20080325002572008032500257CE 2008 3 25 0000H2484 120080318G2820 LINE BEECH 35 V35 1151538CE CONT O550 IO550B SO FUEL SYSTEM CHAFED B WS9RK NONE O OTHER ININSP/MAINT 1 NM07363BC 3 D9763 297203R FUEL LINE MOUNTED ON FIREWALL FABRICATED PER STC SA8676SW WAS CHAFING THE ENGINE TAILPIPE. 1L71 3O3 O 3A15 E3SO 20080403000902008040300090CE 2008 4 3 01030413 120080103G3242314901 BRAKE ASSY BFGOODRICH CESSNA500 560CESSNA 2076750CE MLG LOCKED B PAZRO OTHER E VIBRATION/BUFFET LDLANDING 1 CE03561JS 2290 5600413 UPON LANDING THE AIRCRAFT YAWED TO THE RIGHT AND IN OVERCOMPENSATING THE AIRCRAFT THEN STARTED A SIDEWAYS DRIFT ENOUGH THAT THE LEFT MAIN TIRE FAILED. IT WAS FOUND THAT ONE RIGHT HAND BRAKE STATOR WAS LOCKED AND HAD GROUND THE WHEEL FLAT AND 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. 2L72 4F RTA22CE 20080410002602008041000260EU 2008 4 10 03252008 120080325G3233D52177 HOLDER MESSIER AMD FALC20FALCON200 2730150EU ACTUATOR BROKEN B O OTHER KJ FLUID LOSS WARNING INDICATION LDLANDING 1 SW05 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 WERE MODIFIED AND IDENTIFIED SRD IAW THE S/B. 2L72 4F RTA7EU 20080313000422008031300042SO 2008 3 13 115301 120080218G49101159AC30551103 DUCT GULSTMG1159 GIV 3980115SO APU INLET CRACKED E CLWAK NONE O OTHER ININSP/MAINT 1 SW05589HM6464 1153 A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM). 2L72 4F RTA12EA 20080313000442008031300044SO 2008 3 13 115302 120080218G49101159AC30551103 DUCT GULSTMG1159 GIV 3980115SO APU INLET CRACKED E CLWAK NONE O OTHER ININSP/MAINT 1 SW05589HM6464 1153 A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM). 2L72 4F RTA12EA 20080219000672008021900067CE 2008 2 19 20080101 120080118G2752505212234 ACTUATOR BEECH 90 C90 1152913CE PWA PT6 PT6A21 52043EA T/E FLAP CRACKED B K NONE O OTHER ININSP/MAINT 1 SW99 LJ833 RT OB FLAP ACTUATOR ASSY, PISTON TUBE CRACKED 100 PERCENT IN DEPTH, 100 PERCENT ENTIRE LENGTH OF TUBE. CRACK RUNS PARALLEL TO TUBE . 1L72 3T4 T 3A20 E4EA 20080508001162008050800116SO 2008 5 8 20080420001 120080420G7810 BRACKET MAULE MX7 MX7180A 5460186SO LYC O360 O360* 41514EA ENGINE EXHAUST CRACKED C C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 SO16 ON TAKE-OFF, 50 FEET, PARTIAL POWER LOSS (2,500+ RPM TO 1,100 RPM) AND ENGINE ROUGHNESS. ABORTED TAKE-OFF. WHEN CARBURATOR 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 HEAT. ENTIRE BRACKET WAS ABOUT 12 INCHES LONG. THE 1 INCH LONG PIECE OF THE BRACKET BROKE OFF AND MADE ITS WAY DOWN CARB HEAT DUCTING INTO MIXING CHAMBER OF MUFFLER, UPSTREAM OF VENTURI. BASED ON ENGINE OPERATIONS, BELIEVE PIECE HAD BROKEN F1H71 3O3 ONC3A23 E286 20080519 CE 2008 5 19 20080506FA001 120080506G324610320400AN53 BOLT PARKERHANFIN RAYTHN36 G36 7150061CE RT MLG WHEEL SHEARED B K NONE O OTHER ININSP/MAINT 1 CE07222GL479 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 LANDING 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 WHEELS 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 CHECKE1L71 3O RT3A15 20080701 EA 2008 7 1 2008F00016 220080415G8500 ENGINE GIPPLDGA8 GA8 3900102EU LYC O540 IO540K1A5 41532EA FAILED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 SO237508M 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) 1H71 3O3 ONT 1E4 20080811 CE 2008 8 11 2008F00019 120080715G3260A46270 SWITCH CESSNA500 550 2076604CE MLG OUT OF ADJUST D A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 EA68187JN 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 BE OUT OF ADJUSTMENT. THE SWITCH WAS THEN ADJUSTED IAW MM AND RETURNED TO SERVICE. (K) 1L72 4F A22CE 20080811 GL 2008 8 11 2008F00020 120080711G6100 ROD CIRRUSSR SR20 05628AJGL CONT O360 IO360ES SO PITCH CHANGE MISINSTALLED W O OTHER W INADEQUATE Q C NRNOT REPORTED 1 SW99554PG 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 PITCH CHANGE ROD WAS NOT REMOVED. ON FLIGHT TEST OF THE AC, ENGINE OVERSPEED WAS NOTED AT TAKEOFF TO 2850 RPM, NO SIGNIFICANT LOSS OF OIL PRESSURE WAS NOTED. THE PILOT THROTTLED BACK TO REDUCE PROPELLER SPEED TO LESS THAN 2700 RPM ( WITHIN PERMITTED LIMITATIONS) ENGINE POWER WAS REDUCED TO 48 PERCENT AT THIS POINT AND THE ENGINE SUBSEQUENTLY STOPPED. THE PILOT RESTARTED THE ENGINE, SLIGHTLY EXCEEDING 2700 RPM FOR A SHORT PERIOD. THE PILOT RETURNED THE AIRCRAFT TO BASE, LANDING SAFELY AND REPORTED THE INCIDENT TO THE MAINT MGR. ON INVESTIGATION THE PROP WAS REMOVED AND THE PROTECTIVE CAP WAS I1L71 3O3 ONTA00009CHE1CE 20081110 EA 2008 11 10 2008F00024 220081001G74144371 MAGNETO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE DAMAGED B K NONE O OTHER ININSP/MAINT 1 CE07227BH 172S10662 L33887L2A EXCESSIVE MAGNETO DROP DURING RUNUP AND MAGNETO CHECK. 100 RPM DIFFERENTIAL BETWEEN LT AND RT MAGNETO, ALSO RT MAGNETO RUNNING 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 UNUSUAL WEAR ON BOTH DRIVE GEAR AND DISTRIBUTOR GEAR. DRIVE GEAR MATERIAL NOT REMOVED DURING CLEANUP PROCESS FROM INJECTION MOLDING. PIECES WERE COMING OFF INSIDE MAGNETO. EXCESSIVE CAM WEAR FOR 379.9 HRS. CONTACT POINTS FOUND MISALIGNED, BREAKER POINT ARM HAS FALLEN DOWN & IS RIDING ON THE RIDGE ON CAM. RIDGE CREATED BY EXCESSIVE CAM WEAR. CONDITION MAY CAUSE R1H71 3O3 ONT3A12 1E10 20081210 NE 2008 12 10 2008F00025 120081113G2612 PROBE SKRSKYS76 S76C 8143008NE FIRE WARNING MALFUNCTIONED G K NONE N FALSE WARNING CRCRUISE 1 EA6385PS 760489 NUMBER 2 ENGINE HAD A FIRE CAUTION WARNING LIGHT ILLUMINATE WITH HORN FOR TWO SECONDS. THIS OCCURRED TWICE DURING THE FLIGHT. WHEN THE MECHANICS TRIED TO TROUBLESHOOT THE PROBLEM, COULD NOT DUPLICATE IT. TO FURTHER TROUBLESHOOT, THE AFT NR 1 & 2 FIRE PROBES P/N 76306-07902-104 WERE SWAPPED TO SEE IF THE PROBLEM RE-OCCURRED AND FOLLOWED THE PROBE. 1G72 3U NCH1NE 20090105 EU 2009 1 5 2008F00026 120081216G5311117223121151 FRAME BOLKMS117 BK117B1 5626012EU ZONE 200 CRACKED B K NONE O OTHER ININSP/MAINT 1 GL19330SL 7216 DURING INSP FOUND SPIDER CRACKS AROUND 1 RIVET ON THE DECK UNDER THE TANDEM HYD PACK. FURTHER INSP FOUND 2 FRAMES CRACKED UNDER THE HYD DECK. 1G72 3U H13EU 20090106 EU 2009 1 6 2008F00027 120081215G7797MS3126F1415S CONNECTOR BRAERODH125 HS125700A 4230170EU N1 INDICATOR DEFECTIVE H O OTHER O OTHER NRNOT REPORTED 1 SO19411P 117441070 549E ON NOVEMBER 23, 2008, THE NR 2 ENGINE N1 GAUGE DIGITAL PORTION FAILED. THE MALFUNCTION WAS TRACED TO A DEFECTIVE CONNECTOR AT THE GAUGE. 2L72 4F A3EU 20080111002612008011100261SO 2008 1 11 2008FA0000003 120080102G321339489003 STRUT PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360RB 17025CE MCAULY3AF32C3AF32C512 GL RT MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 SO0169BP 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 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 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 APPROVAL ON BLENDING CRACKED AREA OUT AND AGAIN REQUEST DENIED. FOUND ANOTHER LOWER STRUT IN A SALVAGE YARD WHICH WE PURCHASED ONLY TO FIND THIS STRUT ALSO WAS CRACKED IN THE EXACT SAME SPOT. ALSO I NOTED THAT THE CASTING VARY IN THICKNESS UPTO 1L72 3O3 O A7SO E9CE 5 CP22EA 20080110000122008011000012SO 2008 1 10 2008FA0000004 120080102G321339489003 STRUT PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360RB 17025CE MCAULY3AF32C3AF32C512 GL RT MAIN GEAR CRACKED D K NONE O OTHER ININSP/MAINT 1 SO0169BP 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 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 APPROVAL ON BLENDING CRACKED AREA OUT AND AGAIN REQUEST DENIED. FOUND ANOTHER LOWER STRUT IN A SALVAGE YARD WHICH WE PURCHASED ONLY TO FIND THIS STRUT ALSO WAS CRACKED IN THE EXACT SAME SPOT. THIS STRUT CAME OFF A MODEL PA34-21L72 3O3 O A7SO E9CE 5 CP22EA 20080114000752008011400075CE 2008 1 14 2008FA0000010 120080104G3213390810001 STRUT RAYTHN390 390 7150030CE WILINTFJ44 FJ442A GL LT MLG LEAKING B K NONE K FLUID LOSS ININSP/MAINT 1 CE09701KB30 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 SEALS AND METAL FILLINGS IN INNER BARREL OF STRUT. 1L72 3F4 FRTA00010WIE3GL 20080114000742008011400074CE 2008 1 14 2008FA0000011 120080104G3213390810001 STRUT RAYTHN390 390 7150030CE WILINTFJ44 FJ442A GL RT MLG LEAKING B K NONE K FLUID LOSS ININSP/MAINT 1 CE09701KB30 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 SEALS AND METAL FILLINGS IN INNER BARREL OF STRUT. 1L72 3F4 FRTA00010WIE3GL 20080111002972008011100297EA 2008 1 11 2008FA0000013 220080102G74146393 MAGNETO GULSTM500 500S 0141107SW LYC O540 IO540E1B5 41532EA HARTZLHCC3Y HCC3YR GL ENGINE WORN C D RETURN TO BLOCK L NO TEST TXTAXI/GRND HDL 1 SO1451RF 50 50 CAM LOBE INSIDE MAG THAT OPENS AND CLOSES POINTS WORN OUT. 1H72 3O3 O 6A1 1E4 5 CP25EA 20080114000302008011400030CE 2008 1 14 2008FA0000018 120080108G2701 YOKE CESSNA177 177B 2073708CE LYC O360 O360* 41514EA MISINSTALLED D K NONE W INADEQUATE Q C ININSP/MAINT 1 GL0930673 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 1767037-2 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. 1H71 3O3 O A13CE E286 20080122000462008012200046EU 2008 1 22 2008FA0000036 120080114G3210DIN47108VERZ RETAINING CLIP DIAMONDA42 DA42 2990004EU DOWNLOCK PIN MISSING B K NONE O OTHER ININSP/MAINT 1 SO15966WW13 13 42AC106 DURING PREFLIGHT THE PILOT NOTICED THAT THE MLG DOWNLOCK PIN (PN-D60-3237-11-34) HAD NO RETAINING CLIPS(PN-DIN471-08-VERZ). THE GROOVES IN THE PIN ARE VERY SHALLOW AND ALLOW THE CLIPS TO MIGRATE OFF. 1L72 3I RTA57CE 20080122001942008012200194SO 2008 1 22 2008FA0000041 120080109G7120 MOUNT PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA LT ENGINE CRACKED B B2ERK NONE E VIBRATION/BUFFET ININSP/MAINT 1 EA2325EL 28R7837087 ENGINE MOUNT FOUND CRACKED AT BOTTOM LT WHERE SHOCK MOUNT ATTACHES. (K) 1L71 3O3 O 2A13 1E10 20080212002362008021200236EA 2008 2 12 2008FA0000043 220080111G8520600050507 PUSHROD PIPER PA60 PA60602P 7106015NM LYC O540 IO540* 41532EA ENGINE CORRODED D K NONE O OTHER ININSP/MAINT 1 GL25700LG 608265043 THE AREA IN WHICH THE CORRODED SECTION OF THE PUSHROD ASSY IS LOCATED IS PRONE TO EXHAUST CONTAMINATION SINCE IT IS DIRECTLY 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 CORROSION. INSPECTION OF THIS AREA IS ACCESSIBLE THROUGH THE WING FLAP ACTUATOR ACCESS PANEL. SB 600-122 ADDRESSES THIS SUBJECT. (K) 1M72 3O3 ORTA17WE 1E4 20080212002372008021200237EA 2008 2 12 2008FA0000044 220080111G8520600050507 PUSHROD PIPER PA60 PA60601P 7106012NM LYC O540 IO540* 41532EA ENGINE CORRODED D K NONE O OTHER ININSP/MAINT 1 GL2525RH 2446 61P066979633 THE AREA IN WHICH THE CORRODED SECTION OF THE PUSHROD ASSY IS LOCATED IS PRONE TO EXHAUST CONTAMINATION SINCE IT IS DIRECTLY BEHIND THE ENGINE EXHAUST PIPE OUTLETS. THIS 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 CORROSION. SB 600-122 ADDRESS THIS SUBJECT. INSPECTION IS DONE THROUGH FLAP ACTUATOR ACCESS PANEL. (K) 1M72 3O3 ORTA17WE 1E4 20080212002392008021200239SO 2008 2 12 2008FA0000046 120080104G3297153615 WIRE PIPER PA32 PA32R301T 7103220SO LYC O540 TIO540* 41532EA MLG FAILED D SNSRO OTHER O OTHER NRNOT REPORTED 1 GL13878BT446 3257402 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT. SILICONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT. NEEDS BETTER WIRE AND ROUTING. (K) 1L71 3O3 O A3SO E14EA 20080212002402008021200240SO 2008 2 12 2008FA0000047 120080109G3297153615 WIRE PIPER PA32 PA32R301T 7103220SO LYC O540 TIO540* 41532EA MLG FAILED D SNSRK NONE O OTHER ININSP/MAINT 1 GL135354V528 3257298 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT. SILICONE TYPE WIRE COATING TENDS TO HOLE WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT. NEEDS BETTER WIRE AND ROUTING. (K) 1L71 3O3 O A3SO E14EA 20080131002882008013100288SO 2008 1 31 2008FA0000048 120080104G3297153615 WIRE PIPER PA32 PA32R301T 7103220SO LYC O540 TIO540* 41532EA DOWNLOCK SWITCH FAILED D SNSRK NONE O OTHER ININSP/MAINT 1 GL135354V 3257298 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT. SILICONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT. NEEDS BETTER WIRE AND ROUTING. (K) 1L71 3O3 O A3SO E14EA 20080212002412008021200241SO 2008 2 12 2008FA0000049 120080111G3297153615 WIRE PIPER PA32 PA32R301T 7103220SO LYC O540 TIO540* 41532EA MLG FAILED D SNSRO OTHER O OTHER NRNOT REPORTED 1 GL13999TC 3257356 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT. SILICONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT. NEEDS BETTER WIRE AND ROUTING. (K) 1L71 3O3 O A3SO E14EA 20080212002422008021200242SO 2008 2 12 2008FA0000050 120080104G3297153615 WIRE PIPER PA32 PA32R301T 7103220SO LYC O540 TIO540* 41532EA MLG FAILED D SNSRK NONE O OTHER ININSP/MAINT 1 GL13999TC249 3257356 MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT. SILICONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT. NEEDS BETER WIRE AND ROUTING. (K) 1L71 3O3 O A3SO E14EA 20080212002452008021200245CE 2008 2 12 2008FA0000051 120080107G2752991434446 FLEX DRIVE CESSNA750 750 2076810CE ALLSN AE3007AE3007C GL T/E FLAP WORN B CNQRA UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CE07953QS 7500153 AIRCRAFT EXPERIENCED A FLAP FAIL MESSAGE AFTER TAKEOFF, DIVERTED FOR REPAIR AND THE PILOT ELECTED TO DECLARE AN EMERGENCY 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) 2L72 4J4 FRTT00007WITE6CH 20080131002962008013100296CE 2008 1 31 2008FA0000052 120080116G3060 BOOT BEECH 60 A60 1153604CE LYC O541 TIO541* 41536EA PROPELLER SEPARATED B PZ4RK NONE D INFLIGHT SEPARATION ININSP/MAINT 1 GL114445W P245 A PROPELLER CAME IN FOR REPAIRS WHICH NECESSITATED THE INSTALLATION OF NEW DEICE BOOTS ON ALL 3 BLADES. THE PROP WAS LATER 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 OCCURRED 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 PRECAUTION, THE ADHESIVE WAS REMOVED FROM USE EVEN THOUGH NO DISCREPANT CONDITION COULD BE FOUND. FACILITY VISITED LOCATION1L72 3O3 O A12CE E10EA 20080131002922008013100292CE 2008 1 31 2008FA0000053 120080117G21341303687 PRESSURE SENSOR LEAR 35 35A 5170602CE GARRTTTFE731TFE731* 01518WP AFT BAGGAGE MALFUNCTIONED E B EMER. DESCENT J WARNING INDICATION CLCLIMB 1 SO1155FN 11587 202 LOSS OF CABIN PRESSURE AT 25K FT. PRESSURE SENSOR MALFUNCTIONED 2L72 4F4 F A10CE E6WE 20080131002942008013100294CE 2008 1 31 2008FA0000056 120080123G5514 ATTACH BOLT CESSNA500 560CESSNA 2076750CE PWA JT15 JT15* 52060NE HORIZONTAL STAB UNDERTORQUED B HSRRK NONE O OTHER ININSP/MAINT 1 NM05570EJ 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 ALL 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. 2L72 4F4 TRTA22CE E1NE 20080129000042008012900004SO 2008 1 29 2008FA0000057 120080118G7603455322 THROTTLE CABLE PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA INFLT SEPARATIONB A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 SO15701ER4192 82 2844053 DURING FLIGHT, THE CREW EXPERIENCED A SEPARATION OF THE THROTTLE CABLE. THE POWER SETTING ALLOWED THEM TO MAINTAIN ALTITUDE 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 HOUSING JUST AFT OF THE FUEL SERVO. THERE IS NO TIME/LIFE LIMIT ON THESE CABLES, HOWEVER THE OPERATOR WILL NOW CHANGE THE CABLES DURING EACH ENGINE CHANGE. 1L71 3O3 O 2A13 1E10 20080131002952008013100295NE 2008 1 31 2008FA0000058 220080123G72000319008000 ENGINE UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIUS2F 60010NE MAKING METAL B A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 SW01146CB173 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. 1G72 3U3 UNCR0001RD E34NE 20080131003032008013100303EA 2008 1 31 2008FA0000062 220080102G73142B664 PUMP PIPER PA31 PA31350 7103110SO LYC O540 TIO540* 41532EA FUEL SYSTEM INOPERATIVE D A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 SO05202TC 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 CALLED 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 FOR FLIGHT ABOVE 15,000 FT MSL AND CAN BE DEFERRED IAW PART 91 MEL. AC WENT TO DEPART AIRPORT AND THE LT ENGINE LOST POWER AGAIN DURING THE TAKEOFF ROLL AT ABOUT 40 KNOTS OF AIRSPEED. TROUBLESHOOTING OF ENGINE FUEL PUMP, FUEL NOZZLES REVEAL1L72 3O3 O A20SO E14EA 20080212002592008021200259CE 2008 2 12 2008FA0000063 120080116G30604E11883 BOOT BEECH 60 A60 1153604CE LYC O541 TIO541* 41536EA HARTZLHCF3Y HCF3YR2 GL PROPELLER DEBONDED B PZ4RO OTHER O OTHER NRNOT REPORTED 1 GL114445W4 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 STATED THAT THE GLUE USED TO ADHERE THE BOOT HAD FAILED AFTER REVIEWING PHOTOS SENT TO HIM. IF THIS IS THE CASE, A RECOMMENDATION OF FINDING OUT LOT NUMBER OF ADHESIVE, AND RECALLING ANY WORK DONE USING THIS LOT NUMBER. (K) 1L72 3O3 O A12CE E10EA 5 CP31EA 20080131002892008013100289CE 2008 1 31 2008FA0000066 120080122G3411 FITTING CESSNA206 T206H 2073303CE LYC O360 O360E1A6D 42305EA STATIC SYS FAILED D K NONE O OTHER NRNOT REPORTED 1 NE012095S 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. 1H71 3O3 ORTA4CE E286 20080204001062008020400106 2008 2 4 2008FA0000068 120080130G6500538715 SHAFT TAIL ROTOR CRACKED B K NONE O OTHER ININSP/MAINT 1 WP23 ONE PIECE TRANSVERSE CRACK AROUND THE AREA OF PART THAT HAD LONGITUDINAL INDICATIONS (ORIGIN UNKNOWN BUT POSSIBLY RELATED TO STRESS, FATIGUE OR WEAR), OTHER 4 PIECES ONLY WITH THE SAME LONGITUDINAL INDICATIONS. 20080204001082008020400108EU 2008 2 4 2008FA0000069 120080123G5510T700A5510065000 HINGE SOCATATBM TBM700 8682000EU STABILIZER CRACKED B K NONE O OTHER ININSP/MAINT 1 EA13800GS857 100 149 HINGE FOUND CRACKED IN AREA OF CONCERN IDENTIFIED IN AD 99-07-11, PREVIOUS INSPECTION 100 HOURS EARLIER SHOWED NO SIGN OF CRACKING. 1L71 3T RTA60EU 20080204001022008020400102EU 2008 2 4 2008FA0000070 120080131G5280D605287300 HINGE DIAMONDA42 DA42 2990004EU MLG DOOR BROKEN B N3XRO OTHER E VIBRATION/BUFFET LDLANDING 1 SO15902ER195 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 AIRCRAFT HAD CRACKS DEVELOPING AT THE POINT OF FRACTURE OF THE DAMAGED AIRCRAFT. ALL OF THE HINGE POINTS ON ALL OF THE AIRCRAFT WILL BE CHANGED. 1L72 3I RTA57CE 20080212000382008021200038NM 2008 2 12 2008FA0000071 120080204G5220 LANYARD AMD FALC50FALCON2000 2730170NM CFE CFE73811B NE EMERGENCY WINDOWMISSING B CWQDK NONE O OTHER ININSP/MAINT 1 GL05275QS 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 THE ASSOCIATED WIRING MOUNTED ON THE COVER AND IN THE WINDOW ASSY. (K) 2L72 4F4 FRTA50NM E44NE 20080212000372008021200037NE 2008 2 12 2008FA0000072 220080111G72501808M15G03 SUPPORT CFMINT AIRBUS320 A320* EU CFMINTCFM56 CFM565B42P 13013NE HPT NOZZLE ERODED B QEMYK NONE O OTHER ININSP/MAINT 1 EA35 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 SECTION OF THE COMPONENT, JUST AFT OF THE FWD FLANGE AND ADJACENT TO THE NR 22 AND 23 BOLT HOLES (CLOCKWISE FROM TDC, ALF) THE CAUSE OF THE EROSION IS UNKNOWN. CIRCUMFERENTIAL EROSION TO THE SUPPORT BODY OF THE FINS IS COMMON BUT LOCALIZED EROSION, AS SEEN IN THIS INSTANCE HAS NOT BEEN SEEN PREVIOUSLY. ALL AFFECTED PARTS ARE SCHEDULED FOR RETURN TO MFG FOR FAIL2L72 4F4 FRTA46NM 20080212000352008021200035SO 2008 2 12 2008FA0000073 120080114G534162448003 ATTACH FITTING PIPER PA28 PA28151 7102805SO LYC O320 O320* 41508EA FUSELAGE CORRODED D K NONE O OTHER ININSP/MAINT 1 EA0144542 287415662 THIS FUSELAGE REAR WING ATTACH FITTING WAS BEING REPLACED DUE TO CORROSION PITTS ON FRONT SURFACE. UPON REMOVAL SOME SEVERE PITTING WAS NOTED JUST IB OF THE .3125 INCH WING ATTACH BOLT HOLE ON THE REAR SIDE OF THE FITTING. THIS AREA IS EXPOSED TO OUTSIDE AIR AND MOISTURE AND IS LOCATED IN A DIFFICULT AREA TO INSPECT. THIS ARA IS ALSO MORE CRITICAL IN RELATION 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) 1L71 3O3 O 2A13 E274 20080212000322008021200032SO 2008 2 12 2008FA0000074 220080115G8530AEC642068 CYLINDER CESSNA182 182H 2072718CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL NR 1 DAMAGED B MS2RK NONE O OTHER ININSP/MAINT 1 CE091928X247 18256028 288449R 822386 WHILE PERFORMING A COMPRESSION CHECK TO FIND AN OIL LEAK, FOUND NR 1 CYLINDER WITH O COMPRESSION. PULLED CYLINDER OFF AND FOUND THE PLATING ON THE CYLINDER LOOSE AND FLAKING OFF. (K) 1H71 3O3 ONT3A13 E273 5 CP3EA 20080220000262008022000026SO 2008 2 20 2008FA0000077 220080207G74146310 CAM BEECH 58 58 1152740CE CONT O550 IO550C SO MAGNETO WORN B D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 WP27878JM444 444 TH2065 690181AND6 100 RPM MAGNETO DROP ON PRE-FLIGHT RUN-UP. INSPECTED ALL (4) 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. MAGNETOS, SN'S: 06121306, 06121346, 06120367, AND 06121304. 1L72 3O3 O 3A16 E3SO 20080317002562008031700256EU 2008 3 17 2008FA0000078 120080125G2910GCH1004 HYDRAULIC SYSTEM UROCOPEC120 EC120B 8680987EU CONTAMINATED D K NONE J WARNING INDICATION ININSP/MAINT 1 WP28179CB555 55 1412 HYD POWER PACK PRE-CLOGGING INDICATOR IS DISPLAYED BEFORE FLIGHT. 1G72 3U NCR0001RD 20080319002622008031900262CE 2008 3 19 2008FA0000082 120080218G3397 CAPACITOR BEECH 90 E90 1152914CE PWA PT6 PT6* 52043EA MCAULY4HFR344HFR34C762 NE CABIN LIGHTS BURNED E B EMER. DESCENT B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 SO14662JS LW176 AT CRUISE FL 150, CREW NOTICED SMOKE AND ELECTRICAL ODOR COMING FROM SIDEWALL UNDERNEATH EMERGENCY EXIT. PIC DECLARED EMERGENCY AND LANDED AC WITHOUT FURTHER INCIDENT. UPON INSP OF SIDEWALL UNDER EMERGENCY EXIT, IT WAS NOTICED THAT A SMALL HOLE WHICH APPEARED TO LOOK LIKE A CIGARETTE BURN AT FIRST HAD PENETRATED THROUGH HONEYCOMB MATERIAL AND THE ULTRA SUEDE LINER THAT COVERS THE SIDEWALL. UPON CLOSER INSP BEHIND SIDEWALL, NO ELECTRICAL COMPONENTS OR WIRING ARE LOCATED BEHIND 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. 1L72 3T3 T 3A20 E2NE 6 C3PNE 20080403000402008040300040CE 2008 4 3 2008FA0000084 120080221G29101285094 LINE CESSNA210 T210M 2073451CE CONT O520 TSIO520* 17040SO HYDRAULIC SYS CHAFED D K NONE O OTHER ININSP/MAINT 1 SW15761AV4400 21062110 REPLACED HYDRAULIC TUBE 128509-4 DUE TO CHAFING FROM LONG SCREW IN WRONG LOCATION OF INSPECTION COVER PLATE. THIS WAS FOUND BY INSPECTION AS DESCRIBED IN MFG SEB07-03 AND WHICH HAVE A SUPERSEDED PN AVAILABLE TO NULLIFY THE POTENTIAL PROBLEM. THIS SERIES AND OTHER MODELS SHOULD BE ADDED TO SERVICE BULLETIN APPLICABILITY. 1H71 3O3 O 3A21 E8CE 20080225000042008022500004CE 2008 2 25 2008FA0000085 120080221G29101285094 LINE CESSNA210 T210M 2073451CE HYDRAULIC SYS CHAFED D O OTHER O OTHER NRNOT REPORTED 1 SW15761AV4400 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 NULLIFY THE POTENTIAL PROBLEM. THIS SERIES AND OTHER MODELS SHOULD BE ADDED TO SB APPLICABILITY. 1H71 3O 3A21 20080225000052008022500005CE 2008 2 25 2008FA0000086 120080215G57110411129 SPAR CESSNA150 150G 2071816CE CONT O200 O200* 17020SO WING CORRODED D K NONE O OTHER ININSP/MAINT 1 WP07 3895 15065116 WINGS WERE PREVIOUSLY REMOVED TO FACILITATE TRANSPORTATION. INSP OF THE LT AND RT FWD SPAR BEARING BLOCKS IN THE FUSELAGE (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. THE SAME P/N AND WING ATTACHMENT SYS IS USED ON MOST OF THE AC SERIES HIGH WING AIRCRAFT. 1H71 3O3 O 3A19 E252 20080403000222008040300022CE 2008 4 3 2008FA0000087 120080215G53110411129 SPAR CESSNA150 150G 2071816CE CONT O200 O200* 17020SO WING CORRODED D K NONE O OTHER ININSP/MAINT 1 WP073816J3895 15065116 WINGS WERE PREVIOUSLY REMOVED TO FACILITATE TRANSPORTATION. INSPECTION OF THE LT AND RT FWD SPAR BEARING BLOCKS IN THE FUSELAGE (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. 1H71 3O3 O 3A19 E252 20080402000412008040200041SO 2008 4 2 2008FA0000088 220080207G74146310 CAM BEECH 58 58 1152740CE CONT O550 IO550C SO MAGNETO WORN B D RETURN TO BLOCK RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 WP27878JM444 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. 1L72 3O3 O 3A16 E3SO 20080310003302008031000330CE 2008 3 10 2008FA0000089 120080129G29157629001004001 PRESSURE SWITCH LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE731* 01518WP HYDRAULIC SYS FAILED B WMYRA UNSCHED LANDING O OTHER NRNOT REPORTED 1 SO09444MW2127 131 LT HYDRAULIC PRESSURE SWITCH (S9) FAILED IN FLIGHT, RESULTING IN LOSS OF HYDRAULIC FLUID AND FAILURE OF BOTH LT AND RT HYDRAULIC PUMPS. NECESSITATED A FLIGHT DIVERSION TO AN ALTERNATE AIRPORT WITH AN EMERGENCY DECLARATION. (K) 2L72 4F4 FRTT00008WIE6WE 20080310003322008031000332CE 2008 3 10 2008FA0000091 120080122G3245 TUBE CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA LANDING GEAR FAILED B AW4RO OTHER O OTHER NRNOT REPORTED 1 WP11784WW 17280816 FROM SEPT 7 TO PRESENT, AC HAS EXPERIENCED (3) LANDING GEAR TIRE TUBE FAILURES. FAILURES ALL OCCURRED IN THE SIDEWALL OF 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 BE 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 TUBES (PN 302-013-400 AT 125 HOURS AND 112 HOUR RESPECTIVELY. TUBES WERE FORWARDED TO MFG FOR EVALUATION. EVALUATION IS 1H71 3O3 ONT3A12 1E10 20080310003332008031000333 2008 3 10 2008FA0000092 420080111G2564100102303 LIFE RAFT CABIN UNWANTED DEPLOY D JAVRK NONE O OTHER ININSP/MAINT 1 EA61 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) 20080331000412008033100041GL 2008 3 31 2008FA0000093 320080204G6114 HUB CESSNA188 A188B 2073005CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C98 GL PROPELLER CRACKED B LU4RO OTHER O OTHER NRNOT REPORTED 1 SO19731VX 18803200T 775315 PROPELLER HUB CRACKED. (K) 1L71 3O3 O A9CE E5CE 5 CP3EA 20080310003342008031000334GL 2008 3 10 2008FA0000094 320080204G6114 HUB MCAULY CESSNA337 M337B 2075708CE CONT O360 IO360D 17025SO MCAULY2AF34CD2AF34C61 GL PROPELLER CRACKED D LU4RK NONE O OTHER ININSP/MAINT 1 SO19373AZ 661450 337M0079 RELEVENT INDICATION (CRACKED). (K) 1H72 3O3 ORTA6CE E1CE 5 CP5EA 20080310003352008031000335GL 2008 3 10 2008FA0000095 320080204G6114 HUB MCAULY CESSNA402 402B 207590PCE CONT O520 TSIO520* 17040SO MCAULY3AF32C3AF32C87 GL PROPELLER CRACKED D LU4RK NONE O OTHER ININSP/MAINT 1 SO1995RG 779643 402B0538 RELEVENT INDICATION (CRACKED 2 PLACES). (K) 1L72 3O3 O A7CE E8CE 5 CP22EA 20080310003362008031000336SO 2008 3 10 2008FA0000096 120080128G534386282010 SPAR PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA NLG CRACKED D K NONE O OTHER ININSP/MAINT 1 NM01856ND 4495001 THE SPAR ASSY WAS CRACKED AT THE LT SIDE NOSE GEAR SUPPORT FITTING. THE CRACK RADIATED OUT FROM THE AFT LOWER BOLT ATTACHMENT ( AS VIEWED FROM BELOW THE NOSE STRUCTURE FLOORING) ONCE THE A-FRAME SUPPORT WAS REMOVED, THERE WAS A (2 INCH) CRACK IN THE SPAR WEB (NOT VISIBLE UNTIL THE SUPPORT WAS REMOVED). THE LOWER EXTRUSION HAS BEEN REPLACED WITH NEW AT SOME 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) 1L72 3O3 O A19S0 E286 20080310003462008031000346GL 2008 3 10 2008FA0000099 220080131G723023074076 SCROLL BELL 407 407 1182206SW ALLSN 250C 250C47B GL COMPRESSOR BROKEN D K NONE O OTHER ININSP/MAINT 1 SO0531PB 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 SCROLL. THE OPERATOR CONDUCTS PATROLLING OR POLICE ACTIVITY USING THE AC AND FOUND THE DEFECT WHILE PERFORMING A 100 HR MAINT TASK. THE AFFECTED COMPRESSOR SCROLL WAS COATED WITH SERVETEL WHICH IS AN OEM APPROVED COATING FOR PROTECTION AGAINST CORROSION AND AS INDIDCATED IN THE LOG BOOKS, THIS IS THE 2ND SCROLL TO HAVE BEEN REPLACED. (K) 1G71 3U3 UO H2SW E1GL 20080324004302008032400430CE 2008 3 24 2008FA0000100 120080205G29157629001004001 PRESSURE SWITCH LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP HYDRAULIC SYSTEMFAILED D A UNSCHED LANDING JK WARNING INDICATION FLUID LOSS CRCRUISE 1 SO09444MW 131 APPROXIMATELY 40 MIN IN TO PLANNED FLIGHT, WHILE AT FL410, IN FINAL CRUISE CONDITION, A WHITE ADVISORY CAS MESSAGE APPEARED INDICATING (MAIN HYD QTY LOW). FLIGHT CREW OPENED THE APPROPRIATE CREW CHECKLIST AND FLIGHT MANUAL AND REFERENCED THE 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 PRESSURE. 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 INDICATIO2L72 4F4 FRTT00008WIE6WE 20080319002952008031900295 2008 3 19 2008FA0000101 420080108G2210238006679 YAW DAMPER LEAR 24 24 5170302CE FAULTY B A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 WP01989TL 160 THIS PART FAILED TO OPERATE DURING FIRST FLIGHT, AFTER INSTALLATION, AT CRUISE. 2L72 4J A10CE 20080403000552008040300055 2008 4 3 2008FA0000104 420080224G3197 WIRE HARNESS CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA INSTRUMENT PANELBURNED B K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CE07227BH6 172S10662 WIRING HARNESS BEHIND AUDIO PANEL WAS CHAFING ON BRACKET THAT HELPS SUPPORT STANDBY BATTERY ON THE PFD SIDE AND CAUSED WIRING TO ARC AND BURN (NOTE: HARNESS IS FOR LIGHT DIMMING OF G-1000). FOUND HARNESS PULLED HARD AGAINST BRACKET. THIS CAUSED 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 ASSOCIATED WITH THE LIGHT DIMMING CIRCUIT. THE HARNESS WAS PULLED HARD AGAINST THE STRUCTURE AS TO CHAFE THROUGH THE INSULATION AND ARC/SCORCHED THE STRUCTURE. THE WIRE BURNED THROUGH AND ALSO, DAMAGED OTHER WIRES IN THE HARNESS. HARNESS WAS A1H71 3O3 ONT3A12 1E10 20080331000432008033100043CE 2008 3 31 2008FA0000106 120080211G5340 BRACKET CESSNA500 550 2076604CE VOLT REGULATOR CORRODED B K NONE O OTHER ININSP/MAINT 1 WP21554MB 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. 1L72 4F A22CE 20080331000442008033100044CE 2008 3 31 2008FA0000107 120080209G291098811241 POWERPACK CESSNA210 T210N 2073456CE CONT O520 TSIO520* 17040SO HYD SYSTEM WORN C O OTHER B SMOKE/FUMES/ODORS/SPARKS LDLANDING 1 SW17127TC3309 21063381 SMOKE IN COCKPIT, GEAR NOT FULLY RETRACTED, EXTENDED OK. FOUND HYDRAULIC POWERPACK MOTOR (ORIGINAL) WORNOUT. REMOVED AND REPLACED WITH O/H UNIT. OPS, OK. 1H71 3O3 O 3A21 E8CE 20080331000452008033100045SW 2008 3 31 2008FA0000108 120080227G28415643860 GAUGE MOONEYM20 M20D 5870210SW LYC O360 O360A1D 41514EA HARTZLHCC2Y HCC2YK1 GL FUEL SYSTEM INACCURATE D K NONE N FALSE WARNING ININSP/MAINT 1 GL156608U5103 103 L533036 CH26709E FUEL GAUGE INDICATION IS APPROX 2.5 TO 3 GAL HIGHER THAN WHAT IS IN THE TANK. (K) 1L71 3O3 O 2A3 E286 5 CP920 20080331000482008033100048 2008 3 31 2008FA0000110 420080215G2312 ANTENNA ISRAEL1125 ASTRASPX 4500205EU VHF SYSTEM GOUGED B K NONE O OTHER ININSP/MAINT 1 WP09411MM 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 SKIN. DAMAGE WAS APPARENTLY CAUSED BY IMPROPER REMOVAL OF PREVIOUSLY INSTALLED VHF ANTENNA. REPAIR WAS TO BLEND OUT GOUGES IAW DER EVALUATION. (K) 2L72 4F RTA16NM 20080325000332008032500033GL 2008 3 25 2008FA0000111 120080304G6420ECD00213 BEARING ENSTRMF28 280FX 3300506GL LYC O360 HIO360F1AD 41514EA TAIL ROTOR SEIZED D O OTHER F FLT CONT AFFECTED CRCRUISE 1 NM03285SH1 2120 THE THRUST BEARINGS IN THE TAIL ROTOR BLADE GRIPS ARE OF MATCHED SETS. THESE SETS HAVE A SPECIFIC INSTALLATION ORIENTATION. ORIENTATION OF THESE BEARINGS ARE MARKED WITH A (V). THE (V) IS TO BE ORIENTED TOWARD THE CENTER OF THE TAIL ROTOR SPINDLE HUB. ON THESE SPECIFIC BEARINGS THE (V) WAS MARKED POINTING THE WRONG DIRECTION LEADING TO A REVERSED INSTALLATION CAUSING A SEIZURE OF THE BEARINGS. ALL BEARINGS WERE INSTALLED IN ACCORDANCE WITH ENSTROM SERVICE LETTER 133 DATED JUNE 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. 1G71 3O3 O H1CE 1E10 20080317002642008031700264EU 2008 3 17 2008FA0000114 120080129G2435160SG140Q1XL STARTER GEN UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIUS2F 60010NE ENGINE FAILED D K NONE O OTHER NRNOT REPORTED 1 WP28179CB558 58 1412 STARTER/GENERATOR FAILED TO ENERGIZE. 1G72 3U3 UNCR0001RD E34NE 20080331000522008033100052 2008 3 31 2008FA0000115 420080118G6113C2365 BULKHEAD SNSNCH MAULE MX7 MXT7160 5470204SO LYC O320 O320* 41508EA SNSNCH74D 74DM EA PROP SPINNER CRACKED D K NONE O OTHER ININSP/MAINT 1 SW1157HS 3600 17005C RL1318639A A57306 THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT MOLT HOLES. THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K) 1H71 3O3 O 3A23 E274 5 NP88614 20080331000532008033100053 2008 3 31 2008FA0000116 420080118G6113C2367 BULKHEAD SNSNCH MAULE MX7 MXT7180A 5460187SO LYC O360 O360C4F 42290EA SNSNCH76E 76EM8 EA PROP SPINNER CRACKED D K NONE O OTHER ININSP/MAINT 1 SW11114HS300 21092C L4051336A 37618K THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES. THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K) 1H71 3O3 ONC3A23 E286 5 NP4EA 20080331000542008033100054 2008 3 31 2008FA0000117 420080118G6113C2367 BULKHEAD SNSNCH MAULE MX7 MXT7180A 5460187SO LYC O360 O360C4F 42290EA SNSNCH76E 76EM8 EA PROP SPINNER CRACKED D K NONE O OTHER ININSP/MAINT 1 SW11171HS200 21096C L4089636A THE FWD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES. THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K) 1H71 3O3 ONC3A23 E286 5 NP4EA 20080331000562008033100056 2008 3 31 2008FA0000118 420080118G6113C2367 BULKHEAD MAULE MX7 MXT7180A 5460187SO LYC O360 O360C4F 42290EA SNSNCH76E 76EM8S5 EA FWD SPINNER CRACKED D K NONE O OTHER ININSP/MAINT 1 SW11125HS200 21093C L4056636A 37939K THE FWD BULKHEAD CRACKED THROUGHT THE MOUNT BOLT HOLES. THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K) 1H71 3O3 ONC3A23 E286 5 NP4EA 20080331000572008033100057 2008 3 31 2008FA0000119 420080118G6113C2367 BULKHEAD SNSNCH MAULE MX7 MXT7180A 5460187SO LYC O360 O360C4F 42290EA SNSNCH76E 76EM8 EA PROP SPINNER CRACKED D K NONE O OTHER ININSP/MAINT 1 SW11152HS200 21095C L4081336E 38281K THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES. THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K) 1H71 3O3 ONC3A23 E286 5 NP4EA 20080331000592008033100059GL 2008 3 31 2008FA0000120 120080206G3020 CONTROL ARM DIAMONDA40 DA40 2990002GL LYC O360 O360A4M 41514EA CARB HEAT BROKEN D K NONE O OTHER ININSP/MAINT 1 NM07423FP13 40FC023 CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTAKE. RECOMMEND INSTALLIING THICKER MATERIAL ON CARB HEAT CONTROL ARM LEVER, DIFFERENT WELDING/HEAT TREATING PROCESS, OR DIFFERENT ATTACHMENT PROVISION ALTOGETHER. (K) 1L71 3O3 ONTA47CE E286 20080331000612008033100061GL 2008 3 31 2008FA0000121 120080206G3020D4F732612001 CONTROL ARM DIAMONDA40 DA40 2990002GL LYC O360 O360A4M 41514EA CARB HEAT BROKEN D GO3SK NONE O OTHER ININSP/MAINT 1 NM07418FP31 40FC018 CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTAKE. RECOMMEND INSTALLING THICKER MATERIAL ON CARB HEAT CONTROL ARM LEVER, DIFFERENT WELDING/HEAT TREATING PROCESS, OR DIFFERENT ATTACHMENT PROVISION ALTOGETHER. (K) 1L71 3O3 ONTA47CE E286 20080331000622008033100062CE 2008 3 31 2008FA0000122 120080206G2197 WIRE HARNESS BEECH 90 C90A 1152911CE A/C START CONT MISINSTALLED D K NONE W INADEQUATE Q C ININSP/MAINT 1 CE014764A LJ1161 AIR CONDITIONER NOT COOLING. FOUND WIRING FOR AC START CONTROL PANEL AS WELL AS COMPRESSOR CLUTCH NOT IN PROPER CONFIGURATION IAW WIRING PRINT. AFTER PROPER INSTALLATION OF WIRING AND SUBSEQUENT OPS CHECK, THE MOTOR AND SYS, THE AIR CONDITIONER 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 COMPARTMENT. PROBABLE CAUSE WOULD INDICATE FAILURE OF THE AC START CONTROL PANEL CIRCUITRY THAT SUBSEQUENTLY LEAD TO A NOSE 1L72 3T RT3A20 20080331000632008033100063 2008 3 31 2008FA0000123 420080114G611305502366 BULKHEAD CESSNA172 172H 2072424CE CONT O300 O300* 17022SO PROP SPINNER CRACKED D HE8SK NONE O OTHER ININSP/MAINT 1 CE094987R92 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) 1H71 3O3 ONT3A12 E253 20080325000682008032500068SW 2008 3 25 2008FA0000124 120080114G6220NAS5161A GREASE FITTING BELDEN BELL 212 212 1181420SW M/R HUB BLOCKED W DB5YK NONE O OTHER ININSP/MAINT 1 EA33 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. THIS COULD RESULT IN A LOOSE SPRING IN A ROTATING BEARING. (K) 1G71 4U H4SW 20080325001052008032500105WP 2008 3 25 2008FA0000125 220080212G72108937396 GEAR CASA C212 C212CC 2410204EU GARRTTTPE331TPE33110R 0517 WP GEAR BOX BROKEN W X1NYK NONE O OTHER ININSP/MAINT 1 WP03961BW2170 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 PIECES. 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 2H72 4T4 T A43EU E4WE 20080325001062008032500106NE 2008 3 25 2008FA0000126 220080111G72501808M15G03 SUPPORT CFMINT AIRBUS320 A320* EU CFMINTCFM56 CFM565B4P NE HPT NOZZLE UNSERVICEABLE W QEMYK NONE O OTHER ININSP/MAINT 1 EA35 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 PENETRATION OF THE COMPONENT. THE EROSION WAS LOCATED ON THE SUPPORT BODY SECTION OF THE COMPONENT, JUST AFT OF THE FWD (CLOCKWISE). THE CAUSE OF THE EROSION IS UNKNOWN. CIRCUMFERENTIAL EROSION TO THE SUPPORT BODY OF THE FINS IS COMMON BUT LOCALIZED EROSION, AS SEEN IN THIS INSTANCE HAS NOT BEEN SEEN, PREVIOUSLY. ALL AFFECTED PARTS ARE SCHEDULED FOR RETURN TO MFG FOR FAILURE ANALYSIS. (K) 2L72 4F4 FRTA46NM E38NE 20080331001382008033100138EU 2008 3 31 2008FA0000127 120080206G2497 WIRE AMD FALC50FALCON900 2730160EU GARRTTTFE731TFE731* 01518WP ELECTRICAL DAMAGED B K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 NM09900VL 60 WHILE TROUBLESHOOTING AC ELECTRICAL OUTLETS FOR BEING INOPERATIVE. REMOVED FLOOR PANEL TO ACCESS AC INVERTER AND DETECTED BURNING PLASTIC. FOUND SYSTEM HAD SELF RESETTING CIRCUIT BREAKERS INSTALLED THAT HAD BEEN AND WERE CONTINUING TO RESET AND ALLOWING THE KAPTON WIRE INSULATION AND SPIRAL WRAP TO BURN. ONE OF THE AREAS THAT BURNED WAS ONLY 3 INCHES BELOW 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 INSTANCE. (K) 2L73 4F4 FRTA46EU E6WE 20080331001392008033100139GL 2008 3 31 2008FA0000128 120080215G282251000020 PUMP DIAMONDA40 DA40 2990002GL LYC O360 O360A4M 41514EA FUEL SYS INOPERATIVE D GO3SK NONE O OTHER ININSP/MAINT 1 NM07417FP102 40FC017 AFTER A PREVIOUS FLIGHT, AND BEFORE THE NEXT STUDENTS FLIGHT, THE ELECTRIC FUEL PUMP WAS FOUND TO BE INOPERATIVE. INADEQUATE COOLING IS WHAT WE BELIEVE TO BE THE SOURCE OF THE MALFUNCTIONS. PROVIDE RAM AIR FOR PROPER COOLING OF FUEL PUMP AND MOTOR. (K) 1L71 3O3 ONTA47CE E286 20080331001422008033100142GL 2008 3 31 2008FA0000131 120080307G282251000020 PUMP DIAMONDA40 DA40 2990002GL LYC O360 O360A4M 41514EA FUEL SYS INOPERATIVE D GO3SK NONE O OTHER ININSP/MAINT 1 NM07418FP 40FC018 AFTER A PREVIOUS FLIGHT, AND BEFORE THE NEXT STUDENTS FLIGHT, THE ELECTRIC FUEL PUMP WAS FOUND TO BE INOPERATIVE. INADEQUATE COOLING IS WHAT WE BELIEVE TO BE THE SOURCE OF THE MALFUNCTIONS. PROVIDE RAM AIR FOR PROPER COOLING OF FUEL PUMP AND MOTOR. (K) 1L71 3O3 ONTA47CE E286 20080331001432008033100143GL 2008 3 31 2008FA0000132 120080227G282251000020 PUMP DIAMONDA40 DA40 2990002GL LYC O360 O360A4M 41514EA FUEL SYS INOPERATIVE D GO3SK NONE O OTHER ININSP/MAINT 1 NM07419FP265 40FC019 AFTER A PREVIOUS FLIGHT AND BEFORE THE NEXT STUDENTS FLIGHT, THE ELECTRIC FUEL PUMP WAS FOUND TO BE INOPERATIVE. INADEQUATE COOLING IS WHAT WE BELIEVE TO BE THE SOURCE OF THE MALFUNCTIONS. PROVIDE RAM AIR FOR PROPER COOLING OF FUEL PUMP AND MOTOR. (K) 1L71 3O3 ONTA47CE E286 20080402000402008040200040CE 2008 4 2 2008FA0000137 120080123G3250358250549 ARM BEECH B300 B300B350C CE PWA PT6 PT6* 52043EA STEERING WORN B K NONE O OTHER ININSP/MAINT 1 EA1357SC 6028 FL34 NOSE GEAR STEERING ARM WORN EXCESSIVELY AT ROD END ATTACHMENT POINT FOR STEERING PUSH PULL TUBE. LOSS OF NOSE GEAR STEERING WOULD OCCUR IF ARM WERE TO BREAK. THE ORIGINAL .2500 INCH BOLT HOLE WAS ELONGATED TO A .5 INCH SLOT. THE ARM IS ATTACHED TO THE PILOT'S RUDDER PEDAL TORQUE SHAFT AND IS LOCATED IN A SMALL UNPRESSURIZED PANEL AREA BELOW THE PILOT SIDE FLOORBOARDS. INSPECTIONS ARE OVERLOOKED BECAUSE THIS SEALED PANEL IS NOT OPENED TYPICALLY DURING ROUTINE INSPECTIONS. 2L72 4T3 TRTA24CE E2NE 20080402000132008040200013CE 2008 4 2 2008FA0000146 120080129G322007436051 TORQUE LINK CESSNA182 182G 2072716CE CONT O470 O470* 17026SO ZONE 700 CRACKED C K NONE O OTHER ININSP/MAINT 1 WP0582BG 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) 1H71 3O3 ONT3A13 E273 20080331001752008033100175EU 2008 3 31 2008FA0000148 120080327G6320C632A2103101 HOUSING UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE GEARBOX WORN D K NONE O OTHER ININSP/MAINT 1 SW19179CB622 M569 1412 34224 INPUT BOX HOUSING BEARING WORN. (SHOULDER) 1G72 3U3 UNCR0001RD E34NE 20080401001092008040100109EU 2008 4 1 2008FA0000149 120080227G2497 CONNECTOR DIAMONDA42 DA42 2990004EU THIELTTAE125TAE1250299 EU FUEL RAIL ARCED D O OTHER O OTHER NRNOT REPORTED 1 WP284129M480 42AC068 020201611 CONNECTOR IS NOT MAKING GOOD CONTACT AND CAUSING ARCING. PROBABLE CAUSE IS AUTOMOTIVE QUALITY AND NOT OF THE THREADED TYPE. TO PREVENT OCCURRENCE RECOMMEND USING AVIATION THREADED TYPE PLUG. (K) 1L72 3I3 BRTA57CE E00069EN 20080401001112008040100111CE 2008 4 1 2008FA0000150 120080307G2497S26062 WIRE HARNESS CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MCAULY1C235 1C235LFA GL FLAP MOTOR DETERIORATED D O OTHER O OTHER NRNOT REPORTED 1 CE05467CM 17280859 L2651551A TJ040 UPON INSPECTION OF A PHASE II INSPECTION, IT WAS DISCOVERED THAT THE WIRE BUNDLE MOUNT PN S26062 THAT HOLDS THE FLAP MOTOR WIRE HARNESS HAD DETACHED FROM THE RIB IN THE RT WING AND HAD ALLOWED THE WIRE BUNDLE TO CHAF INTO THE INSPECTION PANEL SUPPORT ON THE WING. THE WIRE BUNDLE HAD (2) WIRES CHAFED THROUGH THE INSULATION AND WAS IN CONTACT WITH THE BARE WIRE. RECOMMEND INSPECTION OF THESE MOUNTS AND REPLACE AS NEEDED, OR ON CONDITION. (K) 1H71 3O3 ONT3A12 1E10 5 NP12EA 20080401001212008040100121EA 2008 4 1 2008FA0000151 220080305G852013B2713485 CRANKSHAFT LYC O360 O360A4A 41514EA ENGINE CRACKED B K NONE O OTHER ININSP/MAINT 1 SW17 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 CRANKCASE. 3 O E286 20080404000012008040400001 2008 4 4 2008FA0000152 120080304G499038809981 PUMP APU OIL FAILED B O OTHER J WARNING INDICATION NRNOT REPORTED 1 SW99 135991468 2 APUS WERE REPORTED LOP AUTO SHUTDOWN. HAVE RECEIVED APU P-195 AND P-141 FROM FOR THE SAME REASON OF REMOVAL. 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 WAS NOTED. DISASSEMBLY OF THE OIL PUMP REVEALED PORT 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. 20080402000432008040200043CE 2008 4 2 2008FA0000153 120080212G2810 CHAIN CESSNA172 172S 2072439CE CONT C85 C8512F 17008SO FUEL CAP LOOSE D O OTHER O OTHER TXTAXI/GRND HDL 1 GL155055Q4413 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 SENDING UNIT LOCKING IT AT A 10 GAL. INDICATION. 1H71 3O3 ONT3A12 E233 20080403000252008040300025CE 2008 4 3 2008FA0000154 120080215G551145A2111XXXX RIB BEECH MU300 400A 1155402CE HORIZONTAL STAB CRACKED B K NONE O OTHER ININSP/MAINT 1 SO13907JE5335 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. 2H72 4F RTA16SW 20080403000262008040300026CE 2008 4 3 2008FA0000155 120080215G551145A2111XXXX RIB BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE HORIZONTAL STAB CRACKED B K NONE O OTHER ININSP/MAINT 1 SO13907JE5335 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. 2H72 4F4 FRTA16SW E25EA 20080403000462008040300046 2008 4 3 2008FA0000156 420080222G25645A320410312 LIFE RAFT AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE731* 01518WP CABIN INOPERATIVE B K NONE O OTHER ININSP/MAINT 1 NM01900KE 1 052 RECEIVED SUBJECT LIFE RAFT FOR ANNUAL INSPECTION FROM REGISTERED OWNER. THE LIFE RAFT WAS RECEIVED BY THIS REPAIR STATION IN A PACKED CONDITION AND IN ITS "AS-REMOVED" CONDITION FROM THE AIRCRAFT. DURING DISASSEMBLY AND PRELIMINARY INSPECTION 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. 2L73 4F4 F A46EU E6WE 20080403000482008040300048 2008 4 3 2008FA0000157 420080108G2210238006679 YAW DAMPER LEAR 24 24 5170302CE ZONE 300 FAULTY B A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 WP01989TL 160 THIS PART FAILED TO OPERATE DURING FIRST FLIGHT AFTER INSTALLATION AT CRUISE. 2L72 4J A10CE 20080403000492008040300049SO 2008 4 3 2008FA0000160 120080225G32450923150 TUBE PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA LT TIRE CUT B O OTHER E VIBRATION/BUFFET LDLANDING 1 GL21359ND118 2842187 UPON LANDING, LT MAIN TIRE DEFLATED UPON DISASSEMBLY TUBE WAS FOUND TO HAVE A SMALL SLIT IN THE OUTSIDE OF THE CIRCUMFERENCE 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 FOLLOWED TO THE LETTER AND PROBLEM STILL EXIST DURING EXTREME TEMP CHANGES EXPERIENCED IN OUR CLIMATE (NORTH DAKOTA). 1L71 3O3 O 2A13 E274 20080403000512008040300051SO 2008 4 3 2008FA0000161 120080225G32450923150 TUBE PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA LT TIRE CUT B O OTHER E VIBRATION/BUFFET LDLANDING 1 GL21359ND118 2842187 UPON LANDING, LT MAIN TIRE DEFLATED. UPON DISASSEMBLY, TUBE WAS FOUND TO HAVE A SMALL SLIT IN THE OUTSIDE OF THE CIRCUMFERENCE 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 FOLLOWED TO THE LETTER AND PROBLEM STILL EXIST DURING EXTREME TEMP CHANGES EXPERIENCED IN OUR CLIMATE (NORTH DAKOTA). 1L71 3O3 O 2A13 E274 20080403000522008040300052EA 2008 4 3 2008FA0000164 220080110G74146393 MAGNETO GULSTM500 500S 0141107SW LYC O540 IO540E1B5 41532EA ENGINE WORN B O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 GL1551RF 100 3298 ENGINE WAS GETTING HARD TO START, CHECKED MAG TIMING AND FOUND LT MAG TIMING OUT OF LIMITS, DISASSEMBLED MAG AND FOUND THE CAM WORN OUT . 100.3 HRS SINCE NEW 1H72 3O3 O 6A1 1E4 20080403000542008040300054EA 2008 4 3 2008FA0000167 220080226G74146393 MAGNETO GULSTM500 500S 0141107SW LYC O540 IO540E1B5 41532EA ENGINE WORN B O OTHER R PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 GL1551RF 81 3298 ENGINE WAS GETTING HARD TO START, CHECKED MAG TIMING AND FOUND LT MAG TIMING OUT OF LIMITS, DISASSEMBLED MAG AND FOUND THE CAM WORN OUT . 81.1 HRS SINCE NEW. 1H72 3O3 O 6A1 1E4 20080403000562008040300056SO 2008 4 3 2008FA0000168 120080226G32450923080 TUBE PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA TIRE FAILED B O OTHER O OTHER TXTAXI/GRND HDL 1 GL21437ND28 2842214 NOSE TIRE FOUND FLAT IN HANGER. DISASSEMBLE FOUND SMALL SLIT IN OUTSIDE CIRCUMFERENCE OF TUBE TYPICAL OF OTHER FLAT TIRES FROM SAME MFG. SAMPLE FAILED TUBES HAVE BEEN RETURNED TO MFG FOR EVALUATION. 1L71 3O3 O 2A13 E274 20080403000612008040300061CE 2008 4 3 2008FA0000169 120080220G2820057313K001301 LINE CESSNA172 172S 2072439CE THIELTTAE125TAE1250299 EU FUEL SYSTEM CRACKED C BA EMER. DESCENT UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 SO191735L3 172S10647 020201880 PILOT WAS FLYING AT 5,500 FEET WHEN THE ENGINE STARTED RUNNING ROUGH. WITHIN MOMENTS THE FADEC (A) LIGHT CAME ON THEN FADEC (B) ILLUMINATED. THE PILOT TRIED TO ACTIVATE THE MANUAL OVERRIDE BUT WAS UNABLE TO PUT OUT THE WARNING LIGHTS. THE RPMS 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 SAFE AND DID NOT REQUIRE ANY SERVICES (FIRE, PARAMEDICS). ATC NOTIFIED THE LOCAL SHERIFF’S DEPARTMENT AND A DEPUTY WAS SENT OUT TO CONFIRM. THE PILOT MOVED THE AC FROM THE ROADWAY TO AVOID DAMAGE OR ANY INCIDENT WITH TRAFFIC. UPON REACHING TH1H71 3O3 BNT3A12 E00069EN 20080403000622008040300062SO 2008 4 3 2008FA0000173 120080228G32450923080 TUBE PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA TIRE FLAT B O OTHER O OTHER LDLANDING 1 GL21350ND70 2842179 ON LANDING, RT MAIN LANDING GEAR TIRE FLAT. UPON DISASSEMBLY FOUND A SMALL SLIT IN THE OUTSIDE CIRCUMFERENCE OF THE TUBE. HAVE FOUND MANY SIMILAR SLITS IN OTHER FAILED TUBES FROM MFG. 1L71 3O3 O 2A13 E274 20080403000642008040300064 2008 4 3 2008FA0000177 120080229G61005038004811 RELAY PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL BURNED B K NONE O OTHER ININSP/MAINT 1 GL15964LB UPON LANDING A POWER/ TORQUE SURGE OF THE LT ENGINE WAS ENCOUNTERED. THE INCREASED THRUST FROM THE LT SIDE AND ICE COVERED RUNWAY CONDITIONS CAUSED AN OFF RUNWAY INCURSION. INVESTIGATION OF THE GROUND FINE SOLENOID SYSTEM RESULTED IN A BURNED K4 RELAY ON THE AFFECTED PC CARD CONTROLLING THE GROUND FINE SYSTEM ON THE LT SIDE. 4 T E4EA 6 CP56GL 20080403000652008040300065NM 2008 4 3 2008FA0000179 120080229G5712 RIB UNIVAR415 415E 0420308NM CONT C85 C85* 17008SO RT WING CORRODED D K NONE O OTHER ININSP/MAINT 1 SW0587346 519 COMPLIANCE WITH AD 2002-26-02 DETECT AND CORRECT CORROSION IN WING CENTER SECTION. FOUND 5 RIVETS CORRODED OFF THE LOWER CENTER RIB ON THE RT WING WALKWAY BOX. 1L71 3O3 O A787 E233 20080403000892008040300089CE 2008 4 3 2008FA0000180 120080229G323265412045 STUD CESSNA501 501 2076603CE LT MLG ACTUATOR BROKEN D K NONE O OTHER UKUNKNOWN 1 SO09793AA 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 NOT TIGHT IN THE GEAR. 1L72 4F A27CE 20080403000912008040300091SO 2008 4 3 2008FA0000181 220080304G8530AEC633099 PISTON BEECH 35 B35 1151506CE CONT E225 E2258 17015SO ENGINE FAILED G A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 CE07 D3633 03593D58 NR 6 PISTON DISINTEGRATED. CAUSE UNKNOWN. PISTON P/N AEC633099 WAS ORIGINALLY MANUFACTURED BY AIRMOTIVE ENGINEERING, INC.(AEC). ENGINE COMPONENTS, INC. (ECI) HAS SINCE BOUGHT OUT AEC. ECI HAS NOT PRODUCED THIS P/N. 1L71 3O3 O A777 E267 20080403000962008040300096NE 2008 4 3 2008FA0000183 220080304G7250304997801 TURBINE BEECH 200 B200 1152922CE PWA PT6 PT6A42 52043NE ENGINE DAMAGED D K NONE O OTHER ININSP/MAINT 1 WP19185XP4837 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 SERVICE SINCE OVERHAUL, INITIAL VISUAL INSPECTION OF THE CT BLADES TIP CLEARANCE REVEALED CLEARANCES IN EXCESS OF ALLOWABLE 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 NOTED IN THE OUTER SECTION OF THE COMBUSTION LINER. AFFECTED COMPONENTS WILL BE SENT TO A P&WC APPROVED REPAIR FACILITY FOR REPAIRS OR REPLACEMENT AS NECESSARY. 1L72 4T4 T A24CE E4EA 20080414000022008041400002NE 2008 4 14 2008FA0000184 220080304G7230304997801 COMPRESSOR BEECH 200 B200 1152922CE PWA PT6 PT6A42 52043NE RT ENGINE DAMAGED D K NONE O OTHER ININSP/MAINT 1 WP19185XP4837 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 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 NOTED IN THE OUTER SECTION OF THE COMBUSTION LINER. AFFECTED COMPONENTS WILL BE SENT TO A MFG APPROVED REPAIR FACILITY FOR REPAIRS OR REPLACEMENT AS NECESSARY. 1L72 4T4 T A24CE E4EA 20080403000982008040300098CE 2008 4 3 2008FA0000186 120080306G7120051351119 MOUNT BRACKET CESSNA172 R172K 2072431CE LT ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 GL15758PX R1723262 FOUND UPPER LT ENGINE MOUNT BRACKET CRACKED WHILE INSPECTING FOR CESSNA SEB07-2 REV 2. THIS SERVICE BULLETIN DOES NOT APPLY TO THIS SERIAL NUMBER, ALTHOUGH A CRACK WAS FOUND. RECOMMEND INCREASING THE SERIAL NUMBER RANGE OF AFFECTED AIRCRAFT. THIS SHOP HAS ALSO NOTED SEAPLANES HAVE A DIFFERENT LOWER MOUNT BRACKET THAN THAT WHICH IS CALLED OUT IN THE SERVICE BULLETIN. RECOMMEND INCLUDING THE PROPER SEAPLANE MOUNT BRACKET NUMBERS FOR AIRCRAFT SO EQUIPPED. 1H71 3O 3A17 20080410002032008041000203SO 2008 4 10 2008FA0000187 120080402G8097767391 SOLENOID PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA STARTER SHORTED B K NONE O OTHER ININSP/MAINT 1 GL21350ND 2842179 DURING PRE-FLIGHT WHEN MASTER SWITCH WAS TURNED ON, THE PROP BEGAN TO ROTATE UNCOMMANDED. TROUBLESHOT TO FUSED STARTER SOLENOID. THIS IS THE SECOND SOLENOID FAILURE OF THIS TYPE IN ONE WEEK TIME, SAME MODEL AIRCRAFT. REPLACED WITH NEW PART, OPS CHECKED GOOD. 1L71 3O3 O 2A13 E274 20080404000062008040400006CE 2008 4 4 2008FA0000188 120080310G32332000300003 ACTUATOR LEAR 45 45LEAR 5170805CE PWA JT12 JT12A8 52042NE LT MLG BYPASSING D O OTHER S AFFECT SYSTEMS CLCLIMB 1 CE09828CA3137 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. 2L72 4F4 JRTT00008WI1E9 20080410002312008041000231EA 2008 4 10 2008FA0000190 220080313G7322 NUT PREAIR PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA FUEL SERVO LOOSE C K NONE O OTHER ININSP/MAINT 1 WP13283PA 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 DATE RANGE OF THIS AD). HOWEVER, WE DECIDED TO CHECK ALL OF OUR AIRCRAFT AND DURING THIS INSPECTION FOUND THE HEX NUT WAS LOOSE ON THIS PARTICULAR SERVO. 1L71 3O3 O 2A13 1E10 20080410002352008041000235EA 2008 4 10 2008FA0000191 220080331G732230802 FLOAT PREAIR MA45 MAULE M7235 M7235C 5460110SO LYC O540 O540B4B5 41532EA CARBURETOR BENT D K NONE O OTHER ININSP/MAINT 1 NM01249RD439 75103715 25069C L2571940A CARBURETOR FLOAT PN 30-802 PLASTIC FLOAT, THE CARBURETOR HAD A HIGH FLOAT LEVEL TWICE AFTER SETTING THE FLOAT TO SPEC IAW MM. THE FLOAT WAS REMOVED DUE TO THE FLOAT LEVER TANG WAS BENDING UNDER NORMAL USE CONTACTING THE NEEDLE VALVE AND RESULTING 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 WITH THE LEVER TANG BENDING IN NORMAL USE. A PN 30-764 FLOAT WAS INSTALLED AND ENGINE WAS NORMAL, NO ROUGHNESS NOTED. PLEASE LOOK IN TO THIS PROBLEM SO AS NO ONE HAS A ROUGH AND RICH RUNNING ENGINE DUE TO THIS PROBLEM AND POSSIBLE EARLIER THA1H71 3O3 ONC3A23 E295 20080410002412008041000241SO 2008 4 10 2008FA0000192 120080218G32309582900 LINK ASSY PIPER PA34 PA34200 7103405SO LYC O360 IO360A1A 41514EA NLG SHEARED G O OTHER O OTHER LDLANDING 1 EA171031U 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 DETERMINE 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 1L72 3O3 O A7SO 1E10 20080410002442008041000244SO 2008 4 10 2008FA0000193 120080321G5720902010XXX SUPPORT BRACKET GRUMAV AMRGENAA5 AA5A 3960106SO ZONE 600 CRACKED D K NONE O OTHER ININSP/MAINT 1 GL15 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 LOADING. 