CARB HEAT ON, ENGINE DIED. TURNED OFF CARB HEAT & ENGINE RESTARTED ON ITS OWN WITHOUT PILOT INPUTS. CONTINUED PATTERN & GRADUALLY REAPPLIED CARB HEAT ON BASE AND FINAL. ON SHORT FINAL ENGINE DIED & PILOT GLIDED TO A SAFE TOUCHDOWN. ABLE TO RESTART ENGINE & TAXI BACK TO PARKING W ITHOUT INCIDENT. FOUND THE SCAT HOSE COMING FROM FRONT BAFFLE DOWN TO FRONT OF EXHAUST SHROUD HAD FILLED WITH WATER. 1 H 7 1 3O 3 O 3A19 E252 20090106 EA 2009 1 6 2008FA0000928 2 20081230 G 7414 66LC35SDNP MAGNETO CESSNA 206 206H 2073301 CE LYC O540 TIO540AJ1A EA RIGHT DAMAGED B O OTHER O OTHER UK UNKNOWN 1 NM 07 5880K 594 T20608581 L12173 RT MAGNETO INTERMITTENT, MAGNETO STAYED HOT AND SOME TIMES IT WILL NOT HAVE ANY CURRENT GOING THROUGH. IF PROPELLER WAS MOVE IT WILL FIRE RT UP, AFTER REMOVED RT MAGNETO AND OPENED FOUND THAT THAT COIL HAS MELTED MOST OF THE GEARS AND CASI NG. 1 H 7 1 3O 3 O RT A4CE E14EA 20090106 CE 2009 1 6 2009F00002 1 20081221 G 5610 10138402522 WINDSHIELD BEECH 90 C90 1152913 CE COCKPIT CRACKED G A UNSCHED LANDING O OTHER CR CRUISE 1 CE 01 736EA LJ1478 ACFT LEVELED OFF AT 20,000 FT AFTER APPROX 45 MIN OF FLIGHT, THERE WAS A SUDDEN BANG, AND CO-PILOTS WINDSHIELD INNER PAN E SPIDER WEB CRACKED. FLT CREW DIVERTED TO NEAREST AIRPORT AND LANDED WITHOUT FURTHER INCIDENT. 1 L 7 2 3T 3A20 20090107 CE 2009 1 7 2009FA0000000 1 20081208 G 3250 66429438 BUNGEE CYLINDER CESSNA 560 560XL 2076702 CE MLG MALFUNCTIONED C K NONE O OTHER IN INSP/MAINT 1 SO 13 669TT 740 5684 DURING TAXI, ACFT PULLS TO LT UNCOMMANDED. ALSO INFLIGHT CREW HEARD A RUBBING NOISE FROM THE LT RUDDER PEDAL. CREW ALSO MENTIONED IN FLIGHT THE RUDDER PEDALS FEEL LIKE THERE IS SOMETHING RUBBING. FOUND JAM NUT ON STEERING BUNGEE HAD LOOSEN ED, ALLOWING THE ROD END TO EXTEND ON THE PUSH ROD. REPLACED STEERING BUNGEE WITH NEW UNIT AND RE-RIGGED THE NOSE STEERI NG. IN THE MAINT PROCEDURE 32-50-00 THERE IS NO MENTION OF SECURING THIS ADJUSTMENT (ROD END BEARING, JAM NUT, PUSH ROD) SUCH AS LOCK TITE 732, OR POSSIBLY EVEN BETTER A WAY TO SAFETY THE JAM NUT. REPLACEMENT OF BUNGEE AND RIGGING THE NOSE STEERING FIXED THE PROBLEM. WORK WAS ACCOMPLISHED AT THE MFG SERVICE CENTER. 2 L 7 2 4F RT A22CE 20090108 SW 2009 1 8 2009FA0000002 1 20081218 G 3233 EM411514 ACTUATOR ECLIPS EA500 ECLIPSEEA500 3350000 SW RT MLG FAULTY C K NONE J WARNING INDICATION CL CLIMB 1 SO 19 929KD 134 000240 DURING CLIMB THE RT MLG FAILED TO FULLY RETRACT. GEAR INTRANSIT INDICATED. ON SELECTION OF LANDING GEAR DOWN, RT MLG F AILED TO EXTEND. ALTERNATE GEAR EXTENSION USED AND GEAR EXTENDED FULLY AND "DOWN AND LOCKED" INDICATED. NORMAL LANDING ACCOMPLISHED. ON JACKS THE RT MLG WOULD ONLY RETRACT ABOUT 45 DEGREES AND WOULD NOT EXTEND FULLY WHEN SELECTED. RT ML G ACTUATOR REPLACED AND SYSTEM FUNCTION TESTED NORMAL. 1 L 7 2 4J RT A00002AC 20090120 SO 2009 1 20 2009FA0000004 2 20081210 G 8520 BOLT CESSNA 210 T210L 2073449 CE CONT O520 TSIO520H 17040 SO ENGINE FAILED G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 GL 15 9426K 21060572 506240 DURING CLIMB TO CRUISE ENGINE MADE A LOUD NOISE AND QUIT RUNNING, ENGINE REMAINED WINDMILLING TO LANDING. VISUAL INSP R EVEALED NR 3 CYLINDER ROD BOLT MISSING, ROD CAP EXITED ENG THRU UPPER CASE, NO EVIDENCE OF OIL STARVATION. 1 H 7 1 3O 3 O 3A21 E8CE 20090120 CE 2009 1 20 2009FA0000005 1 20081223 G 2910 S217840095A HOSE CESSNA 210 T210M 2073451 CE CONT O520 TSIO520* 17040 SO HYD SYSTEM BURST B A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION LD LANDING 1 SO 05 732UR 3658 21061789 RT NLG DOOR ACTUATOR HOSE FAILED CAUSING COMPLETE HYD FLUID LOSS . RESULTING IN LT MAIN GEAR NOT ABLE TO BE FULLY EXTEND ED TO DOWN AND LOCKED POSITION. ACFT MADE EMERGENCY LANDING WITH LT MAIN GEAR PARTIALLY EXTENDED. MINOR DAMAGE. FAILE D HOSE APPEARS TO BE ORIGINAL INSTALLED NEW IN 1977. 1 H 7 1 3O 3 O 3A21 E8CE 20090130 CE 2009 1 30 2009FA0000007 1 20081215 G 3233 35810080602 ACTUATOR BEECH 35 A35 1151504 CE MLG FAILED D O OTHER O OTHER LD LANDING 1 GL 15 473AB 368 D1578 INTERNAL FAILURE WITHIN LANDING GEAR ACTUATOR GEARBOX. GEAR WOULD NOT CYCLE DOWN BY NORMAL OR EMERGENCY EXTENSION. EMERG ENCY HANDLE WOULD NOT ENGAGE. COMPONENT WAS OVERHAULED IN 1983. 1 L 7 1 3O A777 20090120 NE 2009 1 20 2009FA0000012 2 20081230 G 7321 2123M55P04 ECU AIRBUS 320 A320214 3930316 EU CFMINT CFM56 CFM565B4P NE NR 2 ENGINE FAULTY C VQIA A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 15 632VA 3155 577893 FLIGHT 515 LAX TO JFK. DURING CRUISE 3 ECAM WARNINGS, THRUST LEVER FAULT, CTL VALVE FAULT, AND ENG2 FADEC A FAULT. AN ASSOCIATED LAND ASAP AMBER ECAM ADVISORY MSG ALSO APPEARED. CREW ADVISED DISPATCH THAT THEY WERE DIVERTING TO LAS. MX FOLLOWED THE TSM FOR THE FAULTS AND FOUND ENGINE 2 CHANNEL A NOT REPORTING DURING ECU TEST. THE ECU WAS REPLACED AND OP S CHECKED OK PER AMM 73-21-60. IAW THE OPERATORS RECORDS, ALL AIRWORTHINESS DIRECTIVES, SERVICE BULLETINS, STC`S AND PM A`S ARE IN FULL COMPLIANCE WITH THE TYPE DESIGN CERTIFICATE AND ASSOCIATED REGULATORY REQUIREMENTS. THE ACFT WAS RELOCA TED BACK TO SFO. N632VA DEPARTED LAS AT 0741Z AND ARRIVED SFO AT 0842Z. NO FAULTS NOTED. 2 L 7 2 4F 4 F RT A28NM E38NE 20090120 EU 2009 1 20 2009FA0000013 1 20081217 G 6120 CONTROL CABLE STBROS SD3 SD360 8100606 EU RT PROPELLER BROKEN C TXHA O OTHER O OTHER NR NOT REPORTED 1 WP 13 808KR SH3734 THE ACFT RT PROP CABLE BROKE. ACFT RETURNED TO HONOLULU STATION FOR INSPECTION AND REPAIR. 2 H 7 2 4T A41EU 20090129 CE 2009 1 29 2009FA0000014 1 20081210 G 3260 ARM CESSNA 414 414 2075908 CE DOWNLOCK BROKEN D K NONE O OTHER LD LANDING 1 GL 19 52CS 4140615 ON LANDING, THE PILOT SELECTED THE GEAR DOWN AND NEVER GOT A GREEN DOWN AND LOCK LIGHT IN THE CABIN FOR THE RT MAIN GEAR . THE GEAR DOWNLOCK MICRO-SWITCH ACTUATOR ARM WAS BROKEN AND WOULD NOT ACTUATE THE MICRO-SWITCH. THESE ACTUATOR ARMS S EEM TO GET WEAK OVER TIME. THERE WAS NO OTHER REASON FOR THE ARM TO FAIL. (K) 1 L 7 2 3O RT A7CE 20090130 CE 2009 1 30 2009FA0000015 1 20081230 G 3240 632750012 TUBE CESSNA 525 525 2076601 CE BRAKE SYS BROKEN B AWOR K NONE O OTHER IN INSP/MAINT 1 GL 15 793CJ 4959 5250021 DURING AN INSP, DOC 10, LANDING GEAR PNEUMATIC BRAKE SYS FUNCTIONAL CHECK ONE OF THE LINES IN THE RT LANDING GEAR WELL B LEW. FURTHER INVESTIGATION FOUND THAT THE 6327500-12 TUBE ASSY BROKE OFF AT THE FLARE ON THE INBD END OF THE TUBE ASSY. INSP OF THE SAME LINE ON THE LT SIDE FOUND NO DEFECTS. (K) 1 L 7 2 4F RT A1WI 20090129 SO 2009 1 29 2009FA0000016 2 20081217 G 8550 652969 PAN CESSNA 414 414A 2075907 CE CONT O550 TSIO550A 41516 SO ENGINE CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 15 414PS 414A0056 800653 OIL LEAK CAME FROM CRACK IN OIL PAN. CAUSE UNKNOWN. ENG TSMOH 95 HRS. CRACK/ FITTING WITH HOSE ATTACHED FOR REMOTE O IL DRAIN. (K) 1 L 7 2 3O 3 O A7CE E5SO 20090130 WP 2009 1 30 2009FA0000017 1 20081223 G 7820 C16932 MUFFLER ROBSIN R44 R44RAVENII 7640122 WP EXHAUST SYSTEM FAILED D K NONE O OTHER IN INSP/MAINT 1 NE 05 1425K 676 10153 MUFFLER CAN BLOW OUT AT TAIL PIPE CONNECTION AND COLLECTOR FAILURES, BULGES AND BLOW OUTS. WEAK MATERIAL, USE THICKER A ND BETTER MATERIAL. PEOPLE ARE GETTING SICK AND/OR BAD HEADACHES. CO DETECTORS ARE SOUNDING OFF IF YOU HAVE ONE. (K) 1 G 7 1 3O H11NM 20090128 WP 2009 1 28 2009FA0000018 1 20081223 G 7810 C1695 COLLECTOR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE IB AREA 3 TO 1 DAMAGED D O OTHER O OTHER NR NOT REPORTED 1 NE 05 417PK 497 11480 EXHAUST COLLECTORS 3 TO 1 TYPE. BULGES AND BLOW OUTS. 1 G 7 1 3O 3 O H11NM 1E4 20090128 CE 2009 1 28 2009FA0000020 1 20081224 G 3260 45A3951141 UPLOCK HOOK BEECH MU300 400A 1155402 CE NLG DISENGAGED B E81R A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 GL 03 175QS 15 AFTER DEPARTING, FLIGHT CREW OBSERVED RED LANDING GEAR UNSAFE LIGHT IN LANDING GEAR CONTROL HANDLE ILLUMINATED AFTER LAN DING GEAR RETRACTION. RETURNED TO DEPARTURE. FOUND NLG UPLOCK HOOK NOT ENGAGING NOSE GEAR STRUT ASSY AS REQUIRED IAW M M 32-30-00. LANDING GEAR RETRACT/ EXTENSION SYS FUNCTION CHECKS IAW MM 32-00-00 OK. SUSPECT ADJUSTMENT CHANGED SLIGHTL Y FROM AS-BUILT RIGGING DUE TO COMPONENTS WEARING IN, HAVE NOTED SIMILAR CONDITION PREVIOUSLY ON OTHER LOW-TIME ACFT. ( K) 2 H 7 2 4F RT A16SW 20090129 SO 2009 1 29 2009FA0000021 1 20081022 G 3230 SE0521903XXX BEARING GULSTM G1159 GIV 3980115 SO NLG LOOSE D O OTHER O OTHER TX TAXI/GRND HDL 1 WP 19 972MS 1285 WHILE TAXIING ACFT, CREW REPORTED POPPING SOUND COMING FROM NOSE WHEEL WELL AND DURING RT TURNS. FOUND NLG DRAG BRACE U PPER ATTACH VERTICAL BEARING AT FS 119, FINGER TIGHT. INSPECTED OTHER ACFT AND FOUND SAME OCCURRENCE. SB 157 HAS BEEN COMPLIED WITH ON 3/09/2004. 2 L 7 2 4F RT A12EA 20090130 EU 2009 1 30 2009FA0000022 1 20081027 G 7921 MS210435 NUT HUGHES 369 369FF 4470709 EU ALLSN 250C 250C30 03013 GL COOLER BLOWER BACKED OUT B GI3R K NONE O OTHER IN INSP/MAINT 1 WP 01 5185G 0009F OIL COOLER BLOWER DRIVEN PULLEY RETAINING NUT IS BACKING OFF OF SHAFT DURING NORMAL USE. NUT IS A STAINLESS STEEL, SILV ER PLATED, ALL METAL SELF LOCKING TYPE NUT. THIS WAS THE 3RD OCCURRENCE OF THIS TYPE FOR OUR UNIT AND WE ARE ALSO AWARE OF ONE OTHER INCIDENT TO ANOTHER COMPANY. WHEN THE NUT BACKS OFF IT CAUSES THE SHAFT BEARING TO GO BAD WHICH DESTROYS THE OIL COOLER BELT. THIS LEADS TO EXTREME ENGINE OIL AND MAIN TRANSMISSION OIL TEMPERATURES. AFTER INVESTIGATING PN, WE FOUND THAT MFG HAS BEEN USING THIS TYPE NUT FOR A LONG TIMEAND WERE UNSURE IF THE NUT CURRENTLY BEING PRODUCED ARE SU BSTANDARD. UNIT WAS O/H. THE O/H FACILITY HAS BEEN INFORMED OF THESE INCIDENTS AND THEY ARE CURRENTLY INVESTIGATING THE 1 G 7 1 3U 3 U H3WE E1GL 20090129 EA 2009 1 29 2009FA0000024 2 20081204 G 7322 25765463 SERVO CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA MCAULY 3D36C B3D36C432 GL ENGINE LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 13 137P 2060804 L3271948E 80VSA1 FUEL SERVO LEAKED WHILE ACFT WAS PARKED OVERNIGHT. THE MIXTURE WAS IN CUT OFF POSITION. FLIGHT MANUAL, SEC 4, NORMAL P ROCEDURES PAGE 4-23 SECURING ACFT NR 10 STATES: FUEL SELECTOR VALVE RT OR LT TO PREVENT CROSS FEEDING. IF THE FUEL SELE CTOR VALVE WAS TURNED TO OFF, THIS WOULD HAVE PREVENTED. THERE IS A POTENTIAL FOR FUEL TO ENTER ENGINE CYLINDERS AND OI L SUMP IF THE FUEL SERVO MIXTURE CUT OFF LEAKS USING FLIGHT MANUAL PROCEDURES. NEED TO ADDRESS: FLIGHT MANUAL PROCEDURE S TO FUEL SELECTOR VALVE OFF. (K) 1 H 7 1 3O 3 O RT A4CE 1E4 5 C P58GL 20090130 CE 2009 1 30 2009FA0000026 1 20081224 G 3600 AA3216CW PUMP BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO LOW PRESSURE B VJ3R O OTHER O OTHER TX TAXI/GRND HDL 1 WP 07 8242T 19 CE1610 830201R PILOT REPORTED INSTRUMENT AIR PRESSURE LOW AT IDLE ON RUN UP. ON TROUBLESHOOTING, THE MECHANIC DETERMINED THE AIR PUMP WAS NOT PRODUCING ENOUGH PRESSURE AT IDLE. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME. (K) 1 L 7 1 3O 3 O 3A15 E5CE 20090130 GL 2009 1 30 2009FA0000027 1 20081219 G 7797 14251001 WIRE HARNESS CIRRUS SR SR22 2130001 GL ENG COMPARTMENT CHAFED B YEBR O OTHER O OTHER NR NOT REPORTED 1 CE 05 961AG 0255 FOUND THE BLACK PLASTIC WIRE LOOM THAT HOUSES THE MAP WIRING HARNESS FWD OF THE BAFFLE TO HAVE CHAFED THROUGH THE WIRE I NSULATION OF THE WIRES IN SEVERAL LOCATIONS. THIS IS CAUSED BY THE WIRE HARNESS BEING ABLE TO MOVE INSIDE THE LOOM AND THE LOOM BEING MADE FROM A HARDER MATERIAL THAN THE WIRE INSULATION. INSTALL NEW WIRE HARNESS AND REMOVE THE PLASTIC L OOM. SECURE WIRES AS NEEDED. (K) 1 L 7 1 3O NT A00009CH 20090130 EA 2009 1 30 2009FA0000028 2 20081205 G 8520 11B200611SH CRANKCASE PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA ENGINE CRACKED B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 4149G 4622 872 2843191 L3630836A FOUND LT FRONT CRANKCASE CRACKED DURING ROUTINE MX. (K) 1 L 7 1 3O 3 O 2A13 E286 20090130 EA 2009 1 30 2009FA0000029 2 20081206 G 8520 11B200615H1 CRANKCASE PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA ENGINE CRACKED B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 4148P 6916 789 2843177 L3616236A FOUND LT FRONT CRANKCASE CRACKED DURING ROUTINE MX. (K) 1 L 7 1 3O 3 O 2A13 E286 20090130 CE 2009 1 30 2009FA0000030 1 20081228 G 2497 CIRCUIT BREAKER LEAR 55 55LEAR 5170702 CE MAIN BUSS MALFUNCTIONED D A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CE 03 242RB 55B132 ACFT DEPARTED, ENROUTE WITH 2 PASSENGERS, 2 HOURS INTO FLIGHT, JUST PRIOR TO INITIAL DESCENT, ACFT EXPERIENCED A COMPLET E ELECTRICAL FAILURE AND LOSS OF PRESSURIZATION AT FL430. FLIGHT CREW REGAINED CONTROL OF PRESSURIZATION AROUND FL330 A ND RESTORED PWR TO NR 1 COMM RADIO. ACFT DIVERTED AND MADE A VISUAL NO-FLAP APPROACH & LANDING. ACFT OVERRAN RUNWAY AP PROX 50 FT INTO MUD. NO PASSENGERS OR CREW WERE INJURED AND ACFT HAD MINOR DAMAGE. AFTER INITAL INSP, SUSPECT LT MAIN BUSS C/B ISSUE BUT UNABLE TO CONFIRM THIS TO BE THE PROBLEM AT THIS TIME. ADDITIONAL INSP AND MAINT NEEDED TO CONFIRM C /B OVERLOAD. (K) 2 L 7 2 4F A10CE 20090205 SO 2009 2 5 2009FA0000036 2 20081013 G 7414 105005563 MAGNETO CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO HARTZL HCJ3Y PHCJ3YF1 GL ENGINE FAILED D A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 GL 09 651BS 235 1711 360237 FP4833B FLIGHT CREW REPORTED ENGINE SPUTTERED DURING INITIAL CLIMB. UPON INTERNAL VISUAL INSP OF LT MAGNETO, FOUND BROKEN MAGNE TO SHAFT BELOW DRIVE GEAR. ALUMINUM MAGNET CASTING FAILED AT STEEL SHAFT MATING JOINT. ROTATION OF STEEL SHAFT IN ALUM INUM CASTING YIELDED EXCESSIVELY RETARDED TIMING. MAGNETO WAS "FACTORY NEW" WITH 235.4 HOURS TT AND HAS NOT BEEN OPENED PRIOR TO THIS EVENT. A REPLACEMENT "FACTORY NEW" MAGNETO OF THE SAME TYPE WAS INSTALLED TO RESOLVE THE PROBLEM. PREVI OUSLY ON 9/9/2008 AT 1112.0 HOURS AIRCRAFT TOTAL TIME, THE RIGHT MAGNETO WAS FOUND TO HAVE FAILED DURING RUN-UP CHECKS W ITH THE SAME FAILURE MODE. 1 L 7 1 3O 3 O NT A00009CH E1CE 5 C P36EA 20090205 SO 2009 2 5 2009FA0000037 2 20081218 G 7414 105005563 MAGNETO CIRRUS SR SR20 05628AJ GL CONT O360 IO360ES SO HARTZL HCJ3Y PHCJ3YF1 GL ENGINE FAILED D D RETURN TO BLOCK Y ENGINE STOPPAGE TX TAXI/GRND HDL 1 GL 09 70RB 351 1653 360157 FP4526B LT MAGNETO FAILED TO SUSTAIN ENG OPS DURING GROUND RUN-UP CHECK. UPON INTERNAL VISUAL INSP, FOUND BROKEN MAGNETO SHAFT BELOW DRIVE GEAR. ALUMINUM MAGNET CASTING FAILED AT STEEL SHAFT MATING JOINT. ROTATION OF STEEL SHAFT IN ALUMINUM CAST ING YIELDED EXCESSIVELY RETARDED TIMING. MAGNETO WAS "FACTORY NEW" WITH 350.9 HOURS TT AND HAS NOT BEEN OPENED PRIOR TO THIS EVENT. A REPLACEMENT "FACTORY NEW" MAGNETO OF THE SAME TYPE WAS INSTALLED TO RESOLVE THE PROBLEM. FOR PRECAUTIONA RY REASONS, THE RT MAGNETO WAS OPENED AND FOUND TO HAVE THE SAME CRACK BEGINNING. IT WAS ALSO REPLACED WITH A "FACTORY NEW" MAGNETO OF THE SAME TYPE. 1 L 7 1 3O 3 O NT A00009CH E1CE 5 C P36EA 20090205 2009 2 5 2009FA0000050 2 20081229 G 7414 M3458 ROTOR MAGNETO BROKEN D O OTHER O OTHER NR NOT REPORTED 1 NM 02 1059 98100916 THE PILOT REPORTED THAT ON CHECKING THE RT MAGNETO THERE WAS AN EXCESSIVE RPM DROP BUT THAT THE ENGINE STILL OPERATED SM OOTHLY ON THAT MAGNETO. UPON DISASSEMBLY OF THE MAG IT WAS FOUND THAT ONE LEG OF THE CAM SLOT ON THE ROTOR SHAFT WAS COM PLETELY BROKEN OFF AT THE BOTTOM OF THE SLOT. (K) 2008031300047 20080313 00047 SO 2008 3 13 21808 1 20080218 G 4910 1159AC30551103 DUCT GULSTM G1159 GIV 3980115 SO APU INLET CRACKED E CLWA K NONE O OTHER IN INSP/MAINT 1 SW 05 589HM 6464 1153 A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM). 2 L 7 2 4F RT A12EA 2008031300045 20080313 00045 SO 2008 3 13 218081153 1 20080218 G 4910 1159AC30551103 DUCT GULSTM G1159 GIV 3980115 SO APU INLET CRACKED E CLWA K NONE O OTHER IN INSP/MAINT 1 SW 05 589HM 6464 1153 A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM). 2 L 7 2 4F RT A12EA 2008020400103 20080204 00103 EA 2008 2 4 22497 2 20080131 G 8530 AEL14995 RETAINER ECI PIPER PA18 PA18 7101802 SO LYC O360 O360C4P 42289 EA PUSH ROD BROKEN B WS9R K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 8780D 186308 L4080536E ENGINE WAS DISASSEMBLED AND INSPECTED FOR PROP STRIKE INSPECTION. DURING TEST CELL OPERATION THE TECHNICIAN NOTICED AN OIL LEAK AT THE NR4 CYLINDER. FURTHER INSPECTION REVEALED THAT THE PUSH ROD TUBE RETAINER BROKE INSIDE THE ROCKER COVER CAUSING THE TUBE AND SEAL TO FALL OUT OF POSITION. 1 H 7 1 3O 3 O 1A2 E286 20080520 CE 2008 5 20 2568 1 20080501 G 3240 215286 BRAKE ASSY CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE RT MLG BROKEN G O OTHER O OTHER TX TAXI/GRND HDL 1 SO 19 330DK 5500266 RT MLG BRAKE LOCK UP DURING TAXI. AN INSP BY MAINT HAS DETERMINED THAT THE BRAKE STATOR CAME APART AND LOCKED UP THE BR AKE. THE C/A GIVEN WAS FOR THE REMOVAL AND REPLACEMENT OF THE OF THE RT WHEEL AND TIRE ASSY AND BRAKE. A GEAR SWING WAS ALSO PERFORMED IAW MM 32-00. 1 L 7 2 4F 4 F A22CE E1NE 2008041400014 20080414 00014 EU 2008 4 14 325 1 20080325 G 3233 D52177 HOLDER MESSIER AMD FALC20 FALCON200 2730150 EU ACTUATOR BROKEN B GQRR O OTHER K FLUID LOSS LD LANDING 1 SW 05 DRI76878 THE PACKING HOLDER BROKE IN 2 PIECES CAUSING HYDRAULIC FLUID LOSS. THIS PART HAD BEEN MODIFIED IAW SB F200-110 TO PREVE NT FUTURE FAILURES. THIS IS THE SECOND PACKING HOLDER FOUND TO BE BROKEN AFTER MODIFICATION. BOTH PARTS WERE MODIFIED A ND IDENTIFIED SDR IAW THE SB. 2 L 7 2 4F RT A7EU 2008020400107 20080204 00107 2008 2 4 43385883 4 20080129 G 3460 8220868044 FMC RAYTHN DH125 HAWKER800XP 7150012 CE GARRTT TFE731 TFE7315BR WP MALFUNCTIONED C O OTHER F FLT CONT AFFECTED CR CRUISE 1 EA 23 808BL 258634 UNCOMMANDED 360 DEGREE TURN AS COMMANDED BY THE FMS. SB 0057-05 DATED DECEMBER 21, 2005 DELETING A WAYPOINT MAY CAUSE T HE FMS TO INSERT AND FLY AN UNINTENDED TURN. KNOWN PROBLEM WITH OPTIONAL SOLUTION FOR FMS6000 NO SOLUTION FOR FMS5000 I NSTALLED IN AC. 2 L 7 2 4F 4 F RT A3EU E6WE 2008040200014 20080402 00014 2008 4 2 433858831 4 20080129 G 3461 8220891008 FMC BEECH MU300 400A 1155402 CE GARRTT TFE731 TFE7315BR WP FAULTED C O OTHER F FLT CONT AFFECTED CR CRUISE 1 EA 23 808BL RK367 UNCOMMANDED 360 DEGREE TURN AS COMMANDED BY THE FMS. REF SB 0057-05 DATED DECEMBER 21, 2005 DELETING A WAYPOINT MAY CAU SE THE FMS TO INSERT AND FLY AN UNINTENDED TURN. KNOWN PROBLEM WITH OPTIONAL SOLUTION FOR FMS6000 INSTALLED IN AC, NO S OLUTION FOR FMS5000 INSTALLED IN AC. 2 H 7 2 4F 4 F RT A16SW E6WE 20080710 EU 2008 7 10 5APR577Y1 1 20080515 G 3242 244755 BRAKE DISC BFGOODRICH PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL RT MLG BROKEN B 5APR K NONE O OTHER IN INSP/MAINT 1 EA 65 591AF 1174 1174 0137 591 PR0454 KX164 DURING AN ANNUAL INSPECTION THE RIGHT MAIN WHEEL WAS REMOVED TO REPACK THE WHEEL BEARINGS WHEN IT WAS DISCOVERED THAT TH E OUTBOARD BRAKE DISK ON THE RIGHT BRAKE WAS BROKEN INTO TWO PIECES. THE BRAKE ASSEMBLY WAS REMOVED AND REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20080710 EU 2008 7 10 5APR577Y2 1 20080515 G 3242 244755 BRAKE DISC BFGOODRICH PILATS PC12 PC1247 7090552 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL LT MLG BROKEN B 5APR K NONE O OTHER IN INSP/MAINT 1 EA 65 729AF 1566 0599 729 PR0603 KX359 DURING ANNUAL INSPECTION THE LEFT MAIN WHEEL WAS REMOVED TO REPACK THE BEARINGS AND THE TWO OUTBOARD BRAKE DISCS ON THE LEFT BRAKE WERE FOUND TO BE BROKEN. REMOVED AND REPLACED BRAKE ASSEMBLY. 1 L 7 1 4T 4 T RT A78EU E26NE 5 C P210NE 20080710 EU 2008 7 10 5APR577Y3 1 20080515 G 3242 244755 BRAKE DISC BFGOODRICH PILATS PC12 PC1247 7090552 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL RT MLG BROKEN B 5APR K NONE O OTHER IN INSP/MAINT 1 EA 65 729AF 1566 0593 729 PR0603 KX359 DURING ANNUAL INSPECTION RIGHT MAIN WHEEL WAS REMOVED TO REPACK BEARINGS AND THE MIDDLE BRAKE DISC WAS FOUND TO BE BROKE N. REMOVED AND REPLACED BRAKE ASSEMBLY. 1 L 7 1 4T 4 T RT A78EU E26NE 5 C P210NE 2008041400016 20080414 00016 CE 2008 4 14 6001LENG 1 20080327 G 5415 555415046810 ATTACH ANGLE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ENGINE CORRODED B K NONE O OTHER IN INSP/MAINT 1 SW 17 6001L 10071 5500169 ENGINE NACELLE ATTACHING FITTING ANGLE REMOVED FOR CORROSION. PARTS ARE CADMIUM PLATED, BUT NOT PAINTED. ALSO DISCOVERY IMPROPER DRILL HOLES AND RIVET SET DAMAGE AROUND SEVERAL HOLES. 1 L 7 2 4F 4 F A22CE E1NE 2008050800053 20080508 00053 CE 2008 5 8 6001LOXYGEN 1 20080423 G 3510 176174 OXYGEN BOTTLE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE NOSE LEAKING C K NONE O OTHER IN INSP/MAINT 1 SW 17 6001L 5500169 INSTALLED REPAIRED EMERGENCY OXYGEN BOTTLE IN AC AND SERVICED. WHEN BOTTLE WAS TURN ON WAS FOUND TO LEAK FROM ON-OFF VA LVE. UNIT WAS REPAIRED ON JANUARY 21,2008. 1 L 7 2 4F 4 F A22CE E1NE 20080717 CE 2008 7 17 772AF 1 20080603 G 3610 13022 CHECK VALVE BEECH 200 B200 1152922 CE BLEEDD AIR SYS DEFECTIVE B VIBR K NONE O OTHER IN INSP/MAINT 1 SO 13 772AF 5763 BB1001 FLAPPERS IN BLEED AIR INLET CHECK VALVE CAME LOOSE AND CHAFED THE INSIDE OF THE HOUSING. ONE FLAPPER CHAFED A HOLE THRO UGH THE HOUSING. 1 L 7 2 4T A24CE 20080902 CE 2008 9 2 842008N341CS 1 20080730 G 3240 BRAKE CESSNA 500 550 2076604 CE MLG CONTAMINATED C O OTHER O OTHER AP APPROACH 1 EA 63 341CS 5501106 THE LOW BRAKE PRESSURE AND ANTI-SKID INOP ANNUNCIATORS ILLUMINATED IN FLIGHT. AN EMERGENCY WAS DECLARED. DURING LANDIN G ROLL OUT BRAKE PRESSURE CAME BACK AND LIGHTS EXTINGUISHED. THE BRAKES WERE BLED, A SMALL AMOUNT OF AIR NOTED. OPERAT IONAL CHECK OK. ACFT MADE THREE TAKEOFFS AND LANDINGS WITH NO DEFECTS NOTED. ACFT RETURNED TO SERVICE. (S) 1 L 7 2 4F A22CE 2008022500006 20080225 00006 SW 2008 2 25 901012008 1 20080217 G 5210 S16206327957 DOOR SKRSKY S58T S58T 8141800 SW PWA PT6T PT6T6 52045 EA MAIN DEPARTED L O OTHER D INFLIGHT SEPARATION CR CRUISE 1 GL 23 901CH 15313 15313 581464 DURING POSTFLIGHT INSP, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSP OF AC FOUND NO DAMAGE OR MISSING CO MPONENTS OTHER THAN DOOR. REPLACEMENT DOOR WAS INSTALLED AND OPS CHECKED WITH NO DISCREPANCIES NOTED TO AIRFRAME, DOOR M OUNTING, STRUCTURE AND DOOR OPERATION. AC WAS RETURNED TO SERVICE. 2 G 7 1 4U 4 U NC 1H11 E22EA 2008031900266 20080319 00266 SW 2008 3 19 9010208 1 20080217 G 5210 S16206327957 DOOR SKRSKY S58T S58T 8141800 SW PWA PT6T PT6T6 52045 EA ZONE 800 DEPARTED L O OTHER D INFLIGHT SEPARATION CR CRUISE 1 GL 23 901CH 15313 15313 581464 DURING POSTFLIGHT INSPECTION, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSPECTION OF AIRCRAFT FOUND NO DA MAGE OR MISSING COMPONENTS OTHER THAN DOOR. REPLACEMENT DOOR WAS INSTALLED AND OPS CHECKED WITH NO DISCREPANCIES NOTED T O AIRFRAME, DOOR MOUNTING, STRUCTURE AND DOOR OPERATION. AIRCRAFT WAS RETURNED TO SERVICE. 2 G 7 1 4U 4 U NC 1H11 E22EA 2008030600249 20080306 00249 SW 2008 3 6 901CHI0208 1 20080221 G 5210 S16206327957 DOOR SKRSKY S58T S58T 8141800 SW PWA PT6T PT6T6 52045 EA DEPARTED L O OTHER D INFLIGHT SEPARATION CR CRUISE 1 GL 23 901CH 15313 15313 581464 DURING POSTFLIGHT INSPECTION, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSP OF AC FOUND NO DAMAGE OR MISS ING COMPONENTS OTHER THAN DOOR. REPLACEMENT DOOR WAS INSTALLED AND OPS CHECKED WITH NO DISCREPANCIES NOTED TO AIRFRAME, DOOR MOUNTING, STRUCTURE, AND DOOR OPERATION. AIRCRAFT WAS RETURNED TO SERVICE. 2 G 7 1 4U 4 U NC 1H11 E22EA 20080520 CE 2008 5 20 90XR042708 1 20080427 G 2910 AS62306H0073 LINE LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP HYDRAULIC SYS CHAFED E T6FA A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 GL 09 90XR 342 2090 DURING CRUSE FLIGHT THE PILOTS NOTED THAT MAIN HYDRAULIC SYSTEM LOST PRESSURE. INITIATED AN UNSCHEDULED LANDING. AFTER INSPECTION, THE LT ENGINE DRIVEN HYDRAULIC PRESSURE PUMP LINE WAS LEAKING. THE PRESSURE LINE AND BOTH HYDRAULIC PUMPS WERE REPLACED, WITH NEW PARTS, IAW THE MM. 2 L 7 2 4F 4 F RT T00008WI E6WE 20081209 WP 2008 12 9 AALA200810280 1 20081112 G 5320 INTERCOSTAL DOUG DC9 DC983 3022083 WP ZONE 100 CRACKED A AALA K NONE O OTHER IN INSP/MAINT 1 SW 21 9401W 53137 INTERCOSTAL CRACKED IN CEILING OF MID CARGO. REPLACED INTERCOSTAL. 2 L 7 2 4F RT A6WE 20080903 NM 2008 9 3 ABXR080225 1 20080729 G 5330 SKIN BOEING 767 767223 1385123 NM BS 615 S34R DAMAGED C ABXR K NONE O OTHER IN INSP/MAINT 1 GL 23 761CX 22318 SCREW AND COUNTERSINK WASHER INSTALLED IN FUSELAGE SKIN OVER PREVIOUSLY BLENDED AREA AT APPROX STA 615 LONGERON STRINGER 34 RT. DAMAGED AREA COMPLIED WITH ON PREVIOUS REPAIR. (S) 2 L 7 2 4F RT A1NM 20080903 NM 2008 9 3 ABXR080226 1 20080731 G 5330 146T35111 SKIN BOEING 767 767223 1385123 NM BS 1510 S35-36L DAMAGED C ABXR K NONE O OTHER IN INSP/MAINT 1 GL 23 761CX 22318 APPROX 6 INCH CREASE AT STA 1510, LONGERON STRINGER 36-35 LT, BELOW BULK CARGO DOOR IS OUT OF LIMITS. REPAIRED SKIN IAW B767-200 SRM 53-60-1. (S) 2 L 7 2 4F RT A1NM 20080903 NM 2008 9 3 ABXR080228 1 20080801 G 5330 143T35211 SKIN BOEING 767 767223 1385123 NM BS 544 S30-31L DENTED C ABXR K NONE O OTHER IN INSP/MAINT 1 GL 23 761CX 22318 OUTWARD DENT STA 544, STRINGER 31-30 LT REQUIRES REPAIR. REPAIRED AREA IAW B767 SRM 53-00-01, FIGURE 201. (S) 2 L 7 2 4F RT A1NM 2008040400016 20080404 00016 EA 2008 4 4 ACOR032408001 2 20080324 G 7322 383493 PLUG PREAIR RSA5 CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FUEL SERVO LOOSE B ACOR K NONE O OTHER IN INSP/MAINT 1 EA 39 2162Y 1618 70402806 172S9529 L3118151A FUEL SERVO REGULATOR HEX PLUG LOOSE ON NON AFFECTED SERVO RSA-5 S/N 70402806. DATA REFERENCED AD 2008-06-51 E, SB 08-73 -01, AND PRECISION SB PRS-107. SERVO HAS NOT BEEN NEW, REBUILT, OVERHAULED, OR REPAIRED ON OR SINCE AUGUST 22, 2006. 1 H 7 1 3O 3 O NT 3A12 1E10 2008040400017 20080404 00017 EA 2008 4 4 ACOR032508001 2 20080325 G 7322 383493 PLUG PREAIR RSA10ED1 CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA FUEL SERVO LOOSE B ACOR K NONE O OTHER IN INSP/MAINT 1 EA 39 377HA 604 70259806 T20608499 L1183961A FUEL SERVO REGULATOR HEX PLUG LOOSE ON NON AFFECTED SERVO RSA-10 S/N 70259806. DATA REFERENCED AD 2008-06-51 E, SB 08-73 -01, AND PRECISION SB PRS-107. SERVO HAS NOT BEEN NEW, REBUILT, OVERHAULED, OR REPAIRED ON OR SINCE AUGUST 22, 2006 1 H 7 1 3O 3 O RT A4CE E14EA 2008041000201 20080410 00201 CE 2008 4 10 AMCR200800001 1 20080331 G 7312 79646 HEATING ELEMENT CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL RT ENGINE FAILED B AMCR O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 GL 09 279DV 636 070 141148 PILOT REPORTED T2 HEATER FAIL ON RT ENGINE. FOUND T2 PROBE BAD. 1 L 7 2 4F 4 F RT A1WI E3GL 2008040400009 20080404 00009 CE 2008 4 4 B3OR20080079 1 20080318 G 3233 991206313 ACTUATOR CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE MLG OUT OF POSITION B B3OR D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 SW 03 26621 8 5500593 AIRCREW REPORTED LANDING GEAR WARNING HORN SOUNDED AND GEAR-IN-TRANSIT INDICATOR ILLUMINATED AS AIRCRAFT WAS BEING TOWED OVER A BUMP (HANGAR THRESHOLD). SCHEDULED FLIGHT WAS CANCELLED. MAINTENANCE CREW WAS ABLE TO DUPLICATE EVENT BY SLIGH T ACCELERATION OF TOW VEHICLE AND OBSERVED NOSE GEAR DOWN AND LOCKED INDICATOR ALSO EXTINGUISHED IN CONJUNCTION WITH THE OTHER REPORTED INDICATIONS. THE ACTUATOR DEFLECTION TEST IN THE AIRFRAME MM WAS ACCOMPLISHED TO DETERMINE THE SERVICEA BILITY OF THE ACTUATOR'S INTERNAL DOWNLOCK MECHANISM WITH SATISFACTORY RESULTS. DOWNLOCK INDICATOR SWITCH ADJUSTMENT CO ULD NOT BE VERIFIED DUE TO AN ABSENCE OF REQUIRED TESTING EQUIPMENT. THE RECENTLY OVERHAULED ACTUATOR WAS REMOVED FOR R 1 L 7 2 4F 4 F A22CE E1NE 2008040200009 20080402 00009 NE 2008 4 2 B3OR2008030 2 20080125 G 7321 0164548240 FCU SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE ENGINE LEAKING B B3OR K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 5204J 176 3118 9318 FUEL CONTROL UNIT IS LEAKING FUEL FROM A DIAPHRAM BREATHER HOLE IN THE CASING. THE LEAKING HOLE IS LOCATED BELOW AND SL IGHTLY IB OF THE PRESSURE REDUCING VALVE ATTACHED TO THE FCU.FUEL LEAK WAS INITIALLY OBSERVED AS A SEEP, PROGRESSING T O A LOW PRESSURE STEADY TRICKLE THROUGHOUT MULTIPLE ENGINE RUNS. ALL OTHER FUEL CONTROL FUNCTIONS WERE OPERATING NORMAL LY. 1 G 7 1 3U 3 U H9EU E19EU 2008040300038 20080403 00038 EU 2008 4 3 B3OR2008046 1 20080213 G 2910 704A44831141 SERVO CONTROL SNIAS 350 AS350B2 8680813 EU LT HYD SYSTEM LEAKING B B3OR K NONE K J FLUID LOSS WARNING INDICATION IN INSP/MAINT 1 SW 03 5204J 5313 2137 3118 ON A ROUTINE PREFLIGHT INSPECTION, THE LT HYDRAULIC ROLL CONTROL SERVO WAS DISCOVERED TO BE LEAKING HYDRAULIC FLUID AT T HE PISTON SHAFT SEAL. THE LEAK COULD NOT BE DUPLICATED DURING GROUND TESTING WITH A HYDRAULIC POWER CART IAW THE MM INS TRUCTIONS. SUBSEQUENT FLIGHT TESTING REVEALED THE LEAK PERSISTING WITH A LEAK RATE SUSPECTED TO BE SLIGHTLY OUT OF LIMI TS. OF PARTICULAR NOTE: THE LEAK COULD ONLY BE DUPLICATED WHILE ACTUAL FLIGHT LOADS WERE INDUCED. ASIDE FROM THE LEAK, THE HYDRAULIC SERVO WAS REPORTED TO BE FUNCTIONING NORMALLY. UNIT WAS REPLACED. 1 G 7 1 3U H9EU 20081124 NM 2008 11 24 B62R20081106002 1 20081106 G 5411 313W181338113813 SPAR BOEING 777 777236 1385220 NM NR 2 PYLON CORRODED B B62R K NONE O OTHER IN INSP/MAINT 1 EA 21 702BA 35345 27108 NR 2 ENG PYLON STRUT, AFT FAIRING HEAT SHIELD LOWER SPAR STRUCTURE, PITTING CORROSION FOUND THROUGHOUT SPAR STRUCTURE, C HORDS, FRAMES 3, 4 & 5. EVIDENCE OF PITTING CORROSION AND HEAT DAMAGE ON LOWER SIDE OF WEBS. REF 54-51-71 PG 6. POSSI BLE CAUSE WAS AFT FAIRING HEAT SHIELD THERMAL BLANKETS 1 THRU 6 WERE TORN AND WATER LOGGED, SEALS DAMAGED AND STRUT DRAI N CLOGGED. REF AMM 54-54-01 PG 426, 54-54-03 PG 406 AND 54-55-01. AD 2002-07-07 AND SB 777-54A0017 ARE RELATED TO THIS BUT HAVE NOT BEEN ACCOMPLISHED. COMPLIANCE WITH AD WILL CORRECT CONDITION. NOTE: STRUT DRAIN WAS CLOGGED. PRIMARY F IRE SEAL DAMAGED. HEAT SHIELD SEAL DAMAGED. SECONDARY FLUID SEAL DAMAGED. PARTS WILL REQUIRE REPAIR OR REPLACEMENT. 2 L 7 2 4F RT T00001SE 20081124 NM 2008 11 24 B62R20081107003 1 20081107 G 5411 313W3813X FRAME BOEING 777 777236 1385220 NM PYLON CRACKED B B62R K NONE O OTHER IN INSP/MAINT 1 EA 21 702BA 35345 27108 NR 1 & NR 2 ENG PYLON, STRUT AFT FAIRING HEAT SHIELD SPAR STRUCTURE, NR 5 FRAME P/N 313W3813-X HAS A 4.50 INCH CRACK ON THE LOWER AFT INBD CORNER. CRACK IS IN THE SAME LOCATION ON BOTH NR 1 & NR 2 ENG PYLON FRAMES. NR 2 ENG PYLON FRAMES N R 1 THRU NR 4, P/N'S 313W1813-X & 313W3813-X HAVE EVIDENCE OF HEAT DAMAGE AND SURFACE CORROSION. REF SRM 54-51-71 FIGUR E 4. POSSIBLE CAUSE WAS AFT FAIRING HEAT SHIELD THERMAL BLANKETS NR 1 THRU NR 6 (NR 2 ENG PYLON) AND NR 6 (NR 1 ENG PYL ON) WERE TORN AND WATER LOGGED. REF AMM 54-54-01 PG 426, 54-54-03 PG 406 AND 54-55-01 PG 623. AD 2002-07-07 AND SB 777 -54A0017 ARE RELATED TO THIS BUT HAVE NOT BEEN ACCOMPLISHED. COMPLIANCE WITH AD WILL CORRECT CONDITION. 2 L 7 2 4F RT T00001SE 20081121 NM 2008 11 21 B62R20081121001 1 20081106 G 5320 149W1129111037 INTERCOSTAL BOEING 777 777236 1385220 NM FUSELAGE CORRODED B B62R K NONE O OTHER IN INSP/MAINT 1 EA 21 702BA 35345 27108 SECTION 43 WING TO BODY FAIRING STRUCTURE LT SIDE. INTERCOSTALS THAT SUPPORT THE FWD WING TO BODY FAIRINGS HAVE MODERAT E TO SEVERE CORROSION. SURFACE, PITTING, GALVANIC AND EXFOLIATION CORROSION ARE EVIDENT ON THE UPPER AND LOWER FLANGES COMMON TO THE NUT PLATES. THERE IS EVIDENCE OF MOISTURE AND STANDING WATER IN THE AREA FROM STA 888 TO STA 1040 LT SIDE . SOME INTERCOSTALS WILL REQUIRE REPAIR OR REPLACEMENT. REF SRM 53-30-71-01-1. 2 L 7 2 4F RT T00001SE 2008022500241 20080225 00241 2008 2 25 CA080101001 4 20080101 G 3418 501177003 ACTUATOR CNDAIR CL600 CL6002D24 1390016 EA GE CF34 CF348C5B1 30052 NE STICK PUSHER MALFUNCTIONED W O OTHER F FLT CONT AFFECTED LD LANDING 1 CA (CAN) ONLY ON LANDING WHEN THE PILOTS HAVE FLARED THE NOSE UP AND THE MLG HITS THE GROUND DOES THE ELEVATOR SEEM TO LOCK UP PREVENTING THE PILOTS FROM PRESSING THE NOSE DOWN TO LAND. TOOK THE COVER OFF THE REMOVED STICK PUSHER ACTUATOR AND FOUND : 1) NOTICE THE TEETH MARKS AT THE SUPPORT POST NEXT TO THE GEAR. 2) SET SCREW WHICH IS STUCK TO THE MOTOR, THIS IS WHAT WE HEARD WHEN SHAKING THE UNIT. 3) THE SCREW WHICH WAS BOUNCING AROUND INSIDE THE BOX, LOOKS LIKE AT SOME POINT IT WAS JAMMED BETWEEN THE DRIVE GEAR AND SUPPORT POST AS EVIDENCED BY TEETH MARKS ON THE SUPPORT POST. (TC NR 200801010 01) 2 L 7 2 4F 4 F RT A21EA E00063EN 2008022500250 20080225 00250 EA 2008 2 25 CA080102001 1 20080101 G 2750 601R930507 FCU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS UNSERVICEABLE W O OTHER F J FLT CONT AFFECTED WARNING INDICATION LD LANDING 1 CA (CAN) ON APPROACH, GOING THROUGH 6500FT AT 200KTS, FLAP FAIL MESSAGE ILUMINATED WHEN SELECTED FROM 0 TO 8 DEGREES. FLAPS DID NOT MOVE, REMAINED AT 0 DEGREES. FLAPLESS LANDING CARRIED OUT WITHOUT FURTHER INCIDENT. NOTE: NO SKEW DETECTION LIG HTS WERE ILLUMINATED. FAULT CODES RETRIEVED AND HAVE DETERMINED THAT THE NR1 FECU IS AT FAULT. FECU CHANGED IAW THE AMM 27-51-0. RIG AND FUNCTION CHECKS CARRIED OUT, NO FURTHER MESSAGES OR CODES. AIRCAFT RETURNED TO SERVICE AND NO FURTHER I SSUES NOTED. (TC NR 20080102001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500252 20080225 00252 CE 2008 2 25 CA080102002 1 20080101 G 5753 3516505035 BRACKET BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCD4N3 HCD4N3A GL TE FLAPS WORN W K NONE O OTHER IN INSP/MAINT 1 CA 6626 (CAN) FLAPS REMOVED TO INSPECT FLAP BRACKETS (HINGES) TO PREVENT A POSSIBLE FAILURE ( REFERENCE SDR 20071025007). BOTH O B FLAPS WERE WORN IN THE SAME LOCATION THAT FAILED OTHER AC. ON BOTH OB FLAPS, THE OB HINGE, IB BRACKETS P/N: 35165050-3 5 (LT) AND 35-165050-34 (RT), AND THE IB HINGE, OB BRACKET P/N: 35-165050-30 (LT) AND 35-165050-31 (RT). (TC NR 20080102 002) 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2008022500256 20080225 00256 EA 2008 2 25 CA080102006 1 20080101 G 5610 NP13932114 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT BROKEN W O OTHER O OTHER CR CRUISE 1 CA (CAN) (RT WINDSHIELD SHATTERED IN FLIGHT). THE WINDSHIELD WAS REMOVED AND REPLACED. WINDSHIELD, (RT) P/N OFF: 601R330 33-14 P/N ON: NP-139321-14 S/N OFF: 02277H7295 S/N ON: 07212H4821 (TC NR 20080102006) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500263 20080225 00263 SW 2008 2 25 CA080103007 1 20080103 G 6720 NAS130410 BOLT BELL 206001044 BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL T/R PEDAL BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON INSPECTION OF THE AIRCRAFT IT WAS NOTED THAT THE (1) OF THE (3) BOLTS WAS BROKEN AND THE OTHERS SHOWED SIGNS OF CORROSION ALL (3) BOLTS WHERE REPLACED WITH NEW. (TC NR 20080103007) 1 G 7 1 3U 3 U H2SW E4CE 2008022500265 20080225 00265 EA 2008 2 25 CA080104001 1 20080103 G 2750 855D10096 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS UNSERVICEABLE W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) CREW FLYING AT LEVEL 340 FOR 30 TO 40 MIN AND THE FLAP FAIL CAME ON WITH NO SELECTION, FLAPS AT 0 DEG. O FLAP LAND ING. TEMP AT ALTITUDE WAS -60 DEG. FERRIED BOTH BPSU`S REPLACED FLAPS FUNCTIONED CHECKED SER (804406 1/4/2008 06:57) (T C NR 20080104001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008031900171 20080319 00171 EA 2008 3 19 CA080104004 1 20080101 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAILED W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 14801 10343 (CAN) DURING PUSH BACK CREW SELECTED FLAPS TO 20 DEGREES AND RECEIVED A FLAP FAIL CAUTION MESSAGE. MAINT TROUBLESHOOTING LED TO REPLACEMENT OF RT BRAKE POSITION SENSOR UNIT (BPSU) AND RIGGING OF LT AND RT BPSU’S. OF NOTE THE FIRST NEWLY INS TALLED RT BPSU (S/N 172, TSN 17175, TSO 4879, CYCLES 3697) HAD TO BE REPLACED AS IT FAILED THE ELECTRICAL RIGGING. (TC N R 20080104004) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500268 20080225 00268 SW 2008 2 25 CA080104005 1 20080104 G 6220 206011101109 YOKE 206L1 BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL M/R HUB INCORRECT W K NONE O OTHER IN INSP/MAINT 1 CA 10379 135 GDLM53264 (CAN) FOUND TO BE WRONG, YOKE M/R HUB ASSY, WITH THE INCORPORATION OF STC NR SH296NM, INSTALLATION OF ENGINE. CORRECT PN OF YOKE SHOULD BE 206-011-149-101. (TC NR 20080104005) 1 G 7 1 3U 3 U H2SW E1GL 2008022500269 20080225 00269 NM 2008 2 25 CA080105002 1 20080102 G 2910 992236H18697 SWITCH DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYD SYSTEM BROKEN W O OTHER J WARNING INDICATION DE DESCENT 1 CA (CAN) SDR BEING SUBMITTED DUE TO (3) OCCURRENCES OF (RUD PRESS) AND (RUD FULL PRESS) CAUTION MESSAGES OVER A PERIOD OF ( 4) DAYS. (1ST) EVENT OCCURRED DECEMBER 30, 2007 JUST AFTER TAKEOFF AND CAUSED AN AIR TURN BACK TO THE DEPARTURE AIRPORT. MAINT PERFORMED GROUND CHECK, THEN AN OPS CHECK IAW AMM 27-30-38 WITH NO FAULTS FOUND. (2ND) EVENT OCCURRED ON DECEMBER 31, 2007 AGAIN JUST AFTER TAKEOFF. AC RETURNED TO AIRPORT OF DEPARTURE. MAINT TROUBLESHOOTING FOUND RUDDER PRESSURE DRO PS APPROXIMATELY 800-1000 PSI ON NR 1 HYD SYS. RUDDER PRESSURE REGULATOR REPLACED BUT WITH NO FIX. NR 1 HYD SYS BLED AN D ALSO NO FIX. NR 1 LWR ACTUATOR (PN 11200-1 SN UNK) WAS REPLACED AND OPERATION CHECKED IAW AMM 27-20-01 PG 215. (3RD) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008022500271 20080225 00271 WP 2008 2 25 CA080105003 1 20080101 G 8011 BC31510040 STARTER ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INOPERATIVE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 679 (CAN) ENGINE WOULD NOT START, STARTER NOT ENGAGING. SERVICEABLE STARTER INSTALLED, ENGINE STARTED WITH OUT FURTHER INCID ENT. (TC NR 20080105003) 1 G 7 1 3O 3 O H11NM 1E4 2008031900173 20080319 00173 EA 2008 3 19 CA080106001 1 20080104 G 2150 78279015 ACM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE NR 1 SMOKE W C ABORTED TAKEOFF B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TO TAKEOFF 1 CA (CAN) SMOKE IN COCKPIT AND CABIN ON T/O ROLL. DURING T/O ROLL, SMOKE APPEARS IN THE COCKPIT AND CABIN FIRSTS ROWS. ABOR TED T/O, RETURN TO BLOCKS. ACM NR1 DETERMINED TO BE THE SOURCE OF THE SMOKE. ACM NR1 DEFERRED IAW MMEL 21-51-1. (TC NR 2 0080106001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008031900175 20080319 00175 EA 2008 3 19 CA080106003 1 20080103 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS INOPERATIVE W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA (CAN) FLAP FAIL MESSAGE DISPLAYED WHILE AC PARKED AT THE GATE. TROUBLESHOOTING REVEALED BRAKE AND POSITION SENSOR UNIT ( BPSU) RT AND LT OUT OF LIMITS. MAINTENANCE RIGGED LT BPSU AND REPLACED RT BPSU. (TC NR 20080106003) 2 L 7 2 4F 4 F RT A21EA E15NE 2008031900178 20080319 00178 EA 2008 3 19 CA080106004 1 20080102 G 3260 895001 PROXIMITY SENSOR CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C5 30050 NE NLG MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) AFTER TAKEOFF, A LANDING GEAR DISAGREE WARNING MESSAGE WAS DISPLAYED. CREW CYCLED THE GEAR UNTIL SELECTED DOWN AND GEAR LOCKED DOWN INDICATION (3 GREEN LIGHTS). AC PERFORMED A TURNBACK AND LANDED UNEVENTFULLY (AFTER FUEL DUMPING FOR N OT LANDING OVERWEIGHT). TROUBLESHOOTING PINPOINTED TO THE WEIGHT OFF WHEELS NR 2 SENSOR (PX 11), BEING OFF RIGGING LIMIT S. MAINT PERFORMED RE-RIGGING FOLLOWED BY A SUCCESSFUL GROUND TESTS AND AC RETURNED TO SERVICE. AIRFRAME HOURS=7855:04. CYCLES=3748. (TC NR 20080106004) 2 L 7 2 4F 4 F RT A21EA E00063EN 2008022500272 20080225 00272 EU 2008 2 25 CA080107001 1 20080107 G 6410 355A12004008 BLADE SNIAS 350 AS350B2 8680813 EU LYC LTS101 LTS101* NE TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1592 1592 (CAN) ON DAILY INSPECTION, A CRACK IN THE TRAILING EDGE OF THE TIP OF THE TAILROTOR ASSY WAS FOUND. THE CRACK WAS APPROX .5 INCH LONG FROM TIP OF BLADE LEADING TO T/E ON A DIAGONAL. SUSPECT THIS CRACK, IF LEFT, WOULD HAVE CAUSED THE TRAILI NG EDGE CORNER APPROX .7500 OF AN INCH TO DEPART FROM TIP OF THE BLADE. THIS WAS FOUND ON BOTH BLADES ONE BLADE MORE SEV ERE THAN THE OTHER. THERE WAS NO INDICATION OF A TAILROTOR IMPACT. (TC NR 20080107001) 1 G 7 1 3U 3 U H9EU E5NE 2008022500273 20080225 00273 CE 2008 2 25 CA080107002 1 20080103 G 2497 BUSS BAR BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCE4N HCE4N3 NE ELECTRICAL LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 354 (CAN) WHILE PERFORMING SB 24-3871, AN EXTRANEOUS BUSS BAR WAS OBSERVED IN THE RT CB PANEL BETWEEN CB 140 AND CB 255. THI S BUSS BAR WAS ATTACHED ONLY AT ONE END AND WAS LOOSE. NOTE, THE SB ONLY REQUIRES INSPECTION FOR AN EXTRA BUSS BAR BETWE EN CB 327 AND 166. INSPECTION OF BB-1974 SHOWED NO EXTRANEOUS BUSS BARS INSTALLED. (TC NR 20080107002) 1 L 7 2 4T 4 T A24CE E4EA 5 C P10NE 2008020400119 20080204 00119 CE 2008 2 4 CA080107003 1 20080107 G 3230 1018100327 TORQUE KNEE BEECH 200 B200 1152922 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL LT MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE PERFORMING AN INSPECTION ON THE GEAR IT WAS NOTICED THAT GREASE WAS COMING FROM THE HORIZOTAL CRACK IN THE B OTTOM OF THE TORQUE KNEE. A NEW KNEE WAS ORDERED AND REPLACED. (TC NR 20080107003) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2008020400118 20080204 00118 NM 2008 2 4 CA080107004 1 20080102 G 6420 A0311 BEARING ROBSIN R22 R22BETA 7640110 NM LYC O360 O360J2A 41514 EA PITCH CONTROL ROUGH W K NONE O OTHER IN INSP/MAINT 1 CA 1722 (CAN) WHILE DOING AD 2003-04-04 THE BEARINGS WERE FOUND ROUGH ON ROTATION. PART WAS REPLACED WITH NEW. (TC# 20080107004) 1 G 7 1 3O 3 O H10WE E286 200805131 20080513 1 EU 2008 5 13 CA080108005 1 20080107 G 3610 9599021231 HOSE PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL BLEED AIR SYS CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 9247 (CAN) ON CLIMB OUT TO CRUISE ALTITUDE, IT WAS DISCOVERED THE AC WOULD NOT PRESSURIZE, AND THERE WAS NO BLEED AIR HEAT. A C RETURNED TO BASE. FOUND BLEED AIR HOSE CRACKED. (TC NR 20080108005) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 200805141 20080514 1 EA 2008 5 14 CA080108006 1 20080108 G 5752 215150622 SKIN CNDAIR 2151506180 CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE AILERON TAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3481 (CAN) AC UNDERGOING TURBO-PROP CONVERSION AT PRESENT. RT AILERON GEAR TAB INSPECTION REVEALED A CRACK IN THE LOWER SKIN UNDER THE LOWER IB MASS BALANCE WEIGHT MOUNT. THE CRACK IS APPROX 1.75 IN. LONG AND LOCATED LATERALLY, FWD OF THE BALA NCE WEIGHT MOUNT ATTACHMENT FASTENER HOLES. THE REPLACEMENT GEAR TAB WAS INSPECTED AND FOUND CRACKED IN THE SAME LOCATIO N. THE CUSTOMER AND OEM HAVE BEEN INFORMED. (TC NR 20080108006) 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 2008020400117 20080204 00117 EA 2008 2 4 CA080108007 1 20080103 G 7603 C6CE13151 RELEASE CABLE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL BETA SYSTEM BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE RT POWER CONTROL WAS REPORTED STIFF. AFTER AN INSPECTION ON THIS AREA IT WAS NOTICED THE THE BETA RELEASE CABL E HAD BROKEN AND WAS CAUSING THE POWER CABLE TO BE STIFF. A NEW CABLE WAS PURCHASED AND CABLE WAS CHANGED. (TC NR 200801 08007) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2008020400116 20080204 00116 WP 2008 2 4 CA080108009 1 20080108 G 7603 B5642 LINK ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE THROTTLE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 721 (CAN) WHILE CONDUCTING AN INSPECTION, IT WAS NOTED THAT THE BEARING LOOKED TO BE SEPERATED FROM THE LINK. THE LINK WAS R EMOVED AND INDEED IT WAS. THE LINK AND NEW WASHERS (SB-62) WERE INSTALLED AND NO OTHER ISSUES WERE NOTED. WHILE CONDUCTI NG RECENT THROTTLE LINKAGE WASHER INSTALLATION, WE ALSO NOTED THAT SOME OF THE LINKS HAD LITTLE SURFACE DAMAGE ON OTHER LINKS PRE-SB WASHER INSTALLATION. (TC NR 20080108009) 1 G 7 1 3O 3 O H11NM 1E4 2008020400115 20080204 00115 WP 2008 2 4 CA080109001 1 20080108 G 3260 BZE67RNT DOWNLOCK SWITCH CVAC 340 340CVAC 242270A WP ALLSN 501D 501D13D 03004 GL ALLSN A6441 A6441FN606 GL RT MLG INOPERATIVE W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) CREW REPORTED RT MLG GEAR UNSAFE LIGHT ILLUMINATED. REPLACED RT MLG DOWNLOCK SWITCH P/N BZE6-7RNT AND RETURNED TO SERVICE. (TC NR20080109001) 2 L 7 2 4R 4 T 6A6 E282 6 C P898 2008020400114 20080204 00114 NM 2008 2 4 CA080109002 1 20080104 G 3233 NAS771236 BUSHING DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MLG ACTUATOR MISSING W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) REMOVED NR2 MLG RETRACTION ACTUATOR FOR WORK CARD 2339 AND FOUND THE PICKUP FITTING MISSING (HAT) BUSHING. HOWEVE R, THE RETRACTION ACTUATOR WAS ASSEMBLED TO FITTING AND IN SERVICE WITHOUT THIS BUSHING. THIS PLACED SEVERE STRESS ON AT TACHMENT HARDWARE AND FITTING DUE TO THE IMPROPER ASSY. NR2 MLG RETRACTION ACTUATOR FITTING REPLACED ALONG WITH ALL HAR DWARE. NR2 MLG RETRACTION ACTUATOR REPLACED. RD8-54-1178 ACCOMPLISHED ALONG WITH NDT INSPECTION TO AFFECTED NACELLE ST RUCTURE. MISSING BUSHING REFERENCE: IPC 54-40-00, FIG. 20, ITEM 410, P/N NAS77-12-36. (TC NR 20080109002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008020400113 20080204 00113 NM 2008 2 4 CA080109004 1 20080108 G 3260 H1010153 UPLOCK SWITCH BOEING 727 727247 138408F NM PWA JT8 JT8D15 52051 NE NLG FAULTED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) FLIGHT WAS DEPARTING AND THEN DURING THE TAKEOFF ROLL, THE CREW SELECTED THE LANDING GEAR UP. WHEN THE GEAR HAD CY CLED UP THERE REMAINED A RED NOSE GEAR UNSAFE LIGHT. THE CREW CYCLED THE LANDING GEAR 3 TIMES BEFORE THE UNSAFE LIGHT EV ENTUALLY WENT OUT. THE AIRCRAFT RETURNED TO THE RAMP AND THE SYSTEM IS BEING TROUBLESHOT. THIS SDR WILL BE UPDATED WHEN A RECTIFICATION IS ESTABLISHED. (TC NR 20080109004) 2 L 7 3 4F 4 F A3WE E2EA 2008020400112 20080204 00112 NM 2008 2 4 CA080109005 1 20080105 G 2131 CIRCUIT BOARD DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PRESS CONTROLLER BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 30004 30004 60498 (CAN) THE CREW REPORTED A STRONG BURNING ELECTRICAL ODOR UPON ARRIVAL. MAINTENANCE FOUND A FAULTY PRESSURE CONTROLLER. F URTHER INVESTIGATION REVEALED THAT AN ELECTRONIC CIRCUIT BOARD INSIDE THE CONTROLLER HAD SOME BURN MARKS. THE CONTROLLE R WAS REPLACED AND THE AIRCRAFT RELEASED INTO SERVICE. (TC NR 20080109005) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008020400111 20080204 00111 EA 2008 2 4 CA080109009 1 20080107 G 7740 601509173 CONVERTER CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF343A1 30068 NE SIGNAL DATA FAULTY W E A ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA 6586 6586 (CAN) DURING ENGINE START, AT ABOUT 40 TO 50 PERCENT, N2, ALL LIGHTS ON THE ITT TAPE INSTANTLY LIGHTED UP. WE IMMEDIATEL Y SHUTDOWN ENGINE. RESIDUAL ITT WAS ONLY 56 AND NR9702, AFTER MOTORING. VISUALLY INSPECTED THE ENGINE FOR SIGNS OF HEAT OR DAMAGE AND FOUND NOTHING. SUSPECTED INDICATION PROBLEM AND DECIDED TO TRY ANOTHER START. START WAS NORMAL. WHILE WE CRUISED AT FL 390, ABOUT 50NM SOUTH, NOTICED A HIGH ITT (ALL LIGHTS ON AGAIN) ON THE SAME LT ENGINE. IMMEDIATELY WE REDUCED THRUST TO REGAIN WITHIN LIMITS. ABOUT 5 MINUTES LATER, ITT STARTED RISING GRADUALLY, AGAIN WE REDUCED THRUST. CR EW DISCUSSED ALTERNATE PLAN (DIVERTING), ITT STARTED AGAIN. KEPT REDUCING THRUST UNTIL WE HAD TO SHUTDOWN THE LT ENGINE 2 L 7 2 4F 4 F RT A21EA E15NE 2008020400110 20080204 00110 EA 2008 2 4 CA080109011 1 20080106 G 5610 NP13932110 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 5046 (CAN) THE RT WINDSHIELD CRACKED WHILE IN CRUISE. WINDSHIELD WAS REPLACED IAW AMM. (TC NR 20080109011) 2 L 7 2 4F RT A21EA 2008020400109 20080204 00109 EU 2008 2 4 CA080110001 1 20080108 G 2571 L243M3810103 BATTERY BOX UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206B 0 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 98 (CAN) DURING A PREFLIGHT CHECK IT WAS NOTED THAT THE BATTERY TRAY WAS CRACKED. REPLACED WITH NEW PART. (TC NR 200801100 01) 1 G 7 2 3U 3 U O H88EU E42NE 2008033100037 20080331 00037 EA 2008 3 31 CA080110003 1 20080110 G 2797 CONNECTOR CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C5 30050 NE TE FLAPS FAILED W C ABORTED TAKEOFF F J FLT CONT AFFECTED WARNING INDICATION TO TAKEOFF 1 CA (CAN) FLAP FAIL MESSAGE ON POWER UP. CODES READ AND BPSU NR 2 WIRING FAILED. MEL 27-51-02-1 APPLIED. WILL PROVIDE UPDATE WHEN MORE INFO BECOMES AVAILABLE (TC NR 20080110003) 2 L 7 2 4F 4 F RT A21EA E00063EN 2008032000006 20080320 00006 EA 2008 3 20 CA080110006 1 20080105 G 2750 860D10018 FCU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAULTED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 8560 8560 (CAN) THE CREW RECEIVED A FLAP FAIL .5 HR INTO THE FLIGHT CLIMBING BETWEEN 25000 TO 27000 FT. THE AC RETURNED WITHOUT IN CIDENT. MAINT T/S WAS CARRIED OUT AND THE LT AND RT BPSU’S WERE SWAPPED FOR T/S. SUSPECTED FAULTY FECU, FECU REPLACED, F UNCTION CHECK C/O AND TEST FLIGHT C/O SATISFACTORY. (TC NR 20080110006) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022500276 20080225 00276 NM 2008 2 25 CA080111001 1 20080110 G 5610 80260008 WINDSHIELD BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU COCKPIT BROKEN W B A EMER. DESCENT UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) CO-PILOTS FORWARD WINDSHIELD SHATTERED IN FLIGHT AT 25,000 FEET. EMERGENCY DESCENT AND DIVERSION PERFORMED. MAINT REPLACED THE WINDSHIELD AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20080111001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008022500278 20080225 00278 SW 2008 2 25 CA080111002 1 20080107 G 5751 21993 HINGE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1925 (CAN) ON INSPECTION, 4 CRACKS FOUND IN CORNERS (TC NR 20080111002) 1 H 7 1 3O 3 O A21CE E286 5 N P874 2008030600205 20080306 00205 SW 2008 3 6 CA080111003 1 20080102 G 5751 21993 HINGE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4718 (CAN) CRACK FOUND DURING SIRP INSP (TC NR 20080111003) 1 H 7 1 3O 3 O A21CE E286 5 N P874 2008030600206 20080306 00206 SW 2008 3 6 CA080111004 1 20080109 G 6410 212010750105 BLADE BELL BELL 205 205A1 1181414 SW LYC T53 T5317BLYC 41616 NE TAIL ROTOR DELAMINATED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA 4047 AHW00877 (CAN) PILOT HEARD A MUFFED LOW POP SOUND, WITH NO UNUSUAL GAUGE, WARNING LIGHTS, OR VIBRATIONS. UPON DEPARTING FOR ANOTH ER SKI RUN THE PILOT AGAIN NOTED AN UNUSUAL NOISE. AC WAS LANDED, AN EXTERIOR INSP WAS CONDUCTED. IT WAS THEN THAT THE DELAMINATING OF T/R BLADE WAS NOTED. AC REMAINED GROUNDED UNTIL ANOTHER SET OF T/R BLADES WERE INSTALLED. UPON INVESTIGA TION OF THE T/R BLADE IT APPEARS THE DELAMINATING STARTED FROM A PREVIOUS REPAIR ALBEIT ON THE OTHER SIDE OF THE BLADE A CCORDING TO THE COMPONENT LOG CARD. THE AIR FLOW STARTED TO PEEL BACK THE SKIN AT THIS SPOT, AS THE PEELING PROGRESSED S KIN REMAINED INTACT UNTIL THE ADHESIVE STRENGTH OF THE GLUE WAS EXCEEDED AND WE SEE THE SECONDARY PEELING IB AND OB WHER 1 G 7 1 4U 4 U H1SW E17EA 2008030600207 20080306 00207 NE 2008 3 6 CA080111005 2 20080111 G 7421 UREM38S SPARK PLUG PWA R985 R985AN14B 52008 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) (2) SEPARATE OCCASIONS NEW UREM38S SPARK PLUGS WERE REMOVED FROM THE PACKAGE AND FOUND TO HAVE CRACKED CERAMIC INS ULATORS. TO VERIFY THE PLUGS WERE TESTED AND FOUND TO BE MISFIRING. THE CRACKING IN THE CERAMIC DOES NOT APPEAR TO BE SH IPPING OR MISHANDLING DAMAGE AS THERE IS EVIDENCE OF TRACKING IN THE CRACKS. (TC NR 20080111005) 3 R 5E1 2008032000007 20080320 00007 EA 2008 3 20 CA080112001 1 20080110 G 2420 600591435 ADG CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE UNWANTED DEPLOY W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CL CLIMB 1 CA 18107 18107 (CAN) A/C RETURNED DUE TO ADG UNCOMMANDED DEPLOYMENT ON T/O. PRESENTLY THE AUTO DEPLOYMENT SYS IS UNDER MEL UNTIL MAINT PERMITS. UPDATE FURTHER WHEN T/S HAS BEEN C/O. (TC NR 20080112001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600208 20080306 00208 NM 2008 3 6 CA080114001 1 20080109 G 3230 483025 SEQUENCE VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU LT MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 42 (CAN) AFTER TAKEOFF, LT MLG DOOR AMBER LIGHT REMAINED ON (FA CONFIRMED LT MLG DOOR OPEN). GEAR EXTENDED THEN L DOOR AMBE R LIGHT, LT RED, AND GEAR HANDLE LIGHT REMAINED ON (FA CONFIRMED THE GEAR WAS PARTIALLY EXTENDED). AFTER ABOUT 5 MINS, LT GREEN LIGHT ILLUMINATED AND LT MLG DOOR CLOSED. AIR RETURN TO BASE FOR LANDING. MAINT REPLACED LT MLG SOLENOID SEQUE NCE VALVE. (TC NR 20080114001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008030600209 20080306 00209 EU 2008 3 6 CA080114002 1 20080111 G 2160 342B030000AM SWITCH AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE TEMP CONTROL INOPERATIVE W B EMER. DESCENT J WARNING INDICATION CR CRUISE 1 CA (CAN) NR 1 BLEED OVERHEAD SHOWED ON ECAM AIR ENG 1 BLD FAULT COMPLETED ECAM ACTION SHORTLY AFTERWARD AIR ENG 2 BLD FAULT COMPLETED ECAM. BOTH FAN AIR VALVES CHECKED IAW AMM 36-11-54-720-001 NFF. BOTH TCT`S REPLACED ( ENG 1 AND 2) IAW AMM 36 -11-43. ENG RUNS CARRIED OUT PACKS OPERATED NORMAL. (TC NR 20080114002) 2 L 7 2 4F 4 F RT A28NM E29NE 2008030600210 20080306 00210 NM 2008 3 6 CA080114003 1 20080110 G 2421 SENSOR LUCAS 31708001A DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NR 2 A/C GEN OPEN W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 168 (CAN) HAD A FAILURE OF THE NR 2 AC GEN THE PREVIOUS WEEK, THE AC GEN WAS REPLACED WITH AN O/H UNIT. THE AC TOOKOFF AND AT 7000 FEET HAD A NR 2 AC GENERATOR FAIL, THE AC RETURNED TO THE AIRPORT. INVESTIGATION WAS C/O AND FOUND THAT THE SPEE D SENSOR WAS OPEN. THE UNIT SENT BACK TO THE SHOP REPLACED THE SPEED SENSOR, UNIT REINSTALLED ON THE A/C AND FOUND SERVI CEABLE. A/C DEPARTED ON JAN 14-2008 AND NO OTHER REPORT REPORTED. (TC NR 20080114003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008030600211 20080306 00211 NM 2008 3 6 CA080115001 1 20080112 G 3231 AR2674 LATCH BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU MLG DOOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NOSE LANDING GEAR ALTERNATE RELEASE DOOR FAILS TO OPEN DURING PRE FLIGHT CHECK. ALTERNATE EXTENSION DOOR LATCH BRO KEN CAUSING DOOR TO STICK IN CLOSED POSITION. REPLACED LATCH ALL CHECKS OK. (TC NR 20080115001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008030600212 20080306 00212 NM 2008 3 6 CA080115002 1 20080113 G 2913 6617303 PUMP BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU HYD SYSTEM FAILED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA 295 (CAN) DURING TAXI OUT THE NR 2 HYD PUMP CAUTION LIGHT ILLUMINATED. PTU WAS SELECTED ON AT THE TIME. SHUT OFF PTU AND ALL NR 2 HYD SYS CAUTIONS ILLUMINATED AND CONFIRMED NO PRESSURE ON NR 2 SYS. FLUID QTY WAS LOW. RETURNED TO TERMINAL WHERE MAINTENANCE FOUND FLUID COMING FROM ENGINE DRIVEN PUMP DRAIN. REMOVED EDP PUMP AND FOUND DRIVESHAFT SHEARED. PUMP REPL ACED AND SYSTEM FLUSHED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20080115002) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008030600213 20080306 00213 EU 2008 3 6 CA080115003 1 20080107 G 2710 KA6D8X50 ROD END DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE12501 59300 EU AT AILERON BENT W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 CA 98 98 (CAN) WHILE RIGGING THE AILERON SYS FOLLOWING MAINT, NOTICED BOTH THE LT AND RT AILERON CONTROL ROD END FITTINGS WERE BE NT WHERE THE CONTROL ROD IS ATTACHED TO THE BELLCRANK AT THE MOST OB POINT. NEW STRAIGHT FITTINGS WERE INSTALLED BUT THI S CAUSED THE AILERON SYS TO BIND. THERE IS NO REFERENCE IN THE IPC OR MM REFERENCING BENT ROD ENDS AS BOTH ROD ENDS ON T HE CONTROL ROD HAVE THE SAME PN. (TC NR 20080115003) 1 L 7 2 3I 3 B RT A57CE E00069EN 2008030600214 20080306 00214 NM 2008 3 6 CA080115004 1 20080112 G 3330 30180B23D1683 LIGHT DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE CARGO BAY SHORTED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING FLIGHT, THE CREW REPORTED (TO MOC) THAT THEY HAD THE (SMOKE) WARNING ILLUMINATED. THEY WERE TOLD TO DO A TU RNBACK AND RETURN TO AIRPORT WHERE MAINT STAFF MET THE AIRCRAFT. DURING THE INVESTIGATION, MAINT PERSONNEL FOUND THE SI DEWALL BAGGAGE DOOR LIGHT WIRE HAD COME OFF INTERNALLY AND WAS ARCING ON ITS CASE. LIGHT ASSY REPLACED AND ENGINE RUNS C ARRIED OUT. (TC NR 20080115004) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008030600215 20080306 00215 EU 2008 3 6 CA080115005 1 20080114 G 2710 DSPR116X058 PUSHROD DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE12502114 EU AILERON BENT W K NONE O OTHER IN INSP/MAINT 1 CA 9 (CAN) AFTER RECEIVING A REPORT OF AN ANOMALY WITH THE CONTROL ROD FROM ANOTHER OPERATOR, INSPECTED THE ROD ENDS ON OUR A C. ALSO FOUND THE ROD ENDS ON BOTH LT AND RT AILERONS BENT. THE ROD ENDS APPEAR TO HAVE BEEN BENT TO ACCOMODATE THE MOV EMENT OF THE AILERON BUT WE CANNOT FIND A DESCRIPTION OF THIS PROCESSS IN THE MM. (TC NR 20080115005) 1 L 7 2 3I 3 B RT A57CE E00069EN 2008030600216 20080306 00216 EU 2008 3 6 CA080115006 1 20080114 G 2710 DSPR116X058 PUSHROD DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE12501 59300 EU AILERON BENT W K NONE O OTHER IN INSP/MAINT 1 CA 37 (CAN) AFTER RECEIVING A REPORT OF AN ANOMALY WITH THE CONTROL ROD FROM ANOTHER OPERATOR, WE INSPECTED THE ROD ENDS ON OU R AC. WE ALSO FOUND THE ROD ENDS ON BOTH LT AND RT AILERONS BENT. THE ROD ENDS APPEAR TO HAVE BEEN BENT TO ACCOMODATE TH E MOVEMENT OF THE AILERON BUT WE CANNOT FIND A DESCRIPTION OF THIS PROCESSS IN THE MAINTENANCE MANUAL. (TC NR 2008011500 6) 1 L 7 2 3I 3 B RT A57CE E00069EN 2008030600217 20080306 00217 NM 2008 3 6 CA080115007 1 20080115 G 2710 129307 PCU BOEING 727 727247 138408F NM PWA JT8 JT8D15 52051 NE AILERON FROZEN W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 13147 2175 (CAN) THE AC ARRIVED AT DESTINATION AND WAS ON A TURN-AROUND WHEN THE CREW NOTICED ON TAXI OUT, THAT THE AILERONS HAD FR OZEN UP. THE AC RETURNED TO THE RAMP WHERE MAINT INSPECTED THE SYS. IT WAS DETERMINED THAT THE AILERON POWER CONTROL UNI T HAD FROZEN UP. HEAT WAS PLACED ON THE PCU AND THE CONTROLS FREED UP. THE CONTROL UNIT WAS FLUSHED OF ALL WATER CONTAM INATES AND LUBRICATED. HEAT WAS APPLIED TO THE PCU FOR APPROX (4) HOURS. IT HAD BEEN NOTED BY FLIGHT CREW THAT THE AC HA D BEEN IN A RAINY ENVIRONMENT EARLIER IN THE DAY. THE AC WAS COLD SOAKED FOR (4) HOURS IN -10 DEGREES AND A 50KPH WIND. NO FURTHER FAULTS FOUND. (TC NR 20080115007) 2 L 7 3 4F 4 F A3WE E2EA 2008030600218 20080306 00218 EU 2008 3 6 CA080115008 1 20080114 G 2710 DSPR116X058 CONTROL ROD DIAMON DA42 DA42 2990004 EU THIELT TAE125 TAE12501 59300 EU AILERON BENT W K NONE O OTHER IN INSP/MAINT 1 CA 50 (CAN) AFTER RECEIVING A REPORT OF AN ANOMALY WITH THE CONTROL ROD FROM ANOTHER OPERATOR, WE INSPECTED THE ROD ENDS ON OU R AC. ALSO FOUND THE ROD ENDS ON BOTH LT AND RT AILERONS BENT. THE ROD ENDS APPEAR TO HAVE BEEN BENT TO ACCOMODATE THE MOVEMENT OF THE AILERON BUT WE CANNOT FIND A DESCRIPTION OF THIS PROCESSS IN THE MM. (TC NR 20080115008) 1 L 7 2 3I 3 B RT A57CE E00069EN 2008030600219 20080306 00219 EU 2008 3 6 CA080115009 1 20080110 G 6797 GROUND WIRE SNIAS 350 AS350B 8680801 EU LYC LTS101 LTS101600A3 41560 NE HYD SERVO FAILED W A UNSCHED LANDING F FLT CONT AFFECTED AP APPROACH 1 CA 10932 AC67244 (CAN) IN THE PROCESS OF DOING RECURRENT TRAINING FLIGHT. AFTER SEVERAL SIMULATED HYD FAILURES IN AND OUT OF GROUD EFFECT HOVER, PROCEEDED TO PRACTICE THE SIMULATED HYD FAILURE. THE SIMULATED PROCEDURE WAS INITIATED FROM 100 FOOT HOVER WITH A VERBAL WARNING THAT WE NOW HAVE A LOSS OF HYD. AT NO TIME WAS THE HYD ACCUMULATOR TEST BUTTON USED TO SIMULATE, HYD FA ILURE, IE. HORN AND LIGHT. FROM THE HOVER THEY ACCELERATED TO 60 KNOTS, AT WHICH TIME THE HYD ON/OFF SWITCH ON THE COLLE CTIVE WAS SELECTED TO THE HYD OFF POSITION, AND THEY MAINTAINED 60 KNOTS THROUGHOUT THE CIRCUIT. ON DOWNWIND FOR EAST LI MA TAXIWAY AT 500 FEET ABOVE GROUND. THE PILOT IN COMMAND WAS INFORMED TO WIDEN OUT HIS CIRCUIT SO THAT HE WOULD NOT HAV 1 G 7 1 3U 3 U H9EU E5NE 2008032000009 20080320 00009 EA 2008 3 20 CA080115010 1 20080113 G 5250 LATCH CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE LAVATORY DOOR STUCK W O OTHER O OTHER AP APPROACH 1 CA 3261508 (CAN) ON SHORT FINAL A PASSENGER GOT STUCK INTO LAVATORY COMPARTMENT. THE F/A TRIED TO UNLOCK THE DOOR LATCH BUT THE PAS SENGER ELECTED TO KICK THE DOOR OFF. IMPORTANT DAMAGES WERE DONE TO THE DOOR HINGE AND LOCKING MECHANISM. AT THIS TIME, INVESTIGATION COULD NOT IDENTIFY THE CAUSE OF THE INCIDENT. (TC NR 20080115010) 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600221 20080306 00221 NE 2008 3 6 CA080115012 2 20080111 G 7240 COMBUST CHAMBER SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE ENGINE FOD W K NONE O OTHER IN INSP/MAINT 1 CA 2190 22386 (CAN) DURING A 600 HR ENGINE INSPECTION, A BORESCOPE INSPECTION WAS CONDUCTED IN THE COMBUSTION CHAMBER AREA( INTERNAL) AN OBJECT WAS DISCOVERED HANGING OUT INTO THE FLAME PATH JUST UPSTREAM OF THE POWER TURBINE. THE OBJECT WAS PROTRUDING F ROM AN INNER COOLING HOLE IN THE COMBUSTION CHAMBER. AFTER DISCUSSION WITH MFG, THE AC WAS REMOVED AND AN ENGINE TEARDOW N WAS CONDUCTED. THE ITEMS REMOVED AND ENGINE REASSEMBLED AND TESTED ON THE A/C. THE OBJECT COULD NOT BE IDENTIFIED AT T HIS LEVEL AND WAS TAKEN BY THE MFG SERVICE REP FOR TESTING. HAVE A FEW BORESCOPE IMAGES AVAILABLE IF REQUIRED. (TC NR 20 080115012) 1 G 7 1 3U 3 U H9EU E00054EN 20080520 CE 2008 5 20 CA080116001 1 20080115 G 5340 4552803060003 FITTING 45528030040 LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6170 6170 (CAN) DURING DAILY INSP A CRACK WAS NOTICED ON LT MAIN IB LANDING GEAR DOOR ACTUATOR FITTING, A NEW PART IS ORDERED AND WILL BE REPLACED WHEN RECEIVED. LT IB MAIN GEAR DOOR P/N 4552803004-003 FITTING IS ITEM 69 ON ATTACHED IPC. (TC NR 20080 116001) 2 L 7 2 4F 4 F RT T00008WI E6WE 20080520 EU 2008 5 20 CA080116002 1 20080109 G 3230 5322012289 DRAG LINK PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NLG CRACKED W L ABORTED APPROACH J WARNING INDICATION DE DESCENT 1 CA (CAN) DURING DESCENT, THE INTRANSIT LIGHT CAME ON IN THE COCKPIT FOR THE NOSE GEAR. THE GEAR WAS THEN SELECTED DOWN AND LOCKED. THE CAPTAIN AND MAINT FELT THERE WAS MORE THEN JUST A SIMPLE INDICATION PROBLEM AND RETURNED THE AC TO THE HOME BASE. AS A SAFETY PRECAUTION THE PASSENGERS WERE OFFLOADED ON THE RUNWAY. THE RT DRAG LINK WAS FOUND TO BE CRACKED. THER E WAS NO TELLTALE SIGNS THAT WOULD CAUSE THE LINK TO CRACK LIKE IT DID. FROM THE LOOK OF THE CRACK IT WAS ALL NEW. THE R EST OF THE PC-12S IN THE FLEET WERE CHECKED AND NO OTHER DRAG LINKS WERE CRACKED. THE LINK WAS REPLACED, SWINGS WERE COM PLETED AND THE AC WAS RETURNED TO SERVICE. (TC NR 20080116002) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008030600224 20080306 00224 CE 2008 3 6 CA080116007 1 20080112 G 2820 3032791 LINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL LT NACELLE CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) FUEL FLOW INDICATION LINE FOUND CHAFED AND LEAKING. NEW LINE INSTALLED. (TC NR 20080116007) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2008030600226 20080306 00226 CE 2008 3 6 CA080116009 1 20080108 G 7603 11452411411 BELLCRANK BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE POWER LEVER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE RT POWER LEVER BELLCRANK LOCATED IN THE BOTTOM OF THE PEDESTAL WAS REPLACED DUE TO WEAR. AFTER REMOVAL THE PA RT WAS FOUND TO BE CRACKED. (TC NR 20080116009) 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2008030600231 20080306 00231 NE 2008 3 6 CA080116014 2 20080106 G 7310 FUEL SYS CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ENGINE LOW PRESSURE W D RETURN TO BLOCK X J ENGINE FLAMEOUT WARNING INDICATION TX TAXI/GRND HDL 1 CA 77771 (CAN) DURING PRE TAKEOFF ACTIVITES, THE LOW FUEL PRESSURE WARNING ILLUMINATED. AS THE AC TAXIED BACK TO THE RAMP, THE EN GINE SHUT ITSELF DOWN. ENGINE RESTARTS WERE UNSUCCESSFUL. THE FUEL FLOW DIVIDER WAS REPLACED AND THE AC RETURNED TO SER VICE. (TC NR 20080116014) 1 L 7 2 4F 4 F A22CE E1NE 2008030600232 20080306 00232 EA 2008 3 6 CA080116015 2 20080104 G 7250 TURBINE BLADES BELL 412 412 1182202 SW PWA PT6T PT6T3 52045 EA ENGINE FRACTURED W A UNSCHED LANDING E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION HO HOVERING 1 CA TH0463 (CAN) DURING HOVER THE CREW NOTED VIBRATION FOLLOWED BY CHIP DETECTOR LIGHT ILLUMINATION AND LOSS OF POWER. POST FLIGHT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND ASSOCIATED DAMAGE. IT WAS REPORTED THAT THE PILOT HAD DIFFICULTY STARTING THE ENGINE PRIOR TO THIS FLIGHT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTAB LISHED (TC NR 20080116015) 1 G 7 2 4U 4 U H4SW E22EA 2008030600234 20080306 00234 EA 2008 3 6 CA080116017 1 20080115 G 3213 15101103 HOUSING DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL STRUT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 6 YEAR CORROSION INSPECTION, A CRACK WAS FOUND ON THE LT MLG OUTER HOUSING. THE CRACK IS LOCATED ON THE F WD SIDE AT ABOUT THE ONE O’CLOCK POSITION JUST WERE THE HOUSING TAPERS DOWN. EDDY CURRENT WAS USED ON THE CRACK, IT WAS DEEPER THAN THE 0.040. THE LANDING GEAR HAS A 60 000 LANDING LIFE LIMIT AND A 10 000 LANDING INSPECTION REQUIREMENT, THI S GEAR HAD 44 528 LANDINGS SINCE NEW AND 5925 LANDINGS SINCE INSPECTION. THE HOUSING WILL BE REPLACED. (TC NR 200801160 17) 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2008032400428 20080324 00428 EA 2008 3 24 CA080116020 2 20080109 G 7200 ENGINE PIPER PA46 PA46350P 7104602 SO PWA PT6 PT6* 52043 EA MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING B M SMOKE/FUMES/ODORS/SPARKS OVER TEMP CR CRUISE 1 CA RR0005 (CAN) PILOT REPORTED ENGINE TROUBLE AND ATTEMPTED TO RETURN TO BASE. ENGINE WAS SHUTDOWN BY THE PILOT, AND AC LANDED SHO RT OF THE RUNWAY CAUSING SUBSTANTIAL DAMAGE TO THE AIRFRAME. INITIAL INVESTIGATION INDICATES NO OBVIOUS GAS PATH OR TURB INE BLADE DAMAGE, HOWEVER NO OIL WAS VISIBLE ON THE DIPSTICK. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF R OOT CAUSE ONCE ESTABLISHED (TC NR 20080116020) 1 L 7 1 3O 3 T RT A25SO E2NE 2008032400429 20080324 00429 NE 2008 3 24 CA080116021 2 20080109 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE POWER LOSS W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 17458 (CAN) CLIMBING THROUGH 4000 FT, ENGINE PWR WAS LOST. ACTIVATION OF THE EMERGENCY POWER LEVER HAD NO EFFECT. THE ENG WAS SECURED AND THE AC WAS ABLE TO RETURN TO POINT OF DEPARTURE. INITIAL INVESTIGATION REVEALS AN EXTERNAL OIL LEAK AND A SE IZED PROP SHAFT ROTOR. THE ENGINE HAS BEEN IMPOUNDED BY THE AUTHORITIES AND WILL BE INVESTIGATED IN THE MFG FACILITY. UP DATES WILL BE PROVIDED IN DUE COURSE. (TC NR 20080116021) 1 H 7 1 3T 3 T A37CE E4EA 2008032400431 20080324 00431 2008 3 24 CA080116022 4 20080109 G 6122 MOUNT BEECH 95 D95A 1153408 CE LYC O360 IO360B1B 41514 EA HARTZL HCC2Y HCC2YK2 GL GOVERNOR MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA L1832351A (CAN) AFTER ENGINE REPLACEMENT FOR OVERHAUL A PRELIMINARY GROUND RUN WAS CARRIED OUT. IT WAS FOUND THAT THE PROPELLER WO ULD NOT FEATHER WHEN PERFORMING A GOVERNOR CHECK. THE PROBLEM WAS TRACED TO THE GOVERNOR MOUNT PAD WHICH HAD NOT HAD AN OIL GALLERY COMPLETELY DRILLED PREVENTING PROPELLER CONTROL. MAINT REPLACED THE GOVERNOR PAD AND THE AC PROPELLER CONTRO L SYS FUNCTIONED NORMALLY (TC NR 20080116022) 1 L 7 2 3O 3 O 3A16 1E10 5 C P920 2008032400432 20080324 00432 EA 2008 3 24 CA080116023 2 20080111 G 8520 7106403 CRANKCASE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA NR 1 ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1829 RL489461A (CAN) DURING SCHEDULED NR 1 EVENT INSPECTION, AME FOUND LT ENGINE, NR 5 CYL DIFFERENTIAL PRESSURE TEST VERY LOW. NR 5 C YL REMOVED FOR DETAILED INSP AND POSSIBLE REPLACEMENT. UPON FURTHER INSP MAINT FOUND AN APPROX 4 INCH CRACK, STARTING FR OM NR 5 CYL LOWER FWD MOUNT STUD BASE, ALONG CYL. BASE INTO RT CASE EXTENDING APPROX 3.5 INCH TOWARD NR 5 CYL COVER OIL DRAIN PORT IN THE CASE. LT ENGINE REPLACEMENT UNDERWAY. (TC NR 20080116023) 1 L 7 2 3O 3 O A20SO E14EA 2008030600236 20080306 00236 EA 2008 3 6 CA080116024 1 20080113 G 3260 16868101 PROXIMITY SWITCH MESSIER CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B 30069 NE NLG MISINSTALLED W B EMER. DESCENT N FALSE WARNING AP APPROACH 1 CA 07MDT0422 (CAN) DURING APPROACH, GEAR WAS SELECTED DOWN AND NLG INDICATED AMBER. NO GEAR DISAGREE MESSAGE POSTED. GEAR WAS RAISED NORMALLY AND MISSED APPROACH WAS EXECUTED. AT THAT MOMENT QRH ACTIONS WERE CARRIED OUT FOR GEAR MALFUNCTION. NOSE GEAR INDICATION BECAME RED. TROUBLESHOOTING WAS CARRIED OUT VIA RADIO WITH ENGINEERING NOSE GEAR WOULD NOT INDICATE DOWN. A L OW APPROACH WAS CONDUCTED AT AIRPORT TO VISUALLY CHECK NOSE GEAR POSITION. GEAR APPEARED DOWN. EMERGENCY DECLARED. FOL LOWED BY AN UNEVENTFUL LANDING. THE AC WAS PUT IN QUARANTINE FOR TEST ON GROUND AND FINDING OF THE ROOT CAUSE. AFTER D EPLOYMENT TEST ON LANDING GEAR AND FUNCTIONAL TEST ON PSEU THE PROBLEM WAS DISCOVERED. THE PROBLEM WAS AN INAPPROPRIATE 2 L 7 2 4F 4 F RT A21EA E15NE 2008033100039 20080331 00039 NE 2008 3 31 CA080117001 2 20080110 G 7200 ENGINE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE LEFT FLAMED OUT W A UNSCHED LANDING X ENGINE FLAMEOUT CR CRUISE 1 CA 21835 872629 (CAN) FLIGHT,IN CRUISE, LT ENGINE FLAMED OUT WITH NO PREVIOUS WARNINGS. FLIGHT CREW TRIED TO RESTART LT WITHOUT SUCCESS. AC LANDED. NO ENGINE EXCEEDANCES FOUND. NO EVIDENCE OF WATER CONTAMINATION IN MAIN FUEL TANKS AND FUEL FILTER HOUSING. PERFORMED A VISUAL EXTERNAL AC INSP AND NO EVIDENCE OF LIGHTNING STRIKE. CHECKED ENGINE THROTTLE RIGGING, FOUND OK. CHE CKED FEEDBACK CABLE, FOUND OK. DURING T/S THE ENGINE STARTS NORMALLY, AND ALL ENGINE PARAMETERS ARE STABLES AND NORMAL. POWER ASSURANCE CHECK PERFORMED AND ALL ENGINE PARAMETERS ARE WITHIN SERVICEABLE LIMITS. 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600237 20080306 00237 SW 2008 3 6 CA080117002 1 20080117 G 6420 BEARING BELL BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE T/R HUB UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 6085 801 (CAN) FOUND TAIL ROTOR HUB ASSY OB BEARING CAGE INSERT OUT OF IS SOCKET. ASSY SEND FOR O/H. (TC NR 20080117002) 1 G 7 1 4U 4 U H1SW E17EA 2008030600238 20080306 00238 EU 2008 3 6 CA080117003 1 20080111 G 2821 571712A BYPASS VALVE SNIAS 350 AS350BA 8680817 EU LYC LTS101 LTS101600A2 41560 NE FUEL SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) THE AC LANDED AFTER FLYING SEVERAL HOURS ON A SEISMIC JOB. WHILE DOING A QUICK DI, THE ENGINEERS NOTICED FUEL ON T HE TRANSMISSION DECK. IT WAS DISCOVERED THAT THE FUEL FILTER BYPASS INDICATOR PLASTIC HOUSING ON THE BYPASS VALVE ASSY ( PN 57171-2A) WAS CRACKED AND WAS LEAKING FUEL ON THE TRANSMISSION DECK. IT IS NOT KNOW HOW MANY HOURS THE AC FLEW THAT D AY WITH THIS FUEL LEAK. THE VALVE ASSY WAS REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20080117003) 1 G 7 1 3U 3 U NC H9EU E5NE 2008032400434 20080324 00434 NM 2008 3 24 CA080117004 1 20080115 G 5330 143A321220 SKIN BOEING 737 737800* NM BS 480 S21L DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 11057 (CAN) UNDERGOING MAINT, LIGHTNING STRIKE ON RIVET AT BS 480,1.3INCHES BELOW STRINGER 21, LT SIDE. REPAIRED IAW EA 5330- 02286. 2 L 7 2 4F RT A16WE 2008032500001 20080325 00001 WP 2008 3 25 CA080117005 2 20080111 G 7261 8941171 ADAPTER SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE ENG OIL FILTER CRACKED W K NONE K J FLUID LOSS WARNING INDICATION IN INSP/MAINT 1 CA P54055 (CAN) DURING THE DAILY INSPECTION IT WAS NOTICED THAT THERE WAS OIL IN THE BOTTOM OF THE COWLING. FURTHER INSP REVEALED THAT THE (3) OF THE (4) TANGS FOR THE STUDS WHICH HOLD DOWN THE OIL FILTER ADAPTER WERE CRACKED. TOTAL TIME ON THIS PART IS UNDETERMINED BECAUSE IT IS ON CONDITION. 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 2008030600239 20080306 00239 NE 2008 3 6 CA080117006 1 20080116 G 7921 28E252 THERMOSTAT SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL NR1 POSITION UNSERVICEABLE W E ENGINE SHUTDOWN J WARNING INDICATION HO HOVERING 1 CA (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMP BEGAN TO RISE TO LIMIT. (TC NR 20080117006) 1 G 7 2 3U 3 U H1NE E1GL 2008032000010 20080320 00010 EA 2008 3 20 CA080117007 2 20080115 G 7200 ENGINE BEECH 99 99 1154002 CE PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL LEFT FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 11901 4605 PCE22135 (CAN) WHILE DOING PILOT TRAINING, THE LT OIL PRESSURE WARNING LIGHT CAME ON. PILOTS LOOKED DOWN AT OIL PRESSURE GAUGE, T HE PRESSURE WAS DROPPING SO THEY SHUTDOWN THE ENGINE AND FEATHERED THE PROP. THEY RETURN TO BASE. ENGINE REMOVED FOR FUR THER INSPECTION. (TC NR 20080117007) 1 L 7 2 3T 3 T A14CE E4EA 6 C P15EA 2008030600240 20080306 00240 CE 2008 3 6 CA080117008 1 20080114 G 3230 1158200381 SPROCKET BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL MLG WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSP OF THE NLG RETRACT MECHANISM CHAIN FOR TENSION AND LUBRICATION, MAINT NOTED THE DUAL LINK CHAIN WAS ON LY RUNNING ON ONE LENGTH OF CHAIN RATHER THAN (2). AC WAS INSPECTED MORE CLOSLEY AND THE BRAZE/SPROCKET ASSY WHICH IS I NTERMEDIATE BETWEEN LANDING GEAR MOTOR AND RETRACT ACTUATOR FOR THE NOSE GEAR WAS FOUND MISALIGNED AND DISPLACED. UPON R EMOVAL OF THE SPROCKET AND IT`S HOUSING IT WAS NOTED THE UNDERLYING AC STRUCTURE WAS CRACKED AND NOT PROVIDING ADEQUATE SUPPORT TO THE SPROCKET ASSY FOR PROPER OPERATION AND ALIGNMENT. THE LACK OF ALIGNMENT BETWEEN THE CHAIN AND SPROCKET CA USED THE DUAL LINK CHAIN TO SKIP OVER ONE SPROCKET AND ONLY UTILIZE HALF OF THE CHAIN FOR GEAR RETRACTION AND EXTENSION. 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2008022000015 20080220 00015 EA 2008 2 20 CA080117010 1 20080116 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAILED W O OTHER J WARNING INDICATION DE DESCENT 1 CA 13017 13017 (CAN) DURING DESCENT, CREW REPORTED A FLAP FAIL CAUTION MESSAGE WITH NO FLAP SELECTION. AN EMERGENCY WAS DECLARED AND AN UNEVENTFUL FLAPLESS LANDING WAS CARRIED OUT. THE AC WAS FERRIED TO MAINTENANCE BASE WERE THE LT BRAKE POSITION SENSOR U NIT (BPSU) WAS REPLACED AND RIGGED. A SUCCESSFUL FLIGHT TEST WAS COMPLETED AND THE AC RETURNED INTO SERVICE. THE UNIT HA S ACCUMULATED 30:20 FLIGHT HOURS SINCE REPAIR. (TC NR 20080117010) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022000016 20080220 00016 EA 2008 2 20 CA080117011 1 20080116 G 5610 601R3303319 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT FAILED W O OTHER O OTHER DE DESCENT 1 CA 8194 8194 (CAN) LT COCKPIT SIDE WINDOW SHATTERED IN DESCENT. THE CREW DID NOT REPORT ANY IMPACT OR PROBLEM WITH THE WINDOW PRIOR TO INCIDENT. VISUAL INSPECTION OF THE WINDOW INDICATES THAT ONLY THE OUTER PLY WAS DAMAGED. THE SIDE WINDOW WAS REPLACED , TESTED AND THE AC RETURNED TO SERVICE. (TC NR 20080117011) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022000017 20080220 00017 EA 2008 2 20 CA080118000 1 20080116 G 5610 NP1393216 WINDSHIELD CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF343B 30069 NE COCKPIT FAILED W O OTHER O OTHER DE DESCENT 1 CA 8931 (CAN) COPILOTS WINDSHIELD INNER PANE SHATTERED AT 37,000 FT ON DESENT. NO EVIDENCE OF HEATER FAILURE WAS OBSERVED. (TC NR 20080118000) 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600241 20080306 00241 SW 2008 3 6 CA080118001 1 20080105 G 6310 206040230019 FREEWHEEL UNIT BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL MAIN ROTOR LEAKING W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 5 (CAN) AFTER FLIGHT THE FREEWHEEL ASSY WAS DISCOVERED LEAKING FROM THE FWD HSG CAP. FREEWHEEL ASSY CHANGED, LEAK CHECK CA RRIED OUT SERVICEABLE. (TC NR 20080118001) 1 G 7 1 3U 3 U H2SW E4CE 2008030600242 20080306 00242 EU 2008 3 6 CA080118002 1 20080118 G 2571 BATTERY BOX UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE FUSELAGE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 1889 (CAN) DURING DAILY INSPECTION FOUND (2) BROKEN HEAD OF RIVETS ON BATTERY TRAY. RIVETS REPLACED AND AIRCRAFT, SERVICEABLE (TC NR 20080118002) 1 G 7 2 3U 3 U NC R0001RD E34NE 2008022000018 20080220 00018 EA 2008 2 20 CA080118003 1 20080115 G 2420 820465 ADG CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE UNWANTED DEPLOY W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 16687 16687 (CAN) WHILE AC WAS IN CRUISE AT 30000 FT, ADG DEPLOYED UN-COMMANDED. ALL ELECTRICAL SYSTEMS WERE POWERED. TRIED SWITCHI NG BACK TO IDG POWER. ADG WOULD NOT SWITCH OVER. MAINTENANCE REPLACED ADG AUTO DEPLOYMENT CONTROLLER AND ADG RESTORE PUM P. (TC NR 20080118003) 2 L 7 2 4F 4 F RT A21EA E15NE 2008030600243 20080306 00243 NE 2008 3 6 CA080119001 2 20080118 G 7314 15473 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 797 797 (CAN) FUEL PUMP LEAKING OIL FROM DRAIN LINE. PUMP REMOVED AND NEW PUMP INSTALLED. DEFECT RECTIFIED. (TC NR 20080119001) 1 G 7 1 3O 3 O H11NM 1E4 2008022000019 20080220 00019 EA 2008 2 20 CA080121001 1 20080116 G 5610 NP1393219 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE COCKPIT CRACKED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 12588 12588 (CAN) ON CLIMB OUT THROUGH 6000 FT CREW SELECTED WINDSHIELD HEAT. THE (L WSHLD HEAT) EICAS MESSAGE ILLUMINATED. ABOUT 15 SECONDS LATER CAPTAIN’S FRONT WINDSHIELD OUTER PLY BEGAN CRACKING. SPIDER WEB LIKE CRACKING CONTINUED UNTIL WHOLE OUTER PANE APPEARED SHATTERED. CAPTAIN’S FRONT WINDSHIELD WAS REPLACED. AS A PRECAUTION, THE LT WINDSHIELD TEMPERATURE CONTRO LLER PN 1659-1 WAS ALSO REPLACED. (TC NR 20080121001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022000020 20080220 00020 EA 2008 2 20 CA080121002 1 20080120 G 2750 5275102 FCU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS DEFECTIVE W O OTHER F J FLT CONT AFFECTED WARNING INDICATION NR NOT REPORTED 1 CA (CAN) FLAPS FAILED ON INITIAL SELECTION FROM 0 TO 8 DEGREES JUST AFTER PUSHBACK FOR HEADSTART FLIGHT. OAT WAS -29 C OVER NIGHT. MAINTENANCE GOT CODES FROM FECU, CLEARED FAULT AND RESET FLAPS. FLAPS FUNCTION CHECKED SERVICEABLE, BUT DUE TO R ECENT HISTORY IT WAS DECIDED TO FERRY THE AC FOR FURTHER TROUBLESHOOTING. TROUBLESHOOTING IS UNDER WAY AND INFORMATION W ILL BE UPDATED AS SOON AS IS AVAILABLE. (TC NR 20080121002) 2 L 7 2 4F 4 F RT A21EA E15NE 2008032500002 20080325 00002 2008 3 25 CA080121003 4 20080102 G 3497 WIRE BOEING 737 737217 1384464 NM PWA JT8 JT8D17A 52049 NE TAWS COMPUTER INOPERATIVE W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) TAIL 523 ON JAN 2ND APPROACH BACK COURSE ON RWY 15 YELLOWKNIFE 1040FT ASL 350FT AGL LEVEL FLIGHT 140K IN THIS CAS E THE FLIGHT CREW EXPERIENCED A TAWS GENERATED A PICTORIAL DISPLAYED IMPACT WARNING. THE CREW WAS IN VISUAL CONDITIONS A ND SAW NO DANGER OF IMPACT. THE AC LANDING WITHOUT FURTHER INCIDENT. IN THE FOLLOWING WEEKS, AC EQUIPPED WITH THE UNIVER SAL TAWS COMPUTER (STC ST10622SC) EXPERIENCED SIMILAR ANOMALIES. UNIVERSAL AVIONICS WAS CONTACTED CONCERNING THE ISSUE. THIS NORTH REGION AIRPORT DATA BASE WAS ALREADY UNDER REVIEW DUE TO OTHER OPERATOR COMPLAINTS. A NEW DATA BASE WAS RELE ASED AND FORWARDED. ATTEMPTS TO LOAD THE NEW DATA BASE INTO THE TAWS UNITS FAILED DUE TO A COMMUNICATION PROBLEM BETWEEN 2 L 7 2 4F 4 F A16WE E2EA 2008022000021 20080220 00021 EU 2008 2 20 CA080121004 1 20080118 G 7820 L24266710000 BAFFLE ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA MUHBR MTV MTV9* EU EXHAUST CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) INTERNAL BAFFLE ATTACH WELD WAS FOUND CRACKED DURING A 100 HOUR INSPECTION. (TC NR 20080121004) 1 L 7 1 3O 3 O 0 A76EU 1E10 5 C P24NE 2008022000022 20080220 00022 EU 2008 2 20 CA080121005 1 20080118 G 6230 350A37000402 GUIDE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE SWASHPLATE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 602 (CAN) DURING A SCHEDULED 100 HOUR INSPECTION THE COLLECTIVE LEVER WAS RAISED TO EXAMINE THE SWASHPLATE GUIDE. IT WAS DI SCOVERED THAT THE SELF ADHESIVE TAPE APPLIED TO THE GUIDE WAS BUNCHED UP BETWEEN THE ROTATING SWASHPLATE AND THE SWASHPL ATE GUIDE. THE ROTATING SWASHPLATE CONTACTED THE SWASHPLATE GUIDE LEAVING LIGHT WEAR MARKS AROUND THE CIRCUMFERENCE. T HE SWASHPLATE GUIDE WAS REPLACED AND WILL BE SENT TO THE MFG FOR EVALUATION AND SERVICEABILITY CHECK. (TC NR 20080121005 ) 1 G 7 1 3U 3 U H9EU E19EU 2008022000023 20080220 00023 NM 2008 2 20 CA080121007 1 20080116 G 2436 VOLT REGULATOR BOEING 727 727225 1384077 NM PWA JT8 JT8D15 52051 NE ODOR W O OTHER B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING FLIGHT CREW SHUTDOWN CHECKLIST, ON APU POWER, SMOKE ALARM SOUNDED IN THE AC LAVATORY. LAVATORY INSP REVEAL ED SOME SMOKE. ALARM SILENCED WHILE INSPECTING THE LAVATORY AREA. AFTER APPROXIMATELY 30 SECONDS, THE ALARM SOUNDED AG AIN, AND THE AC POWERED DOWN. MAINT INSPECTED THE LWR E/E COMPARTMENT AND FOUND SUBSTANTIAL AMOUNT OF SMOKE WITH AN EL ECTRICAL BURNING ODOR. FIRE DEPARTMENT WAS CALLED BY THE FLIGHT CREW. MAINT DISCONNECTED THE MAIN AC BATTERY AND DISCON NECTED THE BATTERY CHARGER. NO OBVIOUS FAULTS WERE NOTED WITH THE BATTERY OR CHARGER AND BOTH UNITS DID NOT APPEAR TO BE OVERHEATED. THE AC WAS THEN REPOWERED USING ONLY EXTERNAL POWER WITH NO FURTHER SMOKE EVIDENT. INSP OF ALL ELECTRICAL R 2 L 7 3 4F 4 F A3WE E2EA 2008022000024 20080220 00024 WP 2008 2 20 CA080121008 1 20080109 G 6310 369D25351DSN SPRAG CLUTCH HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL MAIN ROTOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 958 (CAN) DURING 300 HOUR INSPECTION PART WAS FOUND TO HAVE PITTING ON SEVERAL ELEMENTS. SPRAG CLUTCH REPLACED. (TC NR 2008 0121008) 1 G 7 1 3U 3 U H3WE E4CE 2008022000027 20080220 00027 SO 2008 2 20 CA080121009 1 20080108 G 2421 ALU8421R ALTERNATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCC4Y HCC4YR2 GL INOPERATIVE W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 278 (CAN) IN CRUISE, AC STARTED TO LOOSE ELECTRICAL POWER. FIRST INDICATION, THE TRANSPONDER FAILED. AC THEN RETURNED TO AIR PORT. BOTH LT AND RT ALTERNATOR FAIL INDICATOR LIGHTS REMAINED OUT DURING THE FLIGHT. UPON INSP NEITHER ALTERNATOR WAS C HARGING THE SYS. THE ONLY POWER SUPPLY WAS THE AC BATTERY. THE LT ALTERNATOR WAS FOUND TO BE UNSERVICEABLE. THE RT ALTER NATOR, BECAUSE OF THE ADDED ELECTRICAL LOAD PUT ON IT, CAUSED THE ALTERNATOR BELT TO SLIP ON THE PULLEY, MAKING THE ALTE RNATOR INOPERATIVE. ALL AC RADIOS, NECESSARY LIGHTS AND DEICING HEAT WAS ON AT THIS TIME. (TC NR 20080121009) 1 L 7 2 3O 3 O A20SO E14EA 5 C P52GL 2008022000028 20080220 00028 EA 2008 2 20 CA080121011 2 20080104 G 7414 BL600646201 MAGNETO ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA RT MAGNETO FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 890 (CAN) DURING MAGNETO CHECK PRIOR TO FLIGHT, THE RT MAGNETO FAILED. MAGNETO REPLACED AND CHECKED SERVICEABLE. (TC NR 2008 0121011) 1 G 7 1 3O 3 O H11NM E295 2008022000029 20080220 00029 NE 2008 2 20 CA080122001 2 20080108 G 7414 BL600646201 MAGNETO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE RT UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 767 (CAN) RT MAGNETO FOUND UNSERVICEABLE ON PREFLIGHT. MAGNETO CHANGED, GROUND RUN AND LEAK CHECK CARRIED OUT SERVICEABLE. ( TC NR 20080122001) 1 G 7 1 3O 3 O H11NM 1E4 2008022000030 20080220 00030 NM 2008 2 20 CA080122002 1 20080105 G 5320 WEB DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2452 (CAN) DURING MAINT ROUTINE INSP, THE NOSE LANDING GEAR GROUND LOCK MECHANISM WAS FOUND HARD TO OPERATE. FURTHER INVESTIG ATION REVEALED THAT THE FLOOR WEB AT ZONE 112, STA X97 WAS CRACKED CAUSING THE GROUND LOCK LEVER TO CONTACT THE PIVOT TU BE ARM. THE CRACKED AREA WAS REPAIRED IN AUGUST 2006 IAW RD8-53-0638. THE AC HAS ACCUMULATED 2451:46 HOURS AND 3379 CYCL ES SINCE REPAIRED. THE OLD PATCH WAS REPLACED IAW THE ABOVE RD AND THE AC WAS RELEASED INTO SERVICE. (TC NR 20080122002) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081104 CE 2008 11 4 CA080122003 1 20080121 G 5350 STRUCTURE CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL TAIL CONE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 16225 (CAN) WHILE INSPECTING SOME ITEMS, MFG CONTINUED AIRWORTHINESS PROGRAM IT WAS NOTICED THAT 2 CRACKS CAME FROM THE RUDDER CABLE HOLES AND ANOTHER CRACK CAME FROM THE NUTPLATE UNDER THE DOUBLER. CONTINUED AIRWORTHINESS INSP 53-40-04 COVERS TH IS INSPECTION BUT IS N/A BY S/N ON OUR ACFT. A NEW BULKHEAD IS ORDERED AND WILL BE CHANGED BEFORE NEXT FLIGHT. (TC NR 20 080122003) 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2008022000031 20080220 00031 SO 2008 2 20 CA080122005 1 20080111 G 3213 753227 YOKE PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YK2 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3004 273354 (CAN) DURING ANNUAL INSP, A CRACK WAS FOUND ON THE OB SIDE OF THE LT MAIN LANDING GEAR YOKE. THE CRACK WAS ALONG THE ED GE OF THE CASTING MARK AT THE TOP WHERE THE OLEO SHAFT IS ATTACHED TO THE YOKE. THE CRACK WAS FOUND BY VISUAL INSPECTION . (TC NR 20080122005) 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2008022000032 20080220 00032 GL 2008 2 20 CA080122007 3 20080122 G 6110 3GFR34C703 PROPELLER CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL LEAKING W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA 202 (CAN) AFTER START UP AND REPOSITION OF AC FOR FUEL, A HYD LEAK WAS NOTED FROM THE PROPELLER, RUNNING FROM THE BLADE ROOT TO THE BLADE TIP. THE PROPELLER WAS REMOVED AND ROUTED TO A OVERHAUL SHOP FOR REPAIR. (TC NR 20080122007) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2008022000033 20080220 00033 NE 2008 2 20 CA080122008 2 20080118 G 8550 LINE DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN1 52008 NE HARTZL HCB3R HCB3R302 GL OIL SYSTEM OBSTRUCTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN ENG WAS REMOVED FOR O/H, IT WAS DISCOVERED THAT IN THE OIL DELIVERY LINE THERE WAS PLASTIC DEBRIS FROM THE CO NTAINERS USED TO REPLENISH THE ENGINE OIL. THERE WAS POOR MAINTENANCE PRACTICE WHEN OPENING THESE CONTAINERS TO POUR TH E OIL IN THE TANK IN THE AC, THE CAPS WERE NOT FULLY REMOVED FROM THE CONTAINERS. THERE WERE NUMEROUS ITEMS IN THE OIL S YS AND THIS HAS THE POTENTIAL TO RESTRICT THE FLOW OF THE OIL RESULTING IN SHUTDOWN OF THE ENGINE. CARE MUST BE TAKEN W HEN CARRYING OUT THIS TASK AND THIS NEEDS TO BE COMMUNICATED TO ANYONE WHO IS SERVICING THESE AC. (TC NR 20080122008) 1 H 7 1 3R 3 R RC A806 5E1 5 C P28EA 2008022000034 20080220 00034 2008 2 20 CA080122009 4 20080120 G 3457 10706 ANTENNA BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL GPS CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) GPS ANTENNA WAS REPLACED DUE TO NO SIGNAL TO UNS-1K FMS. UPON REMOVING ANTENNA FROM FUSELAGE (UPPER COCKPIT ROOF), FOUND HEAVY CORROSION ON ANTENNA AND SOME CORROSION ON FUSELAGE SKIN. A QUICK REVIEW OF THE RECORDS SHOWS THAT THIS ANT ENNA WAS LIKELY INSTALLED AT THE FACTORY (2001) THERE WAS NO SEALANT UNDER THE ANTENNA AND NO GASKET MATERIAL EITHER. TH ERE WAS SOME SEALANT AROUND THE EDGE. THE CO-AX CONNECTER WAS ALSO CORRODED. REPLACED ANTENNA, CLEANED, ETCHED, ALODINED AND PRIMED THE SKIN AND RETURNED A/C TO SERVICE. (TC NR 20080122009) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2008022000036 20080220 00036 SW 2008 2 20 CA080122010 1 20080111 G 6230 206010447109 BEARING BELL 206 206L4 1182110 SW SWASHPLATE ASSY CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 19193 275 EAJG11437 (CAN) DURING A PHASE INSP, MECHANIC FOUND A CHAFED AREA ON TOP OF THE COLLECTIVE LEVER BEARING EAR P/N 206-010-447-109. FURTHER INSP REVEALED CHAFING AT BOTTOM OF BOTH SWASHPLATE ROTATING RING BEARING EARS. CHAFED AREAS APPROX 0.020-0.040 INCH DEPTH. MECHANIC POSITIONED THE COLLECTIVE STICK FULL DOWN AND CYCLIC FULL FWD WHILE CAUTIOUSLY LINING UP EACH ROTAT ING RING WITH THE COLLECTIVE LEVEL FOR A CLEARANCE CHECK. BOTH WERE CONTACTING. REPLACED SWASHPLATE, DRIVE LINK AND M/R PITCH CHANGE LINK ASSY`S. COLLECTIVE AN CYCLIC CONTROLS WERE RE-RIGGED. (TC NR 20080122010) 1 G 7 1 3U NC H2SW 2008022000039 20080220 00039 SO 2008 2 20 CA080123001 2 20080119 G 8530 CYLINDER CESSNA 150 150H 2071818 CE CONT O200 O200A 17020 SO MCAULY 1A101 1A101DCM GL NR 4 LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 721 684508A (CAN) WHILE CARRYING OUT MAINT, CYLINDER NR 4 WAS FOUND LOW ON COMPRESSION 45/80. AIR WAS LEAKING THROUGH THE EXHAUST. (TC NR 20080123001) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2008022000040 20080220 00040 SW 2008 2 20 CA080123002 1 20080122 G 3220 99353 COLLAR GULSTM 690TP 690 0141720 SW GARRTT TPE331 TPE3315251K NM HARTZL HCB3T HCB3TN5 GL NLG WORN W O OTHER J WARNING INDICATION LD LANDING 1 CA (CAN) UNSAFE NOSE GEAR, CIRCLING AT AIRPORT, DECIDED TO FLY AC TO ANOTHER AIRPORT. AC CAME BY SLOW WITH GEAR DOWN. NOSE LOOKED DOWN HOWEVER NOSE WHEEL WAS COCKED TO THE RT. PILOT CIRCLED TO THE WEST UNTIL EMERG EQUIPMENT WAS IN PLACE. THEN LANDED RUNWAY 29. HELD THE NOSE OFF AS LONG AS HE COULD THEN LET IT DOWN. NOSE GEAR COLLAPSED. 4 PEOPLE ON THE TAIL WE PULLED THE NOSE GEAR DOWN, THEN TOWED AC TO OUR HANGAR. IT WAS NOTED THAT THEIR WAS A CROSSWIND WHEN THE AC DEPARTED MINOR DAMAGE TO NOSE DOORS. MAINT IS LOOKING INTO THE PROBLEM. MAINT FOUND EXCESSIVE WEAR IN NOSE GEAR TRUNNION SLOT (PN 9935-1) AND DAMPING COLLAR (PN 9935-1, -3). EXCESSIVE WEAR CAUSED BINDING AND PREVENTED NOSE WHEEL FROM CENTERING WHEN 1 H 7 2 3T 4 T 2A4 E2WE 6 C P15EA 20081229 CE 2008 12 29 CA080123003 1 20080123 G 3245 0923150 TUBE CESSNA 425 425 2076018 CE PWA PT6 PT6A112 52043 NE MCAULY 4HFR34 4HFR34C762 NE NLG TIRE DAMAGED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 51 (CAN) THE FLAT WAS DISCOVERED UPON LANDING AND THE A/C WAS SHUTDOWN BECAUSE IT WAS UNABLE TO TAXI. THE FENDER AND THE WH EEL WERE REPLACED. UPON INSP OF THE FLAT TIRE IT WAS DISCOVERED THAT THE INNER TUBE WAS SPLIT ALONG THE SEAM, THERE WAS NO ISSUES OR HOLES IN THE TIRE AND THE ASSY WAS ASSEMBLED CORRECTLY. 1 L 7 2 3T 3 T RT A7CE E4EA 6 C 3PNE 2008022000043 20080220 00043 SW 2008 2 20 CA080123007 1 20080115 G 2810 71494R FUEL TANK BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL OUTBOARD CRACKED W K NONE K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 2686 (CAN) GAS FUMES WERE DETECTED AROUND AC. WHEN RT OB FUEL TANK WAS REMOVED A CRACK WAS FOUND ON A REPAIRED RADIUS OF THE LATERAL RE-ENFORCEMENT INDENT OF THE TANK. 720 HOURS SINCE THE TANK WAS REPAIRED. (TC NR 20080123007) 1 H 7 1 3O 3 O A21CE E286 5 N P874 2008022000044 20080220 00044 SW 2008 2 20 CA080123008 1 20080115 G 2810 71493R FUEL TANK BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL INBOARD CRACKED W K NONE K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 2686 (CAN) GAS FUMES WERE DETECTED AROUND AC. WHEN THE RT IB FUEL TANK WAS REMOVED A CRACK WAS FOUND AROUND THE FUEL VENT IN TERCONNECT WELD. (TC NR 20080123008) 1 H 7 1 3O 3 O A21CE E286 5 N P874 2008022000056 20080220 00056 NM 2008 2 20 CA080124001 1 20080123 G 3297 471515 WIRE HARNESS BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NR 2 WOW FAULTY W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) GEAR WOULD NOT RETRACT AFTER TAKEOFF, RETURN TO FIELD. CREW ELECTED TO RETURN BASE. MAINTENANCE FOUND THE NLG NR 2 WOW HARNESS TO BE AT FAULT. NEW HARNESS INSTALLED, AIRCRAFT RETURNED TO SERVICE. (TC NR 20080124001) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 2008022000057 20080220 00057 NM 2008 2 20 CA080124002 1 20080124 G 2910 SWIVEL BOEING 727 727247 138408F NM PWA JT8 JT8D15 52051 NE NR 6 SLAT LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 8455 709 (CAN) AC WAS DISPATCHED AND DURING CRUISE FLIGHT, THE FLIGHT ENGINEER NOTICED THAT THE (A) SYS HYDRAULICS INDICATED .125 0 OF A TANK REMAINING. THE CREW DECIDED TO DECLARE AN EMERGENCY AND THE LANDING GEAR NEEDED TO BE CRANKED DOWN. THE AC L ANDED SAFELY AND WAS TOWED OFF THE RUNWAY TO THE RAMP. MAINT TROUBLESHOT THE SNAG AND FOUND THAT THE NR 6 LEADING EDGE SLAT WAS LEAKING HYD FLUID FROM A LEAK IN THE SWIVAL ASSY OF THE SLAT. THE ACTUATOR WAS REMOVED AND REPLACED AND THE HYD SYS WAS REPLENISHED. THE AC WAS FUNCTION TESTED SERVICEABLE AND RETURNED TO SERVICE. (TC NR 20080124002) 2 L 7 3 4F 4 F A3WE E2EA 2008022000059 20080220 00059 SW 2008 2 20 CA080124003 1 20080117 G 3210 D212664201 CROSSTUBE BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE LG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2236 30294 (CAN) WHILE THE ENGINEER WAS CONDUCTING THE DI, A CRACK IN THE AFT DART CROSSTUBE WAS DISCOVERED. THE DART CROSSTUBE FOL LOWS 300/600 HR INSP CYCLE. CROSSTUBE WAS 60.7 FROM 300 HR INSP, AND 360.7 FROM THE 600 HR. CROSSTUBE WAS CHECKED FOR EX CESSIVE DEFLECTION, TOTAL SPREAD WAS 107 INCHES AND SYMMETRICAL TO THE MIDPOINT OF THE CROSSTUBE. THESE MEASUREMENTS ARE ACCEPTABLE WITH THE ICA-D212-664 MANUAL. THE CRACK WAS ON THE LOWER PART OF THE UPPER PORTION OF TUBE AND 4.5 INCHES FR OM MIDPOINT. AT THE TIME OF DISCOVERY THE HELICOPTER WAS BEING USED FOR HELI-SKIING. NO HARD LANDING HAD OCCURED DURING ITS INSTALLATION LIFE. MEMOS TO INSPECT THE OTHER AC LANDING GEAR HAS BEEN SENT TO THE ENGINEERS. (TC NR 20080124003) 1 G 7 1 4U 4 U H1SW E17EA 2008022000060 20080220 00060 WP 2008 2 20 CA080124005 2 20080122 G 7260 8937373 NUT SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE GEAR SHAFT BACKED OUT W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA 2034 (CAN) A/C CAME IN TO THE MAINT HANGER DUE TO HAVING A CHIP LIGHT COME ON IN THE COCKPIT. INSP FROM MAINT NOTICED THAT TH ERE WAS METAL ON THE CHIP DETECTOR OF ENGINE P-54121. AT THAT TIME THE ENGINE WAS FORWARDED TO THE ENGINE SHOP FOR FURTH ER INSP. THE ENGINE WAS DISMANTLED TO FIND THAT THE HIGH SPEED PINION NUT (HSP) PN 893737-3, WAS STARTING TO BACK OFF FR OM ITS OVERHAULED TORQUE SPECIFICATIONS. THE HSP WAS OVERHAULED ON THE 22 JULY 05. THE NUT WHEN TORQUED IS SUPPOSED TO HAVE A PIN PN S815N4-0-200 STAKED BESIDE THE NUT TO PREVENT IT FROM BACKING OFF. UPON FURTHER INSPECTION OF THE PIN AREA IT DOES NOT LOOK LIKE THERE WAS EVER A PIN INSTALLED AT THE TIME OF INSP, WITH THE NUT BACKING OFF OF THE HSP THIS COUL 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 20081104 SW 2008 11 4 CA080124006 1 20080123 G 7921 8945682 LINE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE OIL COOLER CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) LINE FOUND LEAKING BETWEEN OIL COOLER TO FUEL HEATER. THE CHAF WAS FOUND BY THE STEEL IDENTIFIER ON THE LINE. LINE WAS REPLACED AND AREA WAS CORRECTED SO THAT THE NEW LINE WOULD CHAF IN THE FUTURE (TC NR 20080124006) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081104 SW 2008 11 4 CA080124007 1 20080123 G 7921 8945682 LINE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE OIL COOLER CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) LINE FOUND LEAKING BETWEEN OIL COOLER TO FUEL HEATER. THE CHAFE WAS FOUND BY THE STEEL IDENTIFIER ON THE LINE. LIN E WAS REPLACED AND AREA WAS CORRECTED SO THAT THE NEW LINE WOULD NOT CHAFE IN THE FUTURE. (TC NR 20080124007) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081104 WP 2008 11 4 CA080124008 2 20080121 G 7313 310323259 FUEL NOZZLE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED FUEL NOZZLE CHANGE A NOZZLE WAS FOUND TO BE CRACKED IN THE AREA, SECONDARY MANIFOLD FITTING THAT MFG SAYS TO INSPECT. (TC NR 20080124008) 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 20081104 WP 2008 11 4 CA080124009 2 20080120 G 7310 310323259 FUEL NOZZLE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FUEL NOZZLE FOUND CRACKED ON SECONDARY MANIFOLD DURING SCHEDULED NOZZLE CHANGE IN THE AREA THAT MFG SAYS TO INSPEC T FOR CRACKS. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 2008022000061 20080220 00061 EA 2008 2 20 CA080124011 1 20080124 G 5330 SKIN PANEL DHAV DHC7 DHC7102 2802708 EA FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 068 (CAN) WHILE CONDUCTING A CORROSION INSP ON AC, VENEZUELAN REGISTRATION YV1000, IAW THE CUSTOMERS EQUALIZED MAINT PROGRAM . NUMEROUS AREAS OF CORROSION WERE DETECTED THROUGHOUT THE AC. A THRESHOLD AND REPETITIVE CORROSION INSP PROGRAM IS MAN DATED BY ADCF-98-03 AND IS TO BE CARRIED OUT IAW THE AC CORROSION PREVENTION AND CONTROL MANUAL (PSM 1-7-5). NO INFORMAT ION IS AVAILABLE TO KNOW IF THE THRESHOLD OR REPEAT CORROSION INSPECTIONS WERE COMPLIED WITH. WHILE CONDUCTING THE 3-YE AR REPETITIVE DISBOND INSP REQUIRED BY ADCF-94-15 IAW MFG SB 7-51-1 AND THE NDT MANUAL (PSM 1-7-7A) PART 5, SEVERAL AREA S OF DISBOND WERE FOUND ON THE FUSELAGE SKIN PANELS, HORIZONTAL STABILIZER SKIN PANELS AND WING PANELS. IN ADDITION, ARE 2 H 7 4 4T A20EA 2008022000064 20080220 00064 SO 2008 2 20 CA080124013 2 20080109 G 8530 636242 GUIDE CONT CONT O550 IO550D 17042 SO EXHAUST WORN W K NONE O OTHER IN INSP/MAINT 1 CA 296 (CAN) 5 CYLINDER ASSYS RECEIVED FOR REPAIR DUE TO LOW COMPRESSION. ABNORMALLY HIGH WEAR WAS FOUND INSIDE THE EXHAUST GUI DES. WEAR PATTERNS ON THE EXHAUST VALVES AND SEATS INDICATED THAT THEY WERE NOT PROPERLY ALIGNED CAUSING THE VALVE STEMS TO WEAR AGAINST THE GUIDES. (TC NR 20080124013) 3 O E3SO 2008022000065 20080220 00065 SO 2008 2 20 CA080124014 2 20080111 G 8530 628309 GUIDE CONT 655483A11 CONT O200 O200A 17020 SO CYLINDER UNDERSIZE W K NONE O OTHER IN INSP/MAINT 1 CA 188 (CAN) EXHAUST VALVE GUIDES FOUND TO BE 0.002 INCH SMALLER THAN THEY SHOULD BE AFTER 2 CYLINDERS WERE SENT IN FOR REPAIR DUE TO STUCK EXHAUST VALVES. (TC NR 20080124014) 3 O E252 20081219 CE 2008 12 19 CA080124015 1 20080123 G 5753 55250007983 BEARING CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE TE FLAP MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ACFT ARRIVED AT OUR FACILITY FOR PAINT. UPON DISASSEMBLY MX NOTED THE BOLT SECURING THE RT FLAP CENTRE AFT ROLLER WAS LOOSE. FURTHER INVESTIGATION AND REMOVAL DETERMINED THAT THE BEARING AND SHIM REQUIRED TO BE UNDER THE HEAD OF BOL T WAS MISSING AND PROBABLY NOT INSTALLED THE LAST TIME MX WAS DONE IN THAT AREA. 1 L 7 2 4F 4 F A22CE E1NE 2008022000066 20080220 00066 SO 2008 2 20 CA080124016 2 20080123 G 8530 636242 GUIDE CONT 655471A4 CONT O550 IO550D 17042 SO CYLINDER WORN W K NONE O OTHER IN INSP/MAINT 1 CA 803 (CAN) RECEIVED CYLINDER FOR REPAIR DUE TO LOW COMPRESSION. WHEN RESURFACING THE VALVE SEATS IT WAS NOTED THAT THE INTAKE GUIDE AND SEAT DID NOT PROPERLY LINE UP. THIS COULD HAVE CAUSED THE LEAK THAT RESULTED IN LOW COMPRESSION. (TC NR 20080 124016) 3 O E3SO 2008022000067 20080220 00067 CE 2008 2 20 CA080125001 1 20080122 G 7931 OIL SYSTEM CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE PRESSURE UNKNOWN W B E EMER. DESCENT ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 576 (CAN) APPROXIMATELY 5 -7 MINUTES AFTER TAKEOFF, THE WARNING LIGHT (LOW OIL PRESS R ) WAS OBSERVED ON THE M.A.P. AND (0) ON THE OIL PRESSURE INDICATOR TAPE . A PRECAUTIONARY ENGINE SHUTDOWN WAS PERFORMED FOLLOWED BY THE DECLARATION OF AN EME RGENCY. ENG IS STILL UNDER INVESTIGATION TO DETERMINE THE CAUSE. (TC NR 20080125001) 2 L 7 2 4F 4 F RT A22CE E00059EN 2008022000068 20080220 00068 EA 2008 2 20 CA080125002 1 20080122 G 2752 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE FLAP FAILED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA (CAN) THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE ON FINAL AFTER SELECTING FLAP TO 8 DEGREES. AN EMERGENCY WAS DECLARE D AND THE AC CONDUCTED A FLAPLESS LANDING WITHOUT FURTHER INCIDENT. THE AC WAS FERRIED. ALL FLAP ACTUATORS WERE REPLACED AND THE AC WAS RELEASED. A SUCCESSFUL TEST FLIGHT WAS CONDUCTED AND THE AC RETURNED INTO SERVICE. ALL FLAP ACTUATORS WE RE SENT TO THE SHOP FOR LOW TEMPERATURE TORQUE CHECK. RT NR 4 FLAP ACTUATOR P/N 854D100-20 S/N OFF 1911, TSN 8231 TSR 29 46 CSN 6684 CSR 2558 RT NR 3 FLAP ACTUATOR PN 853D100-20 S/N OFF 2604, TSN 8231 TSR 2946 CSN 6684 CSR 2558 RT NR 2 FLAP ACTUATOR P/N 852D100-19 S/N OFF 5996 TSN 2946 TSR 2946 CSN 2558 CSR 2558 RT NR 1 FLAP ACTUATOR PN 852D100-19 SN OFF 5948 2 L 7 2 4F 4 F RT A21EA E15NE 2008022000069 20080220 00069 EA 2008 2 20 CA080126001 1 20080118 G 5610 NP13932113 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE LT/ CAPTAIN BROKEN W O OTHER O OTHER CR CRUISE 1 CA 14906 (CAN) (CAPTAINS WINDSHIELD SHATTERED IN FLIGHT. PRESSURIZATION STAYED NORMAL AND THE AC CONTINUED. MAINT IS GOING TO CH ANGE THE WINDSHIELD). REPLACED THE WINDOW WINDSHIELD, MAIN PILOT, NP-139321-13 01355H5650 TSO: 14906.50 CSO: 12838 (TC NR 20080126001) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022000070 20080220 00070 EA 2008 2 20 CA080126002 1 20080117 G 7603 1603730003 THROTTLE CONTROL CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE LT ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) CREW REPORTED LT ENG REMAINED AT HIGH POWER SETTING WHEN AC BROUGHT TO IDLE. N1 REMAINED BETWEEN 82 AND 91 PERCENT . IFSD PILOT COMMANDED IN FLIGHT SHUTDOWN: CONFIRMED, AFTER (ABORTED APPROACH) PILOT SHUTDOWN THE LT ENG USING FIRE PUS H DURING (GO AROUND). LANDED ON ONE (RT) ENGINE. NOT POSSIBLE TO LAND THE A/C WITH (LT) AT 82 TO 90 PERCENT N1 FWD THRU ST, NO ABILITY TO RETARD LT THRUST LEVER TO REDUCE THRUST AND EFFECT FUEL SHUTOFF. CONTROL ASSY, THROTTLE PUSHPULL (LT ) P/N: 1603730 AND NR 8722, 003 S/N: UKN (TC NR 20080126002) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022000072 20080220 00072 EA 2008 2 20 CA080126003 1 20080116 G 5610 601R3303320 WINDOW CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C5 30050 NE COCKPIT CRACKED W A B UNSCHED LANDING EMER. DESCENT O OTHER CR CRUISE 1 CA 9573 (CAN) AC DIVERTED, FOS SIDE WINDOW CRACKED IN FLT, CREW DECLARED EMRG NO PRESS ISSUES. NOTED CREW USED MASKS. MASKS NOT DROPPED IN CABIN. SIDE WINDOW P/N:601R33033-20, S/N: 04023H4068: CO-PILOT SIDE WINDOW 9573 HRS / 6860 CYCLES (TC NR 200 80126003) 2 L 7 2 4F 4 F RT A21EA E00063EN 2008022000073 20080220 00073 EA 2008 2 20 CA080126004 1 20080124 G 5210 NAS76A16011 BUSHING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE PAX DOOR MIGRATED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 24960 (CAN) CREW REPORTED THAT AT 12000 FT PAX DOOR WARNING MSG POSTED. FOLLOWED QRH AND RETURNED TO FIELD. FOUND BUSHING IN FWD LATCH CAM FITTING MIGRATED. REINSTALLED BUSHING IN UPPER FWD CAM LEVER REF AMM 52-11-23. NOTE: AC WAS PRE SB 601R-5 2-110 CONFIGURATION. MECHANISM GA, PASS DOOR LATCH MFG 601R31903, BUSHING: P/N: NAS76A16-011 MIGRATED 24960:41 TSN / 2 2803 CSN (TC NR 20080126004) 2 L 7 2 4F 4 F RT A21EA E15NE 2008022000074 20080220 00074 EU 2008 2 20 CA080128001 1 20080121 G 2710 19004212401 CONTROL CABLE EMB ERJ190 ERJ190100IGW 3260408 EU GE CF34 CF3410E5A1 30022 NE AILERONS BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AILERON CONTROL CABLES INSP, ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 190-04212-401 AND PN 190-04209 -401, RT PN 190 -05550-401 AND PN 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATED AT LT AND RT WING S RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REFERENCE J/C 27-11-00-003-LT/1 SNAGS NO 128, 165 AND J/C 27-11-00-0 03-RT/2 SNAGS NR 87, 166. THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED O N THE FAIRLEAD. SAME FINDING ON ERJ190 NR 00015 HRS5830 CYCLES 2643, C02 CHECK AND ALSO ERJ190 NR 00013 HRS5720 CYCLES 2 635 C02 CHECK. (TC NR 20080128001) 2 L 7 2 4F 4 F RT A57NM E00070EN 2008022000075 20080220 00075 EA 2008 2 20 CA080128002 1 20080127 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN EXERCISING FLAPS DURING MAINTENANCE COLD WEATHER CHECKS, FLAP FAIL MESSAGE SHOWED AS SOON AS FLAPS SELECTED. A/C FERRIED, MFG FSR CALLED TO ATTEND HANGAR FOR TEARDOWN AND INSPECTION. MORE TO FOLLOW. (TC NR 20080128002) 2 L 7 2 4F 4 F RT A21EA E15NE 20080520 SW 2008 5 20 CA080128004 1 20080128 G 2720 CONTROL CABLE AIRTRC AT802 AT802A 0390308 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MA3 GL RUDDER STUCK W K NONE O OTHER IN INSP/MAINT 1 CA 499 (CAN) DURING INSP, THE LT RUDDER CABLE WAS FOUND SNAGGED ON THE WATER RUDDER CABLE PULLEY GUARD. (TC NR 20080128004) 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2008022000078 20080220 00078 SW 2008 2 20 CA080128007 1 20080118 G 6730 206076062 SERVO BELL 407 407 1182206 SW ALLSN 250C 250C47B GL MAIN ROTOR NOISY W O OTHER O OTHER DE DESCENT 1 CA 6987 (CAN) WORN LINKAGE AND PILOT VALVE CAUSED SERVO TO MAKE LOUD GROWLING NOISE. THIS WAS AN INTERMITTENT PROBLEM THAT COULD BE INDUCED BY CERTAIN CONTOL INPUTS. THE SOUND WAS FINALLY DETERMINED TO BE COMING FROM THE RT SERVO AND IT WAS REPLACE D. THERE WERE NO CONTROL PROBLEMS ENCOUNTERED AND THE SERVO HAS SINCE BEEN OVERHAULED. (TC NR 20080128007) 1 G 7 1 3U 3 U O H2SW E1GL 2008022000079 20080220 00079 SW 2008 2 20 CA080129003 1 20080116 G 7921 MS172244 NUT BELL 407 407 1182206 SW ALLSN 250C 250C47B GL OIL COOLER BLOW UNDERTORQUED W O OTHER O OTHER NR NOT REPORTED 1 CA 1650 1650 (CAN) DURING 100 HR, LUBRICATION OF T/R HANGER BEARINGS, IT WAS NOTED THAT THE AFT HEAT SHIELD WAS FREE TO ROTATE, UP ON FURTHER INSPECTION IT WAS FOUND THAT THE AFT SPANNER NUT WAS LOOSE, BUT THE LOCK WASHER WAS STILL IN THE LOCK POSITION. RECORDS SHOW THAT THIS PART WAS NEVER TAKEN APART OR WORK ON SINCE THE AC LEFT THE FACTORY. (TC NR 20080129003) 1 G 7 1 3U 3 U O H2SW E1GL 2008022000080 20080220 00080 WP 2008 2 20 CA080129005 1 20080128 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 1620 (CAN) DURING OVER HAUL, THE CAGE OF THE SPRAG CLUTCH WAS FOUND CRACKED IN 8 PLACES. (TC NR 20080129005) 1 G 7 1 3O 3 O H11NM 1E4 20080520 EA 2008 5 20 CA080130001 1 20080128 G 3246 AN620A BOLT AIRCRFTPRDTS DHAV DHC6 DHC6100 2802610 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL FLOAT ASSY BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION, THE TIE ROD TO FUSELAGE LUG WAS FOUND TO HAVE ONE OF THE (2) ATTACH BOLTS BROKEN. THE BREAK OCC URRED IN THE THREADED AREA OF THE BOLT. BOTH BOLTS WERE REPLACED AND THE AC WAS RETURNED TO SERVICE. THIS AC IS OPERATED IN A GENERALLY ROUGH WATER ENVIRONMENT, WITH SWELLS, LARGE WAVES AND LARGE BOAT WAKES MAKING THE LANDING AREA CHALLENGI NG AT TIMES. (TC NR 20080130001) 1 H 7 2 3T 3 T RT A9EA E4EA 6 C P15EA 2008022000081 20080220 00081 EU 2008 2 20 CA080130002 1 20080115 G 3212 29022979 HEAD AIRCRUISERS BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL EMERGENCY FLOAT LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN INSPECTION THE EMERGENCY FLOAT SYS WERE DEPLOYED ACCIDENTALLY. (2) REFURBISHED KITS (PN:28022969) WERE O RDERED. BOTH VALVE ASSY (PN: 105-E-0031) WERE REBUILDED INCLUDING SHEARHEAD ASSY. (PN:29022979) NITROGEN PRESSURE WAS BR OUGHT UP TO 3200PSI AND CHECK FOR LEAK. AFTER 2 DAYS PRESSURE STARTED TO DROP SLOWLY. BOTTLE WERE REFILLED WITH NITROGEN TO 3200 PSI AND PRESSURE CONTINUE TO DROP SLOWLY ON LT SIDE. BOTTLE WAS REMOVED FROM FLOAT AND CHECK FOR LEAK. LEAK WAS FOUND COMING FROM SHEARHEAD ASSY. SHEARHEAD WAS REPLACED AND FLOAT RETURNED TO SERVICE. (TC NR 20080130002) 1 G 7 2 3U 3 U H3EU E4CE 2008022100001 20080221 00001 CE 2008 2 21 CA080131003 1 20080116 G 7110 B140048 LATCH BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCE4N HCE4N3 NE COWLING INOPERATIVE W O OTHER O OTHER CR CRUISE 1 CA 309 (CAN) THE LOWER FWD COWLING HOOK AND CAM ASSY FAILING TO LATCH WITH THE UPPER COWL ASSY WHEN INSTALLING THE COWLS ON THE ENGINE. IT IS POSSIBLE TO HAVE THE ALIGNMENT MARKS INDICATE A SUCCESSFUL LATCH WHEN IN FACT THE HOOK MAY HAVE MISSED TH E CAM DURING ROTATION OF THE HOOK. A THOROUGH VERIFICATION OF A SUCCESSFUL LATCH, IN ADDITION TO THE VISUAL ALIGNMENT MA RKS INDICATION, IS REQUIRED WHEN INSTALLING ENGINE COWLS. (TC NR 20080131003) 1 L 7 2 4T 4 T A24CE E4EA 5 C P10NE 2008022100002 20080221 00002 NE 2008 2 21 CA080131008 3 20080109 G 6114 WASHER 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 603 B1991 B1991 (CAN) PROP MODEL 2D30-237 S/N B1991. UPON RECEIPT CUSTOMER WAS COMPLAINING THAT PROP WAS NOT CYCLING. ONCE PROP WAS DISM ANTLED A CRACKED THRUST BEVEL WASHER WAS NOTICED. THE THRUST WASHER IS CRACKED RIGHT THROUGH, CAUSING THE BLADE TO HANG UP INSIDE OF THE BARREL. THIS UNIT HAS 603.3 HRS SLOH IN NOV 17/05. (TC NR 20080131008) 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 2008031900179 20080319 00179 CE 2008 3 19 CA080201001 1 20080130 G 3230 C6189CL CHAIN BEECH 99 99 1154002 CE PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL NLG BENT W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) DURING CLIMB, A LOUD NOISE WAS HEARD AND THE GEAR FAILED TO RETRACT (3) GREEN INDICATION DURING INSP THE AFT NOSE GEAR CHAIN WAS BROKEN AND THE REMOTE CIRCUIT BREAKER WAS FOUND POPPED NOSE CHAIN AND MASTER LINK REPLACED AND SYS INSPEC TED 5 GEAR CYCLES C/O AND NO FAULTS FOUND RECORDS INSPECTED FOR COMPLIANCE WITH AD 72-10-04 PART A FOUND CARRIED OUT AT INTERVALS NOT EXCEEDING 100 HOURS (TC NR 20080201001) 1 L 7 2 3T 3 T A14CE E4EA 6 C P15EA 20080520 2008 5 20 CA080201002 2 20080201 G 7414 1051324 SPRING 107902010 IMPULSE COUPLING MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 CA 1220 (CAN) MAGNETO WAS RECEIVED ON AN ENG FOR INSP, DUE TO VIBRATION. MAG ROTOR WAS SPUN BY HAND TO INSPECT BEARINGS AND WHEN THE IMPULSE COUPLING FLYWEIGHTS CONTACTED THE STOP PINS THE FORCE REQUIRED TO WIND UP THE SPRING WAS FOUND TO BE LESS T HAN NORMALLY REQUIRED. THE MAG HAD A 500 HOUR INSP PERFORMED 116.2 HOURS AGO AND IT APPEARS THAT THE SPRING WAS IMPROPER LY WOUND AT THAT TIME. REPAIR OF MAG IS BEING HELD OFF PENDING ESTIMATE OF ENTIRE ENGINE. (TC NR 20080201002) 20081104 NE 2008 11 4 CA080204001 2 20080201 G 7261 OIL SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE NR 1 ENGINE OVERSERVICED W B E EMER. DESCENT ENGINE SHUTDOWN W J INADEQUATE Q C WARNING INDICATION CR CRUISE 1 CA (CAN) DUE TO HIGH OIL TEMP INDICATION, NR 1 ENGINE WAS SHUTDOWN BY THE CA, ACFT LANDED IN IAD WITHOUT INCIDENT AND TAXIE D TO THE GATE UNDER ITS OWN POWER. MAINT INSPECTED ACFT. INVESTIGATION OF ENGINE WAS BELIEVED TO BE OVER SERVICED. WHEN MAINT OPENED THE OIL TANK APPROX. 3 QUARTS OF OIL SPILLED OUT OF THE TANK. SUSPECT THE REMOTE REPLENISHMENT SYS TO BE A T FAULT FOR THE OVER SERVICING AND HAS PLACED IT ON MEL. AFTER PROPER SERVICING LEVELS ARE MEET AND UNEVENTFUL ENGINE RU NS ARE CARIED OUT THEY PLAN TO PUT THE ACFT BACK INTO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2008031900180 20080319 00180 NM 2008 3 19 CA080204004 1 20080131 G 3232 8290018013 ACTUATOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE RT MLG DOOR UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 21658 166 (CAN) RT MAIN GEAR DOOR CAUTION LIGHT AFTER T/O. GEAR CYCLED WITH NO CHANGE, FLIGHT RETURNED TO BASE. MAINT SUSPECTS T HE FWD DOOR ACTUATOR TO BE AT FAULT. THE ACTUATOR WAS REPLACED AND FUNCTION CHECKS WERE C/O SERVICEABLE. THE ACTUATOR WA S REPAIRED 166 HOURS AGO, I HAVE REQUESTED A TEARDOWN REPORT AND WILL UPDATE FURTHER WHEN THE INFORMATION IS AVAILABLE. CURRENT A/C HOURS: 43033:33 CYCLES: 47150 (TC NR 20080204004) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2008031900182 20080319 00182 NE 2008 3 19 CA080204005 2 20080204 G 7250 3024211 TURBINE WHEEL PWA PT6 PT6A135 52043 NE ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 7075 (CAN) THE CT DISK WAS FOUND WITH (4) VISUAL CRACKS AT (3) OF THE FIRTREES. THE CRACKS ARE LOCATED AT THE EDGE OF THE TOP SERRATION RADIUS WITH THE FIRTREE FACE. THE CRACKS ARE BELIEVED TO BE RELATED TO CORROSION, THEY ARE QUITE OPEN WITH SI GN OF OXIDATION. CRACKS WERE NOTICED VISUALLY AFTER THE REMOVAL OF CORROSION AT THE EDGE ON THE FIRTREE FACE SIDE. THE F PI TEST BEFORE AND AFTER THE REMOVAL OF CORROSION COULD NOT DETECT THE CRACKS. INVESTIGATION IS ON-GOING FURTHER RESULT WILL FOLLOW. (TC NR 20080204005) 4 T E4EA 2008031900185 20080319 00185 SW 2008 3 19 CA080205004 1 20080201 G 5302 427034851103 SUPPORT BELL 427 427 1182207 SW T/R GEARBOX CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 631 (CAN) T/R GEARBOX SUPPORT CAST SURFACE FOUND CRACKED AT LWR FWD LEG, ATTACHMENT POINT FOR THE VERTICAL FIN. (TC NR 20080 205004) 1 G 7 1 3U R00001RC 2008031900186 20080319 00186 EU 2008 3 19 CA080205005 1 20080121 G 7603 350A57105721 BALL JOINT SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE THROTTLE LINK WORN W E ENGINE SHUTDOWN J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) WHEN THROTTLE WAS RETARDED DURING ENGINE START, T4 CONTINUED TO INCREASE. EMERGENCY SHUTOFF PULLED AND ENGINE MOTO RED AS T4 REACHED 900C FOR 2 SECONDS. INVESTIGATION FOUND THE THROTTLE LINK DISCONNECTED BUT THE LOCKING PIN WAS PROPER LY ENGAGED AND IN THE PROPER POSITION. INCIDENT WAS DUPLICATED 2 OUT OF 3 TIME ON TESTING. PARTS INSPECTED AND FOUND, EN D EQUIPPED AND BALL JOINT BOTH WORN. (TC NR 20080205005) 1 G 7 1 3U 3 U H9EU E19EU 20081104 WP 2008 11 4 CA080205007 2 20080129 G 7260 3588941 BEARING SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE GEARBOX WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TACH/GEN IDLER ASSY DUAL SPUR GEAR, CENTER ANTI FRICTION BEARING FOUND WITH AN UNUSUALLY HIGH AMOUNT OF RADIAL PLA Y AND WAS EXTREMELY ROUGH WHEN TURNED OVER BY HAND. THE ENGINE WAS REMOVED DUE TO CARBON STEEL PLATELETS FOUND IN THE OI L SAMPLE. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 2008031900188 20080319 00188 SW 2008 3 19 CA080205008 1 20080204 G 7603 540122519 POWER CABLE GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE3315251K NM HARTZL HCB3T HCB3TN5 GL POWER LEVER FROZEN W E ENGINE SHUTDOWN F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) DURING A TEST FLIGHT, THE LT POWER LEVER CABLE FROZE AND WOULD NOT RESPOND TO INPUTS. THE OAT AT THE TIME WAS -28 DEG C. THE POWER SETTING WAS AT MAX ITT FOR TEST PURPOSES. SINCE THE PILOT COULD NOT REDUCE POWER, THE ENGINE WAS SHUTD OWN AND THE PROPELLER WAS FEATHERED. THE AC RETURNED TO THE AIRPORT AND LANDED WITHOUT INCIDENT. UPON INVESTIGATION, MOI STURE WAS FOUND IN THE POWER LEVER CABLE. THE MOISTURE WAS REMOVED FROM THE CABLE AND THE CABLE WAS INSPECTED SERVICEABL E. THE AC WAS RETURNED TO SERVICE. (TC NR 20080205008) 1 H 7 2 3T 4 T 2A4 E2WE 6 C P15EA 20081104 NE 2008 11 4 CA080206004 2 20080116 G 7200 ENGINE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE LEFT VIBRATION W A E UNSCHED LANDING ENGINE SHUTDOWN E VIBRATION/BUFFET CR CRUISE 1 CA 807605 (CAN) CREW REPORTED SEVERE NOISE AND VIBRATION FELT ON LT ENGINE. SHUT ENGINE DOWN AS PRECAUTION AND RETURNED TO FIELD. ENGINE/QEC REMOVED AND REPLACED. SIGNIFICANT DAMAGE TO TURBINE. 2 L 7 2 4F 4 F RT A21EA E15NE 2008031900194 20080319 00194 NE 2008 3 19 CA080206008 2 20080117 G 7320 COUPLING BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE FUEL SYSTEM WORN W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 93137 (CAN) DURING CRUISE, THE ENGINE PARAMETERS WERE OBSERVED TO INCREASE REACHING NEAR MAXIMUM LIMITS. THE PILOT ELECTED TO SHUTDOWN THE ENGINE AND PERFORM A SINGLE ENGINE LANDING. POST FLIGHT INVESTIGATION REVEALED A WORN COUPLING BETWEEN THE FUEL PUMP AND FUEL CONTROL. (TC NR 20080206008) 1 L 7 2 4T 4 T A24CE E4EA 2008031900196 20080319 00196 NE 2008 3 19 CA080206009 2 20080122 G 7261 OIL SYSTEM CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE ENGINE EMPTY W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB AT APPROX FL190, THE CREW RECEIVED A LOW OIL PRESSURE WARNING AND PERFORMED A COMMANDED SHUTDOWN OF T HE ENGINE. THE AC WAS DIVERTED TO AN ALTERNATE LANDING SITE. POST FLIGHT INSP REVEALED NO INDICATION OF OIL ON THE SIGH T GLASS. NO SIGNS OF EXTERNAL LEAKAGE. THE ENGINE HAS BEEN REMOVED AND RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL B E PROVIDED TO TC WHEN AVAILABLE. (TC NR 20080206009) 2 L 7 2 4F 4 F RT A22CE E00059EN 2008031900197 20080319 00197 NE 2008 3 19 CA080206010 2 20080123 G 7261 OIL SYSTEM DHAV DHC8 DHC8201 2809001 NM PWA PW120 PW123 NE ENGINE LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA AT0006 (CAN) THE CREW RECEIVED A LOW OIL PRESSURE WARNING AND ELECTED TO SHUTDOWN THE ENGINE. SIGNS OF EXTERNAL LEAKAGE WERE FO UND AT POST FLIGHT INSP. THE ENG HAS BEEN REMOVED FOR INVESTIGATION AND REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVE NT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080206010) 2 H 7 2 4T 4 T RT A13NM E20NE 2008031900198 20080319 00198 NE 2008 3 19 CA080206011 2 20080124 G 7310 3035989 TUBE FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE FUEL SYSTEM PUNCTURED W F E A ACTIVATE FIRE EXT. ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 124341 (CAN) DURING CLIMB, AN ANTI-ICE WARNING FAULT WAS NOTED. 20 MINUTES LATER, AN ENGINE FIRE WARNING ANNUNCIATED. THE CREW FIRED ONE EXTINGUISHER BOTTLE AND SHUTDOWN THE ENGINE AND AN EMERGENCY WAS DECLARED. POST LANDING INVESTIGATION REVEALED THAT AN ENGINE SUPPLIED FUEL TUBE (PN 3035989) HAD BEEN PUNCTURED BY APPARENT FRETTING AND ABRASION AGAINST AN AIRFRAME SUPPLIED WIRING HARNESS. THE SUSPECTED TUBE WILL BE RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE FURNISHED AS AV AILABLE. (TC NR 20080206011) 2 H 7 2 4T 4 T RT A817 E20NE 2008031900199 20080319 00199 NE 2008 3 19 CA080206012 2 20080124 G 7200 ENGINE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 70322 (CAN) THE CREW NOTED A LOW OIL PRESSURE WARNING DURING CRUISE AND ELECTED TO SHUTDOWN THE ENGINE. POST FLIGHT INSPECTION REVEALED OIL RESIDUE IN THE TAIL PIPE AND METAL PARTICLES ON THE OIL FILTER. THE ENGINE WAS REMOVED FOR INVESTIGATION. MFG WILL CONTINUE TO INVESTIGATE THE EVENT AND REPORT FINDINGS ONCE ROOT CAUSE IS ESTABLISHED. (TC NR 20080206012) 1 L 7 2 4F 4 F A22CE E1NE 2008031900200 20080319 00200 NE 2008 3 19 CA080206013 2 20080129 G 7261 OIL CAP CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ENGINE LOOSE W E A ENGINE SHUTDOWN UNSCHED LANDING W J INADEQUATE Q C WARNING INDICATION CL CLIMB 1 CA 70730 (CAN) DURING CLIMB AT FL150, THE LOW OIL PRESSURE WARNING ANNUNCIATED AND PRESSURE WAS OBSERVED TO DROP TO 35 PSIG. THE ENGINE WAS SHUTDOWN BY THE CREW WHEN THE PRESSURE REDUCED TO 20 PSIG AND THE AC RETURNED TO BASE. POST FLIGHT INVESTIGA TION INDICATES THAT THE OIL FILLER CAP MAY NOT HAVE BEEN PROPERLY SECURED PRIOR TO THE FLIGHT. (TC NR 20080206013) 1 L 7 2 4F 4 F A22CE E1NE 2008031900201 20080319 00201 EA 2008 3 19 CA080206014 2 20080104 G 8530 SL32006WA21P CYLINDER HEAD LYC O320 O320E2D 41508 EA ENGINE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 292 (CAN) CYLINDER HEAD FOUND CRACKED AT OIL RETURN LINE BOSS, AT PIPE-THREADED FITTING HOLE. (TC NR 20080206014) 3 O E274 2008031900202 20080319 00202 NE 2008 3 19 CA080207005 1 20080108 G 6410 SB7306102 BEARING SKRSKY S92 S92A NE GE CT7TS CT78A 30136 NE T/R BLADE DEBONDED W O OTHER O OTHER NR NOT REPORTED 1 CA 42 A11100355 (CAN) UPON A SCHEDULED 50HR INSP, A BOROSCOPING OF THE TAIL ROTOR BLADES HAD BEEN CARRIED OUT, TO CHECK PIVOT BEARINGS F OR DEBONDING FROM TAIL ROTOR SPARE. ON ONE TAIL ROTOR BLADE A BEARING WAS SUSPECTED TO BE DEBONDED. UPON FURTHER INSPECT ION WITH REMOVAL OF THE BEARING FROM THE TAIL ROTOR BLADE, IT WAS CONFIRMED THAT THE INNER PLATE OF THE PIVOT BEARING WA S TOTALLY SEPARATED FROM THE BLADE SPAR. AFTER LOOKING AT THE BEARING PLATE IT WAS CLEARLY VISIBLE THAT THE ADHESIVE MAT ERIAL USED TO BOND THE PLATE TO THE SPAR HAD ONLY ADHERED TO THE PLATE OF THE BEARING AND NOT TO THE SPAR. (TC NR 200802 07005) 2 G 7 2 4U 4 U R00024BO E8NE 2008031900203 20080319 00203 NE 2008 3 19 CA080207006 2 20080129 G 7310 230360801 LINE BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FUEL SYSTEM MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 30784 3062 (CAN) THE ENGINE FUEL LINES WERE FOUND NOT TO BE CORRECTLY INSTALLED IAW AMM 73-10-08-401. TUBES , FUEL SYS, REMOVAL / INSTALLATION. AFFECTIVITY: ON AC ALL - DATE: EEP 01/02 (P). THIS HAS RESULTED IN (3) OF THE (4) ENGINES FUEL LINES TO CHAFE WITH THE ENG INLET ANTI-ICE AIR SUPPLY TUBE. ONE OF THE ENGINE FUEL LINES WAS CHAFED THROUGH AND WAS ALLOWING FUE L TO LEAK OUT. (TC NR 20080207006) 2 H 7 4 4F 4 F A49EU E6NE 20080520 2008 5 20 CA080207007 4 20080130 G 2562 ELT97A2560000000 ELT DORNER DO32 DO328100 2996000 NM PWA 119 PW119C NE HARTZL HDE6C HDE6C3B NE FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA 134 (CAN) NUMEROUS UNCOMMANDED ELT ACTIVATIONS WITH ELT97. HAVE HAD ACTIVATIONS WITH THE AC INFLIGHT AND PARKED ON THE APRO N. THE LASTEST WAS WITH ELT S/N-4584 ON JANUARY 30, 2008. THE AC HAD BEEN PARKED ON THE APRON FOR ROUGHLY 2 HOURS WHEN THE ELT SIGNAL WAS DETECTED. ALL ELTS HAVE BEEN CONFIRMED AS DEFECTIVE AFTER AN ACTIVATION BY REPLACEMENT OR BY SWAPPING WITH ANOTHER AC. DEFECTIVE ELTS HAVE BEEN RETURNED TO THE MFG FOR REPAIR OR REPLACEMENT. ATTEMPTS TO GET SUPPORT FROM MFG HAVE YEILDED LIMITED RESULTS. (TC NR 20080207007) 2 H 7 2 4T 4 T RT A45NM E20NE 6 C P34NE 2008031900204 20080319 00204 EA 2008 3 19 CA080207010 2 20080204 G 7322 105217 CARBURETOR CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA ENGINE LOOSE W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 731 (CAN) CARB HEAT SEEMED TO HAVE A SLIGHTLY EXCESSIVE DROP AT HIGHER RPM. (TC NR 20080207010) 1 H 7 1 3O 3 O NT 3A12 E274 2008031900205 20080319 00205 EU 2008 3 19 CA080207011 1 20080131 G 6130 312089001 PROP BRAKE AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE NR 2 SEIZED W F ACTIVATE FIRE EXT. J A WARNING INDICATION FLAME/FIRE TX TAXI/GRND HDL 1 CA PCE120893 (CAN) AFTER ARRIVAL AT DESTINATION, THE AC TAXIED TO THE TERMINAL. PRIOR TO PASSENGER DEPLANING, THE CREW OBSERVED A MAS TER WARNING (PROP UNLOCK). THE F/O REPORTED THAT THE NR 2 ENG WAS ON FIRE AND THE NR 2 CONDITION LEVER WAS SELECTED TO S HUTOFF POSITION. THE F/O OBSERVED THAT THE FIRE CONDITION WAS STILL EVIDENT AND THUS THE GROUND ENGINE FIRE CHECK LIST W AS CARRIED OUT. NO FIRE INDICATION WAS OBSERVED ON THE FLIGHT DECK AND INSPECTION OF THE ENG AND NACELLE BY MAINT FOUND NO INDICATION OF FIRE. THE PROP BRAKE REPLACEMENT PROCEDURE WAS COMPLETED, SYS CHECKED SERVICEABLE AND THE AC RETURNED T O SERVICE. (TC NR 20080207011) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2008031900206 20080319 00206 CE 2008 3 19 CA080208001 1 20080206 G 5610 50420066317 WINDOW BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL LT COCKPIT DEPARTED W O OTHER D INFLIGHT SEPARATION CL CLIMB 1 CA (CAN) DURING CLIMBOUT AT APPROX 3PSI DIFFERENTIAL, THE LT COCKPIT SIDE WINDOW BLEW OUT OF AIRCRAFT. IT IS DIFFICULT TO DETERMINE THE CAUSE AS THERE IS VERY LITTLE REMAINING OF THE ORIGINAL WINDOW. (TC NR 20080208001) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 20080520 2008 5 20 CA080208002 4 20080208 G 2562 AK450 ELT BEECH 60 60 1153602 CE LYC O541 TIO541E1C4 41536 EA HARTZL HCF3Y HCF3YR2 GL FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN TESTING THE ELT AT ITS ANNUAL INSP THE ELT HAD NO MODULATION AND NO OUTPUT POWER. THE ELT REPLACED WITH A SER VICEABLE UNIT. (TC NR 20080208002) 1 L 7 2 3O 3 O A12CE E10EA 5 C P31EA 2008031900207 20080319 00207 NE 2008 3 19 CA080208003 2 20080204 G 7210 70BM052000 REDUCTION GB SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA 5479 2482 (CAN) DURING DAILY INSPECTION SMALL FLAKES WERE FOUND ON THE NON-MAGNETIC CHIP PLUG ON (MODULE) MO 5. ENGINE OIL WAS CH ANGED OIL FILTER WAS CHANGED ALL MAG PLUGS INSPECTED AND CLEANED. A/C FLEW FOR 11.1 HRS AND SMALL FLAKES WERE FOUND ON S AME PLUG. A/C WAS GROUNDED AT THIS TIME AND MFG WAS INFORMED. A OIL SAMPLE WAS SENT FOR EVALUATION AND CAME BACK AS NOR MAL. MFG HAS DECIDED TO REPLACE THE MO 5. (TC NR 20080208003) 1 G 7 1 3U 3 U H9EU E00054EN 2008031900208 20080319 00208 EA 2008 3 19 CA080208005 2 20080129 G 8530 734352 PUSHROD MAULE M5 M5235C 5460135 SO LYC O540 O540J1A5 41532 EA HARTZL HCC2Y HCC2YR1 GL ENGINE DEFECTIVE W O OTHER O OTHER NR NOT REPORTED 1 CA 1235 (CAN) THE INTAKE AND EXHAUST PUSHRODS LOCATED AT THE NR1 CYL POSITION WERE NOT DRILLED THROUGH ON ONE END. THIS WOULD NO T ALLOW OIL TO TRAVEL UP THE PUSHROD TO THE ROCKER. (TC NR 20080208005) 1 H 7 1 3O 3 O 3A23 E295 5 C P920 2008031900212 20080319 00212 CE 2008 3 19 CA080211001 1 20080207 G 2720 1303800033 TRANSDUCER BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL RUDDER BOOST FAILED W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 CA 188 188 (CAN) THE AC WAS DISPATCHED ON A MEDIVAC FLIGHT AND UPON STARTING THE TAKEOFF ROLL AN UNCOMMANDED RUDDER INPUT WAS FELT BY THE PILOTS. THE AC RETURNED TO THE HANGER WHERE MAINT BEGAN TO TROUBLESHOOT THE PROBLEM. IT WAS DISCOVERED THAT THE L T RUDDER BOOST TRANSDUCER (P/N130-380003-3) FAILED WHICH SIMULATED ENGINE FAILURE AND CAUSED THE RUDDER BOOST SYS TO ACT IVATE. THE TRANSDUCER WAS REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20080211001) 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 20081222 CE 2008 12 22 CA080211002 1 20080205 G 2750 552500079 ROLLER CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE CENTER FLAP AFT OUT OF ADJUST W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CAMPAIGN NOTICE 851-27-50-043, FLAP CTR AFT BEARING INSTALLATION, COMPLIED WITH. NO FAULTS FOUND ON LT FLAP INSTAL LATION. RT FLAP AFT CENTER ROLLER BEARING FOUND TIGHT, BEARING WOULD NOT TURN UNLESS FLAP WAS HELD WITH PRESSURE APPLIED . NO DAMAGE TO BEARING OR SUPPORT FOUND. AFT CENTER ROLLER BOLT ADJUSTED IAW MM 27-51-04, PG 208 PARA B-5-B(2). WORK DO CUMENTED ON ASD-MP-01 REPORT NR859-02/04/08. 