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. 1L71 3O A16EA 20080404000102008040400010NM 2008 4 4 2008FA0000194 120080319G8120 PIPE COLUMBLC40 LC40550FG3005150010NM CONT O550 TSIO550C SO TURBOCHARGER CRACKED B K NONE O OTHER ININSP/MAINT 1 EA211024Z438 1CF730011 41097 802744 RT TURBO TRANSITION PIPE CRACKED. THIS IS THE THIRD ONE INTO OUR SHOP. 1L71 3O3 ONTA00003SEE5SO 20080404000042008040400004EA 2008 4 4 2008FA0000195 220080229G732025244509 FUEL CONTROL PIPER PA28 PA28R201 7102816SO LYC O360 IO360C1C6 41514EA ENGINE LOOSE C D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 GL11540PU2900 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. 1L71 3O3 O 2A13 1E10 20080414000122008041400012EA 2008 4 14 2008FA0000197 220080321G8530 CYLINDER PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA HARTZLHCE2Y HCE2YR2 GL NR 3 SEPARATED C E ENGINE SHUTDOWN O OTHER NRNOT REPORTED 1 EA21 126 277554157 RL77048 HCE2YR2KBS NR 3 CYLINDER SEPARATED FROM ENGINE CASE. 1L72 3O3 O 1A10 1E4 5 CP9EA 20080414000082008041400008SO 2008 4 14 2008FA0000198 220080318G8530SA530348P15 PISTON CESSNA150 150D 2071810CE CONT O200 O200A 17020SO NR 3 CYLINDER CRACKED D K NONE O OTHER ININSP/MAINT 1 CE016029T885 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. 1H71 3O3 O 3A19 E252 20080414000062008041400006SO 2008 4 14 2008FA0000199 220080318G8500 CASE CESSNA421 421C 2076016CE CONT O520 GTSIO520L 17032SO RT ENGINE CRACKED B E ENGINE SHUTDOWN E VIBRATION/BUFFET NRNOT REPORTED 1 WP0912RJ 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 CAMSHAFT, LIFTERS, MAIN AND ROD BEARINGS. 1L72 3O3 O A7CE E7CE 20080414000092008041400009SO 2008 4 14 2008FA0000200 220080318G8530 CYLINDER CESSNA150 150D 2071810CE CONT O200 O200A 17020SO NR 1 CRACKED D K NONE O OTHER ININSP/MAINT 1 CE016029T 885 15060729 MUFFLER PRESSURE TEST REVEALED CRACKS IN NR 1 CYLINDER EXHAUST PORT, FWD SIDE. UNKNOWN CYLINDER TIME, WAS BORED .015 INCH OVERSIZE. 1H71 3O3 O 3A19 E252 20080414000072008041400007CE 2008 4 14 2008FA0000201 120080318G7820 FLAME TUBE CESSNA CESSNA150 150D 2071810CE CONT O200 O200A 17020SO MUFFLER RUPTURED D K NONE O OTHER ININSP/MAINT 1 CE016029T3900 15060729 RT MUFFLER P/N 0450400-26 WAS REMOVED FOR CYLINDER REPLACEMENT, INSP REVEALED DETERIORATED FLAME TUBES IN OUTLET PIPE AND NR1 INLET PIPE. OUTLET PIPE FLAME TUBE IS NOT READILY VISIBLE LOOKING UP TAIL PIPE. NO ENTRIES IN LOGBOOK INDICATING REPLACEMENT OF EITHER MUFFLER. 1H71 3O3 O 3A19 E252 20080414000182008041400018CE 2008 4 14 2008FA0000202 120080328G7120 MOUNT CESSNA172 172D 2072410CE ENGINE WRONG PART C K NONE W INADEQUATE Q C ININSP/MAINT 1 WP21 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 MOUNT. 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 M1H71 3O NT3A12 20080408000012008040800001SW 2008 4 8 2008FA0000203 120080320G801114912LS STARTER MOONEYM20 M20F 5870214SW LYC O360 IO360A1A 41514EA HARTZLHCC2Y HCC2YK1 GL ENGINE FAILED D O OTHER O OTHER NRNOT REPORTED 1 SW059615M 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 STARTER WAS INSTALLED BUT FAILED AGAIN SEVEN MONTHS AND 62.3 OPERATING HOURS LATER. A SERVICABLE STARTER WAS LOCATED AND INSTALLED IAW ENGINE SERVICE INSTRUCTION 1154L DATED JANARY 27, 2006. OUR SHOP RECOMMENDED THIS CHANGE DUE TO A TREND WE ARE SEEING IN THE LIGHT WEIGHT STARTERS. WE HAVE SEEN AT LEAST 6 FAILURES OR THE STARTER DRIVE GEAR EITHER FAILING TO ENGA1L71 3O3 O 2A3 1E10 5 CP920 20080414000102008041400010NM 2008 4 14 2008FA0000206 120080319G8120654327E TURBOCHARGER COLUMBLC40 LC40550FG3005150010NM CONT O550 TSIO550C SO RIGHT CRACKED B K NONE O OTHER ININSP/MAINT 1 EA21 438 41097 802744 RT TURBO TRANSITION PIPE CRACKED. THIS IS THE THIRD ONE INTO OUR SHOP. 1L71 3O3 ONTA00003SEE5SO 20080414000192008041400019SO 2008 4 14 2008FA0000208 120080328G29101159SCH2393 SHUTOFF VALVE GULSTMG1159 GIV 3980115SO RROYCETAY TAY6108 NE HYD SYSTEM SEIZED C O OTHER J WARNING INDICATION CRCRUISE 1 GL23312EL7509 1105 WHILE AT CRUISE ALTITUDE, THE COMBINE HYDRAULIC SHUTOFF VALVE FAILED TOWARD CLOSED POSITION WHICH IS INDICATED IN THE COCKPIT ON THE EICAS WITH DASHED LINES (VALVE IN TRANSITION) THUS TAKING AWAY YOUR HYDRAULIC PRESSURE INDICATION. WHEN THE VALVE IS FULLY CLOSED THE INDICATION ON THE EICAS IS DIAGONAL SOLID LINES. THE ONLY WAY TO GET THIS VALVE TO MOVE CLOSED IS WITH THE FIRE L HANDLE. 2L72 4F4 FRTA12EA E25NE 20080414000362008041400036EA 2008 4 14 2008FA0000209 220080401G7414M11522 BREAKER POINTS SLICK 6393 PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA MAGNETO WORN E K NONE O OTHER TXTAXI/GRND HDL 1 EA1762BA 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 1L72 3O3 O 1A10 1E4 20080414000132008041400013SO 2008 4 14 2008FA0000210 120080325G8011701122223 SOLENOID PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA STARTER STICKS B H DEACTIVATE SYST/CIRCUITS O OTHER TXTAXI/GRND HDL 1 GL21245ND 2842086 WHEN BATTERY MASTER TURNED ON PROP BEGAN ROTATING UNCOMMANDED. TROUBLESHOT TO FUSED STATER SOLENOID. REPLACED SOLENOID WITH NEW OEM PART PROBLEM PERSISTED. NEW SOLENOID WAS STRUCK WITH A SIDE BLOW AND CONTACTS FREED. REPLACED WITH ANOTHER NEW OEM PART, PROBLEM CORRECTED. 1L71 3O3 O 2A13 E274 20080414000042008041400004SO 2008 4 14 2008FA0000211 220080312G8500654327E DUCT LANCARLC41 LC41550FG 5150001NM CONT O550 TSIO550A 41516SO ENGINE CRACKED B K NONE O OTHER ININSP/MAINT 1 EA21 154 41722 914564 RT TURBO TRANSITION DUCT CRACKED. (NOTE: THIS IS THE SECOND TIME WE HAVE SEEN THIS) 1L71 3O3 ONTA00003SEE5SO 20080414000112008041400011EA 2008 4 14 2008FA0000212 220080319G7322383493 GASKET PREAIR CESSNA206 206H 2073301CE LYC O540 IO540AC1A5 EA FUEL SERVO UNKNOWN D K NONE P NO WARNING INDICATION ININSP/MAINT 1 NM012446X 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. 1H71 3O3 ORTA4CE 1E4 20080414000052008041400005CE 2008 4 14 2008FA0000214 120080207G3040FED2000 DEFOG SYSTEM LEAR 35 35A 5170602CE GARRTTTFE731TFE731* 01518WP COCKPIT BURNED G A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 NM0160WL 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 FURTHER INCIDENT. 2L72 4F4 F A10CE E6WE 20080410001862008041000186CE 2008 4 10 2008FA0000215 120080204G2800 NUT CESSNA206 T206H 2073303CE LYC O540 TIO540AJ1A EA FUEL SERVO LOOSE B Z08RA UNSCHED LANDING O OTHER ININSP/MAINT 1 CE07168JS302 T20608735 WHILE PERFORMING SB PRS-107, FOUND PN 383493 HEX NUT ACCESS PLUG FINGER LOOSE. ALSO, FOUND RED DYE INSIDE FUEL SERVO AIR CHAMBER. THIS AC HAS HAD AN ISSUE WITH LEAN IDLE MIXTURE IN THE PAST. NOTE: HEX NUT WILL BE LOOSER IF ENGINE IS WARMED UP. SUSPECT UNDERTORQUED FROM FACTORY AND RED DYE NOT FLUSHED FROM CHAMBER. SENT TO OVERHAUL FACILITY TO HAVE CORRECTED AND PERFORMED THE REQUIREMENTS OF PRS-107 SB. (K) 1H71 3O3 ORTA4CE E14EA 20080410001702008041000170EA 2008 4 10 2008FA0000216 220080204G7200 NUT CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE LOOSE B Z08RK NONE O OTHER ININSP/MAINT 1 CE07227BH 172S10662 WHILE PERFORMING SB PRS-107, FOUND PN 383493 HEX NUT PLUG FINGER LOOSE. OTE: HEX NUT WILL BECOME LOOSE IF ENGINE IS WARMED UP. SUSPECT UNDERTORQUED FROM THE FACTORY. (K) 1H71 3O3 ONT3A12 1E10 20080410001842008041000184EA 2008 4 10 2008FA0000217 220080204G7320 SERVO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA FUEL SYSTEM UNDERTORQUED C Z08RK NONE O OTHER ININSP/MAINT 1 CE07719JW 172S10527 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 FACTORY 1H71 3O3 ONT3A12 1E10 20080410001932008041000193EA 2008 4 10 2008FA0000218 220080204G7300 SERVO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENG FUEL LOOSE B Z08RK NONE J WARNING INDICATION ININSP/MAINT 1 CE07452SM 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) 1H71 3O3 ONT3A12 1E10 20080414000432008041400043SW 2008 4 14 2008FA0000219 120080205G2820 SELECTOR VALVE MOONEYM20 M20C 5870208SW LYC O360 O360* 41514EA FUEL SYSTEM SEIZED D K NONE O OTHER ININSP/MAINT 1 SW096529U 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 SPILLED LIQUIDS OR MOISTURE FROM CARPET FROM ENTERING UPPER HOUSING VALVE SHAFT BORE. (K) 1L71 3O3 O 2A3 E286 20080414000442008041400044CE 2008 4 14 2008FA0000220 120080222G270105131682 CONTROL WHEEL CESSNA172 172A 2072404CE CONT O300 O300* 17022SO BROKEN D O OTHER O OTHER TXTAXI/GRND HDL 1 NM0834264 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) 1H71 3O3 O 3A12 E253 20080410002462008041000246EA 2008 4 10 2008FA0000221 120080220G7921269D45031 SCROLL SCWZER269 269D 8059501EA ALLSN 250C 250C20 03013GL OIL COOLER FAN CRACKED D K NONE O OTHER ININSP/MAINT 1 SW03411HU 0040 UPON INSPECTION OF OIL COOLER FAN ASSY, FOUND MANY CRACKS AROUND THE TOP MOUNT OF SCROLL ASSY. (K) 1G71 3U3 U0 4H12 E4CE 20080410002052008041000205CE 2008 4 10 2008FA0000223 120080308G5753052390133 SKIN CESSNA182 182M 2072728CE CONT O470 O470* 17026SO TE FLAP CRACKED D K NONE O OTHER ININSP/MAINT 1 SW01717845800 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 SCREWS IN REPLACEMENT OF THE SHEERED RIVETS. PROBABLE CAUSE BY FLAP OVERSPEED WITH HIGH G, LOADS. THIS AIRCRAFT TOWS GLIDERS ALL THE TIME. (K) 1H71 3O3 ONT3A13 E273 20080410001942008041000194SO 2008 4 10 2008FA0000224 120080321G29101159SCH5197 SIGHT GLASS GULSTMGVSP GVSPG550 3980203SO RROYCEBR700 BR700710A110 NE HYD TANK CRACKED C K NONE O OTHER ININSP/MAINT 1 GL1557UH 5163 SIGHT GLASS CRACKED IN SEVERAL LOCATIONS AND LEAKS HYDRAULIC FLUID. THIS TANK IS ONE OF SEVERAL RETURNED FOR THE SAME DEFECT. (K) 2L72 4F4 FRTA12EA E00057EN 20080410002342008041000234NM 2008 4 10 2008FA0000225 120080401G8120654327 TRANSITION DUCT LANCARLC41 LC41550FG 5150001NM CONT O550 TSIO550C SO TURBOCHARGER CRACKED D K NONE O OTHER ININSP/MAINT 1 WP19431PC 41050 DURING ANNUAL INSP FOUND TURBO TRANSITION PART OF EXHAUST CRACKED ALL THE WAY THRU FRONT RADIUS OF THE PIPE. (K) 1L71 3O3 ONTA00003SEE5SO 20080428002982008042800298SO 2008 4 28 2008FA0000226 120080321G29101159SCH5197 SIGHT GLASS GULSTMGIVX GIVXG450 3980205SO RROYCETAY TAY6118 EU HYD SYSTEM CRACKED D K NONE O OTHER ININSP/MAINT 1 EA25612AF224 4069 SIGHT GLASS CRACKED IN SEVERAL LOCATIONS AND LEAKS HYDRAULIC FLUID, THIS TANK IS ONE OF SEVERAL RETURNED FOR THE SAME DEFECT. (K) 2L72 4F4 FRTA12EA E25NE 20080410002192008041000219SO 2008 4 10 2008FA0000227 120080225G321086262003 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA MLG WORN D UC2RK NONE O OTHER ININSP/MAINT 1 GL195341Z2193 4496107 NOSE GEAR DOOR TUBE PN 86262003 FOUND WITH GROOVE WORN INTO TUBE AT APPROX 65 PERCENT OF TUBE THICKNESS IN THE AREA OF THE 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. CURRENTLY THERE IS A NYLON BUSHING PN 452647 THAT IS INSERTED AT THIS PIVOT POINT TO PROVIDE FOR SOME PROTECTION OF THE TUBE. 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 1L72 3O3 O A19S0 E286 20080414000532008041400053SO 2008 4 14 2008FA0000229 120080408G8011701122223 SOLENOID PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA STARTER STICKS B H DEACTIVATE SYST/CIRCUITS S AFFECT SYSTEMS TXTAXI/GRND HDL 1 GL21436ND3478 2842213 AFTER START, STARTER ANNUNCIATOR DID NOT EXTINGUISH. ENGINE SHUTDOWN WITH MIXTURE BUT CONTINUED TO CRANK OVER WITH MASTER TURNED ON. TROUBLESHOOTING REVEALED STARTER CONTACTOR STUCK CLOSED. WHEN STRUCK CONTACTS WOULD OPEN BUT WHEN POWER APPLIED WOULD STICK CLOSED UNTIL STRUCK. 1L71 3O3 O 2A13 E274 20080414000582008041400058SW 2008 4 14 2008FA0000230 120080331G2731 CONTROL TUBE ECLIPSEA500 ECLIPSEEA5003350000SW PITCH TRIM OUT OF ADJUST B CJ6RC ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 GL03875NA 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 REPLACEMENT ACTUATOR SHOULD BE INSTALLED. AFTER INSTALLING NEW PART, DEFECT STILL EXISTED. FURTHER TROUBLESHOOTING REVEALED THAT 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 OPERATED CORRECTLY ON GROUND AND IN SUBSEQUENT OPERATIONAL CHECK FLIGHT. (K) 1L72 4J RTA00002AC 20080414000602008041400060CE 2008 4 14 2008FA0000231 120080331G2820 LINE CESSNA182 182P 2075816CE CONT O470 O470* 17026SO GAS COLATOR LEAKING C K NONE KJ FLUID LOSS WARNING INDICATION ININSP/MAINT 1 SO0320935 18261306 FUEL LEAKING FROM GAS COLATOR BOWL, TIGHTENED AT FACTORY DURING ACCEPTANCE FLIGHT (5.0 HOURS). FUEL LEAKING FROM GAS COLATOR INLET LINE (10 HOURS SINCE NEW) RESULTED IN OFF-AIRPORT LANDING DUE TO FUEL QUANTITY. (K) 1H71 3O3 ONTTA13 E273 20080414000612008041400061WP 2008 4 14 2008FA0000232 120080331G2621130835 CARTRIDGE DOUG DC3 DC3CR183090C3021466WP PWA PT6 PT6* 52043EA FIRE BOTTLE FAILED G VWBRK NONE O OTHER ININSP/MAINT 1 GL13300BF 03692C1 26744 THE FIRE BOTTLE WAS BEING DISCHARGED FOR AN OVERHAUL. THE CARTRIDGE FIRED BUT DID NOT DISCHARGE THE BOTTLE. SUSPECT IMPROPER SETUP OF CARTRIDGE IN BOTTLE. (K) 2L72 4R3 T A669 E2NE 20080414000622008041400062EA 2008 4 14 2008FA0000233 220080318G8530IO360AV CYLINDER MOONEYM20 M20E 5870212SW LYC O360 IO360A1A 41514EA HARTZLHCC2Y HCC2YR1 GL ENGINE WORN D K NONE O OTHER ININSP/MAINT 1 WP0779337 547 CH42539B PILOT REPORTED PARTIAL POWER LOSS ON TAKEOFF. ENG INSP REVEALED THE FOLLOWING DISCREPANCIES AND CORRECTIONS AS NOTE: CYL NR 1 HAD BAD INTAKE VALVE SEAT WITH EXCESSIVE WEAR, AND FUEL INJECTOR AIR SCREEN CONTAMINATED. THIS POSSIBLY CAUSED CYL TO BURN LEAN AND CAUSED EXCESSIVE WEARING ON VALVE SEAT. THIS IN TURN WOULDN’T ALLOW THE INTAKE VALVE TO CLOSE PROPERLY, CRATING ROUGH ENG RUNNING AND OCCASIONAL BACK-FIRING. COMPLETE STUD ASSY WAS REPLACED WITH REBUILT ASSY SN 162, UNDER 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. 1L71 3O3 O 2A3 1E10 5 CP920 20080414000642008041400064SO 2008 4 14 2008FA0000234 120080307G7160 VALVE MAULE M4 M4210C 5460112SO CONT IO360 IO360* 17025CE ALT AIR VALVE BROKEN G O OTHER J WARNING INDICATION CRCRUISE 1 WP1151430 1097C THE ENG AUTOMATIC ALTERNATE INDUCTION AIR VALVE THAT IS PARTIALLY LOCATED INSIDE THE CYLINDRICAL PAPER INDUCTION AIR FILTER CAME APART AND SOME OF ITS PART (2 INCH LONG, .2500 INCH DIAMETER BOLT. 2 INCH LONG SPIRAL SPRING WASHER, AND COTTER 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 HAD DISASSEMBLED THE ALTERNATE AIR VALVE TO PAINT IT AND HE MAY HAVE IMPROPERLY REINSTALLED THE COTTER PIN INTO THE CASTEL1H71 3O3 O 3A23 E1CE 20080414000652008041400065CE 2008 4 14 2008FA0000235 120080301G2510MS27039116 SCREW CESSNA182 R182 2072734CE LYC O540 O540* 41532EA UNDER REAR SEAT IMPROPER PART D LN7RK NONE O OTHER ININSP/MAINT 1 EA13757XU 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 LONG. IF ANYBODY PUT IN THE PROPER LENGTH SCREW, (MS27039-1-12), THEN THE AC WOULD BE LESS SAFE AFTER COMPLYING WITH THE SB. THE PLATE NEEDS 17 EA MS27039-1-12, AND 1 MS27039-1-09. (K) 1H71 3O3 ORT3A13 E295 20080414000662008041400066EU 2008 4 14 2008FA0000236 120080227G32225322012039 PIN PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE NLG STRUT MISMANUFACTURED B Z4MRK NONE O OTHER ININSP/MAINT 1 WP27672SD 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) 1L71 3T4 TRTA78EU E26NE 20080414000672008041400067NE 2008 4 14 2008FA0000237 120080221G64107610105017045 SPAR SKRSKYS76 S76B 8143007NE PWA PT6 PT6* 52043EA T/R BLADE CRACKED C CW1RK NONE O OTHER ININSP/MAINT 1 EA11780P 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 SPAR WAS FOUND TO HAVE CRACKS COMING FROM ELLIPTICAL PLUG AREA. SPAR WAS SUBSEQUENTLY CHANGED, BLADE INSPECTED AND RETURNED TO SERVICEABLE CONDITION. SCRAPED SPAR. 1G72 4U3 T H1NE E2NE 20080414000762008041400076GL 2008 4 14 2008FA0000238 120080227G341151815001 BUSHING CIRRUSSR SR20 05628AJGL CONT IO360 IO360* 17025CE REDUCER INCORRECT C LN7RK NONE O OTHER ININSP/MAINT 1 EA13362HE 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) WAS 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 SEALANT TO ALL MALE PIPE THREAD FITTINGS PRIOR TO STATIC LINE SUMP ARE NOT PIPE THREAD, AND THEREFOR WERE NOT (TAPED). RECOMMEND CHANGING PROCEDURE TO STATE (APPLY THREAD SEALANT TO ALL MALE FITTINGS PRIOR TO ASSY). (K) 1L71 3O3 ONTA00009CHE1CE 20080414000932008041400093WP 2008 4 14 2008FA0000239 120080115G6410MHS54896 NUT HUGHES369 369E 4470707WP TAIL ROTOR BLADESPLIT D K NONE O OTHER ININSP/MAINT 1 NM119460T 0238E ON FINAL TORQUE OF TAIL ROTOR BLADES RETENTION BOLT, NEW NUT SPLIT PRIOR TO ACHIEVING TORQUE. NEW NUT, IS THINNER AND LIGHTER STRENGTH THAN PREVIOUSLY MFG OLDER PN. NEW BOLTS ALSO REQURIE A NEW HIGHT TORQUE VALUE. (K) 1G71 3U H3WE 20080414000942008041400094EA 2008 4 14 2008FA0000240 220080307G8520 BOLT BEECH 80 65B80 1152812CE LYC O540 IGO540B1A 41532EA CONNECTING ROD FAILED G KZ5RA UNSCHED LANDING RYJPARTIAL RPM/PWR LOSS ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 GL15103BA 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) 1L72 3O3 O 3A20 1E11 20080414000632008041400063EU 2008 4 14 2008FA0000241 220080409G8500 ENGINE DIAMONDA42 DA42 2990004EU THIELTTAE125TAE1250299 EU LEFT POWER LOSS D O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 SO1549OTS 42AC090 020201763 AFTER TAKEOFF AND PULLING LANDING GEAR UP, LT ENGINE POWER REDUCTION TO 75 PERCENT FOR ABOUT ONE MINUTE AND POWER WAS RESTORED. THIS SAME ISSUE HAS BEEN INDUCTED TWICE IN LESS THAN 24 HRS. THERE IS NO FEDAC WARNINGS SHOWN ON SYS. A REPORT HAS BEEN SENT TO MFG. 1L72 3I3 BRTA57CE E00069EN 20080414000982008041400098SO 2008 4 14 2008FA0000243 120080410G8120 TURBOCHARGER PIPER PA28 PA28R201T 7102813SO CONT O360 TSIO360FB 17025SO ENGINE FOD D K NONE C F.O.D. ININSP/MAINT 1 SO0547550 28R7703397 232784B TURBOCHARGER COMPRESSOR DAMAGED BY FOD INGESTED THROUGH THE ALTERNATE AIR DOOR. THIS DOOR IS ON TOP OF THE AIR FILTER BOX ALLOWING ANY OBJECT THROWN UP BY THE NOSE WHEEL TO ENTER THE INDUCTION SYSTEM WHEN THE DOOR IS ACTIVATED DURING PREFLIGHT CHECKS. 1L71 3O3 O 2A13 E9CE 20080414000592008041400059CE 2008 4 14 2008FA0000245 120080409G2731 TRIM SYSTEM BEECH 90 C90A 1152911CE PWA PT6 PT6* 52043EA ELEVATOR ICED P O OTHER F FLT CONT AFFECTED CLCLIMB 1 EA21200TR400 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 ELEVATOR FORCE LOADED UP AND UNABLE TO TRIM. WITH LITTLE NUDGES BACK AND FORTH ON THE TRIM WHEEL FOR ABOUT 10 MINUTES, THE SYSTEM BECOMES FREE. EACH TIME I REPORT THIS TO MECHANICS, THEY INSPECT AND LUBRICATE THE SYSTEM AND REPORT EVERYTHING IS SATISFACTORY. THIS WAS MY EXPERIENCE FROM 1984 TO 2005. THE PLANE WAS NORMALLY KEPT IN A HANGAR SO OCCURRENCES WERE INFREQUENT. 1L72 3T3 TRT3A20 E2NE 20080414001042008041400104EA 2008 4 14 2008FA0000246 220080411G8530 CYLINDER PIPER PA31 PA31325 7103105SO LYC O540 TIO540* 41532EA NR 5 DAMAGED D O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 GL21476EB1400 1400 317612059 L167768A NR 5 CYL EXHAUST VALVE BROKEN, SENDING THE HEAD OF THE VALVE THROUGH THE EXHAUST AND LODGING ITSELF INTO THE TURBOCHARGER, EXTENSIVE DAMAGE TO THE CYLINDER, PISTON, AND TURBO. 1L72 3O3 O A20SO E14EA 20080425000572008042500057CE 2008 4 25 2008FA0000247 120080131G324522X8007008 TUBE CLEVELAND CESSNA208 208B 2073701CE PWA PT6 PT6* 52043EA NOSE WHEEL TORN G K NONE O OTHER ININSP/MAINT 1 AL03694MA69 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) 1H71 3T3 T A37CE E2NE 20080417000242008041700024CE 2008 4 17 2008FA0000248 120080204G3260 THROTTLE SWITCH CESSNA210 210J 2073439CE CONT O520 IO520* 17032SO COCKPIT INTERMITTENT D O OTHER O OTHER LDLANDING 1 EA231333T T21059108 GEAR WARNING HORN WAS INOPERATIVE. AC LANDED WITH LANDING GEAR UP. SUBSEQUENT INVESTIGATION DETERMINED THROTTLE MICROSWITCH WAS MAKING INTERMITTENT CONTACT WHEN ENGAGED AND GROUND CONNECTION WAS INSUFFICIENT. CORRECTED BY REPLACING SWITCH AND REPAIRING GROUND CONNECTION. HORN OPERATION SHOULD BE CHECKED VIA TEST FEATURE DURING PREFLIGHT. (K) 1H71 3O3 O 3A21 E5CE 20080425000692008042500069CE 2008 4 25 2008FA0000249 120080207G3233MS28775112 SEAL CESSNA172 172RG 2072438CE LYC O360 O360* 41514EA NLG ACTUATOR LEAKING D K NONE O OTHER ININSP/MAINT 1 SO116562V 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 CYCLING. DAMAGE TO THE AC WAS LIMITED DUE TO THE PROPER EXECUTION OF EMERGENCY LANDING PROCEDURES. THERE WERE NO INJURIES. (K) 1H71 3O3 O 3A17 E286 20080425001062008042500106WP 2008 4 25 2008FA0000250 220080305G7200 ENGINE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33110UG 01514WP ROTOL R321 R321482F8 GL OVERHEATED W LY0FE ENGINE SHUTDOWN MJ OVER TEMP WARNING INDICATION CRCRUISE 1 SO23139LC24465 AC732 P44344 DRG856029 IN CRUISE TO 8000 FT, INDICATION OF RED LIGHT OF OIL PRESSURE WITH 870 DEGREE TEMPERATURE. LIGHT TURNS OFF. AFTER 15 SECONDS, THE LIGHT TURNS ON AGAIN WITH 870 DEGREE TEMPERATURE, BUT THE PRESSURE DOWN NEAR ZERO. THE CREW MADE THE SHUTDOWN ENGINE PROCEDURE. LANDING WITHOUT NOVELTY. AT THE MOMENT THE ENGINE IS WAITING TECH INSPECTOR. (K) 2L72 4T4 TRTA8SW E4WE 6 CP61GL 20080425001122008042500112CE 2008 4 25 2008FA0000252 120080305G8011 MOUNT CESSNA206 T206H 2073303CE LYC O540 TIO540AJ1A EA STARTER FAILED C K NONE O OTHER ININSP/MAINT 1 SW15214CE1 T20608592 ORIGINAL STARTER (TT 433.4) WAS REMOVED BECAUSE IT FAILED (SMELLED BURNED). A REPLACEMENT WAS ORDERED FROM MFG AND INSTALLED. 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 NORMAL WHEN AN AC HAS A KICKBACK. THE PILOT STATED HE DID NOT HAVE A KICKBACK. SENT THE STARTER FOR REPAIR AND WHEN RETURNED, INSTALL AND AGAIN CHECKED THE IGNITION SYS WITH NO ABNORMITIES FOUND. STARTED THE AC (5) TIMES AND HAD THE OWNER1H71 3O3 ORTA4CE E14EA 20080425001272008042500127CE 2008 4 25 2008FA0000254 220080305G7310 SERVO DIAMONDA40 DA40 2990002GL CONT IO360 IO360* 17025CE HARTZLHCC2Y HCC2YR1 GL FUEL INJECTION DAMAGED D U1VSK NONE O OTHER ININSP/MAINT 1 NM07103UV687 40683 L3284951A CH40160B WHILE PERFORMING A 100 HR INSP, THE TECH DISCOVERED FINE METAL PARTICLES COVERING THE THROAT AND VALVE OF THE FUEL INJECTION SERVO (2576568-1, SN 70B10709). THE SERVO WAS SENT TO A REPAIR FACILITY TO DETERMINE WHETHER OR NOT ANY OF THE METAL PARTICLES ENTERED THE SERVOS BLAST TUBES. IT HAS BEEN DETERMINED THAT THE METAL ORIGINATED FROM THE CHAFING OF THE LOOSE 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. 1L71 3O3 ONTA47CE E1CE 5 CP920 20080428003002008042800300CE 2008 4 28 2008FA0000256 120080321G252017001277 PANEL CESSNA182 182Q 2072732CE CONT O470 O470* 17026SO CABIN CORRODED G K NONE O OTHER ININSP/MAINT 1 SO099766015328 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 07000762-23 ITEM 7, PN 1700127-7 AND -10, ITEMS 10 AND 13, PN 1200217-8, ITEM 14 AND 1200193-11, ITEM 15. REMOVAL OF SURFACE CORROSION, CLEANING, BRIGHTING, AND ALODINING THE EFFECTED AREAS TO REMOVING OF COMPLETE SKIN PANELS TO RESTORE STRUCTURAL INTEGRITY OF THE AC. PROBABLE CAUSE IS THE MFG TO PROVIDE A SUITABLE CORROSION BARRIER TO PROTECT THE AC STRUCTURAL INTEGRITY AND THE SKIN PANELS BEING EXPOSED TO CHEMICAL ACTION OF THE ADHESIVES USED TO ATTACH THE SOUNDPROOFING PANELS T1H71 3O3 ONT3A13 E273 20080428003042008042800304NE 2008 4 28 2008FA0000257 220080311G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MALFUNCTIONED E A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CE03957FE 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 SAFELY. AFTER TALKING TO PILOT AND CHECKING POWER ANALYZER AND RECORDER (PAR) THE ITT TEMP REACHED 926 DEGREES. ACCORDING TO MM, ANYTHING OVER 900 DEGREES IN CRUISE FLT REQUIRES TO BE PULLED AND SENT TO OVERHAUL SHOP FOR INSPECTION. WE HAVE BOROSCOPED THE ENGINE AND SEE NO EVIDENCE OF ANY FOD ACCORDING TO OUR CONTRACT MAINT. THERE IS SIGNS OF AN OVERTEMP. FIGURED THAT WITH WHAT THE PAR SHOWS. NOT SURE WHAT CAUSE THE LOUD POP AND THE OVER TEMP. MAYBE THE COMPRESSOR BLEED VAL1H71 3T3 T A37CE E4EA 20080428003072008042800307CE 2008 4 28 2008FA0000258 120080228G5730 TAPE CESSNA140 140 2071602CE CONT C90 C90* 17009SO WING LOOSE D K NONE O OTHER ININSP/MAINT 1 GL033527V 14796 DURING FLIGHT, THE FABRIC PATCH CAME OFF. THE AC WAS LANDED WITH SOME DIFFICULTY BUT WITHOUT INCIDENT. IT IS SPECULATED 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 LOOSE 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 DOWN AND BRUSHED WITH CEMENT, WORKING THE CEMENT UP INTO THE WEAVE OF THE TAPE AND PAYING SPECIAL ATTENTION TO WORKING TH1H71 3O3 ONCA768 E252 20080428003082008042800308GL 2008 4 28 2008FA0000259 120080314G2780 SLAT SYSTEM BOMBDRBD700 BD7001A10 1390006GL RROYCEBR700 BR700710A110 NE MALFUNCTIONED D O OTHER J WARNING INDICATION TOTAKEOFF 1 SW05917GL 9117 FLIGHT CREW REPORTED THAT SHORTLY AFTER ROTATION (AFTER T/O) THEY HAD A (FLICKERING) SLAT HALF SPD AND SLAT/FLAP HALF SPD EICAS MESSAGE. SHORTLY THEREAFTER THEY HAD AN AMBER SLAT FAIL, STALL WARN ADVANCE EICAS MESSAGE, C/B TRIP (E-2 SLAT/FLAP 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 AND THE FOLLOWING FDE MESSAGES: RT MFS NR 3 ACTUATOR/WRG 27656232SX; FLT CONT 2B FAULT (FCU 2 27654282SX; FLAP FAIL LATCHED FAULT NR1 2751000STD. TROUBLESHOOTING BY MAINT AND DEBRIEF FROM THE FLT CREW REVEALED A BOTTLE OF DRINKING WATER HAD2L72 4F4 FRTT00003NYE00057EN 20080428003092008042800309SO 2008 4 28 2008FA0000260 220080227G8530712BCA CYLINDER CESSNA402 402B 207590PCE CONT O520 TSIO520E 17040SO ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW055421M544 402B0021 CRACKED BETWEEN FIN NR1-3, BEHIND INJECTOR. DEFECTIVE PRODUCT. (K) 1L72 3O3 O A7CE E8CE 20080428003952008042800395SO 2008 4 28 2008FA0000261 220080317G8520639193 BUSHING CONT O520 TSIO520WB 17040SO COUNTER WEIGHT BROKEN B VA1RK NONE O OTHER ININSP/MAINT 1 SW19 32 518853 RECEIVED ENGINE IN AFTER 32.2 HOURS SINCE MAJOR OVERHAUL. ENGINE WAS DAMAGED BY COUNTERWEIGHT FAILURE ON CRANKSHAFT. DAMAGED TO THE CRANKCASE, CYLINDERS AND ROD WAS FROM WHAT APPEARED TO BE A BROKEN COUNTERWEIGHT PIN OR FAILURE OF THE COUNTERWEIGHT BUSHING. THE BUSHING WAS FOUND IN SEVERAL PIECES. (K) 3 O E8CE 20080428003962008042800396CE 2008 4 28 2008FA0000262 120080401G5410 HINGE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA ENG COWLING BROKEN D K NONE O OTHER ININSP/MAINT 1 WP09XCBCN BB435 PCE80952 ENGINE ICE VANE HINGE ASSY, BROKEN. HINGE ASSY BREAKS AND FRAGMENTS INTO SMALL PIECES THAT TEND TO BE INGESTED INTO ENGINE, CAUSING FOD. (K) 1L72 4T4 T A24CE E4EA 20080428003862008042800386EA 2008 4 28 2008FA0000263 220080403G8530LW12993 CYLINDER PIPER PA32 PA32301 7103207SO LYC O540 IO540K1G5 41532EA NR 2 CRACKED D K NONE O OTHER ININSP/MAINT 1 AL058200M1311 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) 1L71 3O3 O A3SO 1E4 20080428003872008042800387CE 2008 4 28 2008FA0000264 120080402G3710RA442CW12 PUMP BEECH 58 58 1152740CE CONT O550 IO550* SO VACUUM SYSTEM FAILED B PZ4RK NONE O OTHER ININSP/MAINT 1 GL118050U TH1657 VACUUM PUMP FAILED TO DEVELOP ANY AIR OUTPUT UPON INSTALLATION. REMOVED PUMP AND INSPECTED, SUSPECT VANES ARE NOT SLIDING OUT AGAINST CYLINDER WALL THUS NOT ALLOWING ANY AIR TO BE DEVELOPED. (K) 1L72 3O3 O 3A16 E3SO 20080428003882008042800388WP 2008 4 28 2008FA0000265 220080322G7230307241616 COMPRESSOR RAYTHN900 HAWKER900XP 4220011CE GARRTTTFE731TFE731* 01518WP ENGINE SEPARATED B ZN3RO OTHER E VIBRATION/BUFFET CLCLIMB 1 WP07897QS135 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 REPAIR AND OVERHAUL. (K) 1L72 4F4 FRTA3EU E6WE 20080428003892008042800389CE 2008 4 28 2008FA0000266 120080409G28201200406245 FUEL LINE CESSNA172 172M 2072418CE LYC O320 O320* 41508EA FUEL SYSTEM DEFORMED B HP6RK NONE O OTHER ININSP/MAINT 1 NM0122479732 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) 1H71 3O3 ONT3A12 E274 20080428003902008042800390SW 2008 4 28 2008FA0000267 120080407G5751 RIB BBAVIA7 7GCAA 21101N8SW LYC O320 O320B2B 41508EA SNSNCH74D 74DM EA RT AILERON BOWED C V36RK NONE O OTHER ININSP/MAINT 1 SO13872JM 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 AND THE SUPERFLITE PROCESS. THE REPAIR WAS PAINTED WITH FLEX AGENT ADDED. IAW TECH SUPPORT, AILERON BALANCING WAS NOT REQUIRED. REINSTALLED AILERON. AILERON CLEARANCE AND OPERATION SATISFACTORY. (K) 1H71 3O3 O A759 E274 5 NP88614 20080508000072008050800007CE 2008 5 8 2008FA0000268 120080304G3800 DRAIN CESSNA208 208B 2073701CE PWA PT6 PT6A114 52043NE FUSELAGE PLUGGED B MT9RO OTHER S AFFECT SYSTEMS DEDESCENT 1 SW059546B 208B0126 DURING FLT IN MODERATE TURBULENCE THE AP STARTED TO DISCONNECT, TWICE. THIRD ATTEMPT TO ENGAGE THE AP, THE AC MADE AN UNCOMMANDED 1500 FPM DESCENT. ATTEMPT TO CORRECT THE ATTITUDE WITH THE CWS FUNCTION WAS MADE BUT THE AP WOULD NOT DISENGAGE. THE AP DISCONNECT BUTTON WOULD NOT LET GO EITHER. HAD TO OVERPOWER THE AP CLUTCHES TO REGAIN CONTROL AND ATTEMPTED TO DISCONNECT THE SYS WITH THE C/B, THE AP REMAINED ON AND LIT AFTER PULLED. RECYCLED THE C/B AND WAS SUCCESSFUL. THIS 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 CLO1H71 3T3 T A37CE E4EA 20080428003942008042800394NM 2008 4 28 2008FA0000269 120080401G8120654327 TRANSITION DUCT LANCARLC41 LC41550FG 5150001NM CONT O550 TSIO550C SO TURBOCHARGER CRACKED B L9ORK NONE O OTHER ININSP/MAINT 1 WP19139DC714 41056 914313 DURING ANNUAL INSPECTION FOUND TURBO TRANSITION PART OF EXHAUST CRACKED ALL THE WAY THRU FRONT RADIUS OF THE PIPE. (K) 1L71 3O3 ONTA00003SEE5SO 20080508000092008050800009CE 2008 5 8 2008FA0000270 120080403G322207436062 ATTACH FITTING CESSNA182 182T 2072703CE LYC O540 IO540AB1A5 EA NLG CRACKED B 7TFRK NONE O OTHER ININSP/MAINT 1 WP07783WB1044 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 LANDING BUT NO OTHER DAMAGE NOTED. (K) 1H71 3O3 ONT3A13 1E4 20080508000102008050800010WP 2008 5 8 2008FA0000271 120080403G2820 LINE HUGHES269 269C 4470504WP FUEL SYSTEM LEAKING D K NONE O OTHER ININSP/MAINT 1 SW17111AB5 5 S1911 FUEL LEAKING FROM GASCOLATOR INLET LINE, APPROX 5.0 HRS SINCE NEW. (K) 1G71 3O 4H12 20080508000112008050800011CE 2008 5 8 2008FA0000272 120080112G52803901104580007 DOOR RAYTHN390 390 7150030CE WILINTFJ44 FJ442A GL LT MLG DAMAGED D K NONE O OTHER ININSP/MAINT 1 GL157088S264 RB188 AFTER ROUTINE FLIGHT, THE PILOT WAS PERFORMING HIS PREFLIGHT WALKAROUND INSP IN PREPARATION FOR THE NEXT LEG OF THE FLIGHT. HE NOTICED THAT BOTH MLG OUTER DOORS WERE DAMAGED. MECHANIC/MAINT WENT TO EVALUATE THE DAMAGE TO THE DOORS. RECOMMENDED 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 SATISFACTORILY. AC HAS SINCE BEEN RETURNED TO SERVICE WITH NO FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM. (K) 1L72 3F4 FRTA00010WIE3GL 20080508000122008050800012CE 2008 5 8 2008FA0000273 120080112G5280390110458008 DOOR RAYTHN390 390 7150030CE WILINTFJ44 FJ442A GL RT MLG DAMAGED D K NONE O OTHER ININSP/MAINT 1 GL157088S264 RB188 AFTER ROUTINE FLIGHT, THE PILOT WAS PERFORMING HIS PREFLIGHT WALKAROUND INSP IN PREPARATION FOR THE NEXT LEG OF THE FLIGHT. HE NOTICED THAT BOTH MLG OUTER DOORS WERE DAMAGED. MECH/ MAINT WENT TO EVALUATE THE DAMAGE TO THE DOORS. RECOMMENDED 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 SATISFACTORILY. AC HAS SINCE BEEN RETURNED TO SERVICE WITH NO FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM. (K) 1L72 3F4 FRTA00010WIE3GL 20080508000142008050800014CE 2008 5 8 2008FA0000274 120080128G52803901104500017 DOOR RAYTHN390 390 7150030CE LT MLG DAMAGED D K NONE O OTHER ININSP/MAINT 1 GL1534GN 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 AIRPLANE BE FLOWN BACK UNDER THE AUSPICES OF FAR PART 21.197, SPECIAL FLIGHT PERMITS. THE DOOR WAS EVALUATED BY MAINT AND QUALITY DEPT, AS WELL AS BY THE LOCAL TECH REP, AND DETERMINED UNREPAIRABLE. AC HAS SINCE BEEN RETURNED TO SERVICE WITH NO FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM. (K) 1L72 3F RTA00010WI 20080508000152008050800015CE 2008 5 8 2008FA0000275 120080128G3297 WIRE RAYTHN390 390 7150030CE LT MLG BROKEN D K NONE O OTHER ININSP/MAINT 1 GL1534GN RB58 AFTER LANDING, THE PILOT WAS INFORMED BY FUEL TRUCK DRIVER THAT 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 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 MICROSWITCH WAS BROKEN, AND IT WAS THIS BROKEN WIRING THAT CAUSED THE MICROSWITCH TO FAIL TO ALLOW THE UPLOCK TO PROPERLY ENGAGE THE LOCKING LUG ON THE DOOR. MICROSWITCH AND A NEW LT MLG IB DOOR WERE ORDERED RECEIVED, INSTALLED, RIGGED AND T1L72 3F RTA00010WI 20080428003242008042800324GL 2008 4 28 2008FA0000278 120080415G2100 VALVE DIAMONDA40 DA40 2990002GL CONT IO360 IO360* 17025CE LOOSE D K NONE O OTHER ININSP/MAINT 1 NM11105UV 40685 L3277551A THE ALTERNATE AIR VALVE IS VIBRATING AND CAUSING FRETTING BETWEEN THE INLET RING, PN D41-7166-20-31 AND FLANGE, PN D41-7166-20-33. THE "DUST" IS BEING INGESTED INTO THE FUEL CONTROL SERVO AND ENGINE. THERE NEEDS TO BE A TIGHTER FIT BETWEEN THESE PARTS. 1L71 3O3 ONTA47CE E1CE 20080428003272008042800327EA 2008 4 28 2008FA0000280 220080112G855016991000327 HOSE BEECH 23 C23 1151242CE LYC O360 O360A4G 41514EA OIL COOLER LEAKING G HA DEACTIVATE SYST/CIRCUITSUNSCHED LANDING KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 EA172102W 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 INSTALLED ON THIS AC. PILOT IN THIS CASE WAS ABLE TO KEEP OIL PRESSURE UPON LANDING, THUS AVOIDING A POTENTIALLY SERIOUS SITUATION. AS A RESULT OF THIS OCCURRENCE, ENGINE HAD TO BE DISASSEMBLED, CLEANED, INSPECTED, REPAIRED AS NECESSARY, AND1L71 3O3 O A1CE E286 20080428003282008042800328CE 2008 4 28 2008FA0000281 120080416G7120051313211 MOUNT CESSNA175 175 2072502CE CONT O300 GO300* 17022SO LT ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO116620E1927 723 56120 INSP FOUND UPPER LT BRACKET (0513132-11) WITH A SMALL CRACK ORIGINATING FROM THE LOWER EDGE OF THE ENGINE MOUNT BOLT WASHER. ONLY A SMALL BEND LINE WAS VISIBLE FROM THE COCKPIT SIDE OF THE BRACKET VIA BOROSCOPE. AFTER REMOVAL OF THIS BRACKET A CRACK WAS CLEARLY VISIBLE ON THE ENGINE SIDE OF BRACKET. FOUND UPPER RT BRACKET WITH (3) CRACKS SEPARATING THE BRACKET INTO 4 PIECES. THE THRESHOLD FOR THIS INSP SHOULD BE REDUCED FROM 2500 HRS. A MORE FREQUENT BOROSCOPE INSP WITHOUT 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. 1H71 3O3 ONT3A17 E298 20080508000512008050800051EA 2008 5 8 2008FA0000285 120080402G28221D217 PUMP DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA FUEL SYSTEM FAILED B SCIRK NONE O OTHER ININSP/MAINT 1 NM07359AR 359 BOOST PUMP FAILS AT 11,000 TO 12,000 FT OF ALTITUDE. WORKS FINE ON GROUND. (K) 1H72 3T4 TRTA9EA E4EA 20080508000522008050800052EA 2008 5 8 2008FA0000286 220080414G8530AEL61247 COVER CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO0998874632 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) 1H71 3O3 ONT3A12 E274 5 NP910 20080508000542008050800054EA 2008 5 8 2008FA0000287 220080414G8530AEL61247 COVER CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO0963450191 17275434 L1420839A TK039 FOUND ROCKER BOX COVER CRACKED DURING 100 HOUR INSPECTION. CRACKS CAUSED DUE TO IMPROPER CLEARANCE BETWEEN COVER AND ROCKER 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) 1H71 3O3 ONT3A12 E274 5 NP910 20080508000642008050800064CE 2008 5 8 2008FA0000288 120080401G571212210628 BULKHEAD CESSNA177 177B 2073708CE LYC O360 O360* 41514EA RT WING CRACKED B H5GRK NONE O OTHER ININSP/MAINT 1 EA0799NA 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-AFT FORCES BY AIR LOADS ON THE FLAPS. SO WHY REINFORCE ONLY ONE SIDE? IS IT POSSIBLE THAT THE FACTORY ASSY LINE NEGLECTED1H71 3O3 O A13CE E286 20080508000652008050800065CE 2008 5 8 2008FA0000289 120080401G571212210628 BULKHEAD CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA RT WING CRACKED B H5GRK NONE O OTHER ININSP/MAINT 1 EA07525434336 177RG1206 DURING ROUTINE INSP, 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 FOR-AFT FORCES BY AIR LOADS ON THE FLAPS. SO WHY REINFORCE ONLY ONE SIDE? IS IT POSSIBLE THAT THE FACTORY ASSY LINE NEGLECTED TO IN1H71 3O3 O A20CE 1E10 20080508000592008050800059EU 2008 5 8 2008FA0000290 120080423G3210DIN47108VERZ FASTENER DIAMON DIAMONDA42 DA42 2990004EU THIELTTAE125TAE1250299 EU MLG MISSING B NX4SK NONE O OTHER ININSP/MAINT 1 SO15966WW179 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. 1L72 3I3 BRTA57CE E00069EN 20080508000892008050800089 2008 5 8 2008FA0000291 420080424G3425011N097200 UNKNOWN CESSNA182 T182T 2072738CE LYC O540 TIO540* 41532EA COCKPIT MALFUNCTIONED B O OTHER O OTHER NRNOT REPORTED 1 WP05488PJ75 T18208333 WHEN TURNING THE (CRS) COURSE KNOB, THE INNER KNOB (BARO) BAROMETRIC PRESSURE KNOB WOULD TURN ALSO. CHANGING THE ALTITUDE INDICATED. 1H71 3O3 ONT3A13 E14EA 20080508000672008050800067EA 2008 5 8 2008FA0000292 220080423G7414 CAM SLICK PIPER PA46 PA46350P 7104602SO LYC O540 TIO540AE2A 41532EA MAGNETO WORN C UXCRK NONE O OTHER TXTAXI/GRND HDL 1 SW05855P 49 07100592 4692014 L1291661A BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW. TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICULT TO START. 1L71 3O3 ORTA25SO E14EA 20080707 EA 2008 7 7 2008FA0000293 220080423G7414 CAM SLICK PIPER PA46 PA46R350T 7104610SO LYC O540 TIO540AE2A 41532EA MAGNETO WORN C UXCRK NONE O OTHER TXTAXI/GRND HDL 1 SW05855P 49 07100592 4692014 L1291661A BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW. TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICULT TO START. 1L71 3O3 ORTA25SO E14EA 20080707 EA 2008 7 7 2008FA0000294 220080423G7414 CAM SLICK PIPER PA46 PA46R350T 7104610SO LYC O540 TIO540AE2A 41532EA MAGNETO WORN C UXCRK NONE O OTHER TXTAXI/GRND HDL 1 SW05855P 49 07100592 4692014 L1291661A BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW. TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICULT TO START. 1L71 3O3 ORTA25SO E14EA 20080707 EA 2008 7 7 2008FA0000295 220080423G7414 CAM SLICK PIPER PA46 PA46R350T 7104610SO LYC O540 TIO540AE2A 41532EA MAGNETO WORN C UXCRK NONE O OTHER TXTAXI/GRND HDL 1 SW05855P 49 07100592 4692014 L1291661A BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW. TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICULT TO START. 1L71 3O3 ORTA25SO E14EA 20080508001092008050800109 2008 5 8 2008FA0000296 420080425G3425011N097200 UNKNOWN CESSNA182 T182 2072736CE LYC O540 TIO540* 41532EA COCKPIT MALFUNCTIONED B O OTHER O OTHER NRNOT REPORTED 1 WP05488PJ75 T18208333 WHEN TURNING THE INNER "CRS" COARSE KNOB THE OUTER "BARO" BAROMETRIC PRESSURE KNOB WOULD TURN ALSO. CHANGING THE ALTITUDE. 1L71 3O3 O 3A13 E14EA 20080508001172008050800117 2008 5 8 2008FA0000297 220080426G8550 ADAPTER OIL SYSTEM MISMANUFACTURED C K NONE W INADEQUATE Q C ININSP/MAINT 1 WP15 ORDERED SPIN ON OIL FILTER ADAPTER MODEL NR (TAFL). MACHINED PART WAS NOT COMPLETELY FINISHED. AN IMPORTANT HOLE IN THE OIL PASSAGE DID NOT CONNECT WITH THE OIL DELIVERY LINE BECAUSE IT WASN'T DRILLED DEEP ENOUGH. MFG HAS BEEN COOPERATIVE AND AGREES TO REPLACE, HOWEVER IF ANY OF THESE DEFECTIVE PARTS HAVE BEEN INSTALLED IN THIS CONDITION, ENGINE FAILURE COULD RESULT. (SN 28653L) 200805141 200805141 CE 2008 5 14 2008FA0000300 120080422G531245A3490111 BULKHEAD BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE FUSELAGE CRACKED B KX5RK NONE O OTHER ININSP/MAINT 1 GL15400SF RK221 WHILE PERFORMING AN (A-B) INSPECTION FOUND RT AFT FUSELAGE BLEED AIR LINE ATTACH BRACKETS PULLED FROM AFT FUSELAGE BULKHEAD 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. THE CRACK HAS BEEN FOUND ON BOTH SIDES OF THE AC. (K) 2H72 4F4 FRTA16SW E25EA 200805141 200805141 SO 2008 5 14 2008FA0000301 120080418G7160U086126 MUFF LUSCOM8 8E 8190112SO CONT C85 C8512F 17008SO RT CARB FAILED D K NONE O OTHER ININSP/MAINT 1 NM012004 561 5937 2244612C AFTER A FLIGHT, IT WAS NOTED THAT A PORTION OF SCAT HOSE WAS HANGING FROM THE BOTTOM OF COWLING OPENING. UPON INSPECTION IT WAS FOUND THAT THE CARBURETOR HEAT FLANGE HAD SEPARATED WITH THE SCAT HOSE ATTACHED WITH CLAMP FRO THE IB HALF OF THE RT CARB HEAT MUFF. THE CARB HEAT MUFF HALVES WERE REMOVED AND INSPECTED. EXAMINATION OF THE FAILED ROUND DUCT FLANGE FOUND THE ENTIRE TUBE BROKE OFF AT THE CIRCUMFERENCE ALONG THE EDGE OF THE WELD. SECONDLY, THERE WERE ABOUT (6) SPIDER LIKE CRACKS AROUND THE BROKEN HOLE WHICH PROPAGATED OUTWARD. A TOTAL OF APPROX 16 CRACKS, BROKEN TABS INCLUDING A PREVIOUS (PATCH) REPAIR WERE NOTED ON BOTH IB AND OB MUFF HALVES. AN INNER MUFF RIB WHICH WAS TACK WELDED IN (3) PLACES HA1H71 3O3 O A694 E233 20080520 CE 2008 5 20 2008FA0000302 120080419G7921649964 GASKET CESSNA210 210L 2073448CE CONT O520 IO520* 17032SO OIL COOLER FAILED D O OTHER K FLUID LOSS CRCRUISE 1 SW09132WB140 21060114 295375R THE OIL COOLER ADAPTER GASKET TAILED IN FLIGHT CAUSING (2) QUARTS OF OIL IN ONE HOUR TO BE PUMPED INTO THE ENGINE COWLING. THIS ENGINE IS A FACTORY REMANUFACTURED ENGINE WITH 140 HOURS SINCE REMAIN. ON INSPECTION AND DISASSEMBLY THE OIL COOLER ADAPTER BOLTS DID NOT APPEAR TO BE TORQUED ENOUGH BUT THE GASKET ITSELF WAS BRITTLE AND LEAKING. THE ENGINE AND ADAPTER SURFACE WERE FLAT AND CLEAN. THE REPLACEMENT GASKET APPEARS TO BE A BETTER QUALITY. (K) 1H71 3O3 O 3A21 E5CE 20080520 SO 2008 5 20 2008FA0000303 120080421G322286280003 DRAG LINK PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA NOSE GEAR CRACKED B UC2RK NONE O OTHER ININSP/MAINT 1 GL195328L 4496108 NOSE GEAR DRAG LINK (PN 86280-003) CRACK LOCATED IN PIVOT BOLT HOUSING ON DRAG LINK WHERE A STANDARD (AN175-22A) BOLT ATTACHES NOSE GEAR DOWN LOCK (PN 86275-004). PROBABLE FATIGUE CRACK FROM NORMAL CYCLE TIME ON GEAR. RECOMMEND VISUAL INSP OF AREA AT A SPECIFIC PERIOD OF TIME TO BE DETERMINED BY THE MFG. (K) 1L72 3O3 O A19S0 E286 20080520 2008 5 20 2008FA0000304 420080125G2300G6860113 CONTROL HEAD AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE731* 01518WP COCKPIT BURNED D G O2 MASK DEPLOYED O OTHER DEDESCENT 1 SO15970S 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 WAS NOTED THAT THE NR 2 NAV CONTROL HEAD WAS BLANK AND SUSPECTED AS THE PROBABLE CAUSE AS IT WAS CLOSE TO THE STRONGEST SMELL. NO CIRCUIT BREAKERS POPPED. REMOVAL OF UNIT NAV/COM CONTROL HEAD (PN G6860113 SN298) NOTED ELECTRICAL BURNED SMELL WITH UNIT. PART HAS 9 HOURS SINCE REPAIR/MODIFICATION. UNIT TO BE SENT BACK FOR REPAIR. (K) 2L73 4F4 F A46EU E6WE 200805141 200805141 CE 2008 5 14 2008FA0000305 120080429G3246FN22A524 NUT RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE731* 01518WP WHEEL MISMANUFACTURED C K NONE W INADEQUATE Q C ININSP/MAINT 1 SO01733A 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. THIS IS A NEW PART AND HAS NEVER BEEN INSTALLED. ONLY ONE OF 24 BOUGHT FROM MFG THAT WAS BAD. THIS BOLT/NUT COMBINATION IS WHAT HOLDS THE (2) HALVES OF THE WHEEL TOGETHER. 2L72 4F4 FRTA3EU E6WE 20080520 EU 2008 5 20 2008FA0000306 120080501G352017408031 OXYGEN MASK ISRAEL1124 1124 4500102EU GARRTTTFE731TFE731* 01518WP CABIN COLLAPSED H K NONE O OTHER ININSP/MAINT 1 GL15 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". 2M72 4F4 F A2SW E6WE 20080520 GL 2008 5 20 2008FA0000307 120080225G7921646880 OIL COOLER CIRRUSSR SR20 05628AJGL CONT O360 IO360ES SO WORN C K NONE O OTHER ININSP/MAINT 1 SO15476DA300 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. IF THIS CONDITION IS NOT ADDRESSED BY REPLACEMENT OF SHOE AND OIL COOLER THE POSSIBILITY OF LOSS OF ENGINE OIL IS HIGH. THE 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. 1L71 3O3 ONTA00009CHE1CE 20080520 EU 2008 5 20 2008FA0000308 120080501G352017408031 OXYGEN MASK ISRAEL1124 1124 4500102EU GARRTTTFE731TFE731* 01518WP CABIN COLLAPSED H K NONE O OTHER ININSP/MAINT 1 GL15 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". 2M72 4F4 F A2SW E6WE 20080508000012008050800001SO 2008 5 8 2008FA0000309 120080507G27202223900 TORQUE TUBE PIPER PA24 PA24260 7102406SO RUDDER CONTROL BROKEN B D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 NM059506P3404 245023 DURING MAINTENANCE RUNUP AND TAXI CHECK AFTER MAINTENANCE THE LEFT RUDDER TORQUE TUBE BROKE OFF. IT APPEARED TO HAVE BEEN 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. 1L71 3O 1A15 20080522 NE 2008 5 22 2008FA0000310 220080506G72000319008000 ENGINE UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIUS2F 60010NE MAKING METAL D A UNSCHED LANDING J WARNING INDICATION DEDESCENT 1 SO07197CB278 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. 1G72 3U3 UNCR0001RD E34NE 20080522 NE 2008 5 22 2008FA0000311 220080502G7261 LINE AEROSPSA365 SA365N1 8680668EU TMECA ARRIELARRIEL2C 60054NE P2 OIL LOOSE C EA ENGINE SHUTDOWN UNSCHED LANDING KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NRNOT REPORTED 1 EA0795MD 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 WARNING LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED. 1G72 3U4 U H10EU E00054EN 20080522 NE 2008 5 22 2008FA0000312 220080502G7261 LINE AEROSPSA365 SA365N1 8680668EU TMECA ARRIELARRIEL2C 60054NE P2 OIL LOOSE C EA ENGINE SHUTDOWN UNSCHED LANDING KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NRNOT REPORTED 1 EA0795MD 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 WARNING LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED. 1G72 3U4 U H10EU E00054EN 20080522 NE 2008 5 22 2008FA0000313 220080502G7261 LINE AEROSPSA365 SA365N1 8680668EU TMECA ARRIELARRIEL2C 60054NE P2 OIL BACKED OUT C EA ENGINE SHUTDOWN UNSCHED LANDING KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NRNOT REPORTED 1 EA0795MD 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 WARNING LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED. 1G72 3U4 U H10EU E00054EN 20080522 NE 2008 5 22 2008FA0000314 220080502G7261 LINE AEROSPSA365 SA365N1 8680668EU TMECA ARRIELARRIEL2C 60054NE P2 OIL BACKED OUT C EA ENGINE SHUTDOWN UNSCHED LANDING KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NRNOT REPORTED 1 EA0795MD 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 WARNING LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED. 1G72 3U4 U H10EU E00054EN 20080602 CE 2008 6 2 2008FA0000317 120080506G324610320400AN53 BOLT PARKERHANFIN RAYTHN36 G36 7150061CE ZONE 700 SHEARED B K NONE O OTHER ININSP/MAINT 1 CE07222GL479 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 INSPECTION AND HAS NEVER HAD THE WHEEL HALVES DISASSEMBLED. UPON DISCOVERY OF THE SHEARED BOLT, THE LEFT AND RIGHT WHEELS 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 CHECKED F1L71 3O RT3A15 20080603 EA 2008 6 3 2008FA0000318 220080422G852013B27134 CRANKSHAFT PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA ENGINE CRACKED B UC2RA UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 GL194149T 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) 1L71 3O3 O 2A13 E286 20080603 CE 2008 6 3 2008FA0000320 120080425G5100S34691 BEARING CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA MCAULY2D34C B2D34C207 GL ACTUATOR FAILED D K NONE O OTHER ININSP/MAINT 1 WP09521564247 1533 177RG1180 L1699351A 771391 WHERE THE ROD END BEARING ATTACHES TO THE LATERAL BOLT, FWD. THIS BEARING (S34691 FAILED AT THE BEARING END. THIS BEARING IS UNDER EXTREEM TENSION LOAD AND WAS ORIGINAL. AGE WAS A FACTOR IN FAILING. REPLACING THIS BEARING AT 1000 HR INTERVALS IS NECESSARY. DATE OF THE ACTUATOR WAS 10/77. (K) 1H71 3O3 O A20CE 1E10 5 CP7EA 20080515000012008051500001CE 2008 5 15 2008FA0000321 120080425G571100011001316 SPAR CAP BEECH BEECH 90 E90 1152914CE RT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 NM05692M 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)IN THE REAR ROW OF RIVETS, & EXTENDS TO THE TRAILING EDGE OF CAP. THE A/C PASSED 2-400 HR WING SIRM INSPECTIONS. THE CRACK WAS DETECTED AT THE CURRENT 400 HR INTERVAL WING SIRM INSPECTION. NOTE:BEECH HAS REDUCED INTERVAL FOR EDDY CURRENT INSPECTION 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. 1L72 3T 3A20 20080602 SO 2008 6 2 2008FA0000322 120080505G8010701122223 SOLENOID PIPER PA28 PA28161 7102803SO STARTER SHORTED B H DEACTIVATE SYST/CIRCUITS S AFFECT SYSTEMS TXTAXI/GRND HDL 1 GL21238ND817 2842101 WHEN MASTER SWITCH TURNED ON PROP BEGAN TO ROTATE UNCOMMANDED. TROUBLESHOT TO STUCK STARTER SOLENOID. SOLENOID REPLACED, OPS CHECK GOOD. 1L71 3O 2A13 20080602 SW 2008 6 2 2008FA0000323 120080504G2720183M SLEEVE BBAVIA7 7GCBC 1220601SW LYC O320 O320A2D 41508EA RUDDER CABLE CRIMPED D A UNSCHED LANDING O OTHER TXTAXI/GRND HDL 1 SO0353718 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. 1H71 3O3 ONCA759 E274 20080602 SW 2008 6 2 2008FA0000324 120080507G3110011097203 DISPLAY BBAVIA7 7DC 2110116SW INSTRUMENT PANELDEFECTIVE D O OTHER O OTHER NRNOT REPORTED 1 NM03555Y 93 7DC2078 PRIMARY FLIGHT DISPLAY PANEL HAS A MALFUNCTION IN THE COARSE/BAROMETRIC PRESSURE ADJUSTMENT KNOB. THE DESIGN INCORPORATES 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 OF THE INNER COARSE KNOB RESULTS IN AN INADVERTENT CHANGE IN THE BAROMETRIC PRESSURE. THIS MALFUNCTION CAN BE QUITE DANGEROUS, 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. 1H71 3O A759 20080602 CE 2008 6 2 2008FA0000326 120080425G571100011001316 SPAR CAP BEECH 90 E90 1152914CE WING CRACKED D K NONE O OTHER ININSP/MAINT 1 NM05776DC8204 181 LW235 THE CRACK EMANATES FROM THE 5TH RIVET OUTBOARD OF THE LOWER FORWARD WING BOLT FITTING, 4TH RIVET FROM END OF SPAR CAP, IN THE FRONT ROW OF RIVETS, AND EXTENDS TO THE LEADING EDGE OF CAP. THE A/C PASSED 2-400 HOUR WING SIRM INSPECTIONS. 181 HRS INTO NEXT INTERVAL WAS WHEN CRACK WAS DETECTED DURING ROUTINE MAINTENANCE. BEECH HAS REDUCED INTERVAL FOR EDDY CURRENT 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. 1L72 3T 3A20 20080603 EU 2008 6 3 2008FA0000330 120080502G3242244755 BRAKE DISC BFGOODRICH PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL BROKEN B K NONE O OTHER ININSP/MAINT 1 NE05708AF1656 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. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20080603 EU 2008 6 3 2008FA0000331 120080506G3242244755 BRAKE DISC BFGOODRICH PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL BROKEN B K NONE O OTHER ININSP/MAINT 1 NE05776AF1103 0715 776 PR0657 KX423 FLIGHT CREW REPORTS RIGHT BRAKE GRABBING. REMOVED RIGHT MAIN TIRE ASSEMBLY AND DISCOVERED THE OUTBOARD BRAKE DISC WAS BROKEN INTO TWO PIECES. REPLACED THE RIGHT BRAKE ASSEMBLY. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20080603 EU 2008 6 3 2008FA0000332 120080506G3242244755 BRAKE DISC BFGOODRICH PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL BRAKE ASSY BROKEN B K NONE O OTHER ININSP/MAINT 1 NE05591AF875 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. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20080603 EU 2008 6 3 2008FA0000333 120080425G3520 INDICATOR ISRAEL1124 1124 4500102EU OXYGEN MASK INOPERATIVE C K NONE L NO TEST ININSP/MAINT 1 AL05500KE379 360 PASSENGER OXYGEN MASK FLOW INDICATOR INOPERATIVE. THIS UNIT CAME FROM LOT LC 0521 K OR LOT LC 0526K 2M72 4F A2SW 20080701 CE 2008 7 1 2008FA0000335 120080418G214088D7015EL TUBE BEECH 58 58 1152740CE CONT O550 IO550C SO MCAULY3AF32C3AF32C512 GL HEATER CRACKED B YWBRO OTHER O OTHER NRNOT REPORTED 1 WP17873AN453 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 HAVE 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. 1L72 3O3 O 3A16 E3SO 5 CP22EA 20080701 EU 2008 7 1 2008FA0000336 120080527G7920307194912 PUMP AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE7313 01518WP ENGINE OIL FAILED D O OTHER O OTHER NRNOT REPORTED 1 SO15970S 70 238 IAW MFG RECOMMENDATION, WE REMOVED THE ENGINE OIL PUMP, PN 3071949-11, AND INSTALLED PN 3071949-12 PUMP BECAUSE OF AN ISSUE (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 REPAIRED 8130 FROM MFG TRACKING NR 41056, WO NR 877515-001, DATED 2-4-2008 WITH NO FAULT FOUND. AFTER APPROXIMATELY 10 HOURS, WE HAD WRITE UP OF OIL PRESSURE FLUCTUATING. GROUND RUN AND COULD NOT DUPLICATE, SO WE SWAPPED OIL PRESSURE TRANSMITTERS AND GAUGE WITH OTHER ENGINES FOR TROUBLESHOOTING. THEN THE AIRCRAFT FLEW APPROXIMATELY 38 HOURS WITH EVERYTHING NORM2L73 4F4 F A46EU E6WE 20080701 SW 2008 7 1 2008FA0000337 120080701G6400206011725011 ROD BELL 206 206L3 1182108SW ALLSN 250C 250C30 03013GL TAIL ROTOR CHAFED B ULXRO OTHER O OTHER NRNOT REPORTED 1 WP0183WP 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 ASSEMBLY 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. 1G71 3U3 U H2SW E1GL 20080701 SW 2008 7 1 2008FA0000338 120080530G6200407310104103 SPRING BELL BELL 407 407 1182206SW ALLSN 250C 250C47B GL FRAHM ASSY DAMAGED B O OTHER O OTHER NRNOT REPORTED 1 WP01701WP 53542 ONE OF EIGHT SPRINGS BROKEN CAUSING DAMAGE TO LOWER HOUSING. LOWER HOUSING, SPRINGS 2 EA. AND PLUGS WERE REPLACED. UNKNOWN WHI SPRING BROKE, SPRING WAS FOUND BROKEN ON SCHEDULED 300 HOUR INSPECTION. (K) 1G71 3U3 UO H2SW E1GL 20080701 CE 2008 7 1 2008FA0000339 120080512G561010138402521 WINDSHIELD BEECH 90 C90 1152913CE COCKPIT CRACKED D O OTHER O OTHER NRNOT REPORTED 1 EA25585R 4772 LJ1169 PILOT WAS ON TAKEOFF AND HAD JUST LEVELED OUT FOR FLIGHT AND WINDSHIELD CRACKED ON THE INNER PANE. PILOT RETURNED TO BASE AND THE WINDSHIELD WAS REPLACED. WINDSHIELD WAS SENT TO INSURANCE CO. LAB FOR EVALUATION. (K) 1L72 3T 3A20 20080701 EU 2008 7 1 2008FA0000340 120080512G3233C239251103 ACTUATOR AMD FALC50FALCON50MYST2730106EU MALF MALFUNCTIONED B JGVRK NONE O OTHER ININSP/MAINT 1 CE09900KE9497 052 WHILE PERFORMING THE LANDING GEAR GRAVITY EXTENSION CHECK (MP32-470) DURING THE (B) INSPECTION IT WAS DISCOVERED BOTH MAIN LANDING GEAR ACTUATORS WOULD EXTEND PARTIALLY (APPROXIMATELY 30 PERCENT OF NORMAL TRAVEL) AND STOP. FURTHER TROUBLESHOOTING REVEALED IT TOOK EXTREME PRESSURE TO MOVE THE ACTUATORS TO THE DOWN AND LOCKED POSITION. THE ACTUATORS NORMALLY FREE-FALL TO THE EXTENDED POSITION AND NEED TO BE PULLED INTO THE DOWN AND LOCKED POSITION. BOTH ACTUATOR WERE REPLACED WITH OVERHAULED ACTUATORS. THE FAULTY ACTUATORS WERE SENT TO THE MFG REPAIR FACILITY FOR TEARDOWN AND EVALUATION. THE ACTUATOR PART AND SERIAL NUMBER ARE AS FOLLOWS: LT ACTUATOR/ PN C23925-1103, SN U22, RT ACTUATOR/ PN C23926-1103. 2L73 4F A46EU 20080701 EU 2008 7 1 2008FA0000341 120080512G3233C239261103 ACTUATOR AMD FALC50FALCON50MYST2730106EU MLG MALFUNCTIONED B JGVRK NONE O OTHER ININSP/MAINT 1 CE09900KE 052 WHILE PERFORMING THE LANDING GEAR GRAVITY EXTENSION CHECK (MP32-470) DURING THE (B) INSPECTION IT WAS DISCOVERED BOTH MAIN LANDING GEAR ACTUATORS WOULD EXTEND PARTIALLY (APPROXIMATELY 30 PERCENT OF NORMAL TRAVEL) AND STOP. FURTHER TROUBLESHOOTING 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 REPLACED WITH OVERHAULED ACTUATORS. THE FAULTY ACTUATORS WERE SENT TO THE MANUFACTURER`S REPAIR FACILITY FOR TEARDOWN AND EVALUATION. LT ACTUATOR, PN C239251103, SN U22 / RT ACTUATOR PN C239261103, SN U22. (K) 2L73 4F A46EU 20080715 GL 2008 7 15 2008FA0000343 120080618G5210 HINGE DIAMONDA40 DA40 2990002GL LYC O360 IO360LYC* 41514EA HARTZLHCC2Y HCC2YR1 GL DOOR CRACKED G O OTHER O OTHER NRNOT REPORTED 1 WP07686US 40640 L3262751A CH39554B FOUND CRACKS IN AFT DOOR HINGE. (K) 1L71 3O3 ONTA47CE 1E10 5 CP920 20080715 GL 2008 7 15 2008FA0000345 120080616G5210DA4522100002 DOOR DIAMONDA40 DA40 2990002GL LYC O360 IO360LYC* 41514EA HARTZLHCC2Y HCC2YR1 GL PAX DOOR DEPARTED G O OTHER D INFLIGHT SEPARATION CLCLIMB 1 WP07605US536 40675 L3276151A CH399768 ON TAKEOFF CLIMB OUT, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1L71 3O3 ONTA47CE 1E10 5 CP920 20080715 GL 2008 7 15 2008FA0000346 120080625G5210D4152210000 HINGE DIAMONDA40 DA40 2990002GL REAR CABIN DOOR CRACKED D O OTHER O OTHER NRNOT REPORTED 1 WP074189U991 40768 REAR HINGE DEVELOPING CRACKS IN FIBERS. NORMAL OPERATING CONDITION. PROBABLE CAUSE IS REAR HOLD OPEN CYLINDER CAUSING STRESS ON HINGE POINT. (K) 1L71 3O NTA47CE 20080715 GL 2008 7 15 2008FA0000347 120080625G5210D4152210000 HINGE DIAMONDA40 DA40 2990002GL REAR CABIN DOOR CRACKED D O OTHER O OTHER NRNOT REPORTED 1 WP074191M 40769 REAR HINGE DEVELOPING CRACKS IN FIBERS. NORMAL OPERATING CONDITION. PROBABLE CAUSE IS REAR HOLD OPEN CYLINDER CAUSING STRESS ON HINGE POINT. (K) 1L71 3O NTA47CE 20080715 CE 2008 7 15 2008FA0000348 120080318G2711EM408810 ACTUATOR RAYTHN390 390 7150030CE ROLL TRIM MALFUNCTIONED B E81RK NONE O OTHER ININSP/MAINT 1 GL03837JM758 RB169 IN CONJUNCTION WITH REPAIRS FOR UNCOMMANDED ROLL, TRIM ACTUATION AT KMDW REPLACED RT ROLL TRIM ACTUATOR (HBC PN 390-3810090010) 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) 1L72 3F RTA00010WI 20080715 CE 2008 7 15 2008FA0000349 120080502G322012434262 TORQUE LINK CESSNA210 210M 2073450CE NLG CRACKED B ONFRK NONE O OTHER ININSP/MAINT 1 EA0570HG 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 RECOMMENDED 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) 1H71 3O 3A21 20080715 CE 2008 7 15 2008FA0000350 120080429G352038101550360 HOSE CESSNA500 560CESSNA 2076750CE LAV OXYGEN LEAKING B E81RK NONE O OTHER ININSP/MAINT 1 GL03501CW 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. RECOMMEND TECH CLOSELY INSPECT CABIN OXYGEN SYSTEM COMPONENTS DURING SCHEDULED INSPECTIONS ON OLDER AND HIGH-TIME SERIES AC FOR AGE RELATED DEFECTS. (K) 2L72 4F RTA22CE 20080715 CE 2008 7 15 2008FA0000351 120080429G5230991434317 LATCH CESSNA500 560CESSNA 2076750CE CARGO DOOR BROKEN B E81RK NONE O OTHER ININSP/MAINT 1 GL03501CW 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 FAILURE RATES NOTED. TECHS SHOULD INSPECT THESE LATCHES CLOSELY DURING SCHEDULED PHASE CHECKS TO PREVENT POSSIBLE DOOR OPENING IN FLIGHT. (K) 2L72 4F RTA22CE 20080715 NM 2008 7 15 2008FA0000352 120080514G571241513017 RIB UNIVAR415 415D 0420306NM LT WING CORRODED D K NONE O OTHER ININSP/MAINT 1 GL09940523674 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 WING PANEL. REMOVED DEFECTIVE PART AND INSTALLED NEW PART (415-13017) SUPPLIED BY MFG. CAUSE OF CORROSION UNKNOWN, AS SURROUNDING STRUCTURE WAS NOT AFFECTED. CORRODED PART IS UNTREATED (NOT CORROSION PROOF IN ANY WAY). SUGGEST WING CENTER SECTION OF THESE AIRCRAFT BE CORROSION PROOFED WITH ACF-50 OR WITH CORROSION X OR EQUIVALENT COMPOUND TO PREVENT FURTHER PROBLEMS OF THIS NATURE. (K) 1L71 3O A787 20080715 CE 2008 7 15 2008FA0000353 120080516G3233 SHAFT BEECH 80 65A80 1152808CE LYC O540 IGSO540B1A 41532EA NLG ACTUATOR LACK OF LUBE D O OTHER O OTHER APAPPROACH 1 SW136AQ 4434 LD214 NOSE LANDING GEAR WOULD NOT DEPLOY ON APPROACH TO LANDING. AFTER NLG REMOVAL, IT WAS DISCOVERED THAT THE NLG ACTUATOR DRIVE SHAFT PN 50820218 INTERNAL SPLINE WAS WORN AND SHEARED. LUBE POINTS ON DRIVE SHAFT TO LUBE SPLINES TO REDUCE WEAR. (K) 1L72 3O3 O 3A20 1E7 20080715 NE 2008 7 15 2008FA0000354 320080603G61107826691 BOLT DHAV DHC8 DHC8202 2809007NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE PROPELLER SHEARED B S88RK NONE O OTHER ININSP/MAINT 1 SO19802MR1613 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 TORQUE SEQUENCE, WE BROKE ONE PROP MOUNTING BOLT. WE SENT THE HUB OUT FOR REPAIR AND SENT THE TORQUE WRENCH TO THE CAL PLACE 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 REPLACED 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 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080715 2008 7 15 2008FA0000355 420080513G2215L109BBM ACTUATOR SKRSKYS76 S76B 8143007NE AUTOPILOT SYS MALFUNCTIONED G O OTHER FP FLT CONT AFFECTED NO WARNING INDICATION CRCRUISE 1 EA63150US 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 WILDLY AND TURN TO THE LEFT WHILE THE AIRCRAFT IS IN STRAIGHT AND LEVEL FLIGHT. ONCE THE FLIGHT DIRECTOR LOSES INPUT THE CYCLIC 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 T1G72 4U H1NE 20080715 GL 2008 7 15 2008FA0000357 120080501G322211907005 STRUT CIRRUSSR SR20 05628AJGL CONT O360 IO360ES SO NLG CRACKED D K NONE O OTHER ININSP/MAINT 1 SO15241CP516 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 RAN FROM THE TOP OF THE ARM. JUST FORWARD OF THE STRUT DATA PLATE, THROUGH THE ENTIRE ARM AND STOPPED AT THE BOTTOM WHERE 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 NOSE WHEEL STOP AND NOSE FORK WAS DAMAGED. POSSIBLE CAUSE COULD BE REPEATED UNREPORTED HARD LANDINGS. WOULD RECOMMENDED ALL1L71 3O3 ONTA00009CHE1CE 20080715 EA 2008 7 15 2008FA0000358 120080519G275060093000123 CONTROL BOX CNDAIRCL600 CL6002B16 1900305EA GE CF34 CF343A 30066NE T/E FLAPS FAILED C O OTHER J WARNING INDICATION APAPPROACH 1 SO03779AZ12 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 INTERMITTENT SIGNAL LOSS ON SIGNAL 2 WHEN INSTALLED ON LEFT WING. SWAPPED UNIT TO RIGHT WING AND FLAPS WOULD CONSISTANTLY FAIL INTERMITTENTLY. 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) 2L72 4F4 FRTA21EA E15NE 20080715 EA 2008 7 15 2008FA0000359 120080521G2750600930035 CONTROL HANDLE CNDAIRCL600 CL6002B16 1900305EA GE CF34 CF343A1 30068NE COCKPIT DAMAGED D K NONE O OTHER ININSP/MAINT 1 SO03779AZ3502 5176 807241 AIRCRAFT HAD BEEN EXPERIENCING MULTIPLE INFLIGHT FLAP FAILURES WHICH WERE NOT DUPLICATED ON THE GROUND. DURING TROUBLESHOOTING 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) 2L72 4F4 FRTA21EA E15NE 20080715 CE 2008 7 15 2008FA0000360 120080515G5720662121126 STIFFENER CESSNA560 560XL 2076702CE PWC 545 PW545B NE LT MLG WW MISINSTALLED B X07RK NONE O OTHER ININSP/MAINT 1 CE07698QS 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/ DAMAGED. (K) 2L72 4F4 FRTA22CE E00059EN 20080715 EA 2008 7 15 2008FA0000361 120080521G275060093000117 FCU CNDAIRCL600 CL6002B16 1900305EA GE CF34 CF343A1 30068NE T/E FLAPS FAILED D O OTHER J WARNING INDICATION APAPPROACH 1 SO03779AZ 5176 807245 AC HAS BEEN EXPERIENCING INTERMITTENT FLAP SYSTEM FAILURES IN DIFFERENT MODES OF FLIGHT, PRIMARILY DURING APPROACH. TROUBLESHOOTING IAW MM RECOMMENDED REPLACEMENT OF FLAP CONTROL UNIT DUE TO IMMEDIATE ( INTERMITTENT) FAILURES AFTER FLAP MOVEMENT SELECTION. AFTER INSTALLATION OF THIS UNIT IN AIRPLANE, FLAPS FAILED TAKEOFF CONFIGURATION WARNING SYSTEM CHECK WHEN 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) 2L72 4F4 FRTA21EA E15NE 20080715 CE 2008 7 15 2008FA0000362 120080507G2910620701098 HYDRAULIC LINE CESSNA650 650 2076802CE HYDRAULIC SYSTEMLEAKING D K NONE O OTHER ININSP/MAINT 1 SO15126MT3822 6500044 NOTED HYDR FLUID LEAKING FROM RT WING IN THE MLG AREA. TROUBLESHOOTING REVEALED A GROUND SPOILER HYD LINE. LOCATED ON THE 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) 2L72 4F A9NM 20080715 EU 2008 7 15 2008FA0000363 120080406G6320350A32030004 GEARBOX SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1A2 60030NE MAIN ROTOR DAMAGED D K NONE O OTHER ININSP/MAINT 1 WP13111AK4093 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) 1G71 3U3 UNCH9EU E19EU 20080715 CE 2008 7 15 2008FA0000364 120080509G2731 TRIM SWITCH CESSNA206 P206B 2073309CE CONT O520 IO520F 17032SO PILOTS YOKE INOPERATIVE D O OTHER O OTHER NRNOT REPORTED 1 NM014711F 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 BENT AND JUMPED BETWEEN WIRE POSTS ON BASE OF SWITCH. RESOLDERED CONNECTION, SEAL WITH HEAT SHRINK AND OPERATED SYSTEM OK. (K) 1H71 3O3 O A4CE E5CE 20080715 EA 2008 7 15 2008FA0000365 220080522G8530SLC36005 CYLINDER CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA ENGINE DAMAGED D K NONE O OTHER ININSP/MAINT 1 NM0121295681 17263925 ENGINE WAS OVERHAULED NOV 2001 USING NEW CILINDER ASSEMBLES. BREAK-IN OPERATION PERFORMED WITH MFG SERVICE INSTRUCTION 1427B AND MINERAL OIL. ENGINE OPERATED NEAR DAILY FLIGHTS AVERAGEING .5 HOUR EACH. REGULAR OIL CHANGES USING 15W50 OIL AND 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 VISIBLE 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 I1H71 3O3 ONT3A12 E274 20080715 CE 2008 7 15 2008FA0000366 120080524G7603 ARM CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA THROTTLE CABLE BROKEN B O6WRK NONE O OTHER ININSP/MAINT 1 GL0575528 17267783 L153076T BOLT CONNECTING CARBURETOR THROTTLE ARM TO THROTTLE CABLE FAILED RESULTING IN THROTTLE STICKING OPEN. PILOT PLACED MIXTURE CONTROL IN IDLE CUTOFF POSITION AND ATTEMPTED TO GLIDE TO RUNWAY AT AIRPORT. AIRCRAFT IMPACTED POWER LINES SHORT OF RUNWAY. BOLT WAS NOT RECOVERED. (K) 1H71 3O3 ONT3A12 E274 20080715 CE 2008 7 15 2008FA0000367 120080522G275099105863 MOTOR CESSNA208 208B 2073701CE TE FLAPS BURNED D B EMER. DESCENT B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 NM04110WY295 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. AFTER RETURNING TO AIRPORT, FOUND SEVERAL CIRCUIT BREAKERS HAD POPPED & FLAPS WERE INOPERATIVE & STUCK AT 10 DEGREES. AVIONICS SHOP REPORTED THE FOLLOWING: HIDDEN DAMAGE INSPECTION PERFORMED. BURNED WIRES FOUND IN WIRE BUNDLE RUNNING FROM MAIN FLAP MOTOR TO CIRCUIT BREAKER PANEL & FROM MAIN FLAP MOTOR TO GROUND BLOCK J66. INSULATION OF ADJACENT WIRES ALONG SAM1H71 3T A37CE 20080715 CE 2008 7 15 2008FA0000368 120080509G2430DOFFO10300J ALTERNATOR CESSNA206 206CESSNA 2073302CE CONT O520 IO520F 17032SO ENGINE SEPARATED D K NONE O OTHER ININSP/MAINT 1 NM014711F P2060311 248025R BODY THRU SCREWS BACKING OUT CAUSING ALTERNATOR HALVES TO START TO SEPARATE, THOUGH NO IMMEDIATE ISSUES WITH AICAFTS CHARGING SYSTEM, NOTICED DISCREPANCY UPON VISUAL INSPECTION AFTER LANDING. (K) 1H71 3O3 O A4CE E5CE 20080715 SO 2008 7 15 2008FA0000369 220080322G7414 GEAR CONT O550 IO550N 17042SO MAGNETO STRIPPED G A UNSCHED LANDING E VIBRATION/BUFFET TOTAKEOFF 1 EA612354B 0077 685811 A PRE-TAKEOFF ENGINE RUNUP WAS SATISFACTORY. SHORTLY AFTER LIFTOFF THE AIRCRAFT BEGAN VIBRATING SUBSTANTIALLY. AFTER REACHING PATTERN ALITUDE, REDUCED POWER AND SWITCHED TO LT MAGNETO OPERATION AND THE ENGINE RAN SMOOTHLY. SWITCHED TO RT MAGNETO OPERATION THE ENGINE ESSENTIALLY DIED AND UPON RETURNING TO "LT" THE ENGINE EXPERIENCED AN AFTER FIRE (AKA BACKFIRE) THEN RAN SMOOTHLY ONCE AGAIN. RETURNED TO THE DEPARTURE AIRPORT AND REMOVED THE ENGINE COWLING. REMOVED THE TIMING PLUG 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 120080507G3220 LEG ASSY CESSNA170 170A 2072304CE ROTAX 912 ROTAX912UL EU NLG BROKEN D O OTHER O OTHER NRNOT REPORTED 1 CE015455C 19489 5645575 NOSE LANDING GEAR LEG BROKEN AT FORWARD WELD ON SHOCK ABSORBER ATTACHMENT BRACKET. EXISTING INTERNAL CRACK. PROBABLE CAUSE, BAD WELD. (K) 1H71 3O3 O A799 EXPE3I 20080718 SO 2008 7 18 2008FA0000371 220080510G8500 ENGINE CESSNA172 172G 2072420CE CONT O300 O300D 17022SO VAPOR LOCK D O OTHER O OTHER NRNOT REPORTED 1 SW19172BX 17254216 24635D1D AC WAS BEING FLOWN ON RT FUEL TANK. AFTER RUNNING TANK DRY, PILOT SELECTED RT FUEL TANK AND MOMENTS LATER THE ENG STOPPED PRODUCING POWER AND MADE AN EMERGENCY LANDING. AC FUEL SYS WAS INSPECTED FOR CONTAMINATES AND FAILURES, NONE WERE FOUND. POSSIBLE CAUSE IS VAPOR LOCK IN FUEL SYS FROM RUNNING FUEL TANK TRY. TO PREVENT THIS FROM RECURRING, WOULD BE TO SELECT ANOTHER FUEL TANK PRIOR TO RUNNING THE SELECT FUEL TANK DRY. (K) 1H71 3O3 ONT3A12 E253 20080715 WP 2008 7 15 2008FA0000372 120080514G633023688 RETAINER HILLERUH12 UH12E 4360122WP LYC O540 VO540* 41532EA M/R TRANSMISSIONMISMANUFACTURED B ZYEGK NONE O OTHER ININSP/MAINT 1 EA251523T 1740 RETAINER SUSPECTED LOCALLY MADE INSTALLATION WORD "UP" IS NOT STAMPED ON PART BUT ETCHED ON BY HAND. THICKNESS OF RETAINER IS .045, ACTUAL PART THICKNESS OF NEW RETAINER IS .051. FOUND SHAFTS THAT ARE SHIMMED WITH BAD RETAINERS TO BE SHIMMED IMPROPERLY DUE TO RETAINER THICKNESS AS REQURIED BY MFG O/H MANUAL. SHAFTS WERE OUT OF TOLERANCE BY .014 TO .020. (K) 1G71 3O3 O 4H11 E304 20080715 SO 2008 7 15 2008FA0000373 120080515G3010488699 TIMER PIPER PA31T PA31T1 7103126SO WING DE-ICE SYS MISMANUFACTURED D K NONE W INADEQUATE Q C ININSP/MAINT 1 NM1093CN 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 WIRING, IT WAS FOUND THAT TWO OF THE WIRES COMING OUT OF THE UNIT WERE SWITCHED DURING MFG AND THE BOXES WERE OPERATING OPPOSITE AS IS INTENDED. THERE ARE FOUR WIRES. RED, BLACK, WHITE AND BLUE. THE WHITE AND BLUE WIRES ARE REVERSED. (K) 1L72 3T A8EA 20080715 SO 2008 7 15 2008FA0000374 120080515G3010488699 TIMER PIPER PA31T PA31T1 7103126SO WING DE-ICE MISMANUFACTURED D K NONE W INADEQUATE Q C ININSP/MAINT 1 NM1093CN 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) 1L72 3T A8EA 20080715 CE 2008 7 15 2008FA0000377 120080701G5730501102715 SKIN BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE RT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 WP197232R8914 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 HAS JUST APPEARED WITHIN THEPAST (2) HOURS OF FLIGHT TIME. CAN PINPOINT THIS TIME FRAME SINCE THE 5 YEAR WING BOLTS REMOVAL AND INSPECTION PROCESS WAS COMPLETED JUST 2 FLIGHT HOURS AGO AND NO WING SKIN CRACKS WERE NOTED/ DOCUMENTED AT THAT T1L72 4T4 T A24CE E4EA 20080718 GL 2008 7 18 2008FA0000378 120080415G7931 TRANSMITTER CIRRUSSR SR22 2130001GL CONT O550 IO550* SO OIL PRESSURE MALFUNCTIONED D O OTHER O OTHER NRNOT REPORTED 1 SO13748CD 0086 FOLLOWING ACTIONS WERE TAKEN AS A RESULT OF A PRECAUTIONARY LANDING, WHERE PILOT REPORTED A LOSS OF OIL PRESSURE. AT CRUISE, AT 8000 FT, OIL PRESSURE ANNUNCIATOR LIGHT ILLUMINATED, OIL PRESSURE GAUGE INDICATED NO OIL PRESSURE. AFTER LANDING, OIL PRESSURE RETURNED TO NORMAL. TECH SUPPORT WAS CONTACTED, RECOMMENDED CHECKING OIL PRESSURE SWITCH CONNECTORS. THEY FEED BOTH ANNUNCIATOR AND GAUGE. CONNECTORS WERE CLEANED, CHECKED FOR INTEGRITY AND RECONNECTED. NO PROBLEMS WERE FOUND. 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 CO1L71 3O3 ONTA00009CHE3SO 20080715 EA 2008 7 15 2008FA0000379 120080530G5541 SPAR SCWZERG164 G164B 3952802EA PWA R1340 R1340* 52016NE RUDDER CORRODED D K NONE O OTHER ININSP/MAINT 1 WP253628D 735B FOUND EXTERNAL CORROSION ON RUDDER MAIN TUBULAR SPAR APPROXIMATELY (2) INCHES ABOVE RUDDER CONTROL HORN. POST WAS SEVERELY CORRODED WITH HOLES THRU TUBE. AD 78-08-09 ADDRESSES THIS PROBLEM BUT NOT FOR THIS MODEL AIRCRAFT. (K) 1Q71 3R3 R 1A16 5E2 20080715 SO 2008 7 15 2008FA0000380 220080303G8520 ENGINE CONT O520 IO520CB 17032SO MALFUNCTIONED D O OTHER O OTHER NRNOT REPORTED 1 SW99 2400 502 OH ENGINE AND RETURNED TO SERVICE APROX (2) YEARS AGO, 600 HOURS OPERATION. ENGINE FAILED WHEN POWER WAS REDUCED ON LANDING. THE COUNTERWEIGHT MANAGED TO HOOK ON THE CYLINDER DECK STUD AND DRAG IT INTO THE CASE, GETTING INVOLVED WITH THE ROTATING COMPONENTS. MASSIVE DAMAGE TO THE ENTIRE ROTATING MASS. IT WAS NOTED ON TEARDOWN THAT AT THE CYLINDER DECK STUDS (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 HOLES, 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 120080401G531212210628 BULKHEAD CESSNA177 177RG 2073709CE FUSELAGE CRACKED B H5GRK NONE O OTHER ININSP/MAINT 1 EA077582V2340 177RG0873 DURING ROUTINE INSP, FOUND PART CRACKED. CHECKED (2) OTHER AC THAT HAPPENED TO BE IN SHOP, FOUND (1) OF THEM TO HAVE A SIMILAR CRACK. THIS SECTION OF BULKHEAD IS ATTACH STRUCTURE FOR LWR ATTACH ANGLE FOR IB FLAP DRIVE BELLCRANK. IT IS CURIOUS THAT THE FACTORY INSTALLED SOME EXTRA REINFORCEMENT STRUCTURE (A BRACKET) IN THIS POSITION IN LT WING. THERE ARE EVEN SOME "PILOT DRILL" (PD) HOLES DRILLED AT FACTORY IN RIB AND HEAVY ATTACH ANGLE ON THE AFFECTED RT SIDE. IT WOULD APPEAR THAT BOTH LT AND RT BELLCRANKS WOULD EXPERIENCE SAME FORE-AFT FORCES BY AIR LOADS ON FLAPS. SO WHY REINFORCE ONLY ONE SIDE? IT IS POSSIBLE THAT FACTORY ASSY LINE NEGLECTED TO INSTALL AN INTENDED SIMILAR REINFORCEMENT ON THE RT SIDE? (1H71 3O A20CE 20080715 EU 2008 7 15 2008FA0000382 120080424G79221586108 REGULATOR BRAERODH125 BAE125800A 1500285EU GARRTTTFE731TFE7315R 01518WP OIL SYSTEM DAMAGED D K NONE O OTHER ININSP/MAINT 1 NM07626CG 258041 P91187 RECEIVED O/H OIL TEMP REGULATOR FROM MFG UNDER THEIR WO 815978-001, DATED 04/22/2008. WHILE PERFORMING INCOMING PARTS INSPECTION 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) 2L72 4F4 FRTA3EU E6WE 20080715 WP 2008 7 15 2008FA0000383 220080523G721031020474 HOUSING MTSBSIMU2 MU2B25 5780409CE GARRTTTPE331TPE33110 01514WP GEARBOX CRACKED B A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 SW15856JT 306 PILOT REPORTED LOW AND FLUCTUATING OIL PRESSURE FROM LEFT ENGINE IN FLIGHT AND ELECTED TO SHUT THE ENGINE DOWN. AN UNEVENTFUL SINGLE ENGINE LANDING WAS MADE. THE ENGINE OIL BYPASS VALVE WAS FOUND TO BE IN THE "POPPED" CONDITION, THE OIL FILTER WAS THEN REMOVED AND FOUND TO BE BLACK IN COLOR WITH THE FORWARD SEALING SURFACE BROKEN IN SEVERAL SMALL PIECES. THE REDUCTION GEAR BOX WAS DISASSEMBLED AND THE OIL PRESSURE PUMP REMOVED. THE FORWARD HOUSING WAS CRACKED APPROXIMATELY (3 INCH) RADIALLY AT FWD DETAIL. (K) 1H72 3T4 T A2PC E4WE 20080718 GL 2008 7 18 2008FA0000384 220080519G726123063413 GEAR BELL 206 OH58B 1181503SW ALLSN 250C T63A720 03002GL AIR/OIL SEPARATRBROKEN D A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 SO05 600 AE405555 PILOT REPORTED ENGINE CHIP LIGHTS ON TAKEOFF. ABORTED MISSION AND RETURNED TO HELIPAD. ENG WAS REMOVED AND SENT FOR INVESTIGATION. ENG RECEIVED FOR REPAIR DUE TO ENG CHIP LIGHTS AND METAL IN OIL. DISASSEMBLY REVEALED AIR OIL SEPARATOR GEAR SHAFT HAD BROKEN WHERE STEM MEETS THE BASE. THIS IS THIRD OCCURRENCE ON THIS PARTICULAR ENG ASSY OF SIMILAR GEAR FAILURES. HAVE SEEN AT LEAST 8 OF THESE FAILURES IN T63 ENGINES SINCE THEY HAVE BEEN RELEASED TO PUBLIC. (K) 1G71 3U3 U H2SW E4CE 20080715 CE 2008 7 15 2008FA0000385 120080605G322166426119 TRUNNION CESSNA560 560XL 2076702CE PWA 545 PW545A NE NLG CORRODED B CWQRK NONE O OTHER ININSP/MAINT 1 GL05640QS6122 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 TRUNNION ASSY. NLG TRUNNION SHOULD BE TREATED TO PREVENT DISSIMILAR METAL CORROSION. FILED SLR NR 363322. (K) 2L72 4F4 FRTA22CE E00059EN 20080715 NM 2008 7 15 2008FA0000387 120080610G5340 ATTACH ANGLE BOEING737 737448 13844BUNM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39742VA (REF DU4R2008212) DURING SCHEDULED INSPECTION, FOUND CORROSION IN AFT LOWER CARGO COMPARTMENT AT STA 727A ATTACH ANGLE GBGETWEEN S-27R AND S-26R. (K) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000388 120080610G5310 DOOR FRAME BOEING737 737448 13844BUNM FUSELAGE CRACKED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39742VA 24773 (REF DU4R2008213) DURING SCHEDULED INSPECTION, FOUND 1 INCH LONG CRACK ON FWD CARGO DOOR CUT-OUT AFT FRAME INNER CHORD RADIUS. (K) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000389 120080610G5330 SKIN BOEING737 737448 13844BUNM BS 887 S19R DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39742VA 24773 (REF DU4R2008214) DURING SCHEDULED INSPECTION, FOUND DENT ON LWR RT LOWER AFT FUSELAGE BS 887 S-19R. (K) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000390 120080610G5347 CARGO TRACK BOEING737 737448 13844BUNM CARGO BAY CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39742VA 24773 DURING SCHEDULED INSPECTION, FOUND CORROSION IN THE AFT CARGO COMPARTMENT LT TIE DOWN TRACK LBL 17.20 FROM STA 727B - STA 727E. PARTICULARLY IN FASTENER HOLE UPPER AND LOWER SURFACE. (K) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000391 120080620G5320141A5505 FLOOR SUPPORT BOEING737 73783N 13844HINM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39318TZ 28247 (REF DU4R2008219) DURING SCHEDULED INSPECTION, FOUND CORROSION ON FLOOR SUPPORT CABIN STA 344, BL-0 TO BL-12L. (K) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000392 120080613G5320 FLOOR SUPPORT BOEING737 737448 13844BUNM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39742VA 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) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000393 120080613G5311 FRAME BOEING737 737448 13844BUNM FUSELAGE DAMAGED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39742VA 24773 (REF DU4R2008217) DURING SCHEDULED INSPECTION, FOUND DOUBLE-DRILLED HOLE ON MAIN FRAME UPPER CAP AT BS 986.5 AT FLOOR LEVEL RT. (K) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000394 120080620G5320141A5410 FLOOR SUPPORT BOEING737 73783N 13844HINM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39318TZ 28247 (REF DU4R2008220) DURING SCHEDULED INSPECTION, FOUND CORROSION ON FLOOR SUPPORT CABIN. STA 340, LBL 11. (K) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000395 120080623G5230 SKIN BOEING737 73783N 13844HINM AFT CARGO DOOR DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39304TZ 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 245010, OPS NR 26681. (K) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000396 120080623G5230 SKIN BOEING737 73783N 13844HINM FWD CARGO DOOR DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39304TZ 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) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000397 120080624G5230 SKIN BOEING737 73783N 13844HINM AFT CARGO DOOR DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39304TZ 30675 (DU4R2008223) DURING SCHEDULED INSPECTION, FOUND DENT IN AFT CARGO DOOR (C-2) EXT. SKIN. S/O NR 245010, N/R 26678. (K) 2L72 4F RTA16WE 20080718 NM 2008 7 18 2008FA0000398 120080630G5340 NUT CLIP BOEING737 73783N 13844HINM BS 967 CHAFED B DU4RO OTHER O OTHER NRNOT REPORTED 1 EA39304TZ 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) 2L72 4F RTA16WE 20080718 NM 2008 7 18 2008FA0000399 120080630G5315 FLOORBEAM BOEING737 73783N 13844HINM BS986 CORRODED B DU4RO OTHER O OTHER NRNOT REPORTED 1 EA39304TZ 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) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000400 120080630G5512 SKIN BOEING737 73783N 13844HINM LT HORIZ STAB DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39308TZ 28244 (REF DU4R2008227) DURING SCHEDULED INSPECTION, FOUND OUT OF LIMITS DENT IN LT HORIZ STAB L/E STA 280. S/O 245008, N/R 21578 (K) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000401 120080630G5512 SKIN BOEING737 73783N 13844HINM HORIZ STAB DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39308TZ 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) 2L72 4F RTA16WE 20080715 NM 2008 7 15 2008FA0000402 120080630G5315 FLOORBEAM BOEING737 73783N 13844HINM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39318TZ 28247 DURING SCHEDULED INSPECTION, FOUND CORROSION ON AFT CABIN FLOORBEAM, BS947, RBL 5 TO LBL5. S/O 245009, N/R 26378 (K) 2L72 4F RTA16WE 20080715 EA 2008 7 15 2008FA0000403 220080616G74144371 MAGNETO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE OUT OF POSITION B Z08RK NONE O OTHER ININSP/MAINT 1 CE07987AP 172S10710 CHECKED THE MAGNETO TIMING AND FOUND THAT BOTH MAGNETOS WERE OFF APPROX 5 DEGREES. CURRENTLY SET AT APPROX 30 DEGREES BEFORE 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 POSITION. ORANGE FACTORY PUTTY NOTED ON MAGNETO HOLDOWN NUTS. IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICALLY TO THE ADVANCED 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. 1H71 3O3 ONT3A12 1E10 20080715 EA 2008 7 15 2008FA0000404 220080617G7414M3820 DISTRIBUTOR BLK SLICK CESSNA182 182T 2072703CE LYC O540 IO540AB1A5 EA MAGNETO MISREPAIRED B Z08RK NONE W INADEQUATE Q C ININSP/MAINT 1 CE07658PW 08011866 18282098 DURING INTERNAL MAGNETO INSPECTION, FOUND DISTRIBUTOR BLOCK SPOT FACED AREA FOR POLES. APPEARS TO BE INCORRECTLY SPOT FACED. MATERIAL THAT WAS LEFT BEHIND HAS THE SAME LOFT AS BEARING BOSS AREA ON DISTRIBUTOR BLOCK. THIS CAUSES THE FINGER ON THE DISTRIBUTOR GEAR TO RUB ON THE DISTRIBUTOR BLOCK. (K) 1H71 3O3 ONT3A13 1E4 20080715 EA 2008 7 15 2008FA0000405 220080616G7414 MAGNETO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE OUT OF POSITION B Z08RK NONE O OTHER ININSP/MAINT 1 CE07227BH 172S10662 DURING A PHASE 2 (100 HR) CHECK THE MAGNETO TIMING AND FOUND THE RT MAGNETO ADVANCED TO APPROXIMATELY 27 DEGREES. MFG SPECS CALL FOR 25 DEGREES. LAST CHECK AT 90 HOURS PRIOR, FOUND TO BE OK. SUSPECT MAGNETO DRIFTING IS OCCURING. THE MAGNETOS 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) 1H71 3O3 ONT3A12 1E10 20080715 EA 2008 7 15 2008FA0000406 220080611G74144371 MAGNETO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA POWERPLANT OUT OF POSITION B Z08RK NONE O OTHER ININSP/MAINT 1 CE07712DS98 172S10711 L3404451 DURING THE AC FIRST PHASE 2 INSPECTION (100 HR) FOUND THAT BOTH MAGNETOS WERE OFF APPROXIMATELY 5 DEGREES. CURRENTLY SET 30 DEGREES BEFORE TOP DEAD CENTER PLUS (MFG SUM SAYS 25 DEGREES BTDC) THE AIRCRAFT MAGNETO TO ENGINE TIMING WAS CHECKED WHEN NEW, SHORTLY AFTER DELIVERY 4/25/2008, 4.3 HRS 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 POSITION IN 93 HOURS TIS. THE MAGNETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOING ISSUE WITH MFG OF ENGINE AND MFG OF MAGNETO SB2-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS AS IN THIS C1H71 3O3 ONT3A12 1E10 20080715 EA 2008 7 15 2008FA0000407 220080611G74144371 MAGNETO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA OUT OF POSITION B Z08RK NONE O OTHER ININSP/MAINT 1 CE07712DS 172S10711 L3404451E DURING THE AC FIRST PHASE 2 INSP (100 HR) FOUND THAT BOTH MAGNETOS WERE OFF APPROX 5 DEGREES. CURRENTLY SET 30 DEGREES BEFORE TOP DEAD CENTER PLUS MFG SRM SAYS 25 DEGREES BTDC). THE AIRCRAFT MAGNETO TO ENGINE TIMING WAS CHECKED WHEN NEW, SHORTLY 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 POSITION 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) 1H71 3O3 ONT3A12 1E10 20080715 SO 2008 7 15 2008FA0000408 120080528G32463080D WHEEL PIPER PA23 PA23250 7102308SO LYC O540 IO540* 41532EA LT MLG CORRODED C K NONE O OTHER ININSP/MAINT 1 SO27959C 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 HAD LSAST BEEN DISASSEMBLED 217 HOURS AGO. (K) 1L72 3O3 O 1A10 1E4 20080715 SO 2008 7 15 2008FA0000409 120080607G243432C22491 ALTERNATOR PIPER PA32 PA32R301 7103218SO LYC O540 IO540K1G5 41532EA DAMAGED D O OTHER S AFFECT SYSTEMS NRNOT REPORTED 1 EA1330969 3246230 L3047448A 4 SCREWS THAT HOLD THE RECTIFIER PLATE INTO THE BACK CASE OF ALTERNATOR CAME LOOSE AND CONTACTED THE ROTOR, DESTROYED ALTERNATOR. (K) 1L71 3O3 O A3SO 1E4 20080715 EA 2008 7 15 2008FA0000410 220080527G72503013411 TURBINE AYRES S2 S2RT34NORMAL0970106SO PWA PT6 PT6A34 52043EA ENGINE DAMAGED G O OTHER O OTHER NRNOT REPORTED 1 SW113105E1026 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) 1L71 3T4 T A3SW E4EA 20080715 CE 2008 7 15 2008FA0000411 120080612G3230 ROD END CESSNA310 T310Q 2074244CE LYC O360 IO360A1A 41514EA LANDING GEAR BROKEN G O OTHER O OTHER CLCLIMB 1 EA397044Q T310Q0204 AFTER TAKEOFF, WHEN RETRACTING GEAR, PILOT HEARD LOUD CRACK. NOSE GEAR WOULD NOT RETRACT. AIRCRAFT LANDED WITH NOSE GEAR TRAILING AFT. NOSE GEAR COLLAPLSED ON LANDING. INSPECTION REVEALED ROD END UNDER PILOT`S FLOOR THAT CONNECTS NOSE GEAR RETRACT ROD TO BELLCRANK SEPARATED CAUSING NOSE GEAR TO BECOME DISCONNECTED FROM LANDING GEAR TRANSMISSION. 1L72 3O3 O 3A10 1E10 20080717 NE 2008 7 17 2008FA0000412 220080528G7510101910026191 CONTROL ARM BEECH 200 B200 1152922CE PWA PT6 PT6A42 52043NE LT NACELLE WORN B CWNRO OTHER O OTHER NRNOT REPORTED 1 WP096604L100 BB1121 LT ENGINE NACELLE ICE-VANE CONTROL ARM HAD WORN OUT OR DESTROYED BUSHINGS AT ALL 3 ACTUATING CONTROL ARM DRIVE POINTS AND 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) 1L72 4T4 T A24CE E4EA 20080715 GL 2008 7 15 2008FA0000413 320080423G611405522311 BULKHEAD CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA MCAULY1A170 1A170E GL PROPELLER CRACKED D K NONE O OTHER ININSP/MAINT 1 EA23897LP570 172S8897 REPEATED FINDINGS OF CRACKS AT EDGE OF WASHER FOOT PRINT. ALLOY CHANGE, OR HARDWARE CHANGE MAY HELP. (K) 1H71 3O3 ONT3A12 1E10 5 NP857 20080715 EA 2008 7 15 2008FA0000414 220080701G7310RSA5AD1 INJECTOR CESSNA182 182T 2072703CE LYC O540 TIO540AK1A EA FUEL SERVO CLOGGED G O OTHER R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 EA23101LP569 T18208265 L1165861A PLANE LOST ENGINE POWER, BECAME VERY LEAN, COULD NOT GET FUEL FLOW> 9 GPH. TURNED OUT TO BE ALUMINUM SHAVING FROM ORIGINAL MFG OF FUEL SERVO. CLOGGED MIXTURE HOLE INSIDE FUEL SERVO. THIS WAS A DEFECT FROM TIME OF MANUFACTURE OF FUEL SERVO. EMERGENCY LANDING. (K) 1H71 3O3 ONT3A13 20080718 2008 7 18 2008FA0000415 220080505G7414S6LSC204T MAGNETO BEECH 58 58 1152740CE ENGINE FAILED B NW4RO OTHER O OTHER NRNOT REPORTED 1 SO15142DR4 TH1458 SMOKE WAS REPORTED IN COCKPIT. UPON INVESTIGATION, FOUND PIN HOLE CORRODED IN METAL LINE CLOSE TO AIR CONDITIONER BLOWER 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 MAGNETO. 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) 1L72 3O 3A16 20080715 SO 2008 7 15 2008FA0000416 120080609G5720494718 TAPE PIPER PA28 PA28161 7102803SO WING PEELING D O OTHER O OTHER NRNOT REPORTED 1 NE028369A 288116198 STUDENT PILOT DECLARED AN EMERGENCY AS HE THOUGHT NOISE HE WAS HEARING WAS HIS ENGINE COMING APART. AFTER SAFELY LANDING 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. REMOVED THE OLD WING WALK MATERIAL AND INSTALLED NEW PIECE. (K) 1L71 3O 2A13 20080715 SO 2008 7 15 2008FA0000418 120080628G3246 WHEEL PIPER PA23 PA23250 7102308SO LYC O540 IO540* 41532EA RT MLG BROKEN D PP4RO OTHER O OTHER NRNOT REPORTED 1 EA39959C 217 278154029 DIFFICULTY WAS ENCOUNTERED WHILE AN AMT WAS REMOVING THE RETAINING NUT FROM THE AXLE ON THE RT MAIN GEAR OF AC. HE STOPPED AND DEFLATED THE TIRE. THE WHEEL ASSEMBLY WAS THEN REMOVED WITHOUT RESISTANCE. AFTER REMOVAL ALL BUT ONE OF THE ASSEMBLY RETAINING BOLTS WERE FOUND BROKEN AND THE WHEEL HALVES WERE ALSO BROKEN. CORROSION CAUSED THE PROBLEM. THE WHEEL HAD ACCUMULATED 217 HOURS SINCE IT WAS LAST DISASSEMBLED AND INSPECTED. TT ON THE WHEEL IS UNKNOWN. THE ENTIRE WHEEL ASSEMBLY WAS REPLACED. (K) 1L72 3O3 O 1A10 1E4 20080715 GL 2008 7 15 2008FA0000419 120080618G5210DA4522100002 DOOR DIAMONDA40 DA40 2990002GL REAR PAX DOOR DEPARTED G A UNSCHED LANDING D INFLIGHT SEPARATION TOTAKEOFF 1 WP28686US615 40640 ON TAKE-OFF ROLL AT VR, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1L71 3O NTA47CE 20080715 GL 2008 7 15 2008FA0000420 120080618G5344 HINGE DIAMONDA40 DA40 2990002GL DOOR CRACKED G K NONE O OTHER ININSP/MAINT 1 WP28686US 40640 FOUND CRACKS IN AFT DOOR HINGE. (K) 1L71 3O NTA47CE 20080715 GL 2008 7 15 2008FA0000421 120080618G5210DA4522100002 DOOR DIAMONDA40 DA40 2990002GL REAR PAX DOOR DEPARTED G O OTHER D INFLIGHT SEPARATION TXTAXI/GRND HDL 1 WP28605US225 40675 WHILE TAXIING INOT TAKEOFF POSITION ON RUNWAY, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1L71 3O NTA47CE 20080715 GL 2008 7 15 2008FA0000422 120080616G5210DA4522100002 DOOR DIAMONDA40 DA40 2990002GL AFT PAX DOOR DEPARTED G O OTHER D INFLIGHT SEPARATION CLCLIMB 1 WP28605US536 40675 ON TAKEOFF CLIMBOUT, AFT PASSENGER DOOR DEPARTED AIRFRAME. 1L71 3O NTA47CE 20080715 GL 2008 7 15 2008FA0000424 120080616G5210DA4522100002 DOOR DIAMONDA40 DA40 2990002GL REAR PASSENGER DEPARTED G O OTHER D INFLIGHT SEPARATION CLCLIMB 1 WP28605US 40675 ON TAKEOFF CLIMBOUT, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K) 1L71 3O NTA47CE 20080715 GL 2008 7 15 2008FA0000426 120080618G5344 HINGE DIAMONDA40 DA40 2990002GL DOOR CRACKED G O OTHER O OTHER NRNOT REPORTED 1 WP28686US 40640 FOUND CRACKS IN AFT DOOR HINGE. (K) 1L71 3O NTA47CE 20080717 NM 2008 7 17 2008FA0000427 120080601G275118195816 TRANSMITTER BOEING767 767241 1385115NM GE CF6 CF680C2* GL FLAP POSITION FAULTY W TAMFA UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 SO23770QT 23802 LT FLAP DID NOT MOVE FROM 1 TO UP POSITION. FLIGHT RETURNED TO DEPARTURE. REMOVED AND REPLACED PROXIMITY SENSORS S282 AND 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 103. FLAP POSITION TRANSMITTER NR 5 WAS REMOVED AND REPLACED IAW MM 27-51-45, PG 201-222, OPS CHECK NORMAL, OVERWEIGHT LANDING INSPECTION WAS ACCOMPLISHED IAW MM 05-51-35 PHASE I, OPTION A, PG 201-203, NO DAMAGES WERE FOUND. (K) 2L72 4F4 FRTA1NM E23EA 20080718 2008 7 18 2008FA0000428 420080610G3420 LIGHT BOEING767 767241 1385115NM GE CF6 CF680C2* GL ALTITUDE INDICATILLUMINATED W TAMFO OTHER J WARNING INDICATION NRNOT REPORTED 1 SO23770QT 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) 2L72 4F4 FRTA1NM E23EA 20080717 CE 2008 7 17 2008FA0000429 120080605G322266420003 PISTON CESSNA500 560CESSNA 2076750CE NLG LOOSE B CWQRO OTHER O OTHER NRNOT REPORTED 1 GL05351QS1556 5600451 ( REF CWQR200801) DURING A1-5 PHASE INSPECTION, FOUND EXCESSIVE PLAY INT HE NOSE GEAR FWD AND AFT PLAY CHECK. AFTER FURTHER 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 363222 WITH MFG. (K) 2L72 4F RTA22CE 20080717 EA 2008 7 17 2008FA0000430 120080625G32307455025 CONTROL PANEL CNDAIRCL600 CL6002B16 1900305EA GE CF34 CF34* 30015NE MLG MALFUNCTIONED B RO3RO OTHER O OTHER NRNOT REPORTED 1 CE03614BA1176 5614 LANDING GEAR HANDLE DIFFICULT TO ACTUATE TO UP POSITION. REQUIRED MULTIPLE ATTEMPTS TO ACTUATE GEAR HANDLE. FOUND LIGHTED COVER PANEL LOOSE ON GEAR HANDLE ASSEMBLY. REMOVED LIGHT PANEL TO INVESTIGATE. FOUND ONE SCREW FROM BACKSIDE OF PANEL HAD FALLEN OUT AND WAS INTERFERING WITH GEAR UP RELEASE MECHANISM. REINSTALLED SCREW AND TIGHTENED ALL OTHERS . REINSTALLED LIGHT PANEL. PREFORMED MULTIPLE GEAR SWINGS, NO FAULTS NOTED. (K) 2L72 4F4 FRTA21EA 20080718 NM 2008 7 18 2008FA0000431 120080630G5320715K9004507 ANGLE BOEING717 717200 1383700NM BS 26 CRACKED A MWEAO OTHER O OTHER NRNOT REPORTED 1 GL13970ME 65171 RT UPPER BUCKET, FWD OB Z-FRAME IS CRACKED AT STA 26 APPROXIMATELY 1 INCH LONG. FABRICATED AND INSTALLED ANGLE. (K) 2L72 4F TRA6WE 20080717 CE 2008 7 17 2008FA0000432 120080602G3260602EN166B DOWNLOCK SWITCH CESSNA501 551 2076605CE PWA JT15 JT15D4 52112NE RT MAIN GEAR INOPERATIVE B UPWRO OTHER P NO WARNING INDICATION LDLANDING 1 GL03502CL 5510002 RT MAIN GEAR GREEN INDICATOR DID NOT ILLUMINATE WHEN GEAR EXTENDED GOING INTO LAND. CYCLED GEAR AND GREEN INDICATOR LIGHT REMAINED OUT. AC LANDED WITHOUT INCIDENT. RT MAIN GEAR DOWNLOCK SWITCH FOUND TO BE FAULTY. (K) 1L72 4F4 F A27CE E1NE 20080717 EA 2008 7 17 2008FA0000433 120080521G275160093000123 ASYMMETRY SWITCH CNDAIRCL600 CL6002B16 1900305EA GE CF34 CF343A1 30068NE TE FLAPS FAILED D O OTHER J WARNING INDICATION NRNOT REPORTED 1 CE21779AZ 5176 FLAPS FAIL FOUR DEGREES AFTER SELECTION. USING BREAKOUT BOX, SELECTED THIS BDU AND FLAPS WOULD CONSISTENTLY FAIL. SELECTED OTHER SIDE BDU AND FLAPS WOULD OPERATE NORMALLY. UNIT ALSO RATTLES ON BENCH WHEN CHECKING DRAG TORQUE (UNLOCKED). (K) 2L72 4F4 FRTA21EA E15NE 20080717 2008 7 17 2008FA0000434 120080605G2560 RELEASE MECH SEAT BELT FAILED D O OTHER O OTHER NRNOT REPORTED 1 WP25 SEAT BELT WILL RELEASE WITHOUT PULLING ON THE RELEASE BUCKLE. DURING FLIGHT THE SEAT BELT CAME UNDONE WITHOUT ANYONE PHYSICALLY UNLATCHING THE BELT. CAUSE WAS DUE TO DEFECTIVE LATCH MECHANISM. ALL BELTS WITH CERTAIN BATCH NUMBERS ARE DEFECTIVE. (1-954/784-3178 MFG) (K) 20080717 NM 2008 7 17 2008FA0000435 120080627G3213656174010 CYLINDER BOEING BOEING737 7373B7 1384580NM MLG CRACKED B O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 WP07514AU XC92439 23700 AFTER AIRCRAFT TOW, FLUID WAS OBSERVED LEAKING FROM .5 INCH CRACK (APPROXIMATE) IN THE OUTER CYLINDER OF THE LT MLG SHOCK STRUT. THE CRACK IS LOCATED APPROXIMATELY 26 INCHES BELOW THE SHOCK STRUT AIR VALVE. (K) 2L72 4F RTA16WE 20080717 SO 2008 7 17 2008FA0000436 220080506G8530SA52006A1 CYLINDER BEECH 35 V35 1151538CE CONT O520 IO520BA 17032SO NR 4 CRACKED B BJFRO OTHER O OTHER NRNOT REPORTED 1 EA232024W 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 EQUIPMENT. THIS FACILITIES OPINION IS THAT POOR CASTING TECHNIQUES BY THE MFG LEFT STRESS POINTS FOR THE FORMATION AND CONTINUATION OF CRACKS, AND MORE THAN LIKELY, ANY CYLINDER NOT YET CRACKED, PROBABLY WILL. (K) 1L71 3O3 O 3A15 E5CE 20080717 2008 7 17 2008FA0000437 420080618G221131B641 TRIM SWITCH BEECH 90 C90 1152913CE PWA PT6 PT6A21 52043EA CONTROL WHEEL FAILED B QPIDO OTHER O OTHER NRNOT REPORTED 1 SO19362MC 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 ADVISED REPLACEMENT OF SUSPECTED BAD TRIM SWITCH ASSY AT THIS TIME AS CAUSE OF REPEATED FAILURE. SWITCHES IN ASSY FAILED ALLOWING BOTH UP & DOWN COMMANDS AT THE SAME TIME. TRIM SWITCH ASSY PROVIDED BY MFG, WAS REPLACED & COMPUTER REPAIRED & REINSTALLED. TRIM CIRCUITRY FAILED AGAIN AFTER 3 HOURS OF FLT. COMPUTER REPAIRED & REINSTALLED. TRIM CIRCUITRY FAILED ON INITIAL CHECKOUT. COMPUTER REMOVED FOR REPAIR & TRIM SWITCH CONFIRMED TO BE CAUSING FAILURE AGAIN. TRIM UP SWITCH STUCK I1L72 3T4 T 3A20 E4EA 20080717 CE 2008 7 17 2008FA0000438 120080630G2910605700311 HOSE LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE HYD SYSTEM FAILED E JBGAO OTHER O OTHER NRNOT REPORTED 1 SW11260AN5025 124 PCECA0083 PILOT REPORTED A LOSS OF HYDRAULICS DURING FLIGHT AT CRUISE FL400. INSPECTION REVEALED THAT THE RT ENGINE DRIVEN HYDRAULIC PUMP, PRESSUE SIDE HYDRAULIC LINE WAS LEAKING, AND ALLOWED THE AIRCRAFT`S HYDRAULIC SYSTEM FLUID TO BE DEPLETED. FURTHER INSPECTION REVEALED THAT THE LINE HAD FAILED INTERNALLY AND WHEN PRESSURE WAS APPLIED THE HOSE WOULD SWELL AND BEGIN TO LEAK. THE PROBABLE CAUSE OF THE FAIURE IS AGE AND POSSIBLE EMBRITTLEMENT OF THE HOSE. TO POSSIBLY PREVENT RECURRENCE OF SUCH FAILURES AT TIME INTERVAL FOR REPLACEMENT OF AGEING TEFLON HOSES MAY BE NEEDED. (K) 2L72 4F4 FRTA10CE E35NE 20080717 GL 2008 7 17 2008FA0000439 120080701G2430 BEARING CAP CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO HARTZLHCJ3Y PHCJ3YF1 GL ALTERNATOR CASE CRACKED B YD5RO OTHER O OTHER NRNOT REPORTED 1 GL15391CP 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) 1L71 3O3 ONTA00009CHE3SO 5 CP36EA 20080717 SW 2008 7 17 2008FA0000440 120080610G6720206011725001 ROD BELL 206 206L3 1182108SW ALLSN 250C 250C30 03013GL T/R PITCH CHAFED B ULXRO OTHER O OTHER NRNOT REPORTED 1 WP01600W 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 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 BELLCRANK AND THE RIVETED END CONNE1G71 3U3 U H2SW E1GL 20080717 GL 2008 7 17 2008FA0000441 220080604G723023009670 BEARING BELL 407 407 1182206SW ALLSN 250C 250C47B GL COMPRESSOR FAILED B O OTHER J WARNING INDICATION NRNOT REPORTED 1 SO053WV CAC45603 53713 CAE847787 PILOT REPORTED ENGINE CHIP LIGHT PRECAUTIONARY LANDING MADE TO INVESTIGATE. A CONSIDERABLE AMOUNT OF FERROUS MATERIAL WAS ON THE TOP AND BOTTOM CHIP DETECTORS. NO PENALTY RUNS WERE PERFORMED. AIRCRAFT WAS PLACED ONTO A TRAILER AND MOVED BACK TO BASE WHERE THE ENGINE WAS REMOVED AND FORWARDED TO THE ENGINE SHOP FOR INVESTIGATION. THE DISMANTLE AND INVESTIGATION 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 SPALLING. THE FAILED BEARING WAS REPLACED, THE REMAINDER OF THE ENGINE OIL SYSTEM WAS FLUSHED WITH NO DISCREPANCIES NOTED. E1G71 3U3 UO H2SW E1GL 20080717 2008 7 17 2008FA0000442 120080701G3610AS18954175 COUPLING CFMINTCFM56 CFM567B26US NE ENGINE DUCT MISSING G O OTHER O OTHER NRNOT REPORTED 1 EA33 894464 DURING GROUND RUN AFTER INSTALLATION, HOT AIR ESCAPED FROM THE NOSE COWL ANTI-ICE DUCT AT THE 12 O`CLOCK POSITION CAUSING THERMAL DAMAGE TO THE C-DUCT THERMAL BLANKETS AND TRUST LINK TEFLON WASHERS. INVESTIGATION FOUND DUCT COUPLING PN AS1895-4-175 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 220080617G8530 GUIDE CESSNA210 T210N 2073456CE CONT O550 IO550P 17216EA EXHAUST VALVE OUT OF TOLERANCEC B3ORK NONE O OTHER ININSP/MAINT 1 SW036621A 21063559 AFTER NUMEROUS ATTEMPTS TO TROUBLESHOOT FREQUENT ENGINE MISFIRES OCCURRING PRIMARILY IN THE INITIAL CLIMB STAGES OF FLIGHT, THE ENGINE VALVE TRAIN WAS INSPECTED FOR STICKING VALVES. DIMENSIONAL INSPECTIONS OF THE EXHAUST VALVE GUIDES IN ALL 6 CYLINDERS REVEALED THAT THE EXHAUST VALVE GUIDES WERE BELOW THE MINIMUM ACCEPTABLE DIAMETERS AS PUBLISHED IN THE APPLICABLE O/H MANUAL. IT IS BELIEVED THAT THE EXCESS MATERIAL EXISTS BECAUSE THE GUIDES WERE NOT MEASURED OR REAMED DURING THEMFG ASSY PROCESS. CORRECTIVE ACTION NOT AVAILABLE AT THIS TIME. (K) 1H71 3O3 O 3A21 E3SO 20080717 2008 7 17 2008FA0000444 420080609G6113 BULKHEAD CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA PROP SPINNER CRACKED B OMKRK NONE O OTHER ININSP/MAINT 1 NM03537SP 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 BOLT HOLES WERE FOUND TO BE CRACKED IN THE SAME LOCATION (OUTER APEX OF WASHER IMPRESSION), RANGING FROM .2500 TO 1.0 IN LENGTH. THE MM HAS A NOTE THAT SAYS, "THE MOUNTING BOLT HOLES IN THE FORWARD BULKHEAD MAY BE UNDERSIZED DUE TO THE ORIGINAL TORQUING OF THE MOUNTING BOLTS". IT IS PLAIN TO SEE THIS CRUSHES THE ALUMINUM, CASUING STRESS CONCENTRATIONS AROUND 1H71 3O3 ONT3A12 1E10 20080717 CE 2008 7 17 2008FA0000445 120080611G52101014300329 PIN BEECH B300 B300 1159232CE PWA PT6 PT6* 52043EA PAX DOOR MISSING B XA14O OTHER O OTHER NRNOT REPORTED 1 SW1710TX 3132 FL1 UPPER AFT ENTRANCE DOOR BAYONET SHIFTED OB .7500 INCH CAUSING AC TO DEPRESSURIZE. THIS WAS CAUSED BY A PIN (PN 101-430032-9) 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 50-430032-3 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) 2L72 4T3 TRTA24CE E2NE 20080717 2008 7 17 2008FA0000446 120080109G350080130700 CYLINDER OUT OF TOLERANCEB AY54O OTHER O OTHER NRNOT REPORTED 1 EA35GEZJO OXYGEN CYLINDER (PN 801307-00, SN ST26121) ARRIVED AT WORKSHOP ON 9TH JAN, 2008, REMOVED OFF OF G-EZJO FOR HAVING LOW CONTENTS 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 USED. (K) 20080717 GL 2008 7 17 2008FA0000447 220080529G725023073853 TURBINE WHEEL ALLSN 250C 250C20B 03013GL ENGINE FAILED B K NONE O OTHER ININSP/MAINT 1 SO05 1036 CAT34953 TURBINE ASSY RECEIVED FOR REPAIR DUE TO METAL IN OIL. UPON DISASSEMBLY, IT WAS NOTED THAT THE 1ST STAGE TURBINE WHEEL BLADES 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 OUTER RACE. THE DOWNSTREAM PORTION OF THE STATOR SEAL BELOW THE FRACTURE REMAINED STATIONARY AND THE GRINDING BETWEEN THE STATIONERY PORTION OF THE SEAL AND THE ROTATING PORTION APPEARS TO BE THE SOURCE OF THE METAL. THE TURBINE WHEEL BLADE TIPS 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 220080618G72501975M56G03 NOZZLE BOEING777 777224 1385225NM GE GE90 GE9092B 30036NE ENGINE FAILED B QEMYO OTHER O OTHER NRNOT REPORTED 1 EA35780083927717271 29478 900240 ENGINE SUFFERED AN OVERTEMP AND HPC/HPT ROTOR VIBRATION EXCCEEDANCE. THE CUSTOMER REPORTED METAL PARTICLES IN THE EXHAUST. DURING ENGINE MODULE DISASSEMBLY AT MFG, IT WAS NOTED THAT THE HPT STAGE 2 NOZZLE ASSY EXHIBITED SIGNIFICANT HARDWARE DAMAGE TO THE NOZZLE SEGMENTS, STAGE 1 AND STAGE 2 SHROUDS. (K) 2L72 4F4 FRTT00001SEE00049EN 20080718 SO 2008 7 18 2008FA0000449 120080701G53407955300 FITTING PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA FUSELG TO WNDSHDCORRODED D O OTHER O OTHER NRNOT REPORTED 1 SO15602FT 2841196 STEEL FITTINGS (PN 79553-00) LT AND (PN 79553-01(RT) WERE FOUND WITH SEVERE CORROSION DURING LT AND RT WINDSHIELD REMOVAL, THOSE FITTINGS 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, FOUND SAME PROBLEM IN OTHER AC. (K) 1L71 3O3 O 2A13 E274 20080717 SO 2008 7 17 2008FA0000450 120080701G53407955301 FITTING PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA FUSLG TO WNDSHLDCORRODED D O OTHER O OTHER NRNOT REPORTED 1 SO15602FT 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 PROBLEM IN OTHER AC. (K) 1L71 3O3 O 2A13 E274 20080718 GL 2008 7 18 2008FA0000451 120080609G7810 ELBOW CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO RT EXHAUST MISINSTALLED G K NONE W INADEQUATE Q C ININSP/MAINT 1 NM04266SR 2626 WHILE ACCOMPLISHING SERVICE ADVISORY 08-03 IT WAS DISCOVERED THAT RT SIDE EXHAUST ELBOW WHICH IS INSERTED BETWEEN WASTEGATE OUTLET FITTING AND TAILPIPE WAS ORIGINALLY INSTALLED BACKWARDS A THE FACTORY. THIS INCORRECT INSTALLATION RESULTED IN 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 EXHAUST GAS PATH. (K) 1L71 3O3 ONTA00009CHE3SO 20080717 EU 2008 7 17 2008FA0000452 120080610G3411 PITOT TUBE AEROSPATR72 ATR72212 8680945EU PWA PW120 PW127 NE OBSTRUCTED D C ABORTED TAKEOFF P NO WARNING INDICATION TOTAKEOFF 1 EA21820FX 248 ON TAKEOFF ROLL THE F/O AIRSPEED INDICATOR REMAINED AT ZERO. THE TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE GATE. MAINTENANCE FOUND FOD (SPIDER) IN THE PITOT TUBE. THE TUBE WAS CLEARED AND THE SYSTEM CHECKED GOOD. THE AIRCRAFT WAS RETURNED TO SERVICE. (K) 2H72 4T4 TRTA53EU E20NE 20080717 SO 2008 7 17 2008FA0000453 120080510G3220 BUNGEE PIPER PA28 PA28R201T 7102813SO LT NOSE WHEEL BROKEN G O OTHER O OTHER NRNOT REPORTED 1 WP119581C 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 GREEN NOSE LIGHT. THE PILOT ASSUMED THAT DUE TO PREVIOUS PROBLEMS WITH THE LANDING GEAR INDICATOR LIGHTS THAT THE NOSE GEAR 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) 1L71 3O 2A13 20080718 CE 2008 7 18 2008FA0000454 120080630G551045A21085003 BRACKET BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE HORIZONTAL STAB CRACKED B E81RK NONE O OTHER ININSP/MAINT 1 GL03184AR4512 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 INCORPORATED INTO MM 5-20-02 INSP GUIDE AND SECTION 55-30-00. (K) 2H72 4F4 FRTA16SW E25EA 20080718 CE 2008 7 18 2008FA0000455 120080626G2435M835366026L RELAY RAYTHN390 390 7150030CE STARTER GEN STUCK B E81RK NONE O OTHER ININSP/MAINT 1 GL03404JM444 RB167 INVESTIGATED PILOT REPORT OF RT ENG STARTER/GEN NOT DISENGAGING FROM START FUNCTION AFTER ENG START. FOUND 80K5 RT ENG START LATCH RELAY STUCK IN START FUNCTION. RT STARTER/GEN TERMINAL COVER AND COOLING AIR INLET DUCT SHOW SIGNS OF OVERHEATING. INSPECTED STARTER/GEN, REPLACED 80K5 RELAY, STARTER/GEN FUNCTIONS NORMAL. HAVE REPLACED NUMEROUS 80K3 AND 80K5 START 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) 1L72 3F RTA00010WI 20080718 CE 2008 7 18 2008FA0000456 120080626G30205188001 VALVE RAYTHN390 390 7150030CE ANTI ICE SYSTEM STUCK B E81RK NONE O OTHER ININSP/MAINT 1 GL03404JM 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 ASSY SUBJECTED TO HIDDEN INTERNAL DAMAGE DUE TO ROUGH HANDLING DURING SHIPPING. (K) 1L72 3F RTA00010WI 20080718 SO 2008 7 18 2008FA0000457 220080710G741407010003 MAGNETO CIRRUSSR SR20 05628AJGL CONT O360 IO360ES SO LEFT BURNED D GICRK NONE O OTHER ININSP/MAINT 1 NM01662AJ 1632 DURING ROUTINE MAINT, THE LT MAGNETO WAS DISCOVERED OUT OF TIME TO ENGINE. WAS UNABLE TO RE-TIME MAG WITHOUT RE-STABBING. WHEN REMOVED, OPENED COVER AND FOUND INTERNAL PLASTIC COMPONENTS BURNED WITH SIGNIFICANT AMOUNT OF LOOSE (BURNED) PLASTIC PARTS LOOSE WITHIN MAGNETO. THIS MAGNETO WAS SUPPLIED WITH NEW ENGINE 261.3 HOURS AGO, OTHER THAN MAG TO ENGINE TIMING 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) 1L71 3O3 ONTA00009CHE1CE 20080718 CE 2008 7 18 2008FA0000458 120080702G323050452112 FORK CESSNA340 340A 2076405CE CONT O520 TSIO520* 17040SO MLG FRACTURED G K NONE O OTHER ININSP/MAINT 1 GL1760PP 340A0073 LANDING GEAR DOWN ACTUATION ON 7/2/2008 PRODUCED AN INDICATED UNSAFE NOSE LANDING GEAR LIGHT. AN ATTEMPT TO ACTUATE MANUAL EXTENSION OF THE LANDING GEAR PROVED UNSUCCESSFUL SINCE THE NOSE LANDING GEAR DID NOT EXTEND TO A DOWN AND LOCKED POSITION. 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 DEGRADATION TO THE STRUCTURE OF THIS COMPONENT EXISTED PRIOR TO FAILURE OF THIS COMPONENT. (K) 1L72 3O3 O 3A25 E8CE 20080718 SW 2008 7 18 2008FA0000459 120080701G2400102149 METER BELL 206 206B 1181511SW ALLSN 250C 250C20J 03013GL MALFUNCTIONED C DDZRO OTHER O OTHER NRNOT REPORTED 1 CE036BU 7003 4034 CAE270422 AC MAINT HOBBS METER FOUND RUNNING SLOW. THIS PROBLEM CAUSES THE ACTUAL TT OF THE AC TO BE INCORRECT. THIS PROBLEM CAUSED THE AC TO OVER RUN INSPECTIONS, AND TIME LIFE ITEM. PROBABLE CAUSE OF THIS PROBLEM, HOBBS METERS GETTING OLD AND WORN OUT. RECOMMENDATION TO PREVENT THIS PROBLEM: MAINT HOBBS METER, TO BE CHECKED BY PILOTS CLOCK WEEKLY TO MAKE SURE METER IS RUNNING PROPERLY. (K) 1G71 3U3 U H2SW E4CE 20080718 SW 2008 7 18 2008FA0000460 120080701G2400102149 METER BELL 206 206L4 1182110SW ALLSN 250C 250C30P 03013GL MALFUNCTIONED B DDZRO OTHER O OTHER NRNOT REPORTED 1 CE0375TV 7845 52095 CAE895710 AC MAINT HOBBS METER FOUND RUNNING SLOW. THIS PROBLEM CAUSES THE ACTUAL TT OF THE AC TO BE INCORRECT. THIS PROBLEM CAUSED THE AC TO OVER RUN INSPECTIONS, AND TIME LIFE ITEM. PROBABLE CAUSE OF THIS PROBLEM, HOBBS METERS GETTING OLD AND WORN OUT. RECOMMENDATION TO PREVENT THIS PROBLEM; MAINT, HOBBS METER TO BE CHECKED BY PILOTS CLOCK WEEKLY TO MAKE SURE METER IS RUNNING PROPERLY. 