1 L 7 2 4F 4 F A22CE E1NE 2008031900214 20080319 00214 EA 2008 3 19 CA080211006 2 20080208 G 7310 3011849 LINE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL FUEL SYSTEM CRACKED W A UNSCHED LANDING K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA (CAN) PILOT REPORTED HEAVY GAS ODOR IN COCKPIT AFTER TAKEOFF, ACCOMPANIED BY A MIST. MAINT ENGINEER FOUND A CRACKED FUE L LINE IN THE NR 2 ENGINE NACELLE THAT CONNECTS THE START CONTROL UNIT TO THE FUEL CONTROL UNIT CAUSING A FUEL LEAK THA T WAS SUBSEQUENTLY SUCKED INTO THE ENGINE COMPRESSOR SECTION AND THEN TRANSMITTED TO THE CABIN OF THE AC THROUGH THE BLE ED AIR SYS. (TC NR 20080211006) 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2008031900215 20080319 00215 NM 2008 3 19 CA080211007 1 20080207 G 3213 101683 ROLLER MESSIER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE STRUT SEIZED W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA DEC128384 (CAN) AFTER SELECTING LANDING GEAR DOWN THE LT MAIN GEAR REMAINED UP, THE LANDING GEAR WAS CYCLED UP AND DOWN AGAIN, THE LT GEAR CAME DOWN NORMALLY, (3) GREENS. THE AC WAS FERRIED BACK TO BASE, GEAR DOWN, FOR MAINT. AFTER CARRYING OUT (2) GEAR SWINGS ON JACKS THE LT GEAR REMAINED UP ON THE 2ND DOWN SELECTION, APPROX (1) MINUTE LATER THE LT GEAR RELEASED AND EXTENDED TO DOWN AND LOCKED. IT WAS DISCOVERED THAT THE UPLOCK ROLLER ON THE SHOCK STRUT ASSY WAS SEIZED, THE ROLLER WA S REMOVED LUBRICATED AND RE-INSTALLED. FURTHER RETRACTIONS AND EXTENSIONS WERE CARRIED OUT WITHOUT ANY PROBLEMS, AC RETU RNED TO SERVICE. (TC NR 20080211007) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080520 NM 2008 5 20 CA080211009 1 20080204 G 2710 19004212401 CONTROL CABLE EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE AILERONS BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) C02 CHECK: DURING AILERON CONTROL CABLES INSP ,ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 190-04212-401 AND P/N 190-04209-401, RT P/N 190 -05550-401 AND P/N 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATED AT LT AND RT WINGS RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REFERENCE J/C 27-11-00-003-LT/1 5 AND J/C 27-11-00-00 3-RT/2 . THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. FL EET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211009) 2 L 7 2 4F 4 F RT A57NM E00070EN 20080520 NM 2008 5 20 CA080211011 1 20080111 G 2710 19004212401 CONTROL CABLE EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE AILERONS BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) C02 CHECK: DURING AILERON CONTROL CABLES INSPECTION ,ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 190-04212-40 1 AND P/N 190-04209-401, RT PN 190 -05550-401 AND PN 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATE D AT LT AND RT WINGS RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REF J/C 27-11-00-003-LT/1 AND J/C 27-11-00-003-RT /2 . THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. AIR CA NADA FLEET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211011) 2 L 7 2 4F 4 F RT A57NM E00070EN 20080520 NM 2008 5 20 CA080211012 1 20080123 G 2710 19004212401 CONTROL CABLE EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE AILERONS BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AILERON CONTROL CABLES INSP ,ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 190-04212-401 AND PN 190-04209 -401, RT PN 190 -05550-401 AND PN 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATED AT LT AND RT WING S RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REFERENCE J/C 27-11-00-003-LT/1 SNAGS NR 128, 165 AND J/C 27-11-00-0 03-RT/2 SNAGS NR 87, 166. THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. SAME FINDING ON ERJ190 NR 00015 HRS5830 CYCLES 2643 C02 CHECK AND ALSO ERJ190 NR 00013 HRS5720 CYCLES 263 5 C02 CHECK. FLEET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211012) 2 L 7 2 4F 4 F RT A57NM E00070EN 20080520 EA 2008 5 20 CA080211013 1 20080210 G 2720 274001 PCU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE RUDDER MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 4499 (CAN) TASK NR RJ2-27-900-714 FOR THE BACKLASH AND FUNCTIONAL CHECK OF RUDDER CONTROL SYS WAS CARRIED OUT ON THIS AC DURI NG A HEAVY MAINT CHECK. TEST RESULT PARAMETERS WERE FOUND BEYOND LIMITS. FURTHER INVESTIGATION DURING RECTIFICATION LEAD TO THE DISCOVERY OF THE NR 2 RUDDER PCU LINKAGE ROD BEING FOUND COMPLETELY SHEARED OFF. THERE WERE ALSO DAMAGE TO THE RUDDER ATTACH FITTING AND THE VERTICAL STABILIZER BRACKET. A NEW PCU IS ON ORDER AND THE FAILED UNIT WILL BE REPLACED B EFORE AC IS RELEASED FROM HEAVY CHECK. ENGINEERING DEPART HAS BEEN CONTACTED FOR DAMAGE EVALUATION AND POSSIBLE ISSUE OF A REPAIR EO FOR THE RUDDER FITTING AND BRACKET. THOSE UNITS WILL BE REPLACED AS WELL IF THEY ARE FOUND BEYOND REPAIR. I 2 L 7 2 4F 4 F RT A21EA E15NE 20080520 NM 2008 5 20 CA080211014 1 20080131 G 2710 17005825401 CONTROL CABLE EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE AILERONS BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING CONTROL CABLES INSP ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 170-05825-401, P/N 170-05826-401, RT P /N 170-05827-401, P/N 170-05828-401) WORN AND WITH WIRES BROKEN AT SEVERAL FAIRLEADS, LOCATED AT LT AND RT WINGS IB OF T HE RIB 12, 15, 17 AND AT RIB 20. FLEET ENGINEERING AS BEEN ADVISED (TC NR 20080211014) 2 L 7 2 4F 4 F RT A56NM E00063EN 20080520 NM 2008 5 20 CA080211015 1 20080207 G 2710 17005825401 CONTROL CABLE EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE AILERONS BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 170-05825-401, P/N 170-05826-401, RT PN 170-05827-401, PN 170-05828-401) WORN AND WITH WIRES BROKEN AT SEVERAL FAIRLEADS, LOCATED AT LT AND RT WINGS IB O F THE 17 FLEET ENGINEERING HAVE BEEN ADVISED (TC NR 20080211015) 2 L 7 2 4F 4 F RT A56NM E00063EN 2008031900217 20080319 00217 SW 2008 3 19 CA080211017 1 20080208 G 2913 206076030101 PUMP BELL 206 206L3 1182108 SW HYDRAULIC SYS DAMAGED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING FLIGHT, AC LOST HYDRAULICS. AC LANDED SAFELY. MAINT FOUND HYDRAULICS PUMP SPLINE ROUNDED OFF. TACH GENERATO R SPLINES WORN AS WELL. (TC NR 20080211017) 1 G 7 1 3U H2SW 2008031900219 20080319 00219 CE 2008 3 19 CA080211018 1 20080206 G 3233 508202085 ACTUATOR BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL NLG FAILED W O OTHER J WARNING INDICATION DE DESCENT 1 CA 1711 (CAN) DURING DESCENT INTO INTENDED AIRPORT THE NLG INDICATOR INTRANSIT LIGHT STAYED ILLUMINATED WHEN LANDING GEAR EXTEND ED. MAIN GEAR DOWN AND LOCKED LIGHT WERE GREEN. A FLY-BY WAS CARRIED OUT WITH GROUND MAINT VERIFYING THAT THE NLG WAS IN DEED ONLY HALF WAY DOWN WITH MAINS FULLY DOWN. AN EMERGENCY EXTENSION WAS ATTEMPTED AND FAILED TO EXTEND THE NLG. THE CR EW DECLARED AND EMERGENCY. A LANDING WAS CARRIED OUT WITH ENGINES SHUTDOWN AND PROPS FEATHERED. THE AC WAS LANDED WITH A TOTAL NLG COLLAPSE. THE AC WAS REMOVED FROM RUNWAY. (TC NR 20080211018) 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 20080520 CE 2008 5 20 CA080211019 1 20080104 G 2820 20282004500R SELECTOR CESSNA 172 172M 2072418 CE THIELT TAE125 TAE12501 59300 EU FUEL SYS MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AC WAS BEING RETRO-FITTED WITH A 2.0 TURBO DIESEL ENGINE IAW STC. THE FUEL SYS WAS COMPLETED, FUEL INSTALLED AND I NSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEA DER TANK. THE B-NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE W AS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REP LACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAK S WERE FOUND. THE OTHER (2) FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. (TC NR 20080211019) 1 H 7 1 3O 3 B NT 3A12 E00069EN 2008031900221 20080319 00221 EA 2008 3 19 CA080212001 1 20080212 G 5711 C6WM10271 ADAPTER DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL SPAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON COMPLIANCE WITH SB 6/540 (WING-FRONT SPAR ADAPTER ASSEMBLY (P/N C6WM1027-1) INSPECTION FOR CRACKS) A CRACK WA S FOUND ON THE LT FRONT SPAR ADAPTER. REPLACED LT FRONT SPAR ADAPTER ASSY PN C6WM1027-1 WITH PN C6WM1027-3 IAW SB NR 615 42. (TC NR 20080212001) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081229 CE 2008 12 29 CA080212003 1 20080201 G 5753 55250007 SUPPORT CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE TE FLAP WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A CAMPAIGN NOTICE OF THE RT FLAP CENTER BRG INSTALLATION, BOTH OF THE AFT FLAP BEARINGS WERE FOUND LOOSE AN D WORN DUE TO THE LOCATING PIN ON THE BEARINGS NOT INSTALLED INTO MATING HOLES OF FLAP RIB EXTENSIONS. FLAP ROLLER PN K JS 112603 AND BOTH CENTER AFT FLAP ROLLER SUPPORT BRGS P/N 5525000-79 WERE REPLACED.FLAPS FUNCTION CHECK SERVICEABLE AND ACFT RETURNED TO SERVICE. 1 L 7 2 4F 4 F A22CE E1NE 2008031900223 20080319 00223 EA 2008 3 19 CA080212004 1 20080129 G 5411 C6WM10271 ADAPTER DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL SPAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON COMPLIANCE WITH SB 6/540 (WING-FRONT SPAR ADAPTER ASSY (P/N C6WM1027-1) INSP FOR CRACKS) A CRACK WAS FOUND ON THE RT FRONT SPAR ADAPTER. REPLACED RT FRONT SPAR ADAPTER ASSY PN C6WM1027-1 WITH PN C6WM1027-3 IAW SB NO 61542. ALSO REPLACED WEB SUB ASSY SPAR P/N C6W1030-S102 AND WEB NOSE SPAR C6W1056-62 SRM PSM 1-6-3, CHAPTER 51-10-00 AND 51-30-00. ( TC NR 20080212004) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2008031900227 20080319 00227 EA 2008 3 19 CA080212005 2 20080208 G 7320 LINK BENDIX HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA FUEL INJECTOR DISCONNECTED W R AUTOROTATION R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) THE COTTER PIN SECURING THE IDLE MIXTURE LINK BLOCK TO THE MIXTURE CONTROL ARM BECAME DISLODGED. THIS ALLOWED THE MIXTURE LINK BLOCK TO BECOME DISCONNECTED FROM THE MIXTURE CONTROL ARM. RESULTING A LOSS OF CONTROL OVER FUEL FLOW TO TH E ENGINE AND THE ENGINE RETURNED TO GROUND IDLE POWER. (TC NR 20080212005) 1 G 7 1 3O 3 O 4H12 1E10 2008031900229 20080319 00229 EU 2008 3 19 CA080213001 1 20080208 G 2421 729722C GENERATOR HONEYWELL AIRBUS 310 A310 EU GE CF6 CF680C2A5 NE APU CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 32488 19916 PP1269 (CAN) DURING TROUBLESHOOTING FOR HIGH OIL CONSUMPTION ON THE APU, FOUND A 7 INCHES CRACK ON THE GENERATOR HOUSING. THE I DG WAS REPLACED AND THE UNIT WAS SENT TO THE VENDOR FOR INVESTIGATION. (TC NR 20080213001) 2 L 7 2 4F 4 F RT A35EU E13NE 20080520 CE 2008 5 20 CA080213002 1 20080211 G 3250 MC09543022 TUBE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL NLG STEERING STUCK W K NONE O OTHER IN INSP/MAINT 1 CA 828 (CAN) PROBLEM WAS DISCOVERED DURING PRE-INSP RUN UP. WHEN FULL RUDDER DEFLECTION WAS APPLIED THE RUDDER MOVEMENT WAS RES TRICTED AND WOULD ONLY RELEASE WHEN ALTNATE RUDDER PRESSURE WAS APPLIED. (TC NR 20080213002) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2008031900231 20080319 00231 NM 2008 3 19 CA080213003 1 20080120 G 5610 070303 WINDSHIELD DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE COCKPIT CRACKED W B I EMER. DESCENT CABIN DEPRESSURIZATION O OTHER CR CRUISE 1 CA (CAN) WHILE IN CRUISE FLIGHT, THE F/O HEATED WINDSHIELD SHATTERED WITH NO APPARENT WARNING. THE CREW DEPRESSURIZED THE C ABIN AND DESCENDED IAW THEIR CHECKLISTS AND CONTINUED THE FLIGHT TO THEIR DESTINATION. THE AC WAS ON A NON REVENUE FLIGH T TO A MAINT FACILITY FOR THE COMPLETION OF A C-CHECK. THE WINDOW HAS BEEN REPLACED AND NO DEFINITIVE REASON FOR THE FAI LURE HAS BEEN DETERMINED. THE TT ON THE WINDOW CAN NOT BE ACCURATELY DETERMINED BUT THE WINDOW HAS A MANUFACTURE DATE OF JAN 20, 2000. (TC NR 20080213003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080520 GL 2008 5 20 CA080213004 1 20080206 G 2133 811441A010302 OUTFLOW VALVE BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP CABIN PRESSURE FAILED W B EMER. DESCENT J WARNING INDICATION CL CLIMB 1 CA 607 (CAN) DURING CLIMB, THROUGH FL270, CABIN ROC (RATE OF CLIMB) INCREASED TO 3000 FPM (FT PER MINUTE), CABIN ALTITUDE START ED TO CLIMB. MANUAL PRESSURIZATION WAS SELECTED RESULTING IN AN INABILITY TO REDUCE CABIN ALTITUDE. AC DESCENDED, EICA S (CABIN ALT) MESSAGE POSTED AND OXYGEN MASKS DEPLOYED. AN EMERGENCY WAS NOT DECLARED. TROUBLESHOOTING WAS CARRIED OUT, RT SAFETY VALVE FAILED THE TEST. BOTH SAFETY VALVES WERE REMOVED, THE INVESTIGATION IS ONGOING. (TC NR 20080213004) 2 L 7 2 4F 4 F RT T00005NY E00010LA 20080520 GL 2008 5 20 CA080213005 1 20080103 G 2133 811441A010302 OUTFLOW VALVE BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP CABIN PRESSURE MALFUNCTIONED W B EMER. DESCENT O OTHER CR CRUISE 1 CA 419 419 (CAN) DURING CRUISE AT 45,000 FEET, THE PILOT REPORTED THAT THE CABIN ALT CLIMBED TO 22 000 FT, OXYGEN MASKS DEPLOYED AN D AN EMERGENCY DESCENT WAS CARRIED OUT. WAITING MORE INFO FROM CUSTOMER. THE MFG HAS INSPECTED THE VALVES AND THEY CONC LUDE THE VALVES WERE (NO FAULT FOUND). THE INVESTIGATION IS ONGOING. (TC NR 20080213005) 2 L 7 2 4F 4 F RT T00005NY E00010LA 2008031900234 20080319 00234 NM 2008 3 19 CA080213006 1 20080122 G 3246 314353 WHEEL DHAV DHC8 DHC8106 2809020 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE LT MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE DAILY INSP, IT WAS NOTED THAT THE LT MAIN WHEEL WAS LOOSING AIR ON A DAILY BASIS. THE WHEEL ASSY WAS RE MOVED AND SENT FOR INSP. INSP REVEALED THAT THE INNER RIM HALF WAS CRACKED AT THE FUSE PLUG AND FURTHER INSP REVEALED CR ACKING AT THE BRG RACE. THIS WHEEL WAS REMOVED FOR THE FIRST TIME OFF OF A RECENTLY PURCHASED AC AND TOTAL TIME ON THIS PART IS UNDETERMINED. (TC NT20080213006) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081229 CE 2008 12 29 CA080213007 1 20080131 G 2910 SEEDESCRIPTION HOSE CESSNA 680 680CE 2076811 CE PWC PW306 PW306C 52169 NE HYD SYS LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1036 (CAN) DURING INSP OF FLAP SYS FOUND 6 HYD HOSES FOR SPEED-BRAKE/LIFT-DUMP ACTUATORS WITH MINOR HYD FLUID SEEPAGE. THE FO LLOWING PN HOSES WERE REPLACED. AE1011925E0087, AE1011925E0094, AE1011925E0121, AE1011888E0132, AE1011924E0103, AE101193 3E0086. 2 L 7 2 4F 4 F RC T00012WI E35NE 20080520 EU 2008 5 20 CA080213008 1 20080208 G 2913 PUMP AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE HYD SYSTEM MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) SHORTLY AFTER DEPARTURE, THE CREW OBSERVED A LOW PRESSURE INDICATION ON THE BLUE HYDR SYS. THE AC RETURNED TO POIN T OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINT REPLACED THE BLUE SYS PUMP AND THE AC WAS RETURNED TO SERVICE. (TC NR 20080213008) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 20080520 NE 2008 5 20 CA080213010 3 20080209 G 6114 SEAL HAMSTD 54H60117 LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL HAMSTD 54H 54H60117 NE PUMP HOUSING TORN W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) ON TAKEOFF FROM AIRPORT, THE CREW OBSERVED A LOW OIL INDICATION ON THE NR 1 PROPELLER. THE AC RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINT REPLACED THE NR 1 PROPELLER ASSY. THE AC WAS RETURNED TO SERVICE A FTER SATISFACTORY LEAK CHECK AND GROUND RUN. IT WAS DETERMINED THAT THE FLUID LOSS WAS DUE TO A DAMAGED FRONT PROPELLER PUMP HOUSING SEAL (TC NR 20080213010) 2 H 7 4 4T 4 T A1SO E282 6 C P906 20080521 CE 2008 5 21 CA080213013 1 20080104 G 2823 20282004500R SELECTOR CESSNA 172 172M 2072418 CE THIELT TAE125 TAE12502114 EU FUEL SYSTEM LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AC WAS BEING RETRO-FITTED WITH A 2.0 TURBO DIESEL ENGINE IAW STC. THE FUEL SYS WAS COMPLETED, FUEL INSTALLED AND I NSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEA DER TANK. THE B NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE W AS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REP LACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAK S WERE FOUND. THE OTHER TWO FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. THIS IS THE SECOND PART. (TC 1 H 7 1 3O 3 B NT 3A12 E00069EN 20080522 CE 2008 5 22 CA080213014 1 20080104 G 2823 20282004500R SELECTOR CESSNA 172 172M 2072418 CE THIELT TAE125 TAE1250299 EU FUEL SYSTEM DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AC WAS BEING RETRO-FITTED WITH A 2.0 TURBO DIESEL ENGINE IAW STC. THE FUEL SYS WAS COMPLETED, FUEL INSTALLED AND I NSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEA DER TANK. THE B-NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE W AS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REP LACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAK S WERE FOUND. THE OTHER (2) FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. THIS IS THE THIRD PART. (TC 1 H 7 1 3O 3 B NT 3A12 E00069EN 2008031900237 20080319 00237 GL 2008 3 19 CA080214001 1 20080212 G 2720 2227271400 RUDDER PEDAL DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA COCKPIT CORRODED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 3435 (CAN) IT HAS BEEN NOTICED THAT ALTHOUGH THIS AREA IS LUBRICATED IAW THE MFG MAINT SCHEDULE WITH LPS2, THIS AREA CONTINUO USLY CORRODES TO THE POINT THAT IT AFFECTS THE POSITIONING OF THE RUDDER PEDALS. (TC NR 20080214001) 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 20081104 SW 2008 11 4 CA080214002 1 20080213 G 7714 DRIVE SHAFT SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110U 01514 WP HARTZL HCB3T HCB3TN5 GL TACH GENERATOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TROUBLESHOT NO RPM INDICATION. REMOVED TACH GENERATOR FROM RT ENGINE, DRIVE SHAFT WAS STILL STUCK IN THE ENGINE. I T APPEARS THAT THE SHAFT SEPARATED FROM THE ARMATURE INSIDE. REMOVED THE SHAFT, NO DAMAGE TO THE ENGINE DRIVE. INSTALLED SERVICEABLE PART AND TESTED FINE. (TC NR 20080214002) 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 2008031900242 20080319 00242 CE 2008 3 19 CA080214005 1 20080214 G 2750 1013800005 DRIVE SHAFT BEECH 1900 1900D 1154162 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL FLAP DRIVE SEIZED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) FLAPS WOULD NOT RETRACT AFTER TAKEOFF AND CIRCUIT BREAKER OPENED. AIRCRAFT RETURNED TO AIRFIELD. FLAP DRIVE SHAFT WAS FOUND SEIZED AND BOUND UP NEAR MOTOR. MOTOR AND DRIVE SHAFT WERE REPLACED. (TC NR20080214005) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 20080603 NM 2008 6 3 CA080214007 1 20080121 G 2910 82970009325 HYDRAULIC LINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120 NE HAMSTD 14SF 14SF7 NE HYDRAULIC SYS CRACKED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 34968 (CAN) WHILE ENROUTE THE "IB ROLL SPL HYD" AND NR 1 "HYD ISO VLV" CAUTION LIGHTS ILLUMINATED. CHECKED THE HYD QUANTITY AN D NOTICED NR 1 QUANTITY AT 1.0 AND DECREASING. COMPLETED THE QRH CHECKLIST AND THEN BRIEFED THE F/A AND PASSENGERS. MADE A VISUAL APPROACH AND LANDING WITHOUT ANY FURTHER EVENTS. MAINT INVESTIGATION DETERMINED THE LEAK TO BE FROM THE NR 1 HYD SYS PRESSURE MANIFOLD ENGINE DRIVEN PUMP INLET PRESSURE TUBE FLARE AND FITTING. THE FLARE WAS FOUND TO BE CRACKED AN D THE FITTING HAD EVIDENCE OF PITTING CORROSION. THE TUBE AND FITTING WERE BOTH REPLACED IAW THE AIRCRAFT MM AND SUBSEQU ENTLY TESTED SERVICEABLE. (TC NR 20080214007) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080521 2008 5 21 CA080214008 4 20080213 G 2562 0010009C ELT CABIN CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 1 (CAN) BATTERY CASE FOUND CRACKED DURING ANNUAL RECERTIFICATION. BATTERY KNOWINGLY NEVER DROPPED. UNKNOWN CAUSE OF CRACK, LOCATED AT BOTTOM OF THE CASE IN ANTENNA STOWAGE CHANNEL. (TC NR 20080214008) 20080521 WP 2008 5 21 CA080214009 1 20080114 G 3260 DOWNLOCK SWITCH CVAC 440 440 2422902 WP ALLSN 501D 501D13D 03004 GL ALLSN A6441 A6441FN606 GL MLG DEFECTIVE W L ABORTED APPROACH N FALSE WARNING DE DESCENT 1 CA (CAN) ON APPROACH, ON A FERRY FLIGHT AND WHEN GEARS SELECTED DOWN, THE LT GEAR DID NOT INDICATE DOWN AND LOCKED, LANDING WAS ABORTED. AFTER COMPLETING THE INDICATION, MALFUNCTION CHECKLIST, FOUND IN FACT THAT THE LT GEAR WAS DOWN AND LOCKE D. FOR PRECAUTIONARY MEASURES IN THE COMPANY PROCEDURES AN EMERGENCY LANDING WAS DECLARED THAN PROCEEDED WITH NORMAL LA NDING. FOLLOWING MAINT INVESTIGATION FOUND LT MLG DOWNLOCK SWITCH DEFECTIVE, THE SWITCH WAS REPLACED AND RIGGED IAW MM A ND AC RETUNED TO SERVICE. (TC NR 20080214009) 2 L 7 2 4R 4 T 6A6 E282 6 C P898 20080521 NE 2008 5 21 CA080214010 1 20080209 G 5340 3322203 ATTACH FITTING 3035941 SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL SEATBELT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SUBJECT AC CRASHED ON APPROACH TO LANDING. OPERATOR REPORTED TO THAT AN AFT-FACING CABIN SEAT BELT ATTACH FITTING FAILED ON IMPACT, PERMITTING THE SEAT BELT TO DETACH. INSP OF FAILURE SHOWS THAT UNEXPECTED PRYING LOADS CAUSED THE FA ILURE OF THE ALUMINUM ATTACH FITTING. A DESIGN CHANGE IS REQUIRED TO PREVENT SIMILAR OCCURRENCES. I AM THE APPROVAL HOL DER FOR THE MODIFICATION THAT INTRODUCES THESE SEATS INTO THE AC. HAVE RECOMMENDED THAT THE OPERATOR REFRAIN FROM USING THESE SEATS FOR TAKEOFF AND LANDING UNTIL A FIX CAN BE INCORPORATED. AC IS EN-ROUTE BY TRUCK TO MY FACILITY. I HAVE CON TACTED THE SEAT MFG REQUESTING ENGINEERING ASSISTANCE TO ADDRESS THIS DEFECT. (TC NR 20080214010) 1 G 7 2 3U 3 U H1NE E1GL 20081230 CE 2008 12 30 CA080214011 1 20080124 G 2510 05142121 SEAT BACK CESSNA CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA MCAULY 1C235 1C235LFA GL COCKPIT SEAT BROKEN W O OTHER O OTHER CR CRUISE 1 CA 4056 (CAN) SEAT BACK FRAME BROKEN JUST ABOVE INSERT ON THE OTBD SIDE. NOTEWORTHY ITEM: THIS SEAT DID HAVE A STEAL BAR INSTALL ED IAW AD 2007-05-10. WE DO NOT KNOW WHETHER THIS WAS A CONTRIBUTING CAUSE TO THE FAILURE. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P12EA 20080521 2008 5 21 CA080215001 4 20080207 G 2370 4954200001 VIDEO MONITOR BOEING 767 7673Y0 NM PWA 4060 PW4060 52119 NE CABIN FIRE W O OTHER A B FLAME/FIRE SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 CA (CAN) AFTER LANDING AND AFTER PASSENGERS HAD DEPLANED, THE F/A STILL ONBOARD THE AC NOTICED ONE OF THE BULKHEAD INFLIGHT ENTERTAINMENT MONITORS HAD FLAMES AND SMOKE EMINATING FROM IT. AFTER INSPECTION OF VIDEO MONITOR, MAINT FOUND A PLUG M ELTED AT PIN. HARNESS WAS DISCONNECTED FROM P1 DISCONNECT ABOVE NO SMOKING SEATBELT SIGN. COAX CABLE ALSO DISCONNECTED. MONITOR REMOVED. FOUND CB ON P-37 PANEL IN E/E COMPT POPPED. VIDEO MONITOR MFR P/N: 02190830-1, MFG CODE: P0173 (TC NR 20080215001). 2 L 7 2 4F 4 F RT A1NM E24NE 20081105 2008 11 5 CA080215002 4 20080214 G 3130 7013348931 DAU LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP MALFUNCTIONED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) THIS DAU WAS ORIGINALLY REMOVED FROM ANOTHER OPERATOR ACFT WITH THE FAULT, LOSS OF N1 AND N2 INDICATION. MFG TESTE D THE UNIT AND RETURNED IT TO SERVICE WITH NO FAULT FOUND, WITH ALL THE APPROPRIATE CERTIFICATION. THE UNIT WAS INSTALLE D ON OUR ACFT IN NR1 POSITION WITH THE PROPER FUNCTION CHECK CARRIED OUT. DURING ENGINES RUN, ALL ENGINES INDICATIONS WE RE NORMAL. A FEW HOURS LATER, WHILE THE ACFT WAS TAXIING OUT THE NR1 ENGINE INDICATION STARTED TO FLICKER. ACFT RETURNED TO OUR HANGAR WHERE THE DAU NR1 WAS REPLACED. DAU WILL BE RETURNED TO WILL ALL THE PROPER DOCUMENTATION TO MAKE SURE T HIS UNIT GET FINALLY REPAIRED. (TC NR 20080215002) 2 L 7 2 4F 4 F RT T00008WI E6WE 2008032000011 20080320 00011 SO 2008 3 20 CA080215003 1 20080214 G 7820 9948200 MUFFLER PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA SNSNCH 74D 74DM EA ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND OVER THE PAST YEAR THAT USING PRESSURE TESTING VS VISUAL HAS CAUGHT MANY PIN HOLE LEAKS IN THE MUFFLER. IN TH E PAST WE WERE FINDING LARGE CRACKS IN BEHIND WHEN WE PRESSURE TESTED EVERY 200 HOURS WHICH YOU COULD NOT SEE VISUALLY S O WE BEGAN PRESSURE TESTING ALL THE TIME VERSUS VISUAL. ALSO FOUND THAT AFTER INSTALLATION OF NEW EXHAUST, PIN HOLES BEG AN TO SHOW BETWEEN 800-1000 HOURS LATER AND THEN PIN HOLES WOULD BEGIN TO SHOW EVERY 100 HOURS AFTER THAT. REALIZED THAT IF WE HAD NOT PRESSURE TESTED THE SYS, WOULD NOT FIND THE PIN HOLES AND WE WOULD END UP WITH A MAJOR REPAIR 100 HOURS L ATER. SO WE NOW PRESSURE TEST THE EXHAUST SYS EVERY 100 HRS COMMERCIAL AND ANNUALLY WITH PRIVATES. THIS HAS LOWER THE OV 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 20080521 GL 2008 5 21 CA080215005 2 20080215 G 7230 CASE HALF BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL COMPRESSOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON SPLITTING THE COMPRESSOR CASE HALVES FOR AN INSPECTION, IT WAS NOTED THERE WERE AREAS OF THE PLASTIC COATING TH AT WERE MISSING. CASES REPLACED. (TC NR 20080215005) 1 G 7 1 3U 3 U H2SW E4CE 2008032500003 20080325 00003 SO 2008 3 25 CA080215007 1 20080209 G 5520 486104 BOLT PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL ELEVATOR STOP BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE INSP OF THE ELEVATOR STOPS. WHEN THE DOWN STOP WAS PHYSICALLY TEST FOR SECURITY THE BOLT HEAD POP PED OFF. UPON CLOSER INSP THE BOLT WAS CRACKED AND WAS BEING HELD IN PLACE BY THE NORMAL ELEVATOR DOWN PRESSURE. NO OTHE R DAMAGE WAS NOTED, BOLT REPLACED AC RETURNED TO SERVICE. (TC NR 20080215007) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20080521 EA 2008 5 21 CA080215008 2 20080209 G 7314 RG9080J4A PUMP PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL FUEL SYSTEM ERRATIC W K NONE O OTHER IN INSP/MAINT 1 CA 482 (CAN) RT ENGINE DRIVEN FUEL PUMP REPLACED DUE TO ERATIC PRESSURE INDICATIONS. (TC NR 20080215008) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20080521 WP 2008 5 21 CA080215009 1 20080111 G 2497 CONNECTOR CVAC 440 440 2422902 WP ALLSN 501D 501D13 03004 GL ALLSN A6441 A6441FN606 GL CONTROL PANEL DAMAGED W E F ENGINE SHUTDOWN ACTIVATE FIRE EXT. G J MULTIPLE FAILURE WARNING INDICATION CL CLIMB 1 CA (CAN) ON CLIMBOUT, AT 5500FT, THE ADI, HSI AND VSI WENT UNSERVICEABLE AT THE SAME TIME, COMPLETE LOSS OF ELECTRICAL POWE R, RT SIDE. AT THE SAME TIME, THE NR 2 ENGINE FIRE WARNING (ILLUMINATED) CAME ON ALL 3 ZONES. CREW COMPLETED ENGINE FIRE DRILL. ATC ADVISED OF THE EMERGENCY, THE AC LANDED WITH NO OTHER INCIDENT REPORTED. AFTER INVESTIGATION FOUND THE RT A C CONTROL PANEL CONNECTOR DAMAGED AT PIN NR 10. BOTH THE AC CONTROL PANEL UNIT AND THE CONNECTOR WAS REPLACED AND TESTE D SERVICEABLE. A FLEET CAMPAING WAS CARRIED OUT TO INSPECT ALL THE AC CONTROL PANEL CONNECTORS FOR CONDITION AND NO DEFE CT DETECTED. (TC NR 20080215009) 2 L 7 2 4R 4 T 6A6 E282 6 C P898 20080521 2008 5 21 CA080215010 4 20080214 G 2215 2R5310A SERVO EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE AUTOPILOT MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA 5702 5702 (CAN) AUTOPILOT UNSERVICEABLE, EICAS MESSAGE (AP FAIL) ON FOR APPROX 3-5 SECONDS, THEN DISAPPEARS. AUTOPILOT AILERON SE RVO FAILED. FAULT CODES 22110239PA1 AND 22110239PA2 RECORDED. (TC NR 20080215010) 2 L 7 2 4F 4 F RT A56NM E00063EN 20080521 EA 2008 5 21 CA080215011 1 20080214 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 7867 7867 (CAN) DURING SELECTION OF FLAPS FROM 30 DEG TO 45 DEG ON APPROACH RECEIVED (FLAP FAI) MESSAGE ON EICAS. FLAPS FAILED TO MOVE WITH INDICATION OF 34 DEG. NORMAL LANDING. MAINT INSP FOUND NO ABNORMALITIES. FLAP DRIVE SHAFTS REMOVED AND LUBRICA TED IAW COMPANY POLICY. (TC NR 20080215011) 2 L 7 2 4F 4 F RT A21EA E15NE 20080521 EU 2008 5 21 CA080215012 1 20080214 G 3150 B19030W04 DISPLAY UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE MALFUNCTIONED W O OTHER N FALSE WARNING LD LANDING 1 CA 1874 1874 (CAN) THERE HAS BEEN REPORTS OF NUMEROUS SYS FAILURE REPORTS FROM THE VEMD SUCH AS NF/NR, MODULE, OVERLIMITS, LANE FAILU RES AND LIGHTING FAILURES AND NONE OF THESE FAILURES ACTUALLY OCURRED. THIS IS A PROBLEM WITH THE SOFTWARE AND HAS BEEN A PROBLEM ON THESE UNITS WITH YELLOW FAILURES EVERY DAY. (TC NR 20080215012) 1 G 7 2 3U 3 U NC R0001RD E34NE 20081229 CE 2008 12 29 CA080215013 1 20080207 G 2810 S51812 LINE CESSNA CESSNA 425 425 2076018 CE PWA PT6 PT6A112 52043 NE MCAULY 4HFR34 4HFR34C762 NE BLADDER VENT WORN W K NONE O OTHER IN INSP/MAINT 1 CA 7218 (CAN) LT AND RT NACELLE FUEL BLADERS WERE FOUND COLLAPSED. GROUND HANDLER REPORTED AIR RUSHING INTO TANK AFTER FILLER CA P REMOVAL WHILE PREPARING TO FUEL ACFT. FUEL VENT LINES WITHIN INTEGERAL WING TANK WERE FOUND TO HAVE HARD/BRITTLE RUBB ER COUPLER HOSES WHICH LEAKED FUEL INTO THE VENT SYS AND WAS TRAPPED IN A LOW SYS IN THE VENT LINES CAUSING BLOCKED VENT LINES AND COLLAPSING THE BLADDER TANKS DURING FLIGHT. RUBBERS REPLACED AND SYS OPS NORMAL. 1 L 7 2 3T 3 T RT A7CE E4EA 6 C 3PNE 20080521 EA 2008 5 21 CA080217002 1 20080211 G 5610 NP13932111 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA COCKPIT BROKEN W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 11342 (CAN) CAPTAINS WINDSHIELD BROKE CLIMBING THROUGH 19000 FT. FOLLOWED QRH AND RETURNED TO FIELD. WINDSHIELD IS A POST SB CONFIGURATION (TC NR 20080217002) 2 L 7 2 4F RT A21EA 20080521 EA 2008 5 21 CA080217003 1 20080211 G 5610 NP13932111 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 12616 (CAN) ON ROTATION CAPTAINS WINDSHIELD CRACKED. FOLLOWED QRH AND RETURNED TO THE FIELD. WINDSHIELD IS A POST SB CONFIGUR ATION. (TC NR 20080217003) 2 L 7 2 4F RT A21EA 20080521 EA 2008 5 21 CA080218001 1 20080216 G 3241 90004433 CONTROL UNIT CNDAIR CL600 CL600* 1900302 EA GE CF34 CF348C5 30050 NE ANTI SKID SYS FAULTY W O OTHER J WARNING INDICATION LD LANDING 1 CA 8195 (CAN) ON LANDING, CREW RECEIVED IB ANTI-SKID CAUTION MESSAGE. AFTER TAXIING CLEAR OF ACTIVE RUNWAY IT WAS DETERMINED BOT H LT MAIN TIRES FLAT. MAINT FOUND MDC FAULT CODES INDICATED FAULTY ASCU. ASCU REPLACED, AXLE INSP. FOR OVERTEMP AND TIRE S REPLACED. FUNCTION CHECKS C/O WITH NO FURTHER FAULTS. (TC NR 20080218001) 2 L 7 2 4F 4 F RT A21EA E00063EN 200805141 20080514 1 EU 2008 5 14 CA080218002 1 20080218 G 7130 0292827110 HEAT SHIELD TMECA ARRIEL2B SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE ENGINE CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 5478 2479 (CAN) WHILE REPLACING THE MO5, SEVERAL HOLES WERE NOTICED. THESE HOLES WERE DUE TO RUBBING AND WERE ONLY THROUGH THE OUT ER LAYER OF THE HEAT SHIELD. (TC NR 20080218002) 1 G 7 1 3U 3 U H9EU E00054EN 20081230 CE 2008 12 30 CA080218003 1 20080218 G 3260 30A01002203202 INDICATOR CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA HARTZL HCF3Y HCF3YR1 GL MLG FLOAT MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) IT WAS FOUND DURING AN INSP OF THE FLOATS THAT THE MLG INDICATOR COVERS COULD BE INSTALLED ON THE WRONG FLOAT. IF INSTALLED INCORRECTLY THE GEAR INDICATION IS REVERSED. 1 H 7 1 3O 3 O RT A4CE E14EA 5 C P31EA 20081230 CE 2008 12 30 CA080218004 1 20080218 G 2820 051338216 SELECTOR CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA FUEL SYS WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSP THE FUEL SELECTOR DRIVE ASSY WAS FOUND TO BE WORN OUT. THIS ALLOWED A TANK SELECTION TO BE MADE WITHOU T THE SELECTOR POSITIONING BALL AND SPRING HSG REACHING THE DETENT IN THE FUEL SELECTOR HSG. 1 H 7 1 3O 3 O NT 3A12 E274 20080521 EU 2008 5 21 CA080218005 1 20080218 G 7720 955017820 THERMOCOUPLE SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE ENGINE GROOVED W K NONE O OTHER IN INSP/MAINT 1 CA 478 (CAN) AFTER LESS THAN 500 HRS THERMOCOUPLES FOUND WITH A GROOVE WORN INTO TIPS. THIS IS THE SECOND TIME THIS DEFECT HAS BEEN FOUND. (TC NR 20080218005) 1 G 7 1 3U 3 U H9EU E00054EN 20080521 EU 2008 5 21 CA080218006 1 20080218 G 7722 9550178220 THERMOCOUPLE SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE ENGINE GROOVED W K NONE O OTHER IN INSP/MAINT 1 CA 478 (CAN) AFTER LESS THAN 500 HRS THERMOCOUPLES FOUND WITH A GROOVE WORN INTO TIPS. THIS IS THE SECOND TIME THIS DEFECT HAS BEEN FOUND. (TC NR 20080218006) 1 G 7 1 3U 3 U H9EU E00054EN 20081113 EU 2008 11 13 CA080219002 1 20080208 G 6730 SERVO SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE FLLIGHT CONTROL MALFUNCTIONED W L ABORTED APPROACH E F VIBRATION/BUFFET FLT CONT AFFECTED AP APPROACH 1 CA 10128 2345 (CAN) ALSO APPLIES TO SERVO SC5081-1 S/N 229 TSN 8917.4 TSO 2342.6 AND SERVO SC5082-1 S/N 361 TSN 5634.5 TSO 2345.1. A/C WAS APPOACHING FOR LANDING AND WHEN THE COLLECTIVE WAS REDUCED THERE WAS A VIOLENT VIBRATION, SEVERE ENOUGH TO CAUSE CO NCERN ABOUT LOSS OF CONTROL OF THE HELICOPTER. COLLECTIVE WAS INCREASED AND THE VIBRATION LEVEL RETURNED TO A NORMAL LEV EL. ALL M/R SERVOS WERE REPLACED AT ACRO HELIPRO AND SUBSEQUENT TEST FLYING HAS PROVEN THAT TO BE THE ROOT CAUSE. THERE WAS SOME LOW POWER VIBRATIONS EXPERIENCED IN THE PAST 12 MONTHS AND MOST OF THE RELATED DYNAMIC COMPONENTS HAD BEEN REPL ACED AND INSPECTIONS PERFORMED. THE VIBRATIONS WERE WITHIN LIMITS AND NEVER REACHED A LEVEL OF IMMEDIATE CONCEARN LIKE T 1 G 7 1 3U 3 U H9EU E19EU 20080603 NM 2008 6 3 CA080219004 1 20080218 G 3270 65715611 SKID BOEING 727 727227 1384078 NM PWA JT8 JT8D9A 52048 NE TAIL SKID DEFECTIVE W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) UPON GEAR RETRACTION, TAIL SKID LIGHT REMAINED ILLUMINATED. A/C RETURNED TO STATION WHERE SKID TIP WAS REPLACED, S WITCH CONTACT CONFIRMED AND A/C RETURNED TO SERVICE. (TC NR 20080219004) 2 L 7 3 4F 4 F A3WE E2EA 20080521 NM 2008 5 21 CA080219005 1 20080219 G 5320 654659244 CHANNEL BOEING 737 7374S3 1384711 NM BS 790 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLOOR CHANNEL AT BS 790, RBL 8 AFT CARGO PIT CORRODED AND REPAIRED IAW CUSTOMER EA (TC NR 20080219005) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080219006 1 20080219 G 5321 654659247 FLOOR PANEL BOEING 737 7374S3 1384711 NM AFT CARGO PIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL CORRODED AT BS 767+6, LBL 3 AND REPAIRED IAW CUSTOMER EA. (TC NR 20080219006) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080219007 1 20080219 G 5320 654659249 CHANNEL BOEING 737 7374S3 1384711 NM AFT CARGO PIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 727+8, LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080219007) 2 L 7 2 4F RT A16WE 20080521 EA 2008 5 21 CA080220001 1 20080219 G 7603 3018024 ROD END DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL NR 2 THROTTLE BENT W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) THE PILOT REPORTED A DEFECT NR 2582A: ABOUT 10 MINUTES AFTER TAKEOFF, THE RT ENGINE NR 2 THROTTLE LEVER WAS STUCK. WORKED THE THROTTLE BACK AND FORTH IN CRUISE 3 - 4 TIMES AND FOUND OK. ON FINAL APPROACH INTO ARRIVAL AIRPORT, THE N R 2 THROTTLE WAS DIFFICULT TO MOVE AGAIN. MAINT LATER FOUND THE WIRE WITH A 1.5 INCH LONG RIGID SPOT AT 18 INCHES FROM THE ROD END ATTACHMENT. THE ROD END P/N: 3008787 WAS FOUND BENT ALSO. BOTH PART WERE REPLACED AND RE-RIGGED THE ENGINE I AW MM. THE ENGINE WAS RECENTLY REPLACED AND HAS 3.4 HOURS SINCE LAST OVERHAUL. (TC NR 20080220001) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20080521 SW 2008 5 21 CA080220002 1 20080218 G 5610 2719442004 WINDSHIELD SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE COCKPIT DELAMINATED W O OTHER O OTHER CR CRUISE 1 CA 4902 (CAN) DURING THE CRUISE PORTION OF FLIGHT, THE CREW WITNESSED THE RT SIDE COCKPIT HEATED WINDSHIELD PHYSICALLY DELAMINAT ING . THE CREW INDICATED THE AC WAS OPERATING AT A 6.0 PSI DIFFERENTIAL WHICH IS WITHIN THE MAXIMUM 7.25 PSI DIFFERENTIA L FOR THE AC. NO ACTION WAS TAKEN BY THE CREW OR WAS DEEMED NECESSARY AND THE WINDOW DELAMINATION WAS MONITORED CLOSLY U NTIL LANDING. MAINT HAS REPLACED THE WINDSHIELD. (TC NR 20080220002) 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 20080521 2008 5 21 CA080220003 2 20080220 G 7414 BEARING MAGNETO WORN W K NONE O OTHER IN INSP/MAINT 1 CA 122 (CAN) MAG WAS RECEIVED FOR INSPECTION DUE TO ENGINE OVERSPEED. WHEN THE ROTATING MAGNET (ROTOR) WAS SPUN BY HAND THERE W AS NOTICEABLE SIDE PLAY IN THE BEARINGS. THE END PLAY WAS MEASURED AND FOUND TO BE .003 NR. MFG HAS A LIMIT OF NO SIDE PLAY ALLOWED. THE MAG WAS INSPECTED AND NO OTHER DEFECTS WERE FOUND. SHIMS WERE ADDED TO THE BEARINGS TO THE PROPER PRE LOAD AND THE MAG WAS TESTED AND RETURNED TO SERVICE. THIS WAS A FACTORY NEW MAGNETO WITH ONLY 121.5 HOURS IN SERVICE. (T C NR 20080220003) 20080521 EA 2008 5 21 CA080220005 2 20080130 G 7200 ENGINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6* 52043 EA HARTZL HCB4M HCB4MP3 GL MAKING METAL W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION DE DESCENT 1 CA (CAN) DURING DESCENT, THE PROPELLER AUTO-FEATHERED UNCOMMANDED. THE CREW ELECTED TO SHUTDOWN THE ENGINE AND PERFORMED A SINGLE ENGINE LANDING. POST FLIGHT INSP REVEALED A GRINDING NOISE WHEN TURNING THE PROP BY HAND. REDUCTION GEARBOX WAS C ONTAMINATED WITH OIL. THE ENGINE HAS BEEN SENT FOR INVESTIGATION AND REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT A ND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080220005) 2 L 7 2 4T 3 T RT A24CE E2NE 6 C P56GL 200805141 20080514 1 NE 2008 5 14 CA080220006 2 20080206 G 7250 TURBINE BLADES PWA PW127 AEROSP ATR72 ATR72212 8680945 EU PWA PW120 PW127 NE ENGINE FRACTURED W E A ENGINE SHUTDOWN UNSCHED LANDING K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB, THE ITT WAS NOTED TO RISE TO 800 DEGREES C, FOLLOWED BY SMOKE IN THE CABIN. THE CREW ELECTED TO SHUT DOWN THE ENGINE AND RETURN TO POINT OF DEPARTURE. POST FLIGHT INSPECTION INDICATED FRACTURED POWER TURBINE BLADES AND EV IDENCE OF OIL LEAKAGE. THE ENGINE WILL BE RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE PROVIDED. (TC NR 2008022000 6) 2 H 7 2 4T 4 T RT A53EU E20NE 20080521 NM 2008 5 21 CA080220007 1 20080115 G 7931 OIL SYSTEM DORNER DO32 DO328100 2996000 NM PWA 119 PW119B NE ENGINE LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, THE OIL PRESSURE WAS NOTED TO DROP. THE CREW SHUTDOWN THE ENGINE AND PERFORMED A SINGLE ENGINE LAND ING. ENGINE IS BEING SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ES TABLISHED (TC NR 20080220007) 2 H 7 2 4T 4 T RT A45NM E20NE 20080521 NE 2008 5 21 CA080220008 2 20080211 G 7200 ENGINE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE SEIZED W E A ENGINE SHUTDOWN UNSCHED LANDING R B PARTIAL RPM/PWR LOSS SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF, WHEN SELECTING BLEED AIR ON, THE CREW HEARD TWO (2) LOUD BANGS FOLLOWED BY SEEING SPARKS FR OM THE EXHAUST. PILOT SECURED THE ENGINE AND RETURNED TO POINT OF DEPARTURE. POST FLIGHT INSP REVEALED A SEIZED PROP A ND IMPACT DAMAGE INSIDE EXHAUST DUCT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISH ED (TC NR 20080220008) 2 L 7 2 4T 4 T RT A24CE E26NE 20080521 NM 2008 5 21 CA080220009 1 20080220 G 5320 654659249 CHANNEL BOEING 737 7374S3 1384711 NM AFT CARGO PIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+6, LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220009) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220010 1 20080220 G 5320 654659247 CHANNEL BOEING 737 7374S3 1384711 NM AFT CARGO PIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+6, LBL 8 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220010) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220011 1 20080220 G 5320 654659249 CHANNEL BOEING 737 7374S3 1384711 NM AFT CARGO PIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 847+14 - 867+14, LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220011 ) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220012 1 20080220 G 5340 650163312 STRINGER CLIP BOEING 737 7374S3 1384711 NM BS 294.5 S13L CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TIE CLIP AT BS 294.5, S13L CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220012) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220013 1 20080220 G 5310 651768537 DOOR FRAME BOEING 737 7374S3 1384711 NM L1 DOOR GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) L1 DOOR CUTOUT FRAME AT STA 349, WL 216 GOUGED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220013) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220014 1 20080220 G 4910 656612115 SHROUD BOEING 737 7374S3 1384711 NM APU CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) APU UPPER SHROUD CRACKED FWD OF FWD LATCH REPAIRED IAW CUSTOMER EA. (TC NR 20080220014) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220015 1 20080220 G 5313 65617777 STRINGER SPLICE BOEING 737 7374S3 1384711 NM BS360 S15L CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) STRINGER SPLICE AT BS 360, STR 15L CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220015) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220016 1 20080220 G 5320 65465926 CHANNEL BOEING 737 7374S3 1384711 NM AFT CARGO PIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS767+6, LBL11 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220016) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220017 1 20080220 G 5320 654659247 CHANNEL BOEING 737 7374S3 1384711 NM AFT CARGO PIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 727 F +8, LBL 11 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220017) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220018 1 20080220 G 5534 655484221 SKATE ANGLE BOEING 737 7374S3 1384711 NM VERTICAL STAB CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) V STAB TO FUSELAGE SKATE ANGLE LT CHAFED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220018) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220019 1 20080220 G 5320 6546592503 CHANNEL BOEING 737 7374S3 1384711 NM AFT CARGO PIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 727E+8, RBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220019) 2 L 7 2 4F RT A16WE 200805141 20080514 1 NM 2008 5 14 CA080220020 1 20080220 G 5320 6546592503 CHANNEL BOEING 737 7374S3 1384711 NM FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+6 - BS247+14, RBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 2008022002 0) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220021 1 20080220 G 5320 654659247 CHANNEL BOEING 737 7374S3 1384711 NM AFT CARGO PIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 847+14 - 867, LBL 8 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220021) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080220022 1 20080220 G 5320 654659247 CHANNEL BOEING 737 7374S3 1384711 NM AFT CARGO PIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+4, LBL 8 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220022) 2 L 7 2 4F RT A16WE 20080521 EA 2008 5 21 CA080221001 1 20080212 G 2810 CT2P10011 FUEL TANK DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL FORWARD DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 CA 16085 (CAN) THIS FWD FUEL TANK ENCLOSURE WAS FOUND BADLY DETERIORATED DUE TO ITS AGE, THERE WERE OLD REPAIRS FOUND CARRIED OUT . THIS ASSEMBLY HAD BEEN BULGING DUE TO THE FUEL, CAUSING CLOSER TOLERANCES TO THE ELEVATOR CONTROL PUSH/PULL TUBE. THI S ASSEMBLY HAS NOW BEEN REPLACED WITH A NEW CERTIFIED UNIT MADE FROM ALUMINUM IAW STC SA 06-51 MDL P/N VT2MK1555, ISSUE 1. (TC NR 20080221001) 1 H 7 1 3T 4 T A806 E4EA 6 C P15EA 20081230 CE 2008 12 30 CA080221002 1 20080208 G 7820 PN04504003 MUFFLER CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO MCAULY 1A101 1A101DCM GL EXHAUST SYS DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS IS AN ON GOING ISSUE. THIS EXHAUST MUFFLER PASSED THE VISUAL INSP AS CF90-03. WHEN PRESSURE TESTED WITH AIR A ND WATER, 3 PIN HOLES SHOWED. 2 WERE IN OPEN BARE METAL SURFACE. ONE WAS IN THE LONGITUDINAL SEAM. ANOTHER EXPERIENCED A ME WAS IN MY SHOP FOR OTHER REASONS. ASKED HIM TO VISUALLY INSPECT IAW CF90-03. EVEN THOUGH HE KNEW THERE WERE LEAKS, S O HE LOOKED MORE INTENSELY, HE WAS UNABLE TO FIND ANY, VISUALLY. THIS IS A 50 PERCENT FAILURE RATE FOR ACFT IN MY SHOP. AGAIN, THIS SHOP ONLY DOES BUBBLE TESTS AS THE VISUAL TEST, IAW CF90-03. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 20080521 EA 2008 5 21 CA080221003 1 20080220 G 2913 601R751547 PUMP CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE HYD SYSTEM UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 8050 (CAN) CREW RECEIVED A GEAR DISAGREE MESSAGE AFTER TAKEOFF WITH AN APPLICABLE RED NOSE GEAR INDICATION AND 2 MAIN GEAR AM BER MESSAGES. CREW ACTIONED THEIR QRH AND DO AN ALTERNATE EXTENSION, A/C RETURNED. PSEU CODES RETRIEVED AND THE AC WAS R OUTED WHERE MAINT WILL INVESTIGATE FURTHER. NOSE GEAR OLEO SERVICED TO C/O AND 3A HYD PUMP TO BE REPLACED. MORE INFORMAT ION TO FOLLOW. (TC NR 20080221003) 2 L 7 2 4F 4 F RT A21EA E15NE 20080603 SW 2008 6 3 CA080221004 1 20080209 G 6320 PT6T3B GEARBOX BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE MAIN ROTOR MISMANUFACTURED W O OTHER J WARNING INDICATION HO HOVERING 1 CA 37 (CAN) MAINT WAS TROUBLESHOOTING OIL PRESSURE PROBLEMS. THE POWER SECTION ALWAYS APPEARED THAT IT HAD LOTS OF OIL. VISUAL INDICATION. THE OIL PRESSURE FLUCTUATIONS OCCURRED FEB. 5TH. IN THE TROUBLESHOOTING PROCESS A LITTLE OIL WAS BEING DRA INED AND YET THE VISUAL INDICATION THERE WAS LOTS OF OIL. ON FEB. 9TH THE PWR SECTION WAS REMOVED DUE TO LOSS OF OIL PRE SSURE. A TECH REP WAS BROUGHT TO THE BASE AND IT WAS NOTICED THAT THE LOWER HOLE INTO THE GEARBOX OF THE OIL LEVEL INDIC ATOR WAS NOT DRILLED INTO THE CASE. SINCE THE OIL COULD NOT DRAIN OUT OF THE VISUAL INDICATOR THE OIL LEVEL APPEARED FUL L. (TC NR 20080221004) 1 G 7 1 4U 4 U H4SW E22EA 20081104 SW 2008 11 4 CA080221005 1 20080216 G 5302 206031327101 FITTING BELL 407 407 1182206 SW ALLSN 250C 250C47B GL TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6996 (CAN) LOWER LT TAILBOOM ATTACH FITTING FOUND CRACKED IN WEB AREA ON SCHEDULED INSPECTION. POSSIBLE ALIGNMENT ISSUES FROM THE MFG. REPLACED WITH UPGRADED ONE PIECE FITTING AND LONGERON. (TC NR 20080221005) 1 G 7 1 3U 3 U O H2SW E1GL 20080603 NE 2008 6 3 CA080221007 2 20080208 G 7200 PT6A68 ENGINE PWA PT6 PT6A68 NE MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING J E A WARNING INDICATION VIBRATION/BUFFET FLAME/FIRE NR NOT REPORTED 1 CA (CAN) DURING A TRAINING MISSION, THE PILOT REPORTED HIGH ITT, VIBRATION AND FLAME FROM THE ENGINE EXHAUST AND ELECTED TO SHUTDOWN THE ENGINE. LANDED WITHOUT INCIDENT. ENGINE WILL BE REMOVED AND RETURNED FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221007) 4 T E26NE 20080521 NE 2008 5 21 CA080221008 2 20080213 G 7200 ENGINE DHAV DHC8 DHC8* NM PWA PW121 PW121 52124 NE FLAMED OUT W O OTHER R X PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT AP APPROACH 1 CA (CAN) DURING APPROACH, ENGINE SHUTDOWN UNCOMMANDED AS FLAPS WERE BEING EXTENDED FOR LANDING. POST FLIGHT INSP REVEALED U NSTABLE FUEL FLOW AND LOW ITT AT IDLE POWER. FUEL PUMP AND FUEL CONTROL ARE BEING RETURNED FOR INVESTIGATION. MFG WILL C ONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221008) 2 H 7 2 4T 4 T RT A13NM E20NE 20080521 NE 2008 5 21 CA080221009 2 20080214 G 7320 EEC AEROSP ATR72 ATR72202 8680940 EU PWA PW120 PW124B NE ENGINE FAULTED W A UNSCHED LANDING R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CR CRUISE 1 CA (CAN) DURING CRUISE, AN EEC FAULT WAS FOLLOWED BY AN ENGINE POWER LOSS AND VIBRATION. THE CREW SHUT THE ENGINE DOWN AND DIVERTED THE FLIGHT ACCORDINGLY. POST FLIGHT INVESTIGATION REVEALED BOTH OIL FILTERS TO BE CONTAMINATED WITH DEBRIS AND THAT THE PROPELLER COULD NOT BE ROTATED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLI SHED (TC NR 20080221009) 2 H 7 2 4T 4 T RT A53EU E2ONE 20080521 NE 2008 5 21 CA080221010 2 20080214 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114 52043 NE FAILED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, A LOUD NOISE WAS HEARD FOLLOWED BY REDUCTION IN ENGINE POWER TO ZERO. THE AC LANDED ON A PUBLIC ROA D. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221010) 1 H 7 1 3T 3 T A37CE E4EA 20080603 2008 6 3 CA080221011 4 20080217 G 6122 GOVERNOR AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE PROPELLER LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, THE LOW OIL PRESSURE WARNING WAS ACTIVATED. THE CREW ELECTED TO SHUTDOWN THE ENGINE AND DIVERT THE AIRCRAFT TO AN ALTERNATE LANDING SITE. INITIAL INVESTIGATION REVEALED SIGNIFICANT EXTERNAL OIL LEAKAGE FROM THE PROPELLE R OVERSPEED GOVERNOR AREA. THE COMPONENT WAS REPLACED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUS E ONCE ESTABLISHED (TC NR 20080221011) 2 H 7 2 4T 4 T RT E20NE 200805141 20080514 1 NE 2008 5 14 CA080221012 2 20080214 G 7314 LW15473 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYSTEM LEAKING W O OTHER K FLUID LOSS NR NOT REPORTED 1 CA 936 (CAN) DURING THE PREFLIGHT CHECK THE ENGINE DRIVEN FUEL PUMP FOUND LEAKING OIL. (TC NR 20080221012) 1 G 7 1 3O 3 O H11NM 1E4 20081104 2008 11 4 CA080221013 4 20080214 G 3416 066030620010 ALTIMETER PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL COCKPIT INOPERATIVE W O OTHER J WARNING INDICATION NR NOT REPORTED 1 CA 112 (CAN) FLAG CAME INTO VIEW IN PILOTS ENCODING ALTIMETER AND NEEDLE FROZE. RETURNED TO NORMAL MOMENTS LATER. MAINT WAS NOT ABLE TO DUPLICATE THE SNAG. THERE IS AN SDR 20070914001 PERTAINING TO THE SAME DEFECT ON THIS SN UNIT, AS INSTALLED IN A DIFFERENT PC12. THE REPAIR REPORT AT THAT TIME INDICATED THE DEFECT HAD BEEN CONFIRMED AND REPAIRED. (TC NR 2008022101 3) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20080521 NM 2008 5 21 CA080222001 1 20080219 G 3246 L8121482629 BEARING DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE MLG WHEEL DISINTEGRATED W K NONE O OTHER IN INSP/MAINT 1 CA 19373 233 (CAN) DURING SERVICE CHECK ON THE RAMP, LINE MAINT OBSERVED THAT NR3 MAIN WHEEL ASSY HUB CAP WAS MISSING AND NOTICED THE PRESENCE OF METAL CHIPS. THE AC WAS REMOVED FROM SERVICE. MAIN WHEEL ASSY WAS REMOVED AND THE FOLLOWING DAMAGES WERE O BSERVED: BOTH WHEEL BRGS WERE DISINTEGRATED ALONG WITH DAMAGE TO THE WHEEL HUB AND BRAKE KEYS, BRAKE DISKS, WHEEL NUT AN D MLG AXLE. FOLLOWING OBSERVATIONS WERE NOTICED DURING THE INITIAL INVESTIGATION: THE WHEEL NUT WAS IN PLACE AND SECURE D WITH THE TWO LOCK BOLTS. THERE WAS NO LOCKING WIRE OBSERVED. THE WHEEL HUB CAP WAS MISSING BUT (2) OF THE (3) HOLDING SCREWS WERE STILL FIXED TO THE WHEEL FRAME. INSP OF THE INNER BEARING CLEARLY INDICATES THE CORRECT PN L713049*2-629. PN 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080521 SO 2008 5 21 CA080222002 2 20080221 G 8530 655475A CYLINDER CONT O470 O470* 17026 SO ENGINE UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FACTORY NEW CYLINDER ASSY RECEIVED FROM MFG WITH INCORRECT EXHAUST AND INTAKE VALVE GUIDES INSTALLED. INTAKE GUIDE P/N 655166 AND EXHAUST GUIDE P/N 636242 ARE REQUIRED IAW SB 04-11. UNABLE TO DETERMINE P/N OF GUIDES ACTUALLY INSTALLED IN NEW CYLINDER. SUSPECT INTAKE AND EXHAUST VALVE GUIDES INSTALLED IN WRONG LOCATIONS. CYLINDER SUBJECT TO WARRANTY THR OUGH MFG. (TC NR 20080222002) 3 O E273 20080521 EU 2008 5 21 CA080222003 1 20080220 G 2897 WIRE HARNESS AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE BOOST PUMP CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING TROUBLESHOOTING OF A FUEL BOOST PUMP SNAG, MAINT DISCOVERED THE RELATED WIRING HARNESS HAD BEEN DAMAGED DUE TO CHAFING ON THE EDGE OF THE FIXED CARGO LINER PANEL AT THE AFT SIDE OF THE 91VU SHELF. THE CARGO LINER PANEL IS PART OF THE FIRST AIR CLASS C INTERIOR, STC SA22-122 NOT AN OEM COMPONENT. THE WIRING WAS REPAIRED AND CLEARANCE ADJUSTED TO PRECLUDE FURTHER ISSUE. THE COMPANY HAS INITIATED A FLEET CAMPAIGN TO INSPECT FOR SIMILAR ANOMALIES. (TC NR 20080222003) 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 20080521 NM 2008 5 21 CA080222004 1 20080215 G 2497 284T3501315 ELECTRICAL BOX BOEING 767 767333 1385301 NM GE CF6 CF680C2B6F 30025 NE CARGO HANDLING BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) WIRING DAMAGE FOUND IN FWD CARGO HANDLING ACCESS PANEL P35 DURING THE (XM) VISIT. 57 WIRES BURN, 3 WIRES MAJOR DA MAGED, 1 FOUND CUT, FOUND LUG DAMAGE ON TERMINAL A1,B1,C1 OF RELAY K245 (P35). FOUND WIRES DAMAGE ON CONNECTOR D5886P. AFTER AN INVESTIGATION , FOUND CARGO PDU P/N 43104-14 AT POSITION 7R FAULTY (FOUND INTERNAL WIRES BURNED) ROOT CAUSE , THE FAULTY PDU CAUSED A SHORT IN THE P35 PANEL DAMAGING WIRES AND RELAY (TC NR 20080222004) 2 L 7 2 4F 4 F RT A1NM E13NE 20080521 EA 2008 5 21 CA080222005 1 20080222 G 3234 3620377 O-RING CNDAIR CL215 CL2151A10 1900320 EA PWA R2800 R2800CA3 52026 NE HAMSTD 43E 43E60 NE MLG DETERIORATED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) O-RING LOCATED BEHIND INDICATED SCREW IN DIAGRAM, DETERIORATED CAUSING A HYDRAULIC LEAK. THERE ARE (6) LOCATIONS O N THE AC THAT INCORPORATES THIS VALVE. THIS LEAK WAS DISCOVERED ON THE NLG SELECTOR VALVE LOCATED UNDER CO-PILOTS SIDE. (TC NR 20080222005) 2 H 7 2 4R 4 R RT A14EA 5E8 6 C P871 20080530 EA 2008 5 30 CA080222006 1 20080219 G 2910 LINE DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA HYD SYSTEM PUNCTURED W E F ENGINE SHUTDOWN ACTIVATE FIRE EXT. K A FLUID LOSS FLAME/FIRE TX TAXI/GRND HDL 1 CA 17426 HYDRAULIC PUMP SUPPLY LINE IN THE COCKPIT DEVELOPED A PIN-HOLE FAILURE IN THE WALL OF THE TUBING. THE HYDRAULIC FLUID A T A PRESSURE OF 1650 PSI WAS RELEASED INTO THE CABIN, ATOMIZING AS IT DID SO, THE DIRECTION OF THE SPRAY WAS DIRECTLY AT THE PILOT. THE POWER WIRE FOR THE HYDRAULIC PUMP ARCED AGAINST THE TUBING, IGNITING THE HYDRAULIC MIST AND IGNITING A FLASH FIRE. THE FIREBALL WAS UNABLE TO SUSTAIN ITSELF AND DID NOT IGNITE THE AIRCRAFT ALTHOUGH THE PILOT WAS SET ON FIR E, SUFFERED 1ST AND 2ND DEGREE BURNS TO HIS FACE AND RIGHT HAND. THE PASSENGER DID NOT RECEIVE ANY INJURIES AND WAS INS TRUMENTAL IN EXTINGUISHING THE PILOT, THE SYSTEM HAS BEEN IN THE ACFT SINCE MANUFACTURING, BUT DOES NOT MATCH ROUTING S 1 H 7 1 3T 4 T A806 E4EA 20080603 EU 2008 6 3 CA080222007 1 20080215 G 3211 201660001010 BOLT AIRBUS A321 A321211 3930370 EU CFMINT CFM56 CFM565B3P 13006 NE MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 20789 (CAN) CORRODED FAIL SAFE BOLTS THAT SECURE MAIN LANDING GEAR SIDE STAY ATTACH PINS TO UPPER AND LOWER CARDAN PINS. BOLTS ARE ITEMS 290 AND 296 IN A321 IPC 32-11-18-02E. ITEM 290 IS AN AN6-56A AND ITEM 295 IS AN AN6-62. THE LOWER BOLT ITEM 2 95 IS HEAVILY CORRODED. (TC NR 20080222007) 2 L 7 2 4F 4 F RT A28NM E37NE 20080603 NM 2008 6 3 CA080222008 1 20080222 G 2710 19004209401 CONTROL CABLE EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE AILERON WORN W K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 CA (CAN) DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 190-04212-401, P/N 190-04209-401 , RT P/N 190 -05551-401, P/N 190-04209-401) WORN AND WITH SEVERAL WIRES BROKEN AT FAIRLEAD, LOCATED AT LT AND RT WINGS R IB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. THE WORN AREAS AND BROKEN STRANDS ARE LOCATED UNDER NYLON GROMMETS (P/ N PE49068-501) MOUNTED ON THE FAIRLEAD. MFG WILL COME UP WITH AN SB END OF MARCH (TC NR 20080222008) 2 L 7 2 4F 4 F RT A57NM E00070EN 20080530 NM 2008 5 30 CA080222009 1 20080221 G 2710 17005825401 CONTROL CABLE EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE AILERON WORN W K NONE O OTHER IN INSP/MAINT 1 CA DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 170-05825-401, P/N 170-05826-401, RT P /N 170-05827-401, P/N 170-05828-401) WORN AND WITH WIRES BROKEN AT FAIRLEADS, LOCATED AT LT AND RT WINGS INB OF THE RIB 17. THE WORN AREAS AND BROKEN STRANDS ARE LOCATED UNDER NYLON GROMMETS (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. EMBR AER WILL ISSUE A SB END OF MARCH (TC# 20080222009) 2 L 7 2 4F 4 F RT A56NM E00063EN 20080603 NM 2008 6 3 CA080222010 1 20080221 G 5315 FLOORBEAM EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION FOUND ON FLOORBEAM LOCATED AT Y = 272.0 AND Z = -490.0 JUNCTION WITH FRAMES 16, 17, 18 AND ON FLOORBEAM LOCATED AT Y = -272.0 AND Z = -490.0 AND ON FRAME NR 14 AT Y = -337.0 AND Z = -490.0 ALSO (3) SILL PLATES CORRODED BEYON D LIMITS. CORROSION WAS ALSO FOUND ON FRAME 87, 88, 89 AND 90 UNDER THE AFT RT GALLEY ATTACHMENT POINT AT FLOOR STRUCTUR E. REFERENCE: PICTURE, AFT FUSELAGE, FORWARD FUSELAGE DUE TO NO ALLOWABLE REWORK LIMITS AVAILABLE IN THE SRM (STRUCTURAL REPAIR MANUAL) , ALL AFFECTED PARTS WHERE REPLACED OR REPAIRED AS MFG INSTRUCTION. THE ROOT CAUSE SEEMS TO BE THE LACK OF FLOOR PROTECTION UNDER THE FWD AND AFT GALLEYS. (TC NR 20080222010) 2 L 7 2 4F 4 F RT A56NM E00063EN 200805141 20080514 1 NE 2008 5 14 CA080225001 2 20080212 G 7321 78639114 HMU DHAV DHC8 DHC8* NM PWA PW121 PW121 52124 NE NR 2 ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS AP APPROACH 1 CA 1578 (CAN) AFTER CONFIGURING FOR LANDING (FLAP 35, CONDITION LEVERS MAX) CO-PILOT COMMENTED THAT HE HAD NOTICED A SIGNIFICANT POWER LOSS ON THE NR 2 ENG AND POINTED OUT A REDUCTION IN TORQUE. THE NR 2 TORQUE GAUGE WENT TO 0 PERCENT, CREW DECIDED TO SHUTDOWN THE NR 2 ENG. FUNCTIONAL CHECK OF THE ENG WAS CARRIED OUT BY MAINT STAFF. THE ENG WAS ABLE TO BE STARTED WI TH VERY SLOW ACCELERATION REPORTED AND LOW IDLE OF 60 PERCENT ONLY ACHIEVED - NP 168, FUEL FLOW 160, ITT 550 DEGREES. FO LLOWING COMMUNICATION OF THIS DATA WITH THE ENG MFG, IT WAS DETERMINED THAT THE MOST LIKELY CAUSE OF THE DEFECT WAS HYDR O MECHANICAL FCU (HMU) FUEL SCHEDULE. THE HMU AND FUEL PUMP ASSY WAS REPLACED IAW THE AC MM 72-01-40 AND SUBSEQUENTLY GR 2 H 7 2 4T 4 T RT A13NM E20NE 20080521 NM 2008 5 21 CA080225002 1 20080122 G 3260 83260024101 ROLLER DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE NLG SEIZED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 8236 (CAN) AFTER RETRACTING LANDING GEAR ON TAKEOFF, NOSE GEAR AMBER DOOR LIGHT REMAINED ILLUMINATED. CONDUCTED CHECKS IAW QR H (LANDING GEAR DOOR MALFUNCTIONS) UNABLE TO RECTIFY PROBLEM, RETURNED TO BASE WITH LANDING GEAR EXTENDED FOR NORMAL APP ROACH AND LANDING. INSP OF THE AC BY MAINT AFTER RETURN OF THE AC TO THE TERMINAL DETERMINED THAT THE NLG DOORS WERE CLO SED BUT THE CORRESPONDING INDICATION WAS OF AN UNSAFE CONDITION. FUNCTIONAL CHECK OF THE NLG DOORS AND INDICATING SYS CA RRIED OUT. THE ALTERNATE RELEASE ROLLER TRIPPING ARM BRG WAS DISCOVERED TO BE SEIZED AND THE CLEARANCE BETWEEN THE ROLLE R AND OB TOGGLE LINK OUT OF ADJUSTMENT. ROLLER PN 83260024-101 WAS REPLACED AND THE ALTERNATE RELEASE CABLE ADJUSTED IAW 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080521 NM 2008 5 21 CA080225003 1 20080219 G 2913 6617303 PUMP BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R320 CR3204123F1 GL NR 2 ENGINE SEPARATED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) NR 2 EDP FAILED IN FLIGHT WITH A BANG FOLLOWED SHORTLY AFTER BY NR1 HYD FLUID HOT CAUTION LIGHT ILLUMINATING, FOLL OWED BY THE 1 HYD ISO VALVE TO CLOSING. THE AC MADE A FLAPLESS EMERGENCY LANDING. INITIAL INVESTIGATION BY MAINT FOUND T HAT THE NR2 HYD SYS HAD LOST ITS FLUID, THE NR2 EDP PORT CAP HAD SEPARATED FROM THE EDP PUMP BODY, THE PTU WAS INOPERATI VE (OVERSPEED AND EVIDENCE OF OVERHEAT), PTU FLEX HOSES EVIDENCE OF OVERHEAT. MAINT ACTIONS: REPLACEMENT OF NR1 AND NR2 EDP`S, PTU, PTU SELECTOR VALVE, NR1 AND NR2 HYDR SYS FILTERS, REPLACEMENT OF PTU FLEX HOSES, FLUSHING/BLEEDING OF THE A PPLICABLE HYDR LINES. (TC NR 20080225003) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P5NE 20080521 EA 2008 5 21 CA080225005 1 20080222 G 2421 731579 SHAFT CNDAIR CL601 CL6012A12 1900303 EA GE CF34 CF343A2 30067 NE IDG BROKEN W H DEACTIVATE SYST/CIRCUITS O OTHER CL CLIMB 1 CA (CAN) 3 MINUTES AFTER TAKEOFF, GENERATOR FAILED, AC RETURNED TO BASE. GENERATOR REMOVED, FOUND BROKEN SHAFT INSIDE THE IDG (NOT THE MAIN SHAFT). IT BROKE, MELTED THE COVER AND CAME OUT (TC NR 20080225005) 2 L 7 2 4F 4 F RT A21AE E15NE 20080603 GL 2008 6 3 CA080225006 3 20080221 G 6114 HUB HARTZL HCE4A3D PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL PROPELLER LEAKING W K NONE K FLUID LOSS CR CRUISE 1 CA 663 (CAN) PROPELLER REMOVED DUE TO EXCESSIVE GREASE LEAK FROM BLADE CLAMPS. (TC NR 20080225006) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20080603 2008 6 3 CA080225007 4 20080221 G 2330 6009580001 MONITOR BOEING 757 75728A 1384976 NM RROYCE RB211 RB211535E437 54555 NE CABIN MALFUNCTIONED W O OTHER B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA (CAN) CREW REPORTED A BURNING SMELL IN THE CABIN JUST BEFORE LANDING. IN-FLIGHT ENTERTAINMENT WAS SELECTED OFF AND SMELL DISSIPATED. MAINTENANCE DETERMINED THAT THE SMELL WAS COMING FROM THE NR 7 MONITOR. (TC NR 20080225007) 2 L 7 2 4F 4 F RT A2NM E12EU 20081230 CE 2008 12 30 CA080225009 1 20080221 G 2730 0510105125 CONTROL CABLE CESSNA 180 180K 2072624 CE CONT O470 O470* 17026 SO MCAULY 2A34C C2A34C204 GL ELEVATOR FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA 140, WHERE CABLE RIDES ON THE PHENOLIC BLOCK. 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 20081230 CE 2008 12 30 CA080225010 1 20080204 G 2730 0510105125 CONTROL CABLE CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL ELEVATOR FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA140 AT PHENOLIC BLOCK. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 20081230 CE 2008 12 30 CA080225011 1 20080211 G 2730 0510105125 CONTROL CABLE CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C401 GL ELEVATOR FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA 140 AT THE PHENOLIC BLOCK. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 20080530 EA 2008 5 30 CA080225012 1 20080222 G 5343 19064104 FITTING CNDAIR CL604 CL604 1900301 EA MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 4481 DURING LANDING GEAR 96 MONTH DETAIL INSPECTION HEAVY PITTING CAUSED BY CORROSION. FOUND ON MAIN LANDING GEAR MAIN FITTI NG TRAILING ARM ATTACHMENT INBOARD LUG BUSHING AREA AND BORE, RESULTING CONSIDEABLE AMOUNT OF MATERIAL FROM AFFECTED LOC ATION, LEADING MAIN FITTINGTO REDUCED LOAD CARRYING CAPACITY 2 L 7 2 4F RT A21EA 20090102 CE 2009 1 2 CA080225013 1 20080220 G 3230 26410148 SPRING CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL MLG WORN W K NONE O OTHER IN INSP/MAINT 1 CA 3808 3808 (CAN) ON JACKING THE ACFT, THE RT MAIN SPRING WAS FOUND TO BE LOOSE IN THE CTR SPRING TO SUCH AN EXTENT THAT MAINWHEEL C OULD BE MOVED BACK AND FORTH .1250 ON AN INCH BEFORE THE REMOVAL BEGAN. UPON DISASSEMBLY THE MAIN SPRING WAS REMOVED BY HAND FROM THE CTR SPRING WITHOUT ANY PULLERS BEING USED. AMOUNT OF PLAY WHILE THE MAIN SPRING WAS STILL ASSEMBLED TO THE CTR SPRING SEEMED TO BE EXCESSIVE AND WAS NOT SOMETHING THAT WE HAD EXPERIENCED IN THE PAST. AFTER REMOVAL OF THE MAIN SPRING THE CTR SPRING WAS FOUND TO BE WITHIN LIMITS ON THE LT SIDE BUT OUT OF LIMITS ON THE RT SIDE. MAXIMUM DIAMETER M EASURED AT THE RT CENTER SPRING WAS 2.807 INCH, THE LIMIT IN THE MM IS 2.794 INCH. DURING A SEARCH OF THE ACFT RECORDS N 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20080530 NM 2008 5 30 CA080225014 1 20080222 G 2750 CLUTCH BOEING 737 737200 1384453 NM PWA JT8 JT8D17A 52049 NE TE FLAP DISENGAGED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA DEPARTING YOW THE AIRCRAFT EXHIBITED AN UNCOMMANDED ROLL TO THE LEFT REQUIRING 2-3 UNITS OF RUDDER TRIM TO CORRECT. THE CREW OBSERVED NO ASSYMMETRY INDICATION IN THE FLIGHT DECK BUT IT WAS VISUALLY CONFIRMED THAT THE RIGHT INBOARD AFT FLAP WAS PARTIALLY EXTENDED. MAINTENANCE FOUND THE INBOARD TRAILING EDGE FLAP CLUTCH DISENGAGED. THE MECHANISM WAS INSPECT ED, THE CLUTCH BELLCRANK RESET AND THE SYSTEM FUNCTION CHECKED SERVICEABLE. (TC# 20080225014) 2 L 7 2 4F 4 F A16WE E2EA 200805141 20080514 1 2008 5 14 CA080225015 2 20080225 G 7414 BEARING 106006169 MAGNETO EXCESS PLAY W K NONE O OTHER IN INSP/MAINT 1 CA 930 (CAN) MAG WAS RECEIVED FOR A 500 HR INSP. BEFORE THE MAG WAS DISASSEMBLED THE ROTATING MAGNET (ROTOR) WAS SPUN TO CHECK FOR BRG ROUGHNESS OR END PLAY. SOME SIDE PLAY WAS NOTICED (MFG DOES NOT ALLOW ANY) AND THE END PLAY WAS MEASURED AT .00 3 INCH. THE BRGS WERE INSPECTED, SHIMS WERE ADDED, THE REST OF THE 500 HOUR INSP WAS CARRIED OUT, AND THE MAG WAS RETURN ED TO SERVICE. THE MAG HAD 473.8 HRS SINCE ITS PREVIOUS 500 HR INSP. (TC NR 20080225015) 20081104 EA 2008 11 4 CA080226001 2 20080222 G 7322 THROTTLE BODY PIPER PA18 PA18A135 7101822 SO LYC O320 O320A2B 41508 EA SNSNCH 74DM M74DM EA CARBURETOR LOOSE W K NONE R J PARTIAL RPM/PWR LOSS WARNING INDICATION IN INSP/MAINT 1 CA 279 (CAN) DURING GROUND RUN UP PRIOR TO ANNUAL INSPECTION, ENGINE OBTAINED A MAXIMUM RPM OF 1900. INSPECTION FOUND CARBURETO R THROTTLE BODY SCREWS LOOSE AND FUEL STAINS ON BOWL. CARBURETOR REMOVED AND FORWARDED TO REPAIR FACILITY. (TC N 2008022 6001) 1 H 7 1 3O 3 O 1A2 E274 5 N P88614 20090102 CE 2009 1 2 CA080226002 1 20080219 G 3245 0923150 TUBE CESSNA 425 425 2076018 CE PWA PT6 PT6A112 52043 NE MCAULY 4HFR34 4HFR34C762 NE NLG TIRE DESTROYED W O OTHER E VIBRATION/BUFFET LD LANDING 1 CA (CAN) NOSE WHEEL BLEW OUT ON LANDING. TIRE AND RIM WERE INSPECTED FOR ANOMALIES WHICH WOULD CAUSE A BLOW OUT. NONE FOUND . THE TUBE IS SUSPECTED TO BE THE CAUSE OF CONCERN. ALSO UPON LANDING WITH A FLAT THE FENDER WAS DESTROYED AND THE TAXI LIGHT NEEDED TO BE REPLACED. 1 L 7 2 3T 3 T RT A7CE E4EA 6 C 3PNE 20081104 EU 2008 11 4 CA080226003 1 20080224 G 3110 ANNUNCIATOR SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE MALFUNCTIONED W O OTHER P NO WARNING INDICATION NR NOT REPORTED 1 CA 1403 (CAN) ON A ROUTINE CHECK FOLLOWING START, THE ANNUNCIATOR LIGHT FOR GOV FAILURE (RED) FAILED TO ILLUMINATE WHEN THE ENGI NE GOV SWITCH WAS MOVED FROM AUTO TO MANUAL. OTHER FUNCTIONS ASSOCIATED WITH MOVING TO MANUAL (SOLENOID, VEMD FAILURE CO DES) OPERATED NORMALLY. THE WARNING LIGHT ILLUMINATED DURING THE ANNUNCIATOR (ALL LIGHTS) PUSH TO TEST. THE ANNUNCIATOR PANEL WAS REPLACED WITH THE REPLACMENT UNIT OPERATING NORMALLY. (TC NR 20080226003) 1 G 7 1 3U 3 U H9EU E00054EN 20080521 SW 2008 5 21 CA080226004 1 20080222 G 2420 ALX8403 ALTERNATOR GULSTM 112 112 0144701 SW LYC O360 IO360C1D6 41514 EA HARTZL HCE2Y HCE2YR1BF GL ELECTRICAL UNSERVICEABLE W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) ALTERNATOR FAILED, CAUSING MAIN BATTERY TO DRAIN RESULTING IN COMMUNICATION DIFFICULTIES WHICH CAUSED PILOT TO CON TACT TOWER BY CELL PHONE FOR CLEARANCE TO LAND. NEW UPGRADED ALTERNATOR INSTALLED PN ALX8521R (TC NR 20080226004) 1 L 7 1 3O 3 O A12SO 1E10 5 C P9EA 20080521 EU 2008 5 21 CA080227001 1 20080131 G 2121 BEARING SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R389 R3894123F26 NE BLOWER MOTOR FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 74 (CAN) CABIN CREW NOTED AN ABNORMAL ODOR IN THE CABIN AND ADVISED THE COCKPIT CREW. IT WAS DECIDED TO LAND AT THE CLOSEST AIRPORT AS A PRECAUTION. PRIOR TO LANDING THERE WERE SEVERAL WISPS OF SMOKE OBSERVED IN THE FLOOR/SIDEWALL AREA. THE AC LANDED UNEVENTFUL. MAINT DETERMINED THAT THE SMELL WAS CAUSED BY A FAILED RECIRCULATION BLOWER MOTOR. IT IS BELIEVED TH AT A FAILED BEARING IN THE ASSEMBLY IS THE CAUSE OF THE FAULT. (TC NR 20080227001) 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P30NE 20080521 CE 2008 5 21 CA080227002 1 20080226 G 5210 SL51043 SPINDLE CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE MAIN CABIN DOOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 1583 (CAN) CREW SNAGGED MAIN CABIN DOOR OUTER HANDLE AS BEING SLOPPY. DISASSEMBLED DOOR HANDLE AND FOUND OUTER DOOR HANDLE SP INDLE TO BE EXESSIVELY WORN WHERE PIN FOR ATTACHING OUTER HANDLE FITS. MEASURED REMAINING MATERIAL AND FOUND TO BE 0.028 INCH ON ONE SIDE AND 0.031 INCH ON THE OTHER. REMOVED AND REPLACED SPINDLE WITH NEW AS IT WAS FELT THAT THIS PIECE WOUL D FAIL SOON AND ALLOW THE HANDLE (OUTER) TO COME OFF AND POSSIBLY BE INGESTED BY THE LT ENGINE. (TC NR 20080227002) 2 L 7 2 4F 4 F RT A22CE E00059EN 20080521 EA 2008 5 21 CA080227003 1 20080219 G 7931 OIL SYSTEM CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B 30069 NE ENGINE LOW PRESSURE W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) LOW OIL PRESS WARNING ON NR 2 ENGINE APPROX 3 MINS AFTER TAKEOFF AT 6000FT MSL ON DEPARTURE CLIMBOUT. AFTER IDENTI FICATION OF FAULT AND CONFIRMATION THAT THE FAULT WAS NOT AN INDICATION PROBLEM NR 2 ENGINE WAS SHUTDOWN AND SECURED. RE TURNED SAFELY. THE CAUSE HAS YET TO BE DETERMINED. (TC NR 20080227003) 2 L 7 2 4F 4 F RT A21EA E15NE 20081104 SW 2008 11 4 CA080227004 1 20080201 G 5311 20631308015S FRAME BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE UPPER RT ATTACH POINT ON THE AIRFRAME SIDE CRACKED ON THE FRAME RING ONLY. PART REPLACED WITH NEW FROM MFG. ( TC NR 20080227004) 1 G 7 1 3U 3 U H2SW E4CE 20080521 SW 2008 5 21 CA080227005 1 20080131 G 5320 206031322003 STIFFENER BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT STIFFENER UNDER THE OIL COOLER HANGER BEARING CRACKED FROM FWD ANCHOR NUT WHOLE. REPLACED WITH NEW PART. (TC NR 20080227005) 1 G 7 1 3U 3 U H2SW E4CE 20080521 NE 2008 5 21 CA080227006 2 20080122 G 7414 10885435 CAM ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 320 (CAN) DURING A 500 HR MAG INSPECTION IT WAS NOTED THE CAM WAS TIGHT TO SHAFT, COULD NOT BE REMOVED BY HAND. CAM WAS TAPP ED OFF SHAFT WITH BRASS PUNCH AND HAMMER. WHEN CAM CAME OFF SHAFT IT BROKE INTO 4 PIECES. (TC NR 20080227006) 1 G 7 1 3O 3 O H11NM 1E4 20080530 GL 2008 5 30 CA080227007 2 20080227 G 7230 6898607 BEARING RACE BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL COMPRESSOR SPALLED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 1399 DURING FLIGHT THE PILOT HAD A CHIP LIGHT INDICATION. UPON INSPECTION, THE CHIP PLUG HAD LITTLE DEBRIS AND SMUDGE. THE CHIP WAS CLEANED, REINSTALLED AND FURTHER GROUND RUNS WHERE CARRIED OUT PRIOR TO FLIGHT. NO FURTHER ISSUES WERE NOTED A ND THE FLIGHT CONTINUED. A FEW HOURS LATER ANOTHER CHIP LIGHT HAD ILLUMINATED. THE AIRCRAFT WAS RETURNED TO THE BASE V IA TRUCK AND TRAILER. FURTHER INVESTIGATION REVEALED FWD CHIP PLUG HAD METAL EVIDENT ON THE PLUG. THE COMPRESSOR WAS R EMOVED AND THE NR 1 BEARING INNER RACE SHOWED EVIDENCE OF SPALLING. THE GEARBOX ALSO HAD AN ISSUE ADDRESSED BY ANOTHER SDR RELATED TO THIS AIRCRAFT. WILL SUBMIT PICTURES WHEN THEY ARE AVAILABLE. (TC# 20080227007) 1 G 7 1 3U 3 U H2SW E4CE 20080530 SW 2008 5 30 CA080227008 1 20080227 G 6320 23034787 BEARING RACE BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL GEARBOX SPALLED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 6794 (CAN) METAL WAS FOUND ON ENGINE LOWER CHIP PLUG. THE 2 1/2 BEARING IN THE GEARBOX WAS REMOVED AND FOUND THE SPALLING ON THE OUTER RACE. 1 G 7 1 3U 3 U H2SW E4CE 20080603 NM 2008 6 3 CA080228001 1 20080119 G 3230 C247300016 UPLOCK AIRBUS A319 A319114 3930350 NM GE CFM56 CFM565A 13802 NE NLG FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 29460 AFTER TAKEOFF, THE CREW COULD NOT RETRACT THE NOSE GEAR. THE GEAR WAS RECYCLED WITH NO SUCCESS. THE CREW RETURNED TO L AND AT DEPARTURE AIRPORT. THE NLG UPLOCK ASSEMBLY WAS REPLACED AND A LANDING GEAR SWING CARRIED OUT. DESCRIPTION/ROOT CAUSE, THE UNIT WAS SENT FOR REPAIR WITH THE REQUEST FOR A TEARDOWN REPORT. THE UNIT WAS PRE-TESTED AND FAILED THE LOCK ING TEST. THE LOCK MECHANISM INSIDE THE UNIT FAILED TO LOCK THE HOOK. THE REPAIR FACILITY CONCLUDED THAT THE DRIED GRE ASE CAUSED THE LOCKING MECHANISM TO HANG UP AND PREVENTED THE HOOK FROM LOCKING THE NOSE LANDING GEAR. THE WEAR TO THE UNIT WAS NORMAL AND NO OTHER MECHANICAL DIFFICULTIES WERE OBSERVED. AT TIME OF THIS REPORT THE REPAIR ORGANIZATION WAS 2 L 7 2 4F 4 F RT A28NM E29NE 200805141 20080514 1 NM 2008 5 14 CA080228002 1 20080222 G 5315 17003264001 FLOORBEAM EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION FOUND ON FLOORBEAM LOCATED AT Y = 272 AND Z = -490.0 JUNCTION WITH FRAMES 16, 17, 18 . ALSO (3) SILL PLA TES CORRODED BEYOND LIMITS. CORROSION WAS ALSO FOUND ON FR 87, 88, 89 AND 90 UNDER THE AFT RT GALLEY ATTACHMENT POINT AT FLOOR STRUCTURE. REFERENCE: PICTURE NR AFT FUSELAGE FRAME 87, 89, 90 NR FLOORBEAM FRAME 18 POSSIBLE ROOT CAUSE: FLOOR P ROTECTION UNDERNEATH THE GALLEY NOT ADEQUATE. (TC NR 20080228002) 2 L 7 2 4F 4 F RT A56NM E00063EN 20080521 NM 2008 5 21 CA080228003 1 20080215 G 2150 18279018 ACM DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE FAILED W G A O2 MASK DEPLOYED UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 12421 (CAN) DURING CLIMB, CREW NOTICED A SMELL OF SMOKE IN THE FLIGHT DECK. CREW DONNED OXYGEN MASKS AND COMPLETED THE (OXYGEN DRILL). UNSCHEDULED LANDING COMPLETED. ENGINEERING ONSITE INVESTIGATION CONFIRMED FAILURE OF THE AFT AIR CYCLE MACHINE (ACM). THE AFT ACM WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. ACM HAS BEEN DISPATCHED T O THE MFG FOR REPAIR/OVERHAUL WITH A REQUEST TO PROVIDE A STRIP REPORT. (TC NR 20080228003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080521 NM 2008 5 21 CA080228004 1 20080219 G 3230 483025 SEQUENCE VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R320 CR3204123F1 GL NLG FAILED W O OTHER J WARNING INDICATION CL CLIMB 1 CA 93 (CAN) AN OPERATOR COMPLETED AN EMERGENCY LANDING DUE TO NLG DOOR OPEN INDICATION AFTER SELECTING GEAR UP. UNSCHEDULED LA NDING, CREW FOLLOWED THEIR QRH, PERFORMED ALTERNATE GEAR EXTENSION. NLG SOLENOID SEQUENCE VALVE REPLACED. (TC NT 2008022 8004) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P5NE 20081104 SW 2008 11 4 CA080228007 1 20080124 G 3246 206050297105 SKID BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8330 (CAN) UPON INSTALLATION OF GROUND HANDLING WHEELS IT WAS DISCOVERED THAT THE MOUNTING LUGS ON THE FWD LT SIDE WAS DETACH ED AND LOOSE DUE TO LARGE PERFORATION (HOLE) IN THE ATTACHMENT AREA. FURTHER VISUAL INSPECTION REVEALED CIRCUMFERENTIAL CRACK APPROXIMATELY (3) QUARTERS AROUND THE SKID TUBE, SLIGHTLY FWD OF THE SADDLE LOCATION AND RUNNING AROUND THE BOTTOM PORTION OF THE TUBE. EXTENSIVE CORROSION ALSO DETECTED IN AND AROUND AFFECTED AREA. SKID TUBE REPLACED WITH NEW UNIT. ( TC NR 20080228007) 1 G 7 1 3U 3 U H2SW E4CE 20080521 NM 2008 5 21 CA080228009 1 20080225 G 3260 SENSOR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R320 CR3204123F1 GL MLG DOWNLOCK FAULTED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) AFTER DEPARTURE, AN ABNORMAL GEAR INDICATION WAS OBSERVED. DECISION TO CONTINUE TO NEXT BASE IAW MCC AND OCM. ON A RRIVAL, ALTERNATE GEAR EXTENSION, ACCORDING PROCEDURE PERFORMED. NORMAL INDICATION (3 GREEN) ON MAIN AND ALTERNATE SYS. DURING FINAL: GEAR UNSAFE-INDICATION ON MAIN INDICATION AGAIN, NORMAL INDICATION ON ALTERNATE SYS. UNEVENTFUL LANDING AN D NORMAL DISEMBARKATION ON THE RUNWAY FOLLOWED. PSEU FAULT CODES AS FOLLOWS: LEG 00: LGDLK 1 PROX SENSOR OPEN, LGDLK 1 P ROX SENSOR SHORT, PSEU CHANNEL D FAIL CHANNEL INOP, LGDLK1 UNREASONABLE NEAR, NLGLK2 UNREASONABLE NEAR, NLGLK1 UNREASONA BLE NEAR, NGDRCL UNREASONABLE NEAR, NGWOFW2 UNREASONABLE NEAR NGWOFW1 UNREASONABLE NEAR, NGDN2 UNREASONABLE FAR, NGDN1 U 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P5NE 20080521 NM 2008 5 21 CA080228010 1 20080225 G 2750 734386B TORQUE TUBE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE TE FLAPS SHEARED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) A/C WAS ON APPROACH INTO AIRPORT, THE FLAPS WERE LOWERED TO 15 DEG WHEN THE (FLAP DRIVE CAUTION LIGHT) CAME ON. TH E A/C LANDED WITHOUT INCIDENT. MAINT INSP REVEALED THAT THE LT OB TORQUE TUBE WAS SHEARED OFF. AFTER FURTHER INSP, IT WA S DETERMINED THAT THE TORQUE TUBE WAS SHEARED OFF BY CLAMP INSTALLED ON A DRAIN LINE THAT HAD BEEN CHAFING. THE TORQUE T UBE WAS REPLACED, THE TORQUE SENSOR RIGGED AND THE FLAPS WERE FUNCTION CHECKED SERVICEABLE. (TC NR 20080228010) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080602 SW 2008 6 2 CA080228011 1 20080227 G 3230 2752003042 BELLCRANK SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE3311 01514 WP MCAULY 4HFR34 4HFR34C652 NE NLG MISSING W K NONE O OTHER IN INSP/MAINT 1 CA DURING MAINTENANCE GEAR RETRACTION A "CLICKING" NOISE WAS HEARD FROM THE NOSE GEAR WHEELWELL. THE ROLLER BEARING ON THE RT NOSE GEAR BELLCRANK WAS BROKEN AND ONLY THE INNER RACE REMAINED ON THE BOLT. THE BELLCRANK WAS REPLACED, GEARSWINGS CARRIED OUT AND AIRCRAFT RETURNED TO SERVICE (TC NR 20080228011) 2 L 7 2 4T 3 T RT A8SW E3WE 6 C 3PNE 20080602 SW 2008 6 2 CA080228012 1 20080220 G 3222 MS171536 PIN FRCHLD SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE3311 01514 WP MCAULY 4HFR34 4HFR34C652 NE RH TORQUE KNEE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA PIVOT PIN FOR RT MAIN GEAR TORQUE KNEE WAS PROTRUDING FROM THE TORQUE KNEE. SPRING PIN REMOVED AND INSPECTED. NO DAMAG E FOUND. NEW SPRING PIN INSTALLED. NO FURTHER PROBLEMS SINCE REPLACEMENT OF SPRING PIN (TC NR 20080228012) 2 L 7 2 4T 3 T RT A8SW E3WE 6 C 3PNE 20080602 EA 2008 6 2 CA080229001 1 20080218 G 5610 NP1393222 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT CRACKED W O OTHER O OTHER DE DESCENT 1 CA 10959 FLT NR 6671 - FIRST OFFICER SIDE WINDOW CRACKED ON DESCENT INTO PSP. WINDOW REPLACED (TC NR 20080229001) 2 L 7 2 4F 4 F RT A21EA E15NE 20080602 NE 2008 6 2 CA080229002 2 20080221 G 7200 4129T17G04 ACTUATOR CNDAIR CL600 CL6002D24 1390016 EA GE CF34 CF348C1 30049 NE LT ENGINE CRACKED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION AP APPROACH 1 CA "925 PWM, LT ENG FAILURE ON SHORT FINAL. ON SHORT FINAL (APPROX 1500 FT) CAPT REPORTED LT ENGINE FAILURE. N1 WENT TO 32 PERCENT AND EICAS DISPLAYED LT FADEC AND LT BLEED CAUTION ME PERCENT. CAPT SAW NO OTHER ENGINE RELATED ANOMALIES, IE N O PROBLEMS WITH FUEL FLOW, ITT, OIL PRESSURE OR WARNINGS. CVR AND FDR CIRCUIT BREAKERS HAVE BEEN PULLED. AIRCRAFT VERI FIED NOT IMPOUNDED BY THE NTSB. CONTRACT MX INTERROGATE MDC. MDC REVEALED LH PS3 SENSE LINE, L FMU FAILED AND VG CMD\P OSN DISAGREE. MX INSPECT INLET FOR POSSIBLE INGESTION, NO FINDINGS. EXHAUST AREA LOOKED GOOD AS WELL. OPENED COWLING AND INSPECTED VG ACTUATORS AND AREA. MX THOROUGHLY INSPECTING AREA. WE HAVE SENT MM/IPC REFERENCES OF AREAS TO INSPECT 2 L 7 2 4F 4 F RT A21EA E00063EN 200805141 20080514 1 NM 2008 5 14 CA080229003 1 20080221 G 3260 864202 PROXIMITY SENSOR DHAV DHC8 DHC8* NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NLG INTERMITTENT W D RETURN TO BLOCK N FALSE WARNING TX TAXI/GRND HDL 1 CA (CAN) GEAR UNSAFE (NOSE GEAR) ILLUMINATED DURING TAXI-IN WITH ASSOCIATED GEAR WARNING HORN. AC WAS STOPPED AND SHUTDOWN, EMERGENCY SERVICES REQUESTED FROM TOWER. F/O INSERTED NOSE GEAR LOCK IMMEDIATELY AFTER SHUTDOWN. ENGINEERING INSPECTED THE AC AND TOWED IT TO BAY. MAINT CARRIED OUT INDUCTANCE, CONTINUITY AND MEGGER CHECK OF THE NLG DOWNLOCK SENSOR AND NLG DRAG STRUT SENSOR. THE NLG DRAG STRUT SENSOR 3261-S10 (WDM REF NR) WAS FOUND TO HAVE VARIABLE INSULATION OF 100 MEGA OH MS. THE NLG DRAG STRUT SENSOR WAS REPLACED IAW THE AC MM 32-20-11. NLG RETRACTION AND EXTENSION CHECKS/ TESTS CARRIED OU T IAW AC MM 32-30-00, ALL INDICATIONS CHECKED SERVICEABLE. AC RETURNED TO SERVICE. (TC NR 20080229003) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080521 CE 2008 5 21 CA080229004 1 20080228 G 2420 PULLEY CESSNA 210 210R 2073458 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL ALTERNATOR SEPARATED W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA 51 (CAN) WHILE IN FLIGHT, NR1 ALTERNATOR FAILED, NR1 ALT AMBER LIGHT CAME ON, ON THE GROUND, INSP REVEALED THAT THE DRIVE PULLEY HAD SEPARATED FROM ALTERNATOR, PULLEY FOUND DAMAGED WITH OTHER BROKEN PULLEY PIECES ON THE BUTTOM OF COWLING. RE TAINING NUT HAD GONE AWAY. END SHAFT (ARMATURE) WAS NOT SEIZED. SUSPECT A QC PROBLEM IN THIS CASE. ALTERNATOR REPLACED WITH O/H UNIT. (TC NR 20080229004) 1 H 7 1 3O 3 O RT 3A21 E5CE 5 C P47GL 20080521 CE 2008 5 21 CA080229005 1 20080229 G 5753 0512128 BRACKET CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL TE FLAPS BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 7402 (CAN) ON PREFLIGHT INSPECTION, PILOT FOUND WHEN FLAPS EXTENDED, LT FLAP HAD NO TENSION, AND COULD BE LIFTED TO THE RETRA CT POSITION, POTENTIALLY CAUSING DISIMILAR LIFT WHEN ACTIVATED IN FLIGHT. INSPECTED AREA, AND FOUND LT BRACKET BROKEN A T F.S. 65.33, IB MOUNTING TABS BROKEN. SIMILAR OCCURANCE INSPECTED AREA EACH 100 HRS SINCE, NO INDICATION OF CRACKS PRE VIOUSLY DETECTED. SUSPECT THAT FAILURE IS IMMEDIATE AS BREAKS LOOK NEW. POORLY DESIGNED PART FOR LOADS THAT ARE IMPOSED . (TC NR 20080229005) 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 20080521 2008 5 21 CA080229007 4 20080220 G 2565 416T28243 LEVER BOEING 767 76735H 1385208 NM GE CF6 CF680C2B6F 30025 NE OVERWING SLIDE MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) OVER-WING SLIDE COMPARTMENT DOOR OPENING ACTUATING MECHASIM - LEVER DESCRIPTION: A LEVER THAT JOINS THE FIRING PIN CLEVIS OF THE OFF-WING ESCAPE SLIDE COMPARTMENT DOOR OPENING ACTUATOR TO THE ACTUATING ROD IS BEING INSTALLED UPSIDE-DO WN. THIS APPEARS TO CAUSE THE LEVER TO BIND WITH THE FIRING PIN CLEVIS AND COULD PREVENT NORMAL DOOR OPENING ACTUATION I N A REAL SITUATION. IT SEEMS THAT NO SDR WAS RAISED FOR THE PREVIOUS FINDING. LEVER ORIENTATION CORRECTED IAW DIAGRAMS SUPPLIED IN THE IPC AS WELL AS THOSE DIAGRAMS INCLUDED WITH THE RIGGING INSTRUCTIONS IN THE AMM. ENGINEERING APPROACHED TO ADDRESS A POSSIBLE AMENDMENT TO THE AMM. (TC NR 20080229007) 2 L 7 2 4F 4 F RT A1NM E13NE 20080521 GL 2008 5 21 CA080229008 2 20080206 G 7200 ENGINE BELL 407 407 1182206 SW ALLSN 250C 250C47B GL VIBRATION W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 CA (CAN) EXCESSIVE ENGINE NOISE AND HIGH VIBRATION FELT BY PILOT AT GROUND IDLE. VERFIED BY ENGINEER. COMPLETE ENGINE REMOV ED AND SENT FOR INVESTIGATION. WILL FWD REPORT WHEN AVAILABLE. (TC NR 20080229008) 1 G 7 1 3U 3 U O H2SW E1GL 20080521 GL 2008 5 21 CA080229010 2 20080227 G 7230 SCROLL ALLSN BELL 407 407 1182206 SW ALLSN 250C 250C47B GL COMPRESSOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) COMPRESSOR 390.6 SINCE 2000 HOUR INSP. CRACK LOCATED BY ENGINEER DURING GROUND RUN UP FOLLOWING SCHEDULED INSP. L OCATED BY AIR LEAK FOUND BY BARE HAND CHECK. CRACK LOCATED SLIGHTLY BELOW SCROLL ARMPIT REINFORCEMENT PATCH AREA, NOT IN NORMAL CRACK LOCATION. A SMALL PIECE OF PATCH MATERIAL ALSO FOUND MISSING. COMPRESSOR REMOVED AND SENT FOR REPAIR. (TC NR 20080229010) 1 G 7 1 3U 3 U O H2SW E1GL 20080521 SO 2008 5 21 CA080229011 1 20080226 G 8120 4091701 SHAFT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL TURBOCHARGER SHEARED W A UNSCHED LANDING B R SMOKE/FUMES/ODORS/SPARKS PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 3 (CAN) SHORTLY AFTER TAKEOFF, WHEN SETTING CRUISE POWER, THE LT ENGINE WOULD NOT STAY AT CRUISE POWER. AFTER A COUPLE OF ADJUSTMENTS THE POWER DROPPED FROM 31IN TO AS LOW AS 12IN OF MANIFOLD PRESSURE. THE AIRCRAFT RETURNED FOR LANDING. MAIN T FOUND THE SHAFT THAT CONNECTS THE EXHAUST AND INTAKE TURBINE WHEELS ON THE TURBOCHARGER WAS BROKEN AT THE EXHAUST TURB INE WHEEL. NO REASON COULD BE FOUND FOR THE FAILURE. THE TURBOCHARGER HAD 2.7 HOURS SINCE OVERHAUL. (TC NR 20080229011) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20080521 EA 2008 5 21 CA080229012 2 20080229 G 8530 LW12966 CYLINDER PIPER PA28 PA28140 7102802 SO LYC O540 TIO540J2BD 41532 EA ENGINE UNSERVICEABLE W B A EMER. DESCENT UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA 150 (CAN) PILOT HEARD A BANG WHILE IN CRUISE AND NOTICED A LOSS OF POWER. TURNED BACK TO THE NEAREST AIRPORT TO LAND. UPON I NSPECTION THE AME FOUND THAT THE NR1 INTAKE VALVE WAS MISSING. THE ENGINE WAS REMOVED. WHEN WE REMOVED THE NR1 CYLINDER, WE FOUND THAT THE INTAKE VALVE HAD BROKEN OFF AT THE KEEPERS AND A PIECE HAD SHOT OUT THE SIDE OF THE PORT AND LODGED I TSELF IN THE FINS OF THE NR3 CYLINDER. THERE WAS CONSIDERABLE DAMAGE TO BOTH CYLINDERS. THE REST OF THE VALVE HAS YET TO BE SEEN BUT IT IS EXPECTED TO BE FOUND ONCE WE REMOVE THE INDUCTION COVER. (TC NR 20080229012) 1 L 7 1 3O 3 O 2A13 E14EA 20080521 NM 2008 5 21 CA080303001 1 20080228 G 5315 FLOORBEAM EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 3948 (CAN) CORROSION FOUND ON FLOORBEAM LOCATED AT Y = 272.0 AND Z = -490.0 JUNCTION WITH FRAMES 16, 17, 18, 19 AND ON FLOORB EAM LOCATED AT Y = -272.0 AND Z = -490.0 AND ON FRAME NR12 AND 14 , 14 AT Y = -337.0 AND Z = -490.0 ALSO THREE SILL PLAT ES CORRODED BEYOND LIMITS. CORROSION WAS ALSO FOUND ON FRAME 87, 88, 89 AND 90 UNDER THE AFT RT GALLEY ATTACHMENT POINT AT FLOOR STRUCTURE. REFERENCE: PICTURE NR AFT FUSELAGE, FORWARD FUSELAGE DUE TO NO ALLOWABLE REWORK LIMITS AVAILABLE IN THE SRM (STRUCTURAL REPAIR MANUAL) , ALL AFFECTED PARTS WHERE REPLACED OR REPAIRED AS IAW MFG INSTRUCTION. (TC NR 20080 303001) 2 L 7 2 4F 4 F RT A56NM E00063EN 20080602 NM 2008 6 2 CA080303002 1 20080228 G 2710 17005825401 CONTROL CABLE EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE AILERONS DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 3948 DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 170-05825-401) WORN AND WITH WIRES BRO KEN AT FAIRLEADS, LOCATED AT LT WINGS INB OF THE RIB 17. THE WORN AREAS AND BROKEN STRANDS ARE LOCATED UNDER NYLON GROM METS (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. EMBRAER HAVE BEEN ADVISED (TC NR 20080303002) 2 L 7 2 4F 4 F RT A56NM E00063EN 20080603 SO 2008 6 3 CA080303003 1 20080229 G 2421 BEARING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ALTERNATOR FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 1093 IN CRUISE, THE PILOT NOTICED THE RT ALTERNATOR WARNING LIGHT CAME ON. CHECKED THE BREAKER BUT IT HAD NOT BLOWN. PULLED BREAKER AND LANDED UNEVENTFULLY. MAINTENANCE INSPECTED THE RT ALTERNATOR AND DISCOVERED THAT THE ALTERNATOR BEARING HA D SEIZED AND BROKEN THE BELT. (TC NR 20080303003) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081104 SW 2008 11 4 CA080303004 1 20080303 G 6510 327211 DISC PACK BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL T/R DRIVE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2562 (CAN) DISC PAC WAS REMOVED FOR INSPECTION DURING A SCHEDULED 1200 HOUR INSPECTION. CRACKED DISC WAS DISCOVERED DURING DI SASSEMBLY. ONE DISC OF TEN IN PAC WAS COMPLETELY CRACKED ON BOTH SIDES ON ATTACHEMENT BOLT HOLE SO THAT A PIECE OF THE D ISC WAS BROKEN AWAY. THE REMAINDER OF THE DISCS WERE CORRODED ON BOTH SIDES OF THE DISC IN THE SAME AREA CLOSEST TO THE BOLT HOLE. 1 G 7 1 3U 3 U H2SW E1GL 20080603 GL 2008 6 3 CA080303005 2 20080302 G 7322 23034702 FUEL CONTROL BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 2936 AFTER INSTALLING THE FCU, IT WAS NOTED THAT FUEL WAS LEAKING FROM LOWER THROTTLE ARM HOUSING. FCU WAS REMOVED. (TC NR 2 0080303005) 1 G 7 1 3U 3 U H2SW E4CE 20090102 CE 2009 1 2 CA080303006 1 20080303 G 3411 STATIC PORT BEECH 23 B23 1151240 CE LYC O360 O360A2G 41514 EA SNSNCH 76E M76EMMS EA RT OBSTRUCTED W K NONE O OTHER IN INSP/MAINT 1 CA 2312 2312 (CAN) WHILE DOING A PRE-PURCHASE INSP, DISCOVERED A PIECE OF TAPE COVERING THE RT STATIC PORT. 1 L 7 1 3O 3 O RT A1CE E286 5 N P4EA4 20081104 SW 2008 11 4 CA080303008 1 20080229 G 6520 476400751 GEARBOX BELL 47 47G2 1181008 SW LYC O435 VO435A1D 41516 EA TAIL ROTOR MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA 3110 948 (CAN) UPON WALK AROUND OIL IN GEARBOX LOOKED DIRTY, OIL WAS DRAINED AND METAL WAS FOUND ON MAGNETIC PLUG, TAIL ROTOR GEA RBOX WAS REMOVED FROM SERVICE AND OH ONE INSTALLED AND ACFT WAS RELEASED. MORE INFO WILL BE POSTED AS THE GEARBOX IS DIS ASSEMBLED. 1 G 7 1 3O 3 O H1 E279 20080521 EA 2008 5 21 CA080303009 2 20080301 G 8550 77517 SUMP FOUND FBA FBA2C1 3640103 EA LYC O540 IO540L1A5 41532 EA HARTZL HCC3Y HCC3YR GL ENGINE OIL SYS UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 1100 (CAN) OIL SUMP WAS REMOVED TO INSPECT SUMP BAFFLE IAW SB. INTERNAL CRACK IN THE SUMP WAS FOUND NEAR ONE OF THE MOUNTING LUGS. IAW THE SB, THE OIL SUMP BAFFLE HAD A LACK OF CLEARANCE AND HAD BEEN RUBBING THE BOTTOM OF THE SUMP. BAFFLE, AND SUMP HAD SIGNS OF WEAR. BAFFLE WAS LOOSE, AND HAD (2) BROKEN CONTACT POINTS. ENGINE REMOVED TO FURTHER DETERMINE CONTAM INATION AND SERVICEABILITY. (TC NR 20080303009) 1 H 7 1 3O 3 O NC A7EA 1E4 5 C P25EA 200805141 20080514 1 2008 5 14 CA080304001 4 20080204 G 3418 543036B29 COMPUTER CNDAIR CL600 CL600* 1900302 EA GE CF34 CF343A2 30067 NE STALL WARNING FAULTY W O OTHER W INADEQUATE Q C NR NOT REPORTED 1 CA (CAN) IT TOOK (3) STALL WARNING COMPUTER BEFORE GETTING ONE THAT WAS SERVICEABLE , THEY ALL FAIL THE TEST IAW TEST PROCE DURE MM PSP601-2 CHAP 27-39-00 P 206 207 NB MFG PRODUCTS (TC NR 20080304001). 2 L 7 2 4F 4 F RT A21EA E15NE 20080602 NM 2008 6 2 CA080304003 1 20080229 G 2497 IN3311B DIODE BOEING 737 737522 138449F NM CFMINT CFM56 CFM563C1 13802 EU OPEN W O OTHER P NO WARNING INDICATION CR CRUISE 1 CA EN ROUTE, AFTER SHUTTING OFF CENTER TANK BOOST PUMPS, LEFT CENTER, LEFT AFT AND RIGHT FORWARD LOW PRESSURE LIGHTS DID NO T ILLUMINATE. WINDOW HEAT LIGHTS FOR THE LEFT SIDE WINDOW AND RIGHT FORWARD WINDOW WERE NOT ILLUMINATED. INITIALLY NO MASTER CAUTION, THEN ANTI-ICE MASTER CAUTION. THERE WAS NO LE DEVICES INDICATION. ON DOWNWIND FOR LANDING, THE PRESSUR IZATION WENT FROM AUTO TO STANDBY AND DUMPED PRESSURE. UPON LOWERING GEAR, NO GREEN LIGHTS. THE CREW OVERSHOT AND USED THE GEAR VIEWERS AND A FLY BY TO DETERMINE THE GEAR STATUS. AFTER SPEAKING WITH DISPATCH, THE LIGHTS WERE CYCLED THROU GH BRIGHT/DIM/TEST AND THE GEAR INDICATION RETURNED. THE AIRCRAFT WAS LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE WAS 2 L 7 2 4F 4 F RT A16WE E21EU 20080602 2008 6 2 CA080304004 4 20080303 G 3416 5035PP41 ENCODER ALTIMETER DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA WHEN RECEIVED FOUND WITH TIN BETWEEN CASE AND PIN ON CONNECTION RECEPTACLE. 20080602 EU 2008 6 2 CA080304005 1 20080227 G 2910 A3248021101100 LINE AIRBUS 310 A310304 3930339 EU GE CF6 CF680C GL HYD SYSTEM SPLIT W K NONE K FLUID LOSS IN INSP/MAINT 1 CA WHILE AIRCRAFT WAS UNDER MAINTENANCE IN THE HANGAR, THE HYDRAULIC RETURN LINE FOR YELLOW SYSTEM ALTERNATE BRAKE FAILED W ITH A SPLIT IN THE TUBING APPROX 1.5 INCHES IN LENGTH. AT THE TIME OF THE FAILURE THERE WAS NO HYDRAULIC PRESSURE OR OP ERATION OF THE SYSTEM. THE LINE WAS REPLACED AND SYSTEM TESTED SERVICEABLE. LINE WAS SENT TO AIRBUS FOR ANALYSIS. (TC NR 20080304005) 2 L 7 2 4F 4 F RT A35EU E23EA 20080602 2008 6 2 CA080304006 1 20080304 G 8011 STARTER ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA AFTER INSTALLATION TEST FOR FUNCTIONAL START, THE ENGINE LIGHT STAY ON IN THE COCKPIT. FOUND BY OUR TECHNICIAN THAT THE RECEPTACLE PLUG ON THE STARTER PIN B GROUNDED ALL THE TIME. (TC NR 20080304006) 20080521 EA 2008 5 21 CA080304007 2 20080205 G 8500 ENGINE PIPER PA31 PA31310 7103103 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A SCHEDULED INSP, LARGE QUANTITIES OF FERROUS PARTICLES WERE DISCOVERED IN THE PAPER ELEMENT OF THE ENGINE OIL FILTER. LARGER PIECES WERE ALSO DISCOVERED IN THE OIL SUCTION SCREEN FINGER. THE AC IS GROUNDED PENDING REPLACEMENT OF THE AFFECTED ENGINE. ANALYSIS OF THE FILTER ELEMENT REVEALED FINES AND FLAKES OF CARBON STEEL AMS NR 6440 OR 6444 WHI CH INDICATES CAMSHAFT AND FOLLOWERS, ALTHOUGH THIS IS NOT AS YET SUBSTANTIATED. THE ENGINE HAS BEEN OPERATED FOR 88.1 HO URS SINCE OVERHAUL FOR AN IDENTICAL FAULT WHERE THE NR 5 CAM LOBE WAS FOUND WORN BEYOND LIMITS. THE ENGINE IS CURRENTLY EN ROUTE FROM INDIA TO THE ORIGINAL ENGINE OVERHAUL SHOP FOR PRECISE FAULT IDENTIFICATION. (TC NR 20080304007) 1 L 7 1 3O 3 O RT A20SO E14EA 5 C P33EA 20080521 WP 2008 5 21 CA080304009 2 20080303 G 7321 8978017 FUEL CONTROL SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCB3T HCB3TN5 GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 3518 (CAN) ENGINE HAD BEEN REMOVED IN RUNNING CONDITION FOR SCHEDULED HOT SECTION/GEARBOX INSP. ENG SENT TO ENGINE SHOP. UPON INITIAL START UP FOR THE TEST CELL RUN, THE ENGINE WOULD NOT START. FUEL CAME OUT THE DRAINS AND THE BACK OF THE ENGINE . THE FUEL PUMP PRESSURE WAS TESTED AND WITHIN LIMITS. THE FUEL CONTROL WAS REMOVED AND THE DRIVE SHAFT TURNED WITH NO R ESISTANCE, LIKE SOMETHING HAD FAILED INSIDE. THIS FUEL CONTROL IS POST AD 2006-15-08 COMPLIANT AND THE FIRST FAILURE OF THIS TYPE SEEN BY THE OPERATOR OR THE ENGINE SHOP ON ONE OF THESE PN. UNIT TBO IS 7000 HOURS NORMALLY. UNIT HAS BEEN SE NT FOR REPAIR AND A TEARDOWN REPORT REQUESTED. (TC NR 20080304009) 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 20080521 EA 2008 5 21 CA080304010 1 20080303 G 3230 533407 SELECTOR VALVE CNDAIR CL600 CL6002C10 1390015 EA GE CF700 CF7002D2 30010 NE MLG FAILED W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA (CAN) DISC LANDING GEAR WOULD NOT EXTEND. PERFORMED MANUAL/EMERGENCY EXTENTION. ENG HYDR PUMP PRESSURE WAS NORMAL. REMO VED AND REPLACED LANDING GEAR SELECTOR VALVE IAW AMM 32-32-10. ADDITIONAL INFORMATION: ATTEMPTED TO EXTEND GEAR 3 TIMES BUT FAILED. DID GET A LG DISAGREE WARNING. HAD TO DO A GO AROUND TO GET GEARDOWN. (TC NR 20080304010) 2 L 7 2 4F 4 F RT A21EA E7EA 20080521 CE 2008 5 21 CA080304011 1 20080118 G 3233 99101399 ACTUATOR CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL NLG FAILED W O OTHER Z SIGNIFICANT FAILURE REPORT LD LANDING 1 CA (CAN) AIRCRAFT INDICATED (3 GREEN) ON APPROACH, UPON LANDING, NOSE GEAR RETRACTED RESULTING IN AC DAMAGE. UPON ARRIVAL, MAINT NOTED GEAR INDICATION REMAINED (3 GREEN) AND AC WAS SITTING ON ITS NOSE. THE AC WAS RAISED AND THE NOSE GEAR WAS P ULLED INTO THE DOWN AND LOCKED POSITION. INITIAL INSP OF THE GEAR SYS FOUND ALL TO BE IN WORKING ORDER, GEAR SWINGS PERF ORMED NORMALLY. THE ACTUATOR`S INTEGRAL POSITION INDICATION SWITCH MALFUNCTIONED CAUSING THE HYD SYS PRESSURE TO THE NOS E GEAR ACTUATOR TO STOP PREMATURELY BEFORE THE NOSE GEAR WAS FULLY EXTENDED AND IN THE OVER CENTER POSITION. (TC NR 2008 0304011) 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 20081104 WP 2008 11 4 CA080304012 1 20080302 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 289 (CAN) STARTER - COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BRE AKING OFF) RENDERING THE STARTER U/S AND LEAVING THE MACHINE UNABLE TO START. COLD WEATHER MAY BE A FACTOR OR SIMPLY THE CASTING IN THE ATTACHED FLANGE IS TOO WEAK. 1 G 7 1 3O 3 O H11NM 1E4 20081104 WP 2008 11 4 CA080304013 1 20080228 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 14 (CAN) STARTER -COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BREA KING OFF) RENDERING THE STARTER U/S AND LEAVING THE MACHINE UNABLE TO START. COLD WEATHER MAY BE A FACTOR OR SIMPLY THE CASTING IN THE ATTACHED FLANGE IS TOO WEAK. (TC NR 20080304013) 1 G 7 1 3O 3 O H11NM 1E4 20081104 WP 2008 11 4 CA080304014 1 20080217 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 62 (CAN) STARTER - COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BRE AKING OFF) RENDERING THE STARTER U/S AND LEAVING THE MACHINE UNABLE TO START. COLD WEATHER MAY BE A FACTOR OR SIMPLY THE CASTING IN THE ATTACHED FLANGE IS TOO WEAK. (TC NR 20080304014) 1 G 7 1 3O 3 O H11NM 1E4 20080602 GL 2008 6 2 CA080305001 2 20080303 G 7261 PRESSURE SWITCH AIRBUS 310 A310304 3930339 EU GE CF6 CF680C GL ENGINE OIL MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 47993 1630 DURING CLIMB AT 18000 FEET, NR 1 ENGINE OIL FILTER CLOGGED LIGHT CAME ON. AS PER QRH, NR 1 ENGINE WAS SHUT DOWN. AIRCR AFT RETURNED TO STATION WITH NO FURTHER PROBLEM. THE OIL FILTER WAS REPLACED. NO SIGNIFICANT CONTAMINATION WAS NOTICED . THE OIL SYSTEM WAS DRAINED AND SERVICED AS PER MM. THE OIL DIFFERENTIAL PRESSURE SWITCH WAS REPLACED. A TEST FLIGHT WAS PERFORMED AND THE ENGINE OIL INDICATION SYSTEM WAS NORMAL. AIRCRAFT WAS RETURN TO SERVICE. 2 L 7 2 4F 4 F RT A35EU E23EA 20080521 CE 2008 5 21 CA080305002 1 20080303 G 2121 C4140070102 COOLING FAN CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL COCKPIT NOISY W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA (CAN) ON CLIMBOUT FLIGHT CREW HEARD A LOUD SQUEALING NOISE FROM THE AVIONICS COOLING FAN. IN COLD TEMPERATURES THIS IS T YPICAL OF THE COOLING FAN AND THE FLIGHT CREW DECIDED TO ALLOW THE FAN TO WARM UP. AFTER A COUPLE MINUTES THE FLIGHT CRE W DECIDED TO RETURN. APPROX 5 MINUTES LATER DURING VECTORS BACK THE FLIGHT CREW BEGAN TO SMELL A BURNED SMELL IN THE COC KPIT AND PULLED THE AVIONICS FAN CIRCUIT BREAKER, THE SMELL STOPPED. AT THE TIME, THE FLIGHT CREW ALSO COMMENTED ON SMOK E LIGHT, SMOKE IN THE COCKPIT. THE FLIGHT WAS CONTINUED AND LANDED WITHOUT FURTHER INCIDENT. MAINT REPLACED THE AVIONICS COOLING FAN AND GROUND RUN THE AC WITHOUT ANY ADDITIONAL FAULTS. THE AC WAS RELEASED. (TC NR 20080305002) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20081104 NE 2008 11 4 CA080305003 2 20080228 G 7200 PIN SKRSKY S92 S92A NE GE CT7TS CT78A 30136 NE ENGINE FOD W O OTHER C R F.O.D. PARTIAL RPM/PWR LOSS CR CRUISE 1 CA (CAN) ON RETURN FLIGHT AN EPAC (POWER CHECK) WAS ATTEMPTED BUT WOULD NOT COMPLETE (A USUAL CASE IN PARTICULAR ACFT) NRS WERE NOTED FOR MAINT STAFF AND ON RETURNING TO BASE ANOTHER EPAC WAS RUN AND COMPLETED. MAINT STAFF WAS NOTIFIED UPON AR RIVAL AT AIRPORT AND DAMAGE IN ENGINE PARTICLE SEPARATOR WAS NOTICED. SMALL HANDLE. PIN FROM HINGE ASSY FOUND TO HAVE BE COME DETACHED FROM ASSY AND ENTERED THE ENGINE INTAKE RESULTING IN FOD DAMAGE TO ENGINE. 2 G 7 2 4U 4 U R00024BO E8NE 200805141 20080514 1 NM 2008 5 14 CA080305004 1 20080221 G 3810 14C3308 COUPLER BOEING 737 7378Q8 13844BX NM CFMINT CFM56 CFM567B26US NE POTABLE WATER CRACKED W B G EMER. DESCENT O2 MASK DEPLOYED Z S SIGNIFICANT FAILURE REPORT AFFECT SYSTEMS CR CRUISE 1 CA (CAN) DURING CRUISE, CREW NOTED CABIN ALTITUDE WARNING. UNABLE TO CLOSE OUTFLOW VALVE EITHER ELECTRICALLY OR MANUALLY. E MERGENCY DESCENT PERFORMED, OXYGEN MASKS DROPPED. OUTFLOW VALVE WOULD CLOSE TO THE .2500 POSITION ON GAUGE. ATTEMPTED TO CLOSE VALVE MANUALLY AT 10000FT (OAT +13 DEG C), NO RESPONSE. VALVE CLOSED SUCCESSFULLY AFTER 10 MIN. ON INSP FOUND POR TABLE WATER LEAKING AT FITTING AND FITTING PARTLY SEPARATED WITH WIGGENS COUPLING OPEN. UPON INSP OF REMOVED COUPLING FO UND CRACKED. (TC NR 20080305004) 2 L 7 2 4F 4 F RT A16WE E00055EN 20080521 EU 2008 5 21 CA080305008 1 20080225 G 2421 ALU8521R ALTERNATOR ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA MUHBR MTV MTV9* EU FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 1034 (CAN) PILOT EXPERIENCED A COMPLETE ELECTRICAL FAILURE. SUBSEQUENT INVESTIGATION REVEALED A MELTED INSULATOR ON THE (BATT ) TERMINAL OF THE ALTERNATOR. THE (BATT) WIRE TERMINAL END WAS MELTED AND BROKEN WITH THE FREE END CONTACTING THE ALTERN ATOR CASE. THE FREE WIRE ENABLED A RAPID DISCHARGE OF THE BATTERY. (TC NR 20080305008) 1 L 7 1 3O 3 O 0 A76EU 1E10 5 C P24NE 20080521 SO 2008 5 21 CA080305011 1 20080305 G 2140 CD21252 SWITCH PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2B NE HARTZL HCE3Y HCE3YR2A GL HEATER INTERMITTENT W O OTHER O OTHER CR CRUISE 1 CA 31 (CAN) THE PILOT REPORTED THAT THE HEATER DID NOT WORK. MAINT INVESTIGATED AND DETERMINED THAT THE CYCLING SWITCH WAS DEF ECTIVE AND REPLACED THE SWITCH. THE CREW AGAIN REPORTED THAT THE HEATER DID NOT WORK PROPERLY. MAINT DID MORE TROUBLESHO OTING AND DETERMINED THAT THE CYCLING SWITCH FUNCTIONED PROPERLY INSIDE A HEATED HANGAR. HOWEVER WHEN LEFT OUTSIDE AT AB OUT -20 DEGREES CELSIUS THE SECOND SWITCH ALSO FAILED TO FUNCTION PROPERLY. THE HEATER WAS INSTALLED NEW ABOUT 218 HRS A GO AND THE FIRST CYCLING SWITCH FAILED AFTER 188.3 HRS. (TC NR 20080305011) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20080521 NE 2008 5 21 CA080305012 2 20080219 G 7320 EEC CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE ENGINE MALFUNCTIONED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA (CAN) DURING TAKEOFF ROLL, THE ENGINE ELECTRONIC CONTROL DROPPED OFF LINE. THE CREW ADVANCED THE THRUST LEVER TO ACHIEVE REQUIRED THRUST, BUT THE POWER LEVEL REMAINED 10 PERCENT LESS THAN THE REQUIRED LEVEL.THE FLIGHT WAS ABORTED AND THE AI RCRAFT RETURNED TO THE GATE. TROUBLESHOOTING IS ONGOING. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT C AUSE ONCE ESTABLISHED (TC NR 20080305012) 2 L 7 2 4F 4 F RT A22CE E00059EN 20080521 NE 2008 5 21 CA080305013 2 20080219 G 7200 ENGINE CESSNA 500 550 2076604 CE PWA 530 PW530A NE FLAMED OUT W D RETURN TO BLOCK X J ENGINE FLAMEOUT WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) WHILE DEICING THE AC AND PERFORMING SYSTEMS CHECKS, THE ENGINE FLAMED OUT WHEN BROUGHT TO IDLE POWER. THE ENGINE F LAMED OUT (2) ADDITIONAL TIMES UNDER SIMILAR CIRCUMSTANCES DURING TROUBLESHOOTING. ATTENTION IS FOCUSING ON THE FUEL CON TROL AND AIRFRAME RIGGING. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080305013) 1 L 7 2 4F 4 F A22CE E00053EN 200805141 20080514 1 NE 2008 5 14 CA080305016 2 20080301 G 7200 ENGINE PWC PW545B CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE POWER LOSS W E ENGINE SHUTDOWN R F J PARTIAL RPM/PWR LOSS FLT CONT AFFECTED WARNING INDICATION DE DESCENT 1 CA (CAN) DESCENDING THROUGH FL370, THE ENGINE ELECTRONIC CONTROL REVERTED TO MANUAL AND ENGINE N2 SPEED REDUCED TO 41 PERCE NT ASSOCIATED WITH VIBRATION. THE ENGINE DID NOT RESPOND TO THRUST LEVER INPUT AND THE CREW ELECTED TO SHUTDOWN THE ENGI NE. TROUBLESHOOTING IS ONGOING. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080305016) 2 L 7 2 4F 4 F RT A22CE E00059EN 20081104 WP 2008 11 4 CA080305017 1 20080220 G 6710 369A7304 BRACKET HUGHES 369 369A 4470503 WP ALLSN 250C 250C20B 03013 GL ROTOR CONTROL UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON REMOVAL OF DUAL CONTROLS, A GENERAL INSPECTION OF THE UNDERSEAT AREA REVEALED A CRACK ON THE BEARING CAP OF THE BRACKET ASSEMBLY WHICH IS USED TRANSFERING CONTROL INPUTS FROM CABIN BACK TO THE ROTORS. THE PART WAS REPLACED WITH NO INCIDENT. 1 G 7 1 3U 3 U H3WE E4CE 20080521 EU 2008 5 21 CA080306002 1 20080304 G 2910 HTE400005 VALVE BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33110UG 01514 WP ROTOL R333 R333482F12 GL HYD SYSTEM FAILED W O OTHER K FLUID LOSS CR CRUISE 1 CA (CAN) THE RT NON RETURN VALVE ASSEMBLY DOWNSTREAM OF THE RT HYDRAULIC PUMP FAILED. NON RETURN VALVE ASSEMBLY IS A UNIT T HAT IS SWAGED TOGETHER. THE SWAGE LET GO, ALLOWING HYDRAULIC FLUID TO VENT OVERBOARD. THIS VALVE IS INSTALLED TO PREVENT PRESSURE FROM EITHER ENGINE DRIVEN PUMP GOING TO THE OPPOSITE PUMP IN THE EVENT OF A PUMP FAILURE OR ENGINE SHUTDOWN. T IME AND CYCLES ON PART ARE UNKNOWN BUT IT IS VERY LIKELY ORIGINAL EQUIPMENT. (TC NR 20080306002) 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C P61GL 20081104 2008 11 4 CA080313002 4 20080312 G 3197 CONNECTOR SNIAS 350 AS350BA 8680817 EU INSTRUMENT LIGHT BURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) DURING THE FLIGHT THE PILOT SELECTED THE INSTRUMENT LIGHTS ON. FIVE MIN LATER THE LIGHTS BEGAN TO CYCLE ON AND OFF . THE PILOT TOUCHED THE CONNECTOR AND ELECTRICAL FLAME CAME FROM THE CONNECTOR. THERE WAS A BURNING ODOR BUT NO VISIBLE SMOKE. THE PILOT SHUT THE LIGHTS DOWN AND CONTINUED THE FLIGHT. THE PROBLEM COULD NOT BE REPRODUCED ON THE GROUND, BUT T HE UNIT IS UNSERVICABLE. (TC NR 20080313002) 1 G 7 1 3U NC H9EU 20080602 EU 2008 6 2 CA080313004 2 20080311 G 7200 ENGINE BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU NR 2 MALFUNCTIONED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION AP APPROACH 1 CA DURING APPROACH IN ICING CONDITIONS AND HEAVY PRECIPITATION, WHEN THE PILOT THROTTLED BACK, ENGINE NR 2 FLAMED OUT AND A UTO FEATHERED. THE PILOT DID NOT ATTEMPT TO RE-LIGHT AND LANDED WITH ONE ENGINE OPERATING. MAINTENANCE CHECKED THE OIL S CREEN, FUEL SCREEN AND FUEL TANK SUMPS. NO CONTAMINATION WAS FOUND. MAINTENANCE CONDUCTED HIGH AND LOW POWER ENGINE RUNS AS WELL AS AUTO-FEATHER CHECKS AND FOUND NO PROBLEM WITH THE ENGINE. ROLLS-ROYCE NOTICE TO OPERATES NO. 1142 IS DIRECT ED TO THE FLIGHT CREWS TO "SWITCH ON THE ENGINE IGNITION SWITCHES WHEN MODERATE OR SEVERE ICING IS ENCOUNTERED". THE PIL OT DID NOT HAVE THE ENGINE IGNITION SWITCHES SELECTED TO "ON" DURING THIS EVENT. THE PILOTS HAVE BEEN REMINDED OF THIS 2 L 7 2 3T 4 T A24EU A196 6 C P899 20080521 EA 2008 5 21 CA080314001 1 20080206 G 5610 NP1393225 WINDOW CNDAIR CL600 CL6002B19 1900309 EA COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 7038 (CAN) FLT NR 3874 DISCREPANCY: (CAPT`S SIDE WINDOW FWD UPPER CORNER, MIDDLE PANE CRACKED DURING APPROACH) REQUESTED TH E PN/SN, TSN/CSN INFORMATION. UPDATE 2/6: REPLACED THE WINDOW. (TC NR 20080314001) 2 L 7 2 4F RT A21EA 200805141 20080514 1 NE 2008 5 14 CA080314002 2 20080313 G 7200 CF343B1 ENGINE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE NR 2 FIRE W A F B UNSCHED LANDING ACTIVATE FIRE EXT. EMER. DESCENT B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 CA (CAN) AC LANDED, AFTER THE PILOT HAD DECLARED AN EMERGENCY FURTHER TO A FIRE ON ENG NR 2. THE AC FLEW IN CRUISE AT FL 22 0, WHEN THE PILOT GOT A FIRE ALARM ON ENG 2. THE TEMP (ITT) OF ENGINE SHOWED CLEARLY THAT AN ACTUAL FIRE HAD BROKEN OUT. PILOT DECLARED AN EMERGENCY, APPLIED THE FIRE DRILL, ACTIONED THE FIRE PROTECTION SYS (BOTH BOTTLES) AND WENT IN AN EME RGENCY DESCEND TOWARDS AIRPORT. DURING DESCEND, THE TEMP OF ENG NR 2 STAYED AT A HIGHER LEVEL (760 DEGREE C) THAN ENG NR 1 (600 DEGREE C). THE AC LANDED SAFELY, ATC PERSONNEL WITNESSED A SLIGHT BLACK SMOKE COMING FROM THE ENGINE. THE FIRE B RIGADE WENT INTO ACTION AND USED FIRE EXTINGUISHING AGENT, BUT DID NOT REPORT HAVING ACTUALLY SEEN FLAMES. (TC NR 200803 2 L 7 2 4F 4 F RT A21EA E15NE 20080521 NM 2008 5 21 CA080314003 1 20080307 G 5320 19093649001 BRACKET EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE FUSELAGE CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 3018 3018 (CAN) EXCERPT FROM MESSAGE RECEIVED FROM MAINT ON THAT FINDING: NOTE THE CRACK RUNNING FROM THE HIGHLOCK. FOUND WHILE T /S ON SNAG L4438921. THIS IS THE MAIN SUPPORT FOR THE LOWER END OF THE CONTROL QUADRANT IN THE LT WHEEL WELL THE FLANGE IS SUPPORTING THE BULHEAD THAT CONCERNS FLEXING AND CONTACTING THE LOWER FWD SECTION OF THE CONTROL QUADRANT. MFG INFOR MED OF THE FINDING, REPAIR SUGGESTED TO FLEET ENGINEERING. MORE INFO TO BE PROVIDED. (TC NR 20080314003) 2 L 7 2 4F 4 F RT A57NM E00070EN 20081104 SW 2008 11 4 CA080314004 1 20080306 G 2510 STCSH0631 INERTIA REEL BELL BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE COCKPIT SEAT BINDING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CO-PILOT SEAT SHOULDER HARNESS INERTIAL REEL CABLE FOUND BINDING AGAINST VERTICAL REFERENCE SEAT KIT - PLATE ASSY P/N AAL-292-031-001. FOUND TO BE COMMON PROBLEM WHEN CHECKED ON OTHER ACFT. WILL CONTACT MFG. 1 G 7 1 4U 4 U H4SW E22EA 20080521 EU 2008 5 21 CA080314005 1 20080311 G 3244 542K694 TIRE AIRBUS A330 A330* EU RROYCE RB211 RB211* 54555 NE MLG FAILED W A UNSCHED LANDING O OTHER LD LANDING 1 CA (CAN)THE AC BLEW THE NR (4) MAIN TIRE ON DEPARTURE. THE FLIGHT CREW ELECTEDTO DIVERT, AND ULTIMATELY LANDED APPROXIMATEL Y 15000 KGS OVER THE MAXIMUM STRUCTURAL LANDING WEIGHT OF 185000KGS. DURING TAXI, THE NR (3), RT FWD IB MAIN TIRE DEFLA TED AND THE AC WAS SUBSEQUENTLY SERVICED BY MAINT, BEFORE BEING ABLE TO POSITION TO THE GATE. INVESTIGATION IS ONGOING. SDR WILL BE UPDATED ACCORDINGLY. (TC NR 20080314005) 2 L 7 2 4F 4 F RT A46NM A12EU 20080521 NM 2008 5 21 CA080314006 1 20080312 G 2150 78279018 ACM DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 33905 23037 (CAN) WHILE CARRYING OUT WORK CARD TO REMOVE COMPONENT IT WAS DISCOVERED THERE WAS A 6 INCH CRACK ON THE INNER SIDE OF T HE CHAMBER. (TC NR 20080314006) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080603 GL 2008 6 3 CA080314007 2 20080312 G 7261 ENGINE EMB 135 EMB135ER 3260203 SO ALLSN AE300 AE3007A GL LEAKING W A UNSCHED LANDING K M Y FLUID LOSS OVER TEMP ENGINE STOPPAGE CR CRUISE 1 CA OIL IMPENDING BYPASS INDICATION ILLUMINATED ALONG WITH OIL TEMPERATURE RISING TO 141 DEGREES. THE PILOT COMMANDED THE S HUT DOWN OF THE ENGINE DUE TO OIL TEMPERATURE AND QUANTITY INDICATING THREE QUARTS. AIRCRAFT RETURNED TO CMH WITHOUT IN CIDENT. MAGNETIC INDICATING PLUGS WERE FOUND CLEAN. A SMALL PUDDLE OF OIL IN FAN SECTION AND A LOT OF OIL IN THE EXHAU ST WAS REPORTED. THE OIL FILTER WAS FILLED WITH CARBON DEBRIS. ENGINE HAS ACCUMULATED 0.8 HOURS SINCE LAST REPAIR AND THIS WAS THE 1ST FLIGHT SINCE REPAIRS. ENGINE UNDER INVESTIGATION, FURTHER REPORT WILL BE SUBMITTED AFTER ENGINE TEARDO WN. (TC NR 20080314007) 2 L 7 2 4F 4 F RT T00011AT TE6CH 20080603 NE 2008 6 3 CA080314008 2 20080313 G 7200 ENGINE AIRBUS A319 A319114 3930350 NM GE CFM56 CFM565A 13802 NE FAILED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CL CLIMB 1 CA 30804 14183 DURING CLIMB A LOUD BANG AND VIBRATION WAS FELT, FOLLOWED BY ENG 2 FAIL ON ECAM AT 8300 FT AND CLIMBING. LANDED SAFELY WITH NO ISSUE WITH LANDING. AFTER LANDING DEBRIS WAS FOUND IN ENGINE EXHAUST AND AFT CENTER BODY WAS DAMAGED. INVESTIG ATION INTO CAUSE OF ENGINE FAILURE IS ON GOING AND SDR WILL UPDATED ACCORDINGLY. ENGINE HAS BEEN CHANGED. (TC NR 200803 14008) 2 L 7 2 4F 4 F RT A28NM E29NE 20080603 GL 2008 6 3 CA080314009 2 20080310 G 7230 BEARING EMB 145 EMB145LR 3260212 SO ALLSN AE300 AE3007A GL NR 4 FAILED W K NONE B M SMOKE/FUMES/ODORS/SPARKS OVER TEMP IN INSP/MAINT 1 CA ENGINE REMOVED FOR ITT EXCEEDANCE, AUTO IFSD, SMOKE IN COCKPIT/CABIN, OIL DEBRIS ON ALL CHIP DETECTORS. TEARDOWN OF ENG INE REVEAL NR 4 BEARING FAILURE AND ALSO NR 3 BEARING FAILURE. EXCESSIVE DAMAGE IN COMPRESSOR AREA DUE TO BOTH SUPPORTI NG BEARING FAILURE. FAILED COMPONENTS WILL BE SENT TO THE OEM FOR INVESTIGATION. (TC NR 20080314009) 2 L 7 2 4T 4 F RT T00011AT TE6CH 20081219 CE 2008 12 19 CA080314010 1 20080306 G 3245 G195X6758 TUBE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL TIRE FLAT W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) TIRE WENT FLAT SITTING IN HANGAR. CRACK FOUND IN TUBE AT BASE OF VALVE STEM. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20080603 CE 2008 6 3 CA080314011 1 20080306 G 8011 200SGL119Q2 BRUSHES CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL STARTER FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1181 SLOW SPOOLING OVER ENGINE, ENGINE STARTER BRUSHES WORN OUT (TC NR 20080314011) 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20081104 NE 2008 11 4 CA080314012 1 20080310 G 7921 84300207 THERMOSTAT SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL OIL COOLER STUCK W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMPERATURE INCREASED TO RED LINE. (TC NR 20080314012) 1 G 7 2 3U 3 U H1NE E1GL 20080521 SO 2008 5 21 CA080314013 2 20080307 G 8500 TSIO520EB ENGINE CESSNA 401 401 207590C CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C* GL MAKING METAL W E ENGINE SHUTDOWN O OTHER AP APPROACH 1 CA 714 (CAN) ON FINAL APPROACH INTO AIRPORT THE RT ENGINE MANIFOLD PRESSURE STARTED CHANGING. THE PILOT THEN NOTICED THAT THE R T OIL PRESSURE HAD DROPPED TO THE RED LINE. THE RT PROP WAS FEATHERED AND THE ENGINE WAS SHUTDOWN. SMALL BITS OF METAL W ERE FOUND UNDER THE OIL PRESSURE RELIEF VALVE. THE ENGINE WAS REMOVED AND SENT FOR WARRANTY. (TC NR 20080314013) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 20081105 SW 2008 11 5 CA080314014 1 20080307 G 3246 205050400063 CROSSTUBE BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE MLG BROKEN W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) HELICOPTER WORKING HELI-SKIING. THE PASSENGERS WERE LOADING INTO THE HELICOPTER. ALMOST ALL THE SEATS WERE OCCUPIE D WHEN A SUDDEN SETTLING WITH A METALLIC NOISE ON THE REAR OF THE MACHINE OCCURRED. IT WAS NOTED THAT THE REAR CROSS TUB E WAS CRACKED ALL THE WAY AROUND OR BROKEN UNDERNEATH THE RIGHT HAND CROSS TUBE SADDLE. (ABOUT 1" INSIDE THE SADDLE AREA ) 1 G 7 1 4U 4 U H4SW E22EA 20081104 WP 2008 11 4 CA080314015 1 20080313 G 6320 369D2512311 GEAR HUGHES 369 369 4470702 WP ALLSN 250C 250C20 03013 GL M/R TRANSMISSION BROKEN W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 616 (CAN) ACFT WAS BROUGHT IN WITH XMSN NOISE AND CHIP LIGHT. XMSN WAS OPENED AND A PIECE OF GEAR TOOTH 7/8 OF AN INCH LONG WAS FOUND MISSING. THIS IS THE SECOND OCCURENCE OF THIS TYPE THAT WE HAVE ENCOUNTERED. THE LAST SDR WAS APRIL OF 2005. ( TC NR 20080314015) 1 G 7 1 3U 3 U H3WE E4CE 200805141 20080514 1 EU 2008 5 14 CA080314016 1 20080309 G 2751 A275704050400 SWITCH AIRBUS 310 A310300 3930305 EU GE CF6 CF680C2* GL KRUEGER FLAP CONTAMINATED W D RETURN TO BLOCK N FALSE WARNING CL CLIMB 1 CA (CAN) DURING CLIMB, ECAM WARNING "FLAP KRUEGER NOT RETRACTED LIGHT" CAME ON. FLIGHT RETURNED TO THE STATION. SFCC INDICA TED FAULT COMING FROM THE LT KRUEGER RETRACT SWITCH. MAINT FOUND THE SWITCH BACK SHELL CONTAMINATED WITH WATER. CONNECT OR AND SWITCH CLEANED OUT AND SYS TESTED SERVICEABLE. AC DEPARTED AND SAME SNAG REOCCURRED DURING CLIMB. THE AC RETURNE D TO THE STATION AND WAS REMOVED FROM SERVICE FOR TROUBLESHOOTING. DURING INSP, FOUND SLIGHT DAMAGE ON WIRE, 2 INCHES FR OM CONNECTOR. WIRE PROTECTION CARRIED OUT IAW ESPM 20-53-00 AND SWITCH ASSY REPLACED. SYS TESTED SERVICEABLE. AC WAS RET URN TO SERVICE WITH NO REOCCURRENCE. (TC NR 20080314016) 2 L 7 2 4F 4 F RT A35EU E23EA 20080521 EA 2008 5 21 CA080314017 1 20080306 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS MALFUNCTIONED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) FLAP FAIL MESSAGE SHORT FINAL WHEN CREW WERE SELECTING FROM FLAP 8 TO FLAP 20 POSITION, FLAPS REMAINED AT 8 DEGREE S AND LANDED NORMAL. MAINT REPORTED THAT THE LIST OF FAULTS IN MDC ARE : 1- JAM 2- FECU 3- L MOTOR BRAKE THE FAULT COD ES WERE RETRIEVED FROM THE FECU AND POINT TOWARDS POWER LOSS DUE TO THE SDS LT SKEW DETECTOR FLAGGED. MAINT RESET THE SD U AND FECU. RAN THE FLAPS UP AND DOWN 2 TIMES. THEN THE SDU FLAGGED THE LT SKEW DETECTOR AGAIN. DUMMY BOX INSTALLED, SYS TEM TESTED AND IT WAS CONFIRMED THE SKEW DETECTION IS AT FAULT. MAINT HAS CONFIRMED THAT THE SDU FECU POWER 1 AND 2 LIGH TS FLAGGED, AND THE LT OB PANEL SKEW L4 AND L3 LIGHTS FLAGGED. SKEW DETECT SYS BOUND AT FAULT. SKEW DETECT SYS DEACTIVAT 2 L 7 2 4F 4 F RT A21EA E15NE 20080521 EU 2008 5 21 CA080314018 1 20080307 G 3250 5325012004 BEARING PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NLG STEERING UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 8888 (CAN) FORK BEARING ON NOSE LANDING GEAR STEERING FOUND TWISTED. THIS DEFECT WAS FOUND ON NOSE LANDING GEAR SHOCK ABSORBE R REPAIR AND SERVICE. (TC NR 20080314018) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20080521 GL 2008 5 21 CA080314019 2 20080304 G 7250 6871505 BEARING HILLER UH12 UH12E 4360122 WP ALLSN 250C 250C20 03013 GL NR 5 FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 169 (CAN) CHIP LIGHTS METAL CONTAMINATION ENGINE SHOP DETERMINED NR 5 BEARING FAILURE. (TC NR 20080314019) 1 G 7 1 3O 3 U 4H11 E4CE 20080603 NE 2008 6 3 CA080314021 2 20080209 G 7200 ENGINE SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE MAKING METAL W O OTHER E J VIBRATION/BUFFET WARNING INDICATION TX TAXI/GRND HDL 1 CA 4581 1456 ON THE FIRST GROUND RUN OF THE DAY DURING GROUND WARM UP, A NOISE WAS EMITTED FROM THE ENGINE AND IMMEDIATLEY AFTER NOIS E WAS HEARD THE ENGINE CHIP LIGHT ILLUMINATED. PILOT SHUT ENGINE DOWN. METAL PARTICLES WERE FOUND ON MOS CHIP PLUG AND SOME ON THE ELECTRIC CHIP PLUG. ENGINE WAS REMOVED AND SENT TO TURBOMECA MONTREAL FOR INSPECTION AND REPAIR. WE WERE L UCKY THIS DID NOT HAPPEN IN THE AIR AS WE WOULD BE LOOKING AT A TOTAL ENGINE FAILURE. (TC NR 20080314021) 1 G 7 1 3U 3 U H9EU E00054EN 20080521 SO 2008 5 21 CA080314022 1 20080309 G 2400 W23X1A1G40 CIRCUIT BREAKER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL COCKPIT OPEN W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) CIRCUIT BREAKER FOUND IN OPEN CIRCUIT AND ALSO FOUND ONE FAULTY WIRE WHICH WAS REPLACED. (TC NR 20080314022) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 200805141 20080514 1 EU 2008 5 14 CA080317003 1 20080311 G 2435 COOLING FAN 160SG140Q UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE STARTER GEN SEPARATED W E ENGINE SHUTDOWN O OTHER TX TAXI/GRND HDL 1 CA 128 (CAN) DURING THE ENGINE START SEQUENCE, AN UNUSUAL NOISE WAS HEARD BY THE PIC. THE NOISE WAS MOMENTARY AND OCCURRED SEVE RAL SECONDS AFTER STARTER GENERATOR ENGAGEMENT AND JUST PRIOR TO ENGINE LIGHT OFF. ENGINE PARAMETERS REMAINED NORMAL SO THE START SEQUENCE WAS COMPLETED. AFTER ENGINE STABILIZATION THE ENGINE WAS SHUTDOWN FOR INVESTIGATION AND THE FLIGHT W AS CANCELLED. MAINT WERE ABLE TO DUPLICATE THE NOISE BY ENGAGING THE STARTER FOR SEVERAL SECONDS. THE STARTER GENERATOR WAS REMOVED TO THE BENCH AND THE COVER WAS REMOVED. IT WAS NOTED IMMEDIATELY THAT THE COOLING FAN HAD BECOME SEPARATED FROM THE ARMATURE SHAFT AND WAS ABLE TO SPIN FREELY. BY QUICKLY SPINNING THE FAN AROUND THE SHAFT, THE NOISE HEARD DURIN 1 G 7 2 3U 3 U NC R0001RD E34NE 20080521 2008 5 21 CA080317004 4 20080214 G 8300 GEAR PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO HARTZL HCC2Y BHCC2YF2 GL ACCESSORY G/B FAILED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) LOW OIL PRESSURE LIGHT CAME ON IMMEDIATELY AFTER TAKEOFF. PWR WAS BROUGHT BACK AND AC RETURNED FOR SAFE LANDING. ENGINE WAS SHUTDOWN OFF RUNWAY, PROP FEATHERED AUTOMATICALLY. BOTH SUCTION SCREEN AS WELL AS OIL FILTER INSPECTED, NO ME TAL CONTAMINANTS FOUND. PROP DID NOT TURN FREELY. ALTERNATOR PULLED OFF ON THE BACK OF THE ENGINE. GEAR FOUND LYING LOOS E IN ACCESSORY CASE WITH MULTIPLE BROKEN TEETH ON OTHER GEARS. (TC NR 20080317004) 1 L 7 2 3O 3 O A7SO E9CE 5 C P920 20080521 EA 2008 5 21 CA080317005 2 20080304 G 8520 PISTON PIN CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL NR 1 CYLINDER WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ALUMINUM FOUND IN OIL FILTER DURING 100 HOUR INSP. CYLINDER BOROSCOPED, SUSPECT CYLINDER REMOVED, FWD PISTON PIN F OUND WORN ON NR 1 CYLINDER. (TC NR 20080317005) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 20081222 EA 2008 12 22 CA080317006 2 20080222 G 8530 CYLINDER CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE WORN W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) ALUMINUM FOUND IN OIL FILTER DURING 100 HR INSP. CYLINDER BOROSCOPED, SUSPECT CYLINDER REMOVED, FWD PISTON PIN FOU ND WORN ON NR 1 CYLINDER. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 20081222 CE 2008 12 22 CA080317009 1 20080302 G 2720 04115261 RUDDER BAR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 11625 (CAN) PILOT NOTED LT PILOTS RUDDER PEDAL WAS NOT IN IT`S CORRECT POSITION. THE RUDDER BAR WHICH IS A WELDMENT WAS FOUND TO BE CRACKED AT THE ATTACHMENT POST FOR THE LT RUDDER PEDAL. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 20081230 CE 2008 12 30 CA080318001 1 20080306 G 7160 BRACKET CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA CARB HEAT DETACHED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) DURING ROUTINE INSP TECH NOTICED NO CARB HEAT DROP ON IN-COMING RUN-UP. TECH DISCOVERED THAT ONE OF THE 2 CARB AIR BOX BUTTERFLY VALVE BRACKETS HAD BECOME DETACHED FROM SHAFT AND VALVE WAS NOT OPENING OR CLOSING PROPERLY. 1 H 7 1 3O 3 O NT 3A12 E274 20080603 EA 2008 6 3 CA080318002 2 20080226 G 8530 STUD CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA CYLINDER BROKEN W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA 3495 DURING WALK AROUND, PILOT NOTICED ENGINE OIL COVERING LT SIDE OF FUSELAGE AND EMPENNAGE. MAINTENANCE INSPECTED ENGINE A ND FOUND ON NR 2 CYLINDER, ONE BROKEN THROUGH STUD. OIL WAS RUNNING DOWN THROUGH STUD AND EXITING CYLINDER BASE WHERE A TTACH NUT USED TO BE. OIL LEAK WAS NOT DISCOVERED DURING OR AFTER PREVIOUS NIGHT FLIGHT. (TC NR 20080318002) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P9045 20080521 EA 2008 5 21 CA080318008 2 20080317 G 7310 252429710 SERVO PIPER PA28 PA28R180 7102809 SO LYC O360 IO360B1E 41514 EA HARTZL HCC2Y HCC2YK1 GL FUEL SYSTEM MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 193 (CAN) CHECKED IAW EMERGENCY AWD 2008-06-51. FOUND, DID NOT APPLY BY DATE BUT WHEN VISUALLY INSPECTED FOUND SAME PROBLEM AS REPORTED IN AWD. O/H DATE WAS JANUARY 28, 2005. AWD STATED AUGUST 22, 2006. ALL SERVOS MAY NEED TO BE CHECKED. (TC NR 20080318008) 1 L 7 1 3O 3 O 2A13 1E10 5 C P920 20080602 WP 2008 6 2 CA080319003 2 20080311 G 7313 31038294 NOZZLE GARRTT TPE331 TPE33111U 01514 WP FUEL DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 1791 THE A/C CAME INTO THE HANGER FOR A ROUTINE FUEL NOZZLE AND BOROSCOPE INSPECTION. DURING THE BOROSCOPE INSPECTION OUR NI GHT MAINTENANCE FOUND SOME DISCREPANCIES IN THE ENGINE. FURTHER INSPECTION FROM THE TURBINE SHOP IT WAS NOTED THAT THE NOZZLE SEGMENTS THAT MAKE UP THE NR 1 STATOR ASSEMBLY HAD SOME DAMAGE TO THEM. THE NOZZLE SEGMENTS WERE OVERHAULED FROM SOUTHWEST TURBINE. THE ENGINE WAS REPLACED AND FORWARDED TO THE ENGINE SHOP FOR FURTHER REPAIR. (TC NR 20080319003) 4 T E4WE 20080603 NM 2008 6 3 CA080319004 1 20080307 G 5310 19093649001 SUPPORT EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE MLG WW CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3018 3018 ON AIRCRAFT A CRACK WAS FOUND TO MLG WELL BULKHEAD SUPPORT. THE CRACK STARTS AROUND ONE OF THE ATTACHMENT HOLES AND GOE S UP TO THE MIDDLE OF DISTANCE BETWEEN THE TWO ATTACHMENT HOLES. THE BULKHEAD IS ALSO FLEXING AND CONTACTING THE LOWER SECTOR OF THE AILERON CONTROL QUADRANT. PROBLEM ALSO FOUND ON THE FOLLOWING A/C FIN NUMBER: 307, 309, 311, 313, 315, 31 7, 318, 319, 320, 322, 323, 324, 326, 332 (TC NR 20080319004) 2 L 7 2 4F 4 F RT A57NM E00070EN 20080602 2008 6 2 CA080319005 1 20080319 G 8011 EBB131A DRIVE SYSTEM STARTER SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA 97 STARTER RECEIVED DUE TO DRIVE ASSEMBLY FAILURE. ENGINE COULD NOT BE STARTED BECAUSE DRIVE WOULD NOT ENGAGE. WHEN INSPE CTED THE DRIVE COULD NOT BE TURNED OUT OR SPUN BY HAND TO EXTEND THE GEAR SECTION OF THE DRIVE. STARTER WAS RETURNED TO KELLY AEROSPACE FOR WARRANTY REPLACEMENT. (TC NR 20080319005) 20080602 SW 2008 6 2 CA080319007 1 20080306 G 3260 EN516 SWITCH SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE331* 01514 WP MCAULY 4HFR34 4HFR34C652 NE LT MLG INTERMITTENT W L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 CA ON APPROACH, THE CREW NOTICED THAT THE LT GEAR HAD NO "GREEN" SAFE LIGHT. FLY BY WAS CARRIED OUT CONFIRMED GEAR DOWN. AIRCRAFT LANDED WITHOUT INCIDENT. SWITCH WAS FOUND STICKY. SWITCH REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20 080319007) 2 L 7 2 4T 3 T RT A8SW E2WE 6 C 3PNE 20080602 NE 2008 6 2 CA080319008 2 20080306 G 7200 ENGINE PAC CRESCO CRESCO CE PWA PT6 PT6A34AG 52053 NE POWER LOSS W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA DURING TAKEOFF ROLL, A NOISE WAS HEARD ACCOMPANIED BY LOSS OF ENGINE POWER. THE TAKEOFF WAS ABORTED. INITIAL INSPECTIO N REVEALED FRAGMENTS SIMILAR TO COMPRESSOR BLADE MATERIAL DISTRIBUTED THROUGHOUT THE INLET. TEARS IN THE INLET SCREEN W ERE NOTED. THE ENGINE HAS BEEN REMOVED AND WILL BE INVESTIGATE ROOT CAUSE ONCE ESTABLISHED. 1 L 7 1 4T 4 T NT EXPA1L71 E4EA 20080602 EA 2008 6 2 CA080320002 1 20080318 G 2797 MS27473T20B4 CONNECTOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE FLUTTER DAMPER DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA 19157 TASK NR 27-34-05-710-801 WAS BEING PERFORMED ON THE ELEVATOR FLUTTER DAMPERS. IT FAILED THIS TASK FOR LOW FLUID LEVEL T RANSMITTER SWITCHES. THIS TASK WAS CALLED UP DURING THE AIRCRAFT`S PLANNED HEAVY INSPECTION. T HERE WERE NO REPORTED FA ILURES WHILE THE AIRCRAFT WAS IN-SERVICE PRIOR TO THIS HEAVY MAINTENANCE VISIT. DURING THE COURSE OF TROUBLE SHOOTING, THE AME FOUND THE CONNECTORS P300 AND J300 CORRODED TO THE EXTENT THAT THE PINS M AND N BROKE OFF WHEN THEY WERE DISCONN ECTED. SEVERAL OTHER PINS WERE ALSO FOUND DISCOLORED. CONNECTOR P/N MS27497T20B41S, BACKSHELL P/N HEX41-AB90-21A9-1, C ONNECTOR P/N MS27473T20B41P AND BACKSHELL P/N HEX41-AB00-21A9-1 WERE REPLACED AND SYSTEM FUNCTION CHECKED "SERVICEABLE". 2 L 7 2 4F 4 F RT A21EA E15NE 20080602 SW 2008 6 2 CA080320003 1 20080312 G 5230 2724050083 FRAME SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP CARGO DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 43129 DURING AN AGING AIRCRAFT INSPECTION A CRACK WAS DETECTED VISUALLY EXTENDING FROM THE LOWER AFT LATCH (POSITION 8). WHEN THE DOOR WAS REMOVED FOR REPAIR FURTHER CRACKS WERE DISCOVERED TO THE ATTACHING STRUCTURE FOR BOTH LOWER LATCHES (POSIT IONS 7 AND 8). THIS FAILURE IS BELIEVED TO BE THE RESULT OF FATIGUE, AND IF REMAINED UNDETECTED COULD EVENTUALLY RESULT IN FAILURE OF THE CARGO DOOR. IT SHOULD ALSO BE NOTED THAT AD 98-06-25 REQUIRES AN INSPECTION OF THE LATCHING SYSTEM. (TC NR 20080320003) 2 L 7 2 4T 4 T RT A8SW E4WE 20080602 CE 2008 6 2 CA080320004 1 20080314 G 5320 365533 GASKET CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA SERVO PLUG LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 1861 SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRM OTIVE REPRESENTATIVE. ENGINE REMANUFACTURE DATE OF JULY 14, 2004 DOES NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFE CTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC NR 20080320004) 1 H 7 1 3O 3 O NT 3A12 1E10 20080602 EA 2008 6 2 CA080320005 2 20080314 G 7321 365533 GASKET PRECISIONWND CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FCU LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 1745 AD2008-06-51 FUEL INJECTION SERVO PLUGS, SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE.ENGINE REMANUFACTURE DATE OF SEPT. 8, 2005 DOES NOT FALL W ITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. RIGHT M AGNETO P-LEAD WIRE BROKEN. (TC NR 20080320005) 1 H 7 1 3O 3 O NT 3A12 1E10 20080602 EA 2008 6 2 CA080320006 2 20080314 G 7321 365533 GASKET PRECISIONWND CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FCU LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 1367 SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMO TIVE REPRESENTATIVE. ENGINE REMANUFACTURE DATE OF AUG 18, 2005 AND THE FUEL SERVO WAS REPAIRED JULY 28, 2006 AND BOTH D O NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LO OSE. (TC NR 20080320006) 1 H 7 1 3O 3 O NT 3A12 1E10 20080602 EA 2008 6 2 CA080320007 2 20080314 G 7321 365533 GASKET PRECISIONWND CESSNA 182 182T 2072703 CE LYC O540 IO540AB1A5 EA MCAULY 3D36C B3D36C431 GL FCU LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 293 AD2008-06-51 FUEL INJECTION SERVO PLUGS, SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE. ENGINE REMANUFACTURE DATE OF SEPT 8, 2004 DOES NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC N R 20080320007) 1 H 7 1 3O 3 O NT 3A13 1E4 5 C 20080602 CE 2008 6 2 CA080320010 1 20080307 G 2750 S16612 SWITCH CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA TE FLAPS BROKEN W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 CA INTERNAL RETURN SPRING OF SWITCH BROKEN. TOGGLE NOT RETURNING TO NEUTRAL POSITION. SWITCH REPLACED WITH NEW. (TC NR 20 080320010) 1 H 7 1 3O 3 O NT 3A12 E274 20081105 EU 2008 11 5 CA080320011 1 20080320 G 6230 350A37118322 LOCK SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACKED MAIN ROTOR MAST LOCK. 1 G 7 1 3U 3 U NC H9EU E19EU 20081105 WP 2008 11 5 CA080320012 1 20080312 G 6310 C1883 CROSS TIE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE SPRAG CLUTCH CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 911 (CAN) DURING A IN-HOUSE 1000 HR CLUTCH INSPECTION THE SPRAG CLUTCH CAGE CROSSBAR WAS FOUND CRACKED. NEW PARTS WERE INSTA LLED. 1 G 7 1 3O 3 O H11NM 1E4 20080602 CE 2008 6 2 CA080320013 1 20080319 G 3245 891250 TUBE CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE TIRE FAILED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 626 ON TAXI PILOT FELT AIRCRAFT PULLING TO ONE SIDE AND DISCOVERED FLAT TIRE. TIRE WAS CHANGED AND FLOWN BACK TO BASE. TIR E ASSY WAS DISASSEMBLED AND TUBE WAS FOUND BLOWN WITH ABOUT A FOUR INCH SPLIT IN IT. THE TUBE WAS ALSO FUSED TO THE INS IDE OF THE TIRE IN THE AREA OF THE BALANCE PATCH. THIS WAS THE ORIGINAL TIRE INSTALLED AT CESSNA FACTORY WHEN AIRCRAFT WAS DELIVERED. I AM REPORTING THIS DUE TO AN ABNORMAL NUMBER OF TUBES THAT WE HAVE HAD LET GO IN THE LAST MONTH. TALKI NG TO OTHER OPERATORS HAS INDICATED THAT OTHERS ARE HAVING THE SAME PROBLEM. I HAVE BEEN TOLD BY A TIRE COMPANY THAT TH E BUTYL RUBBER TUBES ARE NOT WORKING WELL IN OUR COLDER CLIMATE. (TC NR 20080320013) 1 H 7 1 3T 3 T NT A37CE E4EA 20080521 2008 5 21 CA080324001 1 20080324 G 3245 600X6 TUBE TIRE DEFECTIVE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BELIEVE TO HAVE ENCOUNTERED A DEFECTIVE TIRE TUBE BATCH. THE TUBES IN QUESTION ARE MFG 6.00 X 6, SOLD UNDER BATCH NR 032358. WE HAVE HAD 5 INSTANCES OF TIRE TUBE FAILURE OUT OF 6, WITH THE CONCERNED TUBE BATCH. (TC NR 20080324001) 20080521 CE 2008 5 21 CA080325006 1 20080312 G 5312 12127071 BULKHEAD CESSNA 206 U206E 2073350 CE CONT O520 IO520F 17032 SO HARTZL HCC3Y HCC3YF1 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BULKHEAD CRACK 1.25 IN LONG AT RT SIDE FROM LIGHTNING HOLE. NEAR STAB ATTACH POINT. (TC NR 20080325006) 1 H 7 1 3O 3 O A4CE E5CE 5 C P25EA 20080521 NM 2008 5 21 CA080325008 1 20080325 G 5315 654681163 FLOORBEAM BOEING 737 737490 1384715 NM BS 986 RBL43 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLOORBEAM FOUND CORRODED DURING VISUAL INSP AND REPAIRED WITH REPAIR PART IAW EA AND SRM. (TC NR 20080325008) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080325009 1 20080325 G 5315 654681179 FLOORBEAM BOEING 737 737490 1384715 NM BS 986 RBL 35-40 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLOORBEAM CAP AT BS 986.5, RBL 35 AND 40 FOUND CORRODED DURING VISUAL INSPECTION AND REPAIRED WITH REPAIR PART IAW CUSTOMER EA AND SRM. (TC NR 20080325009) 2 L 7 2 4F RT A16WE 20080521 NM 2008 5 21 CA080325010 1 20080325 G 5315 654681179 FLOORBEAM BOEING 737 737490 1384715 NM BS 986 RBL 27 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLOORBEAM AT BS 98605, RBL 27, WL 207.5 CORRODED UNDERSIDE UNDER CLIP NUT. REPAIRED WITH REPAIR PART IAW CUSTOMER EA AND SRM. (TC NR 20080325010) 2 L 7 2 4F RT A16WE 20080521 2008 5 21 CA080325011 1 20080325 G 2410 ALV9510R ROTOR ALTERNATOR MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN INSTALLING DRIVE HUB, THE CUSTOMER NOTICED COTTER PIN COULD NOT BE INSERTED WITH NUT TORQUED AND NUT ALIGNED WITH COTTER PIN HOLE LOCATION. WHEN INSPECTED IN-HOUSE THE COTTER PIN HOLES WERE FOUND DRILLED TOO FAR DOWN THE SHAFT. A LSO THE O-RING BETWEEN THE SPACER AND WASHER UNDER THE DRIVE HUB WAS FOUND TO BE TOO BIG TO ALLOW THE WASHER TO SEAT AGA INST THE SPACER. HAS INFORMED US THAT THEY HAD SOME ROTORS LEAVE THEIR FACILITY WITH THIS ISSUE AND THE ALTERNATOR WAS RETURNED TO THEM FOR WARRANTY PURPOSES. (TC NR 20080325011) 20080521 GL 2008 5 21 CA080325013 2 20080320 G 7250 23038136 SHAFT ALLSN 250C 250C47B GL TURBINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3823 (CAN) ENGINE NOISE WAS NOTED AT GROUND IDLE. THE NOISE WAS REDUCED WHEN IN HOVER BUT CONSISTENTLY APPEARED DURING SPOOL DOWN TO GROUND IDLE. THE ENGINE WAS REMOVED AND RETURNED TO THE OVERHAULER FOR REPAIR. THE NOISE WAS CONFIRMED DURING AN ENGINE TEST WITH VIBRATION MEASUREMENTS. ENGINE DISMANTLE AND INSP ON THE 26TH OF FEBRUARY 2008 REVEALED A CRACKED POWE R TURBINE SHAFT. THE CRACK LOOSENED THE FIT AT THE TURBINE 4TH WHEEL CURVIC COUPLING AND CAUSED FRETTING AND THE LOSS OF A COUPLING TOOTH. PT OUTER SHAFT P/N 23038136, S/N KU95766 AND 4TH TURBINE WHEEL RETURNED TO MFG FOR INVESTIGATION. ( TC NR 20080325013) 3 U E1GL 20081105 WP 2008 11 5 CA080325015 1 20080304 G 5100 UNKNOWN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE UNKNOWN W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) UPON TAKE OFF AND AT A SPEED OF 30 KTS AND 10-15FT ALTITUDE (AGL), ACFT YAWED RT WITH ENGINE BACKFIRE AND DECELERA TION AND IMMEDIATE LOW ROTOR HORN. THE PILOT DROPPED THE COLLECTIVE & CONDUCTED EMERGENCY RUN-ON LANDING IN A FIELD SOUT H OF THE HANGAR. UPON SAFE LANDING, THE ENGINE WAS STILL RUNNING AND ACCELERATING AND ROTOR RPM WAS AT 90% AND RISING. A FTER MATCHING THE ENGINE AND ROTOR RPM NEEDLES, THE ACFT WAS LIFTED IN A HOVER AND HOVER TAXIED BACK TO THE HANGAR. NO MECHANICAL PROBLEMS WERE FOUND. THE ACFT WAS GROUND RUN AND HOVERED FOR 30 MINS AT VARIOUS POWER SETTINGS WITH NO FURTHE R INCIDENT. AT THE TIME OF THIS INCIDENT, THIS ACFT HAD THE DART COLD WEATHER BAFFLES INSTALLED. WE HAVE IMPLEMENTED A 1 G 7 1 3O 3 O H11NM 1E4 20081105 SW 2008 11 5 CA080326001 1 20080325 G 8097 WIRE BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE STARTER CHAFED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA (CAN) DURING START UP THE STARTER RELAY CIRCUIT BREAKER WAS POPPING NOT ALLOWING THE STARTER TO START. IT WAS FOUND THA T THERE WERE 2 WIRES LABELED K2D20 AND K3C20 CHAFFED INSIDE THE CO-PILOTS COLLECTIVE. K3C20 HAD BEEN SOLDER SPLICED AND CHAFED AT THE SPLICE AND K2D20 WAS CHAFFED THROUGH THE WIRE. 1 G 7 1 4U 4 U H1SW E17EA 20080521 SW 2008 5 21 CA080326002 1 20080324 G 7810 3101582 EXHAUST DUCT SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCB3T HCB3TN5 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN THE ENG WAS UNDERGOING A PHASE 6 INSP, A CRACK APPROX 3 INCH LONG WAS DISCOVERED IN THE ENGINE EXHAUST DUCT N EAR THE EGT PROBE BOSSES. IT APPEARED TO BE ON A PREVIOUS WELD. REMOVED AND REPLACED THE DUCT. (TC NR 20080326002) 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 20080521 CE 2008 5 21 CA080326003 1 20080324 G 2161 COUPLING CESSNA 650 650 2076802 CE GARRTT TPE731 TFE7313C WP TEMP CONTROL MISINSTALLED W O OTHER O OTHER CR CRUISE 1 CA (CAN) CREW WROTE UP, CABIN PAC STUCK ON FULL COLD. TROUBLESHOOTING CARRIED OUT AND FOUND THAT THE COUPLING FOR CABIN TEM P CONTROL HAD DISCONNECTED FROM THE ENVIROMENTAL CONTROL UNIT. BOTH CLAMPS AND THE COUPLING WERE INTACT HOWEVER THE COUP LING HAD BEEN INSTALLED INCORRECTLY. COUPLING WAS REINSTALLED AND LEAK CHECKED SERVICEABLE. (TC NR 20080326003) 2 L 7 2 4F 4 F A9NM E6WE 20081105 WP 2008 11 5 CA080326004 1 20080304 G 2435 ARMATURE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE STARTER GEN DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 543 (CAN) HOLES MELTED THROUGH ARMATURE CASE IN STARTER. 1 G 7 1 3O 3 O H11NM 1E4 20081105 WP 2008 11 5 CA080327005 1 20080317 G 2435 GEAR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE STARTER GEN DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 27 (CAN) STARTER AND RING GEAR TEETH FOUND DAMAGED DURING A DI 1 G 7 1 3O 3 O H11NM 1E4 20081105 WP 2008 11 5 CA080327006 1 20080304 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INTERMITTENT W O OTHER O OTHER NR NOT REPORTED 1 CA 203 (CAN) STARTER INTERMITTENT 1 G 7 1 3O 3 O H11NM 1E4 20081105 WP 2008 11 5 CA080327007 1 20080307 G 6520 C0211 GEARBOX ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE TAIL ROTOR LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 4 (CAN) TAILROTOR GEARBOX FOUND LEAKING FROM THE INPUT SEAL DURING DI 1 G 7 1 3O 3 O H11NM 1E4 20080521 NE 2008 5 21 CA080328001 2 20080320 G 7250 310703301 BEARING RACE PWA PW120 PW123 NE NR 15 MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA 11000 (CAN) EIR PW100 2008-025, METAL CONTAMINATION OF THE RGB OIL SYS. (TC NR 20080328001) 4 T E20NE 20080603 NE 2008 6 3 CA080328002 2 20080309 G 8530 399353 CYLINDER HEAD DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE NR 2 SEPARATED W A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 5 HEAD SEPERATED FROM NR 2 CYLINDER AFTER 4.9 HRS AIRTIME. CYLINDER HEAD SEPARATION OCCURRED DURING CRUISE FLIGHT. UNEVE NTFUL LANDING CARRIED OUT. REPLACEMENT CYLINDER HEAD INSTALLED AND AIRCRAFT COMPLETED ITS MISSION. (TC NR 20080328002) 1 H 7 1 3R 3 R RC A806 5E1 20080603 CE 2008 6 3 CA080328003 1 20080319 G 5514 12326231 BRACKET CESSNA 210 210J 2073439 CE CONT O520 IO520J 17032 SO HORIZONTAL STAB CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 3218 DURING THE ANNUAL INSPECTION REINFORCEMENT BRACKET (P/N 12 32623-1) WAS FOUND TO HAVE A CRACK RUNNING FROM THE BOTTOM BO LT HOLE TO THE EDGE OF THE BRACKET. THE BRACKET IS ATTACHED TO THE REAR SPAR OF THE LT HORIZ STABILIZER. AFFECTED PART REPLACED. (TC NR 20080328003) 1 H 7 1 3O 3 O 3A21 E5CE 20080603 CE 2008 6 3 CA080328004 1 20080319 G 5312 12120031 DOUBLER CESSNA 210 210J 2073439 CE CONT O520 IO520J 17032 SO BULKHEAD CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 3218 DURING THE ANNUAL INSPECTION A CRACK WAS DETECTED RUNNING FROM THE ANCHOR NUT RIVET HOLE TO THE EDGE OF THE DOUBLER PLAT E, THIS BRACKET IS ATTACHED TO THE REAR FRAME AT STN 209, P/N 12120402-3. AFFECTED PART REPLACED. (TC NR 20080328004) 1 H 7 1 3O 3 O 3A21 E5CE 20080603 2008 6 3 CA080328005 2 20080328 G 7414 10357586 DISTRIBUTOR GEAR MAGNETO WORN W K NONE O OTHER IN INSP/MAINT 1 CA 2000 MAG WAS RECEIVED TIME EXPIRED FOR OVERHAUL. WHEN DISASSEMBLED THE WASHER THAT RETAINS THE NYLON GEAR ON THE SHAFT WAS F OUND LOOSE AND HAD ALMOST WORN TO THE POINT THAT IT COULD HAVE COME OFF THE END OF THE SHAFT AND RUBBED AGAINST THE COIL TAB OR CARBON BRUSH. THIS CONDITION HAS BEEN NOTICED IN MANY OTHER MAGS AND IN CONVERSATION WITH TCM WE HAVE BEEN TOLD TO PUT THE GEAR IN A PRESS AND FLARE THE END OF THE SHAFT OVER MORE TO RETAIN THE WASHER IF IT IS FOUND LOOSE. THE WAS HER IN THIS CASE WAS WORN AND THIS PROCEDURE COULD NOT BE ACCOMPLISHED. THE DATE CODE (BATCH CODE) ON THE GEAR WAS `94` . THE GEAR WAS REPLACED DURING THE OVERHAUL AND THE MAG WAS RETURNED TO SERVICE. (TC NR 20080328005) 20080603 2008 6 3 CA080328006 2 20080328 G 7414 10357586 DISTRIBUTOR GEAR MAGNETO WORN W K NONE O OTHER IN INSP/MAINT 1 CA 2000 MAG WAS RECEIVED TIME EXPIRED FOR OVERHAUL. WHEN DISASSEMBLED THE WASHER THAT RETAINS THE NYLON GEAR ON THE SHAFT WAS F OUND LOOSE AND HAD ALMOST WORN TO THE POINT THAT IT COULD HAVE COME OFF THE END OF THE SHAFT AND RUBBED AGAINST THE COIL TAB OR CARBON BRUSH. THIS CONDITION HAS BEEN NOTICED ON MANY OTHER MAGS AND IN CONVERSATION WITH TCM WE HAVE BEEN TOLD TO PUT THE GEAR IN A PRESS AND FLARE THE END OF THE SHAFT OVER MORE TO RETAIN THE WASHER IF IT IS FOUND LOOSE. THE WAS HER IN THIS CASE WAS WORN AND THIS PROCEDURE COULD NOT BE ACCOMPLISHED. THE DATE CODE (BATCH CODE) ON THE GEAR WAS `94` . THE GEAR WAS REPLACED DURING THE OVERHAUL AND THE MAG WAS RETURNED TO SERVICE. (TC NR 20080328006) 20080603 CE 2008 6 3 CA080328007 1 20080327 G 5280 150450018 ARM CESSNA 401 401B 207590E CE CONT O520 TSIO520EB 17040 SO MLG DOOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA DURING PILOT WALKAROUND THE RT MAIN GEAR DOOR WAS HANGING SLIGHTLY DOWN FROM RETRACTED POSITION. MAINTENANCE TO REPLACE PART. (TC NR 20080328007) 1 L 7 2 3O 3 O A7CE E8CE 20081105 WP 2008 11 5 CA080328008 1 20080308 G 2410 BRUSHES KELLY ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ALTERNATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 847 (CAN) DURING A POST FLIGHT DI THE ALTERNATOR BELT WAS FOUND DAMAGED. CARRIED OUT AN INSPECTION OF THE ALTERNATOR AND FOU ND THE BRUSHES AND SLIP RINGS WORN. 1 G 7 1 3O 3 O H11NM 1E4 20080521 EA 2008 5 21 CA080328010 1 20080327 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAP FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 29317 29317 (CAN) ON APPROACH WHEN MAKING INITIAL FLAP SELECTION CREW RECEIVED FLAP FAULT MESSAGE, FLAPS FAILED TO OPERATE. CREW PER FORMED FLAP (0) LANDING. CREW ADVISE OAT WAS -57 TO -59 FOR ABOUT AN HOUR AT FLIGHT LEVEL 260 PRIOR TO COMMENCING DESCEN T. ON GROUND FLAPS POSITIONED TO 8 DEG AND AC FERRIED WITH FLAPS AT 8 DEG TO MAINT BASE FOR CORRECTIVE ACTION. FLAP FAUL T CODE INDICATED FLAP JAM. MAINT FOLLOWING COMPANY POLICY IS REPLACING ALL FLAP ACTUATORS, CLEANING AND LUBRICATING ALL FLAP DRIVES, NO OBVIOUS ABNORMALITIES NOTED. (TIMES PROVIDED ARE AC TT AS NO SPECIFIC COMPONENT IDENTIFIED AS TO CAUSE ) (TC NR 20080328010) 2 L 7 2 4F 4 F RT A21EA E15NE 20080521 NM 2008 5 21 CA080328011 1 20080328 G 7500 DUCT BOEING 727 727200 138407E NM PWA JT8 JT8D9A 52048 NE BLEED AIR LEAKING W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) AFTER TAKEOFF OUT, NR 2 ENGINE FIRE WARNING CAME ON. THE THROTTLES WERE RETARDED AND THE WARNING EXTINGUISHED. THE AC RETURNED TO AIRPORT. AFTER INVESTIGATION, MAINTENANCE FOUND THE DUCT FOR THE FUEL HEAT VALVE HAD COME OUT OF ITS SL EEVE CAUSING A DUCT LEAK. THE DUCT WAS REPAIRED AND LEAK CHECKED SERVICEABLE. (TC NR 20080328011) 2 L 7 3 4F 4 F RT A3WE E2EA 20080521 EA 2008 5 21 CA080331001 1 20080317 G 5711 21531062212 FRAME CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE FS 434.80 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2531 2531 (CAN) WHILE PERFORMING AD CF-1997-07R2, NDT INSP OF FRONT AND REAR SPAR WING TO FUSELAGE FRAME ANGLES A CRACK WAS DETECT ED ON THE REAR LT OB ANGLE. THE CRACK ORIGINATED AT THE TOP HI-LOK AND WAS HEADED UP ABOUT .1250 TH OF AN INCH. IT COULD NOT BE DETECTED BY THE NAKED EYE. THE AD WAS ACTUALLY DUE AT A/F TIME 2573.4 AND WATER DROPS 9726. WE PERFORMED IT DU RING WINTER MAINT AT A/F 2530.8 AND 9521 WATER DROPS. APPROVED REPAIRS WILL BE CARRIED OUT AND THE AC RELEASED FOR SERV ICE. (TC NR 20080331001) 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 20080521 CE 2008 5 21 CA080331002 1 20080312 G 2510 505530401 CABLE ASSY CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL SEAT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSTALLATION OF SERVICE KIT SK210-175 - SECONDARY SEAT STOP, IT WAS FOUND THAT THE THREADS ON THE HOUSING F OR THE ADJUSTMENT CABLE WERE CRACKED. (TC NR 20080331002) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20080521 EA 2008 5 21 CA080331003 1 20080317 G 5711 2151003268 SPAR CAP CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2531 2531 (CAN) WHILE PERFORM AD CF-1992-26R1, ULTRA SONIC INSPECTION OF THE WING REAR SPAR CAP, CRACKS WERE INDICATED ON BOTH REA R SPAR CAPS. VISUAL INSPECTIONS WERE CARRIED OUT AND CRACKS DISCOVERED ON BOTH SPAR CAPS AT WS 51.00 FS 434.80. THIS A D WAS DUE AT A/F TIME 2651.3 AND WATER DROPS 9820. WE CARRIED IT OUT DURING WINTER MAINT AT A/F TIME 2530.8 AND WATER DR OPS 9521. THE AC MFG WAS CONTACTED AND APPROVED DRAWINGS SENT SHOWING REPAIRS. (TC NR 20080331003) 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 20081105 NE 2008 11 5 CA080331004 2 20080319 G 7314 C8187B PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE AUX FUEL NOISY W K NONE O OTHER IN INSP/MAINT 1 CA 860 (CAN) AUX FUEL PUMP HAD EXCESSIVE NOISE THE PUMP WAS REPLACED. (TC NR 20080331004) 1 G 7 1 3O 3 O H11NM 1E4 20080521 EA 2008 5 21 CA080331006 1 20080328 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 25226 25226 (CAN) FLAP FAILED ON APPROACH , LT FLAP INDICATING 3 DEG , RT INDICATING 4 DEG PARTIAL FLAP LANDING CARRIED OUT. MAINT ACTIONS : ALL 8 FLAP ACTUATORS REPLACED IAW COMPANY FLAP FAIL POLICY. (TC NR 20080331006) 2 L 7 2 4F 4 F RT A21EA E15NE 20080521 NM 2008 5 21 CA080331007 1 20080327 G 5753 17039312001 FLAP TRACK EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE TE FLAPS GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA 3862 (CAN) UPON INSP OF THE IB FLAP TRACK RAILS, GOUGES ARE EVIDENT ON THE UPPER INNER SURFACE FACE AND ON THE UPPER SIDE FAC E THAT ARE OUT OF LIMITS. SEE ALSO SDR 20080318006 FOR DETAILS. RAIL AFT, RAIL, RAIL MAIN 1, RAIL MAIN 2 OUT PN: 170- 39320-001, 170-39060-01, 170-39310-001, 170-39312-001 DUE TO NO ALLOWABLE REWORK LIMITS AVAILABLE IN THE SRM (STRUCTURA L REPAIR MANUAL) , ALL C/A CARRIED OUT IAW MFG INSTRUCTION. REF: IC2007-17005998C, IC2008-17002015A, IC2008-17002163. ( TC NR 20080331007) 2 L 7 2 4F 4 F RT A56NM E00063EN 20080521 EU 2008 5 21 CA080331008 1 20080325 G 3600 B-NUT PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL CRACKED FAILED W O OTHER O OTHER CL CLIMB 1 CA 7625 (CAN) FOLLOWING AN ANNUAL INSP AND A SATCOM AVIONICS UPGRADE IN THE INITIAL CLIMB PHASE OF A TEST FLIGHT , CABIN PRESSUR E WAS INCREASING AT A MAXIMUM RATE. ECS WAS PROMTPLY SHUTDOWN ,CABIN DUMPED, AC LEVELED OFF AND RETURNED TO AIRPORT FOR LANDING. THE SENSE LINE FROM THE CONTROLLER TO THE AUXILLARY VOLUME TANK WAS FOUND TO HAVE A CRACKED B-NUT. UPON A SLIGH T TUG , NUT SEPARATED COMPLETLY AND LINE COULD BE PULLED COMPLETLY FROM FITTING. A NEW LINE WAS INSTALLED , SUBSEQUENT G ROUND RUNS AND TEST FLIGHT PROVED SATISFACTORY. SOME OF THE WIRING NECESSARY FOR THE PROJECTS LEADING UP TO THIS INCIDEN T WAS CARRIED OUT IN THIS AREA (UPPER FIREWALL). IT IS BELIEVED THAT THE LINE MAY HAVE BEEN DISTURBED IE TYWRAPS, PERHA 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20080521 EA 2008 5 21 CA080331009 2 20080320 G 8530 LW12966 CYLINDER PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 469 469 (CAN) DURING A ROUTINE INSP, THERE WAS EVIDENCE OF A CRACK LOCATED AROUND THE INTAKE HSG. THE VALVE COVER WAS REMOVED AN D FURTHER VISUAL INSP REVEALED THE INTAKE VALVE WAS HITTING THE SIDE OF THE INTAKE HOUSING. WE FEEL THE CONSTANT HITTING OF THE HOUSING CAUSED A STRESS CRACK. CYLINDER WAS REPLACED. (TC NR 20080331009) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20080521 EA 2008 5 21 CA080401001 1 20080327 G 7830 W31G1120 WIRE CNDAIR CL600 CL6002B19 1900309 EA THRUST REVERSER BROKEN W E ENGINE SHUTDOWN O OTHER CR CRUISE 1 CA (CAN) ABOUT 20 MINUTES BEFORE EXPECTED ARRIVAL , RECEIVED THAT THERE WAS REV UNLOCKED MESSAGE ON EICAS IN FLIGHT, THE CR EW ACCORDING TOOK QUICK CHECKLIST OPERATION, SHUTDOWN THE LT ENGINE MANUALLY, DID SINGLE ENGINE LANDING PROCEDURES. STA RTED THE TROUBLESHOOTING. CHECKED THE PDU, ETC. FINALLY, FOUND THE PROBLEM, THE WIRE OF THE W31G/1/1-20 OF THROTTLE LOCK OUT THROTTLE LOCKOUT WAS BROKEN, THE BROKEN WIRE WAS TOO SHORT, (ALL THE WIRE SHOULD HAVE THE SAME LENGTH NORMALLY) THE Y SHOULD BE RIGGED TO MAKE SURE EVERYTHING WOULD BE OK, WE CHANGED THE THROTTLE LOCKOUT MICROSWITCH REF AMM78-37-01, AND REF ESPM20-16-10C, DID THE SOLDER SLEEVE WIRE SPLICING OF THROTTLE LOCKOUT MICROSWITCH, TESTING IS NORMAL BETWEEN EVERY 2 L 7 2 4F RT A21EA 20080521 NE 2008 5 21 CA080401002 2 20080313 G 7230 806101 BLADE BOEING 727 72722C 138400F NM PWA JT8 JT8D7B 52053 NE COMPRESSOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 18651 2963 (CAN) WHILE PERFORMING AC DAILY INSP, NR (3) ENGINE C-1 FAN ASSY WAS FOUND TO HAVE SUBSTANTIAL DAMAGE TO (3) BLADES. THE (3) BLADES HAD SIGNIFICANT L/E DEFORMATION WITH ONE EXHIBITING VISUAL CRACKING. THE C-1 FAN WAS REMOVED FROM SERVICE AN D REPLACED. THE AC WAS INSPECTED IAW MFG ABNORMAL OCCURRENCE "BIRD STRIKE". NO FAULTS WERE FOUND. IT HAD BEEN OBSERV ED AT THE END OF THE PRECEDING FLIGHT THAT ICE ACCUMULATION FALLING FROM THE EMPENNAGE AFTER ARRIVAL AND SHUTDOWN. IT IS SPECULATED THAT INGESTION OF ICE AT SOME STAGE OF FLIGHT MAY HAVE OCCURRED. THERE HAD BEEN NO INDICATIONS OF ENG OR AIR FRAME ABNORMALITIES DURING THE FLIGHT AND THE PROCEEDING DAILY INSP HAD NOT REVEALED THE DAMAGE. (TC NR 20080401002) 2 L 7 3 4F 4 F A3WE E2EA 20080602 EA 2008 6 2 CA080401004 2 20080326 G 7200 ENGINE DHAV DHC6 DHC6200 2802620 EA PWA PT6 PT6A20 52043 EA LEFT POWER LOSS W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 4517 ON TAKEOFF, THE LEFT ENGINE LAGGED BEHIND NOT PRODUCING MAX. POWER, TROUBLE SHOOTING FOUND THE TEMPERATURE COMPENSATOR UNIT LEAKING P3 AIR. THE PART WAS REPLACED AND THE PROBLEM WAS FIXED. (TC NR 20080401004) 1 H 7 2 3T 3 T RT A9EA E4EA 20080602 NM 2008 6 2 CA080401005 1 20080401 G 3222 PIN EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE NLG MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA DURING INSPECTION, FOUND NUT ON LOWER DRAG BRACE ATTACHEMENT HINGE PIN NOT SAFETIED WITH CUTTER PIN AND PRC ADRIFT SEE A TTACHEMENT. NO EVIDENCE OF WORK PREVIOUS ACCOMPLISHED ON THE NOSE GEAR. 2 L 7 2 4F 4 F RT A56NM E00063EN 20080602 NM 2008 6 2 CA080401008 1 20080313 G 3213 2821A000003 STRUT EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE LT MLG LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 2604 2604 DURING THE SERVICING OF THE LEFT MAIN GEAR IT AT BEEN NOTICE THAT THE AIR KEPT COMING OUT FROM THE OIL VENT VALVE. AS P ER EMBRAER, TO FIX THE PROBLEM THE MAIN GEAR AS TO BE CHANGE AIR CANADA FLEET AS BEEN ADVISED AND SEEMS TO BE A KNOWN CO NDITION (TC NR 20080401008). 2 L 7 2 4F 4 F RT A57NM E00070EN 20080602 NM 2008 6 2 CA080401010 1 20080401 G 3232 65C330325 ARM BOEING 737 737490 1384715 NM MLG ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 34053 WHILE PERFORMING CUSTOMER T/C (AD 99-10-12) INSPECTION OF MLG ACTUATOR BEAM ARM, UT INSPECTION FINDS THAT RT MLG ACTUATO R BEAM ARM IS CRACKED CYCLES/TSN ARE AIRFRAME. NO EVIDENCE THAT THIS PART HAS BEEN REPLACED SINCE A/C MANUFACTURE. (TC NR 20080401010) 2 L 7 2 4F RT A16WE 20080602 EA 2008 6 2 CA080402001 1 20080331 G 3040 HEATER DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE WINDSHIELD SMOKE W H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) DURING CLIMB, THE CREW OBSERVED SMOKE IN THE COCKPIT AND QUICKLY NOTICED THAT THE SMOKE WAS COMING FROM THE LT WIN DSHIELD ELECTRICAL TERMINALS. THE WINDSHIELD HEATING SYSTEM WAS TURNED OFF AND THE SMOKE STOPPED. DECISION WAS MADE TO TURN BACK AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. LINE MAINTENANCE DISCOVERED THAT THE LT WINDSHIELD L1 TERM INAL WIRE NR 3041-48B12C WAS BURNT. THE RT WINDSHIELD TERMINALS WERE INSPECTED AND THE L2 TERMINAL WIRE NR 3041-40A12NA WAS FOUND WITH BURNT MARKS. BOTH WIRES WERE REPLACED AND THE SYSTEM TESTED SERVICEABLE. THE AIRCRAFT WAS RELEASED AND A VERIFICATION FLIGHT WAS CONDUCTED. (TC NR 20080402001) 2 H 7 2 4T 4 T RT A13NM E20NE 20080602 NE 2008 6 2 CA080402002 2 20080305 G 7532 BLEED VALVE CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE COMPRESSOR MALFUNCTIONED W E ENGINE SHUTDOWN E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA THE CREW EXPERIENCED ENGINE VIBRATIONS, FOLLOWED BY AN EEC MANUAL LIGHT. ENGINE POWER INCREASED AS EXPECTED, BUT THE CR EW WAS UNABLE TO FURTHER MODULATE POWER BY MOVING THE THRUST LEVER. THE ENGINE WAS SHUT DOWN AS A RESULT AND THE FLIGHT CONTINUED TO PLANNED DESTINATION. THE COMPRESSOR BLEED VALVE ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVIC E. THE COMPONENT WILL BE INVESTIGATED AND RESULTS FORWARDED FOR REVIEW. (TC NR 20080402002) 2 L 7 2 4F 4 F RT A22CE E00059EN 20080602 NE 2008 6 2 CA080402005 2 20080314 G 7261 TANK AEROSP ATR42 ATR42* 8680900 EU PWA 120 PW120 NE ENGINE OIL LEAKING W E ENGINE SHUTDOWN K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION DE DESCENT 1 CA DURING DESCENT, OIL MIST WAS NOTED IN THE CABIN FOLLOWED BY A LOW OIL PRESSURE WARNING INDICATION. THE ENGINE WAS SHUT DOWN BY THE CREW. TROUBLESHOOTING REVEALED LOW OIL LEVEL IN THE TANK, AND SIGNS OF EXTERNAL OIL LEAKAGE. THE ENGINE IS TO BE REMOVED FOR INVESTIGATION. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080402005) 2 H 7 2 4T 4 T RT A53EU E20NE 20080602 EA 2008 6 2 CA080402006 2 20080328 G 8530 72877 TAPPET PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA NR 1 CYLINDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1490 WHEN REPLACING NR 1 CYLINDER THE HYDRAULIC TAPPET BODY WAS FOUND CRACKED IN TWO PLACES. (TC NR 20080402006) 1 L 7 2 3O 3 O A20SO E14EA 20080602 EA 2008 6 2 CA080402007 1 20080402 G 3150 WARNING LIGHT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE ILLUMINATED W B E EMER. DESCENT ENGINE SHUTDOWN J WARNING INDICATION DE DESCENT 1 CA AT THE TOP OF DESCENT WHEN PULLING BACK POWER, THE CREW GOT THE "LOW OIL PRES WARNING" ON THE LT ENG, SHORTLY FOLLOWED B Y THE LOW OIL PRES INDICATION. ALL OTHER PARAMETERS NORMAL. CREW THEN ACTIONED EMERGENCY PROCEDURES AND SHUT DOWN LT E NG AND LANDED. (TC NR 20080402007) 2 L 7 2 4F 4 F RT A21EA E15NE 20080602 EA 2008 6 2 CA080402008 1 20080314 G 2435 BRUSHES DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A34 52043 EA STARTER/GEN WORN W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 379 STARTER WOULD NOT OPERATE TO START ENGINE. (TC NR 20080402008) 1 H 7 1 3T 4 T A806 E4EA 20080602 NE 2008 6 2 CA080402010 2 20080316 G 7320 EEC AEROSP ATR72 ATR72 EU PWA PW120 PW124B NE ENGINE MALFUNCTIONED W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA DURING TAKEOFF ROLL, THE ENGINE TORQUE INDICATED 75 PERCENT. THE TAKEOFF WAS ABORTED AND AIRCRAFT TAXIED BACK TO THE RA MP. THE EEC WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. THE REMOVED UNIT WILL BE RETURNED FOR INVESTIGATION AND UPD ATES PROVIDED TO TC. (TC NR 20080402010) 2 H 7 2 4T 4 T RT E2ONE 20080603 EA 2008 6 3 CA080402011 2 20080304 G 7200 ENGINE EMB 312 EMB312 SO PWA PT6 PT6* 52043 EA POWER LOSS W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA DURING TRAINING MANEUVERS, THE PILOT REPORTED A LOSS OF ENGINE POWER. PILOT ATTEMPTED TO RECOVER WITHOUT SUCCESS, AND E JECTED SAFELY. AIRCRAFT CRASHED IN AN EMPTY FIELD. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF RO OT CAUSE ONCE ESTABLISHED. 1 L 7 1 4T 3 T RT E2NE 20080602 NE 2008 6 2 CA080402014 2 20080321 G 7200 ENGINE AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE POWER LOSS W E A ENGINE SHUTDOWN UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA DURING CLIMB, ENGINE POWER WAS LOST ACCOMPANIED BY A LOUD NOISE. THE ENGINE WAS SECURED AND THE AIRCRAFT RETURNED TO BA SE. INITIAL INVESTIGATION REVEALED SEVERE ENGINE DAMAGE INCLUDING FRACTURE OF THE 2ND STAGE POWER TURBINE BLADES. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080402014) 2 H 7 2 4T 4 T RT E20NE 20080602 NE 2008 6 2 CA080402017 2 20080327 G 7200 ENGINE AEROSP ATR72 ATR72201 8680943 EU PWA PW120 PW124B NE MAKING METAL W A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CL CLIMB 1 CA THE OIL PRESSURE INDICATION REDUCED TO ZERO FOLLOWED BY A LOUD NOISE, OIL MIST AND ODOR IN THE CABIN. THE ENGINE THEN F LAMED OUT. INITIAL INSPECTION REVEALED A CONTAMINATED CHIP DETECTOR AND THE PROPELLER DIFFICULT TO TURN. THE ENGINE IS TO BE REMOVED FOR INSPECTION AND UPDATES WILL BE PROVIDED. 2 H 7 2 4T 4 T RT A53EU E2ONE 20080602 2008 6 2 CA080402018 4 20080317 G 6122 GOVERNOR BEECH 1900 1900C 1154161 CE PWA PT6 PT6A67B 52043 NE PROPELLOR MISRIGGED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA TAKEOFF WAS ABORTED WHEN THE ENGINE WOULD NOT PRODUCE FULL POWER. INVESTIGATION REVEALED IMPROPER RIGGING OF THE PROP G OVERNOR. 2 L 7 2 4T 4 T RT A24CE E26NE 20080602 NE 2008 6 2 CA080402019 2 20080401 G 7200 ENGINE AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE DAMAGED W E A ENGINE SHUTDOWN UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CL CLIMB 1 CA THE CREW HEARD A LOUD NOISE ACCOMPANIED BY AN AIRCRAFT YAW. UPON POWER REDUCTION, THE ENGINE SHUT DOWN BY ITSELF. INIT IAL INVESTIGATION REVEALS SEVERE INTERNAL ENGINE DAMAGE. THE ENGINE WILL BE INVESTIGATED AND UPDATES WILL BE PROVIDED. (TC NR 20080402019) 2 H 7 2 4T 4 T RT E20NE 20080602 EA 2008 6 2 CA080403002 1 20080331 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE MALFUNCTIONED W L ABORTED APPROACH F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA 24045 THE POST MAINTENANCE TEST FLIGHT WAS UNSUCCESSFUL. THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE ON APPROACH WHEN THE FL APS WERE SELECTED FROM 0 TO 8 DEGREES. THE FLAP ELECTRONIC CONTROL UNIT (FECU) CODES WERE RETRIEVED. THE RT BRAKE AND P OSITION SENSOR UNIT (BPSU) WAS REPLACED AND RIGGED, THE LT BPSU WAS RE-RIGGED AND THE FECU WAS REPLACED FOR TROUBLESHOOT ING. THE AIRCRAFT WAS RELEASED AND COMPLETED A SUCCESSFUL TEST FLIGHT. RT BPSU, P/N 855D100-9, S/N 372, TSN 24045:44, CSN 13150, TSR 20:02, CSR 12. FECU, P/N 601R93050-7, S/N 331, TSN 14405:58, CSN 10815, TSR 7938:28, CSR 6408. (TC NR 200 80403002) 2 L 7 2 4F 4 F RT A21EA E15NE 20080602 WP 2008 6 2 CA080403003 2 20080331 G 7310 8945682 TUBE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP ENGINE CRACKED W A UNSCHED LANDING R K PARTIAL RPM/PWR LOSS FLUID LOSS CL CLIMB 1 CA DURING TAKEOFF, THE CREW NOTED THE LT ENGINE WAS A LITTLE LOW ON POWER. DECIDED TO RETURN TO THE AIRPORT AS THE FUEL FL OW INDICATION FOR THAT ENGINE WAS ERRATIC. THE LANDING WAS UNEVENTFUL. ONCE ON THE GROUND THE AIRCRAFT WAS INSPECTED B Y MAINTENANCE AND THEY DETERMINED THE LINE FROM THE FUEL FLOW TRANSMITTER TO THE FUEL FLOW DIVIDER HAD SPLIT AT A BEND R ADIUS IN THE TUBE CAUSING A SOMEWHAT LARGE FUEL LEAK. THE LEAK WAS ENOUGH TO AFFECT ENGINE PERFORMANCE. THE LINE WAS F OUND TO BE INSTALLED CORRECTLY WITH NO EXISTING DAMAGE TO THE LINE OR AREA OF THE SPLIT. THE AGE OF THE LINE COULD NOT BE ACCURATELY DETERMINED BUT IT WAS IN VERY GOOD CONDITION AND THE PART NUMBER WAS CORRECT FOR THE ENGINE INSTALLATION. 2 L 7 2 4T 4 T RT A8SW E4WE 20080602 SW 2008 6 2 CA080403005 1 20080331 G 5610 2621126905 WINDSHIELD SWRNGN SA226 SA226T 8780122 SW GARRTT TPE331 TPE33110U 01514 WP COCKPIT CRACKED W B A EMER. DESCENT UNSCHED LANDING W INADEQUATE Q C CR CRUISE 1 CA 1986 IN LEVEL CRUISE AT FLIGHT LEVEL 220 APPROXIMATELY 25 MINUTES AFTER DEPARTURE, THE LEFT HEATED WINDSHIELD SUDDENLY SHATTE RED. ATC WAS ADVISED AND DESCENT REQUESTED FOLLOWED BY REQUEST FOR RETURN TO CYWG. AFTER ESTABLISHING THE RETURN COURS E AND LEVELING AT 9000 FEET, THE PASSENGERS WERE BRIEFED AND THE AIRCRAFT PROCEEDED BACK AT REDUCED CRUISE SPEED AND COM PLETED A NORMAL LANDING. UPON WINDOW REMOVAL NO DISCREPANCIES WERE NOTED WITH THE PREVIOUS INSTALLATION, ALL ATTACHING HARDWARE WAS CORRECT. 2 L 7 2 4T 4 T RT A5SW E4WE 20080602 EU 2008 6 2 CA080403007 1 20080319 G 2121 BEARING AIRBUS A319 A319112 3930323 EU CFMINT CFM565 CFM565B6 13802 NE RECIRC FAN OVERHEATED W B EMER. DESCENT M B J OVER TEMP SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA 19565 NEAR TOP OF CLIMB, COCKPIT ODOR OF ACRID BURNING SMELL NOTICED. NO ECAM OR VISUAL CUES. DURING CRUISE CHECK NOTICED FA N IN AMBER DISPLAYED ON COND PAGE. RECYCLED CAB FAN AND SMELL REOCCURRED IMMEDIATELY. RETURNED TO AIRPORT. THE SHOP R EPORT INDICATED THAT THE REAR BEARING SEIZED, THE FRONT BEARING WAS DRY, THE FAN OVERHEATED BUT THE STATOR WAS ELECTRICA LLY NORMAL. THE FAN WAS DIRTY AND SMELLED OVERHEATING. 2 L 7 2 4F 4 F RT A28NM E37NE 20080602 NE 2008 6 2 CA080403008 2 20080401 G 8550 100243 SHAFT CNDAIR CL215 CL2151A10 1900320 EA PWA R2800 CA3 52026 NE HAMSTD 43E 43E60 NE ENGINE OIL SHEARED W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION LD LANDING 1 CA 946 (CAN) JUST BEFORE TURNING BASE LEG FOR LANDING THE RT BMEP GAUGE FELL TO ZERO. NO OIL WAS OBSERVED LEAKING FROM ENGINE ALTHOUGH THE OIL QUANTITY WAS SLOWLY FALLING. LANDING WAS CARRIED OUT NORMALLY. ON ROLL OUT QUANTITY WAS READING 8 GAL LONS, SO THE RT ENGINE WAS SHUT DOWN. MAINTENANCE DISCOVERED THAT THE SCAVENGE PUMP HAD INGESTED A PIECE OF A CASTLE NU T WHICH HAD BROKEN OFF ONE OF THE NUTS P/N 542 FROM ONE OF THE REDUCTION PINION GEAR SHAFTS. THIS HAD CAUSED THE FAILUR E OF THE GEAR/SHAFT P/N 100243 IN THE ACCESSORY DRIVE CASE. 2 H 7 2 4R 4 R RT A14EA E231 6 C P871 20080602 NE 2008 6 2 CA080403009 2 20080116 G 8520 128495 MAIN BEARING DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 22D 22D30 NE MASTER ROD BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 1474 DURING INSPECTION METAL PIECES FOUND IN ENGINE SUMP. INVESTIGATION DETERMINED THEM TO BE PART OF FLANGE OF MASTER ROD B EARING. ENGINE REMOVED FOR OVERHAUL. 1 H 7 1 3R 3 R RC A806 5E1 5 C P736 20080602 GL 2008 6 2 CA080404001 1 20080303 G 5310 C2TP63ND SPAR DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA WHEN REPLACING FRONT CENTER SPAR DUE CRACK. REAR CENTER SPAR DISCOVERED CORRODED BEHIND CENTER MOUNT BRACKET. SPAR REP LACED. THIS CORROSION WAS NOT VISABLE UNTIL ACCESS TO INSIDE OF TAILPLANE WAS GAINED (TC NR 20080404001) 1 H 7 1 3R 3 R RC A806 5E1 20080602 SW 2008 6 2 CA080404002 1 20080326 G 2913 SHAFT SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HYD PUMP FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1155 DURING A ROUTINE INSPECTION OF THE HYDRAULIC PUMP, THE RETAINING BOLT WHICH HOLDS THE SPLINE DRIVE INTO THE HYDRAULIC PU MP HAD SHEARED. 2 L 7 2 4T 4 T RT A8SW E4WE 20080602 NM 2008 6 2 CA080404004 1 20080402 G 2913 6617303 PUMP BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA HYDRAULIC SYS FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 1339 DURING CRUISE FL 120, NR 2 ENG HYD PRES CAUTION LIGHT ILLUMINATED. HYD NR 2 PRESS - 0 PSI - AFTER PERFORMING ABNORMAL C HECKLIST WITH PTU ON, PRESS 3000 PSI. UNEVENTFUL LANDING. MAINTENANCE CREW REPLACED THE NR 2 ENGINE DRIVEN HYDRAULIC P UMP. 2 H 7 2 4T 4 T RT A13NM E00062EN 20080602 EA 2008 6 2 CA080404005 1 20080331 G 2823 39423091 SHUTOFF VALVE DHAV DHC3 DHC3 2800202 EA GARRTT TPE331 TPE33110R 0517 WP FUEL SYSTEM UNSERVICEABLE W O OTHER O OTHER NR NOT REPORTED 1 CA 77 ENGINE WOULD NOT SHUT DOWN USING NORMAL SHUT DOWN PROCEDURES. EMERGENCY SHUTOFF PROCEDURES USED. TROUBLESHOOTING FOUND FUEL SHUTOFF VALVE U/S (SOLENOID STICKING). REPLACED FUEL SHUTOFF VALVE. ENGINE RUN-UP AND SHUT DOWN NORMAL. AIRCRAF T RETURNED TO SERVICE. 1 H 7 1 3R 4 T A815 E4WE 20080602 NM 2008 6 2 CA080404006 1 20080331 G 2420 1701320 GENERATOR EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE APU FAULTED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA 2802 ON FIN 309 WHILE T/S A LONG HISTORY FAULT OF APU GEN FAULT. ARCING WAS FOUND AT THE LUG T3 ATTACH POINT WITH THE APU GE NERATOR. APU GENERATOR WAS REPLACED. 2 L 7 2 4F 4 F RT A57NM E00070EN 20080602 SO 2008 6 2 CA080404007 1 20080329 G 4990 GTCP36150G APU GULSTM G1159 GIV 3980115 SO RROYCE TAY TAYMK6118 NE LEAKING W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA 5558 21 APU AUTO SHUT DOWN WITH LOW OIL PRESSURE FAULT. OIL QTY RE-ADJUSTED AND APU STILL SHUT DOWN FOR LOW OIL PRESSURE. REPL ACED OIL PRESSURE SWITCH AND APU STILL SHUT DOWN INTERMITTENTLY. AFTER TROUBLE SHOOTING WITH DIRECT OIL PRESSURE GAUGE FOUND OIL PRESSURE DELIVERY WITH INTERMITTENT LOW OIL PRESSURE READING. SUSPECTING OIL PUMP OR PRESSURE REGULATOR. LOA NER APU INSTALLATION IN PROGRESS, MORE INFO WILL BE GIVEN WHEN REPORT OF REPAIR SHOP WILL BE GIVEN. 2 L 7 2 4F 4 F RT A12EA A25NE 20080602 CE 2008 6 2 CA080404009 1 20080404 G 2510 CABLE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL PILOT SEAT OUT OF ADJUST W O OTHER O OTHER TX TAXI/GRND HDL 1 CA FLIGHT CREW DISCREPANCY, PILOTS SEAT DOES NOT SLIDE BACK INTERMITTENTLY. SEAT REMOVED AND VISUALLY INSPECTED. REEL ASS EMBLY CABLE ADJUSTED AND SEAT FUNCTION TESTED WITH NO DEFECTS FOUND. SEVERAL AIRCRAFT IN OUR FLEET OF CESSNA 100 SERIES AIRCRAFT HAVE EXPERIENCED SIMILAR DISCREPANCIES, AND THE PASSENGER SEATED WAS UNABLE TO EXIT THE CABIN. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20080602 NE 2008 6 2 CA080406001 2 20080331 G 7321 0301037950 LINE SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE FUEL CONTROL BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA TUBE WAS DISCOVERED CRACKED AND SEPARATED FROM FLARE AT P2 TAP END DURING ROUTINE INSPECTION. ORIGINALLY, BLACK DEPOSIT S WERE NOTICED AT B-NUT AND WHEN DISASSEMBLED, FOUND COMPLETE FAILURE OF TUBE FROM FLARE END. CLOSE TOLERANCE FIT OF TU BE PROBABLY PROHIBITED ANOMALY FROM BEING NOTICED EARLIER. 1 G 7 1 3U 3 U NC H9EU E19EU 20081105 NE 2008 11 5 CA080407001 2 20080404 G 7200 C632A2116102 HOUSING UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5291 (CAN) CRACK INDICATION FOUND ON UPPER RT AREA OF INPUT HOUSING BOSS. THIS WAS FOUND DURING OVERHAUL OF THE MODULE. PART SENT TO MFG FOR EVALUATION. 1 G 7 2 3U 3 U NC R0001RD E34NE 20080602 2008 6 2 CA080407002 1 20080331 G 3297 472011 WIRE HARNESS NLG WOW MISINSTALLED W O OTHER O OTHER NR NOT REPORTED 1 CA AN OPERATOR FOUND THAT DURING INSTALLATION OF MOD SUM 4-125401, FINDING THE NEW HARNESSES PN.47201-1 THREE OUT OF SIX HA RNESSES PULLED FROM STOCK WERE MISS WIRED. ON CONNECTOR 3261-P32 PINS A-B AND D-E WERE WIRED REVERSED. HARNESSES APPRO PRIATELY REPAIRED IAW MANUFACTURER PROVIDED DATA AND RETURNED TO STOCK. TO ADDRESS THIS ISSUE, SERVICE LETTER DH8-SL-32 -014A ADVISING OF POSSIBLE MANUFACTURING FAULTS WAS RAISED. 20080602 EA 2008 6 2 CA080407003 1 20080406 G 2752 852D1001921 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE FLAP UNSERVICEABLE W O OTHER F J FLT CONT AFFECTED WARNING INDICATION DE DESCENT 1 CA ON APPROACH AT 4000 FT SELECTING FLAPS FROM 0 - 8 DEG, FLAP FAIL MSG APPEARED IMMEDIATELY WITH NO MOVEMENT OF FLAPS. AI RSPEED 215 AT THE TIME. A/C WAS AT -57 DEG FOR 1 HR IN CRUISE, GND -4. FECU INTERGRADED AND FOLLOWING FAULT CODES DISP LAYED AS FECU WAS LOOKED AT: (1) JAM (2) LEFT BPSU (3) 1 5 1B. TRIED TO GO FURTHER AFTER THE STEP OF `GO` IN THE FIM AN D IT WOULD GIVE THE FAULT CODE 1 5 1B CB 1-F4 AND CB 2-F4 AND SYSTEM RESET WITH NO FURTHER FAULTS. FERRY FLIGHT PAPERW ORK COMPLETED. A/C FERRIED. TROUBLESHOOTING GOING ON, ACTION PLAN TO INSPECT AND LUBE ALL DRIVES AND CHANGE ALL FLAP A CTUATORS WITH NEWLY OVERHAULED UNITS SENT. INFORMATION WILL BE UPDATED WHEN AVAILABLE. 2 L 7 2 4F 4 F RT A21EA E15NE 20080602 GL 2008 6 2 CA080407004 1 20080404 G 3234 1760A000004 LEVER BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP MLG LOOSE W O OTHER F FLT CONT AFFECTED CL CLIMB 1 CA AFTER TAKEOFF, IT WAS REPORTED THAT THE CREW WERE UNABLE TO RETRACT THE FLAPS FROM THE 10 DEGREE POSITION TO THE 0 DEGRE E POSITION. PRELIMINARY REPORT STATES THAT A LOOSE SCREW WAS FOUND INSIDE THE FLAP LEVER GUARD. THE FORWARD RIGHT SCRE W LOCATED INSIDE THE GUARD WAS FOUND TO BE PROTRUDING SUFFICIENTLY TO PREVENT THE LEVER FROM MOVING FROM THE 10 DEGREE P OSITION TO THE 0 DEGREE POSITION. ALL THREE REMAINING SCREWS WERE FOUND TO BE SECURE. A VISUAL AND TACTILE INSPECTION CAN BE PERFORMED TO ENSURE THAT ALL 4 SCREWS LOCATED INSIDE THE FLAP LEVER GUARD ARE SLIGHTLY COUNTERSUNK AND DO NOT SHO W ANY SIGNS OF LOOSENESS (REFER TO FIGURE1). PLEASE REPORT ANY ANOMALIES FOUND DURING THIS INSPECTION. 2 L 7 2 4F 4 F RT T00005NY E00010LA 20080602 EA 2008 6 2 CA080407005 2 20080403 G 7200 PT6A20 ENGINE DHAV DHC6 DHC6100 2802610 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL STOPPED W A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 CA 11786 4634 AFTER A NORMAL TAKEOFF, THE CREW WENT THROUGH POWER 1, FLAPS UP AND POWER 2 AND AFTER SETTING POWER 2 PRIOR TO CLIMB CHE CKS, THE CREW HEARD A LOUD POP AND SCRAPPING NOISE FROM THE NUMBER ONE ENGINE. THE FLIGHT CREW OBSERVED THAT THE NUMBER ONE PROPELLER WAS STOPPED AND ALL ENGINE GAUGES WERE AT ZERO. EMERGENCY CHECKLIST WAS FOLLOWED AND THE AIRCRAFT LANDED SAFELY WITH ONE ENGINE RUNNING. ENGINE TO BE REMOVED FOR EVALUATION BY REPAIR FACILITY. 1 H 7 2 3T 3 T RT A9EA E4EA 6 C P15EA 20081105 EU 2008 11 5 CA080407006 1 20080405 G 2913 A5026780 PUMP SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B 60037 NE HYDRAULIC SYS MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 2763 2763 (CAN) DURING NORMAL FLIGHT DURING A BIRD TOWING OPERATION THE PILOT RECEIVED A BING INDICATING A FAILURE. AIRSPEED 60KTS , 1000 FT AGL, 170 FT LINE WITH BIRD, 45 MINUTES INTO FIRST FLIGHT OF THE DAY: " BING " HEARD IN HEADSET, HYD WARNING L IGHT OBSERVED, NOTICE CHANGE OF FEEL TO THE CYCLIC CONTROL (ACCUMULATORS ACTIVATED) CHECKED THAT BOTH HYD SWITCHES HAD N OT BEEN INADVERTENTLY ACTIVATED. OBSERVED AIRSPEED 60KTS, SWITCHED HYD CUT OFF TO ON POSITION, CONTINUED TO DECENT TO A LAKE, SET UP FLAT APPROACH WITH BIRD. RADAR ALT INDICATED BIRD WAS 5 FT OFF GROUND LOAD WAS JETTISONED AT 25KTS IAS PO SITION FOR A SECOND APPROACH AND LANDED HELICOPTER WITHOUT INCIDENT THE HYDR PUMP WAS REPLACED AFTER AND ACFT WAS TEST F 1 G 7 1 3U 3 U H9EU E00054EN 20080602 SW 2008 6 2 CA080407007 1 20080405 G 6322 R476204971 GEAR SET BELL 4762060025 BELL 47 47G4 1181030 SW LYC O540 VO540B1B3 41532 EA COOLING FAN SHEARED W A UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 CA 77 APPROX 100 HRS AGO TRANSMISSION WAS O/H AND NEW PMA GEAR SET WAS INSTALLED S/N GR586A FROM HELICOPTER TECH DURING FLIGHT PILOT HEARD AND FELT NOISE AND MADE A PRECAUTIONARY LANDING AND FOUND COOLING FAN DRIVE PULLEY AND APPROX 1.25 INCHES O F THE DRIVE SHAFT WAS MISSING. WE ARE SENDING IN REMAINING SHAFT SEGMENT WHERE IT SHEARED FOR METALLURGICAL ANALYSIS. 1 G 7 1 3O 3 O 2H3 E304 20080602 EA 2008 6 2 CA080407010 1 20080402 G 3250 CABLE DHAV DHC6 DHC6200 2802620 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL STEERING BROKEN W D RETURN TO BLOCK S AFFECT SYSTEMS TX TAXI/GRND HDL 1 CA STEERING CABLE BROKE ON TAXI WHILE THE AIRCRAFT WAS PREPARING FOR TAKEOFF. 1 H 7 2 3T 3 T RT A9EA E4EA 6 C P15EA 20080602 EU 2008 6 2 CA080408001 1 20080408 G 2520 4030082SRS ATTACH FITTING PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL PAX SEAT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8953 DURING 100 HOUR INSPECTION PASSENGER SEAT RECLINE HYDRAULIC MOUNT ATTACHMENT FOUND CRACKED. SEAT MANUFACTURER IS ERDA. NOT FOUND IN ASSEMBLY MANUFACTURER LIST. REPAIR INFORMATION REQUESTED THROUGH AIRCRAFT MANUFACTURER, PILATUS. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20080602 EA 2008 6 2 CA080408002 1 20080329 G 2750 70745 CONTROL UNIT CNDAIR CL600 CL600* 1900302 EA GE CF34 CF348C5 30050 NE TE FLAP MOTOR FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA 8989 8989 PRIOR TO DEPARTURE FLIGHT CREW COMPLETED A STAB TRIM RESET. SHORTLY AFTER FLAP RETRACTION ON TAKEOFF, FLIGHT CREW RECEI VED AN AP TRIM IS ND ASSOCIATED WITH AN AP PITCH TRIM ‘CAUTION MESSAGE. SUBSEQUENTLY CREW RECEIVED A ELEVATOR SPLIT’ CA UTION MESSAGE. CREW FOLLOWED QRH, CIRCLED TO BURN OFF FUEL AND LANDED BACK AT DEPARTURE AIRPORT WITHOUT INCIDENT. MAIN TENANCE CHECKED ELEVATOR TRIM POSITION FULL NOSE DOWN, NEUTRAL AND FULL NOSE UP OK. AUTO PILOT ELEVATOR SERVO OPERATION CHECKED OK. ELEVATOR SPLIT MESSAGE TROUBLESHOT PER FIM TASK OK. PROBLEM ISOLATED AS MDC DISPLAYED AN INTERNAL FAULT O F THE MOTOR CONTROL UNIT CHANNEL 2 INTERNAL HOLD ON RELAY. MOTOR CONTROL UNIT REPLACED. OPERATIONAL TESTS OF THE SSCU, 2 L 7 2 4F 4 F RT A21EA E00063EN 20080602 NM 2008 6 2 CA080408003 1 20080404 G 2130 CABIN PRESSURE BOEING 757 75728A 1384976 NM RROYCE RB211 RB211535E437 54555 NE MALFUNCTIONED W A UNSCHED LANDING G MULTIPLE FAILURE CL CLIMB 1 CA AIRCRAFT C-GTDX DEPARTING FROM YYZ ON APRIL 4TH 2008, AROUND 7000 FT AN EICAS MSG AUTO PRESSURIZATION SYS 1 AND 2, AIRCR AFT RETURNED BACK TO YYZ AND REQUESTED FIRE TRUCKS ON ARRIVAL DUE TO OVERWEIGHT LANDING. TROUBLESHOOTING CARRIED OUT, B OTH PRESSURIZATION CONTROL UNITS AND STBY ALTIMETER REPLACED AS PRECAUTIONARY MEASURE. FLIGHT TEST CARRIED OUT SUCCESSF ULLY. INVESTIGATION IS ON GOING. 2 L 7 2 4F 4 F RT A2NM E12EU 20080602 EA 2008 6 2 CA080408004 1 20080330 G 3230 101655 UPLOCK ROLLER DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE RH MLG SEIZED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 35895 20079 RT MLG FAILED TO EXTEND ON LANDING GEAR SELECTION, CREW PERFORMED GO-AROUND AND USED ALTERNATE GEAR EXTENSION. ALL LAND ING GEAR EXTENDED AND NORMAL LANDING CARRIED OUT. MAINTENANCE INSPECTION FOUND RT MLG UPLOCK ROLLER SEIZED, ROLLER REPL ACED, GEAR SWINGS COMPLETED AND AIRCRAFT RETURNED TO SERVICE. TIMES PROVIDED ARE SHOCK STRUT TIMES, ROLLER IS NOT SERIA LIZED AND NOT TRACKED FOR ACTUAL TIMES. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080602 EU 2008 6 2 CA080409001 1 20080325 G 2597 40900011 WIRE AIRBUS 310 A310304 3930339 EU GE CF6 CF680C2* GL COFFEEMAKER BURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 4341 483 IN CRUISE AFT GALLEY RT COFFEEMAKER BURNED. ALL C/B’S WERE PULLED. HALON FIRE EXTINGUISHER WAS USED AS A PRECAUTIONARY MEASURE. C/B ON COFFEE MAKER FOUND POPPED. FOUND WIRES TO PRESSURE SWITCH BURNED AND DISCONNECTED. NO OTHER WIRING D AMAGE ON THE COFFEE MAKER. COFFEE MAKER REPLACED AND ROUTED TO SHOP FOR REPAIR. 2 L 7 2 4F 4 F RT A35EU E23EA 20080602 EU 2008 6 2 CA080409003 1 20080407 G 2133 OUTFLOW VALVE AIRBUS 310 A310300 3930305 EU GE CF6 CF680C2* GL CABIN PRESSURE MALFUNCTIONED W B EMER. DESCENT J WARNING INDICATION CR CRUISE 1 CA AFTER 30 MIN IN CRUISE, CAB PRESSURE REG NR 2 FAULT, FOLLOWED BY CAB PRESSURE REG NR 1 FAULT. UNABLE TO CONTROL IN MANU AL. EMERGENCY DESCENT AND QAR PROCEDURES FOLLOWED. PAX MASK SYSTEM ACTIVATED IN AUTO. FLIGHT RETURNED TO STATION AT F L 10,000 FT. ACFT WAS REMOVED FROM SERVICE FOR INVESTIGATION. 2 L 7 2 4F 4 F RT A35EU E23EA 20080602 EA 2008 6 2 CA080409004 1 20080330 G 3040 601R3303313 CONTROLLER CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE WINDSHIELD TEMP OVERTEMP W O OTHER J WARNING INDICATION DE DESCENT 1 CA 14325 14325 ON DESCENT THROUGH 21000 FEET INTO ARRIVAL AIRPORT, CAPTAIN’S LT WINDSCREEN SHATTERED. CREW DONNED OXYGEN MASKS AS A PR ECAUTION. CREW DECLARED AN EMERGENCY WITH ATC AND MADE ANNOUNCEMENT TO THE PASSENGERS. FLIGHT LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE WINDSHIELD ASSEMBLY P/N 601R33033-13, S/N 01057H1890, TIMES AND CYCLES SAME AS THE TEMPERATUR E CONTROLLER. MAINTENANCE ALSO REPLACED THE LT WINDSHIELD TEMPERATURE CONTROLLER SUSPECTING THAT IT HAS CAUSED AN OVERH EAT CONDITION. 2 L 7 2 4F 4 F RT A21EA E15NE 20081105 SW 2008 11 5 CA080409005 1 20080409 G 2450 MS2207375 CIRCUIT BREAKER BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE OVERHEAD PANEL INOPERATIVE W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) WHILE DOING A PREFLIGHT CHECK DURING FLIGHT TRAINING IT WAS NOTED THAT THE LT BOOST PUMP CIRCUIT BREAKER WAS NOT A BLE TO BE CYCLED. THE CIRCUIT BREAKER WAS REMOVED AND REPLACED. AFTER GOING THROUGH THE REST OF THE CIRCUIT BREAKER PANE L IS WAS NOTED THAT IN EXCESS OF 20 BREAKERS WERE DIFFICULT TO OR UNABLE TO BE CYCLED. REQUIRED CIRCUIT BREAKERS WERE RE PLACED. INSPECTION CRITERIA TO NOW INCLUDE CYCLING BREAKERS AT INTERVALS TO REDUCE THE CHANCE OF A BREAKER NOT POPPING W HEN REQUIRED AND CAUSING FURTHER PROBLEMS/DAMAGE. (TC NR 20080409005) 1 G 7 1 4U 4 U H1SW E17EA 20080602 EA 2008 6 2 CA080409006 2 20080330 G 7230 BLADES BELL 412 412 1182202 SW PWA PT6T PT6T3 52045 EA COMPRESSOR TURB FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION AP APPROACH 1 CA ON APPROACH, THE CREW NOTED ENGINE TEMP AT APPROX 900 DEGREES FOLLOWED BY SOME NOISES. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED. INITIAL INVESTIGATION REVEALED LOSS OF COMPRESSOR TURBINE BLADE MATERIAL AND SHROUD SEGMENT MATERIAL, THE ENGINE WAS SENT FOR REPAIR. 1 G 7 2 4U 4 U H4SW E22EA 20080602 EA 2008 6 2 CA080409008 1 20080409 G 5210 33130131 PISTON CNDAIR CL215 CL2151A10 1900320 EA ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4499 ANOTHER OPERATOR INFORMED OUR QUALITY ASSURANCE DEPARTMENT OF THEIR FINDING CRACKS IN THE ACTUATOR THREADED PORTION IN 5 OUT OF 7 ACTUATORS. INSPECTED ALL 14 OF OUR FLEET ACTUATORS AND FOUND 4 TO BE CRACKED ALSO. 2 H 7 2 4R RT A14EA 20081105 NE 2008 11 5 CA080410004 2 20080401 G 7314 LW15473 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 881 (CAN) DURING A DAILY INSP OIL WAS FOUND LEAKING FROM THE ENGINE DRIVEN FUEL PUMP, PART WAS REMOVED AND REPLACED (TC NR 2 0080410004) 1 G 7 1 3O 3 O H11NM 1E4 20080602 EA 2008 6 2 CA080410005 1 20080408 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE RT FLAP SYS UNSERVICEABLE W O OTHER J WARNING INDICATION DE DESCENT 1 CA 3291 ON DESCENT, CREW SELECTED AND RECEIVED FLAPS 8 DEGREES, WHEN THEY ATTEMPTED TO PROCEED TO FLAPS 20 CREW RECEIVED A FLAP FAIL MESSAGE. FLIGHT LANDED WITHOUT INCIDENT. FECU MESSAGE POINTED TO THE RT BPSU AS THE FAULT. THE RT BPSU WAS REPLA CED, FLAP SYSTEM RIGGED AND FUNCTION CHECKED SERVICEABLE. THE A/C RETURNED TO SERVICE WITH NO FURTHER FAULTS. 2 L 7 2 4F 4 F RT A21EA E15NE 20081105 WP 2008 11 5 CA080410006 1 20080409 G 6310 SHAFT ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE CLUTCH WORN W K NONE O OTHER IN INSP/MAINT 1 CA 1998 (CAN) CLUTCH WAS REMOVED FOR GRINDING NOISE ON GROUND RUN. DURING DISASSEMBLY THE OIL IN THE CLUTCH WAS VERY BLACK DUE T O INTERNAL WEAR OF THE SHAFT, HSG AND SPRAG. THE SPRAG CAGE CROSSBAR WAS CRACKED, PEANUT INNER EARS WERE BROKEN OFF, WEA R ON THE INNER SURFACE OF THE PEANUTS (POSSIBLE SLIPPAGE) AND EXCESSIVE CAGE WINDOW WEAR. 1 G 7 1 3O 3 O H11NM 1E4 20080602 SO 2008 6 2 CA080410009 2 20080312 G 8530 AEC631397SN2B22 CYLINDER HEAD CESSNA 414 414 2075908 CE CONT O520 TSIO520N 17040 SO MCAULY 3AF32C 3AF32C505 GL ENGINE CRACKED W A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 105 PILOT FLYING IN CRUISE FLIGHT, WHEN HE HEARD A POP AND EXPERIENCED LOSS OF ENGINE POWER. FEATHERED PROPELLER AND LANDED AT NEAREST AIRPORT. ENGINE CYLINDER REPLACED. 1 L 7 2 3O 3 O RT A7CE E8CE 5 C P22EA 20081105 EU 2008 11 5 CA080411001 1 20080220 G 6700 D107610E ACTUATOR BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL TRIM SYS FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ACTUATOR FAILED, (WOULD NOT RETRACT) ON PRESTART TEST. FAILED IN THE EXTEN POSITION (CYCLIC FULL FWD) (TC NR 20080 411001) 1 G 7 2 3U 3 U H3EU E4CE 20080602 2008 6 2 CA080411002 4 20080409 G 6122 210332 PILOT VALVE WOODWARD GOVERNOR DAMAGED W O OTHER X ENGINE FLAMEOUT NR NOT REPORTED 1 CA 97 THE GOVERNOR WAS MANUFACTURED BY ONTIC, ONTIC HAS THE MANUFACTURING RIGHTS TO THE FORMER WOODWARD GOVERNOR COMPANY PISTO N ENGINE GOVERNORS. THE GOVERNOR WAS RECEIVED FROM THE AIRCRAFT MANUFACTURE, DIAMOND AIRCRAFT INDUSTRIES, FOR REPAIR IN APRIL 2008. ACCORDING TO A CUSTOMER CLAIM/RETURN AUTHORIZATION FORM RECEIVED FROM DIAMOND, THE GOVERNOR WAS REMOVED FR OM AIRCRAFT SERIAL NR 40.438 ON OR ABOUT SEPTEMBER 21, 2005, WITH AIRCRAFT TTSN OF 96.9 HOURS. WITH ORIGINAL COMPLIANT OF ENGINE OVERREVED DURING FLIGHT, COULD NOT CONTROL PROPELLER. THE NAME PLATE ON THE GOVERNOR GIVES A ASSY DATE OF 08/ 04 DURING INSPECTION OF THE GOVERNOR IN OUR SHOP, AFTER REMOVAL OF THE TOP COVER, IT WAS FOUND THAT THE HEAD END HAD SEP 20081105 EU 2008 11 5 CA080411003 1 20080220 G 6700 10513142 ROD END BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL BEARING DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ROD END HAS TEFLON MISSING WITH METAL TO METAL CONTACT (TC NR 20080411003) 1 G 7 2 3U 3 U H3EU E4CE 20080602 NM 2008 6 2 CA080411004 1 20080408 G 2910 6517840330 LINE BOEING 727 727223 1384074 NM PWA JT8 JT8D15 52051 NE HYD SYSTEM LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 CA AFTER TAKEOFF WHEN GEAR SELECTED UP, HYDRAULIC SYSTEM "A" LOW LEVEL LIGHT ILLUMINATED AND HYDRAULIC QUANTITY DROPPED TO 2.0 GAL. FLIGHT CREW DECLARED AN EMERGENCY AND RETURNED FOR APPROACH. PER FLIGHT CREW CHECKLIST GEAR WAS MANUALLY LOWE RED HOWEVER FLIGHT CREW WAS UNABLE TO MANUALLY LOWER THE LT GEAR. TWO ATTEMPTS WERE MADE AND THEN THE FLIGHT CREW SELEC TED ON ONE "A" SYSTEM HYDRAULIC PUMP TO GET THE LT GEAR DOWN AND LOCKED. THE PUMP WAS THEN TURNED OFF AGAIN. THE AIRCR AFT LANDED SUCCESSFULLY WITH NO ADDITIONAL FAULTS. MAINTENANCE PERSONNEL FOUND A PIN HOLE LEAK ON THE A SYSTEM HYDRAULI C RETURN LINE RETURNING FROM THE A SYSTEM HEAT EXCHANGER. A PERMANENT REPAIR WAS CARRIED OUT BY THE INSTALLATION OF A P 2 L 7 3 4F 4 F A3WE E2EA 20080602 GL 2008 6 2 CA080411006 2 20080409 G 7250 23063354 TURBINE BELL 407 407 1182206 SW ALLSN 250C 250C47B GL ENGINE DAMAGED W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA 4509 1226 ON THE THIRD MAIN ROTOR STROBING FLIGHT OF THE MORNING AND WHILE ACCELERATING FROM 100KTS TO 120KTS, A LOW HOWLING NOISE WAS HEARD WHICH INTENSIFIED RAPIDLY AND WAS FOLLOWED IMMEDIATELY BY AN ENGINE CHIP LIGHT. A FORCED LANDING WAS MADE TO A FIELD. AN EXTERNAL INSP INCH BY 4 INCH PIECE OF SHEET METAL WAS FOUND BROKEN AWAY FROM THE AFT RIGHT SIDE OF THE EXH AUST STACK. AFTER REMOVAL OF THE OUTER COMBUSTION CASE MAJOR VISIBLE DAMAGE WAS FOUND TO THE 1ST AND 2ND STAGE TURBINE BLADE TIPS. TURBINE SECTION IS BEING SENT TO STANDARD AERO LTD FOR INSPECTION WITH ROLLS ROYCE PARTICIPATION. 1ST AND 2ND TURBINE WHEEL CYCLES ARE 2004, 3RD AND 4TH STAGE CYCLES ARE 4977. ENGINE DATA COULD NOT BE DOWNLOADED FROM THE ECU, 1 G 7 1 3U 3 U O H2SW E1GL 20080602 CE 2008 6 2 CA080411007 1 20080407 G 3245 0923150 TUBE CESSNA 425 425 2076018 CE PWA PT6 PT6A112 52043 NE MCAULY 4HFR34 4HFR34C762 NE NLG WHEEL LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 62 NOSE TIRE FOUND LOW ON POST FLIGHT INSPECTION BY 10 PSI. NOSE WHEEL ASSY REMOVED FOR TEAR DOWN AND INVESTIGATION. SPAR E BUILT-UP WHEEL ASSY INSTALLED. TEAR DOWN SHOWED INNER TUBE HAD PIN HOLE IN OUTER CIRCUMFERENCE AT ONE END OF A FOLD M ARK. NO OTHER FAULTS FOUND WITH TIRE OR TUBE. 1 L 7 2 3T 3 T RT A7CE E4EA 6 C 3PNE 20080603 GL 2008 6 3 CA080414001 1 20080407 G 5711 SPAR DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5796 CRACKS FOUND WHILE COMPLYING WITH SB2/47. CRACKS JUST VISIBLE WITH FLUORESCENT PENETRANT INSPECTION. WHEN SPAR REMOVED CRACKS WERE VISIBLE TO NAKED EYE ON THE INTERIOR OF SPAR AND ON GUSSET BETWEEN SPAR AND GUSSET. 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 20080603 WP 2008 6 3 CA080414003 1 20080410 G 2435 GEAR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE STARTER GEN WORN W K NONE O OTHER IN INSP/MAINT 1 CA 58 UPON POST FLIGHT INSPECTION, STARTER TEETH FOUND WORN, REMOVED AND INSTALLED NEW STARTER. 1 G 7 1 3O 3 O H11NM 1E4 20080603 WP 2008 6 3 CA080414004 1 20080410 G 6310 CLUTCH ACTUATOR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAIN ROTOR MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 1552 UPON INSPECTION, CARRIED OUT METHOD 2 AND THE ACTUATOR KEPT RUNNING . 1 G 7 1 3O 3 O H11NM 1E4 20080603 EA 2008 6 3 CA080414005 2 20080411 G 7230 3012060 DUCT PWA PT6 PT6A27 52043 EA DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA METAL SWARF FOUND INSIDE COOLING PASSAGES OF DUCT ASSY. 4 T E4EA 20080603 2008 6 3 CA080414006 4 20080407 G 2210 08071 STATIC LINE AIRTRC AT802 AT802A 0390308 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MA3 GL AUTO PILOT SYS DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 CA 697 DURING RE-ACTIVATION OF THE AIRCRAFT, THE MAINTENANCE CREW NOTICED THAT THE STATIC LINE FOR THE AUTO PILOT ALTITUDE HOLD P/N 0807-1 WAS DETERIORATED AND CRACKED. THE LINE WAS REPLACED WITH A SERVICEABLE PART. ALL OTHER AIRCRAFT IN THE FLE ET WILL BE INSPECTED FOR SERVICEABILITY. 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 20080603 NM 2008 6 3 CA080414008 1 20080328 G 3242 BRAKE DISC BFGOODRICH DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MLG BRAKE ASSY WARPED W O OTHER M J OVER TEMP WARNING INDICATION TX TAXI/GRND HDL 1 CA 39505 6254 RAMP CREW NOTICED THAT RT INBOARD (NR 3) MAIN WHEEL WAS FLAT WHILE AIRCRAFT WAS PARKED AT GATE. MAINTENANCE DISCOVERED THE NR 3 BRAKE UNIT WITH A WARPED/OVERHEATED BRAKE DISKS WHICH CAUSED THE FUSE PLUGS ON THE NR 3 MAIN WHEEL TO BLOW. MA INTENANCE REPLACED THE NR 3 BRAKE UNIT AND THE NR 3 AND 4 MAIN WHEEL ASSEMBLIES. TAXI AND FUNCTION CHECKS OF THE BRAKIN G SYSTEM WERE COMPLETED WITH NO FURTHER FAULTS FOUND. WHEEL SHOP CONFIRMED BRAKE UNIT DID OVERHEAT AND THAT IT WAS NOT A FAULT WITH THE UNIT. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080603 2008 6 3 CA080414009 1 20080414 G 3110 7003652631 DISPLAY COCKPIT INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA FAIL AT INSTALLATION, AND CAME BACK OUT WITH THE SAME PROBLEM THAT WE SENT FOR REPAIR. DISPLAY BLANK OUT AFTER POWER UP O 5800145883,DATE REPAIR MARCH 14 2008. 20080603 EU 2008 6 3 CA080415004 1 20080408 G 2750 Z4243130000 CONTROL CABLE ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA TE FLAPS FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA FLAP CENTER CABLE WAS FOUND FRAYED DURING REGULARLY SCHEDULED MAINTENANCE. 1 L 7 1 3O 3 O 0 A76EU 1E10 20080603 SW 2008 6 3 CA080415005 1 20080412 G 5610 2719442004 WINDSHIELD SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP COCKPIT CRACKED W B EMER. DESCENT O OTHER CR CRUISE 1 CA 1233 DURING THE RETURN LEG TO MAIN BASE THE AIRCRAFT EXPERIENCED A RT HEATED WINDSHIELD CRACK IN A SPIDER WEB FASHION. THE AI RCRAFT DESCENDED THE CABIN DIFF WAS LOWERED AND AIRSPEED REDUCED. UPON WINDOW REMOVAL NO DISCREPANCIES WERE NOTED WITH THE PREVIOUS INSTALLATION, ALL ATTACHING HARDWARE WAS CORRECT. 2 L 7 2 4T 4 T RT A8SW E4WE 20080603 NE 2008 6 3 CA080415006 2 20080411 G 7250 BLADE TMECA ARRIEL ARRIEL1B 6OO30 NE TURBINE WHEEL DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 1ST STAGE TURBINE WHEEL BLADE LEADING EDGE DAMAGE IN ZONE 2 ON A TOTAL OF 8 BLADES. THE DAMAGE WAS CAUSED BY THE SEMI-C ONDUCTOR OF THE IGNITER, P/N 9550175400, THAT DISLODGED ITSELF FROM THE HOUSING. THIS WAS FOUND DURING A SCHEDULED 100/1 50 HR ENGINE INSPECTION. THE AFFECTED MO3 HAS BEEN SEND TO MANUFACTURER FOR FUTURE INVESTIGATION. SUBSEQUENTLY ALL OTH ER ENGINE IGNITER WHERE INSPECTED AND REMOVED FROM SERVICE DO TO LOOSENESS OF THE SEMI-CONDUCTOR. PICTURES WERE TAKEN A ND SEND TO MANUFACTURER. 3 U E19EU 20080521 WP 2008 5 21 CA080415007 1 20080411 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 79 (CAN) AFTER FIRST GROUND RUN, STARTER CRACKED, REPLACED STARTER (TC NR 20080415007) 1 G 7 1 3O 3 O H11NM 1E4 20080521 EU 2008 5 21 CA080416001 1 20080414 G 5302 V40GT3911AA SPRING BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL TAIL BOOM BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) COMING OUT OF A MAJOR INSP, WHERE THE EJECTION SPRINGS ON ALL THE COWLS ( P/N 105-62648, 105-62664, 105-62643, 105 -62663 AND 105-30851) WERE REPLACED. SEVERAL EJECTION SPRINGS P/N V40GT39-1-1AA WERE BREAKING INTO (2) PIECES. THIS PROB LEM HAPPENED STATICALLY ON THE GROUND. THESE EJECTION SPRINGS WERE ORDERED NEW FROM MFG, BATCH NR S0000243616 COMING FRO M DIFFERENT LOT NR. BREAKAGE HAPPENS IN THE MFG LOGO STAMPED ON THE EJECTION SPRING. NEW EJECTION SPRINGS SAME PN, SAME BATCH NR USED TO REPLACE BROKEN ONES ON THIS AC. (TC NR 20080416001) 1 G 7 2 3U 3 U H3EU E4CE 20080521 NE 2008 5 21 CA080416002 2 20080416 G 7414 COIL BL6006163 ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MAG WAS RECEIVED FOR 500 HOUR INSP. WHEN VENT PLUG WAS REMOVED DIRTY BROWN OIL WAS FOUND IN THE MAGNETO. UPON DIS ASSEMBLY THE OIL SEAL WAS FOUND TO BE LEAKING. THE COIL WAS LOOSE IN THE HOUSING UNDER THE COIL CLAMPS. THE COIL HAD DAR K BROWN MATERIAL AROUND THE MOUNTING AREA OF THE COIL POLES FROM WEARING AGAINST THE HOUSING. BOTH THE COIL AND HOUSING WERE UNSERVICEABLE DUE TO THE AMOUNT OF WEAR. THE MAGNETO HAD A NEW STYLE OF HOUSING WITH THE LETTERS (TCM) RAISED IN TH E CASTING AND A NEW CONTINENTAL ALPHA SYS DATAPLATE. THIS MAG WAS REBUILT IN JANUARY OF 2007. THE MAG WAS RETURNED TO M FG FOR WARRANTY PURPOSES. (TC NR 20080416002) 1 G 7 1 3O 3 O H11NM 1E4 20080521 2008 5 21 CA080416003 4 20080416 G 2562 ELT10 ELT BBAVIA 7 7GCAA 21101N8 SW LYC O320 O320A2B 41508 EA INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN TESTING UNIT FOR ITS 12 MONTH CERTIFICATION IAW CAR 571 APPENDIX G, UNIT DID NOT HAVE ANY TRANSMIT POWER. ELT TRANSMITTER BOARD REPLACED AND UNIT TESTED SERVICEABLE. (TC NR 20080416003) 1 H 7 1 3O 3 O A759 E274 20080521 WP 2008 5 21 CA080417003 1 20080413 G 7920 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE OIL LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 978 (CAN) DURING INSPECTION THERE WAS EVIDENCE OF OIL COMING OUT OF THE DRAIN LINE. THERE HAS BEEN MANY PUMPS LEAKING FORM T HE SEALS AND THIS ALLOWS ENGINE OIL TO BYPASS AND FLOW OUT OF THE DRAIN. PUMP WAS REPLACED AND AIRCRAFT RETURN TO SERVIC E. DATE CODE ON THE PUMP IS 4105. (TCNR 20080417003) 1 G 7 1 3O 3 O H11NM 1E4 20080521 EU 2008 5 21 CA080417010 1 20080221 G 5610 SEAL SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE CHIN BUBBLE DEPARTED W A UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 CA (CAN) CHIN BUBBLE WINDOW AND SEAL DEPARTED THE AIRCRAFT IN CRUISE FLIGHT. AIRCRAFT WAS LANDED AND CHECKED FOR DAMAGE, NO T FOUND. REVIEW INDCATED THAT THE WINDOW WAS REMOVED FOR MAINT BEFORE THE OCCURANCE. WILL FOLLOW UP FOR SPECIFIC PN (T C NR 20080417010) 1 G 7 1 3U 3 U NC H9EU E19EU 20080521 2008 5 21 CA080418001 1 20080416 G 3310 REE75R RHEOSTAT VIKING 72510090005 PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL RESISTANCE COILS MELTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CONCERNED WITH THE USE OF RHEOSTAT (PN REE75R) FOR REPLACEMENT OF RHEOSTAT SWITCH 20465-1. THE SB 7-33-21 CALLS TH E NEW RHEOSTAT, A RHEOSTAT SWITCH BUT IT DOES NOT HAVE AN "OFF" POSITION LIKE THE ORIGINAL RHEOSTAT SWITCH HAD. AS SUCH, WHEN IT IS TURNED TO THE SIMULATED OFF POSITION, IT IS STILL IN CIRCUIT (EVIDENCED BY THE FACT THAT THE UTILITY LIGHT H AS A SLIGHT GLOW) AND DISSIPATING MAXIMUM WATTAGE. THE HEAT IS TRANSFERRED THROUGH THE RHEOSTAT SHAFT CAUSING KNOB PN M S91528-1C1-B TO BECOME DEFORMED AND HOT TO THE TOUCH. ALSO, THE PANEL MATERIAL ADJACENT TO THE RHEOSTAT SHOWS EVIDENCE OF HEAT DAMAGE (CRACKING/DISCOLORATION). HAVE CONDUCTED BENCH TESTS ON THIS RHEOSTAT TO SIMULATE THE AC CIRCUIT AND HAV 4 T E4EA 6 C P1NE 20080521 NM 2008 5 21 CA080418002 1 20080417 G 2612 FIRE DETECTOR BOEING 727 727247 138408F NM PWA JT8 JT8D15 52051 NE NR 1 NACELLE FALSE INDICATION W F ACTIVATE FIRE EXT. N FALSE WARNING CL CLIMB 1 CA (CAN) AFTER TAKEOFF, AT APPROX 1,000 FEET AGL, THERE WAS A FIRE WARNING ON THE NR 1 ENGINE. THRUST LEVER RETARDED, LIGHT REMAINED ON. EMERGENCY DRILL COMPLETED AND LIGHT EXTINGUISHED AFTER FIRE BOTTLE DISCHARGED. AC RETURNED AND LANDED WIT HOUT FURTHER INCIDENT. THERE WAS NO EVIDENCE OF A FIRE. MAINT FOUND THE FAULT IN THE NR 1 FIRE DETECTION B SYS. (TC NR 20080418002) 2 L 7 3 4F 4 F A3WE E2EA 20080521 2008 5 21 CA080418003 1 20080318 G 3245 302120402 TUBE MLG TIRE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MULTIPLE FAILURES OF INNER TUBES ON VARIETY OF COMPANY C-208 MAIN WHEELS. TUBES FAIL IN DIFFERENT WAYS FROM PIN HO LES TO 18 INCH SPLITS. THERE HAVE BEEN NO FOREIGN OBJECTS FOUND IN THE AFFECTED TIRES AND ASSY PRACTICES HAVE BEEN OBSER VED TO ENSURE CORRECT PROCEDURES ARE BEING FOLLOWED. TUBES ARE PURCHASED FROM A VARIETY OF SUPPLIERS AND ORIGINATE IN DI FFERENT COUNTRIES. (TC NR 20080418003) 20080521 2008 5 21 CA080418004 4 20080417 G 6113 VT2E16231 PLATE DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL PROP SPINNER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 35 (CAN) RECEIVED A CALL REGARDING DAMAGE THAT OCCURRED TO THE PROP BACKING PLATED ON A TURBO BEAVER WE COMPLETED REG, C-FO EU. THIS DAMAGE IS THE RESULT OF OUR INSTALLATION OF OUR PROP POSITION TRANSMITTER MOD STCSA 98-46, VT2E 1623. IDENTIFI ED THE PROBLEM TO BE THE INCOMPATIBILITY BETWEEN THE PROP SPINNER BACKING AND OUR POSITION INDICATOR. THE BACKING PLATE IN QUESTION HAS A DIFFERENT PROFILE FROM THE ONES THAT WE HAVE SEEN BEFORE. COMPARED THIS PROBLEM BACKING PLATE TO OUR A /C AND THERE IS A BIG DIFFERENCE, OURS ALLOWS ALMOST .5 CLEARANCE AND THERE IS NO INTERFERENCE WITH THE CAM ROD THROUGH THE TOTAL MOTION. MFG NEEDS TO IDENTIFY THIS COMPATIBILITY ISSUE IN THE STC AND FOR THE INTERIM SEND OUT A SL TO THE O 1 H 7 1 3T 4 T A806 E4EA 6 C P15EA 20080521 SO 2008 5 21 CA080421001 1 20080408 G 3210 424052 COTTER PIN PIPER 7872331 PIPER PA44 PA44180 7104402 SO LYC O360 LO360E1A6 41514 EA HARTZL HCC2Y HCC2YR2 GL TORQUE LINK MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) COTTER PIN MISSING ON LT MLG TORQUE LINK DURING WALK AROUND. BOLT REMOVED AND FOUND DRY OF LUBRICATION, WHICH COU LD HAVE CAUSE NUT TO TURN AND SHEARING OF COTTER PIN. NEW BOLT INSTALLED AND LUBRICATED ON BOTH MAIN GEAR TORK LINKS. ( TC NR 20080421001) 1 L 7 2 3O 3 O A19S0 E286 5 C P920 20080521 NE 2008 5 21 CA080422002 2 20080417 G 7250 3053094CL BLADE BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL ENGINE DEFORMED W K NONE O OTHER IN INSP/MAINT 1 CA 820 (CAN) THE PILOTS NOTICE THAT THE ENGINE WAS RUNNING 50 DEGREES HOTTER THAN NORMAL. A HOT SECTION (HSI) WAS COMPLETED AND IT WAS FOUND THAT THE OLD SEGMENT 3053094CL WAS INSTALLED 820 HOURS BEFORE WITH A NEW WHEEL AND BLADES. THE SEGMENTS HA D DEFORMED AND THE CT BLADES HAD RUBBED AGAINST THE SEGMENTS CAUSING EXCESSIVE CLEARANCES. THIS WORK HAD BEEN DONE BY MF G. THE HOT SECTION WAS SENT BACK FOR WARRANTY CONSIDERATION . (TC NR 20080422002) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 20080522 2008 5 22 CA080422003 4 20080420 G 8300 COUPLER LKHEED 188 188A 5262602 WP ALLSN 501D 501D13 03004 GL ALLSN A6441 A6441FN606 GL ENG/GEARBOX UNKNOWN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING START SEQUENCE OF NR 4 ENGINE, IT WAS OBSERVED THAT RPM AND ACCELERATION CLIMBED TOO FAST, BEFORE LIGHT OFF , ENGINE START ABORTED AND FOUND ENGINE DECOUPLED FROM GEARBOX. SUSPECT TORQUE SHAFT COUPLER (TC NR 20080422003) 2 L 7 4 4T 4 T RT 4A22 E282 6 C P898 20080522 NE 2008 5 22 CA080423003 2 20080421 G 7320 1520KDC0501 EEC BOMBDR BD700 BD7001A10 1390006 GL RROYCE BR700 BR700710A220 09500 NE ENGINE UNSERVICEABLE W O OTHER O OTHER CR CRUISE 1 CA (CAN) THE AIRCREW REPORTED THE FOLLOWING, AC WAS CRUISING AT FL450 AND CREW REALIZED THAT THE LT ENGINE SPOOLED DOWN TO IDLE WITHOUT PILOT INPUT. CREW ATTEMPTED TO MOVE THE THROTTLE IN EPR AND N1 MODE AND THERE WAS NO REACTION FROM THE LT E NGINE. EICAS MESSAGE (L FADEC FAULT) (CYAN) POSTED. CREW REQUESTED LOWER FLIGHT LEVEL AND LEVELED OFF AT FL370. APU WA S STARTED. THEY DESCENDED FURTHER TO FL290 AND SHUTDOWN THE LT ENGINE TO ATTEMPT A START AND RUN ON THE OPPOSITE ENGINE ELECTRONIC CONTROLLER (EEC) CHANNEL TO REGAIN LT ENGINE CONTROL. ENGINE WAS RESTARTED AND ALL LT ENGINE CONTROLS RETURN ED TO NORMAL OPERATING CONDITIONS. CREW DIVERTED, AS A PRECAUTIONARY MEASURE, IN ORDER TO HAVE THE AC EVALUATED AND REP 2 L 7 2 4F 4 F RT T00003NY E00061EN 20080521 NM 2008 5 21 CA080423004 1 20080416 G 5610 5893543130 WINDSCREEN BOEING 727 727260 138408K NM PWA JT8 JT8D17 52049 NE COCKPIT BURNED W H DEACTIVATE SYST/CIRCUITS A B FLAME/FIRE SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) AFTER COCKPIT SETUP SMOKE AND FLAME WAS OBSERVED BY THE FLIGHT CREW FROM THE TOP LT CORNER OF THE R1 WINDOW. WHEN THE R1 WINDOW HEAT WAS SELECTED OFF THE FLAME AND SMOKE CEASED. THE R1 WINDSCREEN WINDOW HEAT SYS WAS DEFERRED BY MAINT . UPON ARRIVAL AT THE DESTINATION THE R1 WINDOW WAS REPLACED AND THE R1 WINDOW HEAT CONTROLLER WAS ALSO REPLACED AS A PR ECAUTION. THE AC WAS RETURNED TO SERVICE. (TC NR 20080423004) 2 L 7 3 4F 4 F RT A3WE E2EA 20080521 NE 2008 5 21 CA080423011 2 20080330 G 7200 ENGINE CESSNA 500 500CESSNA 2076602 CE PWA JD15 JT15D1A NE MALFUNCTIONED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA (CAN) THE CREW REPORTED VIBRATIONS SHORTLY AFTER TAKEOFF AND WAS ATTEMPTING TO RETURN TO POINT OF DEPARTURE. THE AC CRAS HED. ALL ON BOARD WERE FATALLY INJURED. BOTH ENGINES SHOWED INDICATIONS CHARACTERISTIC OF THE ENGINES PRODUCING LOW POW ER OR WINDMILLING UNDER AIR LOADS AT THE TIME OF IMPACT. THERE WERE NO INDICATIONS OF ANY PRE-IMPACT ANOMALIES TO ANY OF THE COMPONENTS OBSERVED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 2 0080423011) 1 L 7 2 4F 4 F A22CE E25EA 20080521 NE 2008 5 21 CA080423012 2 20080417 G 7261 OIL SYSTEM AMD FALC50 FALCON2000 2730170 NM PWC PW306 PW306C 52169 NE ENGINE LEAKING W A UNSCHED LANDING K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, THE CREW NOTED OIL SMELL FOLLOWED BY VISIBLE VAPOR IN THE CABIN AIR AND OIL PRESSURE GAUGE FLUCTUAT IONS. THE FLIGHT WAS DIVERTED TO AN ALTERNATE LANDING SITE. THE ENGINE WAS SHUTDOWN FOLLOWING LANDING. OIL WAS OBSERVED INSIDE THE BYPASS DUCT AND FAN STATOR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLIS HED. (TC NR 20080423012) 2 L 7 2 4F 4 F RT A50NM E35NE 20080521 EA 2008 5 21 CA080423013 2 20080328 G 7321 FUEL CONTROL BEECH 90 E90 1152914 CE PWA PT6 PT6A28 EA ENGINE MALFUNCTIONED W O OTHER X ENGINE FLAMEOUT AP APPROACH 1 CA (CAN) DURING APPROACH, UPON RETARDING THE POWER LEVER TO IDLE, THE ENGINE ACCELERATED TO 90 PERCENT NG WITH AN ASSOCIATE D TEMPERATURE OF 800 DEGREES. THE PILOT ELECTED TO SHUTDOWN THE ENGINE AND FEATHER THE PROP. THE FUEL CONTROL WAS SUBSEQ UENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20080423013) 1 L 7 2 3T 4 T 3A20 E4EA 20080521 CE 2008 5 21 CA080423014 1 20080417 G 7500 LINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA ENGINE FRACTURED W E ENGINE SHUTDOWN J WARNING INDICATION NR NOT REPORTED 1 CA (CAN) OPERATOR REPORTS (2) EVENTS OF POWER LOSS FOLLOWED BY ENGINE SHUT DOWN. ONE EVENT APRIL 17, 2008, THE OTHER APRIL 18, 2008. BOTH CAUSED BY FRACTURE OF THE PY LINE. AIRCRAFT RETURNED TO SERVICE FOLLOWING 2ND REPLACEMENT OF THE PY LINE . (TC# 20080423014) 2 L 7 2 4T 4 T RT A24CE E4EA 20080522 NM 2008 5 22 CA080424001 1 20080418 G 2910 AE2463510E0124 FLEX LINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYD SYSTEM LEAKING W A UNSCHED LANDING K F FLUID LOSS FLT CONT AFFECTED CR CRUISE 1 CA (CAN) AFTER TAKEOFF WITH GEAR RETRACTON NR 2 HYD SYS QUANTIY DROPPED TO 2 QUARTS, THE CREW ELECTED TO RETURN TO THE AIRF IELD. DURING LANDING THE NR 2 HYD ISOLATION LIGHT CAME ON AND THE AC LOST THE OB SPOILERS, AND STEERING. THE AC WAS TOWE D TO THE HANGAR AND THE LEAK WAS TRACED TO THE NOSE GEAR PRESSURE LINE NEAR THE SWAGE. TT ON THIS PART IS UNDETERMINED. (TC NR 20080424001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080522 SO 2008 5 22 CA080424003 2 20080423 G 7414 10160844 BRUSHES BENDIX BL3492205 CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C93 GL MAGNETO MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 363 (CAN) LT ENGINE REPORTED DIFFICULT TO START. MAGNETO REMOVED AND BENCH TESTED, FOUND TO HAVE LOW AND INCONSISTENT OUTPUT . MAGNETO DISASSEMBLED FOR INSP AND FOUND CARBON BRUSH ASSY NOT INSTALLED IN DISTRIBUTOR GEAR. NO EVIDENCE OF BRUSH OR S PRING REMNANTS FOUND INSIDE OF MAGNETO. MAGNETO RE-ASSEMBLED WITH NEW BRUSH, BENCH TESTED IAW BENDIX OVERHAUL MANUAL X42 000-1. MAGNETO RE-INSTALLED ON ENGINE, ENGINE STARTS NORMAL. (TC NR 20080424003) 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 20080522 NE 2008 5 22 CA080424005 2 20080423 G 7420 90591507 IGNITION LEAD CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE LT ENGINE DEFECTIVE W K NONE O OTHER IN INSP/MAINT 1 CA 1971 (CAN) DURING ROUTINE INSP OF THE ENGINE, THE LT ENG OB IGNITER LEAD WAS FOUND DEFECTIVE. UPON REMOVAL OF IGNITER FROM LE AD, FOUND THE LEAD`S CENTER ELECTRICAL POST LOOSE AT IGNITER END. APPROX ONE INCH OF THE CENTER POST OF LEAD FEEL OUT W ITH CERAMIC INSULATOR AND NOTED BURNING MARKS AROUND WHERE THE CENTER CORE HAD BROKEN AWAY. LEAD REPLACED WITH NEW UNIT . (TC NR 20080424005) 2 L 7 2 4F 4 F RT A22CE E00053EN 20080522 NM 2008 5 22 CA080425002 1 20080421 G 2740 32EN614 WARNING SWITCH BOEING 727 72722C 138400F NM PWA JT8 JT8D7B 52053 NE LOWER STABILIZER CLOSED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) WHILE ATTEMPTING TAKEOFF, TAKEOFF WARNING INTERMITTENT, HORN SOUNDED UPON POWER LEVER ADVANCEMENT. TAKEOFF WAS ABO RTED AND AC RETURNED TO BLOCKS. TROUBLESHOOTING REVEALED THE LOWER HORIZONTAL STABILIZER TAKEOFF WARNING SWITCH WAS NOT CONTACTING ACTUATING CAM. THE SWITCH WAS FOUND TO BE HOLDING CLOSED DUE TO BINDING OF THE ROTARY SHAFT. FURTHER EXAMINAT ION REVEALED SHAFT HAD BEEN BENT. IT IS SPECULATED THAT ICE MAY HAVE BUILD UP ON THE SWITCH ACTUATION (STABILIZER) CAM. THE AC HAD JUST BEEN DE-ICED DUE TO SNOW ACCUMULATION PRIOR TO TAKEOFF ATTEMPT. THE SWITCH WAS REPLACED AND THE AC RETUR NED TO SERVICE. (TC NR 20080425002) 2 L 7 3 4F 4 F A3WE E2EA 20080522 NM 2008 5 22 CA080425006 1 20080425 G 5311 654653969 FRAME BOEING 737 737490 1384715 NM BS 616 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) VISUAL INSPECTION FOUND THAT INNER FRAME CHORD AT BS 616, RT, WL 200 AT STUB BEAM TO BE CRACKED. (TC NR 2008042500 6) 2 L 7 2 4F RT A16WE 20080522 NM 2008 5 22 CA080426001 1 20080423 G 8120 310440001 TURBOCHARGER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NR 1 ENGINE LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 44847 18251 (CAN) AFTER TAKEOFF, CREW HAD LOW OIL PRESSURE INDICATION ON THE NR1 ENGINE, CREW DID PRECAUTIONARY ENGINE SHUTDOWN AND ADVISED THEY WERE RETURNING. FLIGHT LANDED WITHOUT INCIDENT. MAINT INSPECTED THE ENGINE AND FOUND OIL COMING OUT OF LP O UTLET AND COVERING TOP OF THE ENGINE, ALSO FOUND SEAL DAMAGE . THE ENGINE WAS CLEANED, GROUND RUNS WERE C/O AT MAX POWER FOR 30 MIN TO SEE IF ANY SMOKE SMELL TO SHOW CONTAMINATED DUCTING AND TO SEE IF OIL IS STILL COMING OUT. LEAK FROM COMP RESSOR FOUND TO BE BEYOND LIMITS, ENGINE CHANGE TO BE C/O. TEARDOWN REPORT TO FOLLOW WHEN AVAILABLE. (TC NR 20080426001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080522 NM 2008 5 22 CA080428001 1 20080424 G 2761 CASE SMITHSIND DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ACTUATOR RUPTURED W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 49425 (CAN) WHEN TAXING INTO POSITION FOR TAKEOFF, THE CREW RECEIVED A NR1 HYD ISO VALVE AND A ROLL SPLR IB HYD CAUTION LIGHTS . THE AC RETURNED TO GATE AND A HYD LEAK WAS OBSERVED AT THE RT WING. FURTHER INVESTIGATION REVEALED THAT THE RT IB SPOI LER ACTUATOR CASING HAD RUPTURED AND CAUSED THE LEAK. THE ACTUATOR WAS REPLACED, ADJUSTED, LEAK CHECKED AND TESTED SERVI CEABLE. THE AC WAS RELEASED AND RETURNED INTO SERVICE. TSR: 1657:43 CSR: 1678 (TC NR 20080428001) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20080522 EA 2008 5 22 CA080428002 2 20080425 G 8530 05K21104 CYLINDER HEAD MOONEY M20 M20C 5870208 SW LYC O360 O360A1D 41514 EA MCAULY 2D34C 2D34C53 GL ENGINE CRACKED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA 440 (CAN) ON TAKEOFF PILOT FELT SLIGHT VIBRATION THROUGH RUDDER PEDALS. AFTER GETTING TO HIS CRUISE LEVEL THE VIBRATION GOT WORSE. HE RETURNED TO THE AIRPORT, AC WAS BROUGHT INTO MAINT SHOP AND COWLING WAS REMOVED. COMPRESSION TEST WAS COMPLETE D AND IT WAS FOUND THAT NR3 CYL NO COMPRESSION. CYL WAS REMOVED FROM ENGINE. FOUND THAT THERE WAS A HOLE BURNED UNDER TH E EXHAUST VALVE SEAT AND THERE WAS A PART OF THE EXHAUST VALVE MISSING. RECORDS INDICATE THAT AT ENGINE OVERHAUL THE EXH AUST VALVES AND SEATS WERE REPLACED. AME WONDERS IF WHEN THEY CHANGED THE SEAT THAT THEY MAY HAVE CRACKED THE CYL ALLOWI NG THE EXHAUST GASES TO BURN THROUGH THE CYL UNDER THE SEAT. (TC NR 20080428002) 1 L 7 1 3O 3 O 2A3 E286 5 C P7EA 20080522 NM 2008 5 22 CA080428005 1 20080421 G 3246 29685 BEARING BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R320 CR3204123F1 GL WHEEL ASSY FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 238 (CAN) DURING TAXI FOR DEPARTURE, THE AC FOLLOWING THE SUBJECT S/N 4168 AC, REPORTED (SMOKE AND FIRE) FROM THE RT GEAR. T HE F/A CONFIRMED. THE AC STOPPED AND PASSENGERS WERE EVACUATED ON THE TAXIWAY. INSP BY MAINT DETERMINED THE CAUSE TO BE A WHEEL BEARING FAILURE. THE WHEEL WAS REMOVED AND THE AC WAS TOWED TO THE HANGER. MAINT REPLACED THE MAIN WHEEL ASSY A ND THE AC RETURNED TO SERVICE. (TC NR 20080428005) 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P5NE 20081105 EU 2008 11 5 CA080507004 1 20080430 G 6420 FORK BOLKMS 117 BK117B2 5626013 EU LYC LTS101 LTS101750B1 41560 NE TAIL ROTOR BINDING W C R ABORTED TAKEOFF AUTOROTATION F FLT CONT AFFECTED AP APPROACH 1 CA 65 (CAN) ACFT WAS UNDERGOING A TEST FLIGHT FOR RADAR ALTIMETER TROUBLESHOOTING. 5 MINUTES INTO CRUISE FLIGHT, A SUDDEN VIBR ATION WAS INDUCED INTO AIRFRAME AND ALL FLIGHT CONTROLS. PILOT IMMEDIATELY RETURNED TO BASE FOR AN UNSCHEDULED LANDING W ITHOUT INCIDENT. UPON INSP OF ACFT, IT WAS FOUND THAT 1 TAIL ROTOR MOUNTING FORK WAS BINDING WHILE ATTEMPTING TO FEATHER BLADE. IT WAS ALSO NOTED THIS BLADE HAD NO AVAILABLE MOVEMENT IN THE FLAPPING AXIS. REMOVAL OF TAIL ROTOR INNER SLEEVE ASSY. REVEALED 1 OUTER BUSHING WAS PROTRUDING BEYOND THE INNER SLEEVE BY 1.80MM. INSPECTION OF THE MOUNTING FORK ALSO IN DICATED ABRASION MARKS ON THE INSIIDE WHERE THE DISLODGED BUSHING HAD COME INTO CONTACT. SUSPECT ACFT VIBRATION A RESULT 1 G 7 2 3U 3 U NC H13EU E5NE10 20081105 EU 2008 11 5 CA080508007 1 20080506 G 5610 350A25904320 WINDSHIELD UROCOP EC130 EC130B4 8680989 EU TMECA ARRIEL ARRIEL2B1 60056 NE COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1943 1943 (CAN) DURING INSP, A CRACK WAS FOUND IN THE UPPER LT CORNER OF THE PILOTS WINSHIELD. WINDSHIED HAS BEEN REPLACED. THIS I S THE 4TH WINDOW REPLACED ON THIS ACFT IN 1943 HRS. IAW CONVERSATIONS WITH THE MFR THE THICKNESS OF THE WINDOWS WILL BE INCREASED IN THE FUTURE. 1 G 7 2 3U 3 U H9EU E00054EN 20081105 WP 2008 11 5 CA080508020 1 20080428 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA 392 (CAN) ON START ACFT STARTER GEN DID NOT ENGAGE. 1 G 7 1 3O 3 O H11NM 1E4 20081105 NM 2008 11 5 CA080510002 1 20080102 G 6220 BEARING ROBSIN ROBSIN R22 R22BETAII 7640110 NM M/R HEAD WORN W K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 CA 2169 (CAN) PILOT REPORTED A LATERAL VIBRATION HAD BEEN PROGRESSIVELY GETTING WORSE OVER THE PAST WEEK. UPON VISUAL INSP OF TH E MAIN ROTOR HEAD THERE WAS A BLACK PASTE (SMOKING) AROUND ONE OF THE TEETER HINGE BEARINGS. AFTER REMOVING MAIN ROTOR H EAR IT WAS FOUND THAT THE THRUST WASHER HAD BEEN CHAFING THE OTBD FACE OF THE BEARING. THE MAIN ROTOR HEAD WAS REMOVED AND REPLACED WITH A SERVICABLE HEAD. (TC NR 20080510002) 1 G 7 1 3O H10WE 20081105 EU 2008 11 5 CA080513007 1 20080506 G 6320 332A3210073P TRANSMISSION SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU MAIN ROTOR MAKING METAL W A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 CA 2581 (CAN) TRANSMISSION CHIP LIGHT ILLUMINATION. FERROUS METAL CHIPS, WHISKERS AND FLAKES FOUND IN FILTER AND SUMP AND ON CHI P DETECTOR. 2 G 7 2 4U 4 U H4EU E12NE 20081105 WP 2008 11 5 CA080513008 1 20080506 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 1064 (CAN) DURING INSPECTION FOUND THE LT FWD SERVO LEAKING. (TC NR 20080513008) 1 G 7 1 3O 3 O H11NM 1E4 20081105 WP 2008 11 5 CA080514007 1 20080508 G 6510 SHAFT ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA COOLING FAN DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 473 (CAN) ON POST FLIGHT THE COOLING FAN WAS FOUND SPUN ON THE LOWER BEARING AND SHAFT ASSY. (ALIGNMENT MARK MISALIGNED) (TC NR 20080514007) 1 G 7 1 3O 3 O H11NM E295 20081105 SW 2008 11 5 CA080515002 1 20080515 G 6710 CYCLIC CONTROL BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA OBSTRUCTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFTER INSTALLATION OF THE VERTICAL REFERENCE SEAT KIT LISTED ABOVE, IT WAS DISCOVERED DURING FLIGHT CONTROL CLEARA NCE CHECKS THAT THE SEAT IN VARIOUS PLACEMENTS OF IT`S RANGE OF TRAVEL INTERFERED WITH THE FULL MOVEMENT OF THE CYCLIC F LIGHT CONTROL. INCLUDED WITH THIS REPORT IS A DOCUMENT WITH SOME PRELIMIARY APPROXIMATE VALUES AND PICTURES OF THE CLEAR ANCE AND INTERFERANCE THAT EXISTS. INSTALLATION OF THE SEAT KIT AS IAW AAL-292-035-001, UNDER STC APPROVAL NR SH 06-31 1 G 7 1 4U 4 U H4SW E22EA 20081105 SW 2008 11 5 CA080516003 1 20080513 G 6520 212040004103 GEARBOX BELL 412 412EP 1182205 SW PWA PT6T PT6T3 52045 EA TAIL ROTOR LEAKING W O OTHER K FLUID LOSS LD LANDING 1 CA 24 (CAN) 90 DEGREES, GEARBOX STARTED LEAKING AFTER 7.8 HOURS OF FLIGHT. UPON LANDING (TOTAL FLIGHT TIME OF 24.1 HOURS ON TH E HOURMETER),THE OIL LEVEL WAS CHECKED IN THE 90 DEGREE AND FOUND TO BE EMPTY, WITH OIL SPLASHED ALL OVER THE GEARBOX. T HE GEARBOX WAS FILLED WITH OIL TO THE NORMAL LEVEL AND THE ACFT WAS HOVERED FOR HALF AN HOUR AND CHECKED FOR LEAK, WHICH WAS CONFIRMED. THE OIL WAS LEAKING FROM THE PITCH CHANGE MECHANISM. THE OIL FILLER CAP WAS CHECKED FOR BLOCKAGE BUT WAS FOUND OK. 1 G 7 2 4U 4 U H4SW E22EA 20081105 EU 2008 11 5 CA080516013 1 20080515 G 6220 350A37116200 STOP SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE MAIN ROTOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 7162 (CAN) SUPPORT WAS FOUND BROKEN DURING THE AFTER LAST FLIGHT INSPECTION BY THE PILOT. NO SIGN OF FLIGHT CONTROL PROBLEM, VIBRATION OR NOISE WAS NOTICED. WORST CASE SCENARIO, IF THE DROOP RING GOT STUCK BETWEEN ONE BLADE AND THE MAST, IT COUL D BE FATAL SINCE ONLY (2) OUT OF (3) WAS KEEPING THE RING CENTERED. (TC NR 20080516013) 1 G 7 1 3U 3 U H9EU E19EU 20081105 SW 2008 11 5 CA080521002 1 20080513 G 6410 BEARING BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL T/R BLADE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1421 1421 (CAN) DURING THE 100 HR INSP A SMALL CRACK WAS FOUND ON THE INBD FEATHERING BEARING ON ONE OF THE TAIL ROTOR BLADES. CRA CK WAS NOTICED AS A BLACK LINE AT THE TOP OF THE BEARING. THIS IS A CRACK THAT WAS QUITE COMMON 10-15 YEARS AGO AND SEE MS TO HAVE RESURFACED. 1 G 7 1 3U 3 U H2SW E1GL 20081105 SW 2008 11 5 CA080521007 1 20080516 G 6310 206040270 CLUTCH BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL FREEWHEEL UNIT MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 1421 (CAN) NOISE FROM FREEWHEEL ON SPOOLDOWN, NO INDICATIONS ON CHIP PLUG. REMOVED FREEWHEEL ASSY AND FOUND CLUTCH NOT FULLY RELEASING. REPLACED FREEWHEEL ASSY. 1 G 7 1 3U 3 U H2SW E4CE 20081105 SW 2008 11 5 CA080523002 1 20080522 G 6220 AN17420 BOLT BELL 205 205A1 1181414 SW LYC T53 T5317BLYC 41616 NE STAB BAR DAMPER BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE PERFORMING ADI, AME DISCOVERED THAT A STAB BAR DAMPER TUBE ASSY P/N: 204-010-925-009 AND A DAMPER LEVER P/N: 212-010-301-001 WERE MISSING. IT APPEARS THAT THE TUBE ASSY UPPER BOLT P/N: AN174-20 BROKE OFF FIRST AND WAS THE CONTRI BUTING FACTOR OF THE DAMAGE. THE REMAINS OF SUBJECT BOLT (NUT WASHER AND SHANK WILL BE SENT FOR INVESTIGATION/ANALYSIS FOR POSSIBLE METAL FATIGUE AND/OR CORROSION. (REMAINS OF SUBJECT BOLT WERE STILL IN STAB BAR FRAME, INBOARD SIDE) STAB BAR DAMPER P/N: 204-010-937-009 WILL BE REPLACED AS A PRECAUTIONARY MEASURE AND SENT FOR INSVESTIGATION AS WELL FOR A PO SSIBLE INTERNAL FAILURE/SEIZURE WHICH MIGHT HAVE CONTRIBUTED TO SUBJECT BOLT FAILURE. STAB BAR DAMPER TUBE RIGGING FOR 1 G 7 1 4U 4 U H1SW E17EA 20081105 2008 11 5 CA080523005 4 20080516 G 2311 TK760HG TRANSCEIVER SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE UHF SYSTEM INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RADIO WOULD NOT TRANSMIT, REMOVED AND INSTALLED SERVICABLE RADIO. 1 G 7 1 3U 3 U NC H9EU E19EU 20081105 WP 2008 11 5 CA080523006 1 20080518 G 2432 RG2415 BATTERY ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MASTER LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 73 (CAN) DURING DI FOUND THE BATTERY LEAKING, REPLACED WITH A NEW ONE. 1 G 7 1 3O 3 O H11NM 1E4 20081105 GL 2008 11 5 CA080527002 2 20080521 G 7230 23057142 STATOR ALLSN BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL 6TH STAGE MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 3486 (CAN) COMPRESSOR ASSY WAS REMOVED FOR O/H, AT WHICH TIME IT WAS NOTED THE 6TH STAGE STATOR BAND WAS MISSING ONE BLADE, W ITH IMPACT DAMAGE NOTED ON OTHER BLADES ALSO IN THE 6TH BAND. NO DAMAGE NOTED FWD OF 6 TH STAGE. BURNER CAN REMOVED AND TURBINE INSPECTED FOR FOD, BUT NONE WAS FOUND. IT DID NOT APPEAR THAT THE STATOR WENT THROUGH THE ENGINE, HOWEVER, AT TH IS TIME, WE WERE UNABLE TO LOCATE THE DEPARTED BLADE. THE CRACK APPEARS RECENT, AND IT IS BELIEVED THE BLADE CRACKED IN THE LAST 100 HOURS OF OPERATION (TC NR 20080527002) 1 G 7 1 3U 3 U H2SW E4CE 20081105 SW 2008 11 5 CA080528003 1 20080523 G 5302 206032400027S RING BELL BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL TAIL BOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK FOUND ON TAIL BOOM RING DURING ROUTINE INSPECTION. 1 G 7 1 3U 3 U H2SW E1GL 20081105 SW 2008 11 5 CA080528004 1 20080523 G 5300 206031337003 FITTING BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK DETECTED ON FITTING DURING ROUTINE INSPECTION. 1 G 7 1 3U 3 U H2SW E1GL 20081105 SW 2008 11 5 CA080528007 1 20080525 G 5100 427065125111 SHROUD BELL 427 427 1182207 SW PWC PW207 PW207D NE FUSELAGE CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 3800 (CAN) OPERATOR REPORTED A MAIN ROTOR TRANSMISSION OIL LINE FAILURE. INSP REVEALED CHAFING DAMAGE TO THE OIL-LINE SHROUD ASSY FROM THE FIREWALL CLOSEOUT METAL EDGE. 1 G 7 1 3U 3 U R00001RC E42NE 20081105 2008 11 5 CA080528010 4 20080417 G 8300 23068295 GEARSHAFT ALLSN SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL GEARBOX CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE GEARBOX WAS RECEIVED FOR OVERHAUL. A CRACK WAS FOUND DURING THE MPI PROCESS AT THE REPAIR FACILITY. THERE ARE (2) THROUGH CRACKS IN THE REAR SEAL JOURNAL AREA OF THE POWER TAKEOFF GEARSHAFT. THE POWER TAKEOFF (PTO) GEAR IS SN CG 119988. (TC NR 20080528010) 1 G 7 2 3U 3 U H1NE E1GL 20081105 WP 2008 11 5 CA080528014 1 20080522 G 2822 D8187B PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYSTEM UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 609 (CAN) AUX FUEL PUMP UNSERVICEABLE, CHANGED OUT FUEL PUMP WITH A SERVICABLE ONE. (TC NR 20080528014) 1 G 7 1 3O 3 O H11NM 1E4 20081105 NE 2008 11 5 CA080530001 1 20080529 G 6730 S156520421041 SERVO SKRSKY S64 S64E 8142604 NE PWA JFTD12 JFTD12A4A 52047 NE MAIN ROTOR LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 4694 1156 (CAN) DURING A POST-FLIGHT INSP, MECHANIC FOUND MOVEMENT BETWEEN THE FORK AND PISTON. THE PRIMARY SERVO WAS REPLACED. A FTER DISASSEMBLY AT REPAIR STATION, IT WAS DISCOVERED THAT THE MOVEMENT WAS CAUSED BY THE BREAKDOWN OF A LAMINATED REPAI R SHIM INSTALLED BETWEEN THE FORK AND PISTON ROD, CAUSING THE LOSS OF TORQUE BETWEEN THE SERVO FORK AND PISTON ROD. SUB MITTING THIS SDR IAW OUR REPAIR STATION CANADIAN SUPPLEMENT. AN ASB 64B29-8 WAS RELEASED BY THE MFG, ON MAY 24, 2008 (T C NR 20080530001) 2 G 7 2 4U 4 U H4EA E15EA 20081106 EU 2008 11 6 CA080530003 1 20080528 G 6730 SC5083 SERVO SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE FLT CONTROLS WORN W A UNSCHED LANDING F FLT CONT AFFECTED HO HOVERING 1 CA 2895 2895 (CAN) STIFF FLIGHT CONTROLS IN ALL RANGE OF TRAVEL, IN HOVER, CRUISE, LANDING. 1 G 7 1 3U 3 U H9EU E19EU 20081229 NE 2008 12 29 CA080601001 2 20080521 G 7200 70BM035420 MODULE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE ENGINE NOISY W E ENGINE SHUTDOWN O OTHER TX TAXI/GRND HDL 1 CA 2955 2955 (CAN) SQEALING NOISE COMING FROM ENGINE. SHUTDOWN AFTER FLIGHT, SUSPECT TURBINE BLADE RUB. MODULE 2 AND MODULE 3 REMOV ED AND SENT TO MFG. 1 G 7 1 3U 3 U H9EU E19EU 20081106 2008 11 6 CA080602005 1 20080516 G 7810 3031988 EXHAUST DUCT PWA PT6 PT6A27 52043 EA ENGINE CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 13577 1220 (CAN) DAMAGED EXHAUST DUCT, PRIMARY FAILURE WAS TO THE INNER CONE OF THE EXHAUST DUCT, APPEARED TO CRACK AT NR 3 BEARING END AND EVENTUALLY DAMAGED THE T/E OF THE PT ROTOR BLADES. (TC NR 20080602005) 4 T E4EA 20081229 GL 2008 12 29 CA080603005 2 20080602 G 7314 PUMP HUGHES 369 369E 4470707 WP ALLSN 250C 250C20R2 GL FUEL MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) REINFORCED PAPER WIPERS LEFT IN THE FUEL TANK AFTER WORK CARRIED OUT. DURING A 300 HOUR INSP, THERE WAS SIGNIFICA NT FUZZ LIKE DEBRIS FOUND IN THE ENGINE DRIVEN FUEL PUMP FILTER THAT WAS A BLUISH COLOR. WHEN PICKING UP THE HELICOPTE R AT THE SERVICE CTR WHERE THE ACFT WAS DISASSEMBLED, INSPECTED, PAINTED AND REASSEMBLED, USED ONE OF THEIR SHOP TOWELS DURING THE ACCEPTANCE INSP. CALLED THE SERVICE CTR TO CONFIRM THAT THEY WERE USING THIS TYPE OF WIPER. THAT WAS VERIFIE D AS CORRECT. THE FUEL CELL WAS OPENED UP AND A LARGE INTACT WIPER WAS FOUND OVER THE START FUEL PUMP. A SECOND .5 PIECE WAS RECOVERED FROM THE FUEL CELL INTERCONNECT AREA. AN SMS REPORT WAS PREPARED AND OUR INTERNAL SAFETY TEAM IS NOW DOIN 1 G 7 1 3U 3 U H3WE E4CE 20081106 2008 11 6 CA080603006 1 20080528 G 5744 00100018273 HINGE BRACKET RT WING WORN W I CABIN DEPRESSURIZATION O OTHER IN INSP/MAINT 1 CA 1191 (CAN) REAR SPAR, RT LOWER WING AILERON, HINGE BRACKET INNER OUTER SHELL BECOMING LOOSE IN BEARING (REPLACED WITH NEW) (T C NR 20080603006) 20081106 CE 2008 11 6 CA080604005 1 20080530 G 2910 4529101067001 LINE LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP HYDRAULIC SYS CRACKED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 2614 (CAN) DURING CRUISE, THE ACFT EXPERIENCED A HYDRAULIC FAILURE. THE CREW DECLARED AN EMERGENCY, LANDING WITHOUT FLAPS. IN VESTIGATION REVEALED A KINK IN A HYDRAULIC SUPPLY LINE IN THE PYLON AREA OF THE LT ENGINE. A CRACK HAD FORMED IN THE KIN KED AREA AND THE FLUID WAS RELEASED FROM THE PRESSURIZED LINE. 2 L 7 2 4F 4 F RT T00008WI E6WE 20081106 SW 2008 11 6 CA080604011 1 20080528 G 5340 ATTACH FITTING BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE LIFT LINK CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE CONDUCTING A 25 HR INSP, A CRACK WAS NOTED ON THE LIFT LINK BEAM LUG. THE PART WAS REMOVED AND TT OF THE BEA M IS UNKNOWN AT THIS TIME. CRACK WAS FOUND ON THE AFT EAR OF LUG RT SIDE. 1 G 7 1 4U 4 U H1SW E17EA 20081106 NE 2008 11 6 CA080604013 2 20080603 G 7200 ENGINE CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B 30069 NE FLAMED OUT W A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) ACFT TOOKOFF AND ENGINE FLAMED OUT AT 41000 FT, ENGINE RESTARTED AT 25 000 FT AND LANDED SAFELY. ENG MFG WAS CALLE D AND OPERATOR INSTRUCTED TO DO POWER ASSURANCE. AT THE TIME ARCRAFT WAS AT IMC SOME 17NM OFF TRACK DIVERTING AROUND SO ME MODERATE INTENSITY RADAR RETURNS. RADAR PICTURE GAVE NO CAUSE FOR CONCERN WITH THE PATH WHICH WAS CHOSEN AND INDICAT ED THAT ACFT WAS WELL CLEAR OF THE CELLS. LIGHT TURBULENCE BEING EXPERIENCED IN CLOUD WAS NOT NOTEWORTHY AND COMMONPLACE FOR FLIGHTS IN THE REGION. HOWEVER UNEXPECTED UNPAINTED ACTIVITY WAS ENCOUNTERED AND IN CLOSE PROXIMITY TO A LIGHTENING FLASH FOLLOWED BY THE SOUND OF ICE PARTICLES IMPACTING THE ACFT, BUT THE TURBULENCE WAS STILL LIGHT. VERY SHORTLY AFTER 2 L 7 2 4F 4 F RT A21EA E15NE 20081106 EA 2008 11 6 CA080604016 1 20080602 G 5280 ROD CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B 30069 NE MLG DOOR OUT OF RIG W A UNSCHED LANDING E D VIBRATION/BUFFET INFLIGHT SEPARATION CL CLIMB 1 CA (CAN) UPON GEAR RETRACTION DURING TAKEOFF A RHYTHMIC THUMPING SOUND WAS HEARD COMING FROM THE NOSE AREA. A RETURN TO FIE LD WAS REQUESTED AND AN EMERGENCY DECLARED. NO EICAS MESSAGE WAS POSTED AND NOISE STOPPED WHEN GEAR SELECTED DOWN. LAND ING DONE WITHOUT ANY ISSUE. ACFT WAS PUT IN QUARANTINE FOR TEST ON GROUND AND FINDING OF THE ROOT CAUSE. AFTER TROUBLESH OOTING NOISE SUSPECTED TO BE COMING THE NOSE LANDING GEAR DOOR FUNCTIONAL TEST PROCEDURE FTP S604-323001 R RECHECKED FO R -DOOR MECHANISM RIGGING PARA 5.1.2 -GEAR MANUAL RELEASE PARA5.6.4 -LANDING GEAR FUNCTIONAL CHECK PARA 5.8 MINOR ADJU STMENT DONE TO R/H NOSE DOOR ACTUATING ROD SYS WAS CHECKED AND FOUND OK AND ACFT WAS RELEASED FOR FLIGHT TEST. 2 L 7 2 4F 4 F RT A21EA E15NE 20081106 SW 2008 11 6 CA080606002 1 20080603 G 6410 212010750113 BLADE BELL 205 205B SW LYC T53 T5313B 41549 NE TAIL ROTOR CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 573 (CAN) PILOT REPORTED PEDAL VIBRATIONS THROUGHOUT THE DAYS FLYING. AD-2008-10-03 CLEAN AND INSPECT T/R BLADES WAS SCHEDU LED FOR THE 25 HRS AME INSP PORTION OF THE AD AFTER THE DAYS FLYING. AME INSPECTED T/R BLADES AND DETERMINED ONE BLADE TO BE UNSERVICEABLE DUE TO POSSIBLE CRACK. THE SUSPECT DEFECT IS LOCATED AT A 45 DEGREE ANGLE ON/THRU THE MAIN SPAR APRO X .333 OF BLADE LENGTH OUT FROM THE ROOT. THE DEFECT IS APROX 2 INCHES IN LENGTH. T/R BLADE REPLACED WITH SERVICEABLE UN IT AND SENT FOR FURTHER INSP. THERE HAVE BEEN NO DAMAGE OR ABNORMAL INCIDENTS NOTED TO HAVE AFFECTED THE BLADE, AND THER E ARE NO INDICATIONS OF ANY IMPACT OR OTHER DAMAGE IN THE SUSPECT AREA. WILL SEND ADDITIONAL INFO AFTER INSPECT THE BLA 1 G 7 1 4U 4 U H1SW E17EA 20081106 SW 2008 11 6 CA080606004 1 20080604 G 2740 C200G3R SWITCH FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE STAB TRIM INTERMITTENT W A UNSCHED LANDING F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) LT SAS FAILED AND ALL STAB TRIM FUNCTIONS FAILED. MASTER DISCONNECT SWITCH REPLACED AND TEST FLIGHT CARRIED OUT SE RVICIBLE. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081106 SW 2008 11 6 CA080606005 1 20080516 G 3246 LM29749 BEARING FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33110UG 01514 WP MCAULY 4HFR34 4HFR34C652 NE LH NOSE WHEEL LACK OF LUBE W D RETURN TO BLOCK W INADEQUATE Q C TX TAXI/GRND HDL 1 CA (CAN) ON TAXI FOR DEPARTURE THE PILOT NOTICED A VIBRATION FROM THE NOSE GEAR. HE RETURNED AND MAINT FOUND LT NOSE WHEEL INNER BEARING SEAL WAS STICKING OUT FROM ITS SEAT. WHEEL BEARING WAS ALSO FOUND TO BE ROUGH TO THE (FEEL) AND WERE DRY. NOSE WHEEL ASSY REPLACED AND CHECKS CARRIED OUT SERVICIBLE. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081229 NE 2008 12 29 CA080606008 2 20080530 G 7321 350A57147620 CONTROL LEVER SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE FCU INCORRECT W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) GOVERNOR LEVER P/N 350A57-1476-20 WAS FOUND ON FCU WHERE LEVER P/N 350A57-1472-20 SHOULD HAVE BEEN. UPON CONFIRMAT ION WITH MFG THIS WAS CONFIMED. AS THIS ACFT CAME TO US, ON B2 S/N 1685 WE ASSUMED THAT THE INSTALLATION WAS CORRECT. TH E RIGGIN WAS WAY OUT AND WE COULD NOT REACH THE REQUIRED RPM. LEVER WAS REPLACED, RIGING WAS CARRIED OUT AND THE ACFT WA S RETURNED TO SERVICE. 1 G 7 1 3U 3 U H9EU E19EU 20081106 EU 2008 11 6 CA080608003 1 20080603 G 2752 NUT TALLEY 1251T100 BNORM BN2 BN2A26 1520226 EU LYC O540 O540E4C5 41532 EA HARTZL HCC2Y HCC2YK2 GL FLAP ACTUATOR STRIPPED W C ABORTED TAKEOFF O OTHER CL CLIMB 1 CA (CAN) DURING A TRAINING FLIGHT, ON OVERSHOOT FROM A ABORTED LANDING, FLAPS RETRACTED UN-COMMANDED. PILOT REDUCED POWER A ND WAS ABLE TO LAND STRAIGHT AHEAD ON REMAINING RUNWAY. INSPECTION FOUND THE FLAP ACTUATOR STRIPED. ACTUATOR WAS REMOVE D AND SENT FOR OVERHAUL. OVERHAUL FACILITY REPORT THAT THE STRIPPED BRASS NUT WAS MADE OF A SOFTER THAN STANDARD MATERI AL. THERE WAS IN EVIDENCE IN THE AVAILABLE LOGS OF THE TIME IN SERVICE SINCE NEW OR OVERHAULED. OVERHAULED ACTUATOR WAS RE-INSTALLED IN ACFT. 1 H 7 2 3O 3 O A17EU E295 5 C P920 20081106 SW 2008 11 6 CA080609004 1 20080603 G 2742 DL5040M6 ACTUATOR SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE PITCH TRIM UNRESPONSIVE W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA 6486 (CAN) SHORTLY AFTER DEPARTING, AND ACCELERATING THROUGH 200KTS, THE PITCH TRIM STOPPED RESPONDING. TRIM SONALERT WAS SOU NDING WHENEVER THE TRIM SWITCH WAS USED, HOWEVER THE TRIM GAUGE WAS NOT MOVING AND THE ACFT CERTAINLY WAS NOT TRIMMING. THIS WAS ATTEMPTED ON THE CAPTAIN AND F/O`S SIDE, AS WELL AS THE STANDBY TRIM SWITCH ON THE PEDESTAL. THE CREW REDUCED P OWER TO MAKE CONTROLLING THE A/C EASIER AND USED THEIR KNEES TO KEEP THE ACFT LEVEL AND CONTINUED. AS THE ACFT SLOWED FO R ARRIVAL, THROUGH ABOUT 180 KTS, THE TRIM BEGAN RESPONDING AGAIN. THE ACFT LANDED NORMALLY AND MAINT WAS INFORMED. MAI NT REPLACED THE PITCH TRIM ACTUATOR AND THE PROBLEM HAS NOT REOCCURRED. THE ACTUATOR WILL BE SENT FOR REPAIR/OVERHAUL AN 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 20081105 SW 2008 11 5 CA080609005 1 20080605 G 7500 27621009 TUBE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP BLEED AIR LEAKING W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 21639 (CAN) THE CREW OF THE ACFT REPORTED LOW POWER FROM THE NR 1 ENGINE. DURING THE COURSE OF TROUBLESHOOTING MX SUSPECTED A BLEED AIR LEAK CAUSED BY A CRACK IN THE BELLOWS FOR THE BLEED AIR LINE. THIS FLEXIBLE JOINT IS COVERED IN A WIRE HEAT SH IELD AND UPON CUTTING AWAY THE SHIELD TO INSPECT THE BELLOWS IT WAS DISCOVERED THAT THE LEAK WAS ORIGINATING FROM THE SE AM WHERE THE BELLOWS ARE FITTED TO THE RIDGED TUBING. THIS PART WAS MANUFACTURED IN 1980 AND IS BELIEVED TO BE ORIGINAL EQUIPMENT. ANY DEFECT IN THIS AREA WOULD BE IMPOSSIBLE TO DETECT ON A VISUAL INSPECTION. 2 L 7 2 4T 4 T RT A8SW E4WE 20081106 SW 2008 11 6 CA080609006 1 20080531 G 2120 2784142007 DUCT SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE BLEED AIR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE INSP IT WAS DISCOVERED VISUALLY THAT A BLEED AIR LINE TO THE HEAT EXCHANGER OF THE AIR CYCLE MACH INE HAD CRACKED 2 INCHES, ABOUT ONE THIRD THE CIRCUMFERENCE OF THE TUBE. 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 20081106 EA 2008 11 6 CA080609007 1 20080606 G 2751 601R590141 DETECTOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FALSE ACTIVATION W O OTHER N FALSE WARNING AP APPROACH 1 CA 9197 9197 (CAN) ON APPROACH CREW RECEIVED `FLAPS DEGRADED` MESSAGE ON EICAS, WHEN FLAPS SELECTED TO 45DEG, FLAPS CONTINUED TO SELE CTED 45DEG POSITION. AFTER LANDING WHEN SELECTING FLAPS UP, CREW RECEIVED `FLAP FAIL’ MESSAGE AND FLAPS REMAINED AT 43DE G. MAINT OBTAINED FAULT CODES INDICATING SKEW DETECTION ISSUE. FLAPS RESET AND ACFT FERRIED TO MAINT BASE. MAINT INSP FO UND NO OBVIOUS FAULTS AND FLAP OPERATION NORMAL. SKEW DETECTOR BOX REMOVED AND REPLACED WITH DUMMY BOX. ACFT RETURNED TO SERVICE UNDER MEL FOR FLAP SKEW DETECTION UNSERVICEABLE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081106 EU 2008 11 6 CA080609009 1 20080604 G 5753 13760B462 ATTACH FITTING BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33110UG 01514 WP ROTOL R333 R333482F12 GL FLAP SYSTEM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE CARRYING OUT A 7 DAY SERVICE CHECK, TECH FOUND 3 FLAP TO SLAT ATTACHEMENT CLEATS, P/N`S 137201B88, 137202B62 AND 137203B57 WERE FOUND TO BE CRACKED. THE FLAP SECTION WAS REMOVED AND A SERVICEABLE UNIT INSTALLED. FUNCTION CHECKS CARRIED OUT WITH NO FAULTS FOUND AND THE ACFT RELEASED TO SERVICE. THIS IS A KNOWN FAULT WITH THE BAE 3112 ACFT. 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C P61GL 20081106 SW 2008 11 6 CA080610001 1 20080609 G 6230 206010467105 LEVER BELL 206 206B 1181511 SW SWASHPLATE MISMARKED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) MFG HAS BEEN MADE AWARE THAT A QUANTITY OF 94 LEVER ASEMBLIES HAVE BEEN MIS-IDENTIFIED AS -107 INSTEAD OF -105 AS REQUIRED BY ENGINEERING DRAWING NOTE. -105 IS A TIME LIFED COMPONENT AND GOVERNED BY MM CHAPTER 4 , -107 IS NOT. 1 G 7 1 3U H2SW 20081106 2008 11 6 CA080610003 1 20080609 G 5751 25W181001501 SKIN LT AILERON DELAMINATED W O OTHER O OTHER DE DESCENT 1 CA 4411 (CAN) WHILE ON DECENT THROUGH 32,000 FT ENROUTE A MUFFLED BANG WAS HEARD BY THE CREW OF THE ACFT. AFTER A REVIEW OF THE ACFT INDICATIONS AND HANDLING AND GENERAL CONDITION, IT WAS UNCERTAIN WHERE THE NOISE HAD COME FROM. IT HAD BEEN THOUGHT THAT IT MAY HAVE BEEN A CABIN SLIDING DOOR. NO PROBLEMS WERE ENCOUNTERED ON THE APPROACH OR LANDING. MAINT DURING A POS T FLIGHT WALK AROUND FOUND THE LT AILERON UPPER SURFACE DELAMINATING FROM THE HONEYCOMB STRUCTURE FROM ABOUT HALFWAY OUT THE AILERON TO THE INBD EDGE. REPLACEMENT AILERON ON ORDER AND THE DAMAGED ONE WILL BE SENT FOR FURTHER INVESTIGATION. 20081106 EA 2008 11 6 CA080611001 1 20080524 G 2997 M2750012MW3U00 WIRE CNDAIR CL600 CL600* 1900302 EA HYD SYSTEM DAMAGED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) WHILE RUNNING ACFT HYDRAULIC SYS IN HANGAR FOR CONTROL SYS FUNCTIONAL CHECKS, AN AUDIBLE BANG WAS HEARD FROM THE B ACK OF THE CABIN, ALONG WITH A FLASH. (INTERIOR IS REMOVED). CIRCUIT BREAKER FOR HYDRAULIC SYS NR1 (B161) POPPED SHORTLY AFTER THIS OCCURRENCE. UPON INVESTIGATION FOUND DAMAGE WIRE HARNESS BELOW FLOORBOARD AT FS520 BETWEEN BL19 AND BL27. WI RES AFFECTED ARE: HYDR SYS NR1 TRIPLE TWISTED ALL ARE ARCED AND SEVERED: DB93A12WHT, DB94A12BIU, DB95A12ORN, HYDRAULIC SYS NR2 TRIPLE TWISTED INSULATION IS DAMAGED AND MELTED: DB81A12WHT, DB82A12BIU, DB83A12ORN - HYDRAULIC SYSTEM NR3 TRIPL E TWISTED SOOT ON THE WIRE INSULATION WIRES CABLE P/N M27500-12MW3U00 IS KAPTON WIRE. 2 L 7 2 4F RT A21EA 20081106 SW 2008 11 6 CA080611002 1 20080318 G 6220 C807382 BEARING RACE BELL 206 206L4 1182110 SW ALLSN 250C 250C30P 03013 GL PUSH-PULL FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA 5059 (CAN) THE PUSH-PULL CONTROL ASSY CENTER RACE FRACTURED AS A RESULT OF FATIQUE. THE FRACTURE OCCURED NEAR WHERE THE ASSY WAS LOCATED IN AN INSTALLATION-INDUCED BEND RADIUS. 1 G 7 1 3U 3 U NC H2SW E1GL 20081106 SW 2008 11 6 CA080611003 1 20080606 G 2820 412061634105 VENT LINE BELL 412 412 1182202 SW FUEL SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 2307 (CAN) FOUND RT FUEL VENT LINE P/N 412-061-634-105 HAS RUB MARK AT WL 41. LENGTH 0.700X0.100. LOCATION: RT DOOR POST PANE L. CUT MADE WITH SHARP EDGE OF BOTTOM FOOT DOOR. 1 G 7 2 4U H4SW 20081106 GL 2008 11 6 CA080611005 1 20080609 G 5551 BSFS159160 ATTACH BRACKET DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN1 52008 NE HORIZONTAL STAB WORN W K NONE O OTHER IN INSP/MAINT 1 CA 692 (CAN) DURING ANNUAL INSP WITH AN AOG AIR SUPPORT WING ANGLE INSTALLED MODIFICATION, MOVEMENT WAS FOUND IN THE HORIZONTAL STABILIZER FWD ATTACH POINTS. THE HORIZONTAL STABILIZER FWD ATTACH BRACKETS WERE REMOVED AND INSPECTED AND IT APPEARS T HAT THE FUSELAGE FITTING WAS WEARING INTO THE HORIZONTAL STABILIZER ATTACH FITTING (PN BSFS-159/160). 1 H 7 1 3R 3 R RC A806 5E1 20081230 NE 2008 12 30 CA080611006 2 20080525 G 7200 0292005220 ENGINE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE MAKING METAL W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 8428 (CAN) WHILE DOING AIRBORNE SURVEY WORK (BIRD TOWING), ENGINE CHIP LIGHT ILLUMINATED. HELICOPTER DESCENDED TO VALLEY BOTT OM AND MADE A PRECAUTIONARY LANDING. UPON LANDING, THE ENGINE MOMENTARILY DECELLERATED AND THEN RE-ACCELERATED. ENGINE WAS SHUTDOWN AND RAPIDLY DECELERATED ACOMPANIED BY A GRINDING/RUBBING NOISE. POST FLIGHT INSPECTION REVEALED A LARGE AMO UNT OF METAL CHIPS ON THE ENGINE CHIP PLUGS. ENGINE REMOVED AND SENT TO MFG FOR FURTHER INVESTIGATION. 1 G 7 1 3U 3 U H9EU E19EU 20081106 WP 2008 11 6 CA080611007 2 20080610 G 7200 31080981 BEARING FRCHLD SA227 SA227CC 3377522 SW GARRTT TPE331 TPE33110 01514 WP MCAULY 4HFR34 4HFR34C652 NE ENGINE SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 13 (CAN) THE REAR TURBINE WAS FOUND WITH HEAVY SPALLING, GALLING, HEAVY SCORING AND MISSING MATERIAL OFF THE OUTER RACEWAY AND ON THE ROLLING ELEMENTS. THE BEARING HAD ONLY 12.5 HOURS SINCE NEW/CAM. THE ENGINE WAS MAKING A STRANGE GRINDING SOU ND THAT WAS NOTICED BY LINE MAINT. ANOTHER REAR TURBINE BEARING FAILED ON ENGINE P44436C INSTALLED ON AC. THE BEARING O NLY HAD 16.4 HOURS ON IT. INVESTIGATION CARRIED OUT AND BOTH BEARING WERE RECIEVED ON THE SAME PO. THE PO CAME IN WITH 4 BEARING, ANOTHER ONE DISCOVERED ROUGH TO SPIN IN INVENTORY. REMOVED REMAINING 4TH BEARING FROM OUR SYS. MFG CONTACTED I N REGARDS OT THE SITUATION POINTING TOWARDS BAD BATCH. MFG IS RESEARCHING THE PROBLEM. ALL CONTACTED TO ASSIST IN PROBL 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081106 SW 2008 11 6 CA080611009 1 20080605 G 3246 31418A BEARING SEAL FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE NLG WHEEL DISPLACED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A PREFLIGHT WALK AROUND OF THE ACFT THE INNER BEARING SEAL OF THE RT NOSE WHEEL ASSY WAS NOTED TO BE DISPLA CED SO THAT ONE SIDE OF THE SEAL WAS RIDING UP ON THE HUB AND THE OPPOSITE SIDE WAS IN TOWARD THE AXLE TO THE EXTENT THA T THE BEARING ROLLERS WERE VISIBLE. NOSE WHEEL ASSY REPLACED AND ACFT RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081106 SW 2008 11 6 CA080611010 1 20080610 G 3246 LM299710 BEARING RACE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE3311 01514 WP MCAULY 4HFR34 4HFR34C652 NE NOSE WHEEL DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE INNER SEAL WAS NOTED TO BE PROTRUDING MORE THAN NORMAL. WHEEL ASSY WAS REMOVED AND THE INNER RACE WAS FOUND TO NOT BE SEATED ALL THE WAY. SERVICEABLE WHEEL ASSY WAS INSTALLED ON THE ACFT AND ACFT RETURNED TO SERVICE. 2 L 7 2 4T 3 T RT A8SW E3WE 6 C 3PNE 20081106 EA 2008 11 6 CA080612001 1 20080611 G 5753 600143023 VANE BOMBDR CNDAIR CL600 CL600* 1900302 EA GE CF34 CF348E5A1 30062 NE TE FLAP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A DAILY INSPECTION, THE LT INBD FLAP VANE WAS FOUND CRACKED ON THE UPPER SURFACE. THE CRACK IS APPROXIMATEL Y 2 INCHES LONG. FLAP TO BE REMOVED AND SENT OUT FOR FLAP VANE REPLACEMENT. LOANER FLAP TO BE INSTALLED. 2 L 7 2 4F 4 F RT A21EA E00063EN 20081113 NE 2008 11 13 CA080612002 2 20080605 G 7200 ENGINE PWC PW615 PW615FA 52282 NE MALFUNCTIONED W E ENGINE SHUTDOWN J WARNING INDICATION LD LANDING 1 CA (CAN) DURING LANDING TOUCHDOWN AND BRAKING, BOTH ENGINES REPORTEDLY INCREASED UNCOMMANDED TO FULL POWER. CREW ABORTED LA NDING AND PERFORMED A GO-AROUND. DURING BASE LEG, TO CONTAIN AIRSPEED CREW SHUT DOWN RT ENGINE AND AT THIS TIME THE LT E NGINE POWER REDUCED TO FLIGHT IDLE, UNCOMMANDED WITH NO THROTTLE RESPONSE. CREW PERFORMED A LANDING WITH NO INJURES. THE ACFT SUSTAINED 2 BLOWN TIRES. ON SITE INVESTIGATION, DATA DOWNLOADS AND ANALYSIS INDICATES AN ISSUE WITH THE THROTTLE Q UADRANT. THE CAS MSGS AND EVENTS REPORTED BY THE FLIGHT CREW WERE DUPLICATED DURING SIMULATION TESTING. THE NTSB HAS RET AINED THE QUADRANT FOR FURTHER INVESTIGATION. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE 4 F E00073EN 20081106 EA 2008 11 6 CA080612003 1 20080612 G 2820 C6PF1034105 LINE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA FUEL SYSTEM MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) A NEW FUEL TUBE ASSY WAS TO BE INSTALLED BETWEEN FUEL CELL NR 4 AND NR 6. THE INSTALLER FOUND THE TUBE ASSEMBLY TO BE .7500 INCHES TOO SHORT FOR THE LOCATION. 1 H 7 2 3T 4 T RT A9EA E4EA 20081106 EA 2008 11 6 CA080612004 1 20080612 G 2820 C6PF103479 LINE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA FUEL SYS MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) A NEW FUEL TUBE ASSY WAS TO BE INSTALLED BETWEEN FUEL CELL NR 5 AND NR 8 AS PART OF THE MOTIVE FLOW SYS. THE INSTA LLER FOUND THE TUBE ASSY TO BE ONE INCH TOO LONG FOR THE LOCATION. 1 H 7 2 3T 4 T RT A9EA E4EA 20081106 NE 2008 11 6 CA080612005 2 20080612 G 7414 BEARING ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 453 MAG RECEIVED FOR 500 HOUR INSP. BEFORE DISASSEMBLY 0.003 INCH OF END PLAY WAS NOTICED AT THE ROTOR. THIS WAS A FACTORY N EW MAG. MFG REQUIRES 0.0005 TO 0.0015 INCH END PLAY AT ASSY. THE MAG BEARINGS WERE INSPECTED FOR DAMAGE AND NONE WAS FOU ND. THE BEARINGS WERE PROPERLY SHIMMED DURING THE 500 HOUR INSP AND THE MAG WAS RETURNED TO SERVICE. 1 G 7 1 3O 3 O H11NM 1E4 20081106 NE 2008 11 6 CA080612006 2 20080612 G 7414 BEARING BENDIX ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 501 (CAN) MAG WAS RECEIVED FOR A 500 HOUR INSP BEFORE DISASSEMBLY 0.004 INCH OF END PLAY WAS NOTICED AT THE ROTOR. THIS WAS A FACTORY NEW MAGNETO. REQUIRES 0.0005 TO 0.0015 INCH END PLAY AT ASSY. THE MAG BEARINGS WERE INSPECTED FOR DAMAGE AND N ONE WAS FOUND. THE BEARINGS WERE PROPERLY SHIMMED DURING THE 500 HOUR INSPECTION AND THE MAG WAS RETURNED TO SERVICE. 1 G 7 1 3O 3 O H11NM 1E4 20081106 2008 11 6 CA080612007 2 20080612 G 7414 BEARING MAGNETO LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) MAG WAS SOLD TO A CUSTOMER AS AN EXCHANGE UNIT. WHEN INSTALLING THE CUSTOMERS MAGNETO DRIVE 0.004 INCH OF END PLAY WAS NOTICED AT THE ROTOR. MFG REQUIRES 0.0005 TO 0.0015 INCH END PLAY AT ASSY. THIS WAS A FACTORY REBUILT MAGNETO. THE MAG WAS REPAIRED BY PROPERLY SHIMMING THE BEARINGS AND RETURNED TO SERVICE. 20081113 CE 2008 11 13 CA080613004 1 20080605 G 3250 AN310A BOLT CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA COCKPIT MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LEFT RUDDER PEDAL SYSTEM INSPECTED TO VERIFY CLEARANCE BETWEEN THE BOLT AND NUT HOLDING THE BRAKE BELLCRANK LOCATE D BESIDE THE RIGHT RUDDER PEDAL ARM BAR ON THE PILOT SIDE AND THE NOSE GEAR STEERING ARM TUBE ATTACHMENT. BOLT WASHER AN D NUT REPOSITIONED TO ALLOW CLEARANCE. MINOR INTERFERENCE NOTED PRIOR TO REPOSITIONING. INSPECTION CARRIED OUT AFTER FIN DINGS AS DESCRIBED IN SDR 20080613002 (TC# 20080613004) 1 H 7 1 3O 3 O NT 3A12 E274 20081106 CE 2008 11 6 CA080613005 1 20080604 G 2720 AN310A BOLT CESSNA CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL RUDDER PEDAL MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) LT RUDDER PEDAL SYS INSPECTED TO VERIFY CLEARANCE BETWEEN THE BOLT AND NUT HOLDING THE BRAKE BELLCRANK LOCATED BES IDE THE RT RUDDER PEDAL ARM BAR ON THE PILOT SIDE AND THE NOSE GEAR STEERING ARM TUBE ATTACHMENT. BOLT WASHER AND NUT RE POSITIONED TO ALLOW CLEARANCE. MINOR INTERFERENCE NOTED PRIOR TO REPOSITIONING. INSP CARRIED OUT AFTER FINDINGS AS DESCR IBED IN SDR 20080613002. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20081106 SW 2008 11 6 CA080613007 1 20080605 G 3000 2719156003 TRANSDUCER FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP DE ICE SYSTEM DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 6918 (CAN) PILOT REPORTED DEICE PRESSURE GAUGE UNSERVICEABLE. DURING TROUBLESHOOTING MAINT FOUND THE DEICE PRESSURE TRANSDUCE R CONTAMINATED WITH WATER. 2 L 7 2 4T 4 T RT A18SW E4WE 20081106 WP 2008 11 6 CA080613009 1 20080603 G 2435 BC3151004 STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INTERMITTENT W O OTHER O OTHER NR NOT REPORTED 1 CA 824 (CAN) STARTER INTERMITTENT. 1 G 7 1 3O 3 O H11NM 1E4 20081106 CE 2008 11 6 CA080613010 1 20080611 G 6120 A3495 LOCK PLATE MTSBSI MU2 MU2B60 5780460 CE GARRTT TPE331 TPE33110 01514 WP HARTZL HCB4T HCB4TN5 GL PROPELLER WORN W K NONE O OTHER IN INSP/MAINT 1 CA 99 99 (CAN) DURING A ROUTINE PROP INSP, IT WAS FOUND THAT THE PITCH LOCK PLATE ALLOWS THE LATCH PIN TO SLIP OFF THE EDGE AND C OULD JAM THE PIN. THIS COULD PREVENT IN FIGHT ENGINE START. 1 H 7 2 3T 4 T RT A10SW E4WE 6 C P40EA 20081106 SW 2008 11 6 CA080614001 1 20080612 G 2910 LINE BELL 205 205A1 1181414 SW LYC T53 T5317BLYC 41616 NE HYD SYSTEM LEAKING W A UNSCHED LANDING K F FLUID LOSS FLT CONT AFFECTED HO HOVERING 1 CA (CAN) THE PILOT WAS FLYING THE HELICOPTER WHEN THE COLLECTIVE BECAME STIFF TO MOVE. THE PILOT RELEASED THE LOAD AND NR 2 HYDR SYS HAD FAILED. THE PILOT LANDED THE ACFT. IT WAS FOUND THAT NR 2 HYD SYS HAD LOST ALL IT`S FLUID DUE TO A HYDRAUL IC LINE HAD CHAFED THROUGH CREATING A HOLE. MORE DETAILS ARE COMING. 1 G 7 1 4U 4 U H1SW E17EA 20081106 NE 2008 11 6 CA080616001 2 20080611 G 7250 TURBINE PWA PW120 PW123 NE ENGINE OUT OF BALANCE W O OTHER E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 18667 10033 (CAN) EI PW100 2008-059 - VIBRATIONS DURING START, IT HAS BEEN DETERMINED THAT THE POWER TURBINE WAS OUT OF BALANCE THUS CAUSING THIS EVENT. (PRE SB21737) 4 T E20NE 20081105 EU 2008 11 5 CA080616002 1 20080611 G 2820 5282412189 LINE PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE FUEL SYS CORRODED W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) MX FOUND FUEL LEAKING FROM CENTER BELLY PANEL AND DURING INVESTIGATION FOUND A CORRODED FUEL LINE. 1 L 7 1 3T 4 T RT A78EU E26NE 20081106 CE 2008 11 6 CA080616003 1 20080611 G 2612 24418922 FIRE LOOP CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL NACELLE LOOSE W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 13987 13987 (CAN) ENGINE FIRE WARNING INDICATION CAME ON IN FLIGHT. THE ENGINE WAS REPLACED THE PREVIOUS DAY AND THE FIRE WIRE MAY H AVE BEEN DISTURBED AT THAT TIME. THE PILOT LANDED AND THE FIRE WIRE WAS REPLACED AND CHECKED SERVICEABLE. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20081106 EA 2008 11 6 CA080616004 1 20080615 G 2750 860D10018 FCU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE FLAP SYSTEM UNSERVICEABLE W A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 CA (CAN) FLAP FAIL CAUTION MESSAGE ON FLAP RETRACTION. FLAPS WERE SELECTED FROM 8, 0 AND THE FLAP FAIL HAPPENED WITH FLAPS NOW INDICATING 0 ON EACH SIDE. A/C LANDED OVERWEIGHT DUE TO RETURNING WITH FLAP FAIL FDR DATA RETRIEVED AND CALCULATED LANDING VERTICAL SPEED TO BE AT MOST 300 FT/SEC. THIS IS WELL BELOW THE MAX ALLOWABLE OF 360 FT/SEC. NO HEAVY LANDING CH ECK REQUIRED. FECU SHOWS THAT FECU HAS FAILED. TECH OPS ACTION PLAN FOR THE INPUT TORQUE OF THE FLAP DRIVE SYS COMPLETED . NO FAULTS FOUND. WIRING FROM FECU TO FLAP HANDLE, LT AND RT BPSU`S RANG OUT AND ALL CHECKED OK. FECU REPLACED. GROUND TESTED SERVICEABLE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081106 EU 2008 11 6 CA080616005 1 20080611 G 2731 Z4244170000 CONTROL CABLE ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA ELEVATOR TAB FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 3800 (CAN) AFT ELEVATOR TRIM CABLE WAS DISCOVERED FRAYED DURING REGULARLY SCHEDULED MAINT. IT WAS SURMISED THAT FURTHER OPERA TION OF THE TRIM SYS WOULD HAVE LED TO SYS FAILURE BEFORE THE NEXT SCHEDULED INSPECTION. 1 L 7 1 3O 3 O 0 A76EU 1E10 20081106 CE 2008 11 6 CA080617001 1 20080610 G 5720 SUPPORT CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE SPEED BRAKES DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE OTBD HOLE IN THE SPEED BRAKE TRUNNION SUPPORT IS ABOUT .5 HOLE MISALIGNED WITH THE HOLE IN THE RIB WHERE THE U PPER OTBD AILERON CABLE PASSES THROUGH ON BOTH THE LT AND RT WING. THE AILERON CABLES WERE WORN AND HAD WORN INTO THE AF T SIDE OF THE HOLE IN THE TRUNNION SUPPORTS. REPAIR S-550-0699/04RD WAS ISSUED TO BLEND THE TRUNNION SUPPORT AND THE AIL ERON CABLES WERE REPLACED. 1 L 7 2 4F 4 F A22CE E1NE 20081106 CE 2008 11 6 CA080617002 1 20080418 G 5343 05430161 FITTING CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA NLG BROKEN W O OTHER O OTHER NR NOT REPORTED 1 CA 7960 (CAN) AS THE ACFT WAS TAKING OFF, THE NOSE GEAR COLLAPSED. THE ACFT WAS INSPECTED AND THE NOSE GEAR LOWER FITTING WAS FO UND BROKEN. IT IS UNDETERMINED AT THIS TIME IF THIS WAS A RESULT OF AN UNREPORTED HARD LANDING. RETAINED THE BROKEN PART TO CARRY OUT METALLURGY TESTS. 1 H 7 1 3O 3 O NT 3A12 1E10 20081106 NE 2008 11 6 CA080617003 2 20080607 G 8530 EXHAUST VALVE CNDAIR CL215 CL2151A10 1900320 EA PWA R2800 R2800CA3 52026 NE HAMSTD 43E 43E60 NE NR 9 CYLINDER FAILED W E ENGINE SHUTDOWN O OTHER CR CRUISE 1 CA 970 (CAN) DURING CRUISE, THE FLIGHT CREW HEARD THE NR1 ENGINE BACKFIRE. THE ENGINE WAS SHUTDOWN AND THE PROPELLER FEATHERED. DURING INVESTIGATION, THE MAINT CREW DISCOVERED THE EXHAUST VALVE IN CYL NR 9 HAD DROPPED INTO THE CYL. SOME PIECES OF THE VALVE WENT OUT THE EXHAUST PIPE. THE CYL WAS REPLACED, ENG GROUND RUN AND THE MAIN OIL SCREEN WAS INSPECTED. THE AC FT WAS RETURNED TO SERVICE. 2 H 7 2 4R 4 R RT A14EA 5E8 6 C P871 20081106 EU 2008 11 6 CA080617004 1 20080616 G 3040 SHAFT AIRBUS 310 A310300 3930305 EU GE CF6 CF680C2* GL WINDSHIELD WIPER SHEARED W O OTHER O OTHER LD LANDING 1 CA (CAN) ACFT ARRIVED AT GATE WITH CAPTAINS’ WINDSHIELD WIPER ASSEMBLY MISSING. FURTHER INVESTIGATION FOUND THAT CONVERTER SPLINED SHAFT HAD SHEARED OFF CAUSING THE WIPER ASSY TO DEPART ACFT WHILE TAXIING IN FROM LANDING TO APRON. WIPER ASSY W AS FOUND IN TAXIWAY. CONVERTER ASSY REPLACED. 2 L 7 2 4F 4 F RT A35EU E23EA 20081106 NM 2008 11 6 CA080618001 1 20080615 G 3233 AS11510K0330 HOSE BOEING 757 75728A 1384976 NM RROYCE RB211 RB211535E437 54555 NE MLG ACTUATOR LEAKING W O OTHER K FLUID LOSS NR NOT REPORTED 1 CA (CAN) LT TRUCK TILT ACTUATOR RETURN LINE FOUND LEAKING. 2 L 7 2 4F 4 F RT A2NM E12EU 20081230 SW 2008 12 30 CA080618002 1 20080616 G 2510 AAL292030001 SEAT FRAME BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA COCKPIT SEAT INTERFERENCE W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) DURING THE INSTALLATION OF VERTICAL REFERENCE SEAT KIT, IAW STC SH06-31, IT WAS DISCOVERED THAT THE CYCLIC FLIGHT CONTROL STICK IS INTERFERED WITH DUE TO THE SEAT NOW BEING POSITIONED FURTHER FWD AND ELEVATED BECAUSE OF THE KIT INSTAL LATION. AN ELEVATION OF THE INSTALLATION IS ATTACHED TO PROVIDE DETAILS OF THIS ISSUE. THE CYCLIC CONTROL STICK CONTACTS THE SEAT FRAME WHEN THE SEAT IS TILTED. THE CYCLIC CONTROL STICK IS NOT ABLE TO CONTACT THE CONTROL STOP WHEN THE SEAT IS IN THE TILTED POSITION. 1 G 7 1 4U 4 U H4SW E22EA 20081106 NE 2008 11 6 CA080618003 2 20080602 G 7261 SEAL PWA PT6 PT6A60 52043 NE NR 1 BEARING LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING ENG COMPRESSOR RECOVERY WASH, ENGINE OIL LOSS FROM NR 1 BEARING SEAL. MULTIPLE ENGINE SPOOLS ARE REQUIRED T O COMPLETE AN ENG COMPRESSOR RECOVERY WASH IAW ENG MFG. MAINT FOUND IN CARRYING OUT MULTIPLE ENGINE SPOOLS, INTERNAL ENG SCAVANGE PUMPS LOCATED IN THE AGB WERE NOT EFFICIENT ENOUGH THROUGH THE SPOOLING PROCESS AT LOW ENG SPEEDS TO SUCSESSFU LLY SCAVANGE ENOUGH ENGINE OIL OUT OF THE AGB TO AVOID AN OVER FILL CONDITION OF THE AGB. SCAVANGE PUMPS ARE DESIGNED TO TAKE THE USED ENGINE OIL FROM THE AGB AND RGB AND PUMP THE OIL BACK INTO THE MAIN ENGINE OIL RESERVOIR. MAINT FOUND DUR ING ENGINE SPOOLING ALONE, THE PUMPS COULD NOT KEEP THE OIL AT A SAFE LEVEL IN THE AGB IN ORDER TO AVOID THE OIL TO SEEP 4 T E4EA 20081106 NM 2008 11 6 CA080618004 1 20080613 G 5210 BACS12ER06K6 SCREW BOEING 737 737* NM GE CFM56 CFM567B24 NE PAX DOOR ARM MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 17134 17134 (CAN) L1 MAIN CABIN ENTRANCE DOOR WAS FOUND TO HAVE RESTRICTED OPERATION FOR OPENING AND CLOSING UPON ARRIVAL AT THE GAT E. GUIDE ARM LWR RADIUS LINK ATTACHING SCREW AND KEY WASHER WERE FOUND MISSING. PARTS REPLACED. SINCE THIS HAS OCCURRED RECENTLY ON ANOTHER ACFT IS PROCEEDING WITH A PRECAUTIONARY FLEET CAMPAIGN TO INSPECT THE L1 AND L2 DOOR HINGE ARM LINKS AND HARDWARE FOR CONDITION AND SECURITY. THIS WILL BE CARRIED OUT ON WJI’S ENTIRE FLEET OF 737 NGS AND SHOULD BE COMPLE TED WITHIN 90 DAYS OF THE CAMPAIGN DETAILS BEING FINALIZED. 2 L 7 2 4F 4 F RT A16WE E00055EN 20081106 NE 2008 11 6 CA080618005 2 20080616 G 7200 6018T30P14 BLADE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE ENGINE FAN BENT W O OTHER C F.O.D. NR NOT REPORTED 1 CA (CAN) FLIGHT INGESTED A BIRD INTO THE NR1 ENGINE ON APPROACH. MTC INSPECTED AND FOUND A BENT FAN BLADE. ACFT TAKEN OUT O F SERVICE FOR A FAN BLADE REPLACEMENT. THIS WAS REPORTED BY THE CREW PICKING UP THE ACFT FOR THE NEXT FLIGHT, AFTER THEI R WALK AROUND. BENT FAN BLADE FOUND ON THE NR 1 ENGINE AFTER EVIDENCE OF BIRD INGESTION REPORTED BY THE PILOT. ADVISES THAT THE BIRD WENT THROUGH THE CORE. CONTAMINATION FOUND THROUGHOUT THE COMPRESSOR. COMPRESSOR WASH REQUIRED. BLADE REPL ACEMENT IN PROGRESS. 2 L 7 2 4F 4 F RT A21EA E15NE 20081105 EA 2008 11 5 CA080618006 2 20080508 G 8530 LW16740 VALVE LYC LYC O540 TIO540A2C 41532 EA VALVE STEM ELONGATED W K NONE O OTHER IN INSP/MAINT 1 CA 2700 (CAN) VALVE STREACHED TO 6 THOU AND MANUFACTURES LIMITATION IS 2 THOU. CONCERN IS VALVE IS SODIUM FILLED AND WILL DISINT IGRATE IF THE STREACH IS BEYOND MANUFACTURES RECOMMENDATIONS. THE MAIN CONCERN IS THIS ENGINE IS ON CONDITION AND THE CY LINDERS ALL HAVE 2700 HOURS ON THEM AND IF ONE IS STREACHED THE QUESTION NOW IS ARE ALL THE VALVES STREACHED. THE POINT BEING IF YOU ARE WORKING ON AN AIRCRAFT THAT IS GOING ON CONDITION IT IS CLEAR THE VALVES NEED TO BE CHECKED BEFORE THE ENGINE GOES ON CONDITION. 3 O E14EA 20081105 EA 2008 11 5 CA080618007 2 20080602 G 8530 LW16703 CYLINDER LYC O235 O235L2C 41505 EA ENGINE CRACKED W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 CA 225 (CAN) THE LOWER SPARK PLUG HOLE ON CYLINDER NR 4 HAD A CRACK, THE ACFT HAD BEEN INSPECTED ON MAY 24/08 AND THERE WAS NO APPARENT CRACKS OR ISSUES WITH THE CYLINDER, ON JUNE 2 IT WAS RUNNING ROUGH AND BROUGHT TO MX, THERE WAS FOULING OF THE PLUGS AND WHEN THE PLUG WAS REMOVED THE FINE CRACK WAS NOTED. THE OTHER CYLINDERS WERE INSPECTED AND FOUND TO BE CLEAR O F ANY CRACKS. THIS ENGINE HAD BEEN OVERHAULED 225 HOURS PREVIOUSLY AND THE CYLINDERS WERE OVERHAULED AS WELL. THE RECORD S SHOWED THAT THE CYLINDERS WERE OVERHAULED AS PER MANUFACTURERS SPECIFICATIONS. WE WILL CONTINUE TO MONITOR THE OTHER C YLINDERS AND WILL REPORT ANY FUTURE ISSUES REGARDING THESE CYLINDERS. 3 O E223 20081105 EA 2008 11 5 CA080618008 2 20080604 G 7314 A10014044 PUMP PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA FUEL SYSTEM INOPERATIVE W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) WHEN POWER WAS APPLIED THE PUMP WOULD OPERATE UNLESS IT WAS TAPPED WITH A HAMMER. PUMP WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. WILL SUPPLY HOURS ON THE PUMP IN THE NEXT FEW DAYS. 1 L 7 2 3O 3 O A20SO E14EA 20081106 SO 2008 11 6 CA080618009 1 20080604 G 8120 BOLT KELLY PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL TURBOCHARGER MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 15 (CAN) DURING INSP IT WAS DISCOVERED THAT BOTH BOLTS SECURING THE TURBO TO THE UPPER TURBO SUPPORT HAD COME OUT. THE TURB O WAS LEAKING EXHAUST GASES FROM THE SEAM BETWEEN THE TURBINE HOUSING AND THE BEARING HOUSING. WILL SUPPLY HOURS OF THE TURBO THE NEXT FEW DAYS. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081106 EA 2008 11 6 CA080618010 1 20080602 G 5610 NP13932212 WINDSHIELD CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C5 30050 NE COCKPIT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT COCKPIT SIDE WINDOW SHATTERED WHILE SITTING AT THE GATE. REMOVED AND REPLACED THE RT COCKPIT SIDE WINDOW. 2 L 7 2 4F 4 F RT A21EA E00063EN 20081106 NM 2008 11 6 CA080619001 1 20080618 G 3220 BUSHING EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE NLG MIGRATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION, FOUND EVIDENCE OF BUSHING MIGRATED ON NLG RETRACK ACTUATOR , MAIN FITTING ASSY AND UPPER SHOCK STRUT ATTACHMENTS (PRC BROKEN). 2 L 7 2 4F 4 F RT A57NM E00070EN 20081106 2008 11 6 CA080619002 4 20080617 G 2565 101651303 SLIDE LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SLIDE UNIT`S HAVE BEEN DEVELOPING PROBLEMS WITH THE ADHESIVE HOLDING MANY OF THE SEAMS TOGETHER AS THEY AGE BEYOND THE 20 YEAR THRESHOLD. THERE HAVE BEEN SEVERAL INSTANCES WHERE SLIDE TUBES FROM UNITS MFG CIRCA 1984 HAVE RUPTURED UPON INFLATION TEST. MOST RECENTLY, A SLIDE MFG CIRCA 1986 (PN 101651-303, SN B51-325) SHOWED, UPON INFLATION TESTING, THAT MANY OF THE SEAMS HAVE BECOME COMPLETED DISBONDED IN AREAS SUCH AS THE CANOPY AS WELL AS IN BETWEEN THE MAIN UPPER AND L WR INFLATION TUBES. IT APPEARS THAT THE SLIDE UNITS, AS THEY AGE BEYOND 20 YEARS FROM DATE OF MFG, HAVE EXPONENTIALLY IN CREASING FAILURE RATES AS SHOWN WHEN BROUGHT INTO THE SHOP ENVIRONMENT FOR CHECK/OVERHAUL. ONE CAN ONLY ASSUME THAT FAIL 20081105 CE 2008 11 5 CA080619003 1 20080618 G 5343 AN35A BOLT CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE TRUNNION DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CARRIED OUT VISUAL INSPECTION AS PER CAMPAIGN FOUND 4 BOLTS INSTALLED AND WASHERS AND NUTS. REMOVED HARDWARE INSTA LLED NEW PARTS AS PER IPC 53-11-01 ITEM 109 AND 110. REPLACED ARM ASSY P/N 5565619-6 WITH NEW DUE DAMAGED AND NEW BOLT P /N NAS464P5LA28 DUE WORN. 1 L 7 2 4F 4 F A22CE E1NE 20081106 2008 11 6 CA080619004 4 20080418 G 6122 F624L GOVERNOR PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL PROPELLER MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 6 (CAN) AFTER INSTALLATION OF THE OVERHAULED GOVERNOR, THE TEST FLIGHT WAS CARRIED OUT AND THE ENGINE WAS OVER SPED. THE G OVERNOR WAS SENT BACK TO THE REPAIR FACILITY, THE FACILITY REPORTS NOTHING ABNORMAL. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081106 2008 11 6 CA080619005 4 20080619 G 8300 310625801 BEVEL GEAR PWA 120 PW120A NE ASSY GEARBOX MISMANUFACTURED W O OTHER W INADEQUATE Q C NR NOT REPORTED 1 CA (CAN) BEVEL GEAR P/N 3106258-01, S/N A0002WAB WAS FOUND TO BE NON-CONFORMING DUE TO MISSING POST PLATE BAKING OPERATION AFTER THE PART WAS SILVER PLATED. THIS PART WAS INTALLED IN ENGINE S/N 120673 WHICH WAS ALREADY SHIPPED TO THE CUSTOMER. THE CUSTOMER WAS INFORMED BY A LETTER TO RETURNED THE ENGINE WITHIN 60 HRS FLYING TIME IN ORDER TO REPLACED THE PART. 4 T E20NE 20081106 SO 2008 11 6 CA080619006 1 20080323 G 8120 4091709001 TURBOCHARGER PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL ENGINE FAILED W A UNSCHED LANDING E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 1 (CAN) AN OVERHAULED ENGINE COMPLETE WITH NEW TURBOCHARGER WAS INSTALLED. AFTER THE FIRST HOUR OF THE FLIGHT THE TURBOCHA RGER COMPLETELY FAILED. MAINT INSTALLED A NEW TURBOCHARGER AND ACFT RETURNED TO SERVICE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081106 CE 2008 11 6 CA080619007 1 20080617 G 5753 50160018 FLAP TRACK BEECH 100 A100A CE PWA PT6 PT6A28 EA MCAULY 4HFR34 4HFR34C762 NE TE FLAPS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A WALKAROUND THE PILOTS NOTICED EXCESSIVE PLAY ON THE RT OTBD FLAP AT THE INBD HINGE. THE FLAP WAS REMOVED FOR FURTHER INVESTIGATION AND THE INBD FLAP TRACK WAS FOUND TO BE CRACKED AT THE AFT END OF THE TRACK, THE CRACK WEAKEN THE TRACK ALLOWING IT TO SLIGHTLY BEND WITH THE FLIGHT LOADS. NO SECONDARY DAMAGE WAS FOUND. THE FLAP TRACK WAS REPLACED . AND THE ACFT RETURNED TO SERVICE. 1 L 7 2 3T 4 T A14CE E4EA 6 C 3PNE 20081106 EU 2008 11 6 CA080619008 1 20080506 G 2822 P94B12203C PUMP SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE FUEL BOOST INOPERATIVE W O OTHER J WARNING INDICATION CR CRUISE 1 CA 221 (CAN) BOOST PUMP FAILED IN FLIGHT, MOTOR STILL TURNING BUT NOT CREATING PRESSURE. SUSPECT SHEARED SHAFT OR DRIVE. 1 G 7 1 3U 3 U NC H9EU E19EU 20081106 WP 2008 11 6 CA080620002 1 20080615 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA 139 (CAN) STARTER WOULD NOT TURN OVER THE ENGINE, TROUBLESHOOTING REVEALED THE STARTER WOULD NOT ROTATE THE STARTER GEAR. 1 G 7 1 3O 3 O H11NM 1E4 20081106 GL 2008 11 6 CA080620004 1 20080618 G 5541 SPAR DHAV DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE RUDDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FRONT SPAR WAS FOUND CRACKED AFTER THE RUDDER WAS REMOVED FOR REPLACEMENT OF UPPER HINGE BEARING. FRETTING WAS NOT ICED AT BEARING BLOCK TO SPAR MOUNTING SURFACE/BEARING BLOCK WAS REMOVED AND CRACKS FROM THE (2) ATTACH HOLES WERE FOUND . 3 CRACKS FROM ONE HOLE EXTENDED BEYOND THE BEND OF THE FRONT SPAR. RUDDER REMOVED FROM SERVICE FOR REPAIR. 1 H 7 1 3R 3 R RC A806 5E1 20081106 GL 2008 11 6 CA080621001 2 20080611 G 7240 6870992 COMBUST CHAMBER ALLSN 250C 250C20B 03013 GL ENGINE CRACKED W K NONE M J OVER TEMP WARNING INDICATION IN INSP/MAINT 1 CA (CAN) ENGINE REPORTED HIGH OPERATING TEMP. ATTEMPTED POWER CHECK BUT NOTED 790 DEGREE TOT IN HOVER. ABORTED POWER CHECK UPON FURTHER VISUAL INSP FOUND RT ARM PIT CRACKED APPROX 5 INCH CRACK. 3 U E4CE 20081106 EA 2008 11 6 CA080622001 1 20080618 G 3230 750005000 SELECTOR VALVE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE MLG FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) CREW TRIED (4) TIMES TO GET THE MLG DOWN. THEY USED THE EMERGENCY FREE FALL, AND THE MAINS CAME DOWN. (THE NOSE WA S ALL READY DOWN. NO EMERGENCY WAS DECLARED.) CONTACTED REPAIR STATION TO PIN THE LANDING GEAR, AND MAKE READY FOR THE F ERRY FLIGHT. A/C TO FERRY FOR REPAIRS. REMOVED AND REPLACED THE MAIN LANDING SELECTOR VALVE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081106 NM 2008 11 6 CA080623001 1 20080424 G 3250 69355174 ROD END BOEING 737 737* NM PWA JT8 JT8D17 52049 NE STEERING TILLER WORN W O OTHER E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 18425 (CAN) MINOR BUT PERSISTENT VIBRATION COULD BE FELT IN THE STEERING TILLER DURING TAXI, PARTICULARLY AT HIGHER SPEEDS. 2 L 7 2 4F 4 F RT A16WE E2EA 20081106 CE 2008 11 6 CA080623002 1 20080619 G 3230 AA5C MOTOR MTSBSI MU2 MU2B60 5780460 CE GARRTT TPE331 TPE33110 01514 WP HARTZL HCB4T HCB4TN5 GL MLG INOPERATIVE W O OTHER J WARNING INDICATION LD LANDING 1 CA 954 954 (CAN) PILOT SELECTED GEAR DOWN THE DOOR MOTOR CIRCUIT BREAKER POPPED. MANUAL GEAR EXTENSION COMPLETED AND ACFT LANDED WI THOUT INCIDENT. MECHANIC DISPATCHED AND FOUND THE GEAR DOOR ACTUATOR/MOTOR UNSERVICEABLE. ACFT FERRIED TO MAINTENANCE BA SE, DOOR ACTUATOR/MOTOR REPLACED AND GEAR SWING COMPLETED. ACFT RETURNED TO SERVICE. 1 H 7 2 3T 4 T RT A10SW E4WE 6 C P40EA 20081106 EA 2008 11 6 CA080623003 2 20080514 G 8520 LW15628 SEAL PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL CRANKCASE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 98 (CAN) DURING 2 ROUTINE INSP OF THE ENGINE, IT WAS DISCOVERED THAT THE CRANKSEAL WAS LEAKING. A NEW SEAL WAS INSTALLED AT APPROXIMATLEY 50 HRS. THE NEXT SCHEDULED INSP CARRIED OUT AT 98 HRS REVEALED THE SEAL LEAKING AGAIN. THE ENGINE WAS STI LL UNDER WARRENTY AND IT WAS DECIDED TO REMOVE THE ENGINE FROM SERVICE AND INSTALL A NEW ONE. THE ENGINE OVERHAUL FACILI TY WAS REQUESTED TO PROVIDE A TEARDOWN REPORT AS A FOLLOW UP. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081106 EA 2008 11 6 CA080623004 1 20080620 G 5200 215260522 SHAFT CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE DOOR BROKEN W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA 4896 4896 (CAN) DURING AERIAL FIGHT FIGHTING OPERATIONS, THE PILOTS HEARD A LOUD BANG AFTER DROPPING THEIR LOAD OF WATER. THE "RT JACK READY" LIGHT WOULD NOT COME ON AS IT NORMALLY WOULD AFTER THE BOMB DOOR CYCLES AND LOCKS "CLOSED". THE PILOTS RETUR NED TO BASE IAW COMPANY SOPS. MAINT FOUND THAT THE BOMB DOOR CLOSING JACK MOUNTING SPIGOT WAS SHEARED AND THAT THE ACTUA TOR WAS HANGING FROM ITS HYDRAULIC LINES. NO OTHER DAMAGE WAS FOUND, THE SPIGOT WAS REPLACED, THE SYS FUNCTION-TESTED AI RWORTHY,AND THE ACFT RETURNED TO SERVICE. 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 20081114 EA 2008 11 14 CA080623005 1 20080620 G 5240 601R387271 UPLOCK CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE SERVICE DOOR CRACKED W O OTHER J WARNING INDICATION NR NOT REPORTED 1 CA (CAN) PILOT REPORTED THAT THE SERVICE DOOR MESSAGE WAS DISPLAYED. MAINT WAS CALLED TO INVESTIGATE THE PROBLEM AND THEY W ERE TOLD BY THE CREW THAT THE ENGINEER COULD NOT OPEN THE DOOR AND THEY START REMOVING THE DOOR LINER. ONCE REMOVED, THE Y FOUND THAT THE SERVICE DOOR UP-LOCK MECHANISM HAD BROKEN COMPLETELY. BY LOOKING AT THE MATERIAL INSIDE THE CRACK IT WA S NOTICED THERE WERE SIGNS OF DIRT ACCUMULATION IN DIFFERENT AREAS MEANING THAT A CRACK DEVELOPED FOR QUITE SOME TIME. 2 L 7 2 4F 4 F RT A21EA E15NE 20081106 EA 2008 11 6 CA080623006 1 20080620 G 3070 304310 HEAT TAPE CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B 30069 NE WATER LINE BURNED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE 96 MONTH INSPECTION ON ACFT BURNED HEAT TAPE PART NR 3043-10 AND 3043-15 WAS DISCOVERED. THIS TAPE WAS INSTALLED UNDER A DRAWING NR 34-260W011 ON THE AFT WATER SYSTEM LINES (AFT CABIN). THE SURROUNDING INSULATION AND AFFECT ED PIPING WAS DEEPLY BURNED. THE BREAKER NEVER POPPED DURING THIS INCIDENT. 2 L 7 2 4F 4 F RT A21EA E15NE 20081106 EU 2008 11 6 CA080623007 1 20080623 G 3030 HEATER PILATS PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL PITOT TUBE INOPERATIVE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 7257 (CAN) ACFT RETURNED WHEN PITOT STATIC HEAT FAIL LIGHT CAME ON. FOUND RT PITOT TUBE NOT HEATING, REPLACED TUBE TESTED SYS TEM AND PERFORMED LEAK TEST ACFT RETURNED TO SERVICE. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081106 EU 2008 11 6 CA080623008 1 20080618 G 5311 5331412041 FRAME PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 17784 (CAN) CORROSION WAS FOUND ON THE TOP SURFACE OF FUSELAGE FRAMES 21 AND 24 BETWEEN ALL 4 SEAT RAILS. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081106 EU 2008 11 6 CA080623009 1 20080621 G 5311 5331412041 FRAME PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 14225 (CAN) CORROSION FOUND ON TOP SURFACE OF FUSELAGE FRAMES 21 AND 24 BETWEEN ALL 4 SEAT RAILS. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081106 SW 2008 11 6 CA080623010 1 20080622 G 3260 BULB GULSTM 690TP 690 0141720 SW GARRTT TPE331 TPE3315251K NM MLG INDICATOR INOPERATIVE W O OTHER P NO WARNING INDICATION AP APPROACH 1 CA (CAN) DISPATCHED FROM CYLB TO CYMM AT 11:10. ON DOWNWIND RT FOR 07 CYMM SELECTED GEAR DOWN BUT DID NOT GET A GEAR DOWN L IGHT FOR THE LT MAIN. GEAR APPEARED TO BE IN THE NORMAL DOWN POSITION, GEAR UNSAFE LIGHT WAS NOT ILLUMINATED, AND THE HY DRAULIC PRESSURE WAS NORMAL. MX WAS PHONED TO DISCUSS THE ISSUE, AND CONCLUDED THAT IT WAS PROBABLY A DEFECTIVE LIGHT. C YMM RADIO WAS CONTACTED TO HAVE EMERGENCY VEHICLES ALERTED. ACFT CIRCLED WEST OF CYMM UNTIL EMERGENCY VEHICLES ARRIVED A ND THEN PROCEEDED TO LAND WITH NO FURTHER PROBLEMS. AFTER LANDING IT WAS DETERMINED THAT THE LT GEAR LIGHT BULB WAS BURN ED OUT. LT MAIN GEAR LIGHT BULB REPLACED. 1 H 7 2 3T 4 T 2A4 E2WE 20081106 2008 11 6 CA080623011 4 20080623 G 2562 G SWITCH DORNEMARGLN ELT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN PERFORMING THE ANNUAL TESTS REQUIRED BY CAR 571 APPENDIX G FOUND G SWITCH WOULD NOT ACTIVATE. ELT REPLACED WI TH SERVICEABLE UNIT. 20081106 2008 11 6 CA080623012 4 20080620 G 6122 4U1827 GOVERNOR CNDAIR CL215 CL2151A10 1900320 EA PWA R2800 CA3 52026 NE HAMSTD 43E 43E60 NE PROPELLER FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA 33 (CAN) ON APPROACH TO TALBOT LAKE FOR A SCOOP (WATER PICK UP) THE RT ENGINE BEGAN TO SPEED UP UNCOMMANDED TO 3000 RPM AND AN OVERSHOOT WAS INITIATED. THE RPM LEVER WAS RETARDED IN AN ATTEMPT TO CONTROL THE RPM WITH NO RESPONSE. THE PROP OVER SPEED PROCEDURE WAS FOLLOWED AND THE ENGINE RESPONDED TO THROTTLE REDUCTION BUT WOULD NOT FEATHER. THE ENGINE AND PROP R EMAINED STABLE AND LANDING WAS UNEVENTFUL. THE PROP GOVERNOR WAS CHANGED AND THE ACFT WAS RETURNED TO SERVICE. DUE TO TH E TSO AND TYPE OF FAILURE THIS GOVERNOR WILL BE SENT OUT FOR A TEAR DOWN REPORT. A FOLLOW UP REPORT WILL BE GENERATED UP ON RECEIPT OF THE TEAR DOWN REPORT. 2 H 7 2 4R 4 R RT A14EA E231 6 C P871 20081106 EA 2008 11 6 CA080624001 2 20080624 G 7230 COMPRESSOR PWA PT6 PT6A21 52043 EA ENGINE FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) EIR PT6A 2008-040 OVER TEMPERATURE EVENT OCCURRED AS A RESULT OF COMPRESSOR FAILURE DUE TO LOSS OF STACK RIGIDITY, WHICH RESULTED FROM A LOSS OF STRETCH ON THE COMPRESSOR TIE RODS (P/N 3019371). COMPRESSOR SELF-DESTRUCTED. TIE RODS WE RE INSTALLED "NEW" AT PRIOR OVERHAUL (TSO 465 HOURS). TIE RODS WERE FOUND TO BE WITHIN ALLOWABLE HARDNESS RANGE. ENGIN E WAS PREVIOUSLY A PT6A-11 MODEL BUT CONVERTED TO A PT6A-21 VIA TCCA APPROVAL IN SEPT/04. 4 T E4EA 20081106 WP 2008 11 6 CA080624002 1 20080610 G 5345 D2010104 ARM DART ROBSIN R44 R44 7640120 WP MIRROR SEPARATED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) DART HAS RECEIVED REPORTS FROM CUSTOMERS THAT UNDER CERTAIN CIRCUMSTANCES ON D044-715-011 AND D022-716-011 CARGO M IRROR INSTALLATIONS AT CHG001 THE D2010-104 ARM MAY CRACK DURING FLIGHT CAUSING THE D2011-101 MIRROR TO SEPARATE FROM TH E ASSEMBLY. DART SERVICE BULLETIN SB08-2 IS BEING ISSUED TO ALL CUSTOMERS WHO HAVE PURCHASED THESE ASSEMBLIES FROM DART. 1 G 7 1 3O H11NM 20081106 NM 2008 11 6 CA080624003 1 20080624 G 7933 INDICATOR BOEING 727 727225 1384077 NM PWA JT8 JT8D15 52051 NE OIL TEMP MALFUNCTIONED W E ENGINE SHUTDOWN N FALSE WARNING CL CLIMB 1 CA (CAN) ON TAKE-OFF/CLIMB OUT, THE NR 3 ENGINE EGT WAS 60 DEGREES HIGHER THAN ENGINES 1 AND 2. THROUGH 1000 FEET AGL THE N R 3 OIL TEMP WENT INTO THE RED BAND. A REDUCTION IN POWER FOR QUITE THRUST BROUGHT THE OIL TEMP BACK TO THE YELLOW BAND. A RESUMPTION IN POWER RESULTED IN THE OIL TEMO RETURNING TO THE RED BAND. THE ENGINE WAS SHUT DOWN AND THE ACFT RETURNE D FOR LANDING. MX REPLACED THE OIL TEMP INDICATOR AND BULB WHICH RECTIFIED THE PROBLEM. 2 L 7 3 4F 4 F A3WE E2EA 20081106 EU 2008 11 6 CA080624004 1 20080618 G 3397 WIRE UROCOP EC130 EC130B4 8680989 EU TMECA ARRIEL ARRIEL2B1 60056 NE NAV LIGHT CHAFED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 125 (CAN) THE GREEN NAV LIGHT POWER WIRE CHAFED INSIDE THE HORIZONTAL STABILIZER AND THE RESULTING SHORT CIRCUIT POPPED THE 6 AMP CIRCUIT BREAKER BUT NOT BEFORE DAMAGING THE POS LIGHT SWITCH AND THE LIGHT & ANCILLARY CONTROL UNIT (LACU). 1 G 7 2 3U 3 U H9EU E00054EN 20081114 CE 2008 11 14 CA080625001 1 20080606 G 2910 6317003136 LINE CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL HYDRAULIC SYS RUPTURED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 2115 2115 (CAN) ACFT DEPARTED AND EXPERIENCED COMPLETE HYDR FLUID LOSS. ACFT GEAR ALTERNATE EXTENDED AND RETURNED TO AIRPORT. TROU BLESHOOTING REVEALED RUPTURED HYDR PRESSURE LINE INBD OF SERVICE QUICK CONNECT. LINE REPLACED WITH NEW, AND SYS BLED. AC FT RUN FOR 10 MIN AND ALL 3 SYS FILTERS REMOVED AND CHECKED FOR DEBRIS. NONE NOTED. FILTERS REPLACED WITH NEW IAW AMM 29 -10-00. AND SYS BLED. ALL SYS INCLUDING GEAR CYCLED 40 TIMES. ACFT RUN AND SYS CHECKED SERVICEABLE. RUPTURE APPEARED TO BE A MFG FLAW THAT WAS NOT NOTICEABLE DUE TO THE HYDR LINE IDENT LABEL BEING PLACED OVER THE FLAW. 1 L 7 2 4F 4 F RT A1WI E3GL 20081114 SO 2008 11 14 CA080625002 1 20080429 G 2997 CONNECTOR PIPER PA23 PA23250 7102308 SO LYC O540 TIO540C1A 41532 EA HARTZL HCE2Y HCE2YR2 GL HYD POWERPACK LOOSE W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 CA (CAN) HYDR FLUID NOTED LEAKING FROM MANUAL HYDR HAND PUMP UPON POST-TAKEOFF GEAR RETRACTION. ATTEMPT TO RE-EXTEND GEAR W ITH STANDARD SYS OR MANUAL HAND PUMP FAILED. CO2 EMERGENCY DEPLOYED, GEAR EXTENSION UNSUCCESSFUL. S-PIN ON BACK OF PRIOR ITY VALVE REMOVED BY OTHER CREW MEMBER ONBOARD (WITH GUIDANCE FROM AME ON GROUND VIA RADIO). PIN FOUND DIFFICULT TO REMO VE, TOOLS AND CONSIDREABLE FORCE REQUIRED. GEAR IMMEDIATELY EXTENDED WITH NORMAL INDICATIONS ONCE PIN WAS REMOVED, SUCCE SSFUL LANDING EXECUTED. 1 L 7 2 3O 3 O 1A10 E14EA 5 C P9EA 20081114 EU 2008 11 14 CA080625003 1 20080620 G 7500 7275031504 PIPE SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R389 R3894123F26 NE HP BLEEDAIR CRACKED W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA (CAN) ON TAKE OFF ROLL WITH THE CTOT ENGAGED, THE NR1 ENGINE TEMP INCREASED TO 900 DEGREES AT A TORQUE OF 60 PERCENT. TH E CREW REDUCED ENGINE POWER AND AT THIS TIME THEY DID HAVE A STEADY DECREASE IN ENGINE TEMP. THE ACFT RETURNED TO THE RA MP AND MAINT WAS DISPATCHED TO INVESTIGATE THE PROBLEM. UPON OPENING THE ENGINE COWLS MAINT DISCOVERED THAT THE HP BLEED PIPE HAD CRACKED ALL THE WAY AROUND THE LOWER CLAMP CREATING A BLEED AIR LEAK. PIPE WAS REPLACED AND THE ACFT RELEASED BACK INTO SERVICE. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P30NE 20081114 SW 2008 11 14 CA080625004 1 20080618 G 2910 LINE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 29073 NE MCAULY 4HFR34 4HFR34C652 NE HYD SYSTEM CRACKED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH, CREW NOTED A DROP IN HYDR PRESSURE FOLLOWED BY THE ILLUMINATION OF THE HYDR WARNING LIGHTS. THE HYDR PRESSURE WENT TO ZERO AND CREW CREW CONSULTED TO APPROPRIATE CHECKED LIST AND COMPLETED A MANUAL EXTENSION OF THE LANDIN G GEAR USING THE ALTERNATE EXTENSION PROCEDURES. THE ACFT LANDED WITHOUT INCIDENT. AN INSP BY MAINT DETERMINED THAT HYDR FLUID HAD BEEN LOST DUE TO A LEAK IN A HYDR TUBING IN THE LT GEAR WELL. LINE HAD A CRACK AT THE FLARE AND RESULTED IN T HE LEAK. LINE WAS REPLACED WITH NEW, FUNCTION, OPERATION, AND LEAK CHECKS COMPLETED AND THE ACFT RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 20081114 SW 2008 11 14 CA080625005 1 20080612 G 6210 206015001119 BLADE BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL MAIN ROTOR DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA 753 (CAN) DELAMINATION AT ROOT OF BLADE ON UPPER SURFACE OF THE GIP PLATE FINGER. VISUAL SEPARATION NOTED ON DAILY INSP. 1 G 7 1 3U 3 U H2SW E4CE 20081118 SO 2008 11 18 CA080625006 1 20080622 G 2823 SCREW PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA SNSNCH 76E 76EM8S5 EA FUEL SELECTOR IMPROPER PART W D RETURN TO BLOCK W S INADEQUATE Q C AFFECT SYSTEMS TX TAXI/GRND HDL 1 CA (CAN) ON GROUND RUN UP, DURING NORMAL PROCEDURE, PILOT MOVED FUEL SELECTOR TO LT FROM RT AND TRY TO COME BACK TO RT. BUT HANDLE WAS SEIZED ON FUEL SELECTOR PANEL ATTACHING SCREWS. FOUND FUEL SELECTOR COVER SCREWS MAKING CONTACT WITH HANDLE AND PREVENTING MOVEMENT FROM LT TO RT POSITION. COVER REMOVED AND AREA INSPECTED AND NO DAMAGE FOUND. COVER INSTALLED WI TH APPROPRIATE SCREWS AND FUNCTIONAL CHECK C/O. INSTALLATION C/O IAW MM. FUEL SELECTOR PANEL WAS REMOVED AND REINSTALLED FOR THE ELT SWITCH WIRING INSTALLATION. GOOD FUNCTIONAL CHECK OF THE FUEL SELECTOR HAS NOT BEEN COMPLETED AFTER PANEL INSTALLATION. IT IS A GOOD THING PILOT DID A GOOD WALK AROUND AND FUEL SELECTOR CHECK. SUGGEST TO MAKE A INDEPENDENT IN 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA 20081118 CE 2008 11 18 CA080625007 1 20080624 G 5312 1014302851 BULKHEAD BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9057 (CAN) MAINT WAS CARRYING OUT THE FIRST 1000 CYCLE REPETITIVE INSP AFTER INITIAL 10000 CYCLE STRUCTURAL INSP. FOUND A 4 INCH CRACK IN THE FS 280.275 BULKHEAD WEB, ON THE LT SIDE AT THE STRINGER NR 4 CUTOUT. THE BULKHEAD WAS CRACKED ALL THE WAY THROUGH. THICKNESS IS .040 INCH AT THIS AREA. THE CRACK ORIGINATED IN A POORLY DONE STRINGER CUTOUT. THIS IS THE HIGH TIME IN OUR FLIGHT. IT ACCRUES APPROX 1.4 CYCLES/HOUR IN AIR AMBULANCE WORK. 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 20081118 EA 2008 11 18 CA080625008 1 20080612 G 2742 6009230167 ACTUATOR CNDAIR CL601 CL6012A12 1900303 EA GE CF34 CF348E5A1 30062 NE HORIZ STAB MALFUNCTIONED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION NR NOT REPORTED 1 CA 869 869 (CAN) DURING A FLIGHT, PILOT REPORTED A PITCH TRIM CHANNEL NR1 INOP LIGHT ON. TROUBLESHOOT THE TRIM SYS AND FOUND NR1 TR IM ACTUATOR BRAKE COIL OPEN. HORIZ STAB TRIM ACTUATOR (P/N 600-92301-67/21207-008 S/N Y2003) WAS REPLACED WITH A REPAIR ED UNIT WITH TSN 868.8 HRS, CSN 613 CYCLES. UNIT WAS FUNCTIONAL TESTED IAW AMM 27-40-00 TRIM SYS TEST AND PASSED TEST, RETURNED ACFT TO SERVICE. DURING OUR NEXT FLIGHT ON 17 JUNE 08, FOR ABOUT 20 MINUTES THE ACTUATOR WORKED FINE. BUT AFTE R THAT THE PILOT REPORTED CHANNEL NR1 AND NR2 INOP LIGHT ON. AFTER ATTEMPTING TO RESET THE TRIM SYS BY THE AFM RECOMMEND ATION AND FAILED TO RESET, THE PILOT RETURNED TO BASED WITH THE ACTUATOR TRIM FROZEN TO THE LAST SET FLIGHT POSITION. T 2 L 7 2 4F 4 F RT A21AE E00063EN 20081230 NE 2008 12 30 CA080626001 2 20080619 G 7314 LW15473 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYS LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 600 (CAN) OIL LEAK NOTICED PRIOR TO ANNUAL INSP. OIL WAS LEAKING OUT THE VENT LINE FROM THE FUEL PUMP. REMOVED PUMP, REMO VED FUEL VENT FITTING, FOUND VENT CHAMBER FULL OF ENGINE OIL. REPLACED WITH NEW PUMP. 1 G 7 1 3O 3 O H11NM 1E4 20081118 EA 2008 11 18 CA080626002 2 20080624 G 8520 982C9HE2 MAIN BEARING WRIGHT R1820 982C9HE2 67020 EA HAMSTD 43D 43D51 NE NR 1 ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 460 (CAN) ACFT WAS IN CRUISE FLIGHT WHEN PILOT NOTICED OIL TEMP ON NR1 ENGINE INCREASING. A PRECAUTIONARY SHUTDOWN WAS INITI ATED ENGINE FEATHERED ACFT RETURNED AND LANDED WITH NO EVENT. INVESTIGATION FOUND THE MAIN OIL SCREENS CONTAMINATED (SU SPECT MAIN BRG FAILURE) ENGINE IS BEING REMOVED AND REPLACEMENT ENGINE INSTALLED ACFT WILL BE RETURNED TO SERVICE. 4 R E259 6 C P8879 20081118 WP 2008 11 18 CA080627001 1 20080623 G 2435 14924HTH HOUSING ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE STARTER-GEN CRACKED W K NONE O OTHER NR NOT REPORTED 1 CA 24 (CAN) STARTER WAS GRINDING ON STARTUP, UPON FURTHER INVESTIGATION AND REMOVAL OF THE STARTER IT WAS FOUND TO HAVE A CRAC KED HSG. 1 G 7 1 3O 3 O H11NM 1E4 20081118 NE 2008 11 18 CA080627002 2 20080624 G 7200 LTS100750B ENGINE BOLKMS 117 BK117B2 5626013 EU LYC LTS101 LTS101750B1 41560 NE NR 2 FLAMED OUT W O OTHER X ENGINE FLAMEOUT TX TAXI/GRND HDL 1 CA (CAN) DURING NR2 ENGINE START UP PROCEDURE NR2 ENGINE FLAMED OUT. NR2 ENGINE WAS SET TO IDLE AND UPON TURNING ON NR2 GEN ERATOR, ENGINE SPOOLED DOWN. THERE WERE NO SURGES WITH THE INSTRUMENTS. ACFT WAS SHUTDOWN AND INSPECTED. DURING INSP NO FAULTS WERE DETECTED. A FUEL SAMPLE WAS TAKEN AND SHOWED THAT IT WAS CLEAR AND FREE OF WATER. ALL FUEL SUPPLY LINES TO T HE NR2 ENGINE WERE INSPECTED AND FOUND NO FAULTS. ALL AIR LINES WERE REMOVED AND VISUALLY INSPECTED AND CAPPED LEAK CHEC KED AROUND THE FLARES AND NO FAULTS WERE DETECTED. AIR LINES WERE REINSTALLED AND NR2 ENGINE ASSY WAS LEAK CHECKED IAW M M NO FAULTS DETECTED. THE NR2 ENG WAS GROUND RUNNED AND LEAK CHECKED NO FAULTS WERE FOUND. ACFT WAS RETURNED TO SERVICE 1 G 7 2 3U 3 U NC H13EU E5NE10 20081118 2008 11 18 CA080627003 1 20080625 G 2910 MS21926J4 FITTING GULSTM GARRTT TFE731 TFE73140 29001 NE NLG LOOSE W K NONE K J FLUID LOSS WARNING INDICATION DE DESCENT 1 CA 1175 (CAN) ON DESCENT THE LT AND RT HYDR PUMP LIGHTS FLICKERED ON AND OFF. LOW HYD RESERVOIR ALSO ILLUMINATED. ALL SYS FUNCTI ONED NORMAL AND AFTER ACFT WAS STABILIZED ON APPROACH NO FURTHER LIGHTS WERE SEEN DURING OR AFTER LANDING. UPON A POST FLIGHT WALK AROUND HYDR FLUID WAS NOTED DOWN THE BELLY OF THE ACFT FROM NOSEWHEEL WELL BACK. RESERVOIR WAS FOUND LOW AND 1.5 LITRES OF FLUID WAS ADDED. GROUND RUNS WERE CONDUCTED AND NO LEAK WAS SEEN. MAINT WAS DISPATCHED TO THE SCENE, AFTE R JACKING IT WAS FOUND THAT B-NUT ON THE 90 DEGREE FITTING FOR THE DOWNLOCK ACTUATOR HAD BACKED OFF AND THE FITTING WAS FOUND LOOSE WITH THE O-RING AND BACK UP RING DISTORTED. A NEW BACK UP RING AND O-RING WERE INSTALLED , GEAR WAS SWUNG AN 4 F E1NM 20081118 EA 2008 11 18 CA080628002 1 20080622 G 5610 NP13932112 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT CRACKED W K NONE O OTHER CR CRUISE 1 CA 2651 (CAN)"THE FO’S WINDSHIELD SHATTERED IN FLIGHT. THE OUTTER PANE IS BROKE". REMOVED AND REPLACED THE WINDSHIELD. WINDSHI ELD, (RT) NP-139321-12 03017H4489 TSO: 2651.2/CSO: 2069. 2 L 7 2 4F 4 F RT A21EA E15NE 20081119 NE 2008 11 19 CA080630001 2 20080522 G 7200 ENGINE BOEING 737 737217 1384464 NM PWA JT8 JT8D17A 52049 NE NR 2 FAILED W E ENGINE SHUTDOWN E VIBRATION/BUFFET AP APPROACH 1 CA (CAN) - ON DESCENT, A "BUZZING" SOUND WAS HEARD IN THE FLIGHT DECK FOR APPROX 5-10 SEC. THIS WAS FOLLOWED BY 1 OR 2 "POP S" AND THEN A LOUD "BANG" AT WHICH TIME THE NR 2 ENGINE LOST THRUST. NR 2 ENG TEMP CLIMBED BUT THERE WAS NO ENG OVERHEA T OR FIRE WARNING. ATC ADVISED OF EMERGENCY, AFTER LANDING, THE ACFT WAS BROUGHT TO A FULL STOP IN THE MIDDLE OF THE RUN WAY AND THE ENGINE WAS SHUT DOWN. C.F.R. APPROACHED THE ACFT AND NOTICED "SMOKE" AND A "GLOW" FROM THE NR 2 ENGINE. THE RMAL IMAGING OF THE ACFT WAS ALSO PERFORMED. THEY APPLIED FOAM TO THE NR 2 ENGINE AT THIS TIME. CREW OPTED FOR A RAPID DEPLANEMENT THROUGH THE FORWARD L1 EXIT. NO VISIBLE DAMAGE TO THE ENGINE. IT WAS NOTED UPON FURTHER INVESTIGATION THAT 2 L 7 2 4F 4 F A16WE E2EA 20081118 CE 2008 11 18 CA080630002 1 20080623 G 2701 07118505 CONTROL COLUMN CESSNA 185 A185F 2072821 CE LYC O540 IO540* 41532 EA MCAULY D3A34 D3A34C401 GL CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1692 (CAN) WHILE CARRYING OUT AN ANNUAL INSP AND SEB 01-3 R1 HEAVY CORROSION WAS FOUND INTERNALLY IN CONTROL YOKE. A/C HISTO RY SHOWED FRESH WATER SUBMERSION IN 1982. 1 H 7 1 3O 3 O 3A24 1E4 5 C P47GL 20081118 SO 2008 11 18 CA080630003 1 20080425 G 8011 149NLR STARTER PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 61 (CAN) AFTER SITTING FOR 4 MONTHS, THE PILOT TRIED TO START THE ENGINE AND AFTER ONE REVOLUTION THE STARTER QUIT. THE STA RTER WAS REMOVED AND REPLACED. THE ARMATURE END OF THE STARTER HSG WAS BROKEN OUT AND TWISTED, INDICATING THAT SOMETHING WAS BINDING IN THE ARMATURE AREA. STARTER SENT TO MFG FOR TEAR DOWN AND FOLLOW UP. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081118 WP 2008 11 18 CA080630004 1 20080627 G 8010 A1294BBT SWITCH CVAC 440 440 2422902 WP ALLSN 501D 501D13D 03004 GL ALLSN A6441 A6441FN606 GL COCKPIT SHORTED W E ENGINE SHUTDOWN O OTHER IN INSP/MAINT 1 CA (CAN) NR 1 ENG STARTED TO ROTATE WHEN START ARM SWITCH SELECTED TO START POSITION, WHILE NR 1 START BUTTON NOT ENGAGED A ND ATTEMPTING TO START NR2 ENG. NR 1 ENGINE START SWITCH FOUND SHORTING INTERMITTENTLY INTERNALLY WHEN START BUTTON IS ROCKED SIDE TO SIDE. 2 L 7 2 4R 4 T 6A6 E282 6 C P898 20081107 EA 2008 11 7 CA080630005 1 20080629 G 3230 555406 SELECTOR VALVE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE NLG UNSERVICEABLE W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA 22326 8866 (CAN) GEAR DISAGREE MSG ON GEAR DOWN SELECTION, MAINS INDICATING GREEN AND THE NOSE INDICATING WHITE. CREW CYCLED GEAR W ITH SAME RESULT. THEY THEN DID AN ALTERNATE EXTENSION AND GOT THE 3 GREEN INDICATION AND LANDED WITH NO PROBLEM. (LANDIN G GEAR RETRACTION SYSTEM) MX T/S REVEALED THE NLG DOOR SELECTOR VALVE TO BE AT FAULT. THE SELECTOR VALVE WAS REPLACED AN D GEAR SWINGS WERE C/O AND THE ACFT WAS CHECKED SERVICEABLE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081110 EA 2008 11 10 CA080701003 1 20080630 G 5751 SKIN BOMBDR DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE AILERON DAMAGED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) DEPARTING AND DURING CLIMB OUT THE ACFT WAS STRUCK BY LIGHTNING CAUSING DAMAGE TO LT AILERON TIP. DECISION WAS MAD E TO RETURN THE ACFT TO AIRPORT FOR INSPECTION. INSPECTION COMPLETED PER AMM 05-50-31 AND DAMAGE WAS FOUND AT THE LT AIL ERON TIP AND ALL STATIC DISCHARGES. AILERON TIP REPLACED, AILERON BALANCE CHECKED AS PER AMM 57-60-71, ALL STATIC WICKS REPLACED AND CHECKED SERVICEABLE. ACFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 20081110 CE 2008 11 10 CA080701004 1 20080627 G 5210 5043003211 HOOK BEECH BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA PAX DOOR OUT OF ADJUST W B EMER. DESCENT O OTHER CR CRUISE 1 CA (CAN) ACFT DEPRESSURIZED AT 20000 FEET. ACFT DESCENDED TO 10000 FEET AND LANDED WITHOUT INCIDENT MX FOUND THE UPPER FORW ARD DOOR HOOK WAS NOT LATCHING PROPERLY THAT CAUSED THE DOOR SEAL TO BLOW OUT CAUSING THE DECOMPRESSION. DOOR HOOK ADJUS TED AND THE DOOR SEAL WAS SECURED. 1 L 7 2 3T 4 T A14CE E4EA 20081110 EA 2008 11 10 CA080702001 1 20080629 G 5610 NP1393226 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT CRACKED W K NONE O OTHER TX TAXI/GRND HDL 1 CA (CAN) THE FIRST OFFICERS SIDE WINDOW INNER PANE IS CRACKED. FERRIED THE PLANE. SLC REPLACED THE FIRST OFFICERS SIDE WIN DOW. OPS CHECKS GOOD. 2 L 7 2 4F 4 F RT A21EA E15NE 20081110 2008 11 10 CA080702003 4 20080701 G 2297 4986 FUSE STEC 012980201 PIPER PA46 PA46500TP 7104622 SO PWA PT6 PT6A42 52043 NE A/P COMPUTER FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 500 500 (CAN) MANUAL ELECTRIC & AUTO TRIM UNSERVICEABLE - REPLACED FUSE F2 IN ACCORDANCE WITH S-TEC SERVICE BULLETIN SB08-004. 1 L 7 1 3O 4 T RT A25SO E4EA 20081110 NE 2008 11 10 CA080702004 2 20080602 G 7250 TURBINE BLADES BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE ENGINE DAMAGED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA (CAN) DURING T/O A LOUD NOISE WAS HEARD FROM THE ENGINE AND THE T/O WAS REJECTED. THE ACFT WAS STOPPED ON THE RUNWAY AND BOTH ENGINES WERE SHUT DOWN. INSPECTION REVEALED TURBINE BLADE DAMAGE, THE ENGINE WILL BE REMOVED AND FORWARDED TO P&WC FOR INVESTIGATION AND REPAIR. THE ENGINE IS A P&WC RENTAL. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF R OOT CAUSE ONCE ESTABLISHED. 2 L 7 2 4T 4 T RT A24CE E26NE 20081118 NE 2008 11 18 CA080702005 2 20080626 G 7250 TURBINE BELL 205 205B SW LYC T53 T5313B 41549 NE ENGINE DAMAGED W R AUTOROTATION Y ENGINE STOPPAGE AP APPROACH 1 CA (CAN) PILOT CONDUCTED TAKE-OFF SCHEDULED TO CONDUCT LONGLINE OPERATIONS. APPROX 2 MINS AFTER TAKE-OFF THE PILOT HEARD A LOUD BANG FOLLOWED BY TORQUE YAWING. THE PILOT ENTERED AN AUTOROTATION AND LANDED THE ACFT ON A LOGGING ROAD. THE ACFT S USTAINED MINOR DAMAGE DUE TO HARD LANDING. SUBSEQUENT INVESTIGATION REVEALED APPROX 3 INCHES EXIT HOLE IN THE COMBUSTOR ASSY FROM TURBINE BLADE/DISC FAILURE. INSPECTION OF THE LT ACFT COWLING REVEALED APPROX 2 FT OF ENGINE INTERNAL PART SCA TTER DAMAGE. INSPECTION OF THE TAILPIPE AREA REVEALED EXTENSIVE DAMAGE TO ALL WHEEL AND DISC ASSEMBLIES. ACFT INSPECTED AS UN-AIRWORTHY. 1 G 7 1 4U 4 U H1SW E17EA 20081118 NE 2008 11 18 CA080702006 2 20080612 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MALFUNCTIONED W A UNSCHED LANDING Z J SIGNIFICANT FAILURE REPORT WARNING INDICATION CL CLIMB 1 CA (CAN) THE PILOT REPORTED WHILE AT 3000FT AGL, 2-3 MINUTES AFTER TAKEOFF, HE HEARD A LOUD BANG AND OBSERVED THE PROP TORQ UE HAD DROPPED TO ZERO. THE PILOT LANDED THE ACFT SAFELY. THE ENGINE WILL BE FORWARDED FOR INVESTIGATION. MFG WILL HAVE A REPRESENTATIVE ON SITE AND REPORT FINDINGS AS AVAILABLE. 1 H 7 1 3T 3 T A37CE E4EA 20081118 CE 2008 11 18 CA080702007 1 20080624 G 2720 0510105207 CONTROL CABLE CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL RUDDER WORN W K NONE O OTHER IN INSP/MAINT 1 CA 5099 (CAN) BOTH RUDDER CABLES WERE FOUND WORN AT STA 142 WHERE THEY TRAVEL OVER PULLEYS WITH MINIMAL CONTACT ANGLE. BECAUSE THERE IS LITTLE PRESSURE AGAINST THE PULLEYS AT THIS POINT, THEY VIBRATE AND CHAFE AGAINST THE PULLEYS, CAUSING WEAR OF THE STRANDS. AFTER REMOVAL OF THE CABLES, THE STRANDS BROKE EASILY WHEN THE CABLE WAS BENT SHARPLY. THESE ARE GALVANIZE D STEEL CABLES. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20081118 NE 2008 11 18 CA080702008 2 20080308 G 7200 BEARING CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE DISTRESSED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) WHILE AT CRUISE AT FL70, THE ENGINE TORQUE DROPPED BELOW 600FT-LB WITH ASSOCIATED COCKPIT WARNING LIGHT. THE FLIGH T WAS DIVERTED FROM ITS INTENDED DESTINATION AND AN UNEVENTFUL LANDING WAS MADE. THE ENGINE WAS FWD WHERE DISASSEMBLY SH OWED A DISTRESSED NR 1 BEARING. THE BEARING WAS FWDED TO MFG FOR INVESTIGATION. THE EXTENT OF DAMAGE TO THE BEARING PREV ENTED ASSESSMENT OF THE ROOT CAUSE FOR ITS DISTRESS. 1 H 7 1 3T 3 T A37CE E4EA 20081118 EA 2008 11 18 CA080702009 2 20080422 G 7314 DRIVE SHAFT EMB 110 EMB110* SO PWA PT6 PT6A34 52043 EA FUEL PUMP DISTRESSED W A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 CA (CAN) ACCORDING TO REPORTS, CREW DECLARED AN EMERGENCY DUE TO ENGINE DISTRESS. DURING SUBSEQUENT LANDING, A/C EXITED THE RUNWAY BEFORE HITTING A DITCH. THE LANDING GEAR COLLAPSED AND THE NOSE OF THE A/C WAS SEVERELY DAMAGED. THE RUNWAY EXCU RSION WAS CAUSED BY A LOSS OF DIRECTIONAL CONTROL DURING LANDING. DISASSEMBLY (BY THE OPERATOR) OF THE ENGINE ON WHICH THE LOSS OF POWER OCCURRED, SHOWED FUEL PUMP DRIVE SHAFT SPLINE DISTRESS (DE-COUPLE). A LARGE AMOUNT OF CORROSION WAS P RESENT AROUND THE AREA. 1 L 7 2 4T 4 T RT A21SO E4EA 20081118 2008 11 18 CA080702010 4 20080630 G 3197 EC130B4 WIRE UROCOP EC130 EC130B4 8680989 EU TMECA ARRIEL ARRIEL2B1 60056 NE WARNING SYSTEM MISREPAIRED W O OTHER O OTHER IN INSP/MAINT 1 CA 1998 1998 (CAN) THIS SNAG APPEARED AS AN INTERMITTENT WARNING (GONG) IN THE PILOTS HEADSET. THIS GONG ALERTS THE PILOT TO ANY OF T HE RED WARNING LIGHTS ILLUMINATING ON THE CAUTION LIGHT WARNING PANEL. THE GONG WAS PRESENT BUT VERY LOW AND MAY NOT HAV E BEEN HEARD BY THE PILOT IN CASE OF A RED WARNING INDICATION. WIRE SPLICE TO THE ASU CARD NR1 WAS FOUND TO HAVE AN INTE RMITTENT CONNECTION. WIRE WAS REPAIRED AND GONG WARNING WAS RETURNED TO THE PROPER LEVEL. 1 G 7 2 3U 3 U H9EU E00054EN 20081118 EU 2008 11 18 CA080702011 1 20080627 G 2121 EVAC2423H COOLING FAN AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF5 NE NR 2 FAILED W O OTHER J B WARNING INDICATION SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) WHILE TAXIING FOR DEPARTURE (FAB 820) THE CREW OBSERVED A NR2 PACK VALVE FAULT. THE FAULT RECURRED AFTER RESET ACC OMPANIED BY AN AFT SMOKE INDICATION. THE F/A CONFIRMED THE PRESENCE OF SMOKE/HAZE IN THE AFT LAV. WHILE CONDUCTING THE C HECK LIST THE SMOKE INDICATION EXTINGUISHED BUT THE ASSOCIATED ODOR REMAINED EVIDENT. MAINT REPLACED THE NR2 GROUND COO LING FAN AND THE ACFT WAS RETURNED TO SERVICE. THE SMELL AND HAZE WAS ATTRIBUTED TO THE DUCT OVERHEAT CONDITION RESULTAN T FROM THE FAN FAILURE. 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 20081118 EU 2008 11 18 CA080702012 1 20080702 G 6720 ASSB3510127 TUBE 10543079 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL TAIL ROTOR CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) INSP OF THE TAIL ROTOR CONTROL TUBE IAW CAMPAIGN NOTICE 351-67-10-017, A 7X7MM AREA WAS FOUND TO HAVE BEEN CHAFED TO A DEPTH OF .003 INCHES 15MM FWD OF THE PROTECTIVE SLEEVE INSTALLED ON THE CONTROL ROD IN THE 10 O`CLOCK POSITION LOOK ING FWD FROM THE AFT OF THE ACFT. CHAFED AREA TO BE CLEANED UP AND ALODINE APPLIED, AND ON REINSTALLATION OF THE PROTECT IVE BOOT ENSURE NO CONTACT WITH THE CONTROL ROD IS PRESENT. 1 G 7 2 3U 3 U H3EU E4CE 20081118 2008 11 18 CA080702013 4 20080630 G 6122 VALVE CVAC ALLSN 501D 501D13H 03004 GL ALLSN A6441 A6441FN606 GL PITCH LOCK VALVE FAILED W O OTHER F FLT CONT AFFECTED LD LANDING 1 CA (CAN) NR 2 PROPELLER WOULD NOT GO INTO BETA OR REVERSE ON LANDING. PROPELLER GOVERNOR AND PITCH LOCK VALVE REPLACED AND PROP FUNCTION CHECKED SERVICEABLE ON GROUND RUN. 4 T E282 6 C P898 20081118 EA 2008 11 18 CA080703001 2 20080702 G 7414 M3975 COIL SLICK 4370 CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL MAGNETO WORN W O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA 1286 (CAN) SB 3-08 DEALS WITH THE PROBLEM OF COIL HIGH-VOLTAGE OUTPUT TABS BEING BENT SLIGHTLY DURING MAGNETO MFG. THE DISTRI BUTOR ROTOR HAS A SPRING-LOADED CARBON BRUSH THAT RIDES ON THIS TAB, AND IF THE TAB IS NOT PERPENDICULAR TO THE ROTOR SH AFT, L THE BRUSH IS THRUST SIDEWAYS IN THE ROTOR SHAFT BORE, WEARING THE SIDES OF THE BRUSH AND CUTTING A HALF-MOON DEPR ESSION IN THE COIL TAB. THIS TAB WAS SLIGHTLY OFF-LEVEL AND WAS WORN AS DESCRIBED. THE BRUSH WAS ALSO SOMEWHAT WORN ON ITS SIDES. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20081105 CE 2008 11 5 CA080703002 1 20080703 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 12861 (CAN) A HALF-INCH CRACK WAS NOTED RADIATING FROM THE FLANGE BEND RELIEF CUTOUT NEAR THE BOTTOM OF THE LT SIDE OF THE BUL KHEAD AT STATION 108 (IMMEDIATELY INSIDE THE BAGGAGE DOOR), JUST ABOVE FLOOR LEVEL. THIS AREA IS NORMALLY COVERED BY PL ASTIC INTERIOR PANELS. IT WAS DISCOVERED DURING A 200-HOUR INSPECTION, WHICH REQUIRES REMOVAL OF INTERIOR PANELS AND UPH OLSTERY. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20081105 EU 2008 11 5 CA080703004 1 20080702 G 2720 CLEVIS PIN STBROS SC7 SC72 8100510 EU RUDDER CONTROL DETACHED W A UNSCHED LANDING D F INFLIGHT SEPARATION FLT CONT AFFECTED CL CLIMB 1 CA (CAN) ACFT DEPARTED, APPROXIMATELY 30 MILES EN ROUTE, PLAY WAS NOTICED IN THE RT RUDDER PEDAL, THERE WAS NO RESISTANCE WHEN DEPRESSED AND WAS INOPERABLE, LT RUDDER WAS STILL FUNCTIONAL. DECISION WAS MADE TO CONTINUE, ACFT LANDED WITHOUT I NCIDENT. AFTER FURTHER INSPECTION OF RUDDER CONTROL SYSTEM, A CLEVIS PIN HAD BECOME DETACHED FROM RUDDER CONTROL TORQUE TUBE ABOVE REAR CARGO DOOR. IT APPEARS THE SAFTY CLIP THAT COVERS THE PIN AT BOTH ENDS IS MISSING. 1 H 7 2 3T A15EU 20081105 EA 2008 11 5 CA080704002 1 20080702 G 5753 ROD DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA TE FLAPS WORN W K NONE O OTHER IN INSP/MAINT 1 CA CFTFX 173 173 (CAN) DURING AN INSPECTION ON ACFT, IT WAS DISCOVERED THAT THE LT INBD CHORD-WISE FLAP ROD WAS RUBBING AGAINST THE SPAN- WISE ROD. ONCE THEY WERE REMOVED FROM THE ACFT, IT WAS NOTED THAT THE SPAN-WISE ROD HAD A GROOVE WORN IN IT FROM THE OTH ER ROD. A NEW SPAN-WISE ROD WAS INSTALLED. DURING INSTALLATION IT WAS NOTED THAT THE BELL CRANK SUPPORT STRUCTURE WAS PO SSIBLY NOT SITUATED CORRECTLY LEADING TO A LACK OF CLEARANCE BETWEEN THE 2 RODS. THESE ARE RE-LIFED WINGS PURCHASED FROM R.W. MARTIN AND INSTALLED BY ROCKY MOUNTAIN ACFT. THE EXACT CAUSE HAS NOT BEEN DETERMINED YET AND AN UPDATE WILL BE PRO VIDED WHEN THIS IS DETERMINED. 1 H 7 2 3T 4 T RT A9EA E4EA 20081105 2008 11 5 CA080704003 4 20080703 G 2397 3042865102 ELECTRICAL BOX BOEING 737 737* NM CFMINT CFM567 CFM567B22 13802 NE ROW 8 DEF ODOR W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) LIVE TV SCREENS ON SEATS DEF IN ROW 8 NOT DISPLAYING ANY PICTURE (BUT POWER STILL DELIVERED) AND BURNING ELECTRIC/ METAL STRONG ODOR OCCURRING IN VICINITY OF ROW 8. LIVETV SYSTEM TURNED OFF WITH FLIGHT ATTENDANT CONTROL PANEL AND ODOR DISSIPATED WITHIN 10-15 MINUTES. THE IFE SYSTEM WAS DEACTIVATED. MX PLACED THE IFE SYSTEM UNDER MEL. SEB AT ROW 8 RT WAS REPLACED, WIRES AND CONNECTORS INSPECTED AND SYSTEM TESTED SERVICEABLE. 2 L 7 2 4F 4 F RT A16WE E00055EN 20081105 2008 11 5 CA080704004 1 20080704 G 3246 BEARING MLG WHEEL LACK OF LUBE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) EXCESSIVE WHEEL BEARING NOISE WAS NOTED FROM LANDING GEAR DURING TAXIING. INVESTIGATION REVEALED THAT WHEEL BEARIN G GREASE HAD WASHED OUT OF THE BEARING AND ONTO THE WHEEL HALF. WATER HAD PERMEATED THE GREASE AND CAUSED EXCESSIVE COR ROSION TO THE BEARING AND CUP. U/S PARTS WERE REPLACED. THIS IS THE SECOND OCCURRENCE OF THIS PROBLEM. WE DID NOT REPORT THE FIRST 1 AS WE THOUGHT IT WAS AN ISOLATED CASE. HOWEVER, IT APPEARS IT IS NOT. 20081105 NM 2008 11 5 CA080707002 1 20080705 G 2751 INDICATOR BOEING 727 727225 1384077 NM PWA JT8 JT8D15A 52051 NE FLAP SYSTEM BROKEN W O OTHER F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) AFTER TAKE-OFF WHEN RETRACTING FLAPS THE INBD FLAPS STUCK AT APPROXIMATELY 5 DEGREES WITH AN ASYMMETRY. THE ACFT D ECLARED AN EMERGENCY WITH A FLAP PROBLEM AND RETURNED TO CYYC. THE ACFT LANDED WITHOUT FURTHER INCIDENT. TROUBLESHOOTING WAS CARRIED OUT AND THE LT INBD FLAP POSITION TRANSMITTER DRUM CABLE WAS FOUND TANGLED AND HAD NO TENSION. THE DRUM ASS EMBLY WAS FOUND TO BE AT FAULT, AND THE TRANSMITTER ASSEMBLY SPRING TENSION HAD FAILED. THE FLAP POSITION TRANSMITTER AS SEMBLY WAS REPLACED AND THE FLAP ADJUSTMENT/TEST PROCEDURES WERE CARRIED OUT WITH NO FURTHER FAULTS. THE ACFT WAS RETURN ED TO SERVICE. 2 L 7 3 4F 4 F A3WE E2EA 20081105 GL 2008 11 5 CA080707003 2 20080706 G 7321 23065104 BEARING HONEYWELL BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL FCU DRIVESHAFT FAILED W B EMER. DESCENT X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA 1141 (CAN) PILOT NOTED N1 INCREASE DURING CRUISE. REDUCED THROTTLE AND N1 DECREASED ACCORDINGLY. SOME THROTTLE CONTROL WAS POSSIBLE BUT THE ENGINE CONTINUED TO ACCELERATE. THROTTLE WAS REDUCED UNTIL IDLE STOP WAS REACHED AT WHICH TIME IT CONT INUED TO CLIMB. AT APPROX 15 FT AGL THE ENGINE WAS SHUT DOWN AND A SUCCESSFUL AUTO ROTATION WAS CARRIED OUT. NO DAMAGE TO THE ACFT. MX REMOVED FCU IN THE FIELD. UPON REMOVAL IT WAS NOTED FCU DRIVESHAFT BEARING FAILED. ALLOWS AXIAL AND RADIAL PLAY APPROX 1/2" BOTH WAYS. BALL BEARINGS COMPLETELY DISLODGED. LUBE FOUND INTACTED (NO WASHOUT) AND NO CORROSI ON NOTED. REPLACEMENT FCU INSTALLED AND ACFT WAS RUN UP. ACFT DEPARTED BACK TO BASE WITH NO FURTHER ISSUES. 1 G 7 1 3U 3 U H2SW E4CE 20081105 CE 2008 11 5 CA080707004 1 20080526 G 5610 99144111 WINDSHIELD CESSNA 680 680CE 2076811 CE PWC PW306 PW306C 52169 NE COCKPIT CRACKED W O OTHER O OTHER DE DESCENT 1 CA 1114 1114 (CAN) ON DESCENT FOR LANDING THE PILOT NOTED A LT WINDSHIELD INOP ICAS MSG AND SHORTLY AFTER THE PILOTS WINDSHIELD OUTER PANE SHATTERED. THE ACFT LANDED WITHOUT FURTHER PROBLEMS AND THE ACFT WAS FLOWN TO A SERVICE CENTER WHERE THE WINDSHIEL D WAS REPLACED. 2 L 7 2 4F 4 F RC T00012WI E35NE 20081113 CE 2008 11 13 CA080707005 1 20080407 G 3220 12436351 TORQUE LINK CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE CARRING INP ON UPPER TORQUE LINK IAW CONTINUED AIRWORTHINESS PROGRAM 32-50-02 THE TORQUE LINK WAS FOUND CRAC KED. A NEW LINK WAS INSTALLED WITH NEW BOLTS. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 20081113 SW 2008 11 13 CA080707006 1 20080616 G 6510 407040416103 SHAFT BELL 407 407 1182206 SW ALLSN 250C 250C47B GL TAIL ROTOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 6360 6360 (CAN) WHILE REMOVING THE TAIL ROTOR FROM THE ACFT, THE ENGINEER PERFORMING THE WORK NOTED THAT SEPARATING THE HUB FROM T HE OUTPUT DRIVE SHAFT WAS SUBSTATIALLY MORE DIFFICULT THAN NORMAL. ONCE THE TAIL ROTOR WAS REMOVED IT WAS NOTED THAT THE INCORRECT TYPE OF LUBRICANT HAD BEEN APPLIED DURING THE LAST INSTALLATION OF THE TAIL ROTOR. THE TR GEARBOX WAS SENT TO A REPAIR FACILITY FOR A SCHEDULED INSP AND THE TR OUTPUT SHAFT WAS SUBSIQUENTLY SCRAPPED DUE TO CORROSION OF THE TR AND TAIL ROTOR OUTPUT SHAFT DRIVE SPLINES. 1 G 7 1 3U 3 U O H2SW E1GL 20081113 CE 2008 11 13 CA080707007 1 20080422 G 2730 BEARING CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL CONTROL TUBE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 16227 (CAN) WHILE INSP IT WAS NOTICE THAT THE LT CONTROL TUBE WAS ROUGH AS IT WAS PULLED OUT AND PUSHED IN. AFTER TAKING IT OF F, IT WAS NOTICED THAT THE BEARINGS HAD WORN THE TUBE TO ITS LIMITS. THE CONTROL TUBE AND THE BEARINGS WERE CHANGED. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 20081113 2008 11 13 CA080707008 4 20080407 G 6113 TCB43940008 SPINNER PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL LT PROP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE DOING AN INSP, PROP SPINNER WAS FOUND CRACKED. THE CRACK STARTED FROM THE THE SCREW HOLES. A NEW SPINNER WAS INSTALLED AND THE PROP WAS BALANCED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081113 NE 2008 11 13 CA080707009 2 20080703 G 7230 0292208260 DIFFUSER AEROSP AS355 AS355* EU TMECA ARRIEL ARRIEL1D1 60053 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING MAINT FOR REPLACEMENT OF THE T2 BLADES AND WHEEL, AFTER REMOVING OUTER CASING OF THE M03 THE OUTSIDE SURFAC E OF THE DIFFUSER WAS FOUND CRACKED FROM ONE SIDE TO THE OTHER. A SERVICEABLE M03 WAS INSTALLED AND THE HELICOPTER WAS RETURN TO SERVICE. DAMAGED M03 WAS SENT TO MFG FOR INVESTIGATION. THE M03 HAD 1479.3 HRS TSO. 1 G 7 2 3U 3 U H11EU E19EU 20081113 SO 2008 11 13 CA080707010 1 20080516 G 2750 WORM GEAR CALCO PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL FLAP XMSN WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE INSP, IT WAS NOTICED THAT BOTH FLAP TRANSMISSION WERE WORN OUT OF LIMITS. OVERHAULED FLAP TRANMISSIONS WERE INSTALLED. THEY WERE BOTH WITHIN LIMITS AT THE LAST INSP. ONCE THEY START TO WEAR THEY REALLY WEAR FAST. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081113 CE 2008 11 13 CA080707011 1 20080528 G 3020 BUSHING BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL ICE VANE LINK WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AT THE INSP IT WAS NOTICED THAT THE ICE VANE BUSHINGS WERE WORN CAUSING THE VANE TO MOVE ENOUGH TO ALLOW THE ICE V ANE LIGHT TO COME ON. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 20081113 EU 2008 11 13 CA080707012 1 20080629 G 5302 SKIN AEROSP AS355 AS355* EU TMECA ARRIEL ARRIEL1D1 60053 NE TAILBOOM DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) THE HELICOPTER EXPERIENCED A HARD LANDING AFTER BEING PUSHED SIDEWAYS BY A GUST OF WIND. THE RT SKID CAUGHT THE GR OUND FIRST AND THE HELICOPTER STARTED TO YAW SEVERLY, PILOT DROPPED COLLECTIVE AND LANDED THE HELICOPTER IMMEDIATELY. TH E TAILBOOM SUSTAINED DAMAGE CAUSED BY THE SUDDEN YAW, SERVICEABLE TAILBOOM AND HARD LANDING INSP C/W IAW MM AND RETURNED TO SERVICE. 1 G 7 2 3U 3 U H11EU E19EU 20081113 NE 2008 11 13 CA080707013 2 20080627 G 7210 310830601 SLEEVE PWA PT6 PT6A67D NE NR 5 BRG JOURNAL DISLODGED W K NONE O OTHER IN INSP/MAINT 1 CA 17526 7040 (CAN) THE ASSEMBLY HAD ACCUMULATED IN EXCESS OF 7000 HOURS SINCE THE SLEEVE WAS INSTALLED ON THE NR 5 BEARING JOURNAL, A ND THE POWER SECTION WAS BEING RETURNED TO THE SHOP FOR A SCHEDULED OVERHAUL. DURING INSPECTION OF THE 2ND STAGE REDUC TION CARRIER IAW OHM 3038337, SEC.72-10-00 INSPECTION, PARA.6AM IT WAS FOUND THAT THE NR 5 BEARING JOURNAL SLEEVE HAD MO VED AWAY FROM THE CARRIER SHOULDER BY APPROXIMATELY 0.021. NO OTHER DEFECTS WERE NOTED ON THE SLEEVE. 4 T E26NE 20081113 SO 2008 11 13 CA080707014 1 20080606 G 3230 42042000 ARM PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA LT MLG RETRACT BROKEN W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING TAKEOFF, COULDN`T GET GEAR UP, LT GREEN LIGHT STAYS ON. UPON INSP AFTER LANDING, LT RETRACTION ARM WAS FOUN D BROKEN. CRACK WAS ORIGINATED FROM ONE OF THE BOLT HOLES. NEW PART WAS ORDERED. 1 L 7 2 3O 3 O A20SO E14EA 20081113 SW 2008 11 13 CA080708001 1 20080622 G 2820 S0310015HT O-RING GULSTM GULSTM 690TP 690D 3970405 SW GARRTT TPE331 TPE3315 01514 WP ROTOL R306 R306382F7 GL COUPLING WORN W O OTHER K FLUID LOSS NR NOT REPORTED 1 CA (CAN) AFTER LANDING AND DURING WALK AROUND FLIGHT CREW FOUND FUEL LEAKING FROM RT WING OTBD OF NACELLE. FURTHER INSP BY MAINT FOUND FUEL LEAKING FROM FUEL INTERCONNECT PIPE COUPLING ASSY. NEW O-RINGS INSTALLED, LEAK CHECKS CARRIED OUT AND A CFT RETURNED TO SERVICE. 1 H 7 2 3T 4 T 2A4 E4WE 6 C P8EU 20081113 EA 2008 11 13 CA080708002 1 20080706 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE RT TE FLAP UNSERVICEABLE W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) ACFT WAS SET UP IN LANDING CONFIGURATION WITH FLAPS AT 45 DEGREES. ON SHORT FINAL, CREW RECEIVED A FLAP FAILURE IN DICATION. FLIGHT DID LAND NORMALLY. HOWEVER, WERE UNABLE TO RETRACT FLAPS ONCE ON THE GROUND. RT BPSU SHOWN TO BE AT FAULT. BPSU REPLACED AND COMPLETE SYS RIG CARRIED OUT. FUNCTION CHECKED SERVICEABLE WITH NO FURTHER FAULTS FOUND. 2 L 7 2 4F 4 F RT A21EA E15NE 20081113 CE 2008 11 13 CA080708004 1 20080626 G 3230 PDLM60 CIRCUIT BREAKER BEECH BEECH 100 100BEECH 1152916 CE GARRTT TPE331 TPE3316252B 01514 WP HARTZL HCB4T HCB4TN5 GL LANDING GEAR FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) ACFT DEPARTED, OR AFTER SCHEDULED MAINT WAS COMPLETED. IN THE CLIMB OUT IT WAS NOTICED BY THE CREW THAT THE LANDIN G GEAR FAILED TO RETRACT. THE ACFT LANDED WITHOUT INCIDENT. UPON INSP IT WAS FOUND THAT THE CIRCUIT BREAKER HAD FAILED B UT HAD NOT ACTUALLY POPPED. THE BREAKER WAS BENCH TEST AND CONTINUED TO NOT ALLOW POWER THOUGH DESPITE BEING PROPERLY DE PRESSED. THE BREAKER WAS REPLACED WITH A NEW ONE AND THE SYS FUNCTION TESTED NORMAL. 1 L 7 2 3T 4 T A14CE E2WE 6 C P40EA 20081113 CE 2008 11 13 CA080708005 1 20080708 G 2731 55657562 WHEEL CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ELEVATOR TRIM DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN A SMALL FORCE WAS APPLIED TO THE INDICATOR POINTER AND THE TRIM WHEEL WAS ROTATED THE POINTER JUMPED OUT OF I TS GROOVE. INSPECTION FOUND THAT THE GROOVES WERE NOT WORN AND THE SYSTEM LOOKED NORMAL BUT WHEN THE WHEEL WAS ROTATED W ITH 1 FINGER APPLYING PRESSURE TO THE SIDE OF THE WHEEL IT WOBBLED AND ALLOWED THE PIN RIDING IN THE GROOVE TO BECOME DI SENGAGED. PINCHING THE WHEEL WITH A THUMB AND FINGER OR TURNING THE WHEEL WITH THE PALM OF THE HAND ON THE TOP DID NOT A LLOW THE PIN TO DISENGAGE. 1 L 7 2 4F 4 F A22CE E1NE 20081113 NE 2008 11 13 CA080708006 2 20080621 G 7314 LW15473 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYS LEAKING W O OTHER O OTHER NR NOT REPORTED 1 CA 98 (CAN) DURING A GROUND RUN OF THE ACFT THE ENGINE FUEL PUMP WAS LEAKING. 1 G 7 1 3O 3 O H11NM 1E4 20081113 WP 2008 11 13 CA080708007 1 20080630 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INOPERATIVE W O OTHER O OTHER NR NOT REPORTED 1 CA 344 (CAN) STARTER BENDIX IS NOT FUNCTIONING/STARTER WOULD NOT ENGAGE THE RING GEAR. 1 G 7 1 3O 3 O H11NM 1E4 20081113 WP 2008 11 13 CA080708008 1 20080629 G 6310 C0511 ACTUATOR ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA CLUTCH LOOSE W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) THE CLUTCH ACTUATOR LOWER MOTOR HSG FLANGE TO WORM GEAR FOUND LOOSE. 1 G 7 1 3O 3 O H11NM E295 20081113 SO 2008 11 13 CA080708009 1 20080620 G 8011 STARTER PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE UNSERVICEABLE W O OTHER O OTHER NR NOT REPORTED 1 CA 641 (CAN) THE STARTER WOULD NOT ENGAGE, REPLACED WITH A SERVICABLE STARTER. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081113 2008 11 13 CA080708010 4 20080708 G 3452 TRANSPONDER CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ATC INTERMITTENT W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MODE C ALTITUDE REPORTING INTERMITTENTLY REPORTS FALSE ALTITUDES. VISUAL INSP FOUND A CHAFED MODE C A1 CODE WIRE I N THE ALTITUDE ENCODER WIRING. WIRE WAS CHAFFING (DUE TO VIBRATION) ON THE THROTTLE CABLE DIRECTLY BEHIND THE CENTER RAD IO PANEL. WIRE WAS REPAIRED AND CHAFE PROTECTION WAS ADDED TO THE WIRE HARNESS. MODE C DATA INTEGRATION CHECK WAS PERFOR MED IAW CARS STD 571 APPENDIX F, ITEM K. 1 H 7 1 3O 3 O NT 3A12 1E10 20081113 NM 2008 11 13 CA080708011 1 20080708 G 2497 WIRE BOEING 737 737400 138449A NM COCKPIT CHAFED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA 35061 (CAN) P5 OVERHEAD COCKPIT PANEL WAS OPENED DURING NORMAL MX ACTIVITIES AT THE C2 MX EVENT. ARCING WAS NOTED BETWEEN THE DOOR WARNING MODULE AND ADJACENT WIRE BUNDLES. DAMAGE TO WIRING WAS ALSO FOUND AT THE P5-13, ELECTRICAL METERS AND GALLE Y POWER MODULE. INSPECTION REVEALED NO AFFECT TO ACFT STRUCTURE, BUT 6 WIRES WERE FOUND CHAFFED REVEALING THEIR RESPECTI VE CONDUCTORS (REF A AND C). A 7TH WIRE WAS FOUND SEVERED. THE MODULES WILL BE TESTED FOR SERVICEABILITY AS A SMALL BURN MARK WAS FOUND AT THE CORNER OF THE CASE. THE FOLLOWING WIRES ARE TO BE REPLACED TO CORRECT THE DEFECTS FOUND: 1. W03 6-650-22, WDM ATA 29-11-01. W036-8769-22, WDM ATA 24-31-11. W036-15A-24, WDM ATA 21-58-03 PG1 4. W036-043-22, WDM ATA 24 2 L 7 2 4F RT A16WE 20081113 NE 2008 11 13 CA080709001 2 20080706 G 7320 7982133007 EEC DHAV DHC8 DHC8315 2809010 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE ENGINE MALFUNCTIONED W A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CL CLIMB 1 CA (CAN) ON TAKE OFF, THROUGH 400 FT WITH BLEEDS ON AND CLIMB POWER SET 90% NH + 900 RPM, ENGINE LT EXPERIENCED A SURGE. LT NH WENT 110%, THEN DROPPED TO 70%. RESTABILIZED AT 90%. REDUCED POWER TO BOTH ENGINES. RETURNED FOR LANDING. GROUND RUN S WERE COMPLETED COULD NOT DUPLICATE, THE DATA FROM THE ONBOARD ACFT FLIGHT INFORMATION REPORTING SYSTEM (AFIRS) AND IT WAS FOUND THAT THERE WAS AN INCREASE IN FUEL FLOW TO THE ENGINE CAUSING THE POWER SURGE. THE ENGINE ELECTRONIC CONTROL U NIT (EECU) WAS REPLACED THE ENGINES WERE GROUND RUN AND NO FAULTS WERE FOUND. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081113 EU 2008 11 13 CA080709002 1 20080708 G 3220 5322012289 DRAG LINK PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6663 (CAN) NLG DRAG LINK FOUND CRACKED DURING PREFLIGHT INSP. DRAG LINK REPLACED WITH NEW. THIS IS THE 3RD ONE FOUND CRACKED ON 3 DIFFERENT ACFT IN THE LAST 6 MONTHS IN THE EXACT SAME SPOT. ALL DRAG BRACES SENT TO MFG FOR INVESTIGATION. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081113 NM 2008 11 13 CA080709003 1 20080709 G 2710 CONTROL CABLE EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE AILERONS MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 2634 (CAN) FOUND BALL END OF LT AND RT AILERON CONTROL CABLES NOT FULLY ENGAGED IN WW BELLCRANK CABLE SLOT.(FWD CABLE) BALL END OF LT AND RT AILERON CONTROL CABLES IN WW BELLCRANK CABLE SLOT.(FWD CABLE) REENGAGED PROPERLY IN ACCORDANCE WITH AMM 27-11-03-400-801. SEE ATTACH PICTURE 2 L 7 2 4F 4 F RT A57NM E00070EN 20081113 NM 2008 11 13 CA080709004 1 20080709 G 5753 19092001405 CARRIAGE EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE LT TE FLAP GROOVED W K NONE O OTHER IN INSP/MAINT 1 CA 2634 (CAN) LT INBD FLAP MAIN 1 CARRIAGE ASSY (P/N 190-92001-405) FOUND GROOVED INSIDE BY LOOSE BOLT FROM TRACK ASSY. ENGINEE RING ADVISED THE ROOT CAUSE OF THE DAMAGE OF THE FLAP CARRIAGE IS CAUSE BY THE FLAP TRACK MECHANISM LOOSE BOLT. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081113 EU 2008 11 13 CA080709005 1 20080706 G 2720 RS87 RETAINING RING BRAERO BAG JETSTM JETSTM3212 1500217 EU GARRTT TPE331 TPE33110UG 01514 WP ROTOL R333 R333482F12 GL RUDDER PEDAL MISSING W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 500 (CAN) RUDDER PEDAL BECAME DISENGAGED FROM PEDAL SPIGOT, RS87 RETAINING RING CAME OUT OF RETAINING SLOT. RETAINING RING S EEMED TO HAVE INSUFFICIENT TENSION TO STAY IN SLOT. NEW RING INSTALLED AND NO FURTHER PROBLEMS. FLEETWIDE INSPECTION CAR RIED OUT AND NO SIMILAR PROBLEMS FOUND. 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C P61GL 20081113 NM 2008 11 13 CA080709006 1 20080703 G 2710 19005549401 CONTROL CABLE EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE AILERONS BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 1407 (CAN) DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 190-04212-401, PN 190-04209-401, PN 190-05549-401, RT PN 190 -05551-401, PN 190-05550-401, PN 190-04209-401) WORN AND WITH SEVERAL WIRES BROKEN AT FAIRLE AD. EMBRAER CAME UP WITH 2 SERVICES BULLETIN: SB190-27-0017 EMBRAER FLIGHT CONTROLS - AILERON - CABLES WEAR SB170-2 7-0028 EMBRAER FLIGHT CONTROLS - AILERON - CABLES WEAR 2 L 7 2 4F 4 F RT A57NM E00070EN 20081113 NM 2008 11 13 CA080709007 1 20080709 G 3220 19070150404 BUSHING EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE NLG MIGRATED W K NONE O OTHER IN INSP/MAINT 1 CA 2634 (CAN) DURING INSPECTION FOUND BUSHING MIGRATED ON NLG RETRACK ACTUATOR LOWER ATTACHMENT (PRC BROKEN) AND ON RT MLG SIDE STAY LOWER ATTACHMENT. NLG SHOCK STUT ASSY PN 190-70453-401 SN 00053 MLG SIDE STAY PN 190-70150-404 SN 00053 AFTER IN VESTIGATION FOUND NO CLEARANCE FIT, EMBRAER HAS BEEN ADVISED OF THE PROBLEM. THIS PROBLEM HAS BEEN ALREADY FOUND ON NUME ROUS ACFT 2 L 7 2 4F 4 F RT A57NM E00070EN 20081113 EA 2008 11 13 CA080709008 2 20080704 G 8530 EXHAUST VALVE LYC O540 O540* 41532 EA ENGINE SEIZED W O OTHER E VIBRATION/BUFFET DE DESCENT 1 CA (CAN) DURING A FLIGHT IN THE R44 HELICOPTER, THE PILOT NOTICED A SIGNIFICANT VIBRATION APPROX. 2 HOURS INTO THE FLIGHT. THE VIBRATION LASTED 45 SECONDS. THERE WERE NO AUDIBLE ALARMS & ALL GAUGES READ NORMAL. THE A/C WAS DESCENDING WITHOUT CONTOL INPUTS,AFTER THE 45 SECOND VIBRATION SUBSIDED.A/C RETURNED TO BASE. THE A/C WAS STARTED THE FOLLOWING DAY THE VIB RATION WAS NOTED @102% IN HOVER ,A/C LANDED,WAS SHUT DOWN AND SB388C(VALVE CLEARANCE CHECK) WAS CARRIED OUT.NUMBER 3 AND NR 6 EXHUAST VALVES WERE SEIZED WITH BENT PUSH RODS.CYLINDER NUMBER 1, 2,,4 VALVES WERE BELOW THE ALLOWABLE CLEARANCE 3 O E295 20081113 NE 2008 11 13 CA080709009 3 20080703 G 6111 SFA13N1ROA1D BLADE CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE PROP ASSY LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 10 (CAN) 3 BLADES FOUND LEAKING AFTER 10 HRS OF INSTALLATION. THESE BLADES WERE ALREADY SENT FOR TEFLON STRIP REPLACEMENT DUE TO THE SAME KIND OF SNAG EARLIER THIS SPRING. 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 20081113 NE 2008 11 13 CA080709010 2 20080706 G 8550 SCAVENGE PUMP DOUG DC6 DC6B 3021712 WP PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE ENGINE FAILED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA (CAN) NR4 BMEP WENT TO 0. OIL TANK QUANTITY DROPPED FROM 25GALS TO 12 GALS IN A FEW MINUTES. ENGINE WAS FEATHERED AND LA NDING CARRIED OUT WITHOUT FURTHER INCIDENT. 2 L 7 4 4R 3 R 6A4 ATC14 6 C P871 20081113 GL 2008 11 13 CA080709011 3 20080709 G 6111 A1851B BEARING RACE HARTZL HCB3R HCB3R304 GL PROPELLER FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PROPELLER WAS RECEIVED IN SHOP FOR REMOVAL OF A BROKEN OFF GREASE NIPPLE IN BLADE CLAMP. BLADE CLAMP REQUIRED REMO VAL TO EXTRACT BROKEN GREASE NIPPLE. WHEN THE CLAMP WAS REMOVED A CHIP OF THE OTBD BEARING FELL OUT. AFTER EXAMINING THE BEARING IT WAS DETERMINED THAT THE ENTIRE ASSEMBLY SHOULD BE REPLACED DUE TO EXCESSIVE RACE AND BALL WEAR. IT SHOULD BE NOTED THAT THE GREASE IN THIS CLAMP WAS BLACK FROM METAL WEAR WHEREAS THE GREASE IN THE OTHER 2 BLADE CLAMPS WAS IN NOR MAL CONDITION FOR THIS PROP TYPE. BEARING WAS REPLACED AND PROPELLER RETURNED TO SERVICE. 5 C P28EA 20081113 SW 2008 11 13 CA080710001 1 20080708 G 5620 412670101 WINDOW BELL 412 412EP 1182205 SW PWA PT6T PT6T3 52045 EA PAX DOOR MISSING W O OTHER O OTHER DE DESCENT 1 CA 5 (CAN) WHILE THE ACFT WAS IN A DIVE, IN ORDER TO REACH VNE FOR RADS READING, AFT RT PASSENGER DOOR WINDOW WAS LOST IN FLI GHT AT 138 KNOTS. 1 G 7 2 4U 4 U H4SW E22EA 20081113 SW 2008 11 13 CA080710002 1 20080618 G 2550 26801500 CABLE BELL 427 427 1182207 SW PWC PW207 PW207D NE CARGO HOOK ASSY BROKEN W O OTHER O OTHER CR CRUISE 1 CA 284 (CAN) MANUAL RELEASE CABLE BROKE AT CARGO HOOK FITTING CAUSING HOOK TO RELEASE INFLIGHT. 1 G 7 1 3U 3 U R00001RC E42NE 20081113 EU 2008 11 13 CA080710003 1 20080704 G 2822 045004B145A SWITCH SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B1 60056 NE FUEL PUMP FAILED W H DEACTIVATE SYST/CIRCUITS O OTHER TX TAXI/GRND HDL 1 CA 435 (CAN) FUEL PUMP WOULD NOT TURN ON 1 G 7 1 3U 3 U H9EU E00054EN 20081113 CE 2008 11 13 CA080710004 1 20080709 G 7120 J124532 MOUNT CESSNA 210 210R 2073458 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL ENGINE DEFORMED W K NONE O OTHER IN INSP/MAINT 1 CA 1863 (CAN) DURING ENGINE INSPECTION NOTED THAT THE LT AND RT FORWARD ENGINE MOUNTS WERE SAGGING TO THE POINT THAT DURING TAKE OFF POWER ON ENGINE AND INTAKE PIPE HOSE CLAMP MADE CONTACT WITH THE UPPER PORTION OF ENGINE MOUNT. THE LORD MOUNT APPE ARED TO BE SAGGING/DROOPING BUT NOT SEPERATED ANYWHERE. BOTH FRONT ENGINE MOUNTS REPLACED WITH NEW. 1 H 7 1 3O 3 O RT 3A21 E5CE 5 C P47GL 20081113 NE 2008 11 13 CA080710005 2 20080708 G 8530 EXHAUST VALVE PWA R985 R985AN14B 52008 NE ENGINE DAMAGED W O OTHER R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CR CRUISE 1 CA 1513 1513 (CAN) EXHAUST VALVE BROKE/SEPARATED DURING FLIGHT. BASE OF VALVE STAYED IN COMBUSTION SECTION OF CYLINDER AS ENGINE RAN CAUSING DAMAGE TO PISTON, AND UPPER CYLINDER COMBUSTION CHAMBER. PILOT REPORTED DECREASE IN POWER/VIBRATION AND UPON THR OTTLING BACK, AN INCREASE IN VIBRATION. ACFT LANDED WITHOUT INCIDENT. CYLINDER HEAD FOUND TO HAVE BEEN BROKEN OFF, MOST OF CYLINDER PARTS RECOVERED IN COWLING EXCEPT FOR EXHAUST SYSTEM. LOWER EX VALVE BASE SHOWS SIGN OF HAVING BEEN CRUSHED ABOVE PISTON REPEATEDLY UNTIL CYLINDER FAILED. UNKNOWN AS TO IF EXHAUST VALVE WAS REPLACED NEW, WITH SERVICEABLE, OR OV ERHAULED AT LAST ENGINE OVERHAUL. 3 R 5E1 20081113 SW 2008 11 13 CA080710006 1 20080709 G 5410 205030195030 BEAM BELL 205 205A1 1181414 SW LYC T53 T5317BLYC 41616 NE LT NACELLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION, NOTICED A CRACK ON THE LT MAIN BEAM CAP UPPER WEB NEAR THE FORWARD ENGINE FIRE WALL. THE ACFT W AS GROUNDED. THE AIRFRAME TIME 15185 HOURS. THE TIME ON THE MAIN BEAM CAP IS UNKNOWN. 1 G 7 1 4U 4 U H1SW E17EA 20081113 EU 2008 11 13 CA080711001 1 20080708 G 2121 BC112A2 FAN SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R389 R3894123F26 NE CABIN OVERHEATED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) ON JULY 8/2008, SHORTLY AFTER TAKEOFF THE CREW NOTICED AN ELECTRICAL ODOR WHICH WAS ALSO CONFIRMED BY THE F/A. THE CREW DECLARED AN EMERGENCY AND PROCEEDED TO LAND WITHOUT INCIDENT. MX WAS DISPATCHED TO THE ACFT WHERE IT WAS NOTICED T HAT WHEN THE FLIGHT DECK RECIRCULATION FAN WAS SELECTED THE CONTROL BREAKER POPPED. THE CENTER ISLE FLOOR BOARDS WERE RE MOVED AND AN INSPECTION WAS CARRIED OUT ON BOTH FANS. IT WAS DETERMINED THAT THE FLIGHT DECK FAN HAD OVERHEATED AND WAS THE SOURCE OF THE PROBLEM. MX MEL`ED THE FAN AND THE CREW CARRIED OUT A TEST FLIGHT AS AN EXTRA PRECAUTION. THE ACFT WAS RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P30NE 20081113 2008 11 13 CA080711002 4 20080709 G 3451 6221234013 INDICATOR SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE DME BURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA (CAN) ON APPROACH THE CREW REPORTED A LOUD POP WHICH WAS FOLLOWED BY AN ELECTRICAL ODOR AND THE DME WENT OFF LINE. THE C REW SHUT DOWN ALL NON-ESSENTIAL AVIONICS AND CONTINUED WITHOUT INCIDENT. THE ACFT WAS THEN POSITIONED AT THE HANGAR WHER E MX REMOVED AND CARRIED OUT AN INSPECTION ON THE DME INDICATOR. UPON A CLOSER LOOK IT WAS NOTICED THAT THE CAPACITOR HA D FAILED. IT WAS DETERMINED THAT THE INDICATOR WAS THE SOURCE OF THE PROBLEM. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 20081113 EA 2008 11 13 CA080711003 1 20080704 G 2810 2156400212 FUEL CELL CNDAIR CL215 CL2156B11215 EA LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING A FUEL CELL CHANGE DUE TO A LEAK PROBLEM, THE TECHNICIAN DID A LEAK TEST ON THE NEW 1 THAT WAS COMING FROM THE STORE AND RECEIVED FROM DIRAZUR- ZODIAC GROUP ON JULY 2007,(WELL PRESERVE). H E FOUND THAT IT WAS LEAKING FROM THE C ENT. NOTE: WE’VE HAD SO MANY PROBLEMS WITH THESE CELLS THAT WE MADE AN INTERNAL PROCEDURE TO TEST THEM BEFORE INSTALLAT ION 2 H 7 2 4T RT A14EA 20081113 GL 2008 11 13 CA080711004 1 20080627 G 2150 347074 BEARING BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP ACM IMPELLER DRAGGING W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) CREW REPORTS THEY WERE ON TAXI WAY, HAVING JUST LEFT THE FBO WHEN THICK GREY SMOKE STARTED ROLLING OUT OF THE VENT S. THE CABIN FILLED UP QUICKLY ENOUGH THEY WERE STARTING TO HAVE TROUBLE BREATHING. ONLY THING THEY MANAGED TO DO WAS SH UT DOWN AND GET OUT OF ACFT. RAMP AGENT FOR THE FBO DROVE UP IN A TRUCK, SAW WHAT WAS GOING ON, AND CALLED THE FIRE DEPA RTMENT. FD USED THERMAL IMAGING TO DETERMINE THERE WAS NO FIRE AND LEFT. NO EMERGENCY WAS DECLARED. 2 L 7 2 4F 4 F RT T00005NY E00010LA 20081113 SO 2008 11 13 CA080711005 2 20080620 G 8530 AEC646263 PISTON CESSNA 182 182K 2072724 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL SKIRT BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 517 (CAN) A PIECE OF NR 2 PISTON SKIRT WAS BROKEN OFF AT THE OIL CONTROL RING GROOVE. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 20081113 NE 2008 11 13 CA080711006 2 20080701 G 7230 BLADES PILATS PC12 PC12 7090550 EU PWA PT6 PT6A67B 52043 NE COMPRESSOR DAMAGED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE AT FL200, THE PILOT NOTED THE ENGINE TEMPERATURE RAPIDLY RAISING TO 850°C WITH POWER TURBINE SPEED D ECREASING. HE ELECTED TO SHUT THE ENGINE DOWN AND PERFORMED A SUCCESSFUL DEAD STICK LANDING. POST FLIGHT ENGINE EXAMINA TION REVEALED HEAVY RUBBING DAMAGE IN THE COMPRESSOR SECTION. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADV ISE OF ROOT CAUSE ONCE ESTABLISHED. 1 L 7 1 3T 4 T RT A78EU E26NE 20081113 CE 2008 11 13 CA080711007 1 20080626 G 7932 30B385103 SENSOR CESSNA 680 680CE 2076811 CE PWC PW306 PW306C 52169 NE RT ENGINE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1155 1155 (CAN) DURING MX VISUAL CHECK OF RT ENGINE A SMALL AMOUNT OF OIL WAS NOTED AROUND THE ENGINE LOW LEVEL OIL SENSOR. FURTH ER INVESTIGATION FOUND OIL LEAKING INTERNALLY THROUGH SENSOR AND EXITING OUT OF CANNON PLUG. RT LOW LEVEL OIL SENSOR WAS REPLACED WITH NEW AND NO FURTHER LEAKS WERE DETECTED. 2 L 7 2 4F 4 F RC T00012WI E35NE 20081113 EA 2008 11 13 CA080711008 1 20080706 G 3240 AE87996E LINE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE NR 2 BRAKE ASSY DISCONNECTED W O OTHER B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 CA (CAN) ACFT HAD A NORMAL LANDING ON ARRIVAL IN IND, HOWEVER WHILE ATTEMPTING TO TAXI OFF THE RUNWAY, EXCESSIVE POWER WAS REQUIRED TO TAXI. IT WAS SUSPECTED THAT NR 2 BRAKE ASSEMBLY HAD SEIZED AS SMOKE COMING FROM THE NR 2 BRAKE. CONTRACT MX INVESTIGATED THE ACFT AND THE QUICK DISCONNECT HYDRALIC LINE TO THE NR 2 BRAKE OFF. THE QUICK DISCONNECT WAS RESECURED AND THE BRAKES WERE FUNCTION CHECKED SERVICEABLE. THERE HAS BEEN NO FURTHER OCCURANCES TO DATE. IT IS SUSPECTED THAT THE QUICK DISCONNECT CONNECTOR MAY HAVE BACKED OFF CAUSING THE DRAGGING BRAKE CONDITION. 2 L 7 2 4F 4 F RT A21EA E15NE 20081113 NE 2008 11 13 CA080711009 2 20080629 G 7261 ENGINE CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE OIL CONSUMPTION W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) DURING T/O ROLL, THE PILOT RECEIVED A LOSS OF OIL PRESSURE WARNING AND ABORTED T/O. THE ACFT RETURNED TO THE RAMP WHERE THEY OBSERVED NO OIL ON THE SIGHT GLASS. OIL WAS NOTED IN THE EXHAUST AND A GROUND RUN SHOWED A CONSUMPTION OF 2 Q UARTS IN 10 MIN. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 L 7 2 4F 4 F RT A22CE E00059EN 20081113 EU 2008 11 13 CA080711010 1 20080705 G 7797 CONNECTOR BAG ATP ATP EU PWA PW120 PW126A NE ENGINE CONTAMINATED W O OTHER R X PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT CR CRUISE 1 CA (CAN) DURING FLIGHT, THE ENGINE TORQUE STARTED TO FLUCTUATE BETWEEN 60% TO 120% AND THE ENGINE SHUT ITSELF DOWN. TROUBLE SHOOTING REVEALED HEAVY CONTAMINATION ON 1 OF THE CONNECTORS OF THE ENGINE ELECTRONIC CONTROL. THE CONNECTOR WAS CLEANED , GROUND RUN PERFORMED AND ACFT RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A27NM E2ONE 20081113 NE 2008 11 13 CA080711011 2 20080706 G 8530 399354 CYLINDER HEAD DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE ENGINE SEPARATED W A UNSCHED LANDING E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 372 (CAN) IN FLIGHT ENGINE BECAME ROUGH - POPPING/BANGING SOUND PRECAUTION AND LANDING COMPLETED ENGINE INSPECTED - CYL NR 3 HEAD FOUND BROKEN FROM BARREL. REMAINDER OF CYLS VISUALLY INSPECTED WITH NO DAMAGES FOUND. CYL NR 3 ASSY. REPLACED WITH OVERHAULED UNIT. - GROUND RUN SATISFACTORY. RERUN TO AWD 78-08-07 (VISUAL INSP.) CYLINDER FAILURE IS NOT UNHEARD OF ON THESE AIRPLANES 1 H 7 1 3R 3 R RC A806 5E1 20081113 SO 2008 11 13 CA080711012 1 20080705 G 8011 MHB4016R STARTER PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA 48 (CAN) THE STARTER WOULD NOT WORK AT ALL, REPLACED WITH A SERVICEABLE STARTER. 1 L 7 2 3O 3 O A20SO E14EA 20081113 EA 2008 11 13 CA080712001 1 20080711 G 3240 2604141 HOUSING CNDAIR CL215 CL2151A10 1900320 EA PWA R2800 CA3 52026 NE BRAKE PISTON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1057 (CAN) DURING NDT AT OVERHAUL, 2 CRACKS DISCOVERED AT BOTTOM OF PISTON BORE IN BRAKE HOUSING. THESE HOUSINGS ARE NDT`D AT OVERHAUL AND EVERY BRAKE LINING CHANGE PER THE BF GOODRICH MANUAL 32-48-24 PAGE 512. 2 H 7 2 4R 4 R RT A14EA E231 20081113 CE 2008 11 13 CA080714001 1 20080708 G 5343 TRUNNION CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ATTACHMENT HARDWARE THAT WAS FOUND INSTALLED IN THE CHANNEL-TRUNION BRACE WAS NOT WHAT IS CALLED FOR IN ACFT I.P. C. 53-11-01 01 .THE INSTALLED HARDWARE WAS 4 AN3-5A BOLTS WITH AN960-3 WASHERS UNDER BOTH THE HEAD OF THE BOLTS AND UNDE R THE NUTS. THE LENGTH OF THE BOLT AT THE FORWARD LT CORNER OF THE CHANNEL-TRUNION BRACE WAS TOO LONG WHEN INSTALLED AND INTERFERED WITH THE AFT TRAVEL OF THE STEERING ARM LOCATED JUST BELOW THE CHANNEL-TRUNION BRACE SUPPORT ASSEMBLY. THE I .P.C. CALLS FOR 4MS27039-1-07 SCREWS AND 4 MS21042-3 NUTS (NO WASHERS ARE CALLED FOR IN THE INSTALLATION). 1 L 7 2 4F 4 F A22CE E1NE 20081113 SO 2008 11 13 CA080714003 1 20080714 G 8120 4091709001 TURBOCHARGER PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA ENGINE FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 800 (CAN) RT TURBOCHARGER FAILED SHORTLY AFTER T/O. ENGINE SHUTDOWN AND ACFT RETURNED TO AIRPORT FOR AN UNEVENTFUL LANDING. 1 L 7 2 3O 3 O A20SO E14EA 20081113 NM 2008 11 13 CA080714004 1 20080712 G 8097 WIRE AIRBUS A319 A319114 3930350 NM CFMINT CFM56 CFM565A1 NE START VALVE DAMAGED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER DEPARTURE FROM TORONTO DURING THE CLIMB, THE CREW STARTED RECEIVING UNEXPECTED ECAM MSGS REGARDING THEIR NR 2 ENGINE. THE CLIMB WAS STOPPED AT FL230 WHERE THE CREW TRIED TO WORK OUT THE ECAM ITEMS WITH MX. THE ENGINE LOST ALL PO WER AND WAS SHUT DOWN. THERE WAS NO FIRE WARNING. THE FLIGHT RETURNED TO TORONTO WHERE AN UNEVENTFUL OVERWEIGHT LANDING TOOK PLACE. THERE WAS NO ADVERSE PASSENGER REACTIONS REPORTED BY THE FLIGHT CREW. 2 L 7 2 4F 4 F RT A28NM E29NE 20081113 EA 2008 11 13 CA080714005 1 20080708 G 1400 TBC6EM106727 BOLT DHAV DHC6 DHC6 2802606 EA DRAIN VALVE MISMANUFACTURED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) TBAL HAD A CUSTOMER REPORT OF THE LOCK WIRE TEARING THROUGH THE LOCK WIRE HOLE DURING INSTALLATION ON 2 OF THE 4 P URCHASED DRAIN VALVE BOLTS. ALL BOLTS IN STOCK WERE PULLED FROM THE SHELF AND EXAMINED. THE BOLTS CONFORMED TO THE TBAL DRAWING. THE BOLTS THAT WERE ON THE 1 END OF THE TOLERANCE WERE CLOSE TO THE EDGE. AN OEM BOLT WAS PURCHASED AND COMPAR ED TO TBAL DRAWINGS. THE LOCK WIRE HOLE WAS CLOSER TO THE EDGE OF THE HEAD ON THE TBAL PART WHEN COMPARED AGAINST THE OE M. A TOTAL OF 11 BOLTS WERE SOLD. THE CUSTOMER WITH THE 2 OF 4 BOLTS IS RETURNING 2 BAD ONES AND USING THE 2 GOOD ONES. WE ARE IN THE PROCESS OF CONTACTING THE REMAINING 4 CUSTOMERS WHO HAD PURCHASED THE BOLTS TO ADVISE THEM OF THE PROBLEM. 1 H 7 2 3T RT A9EA 20081118 2008 11 18 CA080714006 4 20080714 G 2565 LINE BFGOODRICH ESCAPE SLIDE MISROUTED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) FIRST VISIT IN SLIDE SHOP OF THE ERJ-175 SLIDE S/N ED0522 FTN 4W94YL DURING THE INCOMING INSPECTION IT WAS DISCOVE RED THAT THE FOLLOWING PROBLEMS WOULD HAVE PREVENTED THE DEPLOYMENT OF THE SLIDE EITHER MANUALLY OR AUTOMATICALLY. CORD WAS FORGOTTEN ON THE SPEED LACING LOOP THUS PREVENTING AUTO DEPLOY. PHOTO FIG. 1 THE MANUAL FIRING LINE WAS NOT ROUTED PROPERLY. PHOTOS ARE FIG. 2 AND 3. 20081110 GL 2008 11 10 CA080714007 2 20080711 G 7250 9362M43P02 TURBINE WHEEL GE CF6 CF680C2* GL ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 45222 13716 (CAN) DURING SHOP INSPECTION CRACKS FOUND ON FWD DOVETAIL SEPARATIONS IN EXCESS OF MANUAL LIMITS. 4 F E23EA 20081110 EA 2008 11 10 CA080714008 1 20080710 G 2820 SLEEVE GE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE WORN W E ENGINE SHUTDOWN J WARNING INDICATION CL CLIMB 1 CA (CAN) DEFECT: ON CLIMB OUT, "L FUEL LO PRESS" MSG WAS ON AS PER DEFECT 309471. THE "L EJECTOR MAIN" EICAS MASTER CAUTION CAME ON AND L ENGINE RUNNING ROUGH. "FUEL IMBALANCE" EICAS CAME ON, CENTER FUEL TANK NOW @ 1600 LBS. LT ENGINE SHUT DOW N CARRIED OUT. RECTIFICATION: AFTER INVESTIGATION, FOUND A COUPLING DISCONNECTED ON MAIN LT ENGINE FUEL FEED LINE LOCAT ED IN THE CENTER TANK. REASON WHY THE CENTER TANK WAS @ 1600 LBS AND CAUSED AN IMBALANCE. FOUND SLEEVE/COUPLING DAMAGE D. NEW COUPLING ASSEMBLY REINSTALLED PROPERLY ON ENGINE FUEL FEED LINE, ENGINE RUNS, LEAK CHECK CARRIED OUT AND ACFT BA CK IN SERVICE 2 L 7 2 4F 4 F RT A21EA E15NE 20081110 NM 2008 11 10 CA080715001 1 20080625 G 2913 6617303 PUMP BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA HYDRAULIC SYS FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 4584 (CAN) DURING CRUISE FLIGHT EDP NR 1 FAILED AND HYDRAULIC PRESSURE WAS LOST. SPU TURNED ON THEN TURNED OFF DUE TO LOSS OF HYDRAULIC FLUID NR 1 SYSTEM. ACFT LANDED AT DESTINATION AIRPORT WITHOUT INCIDENT. GROUND INSPECTIONS REVEALED METAL I N CASE DRAIN FILTER. EDP REPLACED AND ACFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E00062EN 20081110 CE 2008 11 10 CA080715002 1 20080715 G 5342 04310093 ATTACH FITTING CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 11005 (CAN) LT ATTACH FITTING CRACKED AT LOWER OUTSIDE RADIUS ADJACENT TO AN 4-6A ATTACH BOLT. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 20081112 CE 2008 11 12 CA080715003 1 20080702 G 2421 COMMUTATOR KELLY CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO ALTERNATOR FAILED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC DE DESCENT 1 CA 289 (CAN) FLIGHT CREW NOTICED THE ALTERNATOR WAS NOT CHARGING ON DESCENT. UPON CLOSER INSPECTION IT WAS FOUND THAT THE COMMU TATOR AND BRUSHES WITHIN THE RECENTLY O/H ALTERNATOR SHOWED SIGNS OF SIGNIFICANT ABNORMAL WEAR. THE ALTERNATOR WAS LOW TIME AND HAD NOT GONE THROUGH ITS 500 HR INSPECTION YET SO IT WAS DETERMINED THAT THE WEAR HAD BEGUN FROM THE TIME OF O/ H. THE ALTERNATOR WAS REPLACED WITH ANOTHER O/H ALTERNATOR & RETURNED TO SERVICE. 1 H 7 1 3O 3 O A4CE E5CE 20081112 EU 2008 11 12 CA080715004 1 20080714 G 2421 31342001 SHAFT SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R389 R3894123F25 NE GENERATOR SHEARED W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CR CRUISE 1 CA 418 (CAN) RT AC GENERATOR FAIL LIGHT ILLUMINATED IN FLIGHT, SYSTEM WAS DEFERRED AS PER THE MEL. WHEN ACFT WAS AT A MX BASE, THE AC GENERATOR WAS REMOVED AND FOUND TO HAVE A SHEARED SHAFT. GENERATOR WAS REPLACED. NO FURTHER ISSUES. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P30NE 20081112 EU 2008 11 12 CA080715005 1 20080711 G 5415 417157001 BRACKET SNIAS 350 AS350BA 8680817 EU LYC LTS101 LTS101* NE FUEL FILTER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 175 (CAN) DURING THE 100 HRS INSPECTION ON THE ENGINE, THE AME DISCOVERED 2 CRACKS ON THE ENGINE HIGH PRESSURE FUEL FILTER S UPPORT, 1 AT THE TOP AND 1 AT THE BOTTOM ASSEMBLY HOLDING HOLES GOING FROM EACH HOLE TO THE EDGE OF SUPPORT. 1 G 7 1 3U 3 U NC H9EU E5NE 20081112 SO 2008 11 12 CA080715006 2 20080708 G 8530 STUD SUPERIOR CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO CYLINDER HEAD FAILED W A UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 CA 735 (CAN) A COMPLETE SEPARATION OF THE CYLINDER HEAD FROM THE BARREL OCCURRED. THE SEPARATION SEEMED TO HAVE STARTED IN THE EXHAUST PORT AREA. 1 H 7 1 3O 3 O A4CE E5CE 20081112 SW 2008 11 12 CA080715007 1 20080715 G 6410 206011809005 PITCH HORN BELL BELL 206 206B 1181511 SW ALLSN 25OC 250C20R GL T/R HUB DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) THE PITCH HORN STUD FAILED WHILE INSTALLING A NUT P/N MS14145L5. A "CLICKER-TYPE" TORQUE WRENCH SET TO 60 INCH/LBS WAS USED TO INSTALL THE NUT. THE REQUIRED FINAL TORQUE FOR THIS NUT IS 50-60 INCH/LBS PLUS TARE. THE TIGHTENING TORQUE NEVER REACHED 60 INCH/LBS. 1 G 7 1 3U 3 U H2SW E4CE 20081112 CE 2008 11 12 CA080716001 1 20080715 G 2121 99101133 COOLING FAN CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE NOISY W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) FLOOD COOLING FAN NOISY. FUNCTIONAL CHECK CONFIRMED SNAG, UNIT REMOVED FROM ACFT AND REPLACED WITH OVERHAULED UNI T. 1 L 7 2 4F 4 F A22CE E1NE 20081112 EA 2008 11 12 CA080716002 1 20080710 G 2810 K215T640024 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE NR 4 LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) FUEL LEAK FROM RT WING. CHANGED NR4 RT PN-K215 T64002-4 SN 89306. 2 H 7 2 4T 4 T RT A14EA E20NE 20081112 EU 2008 11 12 CA080716003 1 20080714 G 5415 417157001 BRACKET SNIAS 350 AS350BA 8680817 EU LYC LTS101 LTS101* NE FUEL FILTER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 790 (CAN) CRACK DISCOVERED DURING ENGINE VISUAL INSPECTION ON THE HIGH PRESSURE FUEL ASSEMBLY SUPPORT, CRACK ON THE TOP HOLD ING HOLE, FROM HOLE TO THE EDGE OF SUPPORT. 1 G 7 1 3U 3 U NC H9EU E5NE 20081112 EU 2008 11 12 CA080716004 1 20080624 G 6220 350A31182703 FREQ ADAPTER SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE MAIN ROTOR HEAD WORN W O OTHER O OTHER NR NOT REPORTED 1 CA 5299 (CAN) WORN TO SERVICEABLE LIMITS, RUBBER DEBONDING FROM ITS METHC SURFACE. REPLACED WITH A NEW SET. 1 G 7 1 3U 3 U H9EU E19EU 20081112 EU 2008 11 12 CA080716007 1 20080707 G 5350 FAIRING AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE FUSELAGE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FIRST AIR HAS OBSERVED SEVERAL OCCURRENCES OF DEGRADATION IN THE SURFACE PROTECTION COATING ON THE ACFT LOWER CENT ER SECTION FAIRING PANELS. THE MATERIAL IS APPLIED IN ACCORDANCE WITH ATR SERVICE BULLETIN ATR42-53-0102. INVESTIGATION HAS FOUND THAT THE DEGRADATION APPEARS TO BE ATTRIBUTED TO FLUID CONTAMINATION FROM THE HYDRAULIC SYSTEMS WHICH ARE HOUS ED WITHIN THE LANDING GEAR BAY AREA WHICH IS FAIRED IN BY THE AFFECTED PANELS. 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 20081112 NM 2008 11 12 CA080716008 1 20080714 G 2781 H1010271 POSITION SWITCH BOEING 727 727243 138408D NM PWA JT8 JT8D9A 52048 NE NR 6 L/E SLAT MALFUNCTIONED W L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 CA 1450 (CAN) ON APPROACH AN IN-TRANSIT INDICATION WAS ILLUMINATED ON THE NR 6 L/E SLAT. THE CREW ELECTED TO RETURN TO VANCOUVER WHERE THEY LANDED WITHOUT INCIDENT. INSPECTION REVEALED THAT THE NR 6 L/E SLAT WAS FUNCTIONING CORRECTLY BUT THE L/E SL AT POSITION SWITCH WAS UNSERVICEABLE. THE SWITCH WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE. 2 L 7 3 4F 4 F RT A3WE E2EA 20081112 2008 11 12 CA080716009 4 20080716 G 2562 E01G G SWITCH ELT STICKING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ANNUAL BENCH RECERTIFICATION OF ELT, THE OPS OF THE G-SWITCH WAS TESTED AND FOUND TO BE STICKING INTERMITTE NTLY. THE G- SWITCH WAS REPLACED AND OPS WAS TESTED SEVERAL TIMES TO ENSURE NEW G SWITCH IS OPERATING CORRECTLY. NO FU RTHER PROBLEMS NOTED 20081112 GL 2008 11 12 CA080717001 2 20080705 G 7323 23076061 GOVERNOR BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL TURBINE MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 246 (CAN) DURING GROUND RUN THE GOVERNOR WOULD NOT MAINTAIN ENGINE RPM. REMOVED AND SERVICEABLE GOVERNOR INSTALLED. 1 G 7 1 3U 3 U H2SW E4CE 20081112 WP 2008 11 12 CA080717002 1 20080714 G 6310 C0512REVU ACTUATOR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE CLUTCH INOPERATIVE W O OTHER O OTHER NR NOT REPORTED 1 CA 1067 (CAN) THE CLUTCH WOULD NOT ENGAGE, FERRY FLIGHT PERMIT APPROVED AND ACFT RETURNED TO BASE. THE MICROSWITCH WAS FOUND FAU LTY, CLUTCH ACTUATOR R&R WITH A SERVICEABLE ACTUATOR 1 G 7 1 3O 3 O H11NM 1E4 20081112 NM 2008 11 12 CA080717003 1 20080716 G 5347 17003263001 SEAT TRACK EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 5800 (CAN) EVIDENCE OF CORROSION FOUND AT SEVERAL AREAS. REFERENCE: J/C NR Z220-005-U & NON-ROUTINE NR 46, 48 CORROSION FOUN D ON FLOOR BEAM LOCATED AT Y = 225.0 AND Z = -490.0 JUNCTION WITH FRAMES 17 AND ON FLOOR BEAM LOCATED AT Y = -255.0 AND Z = -490.0 JUNCTION WITH FRAME NR 19. SEAT TRACKS AFFECTED: P/N 170-03264-001 AND P/N 170-03263-001 2 L 7 2 4F 4 F RT A56NM E00063EN 20081112 EU 2008 11 12 CA080717005 1 20080715 G 6730 SC5083SN2353 SERVO SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE MALFUNCTIONED W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 CA 2017 (CAN) ON A EUROCOPTER AS350 B2 DURING HYDRAULIC TEST PROCEDURES FOR FIRST FLIGHT OF THE DAY THE PILOT ENCOUNTERED THE C YCLIC BEING DRIVEN HARD OVER TO THE LT STOP. DURING TROUBLESHOOTING THIS PROBLEM WAS NOT EASILY REPEATABLE EVERYTIME THE TEST WAS COMPLETED. REMOVAL OF THIS COMPONENT HAS SO FAR REMOVED THE ISSUE. THE SERVO HAS BEEN SENT OUT FOR TEST AND RE PAIR. 1 G 7 1 3U 3 U H9EU E19EU 20081112 SW 2008 11 12 CA080718001 1 20080713 G 6230 BEARING BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE M/R MAST DAMAGED W A UNSCHED LANDING J WARNING INDICATION HO HOVERING 1 CA 6478 17 (CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPS, UPON DESCENT WITH AN EXTERNAL LOAD, THE MASTER CAUTION WARNING INDICATI ON ILLUMINATED. THE PIC CHECKED THE CAUTION PANEL TO FIND A TRANSMISSION OIL PRESSURE CAUTION LIGHT ILLUMINATED AND THE TRANSMISSION OIL PRESSURE GAUGE INDICATING ZERO PRESSURE. THE PIC DISCONTINUED ANY FURTHER OPS AND PROCEEDED TO LAND NOR MALLY IN AN ADJACENT CUT BLOCK. A POST-SHUTDOWN INSPECTION BY THE AME REVEALED AN ABUNDANCE OF ALUMINUM METAL SHAVINGS I N THE OIL SYSTEM AND OIL FILTER. FURTHER DISASSEMBLY AND INSPECTION OF THE OIL SUMP SCREEN AND SUBSEQUENT REMOVAL OF THE OIL PUMP INDICATED EVEN MORE METAL SHAVINGS BUT THE ORIGIN OF THE MATERIAL COULD NOT DETERMINED. DURING THE FIELD REMO 1 G 7 1 4U 4 U H1SW E17EA 20081112 EU 2008 11 12 CA080718002 1 20080715 G 3222 5322012289 DRAG LINK PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TAIL GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 7560 (CAN) THIS IS THE 4TH LINK WE HAVE FOUND CRACKED IN OUR FLEET IN SAME LOCATION. PLEASE SEE PREVIOUS SDR`S FOR PICTURES. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081112 EA 2008 11 12 CA080718003 1 20080712 G 5610 NP139322001 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA (CAN) FLT NR 5820, CAPTAINS SIDE WINDSHIELD CRACKED. WINDOW CRACKED FROM LOWER LT CORNER TO UPPER RT CORNER. CALLED AMER ICAN EAGLE AND THEY DETERMINED IT WAS THE INNER PLY. ACFT TO FERRY IN THE MORNING TO COS. CAPTAIN SIDE WINDSHIELD R&R. 2 L 7 2 4F 4 F RT A21EA E15NE 20081112 EU 2008 11 12 CA080718004 1 20080717 G 3251 176SF2DT102W0162 POTENTIOMETER DORNER DO228 DO228202 2992030 EU GARRTT TPE331 TPE331* 01514 WP STEERING MALFUNCTIONED W C ABORTED TAKEOFF H ELECT. POWER LOSS-50 PC TO TAKEOFF 1 CA 7 (CAN) ON TAKE OFF ACFT ROTATED PILOT FELT SOMETHING ABNORMAL IN RUDDER PEDALS, SELECTED GEAR UP , GEAR HANDLE WOULD NOT MOVE, PILOT OBSERVED GEAR HANDLE LOCK STILL IN PLACE. ACFT FLOWN BACK TO BASE , PILOT DID A LOW FLYBY WHERE IT WAS CONFI RMED THAT THE NOSE GEAR STEERING WAS ALL THE WAY TO THE LT. ACFT LANDED SAFELY UPON NOSE TOUCHED DOWN IT CENTERED ITSEL F AND WAS TAXIED BACK USING ENGINE DIFFERENTIAL POWER. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE STEERING POTENTI OMETER HAD FAILED CAUSING THE NOSE GEAR TO GO LT DISENGAGING THE NOSE GEAR STEERING NOT ALLOWING THE NOSE GEAR CENTERING SWITCH TO CENTER GEAR FOR GEAR RETRACTION. 2 H 7 2 4T 3 T RT A16EU E2WE 20081112 EA 2008 11 12 CA080718005 2 20080714 G 7314 91380003 PUMP BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA FUEL SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 3516 (CAN) AFTER REPLACING THE ENGINE, A LEAK CHECK WAS COMPLETED AND IT WAS FOUND THAT THE LP FUEL PUMP WAS LOOSING FUEL OUT THE VENT LINE. THE PUMP WAS REPLACED WITH NO FURTHER PROBLEMS. 1 L 7 2 4T 4 T A24CE E4EA 20081112 NE 2008 11 12 CA080718006 2 20080714 G 8530 127951 WASHER CNDAIR CL215 CL2151A10 1900320 EA PWA R2800 CA3 52026 NE INTAKE VALVE BROKEN W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1188 (CAN) DURING AN OIL LEAK REPAIR ON THE R2800 RT ENGINE, IT WAS DISCOVERED THAT THE ROCKER CAP ON CYLINDER NR 4 WAS CRACK ED. CAP WAS REMOVED AND FOUND THAT 1/3 OF THE INTAKE VALVE UPPER WASHER WAS BROKEN OFF AND THE PIECE WAS LAYING IN THE R OCKER BOX AREA. INSPECTION REVEALED THAT THE WASHER PIECE HAD BEEN PUSHED AROUND THE ROCKER BOX AREA, CRACKING THE ROCKE R CAP, DAMAGING THE INTAKE VALVE SPRING, AND SCRATCHING THE INTERIOR OF THE ROCKER BOX AREA. MAIN ENGINE OIL SCREEN WAS CHECKED FOR CONTAMINATION. SMALL AMOUNT OF NON FERROUS METAL FOUND IN SCREEN. SCREEN CLEANED AND RE-INSTALLED. NR 4 CYL INDER WAS REPLACED WITH AN OVERHAULED UNIT. ACFT RUN UP, ENGINES CHECKED FOR POWER AND LEAKS, AND ACFT WAS RETURNED TO S 2 H 7 2 4R 4 R RT A14EA E231 20081112 SW 2008 11 12 CA080718007 1 20080717 G 6320 206040184001 PUMP BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TRANSMISSION DISLODGED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION HO HOVERING 1 CA 28 (CAN) THE SEAL FOR THE TRANSMISSION OIL PUMP BECAME DISLODGED, AND LOSS OF OIL OCCURRED. 1 G 7 1 3U 3 U H2SW E4CE 20081112 CE 2008 11 12 CA080721001 1 20080714 G 4997 WIRE LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE APU CHAFED W F ACTIVATE FIRE EXT. N FALSE WARNING TX TAXI/GRND HDL 1 CA 30 (CAN) PATS APU INSTALLATION STC SA95-34 FIRE WARNING AFTER 20 MIN OF APU OPERATION PRIOR TO ENGINE START. APU AUTO SHUTD OWN AND FIRE EXT FIRED. VISUAL INSPECTION OF EXTERIOR OF APU ENCLOSURE SHOWED NO EVIDENCE OF FIRE. APU REMOVED AND FOUND WIRES APU2002-20B, APU200-20A AND APU1019-16 CHAFED. APU2000-20A HAD SHORTED TO FIRE LOOP IN 2 LOCATIONS RESULTING IN ARCING AND OVERHEAT OF THE LOOP IN THAT LOCATION. ALL WIRING REPLACED, HIGH TEMP SPIRAL WRAP INSTALLED TO PROTECT WIRING . BOMBARDIER ADVISED VIA FIELD SERVICE REP. 2 L 7 2 4F 4 F RT A10CE E35NE 20081112 CE 2008 11 12 CA080721003 1 20080721 G 5552 26340231 FITTING CESSNA CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE BEARING SUPPORT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE MOVEMENT OF THE ELEVATOR WAS NOTED AS NOT BEING `SMOOTH`. ON INVESTIGATION IT WAS FOUND THAT THE BEARING IN TH E SUPPORT BRACKET WAS SEIZED AND THAT THE SUPPORT BRACKET ALSO HAD CORROSION. THE BRACKET (AND BEARING) WILL BE REPLACED WITH NEW BEFORE NEXT FLIGHT. 1 H 7 1 3T 3 T A37CE E4EA 20081112 WP 2008 11 12 CA080721005 1 20080721 G 6310 C0511 ACTUATOR ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA CLUTCH DAMAGED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) DURING 100 INSPECTION AND ACTUATOR FUNCTION TEST, 1 OF THE COLUMN SPRINGS SWITCH DID NOT RESPOND. FANWHEEL ASSY RE MOVED AND SWITCHES CHECKED MANUALLY AND FOUND SERVICEABLE. IT SEEMS LIKE THE SPRINGS ON 1 SIDE DID NOT PUSH THE SWITCH C OMPLETELY AND THERE WAS ONLY 1 SWITCH ACTIVE. ACTUATOR ASSEMBLY SENT TO R.H.C. 1 G 7 1 3O 3 O H11NM E295 20081112 SW 2008 11 12 CA080722001 1 20080713 G 6320 BEARING BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE M/R MAST DAMAGED W A UNSCHED LANDING J WARNING INDICATION HO HOVERING 1 CA 6478 17 (CAN) UPON DESCENT WITH AN EXTERNAL LOAD, MASTER CAUTION WARNING INDICATION ILLUMINATED. THE PIC CHECKED THE CAUTION PAN EL TO FIND A TRANSMISSION OIL PRESSURE CAUTION LIGHT ILLUMINATED, TRANSMISSION OIL PRESSURE GAUGE INDICATING ZERO PRESSU RE. A POST-SHUTDOWN INSP BY AME REVEALED AN ABUNDANCE OF ALUMINUM METAL SHAVINGS IN THE OIL SYS AND OIL FILTER. FURTHER DISASSEMBLY AND INSP OF OIL PUMP INDICATED EVEN MORE METAL SHAVINGS BUT ORIGIN OF THE MATERIAL COULD NOT DETERMINED. DU RING THE FIELD REMOVAL OF THE TRANSMISSION, IT WAS DISCOVERED THAT THE LOWER BEARING RACE RETAINING NUT ON THE MAST ASSY HAD BROKEN FREE OF IS TORQUE AND LOCKING DEVICE. NUT BACKED OFF ALL THE WAY TO LAST THREAD CARVING A ONE INCH DEEP GROO 1 G 7 1 4U 4 U H1SW E17EA 20081112 EU 2008 11 12 CA080722002 1 20080707 G 2731 EM40112 ACTUATOR PIAGIO PIAGIO P180 P180 6960204 EU PWA PT6 PT6A66 52043 NE HARTZL HCE5N HCE5N3 GL ELEVATOR TRIM MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA 605 (CAN) THE HORIZONTAL STABILIZER PRIMARY TRIM FAILED IN THE DOWN MODE ONLY. THE ACFT THEN PROCEEDED TO THE NEAREST AIRPOR T. MAINT CONFIRMED THE SNAG ON THE GROUND. AFTER REPLACING THE HORIZONTAL TRIM ACTUATOR THE SYS FUNCTIONED NORMAL. 1 H 7 2 3O 4 T RT A59EU E26NE 5 C PZONE 20081112 EU 2008 11 12 CA080722003 1 20080716 G 6310 350A351069 GIMBAL PIN SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ACFT WAS INSPECTED FOLLOWING A HARD LANDING, MAIN AND TAIL ROTOR STRIKES IAW MET 05.53.00.603, 604 AND 605. GIMBA L PINS (ALL 4 OF THEM) WERE SENT ALONG WITH OTHER PARTS FOR NDT (NO REQUIREMENT TO CHECK THE GIMBAL PINS AFTER AN INCIDE NT), AND 3 OF 4 WERE FOUND TO HAVE CRACKS IN THE FLANGED END, CAUSING REJECTION OF THE 3 PINS. PINS ARE PART OF ENG TO MAIN GEAR BOX COUPLING, HOLDING COUPLING TUBE TO GIMBAL RING AND GIMBAL RING TO ROTOR BRAKE HSG. DAMAGED ACFT HAS YET T O BE REASSEMBLED TO FLIGHT CONDITION). 1 G 7 1 3U 3 U H9EU E19EU 20081112 NE 2008 11 12 CA080722004 2 20080718 G 7314 SEAL CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL FUEL PUMP LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 4973 (CAN) ON DAILY INSP, FUEL WAS DISCOVERED IN THE OIL SEAL DRAIN COLLECTOR CAN. FURTHER INVESTIGATION FOUND FUEL LEAKING F ROM THE SEAL ON THE FUEL HIGH PRESSURE PUMP. THERE WAS NO INDICATION OF GREASE WASH OUT OF THE FCU BRG. THE FUEL PUMP WA S REPLACED WITH A SERVICEABLE UNIT. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20081230 EU 2008 12 30 CA080722005 1 20080716 G 6230 350A37122021 STOP TMECA SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE M/R SHAFT CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 6074 (CAN) ON ROUTINE MAST RECONDITIONING AND INSP (6 YEAR INSP REQUIREMENT), THE RING WAS SENT FOR NDT ALONG WITH THE REST O F THE PARTS FROM THE ASSY (NO NDT REQUIREMENT FOR THE RING AT ANY POINT, OR FOR ANY PART OF THE ASSY AT THE 6 YEAR INSP) . THERE WAS A STRESS CRACK DURING MPI CHECK, WHICH WAS CAUSE FOR REJECTION OF THE PART. THE RING IS LOCATED AT THE TOP OF THE MAIN ROTOR SHAFT, WHERE THE ROTOR HEAD ATTACHES, AND ROTATES WITH THE MAIN ROTOR SHAFT/HEAD. THE CUSTOMER WAS NOT IFIED OF THE DEFECT AND THE PART WAS REPLACED. 1 G 7 1 3U 3 U H9EU E19EU 20081112 EA 2008 11 12 CA080722007 1 20080718 G 5700 C6FSM244335 BUSHING DHAV DHC6 DHC6 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL WING LUG MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BUSHINGS MISSING FROM WING PICKUP LUGS ON ORIGINAL FRAMES INSTALLED IN ACFT. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081112 2008 11 12 CA080722008 2 20080722 G 7414 M3548 ROTOR MAGNETO BROKEN W K NONE P NO WARNING INDICATION IN INSP/MAINT 1 CA 364 (CAN) MAGNETO INSPECTED FOR SB 2-08/3-08 COMPLIANCE. DISTRIBUTOR GEAR FAILED, ROTOR GEAR FAILED, CARBON BRUSH FAILED. DU RING REMOVAL OF ROTOR GEAR FOR REPLACEMENT, BROKEN POST LODGED IN GEAR. DISTRIBUTOR GEAR AND ROTOR GEAR WERE HOLDING THE BROKEN POST IN PLACE DURING OPERATION. EDGE OF BROKEN POST WAS WORN INDICATING BREAK OCCURRED SOME TIME AGO. 20081112 NE 2008 11 12 CA080722009 1 20080722 G 7603 S6130620173 THROTTLE PLATE SKRSKY S61 S61A 814210C NE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) S61 ENGINEERS WERE REPLACING A EMERGENCY THROTTLE PLATE P/N S6130-62017-3 WITH A PLATE THAT HAD BEEN RECEIVED. ON INSTALLATION WHEN TIGHTENING THE BOLTS, THE PLATE SHATTERED AT THE FWD BOLT HOLE. ALL 10 PLATES RECEIVED IN FROM THIS VE NDOR HAVE BEEN ACCOUNTED FOR AND ARE IN QUARANTINE. PRELIMINARY INSP OF THE PART HAVE REVEALED THE FOLLOWING: DEFECTIVE PLATE WAS IDENTIFIED WITH THE PROPER P/N IAW THE S61 IPC FIGURE 118 ITEM 25 AND APPEARED TO MEET FIT FORM AND FUNCTION. A TEST DONE ON ONE OF THE PLATES REMOVED FROM SERVICE WHICH INDICATED THE PART TO BE FERROUS, HOWEVER WAS EXTREMELY BR ITTLE AS IT FAILED INSTANTLY UNDER MINIMAL PRESSURE WITHOUT BENDING. SUSPECTED BOGUS PARTS. 2 G 7 2 4U H2EA 20081112 NM 2008 11 12 CA080723001 1 20080720 G 3260 7002537 CONTROL UNIT DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE MLG MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING LD LANDING 1 CA 673 (CAN) LANDING GEAR INOPERATIVE CAUTION LIGHT ILLUMINATED DURING DESCENT, LIGHT WAS CONTINUOUS ALL THE WAY BACK TO BASE. REMOVED AND REPLACED ADVISORY CONTROL UNIT IAW AMM 33-13-00. PERFORMED LANDING GEAR RETRACTION TEST-RESULTS SATISFACTORY . 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081112 NE 2008 11 12 CA080723002 2 20080708 G 7261 RETAINING NUT PWC PW308 PW308C 52182 NE OIL PUMP ASSY DISLODGED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 791 (CAN) THE LOW OIL PRESSURE WARNING ACTIVATED DURING TAKEOFF ROLL AND TAKEOFF WAS ABORTED. SUBSEQUENT INSP REVEALED THE O IL PUMP GEARSHAFT RETAINING NUT AND TAD WASHER COMPLETELY DISLODGED FROM THE SHAFT. MFG WILL INVESTIGATE TO REVIEW ASSY PROCEDURES AND REPORT ON ROOT CAUSE ONCE ESTABLISHED. 4 F E00065EN 20081112 GL 2008 11 12 CA080723003 3 20080718 G 6111 SEALANT AIRTRC AT802 AT802 0390305 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MA3 GL BLADE CLAMP FAILED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB OUT PILOT EXPERIENCED A BUILD UP OF GREASE ON WINDSHIELD. PILOT ABORTED LOAD IN DESIGNATED AREA AND R ETURNED TO BASE. UPON INSP GREASE APPEARED TO BE COMING FROM 1 OR 2 BLADE CLAMPS. BLADE CLAMP SEALS WERE REPLACED IN BOT H UNITS. NO OBVIOUS DAMAGE WAS FOUND ON REMOVED SEALS OR PROP ASSY. SEALANT MAY HAVE FAILED. ACFT WAS RETURNED TO SERVIC E AFTER GROUND FUNCTION CHECKS. 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 20081112 EU 2008 11 12 CA080723004 1 20080527 G 6710 350A27134320 STOP AEROSP AS355 AS355F2 8680812 EU ALLSN 250C 250C20B 03013 GL COLLECTIVE DAMAGED W O OTHER W INADEQUATE Q C NR NOT REPORTED 1 CA (CAN) ACFT WAS CLIMBING AT APPROX 6000` ASL. (OAT 1°C). COLLECTIVE HIT ITS UPPER STOP DURING A POWER INCREASE. AT THIS P OINT TORQUE READING WAS APPROX 65 PERCENT. T4 AND NG WERE WELL WITHIN MAX CONTINUOUS LIMITATIONS. ON 14 MAY 2006, SB 67 .00.12 REV. 2 WAS CARRIED OUT ON THE ACFT. THIS MODIFICATION INVOLVED THE INSTALLATION AND POSITIONING OF A NEW STOP PLA TE ON THE UPPER PART OF THE COLLECTIVE QUADRANT. POSITIONING THIS STOP PLATE (P/N 350A27-1343-20) IAW INSTRUCTIONS PROVI DED IN SB 67.00.12 REV. 2 PARAGRAPH 2.B.2 RESULTS IN THE UPPER COLLECTIVE TRAVEL BEING LIMITED. END RESULT WAS THE SERVO INPUT RODS UPWARD TRAVEL BEING LIMITED BY APPROX 6MM AT FULL COLLECTIVE. PARAGRAPH 2.B.3. OF SB 67.00.12 REQUIRES THAT 1 G 7 2 3U 3 U H11EU E4CE 20081112 EU 2008 11 12 CA080723005 1 20080722 G 2730 Z4244120000 CABLE ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA MUHBR MTV MTV9* EU ELEV TRIM TAB FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 1899 (CAN) CABLE WAS DISCOVERED FRAYED DURING REGULARY SCHEDULED MAINT. 1 L 7 1 3O 3 O 0 A76EU 1E10 5 C P24NE 20081112 CE 2008 11 12 CA080723006 1 20080721 G 2421 ALTERNATOR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL FAILED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) DURING CRUISE, PILOT NOTICED KX155 NAV/COM FLASHING ITS DISPLAY AND VOR NEEDLE ERATIC. PILOT DECLARED NORDO AND LA NDED SAFELY WITHOUT FURTHER INCIDENCE. MAINT ATTEPTED TO START ACFT AND DISCOVERED BATTERY ALMOST DEAD. ACFT CHARGING SY S HAD MALFUNCTIONED DURING FLIGHT AND PILOTS WERE UNAWARE OF THE PROBLEM. MFG INSTALLED AMMETER SHOWS VERY LITTLE NEEDLE DEFLECTION WHEN SYS IS OPERATING NORMALLY, EVEN UNDER HEAVY LOAD. ALSO, EARLIER 152`S WERE PROVIDED WITH AN OVERVOLT RE D LIGHT ONLY. LATER 152S INCORPORATE AN UNDERVOLT LIGHT WHICH IS MORE USEFULL. MAINTENANCE CHARGED BATTERY AND REPAIRED BROKEN RING TERMINAL ON ALTERNATOR FIELD WIRE, ACFT RETURNED TO SERVICE. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 20081112 WP 2008 11 12 CA080724001 1 20080707 G 2822 C81878 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL BOOST FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 610 (CAN) FUEL PUMP WARNING LIGHT ILLUMINATED IN FLIGHT. AUX. PUMP HAD FAILED. ENGINE CONTINUED RUNNING ON MECHANICAL PUMP. A/C FLOWN TO MAINT BASE, ELECTRIC PUMP REPLACED. FUNCTION AND LEAK CHECK PERFORMED. CAUSE OF PUMP FAILURE UNKNOWN. 1 G 7 1 3O 3 O H11NM 1E4 20081112 WP 2008 11 12 CA080724003 2 20080717 G 7230 31037081 BEARING SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33110UG 01514 WP MCAULY 4HFR34 4HFR34C652 NE COMPRESSOR SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 1917 (CAN) SN OF THE PART IS MS030633106124 WAS UNABLE TO PUT THIS INTO SN FIELD. A/C WAS DOWN FOR A ROUTINE OIL SAMPLE. AT THIS TIME THE OIL SAMPLE WAS NOTED TO HAVE A UNUSUAL AMOUNT OF METAL IN THE OIL SAMPLE. THE ENGINE SHOP WAS INFORMED TO HAVE A LOOK AT THE METAL AND IT WAS DETERMINED FROM ENGINE SHOP THAT THE ENGINE NEEDED REPAIR AT THAT TIME. UPON DISSASE MBLY OF THE ENGINE GEAR BOX IT WAS FOUND THAT THE COMPRESSOR BALL BEARING WAS STARTING TO HAVE METAL SPAWLING COMING FRO M THE INNER RACE. THE ENGINE WAS REPAIRED ON WING AND WITH A NEW COMPRESSOR BEARING ALL METAL FLUSHED FROM ENGINE AND TH E A/C WAS RETURNED TO SERVICE WITH NO MORE ISSUES. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 20081112 CE 2008 11 12 CA080724004 1 20080721 G 7720 INDICATOR BEECH 100 100BEECH 1152916 CE GARRTT TPE331 TPE3316252B 01514 WP HARTZL HCB4T HCB4TN5 GL ITT MALFUNCTIONED W O OTHER N FALSE WARNING CR CRUISE 1 CA (CAN) WHILE RETURNING TO HOME BASE AT CRUISE FLIGHT, FLIGHT CREW NOTICED THAT THE LT ITT GAUGE WAS ERRATIC. THERE WAS NO NOTICE IN ENGINE PERFORMANCE NOR WERE ANY OF THE REMAINING ENGINE INSTRUMENTS SUPPORTING ENGINE PERFORMANCE ISSUES. UPO N RETURN TO BASE, MAINT TROUBLESHOT THE ITT SYS AND DISCOVERED THAT THE ITT HARNESS HAS 3000 OHMS TO GROUND WHERE THE MI NIMUM LIMITS ARE 100000 OHMS. A NEW HARNESS HAS BEEN ORDERED AND WILL BE INSTALLED. THIS SDR HAS BEEN REPORTED PREVIOUSL Y UNDER SDR’S 20080103005 AND 20070223002. SUPPLEMENTARY SDR TO FOLLOW WITH ASSY AND PART FAILURE INFORMATION. 1 L 7 2 3T 4 T A14CE E2WE 6 C P40EA 20081112 NE 2008 11 12 CA080724006 2 20080717 G 7321 0164548250 FUEL CONTROL TMECA ARRIEL ARRIEL1D1 60053 NE ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 561 (CAN) MAIN ROTOR RPM KEPT DECREASING AFTER ADJUSTMENT, OIL ALSO FOUND IN THE INPUT SEAL DRAIN TUBE. NO LONGER ABLE TO AD JUST IAW MM. UNIT REPLACED WITH SERVICEABLE FCU AND DEFECTIVE UNIT SENT TO MFG FOR INVESTIGATION AND WARRANTY REPAIR. 3 U E19EU 20081112 WP 2008 11 12 CA080724007 1 20080722 G 3411 PITOT SYSTEM DOUG DC6 DC6B 3021712 WP PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE NR 2 CLOGGED W C ABORTED TAKEOFF G MULTIPLE FAILURE TO TAKEOFF 1 CA (CAN) BOTH NR 1 AND NR 2 PITOT SYS INDICATED NO AIRSPEED ON TAKEOFF RUN. TAKEOFF WAS ABORTED. BUGS AND SIMILAR DEBRIS FO UND IN BOTH PITOT SYS. APAR LINES BLOWN OUT, PITOT SYS FUNCTION CHECKED SERVICEABLE. 2 L 7 4 4R 3 R 6A4 ATC14 6 C P871 20081113 2008 11 13 CA080724008 4 20080628 G 6122 1219310 PLUG WOODWARD DIAMON DA40 DA40 2990002 GL HARTZL HCC2Y HCC2YR1 GL PROP GOVERNOR FAILED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CL CLIMB 1 CA 300 (CAN) WE WERE CLIMBING OUT OF KSBM GOING THRU 4,000 FEET MSL, WHEN THE ENGINE/PROP OVER SPEEDED. IT TOPPED OUT AT SOMETH ING OVER 3,100 RPM. IT TOOK ABOUT 5 TO 10 SECONDS TO GET THE POWER PULLED OFF. BY CAREFUL USE OF THE THROTTLE (2650 RPM MAX), WE WERE ABLE TO MAINTAIN FLYING SPEED, LEVEL FLIGHT AT ABOUT 80 TO 85 KTS. DIVERTED AND DECLARED AN EMERGENCY. TH E LANDING WAS ACCOMPLISHED WITHOUT ANY PROBLEMS AND NO FURTHER DAMAGE WAS SUSTAINED TO THE ACFT. BEGAN THE INVESTIGATI ON INTO WHAT CAUSED THE FAILURE. AFTER ELIMINATING SOME OTHER PROBABLE CAUSES WE CAME TO THE PROPELLER GOVERNOR. IT LOO KS AS IF A SCREW PLUG BACKED OUT OF AN INTERNAL PASSAGE WITHIN THE GOVERNOR, DUMPING THE OIL PRESSURE AND CAUSING THE PR 1 L 7 1 3O NT A47CE 5 C P920 20081112 CE 2008 11 12 CA080725001 1 20080709 G 2460 70002450 CIRCUIT BREAKER CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE LT POWER FEED TRIPPED W O OTHER O OTHER CR CRUISE 1 CA 261 (CAN) LT POWER FEED CIRCUIT BREAKER (ONE OF 3 IN PARALLEL) POPS OPEN IN FLIGHT. P/N 700-024-50 REPLACED NEW. 2 L 7 2 4F 4 F RT A22CE E00059EN 20081112 NE 2008 11 12 CA080725002 1 20080716 G 2913 66WAP2001 BOLT SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE HYD PUMP BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON POST FLIGHT INSP, ONE BOLT HEAD WAS FOUND DETACHED FROM THE PUMP ASSY. HAVE EXPERIENCED ONE PREVIOUS OCCURENCE , SEE SDR20060818006. 2 G 7 2 4U 4 U 1H15 1E3 20090102 EU 2009 1 2 CA080725003 1 20080720 G 2910 HYDRAULIC SYSTEM UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE MALFUNCTIONED W K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 CA (CAN) AT GROUND IDLE, THE NORMAL PROCEDURE IS TO TEST ACCUMULATORS BY PUSHING THE ACCUMULATORS BUTTON ON, AND THE HYD LI GHT ILLUMINATES , AND PROCEED TO TEST THE ACTUATORS BY MOVING THE CYCLIC FWD AND AFT, ABOUT 4-5 INCHES TRAVEL, EIGHT TIM ES, THEN RT AND LT, THE SAME. NORMAL (NORMALLY, DO NOT TOTALLY DEPLETE THE ACCUMULATOR’S PRESSURE). THIS WAS NORMAL, NO PROBLEM ANY OF THE TEST OF THIS SYS AT ANY TIME. PUSH THE SWITCH AGAIN, AND THE ACCUMULATORS BACK ON, HYD LIGHT OUT. T HE HYD CUT OFF TEST. STILL OPERATING AT GROUND IDLE. COLLECTIVE LOCKED DOWN, SWITCHING OFF THE HYD SWITCH ON COLLECTIVE, HYD LIGHT ILLUMINATES, AND WHAT THE CYCLIC IS SUPPOSED TO DO IS PULL IT SELF TO THE CENTER NEUTRAL POSITION, WITH RESIS 1 G 7 2 3U 3 U NC R0001RD E34NE 20081112 NM 2008 11 12 CA080728001 1 20080723 G 2432 20412 BATTERY DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE MASTER OVERTEMP W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 14134 594 (CAN) DURING CRUISE THE CREW RECEIVED A MAIN BATTERY HOT WARNING MESSAGE. THE HIGH TEMP WAS CONFIRMED ON THE BATTERY TEM P MONITOR. THE CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT. THE BATTERY TEMPERATURE WAS EVALUATED AT 180°C. THE BATTERY COMPARTMENT WAS CLEANED, THE BATTERY REPLACED. ACFT WAS RELEASED AND RETURNED INTO SERVICE. BATTERY HAS BEE N RETURNED TO THE COMPANY IN-HOUSE COMPONENT SHOP TO DETERMINE THE CAUSE OF THE THERMAL RUN-AWAY. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081112 NM 2008 11 12 CA080728003 1 20080725 G 2710 PCU BOEING 727 727243 138408D NM PWA JT8 JT8D9A 52048 NE AILERONS FAILED W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ENROUTE, CREW NOTICED HYD SYS (A) QUANTITY DECREASING RAPIDLY. SYS (A) HYDR WERE SHUTOFF AND EMERGENCY DECLARED. U PON ARRIVAL AT DESTINATION, A/C REQUIRED TOWING TO RAMP WHERE MAINT DISCOVERED THE AILERON PCU HAD FAILED. THE AILERON P CU WAS REPLACED AND A/C RETURNED TO SERVICE. 2 L 7 3 4F 4 F RT A3WE E2EA 20081112 EU 2008 11 12 CA080728004 1 20080708 G 2530 8001060000LH OVEN AIRBUS 310 A310304 3930339 EU DIRTY W A UNSCHED LANDING W B INADEQUATE Q C SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA 7873 5582 (CAN) FLIGHT RETURNED TO THE STATION DUE TO CABIN SMOKE FROM FWD OVEN (DARK SMOKE). CABIN DETECTOR ACTIVATED. BOTH FWD O VENS INSPECTED AND ELECTRICAL CONNECTION CHECKED AND FOUND SERVICEABLE. LT OVEN INSERTS FOUND DIRTY (FOOD RESIDUE). OVEN REPLACED AND SERVICEABLE IAW MM25-30-00. OVEN ROUTED TO REPAIR SHOP FOR INVESTIGATION. 2 L 7 2 4F RT A35EU 20081112 EU 2008 11 12 CA080728005 1 20080721 G 2897 NSA931322100 CIRCUIT BREAKER AIRBUS 310 A310300 3930305 EU GE CF6 CF680C2A5 NE FUEL PUMP BURNED W O OTHER H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA (CAN) DURING TROUBLESHOOTING OF THE INOPERATIVE LT OUTER TANK FUEL PUMP (DEACTIVATED IAW MEL) THE CIRCUIT BREAKER 3QA WA S FOUND BURNED, BODY CRACKED AND ONE LEG MISSING. CIRCUIT BREAKER WAS REPLACED AND SYS TESTED SERVICEABLE. A DETAILED VI SUAL INSPECTION CAMPAIN WAS INITIATED TO INSPECT ALL CIRCUIT BREAKERS IN THE 101VU ELECTRICAL PANEL. 2 L 7 2 4F 4 F RT A35EU E13NE 20081112 NM 2008 11 12 CA080728006 1 20080725 G 2897 F759857SC WIRE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE SWITCH CHAFED W O OTHER N FALSE WARNING TX TAXI/GRND HDL 1 CA 40501 40501 (CAN) DURING TAXI, NR2 TANK FUEL LOW LEVEL CAUTION LIGHT ILLUMINATED. MAINT GROUND RUN AND NR2 TANK LOW LEVEL LIGHT INTE RMITTENT. ACFT DISPATCHED UNDER MEL FOR FUEL LOW LEVEL INDICATION. LATER MAINT INSP DURING SWITCH REPLACEMENT, FOUND SWI TCH WIRE CHAFED ON CONDUIT. SWITCH ASSY REPLACED. (NOTE: PART IS CONSIDERED AN EXPENDABLE AND PART TIMES NOT TRACKED. TI ME PROVIDED ARE ACFT TIMES). 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081112 SW 2008 11 12 CA080728007 1 20080722 G 5280 STRUCTURE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE MLG DOOR BENT W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH PILOT EXTENDED GEAR AND HAD GREEN INDICATION FOR NOSE AND LT MAIN GEAR ONLY, INTRANSIT LIGHT WAS ON FO R RT GEAR. PILOT RECYCLED GEAR AND ALL 3 GREEN INDICATIONS WERE NOW PRESENT. ACFT LANDED WITHOUT FURTHER PROBLEMS. MAINT WAS CALLED AS THE RT GEAR DOORS WERE BENT JUST AFT OF THE FRONT HINGE. IT APPEARED THAT THE DOOR WAS HUNG UP ON THE FRO NT EDGE OF THE GEAR DOOR AND WAS BENT WHEN THE GEAR WAS SELECTED DOWN. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 20081112 2008 11 12 CA080728008 4 20080722 G 6122 31039391 FITTING SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE PROP GOVERNOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON INSPECTION, IT WAS DISCOVERED THAT THERE WAS AN OIL LEAK AROUND THE RT ENGINE PROP GOVERNOR. UPON FURTHER INSPE CTION IT WAS FOUND THAT THE FITTING WAS CRACKED HALF WAY AROUND THE FITTING. FITTING REPLACED AND ACFT RETURNED TO SER VICE. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 20081112 EU 2008 11 12 CA080728009 1 20080719 G 6410 355A12004008 BLADE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2989 2989 (CAN) FOUND T/R BLADE CRACKED NEAR TIP OF BLADE AND TRAILING EDGE ON DAILY INSPECTION. BLADE REMOVED FOR EVALUATION BY M FG. 1 G 7 1 3U 3 U H9EU E19EU 20081112 SW 2008 11 12 CA080728010 1 20080704 G 6730 212076005011 PILOT VALVE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA LT CYCLIC CHATTERING W A UNSCHED LANDING E F VIBRATION/BUFFET FLT CONT AFFECTED CR CRUISE 1 CA (CAN) ACFT ENCOUNTERED VIBRATION, FELT THROUGH FLIGHT CONTROLS. VIBRATION WORSENED RAPIDLY DURING RETURN TO BASE. UPON A RRIVAL TO BASE, ENGINEER INSPECTED ACFT AND FOUND LT CYCLIC SERVO PILOT VALVE TO BE CHATTERING EXCESSIVELY, CAUSING UNCO MMANDED CYCLIC INPUTS. ACFT WAS GROUNDED. CYCLIC SERVO REPLACED, A/C TEST FLOWN AND WAS RELEASED FOR RETURN TO SERVICE. SUSPECT SERVO WAS SENT TO O/H FACILITY FOR EVALUATION, FOUND EXCESSIVE WEAR ON PILOT VALVE ASSY. 1 G 7 1 4U 4 U H4SW E22EA 20081112 EU 2008 11 12 CA080729001 1 20080718 G 2120 GUARD PILATS PC12 PC1247 7090552 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL REEFER PACK CUT W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) THE REFRIGERATION PACK MOTOR BELT SLIPPED ON THE MOTOR GEAR CAUSING THE WEAR ON THE GEAR. THE MOTOR GEAR LIP TO ST OP THE BELT FROM GOING OUT OF THE GEAR IS WORN OUT ALSO, CHAFING THE BELT PLASTIC GUARD. THE GUARD IS CUT. 1 L 7 1 4T 4 T RT A78EU E26NE 5 C P210NE 20081112 SO 2008 11 12 CA080729003 1 20080724 G 5310 MS212505 BOLT LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL HAMSTD 54H 54H60117 NE FUSELAGE FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 5040 (CAN) ENROUTE, THE LOAD MASTER OBSERVED AN UNUSUAL SOUND FROM THE CARGO BAY AREA. UPON INVESTIGATION AN UNUSUAL GAP WAS NOTICED BETWEEN THE LANDING GEAR BAY WEB AND THE BOTTOM EDGE OF THE DRAG ANGLE VERTICAL FLANGE. THE GAP WAS ESTIMATED AT .125 FROM STA 570 TO 580. THE CREW ELECTED TO RETURN WHERE THE ACFT LANDED WITHOUT INCIDENT. INVESTIGATION REVEALED TH AT AN APPARENT FASTENER FAILURE COMMON TO THE STA 577 BEAM AND THE DRAG ANGLE GENERATED THE GAP. THE ACFT WAS REPOSITION ED UNDER PERMIT WHERE FURTHER ASSESSMENT IS ONGOING. 2 H 7 4 4T 4 T A1SO E282 6 C P906 20081113 EU 2008 11 13 CA080729006 1 20080727 G 2913 AIR29804 COVER LKHEED BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU HYDRAULIC PUMP LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) WHILE ENROUTE FROM YBK TO YTH FAMO EXPERIENCED LOSS OF HYDRAULIC PRESSURE. AN EMERGENCY WAS DECLARED AND THE ACFT DIVERTED TO YTH WHERE AN UNEVENTFUL LANDING WAS MADE. DURING THE FLIGHT HYDRAULIC PRESSURE WAS SEEN TO RISE AND FALL A N R OF TIMES. EMERGENCY U/C ACTUATION WAS NOT REQUIRED. UNDER INSPECTION THE RT HYDRAULIC PUMP WAS FOUND TO BE LEAKING. TH E PUMP WAS CHANGED AND THE SYSTEM EXHIBITED NO DEFECTS DURING FUNCTION TESTING. THE PUMP WAS INSPECTED AND THE LEAK WAS FOUND TO BE FROM THE TOP EDGE OF THE END COVER THROUGH A NR OF PIN HOLES IN THE CASTING. THERE WERE NO LEAKS THROUGH THE PUMP FIXTURES AND FITTINGS. THE PUMP WILL BE SENT FOR STRIP EVALUATION. 2 L 7 2 3T 4 T A24EU A196 20081112 GL 2008 11 12 CA080729007 1 20080725 G 5730 SKIN DIAMON DA40 DA40 2990002 GL WING DEBONDED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) A INSP CARRIED OUT ON WING, SHOWED GAPS IN THE SPAR TO SKIN BOND LINES. DO NOT BELIEVE THIS TO BE AN IMMEDIATE SAF ETY ISSUE BUT ARE WORKING QUICKLY AND DILIGENTLY TO GET TO ROOT CAUSE AND CORRECTIVE ACTION. 1 L 7 1 3O NT A47CE 20081112 NE 2008 11 12 CA080730001 2 20080623 G 7220 4037T84P03 NUT GE CF34 CF343B1 30070 NE ENGINE MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SHOP VISIT, ONE VARIABLE VANE SPINDLE NUT WAS FOUND MISSING ON STAGE 5 VANE. THE LEVER ARM REMAINED ENGAGED . A NUT WAS INSTALLED IAW THE ENGINE MANUAL 72-32-00 AS RECOMMENDED IAW SB 72-0184. 4 F E15NE 20081112 NM 2008 11 12 CA080730002 1 20080730 G 2611 774001 SMOKE DETECTOR BOEING 727 727225 1384077 NM PWA JT8 JT8D15 52051 NE NR 6 FAILED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 2774 (CAN) ON CLIMB THROUGH FL290 CARGO SMOKE 6TH POSITION LIGHT ILLUMINATED AND FIRE WARNING BELL SOUNDED. ACFT RETURNED. ON ARRIVAL, NO SMOKE DETECTION LIGHTS WERE ILLUMINATED ON FE PANEL. CARGO AREA INSPECTED FOR SMOKE. NONE FOUND. SUSPECTED FAILURE OF NR 6 SMOKE DETECTOR. PART REMOVED AND REPLACED. SYSTEM FUNCTION CHECKED SERVICEABLE. 2 L 7 3 4F 4 F A3WE E2EA 20081112 SO 2008 11 12 CA080730003 2 20080730 G 8530 SPRING ECI CONT O520 IO520F 17032 SO EXHAUST VALVE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 13 (CAN) CYLINDER WAS PULLED DUE TO LOW COMPRESSION. WHEN THE ROCKER COVER WAS REMOVED IT WAS DISCOVERED THAT BOTH THE INNE R AND OUTER EXHAUST VALVE SPRINGS WERE BROKEN INTO MANY PIECES. 3 O E5CE 20081112 EA 2008 11 12 CA080730004 1 20080714 G 5522 85520056 SKIN DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 40619 40619 (CAN) DURING MAINT, VISUAL INSP OF VERTICAL FIN/HORIZONTAL STABILIZER , A CRACK 2.25 INCHES LONG ENCOMPASSING (2) RIVETS AT RIB YH 13.80 EXTENDING FWD FROM A POINT3.5 INCHES FROM THE AFT T/E, WAS NOTED. DAMAGE REPAIR IAW REPAIR DRAWING RD8- 55-1968 AND SRM PRACTICES. AIRCRAFT RETURNED TO SERVICE. DAMAGE BELIEVED TO BE FATIGUE RELATED AS NO NOTED IMPACT DAMAG E. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081112 NE 2008 11 12 CA080730005 2 20080728 G 7321 0164548540 FUEL CONTROL SNIAS 350 AS350* EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE FAILED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) FLUCTUATION OF NG (+/- 2 PERCENT) IN CRUISE FLIGHT. ACFT LANDED AT THE BASE NORMALLY. ENGINE INSPECTED. RUN-UP CAR RIED OUT, NG FLUCTUATION CONFIRMED ON THE GROUND (82.5 TO 84.5 PERCENT), NR FLUCTUATION ON THE GROUND (374 - 380). FCU R EPLACED (PART REMOVED WAS 1369.6 HOURS TSO). TEST FLIGHT CONDUCTED AFTER FCU REPLACEMENT AND FOUND SATISFACTORY. 1 G 7 1 3U 3 U H9EU E19EU 20081112 EA 2008 11 12 CA080730006 2 20080713 G 7200 ENGINE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA FAILED W E ENGINE SHUTDOWN J WARNING INDICATION CL CLIMB 1 CA (CAN) 10 MINUTES AFTER TAKEOFF, THE ENGINE OIL PRESSURE AND TORQUE INDICATION DECREASED BELOW ALLOWABLE LIMITS. THE ENGI NE WAS SHUTDOWN AND SECURED BY THE FLIGHT CREW. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A13NM E00062EN 20081112 EA 2008 11 12 CA080730007 2 20080706 G 7250 ENGINE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA NR 1 ERRATIC W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) DURING TAKEOFF ROLL THE NR 1 ITT DROPPED TO 230 DEGREES AND WAS ERRATIC. THE PILOT ELECTED TO ABORT THE TAKEOFF AN D RETURNED TO THE GATE. TROUBLESHOOTING DISCLOSED FAULT CODE (FC) 973 T6 OPEN CIRCUIT. FURTHER INTERROGATION OF FC CONFI RMED 973 PRESENT ON BOTH A&B CHANNELS. THE T6 HARNESS WAS REPLACED AND THE ACFT RETURNED TO SERVICE. ERRATIC ITT INDICAT ION WAS NOTED BY THE CREW DURING THE PREVIOUS FLIGHT. 2 H 7 2 4T 4 T RT A13NM E00062EN 20081112 NE 2008 11 12 CA080730008 2 20080503 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE POWER LOSS W B A EMER. DESCENT UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB AT APPROX 3,000 FEET ABOVE GROUND LEVEL, PILOT HEARD A LOUD BANG AND EXPERIENCED COMPLETE LOSS OF POW ER . PILOT DECLARED EMERGENCY AND PERFORMED A DEAD STICK LANDING. AN UNEVENTFUL LANDING WAS ACCOMPLISHED. POST INSP REVE ALED CT BLADE DISTRESS. ENGINE WAS REMOVED AND SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND AD VISE OF ROOT CAUSE ONCE ESTABLISHED. 1 H 7 1 3T 3 T A37CE E4EA 20081112 CE 2008 11 12 CA080730009 1 20080424 G 7930 OIL SYSTEM CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE ENGINE LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) DURING TAXI, THE CHIP DETECTOR LIGHT CAME ON ACCOMPANIED BY A RAPID LOSS OF OIL PRESSURE AND RAPID RAISE IN OIL TE MPERATURE. THE PILOT IMMEDIATELY SHUTDOWN THE ENGINE. ON-GROUND INSP, REVEALED METAL IN OIL FILTER AND ON THE CHIP DETEC TOR. THE ENGINE WAS REMOVED AND SHIPPED FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 H 7 1 3T 3 T A37CE E4EA 20081112 SW 2008 11 12 CA080731001 1 20080727 G 3222 55010011 DRAG BRACE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCB3T HCB3TN5 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A DAILY INSP BY MAINT PERSONNEL, THE NR 3 LUG SECURING THE UPLOCK HOOK TORQUE SHAFT TO THE DRAG BRACE WAS F OUND CRACKED IN HALF AND SEPARATED FROM THE DRAG BRACE. REPLACED WITH A SERVICEABLE DRAG BRACE, RIGGED AND ADJUSTED WIT H NO FURTHER ISSUES. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 20081112 SW 2008 11 12 CA080731002 1 20080729 G 6320 212040143001 BEARING BELL BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE TRANSMISSION ROUGH W K NONE O OTHER IN INSP/MAINT 1 CA 875 (CAN) UPON A SCHEDULED INSPECTION OF THE TRANSMISSION WAFFER FILTER AN EXCESSIVE AMOUNT OF FERROUS METAL WAS FOUND. THER E HAD BEEN NO METAL FOUND ON THE CHIP DETECTOR OR IN THE COURSE INLET SCREEN. A SWEEP OF THE SUMP WITH A MAGNET FOUND NO METAL. AFTER DISSASEMBLY AND INSPECTION OF THE TRANSMISSION, GEARS, AND BEARINGS, THE BEARING SET P/N 212-040-143-001 I N THE HYDRAULIC PUMP AND TACHOMETER DRIVE ASSEMBLY OFFSET QUILL WAS FOUND TO BE ROUGH. 1 G 7 1 4U 4 U H1SW E17EA 20081112 EU 2008 11 12 CA080801001 1 20080726 G 2910 FLEX LINE BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU HYD SYSTEM CHAFED W O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH, THE CREW OBSERVED A LOSS OF HYDRAULIC PRESS AFTER GEAR WAS SELECTED DOWN. THE ACFT LANDED WITHOUT FUR THER INCIDENT. MAINT IDENTIFIED THE HYDRAULIC LINE FROM THE PUMP THE HIGH PRESSURE FILTER AS THE SOURCE OF THE LEAK. TH E LINE WAS REPLACED AND THE ACFT RETURNED TO SERVICE. 2 L 7 2 3T 4 T A24EU A196 6 C P899 20081112 EU 2008 11 12 CA080801002 1 20080728 G 2460 SM400D30 CONTACT AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF5 NE DC BUSS FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DEPARTING, CREW OBSERVED A NR 1 DC BUSS FAIL INDICATION WITH NO GENERATOR FAULT INDICATION. THE CREW OBSERVED THAT THE NR 1 DC BUS WAS RECOVERED WHEN THE NR 1 GENERATOR WAS SELECTED OFF. THE ACFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. MAINT REPLACED THE NR 1 GENERATOR CONTACTOR (12PU) AND THE ACFT WAS RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 20081112 NE 2008 11 12 CA080801003 2 20080728 G 7200 ENGINE BOEING 727 727233 138408A NM PWA JT8 JT8D15 52051 NE POWER LOSS W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) WHILE AIRCRAFT WAS IN CRUISE ENROUTE, THE ACFT EXPERIENCED AN UNCOMMANDED POWER LOSS, DECELERATING TO FLIGHT IDLE. THE CREW SELECTED NR 2 THRUST TO IDLE AND THE ACFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. T HE ACFT FERRIED FOR ENGINE REPLACEMENT. 2 L 7 3 4F 4 F RT A3WE E2EA 20081112 EU 2008 11 12 CA080801004 1 20080723 G 5754 A5724853200000 ACCESS PANEL AIRBUS 310 A310300 3930305 EU GE CF6 CF680C2* GL SLAT TRACK MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON ARRIVAL, LEADING EDGE SLAT TRACK ACCESS PANEL 512HB FOUND MISSING. ADJACENT PANEL 512JB ALSO FOUND DAMAGED. LOS T IN FLIGHT. PANEL 512HB REPLACED AND PANEL 512JB REPAIRED IAW SRM. 2 L 7 2 4F 4 F RT A35EU E23EA 20081112 CE 2008 11 12 CA080801005 1 20080729 G 2750 C1452501 MOTOR CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL TE FLAPS UNSERVICEABLE W O OTHER F FLT CONT AFFECTED CL CLIMB 1 CA 238 238 (CAN) AFTER TAKEOFF THE CREW SELECTED FLAP UP AND THE CIRCUIT BREAKER POPPED. AIRCRAFT FLEW TO MAINT BASE WERE THE CREW SELECTED PROPER FLAP WITH THE STANBY FLAP SYS AND LANDED WITHOUT INCIDENT. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20081112 NE 2008 11 12 CA080801007 2 20080801 G 7414 BEARING ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO WORN W K NONE O OTHER IN INSP/MAINT 1 CA 487 (CAN) MAG WAS RECEIVED FOR 500 HOUR INSP BEFORE DISASSEMBLY THE ROTOR BEARING END PLAY WAS MEASURED AT 0.003 INCH. THE A LLOWABLE END PLAY IS 0.0005 TO 0.0015 INCH. WHEN DISASSEMBLED THE COIL WAS FOUND TO BE SLIGHTLY LOOSE IN THE MAG HOUSING . THE BEARINGS WERE RESHIMMED AND INSPECTED, THE COIL CLAMPS WERE REPLACED AND THE COIL WAS NO LONGER LOOSE IN THE HOUSI NG. THE REST OF THE 500 HOUR INSP WAS CARRIED OUT AND THE MAG WAS RETURNED TO SERVICE. 1 G 7 1 3O 3 O H11NM 1E4 20081112 NE 2008 11 12 CA080801008 2 20080801 G 7414 COIL ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 487 (CAN) MAG WAS RECEIVED FOR 500 HOUR INSP. WHEN DISASSEMBLED THE COIL WAS FOUND SLIGHTLY LOOSE IN THE MAG HOUSING. THE CO IL CLAMPS WERE REPLACED AND THE COIL WAS NO LONGER LOOSE IN THE HOUSING. THE REST OF THE 500 HOUR INSP WAS CARRIED OUT A ND THE MAG WAS RETURNED TO SERVICE. 1 G 7 1 3O 3 O H11NM 1E4 20081112 EU 2008 11 12 CA080804001 1 20080731 G 3340 RG1007AA03 FLASHER AIRBUS 310 A310304 3930339 EU GE CF6 CF680C2A5 NE EXTERIOR LIGHT BURNED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPPER SLOWER BEACON AND STROBE LIGHTS INOP. FOUND FLASHER UNIT U/S (RECEPTACLE CONNECTOR BURNED & PARTIALLY MELTED INSIDE). CONNECTING ELECTRICAL PLUG INSULATION SLIGHTLY BURNED AND PINS DAMAGED. CONNECTOR P/N E0052R14B15SNE AND TIMER UNIT REPLACED. PARTS ROUTED TO ENGINEERING FOR INVESTIGATION. 2 L 7 2 4F 4 F RT A35EU E13NE 20081112 EU 2008 11 12 CA080804002 1 20080801 G 2131 CONTROLLER AIRBUS 330 A330342 EU RROYCE RB211 RB211TRENT77 NE CABIN PRESSURE MALFUNCTIONED W O OTHER O OTHER CR CRUISE 1 CA (CAN) CREW DID AN EMERGENCY DESCENT DUE ECAM WARNING EXCESSIVE CABIN ALTITUDE WITH CPC NR 1 FAULT. THE EMERGENCY DESCENT STARTED FROM FL320 TO FL090. THE CABIN ALTITUDE REACHED 12000 FT. DURING THE DESCENT THEY GOT MESSAGE "CABIN PR SAFETY VALVE OPEN". DURING TROUBLESHOOTING NR 1 CPC INTERROGATION WAS SHOWING NR 1 DELTAP SYS. SYS RESET AND ALL INDICATION T ESTED SERVICEABLE. AFTER RETURN FLIGHT TO BASE, BOTH SAFETY VALVES WERE REPLACED AS PRECAUTIONARY. 1 L 7 2 4F 4 F RT A46NM E39NE 20081112 CE 2008 11 12 CA080804003 1 20080718 G 7931 OIL SYSTEM CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ENGINE LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE FLIGHT, THE MASTER CAUTION WARNING SYS CAME ON IN CONJUNCTION WITH THE LOW OIL PRESSURE ANNUNCIATOR. THE CREW ELECTED TO SHUT THE ENGINE DOWN WHEN THE OIL PRESSURE WAS AT OR BELOW 30 PSI. AN UNEVENTFUL SINGLE ENGINE LAND ING FOLLOWED. TROUBLESHOOTING COULD NOT IDENTIFY THE PROBLEM AND THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGAT ION AND REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 L 7 2 4F 4 F A22CE E1NE 20081113 GL 2008 11 13 CA080805001 1 20080707 G 3246 FLOAT AMTR TUNDRA TUNDRA 05607NZ GL LEFT NOSE BROKEN W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) ON RETRACTING LANDING GEAR AFTER TAKEOFF IT WAS NOTICED THAT THE LT NOSE GEAR ONLY PARTIALLY RETRACTED. GEAR WAS C YCLED 3 TIMES BUT LT NOSE GEAR STAYED IN A SEMI RETRACTED STATE. DECISION WAS MADE TO LAND ON RUNWAY WITH GEAR RETRACTED - NO DAMAGE, NO INJURY. INVESTIGATION BY OWNER REVEALED THE ROD WHICH ACTIVATES NOSE GEAR ONLEFT FLOAT BROKE. MONTANA F LOAT COMPANY, THE MANUFACTURER WILL SUPPLY 2 NEW RODS 7/16" THICK - OLD RODS 3/8" THICK. 1 H 7 1 3O NT EXPA1H71 20081113 EA 2008 11 13 CA080805002 2 20080728 G 7313 311991901 SLEEVE BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA FUEL NOZZLE WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) WHILE CARRYING OUT A SCHEDULED HOT SECTION INSPECTION ON THE ABOVE ENGINE, IT WAS DISCOVERED THAT 2 NOZZLE SHEATHS WERE OF AN INCORRECT PART NR FOR THE MODEL OF ENGINE INSTALLED. THE PART NRS ARE BOTH FOR A PT6A-50 ENGINE. EVEN THOUGH WE OPERATE THIS MODEL OF ENGINE, OUR INVENTORY RECORDS DO NOT SHOW THIS PART EVER BEING ISSUED TO THIS ACFT. THERE IS A POSSIBILITY THAT THESE 2 SHEATHS HAD BEEN INSTALLED AT ENGINE OVERHAUL, T.S.O. 3522 HRS. 2 REPLACEMENT SHEATHS OF THE C ORRECT PART NR WERE INSTALLED AND THE ENGINE RETURNED TO SERVICE. 1 L 7 2 3T 4 T RT 3A20 E4EA 20081112 SW 2008 11 12 CA080805003 1 20080803 G 5302 SKIN BELL 407 407 1182206 SW ALLSN 250C 250C47B GL TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2798 (CAN) CRACK FOUND BETWEEN THE TAIL ROTOR SUPPORT AND TAILBOOM AT FUSELAGE STA 375 APPROX. ALSO SEVERAL RIVETS WERE FOUND SMOKING. THE HELICOPTER WAS USED TO MOVE DRILL ON A REGULAR BASIS WITHOUT EXCEEDING THE LOAD CAPACITY. TAILBOOM REMOVED P/N407-530-014-101 S/N 53037 AND SERVICEABLE TAILBOOM INSTALLED P/N 407-030-801-205D PROCURED FROM MFG. 1 G 7 1 3U 3 U O H2SW E1GL 20081119 NM 2008 11 19 CA080805005 1 20080731 G 3231 483025 SEQUENCE VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU MLG DOOR INOPERATIVE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING DEPARTURE, THE LANDING GEAR WAS SELECTED UP, THE RT MLG DOOR WAS SLOW TO CLOSE (APPROX 10 MINUTES). THE F/A VERIFIED THE DOOR WAS OPEN. THE DOOR THEN CLOSED WITHOUT ACTION FROM THE PILOT. PSEU FAULT CODE RGDCL UNREASONABLE FAR. RT MLG SOLENOID SEQUENCE VALVE REPLACED. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081119 NM 2008 11 19 CA080805006 1 20080801 G 2913 6617303 PUMP BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA HYD SYSTEM DAMAGED W A UNSCHED LANDING J WARNING INDICATION AP APPROACH 1 CA (CAN) DURING APPROACH, NR 2 HYD PUMP CAUTION LIGHT ILLUMINATED. PTU WAS SELECTED ON SO ALL SYSTEMS OPERATED NORMAL FOR R OUTINE LANDING. EDP CASE HALVES LOOSE AND PUMP NOT MAKING PRESSURE. PUMP REPLACED. 2 H 7 2 4T 4 T RT A13NM E00062EN 20081119 EA 2008 11 19 CA080805007 2 20080801 G 8530 65678 BOLT CURTIS GRUMAN TS2 TS2ACALFORST 3951102 WP WRIGHT R1820 982C9HE2 67020 EA EXAUST ROCKER SHEARED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA (CAN) IN CRUISE FLIGHT, THE NR 1 ENGINE LOST POWER AND BEGAN TO BACKFIRE. ENGINE SHUT DOWN AND FEATHERED. UPON INSPECTIO N OF ENGINE NR 9 CYLINDER EXHAUST ROCKER BOLT FOUND SHEARED AT NUT AND BOLT HAD DISENGAGED FROM CYLINDER EAR ASSEMBLY. N EW BOLT AND NUT ASSEMBLY INSTALLED, VALVE CLEARENCES ADJUSTED, MAIN OIL SCREEN AND NO CONTAMINATION FOUND. ENGINE GROUND RUN SERVICEABLE AND RETURNED TO SERVICE. 2 H 7 2 4R 4 R A25WE E259 20081119 NE 2008 11 19 CA080805008 2 20080805 G 7414 106006169 MAGNETO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA 608 (CAN) MAG WAS RECEIVED FOR 500 HOUR INSP. BEFORE DISASSEMBLY 0.003 INCH END PLAY WAS NOTICED ON THE ROTOR BEARINGS (0.00 15 INCH IS MAX. ALLOWABLE). WHEN DISASSEMBLED THE WASHER THAT RETAINS THE DISTRIBUTOR GEAR ON THE SHAFT WAS SLIGHTLY LOO SE. MFG HAS BEEN CONTACTED IN THE PAST ABOUT THIS ISSUE AND HAS INSTRUCTED US TO USE A PRESS ON THE END OF THE SHAFT TO REFLARE IT TO RETAIN THE WASHER. THE COIL WAS ALSO FOUND MOVING SLIGHTLY AGAINST THE HOUSING POLES AND WHEN THE COIL CLA MP SCREWS WERE REMOVED TO INSPECT THIS THE SCREWS WERE FOUND TO BE NOT VERY TIGHT. THE ROTOR BEARINGS WERE RESHIMMED, TH E DIST. GEAR SHAFT WAS REFLARED, AND THE COIL CLAMP SCREWS WERE TIGHTENED. THE REST OF THE 500 HOUR INSP. WAS CARRIED OU 1 G 7 1 3O 3 O H11NM 1E4 20081119 NE 2008 11 19 CA080805009 2 20080805 G 7414 10160858 HOUSING ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 608 (CAN) MAG WAS RECEIVED FOR 500 HOUR INSP. A CRACK WAS NOTICED IN ONE OF THE MOUNTING EARS OF THE MAG HSG. THIS IS A NEW STYLE OF HSG CASTING FROM MFG WITH THE LARGE RAISED LETTERS ON THE OUTSIDE OF THE HSG AND THE WORD "EMPIRE" INSIDE THE H SG NEXT TO THE BRG AREA. WE HAVE NOTICED A HIGHER NR OF THESE NEW STYLE HSGS CRACKING AT THIS LOCATION. OLDER CASTINGS W OULD OCCASIONALLY CRACK IF THE MOUNTING NUTS WERE OVERTORQUED, WHEREAS THESE NEW ONES SEEM TO BE WEAKER AND CRACK MORE O FTEN. THE MAG WAS REMOVED FROM SERVICE. 1 G 7 1 3O 3 O H11NM 1E4 20081119 NM 2008 11 19 CA080805010 1 20080802 G 3060 HEATER HAMSTD DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PROP BLADE BURNED W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA 10316 10316 (CAN) THE CREW OBSERVED SPARKS COMING FROM THE FRONT OF THE RT ENGINE. THE CREW SHUTDOWN THE ENGINE IN FLIGHT AND DECLAR ED AN EMERGENCY. THE ACFT LANDED SHORTLY AFTER WITHOUT INCIDENT. INVESTIGATION REVEALED THAT THE RT PROPELLER BLADE NR2 ELECTRICAL HEATER BURNED CAUSING THE HEATING ELEMENT TO PRODUCE ELECTRICAL SPARKS. THE BLADE ASSY WAS REPLACED, THE BLAD E ANTI-ICING SYS TESTED AND THE ACFT RETURNED INTO SERVICE. THE BLADE WAS SENT TO AN EXTERNAL SHOP FOR REPAIR. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081119 GL 2008 11 19 CA080805011 2 20080801 G 7230 3896888M SCROLL BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL COMPRESSOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 21976 (CAN) WHILE CARRYING OUT A DAILY CHECK, A CRACK WAS FOUND ON THE COMPRESSOR SCROLL ON TOP, PARALLEL TO SHROUD HSG AND NE AR THE RT ELBOW. ACFT WAS GROUNDED. COMPRESSOR ASSY IS AN ON-CONDITION ITEM BUT THERE IS AN INSP EVERY 2000 HOURS. AS YO U CAN SEE THIS SCROLL WAS VERY HIGH TIME. SINCE LAST 2000 HOUR INSP 374.8 HOURS. TO THE 2000 HR INSP INVOLVES INSPECTIN G THE SPUR ADAPTER GEAR AND ITS MATING GEAR. BELIEVE THAT THE SCROLL IS THE SAME TIME AS THE COMPRESSOR ASSY. 1 G 7 1 3U 3 U H2SW E1GL 20081117 CE 2008 11 17 CA080805012 1 20080730 G 3234 1013841377 SELECTOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE LANDING GEAR DEFECTIVE W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) UPON APPROACH THE CREW WAS UNABLE TO EXTEND THE GEAR NORMALLY AND HAD TO PERFORM AN EMERGENCY EXTENSION. A SUCCESS FUL LANDING WAS CARRIED. UPON INVESTIGATION, IT WAS DETERMINED THE PROBLEM WAS IN THE LANDING GEAR SELECTOR ASSY. THE PI VOT SCREW FOR THE MICROSWITCH ACTUATING LEVER HAD BACKED OUT SEVERAL THREADS. THIS ALLOWED THE LEVER TO MIGRATE OUT WITH THE SCREW. WHEN THE GEAR WAS SELECTED UP THE ACTUATING LEVER CAME TO REST ON PART OF THE GEAR SELECTOR HSG. AS SUCH, WH EN THE CREW SELECTED GEAR DOWN THE SWITCHES WERE NOT RELEASED AND THE GEAR REMAINED IN THE RETRACTED POSITION. THREAD LO CKING COMPOUND WAS APPLIED TO THE PIVOT SCREW AND THE SCREW WAS TIGHTENED. SEVERAL GEAR SWINGS WERE SUCCESSFULLY COMPLET 1 L 7 2 4T 4 T A24CE E4EA 20081117 2008 11 17 CA080805013 4 20080805 G 6113 35323012 BULKHEAD PIPER PA28 PA28151 7102805 SO LYC O320 O320E3D 41508 EA SNSNCH 74D 74DM EA SPINNER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ANNUAL INSP FWD SPINNER BULKHEAD WAS FOUND TO BE CRACKED AT SCREW ATTACHMENT HOLE. NEW PART WAS ORDERED FR OM MFG IAW APPLICABLE PARTS CATALOGUE. NEW PART RECEIVED WAS STAMPED WITH CORRECT PN AS ORDERED, BUT WAS PHYSICALLY DIF FERENT IN DEPTH AND WOULD NOT FIT. MFG WAS CONTACTED (VIA AVIATION UNLIMITED AND A SECOND SPINNER BACK PLATE IS BEING SHIPPED). 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 20081117 SO 2008 11 17 CA080805014 2 20080709 G 8530 CAMSHAFT CESSNA 185 A185F 2072821 CE CONT O550 IO550D 17042 SO MCAULY D3A34 D3A34C401 GL ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSP , NR2 CYL WAS REMOVED DUE TO LOW COMPRESSION. DISCOVERED LIFTERS ON NR1 CYL HAD PITTING AND SPALLING. FURTHER INVESTIGATION REVEALED THE CAMSHAFT WAS CORRODED AND WORN ALSO. ENGINE REMOVED FOR REPAIR. ENGINE HAS 670 HOUR T SOH. UPON TEARDOWN, CRANKSHAFT HAD CORROSION, AND THE OIL PUMP WAS DAMAGED DUE TO METAL CONTAMINATION IN ENGINE, AND MOR E LIFTERS HAD DAMAGE. THE ACFT HAS ALWAYS BEEN HANGERED, OUT OF THE COLD. WHEN IT WAS OUT IN THE COLD, A PREHEAT SYS WAS UTILIZED. ACFT FLEW ON THE AVERAGE 3 TO 4 HOURS PER WEEK WITH APPROX 2 HOUR DURATION PER FLIGHT. CANNOT DETERMINE WHAT THE CAUSE OF THE CORROSION IS WHICH CAUSED THE METAL CONTAMINATION. 1 H 7 1 3O 3 O 3A24 E3SO 5 C P47GL 20081117 NE 2008 11 17 CA080806001 2 20080723 G 7321 FUEL CONTROL BEECH 200 200CBEECH 1152926 CE PWA PT6 PT642A NE ENGINE MALFUNCTIONED W O OTHER F FLT CONT AFFECTED LD LANDING 1 CA (CAN) DURING LANDING, THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION WHICH CAUSED THE PILOT TO HAVE DIFFICULTY CONTR OLLING THE ACFT, CAUSING IT TO SKID IN THE GRASS AND MUD AT THE SIDE OF THE RUNWAY. THE FUEL CONTROL WAS REPLACED AND TH E RIGGING WAS ADJUSTED. THE FUEL CONTROL WILL BE INVESTIGATED AND UPDATES PROVIDED. 1 L 7 2 4T 4 T A24CE E4EA 20081117 2008 11 17 CA080806002 4 20080729 G 3160 8221577012 DISPLAY BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP COCKPIT MALFUNCTIONED W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) PILOT REPORTED, DURING PREFLIGHT. THEY STARTED THE APU. AFTERWARDS, PILOT SELECTED THE AIR SOURCE TO (NORMAL) THEN SMOKE BEGAN EMITTING FROM THE RT SIDE OF THE COCKPIT BETWEEN THE GLARESHIELD AND WINDOW. PILOT SELECTED THE AIR SOURCE TO (OFF) THEN SHUTDOWN THE APU. FOUND COPILOT`S MFD AS THE SOURCE OF THE SMOKE. REMOVED AND REPLACED COPILOT`S MFD. OPS GOOD. EXTENSIVE GROUND TESTING INCLUDING OPS OR AIR COND SYS WAS CARRIED OUT AND ALL WAS FOUND TO BE NORMAL. 2 L 7 2 4F 4 F RT T00005NY E00010LA 20081117 EA 2008 11 17 CA080806003 2 20080726 G 7260 GEARBOX BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA ENGINE DISCONNECTED W O OTHER X ENGINE FLAMEOUT AP APPROACH 1 CA (CAN) DURING FINAL APPROACH, THE ENGINE FLAMED OUT. RELIGHT ATTEMPT WAS UNSUCCESSFUL. AN UNEVENTFUL SINGLE ENGINE LANDIN G FOLLOWED. POST EVENT TROUBLESHOOTING, FOUND THAT THE ENGINE COULD NOT BE RE-STARTED. ACCESSORIES GEARBOX DE-COUPLE IS CONFIRMED. THE AFFECTED COMPONENTS WILL BE REMOVED AND FWDED FOR INVESTIGATION. 2 L 7 2 4T 4 T RT A24CE E4EA 20081117 NE 2008 11 17 CA080806004 2 20080729 G 7200 ENGINE PILATS PC12 PC12 7090550 EU PWA PT6 PT6A67B 52043 NE MALFUNCTIONED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION TO TAKEOFF 1 CA (CAN) DURING T/O, THE ENGINE STARTED TO SURGE FOLLOWED BY A RISE IN INDICATED TEMPERATURE. THE PILOT ELECTED TO RETURN T O HIS POINT OF DEPARTURE, WHERE A SAFE LANDING WAS PERFORMED. THE ENGINE TEMP REACHED 970°C FOR ONE MINUTE. THE ENGINE W ILL BE REMOVED AND FWDED FOR INVESTIGATION AND REPAIR. 1 L 7 1 3T 4 T RT A78EU E26NE 20081117 CE 2008 11 17 CA080806005 1 20080801 G 8120 TURBOCHARGER BEECH 60 B60 1153605 CE LYC O541 TIO541E1C4 41536 EA HARTZL HCF3Y HCF3YR2 GL LT ENGINE MALFUNCTIONED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) PILOT REPORTED LOW MANIFOLD PRESSURE ON LT ENG IN CLIMB OUT, ACFT RETURNED TO THE AIRPORT. MAINT BACK FLUSHED THE LT TURBO WASTEGATE AND CONTROLLER, GROUND RUN OK. NO OTHER DEFECTS NOTED, ACFT RETURNED TO SERVICE. 1 L 7 2 3O 3 O A12CE E10EA 5 C P31EA 20081117 EA 2008 11 17 CA080806006 1 20080804 G 7110 COWLING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE NR 2 ENGINE DEPARTED W K NONE P NO WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) AS INDICATED BY MAINT CONTROL, ACFT DEPARTED. MISSING COWLING FROM NR2 ENGINE WAS DISCOVERED DURING WALKAROUND INS P BY GROUND MAINT. IT WAS ALSO APPARENT THAT PORTIONS OF THE COWLING THAT DEPARTED ENGINE, STRUCK THE LEADING EDGES OF T HE LT AND RT HORIZONTAL STAB. CREW DID NOT HAVE ANY ABNORMAL INDICATIONS DURING FLIGHT, IAW MAINT CONTROL COMMENT TO FS R. PLEASE REFER TO ADR RRAD-C08-21754681. 2 L 7 2 4F 4 F RT A21EA E15NE 20081117 NE 2008 11 17 CA080806007 2 20080805 G 7260 GEARBOX CNDAIR CL601 CL6012A12 1900303 EA GE CF34 CF348E5A1 30062 NE NR 1 ENGINE DEFECTIVE W E A ENGINE SHUTDOWN UNSCHED LANDING K FLUID LOSS CR CRUISE 1 CA (CAN) DURING FLIGHT, CREW NOTICED THEY LOST THE NR1 ENGINE OIL INDICATION AND GOT THE RED LED. SHUTDOWN ENGINE AND MADE AN UNEVENTFUL LANDING. CREW NOTICED A PUDDLE OF OIL UNDER THE NR1 ENGINE AFTER LANDING. DURING THE TROUBLESHOOTING, TH EY REMOVED THE DRAIN MAST AND INSTALL PLASTIC BAG TO THE DIFFERENT DRAIN LINES. AFTER STARTING THE ENGINE, THE PLASTIC B AG FOR THE ACCESSORY GEAR BOX DRAIN WAS FULL OF OIL. SHUTDOWN THE ENGINE, THEY ARE NOW WAITING FOR THE MRP TO CHANGE TH E AGB. 2 L 7 2 4F 4 F RT A21AE E00063EN 20081117 NM 2008 11 17 CA080806008 1 20080730 G 2133 88060B010003 OUTFLOW VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU CABIN PRESSURE FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) ACFT RETURNED DUE TO DEPRESSURIZATION AND BURNING ODOR IN THE COCKPIT. ATC CALLED LOCAL STANDBY, NO PAN/MAYDAY DEC LARED. ACFT LANDED SAFELY AND WITHOUT INCIDENT. MAINT INTEROGATEED THE CDS, THE FOLLOWING CODES IDENTIFIED: AFT OUTFLO W VALVE FAIL CPC/OFF VALVE DATA FAIL. AFT OUTFLOW VALVE REPLACED. FUNCTION CHECKS OF ECS SYSTEM CARRIED OUT COULD NOT I DENTIFY ANY ODORS. AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081117 EA 2008 11 17 CA080806009 1 20080718 G 2730 C6CTM102827 DRIVE ASSY DHAV C6CT10103 DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA ELEVATOR STRIPPED W A UNSCHED LANDING Z E SIGNIFICANT FAILURE REPORT VIBRATION/BUFFET CL CLIMB 1 CA (CAN) DURING CLIMB OUT AT 800 FEET ALTITUDE THE ACFT SUDDENLY STARTED TO SHAKE VIOLENTLY. THE PILOT ABORTED THE CLIMB, P ROCEEDED STRAIGHT AHEAD FOR 4 MILES TO A LANDING STRIP AND LANDED SAFELY WITH NO INJURIES TO PERSONS ON BOARD. UPON INVE STIGATION AS TO THE CAUSE OF THE SHAKING IT WAS DISCOVERED THAT THE CLEVIS END P/N C4CM1956-11 HAD PULLED COMPLETELY OUT OF THE SCREW DRIVE P/N C6CTM1028-27 IN THE ELEVATOR SCREW JACK ASSY P/N C6CT1010-3. THIS ALLOWED THE TRIM TAP TO FLUTTE R WHICH IN TURN CAUSED THE ELEVATOR TO FLUTTER INDUCING A VIOLENT SHAKING OF THE ACFT. 1 H 7 2 3T 4 T RT A9EA E4EA 20081117 EA 2008 11 17 CA080806010 1 20080705 G 7603 74491147 CABLE ASSY CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE THROTLE BROKEN W E A ENGINE SHUTDOWN UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA 18500 (CAN) WHILE ATTEMPTING TO REDUCE RT ENGINE PWR AFTER TAKEOFF AND CLIMB, FLT CREW REPORTED THAT THE RT ENG WOULD NOT RESP OND TO THROTTLE LEVER INPUTS. THE RT ENGT WAS SHUTDOWN VIA FIRE PUSH SWITCH/LIGHT, ACFT DIVERTED TO IAD AND LANDED WITHO UT FURTHER INCIDENT. PRIOR TO TAKEOFF (ON TAXI OUT), THE FLT CREW NOTICED THAT THE RT THROTTLE LEVER WAS VERY STIFF TH AT THEY ATTRIBUTED TO FRICTION LOCKS. UPON ADDING POWER FOR TAKEOFF, THEY NOTICED THAT THE THROTTLE LEVERS WERE VERY STI FF AT FIRST, THEN THERE WAS A DEFINITE "POP" AND THEN THE LEVERS ADVANCED EASILY TO THE FLEX THRUST SETTING (87 PERCENT) . THE REMAINDER OF THE TAKEOFF WAS NORMAL. WHEN ADVANCING PWR LEVERS TO CLIMB THRUST (92 PERCENT N1), BOTH ENGINES RESPO 2 L 7 2 4F 4 F RT A21EA E15NE 20081117 CE 2008 11 17 CA080806011 1 20080716 G 2550 D2010103 ARM DART D500560041 DART G G 2700102 CE CARGO BAY CRACKED W O OTHER O OTHER UK UNKNOWN 1 CA (CAN) MFG HAS RECEIVED A REPORT THAT UNDER CERTAIN CIRCUMSTANCES ON THE D500-560-041 CARGO MIRROR INSTALLATION AT CHG001 THE D2010-103 ARM MAY CRACK DURING FLIGHT CAUSING THE D2011-101 MIRROR TO SEPARATE FROM THE ASSY. SB08-3 IS BEING ISSUE D TO ALL CUSTOMERS WHO HAVE PURCHASED ASSEMBLIES. 1 L 7 1 3R TC674 20081117 EA 2008 11 17 CA080806012 2 20080801 G 8530 SL360000WA20P CYLINDER HEAD BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL ENGINE CRACKED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA 1854 (CAN) DURING CLIMB OUT WITH GLIDER IN TOW, THE PILOT REPORTED AN ENGINE VIBRATION. THEY IMMEDIATELY INSTRUCTED THE GLIDE R TO RELEASE AND THEN PREFORMED A DOWN WIND LANDING AND RETURN TO HANGER. UPON SHUTDOWN AND INSP IT WAS FOUND THAT CYL N R1 HEAD HAD CRACKED AND SEPARATED FROM THE REMAINDER OF THE CYL. 1 H 7 1 3O 3 O A21CE E286 5 N P874 20081117 SW 2008 11 17 CA080806013 1 20080728 G 3244 280250 TIRE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL TAIL WHEEL DAMAGED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 125 (CAN) TAIL WHEEL FOUND FLAT DURING TAXI, UPON DISASSEMBLY IT WAS FOUND THAT THE INNER CORDS WERE FOUND LET GO AND CUT TH E TUBE. TIRE, BATCH NR WAS EITHER 0321672 OR 0422043. 1 H 7 1 3O 3 O A21CE E286 5 N P874 20081117 SW 2008 11 17 CA080806014 1 20080727 G 3244 280250 TIRE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL TAIL WHEEL DAMAGED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 124 (CAN) TAIL WHEEL FOUND FLAT DURING TAXI, UPON DISASSEMBLY IT WAS FOUND THAT THE INNER CORDS WERE FOUND LET GO AND CUT TH E TUBE. TIRE, BATCH NR WAS EITHER 0321672 OR 0422043. 1 H 7 1 3O 3 O A21CE E286 5 N P874 20081117 SW 2008 11 17 CA080806015 1 20080728 G 3244 280250 TIRE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2A 41514 EA MCAULY 1A200 1A200* GL TAIL WHEEL DAMAGED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 160 (CAN) TAIL WHEEL TIRE FOUND FLAT DURING TAXI, UPON DISASSEMBLY IT WAS FOUND THAT THE INNER CORDS WERE FOUND LET GO AND C UT THE TUBE. 1 H 7 1 3O 3 O A21CE E286 5 N P874 20081117 SW 2008 11 17 CA080806016 1 20080625 G 5711 31692 SPAR BBAVIA 8 8GCBC 1220803 SW WING CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA 976 (CAN) PART FOUND CORRODED AT SPAR ATTACHMENT BOLT HOLE. 1 H 7 1 3O A21CE 20081117 SW 2008 11 17 CA080806017 1 20080625 G 5711 31692 SPAR BBAVIA 8 8GCBC 1220803 SW WING CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA 976 (CAN) PART FOUND CORODED AT SPAR ATTACHMENT BOLT HOLE. 1 H 7 1 3O A21CE 20081117 NM 2008 11 17 CA080807001 1 20080729 G 2520 5045802158003 SEAT BELT EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE CABIN FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 3059 (CAN) F/A SEAT LAP BELTS AT DOOR LT NR1 AND DOOR RT NR2 FRAYED SEVERAL PLACES. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081117 NM 2008 11 17 CA080807002 1 20080806 G 2520 5045802158003 SEAT BELT 5045804078 EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE CABIN FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 5704 (CAN) F/A SEAT LAP BELT AT DOOR LT NR1, NR2 AND DOOR RT NT2 FRAYED SEVERAL PLACES. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081119 NE 2008 11 19 CA080807003 3 20080718 G 6110 7149A0 THRUST WASHER HAMSTD HAMSTD 23E 23E50 NE BLADE SHANK CRACKED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 CA 471 (CAN) THE CRACKED BLADE RING IS PART OF THE BLADE ASSEMBLY. A CRACKED RING TYPICALLY RESTRICTS BLADE ROTATION AND CAN SE T UP A VIBRATION. PROPELLER WAS REMOVED AND AFTER TEAR DOWN AND INSPECTION A CRACKED BLADE RING (THRUST WASHER) WAS DETE RMINED AND OTHER DAMAGE TO THE BARREL ASSEMBLY. REPLACED BLADE THAT HAD THE BROKEN BLADE RING AND OTHER DAMAGED PARTS. P ROPELLER ASSEMBLED BALANCED AND RETURNED TO SERVICE. 6 C P603 20081119 NM 2008 11 19 CA080807004 1 20080806 G 2761 HOUSING SMITHSIND DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ACTUATOR FRACTURED W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 44413 (CAN) WHEN THE FLIGHT/TAXI SWITCH WAS SELECTED TO FLIGHT IN PREPARATION FOR TAKE OFF, THE CREW RECEIVED SOME HYDRAULIC C AUTION LIGHTS ASSOCIATED WITH A LOW HYDRAULIC LEVEL INDICATION ON THE NR 1 SYSTEM . THE ACFT RETURNED TO THE GATE AND A MAJOR HYDRAULIC LEAK WAS OBSERVED AT THE RT WING. MX FOUND THE INBD FLIGHT SPOILER ACTUATOR CASING CRACKED. THE ACTUATOR WAS REPLACED, LEAK CHECKED, TESTED AND THE ACFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081117 EA 2008 11 17 CA080807005 1 20080807 G 5520 C6TEM101229 HINGE FITTING DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA ELEVATOR MISMANUFACTURED W O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) THE HINGE ARM ASSY WAS RECEIVED FROM THE OEM WITH THE BONDING STRAP AND TAB INSTALLED ON THE UPPER ARM OF THE ASSY WHICH IF INSTALLED WOULD RESTRICT TRAVEL OF THE ELEVATOR. THE BONDING STRAP IS A FIXED LENGTH AND RIVETED IN PLACE. ADD ITIONALLY TO MAKE THE TAB BOND PROPERLY TO THE ARM PAINT WAS REMOVED FROM THE ASSY AND NOT REFINISHED. THE AREA THIS PAR T IS INSTALLED IN IS EXPOSED TO THE ENGINE GAS PATH THEREBY MAKING IT A HIGH CORROSION AREA. ALSO UPON FURTHER EXAMINATI ON THE BONDING TAB WAS FOUND LOOSE DUE TO THE COUNTER SINK(S) SIZE. THIS PART HAS BEEN SENT BACK TO THE OEM FOR REPLACEM ENT. 1 H 7 2 3T 4 T RT A9EA E4EA 20081117 EU 2008 11 17 CA080807006 1 20080701 G 7160 1350P5103 SEAL SNIAS 350 AS350BA 8680817 EU LYC LTS101 LTS101750A1 41560 NE ENGINE DAMAGED W E ENGINE SHUTDOWN X ENGINE FLAMEOUT IN INSP/MAINT 1 CA (CAN) CONVERTED LAST FEB, AT THE SAME TIME INSTALLED AN FDC ENGINE AIR FILTER. JULY 1ST 2008 THE PILOT WAS STARTING THE ENGINE GOT TO AROUND 60 PERCENT TORQUE WHEN COMPRESSOR STALLS OCCURRED. HE SHUTDOWN. UPON INSP FOR COMPRESSOR STALLS IT WAS FOUND THE COMPRESSOR WAS FOD. FOUND THAT A PIECE OF THE SEAL P/N 1350P5-103 HAD COME OFF AND FOD THE ENGINE. 1 G 7 1 3U 3 U NC H9EU E5NE 20081117 2008 11 17 CA080807007 4 20080805 G 6113 C4383 SUPPORT CESSNA 180 180C 2072608 CE CONT O470 O470K 17026 SO MCAULY 2A34C 2A34C203 GL SPINNER BROKEN W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 CA 215 (CAN) PLASTIC SPINNER SUPPORT CRACKS AND BREAKS INSIDE SPINNER CAUSING VIBRATION, SEEMS PLASTIC IS SOFTER DURING THE HOT SUMMER MONTHS AND FLEXES MORE. 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 20081117 EU 2008 11 17 CA080808001 1 20080807 G 3233 A5341130500200 ATTACH FITTING AIRBUS 310 A310304 3930339 EU GE CF6 CF680C2* GL NLG ACTUATOR BROKEN W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) ON LDG GEAR UP SELECTION NOSE GEAR SHOWED UNSAFE DOOR NOT UP. ECAM/QRH CARRIED OUT. ACFT RETURNED TO THE STATION. FOUND NLG UP LOCK ACTUATOR ATTACHMENT FITTING ASSY P/N A5341130500200 WITH BROKEN LUGS. NEW ATTACHMENT FITTING INSTALL ED. 2 L 7 2 4F 4 F RT A35EU E23EA 20081117 CE 2008 11 17 CA080808002 1 20080731 G 8011 534685 BEARING CONT 643259A18 CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO HARTZL HCJ3Y PHCJ3YF1 GL STARTER WORN W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ACFT WAS IN CRUISE FLIGHT WHEN PILOT NOTICED OIL PRESSURE STARTED TO FLUCTUATE. A PRECAUTIONARY LANDING WAS MADE. IT WAS OBSERVED THAT THE OIL LEVEL WAS LOW AND AN EXCESSIVE AMOUNT OF OIL WAS IN THE ENGINE COMPARTMENT AND IN THE BELLY OF THE ACFT. UPON MAINT INSP, IT WAS FOUND THAT THE STARTER ADAPTER PULLEY BEARING WAS BADLY WORN, DAMAGING THE OIL SEA L ALLOWING FOR AN OIL LEAK. THE STARTER ADAPTER WAS REPLACED, OIL FILTER CHECKED FOR FOREIGN MATERIAL, OIL REPLENISHED, AND A LEAK CHECK WAS CARRIED OUT. THE AIRCRAFT WAS RETURNED TO SERVICE. 1 H 7 1 3O 3 O A4CE E5CE 5 C P36EA 20081119 2008 11 19 CA080808004 1 20080722 G 2910 25W711008171 LINE GARRTT TFE731 TFE73140 29001 NE HYD SYSTEM CRACKED W O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA 1219 (CAN) ON APPROACH INTO TORONTO PEARSON THE CREW NOTICED THAT THE AUX HYDRAULIC LOW PRESSURE ANNUNCIATOR AND FLUID LOW LE VEL LIGHT ILLUMINATED ON THE ACFT. AFTER STABILIZING THEIR APPROACH, ALL LIGHTS WENT OUT. AFTER LANDING THE LOW LEVEL LI GHT CAME ON ONCE AGAIN WITH NO FURTHER LOW AUX HYD PRESSURE NOTED. AN INVESTIGATION FOUND THE RESERVOIR TANK LOW AND THE LINE FROM THE AUX PUMP AREA TO THE HYDRAULIC FILTER HAD A VERY FINE CRACK THAT HAD ORIGINATED ALONG A TOOLING MARK, THA T WAS ONLY VISIBLE WHEN RUNNING AND UNDER A 10 POWER MAGNIFYING GLASS. THE LINE WAS REPLACED AND RESERVOIR SERVICED WITH NO FURTHER PROBLEMS. 4 F E1NM 20081117 WP 2008 11 17 CA080808005 2 20080805 G 7321 VALVE WOODWARD SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCB3T HCB3TN5 GL FUEL CONTROL INOPERATIVE W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 1162 (CAN) CREW REPORTED MINOR ISSUE WITH STIFF POWER LEVER ON ONE ENGINE. MAINT EXAMINED THE CONTROL LINKAGE AND FOUND THAT THE FUEL CONTROL`S MANUAL FUEL VALVE (MFV) WOULD NOT REACH FULL TRAVEL (APPROX 85 PERCENT OF TRAVEL) REMOVED THE UNIT F OR REPAIR. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 20081117 SO 2008 11 17 CA080811001 1 20080729 G 2434 2CM353C1H ALTERNATOR LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL HAMSTD 54H 54H60117 NE NR 2 FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION AP APPROACH 1 CA (CAN) ON DESCENT, CREW OBSERVED THE NR 2 GENERATOR FAIL WAS ILLUMINATED. THE NR2 ENGINE WAS SHUTDOWN AND THE ACFT RETURN ED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINT REPLACED THE NR2 GENERATOR AND THE ACFT WAS RETURNED TO SERVICE. 2 H 7 4 4T 4 T A1SO E282 6 C P906 20081117 NE 2008 11 17 CA080811002 2 20080806 G 8530 CYLINDER CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE NR 1 ENGINE DAMAGED W E ENGINE SHUTDOWN Z SIGNIFICANT FAILURE REPORT CR CRUISE 1 CA (CAN) NR 1 ENGINE BACKFIRED IN FLIGHT. ENGINE WAS SHUTDOWN AND PROP FEATHERED. NR 2 CYLINDER EXHAUST EAR WAS FOUND CRA CKED. CYLINDER WAS REPLACED AND ENGINE GROUND RUNS SERVICEABLE. 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 20081117 NM 2008 11 17 CA080811003 1 20080810 G 3242 214664 BRAKE ASSY 214664 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LANDING GEAR DAMAGED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 986 (CAN) WHILE THE ACFT WAS BEING TOWED OFF THE RAMP A STRANGE NOISE WAS HEARD IN THE RT WHEEL AREA. UPON INVESTIGATION IT WAS FOUND THAT 3 OF THE 6 TORQUE PLATE TO PISTON HSG RETAINING BOLTS ON THE RT INBD BRAKE UNIT HAD SHEARED. NO OTHER DA MAGE WAS NOTICED. THE BRAKE UNIT WAS REPLACED WITH A SERVICEABLE UNIT AND THE ACFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081117 SW 2008 11 17 CA080811004 1 20080808 G 2910 205076302001 TUNING UNIT BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE HYDRAULIC SYS CRACKED W H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING K F FLUID LOSS FLT CONT AFFECTED CR CRUISE 1 CA 13967 (CAN) TUBE ASSY WAS REPLACED EARLIER IN APRIL 2008 DURING WINTER MAINT. SINCE SINGLE HYDR SYS PARTS ARE HARD TO FIND ITE MS, SERVICEABLE PART WAS INSTALLED WITH APPROPRIATE CERTIFICATION. VISUAL INSP DIDN`T REVEALED ANY DAMAGE AND NO LEAK WA S NOTICED AT THIS TIME. PART HAD 79 HRS SINCE INSTALLATION WHEN FAILED. 1 G 7 1 4U 4 U H1SW E17EA 20081119 SW 2008 11 19 CA080811006 1 20080807 G 7603 2761000009 ROD END SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP RT POWER LEVER WORN W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) THE FUEL CONTROL WAS BEING REPLACED ON THE RT ENGINE. WHEN THE STARTER GENERATOR WAS REMOVED IT WAS APPARENT THAT THE POWER LEVER, WHERE IT ATTACHES TO THE PROP PITCH CONTROL BY A ROD END, WAS SEVERELY WORN. THE TIME SINCE INSTALL IS NOT KNOWN, HOWEVER THE ROD END DID NOT LOOK PARTICULARLY OLD. THE CAD PLATING WAS STILL ON THE PART. IT HAD BEEN APPROX 80-90 HOURS SINCE THE LAST SCHEDULED INSPECTION. THIS IS THE THIRD INSTANCE IN RECENT MONTHS WITH THE SAME PART NR ROD E ND. (SOME WORSE THAN OTHERS) THE PART APPEARS TO BE FINE AT INSPECTION THEN FAILS SUDDENLY. AT A CERTAIN POINT IN THE LA ST FEW YEARS THE PART CHANGED, THE NR IS THE SAME BUT THE PART WAS PHYSICALLY DIFFERENT. THE NEWER ONES ARE THE PROBLEM 2 L 7 2 4T 4 T RT A8SW E4WE 20081118 EA 2008 11 18 CA080811007 2 20080807 G 7322 383493 PLUG 25245009 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL FUEL SERVO LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE ACCOMPLISHING REPETITIVE INSP (50HR) FOR AD2008-08-14, FOUND BOTH ENGINE FUEL SERVO PLUGS LOOSE. BOTH PLUGS REMOVED, INSPECTED, RETORQUED AND SAFETIED IAW AD REQUIREMENTS. NO ENGINE PERFORMANCE SNAGS REPORTED. LT ENGINE: TIO-540 -J2BD S/N: L6203-61A, SERVO P/N: 2524500-9 S/N: 83731, TSO: 345.5 HRS RT ENGINE: LTIO-540-J2BD S/N: L2363-68A, SERVO P/N 2524500-9 S/N: 52869, TSO: 345.5 HRS. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081117 CE 2008 11 17 CA080812001 1 20080716 G 3340 S21601 SWITCH CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA STROBE LIGHT FAULTY W A UNSCHED LANDING B B SMOKE/FUMES/ODORS/SPARKS SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) ON JULY 16, 2008 AT APPROX. 13:00, PILOT REPORTED SMOKE IN COCKPIT AND PLASTIC BURNING SMELL. ACFT ELECTRONICS WER E SHUTDOWN AND SMOKE DISSIPATED. DURING POST FLIGHT INSP, MAINT DISCOVERED A FAULTY STROBE LIGHT SWITCH, AND REPLACED T HE DEFECTIVE SWITCH. ACFT SYS TESTED WITH NO FURTHER DEFECTS FOUND. 1 H 7 1 3O 3 O NT 3A12 E274 20081117 CE 2008 11 17 CA080812002 1 20080808 G 3252 22430211 CLEVIS CESSNA 24421141 CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL SHIMMY DAMPER BROKEN W D RETURN TO BLOCK E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 9102 (CAN) DAMPER SHAFT CLEVIS BROKE AT NOSE STRUT ATTACHMENT ALLOWING UNRESTRAINED MOTION OF SHIMMY DAMPER. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 20081117 EA 2008 11 17 CA080812003 2 20080808 G 8530 LW13623 PISTON CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE DAMAGED W D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CA 244 (CAN) TOP COMPRESSION RING BROKEN, OIL RING SEIZED, PISTON BURNED FROM BLOWBY, CONNECTING ROD UPPER BRG LOOSE, BRG BORE OUTSIDE SERVICE LIMITS. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 20081124 NE 2008 11 24 CA080812004 2 20080721 G 7261 MS920807 BOLT DHAV DHC8 DHC8314 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE ENGINE OIL LINE LOOSE W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF, THE NR 1 ENGINE LOST OIL PRESSURE AND WAS SUBSEQUENTLY SHUTDOWN. THE ACFT RETURNED TO THE A IRPORT FOR AN APPROACH, HOWEVER, THE VISIBILITY WAS TOO LOW, A MISSED APPROACH WAS EXECUTED FOLLOWED BY A NR OF HOLDS UN TIL THE WEATHER WAS APPROPRIATE TO TRY A SECOND APPROACH. THE ACFT LANDED SAFELY AFTER A SECOND APPROACH. FURTHER INSPEC TION FOUND THE OIL LINE FLANGE BOLTS LOOSE ON THE NR 1 ENGINE, ALLOWING ALL THE OIL TO BE PUMPED OUT OF THE ENGINE. THES E BOLTS ARE NOT DRILLED AND THEREFORE CANNOT BE SAFETY WIRED. PRATT SB 21178 REPLACES THE INSERTS WITH SELF LOCKING INSE RTS. THE BOLTS WERE RETORQUED, OIL REPLENISHED AND THE ACFT WAS RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT E20NE 6 C P7NE 20081117 NE 2008 11 17 CA080812005 2 20080803 G 8530 71167 EXHAUST VALVE PWA 399359 DHAV DHC3 DHC3 2800202 EA PWA R1340 R1340* 52016 NE HAMSTD 23D 23D40 NE CYLINDER BROKEN W A UNSCHED LANDING E VIBRATION/BUFFET NR NOT REPORTED 1 CA 6862 1070 (CAN) EXHAUST VALVE BROKE IN CRUISE FLIGHT 15 MIN AFTER DEPARTURE. PARTIAL POWER LOSS - ENGINE VIBRATION. PRECAUTIONARY LANDING EXECUTED. SERVICEABLE CYL COMPLETE INSTALLED AFTER LOCATING THE DEFECT/FAILURE. ACFT RETURNED TO SERVICE. 1 H 7 1 3R 3 R A815 5E2 6 C P719 20081119 SW 2008 11 19 CA080813002 1 20080813 G 6410 206011809109 PITCH HORN BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL TAIL ROTOR LOOSE W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 CA (CAN) THE STUD WHICH HOLDS THE PITCH LINKS ONTO THE PITCH HORN CAME LOOSE. THIS CAUSED A VIBRATION FELT IN THE PEDALS. T HE TAILROTOR HUB WAS 2400 HOURS TSO AND BLADES WERE 2300 TSN. THERE IS NO REQUIREMENT TO OVERHAUL THE PITCH HORNS SO NO RECORD AS TO TOTAL TIME SINCE NEW ON THE PITCH HORNS. IF LEFT UNATTENDED THIS MAY HAVE CAUSED FURTHER FLIGHT SAFETY AND UNCONTROL OF THE TAIL ROTOR. 1 G 7 1 3U 3 U H2SW E4CE 20081117 EA 2008 11 17 CA080813003 1 20080812 G 2910 AE4760H0592055 HYDRAULIC LINE CNDAIR CL601 CL6013A 8070802 EA GE CF34 CF343A2 30067 NE HYDRAULIC SYS BURST W O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 CA 4785 (CAN) IN FLIGHT NR 2 HYDR "LO PRESS" CAME ON, FWD BY "LO LEVEL". NR 2 HYDR FLUID COMPLETLY LOST THROUGH A BURST HYDR PR ESSURE HOSE IN RT NACELLE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081117 CE 2008 11 17 CA080813004 1 20080806 G 3250 55656195 ARM CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE NLG STEERING DAMAGED W K NONE O OTHER UK UNKNOWN 1 CA 6500 (CAN) CAMPAIGN NOTICE 851-53-11-047 WAS BEING ACCOMPLISHED WHEN DAMAGE TO THE NOSE GEAR STEERING ARM WAS DISCOVERED. THE FWD ATTACHMENT HARDWARE REMOVED FROM THE CHANNEL-TRUNION BRACE WAS FOUND TO BE MS27039-1-10 AND AN960-3 WASHERS, WHEN M S27039-1-07 AND NIL WASHERS ARE CALLED FOR IN THE MFG IPC. THE LENGTH OF THE INSTALLED SCREWS WERE SUCH THAT WHEN FULL N OSE WHEEL DEFLECTION WAS ACHIEVED THERE WAS INTERFERENCE BETWEEN THE SCREW AND THE STEERING ARM CAUSING THE DAMAGE. STE ERING ARM P/N 5565619-5 REPAIRED IAW ASEO 851-32-50-0212 BLEND REPAIR. CORRECT HARDWARE (MS27039-1-07 SCREWS AND MS2104 2-3 NUTS) INSTALLED ON CHANNEL-TRUNION BRACE. 1 L 7 2 4F 4 F A22CE E1NE 20081117 EA 2008 11 17 CA080813005 1 20080812 G 2751 756158 TORQUE SENSOR DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE TE FLAP INOPERATIVE W D RETURN TO BLOCK J WARNING INDICATION CR CRUISE 1 CA (CAN) FLAP DRIVE CAUTION LIGHT IN CRUISE. ELECTED TO RETURN A/C TO DEPARTURE FOR REPAIR. CONFIRMED FAULT TO TORQUE SENS OR ASSY S/N:0570 (ROGUE UNIT). WHEN LT SWITCH IS COLD SPRAYED "FLAP DRIVE" CAUTION LIGHT COMES ON WITH TQ SENSOR CENTER ED. TORQUE SENSOR ASSY P/N:756158 REQUIRES REPLACEMENT. (RESOLVED ON W/O: 27127 TASKCARD: NR-00001) FLAP DRIVE TORQUE SENSOR ASSY REPLACED. RII INSPECTION COMPLETED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081119 EA 2008 11 19 CA080813006 2 20080801 G 8520 SL18840 CAMSHAFT CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA ENGINE WORN W K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CA 1150 (CAN) NR 3 AND NR 4 INTAKE LOBE IS ROUNDED OFF AND SUBSEQUENTLY METAL WAS FOUND IN THE OIL FILTER DURING ROUTINE MX. 1 H 7 1 3O 3 O NT 3A12 E274 20081117 EU 2008 11 17 CA080813007 1 20080812 G 5544 5554012215 COVER PLATE 5554012038 PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL RUDDER DAMAGED W O OTHER F FLT CONT AFFECTED TO TAKEOFF 1 CA 19069 (CAN) PILOT INDICATES RUDDER MOVEMENT STIFF. MORE RT RUDDER REQUIRED AT TAKE-OFF. INSP BY MAINT REVEALED THAT THE COVER PLATE AT THE BOTTOM OF THE RUDDER WAS BENT OUT OF SHAPE CAUSING INTERFERENCE WITH THE RUDDER MOVEMENT. INSP OF OTHER AC FT REVEALS THAT THIS COVER PLATE CAN RUB ON THE RUDDER STOP OVER TIME AND MAY BE THE BEGINNING OF THE CAUSE OF THIS PROB LEM. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081117 CE 2008 11 17 CA080813008 1 20080813 G 3097 WIRE CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL DEICE SYS CHAFED W K NONE N FALSE WARNING NR NOT REPORTED 1 CA (CAN) PILOT REPORTED INTERMITTENT "DE-ICE PRESSURE" ANNUNCIATOR ILLUMINATION WHEN DE-ICE WAS NOT SELECTED. ON INVESTIGAT ION A CHAFED WIRE WAS FOUND IN ZONE 527. THE WIRE HAD CHAFED ON THE LT CABIN ENTRY LIGHT FIXTURE CAUSING AN INTERMITTENT SHORT TO GROUND ACTIVATING THE LIGHT. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 20081118 SW 2008 11 18 CA080813009 1 20080320 G 6420 212011701 BELLCRANK BELL 212011701 BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE TAIL ROTOR IMPROPER PART W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING T/R RIGGING CHECK, IT WAS NOTED THAT WHEN FULL LT PEDAL WAS APPLIED, THE COUNTERWEIGHT LINK TO COUNTER WEIG HT ARM HARDWARE WOULD CONTACT T/R CROSSHEAD ASSY. UPON INVESTIGATION THE WRONG P/N OF COUNTERWEIGHT BELLCRANK ASSY`S WER E INSTALLED FOR THE PARTICULAR P/N OF THE T/R HUB ASSY. THIS A/C HAS T/R HUB ASSY P/N 212-011-701-125 INSTALLED AT THIS TIME. 1 G 7 1 4U 4 U H4SW E22EA 20081118 SW 2008 11 18 CA080813011 1 20080526 G 6410 BLADE BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE TIAL ROTOR UNKNOWN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) INSP OF T/R HUB AND BLADE ASSY REVEALED AN INTERFERENCE BETWEEN BOTH T/R BLADES AND T/R YOKE AT THE LEADING EDGE/R OOT. T/R BLADES REMOVED AND DRESSED OUT TO PROVIDE .010" CLEARANCE BETWEEN YOKE AND BLADES (IAW PSE). YOKE INSPECTED FOR DAMAGE, NONE FOUND. 1 G 7 1 4U 4 U H4SW E22EA 20081119 NE 2008 11 19 CA080813012 2 20080811 G 7250 TURBINE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE ENGINE FAILED W B R EMER. DESCENT AUTOROTATION K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 CA (CAN) HELICOPTER WAS RETURNING TO AIRPORT, ENGINE CHIP LIGHT CAME ON, FOLLOWED SHORTLY BY A POPPING SOUND FROM ENGINE, A VIBRATION IN AIRFRAME & LOW ROTOR HORN. AN AUTOROTATION INITIATED & WHEN PILOT FLARED TO LAND, NOTICED ENGINE STILL DEV ELOPING POWER. ACFT LANDED UNDER POWER WITH NO FURTHER INCIDENT. INITIAL INVESTIGATION SHOWED MANY BIG CHUNKS OF METAL ON CHIP PLUGS & IN OIL STRAINERS. METAL ALSO FOUND ON ENGINE DECK. REAR BEARING VENT LINE FOUND OFF THE 2 O’CLOCK VENT STRUT & A LARGE AMOUNT OF OIL BLOWN OUT VENT ONTO ENGINE, ENGINE DECK & TAILBOOM (APPROX. 2 QUARTS LOST). THIS WOULD EXP LAIN INTENSE SMOKE OBSERVED COMING FROM ENGINE DURING AUTOROTATION & LANDING. RUBBING NOISES CAN BE HEARD WHEN TURNING C 1 G 7 1 3U 3 U H9EU E19EU 20081118 NE 2008 11 18 CA080814001 2 20080703 G 7200 ENGINE BAG ATP ATP EU PWA PW120 PW126A NE FLAMED OUT W K NONE X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) THE ENGINE FLAMED OUT AND THEN RELIT (AUTO RELIGHT) WITHIN 2 SEC. THE OCCURRENCE HAPPENED APPROXIMATELY 10 MIN. AF TER ENCOUNTERING SEVERE WEATHER INCLUDING HAIL AND MODERATE TURBULENCE. THE FLIGHT CONTINUED TO DESTINATION WITHOUT FURT HER PROBLEMS. POST FLIGHT INSPECTION SHOWED NO DAMAGE AND THE A/C CONTINUED IN SERVICE. 2 L 7 2 4T 4 T RT A27NM E2ONE 20081118 NE 2008 11 18 CA080814002 2 20080428 G 7200 PLANETARY GEAR CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE ENGINE DISTRESSED W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER T/O, THE PILOT NOTED ENGINE VIBRATION FOLLOWED BY AN OIL PRESSURE DROP. HE RETURNED TO THE POINT OF DEPARTUR E WHERE AN UNEVENTFUL LANDING WAS PERFORMED UNDER POWER. THE ENGINE WAS FWDED TO MFG WHERE 1ST STAGE PLANET GEAR DISTRES S WAS FOUND. THE AFFECTED HARDWARE WILL BE RETURNED TO MFG FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 H 7 1 3T 3 T A37CE E4EA 20081118 NE 2008 11 18 CA080814003 2 20080730 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE FOD W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA (CAN) PILOT ABORTED TAKE-OFF DUE TO ENGINE POWER LOSS. POST FLIGHT INSP REVEALED POWER TURBINE AND 1ST STAGE COMPRESSOR FOD. ENGINE WAS REMOVED AND SENT FOR EVALUATION AND REPAIR. SUSPECT HARDWARE WILL BE FWDED TO MFG FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 H 7 1 3T 3 T A37CE E4EA 20081119 NE 2008 11 19 CA080814004 2 20080809 G 7261 LINE BOEING 767 7673Y0 NM GE CF6 CF680C2B6F 30025 NE ENGINE OIL SYS CRACKED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) NR 1 ENGINE DUE HOC OCCURRED AUG 8/9. ON INVESTIGATION IT APPEARS THERE IS A LEAK FROM THE TAIL BEARING HOUSING FE ED TUBE NEAR THE AFT SUMP HOUSING & REPLACED THE OIL FEED LINE. ACTUAL ROOT CAUSE IS NOT YET KNOWN (CRACKED LINE LOOSE OR DAMAGED FITTING). OIL TRENDING DID NOT SHOW ANY CONSUMPTION OR PRESSURE ANOMALIES PRIOR TO THE EVENT. 2 L 7 2 4F 4 F RT A1NM E13NE 20081118 NE 2008 11 18 CA080814005 2 20080730 G 7200 ENGINE CESSNA 680 680CE 2076811 CE PWC PW306 PW306C 52169 NE LEFT POWER LOSS W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA (CAN) DURING TAKE-OFF, THE LT ENGINE POWER ROLLED BACK ABOUT 8-10 PERCENT. WHILE ON CLIMB AND WHILE LEVELING-OFF AT 6,00 0 FT, SEVERAL OTHER ROLL-BACKS WERE NOTED. ACCORDING TO THE PIC, THESE SEEMED TO OCCUR AFTER A TLA ADJUSTMENT. CREW STAB ILIZED ACFT AT 6,000 FT AND DECIDED TO DIVERT. AN UNEVENTFUL DUAL ENGINE LANDING WAS ACCOMPLISHED. TROUBLESHOOTING REVEA LED POSSIBLE ISSUE WITH LT ENGINE FCU. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISH ED. 2 L 7 2 4F 4 F RC T00012WI E35NE 20081118 EA 2008 11 18 CA080814006 1 20080812 G 7732 6233M30A TRANSDUCER CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE VIBRATION ANLYZR UNSERVICEABLE W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) ON THE TAKE-OFF ROLL AT APRX 60KTS, THE FLIGHT CREW REJECTED TAKE-OFF DUE TO AN N2 ENGINE VIBRATION CAUTION MESSAG E. VIBE ICON ON LT ENG APPROX 87 PERCENT. SECOND RUN REVEALED NO VIBE RISE ON INDICATOR BUT GETTING VIBE AMBER MESSAGE . CREW DID NOT FEEL ANYTHING BUT WANTED INSP BEFORE APPLYING MEL. LT N2 VIBE `VIB` ICON INDICATES CORE HAS EXCEEDED 1. 7 MILS. N1 VIBE INDICATION AND NEEDLES WILL NOT CORRELATE TO AN N2 VIBE INDICATION. NO CHIP FLAGS NOTED. BORESCOPE INSP OF COMPRESSOR AND HP TURBINE CARRIED OUT AND FOUND WITHIN LIMITS. NR1 ENGINE VIBE TRANSDUCER REPLACED. HIGH POWERED RUN S CARRIED OUT AND VIBE INDICATIONS ALL CHECK OK. SYSTEM CHECKED SERVICEABLE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081118 EU 2008 11 18 CA080814007 1 20080814 G 3246 Z0DN6068757295 WHEEL HALF PARKER40270 SOCATA TBM TBM700 8682000 EU RT MLG CRACKED W O OTHER O OTHER LD LANDING 1 CA (CAN) DURING LANDING ROLL, PILOT NOTICED ABNORMAL "FEEL" OF ACFT AND STEERING. DISCOVERED FLAT TIRE ON RT MAIN WHEEL. A CFT RECOVERED FROM RUNWAY. DISASSEMBLED WHEEL AND PERFORMED DYE PENETRANT INSP ON WHEEL HALVES. CRACK INDICATION VERY EV IDENT IN INNER BEAD RADIUS OF OUTER WHEEL HALF SUB-ASSEMBLY, AND ALSO VISIBLE ON OUTER SURFACE. PART IS SUBJECT TO REPET ITIVE NDT INSPECTIONS. WHEEL HALF SUB-ASSEMBLY REPLACED. 1 L 7 1 3T RT A60EU 20081118 NE 2008 11 18 CA080814008 2 20080802 G 7200 ENGINE CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE LEFT MALFUNCTIONED W K NONE Y ENGINE STOPPAGE AP APPROACH 1 CA (CAN) WHILE ON APPROACH, THE LT ENGINE ROLLED BACK AND WOULD NOT RESPOND TO THROTTLE MOVEMENTS. WHILE CREW WAS PERFORMIN G EMERGENCY CHECKLIST FOR ENGINE SHUTDOWN. THE LT ENGINE SHUTDOWN ON ITS OWN. ACFT LANDED WITHOUT INCIDENT. MFG WILL C ONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 L 7 2 4F 4 F RT A22CE E00053EN 20081118 NE 2008 11 18 CA080814009 2 20080804 G 7200 ENGINE EMB 120 EMB120 3260201 SO PWA PW118 PW118B NE MALFUNCTIONED W E C ENGINE SHUTDOWN ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) WHILE ON INITIAL TAKEOFF ROLL PHASE, PILOT APPLIED POWER ON BOTH ENGINES BUT NOTICED FUEL AND OIL PRESSURE DECREAS ING ON ONE ENGINE. PILOTS DECIDED TO ABORT TAKEOFF, SHUTDOWN THE AFFECTED ENGINE AND RETURN TO GATE. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 L 7 2 4T 4 T RT A31SO E20NE 20081118 NE 2008 11 18 CA080814010 2 20080804 G 7200 ENGINE CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE NR 1 SHUTDOWN W A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CA (CAN) THE ACFT WAS ON A FIREFIGHTING MISSION. JUST AFTER A WATER DROP, AS THE PILOT APPLIED FOR POWER, THE NR1 ENGINE WE NT INTO AUTOFEATHER AND SHUTDOWN BY ITSELF. THE PILOT FOLLOWED PROCEDURES AND RESTARTED THE ENGINE. THE ACFT LANDED SAFE LY. TROUBLESHOOTING IS FOCUSING ON ELECTRICAL HARNESS AND POSSIBLE OVERTORQUE. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A14EA E20NE 20081119 NM 2008 11 19 CA080814011 1 20080806 G 5330 LAP JOINT EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE FUSELAGE LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 7037 (CAN) INITIALLY SNAGGED BY A FAA INSPECTOR FOR TRACES OF AIR LEAK AT THE LAP JOINT BELOW THE 7TH WINDOW ON THE LT SIDE ( NEAR FR74, STR12L). FURTHER INVESTIGATION IN YYZ DISCOVERED THAT THERE WAS A TOTAL OF 12 LEAK POINTS ON THE LT AND 11 ON THE RT SIDE. THE ACFT DID PASS THE AMM CABIN PRESSURIZATION LEAKAGE TEST (21-31-00). 2 L 7 2 4F 4 F RT A56NM E00063EN 20081119 NE 2008 11 19 CA080814012 2 20080804 G 7200 ENGINE LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE MALFUNCTIONED W C ABORTED TAKEOFF M B J OVER TEMP SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TO TAKEOFF 1 CA (CAN) AT THE BEGINNING OF THE TAKE-OFF ROLL, PILOT REPORTED NO RESPONSE TO THROTTLE LEVER MOVEMENT, WITH T4.5 INDICATED TEMPERATURE PEAKING AT 870 TO 900 C. THE TAKE-OFF WAS SAFELY ABORTED. THE ENGINE TEMPERATURE REMAINED HIGHER THAN THE SI STER ENGINE AFTER SHUTDOWN AND A BURNED ODOR WAS NOTICED, WITH SOME SMOKE COMING FROM THE EXHAUST. ENGINE IS BEING REMOV ED AND SENT FOR INVESTIGATION. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLI SHED. 2 L 7 2 4F 4 F RT A10CE E35NE 20081119 EA 2008 11 19 CA080814013 2 20080812 G 7200 ENGINE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA LEFT FAILED W C ABORTED TAKEOFF E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 CA (CAN) DURING TAKE OFF ROLL AT AROUND 60 KNOTS, LT ENGINE ITT ENGINE WARNING ILLUMINATED AND CREW FELT THE ACFT YAW. ENGI NE WAS SECURED AND ACFT RETURNED TO GATE WITHOUT INCIDENT. METALLIC DEBRIS OBSERVED ON THE RUNWAY AND IN ENGINE EXHAUST DUCT. ENGINE TO BE REMOVED AND SENT TO PWC FOR INVESTIGATION. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADV ISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A13NM E00062EN 20081119 WP 2008 11 19 CA080815001 2 20080811 G 7321 FUEL CONTROL DORNER DO228 DO228202 2992030 EU GARRTT TPE331 TPE3315 01514 WP NR 1 ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN F FLT CONT AFFECTED NR NOT REPORTED 1 CA (CAN) ACFT WAS RELEASED TO A SATISFACTORY TEST FLIGHT FOLLOWING NR 1 ENGINE CHANGE. A NTS IN FLIGHT SHUT DOWN WAS TO BE PERFORMED BEFORE ACFT COULD BE RELEASED BACK TO SERVICE. ACFT DEPARTED AND HAD A NORMAL TAKE OFF AND PROCEED WITH NTS S HUT DOWN. PILOT PROCEEDED TO PULL SPEED LEVER BACK FOR FUEL SHUT AND THEN TO FEATHER POSITION AND THEN ENGINE SHUT DOWN AND FEATHERED & ALL WAS NORMAL. PILOT THEN PROCEEDED TO TAKE SPEED LEVER OUT OF FEATHER TO SPEEDS LOW TO RESTART ENGINE AND FOUND THE SPEED LEVER WAS JAMMED AND WOULD NOT MOVE. PILOT THEN LANDED ACFT SINGLE ENGINE WITH NO PROBLEMS. SPEED LE VER CONTROLS WERE CHECKED AND FOUND THAT THE LEVER ON THE FCU WAS OVERCENTERING CAUSING THE JAMMING OF THE CONTROLS. ENG 2 H 7 2 4T 4 T RT A16EU E4WE 20081119 NM 2008 11 19 CA080815002 1 20080813 G 2432 4011769 BATTERY DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MASTER OVERHEATED W H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING M J OVER TEMP WARNING INDICATION CL CLIMB 1 CA 21080 478 (CAN) DURING CLIMB OUT FROM YWK, THE CREW RECEIVED A "MAIN BAT HOT" RED WARNING MSG ASSOCIATED WITH A HIGH TEMPERATURE O N THE BATTERY TEMPERATURE MONITOR. THE ACFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. MX CONFIRMED THE BATTERY SUFFE RED FROM A THERMAL RUN-AWAY. THE MAIN BATTERY WAS REPLACED AND THE ACFT RETURNED INTO SERVICE. THE BATTERY TEMPERATURE W AS NOT RECORDED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081119 NE 2008 11 19 CA080815004 2 20080812 G 7200 ENGINE CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE RIGHT FIRE W A UNSCHED LANDING A FLAME/FIRE NR NOT REPORTED 1 CA (CAN) DURING A FIRE FIGHTING MISSION, RT ENGINE WAS SHUT DOWN DUE TO A FIRE WARNING. AN EMERGENCY WAS DECLARED, ACFT DIV ERTED AND LANDED SAFELY. POST FLIGHT INSPECTION REVEALED EVIDENCE OF A FIRE EXTERNAL TO THE ENGINE CASING WITH DAMAGE TO FIREWALL. A MANUFACTURER FIELD SUPPORT REPRESENTATIVE WILL BE ON SITE 14 AUG TO SUPPORT ON SITE INVESTIGATION. MANUFAC TURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A14EA E20NE 20081119 EA 2008 11 19 CA080815005 2 20080803 G 7314 SPLINE BEECH STC STC90BEECH PWA PT6 PT6A20 52043 EA FUEL PUMP WORN W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA (CAN) DURING SKYDIVING OPS, SHORTLY AFTER TAKE-OFF ACFT CRASHED UNDER UNKNOWN CIRCUMSTANCES. IT WAS REPORTED THAT PILOT WAS ATTEMPTING TO RETURN TO THE POINT OF DEPARTURE WHEN THE ACCIDENT OCCURRED. PRELIMINARY ASSESSMENT OF ENGINES REVEALE D LT ENGINE WITH SEVERELY WORN FUEL PUMP SPLINE. ENGINES WILL BE FORWARDED TO MANUFACTURER MONTREAL FOR INVESTIGATION. M ANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 L 7 2 3O 3 T 3A20 E4EA 20081119 EA 2008 11 19 CA080815006 2 20080713 G 8520 LW15288 CONNECTING ROD PIPER PA44 PA44180 7104402 SO LYC O360 LO360E1A6 41514 EA NR 4 CYLINDER BROKEN W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) ENGINE FAILED DUE TO FAILURE OF NR 3-4 CONNECTING RODS. I WAS NOT ABLE TO REMOVE NR 3 OR 4 CYLINDER DUE TO FLANGES BENT OVER ON INSIDE OF CRANK CASE CRANK SHAFT MAY HAVE FAILED. FOR FURTHER INFO CONTACT: FRANK FILION 1 L 7 2 3O 3 O A19S0 E286 20081112 NM 2008 11 12 CA080815009 1 20080117 G 3240 BRAKE EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE MLG CHATTERING W O OTHER S AFFECT SYSTEMS TX TAXI/GRND HDL 1 CA (CAN) AS REPORTED BY FLIGHT CREW: LT BRAKE CHATTERS WHEN PRESSED, VERY PRONOUNCED AT TIMES CARBON DISK FAILURE CONFIRMED . 2 L 7 2 4F 4 F RT A56NM E00063EN 20081112 NM 2008 11 12 CA080818001 1 20080814 G 2913 661733 PUMP BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU HYD SYSTEM LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 4815 (CAN) DURING CRUISE OPERATION FLIGHT CREW OBSERVED NR 1 HYDR SYS CAUTION LIGHT ON, FLIGHT DIVERTED TO BASE. CREW CONFIRM ED NO PRESSURE FROM NR 1 EDP SELECTED SPU CONFIRMED PRESSURE 3000 PSI AND NO QUANTITY LOSS. ON GROUND TROUBLESHOOTING RE VEALED EDP HAD 5 PUNCTURES THROUGH CASING & SOURCE OF SMALL AMOUNT OF HYDR FLUID LOSS. NR 1 ENGINE DRIVEN PUMP REPLACED. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081113 CE 2008 11 13 CA080818002 1 20080707 G 2730 CONTROLLER BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL ELEVATOR FROZEN W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) APPROXIMATELY 50 MIN OUT, AUTOPILOT BEGAN TO CLIMB, THE A/P WAS DISCONNECTED AND ACFT MANUALLY BROUGHT BACK TO ALT ITUDE. A/P WAS REENGAGED AND THEN BEGAN TO DESCEND FOLLOWED BY THE AP TRIM FAIL ANN. A/P DISCONNECTED, ELECTRIC TRIM CHE CK AND APPEARED SERVICEABLE FLIGHT WAS CONTINUED. ON DESCENT, TRIM WAS NOTED TO HAVE LITTLE EFFECT AND EXCESSIVE CONTROL FORCES WERE REQUIRED. AFTER LANDING THE TRIM WAS INSPECTED AND THE ELEVATOR WAS FOUND TO BE FROZEN IN A NOSE UP POSITIO N. AN AME WAS DISPATCHED TO INSPECT THE FLIGHT CONTROLS AFFECTED. THE ENTIRE ELEVATOR AND TRIM SYS WAS INSPECTED WITH NO DISCREPANCIES NOTED. AUTOPILOT SYS AND SERVOS INSPECTED AND TESTED WITH NO FAULTS NOTED. ELEVATOR AND TRIM JACKS WERE L 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 20081113 EU 2008 11 13 CA080818003 1 20080806 G 7500 32156281 O-RING ISRAEL 1125 ASTRASPX 4500205 EU GARRTT TFE731 TFE73140 29001 NE BLEED SYSTEM FAILED W A UNSCHED LANDING M J OVER TEMP WARNING INDICATION CL CLIMB 1 CA 3008 3008 (CAN) RT BLEED LEAK LIGHT ILLUMINATED IN CLIMB OUT. AC RETURNED TO BASE. CONFIRMED LT BLEED LEAK ON GROUND DURING HIGH P OWER ENGINE RUNS. COULD NOT DUPLICATE RT BLEED LEAK ON GROUND. FOUND BOTH BLEED SWITCHING VALVES LEAKING FROM REGULATOR FITTING ASSY. DUE TO BAKED O-RINGS ALLOWING HIGH PRESSURE BLEED AIR INTO AFT EQUIPMENT BAY AREA. THIS CAUSED THE SUBSEQ UENT ACTIVATION OF BLEED LEAK WARNING ILLUMINATION AT 250 DEG F. BOTH VALVES REPLACED O-RING NOT FIELD REPLACEABLE. 2 L 7 2 4F 4 F RT A16NM E1NM 20081113 CE 2008 11 13 CA080819001 1 20080814 G 2510 5055301401 CABLE ASSY CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA SEAT BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 325 (CAN) ON AUGUST 14, 2008, PILOT REPORTED "PILOT SEAT DOESN`T MOVE BACK, COULD NOT GET OUT". INVESTIGATION BY MAINT FOUND THAT THE CABLE ASSEMBLY FOR THE PILOT SEAT SECONDARY SEAT STOP HAD FAILED PREVENTING THE INERTIAL REEL FROM RELEASING T O ALLOW THE SEAT TO MOVE. THE CABLE HAD BROKEN IMMEDIATELY AFTER THE SWAGED END. 1 H 7 1 3O 3 O NT 3A12 E274 20081113 EA 2008 11 13 CA080819002 1 20080715 G 5610 NP1393226 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) "F/O SIDE WINDOW SHATTERED JUST AFTER TAKE OFF (RETURNED), DETERMINED TO BE CENTER PANE". REMOVED AND REPLACED THE F/O`S SIDE WINDSHIELD. 2 L 7 2 4F 4 F RT A21EA E15NE 20081113 EA 2008 11 13 CA080819003 1 20080715 G 5610 NP1393226 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) "F/O WINDSHIELD SHATTERED ENROUTE, DIVERTED ". REMOVED AND REPLACED THE F/O`S WINDSHIELD. 2 L 7 2 4F 4 F RT A21EA E15NE 20081113 EA 2008 11 13 CA080819004 1 20080815 G 5610 NP1393215 WINDSHIELD CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C5 30050 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 14795 (CAN) "DISC - AFTER TAKEOFF CAPTAIN`S WINDSHIELD CRACKED. NO OTHER PROBLEMS NOTED. REMOVED AND REPLACED PILOTS WINDSHIEL D. 2 L 7 2 4F 4 F RT A21EA E00063EN 20081113 EA 2008 11 13 CA080819005 1 20080816 G 5610 NP13932210 WINDOW CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C5 30050 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 12265 (CAN) DISC - IN CRUISE FLIGHT, F/O SIDE WINDSHIELD CRACKED AND WINDSHIELD HEAT ON RT SIDE FAILED.. ACFT RETURNED. NO PRE SS PROBLEM. ALL OTHER SYS NORMAL. REMOVED AND REPLACED F/O SIDE WINDOW. 2 L 7 2 4F 4 F RT A21EA E00063EN 20081113 NM 2008 11 13 CA080819006 1 20080818 G 2913 5116403 PUMP EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE HYD SYSTEM FAILED W O OTHER K FLUID LOSS CR CRUISE 1 CA (CAN) WHILE ENROUTE, THE NR 1 HYD SYS FAILED. AFTER CONSULTATION WITH MAINT, FLIGHT CONTINUED AND LANDED WITHOUT INCIDEN T. NR 1 EDP REPLACED REF AMM 29-11-01 PB 401,-422 AND TESTED REF AMM 29-11-01 P 501-5 12. NO FAULTS OR LEAKS. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081118 EU 2008 11 18 CA080819008 1 20080805 G 6230 NUT BOLKMS 117 BK117B2 5626013 EU LYC LTS101 LTS101750B1 41560 NE MAIN ROTOR LOOSE W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA (CAN) VIBRATION NOTICEABLE ON COLLECTIVE CONTROL PWR CHANGES. FURTHER INVESTIGATION REVEALED THAT THE MAIN ROTOR MAST HA D .2500 INCH VERTICAL PLAY. ON THE REMOVAL PROCEDURE OF THE MAIN ROTOR MAST FROM THE GEARBOX IT WAS NOTED THAT THE MAST NUT HAD NO TORQUE. A THOROUGH INSPECTION OF THE ACCESSIBLE GEARBOX COMPONENTS WAS CONDUCTED WITH NO FAULTS DETECTED, THE MAIN ROTOR MAST WAS REINSTALLED AND THE ACFT FLOWN WITH NO FURTHER VIBRATION DETECTED. 1 G 7 2 3U 3 U NC H13EU E5NE10 20081118 GL 2008 11 18 CA080819009 1 20080815 G 3234 17C17616A3 VALVE BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP LANDING GEAR UNKNOWN W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) DURING FINAL APPROACH THE PILOT SELECTED THE LANDING GEAR DOWN AND THERE WAS NO MOVEMENT. MOMENTARILY THE PROX SYS FAULT CYAN CAS POSTED, BUT CLEARED WITHIN SECONDS. THE PILOT PUT THE GEAR HANDLE BACK UP. THEN SELECTED IT BACK DOWN. A GAIN THE GEAR DID NOT MOVE. HE THEN GRABBED THE QRH AND CARRIED OUT THE EMER PROCEDURES TO DEPLOY THE GEAR. WHEN THE EM ER LG HANDLE WAS PULLED THE GEAR DEPLOYED AND ACHIEVED 3 GREEN IN A FEW SECONDS. THE LANDING WENT SMOOTHLY. 2 L 7 2 4F 4 F RT T00005NY E00010LA 20081118 SW 2008 11 18 CA080819010 1 20080808 G 2435 23079010 STARTER GEN FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR 29081 NE MCAULY 4HFR34 4HFR34C652 NE RIGHT FAILED W K NONE J WARNING INDICATION DE DESCENT 1 CA 710 (CAN) UPON DESCENT, THE RT GENERATOR FAILED AND COULD NOT BE RESET. MAINT WAS CALLED UPON LANDING AND FOUND THE AFT PART OF THE STARTER GENERATOR HAD FAILED. REAR COVER WAS DESTROYED, REAR FAN BLADES WERE ALL BROKEN AND REAR BEARING WAS DES TROYED. UNIT REPLACED AND ACFT CHECKED SERVICEABLE. INVESTIGATION INTO FAILURE PENDING. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081124 SW 2008 11 24 CA080819011 1 20080810 G 7500 8943825 TUBE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE3311 01514 WP MCAULY 4HFR34 4HFR34C652 NE LT ENGINE BLEED FRACTURED W O OTHER J WARNING INDICATION TO TAKEOFF 1 CA (CAN) TUBE HAD BROKEN AT WELDMENT THAT ATTACHES THE TUBE TO THE FLANGE THAT BOLTS IT TO THE ENGINE BLEED. AIR PORT WAS CRACKED 90% OF THE WAY AROUND WELD. THIS CAUSED THE ENGINE TO NOT REACH TARGET TORQUES UNLESS WATER METH WAS USED. UNI T WAS REPLACED AND ACFT RETURNED TO SERVICE. 2 L 7 2 4T 3 T RT A8SW E3WE 6 C 3PNE 20081118 EU 2008 11 18 CA080819012 1 20080817 G 2750 945020220 DRIVE SHAFT PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TE FLAP SHEARED W K NONE F FLT CONT AFFECTED AP APPROACH 1 CA 6330 (CAN) LT INBD FLAP FLEXABLE DRIVE SHAFT SHEARED AT INBD DRIVE END. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081120 2008 11 20 CA080819013 4 20080812 G 6122 10185 COTTER PIN DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HARTZL HCB3R HCB3R304 GL GOVERNOR MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ENG INSP, TWO COTTER PIN TAILS WERE FOUND IN ENG ACCY SUMP. INVESTIGATION INTO SOURCE OF PIN TAILS REVEALED THAT COTTER PIN (P/N 10185) SECURING NUT (P/N 23212) FOR GOVERNOR DRIVE GEAR SHAFT (P/N 2715) IN ACCY SECTION WAS MISSI NG. THERE WAS EVIDENCE OF PIN HAVING GONE THROUGH THE GEARS AND REDUCED TO METAL PARTICLES. OVERHAUL SHOP WAS CONTACTED AND REVEALED THAT THEY HAD A NEW EMPLOYEE ASSEMBLING THIS SECTION OF ENG, AND WAS USING STANDARD COTTER PIN INSTALLATION PROCEDURE. IN THIS LOCATION, IF THE PIN IS INSTALLED WITH TAIL FOLDED BACK OVER END OF SHAFT, IT WILL CONTACT INSIDE O F GOVERNOR BASE AND BREAK OFF. ONCE THIS HAPPENS, THE SHORT END OF COTTER PIN CAN ROTATE AND ALSO CONTACT THE INSIDE OF 1 H 7 1 3R 3 R RC A806 5E1 5 C P28EA 20081118 EA 2008 11 18 CA080820001 2 20080817 G 7261 766859C SCAVENGE PUMP BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NR 2 ENGINE LOOSE W E ENGINE SHUTDOWN J WARNING INDICATION DE DESCENT 1 CA 3083 (CAN) AT 15000 FT IN THE DESCENT, THERE WAS A SUDDEN LOSS OF OIL PRESSURE ON THE NR 2 ENG. GAUGE INSTANTLY SHOWED ZERO W ITH THE NR 2 OIL PRESS WARNING AND CHIME. CREW IMMEDIATELY SHUT DOWN THE NR 2 ENG, TAKING ABOUT 5 TO 10 SECONDS TO COMPL ETE MEMORY ITEMS. AFTER ENGINE/PROP FEATHERED, THERE SEEMED TO BE NO OTHER PROBLEMS. CASTELLATED NUT ON THE OIL SCAVEN GE PUMP FOUND LOOSE. WITH INPUT SHAFT ROTATING THE SPUR GEAR WAS NOT ROTATING WHICH WAS DRIVE FOR THE ADJACENT SHAFT. R GB SCAVENGE IS LOCATED ON THIS SHAFT WHICH WAS NOT ROTATING. OIL SCAVENGE PUMP BEING REPLACED. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081118 2008 11 18 CA080820002 4 20080815 G 5301 RELEASE MECH BELL 407 407 1182206 SW ALLSN 250C 250C47B GL MALFUNCTIONED W O OTHER O OTHER HO HOVERING 1 CA (CAN) HELI BASKET D407-663-011 INSTALLED IAW INSTRUCTIONS. DURING TRAINING (SLING OPERATION) MANUAL RELEASE WAS USED AND FUNCTIONED AS NORMAL DURING THE TRAINING SEQUENCE. ON THE NEXT PICK UP, THE LOAD WAS HOOKED UP ON THE HOOK AND THE PILO T PULLED INTO AN HOVER AND THEN THE CABLE RELEASED WITHOUT ANY ACTION FROM THE PILOT. HE LANDED IMMEDIATELY. FURTHER IN VESTIGATION FOUND THE MANUAL RELEASE CABLE SNAG ON THE OUTSIDE OF THE HOLE CENTER FRAME P/N D2796 STATION 115.75 WHICH P REVENTED THE HOOK TO CLOSE SECURELY. MFG HAS BEEN INFORMED ABOUT THE INCIDENT AND PICTURES WERE FORWARDED AS WELL. 1 G 7 1 3U 3 U O H2SW E1GL 20081118 NM 2008 11 18 CA080821001 1 20080215 G 3242 900005831PR BRAKE EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE NR 1 BRAKE MALFUNCTIONED W K NONE J WARNING INDICATION LD LANDING 1 CA (CAN) NUMEROUS LANDING GEAR NO DISPATCH AND EMERGENCY BRAKE FAULT MESSAGES AFTER TOUCHDOWN NR1 BRAKE REPLACED. CONSIDERE D SERVICEABLE. 2 L 7 2 4F 4 F RT A56NM E00063EN 20081118 NM 2008 11 18 CA080821002 1 20080704 G 3242 900005832PR DISK EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE NR 4 BRAKE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NR 4 MAIN WHEEL BRAKE CARBON DISK BADLY DETERIORATED. 2 L 7 2 4F 4 F RT A56NM E00063EN 20081118 NM 2008 11 18 CA080821003 1 20080714 G 3242 900005832PR BRAKE EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE NR 1 DAMAGED W O OTHER O OTHER IN INSP/MAINT 1 CA (CAN) BRAKE ASSY BREAKING UP. 2 L 7 2 4F 4 F RT A56NM E00063EN 20081118 NM 2008 11 18 CA080821004 1 20080719 G 3242 900005831PR BRAKE ASSY EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE NR 4 FAILED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) ON PUSHBACK REPORT OF NR 4 BRAKE ASSY FAILURE, AS REPORTED BY STATION SERVICES CREW BRAKE ASSY REPLACED. 2 L 7 2 4F 4 F RT A56NM E00063EN 20081118 NM 2008 11 18 CA080821005 1 20080802 G 3242 900005831PR BRAKE ASSY EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE NR 2 FAILED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) ON TAXI OUT TO THE RUNWAY, ECAS MESSAGE "BRK LT FAULT" CAME ON. FOUND NR 2 BRAKE ASSY FAILED. (CARBON FAILURE) 2 L 7 2 4F 4 F RT A56NM E00063EN 20081118 CE 2008 11 18 CA080821006 1 20080818 G 3221 030A311201 ATTACH FITTING MTSBSI MU2 MU2B60 5780460 CE GARRTT TPE331 TPE33110 29053 NE HARTZL HCB4T HCB4TN5 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 15949 15949 (CAN) DURING ROUTINE INSP, THE NOSE LANDING GEAR TRUNNION ATTACH FITTING WAS FOUND TO BE CRACKED. THE CRACK WAS MEASURED AT .3125 OF AN INCH. FITTING REPLACED. 1 H 7 2 3T 4 T RT A10SW E4WE 6 C P40EA 20081118 NM 2008 11 18 CA080821007 1 20080809 G 3242 900005831PR BRAKE EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE LT MLG DEFECTIVE W O OTHER O OTHER LD LANDING 1 CA (CAN) LT MAIN BRAKE TEMPS OB 365/IB149, RT BRAKES IB 148/OB130, BRAKES FELT SOFT, BRAKES REPLACED. CAUSE: CARBON OXIDA TION. 2 L 7 2 4F 4 F RT A56NM E00063EN 20081120 SW 2008 11 20 CA080821008 1 20080820 G 5311 FRAME BELL 206 206L4 1182110 SW ALLSN 250C 250C30P 03013 GL FUSELAGE CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) HYDR SERVO PILOT VALVE SUPPORT RUBBING AGAINST MAIN FRAME. WEAR MARK IS APPARENT ON LT SUPPORT. PICTURES AVAILABLE ON REQUEST AND INFO FWD TO MFG CUSTOMER SUPPORT FOR ACTION. 1 G 7 1 3U 3 U NC H2SW E1GL 20081118 NM 2008 11 18 CA080821009 1 20080809 G 3242 90000582WT BRAKE EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE NR 1 DISINTEGRATED W K NONE J WARNING INDICATION LD LANDING 1 CA (CAN) BRAKE NR 1 DISINTEGRATED AND M/W CHANGED DUE TO BRAKE STUCK IN TIRE. BRAKE NR 1 CHANGED. 2 L 7 2 4F 4 F RT A56NM E00063EN 20081118 EU 2008 11 18 CA080821010 1 20080821 G 3040 320570 SPLICE PILATS PC12 PC1247 7090552 EU PWA PT6 PT6A67 52043 NE HARTZL HCE4A HCE4A3D GL WINDSHIELD HEAT BURNED W O OTHER M W OVER TEMP INADEQUATE Q C IN INSP/MAINT 1 CA 19 (CAN) DURING AN UNRELATED INSTALLATION OF A SATPHONE SYS AN AMP TYPE SPLICE IN THE EXISTING ACFT WIRING WAS NOTED TO BE BURNED AND DISCOLORED. FURTHER INSP INDICATED THAT THE WIRING WAS FOR THE WINDSHIELD HEAT SYS. THE WIRE, NR 1H81A12 AS W AS ALSO DISCOLORED AND BURNED. THERE WERE NO INDICATIONS OF BURNING IN THE SURROUNDING AREA. THE BURNED SPLICE WAS FOUND TO BE POORLY CRIMPED TO THE WIRE. WHEN THE WIRE WAS UNTIED FOR REPAIR IT FELL OUT OF THE SPLICE. THE ADJACENT SPLICE AS DAMAGED AND REQUIRED REPLACEMENT. A FURTHER INSP FOUND ALL 4 SPLICES WERE IMPROPERLY CRIMPED. REMAINDER OF THE WINDSHIE LD HEAT WIRING WAS COMPLETED AND NO FAULTS FOUND. THE WIRES 1H83A12,1H85A12,1H80B12,1H81A12 AND SPLICES WERE ALL REPLACE 1 L 7 1 4T 4 T RT A78EU E26NE 5 C P210NE 20081118 SW 2008 11 18 CA080821011 1 20080215 G 6210 206010200133 BALANCE WEIGHT 206010200133 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL BLADE DEBONDED W O OTHER E VIBRATION/BUFFET AP APPROACH 1 CA 3104 (CAN) IT WAS THOUGHT THAT THE BLADE TIE DOWN WAS LEFT ON THE ACFT. THIS WAS NOT THE CASE IAW A REPORT. THE FOLLOWING OCC URRED. INSP AND SCRAPPED THE M/R BLADE DUE TO WEIGHT POCKET RETAINING HOLES DAMAGED BEYOND LIMITS. DAMAGE CAUSED BY TELL TALE LEAD COUPON (SIZE 1.0`X1.0`X.5`) BONDED TO THE TOP SIDE OF INNER SPAR AT STN. 113.5 DEBONDED INFLIGHT AND BEING FL UNG BY CENTRIFUGAL FORCE OUT THE TIP CAP OF BLADE. THE CENTRIFUGAL FORCE OUT THE TIP CAP OF COUPON HAD ENOUGH INERTIA TO PUSH OUT THE WEIGHT POCKET ON THE T/E SIDE AND TEAR THE SCREWS OUT OF THE SPAR RETAINING HOLES OF TOP AND BOTTOM SPAR A T T/E SIDE OF SPAR. TIP CAP WAS BENT ON L/E AND T/E UNTIL THEIR WAS SUFFIENT OPENING TO ALLOW THE LEAD COUPON TO EXIT BL 1 G 7 1 3U 3 U H2SW E4CE 20081118 CE 2008 11 18 CA080821012 1 20080817 G 5610 66561000010 WINDSHIELD LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP COCKPIT BROKEN W O OTHER Z SIGNIFICANT FAILURE REPORT CR CRUISE 1 CA (CAN) WHILE IN CRUISE AT FLT 400 ENROUTE, THE RT WINDSHIELD OUTTER PLY SHATTERED, CAUSING A LOUD BANG. NO DEPRESSURISATI ON OCCUR, RT WINDSHILED HEAT BECAME INOPERATIVE. RT WINDSHIELD REPLACED WITH NEW ONE. ACFT RETURN TO SERVICE. 2 L 7 2 4F 4 F RT T00008WI E6WE 20081118 2008 11 18 CA080821013 4 20080818 G 3416 066030620010 ALTIMETER PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL DEFECTIVE W O OTHER O OTHER DE DESCENT 1 CA 466 (CAN) PILOT REPORTED THAT AUTOPILOT CAUSING ACFT TO PORPOISE ON DESCENT FROM 18,000 FT (WHEN BARO RESET), THEN GOES AWAY . REPLACED ENCODING ALTIMETER AND PROBLEM SOLVED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081118 WP 2008 11 18 CA080822001 1 20080728 G 6310 C0511 ACTUATOR ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA CLUTCH FAILED W K NONE O OTHER UK UNKNOWN 1 CA 788 (CAN) THE CLUTCH ACTUATOR WOULD NOT FULLY ENGAGE, SERVICABLE ACTUATOR INSTALLED. 1 G 7 1 3O 3 O H11NM E295 20081118 NE 2008 11 18 CA080822002 2 20080731 G 7322 25766304 SERVO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYSTEM UNSERVICEABLE W K NONE O OTHER NR NOT REPORTED 1 CA 1595 (CAN) THE ENGINE HAD ROUGH IDLING, TROUBLESHOOTING REVEALED AN EXCESSIVE AMOUNT OF FUEL WAS BEING INJECTED OUT OF THE FU EL INJECTORS. INSTALLED A SERVICABLE FUEL SERVO. 1 G 7 1 3O 3 O H11NM 1E4 20081118 WP 2008 11 18 CA080822003 1 20080803 G 6310 C0511 ACTUATOR ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA CLUTCH FAILED W K NONE O OTHER TX TAXI/GRND HDL 1 CA (CAN) THE CLUTCH WOULD NOT ENGAGE DURING ACFT START. REPLACED CLUTCH ACTUATOR. 1 G 7 1 3O 3 O H11NM E295 20081118 WP 2008 11 18 CA080822004 1 20080804 G 2435 BC3151004 STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE INOPERATIVE W K NONE O OTHER TX TAXI/GRND HDL 1 CA 372 (CAN) THE STARTER WOULD NOT ENGAGE, REPLACED WITH SERVICABLE STARTER. 1 G 7 1 3O 3 O H11NM 1E4 20081118 SW 2008 11 18 CA080822005 1 20080805 G 2432 RG206 BATTERY BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL MAIN DISCHARGED W K NONE O OTHER TX TAXI/GRND HDL 1 CA 157 (CAN) DURING ACFT START, THE BATTERY WAS FOUND WITH NO CHARGE, BATTERY REPLACED. 1 G 7 1 3U 3 U H2SW E4CE 20081118 WP 2008 11 18 CA080822006 1 20080715 G 6310 C0512 CLUTCH ACTUATOR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FAILED W K NONE O OTHER NR NOT REPORTED 1 CA 667 (CAN) CLUTCH WOULD NOT ENGAGE, SERVICABLE CLUTCH ACTUATOR INSTALLED. 1 G 7 1 3O 3 O H11NM 1E4 20081118 WP 2008 11 18 CA080822007 1 20080730 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FAILED W K NONE O OTHER NR NOT REPORTED 1 CA 623 (CAN) THE STARTER WAS GRINDING DURING START, STARTER REPLACED. 1 G 7 1 3O 3 O H11NM 1E4 20081118 WP 2008 11 18 CA080822008 1 20080729 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FAILED W K NONE O OTHER UK UNKNOWN 1 CA (CAN) THER STARTER WOULD NOT START. 1 G 7 1 3O 3 O H11NM 1E4 20081118 WP 2008 11 18 CA080822009 1 20080727 G 2435 BC3151004 STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FAILED W K NONE O OTHER TX TAXI/GRND HDL 1 CA 687 (CAN) STARTER FAILED ON START UP, STARTER REPLACED. 1 G 7 1 3O 3 O H11NM 1E4 20081118 NE 2008 11 18 CA080822010 2 20080714 G 7322 25766304 FCU ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INOPERATIVE W K NONE O OTHER NR NOT REPORTED 1 CA 1996 (CAN) THE ENGINE WAS RUNNING TOO RICH, TROUBLESHOOTING REVEALED COULD NOT ADJUST FUEL INJECTOR SERVO, REPLACED FCU. 1 G 7 1 3O 3 O H11NM 1E4 20081118 SO 2008 11 18 CA080822011 1 20080725 G 3710 441CC7 PUMP PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL VACUUM SYS SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA 452 (CAN) DURING INSPECTION THE LT ENGINE VACUUM PUMP FOUND SEIZED, REPLACED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081118 WP 2008 11 18 CA080822012 1 20080718 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE DAMAGED W K NONE O OTHER UK UNKNOWN 1 CA 55 (CAN) THE STARTER WAS INTERMITTENT, ON INSPECTION WAS FOUND TO HAVE TEETH MISSING. 1 G 7 1 3O 3 O H11NM 1E4 20081118 NE 2008 11 18 CA080822013 2 20080703 G 7322 25766304 FCU ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION THE MIXTURE CONTROL FOUND TO BE BINDING IN THE RICH POSITION, REMOVED DUE TO STIFF MIXTURE LEVER . 1 G 7 1 3O 3 O H11NM 1E4 20081118 GL 2008 11 18 CA080822014 2 20080707 G 7261 LABYRINTH SEAL BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION, OIL WAS FOUND POOLING IN EXHAUST COLLECTOR, SUSPECT NR 5 LAB SEAL. 1 G 7 1 3U 3 U H2SW E4CE 20081124 CE 2008 11 24 CA080822015 1 20080822 G 3060 WIRE CESSNA 441 441 2076020 CE GARRTT TPE331 TPE33110N 29062 NE MCAULY 4HFR34 4HFR34C660 NE PROP DE-ICE BOOT SHORTED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA (CAN) AFTER LANDING, THE ACFT EXPERIENCED A SMALL AMOUNT OF SMOKE IN THE COCKPIT, FOLLOWED IMMEDIATELY BY THE SWITCH CIR CUIT BREAKER POPPING. THE AMMETER FOR THE PROP DE-ICE WAS PEGGED TO THE FULL RT, ONCE THE SYSTEM WAS SWITCHED OFF THE M ETER STILL INDICATED IN THE GREEN. MX INSPECTION REVEALED THE WIRE LEAD OFF THE PROP DE-ICE BOOT WAS TOO LONG AND WAS R UBBING AGAINST THE INSIDE OF THE SPINNE. THE SHORT TO GROUND WENT THROUGH THE BRUSH BLOCK ASSEMBLY TO THE AMMETER IN TH E COCKPIT. 1 L 7 2 3T 4 T RT A28CE E4WE 5 C 3PNE 20081118 2008 11 18 CA080822016 4 20080820 G 3421 1013800803 GYRO BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL ATTITUDE FAILED W O OTHER I FLT. ATTITUDE INST. UK UNKNOWN 1 CA (CAN) THE RT ATTITUDE INDICATOR IS AN AIR DRIVEN UNIT. THIS ACFT HAS HAD NUMEROUS FAILURES. INTERVALS RANGE FROM SEVERAL MONTHS OR MORE TO A FEW DAYS. GENERALLY IF ONE FAILS, THE NEXT ONE FAILS, AND THEN MAY LAST FOR MONTHS. THESE UNITS HAV E TYPICALLY COME FROM SEVERAL DIFFERENT VENDORS. THE ACFT SYSTEMS HAVE BEEN CHECKED THOROUGHLY WITH NO FAULTS FOUND. IT RUNS ON VACUUM, AND THE SUCTION IS EXACTLY IN THE MIDDLE OF MM SPECS. CONTINUING TO MONITOR AND INVESTIGATE THE DEFECT . THERE HAVE BEEN FAILURES ON OTHER ACFT AS WELL, BUT NOT AT THE SAME RATE AS THIS ONE. 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 20081118 NM 2008 11 18 CA080825001 1 20080825 G 6120 666000459 CONTROL UNIT BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NR 2 ENGINE SHORTED W E ENGINE SHUTDOWN F FLT CONT AFFECTED DE DESCENT 1 CA (CAN) DURING FLIGHT THE PROP SPEED SHOWED 1070 RPM IN DESCENT WITH PEC CAUTION. CREW PREFORMED NR2 ENGINE IFSD AND RETUR NED TO BASE. MAINT REVIEWED CDS AND FOUND FC 160 CH A&B. FIM TASK FOLLOWED AND FOUND MPU SHORTED TO GROUND. MPU REPLACE D AND EGR C/O SATIS. ACFT RELEASED FOR SERVICE. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081118 EU 2008 11 18 CA080825002 1 20080822 G 2913 993378 PUMP VICKERS PPEV3008EA PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL HYDRAULIC SYS CRACKED W K NONE K FLUID LOSS AP APPROACH 1 CA 2220 2220 (CAN) ON LANDING, HYDR PUMP CONTINUED TO CYCLE, AFTER LANDING WHEN ACFT PARKED, HYDR FLUID DRIPPING FROM FUSELAGE NEAR H YDR PUMP LOCATION. WHEN PUMP OPERATED FLUID SPRAYED FROM CRACK IN END PLATE OF PUMP, PUMP ASSY REPLACED WITH SERVICABLE UNIT. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081120 SO 2008 11 20 CA080825003 1 20080814 G 2750 487084 SOLENOID 4018542 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL TE FLAP FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) FLIGHT CREW REPORTED DURING SHORT FINAL, SELECTING THE FLAPS FROM 25 DEGREES TO 40 DEGREES, THE ACFT YAWED SEVEREL Y. VISUAL CHECK OF THE FLAP REVEALED THE LT FLAP AT FULL DOWN AND THE RT FLAP AT APPROX 25 DEGREES. THE ACFT LANDED WITH OUT FURTHER INCIDENT. MAINT CONFIRMED THE ASYMMETRIC CONDITION AND FOUND THE LT FLAP DRIVING PAST THE "DOWN" LIMIT SWITC H ACTUATION POINT AND THE LT FLAP L/E ALSO BUCKLED AT THE MID-FLAP TRACK AREA. LT AND RT FLAP TRANSMISSIONS, MOTOR AND D RIVE CABLES WERE INSPECTED. SUSPECT THE ASYMMETRIC CONDITION DUE TO LT FLAP DRIVING PAST THE DOWN LIMIT AND THE EXCESSIV E DRIVING TORQUE CAUSED THE INTERNAL DRIVE CABLE SPLINES TO SKIP CAUSING THE SPLIT FLAP CONDITION. THE FOLLOWING MAINT 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081118 SO 2008 11 18 CA080825004 1 20080820 G 2460 4817102 CLAMP PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL FAULTY W O OTHER G MULTIPLE FAILURE IN INSP/MAINT 1 CA (CAN) FLIGHT CREW REPORTED ALL FLIGHT CONTROL TRIM AND BOTH ENGINE COWL FLAP INDICATORS INOP. MAINT INVESTIGATION ISOLAT ED THE VOLTAGE CLAMPER AT FAULT. AFTER REMOVAL OF FAULTY CLAMPER FOUND THE INTERNAL RESISTOR BADLY BURNED AND PARTIALLY MELTED. VOLTAGE CLAMPER P/N 48171-02 REPLACED AND ALL INDICATIONS CHECKED SERVICEABLE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081201 CE 2008 12 1 CA080826001 1 20080812 G 3260 3086070843004 LIGHT BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL MLG INDICATOR INOPERATIVE W O OTHER P NO WARNING INDICATION DE DESCENT 1 CA (CAN) LANDING GEAR MOTOR CONTROL CIRCUIT BREAKER FOUND POPPED WHEN THE GEAR WAS SELECTED DOWN FOR LANDING. GEAR WAS LOWE RED BY EMERGENCY EXTENSION INDICATING (3) GREEN BUT THE IN TRANSIT LIGHT WAS STILL ON. ACFT EXPERIENCED A NOSE GEAR COL LAPSE ON LANDING. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THERE WERE NO DIVIDERS IN THE HEAD OF THE GEAR DOWN LIGHT BLOCK. THIS ALLOWED LIGHT FROM THE MAIN GEAR DOWN AND LOCK LIGHT TO ILLUMINATE THE NOSE INDICATOR. IT GAVE A FALSE INDICATION THAT ALL 3 GEAR WERE IN THE DOWN AND LOCK POSITION. A NEW INDICATOR WAS INSTALLED SHOWING A POSITIVE INDIC ATION OF THE NOSE NOT LOCKED. 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 20081118 EA 2008 11 18 CA080826002 2 20080824 G 7321 252444057 FCU BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL LT ENGINE FAILED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 2545 (CAN) WHEN POWER WAS APPLIED TO ENGINE AFTER A TOUCHDOWN, A CONSIDERABLE YAW TO THE LT WAS FELT BY THE PILOTS. ACFT WAS MOVED OFF THE RUNWAY AND A MAINT RUN-UP OF ENGINES INDICATED A POWER LOSS IN THE LT ENGINE. AFTER TROUBLESHOOTING THE E NGINE A REPLACEMENT FCU WAS INSTALLED. ENG RUNS AND FLIGHTS WERE COMPLETED WITH NO FURTHER PROBLEMS. 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 20081124 EU 2008 11 24 CA080826003 1 20080815 G 2440 UNKNOWN SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE GROUND POWER UNKNOWN W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) GPU VOLTAGE SPIKED WHILE PROVIDING POWER FOR ENGINE START. GROUND POWER WAS SHUT OFF AND ENGINES STARTED USING IN TERNAL BATTERIES. BOTH ESSENTIAL DC ELECTRICAL CBS FOUND TRIPPED WHILE PERFORMING TAXI CHECK LIST. RETURNED TO GATE. 2 L 7 2 4T 4 T RT A52EU E8NE6 20081118 EU 2008 11 18 CA080826004 1 20080819 G 3213 STRUT SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE LT MLG CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF CHECKS COMPLETED AND CONDITION LEVER RETARDED, RESULTING IN CONFIG WARNING AND OAT LIGHT ILLUMINATIN G. THIRD OCCURANCE. UNSCHEDULED LANDING MADE. (FUEL BURNED OFF TO ACCOMODATE LANDING WEIGHT) THE LT MLG WAS NOT FULLY EX TENDED DUE TO AIR REMAINING IN THE OLEO. THE LG SERVICING WAS REPEATED USING A POWER SERVICING CART, NO FURTHER FAULTS F OUND ON SUBSEQUENT GEAR SWINGS. 2 L 7 2 4T 4 T RT A52EU E8NE6 20081120 EU 2008 11 20 CA080826005 1 20080818 G 3260 SQUAT SWITCH SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE LANDING GEAR OUT OF RIG W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF CHECKS WERE COMPLETED AND CONDITION LEVERS RETARDED, CONFIG WARNING AND OAT LIGHT CAME ON. UNSCHEDUL ED LANDING COMPLETED, RETURNED TO BASE. GEAR SWING COMPLETED, FAULT NOT DUPLICATED. LANDING GEAR HAD BEEN SERVICED PRIOR TO FLIGHT. RE-SERVICED MLG, GEAR SWING COMPLETED, NO FAULT FOUND. SECOND TAKEOFF COMPLETED WITH THE SAME RESULTS AS TH E FIRST. SECOND UNSCHEDULED LANDING MADE. FLIGHT CANCELLED. LG POSITION WARNING SYS INSP INDICATED A PROBLEM WITH THE LT INBD SQUAT SWITCH RIGGING. SWITCH RE-RIGGED LG SWING COMPLETED, NO FURTHER FAULTS FOUND. 2 L 7 2 4T 4 T RT A52EU E8NE6 20081118 2008 11 18 CA080826006 1 20080825 G 5414 85410587 SKIN PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE LT NACELLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A WALKAROUND, THE LT NACELLE SKIN PANEL 85410587 DISPLAYS A SMALL CRACK FROM ONE OF THE UPPER AFT FASTENERS TO THE SKIN EDGE, AND A LARGE 4 INCH+ CRACK RUNNING ALONG THE LENGTH OF THE SKIN PANEL. AS THE SKIN PANEL IS NOTED AS B EING BULGED OVER APPROX .6666 OF ITS LENGTH IT IS PROBABLE THAT THE LONG CRACK IS DUE TO THIS SKIN DEFECT. THE SKIN WILL BE REMOVED AND THIS SDR WILL BE UPDATED. 4 T E20NE 6 C P7NE 20081120 CE 2008 11 20 CA080826007 1 20080826 G 7931 26060154RX INDICATOR CESSNA 208 208 2073702 CE PWA PT6 PT6A114 52043 NE HARTZL HCB3T HCB3TN3 GL OIL PRESSURE DEFECTIVE W O OTHER O OTHER NR NOT REPORTED 1 CA 107 (CAN) OIL PRESSURE NEEDLE INDICATES HIGH OIL PRESSURE WHEN ENGINE IS OPERATING (100- 105 PSI) READS OFF OF ZERO WHEN ENG INE IS NOT OPERATING (10-15 PSI) 106.5 HRS SINCE OVERHAUL. 1 H 7 1 3T 3 T NT A37CE E4EA 6 C P15EA 20081120 CE 2008 11 20 CA080826008 1 20080825 G 3240 6119 CYLINDER PN9122 CESSNA 172 172K 2072430 CE LYC O320 O320E2D 41508 EA MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 4258 (CAN) CYLINDER CASTING COMPOSED OF ALUM STEEL ANCHOR BOLTS MOUNTED IN CASTING CAUSED CORROSSION OF ALUM BOSS BORES WHICH OVER TIME CAUSED THE BOSS CASTING TO CRACK DUE TO THE (SWELLING) ACTION OF THE CORROSION NEXT TO THE STEEL PINS. DUE TO THE NORMAL DIRT CREATED BY BRAKING VISUAL INSP DIFFICULT WITHOUT REMOVAL FOR CLEANING. BOTH ANCHOR BOLT BOSSES CRACKED ON BOTH CALIPERS (4 CRACKS). 1 H 7 1 3O 3 O NT 3A12 E274 20081120 SO 2008 11 20 CA080827001 1 20080827 G 5210 12030027001 SHIM 1454101760 EMB 145 EMB145LR 3260212 SO PAX DOOR CORRODED W O OTHER O OTHER IN INSP/MAINT 1 CA 20785 (CAN) DURING 4Y, 8Y CHECK, BOTH SHIM P/N: 120-30027-001 LOCATED BETWEEN BRACKET P/N:145-25211-601, 145-25211-602 WAS FOU ND HEAVELY CORRODED. DUE TO THE EXPENSION PRODUCE BY THE CORROSION, SOME BRACKET FASTENER WAS BROKEN AND THE ATTACHED FR AME P/N: 145-25299-001 WAS DEFORMED. (TC NR 20080827001) 2 L 7 2 4T RT T00011AT 20081120 NM 2008 11 20 CA080828001 1 20080826 G 7920 AE7077093 FLEX LINE DHAV DHC8 DHC8202 2809007 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE NR 2 ENGINE DAMAGED W E ENGINE SHUTDOWN K FLUID LOSS CR CRUISE 1 CA (CAN) AN ACFT EXPERIENCED AN IN-FLIGHT ENGINE INCIDENT. THE CREW OBSERVED SUDDENLY THE OIL PRESSURE INDICATOR DROPPED T O "0" ASSOCIATED WITH THE ENG NR 2 LOW PRESS CAUTION LIGHT AND MASTER WARNING LIGHT. FLIGHT CREW SHUT DOWN THE ENGINE NR 2 IAW QRH PROCEDURES, ACFT MADE A SATISFACTORY SINGLE ENGINE LANDING. ON GROUND, MAINT PERFORMED EXTERNAL VISUAL INSP A ROUND ENG AND WAS FOUND CONSIDERABLE EVIDENCE OF OIL LEAKAGE, DETAILED INSP TO ENG DISCOVERED THE HOSE ASSY FLEXIBLE RT P/N DSC391-3 WITH ABNORMAL DAMAGE IN THE JOIN ZONE (BETWEEN FLEXIBLE HOSE AND RIGID TUBE). THE RT FLEXIBLE HOSE ASSY WAS REPLACED IAW EMM AND BUILD UP MANUAL, PERFORMED RUN TEST FOR OIL LEAKS AND THE ACFT WAS RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081120 EA 2008 11 20 CA080828002 1 20080818 G 5610 NP13932112 WINDSHIELD CNDAIR CL600 CL6002C10 1390015 EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 10871 (CAN) BEGIN QUOTE "DISC - WINDOW SHATTERED INFLIGHT WHEN FLYING C/A - RAR FOS WINDOW" END QUOTE. 2 L 7 2 4F RT A21EA 20081120 EA 2008 11 20 CA080828003 1 20080820 G 2910 601R752863 HYDRAULIC LINE CNDAIR CL600 CL6002B19 1900309 EA HYDRAULIC SYS CRACKED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKE OFF IN ROUTE, THE MESSAGE HYD NR1 LOW PRESS CAUTION CAME ON EICAS . CREW COMPLIED WITH QRH AND RETURNED . AFT EQUIPMENT WAS SOAKED WITH SKYDROL. A LEAK WAS FOUND ON A RETURN LINE ON THE HYD NR1 MANIFOLD. THE LINE AND ELBO W WERE REPLACED , ACFT BACK TO SERVICE. 2 L 7 2 4F RT A21EA 20081124 EU 2008 11 24 CA080828004 1 20080828 G 2720 137312E401 FITTING BAG JETSTM JETSTM3112 1500220 EU GARRTT TPE331 TPE33110UGR 29069 NE RUDDER WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TAPER PINS PN SP28N14 FOUND SLIGHTLY LOOSE AT SPRING END FITTING ASSY. 2 L 7 2 4T 4 T RT BA15CAA E4WE 20081120 NE 2008 11 20 CA080828005 2 20080827 G 7260 31070371 SPUR GEAR GARRTT TPE331 TPE33110UGR 29069 NE MCAULY 4HFR34 4HFR34C652 NE GEARBOX DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FRONT GEAR CASE ON ENG REMOVED FOR TORQUE RING REPLACEMENT. PITTING FOUND ON SPUR AND HELICAL GEAR ASSY. CONSULTA TION WITH ENGINE OVERHAUL FACILITY IS ON GOING. 4 T E4WE 6 C 3PNE 20081120 CE 2008 11 20 CA080828006 1 20080827 G 7197 WIRE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL OUT OF POSITION W E ENGINE SHUTDOWN F FLT CONT AFFECTED DE DESCENT 1 CA (CAN) WHEN DESCENDING THROUGH FL 180, CREW NOTICED RT ENG WOULD NOT GO BELOW 1600 FT/LBS TORQUE WITH PWR LEVER AT FLIGHT IDLE. CREW CHECKED REMAINING RT INSTRUMENTS AND CONFIRMED IT WAS NOT AN INDICATION ISSUE. RT PROP LEVER WAS OPERATED W ITH TORQUE INCREASE ON FWD MOVEMENT, NORMAL OPERATION. PWR LEVER WAS MOVED FWD TO HIGHER POWER SETTING AND ENG RESPONDE D. STILL, WHEN RETARDING PWR LEVER TO FLIGHT IDLE, TORQUE REMAINED AT 1600 FT/LBS. CREW THEN DETERMINED THAT IT WAS CONS IDERED A RUNAWAY TORQUE SITUATION, DECLARED AN EMERGENCY, THEN SHUTDOWN AND SECURED THE RT ENG. A SAFE LANDING WAS CARRI ED OUT AT THE DESTINATION AIRPORT STOPPING 3/4 DOWN THE RUNWAY. EMERGENCY CREWS MET THE ACFT AND ALL PASSENGERS AND CREW 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 20081120 NE 2008 11 20 CA080829001 2 20080827 G 7421 REM40E SPARK PLUG DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE ENGINE DEFECTIVE W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CA (CAN) ON TROUBLESHOOTING LT MAG DROP (100 RPM), REAR SPARK PLUGS WERE REPLACED WITH NEW SPARK PLUGS OBTAINED FROM RELIAB LE SOURCE WITH CERTIFICATION. ENG WAS GROUND RUN AND MAG CHECK CONDUCTED AND RPM DROP ON LT MAG WAS 150RPM. AFTER INSPEC TING LT MAG AND IGNITION LEADS IT WAS DISCOVERED THAT THE NEW SPARK PLUG IN NR 7 CYL REAR WAS NOT FIRING. THE SPARK PLUG WAS REPLACED AND ENG RUN WITH SATISFACTORY RPM DROP ON LT MAG. 1 H 7 1 3R 3 R RC A806 5E1 20081120 NM 2008 11 20 CA080829002 1 20080805 G 2497 91252ZC7C4001 CONTACTOR BOEING 737 737232 1384475 NM PWA JT8 JT8D17 52049 NE ELECTRICAL SYS FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC TO TAKEOFF 1 CA (CAN) AFTER LIFTOFF, SEVERAL FAILURES OCCURED. ANTISKID INOP, F/O PITOT INOP, NR2 EPR GUAGE INOP, NR2 AFT FUEL PUMP INOP , PINNED ASSOCIATED LIGHTS TO TRANSFER BUS PROBLEMS. LANDING BOTH 115V AND 28V AC TRANSFER BUS INOP. NR2 TRANSFER BUS CO NTACTOR WAS FOUND TO HAVE A VOLTAGE DROP ACROSS THE C1 AND C2 CONTACTS. ALSO HEARD LOOSE PARTS RATTLING WITHIN THE SELF CONTAINED RELAY. RELAY WAS REPLACED. (TC NR 20080829002) 2 L 7 2 4F 4 F RT A16WE E2EA 20081120 EU 2008 11 20 CA080829003 1 20080829 G 2841 SIC6734 MODULE GE SIC505911 AIRBUS A319 A319112 3930323 EU CFMINT CFM56 CFM565B6P 13018 NE FUEL SYSTEM IMPROPER PART W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DISCOVERED DURING THE SHOP`S PRELIMINARY INSP OF A FQIC UNIT, THAT THIS DASH 11 UNIT HAD INSTALLED (2) CPU MODULES (P/N SIC6734, S/N`S 545 AND 575) THAT WOULD NORMALLY BE FOUND ON A SIC5059-04 UNIT. IN OTHER WORDS, A -11 UNIT WAS RECE IVED WITH -04 CPU BOARDS, WHICH IS NOT CONSIDERED A PROPER CONFIGURATION. ACFT WAS UNDER A "N" (USA) REGISTRATION WHEN T HE COMPUTER WAS FITTED TO THE ACFT. 2 L 7 2 4F 4 F RT A28NM 20081120 EA 2008 11 20 CA080829004 2 20080826 G 7314 200F5002R PUMP PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA FUEL SYSTEM LEAKING W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 402 (CAN) THE FUEL WAS FOUND DURING REGULAR INSP LEAKING, FUEL PUMP WAS REPLACED WITH SIMILAR ONE. THE PROBLEM DIDN’T AFFECT THE ENG PERFORMANCE. FUEL TRACE WAS LOCATED BETWEEN BODY STAGE OF THE PUMP. THIS IS THE FIRST PROBLEM OF LEAK WITH THIS TYPE. 1 L 7 2 3O 3 O A20SO E14EA 20081126 EA 2008 11 26 CA080829005 2 20080829 G 7414 6350 MAGNETO GROB 120 G120A 1660208 EU LYC O540 AEIO540D4D5 EA HARTZL HCC3Y HCC3YR GL ENGINE FAILED W D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA 7 7 (CAN) ACFT FLOWN ON LOCAL FLIGHT TRAINING SORTIE WITH INSTRUCTOR AND STUDENT ON BOARD. INSTRUCTOR REPORTED NO NOTICEABLE ENGINE ROUGHNESS OR PWR LOSS DURING FLIGHT. AFTER TAXI TO PARKING POSITION, INSTRUCTOR EGRESSED A/C AND ADVISED STUDEN T TO CARRY-OUT SHUTDOWN CHECKLIST. AS INSTRUCTOR WALKED CLEAR OF ACFT HE NOTICED ENGINE CUT-OUT DURING THE STUDENTS DEAD MAG TEST PRE SHUTDOWN. POST BRIEFING INTERVIEW WITH STUDENT CONFIRMED THAT ENG WOULD NOT CONTINUE TO OPERATE ON RT MAGN ETO ALONE. DISCREPANCY WAS REPORTED TO MAINT AND ENTERED AS SUCH IN JOURNEY LOG. MAINT CONFIRMED DEAD MAG ON ENG RUN-UP. TIMING CHECK IN HANGAR SHOWED NO FAULTS. REMOVAL/DISASSEMBLY OF MAGNETO SHOWED EVIDENCE OF OVERHEATING/ELECTRICAL SHORT 1 L 7 1 3O 3 O RT A49CE 1E4 5 C P25EA 20081120 SO 2008 11 20 CA080829006 1 20080829 G 2720 4004009 TORQUE TUBE 4004638 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2A GL RUDDER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA * (CAN) DUE FOR INSP IAW SB 1105A, AWD 2003-24-07, EXTERNAL RUST FOUND. HOLE DRILLED IN TOP OF TUBE, SEVERE CORROSION FOU ND ON LOWER INTERNAL SURFACES. PART REMOVED FROM SERVICE UNSERVICEABLEV. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081120 CE 2008 11 20 CA080829007 1 20080828 G 3240 420001263 VALVE 99123682 CESSNA 525 525B 2076616 CE RESERVOIR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 361 (CAN) DURING DAILY INSP, THE PRESSURE WAS FOUND LOW ON THE EMERGENCY GEAR/BRAKE RESERVOIR. BOTTLE WAS REMOVED, VALVE AN D FITTINGS WERE LEAK CHECKED WITH SNOOP AND CRACK WAS FOUND IN BOTTOM OF VALVE NEAR GAUGE BOSS. 1 L 7 2 4F RT A1WI 20081120 CE 2008 11 20 CA080902001 1 20080806 G 2710 0510105364 CONTROL CABLE CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL AILERON FRAYED W K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 CA 2197 (CAN) DURING IMPORT INSP, THE LT AFT AILERON CABLE WAS CHAFING ON THE PHANOLIC RUB STRIP ATTACHED TO THE RIB EXTENSION A T WS 71.125 RESULTING IN SEVERE DAMAGE TO THE CABLE. CABLE REPLACED. UNFORTUNATELY THE CABLE HAD BEEN REMOVED BEFORE PIC TURES WERE TAKEN OF THE WORN CABLE. UWN1 AND 3 SIMULATE THE CABLE OVER THE CHAFE STRIP USING THE NEW CABLE, AND UWN2 SH OWS THE DAMAGED OLD CABLE. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 20081120 CE 2008 11 20 CA080902002 1 20080827 G 2432 4076 BATTERY MTSBSI MU2 MU2B60 5780460 CE GARRTT TPE331 TPE33110 29053 NE HARTZL HCB4T HCB4TN5 GL THERMAL RUNAWAY W H DEACTIVATE SYST/CIRCUITS M OVER TEMP IN INSP/MAINT 1 CA 11 (CAN) DURING DAILY INSP OF ACFT, GPU USED. ACFT KEY TURNED (ON) TO CHARGE BATTERIES. APPROX. 2.5 HRS LATER, VENTING OF B ATTERY NOTICED FROM ACFT. SMELL OF BURNING PLASTIC. GPU DISCONNECTED, KEY (OFF). ACFT MOVED OUTSIDE. AIRPORT FIRE DEPT. REMOVED NR 1 BATTERY AND ALLOWED TO COOL. THERMAL RUNAWAY ALONG WITH GPU PRODUCING 30 VOLTS NOT 28.8 V. 1 H 7 2 3T 4 T RT A10SW E4WE 6 C P40EA 20081124 EU 2008 11 24 CA080902003 1 20080826 G 2750 978732000 CONTROL SYSTEM PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL FLAP SYS MALFUNCTIONED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 CA 6586 (CAN) CREW REPORTED FLAPS MOVED ONLY A FEW DEGREES UP AFTER SELECTING "0" FROM TAKEOFF POSITION "15" IN THE INITIAL CLIM B PHASE. "FLAP" CAUTION ILLUMINATED. ACFT RETURNED TO BASE, TROUBLESHOOTING REVEALED POWER DRIVE UNIT AT FAULT. PDU R EPLACED, FUNCTION CHECKS SATISFACTORY. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081120 CE 2008 11 20 CA080902004 1 20080816 G 3233 1FA1004323 BARREL 1143800411 BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL MLG ACTUATOR CRACKED W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED INSP THE LT MLG ACTUATOR (FRISBY) WAS SEEN TO BE LEAKING. THE ACTUATOR WAS REPLACED ON THE ACFT. WHILE IN REPAIR THE BARREL OF THE ATUATOR FAILED NDT FOR A CRACK IN THE THREADED AREA. THIS AREA IS NOT INCLUDED IN SB 3 2-3870 WHICH CALLS FOR NDT OF THE END CAP. 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 20081120 SO 2008 11 20 CA080902005 1 20080831 G 3213 15200 HOUSING ERAM 110P241021 EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL NLG STRUT BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 1888 (CAN) WHEN LANDING AT THE AIRPORT ON A TRAINING FLIGHT THE NLG PARTIALLY RETRACTED TOWARDS THE REAR OF THE ACFT. THE ACF T PITCHED RT AND FULL LT BRAKE WAS USED TO KEEP THE ACFT ON THE RUNWAY. THE ACFT MOMENTARILY LT THE RT SIDE OF THE RUNWA Y AND STRUCK A RUNWAY LIGHT WITH THE RT PROPELLER. THE AFT THEN CAME TO A COMPLETE STOP ON THE RUNWAY. UPON INSP OF THE ACFT IT WAS FOUND THAT THE NLG STRUT HSG WAS BROKEN AT THE RT TRUNNION LINK. THIS ALLOWED THE GEAR LEG TO TURN AND MOVE REARWARD UNDER THE ACFT. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 20081120 EU 2008 11 20 CA080902006 1 20080813 G 6123 AUTOFEATHER SYS AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE NR 2 ENGINE MALFUNCTIONED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA 11 (CAN) THE TAKEOFF WAS ABORTED DUE TO THE NR 2 ENGINE ANALOGUE TORQUE INDICATION BEING STUCK AT 120 PERCENT. THE NR 2 ENG INE AFU WAS REPLACED AND THE ACFT RELEASED FOR SERVICE. 2 H 7 2 4T 4 T RT E20NE 20081120 NE 2008 11 20 CA080902007 2 20080815 G 7250 TURBINE AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE ENGINE DAMAGED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE AT 10000 FEET, THE OIL PRESSURE DROPPED TO THE RED BAND ACCOMPANIED BY A LOW OIL PRESSURE WARNING. T HE ENGINE WAS SHUT DOWN. POST EVENT EXAMINATION OF THE ENG SHOWED DAMAGE IN THE POWER TURBINES. THE ENGINE WILL BE REMOV ED AND SENT FOR REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT E20NE 20081120 NE 2008 11 20 CA080902008 2 20080819 G 7200 ENGINE CESSNA 560 560XL 2076702 CE PWC 545 PW545B NE FLAMED OUT W D RETURN TO BLOCK X ENGINE FLAMEOUT TX TAXI/GRND HDL 1 CA (CAN) WHILE TAXIING FOR TAKEOFF, THE PILOT RETARDED THE POWER LEVER FROM MID POSITION TO IDLE AND THE ENGINE FLAMED OUT. POST EVENT TROUBLESHOOTING SHOWED THAT THE ENGINE WOULD NOT START. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 L 7 2 4F 4 F RT A22CE E00059EN 20081120 EU 2008 11 20 CA080902009 1 20080809 G 6123 AUTOFEATHER SYS AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE RT ENGINE UNKNOWN W E A ENGINE SHUTDOWN UNSCHED LANDING F R FLT CONT AFFECTED PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) DURING CLIMB THE RT ENGINE PROPELLER FEATHERED UNCOMMANDED. PILOT SHUTDOWN THE ENGINE AND RETURNED TO AIRPORT, WHE RE AN UNEVENTFUL SINGLE ENGINE LANDING TOOK PLACE. THE AFU IS SUSPECT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADV ISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT E20NE 20081120 NE 2008 11 20 CA080902010 2 20080805 G 7321 FUEL CONTROL FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE LT ENGINE UNKNOWN W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE THE LT ENGINE EXPERIENCED A SUDDEN TORQUE AND ITT INCREASE. THE CREW RETARDED THE POWER LEVER BUT TH E TORQUE OSCILLATED BETWEEN 0 AND 60 PERCENT WITH ELEVATED ITT. THE ENGINE WAS SHUTDOWN. THE MFCU AND PUMP WERE REMOVED AND SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A817 E20NE 20081126 NE 2008 11 26 CA080902011 2 20080902 G 7414 BL600646201 MAGNETO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE CONTAMINATED W O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA 498 (CAN) MAG WAS RECEIVED FOR 500 HR INSP. END PLAY WAS NOTICED BEFORE DISASSEMBLY (0.003", 0.0015" IS MAX ALLOWABLE). WHEN MAG WAS DISASSEMBLED A COATING OF ENGINE OIL WAS FOUND ON ALL MAG COMPONENTS. THE COIL TAB WAS NOT LEVEL AND WAS PROTRU DING ABOVE MAG HSG PARTING SURFACE. THE COIL TAB SHOULD BE LEVEL + OR - 5 DEGREES, THIS TAB WAS BENT APPROXIMATELY 10 DE GREES UP. TAB HAD CONTACTED THE METAL WASHER ON THE DISTRIBUTOR GEAR AND HAD STARTED TO WEAR THE TAB AND WASHER. THE COI L TAB WAS BENT BACK TO LEVEL, THE OIL SEAL WAS REPLACED AND THE ROTATING MAGNET BRGS WERE INSPECTED AND RESHIMMED TO MFG SPECS. THE MAG WAS THEN RETURNED TO SERVICE. 1 G 7 1 3O 3 O H11NM 1E4 20081120 CE 2008 11 20 CA080903001 1 20080902 G 8011 149NL STARTER CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL ENGINE MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 1222 (CAN) DURING FIRST START OF THE DAY THE PILOT NOTED A GRINDING NOISE WHEN THE STARTER WAS ENGAGED. THE BENDIX WAS SUSPEC TED TO NOT COMPLETELY ENGAGE RING GEAR. STARTER WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 20081120 SO 2008 11 20 CA080903004 1 20080801 G 7920 SA00402SE HOUSING SA00402SE PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL OIL FILTER CRACKED W O OTHER K FLUID LOSS NR NOT REPORTED 1 CA 350 (CAN) RT ENGINE OIL FILTER SEPARATED FROM HSG SHORTLY AFTER TAKEOFF. ENGINE SHUTDOWN IN-FLIGHT. ACFT LANDED SAFELY. ACD REMOTE OIL FILTER HSG THREADED STUD FOUND CRACKED. ONE PORTION OF THREADED STUD REMAINED IN FILTER AND THE OTHER HALF RE MAINED IN THE FILTER HSG. RT REMOTE FILTER HSG THREADED STUD FOUND TO HAVE 0.020" WALL THICKNESS AT THE NON-THREADED PO RTION. LT ENGINE ACD REMOTE FILTER HSG INSPECTED AND THREADED STUD FOUND TO HAVE ONLY 0.017" WALL THICKNESS AT THE NON- THREADED PORTION. SUSPECT THAT BOTH PARTS WERE INCORRECTLY MACHINED. A REPLACEMENT PART FROM MFG HAD 0.060" WALL THICK NESS. 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 20081120 WP 2008 11 20 CA080903005 1 20080813 G 2435 14924HT MOUNT ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE STARTER CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) STARTER MOUNT PAD CRACKED THROUGH BY FRONT MOUNTING HOLES. 1 G 7 1 3O 3 O H11NM 1E4 20081120 EA 2008 11 20 CA080903006 1 20080831 G 3230 NAS16128 O-RING CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B 30069 NE LANDING GEAR DETERIORATED W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 5135 (CAN) DEPARTING, EN ROUTE, NR3 HYDR SYS LO PRESS. LIGHT CAME (ON) AND QTY READ 2 PERCENT. ACFT RETURNED TO BASE. INVESTI GATION SHOWED A (BLOWN) SEAL ON PRIORITY VALVE IN THE LANDING GEAR WHEEL WELL. O-RING FOUND DETERIORATED. REPLACED O-R ING, FUNCTION TESTED AND RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081120 NM 2008 11 20 CA080903007 1 20080208 G 5320 HL10878 COLLAR BOEING 777 777222 1385219 NM FASTENER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 40041 (CAN) FOUND DURING INSP, SEVERAL HI-LOCK COLLARS CRACKED. ALL HI-LOCK COLLARS REPLACED IAW SRM 51-40-02. 2 L 7 2 4F RT T0001SE 20081120 SW 2008 11 20 CA080903008 1 20080828 G 5610 2719442003 WINDSHIELD SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE COCKPIT CRACKED W I CABIN DEPRESSURIZATION O OTHER DE DESCENT 1 CA (CAN) CAPTAINS WINDOW SHATTERED ON DECENT DURING FINAL LEG INTO BASE. SHORTLY AFTER ENTERING CLOUD WITH ICING. W/S HEAT WAS ON LOW. MAINT REPLACED THE WINDSHEILD. NO EXTERNAL DAMAGE COULD BE FOUND ON THE WINDOW WHICH MAY HAVE CAUSED THE FAI LURE. THE TREND OF PREMATURE FAILURES OF THESE WINDOWS FOR THIS OPERATOR CONTINUES AS IS LIKEY CAUSED DUE TO SUBSTANDARD PARTS. 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 20081120 2008 11 20 CA080903009 1 20080903 G 3411 FITTING GARRTT TFE731 TFE73140 29001 NE PITOT/STATIC SYS LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE CARRYING OUT AN AUTO SLAT CHECK, DURING AN A-CHECK, THE STATIC SYS WAS REQUIRED TO SIMULATE 25,000 FT AGL. A N EXCESSIVE LEAK RATE WAS NOTICED ON THE NR1 SIDE AND ISOLATED TO THE FLEX LINE AT THE NR1 ADC STATIC FITTING. UPON FIND ING THE NR1 SYS PROBLEM THE NR2 SYS WAS ALSO CHECKED AND THE SAME LINE ON THE NR2 SIDE WAS ALSO FOUND DEFECTIVE. 4 F E1NM 20081120 SW 2008 11 20 CA080903010 1 20080828 G 5610 2719442003 WINDSHIELD SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE COCKPIT CRACKED W I CABIN DEPRESSURIZATION O OTHER DE DESCENT 1 CA (CAN) ON DESCENT AT APPROX 13000FT THE LT HEATED WINDSHIELD CRACKED. MAINT REPLACED THE WINDSHEILD AND NO PREXISTING DAM AGE WAS FOUND WHICH WOULD HAVE CONTRIBUTED TO THE WINDOW CRACKING. PREMATURE FAILURE OF THESE WINDOWS IS NOT UNCOMMON. 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 20081120 NM 2008 11 20 CA080903011 1 20080903 G 2913 6617303 SHAFT BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU HYDRAULIC PUMP SHEARED W O OTHER J WARNING INDICATION DE DESCENT 1 CA (CAN) DURING DESCENT ENGINE THE NR2 HYDR PUMP CAUTION LIGHT CAME ON ACFT CONTINUE NORMAL LANDING. NR2 HYDR PRESS BEING M AINTAINED BY PTU MAINT. FOUND EDP SHAFT SHEARED. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081120 EA 2008 11 20 CA080903012 1 20080827 G 2810 215640014 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE LT WING LEAKING W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 1744 (CAN) FUEL LEAKING FROM LT WING. FUEL CELLS REMOVED LEAK CHECKED. FUEL CELL NR1 FAILED LEAK CHECK. CELL REINSTALLED, SYS LEAK CHECKED FOUND SERVICEABLE. 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 20081118 EA 2008 11 18 CA080903013 1 20080827 G 2810 215640024 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE LT WING LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1744 (CAN) FUEL LEAKING FROM LT WING. FUEL CELLS REMOVED LEAK CHECKED. FUEL CELL NR 3 FAILED LEAK CHECK. NEW CELL INSTALLED S YSTEM LEAK CHECKED AND FOUND SERVICEABLE. 2 H 7 2 4T 4 T RT A14EA E20NE 20081118 EA 2008 11 18 CA080903014 1 20080827 G 2810 K215T6400212 FUEL CELL CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE LT WING LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) FUEL LEAKING FROM LT WING. FUEL CELLS REMOVED LEAK CHECKED. FUEL CELL NR 4 FAILED LEAK CHECK. NEW CELL INSTALLED S YSTEM LEAK CHECKED AND FOUND SERVICEABLE. 2 H 7 2 4T 4 T RT A14EA E20NE 20081118 WP 2008 11 18 CA080903015 1 20080816 G 2435 GEAR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE STARTER GEN WORN W K NONE O OTHER IN INSP/MAINT 1 CA 277 (CAN) STARTER TEETH FOUND WORN, REPLACED WITH A SERVICEABLE STARTER. 1 G 7 1 3O 3 O H11NM 1E4 20081118 2008 11 18 CA080903016 2 20080903 G 7414 ROTOR SLICK MAGNETO BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 135 (CAN) CUSTOMER RETURNED MAG FOR WARRANTY PURPOSES. MAG ROTOR SHAFT WAS BROKEN BETWEEN THE DRIVE END BEARING AND THE MAGN ET PORTION. THE BREAK STILL ALLOWED THE ROTOR TO SPIN BUT THE ROTOR STARTED TO CONTACT THE HOUSING. THE CUSTOMER CLAIMS THAT THIS IS THE SECOND MAG THEY HAVE SEEN WITH THIS TYPE OF FAILURE. THIS MAG HAD THE NAS1149CO632R WASHER INSTALLED UN DER THE DRIVE GEAR AS PER TCM SB03-7. THE HUB WAS INSPECTED AS PER SLICK SB1-07 AND NO CRACKING WAS FOUND. MAG WAS RETUR NED TO MANUFACTURER FOR FURTHER INVESTIGATION. 20081118 2008 11 18 CA080904001 4 20080902 G 2562 BATTERY ELT LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) ELT WAS FUNCTION TESTED DURING ROUTINE SCHEDULED INSPECTION AND WOULD NOT TRANSMIT. SUBSEQUENT INSPECTION AT AVION ICS SHOP REVEALED LEAKING BATTERY. 20081118 CE 2008 11 18 CA080904002 1 20080826 G 3060 BOOT CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA MCAULY 3D36C B3D36C432 GL PROP DEICE SEPARATED W K NONE O OTHER IN INSP/MAINT 1 CA 523 (CAN) DEICE BOOT RETAINING STRAP SEPARATING FROM NR 3 BLADE, DISCOVERED DURING ANNUAL INSP. (AT ELECTRICAL LEAD AREA). N R 3 DEICE BOOT REPLACED. MCCAULEY SL2006-5 PERFORMED ON ALL 3 BOOTS. 1 H 7 1 3O 3 O RT A4CE E14EA 5 C P58GL 20081219 WP 2008 12 19 CA080904003 1 20080901 G 6310 C1883 SPRAG CLUTCH ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAIN ROTOR DAMAGED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA 3773 1921 (CAN) UNTIL THE OFFICIAL REPORT ARRIVES, THIS IS WHAT IS DETERMINED HAPPENED. DURING TAKEOFF THE PILOT EXPERIENCED A LOU D NOISE AND THEN ACFT YAWED SLIGHTLY. THE ACFT LANDED WITHOUT INCIDENT. THE CLUTCH WAS REPLACED AND ACFT RETURNED TO S ERVICE. DETAILS WILL BE BROUGHT FORWARD ONCE THE CLUTCH IS DISASSEMBLED AND A TEAR DOWN REPORT IS AVAILABLE. 1 G 7 1 3O 3 O H11NM 1E4 20081118 EU 2008 11 18 CA080904004 1 20080903 G 3210 9321921210 BOLT PILATS PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL PIVOT PIN BROKEN W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 322 (CAN) ON TAKE OFF THE PILOTS NOTED AN AIR/GROUND LIGHT ON AND THE GEAR WAS UNABLE TO RETRACT. THE PILOTS RETURNED TO THE AIRPORT AND MX LOOKED AT THE PROBLEM. THE ACFT WAS PLACED UP ON JACKS AND UPON INSPECTION IT WAS NOTED THAT 1 OF THE WE IGHT ON WHEEL SWITCHES WAS MAKING CONTACT WITH THE TARGET. THE WOW SWITCH WHICH WAS MAKING CONTACT WAS INSPECTED CLOSER AND FOUND THAT THE PIVOT PIN HAD TWISTED. THE PIVOT PIN IS HELD IN PLACE WITH A BOLT AND THE BOLT WAS FOUND SHEARED INTO 3 PIECES. THE BOLT HEAD AND NUT WAS HELD IN PLACE BY THE SEALANT THAT PREVENTS WATER ENTERING ALONG THE BOLT. THE PIVOT PIN WAS REMOVED AND THE SHANK OF THE BOLT WAS REMOVED AND THE GEAR WAS VISUALLY INSPECTED AND FOUND SERVICEABLE. A NEW 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081118 EA 2008 11 18 CA080904006 2 20080904 G 7414 COIL BENDIX PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA MAGNETO DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 463 (CAN) MAG WAS RECEIVED FOR 500 HOUR INSPECTION. WHEN DISASSEMBLED THE COIL TAB WAS FOUND TO BE BENT DOWN AND ALMOST TOUC HING THE INSULATION COVERING THE COIL (APPROX. 10 DEGREES). THE CARBON BRUSH HAD WORN THE EXTERNAL EDGE ONLY. THIS TAB I S SUPPOSED TO BE LEVEL + OR - 5 DEGREES. THE TAB WAS BENT BACK UP DURING THE 500 HOUR INSPECTION AND RETURNED TO SERVICE . 1 L 7 2 3O 3 O A20SO E14EA 20081119 2008 11 19 CA080905001 1 20080903 G 3246 9595601143 GROMMET BFGOODRICH MLG WHEEL MISMARKED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) VALVE STEM GROMMET SEAL PN TRRG30 WAS CROSS REFERENCED THEN ORDERED FROM AN ACFT MANUFACTURE SUPPLIER USING THE CR OSS REFERENCE NR OF 959.56.01.143. A BAG OF 10 SEALS WERE RECEIVED AS LABELED 959.56.01.143 ON THE OUTER PACKAGING. A VI SUAL CONFIRMATION AT A LATER DATE DETERMINED THAT THE PACKAGING RECEIVED FROM THE SUPPLIER ACTUALLY CONTAINED VENDOR PN TRRG6 SEALS. THE REMAINDER OF THE STOCK WAS PULLED AND THE SUPPLIER NOTIFIED. 1 SEAL HAD BEEN ISSUED TO A WHEEL REPAIR. THE WHEEL WAS PULLED FROM STOCK AND THE SEAL WAS REPLACED WITH THE CORRECT SEAL. THE TRRG6 SEAL AND THE CORRECT PN TRRG3 0 (959.56.01.143) SEAL WERE NOTED VERY SIMILAR IN SIZE AND APPEARANCE. THE SUPPLIER WAS NOTIFIED, AN INVESTIGATION REVEA 20081119 EA 2008 11 19 CA080905002 1 20080902 G 2497 M275008SP3U00 WIRE HARNESS HAMFLU 761339D CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE ADG BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 19543 (CAN) FOLLOWING THE COMPLETION OF AD CF2008-09, WHILE PERFORMING A FUNCTION CHECK OF THE AIR DRIVEN GENERATOR, 2 OF THE 3 MAIN FEED WIRES WERE FOUND BROKEN AFT OF THE CONNECTOR P1XC. CLOSER INSPECTION OF THE WIRES REVEALED PITTING CORROSI ON AND BREAK IN SEVERAL STRANDS OF THE WIRES. ALL 3 WIRES WERE REPLACED AS AN ASSEMBLY P/N M27500-8SP3U00. 2 L 7 2 4F 4 F RT A21EA E15NE 20081119 NE 2008 11 19 CA080905003 2 20080903 G 7530 658385 CONTROLLER BOEING 727 727260 138408K NM PWA JT8 JT8D17 52049 NE BLEED SYSTEM MALFUNCTIONED W O OTHER E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA (CAN) AT FL300, TOP OF DESCENT, AS THRUST REDUCTION COMMENCED, LARGE BANG WAS EXPERIENCED BY THE FLIGHT CREW WITH FLUCTU ATIONS IN NR 2 ENGINE PARAMETERS. ENGINE WAS IDLED FOR THE REMAINDER OF THE FLIGHT AND SHUT DOWN UPON LANDING. MX PERSO NNEL CARRIED OUT TROUBLESHOOTING AND THE PRESSURE RATIO BLEED CONTROLLER WAS REPLACED. THE PRBC HAS BEEN SENT TO AN OVE RHAUL FACILITY AND AWAITING COMPLETE STRIP REPORT TO VERIFY DEFECTIVE PRBC. 2 L 7 3 4F 4 F RT A3WE E2EA 20081119 SW 2008 11 19 CA080905004 1 20080904 G 2497 WIRE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR 29081 NE MCAULY 4HFR34 4HFR34C652 NE MASTER SWITCH BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) RT AVIONICS AUX MASTER SWITCH WAS SELECTED ON AND SMOKE WAS NOTICED WITHIN 5 SECONDS. SWITCH WAS SELECTED OFF AND SMOKE STOPPED. NO OTHER ABNORMALITIES WERE NOTICED EXCEPT VISUAL BLACK DISCOLORATION ON F/O PHONE JACK OF HEADSET. THIS OCCURRED ON THE GROUND IN BETWEEN FLIGHTS. MX WAS DISPATCHED AND FOUND THAT THE WIRING FROM THE AUX AVIONICS SWITCH WAS BURNT AND ALSO 1 WIRE FROM THE 50AMP CB WAS BURNT. ALL AFFECTED WIRING WAS REPLACED AND ALL SYSTEMS AFFECTED TESTED AND NO FURTHER FAULTS FOUND. SUSPECT WIRE FROM AUX SWITCH CHAFED AGAINST 50AMP CB WIRE. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081119 NE 2008 11 19 CA080905005 2 20080824 G 7250 TURBINE BLADES CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE ENGINE FRACTURED W B A EMER. DESCENT UNSCHED LANDING Y A ENGINE STOPPAGE FLAME/FIRE CR CRUISE 1 CA (CAN) APPROX 45 MINUTES INTO THE FLIGHT PILOT REPORTED ENGINE TROUBLE AND WAS ATTEMPTING AN EMERGENCY LANDING. CONTROL O F THE ACFT WAS LOST DURING LANDING AND THERE WAS A POST CRASH FIRE. EXAMINATION OF THE ENGINE REVEALED FRACTURED COMPRES SOR TURBINE (CT) BLADES. CT BLADES ARE ORIGINAL TO ENGINE MFG. MFG HAS REQUESTED COMPRESSOR TURBINE DISK AND BLADES TO B E RETURNED FOR ANALYSIS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 H 7 1 3T 3 T A37CE E4EA 20081222 NE 2008 12 22 CA080905006 2 20080904 G 7323 B2475 GOVERNOR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE FAILED W O OTHER O OTHER LD LANDING 1 CA 1557 (CAN) PILOT WAS LANDING THE ACFT AND THE RPM DROPPED DUE TO THE GOVERNOR NOT HOLDING THE REQUIRED RPM, GOVERNOR REPLACED . 1 G 7 1 3O 3 O H11NM 1E4 20081119 CE 2008 11 19 CA080905007 1 20080904 G 5220 TAB BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA EMERGENCY EXIT BENT W K NONE O OTHER IN INSP/MAINT 1 CA 1206 1206 (CAN) EMERGENCY EXIT DOOR LATCH APPEARS AS THOUGH THE LATCH TAB HAD BEEN BENT SO THAT IT COULD BE INSTALLED IN THIS MAN NER. IN THIS MODE, THE LATCH CAN ALWAYS (EVEN WHEN PRESSURIZED) BE OPENED AS THE TAB PASSES OVER THE SAFETY PLUNGER. THE TAB SHOULD CONTACT THE PLUNGER WHEN PRESSURIZED AND ENTER THE SLOT FURTHER DOWN THE PLUNGER SHAFT WHEN THE PLUNGER IS P ROTRUDING IN THE UNPRESSURIZED MODE. REMOVING THE LATCH ASSEMBLY AND REPOSITIONING THE STEEL TAB TO CORRECTLY INTERFACE WITH THE PLUNGER HAS FIXED THE PROBLEM AND THE ASSEMBLY IS NOW SERVICEABLE. WE OPINED THAT THIS CONDITION LIKELY EXISTE D SINCE MANUFACTURE. AN INSPECTION OF THE REMAINDER OF OUR FLEET FOR THIS CONDITION REVEALED NO OTHER FAULTS. 1 L 7 2 3T 4 T RT 3A20 E4EA 20081119 SW 2008 11 19 CA080905008 1 20080902 G 2150 20475546 A/C PACK FRCHLD SA227 SA227CC 3377522 SW GARRTT TPE331 TPE33111U 29073 NE MCAULY 4HFR34 4HFR34C652 NE LT DAMAGED W O OTHER B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA (CAN) ON APPROACH, THE PILOT NOTICED SMOKE COMING OUT OF FRESH AIR VENTS AND MOMENTS LATER LT WING OVERHEAT LIGHT CAME O N. ACFT LANDED WITHOUT INCIDENT. MX WENT TO LOOK AND FOUND THAT THE LT COOLING TURBINE HAD A CATASTROPHIC FAILURE. THE L T BLEED SYSTEM WAS MEL`D AND DISABLED. NUMEROUS RUNS WERE COMPLETED WITH NO FURTHER SMOKE COMING INTO CABIN. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081119 SO 2008 11 19 CA080908001 1 20080829 G 7120 6666200 MOUNT PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 7948 (CAN) CRACKS WHERE TUBES ARE WELDED TO NOSE STRUT. CHAFING WHERE AERO DUCT HOSE TOUCHED MOUNT. 1 L 7 1 3O 3 O 2A13 E274 20081119 EA 2008 11 19 CA080908002 2 20080827 G 7414 K3975 COIL SLICK CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MAGNETO OPEN W D RETURN TO BLOCK R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 1895 (CAN) PILOTS NOTED A DEAD LT MAGNETO WHEN PERFORMING PRE FLIGHT RUNUP. MAGNETO WAS REMOVED AND DISASSEMBLED AND FOUND TH AT THE COIL SECONDARY WINDING WAS OPEN CIRCUIT (SHOULD BE BETWEEN 1500-20,000) - MANGETO WAS REPLACED. 1 H 7 1 3O 3 O NT 3A12 1E10 20081119 CE 2008 11 19 CA080908003 1 20080902 G 2810 1183810021 FLOAT VALVE BEECH 200 B200 1152922 CE PWA PT6 PT642A NE FUEL CELL DISLODGED W O OTHER O OTHER NR NOT REPORTED 1 CA 757 (CAN) ATTACH PIN MIGRATED OFF ALLOWING FLOAT TO BECOME DISLODGED FROM FLOAT VALVE PIN 118-381002-1. ATTACH PIN MIGRATED TO ORIGINAL POSITION AFTER FLOAT BECAME DISLODGED. THE FLOAT WAS LOCATED AT THE RT FUEL FILLER. THE NEW VALVE WAS DATED IN 2000 WHILE THE DEFECTIVE VALVE WAS DATED JULY, 2005. THE NEW VALVE WAS OF A DIFFERENT CONSTRUCTION IN THE ATTACH PIN AREA LESS CONDUCIVE TO ALLOWING DISLODGING OF THE FLOAT. 1 L 7 2 4T 4 T A24CE E4EA 20081119 NM 2008 11 19 CA080908004 1 20080902 G 2722 2334003001 ACTUATOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE RUDDER BYPASSING W O OTHER F G FLT CONT AFFECTED MULTIPLE FAILURE NR NOT REPORTED 1 CA 41801 41801 (CAN) FLT CREW REPORTED RUDDER TRIM INDICATOR SHOWS 40% RT DEFLECTION TO CENTRE BALL ON HSI. MX REPLACED THE RUDDER TRIM ACTUATOR AND CHECKED SYSTEM SERVICEABLE. ON THE NEXT FLIGHT THE CREW REPORTED NO APPRECIABLE CHANGE AND THAT IT APPEARE D THEY WERE CROSS CONTROLLING THE ACFT WITH THE TRIMS. MX DISCOVERED THAT BOTH THE NR 1 AND 2 SYSTEM RUDDER ACTUATORS W ERE INTERNALLY BYPASSING FLUID. MX WAS ABLE TO MOVE RUDDER BY HAND EVEN WITH FULL HYDRAULIC SYSTEM PRESSURE. BOTH RUDDER ACTUATORS PN 233400-3001, SN 0575 (NR 1), SN 0580 (NR 2), IPC 27-20-00 FIG 5, ITEM 618 WERE REPLACED AND OPS, FUNCTIONA L AND LEAK CHECKS COMPLETED. RUDDER CABLES TENSIONED. ACFT TEST FLOWN SATISFACTORILY AND RETURNED TO SERVICE. NOTE:MX TA 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081119 EU 2008 11 19 CA080908005 1 20080908 G 5753 Z4243300014 SPRING ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA FLAP SPRING BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLAP SPRING LOCK WAS DISCOVERED CRACKED DURING SCHEDULED MX. SPRING BROKE COMPLETELY DURING REMOVAL. 1 L 7 1 3O 3 O 0 A76EU 1E10 20081119 SW 2008 11 19 CA080908006 1 20080507 G 6320 430040003 TRANSMISSION BELL 430 430 1182150 SW MAIN ROTOR DAMAGED W B A EMER. DESCENT UNSCHED LANDING C J F.O.D. WARNING INDICATION CR CRUISE 1 CA (CAN) WHILE IN CRUISE FROM AN OIL RIG , THE PILOT HEARD A LOUD BANG AND THE ACFT YAWED LT AND RT AND WAS FOLLOWED BY A L OUD RUMBLING SOUND. THE COCKPIT INDICATION SHOWED THAT THE ACFT HAS A TRANSMISSION CHIP AND A CHIP SUMP CAUTION. THE PIL OT DESCENDED DOWN TO APPROXIMATELY 400 FEET READY TO PREPARE FOR DITCHING. AFTER APPROXIMATELY 1 1/2 TO 2 MINUTES, THE R UMBLING STOPPED AND THE ACFT NOISE WENT BACK TO NORMAL. THE PILOT PROCEEDED TO LAND WITHOUT EVENT AND SHUT DOWN THE HELI COPTER. AFTER INSPECTION, NUMEROUS CHIPS AND FLAKES OF METAL ON THE SUMP PUMP CHIP DETECTOR, COLLECTOR GEAR DETECTOR AND THE MAGNETIC DRAIN PLUG. SOME METAL FOUND ON THE LT INPUT QUILL CHIP DETECTOR AND IN THE OIL FILTER. TRANSMISSION WILL 1 G 7 2 3U RT H9SW 20081119 SO 2008 11 19 CA080908007 2 20080828 G 8530 07502385AWL RISER CESSNA 185 A185E 2072818 CE CONT O520 IO520F 17032 SO NR 5 CYLINDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 680 (CAN) DURING 100 HOUR INSPECTION AME FOUND RT EXHAUST STACK CRACKED AT NR 5 CYLINDER, PART WAS REPLACED WITH PART NR 075 0161-31. 1 H 7 1 3O 3 O 3A24 E5CE 20081119 EA 2008 11 19 CA080908008 2 20080906 G 8530 AEL85099 CYLINDER CESSNA 172 172N 2072434 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL NR 1 SEPARATED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 2577 2577 (CAN) ACFT WAS CLIMBING OUT ON A TRAINING FLIGHT. SHORTLY AFTER HEARD A LOUD BANG AND RPM DROPPED TO APPROX 1200. TURNED BACK AND LANDED SAFELY FOUND THE NR1 CYL HEAD SEPARATED FROM THE BARREL WITH APPROX 1 INCH OF BARREL EXPOSED PAST THE C YLINDER FINS. NR1 INTAKE LIFTER WAS DAMAGED AS WELL AS THE ENG CRANKCASE, ENG REMOVED FOR OVERHAUL. ENG WAS OPERATING ON AN ON-CONDITION PROGRAM. (@2567 HOURS, TBO IS 2000) FIRST FAILURE OF THIS TYPE. CYL WAS NOT AFFECTED BY AD 2006-12-07 A ND WAS IN FACT NOTED AS AN ACCEPTABLE REPLACEMENT CYLINDER FOR THE PN MENTIONED IN THE AD. ENGINE WAS INSTALLED IN THIS AIRFRAME. REPLACED ORIGINAL ENGINE. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20081124 CE 2008 11 24 CA080908009 1 20080908 G 5511 12326212 SPAR CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION AN AME FOUND THAT THE RT AND LT REAR SPAR WAS HEAVILY CORRODED (LEVEL 3) AND CRACKED UNDER THE OTBD HINGE BRACKET. 1 H 7 1 3O 3 O A4CE E5CE 20081124 CE 2008 11 24 CA080908010 1 20080808 G 5312 071111229 BULKHEAD CESSNA 185 A185F 2072821 CE CONT O550 IO550D 17042 SO FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING NON-ROUTINE MX REPAIRS AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER RT CORNER AT REAR FLOAT FITTING. CUSTOMER WAS NOTIFIED. 1 H 7 1 3O 3 O 3A24 E3SO 20081124 CE 2008 11 24 CA080909001 1 20080907 G 2435 COOLING FAN TRW BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA STARTER GEN BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 1581 662 (CAN) WHILE PERFORMING AN INSPECTION, THE ENGINEER PULLED THE STARTER-GENERATOR AND NOTICED THE COOLING FAN BROKEN. UPON FURTHER INVESTIGATION, THE ENGINEER NOTICED THAT 1 OF THE BROKEN FAN BLADES WAS PROVIDING A GROUND PATH INTERNALLY BETW EEN THE GENERATOR AND THE CASE. 1 L 7 2 3T 4 T A14CE E4EA 20081124 2008 11 24 CA080909003 2 20080909 G 7414 M3611 CAM SLICK MAGNETO WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MAG WAS INSTALLED ON AN OVERHAULED ENGINE APPROX. 1 YEAR AGO, CUSTOMER HAS YET TO INFORM US AS TO HOURS ON UNIT. T HE MAG WAS DISASSEMBLED FOR INSPECTION AND THE CAM THAT OPENS THE CONTACT POINTS WAS FOUND TO BE EXCESSIVELY WORN. THIS IS COVERED BY SLICK BULLETIN SB2-08. THE CAM WAS WORN TO THE EXTENT THAT IT WAS BARELY OPENING THE POINTS. THE MAG WAS R ETURNED TO UNISON/SLICK FOR INSPECTION. 20081124 2008 11 24 CA080909004 2 20080909 G 7414 M3611 CAM SLICK LOBES WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) (2ND MAG) MAG WAS INSTALLED ON AN OVERHAULED ENGINE APPROX. 1 YEAR AGO. CUSTOMER HAS YET TO INFORM US AS TO HOURS ON UNIT. THE MAG WAS DISASSEMBLED FOR INSPECTION AND THE CAM THAT OPENS THE POINTS WAS FOUND TO BE EXCESSIVELY WORN. THI S IS COVERED BY SLICK BULLETIN SB2-08. THE CAM WAS WORN TO THE EXTENT THAT IT WAS BARELY OPENING THE POINTS. THE MAG WAS RETURNED TO UNISON/SLICK FOR INSPECTION. 20081124 EA 2008 11 24 CA080909005 1 20080819 G 2750 1104SD1201 SHAFT CNDAIR CL600 CL6002B19 1900309 EA TE FLAPS BROKEN W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 20680 (CAN) AFTER LANDING AND ON RETRACTION OF THE FLAPS, THE CREW RECEIVED A FLAP FAIL CAUTION MSG. PIREP: FLAP FAIL CAUTION . WHEN FLAP SELECTOR MOVED FROM 45 DEG TO 8 DEG, FLAPS STOPPED AT THE 22 DEG POSITION. MX EXAMINED THE FLAPS AT THE GAT E AND DETERMINED THAT THERE WAS EVIDENCE OF OIL CANNING ON THE TOP SURFACE SKIN OF THE RT INBD FLAP. THE ACFT WAS TAKEN OUT OF SERVICE AND PROCESSED TO THE HANGAR FOR FURTHER INVESTIGATION. LOCATED A BROKEN FLEX SHAFT TIP AT THE INBD SIDE OF THE OTBD ACTUATOR FOR THE INBD FLAP. ALL DAMAGED PARTS INCLUDING THE FLAP SURFACE WERE REPLACED. 2 L 7 2 4F RT A21EA 20081124 CE 2008 11 24 CA080910001 1 20080903 G 7160 155212914 INTAKE DUCT CESSNA 337 337F 2075725 CE CONT O360 IO360C 17025 SO MCAULY 2AF34C D2AF34C306 GL CRACKED W O OTHER E VIBRATION/BUFFET AP APPROACH 1 CA 2712 (CAN) DURING A ROUTINE PATROL FLIGHT THE PILOT EXPERIENCED A VIBRATION IN THE AREA OF THE REAR ENGINE. HE ELECTED TO RET URN TO THE AIRPORT AND MADE AN UNSCHEDULED LANDING WITHOUT INCIDENT. UPON INSPECTION BY THE MX CREW, IT WAS DISCOVERED T HAT THE FWD EDGE OF THE INNER & OUTER SECTIONS OF THE AIR COOLING DUCT HAD PARTIALLY SEPARATED FROM THE NOSE CAP. THIS A LLOWED ROM AIR TO FLOW BETWEEN THE INNER & OUTER SECTIONS AND CAUSED THE INNER DUCT TO VIBRATE AND SUBSEQUENTLY CRACK & BREAK. 1 H 7 2 3O 3 O A6CE E1CE 5 C P5EA 20081124 WP 2008 11 24 CA080910002 1 20080818 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE INOPERATIVE W O OTHER O OTHER NR NOT REPORTED 1 CA 345 (CAN) THE STARTER WAS NOT CRANKING OVER ENGINE, STARTER REPLACED. 1 G 7 1 3O 3 O H11NM 1E4 20081124 SO 2008 11 24 CA080910003 2 20080715 G 8520 COTTER PIN CONT CONT O200 O200A 17020 SO CONNECTING ROD MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NO COTTER PINS IN ANY OF THE 8 CON-ROD BOLTS DISCOVERED UPON DISMANTLE FOR PROPELLER STRIKE INSPECTION. 3 O E252 20081119 NE 2008 11 19 CA080910004 2 20080909 G 7530 SWITCH EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE NR 2 FAULTY W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING THE DEPARTURE, THE FLIGHT HAD A NR2 BLEED VALVE FAILURE INDICATION WHICH WAS RESET. AND THEN FAILED AGAIN, FOLLOWED WITHIN 2 MINUTES WITH A BLEED NR1 FAILURE. QRH PROCEEDURES WERE FOLLOWED AND THE FLIGHT RETURNED TO LAND. THE F LIGHT WAS NOT OVERWEIGHT FOR LANDING AND THERE WAS NO EMERGENCY DECLARED. BLEED NR1 FAULT CODE HAS BEEN TROUBLESHOT. B LEED O/P SWITCH NR2 REPLACED IAW AMM. TORQUE MOTOR LINES TO VALVE CHECKED OK. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081119 SW 2008 11 19 CA080910005 1 20080709 G 6510 407340340103 DISC PACK BELL 407 407 1182206 SW ALLSN 250C 250C47B GL T/R DRIVESHAFT CRACKED W O OTHER Z SIGNIFICANT FAILURE REPORT IN INSP/MAINT 1 CA (CAN) FOUND (3) DISCS CRACKED AND ALL DISCS CORRODED ON THE FWD NR 1 POSITION. 1 G 7 1 3U 3 U O H2SW E1GL 20081119 NE 2008 11 19 CA080910006 2 20080820 G 7314 C8187B PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYSTEM MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 993 (CAN) FUEL PUMP ELECTRICALLY MALFUNCTIONING, REPLACED FUEL PUMP. 1 G 7 1 3O 3 O H11NM 1E4 20081126 SO 2008 11 26 CA080911001 1 20080908 G 8120 89682002 SHROUD PIPER PA46 PA46350P 7104602 SO LYC O540 TIO540AE2A 41532 EA AIR PUMP LOOSE W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA 2626 (CAN) THE LWR AIRPUMP COOLING SHROUD ASSY, ALTHOUGH NOT LOOSE TO THE TOUCH, WAS ABLE TO ROTATE WITH A LIGHT TO MODERATE PUSH. THIS ROTATION ALLOWED THE AIR INLET DUCT AND CLAMP TO CONTACT THE LINKAGE ON THE TURBO CONTROLLER. THE SHROUD RO TATION OCCURRED DURING FULL POWER, THIS TRAPPED THE LINKAGE ON THE TURBO CONTROLLER IN THE CLIMB POWER POSITION. THE LO WER AIRPUMP COOLING SHROUD ASSEMBLY(P/N 89682-002), ROD(P/N 89682-008), HOSE (P/N 89684-002), AND CLAMP(P/N 5544-896) WE RE REPLACED WITH NEW. THE NEW SHROUD AND CLAMP WERE POSITIONED TO PROVIDE MAXIMUM CLEARANCE TO THE TURBO CONTROLLER. THE NEW SHROUD AND ROD FIT IS MORE SECURE TO PREVENT FURTHER ROTATION. AN ENGINE GROUND RUN WAS CARRIED OUT SATISFACTORILY 1 L 7 1 3O 3 O RT A25SO E14EA 20081119 EA 2008 11 19 CA080911002 1 20080909 G 5610 601R330339 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT CRACKED W K NONE Z SIGNIFICANT FAILURE REPORT DE DESCENT 1 CA 18238 18238 (CAN) ON DESCENT THE LT WINDSHIELD CRACKED AT FL370 AND THE LT WINDSCREEN HEAT CAUTION CAME ON. AN EMERGENCY WAS DECLARE D, BUT THE A/C LANDED WITHOUT INCIDENT. THIS WINDSHIELD HAD OVER 18,000 HRS AND WAS WELL ABOVE THE AVERAGE FOR NORMAL FA ILURE RATES. 2 L 7 2 4F 4 F RT A21EA E15NE 20081119 NM 2008 11 19 CA080911003 1 20080905 G 2782 1U1110 ACTUATOR BOEING 727 727225 1384077 NM PWA JT8 JT8D9A 52048 NE KRUEGER FLAP FAILED W A UNSCHED LANDING K FLUID LOSS CL CLIMB 1 CA (CAN) DURING CLIMB THROUGH APPROX 2,000 FT NR1 ENGINE LOW HYDR PRESSURE LIGHT ILLUMINATED, SYS `A` HYDRAULIC OIL AND PRE SSURE LOSS. ACFT RETURNED TO DEPARTURE. NR5 KRUGER FLAP ACTUATOR FOUND FAILED AND ATTACH BRACKET DAMAGED. REPLACED ACTUA TOR AND TESTED IAW AMM 29-11-00 AND 27-81-22. KRUEGER FLAP ATTACH BRACKET REPAIRED IAW SRM 51-10-2. ACFT RETURNED TO SER VICE. 2 L 7 3 4F 4 F A3WE E2EA 20081119 EU 2008 11 19 CA080911004 1 20080908 G 3220 5322012165 BARREL NUT PILATS 532001203 PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NLG CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) NLG OLEO WAS STICKING AND NOT EXTENDING WHEN GEAR UP WAS SELECTED. WITH THE TIRE FALLING SHORT OF THE BACK OF THE WHEEL WELL IT MAKE CONTACT WITH THE NOSE GEAR DOOR RODS. BOTH LT AND RT RODS BUSTED OFF LEAVING THE DOORS FLOATING. THE NOSE WHEEL BEING SHORT CONTACTED AND RUBBED THE GEAR UP BUMPER AND LIGHTLY TOUCHED THE RT GEARDOOR LEAVING A BLACK RUBBE R MARK. UPON INSP, IT WAS FOUND THAT THE BARREL NUT STARTED TO CORRODE INTERNALLY UNDER THE PHENOLIC BUSHING FORCING THE PHENOLIC BUSHING AGAINST THE OLEO. BARREL NUT AND SEALS REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081126 NM 2008 11 26 CA080911005 1 20080911 G 7920 443330 O-RING BOEING 727 727247 138408F NM PWA JT8 JT8D15 52051 NE GEARBOX OIL LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) WHILE CLIMBING OUT, NOTICED ENG NR 1 OIL QUANTITY INDICATOR SLOWLY DECREASING, QUANTITY WAS 1 GALLON AT TOP OF CL IMB. AT MID POINT, QUANTITY DECREASED TOWARD ZERO. ENGINE SHUTDOWN DRILL AND CHECK LIST COMPLETED. ENGINE WINDMILLING SUPPLEMENT COMPLETED PRIOR TO DESCENT. ALL OTHER ENGINE INDICATIONS NORMAL PRIOR TO SHUTDOWN. OPENED COWLING ON NR 1 E NG, CHECKED FOR OIL LEAK, NOTHING OBVIOUS, ADDED 12 QUARTS OF OIL IAW MM 12-13-001-2. NR 1 ENG RUN AT IDLE TO LEAK CHE CK, SIGNIFICANT OIL LEAK FROM GEARBOX TO OIL COOLER TUBE. FOUND OIL LINE HAD TENSION ON IT WHEN REMOVING TUBE. SEAL SP LIT AND REAR PIECE MISSING. PROCURED SEAL P/N 443330 (REV.A). CPN 0043234 INSTALLED SEAL AND REPOSITIONED TUBE, REMOVE 2 L 7 3 4F 4 F A3WE E2EA 20081119 NE 2008 11 19 CA080911006 2 20080904 G 7200 JT8D9A ENGINE BOEING 727 727227 1384078 NM PWA JT8 JT8D9A 52048 NE NR 2 FAILED W A E UNSCHED LANDING ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 54469 1313 (CAN) AFTER T/O AND CLIMB OUT, NR2 ENGINE LOST OIL QTY AND OIL TEMP ROSE RAPIDLY INTO RED INDICATION. INFLIGHT SHUTDOWN COMPLIED WITH AND ACFT RETURNED TO DEPARTURE. NR2 ENGINE REPLACED IAW AMM AND KFL TASK CARDS, ACFT RETURNED TO SERVICE. ENGINE TO BE EVALUATED IN ENGINE SHOP FOR CAUSE. 2 L 7 3 4F 4 F A3WE E2EA 20081119 NE 2008 11 19 CA080912001 2 20080825 G 7321 ECU PWA PW121 PW121 52124 NE NR 1 ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN J X WARNING INDICATION ENGINE FLAMEOUT CR CRUISE 1 CA (CAN) DURING FLIGHT, THE PILOT NOTICED FLUCTUATION OF NR1 ENGINE PARAMETERS. WHILE ATTEMPTING TO ADJUST PROPELLER SPEED, ENGINE FLAMED OUT. AN ATTEMPT TO RESTART ENGINE IN-FLIGHT WAS NOT SUCCESSFUL. DURING GROUND INSP, ALL ENGINE PARAMETERS FLUCTUATED WITH ECU "ON" AND ALL PARAMETERS STABLIZED WITH ECU "OFF". THE ECU WAS REPLACED. 4 T E20NE 20081119 NE 2008 11 19 CA080912002 2 20080826 G 7320 HMU BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE LT ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA (CAN) ACFT EXPERIENCED LOSS OF POWER TO FLIGHT IDLE (FI) ON LT ENGINE DURING FLIGHT WHICH LEAD TO A COMMANDED ENGINE IN- FLIGHT SHUTDOWN + RESTART WITH INABILITY TO GO ABOVE FI. FLIGHT WAS DIVERTED WHERE THE A/C LANDED WITH THE LT ENGINE AT FI POWER. EXTENSIVE TROUBLESHOOTING LED TO HMU REPLACEMENT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4F 4 F RT A16SW E25EA 20081119 EA 2008 11 19 CA080912003 2 20080902 G 8530 SL11625 PLUG CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 1300 (CAN) THE PISTON PIN PLUGS IN TWO CYLINDERS ON THE ENGINE WORE UNUSUALLY AND CAUSED ALUMINUM METAL CONTAMINATION THROUGH OUT THE ENGINE. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 20081119 CE 2008 11 19 CA080912004 1 20080912 G 5753 3516505030 HINGE BRACKET BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL TE FLAP DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE REPLACEMENT OF THE REAR SPAR LT BRACKET, THE LT OTBD FLAP WAS REMOVED FOR ACCESS AND FOUND THE INBD HIN GE OTBD BRACKET WITH DAMAGE CAUSED BY THE ROLLER BEARING FLANGE APROX 0.025 DEEP. DECIDED TO PERFORM DVI OF ALL REMAINI NG FLAP ROLLER ASSY AND REMOVE THE RT OTBD FLAP. FOUND THE SAME DAMAGE ON THE RT OTBD FLAP INBD HINGE OTBD BRACKET. INVE STIGATION SHOWED THAT THE BEARINGS AND FLAPS WERE INSTALLED CORRECTLY. BRACKETS ARE BEING REPLACED. 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 20081120 CE 2008 11 20 CA080912005 1 20080911 G 2497 10936102247 WIRE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL LT NACELLE BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) LT ENGINE FAILED TO ROTATE ON START UP. MAINT DISCOVERED LT STARTER GEN WIRE FEED THRU ASSY (CONSISTS OF 3 PARALLE L HEAVY GUAGE WIRES) TERMINAL ENDS BURNED OFF AT START CONTROL PANEL TERMINAL. NEW WIRE FEED THRU ASSY ON ORDER. START C ONTROL PANEL ON ORDER. WILL CARRY OUT A FLEET WIDE INSP OF LT AND RT NACELLES FOR WIRE FEED THRU TERMINAL ENDS FOR CONDI TION. 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 20081120 SW 2008 11 20 CA080912006 1 20080908 G 7920 991930811 TUBE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 29073 NE MCAULY 4HFR34 4HFR34C652 NE OIL SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING THE PREFLIGHT WALKAROUND, THE FLIGHT CREW NOTICED OIL DRIPPING FROM THE RT ENGINE. MX WAS DISPATCHED TO THE LOCATION WHERE THE STAINLESS STEEL TUBE ASSY FROM THE ENGINE PROP GOVERNOR TO THE NEGATIVE TORQUE SENSING (NTS)MANIFOLD WAS FOUND LEAKING. DURING REMOVAL, 1 FLARED END OF THE TUBE WAS FOUND CRACKED 3/4 OF THE WAY AROUND THE CIRCUMFERENCE O F THE TUBE. TOSL TIME ON THE TUBE COULD NOT BE DETERMINED. THIS SAME PN TUBE HAS BEEN FOUND CRACKED PREVIOUSLY ON OTHER ACFT. THE CRACK WAS LIKELY DUE TO IMPROPER ALIGNMENT OF THE TUBE ASSY DURING INSTALLATION ON THE PROP GOVERNOR. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 20081120 2008 11 20 CA080912007 1 20080817 G 5210 ATTACH FITTING BRAERO 1371008C409 GARRTT TPE331 TPE33110UGR 29069 NE PAX DOOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SEVERE CORROSION NOTED AT MAIN CABIN DOOR ATTACH FITTINGS. CORROSION ALSO NOTED UNDER SEVERAL DOOR SEAL CLIPS. DOO R DEEMED BEYOND ECOMONICAL REPAIR AND REPLACED WITH SERVICEABLE UNIT. 4 T E4WE 20081120 2008 11 20 CA080912008 1 20080912 G 5210 FITTING BRAERO 1371008C409 GARRTT TPE331 TPE33110UGR 29069 NE PAX DOOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS DOOR WAS INSTALLED AS A REPLACEMENT DUE TO SEVERE CORROSION FOUND ON ORIGINAL DOOR. REPLACEMENT DOOR INSPECTE D AND CORROSION DISCOVERED UNDER SEVERAL DOOR INFLATION SEAL CLIPS. CLIPS REMOVED AND CORROSION REMOVED AND SURFACES TRE ATED. CLIPS REINSTALLED. 4 T E4WE 20081126 GL 2008 11 26 CA080915006 1 20080826 G 3260 WARNING LIGHT BOMBDR BD700 BD7001A10 1390006 GL HNYWL AS907 AS90711A 33908 WP MLG ILLUMINATED W A UNSCHED LANDING J WARNING INDICATION AP APPROACH 1 CA (CAN) DURING FLT, "GEAR SYS FAIL" CAUTION MESSAGE POSTED. CREW VERIFIED ACTIVE FAULTS IN CAIMS TO FIND LGECU CHANNEL B FAILED. CREW PROCEEDED TO PREPARE FOR LANDING FOLLOWING ACFT FLT MANUAL PROCEDURE FOR GEAR SYS FAIL MESSAGE. MANUAL LAND ING GEAR EXTENSION PROCEDURE WAS CARRIED OUT IAW AFM. ON APPROACH, ACFT DESCENDED TO AN ALTITUDE OF 500 FEET WHEN ENHAN CED GROUND PROXIMITY WARNING SYSTEM "TOO LOW GEAR" UN-MUTABLE AURAL WARNING SOUNDED, WHICH PROMPTED PILOT TO GO AROUND A ND VERIFY THE REASON FOR THIS WARNING. AFTER VERIFICATION CREW MADE A SECOND ATTEMPT ON APPROACH AND THE "TOO LOW GEAR" AURAL WARNING SOUNDED AGAIN DISREGARDED BY CREW TO FINALIZE LANDING. ON TOUCH DOWN, THE PILOT NOTICED THAT THE LT ENGIN 2 L 7 2 4F 4 F RT T00003NY E00010LA 20081120 WP 2008 11 20 CA080915007 1 20080816 G 2822 D7431 PUMP ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE FUEL SYSTEM FAULTY W K NONE O OTHER NR NOT REPORTED 1 CA 267 (CAN) THE AUX FUEL PUMP LIGHT WOULD NOT EXTINGUISH, AUX PUMP REPLACED. 1 G 7 1 3O 3 O H11NM 1E4 20081120 EU 2008 11 20 CA080916001 1 20080911 G 3233 72MEF20151 SWIVEL FITTING SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R389 R3894123F25 NE RT MLG SHEARED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKE-OFF, DURING GEAR RETRACTION, THE RT MLG DOWNLOCK ACTUATOR SWIVEL FITTING LOCATED ON THE DRAG BRAC, FAIL ED. THIS CAUSED A SUBSTANTIAL LOSS OF FLUID. AN EMERGENCY GEAR EXTENSION WAS CARRIED OUT AND THE ACFT RETURNED TO BASE WITH NO FURTHER PROBLEMS. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P30NE 20081120 CE 2008 11 20 CA080916002 1 20080806 G 2752 ROLL PIN CESSNA C1450046RX CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL TE FLAP SHEARED W O OTHER F P FLT CONT AFFECTED NO WARNING INDICATION IN INSP/MAINT 1 CA 2998 (CAN) DURING ROUTINE INSPECTION, STANDBY FLAP SYSTEM OPS DISCOVERED INOPERATIVE (MOTOR TURNING - NO FLAP MOVEMENT). UPON FURTHER INVESTIGATION, ROLL PIN SECURING STANDBY DRIVE TO WARM GEAR WAS FOUND TO BE SHEARED RENDERING STAND BY FLAP OPS U/S. SUSPECT FAILURE WAS DUE TO AGE OF PART. RECOMMEND TESTING OF STAND BY FLAP SYSTEM PER A/C MAN. N.M. AT EACH INSPEC TION. IN THIS INSTANCE PRIMARY FLAP OPS WERE NOT AFFECTED. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 20081120 EU 2008 11 20 CA080916004 1 20080915 G 4940 CONTROL BOX AMD FALC50 FALCON50MYST 2730106 EU GARRTT TFE731 TFE73131C 01518 NE COCKPIT DEFECTIVE W K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 12101 (CAN) PILOTS HAVE BEEN REPORTING INTERMITTENT SULPHUR SMELL IN THE ACFT. WHILE TROUBLESHOOTING, THE MECHANIC NOTICED THA T THE APU DOOR WAS OPEN AND APU MASTER AS OFF. WHEN THE APU SWITCH WAS CYCLED TO CLOSE THE DOOR, SPARKS STARTED TO APPEA R NEXT TO START SWITCH IN THE COCKPIT. UPON REMOVAL OF THE CONTROL BOX, IT WAS NOTICED THAT THE RUBBER SLEEVE AROUND THE START SWITCH WAS MELTED AND THERE WERE SIGNS OF BURNING ON THE WIRES COMING OUT OF THE SWITCH. 2 L 7 3 4F 4 F A46EU E6WE 20081126 2008 11 26 CA080916005 4 20080830 G 3457 GNS530430W GPS MALFUNCTIONED W O OTHER G H MULTIPLE FAILURE ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) GNS530W AND GNS430W SIMULTANEOUSLY LOOSE SATELLITE RECEPTION. SATELLITES ARE REAQUIRED BETWEEN 2 AND 20 MINUTES LA TER. EXTENSIVE TROUBLESHOOTING FOUND NO FAULT WITH THE INSTALLATION. MFG PRODUCT SUPPORT INDICATED THAT SIMILAR REPORTS HAVE BEEN RECEIVED FROM OPERTORS IN ALASKA AND THE ANOMOLY APPEARS AT AROUND THE LATITUDE OF FAIRBANKS. THERE IS A PROBL EM WITH THE GNS SOFTWARE AND THE ALASKA WAAS GROUND STATION. THE WAAS ENGINE IN THE GNS NAVIGATOR MUST BE SHUT OFF IN TH AT AUXILLARY MENU SETUP PAGE TO PREVENT SATELLITE LOSS IN NORTHERN LATTITUDES. THIS INFORMATION IS NOT READILLY AVAILABL E TO OPERATORS AND OWNERS. 20081222 CE 2008 12 22 CA080916006 1 20080912 G 5551 04320049 ATTACH BRACKET CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CARRIED OUT SEB 03-6 ON VERTICAL TAIL ATTACH BRKT AND STAB SPAR. SPAR WAS NOT CRACKED BUT THE STEEL ATTACH BRKT WA S CRACKED AROUND A RIVET HOLE FOR THE PREVIOUSLY INSTALLED NUT PLATES. AD PREVIOUSLY ALLOWED REMOVAL OF NUT PLATES. THI S OPERATOR HAS SEEN AT LEAST TWO OTHER FAILURES OF THIS PART. A/C TT IS ~22,950 HOURS OPERATING IN AN FTU. REPLACED PAR T WITH A USED, INSPECTED SERVICEABLE PART DUE TO NO PARTS SUPPORT FROM MFG. NOTE: NO PICTURE, NOT ABLE TO TAKE A PICTU RE FROM THE INSIDE OF THE BRACKET. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P9045 20081120 CE 2008 11 20 CA080916007 1 20080728 G 2436 C6110040101 VOLT REGULATOR CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO ELECTRICAL SYS SHORTED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) ACFT WAS IN CRUISE FLIGHT WHEN THE PILOT NOTICED THE ELECTRICAL SYSTEM WAS DRAINING THE BATTERY. THE ACFT LANDED A ND WSA INVESTIGATED BY MX. IT WAS FOUND THAT THE BATTERY WAS DISCHARGED AND THE ELECTROLYTE HAD BOILED FROM THE BATTERY. FURTHER INVESTIGATION REVEALED THE VOLTAGE REGULATOR WAS AT FAULT, ALLOWING THE ALTERNATOR TO OVERVOLT THE BATTERY AND DESTROY IT. THE BATTERY COMPARTMENT WAS CLEANED AND A NEW BATTERY WAS INSTALLED, A NEW VOLTAGE REGULATOR WAS INSTALLED A ND A NEW ALTERNATOR WAS ALSO INSTALLED AS A PRECAUTIONARY MEASURE. THE ACFT WAS GROUND RUN & ELECTRICAL SYSTEM CHECKED S ERVICEABLE. 1 H 7 1 3O 3 O A4CE E5CE 20081120 2008 11 20 CA080916008 1 20080913 G 3040 MOTOR GARRTT TPE331 TPE3312201A WP WINDSHIELD MALFUNCTIONED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) SKYVAN EN ROUTE WITH 2 CREW ,1 PASSENGER ON BOARD ADVISED ARCTIC RADIO THEY HAD SMOKE IN COCKPIT, CREW REQUESTED E MERGENCY VEHICLES, ACFT LANDED SAFELY, CREW AND PASSENGER WERE CHECKED AT LOCAL NURSING STATION AND RELEASED. FURTHER IN VESTIGATING PROBLEM, IT WAS FOUND THAT THE WINDSHIELD WIPER MOTOR HAD BURNT OUT. WIPER MOTOR WAS REPLACED WITH A SERVICE ABLE UNIT , FUNCTION CHECKED AND RELEASED BACK TO SERVICE. TOTAL TIME ON WIPER MOTOR UNKNOWN. 4 T E3WE 20081120 2008 11 20 CA080917001 1 20080826 G 2820 3014884 TUBE PWA PT6T PT6T3B 52045 NE FUEL SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 3219 (CAN) FUEL FOUND LEAKING ONTO ENGINE DECK FROM AT BRAZE ON BOTTOM "B" NUT FITTING ON TUBE. TUBE LOCATED ON FORWARD FACE OF ENGINE ACCESSORY GEARBOX. ACFT WAS GROUNDED UNTIL PART WAS REPLACED. 4 U E22EA 20081120 EA 2008 11 20 CA080917002 1 20080911 G 3213 8A04000021 SUPPORT 8000FLOATS DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA MLG AXLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEEL ASSEMBLIES AND BRAKES REMOVED FOR INSPECTION AND REBUILD. IT WAS DISCOVERED THAT THE AXLE SUPPORT BODIES ON BOTH MAIN GEAR ASSEMBLIES HAD CRACKS AND REQUIRED REPLACEMENT. THIS WAS FOUND ON A 200 HR. INSPECTION. 1 H 7 1 3R 4 T A815 E4EA 20081126 NM 2008 11 26 CA080917003 1 20080916 G 2133 3964401 SHUTOFF VALVE BOEING 727 727247 138408F NM PWA JT8 JT8D15A 52051 NE A/C PACK FAILED W J A DUMP FUEL UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMBOUT, SEPT 16 2008, PRESSURIZATION FAILED TO OPERATE NORMALLY. WHEN CLIMBING THROUGH 23,000 FT, CABIN A LTITUDE EXCEEDED 10000 FT. FUEL DUMP CARRIED OUT IN ORDER FOR ACFT TO RETURN TO DEPARTURE. CABIN PRESSURIZATION LEAK CH ECK CARRIED OUT, NO FAULTS. PRESSURIZATION CONTROLLER AND PRESSURIZATION CONTROL PANEL REPLACED. GROUND PRESSURIZATION C HECKS CARRIED OUT WITH NO FAULTS DETECTED. ON SEPT 17, 2008, ACFT WAS DEPARTED. AS THE ACFT CLIMBED THROUGH 25000 FT, CA BIN PRESSURIZATION FAILED TO OPERATE NORMALLY WITH MINIMAL CONTROL. ACFT RETURNED TO DEPARTURE FOR FURTHER TROUBLESHOOTI NG. TROUBLESHOOTING REVEALED NO PROBLEMS WITH THE PRESSURIZATION SYS BUT HAS REVEALED THAT THE RT PACK FLOW CONTROL AND 2 L 7 3 4F 4 F A3WE E2EA 20081120 CE 2008 11 20 CA080917004 1 20080907 G 2750 C3010010211 COUPLING CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL TE FLAP FAILED W O OTHER F FLT CONT AFFECTED IN INSP/MAINT 1 CA (CAN) FLAP COUPLING FAILED DURING NORMAL LANDING PROCEDURES. UPON FAILING, THE PART BROKE INTO 2 PIECES, DISCONNECTING T HE FLAP MOTOR FROM THE ACTUATOR ASSEMBLY. THIS RESULTED IN THE FLAPS STOPPING WHILE PARTIALLY EXTENDED. THE FLAPS WERE L EFT PARTIALLY EXTENDED FOR LANDING. THE CREW ELECTED NOT TO USE THE STANDBY FLAP MOTOR TO AVOID THE POTENTIAL FOR FURTHE R DAMAGE TO THE FLAP ACTUATOR ASSEMBLY. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 20081124 NE 2008 11 24 CA080917005 2 20080910 G 7200 90623 ENGINE BOEING 777 777* UTILUSE NM GE GE90 GE90115B 30048 NE NR 1 VIBRATION W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 889 (CAN) IN CRUISE, THE FLIGHT EXPERIENCED A NR 1 ENGINE VIBRATION. THE ENGINE CONTINUED OPERATING NORMALLY BUT WITH VIBRA TION. THE FLIGHT DIVERTED TO FAIRBANKS, ALASKA. AN ENGINE HAS BEEN SCHEDULED AND TOOLS, PARTS AND MANPOWER ARE CURRENT LY BEING SHIPPED TO ALASKA. ACFT IS OUT OF SERVICE. \ETQ INVESTIGATION NR 2917 INITIATED. 2 L 7 2 4F 4 F RT T00001SE E00049EN 20081120 2008 11 20 CA080917006 4 20080902 G 6122 GOVERNOR CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE PROPELLER OUT OF ADJUST W E C ENGINE SHUTDOWN ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) DURING TAXI ROLL IN PREPARATION FOR TAKE-OFF, THE COMPRESSOR TURBINE SPEED (NG) DROPPED BY APPROX 2%. PILOT ADVANC ED POWER LEVER AND ITT ROSE TO 740 DEG C WITH NO INCREASE IN NG. THE LOW OIL PRESSURE ANNUNCIATED AND PILOT OBSERVED ZER O OIL PRESSURE. THE PROPELLER FEATHERED UNCOMMANDED AND THE PILOT SHUT THE ENGINE DOWN. THE PROP GOVERNOR WAS ADJUSTED A ND THE ACFT RETURNED TO SERVICE. 1 H 7 1 3T 3 T A37CE E4EA 20081120 EA 2008 11 20 CA080917007 2 20080823 G 7200 ENGINE DHAV DHC8 DHC8* NM PWC 150 PW150A EA MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB PASSING THRU FL15, THE LOW OIL PRESSURE WARNING WAS ACTIVATED AND THE COCKPIT INDICATION WAS SEEN FAL LING. THE CREW SHUT THE ENGINE DOWN AND THE ACFT RETURNED TO THE POINT OF DEPARTURE. NO TROUBLESHOOTING WAS DONE BY TH E OPERATOR AND THE ENGINE WAS REPLACED. THIS WAS THE 2ND EVENT IN 7 DAYS. THE FIRST EVENT LED TO THE REPLACEMENT OF THE OIL PUMPS. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A13NM E00062EN 20081120 CE 2008 11 20 CA080917008 1 20080808 G 5312 071111210 BULKHEAD CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION AN AME FOUND CRACKS IN LOWER LT AND RT CORNER AT REAR FRONT ATTACH, WHICH HAD BEEN PR EVIOUSLY REPAIRED AND HAS CRACKED AGAIN. 1 H 7 1 3O 3 O 3A24 E5CE 20081120 NE 2008 11 20 CA080917009 2 20080904 G 7200 ENGINE LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE SHUTDOWN W D RETURN TO BLOCK R X PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT TX TAXI/GRND HDL 1 CA (CAN) PILOT REPORTED THAT DURING TAXI THE ENGINE EXPERIENCED UNCOMMANDED ROLL BACK AND SHUTDOWN. TROUBLESHOOTING INDICA TED THAT THE ENGINE MAY HAVE ALSO EXPERIENCED AN OVERTEMP CONDITION AND WAS REMOVED FROM SERVICE FOR INSPECTION. P&WC W ILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 L 7 2 4F 4 F RT A10CE E35NE 20081120 CE 2008 11 20 CA080917010 1 20080808 G 5312 071111229 BULKHEAD CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER LT CORNER AT REAR FLOAT FITTING. CUSTOMER WAS NOTIFIED. 1 H 7 1 3O 3 O 3A24 E5CE 20081120 CE 2008 11 20 CA080917011 1 20080808 G 5312 071111229 BULKHEAD CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A NON-ROUTINE INSPECTION AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER LT AND RT CORNERS AT REAR FLOAT FITTING S. 1 H 7 1 3O 3 O 3A24 E5CE 20081120 NE 2008 11 20 CA080917012 2 20080907 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MALFUNCTIONED W B A EMER. DESCENT UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) DURING A 5 MIN. RE-POSITIONING FLIGHT, THE ENGINE LOST POWER AND AN EMERGENCY LANDING WAS ATTEMPTED. THE ENGINE W ILL BE RETURNED TO P&WC FOR INVESTIGATION. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE EST ABLISHED. 1 H 7 1 3T 3 T A37CE E4EA 20081120 NE 2008 11 20 CA080917013 2 20080908 G 7200 ENGINE BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE RIGHT MALFUNCTIONED W E ENGINE SHUTDOWN K J B FLUID LOSS WARNING INDICATION SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) A YAW OF THE ACFT CAUGHT THE ATTENTION OF THE PILOT AND A QUICK REVIEW OF THE COCKPIT GAGES REVEALED THAT THE RT E NGINE TORQUE WAS FLUCTUATING BETWEEN APPROXIMATELY 20% TO 40% WITH THE TEMPERATURE INDICATION RISING TO APPROXIMATELY 82 0 DEGREES. THE PILOT VISUALLY CONFIRMED THAT LARGE AND SMALL SPARKS WERE EMANATING FROM THE ENGINE EXHAUST. THE PILOT PROCEEDED TO SHUT THE ENGINE DOWN BEFORE MAKING AN UNEVENTFUL SINGLE ENGINE LANDING. GROUND INSPECTION FOUND FUEL LEAKI NG FROM THE COWLING. THE ENGINE WILL BE REMOVED. 2 L 7 2 4T 4 T RT A24CE E4EA 20081120 NE 2008 11 20 CA080917014 2 20080901 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE DEFECTIVE W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, THE ENGINE LOST OIL PRESSURE. AN AIR TURNBACK WAS INITIATED AND THE ACFT LANDED AT THE POINT OF DE PARTURE WITH THE ENGINE RUNNING. POST FLIGHT INSPECTION FOUND OIL LEAKING AROUND THE ENGINE INTAKE AREA. THE ENGINE WI LL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIR. P&WC WILL CLOSELY MONITOR THE INVESTIGATION RESULTS AND ISSUE UPDATES TO TC. 1 H 7 1 3T 3 T A37CE E4EA 20081120 NE 2008 11 20 CA080917015 2 20080905 G 7250 TURBINE BLADES AEROSP ATR42 ATR42* 8680900 EU PWA PW121 PW121 52124 NE ENGINE DISTRESSED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, THE PILOT OBSERVED AN ENGINE OIL PRESSURE DROP TO THE RED ZONE. HE ELECTED TO SHUTDOWN AND SECURE THE ENGINE BEFORE MAKING A SINGLE ENGINE LANDING AT DESTINATION. GROUND INSPECTION FOUND LOW PRESSURE TURBINE BLADE DIS TRESS. 2 H 7 2 4T 4 T RT A53EU E20NE 20081120 NE 2008 11 20 CA080917016 2 20080908 G 7200 ENGINE BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE MALFUNCTIONED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING A RE-POSITIONING FLIGHT, THE PILOT NOTED LOW AND FLUCTUATING OIL PRESSURE. THE ENGINE WAS SHUT DOWN AND SE CURED AND A SINGLE ENGINE LANDING WAS PERFORMED. GROUND INSPECTION FOUND CONTAMINATION IN THE OIL FILTER AND FILTER BOW L. THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIR. P&WC WILL CONTINUE INVESTIGATING THE EVENT A ND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4F 4 F RT A16SW E25EA 20081126 SW 2008 11 26 CA080917017 1 20080911 G 2597 CONNECTOR ARTEX BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ELT MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) INSTALLATION OF NEW 406 ELT ON INSTALLATION OF CONNECTOR FOR REMOTE SWITCH THE ELT WAS SET OFF. THE ELT WAS NOT FU LLY INSTALLED SO THE ELT ACTIVATION WAS NOT NOTICED. HAVE SINCE SPOKE WITH THE MFG AND FOUND THAT THIS IS A COMMON PROBL EM WITH THE INSTALLATION OF THE CONNECTOR NOT BEING INSERTED EXACTLY STRAIGHT, CAUSING THE PINS TO GROUND AND ACTIVATE E LT. POSSIBLE PROBLEM EVERY TIME YOU INSTALL OR REMOVE THIS ELT. THERE IS NO OFF SWITCH TO PREVENT THIS REOCCURRENCE JUST POSSIBILITY OF MONITORING 121.5 FOR ACCIDENTAL ACTIVATION AND RESET OF ELT IF IT GOES OFF. 1 G 7 1 3U 3 U H2SW E4CE 20081124 2008 11 24 CA080917018 4 20080911 G 8300 GEARBOX PWC PW610 PW610FA 52267 NE ENGINE DAMAGED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) IN CRUISE, THE PILOT NOTICED A LOW OIL PRESSURE WARNING AND ELECTED TO SHUT THE ENGINE DOWN. WHILE DESCENDING THE CREW DECIDED TO RESTART THE ENGINE AND COMPLETE THE FLIGHT WITH THE LOW OIL PRESSURE INDICATION. ON THE GROUND, THE PI LOT COULD NOT RESTART THE ENGINE. INITIAL TROUBLESHOOTING MAY HAVE INDICATED DAMAGE TO THE ACCESSORY GEARBOX AND THE EN GINE HAS BEEN REPLACED. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 4 F E00074EN 20081120 NE 2008 11 20 CA080917019 2 20080913 G 7220 INLET GUIDE VANE AMD FALC50 FALCON2000 2730170 NM PWC PW308 PW308C 52182 NE NR 1 ENGINE MALFUNCTIONED W K NONE Y J ENGINE STOPPAGE WARNING INDICATION AP APPROACH 1 CA (CAN) IT IS REPORTED THAT 10 MINUTES BEFORE LANDING, ENGINE NR 1 SHUTDOWN BY ITSELF FOLLOWED BY A "NO DISPATCH" MSG ON T HE COCKPIT DISPLAY. TROUBLESHOOTING SHOWED THAT THE IGV POSITION DID NOT MATCH THE REQUESTED VALUE. THE VIGV WAS REPLA CED AND THE FAULT CLEARED. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 L 7 2 4F 4 F RT A50NM E00065EN 20081120 EU 2008 11 20 CA080918002 1 20080912 G 5753 S5751202320 A/C PACK SNIAS S57512007004 AEROSP ATR72 ATR72212 8680945 EU TE FLAP BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING C-CHECK INSPECTION (1C, 2C, 4C, CPCP2, A8), WHILE PERFORMING A DVI INSPECTION ON THE L INBD FLAP, THE INSPE CTION REVEALED THAT THE FWD PICK-UP FITTING INBD LOG AT RIB 5 WAS BROKEN IN HALF. THE FITTING LOT NR IS P4110. THE BROKE N OFF PIECE WAS FOUND IN THE FLAP FAIRINGS. 2 H 7 2 4T RT A53EU 20081120 CE 2008 11 20 CA080918003 1 20080917 G 2434 00317 ALTERNATOR CESSNA 337 337G 2075730 CE CONT O360 IO360G 17025 SO MCAULY 2AF34C D2AF34C306 GL FWD ENGINE DAMAGED W K NONE J WARNING INDICATION CR CRUISE 1 CA 577 (CAN) THE ACFT, A CESSNA 337G WAS ON A RETURN FLIGHT TO MAIN BASE WHEN THE PILOT NOTICED A INDICATION OF A FAILED FRONT ENGINE ALTERNATOR. THE ACFT LANDED WITHOUT INCIDENT AND MX INVESTIGATED THE PROBLEM. DURING REMOVAL OF THE FRONT ALTER NATOR, IT WAS DISCOVERED THAT THE DRIVE SHAFT HAD BEEN SHEARED OFF. THE DRIVE GEAR IN THE ENGINE WAS INSPECTED AND FOUN D SERVICEABLE. A SERVICEABLE ALTERNATOR WAS INSTALLED AND THE ACFT RELEASED FOR SERVICE. THE U/S ALTERNATOR HAD A TOTAL OF 577 HRS SINCE O/H. WE HAVE HAD REPORTS OF SIMILAR PROBLEMS WITH THESE ALTERNATORS IN THE PAST. 1 H 7 2 3O 3 O A6CE E1CE 5 C P5EA 20081125 SW 2008 11 25 CA080918004 1 20080914 G 2913 HOUSING VICKERS SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HYDRAULIC PUMP SEPARATED W D RETURN TO BLOCK K FLUID LOSS TX TAXI/GRND HDL 1 CA 3 (CAN) DURING ENGINE START THE NR 2 ENGINE HYDRAULIC PUMP BEGAN TO LEAK SIGNIFICANTLY CAUSING A LOSS OF SYSTEM PRESSURE A ND FLUID. UPON INSPECTION BY MX THE PUMP WHICH WAS JUST INSTALLED 2.5 HRS PRIOR WAS FOUND TO HAVE SEPARATED AT THE PUMP HOUSING HALVES AND THE O RING SEAL WAS EXTRUDED. THE INTERNAL WRENCHING BOLTS WHICH HOLD THE HALVES TOGETHER APPEARED T O HAVE PULLED OUT OF THE THREADS ALLOWING THE PUMP HALVES TO SEPARATE TO THE POINT OF PUMP FAILURE. THE COMPANY WILL SE ND THE PUMP FOR WARRANTY REPAIR. 2 L 7 2 4T 4 T RT A8SW E4WE 20081125 SW 2008 11 25 CA080918005 1 20080914 G 7603 2543161 SPRING BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL THROTTLE RETURN BROKEN W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA 101 (CAN) DURING TAKEOFF THE LOW ROTOR HORN SOUNDED. THE PILOT ABORTED THE TAKEOFF, SHUT DOWN THE ENGINE AND CALLED MX. WH EN THE ENGINE COWL WAS OPENED THE FCU THROTTLE RETURN SPRING WAS FOUND IN THE BOTTOM OF THE ENGINE PAN. 1 G 7 1 3U 3 U H2SW E4CE 20081125 CE 2008 11 25 CA080918006 1 20080909 G 2731 12601491 ACTUATOR CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO ELEVATOR TRIM CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION A AME FOUND HEAVY CORROSION (LEVEL 3) ON THE ACTUATOR. HE R&R THE PART. 1 H 7 1 3O 3 O A4CE E5CE 20081126 2008 11 26 CA080919001 4 20080917 G 2562 MOUNT BRACKET PIPER PA28 PA28180 7102808 SO LYC O360 O360A4A 41514 EA ELT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE EXISTING ELT MOUNTING BRACKET WAS INSPECTED PRIOR TO REPLACEMENT OF THE VHF ELT WITH A 406 MHZ ELT. UPON REMO VING THE NARCO ELT10 MOUNTING TRAY, IT WAS DISCOVERED THAT ACFT ELT MOUNTING BRACKET WAS CRACKED AT EACH MOUNTING TRAY S CREW HOLE LOCATION. THE NARCO ELT TRAY WAS FOUND TO BE MOUNTED TO THE BRACKET USING ACCEPTABLE AN SCREWS AND SELF-CAPTI VE NUTS. THERE WERE NO WASHERS USED BETWEEN THE SELF-CAPTIVE NUTS AND THE BOTTOM SIDE OF THE ACFT MOUNTING BRACKET. AS PART OF THE 406MHZ ELT UPGRADE AND MODIFICATION REPORT, THE OLD BRACKET WAS REMOVED, A NEW BRACKET WAS FABRICATED AND I NSTALLED. 1 L 7 1 3O 3 O 2A13 E286 20081125 WP 2008 11 25 CA080919002 1 20080916 G 2421 ALX8521RS ALTERNATOR ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 128 (CAN) ALTERNATOR HAS STRIPPED HOUSING 1 G 7 1 3O 3 O H11NM E295 20081125 WP 2008 11 25 CA080919003 1 20080910 G 6310 C0512 ACTUATOR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE CLUTCH DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 712 (CAN) CLUTCH ACTUATOR FOUND U/S DURING INSPECTION, SERVICEABLE ACTUATOR INSTALLED. 1 G 7 1 3O 3 O H11NM 1E4 20081126 EA 2008 11 26 CA080919004 2 20080916 G 7261 NUT 766859C BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU OIL PUMP LOOSE W E ENGINE SHUTDOWN J WARNING INDICATION DE DESCENT 1 CA (CAN) DURING DESCENT NR 2 ENGINE INDICATED LOW OIL PRESSURE. ENGINE WAS SHUTDOWN AND UNEVENFUL LANDING WAS CARRIED OUT. MX BORESCOPE INSP FOUND THE OIL PUMP DRIVE SHAFT NUT BECAME LOOSE. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081125 WP 2008 11 25 CA080919005 1 20080908 G 6310 C0183 CLUTCH ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAIN ROTOR DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA 1920 (CAN) LOUD BANGING NOISE IN ACFT. CLUTCH REMOVED FOR TEARDOWN INSPECTION, SERVICEABLE CLUTCH INSTALLED. 1 G 7 1 3O 3 O H11NM 1E4 20081125 WP 2008 11 25 CA080919006 1 20080826 G 6310 C0512 CLUTCH ACTUATOR ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAIN ROTOR DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA 1747 (CAN) DRIVE BELTS SLIPPING, SERVICEABLE ACTUATOR INSTALLED. 1 G 7 1 3O 3 O H11NM 1E4 20081126 EU 2008 11 26 CA080919007 1 20080917 G 2110 139312 SUPERCHARGER BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU CABIN PRESSURE INOPERATIVE W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 3982 (CAN) WHILE IN CRUISE FLIGHT, ENROUTE, CREW NOTICED A STRANGE ODOR COMING FROM THE CABIN. CREWMAN ONBOARD WENT TO LOOK IN THE CABIN AND NOTICED TEMPERATURE IN THE CABIN WAS VERY HOT AND THERE WAS LIGHT HAZE OR SMOKE IN SAFELY. MX INSPECTE D THE ACFT AND FOUND THAT BOTH CABIN SUPERCHARGER INTAKE FILTERS WERE NEARLY COMPLETELY CLOGGED. FURTHER INSP REVEALED SOME SCORING ON THE INSIDE WALLS AND ROTORS OF THE CABIN SUPERCHARGERS. INLET FILTERS WERE CLEANED AND BOTH LT AND RT C ABIN SUPERCHARGERS REPLACED. GROUND RUNS AND FLIGHT TEST WERE COMPLETED, THE ACFT WAS FOUND SERVICEABLE AND RELEASED FO R SERVICE. 2 L 7 2 3T 4 T A24EU A196 6 C P899 20081125 CE 2008 11 25 CA080919008 1 20080825 G 8011 149NL STARTER CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 98 (CAN) STARTER FAILS TO ENGAGE, SERVICEABLE STARTER INSTALLED. 1 H 7 1 3O 3 O NT 3A12 1E10 20081125 2008 11 25 CA080919009 2 20080918 G 7414 ROTOR MAGNETO BROKEN W O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA (CAN) CUSTOMER COMPLAINED ABOUT DEAD MAG. TIME IN SERVICE IS UNKNOWN. MAG WAS OPENED AND INSPECTED. THE ROTOR GEAR VAN E SHOWED INDICATIONS OF RUBBING ON THE HALL EFFECT SENSOR AND HAD CONTACTED THE SENSOR. THIS STOPPED THE ROTOR GEAR WHI CH IS INSTALLED IN THE SLOT AND BROKE THE ROTOR SHAFT AT THE BASE OF THE SLOT. THIS INFORMATION IS BEING SENT TO SLICK FOR EXAMINATION. 20081125 EA 2008 11 25 CA080919010 2 20080908 G 7414 10600646201 MAGNETO ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ENGINE MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA 331 (CAN) REMOVED DUE TO ERRATIC ENGINE RPM. 1 G 7 1 3O 3 O H11NM E295 20081126 NE 2008 11 26 CA080919011 2 20080918 G 7414 BEARING BL6006163 ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO EXCESS PLAY W O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA 458 (CAN) MAG WAS RECEIVED FOR 500 HR INSP. BEFORE MAG WAS DISASSEMBLED THE BEARINGS WERE CHECKED BY SPINNING THE ROTATING MAGNET. THE END PLAY WAS MEASURED AT 0.004", MFG LIMIT IS 0.0015" MAX. THE BEARINGS WERE RESHIMMED, THE REST OF THE 50 0 HR INSP WAS CARRIED OUT AND THE MAG WAS RETURNED TO SERVICE. 1 G 7 1 3O 3 O H11NM 1E4 20081201 CE 2008 12 1 CA080921001 1 20080919 G 3220 AN17621A BOLT CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO HARTZL HCJ3Y PHCJ3YF1 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ROUTINE MX AND ENGINE CHANGE, NLG WAS REMOVED FOR ACCESS TO REPLACE LOOSE RIVETS IN ENG NACELLE AREA. INSP OF NLG ATTACH BOLTS SHOWED SIGNS OF CRACKS JUST UNDER THE HEAD OF THE BOLT. LPI INSP OF THE BOLT SHANKS CONFIRMED CRAC KS. BOLTS WERE BOTH REPLACED. AFTT 12484.6 HOURS, A REVIEW OF ACFT HISTORY FOUND NO RECORD OF THESE BOLTS HAVING BEEN REPLACED. A REVIEW OF THE MFG SERIES CAP, CONTINUED AIRWORTHINESS PROGRAM, SHOWED NO INITIAL INSP OR REPLACEMENT REQUIR EMENTS. 1 H 7 1 3O 3 O A4CE E5CE 5 C P36EA 20081201 NM 2008 12 1 CA080922001 1 20080917 G 3244 DR0231T TIRE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU NR 3 FAILED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 255 (CAN) PASSENGER REPORTED NR 3 TIRE BURST DURING TAKE OFF. CREW EXTENDED GEAR AND FA CONFIRMED TIRE WAS BLOWN. ACFT RET URNED TO BASE FOR LANDING. OPERATOR REPORTED TIRE WAS ON SECOND RETREAD WITH 238 CYCLES 255 HOURS. AXLE WAS NOT DAMAGED AND IS NOT BEING REPLACED. THE RUNWAY WAS SWEPT AFTER THE INCIDENT AND NO DEBRIS OTHER THAN BITS OF TIRE WERE FOUND. I NSPECTION COMPLETED AND TIRE REPLACED, 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081201 EA 2008 12 1 CA080922002 2 20080822 G 7414 IMPULSE COUPLING CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL MAGNETO MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA CGGPE (CAN) ENGINE WAS OVERHAULED AND STORED UNTIL AUGUST 2008. DURING INSTALLATION ON AUG. 22, 2008, IT WAS NOTICED THAT THE RE WAS NOT :CLICKING: OF THE MAGNETO IMPULSE COUPLINGS AS THE PROPELLER WAS ROTATED A NR OF TIMES. BOTH MAGNETO (UNISON 4381`S, S/N 07031616 AND 07031617) WERE REMOVED FROM THE ENG AND INSPECTED, THE PAWLS ON THE IMPULSE COUPLINGS ON BOTH M AGNETOS WOULD NOT ENGAGE PROPERLY OR AT ALL. IT APPEARED THAT THE IMPULSE COUPLINGS HAD BEEN ASSEMBLED INCORRECTLY. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 20081125 NE 2008 11 25 CA080922003 2 20080915 G 7313 301114521 ADAPTER CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL REAR FUEL NOZZLE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 400 (CAN) DURING LEAK TEST AFTER CLEANING LEAKAGE NOTED AT THE HEAD FUEL NOZZLE ADAPTER. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 20081128 SW 2008 11 28 CA080922005 1 20080909 G 2910 2781032273 LINE FRCHLD SA227 SA227CC 3377522 SW GARRTT TPE331 TPE33111U 29073 NE MCAULY 4HFR34 4HFR34C652 NE HYDRAULIC SYS CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) PILOT REPORTED HYD FLUID LEAKING IN LT WW. SMALL PINHOLE WAS FOUND IN LINE. LINE REPLACED AND ACFT RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081128 EA 2008 11 28 CA080922006 1 20080915 G 2150 78279015 ACM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE LEFT ODOR W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA 13244 13244 (CAN) ON FINAL APPROACH, SMOKE SMELL IN FLIGHT DECK. AT THE SAME TIME UNABLE TO CONTROL LT PACK IN AUTO OR MANUAL MODE. ALSO DISPLAY FAN OR AIR IN FAN MAKING GRINDING NOISE. BOTH FANS PLACED IN FLT ALTN MODE AND SMOKE STOPPED. 2 L 7 2 4F 4 F RT A21EA E15NE 20081128 EA 2008 11 28 CA080923002 1 20080922 G 5610 6003303021 WINDOW CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B 30069 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 4341 (CAN) WHILE IN CRUISE, CREW EXPERIENCED THE FAILURE OF THE COCKPIT LT SIDE WINDOW OUTER MAIN PLY. A CRACK SPANNED FROM THE LOWER FWD FRAME, TO THE FWD SECTION OF THE UPPER FRAME OF THE WINDSHIELD. THE ACFT HAD DEPARTED AND WAS ENROUTE SOU THBOUND WHEN THE FAILURE OCCURRED. 2 L 7 2 4F 4 F RT A21EA E15NE 20081128 EU 2008 11 28 CA080923003 1 20080912 G 5397 52802800 WIRE BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL CARGO HOOK BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ACFT OVERHAULED, CAME BACK TO BASE LAST WEEK OF AUGUST, NO SLING LOAD OPERATION HAS BEEN LOGGED. ELECTRICAL WIRE FOUND BROKEN AT HOOK CONNECTOR LOCATION. ELECTRICAL WIRE ATTACHED WITH CLAMPS (4X) ALONG THE SWING CABLE SUPPORT. THE ROUTING SEEMED TO BE TOO TIGHT. 1 G 7 2 3U 3 U H3EU E4CE 20081125 SW 2008 11 25 CA080923004 1 20080922 G 7933 OIL SYSTEM BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL ENGINE OVERTEMP W A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 CA (CAN) ENGINE OIL TEMPERATURE INCREASED TO 100 DEG. C. 1 G 7 1 3U 3 U H2SW E4CE 20081128 NE 2008 11 28 CA080923006 2 20080806 G 7250 3022312 TURBINE WHEEL BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE ENGINE DISINTEGRATED W C ABORTED TAKEOFF X J ENGINE FLAMEOUT WARNING INDICATION TO TAKEOFF 1 CA 10566 (CAN) WHILE HOVERING DURING TAKEOFF, NR1 PWR SECTION LOST POWER (PILOT REPORTED HEARING LOUD BANG). ACFT PUT DOWN WITHO UT FURTHER INCIDENT, NR2 POWER SECTION SHUTDOWN. POWER SECTION REPLACED. ACFT RETURNED TO SERVICE. PRELIMINARY INSP R EVEALED FAILURE OF THE PT DISK. PARTIAL BLADE SEPARATION AND FOD TO EXHAUST DUCT. 1 G 7 1 4U 4 U H4SW E22EA 20081128 NM 2008 11 28 CA080924001 1 20080920 G 3240 900005831PR BRAKE ASSY EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE NR 3 FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 2416 (CAN) 100 M FROM STOPPING AT THE GATE, THE RT BRAKE STARTED TO GRAB. BRAKE TEMPS ALL NORMAL RANGE. AFTER SHUTDOWN, INS PECTED RT MAIN BRAKE ASSY AND APPEARS THAT BRAKE PAN AND ASSY CAME APART. NR3 MLG WHEEL AND BRAKE ASSY REMOVED. LG AND ACFT INSPECTED, NO ADDITIONAL DEFECTS NOTED. NEW BRAKE AND WHEEL ASSYS INSTALLED AND TESTED SERVICEABLE. 2 L 7 2 4F 4 F RT A56NM E00063EN 20081125 SW 2008 11 25 CA080924002 1 20080924 G 5302 205001731101 SUPPORT BELL 412 412 1182202 SW PWA PT6T PT6T3 52045 EA TAIL ROTOR SERVO CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2322 (CAN) CRACKS FOUND IN SUPPORT CASTING NEAR UPPER ATTACHMENT TO AIRFRAME. 1 G 7 2 4U 4 U H4SW E22EA 20081125 SW 2008 11 25 CA080924003 1 20080924 G 5302 205001731101 SUPPORT BELL 412 412 1182202 SW PWA PT6T PT6T3 52045 EA TAIL ROTOR SERVO CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2322 (CAN) CRACKS FOUND IN SUPPORT CASTING NEAR UPPER ATTACHMENT TO AIRFRAME. 1 G 7 2 4U 4 U H4SW E22EA 20081125 SW 2008 11 25 CA080924004 1 20080924 G 5302 205001731001 SUPPORT BELL 412 412 1182202 SW PWA PT6T PT6T3 52045 EA TAIL ROTOR SERVO CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2322 (CAN) TAIL ROTOR SERVO SUPPORT FOUND CRACKED NEAR UPPER ATTACHMENT FLANGES. 1 G 7 2 4U 4 U H4SW E22EA 20081128 SW 2008 11 28 CA080924005 1 20080918 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 1118 (CAN) ACFT WAS ON A MEDEVAC FLIGHT AT NIGHT AT CRUISE ALTITUDE OF 16000 FT WHEN THE FLIGHT CREW HEARD A NOISE LIKE A SLA P. THEY COULD SEE THEN THAT THE RT WINDSHIELD WAS CRACKED. ACFT RETURNED WITHOUT FURTHER INCIDENT. INSP FOUND THE WIND SHIELD OUTER PANEL HAD SHATTERED. WINDSHIELD IS BEING RETURNED FOR INSP AND WARRANTY CONSIDERATION. WINDSHIELD REMOVED FROM ACFT AND STRUCTURE INSPECTED. NO DEFECTS FOUND. 1 H 7 2 3T 4 T 2A4 E4WE 6 C P8EU 20081128 2008 11 28 CA080924007 1 20080924 G 2820 LINE GARRTT TFE731 TFE73140 29001 NE FUEL SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSP IN THE RT WW THE MAIN FUEL LINE TO THE RT ENGINE WAS FOUND TO BE CHAFING ON THE LAV SINK HEATED DRAIN LINE. THE DAMAGE WAS BEYOND LIMITS AND THE FUEL LINE WAS REPLACED. 4 F E1NM 20081128 2008 11 28 CA080924008 1 20080924 G 2820 25W653120634 LINE GARRTT TFE731 TFE73140 29001 NE FUEL SYSTEM CHAFED W K NONE O OTHER NR NOT REPORTED 1 CA (CAN) IT WAS REPORTED THAT FUEL WAS SLOWLY TRANSFERRING FROM THE RT WING INTO THE CENTER TANK WHEN THE ACFT WAS STATIC. THE MOTIVE FLOW LINE PN 25W653120-634 AT THE CENTRAL TANK LOWER TRANSFER JET PUMP WAS FOUND TO BE CHAFING ON THE FUEL Q TY PROBE MOUNTING BRACKET. THE LINE WAS REPLACED. 4 F E1NM 20081128 EA 2008 11 28 CA080924009 1 20080924 G 3210 C6UM11104 ATTACH FITTING DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE 12 MONTH INSP OF THE MLG WHICH CONSISTS OF INSPECTING THE WELDS FOR CRACKS, A CRACK WAS DETECTED ON THE BOTTOM OF THE AFT ATTACH TUBE APPROX 5 INCHES FROM THE AFT GEAR ATTACH FITTING. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081128 NE 2008 11 28 CA080924011 2 20080922 G 7200 TORQUE SHAFT AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE NR 1 ENGINE CRACKED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE TORQUE WAS LOST ON NR 1 ENGINE, SUBSEQUENTLY THE ENGINE WAS SHUTDOWN BY THE CREW. POST FLIGHT INSPE CTION REVEALED A CRACKED TORQUE SHAFT AT THE WELD JOINT. ENGINE IS BEING REMOVED FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT E20NE 20081128 NE 2008 11 28 CA080924012 2 20080815 G 7200 ENGINE BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE LEFT FAILED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION HO HOVERING 1 CA (CAN) ACFT WAS IN HOVER AND WAS TRANSITIONING TO FWD FLIGHT WHEN THE LT ENGINE ROLLED BACK IN POWER AND SHUTDOWN. PILOT LANDED THE ACFT SUCCESSFULLY ON 1 ENGINE. LT ENGINE WAS REMOVED AND SENT TO MFG FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 G 7 1 4U 4 U H4SW E22EA 20081128 NE 2008 11 28 CA080924013 2 20080922 G 7200 ENGINE DORNER DO32 DO328100 2996000 NM PWA 119 PW119B NE FLUCTUATES W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) AT ABOUT 50 METERS FROM THE ARRIVAL GATE, THE ENG PARAMETERS STARTED FLUCTUATING. PILOT SHUTDOWN THE ENG. NO REP ORTED DAMAGE. TROUBLESHOOTING IN PROGRESS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTA BLISHED. 2 H 7 2 4T 4 T RT A45NM E20NE 20081128 NM 2008 11 28 CA080925001 1 20080914 G 5610 80260008 WINDOW BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA 371 (CAN) RT WINDSHIELD CRACKED DURING CRUISE. REDUCED SPEED TO 180 KTS AND DESCENDED TO FL100 AND LANDED AT DESTINATION. MX REPLACED WINDSHIELD. ACFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081128 CE 2008 11 28 CA080925002 1 20080924 G 5511 053200198 SPAR CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA HORIZONTAL STAB CRACKED W A UNSCHED LANDING C A F.O.D. FLAME/FIRE NR NOT REPORTED 1 CA 9629 (CAN) DURING THE 100 HRS/ANNUAL INSP, IT WAS DISCOVERED THAT THE HORIZONTAL STABILIZER FRONT SPAR ASSY (PN 0532001-98) A ND THE RE-INFORCEMENT SPAR (PN 0531037-1) HAVE CRACKS AT 2 PLACES, ABOUT .5 INCH IN LENGTH, RADIATING FROM THE CENTER LI GHTENING HOLE BETWEEN BOLT ATTACHMENT AREA. 1 H 7 1 3O 3 O NT 3A12 E274 20081128 EA 2008 11 28 CA080925003 2 20080919 G 7414 BL600646201 MAGNETO ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ENGINE FAILED W O OTHER X ENGINE FLAMEOUT DE DESCENT 1 CA 151 (CAN) PILOT SNAGGED THERE WAS A HIGH ENGINE RPM RISE. MAGNETO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. 1 G 7 1 3O 3 O H11NM E295 20081128 EA 2008 11 28 CA080925004 2 20080919 G 7414 BL600646201 MAGNETO ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ENGINE FAILED W O OTHER X ENGINE FLAMEOUT AP APPROACH 1 CA (CAN) PILOT REPORTED THERE WAS A HIGH ENGINE RPM RISE. MAGNETO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. THIS IS DUPLICATED ON REPORT 20080925003. 1 G 7 1 3O 3 O H11NM E295 20081201 NE 2008 12 1 CA080925006 2 20080908 G 7200 ENGINE SKRSKY S64 S64E 8142604 NE PWA JFTD12 JFTD12A4A 52047 NE NR 2 MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION DE DESCENT 1 CA (CAN) WHILE DEPARTING AREA WITH AN AIRSPEED OF 30 TO 40 KNOTS AND A 500 FT PER MINUTE RATE OF DESCENT, NR 2 ENGINE N1 L OW RPM AUDIO HORN SOUNDED ALONG WITH ILLUMINATION OF NR 2 ENGINE LOW OIL PRESSURE LIGHT. A SCAN OF THE ENGINE GAUGES REV EALED THE NR 2 ENGINE HAD LOW N1 RPM WITH A CLIMBING T5 TEMP. THE FLIGHT CREW IDENTIFIED THE PROBLEM AS AN ENG ROLL BACK AND ONCE THE LOAD WAS SAFELY JETTISONED, A SHUTDOWN OF THE NR 2 ENGINE WAS CARRIED OUT. THE ACFT THEN RETURNED TO ITS S ERVICE LANDING AND MADE AN SINGLE ENGINE LANDING. A POST FLIGHT INSPECTION OF THE T5 RECORDING SYS REVEALED THE ENGINE TEMP HAD REACHED 798 DEGREES C. THE ENGINE, FREE TURBINE ASSY AND FCU WERE REPLACED AND AFTER A COMPLETE GROUND CHECK TH 2 G 7 2 4U 4 U H4EA E15EA 20081202 NE 2008 12 2 CA080925007 2 20080908 G 7321 FUEL CONTROL SKRSKY S64 S64E 8142604 NE PWA JFTD12 JFTD12A4A 52047 NE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING R M J PARTIAL RPM/PWR LOSS OVER TEMP WARNING INDICATION NR NOT REPORTED 1 CA (CAN) LIGHT A SCAN OF THE ENG GAUGES REVEALED THE NR 2 ENGINE HAD LOW N1 RPM WITH A CLIMBING T5 TEMP. FLIGHT CREW IDEN TIFIED THE PROBLEM AS AN ENG ROLL BACK AND ONCE THE LOAD WAS SAFELY JETTISONED A SHUTDOWN OF THE NR (2) ENGINE WAS CARRI ED OUT. THE ACFT THEN RETURNED TO IT`S SERVICE LANDING AND MADE AN SINGLE ENGINE LANDING. A POST FLIGHT INSP OF THE T5 RECORDING SYS REVEALED THE ENGINE TEMP HAD REACHED 798 DEGREES C. THE ENG, FREE TURBINE ASSY AND FCU WERE REPLACED AND A FTER A COMPLETE GROUND CHECK ACFT WAS RETURNED TO SERVICE. THE ENG, FREE TURBINE AND FCU WERE RETURNED TO MFG FOR AN OV ER TEMP INSP AND EVALUATION AS TO A POSSIBLE CAUSE OF THE ROLL BACK. 2 G 7 2 4U 4 U H4EA E15EA 20081128 SW 2008 11 28 CA080925009 1 20080804 G 2435 23032027 STARTER GEN BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) STARTER WAS SNAGGED BY PILOT WHICH MOTORED UNDER ITS OWN POWER. EXCESSIVE ROTATION CAUSED INTERNAL DAMAGE. STARTE R WAS REPLACED AND NO ISSUES WERE NOTED. 1 G 7 1 3U 3 U H2SW E4CE 20081128 WP 2008 11 28 CA080925012 1 20080924 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 1781 (CAN) CLUTCH WAS REMOVED FROM ACFT FOR VISUAL INSP DUE TO ISSUES WITH CLUTCH ASSY`S. TEARDOWN REVEALED THE FOLLOWING: C AGE CRACKED AT 1 CROSSBAR, SHAFT C166-4 WORN UNDERSIZE, HSG C167-3 WORN OVERSIZE AND OIL WAS VERY BLACK. 1 G 7 1 3O 3 O H11NM 1E4 20081202 GL 2008 12 2 CA080925013 1 20080918 G 2421 ALU8521LS ALTERNATOR DIAMON DA40 DA40 2990002 GL INTERMITTENT W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CL CLIMB 1 CA 6 (CAN) INSUFFICIENT CLEARANCE BETWEEN THE HEAD OF THE FIELD TERMINAL STUD AND HSG. BRUSH HOLDER ASSY WHEN FLEXED INWARD, CAUSES THE HSG AND HEAD OF THE STUD TO TOUCH. IF YOU REMOVED THE BRUSH HOLDER ASSY YOU WILL NOTICE THAT THE RING TERMI NAL THAT IS CRIMPED TO THE BRUSH LEAD IS SLIGHTLY LARGER THAN THE HEAD OF THE TERMINAL BOLT. IT IS ACTUALLY THE RING TE RMINAL THAT TOUCHES THE HSG. THIS TRIPS THE VOLTAGE REGULATOR OFF LINE. THE ALTERNATOR SWITCH NEEDS TO BE CYCLED TO RE SET THE REGULATOR. 1 L 7 1 3O NT A47CE 20081128 WP 2008 11 28 CA080925014 1 20080923 G 6310 C1883 SPRAG CLUTCH ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAIN ROTOR CHIPPED W O OTHER O OTHER LD LANDING 1 CA 596 (CAN) PILOT HEARD POSSIBLE NOISE WITH SLIPPAGE OF DRIVE TRAIN. CLUTCH WAS REMOVED TO VERIFY NO INTERNAL DAMAGE. THE FO LLOWING WAS FOUND DURING A TEARDOWN: 1 PEANUT INNER EAR CHIPPED, SHAFT PN C166-4 WORN UNDERSIZE, HSG C167-3 WORN OVERSIZ E AND OIL VERY BLACK. 1 G 7 1 3O 3 O H11NM 1E4 20081128 NE 2008 11 28 CA080926001 2 20080925 G 7414 103571651 COIL ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO WORN W K NONE O OTHER IN INSP/MAINT 1 CA 235 (CAN) IT WAS FOUND WHEN THE MAG WAS ASSEMBLED NEW, THE HIGH TENSION TAB OF THE COIL WAS NOT MADE PARALLEL WITHIN THE HOU SING SPLIT LINE. THIS CAUSED THE BRUSH TO WEAR A DEEP GROOVE INTO THE TAB. THE BRUSH (10-160844) ALSO RECEIVED DAMAGE IN THE FORM OF A STEP GROUND INTO THE SIDE OF IT FROM THE SIDE LOAD IMPOSED BY THE BENT TAB. 1 G 7 1 3O 3 O H11NM 1E4 20081128 NM 2008 11 28 CA080926002 1 20080926 G 2910 82920010227 PIPE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE HYD SYSTEM DAMAGED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA 12782 (CAN) DURING TAXI OUT THE FLIGHT CREW REPORTED A LOSS OF NR 2 HYDR QUANTITY AND HYDR LOW PRESSURE CAUTION LIGHT. MX DIS COVERED A HYDR TUBE LOCATED AT APPROX STA X409.00 RT SIDE HAD A (2) CENTIMETER CRACK LONGITUDINALLY ON THE INNER RADIUS OF A 90 BEND. TUBE WAS PART OF THE MLG DOWN SYS, PRESSURE LINE, NR 2 HYDR. TUBE WAS REPAIRED IAW THE AMM AND ACFT RETU RNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081128 SW 2008 11 28 CA080926003 1 20080914 G 2720 27720065 ARM SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCB3T HCB3TN5 GL RUDDER PEDAL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FOUND 3 OF 4 RUDDER PEDAL ATTACH ARMS CRACKED ON LWR END, WHERE THE TORQUE TUBE THAT THE PEDAL IS MOUNTED TO ATTAC HES TO THE CAST ARM. MATERIAL THICKNESS IS APPROX .2500 INCH IN THAT AREA. ACFT IS 17,800 TOTAL TIME, LOW FOR THIS TYPE OF ACFT. HAVE PREVIOUSLY FOUND 1 OTHER CRACKED ARM. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 20081128 CE 2008 11 28 CA080926004 1 20080922 G 2840 S38521 RESISTOR CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL FUEL INDICATOR WORN W K NONE N FALSE WARNING IN INSP/MAINT 1 CA (CAN) DURING GROUND RUN, NOTICED THAT THE LOW FUEL WARNING LIGHT FOR THE LT SIDE WOULD FLICK ON. IF YOU WERE QUICK ENOU GH TO CATCH IT THE LT FUEL QUANTITY NEEDLE WOULD TWITCH AT THE SAME TIME. WITH THE SENDER REMOVED THE RESISTANCE IN THE SENDER WAS CHECKED WITH A DIGITAL MULTI METER. NORMAL OPERATION FROM THE EMPTY TO FULL IS 2 OHMS TO 90 OHMS. THE SENDER WAS FINE AT THE EMPTY POSITION AT 2 ISH OHMS UP TO 63 OHMS. PAST 63 UP TO FULL THE RESISTANCE COULD SPIKE UPWARDS AROUN D 350 OHNS WHEN THE FLOAT ARM WAS WIGGLED. UNIT WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 20081201 EU 2008 12 1 CA080926005 1 20080925 G 2597 E0111241057 CONNECTOR AIRBUS 310 A310 EU GE CF6 CF680 30025 NE GALLEY POWER DAMAGED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) DURING STATION TRANSIT, CABIN CREW REPORTED SMOKE COMING FROM AFT GALLEY, WITH SMOKE WARNING, WHEN GALLEY ELECTRIC AL PWR WAS PUT ON. GALLEY POWER WAS REMOVED FROM THE AFT GALLEY. DURING MX INVESTIGATION, THE GALLEY CONNECTOR 38 MC W AS FOUND DAMAGED WITH PINS AND SOCKET BURNED. CONNECTOR WAS REPLACED AND CAMPAIGN WAS INITIATED TO INSPECT ACFT EQUIPMEN T WITH THE SAME TYPE OF INSTALLATION. 2 L 7 2 4F 4 F RT A35EU E13NE 20081202 EA 2008 12 2 CA080927001 2 20080926 G 8520 130L119 PISTON RING ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ENGINE BROKEN W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 1547 (CAN) PILOT REPORTED ENGINE ROUGH AT 80 PERCENT RPM. ACFT WAS GROUNDED AND A COMPRESSION CHECK WAS CONDUCTED. CYLINDER 1 WAS FOUND TO HAVE 58/80 PSI. CYLINDER AND PISTON REMOVED AND COMPRESSION RING WAS FOUND CRACKED. PISTON/CYLINDER REP LACED. ACFT RETURNED TO SERVICE. 1 G 7 1 3O 3 O H11NM E295 20081202 NE 2008 12 2 CA080929003 2 20080918 G 7321 8237002 FUEL CONTROL CESSNA 560 560XL 2076702 CE PWA 545 PW545A NE ENGINE FAILED W L ABORTED APPROACH X J ENGINE FLAMEOUT WARNING INDICATION DE DESCENT 1 CA 3308 3308 (CAN) ON DESCENT THROUGH 12000 FT, THE ENGINE EEC WARNING ACTIVATED, OIL PRESSURE DROPPED AND ENGINE SPOOLED DOWN TO 0. APPROACH REJECTED AND EMERGENCY DECLARED, ACFT DIVERTED. TROUBLESHOOTING CARRIED OUT, AS REQUESTED BY MFG, FUEL IS NOT PASSING THROUGH THE FCU, UNIT REMOVED FOR REPAIR/OVERHAUL, A REPLACEMENT UNIT HAS BEEN ORDERED. 2 L 7 2 4F 4 F RT A22CE E00059EN 20081209 SW 2008 12 9 CA080929005 1 20080924 G 6720 369X2172313 PITCH LINK DOUG 500N MD500N 3030001 SW ALLSN 250C 250C20B 03013 GL TAIL ROTOR SEPARATED W K NONE O OTHER IN INSP/MAINT 1 CA 219 (CAN) THE PITCH CHANGE ROD END BEARING BALL WAS FOUND SEPARATED FROM THE PITCH LINK. THE PILOT REPORTED THAT THE TAIL R OTOR FELT DIFFERENT UPON LANDING. IT WAS FOUND BY THE PILOT WHEN DOING A POST FLIGHT INSPECTION. AN AME WAS DISPATCHED TO ATTEND THE PROBLEM. BOTH PITCH CHANGE RODS WERE REPLACED AND THE HELICOPTER WAS RETURNED TO SERVICE. 1 G 7 1 3U 3 U NC H3WE E4CE 20081202 WP 2008 12 2 CA080929006 1 20080929 G 6310 C0183 CLUTCH ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAIN ROTOR INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA 955 (CAN) THE C188-3 SPRAG S/N S164 REV G HAS 2 PEANUTS WITH 5 BROKEN EARS. C166-4 SHAFT SPRAG JOURNAL WORN UNDERSIZE, C167- 3 HOUSING SPRAG JOURNAL WORN OVERSIZE. 1 G 7 1 3O 3 O H11NM 1E4 20081202 CE 2008 12 2 CA080929007 1 20080920 G 2843 38522 INDICATOR CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170* GL FUEL QTY INOPERATIVE W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) FUEL QUANTITY SENDER FOUND ELECTRICALLY UNSERVICEABLE, READING EMPTY WHEN TANKS WERE FULL. SERVICEABLE FUEL SENDE R INSTALLED. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 20081202 EA 2008 12 2 CA080930001 1 20080928 G 5280 CC670105202003 DOOR CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C1 30049 NE LT MLG MISSING W O OTHER D INFLIGHT SEPARATION AP APPROACH 1 CA (CAN) DURING THE WALKAROUND THE CREW NOTICED THE LT MLG DOOR WAS MISSING. THE DOOR SEPARATED FROM ACFT DURING THE FLIG HT. THE PRELIMINARY ASSESSMENT FROM PICTURES SHOWS THE HINGE FITTINGS CRACKED AND THE ROD END SNAPPED ON THE DOOR ATTAC HMENT POINT. LAST STRUCTURAL INSPECTION IAW AD CF2003-23 DONE 12 SEPT 2008. 2 L 7 2 4F 4 F RT A21EA E00063EN 20081202 GL 2008 12 2 CA080930002 3 20080914 G 6110 PROPELLER FOUND FBA FBA2C 3640102 EA LYC O540 O540A1C5 41532 EA HARTZL HC92Z HC92ZK1 GL VIBRATION W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) PROPELLER REMOVED FOR EVALUATION DUE TO SMALL VIBRATION. NOT CONSIDERED SERIOUS. 1 H 7 1 3O 3 O A7EA E295 5 C P892 20081202 NE 2008 12 2 CA080930003 2 20080831 G 7261 SEAL BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE ENGINE OIL LEAKING W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, THE OIL PRESSURE STARTED TO FLUCTUATE FOLLOWED BY A DROP TO ZERO, WHICH WAS ACCOMPANIED BY A GEARBO X CHIP DETECTOR WARNING FOR NR 2 POWER SECTION. A SINGLE ENGINE LANDING WAS PERFORMED. TROUBLESHOOTING FOUND LITTLE OIL LEFT IN THE ENGINE AND A LEAK AT NR 2 PT GOVERNOR SEAL. THE CHIP DETECTOR WAS FOUND CONTAMINATED. THE POWER SECTION A ND GEARBOX TC2523 WILL BE REMOVED AND FORWARDED FOR REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROO T CAUSE ONCE ESTABLISHED. 1 G 7 1 4U 4 U H4SW E22EA 20081202 CE 2008 12 2 CA080930004 1 20080929 G 2730 05117821 YOKE CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C401 GL ELEV CONTROL CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) ASSEMBLY WAS FOUND CORRODED WHEN INSPECTED IAW SEB01-3. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 20081202 CE 2008 12 2 CA080930005 1 20080929 G 5340 0512128 BRACKET CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO FLAP PULLEY BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT FLAPS HAVE EXCESSIVE PLAY WHEN DEPLOYED. SYSTEM INVESTIGATED AND LT SIDE FLAP PULLEY BRACKET FOUND BROKEN. 1 H 7 1 3O 3 O 3A24 E5CE 20081202 CE 2008 12 2 CA080930006 1 20080723 G 3246 4040A WHEEL CESSNA 401 401 207590C CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C505 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT MAIN WHEEL ASSY BEAD AREA FOUND CRACKED. WHEEL REPLACED WITH SERVICEABLE UNIT. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 20081202 CE 2008 12 2 CA080930007 1 20080930 G 3210 24410071 SPACER LEAR 35 35A 5170602 CE GARRTT TFE731 TFE73122B 01518 WP LT MLG ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON REMOVAL OF LT GEAR ACTUATOR DUE TO HYDR BYPASS, CONICAL SPACER, P/N 2441007-1, ITEM NR 32 IN IPC 32-32-20, WA S FOUND CRACKED. RT ACTUATOR REMOVED, SPACER VISUALLY INSPECTED. NO CRACK INDICATIONS. BOTH ACTUATOR PILLARS REMOVED, CL EANED AND MAGNETIC PARTICLE INSPECTED IAW NDT MANUAL. NO DEFECTS NOTED. SURROUNDING AREA VISUALLY INSPECTED, NO DEFECTS NOTED. ACTUATORS INSTALLED WITH NEW SPACERS ON BOTH SIDES IAW ACFT MM. F/C OF GEAR C/O SERVICEABLE. 2 L 7 2 4F 4 F A10CE E6WE 20081202 SO 2008 12 2 CA080930008 1 20080929 G 8120 SEAL PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL TURBOCHARGER LEAKING W O OTHER K FLUID LOSS LD LANDING 1 CA (CAN) PILOT SAW THICK BLUE SMOKE FROM LT ENG JUST AFTER LANDING AT HOME BASE. OIL PRESSURE INDICATIONS APPEARED NORMAL. DURING INVESTIGATION FOUND LT TO BE 5 QUARTS LOW ON OIL, WITH NO VISIBLE EXTERNAL LEAKS. CYL COMPRESSION CHECK SHOWED NO FAULTS. TURBO CHARGER EXHAUST PIPE SHOWED WET OIL ON INSIDE OF EXIT PIPE. PIPE REMOVED FROM TURBOCHARGER AND FOUND OIL STAIN IN EXHAUST TURBINE. REPLACED TURBO AND GROUND CHECKED SERVICEABLE. NO FAULTS REPORTED AFTER SUBSEQUENT FLIG HTS. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20081202 CE 2008 12 2 CA080930009 1 20080920 G 2910 1013880175 LINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL HYDRAULIC SYS RUPTURED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) AFTER LANDING A HYDR LEAK WAS DISCOVERED BY THE MX CREW. IT TURNED OUT TO BE THE RT MLG "REGULAR EXTEND" HYDR LIN E. THE LINE HAD RUPTURED ABOUT 1 INCH FROM THE END FITTING RESULTING IN A SUBSTANTIAL FLUID LOSS. THE LINE WAS REPLACE D WITH NO FURTHER ISSUES. 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 20081202 NM 2008 12 2 CA081001001 1 20080916 G 7920 PUMP BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ENGINE OIL LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION DE DESCENT 1 CA (CAN) DURING DESCENT, THE LOW OIL PRESSURE WARNING FOR THE NR 2 ENGINE SOUNDED. THE PILOT ELECTED TO SHUTDOWN AND SECUR E THE ENGINE AND AN UNEVENTFUL SINGLE ENGINE LANDING WAS PERFORMED AT DESTINATION. GROUND INSPECTION REVEALED NO SIGNS OF EXTERNAL OIL LEAKAGE, HOWEVER THE OIL TANK SHOWED "EMPTY". INITIAL TROUBLESHOOTING REVEALED INTERNAL DISTRESS OF THE OIL PUMP ASSY. THE ENGINE HAS BEEN REMOVED AND WILL BE RETURNED FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING TH E EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A13NM E00062EN 20081202 EU 2008 12 2 CA081001002 1 20080930 G 2440 TERMINAL SAAB SF340 340B 7860101 EU EXTERNAL POWER MELTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ACFT ARRIVED FROM CUSTOMER WITH EXTERNAL POWER INOP (MEL). AFTER INVESTIGATION, FOUND THE + TERMINAL MELTED AT TH EN EXT PWR CONNECTOR. SHEET METAL REPAIR WAS PREVIOUSLY DONE AT THE EXT PWR CONNECTOR ATTACHMENT. BOTH TERMINALS WERE CRACKED HALF WAY. 2 L 7 2 4T RT A52EU 20081202 CE 2008 12 2 CA081001003 1 20080919 G 5751 122005211 SKIN CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AT INSPECTION THE LT AILERON OTBD HINGE ASSY WAS FOUND CRACKED. THE CRACKS WERE LOCATED AT THE BEND RADIUS OF THE LOWER AFT ATTACH ANGLES. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 20081202 SW 2008 12 2 CA081001004 1 20080927 G 5302 206031329103S FITTING BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPPER LT TAILBOOM ATTACHMENT FITTING ON THE FUSELAGE SIDE FOUND CRACKED FROM THE RIVET HOLES. 1 G 7 1 3U 3 U H2SW E1GL 20081202 2008 12 2 CA081001006 4 20080924 G 2397 GNS430 WIRE UROCOP EC130 EC130B4 8680989 EU TMECA ARRIEL ARRIEL2B1 60056 NE COMM 1 SHORTED W O OTHER H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA 31 (CAN) NO PILOT OR COPILOT SIDE TONE ON COMM 1. TECH FOUND THE AUDIO PHONE WIRE SHORTED BY THE SHIELDING. REPAIRED AND SIDE TONES WERE RETURNED TO NORMAL. 1 G 7 2 3U 3 U H9EU E00054EN 20081202 SW 2008 12 2 CA081001007 1 20081001 G 2821 ZT2CV06A08B CHECK VALVE BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL FUEL SYSTEM DIRTY W K NONE O OTHER IN INSP/MAINT 1 CA 13135 (CAN) AFTER A FUEL FILTER REPLACEMENT A 2 MINUTE RUN IS REQUIRED WITH BOOST PUMPS OFF TO ENSURE THERE ARE NO AIR LEAKS I N THE FUEL SYS. DURING THIS 2 MINUTE GROUND RUN THE ENG FLAMED OUT AFTER APP 90 SECONDS INDICATING AN AIR LEAK. FUEL S YS INSPECTED AND THE INLINE FUEL/CHECK VALVE WAS FOUND STUCK IN THE OPEN POSITION. WHEN THIS VALVE IS STUCK OPEN AIR CA N BE SUCKED FROM THE FRONT FUEL TANKS IF THEY ARE EMPTY. CHECK VALVES CLEANED AND HELICOPTER WAS GROUND RUN SATISFACTOR ILY. THIS WAS POSSIBLY CAUSED BY FUELING FROM DRUMS FOR AN EXTENDED PERIOD OF TIME AND A SMALL QUANTITY OF DIRT ENTERED THE FUEL SYS. 1 G 7 1 3U 3 U H2SW E1GL 20081202 NM 2008 12 2 CA081001008 1 20080814 G 3000 XD4N RELAY DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE DEICE SYSTEM FAILED W O OTHER J WARNING INDICATION DE DESCENT 1 CA 40935 40935 (CAN) DURING DESCENT FROM FL250, AS POWER WAS REDUCED BELOW 30 PERCENT TORQUE. WHEN DESCENDING THROUGH 23000` CABIN STA RTED TO CLIMB RAPIDLY. DE-ICE PRESSURE CAUTION LIGHT ILLUMINATED. NO LOUD NOISES OR SQUEALS. MX INVESTIGATION FOUND RE LAY 2121-K6 AT FAULT. RELAY REPLACED, ACFT RETURNED TO SERVICE. (NOTE: PART IS CONSIDERED AN EXPENDABLE AND TIMES NOT T RACKED, TIMES PROVIDED ARE AIRFRAME TIMES) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081202 CE 2008 12 2 CA081002001 1 20081002 G 3260 SA24SDX111 SWITCH CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C505 GL MLG INTERMITTENT W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) LANDING GEAR INTERMITTENTLY WOULD NOT RETRACT. FOUND ANNUNCIATOR PRESS TO TEST SWITCH INTERMITTENT. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 20081202 CE 2008 12 2 CA081002002 1 20081002 G 3230 1002573 PISTON CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA HARTZL HCF3Y HCF3YR1 GL MLG SEPARATED W O OTHER O OTHER NR NOT REPORTED 1 CA 51 (CAN) RT MLG FAILED TO RETRACT. FOUND HYDRAULIC CYLINDER PISTON HAD SEPARATED FROM CYLINDER RAM. 1 H 7 1 3O 3 O RT A4CE E14EA 5 C P31EA 20081202 CE 2008 12 2 CA081002003 1 20080929 G 8120 407809001 TURBINE WHEEL CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520C 17040 SO MCAULY 3AF32C 3AF32C87 GL TURBOCHARGER SEIZED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 774 (CAN) TURBINE WHEEL SEIZED. TURBOCHARGER REMOVED, OVERHAULED TURBOCHARGER INSTALLED. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 20081202 NM 2008 12 2 CA081002004 1 20081001 G 2432 BATTERY BOEING 737 737275C 13844AS NM PWA JT8 JT8D17 52049 NE MASTER OVERHEATED W O OTHER B M SMOKE/FUMES/ODORS/SPARKS OVER TEMP TX TAXI/GRND HDL 1 CA (CAN) PASSENGERS WERE ON THE ACFT, ACFT WAS ON EXTERNAL GROUND POWER AT THE TIME. WHEN THE PILOTS WENT TO START THE APU , THEY NOTICED THE START WAS NOT NORMAL, AND THE APU ALSO DID NOT START. APU OVERSPEED CAUTION LIGHT ILLUMINATED. CAPT AIN WENT TO THE E&E BAY TO RESET THE APU BOX. APU START ATTEMPTED AGAIN, SAME RESULT. PILOT AGAIN RESET THE APU CONTRO L BOX, AND THAT WAS WHEN HE NOTICED THE BATTERY SMOKING/VENTING. IT WAS HOT TO THE TOUCH. PEOPLE WERE REMOVED FROM THE ACFT. MX CONFIRMED THE BATTERY WAS STILL HOT, AND IT WAS REMOVED. A NEW OVERHAULED BATTERY WAS INSTALLED, AND THE BAT TERY CHARGING CIRCUIT WAS TESTED IAW WORKCARD. NO FAULTS WERE NOTICED, ACFT WAS RELEASED BACK INTO SERVICE. 2 L 7 2 4F 4 F RT A16WE E2EA 20081126 CE 2008 11 26 CA081002005 1 20080929 G 2820 10192000015 LINE BEECH 200 B200C 1152924 CE PWA PT6 PT642A NE HARTZL HCB3T HCB3TN3 GL FUEL SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING DAILY INSP, WITH POWER ON A FEW MOMENTS, NOTICED FUEL LEAKING FROM LT GEAR WELL. POWER TURNED OFF, NOTED FU EL LEAKING FROM SUPPLY LINE WHICH IS LOCATED BETWEEN AUX FUEL TANK AND NACELLE FUEL TANK. ON CLOSER INSP NOTICED WHERE FUEL LINE PASSED THROUGH OPENING IN A BULKHEAD, LINE RUBBING AGAINST B-NUT OF A HYD LINE. AFTER REMOVAL OF LINE, A WORN AREA & CRACK IN THE MIDDLE OF IT WAS FOUND TO BE THE CAUSE OF THE FUEL LEAK. THIS FUEL LINE WOULD ONLY LEAK IF FUEL WAS BEING TRANSFERRED FROM THE AUX TANK TO THE NACELLE FUEL TANK, OTHERWISE THE MOTIVE CHECK VALVE WOULD HAVE CLOSED AND NO T ALLOWED FUEL TO FLOW BACK FROM THE NACELLE TANK. PILOT HAD LEFT THE AUX FUEL TRANSFER OVERRIDE SWITCH IN THE MANUAL PO 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 20081120 2008 11 20 CA081002006 1 20080926 G 5200 ACTUATOR CNDAIR 215T752204 PWA PW120 PW123 NE DOOR LEAKING W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 129 129 (CAN) FOUND LEAKING AT THE PREES LINE CONNECTION, TSO129HRS, TOTAL DROPS 398 FOUND LEAKING DURING AN INSPECTION BY THE T ECHNICAL ENGINEER. 4 T E20NE 20081120 CE 2008 11 20 CA081002007 1 20080924 G 5553 04311481 FITTING CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA VERTICAL STAB FRACTURED W C ABORTED TAKEOFF F FLT CONT AFFECTED NR NOT REPORTED 1 CA (CAN) ACFT BROUGHT TO MX DUE TO ACFT NOT RESPONDING CORRECTLY, VERTICAL STABILATOR WAS INSPECTED AND A FRACTURE WAS FOUN D IN THE BRACKET. IT APPEARED TO BE A STRESS FRACTURE IN THE FITTING. WE WOULD LIKE ALL CESSNA OWNERS TO UNDERSTAND TH AT IF THE TAIL HITS THE GROUND OR IT RUBS THE GROUND IN ANY WAY THAT IT SHOULD BE INSPECTED. THIS ACFT HAD BEEN INSPECT ED APPROX 50 HOURS PRIOR AND THERE WAS NO FRACTURE AT THAT TIME. ALL OF THE FITTINGS AND BOLTS RELATED TO THE ATTACH PO INT OF THE VERTICAL FIN WERE REPLACED AND THE FIN WAS INSPECTED FOR ANY DAMAGE. WE ARE GOING TO CONTINUE TO MONITOR THE SE FITTINGS ON ALL 152`S AND IF FURTHER INFORMATION ABOUT THIS ISSUE BECOMES APPARENT TO US WE WILL UP DATE. 1 H 7 1 3O 3 O NT 3A19 E223 20081120 2008 11 20 CA081002008 2 20080925 G 7414 10357584 DISTRIBUTOR GEAR CONT 106006141 MAGNETO DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MAGNETO RECEIVED WITH TEETH BROKEN OFF THE DISTRIBUTOR GEAR. 20081120 EA 2008 11 20 CA081003001 1 20080926 G 5610 NP13932211 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT CRACKED W K NONE O OTHER CR CRUISE 1 CA (CAN) CAPTAINS SIDE WINDOW CENTER PANE SHATTERED ENROUTE. MX CHANGED THE WINDOW. 2 L 7 2 4F 4 F RT A21EA E15NE 20081120 NE 2008 11 20 CA081003002 2 20081001 G 7397 1710101 WIRE HARNESS EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE FADEC DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 6526 (CAN) FADEC WIRING HARNESS DAMAGED (WHICH REQUIRED REPLACEMENT) DUE TO THE LOWER SEAL ON THE PYLON PRE-COOLER LEAKING (N O LEAK/HEAT DETECTION IN THIS AREA). ATTACHED ARE PICTURES. BELOW ARE THE FIN`S AFFECTED WITH TIMES AND CYCLES. ACFT IND UCTED FOR THE FREEZE PROTECTION MOD. 2 L 7 2 4F 4 F RT A56NM E00063EN 20081120 2008 11 20 CA081003003 1 20080925 G 8011 149NL HOUSING STARTER LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 43 (CAN) REAR HOUSING DISCOVERED LOOSE DURING SCHEDULED MX. 20081120 2008 11 20 CA081003004 1 20080912 G 8011 149NL HOUSING STARTER LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 207 (CAN) REAR HOUSING DISCOVERED LOOSE DURING SCHEDULED MX. 20081120 2008 11 20 CA081003005 1 20080924 G 8011 ATTACH BOLT 149NL STARTER LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 655 (CAN) MOTOR TO HOUSING ATTACH BOLTS LOOSE. 20081124 NE 2008 11 24 CA081003006 2 20080930 G 7322 FLOAT BENDIX DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE CARBURETOR DAMAGED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION DE DESCENT 1 CA (CAN) FLIGHT CREW REPORTS THAT THE ENGINE FALTERED ON SHORT FINAL AND QUIT COMPLETELY AS THE FLOATPLANE CAME OFF THE STE P. AFTER BEING TOWED TO THE DOCK, FUEL WAS OBSERVED POURING OUT OF THE CARBURETOR. THE FLOAT VALVE APPEARED TO BE STUC K IN THE FULL OPEN POSITION. CARBURETOR WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE. THE CARBURETOR HAD BEEN INST ALLED 2 HOURS PREVIOUS FROM OVERHAUL. 1 H 7 1 3R 3 R RC A806 5E1 20081124 SW 2008 11 24 CA081003007 1 20080925 G 3233 LA11C2110 ACTUATOR MOONEY M20 M20F 5870214 SW LYC O360 IO360LYC* 41514 EA MLG FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) LANDING GEAR FAILED TO EXTEND ELECTRICALLY. ACTUATOR TEAR DOWN REVEALED THE MOTOR HAD FAILED. 1 L 7 1 3O 3 O 2A3 1E10 20081124 SO 2008 11 24 CA081003009 2 20081001 G 8530 652420902 THRU BOLT CONT O360 IO360KB 17025 SO NR 6 CYLINDER BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 855 (CAN) ON A PRE-FLIGHT INSPECTION, THE PILOT NOTICED A LOOSE WASHER ON THE FRONT OF THE ENGINE. AFTER FURTHER INSPECTION IT WAS DISCOVERED THAT THE TOP FWD ENGINE THROUGH BOLT FOR NR 6 CYLINDER WAS BROKEN ON THE CYLINDER SIDE. THE LOOSE WA SHER WAS BECAUSE THE BOLT SNAPPED AND THERE WAS NO TORQUE ON THE OTHER SIDE AND THE NUT HAD WORKED ITS WAY LOOSE (IT WAS NEVER FOUND). THE BROKEN PIECE OF BOLT AND NUT FROM THAT SIDE WERE FOUND ON TOP OF THE FWD ENGINE BAFFLE. ALL OTHER B OLTS IN THE AREA WERE TORQUE CHECKED AND FOUND SERVICEABLE. NO OTHER DEFECTS WERE NOTED. 3 O E1CE 20081124 CE 2008 11 24 CA081004001 1 20081001 G 3245 302247400 TUBE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL NLG FOD W O OTHER C F.O.D. NR NOT REPORTED 1 CA (CAN) TUBE HAD A HOLE CHAFED IN IT - NO EVIDENCE OF FOD INSIDE TIRE FROM INITIAL ASSY TO CAUSE WEAR HOLE. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20081126 CE 2008 11 26 CA081006001 1 20081002 G 3250 05430223 STEERING SYS CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA INOPERATIVE W O OTHER F FLT CONT AFFECTED TO TAKEOFF 1 CA (CAN) INSTRUCTOR WITH A STUDENT PILOT ON BOARD REPORTED THAT ALTHOUGH RUDDER PEDAL TRAVEL APPEARED TO BE NORMAL DURING T AXI, AT THE POINT OF LIFT OFF RUDDER PEDAL MOVEMENT WAS RESTRICTED TO RT RUDDER ONLY. RUDDER COULD NOT BE MOVED TO THE L T. THE ACFT CONTINUED WITH A NORMAL CIRCUIT AND LANDED WITHOUT INCIDENT WHEREUPON THE RUDDER PEDAL MOVEMENT APPEARED TO RETURN TO NORMAL OPERATION. MAINT INSP WAS REQUESTED FOR THE ACFT. IT WAS DISCOVERED THAT THE LT STEERING TUBE ASSY, P/N 0543022-3 HAD LOST THE CUSHIONING EFFECT OF THE INTERNAL SPRING. THIS IN EFFECT HAD LEFT THE TUBE ASSY TO ACT AS A SOLI D ROD, WHERE AFTER LIFT OFF WITH THE NOSE OLEO EXTENDED AND THE NOSE WHEEL LOCKED IN THE CENTER POSITION, IT WOULD HAVE 1 H 7 1 3O 3 O NT 3A19 E223 20081124 GL 2008 11 24 CA081006002 1 20080929 G 2420 1707580A CONVERTER BOMBDR BD700 BD7001A10 1390006 GL DAMAGED W O OTHER M B G OVER TEMP SMOKE/FUMES/ODORS/SPARKS MULTIPLE FAILURE TX TAXI/GRND HDL 1 CA (CAN) ON GROUND, DURING GROOMING THE ACFT, THE AC POWER DROPPED OFF. WHEN IT WAS RE-APPLIED, COCKPIT DISPLAYS SHOWED AC SYSTEM IN MAGENTA (NO COMMUNICATION). FOUND THE EXTERNAL AC/DC CONVERTOR CARD LOCATED IN THE AC POWER CENTER HAD A BUR NED TRACE. THE MICROPROCESSOR CARD LOCATED ABOVE THE AC/DC CONVERTER CARD HAD A SMALL AMOUNT OF SOOT BUT NO VISIBLE DAM AGE. THE PRIMARY LOGIC CARD WAS SOOTY AND , WHEN THE SOOT WAS WASHED OFF, A SMALL AREA ABOUT 3 SQUARE INCHES WAS DISCOL ORED. AC POWER CENTER REPLACED TO DISPATCH THE ACFT. 2 L 7 2 4F RT T00003NY 20081124 NM 2008 11 24 CA081006003 1 20081001 G 3231 CONTROL ROD DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE NLG DOOR BROKEN W A UNSCHED LANDING E D VIBRATION/BUFFET INFLIGHT SEPARATION CL CLIMB 1 CA (CAN) ON CLIMB OUT, THE CREW NOTED A VIBRATION AND BANGING NOISE FROM THE NOSE OF THE ACFT. THE ACFT RETURNED AND THE G ROUND CREW NOTED THAT THE RT NLG DOOR WAS OPEN AND THAT THE DOOR CONTROL ROD AND TENSION SPRING (PN 83232010-105) FOR TH E RT DOOR WAS BROKEN. THERE WAS NO DAMAGE TO THE SURROUNDING STRUCTURE. THE CONTROL ROD WAS SHEARED AT THE UPPER PERMA SWAGE ON THE ROD. GEAR INDICATION WAS NORMAL TO THE CREW. THE BARTS WHERE REPLACED AND THE ACFT RELEASED BACK TO SERVI CE. 2 H 7 2 4T 4 T RT A13NM E20NE 20081120 SO 2008 11 20 CA081006004 1 20081003 G 7160 434179 GROMMET 86245041 PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6D 42305 EA CARB HEAT BOX MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 406 (CAN) DURING A DEFECT RECTIFICATION ON OUR OTHER ACFT, IT WAS FOUND THAT THE LWR GROMMET AND BUSHING P/N 453-991 WAS MIS SING ON THE LT ENGINE CARB HEAT BOX. THIS GROMMET SUPPORTS THE SHAFT IN THE CARB HEAT BOX. THIS PROMPTED THE INSP OF THI S ACFT, WHICH FOUND THE BOTTOM GROMMET AND BUSHING MISSING FROM ITS LT ENGINE. 1 L 7 2 3O 3 O A19S0 E286 20081124 EA 2008 11 24 CA081007001 2 20081003 G 7320 312240015 FADEC BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA NR 2 ENGINE MALFUNCTIONED W D RETURN TO BLOCK Y J ENGINE STOPPAGE WARNING INDICATION TX TAXI/GRND HDL 1 CA 115 (CAN) DURING PUSH-BACK FROM THE GATE WITH BOTH ENGINES RUNNING (PROPS FEATHERED), THE NR 2 ENGINE HAD AN UN-COMMANDED SH UTDOWN WITH AN ASSOCIATED NR 2 ENG FADEC FAIL WARNING LIGHT AND POWERPLANT MSG. INTERROGATION OF THE CDS REVEALED THE F OLLOWING FAULT CODES: 705, 707, 734, MPT, 737, 740, 748 & 749. FIM TASKS ARE CURRENTLY IN WORK, BUT AS FAULT CODES 705 & 707 ARE INDICATING AN INTERNAL FAULT IN THE FADEC. FADEC REPLACED IAW AMM TASK 73-21-01-400-801, FAULT CODES CLEARED, PLA TRIM AND ENGINE RUNS CARRIED OUT SUCCESSFULLY. 2 H 7 2 4T 4 T RT A13NM E00062EN 20081124 NE 2008 11 24 CA081007002 2 20080906 G 7200 ENGINE SKRSKY S92 S92A NE GE CT7TS CT78A 30136 NE MALFUNCTIONED W E ENGINE SHUTDOWN J WARNING INDICATION NR NOT REPORTED 1 CA (CAN) POST LANDING AND TAXI. ACFT WAS STATIONARY WITH BOTH ENGINES IN THE GROUND IDLE POSITION WITH ROTORS TURNING. PI LOT OBSERVED ROTOR SPEED WAS NEARING A KNOWN "AVOID RANGE" AND ELECTED TO NUDGE THE NR 1 ENGINE CONTROL LEVER FORWARD TO INCREASE ROTOR SPEED SLIGHTLY ABOVE THE AVOID RANGE. DURING THE EXECUTION OF THIS MARGINAL CONTROL LEVER MOVEMENT, THE RELATED ENGINE THEN UNEXPECTEDLY SHUTDOWN. NO OTHER INDICATIONS OF A PROBLEM WERE OBSERVED BY EITHER PILOT. THE HUMS DATA WAS DOWNLOADED AND DURING REVIEW IT WAS DISCOVERED THAT DURING THE CONTROL LEVER INCREASE, THE NR 1 ENGINE TGT SPIK ED TO 1100 DEGREES C FOR A PERIOD OF 3 SECONDS BEFORE THE AUTOMATED PROTECTIVE CIRCUITS OF THE FADEC SHUT THE ENGINE DOW 2 G 7 2 4U 4 U R00024BO E8NE 20081124 NM 2008 11 24 CA081007003 1 20081006 G 5754 NAS86034NAS86 SCREW BOMBDR CL600 CL6002D15 NM GE CF34 CF348C5 30050 NE SLAT LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ALL SCREWS ON TOP OF WING UNDER THE SLATS WERE FOUND LOOSE. 2 SCREWS , 1 ON EACH SIDE, WERE FOUND PROTRUDING BEYON D THE WING SURFACE CAUSING MINOR DAMAGE TO THE UNDER SKING SURFACE OF THE SLAT. ALL SCREWS WERE TIGHTENED BACK. 2 L 7 2 4F 4 F RT A21EA E00063EN 20081124 NM 2008 11 24 CA081007004 1 20080929 G 2130 10010602 CIRCUIT CARD EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE CABIN PRESSURE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER DEPARTURE AT APPROX 1500`, BLEED NR 1 AND NR 2 FAILED EICAS MSGS APPEARED, AND QRH CARRIED OUT (RESET) BUT U NSUCCESSFUL. ACFT DID NOT PRESSURIZE, AND RETURNED TO BNA FOR MX. OTHER PNS AND SNS AFFECTED: 2 L 7 2 4F 4 F RT A56NM E00063EN 20081120 2008 11 20 CA081007005 4 20081007 G 3160 071015980301 CONTROLLER PILATS PC12 PC1247 7090552 EU PWA PT6 PT6A67 52043 NE MFD FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 100 100 (CAN) THE ABOVE MFD CONTROLLER IS A JOYSTICK TYPE CONTROL THAT ALLOWS THE CREW TO MAKE SELECTIONS ON THE MFD SCREEN IN T HE MFG APEX SYS. THE JOYSTICK FAILS TO MOVE THE CURSOR TO THE RT AS DISPLAYED ON THE MFD SCREEN. THE CONTROLLER WAS REPL ACED WITH A NEW ITEM THAT CLEARED THE PROBLEM THIS IS THE SECOND REPLACEMENT ON THIS ACFT SINCE NEW 150 HRS TT. 1 L 7 1 4T 4 T RT A78EU E26NE 20081126 EU 2008 11 26 CA081007006 1 20081007 G 2910 MS287786 O-RING BAG JETSTM JETSTM3112 1500220 EU GARRTT TPE331 TPE33110 29053 NE ROTOL R333 R333482F12 GL COUPLING FAILED W O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA (CAN) DURING GEAR DOWN LANDING CHECKS, ONLY NOSE GEAR LOCKED, BOTH MLG UNSAFE. REQUESTED LOW AND OVER-CYMM FSS CONFIRME D 3 GEAR DOWN. RE-POSITIONED TO A SAFE AREA AND PERFORMED ITEMS LISTED ON QRH. PUMPED GEAR DOWN MANUALLY, GEAR WAS CONFI RMED 3 DOWN AND LOCKED. LANDED, WITH NO STEERING AND LIMITED BRAKE USE. STOPPED ACFT ON TAXIWAY A. TOWED TO HANGER WITH PAX EMERGENCY SERVICES ON STANDBY FOR THIS INCIDENT. MAINT INSP CONFIRMED LT HYDR PUMP PRESSURE RETURN INLET BANJO COUP LING BASE O-RING HAD FAILED, CAUSING EXCESSIVE FLUID LOSS. REMOVED AND REPLACED DEFECTIVE O-RING WITH NEW. HYD SYS REP LENISHED GEAR, FLAP, STEERING, BRAKE SYSTEMS BLED, GEAR SWINGS C/O AND SYS F/C C/O SYS SERVICED AND L/C C/W. 2 L 7 2 4T 4 T RT BA15CAA E4WE 6 C P61GL 20081124 EU 2008 11 24 CA081007007 1 20080929 G 5310 350A38101832 CROSSBEAM SNIAS 350 AS350BA 8680817 EU ALLSN 250C 250C30 03013 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4692 702 (CAN) A BI DIRECTIONAL CROSS BEAM WAS SENT OUT FOR NDT INSPECTION AND A CRACK INDICATION WAS FOUND INBD RADIUS OF CROSS BEAM WHERE THE LAMINATED MOUNT ATTACHES. A SECOND NDT INSPECTION WAS PERFORMED WITH THE SAME RESULTS. 1 G 7 1 3U 3 U NC H9EU E1GL 20081124 CE 2008 11 24 CA081007008 1 20081007 G 3340 CM358910 SWITCH CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA TAXI LIGHT INOPERATIVE W O OTHER P NO WARNING INDICATION NR NOT REPORTED 1 CA 566 (CAN) TAXI LIGHT SWITCH FAILED WITH 566 HRS OF ACFT OPS FAULT WAS FOUND WHEN TRYING TO CHECK TAXI LIGHT FOR OPS. SWITCH WAS REPLACED 7 MONTHS AGO AND 566 HRS OF OPS. 1 H 7 1 3O 3 O NT 3A12 1E10 20081124 CE 2008 11 24 CA081007009 1 20081001 G 3397 903641241 C/BREAKER PANEL BEECH 200 B200 1152922 CE PWA PT6 PT642A NE COCKPIT BURNED W B A EMER. DESCENT UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) PILOTS REPORTED FLAMES AND FIRE FROM LOWER RT CORNER OF THE RT CIRCUIT BREAKER PANEL AND MADE AN EMERGENCY LANDING . THE CIRCUIT BREAKER FOR THE EDGE LIGHTED PANEL LIGHTS OPENED AS A RESULT OF THE SHORT AT 1 BULB BUT NOT BEFORE THE HEA T HAD BURNED PART WAY THROUGH THE EDGE LIGHTED PANEL AND STARTED TO HEAT THE OVER LYING CIRCUIT BREAKER PANEL. NO FURTHE R DAMAGE WAS NOTED. THIS EDGE LIGHTED PANEL WAS PREVIOUSLY INSPECTED AS PER THE MM ABOUT 565 HOURS AGO. 1 L 7 2 4T 4 T A24CE E4EA 20081124 SW 2008 11 24 CA081007010 1 20081002 G 3240 5011639 DISC SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 29073 NE MCAULY 4HFR34 4HFR34C652 NE BRAKE WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS BRAKE ASSEMBLY WAS REMOVED FROM ACFT ON THE RT - O/B GEAR FOR BRAKE WEAR BEYOND LIMITS. UPON TEAR DOWN THE L UGS WERE FOUND TO HAVE WORN APPROXIMATELY 40% WHILE THE RIM SIDE HAD MINIMAL WEAR AND THE RIM WAS RETURNED TO SERVICE. THIS TYPE OF WEAR IS NOT COMMON AS THEY WEAR CONSISTENTLY SIMILAR. FURTHER INVESTIGATION WILL BE ACCOMPLISHED IN ORDER TO POSSIBLY DETERMINE OTHER CAUSES AS TO WHY THE UNEVEN WEAR PATTERN. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 20081126 CE 2008 11 26 CA081008001 1 20080818 G 3220 FORK CESSNA 172 172N 2072434 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6816 (CAN) DURING A ROUTINE OPERATION, NR 2 INSP, A SUSPECTED CRACK WAS FOUND ON NLG FORK. EDDY CURRENT REVEALED A LARGE DEF LECTION IN THE SUSPECTED AREA. SUBSEQUENTLY THE INSP WAS CONDUCTED ON THE OPPOSITE SIDE OF THE NLG FORK WITH THE SAME RE SULTS. ADDITIONALLY FPI WAS ALSO DONE TO SHOW VISUALLY UNDER BLACK LIGHT. CRACKS WERE CLEARLY VISIBLE ON BOTH SIDES OF T HE FORK UNDER THE BLACK LIGHT. THE ACFT WAS REMOVED FROM SERVICE AND A NEW NLG FORK ASSY WAS ORDERED FROM MFG AND INSTAL LED UPON ARRIVAL. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20081124 GL 2008 11 24 CA081008002 1 20080923 G 2410 2224121400 BRACKET DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO ALTERNATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 715 (CAN) ON SEPTEMBER 2, 2008, DURING A ROUTINE 100 HOUR INSPECTION THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE CRACKED ON THE INSIDE RADIUS OF THE BRACKET RIGHT NEXT TO 1 OF THE 2 MOUNTING BOLT HOLES. THIS WAS THE SECOND CRACKED BRACKET F OUND ON THIS ACFT AND BOTH CRACKS HAVE BEEN LOCATED IN THE IDENTICAL LOCATIONS. 1 L 7 1 3O 3 O NT TA4CH E7SO 20081124 GL 2008 11 24 CA081008003 1 20080923 G 2410 2224121400 BRACKET DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO ALTERNATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 448 (CAN) ON MARCH 14, 2008, DURING A ROUTINE 100 HOUR INSPECTION THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE CRACKED ON THE INSIDE RADIUS OF THE BRACKET RIGHT NEXT TO 1 OF THE 2 MOUNTING BOLT HOLES. 1 L 7 1 3O 3 O NT TA4CH E7SO 20081124 SW 2008 11 24 CA081008006 1 20081007 G 5210 205D10282 WINDOW FRAME BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE JUMP DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 10 INCH CRACK FOUND AT UPPER LT CORNER OF WINDOW FRAME. 1 G 7 1 4U 4 U H4SW E22EA 20081124 NM 2008 11 24 CA081008007 1 20081008 G 5210 SB003T0023 PANEL DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE COCKPIT DOOR MISALIGNED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLEX IN LAV WALL IS CAUSING SIGNIFICANT IN-SERVICE MISALIGNMENT OF PONS INSTALLED IN LATCH HOUSING USING TTF-SB-03 T002-001. REFER TO PROTECTED "A" AD CF-2008-26R1 AND STC SA03-70, SB TTF-SB-03T002-001 REV "D". 2 H 7 2 4T 4 T RT A13NM E20NE 20081124 EA 2008 11 24 CA081009001 1 20081002 G 3810 5000120701 WATER HEATER CNDAIR CL601 CL6013A 8070802 EA FWD GALLEY DAMAGED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) ON CLIMB OUT SMOKE WAS OBSERVED COMING OUT OF THE FUEL CONTROL PANEL IN THE FORWARD GALLEY. THE WATER HEATER INSU LATION BLANKET IN THE FORWARD GALLEY HAD EVIDENCE OF HEAT DAMAGE. INSTALLATION OF THIS PART IN THE FORWARD GALLEY OF TH E ACFT IS A PART OF SUPPLEMENTAL TYPE CERTIFICATE ST09049SC. THE PART IN QUESTION HAS BEEN FORWARDED TO THE TSB. 2 L 7 2 4F RT A21EA 20081124 CE 2008 11 24 CA081009002 1 20080918 G 5753 S16612 SWITCH CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA TE FLAP DAMAGED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 5911 (CAN) THE FLAP SWITCH SHOULD SPRING BACK TO OFF POSITION WHEN PRESSURE IS RELEASED. THE PILOT SELECTED 20° OF FLAP TOOK PRESSURE OFF SWITCH BUT THE FLAPS EXTENDED TO 40° NEW SWITCH INSTALLED. 1 H 7 1 3O 3 O NT 3A12 E274 20081124 GL 2008 11 24 CA081009003 2 20081002 G 7323 23065123 GOVERNOR BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL TURBINE INOPERATIVE W O OTHER O OTHER NR NOT REPORTED 1 CA 1234 (CAN) BENDIX KING GOVERNOR NOT RESPONDING WHEN BEEPED, 1 G 7 1 3U 3 U H2SW E4CE 20081124 NM 2008 11 24 CA081009004 1 20081003 G 2421 ALX8521R ALTERNATOR ROBSIN R22 R22BETA 7640110 NM LYC O360 O360J2A 41514 EA INOPERATIVE W O OTHER O OTHER NR NOT REPORTED 1 CA 331 (CAN) ALTERNATOR LIGHT ILLUMINATED IN FLIGHT, ALTERNATOR CHECKED AND NOT CHARGING. 1 G 7 1 3O 3 O H10WE E286 20081124 NE 2008 11 24 CA081009005 2 20080929 G 7414 10600646201 MAGNETO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA 90 (CAN) ENGINE TACH FLUCTUATING, MAGNETO REPLACED. 1 G 7 1 3O 3 O H11NM 1E4 20081124 WP 2008 11 24 CA081009006 1 20080930 G 2435 BC3151004 STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA 359 (CAN) STARTER NOT ENGAGING. 1 G 7 1 3O 3 O H11NM 1E4 20081124 NM 2008 11 24 CA081009007 1 20081009 G 2781 651781823 SWITCH DECOTO BOEING 727 727247 138408F NM PWA JT8 JT8D15 52051 NE SLAT ACTUATOR FAILED W J A DUMP FUEL UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 47 (CAN) JUST AFTER DEPARTURE FROM YYZ, THE PILOTS NOTICED WHEN SELECTING FLAPS 5 TO FLAPS 2, THE LEADING EDGE FLAP INDICAT OR ON THE FORWARD PANEL WENT MOMENTARILY GREEN THEN BACK TO AMBER. THE LEADING EDGE INDICATOR ON THE REAR PANEL INDICAT ED THE NR 1 LEADING EDGE IN TRANSIT. FUEL WAS DUMPED IN ORDER TO REDUCE LANDING WEIGHT OF THE ACFT AND THE ACFT RETURNE D TO YYZ. MX TROUBLESHOT THE SYSTEM AND INSTALLED A JUMPER CABLE ON THE SLAT ACTUATOR TO ENABLE THE ACFT TO DEPART. 2 L 7 3 4F 4 F A3WE E2EA 20081124 NM 2008 11 24 CA081009008 1 20081008 G 2497 WIRE BOMBDR CL600 CL6002D15 NM GE CF34 CF348C5 30050 NE CHAFED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA (CAN) FLIGHT ATTENDANT REPORTED A BURNING ODOR IN THE CABIN. THE ACFT LANDED UNEVENTFULLY. THE CAUSE OF THE ODOR WAS T RACED TO CHAFED WIRE ABOVE THE FORWARD LAVATORY. 2 L 7 2 4F 4 F RT A21EA E00063EN 20081124 GL 2008 11 24 CA081009009 1 20080927 G 2497 WIRE KELLY DIAMON DA40 DA40 2990002 GL CONT IO360 IO360* 17025 CE ALTERNATOR BROKEN W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) A+ TERMINAL MELTED OFF ALTERNATOR AND LOOSE. PROBLEM CAUSED BY BROKEN TERMINAL ON A+ WIRE GOING TO ALTERNATOR. WI RE WAS ORIGINALLY VERY TIGHT CAUSING THE BREAKAGE, THEN IT ARCED CAUSING HEAT AND EVENTUAL FAILURE. 1 L 7 1 3O 3 O NT A47CE E1CE 20081126 NE 2008 11 26 CA081009010 2 20080929 G 7532 PN1422010 CLEVIS EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE BLEED VALVE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) (ENGINE INTAKE VARIABLE BLEED VALVE ACTUATOR) INTERFERENCE HAS OCCURRED BETWEEN THE SUBJECT CLEVIS LUG AND ADJACEN T HARDWARE. THE DAMAGE APPEARS TO BE A RESULT OF CONTACT WITH AN ADJACENT BOLT HEAD. ACTUATOR ASSY: P/N 8100-052, S/N WYGB1199 (CLEVIS: P/N 1422-010 [REF CMM 75-30-02, FIGURE 01, ITEM 010) 2 L 7 2 4F 4 F RT A57NM E00070EN 20081126 GL 2008 11 26 CA081009011 1 20081007 G 2720 2227271100 RUDDER PEDAL DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA COCKPIT WORN W K NONE O OTHER IN INSP/MAINT 1 CA 3498 (CAN) ACFT WAS INSPECTED BY MAINT TO REPLACE A DEFECTIVE RUDDER PEDAL ADJUSTING CABLE. UPON COMPLETION OF THE JOB IT WAS NOTICED THAT THE SLIDE ASSY WAS NOT ABLE TO MAKE FULL TRAVEL. CLOSER INSP FOR OTHER SYMPTOMS REVEALED THAT THE RUDDER C ABLE HAD WORN THROUGH THE S-TUBE THAT IS WELDED TO THE PEDAL ASSY. CABLE WAS EXPOSED THROUGH THE LWR BEND OF THE S-TUBE TO A POINT WHERE IT JAMMED IN ITS WEAR HOLE AND RESTRICTING THE SLIDE ACTION. THE PEDAL ASSY AND THE CABLE WERE REMOVED FOR CLOSER INSP AND REPLACEMENT PARTS ARE ON ORDER. WEAR ON THE S-TUBE BECOMES CRITICAL WHEN THE CABLE BECOMES VISIBLE FROM THE OUTSIDE OF THE TUBE. IT IS ALSO AN AREA THAT YOU WOULD NOT EXPECT THIS TO HAPPEN THEREFORE IT COULD BE OVERLOO 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 20081126 NM 2008 11 26 CA081010001 1 20080927 G 2820 LINE BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE FUEL SYSTEM CRACKED W O OTHER K E FLUID LOSS VIBRATION/BUFFET AP APPROACH 1 CA (CAN) EXPERIENCED A LT ENG FUEL LEAK DURING APPROACH/LANDING. MAINT IDENTIFIED AND REPLACED A CRACKED P/N BRH19082 FUEL PIPE. ON 28 SEP/08, ACFT WAS FERRIED. WHEN ACFT WAS ON TAXI INTO THE RAMP, ANOTHER ACFT BEHIND REPORTED FUEL POURING FR OM UNDER THE LT ENGINE. MAINT FOUND THAT PIPE WAS CRACKED AGAIN. SEVERAL FIRE LOOP BRACKETS WERE ALSO FOUND CRACKED. TH E LT ENG WAS REPLACED, S/N 13243 OFF, THIS ENG HAD JUST BEEN INSTALLED ON 2 SEP/08, AT TIME OF REMOVAL: TSI 55 HOURS, CS I 35 CYCLES. HIGH VISIBILITY EVENT BY THE FAA DUE TO FUEL LEAK. ENG 13243 IN FOR INVESTIGATION. TEST BED RUN CONFIRMED H IGH VIBRATION EMANATING FROM ACCY GEARBOX, WHEN ENGINE POWERED UP AN OIL LEAK EMANATED FROM THE GEARBOX AT FUEL PUMP LOC 2 L 7 2 4F 4 F TR A6WE E00061EN 20081124 NE 2008 11 24 CA081010002 2 20081009 G 7310 63E951 HOUSING GRIMES CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE FUEL FILTER LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) MX DISCOVERED NR 1 ENGINE FUEL FILTER ASSEMBLY LEAKING FROM THE TOP OF THE FILTER HOUSING. HOUSING IS EITHER CRAC KED AROUND TOP FITTING OR IS LEAKING THROUGH PRC AROUND FITTING. FUEL FILTER ASSEMBLY 4106T62P01 REF IPC 73-11-00 FIG 1 ITEM 110A INSTALLED. ENGINE TTSN: 26020 HOURS, CYCLES 21453. AFTT: 31453 HOURS, CYCLES: 26057 2 L 7 2 4F 4 F RT A21EA E15NE 20081124 EA 2008 11 24 CA081010003 1 20081010 G 2750 855D10011 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE RT WING TE FLAP UNSERVICEABLE W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA 10100 10100 (CAN) ON APPROACH, AND UPON INITIAL FLAP SELECTION THE CREW RECEIVED FLAP FAILURE CAUTION MSG. CREW CARRIED OUT A FLAP ZERO LANDING. CREW SAID LANDING WAS UNEVENTFUL. NO EMERGENCY DECLARED, NO CALL OUT REQUIRED. WILL UPDATE INFO AS RECE IVED. 2 L 7 2 4F 4 F RT A21EA E15NE 20081124 SW 2008 11 24 CA081010004 1 20081003 G 3040 HEATER GULSTM 680 680 0141602 SW PWC PW306 PW306C 52169 NE WINDSHIELD SMOKE W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA 613 (CAN) SMOKE DETECTED IN COCKPIT ON ENGINE STARTUP. PROBLEM ISOLATED TO LT WINDSHIELD. RECTIFIED BY REPLACEMENT OF PART. 1 H 7 2 3O 4 F 2A4 E35NE 20081124 EA 2008 11 24 CA081010005 1 20081002 G 5343 VALTBS112091 ATTACH FITTING DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA WING/MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION A AME FOUND THE WING GEAR/STRUT ATTACH FITTING TO BE CORRODED (LEVEL 3). 1 H 7 1 3T 4 T A806 E4EA 20081124 EA 2008 11 24 CA081010006 1 20081002 G 2731 C2T29A TORQUE TUBE DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA ELEVATOR TRIM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE 100 HOUR INSPECTION A AME FOUND THE ELEVATOR TRIM TORQUE TUBE TO BE CRACKED, PART WAS REPLACED AN D CUSTOMER WAS ADVISED. 1 H 7 1 3T 4 T A806 E4EA 20081124 EA 2008 11 24 CA081010007 1 20081002 G 3246 VALBVS12601 FITTING DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA MLG FLOAT SPLIT W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION A AME FOUND THE FLOAT FITTING TO HAVE TYPE 3 CORROSION THAT CAUSED FITTING TO SPLIT. FITTING REPLACED WITH NEW PART. 1 H 7 1 3T 4 T A806 E4EA 20081124 EA 2008 11 24 CA081010008 2 20081003 G 7414 4371 MAGNETO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA 156 (CAN) POOR MAG DROP, TIMING LIGHT FLICKERING BEFORE 25 DEGREES. MAGNETO REPLACED WITH A SERVICEABLE MAGNETO. 1 H 7 1 3O 3 O NT 3A12 1E10 20081124 EA 2008 11 24 CA081010009 2 20081003 G 7414 4371 MAGNETO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 156 (CAN) POOR MAG DROP. TIMING LIGHT FLICKERING BEFORE 25 DEGREES. REPLACED WITH SERVICEABLE MAGNETO. 1 H 7 1 3O 3 O NT 3A12 1E10 20081124 EA 2008 11 24 CA081010010 2 20081002 G 7321 SCREW DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA FCU CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION POST RUN UP THE AME FOUND THE IDLE NEEDED TO BE ADJUSTED. UPON LOOSENING IDLE SCREW JAM NUT IDLE SCREW FAILED DUE TO LEVEL 3 CORROSION. FCU REMOVED AND SENT FOR REPAIR. 1 H 7 1 3T 4 T A806 E4EA 20081124 SW 2008 11 24 CA081010011 1 20081010 G 3500 AS4857D01 TEE FITTING GULSTM 680 680 0141602 SW PWC PW306 PW306C 52169 NE OXYGEN SYSTEM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1251 (CAN) DURING MX WALK AROUND FOUND LT OXYGEN SYSTEM LEAKING. UPON INVESTIGATION FOUND TEE FITTING LOCATED AT LT FUSELAGE OXYGEN GAUGE CRACKED AT 2 POINTS. IT APPEARS THAT UPON ORIGINAL INSTALLATION OF FITTING IT WAS OVER TORQUED. FITTING REPLACED WITH NEW. LEAK CHECKS CARRIED OUT. SYSTEM FUNCTION CHECKED SERVICEABLE. 1 H 7 2 3O 4 F 2A4 E35NE 20081124 2008 11 24 CA081014001 1 20081010 G 6100 SHAFT PWA 118 PW118 NE PROPELLER CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) EIR PW100-0477 CRACKED PROPELLER SHAFT. 4 T E20NE 20081124 CE 2008 11 24 CA081014002 1 20081008 G 2730 07606861 CONTROL TUBE CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO MCAULY 2A34C C2A34C204 GL LT ELEVATOR GOUGED W O OTHER W INADEQUATE Q C NR NOT REPORTED 1 CA 9986 (CAN) THE BOLT PN AN21-10 ATTACHING THE LT ELEVATOR CONTROL CABLE PN 0510105-90 TO THE LT BELLCRANK CONTROL ARM ASSEMBLY PN 0760686-1 IS RUBBING ON THE LT BELLCRANK CONTROL TUBE SUPPORT PN 0760693-1. THE DAMAGE IS 0.039 DEEP, 1.750 LONG AN D 0.250 WIDE. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 20081124 CE 2008 11 24 CA081014003 1 20081009 G 2731 071250012 ACTUATOR CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL HORIZ STAB TRIM SEPARATED W O OTHER F FLT CONT AFFECTED LD LANDING 1 CA 100 (CAN) ACFT HORIZONTAL STAB TRIM JAM ON LANDING. ELEVATOR CONTROLS BECAME LIGHT. ACFT LANDED WITHOUT INCIDENT. UPON INS PECTION AT THE DOCK, THE PILOT FOUND THE HORIZONTAL STAB WAS COMPLETELY LOOSE, STAB COULD BE MOVED FULL TRAVEL UP AND D OWN WITH NO RESISTANCE FROM THE TRIM JACKS. MX FOUND THE TRIM JACK BARREL COULD BE SLID ON TO THE SCREW OF THE SCREW JA CK WITH HAND PRESSURE, WHEN NORMALLY THEY HAVE TO BE SCREWED ON TO THE ACTUATOR SCREW. BOTH BARRELS WERE FOUND TO HAVE THREADS ONLY ON 1 SIDE OF THE BARREL, INSTEAD OF COMPLETELY AROUND THE INSIDE OF THE BARREL. THE ACTUATORS WERE REPLACE D AND CESSNA DISTRIBUTOR CONTACTED DUE TO THE ACTUATORS IN QUESTION WERE ONLY 3 MONTHS OLD AND 100HRS. SINCE NEW TIME IN 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 20081124 NM 2008 11 24 CA081014004 1 20080917 G 5210 1700375200 SEAL EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE PAX DOOR GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) T FWD PAX DOOR AFT LATERAL SEAL (PN 170-03752-001) WAS FOUND GOUGED AT 3 LOCATIONS. PLEASE REFER TO THE ATTACHED P ICTURES FOR DETAILS, TYPICAL DAMAGE SEEN TO THE PAX/SERVICE DOOR CUTOUT SEAL RESTS. EMB HAS ISSUED A “TYPICAL” IC APPRO VAL THAT PERMITS PERMANENT BLENDING OF UP TO 20% THICKNESS. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081124 NE 2008 11 24 CA081014005 2 20081006 G 7322 87327003 ARM PIPER PIPER PA44 PA44180 7104402 SO LYC O360 LO360A1H6 42294 NE CARB HEAT SEPARATED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 379 (CAN) THE ACFT RETURNED TO THE RAMP WITH REPORTED RT CARB HEAT U/S. INVESTIGATION REVEALED THE WELD SECURING THE ACTUATO R ARM ONTO THE CARB AIR DOOR HAD BROKEN CAUSING THE ARM TO SEPARATE FROM THE SHAFT. THE WELD APPEARED TOO THIN IN COMPA RISON TO THE LT ENGINE CARB AIR DOOR ASSY. 1 L 7 2 3O 3 O A19S0 E286 20081124 SO 2008 11 24 CA081014006 1 20081006 G 7160 434179 GROMMET PIPER PIPER PA44 PA44180 7104402 SO LYC O360 LO360A1H6 42294 NE AIR BOX MISSING W O OTHER O OTHER NR NOT REPORTED 1 CA 379 (CAN) DURING A DEFECT RECTIFICATION ON THE CARB AIR DOOR ON THE RT ENGINE IT WAS DISCOVERED THAT THE LT ENGINE CARB AIR DOOR LOWER SHAFT SUPPORT BUSHING PN, 453-991 AND GROMMETT WERE MISSING. 1 L 7 2 3O 3 O A19S0 E286 20081126 CE 2008 11 26 CA081014007 1 20081001 G 3246 1368520629 BEARING BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE WHEEL FAILED W O OTHER S AFFECT SYSTEMS TX TAXI/GRND HDL 1 CA (CAN) LT MLG OTBD MAIN WHEEL ASSY BECAME DETACHED FROM THE AXLE ASSY, ONLY BEING HELD ON BY THE OUTER MAIN WHEEL AXLE NU T AND BRG CONE. INITIAL INVESTIGATION CONFIRMED THAT THIS WAS THE RESULT OF AN EXTREME BEARING FAILURE. FAILURE WAS TO SUCH EXTENT THAT IT ACTUALLY WELDED THE INNER BRG RACE PERMANENTLY TO THE AXLE AND HEAT TRANSFER TO THE NR2 WHEEL ALSO R ESULTED IN A BEARING BURN WHICH IS NOT SEVERE IN MATTER BUT IS AN INDICATION OF HOW FAR THE INITIAL FAILURE EXTENDED. DA MAGE REQUIRED REMOVAL OF THE LT GEAR LEG AND INSTALLATION OF A SERVICEABLE GEAR LEG. BOTH MAIN WHEEL ASSEMBLIES AFFECTE D WERE REPLACED. ACFT WAS THEN RETURNED TO SERVICE. ONE WHEEL ASSY WAS DESTROYED AND THE OTHER SENT OUT FOR TESTING. BEA 2 L 7 2 4T 4 T RT A24CE E26NE 20081126 SW 2008 11 26 CA081014009 1 20080904 G 3397 WIRE BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL AT NAV LIGHT CHAFED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) PILOT TURNS ON ALL REQUIRED BREAKERS FOR FLIGHT INCLUDING NAV LIGHTS. PRE LIFT-OFF THE PILOT NOTES THE BREAKER FOR THE NAV LIGHTS AT MIDPOINT. PILOT RESETS SWITCH AND LIFTS OFF. AS THE ACFT FLIES THROUGH 300 FT, THE PILOT TURNS ON TH E HEATER AND IN A FEW SECONDS SEES A MIST COMING FROM OVERHEAD PANEL. HEATER IS SWITCHED OFF THEN PILOT REALIZES ITS SMO KE FROM HOT WIRES. BATTERY, GENERATOR IS SWITCHED OFF AND ACFT RETURNS UNEVENTFUL TO THE TAKEOFF AREA. UPON INVESTIGATIO N, AN INITIAL SHORT IN THE NAVIGATIONAL LIGHTS CAUSED THE BREAKER TO TRIP. THE PILOT RESETS THE BREAKER WHICH CAUSES THE BREAKER POINTS TO WELD AND MAINTAIN CURRENT TO THE SHORTED NAV LIGHTS. THIS CAUSED THE WIRE FROM THE BUSS TO THE BREAKE 1 G 7 1 3U 3 U H2SW E4CE 20081124 CE 2008 11 24 CA081015001 1 20081006 G 2910 6000100184 LINE LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE HYD SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 3249 (CAN) RETURN LINE FROM HYDRAULIC RETURN FILTER TO HYDRAULIC RESERVOIR 1/2" CRACK AT 90 DEGREE BEND ON LINE. CAUSE, MAIN HYDRAULIC SYSTEM RETURN LINE CHATTERING AGAINST A HYDRAULIC LINE WHICH GOES FROM THE AUXILIARY HYDRAULIC PUMP TO AUXILIA RY PUMP INLINE FILTER. 2 L 7 2 4F 4 F RT A10CE E35NE 20081124 EA 2008 11 24 CA081015002 2 20081006 G 8530 AEL11795 SPRING BNORM BN2 BN2B27 7080227 EU LYC O540 O540E4C5 41532 EA HARTZL HCC2Y HCC2YK2 GL INTAKE VALVE BROKEN W O OTHER O OTHER NR NOT REPORTED 1 CA 333 (CAN) DURING INSPECTION OF LYCOMING SB 388C FOUND BROKEN INNER SPRING PART NR AEL11795 ON INTAKE AND EXHAUST VALVE. 1 H 7 2 3O 3 O A17EU E295 5 C P920 20081124 NE 2008 11 24 CA081015003 2 20081015 G 7497 BL60064620 WIRE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO MISROUTED W O OTHER O OTHER NR NOT REPORTED 1 CA 1287 (CAN) TACH WIRE CHAFING ON TACH POINT CONNECTOR TACH WIRES INCORRECTLY ROUTED. TCM SB663A NOT COMPLIED WITH FOR WIRE RO UTING. LAST MX ON MAGNETO WAS PRO AERO. MAGNETO WAS REMOVED DUE TO ENGINE/ACFT OVERSPEED. 1 G 7 1 3O 3 O H11NM 1E4 20081124 NE 2008 11 24 CA081015004 2 20081015 G 7497 10400586 WIRE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE TACH MISROUTED W O OTHER O OTHER NR NOT REPORTED 1 CA 235 (CAN) TACH WIRES INCORRECTLY ROUTED COIL PRIMARY WIRE INCORRECTLY ROUTED. TCM SB663A NOT COMPLIED WITH FOR WIRE ROUTING. MAGNETO WAS REMOVED FOR ENGINE/ACFT OVERSPEED. 1 G 7 1 3O 3 O H11NM 1E4 20081124 NE 2008 11 24 CA081015005 2 20081015 G 7497 10400586 WIRE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE TACH PINCHED W O OTHER O OTHER NR NOT REPORTED 1 CA 90 (CAN) TACH WIRE WAS PINCHED BETWEEN HOUSING AND CAPACITOR TACH WIRES INCORRECTLY ROUTED TCM SB663A NOT COMPLIED WITH FOR WIRE ROUTING MAGNETO WAS REMOVED FOR FLUCTUATING ENGINE TACH NEEDLE . 1 G 7 1 3O 3 O H11NM 1E4 20081124 EA 2008 11 24 CA081015006 2 20081015 G 7497 10400586 WIRE ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA TACH CHAFED W O OTHER O OTHER NR NOT REPORTED 1 CA 151 (CAN) TACH WIRES CHAFED THROUGH AND GROUNDING TO THE COIL PRIMARY CONNECTOR. TACH WIRES INCORRECTLY ROUTED TCM SB663A N OT COMPLIED WITH FOR WIRE ROUTING. VERY HIGH RESISTANCE FOUND BETWEEN THE TERMINALS OF THE TACH POINTS, WHEN CLOSED 120 0-1500 OHMS, PROBLEM IS BLACK COATING ON TACH POINT ARM CAUSING A HIGH RESISTANCE. MAGNETO REMOVED FROM ACFT BECAUSE IT WANTED TO OVERSPEED. 1 G 7 1 3O 3 O H11NM E295 20081124 NM 2008 11 24 CA081016001 1 20081010 G 2781 1702286A SENSOR EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE FLAP SKEW INOPERATIVE W O OTHER J WARNING INDICATION AP APPROACH 1 CA 1688 (CAN) FLIGHT WAS INBOUND WHEN THE CREW HAD A FAILURE ON SLAT/FLAP 1 SELECTION. ALSO SPOILER FAULT, AOA FAIL AND SHAKER ANTICIPATED CAS MSGS. THE ACFT LANDED AND TAXIED TO THE GATE WITH HOT BRAKES. FOUND OPEN CIRCUIT BETWEEN PINS 2 AND 4 OF THE LT OB SKEW SENSOR. REPLACED SENSOR AS PER MM 27-83-01, CHECKED SERVICEABLE. ALL OTHER FAULTS CORRELATED TO SLAT FAILURE. 2 L 7 2 4F 4 F RT A56NM E00063EN 20081124 NM 2008 11 24 CA081016002 1 20081006 G 2781 1702286A SENSOR EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE SLAT SKEW FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH, WHEN FLAP 2 SELECTED, EICAS SLAT FAIL MSG. QRH CARRIED OUT. UNEVENTFUL LANDING. SKEW SENSOR 2 AND 3 AFFECTED AND REPLACED PER AMM 27-83-01. OPS CHECK SERVICEABLE. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081126 EA 2008 11 26 CA081016003 1 20081010 G 4930 MS29513021 O-RING CNDAIR CL601 CL6012A12 1900303 EA GE CF34 CF348E5A1 30062 NE EMI FILTER FAILED W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA 2790 (CAN) ACFT, PRIOR TO ENG START APU HAD AN UNCOMMANDED SHUTDOWN. WHILE CARRYING OUT COCKPIT TROUBLESHOOTING PILOTS OBSERV ED APU BOOST PUMP FAIL LIGHT WAS ILLUMINATED. APU BOOST PUMP WAS SUSPECT BECAUSE IT HAD JUST BEEN CHANGED THE PREVIOUS D AY FOR SAME SNAG. BOOST PUMP ELECTRICAL CONNECTOR MALE PINS WERE FOUND CHARRED AND MELTED. FEMALE PORTION OF CONNECTOR WAS ALSO FOUND CHARRED AND FUEL SOAKED. SUSPECT O-RING THAT PREVENTS FUEL FROM ENTERING CONNECTOR HAD FAILED ALLOWING FU EL TO DEGRADE THE INSULATION MATERIAL TO THE POINT WERE THE PINS SHORTED OUT. A NEW EMI FILTER HARNESS AND BOOST PUMP WE RE INSTALLED AND ACFT RETURNED TO SERVICE. FYI THE APU BOOST PUMP FUEL IS USED TO COOL. APU LUBRICATING OIL. WITH NO F 2 L 7 2 4F 4 F RT A21AE E00063EN 20081124 NE 2008 11 24 CA081016004 2 20081008 G 7310 10608486 HOSE BOEING 727 727225 1384077 NM PWA JT8 JT8D15 52051 NE FUEL SYSTEM LEAKING W D RETURN TO BLOCK K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) DURING DEPARTURE OF THE ACFT PRIOR TO ENGINE START, FUEL WAS NOTICED LEAKING FROM NR 3 ENGINE. MX REQUESTED NORMA L ENGINE START TO VERIFY FUEL LEAK. ENGINE WAS SHUT DOWN, AND ACFT TOWED BACK TO GATE FOR FURTHER INVESTIGATION. THE F UEL HOSE ASSEMBLY WAS R&R WITH A SERVICEABLE ASSEMBLY. ENGINE GROUND RUN WAS CARRIED OUT AND LEAK CHECKED WITH NO FURTH ER LEAKS OBSERVED. THE ACFT WAS RETURNED TO SERVICE. 2 L 7 3 4F 4 F A3WE E2EA 20081124 EA 2008 11 24 CA081016005 1 20081014 G 2751 601R930301 TRANSMITTER CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE FLAP POSITION FAILED W O OTHER O OTHER CL CLIMB 1 CA (CAN) CLIMBING THROUGH 12000 FT AT 250 KIAS ACFT NOSED OVER AS FLAPS WENT TO AT LEAST 25 DEGREES AND AUTOPILOT KICKED OF F. ACFT SLOWED TO 200 KIAS WHILE RETURNING TO DEPARTURE AIRPORT. FLAPS CONTINUOUSLY CYCLED FROM 0 TO 12 DEGREES. CIRC UIT BREAKERS 1F4 AND 2F4 WERE PULLED. A 0 DEGREE FLAP LANDING WAS PERFORMED. MX REPLACED THE FLAP POSITION TRANSMITTER AND THE SKEW DETECTION HARNESS PN K601R50533-3. AFTT: 27877:46, CYCLES: 23108. 2 L 7 2 4F 4 F RT A21EA E15NE 20081126 NM 2008 11 26 CA081016006 1 20081008 G 2782 1703911 ACTUATOR EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE NR 4 SLAT MALFUNCTIONED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA 4135 (CAN) SLAT FAIL ON APPROACH CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT. T/S IAW FIM, SLAT INHIBIT CLEARED, O PS CHECK PASSED. CONSIDERED TRANSITORY CONDITION OF THE SLAT CONTROL SYS. 2 SLAT ACTUATORS REPLACED: LT SLAT ACT POS 04L REPLACED, P/N S/N AND TIMES GIVEN ABOVE. ALSO, RT NR 5 SLAT ACTUATOR REPLACED, P/N 1703909, S/N 0174, FH: 8052, FC: 366 5. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081126 2008 11 26 CA081016007 2 20081015 G 7414 D6RN3200 MAGNETO RT ENGINE INOPERATIVE W O OTHER R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA (CAN) DURING PREFLIGHT RUN-UP RT ENG, RT MAGNETO EXPERIENCED EXCESSIVE DROP AND WAS RUNNING ROUGH. UPON INVESTIGATION OF THE MAGNETO IT WAS FOUND THAT THE DISTRIBUTOR GEAR BUSHING HAD WORN IN THE DISTRIBUTOR BLOCK HSG CAUSING A MISS FIRING CONDITION. MAGNETO WAS REPLACED. 20081126 NM 2008 11 26 CA081016008 1 20081003 G 7830 65378786 SWITCH BOEING 727 7272Q6 138407V NM PWA JT8 JT8D17 52049 NE THRUST REVERSER INOPERATIVE W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) ON CLIMB OUT, NR 3 ENGINE THRUST REVERSER OPERATING LIGHT ILLUMINATED THROUGH 5000 FT. THE ACFT RETURNED TO THE AI RPORT. THE NR3 ENG THRUST REVERSER WAS DEACTIVATED AND MEL APPLIED. UPON REACHING THE DESTINATION, THE NR3 ENGINE THRUST REVERSER SWITCH WAS REPLACED, ENGINE RUN CARRIED OUT AND THE THRUST REVERSER WAS FUNCTIONALLY CHECKED AS SERVICEABLE. T HE DEFERRAL WAS CLEARED AND THE ACFT WAS RETURNED TO SERVICE. 2 L 7 3 4F 4 F RT A3WE E2EA 20081126 NM 2008 11 26 CA081016009 1 20081010 G 2797 19019566401 WIRE HARNESS EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE LE SLAT DEFECTIVE W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA (CAN) SLAT FAIL MESSAGE ON FLAP 5 SELECTION ON APPROACH. CREW CARRIED OUT A MISSED APPROACH, QRH WAS FOLLOWED AND LANDED UNEVENTFULLY ON SECOND TRY. SLAT HARNESS REPLACED, OPS TEST CARRIED OUT IAW AMM 27-80-00-710-801A, NO FAULTS NO EICAS M ESSAGES. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081126 CE 2008 11 26 CA081016011 1 20081010 G 2720 1295240823 TORQUE TUBE BEECH 1295240821 BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE RUDDER CONTROL BROKEN W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 17702 (CAN) RUDDER PEDALS LINKAGE (UNDER FLOOR) - LT TORQUE TUBE BROKEN JUST INBD OF THE LT RUDDER PEDAL BLOCK. RUDDER TORQUE TUBE FAILURE STARTED AT TAPER PIN HOLE USED TO SECURE THE RUDDER PEDAL ASSY BLOCK TO THE SHAFT. FAILURE APPEARS TO BE FR OM AN OVERLOAD CONDITION WITH AN INITIAL CRACK AND THEN A SECONDARY CRACK AT ABOUT 90 DEGREES. A THIRD CRACK ALSO FOUND PARALLEL TO INITIAL CRACK. FAILURE OF THIS TYPE WOULD BE HARD TO PICK UP ON A VISUAL INSP AS EARLY FAILURE TAKES PLACE I N AN AREA NOT VISIBLE UNTIL UNIT IS DISMANTLED. ONCE FAILURE PROGRESSED TO COMPROMISE THE TORSION ABILITY OF THE SHAFT I T WOULD SPREAD RAPIDLY TO COMPLETE FAILURE. COMPLETE RUDDER AND STEERING SYS WAS INSPECTED TO DETERMINE IF RELATED SYS 2 L 7 2 4T 4 T RT A24CE E26NE 20081124 EA 2008 11 24 CA081016012 2 20080925 G 7230 COMPRESSOR BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA ENGINE SEIZED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ACFT WAS EN ROUTE WHEN THE LT ENGINE LOST POWER. THE CREW COMPLETED EMERGENCY PROCEDURES, SECURED THE ENGINE AND FEATHERED THE PROPELLER. THEY DECLARED AN EMERGENCY AND CONTINUED TO DESTINATION, WHERE THE ACFT PERFORMED A SINGLE ENG INE LANDING. POST FLIGHT INSPECTION REVEALED A SEIZED COMPRESSOR AND OIL FILTER CONTAMINATION. THE ENGINE WILL BE REMO VED AND FORWARDED TO STANDARD AERO FOR INVESTIGATION AND REPAIR. 2 L 7 2 4T 4 T RT A24CE E4EA 20081124 NE 2008 11 24 CA081016014 2 20081002 G 7321 FUEL CONTROL GULSTM 200 200 4500308 NM PWC PW306 PW306A 52165 NE ENGINE MALFUNCTIONED W D RETURN TO BLOCK X J ENGINE FLAMEOUT WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) 2 TO 3 MINUTES AFTER ENGINE START, IT FLAMED OUT UNCOMMANDED. NO FAULT CODES WERE RECORDED ON THE FADEC. INSPECT ION FOUND THE FAN FREE TO ROTATE WITH NO EVIDENCE OF INGESTION. THE PILOT MOTORED THE ENGINE AND THEN PERFORMED AN ENGI NE START. THE BOOST PUMP AND MOTIVE FLOW WERE OPERATING NORMALLY. THE ACFT IS SCHEDULED TO BE FLOWN TO BASE FOR MX. P& WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 L 7 2 4F 4 F RT A53NM E35NE 20081124 NE 2008 11 24 CA081016015 2 20081002 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE FIRE W E F B ENGINE SHUTDOWN ACTIVATE FIRE EXT. EMER. DESCENT A R J FLAME/FIRE PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING FLIGHT, THE PILOT SAW FLAMES COMING OUT OF THE ENGINE EXHAUST BEFORE LOSING POWER. HE DECLARED EMERGENCY A ND DIVERTED THE FLIGHT TOWARDS A NEARBY AIRPORT. HE WAS NOT ABLE TO MAKE THE AIRPORT AND HE WAS FORCED TO LAND ON A ROA D. THE PILOT WAS NOT INJURED AND THE ACFT SUFFERED NO DAMAGE. THE ACFT WAS LATER TOWED TO THE AIRPORT WHERE FAA IS INV ESTIGATING. THE ENGINE WILL BE REMOVED AND FORWARDED TO STANDARD AERO FOR INVESTIGATION. 1 H 7 1 3T 3 T A37CE E4EA 20081106 2008 11 6 CA081017001 4 20081012 G 8300 3022375 SEAL BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA ACCESSORY G/B FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 7524 7524 (CAN) PILOTS SHUT DOWN NR 1 ENGINE, DUE TO OIL PRESSURE FLUCTUATION AND OIL PRESS. ANNUNCIATOR ILLUMINATION. ACFT RETURN ED TO YXS MX BASE. OIL LOSS WAS FOUND TO BE COMING FROM THE HP PUMP DRAIN. OIL SEAL REPLACED, OIL CONSUMPTION ELIMINATE D. EXPLORATORY WORK COMPLETED AS PER PRATT AND WHITNEY MX MANUAL. ACFT RELEASED AS PER PRATT AND WHITNEY MX MANUAL PUTT ING IN PLACE BOTH OIL FILTER/SCREEN AND CHIP DETECTOR INSPECTIONS. 2 L 7 2 4T 4 T RT A24CE E4EA 20081106 EA 2008 11 6 CA081017002 1 20081007 G 6120 8210004 CSU DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL RT ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 1525 (CAN) THE ACFT WAS IN CRUISE FLIGHT WHEN THE TORQUE ON THE RT ENGINE SURGED AND THE PROPELLER BEGAN TO FEATHER. AS THE P OWER WAS BROUGHT BACK THE PROPELLER STOPPED FEATHERING. A PRECAUTIONARY ENGINE SHUTDOWN WAS PERFORMED AND THE ACFT RETUR NED TO BASE WITHOUT FURTHER INCIDENT. THE ENGINE AND ASSOCIATED SYSTEMS WERE TROUBLESHOT, WHICH DETERMINED THAT THE PROP ELLER GOVERNOR WAS AT FAULT. THE GOVERNOR WAS CHANGED, A GROUND RUN AND A TEST FLIGHT WERE PERFORMED WITH NO FURTHER PRO BLEMS. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081106 NM 2008 11 6 CA081017003 1 20081007 G 5720 190933321001 FAIRLEAD EMB ERJ190 ERJ190100IGW 3260408 NM DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT WING AILERON FAIRLEAD BRACKETS. REMOVAL OF THE PLASTIC FAIRLEADS FOUND THAT THE CABLES DID NOT SIT ROUGHLY IN T HE MIDDLE OF THE BRACKET HOLES. COMPARISON OF THE BRACKETS ON MSN 19000049 TO OTHER EMBRAER E190’S IT WAS SUSPECTED THAT THE WRONG BRACKETS HAVE BEEN INSTALLED FROM FACTORY. PICTURES ATTACHED OF THE BRACKETS INSTALLED ON MSN 19000049 AS REF ERENCE. PER E190 SRM 57-50-00 FIGURE 45A THE CORRECT BRACKETS ARE 190-933321-001, 190-93298-001, 190-93298-001 AND 190- 93318-001 (FROM IB MOST TO OB MOST BRACKETS). 2 L 7 2 4F RT A57NM 20081106 WP 2008 11 6 CA081017004 2 20081017 G 7230 31081822 BLADE NORMALAIR GARRTT TPE331 TPE33110UA 01514 WP IMPELLER DAMAGED W D RETURN TO BLOCK E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 4210 4210 (CAN) IT WAS NOTICED ON A GROUND RUN AFTER THE ENGINE WAS INSTALLED THAT THERE WAS A SQUEALING NOISE COMING FROM THE ENG INE. THE ENGINE WAS REMOVED AND FORWARDED TO THE ENGINE SHOP FOR EVALUATION. UPON DISASSEMBLY THE NR 1 IMPELLER WAS FOUN D TO HAVE A PIECE OF THE BLADE MISSING. THE NR 1 IMPELLER HAS NO OTHER DAMAGE EXCEPT WHERE THE BLADE PIECE IS MISSING. T HE NR 1 IMPELLER WILL BE FORWARDED TO A METALURGY FACILITY FOR EVALUATION TO DETERMINE WHY THE BLADE PIECE BROKE OFF. TH ERE WAS SUBSTANTIAL DAMAGE TO THE ENGINE FROM THE IMPELLER BLADE PIECE. 4 T E4WE 20081106 EA 2008 11 6 CA081017005 1 20081017 G 2910 AE4760H0592055 LINE CNDAIR CL600 CL600* 1900302 EA GE CF34 CF343A2 30067 NE NR 2 EDP BURST W O OTHER K S FLUID LOSS AFFECT SYSTEMS CR CRUISE 1 CA (CAN) AFTER TAKEOFF IN CRUISE AND ON THE WAY NR 2 HYD PRESS LOST MASTER CAUTION ON REPORT BY THE CAPTAIN, HE STILL HAD H IS NR 1 AND NR 3 HYD SYSTEM. ACFT LANDED SAFELY WITHOUT ANY EMERGENCY REQUEST. NR 2 ENGINE HYD PUMP OUTLET LINE FOUND BU STED, LINE REPLACED. NR 2 HYD PUMP CHANGED AS MTCE PREVENTIVE AND NR 2 HYD FILTER CHECKED FOR FOD. NOTHING WAS FOUND. 2 L 7 2 4F 4 F RT A21EA E15NE 20081106 SW 2008 11 6 CA081017006 1 20080925 G 5302 214001920101 HORN BELL 214 214B1 1182105 SW LYC T55 T5508D 41555 NE ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2034 (CAN) BOTH `EARS` (LT & RT) OF THE HORN TO WHICH THE ELEVATORS ATTACH CRACKED. COMMON PROBLEM WITH THESE HELICOPTERS. SE NT A PREVIOUSLY CRACKED HORN TO BELL HELICOPTER FOR ENGINEERING ANALYSIS, BUT HAVE NOT HEARD ANY RESULTS YET. 2 G 7 1 4U 4 U H6SW E4NE 20081106 GL 2008 11 6 CA081017007 2 20081017 G 7323 23065123 GOVERNOR BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL ENGINE MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA 1683 (CAN) UPON REMOVAL OF THE GOVERNOR IT WAS NOTED THAT THE DRIVE GEAR HAD COME SEPARATED. ALL PARTS WERE FOUND IN THE DRIV E GEAR FOR THE GOVERNOR. THERE WAS DIFFICULTY GETTING FULL RANGE OF THE GOVERNOR, COULD NOT ADJUST FOR 100 PERCENT ON TH E GROUND. THE DRIVE GEAR USUALLY HAS A BONDING MATERIAL ON THE END OF THE WASHERS THAT WAS NO LONGER THERE. THE GOVERNOR WAS CHANGED AND FUNCTIONALLY CHECKED SERVICEABLE. 1 G 7 1 3U 3 U H2SW E4CE 20081106 SW 2008 11 6 CA081017008 1 20081003 G 5302 204032806079A LONGERON BELL 204 204B 1181404 SW LYC T53 T5311B 41549 NE TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A VISUAL INSPECTION OF THE ACFT THE AME NOTICED A CRACK IN THE UPPER LT TAILBOOM LONGERON APROX. 3 INCHES A FT OF THE TAILBOOM ATTACHMENT FITTING. ACFT GROUNDED FOR REPAIRS. 1 G 7 1 4U 4 U H1SW E1EA 20081106 CE 2008 11 6 CA081020001 1 20081003 G 5551 MOUNT CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL RUDDER CONTROL MISINSTALLED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) METAL FILINGS WERE FOUND UNDER THE RUDDER SERVO DUE TO THE MOUNTING STRUCTURE HAVING BEEN INSTALLED OFFSET FROM TH E FACTORY. THIS CAUSED THE RUDDER CABLE TO EXIT THE DRUM ON AN ANGLE AND RUB THE CAPSTAN. THE SERVO WAS REPLACED AND A P ERMANENT FIX IS SCHEDULED FOR MAR. 09 AT CESSNA CITATION SERVICE CENTER. PICTURES ARE AVAILABLE. 1 L 7 2 4F 4 F RT A1WI E3GL 20081106 CE 2008 11 6 CA081020002 1 20081011 G 3213 TORQUE LINK BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6035 (CAN) DURING REGULAR MX, A MECHANIC NOTICED A CRACK ON THE UPPER TORQUE LINK OF THE LT MLG. THE TORQUE LINK WAS REPLACED AND ACFT RETURNED TO SERVICE. THE RT MLG TORQUE LINKS WERE INSPECTED WITH NO FAULTS FOUND. 1 L 7 2 3T 4 T A14CE E4EA 20081106 CE 2008 11 6 CA081020003 1 20081019 G 8011 MMU6001 STARTER CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE BROKEN W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) SNAG REPORTED THAT ACFT WOULD NOT START. UPON INVESTIGATING IT WAS NOTED THAT THE STARTER HOUSING WHERE IT ATTACHE S TO ENGINE WAS BROKEN. ALSO NOTED THAT THE BENDIX DRIVE TEETH WERE MISSING/SHEARED OFF. ENGINE CASE INSPECTED FOR DAMAG E, NONE FOUND NEW STARTER INSTALLED AND FUNCTION CHECKED SERVICEABLE. A CHECK ON STARTER SOLENOID SHOWED NO FAULTS. SUS PECT STARTER WAS RE-ENGAGED BY PILOT AFTER ENGINE WAS RUNNING. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 20081222 EU 2008 12 22 CA081020004 1 20081002 G 6720 350A21136324 BRACKET SNIAS 350 AS350* EU TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) A US OPERATOR HAS REPORTED 7 CASES OF THE RT TAIL ROTOR BELLCRANK MOUNTING BRACKET CRACKING. ALL THESE ACFT HAVE LIMITED LT PILOT MODIFICATION STC SH96-32 (FAA STC SR00429NY). LIMITED HAS ISSUED A SB ECL-122 REQUIRING AN INSP BEFORE NEXT FLIGHT REPEATED AT 50 HOURS THEN EVERY 100 HOURS. 1 G 7 1 3U H9EU 20081106 GL 2008 11 6 CA081020005 3 20081017 G 6114 HCD4N3C SEAL BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL PROPELLER WORN W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 3135 (CAN) DURING WALK AROUND, RT PROPELLER NOTED TO HAVE OIL DRIPPING FORM THE BLADE FACES. SOME OIL WAS NOTED TO BE ON THE UPPER ENGINE COWL, HOWEVER THE REST OF THE ENGINE WAS DRY. PROP SPINNER WAS REMOVED, INSIDE OF SPINNER WAS DRY AS WELL. GROUND RUN CARRIED OUT WITH SPINNER REMOVED, AND OIL WAS NOTED TO BE LEAKING FROM THE FRONT OF THE PROP CYLINDER, THE PR OP HAD TO BE EXERCISED FROM REVERSE, FINE PITCH AND FEATHER TO GET IT TO SHOW ANY LEAKAGE, THE LEAK WAS COMING FROM THE PITCH CHANGE ROD AND REVERSE ADJUST LEVER, THE MAJORITY OF THE OIL LEAKAGE ENDED UP ON THE BLADES ONLY, THE CYLINDER DID NOT SHOW VERY MUCH OIL LEAKAGE AT ALL, THE OIL SEEMED TO JUST SLING OUT ONTO THE BLADES AND A LITTLE BIT ON THE UPPER C 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 20081106 SW 2008 11 6 CA081020006 1 20081019 G 3230 KRP5064 BEARING FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE MLG DAMAGED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) UPON TAKEOFF THE CREW REPORTED THAT THE RT GEAR WOULD NOT REMAIN LOCKED. ACFT RETURNED TO BASE AND UPON MX INSPECT ION IT WAS FOUND THAT THE UP-LOCK HOOK BEARING AND ATTACHING HARDWARE WERE MISSING. IT WAS ALSO NOTED THAT THE UP-LOCK H OOK SHAFT ATTACH POINTS HAD BEEN MARRED. THIS LEADS US TO BELIEVE THAT THE BEARING WAS INSTALLED AND EITHER THE BEARING OR BOLT FAILED. FAILED PARTS WERE REPLACED - GEAR SWINGS CARRIED OUT AND ACFT RETURNED SERVICE. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081106 2008 11 6 CA081020007 4 20081019 G 2330 3042865102 ELECTRICAL BOX BOEING 737 737* NM GE CFM56 CFM567B24 NE SEAT ROW 16ABC ODOR W H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) FLIGHT ATTENDANTS NOTICED ELECTRICAL ODOR AT ROW 16 AND SHORTLY AFTER THE ROW 16ABC MALFUNCTIONED. LIVETV SYSTEM S HUT OFF IN FLIGHT DECK AND FLIGHT ATTENDANT STATION. THE SEB P/N 3042865-102 S/N 1792 WAS REMOVED. THIS SDR WILL BE UPDA TED WHEN SEB TEARDOWN INFORMATION IS AVAILABLE. 2 L 7 2 4F 4 F RT A16WE E00055EN 20081219 SW 2008 12 19 CA081020008 1 20081009 G 5610 2621126005 WINDSHIELD SWRNGN SA226 SA226T 8780122 SW GARRTT TPE331 TPE3311 01514 WP COCKPIT CRACKED W B EMER. DESCENT O OTHER CR CRUISE 1 CA 177 (CAN) DURING CRUISE FLIGHT THE LT COCKPIT WINDSHIELD GLASS CRACKED WITH AN EXPLOSIVE BANG. THE CREW IMMEDIATELY DESCEND ED AND REDUCED CABIN PRESSURE TO AVOID THE POSSIBILITY OF THE WINDOW GLASS BLOWING OUT. THE WINDOW WAS INSTALLED ON APR IL 11, 2006 AND HAD A TOTAL OF 177 HOURS SINCE OVERHAUL AND INSTALLATION. THE ACFT WAS IN THE USA AT THE TIME OF THE OC CURRENCE AND THE ACFT WAS FLOWN TO ITS INTENDED DESTINATION AS IT WAS ONLY ABOUT 30 MINUTES FROM THE DESTINATION AT THE TIME OF OCCURRENCE. THE WINDOW WAS REPLACED BY APPROPRIATELY RATED FAA REPAIR STATION. THE WINDOW WILL BE SENT TO THE MANUFACTURER FOR WARRANTY AND EXAMINATION. 2 L 7 2 4T 3 T RT A5SW E3WE 20081229 SW 2008 12 29 CA081020009 1 20081007 G 3244 196K089 TIRE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33110U 29066 NE MCAULY 4HFR34 4HFR34C652 NE MLG SEPARATED W O OTHER C F.O.D. TX TAXI/GRND HDL 1 CA (CAN) DURING GROUND HANDLING PROCEDURES THE NR2 MAIN WHEEL WAS FOUND TO BE SHREDDED AND THE TREAD PORTION OF THE TIRE MI SSING. THIS TIRE WAS A RECAPPED TIRE RECEIVED FROM A CERTIFIED FAA REPAIR STATION. THE TIRE WHEN IT SHREDDED CAUSED DAM AGE TO THE ACFT FLAP AND SURROUNDING WW WHICH REQUIRED REPLACEMENT OF THE FLAP AND REPAIR OF THE WW AREA. MAINT REPAIRE D THE ACFT AND REPLACED THE TIRE. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 20081106 SO 2008 11 6 CA081020010 1 20081015 G 7930 FITTING PIPER PA31T PA31T2 7103127 SO PWA PT6 PT6A135 52043 NE HARTZL HCB3T HCB3TN3 GL OIL PRESS LINE FAILED W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 59 (CAN) DURING TAXIING OF THE ACFT, THE CREW NOTED THE ANNUNCIATOR FOR OIL PRESSURE ON THE LT ENGINE CAME ON. THEY SHUTDOW N THE LT ENGINE AND TAXIED THE ACFT USING 1 ENGINE BACK TO THE HANGER. AFTER INSPECTION, IT WAS FOUND THAT THE HOSE ASSE MBLY FROM THE ENGINE OIL COOLER TO THE ENGINE HAD FAILED AND WAS LEAKING ENGINE OIL FROM WHERE THE HOSE IS SECURED INTO THE FITTING ASSEMBLY ON THE HOSE ASSEMBLY. THE HOSE ASSEMBLY WAS REPLACED WITH A NEW HOSE ASSEMBLY. THE ENGINE CHIP DETE CTOR AND ENGINE FILTER WAS INSPECTED WITH NO FAULTS FOUND. THE WAS SERVICED WITH OIL AND SATISFACTORY OPS AND LEAK CHECK S WHERE CARRIED OUT WITH NO FAULTS FOUND. THE HOSE ASSEMBLY WAS REPLACED PRIOR BECAUSE THE HOSE ASSEMBLY TIME LIMIT WAS 1 L 7 2 3T 4 T RT A8EA E4EA 6 C P15EA 20081107 WP 2008 11 7 CA081020011 1 20081016 G 7714 TACHOMETER ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 CA (CAN) DURING DESCENT FROM ALTITUDE TO BEGIN LOW LEVEL FLIGHT FOR PIPE LINE SURVEILLANCE AT APPROX. 75 KNOTS INDICATED AI RSPEED AND VSI AT APPROX. 500 FPM, THE ENGINE RPM TACH INDICATED ENGINE OVERSPEED WELL ABOVE 110%. ALL OTHER ENGINE PARA METERS REGISTERED WITHIN LIMITS, INCLUDING THE ROTOR RPM TACH. NO WARNING OR CAUTION LIGHTS. THE THROTTLE WAS LOWERED T O MAINTAIN NR RPM WHEN LOW ROTOR RPM HORN SOUNDED. A POWER ON LANDING PERFORMED WHILE ATTEMPTING TO MAINTAIN ENGINE TAC H INDICATING WITHIN LIMITS. LOW ROTOR HORN SOUNDED REPEATEDLY DURING DESCENT WHILE ENGINE TACH INDICATED OVER 102%. 20 MINUTES INTO THE FLIGHT, THE PILOT NOTICED A CHANGE IN ENGINE NOISE TO A HIGHER FREQUENCY, BUT NO ABNORMALITIES FOUND ON 1 G 7 1 3O 3 O H11NM 1E4 20081107 NE 2008 11 7 CA081020012 2 20081019 G 8530 VALVE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE STUCK W A UNSCHED LANDING E VIBRATION/BUFFET NR NOT REPORTED 1 CA (CAN) DURING STRAIGHT AND LEVEL CRUISE FLIGHT, THE PILOT NOTICED A SUDDEN INCREASE IN VIBRATION, THOUGHT TO BE COMING FR OM THE ENGINE, AND AN INCREASE IN MANIFOLD PRESSURE. HE OPTED TO TURN AROUND AND LAND AT A NEARBY CAMP. DURING HIS DESCE NT, THE VIBRATION STOPPED AND ENGINE PERFORMANCE RETURNED TO NORMAL. A COMPRESSION CHECK WAS FOUND NORMAL ON ALL CYLINDE RS. A WIGGLE CHECK ON THE EXHAUST VALVES WAS FOUND SATISFACTORY, HOWEVER, 1 OF THE VALVES WAS AT 0.014 WHILE ALL THE OTH ERS WERE AT 0.020 OR BETTER. IT IS SUSPECTED THAT THIS EXHAUST VALVE BECAME STUCK AND THEN CAME FREE AGAIN. 1 G 7 1 3O 3 O H11NM 1E4 20081107 CE 2008 11 7 CA081021001 1 20081001 G 3220 NAS150A48 BOLT BEECH BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE NLG LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BOLT WAS FOUND LOOSE ON RT SIDE OF NLG. THE COTTER PIN AND NUT WERE MISSING. 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 20081107 NM 2008 11 7 CA081021002 1 20081018 G 3260 401020101 SENSOR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA NLG DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4571 (CAN) ON INSPECTION FOUND NOSE GEAR DOOR CLOSED SENSOR CRACKED. SENSOR REPLACED IAW AMM 32-61-06-04 2 H 7 2 4T 4 T RT A13NM E00062EN 20081107 2008 11 7 CA081021003 4 20081019 G 3120 49712631 PRINTER CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE ACARS SMOKE W G O2 MASK DEPLOYED B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA 5044 5044 (CAN) DURING DESCENT TO YOW, CREW NOTICED SMOKE COMING FROM THE ACARS PRINTER, ELECTRICAL CIRCUIT BREAKER POPPED AND SMO KE STOPPED. NO EMERGENCY DECLARED AND THE ACFT LANDED WITHOUT FURTHER INCIDENT. ACARS PRINTER DIFFERED IAW MEL 23-22-0 A ND CIRCUIT BREAKER SECURED. 2 L 7 2 4F 4 F RT A21EA E15NE 20081107 NM 2008 11 7 CA081021004 1 20081019 G 3260 SENSOR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA NLG DOOR OUT OF RIG W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA (CAN) NOSE GEAR DOOR LIGHT FLICKERING ON AND OFF IN FLIGHT. RIGGED NOSE GEAR DOOR PROXIMITY SENSOR IAW AMM 32-61-06. CY CLED NOSE GEAR DOORS AND NO OTHER FAULTS FOUND. 2 H 7 2 4T 4 T RT A13NM E00062EN 20081107 GL 2008 11 7 CA081021005 2 20081020 G 7323 23065121 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE MALFUNCTIONED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 1329 (CAN) PILOT REPORTED ROTOR SPEED HUNTING IN CRUISE SO THE GOVERNOR WAS REMOVED TO CLEAN THE ORIFICES. ONCE REMOVED IT WA S NOTICED THAT THE EPOXY BOND ON THE END OF THE DRIVESHAFT WAS MISSING AND THE SPLINE DRIVE WAS LOOSE ON THE GOVERNOR DR IVESHAFT. IF LEFT THIS WOULD LIKELY TURN INTO WHAT WAS REPORTED IN SDR 20071015004 AND COULD LEAD TO AN ENGINE DECEL OR SHUT DOWN. 1 G 7 1 3U 3 U H3WE E4CE 20081107 EU 2008 11 7 CA081021006 1 20081020 G 2730 258CT29115A JACKSCREW HAWKER BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE7315R 01518 WP TRIM ACTUATOR FROZEN W K NONE O OTHER IN INSP/MAINT 1 CA 8137 (CAN) CREW REPORT THE ELEVATOR TRIM WAS DIFFICULT TO MOVE IN FLIGHT. UPON INSPECTION BY MX IT WAS FOUND THE ACTUATOR WAS CORRODED INTERNALLY AND THE GREASE WAS CONTAMINATED AND HARDENED. HAWKER BEECHCRAFT ALREADY HAS SB 27-3840 R1 TO CHECK FOR THIS SAME ISSUE WITH THESE ACTUATORS. BOTH LT AND RT ACTUATORS WERE REPLACED DUE TO THIS ISSUE AND THE ACFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A3EU E6WE 20081107 NM 2008 11 7 CA081021007 1 20081017 G 7921 28E997 OIL COOLER DHAV DHC8 DHC8106 2809020 NM PWA PW121 PW121 52124 NE NR 1 ENGINE LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) NR 1 ENGINE OIL PRESSURE BELOW 40 PSI. NR 1 ENGINE SHUT DOWN IN FLIGHT. AFTER THE ACFT RETURNED TO BASE IT WAS FOU ND AN OIL LEAK FROM THE NR 1 ENGINE OIL COOLER. 2 H 7 2 4T 4 T RT A13NM E20NE 20081107 CE 2008 11 7 CA081022001 1 20081021 G 5343 AN35A BOLT CESSNA CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE MLG TRUNNION WRONG PART W O OTHER W INADEQUATE Q C NR NOT REPORTED 1 CA (CAN) CARRY OUT INSPECTION AS PER CAMPAIGN 851-53-11-047 CESSNA 550 CHANNEL-TRUNION BRACE. FOUND INCORRECT HARDWARE INS TALLED. NO VISUAL DAMAGE TO STEERING ARM. REPLACED HARDWARE AS PER CAMPAIGN. NO RESTRICTED TRAVEL FOUND. 1 L 7 2 4F 4 F A22CE E1NE 20081107 NM 2008 11 7 CA081022002 1 20081014 G 3240 14209114 CONTROL MODULE EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE RT BRAKES FAILED W O OTHER J WARNING INDICATION LD LANDING 1 CA 3089 (CAN) AFTER LANDING, DURING DECELERATION ON RUNWAY AT APPROX 80 KTS, LT AND RT BRAKE FAULT MSG APPEARED ON EICAS ACCOMPA NIED BY COMPLETE LOSS OF BRAKING. AFTER APPROX 8 SECONDS BRAKING RETURNED TO NORMAL AND EICAS MSG DISAPPEARED. SERVICE N EWS LETTER SNL190-32-0023R00 IS RELATED NO MX MSG CORRELATION WITH LT AND RT BRAKE MSG. IN CMC MX MSG HISTORY OF OCT 14 LEG 3 FOUND MSG: "MAU2 BCM2/MAU2 NWSCM" CODE 32533301NWS. PER FIM 32-53-00-810-813-A00, BCM2 WAS REPLACED PER MM 2 L 7 2 4F 4 F RT A57NM E00070EN 20081230 CE 2008 12 30 CA081022003 1 20081020 G 5240 H1721050100 LATCH LEAR 35 31A 5170531 CE GARRTT TFE731 TFE73123B WP SERVICE DOOR UNSERVICEABLE W O OTHER E VIBRATION/BUFFET DE DESCENT 1 CA (CAN) SINGLE POINT FUEL DOOR LATCH OPENED IN FLIGHT. 2 L 7 2 4F 4 F RT A10CE E6WE 20081107 EU 2008 11 7 CA081022004 1 20081015 G 2421 200322 GENERATOR AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE NR 1 FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE THE NR 1 A/C WILD GENERATOR WENT OFF LINE. MX INSPECTED AND FOUND NR 1 AC WILD GENERATOR HAD FAILED INTERNALLY WITH SMALL SCREWS, WASHERS, ETC LAYING ON OUTLET COOLING SCREEN. TSO UNKNOWN. 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 20081107 NM 2008 11 7 CA081022005 1 20081021 G 3260 401020101 PROXIMITY SENSOR DHAV DHC8 DHC8* NM PWC 150 PW150A EA RT MLG OUT OF RIG W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) RT MLG FAILED TO RETRACT NORMAL, AMBER DOOR LIGHT, HANDLE LIGHT AND RED DISAGREEMENT LIGHT ILLUMINATED. RT MLG PR OXIMITY SENSOR FOR UPLOCK INDICATION RIGGED AS PER AMM 32-61-06-400-802. GAP SET TO .045, MH 8.621 2 H 7 2 4T 4 T RT A13NM E00062EN 20081107 WP 2008 11 7 CA081022006 2 20081019 G 7261 CARBON SEAL DORNER DO228 DO228202 2992030 EU GARRTT TPE331 TPE3315 01514 WP NR 1 ENGINE LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 CA (CAN) NR 1 ENGINE CREW SHUT DOWN DUE TO STEADY DROP OF OIL PRESSURE AND TORQUE FLUCTUATION, BELIEVED LATER THAT THE REAR CARBON SEAL BEGAN TO LEAK THUS INGESTION OIL IN ENGINE AND BURNT. ENGINE REMOVED FROM ACFT TO BE SENT FOR FURTHER TESTI NG AT ENGINE SHOP. 2 H 7 2 4T 4 T RT A16EU E4WE 20081230 GL 2008 12 30 CA081022008 1 20081021 G 2710 AN2412 CLEVIS BOLT DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 22D 22D30 NE CONTROL CABLE WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN AILERON CABLE (IN WING) REPLACEMENT THE CLEVIS BOLTS WERE FOUND TO BE WORN MORE THAT 30 PERCENT, REPLACE D WITH NEW AN 24-12 CLEVIS BOLTS. 1 H 7 1 3R 3 R RC A806 5E1 5 C P736 20081107 NE 2008 11 7 CA081022009 2 20081007 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE DAMAGED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB, THE PILOT HEARD AN UNUSUAL NOISE FROM THE ENGINE FOLLOWED BY A DECREASE IN COMPRESSOR TURBINE SPEED. THE PILOT RETURNED TO HIS POINT OF DEPARTURE WHERE AN UNEVENTFUL LANDING WAS MADE. THE ENGINE WAS NOT SHUT DOWN AND THE EMERGENCY POWER LEVER WAS NOT USED. THE ENGINE HAS BEEN SENT TO REPAIR STATION FOR INVESTIGATION, MANUFACTURER WILL CON TINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 H 7 1 3T 3 T A37CE E4EA 20081230 CE 2008 12 30 CA081022010 1 20081002 G 2752 503801537 DRIVE ASSY BEECH BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE FLAP ACTUATOR SHEARED W L ABORTED APPROACH F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) ON APPROACH THE FLAPS WERE SELECTED TO 17 DEG BUT FAILED TO EXTEND PAST 10 DEG. THE FLIGHT CREW INITIATED AN OVERS HOOT TO TROUBLESHOOT THE PROBLEM, THEY WERE UNABLE TO FIX THE BROKEN FLAPS AND RETURNED TO BASE. MX REPLACED THE FLAP DR IVE AND NO FURTHER FAULTS WITH SYS FOUND. 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 20081230 NM 2008 12 30 CA081023001 1 20081023 G 2710 BEARING DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE CABLE PULLEY SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING FLAP INSP, AN ENGINEER FOUND AN AILERON PULLEY INSIDE THE WING BOX SEIZED. FURTHER INVESTIGATION REVEALED THE ADJACENT PULLEY WAS ALSO CORRODED. BOTH PULLEYS WERE REPLACED AND THE ACFT RETURNED TO SERVICE. 1915 HRS WERE REMAI NING BEFORE COMPLETION OF TASK 2710/02 (11000 HRS). 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 NM 2008 12 30 CA081023002 1 20081013 G 2910 19071270901 RESTRICTOR VALVE EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE HYDRAULIC SYS CRACKED W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) HYD LEAK 10 DPM ON SYS NR2 RETURN LINE AND UNION FREE FALL SELECTOR VALVE RT WW AREA. WRENCH CHECK NIL FIX. FOUND RESTRICTOR VALVE CRACKED ON EMERGENCY EXTENSION SELECTOR VALVE. RESTRICTOR VALVE REPLACED, BUT STILL HAD A LEAK. UPON CL OSE INSP, FOUND A VERTICAL CRACK IN THE THREADED PORTION OF THE VALVE UNDER THE B-NUT (BOTH RESTRICTOR VALVES). THESE FI NDINGS RAISED THE CONCERNS OF ATTACHING A STAINLESS STEEL LINE AND B-NUT TO THE LIGHTER ALUMINUM RESTRICTOR VALVE. A 1.1 250 IN WRENCH IS REQUIRED TO TIGHTEN THE "B" NUT. NOTE, WE ALSO REPLACED THE HYD LINE ASSY. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081107 NM 2008 11 7 CA081023003 1 20081019 G 2797 19019564401 WIRE HARNESS EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE SLAT SYSTEM DAMAGED W A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 CA (CAN) ON FLAP RETRACTION AFTER T/O. SLAT FAIL EICAS MSG DISPLAYED. CARRIED OUT QRH FOR SLAT FAIL. DID NOT RECTIFY PROBLE M. ACFT RETURNED RT SLAT SKEW SENSOR HARNESS W611 REPLACED AS PER AMM 27-83-07 PB 401, RT SLAT 2/3 SKEW SENSOR REPLACED AS PER AMM 27-83-01 PB- 401. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081230 NE 2008 12 30 CA081023004 1 20081016 G 7922 28E251 THERMOSTAT SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL NR 2 OIL COOLER UNSERVICEABLE W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMP 8 EXCEEDED RED LINE LIMIT. 1 G 7 2 3U 3 U H1NE E1GL 20081222 SW 2008 12 22 CA081023005 1 20080727 G 5302 205032807003 FITTING BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE CONDUCTING 100 HR INSP NOTED AREA IN LT LOWER TAIL BOOM LONGERON AT FWD FITTING TO BE CRACKED. NDT CONFIRMED A CRACK INDCATION OF 1.5 INCHES LONG IN THE FITTING. 1 G 7 1 4U 4 U H1SW E17EA 20081222 SO 2008 12 22 CA081024001 1 20081024 G 5343 6705403 TRUNNION PIPER PA32 PA32R300 7103213 SO LYC 0540 IO540K1G5D 41532 SO HARTZL HCC3Y HCC3YR GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4771 (CAN) FOUND GREASE LEAKING FROM TOP PORTION OF THE LWR BRG SUPPORT. CLEANED AREA AND RE GREASED TRUNNION. GREASE WAS FOU ND COMING OUT OF CRACK. THE CRACK IS APPROXIMATELY ONE INCH LONG, HORIZONTAL. THIS CRACK INDICATION DOES APPEAR TO BE CA USED BY IMPROPER GROUND HANDLING. STEPS ARE BEING TAKEN TO REPLACE PART AT THIS TIME. 1 L 7 1 3O 3 O A3SO 1E4 5 C P25EA 20081230 NE 2008 12 30 CA081024002 1 20081021 G 2910 9265004900101 HEAT EXCHANGER SKRSKY S92 S92A NE GE CT7TS CT78A 30136 NE HYD SYSTEM CRACKED W O OTHER K FLUID LOSS CR CRUISE 1 CA (CAN) ENROUTE AT 7000 FT, ACFT STARTED TO NOD UNCHARACTERISTICALLY. IT WAS NOTED THAT THE NR 1 HYD SYS PRESSURE WAS HIGH (IN THE RED). DECISION TO RETURN MADE AND NR 1 HYD SYS DE-SELECTED BUT PRESSURE REMAINED HIGH. NO OTHER ADVISORY/CAUTIO N LIGHTS WERE ON AT THIS POINT. ABOUT 10 MINUTES AWAY FROM DESTINATION, PRESSURE DROPPED AND "HYD NR 1 RESEV LOW" LIGHT CAME ON FOLLOWED BY M/R AND T/R SERVO NR 1 PRESS, HYD NR 1 PUMP FAIL, PSAS PRESS AND AUTO-PILOT FAIL LIGHTS. EMERGENCY C HECKLIST CONSULTED AND CARRIED OUT. ACFT LANDED AND SHUTDOWN WITH NO FURTHER INCIDENT. PAX WERE BRIEFED IN-FLT AND AT SHUTDOWN. THE HYD NR 1 SIDE OF THE RT HEAT EXCHANGER FOUND TO HAVE CRACK AT BOTTOM OF HSG. NR 1 HYD SYS DRAINED OUT ALL 2 G 7 2 4U 4 U R00024BO E8NE 20081107 WP 2008 11 7 CA081024003 1 20081015 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INOPERATIVE W O OTHER O OTHER NR NOT REPORTED 1 CA 413 (CAN) STARTER GEN WOULD NOT ENGAGE ENGINE, REPLACED WITH SERVICEABLE STARTER GEN. 1 G 7 1 3O 3 O H11NM 1E4 20081107 WP 2008 11 7 CA081024004 1 20081011 G 6730 D2121 SERVO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE PILOT VALVE LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 CA 1690 (CAN) SERVO LEAKING FROM PILOT VALVE 1 G 7 1 3O 3 O H11NM 1E4 20081107 WP 2008 11 7 CA081024005 1 20081011 G 6730 D2121 SERVO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE PILOT VALVE LEAKING W O OTHER K FLUID LOSS NR NOT REPORTED 1 CA (CAN) SERVO LEAKING FROM PILOT VALVE 1 G 7 1 3O 3 O H11NM 1E4 20081230 2008 12 30 CA081024006 4 20081010 G 2216 GROUND WIRE LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE7312 01518 WP TRIM SYS OPEN W O OTHER F FLT CONT AFFECTED LD LANDING 1 CA (CAN) ON LANDING, A WHITE CAS MESSAGE (SECONDARY TRIM FAULT) APPEARED. SYS TROUBLESHOT AND FOUND AN OPEN GROUND WIRE AT RBA0664N-22 AT SPLICESP322. SPLICE REPAIRED AND FUNCTION CHECKED SERVICEABLE. 2 L 7 2 4F 4 F RT T00008WI E6WE 20081107 NE 2008 11 7 CA081025001 2 20081024 G 7530 BRH10211MS3215 PIN BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE LINKAGE MISSING W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 10795 (CAN) ON 26 SEPT, ENGINE RECORDED 73-2138, BBV/FMU MECHANICAL FAULT. BVV AND FMU WAS CHANGED. ENGINE GOOD FOR 2 FLIGHTS BEFORE ENG SYS FAIL CAME BACK INFLIGHT FOR THE SAME FAULT. ACFT DIVERTED, OPERATOR REPORTS PROBLEMS WITH THE BVV LINKAGE THAT CANNOT BE CORRECTED ONWING. ENGINE WAS REMOVED IN UNSERVICEABLE CONDITION DUE TO BOOSTER BLEED VALVE MECHANISM MAL FUNCTION. IT HAS BEEN REPORTED BY OPERATOR THAT BVV LEVER WAS NOT OPERATING PROPERLY. ENGINE AT ROLLS ROYCE CANADA FOR R EPAIR TO DETERMINE THE ROOT CAUSE OF MECHANISM MALFUNCTION. STRIP WAS CARRIED OUT TO EXPOSE THE BOOSTER BLEED VALVE MECH ANISM AND IT WAS NOTED THAT PIN AND RETAINING RING WERE MISSING. THIS PIN IS THE JUNCTION BETWEEN THE BELL CRANK LEVER 2 L 7 2 4F 4 F TR A6WE E00061EN 20081107 NE 2008 11 7 CA081025002 2 20081010 G 7320 251818 BRACKET BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE ENGINE BROKEN W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 22738 (CAN) ENGINE AUTO IFSD, ACFT DIVERTED TO ATL UNEVENTFUL LANDING. FSO CABLE RELEASE, PIECES FOUND IN THE TAILPIPE. LPT3 S CUFFED AND NICKED CONSISTENT WITH CABLE DAMAGE. NO EVIDENCE OF A TURBINE FAILURE. LP SYSTEM FREE TO TURN SMOOTHLY. ENGIN E IN RRC FOR INVESTIGATION. FURTHER DETAIL WILL BE SUBMITTED. 2 L 7 2 4F 4 F TR A6WE E00061EN 20081107 CE 2008 11 7 CA081027001 1 20081023 G 6120 8930861 SHAFT MTSBSI MU2 MU2B36 5780412 CE GARRTT TPE331 TPE33110 01514 WP HARTZL HCB3T HCB3TN5 GL PROPELLER BINDING W O OTHER F FLT CONT AFFECTED DE DESCENT 1 CA 25508 5965 (CAN) PROP OVERSEED DURING DESCENT. FOUND ENGINE INNER CONCENTRIC SHAFT TO BE BINDING ON OUTER CONCENTRIC SHAFT. AS POWE R LEVER IS RETARDED, INNER CONCENTRIC SHAFT ROTATES SLIGHTLY CLOCKWISE INCREASING PROP GOVERNOR HIGH SETTING. THERE IS N O PROVISION FOR LUBRICATION IN THIS AREA AND IT ONLY RELIES ON SPRING FORCE TO RETURN THE PROP GOVERNOR TO A LOWER SETTI NG. INNER SHAFT REMOVED, CLEANED, LUBRICATED AND REINSTALLED 1 H 7 2 3T 4 T RT A10SW E4WE 6 C P15EA 20081230 EA 2008 12 30 CA081027002 1 20080910 G 2435 23048016 STARTER GEN DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A135 52043 NE HARTZL HCB3T HCB3TN3 GL WORN W K NONE O OTHER IN INSP/MAINT 1 CA 612 (CAN) STARTER GEN HAD LONG LIFE BRUSHES INSTALLED AT OVERHAUL. BRUSHES ONLY LASTED 611.5 HRS WHEN THEY SHOULD HAVE WENT THEIR 1200 HOURS. ONE BRUSH WAS RT AT THE LIMIT WHERE THE OTHER BRUSH WAS ABOUT 40 PERCENT WORN ONLY. 1 H 7 1 3R 4 T A815 E4EA 6 C P15EA 20081230 EA 2008 12 30 CA081027003 2 20081025 G 7321 SHAFT BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL FCU THROTTLE STIFF W E ENGINE SHUTDOWN F FLT CONT AFFECTED AP APPROACH 1 CA 2888 (CAN) UPON APPROACH, THE LT ENG PWR LEVER WAS RETARDED WITH NO EFFECT ON ENG. THE ENG REMAINED AT 91 PERCENT NG. THE APP ROACH WAS ABORTED AND THE ACFT DIVERTED. ON ARRIVAL, AN EMERGENCY WAS DECLARED AND THE LT WAS SHUTDOWN IN ORDER TO CARRY OUT THE LANDING. MX INVESTIGATION DETERMINED THE INPUT SHAFT ON THE FCU WAS VERY STIFF, THE FCU WAS REPLACED AND THE AC FT RETURNED TO SERVICE. 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 20081222 EA 2008 12 22 CA081027004 1 20081024 G 5280 491184 BRACKET CNDAIR CL600 CL600* 1900302 EA GE CF34 CF348C5 30050 NE RT MLG DOOR LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) INBD MLG RT DOOR ATTACHMENT BRACKET ON STRUT FOUND LOOSE DURING HEAVY MAINT VISIT. REFERENCE: CMM 32-11-05, FIGUR E 1, PAGE 1019, ITEM 290. IT IS WORTH NOTING THAT THIS IS THE 2ND TIME, IN THE MONTH OF OCTOBER 2008, THAT THIS ISSUE H AS BEEN RAISED. PREVIOUSLY, A MAINT IRREGULARITY REPORT SUBMITTAL, DATED 03 OCTOBER 2008, REVEALED THAT THE SAME PROBLEM WAS FOUND. NO SDR RAISED FOR THIS ONE. 2 L 7 2 4F 4 F RT A21EA E00063EN 20081229 CE 2008 12 29 CA081027005 1 20081022 G 3233 ADI79990038 FORK ADI7999003 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL ACTUATOR BROKEN W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF THE PILOT SELECTED GEAR UP, RT MLG FAILED TO RETRACT. GEAR WAS CYCLED WITH NO SUCCESS. GEAR WAS RE TURNED TO DOWN POSITION AND THERE WERE 3 GREEN LIGHTS. DISPATCH AND MX WERE CONTACTED AND IT WAS DECIDED TO RETURN TO BA SE. LANDING WAS UNEVENTFUL. UPON INSP BY MX, THE RT MLG ACTUATOR FORK END THAT ATTACHES TO THE UPPER DRAG BRACE WAS SHE ARED OFF, HOWEVER THE DOWNLOCK WAS STILL IN PLACE. IT LOOKED LIKE THE FORK END HAD DEVELOPED A FATIGUE CRACK AND FINALLY LET GO JUST ABOVE THE LOCK NUT THAT HOLDS THE FORK END IN PLACE ON THE ACTUATOR. THE FORK END, AND TAB WASHER WERE REPL ACED WITH NEW PARTS. CYCLES OR HRS ON BROKEN FORK END IS UNKNOWN. THE GEAR WAS INSPECTED FURTHER AND NO OTHER DEFECTS FO 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 20081230 EU 2008 12 30 CA081027006 1 20081023 G 2130 BUTTERFLY VALVE AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE CABIN PRESSURE STICKING W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) FOLLOWING DEPARTURE, THE ACFT FAILED TO PRESSURIZE IN AUTO OR MANUAL MODE. THE ACFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. THE GROUND AIR CONNECTION CHECK VALVE WAS FOUND TO BE STUCK IN THE OPEN POSITION. MAINT CLEANED AND LUBRICATED THE VALVE TO RESTORE PROPER FUNCTION. THE SYS WAS GROUND CHECKED SERVICEABLE AND THE ACFT RETURNED TO SERVICE WITH NO FURTHER PROBLEM REPORTED. 