1G71 3U3 UNCH2SW E1GL 20080718 NM 2008 7 18 2008FA0000461 120080703G5315 FLOORBEAM BOEING737 73783N 13844HINM GE CFM56 CFM56* 13802NE BS294 CORRODED B DU4RO OTHER O OTHER NRNOT REPORTED 1 EA39304TZ 30675 DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AROUND FASTENERS AT BS 294 FROM RBL-2 TO RBL 43. SO NR 245010 NR 27077. (K) 2L72 4F4 FRTA16WE E2GL 20080718 NM 2008 7 18 2008FA0000462 120080704G5315 FLOORBEAM BOEING737 73783N 13844HINM GE CFM56 CFM56* 13802NE BS 328, RBL26 CORRODED B DU4RO OTHER O OTHER NRNOT REPORTED 1 EA39304TZ 30675 DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AT BS 328, RBL 26 AFT SIDE OF BEAM FOUND TO BE BEYOND LIMITS. (K) 2L72 4F4 FRTA16WE E2GL 20080718 NM 2008 7 18 2008FA0000463 120080703G5315 FLOORBEAM BOEING737 73783N 13844HINM GE CFM56 CFM56* 13802NE BS328 CORRODED B DU4RO OTHER O OTHER NRNOT REPORTED 1 EA39304TZ 30675 DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AT BS 328 FROM RBL 13 TO RBL 50. (K) 2L72 4F4 FRTA16WE E2GL 20080718 NM 2008 7 18 2008FA0000464 120080707G5315 FLOORBEAM BOEING737 73783N 13844HINM GE CFM56 CFM56* 13802NE BS 344 CHAFED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39304TZ 30675 DURING SCHEDULED INSP, FOUND CLIP NUTS CHAFING FLOORBEAM IN FWD CABIN BS 344, LBL 0 TO LBL 55. (K) 2L72 4F4 FRTA16WE E2GL 20080718 NM 2008 7 18 2008FA0000465 120080707G5315 FLOORBEAM BOEING737 73783N 13844HINM GE CFM56 CFM56* 13802NE BS344, LBL10 CORRODED B DU4RO OTHER O OTHER NRNOT REPORTED 1 EA39304TZ 30675 DURING SCHEDULED INS, FUND FWD CABIN BS 344, LBL10, FLOORBEAM CORRODED. (K) SO 245010, NR27110 2L72 4F4 FRTA16WE E2GL 20080718 2008 7 18 2008FA0000466 420080711G34604052500927 COMPUTER BOEING767 767* NM FMC FAILED W ANCFO OTHER O OTHER NRNOT REPORTED 1 SO23421AV 25421 AIR TURNBACK DUE PILOT REPORT 4273256-1; EICAS MSG L FMC FAIL DISPLAYED. FIM 34-61-00 FOLLOWED L FMC PWR RESET ALL INDICATIONS NORMAL. PLS MONITOR FURTHER. AS A PREVENTIVE ACTION DURING OVERNIGHT; IAW AMM 34-61-01/401 WAS REMOVED AND REPLACED THE FLIGHT MANAGEMENT COMPUTER. (K) 2L72 4F RTA1NM 20080718 GL 2008 7 18 2008FA0000467 120080512G6100 SNAP RING NAMER T6 AT6F 6400420GL HAMSTD23D 23D40 NE PROP GOVERNOR MISSING D O OTHER O OTHER NRNOT REPORTED 1 SW15767WB 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 CAUSED PROPELLER AND ENG TO LEAK OIL. (K) 1L71 3R A2575 6 CP719 20080718 CE 2008 7 18 2008FA0000468 120080701G5344NAS405 HINGE BEECH 80 65B80 1152812CE LYC O720 IO720A1B 41546EA CABIN DOOR CRACKED C O OTHER O OTHER NRNOT REPORTED 1 WP1344MA LD412 L15595YA (2) OF THE HINGE LINKS HAD CRACKED OFF ON ONE END. UPON DISASSEMBLY IT WAS DETERMINED THAT A CRACK HAD FORMED LENGTHWISE BETWEEN THE FASTENERS AND THE HINGE LINKS. POSSIBLE CAUSE MAY HAVE BEEN FATIGUE. (K) 1L72 3O3 O 3A20 1E15 20080721 GL 2008 7 21 2008FA0000469 120080616G5340 MOUNT CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO ALTERNATOR CRACKED C O OTHER O OTHER NRNOT REPORTED 1 SW15710CD849 100575 0013 685689 STANDBY ALTERNATOR MOUNTING FLANGE CRACKED IN (2) PLACES. OIL GALLING AT MOUNT FLANGE WHERE CRACKS WERE NOTED. (K) 1L71 3O3 ONTA00009CHE3SO 20080721 SW 2008 7 21 2008FA0000470 120080701G5343ED12758 CLEVIS GULSTM690TP 690A 0141722SW GARRTTTPE331TPE33112UHR WP RT MLG ACTUATOR BROKEN B BOERK NONE O OTHER ININSP/MAINT 1 GL19122AV 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 WAS FOUND THAT CLEVIS ASSY FROM UPPER STRUT HSG TO MAIN ACTUATOR HAD BROKEN IN (2) PIECES, (1) PART STILL ATTACHED TO ACTUATOR AND THE OTHER WAS STILL IN THE UPPER STRUT ASSY. AN OEM SL REQUIRING THAT THE CLEVIS BE REMOVED EA 500 HR AND INSPECTED BY A LEVEL II INSPECTOR. THIS CLEVIS HAD 274 HR ON IT SINCE THAT INSPECTION, WHERE IT WAS FOUND AIRWORTHY. ON THESE AC THERE IS A MAIN ACTUATOR AND AN AUXILLIARY ONE WITH ITS OWN CLEVIS MOUNTING ALSO. LANDING GEAR CAME DOWN AND LOC1H72 3T4 T 2A4 E4WE 20080721 NM 2008 7 21 2008FA0000471 120080601G7700PT25 SENSOR BOEING777 7772Q8 1385238NM GE GE90 GE9094B 30045NE RT ENGINE FAILED W ASMFO OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 SW23745AM10004 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 CORRECT. THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO AIRCRAFT LANDED WITH 211, 400 KGS AND MAXIMUM LANDING WEIGHT IS 213 KGS. (K) 2L72 4F4 FRTT00001SEE00049EN 20080721 NE 2008 7 21 2008FA0000472 220080606G7200 ENGINE BOEING777 7772Q8 1385238NM GE GE90 GE9094B 30045NE RIGHT FAILED W ASMFK NONE O OTHER ININSP/MAINT 1 SW23745AM10838 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) 2L72 4F4 FRTT00001SEE00049EN 20080721 NE 2008 7 21 2008FA0000473 220080619G7200 ENGINE DOUG DC9 DC987 3022087WP PWA JT8 JT8D219 52053NE RIGHT VIBRATION W ASMFO OTHER EJ VIBRATION/BUFFET WARNING INDICATION NRNOT REPORTED 1 SW23205AM 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) 2L72 4F4 FRTA6WE E9NE 20080725 NM 2008 7 25 2008FA0000474 120080709G5230 SKIN BOEING737 737448 13844BUNM CFMINTCFM56 CFM563C 13802EU CARGO DOOR DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39742VA 24773 DURING SCHEDULED INSPECTION, FOUND NUMEROUS DENT ON AFT CARGO EXT DOOR SKIN. S/O 312001, OPS 24422. (K) 2L72 4F4 FRTA16WE E21EU 20080728 NM 2008 7 28 2008FA0000475 120080627G5315 FLOORBEAM BOEING737 737448 13844BUNM CFMINTCFM56 CFM563C 13802EU BS 986 CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39742VA 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) 2L72 4F4 FRTA16WE E21EU 20080725 WP 2008 7 25 2008FA0000476 120080617G324595502677 WHEEL DOUG DC9 DC983 3022083WP PWA JT8 JT8D* NE NLG LOOSE W ANCFC ABORTED TAKEOFF E VIBRATION/BUFFET TOTAKEOFF 1 SO23160BS1211 53463 REJECTED TAKEOFF, DURING T/O ROLL, THERE WAS AND ABNORMAL AND ABRUPT VIBRATION IN THE NOSE SECTION. IAW AMM 32-21-04, PAGE 201/210 WAS CHECKED TORQUE LINKS ASSY BY LOOSE AND ADJUSTMENT ALSO WERE CHECK BOTH NOSE WHEELS, IAW AMM 32-40-02 PAGE 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) 2L72 4F4 FRTA6WE E2EA 20080725 NM 2008 7 25 2008FA0000477 120080602G21301305027 SELECTOR BOEING767 767284 1385184NM CABIN PRESSURE INOPERATIVE W ANCFO OTHER J WARNING INDICATION CRCRUISE 1 SO23988AN 24742 AIR TURN BACK, CABIN ALT, CABIN ALTITUDE LIGHT EICAS MSG DISPLAYED OPERATIONAL AND MANUAL MODE RESTORED CABIN PRESS CABIN AUTO INOP 1 AND 2. IAW AMM 21-31-01/401. CABIN PRESSURE SELECTOR WAS REPLACED AND WAS ACCOMPLISHED CABIN PRESSURE CONTROL SYS, OPS TEST IAW TASK 21-31-00-705-001. TEST SATISFACTORY. (K) 2L72 4F RTA1NM 20080725 NM 2008 7 25 2008FA0000478 120080618G5610 WINDOW BOEING767 767259 1385136NM COCKPIT LEAKING W ANCFC ABORTED TAKEOFF W INADEQUATE Q C TOTAKEOFF 1 SO23985AN 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) 2L72 4F RTA1NM 20080725 NM 2008 7 25 2008FA0000479 120080617G2750 FLAP SYSTEM BOEING767 767283ER 1385149NM TE FLAPS MALFUNCTIONED W ANCFO OTHER J WARNING INDICATION LDLANDING 1 SO23728CG 24728 EMERGENCY LANDING, EICAS MSG TE FLAP DISAGREE DISPLAYED, TRAILING EDGE LIGHT ILLUMINATED WHEN ANY TE FLAP POSITION SELECTED. 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) 2L72 4F RTA1NM 20080725 CE 2008 7 25 2008FA0000480 120080415G32332317100016 ACTUATOR LEAR 60 60LEAR 5170707CE NLG FAILED G K NONE O OTHER ININSP/MAINT 1 SO14 50038 THE NLG ACTUATOR HAD IMPACT MARKS FROM THE LOCKING BALLS IN THE LOCKING CHANNEL. THESE IMPACT MARKS ALSO PUSHED PISTON MATERIAL OUT OF THE CHANNEL CAUSING INTERFERENCE WITH THE LOCKING SLEEVE. THIS INTERFERENCE CREATED METAL SHAVINGS THAT INTERFEERED WITH THE DOWN LOCK MECHANISM. (K) 2L72 4F RTA10CE 20080725 EU 2008 7 25 2008FA0000481 120080702G26970292697390 CONNECTOR SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B 60037NE FIRE DETECTION CONTAMINATED B QMLRA UNSCHED LANDING N FALSE WARNING CRCRUISE 1 NM03902CF3746 3630 22351 DURING CRUISE FLIGHT, THE ENGINE FIRE LIGHT ILLUMINATED. DURING THE DESCENT FOR A PRECAUTIONARY LANDING, THERE WAS NO SMOKE TRAILING THE AC AND THE ENGINE FIRE LIGHT EXTINGUISHED AND ILLUMINATED SEVERAL TIMES. AFTER SECURING THE AC UPON LANDING, THE PILOT INSPECTED THE ENGINE AREA AND NO FIRE DAMAGE WAS NOTED. THE MAINTENANCE STAFF CAME OUT AND FOUND MOISTURE 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) 1G71 3U3 U H9EU E00054EN 20080725 EU 2008 7 25 2008FA0000482 120080706G2150060018 BELT SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE AIR CONDITIONER BROKEN B QMLRA UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 NM03152AC 3574 IMMEDIATELY AFTER TAKEOFF AND LEVELING FOR CRUISE, THE AIR CONDITIONER WAS TURNED ON. WITHIN A SHORT TIME A STRONG ACRID 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 AND NO DAMAGE WAS DONE TO THE FIELD BY THE AIRCRAFT. AN AMBULANCE WAS IMMEDIATELY DISPATCHED TO THE SCENE AND THE PATIENT TRANSFERRED TO THE AMBULANCE FOR TRANSPORT. THE DUTY MECHANIC WAS IMMEDIATELY CALLED. THE MECHANIC INSPECTED THE AIRCRAFT, DETERMINED THE CAUSE OF THE ACRID SMELL AS THE AIR CONDITIONER BELT. THE MECHANIC THEN INSPECTED THE AIR CONDITIO1G71 3U3 U H9EU E19EU 20080725 EU 2008 7 25 2008FA0000483 120080704G2150060018 BELT SNIAS 350 AS350B3 8680954EU TMECA ARRIUSARRIUS2B1 NE AIR CONDITIONER BROKEN B QMLRA UNSCHED LANDING BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CRCRUISE 1 NM03105LN 3249 GROUND CREW NOTICED THE SMELL OF FUEL AND VAPOR COMING FROM AIRCRAFT AFTER LIFTING FROM SCENE. PIC NOTIFIED OF THE CIRCUMSTANCES. PIC MADE A PRECAUTIONARY LANDING WITH PATIENT ON BOARD. PIC DETERMINED THAT THE VAPOR WAS COMING FROM THE AIR CONDITIONER, AND NO FUEL LEAK. (K) 1G71 3U3 U H9EU E34NE 20080725 CE 2008 7 25 2008FA0000484 120080516G2497 WIRE CESSNA208 208B 2073701CE STARTER GEN SHORTED D K NONE O OTHER ININSP/MAINT 1 WP21 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 STAYS 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 REVEALED 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) 1H71 3T A37CE 20080725 NE 2008 7 25 2008FA0000485 220080709G7320256072 FLOW DIVIDER CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE NR 1 ENGINE FUELFAILED B B3ORA UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 SW036001L 5500169 71709 DURING CLIMB OUT AFTER TAKEOFF, NR 1 ENGINE COULD ONLY PRODUCE 85 PERCENT N1. WHILE RETURNING TO BASE , ENGINE SHUT ITSELF DOWN ON 2 MILE FINAL. TROUBLESHOOTING FOUND THAT FUEL FLOW DIVIDER HAD MALFUNCTIONED. FUEL FLOW DIVIDER WAS REMOVED FROM SERVICE, AND REPLACED WITH AN OVERHAULED UNIT. AIRCRAFT WAS RETURNED TO SERVICE. (K) 1L72 4F4 F A22CE E1NE 20080725 2008 7 25 2008FA0000486 420080618G2200 TRIM SWITCH BEECH 90 C90 1152913CE AUTO PILOT FAILED B QPIRK NONE O OTHER ININSP/MAINT 1 SO19362MC 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. MICRO 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 AND REINSTALLED ON 2/17/2008. TRIM CIRCUITRY FAILED ON INITIAL CHECKOUT. COMPUTER WAS REMOVED FOR REPAIR AND THE TRIM S1L72 3T 3A20 20080725 2008 7 25 2008FA0000487 320080717G6110D5258 BULKHEAD BEECH 33 F33A 1151425CE CONT O520 IO520* 17032SO PROP MOUNT CRACKED B CNZ2K NONE O OTHER ININSP/MAINT 1 WP01500JL1279 CE1603 PROPELLER SPINNER BULKHEAD CRACKING BETWEEN ATTACH BOLT HOLES IN (2) PLACES. CRACK COULD BE INDUCED FROM VIBRATION. INSPECT VISUALLY EVERY PRE-FLIGHT. A BETTER HEAT TREATING PROCESS MAY STRENGTHEN THE BULKHEAD AND REDUCE THE CRACKING FROM VIBRATION. (K) 1L71 3O3 O 3A15 E5CE 20080725 EA 2008 7 25 2008FA0000488 220080423G72103028266 HOUSING PWA PT6 PT6A27 52043EA RGB BROKEN B UTURK NONE O OTHER ININSP/MAINT 1 SO19 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 120080620G5410109910029165 INLET BEECH 90 C90A 1152911CE LWR AFT COWLINGSCRACKED B O OTHER O OTHER NRNOT REPORTED 1 GL055115H901 LJ1705 LT AND RT WELD ASSY CRACKED ALONG A WELDED SEAM. THE CRACKS ARE APPROXIMATELY 12 INCHES LONG. THESE WELD ASSY ARE A PORTION OF THE ENGINE INLET. A PORTION OF THE INLET AIR IS USED FOR THE OIL COOLER AND SOME AIR IS BYPASSED AND EXITS FROM 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 RECOMMENDATIONS TO PREVENT IT FROM HAPPENING AGAIN. OUR ONLY RECOMMENDATION IS TO INSPECT THIS AREA IN BOTH LT AND RT COWLING1L72 3T RT3A20 20080728 NE 2008 7 28 2008FA0000490 220080622G7200 ACOUSTIC LINER DOUG DC9 DC987 3022087WP PWA JT8 JT8D219 52053NE LEFT DAMAGED W ASMFO OTHER O OTHER NRNOT REPORTED 1 SW23216AM452717361 49586 AC RETURNED TO PLATFORM, DURING ENGINE ACCELERATION UP TO 1.4 EPR, STRONG NOISE IN THE RT ENG WAS HEARD. MAINT PERFORMED AN INSPECTION AND DETECTED ACOUSTIC LINER DELAMINATION OF THE DIFFUSER OUTER FAN DUCT, BUT WITHIN LIMITS TO OPERATE TEN 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) 2L72 4F4 FRTA6WE E9NE 20080728 GL 2008 7 28 2008FA0000491 220080709G723066032 BLADE CESSNA525 525 2076601CE WILINTFJ44 FJ441A GL IP ROTOR BLADE DEPARTED B FCPRK NONE O OTHER ININSP/MAINT 1 NM09678RF1040 5250537 2091 DURING ROUTINE INSP, FOUND DAMAGE TO THE 1ST STAGE STATOR ASSY, UPON FURTHER INSPECTION, FOUND 1 BLADE HAD FAILED AND DEPART THE LP ROTOR ASSY CAUSING DAMAGE TO THE REST OF THE ENGINE DOWN STREAM. (K) 1L72 4F4 FRTA1WI E3GL 20080725 GL 2008 7 25 2008FA0000492 120080630G2421 FAN CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO HARTZLHCJ3Y PHCJ3YF1 GL ALTERNATOR CRACKED B O OTHER O OTHER NRNOT REPORTED 1 SW99PROMZ 3041 691724 FP6763 ALTERNATOR NR 2 (BELT DRIVEN ALTERNATOR) COOLING FAN DEVELOPED CRACK AT FAN BLADE RADIUS. CRACK ELONGATED UNTIL FAN SEPARATED FROM ALTERNATOR. (K) 1L71 3O3 ONTA00009CHE3SO 5 CP36EA 20080728 GL 2008 7 28 2008FA0000493 120080623G5397 WIRE CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO ALT AIR DOOR FATIGUED C O OTHER O OTHER NRNOT REPORTED 1 WP05683SR 2766 691392 WIRES THAT CONNECT TO THE ALTERNATE AIR DOOR (WHICH ARE SOLDERED TO THE SWITCH) FOR THE TORNADO ALLEY TURBO SYSTEM ARE BECOMING FATIGUED AND SOLDER IS BREAKING AT SWITCH. IF THE ALTERNATE AIR WAS TO OPEN AND THESE WIRES WERE BROKEN, IT WOULD NOT GIVE THE PILOT AN INDICATION THAT THE ALTERNATE AIR DOOR WAS OPEN. (K) 1L71 3O3 ONTA00009CHE3SO 20080725 SO 2008 7 25 2008FA0000494 120080715G2170234018623 WATER SEPARATOR GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 WP21595PE 141 1373 BOTH UNITS O/H AT MFG. WHEN CHANGING SOCK, FOUND RUST STAINS ON SOCK. REMOVED AND FOUND RETAINING CHAIN PN 834639 RUSTED. 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 GASKET. ALSO FOUND INSIDE SAME UNIT WAS A PIECE OF MASKING TAPE (2 INCHES X 6 INCHES) WITH SN OF UNIT WRITTEN WITH A RED MARKER STILL AFFIXED TO INNER COATING OF AFT SECTION. WO NR TTT91055 (SN 49-945) DATED SEPT 28, 2006. AND CLJ14812 (SN 67-272) DATED SEPT 24, 2007. (K) 2L72 4F4 FRTA12EA E25NE 20080728 EU 2008 7 28 2008FA0000495 120080525G2800 FUEL SYS RHNFLUEXT300EA300L 70218DGEU LYC O540 AEIO540* EA MALFUNCTIONED D A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION NRNOT REPORTED 1 NE0522MW 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. MADE A PRECAUTIONARY LANDING. MECH DECOWLED ACFT AND CONFIRMED THAT FUEL COULD BE SOURCED INTO THE SERVO FROM EITHER THE W1M71 3O3 ONCEA67U 1E4 20080725 2008 7 25 2008FA0000496 420080618G220030B641 TRIM SWITCH CENTURY AMTR SUKHOISU26MX 1152913GL PWA PT6 PT6A21 52043EA CONTROL COLLUMN INOPERATIVE B QPIDO OTHER O OTHER NRNOT REPORTED 1 SO19362MC 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 FAILURE. MICRO SWITCHES IN ASSY FAILED ALLOWING BOTH UP AND DOWN COMMANDS AT THE SAME TIME. TRIM SWITCH ASSY PROVIDED BY MFG WAS REPLACED AND COMPUTER REPAIRED AND REINSTALLED ON FEB 17, 2008. TRIM CIRCUITRY FAILED ON INITIAL CHECKOUT. COMPUTER WAS REMOVED FOR REPAIR AND THE TRIM SWITCH WAS CONFIRMED TO BE CAUSING THE FAILURE AGAIN. THE TRIM UP MICRO SWITCH1M71 3R4 TNCEXPA1M71E4EA 20080728 NM 2008 7 28 2008FA0000497 120080620G2701 BOOT ADAMACA500 A500 05614IQNM CONT O550 TSIO550E 17043SO CONTROL COLLUMN MISINSTALLED D O OTHER W INADEQUATE Q C NRNOT REPORTED 1 WP27896MH 0008 AT LOCATION WHERE CONTROL "STICK" PASSES THROUGH L/R SIDE ARM REST, THE BOOT SURROUNDING BASE OF STICK LIES OPEN TO CONTROL MECHANISMS. WHERE THE STICK ENTERS THE COCKPIT, THE LEATHER BOOT THAT IS DESIGNED TO COVER THE AREA BENEATH THE STICK, IS PARTIALLY OPEN. THIS ALLOWS FOREIGN OBJECTS, PLACED ALONG THIS AREA, TO FALL DOWN INTO WHERE CONTROLS COULD BECOME JAMMED. THIS HAS ALREADY OCCURRED, RESULTING IN LOSS OF VERTICAL CONTROL. MFG NEEDS TO ISSUE AN IMMEDIATE AD AND ISSUE REMEDY FOR THIS SAFETY OF FLIGHT ISSUE. (K) 1L72 3O3 ORTA00009DEE5SO 20080725 CE 2008 7 25 2008FA0000498 120080711G551004320049 BRACKET CESSNA150 152 2071835CE LYC O235 O235* 41505EA HORIZONTAL STAB CRACKED D K NONE O OTHER ININSP/MAINT 1 WP2766970 15281696 WHILE CONDUCTING A 100 HOUR INSPECTION ON THE AIRCRAFT, COMPLYING WITH AD80-11-04 (NUTPLATE INSPECTION). UPON INSPECTION, IT WAS FOUND THAT NOT ONLY WAS THERE A CRACKED NUTPLATE, BUT THERE IS ALSO A (1 INCH) CRACK IN THE WELDED BRACKET- THE PART THAT THE NUTPLATES MOUNT TO. IT CAN BE SEEN IN MFG ILLUSTRATED PARTS CATALOG, FIGURE 18, ITEM NR 10. UPON REMOVING THE BRACKET FROM THE AIRCRAFT, ALSO DISCOVERED THAT A LARGE PORTION OF THE STEEL BRACKET HAD BEEN RUSTED; PARTICULARLY IN THE WELDED AREAS. BECAUSE MFG NO LONGER MAKES THIS PART, ACQUIRED A SERVICEABLE PART, INSPECTED THE WELDS, TREATED THE CORROSION, AND INSTALLED IT ON THE AIRCRAFT. (K) 1H71 3O3 ONT3A19 E223 20080725 CE 2008 7 25 2008FA0000499 120080716G275098600581 CONTROL CABLE CESSNA210 T210L 2073449CE CONT O520 TSIO520* 17040SO FLAPS DEFECTIVE D O OTHER O OTHER NRNOT REPORTED 1 SW152423S 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, OF NEW MFG FLAP FOLLOW UP CABLE, OPERATION WAS VERY ROUGH AND INTERMITTENT. SMOOTH OPERATION IS CRITICAL TO MEET MM SPECS 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 OTHE1H71 3O3 O 3A21 E8CE 20080725 CE 2008 7 25 2008FA0000500 120080713G7897 WIRE CESSNA500 550 2076604CE PWA JT15 JT15D5 52112NE THRUST REVERSER CHAFED D A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 EA2367SF 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, THE PILOT CYCLED THE LT THRUST REVERSER AND THE LIGHT EXTINGUISHED. THE TRIP WAS CANCELLED UNTIL THE AIRCRAFT COULD BE INSPECTED. INVESTIGATION REVEALED A WIRE FOR THE DEPLOY SWITCH HAD CHAFED TO GROUND AT THE STRUCTURE OF THE LT THRUST REVERSER 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) 1L72 4F4 F A22CE E25EA 20080728 CE 2008 7 28 2008FA0000501 120080715G5730 SKIN BEECH 300 300BEECH 1152930CE WING DAMAGED B KX5RK NONE O OTHER ININSP/MAINT 1 GL15613BA 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 OF THE SKIN LAP AT WS 209.016 WERE UNDER DRIVEN. THESE RIVETS WERE INSTALLED NEW AT THE FACTORY. AIRCRAFT HAS A TT OF 1659.1. RECOMMEND INSPECTING THESE RIVET FOR POPPED PAINT AND SMOKING CONDITION AND INSTALLING NEW RIVETS IAW AC 43.13-1B. (K) 2L72 4T A24CE 20080728 2008 7 28 2008FA0000502 420080718G22006222263016 AMPLIFIER ISRAEL1124 1124A 4500103EU GARRTTTFE731TFE731* 01518WP AUTOPILOT INOPERATIVE D O OTHER O OTHER NRNOT REPORTED 1 SO19818JH 341 AFTER (1) HOUR DISENGAGES AUTOPILOT. PRELIMINARY INSPECTION RESULTS, NO DEFECTS NOTED AFTER BENCH CHECK. (K) 2M72 4F4 F A2SW E6WE 20080728 CE 2008 7 28 2008FA0000503 120080715G5730 SKIN BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE RT WING DAMAGED B KX5RK NONE O OTHER ININSP/MAINT 1 GL15291B FL559 AIRCRAFT WAS BROUGHT IN FOR PHASE INSPECTION. DURING INSPECTION A DOUBLER ROW OF RIVETS AT WING STATION 209.016 WERE FOUND WITH PAINT POPPING OFF OF THE RIVET HEADS. USED BOROSCOPE TO INSPECT RIVET BUCKTAILS. FOUND ALL OF THE RIVETS IN THE DOUBLE ROW OF THE SKIN LAP AT WS 209.016 WERE UNDER DRIVEN. THESE RIVETS WERE INSTALLED NEW AT THE FACTORY. AIRCRAFT 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) 2L72 4T4 T A24CE E4EA 20080728 GL 2008 7 28 2008FA0000505 320080722G61971219310 CONNECTOR WOODWARD DIAMONDA40 DA40 2990002GL CONT IO360 IO360* 17025CE HARTZLHCC2Y HCC2YR1 GL PROP GOVERNOR DAMAGED B WOGRA UNSCHED LANDING N FALSE WARNING CLCLIMB 1 GL03412PJ300 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. UPON 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 THE PLUG AND INDEPENDENT SECOND PARTY VERIFICATION OF TORQUE DURING ASSEMBLY IS SUGGESTED. (K) 1L71 3O3 ONTA47CE E1CE 5 CP920 20080728 SO 2008 7 28 2008FA0000506 120080702G7714ACA500 TRANSMITTER GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU LT ENGINE MALFUNCTIONED G O OTHER O OTHER NRNOT REPORTED 1 SO1961WH 1075 TRANSMITTER CAUSED LT ENGINE TO SPOOL BACK TO IDLE, AC RETURNED TO AIRPORT AND LANDED WITH NO INCIDENT. (K) 2L72 4F4 FRTA12EA E25NE 20080728 CE 2008 7 28 2008FA0000507 120080715G5730 SKIN BEECH 300 300BEECH 1152930CE WING DAMAGED B KX5RO OTHER O OTHER NRNOT REPORTED 1 GL15613BA FL396 AIRCRAFT WAS BROUGHT IN FOR INSPECTION OF DOUBLER 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 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) 2L72 4T A24CE 20080728 CE 2008 7 28 2008FA0000508 120080716G52105043006221 BRACKET BEECH 200 B200 1152922CE PAX DOOR LATCH MISINSTALLED D O OTHER W INADEQUATE Q C NRNOT REPORTED 1 EA05786DD661 BB1171 BB1171 PILOT REPORTED DOOR CAME OPEN IN FLIGHT. UPON LANDING, IT WAS FOUND THE MAIN CABIN DOOR HAD DEPARTED AIRCRAFT. DOOR WAS 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 AND TWISTED. 3) MAIN CABIN DOOR LATCH BRAZE ASSEMBLY WAS CATCHING ON HOOK. DID NOT ALLOW FOR A SMOOTH TRANSITION TO A LOCKED POSITION. (K) 1L72 4T A24CE 20080805 SO 2008 8 5 2008FA0000509 120080722G32509539500 ARM PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360* 17025SO NLG STEERING WORN B BIERO OTHER O OTHER NRNOT REPORTED 1 EA212190K4792 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 INSPECTION GUIDE. SB 1123B GIVES THE SERVICE LIMITS TO THE STEERING ARM CENTER PIVOT BUSHINGS AND CENTER PIVOT SLEEVE. HOWEVER THE MORE CRITICAL COMPONENT, THE NLG MOUNT ASSY IS NOT ADDRESSED FOR THE SERVICE LIMIT OF THE STEERING ARM MOUNTING TABS. MFG SHOULD INCORPORATE SERVICE LIMIT DATA THAT COVERS THE NLG MOUNT ASSY AND REPAIR DATA. (K) 1L72 3O3 O A7SO E9CE 20080811 EU 2008 8 11 2008FA0000511 120080719G2435105SG1220 STARTER GEN SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE ENGINE FAILED B HDNRO OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 SW03350BH 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 STARTER GENERATOR WAS REPLACED AND AN OPERATIONAL CHECK OF THE SYSTEM WAS SATISFACTORY. (K) 1G71 3U3 U H9EU E19EU 20080811 CE 2008 8 11 2008FA0000512 120080702G276012SX1T SWITCH RAYTHN390 390 7150030CE SPOILERS FAILED B E81RO OTHER J WARNING INDICATION CRCRUISE 1 GL03972PF1146 RB38 PILOT REPORTED SPOILER FAIL INDICATION IN CRUISE FLIGHT. ALL SPOILER PANELS DEPLOYED UPON LANDING. SCU FAULT CODE 44R4RV3V INDICATED. ADJUSTED LT & RT SPOILER FINAL POSITION LVDT`S AS REQUIRED IAW MM 27-60-00-501. REPLACED LT THROTTLE SWITCH S1, SPOILER SYS FUNCTIONAL CHECKS NORMAL, NO FAULTS INDICATED SUSPECT LT THROTTLE S1 SWITCH TO HAVE PREMATURE INTERNAL FAULT. RECOMMEND MFG INVESTIGATE IF FLEET IS EXPERIENCING PREMATURE FAILURES OF THROTTLE SWITCHES AND REDESIGN SWITCH IF REQUIRED. (K) 1L72 3F RTA00010WI 20080811 NM 2008 8 11 2008FA0000513 120080730G5753 SPAR BOEING737 737448 13844BUNM CFMINTCFM56 CFM563C 13802EU LT TE FLAP CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39742VA 24773 DURING SCHEDULED INSPECTION, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD. (K) 2L72 4F4 FRTA16WE E21EU 20080811 NM 2008 8 11 2008FA0000514 120080730G5753 SPAR BOEING737 737448 13844BUNM CFMINTCFM56 CFM563C 13802EU LT WING TE FLAP CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39742VA 24773 DURING SCHEDULED INSP, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD. (K) 2L72 4F4 FRTA16WE E21EU 20080811 WP 2008 8 11 2008FA0000515 120080729G5530 INLET DOUG DC9 DC982 3022082WP PWA JT8 JT8D* NE HEAT EXCHANGER CRACKED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39886GA 49931 DURING SCHEDULED INSP, FOUND VERTICAL STABILIZER L/E AT HEAT EXCHANGER INLET IS CRACKED APPROX 6.5 INCHES LONG ON LT SIDE. FOUND TO BE OUT OF LIMITS IAW SRM 55-05 FIG 3. (K) 2L72 4F4 F A6WE E2EA 20080811 EA 2008 8 11 2008FA0000516 220080721G8550CH481101 OIL FILTER CESSNA150 152 2071835CE LYC O235 O235* 41505EA ENGINE CONTAMINATED D K NONE O OTHER ININSP/MAINT 1 NE014900H1 15284009 FILTER INSTALLED AND OIL CHANGE RUN-UP NORMAL. FIRST FLIGHT AFTER OIL CHANGE, PILOT NOTICED OIL PRESSURE DROPPING AND HIGH OIL TEMP, UNABLE TO CORRECT, PILOT RETURNED TO ORIGIN AND REPORTED FINDINGS. INVESTIGATION FOUND FILTER ELEMENT DEBRIS UNDER PRESSURE RELIEF VALVE CAUSING LOW OIL PRESSURE, UPON FURTHER INVESTIGATION A SECOND FILTER OF SAME DATE CODE WAS FOUND TO HAVE LOOSE DEBRIS IN THE FILTERED SIDE OF THE FILTER ELEMENT AND THE ELEMENT WAS BONDED ON ONE END ONLY. THE 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 INSTALLE1H71 3O3 ONT3A19 E223 20080811 EU 2008 8 11 2008FA0000517 120080801G3210DIN4718ZP FITTING DIAMONDA42 DA42 2990004EU THIELTTAE125TAE12501 59300EU MLG LOOSE D O OTHER O OTHER NRNOT REPORTED 1 EA17119BJ 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) 1L72 3I3 BRTA57CE E00069EN 20080811 SO 2008 8 11 2008FA0000518 220080717G8520654837 CAMSHAFT CONT O550 IO550B SO ENGINE WORN B Y2GRO OTHER O OTHER NRNOT REPORTED 1 EA23 2079 296655 CAMSHAFT LOBES WORN EXCESSIVELY FORM CORROSION PITS. (K) 3 O E3SO 20080811 EA 2008 8 11 2008FA0000519 220080717G8520LW19173 CAMSHAFT LYC O540 IO540* 41532EA ENGINE WORN B Y2GRO OTHER O OTHER NRNOT REPORTED 1 EA23 1329 L100268A CAMSHAFT LOBES WORN FROM CORROSION PITS. (K) 3 O 1E4 20080811 EA 2008 8 11 2008FA0000520 120080624G2730C6CTM102827 JACKSCREW DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6* 52043EA LT ELEVATOR DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 WP09300DZ 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) 1H72 3T3 TRTA9EA E2NE 20080811 CE 2008 8 11 2008FA0000521 120080723G712010191012253 MOUNT BEECH 300 300BEECH 1152930CE PWA PT6 PT6* 52043EA LT ENGINE CRACKED B GSPRK NONE O OTHER ININSP/MAINT 1 WP0573WC 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 FROM THE TOP OF THE WELD AND WAS APPROXIMATELY 1 INCH IN LENGTH. THE ADJACENT AREAS DID NOT APPEAR DAMAGED.. TECH SUPPORT WAS CONTACTED AND THE MOUNT SENT TO A QUALIFIED WELDER FOR REPAIR. CAUSE OF CRACK IS UNKNOWN. (K) 2L72 4T3 T A24CE E2NE 20080811 SO 2008 8 11 2008FA0000522 120080731G253050231L0V5280 PAN GULSTMG1159 GIV 3980115SO PWC PW615 PW615FA 52282NE OVEN MISINSTALLED D O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 SO13416QS 1316 CABIN SMOKE DUE TO DRIP PAN IN OVEN BEING IMPROPERLY INSTALLED CAUSING DRIPPINGS FROM FOOD TO CONTACT OVEN LOWER BURNER ELEMENTS. (K) 2L72 4F4 FRTA12EA E00073EN 20080811 SO 2008 8 11 2008FA0000523 120080707G8120LW18302 MOUNT PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA TURBOCHARGER BROKEN D O OTHER O OTHER NRNOT REPORTED 1 EA233580X 318052085 L628661A FOUND MOUNT FOR TURBOCHARGER TO BE BROKEN COMPLETELY THROUGH ON IB LOWER TUBE ON RT ENGINE. CRACK WAS APPROXIMATELY 4 TO 5 INCHES FROM FWD LOWER ATTACH POINT. NO REPORTED VIBRATION ISSUES OF OPERATIONAL ISSUES. (K) 1L72 3O3 O A20SO E14EA 20080811 2008 8 11 2008FA0000524 420080802G2300G888012 CONTROL HEAD AMD FALC50FALCON50MYST2730106EU GARRTTTPE331TPE3313 01514WP NR 1 NAV/COMM FAILED D O OTHER BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION DEDESCENT 1 SO14980S 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 LANDING. SHORTLY THEREAFTER WHILE DESCENDING TO 6000 FT THE SMOKE AND ELECTRICAL ODOR CLEARED AND NOTED NR 1 NAV/COM CONTROL 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 PART INSTALLED. REMOVED UNIT PN G8060-12, SN 273 SENT FOR EVALUATION AND REPAIR. (K) 2L73 4F4 T A46EU E4WE 20080811 EA 2008 8 11 2008FA0000525 220080722G7414AB382584 CONTACTOR BENDIX BLANCA17 1731ATC 1220437GL LYC O540 TIO540* 41532EA MAGNETO BROKEN G K NONE O OTHER ININSP/MAINT 1 SW13222SN 31004 A BROKEN CONTACT BREAKER WAS FOUND DURING TROUBLESHOOTING AN IGNITION PROBLEM. THE CONTACTOR RIVET WAS BROKEN ON THE MAGNETO. THE CONTACTOR RIVET MAY BE INSUFFICIENT TO PROPERLY HOLD THE CONTACTOR IN PLACE. (K) 1L71 3O3 O A18CE E14EA 20080811 SO 2008 8 11 2008FA0000526 220080619G7414K3823 DISTRIBUTOR CESSNA182 182Q 2072732CE CONT O470 O470* 17026SO MAGNETO WORN B AKGRO OTHER O OTHER NRNOT REPORTED 1 CE0516MS 182 18267267 REMOVED NEW MAGNETOS PN 6310, SN 07061208 & 07061310.. ACCOMPLISHED SB 3-08 PREMATURE CARBON BRUSH WEAR. BOTH CARBON BRUSHES HAD PREMATURE WEAR AS DEPICTED IN THE CENTER ILLUSTRATION FIG 1, PAGE 3 OF 5. (K) 1H71 3O3 ONT3A13 E273 20080811 SO 2008 8 11 2008FA0000527 220080619G7414M1827 CAM CESSNA182 182Q 2072732CE CONT O470 O470* 17026SO MAGNETO WORN B AKGRO OTHER O OTHER NRNOT REPORTED 1 CE0516MS 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) 1H71 3O3 ONT3A13 E273 20080811 CE 2008 8 11 2008FA0000528 120080729G3222 STRUT CESSNA172 172RG 2072438CE LYC O360 O360* 41514EA NLG DAMAGED B QFBRO OTHER E VIBRATION/BUFFET NRNOT REPORTED 1 NM016448V 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 CULPRIT. 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 TRAINING, WAS IS SUSPECT PLAYS SOME ROLE BUT BELIEVE THE PROBLEMS HAD BEEN DETECTED BEFORE AND ONLY THE BOLT WAS REPLACED. (K) 1H71 3O3 O 3A17 E286 20080811 EA 2008 8 11 2008FA0000529 220080730G853074230 GUIDE CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA CYLINDER HEAD SEIZED D A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 WP07543ER889 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 CYLINDER HEAD. OPERATOR HAS AIRCRAFT WITH THE NEW ROLLER TAPPET ENGINES. HAVE BEEN PERFORMING A SB388C INSPECTION ON THE REST OF THE FLEET AND HAVE FOUND THE MAJORITY OF THE EXHAUST VALVES FOR ALL CYLINDERS TO BE TIGHT IN THE GUIDES. MFG RECOMMENDS A 1000 HOUR INTERVAL FOR THESE ENGINES FOR SB388C INSPECTION. WILL BE INITIATING A 600 HOUR INTERVAL FOR THE SB388C FOR OUR FLEET. HAVE REVISED LEANING PROCEDURES. (K) 1H71 3O3 ONT3A12 1E10 20080811 SO 2008 8 11 2008FA0000530 120080714G2420365662R STATOR PIPER PA32 PA32R300 7103213SO LYC 0540 IO540K1G5D 41532SO HARTZLHCC3Y HCC3YR GL ALTERNATOR SHORTED C A UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION NRNOT REPORTED 1 SW112125V 32R7780431 L1664445A DY4143A THE AC SUFFERED LOSS OF ELECTRICAL POWER WHILE IN CONTACT WITH ATC WHEN LOST RADIO CONTACT. CONTACTED BKP VIA CELL PHONE 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 SKID OFF RUNWAY. DAMAGE WAS CONFINED TO THE PROP, MLG DOORS AND RT WING L/E, WING TIP. NO FLIGHT PLAN HAD BEEN FILED AND VFR CONDITIONS PREVAILED. NO INJURIES. TESTED ALTERNATOR FOUND STATOR HAD SHORTED OUT, IN TURN HAD SHORTED OUT RECTIFIER. (K) 1L71 3O3 O A3SO 1E4 5 CP25EA 20080811 EA 2008 8 11 2008FA0000531 220080728G7314 SEAL PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2B 41979EA NR 2 ENG LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 SO053589X E2048 318052138 L244768A FUEL PUMP DRIVE SHAFT SEAL FAILED RESULTING IN LARGE FUEL LEAK AT DRAIN. (K) 1L72 3O3 O A20SO E14EA 20080811 GL 2008 8 11 2008FA0000532 120080801G2450 BUSS BAR CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO CB PANEL LOOSE B YEBRK NONE O OTHER ININSP/MAINT 1 CE05839CT 2938 PILOT REPORTED THE NR 2 ALTERNATOR WAS INTERMITTENT. WHILE TROUBLESHOOTING THE NR 2 ALTERNATOR, FOUND 13 SCREWS LOOSE AND 1 SCREW MISSING ON THE COPPER CIRCUIT BREAKER BUSS BAR. THE 1 SCREW MISSING WAS ON THE NR 2 ALTERNATOR CIRCUIT BREAKER 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) 1L71 3O3 ONTA00009CHE3SO 20080811 CE 2008 8 11 2008FA0000533 120080714G716045A35042003 SKIN BEECH MU300 400A 1155402CE RT ENGINE INLET CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SO19470LX1491 RK478 REPORTED RT ENG INLET CRACKED AT 9:00 POSITION. THE INLET WAS REMOVED AND REPAIRED AND REINSTALLED ON THE AC. (K) 2H72 4F RTA16SW 20080808 SO 2008 8 8 2008FA0000534 120080712G28201500106151 LINE PIPER PA46 PA46500TP 7104622SO PWA PT6 PT6* 52043EA FUEL SYSTEM CHAFED D O OTHER K FLUID LOSS NRNOT REPORTED 1 SO075339G 4697095 FOUND FUEL LINE, PN 1500106-151, CHAFED AGAINST THROTTLE CABLES , PROP CONTROL CABLES BELOW THROTTLE. THIS LINE PROVIDES FUEL PRESSURE TO THE 2 MANUAL ENGINE PRIMER PUMPS AT THE BASE OF THE QUADRANT. HAD THIS LINE CHAFED THROUGH, FUEL UNDER PRESSURE WOULD HAVE FLOWED INTO THE AIRPLANE CABIN. THE ONLY WAY TO SHUT OFF FUEL FLOW TO THIS LINE WOULD BE TO CLOSE THE FRONT ENGINE FUEL SELECTOR VALVE, AND SHUT DOWN THE FRONT ENGINE. THIS IS A POTENTIAL HAZARDOUS CONDITION AND COULD CAUSE AN INFLIGHT CABIN FIRE WITH RESULTANT LOSS OF LIFE AND AIRCRAFT IF NOT FOUND AND CORRECTED. (K) 1L71 3O3 TRTA25SO E2NE 20080811 SW 2008 8 11 2008FA0000535 120080730G32345040560006 DOWNLOCK MOONEYM20 M20B 5870206SW LYC O360 O360A1A 41514EA MCAULY2A36C D2A36C* GL CONTROL LEVER WORN C O OTHER O OTHER NRNOT REPORTED 1 SW19745423371 1853 L402336 58618 LANDING GEAR LEVER BECAME DISENGAGED FROM THE DOWN LOCK LATCHING ASSY ON THE PILOT`S LOWER CENTER INSTRUMENT PANEL. AC WAS ON THE GROUND DURING LANDING ROLLOUT. THIS ALLOWED GEAR TO COLLAPSE. SB M20-88B, 5/10/94. (K) 1L71 3O3 O 2A3 E286 5 CP880 20080811 EA 2008 8 11 2008FA0000537 120080724G5730 SKIN CNDAIRCL600 CL6001A11 1900308EA WING CORRODED B ZLJRO OTHER O OTHER NRNOT REPORTED 1 EA17100QR 1043 SURFACE CORROSION (PITTING) DISCOVERED ON BOTH WINGS LOWER SURFACES ADJACENT TO AND OB OF WHEEL WELLS, CORROSION DEEMED UNUSUALLY SEVERE. (K) 2L72 4F RTA21EA 20080811 NM 2008 8 11 2008FA0000538 120080730G5753 SPAR BOEING737 737448 13844BUNM CFMINTCFM56 CFM563C 13802EU LT WING TE FLAP CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 EA39742VA 24773 DURING SCHEDULED INSP, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD. (K) 2L72 4F4 FRTA16WE E21EU 20080811 CE 2008 8 11 2008FA0000539 120080502G324415117300 WHEEL BEECH 200 B200 1152922CE MLG CRACKED B E5WRK NONE O OTHER ININSP/MAINT 1 GL21200ND2738 BB1612 CRACK INDICATIONS LOCATED IN BEED AREA OF WHEELS REAVEALED BY FLUORESCENT PENETRANT. (K) 1L72 4T A24CE 20080903 CE 2008 9 3 2008FA0000540 120080502G32464088 WHEEL BEECH 200 B200 1152922CE PWA PT6 PT6* 52043EA MLG CRACKED B HJ2RK NONE O OTHER ININSP/MAINT 1 GL21200ND BB1612 CRACK INDICATIONS LOCATED IN BEAD AREA OF WHEELS, REVEALED BY FLUORESCENT PENETRANT. (K) 1L72 4T3 T A24CE E2NE 20080903 WP 2008 9 3 2008FA0000541 220080801G725030753507 MODULE RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE7315BR WP LPT FAILED B O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 GL03225PB3495 258558 107662 AIRCRAFT EXPERIENCED A VIBRATION IN FLIGHT. CREW SHUTDOWN NR 1 ENGINE AND LANDED. MAINT CREWS DETERMINED THE THIRD STAGE 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 INVESTIGATION AND REPAIR. (K) 2L72 4F4 FRTA3EU E6WE 20080903 SW 2008 9 3 2008FA0000542 120080728G6220471201281 BEAM BELL 47 47G 1181002SW MAIN ROTOR CRACKED B E5WRK NONE O OTHER ININSP/MAINT 1 GL21 BEAM CRACK INDICATION AT EAR END (FPT). HUB - CRACK INDICATIONS AT RADIUS ON STUB ENDS (FMT). (K) 1G71 3O H1 20080903 SW 2008 9 3 2008FA0000543 120080728G6220471201171 HUB BELL 47 47G 1181002SW MAIN ROTOR CRACKED B E5WRO OTHER O OTHER NRNOT REPORTED 1 GL21 BEAM - CRACK INDICATION AT EAR END (FPT). HUB - CRACK INDICATIONS AT RADIUS ON STUB ENDS. (K) 1G71 3O H1 20080903 EU 2008 9 3 2008FA0000544 120080730G2421ALU8521 ALTERNATOR SOCATATB9 TB9 8680694EU LYC O320 O320D2A 41508EA ENGINE FAILED B NI1RO OTHER O OTHER NRNOT REPORTED 1 CE03 1 ALTERNATOR WILL FAIL ABOVE 2500 RPM, LOW VOLTAGE LIGHT COMES ON AND THE VOLTMETER INDICATES BATTERY VOLTAGE. OPS CHECK DURING 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 ALTERNATORS FROM INVENTORY PRODUCE THE SAME SYMPTOMS, SN E113128 AND F043304. BOTH ALTERNATORS FAILED WITHIN 2 HOURS OF OPERATION. BOTH WERE O/H UNITS. (K) 1L71 3O3 ONTAS1EU E274 20080903 CE 2008 9 3 2008FA0000545 120080712G361065550384 BELLOWS CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE RUPTURED B QFYRK NONE O OTHER ININSP/MAINT 1 EA6317PL 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 FLEXIBLE CONNECTOR. THE PROBLEM WAS DISCOVERED ON A MAINT RUN UP AT WHICH TIME THE FIRE DETECTION SYS WAS ACTIVATED FROM AN OVERHEAT SITUATION. RECOMMEND REMOVING THE ELBOWS AND CHECKING THE BELLOWS FOR CRACKS WITH A BORESCOPE. (K) 2L72 4F4 FRTA22CE E25EA 20080903 CE 2008 9 3 2008FA0000546 120080717G275098600581 CONTROL CABLE CESSNA210 T210L 2073449CE CONT O520 TSIO520* 17040SO TE FLAPS DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 SW152423S 21061275 ORDERED NEW FLAP FOLLOW UP CABLE; TO REPLACED ORIGINAL CABLE WHICH HAD BECOME DEFECTIVE DUE TO NORMAL USAGE AND AGE. 1H71 3O3 O 3A21 E8CE 20080903 SW 2008 9 3 2008FA0000547 120080628G3260560006 DOWNLOCK MOONEYM20 M20B 5870206SW LYC O360 O360A1A 41514EA MLG WORN C O OTHER O OTHER TXTAXI/GRND HDL 1 SW19745423371 1853 L402336 LANDING GEAR LEVER BECAME DISENGAGED FROM THE DOWNLOCK LATCHING ASSY ON THE PILOT`S LOWER CENTER INSTRUMENT PANEL. AC WAS ON THE GROUND DURING LANDING ROLLOUT. THIS ALLOWED GEAR TO COLLAPSE, SB M20-88B, 5-10-94. (K) 1L71 3O3 O 2A3 E286 20080903 SO 2008 9 3 2008FA0000548 120080804G533069904000 SKIN PIPER PA32 PA32R301T 7103220SO LYC O540 TIO540* 41532EA FUSELAGE CRACKED B L6QRK NONE O OTHER ININSP/MAINT 1 EA05121TF1520 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. DAMAGE APPEARS TO HAVE BEEN CAUSED BY PROLONGED OIL CANNING OF THE UPPER SKIN PANEL FROM AERODYNAMIC LOADS AGAINST THE ANTENNA 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 1L71 3O3 O A3SO E14EA 20080903 SO 2008 9 3 2008FA0000549 120080804G533099813004 DOUBLER PIPER PA32 PA32R301T 7103220SO LYC O540 TIO540* 41532EA FUSELAGE CRACKED B L6QRK NONE O OTHER ININSP/MAINT 1 EA05121TF1520 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. DAMAGE APPEARS TO HAVE BEEN CAUSED BY PROLONGED OIL CANNING OF THE UPPER SKIN PANEL FROM AERODYNAMIC LOADS AGAINST THE ANTENNA 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 1L71 3O3 O A3SO E14EA 20080903 EA 2008 9 3 2008FA0000550 120080729G6300269D53085 DRIVE SHAFT SCWZER269 269D 8059501EA ALLSN 250C 250C20 03013GL MAIN ROTOR UNSERVICEABLE D K NONE O OTHER ININSP/MAINT 1 SW17277DT674 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 STOP RETAINER PLATE (PN 269A1320), DROOP STOP RETAINER RING (PN 269D1329), DROOP STOP RETAINER (PN 269A1332) AND UPPER SCISSORS SUPPORT (PN 269A1328-901) TO THRUST BEARING TUBE SPACER ASSY (PN 269A13183). ONCE THESE PARTS WERE REMOVED, THE DRIVE SHAFT WAS REMOVED FOR INSP. ONCE DRIVE SHAFT WAS REMOVED THE DRIVE SHAFT THRUST BRG WAS REMOVED FOR INSP AND CORROSION WAS FOUND ON DRIVE SHAFT THRUST BRG JOURNAL. CORROSION WAS REMOVED AND FURTHER VISUAL EXAMINATION REVEALED A POSSIBLE1G71 3U3 U0 4H12 E4CE 20080903 2008 9 3 2008FA0000551 220080806G7261 BEARING DOUG MD90 MD9030 3023690NM OIL PUMP SEIZED B HZ3RK NONE O OTHER ININSP/MAINT 1 WP07 PUMP SEIZED, OIL PUMP BEARING BRACKET SHOWED SIGNS OF RUBBING WITH THE OIL PUMP GEAR. PENDING ENGINEERING EVALUATION. (K) 2L72 4F RTA6WE 20080903 CE 2008 9 3 2008FA0000552 120080521G2910SA7670024001 LINE RAYTHNDH125 HAWKER800XP 7150012CE HYD SYSTEM RUPTURED D A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 GL23484JC 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 GEAR ACTUATION WAS IN PROCESS. SUSPECT MFG DEFECT. AC MFG NOTIFIED. THIS IS FIRST INSTANCE OF THIS FOR THS AC. LT MLG DOOR HYDR LINE RUPTURED 2 MONTHS BEFORE IN THE SAME EXACT WAY AND CAUSED THE SAME DAMAGE. MFG NOTIFIED AGAIN. 2L72 4F RTA3EU 20080903 CE 2008 9 3 2008FA0000553 120080808G2910SA7670024001 LINE RAYTHNDH125 HAWKER800XP 7150012CE HYD SYSTEM RUPTURED D A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 GL23484JC2369 258644 HYDR FLEXIBLE LINE TO THE LT LANDING GEAR DOOR ACTUATOR RUPTURED DURING FLIGHT. LOSS OF FLUID CAVITATED LT AND RT ENG DRIVEN 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. SAME LINE RUPTURED 2 MONTH PREVIOUSLY ON RT SIDE ACTURATOR CAUSING SAME DAMAGE. MFG AGAIN NOTIFIED. (K) 2L72 4F RTA3EU 20080902 CE 2008 9 2 2008FA0000554 120080813G7160125083029 INTAKE DUCT CESSNA206 TU206G 2073357CE INDUCTION BOX CRACKED C K NONE O OTHER ININSP/MAINT 1 SW17602MB10 U20604052 MANUFACTURER SUPPLIED ENG INTAKE DUCT BEFORE THE AIR FILTER IS SUBJECT TO CRACKING IN MULTIPLE LOCATIONS. THIS PARTICULAR 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 COMPOSITE MATERIAL IS NO LONGER AVAILABLE. (S) 1H71 3O A4CE 20080825 EA 2008 8 25 2008FA0000555 120080804G3260 INDICATION SYS CNDAIRCL600 CL6002B16 1900305EA MLG MALFUNCTIONED C O OTHER P NO WARNING INDICATION LDLANDING 1 SW99190MP 5161 ON APPROACH TO KSSI, WHEN LANDING GEAR DEPLOYED, ONLY RECEIVED NOSE DOWN INDICATION, NO MAIN GEAR DOWN INDICATION. CYCLED SEVERAL TIMES. CREW DIVERTED TO KAGS AND USED EMERGENCY PROCEDURE TO LOWER GEAR. ALL GEAR DOWN AND LOCKED FOR LANDING. MAINTENANCE WAS UNABLE TO DUPLICATE. CHECKED ADJUSTMENTS OF MAIN LANDING GEAR PROXIMITY SWITCHES, VISUALLY INSPECTED 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 FLIGHT WAS ACCOMPLISHED AFTER MAINTENANCE WITH ALL OPERATIONS NORMAL. THERE IS NO HISTORY OF THIS DISCREPANCY ON THIS AC2L72 4F RTA21EA 20080902 CE 2008 9 2 2008FA0000556 120080702G29311240583000 TRANSDUCER LEAR 60 60LEAR 5170707CE HYD PRESSURE MALFUNCTIONED C O OTHER J WARNING INDICATION LDLANDING 1 SW99262FX633 323 HYDRAULIC PRESSURE GAUGE READ ZERO ON LANDING CHECK. FLAPS AND LANDING GEAR EXTENDED NORMALLY. GAUGE WAS SEEN TO FLUCTUATE BETWEEN NORMAL TO 1000 PSI TO ZERO PSI ON APPROACH. BRAKES AND THRUST REVERSERS OPERATED NORMALLY. GAUGE READS ZERO DURING TAXI. CREW DECLARED AN IFE AS A PRECAUTION. MAINTENANCE REPLACED THE HYDRAULIC PRESSURE TRANSDUCER. OPS CHECK AND LEAK CHECK PERFORMED SATISFACTORILY. (S) 2L72 4F RTA10CE 20080826 NM 2008 8 26 2008FA0000557 120080801G2742900C2010375103 CONTROL ROD DOUG MD900 MD900 3027375NM VERTICAL STAB BROKEN C A UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 WP25902RN 90000121 EXPERIENCED EXCESSIVE LT PEDAL (2-3 INCHES) DURING CRUISE FLIGHT AT 70 TO 80 PERCENT TRANSMISSION TORQUE. DURING POST FLIGHT FOUND THAT THE LT VERTICAL STABILIZER MOVED FREELY. FURTHER INSPECTION REVEALED THAT THE LT VERTICAL STABILIZER CONTROL SYSTEM (VSCS) ACTUATOR CONTROL ROD WAS BROKEN AT THE THREADED PORTION. (S) 1G72 3U NCH19NM 20080903 CE 2008 9 3 2008FA0000558 120080801G57530425118 FITTING CESSNA140 140 2071602CE LT TE FLAP CORRODED D K NONE O OTHER ININSP/MAINT 1 GL0376671 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 DURING PREFLIGHT SHOULD HELP DETECT THE PROBLEM SO THAT CORRECTIVE ACTION CAN BE TAKEN. 1H71 3O NCA768 20080903 EA 2008 9 3 2008FA0000559 220080810G7414 DRIVE SHAFT PIPER PA28 PA28R200 7102811SO LYC O360 IO360C1C 41514EA MAGNETO BROKEN D K NONE O OTHER ININSP/MAINT 1 CE012952R 03092108 28R35344 DISTRIBUTOR (POINT CAM SHAFT BROKE FLUSH WITH UPPER MAG GEAR INNER RACE CAUSING TOTAL MAG FAILURE. PART WAS RETURNED TO OWNER. (K) 1L71 3O3 O 2A13 1E10 20080903 CE 2008 9 3 2008FA0000560 120080808G3222S18271 VALVE CESSNA172 R172K 2072431CE NOSE STRUT DAMAGED D K NONE O OTHER ININSP/MAINT 1 SW099927V R1722354 A NEW VALVE WAS ORDERED AND INSTALLED TO CURE A SUSPECTED LEAK IN THE VALVE CORE. THE NEW VALVE ARRIVED WITH A BRIGHT APPEARANCE, EITHER CHROME OR NICKEL PLATED. WITH THE NEW VALVE INSTALLED, THE STRUT LEAK WORSENED. AN EXTERNAL INSP REVEALED 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 THREADS WITH A PICK AND THE VALVE WAS REINSTALLED WITHOUT FURTHER DIFFICULTY. SUBMITTER ADMITS THAT THE PLATING RESULTS IN1H71 3O 3A17 20080903 SO 2008 9 3 2008FA0000561 120080513G2497 WIRE PIPER PA44 PA44180 7104402SO LYC O320 O320* 41508EA ALTERNATOR BROKEN D O OTHER O OTHER NRNOT REPORTED 1 SO152163F H092370 447995167 INTERNAL FAILURE DUE TO BROKEN WIRES INTERNALLY, HEAVY SPARKING INSIDE ENGINE COMPARTMENT. (K) 1L72 3O3 O A19S0 E274 20080903 CE 2008 9 3 2008FA0000562 120080627G531112943003723 FRAME BEECH 1900 1900D 1154162CE PWA PT6 PT6* 52043EA FS 363.25 CRACKED B E81RK NONE O OTHER ININSP/MAINT 1 GL03534M 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, BECAUSE OF THE MISSING CLIP, MAY HAVE ADDED TO THE FRAME FAILURE. THE DAMAGE WAS REPAIRED IAW SRM AND DER REPORT. (K) 2L72 4T3 TRTA24CE E2NE 20080903 CE 2008 9 3 2008FA0000563 120080808G28105038903417 FUEL CELL BEECH B300 B300 1159232CE PWA PT6 PT6A60A 52043NE LT WING PLUGGED B E81RO OTHER O OTHER NRNOT REPORTED 1 GL03350RV60 FL585 PILOT REPORTED FUEL IMBALANCE OF 200 LBS AFTER TOPPING OFF TANKS. FUEL QUANTITY INDICATING AND FUEL VENT SYSTEM WERE CHECKED AND CONFIRMED GOOD. DURING DEFUEL, NOTED THAT LT WING TRANSFER TO LT NACELLE TANK WAS TOO SLOW TO ALLOW FULL SERVICING OF LT WING FUEL SYSTEM . ACCESSED FUEL TRANSFER TUBE FROM INSIDE OF LT IB AFT FUEL CELL, TO NACELLE FUEL TANK, AND FOUND IT PLUGGED WITH A RAG. REMOVED RAG, CLEANED WING FUEL STRAINER, AND SECURED FUEL SYSTEM. LT FUEL SYSTEM CAN NOW BE SERVICED TO FULL. (K) 2L72 4T4 TRTA24CE E4EA 20080903 CE 2008 9 3 2008FA0000565 120080813G7160125083029 INTAKE DUCT CESSNA206 TU206G 2073357CE CONT O550 IO550* SO ENGINE CRACKED B RC0RO OTHER O OTHER NRNOT REPORTED 1 SW17602MB10 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 REINFORCE THIS DUCT. THIS REPAIR STATION IS LOOKING INTO THIS ALTERATION TO THIS DUCT WHEICH MAY REQUIRE DER SUPPORT. AT PRESENT, THE DUCTS ARE REQUIRING REPAIRS OF REPLACEMENT EVERY 50 HOURS. A PMA REPLACEMENT DUCT MADE FROM COMPOSITE MATERIAL IS NO LONGER AVAILABLE. (K) 1H71 3O3 O A4CE E3SO 20080827 NM 2008 8 27 2008FA0000566 120080218G7830315A2502102 PANEL BOEING737 737 UTILSYSNM THRUST REVERSER DELAMINATED B Z6WRO OTHER O OTHER NRNOT REPORTED 1 CE07 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 DELAMINATION AND CONTINUES TO GROW. THE PANEL IS BEING SCRAPPED AS A RESULT. THE BONDING SURFACE OF THE PERFORATED PANEL APPEARS TO HAVE BEEN INADEQUATELY PREPPED PRIOR TO BONDING IN THE ORIGINAL BUILD. THIS CONDITION WAS DISCOVERED AT SPIRIT AEROSYSTEMS REPAIR STATION Z6WR3367 WHERE IT WAS SENT FOR REPAIR FROM CONTINENTAL AIRLINES. (S) 2L72 4F RTA16WE 20080828 NM 2008 8 28 2008FA0000567 120080822G5313 LONGERON DOUG MD80 MD83 3023681NM BS 154 L23L DAMAGED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15874GA 49643 DURING SCHEDULED REPAIR, FOUND DOUBLE DRILLED ON LONGERON 23L AT FS 154.5. (S) 2L72 4F RT 20080828 NM 2008 8 28 2008FA0000568 120080822G5313 LONGERON DOUG MD80 MD83 3023681NM BS 150 L23L DAMAGED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15874GA 49643 DURING SCHEDULED REPAIR, MISDRILLED 3 EACH HOLES AT FS 150 AND 3 INCHES BELOW LONGERON 23L. (S) 2L72 4F RT 20080903 EU 2008 9 3 2008FA0000570 120080729G6220704A33651158 BEARING SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1 60030NE M/R SWASHPLATE WORN B P49RK NONE O OTHER ININSP/MAINT 1 EA65277HC688 M1687 2052 COMPLIED WITH 2 YEAR / 500 HR INSP. TASK 62.30.00.601 M/R SHAFT INSP. WHILE PERFORMING INSP OF SWASHPLATE GUIDE UNIBALL 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, OUTER 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) 1G71 3U3 UNCH9EU E19EU 20080903 CE 2008 9 3 2008FA0000571 120080722G2730 CONTROL CABLE MTSBSIMU2 MU2B36A 5780413CE ELEVATOR BROKEN B IZ2RK NONE O OTHER ININSP/MAINT 1 SW15868MA9216 708SA PILOT COMPLAINED OF POOR ELEVATOR TRIM OPS. UPON INSP, FOUND ELEVATOR TRIM CABLE 311AS-14-7245 BROKEN (RT CABLE). 311AS-14-7362 (LT CABLE), 010A-61179-81 (RT AFT) CABLES FRAYED. IDLER PULLEY SHAFT ON PITCH TRIM SERVO SHEARED. REPLACED CABLES & SERVO, OPS CHECKED. RIGGED AS NEEDED. 1H72 3T A10SW 20080903 SO 2008 9 3 2008FA0000572 120080818G323335380000000 ACTUATOR GULSTMG159 G159 3952202SO GARRTTTFE731TFE7314R 01518WP RT MLG LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 NM075950C774 213 RT MLG SIDE BRACE ACTUATOR LEAKING FROM SWITCH ASSY. SIDE BRACE ACTUATOR REMOVED, REPLACED WITH REPAIRED ACTUATOR ASSY. 2L72 4T4 F 1A17 E6WE 20080903 CE 2008 9 3 2008FA0000573 120080821G28421183810025 FLOAT VALVE RAYTHN390 390 7150030CE FUEL TANK SEPARATED D K NONE N FALSE WARNING ININSP/MAINT 1 WP013725L1219 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 INSIDE FUEL TANK AREA. RECOMMEND INSP OF LT & RT FWD VENT VALVE FLOAT ASSEMBLIES AT NEXT EARLIEST TIME OR INSP. REPLACE ALL SUSPECTED OR FAULTY FLOAT VALVES. 1L72 3F RTA00010WI 20080903 SO 2008 9 3 2008FA0000574 220080815G7414 IMPULSE COUPLING CESSNA182 182N 2072730CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C203 GL MAGNETO FAILED D K NONE O OTHER ININSP/MAINT 1 WP07925511736 18260256 275543R 891141 PILOT PERFORMED PRE-FLIGHT INSP DISCOVERED OIL ON FWD PORTION OF COWLING, SLIGHT OIL RESIDUE ON WINDSHIELD. MECHANIC REMOVED 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, WE DON`T HAVE FURTHER INFORMATION TO ASCERTAIN THIS CONDITION) SHATTERED MAGNETO BODY HSG. MAGNETO WAS STILL FIRING, FIXED TO ENGINE (NOT LOOSE) ENGINE OPS WAS REPORTED NORMAL UPON ARRIVAL OF LAST FLIGHT, WHICH SEEMS TO INDICATE THAT MAGNETO HAD OPERATED IN THIS CONDITION FOR WHAT APPEARS TO BE AT LEAST AN HOUR OR MORE. NO MISFIRE OR MAGNETO DROP DETECTED. 1H71 3O3 ONT3A13 E273 5 CP3EA 20080904 NM 2008 9 4 2008FA0000575 120080821G2421 SHAFT DOUG MD90 MD9030 3023690NM AC GENERATOR SEIZED C HZ3RK NONE O OTHER ININSP/MAINT 1 WP07 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 FROM THE BEARING FAILURE. PENDING ENGINEERING EVALUATION. (K) 2L72 4F RTA6WE 20081001 EA 2008 10 1 2008FA0000577 220080612G8530AEL12688P020 VALVE SEAT LYC O360 IO360A1A 41514EA CYLINDER HEAD DAMAGED B Y2GRO OTHER O OTHER NRNOT REPORTED 1 EA23 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 OVERHAULED CYLINDER. (K) 3 O 1E10 20081001 EA 2008 10 1 2008FA0000578 220080716G8530AEL12688P020 VALVE SEAT LYC O360 IO360C1E6 41514EA CYLINDER HEAD DAMAGED B Y2GRK NONE O OTHER ININSP/MAINT 1 EA23 INTAKE VALVE SEAT CAME LOOSE FROM THE SEAT BORE IN THE CYLINDER HEAD. THE LOOSE SEAT DAMAGE TO CYLINDER HEAD, VALVE, AND VALVE SEAT. INTERFERENCE FIT BETWEEN THE VALVE SEAT AND THE CYLINDER HEAD WAS NOT CORRECT. THIS WAS AN OVERHAULED CYLINDER. (K) 3 O 1E10 20080909 SO 2008 9 9 2008FA0000579 120080610G2916 RESERVOIR PIPER PA31 PA31325 7103105SO LYC O540 LTIO540F2BD 41533EA HYD SYSTEM LOW G O OTHER J WARNING INDICATION APAPPROACH 1 CE01727HB 318112006 L266868A ON FINAL APPROACH THE LANDING GEAR HANDLE WAS PLACED IN THE DOWN POSITION. THE GEAR WAS VIEWED IN THE MIRROR AT 45 DEGREE 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 SERVICED. TRAINING WAS CONDUCTED FOR ALL MAINT ON PROPERLY SERVICING THE POWERPACK. THIS CAN BE TRICKY AS IT IS DIFFICULT TO SEE THE FLUID LEVEL. (K) 1L72 3O3 O A20SO E14EA 20080909 CE 2008 9 9 2008FA0000580 120080827G2435 BEARING CESSNA500 S550 2076607CE PWA JT15 JT15D4 52112NE STARTER GEN FAILED B OW5RO OTHER O OTHER NRNOT REPORTED 1 GL27802Q 95264 S5500157 PCE102330 FRONT BEARING FAILURE IN FLIGHT. (K) 1L72 4F4 FRTA22CE E1NE 20081001 SO 2008 10 1 2008FA0000581 120080812G5100SL53E19600 VERNATHERM PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2A GL FAILED D O OTHER O OTHER TXTAXI/GRND HDL 1 AL0327663392 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 PRESSURE WAS NORMAL.(K) 1L72 3O3 O A20SO E14EA 5 CP33EA 20081006 EA 2008 10 6 2008FA0000583 220080708G8530 CYLINDER HEAD CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA MCAULY2D34C B2D34C16 GL ENGINE SEPARATED G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 WP195268U 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 FOUND TO HAVE SHEARED. ONLY ONE HOLD DOWN STUD WAS LT INTACT. THERE WAS NO HISTORY IN THE AC LOGS TO INDICATE IF THE HOLD DOWN STUDS HAD BEEN REPLACED. (K) 1H71 3O3 O 3A17 E286 5 CP7EA 20080909 CE 2008 9 9 2008FA0000584 120080731G2510551900921 SEAT FRAME CESSNA500 550 2076604CE COCKPIT SEAT CRACKED D O OTHER O OTHER NRNOT REPORTED 1 CE0564TF 5500064 UPPER CHAIR BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW STO-1042WI STRUCTURAL SEAT REPAIR. (K) 1L72 4F A22CE 20081006 2008 10 6 2008FA0000585 120080818G242111522185 GENERATOR FAILED B HZ3RK NONE O OTHER ININSP/MAINT 1 WP07 1572 FAILS SATURATION CURVE CHECK-ZERO VOLTS ANY PHASE. BROKEN LOWER CROSSOVER ON ROTOR. PENDING ENGINEERING EVALUATION. (K) 20081003 EA 2008 10 3 2008FA0000586 220080915G8520TT73806 PUSHROD LYC O235 O235L2C 41505EA ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 WP11 L1972215 (3) PUSHRODS (TT73806) WERE INSTALLED IN THIS ENGINE AND ALL 3 HAD APPROXIMATELY A .3750 INCH VERTICAL CRACK ON BOTH ENDS. CAUSE UNKNOWN - NO RECOMMENDATIONS. (K) 3 O E223 20081006 2008 10 6 2008FA0000587 420080819G6113D57691P DOME MOONEYM20 M20E 5870212SW LYC O360 IO360A1A 41514EA HARTZLHCC2Y HCC2YR1 GL SPINNER CRACKED B NT3RO OTHER O OTHER CRCRUISE 1 WP259485V22 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 BROKE 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. PROBABLE CAUSE: SPINNER DOME IS TOO LARGE FOR A SPINNER WITHOUT A FORWARD BULKHEAD FOR SUPPORT. (K) 1L71 3O3 O 2A3 1E10 5 CP920 20081003 SO 2008 10 3 2008FA0000588 120080826G3220502341 BOLT PIPER PA44 PA44180 7104402SO NG LOCKING PAW SHEARED D MOVVK NONE O OTHER ININSP/MAINT 1 WP21239AT 4496038 DURING FAA CHECK RIDE, THE NOSE LANDING GEAR DID NOT PROVIDE A GREEN LIGHT AND THE GEAR UNSAFE WARNING LIGHT AND HORN OPERATED. 