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 20081230 CE 2008 12 30 CA081028001 1 20081001 G 2497 70002405D CIRCUIT BREAKER CESSNA 680 680CE 2076811 CE PWC PW306 PW306C 52169 NE LT POWER FEED TRIPPED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 81 (CAN) LT POWER FEED CIRCUIT BREAKER (1 OF 3 IN PARALLEL) POPS OPEN IN FLIGHT. P/N 700-024-50 REPLACED NEW. NOTE: THIS C /B WAS REPLACED AT 261 HRS. AND AGAIN AT 342 HRS. 2 L 7 2 4F 4 F RC T00012WI E35NE 20081222 SW 2008 12 22 CA081028003 1 20081024 G 6320 407040035101 BEVEL GEAR BELL BELL 407 407 1182206 SW ALLSN 250C 250C47B GL TRANSMISSION DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 6089 1122 (CAN) TRANSMISSION CHIP LIGHT ILLUMINATED. MECHANIC FOUND SMALL DEBRIS ON THE LWR CHIP PLUG. UPON INSP BY THE OVERAUL SH OP, THEY DISCOVERED THE BEVEL GEAR DAMAGED. A SMALL PIECE OF GEAR TOOTH APPROX. .360X.073 HAD BROKEN OFF THE GEAR ASSY A ND DISCOVERED THE BEVEL GEAR CRACKED AT THE DAMAGED GEAR TOOTH ARED. 1 G 7 1 3U 3 U O H2SW E1GL 20081230 GL 2008 12 30 CA081028004 1 20081021 G 2720 2227271200 TUBE DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA RUDDER CONTROL WORN W K NONE O OTHER IN INSP/MAINT 1 CA 1742 (CAN) DURING ROUTINE INSP/OPS CHAEK IT WAS FOUND THAT THE S-TUBE WHICH ALLOWS FOR THE POSITIONING OF THE RUDDER PEDAL ON THE PILOTS RT SIDE, HAD WORN THE CABLE TO THE POINT OF FINDING A FEW BROKEN CABLE STRANDS. THE RUDDER CABLES WERE ONLY DUE FOR REPLACEMENT AT 3000 HRS. 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 20081230 WP 2008 12 30 CA081028005 1 20081022 G 2435 14924HTH STARTER GEN ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE DISENGAGED W O OTHER O OTHER NR NOT REPORTED 1 CA 201 (CAN) STARTER WOULD NOT ENGAGE THE RING GEAR. 1 G 7 1 3O 3 O H11NM 1E4 20090102 WP 2009 1 2 CA081028006 1 20081024 G 6310 C0183 BAR ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA SPRAG CLUTCH CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 930 (CAN) DURING AN AES MIDLIFE INSP FOUND: SPRAG CAGE CRACKED (2) CROSSBARS SHAFT WORN UNDERSIZE HOUSING WORN OVERSIZE. 1 G 7 1 3O 3 O H11NM E295 20090102 GL 2009 1 2 CA081028007 1 20081020 G 5320 C2CE329A BRACKET DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 22D 22D30 NE FIREWALL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSP, AN AME FOUND A CRACK IN RADIUS OF MIXTURE CONTROL BRACKET ATTACHED TO FIREWALL, BRACKET WA S REMOVED, REPAIRED AND REINSTALLED. 1 H 7 1 3R 3 R RC A806 5E1 5 C P736 20090102 EA 2009 1 2 CA081029001 1 20081027 G 2820 TUBE CNDAIR CL604 CL604 1900301 EA FUEL SYS DAMAGED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) WHILE TROUBLESHOOTING A FUEL TRANSFER PROBLEM ON THE CHALLENGER 604, SERIAL NR 5320, WE FOUND 3 DAMAGED FUEL TUBE S IN THE CENTER FUEL TANKS, 2 IN THE RT SIDE AND 1 IN THE LT SIDE. ALL 3 FUEL TUBES WERE REPLACED. 2 L 7 2 4F RT A21EA 20090102 SO 2009 1 2 CA081029002 1 20081027 G 7721 1020007 PROBE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL CYLINDER HEAD MALFUNCTIONED W E ENGINE SHUTDOWN N FALSE WARNING CR CRUISE 1 CA (CAN) PILOT OBSERVED LT ENG CYLINDER HEAD TEMP OVER RED-LINE. OTHER ENG PERIMETERS WERE NORMAL. PILOT CHOSE TO SHUTDOWN THE ENG AND FEATHER THE PROPELLER. LANDED WITHOUT INCIDENT. MAINT TROUBLESHOT AND FOUND LT ENGINE CHT READ 150 DEGREES W HEN ENGINE WAS COLD. CHANGED THE PROBE TO P/N AN5546-1 IAW IPC. THE PROBE REMOVED IS AN FAA/PMA ALTERNATE TO THE REQUIRE D P/N IN THE IPC. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20090102 NM 2009 1 2 CA081029003 1 20081024 G 6120 30005000024 SIGNAL COND UNIT DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE PROPELLER INOPERATIVE W E ENGINE SHUTDOWN F FLT CONT AFFECTED CL CLIMB 1 CA 35236 35236 (CAN) JUST AFTER TAKEOFF, NR 2 ENGINE WENT TO FEATHER. AUTO FEATHER WAS ARMED/CREW HAD NOT COMMANDED AN ENG FEATHER. CRE W COMPLETED SHUT DOWN OF NR2 ENG, DECLARED AN EMERGENCY AND RETURNED TO ORIGINATING AIRPORT. NO OTHER INCIDENTS DURING L ANDING. MAINT INTERROGATION OF FDR RECORD SHOWS ELECTRONIC FEATHER SIGNAL WAS GENERATED BY THE TSCU AND SYSTEMS RESPONDE D TO THIS SIGNAL AND COMMENCED FEATHERING OF THE NR 2 ENGINE. ENG MFG EXAMINATION OF FDR DATA SHOWS ENGINE AND PROP OVER TORQUE DURING ENGINE FEATHER. DILASTIC TEST OF ENG HARNESS AND TSCU SHOWED NO CONFIRMED FAULTS. ENG HARNESS AND TSCU (T SCU SUSPECTED) REPLACED FOR TROUBLESHOOTING. ENGINE OVER TORQUE INSPECTIONS COMPLETED AND ALLOWED TO CONTINUE IN SERVICE 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090102 EA 2009 1 2 CA081029004 1 20081026 G 2750 8004301 CONTROL UNIT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS UNSERVICEABLE W O OTHER F FLT CONT AFFECTED DE DESCENT 1 CA (CAN) ON DECENT CREW SELECTED FLAPS DOWN AND FLAPS STOPPED AT 3 DEGREES. CREW ELECTED TO DO A GO AROUND AND PERFORMED TH EIR CHECKLIST. ADVISED TOWER THEY WOULD LIKE TRUCKS ON STANDBY BUT DID NOT DECLARE AN EMERGENCY. CREW BRIEFED F/A AND MADE ANNOUNCEMENT TO PASSENGERS THEY WOULD BE LANDING A LITTLE FASTER THAN USUAL. FLIGHT LANDED WITHOUT INCIDENT. RESET OF FLAP SYS AND MEL 27-02 APPLIED. NEXT FLIGHT HAD FLAP SNAG INTO. ACFT THEN FLOWN WHERE THE FLAP SKEW DETECT CONTROL U NIT REPLACED AND SYS CHECKED SERVICABLE. 2 L 7 2 4F 4 F RT A21EA E15NE 20090105 NE 2009 1 5 CA081029005 2 20080915 G 7261 OIL SYSTEM STBROS SD3 SD360 8100606 EU PWA PT6 PT6A65AR 52043 NE ENGINE LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, THE PILOTS OBSERVED ENG TEMPERATURE RISING THRU 800°C AND PEAKING OVER 1000°C. FLAMES WERE NOTICED FROM THE EXHAUST. THE ENG WAS SHUTDOWN AND FIRE BOTTLES DISCHARGED. A SINGLE ENG LANDING FOLLOWED. POST FLIGHT INSPECTI ON REVEALED OIL LEAKING FROM GAS GENERATOR CASE AND EXHAUST AREA. THE ENG WAS REMOVED AND SENT FOR INVESTIGATION WHERE T EARDOWN REVEALED A NR 1 BEARING DISTRESS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABL ISHED. 2 H 7 2 4T 4 T A41EU E4EA 20090102 NE 2009 1 2 CA081029006 2 20081016 G 7250 TURBINE AEROSP ATR72 ATR72201 8680943 EU PWA PW120 PW124B NE LT ENGINE SEIZED W C ABORTED TAKEOFF X J ENGINE FLAMEOUT WARNING INDICATION TO TAKEOFF 1 CA (CAN) DURING TAKEOFF, THE PILOT REPORTED LT ENG TQ INCREASE TO 109 PERCENT. THE PLA WAS MOVED TO GI BUT THE ENG SHUTDOWN ITSELF. THE ACFT WAS DIVERTED TO THE GATE. DURING TROUBLESHOOTING, THE ENG PARAMETERS WERE DOWNLOADED AND ANALYZED. REV IEW SHOWED A DROP OF NH FROM 92 PERCENT TO 0, AND FUEL FLOW REDUCING FROM 550 TO 300, AND THEN TO ZERO. THE NL SENSOR AN D THE TMM CHIP DETECTOR WERE INSPECTED AND FOUND CONTAMINATED. THE STARTER GEN WAS REMOVED IN ORDER TO ROTATE THE HP SHA FT BUT THE HP TURBINE WAS SEIZED. BORESCOPE INSP PERFORMED AND CONFIRMED THAT THE HP TURBINE WAS NOT ROTATING. SUSPECTIN G DISTRESS IN THE TOWERSHAFT AREA, THE COVER OF THE AGB DRIVE WAS REMOVED. INSP SHOWED A TOWERSHAFT WITH SIGNIFICANT RAD 2 H 7 2 4T 4 T RT A53EU E2ONE 20090102 CE 2009 1 2 CA081030001 1 20081012 G 2160 HYLZ503361 CONTROLLER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL A/C SYSTEM SMOKE W O OTHER B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 CA (CAN) THE FLIGHT CREW REPORTED SMOKE IN THE CABIN, THE ACFT LANDED SAFELY. MX INSPECTED AND SMOKE WAS THOUGHT TO BE COMI NG FROM THE VENT BLOWER, THE BLOWER WAS REPLACED, GROUND RUN-UP CHECK WAS CARRIED OUT AND NO SMOKE WAS EVIDENT COMING FR OM AIR CONDITIONING SYS. DURING TEST FLIGHT, THERE WAS NO HEATING CONTROL IN AUTO MODE. THE SYS WAS SWITCHED TO MANUAL A ND HEAT CONTROLLING WAS POSSIBLE. WHEN THE SYS WAS SWITCHED BACK TO AUTO, A SLIGHT BURNING SMELL WAS NOTICED BUT THERE W AS NO SMOKE IN THE CABIN. THE SYS WAS TURNED OFF AND THE ACFT RETURNED TO BASE. THE CABIN TEMP CONTROLLER WAS REMOVED AN D INSPECTED. THERE WAS EVIDENCE OF DAMAGE AND ARCING ON THE UNIT AND IT WAS REPLACED AND THE ACFT RETURNED TO SERVICE. 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 20081230 EA 2008 12 30 CA081030002 1 20081024 G 3246 472439473232 SEAL CLEVELANDPNU DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL WHEEL WRONG PART W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS PROBLEM WAS IDENTIFIED WHILE CARRYING OUT ROUTING MX ON AMPHIBIAN FLOAT MAIN WHEELS. THE MFG PARTS BOOK SPEC IFIED WHEEL GREASE SEAL THAT WHEN INSTALLED WERE 0.010 TOO SMALL OF A DIAMETER, CAUSING THE SEAL TO FALL OUT OF POSITION . HAVE CONTACTED THE OEM MFG TO DISCUSS THIS ISSUE AND THEY CONFIRMED THE GREASE SEAL LISTED IN THE PARTS MANUAL IS TOO SMALL OF A DIAMETER AND THAT THEY ARE IN THE PROCESS OF AMMENDING THEIR PARTS MANUAL TO SHOW THE CORRECT SEAL. THESE F LOATS ONLY HAVE 32 HOURS TSN, MFG FAILED TO INFORM THEIR CUSTOMERS OF THIS PROBLEM WITH THE SIZE OF THE GREASE SEAL. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081230 NM 2008 12 30 CA081030003 1 20081016 G 2751 1817392 TRANSMITTER BOEING 737 737201 1384454 NM PWA JT8 JT8D17 52049 NE LT FLAP POSITION FAILED W L ABORTED APPROACH F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) DURING FINAL APPROACH, WHEN THE PILOTS SELECTED FLAPS 25, THE FLAPS STOPPED SLIGHTLY PAST FLAPS 15. THE PILOTS SEL ECTED FLAPS UP AND OVERSHOT THE APPROACH. THE FLAPS RETRACTED OK. ON THE NEXT APPROACH, THE FLAPS OPERATED NORMALLY. MX INSPECTED AND OPERATED THE FLAPS SYS AND FOUND NO FAULTS. REPLACED THE COCKPIT FLAP INDICATOR, SUSPECTING THE ACFT HAD A FALSE FLAP ASSYMETRY PROBLEM. THE ACFT FLEW THE NEXT 2 DAYS WITH NO PROBLEMS. THE FOLLOWING DAY, THE ACFT EXPERIENCED THE SAME PROBLEM ON APPRAOCH INTO AIRPORT. ON THIS OCCURANCE THE PILOTS HAD TIME TO SELECT THE FLAPS UP AND RESELECT TH E FLAPS DOWN. ON THE SECOND TRY, THE FLAPS OPERATED NORMALLY. MX INSPECTED AND FUNCTIONED THE FLAP SYS A SECOND TIME AN 2 L 7 2 4F 4 F A16WE E2EA 20081230 WP 2008 12 30 CA081030004 1 20080313 G 7810 C1693 EXHAUST DUCT ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE DEFORMED W O OTHER S AFFECT SYSTEMS NR NOT REPORTED 1 CA (CAN) VISUAL INSP (CF90-03R2) FOUND DEFORMATION AND CRACK IN MUFFLER ASSY AT THE BASE OF THE EXHAUST PIPE WITH SUBSEQUEN T LEAK OF EXHAUST GASES INTO CABIN HEAT SYS, NO CO WARNING LIGHTS OR PILOT REPORTS POSTED. PART REPLACED AS REQ`D. 1 G 7 1 3O 3 O H11NM 1E4 20081230 SW 2008 12 30 CA081031001 1 20081031 G 6510 327211 COUPLING BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL T/R DRIVE SHAFT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A SHEDULED 100/300 HR INSP OF THE FWD T/R DRIVESHAFT SEGMENT THOMAS COUPLINGS, THE FWD THOMAS COUPLING WAS FOUND CRACKED. UPON FURTHER DISSASSEMBLY ONLY ONE OF THE LAMIATES WAS FOUND CRACKED. THE COUPLING WAS REMOVED FROM SERVI CE AND REPLACED NEW. THE AFT COUPLING WAS ALSO INSPECTED FUTHER WITH NO DAMAGE NOTED. 1 G 7 1 3U 3 U H2SW E1GL 20081230 SW 2008 12 30 CA081031002 1 20081029 G 3210 ESI2440 HOUSING GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE33110T 29065 NE HARTZL HCB3T HCB3TN5 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9283 53 (CAN) DURING THE REQUIRED 5 YEAR OVERHAUL ON THE LANDING GEAR, A CRACK WAS DISCOVERED ON THE MLG HSG VISUALLY. IR WAS CONFIRMED USING NDT METHODS LPI AS WELL AS EDDY CURRENT FOR CONFIRMATION. EDDY CURRENT READING INDICATED A DEPTH OF .04 0". THIS WAS THE FIRST OVERHAUL OF THIS LANDING GEAR BY THE OPERATOR SINCE PURCHASE 3 YEARS AGO. 1 H 7 2 3T 4 T 2A4 E4WE 6 C P15EA 20081230 SW 2008 12 30 CA081031004 1 20081031 G 2710 ROLL PIN AIRTRC AT802 AT802A 0390308 SW PWA PT6 PT6A67A 52043 NE AILERON PUSHROD MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 14 (CAN) LT WING AILERON PUSHROD ASSY FOUND TO BE MISSING ONE ROLL PIN THAT RETAINS THE INBD END ROD END BEARING. THIS IS A DEFECT FROM THE FACTORY (INSIDE OF HOLE IS PAINTED). ALL OTHER ROD ENDS INSPECTED NO OTHER DEFECTS FOUND, ARROW SHOWS M ISSING PIN HOLE. 1 L 7 1 3T 4 T NC A19SW E26NE 20081230 2008 12 30 CA081103001 4 20081016 G 2300 DISPLAY BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP FAILED W O OTHER H ELECT. POWER LOSS-50 PC DE DESCENT 1 CA (CAN) IN FLIGHT DURING DESCENT ACFT LOST ALL RADIOS AND NR 2 MFD. THEY WERE ABLE TO COMMUNICATE TO ATC BY GOING TO THE R EVERSIONARY PANEL AND TURNING THE TUNE KNOB TO THE COMM1 121.5 SELECTION. LANDING WAS UNEVENTFUL. AFTER LANDING 20 MIN UTES LATER CREW INDICATED THAT ALL THE FREQUENCIES WENT AMBER AND LOST THEIR ABILITY TO TUNE THE RADIO THROUGH THE FMS. WHEN THEY WOULD TRY TO TUNE THE RADIOS THE FREQUENCIES WOULD CHANGE ON THERE OWN. THE TRANSPONDER WAS ALSO INTERMITTENT, AND THEN THE COPILOT`S MFD WENT BLACK. HAD THE CREW GO INTO THE MDC FAULT HISTORY AND THEY CAME UP WITH A LOT OF FAULT S. PLEASE SEE ATTACHED PIC`S BELOW FOR FAULTS AND THE B3 CODES. CREW THEN DID A COMPLETE POWER DOWN ACFT AND WAIT A FEW 2 L 7 2 4F 4 F RT T00005NY E00010LA 20081230 NM 2008 12 30 CA081103002 1 20080716 G 3320 BR63031023 SOCKET DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE CABIN LIGHTS MELTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A C-CHECK INSP OF THE CABIN LIGHTING SYS IT WAS FOUND THAT THE NR 5 FLOURESCENT CABIN LIGHTING BALLAST WAS MELTED AT THE BULB SOCKET. BALLAST WAS REMOVED AND REPLACED. TT ON THE BALLAST CAN NOT BE ACURATLY DETERMINED BUT WITH A DATE STAMP OF FEB 11, 1987 IS LIKLEY ORIGINAL EQUIPMENT. LIGHT WAS FUNCTIONING AT THE TIME THE DEFECT WAS FOUND. ONE OTHER LIGHTING BALLAST WAS ALSO FOUND WITH MINOR DAMAGE OF A SIMILAR NATURE. IT WAS REPLACED AS WELL. SUBMITTED LATE AS THE C-CHECK WAS COMPLETED BY AN OUTSOURCE FACILITY AND UNTIL RECENTLY WAS NOT AWARE OF THE DAMAGED PARTS. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 EA 2008 12 30 CA081103003 1 20081102 G 2910 82970009325 LINE DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE HYD SYSTEM CHAFED W A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 CA 38294 38294 (CAN) DURING CRUISE FLIGHT, THE ACFT REPORTED LOSING NR1 HYD SYS FLUID AND ACTIVATION OF NR1 ISO VALVE. COMMERCIAL DECIS ION MADE FOR ACFT TO RETURN TO ORIGINATING AIRPORT. FLAP (0) DEGREES AND LANDING CARRIED OUT THAT WAS DUE TO ACTIVATION OF NR1 HYD SYS ISO VALVE. MAINT INSP FOUND HYD LINE FROM ENG DRIVEN PUMP TO PRESSURE MANIFOLD CHAFED AT NACELLE CLAMP. LINE REPLACED. ENG DRIVEN PUMP REPLACED AS PUMP HAD OPERATED AFTER FLUID DEPLETION. LEAK AND FUNCTION CHECKS CARRIED OUT . ACFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 2008 12 30 CA081103004 4 20081008 G 8300 310186401 BEARING CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL ACCESSORY G/B FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 7114 2318 (CAN) NR 1 BRG FAILED WITHOUT OUTSIDE INFLUENCE. RESULTANT METAL CONTAMINATION CONTAINED TO THE GB, MAIN OIL FILTER AND OIL PUMP. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20081230 SW 2008 12 30 CA081103005 1 20081030 G 8000 31057463 IGNITION SWITCH SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 29073 NE MCAULY 4HFR34 4HFR34C652 NE ENGINE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) OIL LEAK ON THE ENG FROM LWR ENG COWL FOUND. TROUBLESHOOTING REVEALED THE PROBLEM AS A AUTO IGNITION PRESSURE SWIT CH LEAKING AT THE BASE WELD. INSP WITH A MAGNIFYING GLASS FOUND A CRACK APR .7500 AROUND THE CIRCUMFERENCE OF THE WELD. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 20081230 EU 2008 12 30 CA081104001 1 20081028 G 3231 HOSE BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE7315R 01518 WP DOOR ACTUATOR LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) PILOTS REPORTED LOSS OF HYD PRESSURE AFTER LANDING WHILE TAXING BACK TO AMO. ON INSP, FOUND IN THE RT GEAR WELL A FLEX HYD LINE INSTALLED WITH A SLIGHT TWIST ON IT. THE LOCKWIRE ON THE B-NUT WAS LOOSE, AND THE TWIST ON THE HYD LINE A IDED IN ALLOWING THE B-NUT TO BACK OFF CAUSING THE HYDR LEAK IN THE RT GEAR WELL. AREA CLEANED UP. THE LINE WAS INSPECT ED FOR CRACKS AND PROPER ALIGNMENT RE-INSTALLED RE-TORQUES AND RE-LOCKWIRED. INSPECTED HYDR PRESSURE FILTER AND FOUND IT TO BE SERVICEABLE AND RE-INSTALLED FILTER. CARRIED OUT HYD FUNCTIONS AND LEAK CHECKS ON THE ACFT USING GROUND HYD CART. THERE WERE NO APPARENT LEAKS FOUND. CARRIED OUT GROUND RUNS ON AIRCRAFT, BLED HYD PUMPS AND CHECKED SYS PRESSURE AND CY 2 L 7 2 4F 4 F RT A3EU E6WE 20081222 NE 2008 12 22 CA081104002 2 20081031 G 7230 COMPRESSOR DOUG DC3 DC3C 3021457 WP PWA PT6 PT6A67R 52043 NE HARTZL HCB5M HCB5MA3 GL RT EINGE SEIZED W A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CA (CAN) DURING CRUISE, THE RT GENERATOR KICKED OFF-LINE. SHORTLY AFTER THAT TEMP INDICATIONS IN THE RT ENG CLIMBED CAUSING THE FLIGHT CREW TO SHUT DOWN THE ENGINE AND CONTINUE ON TO LAND AT THE SCHEDULED POINT OF LANDING. THE STARTER GEN WAS REMOVED AND THE COMPRESSOR SECTION OF THE ENGINE WAS FOUND TO BE SEIZED. 2 L 7 2 4R 4 T A669 E26NE 6 C P44GL 20081222 GL 2008 12 22 CA081104003 1 20080927 G 2410 07A19474 BRACKET DIAMON DA40 DA40 2990002 GL LYC O360 IO360M1A NE MUHBR MTV MTV3BC EU ALTERNATOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 805 (CAN) DURING A ROUTINE INSP, THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE BROKEN ACROSS THE WIDTH OF THE BRACKET ADJA CENT ONE OF THE MOUNTING HOLES. (REAR MOUNTING BOLT THAT IS USED TO ATTACH THE BRACKET TO THE ENGINE). 1 L 7 1 3O 3 O NT A47CE 1E10 5 C USSR 20081222 NM 2008 12 22 CA081104004 1 20081031 G 5554 17063073405 FITTING EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE RUDDER BROKEN W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA 6515 (CAN) ON PUSHBACK, RECEIVED FLIGHT CONTROL- NO DISPATCH MESSAGE. INVESTIGATION FOUND THE RUDDER UPPER FTG LUG BROKEN. RU DDER PCU ACTUATOR WAS INSTALLED 2007-05-17. CAUSE WAS FOUND TO BE MISSING SLIDING BUSHING, P/N 170-62218-003, IPC 27-21 -05 FIG.01 ITEM 170. THE ITEM WAS FOUND GREASED BUT NOT WORN IN A NEARBY CAVITY OF THE RUDDER. THIS IS CONFIRMED BY A CU T/SLICED COTTER PIN THAT IS STILL IN THE BOLT, WHICH WAS PULLED THROUGH THE LOWER LUG, AND CAUSED DAMAGE ON THE FLANGED BUSHING IN THE LOWER LUG, BUT NO DAMAGE WAS FOUND ON THE INSIDE OF THE SLIDING BUSHING. THE BUSHING WHEN CORRECTLY INSTA LLED, SITS INSIDE THE FLANGED BUSHING, AND PREVENTS SIDE LOADS FROM BEING APPLIED ON THE LUGS WHEN THE ATTACH BOLT IS TO 2 L 7 2 4F 4 F RT A56NM E00063EN 20081222 EU 2008 12 22 CA081105001 1 20081105 G 2822 D107318D1 PUMP BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL FUEL BOOST MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) TWICE NOW WE HAD FOUND THE FWD MAIN TANK BOOST PUMPS WHERE INSTALLED IN THE WRONG ORIENTATION, THE TRANSFER TUBES (FEED LINE) WAS PULL OUT OF THE FEED TANK. THE FORWARD TRANSFER PUMP HAS SYMMETRICAL MOUNTING HOLE. THE ORIENTATION OF T HE PUMP DETERMINES THE FUEL FEED LINE POSITION. IF THE PUMP IS ROTATED THE FUEL FEED LINE MAY COME OUT OF POSITION. THIS HAS FOR CONSEQUENCE TO REDUCE THE FUEL TRANSFER TO THE FEED TANK. THE PROPER INSTALLATION FOR THE FORWARD FEED PUMP IS THE FEED LINE ATTACHING HARDWARE SHOULD BE ORIENTED 12.00 O`CLOCK, WITH THE LONGITUDINAL AXIS. (SEE FIGURE 62-3 DETAIL F ) IN THIS CASE THE HARDWARE WAS LOCATED AT 8.00 O`CLOCK. 1 G 7 2 3U 3 U H3EU E4CE 20081222 NE 2008 12 22 CA081105002 2 20080908 G 7200 ENGINE SKRSKY S64 S64E 8142604 NE PWA JFTD12 JFTD12A4A 52047 NE OVERTEMP W E A ENGINE SHUTDOWN UNSCHED LANDING R M J PARTIAL RPM/PWR LOSS OVER TEMP WARNING INDICATION DE DESCENT 1 CA (CAN) WHILE DEPARTING AREA WITH AN AIRSPEED OF 30 TO 40 KNOTS AND A 500 FT PER MINUTE RATE OF DESCENT, NR 2 ENG N1 LOW RPM AUDIO HORN SOUNDED ALONG WITH ILLUMINATION OF NR 2 ENG LOW OIL PRESSURE LIGHT. A SCAN OF ENG GAUGES REVEALED NR 2 EN G HAD LOW N1 RPM WITH A CLIMBING T5 TEMP. FLT CREW IDENTIFIED PROBLEM AS AN ENG ROLL BACK AND SHUTDOWN OF NR 2 ENGINE CA RRIED OUT. ACFT THEN RETURNED TO LANDING AREA AND MADE AN SINGLE ENG LANDING. A POST FLT INSP OF T5 RECORDING SYS REVEA LED ENGINE TEMP HAD REACHED 798 DEGREES C. ENGINE, FREE TURBINE ASSEMBLY AND FUEL CONTROL UNIT REPLACED AND AFTER A COMP LETE GROUND CHECK ACFT RETURNED TO SERVICE. ENGINE, FREE TURBINE AND FUEL CONTROL UNIT WERE RETURNED FOR AN OVER TEMP I 2 G 7 2 4U 4 U H4EA E15EA 20081222 EU 2008 12 22 CA081105003 1 20081102 G 3250 5322012040 LANDING GEAR PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NOSE MALFUNCTIONED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) WHILE TAXING FOR TAKEOFF, THE NOSE STEERING BECAME VERY STIFF. PILOT RETURNED TO THE RAMP AND MAINT DISCOVERED THA T WITH THE ACFT WEIGHT ON THE STRUT, AND EVEN WITH THE SCISSORS DISCONNECTED, THE STEERING WAS EXTREMELY HARD, AND MADE A RATCHETING SOUND. THE NOSE GEAR ASSY WAS REPLACED AND THE ACFT RETURNED TO SERVICE. AWAITING TEAR DOWN REPORT ON NOSE GEAR ASSY TO ASCERTAIN CAUSE. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081222 NM 2008 12 22 CA081105004 1 20081103 G 2910 LINE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU HYD SYSTEM RUPTURED W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) CREW NOTICED HYD QTY LOSS ON NR 2 SYS. REPORTEDLY, NR 2 HYD ISOLATON VALVE CAUTION LIGHT CAME ON, BUT HYD PRESSURE REMAINED NORMAL. THE CREW DECIDED TO PERFORM ALTERNATE GEAR EXTENSION FOR LANDING. ACFT TOWED TO HANGAR, WHERE TECHNIC IANS DISCOVERED RUPTURED HYD LINE IN NR 1 MLG GEAR BAY. LINE HAD BEEN CHAFED FROM A BONDING CLAMP (AN735C4). TECH REPORT ED BONDING CLAMP WAS LOOSE, AND APPEARED TO BE INSTALLED WITHOUT SEALANT. RUPTURED HYD LINE WAS FOR THE NR 1 MLG DOWNLOC K ACTUATOR. LINE REPAIRED WITH A PERMASWAGED SPLICE SECTION, AND A/C RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081219 NM 2008 12 19 CA081105005 1 20081103 G 2910 82974351003 LINE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA HYD SYSTEM LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING FLIGHT, CREW NOTICED NR 2 HYD ISO VALVE CAUTION LIGHT CAME ON, NR 2 HYDRAULIC PRESSURE REMAINED NORMAL, AND THERE WAS A "SMALL QUANTITY" OF FLUID REMAINING IN NR 2 SYSTEM. CREW DECLARED EMERGENCY LANDING. CREW PERFORMED AN ALT ERNATE GEAR EXTENSION, AND ACFT LANDED. ACFT TOWED TO HANGAR WHERE TECHNICIANS DISCOVERED HYDRAULIC FLUID DRIPPING FROM NR 2 NACELLE, O/B OF JET PIPE CENTER SECTION. JET PIPE REMOVED AND TECHNICIANS DISCOVERED A SPLIT IN THE HYDRAULIC LIN E, WHERE IT HAD BEEN CHAFFING ON THE FWD JET PIPE SHROUD DAMAGED LINE WAS PART OF MLG `NR 2 GEAR UP` PIPING, P/N 8297435 1-003. LINE TO BE REPLACED. 2 H 7 2 4T 4 T RT A13NM E00062EN 20081222 NE 2008 12 22 CA081105006 2 20081028 G 7200 ENGINE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE NR 2 MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB SHORTLY AFTER T/O, THE NR 2 ENGINE HAD AN UNCOMMANDED AUTOFEATHER AND SUBSEQUENT OVERTORQUE. THE CREW SHUT THE ENGINE DOWN AND THE ACFT RETURNED TO THE POINT OF DEPARTURE WHERE AN UNEVENTFUL SINGLE ENGINE LANDING WAS ACCO MPLISHED. TROUBLESHOOTING LED TO THE REPLACEMENT OF THE TORQUE SIGNAL CONDITIONER UNIT AND THE TORQUE SENSOR. MM REQUIRE MENTS ARE BEING PERFORMED FOR THE OVERTORQUE CONDITION BEFORE A DECISION FOR FURTHER ACTION IS TAKEN. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 NE 2008 12 30 CA081105007 2 20081029 G 7200 ENGINE PWA PT6 PT6A68 NE MAKING METAL W B A EMER. DESCENT UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA (CAN) DURING FLIGHT TEST, THE ENG HAD A PARTIAL FEATHERING OF THE PROPELLER LEADING TO A PARTIAL LOST OF THRUST. THE ENG INE "CHIP LIGHT" CAME APPROX 20 SECONDS AFTER LOST OF THRUST. THE PILOT REDUCED POWER TO FLIGHT IDLE AND RETURNED TO BAS E. POST FLIGHT INSP REVEALED METALLIC DEBRIS ON THE CHIP DETECTOR AND MAIN OIL FILTER. THE ENGINE WILL BE RETURNED TO MF G FOR INVESTIGATION. UPDATES WILL BE PROVIDED IN DUE COURSE. 4 T E26NE 20081229 NE 2008 12 29 CA081105008 2 20081031 G 7261 CARBON SEAL AMD FALC50 FALCON2000 2730170 NM PWC PW308 PW308C 52182 NE ENGINE CRACKED W C ABORTED TAKEOFF K J FLUID LOSS WARNING INDICATION TO TAKEOFF 1 CA (CAN) DURING TAKEOFF ROLL, AT 90 KNOTS, THE OIL PRESSURE DROPPED TO ZERO AND THE LOW OIL PRESSURE WARNING ANNUNCIATED. T HE CREW RETARDED THE POWER TO IDLE, ABORTED THE T/O AND RETURNED TO THE RAMP. TROUBLESHOOTING FOUND AN OIL LEAK FROM A C RACKED CARBON SEAL ON THE FRONT HYD PUMP DRIVE PAD. THE ACFT WAS RETURNED TO SERVICE FOLLOWING ITS REPLACEMENT. 2 L 7 2 4F 4 F RT A50NM E00065EN 20081222 NE 2008 12 22 CA081105009 2 20081101 G 7200 ENGINE CESSNA 500 550 2076604 CE PWA 530 PW530A NE NR 2 FLAMED OUT W A UNSCHED LANDING R X J PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE AT FL270, THE PILOT NOTICED A POWER ROLL BACK ON NR 2 ENGINE. HE IMMEDIATELY DIVERTED THE ACFT TO A N ALTERNATE AIRPORT. THE ENGINE THEN FLAMED OUT AND THE PILOT MADE A SINGLE ENGINE LANDING. THE FUEL CONTROL WAS REPLA CED AND THE ACFT RELEASED TO SERVICE. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 L 7 2 4F 4 F A22CE E00053EN 20081222 WP 2008 12 22 CA081105010 1 20081105 G 5340 C8303 ANGLE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ELT MOUNT CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 2149 (CAN) FOUND CRACKED ANGLE DURING INSPECTION OF ELT MOUNT. 1 G 7 1 3O 3 O H11NM 1E4 20081229 EA 2008 12 29 CA081105011 1 20080924 G 5240 33130131 PISTON CNDAIR CL215 CL2151A10 1900320 EA PWA R1340 CWASP 52016 NE HAMSTD 43E 43E60 NE ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 256 (CAN) DURING ANNUAL INSP, WATER DOOR UNLATCHING JACKS WERE REMOVED FOR INSPECTION. THE PISTONS OF THE JACKS WERE INSPECT ED USING LIQUID PENETRANT INSPECTION FOR PRECAUTIONARY REASONS. BOTH PISTONS OF THE ACTUATORS WERE FOUND TO HAVE INDICAT IONS SHOWING THERE WERE CRACKS. BOTH SHAFTS WERE SENT TO OUR AMO`S NDT COMPANY FOR MAGNETIC PARTICLE INSPECTION TESTING TO VERIFY THE CRACKS. CRACKS WERE VERIFIED. SERVICE BULLETIN 215-528 WAS CREATED TO ELIMINATE THE POSSIBILITY OF THE PIS TONS CRACKING. BOTH OF THESE ACTUATORS HAD BEEN THROUGH OUR OVERHAUL SHOP. ONE ACTUATOR WAS REPAIRED, THE OTHER WAS OVER HAULED. IN BOTH CASES, THE ACTUATORS HAD NEW PISTONS INSTALLED AND ACCUMULATED. 2 H 7 2 4R 3 R RT A14EA ATC14 6 C P871 20081229 EA 2008 12 29 CA081105012 1 20081020 G 2751 601R930303 TRANSMITTER CNDAIR CL600 CL6002B19 1900309 EA MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA 12282 (CAN) UPON REACHING FL280 (CRUISING ALT) THE FLT CREW REPORTED THAT THEY RECEIVED THE SAME INDICATIONS ON EICAS AS THEY WOULD HAVE RECEIVED ON APPROACH (BRAKE TEMP, GEAR ICONS AND FLAP INDICATOR AND SPEED RASTER MOVING DOWN TO 210 KTS) AND THAT DURING THESE INDICATIONS, ACFT WITH AUTOPILOT ENGAGED STARTED TO PORPOSE UP AND DOWN +/- 50 TO 100 FT. THE FLAP DEG RADED (S) MSG WAS POSTED AS WELL. DURING THESE ALTITUDE FLUCTUATIONS, F/A WAS ASKED TO VERIFY WHETHER FLAPS WERE MOVING . SHE INDICATED TO CREW THAT THE FLAPS WERE NOT MOVING. ATC WAS NOTIFIED AND ACFT DIVERTED. JUST BEFORE THE FLT CREW S TARTED THEIR DEVIATION, THE ACFT NOSED OVER BRIEFLY WITH ABOUT A 500 FT LOSS IN ALTITUDE BUT INSTANTLY RECOVERED BACK TO 2 L 7 2 4F RT A21EA 20081229 2008 12 29 CA081106001 4 20081104 G 2562 E01 ELT INOPERATIVE W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) WHILE COMPLETING AN ANNUAL BENCH RECERTIFICATION CHECK ON AN ELT, NO POWER OUTPUT COULD BE MEASURED ON BOTH 121.5 AND 243 MHZ FREQUENCIES. THE UNIT WAS STILL UNDER WARRANTY BY THE MFG AND IT WAS BELIEVED THIS WAS THE FIRST CHECK SINCE BEING PUT INTO SERVICE. THE UNIT WAS RETURNED TO THE MFG FOR REPAIR. 20081229 2008 12 29 CA081106002 4 20081104 G 2562 E01 ELT MALFUNCTIONED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) DURING THE ANNUAL BENCH RECERTIFICATION INSP OF AN ELT THE VALUE OF MEASURED CURRENT DRAW WAS OBSERVED TO EXCEED T HE MFG SPECIFICATION BY 50MA. THE UNIT WAS STILL UNDER THE MFG WARRANTY AND IT WAS BELIEVED THIS INSP WAS THE FIRST CHEC K COMPLETED SINCE BEING PUT INTO SERVICE. THE ELT WAS RETURNED TO THE MFG FOR REPAIR. 20081229 EA 2008 12 29 CA081106003 2 20081030 G 8520 CASE CESSNA 150 152 2071835 CE LYC O235 O235N2C 41505 EA SNSNCH 72C 72CK EA ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINT (OIL CHANGE) OIL WAS DISCOVERED LEAKING FROM THE UPPER ENGINE CRANK CASE. FUTHER INSP CONFI RMED A CRACK 3 INCHES LONG BETWEEN CYLINDER NR 2 AND 4. ENGINE WAS REMOVED FOR REPAIR. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P9045 20081229 GL 2008 12 29 CA081106004 1 20081010 G 2840 FLOAT GE DHAV DHC2 DHC2MKI 2801830 GL PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE FUEL TRANSMITTER DETACHED W O OTHER N FALSE WARNING NR NOT REPORTED 1 CA (CAN) GENERAL ELECTRIC FUEL TRANSMITTER MODEL NR 56949-248, TYPE TJ-13. FUEL GAUGE READINGS WERE STUCK AT 22 GAL, INDICA TING ON CENTER FUEL CELL. INVESTIGATION REVEALED THAT THE FUEL TRANSMITTER. FLOAT HAD BECOME DETACHED FROM THE FUEL TRAN SMITTER. FUEL TRANSMITTER REMOVED, REPAIRED, TESTED AND REINSTALLED. 1 H 7 1 3R 3 R RC A806 5E1 5 C P206 20081229 SO 2008 12 29 CA081106005 1 20081031 G 7820 BAFFLE PIPER PA28 PA28180 7102808 SO LYC O360 O360A4A 41514 EA SNSNCH 76E 76EM8S5 EA MUFFLER FAILED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA (CAN) POWER LOSS ON TAKEOFF DUE TO BAFFLE FAILURE INSIDE MUFFLER WHICH RESTRICTED EXHAUST OF ENGINE CAUSING PARTIAL POWE R LOSS. 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA 20081229 GL 2008 12 29 CA081106006 1 20081105 G 3220 ARM DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA NLG WHEEL FORK CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2010 (CAN) BOTH ARMS OF THE NLG WHEEL FORK ASSY WERE FOUND CRACKED APPROXIMATELY 1.75 INCH FWD OF THE WHEEL AXLE BOLT. BOTH A RMS ARE CRACKED THRU THE LOWER PORTION AND A .25 INCH CRACK HAS STARTED ON THE UPPER SIDE OF THE ARMS. 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 20081229 EA 2008 12 29 CA081106007 1 20081103 G 2440 671GA01Y00 POWER UNIT CNDAIR CL600 CL600* 1900302 EA GE CF34 CF348C5 30050 NE APU BURNED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC IN INSP/MAINT 1 CA (CAN) NOT ACCEPTING AC EXTERNAL OR APU GEN AC. MX DETECT A BURNED CONTACTOR. CURRENTLY ACFT EXTERNAL AVAILABLE LIGHT I S ON. ACFT ONLY MAINTAINS POWER FOR 3 SECONDS, AND KICKS OFF. MFG HAS ISSUED A CONCESSION SL STATING NO OBJECTION TO F ERRY PROVIDED THE FOLLOWING MTC PROCEDURES BE ACCOMPLISHED. DISCONNECT CONNECTORS K119-S4 AND K119-S3 2. CAP AND STOW C ONNECTORS K119-S4 AND K119-S3 IAW EEC/SPM 20-12-05 3. APU GENERATOR IS INHIBITED IAW MEL 24-22-01 4. EXTERNAL ACFT POWER SYS IS INHIBITED IAW MEL 24-41-03 FROM A FLT OPS PERSPECTIVE, FOR ENGINE START. START ENG IAW QRH SUPP-2 ENGINE START (BATTERY/EXTERNAL AIR) PROCEDURE. 2 L 7 2 4F 4 F RT A21EA E00063EN 20081222 NM 2008 12 22 CA081107001 1 20081104 G 6322 B1741 MOUNT ROBSIN R22 R22BETAII 7640110 NM FAN WHEEL ASSY CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 162 (CAN) AT REINSTALLATION OF FANWHEEL ASSEMBLY, FOUND TAPERED MOUNTING FLANGE COMPLETELY CRACKED LONGITUDINALLY. UNIT SEN T TO MANUFACTURER FOR WARRANTY EXCHANGE. 1 G 7 1 3O H10WE 20081222 WP 2008 12 22 CA081107002 1 20081104 G 5340 C8303 ANGLE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ELT MOUNT SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA 2197 (CAN) THE ANGLE USED AS PART OF ELT INSTALLATION WAS FOUND SHEARED DURING 2200 HR OVERHAUL TEARDOWN. 1 G 7 1 3O 3 O H11NM 1E4 20081229 CE 2008 12 29 CA081107003 1 20081103 G 5347 MC07106582 SEAT TRACK CESSNA 182 182J 2072722 CE CONT O470 O470R 17026 SO LT PILOTS/LTPAS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2250 (CAN) 3 CRACKS LT PAS RAIL, 1 CRACK LT PILOTS RAIL, SEAT RAILS SOME WEAR, WEAR WITHIN LIMITS. 1 H 7 1 3O 3 O NT 3A13 E273 20081222 NE 2008 12 22 CA081107004 2 20081026 G 7414 106006169 MAGNETO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INTERMITTENT W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) MAGNETO INTERMITTENT. 1 G 7 1 3O 3 O H11NM 1E4 20081222 NE 2008 12 22 CA081107005 2 20081026 G 7414 1060064620 MAGNETO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE INTERMITTENT W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) MAGNETO INTERMITTENT. 1 G 7 1 3O 3 O H11NM 1E4 20081222 WP 2008 12 22 CA081107006 1 20081029 G 6310 C0511 ACTUATOR ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA CLUTCH MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) CLUTCH ACTUATOR REMOVED DUE TO FAULTY SWITCHES. 1 G 7 1 3O 3 O H11NM E295 20081229 GL 2008 12 29 CA081107007 2 20081030 G 7323 23076061 DRIVE SHAFT BELL 206 206B1 1181503 SW ALLSN 250C 250C20B 03013 GL TURBINE GOVERNOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 2021 2021 (CAN) DURING REMOVAL OF THE GOVERNOR FOR SCHEDULED OVERHAUL, AT REMOVAL FROM ENGINE GEARBOX, THE CLIP THAT RETAINS THE D RIVEGEAR ON THE PT SHAFT WAS NOT LOCATED IN THE GROOVE ON THE SHAFT, AND THE WASHERS THAT ARE RETAINED BY THE CLIP AND S ET AGAINST THE DRIVE GEAR, WERE FOUND SITTING IN THE MALE SPLINE OF THE GEARBOX DRIVE. IT APPEARS AS THOUGH THE END OF T HE DRIVESHAFT WAS WORN DOWN TO ALLOW THE CIRCLIP TO BECOME DISLODGED FROM THE GROOVE AND WORK IT`S WAY OFF THE SHAFT, HO WEVER THE DAMAGE TO THE SHAFT COULD HAVE BEEN DUE TO THE DISLODGED WASHERS SITTING IN THE DRIVE SPLINE. THE ONLY ITEM FO UND RETAINING THE DRIVEGEAR WAS THE SPRING ON THE BACK SIDE OF IT. THE ENGINEER INSPECTED THE GEARBOX DRIVE BUT WAS UNAB 1 G 7 1 3U 3 U H2SW E4CE 20081229 EU 2008 12 29 CA081107008 1 20081104 G 6220 117775P BALL JOINT SNIAS 350 AS350* EU LYC LTS101 LTS101* NE STARFLEX DEFECTIVE W O OTHER O OTHER NR NOT REPORTED 1 CA 277 (CAN) IT WAS DISCOVERED DURING A DAILY INSP THAT THE TEFLON LINING INSIDE ONE OF THE STARFLEX BALL JOINTS WAS DISPLACED. THE BEARING WAS REPLACED BEFORE FURTHER FLIGHT AND IT WAS NOTICED THAT THE TEFLON WAS STILL GLUED FIRMLY IN PLACE BUT I T WAS MISALIGNED FROM ITS ORIGINAL POSITION. 1 G 7 1 3U 3 U H9EU E5NE 20081222 2008 12 22 CA081110001 4 20081101 G 2562 C362042702 BATTERY DHAV DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ULB INCORRECT W K NONE W L INADEQUATE Q C NO TEST IN INSP/MAINT 1 CA (CAN) WRONG BATTERY INSTALLED IN UNIT. CORRECT BATTERY INSTALLED INTO ULB. REF WO NR 214939 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081222 CE 2008 12 22 CA081110002 1 20081105 G 3260 1003810061 SWITCH BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA NLG INTERMITTENT W L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 CA (CAN) AFTER PILOT SELECTED GEAR DOWN, THERE WAS NO INDICATION THE NOSE GEAR WAS DOWN AND LOCKED, ACFT DIVERTED BACK TO M X BASE. ON ROUTE NOSE GEAR INDICATION CAME ON. ACFT LANDED WITHOUT INCIDENT. MX REPLACED NOSE GEAR DOWN LOCK INDICATO R SWITCH AND RETURNED TO SERVICE. 1 L 7 2 3T 4 T A14CE E4EA 20081229 GL 2008 12 29 CA081110003 1 20081106 G 5311 SPAR DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO FUSELAGE DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA 5972 (CAN) DURING THE 6000 HOUR INSP DELAMINATIONS AND CRACKS WERE DISCOVERED ON THE SPAR BRIDGE. THE DELAMINATIONS AND CRACK S WERE FOUND ON THE RT SIDE ON THE AFT UPPER CORNER AT THE FILLET FROM BRIDGE TO SKIN INSIDE OF THE FUESLAGE AS VIEWED F ROM THE GAS TANK AREA. A SERIES OF INTERCONNECTED CRACKS THAT APPREAR TO BE IN THE RESIN ONLY. OVERALL LENGTH IS APPROX 40 MM, VARYING IN DEPTH FROM SURFACE CRACKS TO APPROX 3 MMM DEEP. THE LT SIDE HAD DELAMINATIONS AND CRACKS ON THE UPPER AFT CORNER AT THE FILLET FROM BRIDGE TO SKIN INSIDE OF THE FUSEALGE (THE OPPOSITE TO THE RT SIDE). LENGTH WAS 6-8MM AND DEPTH 5MM. 1 L 7 1 3O 3 O NT TA4CH E7SO 20081222 EA 2008 12 22 CA081110004 1 20081109 G 5751 CONTROL CABLE DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE AILERONS DISLODGED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) RT WING FWD AILERON CONTROL CABLE FOUND SITTING BEHIND THE AILERON INPUT ROD QUADRANT GUARD. CABLE MOVED OUT OF I TS LOCATION WITH SLIGHT FINGER ACTION. CABLE HAS LIGHT RUBBING MARK BUT ALUMINUM QUADRANT GUARD FOUND BADLY GROOVED. W INGS CONTROL CABLE TENSION TOOK ON BOTH SIDE. LT SIDE MEASURED AT 30 LBS AND RT SIDE AT 20 LBS. RIGGING TENSION IS BET WEEN 55 AND 65 LBS AT 20 DEGREES CELSIUS. TENSION TOOK WITH CABLE MISROUTED AND AT PROPER PLACE, NO SIGNIFICANT TENSIO N DIFFERENCE AT 2-3 LBS. LT SIDE CABLE SECTION INSPECTED AT SAME LOCATION, CABLE FOUND ROUTED PROPERLY. 2 H 7 2 4T 4 T RT A13NM E20NE 20081229 GL 2008 12 29 CA081110005 1 20081109 G 3220 203220080 FORK DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO NOSE GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1541 (CAN) ON PREFLIGHT OF ACFT, PILOT DISCOVERED CRACKS IN NOSE WHEEL FORKS APPROXIMENTLY 1 INCH FROM AXLE AT RADUS OF MACHI NING (MACHINED FOR WEIGHT REDUCTION DURING PRODUCTION), ON SIDE OF FORKS. RT SIDE IS CRACKED DEPTH OF MACHINE AREA ON TOP AND .7500+ ON THE BOTTOM LT SIDE OF FORK CRACKED BOTTOM DEPTH OF MACHINING AND .5+ ON TOP. ACFT WAS HAD PROPELLER STIKE ON LANDING APPROX 1000 HRS AGO, NOSE GEAR LEG WAS REPLACED AT THAT TIME AND FORK VISUALY INSPECTED WITH NO CRACKS DETECTED. NO CRACKS WERE NOTED DURING 100 HR INSP THAT WAS COMPLETED 75 HR AGO. NO OTHER REPORTED HARD LANDING HAVE BE EN REPORTED. ACFT INSPECTED, NO OTHER DAMAGE DETECTED. MFG HAS ASKED FOR PARTS TO BE RETURNED FOR ENGINEERING EVALUATI 1 L 7 1 3O 3 O NT TA4CH E7SO 20081222 WP 2008 12 22 CA081110006 1 20081030 G 2432 B4151 RELAY ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA BATTERY FAILED W O OTHER H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA 386 (CAN) BATTERY WOULD NOT COME ONLINE ALTHOUGH FULL BATTERY VOLTAGE WAS OBSERVED AT BATTERY CONNECTIONS. BATTERY RELAY WA S REPLACED AND ACFT RETURNED TO SERVICE. 1 G 7 1 3O 3 O H11NM E295 20081222 NM 2008 12 22 CA081110007 1 20081110 G 5310 87140011001 STRUCTURE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE FUSELAGE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 51173 (CAN) BIRD STRIKE JUST UNDER NOSE AREA. FOUND NR 2 LOWER COWL WITH INTERNAL CONE DAMAGE, LOWER COWL REMOVED. ENGINE B OROSCOPED WITH MINIMAL DEBRIS FOUND INSIDE ENGINE. NO DAMAGE NOTED NO DEBRIS FOUND ON LP COMPRESSOR. AIRFRAME INSPECTI ON STILL TO BE CARRIED OUT. AIRFRAME INSPECTION COMPLETED AS PER MM CHAPTER 5. PROP INSPECTED AS PER HS MM.61.10. NEW LOWER COWL INSTALLED, GROUND RUN COMPLETED FOR POWER ASSURANCE AND TESTING OF LOWER COWL. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081229 EA 2008 12 29 CA081111001 1 20081107 G 2150 8084402 BYPASS VALVE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE NR 1 ACM STUCK W O OTHER B G M SMOKE/FUMES/ODORS/SPARKS MULTIPLE FAILURE OVER TEMP TX TAXI/GRND HDL 1 CA (CAN) ON TAXI IN, CREW NOTICED ONE OF THEIR AIR-CONDITIONING PACKS WAS OVER TEMPING. THEY WHERE NOT ABLE TO CONTROL IT, SOON NOTICED SMOKE ON FLIGHT DECK. F/A WAS NOTIFIED AND A RAPID DEPLANEMENT WAS CONDUCTED AT GATE. MX FOUND THE DUAL BYP ASS VALVE STUCK IN THE FULL HOT POSITION. NR 1 ACM WAS ALSO FOUND SEIZED (P/N 782790-15, S/N 930930. TSN 28517 HOURS, C YCLES 14277, TSO 878735). IN ADDITION COMPRESSOR OUTLET OVERTEMP SWITCHES (P/N 750659-16. RATED TO 415°F) WERE FOUND IN STALLED IN THE LT AND RT DUCT OVERTEMP SWITCH POSITIONS INSTEAD OF (P/N 750665-9. RATED TO 220°F). THIS WAS REPORTED TO COMPANY MX SAFETY DEPT. BYPASS VALVE, NR 1 ACM AND THE SWITCHES WERE REPLACED, FUNCTION CHECKED SERVICEABLE AND THE ACF 2 L 7 2 4F 4 F RT A21EA E15NE 20081230 EA 2008 12 30 CA081111002 1 20081028 G 2612 FIRE WARNING CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE ILLUMINATED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA EXPERIENCED AN EMERGENCY EVACUATION A/P ON TAXIWAY (M), DUE SMALL FIRE EMITTING FROM ENG WHILE TAXIING. LOCAL ARRF RESPO NDED, PASSENGERS & CREW EVACUATED ACFT WITHOUT INCIDENT. MX VISUALLY INSPECTED ACFT & ENG WITH NO DEFECTS NOTED. ENGINES WERE RUN UP WITH NO DEFECTS NOTED. MX ISSUED A SPECIAL FLT PERMIT FOR FURTHER INVESTIGATION. NO INFORMATION TO DETERMI NE IF THERE WAS FLAME AS WELL AS SMOKE, ASSUMED FIRE REPORTED RESTRICTED TO ONE OR BOTH ENG JETPIPES. REPORT MENTIONS "L T ENGINE FLAMES/FIRE". 2 L 7 2 4F 4 F RT A21EA E15NE 20081222 NM 2008 12 22 CA081111003 1 20081107 G 5610 8SC0043014 WINDSHIELD DHAV DHC8 DHC8106 2809020 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) DURING CLIMB OUT, THE CREW WITNESSED THE RT COCKPIT HEATED WINDSHIELD CRACK. THE CRACK SLOWLY KEPT PROGRESSING TO A LENGTH OF ABOUT 5 INCHES. THE CREW INITIATED A RETURN TO BASE AND LANDED WITHOUT FURTHER INCIDENT. MX R&R THE WINDS HIELD. NO CAUSE AS TO THE FAILURE COULD BE DETERMINED, OTHER THAN IT APPEARS TO HAVE ORIGINATED AT THE EDGE OF THE WIND OW AT A HEATING ELEMENT. THE TOTAL TIME ON THIS WINDSHIELD COULD NOT BE DETERMINED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081222 EA 2008 12 22 CA081111004 1 20081110 G 2750 CONTROL UNIT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) FLAPS SELECTED TO 20 DEGREES FOR TAKE-OFF. AFTER TAKE-OFF, FLAPS WERE SELECTED TO 8 DEGREES AND THE FLAPS LOCKED AT 20 DEGREES. FLAP FAIL CAUTION EICAS MSG AS WELL. FOUND SKEW DETECT FAULT LIGHTS ILLUMINATED, BOX RESET CARRIED OUT ALONG WITH BREAKER RESET. FLAPS CYCLED NUMEROUS TIMES WITHOUT FAILURE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081229 NM 2008 12 29 CA081111005 1 20081104 G 3230 483003 SELECTOR VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU MLG SHORTED W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) CREW REPORTED A NOSE STEERING CAUTION ON TAKEOFF. UPON LANDING, ALL 3 GEARS SHOW RED WITH GEAR DOWN SELECTION. ALT ERNATE EXTENSION USED IAW QRH. ALL GREEN WITH ALT EXTENSION. FAULT CODES HAVE BEEN RETRIEVED AND ENTERED INTO THERE COMP UTER SYS. MX FOUND A SHORT TO GROUND IN THE UP SOLENOID OF THE LANDING GEAR SELECTOR VALVE. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081229 EA 2008 12 29 CA081111006 1 20081020 G 2916 9604501 RESERVOIR CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C5B1 30052 NE HYD SYSTEM LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) NR3 HYD SYS LOW PRESSURE CAUTION MESSAGE DURING CLIMB. INBD SPOILERS CAUTION MESSAGE ALSO PRESENT DUE TO HYD LOW P RESSURE. ACFT DECLARED EMERGENCY, ALTERNATE EXTENSION USED TO DEPLOY LANDING GEAR, AND RETURNED TO FIELD. FLUID LOSS WAS DISCOVERED FROM HYD SYS NR 3 RESERVOIR. HYD RESERVOIR WAS CHANGED AND ALL SYS TESTED AND FUNCTIONED SATIS. ACFT RET URNED TO SERVICE. NO P/N`S OR S/N`S AVAILABLE AT THIS TIME. UPDATE: 17-NOV-08, 08:08, "P/N 960450-1 S/N OFF: 239 S/N ON : 484". 2 L 7 2 4F 4 F RT A21EA E00063EN 20081229 NM 2008 12 29 CA081112001 1 20081110 G 3260 401020101 PROXIMITY SENSOR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU LT MLG UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 6338 (CAN) PILOTS REPORT: AFTER GEAR SELECTED UP, LT MAIN GEAR DOOR REMAINED OPEN WITH AMBER ADVISORY LIGHT. CONTINUED CLIMB NOT ABOVE 185KTS, CONDUCTED AFTER TAKE-OFF CHECKLIST. QRH CONSULTED AND ACTIONED ALTERNATE GEAR EXTENSION. LINE MX CON FIRMED DEFECT AND INVESTIGATION REVEALED THE `LT GEAR DOOR CLOSED` PROX SENSOR TO BE UNSERVICEABLE. UNSERVICEABLE SENSOR REPLACED WITH A NEW ITEM AND THE INSTALLED SENSOR WAS RIGGED IAW THE ACFT MM. ACFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081229 NM 2008 12 29 CA081112002 1 20080529 G 5714 85730800002 SHROUD BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA WING BOX MISMANUFACTURED W O OTHER O OTHER CR CRUISE 1 CA 9 9 (CAN) DURING PRODUCTION OF 4208 IT WAS DISCOVERED THAT THE CENTER WING LOWER SHROUD RT DRAIN HOLES WERE NOT PRESENT. A D ISCREPANCY WAS RAISED AND CLEARED BY DRILLING NEW HOLES IN SITER. UPON THE DELIVERY/ACCEPTANCE FLIGHT, IT WAS DISCOVERED THAT THE AFT COFFEE MARKER WAS UNSERVICEABLE. A TECHNICAL INVESTIGATION REVEALED 6 OF 9 (115 VAC) WIRES DAMAGED. A REPA IR WAS MADE IAW WDM 20-16-00. A SMS/SRS WAS RAISED. 2 H 7 2 4T 4 T RT A13NM E00062EN 20081229 EU 2008 12 29 CA081112003 1 20081030 G 7500 9550170290 PRESSURE SWITCH UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE ENGINE FAILED W E ENGINE SHUTDOWN X J ENGINE FLAMEOUT WARNING INDICATION LD LANDING 1 CA AFTER A LANDING AND COOLDOWN THE PILOT PRESSED THE START/DETENT SWITCH TO MOVE THE TWIST GRIP TO CUTOFF. THE ENGINE IMME DIATELY FLAMED OUT WHEN THE SWITCH WAS DEPRESSED (TWIST GRIP WAS NOT TURNED). THEN ATTEMPTED TO RECREATE THIS PROBLEM A ND IT HAPPENED AT ALL ENGINE SPEEDS. AFTER TROUBLESHOOTING IT WAS DETERMINED THAT THE P3 PRESSURE SWITCH WAS THE PROBLEM . 1 G 7 2 3U 3 U NC R0001RD E34NE 20081229 GL 2008 12 29 CA081112004 1 20081110 G 5755 GT41501009 SPOILER SYS BOMBDR BD700 BD7001A10 1390006 GL RROYCE BR700 BR700710A220 09500 NE MALFUNCTIONED W A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF AND DURING CLIMB, A LATERAL CONTROL MOVEMENT TO THE LT WAS NOTICED . ONE SPOILERON DEPLOYED ON THE L T WING (2 PAIR OF MULTI-FUNCTION SPOILER (MFS) IAW WING ON THIS ACFT). THE LT NR 2 MFS WAS AMBER LINE ON THE FLIGHT CONT ROL SYNOPTIC PAGE. SEVERAL EXTRACT AND RETRACT ACTIONS ON THE SPOILERS SYS PERFOMED, WITHOUT SUCCESS AND AILERON TRIM WA S ADJUSTED TO CORRECT THE ACFT LEVELING. CREW DECIDED TO ABORT THE FLIGHT AND LAND TO THE AIRPORT DEPARTURE . AFTER LAN DING ,THE LT NR 2 MFS WAS STILL FULLY DEPLOYED AND RETRACTED BY ITSELF WITH THE BLEED DOWN OF HYD PRESSURE OF THE SYSTEM . (HYD OFF) 2 L 7 2 4F 4 F RT T00003NY E00061EN 20081229 NM 2008 12 29 CA081112005 1 20081107 G 2697 FRF6E12S3S CONNECTOR BOEING 727 727247 138408F NM PWA JT8 JT8D15A 52051 NE FIRE WARNING SYS DAMAGED W F ACTIVATE FIRE EXT. N FALSE WARNING CL CLIMB 1 CA (CAN) AT APPROX 700 FT, AGL T/O YHZ FIRE WARNING LIGHTS ON GLARE SHIELD WERE DIMMLY ILLUMINATED. NO AURAL WARNING. APU F IRE HANDLE ILLUMINATED. SWITCH PULLED AND BOTTLE DISCHARED. ACFT RETURNED TO DEPARTURE. RECTIFICATION AFTER TROUBLES HOOTING FOUND APU FIRE SENSOR/RESPONDER CONNECTOR D1428 SEVERELY CORRODED. INTERIOR OF CONNECTOR FOUND PACKED WITH GREE NISH REDIDUE. BOTH ENDS OF CONNECTOR (SOCKETS AND PINS) CLEANED AND INSPECTED. APU FIRE DETECTION SYS TESTED IAW AMM 2 6-15-00 FOLLOWUP: REF: WRI 26-11/3077 APU FIRE SENSOR/RESPONDER CONNECTOR D1428 TO BE REPLACE. FOUND CONNECTOR WEATHER GASKET DAMMAGED CAUSING CORRROSION IN SOCKETS. 2 L 7 3 4F 4 F A3WE E2EA 20081222 SO 2008 12 22 CA081112006 1 20081106 G 3245 40140 TUBE PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA MLG TIRE FLAT W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) AFTER LANDING, IT WAS NOTICED THAT THE NOSEWHEEL WAS FLAT. DISASSEMBLY OF THE NOSEWHEEL HUB SHOWED A POSSIBLE WEAR SPOT BETWEEN THE TIRE AND TUBE. THE TUBE WAS DAMAGED DURING THE LANDING AND TAXI SO IT IS NOT KNOWN IF THIS WAS THE AC TUAL CAUSE OF THE PROBLEM. 1 L 7 2 3O 3 O A20SO E14EA 20081222 NE 2008 12 22 CA081112007 2 20081031 G 7200 ENGINE PIAGIO P180 P180 6960204 EU PWA PT6 PT6A66 52043 NE MAKING METAL W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA (CAN) DURING FLIGHT, THE ENGINE LOST TORQUE AND OIL PRESSURE. THE PILOT SHUT IT DOWN AND PERFORMED A SINGLE ENGINE LAND ING. POST FLIGHT INSPECTION FOUND THE PROPELLER SEIZED AND METAL DEBRIS IN THE EXHAUST. MANUFACTURER WILL CONTINUE INV ESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 H 7 2 3O 4 T RT A59EU E26NE 20081229 CE 2008 12 29 CA081112008 1 20081112 G 3210 130909B19 BOLT BEECH BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE SUPPORT BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 3428 (CAN) SUPPORT ASSY BRACKET ON BOTH SIDES OF THE NLG ACTUATOR PIVOT HAD 5 OF THE 6 BOLT HEADS SHEARED OFF LEAVING THE BOL T SHANK AND CAPTURE NUT. 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 20081229 EA 2008 12 29 CA081112009 2 20081031 G 7200 ENGINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA NR 2 FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE AT FL180, THE CREW FELT A STRONG JOLT AND VIBRATIONS THROUGH THE AIRFRAME. A QUICK REVIEW OF THE GAG ES SHOWED A POWER LOSS ON NR 2 ENG. THE ENG WAS SECURED AND THE CREW PERFORMED A SINGLE ENGINE LANDING. GROUND INSP FOU ND NOTHING OF SIGNIFICANCE AND THE ACFT WAS FERRIED BACK TO BASE. DURING FINAL APPROACH OF THE FERRY FLIGHT, THE ENGINE LOST TORQUE BUT RECOVERED WITHOUT ANY PILOT INPUTS. THE ACFT LANDED SAFELY AT DESTINATION. MFG WILL CONTINUE INVESTIGA TING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 L 7 2 4T 4 T RT A24CE E4EA 20081229 NE 2008 12 29 CA081112010 2 20081104 G 7532 BLEED VALVE PWA 305 PW305B 52128 NE ENGINE MALFUNCTIONED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION LD LANDING 1 CA (CAN) DURING LANDING, THE ENGINE FLAMED OUT. RE-START ATTEMPT WAS UNSUCCESSFUL. TROUBLESHOOTING LED TO THE REPLACEMENT O F THE COMPRESSOR BLEED VALVE ASSY. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 4 F E35NE 20081229 WP 2008 12 29 CA081112011 1 20081031 G 2421 GENERATOR DOUG DC3 DC3C 3021457 WP PWA PT6 PT6A67R 52043 NE HARTZL HCB5M HCB5MA3 GL NR 2 INOPERATIVE W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, THE CREW OBSERVED THE NR 2 GENERATOR GO OFF LINE WITH AN INCREASE IN ENG TEMP. IT WAS SHUTDOWN AND A SINGLE ENG LANDING FOLLOWED. POST FLIGHT INSP FOUND THE COMPRESSOR HARD TO ROTATE. THE ENGINE WILL BE REMOVED AND FOR WARDED FOR INVESTIGATION AND REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHE D. 2 L 7 2 4R 4 T A669 E26NE 6 C P44GL 20081229 EU 2008 12 29 CA081112012 1 20081111 G 3230 5322012289 DRAG LINK 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 9376 (CAN) ON CALL MAINT RECEIVED A PHONE CALL FROM CAPTAIN, PILOT REPORTED HEARING A LOUD NOISE FROM THE NOSE GEAR AREA WHEN DEPARTING THE NORTHERN AIRPORT. HE SAID THE NOSE GEAR TRANSIT LIGHT DID NOT EXTINGUISH AND HE THEN PROCEEDED TO RESWING THE GEAR WHICH THEN CAUSED THE LIGHT TO EXTINGUISH. ON DECENT, HE EXTENDED THE GEAR AND SAID THE NOSE GEAR TOOK LONGER THAN NORMAL TO FULLY EXTEND AND GIVE GREEN DOWN AND LOCKED INDICATION. MX INSTRUCTED HIM TO VISUALLY INSPECT THE NOSE GE AR AND GEAR BAY AND FOUND NOTHING UNUSUAL. THE DESISON WAS MADE TO RETURN TO DEPARTURE WITH THE GEAR EXTENDED. MX WAS T HERE TO MEET THE ACFT WHEN IT RETURNED. THE ACFT WAS HANGERED AND PLACED ON JACKS. MX THEN DID A GEAR SWING AND THE NOSE 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081229 2008 12 29 CA081113001 4 20081113 G 3460 0710159803 CONTROLLER PILATS PC12 PC1247 7090552 EU PWA PT6 PT6A67 52043 NE MFD FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 147 147 (CAN) WE HAVE JUST EXPERIENCED THE 4TH FAILURE OF THE KMC 2220 MFD CONTROLLER. THE JOYSTICK FUNCTION FAILS TO ALLOW CU RSOR MOVEMENT ON THE FLIGHT SCREENS AND DOES NOT ALLOW FLIGHT CREWS TO ENTER OR MODIFY ROUTING IN FLIGHT. THE REPLACEME NT UNIT CLEARED PROBLEM FOR NOW. HAVE BEEN TOLD MFG IS LOOKING INTO THE PROBLEM AS WE ARE NOT THE ONLY CUSTOMER HAVING THIS ISSUE. 1 L 7 1 4T 4 T RT A78EU E26NE 20081229 2008 12 29 CA081113002 2 20081113 G 7497 WIRE MAGNETO CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) COIL TO POINTS WIRE WORN THROUGH TO STRANDS DUE TO RUBBING ON FRAME OF DISTRIBUTOR BLOCK. 20081229 2008 12 29 CA081113003 2 20081022 G 7414 K3822 DISTRIBUTOR GEAR MAGNETO LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DISTRIBUTOR FINGER LOOSE ON GEAR ASSY. 20081229 NM 2008 12 29 CA081113004 1 20081112 G 7500 ZZ84M46P01 DUCT EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE BLEED AIR SYS SPLIT W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT PRECOOLER INLET RUBBER DUCT SHOWS SIGNS WHERE THE SEAM HAS COME APART, AS A RESULT THE FAN AIR HAS FROM THE SPL IT SEAM HAS CAUSED DAMAGE TO THE THRUST REVERSER HEAT SHIELD. T/R FIRE BLANKET PN 104M1031-22, SN6011203-013 THIS HAS AL SO OCCURRED ON ACFT FIN 317 C-FHKI SN 190-0052 AND FIN 342.C-FNAP SN 190-00142. 2 L 7 2 4F 4 F RT A57NM E00070EN 20081229 EA 2008 12 29 CA081113005 1 20081112 G 2751 8004301 DETECTION SYS CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE FLAP SYSTEM FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 18700 (CAN) FLAP FAIL, SELECTED 20, FAILED AT 8 DEGREES. ON APPROACH, CREW UNAWARE OF OAT DUE TO WORK LOAD. FLAP SKEW DETECT ION UNIT REPLACED IAW AMM 27-51-15, PG 401. FLAPS CHECKED SERVICEABLE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081230 SO 2008 12 30 CA081113006 1 20081107 G 3246 06104700 WHEEL PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA HARTZL HCC2Y HCC2YK2 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6560 (CAN) DURING A TIRE CHANGE, THE AME NOTICED A 4 INCH CRACK ALONG THE WHEEL, WHERE THE TIRE BEAD SITS. THIS TYPE OF FINDI NG IS RATHER UNUSUAL AT THE AMO. NO HARD OR UNUSUAL LANDINGS WERE REPORTED. THE WHEEL HALF WAS REPLACED, AND THE ACFT RE TURNED TO SERVICE. 1 L 7 2 3O 3 O A7SO 1E10 5 C P920 20081230 SW 2008 12 30 CA081113007 1 20081104 G 6420 407012108101 BUSHING BELL 407 407 1182206 SW PITCH HORN ASSY DEFORMED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WASHER BETWEEN THE T/R PITCH HORN AND PITCH LINK FOUND DEFORMED. 1 G 7 1 3U O H2SW 20081230 SW 2008 12 30 CA081113008 1 20081016 G 6210 206010200133 TAB BELL 206 206B 1181511 SW ROTOR BLADE DEFORMED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 CA 11 (CAN) LOUD BANG WAS NOTED WITHING 10 MINUTES OF FLIGHT. LEVEL OF VIBRATION DID NOT INCREASE. INSP AFTER LANDING FOUND TH AT THE TRIM TAB WAS DEFORMED (UPPER SIDE WAS BENT UPWARD AND LOWER SIDE BENT DOWNWARD). PEEL-PLY HAS BEEN LEFT ON THE TR IM TAB. 1 G 7 1 3U H2SW 20081230 NM 2008 12 30 CA081114001 1 20081113 G 3297 464605 WIRE HARNESS BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU PROXIMITY SWITCH SHORTED W A UNSCHED LANDING J WARNING INDICATION AP APPROACH 1 CA (CAN) CREW SELECTED GEAR DOWN AND GOT 3 GREENS AND LT MLG DOOR AMBER LIGHT. ALTERNATE EXTENSION C/O AND CREW OBSERVED A LTERNATE INDICATION SHOWED LT MLG (UNSAFE). CREW DECLARED EMERGENCY AND LANDED. PAX DEPLANED ON RUNWAY AND AFTER GEARS W ERE PINNED ACFT TAXIED TO GATE. FAULT CONFIRMED BY PSEU TO BE LT LGDNLK2 OPEN CIRCUIT. PROXIMITY SWITCH HARNESS ASSY PN 46460-5 REPLACED AND ACFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081230 2008 12 30 CA081114002 4 20081111 G 3413 4067644901 INDICATOR DHAV DHC8 DHC8106 2809020 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE IVSI FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CL CLIMB 1 CA (CAN) AFTER TAKOFF, CAPTAINS SIDE IVSI FAILED, ACFT RETURNED TO AIRPORT - IVSI REPLACED AND FUNCTION CHECK SERVICEABLE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 GL 2008 12 30 CA081114003 1 20081112 G 2720 2227271300 PEDAL DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA RUDDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3313 (CAN) DURING ROUTINE INSP THE RUDDER PEDAL WAS FOUND CRACKED. 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 20081230 NE 2008 12 30 CA081114004 1 20081103 G 6320 S613522032001 GEARBOX SKRSKY S61 S61N 8142104 NE MAIN ROTOR MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA CFCLM (CAN) MGB HAD A INDICATION ON THE MGB BEING CONTAMINATED WITH METAL. REMOVED THE MGB AND RETURNED IT TO MANUFACTURER WHO DISASSEMBLED THE MGB TO FIND THAT THE CAUSE OF THE METAL CONTAMINATION WAS FROM THE UPPER BRG SUPPORT NUT, P/N: S6135-2 2032-001 THE CAUSE OF THE METAL CONTAMINATION WAS FROM THE UPPER BRG SUPPORT NUT. 2 G 7 2 4U 1H15 20081230 NE 2008 12 30 CA081114005 2 20081104 G 7230 8934825 IMPELLER SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 29073 NE COMPRESSOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2407 (CAN) HOT SECTION INSPECTION WAS BEING CARRIED OUT BY ENGINE SHOP ON ENGINE SN P44659C AND IT WAS NOTED THAT THE IMPELLE R WAS CRACKED. THIS IMPELLER IS NOT TRACKED. THE TIMES ON THE IMPELLER SINCE INSTALL ARE 2407.0 AND 3434 CYCLES. THIS IS NOT THE 1ST INSTANCE OF PROBLEMS IN THIS 2ND STAGE IMPELLER. 2 L 7 2 4T 4 T RT A8SW E4WE 20081230 2008 12 30 CA081114006 2 20081113 G 7200 SB3208A1 BEARING ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RECEIVED NEW BEARING FROM WHS 290 WITH CORROSION ON BEARING JOURNAL AND ROLLERS. CURE DATE ON PACKAGE IS 0206, BEA RING PN SB3208A-1. BATCH PN 0605118341. HSI HAVE BEEN INFORM OF VARIOUS BEARINGS DELIVERED THAT HAVE SIGNS OF CORROSION ON THEM. 20081230 NM 2008 12 30 CA081114007 1 20081114 G 5710 85720013006 STRUCTURE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE RT WING LE DAMAGED W O OTHER C F.O.D. LD LANDING 1 CA 45006 (CAN) BIRD STRIKE ON LANDING RT WING ENGINE AREA. LE NR 3, ACFT INSPECTED IAW AMM 05-50-26. IMPACT DAMAGE CONCENTRATED AT RT NR 3 LE. RT NR 3 LE REPLACED IAW AMM, LEAK AND FUNCTION CHECKED. SERVICEABLE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 EA 2008 12 30 CA081114008 1 20081113 G 5714 FASTENER DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL WING BOX LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 5636 (CAN) DURING INSP, THERE WAS SEVERAL CHERRY MAX RIVETS FOUND TO BE LOOSE ON THE UNDERSIDE OF THE RT WING BETWEEN STATION 35.15 AND 97.50. THE RIVETS WERE ALL LOCATED ON A TRIPLE ROW OF RIVETS AT THE AFT SPAR. FURTHER INSPECTION REVEALED A T OTAL OF 160 RIVETS NEEDING REPLACEMENT. THE RIVETS WERE REPLACED AND THE ACFT RETURNED TO SERVICE. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20081230 NM 2008 12 30 CA081114009 1 20081112 G 5310 STRUCTURE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE FUSELAGE DAMAGED W O OTHER C F.O.D. DE DESCENT 1 CA (CAN) FLT ENCOUNTERED MULTIPLE BIRD STRIKES AT 4000 FT, DURING AN APPROACH FOR LANDING INTO AIRPORT. CREW CONTINUED ON D ESCENT PATH AND LANDING UNEVENTFUL. MX REQUESTED. SUBSTANTIAL DAMAGE TO THE RT SIDE OF RADOME AND STRUCTURE IMMEDIATELY BEHIND RADOME FROM IMPACT OF GOOSE. ALSO EVIDENCE OF ANOTHER GOOSE HAVING STRUCK THE LT SIDE OF ACFT. POINT OF IMPACT BE ING JUST ABOVE LT ENGINE INTAKE. GOOSE HAD SUBSEQUENTLY ENTERED INTAKE AND EXITED THROUGH THE OPEN ENG INTAKE BYPASS DOO R THAT WAS DAMAGED AS WELL. ACFT INSPECTED IN AIRPORT. RADOME REPLACED AND ACFT WAS THEN FERRIED TO MX BASE, UNDER A FE RRY FLT PERMIT. RADOME REMOVED AGAIN TO FACILITATE REPAIRS TO BULKHEAD ON NOSE BEHIND RADOME. WEATHER RADAR ALSO REPLACE 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 2008 12 30 CA081115001 4 20081112 G 2312 G340ENI CONTROL HEAD CVAC 340 340CVAC 242270A WP ALLSN 501D 501D13D 03004 GL ALLSN A6441 A6441FN606 GL COCKPIT CONTAMINATED W O OTHER H ELECT. POWER LOSS-50 PC AP APPROACH 1 CA (CAN) DURING APPROACH COM BECAME TEMPORARILY UNUSABLE DUE TO WATER CONTAMINATION IN COMM CONTROL HEAD. PART REMOVED AND DRIED OUT AND FUNCTION TESTED SERV, NO FURTHER PROBLEMS. 2 L 7 2 4R 4 T 6A6 E282 6 C P898 20081230 EA 2008 12 30 CA081117002 1 20081114 G 2750 865D1007 DRIVE SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) FLAP FAIL MESSAGE AFTER SELECTING FLAP, FLAPS FAILED AT 8 DEGREES. ACFT LANDED SAFELY WITH FLAPS AT 8 DEGREES. REPLACED PDU, COMPLETED FLAP TORQUE CHECK, CHECKED FOR ACTUATOR OVER TEMP IAW AMM 27-52-01-000-8001 AND AMM 27-53-00-750 -802. FLAP SYS CHECKS SERVICEABLE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081230 SW 2008 12 30 CA081117003 1 20081113 G 8012 31057463 IGNITION SWITCH SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE3311 01514 WP MCAULY 4HFR34 4HFR34C652 NE COCKPIT CRACKED W A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA (CAN) ACFT DEPARTED AIRPORT AND CREW NOTICED SMOKE IN THE CABIN. THE CREW TURNED THE TEMP CONTROLLER OFF - THE BLEEDS WE RE TURNED OFF WHICH DUMPED THE CABIN PRESSURIZATION. THE LOW OIL PRESSURE LIGHT CAME ON ALONG WITH THE EGT STARTING TO RISE. ENGINE WAS THEN SHUTDOWN AND FEATHERED AT THIS POINT. ACFT RETURNED TO POINT OF ORIGIN AND LANDED WITHOUT INCIDEN T. MX WAS CONTACTED AND THEY DISCOVERED THE AUTO IGNITION SWITCH WAS CRACKED ALLOWING THE ENGINE OIL TO BLEED OUT OF THE ENGINE. THE SWITCH WAS REPLACED - GROUND RUNS CARRIED OUT IAW EMM AND ACFT RETURNED TO SERVICE. 2 L 7 2 4T 3 T RT A8SW E3WE 6 C 3PNE 20081230 EU 2008 12 30 CA081117004 1 20081114 G 6700 ASNA013735E2 BEARING RACE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE INNER R ACE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) A 12 YEAR INSP WAS BEING CARRIED OUT ON THE HELICOPTER. 2 CRACKS WERE FOUND ON THE INNER RACE OF A BALL BEARING A SSY. THE CRACKS ORIGNALLY STARTED FROM THE RIVET HOLES. THE BEARING ASSY/SUPPORT ATTACH THE INNER RACE OF BEARING BY 4 R IVETS TO THE PILOT`S CYCLIC FOR AND AFT TORQUE TUBE LOCATED UNDER THE CABIN FLOOR. THIS IS THE SECOND 12 YEAR INSPECTION FOR THIS HELICOPTER. 1 G 7 1 3U 3 U H9EU E19EU 20081230 2008 12 30 CA081117005 4 20081113 G 2210 103791101 CIRCUIT BOARD BEECH 200 200BEECH 1152920 CE PWA PT6 PT642A NE HARTZL HCE4N HCE4N3 NE AUTOPILOT INTERMITTENT W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CL CLIMB 1 CA 428 (CAN) ACFT IN NORMAL CLIMB CONFIGURATION WITH FCS DISPLAYING CLIMB (GREEN) AND ALT ARM (WHITE.) THE VERTICAL MODE DISPLA Y MAY THEN CHANGE TO ALT (GREEN) EVEN THOUGH THE TARGET ALTITUDE IS SEVERAL THOUSAND FT ABOVE (E.G. WITH THE ALT SELECT SET FOR 20,000 FEET, THRU, SAY, 12,000 FT THE VERTICAL MODE WILL CHANGE FROM CLIMB TO ALT) WITH THE VERTICAL MODE IN ALT AND STILL SEVERAL THOUSAND FT BELOW SELECTED ALTITUDE THE ACFT WILL BEGINNING PITCHING UP SEVERAL DEGRESS (+10 DEGREES OR HIGHER) REQUIRING AUTOPILOT DISCONNECT, RESET AND MONITORING BY THE PILOT. ALTITUDE ALERTER REMOVED FOR INSP. INTER NAL PRINTED CIRCUIT BOARD IDENTIFIED AS THE PROBLEM SOURCE AND SUBSEQUENTLY REPLACED. 1 L 7 2 4T 4 T A24CE E4EA 5 C P10NE 20081230 EA 2008 12 30 CA081117006 1 20080926 G 7160 CT2EC10221 YOKE DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL INTAKE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSP, THE YOKE LT INTAKE COWL BROKE AT MACHINED LOCKING TAB EAR CUT OUT UPON INSTALLATION WHILE RIVETING, LT YOKE-INTAKE COWL WAS REPLACED. 1 H 7 1 3T 4 T A806 E4EA 6 C P15EA 20081230 SO 2008 12 30 CA081117007 2 20081115 G 8530 CYLINDER CONT O300 O300C 17022 SO NR 3 CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) NR 3 CYLINDER ASSY WAS FOUND CRACKED BETWEEN THE CYLINDER HEAD AND THE BARREL, APPROX .7500 AROUND THE CICUMFERENC E OF THE ASSY. THIS RESULTED IN LOSS OF COMPRESSION AND ENGINE VIBRATION. 3 O E253 20081230 CE 2008 12 30 CA081118001 1 20081115 G 3040 MS24166DI RELAY BEECH BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL WINDSHIELD HEAT UNSERVICEABLE W H DEACTIVATE SYST/CIRCUITS M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 CA (CAN) CREW DEFECT PILOT WINDSHIELD HEAT NOT WORKING, TROUBLESHOOT TO LOW HEAT RELAY, TERMINAL A2 MELTED OFF THE RELAY AS SY, DAMAGING WIRES ATTACHED TO THE TERMINAL APPROX 3 INCHES BACK THE WIRE COVER MELTED OFF. RELAY WAS REPLACED AND SYS O PERATES PROPERLY. 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 20081230 SW 2008 12 30 CA081118003 1 20081103 G 7603 701981 LOCK TAB AIRTRC AIRTRC AT500 AT502B 0390307 SW PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL POWER LEVER CRACKED W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 4325 (CAN) FCU FUEL CONDITION LEVER LOCK SPRING TAB THAT IS USED TO PREVENT THE LEVER MOVING TO FUEL CUT-OFF HAS FAILED. 1 L 7 1 3T 4 T NC A17SW E4EA 6 C P15EA 20081230 NM 2008 12 30 CA081118004 1 20081116 G 2910 82970009325 LINE DHAV DHC8 DHC8201 2809001 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE NR 2 HYD SYS CRACKED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA 24324 (CAN) ON DESCENT AT NIGHT IN HEAVY RAIN, FLIGHT CREW GOT NR 2 HYD PUMP CAUTION FOLLOWED BY TOTAL LOSS OF QUANTITY IN NR 2 HYD SYS. LEVELED AT F110 FOLLOWED QRH, DECLARED PAN, BRIEFED F/A AND PASSENGERS ON RETURN TO BASE FOR NORMAL LANDING WITH PRECAUTIONARY SERVICES IN ATTENDANCE. LINE MAINT INVESTIGATION AND CONFIRMED DEFECT, TRACED LEAK TO `RIGID LINE` P/ N 82970009-325. WALL OF LINE FOUND CRACKED ADJACENT TO AN END FITTING. RIGID LINE REPLACED WITH NEW ITEM. AS ENGINE DRI VEN HYD PUMP WAS RUN IN FLIGHT FOR LONGER THAN FIFTEEN MINUTES, IT WAS ALSO REPLACED AS REQUIRED BY ACFT MANUAL. ALL SYS FUNCTIONED IAW THE AIRCRAFT`S MM. THE ACFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 GL 2008 12 30 CA081118005 1 20081117 G 2720 TUBE DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA RUDDER PEDAL WORN W K NONE O OTHER IN INSP/MAINT 1 CA 4521 (CAN) INSP OF THE RUDDER PEDAL ASSY REVEALED EXCESSIVE WEAR ON THE S TUBE CAUSED BY WEAR FROM THE RUBBER CABLE. THE WEAR WAS DETECTED BY VISUALLY CHECKING THE OUTSIDE OF THE S TUBE FOR MATERIAL DEFORMATION IN THE AREA WHERE THE CABLE CAUSES THE MOST FRICTION ON THE INSIDE OF THE TUBE. THE RUDDER PEDAL ASSY AND CABLE WERE REPLACED WITH NEW. 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 20081230 NM 2008 12 30 CA081118006 1 20081114 G 3220 82253 TUBE MESSIER 8200103 DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE NLG BROKEN W O OTHER O OTHER LD LANDING 1 CA (CAN) ON SELECTING LANDING GEAR DOWN-PILOT REPORTED A LOUD CRACKING NOISE FROM THE NLG AREA. COULD NOT CONFIRM THAT THE GEAR WAS DOWN AND LOCKED USING NORMAL OR ALTERNATE VERIFICATIONS. AN EMERGENCY LANDING WAS MADE SUCCESSFULLY AFTER A FLY BY INSP SHOWED THAT THE NLG WAS EXTENDED. ACFT MADE A SUCCESSFUL LANDING AND WAS SECURED ON NOSE JACK INSPECTED . INSP REVEALED THAT THE PIVOT TUBE HAD CRACKED AND THAT THE DOWN LOCK HAD NOT GONE FULLY OVERCENTER. PART REPLACED AND ACFT WA S REMOVED OFF THE RUNWAY. AN PHYSICAL INSP OF THE PIVOT TUBE REVEALED THAT THIS WAS A PRE-MOD PIVOT TUBE AND NOT IAW AD CF-95-15. MFG`S ARE INVESTIGATING THE EVENT. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 CE 2008 12 30 CA081118008 1 20081115 G 3310 1015245001 PANEL BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL COCKPIT SMOKE W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 14882 14882 (CAN) ACFT RETURNED SHORTLY AFTER DEPARTURE DUE TO AN ELECTRICAL ODOR AND A WISP OF SMOKE AT THE CO-PILOTS CONTROL WHEEL . IT LASTED FOR A FEW SECONDS AND THEN DISAPPEARED. MX INSPECTED THE ACFT UPON ARRIVAL AND FOUND THAT THE EDGE-LIGHTED P ANEL AT THE CO-PILOTS CLOCK WAS AT FAULT. THE LIGHTING WAS DISABLED AND DEFERRED IAW THE MEL UNTIL REPLACEMENT PARTS ARR IVE. THE AREA WAS INSPECTED AND ADJACENT SYS TESTED WITH NO ADDITIONAL FAULTS NOTED AND THE ACFT RELEASED. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 20081230 SW 2008 12 30 CA081118010 1 20081118 G 7120 5082119 MOUNT AIRTRC AT602 AT602 0390309 SW PWA PT6 PT6A65AG 52043 NE HARTZL HCB5M HCB5MP3 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2498 (CAN) DURING THE 300HR/ANNUAL INSP, ENGINE MOUNT WAS BEING INSPECTED IAW AD2008-10-12 AND AIR TRACTOR`S SL NR 253C, A C RACK WAS FOUND ON THE LT LOWER ENGINE ATTACH POINT VIA 10X MAGNIFYING GLASS. ACFT HAS BEEN NOTIFIED ABOUT THE CRACK AND A NEW ENGINE MOUNT HAS BEEN SINCE INSTALLED WITH THE GUSSET UPGRADE IAW AD2008-10-12 AND SL NR 253C WHICH WAS SUPPLIED BY THE MFG. 1 L 7 1 3T 4 T NC A19SW E4EA 6 C P44GL 20081230 NM 2008 12 30 CA081119001 1 20081119 G 5330 SKIN EMB ERJ170 ERJ170100SE 3260406 NM FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACKS WERE SUSPECTED AFTER GVI AND CONFIRM BY NDT RADIATING FROM ONE FASTENER HOLE IN LT FUSELAGE SKIN PANEL AT F RAME 94 STR 03 AND 04 LT AND SAME AT FRAME 94 STR 03 AND 04 RT. 2 L 7 2 4F RT A56NM 20081230 EA 2008 12 30 CA081119002 1 20081118 G 2751 800440304 PROXIMITY SENSOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAILED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA (CAN) FLIGHT WAS SET UP FOR LANDING AND SELECTED FLAPS TO 8 DEGREES. FLAPS ON 1 SIDE CAME DOWN TO 2 DEGREES AND FLAPS ON THE OTHER SIDE REMAINED AT 0 DEGREES. AN EMERGENCY WAS DECLARED AND PASSENGERS WERE BRIEFED. FLIGHT LANDED WITHOUT FURT HER INCIDENT AND STOPPED ON RUNWAY FOR FIRE CREWS TO DO A WALK AROUND AND THEN TAXIED TO THE GATE. MX TROUBLESHOOTING IA W FAULT CODES AND SKEW DETECTOR INDICATION LED TO REPLACEMENT OF THE LT L3 (P/N 8044-04, S/N 2676) AND L4 (P/N 80-044-03 , S/N 2676) SKEW DETECTOR PROXIMITY SENSORS. FLAP OPERATION AND SKEW DETECTOR SYS OPS CHECKS CARRIED OUT WITH NO FURTHER FAULTS AND THE ACFT WAS RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081230 NE 2008 12 30 CA081119003 2 20081118 G 7261 0292507350 BEARING SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE BLOCKED W K NONE O OTHER IN INSP/MAINT 1 CA 3412 660 (CAN) OIL WAS COMING OUT OF TURBINE EXHAUST AND M03 BEARING VENT TUBE ON START UP. DISASSEMBLED THE ENGINE AND FOUND M03 REAR BEARING CAKED WITH BURNED OIL. M03 REAR BEARING OIL RETURN TUBE PARTIALLY BLOCKED WITH BURNED OIL. 1 G 7 1 3U 3 U H9EU E19EU 20081230 NM 2008 12 30 CA081119004 1 20081118 G 2750 MS391130Z MOTOR BOEING 727 727225 1384077 NM PWA JT8 JT8D9A 52048 NE TE FLAPS FAILED W O OTHER K FLUID LOSS CR CRUISE 1 CA (CAN) ENROUTE, SYS A HYD QTY DROPPED TO ZERO. MX FOUND OTBD FLAP HYD MOTOR FAILED. MOTOR REPLACED AND SYS CHECKED SERV ICABLE. 2 L 7 3 4F 4 F A3WE E2EA 20081230 EU 2008 12 30 CA081120001 1 20081119 G 2560 SL12 BUCKLE GROB GROB G115 G115C 1660303 EU LYC O320 O320D1A 41508 EA SEAT BELT ASSY UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA 437 (CAN) BUCKLE WOULD NOT RELEASE. 1 L 7 1 3O 3 O NT A57EU E274 20081230 CE 2008 12 30 CA081120002 1 20081118 G 2840 MONITOR BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA MCAULY 4HFR34 4HFR34C762 NE FUEL QTY FAULTY W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PILOT REPORT ERRATIC ON FUEL QTY INDICATION. TROUBLESHOOTING REVEALED FAULTY CONTROL MONITOR. MONITOR REPLACED BY REPAIRED UNIT THAT FAILED 2 DAYS LATER, REPLACED WITH OTHER ONE FROM SAME VENDOR THAT DOESN`T WORK, SWAPPED WITH AN SER VICEABLE UNIT FROM AN OTHER ACFT (FLTS) TO CONFIRMED TROUBLESHOOTING. IT TAKES 3 DIFFERENT UNIT TO FINALLY FIXED THE PRO BLEM. 1 L 7 2 3T 4 T A14CE E4EA 6 C 3PNE 20081230 NM 2008 12 30 CA081120003 1 20081107 G 3240 900005831PR BRAKE SYS EMB ERJ170 ERJ170200SU NIR NM GE CF34 CF348E5A1 30062 NE MLG DISINTEGRATED W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) DURING PUSHBACK, GRND PERSONNEL REPORTED SMOKING BRAKES. FOUND NR3 BRAKE ROTORS HAD FAILED. REPLACED BOTH NR3 WHEE L AND BRAKE ASSY IAW AMM 32-49-05 AND 32-49-11. S/N OF THE BRAKE IS JAN05-0530. 2 L 7 2 4F 4 F RT A56NM E00063EN 20081230 SW 2008 12 30 CA081120004 1 20081116 G 6220 K974004107 MOUNT KAMAN K1200 K1200 05625F6 SW LYC T53 T5317A 41549 NE M/R HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK DISCOVERED ON LT FWD STRUT MOUNT FITTING. 1 G 7 1 4F 4 U NT TR7BO E17EA 20090102 NE 2009 1 2 CA081120005 2 20081106 G 7532 BRH10211 BLEED VALVE BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) IT HAS BEEN REPORTED BY OPERATOR THAT BVV LEVER WAS NOT OPERATING PROPERLY. ENG WAS REMOVED IN UNSERVICEABLE CONDI TION DUE TO BOOSTER BLEED VALVE MECHANISM MALFUNCTION. ENG IN RRC FOR REPAIR. DURING INITIAL INSP, IT WAS CONFIRMED TH AT BOOSTER BLEED VALVE RING ASSY (ATA 72-38-19 01-400) WAS NOT OPERATING PROPERLY. STRIP WAS CARRIED OUT TO EXPOSE THE B OOSTER BLEED VALVE MECHANISM AND IT WAS NOTED THAT ONE PIN (ATA 72-38-19 01-408) AND ONE RETAINING RING (ATA 72-38-19 01 -409) WERE MISSING. THIS PIN IS AT THE CONNECTION BETWEEN THE BELL CRANK LEVER ASSY (ATA 72-38-19 01-100) AND THE BOOSTE R BLEED VALVE RING ASSY (ATA 72-38-19 01-409) AT TOP DEAD CENTER POSITION (ACTUATING ROD POSITION). (6) REMAINING PINS 2 L 7 2 4F 4 F TR A6WE E00061EN 20081230 EU 2008 12 30 CA081120006 1 20081119 G 6220 350A37116200 STOP SNIAS 350 AS350B2 8680813 EU LYC LTS101 LTS101* NE MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2834 (CAN) CRACK DISCOVERED ON 2 OF THE 3 YOKE, STOP, ASSYS REMOVED FROM THE ACFT DURING NDT. THE CRACKS ARE ALLONG THE SECON D RADIUS FROM THE TOP, AND WERE NOT VISIBLE TO THE NAKED EYE. 1 G 7 1 3U 3 U H9EU E5NE 20081230 EU 2008 12 30 CA081120007 1 20081119 G 6220 350A37116200 STOP SNIAS SNIAS 350 AS350B1 8680811 EU ROTOR SHAFT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10002 (CAN) CRACK DETECTED IN 2 OF THE 3 YOKE, STOP, ASSYS ON THE MAST. FOUND DURING A 6 YEAR CORROSION INSPECTION OF THE MAST . THE PARTS WERE SENT FOR NDT AS PART OF THE AVIATION INSP PROCEDURES FOR THE MAST ASSY (NO MFG REQUIREMENT IN THE TECHN ICAL PUBLICATIONS TO NDT THESE PARTS). CRACK NOTED IN THE SECOND RADIUS FROM THE TOP. 1 G 7 1 3U H9EU 20081230 2008 12 30 CA081121001 4 20081120 G 3420 7004544314 SYMBOL GENERATOR DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE NR 1 FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 30171 458 (CAN) SHORTLY AFTER TAKEOFF, THE CAPT`S PRIMARY FLIGHT DISPLAYS WERE MALFUNCTIONING, CAPTS EADI AND EHSI ARE BLANKING OU T INTERMITTENTLY , CREW ELECTED TO RETURN TO ORIGINATING AIRPORT. MX REPLACED NR 1 SYMBOL GENERATOR AND ACFT RETURNED T O SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 EA 2008 12 30 CA081121002 1 20081120 G 2750 855D1009 CONTROL UNIT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS FAILED W D RETURN TO BLOCK F J FLT CONT AFFECTED WARNING INDICATION TX TAXI/GRND HDL 1 CA 27770 27770 (CAN) DURING PUSH BACK FROM THE GATE, FLAP LEVER WAS MOVED TO 8 DEGREES BY THE FLIGHT CREW BUT THE FLAP DIDN`T EXTEND AN D "FLAP FAIL" CAUTION MESSAGE APPEARED ON THE ENGINE INDICATION AND CREW ALERTING SYS (EICAS). THE ACFT WAS TOWED BACK T O THE GATE. FLAP ELECTRONIC CONTROL UNIT (FECU) FAULT CODES WERE RETRIEVED AND DECISION WAS MADE TO REPLACE THE RT BRAKE POSITION SENSOR UNIT (BPSU). THE UNIT WAS REPLACED AND THE ACFT RETURNED INTO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 20081230 NM 2008 12 30 CA081121003 1 20081119 G 2150 8209063 ACM BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU RIGHT ODOR W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) IN CRUISE F/A CALLED TO REPORT SMELL AND MIST. ASKED FOR AN UPDATE IF IT WORSENED, THEN PREPARED FOR OXYGEN DRILL IAW QRH. ON APPROACH TO LAND THE (CABIN PACK HOT CAUTION) LIGHT CAME ON. THE QRH WAS CONSULTED AGAIN AND THEN THE CAUTIO N LIGHT WENT OUT. WE THEN LANDED AND COMPLETED THE FLIGHT NORMALLY. ON-SITE LINE MX INVESTIGATION IDENTIFIED THE RT (CA BIN) AIR CYCLE MACHINE (ACM) TO BE NON-OPERATIONAL DUE BEING SEIZED. FUNCTIONAL CHECK AIR CONDITIONING SYS SATISFACTORY WITH FLIGHT COMPARTMENT PACK ONLY WITH TEMP COMTROL AT 1 O`CLOCK POSITION. ACFT POSITIONED BACK TO MX BASE UNDER MEL 21- 50-1PROVISIONS. ACM REPLACED AND TESTED IAW THE MM 21-51-21. ACFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081230 EU 2008 12 30 CA081121004 1 20081121 G 5751 SEAL PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL LT AILERON SPLIT W K NONE O OTHER IN INSP/MAINT 1 CA 7654 7654 (CAN) THE AILERONS WERE REMOVED AT THE ANNUAL INSP FOR BEARING REPLACEMENT. A SMALL RIP WAS FOUND IN THE INNER SEAL OF T HE LT AILERON WHICH ATTACHES BETWEEN THE WING AND THE AILERON BALANCE WEIGHT ATTACHMENT. WHEN THE MS35207-XXX SCREWS WER E REMOVED THE WERE FOUND TO BE CORRODED. THE AREA WAS INSPECTED FOR CORROSION CLEANED AND NEW SCREWS INSTALLED WITH CPC GRADE 2 COMPOUND. THE RT AILERON WAS INSPECTED AND FOUND WITH SIMILAR CORROSION. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20081230 CE 2008 12 30 CA081121005 1 20081119 G 2435 23080023A STARTER GEN LEAR 35 31A 5170531 CE GARRTT TFE731 TFE73123B WP NR 1 FAILED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA 235 (CAN) GENERATOR FELL OFF, INE AND A SLIGHT VIBRATION WAS FELT. 2 L 7 2 4F 4 F RT A10CE E6WE 20081230 GL 2008 12 30 CA081121006 1 20081120 G 2720 2227271200 TUBE DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA RUDDER PEDAL WORN W K NONE O OTHER IN INSP/MAINT 1 CA 2794 (CAN) DURING THE ACFT PRE-FLIGHT THE PILOT REPORTED THAT THE RUDDER PEDAL ASSY ON THE RT SIDE WAS DIFFICULT TO ADJUST AL ONG THE SLIDE TUBE ASSY. CLOSER INSPECTION BY MAINT REVEALED THAT THE RT OTBD FWD RUDDER CABLE HAD WORN THROUGH THE S-TU BE THAT IS WELDED TO THE PEDAL ASSY. CABLE WAS EXPOSED THROUGH THE LOWER BEND OF THE S-TUBE TO A POINT WHERE IT WAS JAM MED IN ITS WEAR HOLE THUS RESRICTING THE SLIDE ACTION OF THE PEDAL ASSY. THE DEFECTIVE PARTS ARE BEING REMOVED FOR REPLA CEMENT WITH NEW. 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 20081230 GL 2008 12 30 CA081121007 1 20081107 G 2910 1005354226007 LINE BOMBDR BD100 BD1001A10 1390044 GL HYDRAULIC SYS CHAFED W O OTHER K FLUID LOSS CR CRUISE 1 CA 5443 (CAN) ACFT LOST ALL HYD FLUID IN THE RT SYS DURING FLIGHT. NO INFO ON FLIGHT PROFILE, CAS MESSAGES OR QTY`S NOTED. CREW UNAVAILABLE FOR DEBRIEF AT THIS TIME. REPLACED AFFECTED LINE, CLAMP AND HARDWARE. 2 L 7 2 4F RT T00005NY 20081230 GL 2008 12 30 CA081121009 1 20080711 G 2910 1005354226007 LINE BOMBDR BD100 BD1001A10 1390044 GL HYDRAULIC SYS CHAFED W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 5162 (CAN) DURING CRUISE FLIGHT, THE AMBER (R HYD PRESS LOW) CAS MESSAGE ILLUMINATED. PILOT OBSERVED THE HYD SYNOPTIC PAGE AN D NOTED THE FLUID LEVEL IN THE RT HYD RESERVOIR BEGAN DROPPING. ACFT BEGAN DESCENT. DURING APPROACH, PILOT NOTED THE RT HYD RESERVOIR QUANTITY WAS READING (4 PERCENT). AFTER LANDING, VISUAL INSP OF THE ACFT REVEALED HYD FLUID STREAMING FROM THE WHEEL WELL AREA TO THE TAIL OF THE ACFT. FOUND LINE IN THE AFT EQUIPMENT BAY HAD A HOLE CHAFED INTO IT BY A FAIRLE AD BLOCK. 2 L 7 2 4F RT T00005NY 20081230 2008 12 30 CA081121010 1 20081119 G 3411 20131421B STATIC LINE PITOT/STATIC SY UNBONDED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) FITTING GLUE AND LINE GOING TO IT IS ALUMINUM WITH A COMPRESSION FITTING WHEN LINE WAS TIGHTEN TO ENSURE NO STATIC LEAK THE GLUE THAT ADHEARS THE FITTING LET GO THIS SUBMITTED ON BEHALF OF SKYLINE MAINT AND AVIONICS AMO 21-80. 20081230 NM 2008 12 30 CA081121011 1 20081120 G 3230 656021132 ACCESSORY UNIT BOEING 727 727227 1384078 NM PWA JT8 JT8D9A 52048 NE MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) JUST AFTER TAKEOFF, THE CREW ATTEMPTED TO SELECT GEAR UP, THE GEAR HANDLE WOULD NOT GO PAST THE OFF POSITION. ACF T RETURNED TO WHERE MAINT REPLACED THE LANDING GEAR ACCY UNIT. A/C RETURNED TO SERVICE. 2 L 7 3 4F 4 F A3WE E2EA 20081230 EU 2008 12 30 CA081121012 1 20081120 G 2913 S40 COUPLING SLEEVE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE HYD PUMP WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING DISASSEMBLY FOR OTHER WORK THE HYD PUMP WAS REMOVED AND THE SPLINE DRIVE WAS FOUND EXTREMELY WORN. PART S40 WAS FOUND TO HAVE ALMOST NO SPLINE AT ALL REMAINING AND THE JOINING HYD PUMP PN A5026780 HAD IT`S SPLINES WORN TO HALF THEIR NORMAL WIDTH. THERE IS ALREADY AN AD CF2004-10 AND AN SB 29.00.04 ON THIS ISSUE. ESTIMATED TIME TO FAILURE OF HYD DRIVE WAS LESS THAT 100 HOURS. 1 G 7 1 3U 3 U H9EU E19EU 20081230 NM 2008 12 30 CA081122001 1 20080929 G 5312 BULKHEAD BOEING 727 727225 1384077 NM PWA JT8 JT8D9A 52048 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING WALK-AROUND INSP, FOUND BELTFRAME AT 9G BULKHEAD CRACKED BY LT CARGO CAN CUTOUT. TEMPORARY REPAIR CARRIED O UT. A/C FERRIED. PERMANENT REPAIR CARRIED OUT. ACFT RETURNED TO SERVICE. 2 L 7 3 4F 4 F A3WE E2EA 20081230 EA 2008 12 30 CA081122002 1 20081117 G 2752 852D10021 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA TE FLAPS FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 2078 (CAN) FLAP FAIL IN APPROACH WHEN SELECTED FROM 0 DEGREE. FLAP FAILED AT 0 DEGREE. 2 L 7 2 4F RT A21EA 20081230 EA 2008 12 30 CA081122003 1 20081117 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) DECENDING THROUGHT 10,000 FT, FLT CREW REPORTED FLAP FAIL MSG WITH FLAPS AT 0 DEG, AIRSPEED WAS 250 KTS. QRH FOLL OWED AND ACFT LANDED WITHOUT FURTHER INCIDENT. COMPLIED WITH FLAP RESET IAW SUPPLEMENT 98-018B (CB RESET) AND FLAPS OPS CHECKED NORMAL. ACFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 20081230 EA 2008 12 30 CA081122004 1 20081116 G 2742 AV67023105 ACTUATOR CNDAIR CL600 CL6002C10 1390015 EA HORIZONTAL STAB LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AV670-23105-003 (LT) AND -004 (RT) DURING ROUTINE MX ON THE HORIZONTAL STAB TRIM ACTUATOR (HSTA), LOOSE BOLTS (IT EMS 24 AND 35) WERE FOUND IN THE UPPER BOLT LOCATIONS OF THE RT AND LT HSTA UPPER ATTACHMENT FITTING ASSY ITEM 33). 2 L 7 2 4F RT A21EA 20081230 EA 2008 12 30 CA081122005 1 20081111 G 2120 UNKNOWN CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE SMOKE W C ABORTED TAKEOFF B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TO TAKEOFF 1 CA (CAN) "A08C0232: AS FLIGHT WAS ON THE TAKEOFF RUN, WHEN THE CREW RECEIVED A CAUTION MESSAGE FOR SMOKE IN THE LAVATORY. T HE TAKEOFF WAS REJECTED AT 60 KTS AND ARFF WAS CALLED OUT. THE FLIGHT RETURNED TO THE APRON, PASSENGERS WERE DEPLANED, A ND MX INSPECTED THE AIR CONDITIONING PACKS AND THE ACFT WAS RETURNED TO SERVICE. AFTER DE-ICING AGAIN, ANOTHER TAKEOFF W AS ATTEMPTED, BUT WAS REJECTED AT 100 KTS WHEN THE SMOKE IN THE LAVATORY CAUTION MESSAGE OCCURRED AGAIN. THE ACFT WAS IN SPECTED AND FERRIED, WHERE MX IS CHANGING THE RT ENGINE (GE CF34-3B1). 2 L 7 2 4F 4 F RT A21EA E15NE 20081230 EA 2008 12 30 CA081122006 1 20081110 G 5610 NP13922001 WINDOW CNDAIR CL600 CL6002B19 1900309 EA COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA (CAN) F/O SIDE WINDOW IS CRACKED. INNER PLY. ALSO SMALL SLIVER FROM RT WINDOW HAS CHIPPED OFF APPROX 2 INCHES BY .25 IN CH AT THE WINDOW EDGE. CALLED TO VERIFY THE CRACKED PLY. ACFT TO FERRY UNPRESSURIZED FOR REPAIRS". 2 L 7 2 4F RT A21EA 20081230 WP 2008 12 30 CA081124001 1 20081006 G 3246 BUNGEE FEDERAL DOUG DC3 DC3CS4C4G 3021460 WP PWA PT6 PT6A67R 52043 NE SKI MISMARKED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) DURING AERIAL WORK WITH SKIS INSTALLED THE RT MAIN GEAR DID NOT EXTEND FULLY. WITH THE ASSISTANCE OF A BELLY MOUNT ED CAMERA THE CAUSE WAS DETERMINED TO BE THE SKI FWD LIMIT CABLE ASSY. THE LANDING GEAR WAS CYCLED AND EXTENDED SUCCESSF ULLY. BOTH LT AND RT SKI FWD LIMIT CABLE ASSEMBLIES WERE REPLACED. THE ENSUING INVESTIGATION DETERMINED THAT THE BUNGEE ASSEMBLIES ON THE FWD LIMIT CABLE ASSEMBLIES WERE TOO LONG ALLOWING THE CABLE TO HOOK ITSELF UNDER THE SKI PIVOT BOLT NO T ALLOWING THE LANDING GEAR TO EXTEND FULLY. THE PROPER LENGTH BUNGEE WOULD NOT ALLOW THE CABLES TO BE LOCATED IN THAT A REA. THE ORIGINALLY INSTALLED BUNGEE ASSEMBLIES WERE UNITS SUPPLIED BY THE ACFT STC HOLDER, WHO HAS BEEN NOTIFIED OF THE 2 L 7 2 4R 4 T A669 E26NE 20081230 EA 2008 12 30 CA081124002 1 20081123 G 2497 D3899920MJ43SN CONNECTOR CNDAIR CL600 CL6002D24 1390016 EA BURNED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) AT APPROX 1540Z AT 15000 FT 220 KIAS AS THE PF WAS CHECKING THAT THE PITCH DISCONNECT SYS WAS RE-ENGAGED. A LOUD N OISE WAS HEARD IN THE COCKPIT, AT THE SAME TIME THE PILOTS WINDSHIELD WIPER MOVED .2500 DISPLACEMENT AND THE A/SKID INBD , INBD BRAKE BRESS AND OB BRAKE PRESS CAUTION MESSAGES POSTED. MDC WAS CHECKED FOR FAULTS AND INDICATED TRU 1, ESS TRU 1 AND A/SKID INBD HAD FAILED. CB`S CHECKED, 1B5 TRU 1, 1G4 ANTI-SKID, 1G5 WIPER PILOT, 1G10 MAINT LIGHT, 1T2 ESS TRU 1, A ND 2G3 BRAKE PRESS IND FOUND TO BE POPPED. DUE TO ELECTRICAL FAILURE AND NO INDICATIONS OF BRAKE PRESSURE, EMERGENCY DEC LARED AND EMERGENCY VEHICLES REQUESTED FOR LANDING. AFTER LDG, ACPC CB`S FOR HYD PUMP 1B, 2B, 3A POPPED. 2 L 7 2 4F RT A21EA 20081230 SW 2008 12 30 CA081124003 1 20081121 G 3260 MS243314 SWITCH SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE MLG FAILED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) AFTER TAKEOFF CREW WAS UNABLE TO RETRACT THE ACFT LANDING GEAR. THE CREW ELECTED TO RETURN TO AIRPORT OF ORIGIN AN D CONTACT MX. THE ACFT WAS FERRIED HOME WITH THE GEAR DOWN. UPON INSP FROM MX, THE MLG SAFETY SWITCH WHICH CONTROLS THE AIR/GROUND PORTION OF THE LANDING CONTROL SYS WAS FOUND TO BE INOPERATIVE. MX CHANGED THE SWITCH AND THE GEAR FUNCTIONE D CHECKED SERVICEABLE. TOTAL TIME ON THE SWITCH COULD NOT BE DETERMINED. 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 20081230 SW 2008 12 30 CA081124004 1 20081117 G 3260 MS243314 SWITCH SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110U 29066 NE HARTZL HCE4N HCE4N3 NE INTERNAL FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN ATTEMPTED ENGINE START THE CREW WAS UNABLE TO GET ENGINE ROTATION OR LIGHT OFF. MX INVESTIGATED AND DETE RMINED THE MLG SAFETY MICROSWITCH WHICH CONTROLS THE AIR/GROUND PORTION OF THE ENGINE START CONTROL SYS TO BE INOPERATIV E. MX REPLACED THE SWITCH AND RETURNED THE ACFT TO SERVICE. 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 20081230 SW 2008 12 30 CA081124005 1 20081120 G 3260 1EN516 SWITCH SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE NLG FAILED W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) THE CREW COULD NOT GET A NOSE GEAR DOWN AND LOCKED INDICATION AFTER SEVERAL DOZEN GEAR POSITION CYCLES OR WITH MAN UAL GEAR EXTENSION. WITH THE LAST ATTEMPT IT ILLUMINATED WITH ELECTRICAL SELECTION. EMERGENCY SERVICES AT AIRPORT WERE O N STANDBY. THE ACFT LANDED AND MX DISCOVERED THAT ONE OR BOTH OF THE NOSE LANDING GEAR DOWNLOCK SWITCHES WAS INOPERATIV E. MX REPLACED BOTH SWITCHES AS A PRECAUTION AND GEAR FUNCTIONAL CHECKS COMPLETED. NO FURTHER PROBLEMS WITH THE LANDING GEAR SYS HAVE OCCURED. 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 20081230 SW 2008 12 30 CA081124006 1 20081121 G 3260 1EN516 SWITCH SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCE4N HCE4N3 NE NLG FAILED W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) ON APPROACH TO LAND THE FLIGHT CREW COULD NOT GET THE GREEN DOWN AND LOCKED LIGHT FOR THE NLG TO ILLUMINATE. THE G EAR WAS CYCLES SEVERAL TIMES AND THE EMERGENCY GEAR EXTENSION USED. AFTER SEVERAL MINUTES THE NOSE GEAR DOWN AND LOCKED GREEN LIGHT ILLUMINATED AND THE ACFT LANDED WITHOUT FURTHER INCEDENT. MX TRACED THE PROBLEM TO A INOPERATIVE NOSE LANDI NG GEAR DOWNLOCK MICRO SWITCH. BOTH DOWNLOCK MICROSWITCHES WERE REPLACED AS A PRECAUTION AND THE LANDING GEAR FUNCTION T ESTED. THERE HAS BEEN NO FURTHER RECURRANCE OF THIS ISSUE. 2 L 7 2 4T 4 T RT A8SW E4WE 5 C P10NE 20081230 NM 2008 12 30 CA081124007 1 20081121 G 5751 SUPPORT BRACKET DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE AILERONS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING HEAVY CHECK INSPECTION FOR ACFT (316), BOTH THE LT AND RT AILERON INPUT QUADRANT SUPPORT BRACKET ASSEMBLIES , ON BOTH THE INBD AND OTBD SIDES, WERE FOUND TO HAVE SIGNIFICANT CRACKING. FLEET CAMPAIGN HAS BEEN INITIATED TO INSPE CT THE AFOREMENTIONED ASSEMBLIES ON THE DHC8-300 SERIES ACFT. REFERENCE IPC 27-12-00, FIGURE 10, PAGE 0, ITEM 130. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 NM 2008 12 30 CA081125001 1 20081125 G 2497 WIRE HARNESS BOEING 757 75728A 1384976 NM RROYCE RB211 RB211535E437 54555 NE CHAFED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) IN FLIGHT CREW NOTICED SMOKE AND FLASHES ABOVE ROW 4DEF. MX FOUND WIRING HARNESS CHAFED BY CEILING PANEL RESULTIN G IN EXPOSED WIRES ARCHING. 2 L 7 2 4F 4 F RT A2NM E12EU 20081230 NM 2008 12 30 CA081125002 1 20081125 G 2910 DSC252A40272 FLEX LINE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE HYD SYSTEM BROKEN W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA 16282 (CAN) AFTER LANDING AND PARKING, VISIBLE SMOKE FROM RT LDG. SMOKE DUE TO AN HYD LEAK FROM BRAKE NR 3 BOKEN FLEXIBLE HOSE . HOSE REPLACED IAW AMM 32-42-52. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081230 NM 2008 12 30 CA081125003 1 20081118 G 5610 80260008 WINDSHIELD BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17 EU COCKPIT FAILED W O OTHER O OTHER AP APPROACH 1 CA 568 (CAN) AT ABOUT 500 FT ON FINAL APPROACH TO THE AIRPORT THE RT WINDSHIELD SHATTERED. THE FLIGHT CREWS INITIAL REACTION W AS THAT THE WINDSHIELD HAD SUFFERED A BIRD STRIKE, BUT THIS WAS NOT THE CASE. THERE WAS NO EVIDENCE OF A BIRD STRIKE AND IT WAS THE INNER GLASS PLY THAT SHATTERED AND COVERED THE COPILOT WITH FINE GLASS DEBRIS. THE RESISTANCE OF THE HEATING ELEMENT (TERMINAL L1 AND L2) AND THE TEMPERATURE HEAT SENSORS (TERMINALS CB, DA AND FE) WAS CHECKED AND ALL FOUND TO BE WITHIN THE SPECIFICATIONS THE TEST REQUIREMENTS OF CMM 56-10-12. RT WINDSHIELD REMOVED AND REPLACED WITH A NEW WINDSHIE LD IAW AMM TASKS 56-10-01-000-801, 56-10-01-400-801 AND 30-41-00-710-802. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P17BO 20081230 SO 2008 12 30 CA081125004 2 20081112 G 8500 IO360KB ENGINE CESSNA 172 R172K 2072431 CE CONT O360 IO360KB 17025 SO MCAULY 2A34C 2A34C203 GL MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 2050 (CAN) LOSS OF OIL PRESSURE DURING FLIGHT. PRECAUTIONARY LANDING ON NEARBY LAKE. INSP REVEALED HEAVY METAL CONTAMINATION IN OIL SCREEN, POSSIBLY CRANKSHAFT BEARING. 1 H 7 1 3O 3 O 3A17 E1CE 5 C P3EA 20081230 SW 2008 12 30 CA081125005 1 20081124 G 6500 1400191 WASHER BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL PITCH CHANGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE VERTICAL FIN WAS REMOVED TO FACILITATE SEAL REPLACEMENT OF THE PITCH CHANGE MECHANISM. THE RADIUS WASHERS THAT ARE USED ON THE VERTICAL FIN ATTACHMENT WERE INSPECTED, AND IT WAS NOTED THAT 3 OF THE 4 WASHERS HAD CRACKS ON THE OUTS IDE PERIMETER OF THE WASHER. THE WASHERS P/N 140-019-1 WERE REPLACED AND THE FIN RE-INSTALLED. IT IS NOT KNOWN IF THIS C ONDITION IS DUE TO OVERTIGHTENING OF THE FASTENER, OR THE INCREASE IN TORQUE VALUE FOLLOWING ISSUANCE OF ASB 206-06-107. 1 G 7 1 3U 3 U H2SW E4CE 20081230 NE 2008 12 30 CA081125006 2 20081111 G 7200 ENGINE CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE FLAMED OUT W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION LD LANDING 1 CA (CAN) DURING SHORT FINAL, UPON REDUCING THE POWER TO IDLE, THE ENGINE FLAMED OUT. THE EVENT OCCURRED AT AN ALTITUDE OF A PPROX. 100 FEET AND THE CREW LANDED THE ACFT SINGLE ENGINE. NOV. 12 2008: ENGINE FLAME-OUT EVENT OCCURRED WHILE DEPLOY ING THE THRUST REVERSERS DURING LANDING ROLLOUT. THIS IS THE SECOND EVENT IN 2 DAYS ON THE SAME ENGINE. TROUBLESHOOTING IS ON-GOING WITH THE HELP OF MFG`S. 2 L 7 2 4F 4 F RT A22CE E25EA 20081230 NE 2008 12 30 CA081125007 2 20081104 G 7200 ENGINE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE VIBRATION W O OTHER E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) AT FL100 IN STEADY STATE, THE PILOT HEARD A STRONG NOISE COMING FROM THE ENG AND THE INSTRUMENTS INDICATED TEMP AT 800°C, NG AT 100 PERCENT AND TORQUE AT 2000 FT-LB. THE POWER LEVER WAS RETARDED AND PARAMETERS CAME BACK TO (NORMAL). THE FLIGHT CONTINUED AND DURING FINAL APPROACH, THE POWER REDUCED TO IDLE UNCOMMANDED AND THE ENG STOPPED RESPONDING TO POWER LEVER INPUTS. THE PILOT WAS ABLE TO LAND SAFELY WITH IDLE POWER. ONCE ON THE GROUND, THE COWLING WAS OPENED AND SM OKE WAS OBSERVED COMING OUT OF THE ENGINE. THE ENG WILL BE REMOVED AND FWD FOR INVESTIGATION. UPDATES WILL BE PROVIDED T O TC. 1 H 7 1 3T 3 T A37CE E4EA 20081230 NE 2008 12 30 CA081125008 2 20081112 G 7200 ENGINE PWA PW120 PW127 NE NR 2 MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB, THE CREW FELT A SUDDEN YAW AND OBSERVED NR 2 ENGINE TEMP GAGE AT MAX. READING ACCOMPANIED BY AN EEC FAULT. NO UNUSUAL NOISES WERE REPORTED BUT PERSONNEL IN THE REAR OF CABIN REPORTED A SPIKE OF FLAME FROM THE EXHAUST. TH E CREW ELECTED TO SHUT THE ENGINE DOWN AND A SINGLE ENGINE LANDING WAS PERFORMED. GROUND INSP FOUND ALL 3 ENGINE ROTORS NOT CAPABLE OF ROTATION. ENGINE WILL BE REMOVED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 4 T E20NE 20081230 NE 2008 12 30 CA081125009 2 20081017 G 7323 GOVERNOR AEROSP ATR42 ATR42300 8680920 EU PWA PW121 PW121 52124 NE OVERSPEED LEAKING W E ENGINE SHUTDOWN J WARNING INDICATION CL CLIMB 1 CA (CAN) TEN MINUTES AFTER TAKEOFF, THE CREW GOT A RT ENG LOW OIL PRESSURE WARNING. THE PROPELLER DID NOT AUTO FEATHER AND THE CREW ATTEMPTED TO FEATHER THE PROPELLER MANUALLY WITHOUT SUCCESS. THE ENGINE REMAINED FUNCTIONING FOR FIVE MINUTES B EFORE THE CREW ELECTED TO SHUT IT DOWN. THE PROP HOWEVER DID NOT FEATHER AND THE ACFT FLEW FOR 60 MINUTES WITH THE ENGIN E SHUTDOWN BUT PROP WINDMILLING AT AROUND 70 PERCENT NP. A SINGLE ENGINE LANDING FOLLOWED. GROUND INSP FOUND AN OIL LEAK AT THE OVERSPEED GOVERNOR HYD PUMP MOUNTING PAD. CHIP DETECTOR CONTAMINATION AND SEIZED LP IMPELLER WAS ALSO OBSERVED. ENGINE WAS REMOVED AND FWD FOR REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLIS 2 H 7 2 4T 4 T RT A53EU E20NE 20081230 NE 2008 12 30 CA081125010 2 20081113 G 7200 OIL SYSTEM BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE ENGINE LEAKING W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) DURING CRUISE AT FL270, THE PILOT NOTICED OIL ODOR AND SMOKE IN CABIN. HE ELECTED TO SHUTDOWN THE ENG AND SHORTLY AFTER, PERFORMED A UNEVENTFUL SINGLE ENGINE LANDING. POST FLIGHT INSP AND GROUND RUNS REVEALED OIL COMING OUT OF THE INL ET AND COMPRESSOR BLEED VALVE. WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 L 7 2 4T 4 T A24CE E4EA 20081230 2008 12 30 CA081125011 1 20081113 G 6100 SLEEVE PWA PT6 PT6A68 NE PROP TRANSFER DAMAGED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS AP APPROACH 1 CA (CAN) WHILE IN THE VFR PATTERN THE ACFT EXPERIENCED A LOSS OF POWER ACCOMPANIED BY A CHIP LIGHT. THE ENG STABILIZED AT A REDUCED POWER SETTING AND 85 PERCENT NP AND THE CREW MADE AN EMERGENCY LANDING. AN INSP OF THE PROPELLER TRANSFER SLEEV E REVEALED BLUING. THE ENGINE IS TO BE REMOVED AND REPLACED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROO T CAUSE ONCE ESTABLISHED. 4 T E26NE 20081230 NE 2008 12 30 CA081125012 2 20081116 G 7200 ENGINE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE LEFT FAILED W A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, WITH NO WARNING THE LT ENG SHUTDOWN ACCOMPANIED WITH A LOUD NOISE. THE FIRE WARNING FOLLOWED AND TH E CREW DISCHARGED BOTH FIRE BOTTLES BEFORE DIVERTING THE FLIGHT WHERE A SINGLE ENGINE LANDING WAS ACCOMPLISHED. POST FLI GHT INSP REVEALED THAT THE PROPELLER WAS HARD TO ROTATE AND DEBRIS WERE FOUND IN THE ENG TAILPIPE. MFG WILL CONTINUE INV ESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A13NM E20NE 20081230 NE 2008 12 30 CA081125013 2 20081115 G 7321 EEC AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE LT ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) DURING CLIMB PASSING FL110, A SEVERE YAW TO THE LT WAS FELT AND THE CREW NOTED THAT THE LT ENG INDICATED 0 TORQUE (ENGINE STILL RUNNING). ATTEMPTS TO REGAIN ENG PWR WERE UNSUCCESSFUL AND THEY ELECTED TO RETURN TO THE POINT OF DEPARTUR E. SHORTLY AFTER, VIBRATIONS WERE FELT AND THE CREW SHUT THE ENGINE DOWN. A SINGLE ENGINE LANDING FOLLOWED. TROUBLESHOOT ING LED TO THE REPLACEMENT OF THE ENGINE ELECTRONIC CONTROL BEFORE THE ACFT WAS RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT E20NE 20090102 EA 2009 1 2 CA081125014 1 20081011 G 2822 RR12830 PUMP DHAV DHC6 DHC6100 2802610 EA PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL FUEL BOOST DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 6 (CAN) OVERHAULED FUEL BOOST PUMP MAKING GRINDING NOSE WHEN TURNED ON. PUMP REMOVED AND REPLACED WITH OVERHAULED BOOST P UMP. FAILED PUMP HAD ONLY 6.1 HOURS TIME IN SERVICE SINCE OVERHAUL AND 5 FLIGHT CYCLES. FAILED PUMP RETURNED TO INSTALL ER. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 20090102 NE 2009 1 2 CA081125015 2 20081115 G 7200 ENGINE UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206B 0 NE NR 1 MAKING METAL W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE FLIGHT, THE NR 1 ENG CHIP DETECTOR LIGHT ILLUMINATED. THE PILOT "BURNED" THE CHIP DETECTOR AND THE L IGHT WENT OUT. SHORTLY AFTER THE LIGHT CAME ON AGAIN AND THE PILOT BURNED AGAIN AND THE LIGHT WENT OUT. HE DECIDED TO AB ORT THE MISSION AND RETURN TO BASE DURING WHICH TIME HE HEARD A LOUD NOISE FROM THE ENGINE WITH PARAMETER DECAYING. THE ENG WAS SECURED AND AN UNEVENTFUL SINGLE ENGINE LANDING FOLLOWED. GROUND INSP FOUND HEAVY METAL CONTAMINATION AND FRACTU RED POWER TURBINE BLADES. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 G 7 2 3U 3 U O H88EU E42NE 20090102 NE 2009 1 2 CA081125016 2 20081117 G 7200 ENGINE LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE SHUTDOWN W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE AT FL190, THE ENGINE SPOOLED DOWN UNCOMMANDED. EMERGENCY WAS DECLARED AND THE FLIGHT DIVERTED AND A SINGLE ENGINE LANDING WAS ACCOMPLISHED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLIS HED. 2 L 7 2 4F 4 F RT A10CE E35NE 20090102 EA 2009 1 2 CA081125017 2 20081107 G 7230 BLADES PWA PT6 PT6A28 EA COMPRESSOR FRACTURED W A UNSCHED LANDING R X J PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE AT FL170, THE LT ENG LOST POWER AND THE TEMP INCREASED TO 850 DEGREES C. (1) PASSENGER SAW FLAMES O UT THE EXHAUST. THE ENG WAS SHUTDOWN AND A SINGLE ENGINE LANDING FOLLOWED. POST FLIGHT INSP FOUND FRACTURED COMPRESSOR T URBINE BLADES. THE ENG WILL BE INVESTIGATED AT IN PRESENCE OF A MFG REP AND UPDATES WILL BE PROVIDED. 4 T E4EA 20090102 EA 2009 1 2 CA081125018 2 20081116 G 7250 BLADES PWA PT6 PT6A6 52043 EA POWER TURBINE FAILED W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 CA (CAN) ACFT TYPE ID PC-9. WHILE APPLYING POWER DURING A TOUCH AND GO, THE ENGINE STARTED VIBRATING. THE PILOT REDUCED THE POWER TO IDLE AND ABORTED T/O. AS THE A/C SLOWED DOWN ON THE RUNWAY, OIL BEGAN TO SPRAY OVER THE CANOPY. ONCE CLEARED OF THE RUNWAY, THE PROPELLER SLOWED DOWN RAPIDLY AND THE ENG WAS IMMEDIATELY SHUTDOWN. POST FLIGHT INSP FOUND FRACTURED PT BLADES, THE EXHAUST DUCT HAS A HOLE THROUGH THE INNER "SKI JUMP", THE EXHAUST STACK HAS MULTIPLE HOLES AND DENTS AND THE ENGINE COWLING IS DENTED. MFG IS REQUESTED THE ENG BE FWD TO PLT 5 FOR INVESTIGATION. 3 T E4EA 20090102 NE 2009 1 2 CA081125019 2 20081119 G 7261 OIL SYSTEM LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE RT ENGINE LEAKING W B EMER. DESCENT K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA (CAN) APPROX 20 MILES SOUTH OF AIRPORT, THE PILOT REPORTED SMOKE IN CABIN. HE DECLARED AN EMERGENCY AND THEY WERE GIVEN PRIORITY TO LAND. MX PERFORMED GROUND RUNS AND FOUND THE RT ENG OIL LEAKING INTO THE BYPASS AIR AND REACHING CABIN BLEE D AIR DUCTS. THE ENG IS BEING REMOVED. 2 L 7 2 4F 4 F RT A10CE E35NE 20090102 NE 2009 1 2 CA081125020 2 20081121 G 7200 ENGINE AGUSTA A109 A109E 0260119 EU PWC PW206C PW206C NE NR 2 MAKING METAL W E A ENGINE SHUTDOWN UNSCHED LANDING R R PARTIAL RPM/PWR LOSS PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) PILOT REPORTED NR 2 ENG CHIP LIGHT ILLUMINATED AT TOP OF CLIMBOUT, IMMEDIATELY FOLLOWED BY A SURGE AND POWER LOSS. PILOT PREPARED FOR A RUN-ON LANDING. NR 2 ENG WAS SECURED, PASSENGERS WERE BRIEFED AND TRAFFIC AND DISPATCH WERE ALERTE D. NR 1 ENG WENT TO 124 PERCENT TORQUE AFTER NR 2 ENG POWER LOSS. SUCCESSFUL RUN-ON LANDING WAS ACCOMPLISHED AND ACFT W AS GROUND-TAXIED TO PARKING AREA. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 G 7 2 3U 3 U RT H7EU E42NE 20090102 NM 2009 1 2 CA081126001 1 20081120 G 2720 3985001007 CONTROL UNIT BOMBDR DHC8 DHC8402 1390042 NM PWC 150 PW150A EA RUDDER FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA 4779 (CAN) WHILE PERFORMING TASK 27-21-28-710-801 OPS TEST OF THE RUDDER SHUT-OFF VALVES, NR1 RUDDER SHUT-OFF VALVE FAILED TO CLOSE WHEN SELECTED OFF. THE FLIGHT CONTROL ELECTRONIC CONTROL UNIT (FCECU) WAS REPLACED. THE TASK WAS PERFORMED AND P ASSED THE TEST. THE FCECU WAS TESTED IAW AMM 27-00-01. 2 H 7 2 4T 4 T RT A13NM E00062EN 20090102 NM 2009 1 2 CA081126002 1 20081116 G 5230 DOOR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA CARGO NOT CLOSED W A UNSCHED LANDING W J INADEQUATE Q C WARNING INDICATION CL CLIMB 1 CA (CAN) AIR TURNBACK: AFTER T/O FUSELAGE DOOR WARNING LIGHT CAME ON. AFT CARGO DOOR INDICATION. ON INSP AFTER LANDING IT WAS NOTICED THE THE AFT CARGO DOOR HANDLE WAS POPPED OUT. THE DOOR WAS CLOSED BUT NOT LOCKED. AFT CARGO DOOR WAS FUNCTI ONED AND CLOSED AND LOCKED. SUSPECT THAT THE GROUND CREW DID NOT FULLY PUSH THE HANDLE INTO THE CORRECT POSITION. 2 H 7 2 4T 4 T RT A13NM E00062EN 20090102 NM 2009 1 2 CA081126003 1 20081124 G 5270 SENSOR BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA DOOR LOCK OUT OF RIG W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) AIR TURNBACK: FUSELAGE DOOR WARNING LIGHT IN FLIGHT. RIGGED EMERGENCY EXIT DOOR PROXIMITY SENSOR EDRCLLK IAW AMM 52-71-01. INDUCTANCE 8.600MH. 2 H 7 2 4T 4 T RT A13NM E00062EN 20090102 2009 1 2 CA081126005 4 20081104 G 3457 S67157520 ANTENNA CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C 03047 GL NR 2 GPS MALFUNCTIONED W O OTHER H ELECT. POWER LOSS-50 PC LD LANDING 1 CA (CAN) FLIGHT CREW REPORTED NR 2 FMS DRIFTED 8NM AT END OF THE LEG. NR 2 GPS ANTENNA REPLACED AND TESTED SERVICEABLE IAW 34-54-01. 2 L 7 2 4J 4 F RT T00007WI TE6CH 20090102 NM 2009 1 2 CA081126006 1 20081010 G 2910 82920010263 LINE DHAV DHC8 DHC8103 1386005 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE HYDRAULIC SYS CRACKED W O OTHER K FLUID LOSS CR CRUISE 1 CA 6726 (CAN) DURING CRUISE FLIGHT SEVERAL DROPS OF HYD FLUID WERE DISCOVERED COMING FROM THE RT OVERHEAD CEILING. SOME FLUID FE LL ON THE PASSENGERS IN THE AREA. NO INJURIES REPORTED. NO EMERGENCY ACTION/PROCEDURES CONDUCTED. AFTER AN UNEVENTFUL LANDING MX DETERMINED THE LEAK TO BE FROM A HYD TUBE FITTING. THE TUBE WAS REPAIRED AND THE ACFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090102 2009 1 2 CA081126007 4 20081021 G 3100 7014300901 DISPLAY CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C 03047 GL NR 4 FAILED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC CL CLIMB 1 CA (CAN) RE-OCCURRING DEFECT 2008/10/21 -FLIGHT CREW REPORTED NR 4 DISPLAY UNIT FLICKED ON START-UP. FAULT COULD NOT BE DUP LICATED AND WAS SWAPPED TO NR4 POSITION FOR TROUBLESHOOTING PURPOSES. 2008/10/22 -FLIGHT CREW REPORTED NR3 DISPLAY UNIT FAILED AT THE TOP OF DESCENT. NR 3 DISPLAY UNIT DEFERRED IAW MEL. 2008/10/24 -NR 3 DISPLAY UNIT REPLACED WITH REPAIRED UNIT FROM MFG AND CHECKED SERVICEABLE IAW AMM 34. 2008/10/30 -MX REPORTED NR 3 DISPLAY UNIT STARTING FLASHING INTERMIT TENT WHITE DIAMONDS AND BLACK SCREEN DURING EXTENDED OPERATION. NR 3 DISPLAY UNIT DEFERRED IAW MEL. RE-OCCURRING DEFECT FORM GENERATED. TEAR DOWN REPORT OF THIS UNIT IDENTIFIED THIS AS BEING THE REASON FOR REMOVAL FROM PREVIOUS AIRCRAFT. 2 L 7 2 4J 4 F RT T00007WI TE6CH 20090102 WP 2009 1 2 CA081126008 1 20081121 G 2435 14924HTH CASE ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE STARTER GEN CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 41 (CAN) STARTER CASING CRACKED. 1 G 7 1 3O 3 O H11NM 1E4 20090102 NE 2009 1 2 CA081127001 1 20081103 G 6320 S613520670043 HOUSING SKRSKY S61 S61N 8142104 NE M/R GEARBOX CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) CRACK FOUND ON THE FRONT/RT SIDE OF LWR HSG REPAIR TO LWR HSG CARRIED OUT IAW RDC NO: P-RH07-038 H1E-02. THIS AR EA OF THE HSG IS ALWAYS HIGHLY SCRUTANIZED DURING NDT. 2 G 7 2 4U 1H15 20090102 NE 2009 1 2 CA081127002 1 20081103 G 6230 BEARING SKRSKY S61 S61A 814210C NE MAST FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) S61MGB S/N: A14-J-10-79-1119 SUPPLIED, HAD A INDICATION ON THE MGB BEING CONTAMINATED WITH METAL. REMOVED THE MGB FROM THE ACFT, AND RETURNED IT TO HELI-ONE TSN: 15634:00 TSO: 772:29 HELI-ONE DISASSEMBLED THE MGB TO FIND THAT THE MAST DUPLEX BRG P/N:SB1357-103 ,S/N: J0359 WAS THE CAUSE OF THE CONTAMINATION. REPLACEMENT OF BRG REQUIRED. MAST DUPLEX BRG P/N:SB1357-103 ,S/N: J0359 COMPANY SQID NR08-07990. 2 G 7 2 4U H2EA 20090102 NE 2009 1 2 CA081127003 1 20081030 G 6230 GUIDE SKRSKY S76 S76A 8143006 NE SWASHPLATE MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MGB PN: 76351-09600-043 S/N:A231-00085 FOLLOWING INSP OF SWASHPLATE GUIDE PN:76351-09029-101,SN:A028-00343 FROM AB OVE MENTIONED MGB,THE MEASUREMENT TAKEN AT RADIUS (J ) (REF:SA4047-76-7-8,CHG.9) INDICATES BELOW MINIMUM REQ`D RADIUS OF .040 INCH. IAW O/H MANUAL REF, SWASHPLATE GUIDES ARE AMONG THE LIST OF ITEMS CLASSIFIED AS FLIGHT SAFETY PARTS. PART H AS BEEN TAGGED REJECTED AS THIS MINIMUM .040 INCH RADIUS IS CONSIDERED A CRITICAL CHARACTERISITIC. RETURN TO VENDOR FOR WARRANTY (THIS PART HAS A TIME LIFE OF 20,000 HRS AND HAS ONLY BEEN IN SERVICE FOR ONE MGB O/H OF 3242.7 HRS, SEE MGB LO G CARDS) MOST LIKELY MACHINED INCORRECTLY DURING MFG PROCESS. SQID NR 08-07896. 1 G 7 2 3U H1NE 20090102 NE 2009 1 2 CA081127004 1 20080911 G 6230 SB3354102 CONE SKRSKY S76 S76 8143010 NE M/R GEARBOX BRG DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) INSPECTION OF CAGE SHAKE ON TAPERED ROLLER BRGS PN: SB3354-102 WAS DIMENSIONALLY INSPECTED IAW (SA4047-76-7-8 CHAN GE 9, 31/MARCH/2006 IAW PARA. 2-52A) AND DETERMINED TO EXCEED AVERAGE MAXIMUM ALLOWABLE CAGE SHAKE LIMITS (.017 INCH) PR IOR TO INSTALLATION ON MGB PN: 76351-09600-044 SN:A231-00184. RETURN TO VENDOR FOR WARRANTY. UNSERVICEABLE BRG CONE RET URNED TO VENDOR AWAITING WARRANTY RMA NR. (COMPANY SQID NR 08-06654) 1 G 7 2 3U H1NE 20090102 NE 2009 1 2 CA081127005 3 20081112 G 6114 E6468 HUB BEECH 56 56TC 1152736 CE HARTZL HCE4A HCE4A3A NE PROPELLER WORN W O OTHER O OTHER NR NOT REPORTED 1 CA 2209 (CAN) PROPELLER CAME IN FOR SHIFTED PRELOAD PLATES. HUB DID NOT SEEM TO SEAL (MATE) PROPERLY. THERE WERE HEAVY WEAR MARK S ON THE CENTER SECTION OF THE MATING SURFACES ONLY. TEFLON WAS WORN THROUGH ON ALL (4) BLADES. ONE OTBD BRG RACE WAS BA DLY CHIPPED AND SHOWED SIGNS OF CRACKING. 1 L 7 2 3O 3A16 5 C P10NE 20090102 NE 2009 1 2 CA081127007 1 20080708 G 6320 7635109626 SHAFT SKRSKY S76 S76 8143010 NE M/R GEARBOX CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MGB PN:76351-09600-044 SN:A231-00044 IN FOR OVERHAUL. FOLLOWING CLEANING AND INSP OF NEW SPLINE SHAFT, CORROSION W AS FOUND AT INNER AND OUTER SPLINES. ALL REMAINING SPLINES SHAFTS (QTY:6) PULLED FROM STOCK AND INSPECTED, NO EVIDENCE OF CORROSION FOUND. CORROSION PITTING FOUND ON NEW SPLINE SHAFT PULLED FROM STOCK. RETURN TO VENDOR FOR FULL WARRANTY COMPANY SQID NR 08-05027. 1 G 7 2 3U H1NE 20090102 NE 2009 1 2 CA081127008 1 20080620 G 6320 7635109058102 PINION GEAR SKRSKY S76 S76 8143010 NE M/R GEARBOX CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION PITTING FOUND ON BORE ID OF (2) HELICAL PINIONS HSI (P.A.P) MGB PN:76351-09500-044 SN:A081-00196 REC`D FOR O/H. PRIOR TO ASSY INSP OF NEW CUSTOMER SUPPLIED HELICAL PINIONS (X2), REVEALED CORROSION PITTING IN BORE ID OF BOTH PINIONS AT AREA OF FWD ROLLER PATHWAY. COMPANY SQID NR08-04520. 1 G 7 2 3U H1NE 20090102 NE 2009 1 2 CA081127009 1 20080611 G 6320 7635109028105 SHAFT SKRSKY S76 S76 8143010 NE M/R GEARBOX CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION FOUND ON NEW QUILL SHAFT MAIN GEARBOX O/H PN:76351-09500-044, SN:A081-00110 FOLLOWING CLEANING AND INSPE CTION OF NEW QUILL SHAFT (P/N,S/N LISTED BELOW), MULTIPLE CORROSION PITTING CLUSTERS FOUND ON INTERNAL SPLINES AND ID OF PART. 1 G 7 2 3U H1NE 20090102 2009 1 2 CA081127010 1 20080611 G 6320 7635109028105 SHAFT M/R GEARBOX CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) EXCESSIVE CORROSION FOUND ON NEW QUILL SHAFT. MAIN GEARBOX O/H PN:76351-09500-044, SN:A081-00058 DURING CLEAN-UP A ND INSP OF NEW QUILL SHAFT (PN, SN MENTIONED BELOW) MULTIPLE CORROSION PITTING CLUSTERS FOUND ON INTERNAL SPLINES AND ID OF PART. RETURN TO VENDOR FOR FULL WARRANTY UNSERVICEABLE QUILL SHAFT RETURN TO VENDOR AWAITING WARRANTY RMA NR COMPA NY SQID NR 08-04306. 20090102 NE 2009 1 2 CA081127011 1 20080606 G 6320 SB3202A2 BEARING SKRSKY S76 S76A 8143006 NE M/R GEARBOX FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PERFORMED CAGE SHAKE ON NEW BRGS IAW MFG ACFT ENGINEERING INSTRUCTION EI NR E76-702-35-1601. RESULTS FAILED INSP R ETURN TO VENDOR FOR WARRANTY. UNSERVICEABLE BRG RETURN TO VENDOR AWAITING WARRANTY RMA NR COMPANY SQID NR 08-04194. 1 G 7 2 3U H1NE 20090102 NE 2009 1 2 CA081127012 1 20080417 G 6320 7635109008056 HOUSING SKRSKY S76 S76A 8143006 NE M/R GEARBOX CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) GEARBOX REMOVED FOR EXCESSIVE CORROSION AROUND OIL FILTER HSG FITTING. MAIN GEARBOX RECEIVED AT HELI-ONE FOR REPAI R AT TT:10961:18 HRS. TSO:2969:48 HRS. FLUID ADAPTER (FITTING) REMOVED FROM LWR HSG OIL FILTER AREA AND CORROSION WAS CL EANED/REMOVED TO ALLOW FOR INSPECTION. EXTENSIVE CORROSION WAS FOUND AT FLUID ADAPTER PORT AND LOCK RING AREA BEYOND MA XIMUM REPAIRABLE LIMITS IAW REF:SA4047- 76-7-8,CHG.9-31MAR2006. REPLACE UNSERVICEABLE LOWER HOUSING P/N:76351-09008-056 S/N:C065-00098 (T.T: UNK) WITH NEW/OVERHAULED EQUIPPED WITH NEW VERSION FLUID ADAPTER P/N:RFSK9812-13. MOST LIKELY INSU FFICIENT SURFACE PROTECTION AT DAMAGED AREA. 1 G 7 2 3U H1NE 20090102 NE 2009 1 2 CA081127013 1 20080320 G 6320 SB2151107 BEARING SKRSKY S76 S76A 8143006 NE UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) GEARBOX MAKING METAL TSN:2969:43 HRS. GEARBOX RECIEVED FOR PREMATURE OVERHAUL DUE TO METAL CONTAMINATION. DURING INSP PROCESS , RT SPUR PINION ALIGNMENT ROLLER BRG SB2151-107 S/N:2659 (LOCATED AT UPPER HSG COUNTERBORE) WAS FOUND TO B E BREAKING UP AT OUTER RACE ROLLER PATHWAY. FOLLOWING COMPLETION OF GB INSP THIS BRG WAS CONSIDERED AS THE SOURCE FOR TH E METAL CONTAMINATION. REPLACE BRG DURING OVERHAUL. 1 G 7 2 3U H1NE 20090102 NE 2009 1 2 CA081128001 2 20081125 G 7250 PW120A TURBINE DHAV DHC8 DHC8101 2809002 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NR 2 ENGINE FAILED W L ABORTED APPROACH O OTHER AP APPROACH 1 CA 27846 17199 (CAN) PRIOR TO TAKEOFF, THE CREW FELT A THUD AND GRINDING NOISE FROM THE NR 2 ENGINE AT 70 PERCENT TORQUE. THE ENGINE WA S IMMEDIATELY SHUTDOWN, BUT BY THE TIME THE TORQUE REDUCED TO ZERO PSI AND THE ITT OF THE ENG REACHED UP TO 1200 DEGREE CELSIUS. ENG WAS IMMEDIATELY SHUTDOWN AND TAKEOFF WAS ABANDONED. ON RETURN AT THE RAMP, BROKEN PIECES OF BLADES OF PWR T URBINE WERE FOUND IN THE TAIL EXHAUST PIPE. ALL PARAMETERS OF BOTH ENGINES WERE WITHIN LIMIT. AS SOON AS THE TAKEOFF ROL L INITIATED AND PWR WAS ADVANCED THROUGH 70 PERCENT TORQUE, A THUD AND GRINDING NOISE WAS HEARD FROM RT SIDE (NR 2 ENG) AND ACFT STARTED SWINGING TO THE RT. IMMEDIATELY, THE TAKEOFF WAS REJECTED AND WHILE LOWERING THE POWER LEVERS THE TORQU 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090102 NE 2009 1 2 CA081128002 1 20081103 G 6320 S613723053102 BEVEL GEAR SKRSKY S61 S61A 814210C NE M/R GEARBOX UNSERVICEABLE W O OTHER O OTHER IN INSP/MAINT 1 CA 770 (CAN) BROKEN GEAR TOOTH FOUND IN FILTER REPAIR-BROKEN GEAR TOOTH FOUND IN FILTER OF S61 MGB SN: A14-215. MGB WAS REMOVED FROM ACFT HS-HTA AND REURNED TO HELI-ONE TO BE REPAIRED TSN: 31804:41 TSO: 769:56 DISASSY DONE AT HELI-ONE TO FIND THAT THE INPUT BEVEL GEAR PN: S6137-23053-102 SN: E128-00271WAS THE DAMAGED PART. INPUT BEVEL GEAR PN: S6137-23053-102 SN: E 128-00271. COMPANY SQID NR 08-08045. 2 G 7 2 4U H2EA 20090102 NE 2009 1 2 CA081128003 1 20081127 G 6320 GEARBOX SKRSKY S76 S76 8143010 NE MAIN ROTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MGB CHIP LIGHT INDICATION MGB PN:76351-09600-044,SN:A231-00107 REC`D AT HELI-ONE FOR REPAIR. TSN:8638:39 TSO:2516: 54 FOLLOWING DISASSEMBLY AND INSPECTION OF MGB, RT OUTPUT ALIGNMENT BRG WAS IDENTIFIED AS THE CAUSE FOR METAL GENERATION WITH HEAVY SPALLING EVIDENT AT ROLLER PATHWAY OF OUTER RACE. FLUSH MGB AND REPLACE DISCREPANT BEARING. COMPANY SQID N R 08-8606. 1 G 7 2 3U H1NE 20090102 NE 2009 1 2 CA081128004 1 20081127 G 6320 SB2151107 BEARING SKRSKY S76 S76 8143010 NE M/R GEARBOX DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 2037 (CAN) MGB CHIP LIGHT INDICATIONS MGB P/N:76351-09600-044 S/N:A231-00299 REC`D AT HELI-ONE FOR REPAIR. TSN:2037:48 HRS. F OLLOWING DISASSY AND INSP OF MGB THE RT OUTPUT ALIGNMENT BRG WAS FOUND TO BE THE CAUSE FOR THE METAL GENERATION WITH HEA VY SPALLING AT ROLLER PATHWAY OF BRG OUTER RACE. ADDITIONAL BRS INDICATE INITIAL STAGES OF SPALLING. REPLACE WITH SERVI CEABLE BRS. COMPANY SQID NR 08-08605. 1 G 7 2 3U H1NE 20090102 2009 1 2 CA081128005 4 20081127 G 3120 285T08551 FDAS CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE COCKPIT ODOR W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) ON CRUISE THE F/A REPORTED A STRONG ODOR IN THE CABIN, PILOT CONFIRMED THE STRONG SMELL AND DIVERTED FLIGHT TO BAS E AND DECLARE AN EMERGENCY LANDING. AFTER MX INVESTIGATION, FOUND THE FDAS "FLIGHT DECK ACCESS SYS" AT FAULT. ELECTRICA L ODOR COMING FROM THIS COMPONENT. 2 L 7 2 4F 4 F RT A21EA E15NE 20090102 EA 2009 1 2 CA081128006 2 20081126 G 8530 VALVE SEAT PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE WORN W O OTHER O OTHER NR NOT REPORTED 1 CA 1452 (CAN) INTAKE VALVE STAYING OPEN, INTAKE VALVE AND SEAT WORN. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 20090102 EA 2009 1 2 CA081129001 1 20081125 G 5610 NP1393229 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 9278 (CAN) IN FLIGHT LT SIDE WINDOW SHATTERED. FLIGHT DIVERTED MX REPLACED SIDE WINDOW. 2 L 7 2 4F 4 F RT A21EA E15NE 20090102 EA 2009 1 2 CA081129003 1 20081122 G 3260 WARNING LIGHT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE MLG ILLUMINATED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, LANDING GEAR DID NOT RETRACT WHEN SELECTED UP. LANDING GEAR LIGHT REMAINED GREEN. FLT CREW ALSO REP ORTED INBD ANTI-SKID (C) AND PARK BRAKE SOV (C) MSG. ALL MSGS CLEARED WHEN GEAR SELECTED DOWN. ACFT RETURNED TO DEPARTUR E AIRPORT AND LANDED WITHOUT FURTHER INCIDENT. 2 L 7 2 4F 4 F RT A21EA E15NE 20090102 EA 2009 1 2 CA081129005 1 20081116 G 2150 GG670950093 ACM CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C5B1 30052 NE LEFT SEIZED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 5579 (CAN) AFTER LANDING AND TAXI TO GATE, FLT CREW REPORTED SMOKE STARTED COMING FROM VENTS IN COCKPIT. CREW ELECTED TO STOP SHORT OF THE GATE AND EVACUATE THE ACFT. ACFT WAS EVACUATED WITHOUT INCIDENT. MX INSPECTED ACFT AND FOUND THAT THE LT ACM HAD SEIZED. NO OTHER DEFECTS WERE NOTED. LT PACK WAS DEFERRED IAW THE MEL AND ACFT RETURNED TO SERVICE. 17 NOV 08: MX REMOVED AND REPLACED THE LT ACM AND OPS CHECKED. NO FURTHER DEFECTS NOTED. LT PACK REMOVED FROM DEFERRAL AND ACFT RET URNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E00063EN 20090102 NM 2009 1 2 CA081201001 1 20081128 G 2510 412310416 SEAT BACK EMB ERJ190 ERJ190100IGW 3260408 NM GE CF34 CF3410E5A1 30022 NE COCKPIT LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE ATTACH SCREWS HOLDING SEAT BACK BRACKET TO SEAT ARM ARE LOOSE, THE BRACKET ATTACHES THE SEAT BACK TO THE ARM. THE SCREWS ARE 0.5 INCHES IN LENGTH, THE SWIVEL BRACKET ATTACH POINT WAS ALSO LOOSE. REF: 4/MM 41402003, IPL 25-22-90 PA GE 10044 FIGURE 7 ITEMS 5 & 10. CHAIR PN ARE414140003-105, 41414003-111,41414003-113,41404003-103 & 41404003-105. 2 L 7 2 4F 4 F RT A57NM E00070EN 20090102 CE 2009 1 2 CA081201002 1 20081201 G 3340 0713035 SWITCH CESSNA 172 172K 2072430 CE LYC O320 O320E2D 41508 EA LANDING LIGHT OVERHEATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LANDING LIGHT SWITCH MAY BE ORIGINAL (8865 HRS) DETENTS BECAME "STICKY" AND NOT AS POSITIVE AS NORMAL. SWITCH FUNC TION DID NOT FAIL. INSP REVEALED PWR SUPPLY WIRE END AND LUG ON SWITCH OVERHEATED. DISASSY SHOWED LUG CONTACT RIVET DET ERIORATED AS WELL AS MYCARTA TYPE BOARD MATERIAL DISINTEGRATING DUE TO HEAT DAMAGE AROUND THE RIVET. MFG REQUIRES NEWER STYLE (1970 AND NEWER) LANDING LIGHT SWITCHES TO BE REPLACED EVERY 5 YEARS THIS OLDER STYLE SWITCH THOUGH LIKELY ABLE T O CARRY MORE CURRENT SHOULD BE INSPECTED VISUALLY ANNUALLY TO DETERMINE IF OVERHEATING IS AN ISSUE. 1 H 7 1 3O 3 O NT 3A12 E274 20090203 CE 2009 2 3 CA081201003 1 20081009 G 3597 P108 CONNECTOR LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE731* 01518 WP O2 SYSTEM MISINSTALLED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) PASSENGER O2 MASK WOULD NOT DEPLOY WHEN TESTED. SYSTEM TROUBLESHOT AND FOUND CONNECTOR P108 WAS NOT INSTALLED COR RECTLY. CONNECTOR REMOVED, INSPECTED AND REINSTALLED .O2 MASK FUNCTION CHECKED SERVICEABLE IAW AMM 35. 2 L 7 2 4F 4 F RT T00008WI E6WE 20090102 2009 1 2 CA081201004 1 20081201 G 8011 BOLT STARTER MISSING W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 498 498 (CAN) STARTER CASE THROUGH BOLTS. BOLTS HAVE LOOSENED OFF TO THE POINT OF CAUSING ELECTRICAL SHORTING WITHIN THE STARTER DUE TO THE HALVES BEING LOOSE FROM EACH OTHER. ONE BOLT COMPLETELY MISSING. SPARKS AND ARCING VISUALLY OBSERVED AT BEND IX HSG DURING STARTER OPERATION. 20090102 WP 2009 1 2 CA081201005 2 20081130 G 7200 31037505 GASKET GARRTT TPE331 TPE33110UA 01514 WP ENGINE LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 24 (CAN) THIS ENG WAS NOTED TO HAVE A OIL LEAK COMING FROM THE BOTTOM OF THE DIAPHRAGM AT THE 2 BOTTOM BOLT HOLES CLOSEST T O THE CHIP DETECTOR. THE GASKET WAS NOTED TO BE STICKING OUT AND NOT SEALING PROPER. UPON FURTHER INVESTIGATION THE OLD STYLE GASKETS PN 3103750-1/-3/-4 WERE CHANGED UP TO A 3103750-5 TO PREVENT THIS ISSUE. REF: SB TPE331-72-2084 FOR THE UP GRADED GASKETS. THE 3103750-5 GASKET WAS INSTALLED ONLY 23.5 HRS PRIOR TO THIS OIL LEAK AT A REPAIR. THE CASE BOLTS WERE CHECKED AND WERE AT THERE PROPER TORQUE. 4 T E4WE 20090102 CE 2009 1 2 CA081201006 1 20081201 G 5310 NAS1473A3K DOME NUT CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C 03047 GL WINDSHIELD POST CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE REPLACEMENT OF THE RT WINDSHIELD, DUE TO A BROKEN OUTER PANE, HEAVY CORROSION WAS NOTED COMING OUT OF T HE DOME NUTS. THE WINDSHIELD IS INSTALLED FROM THE OUTSIDE AND THE SCREWS ARE HELD IN PLACE BY THESE DOME NUTS THAT RIVE TED IN PLACE AROUND THE PERIMETER OF THE FRAME. EACH DOME NUT WAS BOROSCOPED AND FOUND THAT A MAJORITY WERE SPLIT OR CRU MBLED DUE TO CORROSION. ALL DOME NUTS WERE REPLACED AND THE WINDSHIELD RE-INSTALLED. 2 L 7 2 4J 4 F RT T00007WI TE6CH 20090102 CE 2009 1 2 CA081201007 1 20081128 G 2720 04115264 RUDDER BAR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA RT RUDDER CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 10660 (CAN) SCREWS ATTACHING CENTER CONTROL CONSOLE COVER PN 0413463-5 WERE TOO LONG AND CHAFING IN TO THE RT SIDE OF THE RUDD ER PEDAL TORQUE TUBE. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P9045 20090102 NM 2009 1 2 CA081201008 1 20080919 G 6320 B7936S CHIP DETECTOR DOUG 600N 600N 3027377 NM ALLSN 250C 250C47M 03013 GL TRANSMISSION CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 800 (CAN) BOTH TEDESCO B7936S CHIP DETECTOR BASES FOUND CRACKED AT BASE OF O-RING FLANGE. CAUSED BY OVERTORQUE DURING AN EAR LIER INSTALLATION. CRACKS NOT VISIBLE UNTIL CHIP DETECTORS WERE REMOVED TO DRAIN TRANSMISSION OIL. 1 G 7 1 3U 3 U NC H3WE E1GL 20090102 NM 2009 1 2 CA081201009 1 20081128 G 5302 500N34247 ANGLE DOUG 600N 600N 3027377 NM ALLSN 250C 250C47M 03013 GL TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 800 (CAN) FUSELAGE ANGLE FOUND CRACKED DURING A TAILBOOM INSPECTION. PART IS NOT READILY VISIBLE OR A PLACE OF INTEREST DURI NG INSPECTIONS AND MAY HAVE GONE SOME TIME AS CRACKED. PART IS TO BE REPLACED BEFORE FURTHER FLIGHT. 1 G 7 1 3U 3 U NC H3WE E1GL 20090203 SW 2009 2 3 CA081201010 1 20080901 G 2910 HOSE BELL 206 206B 1181511 SW HYD SYSTEM CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) UPON ENGINE SHUTDOWN WALK-AROUND, PILOT REPORTED A TRANSMISSION OIL LEAK ON MACHINE. LEAK INSPECTED AND FOUND TO BE FROM THE MAIN HYDRAULIC PUMP HOSE. HOSE HAD CHAFED THROUGH ON A MS21919WDG CLAMP HOLDING IT DOWN TO THE TOP DECK OF A/C. WDG CLAMP SERIES IS NOT DESIGNED FOR USE AROUND OILS AND THIS IS BELIEVED TO HAVE CAUSE THE RUBBER CUSHION ON THE CLAMP TO DETERIORATE AGAINST THE STAINLESS STEEL BRAIDED HOSE AND CAUSE A METAL ON METAL CONTACT THAT WENT UNDISCOVERED UNTIL HOSE FAILURE. WDG CLAMP AND HOSE ASSY WERE SUBSEQUENTLY REPLACED. 1 G 7 1 3U H2SW 20090204 SW 2009 2 4 CA081201011 1 20081001 G 6320 206031554003 SPINDLE BELL BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TRANSMISSION WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TRANSMISSION MOUNTS REMOVED DUE TO BEARING WEAR. UPON FURTHER INSP, SPINDLE ALSO FOUND DAMAGED IN LOCATION OF WAS HER P/N 206-030-507-001. HARD WASHER MOVEMENT DUE TO BEARING WEAR HAD WORN INTO THE RADII OF THE SPINDLE MOUNTING AREA. SPINDLE SCRAPED. SPINDLE HARDNESS NOT TESTED. 1 G 7 1 3U 3 U H2SW E4CE 20090102 NM 2009 1 2 CA081201012 1 20081129 G 3251 651781412 ACTUATOR BOEING 727 727225 1384077 NM PWA JT8 JT8D9A 52048 NE STEERING UNIT WORN W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) A "CLUNK" IN THE NOSE WHEEL STEERING TILLER WAS REPORTED. BOTH STEERING ACTUATOR ROD ENDS WERE FOUND PULLING OUT O F THE PISTONS. BOTH STEERING ACTUATORS WERE REPLACED. A/C RETURNED TO SERVICE. 2 L 7 3 4F 4 F A3WE E2EA 20090102 2009 1 2 CA081202001 1 20081201 G 3244 301003530 TIRE MLG BULGED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) A BULGE WAS NOTICED ON THE TIRE DURING A PRE-FLIGHT INSP. SUBSEQUENT INSP UPON REMOVAL REVEALED A RIP IN THE INNER TIRE CARCASS. 20090102 NM 2009 1 2 CA081202002 1 20081129 G 3250 C247360011 STEERING SYS AIRBUS A319 A319114 3930350 NM CFMINT CFM56 CFM565A1 NE NLG MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 33128 (CAN) NW STEERING SWING TO THE LT DURING TO ROLL AT APPROX 100 KTS. NEEDED FULL RUDDER AND RT BRAKE TO MAINTAIN CENTERLI NE. STEERING CONTROL UNIT 6GC REPLACED IAW MM S/N H0714. 2 L 7 2 4F 4 F RT A28NM E29NE 20090102 NE 2009 1 2 CA081202003 2 20081106 G 7250 311074102 RETAINING RING PWA PT6 PT6A114A 52043 NE TURBINE SECTION DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 2760 2760 (CAN) ENGINE WAS RECEIVED FOR INVESTIGATION/REPAIR DUE TO SHIFTING OF CT SHROUD SEGMENTS. THE CT SHROUD SEGMENT-RETAININ G RING WAS OF POST SB 1627 CONFIGURATION AND THE CT SHROUD SEGMENTS (P/N 3035673CL12) POST SB 1628. DURING INVESTIGATION , HEAVY RUB SPOTS WERE NOTED ON QTY. 1-CT SHROUD SEGMENT AND ALL THE CT BLADES. THE CT SHROUD SEGMENTS RETAINING RING WA S FOUND DISENGAGED FROM THE RETAINING CAVITY OF CT SHROUD HSG, CAUSING LOOSENING AND DROOPING OF CT SHROUD SEGMENT. THIS RESULTED IN HEAVY RUB BETWEEN THE CT BLADES AND SHROUD SEGMENT. THE CT TIP CLEARANCES WERE INCREASED TO APPROX 0.048 IN CH, WHICH ADVERSELY AFFECTED ENGINE PERFORMANCE. NO CURLING/BOWING OF CT SHROUD SEGMENTS WAS OBSERVED. NO OVER HEATING/B 3 T E4EA 20090204 EU 2009 2 4 CA081202004 1 20081113 G 6710 350A27035106 CONTROL TUBE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D1 60053 NE COLLECTIVE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 14378 (CAN) EVERY 12 YEARS THE HELICOPTER GOES INTO THE SHOP FOR A MAJOR INSPECTION AS PART OF THE INSP, IS A HARDNESS TEST ON THE COLLECTIVE CONTROL TUBE. THE TUBE IS TESTED AND IT FAILED THE HARDNESS TEST. THE HARDNESS TEST REQUIRED IS 230 HV -5 KG LOAD. THE AVERAGE LOAD FOR THIS COLLECTIVE TUBE WAS 168.1 HV, (FAILED THE HARDNESS TEST). 1 G 7 1 3U 3 U H9EU E19EU 20090102 CE 2009 1 2 CA081203001 1 20081120 G 2840 100380006119 PROBE BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL RT AUX TANK SEPARATED W K NONE N FALSE WARNING IN INSP/MAINT 1 CA (CAN) DURING A 3RD PHASE 600 HR INSP, A SNAG WAS CREATED TO FIX A DISCREPANCY IN THE RT FUEL QUANTITY INDICATING SYS. TH E RT FUEL TANK READING WAS 300 LBS LOW. MAINT INSPECTED SYS AND ISOLATED THE PROBLEM TO THE RT AUX FUEL TANK PROBE. UPO N A CLOSER INSP IT WAS DISCOVERED THAT THE PROBE HSG AT SEPARATED FROM THE SENDING UNIT. THE PLASTIC RIVETS HAD SHEARED. THE PARTS WERE RECOVERED FROM THE AUX TANK AND WERE ALL ACCOUNTED FOR. A NEW SERVICEABLE UNIT WAS INSTALLED AND THE SYS WAS TESTED SERVICEABLE. 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 20090106 NE 2009 1 6 CA081203002 2 20081125 G 7200 ENGINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE RIGHT MALFUNCTIONED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA (CAN) ON TAKEOFF ROLL WITH PASSENGERS ON BOARD POWER WAS ADVANCED THROUGH 70 PERCENT TORQUE. A THUD AND GRINDING NOISE W AS HEARD FROM THE RT SIDE. TAKEOFF WAS ABORTED AND AC RETURNED TO THE GATE. ENG TO BE REMOVED AND SENT FOR INVESTIGATIO N. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A13NM E20NE 20090106 EA 2009 1 6 CA081203003 2 20081125 G 7200 ENGINE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA MALFUNCTIONED W B A EMER. DESCENT UNSCHED LANDING K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) SHORTLY AFTER TAKE OFF OIL MIST IN CABIN WAS DETECTED. THE ACFT IMMEDIATELY TURNED BACK, DECLARED AN EMERGENCY, AN D LANDED. THE LOCAL AIRWORTHINESS AUTHORITIES ARE INVESTIGATING THE EVENT. POST FLIGHT INSP REVEALED OIL IN THE VICINITY OF THE P2.2 BLEED VALVE. INSP AND BORESCOPE SHOWS LP COMPRESSOR AND BLEED VALVES WET. NO EVIDENCE OF DISTRESSED COMPONE NTS. EMU DATA REQUESTED. ENGINE BEING REMOVED FOR INVESTIGATION AT MFG. UPDATES WILL BE PROVIDED. 2 H 7 2 4T 4 T RT A13NM E00062EN 20090106 2009 1 6 CA081203004 1 20081118 G 6420 S611033406101 SPINDLE S61TRH TAIL ROTOR UNSERVICEABLE W O OTHER O OTHER NR NOT REPORTED 1 CA 3464 1747 (CAN) S61 TAIL ROTOR SPINDLE FAILED NITAL ETCH INSP IAW SB61B10-18J S/N`S K071-00144, K071-00132, K071-00137. 