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. THIS PREVENTED THE PAW FROM ACTUATING PROPERLY AND CLOSING THE DOWN LIMIT SWITCH. UPON REPLACEMENT WITH A NEW BOLT, THE PAW ACTUATED PROPERLY AND THE GEAR RETRACTION AND EMERGENCY EXTENSION WERE NORMAL WITH PROPER INDICATIONS. (K) 1L72 3O A19S0 20081006 GL 2008 10 6 2008FA0000589 120080826G2110220045510 DRIVE SHAFT CIRRUSSR SR22 2130001GL CONT O550 IO550* SO COMPRESSOR SHEARED B 5CSRK NONE O OTHER ININSP/MAINT 1 SW05433CF 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 WARRANTY. WE HAVE TRIED SEVERAL RECOMMENDATION FROM MFG TO SOLVE THIS PROBLEM TO NO AVAIL. (K) 1L71 3O3 ONTA00009CHE3SO 20081006 CE 2008 10 6 2008FA0000590 120080813G3222998201005 STRUT BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE NLG MALFUNCTIONED C E81RK NONE O OTHER ININSP/MAINT 1 GL031250 FA88 POSITION OF THIS TORQUE LINK MOUNT RELATIVE TO THE SHIMMY DAMPNER ARMS HOLE ARE SUCH THAT THE TWO PARTS INTERFERE WITH EACH OTHER AND DON’T ALLOW THE STRUT TO COMPRESS CLOSER THAN 2 INCHES FROM FULLY COLLAPSED. (K) 2L72 4T4 T A24CE E4EA 20081003 EA 2008 10 3 2008FA0000591 220080805G8520ST203P010 PISTON RING CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA ENGINE MISMANUFACTURED D K NONE W INADEQUATE Q C ININSP/MAINT 1 CE032170Q25 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 OPERATING SO POORLY, DUE TO BLOW-BY, THAT IT WAS CONSIDERED UNSAFE AND GROUNDED. INDEPENDENT HARDNESS TESTING BY QUALITY TESTING SVCS, INC, COMFIRMED THE RINGS WERE SOFT. COMPARATIVE TESTS WERE PERFORMED AGAINST PISTON RINGS. AFTER SWITCHING TO OTHER, THERE HAVE BEEN NO PROBLEMS.(K) 1H71 3O3 O A20CE 1E10 20081006 CE 2008 10 6 2008FA0000592 120080821G323012801111 SWIVEL FITTING CESSNA182 R182 2072734CE LT GEAR LEG FAILED H O OTHER O OTHER TXTAXI/GRND HDL 1 GL034652T R18201725 BRAKE SWIVEL JOINT FAILED LEADING TO FAILURE OF LT BRAKE WHEN EXITING RUNWAY. (K) 1H71 3O RT3A13 20081006 EU 2008 10 6 2008FA0000593 120080811G3520MC1014101 OXYGEN MASK BRAERODH125 BAE125800A 1500285EU CABIN FAILED D G13RK NONE O OTHER ININSP/MAINT 1 GL13862CW 258062 THREE OXYGEN MASKS WERE FOUND TO HAVE THE SAME FAULT. WHEN THE EMERGENCY/PRESS TO TEST CONTROL WAS TURNED TO EMERGENCY THERE WAS NOT A POSITIVE INCREASE IN PRESSURE. REF MFG MM 35-20-52, PAGE 502 TEST (13). PROBABLE CAUSE: UNKNOWN, RECOMMENDATION: INCREASE HOW OFTEN CREW OXYGEN MASKS ARE TESTED AND INSURE THAT THEY ARE BEING TESTED PROPERLY.(K) 2L72 4F RTA3EU 20081006 EU 2008 10 6 2008FA0000594 120080811G3520MC1014101 OXYGEN MASK BRAERODH125 BAE125800A 1500285EU CABIN DAMAGED D G13RK NONE O OTHER ININSP/MAINT 1 GL13897CW 258077 THREE OXYGEN MASKS WERE FOUND TO HAVE THE SAME FAULT. WHEN THE EMERGENCY/PRESS TO TEST CONTROL WAS TURNED TO EMERGENCY THERE WAS NOT A POSITIVE INCREASE IN PRESSURE. REF MFG MM 35-20-52, PAGE 502 TEST (13). PROBABLE CAUSE: UNKNOWN, RECOMMENDATION: INCREASE HOW OFTEN CREW OXYGEN MASKS ARE TESTED AND INSURE THAT THEY ARE BEING TESTED PROPERLY. (K) 2L72 4F RTA3EU 20081007 EA 2008 10 7 2008FA0000595 120080821G324160025663 PCB CNDAIRCL600 CL600* 1900302EA MLG UNSERVICEABLE D K NONE O OTHER ININSP/MAINT 1 NM01604SJ JAN82118 1042 UPON LANDING, THE LT OB TIRE BLEW. UPON INSP, TIRE SHOWED SIGNS OF A SEVERE SKID. TESTED THE ANTISKID SYS & TESTED NORMAL. 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 TECH SUPPORT & INFORMED THE COMPUTER HAD 2 IDENTICAL PCB CARDS THAT COULD BE SWAPPED FOR TROUBLESHOOTING PURPOSES. ONE CARD 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. R2L72 4F RTA21EA 20081007 CE 2008 10 7 2008FA0000596 120080821G782083004 MUFFLER CESSNA150 150H 2071818CE CONT O200 O200A 17020SO ENGINE FAILED D K NONE O OTHER ININSP/MAINT 1 SW0522355339 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) 1H71 3O3 O 3A19 E252 20081003 NE 2008 10 3 2008FA0000597 220080826G7250305086010 SUPPORT AMD FALC50FALCON2000 2730170NM CFE CFE73811B NE NR 4 BEARING CRACKED B ZN3RK NONE O OTHER ININSP/MAINT 1 WP0748CG 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 INTERFERENCE FIT TO ELIMINATE MOVEMENT. (K) 2L72 4F4 FRTA50NM E44NE 20081007 GL 2008 10 7 2008FA0000598 120080814G5344DA4522100002 HINGE DIAMONDA40 DA40 2990002GL AFT PAX DOOR BROKEN D L10RK NONE O OTHER ININSP/MAINT 1 GL11681DS523 40611 THE REAR CABIN DOOR AFT HINGE HAS BROKE AS DECRIBED IN AC 43-16A ALERT 360. PROBABLE CAUSE IS REAR HOLD-OPEN CYLINDER. 1L71 3O NTA47CE 20081006 GL 2008 10 6 2008FA0000599 120080814G5210DA4522100002 HINGE DIAMONDA40 DA40 2990002GL AFT CABIN DOOR CRACKED D L10RK NONE O OTHER ININSP/MAINT 1 GL11504DS 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 HOLD-OPEN CYLINDER. (K) 1L71 3O NTA47CE 20081006 CE 2008 10 6 2008FA0000600 120080702G3240 BRAKE ASSY CESSNA525 525B 2076616CE WILINTFJ44 FJ44 66000GL MLG MALFUNCTIONED D O OTHER O OTHER TXTAXI/GRND HDL 1 GL0392MA 525B0048 NORMAL LANDING UNTIL BRAKE APPLICATION, AT BRAKE APPLICATION AC YAWED AGRESSIVELY TO THE LT. AC WAS CONTROLLED WITH RT BRAKE AND NOSE WHEEL STEERING. RT BRAKE APPEARED WEAK, AS SPEED DECREASED DIRECTION CONTROL WAS HARDER TO MAINTAIN. AC DECELERATED SLOWER THAN NORMAL APPROACHING END OF RUNWAY. EMERGENCY BRAKE WAS APPLIED. LT BRAKE GRABBED FORCING THE ACFT OFF THE RUNWAY INVESTIGATION IN TO SOURCE OF THE PROBLEM IS ON GOING. PN AND PART NAME WILL FOLLOW AFTER MFG TEST COMPONENTS. (K) 1L72 4F4 FRTA1WI E3GL 20081003 CE 2008 10 3 2008FA0000601 120080901G8011149NL STARTER CESSNA172 172S 2072439CE ENGINE FAILED B NO1YK NONE O OTHER ININSP/MAINT 1 EA35GMEGS55 10723 STARTER MOTOR FAILURE, AFTER PRE-FLIGHT CHECK, THE STARTER MOTOR WAS UNABLE TO TURN THE ENGINE OVER. (K) 1H71 3O NT3A12 20081003 CE 2008 10 3 2008FA0000602 120080814G792199103434 OIL COOLER CESSNA208 208 2073702CE PWA PT6 PT6A114 52043NE CRACKED B MT9RK NONE O OTHER ININSP/MAINT 1 SW059762F 20800181 PCE17397 UPPER MOUNTING FLANGE HAS A 1.25 INCH CRACK AGAINST OIL COOLER BODY. (K) 1H71 3T3 TNTA37CE E4EA 20081003 CE 2008 10 3 2008FA0000603 120080723G2820 RING RAYTHN390 390 7150030CE WILINTFJ44 FJ442A GL REFUELING SYS DISLODGED W NUUYK NONE K FLUID LOSS ININSP/MAINT 1 EA35390EV RB PRESSURE REFUELING CONNECTION CAP FOUND WITH SEALING RING DISLODGED AND HOLDING THE CHECK VALVE OPEN WHEN THE CAP IS INSTALLED. FUEL LEAK FROM CAP CAUSING FUEL TO FLOW FROM IT UP THE SIDE OF THE AC. THE FUEL FLOWING UP THE OUTSIDE OF THE ACFT HAS BEEN DRAWN INTO THE REAR MAINT BAY BY DIFFERENTIAL PRESSURE AT THE GROUND POWER SOCKET AND SPRAYED OVER FLYING CONTROL CABLES AND ELECTRICAL EQUIPMENT IN THE MAINT BAY AND TAIL CONE, THE DE-ICE CONTROL UNIT, STROBE POWER SUPPLY, PITCH TRIM COMPUTER, COCKPIT VOICE RECORDER AND MAIN POWER DISTRIBUTION AND RELAY BOX ARE ALL CONTAMINATED. (K) 1L72 3F4 FRTA00010WIE3GL 20081003 GL 2008 10 3 2008FA0000604 120080814G5610 CANOPY AMTR ZODIACCH601XL 05615PWGL COCKPIT DAMAGED G K NONE O OTHER ININSP/MAINT 1 SW05451BB 601051S CANOPY OPENED IN FLIGHT RESULTING IN THE ACFT ENTERING INTO A NOSE DIVE ATTITUDE AND IMPACTING THE GROUND SERIOUSLY INJURING 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 CANOPY LOCKS TO LATCH DOWN ON. THE CANOPY PLEXIGLASS IS VERY THIN AND COVERS A LARGE CANOPY AIRFRAME AREA WHICH MAKES THE CANOPY LOOSE AND WOBBLY. THE TWO GASEOUS RETRACT/ EXTEND SHOCKS ON EACH SIDE OF THE FWD CANOPY ALSO APPEAR TO BE TOO STRONG (40 PSI EACH) WHICH MAY CAUSE THE CANOPY TO HAVE A TENDENCY TO EXTEND IN THE OPEN POSITION IN FLIGHT. IN GENERAL, THE1L71 EXPA1L71 20081003 CE 2008 10 3 2008FA0000605 120080807G3246D30260 WHEEL CESSNA172 172M 2072418CE LYC O320 O320* 41508EA LT MLG FAILED G K NONE O OTHER ININSP/MAINT 1 CE179925V4450 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 E1H71 3O3 ONT3A12 E274 20081006 CE 2008 10 6 2008FA0000606 120080815G322263420003 FORK CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL NLG BROKEN B K NONE O OTHER ININSP/MAINT 1 GL25300BV1928 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 RESULTANT 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 CAUSE. (K) 1L72 4F4 FRTA1WI E3GL 20081007 NE 2008 10 7 2008FA0000607 220080906G7250BRR19985 TURBINE BLADES GULSTMGV GULFSTREAMGV3980116SO RROYCEBR700 BR700710A110 NE HP TURBINE CRACKED C K NONE O OTHER ININSP/MAINT 1 WP01551GA3516 606 11325 DURING A RECENT MID LIFE INSPECTION OF THIS ENGINE BY THE MFG, 58 OF 74 FIRST STATE TURBINE BLADES WERE FOUND CRACKED BEYOND SERVICEABLE LIMITS. THIS WAS A HIGH FAILURE RATE CONSIDERING THE LOW TOTAL ENGINE HOURS. A REPORT FROM THE MFG INTENDING TO PROVIDE AN UNDERSTANDING FOR THE HIGH RATE OF FAILURE STATED THAT SAND WAS INGESTED AND WAS BLOCKING SOME COOLING HOLES LEADING TO THERMAL STRESSES WHICH CAUSED THE CRACKS. OF INTEREST IS THAT WHILE BOTH ENGINES ON THIS PARTICULAR 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 2L72 4F4 FRTA12EA E00057EN 20081007 GL 2008 10 7 2008FA0000608 220080904G72002544198 BEARING HONEYWELL BELL 206 206L1 1182107SW ALLSN 250C 250C30 03013GL PT GOVERNOR FAILED B HEFRO OTHER O OTHER NRNOT REPORTED 1 WP01396RL 1648 BR44409 45396 890360 SPOOL BEARING ASSY (PN 2544198) FAILED INTERNALLY. BEARING ASSY NO LONGER ROTATES AND CAUSED DRIVE SHAFT (PN 2539033) GUIDE POST AND FORK ON GOVERNOR LEVER ASSY. (PN 2523293) TO BEND. ONE FLYWEIGHT (PN 2544200) WAS DAMAGED FROM THE SPOOL BEARING CHAFING. (K) 1G71 3U3 U H2SW E1GL 20081003 GL 2008 10 3 2008FA0000609 220080905G7230 BLADE BELL 206 206B3 1181506SW ALLSN 250C 250C20J 03013GL COMPRESSOR FAILED B HEFRO OTHER O OTHER NRNOT REPORTED 1 WP0143MA 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) 1G71 3U3 U H2SW E4CE 20081003 GL 2008 10 3 2008FA0000610 220080908G72002544198 BEARING BELL 206 206L4 1182110SW ALLSN 250C 250C30 03013GL SPOOL FAILED B HEFRO OTHER O OTHER NRNOT REPORTED 1 WP01520RL2932 942 52052 CAE895008 SPOOL BEARING ASSY FAILED INTERNALLY. BEARING ASSY NO LONGER ROTATES AND CAUSED DRIVE SHAFT GUIDE POST AND FORK IN GOVERNOR LEVER ASSY TO BEND. THE UPPER BEARING LOWER SHIELD AND RETAINER HAS COME OFF. THE LOWER BEARING IS INTACT BUT NO LONGER ROTATES. (K) 1G71 3U3 UNCH2SW E1GL 20081007 SO 2008 10 7 2008FA0000611 120080814G32004049B TUBE MAULE MX7 MXT7160 5470204SO LYC O320 O320* 41508EA AT FORK OLEO SHEARED B TODRO OTHER O OTHER NRNOT REPORTED 1 CE0731865572 17003C OLEO TUBE (PN 4049B) SHEARED OFF AT FORK ASSY (PN 4086E) UPON LANDING DAMAGE DONE TO PROP, ENGINE, ENGINE MOUNT, NOSE GEAR 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) 1H71 3O3 O 3A23 E274 20081003 2008 10 3 2008FA0000612 220080903G7414 BEARING CESSNA182 182T 2072703CE MAGNETO BURNED B L9ORK NONE O OTHER ININSP/MAINT 1 WP1953610503 02111750 18281223 REMOVED MAGNETO TO S/B3-08 AND MFG 500 HOUR INSPECTION. REMOVED HARNESS CAP FOUND A LIGHT SMOKE COLORED FILM COVERING CAP AND DISTRIBUTOR BLOCK. REMOVED MAGNETO FROM ENGINE FOUND BEARING BAR BURNED THROUGH ON LEFT SIDE WHEN VIEWED FROM DRIVE END. (K) 1H71 3O NT3A13 20081007 GL 2008 10 7 2008FA0000613 320080903G6111C13019S CLAMP BEECH 90 F90 1152909CE PWA PT6 PT6A60A 52043NE HARTZLHCB4T HCB4TN3 GL BLADE FAILED B ZY2RK NONE O OTHER ININSP/MAINT 1 WP2390BD 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 THE SAME FINDINGS. BLADE CLAMP WAS REMOVED AND REPLACED WITH AN OHC CLAMP ASSY. ALL WORK WAS PERFORMED IAW SRM 118F, 202A, AND 133C. (K) 1L72 4T4 T A31CE E4EA 6 CP40EA 20081007 GL 2008 10 7 2008FA0000614 320080909G6110B3476A2 ROD DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL PROPELLER BROKEN B LU4RK NONE O OTHER ININSP/MAINT 1 SO19V2LFC BUA26256 BUA26256 BETA ROD CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALFUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20081007 GL 2008 10 7 2008FA0000615 320080909G6110B30012 RING HARTZL DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL PROPELLER BROKEN B LU4RK NONE O OTHER ININSP/MAINT 1 SO19V2LFC29388 BUA26256 BETA RING CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALFUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20081007 2008 10 7 2008FA0000616 420080815G2562DCELL BATTERY PIPER PA28 PA28161 7102803SO ELT LEAKING B KABRK NONE K FLUID LOSS ININSP/MAINT 1 GL1344FT 297 043551 287716219 BATTERYS LEAK ACID ON TO SPRINGS AND CORRODED THEM. (K) 1L71 3O 2A13 20081007 CE 2008 10 7 2008FA0000617 120080822G2121903840311 BLOWER BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCD4N3HCD4N3A GL VENT FAILED B BNGRA UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 GL19904RB 764 LJ1088 PCE25175 FY2838 PILOT DETECTED SMOKE IN CABIN, LANDED. TROUBLESHOT ODOR, CHECK IN ENGINE BAYS, NO DEFECT NOTED. FOUND CABIN VENT BLOWER NOT WORKING, CHECKED BLOWER SYSTEM WIRING, NO DEFECTS NOTED, CHECKED VENT BLOWER UNDER PILOT FLOOR AND FOUND BLOWER MOTOR LOCKED UP. REMOVED ASSY FOUND MOTOR HAD BURNED, ELEC ODOR. REMOVED AND REPLACED VENT BLOWER WITH OVERHAULED UNIT. OPERATION CHECKED NORMAL. THIS MOTOR RUNS ON LOW SPEED ANYTIME AUTO COOL OR AUTO HEAT SWITCH IS ON OR WITH BLOWER SWITCH IN LOW OR HIGH AND ENGINES ARE RUNNING. DURING INSPECTION WITH THIS LOCATION OPEN, CHECK BLOWER FOR PROPER OPERATION AND SPEED. (K) 1L72 3T4 TRT3A20 E4EA 5 CSTC 20081007 SO 2008 10 7 2008FA0000618 120080819G28103848808 TANK PIPER PA32 PA32R301 7103218SO LYC O540 IO540* 41532EA FUEL LEAKING B SVTRK NONE K FLUID LOSS ININSP/MAINT 1 GL0353646607 3246214 THE ACFT OPERATOR DROPPED THE ACFT OFF WITH A COMPLAINT OF A FUEL LEAK IN THE LT WING. THERE WAS EXTERNAL STAINING AT THE IB AFT EDGE OF THE TANK ASSY WHERE IT ATTACHES TO THE WING SKIN. THE TANK WAS REMOVED FROM THE AIRCRAFT TO LOOK FOR THE LEAK. IT APPEARS THAT THE SEALANT HAD DISSOLVED OR WASHED OUT OF THE TANK. THE TANK WAS SENT FOR INSPECTION AND REPAIR. THEY VERIFIED THAT THE SEAM WAS LEAKING AND REPAIRED IT. THERE WAS NO VISIBLE PHYSICAL DAMAGE TO THE TANK OR MOUNTING STRUCTURE. AT THE AGE OF THIS AIRCRAFT, WOULD NOT EXPECT TO SEE A TANK LEAK LIKE THIS UNLESS THE SEALANT WAS IMPROPERLY MIXED AT THE FACTORY OR ASSY OR SOME COMPONENT IN THE FUEL WAS DISSOLVING THE SEALANT. (K) 1L71 3O3 O A3SO 1E4 20081007 CE 2008 10 7 2008FA0000619 120080915G2400 CONTACT BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE RELAY ERODED B CRORO OTHER O OTHER NRNOT REPORTED 1 EA03300TN415 FA168 HAD 3 FAILURES OF THE SAME RELAY, FIRST RELAY LASTED 457 HOURS, SECOND RELAY LASTED 187 HOURS, AND THE THIRD RELAY LASTED 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) 2L72 4T4 T A24CE E4EA 20081007 2008 10 7 2008FA0000620 420080915G2397M3902957357 SOCKET SKRSKYS76 S76B 8143007NE CONNECTOR MISINSTALLED B AMCRO OTHER W INADEQUATE Q C NRNOT REPORTED 1 GL09520AC2422 760380 CREW COULD NOT TRANSMIT ON AN FM FREQUENCY THROUGH NR 1 AUDIO CONTROL BOX. MAINT FOUND CONNECTOR PIN SOCKET INSTALLED BACKWARD. THE PART FOR THE WIRE WAS INSTALLED TOWARD THE PIN SIDE, AND THE PIN SIDE HAD THE WIRE CRIMPED INTO IT. THE SOCKET IS SYMMETRICAL. UNIT HAS BEEN LIKE THIS FOR MANY YEARS. (K) 1G72 4U H1NE 20081003 NE 2008 10 3 2008FA0000621 220080826G7230307241613 COMPRESSOR WHEEL AMD FALC90FALCON900EX 2730009EU GARRTTTFE731TFE73160 NE ENGINE SEPARATED B ZN3RO OTHER O OTHER NRNOT REPORTED 1 WP0758CG 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 THE FORM OF A DISC POST SEPARATION. (K) 2L73 4F4 FRTA46EU E1NM 20081003 CE 2008 10 3 2008FA0000622 120080904G7810265202231 COWLING CESSNA208 208B 2073701CE PWA PT6 PT6A114 52043NE EXHAUST CRACKED B MT9RO OTHER O OTHER NRNOT REPORTED 1 SW059634B 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) 1H71 3T3 T A37CE E4EA 20081003 CE 2008 10 3 2008FA0000623 120080905G5730 SKIN CESSNA310 310Q 2074242CE LT WING CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SW13100EL 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. CRACK WAS FOUND VISUALLY DURING COMPLIANCE WITH MEB76-2 MAIN LANDING GEAR RIB SIDE BRACE CRACKS, DURING INSTALLATION OF SK414-8E. (K) 1L72 3O 3A10 20081003 SO 2008 10 3 2008FA0000624 220080905G8520 BUSHING CESSNA414 414A 2075907CE CONT O520 TSIO520NB 17040SO PISTON PIN CRACKED D K NONE O OTHER ININSP/MAINT 1 SW13414NC 414A0484 DURING CYLINDER NR 2 REMOVAL TO CORRECT CRACKED CYLINDER, FOUND CONNECTING ROD PISTON P/N BUSHING CRACKED WITH LARGE PIECE MISSING FROM EDGE. FAILURE IS AS NOTED IN MFG SB071. REMOVED ALL 6 CYLINDERS FROM ENGINE AND FOUND 4 MORE BUSHINGS CRACKED IN SAME LOCATION. MFG HAS CHANGED BUSHING SLIP LOCATION TO POSITION IAW FIGURE 3 OF SB B807. (K) 1L72 3O3 O A7CE E8CE 20081007 SO 2008 10 7 2008FA0000625 220080905G8520 BUSHING CESSNA421 421C 2076016CE CONT O520 GTSIO520N 17032SO PISTON PIN CRACKED D K NONE O OTHER ININSP/MAINT 1 SW13410AJ 421C1093 823531R DURING CYLINDER NR 5 REMOVAL TO CORRECT HIGH OIL CONSUMPTION , FOUND CONNECTING ROD PISTON PIN BUSHING CRACKED WITH LARGE PIECE MISSING FROM EDGE. FAILURE IS AS NOTED IN MFG SB SB07-1. REMOVED ALL 6 CYLINDERS FROM ENGINE AND FOUND 4 MORE BUSHINGS CRACKED IN SAME LOCATION. MFG HAS CHANGED BUSHING SLIP LOCATION TO POSITION IAW FIGURE 3 OF SB SB071. (K) 1L72 3O3 O A7CE E7CE 20081003 CE 2008 10 3 2008FA0000627 120080723G5753710516000015 HINGE BRACKET BEECH 76 76 1153005CE LYC O360 O360* 41514EA LT WING TE FLAP CORRODED G BEJSO OTHER O OTHER NRNOT REPORTED 1 SO156708A7712 ME302 LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFORM VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN. (K) 1L72 3O3 O A29CE E286 20081007 CE 2008 10 7 2008FA0000628 120080722G575310516000015 HINGE BRACKET BEECH 76 76 1153005CE LYC O360 O360* 41514EA LT WING TE FLAP CORRODED G BEJSO OTHER O OTHER NRNOT REPORTED 1 SO156638D9976 ME268 LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORT RIBS, WHERE HINGE BRACKET PIN FLAP. UNABLE TO PERFORM VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED INSIDE OF SKIN. (K) 1L72 3O3 O A29CE E286 20081003 CE 2008 10 3 2008FA0000629 120080722G575310516000015 HINGE BRACKET BEECH BEECH 76 76 1153005CE LYC O360 O360* 41514EA LT WING TE FLAP CORRODED G BEJSK NONE O OTHER ININSP/MAINT 1 SO15110SU11007 ME81 LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFORM VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN. (K) 1L72 3O3 O A29CE E286 20081003 CE 2008 10 3 2008FA0000630 120080723G575310516000015 HINGE BRACKET BEECH BEECH 76 76 1153005CE LYC O360 O360* 41514EA LT WING TE FLAP CORRODED G BEJSK NONE O OTHER ININSP/MAINT 1 SO15278D 16533 ME23 LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFORM VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN. (K) 1L72 3O3 O A29CE E286 20081006 2008 10 6 2008FA0000631 420080911G6122210044 ROD WOODWARD BEECH 58 58 1152740CE GOVERNOR BROKEN B LU4RO OTHER O OTHER NRNOT REPORTED 1 SO196681L 1098981 TH1088 LIFT ROD WAS DISCOVERED BROKEN AT DISASSEMBLY. (K) 1L72 3O 3A16 20081007 2008 10 7 2008FA0000632 420080911G6122B20429 DRIVE SYSTEM MCAULY CONT O520 IO520* 17032SO BROKEN B LU4RO OTHER O OTHER NRNOT REPORTED 1 SO19CGFLM 790221 SPRING-DRIVE DISCOVERED BROKEN AT DISASSEMBLY. (K) 3 O E5CE 20081007 SW 2008 10 7 2008FA0000633 120080826G6711206076031107 SERVO BELL 206 206B3 1181506SW RT CYCLIC MALFUNCTIONED C O OTHER F FLT CONT AFFECTED TXTAXI/GRND HDL 1 SW996NJ 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 DOWN 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 I1G71 3U H2SW 20081007 SO 2008 10 7 2008FA0000635 220080824G8500 ENGINE CESSNA172 172F 2072414CE CONT O300 O300D 17022SO POWER LOSS B IGBRO OTHER O OTHER NRNOT REPORTED 1 WP018546U 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 DECISION WAS MADE TO LAND AT RADAR FACILITY. BY THIS TIME THE ENGINE HAD STOPPED. WE MADE THE EMERGENCY LANDING AT THE FACILITY 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. 1H71 3O3 ONT3A12 E253 20081007 CE 2008 10 7 2008FA0000636 120080910G323320410202 PIVOT ASSY CESSNA177 177RG 2073709CE MLG ACTUATOR SHEARED B H5GRO OTHER O OTHER NRNOT REPORTED 1 EA077503V4800 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. THIS ALLOWED/CAUSED THE TUBULAR MOUNT STRUCTURE TO FLEX FROM SIDE TO SIDE AND CRACK MOST OF THE WAY THROUGH. (K) 1H71 3O A20CE 20081007 SO 2008 10 7 2008FA0000637 120080902G5510510229615 ANGLE AMRGENAA5 AA5B 3960105SO HORIZONTAL STAB CRACKED B H5GRO OTHER O OTHER NRNOT REPORTED 1 EA07286654640 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 BELIEVE THE SINGLE MOST CAUSE TO BE PILOTS AND MAINT PUSHING DOWN ON THE FWD SSPAR AREA TO RAISE THE NOSEWHEEL OFF THE GROUND. (K) 1L71 3O A16EA 20081007 SO 2008 10 7 2008FA0000638 120080902G5510510229616 ANGLE AMRGENAA5 AA5B 3960105SO HORIZONTAL STAB CRACKED B H5GRO OTHER O OTHER NRNOT REPORTED 1 EA07286654640 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) 1L71 3O A16EA 20080930 GL 2008 9 30 2008FA0000639 120080902G575313431003 HINGE CIRRUSSR SR22 2130001GL CONT O550 IO550* SO TE FLAPS CORRODED B ACORO OTHER O OTHER NRNOT REPORTED 1 EA39121HC724 0277 FLAP HINGES IN ALL POSITIONS BOTH LT AND RT HAVE INTERGRANDULAR CORROSION NEAR THE POINT OF FAILURE. PN 13431-003, PN 13431-004, 13432-002, QTY 2, 13433-006, 13433-005. CONDITION WAS FOUND AT ANNUAL INSPECTION. (K) 1L71 3O3 ONTA00009CHE3SO 20081007 SO 2008 10 7 2008FA0000640 220080801G7414M3215 BRUSHES COLUMBLC41 LC41550FG4005150011NM CONT O550 TSIO550C SO MAGENTO WORN B BIERO OTHER O OTHER NRNOT REPORTED 1 EA21623TS243 41668 914471 DETECTED NUMEROUS MAGNETOS WITH CARBON BLOCKS AND COILS TABS THAT ARE PREMATURELY WEARING OUT IN MAGNETO PN 6320. HAVE HAD CUSTOMERS WITH MAGNETO FAILURES AS EARLY AS 5.5 HOURS ON THEIR NEW MAGNETOS. EVEN THOUGH MFG HAS IDENTIFIED THIS ISSUE AND PUT OUT GUIDANCE TO INSPECT MAGNETOS WITHIN THE NEXT 50 HOURS OF OPERATION AS OF MAY 2, 2008, THIS ISSUE IS A MAJOR CONCERN TO ALL CUSTOMERS DUE TO THE PERFORMANCE ISSUES THEY HAVE EXPERIENCED WITH THESE MAGNETOS AND THE ADDITIONAL DOWN-TIME OF THE AC DUE TO THE FREQUENT INSP REQUIRED (EVERY 100 HRS). MFG NEEDS TO RESOLVE THEIR PRODUCT DEFICIENCY IMMEDIATELY AND THE ANSWER SHOULDN’T BE THE CUSTOMERS BEAR THE COST OF REPLACEMENT OR THE ADDED COST OF FREQUENT INSPECTIONS.1L71 3O3 ONTA00003SEE5SO 20081007 EU 2008 10 7 2008FA0000641 120080917G3230A223801 SWITCH AMD FALC20FALCON20C5 2730107EU GARRTTTFE731TFE7315BR WP MLG INOPERATIVE B DJSRA UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL23531FL 2389 113 P95155C LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K) 2L72 4F4 FRTA7EU E6WE 20081007 EU 2008 10 7 2008FA0000642 120080919G3230123371 CONTROL SWITCH AMD FALC20FALCON20C5 2730107EU GARRTTTFE731TFE7315BR WP MLG INOPERATIVE B DJSRA UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL23531FL 2389 113 P95155C LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K) 2L72 4F4 FRTA7EU E6WE 20081003 NM 2008 10 3 2008FA0000643 120080918G80116420871A7 ADAPTER COLUMBLC42 LC42550FG3505150012NM CONT O550 IO550N 17042SO STARTER FAILED B BIERO OTHER K FLUID LOSS NRNOT REPORTED 1 EA21964SG 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 ATTACHED TO THIS SDR WITH ADDITIONAL INFORMATION. (K) 1L71 3O3 ONTA00003SEE3SO 20081003 GL 2008 10 3 2008FA0000644 320080918G6111A66315A CLAMP HARTZLHCA2 HCA2MVK2 GL PROPELLER BLADE BROKEN B ME4RO OTHER O OTHER NRNOT REPORTED 1 SO19C6BH4 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 BROKEN IN HALF. (K) 5 CP24EA 20081003 GL 2008 10 3 2008FA0000645 320080918G6111A321 BOLT HARTZLHCA2 HCA2MVK2 GL BLADE CLAMP BROKEN B ME4RO OTHER O OTHER NRNOT REPORTED 1 SO19 H138 A-321 CLAMP BOLT WAS FOUND TO BE BROKEN DURING TEARDOWN INSPECTION. BOLT IS CRACKED IN (2) PIECES APPROXIMATELY .5 THE LENGTH DOWN THE TREADED AREA. CLAMP THAT IT WAS ATTACHED TO WAS LATER FOUND TO BE CRACKED DURING MAG PARTICLE INSPECTION. (K) 5 CP24EA 20081008 SW 2008 10 8 2008FA0000646 120080901G6210407015001111 BLADE BELL 407 407 1182206SW MAIN ROTOR CRACKED B UOHRO OTHER O OTHER NRNOT REPORTED 1 GL13407LG 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 THAT THIS CONDITION IS CALLED "TRACER STRANDS" AND IS A CONDITION NEEDING REPAIR. PRODUCT SUPPORT ALSO INFORMED US THAT THIS WOULD BE REFERENCED INT THE MANUALS IN THE NEAR FUTURE AND THAT NEWER BLADES HAVE BEEN CORRECTED FOR THIS PROBLEM. (K) 1G71 3U O H2SW 20081008 EA 2008 10 8 2008FA0000647 120080912G5347SH670RPA0045 SEAT TRACK CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF34* 30015NE FS 424-513 CORRODED B O OTHER O OTHER NRNOT REPORTED 1 GL03636BR 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) 2L72 4F4 FRTA21EA 20081008 EA 2008 10 8 2008FA0000648 120080912G5347SH670RPA0045 SEAT TRACK CNDAIRCL600 CL6002B19 1900309EA FS 409 CORRODED B O OTHER O OTHER NRNOT REPORTED 1 GL03636BR 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 SRM 51-41-00. (K) 2L72 4F RTA21EA 20081008 EA 2008 10 8 2008FA0000649 220080922G74147710398 MAGNETO CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA LEFT SEIZED D A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 SO13712TT 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 CHECK 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 ENGINE. THE INTERNAL PARTS MELTED AND DESTROYED. INSP OF THE INSIDE OF THE ENGINE DRIVE GEARS AND CASE DID NOT REVEAL ANY DAMAGE. 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 MAINT1H71 3O3 ONT3A12 E274 20081008 CE 2008 10 8 2008FA0000650 120080905G532045A336065 BRACKET BEECH MU300 400A 1155402CE FUSELAGE CRACKED B E81RK NONE O OTHER ININSP/MAINT 1 GL0395GK 8304 RK27 DURING SCHEDULED AIRFRAME INSPECTION FOUND PN 45A33606-5 AND PN 45A33606-6 CABIN UNDER FLOOR REINFORCING BRACKETS AT CABIN 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 CAREFULLY DURING SCHEDULED INSPECTIONS ON HIGHER TIME AIRCRAFT, AND/OR AIRCRAFT WITH PREVIOUS HISTORY OPERATED BY CHARTER/AIR TAXI/ FRACTIONAL OPERATORS. (K) 2H72 4F RTA16SW 20081008 SO 2008 10 8 2008FA0000651 120080828G534367054803 TRUNNION PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA NLG CRACKED D K NONE O OTHER ININSP/MAINT 1 EA1327GS 28R7737160 AIRCRAFT CAME IN FOR HARD STARTING. WHILE REMOVING LOWER COWL, TO ACCESS LOWER SPARK PLUGS, TECH NOTICED THE NOSE LANDING GEAR TRUNNION CRACKED WHERE DRAG BRACE ATTACHES TO IT. (K) 1L71 3O3 O 2A13 1E10 20081008 NE 2008 10 8 2008FA0000652 220080822G8500 ENGINE AIRTRCAT300 AT301 0390103SW PWA R1340 R1340* 52016NE STOPPED D O OTHER Y ENGINE STOPPAGE NRNOT REPORTED 1 SW032391Z 3010452 12403 ENGINE QUIT IN MID-AIR. ENGINE HAD 1195.0 HOURS SINCE MAJOR OVERHAUL. (K) 1L71 3R3 R A9SW 5E2 20081008 EA 2008 10 8 2008FA0000653 120080816G5347 SEAT TRACK CNDAIRCL600 CL6002B19 1900309EA BS 409-559 CORRODED D O OTHER O OTHER NRNOT REPORTED 1 GL03636BR 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) 2L72 4F RTA21EA 20081008 EA 2008 10 8 2008FA0000654 220080723G8530HIO360F1AD CYLINDER HEAD ENSTRMF28 F28F 3300412GL LYC O360 HIO360* 41514EA ENGINE DAMAGED G K NONE O OTHER ININSP/MAINT 1 GL138626E 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. HELICOPTER WAS DESTROYED BY FIRE. (K) 1G71 3O3 O H1CE 1E10 20081006 WP 2008 10 6 2008FA0000655 120080921G7810C1691 MUFFLER ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA ENGINE CRACKED D O OTHER O OTHER NRNOT REPORTED 1 GL033203D200 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) 1G71 3O3 O H11NM 1E4 20081008 WP 2008 10 8 2008FA0000656 120080921G7820C1691 MUFFLER ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA EXHAUST BULGED D O OTHER O OTHER NRNOT REPORTED 1 GL03510KJ799 10338 MUFFLER FOUND - BULGED - BLISTERED AND HEAT CRACKED AT TAILPIPE TRANSITION. (K) 1G71 3O3 O H11NM 1E4 20081006 CE 2008 10 6 2008FA0000657 120080919G7810265202231 COWLING CESSNA208 208 2073702CE PWA PT6 PT6A114 52043NE EXHAUST CRACKED B MT9RO OTHER O OTHER NRNOT REPORTED 1 SW059653F 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) 1H71 3T3 TNTA37CE E4EA 20081008 SO 2008 10 8 2008FA0000658 120080901G57116707002 SPAR PIPER PA28 PA28R200 7102811SO LT WING CRACKED D O OTHER O OTHER NRNOT REPORTED 1 EA13 LT WING SPAR CRACKED IN THE AREA OF WHERE THE PIVOT BLOCK IS INSTALLED. (K) 1L71 3O 2A13 20081008 CE 2008 10 8 2008FA0000659 120080916G252071500 SEAT BBAVIA8 8KCAB 2110612CE CABIN FAILED D O OTHER O OTHER NRNOT REPORTED 1 GL137698S 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) 1H71 3O A21CE 20081008 SO 2008 10 8 2008FA0000660 220080917G741410357174 CONTACT BEECH 35 G35 1151516CE CONT E225 E2258 17015SO RT MAGNETO FAILED D O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 NM014998B34 F159517DR D4516 33951 RT MAGNETO FAILED COMPLETELY IN FLIGHT DUE TO THE TIP OF THE CONTACT POINTS HAVING SEPARATED FROM HE ASSY. THIS LEFT THE 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 INFORMATION 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) 1L71 3O3 O A777 E267 20081008 GL 2008 10 8 2008FA0000661 120080917G8011 CASTING DIAMONDA40 DA40 2990002GL CONT IO360 IO360* 17025CE STARTER BROKEN B MZERO OTHER O OTHER TXTAXI/GRND HDL 1 GL15273DS F4L08012 40954 L3417151E CUSTOMER ATTEMPTED TO START ENGINE. WHILE CRANKING ENGINE, CUSTOMER REPORTED A LOUD "CLUNK" AND THE PROPELLER STOPPED ROTATING. INVESTIGATED PROBLEM AND FOUND THE STARTER DRIVE CASTING BROKE FROM STARTER MOTOR. THE CASTING INCLUDED A BEARING FOR THE STARTER DRIVE SHAFT. SHAFT AND BENDIX GEAR WAS STILL ATTACHED TO THE STARTER MOTOR. (K) 1L71 3O3 ONTA47CE E1CE 20081008 CE 2008 10 8 2008FA0000662 120080922G2810 SEAL RAYTHN390 390 7150030CE WILINTFJ44 FJ442A GL FUEL CAP DISLODGED W K NONE K FLUID LOSS TXTAXI/GRND HDL 1 EA35390EU RB242 PRESSURE REFUELING CONNECTION CAP FOUND WITH SEALING RING DISLODGED AND HOLDING THE CHECK VALVE OPEN WHEN THE CAP IS INSTALLED. 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 SPRAYED 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. 1L72 3F4 FRTA00010WIE3GL 20081006 NE 2008 10 6 2008FA0000663 220080826G731450466 PUMP RKWELLNA265 NA26560 7630106CE PWA JT12 JT12A8 52042NE LT ENGINE FUEL WORN C UVVRA UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CE03XCCAM6367 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-OFF POSITION AND MADE AN UNEVENTFUL LANDING. FUEL CONTROL, PN 706633, SN 55832 WAS REMOVED FROM THE ENGINE DRIVEN FUEL PUMP AND WAS FOUND THAT THE FUEL CONTROL DRIVE SHAFT REMAINED ENGAGED IN FUEL CONTROL DRIVE SPLINE ON THE FUEL PUMP. FURTHER INSPECTION OF FUEL CONTROL UNIT REVEALED THAT THE FUEL CONTROL DRIVE SHAFT RETAINER PLATE HAD WORN COMPLETELY THROUGH AND ALLOWED DISENGAGEMENT OF FUEL CONTROL DRIVE SHAFT FROM FUEL CONTROL UNIT. FUEL PUMP, PN 50466, SN 3ACF34 WAS INSPE2L72 4J4 JRTA2WE 1E9 20081015 SO 2008 10 15 2008FA0000665 120081006G2460454668 CIRCUIT BREAKER PIPER PA28 PA28161 7102803SO COCKPIT FAILED B K NONE HG ELECT. POWER LOSS-50 PC MULTIPLE FAILURE NRNOT REPORTED 1 CE058325T6923 288116134 FIVE CIRCUIT BREAKERS FAILED INTERMITTENTLY. THE FAILED CIRCUIT BREAKERS WERE ALL RATED AT 5 AMPS, PIPER P/N 454668, DATE CODE 7903. THE FIVE CIRCUITS AFFECTED WERE; ENGINE GAUGES, TURN COORDINATOR, INSTRUMENT PANEL LIGHTS, OVERHEAD LIGHTS AND RADIO LIGHTS. 1L71 3O 2A13 20081015 CE 2008 10 15 2008FA0000666 120080910G55425533000095 SKIN CESSNA500 560CESSNA 2076750CE RUDDER CRACKED B K NONE O OTHER ININSP/MAINT 1 SW99905LC7599 5600334 THE LOWER FORWARD RUDDER SKIN IS CRACKED 2.5 INCHES, THIS WAS FOUND DURING ROUTINE PHASE INSPECTIONS. THE RUDDER SKIN PART NUMBER IS 5533000-95. THIS IS THE THIRD CRACK FOUND IN THE SAME LOCATION ON THE SAME MODEL AIRPLANE THIS CALENDER YEAR. 2L72 4F RTA22CE 20081015 CE 2008 10 15 2008FA0000667 120081007G56106656100000009 WINDSHIELD LEAR 45 45LEAR 5170805CE COCKPIT CRACKED E A UNSCHED LANDING O OTHER CLCLIMB 1 GL13241LJ1778 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 PLY WINDSHIELD HAD FAILED. STANDARD AERO - LAX CURRENTLY REPLACING WINDSHIELD WITH NEW. 2L72 4F RTT00008WI 20081015 NE 2008 10 15 2008FA0000668 220081003G853066713 GUIDE LYC ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE UNDERSIZE D O OTHER R PARTIAL RPM/PWR LOSS CRCRUISE 1 SW994126A464 12096 L3247448E MOMENTARY SEVERE VIBRATION, POWER LOSS AND ENGINE RPM DROP OCCURRED IN-FLIGHT THEN RETURNED TO NORMAL. COMPRESSION CHECK (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. NO REOCCURRENCE REPORTED. 1G71 3O3 O H11NM 1E4 20081017 CE 2008 10 17 2008FA0000669 120081002G2752232507911 ATTACH BRACKET LEAR 35 35A 5170602CE T/E FLAP CRACKED B AJCAK NONE O OTHER ININSP/MAINT 1 SW15308BW9341 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 OF THE ORIGINAL ALUM RIVETS. 2L72 4F A10CE 20081016 CE 2008 10 16 2008FA0000671 120080924G2797CC75LA61 WIRE HARNESS CESSNA208 208B 2073701CE FLAP SYSTEM CHAFED B MT9RO OTHER O OTHER NRNOT REPORTED 1 SW059738B11206 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 LIGHTS 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) 1H71 3T A37CE 20081016 CE 2008 10 16 2008FA0000672 120080926G534065651285 CHANNEL CESSNA500 560CESSNA 2076750CE CABLE PULLEY MISLOCATED B CWQRK NONE O OTHER ININSP/MAINT 1 GL05809QS 5600698 DURING PHASE 5 INSP, FOUND ELEVATOR TRIM CABLE CONTACTING ELEVATOR SELECTOR DRIVE CHAIN. FOUND THE TRIM CABLE PULLEY CHANNEL BRACKET MIS-LOCATED. ORDERED NEW CHANNEL BRACKET AND RELOCATED PULLEY TO CLEAR SECTOR DRIVE CHAIN. (K) 2L72 4F RTA22CE 20081015 CE 2008 10 15 2008FA0000673 120080924G5350671261713 FRAME CESSNA750 750 2076810CE TAIL CONE CRACKED B CWQRK NONE O OTHER ININSP/MAINT 1 GL05960QS 7500160 DURING ROUTINE INSP, FOUND FWD FRAME PN 6712617-13 CRACKED IN (2) LOCATIONS, ON THE TOP LT AND RT SIDES. ALSO FOUND FRAME AFT OF THIS ONE CRACKED. PN 6712617-14 ON THE TOP RT SIDE. (K) 2L72 4J RTT00007WI 20081015 CE 2008 10 15 2008FA0000674 120080924G5350671261713 FRAME CESSNA750 750 2076810CE TAIL CONE CRACKED E CWQRK NONE O OTHER ININSP/MAINT 1 GL05978QS 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) 2L72 4J RTT00007WI 20081016 CE 2008 10 16 2008FA0000675 120080908G2731666000134 CONTROL CABLE CESSNA560 560XL 2076702CE ELEVATOR TRIM BROKEN B CWQRK NONE O OTHER ININSP/MAINT 1 GL05641QS 5605295 DURING ROUTINE INSP, FOUND BROKEN STRANDS ON ELEVATOR TRIM CABLE ASSY PN 666000134. DAMAGE FOUND WHERE CABLE PASSES THROUGH A SERIES OF "S" PULLEYS. (K) 2L72 4F RTA22CE 20081016 CE 2008 10 16 2008FA0000676 120080908G2731666000134 CONTROL CABLE CESSNA560 560XL 2076702CE TAIL BROKEN B CWQRK NONE O OTHER ININSP/MAINT 1 GL05627QS 5605227 DURING ROUTINE INSP, FOUND CABLE STRANDS BROKEN AND FRAMED. THE DAMAGED AREA OF THE CABLE IS WHERE IT GOES OVER A SERIES OF "S" PULLEYS MOUNTED IN THE HORIZ STAB. SHOULD MAKE THIS A TIME CHANGE ITEM. (K) 2L72 4F RTA22CE 20081016 2008 10 16 2008FA0000677 420080930G2562AK451 ELT PIPER PA34 PA34200T 7103406SO CABIN FAILED B BIERK NONE O OTHER ININSP/MAINT 1 EA212190K 347970096 ELT EMERGENCY LOCATOR TRANSMITTER WILL NOT TEST PROPERLY ON A CONSISTENT BASIS BY DISPLAYING CORRECT 3-DIGIT COUNTRY CODE OR 15 DIGIT HEX ID CODE. THIS ELT HAS BEEN TESTED WITH (2) DIFFERENT 406 MHZ TESTERS DISTRIBUTED BY PN 453-1000 AND PN 453-0131 (MEASURE MODEL MEZ 1000 AND PSION ORGANIZER II MODEL LZ64) AND THE PERFORMANCE OF THE 451 ELT HAS BEEN UNSATISFACTORY. INCONSISTENT RESULTS INCLUDED A DIFFERENT COUNTRY CODE DISPLAYED (305) RATHER THAN CODE 369 OR 366 FOR THE USA AND DIFFERENT 15 DIGIT HEX ID CODE OF 26273300A5FF7FE RATHER THAN THE ACTUAL CODE FOR THE UNIT BEING TESTED (2E285980E4FFBFF). RAN ADDITIONAL TESTS DUE TO THE INCONSISTENT RESULTS AND THE UNIT FAILED TO OPERATE PROPERLY. UNIT WAS REPLACE1L72 3O A7SO 20081015 2008 10 15 2008FA0000678 420080930G2562AK451 ELT PIPER PA34 PA34200T 7103406SO CABIN NO TEST B BIERK NONE L NO TEST ININSP/MAINT 1 EA212190K 347970096 ELT EMERGENCY LOCATOR TRANSMITTER WILL NOT TEST PROPERLY ON A CONSISTENT BASIS BY DISPLAYING CORRECT 3-DIGIT COUNTRY CODE OR 15 DIGIT HEX ID CODE. THIS ELT HAS BEEN TESTED WITH (2) DIFFERENT 406 MHZ TESTERS. DISTRIBUTED, PN 453-1000 AND 453-0131 AND THE PERFORMANCE OF THE 451 ELT HAS BEEN UNSATISFACTORY. INCONSISTENT RESULTS INCLUDED A DIFFERENT COUNTRY CODE DISPLAYED (305) RATHER THAN CODE 369 OR 366 FOR THE USA AND DIFFERENT 15 DIGITS HEX ID CODE OF 26273300A5FF7FE RATHER 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. (K1L72 3O A7SO 20081016 NM 2008 10 16 2008FA0000679 120080829G291025W711008293 LINE ISRAEL1125 1125 NM HYD RESERVOIR CHAFED B JGVRO OTHER K FLUID LOSS NRNOT REPORTED 1 CE09111EL 055 TROUBLESHOT HYDRAULIC SYS AND FOUND THE AUXILIARY HYDRAULIC SYS RETURN LINE THAT CONNECTS THE RETURN HYDRAULIC FILTER TOT THE AUXILIARY HYDRAULIC TANK CHAFED, WHICH CAUSED A SLOW LEAK IN THE HYDRA SYS. ACCOMPLISHMENT OF SB 1125-29-254 "HYDRAULIC TUBE CLEARANCE" PROVIDES INSTRUCTIONS FOR A ONE TIME INSP OF THE CLEARANCE BETWEEN THE PRESSURE TUBE AND THE RETURN TUBE IN THE AREA OF THE HYDR AUXILIARY RESERVOIR. PROCEDURES ARE GIVEN TO ADJUST OR REPLACE THE AFFECTED TUBE ASSEMBLIES DEPENDENT UPON THE INSPECTION FINDINGS. ACFT WAS REPAIRED BY REPLACEMENT OF AUXILIARY HYDRA RETURN TUBE PN 25W711008-293 AND ENSURING CLEARANCES WERE MET IAW THE ACCOMPLISHMENT INSTRUCTIONS OF SB 1125-29-254. (K) 2L72 4F RTA16NM 20081016 GL 2008 10 16 2008FA0000680 320080929G6110A3204 SCREW PIPER PA32 PA32300 7103212SO HARTZLHCC2Y HCC2YK1 GL PROP BLADE WORN B K NONE O OTHER ININSP/MAINT 1 NM11 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 NOTICEABLE. 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) 1L71 3O A3SO 5 CP920 20081028 SO 2008 10 28 2008FA0000681 220081014G8530AEC631397 CYLINDER BEECH 36 A36 1151604CE CONT O550 IO550* SO NR 1 CRACKED D C ABORTED TAKEOFF E VIBRATION/BUFFET TOTAKEOFF 1 SW996036 355 E1422 296794R AIRCRAFT OWNER REPORTED SEVERE VIBRATION. AFTER INSPECTION IT WAS FOUND THAT SPINNER BULKHEAD WAS SEVERELY CRACKED. AFTER FURTHER INSPECTION NR 1 CYLINDER WAS FOUND TO BE CRACKED ALL AROUND THE CIRCUMFERENCE OF THE CYLINDER DIAMETER. THE CRACK 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 IDENTIFIES 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 UNEVE1L71 3O3 O 3A15 E3SO 20081016 CE 2008 10 16 2008FA0000682 120080621G272005701051 CONTROL CABLE CESSNA170 170A 2072304CE RUDDER BROKEN C K NONE O OTHER ININSP/MAINT 1 GL219739A6459 19200 CABLE BROKE AFT OF REAR PULLEY AND BULKHEAD. NO INSPECTION HOLES IN THIS AREA. (K) 1H71 3O A799 20081020 EU 2008 10 20 2008FA0000683 120080919G3210 LANDING GEAR AMD FALC20FALCON20C5 2730107EU GARRTTTFE731TFE7315BR WP FAILED B DJSRA UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL23531FL 113 P95155C LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K) 2L72 4F4 FRTA7EU E6WE 20081020 EU 2008 10 20 2008FA0000684 120080917G3260A223801 POSITION SWITCH AMD FALC20FALCON20C5 2730107EU MLG INOPERATIVE B DJSRA UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION CLCLIMB 1 GL23531FL 113 LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K) 2L72 4F RTA7EU 20081020 CE 2008 10 20 2008FA0000685 120080926G2697 WIRE LEAR 45 45LEAR 5170805CE FIRE DETECTION CHAFED B HMGRO OTHER O OTHER NRNOT REPORTED 1 SW1545NM 1158 253 APU FIRE DETECT CIRCUIT BREAKER POPPED ON RT COCKPIT CIRCUIT BREAKER PANEL DURING POWER UP OF AIRCRAFT. TROUBLESHOT SYSTEM 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 NOT GREAT ENOUGH TO KEEP THE WIRING FROM CHAFING. HAVE NOTIFIED MFG TECH SUPPORT. (K) 2L72 4F RTT00008WI 20081020 CE 2008 10 20 2008FA0000686 120080929G29106317003136 LINE CESSNA525 525 2076601CE HYD SYSTEM RUPTURED B EWCRO OTHER K FLUID LOSS NRNOT REPORTED 1 EA3944CK 2416 5250401 RUPTURE OF TUBE AT SIDE WHERE BENDING DIES LT MARKING BOTH ABOVE AND BELOW OPENING. AFTER TAKEOFF, LOW FLUID AND PRESSURE WARNING LIGHTS CAME ON AND ACFT RETURNED TO AIRPORT. ACFT WAS TURNED OVER TO SERVICE CENTER. LEAK WAS LOCATED AND THE LINE REPLACED ALONG WITH BOTH HYDRAULIC PUMPS. (K) 1L72 4F RTA1WI 20081020 EA 2008 10 20 2008FA0000688 220081001G7314154739704 PUMP CESSNA182 182S 2072701CE LYC O540 IO540AB1A5 EA FUEL SYSTEM CRACKED D O OTHER K FLUID LOSS NRNOT REPORTED 1 FS6066419 18280132 L2616748A PUMP HOUSING CRACKED ALONG SEAM. POSSIBLE WEAK SPOT UPON MANUFACTURING. (K) 1H71 3O3 ONT3A13 1E4 20081028 CE 2008 10 28 2008FA0000689 120081003G27316660161156660161PUSHROD CESSNA560 560XL 2076702CE ELEVATOR TAB WORN C K NONE E VIBRATION/BUFFET CRCRUISE 1 NM07669TT694 5605684 ON RETURN FLIGHT TO HOME STATION, CREW COMPLAINED OF SLIGHT VIBRATION IN FLIGHT. CREW FELT THE VIBRATION WAS ISOLATED TO 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 FLIGHT REVEALED NO FURTHER ISSUE. 2L72 4F RTA22CE 20081028 SO 2008 10 28 2008FA0000690 220081017G8530AEC631397 CYLINDER CESSNA414 414A 2075907CE CONT O520 TSIO520NB 17040SO MCAULY3AF32C3AF32C505 GL ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 CE05414AN654 414A0819 813675R UPON INSPECTION FOUND THAT NR 1 AND NR 5 CYLINDERS WERE CRACKED AND LEAKING FUEL ORIGINATING JUST INBOARD OF THE FUEL NOZZLE BETWEEN THE 16TH AND 18TH COOLING FINS. CYLINDERS WERE NEW WHEN INSTALLED AT ENGINE OVERHAUL. 1L72 3O3 O A7CE E8CE 5 CP22EA 20081023 2008 10 23 2008FA0000693 420080911G6122210044 ROD BEECH 58 58 1152740CE CONT O520 IO520C 17032SO GOVERNOR BROKEN B LU4RK NONE O OTHER ININSP/MAINT 1 SO196681L TH1088 LIFT ROD WAS DISCOVERED BROKEN AT DISASSEMBLY. (K) 1L72 3O3 O 3A16 E5CE 20081023 2008 10 23 2008FA0000694 420080911G6122B20429 SPRING DRIVE MCAULY CONT O520 IO520* 17032SO GOVERNOR BROKEN B LU4RO OTHER O OTHER NRNOT REPORTED 1 SO19CGFLM 790221 SPRING DRIVE DISCOVERED BROKEN AT DISASSEMBLY. (K) 3 O E5CE 20081023 EA 2008 10 23 2008FA0000695 120080909G6120B3476A2 ROD HARTZL DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL BETA SYSTEM BROKEN B LU4RO OTHER O OTHER NRNOT REPORTED 1 SO19V2LFC BUA26256 BETA ROD CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALFUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20081023 EA 2008 10 23 2008FA0000696 120080909G6120B30012 BETA RING DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL PROPELLER BROKEN B LU4RO OTHER O OTHER NRNOT REPORTED 1 SO19V2LFC BUA26256 BETA RING CRACKED, BROKEN. PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALFUNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR. (K) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20081023 SO 2008 10 23 2008FA0000697 220080930G7414 SPRING CIRRUSSR SR20 05628AJGL CONT O360 IO360ES SO IMPULSE COUPLINGBROKEN D O OTHER O OTHER TXTAXI/GRND HDL 1 GL21622CP4 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 WOULD NOT STAY RUNNING. ACFT WAS BROUGHT IN FOR MAINT AND IT WAS DISCOVERED THAT THE MAGNETO IMPULSE COUPLING SPRING WAS BROKEN IN THE LEFT MAGNETO. THE LT MAGNETO WAS REMOVED AND REPLACED, GROUND RUN CHECK WAS GOOD, AND ACFT WAS RETURNED TO SERVICE. (K) 1L71 3O3 ONTA00009CHE1CE 20081030 NM 2008 10 30 2008FA0000698 120081019G3510 VALVE BOEING767 7673CB 1385187NM OXYGEN BOTTLE OUT OF ADJUST B O OTHER W INADEQUATE Q C ININSP/MAINT 1 NM01592HA 33468 AIR NEW ZEALAND FAA REPAIR STATION ANZY 188C AKL - FLT NZ707 - DURING PRE-FLIGHT, TECH CREW NOTED THAT CREW OXY PRESSURE 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 NOT SAFETY WIRED. BOTTLE VALVE SUBSEQUENTLY FULLY OPENED AND COPPER WIRED IN POSITION AS REQUIRED. CREW OXYGEN CHECKS NOW NORMAL WITH NO NOTICEABLE DROP IN PRESSURE ON EICAS. AIR NEW ZEALAND MAINTENANCE QUALITY RISK AND SAFETY (MQRS) SAFETY INVESTIGATION GROUP HAS RAISED THE FOLLOWING AIR NEW ZEALAND INVESTIGATION (08/SI/135). 2L72 4F RTA1NM 20081027 CE 2008 10 27 2008FA0000699 120081010G531350440012319 STRINGER BEECH 90 C90 1152913CE PWA PT6 PT6* 52043EA FS 298 CRACKED D O OTHER O OTHER NRNOT REPORTED 1 CE01902XP5781 LJ1136 REAR PRESSURE BULKHEAD, FS 298.00, ON RT SIDE. STRINGER NR 9 WAS FOUND CRACKED ON THE AFT SIDE OF THE REAR PRESSURE BULKHEAD AT THE POINT WHERE THE ZEE STIFFENER IS ATTACHED TO THE STRINGER WITH (6) RIVETS. (K) 1L72 3T3 T 3A20 E2NE 20081027 NE 2008 10 27 2008FA0000700 320080718G61116607132886 BLADE ROTOL R389 R3894123F25 NE PROPELLER CRACKED B MS1RK NONE O OTHER ININSP/MAINT 1 EA27 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 CP30NE 20081027 2008 10 27 2008FA0000701 420081006G22104006719910 SERVO MTSBSIMU2 MU2B60 5780460CE GARRTTTPE331TPE331* 01514WP YAW DAMPENER CONTAMINATED D K NONE O OTHER ININSP/MAINT 1 NM07544CB 46 1536SA 8/11/08 INSTALLED YAW DAMPENER. 10/06/08 - CUSTOMER COMPLAINT OF INDUCED YAW WHEN ENGAGING AUTO PILOT. REMOVED YAW DAMPENER AND FOUND UNIT CONTAMINATED WITH WATER. UNIT IS MOUNTED WITH DRIVE SHAFT UP AND WITH NO DRAIN, THIS PROVIDES FOR WATER TO BE TRAPPED IN THE SERVO. RECOMMEND SEALING THE UNIT BETTER OR PROVIDING DRAINS FOR UNIT. (K) 1H72 3T3 TRTA10SW E2WE 20081027 SO 2008 10 27 2008FA0000702 120081016G32106569100 TORQUE LINK PIPER J3 J3C65 7100510SO MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 EA23701275440 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) 1H71 3O A691 20081027 CE 2008 10 27 2008FA0000703 120081002G2730NAS428420 BOLT BEECH 200 200BEECH 1152920CE ELEVATOR CONTROLOUT OF ADJUST B ML2RK NONE O OTHER ININSP/MAINT 1 GL11124EK 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 NOT PROVIDING A STOP FOR THE BALLAST. IN THIS CONDITION, THE POSSIBILITY EXISTS FOR THE INTERCONNECT LINK BETWEEN THE BALLAST WEIGHT BELLCRANK AND THE CONTROL COLUMN BRACKET TO TRAVEL PAST AN OVERCENTER CONFIGURATION AND MAY PREVENT PROPER CONTROL OF THE ELEVATOR SYSTEM IF THE ELEVATOR PRIMARY OR SECONDARY STOPS FAIL OR ARE ADJUSTED INCORRECTLY. THE PHASE INSPECTION BEING CONDUCTED IS THE INITIAL INSPECTION ON THE AC, AND LOG RESEARCH DID NOT REVEAL ANY PRIOR MAINTENANCE ON THE ELEVATOR CONTROL SYSTEM RIGGING. (K) 1L72 4T A24CE 20081030 NM 2008 10 30 2008FA0000704 120081024G57119252502 SPAR CAP LKHEEDP3A P3A 5260103NM RT WING FRACTURED B K NONE K FLUID LOSS ININSP/MAINT 1 WP00921AU168421465 151385 DURING INSPECTION TO DETERMINE THE SOURCE OF A FUEL LEAK A FRACTURE WAS FOUND IN THE LOWER FORWARD RIGHT SPAR CAP AT WING 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 VERTICAL FLANGE SEVERING THE FLANGE. A THIRD FRACTURE WAS APPRECIATED AT WS 71R IN THE SPAR WEB. THE CRACK APPEARS TO START AT A HI-LOK PIN HOLE AT THE LOWER CAP AND PROPAGATES APPROXIMATELY THREE INCHES VERTICAL WITH SOME INBOARD TRACK. 2L74 4T RTA32NM 20081027 CE 2008 10 27 2008FA0000705 120080929G29106317003136 LINE CESSNA525 525 2076601CE HYDRAULIC SYS RUPTURED B EWCRO OTHER O OTHER NRNOT REPORTED 1 EA3944CK 5250401 RUPTURE OF TUBE AT SIDE WHERE BENDING DIES LEFT MARKING, BOTH ABOVE AND BELOW OPENING. AFTER TAKEOFF, LOW FLUID AND PRESSURE WARNING LIGHTS CAME ON AND ACFT RETURNED TO DEPARTURE. ACFT WAS TURNED OVER TO REPAIR STATION. LEAK WAS LOCATED AND LINE REPLACED ALONG WITH BOTH HYDRAULIC PUMPS. (K) 1L72 4F RTA1WI 20081027 SO 2008 10 27 2008FA0000706 120081014G324616109302 WHEEL PIPER PA32 PA32R300 7103213SO MLG CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SW151228H 32R7780146 WHEEL FOUND CRACKED, INNER HALF APPROX 2 INCH LONG. (K) 1L71 3O A3SO 20081031 SO 2008 10 31 2008FA0000707 120081026G57129560401 SPAR CAP PIPER PA34 PA34200 7103405SO RT WING CORRODED D K NONE W INADEQUATE Q C ININSP/MAINT 1 SO05142584695 347350180 DURING ANNUAL INSPECTION, SEVERE INNER GRANULAR CORROSION WAS FOUND IN THE RIGHT WING, MAIN UPPER SPAR CAP AT THE AFT PORTION 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. 1L72 3O A7SO 20081028 CE 2008 10 28 2008FA0000708 120080924G3010 LINE CESSNA208 208B 2073701CE DE-ICE SYSTEM FROZEN D K NONE NL FALSE WARNING NO TEST ININSP/MAINT 1 SO03 DURING MX OPERATION OF DE-ICE BOOTS MINUTES AFTER ACFT RETURNED FROM FLT, OPERATION OF THE DEICE BOOTS PRODUCED NORMAL COCKPIT INDICATION (GREEN PRESSURE LIGHT). NOTICED, THOUGH, THAT THE RT WING DEICE BOOTS DID NOT INFLATE DESPITE THE INFLATION INDICATION IN THE COCKPIT. FROZEN WATER WAS FOUND AT A BEND IN THE DEICE AIR SUPPLY DUCTING IN THE RT WING ROOT. THIS 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 CALIBRATED LEAK IN PNEUMATIC SUPPLY DUCTING IN THE FUSELAGE/ WING TO PREVENT THE ACCUMULATION OF WATER. (K) 1H71 3T A37CE 20081028 SO 2008 10 28 2008FA0000709 120081014G324616109302 WHEEL PIPER PA32 PA32R300 7103213SO LYC O540 TIO540* 41532EA MLG CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SW151228H 32R7780146 CLEVELAND WHEEL, HOLE FOUND CRACKED, INNER HALF APPROX 2 INCHES LONG. (K) 1L71 3O3 O A3SO E14EA 20081104 CE 2008 11 4 2008FA0000710 120081027G6120 TUBE BEECH 95 95B55 1152729CE NACELLE CHAFED D K NONE O OTHER ININSP/MAINT 1 CE03527T 4985 TC576 ALUMINUM TUBING TO PROP GOVERNOR FOUND CHAFED DUE TO TIE RAP RUBBING TUBE. FABRICATED NEW TUBE, INSTALLED AND LEAK CHECKED. 1L72 3O RT3A16 20081104 GL 2008 11 4 2008FA0000721 220081027G7260KHU17D31 RELAY CESSNA206 U206G 2073356CE ALLSN 250C 250C20 03013GL HARTZLHCC3Y HCC3YN GL ENGINE BAY INTERMITTENT B C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 GL19891LL4565 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 RELAY FOR THE CHIP DETECTORS. 1H71 3O3 U A4CE E4CE 5 CP25EA 20081104 EA 2008 11 4 2008FA0000722 220081029G7322105217 CARBURETOR CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL ENGINE DAMAGED D O OTHER E VIBRATION/BUFFET TOTAKEOFF 1 NM031401E247 247 17270986 L291176T WA44044 PILOT WAS MAKING 3RD TOUCH AND GO, ON CLIMBOUT ENGINE STARTED VIBRATING EXCESSIVELY, POWER WAS REDUCED AT PATTERN ALTITUDE, MIXTURE ADJUSTED, SWITCHED MAGNETO'S FROM R TO L WITH NO CHANGE IN THE VIBRATION. AIRCRAFT LANDED AND SUBSEQUENT OPERATION 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 LYCOMING. 1H71 3O3 ONT3A12 E274 5 NP910 20081104 NM 2008 11 4 2008FA0000723 120081029G57119252511 SPAR CAP LKHEEDP3A P3A 5260103NM RT WING CRACKED B K NONE O OTHER ININSP/MAINT 1 SW99921A 168421465 151385 DURING FURTHER EVALUATION FOLLOWING PREVIOUSLY REPORTED DAMAGE A SECOND CRACK WAS FOUND ON THE FORWARD LOWER CAP AT BUTTLINE 56R. THE CRACK WAS VISUALLY IDENTIFIED AND CONFIRMED WITH EDDY-CURRENT SURFACE SCAN. 2L74 4T RTA32NM 20081104 NM 2008 11 4 2008FA0000724 120081029G57119252502 SPAR CAP LKHEEDP3A P3A 5260103NM RT WING CRACKED B K NONE O OTHER ININSP/MAINT 1 SW99921A 168421465 151385 DURING FURTHER EVALUATION FOLLOWING PREVIOUSLY REPORTED DAMAGE A TERTIARY FRACTURE WAS FOUND ON THE FORWARD SPAR CAP, HORIZONTAL FLANGE, WING STA 143.5. THE FRACTURE WAS VISUALLY IDENTIFIED AND CONFIRMED WITH EDDY CURRENT. AN INTERNAL VISUAL EXAMINATION IDENTIFIED THE AFT HORIZONTAL FLANGE AND VERTICAL FLANGE HAD ALSO BEEN FRACTURED. THE AFT FLANGE IS FRACTURED APPROXIMATELY .750 INCHES, PROPAGATING AFT TOWARD THE FLANGE END. THE VERTICAL FLANGE FRACTURE PROPAGATED THROUGH THE FILLET RADIUS UP TO THE FIRST HORIZONTAL ROW OF HI-LOK PINS. THE FRACTURE LENGTH IS APPROXIMATELY ONE INCH. FRACTURES WERE CONFIRMED WITH EDDY-CURRENT SURFACE SCAN. 2L74 4T RTA32NM 20081104 SO 2008 11 4 2008FA0000725 120081029G57536232800162328000RIB PIPER PA28 PA28180 7102808SO TE FLAP CORRODED D K NONE O OTHER ININSP/MAINT 1 SW99 DURING ANNUAL INSPECTION FOUND ALL FLAPS, LEADING EDGE RIBS WERE SEVERELY CORRODED. DETECTION METHOD WAS TO TAKE THE FOREFINGER AND THUMB AND SQUEEZE LEADING EDGE AT THE RIB, GOT A CRUNCHING FEEL AND SOUND. 1L71 3O 2A13 20081104 CE 2008 11 4 2008FA0000726 120081016G212066151007 TUBE CESSNA560 560XL 2076702CE AC BAY CRACKED D K NONE O OTHER ININSP/MAINT 1 EA27 2331 5333 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 2L72 4F RTA22CE 20081104 2008 11 4 2008FA0000727 420081029G2210 AUTOPILOT SYS ECLIPSEA500 ECLIPSEEA5003350000SW COCKPIT UNKNOWN C A UNSCHED LANDING G MULTIPLE FAILURE CRCRUISE 1 SW99678P 191 FLIGHT FROM SDL TO TUL, DIVERT TO ABQ. AUTOPILOT DISENGAGED VIOLENTLY AT 410 AND YD OFF. REFER TO QRH RESET CB. AUTOPILOT BACK ON AT 390. 40 SECONDS LATER, AUTOPILOT AND YD DISENGAGED. UNABLE TO RESET CB. FL 370 AUTOPILOT BACK ON AND 30 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 ELECTED TO DIVERT TO ABQ. AIRCRAFT IS BEING WORKED ON AT FACTORY SERVICE CENTER. UNKNOWN CAUSE AT THIS TIME. 1L72 4J RTA00002AC 20081031 EU 2008 10 31 2008FA0000729 120080930G2120 UNKNOWN SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B 60037NE CABIN ODOR B QMLRA UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 NM03106LN 3251 SHORTLY AFTER TAKEOFF, PERSONNEL ONBOARD REPORTED A BURNING ODOR TO THE PILOT. ABORTED FLT AND RETURNED TO HELIPAD TO INVESTIGATE. MECH PERFORMED AN INSPECTION OF THE AIRFRAME, ENGINE, WIRING, HOSES AND THE BELTS OF ALL COMPONENTS. NO DEFECTS OR THE SOURCE OF A BURNING ODOR WAS FOUND. SUBSEQUENT CHECK FLIGHT WAS PERFORMED BY THE PILOT & MECHANIC TO INVESTIGATE FOR BURNING ODOR, NONE FOUND. THE ACFT WAS RETURNED TO SERVICE. (K) 1G71 3U3 U H9EU E00054EN 20081031 NE 2008 10 31 2008FA0000730 220080903G73212523631 BELLOWS PWA PT6 PT6A34AG 52053NE FCU DAMAGED B IG0RK NONE L NO TEST ININSP/MAINT 1 NM03 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 120081030G3210244110010 PIVOT ASSY CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA MCAULY2D34C B2D34C220 GL LT MLG SHEARED B A UNSCHED LANDING J WARNING INDICATION LDLANDING 1 GL005319V2532 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. 1H71 3O3 O 3A17 E286 5 CP7EA 20081104 CE 2008 11 4 2008FA0000732 120081016G212066151007 TUBE CESSNA560 560XL 2076702CE AC BAY CRACKED D K NONE O OTHER ININSP/MAINT 1 EA273 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 2L72 4F RTA22CE 20081104 SW 2008 11 4 2008FA0000733 120081030G3233B10006 COUPLING DUKES MOONEYM20 M20E 5870212SW LANDING GEAR FAILED G O OTHER O OTHER LDLANDING 1 WP09204WF3483 210021 DURING APPROACH FOR LANDING, THE PILOT WAS UNABLE TO GET THE LANDING GEAR TO EXTEND, EITHER NORMALLY OR USING THE EMERGENCY GEAR EXTENSION SYSTEM. A GEAR-UP LANDING WAS ACCOMPLISHED WITH ONLY MINOR DAMAGE AND NO INJURIES. SUBSEQUENT INVESTIGATION DETERMINED THAT THE COUPLING (P/N B100-06) BETWEEN THE LANDING GEAR MOTOR TRANSMISSION AND THE DRIVE ACTUATOR HAD BROKEN. THE COUPLING HAS NO REPLACEMENT REQUIREMENTS, BUT IS RECOGNIZED IN MOONEY SERVICE INSTRUCTION M20-89 AS A PART THAT COULD FAIL DUE TO AGE HARDENING AND DETERIORATION. THE AIRCRAFT OWNER WAS NOT AWARE OF THIS CONDITION. 1L71 3O 2A3 20081104 EA 2008 11 4 2008FA0000735 220080925G7414M3828 GEAR SLICK CESSNA182 182T 2072703CE LYC O540 IO540AB1A5 EA MAGNETO DAMAGED B Z08RK NONE O OTHER ININSP/MAINT 1 CE07658PW 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) 1H71 3O3 ONT3A13 1E4 20081104 2008 11 4 2008FA0000737 220080905G7200 ENGINE AMD FALC20FALCON200 2730150EU FOD B UO2RA UNSCHED LANDING CJ F.O.D. WARNING INDICATION CLCLIMB 1 GL1969EC 498 AFTER TAKEOFF, OVERSPEED WARNING LIGHT ILLUMINATED. RPM REDUCTION USING PROP GOVERNOR CONTROL NOT SUCCESSFUL, USED THROTTLE CONTROL TO REDUCE ENGINE RPM. LANDED WITHOUT INCIDENT. REPAIR STATION INSPECTED AND DUPLICATED PROBLEM ON ENGINE GROUND 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 SUBSTANTIAL METAL SHAVING AND SMALL PIECES OF METAL AND (2) SMALL SILVER COLOR BALLS (SUSPECT BALL BEARING OF SOME SORT). THE ENGINE WAS REMOVED FOR TEAR DOWN INSP AND REPAIR. ENGINE TEAR DOWN REVEALED DESTRUCTION OF BOTH INTAKE AND EXHAUST LIFTER2L72 4F RTA7EU 20081104 2008 11 4 2008FA0000738 220080913G8500 ENGINE AMD FALC20FALCON200 2730150EU MAKING METAL B UO2RA UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL1969EC 498 AFTER TAKEOFF, OVERSPEED WARNING LIGHT ILLUMINATED. RPM REDUCTION USING PROP GOVERNOR CONTROL NOT SUCCESSFUL & USED THROTTLE 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). BECAUSE 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. ENGINE TEAR DOWN REVEALED DESTRUCTION OF BOTH INTAKE & EXHAUST LIFTER BODIES OF NR 1 CYLINDER & EXTENSIVE DAMAGE OF ENGINE. A2L72 4F RTA7EU 20081113 CE 2008 11 13 2008FA0000739 120081103G3710 ADAPTER CESSNA172 172M 2072418CE VACUUM SYS DAMAGED B K NONE O OTHER CRCRUISE 1 SW99308305902 17264138 AIRCRAFT HAD A FRESHLY OVERHAULED ENGINE INSTALLED AND WAS MAKING ITS FIRST FLIGHT. DURING CRUISE, IN VFR CONDITIONS, THE 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 VACUUM PUMP FOUND THAT THE SPLINED SHAFT HAD MELTED AWAY AND ITS PARTICLES WERE CAUGHT BETWEEN PUMP AND ADAPTER. MAINTENANCE NOTED THAT THE OIL DISTRIBUTION HOLES BETWEEN THE ADAPTER AND THE ENGINE WERE ALIGNED PROPERLY. NO IMMEDIATE CAUSE1H71 3O NT3A12 20081106 EA 2008 11 6 2008FA0000740 220081001G7414AB382585 CONTACT ROBSINR22 R22BETA 7640110NM LYC O360 O360J2A 41514EA MAGNETO DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 NM097087J 2873 CONTACT ASSY, AS A NEW ASSY OPENS BEYOND THE MAXIMUM .024 INCH. THIS IS A REOCCURRING PROBLEM WITH BOTH THE LT AND THE RT CONTACT ASSEMBLIES. CIRCUMSTANCES ARE WHEN THE POINTS ARE REPLACED. (K) 1G71 3O3 O H10WE E286 20081106 EU 2008 11 6 2008FA0000741 120081026G6322MS210436 NUT HUGHES369 369FF 4470709EU ALLSN 250C 250C30 03013GL BLOWER BACKED OUT D K NONE O OTHER ININSP/MAINT 1 WP195185G 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 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 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. 1G71 3U3 U H3WE E1GL 20081106 EA 2008 11 6 2008FA0000742 220080925G74144371 MAGNETO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE CONTAMINATED B Z08RK NONE O OTHER ININSP/MAINT 1 CE07452SM5 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 OF HOURS ON MAGNETOS. THIS IS CAUSING THE CARBON DUST TO COLLECT AND BUILDUP INSIDE MAGNETOS. (K) 1H71 3O3 ONT3A12 1E10 20081107 SW 2008 11 7 2008FA0000743 120080929G5541442283 SPAR GULSTM112 114 7630314SW RUDDER CRACKED D O OTHER O OTHER NRNOT REPORTED 1 EA654945W603 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 SAME FAILED CONDITION ON SN 14408. RECOMMEND THAT DOUBLER BE INSTALLED TO STRENGTHEN SPAR IN THIS AREA. (K) 1L71 3O A12SO 20081110 CE 2008 11 10 2008FA0000745 120080922G2820AN8156D CONNECTOR RAYTHNB300 B300RAYTHEON7150007CE RT AUX TANK DISCONNECTED C O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 SO15102FL 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) 2L72 4T RTA24CE 20081107 NE 2008 11 7 2008FA0000746 220081015G7314 PUMP BOEING727 727200 138407ENM PWA JT8 JT8D217C 52053NE FUEL SYS MALFUNCTIONED A I5PAA UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 WP13705AA 22462 726206U CRUISE NR 1 ENG STARTED TO SPOOL DOWN OTHER PARAMETERS ARE NORMAL, PERFORMED IN-FLIGHT START CHECKLIST SEVERAL TIMES INCLUDING 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 ENG 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 OPERATIONAL CHECK, OK. (K) 2L73 4F4 FRTA3WE E9NE 20081121 CE 2008 11 21 2008FA0000747 120081106G3520C3512000205 OXYGEN MASK CESSNA500 550 2076604CE CABIN TORN B K NONE O OTHER ININSP/MAINT 1 SW9943SA 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 ON THESE MASKS ARE THE 3RD QUARTER OF 1999, THE AD ONLY ADDRESSES MASKS WITH A CURE DATE FROM 3RD QUARTER 1993 TO 1ST QUARTER 1997. THESE TEARS COULD LEAD TO LEAKAGE AND POSSIBLE INSUFFICIENT OXYGEN DELIVERY AS DESCRIBED IN THE ORIGINAL A/D. 1L72 4F A22CE 20081110 2008 11 10 2008FA0000748 120081101G2810CB959 FUEL TANK DAMAGED B RYHRO OTHER O OTHER NRNOT REPORTED 1 NM03 FUEL TANKS WERE FOUND TO HAVE SIGNIFICANT LEAKS IN AN AREA NOT CLOSE TO ANY SEAMS, WELDS, OR BOSSES. THERE WERE NO VISIBLE 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 UNAIRWORTHY PENDING FURTHER TESTINGS AS A PRECAUTION. (K) 20081128 GL 2008 11 28 2008FA0000750 220081106G720044904 STIFFENER WILINT WILINTFJ44 FJ443A 66006GL LP TURBINE SEPARATED B K NONE O OTHER ININSP/MAINT 1 GL23 1858 AU00307 141224 WHILE UNDERGOING A CHECK 3 MAINT INSP DURING EARLY NOVEMBER 2008, THE STIFFENING RING ON THE 1ST LOW PRESSURE TURBINE NOZZLE 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 220081024G7414SS1001 BOOSTER SLICK HUGHES269 269C1 8059504SW LYC O360 HIO360G1A 41898EA ZONE 100 EXPLODED D EH ENGINE SHUTDOWN DEACTIVATE SYST/CIRCUITS BA SMOKE/FUMES/ODORS/SPARKS FLAME/FIRE TOTAKEOFF 1 SW412014T701 50 0313 L3373151A START MAGNETO, START BOOSTER BOX PN SS1001 BLEW THE TOP PORTION APART. IT CAUGHT ON FIRE AND SMOKE WENT EVERYWHERE. INSPECTED 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 REPLACED 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. 1G71 3O3 OO 4H12 1E10 20081125 CE 2008 11 25 2008FA0000752 120081103G3320CLE23602 LIGHT CESSNA560 560XL 2076702CE CABIN BURNED OUT C K NONE O OTHER ININSP/MAINT 1 SO13669TT714 5684 DURING POSTFLIGHT FOUND CABIN (LT) UPWASH, AND (RT) DOWNWASH LED LIGHT ELEMENTS INOP. INTIALLY TROUBLESHOOTING FOUND CIRCUIT 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 EXCESSIVE 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. DEFECTIVE PART WAS RETURNED TO MFG CPD. 2L72 4F RTA22CE 20081125 SO 2008 11 25 2008FA0000753 220081107G7414 IMPULSE COUPLING CONT O550 IO550N 17042SO MAGNETO INOPERATIVE D K NONE O OTHER ININSP/MAINT 1 GL15502BZ1021 D05KA054 917755 WHILE REMOVING MAGNETO FOR EXCHANGE FOUND IMPULSE COUPLING INOPERABLE. THIS IS THE SECOND LOW TIME MAGNETO OF THIS MODEL FOUND WITH A BAD IMPULSE COUPLING. 3 O E3SO 20081125 EA 2008 11 25 2008FA0000754 220081111G74144371 MAGNETO PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA ENGINE OUT OF POSITION D K NONE O OTHER ININSP/MAINT 1 GL039360C90 287890401 L2454636A EXCESSIVE TIMING DRIFT. BOTH MAGS SET 25 DEGREES BTDC ON NR1 CYLINDER. NEXT FIRING ORDER (NR 3 CYLINDER) IS OFF 6 DEGREES BETWEEN LT/RT MAG. NEXT FIRING ORDER (NR2 CYLINDER) IS NORMAL. LAST FIRING ORDER (NR4 CYLINDER) IS OFF 6 DEGREES BETWEEN 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. 1L71 3O3 O 2A13 E286 20081112 EU 2008 11 12 2008FA0000755 120080930G7603 JOINT PIAGIOP180 P180 6960204EU CONTROL CABLE DAMAGED C K NONE O OTHER ININSP/MAINT 1 SW9923RF 1080 RT ENGINE POWER CONTROL CABLES FREEZING AT ALTITUDE. INSPECTED CABLE AND FOUND THE STAINLESS STEEL SLEEVE DISCONNECTED AT JOINT TO FLEX SLEEVE. IT APPEARS TO BE A SILVER SOLDERED JOINT, AND SOLDER FAILED ALLOWING MOISTURE TO ENTER THE INTERNAL OF CABLE AND FREEZE WHICH COULD CAUSE LOSS OF MOTION OF THE CONTROL CABLES AND CAUSE FUEL CONTROL CABLES NOT TO ACHIEVE FULL TRAVEL, RESTRICTING ENGINE POWER. 1H72 3O RTA59EU 20081125 CE 2008 11 25 2008FA0000756 120081112G7120051313211 MOUNT CESSNA175 175 2072502CE ZONE 100 CRACKED G K NONE O OTHER ININSP/MAINT 1 GL23175UK 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. 1H71 3O NT3A17 20081112 SW 2008 11 12 2008FA0000757 120080718G5610 WINDOW ECLIPSEA500 ECLIPSEEA5003350000SW COCKPIT FAILED C O OTHER O OTHER NRNOT REPORTED 1 EA61136EA 000136 THERE WAS A POPPING NOISE COMING FRAOM THE VICINITY OF THE PILOTS WINDOW, WINDOW WAS REPLACED. 1L72 4J RTA00002AC 20081112 SW 2008 11 12 2008FA0000758 120080818G2621FX002002 EXTINGUISHER ECLIPSEA500 ECLIPSEEA5003350000SW RT NACELLE LEAKING C O OTHER K FLUID LOSS NRNOT REPORTED 1 EA61575CC 000075 RT ENGINE FIRE EXTINGUISHER CARTRIDGE LEAKED THROUGH DISCHARGE NOZZLE AND EXPOSED THE ENGINE AND COMPONENTS TO HIGHLY CORROSIVE CHEMICAL. ENGINE REMOVED FOR CLEAN UP AND REPAIR BY MANUFACTURER. 1L72 4J RTA00002AC 20081112 SW 2008 11 12 2008FA0000759 120080911G5340 RETAINER ECLIPSEA500 ECLIPSEEA5003350000SW COCKPIT WINDOW UNKNOWN C K NONE O OTHER ININSP/MAINT 1 EA61568EA 000168 A POPPING NOISE COMING FROM THE VICINITY OF THE CO PILOTS WINDOW. SIDE WINDOW RETAINERS WERE REPLACED. 1L72 4J RTA00002AC 20081125 SO 2008 11 25 2008FA0000760 220081112G8530AEC631397 CYLINDER CESSNA188 188B 2073007CE CONT O550 IO550D 17042SO MCAULYD3A34 D3A34C401 GL ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 CE0778417 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). 1L71 3O3 O A9CE E3SO 5 CP47GL 20081126 SO 2008 11 26 2008FA0000761 120081113G53477745405 SEAT TRACK PIPER PA38 PA38112 7103812SO ZONE 100 CRACKED D K NONE O OTHER ININSP/MAINT 1 NM092472D 3879A0327 PASSENGER SEAT WAS REMOVED FOR ANNUAL INSPECTION. UPON VISUAL INSPECTION OF SEAT RAILS, A CRACK WAS DISCOVERED GOING THROUGH THE ENTIRE RAIL. THE SEAT RAIL MUST BE REPLACED IN ORDER TO FACILITATE SAFE FLIGHT. 1L71 3O A18SO 20081118 CE 2008 11 18 2008FA0000762 120081020G2721S22952593 CHAIN CESSNA CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA RUDDER TRIM BROKEN B BGSRK NONE O OTHER ININSP/MAINT 1 EA21169EC288 172RG0515 L2843836A DURING A NON RELATED MAINTENANCE ACTION, THE MECHANIC NOTICED THE RUDDER TRIM WHEEL WAS MOVING WITH NO RESISTANCE. THE MECHANIC INSPECTED FURTHER AND FOUND THE CHAIN HAD SEPARATED AT ONE OF THE LINKS. AFTER CLOSER EXAMINATION IT HAS BEEN FOUND 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) 1H71 3O3 O 3A17 E286 20081118 CE 2008 11 18 2008FA0000763 120081008G2720717 SOLENOID VALVE BEECH 90 C90 1152913CE RUDDER STUCK B E81RO OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 GL03261GB5351 LJ1119 INVESTIGATED PILOT REPORT OF RUDDER BOOST CONSTANTLY KICKING TO LEFT. FOUND PN 717 LT SOLENOID VALVE STUCK IN OPEN POSITION. ALSO FOUND (3) PN AN9181D RUDDER BOOST CONTROL SYSTEM CROSS FITTING CRACKED AND WATER IN SYSTEM. PURGED WATER FROM 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) 1L72 3T 3A20 20081118 CE 2008 11 18 2008FA0000764 120081021G276021EN96 SWITCH BEECH MU300 400A 1155402CE SPEED BRAKE SYS CORRODED B E81RO OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 GL0348SE RK48 INVESTIGATED PILOT REPORT OF UNCOMMANDED "SPEEDBRAKE EXTENDED" ANNUNCIATOR LIGHT ILLUMINATION IN FLIGHT. FOUND HIGH RESISTANCE 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 WEAR AND/OR LONGTERM WATER/DIRT CONTAMINATION. RECOMMEND SIMILAR SWITCHES ON BE 400 SERIES AIRCRAFT BE REPLACED WITH IMPROVED SWITCHES WITH BETTER SEALING CAPABILITIES BY RECOMMENDED SERVICE BULLETIN OR SIMILAR. (K) 2H72 4F RTA16SW 20081118 2008 11 18 2008FA0000765 420081020G345713824120211 GPS SNIAS 350 AS350BA 8680817EU COCKPIT OVERHEATED B H0CRAH UNSCHED LANDING DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 WP0129FX 2085 DURING FLIGHT, THE TRIMBLE GPS OVERHEATED AND EMITTED SMOKE. THE PILOT MADE A PRECAUTIONARY LANDING AND SECURED POWER TO THE GPS BY REMOVING THE FUSE. THE UNIT HAD BEEN INSTALLED SINCE 1996. (K) 1G71 3U NCH9EU 20081124 GL 2008 11 24 2008FA0000766 120080808G2752EM41165 ACTUATOR AMTR LANCARLANCAIR320 056300AGL TE FLAP FAILED C TOWRO OTHER O OTHER NRNOT REPORTED 1 GL09320LA 269 MULTIPLE FLAP ACTUATION FAILURES. (K) 1L71 3O RTEXPA1L71 20081124 CE 2008 11 24 2008FA0000769 120081010G27101260505315 CONTROL CABLE CESSNA210 210N 2073453CE CONT O520 IO520* 17032SO TR AILERON WORN B TF2RK NONE O OTHER ININSP/MAINT 1 CE056523N3369 21063081 DURING ANNUAL INSP, THE RT AILERON RETURN CABLE WAS FOUND WORN BEYOND LIMITS BY THE WHITE PLASTIC PULLEY NEAR THE LEADING EDGE AT THE WING ROOT. (K) 1H71 3O3 O 3A21 E5CE 20081120 CE 2008 11 20 2008FA0000770 120081026G2720441921933 RUDDER PEDAL CESSNA680 680CE 2076811CE PWC PW306 PW306C 52169NE COCKPIT JAMMED B CNQRK NONE O OTHER DEDESCENT 1 CE01370QS 6800099 ON ACFT DEPARTURE, THE RUDDER PEDALS JAMMED ON THE COCKPIT SIDE PANELS ON THE TAKEOFF. AN EMERGENCY WAS DECLARED AND THE 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 (SERVICE CONDITION REPORT) HAS BEEN SUBMITTED TO ENGINEERING FOR REVIEW TO CHANGE SECURING METHOD FROM VELCRO TO A FASTENER TYPE INSTALLATION. (K) 2L72 4F4 FRCT00012WIE35NE 20081120 CE 2008 11 20 2008FA0000771 120081026G2720 RUDDER PEDAL CESSNA680 680CE 2076811CE PWC PW306 PW306C 52169NE COCKPIT JAMMED B CNQRO OTHER O OTHER DEDESCENT 1 CE07370QS 6800099 ON ACFT DEPARTURE, THE RUDDER PEDALS JAMMED ON THE COCKPIT SIDE PANELS ON THE TAKEOFF. AN EMERGENCY WAS DECLARED AND THE 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 (SERVICE CONDITION REPORT) HAS BEEN SUBMITTED TO ENGINEERING FOR REVIEW TO CHANGE SECURING METHOD FROM VELCRO TO A FASTENER TYPE INSTALLATION. (K) 2L72 4F4 FRCT00012WIE35NE 20081120 CE 2008 11 20 2008FA0000772 120081002G275067183281 CONTROLLER CESSNA750 750 2076810CE ALLSN AE3007AE3007C 03047GL TE FLAP FAILED B CNQRO OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 CE0778SL 7500238 FLAPS HARD FAILED DURING FLIGHT. FOUND THAT THE FLAP CONTROLLER HARD FAILED DURING COLD SOAKING. REPLACED FLAP CONTROLLER AND ACCOMPLISHED SATISFACTORY FLAP FUNCTIONAL CHECK WITH NO DEFECTS NOTED. RETURNED ACFT TO SERVICE. (K) 2L72 4J4 FRTT00007WITE6CH 20081120 SO 2008 11 20 2008FA0000773 220080929G853065315 CYLINDER CESSNA150 150L 2071826CE CONT O200 O200A 17020SO ENGINE CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SO155307Q1081 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 COMPLETE LOSS OF ENGINE POWER. (K) 1H71 3O3 O 3A19 E252 20081120 EU 2008 11 20 2008FA0000774 120081031G5210709010401101 TRIM TAB AGUSTAA109 A119 0261102EU PWA PT6 PT6B37A 52179NE MAIN ROTOR BLADEDELAMINATED D K NONE O OTHER ININSP/MAINT 1 EA17315PD 14035 PU0041 UPON POST FLIGHT IT WAS NOTICED THE MAIN ROTOR BLADE TRIM TAB WAS SERIOUSLY DELAMINATED AND SEPARATED IN FLIGHT. THIS PROBLEM 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 THIS PROBLEM AND STILL HAS NOT CORRECTED IT. PROBABLE CAUSE IS THE BONDING MATERIAL AND/OR THE BONDING PROCEDURE. (K) 1G71 3U4 U H7EU E4EA 20081120 EA 2008 11 20 2008FA0000775 220081027G7322383493 SERVO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 SO115339M2362 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) 1H71 3O3 ONT3A12 1E10 20081125 EA 2008 11 25 2008FA0000776 220081024G8530AEL75838 GUIDE BELL 47 47G4A 1181031SW LYC O540 VO540B1B3 41532EA NR 1 CYLINDER WORN G PFIGK NONE O OTHER ININSP/MAINT 1 GL1324HM 7688 L245043 DURING INVESTIGATION OF AN ACCIDENT IN WHICH ACFT LOST POWER AND WAS FORCED TO LAND THE FOLLOWING WAS DISCOVERED: COMPRESSION 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 OF A HIGH CHROME CONTENT NI-RESIST VALVE GUIDE. ECI VALVE GUIDE AEL 75838 WAS FOUND INSTALLED. THIS IS A NI-RESIST VALVE GUIDE. ECI VALVE GUIDE AEL 75838 WAS FOUND INSTALLED. THIS IS A NI-RESIST GUIDE. HOWEVER IT DOES NOT HAVE THE CHROM1G71 3O3 O 2H3 E304 20081120 CE 2008 11 20 2008FA0000777 120081024G2820 FUEL LINE CESSNA340 340A 2076405CE CONT O520 TSIO520* 17040SO FUEL SYSTEM CORRODED D O OTHER K FLUID LOSS NRNOT REPORTED 1 GL07340SU3808 340A0979 THE FUEL CROSSFEED LINE LT TANK TO RT ENGINE, HAD CORRODED TO THE POINT OF LEAKAGE. THE CORRODED AREA WAS UNDER THE CABIN FLOOR BEHIND THE CO-PILOT SEAT. THE DUCTWORK FOR THE CABIN VENTILATION SYSTEM LAYS ON THE LINE THIS LOCATION. THE CORROSION WAS LIMITED TO THE AREA OF CONTACT. PIN HOLES HAD DEVELOPED ALLOWING A SMALL QUANTITY OF FUEL TO LEAK, NOT ENOUGH 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) 1L72 3O3 O 3A25 E8CE 20081120 CE 2008 11 20 2008FA0000778 120081029G551165320104 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000779 120081029G551165320125 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000780 120081029G551165320124 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000781 120081029G551165320134 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000782 120081029G551165320144 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000783 120081029G551165320104 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000784 120081029G551165320114 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000785 120081029G551165320124 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000786 120081029G551165320135 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000787 120081029G551165320134 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000788 120081029G551165320145 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000789 120081029G551165320144 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000790 120081029G551165320154 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09371QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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 PARRALLEL TO THE EDGE OF THE RIBS. THE CRACKS WERE LOCATEDIN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000791 120081029G551165320104 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000792 120081029G551165320114 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HLES 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000793 120081029G551165320125 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000794 120081029G551165320124 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000795 120081029G551165320135 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000796 120081029G551165320134 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000797 120081029G551165320145 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000798 120081029G551165320154 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000799 120081029G551165320104 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000800 120081029G551165320114 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000801 120081029G551165320125 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000802 120081029G551165320124 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000803 120081029G551165320123 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000804 120081029G551165320135 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000805 120081029G551165320134 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000806 120081029G551165320133 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000807 120081029G551165320145 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000808 120081029G551165320144 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000809 120081029G551165320143 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000810 120081029G551165320163 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000811 120081029G551165320174 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09330QS 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 WERE FOUND. ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA. AFTER 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) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000812 120081029G551165320104 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000813 120081029G551165320125 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000814 120081029G551165320124 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000815 120081029G551165320135 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000816 120081029G551165320134 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000817 120081029G551165320145 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000818 120081029G551165320144 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000819 120081029G551165320154 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000820 120081029G551165320164 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000821 120081029G551165320193 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000822 120081029G551165320144 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000823 120081029G551165320114 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000824 120081029G551165320124 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000825 120081029G551165320124 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000826 120081029G551165320135 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000827 120081029G551165320134 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000828 120081029G551165320145 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000829 120081029G5511 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000830 120081029G551165320154 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000831 120081029G551165320164 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081120 CE 2008 11 20 2008FA0000832 120081029G551165320174 RIB CESSNA500 560CESSNA 2076750CE HORIZ STAB CRACKED B JQ0RK NONE O OTHER ININSP/MAINT 1 CE09363QS 5600536 WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB. AFTER 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 VERY LIMITED. (K) 2L72 4F RTA22CE 20081124 EA 2008 11 24 2008FA0000833 220081101G7414M3008 DISTRIBUTOR GEARSLICK CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA MAGNETO DESTROYED D DF2SK NONE O OTHER ININSP/MAINT 1 SW154260Q1186 04070369 17260160 CONTACT PIN ON THE DISTRIBUTOR GEAR COMES LOOSE AND IS UNUSEABLE. PLASTIC HOLDING IT ON IS CRACKED. (K) 1H71 3O3 ONT3A12 E274 20081126 GL 2008 11 26 2008FA0000834 220081106G725072165 TURBINE NOZZLE WILINTFJ44 FJ44 66000GL ENGINE SEPARATED D K NONE O OTHER ININSP/MAINT 1 GL09 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 PROBABLE CAUSE IS A SUSPECT MFG OPERATION. HELD FOR INVESTIGATION. (K) 4 F E3GL 20081125 GL 2008 11 25 2008FA0000835 220080930G731323031938 DIAPHRAGM ALLSN 250C 250C20B 03013GL NOZZLE CRACKED C HEFRK NONE O OTHER ININSP/MAINT 1 WP01 1568 CAT34079 FLOURESCENT PENTRANT INSPECTION PRODUCED INDICATIONS AT 2 LOCATIONS ALONG BRAZING WHERE DIAPHRAGM AND OUTER RING ARE JOINED. INDICATIONS ARE APPROXIMATELY 1.60 AND 2.50 INCHES LONG, APPROX 180 DEGREES APART. VOIDS IN BRAZING ARE ALSO PRESENT AT 2 LOCATIONS. (K) 3 U E4CE 20081125 CE 2008 11 25 2008FA0000836 120081120G2750 FLAP SYSTEM CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160CTM GL ZONE 600 FAILED C A UNSCHED LANDING J WARNING INDICATION APAPPROACH 1 SW99 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 RT FLAP INBD ROLLER SUPPORT JAMMED IN THE FLAP TRACK ASSY AND THE FLAP RETRACTED CROOKED AND JAMMED AGAINST THE RT AILERON LEAVING THE RT AILERON STUCK IN THE UP POSITION AND CAUSING AN ASYMMETRICAL FLAP CONDITION WHICH CAUSED THE AIRPLANE TO PULL TO THE RT. WITH FULL LT PRESSURE ON THE YOKE AND WITH RUDDER THE PILOT WAS ABLE TO CONTROL THE AIRPLANE. THE PILOT WAS ABLE TO TURN LT AND WITHOUT FURTHER INCIDENT FLY THE PATTERN AND LAND THE AIRPLANE SAFELY. 1H71 3O3 ONT3A12 E274 5 NP910 20081201 NM 2008 12 1 2008FA0000838 120081121G36107732873 PRECOOLER BOEING767 767222 1385122NM ZONE 400 FRACTURED B K NONE O OTHER ININSP/MAINT 1 EA39767VA7738777387 21870 NR1 PYLON PRECOOLER CRACKED IN SEVERAL PLACES. REMOVED AND REPLACED NR1 ENG PRECOOLER IAW MM 36-11-15. WORK PERFORMED ON NR 35501 S/O 599197. 2L72 4F RTA1NM 20081201 EU 2008 12 1 2008FA0000839 120081122G7700NE00000133101 SENSOR DIAMONDA42 DA42 2990004EU THIELTTAE125TAE1250299 EU CRANKSHAFT DIRTY D O OTHER R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 SW99490TS244 42AC090 020201763 FADEC CONTROLLED POWERPLANT/ HAD UNCOMMANDED POWER REDUCTION TO 75 PERCENT (3 SEPARATE WRITE-UPS) ACCOMPANIED BY MINOR ENGINE SURGING AT VARIOUS TIMES DURING NORMAL CRUISE FLIGHT. MFG FIX WAS RE-DESIGNED FADEC SOFTWARE, THAT DID NOT ALLEVIATE THE PROBLEM. WHILE PERFORMING A CLUTCH PLATE INSPECTION THE AREA WAS CLEANED AS WELL AS THE CRANKSHAFT POSITION SENSORS, 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. 1L72 3I3 BRTA57CE E00069EN 20081202 SW 2008 12 2 2008FA0000840 120081124G2400MS902982 GROUND STUD MOONEYM20 M20K 5870220SW CONT O360 TSIO360* 17025SO AIRFRAME MISINSTALLED D K NONE W INADEQUATE Q C ININSP/MAINT 1 SO13305P 2847 250524 AIRFRAME GROUND PLUG IN HAS NEVER BEEN CONNECTED TO AIRFRAME GROUND. BASE OF RECEPTACLE WAS INSULATED FROM AIRFRAME GROUND BY PRIMER ON METAL ANGLE. WE FOUND COMPLETE ISOLATION FROM GROUND POINT TO FUEL FILLER OPENING, NO GROUND ON OUR FUELING 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. 1L71 3O3 O 2A3 E9CE 20081202 GL 2008 12 2 2008FA0000841 120081124G5210 LATCH DIAMONDA40 DA40 2990002GL CONT IO360 IO360* 17025CE HARTZLHCC2Y HCC2YR1 GL PAX DOOR DISENGAGED P BA EMER. DESCENT UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 SW99661DS1050 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. BACK 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 DESIGN 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 AS LONG AS I COULD. IT FINALLY GOT INTO THE AIR SCREAM AND WAS JERKED OUT OF MY HAND AND THEN THE DOOR DEPARTED THE AIRCRAFT. DECLARED AN EMERGENCY AND LANDED. 1L71 3O3 ONTA47CE E1CE 5 CP920 20081202 SW 2008 12 2 2008FA0000842 120081124G2897 GROUND WIRE BELL 206 206B3 1181506SW BOOST PUMP MISSING D K NONE O OTHER ININSP/MAINT 1 WP28304PD6486 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. 1G71 3U H2SW 20081202 SO 2008 12 2 2008FA0000843 120081110G5414 COWLING PIPER PA32 PA32300 7103212SO LYC O540 IO540* 41532EA ZONE 400 BROKEN G A UNSCHED LANDING D INFLIGHT SEPARATION CLCLIMB 1 SO192772P6938 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 6905.8 HRS. OWNER STATED NO ADDITIONAL MAINT SINCE THAT TIME. 1L71 3O3 O A3SO 1E4 20081202 SW 2008 12 2 2008FA0000844 120081124G2897 GROUND WIRE BELL 206 206B3 1181506SW BOOST PUMP MISSING D K NONE O OTHER ININSP/MAINT 1 WP07305PD2853 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. 1G71 3U H2SW 20081202 SW 2008 12 2 2008FA0000845 120081124G2897 GROUND WIRE BELL 206 206B3 1181506SW BOOST PUMP MISSING D K NONE O OTHER ININSP/MAINT 1 WP07306PD 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. 1G71 3U H2SW 20081201 SW 2008 12 1 2008FA0000846 120081124G2897 GROUND WIRE BELL 206 206B3 1181506SW ALLSN 250C 250C20J 03013GL BOOST PUMP MISSING D K NONE J WARNING INDICATION ININSP/MAINT 1 WP07306PD1990 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. 1G71 3U3 U H2SW E4CE 20081202 CE 2008 12 2 2008FA0000847 120081125G8011S539800M015 SPRING BEECH 95 95B55 1152729CE CONT O470 IO470L 17026SO STARTER ADAPTER BROKEN G K NONE O OTHER ININSP/MAINT 1 SW135716V14 14 CAS2234 TC990 272745R STARTER ADAPTER P/N 635050-A4, STARTER SPRING FAILED. STARTER ADAPTER OVERHAULED, RETURNED TO SERVICE AFTER OVERHAUL. PART SOLD, STARTER ADAPTER INSPECTED AND RETAGGED AND SOLD TO MFG. MAINT INSTALLED STARTER ADAPTER AND SPRING FAILED 14 HOURS LATER. 1L72 3O3 ORT3A16 3E1 20081202 EA 2008 12 2 2008FA0000848 220081119G7310STD2048ORLW18733HOSE CESSNA182 182 2072702CE LYC O540 TIO540AK1A EA FUEL SYSTEM DETERIORATED D O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 NM0972758554 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 CONTAMINANTS 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 NOZZLE TUBES. WE INSTALLED NEW HOSES. PERHAPS HOSE P/N LW-18737 SHOULD BE REPLACED AT 500 HOUR INTERVALS. 1H71 3O3 ONT3A13 20081201 SW 2008 12 1 2008FA0000849 120081101G243530B4521A STARTER GEN NAMER T28C T28C 6402509SW ENGINE FAILED B XB2RK NONE O OTHER ININSP/MAINT 1 WP0139FS 624480 STARTER GEN PREVIOUSLY HAD A FIELD FAILURE-COMPLETE MELT DOWN AFTER APPROX 12 FLIGHTS AFTER OVERHAUL. IT WAS REPAIRED UNDER WARRANTY AND REINSTALLED. AFTER APPROX 4 FLIGHTS IT WOULD NOT CONSISTENTLY CARRY THE LOAD. ACFT REGULATION/CHARGING SYST CHECKED AND FOUND CORRECT. THE INSP COVER ON THE GENERATOR WAS REMOVED AND DAMAGE TO THE COMMUTATOR WAS FOUND PROBABLY DUE TO THE PREVIOUS FAILURE. INSP OF 1 SET OF BRUSHES REVEALED GROOVED FACES AND THE LACK OF PROPER BRUSH RUN AT OVERHAUL. AS STATED THIS IS 2ND FAILURE OF THIS ITEM IN A VERY SHORT TIME, THESE FAILURES ARE OBVIOUSLY DUE TO THE LACK OF PROPER PROCEDURES/ WORKMANSHIP BEING FOLLOWED. (K) 1L71 4R RTEXPA1L71 20081201 2008 12 1 2008FA0000850 420081024G2565 PIN BOEING767 767238 1385114NM PWA JT9 JT9D7R4D 52054NE EVAC SLIDE INSTALLED B M4QRK NONE L NO TEST ININSP/MAINT 1 SW19673BF43 23402 A SLIDE DEPLOYMENT OF THE RT AFT ENTRY DOOR OF THE ACFT WAS ATTEMPTED IN CONJUNCTION WITH A DITCHING DEMONSTRATION IN SUPPORT OF OUR FAR PART 125 CONFORMITY ASSESSMENT BY FSDO - 25. THE SLIDE DID NOT EXTRACT FROM THE DOOR BUSTLE AS THE DOOR 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 DOOR AND DROPPED PROPERLY, HOWEVER IT DID NOT INFLATE. THE IN-CABIN FA OPERATING THE DOOR ATTEMPTED TO MANUALLY INFLATE 2L72 4F4 FRTA1NM E3NE 20081210 CE 2008 12 10 2008FA0000851 120081023G326012707332 WARNING SYSTEM CESSNA210 210N 2073453CE LANDING GEAR MALFUNCTIONED B H DEACTIVATE SYST/CIRCUITS N FALSE WARNING CRCRUISE 1 SW996621A78 21063559 821099R WHILE FLYING THROUGH RAIN IN IFR CONDITIONS, THE LANDING GEAR NOT DOWN/LOCKED WARNING HORN SOUNDED FALSELY EVEN THOUGH THROTTLE WAS NOT RETARDED TO DESCENT CONFIGURATION. AIRCREW PULLED WARNING HORN CIRCUIT BREAKER TO TEMPORARILY CANCEL THE HORN WHICH ALSO DEACTIVATES THE NORMAL FUNCTION OF THE STALL/GEAR WARNING SYSTEM. THE HORN IS VERY LOUD INTERFERING WITH ATC COMMUNICATIONS DURING A CRITICAL PHASE OF FLIGHT. TROUBLESHOOTING REVEALED THE THROTTLE SWITCH INPUT ON THE DUAL WARNING UNIT IS HYPERSENSITIVE TO A HIGH RESISTANCE GROUND, I.E. MOISTURE ACCUMULATION AT THE THROTTLE SWITCH TERMINAL. 1H71 3O 3A21 20081210 SO 2008 12 10 2008FA0000852 220081129G8550ES48109 OIL FILTER CESSNA172 172A 2072404CE CONT O300 O300D 17022SO ENGINE RUPTURED P E ENGINE SHUTDOWN K FLUID LOSS TXTAXI/GRND HDL 1 SW997830T2 2 47430 ON 11/26/2008, APPROXIMATELY 1 MINUTE AFTER START-UP THE OIL FILTER RUPTURED RESULTING IN MASSIVE LOSS OF ENGINE OIL. THE OIL FILTER WAS THE LAST OF FOUR THAT WERE PURCHASED ON 10/05/2006. THE ENGINE WAS SHUT DOWN UPON NOTICE OF LOW OIL PRESSURE AND HAS BEEN DETERMINED TO BE UNHARMED BY THE LOCAL AP MECHANIC. 1H71 3O3 O 3A12 E253 20081210 CE 2008 12 10 2008FA0000853 120081130G2421ASG120001 ALTERNATOR CESSNA303 T303 2073820CE ENGINE SHORTED D HD DEACTIVATE SYST/CIRCUITSRETURN TO BLOCK BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TXTAXI/GRND HDL 1 SW99303ET149 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 DISCOVERY 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. 1L72 3O A34CE 20081219 GL 2008 12 19 2008FA0000854 220081201G720023038229 SPUR GEAR BELL 206 OH58A 1181579SW ALLSN 250C 250C20C 03013GL ENGINE BROKEN B K NONE O OTHER ININSP/MAINT 1 SW99306HP 7120794 AE405466 GAS PRODUCER TRAIN IDLER SPUR GEARSHAFT PN: 23038229. SHEARED IN HALF, PRODUCING METAL IN OIL. WHEN TECHNICIAN DISASSEMBLED GEARBOX FOUND THAT GEARSHAFT WAS THE SOURCE OF THE METAL 1G71 3U3 U H2SW E4CE 20081219 2008 12 19 2008FA0000855 220081201G721023038229 SPUR GEAR BELL 206 OH58A 1181579SW GEARBOX SHEARED B K NONE O OTHER ININSP/MAINT 1 SW99306HP1954 162 7120794 GAS PRODUCER TRAIN IDLER SPUR GEARSHAFT PN: 23038229. SHEARED IN HALF, PRODUCING METAL IN OIL. WHEN TECHNICIAN DISASSEMBLED GEARBOX FOUND THAT GEARSHAFT WAS THE SOURCE OF THE METAL 1G71 3U H2SW 20081202 CE 2008 12 2 2008FA0000856 120081124G3230SM50D7 RELAY BEECH 33 F33A 1151425CE LANDING GEAR INTERMITTENT B VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP078252T184 CE1545 PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE UP POSITION. THE GEAR FAILED TO RETRACT, 3-4 MINUTES LATER THE PILOT 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) 1L71 3O 3A15 20081203 EA 2008 12 3 2008FA0000857 220080314G7414 SHAFT PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA MAGNETO BROKEN B ZF7RO OTHER O OTHER NRNOT REPORTED 1 WP079126M110 07071657 2816104 RL1306439A ROTATING MAGNET SHAFT BROKE IN HALF. BROKE DIRECTLY BELOW WHERE THE ROTOR CAM GOES. (K) 1L71 3O3 O 2A13 E274 20081202 GL 2008 12 2 2008FA0000858 220081118G7412106149504 EXCITER BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL POWERPLANT INTERMITTENT B BJFRO OTHER O OTHER TXTAXI/GRND HDL 1 EA23739NM 51124 ENGINE HAD AN INTERMITTENT DELAYED LIGHTOFF CAUSING HOT STARTS. REPLACING THE IGNITION EXCITER CORRECTED THE PROBLEM. THE 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) 1G71 3U3 U H2SW E1GL 20081202 CE 2008 12 2 2008FA0000859 120081113G3211 SUPPORT CESSNA414 414A 2075907CE TRUNNION CRACKED B E5WRK NONE O OTHER ININSP/MAINT 1 GL21901BA6946 414A0232 ON THE FWD TRUNNION SUPPORT, A CRACK WAS LOCATED ON THE LT AND RT SIDES. EDDY CURRENT INSP USED. (K) 1L72 3O A7CE 20081203 SO 2008 12 3 2008FA0000860 120081118G324016405700 BRAKE DISC PIPER PA23 PA23250 7102308SO RT MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 GL0963954238 277854085 THE DISC WAS FOUND DURING ROUTINE MAINTENANCE TO HAVE A RADIAL CRACK EXTENDING FROM APPROX .5 INCH FROM THE OUTER CIRCUMFERENCE TO OUTER EDGE AND ABOUT HALF WAY THROUGH THE THICKNESS OF THE DISK. (K) 1L72 3O 1A10 20081203 GL 2008 12 3 2008FA0000861 120081117G801114924LS STARTER DIAMONDA40 DA40 2990002GL LYC O360 IO360M1A NE ENGINE BROKEN D O OTHER O OTHER NRNOT REPORTED 1 SW03203US 40903 L3393551E STARTER HOUSING BROKE AT FRONT CASTING BREAKING OFF FRONT MOTOR SHAFT SUPPORT BEARING WHICH ALLOWED STARTER SHAFT TO DROP DOWN PREVENTING POSITIVE ENGAGEMENT OF STARTER TO FLY WHEEL. CONVERSATION WITH AIRCRAFT MFG NOTED THIS IS NOT AN ISOLATED INCIDENT AND THERE ARE DEFECTS IN THE FRONT CASTINGS. (K) 1L71 3O3 ONTA47CE 1E10 20081202 CE 2008 12 2 2008FA0000862 120081114G574310112002584 BRACKET BEECH 200 200BEECH 1152920CE PWA PT6 PT6* 52043EA RT MLG SUPPORT CRACKED C K NONE O OTHER ININSP/MAINT 1 EA2740R BC07 A 1.4 INCH LONG CRACK WAS FOUND IN THE RT MLG DRAG BRACE SUPPORT BRACKET DURING INSPECTION. DURING THE REMOVAL OF THE PART (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) 1L72 4T3 T A24CE E2NE 20081203 EA 2008 12 3 2008FA0000863 120081110G6320269A510351 PINION GEAR SCWZER269 269D 8059501EA ALLSN 250C 250C20W NE TRANSMISSION WORN D BS2RO OTHER O OTHER NRNOT REPORTED 1 SW17297BJ S0005 0029 CAE845042 DURING SHUT-DOWN, PILOTS REPORTED CLUNKING NOISE. UPON FURTHER INSPECTION, NOISE WAS LOCATED AT UPPER PULLEY SPRAG CLUTCH AREA. REMOVED UPPER PULLEY AND FOUND M/R TRANSMISSION INPUT PINION (PN:269A5103-51) WORN EXCESSIVELY DUE TO LOOSE AFT 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 PROCEDURE. (K) 1G71 3U3 U0 4H12 E4CE 20081203 CE 2008 12 3 2008FA0000864 120081108G323315232003 ACTUATOR CESSNA500 560CESSNA 2076750CE NLG LEAKING B FZPRK NONE O OTHER ININSP/MAINT 1 NM1145KB 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. TROUBLESHOOTING REVEALED THAT THE NOSE GEAR ACTUATOR WAS LEAKING INTERNALLY, FILLING THE NITROGEN EMERGENCY EXTENSION SYSTEM 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 HAD2L72 4F RTA22CE 20081203 CE 2008 12 3 2008FA0000865 120080920G6220368200119 ROD BEECH 33 F33A 1151425CE NOSE GEAR BENT D K NONE O OTHER ININSP/MAINT 1 EA056431X2333 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 GEAR ROD END CAN BE ACCESSED IN WHEEL WELL AFT RT SIDE ATTACHED TO KEEL UNDER SHIELD. THIS IS A GOOD PLACE TO LOOK AT HARD LANDINGS AND DURING ANNUAL INSPECTIONS. PILOT INTERVIEWED AND SAID HE DID NOT HAVE HARD LANDING OR PORPOISE ACFT. PN OF ROD IS 36-820011-9, PN FOR ROD END IS ANDE5-323. (K) 1L71 3O 3A15 20081203 CE 2008 12 3 2008FA0000866 120081117G712026510088 MOUNT CESSNA208 208B 2073701CE PWA PT6 PT6A114 52043NE ENGINE CRACKED B MT9RO OTHER O OTHER NRNOT REPORTED 1 SW059750B12988 208B0100 PCE17240 THE CENTER ENGINE MOUNT BRACKET WAS FOUND TO HAVE CRACKS INSIDE THE ASSY AT THE TERMINATION END OF BOTH WELDS. (K) 1H71 3T3 T A37CE E4EA 20081202 CE 2008 12 2 2008FA0000867 120081117G712026510127 MOUNT CESSNA208 208B 2073701CE PWA PT6 PT6A114 52043NE LT ENGINE CRACKED B MT9RO OTHER O OTHER NRNOT REPORTED 1 SW059750B 208B0100 THE LT ENGINE MOUNT BRACKET WAS FOUND TO HAVE CRACKS INSIDE THE ASSY AT THE TERMINATION END OF BOTH WELDS. (K) 1H71 3T3 T A37CE E4EA 20081202 SO 2008 12 2 2008FA0000868 120081121G534067271800 BRACKET PIPER PA28 PA28R201 7102816SO NLG ACTUATOR CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SW994142N16129 2837012 NOSE GEAR ACTUATOR AFT ATTACH POINT CRACKED. PROBABLE CAUSE IS TIME IN SERVICE. CHANGE AT A REASONABLE TIME. (K) 1L71 3O 2A13 20081202 SO 2008 12 2 2008FA0000869 120081029G534067271800 BRACKET PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA NLG ACTUATOR CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SW994155G 2837017 NOSE GEAR ACTUATOR AFT ATTACH POINT CRACKED. PROBABLE CAUSE IS TIME IN SERVICE. CHANGE AT A REASONABLE TIME. (K) 1L71 3O3 O 2A13 1E10 20081203 2008 12 3 2008FA0000870 120081028G8011774960A4 STARTER ENGINE MISMANUFACTURED D SI3RO OTHER W INADEQUATE Q C NRNOT REPORTED 1 EA63 425 FOUND BAFFLES INSTALLED INCORRECTLY, INCORRECT HOUSING INSTALLED AND VARIOUS INTERNAL PARTS. (K) 20081203 CE 2008 12 3 2008FA0000871 120081101G5100 SPAR BEECH 18 H18 1151012CE PWA R985 R985* 52008NE UNKNOWN CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SW076GJ 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) 1L72 3R3 R A765 5E1 20081202 EA 2008 12 2 2008FA0000874 220081118G7414M3820 DISTRIBUTOR PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA MAGNETO DAMAGED B O OTHER O OTHER NRNOT REPORTED 1 SW9963954881 277854085 SUBJECT PART APPEARS TO HAVE NOT RETAINED ITS LOWER BEARING THAT SUPPORTS THE DISTRIBUTOR GEAR. THE PART WAS FOUND TO BE 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) 1L72 3O3 O 1A10 1E4 20081203 SO 2008 12 3 2008FA0000875 120081118G324016405700 BRAKE DISC PIPER PA23 PA23250 7102308SO MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 SW9963954277 277854085 THE DISC WAS FOUND DURING ROUTINE MAINTENANCE TO HAVE A RADIAL CRACK EXTENDING FROM APPROX .75 INCH FROM THE OUTER CIRCUMFERENCE TO OUTER EDGE AND ABOUT HALF WAY THROUGH THE THICKNESS OF THE DISC. (K) 1L72 3O 1A10 20081202 CE 2008 12 2 2008FA0000876 120081117G32406364106 BRAKE CABLE CESSNA525 525B 2076616CE LT BRAKE FAILED B JVGRK NONE O OTHER ININSP/MAINT 1 CE0992MA 525B0048 LET ACFT SIT OVER NIGHT WITH PARKING BRAKE APPLIED AND FOUND BRAKE SYS TO STILL HAVE 700 PSI IN BRAKE SYS. RELEASED PARKING BRAKE AND FOUND THAT THE LT BRAKE STILL HAD 160 PSI RESIDUAL PRESSURE AND RT SIDE HAD ZERO RESIDUAL PRESSURE. VERIFIED RT WHEEL ASSY WOULD ROTATE, CHECK LT SIDE AND LT WHEEL ASSY WOULD NOT ROTATE. INSPECTED INSIDE PORTION OF BRAKE METERING VALVE IN CABIN AND NOTICED THAT THE LT ACTUATION CABLE CLEVIS END COULD GET HOOKED ON EDGE OF CABLE BALL END. WHEN THAT HAPPENS 160 PSI REMAINS ON LT BRAKE. WHEN CABLE IS POSITIONED PROPERLY LT BRAKE HAS NO RESIDUAL PRESSURE ON GAUGE AND LT WHEEL ROTATES. OBTAINED NEW AFT BRAKE CABLES FROM MFG AND MODIFIED IAW ENGINEERING CO NR 525-1495. REMOVED O1L72 4F RTA1WI 20081203 2008 12 3 2008FA0000877 420081120G2360 GROUND STUD CESSNA510 510 2076617CE PWC PW615 PW615FA 52282NE RT WING LOOSE B JGVRK NONE O OTHER ININSP/MAINT 1 CE09551WH 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 632DB WAS REMOVED AND UPON FURTHER INSP THE PARTS WERE FOUND FLOATING AROUND INSIDE THIS AY WHICH ALSO HOUSES THE AILERON CONTROL SECTOR. SOME TYPE OF SAFETY SHOULD BE INCLUDED ON GROUNDING JACK TO PREVENT IT FROM COMING APART AND POTENTIALLY JAMMING THE AILERON. (K) 1L72 4F4 FRTA00014WIE00073EN 20081217 SW 2008 12 17 2008FA0000878 120081127G3220 TUBE MOONEYM20 M20F 5870214SW NLG BROKEN G A UNSCHED LANDING O OTHER CLCLIMB 1 SO116829V3000 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 DIFFERENTLY". HE CONTINUED TO ACCELERATE BRIEFLY AND THEN DECIDED TO ABORT THE TAKE-OFF. INCIDENT INVESTIGATION FOUND ACFT ON ITS NOSE WITH THE NOSE LANDING GEAR FOLDED BACK UNDERNEATH THE ACFT. INSPECTION REVEALED THAT THE TUBING OF THE NLG LEG ASSEMBLY WAS BROKEN. THERE WERE POSSIBLE STRESS FRACTURES AT THE WELS POINTS ON BOTH SIDES OF THE STRUCTURE. 1L71 3O 2A3 20090107 SW 2009 1 7 2008FA0000879 120081127G3220540004501 LEG ASSY MOONEYM20 M20F 5870214SW NLG BROKEN D C ABORTED TAKEOFF O OTHER TOTAKEOFF 1 SO11V68293000 220012 PILOT STATED THAT HE HEARD A LOUD NOISE DURING TAKE-OFF AND THAT THE AIRCRAFT BEGAN TO "HANDLE DIFFERENTLY." HE CONTINUED TO ACCELERATE BRIEFLY, LIFTED OFF AND THEN DECIDED TO ABORT THE TAKEOFF. THE ACFT CAME TO REST ON ITS NOSE WITH THE NOSE L/G FOLDED BACK BENEATH THE ACFT. INSP OF THE NOSE GEAR REVEALED THAT THE NLG LEG TUBING HAD BROKEN AT THE WELD POINTS ON THE UPPER ENDS OF THE TUBING. CLOSER INVESTIGATION SHOWED POSSIBLE FATIGUE CRACKS AT THE FWD PORTION OF THE WELDED JOINTS. 1L71 3O 2A3 20090106 GL 2009 1 6 2008FA0000880 120081122G793112635002 SENSOR CIRRUSSR SR20 05628AJGL CONT IO360 IO360* 17025CE OIL SYSTEM DEFECTIVE G O OTHER N FALSE WARNING APAPPROACH 1 SO19212LV678 678 1547 360009 SENSOR PRODUCED A FALSE HIGH OIL PRESSURE INDICATION DURING ACFT APPROACH TO AIRPORT. PROBABLE CAUSE WAS INTERNAL FAILURE, RECOMMENDATIONS TO PREVENT RECURRENCE ARE UNAVAILABLE, AS THE FREQUENCY OF THIS TYPE OF OCCURRENCE HAS BEEN VERY LOW. 1L71 3O3 ONTA00009CHE1CE 20090106 SO 2009 1 6 2008FA0000881 220081209G74144310 MAGNETO DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO LEFT FAILED B K NONE O OTHER ININSP/MAINT 1 WP23293DC22 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. 1L71 3O3 ONTTA4CH E7SO 20090107 SW 2009 1 7 2008FA0000882 120081209G2710473501 BELLCRANK GULSTM112 112A 7630302SW ZONE 500 MISREPAIRED D K NONE O OTHER ININSP/MAINT 1 WP191420J1560 1560 420 EXCESSIVE AILERONS T/E FREE PLAY. SUSPECTED AIL SYS CUMULATIVE WEAR. UPON FURTHER CLOSE VISUAL INSP, FOUND AILERONS BELLCRANK 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 WORN AND REINSTALLED/SECURED SAME WITH SOLID AD RIVETS. COMMANDER IPC PAGE 2-195 ITEMS 25, 27 BELLCRANK ASSY PIVOT BEARIN1L71 3O A12SO 20090107 EA 2009 1 7 2008FA0000884 220081210G7322229164 DISCHARGE TUBE CESSNA172 172P 2072436CE LYC O320 O320* 41508EA FUEL PUMP LOOSE D K NONE O OTHER ININSP/MAINT 1 SW9964204669 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 THE PUMP DISCHARGE TUBE MISSING AND FOUND AT THE BOTTOM OF THE CARB AIRBOX. 1H71 3O3 ONT3A12 E274 20090107 CE 2009 1 7 2008FA0000885 120081211G325066426438 JAM-NUT CESSNA560 560XL 2076702CE STEERING BUNGEE LOOSE D K NONE O OTHER CRCRUISE 1 SO13669TT740 560XL5684 DURING ALL FLIGHT REGIMES (CLIMB/CRUISE/DESCENT) CREW FELT RESISTANCE WHEN LT RUDDER PEDAL WAS DEPRESSED. NO CHANGE IN FEEL WITH LANDING GEAR POSITION (UP OR DOWN). ON GROUND RESISTANCE COULD NOT BE FELT, HOWEVER ACFT WOULD PULL LT WHILE TAXIING. INITIAL FINDINGS REVEALED THE JAM NUT ON THE NOSE STEERING BUNGEE ASSY HAD BACKED OFF AND THE CLEVIS END OF THE BUNGEE 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 DU2L72 4F RTA22CE 20090106 NE 2009 1 6 2008FA0000886 220081111G8530 CYLINDER PIPER PA31 PA31310 7103103SO LYC O540 TIO540J2B NE HARTZLHCC2Y HCC2Y* GL ENGINE SEPARATED D K NONE RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CRCRUISE 1 EA09801JK 787 318012014 L528061A FH998 PILOT NOTED REDUCTION OF PWR, THEN VIBRATION IN CRUISE FLIGHT. VISUAL INSP REVEALED NR1 CYL INTAKE TUBE SEPARATED FROM SUMP INLET AND WEDGED APPROX 1 INCH AFT OF INLET. FUEL INJECTOR LINE BROKE AT INJECTOR. BOTTOM (2) CYL HOLD DOWN STUDS BROKE AND (1) BOTTOM, (1) TOP HOLD DOWN NUTS BACKED OFF. SUSPECT CYL HEAD SEPARATION. 1L71 3O3 ORTA20SO E14EA 5 CP920 20081217 2008 12 17 2008FA0000887 420081028G2211GFC700 AUTOPILOT SYS CESSNA510 510 2076617CE MALFUNCTIONED P H DEACTIVATE SYST/CIRCUITS O OTHER APAPPROACH 1 SW99510AZ20 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 COURSE. 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 AUTO-SET COURSE TO 120. THE PILOT CAN TURN THE NEEDLE TO THE CORRECT COURSE OF 300, AND THE HSI WILL PROVIDE CORRECT SENSING. AUTOPILOT WILL NOT CAPTURE THAT COURSE & WILL FLY RIGHT THROUGH LOCALIZER TOWARD TERRAIN. MANUFACTURERS AND FAA/N1L72 4F RTA00014WI 20081219 CE 2008 12 19 2008FA0000888 120081215G2751DT2RA7 SWITCH BEECH 90 C90 1152913CE TE FLAPS BENT B O OTHER O OTHER TXTAXI/GRND HDL 1 SW99964G 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 WAS 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 RELATED TO ICE OR FOD DEBRIS. 1L72 3T 3A20 20081230 EU 2008 12 30 2008FA0000889 120081119G65204639306038 PINION GEAR BOLKMS105 BO105LSA3 5626020EU TAIL ROTOR DRIVEDEFORMED W ZF6YK NONE O OTHER ININSP/MAINT 1 EA33315LS 2033 THE MAIN TRANSMISSION WAS DELIVERED FOR OVERHAUL. THERE WAS NO NOTICE ABOUT AN INCIDENT OR A CHIP WARNING. CHIP DETECTOR 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) 1G72 3U H3AU 20081222 EU 2008 12 22 2008FA0000890 120081119G65004639306006 BEARING BOLKMS105 BO105LSA3 5626020EU TAIL ROTOR DRIVECRACKED W ZF6YK NONE O OTHER ININSP/MAINT 1 EA33315LS603 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 ASSOCIATED 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) 1G72 3U H3AU 20081229 EU 2008 12 29 2008FA0000891 120081111G6310 COUPLING AEROSPAS355 AS355N 8680818EU TMECA ARRIUSARRIUS1A NE MAINTRANSMISSIONMISINSTALLED D K NONE W INADEQUATE Q C ININSP/MAINT 1 NE05766AM 5601 21252126 ENGINE TO MAIN TRANS COUPLINGS FOUND TO BE INCORRECTLY ASSEMBLED. THS WAS FOUND DURING A PRE-FLIGHT INSP. THE COUPLINGS HAVE NOW BEEN ASSEMBLED CORRECTLY. (K) 1G72 3U3 URTH11GU E34NE 20081230 CE 2008 12 30 2008FA0000892 120081001G2510 CLEVIS PIN CESSNA172 172N 2072434CE LYC O320 O320* 41508EA PILOT SEAT MISSING D K NONE O OTHER ININSP/MAINT 1 SW9975743 17267920 CLEVIS PIN THAT SUPPORTS BACK OF PILOTS SEAT WORN OVER .2500 THRU. THIS PIN SLIDES IN A CURVED PORTION OF THE LOWER FRAME 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 WEARS ON IT. JUST PERIODICALLY REPLACING THE CLEVIS PIN SHOULD SUFFICE UNLESS THE COARSE WEARING IN THE BELLCRANK IS OBSER1H71 3O3 ONT3A12 E274 20090107 NE 2009 1 7 2008FA0000893 220081217G73142PR600CWT PUMP DOUG DC3 C47 3021461WP PWA R1830 R183092 52020NE LT ENGINE FUEL LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 CE19982Z 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 PUMP. SYS WAS PRESSURIZED BY THE ELECTRIC FUEL PRESSURE BOOST PUMP AND A LEAK WAS DETERMINED TO BE APPROX (1) DROP PER SECOND AT A PRESSURE OF 18 PSI. 2L72 4R4 R A669 5E4 20090106 SO 2009 1 6 2008FA0000894 220081215G73146467683A1 PUMP CESSNA210 T210N 2073456CE CONT O520 TSIO520* 17040SO ENGINE SHEARED E WNHAC ABORTED TAKEOFF Y ENGINE STOPPAGE TOTAKEOFF 1 WP255340Y2 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 TAKEOFF INITIATION, POWER SETTINGS WERE " NORMAL, SMOOTH, AND HEALTHY." AT ACFT ROTATION (65-70 KNOTS), PILOT REPORTED MANIFOLD 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. INSPECTED ENG AND FOUND ENG DRIVEN FUEL PUMP DRIVE SHAFT SHEARED. CURRENTLY IN CONTACT WITH MFG ABOUT THE INCIDENT. 1H71 3O3 O 3A21 E8CE 20090107 NM 2009 1 7 2008FA0000895 120081212G6310A1902 BELT ROBSIN ROBSINR22 R22BETA 7640110NM LYC O360 O360J2A 41514EA CLUTCH ASSY DEFECTIVE E A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 WP23558LA1968 3153 L3771936A THE PILOT REPORTED A CLUTCH LIGHT COMING ON FOR MORE THAN 5 SECONDS, FOLLOWED THE PROCEDURES IN THE POH AND MADE A PRECAUTIONARY LANDING. UPON VISUAL INSP IT WAS DEFECTED THAT ONE OF THE DRIVE BELTS IN THE CLUTCH SYS HAD FAILED AND CAUSED THE CLUTCH ACTUATOR TO ENGAGE CAUSING THE CLUTCH LIGHT TO ILLUMINATE. THERE WERE NO DAMAGES TO THE ROTORCRAFT OR ANY INJURIES TO THE PILOTS. DRIVE BELTS WHERE REPLACED AND THE ROTORCRAFT WAS RETURNED TO SERVICED. 1G71 3O3 O H10WE E286 20090106 CE 2009 1 6 2008FA0000896 120081201G3010671440211 TUBE CESSNA750 750 2076810CE ANTI-ICE SYSTEM MISMANUFACTURED C NOZRO OTHER W INADEQUATE Q C NRNOT REPORTED 1 WP239NG 4141 7500213 LT WING INBD HEATED LEADING EDGE AIR DISTRIBUTION TUBE PN 6714402-11 HAS AN INCOMPLETE WELD ON THE PERIPHERY OF THE FITTING. HAD ANIT-ICE TUBE PN 671440211 WELDED IAW DWG 6714402 DWG 001. REINSTALLED L/E AND SEALED SEAMS. (K) 2L72 4J RTT00007WI 20090107 SW 2009 1 7 2008FA0000897 120081214G6210206011135005 BOLT BELL BELL 206 206L3 1182108SW MAIN ROTOR DEBONDED D K NONE O OTHER LDLANDING 1 EA23739NM12938 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. THIS ALLOWED LEAD BALANCE WEIGHTS TO ALSO FALL OUT OF BOLT. THIS PLUG IS BONDED INTO THE BOLT AT MFG AND APPEARS TO NOT HAVE HAD ADEQUATE ADHESIVE APPLIED. 1G71 3U H2SW 20090105 CE 2009 1 5 2008FA0000898 120081222G5311 FRAME LEAR 35 35A 5170602CE GARRTTTFE731TFE731* 01518WP FUSELAGE CORRODED D K NONE O OTHER ININSP/MAINT 1 SO19244LJ4361 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 , AND AREA WAS VERY WET. 2L72 4F4 F A10CE E6WE 20090106 EA 2009 1 6 2008FA0000899 220081016G852013B21431 CRANKSHAFT CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE BROKEN B YYBRK NONE O OTHER ININSP/MAINT 1 GL036478P 15285025 THE ENGINE WAS REMOVED DUE TO ABNORMAL NOISE AND ROUGHNESS, UPON TEARDOWN INSP, FOUND THE CRANKSHAFT BROKEN IN TWO AT THE CENTER MAIN BEARING AREA. THE CTR MAIN BRG SHOWED DISTRESS, BUT DID NOT INDICATE ANY LACK OF LUBRICATION. THE CRANKCASE 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) 1H71 3O3 ONT3A19 E223 20090105 CE 2009 1 5 2008FA0000900 120081009G323399121204 ACTUATOR CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE NOSE GEAR BYPASSING B BGSRK NONE O OTHER ININSP/MAINT 1 EA213FA 5600023 HYD LOW LEVEL LIGHT CAME ON AFTER TAKEOFF AND REMAINED ON UNTIL FLAPS AND GEAR WERE SELECTED UP AND LOCKED. REPLACED NOSE GEAR ACTUATOR DUE TO INTERNALLY BYPASSING INTO THE EMERGENCY SIDE FOR GEAR EXTENSION. SENT NOSE GEAR ACTUATOR OUT FOR OVERHAUL AND INSTALLED AN OVERHAULED ACTUATOR. (K) 2L72 4F4 FRTA22CE E25EA 20090106 CE 2009 1 6 2008FA0000901 120081202G3230390814101007 DAMPER RAYTHN390 390 7150030CE BUMPER MISSING WRONG PART B E81RK NONE W INADEQUATE Q C ININSP/MAINT 1 GL03100WE RB45 INVESTIGATED PILOT REPORT OF MLG DOORS NOT CLOSING INDICATION FOLLOWING GEAR RETRACTION. FOUND RUBBER BUMPER MISSING FROM LT MAIN GEAR UPLOCK DAMPER ASSY, LT MAIN GEAR UPLOCK DAMPER ASSY CAUSING LT MN GEAR UPLOCK HOOK NOT TO RESET AND ENGAGE ROLLER FOLLOWING GEAR RETRACTION DUE TO EXCESSIVE UP-TRAVEL OF LT MAIN GEAR. REPLACED LT MAIN GEAR UPLOCK DAMPER WITH SERVICEABLE, SUPERSEDING PN 3908141010013 DAMPER ASSY. LANDING GEAR RETRACTION/ EXTENSION OPERATIONS NORMAL. 