20090107 EA 2009 1 7 CA081203005 2 20080502 G 7250 TURBINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA RT ENGINE DAMAGED W O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA (CAN) ACFT CRASHED UNDER UNKNOWN CIRCUMSTANCES. DURING THE FLT, THE PILOT RADIOED THAT HE HAD A LOSS OF PWR FROM ONE ENG FOLLOWED BY A "MAYDAY" CALL, APPROX 14 MIN LATER, DURING WHICH HE SAID THE SECOND ENGINE STOPPED OPERATING. THE ACFT WA S EQUIPPED WITH A FDR AND CVR. EXAMINATION OF ENGINES, REVEALED THE LT ENGINE DISPLAYED ROTATIONAL SIGNATURES CHARACTERI STIC OF THE ENGINE DEVELOPING POWER AT IMPACT. NO PRE-IMPACT ANOMALIES EVIDENT. THE RT ENGINE DISPLAYED EVIDENCE OF PRE- IMPACT DISTRESS CONSISTING OF THE FRACTURE AND RELEASE OF COMPRESSOR TURBINE (CT) BLADE MATERIAL DUE TO CONTACT WITH A P ROTRUDING CT BLADE SHROUD SEGMENT. THE CT DISK, VANE AND SHROUD ASSY WAS REQUESTED TO BE RETURNED TO MFG FOR DETAILED EX 2 L 7 2 4T 4 T RT A24CE E4EA 20090106 2009 1 6 CA081203006 1 20081202 G 6420 S611033406 SPINDLE TAIL ROTOR UNSERVICEABLE W O OTHER O OTHER NR NOT REPORTED 1 CA 1748 1747 (CAN) S61 TAIL ROTOR SPINDLE FAILED INITIAL ETCH INSP IAW SB61B10-18J S/N`S K071-00394, K071-00392. 20090102 NE 2009 1 2 CA081203007 2 20081126 G 7200 ENGINE EMB 120 EMB120 3260201 SO PWA 118 PW118 NE MAKING METAL W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB AT FL60, THE CREW NOTICED A LOW ENGINE OIL PRESSURE LIGHT, FOLLOWED BY A POPPING NOISE. THE ENG WAS S HUTDOWN AND THE ACFT WAS DIVERTED BACK TO BASE. GROUND INSP FOUND THE TURBOMACHINE CHIP DETECTOR COVERED WITH METAL SHAV INGS AND THE LP AND HP ROTORS INCAPABLE OF ROTATION. THE ENG HAD RECENTLY UNDERGONE A HOT SECTION INSP. MFG WILL CONTINU E INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 L 7 2 4T 4 T RT A31SO E20NE 20090102 NE 2009 1 2 CA081203008 2 20081128 G 7323 GASKET FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE OVRSPD GOVERNOR TORN W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AT TOP OF CLIMB, OIL PRESSURE FLUCTUATION WAS REPORTED FOLLOWED BY LOW OIL PRESSURE INDICATION. THE ENGINE WAS SHU TDOWN BY THE PILOT. ON RETURN TO GATE, THE ENG COWL WAS FOUND COVERED WITH OIL. OVERSPEED GOVERNOR GASKET FOUND DETERIOR ATED. GASKET WAS REPLACED. 2 H 7 2 4T 4 T RT A817 E20NE 20090102 NE 2009 1 2 CA081203009 2 20081125 G 7321 7898422009L6 EEC DHAV DHC8 DHC8* NM PWA 120 PW120A NE ENGINE MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) PILOT REPORTED SHUTTING ENGINE DOWN IN FLIGHT DUE TO EXCESSIVE TORQUE FLUCTUATIONS. EEC WAS REPLACED AND DEFECT RE CTIFIED. THE SUSPECT EEC HAS BEEN SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT C AUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A13NM E20NE 20090102 NE 2009 1 2 CA081203010 2 20081027 G 7297 WIRE HARNESS AEROSP ATR42 ATR42* 8680900 EU PWA PW120 PW127 NE ENGINE DAMAGED W E ENGINE SHUTDOWN R F PARTIAL RPM/PWR LOSS FLT CONT AFFECTED CR CRUISE 1 CA (CAN) THE ENG EXPERIENCED REPEATED EVENTS OF TORQUE FLUCTUATIONS BETWEEN THE 20TH AND 24TH OF OCTOBER FOR WHICH TROUBLES HOOTING HAD BEEN DONE. ON OCT. 27, THE PROBLEM RE-APPEARED AND WAS ACCOMPANIED BY NO RESPONSE TO THROTTLE MOVEMENTS. THE ENGINE WAS SHUTDOWN AND RE-STARTED IN MANUAL MODE WITH NO FURTHER PROBLEMS TILL THE FLIGHT ENDED. FURTHER TROUBLESHOOTI NG LED TO THE REPLACEMENT OF THE FUEL CONTROL AND ENGINE WIRING HARNESS, WHICH HAVE BEEN SENT FOR INVESTIGATION. MFG WIL L CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A53EU E20NE 20090102 NM 2009 1 2 CA081203011 1 20081202 G 2710 85711569001 BRACKET DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE AILERON CONTROL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 42293 (CAN) LT AILERON INPUT BRACKET FOUND CRACKED. LT AILERON QUADRANT BRACKET REMOVED P/N 85711569-001. POST S/B 8-57-27 Q UADRANT BRACKET TO BE INSTALLED. NEW BRACKET IS IN SHEET METAL SHOP. REMOVED AND REPLACED NEW LT AILERON QUADRANT BRAC KET IAW SB 8-57-27. LT WING AILERON TERMINAL QUADRANT, PREVIOUSLY REMOVED FOR SHEET METAL ACCESS, INSTALLATION COMPLETE D AS IAW AMM 27-12-31 TOTHE END OF STEP 12. INDEPENDENT INSP CARRIED OUT ON DEFECT 814228. M7109 FUNCTION TEST 1.C. COM PLETED FOR THOSE PORTIONS OF THE SYS THAT HAVE BEEN DISTURBED AND FOUND TO WORK NORMALLY M7128. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090102 WP 2009 1 2 CA081203012 1 20081126 G 6120 6506196 VALVE CVAC 580 580 2422806 WP PROP PITCH LOCK FAILED W E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION AP APPROACH 1 CA (CAN) IN FLIGHT, CREW EXPERIENCED A FAILURE OF THE NR 2 ENG PITCH LOCK VALVE. ENGINE WAS E-HANDLED AND AC LANDED WITHOUT INCIDENT. MAINT REPLACED THE NR 2 PITCH LOCK VALVE AND ACFT RETURNED TO SERVICE. 2 L 7 2 4T RT 20090102 EA 2009 1 2 CA081204001 1 20081202 G 2820 CN6273003001 PIPE CNDAIR CL600 CL600* 1900302 EA GE CF34 CF348C5 30050 NE FUEL FLOW CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 9796 9796 (CAN) MX FOUND NR1 ENGINE MOTIVE FLOW PIPE CHAFED LEAKING FUEL. PIPE WAS REPLACED, ENGINE RUNS AND LEAK CHECKS COMPLETED SATISFACTORY. CAUSE OF CHAFING COULD NOT BE CONFIRMED. IT WAS REPORTED THAT THE NEAREST DRAIN LINE WAS AT LEAST .5 INCH AWAY AND ALL SEEMED PROPERLY SECURED. 2 L 7 2 4F 4 F RT A21EA E00063EN 20090102 NM 2009 1 2 CA081204002 1 20081108 G 2497 WIRE DHAV DHC8 DHC8201 2809001 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ALTERNATOR DAMAGED W D RETURN TO BLOCK H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA (CAN) NR1 AND NR2 AC GEN ANNUNCIATIONS ILLUMINATED DURING TAXI. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE FOLLOWI NG DISCREPANCY HAD OCCURED. FOUND WIRE 2421-10002FILB-1 AND WIRE 2421-2000IGI2A-1 WORN THROUGH AND SHORTED AT STA YH59: 00 ON LT WING REAR SPAR. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090102 EU 2009 1 2 CA081204003 1 20081204 G 2710 04820203 SENSOR AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE LT AILERON UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FDR CORRELATION CHECK REVEALED LT AILERON ROLL SENSOR UNSERVICEABLE. SENSOR INSPECTED. OPERATING CABLE FRAYED AN D BINDING. SENSOR REPLACED. 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 20090102 NE 2009 1 2 CA081204005 3 20081204 G 6111 SFA13MIROASK112 BLADE AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6717 (CAN) LEADING EDGE NICKEL SHEATH VISUALLY INSPECTED AND A CRACK NOTED. IF PRESSURE APPLIED TO BLADED CRACK BECAME MORE N OTICEABLE. BLADE REMOVED FROM SERVICE. 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 20090102 NM 2009 1 2 CA081204006 1 20081203 G 3397 WIRE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF* NE CABIN LIGHT SHORTED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 42386 (CAN) SPARKS/SMOKE FROM SIDEWALL LIGHT 1C, BALLAST CONFIRMED THE SOURCE. CREW DROPPED PSU PANEL TO FUND THE SOURCE AND C ONFIRM SHORTING OF THE FORE/AFT WIRES TO THE AFT JUNCTION BOX. WIRING REPAIRED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090204 EA 2009 2 4 CA081204007 1 20081202 G 3234 SHAFT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE MLG HANDLE WORN W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) DURING MX OPERATION OF THE LANDING GEAR MANUAL RELEASE HANDLE IT STUCK IN THE RELEASE POSITION. MX TROUBLESHOOTIN G FOUND THE RELEASE HANDLE SHAFT BINDING DUE TO INTERNAL WEAR AND SLIGHTLY BENT. RELEASE HANDLE ASSY WAS REPLACED IAW A MM 32-34-01. ACF TT 14745 HOURS, 123110 CYCLES. 2 L 7 2 4F 4 F RT A21EA E15NE 20081229 SW 2008 12 29 CA081204008 1 20081127 G 5210 4744 HINGE PIN BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2A 41514 EA MCAULY 1A200 1A200* GL PAX DOOR RUSTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AN ATTEMPT TO REMOVE THE ENTRANCE DOOR USING THE EMERGENCY EXIT HANDLE FOUND THAT THE SYS HAD BECOME SEIZED. UPO N CLOSER INSP, IT WAS FOUND THAT THE HINGE PIN (DISPITE PERIODIC LUBING) HAD BECOME RUSTED TO THE AIRFRAME PIN TABS. THE DOOR CONTINUED TO OPEN AND CLOSE PROPER USING THE NORMAL SYS. THE ONLY SYS THAT FAILED IS THE JETTISON PORTION OF THE S YS. THE MM DOES NOT CALL FOR LUBBING OR FUNCTION CHECKING THIS SYS. IT HAS BEEN APPROXIMATELY 2000 HRS SINCE THE LAST RE CORDED REMOVAL OF THE DOOR. 1 H 7 1 3O 3 O A21CE E286 5 N P874 20081219 CE 2008 12 19 CA081204009 1 20081201 G 7820 175400125 MUFFLER CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL ENGINE LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 799 (CAN) WHILE CARRYING OUT AD CF90-03R2 A SMALL LEAK WAS NOTED AT THE TOP OF THE EXHAUST PIPE JUNCTION WITH THE MUFFLER BO DY. THIS IS A COMMON PLACE FOR THESE MUFFLERS TO FAIL. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20081219 CE 2008 12 19 CA081204010 1 20081201 G 7820 175400122 MUFFLER CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1611 (CAN) DURING PREFLIGHT INSPECTION, A 2" CRACK IN THE END OF TAILPIPE WAS NOTED, RUNNING PARALLEL TO THE PIPE AXIS. THE C RACK APPEARS TO BE AT THE EDGE OF A HOT SPOT CAUSED BY THE WAY THE EXHAUST GASES FLOW OUT OF THE PIPE AND MAY HAVE BEEN A RESULT OF THERMAL STRESSES SET UP BY UNEVEN HEATING. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20081222 NM 2008 12 22 CA081204011 1 20081129 G 2931 7G773 PRESSURE SWITCH DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYDRAULIC SYS MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) NR 2 EDP AMBER LIGHT CAME ON AT 30 KTS. DURING TAKE-OFF ROLL. ABORTED TAKE-OFF. PRESS WAS NORMAL ON THE INDICATO R, BUT THE NR 2 EDP AMBER CAUTION LIGHT IS ON. TR128. CONNECTOR ON PRESSURE SWITCH CLEANED. NR 2 SYSTEM HYD PRESSURE S WITCH REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090204 EA 2009 2 4 CA081204012 1 20081202 G 5610 NP139321003 WINDSHIELD CNDAIR CL600 CL6002C10 1390015 EA COCKPIT BROKEN W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) DURING CRUISE, RT (F/O) WINDSHIELD SHATTERED, WITH NO LOSS OF PRESSURIZATION. CAPTAIN DESCENDED AND DECLARED AN E MERGENCY LANDING RT WINDSHIELD (P/N OFF: NP139321-003) CHANGED IAW AMM 56-11-01. 2 L 7 2 4F RT A21EA 20090204 NE 2009 2 4 CA081204013 2 20081127 G 7261 GE6087T04P0 SCREEN CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE SCAV PUMP OBSTRUCTED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 21013 (CAN) IFSD EN ROUTE FROM PHL - PIT. LOSS OF ENGINE OIL PRESSURE AT FLIGHT FL340. LEFT ENGINE RED OIL PRESSURE CAS MESS AGE ILLUMINATED. OIL PRESSURE READ 23 PSI PRIOR TO ENGINE SHUTDOWN. OIL TEMP WAS NORMAL PRIOR TO ENGINE SHUTDOWN. AIR CRAFT WAS DIVERTED MADE AN UNEVENTFUL LANDING AT PIT. INSPECTION BY MAINTENANCE REVEALED COKING AROUND THE SCREEN. LUB E PUMP WAS REMOVED AND REPLACED IAW TO 70-21-01. AIRCRAFT RETURNED TO SERVICE WITH NORMAL OPERATION. (TC NR 2008120401 3) 2 L 7 2 4F 4 F RT A21EA E15NE 20081219 NE 2008 12 19 CA081205001 2 20080723 G 7200 ENGINE DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE NR 2 DAMAGED W A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 CA 9400 (CAN) AN ACFT RETURNED TO BASE DUE TO ENGINE NR 2 FIRE WARNING LIGHT ILLUMINATE. ENGINE FOUND DAMAGED AND REMOVED FOR I NVESTIGATION. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20081229 2008 12 29 CA081205002 4 20081123 G 3400 8221577202 DISPLAY CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B 30069 NE MFD 1 INOPERATIVE W O OTHER H ELECT. POWER LOSS-50 PC DE DESCENT 1 CA (CAN) 30 MINUTES PRIOR TO LANDING, THE PILOT PRIMARY FLIGHT DISPLAY(PFD 1) WENT BLANK. THEN IAW AFM (SECTION 05-15-1) TH E CREW SELECTED THE REVERSION MODE TO HAVE THE MULTIFUNCTION DISPLAY (MFD 1) IN COMPRESSED MODE, AT THAT TIME THE MFD 1 ALSO WENT BLANK. THE CREW RESELECTED REVERSION TO NORMAL, BOTH DISPLAY RETUNED TO NORMAL. APPROXIMATELY 10 MINUTES LATER , THE PFD 1 BLANK AGAIN AND OPERATED ON AND OFF EVERY 2- 3 MINUTES UNTIL LANDING. CONDITION WAS NO LONGER PRESENT AFTER FLIGHT AND REVERSION SYS WORKED NORMALLY. WIRING VERIFICATION DONE NO ANOMALY NOTED. AFD (PFD 1 POSITION) REPLACED IAW A MM 31-61-00. THE MFD 1 (P/N: 822-1917-202 S/N: 2NKRG) WAS ALSO REPLACED BUT A PRECAUTIONARY MEASURE . ACFT RETUNED TO SE 2 L 7 2 4F 4 F RT A21EA E15NE 20081222 EA 2008 12 22 CA081205003 1 20081204 G 5720 SUPPORT BRACKET DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE AILERONS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT AND RT WING AILERON INPUT QUADRANT SUPPORT BRACKETS AT YW414.00 CRACKED. QUADRANT SUPPORT BRACKETS REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 20090203 SW 2009 2 3 CA081205004 1 20081126 G 7603 C8102415 CONTROL CABLE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP POWER LEVER BROKEN W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 CA (CAN) DURING TAXI, CREW SELECTED SPEEDS HIGH & APPLIED POWER. AS POSITIVE TORQUES WERE CALLED TROUGH ABOUT 1200FT/LBS, A SNAP WAS HEARD & THE LT POWER LEVER ADVANCED FORWARD WITH NO FURTHER ENGINE POWER INCREASE. TAKEOFF ABORTED & CREW SL OWLY REDUCED POWER TO FLIGHT IDLE. LT ENGINE DID NOT RESPOND TO FURTHER POSITIVE POWER LEVER INPUTS BUT WOULD RESPOND W HEN REDUCED TO FLT IDLE. ACFT TAXIED BACK TO APRON & SHUTDOWN. MX DETERMINED LT ENGINE POWER LEVER CABLE SECTION FROM POWER LEVER QUADRANT TO WING ROOT HAD BROKEN. NO DEFINITIVE CAUSE FOR BREAK DETERMINED BUT IT WAS AT THE POINT WHERE PR OPER ROUTING OF CABLE REQUIRES A SIGNIFICANT BEND IN CABLE ASSY. CABLE REPLACED & ACFT RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A8SW E4WE 20081229 NM 2008 12 29 CA081205006 1 20081202 G 3240 244300 STATOR BFGOODRICH BOEING 727 727223 1384074 NM PWA JT8 JT8D15 52051 NE BRAKE ASSY BROKEN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) DURING PUSHBACK ON C-FCJF EXCESSIVE FORCE WAS REQUIRED TO MOVE ACFT AND DETERMINED NR2 MAIN WHEEL WAS DEFLATED. AC FT PULLED BACK TO GATE FOR INVESTIGATION. MAINT WAS UNABLE TO REMOVE NR2 WHEEL. AFTER SEVERAL EFFORTS WITHOUT SUCCESS I T WAS DECIDED THE TIRE AND POSSIBLY THE WHEEL WOULD HAVE TO BE CUTOFF. AFTER CUTTING A SECTION OF THE TIRE OFF IT WAS D ETERMINED A PIECE OF THE BRAKE STATOR HAD BROKEN OFF AND PENETRATED THE WHEEL HUB AS THE ACFT WAS TOWED DEFLATING THE TI RE AND MAKING IT IMPOSSIBLE TO REMOVE WHEEL. THE BROKEN PIECE OF THE STATOR WAS REMOVED ALLOWING REMOVAL OF THE WHEEL. WHEEL AND BRAKE ASSY REPLACED. 2 L 7 3 4F 4 F A3WE E2EA 20081222 CE 2008 12 22 CA081205007 1 20081204 G 3710 5100106377 LINE CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C505 GL VACUUM SYS CORRODED W O OTHER O OTHER CR CRUISE 1 CA 5291 (CAN) UPON REACHING CRUISE FLIGHT AND ACTIVATING AIRFRAME PNEUMATIC DE-ICE SYSTEM, THE BOOTS WOULD REMAIN PARTIALLY TO M OSTLY INFLATED. THIS PROBLEM WOULD NOT DUPLICATE ON A GROUND RUN. THE VACUUM LINE TO THE FLOW VALVES WAS INSPECTED AN D A LINE ASSEMBLY TO THE TAIL FLOW VALVE WAS FOUND CORRODED WHERE IT PASSED OVER AN ENVIRONMENTAL DUCT AT APPROX. MID CA BIN. THE LINE ASSEMBLY WAS REPAIRED. THE ACFT WAS GROUND RUN AND FLOWN TO CRUISE ALTITUDE TO MAX. CABIN PRESSURE DIFF ERENTIAL, AND THE PNEUMATIC DE-ICE SYSTEM FUNCTIONED PROPERLY. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 20081229 SW 2008 12 29 CA081205008 1 20081204 G 5610 HYLZ88821 WINDSHIELD FRCHLD SA227 SA227CC 3377522 SW GARRTT TPE331 TPE33111U 29073 NE MCAULY 4HFR34 4HFR34C652 NE COCKPIT FAILED W O OTHER O OTHER AP APPROACH 1 CA (CAN) ON APPROACH THE LT WINDSHIELD SHATTERED. MX WAS DISPATCHED TO REPLACE THE WINDSHIELD. THE TEMP CONTROLLER WAS FOUN D TO BE DEFECTIVE ALSO. TEMP CONTROLLER REPLACED ALONG WITH WINDSHIELD AND ACFT RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 20081219 EA 2008 12 19 CA081207001 2 20081202 G 7414 106006169 MAGNETO LYC O540 O540F1B5 41532 EA ENGINE FAILED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA 302 (CAN) AFTER START MAG CHECK PERFORMED AND LT MAG FAILED. MX WAS NOTIFIED AND WHEN MAG WAS LOOKED AT FOUND THAT THE BREA KER POINT WIRES HAD VIBRATED OFF. WIRES REPAIRED AND REINSTALLED. 3 O E295 20081219 CE 2008 12 19 CA081208001 1 20081119 G 3222 SK1759 FORK CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL NOSE GEAR CRACKED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 15146 15146 (CAN) ON ROLL OUT FROM LANDING NOSE WHEEL BROKE OFF. ACFT SLID APPROX. 400` ON NOSE AND CAME TO A STOP. APPARENT CAUSE METAL FATIGUE OF NOSE WHEEL FORK. TSB HAS SECURED FAULTY PARTS AND INVESTIGATING FURTHER. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20081222 NM 2008 12 22 CA081208002 1 20081207 G 3231 483023 SEQUENCE VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA LT MLG DOOR MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 1398 (CAN) FLIGHT CREW REPORT: LT MAIN AMBER GEAR DOOR LIGHT FAILED TO EXTINGUISH ON GEAR RETRACTION (VISUALLY OPEN). ALT EXT ENSION PERFORMED. REPLACED LT MLG SSV IAW 32-31-41 2 H 7 2 4T 4 T RT A13NM E00062EN 20081222 SO 2008 12 22 CA081208005 1 20081208 G 8120 BEARING PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA TURBOCHARGER FAILED W A D UNSCHED LANDING RETURN TO BLOCK E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 36 (CAN) SHORTLY AFTER TAKE-OFF THE PILOT HEARD A "BANG" FROM THE RT ENGINE AND NOTICED A LOSS OF MANIFOLD PRESSURE. HE TH EN RETURNED TO THE AIRPORT WITH NO PROBLEMS ENROUTE. MX FOUND THE TURBO CHARGER SHAFT BEARING HAD FAILED. THE TURBO CH ARGER WAS REPLACED, OIL SUMP CLEANED, OIL FILTER REPLACED AND GROUND RUN ACCEPTABLE. 1 L 7 2 3O 3 O A20SO E14EA 20090204 EU 2009 2 4 CA081208007 1 20081201 G 2435 23085024 STARTER GEN PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NR 1 MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA 54 (CAN) PILOT REPORTED WAS NR 1 GENERATOR WENT OFF LINE PRIOR TO TAKEOFF. WAS UNABLE TO RESET RETURNED TO BLOCKS. NR 1 G ENERATOR REPLACED AND GROUND RUN PERFORMED, ALL FOUND SATISFACTORY. (TC NR 20081208007) 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20090205 CE 2009 2 5 CA081208008 1 20081208 G 2435 200SGL119Q2 STARTER GEN CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 110 (CAN) GENERATOR FAILED IN FLIGHT 12 MILES FROM YWG ENROUTE TO YQT. AIRCRAFT RETURNED TO YWG (TC NR 20081208008). 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 20090205 NM 2009 2 5 CA081208009 1 20081201 G 5751 BRACKET DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE AILERONS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING MAINTENANCE INSPECTION BOTH THE LT AND RT AILERON QUADRANT SUPPORT BRACKETS WERE FOUND CRACKED. PART NUMBE RS INCLUDED, LT END PIECE P/N 85711570-101, RT END PIECE P/N 85711570-102, LT BOTTOM PLATE P/N 85711572-101, RT BOTTOM P LATE 85711572-102, OF NOTE WHEN THE RT END PIECE WAS REMOVED THERE APPEARED TO BE EVIDENCE OF AN APPARENT PREVIOUS WELD REPAIR OF UNKNOWN ORIGIN. A CHECK OF THE AIRCRAFT MAINTENANCE HISTORY COULD NOT FIND A RECORD OF SUCH A REPAIR. ALL CR ACKED BRACKETS WERE REPLACED. (TC NR 20081208009) 2 H 7 2 4T 4 T RT A13NM E20NE 20081222 2008 12 22 CA081208011 1 20081126 G 7830 9007M60G46 COWLING GE CF6 CF650C2 30018 NE THRUST REVERSER DELAMINATED W E ENGINE SHUTDOWN E D VIBRATION/BUFFET INFLIGHT SEPARATION DE DESCENT 1 CA (CAN) ON DESCENT INTO YYC, WITH POWER LEVERS AT IDLE, THE ACFT SHUDDERED MOMENTARILY. THE NR 2 THRUST REVERSER UNLOCK L IGHT ILLUMINATED AND IN-FLIGHT SHUT DOWN OF NR 2 ENGINE WAS CARRIED OUT. THE ACFT LANDED WITHOUT INCIDENT AND AN INSPEC TION WAS CARRIED OUT ON NR 2 ENGINE. NR 2 ENGINE RT TRANSLATING COWL WAS FOUND DELAMINATED WITH A SECTION OF THE COWL M ISSING. THE COWL WAS REPLACED, FUNCTION CHECKED AND THE ACFT RETURNED TO SERVICE. 4 F E23EA 20090203 EA 2009 2 3 CA081209005 1 20081208 G 5711 215003268 SPAR CAP CNDAIR CL215 CL2151A10 1900320 EA WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4895 (CAN) WHILE PERFORMING AD 92-26R1 NO DEFECTS WERE FOUND DURING ULTRASONIC INSPECTION OF REQUIRED INSPECTION AREA. DUE T O PREVIOUS CONCERNS (3) WITH FINDING CRACKS OUTSIDE OF INSPECTION AREA FURTHER INVESTIGATION WAS PERFORMED. CRACKS WERE FOUND IN LOWER SPAR CAP, LOWER WING SKIN AND BOTH REINFORCING STRAPS. 2 H 7 2 4R RT A14EA 20081222 SW 2008 12 22 CA081209006 1 20080611 G 6300 206040015103 DRIVE SHAFT BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL M/R DRIVE FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA (CAN) ON DESCENT PILOT SMELLED BURNING GREASE. AFTER LANDING AND POST FLIGHT INSPECTION FOUND GREASE THROWN FROM DRIVES HAFT COUPLING. DRIVESHAFT WAS REPLACED AND FOUND ISOLATION MOUNT TO BE WEAK. REPLACED ISOLATION MOUNT AND PROBLEM WENT AWAY. 1 G 7 1 3U 3 U H2SW E4CE 20081222 CE 2008 12 22 CA081210001 1 20081108 G 3245 5005 TUBE CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MLG TIRE TORN W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) THE NOSE TIRE INNER TUBE HAD 195 HRS SINCE NEW. IT WAS FOUND RIPPED. NO HARD LANDING WAS REPORTED. THE INSIDE OF THE TIRE WAS FOUND FREE OF ANY DEFECTS. 1 H 7 1 3O 3 O NT 3A12 E274 20081222 CE 2008 12 22 CA081210002 1 20081208 G 3245 5005 TUBE CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA NLG TIRE TORN W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) THE NOSE WHEEL TIRE INNER TUBE HAD 220 HRS SINCE NEW. IT WAS FOUND TORN ON THE SIDE WALL. NO HARD LANDING WAS RE PORTED. THE INSIDE OF THE TIRE WAS FOUND FREE OF DEFECTS. THIS TO ME IS AN OBVIOUS MANUFACTURING PROBLEM. IT HAPPENED ON TAXI FROM THE RUNWAY AFTER NORMAL LANDING. 1 H 7 1 3O 3 O NT 3A12 E274 20081222 SO 2008 12 22 CA081210003 1 20081208 G 3245 5005 TUBE PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA NLG TIRE TORN W O OTHER O OTHER NR NOT REPORTED 1 CA 391 (CAN) THE NOSE WHEEL TIRE INNER TUBE WAS FOUND TORN. THE ACFT SAT OVER NIGHT. THE INNER TUBE HAD 391 HRS SINCE NEW. T HE NOSE TIRE WAS INSP, NO DEFECTS FOUND. 1 L 7 1 3O 3 O 2A13 E274 20090203 GL 2009 2 3 CA081210004 1 20081209 G 2421 A3579101 GENERATOR BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP APU FIRE W O OTHER A B J FLAME/FIRE SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION DE DESCENT 1 CA (CAN) AFTER APU START AT FL100 JUST BEFORE APU GEN ON LINE APU FIRE CAS MESSAGE POSTED. PILOTS ARM APU BOTTLE MESSAGE D ISAPPEARED. PILOTS SHUTDOWN APU AND LAND A/C SAFELY. IN AFT EQUIPMENT BAY PILOTS NOTED AN ODOR OF BURNED WIRE. AFTER INSPECTION OF APU GENERATOR FOUND GENERATOR ON FIRE. FIRE WENT OUT VIA COOLING DUCT TO EDUCATOR SENSING ELEMENT OF APU FIRE DETECTION SYSTEM. APU DOOR SHOWING SIGNS OF FIRE. 2 L 7 2 4F 4 F RT T00005NY E00010LA 20081222 NM 2008 12 22 CA081210005 1 20081209 G 3213 654611635 CYLINDER BOEING 737 737232 1384475 NM PWA JT8 JT8D17 52049 NE STRUT WORN W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA 37952 16636 (CAN) RT MLG LOST FLUID. DURING ATTEMPTED SEAL CHANGE, THE INNER CYLINDER OF THE GEAR HAD A 6" BY 2" PIECE OF CHROME MI SSING FROM THE INNER CYLINDER. 2 L 7 2 4F 4 F RT A16WE E2EA 20090203 CE 2009 2 3 CA081210006 1 20081208 G 5220 115430100661A SKIN BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE EMERGENCY EXIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9902 (CAN) WHEN COMPLYING WITH SPECIAL INSPECTION "ESCAPE HATCHES AND ASSOCIATED AREAS", A CRACK WAS FOUND AT THE LOWER FORWA RD CORNER OF THE BONDED RT EMERGENCY EXIT DOOR SKIN, EXACTLY AS PICTURED IN THE MAINTENANCE MANUAL. REPLACED SKIN ASSEM BLY WITH NEW. CRACKS ARE DIFFICULT TO DETECT DUE TO FILLER USED BY THE MANUFACTURER TO BLEND THE RADIUS AFTER FITTING T HE SKIN. OUR INSPECTION TSK IS AMENDED TO INDICATE THE INTERIOR PANEL IS TO BE REMOVED AND INSPECTED FROM THE INSIDE. HIGH TIME/HIGH CYCLE B300 OF OUR FLEET OF FIVE AIRCRAFT. 2 L 7 2 4T 4 T A24CE E4EA 20081229 NE 2008 12 29 CA081210008 2 20081204 G 7250 FW45914 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 5094 (CAN) SURGE/IFSD/ENGINE SHUTDOWN IN FLIGHT WITH TGT CLIMBING THROUGH 1100 C. BOROSCOPE OF ENGINE 13299 TODAY FOUND THA T 2 OFF HPT STAGE 1 BLADES SUFFERED FROM A BELOW-PLATFORM FAILURE. THE 2 FAILED BLADES ARE SEPARATED BY 28 BLADES. THE A IRFOILS ON ALL OF THE REMAINING BLADES HAVE BEEN KNOCKED OFF ABOVE THE PLATFORM. 2 L 7 2 4F 4 F TR A6WE E00061EN 20081222 NE 2008 12 22 CA081210009 2 20081201 G 7200 ENGINE AEROSP ATR42 ATR42* 8680900 EU PWA 120 PW120 NE ODOR W E ENGINE SHUTDOWN B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, THE PILOTS NOTICED OIL ODOR AND MIST IN THE CABIN. THEY TURNED THE AIR BLEED FROM THE ENGINE OFF A ND THE MIST AND ODOR DISAPPEARED. SOON AFTER, OIL PRESSURE FLUCTUATIONS AND THEN A DROP IN PRESSURE OCCURRED. THE PILO TS SHUT DOWN THE ENGINE AND PERFORMED A SINGLE ENGINE LANDING. GROUND INSPECTION FOUND LOW OIL LEVEL, BOROSCOPE INSPECT ION OF THE AIR INLET WAS MADE AND REVEALED OIL LEAK FROM C OR D FLANGE AND THE REAR INLET CASE IS FLOODED WITH OIL. THE ENGINE WILL BE REMOVED. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A53EU E20NE 20081229 NE 2008 12 29 CA081210010 2 20081127 G 7200 ENGINE FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE POWER LOSS W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB AFTER T/O, ENGINE POWER LOSS OCCURRED (AT APPROX 300 FT ALTITUDE). THE ENGINE WAS SECURED AND A TURNB ACK INITIATED. THE ACFT MADE A SINGLE ENGINE LANDING. POST EVENT INSP FOUND FRACTURED HP BLADES. MFG WILL CONTINUE INVES TIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A817 E20NE 20090203 EA 2009 2 3 CA081210011 2 20081210 G 7200 ENGINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA NR 1 SHUTDOWN W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) NR 1 ENGINE SHUTDOWN CARRIED OUT AFTER TAKEOFF. HERE IS THE DEFECT ENTERED BY THE FLIGHT CREW "LT PROP RPM ONLY G OES TO 1500 RPM ON TAKEOFF AS POWER REDUCED RPM DROPS". THE INCIDENT IS UNDER INVESTIGATION. 2 L 7 2 4T 4 T RT A24CE E4EA 20090203 EU 2009 2 3 CA081210012 1 20081208 G 5530 313108 BRACKET ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE73131G 29003 NE VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9341 (CAN) FOUND CRACK IN BRACKET LOCATED ON THE FORWARD SIDE OF THE VERTICAL STAB ATTACH FITTING AT FS 521.75. THREE CRACK S EXTEND FROM THE RIGHT OUTBOARD ATTACHMENT BOLT HOLE. THE ATTACHING BOLTS RUNS HORIZONTALLY FWD AND AFT THROUGH THE RU DDER STOP BRACKET, VERTICAL STAB ATTACH FITTING, AND THROUGH THE BRACKET (P/N: 313108) WHICH IS CRACKED. REFERENCE IPC: 53-40-00 FIG 1 (SHEET 2) PAGE 1, PART SHOWN DIRECTLY BELOW ITEM 32. 2 M 7 2 4F 4 F A2SW E6WE 20081222 NE 2008 12 22 CA081210013 2 20081128 G 7414 BL600646201 MAGNETO ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE ENGINE UNSERVICEABLE W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) MAGNETO FOUND U/S. 1 G 7 1 3O 3 O H11NM 1E4 20081229 EA 2008 12 29 CA081211002 3 20080116 G 6111 W69EK763 PROPELLER DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA TIP OF BLADE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 354 (CAN) PRIOR TO A TRAINING FLIGHT WITH A STUDENT A WALK AROUND WAS PERFORMED ON THE ACFT WHERE IT WAS NOTED THAT ONE OF T HE PROPELLER BLADE LEADING EDGE TIPS HAD AN INDICATION OF POSSIBLE ROCK CHIP DAMAGE OF APPROXIMATELY .2500 INCH IN LENGT H AND LESS THAN A .0625 INCH IN DEPTH. IT SHOULD ALSO BE NOTED THAT THE PREVIOUS CREW HAD REPORTED A SLIGHT ENGINE VIBR ATION AT 1700 RPM. UPON INSP BY AN AME IT WAS DETERMINED THAT IN FACT THERE WAS A SLIGHT NICK POSSIBLY CAUSED BY A SMALL ROCK. UPON FURTHER INVESTIGATION A CRACK WAS FOUND THAT WAS LOCATED AT THE MIDPOINT OF THE BLADE AT THE VERY TIP AND EX TENDED INWARD APPROX 2 INCHES. BY APPLYING PRESSURE TO EITHER OPPOSING SIDES OF THE BLADE TIP THE CRACK BECAME VERY APPA 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 20081229 EA 2008 12 29 CA081211003 3 20081110 G 6111 W69EK763T PROPELLER DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA TIP OF BLADE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 331 (CAN) IN BETWEEN AND PRIOR TO A TRAINING FLIGHT THE PILOT AND STUDENT CONDUCTED A WALK AROUND WHERE IT WAS NOTICED THAT ON THE NR1 BLADE TIP THERE APPEARED TO BE A CRACK EMANATING FROM THE CENTER OF THE BLADE TIP WHICH EXTENDED INWARD TOWAR DS THE ROOT. AN AME CONDUCTED A VISUAL INSPECTION UNDER 10X MAGNIFICATION AND VERIFIED THAT A CRACK EXISTED FROM THE CEN TER OF THE NR1 BLADE TIP AND EXTENDED APPROX 2 INCHES INWARD TRAVELLING TOWARDS THE BLADE ROOT. THE AIRCRAFT WAS IMMEDIA TELY REMOVED FROM SERVICE WHERE A NEW PROPELLER ASSEMBLY WAS INSTALLED. 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 20090203 NM 2009 2 3 CA081211004 1 20081203 G 5310 85312397101 BRACKET DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE WINDOW CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) DURING THE ACCOMPLISHMENT OF TASK 5310/06C, WINDSHIELD AND SIDE WINDOW LOWER SILL JOINT TO SIDE POST, THE BRACKET CONNECTED TO UNDERSIDE OF THE LOWER SILL TO THE SIDE POST (RIGHT SIDE) WAS FOUND TO HAVE A 2 1/2 INCH CRACK IN IT. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090206 EA 2009 2 6 CA081211005 1 20081204 G 5330 21530023 SKIN CNDAIR CL215 CL2156B11215 EA FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A MX INSPECTION, AN EMPLOYEE FOUND A CRACK ON THE TOP SKIN FS 388 RSTR 9. DWG 215-30023-175 AOM 53-30-00-10 3 REV A. 2 H 7 2 4T RT A14EA 20081222 CE 2008 12 22 CA081212002 1 20081205 G 2421 BEARING CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO ALTERNATOR FAILED W H DEACTIVATE SYST/CIRCUITS B H SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 16 (CAN) IN CRUISE PILOT NOTICED SPARKS COMING FROM RT ENGINE. UPON EXAMINATION ON GROUND BY MX, ALTERNATOR OUTER BRG. FAI LED. SHAFT DEFORMED FROM HEAT. FAILURE OF CRANKSHAFT ALTERNATOR DRIVE GEAR CAUSED MAJOR INTERNAL ENGINE DAMAGE. 1 L 7 2 3O 3 O A7CE E7CE 20090203 NE 2009 2 3 CA081212003 2 20081212 G 7320 J2009P03 PLUG CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE MFC LOOSE W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE CHECK, A FUEL LEAK WAS DISCOVERED COMING FROM THE NR 2 ENGINE MFC. UPON FURTHER INVESTIGATION A PLUG WAS FOUND LOOSE. THE PLUG WAS REMOVED, THE O-RING REPLACED AND THE PLUG RE-INSTALLED. A LEAK CHECK WAS CARRIED OU T WITH NO LEAKS NOTED IPC REF IS 73-11-00, FIG. 5-380. A RECORDS CHECK WAS CARRIED OUT AND NO PREVIOUS WORK WAS NOTED I N THIS AREA. THIS PLUG IS NORMALLY NOT TOUCHED IN SERVICE, IT WOULD NORMALLY ONLY BE LOOKED AT DURING OVERHAUL OR BENCH CHECK. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 CE 2009 2 3 CA081212004 1 20081209 G 3244 301401311 TIRE CESSNA 441 441 2076020 CE GARRTT TPE331 TPE33110N 29062 NE MLG DEFECTIVE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 184 (CAN) DEFECT IN SIDEWALL CAUSED SIGNIFCANT LOSS OF PRESSURE. 1 L 7 2 3T 4 T RT A28CE E4WE 20090203 NE 2009 2 3 CA081212005 3 20081212 G 6111 6607122666 BLADE SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R389 R3894123F25 NE NR 2 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 38984 4641 (CAN) THE PROP IN QUESTION WAS REMOVED FOR DISASSEMBLY TO BE SENT FOR DELAMINATION BEYOND LIMITS TO THE MANUFACTURER. W HEN THE PROP ASSEMBLY WAS DISASSEMBLED, A RADIAL CRACK WAS DISCOVERED IN NR 2 BLADE MEASURING IN EXCESS OF 6 INCHES IN T HE HUB OF THE BLADE S/N: SF340-132/234. IT WAS DISCOVERED VISUALLY AND HAS SUBSEQUENTLY BEEN SENT FOR REPAIR TO THE MAN UFACTURER. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P30NE 20090203 NE 2009 2 3 CA081212006 2 20081209 G 7210 310838801 WASHER PWC DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE NR 9 BEARING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NR 2 ENGINE RGB METAL CHIP FOUND ON CHIP DETECTOR. DETERMINED TO BE NON-ALLOWABLE CATEGORY 1 DEBRIS, IDENTIFIABLE FRAGMENT. ALSO WASHER WAS CRACKED ENGINE S/N 123037 RGB S/N 123124 DEBRIS IDENTIFIED AS NR 9 BEARING KEY TAB WASHER T AB. IN CONSULTATION WITH MANUFACTURER THE COMPONENT WAS GIVEN A 10 HOUR REINSPECT, .10 HOUR, REINSPECT COMPLETED WITH NO FURTHER ANOMALIES. 2 H 7 2 4T 4 T RT A13NM E20NE 20090203 2009 2 3 CA081212007 2 20081027 G 7414 4372 STOP PIN MAGNETO WORN W K NONE O OTHER IN INSP/MAINT 1 CA 764 (CAN) EXCESSIVE WEAR WAS NOTED ON IMPULSE COUPLING STOP PIN. 20090206 2009 2 6 CA081212008 2 20081212 G 7414 4372 STOP PIN MAGNETO WORN W K NONE O OTHER IN INSP/MAINT 1 CA 328 (CAN) EXCESSIVE WEAR WAS NOTED ON IMPULSE COUPLING STOP PIN. 20090203 CE 2009 2 3 CA081212010 1 20081209 G 3260 WARNING LIGHT BEECH 200 200BEECH 1152920 CE MLG UNKNOWN W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) ON DEC 9TH, RETURNING FROM KGEG TO CYYC - ON TAKEOFF, WHEN THE GEAR WAS RETRACTED, THE FLIGHT CREW NOTICED THE "RE D" GEAR LIGHTS WERE INDICATING THAT THE GEAR WAS NOT FULLY RETRACTED. FLIGHT CREW CYCLED THE GEAR ONCE MORE AND ON THAT ATTEMPT WERE ABLE TO CONFIRM THAT THE GEAR WAS LOCKING DOWN, BUT ONCE BROUGHT UP THE RED LIGHTS DID NOT GO OUT. THE FL IGHT CREW DID A VISUAL INSPECTION OF EACH MAIN GEAR WHEEL AND CONFIRMED THAT THE MAIN WHEELS WERE INDEED UP. AT ALTITUD E, THE FLIGHT CREW CYCLED THE GEAR ONCE MORE AND THE LIGHTS WENT OUT INTERMITTENTLY, BUT SHORTLY AFTER STARTED TO COME O N AGAIN. THE FLIGHT CREW MAINTAINED THE GEAR EXTENSION SPEED OF 181KTS FOR THE REMAINDER OF THE FLIGHT. OTHER THAN HAV 1 L 7 2 4T A24CE 20090203 CE 2009 2 3 CA081212011 1 20081204 G 8000 C2925010105 SWITCH CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL STARTER UNSERVICEABLE W O OTHER M B H OVER TEMP SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 CA (CAN) HAD STARTER FAILURES WHERE THEY SEIZED AND OVERHEATED. INVESTIGATION REVEALED THAT IF PILOT AGGRESSIVELY ROTATED KEY IN CLOCKWISE DIRECTION THAT KEY WOULD JAM AND LEAVE SWITCH IN THE START POSITION. THIS WOULD CAUSE THE STARTER TO R EMAIN ENGAGED UNTIL IT SMOKED. REPLACED SWITCH WITH NEW, ALL CORRECT. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 20090203 EU 2009 2 3 CA081212013 2 20081006 G 7210 SPLINE ROTAX ROTAX 912 ROTAX912F3 EU PROP SHAFT CHIPPED W K NONE O OTHER IN INSP/MAINT 1 CA 1465 44 (CAN) METAL CHIP FOUND ON MAGNETIC PLUG DURING SERVICING. TRACED TO GEARBOX. GEARBOX REMOVED AND CHIP WAS FOUND TO BE FROM TOP SPLINE OF THE PROPSHAFT JUST ABOVE THE RING HALF. POSSIBLE CAUSE, COULD BE FROM A "STEP" WORN IN FROM RING HAL F. IF RING HALF WAS INSTALLED WITH THIS STEP RESTING ON THE RING SURFACE IT COULD CAUSE A STRESS POINT. THERE IS A SLI GHT CORRESPONDING WEAR MARK 180 DEGREES FORM THE CHIP THAT INDICATES THE CHIP IS RELATED TO THE PREV RING HALF LOCATION. PROPSHAFT HAD PASSED NDT 44.5 HRS PRIOR (OVERHAUL). AREA COULD HAVE BEEN UNDER HIGH LOAD DUE TO STEP WORN INTO SPLINE . PROPSHAFT REPLACED. INCLUDE INSPECTION FOR THIS TYPE OF WEAR IN FUTURE WORK. 3 O E00051EN 20090206 2009 2 6 CA081212015 4 20081117 G 2562 97A256000000 ELT CABIN MALFUNCTIONED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) A NR OF INSTANCES OF UNCOMMANDED TRANSMISSIONS HAVE OCCURRED ON 406MHZ ELTS INSTALLED ON OUR ACFT. 20090203 NM 2009 2 3 CA081214001 1 20081213 G 2820 8SC0764 CHECK VALVE BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA FUEL SYSTEM FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) DURING THE UNSCHEDULED REMOVAL OF THE NR 2 ENGINE FUEL FLOW TRANSMITTER, RESIDUAL AIRFRAME FUEL WOULD NOT STOP FLO WING. FURTHER INVESTIGATION REVEALED THE RIGHT WING FUEL TANK "MOTIVE FLOW CHECK VALVE" STUCK OPEN. MOTIVE FLOW CHECK VALVE REMOVED AND REPLACED AS PER AMM 28-11-11. 2 H 7 2 4T 4 T RT A13NM E00062EN 20090203 2009 2 3 CA081215003 4 20081209 G 6113 05503214 SPINNER 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 148 (CAN) CRACKS PERPENDICULAR TO TOP OF PROP BOLT HOLES BARELY VISIBLE TO THE NAKED EYE, CONFIRMED WITH LPI. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20090203 EA 2009 2 3 CA081215009 1 20081210 G 2750 855D10011 BPSU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA 11166 (CAN) DURING FINAL SEGMENT OF CLIMB, THE FLT CREW RECEIVED A FLAP FAIL MSG ON EICAS. THE FLAPS WERE AT ZERO AND WERE IN DICATING ZERO AT THE TIME. THE QRH WAS FOLLOWED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE CHECKED FECU FOR FAULT CODES AND FOUND CODES FOR RT BPSU, FECU AND WIRING FOR RT BPSU. THE SYSTEM WAS RESET, THE FLAPS WERE OPS CHECKED AND NO FURTHER DEFECTS NOTED. AIRCRAFT RETURNED TO SERVICE. IN CRUISE FLIGHT, THE FLT CREW RECEIVED A FLAP FAIL MSG. THE FLIGHT CONTROL SYNOPTIC PAGE INDICATED THE FLAPS WERE OUTLINED IN YELLOW SHOWING ZERO DEGREES OF EXTENSION. THE AI RCRAFT LANDED BACK WITHOUT INCIDENT. MAINTENANCE PULLED FECU CODES (SEE ATTACHED) WHICH INDICATED R BPSU OR WIRING. TH 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 SW 2009 2 3 CA081216001 1 20081110 G 5311 206033107117 FRAME BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON REMOVAL OF AFT CABIN HAT RACK ASSY RT FRAME ASSY WAS FOUND CRACKED. FRAME ASSY WAS REMOVED AND REPLACED NEW. 1 G 7 1 3U 3 U H2SW E1GL 20090203 SW 2009 2 3 CA081216002 1 20081110 G 5311 206033302031 FRAME BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON REMOVAL OF BELL INSTALLED HEATER ASSY. A VISUAL INSPECTION WAS COMPLETED OF THE AREA`S SURROUNDING STRUCTURE . THE LT AFT FRAME ASSY WAS FOUND CRACKED BEYOND LIMITS. THE CRACK WAS NOTED TO PROTRUDE FROM A RIVET HOLE ACROSS THE FACE OF THE FRAME. FRAME ASSY WAS REMOVED AND REPLACED NEW. 1 G 7 1 3U 3 U H2SW E1GL 20090203 EA 2009 2 3 CA081216003 2 20081211 G 7200 ENGINE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA 3823 (CAN) PILOTS HEARD A GRINDING SOUND FROM THE EXHAUST STACK WHEN PUTTING ON THE PROP TIE`S AFTER A FLIGHT. MAINTENANCE C ONFIRMED THE SOUND AND UPON REMOVING A EXHAUST STACK TO INVESTIGATE THEY VISUALLY CONFIRMED THAT THERE APPEARED TO BE A PIECE OF METAL CONTACTING THE NR 2 POWER TURBINE. POWER SECTION WAS REMOVED AND REPLACED AND IS IN AT STANDARD AERO WIN NIPEG FOR FURTHER INVESTIGATION AND REPAIR. TSO 3823.0, CSO 2033 (TTSN AND TCSN UNAVAILABLE AS LOG BOOKS ARE AT OVERHAUL FACILITY). 1 L 7 2 4T 4 T A24CE E4EA 20090203 SW 2009 2 3 CA081216004 1 20081214 G 5610 2719442004 WINDSHIELD SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP COCKPIT CRACKED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 3686 (CAN) DURING TAXI AS THE CREW TURNED INTO A 35 KNOT HEADWIND THE FIRST OFFICER WINDSHIELD SHATTERED. THE WINDSHEILD HEA T WAS SELECTED TO LOW AND THE OUTSIDE AIR TEMPERATURE WAS -36 DEGREES CELCIUS. MAINTENANCE REPLACED THE WINDSHIELD IN A CCORDANCE WITH THE AMM AND WAS RELEASED TO SERVICE. 2 L 7 2 4T 4 T RT A8SW E4WE 20090203 EA 2009 2 3 CA081216005 1 20081212 G 2750 FCU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) FLAPS FAILED AT 3 DEGREES ON APPROACH. NORMAL LANDING FOLLOWED. CREW ABLE TO RESET SYSTEM ON THE GROUND AND FLIG HT CONTINUED UNDER MEL. SECOND FLAP FAILURE ON AIRCRAFT 107 IN AS MANY FLIGHTS. FLAPS FAILED AT 23 DEGREES INBOUND. N ORMAL LANDING OCCURRED. MX RECTIFICATION TO FOLLOW ALL ACTUATORS REPLACED, RT BPSU REPLACED, LT NR 3 FLAP FLEX DRIVE RE PLACED, RT NR 1AND NR 4 FLAP FLEX DRIVES REPLACED. A/C THEN HAD TEST FLIGHT AND HAD ANOTHER FAILURE AT 38 DEGREES EXTEN SION. FLAP ELECTRONIC CONTROL UNIT AND FLAP PDU REPLACED AND A/C TEST FLIGHT WAS SUCCESSFUL. A/C RETURNED TO SERVICE D EC 18,2008. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 NE 2009 2 3 CA081217001 2 20081213 G 7230 COMPRESSOR BOEING 737 737201 1384454 NM PWA JT8 JT8D17 52049 NE NR 2 ENGINE FOD W C ABORTED TAKEOFF C A F.O.D. FLAME/FIRE TO TAKEOFF 1 CA CFJLB 43057 (CAN) AIRCRAFT WAS ON TAKEOFF ROLL WHEN THE PILOTS HEARD A LOUD BANG FROM ENGINE NR 2 & EXPERIENCED A YAW TO THE RIGHT A S THEY APPROACHED 110 KNOTS. THE PILOTS THROTTLED BACK, ABORTED THE TAKEOFF, TAXIED BACK TO THE RAMP AND SHUTDOWN THE E NGINES. PASSENGERS OBSERVED FLAMES EXPEL FROM NR 2 ENGINE INLET AND EXHAUST WHEN THE BANG OCCURRED. CONDUCTED AN INIT IAL VISUAL INSPECTION AND FOUND PART OF A RUBBER SEAL MISSING AND DETACHED FROM THE C2 INLET GUIDE VANE. THERE IS NO DA MAGE TO THE C1, C2 OR T4. REQUESTED AN EXTERNAL A BORESCOPE INSPECTION TO DETERMINE IF THERE IS DAMAGE TO THE INTERNAL PART OF ENGINE. NO EVIDENCE OF FOD INGESTION. 2 L 7 2 4F 4 F A16WE E2EA 20090203 EA 2009 2 3 CA081217002 1 20081216 G 3230 LANDING GEAR CNDAIR CL600 CL6002C10 1390015 EA GE CF34 CF348C5 30050 NE LEFT INOPERATIVE W O OTHER J WARNING INDICATION LD LANDING 1 CA (CAN) LANDED WITHOUT LT MLG NOT FULLY EXTENDED. THE FLT CREW ATTEMPTED TO EXTEND GEAR, BUT NEVER GOT A LT MLG GREEN DOW N AND LOCKED INDICATION. THEY CYCLED THE GEAR 3 TIMES, BUT STILL WERE UNABLE TO GET GOOD INDICATION. THEY PERFORMED A MANUAL EXTENSION AND AGAIN DID NOT GET THE GEAR TO EXTEND. AC LANDED ON RT MLG ON TOUCH DOWN AND COMPLETED ITS LANDING W/THE LT WING HITTING THE RUNWAY. 2 L 7 2 4F 4 F RT A21EA E00063EN 20090203 EA 2009 2 3 CA081217003 1 20081216 G 2120 601R95655 DUCT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE CABIN AIR FAILED W B EMER. DESCENT J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE THE PILOT NOTICED THE AIRCRAFT CABIN ALTITUDE WAS CLIMBING SO HE INITIATED AN EMERGENCY DESCENT. HE THEN HEARD A LOUD POP/BANG THAT SOUNDED LIKE IT CAME FROM THE AFT OF THE AIRCRAFT. NOT TO LONG AFTER THAT ALL THE OXYG EN MASKS DEPLOYED IN THE CABIN. THE AIRCRAFT ALSO HAD A MEL FOR THE RIGHT PACK PRIOR TO THE FLIGHT THE CAPITAN DID NOT DECLARE AN EMERGENCY AND THE PLANE LANDED WITHOUT INCIDENT. MX FOUND A SUPPLY DUCT COMING FROM THE LEFT PACK GOING BEH IND THE APU INTO THE AFT PRESSURE BULKHEAD BLOWN. THEY ARE ORDERING PARTS AND WILL REPAIR ACCORDINGLY 17- O2 GENERATORS WERE ACTIVATED. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 EA 2009 2 3 CA081217004 1 20081213 G 3260 PROXIMITY SENSOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE MLG OUT OF ADJUST W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 19856 (CAN) ON TAKEOFF WHEN THE LANDING GEAR WAS SELECTED UP, THE EICAS DISPLAYED "GEAR DISAGREE" MSG FOLLOWED BY "NOSE GEAR D OOR" MSG. THE QRH WAS FOLLOWED AND THE GEAR WAS LOWERED AND THE MESSAGE CLEARED. THE AIRCRAFT RETURNED AND PERFORMED A LOW PASS SO THE TOWER COULD VERIFY ALL GEAR DOWN. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. THE AIRCRAFT WAS THE N FERRIED WITH GEAR DOWN AND PINNED. MAINTENANCE READJUSTED THE PROX SENSOR TARGET FOR PROX SENSOR PS14GA (NOSE GEAR EX TEND/CENTER PROX SENSOR) AND THE SYSTEM CHECKED NORMAL. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 NE 2009 2 3 CA081217005 2 20081210 G 7261 SCREEN CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE RT ENG OIL CONTAMINATED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) FLT CREW REPORTED R ENGINE OIL PRESS (W) MSG AT CRUISE. WARNING PERSISTED AT POWER SETTINGS ABOVE IDLE. COMPLIED WITH QRH AND DIVERTED TO PHL. ENGINE REMAINED AT IDLE DURING THE 40 MIN FLIGHT TO PHL. LOWEST OIL PRESSURE SHOWN WAS 24 PSI. AIRCRAFT LANDED IN PHL WITHOUT FURTHER INCIDENT. MAINTENANCE REMOVED RT LUBE/SCAVENGE PUMP AND FOUND SCREENS C OKED UP CAUSING RESTRICTION. CLEANED SCREENS IN ACCORDANCE WITH EO 8/016/479 AND REINSTALLED PUMP IN ACCORDANCE WITH AM M 79-21-01. OPS CHECKS CARRIED OUT AND NO FURTHER DEFECTS NOTED. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 CE 2009 2 3 CA081217006 1 20081215 G 3240 61702935 CONTROL CABLE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE PARKING BREAK FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 516 516 (CAN) THE CRIMP THAT RETAINS THE CABLE SHEATH TO THE CABLE ATTACH POINT FAILED ALLOWING THE SHEATH TO MOVE CAUSING THE P ARK BRAKE TO NOT RELEASE. THIS CABLE IS POST SB 550-32-50. 1 L 7 2 4F 4 F A22CE E1NE 20090203 CE 2009 2 3 CA081217007 1 20081206 G 2750 MS250261 LIMIT SWITCH BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA TE FLAPS FAILED W G A O2 MASK DEPLOYED UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB, JUST BEFORE 10000 FT, CREW NOTICED ODOR OF ELECTRICAL SMOKE IN COCKPIT. AS ACFT LEVELED OFF AT 1000 0 FT, CABIN CREW INFORMED FLT CREW OF AN ODOR OF SMOKE CABIN. DONNED O2 MASKS, NOTIFIED ATC & INFORMED THEM OF SMOKE IN COCKPIT & RECEIVED A CLEARANCE TO PROCEED TO THE NEAREST AIRPORT. WHILE DOING THE BEFORE LANDING CHECKLIST THE FLAPS W OULDN`T EXTEND, A FLAPLESS LANDING COMPLETED WITHOUT FURTHER INCIDENT. POST FLT INSP FOUND FLAP CIRCUIT BREAKER POPPED & FLAPS RETRACTED HARD AGAINST THEIR STOPS. IT IS SUSPECTED THE UP LIMIT SWITCH FAILED ALLOWING SYSTEM TO THINK THAT T HE FLAPS WERE NOT ALL THE WAY UP. MOTOR OVERHEATED BEFORE TRIPPING THE CIRCUIT BREAKER, CAUSING THE ELECTRICAL SMOKE O 1 L 7 2 3T 4 T A14CE E4EA 20090203 SW 2009 2 3 CA081217008 1 20081201 G 5302 206020113215A TAIL BOOM BELL 407 407 1182206 SW DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORE ASSEMBLY 206-020-113-215A BONDED IN VERTICAL FINS ASSEMBLIES 206-020-113-233 FOUND WITH VOIDS IN THE ADHESIVE AT THE LOWER PORTION OF THE FIN NEAR THE TAILROTOR SKID ATTACHMENT POINT. 1 G 7 1 3U O H2SW 20090203 NM 2009 2 3 CA081217011 1 20081215 G 5610 NP15790113 WINDSHIELD DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 16661 (CAN) DURING CLIMB LT WINDSHIELD CRACKED. AIRCRAFT RETURNED TO DESTINATION AIRPORT. UNEVENTFUL LANDING. MAINTENANCE R EPLACED THE DAMAGED WINDSHIELD AND THE AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090203 EU 2009 2 3 CA081217012 1 20081217 G 3213 4321012188 BEARING PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL MLG STRUT WORN W K NONE O OTHER IN INSP/MAINT 1 CA 6340 (CAN) RIGHT MAIN LANDING GEAR SHOCK ABSORBER STRUT LOWER BEARING WORN AND LOOSE INTERNALLY. REPLACED WITH NEW. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 20090203 EU 2009 2 3 CA081217013 1 20081208 G 7930 OIL SYSTEM AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE ENGINE LOW PRESSURE W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF, THE PILOT NOTICED A LOW OIL PRESSURE INDICATION. THE ENGINE WAS SHUTDOWN AND THE FLIGHT RE TURNED TO ORIGIN FOR AN UNEVENTFUL SINGLE ENGINE LANDING. GROUND INSPECTION REVEALED A POSSIBLE FRACTURED TOWERSHAFT. WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT E20NE 20090203 NE 2009 2 3 CA081217014 2 20081208 G 7200 ENGINE FOKKER F27 F27MK500 4990629 EU PWA PWA120 PW125B NE MAKING METAL W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING T/O CLIMB, THE ENGINE OUT LIGHT CAME ON AND THE CREW ELECTED TO SHUT THE ENGINE DOWN AND RETURN TO THE POIN T OF DEPARTURE FOR AN UNEVENTFUL SINGLE LANDING. GROUND INSPECTION SHOWED OIL FILTER BYPASS INDICATORS ACTIVATED AND ME TAL WAS FOUND ON THE CHIP DETECTORS. A RECOMMENDATION TO REMOVE THE ENGINE HAS BEEN MADE. 2 H 7 2 4T 4 T A817 E20NE 20090203 SW 2009 2 3 CA081217015 1 20081210 G 6320 HOUSING BELL 412 412EP 1182205 SW PWA PT6T PT6T3 52045 EA M/R GEARBOX CRACKED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, OIL PRESSURE WAS LOST ON THE COMBINING GEARBOX AND THE PILOT PERFORMED AN UNSCHEDULED LANDING OFF B ASE. THE HELO HAD TO BE TRANSPORTED BACK ON A TRUCK. INSPECTION OF THE ENGINE REVEALED A CRACK IN THE GEARBOX HOUSING FROM WHICH THE OIL ESCAPED. THE GEARBOX WILL BE REMOVED AND FORWARDED TO P&WC FOR INVESTIGATION. UPDATES WILL BE PROVI DED IN DUE COURSE. 1 G 7 2 4U 4 U H4SW E22EA 20090203 SW 2009 2 3 CA081217016 1 20081212 G 2435 M2040AC2 BEARING BFGOODRICH SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP STARTER GEN FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 822 (CAN) STARTER GENERATOR FAILED IN FLIGHT CAUSING THE RT GEN FAIL LIGHT TO ILLUMINATE. UPON LANDING AND INSPECTION BY MA INTENANCE THE GENERATOR WAS FOUND TO HAVE DAMAGE RELATED TO COMPONENT FAILURE. THE GENERATOR WAS REPLACED AND SENT TO P ERIMETER`S OVERHAUL FACILITY. THE TEARDOWN REPORT INDICATES FAILURE OF BOTH GENERATOR BEARINGS (PN M2040AC-2). GENERAT OR WAS LAST INSPECTED AT 487.6 HOURS IN ACCORDANCE WITH THE MANUFACTURERS CMM SINCE LAST OVERHAUL AND PASSED THE INSPECT ION AND WAS RETURNED TO SERVICE. AT 822.4 THE BEARINGS FAILED CAUSING THE GENERATOR SYSTEM FAILURE. BOTH THE STATOR AN D ARMATURE ASSY WERE DAMAGED BEYOND REPAIR. NO DEFINITIVE CAUSE CAN BE DETERMINED. 2 L 7 2 4T 4 T RT A8SW E4WE 20090203 GL 2009 2 3 CA081218001 1 20081208 G 5512 SKIN DIAMON DA20 DA20A1 2990000 GL ROTAX 912 ROTAX912F3 EU HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5400 (CAN) DURING ROUTINE MAINTENANCE, A 1 1/2 INCH LONG CRACK WAS NOTICED IN THE LEADING EDGE OF THE HORIZONTAL STABILIZER. TAP TESTING INDICATED POSSIBLE DELAMINATION, SO THE STABILIZER WAS REMOVED FROM AIRCRAFT AND SENT TO COMPOSITE REPAIR S HOP (XU AVIATION) FOR FURTHER EVALUATION AND REPAIR. 1 L 7 1 3O 3 O NT TA4CH E00051EN 20090203 2009 2 3 CA081218003 4 20081216 G 3160 8221917202 DISPLAY CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B 30069 NE COCKPIT MALFUNCTIONED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) IN CRUISE FL 380, 3.5 HOURS IN FLIGHT, THE MFD NR 2 LOWER WINDOW STARTED TO CYCLE BETWEEN THE DIFFERENT FORMATS (P POS, PLAN, TCAS ECT) AT FEW SECONDS INTERVAL WITH UNDEFINED SYMBOLS/TEXT LINE (HIEROGLYPH). AT THAT TIME THE PFDS 1 AND 2, MFD 1 SHOWED NORMAL INFORMATION. THEN, THE COMS AND NAVS ACTUAL AND PRE SELECTED FREQUENCIES, WOULD HAVE DIGITS CHA NGING ON THEIR OWN, SOMETIMES THE FREQUENCIES WOULD BE GREEN OR AMBER ON BOTH CDUS TUNING PAGE AND MFDS RADIO MENUS. TH E NAVS TUNING MODE WOULD BE CHANGING BY THEMSELVES BETWEEN AUTO/MAN. SUBSEQUENTLY, THE COMMUNICATION WITH BOTH VHF COMS WAS NO LONGER POSSIBLE WITH AIR TRAFFIC CONTROL. ONBOARD SATELLITE AIRPHONE WAS USE. THE FLIGHT WAS REDIRECTED TO A C 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 SO 2009 2 3 CA081218004 1 20081201 G 3245 TUBE PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA TIRE FAILED W O OTHER E VIBRATION/BUFFET LD LANDING 1 CA 391 (CAN) WHEN THE AIRCRAFT LANDED IT WAS DISCOVERED THAT THE NOSEWHEEL WAS FLAT. INSPECTION DID NOT REVEAL A DIRECT CAUSE FOR THE TUBE TO FAIL. THERE WERE SEVERAL SEVERE WEATHER CHECK CRACKS IN THE TUBE WHEN THE TIRE WAS DISASSEMBLED. THE C OMPANY IS INSTALLING A PROCEDURE FOR INSPECTING NEW TUBES BEFORE INSTALL AS WELL AS PROPER WHEEL BUILD UP PROCEDURES. T HE COMPANY IS ALSO IMPLEMENTING A 12 MONTH INSPECTION AND REPLACEMENT SCHEDULE FOR THE NOSEWHEELS ON THE NAVAJO AIRCRAFT . 1 L 7 2 3O 3 O A20SO E14EA 20090203 EA 2009 2 3 CA081218005 1 20081217 G 2752 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) FLAP FAIL ON APPROACH. WHEN FLAPS SELECTED THE FLAPS DID NOT MOVE FROM ZERO DEGREES. FLAPLESS APPROACH AND LANDI NG CARRIED OUT WITHOUT FURTHER INCIDENT. ACFT FERRIED FOR FLAP REPAIR. ALL FLAP ACTUATORS REPLACED, RT NR 1 FLAP DRIVE ASSY REPLACED DUE TO DAMAGED CORE, RT NR 2 AND NR 3 DRIVE CABLES FOUND WITH MOISTURE CONTAMINATION-CORE AND CASINGS CLE ANED AND RELUBED. LT NR 1 FLAP DRIVE FOUND WITH MOISTURE CONTAMINATION-CLEANED AND RELUBED. LT NR 5 FLAP DRIVE DEFORME D BEYOND LIMITS. REPLACED FLAP POWER DRIVE UNIT. ACFT TEST FLOWN SUCCESSFULLY AND RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 SW 2009 2 3 CA081218006 1 20081217 G 7931 8974072 BYPASS VALVE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP OIL FILTER LEAKING W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) THE CREW REPORTED THAT ONE TIRE HAD BLOWN DUE TO FROZEN BRAKES. AN AME WAS SENT TO CHANGE THE WHEEL AND FLY BACK TO THE BASE WITH THE AIRCRAFT. UPON RETURN TO BASE, A LARGE OIL LEAK WAS NOTED COMING FROM THE NR 2 ENGINE. IT WAS EVE NTUALLY DETERMINED BY MAINTENANCE STAFF TO BE THE OIL FILTER BYPASS PIN. THE PIN POPS OUT IF THE OIL SYSTEM BECOMES CON TAMINATED. THE PIN WAS NOT EXTENDED, HOWEVER, IT WAS LEAKING OIL. THE OIL LEAK WAS INITIALLY THOUGHT TO BE AN STARTER GENERATOR OIL SEAL, DUE TO THE VOLUME OF OIL LEAKED THROUGHOUT THE ENGINE COMPARTMENT. A SECOND GROUND RUN DISCOVERED T HE LEAK FROM THE BYPASS PIN AREA. PRELIMINARY REPORT, THE DEFECT IS BEING REPAIRED NOW. UNKNOWN TSO ON THE PART, HOWEV 2 L 7 2 4T 4 T RT A8SW E4WE 20090203 2009 2 3 CA081222007 4 20081219 G 2350 164ZS01Y AUDIO PANEL AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE7312 01518 WP COCKPIT MALFUNCTIONED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 6069 6069 (CAN) DURING THE BASIC INSPECTION WITH AIRCRAFT POWER ON, FUMES AND LIGHT SMOKE WHERE NOTICED IN THE COCKPIT. AFTER INS PECTION THE AUDIO WARNING PANEL BOX WAS FOUND TO BE THE CAUSE. THE AUDIO WARNING PANEL BOX WAS REPLACED WITH A REPAIRED SERVICEABLE UNIT FROM DASSAULT AND TESTED SERVICEABLE P/N 164ZS01Y S/N 202. REMOVED AND S/N 175, INSTALLED. 2 L 7 2 4F 4 F A33EU E6WE 20090203 SW 2009 2 3 CA081222008 1 20081208 G 6730 222382001101 SERVO BELL 222 222U 1182140 SW LYC LTS101 LTS101750C1 41560 NE UNKNOWN W O OTHER F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) SOLID RESISTANCE FELT WITH AFT CYCLIC MOVEMENT DURING OPERATIONS WITH FORCE TRIM ON & UTILIZING CYCLIC TRIM RELEAS E SWITCH. ON FIRST OCCURRENCE RESISTANCE RELEASED WITH A FIRM BUMP & FAULTY LT CYCLIC TRIM RELEASE SWITCH SUSPECTED HOW EVER WITH SECOND OCCURRENCE SWITCHING FORCE TRIM OFF HAD NO EFFECT & RESISTANCE ONCE AGAIN RELEASED WITH A FIRM BUMP AFT ER SEVERAL SECONDS. ALL THE MAIN ROTOR CONTROLS WERE INSPECTED FOR FREEDOM OF MOVEMENT & TRAVEL, NO DEFECTS NOTED. A G PU FOR HYD SYSTEM ATTACHED & SYSTEM 1 & 2 CHECKED. NO DEFECTS. WHEN CYCLIC MOVED FOR & AFT WHEN POWERED BY ONLY 1 HYD SYSTEM NOTICED THAT CYCLIC STICK SEEMED TO BE MOTORED (DRIVEN) FOR & AFT BY SERVO ACTUATOR. SERVO HAD 23.8 HOURS SINCE 1 G 7 2 3U 3 U H9SW E5NE 20090203 NM 2009 2 3 CA081222009 1 20081218 G 2421 31708001A GENERATOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NR 1 AC MALFUNCTIONED W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CL CLIMB 1 CA 26071 1768 (CAN) SHORTLY AFTER TAKE OFF, THE FLIGHT CREW RECEIVED "NR 1 AC GEN" AND "NR 2 AC GEN" CAUTION LIGHTS. SYSTEMS WERE RES ET AND NR 2 AC GENERATOR RETURNED ON LINE. DECISION WAS MADE TO RETURN AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT . THE NR 1 AC GENERATOR WAS REPLACED AND THE PHASE A AND C WIRES LOCATED UNDER THE RT FLAP BETWEEN THE NACELLE AND THE FUSELAGE WERE REPAIRED. BOTH WIRES WERE SHORTED DUE TO CHAFING. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090203 CE 2009 2 3 CA081222010 1 20081221 G 5610 10138402523 WINDSHIELD BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 4500 (CAN) WINDSHIELD CRACKED AFTER TAKEOFF, CRACKS EMANATED VERTICALLY FROM THE BOTTOM INBOARD EDGE. UNIT TTSN 4500 HOURS. 2 L 7 2 4T 4 T A24CE E4EA 20090203 NE 2009 2 3 CA081223001 2 20081219 G 7230 311194301 BEARING PWA 118 PW118 NE NR 3 FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) NR 3 BEARING FAILURE FOUND AT DISASSEMBLY. 4 T E20NE 20090203 NE 2009 2 3 CA081223002 2 20081217 G 7200 MS945226 BEARING PWA PW120 PW123 NE ENGINE SEIZED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) ENGINE BEARING SEIZED. 4 T E20NE 20090203 2009 2 3 CA081223004 4 20081221 G 3460 4082499902 COMPUTER BOEING 737 737800* NM FLIGHT CONTROL MALFUNCTIONED W L ABORTED APPROACH F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) CREW REPORT STABILIZER LIGHT CAME ON. ATC INFORMED AND CREW BROKE OFF APPROACH AND DETERMINED THAT THERE WAS NO S TABILIZER TRIM. AIRCRAFT RETURNED TO AIRPORT AND CONDUCTED A SAFE LANDING. MAINTENANCE TROUBLESHOT REPORTED SNAG AND F OUND FAULT APPEARED TO LIE WITH THE FLIGHT CONTROL COMPUTER. UNIT REPLACED AND SYSTEM CHECKED SERVICEABLE. AIRCRAFT RE TURNED TO SERVICE. 2 L 7 2 4F RT A16WE 20090203 EA 2009 2 3 CA081223005 1 20081208 G 5531 215221182 RIB CNDAIR CL215 CL2156B11215 EA PWA PW120 PW123 NE VERTICAL STAB CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) CRACK 35 MM LONG ON RIB OF VERTICAL STAB AT WL 396. 2 H 7 2 4T 4 T RT A14EA E20NE 20090203 GL 2009 2 3 CA081223007 1 20081123 G 7921 AE7010101H0114 HOSE DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO OIL COOLER LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 577 (CAN) AIRCRAFT WAS ON A REGULAR TRAINING FLIGHT WHEN THE CREW NOTICED THAT THE OIL PRESSURE INDICATION HAD FALLEN OUT OF THE GREEN ARC AND REMAINED LOW UNTIL THE AIRCRAFT WAS ABLE TO RETURN TO BASE. ONCE THE AIRCRAFT HAD RETURNED AND WAS I NSPECTED MY MAINTENANCE, IT WAS DETERMINED THAT THERE WAS A SIGNIFICANT OIL LEAK. FURTHER INVESTIGATION REVEALED THAT T HE OIL COOLER HOSE HAD A PUNCTURE AND THAT WAS THE LIKELY CAUSE OF THE FAILURE. THE ENGINE WAS REMOVED AND SENT OUT FOR BULK INSPECTION. A REPLACEMENT ENGINE WAS INSTALLED ALONG WITH NEW OIL COOLER HOSES. THE FAULTY HOSE WAS INSPECTED, T ESTED AND RETURNED TO THE MANUFACTURER FOR ANALYSIS. 1 L 7 1 3O 3 O NT TA4CH E7SO 20090203 NE 2009 2 3 CA081223008 2 20081223 G 7414 22021081806 BEARING ROBSIN R44 R44RAVENII 7640122 WP LYC O540 IO540AE1A5 41530 NE MAGNETO LACK OF LUBE W K NONE O OTHER IN INSP/MAINT 1 CA 474 (CAN) MAG RECEIVED FOR 500 HR INSPECTION, ROTATING MAGNET SHAFT SPUN BEFORE DISASSEMBLY TO INSPECT BEARING CONDITION & P RELOAD. NO END PLAY OR ROUGHNESS FELT, WHEN MAG WAS DISASSEMBLED, DISCOVERED THAT AT O/H IN SEPT 2007. NO GREASE HAD B EEN PACKED INTO BEARINGS. BEARINGS WERE LUBRICATED BY OIL THAT EACH BEARING IS PACKAGED WITH WHEN NEW. ONLY OTHER SOUR CE OF LUBRICATION WAS A SMALL AMOUNT OF OIL THAT HAD LEAKED INTO MAG PAST OIL SEAL. LACK OF LUBRICATION COULD CAUSE MAG NETO & ENGINE FAILURE, EVEN THOUGH BEARINGS DID NOT APPEAR DAMAGED THEY WERE REPLACED, MAG WAS RETURNED TO SERVICE. 1 G 7 1 3O 3 O H11NM 1E4 20090203 EA 2009 2 3 CA081229001 1 20081225 G 5610 04093H1031 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 10575 10575 (CAN) DURING CLIMB, THE RT WINDSHIELD CRACKED LIMITING THE FIRST OFFICER VIEW. AN EMERGENCY WAS DECLARED, THE AIRCRAFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. AT THIS TIME, NO IMPACT WERE REPORTED BY THE FLIGHT CREW. VISUAL INSPECT ION OF THE WINDSHIELD INDICATES THAT THE EXTERNAL AND INTERNAL LAYERS ARE CRACKED. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 GL 2009 2 3 CA081229003 2 20081224 G 7323 23070101 GOVERNOR BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ENGINE FAILED W B A EMER. DESCENT UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CL CLIMB 1 CA 1419 (CAN) PILOT ENCOUNTERED HIGH SIDE GOVERNOR FAILURE. TORQUE INCREASED FROM 85 TO 100 PERCENT DURING CLIMB WITH NO COLLEC TIVE INPUT. NR/N2 INCREASED TO 110 PERCENT AND THROTTLE WAS ROLLED TO IDLE WITH NO INITIAL EFFECT. NR/N2 THEN DROPPED TO 90 PERCENT. A DESCENT AND SHORT RUN-ON LANDING WAS MADE USING MANUAL THROTTLE MOVEMENTS. NO DAMAGE OCCURRED. REPLA CEMENT OF GOVERNOR CURED PROBLEM AFTER TROUBLESHOOTING IN ACCORDANCE WITH ROLLS ROYCE 250 C30P MM. REMOVED GOVERNOR WIL L BE SENT TO REPAIR STATION FOR INSPECTION. 1 G 7 1 3U 3 U H2SW E1GL 20090203 EA 2009 2 3 CA081229004 1 20081226 G 5210 601R317047 HANDLE CNDAIR CL600 CL600* 1900302 EA GE CF34 CF348C5 30050 NE PAX DOOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 10811 10811 (CAN) WHEN GROUND CREW ATTEMPTED TO OPEN AIRCRAFT FOR MORNING DEPARTURE, OUTER DOOR HANDLE SNAPPED OFF IN HIS HAND. MAI NTENANCE INSPECTED AND REPLACED MAIN CABIN DOOR HANDLE ASSEMBLY AND FUNCTION CHECKED AS PER MANUFACTURERS MAINTENANCE MA NUAL. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E00063EN 20090203 NE 2009 2 3 CA081231001 2 20081229 G 7200 ENGINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NR 1 OVERTORQUED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB THE CREW OBSERVED AN OVERTORQUE ON THE NR 1 ENGINE, THE POWER LEVER WAS REDUCED AND THE ENGINE STABIL IZED AROUND 93 PERCENT OF TORQUE BEFORE RAISING AGAIN. DECISION WAS MADE TO PERFORM AN INFLIGHT SHUTDOWN. THE CREW DE CLARED AN EMERGENCY, RETURNED TO THE AIRPORT AND LANDED WITHOUT FURTHER INCIDENT. IT IS UNKNOWN AT THIS TIME WHAT HAS C AUSED THE ENGINE OVERTORQUE. THE ENGINE IS BEING REPLACED AND WILL BE SHIPPED TO AN OVERHAUL FACILITY. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090203 NE 2009 2 3 CA081231002 2 20081231 G 7414 GE5298 DRIVE GEAR BOSCH PWA R985 R985AN14B 52008 NE MAGNETO WORN W D RETURN TO BLOCK R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 778 (CAN) ON INSPECTION MAGNETO WAS FOUND TO HAVE ERATIC TIMING ON DRIVE GEAR PART NUMBER GE5298, LOOSE ON SHAFT AND EXCESSI VE WEAR ON KY11-14 - KEY WOODRUFF FOR DRIVE GEAR. 3 R 5E1 20090203 CE 2009 2 3 CA081231003 1 20081221 G 5610 10138402524 WINDSHIELD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) WINDSHIELD CRACKED AS AIRCRAFT CLIMBED OUT OF YYC. AIRCRAFT RETURNED TO YYC. MAINTENANCE REPLACED WINDSHIELD AND RETURNED AIRCRAFT TO SERVICE. 1 L 7 2 4T 4 T A24CE E4EA 20090203 CE 2009 2 3 CA081231004 1 20081221 G 5610 10138402523 WINDSHIELD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA COCKPIT CRACKED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) AFTER START PILOT NOTED THAT THE WINDSHEILD WAS CRACKED. ENGINES WERE SHUT DOWN AND MAINTENANCE REPLACED THE WIND SHEILD AND RETURNED THE AIRCRAFT TO SERVICE. 1 L 7 2 4T 4 T A24CE E4EA 20090203 EA 2009 2 3 CA090102002 1 20081224 G 2750 FLAP SYSTEM CNDAIR CL604 CL604 1900301 EA GE CF34 CF343B 30069 NE TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) ON APPROACH THE FLAP FAILED TO EXTEND AND THE AIRCRAFT DIVERTED WHERE THEY LANDED WITH THE FLAPS UP. UPON INSPECT ION FOUND THE FLAPS WOULD NOT MOVE AND WERE IN ASYMMETRIC CONDITION. BOTH THE LT AND RT BDU WERE REPLACED AND THE FLAP SYSTEM TESTED SERVICEABLE. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 CE 2009 2 3 CA090102004 1 20081231 G 5310 97430000149 DOOR FRAME BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE BS 201 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6727 (CAN) WHILE CARRYING OUT SPECIAL INSPECTION, INSPECT ESCAPE HATCHES AND ASSOCIATED CLOSURE AREA. FOUND THE RT AFT EMERG ENCY EXIT CROSS TIE CRACKED THROUGH AT FS 201.775, AFT RT ESCAPE HATCH FRAME. THERE WERE TWO RIVETS SHEARED OFF IN THE SAME AREA AND THE .125 INCH THICK PIECE HAD BUCKLED. NO ADDITIONAL DAMAGE WAS NOTED IN THE FUSELAGE. THIS WAS THE FIRS T 1000 LANDING REPETITIVE INSPECTION AFTER THE INITIAL 5000 LANDING INSPECTION. PART WILL BE REPLACED WITH FACTORY NEW PART. 2 L 7 2 4T 4 T A24CE E4EA 20090203 CE 2009 2 3 CA090105001 1 20081208 G 3210 STRUCTURE CESSNA 172 172M 2072418 CE LYC O360 O360A4M 41514 EA MLG WORN W O OTHER O OTHER NR NOT REPORTED 1 CA 15 (CAN) WORN ATTACH HOLE, CAUSING FORE AND AFT MOVEMENT OF THE WHEEL. 1 H 7 1 3O 3 O NT 3A12 E286 20090203 CE 2009 2 3 CA090105002 1 20081224 G 5610 50420066103 WINDOW BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A34 52043 EA HARTZL HCB4T HCB4TN3 GL COCKPIT FAILED W B G EMER. DESCENT O2 MASK DEPLOYED O OTHER CR CRUISE 1 CA 15865 (CAN) AT 16000 FT LEVEL CRUISE, WINDOW FAILURE OCCURRED, COMPLETE WINDOW FAILED LEAVING ONLY APPROX 2 INCHES OF WINDOW A TTACHED TO AIRFRAME WINDOW SEAL STAYED ATTACHED TO AIRFRAME. CRAZING, PITS AND SCRATCHES REMOVED FROM WINDOW FEB 10, 2 000, WINDOW MEASURED AFTER REPAIR. .304-.321, COMPLETED BY AVGLASS USA. 1 L 7 2 3T 4 T A14CE E4EA 6 C P40EA 20090203 EA 2009 2 3 CA090105006 1 20081231 G 2750 865D1007 DRIVE UNIT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA 14963 14963 (CAN) THIS AIRCRAFT WAS UNDER A FERRY PERMIT TO YYC FOR A BROKEN OUTER DOOR HANDLE. THE FLAPS WHERE AT 8 DEGREES BEFORE DEPARTURE. AFTER TAKEOFF THE FLAP FAIL MESSAGE WAS POSTED WITH FLAPS STILL AT 8 DEGREES. THE PILOT RETURNED TO YZF DU E TO INSUFFICIENT FUEL TO REACH YYC WITH FLAPS AT 8 DEGREES. THE AIRCRAFT IS GOING TO FERRY TO YYC WITH FLAPS SET AT 8 DEGREES. FLAP POWER DRIVE UNIT REPLACED AND FLAP SYSTEM CHECKED SERVICEABLE. A/C RETURNED TO SERVICE (RESOLVED ON W/O: 174456 TASKCARD: NR-00002) DEFECT NR 819812. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 NM 2009 2 3 CA090105007 1 20081220 G 6120 699018002 PCU BOMBDR DHC8 DHC8400 NM PWC 150 PW150A EA NO 1 ENGINE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) POWERPLANT INDICATION ON ED NR 1 TRU AND AC GEN ZERO INDICATION WHILE TAXIING. ACTION TAKEN AT MNL, RETRIEVE FAUL T CODE 388 AND 1504 AND CLEARED POWERPLANT MESSAGE. PEC REPLACED. PERFORMED FAULT CODE ISOLATION AND OPERATIONAL CHECK OF RADIO ALTIMETER AND FAULT ISOLATION ON POWERPLANT ELECTRONIC UNIT (PEC). PERFORMED ENGINE RUN-UP FOUND SATISFACTORY IN ACCORDANCE WITH Q400 TASK 77-31-00-810-805, 61-20-07-810-815, 32-61-00-710-801. 2 H 7 2 4T 4 T RT A13NM E00062EN 20090203 CE 2009 2 3 CA090105008 1 20081224 G 5540 ATTACH BRACKET CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL RUDDER WEIGHT BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 10742 (CAN) RUDDER BALANCE WEIGHT EXCEEDED MAY ALLOWABLE WEIGHT OF 4.38 LBS PLUS .25 LBS BY 1.5 LBS WEIGHT WAS ADDED TO BALANC E WEIGHT FOLLOWING PAINTING OF RUDDER. EXCESSIVE WEIGHT CAUSED ATTACH POINTS TO FAIL ALLOWING THE BALANCE WEIGHT TO BE ABLE TO SHIFT IN SUCH A MANNER THAT COULD CAUSE FLIGHT CONTROL BLOCKAGE. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 20090203 EA 2009 2 3 CA090105009 1 20081229 G 2752 852D10019 ACTUATOR CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30068 NE TE FLAPS MALFUNCTIONED W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA (CAN) FIRST FLIGHT OF THE DAY. PILOTS WERE TAXIING AND SELECTED FLAPS TO 20 DEGREES AND THE FLAPS STAYED AT 0. OAT -33 DEGREES C. ACFT FERRIED FOR REPAIR. ALL FLAP ACTUATORS REPLACED WITH POST SB ACTUATORS, FLAP DRIVE LUBE TASK COMPLETE D, RIGGING AND FUNCTION CHECKS COMPLETED, AND A/C SUCCESSFULLY TEST FLOWN AND RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 EA 2009 2 3 CA090105012 2 20081210 G 7200 ENGINE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA COKED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING FLIGHT, THE CREW OBSERVED A RAPID RISE IN ENGINE TEMPERATURE AND TORQUE WITH FLAMES COMING OUT THE RIGHT EN GINE EXHAUST STACKS. THE ENGINE THEN FLAMED OUT, THE FLIGHT WAS DIVERTED WHERE A SINGLE ENGINE LANDING WAS ACCOMPLISHED . DISASSEMBLY OF THE ENGINE BY THE OPERATOR REVEALED A LARGE PIECE OF CARBON COMPLETELY BLOCKING ONE OF THE CT GUIDE VA NE, CT BLADES HEAVILY ERODED AND HEAVY CARBON DEPOSITS ON THE COMBUSTION LINER. WILL CONTINUE INVESTIGATING THE EVENT A ND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1 L 7 2 3T 4 T A14CE E4EA 20090204 2009 2 4 CA090105014 1 20081217 G 6123 AUTOFEATHER SYS PWA PW120 PW124B NE MALFUNCTIONED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB THE ENGINE TORQUE DROPPED TO 22 PERCENT AND THEN ZERO. THE ENGINE WAS SECURED AND THE A/C RETURNED T O THE POINT OF DEPARTURE, WHERE A SINGLE ENGINE LANDING WAS PERFORMED. POST FLIGHT TROUBLESHOOTING LED TO THE REPLACEME NT OF THE AUTO FEATHER UNIT BEFORE THE ACFT WAS RETURNED TO SERVICE. WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE O F ROOT CAUSE ONCE ESTABLISHED. 4 T E2ONE 20090204 WP 2009 2 4 CA090106002 1 20081223 G 3260 DOWNLOCK SWITCH CVAC 340 340CVAC 242270A WP ALLSN 501D 501D13D 03004 GL MLG OUT OF ADJUST W L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 CA (CAN) ON APPROACH, CREW EXPERIENCED A LT GEAR UNSAFE LIGHT. AFTER DETERMINING THE GEAR TO BE DOWN, ACFT LANDED UNEVENTF ULLY. MAINTENANCE ADJUSTED THE DOWN LOCK SWITCH AND ACFT WAS RETURNED TO SERVICE 2 L 7 2 4R 4 T 6A6 E282 20090206 SO 2009 2 6 CA090107004 1 20081223 G 5712 4042306 RIB PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA LT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING MX, RIB P/N 40423-06, WHICH RUNS THROUGH THE LT WW, WAS FOUND CRACKED THROUGH AT THE NARROWEST PART OF THE RIB AT THE TOP CENTER OF THE WW. THE WING SKIN IMMEDIATELY ABOVE AND ATTACHED TO THE RIB ALSO HAD A SMALL CRACK WHICH CO INCIDED WITH THE RIB CRACK. 1 L 7 2 3O 3 O A20SO E14EA 20090206 EA 2009 2 6 CA090107006 1 20081229 G 5610 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 13762 (CAN) CAPTAINS SIDE WINDOW SHATTERED IN FLIGHT. FOLLOWED QRH, DIVERTED TO NEAREST AIRPORT AND LANDED WITHOUT FURTHER IN CIDENT. R&R CAPTAINS SIDE WINDSHIELD IAW AMM 56-11-01 AND CARRIED OUT LEAK CHECKS. ACFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 20090206 2009 2 6 CA090107008 4 20081226 G 3417 8220372445 ADC CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE NR 1 MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 4396 (CAN) JUST AFTER TAKEOFF, THE CREW RECEIVED RED FLAGS FOR THE CAPTAINS AIRSPEED, ALTIMETER AND VSI MOMENTARILY. INDICAT IONS RETURNED TO NORMAL SHORTLY AFTER. THE FLIGHT RETURNED TO THE DEPARTURE AIRFIELD AND LANDED WITHOUT FURTHER INCIDENT . MX R&R THE NR 1 ADC AND OPS CHECKED SERVICEABLE. ACFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 20090206 EA 2009 2 6 CA090107009 1 20081222 G 2750 FLAP SYSTEM CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) FLT CREW REPORTED FLAP FAIL MSG WHILE ON APPROACH WHEN FLAPS SELECTED OUT OF 0 DEG. QRH FOLLOWED AND LANDED WITH FLAPS AT 0 DEG WITH NORMAL BRAKING. 2 L 7 2 4F 4 F RT A21EA E15NE 20090206 EA 2009 2 6 CA090107011 1 20081219 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 (CAN) EXPERIENCED FLAP FAILURE. REPLACED BPSU. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 EA 2009 2 3 CA090107014 1 20081216 G 3020 5399001 ANTI-ICE VALVE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 12356 (CAN) FLT CREW REPORTED RIGHT COWL ANTI-ICE MESSAGE IN FLIGHT WITH ANTI-ICE SELECTED ON. COMPLETED QRH AND MESSAGE PERS ISTED. DIVERTED AND LANDED WITHOUT FURTHER INCIDENT. REMOVED AND REPLACED RIGHT COWL ANTI-ICE VALVE AND OPS CHECKED SE RVICEABLE. AIRCRAFT RETURNED TO SERVICE. ANTI-ICE VALVE 5399-00-1 0186A FAILED RIGHT COWL 13148/12356 (VALVE TIMES). 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 EA 2009 2 3 CA090107015 1 20081215 G 4930 600970249 LINE CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE APU FUEL SYSTEM CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 19855 (CAN) WHILE SERVICING APU MAINTENANCE NOTICED A FUEL SMELL. OPENED PANEL AND RAN APU. FOUND APU INLET BELLOWS RETAININ G CLIP RIGHT SIDE SLID AFT AND CHAFED HOLE IN METERED FUEL LINE TO NOZZLES. FUEL WAS DRIPPING ON IGNITER BOX. REMOVED AND REPLACED FUEL LINE AND REPOSITIONED RETAINING CLIP AND PLACED SPIRAL WRAP ON FUEL LINE BEHIND CLIP. AIRCRAFT RETURN ED TO SERVICE. FUEL LINE 600-97024-9 N/A CHAFED APU COMPARTMENT 20830/19855. 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 EA 2009 2 3 CA090107016 1 20081022 G 4920 38004883 APU CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 30070 NE SMOKE W O OTHER B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 CA 20144 (CAN) FLT CREW REPORTED SMOKE IN FLIGHT DECK AFTER LANDING. SMOKE DISSIPATED AFTER PACKS SELECTED OFF, APU 3800488-3 P- 601 19506/20144 (APU TIMES). 2 L 7 2 4F 4 F RT A21EA E15NE 20090203 EU 2009 2 3 CA090108002 1 20081229 G 3260 A254210012 UPLOCK AIRBUS 310 A310304 3930339 EU GE CF6 CF680C2* GL NLG FAILED W O OTHER N FALSE WARNING DE DESCENT 1 CA 59564 (CAN) IN DESCENT TO LGW, FLIGHT CREW REPORTED, L/G NOSE WHEEL UNSAFE INDICATION. PERFORMED L/G GRAVITY EXTENT ION. NLG UPLOCK ASSY WAS REPLACED AND OPERATIONAL CHECK WAS CARRIED OUT SERVICEABLE. AS SAFETY PRECAUTION, BOTH NOSE LANDING GE AR DOOR SEQUENCE VALVE WERE REPLACED. 2 L 7 2 4F 4 F RT A35EU E23EA 20090203 SW 2009 2 3 CA090108003 1 20081226 G 5310 DOOR FRAME BBAVIA 7 7AC 2110102 SW FUSELAGE CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA 2508 (CAN) DOOR TUBE RUSTED THROUGH LOWER END, REPLACED. 1 H 7 1 3O A759 20090203 NM 2009 2 3 CA090109002 1 20081214 G 7930 8D1437 PRESSURE SWITCH DHAV DHC8 DHC8301 1386003 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA (CAN) NR 1 ENG OIL PRESS WARNING LIGHT ILLUMINATION IN FLIGHT, ENGINE SHUTDOWN IN ACCORDANCE WITH QRH/AFM, AIRCRAFT RETU RNED TO DEPARTURE AIRPORT AND LANDED SAFELY. MAINTENANCE DETERMINED NR 1 OIL PRESSURE SWITCH FAILED. SWITCH REMOVED AN D REPLACED. ENGINE RUNS CARRIED OUT, OPERATION SATISFACTORY. AIRCRAFT RETURNED TO SERVICE. SWITCH MANUFACTURER (CUSTO M CONTROL SENSORS) NOT IN THE DROP DOWN LIST. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090204 CE 2009 2 4 CA090112004 1 20081214 G 2823 C2915030101 SELECTOR CESSNA 206 U206D 2073342 CE CONT O520 IO520F 17032 SO MCAULY 2A34C D2A34C58 GL FUEL SYSTEM LEAKING W O OTHER O OTHER NR NOT REPORTED 1 CA 10851 10851 (CAN) FUEL SELECTOR CLOSED DUE TO FLEX HOSES IN ENGINE COMPARTMENT BEING REPLACED. AFTER HOSES INSTALLATION FUEL SELECT OR OPEN TO CHECK FOR LEAKS, FUEL LEAK FOUND ON BELLY. FUEL SELECTOR WAS LEAKING ON THE TOP, SOURCE OF LEAK SHAFT ON THE TOP. SELECTOR WAS ORIGINAL INSTALLATION (1969). UNIT REPLACED WITH NEW UNIT FROM CESSNA. NO FURTHER LEAKS. (TC NR 20 090112004) 1 H 7 1 3O 3 O A4CE E5CE 5 C P3EA 20090205 SO 2009 2 5 CA090112008 2 20081031 G 7414 GASKET BENDIX PIPER PA28 PA28R201T 7102813 SO CONT O360 TSIO360FB 17025 SO MAGNETO LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 23 (CAN) ENGINE INSPECTED FOR OIL LEAK AT REAR ACCESSORY SECTION, FOUND OIL COMING FROM RIGHT MAGNETO ATTACH GASKET. MAGNE TO REMOVED, GASKET AND ENGINE MATING SURFACE INSPECTED OK. MOUNTING FLANGE ON MAGNETO INSPECTED AND FOUND CRACKED IN AR EA WHERE BOTH HOLD DOWN CLAMPS MAKE CONTACT, FLANGE WAS ON THE VERGE OF BREAKING OFF COMPLETELY WHICH WOULD RESULT IN MA GNETO FAILURE AND POSSIBLE COMPLETE ENGINE OIL LOSS. LEFT MAGNETO REMOVED FOR INSPECTION, FOUND SATISFACTORY. AIRCRAFT OWNER REPORTED THAT LEFT MAGNETO WAS REPLACED FOR SAME REASON ABOUT 50 HOURS EARLIER. SUSPECT CAUSE OF CRACKING FLANGE S IS FROM OVERTORQUING HOLD DOWN CLAMP NUTS. (TC NR 20090112008) 1 L 7 1 3O 3 O 2A13 E9CE 20090206 CE 2009 2 6 CA090116004 1 20081229 G 7500 MOTOR CESSNA 500 560CESSNA 2076750 CE PWC 545 PW545B NE HBV TORQUE FAILED W E ENGINE SHUTDOWN E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA 654577883 (CAN) THE CREW REPORTED VIBRATION ON RT ENGINE AND THE EEC REVERTED TO MANUAL MODE. THEY OBSERVED A SUDDEN RISE IN ENGIN E TEMPERATURE AND ELECTED TO SHUT IT DOWN BEFORE MAKING A SINGLE ENGINE LANDING. REPLACED THE BLEED-OFF VALVE AND TORQUE MOTOR BEFORE THE ACFT WAS RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A22CE E00059EN 20090206 NE 2009 2 6 CA090116006 2 20081224 G 7250 TURBINE BLADES DHAV DHC8 DHC8301 1386003 NM PWA 120 PW123D 52152 NE ENGINE FRACTURED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB, AT FL68, THE ENGINE LOST POWER. IT WAS SHUT DOWN AND SECURED AND THE ACFT RETURNED TO THE POINT OF DEPARTURE WHERE A SINGLE ENGINE LANDING WAS ACCOMPLISHED. GROUND INSPECTION FOUND THAT THE PROPELLER WOULD NOT ROTATE A ND POWER TURBINE BLADES WERE FRACTURED. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLI SHED. 2 H 7 2 4T 4 T RT A13NM E20NE 20090206 NE 2009 2 6 CA090116007 2 20081222 G 7200 ENGINE AEROSP ATR72 ATR72 EU PWA PW120 PW127 NE POWER LOSS W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, THE ENGINE TORQUE AND TEMPERATURE INCREASED UNCOMMANDED. CREW REDUCED POWER BUT THE ENGINE DID NOT RESPOND AND WAS SHUT DOWN AND SECURED. A SINGLE ENGINE LANDING WAS ACCOMPLISHED AT THE POINT OF ORIGIN. THE ENGINE WI LL BE REMOVED AND INVESTIGATED. 2 H 7 2 4T 4 T RT E20NE 20090206 NE 2009 2 6 CA090116008 2 20081229 G 7200 ENGINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MAKING METAL W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB, THE CREW NOTED A RAPID INCREASE IN FUEL FLOW, FOLLOWED BY A RAPID RISE IN TEMPERATURE AND TORQUE ON THE LT ENGINE. THE ENGINE DID NOT RESPOND TO POWER LEVER MOVEMENTS AND AN UNCOMMANDED IFSD OCCURRED. A SINGLE ENGINE LA NDING WAS MADE AT THE POINT OF DEPARTURE. GROUND INSPECTION FOUND METAL PARTICLES IN THE OIL TANK. THE ENGINE WILL BE R EMOVED. WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 20090206 GL 2009 2 6 CA090119011 1 20081228 G 2421 A3579101 GENERATOR BOMBDR BD100 BD1001A10 1390044 GL HNYWL AS907 AS90711A 33908 WP FAULTED W O OTHER H ELECT. POWER LOSS-50 PC LD LANDING 1 CA (CAN) ACFT ARRIVED WITH RT GEN FAULT. RT COWL OPEN, FOUND GEN DAMAGED AND DISLODGED OUT FROM IT`S EXHAUST HOUSING. SHAFT DIDN`T SHEARED. THE BACK MATING PLATE AT THE GEARBOX ASSY SLIGHTLY CHAFED DUE TO IN CONTACT WITH GEN SHAFT. LMM AS907-1 -1A CHAP 72-61-01, FIG 801,PG 802, ITEM 170) 2 L 7 2 4F 4 F RT T00005NY E00010LA 2008032500060 20080325 00060 NM 2008 3 25 CO1Y200800001 1 20080307 G 5340 ARB71701 SUPPORT FITTING DOUG MD11 MD11F 3023600 NM MLG DOOR CORRODED B CO1Y K NONE O OTHER IN INSP/MAINT 1 EA 33 725BC 48503 AT LT MLG AND DOORS, FOUND BOLTS LOWER AND UPPER WITH PLI LOOSE ON LT FRAME SUPPORT. 2 L 7 3 4F RT A22WE 2008041400015 20080414 00015 NM 2008 4 14 CO1Y200800002 1 20080327 G 5510 STRUCTURE DOUG MD11 MD11F 3023600 NM ZONE 400 CORRODED B CO1Y K NONE O OTHER IN INSP/MAINT 1 EA 33 725BC 48503 AT HORIZONTAL STABILIZER CTR SECTION, FOUND CORROSION INSIDE BARREL NUT HOLE NR 36 LT HORIZ STAB. 2 L 7 3 4F RT A22WE 2008042800318 20080428 00318 NM 2008 4 28 CO1Y200800003 1 20080114 G 5755 ARC44231 HINGE BRACKET DOUG MD11 MD11 3023602 NM LT SPOILER WORN B CO1Y K NONE O OTHER IN INSP/MAINT 1 EA 33 725BC 48503 LT SPOILER NR1 FOUND WITH PLAY. 2 L 7 3 4F RT A22WE 2008022500008 20080225 00008 NE 2008 2 25 CRSCW1R075K 1 20080221 G 6410 7610105017045 SPAR SKRSKY SKRSKY S76 S76B 8143007 NE PWA PT6 PT6* 52043 EA T/R BLADE CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 11 780P 2905 A11602002X 760359 DURING A ROUTINE INSP, A SLIGHT, OCCASIONAL CLICK WAS HEARD WHILE FLEXING TAIL ROTOR BLADE. BLADE ASSY (P/N 76101-05501- 042, S/N A245-00153) WAS REMOVED FOR PRECAUTIONARY MEASURES AND SENT FOR INSP/EVALUATION. UPON DISASSEMBLY AND INSP, SPA R WAS FOUND TO HAVE CRACKS COMING FROM ELIPITICAL PLUG AREA. SPAR WAS SUBSEQUENTLY CHANGED, BLADE INSPECTED AND RETURNED TO SERVICABLE CONDITION. SCRAPED SPAR TOTAL TIME WAS 2905.8 HOURS. THIS IS THE SECOND SPAR WE HAD CRACKED. 1 G 7 2 4U 3 T H1NE E2NE 2008020400104 20080204 00104 CE 2008 2 4 CWQR200801 1 20080129 G 5330 651201026 SKIN CESSNA 500 560CESSNA 2076750 CE PWA 530 PW535A NE FUSELAGE CRACKED B DXTA K NONE O OTHER IN INSP/MAINT 1 GL 05 839QS 5600690 DURING A PHASE 1-4 INSPECTION THE TECHNICIAN NOTICED A SMALL CRACK IN THE PAINT UNDER THE RT ENGINE PYLON. REMOVED THE P AINT AND FOUND A 1.5 INCH CRACK. STARTING AT THE FWD BOTTOM CUT OUT FOR THE FWD SUPPORT BEAM. APPEARS THAT THERE WAS NOT ENOUGH CLEARANCE IN THE TAILCONE SKIN FOR THE MOVEMENT OF THE ENGINE BEAM WHEN THE AIRCRAFT WAS MANUFACTURED. SUBMITTE D TO MFG ENGINEERING FOR REPAIR. 2 L 7 2 4F 4 F RT A22CE E00053EN 20080909 CE 2008 9 9 CWQR200808 1 20080821 G 5320 661503517 SUPPORT BRACKET CESSNA 560 560XL 2076702 CE FUSELAGE CRACKED B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 679QS 5605279 DURING A PHASE 1-4 INSP, FOUND THE SUPPORT BRACKET CRACKED, CRACK IS LOCATED IN THE SUPPORT BRACKET FOR THE ECU, THE CRA CK INTERSECTS A HOLE FOR THE NUTPLATE THAT ATTACHES ONE OF THE ECU MOUNTING BOLTS. SERVICE CONDITION REPORT HAS BEEN FIL ED WITH MFG UNDER SCR# 376154. 2 L 7 2 4F RT A22CE 20081001 CE 2008 10 1 CWQR200809 1 20080821 G 5320 661503515 SUPPORT BRACKET CESSNA 560 560XL 2076702 CE FUSELAGE CRACKED B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 679QS 5605279 DURING A PHASE 104 INSPECTION, FOUND THE SUPPORT BRACKET CRACKED. CRACK IS ABOUT 1.5 INCHES LONG AND IS CENTERED AT THE ATTACH POINT FOR THE VALVE. SERVICE CONDITION REPORT HAS BEEN FILED WITH MFG UNDER SCR NR 376160. (K) 2 L 7 2 4F RT A22CE 2008031300048 20080313 00048 SO 2008 3 13 DAL26220220 1 20080218 G 4910 1159AC30551103 DUCT GULSTM G1159 GIV 3980115 SO APU INLET CRACKED E CLWA K NONE O OTHER IN INSP/MAINT 1 SW 05 589HM 6464 1153 A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM). 2 L 7 2 4F RT A12EA 2008031700252 20080317 00252 EU 2008 3 17 DJSR20080125 1 20080125 G 3610 32156321 PRESSURE VALVE AMD FALC20 FALCON20C5 2730107 EU GARRTT TFE731 TFE731* 01518 WP BLEED AIR SYS MALFUNCTIONED B DJSA A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 GL 23 531FL 15 113 NR 1 BLEED OVERHEAT LIGHT ILLUMINATED PASSING 15,000 WITH CORRESPONDING CABIN PRESSURE FLUCTUATIONS. 2 L 7 2 4F 4 F RT A7EU E6WE 2008031000343 20080310 00343 EU 2008 3 10 DJSR20080205 1 20080205 G 5610 MY20268109 WINDSHIELD AMD FALCON FALCON20 2730103 EU GARRTT TFE731 TFE731* 01518 WP COCKPIT CRAZED D DJSR A UNSCHED LANDING O OTHER CL CLIMB 1 GL 23 541FL 3 48 F/O`S WINDSHIELD OUTER PANE CRAZED OBSTRUCTING F/O`S VISION. (K) 2 L 7 2 4F 4 F RT A7EU E6WE 2008032000021 20080320 00021 EU 2008 3 20 DJSR20080226 1 20080226 G 3231 MECHANISM AMD FALC20 FALCON 2720302 EU GARRTT TFE731 TFE731* 01518 WP NLG DOOR ICED B DJSA A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 GL 23 521FL 15493 68 NOSE GEAR DOOR WOULD NOT CLOSE IN FLIGHT. 2 L 7 2 4F 4 F A7EU E6WE 2008042800344 20080428 00344 2008 4 28 DJSR20080417 4 20080417 G 3417 065008206 AIR DATA MODULE AMD FALC20 FALCON20C5 2730107 EU GARRTT TFE731 TFE731* 01518 WP COCKPIT MALFUNCTIONED B DJSA A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 GL 23 511FL 68 122 ALTIMETER SYSTEMS SHOWING MISCOMPARE (EXCEEDING 50 FT AT 5000 FT). 2 L 7 2 4F 4 F RT A7EU E6WE 2008012200089 20080122 00089 WP 2008 1 22 DSC4331DL6292 2 20080110 G 7210 31022811 RETAINER SEAL GARRTT TPE331 TPE33110R 0517 WP ENGINE CRACKED B K NONE L NO TEST IN INSP/MAINT 1 SO 15 P37369C NO GEARCASE NEGATIVE PRESSURE INDICATED DURING ENGINE TEST STAND FUNCTIONAL TESTING. TROUBLESHOOTING FOUND CRACKS IN SE AL RETAINER. SUBJECT RETAINER IS MADE WITH ALUMINUM. OLDER PN 693905-10 IS MADE WITH STEEL. SB 72-0224 AUTHORIZED INST ALLATION OF ALUMINUM RETAINER. 4 T E4WE 20080603 EU 2008 6 3 DT1R200800001 1 20080508 G 2700 1090020477 LEVER AGUSTA A109 A109S 0260103 EU YAW TRIM SYSTEM DAMAGED B K NONE O OTHER IN INSP/MAINT 1 EA 17 167JC 40 22067 OPENED THE ACCESS PANEL UNDER THE CO-PILOT'S SEAT, FOUND THE YAW TRIM LEVER (PN 109-0020-47-7 NSN) DETACHED FROM THE YAW TRIM MOTOR SHAFT. NO DAMAGE NOTED TO THE MOTOR SHAFT. THE LEVER WAS INTACT BUT DAMAGED AT THE POINT WHERE IT CONTACTS THE SHAFT, BUT HAD THE CORRECT HARDWARE AND COTTER PIN INSTALLED. THE APPLICABLE PUSH-ROD END (ATTACHED TO THE LEVER) WAS ALSO LOOSE. INSPECTED AND RETORQUED THE ROD-END. REPLACED AND TORQUED THE LEVER, REINSTALLED TO THE YAW TRIM MOTOR SHAFT, AND COMPLETED OPERATIONAL CHECK WITH NO DEFECTS NOTED. 1 G 7 1 3U RT H7EU 20080828 NM 2008 8 28 DU4R2008238 1 20080822 G 5322 SHEAR TIE DOUG MD80 MD83 3023681 NM FS 148 L22L DAMAGED B DU4R O OTHER O OTHER NR NOT REPORTED 1 SO 15 874GA 49643 ACFT ARRIVED, WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE. (S) 2 L 7 2 4F RT 20080828 NM 2008 8 28 DU4R2008238A 1 20080822 G 5330 SKIN DOUG MD80 MD83 3023681 NM FS 148 L22L DAMAGED B DU4R O OTHER W INADEQUATE Q C NR NOT REPORTED 1 SO 15 874GA 49643 ACFT ARRIVED, WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE. (S) 2 L 7 2 4F RT 20081201 NM 2008 12 1 DU4R2008263 1 20081124 G 5315 36726 FLOORBEAM BOEING 737 7378Q8 13844BX NM FUSELAGE CORRODED B DU4R K NONE O OTHER IN INSP/MAINT 1 SO 15 171LF 30637 FOUND CORROSION IN AFT PIT ON TOP SURFACE OF FLOORBEAM AT BS 787 TO BS 847 RBL 16. 2 L 7 2 4F RT A16WE 20090105 NM 2009 1 5 DU4R2008273 1 20081213 G 5314 KEELBEAM BOEING 757 75723APF 1384966 NM BS 956 CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION AT TIMCO-LCQ, LAKE CITY, FL FOUND KEEL BEAM LOWER SURFACE CORSS BRACE HAS CORROSION AT BS 95 6S/O 318002 N/R #35360 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008274 1 20081213 G 5314 KEELBEAM BOEING 757 75723APF 1384966 NM BS 1040 CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND KEELBEAM LOWER SURFACE CROSS BRACE HAS CORROSION AT BS 1040. 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008275 1 20081216 G 5730 SKIN BOEING 757 75723APF 1384966 NM LT WING CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND LT WING HAD CORROSION IN UPPER SKIN AT ALL VORTEX GENERATORS 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008276 1 20081216 G 5330 SKIN BOEING 757 75723APF 1384966 NM BS 600-612 DENTED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND 3 EA. DENTS IN LOWER FWD FUSELAGE BELOW MLG DOOR SCUFF PLATE BS 600-612. 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008277 1 20081216 G 5330 SKIN BOEING 757 75723APF 1384966 NM BS 1125 DENTED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND DENT IN EXT. FUSELAGE SKIN BS 1125, S-10L LAP SEAM. 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008278 1 20081216 G 5330 SKIN BOEING 757 75723APF 1384966 NM BS 1364-1410 DAMAGED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND NUMEROUS CREASES IN EXT. FUSELAGE SKIN BS 1364 - 1410, S-26L TO S-26R 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008279 1 20081217 G 5711 SPAR BOEING 757 75723APF 1384966 NM LT WING CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION ON LT WING REAR SPAR BELOW LEFT AFT BOOST PUMP RSS 185. 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008280 1 20081217 G 5314 KEELBEAM BOEING 757 75723APF 1384966 NM BS 996 CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION ON KEELBEAM LOWER SURFACE CROSS BRACE AT BS 996. 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008281 1 20081216 G 5330 SKIN BOEING 757 75723APF 1384966 NM BS 1932-1936 CORRODED B R AUTOROTATION O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION ON EXT SKIN AROUND APU OIL FUEL DRAIN MAST RT APD ACCESS DOOR. 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008282 1 20081217 G 5320 SUPPORT BOEING 757 75723APF 1384966 NM BS 1098 CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION ON WING TO BODY FAIRING SUPPORT ABOVE RT WING AT BS 1098. 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008283 1 20081210 G 5320 148N31388000 STRAP BOEING 757 75723APF 1384966 NM ZONE 300 CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND HEAVY CORROSION ON 2 EA. SUPPORT STRAPS REMOVED FROM BS 1825, B/O 0, RT SIDE TO HORI Z STAB. 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008284 1 20081217 G 5711 112N100217 SPAR BOEING 757 75723APF 1384966 NM ZONE 500 CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION ON WEB, LT WING REAR SPAR, ABOVE LT AFT BOOST PUMP WS 188 2 L 7 2 4F RT A2NM 20090105 NM 2009 1 5 DU4R2008285 1 20081228 G 5512 SKIN BOEING 757 75723APF 1384966 NM ZONE 900 CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 15 868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION IN SEVERAL AREAS OF UPPER SURFACE SKINS ON LT HORIZONTAL STABILIZER. 2 L 7 2 4F RT A2NM 20080828 NM 2008 8 28 DUR42008238B 1 20080822 G 5313 LONGERON DOUG MD80 MD83 3023681 NM FS 148 L22L DAMAGED B DU4R O OTHER O OTHER NR NOT REPORTED 1 SO 15 874GA 49643 ACFT ARRIVED WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE. (S) 2 L 7 2 4F RT 2008050800097 20080508 00097 NM 2008 5 8 DXTA200803018 1 20080424 G 2613 RP16100 SENSOR AMD FALC50 FALCON2000 2730170 NM PWC PW308 PW308C 52182 NE BLEED AIR SYS INOPERATIVE E DXTA A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 GL 07 223QS 430 86 BLEED OVERHEAT LIGHT CAME ON 2 MIN AFTER TAKEOFF. CHECKLIST ACCOMPLISHED AND CREW WAS UNABLE TO ISOLATE THE MALFUNCTION . FAULT CODE 404 AND 428. BLEED OVERHEAT COMES ON WITH APU BLEED ON AND ENGINE OFF. REMOVED & REINSTALLED TEMP SENSOR L70HU. OPS & LEAK CHECKS GOOD IAW MM 36-70-00 2 L 7 2 4F 4 F RT A50NM E00065EN 20080715 CE 2008 7 15 E812008F00000 1 20080213 G 5320 50430043619 CHANNEL BEECH B300 B300 1159232 CE FUSELAGE CRACKED B E81R K NONE O OTHER IN INSP/MAINT 1 GL 03 37TD 6102 FL25 INVESTIGATED PILOT COMPLAINT OF LOOSE FUSELAGE SKIN RIVETS AT CABIN DOOR HINGE AREA. FOUND FUSELAGE DOOR FRAME CHANNEL C RACKED. CABIN DOOR DAMPER ACTION ALSO REPORTED AND FOUND TO BE WEAK. SUSPECT CAUSED BY CABIN DOOR "BOTTOMING OUT" EXCESS IVELY HARD OR EXCESSIVE WEIGHT ON DOOR OVER REPEATED CYCLES. TECH/ INSPECTORS SHOULD CHECK DOOR DAMPNER OPERATION AT SC HEDULED PHASE INSPECTIONS AND CORRECT IF WEAK OPERATION NOTED. EVIDENCE OF LOOSE HINGE AREA RIVETS SHOULD ALSO BE INVES TIGATED FOR POSSIBLE CRACKED STRUCTURE UNDER THRESHOLD. (K) 2 L 7 2 4T RT A24CE 2008050800091 20080508 00091 NE 2008 5 8 EY2R080424001 3 20080424 G 6111 7826761 BEARING EMB 120 EMB120 3260201 SO HAMSTD 14RF 14RF9 NE BLADE CRACKED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 (0087319) CRACKED RACE. 2 L 7 2 4T RT A31SO 6 C P11NE 2008011400041 20080114 00041 EA 2008 1 14 FAA010808001 2 20080108 G 7200 MILH60001 BREATHER TUBE AYRES S2 S2RT15NORMAL 0970105 SO PWA PT6 PT6* 52043 EA ENGINE COLLAPSED D K NONE O OTHER IN INSP/MAINT 1 SO 07 2281A 7940 T15034 ENGINE BREATHER HOSE SWELLED ON INSIDE FROM THE ORIGINAL 1INCH DIAMETER TO .3750 INCH DIAMETER FROM HOT OIL FUMES. THRUS H ADDRESSED THE SAME PROBLEM ON THE MFG POWERED LINE. THIS IS NOT AN ISOLATED INCIDENT. THE CONDITION NOTED CAN ONLY BE FOUND AFTER HOSE REMOVAL. EXTERIOR OF HOSE LOOKS OK. SUGGEST A SCHEDULE OF REPLACEMENT EVERY 2000 HOURS. 1 L 7 1 3T 3 T A3SW E2NE 2008013100007 20080131 00007 EU 2008 1 31 FAA011808001 2 20080104 G 7321 CASC514 FUEL CONTROL GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU ENGINE INOPERATIVE C O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 EA 25 396U 4905 1350 16820 ON APPROACH TO TTN THE AUTO THROTTLES DISENGAGED. THE RT LEVER KNOB WAS ONE KNOB AFT OF THE LT. WHEN RT LEVER WAS ADVAN CED FORWARD THE RT ENGINE DID NOT RESPOND TO THROTTLE MOVEMENT. 2 L 7 2 4F 4 F RT A12EA E25NE 2008013100008 20080131 00008 SO 2008 1 31 FAA011808002 1 20080110 G 7930 OIL SYSTEM GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU ENGINE LOW PRESSURE D O OTHER J WARNING INDICATION CL CLIMB 1 EA 17 396U 4905 1350 16820 30 MINUTE INTO THE FLIGHT OIL PRESSURE DROPPED TO 7 PSI. NO ASSOCIATED CAS MESSAGE. OIL TEMP WAS SLIGHTLY HIGHER THAN LT ENGINE. FUEL TEMP WAS 19 DEGREES HIGHER THAN LT. DURING DESCENT OIL PRESSURE CAME BACK TO 47 PSI. 2 L 7 2 4F 4 F RT A12EA E25NE 2008013100298 20080131 00298 CE 2008 1 31 FAA012408001 1 20080124 G 2710 556536118 CABLE CESSNA 500 550 2076604 CE AILERON WORN B N81R K NONE O OTHER IN INSP/MAINT 1 GL 09 338B 5501132 DURING A PHASE 5 IT WAS FOUND THAT THE AILERON CABLES WERE LOCATED IN THE WRONG GROVES OF THE FUSELAGE SECTOR, CAUSING G ROOVES TO BE WORN INTO THE SECTOR BY THE CABLES. THERE IS A SPECIAL "NOTE" IN THE MAINTENANCE MANUAL 27-11-08 SECTION 7 FOR THE AILERON LEFT WING CONTROL CABLE REMOVAL/INSTALLATION, STATING CABLES 8 AND 9 ROUTE AROUND THE SECTOR ASSEMBLY IN THE LOWER GROOVE. THIS IS THE FIRST INSPECTION OF THIS SINCE THE AIRCRAFT WAS NEW AND THE IMPROPER ROUTING WAS DONE AT THE FACTORY. CORRECTIVE ACTION WAS TO REPLACE THE PART. 1 L 7 2 4F A22CE 2008031200003 20080312 00003 CE 2008 3 12 FAA021208001 1 20080212 G 2810 FUEL CAP CESSNA 172 172 2072402 CE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 15 4413 LEFT FUEL GAUGE INDICATED 10 GAL. IN TANK AT ALL FUEL LEVELS. THE TANK WAS DRAINED AND ACCESS COVER REMOVED. THE FUEL CA P RETAINING CHAIN WAS FOUND TO HAVE COME LOOSE ON THE TANK END "S" HOOK AND WRAPPED AROUND THE ARM ON THE FUEL LEVEL SEN DING UNIT LOCKING IT AT A 10 GAL. INDICATION. 1 H 7 1 3O NT 3A12 2008041400001 20080414 00001 2008 4 14 FAA030408001 1 20080304 G 4990 PUMP APU ENGINE FAILED B O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 99 13599 1468 2 APUS WERE REPORTED LOP AUTO SHUTDOWN. DISASSEMBLY OF THE ENGINES REVEALED LP ROLLER BEARING FAILURE. ONE OF THE ENGINE 'S BEARING DID NOT HAVE LUBRICATION AT ALL. THE OIL PUMPS P/N 3880998-1 WERE ROUTED TO BENCH TEST AND LOW PERFORMANCE W AS NOTED. DISASSEMBLY OF THE OIL PUMP REVEALED PORT PLATE P/N 3603681-1 HAD SIGNIFICANTLY WORN. IT ALLOWED THE PORT PLAT E MOVE TO RESTRICT THE OIL INLET PORT AND OUTLET PORT AND CAUSED LOW PUMP PERFORMANCE. THE BEARING FAILURE WAS A CONSEQU ENCE OF INSUFFICIENT OIL PRESSURE. 2008041400003 20080414 00003 CE 2008 4 14 FAA031008001 1 20080310 G 2497 WIRE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE COCKPIT ARCED B B A EMER. DESCENT UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 17 43SA 10256 5500086 PILOT REPORTED CB LABELED LT CB PANEL OPENED IN FLIGHT, PILOT BLEW THE GEAR DOWN AND INITIATED A FLYBY OF THE TOWER TO A SSURE THE GEAR WAS DOWN. AC LANDED WITHOUT FURTHER INCIDENT. MAINT INVESTIGATION REVEALED THAT THE CROSSOVER POWER WIRE FROM THE CO-PILOTS CB PANEL HAD RUBBED AND ARCED TO THE NUT AND COTTER KEY ATTACHING THE AILERON CABLE LINK FROM THE PI LOTS CONTROL COLUMN TO THE OB LT FWD AILERON CABLE. THE WIRE WAS NOT PROPERLY ROUTED OR SECURED. THE WIRE LAYS UNDERNEAT H THE AIR CONDITIONER DUCTING AND IS NOT VISIBLE WITH ONLY THE COCKPIT FLOORBOARDS REMOVED. THE WIRE SUPPLIES POWER FROM THE CO-PILOTS CB PANEL TO THE PILOTS CIRCUIT BREAKER PANEL BUSS THAT SUPPLIES POWER TO THE FOLLOWING BREAKERS ACM-2, W/ 1 L 7 2 4F 4 F A22CE E1NE 2008040300042 20080403 00042 CE 2008 4 3 FAA08222001 1 20080222 G 2520 3037091BS SEAT RAYTHN DH125 HAWKER800XP 7150012 CE GARRTT TFE731 TFE731* 01518 WP MISINSTALLED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 01 800RC 258660 DURING PRE-FLIGHT INSPECTION IT WAS NOTED THAT NR2 RT SEATBACK WOULD NOT BREAK OVER AND FOLD FWD IAW PLACARD TO REMOVE E SCAPE HATCH. THIS CONDITION PREVENTS ESCAPE HATCH FROM BEING EASILY REMOVED. FURTHER INVESTIGATION REVEALED THAT THE N R2 RT SEAT HAD BEEN SWAPPED WITH THE NR1 LT SEAT. SEATS ARE A DIFFERENT PN. THIS APPARENTLY HAPPENED AT LAST MAJOR MAI NT, QUITE SOME TIME AGO. SEATS ARE A DIFFERENT PN, BUT WE COULD NOT FIND IN WRITING THAT SPECIFIED THIS INFORMATION NOR IS THERE A REQUIRED INSP TO CHECK FOR THIS CONDITION. TALKS WITH MFG TECH INDICATE THAT THIS CONDITION IS FOUND FROM T IME TO TIME. ACCOMPLISH AN IMMEDIATE INSP TO VERIFY THAT THE CORRECT PN SEAT IS IN THE NR2 RT POSITION AND CORRECT ANY 2 L 7 2 4F 4 F RT A3EU E6WE 2008012900011 20080129 00011 CE 2008 1 29 FAA20080118 1 20080118 G 2752 505212234 ACTUATOR BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA ZONE 600 CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 09 85TB LJ833 RT OB FLAP ACTUATOR ASSY, PISTON TUBE CRACKED 100 PERCENT IN DEPTH, 100 PERCENT ENTIRE LENGTH OF TUBE. CRACK RUNS PARAL LEL TO TUBE . 1 L 7 2 3T 4 T 3A20 E4EA 2008040200027 20080402 00027 CE 2008 4 2 FAA2008123001 1 20080123 G 6120 5221220F PILOT VALVE WOODWARD BEECH 58 58 1152740 CE CONT O550 IO550* SO PROP GOVERNOR BROKEN B E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 EA 63 401BC 697 00066 TH1668 PROPELLER WENT TO FEATHER IN FLIGHT AND WAS UNABLE TO UNFEATHER. AFTER RECEIVING THE GOVERNOR FOR INSPECTION IT WAS DISC OVERED THAT THE BOTTOM END OF THE PILOT VALVE (P/N 5221-220) HAD BROKEN OFF AND WAS MISSING. IT WAS PRESUMED THAT IT EXI TED THE BOTTOM END OF THE DRIVE GEAR AND ENTERED THE ENGINE SUMP. THE OPERATOR WAS NOTIFIED AND THE MISSING PIECE WAS RE TRIEVED. 1 L 7 2 3O 3 O 3A16 E3SO 20081217 CE 2008 12 17 H51R08001 1 20081203 G 2620 2MD31AX287G SWITCH LEAR 35 31A 5170531 CE EXTINGUISHERS STICKING B H51R K NONE L NO TEST IN INSP/MAINT 1 NM 03 420LJ 3052 111 FAILURE OF SWITCH IN THE ENGINE FIRE PULL SWITCH ASSY. AFTER ACCESSING THE FIRE PULL SWITCH ASSEMBLY TO VERIFY AIRWORTH INESS DIRECTIVE 95-21-03, AMENDMENT 39-9388, APPLICABILITY, THE S4 MICROSWITCH FAILED IN THE CLOSED POSITION. THE AIRWO RTHINESS DIRECTIVE WAS ISSUED FOR THIS PROBLEM, BUT WAS NOT APPLICABLE TO THIS SWITCH BY S/N, SUSPECT ADDITIONAL LOTS MA Y BE EFFECTED. AFTER REASSEMBLY OF GLARESHIELD, FUNCTIONAL TESTS REVEALED THE MICROSWITCH HAD STUCK CLOSED, PREVENTING LT ENGINE BLEED AIR FROM WORKING. VISUAL INSPECTION OF SWITCH SHOWS THE S4 MICROSWITCH ACTUATOR STUCK IN THE RECESSED P OSITION. SWITCH P/N 6608214-3, S/N 2280, F.T. DATE FEB '93, MANUFACTURE EATON P/N 865001-3 AD WAS FOR SWITCHES S/N 232 2 L 7 2 4F RT A10CE 2008040200037 20080402 00037 2008 4 2 HN8R200800001 4 20080122 G 6122 6602263 CONTROL CABLE MOONEY M20 M20J 5870219 SW LYC O360 IO360A1A 41514 EA PROP GOVERNOR BROKEN B HN8R K NONE L NO TEST IN INSP/MAINT 1 CE 05 58102 298 243008 PROPELLER GOVERNOR CONTROL CABLE BROKE WHILE AIRCRAFT WAS ON GROUND. 1 L 7 1 3O 3 O 2A3 1E10 2008040400003 20080404 00003 NM 2008 4 4 IU6R232726 1 20080306 G 2710 654484515 MANIFOLD BOEING 737 737 UTILSYS NM BROKEN B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 71885 FILTER BOWL BORE OF MANIFOLD BROKE OFF AT THE THREADS. 2 L 7 2 4F RT A16WE 20080522 2008 5 22 LJER050608 2 20080506 G 7414 10357424 BUSHING S4LSC200 ROBSIN R22 R22BETA 7640110 NM MAGNETO LOOSE B LJER K NONE O OTHER IN INSP/MAINT 1 NM 09 7155W 531 531 E07DA122R 2759 ROTOR BUSHING DEBONDED AND LOOSE, CAUSED ROTOR AND GEAR PLAY. MAGNETO FAILED. 1 G 7 1 3O H10WE 2008050800025 20080508 00025 CE 2008 5 8 LJER210408 1 20080421 G 3233 12810016 HOUSING CESSNA 172 172RG 2072438 CE LYC O360 O360* 41514 EA LT MLG ACTUATOR CRACKED B LJER A UNSCHED LANDING O OTHER CL CLIMB 1 NM 09 9877B 594 172RG1066 LANDING GEAR FAILED TO RETRACT. LT MAIN ACTUATOR HOUSING CRACKED AT MOUNTING HOLE. 1 H 7 1 3O 3 O 3A17 E286 20080715 CE 2008 7 15 MT9R00000040 1 20080530 G 7603 SL60061 POWER LEVER CESSNA 208 208B 2073701 CE PWA PT6 PT6* 52043 EA ENGINE CONTROL BROKEN B MT9R O OTHER O OTHER NR NOT REPORTED 1 SW 05 1324G 208B0777 ENGINE CONTROL QUADRANT POWER LEVER SPRING STOP BROKEN. (K) 1 H 7 1 3T 3 T A37CE E2NE 2008041000237 20080410 00237 GL 2008 4 10 MV1R200808061 2 20080402 G 7210 6898785 SHAFT ALLSN SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30S 03013 GL NR1 PTO GEAR CRACKED B MV1R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 17 38 2822 1058 CAG90287 760087 CAE890282 OIL LEAK FROM OUTPUT SHAFT NR 1 ENGINE. INSPECTED AREA NO DEFECTS FOUND AT THAT TIME. REPLACED SHAFT SEAL. GROUND OPS AN D LEAK CHECK GOOD. AFTER FLIGHT OIL LEAK RETURNED. ON GROUND RUN NO LEAK UNTIL ROTOR WAS RELEASED. OIL LEAK WAS AT OUTPU T SHAFT. FOUND PTO OUTPUT SHAFT CRACKED. REMOVED ENGINE SENT TO ENGINE SHOP FOR INSPECTION AND REPAIR. 1 G 7 2 3U 3 U H1NE E1GL 20080520 CE 2008 5 20 MV1R200808136 1 20080429 G 2121 1013841761 BLOWER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA ZONE 100 BURNED OUT B MV1R B G H A EMER. DESCENT O2 MASK DEPLOYED DEACTIVATE SYST/CIRCUITS UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 EA 17 35 1486 178 BB88 DURING FLIGHT, SMOKE INITIATED FROM BEHIND INSTRUMENT PANEL CENTER BELOW. PROJECT POWER TERMINATED. ALL ELECTRICAL POWER NOT NECESSARY FOR FLIGHT, OFF. EMERGENCY LANDING, ON GROUND MAINT FOUND VENT BLOWER ASSY INOP AND BURNED. BLOWER MEL'D AND FLOWN WITHOUT FURTHER INCIDENT. 1 L 7 2 4T 4 T A24CE E4EA 20090106 NE 2009 1 6 MV1R200808429 1 20081217 G 6210 7615009100053 BLADE SKRSKY S76 S76A 8143006 NE MAIN ROTOR DELAMINATED B K NONE O OTHER IN INSP/MAINT 1 EA 17 38 213 S760087 DURING 3 YEAR MAIN ROTOR BLADE INSP FOUND DELAMINATION IN BLACK MAIN ROTOR BLADE ROOT END. DATA SENT TO MFG FOR EVALUATI ON. TOTAL DELAMINATED AREA IS 1.472 SQUARE INCHES. 1 G 7 2 3U H1NE 20080717 CE 2008 7 17 N772AF 1 20080602 G 5540 10164001423 HINGE BEECH 200 B200 1152922 CE RUDDER CORRODED B VIBR K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 SO 13 772AF 5763 BB1001 CENTER RUDDER HINGE FOUND TO HAVE EXCESSIVE CORROSION. 1 L 7 2 4T A24CE 2008050800042 20080508 00042 CE 2008 5 8 O7TR200800001 1 20080311 G 8120 46C22924E TURBOCHARGER CESSNA 182 T182T 2072738 CE ENGINE FAILED B O7TR K NONE O OTHER IN INSP/MAINT 1 WP 17 MAJOR TURBO FAILURE DUE TO SEPARATION OF TURBINE WHEEL HEAD FROM SHAFT. 1 H 7 1 3O NT 3A13 20081210 CE 2008 12 10 OMKR2008-0002 1 20081124 G 5100 UNKNOWN CESSNA 206 T206H 2073303 CE LYC O540 TIO540AJ1A EA UNKNOWN B OMKR O OTHER O OTHER IN INSP/MAINT 1 NM 03 6197S T20608875 L1311661E NEW AIRCRAFT FROM FACTORY. PERFORMED AD SEARCH DUE TO EXPORT REQUIREMENT DURING ANNUAL. FOUND CESSNA SUPPLIED AD LIST DID NOT MATCH LYCOMING SUPPLIED LIST, AND CESSNA HAD CHANGED 8 AD SIGN-OFFS FROM LYCOMING. CESSNA CONTACTED, AND SAID T HEY HAD TO CHANGE LYCOMING'S LIST BECAUSE IT WAS IN ERROR. LYCOMING CONTACTED WITH NO REPLY YET. STRAIGHT FLIGHT PMI B ROUGHT INTO LOOP, AND WANTED SDR FILLED OUT. PMI WILL ALSO ACTION. VERY SERIOUS IN NATURE AS LYCOMING SAYS THEY CHANGE D NUMEROUS PARTS FOR AD COMPLIANCE, INCLUDING THE CRANKSHAFT, WHEN THESE AD'S DO NOT APPLY IN THE FIRST PLACE. SUSPECT YOU WILL FIND LARGE RUN OF LYCOMING ENGINES WITH THIS SAME PROBLEM. THESE ENGINES ARE NOT AIRWORTHY WITH FALSE AD LISTS 1 H 7 1 3O 3 O RT A4CE E14EA 20081210 CE 2008 12 10 OMKR2008-0003 1 20081124 G 5100 NONE CESSNA 208 208B 2073701 CE NONE B OMKR K NONE O OTHER IN INSP/MAINT 1 NM 03 22430 208B2011 NEW ACFT FROM FACTORY. PERFORMED AD SEARCH DUE TO EXPORT REQUIREMENT DURING ANNUAL. FOUND NUMEROUS ADS SIGNED OFF AS C OMPLIED WITH THAT WERE N/A TO ACFT. MANY LISTED PARTS THAT WERE SUPPOSEDLY CHANGED. CONTACTED CESSNA. WAS ASKED WHY W ITH SO MANY NEW ACFT BEING RELEASED, NO ONE ELSE WAS COMPLAINING. AFTER SEVERAL PHONE CONVERSATIONS AND SEVERAL CORRECT ED LISTS, FINALLY HAD AN ACCEPTABLE LIST. 2 ADS WERE NOT ACCOUNTED FOR AND HAD BEEN ISSUED PRIOR TO THE ACFT BORN-ON DA TE. STRAIGHT FLIGHT PMI BROUGHT INTO THE LOOP AND WANTED A SDR SUBMITTED. HE IS ALSO WORKING. EXPECT SERIES OF THESE CARAVANS TO HAVE SAME PROBLEM. THESE ACFT ARE NOT AIRWORTHY WITH FALSE AD LISTS. 1 H 7 1 3T A37CE 2008020400101 20080204 00101 EU 2008 2 4 PAI52008S4818 1 20080130 G 5540 STRUCTURE PIAGIO P180 P180 6960204 EU RUDDER CHAFED B PAI5 K NONE O OTHER IN INSP/MAINT 1 SO 05 134SL 2797 1100 DURING D-CHECK INSPECTION, FOUND RUDDER TORQUE CHAFED BY AFT FAIRING P/N 80-561004-401. 1 H 7 2 3O RT A59EU 2008022500009 20080225 00009 EU 2008 2 25 PAI52008S4858 1 20080212 G 5512 SKIN PIAGIO P180 P180 6960204 EU PWA PT6 PT6* 52043 EA HORIZONTAL STAB CRACKED B PAI5 K NONE O OTHER IN INSP/MAINT 1 SO 05 138SL 5072 1103 DURING D-CHECK INSPECTION, FOUND CRACK 2.5 INCHES LONG IN HORIZONTAL STABILIZER LT LOWER COMPOSITE SKIN. CRACK IS AT IB END OF LT HORIZONTAL STABILIZER, 5 INCHES AFT OF LEADING EDGE. 1 H 7 2 3O 3 T RT A59EU E2NE 2008032800102 20080328 00102 CE 2008 3 28 PAI52008S4877 1 20080209 G 3220 07436062 SUPPORT FITTING CESSNA 182 182T 2072703 CE NLG BROKEN B PAI5 K NONE O OTHER IN INSP/MAINT 1 SO 05 470P 719 18281290 PILOT COMPLAINED OF NOSE WHEEL SHIMMY. INSPECTION FOUND RIGHT-HAND SIDE OF NOSE GEAR LOWER SUPPORT FITTING BROKEN. 1 H 7 1 3O NT 3A13 20080602 NE 2008 6 2 PJ6G20080147 2 20080414 G 7200 310718501 GAS GENERATOR AIRTRC AT802 AT802 0390305 SW PWC PT6 PT6A67AG 52211 NE HARTZL HCB5M HCB5MA3 GL ENGINE ERODED D PJ6G O OTHER P NO WARNING INDICATION AG AGRICULTURE 1 SW 11 627JP 566 566 8020238 PCERD0147 'C' FLANGE EROSION AT SCAVENGE TUBE OIL COUPLING WITH ASSOCIATED PARTIALLY SEVERED 'T' BOLT. 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 20090114 NM 2009 1 14 R5KB20081220001 1 20081220 G 5320 WEB BOEING 727 727212 138407G NM BS 1213 CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 33 727NK 21945 WEB CORRODED AT BS 1213 WL 177 RBL 5. 2 L 7 3 4F A3WE 2008013100305 20080131 00305 2008 1 31 RC2R130L 4 20080123 G 6122 5221220F PILOT VALVE B210800REVJ BEECH 58 58 1152740 CE CONT O520 IO520CB 17032 SO GOVERNOR BROKEN B O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 NE 03 401BC 697 00066 TH1668 PROPELLER WENT TO FEATHER IN FLIGHT AND WAS UNABLE TO UNFEATHER. AFTER RECEIVING THE GOVERNOR FOR INSPECTION IT WAS DISC OVERED THAT THE BOTTOM END OF THE PILOT VALVE (P/N 5221-220) HAD BROKEN OFF AND WAS MISSING. IT WAS PRESUMED THAT IT EXI TED THE BOTTOM END OF THE DRIVE GEAR AND ENTERED THE ENGINE SUMP. THE OPERATOR WAS NOTIFIED AND THE MISSING PIECE WAS RE TRIEVED. 1 L 7 2 3O 3 O 3A16 E5CE 2008041400040 20080414 00040 NM 2008 4 14 RI3R200800001 1 20080331 G 2840 403501 TSU BOEING 737 737* NM INTERNAL CONTAMINATED B RI3R K NONE J WARNING INDICATION IN INSP/MAINT 1 SO 15 WHILE PERFORMING TROUBLESHOOTING AND REPAIR OF 4035-01 SERIES TRANSIENT SUPPRESSION UNITS (TSU) IAW COMPONENT MM 28-44-6 4, REV 2, DATED 20/04/2007, IT WAS DISCOVERED THAT VARIOUS UNITS (7 TOTAL) SHOWED EVIDENCE OF CONTAMINATION ON INTERIOR SURFACES FROM WHAT APPEARS TO BE MOISTURE INTRUSION THROUGH THE CASE SEALS. AFFECTED UNITS HAVE BEEN PLACED IN QUARANTI NE. IMMEDIATELY NOTIFIED THE ORIGINAL EQUIPMENT MFG AND PRODUCTION AUTHORITY HOLDER, OF THE FINDINGS. COORDINATING WIT H ENGINEERING AND QUALITY REPRESENTATIVES ON FURTHER ACTION AND FINAL DISPOSITION. AFFECTED UNITS TO REMAIN IN QUARANT INE UNTIL GUIDANCE IS RECEIVED. CONSULTED WITH FSDO, PMI. RECOMMENDED ACTION: SUBMIT SDR IAW 14 CFR PART 145.221 AND R 2 L 7 2 4F RT A16WE 2008041400103 20080414 00103 NM 2008 4 14 RI3R200800002 1 20080409 G 2840 403501 TSU BOEING 737 737* NM CONTAMINATED B RI3R O OTHER O OTHER NR NOT REPORTED 1 SO 15 WHILE PERFORMING PRELIMINARY INSPECTION AND TROUBLESHOOTING OF THE TRANSIENT SUPPRESSION UNIT (TSU) 4035-01, S/N 1308, I T WAS DISCOVERED THAT THE UNIT SHOWED EVIDENCE OF INTERNAL CONTAMINATION. THE CONTAMINATION APPEARS TO BE CAUSED BY MOI STURE INGRESS INTO THE UNIT. THE UNIT HAS BEEN PLACED IN QUARANTINE, AND PAH/OEM HAS BEEN NOTIFIED OF THE FINDING. 2 L 7 2 4F RT A16WE 2008040400008 20080404 00008 GL 2008 4 4 SJ3R025859 3 20080314 G 6110 D495 FORK PILATS PC12 PC12 7090550 EU PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3D GL PROPELLER ASSY CRACKED B SJ3R K NONE O OTHER IN INSP/MAINT 1 GL 05 2185 1361 HJ494 CRACK INDICATIONS FOUND DURING MAG PARTICLE INSPECTION. CRACKS ARE LOCATED ON THE THIN SIDE OF ALL (4) FORK SLOTS RADI. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2008040200035 20080402 00035 NE 2008 4 2 SJ3R080124001 3 20080124 G 6110 B6545 CAM FOLLOWER BEECH 1900 1900D 1154162 CE PWC PT6 PT6A42A 52043 NE HARTZL HCE4A HCE4A3I NE PROP BLADE BROKEN B SJ3R K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 GL 05 HJ1430 REMOVED DUE TO SUSPECTED INTERNAL HUB COMPONENT FAILURE. BLADE S/N 4152 WAS FOUND TO ROTATE FREELY +/- 12.5 DEGREE POST FIRST GROUND RUN AFTER INSTALLATION. INSPECTION AFTER DISASSEMBLY REVEALED ONE BROKEN B-6545 PITCH CHANGE KNOB CAM FOL LOWER. THIS PART WAS INSTALLED NEW AT OVERHAUL AND FAILED ON FIRST GROUND RUN. 2 L 7 2 4T 4 T RT A24CE E4EA 5 C P10NE 2008042300168 20080423 00168 NM 2008 4 23 SROM2008001 1 20080406 G 5350 654869089 SUPPORT BOEING 737 737205 1384456 NM LT MLG WW GOUGED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 39285 23466 LEFT HAND MAIN LANDING GEAR WHEEL WELL FAIRING SUPPORT GOUGED AT AFT OUTBOARD SIDE. REPAIRED LT MLG WHEEL WELL SUPPORT A T AFT OUTBOARD SIDE IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 073-1236-08-476 AND ASI SOLUTIONS DRAWING 5350476-1 , REV IR, DATED MARCH 13, 2008. REFERENCE NON-ROUTINE CARD 27, DATED 02/27/08. 2 L 7 2 4F RT A16WE 2008042300176 20080423 00176 NM 2008 4 23 SROM2008002 1 20080406 G 5315 FLOORBEAM BOEING 737 737205 1384456 NM FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 CORROSION ON AFT GALLEY FLOORBEAM AT STA BS 980 RBL 4. BLENDED AND FOUND CORROSION ON AFT GALLEY FLOORBEAM AT STA BS 98 0 RBL 4 TO BE BEYOND LIMITS. REPAIRED AFT GALLEY FLOORBEAM AT STA BS 980 RBL 4 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-4. REFERENCE NON-ROUTINE CARD 488, DATED 03/04/08. 2 L 7 2 4F RT A16WE 20080714 NE 2008 7 14 SROM20080023 2 20080523 G 7200 JT8D17A ENGINE BOEING 737 737205 1384456 NM PWA JT8 JT8D17A 52049 NE NR 1 BIRD INGESTION C SROM E L ENGINE SHUTDOWN ABORTED APPROACH C J R F.O.D. WARNING INDICATION PARTIAL RPM/PWR LOSS AP APPROACH 1 AL 03 736BP 36699 2561 23465 709500 INGESTED LARGE BIRD ON APPROACH TO AKU, SHUT-DOWN ENGINE AND COMPLETED MISSED APPROACH. DIVERTED TO SCC AND MADE UNEVEN TFUL LANDING. REMOVED AND REPLACED NR 1 ENGINE. 2 L 7 2 4F 4 F RT A16WE E2EA 20081126 2008 11 26 SROM20080024 4 20080926 G 2565 D31355440 SLIDE BOEING 737 737205 1384456 NM R2 DOOR INOPERATIVE I SROM K NONE L NO TEST IN INSP/MAINT 1 AL 03 733PA 23466 DURING MINI EVACUATION DEMONSTRATION TRAINING SLIDE DEPLOYED BUT DID NOT INFLATE. WAITING ON TEAR DOWN REPORT FOR FINAL DISPOSITION. 11/20/08 FINAL DISPOSITION. TEARDOWN REPORT INDICATED NO FINDINGS. 2 L 7 2 4F RT A16WE 2008042300186 20080423 00186 NM 2008 4 23 SROM2008003 1 20080406 G 5315 FLOORBEAM BOEING 737 737205 1384456 NM FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 CORROSION ON UPPER CAP OF FLOORBEAM AT STA BS 294.5 BETWEEN LBL 12 AND RBL 50. CORROSION ON UPPER CAP OF FLOORBEAM AT S TA BS 294.5 BETWEEN LBL 12 AND RBL 50 BLENDED BEYOND LIMITS IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM) , 53-10-1. REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-9. REFERENCE NON-ROUTINE CARD 494, DATED 03/04/08. 2 L 7 2 4F RT A16WE 2008042300171 20080423 00171 NM 2008 4 23 SROM2008004 1 20080406 G 5315 FLOORBEAM BOEING 737 737205 1384456 NM FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 CORROSION FOUND ON FLOORBEAM STA BS 1016 BL 5 THRU BL 38 LEFT HAND. CORROSION ON FLOORBEAM STA BS 1016 BL 5 THRU BL 28 LEFT REMOVED AND FOUND TO BE BEYOND LIMITS IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-01, FIGUR E 1. FLOORBEAM REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-04, FIGURE 1. REFERENCE NO N-ROUTINE CARD 19, DATED 03/04/08. 2 L 7 2 4F RT A16WE 2008042300133 20080423 00133 NM 2008 4 23 SROM2008005 1 20080406 G 5320 TORQUE BOX BOEING 737 737205 1384456 NM FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 CORROSION BETWEEN STA BS 1118 AND STA BS 1138 IN THE RIGHT HAND TORQUE BOX, BY THE APU INLET DUCT. CORROSION BETWEEN STA BS 1118 AND STA BS 1138 IN THE RIGHT HAND TORQUE BOX, BY THE APU INLET DUCT REMOVED IN ACCORDANCE WITH BOEING 737 STRUC TURAL REPAIR MANUAL (SRM), 51-10-06. ORIGINAL MATERIAL 0.063, AMOUNT OF REMOVED MATERIAL 0.025, OUT OF LIMITS IN ACCORD ANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-01, PAGE 45, DETAIL V. FORMED SECTION REPAIR CARRIED OUT IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-03. 2 L 7 2 4F RT A16WE 2008042300178 20080423 00178 NM 2008 4 23 SROM2008006 1 20080406 G 5330 SKIN BOEING 737 737205 1384456 NM FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 CRACK IN FUSELAGE SKIN AT STA BS 760 STR 19L, (NDT CONFIRMED CRACK). REPAIRED FUSELAGE SKIN AT STA BS 760 STR 19L IN AC CORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-30-03, FIGURE 48, FASTENERS INSTALLED IN ACCORDANCE WITH SRM 51-30-02. REFERENCE NON-ROUTINE CARD 542, DATED 03/04/08. 2 L 7 2 4F RT A16WE 2008042300177 20080423 00177 NM 2008 4 23 SROM2008007 1 20080406 G 2520 43100001 BAR 87513 BOEING 737 737205 1384456 NM SEAT CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 REPAIR CRACKED SPREADER BARS ON PASSENGER SEATS. REPAIRED CRACKED SPREADER BARS ON PASSENGER SEATS IN ACCORDANCE WITH C PAI EO C007-2525-B737-01 AND FAA DER APPROVED 8110-3, 080-1226-08-471 AND ASI DRAWING 2520471-1, REV IR, DATED MARCH 19, 2008. REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CARD 160, DATED 02/28/08. 2 L 7 2 4F RT A16WE 2008042300188 20080423 00188 NM 2008 4 23 SROM2008008 1 20080406 G 5314 KEELBEAM BOEING 737 737205 1384456 NM FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 LOWER CHORDS OF KEEL BEAM IN MAIN LANDING GEAR HAS CORROSION AT LOWER FLANGE IN SEVERAL AREAS UPPER & LOWER SURFACES FRO M STA BS 663-727 RBL 6.5 & LBL 6.5. REPAIRED LOWER CHORD OF KEEL BEAM IN MLG WHEEL WELL AT LOWER FLANGE IN ACCORDANCE W ITH BOEING MESSAGE 1-789220434-4, DATED MARCH 28, 2008. FASTENERS INSTALLED IN ACCORDANCE WITH BOEING 737 STRUCTURAL RE PAIR MANUAL (SRM), 51-30-2. REFERENCE NON-ROUTINE CARD 570, DATED 03/04/08. 2 L 7 2 4F RT A16WE 2008042300172 20080423 00172 NM 2008 4 23 SROM2008009 1 20080406 G 5320 FITTING BOEING 737 737205 1384456 NM FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 CLIP CRACKED AT STA BS 1006 STR 21L. REPLACED CLIP AT STA BS 1006 STR 21L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPA IR MANUAL (SRM), 51-10-01 AND 51-30-02. REFERENCE NON-ROUTINE CARD 578, DATED 03/04/08. 2 L 7 2 4F RT A16WE 2008042300173 20080423 00173 NM 2008 4 23 SROM2008010 1 20080406 G 5320 FITTING BOEING 737 737205 1384456 NM FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 STRINGER TO FRAME CLIP REQUIRES BLENDING AT STA BS 907 STR 25L (REAR CARGO PIT). INSTALLED NEW CLIP AT STA BS 907 STR 2 5L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-03. REFERENCE NON-ROUTINE CARD 586, DATED 03/04/ 08. 2 L 7 2 4F RT A16WE 2008042300169 20080423 00169 NM 2008 4 23 SROM2008011 1 20080406 G 5340 STRINGER CLIP BOEING 737 737205 1384456 NM FUSELAGE DAMAGED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 STRINGER TIE CLIP DAMAGED AT STA BS 500A, STR 25R. REPLACED STRINGER TIE CLIP AT STA BS 500A STR 25R IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-1, PAGE 9, SECTION 7 AND 51-30-03. REFERENCE NON-ROUTINE CARD 590, DA TED 03/04/08. 2 L 7 2 4F RT A16WE 2008042300181 20080423 00181 NM 2008 4 23 SROM2008012 1 20080406 G 5330 SKIN BOEING 737 737205 1384456 NM FUSELAGE DAMAGED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 LIGHTNING STRIKE AT STA BS 933 STR 25.5R. REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-30- 03, FIGURE 23 (PERMANENT REPAIR), SECTION 1, PARAGRAPH 3., (NDT08-0509). REFERENCE NON-ROUTINE CARD 602, DATED 03/04/08 . 2 L 7 2 4F RT A16WE 2008042300134 20080423 00134 NM 2008 4 23 SROM2008013 1 20080406 G 5320 ATTACH FITTING BOEING 737 737205 1384456 NM FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 CRACK IN INTERCOSTAL ATTACH CLIP AT STA BS 360 STR 11L. REPLACED INTERCOSTAL ATTACH CLIP AT STA BS 360 STR 11L IN ACCOR DANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-2, FIGURE 1, 51-20-1, FIGURE 7, 51-30-2, 7.D.(6), AND 51-30- 2, FIGURE 7,3,11 AND 12. REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CARD 647, DATED 03/05/08. 2 L 7 2 4F RT A16WE 2008042300170 20080423 00170 NM 2008 4 23 SROM2008014 1 20080406 G 5320 ATTACH FITTING BOEING 737 737205 1384456 NM FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 CRACK IN INTERCOSTAL ATTACH CLIP STA BS 294.5 STR 11L. REPLACED INTERCOSTAL ATTACH CLIP STA BS 294.5 STR 11L IN ACCORDA NCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-2, FIGURE 1, 51-20-1, FIGURE 7, 51-30-2, 7.D.(6), AND 51-30-2, FIGURE 7, 3, 11 AND 12. REFERENCE NON-ROUTINE CARD 648, DATED 03/05/08. 2 L 7 2 4F RT A16WE 2008042300135 20080423 00135 NM 2008 4 23 SROM2008015 1 20080406 G 5311 FRAME BOEING 737 737205 1384456 NM FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 CRACK ON BODY FRAME INNER CHORD STA BS 616 LEFT HAND AT STUB BEAM LOWER CHORD. REPAIRED BODY FRAME INNER CHORD STA BS 6 16 LT AT STUB BEAM LOWER CHORD IN ACCORDANCE WITH BOEING SB 737-53A-1254. REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CAR D 672, DATED 03/05/08. 2 L 7 2 4F RT A16WE 2008042300167 20080423 00167 NM 2008 4 23 SROM2008016 1 20080406 G 5514 BUSHING BOEING 737 737205 1384456 NM HORIZ STAB LOOSE C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 LOOSE BUSHING ON STABILIZER SCREW JACK LOWER RIGHT HAND MOUNTING STRUCTURE (P/N 6-37464-1). REPLACED BUSHING ON STABILI ZER SCREW JACK LOWER RT MOUNTING STRUCTURE IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 078-1236-08-473 AND ASI SOLU TIONS DRAWING 5340473-1, REV IR, DATED MARCH 14, 2008. REFERENCE NON-ROUTINE CARD 740, DATED 03/06/08. 2 L 7 2 4F RT A16WE 2008042300174 20080423 00174 NM 2008 4 23 SROM2008017 1 20080406 G 7830 65MK781031 BRACKET BOEING 737 737205 1384456 NM PWA JT8 JT8D17A 52049 NE NR 1 ENGINE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 39277 23466 709507 LEFT HAND ENGINE TAILPIPE CRACKED AT BRACKET MOUNT (3 O'CLOCK POSITION). REPAIRED LEFT HAND ENGINE TAILPIPE BRACKET MOU NT (3 O'CLOCK POSITION) IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 073-1236-08-477 AND ASI SOLUTIONS DRAWING 78304 77-1, REV IR, DATED MARCH 18, 2008. REFERENCE NON-ROUTINE CARD 826, DATED 03/11/08. 2 L 7 2 4F 4 F RT A16WE E2EA 2008042300175 20080423 00175 NM 2008 4 23 SROM2008018 1 20080406 G 5315 FLOORBEAM BOEING 737 737205 1384456 NM FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 LOWER LONGITUDINAL FLOORBEAM CHORD CRACKED AT LBL 24.5 STA BS 663. REPLACED LOWER LONGITUDINAL FLOORBEAM CHORD AT LBL 2 4.5 STA BS 663 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-01 AND BOEING DRAWING 65-45410. REFE RENCE NON-ROUTINE CARD 843, DATED 03/18/08. 2 L 7 2 4F RT A16WE 2008042300183 20080423 00183 NM 2008 4 23 SROM2008019 1 20080406 G 5315 FLOORBEAM BOEING 737 737205 1384456 NM FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 LOWER LONGITUDINAL FLOORBEAM CHORD CRACKED AT RBL 24.5 STA BS 663. REPLACED LOWER LONGITUDINAL FLOORBEAM CHORD AT RBL 2 4.5 STA BS 663 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-01 AND BOEING DRAWING 65-45410. REFE RENCE NON-ROUTINE CARD 844, DATED 03/18/08. 2 L 7 2 4F RT A16WE 2008042300189 20080423 00189 NM 2008 4 23 SROM2008020 1 20080406 G 5315 FLOORBEAM BOEING 737 737205 1384456 NM FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 CORROSION ON FLOOR I-BEAM AT STA BS 344 LBL 18 THRU RBL 39. REPAIRED FLOOR I-BEAM AT STA BS 344 LBL 18 THRU RBL 39 IN A CCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-9, FIGURE 5. REFERENCE NON-ROUTINE CARD 858, DATED 03/2 5/08. 2 L 7 2 4F RT A16WE 2008042300195 20080423 00195 NM 2008 4 23 SROM2008021 1 20080406 G 5320 TORQUE BOX BOEING 737 737205 1384456 NM FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 CRACKED APU TORQUE BOX WEB AT STA BS 1115 RBL 2. HFEC CARRIED OUT IN ACCORDANCE WITH BOEING 737 NDT MANUAL 51-00-00, FI GURE 23, PART 6 ON A CUT-OUT ON THE APU TORQUE BOX, STA BS 1115. NO DEFECTS EVIDENT (NDT08-0461). APU TORQUE BOX WEB A T STA BS 1115 RBL 2 REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-01, FIGURE 1 AND INSTAL LED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-02, FIGURE 3 AND 11. REFERENCE NON-ROUTINE CARD 859, DATED 03/25/08. 2 L 7 2 4F RT A16WE 2008042300184 20080423 00184 NM 2008 4 23 SROM2008022 1 20080405 G 5314 KEELBEAM BOEING 737 737205 1384456 NM FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733PA 23466 LOWER CHORD OF KEEL BEAM IN MLG HAS CORROSION ON VERTICAL AND HORIZONTAL FLANGES IN SEVERAL AREAS FROM STA BS 663-727 LB L 615. REPAIRED LOWER CHORD OF KEEL BEAM ON LT SIDE BETWEEN STA BS 663 THRU 727 IN ACCORDANCE WITH FAA DER APPROVED FOR M 8110-3, 095-1236-08-483 AND ASI SOLUTIONS DRAWING 5310483-1, REV IR, DATED APRIL 4, 2008. CORROSION BLENDED IN ACCOR DANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-06 AND FAIRED AT A 10:1 RATIO IN ACCORDANCE WITH SRM 51-10-0 6. ALL PARTS TREATED AND PROTECTED IN ACCORDANCE WITH SRM 51-10-2. ALL FASTENERS INSTALLED IN ACCORDANCE WITH SRM 51-3 0-2. REFERENCE NON-ROUTINE CARD 876, DATED 03/31/08. 2 L 7 2 4F RT A16WE 2008041000163 20080410 00163 2008 4 10 STS004 4 20080402 G 2564 1218FASA6311701 LIFE RAFT EMB 135 EMB135KL 3260302 SO MISINSTALLED B K NONE O OTHER IN INSP/MAINT 1 SO 15 WL7R 2 THE CONFIGURATION BETWEEN THE FIRING HEAD BELL HOUSING AND THE LINK VALVE ARE NOT LOCATED PROPERLY. THE CAUSES THE LENG TH OF THE FREE LANYARD TO THE LINK VALVE TO BE REDUCED. THIS MAY CAUSE THE LIFE RAFT TO NOT DEPLOY IN THE SECONDARY MET HOD FOR INFLATION VERSUS ACTIVATING THE PRIMARY INFLATION METHOD, THE RIPCORD HANDLE. 2 L 7 2 4F RT T00011AT 200805141 20080514 1 NE 2008 5 14 SWDG08RD0113 2 20080508 G 7210 3030988 SEAL PWC AIRTRC AT802 AT802A 0390308 SW PWC PT6 PT6A67AG 52211 NE HARTZL HCB5M HCB5MA3 GL RGB DEFORMED D SWDG K NONE K FLUID LOSS IN INSP/MAINT 1 SW 11 804DG 738 PCERD0113 802A0089 PCERD0113 EXCESSIVE OIL LEAKAGE AROUND PROP SHAFT. FOUND FELT SEAL MISALIGNED AND INTERFERING WITH THE SHAFT SEAL. 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 200805141 20080514 1 2008 5 14 SWDG20085569 4 20080414 G 6122 311849703 GOVERNOR AIRTRC AT802 AT802A 0390308 SW PWC PT6 PT6A67AG 52211 NE HARTZL HCB5M HCB5MA3 GL PROPELLER LEAKING D SWDG A UNSCHED LANDING K R FLUID LOSS PARTIAL RPM/PWR LOSS AG AGRICULTURE 1 SW 11 804DG 721 721 802A0089 PCERD0113 HBA1298 GOVERNOR HAS EXCESSIVE BETA VALVE OIL LEAKAGE AND ERRATIC TORQUE FLUCTUATION. PART REMOVED AND SENT TO REPAIR STATION F OR EVALVUATION. 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2008022500007 20080225 00007 CE 2008 2 25 TIMR20080001 1 20080213 G 3233 993880081 ACTUATOR BEECH 99 C99 1154006 CE PWA PT6 PT6A36 52043 NE MLG LEAKING B TIMA O OTHER J WARNING INDICATION CL CLIMB 1 NM 07 239AL 4731 U239 LT MLG DID NOT RETRACT AFTER TAKEOFF. PILOT FLEW AC TO HOME BASE WITH GEAR DOWN. INVESTIGATION REVEALED THAT FLUID WAS PASSING THE PISTON INTERNALLY. 1 L 7 2 3T 4 T A14CE E4EA 2008011100307 20080111 00307 EA 2008 1 11 UE5R010208001 2 20080102 G 7313 3013635 NOZZLE DHAV DHC6 DHC6 2802606 EA PWA PT6 PT6A28 EA ENGINE SHEARED B UE5R K NONE O OTHER IN INSP/MAINT 1 EA 61 WHEN INSTALLING NOZZLE PN 3013635 ONTO NOZZLE ADAPTER ASSEMBLY USING SPECIFIED OHM TORQUE, NOZZLE SHEARED OFF COMPLETELY AT BASE OF THREADS. 1 H 7 2 3T 4 T RT A9EA E4EA 2008041000258 20080410 00258 CE 2008 4 10 VIB8368K 1 20080320 G 3220 BRACE BEECH 100 B100 1152919 CE NLG CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 13 97WD 7178 BE97 DISASSEMBLED NLG DURING SCHEDULED MAINT AND FOUND SIGNIFICANT CORROSION OVER MOST OF THE NOSE LANDING GEAR V BRACE, PN 5 0-820204. WE ALSO FOUND A CRACK OF 0.008 INCH IN THE NOSE BARREL, PN 99-820100-5, WHERE IT LOOKED LIKE IT HAD BEEN REPAI RED IN THE PAST. WE ALSO FOUND A CRACK OF 0.020 INCH IN THE V BRACE, PN 99-810028-989, OF THE LT LANDING GEAR. 1 L 7 2 4T A14CE 20081126 EA 2008 11 26 VJ1R20081118001 1 20081107 G 3810 500120701 WATER HEATER CNDAIR CL600 CL6002B16 1900305 EA ZONE 900 OVERTEMP B VJ1R B A H EMER. DESCENT UNSCHED LANDING DEACTIVATE SYST/CIRCUITS M B OVER TEMP SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 SW 05 CGQWI 5016 ACFT AT CRUISING ALTITUDE WHEN A PASSENGER ADVISED THE CREW THAT THEY COULD ODOR SOMETHING BURNING IN THE CABIN AREA. TH E CREW DECLARED AN EMERGENCY AND DIVERTED. AFTER LANDING, THE PROBLEM WAS DETERMINED TO BE THE LAVATORY WATER HEATER HAD OVER HEATED CAUSING THE HEATER BLANKET TO EMIT SMOKE AND FUMES. THE WATER HEATER SYS WAS DISABLED BY PULLING THE SYS CI RCUIT BREAKER AND THE ACFT RETURNED TO DEPARTURE. THIS IS THE THIRD SUCH INCIDENT INVOLVING CANADIAN REGISTERED AIRCRAFT . THE WATER HEATERS WERE UTILIZED FROM 1981 TO 1997 IAW STC SA4370SW IN APPROX 200 NEW ACFT EXECUTIVE INTERIOR INSTALLA TIONS. THERE ARE POSSIBLY (2) PER INTERIOR ONE LOCATED BEHIND THE GALLEY AND ONE LOCATED BEHIND THE LAVATORY VANITY. A C 2 L 7 2 4F RT A21EA 2008041400041 20080414 00041 2008 4 14 WL7R040208001 4 20080402 G 2564 HOUSING EMB 135 EMB135KL 3260302 SO LIFE RAFT MISINSTALLED B WL7R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 15 2 THE CONFIGURATION BETWEEN THE FIRING HEAD BELL HSG AND THE LINK VALVE ARE NOT LOCATED PROPERLY. THIS CAUSES THE LENGTH OF THE FREE LANYARD TO THE LINK VALVE TO BE REDUCED. THIS MAY CAUSE THE LIFE RAFT TO NOT DEPLOY IN THE SECONDARY METHOD FOR INFLATION VERSUS ACTIVATING THE PRIMARY INFLATION METHOD, THE RIPCORD HANDLE. 2 L 7 2 4F RT T00011AT 2008040400007 20080404 00007 SO 2008 4 4 WS9R030608001 2 20080306 G 8530 AEC631397 CYLINDER BEECH 36 A36 1151604 CE CONT O550 IO550B SO ENGINE CRACKED B WS9R K NONE O OTHER IN INSP/MAINT 1 NM 07 205 814500 CRACK BETWEEN 3RD AND 4TH CYLINDER HEAD, COOLING FIN. 1 L 7 1 3O 3 O 3A15 E3SO 2008040400011 20080404 00011 SO 2008 4 4 WS9R031108001 2 20080311 G 8530 CYLINDER HEAD CESSNA 180 180C 2072608 CE CONT O470 O470L 17026 SO ENGINE CRACKED B WS9R K NONE O OTHER IN INSP/MAINT 1 NM 07 001 069693R VISUAL INSPECTION OF THE CYLINDER AS IT WAS RECEIVED FROM THE MFG, REVEALED CRACKED FINS NEAR THE FUEL INJECTOR NOZZLE. 1 H 7 1 3O 3 O 5A6 E273 2008040400012 20080404 00012 EA 2008 4 4 WS9R031908001 2 20080319 G 8530 AEL14995 RETAINER PIPER PA28 PA28* SO LYC O360 O360A4M 41514 EA CYLINDER BROKEN B WS9R K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 L2841136A DISCOVERED THAT ALL (4) OF THE PUSH ROD TUBE RETAINERS WERE BROKE UPON REMOVING THE ROCKER BOX COVERS. THIS ENGINE HAD JUST BEEN OVERHAULED AND HAS TEST CELL TIME ONLY. 1 L 7 1 3O 3 O 2A13 E286 2008040100120 20080401 00120 NM 2008 4 1 Y5CR200700003 1 20080122 G 6200 369D25351 SPRAG CLUTCH DOUG MD500 MD500E 3027372 NM MAIN ROTOR BROKEN B Y5CR K NONE O OTHER IN INSP/MAINT 1 WP 05 760 DURING A 300HR. INSPECTION ON THE O/R CLUTH THE CUSTOMER FOUND A BROKEN SPRAG CLIP ON THE SPRAG ASSY. 1 G 7 2 3U NC 20080520 NM 2008 5 20 Y5CR200700004 1 20080501 G 6320 369D2512311 BEVEL GEAR DOUG DOUG MD500 MD500E 3027372 NM M/R TRANSMISSION BROKEN B Y5CR K NONE O OTHER IN INSP/MAINT 1 WP 05 616 3668 M/R TRANSMISSION GEAR HAS BROKEN TOOTH. 1 G 7 2 3U NC 2008040300044 20080403 00044 WP 2008 4 3 YZ4R200800001 1 20080222 G 2620 3260007 EXTINGUISHER DOUG DC3 DC3CR183090C 3021466 WP PWA PT6 PT6* 52043 EA INOPERATIVE B YZ4R O OTHER O OTHER NR NOT REPORTED 1 EA 39 300BF 26744 FIRE EXTINGUISHER DID NOT ACTIVATE. THE FIRE EXTINGUISHER IS FILLED WITH 4.5 POUNDS OF HALON 1301 AND PRESSURIZED TO 600 PSIG WITH DRY NITROGEN. THE CONTENTS ARE HELD IN THE CYLINDER BY A PLUG VALVE, PN 13038 WITH AN O-RING SEAL. THIS PLUG VALVE IS COMPRESSED BY THE HOUSING ASSY, PN 33370004. THE HOUSING ASSY IS THREADED INTO THE STEM, PN 31840000. THE DISCH ARGE OUTLET IS BETWEEN THE HOUSING ASSY AND STEM. THE OUTLET ASSY SWIVELS ABOUT THE STEM AND HOUSING ASSY FOR ALIGNMENT AT TIME OF INSTALLATION IN AN AIRCRAFT. WHEN THE FIRE EXTINGUISHER IS FILLED, THE PLUG VALVE AND HOUSING ASSY ARE IN CO MPRESSION. THE HOUSING ASSY IS MFG WITH VARIOUS MACHINED GROOVES AND IS DESIGNED FOR THE COMPRESSIVE FORCES. WHEN THE CA 2 L 7 2 4R 3 T A669 E2NE 2008012200061 20080122 00061 CE 2008 1 22 ZB0R20080001 1 20080111 G 2842 S35942 SENSOR CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA FUEL QTY INTERMITTENT B ZB0R O OTHER N FALSE WARNING CR CRUISE 1 EA 39 272RP 420 40 172S8405 RT FUEL QUANTITY INTERMITTENT AT HIGH FUEL LEVELS. 1 H 7 1 3O 3 O NT 3A12 1E10 2008012200056 20080122 00056 CE 2008 1 22 ZB0R20080002 1 20080111 G 2842 S35942 SENSOR CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA FUEL QTY INTERMITTENT B ZB0R O OTHER N FALSE WARNING CR CRUISE 1 EA 39 963AC 226 45 172S8259 RT FUEL QUANTITY INTERMITTENT AT HIGH FUEL LEVELS. 1 H 7 1 3O 3 O NT 3A12 1E10