1L72 3F RTA00010WI 20090102 WP 2009 1 2 2008FA0000902 120081208G7500369H8407 TUBE HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL BLEED AIR UNSERVICEABLE B BS2RK NONE O OTHER ININSP/MAINT 1 SW178617F272 570128D CAE830481 THIS DEFECT WAS DETECTED DURING TROUBLESHOOTING FOR AN ENGINE PWR PROBLEM. THIS FLEX TYPE TUBE ASSY WAS INSTALLED IN CONJUCTION 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 WAS RE-INSTALLED. THE STC KIT WILL NOT FIT IN THE ENGINE COMPARTMENT WITHOUT THE USE OF THE FLEX BLEED AIR TUBE. THESE TUBE ASSY ARE VERY SENSITIVE TO BREAKAGE AFTER THEY HAVE TAKEN A SET. (K) 1G71 3U3 U H3WE E4CE 20090105 CE 2009 1 5 2008FA0000903 120081208G3244850108PR TUBE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL TIRE LEAKING C MT9RK NONE O OTHER ININSP/MAINT 1 SW051120N 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 REPLACED 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 MATERIAL 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) 1H71 3T3 T A37CE E4EA 5 CP60GL 20090106 NE 2009 1 6 2008FA0000904 220081209G725030606266 TURBINE BLADES AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE73140 29001NE NR 2 ENGINE DAMAGED B JGVRO OTHER O OTHER NRNOT REPORTED 1 CE09373RS 0259 THE THIRD STAGE LP TURBINE DISK ON NR 2 ENG HAD A BLADE (PN 30606901) BREAK IN FLIGHT DAMAGING THE EXHAUST NOZZLE AND THE AFTER BODY OF THE ENG. THE BLADES OF THE TURBINE DISK HAD A 2500 HOUR MPI REQUIRED EDDY CURRENT INSP COMPLETED AT 2458.6 TSN AND 1979 CSN. THE NEXT INSP APPEARS TO BE DUE IN 216.5 HRS. (K) 2L73 4F4 F A46EU E1NM 20090106 SO 2009 1 6 2008FA0000905 220081201G8530ECC712CN CYLINDER BEECH 58 58 1152740CE CONT O550 IO550C SO ENGINE SEPARATED D K NONE O OTHER ININSP/MAINT 1 EA25333ZX TH1739 NR 1 CYL FAILED, HEAD SEPARATED FROM BARREL. ALL CYL, WERE OVERHAULED, 5/12/2004, 817.5 HRS AGO. (K) 1L72 3O3 O 3A16 E3SO 20090106 EU 2009 1 6 2008FA0000906 120081122G8120 SEAL GARRTT SOCATATB20 TB21 8680697EU LYC O540 TIO540AB1A 41533EA TURBOCHARGER FAILED D K NONE O OTHER ININSP/MAINT 1 CE092802W 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, THE 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 WAS DRAINED FROM SUMP, YIELD WAS 1.5 QTS. (K) 1L71 3O3 ORTA51EU E14EA 20090106 SO 2009 1 6 2008FA0000907 220081208G8530539491 CYLINDER BEECH 33 35C33 1151408CE CONT O470 IO470K 17026SO MCAULY2A36C 2A36C23 GL ENGINE CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 WP07653P 295 CD991 818526R 652989 ANNUAL INSP REVEALED A LARGE QUANITY OF VERY BLACK OIL RUNNING DOWN THE ENGINE MOUNT LEG AND AIRFRAME STRUCTURE. FURTHER 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 BARREL CONNECTION. CYLINDERS WERE REMOVED AND INSPECTED BUT IT COULD NOT BE CONFIRMED IF CRACK EXISTED OR IF LEAK WAS THROUGH THE THREADS. THE LOW TIME ON NEW MFG CYLINDERS INDICATES THAT THE PROBLEM COULD BE IN THE MFG PROCESS. NOTE: ENGINE WAS REBUILT / ZERO TIMED USING NEW CYLINCERS ON 5/20/2001. (K) 1L71 3O3 O 3A15 3E1 5 CP880 20090107 SO 2009 1 7 2008FA0000908 220080810G8520510384 CONNECTING ROD PIPER J3 J3C65 7100510SO CONT C90 C908F 17009SO ENGINE FAILED D K NONE O OTHER ININSP/MAINT 1 GL1542080 14307 4077788 NR 1 CONNECTING ROD FAILED IN FLT, OFF-AIRPORT LANDING AND SUBSTANTIAL DAMAGE. CONNECTING ROD FAILED SLIGHTLY ABOVE CRANKSHAFT; 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 LUBRICATION 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. ENG EXHAUST WAS CLEAN AND THERE WAS NO EVIDENCE OF EXTERNAL OIL LEAKAGE ON THE ENG; REGARDLESS, OIL QUANTITY IN THE ACFT 1H71 3O3 O A691 E252 20090106 GL 2009 1 6 2008FA0000909 220080825G726123038229 SEPARATOR ALLSN 250C T63A720 03002GL AIR/OIL BROKEN D K NONE O OTHER ININSP/MAINT 1 SW99 AE405466 CUSTOMER HAD CHIP LIGHT INDICATING METAL GENERATION IN ENG. INVESTIGATION/ DISASSEMBLY REVEALED THE AIR OIL SEPARATOR GEAR 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 FAIL 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 120081226G7120AN721 BOLT CESSNA500 550 2076604CE ENGINE MOUNT INCORRECT D K NONE O OTHER ININSP/MAINT 1 SW05649WM500 42030 DURING UNSCHEDULED MAINT THE ENG WAS REMOVED FROM THE MOUNTS, (1) ENG MOUNT HAD THE HELICOIL PULL OUT OF THE CASTING NECESSITATING 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 COTTER 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. 1L72 4F A22CE 20090106 CE 2009 1 6 2008FA0000911 120081201G3230HMX5FG ROD END CESSNA310 310R 2074245CE CONT O520 IO520M 17032SO LT MLG CRACKED C K NONE J WARNING INDICATION ININSP/MAINT 1 GL1777RG 12579 310R0636 PILOT REPORTED NO LT GEAR DOWN LIGHT AND ALSO HEARD A LOUD BANG WHEN GEAR WAS RETRACTED. PILOT DID SEVERAL FLYBYS FOR MECHANICS ON GROUND, GEAR APPEARED TO BE DOWN. PILOT LANDED WITHOUT INCIDENT AND STOPPED ON RUNWAY. GEAR WAS NOT COMPLETELY LOCKED. GEAR WAS SECURED AND ACFT WAS TAXIED TO MAINT. WHEN PLACED ON JACKS, THE ROD END (HEIM END) ON THE IB LT MAIN 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) 1L72 3O3 O 3A10 E5CE 20090106 CE 2009 1 6 2008FA0000912 120081201G7400 IGNITION SYS CESSNA182 182C 2072708CE CONT O470 O470L 17026SO EGNINE DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 GL158595T 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 AND FLAT SAND FLANGES AND REMOVE DENTS. REPLACE ALL INTAKE FLANGE GASKETS AND HOSES. PRESSURE TEST INTAKE MANIFOLD. REMOVE AND REPAIR MA4-5 CARB. RUNUP OK. 8/16/2007 TACH 542.7 - CHECK MAG TO ENG TIMING. RUN-UP AND LEAK CHECK OK. SOLUTION; 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) 1H71 3O3 ONT3A13 E273 20090102 EU 2009 1 2 2008FA0000917 120081217G2435 BEARING UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE STARTER GEN UNSERVICEABLE D K NONE O OTHER ININSP/MAINT 1 EA07451F 1781 1124 PILOT COMPLAINED OF A SEVERE ENGINE VIBRATION AND HOWLING NOISE EMANATING FROM THE ENGINE AREA, DURING ALL PHASES OF ENGINE OPERATION. THE STARTER WAS REPLACED AND THE VIBRATION CEASED. (K) 1G72 3U3 UNCR0001RD E34NE 20090106 NE 2009 1 6 2008FA0000918 220081215G7414103827991 MAGNETO MOONEYM20 M20J 5870219SW LYC O360 IO360A3B6D 41828NE ENGINE MALFUNCTIONED B C41RO OTHER O OTHER TXTAXI/GRND HDL 1 SO13201TC 240173 L1710951AC STARTED THE ACFT NORMALLY, TAXIED FROM HANGAR TO THE SELF-SERVE FUEL PUMP AND SHUTDOWN. FUELED ACFT. ATTEMPTED TO START THE ACFT AFTER FUELING. THE ENG TURNED OVER NORMALLY, BUT DID NOT FIRE. TROUBLESHOOTING REVEALED NO SPARK OUTPUT FROM 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 OVERHAULED EXCHANGE UNIT. PROBABLE CAUSE/ RECOMMENDATIONS TO PREVENT RECURRENCE; NO ADDITIONAL INSP REQUIREMENTS ARE RECOMMENDED. A FAILURE SO SOON AFTER OVERHAUL SUGGESTS A DEFECT IN THE PARTS OR A FAILURE IN THE OVERHAUL PROCESS. THE LARGEST1L71 3O3 O 2A3 1E10 20090107 CE 2009 1 7 2008FA0000919 120081210G571152221003 SPAR CESSNA402 402B 207590PCE CONT O520 TSIO520EB 17040SO MCAULY3AF32C3AF32C87 GL LT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 WP13141MC10940 402B0547 DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR. THE MAIN GEAR IS ATTACHED AT THE OTBD END. THE CRACKS WERE AT THE 11, 2, 5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LENGTH 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 WENT THROUGH THE SCREW HOLES AND EXTENDED UP T 2+ INCHES. THE CRACKS WERE OBSERVED 2671 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 KNOWN IF TH1L72 3O3 O A7CE E8CE 5 CP22EA 20090106 CE 2009 1 6 2008FA0000920 120081216G323312810016 ACTUATOR CESSNA172 172RG 2072438CE RT MLG CRACKED D JU8SO OTHER O OTHER NRNOT REPORTED 1 GL259423D1940 172RG0285 ON 7/08/2008, RT MLG NOT FULLY RETRACTED REPORTED BY ATC. THE PILOTS NOTICED THE RT MLG WAS NOT FULLY RETRACTED. THE LANDING 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 ACTUATOR 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 DURING1H71 3O 3A17 20090106 CE 2009 1 6 2008FA0000921 120081210G5711522210003 SPAR CESSNA402 402B 207590PCE CONT O520 TSIO520EB 17040SO MCAULY3AF32C3AF32C87 GL LT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 WP13402CA12660 402B0842 DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR. THE MAIN GEAR IS ATTACHED AT THE OTBD END. THE CRACKS WERE AT THE 11, 2, 5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LENGTH. 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 RING AND NUT PLATES OF THE OPPOSITE SIDE. THESE CRACKS WENT THROUGH THE SCREW HOLES AND EXTENDED UP TO 1.5 INCH. THE CRACKS WERE OBSERVED 1600 HOURS AFTER THE MAIN SPAR CAP MODIFICATIONS. SIMILAR CRACKS OF VARYING DEGREE HAVE BEEN OBSERVED IN 5 OF 8 ACFT. ALL HAVE THE MOD. IT IS NOT KNOWN IF THERE IS ANY CORROLATION. (K) 1L72 3O3 O A7CE E8CE 5 CP22EA 20090106 CE 2009 1 6 2008FA0000922 120081210G571152221003 SPAR CESSNA402 402B 207590PCE CONT O520 TSIO520NB 17040SO LT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 WP13106GP16296 402B1235 DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR. THE MAIN GEAR IS ATTACHED AT THE OTBD END. THE CRACKS WERE AT THE 11,2,5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LENGTH. 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 OBSERVED 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) 1L72 3O3 O A7CE E8CE 20090106 EU 2009 1 6 2008FA0000923 120081212G322225UN561 AXLE BRAERODH125 HS125700A 4230170EU NLG WORN B X42RK NONE O OTHER ININSP/MAINT 1 GL03483FG521 257094 CONTINUOUS NOSE GEAR VIBRATIONS UPON LANDING. TEARDOWN AND INSPECTION OF NOSE GEAR AXLE BARREL ASSY REVEALED THE NOSE AXLE TO BE WORN BEYOND LIMITATIONS. (2) .005" GROOVES WORN INTO AXLE. (1) ON EACH SIDE WHERE THE AXLE BARREL COVER PLATE SEALS ARE LOCATED. NO WEAR IS PERMITTED AS PER THE OVERHAUL MANUAL. (K) 2L72 4F A3EU 20090102 CE 2009 1 2 2008FA0000924 120081201G2710500000066 CONTROL CABLE CESSNA421 421B 2076014CE LT AILERON CABLEFRAYED D O OTHER O OTHER NRNOT REPORTED 1 GL13 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 PULLEYS 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 WING 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 BROKE1L72 3O A7CE 20090107 CE 2009 1 7 2008FA0000925 120081215G28206017001079 VENT LINE BEECH 58 58 1152740CE RT WING LEAKING B EHHRK NONE K FLUID LOSS ININSP/MAINT 1 EA17584RF1933 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 ACFT 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 BUSHING WHERE THE LEAK WAS OBSERVED. (K) 1L72 3O 3A16 20090102 CE 2009 1 2 2008FA0000926 120081201G2710500000067 CONTROL CABLE CESSNA421 421B 2076014CE LT AILERON FRAYED D O OTHER O OTHER NRNOT REPORTED 1 GL13 68494 TT ON CABLES UNKNOWN SUSPECT ORIGINAL. FOUND LT AFT AILERON CABLE FRAYED AT WING STA 59 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 PULLEYS AT THIS STATION WERE TURNING FREELY. WHEN INSTALLING NEW CABLE NOTICED THE FWD AILERON CABLE WITH BROKEN STRANDS ALSOAT WING STATION 87.29, ALSO REQUIRING CABLE REPLACEMENT. SUGGEST THAT EVERYONE BE REMINDED OF THIS LOCATION AND OF WING STA 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 AILERONS HAD TO BE MOVED TO THE TRAVEL LIMITS TO BE COMPLETELY INSPECTED, AS THE CABLES WERE BROKEN IN SMALL LOCAL1L72 3O A7CE 20090120 SO 2009 1 20 2008FA0000927 220081201G8500S1053E16T HOSE CESSNA150 A150K 2071824CE CONT O200 O200* 17020SO AIR INTAKE CONTAMINATED D A UNSCHED LANDING RY PARTIAL RPM/PWR LOSS ENGINE STOPPAGE CLCLIMB 1 AL058450M 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 WITHOUT INCIDENT. FOUND THE SCAT HOSE COMING FROM FRONT BAFFLE DOWN TO FRONT OF EXHAUST SHROUD HAD FILLED WITH WATER. 1H71 3O3 O 3A19 E252 20090106 EA 2009 1 6 2008FA0000928 220081230G741466LC35SDNP MAGNETO CESSNA206 206H 2073301CE LYC O540 TIO540AJ1A EA RIGHT DAMAGED B O OTHER O OTHER UKUNKNOWN 1 NM075880K594 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 CASING. 1H71 3O3 ORTA4CE E14EA 20090106 CE 2009 1 6 2009F00002 120081221G561010138402522 WINDSHIELD BEECH 90 C90 1152913CE COCKPIT CRACKED G A UNSCHED LANDING O OTHER CRCRUISE 1 CE01736EA LJ1478 ACFT LEVELED OFF AT 20,000 FT AFTER APPROX 45 MIN OF FLIGHT, THERE WAS A SUDDEN BANG, AND CO-PILOTS WINDSHIELD INNER PANE SPIDER WEB CRACKED. FLT CREW DIVERTED TO NEAREST AIRPORT AND LANDED WITHOUT FURTHER INCIDENT. 1L72 3T 3A20 20090107 CE 2009 1 7 2009FA0000000 120081208G325066429438 BUNGEE CYLINDER CESSNA560 560XL 2076702CE MLG MALFUNCTIONED C K NONE O OTHER ININSP/MAINT 1 SO13669TT740 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 LOOSENED, ALLOWING THE ROD END TO EXTEND ON THE PUSH ROD. REPLACED STEERING BUNGEE WITH NEW UNIT AND RE-RIGGED THE NOSE STEERING. 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. 2L72 4F RTA22CE 20090108 SW 2009 1 8 2009FA0000002 120081218G3233EM411514 ACTUATOR ECLIPSEA500 ECLIPSEEA5003350000SW RT MLG FAULTY C K NONE J WARNING INDICATION CLCLIMB 1 SO19929KD134 000240 DURING CLIMB THE RT MLG FAILED TO FULLY RETRACT. GEAR INTRANSIT INDICATED. ON SELECTION OF LANDING GEAR DOWN, RT MLG FAILED 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 MLG ACTUATOR REPLACED AND SYSTEM FUNCTION TESTED NORMAL. 1L72 4J RTA00002AC 20090120 SO 2009 1 20 2009FA0000004 220081210G8520 BOLT CESSNA210 T210L 2073449CE CONT O520 TSIO520H 17040SO ENGINE FAILED G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 GL159426K 21060572 506240 DURING CLIMB TO CRUISE ENGINE MADE A LOUD NOISE AND QUIT RUNNING, ENGINE REMAINED WINDMILLING TO LANDING. VISUAL INSP REVEALED NR 3 CYLINDER ROD BOLT MISSING, ROD CAP EXITED ENG THRU UPPER CASE, NO EVIDENCE OF OIL STARVATION. 1H71 3O3 O 3A21 E8CE 20090120 CE 2009 1 20 2009FA0000005 120081223G2910S217840095A HOSE CESSNA210 T210M 2073451CE CONT O520 TSIO520* 17040SO HYD SYSTEM BURST B A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION LDLANDING 1 SO05732UR3658 21061789 RT NLG DOOR ACTUATOR HOSE FAILED CAUSING COMPLETE HYD FLUID LOSS . RESULTING IN LT MAIN GEAR NOT ABLE TO BE FULLY EXTENDED TO DOWN AND LOCKED POSITION. ACFT MADE EMERGENCY LANDING WITH LT MAIN GEAR PARTIALLY EXTENDED. MINOR DAMAGE. FAILED HOSE APPEARS TO BE ORIGINAL INSTALLED NEW IN 1977. 1H71 3O3 O 3A21 E8CE 20090130 CE 2009 1 30 2009FA0000007 120081215G323335810080602 ACTUATOR BEECH 35 A35 1151504CE MLG FAILED D O OTHER O OTHER LDLANDING 1 GL15473AB 368 D1578 INTERNAL FAILURE WITHIN LANDING GEAR ACTUATOR GEARBOX. GEAR WOULD NOT CYCLE DOWN BY NORMAL OR EMERGENCY EXTENSION. EMERGENCY HANDLE WOULD NOT ENGAGE. COMPONENT WAS OVERHAULED IN 1983. 1L71 3O A777 20090120 NE 2009 1 20 2009FA0000012 220081230G73212123M55P04 ECU AIRBUS320 A320214 3930316EU CFMINTCFM56 CFM565B4P NE NR 2 ENGINE FAULTY C VQIAA UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 WP15632VA 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 OPS CHECKED OK PER AMM 73-21-60. IAW THE OPERATORS RECORDS, ALL AIRWORTHINESS DIRECTIVES, SERVICE BULLETINS, STC`S AND PMA`S ARE IN FULL COMPLIANCE WITH THE TYPE DESIGN CERTIFICATE AND ASSOCIATED REGULATORY REQUIREMENTS. THE ACFT WAS RELOCATED BACK TO SFO. N632VA DEPARTED LAS AT 0741Z AND ARRIVED SFO AT 0842Z. NO FAULTS NOTED. 2L72 4F4 FRTA28NM E38NE 20090120 EU 2009 1 20 2009FA0000013 120081217G6120 CONTROL CABLE STBROSSD3 SD360 8100606EU RT PROPELLER BROKEN C TXHAO OTHER O OTHER NRNOT REPORTED 1 WP13808KR SH3734 THE ACFT RT PROP CABLE BROKE. ACFT RETURNED TO HONOLULU STATION FOR INSPECTION AND REPAIR. 2H72 4T A41EU 20090129 CE 2009 1 29 2009FA0000014 120081210G3260 ARM CESSNA414 414 2075908CE DOWNLOCK BROKEN D K NONE O OTHER LDLANDING 1 GL1952CS 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 SEEM TO GET WEAK OVER TIME. THERE WAS NO OTHER REASON FOR THE ARM TO FAIL. (K) 1L72 3O RTA7CE 20090130 CE 2009 1 30 2009FA0000015 120081230G3240632750012 TUBE CESSNA525 525 2076601CE BRAKE SYS BROKEN B AWORK NONE O OTHER ININSP/MAINT 1 GL15793CJ4959 5250021 DURING AN INSP, DOC 10, LANDING GEAR PNEUMATIC BRAKE SYS FUNCTIONAL CHECK ONE OF THE LINES IN THE RT LANDING GEAR WELL BLEW. 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) 1L72 4F RTA1WI 20090129 SO 2009 1 29 2009FA0000016 220081217G8550652969 PAN CESSNA414 414A 2075907CE CONT O550 TSIO550A 41516SO ENGINE CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 GL15414PS 414A0056 800653 OIL LEAK CAME FROM CRACK IN OIL PAN. CAUSE UNKNOWN. ENG TSMOH 95 HRS. CRACK/ FITTING WITH HOSE ATTACHED FOR REMOTE OIL DRAIN. (K) 1L72 3O3 O A7CE E5SO 20090130 WP 2009 1 30 2009FA0000017 120081223G7820C16932 MUFFLER ROBSINR44 R44RAVENII 7640122WP EXHAUST SYSTEM FAILED D K NONE O OTHER ININSP/MAINT 1 NE051425K676 10153 MUFFLER CAN BLOW OUT AT TAIL PIPE CONNECTION AND COLLECTOR FAILURES, BULGES AND BLOW OUTS. WEAK MATERIAL, USE THICKER AND BETTER MATERIAL. PEOPLE ARE GETTING SICK AND/OR BAD HEADACHES. CO DETECTORS ARE SOUNDING OFF IF YOU HAVE ONE. (K) 1G71 3O H11NM 20090128 WP 2009 1 28 2009FA0000018 120081223G7810C1695 COLLECTOR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE IB AREA 3 TO 1 DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 NE05417PK497 11480 EXHAUST COLLECTORS 3 TO 1 TYPE. BULGES AND BLOW OUTS. 1G71 3O3 O H11NM 1E4 20090128 CE 2009 1 28 2009FA0000020 120081224G326045A3951141 UPLOCK HOOK BEECH MU300 400A 1155402CE NLG DISENGAGED B E81RA UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL03175QS15 AFTER DEPARTING, FLIGHT CREW OBSERVED RED LANDING GEAR UNSAFE LIGHT IN LANDING GEAR CONTROL HANDLE ILLUMINATED AFTER LANDING GEAR RETRACTION. RETURNED TO DEPARTURE. FOUND NLG UPLOCK HOOK NOT ENGAGING NOSE GEAR STRUT ASSY AS REQUIRED IAW MM 32-30-00. LANDING GEAR RETRACT/ EXTENSION SYS FUNCTION CHECKS IAW MM 32-00-00 OK. SUSPECT ADJUSTMENT CHANGED SLIGHTLY FROM AS-BUILT RIGGING DUE TO COMPONENTS WEARING IN, HAVE NOTED SIMILAR CONDITION PREVIOUSLY ON OTHER LOW-TIME ACFT. (K) 2H72 4F RTA16SW 20090129 SO 2009 1 29 2009FA0000021 120081022G3230SE0521903XXX BEARING GULSTMG1159 GIV 3980115SO NLG LOOSE D O OTHER O OTHER TXTAXI/GRND HDL 1 WP19972MS 1285 WHILE TAXIING ACFT, CREW REPORTED POPPING SOUND COMING FROM NOSE WHEEL WELL AND DURING RT TURNS. FOUND NLG DRAG BRACE UPPER 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. 2L72 4F RTA12EA 20090130 EU 2009 1 30 2009FA0000022 120081027G7921MS210435 NUT HUGHES369 369FF 4470709EU ALLSN 250C 250C30 03013GL COOLER BLOWER BACKED OUT B GI3RK NONE O OTHER ININSP/MAINT 1 WP015185G 0009F OIL COOLER BLOWER DRIVEN PULLEY RETAINING NUT IS BACKING OFF OF SHAFT DURING NORMAL USE. NUT IS A STAINLESS STEEL, SILVER 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 SUBSTANDARD. UNIT WAS O/H. THE O/H FACILITY HAS BEEN INFORMED OF THESE INCIDENTS AND THEY ARE CURRENTLY INVESTIGATING THE1G71 3U3 U H3WE E1GL 20090129 EA 2009 1 29 2009FA0000024 220081204G732225765463 SERVO CESSNA206 206H 2073301CE LYC O540 IO540AC1A5 EA MCAULY3D36C B3D36C432 GL ENGINE LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 EA13137P 2060804 L3271948E 80VSA1 FUEL SERVO LEAKED WHILE ACFT WAS PARKED OVERNIGHT. THE MIXTURE WAS IN CUT OFF POSITION. FLIGHT MANUAL, SEC 4, NORMAL PROCEDURES PAGE 4-23 SECURING ACFT NR 10 STATES: FUEL SELECTOR VALVE RT OR LT TO PREVENT CROSS FEEDING. IF THE FUEL SELECTOR VALVE WAS TURNED TO OFF, THIS WOULD HAVE PREVENTED. THERE IS A POTENTIAL FOR FUEL TO ENTER ENGINE CYLINDERS AND OIL SUMP IF THE FUEL SERVO MIXTURE CUT OFF LEAKS USING FLIGHT MANUAL PROCEDURES. NEED TO ADDRESS: FLIGHT MANUAL PROCEDURES TO FUEL SELECTOR VALVE OFF. (K) 1H71 3O3 ORTA4CE 1E4 5 CP58GL 20090130 CE 2009 1 30 2009FA0000026 120081224G3600AA3216CW PUMP BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO LOW PRESSURE B VJ3RO OTHER O OTHER TXTAXI/GRND HDL 1 WP078242T19 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) 1L71 3O3 O 3A15 E5CE 20090130 GL 2009 1 30 2009FA0000027 120081219G779714251001 WIRE HARNESS CIRRUSSR SR22 2130001GL ENG COMPARTMENT CHAFED B YEBRO OTHER O OTHER NRNOT REPORTED 1 CE05961AG 0255 FOUND THE BLACK PLASTIC WIRE LOOM THAT HOUSES THE MAP WIRING HARNESS FWD OF THE BAFFLE TO HAVE CHAFED THROUGH THE WIRE INSULATION 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 LOOM. SECURE WIRES AS NEEDED. (K) 1L71 3O NTA00009CH 20090130 EA 2009 1 30 2009FA0000028 220081205G852011B200611SH CRANKCASE PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA ENGINE CRACKED B UC2RK NONE O OTHER ININSP/MAINT 1 GL194149G4622 872 2843191 L3630836A FOUND LT FRONT CRANKCASE CRACKED DURING ROUTINE MX. (K) 1L71 3O3 O 2A13 E286 20090130 EA 2009 1 30 2009FA0000029 220081206G852011B200615H1 CRANKCASE PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA ENGINE CRACKED B UC2RK NONE O OTHER ININSP/MAINT 1 GL194148P6916 789 2843177 L3616236A FOUND LT FRONT CRANKCASE CRACKED DURING ROUTINE MX. (K) 1L71 3O3 O 2A13 E286 20090130 CE 2009 1 30 2009FA0000030 120081228G2497 CIRCUIT BREAKER LEAR 55 55LEAR 5170702CE MAIN BUSS MALFUNCTIONED D A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CRCRUISE 1 CE03242RB 55B132 ACFT DEPARTED, ENROUTE WITH 2 PASSENGERS, 2 HOURS INTO FLIGHT, JUST PRIOR TO INITIAL DESCENT, ACFT EXPERIENCED A COMPLETE ELECTRICAL FAILURE AND LOSS OF PRESSURIZATION AT FL430. FLIGHT CREW REGAINED CONTROL OF PRESSURIZATION AROUND FL330 AND RESTORED PWR TO NR 1 COMM RADIO. ACFT DIVERTED AND MADE A VISUAL NO-FLAP APPROACH & LANDING. ACFT OVERRAN RUNWAY APPROX 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) 2L72 4F A10CE 20090205 SO 2009 2 5 2009FA0000036 220081013G7414105005563 MAGNETO CIRRUSSR SR20 05628AJGL CONT O360 IO360ES SO HARTZLHCJ3Y PHCJ3YF1 GL ENGINE FAILED D A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 GL09651BS235 1711 360237 FP4833B FLIGHT CREW REPORTED ENGINE SPUTTERED DURING INITIAL CLIMB. UPON INTERNAL VISUAL INSP OF LT MAGNETO, FOUND BROKEN MAGNETO SHAFT BELOW DRIVE GEAR. ALUMINUM MAGNET CASTING FAILED AT STEEL SHAFT MATING JOINT. ROTATION OF STEEL SHAFT IN ALUMINUM 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. PREVIOUSLY ON 9/9/2008 AT 1112.0 HOURS AIRCRAFT TOTAL TIME, THE RIGHT MAGNETO WAS FOUND TO HAVE FAILED DURING RUN-UP CHECKS WITH THE SAME FAILURE MODE. 1L71 3O3 ONTA00009CHE1CE 5 CP36EA 20090205 SO 2009 2 5 2009FA0000037 220081218G7414105005563 MAGNETO CIRRUSSR SR20 05628AJGL CONT O360 IO360ES SO HARTZLHCJ3Y PHCJ3YF1 GL ENGINE FAILED D D RETURN TO BLOCK Y ENGINE STOPPAGE TXTAXI/GRND HDL 1 GL0970RB 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 CASTING 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 PRECAUTIONARY 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. 1L71 3O3 ONTA00009CHE1CE 5 CP36EA 20090205 2009 2 5 2009FA0000050 220081229G7414M3458 ROTOR MAGNETO BROKEN D O OTHER O OTHER NRNOT REPORTED 1 NM02 1059 98100916 THE PILOT REPORTED THAT ON CHECKING THE RT MAGNETO THERE WAS AN EXCESSIVE RPM DROP BUT THAT THE ENGINE STILL OPERATED SMOOTHLY ON THAT MAGNETO. UPON DISASSEMBLY OF THE MAG IT WAS FOUND THAT ONE LEG OF THE CAM SLOT ON THE ROTOR SHAFT WAS COMPLETELY BROKEN OFF AT THE BOTTOM OF THE SLOT. (K) 20080313000472008031300047SO 2008 3 13 21808 120080218G49101159AC30551103 DUCT GULSTMG1159 GIV 3980115SO APU INLET CRACKED E CLWAK NONE O OTHER ININSP/MAINT 1 SW05589HM6464 1153 A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM). 2L72 4F RTA12EA 20080313000452008031300045SO 2008 3 13 218081153 120080218G49101159AC30551103 DUCT GULSTMG1159 GIV 3980115SO APU INLET CRACKED E CLWAK NONE O OTHER ININSP/MAINT 1 SW05589HM6464 1153 A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM). 2L72 4F RTA12EA 20080204001032008020400103EA 2008 2 4 22497 220080131G8530AEL14995 RETAINER ECI PIPER PA18 PA18 7101802SO LYC O360 O360C4P 42289EA PUSH ROD BROKEN B WS9RK NONE K FLUID LOSS ININSP/MAINT 1 NM078780D 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. 1H71 3O3 O 1A2 E286 20080520 CE 2008 5 20 2568 120080501G3240215286 BRAKE ASSY CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE RT MLG BROKEN G O OTHER O OTHER TXTAXI/GRND HDL 1 SO19330DK 5500266 RT MLG BRAKE LOCK UP DURING TAXI. AN INSP BY MAINT HAS DETERMINED THAT THE BRAKE STATOR CAME APART AND LOCKED UP THE BRAKE. 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. 1L72 4F4 F A22CE E1NE 20080414000142008041400014EU 2008 4 14 325 120080325G3233D52177 HOLDER MESSIER AMD FALC20FALCON200 2730150EU ACTUATOR BROKEN B GQRRO OTHER K FLUID LOSS LDLANDING 1 SW05 DRI76878 THE PACKING HOLDER 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 WERE MODIFIED AND IDENTIFIED SDR IAW THE SB. 2L72 4F RTA7EU 20080204001072008020400107 2008 2 4 43385883 420080129G34608220868044 FMC RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE7315BR WP MALFUNCTIONED C O OTHER F FLT CONT AFFECTED CRCRUISE 1 EA23808BL 258634 UNCOMMANDED 360 DEGREE TURN AS COMMANDED BY THE FMS. SB 0057-05 DATED DECEMBER 21, 2005 DELETING A WAYPOINT MAY CAUSE THE FMS TO INSERT AND FLY AN UNINTENDED TURN. KNOWN PROBLEM WITH OPTIONAL SOLUTION FOR FMS6000 NO SOLUTION FOR FMS5000 INSTALLED IN AC. 2L72 4F4 FRTA3EU E6WE 20080402000142008040200014 2008 4 2 433858831 420080129G34618220891008 FMC BEECH MU300 400A 1155402CE GARRTTTFE731TFE7315BR WP FAULTED C O OTHER F FLT CONT AFFECTED CRCRUISE 1 EA23808BL RK367 UNCOMMANDED 360 DEGREE TURN AS COMMANDED BY THE FMS. REF SB 0057-05 DATED DECEMBER 21, 2005 DELETING A WAYPOINT MAY CAUSE THE FMS TO INSERT AND FLY AN UNINTENDED TURN. KNOWN PROBLEM WITH OPTIONAL SOLUTION FOR FMS6000 INSTALLED IN AC, NO SOLUTION FOR FMS5000 INSTALLED IN AC. 2H72 4F4 FRTA16SW E6WE 20080710 EU 2008 7 10 5APR577Y1 120080515G3242244755 BRAKE DISC BFGOODRICH PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL RT MLG BROKEN B 5APRK NONE O OTHER ININSP/MAINT 1 EA65591AF1174 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 THE OUTBOARD BRAKE DISK ON THE RIGHT BRAKE WAS BROKEN INTO TWO PIECES. THE BRAKE ASSEMBLY WAS REMOVED AND REPLACED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20080710 EU 2008 7 10 5APR577Y2 120080515G3242244755 BRAKE DISC BFGOODRICH PILATSPC12 PC1247 7090552EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL LT MLG BROKEN B 5APRK NONE O OTHER ININSP/MAINT 1 EA65729AF1566 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. 1L71 4T4 TRTA78EU E26NE 5 CP210NE 20080710 EU 2008 7 10 5APR577Y3 120080515G3242244755 BRAKE DISC BFGOODRICH PILATSPC12 PC1247 7090552EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL RT MLG BROKEN B 5APRK NONE O OTHER ININSP/MAINT 1 EA65729AF1566 0593 729 PR0603 KX359 DURING ANNUAL INSPECTION RIGHT MAIN WHEEL WAS REMOVED TO REPACK BEARINGS AND THE MIDDLE BRAKE DISC WAS FOUND TO BE BROKEN. REMOVED AND REPLACED BRAKE ASSEMBLY. 1L71 4T4 TRTA78EU E26NE 5 CP210NE 20080414000162008041400016CE 2008 4 14 6001LENG 120080327G5415555415046810 ATTACH ANGLE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ENGINE CORRODED B K NONE O OTHER ININSP/MAINT 1 SW176001L10071 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. 1L72 4F4 F A22CE E1NE 20080508000532008050800053CE 2008 5 8 6001LOXYGEN 120080423G3510176174 OXYGEN BOTTLE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE NOSE LEAKING C K NONE O OTHER ININSP/MAINT 1 SW176001L 5500169 INSTALLED REPAIRED EMERGENCY OXYGEN BOTTLE IN AC AND SERVICED. WHEN BOTTLE WAS TURN ON WAS FOUND TO LEAK FROM ON-OFF VALVE. UNIT WAS REPAIRED ON JANUARY 21,2008. 1L72 4F4 F A22CE E1NE 20080717 CE 2008 7 17 772AF 120080603G361013022 CHECK VALVE BEECH 200 B200 1152922CE BLEEDD AIR SYS DEFECTIVE B VIBRK NONE O OTHER ININSP/MAINT 1 SO13772AF5763 BB1001 FLAPPERS IN BLEED AIR INLET CHECK VALVE CAME LOOSE AND CHAFED THE INSIDE OF THE HOUSING. ONE FLAPPER CHAFED A HOLE THROUGH THE HOUSING. 1L72 4T A24CE 20080902 CE 2008 9 2 842008N341CS 120080730G3240 BRAKE CESSNA500 550 2076604CE MLG CONTAMINATED C O OTHER O OTHER APAPPROACH 1 EA63341CS 5501106 THE LOW BRAKE PRESSURE AND ANTI-SKID INOP ANNUNCIATORS ILLUMINATED IN FLIGHT. AN EMERGENCY WAS DECLARED. DURING LANDING ROLL OUT BRAKE PRESSURE CAME BACK AND LIGHTS EXTINGUISHED. THE BRAKES WERE BLED, A SMALL AMOUNT OF AIR NOTED. OPERATIONAL CHECK OK. ACFT MADE THREE TAKEOFFS AND LANDINGS WITH NO DEFECTS NOTED. ACFT RETURNED TO SERVICE. (S) 1L72 4F A22CE 20080225000062008022500006SW 2008 2 25 901012008 120080217G5210S16206327957 DOOR SKRSKYS58T S58T 8141800SW PWA PT6T PT6T6 52045EA MAIN DEPARTED L O OTHER D INFLIGHT SEPARATION CRCRUISE 1 GL23901CH1531315313 581464 DURING POSTFLIGHT INSP, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSP OF AC FOUND NO DAMAGE OR MISSING COMPONENTS OTHER THAN DOOR. REPLACEMENT DOOR WAS INSTALLED AND OPS CHECKED WITH NO DISCREPANCIES NOTED TO AIRFRAME, DOOR MOUNTING, STRUCTURE AND DOOR OPERATION. AC WAS RETURNED TO SERVICE. 2G71 4U4 UNC1H11 E22EA 20080319002662008031900266SW 2008 3 19 9010208 120080217G5210S16206327957 DOOR SKRSKYS58T S58T 8141800SW PWA PT6T PT6T6 52045EA ZONE 800 DEPARTED L O OTHER D INFLIGHT SEPARATION CRCRUISE 1 GL23901CH1531315313 581464 DURING POSTFLIGHT INSPECTION, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSPECTION OF AIRCRAFT FOUND NO DAMAGE OR MISSING 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. 2G71 4U4 UNC1H11 E22EA 20080306002492008030600249SW 2008 3 6 901CHI0208 120080221G5210S16206327957 DOOR SKRSKYS58T S58T 8141800SW PWA PT6T PT6T6 52045EA DEPARTED L O OTHER D INFLIGHT SEPARATION CRCRUISE 1 GL23901CH1531315313 581464 DURING POSTFLIGHT INSPECTION, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSP OF AC FOUND NO DAMAGE OR MISSING 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. 2G71 4U4 UNC1H11 E22EA 20080520 CE 2008 5 20 90XR042708 120080427G2910AS62306H0073 LINE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP HYDRAULIC SYS CHAFED E T6FAA UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 GL0990XR 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. 2L72 4F4 FRTT00008WIE6WE 20081209 WP 2008 12 9 AALA200810280 120081112G5320 INTERCOSTAL DOUG DC9 DC983 3022083WP ZONE 100 CRACKED A AALAK NONE O OTHER ININSP/MAINT 1 SW219401W 53137 INTERCOSTAL CRACKED IN CEILING OF MID CARGO. REPLACED INTERCOSTAL. 2L72 4F RTA6WE 20080903 NM 2008 9 3 ABXR080225 120080729G5330 SKIN BOEING767 767223 1385123NM BS 615 S34R DAMAGED C ABXRK NONE O OTHER ININSP/MAINT 1 GL23761CX 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) 2L72 4F RTA1NM 20080903 NM 2008 9 3 ABXR080226 120080731G5330146T35111 SKIN BOEING767 767223 1385123NM BS 1510 S35-36L DAMAGED C ABXRK NONE O OTHER ININSP/MAINT 1 GL23761CX 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) 2L72 4F RTA1NM 20080903 NM 2008 9 3 ABXR080228 120080801G5330143T35211 SKIN BOEING767 767223 1385123NM BS 544 S30-31L DENTED C ABXRK NONE O OTHER ININSP/MAINT 1 GL23761CX 22318 OUTWARD DENT STA 544, STRINGER 31-30 LT REQUIRES REPAIR. REPAIRED AREA IAW B767 SRM 53-00-01, FIGURE 201. (S) 2L72 4F RTA1NM 20080404000162008040400016EA 2008 4 4 ACOR032408001 220080324G7322383493 PLUG PREAIR RSA5 CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA FUEL SERVO LOOSE B ACORK NONE O OTHER ININSP/MAINT 1 EA392162Y1618 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. 1H71 3O3 ONT3A12 1E10 20080404000172008040400017EA 2008 4 4 ACOR032508001 220080325G7322383493 PLUG PREAIR RSA10ED1 CESSNA206 T206H 2073303CE LYC O540 TIO540AJ1A EA FUEL SERVO LOOSE B ACORK NONE O OTHER ININSP/MAINT 1 EA39377HA604 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 1H71 3O3 ORTA4CE E14EA 20080410002012008041000201CE 2008 4 10 AMCR200800001 120080331G731279646 HEATING ELEMENT CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL RT ENGINE FAILED B AMCRO OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 GL09279DV636 070 141148 PILOT REPORTED T2 HEATER FAIL ON RT ENGINE. FOUND T2 PROBE BAD. 1L72 4F4 FRTA1WI E3GL 20080404000092008040400009CE 2008 4 4 B3OR20080079 120080318G3233991206313 ACTUATOR CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE MLG OUT OF POSITION B B3ORD RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 SW0326621 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 SLIGHT 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 SERVICEABILITY OF THE ACTUATOR'S INTERNAL DOWNLOCK MECHANISM WITH SATISFACTORY RESULTS. DOWNLOCK INDICATOR SWITCH ADJUSTMENT COULD NOT BE VERIFIED DUE TO AN ABSENCE OF REQUIRED TESTING EQUIPMENT. THE RECENTLY OVERHAULED ACTUATOR WAS REMOVED FOR R1L72 4F4 F A22CE E1NE 20080402000092008040200009NE 2008 4 2 B3OR2008030 220080125G73210164548240 FCU SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE ENGINE LEAKING B B3ORK NONE K FLUID LOSS ININSP/MAINT 1 SW035204J 176 3118 9318 FUEL CONTROL UNIT IS LEAKING FUEL FROM A DIAPHRAM BREATHER HOLE IN THE CASING. THE LEAKING HOLE IS LOCATED BELOW AND SLIGHTLY 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 NORMALLY. 1G71 3U3 U H9EU E19EU 20080403000382008040300038EU 2008 4 3 B3OR2008046 120080213G2910704A44831141 SERVO CONTROL SNIAS 350 AS350B2 8680813EU LT HYD SYSTEM LEAKING B B3ORK NONE KJ FLUID LOSS WARNING INDICATION ININSP/MAINT 1 SW035204J5313 2137 3118 ON A ROUTINE PREFLIGHT INSPECTION, THE LT HYDRAULIC ROLL CONTROL SERVO WAS DISCOVERED TO BE LEAKING HYDRAULIC FLUID AT THE PISTON SHAFT SEAL. THE LEAK COULD NOT BE DUPLICATED DURING GROUND TESTING WITH A HYDRAULIC POWER CART IAW THE MM INSTRUCTIONS. SUBSEQUENT FLIGHT TESTING REVEALED THE LEAK PERSISTING WITH A LEAK RATE SUSPECTED TO BE SLIGHTLY OUT OF LIMITS. 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. 1G71 3U H9EU 20081124 NM 2008 11 24 B62R20081106002 120081106G5411313W181338113813SPAR BOEING777 777236 1385220NM NR 2 PYLON CORRODED B B62RK NONE O OTHER ININSP/MAINT 1 EA21702BA35345 27108 NR 2 ENG PYLON STRUT, AFT FAIRING HEAT SHIELD LOWER SPAR STRUCTURE, PITTING CORROSION FOUND THROUGHOUT SPAR STRUCTURE, CHORDS, FRAMES 3, 4 & 5. EVIDENCE OF PITTING CORROSION AND HEAT DAMAGE ON LOWER SIDE OF WEBS. REF 54-51-71 PG 6. POSSIBLE CAUSE WAS AFT FAIRING HEAT SHIELD THERMAL BLANKETS 1 THRU 6 WERE TORN AND WATER LOGGED, SEALS DAMAGED AND STRUT DRAIN 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 FIRE SEAL DAMAGED. HEAT SHIELD SEAL DAMAGED. SECONDARY FLUID SEAL DAMAGED. PARTS WILL REQUIRE REPAIR OR REPLACEMENT. 2L72 4F RTT00001SE 20081124 NM 2008 11 24 B62R20081107003 120081107G5411313W3813X FRAME BOEING777 777236 1385220NM PYLON CRACKED B B62RK NONE O OTHER ININSP/MAINT 1 EA21702BA35345 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 NR 1 THRU NR 4, P/N'S 313W1813-X & 313W3813-X HAVE EVIDENCE OF HEAT DAMAGE AND SURFACE CORROSION. REF SRM 54-51-71 FIGURE 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 PYLON) 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. 2L72 4F RTT00001SE 20081121 NM 2008 11 21 B62R20081121001 120081106G5320149W1129111037 INTERCOSTAL BOEING777 777236 1385220NM FUSELAGE CORRODED B B62RK NONE O OTHER ININSP/MAINT 1 EA21702BA35345 27108 SECTION 43 WING TO BODY FAIRING STRUCTURE LT SIDE. INTERCOSTALS THAT SUPPORT THE FWD WING TO BODY FAIRINGS HAVE MODERATE 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. 2L72 4F RTT00001SE 20080225002412008022500241 2008 2 25 CA080101001 420080101G3418501177003 ACTUATOR CNDAIRCL600 CL6002D24 1390016EA GE CF34 CF348C5B1 30052NE STICK PUSHER MALFUNCTIONED W O OTHER F FLT CONT AFFECTED LDLANDING 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 20080101001) 2L72 4F4 FRTA21EA E00063EN 20080225002502008022500250EA 2008 2 25 CA080102001 120080101G2750601R930507 FCU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE TE FLAPS UNSERVICEABLE W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION LDLANDING 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 LIGHTS 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 ISSUES NOTED. (TC NR 20080102001) 2L72 4F4 FRTA21EA E15NE 20080225002522008022500252CE 2008 2 25 CA080102002 120080101G57533516505035 BRACKET BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE HARTZLHCD4N3HCD4N3A GL TE FLAPS WORN W K NONE O OTHER ININSP/MAINT 1 CA 6626 (CAN) FLAPS REMOVED TO INSPECT FLAP BRACKETS (HINGES) TO PREVENT A POSSIBLE FAILURE ( REFERENCE SDR 20071025007). BOTH OB FLAPS WERE WORN IN THE SAME LOCATION THAT FAILED OTHER AC. ON BOTH OB FLAPS, THE OB HINGE, IB BRACKETS P/N: 35165050-35 (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 20080102002) 1L72 4T4 T A24CE E4EA 5 CSTC 20080225002562008022500256EA 2008 2 25 CA080102006 120080101G5610NP13932114 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT BROKEN W O OTHER O OTHER CRCRUISE 1 CA (CAN) (RT WINDSHIELD SHATTERED IN FLIGHT). THE WINDSHIELD WAS REMOVED AND REPLACED. WINDSHIELD, (RT) P/N OFF: 601R33033-14 P/N ON: NP-139321-14 S/N OFF: 02277H7295 S/N ON: 07212H4821 (TC NR 20080102006) 2L72 4F4 FRTA21EA E15NE 20080225002632008022500263SW 2008 2 25 CA080103007 120080103G6720NAS130410 BOLT BELL 206001044 BELL 206 206L 1181522SW ALLSN 250C 250C20R2 GL T/R PEDAL BROKEN W K NONE O OTHER ININSP/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) 1G71 3U3 U H2SW E4CE 20080225002652008022500265EA 2008 2 25 CA080104001 120080103G2750855D10096 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS UNSERVICEABLE W O OTHER J WARNING INDICATION CRCRUISE 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 LANDING. TEMP AT ALTITUDE WAS -60 DEG. FERRIED BOTH BPSU`S REPLACED FLAPS FUNCTIONED CHECKED SER (804406 1/4/2008 06:57) (TC NR 20080104001) 2L72 4F4 FRTA21EA E15NE 20080319001712008031900171EA 2008 3 19 CA080104004 120080101G2750855D1009 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS FAILED W D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA 1480110343 (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 INSTALLED RT BPSU (S/N 172, TSN 17175, TSO 4879, CYCLES 3697) HAD TO BE REPLACED AS IT FAILED THE ELECTRICAL RIGGING. (TC NR 20080104004) 2L72 4F4 FRTA21EA E15NE 20080225002682008022500268SW 2008 2 25 CA080104005 120080104G6220206011101109 YOKE 206L1 BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL M/R HUB INCORRECT W K NONE O OTHER ININSP/MAINT 1 CA 10379135 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) 1G71 3U3 U H2SW E1GL 20080225002692008022500269NM 2008 2 25 CA080105002 120080102G2910992236H18697 SWITCH DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD SYSTEM BROKEN W O OTHER J WARNING INDICATION DEDESCENT 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 DROPS APPROXIMATELY 800-1000 PSI ON NR 1 HYD SYS. RUDDER PRESSURE REGULATOR REPLACED BUT WITH NO FIX. NR 1 HYD SYS BLED AND 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) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080225002712008022500271WP 2008 2 25 CA080105003 120080101G8011BC31510040 STARTER ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE INOPERATIVE W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 679 (CAN) ENGINE WOULD NOT START, STARTER NOT ENGAGING. SERVICEABLE STARTER INSTALLED, ENGINE STARTED WITH OUT FURTHER INCIDENT. (TC NR 20080105003) 1G71 3O3 O H11NM 1E4 20080319001732008031900173EA 2008 3 19 CA080106001 120080104G215078279015 ACM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE NR 1 SMOKE W C ABORTED TAKEOFF BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TOTAKEOFF 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. ABORTED 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 20080106001) 2L72 4F4 FRTA21EA E15NE 20080319001752008031900175EA 2008 3 19 CA080106003 120080103G2750855D1009 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS INOPERATIVE W K NONE J WARNING INDICATION ININSP/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) 2L72 4F4 FRTA21EA E15NE 20080319001782008031900178EA 2008 3 19 CA080106004 120080102G3260895001 PROXIMITY SENSOR CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C5 30050NE NLG MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 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 NOT LANDING OVERWEIGHT). TROUBLESHOOTING PINPOINTED TO THE WEIGHT OFF WHEELS NR 2 SENSOR (PX 11), BEING OFF RIGGING LIMITS. MAINT PERFORMED RE-RIGGING FOLLOWED BY A SUCCESSFUL GROUND TESTS AND AC RETURNED TO SERVICE. AIRFRAME HOURS=7855:04. CYCLES=3748. (TC NR 20080106004) 2L72 4F4 FRTA21EA E00063EN 20080225002722008022500272EU 2008 2 25 CA080107001 120080107G6410355A12004008 BLADE SNIAS 350 AS350B2 8680813EU LYC LTS101LTS101* NE TAIL ROTOR CRACKED W K NONE O OTHER ININSP/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 TRAILING EDGE CORNER APPROX .7500 OF AN INCH TO DEPART FROM TIP OF THE BLADE. THIS WAS FOUND ON BOTH BLADES ONE BLADE MORE SEVERE THAN THE OTHER. THERE WAS NO INDICATION OF A TAILROTOR IMPACT. (TC NR 20080107001) 1G71 3U3 U H9EU E5NE 20080225002732008022500273CE 2008 2 25 CA080107002 120080103G2497 BUSS BAR BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE HARTZLHCE4N HCE4N3 NE ELECTRICAL LOOSE W K NONE O OTHER ININSP/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. THIS BUSS BAR WAS ATTACHED ONLY AT ONE END AND WAS LOOSE. NOTE, THE SB ONLY REQUIRES INSPECTION FOR AN EXTRA BUSS BAR BETWEEN CB 327 AND 166. INSPECTION OF BB-1974 SHOWED NO EXTRANEOUS BUSS BARS INSTALLED. (TC NR 20080107002) 1L72 4T4 T A24CE E4EA 5 CP10NE 20080204001192008020400119CE 2008 2 4 CA080107003 120080107G32301018100327 TORQUE KNEE BEECH 200 B200 1152922CE PWA PT6 PT642A NE HARTZLHCB3T HCB3TN3 GL LT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE PERFORMING AN INSPECTION ON THE GEAR IT WAS NOTICED THAT GREASE WAS COMING FROM THE HORIZOTAL CRACK IN THE BOTTOM OF THE TORQUE KNEE. A NEW KNEE WAS ORDERED AND REPLACED. (TC NR 20080107003) 1L72 4T4 T A24CE E4EA 6 CP15EA 20080204001182008020400118NM 2008 2 4 CA080107004 120080102G6420A0311 BEARING ROBSINR22 R22BETA 7640110NM LYC O360 O360J2A 41514EA PITCH CONTROL ROUGH W K NONE O OTHER ININSP/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) 1G71 3O3 O H10WE E286 200805131 200805131 EU 2008 5 13 CA080108005 120080107G36109599021231 HOSE PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL BLEED AIR SYS CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 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. AC RETURNED TO BASE. FOUND BLEED AIR HOSE CRACKED. (TC NR 20080108005) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 200805141 200805141 EA 2008 5 14 CA080108006 120080108G5752215150622 SKIN CNDAIR 2151506180 CNDAIRCL215 CL2151A10 1900320EA PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE AILERON TAB CRACKED W K NONE O OTHER ININSP/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 BALANCE WEIGHT MOUNT ATTACHMENT FASTENER HOLES. THE REPLACEMENT GEAR TAB WAS INSPECTED AND FOUND CRACKED IN THE SAME LOCATION. THE CUSTOMER AND OEM HAVE BEEN INFORMED. (TC NR 20080108006) 2H72 4R3 RRTA14EA ATC14 6 CP871 20080204001172008020400117EA 2008 2 4 CA080108007 120080103G7603C6CE13151 RELEASE CABLE DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL BETA SYSTEM BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE RT POWER CONTROL WAS REPORTED STIFF. AFTER AN INSPECTION ON THIS AREA IT WAS NOTICED THE THE BETA RELEASE CABLE HAD BROKEN AND WAS CAUSING THE POWER CABLE TO BE STIFF. A NEW CABLE WAS PURCHASED AND CABLE WAS CHANGED. (TC NR 20080108007) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20080204001162008020400116WP 2008 2 4 CA080108009 120080108G7603B5642 LINK ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE THROTTLE DAMAGED W K NONE O OTHER ININSP/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 REMOVED AND INDEED IT WAS. THE LINK AND NEW WASHERS (SB-62) WERE INSTALLED AND NO OTHER ISSUES WERE NOTED. WHILE CONDUCTING 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) 1G71 3O3 O H11NM 1E4 20080204001152008020400115WP 2008 2 4 CA080109001 120080108G3260BZE67RNT DOWNLOCK SWITCH CVAC 340 340CVAC 242270AWP ALLSN 501D 501D13D 03004GL ALLSN A6441 A6441FN606 GL RT MLG INOPERATIVE W O OTHER N FALSE WARNING APAPPROACH 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) 2L72 4R4 T 6A6 E282 6 CP898 20080204001142008020400114NM 2008 2 4 CA080109002 120080104G3233NAS771236 BUSHING DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE MLG ACTUATOR MISSING W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) REMOVED NR2 MLG RETRACTION ACTUATOR FOR WORK CARD 2339 AND FOUND THE PICKUP FITTING MISSING (HAT) BUSHING. HOWEVER, THE RETRACTION ACTUATOR WAS ASSEMBLED TO FITTING AND IN SERVICE WITHOUT THIS BUSHING. THIS PLACED SEVERE STRESS ON ATTACHMENT HARDWARE AND FITTING DUE TO THE IMPROPER ASSY. NR2 MLG RETRACTION ACTUATOR FITTING REPLACED ALONG WITH ALL HARDWARE. NR2 MLG RETRACTION ACTUATOR REPLACED. RD8-54-1178 ACCOMPLISHED ALONG WITH NDT INSPECTION TO AFFECTED NACELLE STRUCTURE. MISSING BUSHING REFERENCE: IPC 54-40-00, FIG. 20, ITEM 410, P/N NAS77-12-36. (TC NR 20080109002) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080204001132008020400113NM 2008 2 4 CA080109004 120080108G3260H1010153 UPLOCK SWITCH BOEING727 727247 138408FNM PWA JT8 JT8D15 52051NE NLG FAULTED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) FLIGHT WAS DEPARTING AND THEN DURING THE TAKEOFF ROLL, THE CREW SELECTED THE LANDING GEAR UP. WHEN THE GEAR HAD CYCLED UP THERE REMAINED A RED NOSE GEAR UNSAFE LIGHT. THE CREW CYCLED THE LANDING GEAR 3 TIMES BEFORE THE UNSAFE LIGHT EVENTUALLY 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) 2L73 4F4 F A3WE E2EA 20080204001122008020400112NM 2008 2 4 CA080109005 120080105G2131 CIRCUIT BOARD DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE PRESS CONTROLLERBURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA 3000430004 60498 (CAN) THE CREW REPORTED A STRONG BURNING ELECTRICAL ODOR UPON ARRIVAL. MAINTENANCE FOUND A FAULTY PRESSURE CONTROLLER. FURTHER INVESTIGATION REVEALED THAT AN ELECTRONIC CIRCUIT BOARD INSIDE THE CONTROLLER HAD SOME BURN MARKS. THE CONTROLLER WAS REPLACED AND THE AIRCRAFT RELEASED INTO SERVICE. (TC NR 20080109005) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080204001112008020400111EA 2008 2 4 CA080109009 120080107G7740601509173 CONVERTER CNDAIRCL600 CL6002B16 1900305EA GE CF34 CF343A1 30068NE SIGNAL DATA FAULTY W EA ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CRCRUISE 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 IMMEDIATELY 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. CREW DISCUSSED ALTERNATE PLAN (DIVERTING), ITT STARTED AGAIN. KEPT REDUCING THRUST UNTIL WE HAD TO SHUTDOWN THE LT ENGINE 2L72 4F4 FRTA21EA E15NE 20080204001102008020400110EA 2008 2 4 CA080109011 120080106G5610NP13932110 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 5046 (CAN) THE RT WINDSHIELD CRACKED WHILE IN CRUISE. WINDSHIELD WAS REPLACED IAW AMM. (TC NR 20080109011) 2L72 4F RTA21EA 20080204001092008020400109EU 2008 2 4 CA080110001 120080108G2571L243M3810103 BATTERY BOX UROCOPEC135 EC135P1 8680990EU PWA PW206 PW206B 0 NE FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 98 (CAN) DURING A PREFLIGHT CHECK IT WAS NOTED THAT THE BATTERY TRAY WAS CRACKED. REPLACED WITH NEW PART. (TC NR 20080110001) 1G72 3U3 UO H88EU E42NE 20080331000372008033100037EA 2008 3 31 CA080110003 120080110G2797 CONNECTOR CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C5 30050NE TE FLAPS FAILED W C ABORTED TAKEOFF FJ FLT CONT AFFECTED WARNING INDICATION TOTAKEOFF 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) 2L72 4F4 FRTA21EA E00063EN 20080320000062008032000006EA 2008 3 20 CA080110006 120080105G2750860D10018 FCU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS FAULTED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 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 INCIDENT. MAINT T/S WAS CARRIED OUT AND THE LT AND RT BPSU’S WERE SWAPPED FOR T/S. SUSPECTED FAULTY FECU, FECU REPLACED, FUNCTION CHECK C/O AND TEST FLIGHT C/O SATISFACTORY. (TC NR 20080110006) 2L72 4F4 FRTA21EA E15NE 20080225002762008022500276NM 2008 2 25 CA080111001 120080110G561080260008 WINDSHIELD BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU COCKPIT BROKEN W BA EMER. DESCENT UNSCHED LANDING O OTHER CRCRUISE 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) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20080225002782008022500278SW 2008 2 25 CA080111002 120080107G575121993 HINGE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL AILERON CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1925 (CAN) ON INSPECTION, 4 CRACKS FOUND IN CORNERS (TC NR 20080111002) 1H71 3O3 O A21CE E286 5 NP874 20080306002052008030600205SW 2008 3 6 CA080111003 120080102G575121993 HINGE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL AILERON CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4718 (CAN) CRACK FOUND DURING SIRP INSP (TC NR 20080111003) 1H71 3O3 O A21CE E286 5 NP874 20080306002062008030600206SW 2008 3 6 CA080111004 120080109G6410212010750105 BLADE BELL BELL 205 205A1 1181414SW LYC T53 T5317BLYC 41616NE TAIL ROTOR DELAMINATED W A UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 CA 4047 AHW00877 (CAN) PILOT HEARD A MUFFED LOW POP SOUND, WITH NO UNUSUAL GAUGE, WARNING LIGHTS, OR VIBRATIONS. UPON DEPARTING FOR ANOTHER 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 INVESTIGATION OF THE T/R BLADE IT APPEARS THE DELAMINATING STARTED FROM A PREVIOUS REPAIR ALBEIT ON THE OTHER SIDE OF THE BLADE ACCORDING TO THE COMPONENT LOG CARD. THE AIR FLOW STARTED TO PEEL BACK THE SKIN AT THIS SPOT, AS THE PEELING PROGRESSED SKIN REMAINED INTACT UNTIL THE ADHESIVE STRENGTH OF THE GLUE WAS EXCEEDED AND WE SEE THE SECONDARY PEELING IB AND OB WHER1G71 4U4 U H1SW E17EA 20080306002072008030600207NE 2008 3 6 CA080111005 220080111G7421UREM38S SPARK PLUG PWA R985 R985AN14B 52008NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) (2) SEPARATE OCCASIONS NEW UREM38S SPARK PLUGS WERE REMOVED FROM THE PACKAGE AND FOUND TO HAVE CRACKED CERAMIC INSULATORS. TO VERIFY THE PLUGS WERE TESTED AND FOUND TO BE MISFIRING. THE CRACKING IN THE CERAMIC DOES NOT APPEAR TO BE SHIPPING OR MISHANDLING DAMAGE AS THERE IS EVIDENCE OF TRACKING IN THE CRACKS. (TC NR 20080111005) 3 R 5E1 20080320000072008032000007EA 2008 3 20 CA080112001 120080110G2420600591435 ADG CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE UNWANTED DEPLOY W A UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CLCLIMB 1 CA 1810718107 (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) 2L72 4F4 FRTA21EA E15NE 20080306002082008030600208NM 2008 3 6 CA080114001 120080109G3230483025 SEQUENCE VALVE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU LT MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 42 (CAN) AFTER TAKEOFF, LT MLG DOOR AMBER LIGHT REMAINED ON (FA CONFIRMED LT MLG DOOR OPEN). GEAR EXTENDED THEN L DOOR AMBER 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 SEQUENCE VALVE. (TC NR 20080114001) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20080306002092008030600209EU 2008 3 6 CA080114002 120080111G2160342B030000AM SWITCH AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE TEMP CONTROL INOPERATIVE W B EMER. DESCENT J WARNING INDICATION CRCRUISE 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) 2L72 4F4 FRTA28NM E29NE 20080306002102008030600210NM 2008 3 6 CA080114003 120080110G2421 SENSOR LUCAS 31708001A DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NR 2 A/C GEN OPEN W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 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 SPEED SENSOR WAS OPEN. THE UNIT SENT BACK TO THE SHOP REPLACED THE SPEED SENSOR, UNIT REINSTALLED ON THE A/C AND FOUND SERVICEABLE. A/C DEPARTED ON JAN 14-2008 AND NO OTHER REPORT REPORTED. (TC NR 20080114003) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080306002112008030600211NM 2008 3 6 CA080115001 120080112G3231AR2674 LATCH BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU MLG DOOR BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) NOSE LANDING GEAR ALTERNATE RELEASE DOOR FAILS TO OPEN DURING PRE FLIGHT CHECK. ALTERNATE EXTENSION DOOR LATCH BROKEN CAUSING DOOR TO STICK IN CLOSED POSITION. REPLACED LATCH ALL CHECKS OK. (TC NR 20080115001) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20080306002122008030600212NM 2008 3 6 CA080115002 120080113G29136617303 PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU HYD SYSTEM FAILED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/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 REPLACED AND SYSTEM FLUSHED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20080115002) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20080306002132008030600213EU 2008 3 6 CA080115003 120080107G2710KA6D8X50 ROD END DIAMONDA42 DA42 2990004EU THIELTTAE125TAE12501 59300EU AT AILERON BENT W O OTHER F FLT CONT AFFECTED NRNOT 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 BENT WHERE THE CONTROL ROD IS ATTACHED TO THE BELLCRANK AT THE MOST OB POINT. NEW STRAIGHT FITTINGS WERE INSTALLED BUT THIS CAUSED THE AILERON SYS TO BIND. THERE IS NO REFERENCE IN THE IPC OR MM REFERENCING BENT ROD ENDS AS BOTH ROD ENDS ON THE CONTROL ROD HAVE THE SAME PN. (TC NR 20080115003) 1L72 3I3 BRTA57CE E00069EN 20080306002142008030600214NM 2008 3 6 CA080115004 120080112G333030180B23D1683 LIGHT DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE CARGO BAY SHORTED W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING FLIGHT, THE CREW REPORTED (TO MOC) THAT THEY HAD THE (SMOKE) WARNING ILLUMINATED. THEY WERE TOLD TO DO A TURNBACK AND RETURN TO AIRPORT WHERE MAINT STAFF MET THE AIRCRAFT. DURING THE INVESTIGATION, MAINT PERSONNEL FOUND THE SIDEWALL BAGGAGE DOOR LIGHT WIRE HAD COME OFF INTERNALLY AND WAS ARCING ON ITS CASE. LIGHT ASSY REPLACED AND ENGINE RUNS CARRIED OUT. (TC NR 20080115004) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080306002152008030600215EU 2008 3 6 CA080115005 120080114G2710DSPR116X058 PUSHROD DIAMONDA42 DA42 2990004EU THIELTTAE125TAE12502114 EU AILERON BENT W K NONE O OTHER ININSP/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 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 20080115005) 1L72 3I3 BRTA57CE E00069EN 20080306002162008030600216EU 2008 3 6 CA080115006 120080114G2710DSPR116X058 PUSHROD DIAMONDA42 DA42 2990004EU THIELTTAE125TAE12501 59300EU AILERON BENT W K NONE O OTHER ININSP/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 OUR AC. WE 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 MAINTENANCE MANUAL. (TC NR 20080115006) 1L72 3I3 BRTA57CE E00069EN 20080306002172008030600217NM 2008 3 6 CA080115007 120080115G2710129307 PCU BOEING727 727247 138408FNM PWA JT8 JT8D15 52051NE AILERON FROZEN W D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA 131472175 (CAN) THE AC ARRIVED AT DESTINATION AND WAS ON A TURN-AROUND WHEN THE CREW NOTICED ON TAXI OUT, THAT THE AILERONS HAD FROZEN UP. THE AC RETURNED TO THE RAMP WHERE MAINT INSPECTED THE SYS. IT WAS DETERMINED THAT THE AILERON POWER CONTROL UNIT HAD FROZEN UP. HEAT WAS PLACED ON THE PCU AND THE CONTROLS FREED UP. THE CONTROL UNIT WAS FLUSHED OF ALL WATER CONTAMINATES AND LUBRICATED. HEAT WAS APPLIED TO THE PCU FOR APPROX (4) HOURS. IT HAD BEEN NOTED BY FLIGHT CREW THAT THE AC HAD 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) 2L73 4F4 F A3WE E2EA 20080306002182008030600218EU 2008 3 6 CA080115008 120080114G2710DSPR116X058 CONTROL ROD DIAMONDA42 DA42 2990004EU THIELTTAE125TAE12501 59300EU AILERON BENT W K NONE O OTHER ININSP/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 OUR 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) 1L72 3I3 BRTA57CE E00069EN 20080306002192008030600219EU 2008 3 6 CA080115009 120080110G6797 GROUND WIRE SNIAS 350 AS350B 8680801EU LYC LTS101LTS101600A3 41560NE HYD SERVO FAILED W A UNSCHED LANDING F FLT CONT AFFECTED APAPPROACH 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 FAILURE, IE. HORN AND LIGHT. FROM THE HOVER THEY ACCELERATED TO 60 KNOTS, AT WHICH TIME THE HYD ON/OFF SWITCH ON THE COLLECTIVE WAS SELECTED TO THE HYD OFF POSITION, AND THEY MAINTAINED 60 KNOTS THROUGHOUT THE CIRCUIT. ON DOWNWIND FOR EAST LIMA TAXIWAY AT 500 FEET ABOVE GROUND. THE PILOT IN COMMAND WAS INFORMED TO WIDEN OUT HIS CIRCUIT SO THAT HE WOULD NOT HAV1G71 3U3 U H9EU E5NE 20080320000092008032000009EA 2008 3 20 CA080115010 120080113G5250 LATCH CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE LAVATORY DOOR STUCK W O OTHER O OTHER APAPPROACH 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 PASSENGER 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) 2L72 4F4 FRTA21EA E15NE 20080306002212008030600221NE 2008 3 6 CA080115012 220080111G7240 COMBUST CHAMBER SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B 60037NE ENGINE FOD W K NONE O OTHER ININSP/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 FROM AN INNER COOLING HOLE IN THE COMBUSTION CHAMBER. AFTER DISCUSSION WITH MFG, THE AC WAS REMOVED AND AN ENGINE TEARDOWN WAS CONDUCTED. THE ITEMS REMOVED AND ENGINE REASSEMBLED AND TESTED ON THE A/C. THE OBJECT COULD NOT BE IDENTIFIED AT THIS LEVEL AND WAS TAKEN BY THE MFG SERVICE REP FOR TESTING. HAVE A FEW BORESCOPE IMAGES AVAILABLE IF REQUIRED. (TC NR 20080115012) 1G71 3U3 U H9EU E00054EN 20080520 CE 2008 5 20 CA080116001 120080115G53404552803060003 FITTING 45528030040 LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP ACTUATOR CRACKED W K NONE O OTHER ININSP/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 20080116001) 2L72 4F4 FRTT00008WIE6WE 20080520 EU 2008 5 20 CA080116002 120080109G32305322012289 DRAG LINK PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL NLG CRACKED W L ABORTED APPROACH J WARNING INDICATION DEDESCENT 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. THERE 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 REST OF THE PC-12S IN THE FLEET WERE CHECKED AND NO OTHER DRAG LINKS WERE CRACKED. THE LINK WAS REPLACED, SWINGS WERE COMPLETED AND THE AC WAS RETURNED TO SERVICE. (TC NR 20080116002) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20080306002242008030600224CE 2008 3 6 CA080116007 120080112G28203032791 LINE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL LT NACELLE CHAFED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) FUEL FLOW INDICATION LINE FOUND CHAFED AND LEAKING. NEW LINE INSTALLED. (TC NR 20080116007) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20080306002262008030600226CE 2008 3 6 CA080116009 120080108G760311452411411 BELLCRANK BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE POWER LEVER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE RT POWER LEVER BELLCRANK LOCATED IN THE BOTTOM OF THE PEDESTAL WAS REPLACED DUE TO WEAR. AFTER REMOVAL THE PART WAS FOUND TO BE CRACKED. (TC NR 20080116009) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20080306002312008030600231NE 2008 3 6 CA080116014 220080106G7310 FUEL SYS CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ENGINE LOW PRESSURE W D RETURN TO BLOCK XJ ENGINE FLAMEOUT WARNING INDICATION TXTAXI/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 ENGINE SHUT ITSELF DOWN. ENGINE RESTARTS WERE UNSUCCESSFUL. THE FUEL FLOW DIVIDER WAS REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20080116014) 1L72 4F4 F A22CE E1NE 20080306002322008030600232EA 2008 3 6 CA080116015 220080104G7250 TURBINE BLADES BELL 412 412 1182202SW PWA PT6T PT6T3 52045EA ENGINE FRACTURED W A UNSCHED LANDING ERJVIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION HOHOVERING 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 ESTABLISHED (TC NR 20080116015) 1G72 4U4 U H4SW E22EA 20080306002342008030600234EA 2008 3 6 CA080116017 120080115G321315101103 HOUSING DHAV DHC7 DHC7102 2802708EA PWA PT6 PT6A50 52043EA HAMSTD24PF 24PF305 GL STRUT CRACKED W K NONE O OTHER ININSP/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 FWD 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, THIS GEAR HAD 44 528 LANDINGS SINCE NEW AND 5925 LANDINGS SINCE INSPECTION. THE HOUSING WILL BE REPLACED. (TC NR 20080116017) 2H74 4T4 T A20EA E4EA 6 CP1NE 20080324004282008032400428EA 2008 3 24 CA080116020 220080109G7200 ENGINE PIPER PA46 PA46350P 7104602SO PWA PT6 PT6* 52043EA MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING BM SMOKE/FUMES/ODORS/SPARKS OVER TEMP CRCRUISE 1 CA RR0005 (CAN) PILOT REPORTED ENGINE TROUBLE AND ATTEMPTED TO RETURN TO BASE. ENGINE WAS SHUTDOWN BY THE PILOT, AND AC LANDED SHORT OF THE RUNWAY CAUSING SUBSTANTIAL DAMAGE TO THE AIRFRAME. INITIAL INVESTIGATION INDICATES NO OBVIOUS GAS PATH OR TURBINE BLADE DAMAGE, HOWEVER NO OIL WAS VISIBLE ON THE DIPSTICK. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080116020) 1L71 3O3 TRTA25SO E2NE 20080324004292008032400429NE 2008 3 24 CA080116021 220080109G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE POWER LOSS W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 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 SEIZED PROP SHAFT ROTOR. THE ENGINE HAS BEEN IMPOUNDED BY THE AUTHORITIES AND WILL BE INVESTIGATED IN THE MFG FACILITY. UPDATES WILL BE PROVIDED IN DUE COURSE. (TC NR 20080116021) 1H71 3T3 T A37CE E4EA 20080324004312008032400431 2008 3 24 CA080116022 420080109G6122 MOUNT BEECH 95 D95A 1153408CE LYC O360 IO360B1B 41514EA HARTZLHCC2Y HCC2YK2 GL GOVERNOR MISMANUFACTURED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA L1832351A (CAN) AFTER ENGINE REPLACEMENT FOR OVERHAUL A PRELIMINARY GROUND RUN WAS CARRIED OUT. IT WAS FOUND THAT THE PROPELLER WOULD 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 CONTROL SYS FUNCTIONED NORMALLY (TC NR 20080116022) 1L72 3O3 O 3A16 1E10 5 CP920 20080324004322008032400432EA 2008 3 24 CA080116023 220080111G85207106403 CRANKCASE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA NR 1 ENGINE CRACKED W K NONE O OTHER ININSP/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 CYL REMOVED FOR DETAILED INSP AND POSSIBLE REPLACEMENT. UPON FURTHER INSP MAINT FOUND AN APPROX 4 INCH CRACK, STARTING FROM 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) 1L72 3O3 O A20SO E14EA 20080306002362008030600236EA 2008 3 6 CA080116024 120080113G326016868101 PROXIMITY SWITCHMESSIER CNDAIRCL604 CL604 1900301EA GE CF34 CF343B 30069NE NLG MISINSTALLED W B EMER. DESCENT N FALSE WARNING APAPPROACH 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 LOW APPROACH WAS CONDUCTED AT AIRPORT TO VISUALLY CHECK NOSE GEAR POSITION. GEAR APPEARED DOWN. EMERGENCY DECLARED. FOLLOWED BY AN UNEVENTFUL LANDING. THE AC WAS PUT IN QUARANTINE FOR TEST ON GROUND AND FINDING OF THE ROOT CAUSE. AFTER DEPLOYMENT TEST ON LANDING GEAR AND FUNCTIONAL TEST ON PSEU THE PROBLEM WAS DISCOVERED. THE PROBLEM WAS AN INAPPROPRIATE 2L72 4F4 FRTA21EA E15NE 20080331000392008033100039NE 2008 3 31 CA080117001 220080110G7200 ENGINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE LEFT FLAMED OUT W A UNSCHED LANDING X ENGINE FLAMEOUT CRCRUISE 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. CHECKED 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. 2L72 4F4 FRTA21EA E15NE 20080306002372008030600237SW 2008 3 6 CA080117002 120080117G6420 BEARING BELL BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE T/R HUB UNSERVICEABLE W K NONE O OTHER ININSP/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) 1G71 4U4 U H1SW E17EA 20080306002382008030600238EU 2008 3 6 CA080117003 120080111G2821571712A BYPASS VALVE SNIAS 350 AS350BA 8680817EU LYC LTS101LTS101600A2 41560NE FUEL SYSTEM CRACKED W K NONE K FLUID LOSS ININSP/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 THE 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 DAY WITH THIS FUEL LEAK. THE VALVE ASSY WAS REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20080117003) 1G71 3U3 UNCH9EU E5NE 20080324004342008032400434NM 2008 3 24 CA080117004 120080115G5330143A321220 SKIN BOEING737 737800* NM BS 480 S21L DAMAGED W K NONE O OTHER ININSP/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. 2L72 4F RTA16WE 20080325000012008032500001WP 2008 3 25 CA080117005 220080111G72618941171 ADAPTER SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE ENG OIL FILTER CRACKED W K NONE KJ FLUID LOSS WARNING INDICATION ININSP/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. 2L72 4T4 TRTA8SW E4WE 5 CP10NE 20080306002392008030600239NE 2008 3 6 CA080117006 120080116G792128E252 THERMOSTAT SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL NR1 POSITION UNSERVICEABLE W E ENGINE SHUTDOWN J WARNING INDICATION HOHOVERING 1 CA (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMP BEGAN TO RISE TO LIMIT. (TC NR 20080117006) 1G72 3U3 U H1NE E1GL 20080320000102008032000010EA 2008 3 20 CA080117007 220080115G7200 ENGINE BEECH 99 99 1154002CE PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL LEFT FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 119014605 PCE22135 (CAN) WHILE DOING PILOT TRAINING, THE LT OIL PRESSURE WARNING LIGHT CAME ON. PILOTS LOOKED DOWN AT OIL PRESSURE GAUGE, THE PRESSURE WAS DROPPING SO THEY SHUTDOWN THE ENGINE AND FEATHERED THE PROP. THEY RETURN TO BASE. ENGINE REMOVED FOR FURTHER INSPECTION. (TC NR 20080117007) 1L72 3T3 T A14CE E4EA 6 CP15EA 20080306002402008030600240CE 2008 3 6 CA080117008 120080114G32301158200381 SPROCKET BEECH 99 99 1154002CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL MLG WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSP OF THE NLG RETRACT MECHANISM CHAIN FOR TENSION AND LUBRICATION, MAINT NOTED THE DUAL LINK CHAIN WAS ONLY RUNNING ON ONE LENGTH OF CHAIN RATHER THAN (2). AC WAS INSPECTED MORE CLOSLEY AND THE BRAZE/SPROCKET ASSY WHICH IS INTERMEDIATE BETWEEN LANDING GEAR MOTOR AND RETRACT ACTUATOR FOR THE NOSE GEAR WAS FOUND MISALIGNED AND DISPLACED. UPON REMOVAL 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 CAUSED THE DUAL LINK CHAIN TO SKIP OVER ONE SPROCKET AND ONLY UTILIZE HALF OF THE CHAIN FOR GEAR RETRACTION AND EXTENSION.1L72 3T4 T A14CE E4EA 6 CP15EA 20080220000152008022000015EA 2008 2 20 CA080117010 120080116G2750855D1009 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS FAILED W O OTHER J WARNING INDICATION DEDESCENT 1 CA 1301713017 (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 UNIT (BPSU) WAS REPLACED AND RIGGED. A SUCCESSFUL FLIGHT TEST WAS COMPLETED AND THE AC RETURNED INTO SERVICE. THE UNIT HAS ACCUMULATED 30:20 FLIGHT HOURS SINCE REPAIR. (TC NR 20080117010) 2L72 4F4 FRTA21EA E15NE 20080220000162008022000016EA 2008 2 20 CA080117011 120080116G5610601R3303319 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT FAILED W O OTHER O OTHER DEDESCENT 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) 2L72 4F4 FRTA21EA E15NE 20080220000172008022000017EA 2008 2 20 CA080118000 120080116G5610NP1393216 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF343B 30069NE COCKPIT FAILED W O OTHER O OTHER DEDESCENT 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) 2L72 4F4 FRTA21EA E15NE 20080306002412008030600241SW 2008 3 6 CA080118001 120080105G6310206040230019 FREEWHEEL UNIT BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL MAIN ROTOR LEAKING W O OTHER K FLUID LOSS ININSP/MAINT 1 CA 5 (CAN) AFTER FLIGHT THE FREEWHEEL ASSY WAS DISCOVERED LEAKING FROM THE FWD HSG CAP. FREEWHEEL ASSY CHANGED, LEAK CHECK CARRIED OUT SERVICEABLE. (TC NR 20080118001) 1G71 3U3 U H2SW E4CE 20080306002422008030600242EU 2008 3 6 CA080118002 120080118G2571 BATTERY BOX UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE FUSELAGE BROKEN W K NONE O OTHER ININSP/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) 1G72 3U3 UNCR0001RD E34NE 20080220000182008022000018EA 2008 2 20 CA080118003 120080115G2420820465 ADG CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE UNWANTED DEPLOY W O OTHER H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA 1668716687 (CAN) WHILE AC WAS IN CRUISE AT 30000 FT, ADG DEPLOYED UN-COMMANDED. ALL ELECTRICAL SYSTEMS WERE POWERED. TRIED SWITCHING BACK TO IDG POWER. ADG WOULD NOT SWITCH OVER. MAINTENANCE REPLACED ADG AUTO DEPLOYMENT CONTROLLER AND ADG RESTORE PUMP. (TC NR 20080118003) 2L72 4F4 FRTA21EA E15NE 20080306002432008030600243NE 2008 3 6 CA080119001 220080118G731415473 PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYS LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 797 797 (CAN) FUEL PUMP LEAKING OIL FROM DRAIN LINE. PUMP REMOVED AND NEW PUMP INSTALLED. DEFECT RECTIFIED. (TC NR 20080119001) 1G71 3O3 O H11NM 1E4 20080220000192008022000019EA 2008 2 20 CA080121001 120080116G5610NP1393219 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE COCKPIT CRACKED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 1258812588 (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 CONTROLLER PN 1659-1 WAS ALSO REPLACED. (TC NR 20080121001) 2L72 4F4 FRTA21EA E15NE 20080220000202008022000020EA 2008 2 20 CA080121002 120080120G27505275102 FCU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE TE FLAPS DEFECTIVE W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION NRNOT REPORTED 1 CA (CAN) FLAPS FAILED ON INITIAL SELECTION FROM 0 TO 8 DEGREES JUST AFTER PUSHBACK FOR HEADSTART FLIGHT. OAT WAS -29 C OVERNIGHT. MAINTENANCE GOT CODES FROM FECU, CLEARED FAULT AND RESET FLAPS. FLAPS FUNCTION CHECKED SERVICEABLE, BUT DUE TO RECENT HISTORY IT WAS DECIDED TO FERRY THE AC FOR FURTHER TROUBLESHOOTING. TROUBLESHOOTING IS UNDER WAY AND INFORMATION WILL BE UPDATED AS SOON AS IS AVAILABLE. (TC NR 20080121002) 2L72 4F4 FRTA21EA E15NE 20080325000022008032500002 2008 3 25 CA080121003 420080102G3497 WIRE BOEING737 737217 1384464NM PWA JT8 JT8D17A 52049NE TAWS COMPUTER INOPERATIVE W O OTHER N FALSE WARNING APAPPROACH 1 CA (CAN) TAIL 523 ON JAN 2ND APPROACH BACK COURSE ON RWY 15 YELLOWKNIFE 1040FT ASL 350FT AGL LEVEL FLIGHT 140K IN THIS CASE THE FLIGHT CREW EXPERIENCED A TAWS GENERATED A PICTORIAL DISPLAYED IMPACT WARNING. THE CREW WAS IN VISUAL CONDITIONS AND SAW NO DANGER OF IMPACT. THE AC LANDING WITHOUT FURTHER INCIDENT. IN THE FOLLOWING WEEKS, AC EQUIPPED WITH THE UNIVERSAL 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 RELEASED AND FORWARDED. ATTEMPTS TO LOAD THE NEW DATA BASE INTO THE TAWS UNITS FAILED DUE TO A COMMUNICATION PROBLEM BETWEEN2L72 4F4 F A16WE E2EA 20080220000212008022000021EU 2008 2 20 CA080121004 120080118G7820L24266710000 BAFFLE ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA MUHBR MTV MTV9* EU EXHAUST CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) INTERNAL BAFFLE ATTACH WELD WAS FOUND CRACKED DURING A 100 HOUR INSPECTION. (TC NR 20080121004) 1L71 3O3 O0 A76EU 1E10 5 CP24NE 20080220000222008022000022EU 2008 2 20 CA080121005 120080118G6230350A37000402 GUIDE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE SWASHPLATE WORN W K NONE O OTHER ININSP/MAINT 1 CA 602 (CAN) DURING A SCHEDULED 100 HOUR INSPECTION THE COLLECTIVE LEVER WAS RAISED TO EXAMINE THE SWASHPLATE GUIDE. IT WAS DISCOVERED THAT THE SELF ADHESIVE TAPE APPLIED TO THE GUIDE WAS BUNCHED UP BETWEEN THE ROTATING SWASHPLATE AND THE SWASHPLATE GUIDE. THE ROTATING SWASHPLATE CONTACTED THE SWASHPLATE GUIDE LEAVING LIGHT WEAR MARKS AROUND THE CIRCUMFERENCE. THE SWASHPLATE GUIDE WAS REPLACED AND WILL BE SENT TO THE MFG FOR EVALUATION AND SERVICEABILITY CHECK. (TC NR 20080121005) 1G71 3U3 U H9EU E19EU 20080220000232008022000023NM 2008 2 20 CA080121007 120080116G2436 VOLT REGULATOR BOEING727 727225 1384077NM PWA JT8 JT8D15 52051NE ODOR W O OTHER BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING FLIGHT CREW SHUTDOWN CHECKLIST, ON APU POWER, SMOKE ALARM SOUNDED IN THE AC LAVATORY. LAVATORY INSP REVEALED SOME SMOKE. ALARM SILENCED WHILE INSPECTING THE LAVATORY AREA. AFTER APPROXIMATELY 30 SECONDS, THE ALARM SOUNDED AGAIN, AND THE AC POWERED DOWN. MAINT INSPECTED THE LWR E/E COMPARTMENT AND FOUND SUBSTANTIAL AMOUNT OF SMOKE WITH AN ELECTRICAL BURNING ODOR. FIRE DEPARTMENT WAS CALLED BY THE FLIGHT CREW. MAINT DISCONNECTED THE MAIN AC BATTERY AND DISCONNECTED 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 R2L73 4F4 F A3WE E2EA 20080220000242008022000024WP 2008 2 20 CA080121008 120080109G6310369D25351DSN SPRAG CLUTCH HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL MAIN ROTOR CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 958 (CAN) DURING 300 HOUR INSPECTION PART WAS FOUND TO HAVE PITTING ON SEVERAL ELEMENTS. SPRAG CLUTCH REPLACED. (TC NR 20080121008) 1G71 3U3 U H3WE E4CE 20080220000272008022000027SO 2008 2 20 CA080121009 120080108G2421ALU8421R ALTERNATOR PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCC4Y HCC4YR2 GL INOPERATIVE W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA 278 (CAN) IN CRUISE, AC STARTED TO LOOSE ELECTRICAL POWER. FIRST INDICATION, THE TRANSPONDER FAILED. AC THEN RETURNED TO AIRPORT. BOTH LT AND RT ALTERNATOR FAIL INDICATOR LIGHTS REMAINED OUT DURING THE FLIGHT. UPON INSP NEITHER ALTERNATOR WAS CHARGING THE SYS. THE ONLY POWER SUPPLY WAS THE AC BATTERY. THE LT ALTERNATOR WAS FOUND TO BE UNSERVICEABLE. THE RT ALTERNATOR, BECAUSE OF THE ADDED ELECTRICAL LOAD PUT ON IT, CAUSED THE ALTERNATOR BELT TO SLIP ON THE PULLEY, MAKING THE ALTERNATOR INOPERATIVE. ALL AC RADIOS, NECESSARY LIGHTS AND DEICING HEAT WAS ON AT THIS TIME. (TC NR 20080121009) 1L72 3O3 O A20SO E14EA 5 CP52GL 20080220000282008022000028EA 2008 2 20 CA080121011 220080104G7414BL600646201 MAGNETO ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA RT MAGNETO FAILED W K NONE O OTHER ININSP/MAINT 1 CA 890 (CAN) DURING MAGNETO CHECK PRIOR TO FLIGHT, THE RT MAGNETO FAILED. MAGNETO REPLACED AND CHECKED SERVICEABLE. (TC NR 20080121011) 1G71 3O3 O H11NM E295 20080220000292008022000029NE 2008 2 20 CA080122001 220080108G7414BL600646201 MAGNETO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE RT UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA 767 (CAN) RT MAGNETO FOUND UNSERVICEABLE ON PREFLIGHT. MAGNETO CHANGED, GROUND RUN AND LEAK CHECK CARRIED OUT SERVICEABLE. (TC NR 20080122001) 1G71 3O3 O H11NM 1E4 20080220000302008022000030NM 2008 2 20 CA080122002 120080105G5320 WEB DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2452 (CAN) DURING MAINT ROUTINE INSP, THE NOSE LANDING GEAR GROUND LOCK MECHANISM WAS FOUND HARD TO OPERATE. FURTHER INVESTIGATION REVEALED THAT THE FLOOR WEB AT ZONE 112, STA X97 WAS CRACKED CAUSING THE GROUND LOCK LEVER TO CONTACT THE PIVOT TUBE ARM. THE CRACKED AREA WAS REPAIRED IN AUGUST 2006 IAW RD8-53-0638. THE AC HAS ACCUMULATED 2451:46 HOURS AND 3379 CYCLES SINCE REPAIRED. THE OLD PATCH WAS REPLACED IAW THE ABOVE RD AND THE AC WAS RELEASED INTO SERVICE. (TC NR 20080122002) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081104 CE 2008 11 4 CA080122003 120080121G5350 STRUCTURE CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL TAIL CONE CRACKED W K NONE O OTHER ININSP/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 THIS 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 20080122003) 1H71 3O3 O A4CE E5CE 5 CP47GL 20080220000312008022000031SO 2008 2 20 CA080122005 120080111G3213753227 YOKE PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA HARTZLHCE2Y HCE2YK2 GL MLG CRACKED W K NONE O OTHER ININSP/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 EDGE 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) 1L72 3O3 O 1A10 1E4 5 CP9EA 20080220000322008022000032GL 2008 2 20 CA080122007 320080122G61103GFR34C703 PROPELLER CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL LEAKING W O OTHER K FLUID LOSS TXTAXI/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) 1H71 3T3 T A37CE E4EA 5 CP60GL 20080220000332008022000033NE 2008 2 20 CA080122008 220080118G8550 LINE DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN1 52008NE HARTZLHCB3R HCB3R302 GL OIL SYSTEM OBSTRUCTED W K NONE O OTHER ININSP/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 CONTAINERS USED TO REPLENISH THE ENGINE OIL. THERE WAS POOR MAINTENANCE PRACTICE WHEN OPENING THESE CONTAINERS TO POUR THE OIL IN THE TANK IN THE AC, THE CAPS WERE NOT FULLY REMOVED FROM THE CONTAINERS. THERE WERE NUMEROUS ITEMS IN THE OIL SYS AND THIS HAS THE POTENTIAL TO RESTRICT THE FLOW OF THE OIL RESULTING IN SHUTDOWN OF THE ENGINE. CARE MUST BE TAKEN WHEN CARRYING OUT THIS TASK AND THIS NEEDS TO BE COMMUNICATED TO ANYONE WHO IS SERVICING THESE AC. (TC NR 20080122008) 1H71 3R3 RRCA806 5E1 5 CP28EA 20080220000342008022000034 2008 2 20 CA080122009 420080120G345710706 ANTENNA BEECH B300 B300 1159232CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL GPS CORRODED W K NONE O OTHER ININSP/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 ANTENNA WAS LIKELY INSTALLED AT THE FACTORY (2001) THERE WAS NO SEALANT UNDER THE ANTENNA AND NO GASKET MATERIAL EITHER. THERE 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) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20080220000362008022000036SW 2008 2 20 CA080122010 120080111G6230206010447109 BEARING BELL 206 206L4 1182110SW SWASHPLATE ASSY CHAFED W K NONE O OTHER ININSP/MAINT 1 CA 19193275 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 ROTATING 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) 1G71 3U NCH2SW 20080220000392008022000039SO 2008 2 20 CA080123001 220080119G8530 CYLINDER CESSNA150 150H 2071818CE CONT O200 O200A 17020SO MCAULY1A101 1A101DCM GL NR 4 LEAKING W K NONE O OTHER ININSP/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) 1H71 3O3 O 3A19 E252 5 NP918 20080220000402008022000040SW 2008 2 20 CA080123002 120080122G322099353 COLLAR GULSTM690TP 690 0141720SW GARRTTTPE331TPE3315251K NM HARTZLHCB3T HCB3TN5 GL NLG WORN W O OTHER J WARNING INDICATION LDLANDING 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 1H72 3T4 T 2A4 E2WE 6 CP15EA 20081229 CE 2008 12 29 CA080123003 120080123G32450923150 TUBE CESSNA425 425 2076018CE PWA PT6 PT6A112 52043NE MCAULY4HFR344HFR34C762 NE NLG TIRE DAMAGED W O OTHER O OTHER TXTAXI/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 WHEEL 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. 1L72 3T3 TRTA7CE E4EA 6 C3PNE 20080220000432008022000043SW 2008 2 20 CA080123007 120080115G281071494R FUEL TANK BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL OUTBOARD CRACKED W K NONE KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS ININSP/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) 1H71 3O3 O A21CE E286 5 NP874 20080220000442008022000044SW 2008 2 20 CA080123008 120080115G281071493R FUEL TANK BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL INBOARD CRACKED W K NONE KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS ININSP/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 INTERCONNECT WELD. (TC NR 20080123008) 1H71 3O3 O A21CE E286 5 NP874 20080220000562008022000056NM 2008 2 20 CA080124001 120080123G3297471515 WIRE HARNESS BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NR 2 WOW FAULTY W A UNSCHED LANDING N FALSE WARNING CLCLIMB 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) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20080220000572008022000057NM 2008 2 20 CA080124002 120080124G2910 SWIVEL BOEING727 727247 138408FNM PWA JT8 JT8D15 52051NE NR 6 SLAT LEAKING W O OTHER KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 8455 709 (CAN) AC WAS DISPATCHED AND DURING CRUISE FLIGHT, THE FLIGHT ENGINEER NOTICED THAT THE (A) SYS HYDRAULICS INDICATED .1250 OF A TANK REMAINING. THE CREW DECIDED TO DECLARE AN EMERGENCY AND THE LANDING GEAR NEEDED TO BE CRANKED DOWN. THE AC LANDED 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) 2L73 4F4 F A3WE E2EA 20080220000592008022000059SW 2008 2 20 CA080124003 120080117G3210D212664201 CROSSTUBE BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE LG CRACKED W K NONE O OTHER ININSP/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 FOLLOWS 300/600 HR INSP CYCLE. CROSSTUBE WAS 60.7 FROM 300 HR INSP, AND 360.7 FROM THE 600 HR. CROSSTUBE WAS CHECKED FOR EXCESSIVE 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 FROM 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) 1G71 4U4 U H1SW E17EA 20080220000602008022000060WP 2008 2 20 CA080124005 220080122G72608937373 NUT SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE GEAR SHAFT BACKED OUT W K NONE J WARNING INDICATION ININSP/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 THERE WAS METAL ON THE CHIP DETECTOR OF ENGINE P-54121. AT THAT TIME THE ENGINE WAS FORWARDED TO THE ENGINE SHOP FOR FURTHER INSP. THE ENGINE WAS DISMANTLED TO FIND THAT THE HIGH SPEED PINION NUT (HSP) PN 893737-3, WAS STARTING TO BACK OFF FROM 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 COUL2L72 4T4 TRTA8SW E4WE 5 CP10NE 20081104 SW 2008 11 4 CA080124006 120080123G79218945682 LINE FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE OIL COOLER CHAFED W K NONE K FLUID LOSS ININSP/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) 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081104 SW 2008 11 4 CA080124007 120080123G79218945682 LINE FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE OIL COOLER CHAFED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) LINE FOUND LEAKING BETWEEN OIL COOLER TO FUEL HEATER. THE CHAFE WAS FOUND BY THE STEEL IDENTIFIER ON THE LINE. LINE WAS REPLACED AND AREA WAS CORRECTED SO THAT THE NEW LINE WOULD NOT CHAFE IN THE FUTURE. (TC NR 20080124007) 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081104 WP 2008 11 4 CA080124008 220080121G7313310323259 FUEL NOZZLE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE ENGINE CRACKED W K NONE O OTHER ININSP/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) 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20081104 WP 2008 11 4 CA080124009 220080120G7310310323259 FUEL NOZZLE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FUEL NOZZLE FOUND CRACKED ON SECONDARY MANIFOLD DURING SCHEDULED NOZZLE CHANGE IN THE AREA THAT MFG SAYS TO INSPECT FOR CRACKS. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20080220000612008022000061EA 2008 2 20 CA080124011 120080124G5330 SKIN PANEL DHAV DHC7 DHC7102 2802708EA FUSELAGE CORRODED W K NONE O OTHER ININSP/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 MANDATED BY ADCF-98-03 AND IS TO BE CARRIED OUT IAW THE AC CORROSION PREVENTION AND CONTROL MANUAL (PSM 1-7-5). NO INFORMATION IS AVAILABLE TO KNOW IF THE THRESHOLD OR REPEAT CORROSION INSPECTIONS WERE COMPLIED WITH. WHILE CONDUCTING THE 3-YEAR 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 AREAS OF DISBOND WERE FOUND ON THE FUSELAGE SKIN PANELS, HORIZONTAL STABILIZER SKIN PANELS AND WING PANELS. IN ADDITION, ARE2H74 4T A20EA 20080220000642008022000064SO 2008 2 20 CA080124013 220080109G8530636242 GUIDE CONT CONT O550 IO550D 17042SO EXHAUST WORN W K NONE O OTHER ININSP/MAINT 1 CA 296 (CAN) 5 CYLINDER ASSYS RECEIVED FOR REPAIR DUE TO LOW COMPRESSION. ABNORMALLY HIGH WEAR WAS FOUND INSIDE THE EXHAUST GUIDES. 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 20080220000652008022000065SO 2008 2 20 CA080124014 220080111G8530628309 GUIDE CONT 655483A11 CONT O200 O200A 17020SO CYLINDER UNDERSIZE W K NONE O OTHER ININSP/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 120080123G575355250007983 BEARING CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE TE FLAP MISSING W K NONE O OTHER ININSP/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 BOLT WAS MISSING AND PROBABLY NOT INSTALLED THE LAST TIME MX WAS DONE IN THAT AREA. 1L72 4F4 F A22CE E1NE 20080220000662008022000066SO 2008 2 20 CA080124016 220080123G8530636242 GUIDE CONT 655471A4 CONT O550 IO550D 17042SO CYLINDER WORN W K NONE O OTHER ININSP/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 20080124016) 3 O E3SO 20080220000672008022000067CE 2008 2 20 CA080125001 120080122G7931 OIL SYSTEM CESSNA560 560XL 2076702CE PWC 545 PW545B NE PRESSURE UNKNOWN W BE EMER. DESCENT ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CLCLIMB 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 EMERGENCY. ENG IS STILL UNDER INVESTIGATION TO DETERMINE THE CAUSE. (TC NR 20080125001) 2L72 4F4 FRTA22CE E00059EN 20080220000682008022000068EA 2008 2 20 CA080125002 120080122G2752 ACTUATOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE FLAP FAILED W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION APAPPROACH 1 CA (CAN) THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE ON FINAL AFTER SELECTING FLAP TO 8 DEGREES. AN EMERGENCY WAS DECLARED 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 WERE 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 2946 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 59482L72 4F4 FRTA21EA E15NE 20080220000692008022000069EA 2008 2 20 CA080126001 120080118G5610NP13932113 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE LT/ CAPTAIN BROKEN W O OTHER O OTHER CRCRUISE 1 CA 14906 (CAN) (CAPTAINS WINDSHIELD SHATTERED IN FLIGHT. PRESSURIZATION STAYED NORMAL AND THE AC CONTINUED. MAINT IS GOING TO CHANGE THE WINDSHIELD). REPLACED THE WINDOW WINDSHIELD, MAIN PILOT, NP-139321-13 01355H5650 TSO: 14906.50 CSO: 12838 (TC NR 20080126001) 2L72 4F4 FRTA21EA E15NE 20080220000702008022000070EA 2008 2 20 CA080126002 120080117G76031603730003 THROTTLE CONTROL CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE LT ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN F FLT CONT AFFECTED APAPPROACH 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 PUSH DURING (GO AROUND). LANDED ON ONE (RT) ENGINE. NOT POSSIBLE TO LAND THE A/C WITH (LT) AT 82 TO 90 PERCENT N1 FWD THRUST, 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) 2L72 4F4 FRTA21EA E15NE 20080220000722008022000072EA 2008 2 20 CA080126003 120080116G5610601R3303320 WINDOW CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C5 30050NE COCKPIT CRACKED W AB UNSCHED LANDING EMER. DESCENT O OTHER CRCRUISE 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 20080126003) 2L72 4F4 FRTA21EA E00063EN 20080220000732008022000073EA 2008 2 20 CA080126004 120080124G5210NAS76A16011 BUSHING CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE PAX DOOR MIGRATED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 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-52-110 CONFIGURATION. MECHANISM GA, PASS DOOR LATCH MFG 601R31903, BUSHING: P/N: NAS76A16-011 MIGRATED 24960:41 TSN / 22803 CSN (TC NR 20080126004) 2L72 4F4 FRTA21EA E15NE 20080220000742008022000074EU 2008 2 20 CA080128001 120080121G271019004212401 CONTROL CABLE EMB ERJ190ERJ190100IGW3260408EU GE CF34 CF3410E5A1 30022NE AILERONS BROKEN W K NONE O OTHER ININSP/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 WINGS 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 27-11-00-003-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 2635 C02 CHECK. (TC NR 20080128001) 2L72 4F4 FRTA57NM E00070EN 20080220000752008022000075EA 2008 2 20 CA080128002 120080127G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE TE FLAPS FAILED W K NONE O OTHER ININSP/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) 2L72 4F4 FRTA21EA E15NE 20080520 SW 2008 5 20 CA080128004 120080128G2720 CONTROL CABLE AIRTRCAT802 AT802A 0390308SW PWA PT6 PT6A67A 52043NE HARTZLHCB5M HCB5MA3 GL RUDDER STUCK W K NONE O OTHER ININSP/MAINT 1 CA 499 (CAN) DURING INSP, THE LT RUDDER CABLE WAS FOUND SNAGGED ON THE WATER RUDDER CABLE PULLEY GUARD. (TC NR 20080128004) 1L71 3T4 TNCA19SW E26NE 6 CP44GL 20080220000782008022000078SW 2008 2 20 CA080128007 120080118G6730206076062 SERVO BELL 407 407 1182206SW ALLSN 250C 250C47B GL MAIN ROTOR NOISY W O OTHER O OTHER DEDESCENT 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 REPLACED. THERE WERE NO CONTROL PROBLEMS ENCOUNTERED AND THE SERVO HAS SINCE BEEN OVERHAULED. (TC NR 20080128007) 1G71 3U3 UO H2SW E1GL 20080220000792008022000079SW 2008 2 20 CA080129003 120080116G7921MS172244 NUT BELL 407 407 1182206SW ALLSN 250C 250C47B GL OIL COOLER BLOW UNDERTORQUED W O OTHER O OTHER NRNOT 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) 1G71 3U3 UO H2SW E1GL 20080220000802008022000080WP 2008 2 20 CA080129005 120080128G6310C1883 SPRAG CLUTCH ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAIN ROTOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1620 (CAN) DURING OVER HAUL, THE CAGE OF THE SPRAG CLUTCH WAS FOUND CRACKED IN 8 PLACES. (TC NR 20080129005) 1G71 3O3 O H11NM 1E4 20080520 EA 2008 5 20 CA080130001 120080128G3246AN620A BOLT AIRCRFTPRDTS DHAV DHC6 DHC6100 2802610EA PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL FLOAT ASSY BROKEN W K NONE O OTHER ININSP/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 OCCURRED 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 CHALLENGING AT TIMES. (TC NR 20080130001) 1H72 3T3 TRTA9EA E4EA 6 CP15EA 20080220000812008022000081EU 2008 2 20 CA080130002 120080115G321229022979 HEAD AIRCRUISERS BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL EMERGENCY FLOAT LEAKING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING AN INSPECTION THE EMERGENCY FLOAT SYS WERE DEPLOYED ACCIDENTALLY. (2) REFURBISHED KITS (PN:28022969) WERE ORDERED. BOTH VALVE ASSY (PN: 105-E-0031) WERE REBUILDED INCLUDING SHEARHEAD ASSY. (PN:29022979) NITROGEN PRESSURE WAS BROUGHT 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) 1G72 3U3 U H3EU E4CE 20080221000012008022100001CE 2008 2 21 CA080131003 120080116G7110B140048 LATCH BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE HARTZLHCE4N HCE4N3 NE COWLING INOPERATIVE W O OTHER O OTHER CRCRUISE 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 THE CAM DURING ROTATION OF THE HOOK. A THOROUGH VERIFICATION OF A SUCCESSFUL LATCH, IN ADDITION TO THE VISUAL ALIGNMENT MARKS INDICATION, IS REQUIRED WHEN INSTALLING ENGINE COWLS. (TC NR 20080131003) 1L72 4T4 T A24CE E4EA 5 CP10NE 20080221000022008022100002NE 2008 2 21 CA080131008 320080109G6114 WASHER HAMSTD DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE PROPELLER CRACKED W K NONE O OTHER ININSP/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 DISMANTLED 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) 1H71 3R3 RRCA806 5E1 5 CP206 20080319001792008031900179CE 2008 3 19 CA080201001 120080130G3230C6189CL CHAIN BEECH 99 99 1154002CE PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL NLG BENT W A UNSCHED LANDING O OTHER CLCLIMB 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 INSPECTED 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) 1L72 3T3 T A14CE E4EA 6 CP15EA 20080520 2008 5 20 CA080201002 220080201G74141051324 SPRING 107902010 IMPULSE COUPLINGMISMANUFACTURED W K NONE O OTHER ININSP/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 THAN NORMALLY REQUIRED. THE MAG HAD A 500 HOUR INSP PERFORMED 116.2 HOURS AGO AND IT APPEARS THAT THE SPRING WAS IMPROPERLY 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 220080201G7261 OIL SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE NR 1 ENGINE OVERSERVICED W BE EMER. DESCENT ENGINE SHUTDOWN WJ INADEQUATE Q C WARNING INDICATION CRCRUISE 1 CA (CAN) DUE TO HIGH OIL TEMP INDICATION, NR 1 ENGINE WAS SHUTDOWN BY THE CA, ACFT LANDED IN IAD WITHOUT INCIDENT AND TAXIED 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 AT FAULT FOR THE OVER SERVICING AND HAS PLACED IT ON MEL. AFTER PROPER SERVICING LEVELS ARE MEET AND UNEVENTFUL ENGINE RUNS ARE CARIED OUT THEY PLAN TO PUT THE ACFT BACK INTO SERVICE. 2L72 4F4 FRTA21EA E15NE 20080319001802008031900180NM 2008 3 19 CA080204004 120080131G32328290018013 ACTUATOR DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE RT MLG DOOR UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 21658166 (CAN) RT MAIN GEAR DOOR CAUTION LIGHT AFTER T/O. GEAR CYCLED WITH NO CHANGE, FLIGHT RETURNED TO BASE. MAINT SUSPECTS THE FWD DOOR ACTUATOR TO BE AT FAULT. THE ACTUATOR WAS REPLACED AND FUNCTION CHECKS WERE C/O SERVICEABLE. THE ACTUATOR WAS 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) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080319001822008031900182NE 2008 3 19 CA080204005 220080204G72503024211 TURBINE WHEEL PWA PT6 PT6A135 52043NE ENGINE CORRODED W K NONE O OTHER ININSP/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 SIGN OF OXIDATION. CRACKS WERE NOTICED VISUALLY AFTER THE REMOVAL OF CORROSION AT THE EDGE ON THE FIRTREE FACE SIDE. THE FPI 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 20080319001852008031900185SW 2008 3 19 CA080205004 120080201G5302427034851103 SUPPORT BELL 427 427 1182207SW T/R GEARBOX CRACKED W K NONE O OTHER ININSP/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 20080205004) 1G71 3U R00001RC 20080319001862008031900186EU 2008 3 19 CA080205005 120080121G7603350A57105721 BALL JOINT SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE THROTTLE LINK WORN W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) WHEN THROTTLE WAS RETARDED DURING ENGINE START, T4 CONTINUED TO INCREASE. EMERGENCY SHUTOFF PULLED AND ENGINE MOTORED AS T4 REACHED 900C FOR 2 SECONDS. INVESTIGATION FOUND THE THROTTLE LINK DISCONNECTED BUT THE LOCKING PIN WAS PROPERLY ENGAGED AND IN THE PROPER POSITION. INCIDENT WAS DUPLICATED 2 OUT OF 3 TIME ON TESTING. PARTS INSPECTED AND FOUND, END EQUIPPED AND BALL JOINT BOTH WORN. (TC NR 20080205005) 1G71 3U3 U H9EU E19EU 20081104 WP 2008 11 4 CA080205007 220080129G72603588941 BEARING SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE GEARBOX WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TACH/GEN IDLER ASSY DUAL SPUR GEAR, CENTER ANTI FRICTION BEARING FOUND WITH AN UNUSUALLY HIGH AMOUNT OF RADIAL PLAY AND WAS EXTREMELY ROUGH WHEN TURNED OVER BY HAND. THE ENGINE WAS REMOVED DUE TO CARBON STEEL PLATELETS FOUND IN THE OIL SAMPLE. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20080319001882008031900188SW 2008 3 19 CA080205008 120080204G7603540122519 POWER CABLE GULSTM690TP 690A 0141722SW GARRTTTPE331TPE3315251K NM HARTZLHCB3T HCB3TN5 GL POWER LEVER FROZEN W E ENGINE SHUTDOWN F FLT CONT AFFECTED CRCRUISE 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 SHUTDOWN AND THE PROPELLER WAS FEATHERED. THE AC RETURNED TO THE AIRPORT AND LANDED WITHOUT INCIDENT. UPON INVESTIGATION, MOISTURE WAS FOUND IN THE POWER LEVER CABLE. THE MOISTURE WAS REMOVED FROM THE CABLE AND THE CABLE WAS INSPECTED SERVICEABLE. THE AC WAS RETURNED TO SERVICE. (TC NR 20080205008) 1H72 3T4 T 2A4 E2WE 6 CP15EA 20081104 NE 2008 11 4 CA080206004 220080116G7200 ENGINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE LEFT VIBRATION W AE UNSCHED LANDING ENGINE SHUTDOWN E VIBRATION/BUFFET CRCRUISE 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. 2L72 4F4 FRTA21EA E15NE 20080319001942008031900194NE 2008 3 19 CA080206008 220080117G7320 COUPLING BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE FUEL SYSTEM WORN W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 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) 1L72 4T4 T A24CE E4EA 20080319001962008031900196NE 2008 3 19 CA080206009 220080122G7261 OIL SYSTEM CESSNA560 560XL 2076702CE PWC 545 PW545B NE ENGINE EMPTY W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB AT APPROX FL190, THE CREW RECEIVED A LOW OIL PRESSURE WARNING AND PERFORMED A COMMANDED SHUTDOWN OF THE ENGINE. THE AC WAS DIVERTED TO AN ALTERNATE LANDING SITE. POST FLIGHT INSP REVEALED NO INDICATION OF OIL ON THE SIGHT GLASS. NO SIGNS OF EXTERNAL LEAKAGE. THE ENGINE HAS BEEN REMOVED AND RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE PROVIDED TO TC WHEN AVAILABLE. (TC NR 20080206009) 2L72 4F4 FRTA22CE E00059EN 20080319001972008031900197NE 2008 3 19 CA080206010 220080123G7261 OIL SYSTEM DHAV DHC8 DHC8201 2809001NM PWA PW120 PW123 NE ENGINE LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA AT0006 (CAN) THE CREW RECEIVED A LOW OIL PRESSURE WARNING AND ELECTED TO SHUTDOWN THE ENGINE. SIGNS OF EXTERNAL LEAKAGE WERE FOUND AT POST FLIGHT INSP. THE ENG HAS BEEN REMOVED FOR INVESTIGATION AND REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080206010) 2H72 4T4 TRTA13NM E20NE 20080319001982008031900198NE 2008 3 19 CA080206011 220080124G73103035989 TUBE FOKKERF27 F27MK50 EU PWA PWA120PW125B NE FUEL SYSTEM PUNCTURED W FEA ACTIVATE FIRE EXT. ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 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 AVAILABLE. (TC NR 20080206011) 2H72 4T4 TRTA817 E20NE 20080319001992008031900199NE 2008 3 19 CA080206012 220080124G7200 ENGINE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 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) 1L72 4F4 F A22CE E1NE 20080319002002008031900200NE 2008 3 19 CA080206013 220080129G7261 OIL CAP CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ENGINE LOOSE W EA ENGINE SHUTDOWN UNSCHED LANDING WJ INADEQUATE Q C WARNING INDICATION CLCLIMB 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 INVESTIGATION INDICATES THAT THE OIL FILLER CAP MAY NOT HAVE BEEN PROPERLY SECURED PRIOR TO THE FLIGHT. (TC NR 20080206013) 1L72 4F4 F A22CE E1NE 20080319002012008031900201EA 2008 3 19 CA080206014 220080104G8530SL32006WA21P CYLINDER HEAD LYC O320 O320E2D 41508EA ENGINE CRACKED W K NONE K FLUID LOSS ININSP/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 20080319002022008031900202NE 2008 3 19 CA080207005 120080108G6410SB7306102 BEARING SKRSKYS92 S92A NE GE CT7TS CT78A 30136NE T/R BLADE DEBONDED W O OTHER O OTHER NRNOT 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 FOR DEBONDING FROM TAIL ROTOR SPARE. ON ONE TAIL ROTOR BLADE A BEARING WAS SUSPECTED TO BE DEBONDED. UPON FURTHER INSPECTION WITH REMOVAL OF THE BEARING FROM THE TAIL ROTOR BLADE, IT WAS CONFIRMED THAT THE INNER PLATE OF THE PIVOT BEARING WAS TOTALLY SEPARATED FROM THE BLADE SPAR. AFTER LOOKING AT THE BEARING PLATE IT WAS CLEARLY VISIBLE THAT THE ADHESIVE MATERIAL USED TO BOND THE PLATE TO THE SPAR HAD ONLY ADHERED TO THE PLATE OF THE BEARING AND NOT TO THE SPAR. (TC NR 20080207005) 2G72 4U4 U R00024BOE8NE 20080319002032008031900203NE 2008 3 19 CA080207006 220080129G7310230360801 LINE BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE FUEL SYSTEM MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 307843062 (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 FUEL TO LEAK OUT. (TC NR 20080207006) 2H74 4F4 F A49EU E6NE 20080520 2008 5 20 CA080207007 420080130G2562ELT97A2560000000ELT DORNERDO32 DO328100 2996000NM PWA 119 PW119C NE HARTZLHDE6C HDE6C3B NE FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA 134 (CAN) NUMEROUS UNCOMMANDED ELT ACTIVATIONS WITH ELT97. HAVE HAD ACTIVATIONS WITH THE AC INFLIGHT AND PARKED ON THE APRON. 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) 2H72 4T4 TRTA45NM E20NE 6 CP34NE 20080319002042008031900204EA 2008 3 19 CA080207010 220080204G7322105217 CARBURETOR CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA ENGINE LOOSE W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA 731 (CAN) CARB HEAT SEEMED TO HAVE A SLIGHTLY EXCESSIVE DROP AT HIGHER RPM. (TC NR 20080207010) 1H71 3O3 ONT3A12 E274 20080319002052008031900205EU 2008 3 19 CA080207011 120080131G6130312089001 PROP BRAKE AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE NR 2 SEIZED W F ACTIVATE FIRE EXT. JA WARNING INDICATION FLAME/FIRE TXTAXI/GRND HDL 1 CA PCE120893 (CAN) AFTER ARRIVAL AT DESTINATION, THE AC TAXIED TO THE TERMINAL. PRIOR TO PASSENGER DEPLANING, THE CREW OBSERVED A MASTER WARNING (PROP UNLOCK). THE F/O REPORTED THAT THE NR 2 ENG WAS ON FIRE AND THE NR 2 CONDITION LEVER WAS SELECTED TO SHUTOFF POSITION. THE F/O OBSERVED THAT THE FIRE CONDITION WAS STILL EVIDENT AND THUS THE GROUND ENGINE FIRE CHECK LIST WAS 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 TO SERVICE. (TC NR 20080207011) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20080319002062008031900206CE 2008 3 19 CA080208001 120080206G561050420066317 WINDOW BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL LT COCKPIT DEPARTED W O OTHER D INFLIGHT SEPARATION CLCLIMB 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) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20080520 2008 5 20 CA080208002 420080208G2562AK450 ELT BEECH 60 60 1153602CE LYC O541 TIO541E1C4 41536EA HARTZLHCF3Y HCF3YR2 GL FAILED W K NONE O OTHER ININSP/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 SERVICEABLE UNIT. (TC NR 20080208002) 1L72 3O3 O A12CE E10EA 5 CP31EA 20080319002072008031900207NE 2008 3 19 CA080208003 220080204G721070BM052000 REDUCTION GB SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B 60037NE MAKING METAL W K NONE O OTHER ININSP/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 CHANGED OIL FILTER WAS CHANGED ALL MAG PLUGS INSPECTED AND CLEANED. A/C FLEW FOR 11.1 HRS AND SMALL FLAKES WERE FOUND ON SAME PLUG. A/C WAS GROUNDED AT THIS TIME AND MFG WAS INFORMED. A OIL SAMPLE WAS SENT FOR EVALUATION AND CAME BACK AS NORMAL. MFG HAS DECIDED TO REPLACE THE MO 5. (TC NR 20080208003) 1G71 3U3 U H9EU E00054EN 20080319002082008031900208EA 2008 3 19 CA080208005 220080129G8530734352 PUSHROD MAULE M5 M5235C 5460135SO LYC O540 O540J1A5 41532EA HARTZLHCC2Y HCC2YR1 GL ENGINE DEFECTIVE W O OTHER O OTHER NRNOT 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 NOT ALLOW OIL TO TRAVEL UP THE PUSHROD TO THE ROCKER. (TC NR 20080208005) 1H71 3O3 O 3A23 E295 5 CP920 20080319002122008031900212CE 2008 3 19 CA080211001 120080207G27201303800033 TRANSDUCER BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL RUDDER BOOST FAILED W C ABORTED TAKEOFF F FLT CONT AFFECTED TOTAKEOFF 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 LT RUDDER BOOST TRANSDUCER (P/N130-380003-3) FAILED WHICH SIMULATED ENGINE FAILURE AND CAUSED THE RUDDER BOOST SYS TO ACTIVATE. THE TRANSDUCER WAS REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20080211001) 2L72 4T4 T A24CE E4EA 6 CP56GL 20081222 CE 2008 12 22 CA080211002 120080205G2750552500079 ROLLER CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE CENTER FLAP AFT OUT OF ADJUST W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CAMPAIGN NOTICE 851-27-50-043, FLAP CTR AFT BEARING INSTALLATION, COMPLIED WITH. NO FAULTS FOUND ON LT FLAP INSTALLATION. 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 DOCUMENTED ON ASD-MP-01 REPORT NR859-02/04/08. 1L72 4F4 F A22CE E1NE 20080319002142008031900214EA 2008 3 19 CA080211006 220080208G73103011849 LINE BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL FUEL SYSTEM CRACKED W A UNSCHED LANDING KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CLCLIMB 1 CA (CAN) PILOT REPORTED HEAVY GAS ODOR IN COCKPIT AFTER TAKEOFF, ACCOMPANIED BY A MIST. MAINT ENGINEER FOUND A CRACKED FUEL LINE IN THE NR 2 ENGINE NACELLE THAT CONNECTS THE START CONTROL UNIT TO THE FUEL CONTROL UNIT CAUSING A FUEL LEAK THAT WAS SUBSEQUENTLY SUCKED INTO THE ENGINE COMPRESSOR SECTION AND THEN TRANSMITTED TO THE CABIN OF THE AC THROUGH THE BLEED AIR SYS. (TC NR 20080211006) 1L72 3T4 T A14CE E4EA 5 CSTC 20080319002152008031900215NM 2008 3 19 CA080211007 120080207G3213101683 ROLLER MESSIER DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE STRUT SEIZED W L ABORTED APPROACH J WARNING INDICATION APAPPROACH 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 WAS REMOVED LUBRICATED AND RE-INSTALLED. FURTHER RETRACTIONS AND EXTENSIONS WERE CARRIED OUT WITHOUT ANY PROBLEMS, AC RETURNED TO SERVICE. (TC NR 20080211007) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080520 NM 2008 5 20 CA080211009 120080204G271019004212401 CONTROL CABLE EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE AILERONS BROKEN W K NONE O OTHER ININSP/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 27-11-00-003-RT/2 . THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. FLEET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211009) 2L72 4F4 FRTA57NM E00070EN 20080520 NM 2008 5 20 CA080211011 120080111G271019004212401 CONTROL CABLE EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE AILERONS BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) C02 CHECK: DURING AILERON CONTROL CABLES INSPECTION ,ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 190-04212-401 AND P/N 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 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 CANADA FLEET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211011) 2L72 4F4 FRTA57NM E00070EN 20080520 NM 2008 5 20 CA080211012 120080123G271019004212401 CONTROL CABLE EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE AILERONS BROKEN W K NONE O OTHER ININSP/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 WINGS 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 27-11-00-003-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 2635 C02 CHECK. FLEET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211012) 2L72 4F4 FRTA57NM E00070EN 20080520 EA 2008 5 20 CA080211013 120080210G2720274001 PCU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE RUDDER MALFUNCTIONED W K NONE O OTHER ININSP/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 DURING 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 BEFORE 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. I2L72 4F4 FRTA21EA E15NE 20080520 NM 2008 5 20 CA080211014 120080131G271017005825401 CONTROL CABLE EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE AILERONS BROKEN W K NONE O OTHER ININSP/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 THE RIB 12, 15, 17 AND AT RIB 20. FLEET ENGINEERING AS BEEN ADVISED (TC NR 20080211014) 2L72 4F4 FRTA56NM E00063EN 20080520 NM 2008 5 20 CA080211015 120080207G271017005825401 CONTROL CABLE EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE AILERONS BROKEN W K NONE O OTHER ININSP/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 OF THE 17 FLEET ENGINEERING HAVE BEEN ADVISED (TC NR 20080211015) 2L72 4F4 FRTA56NM E00063EN 20080319002172008031900217SW 2008 3 19 CA080211017 120080208G2913206076030101 PUMP BELL 206 206L3 1182108SW HYDRAULIC SYS DAMAGED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING FLIGHT, AC LOST HYDRAULICS. AC LANDED SAFELY. MAINT FOUND HYDRAULICS PUMP SPLINE ROUNDED OFF. TACH GENERATOR SPLINES WORN AS WELL. (TC NR 20080211017) 1G71 3U H2SW 20080319002192008031900219CE 2008 3 19 CA080211018 120080206G3233508202085 ACTUATOR BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL NLG FAILED W O OTHER J WARNING INDICATION DEDESCENT 1 CA 1711 (CAN) DURING DESCENT INTO INTENDED AIRPORT THE NLG INDICATOR INTRANSIT LIGHT STAYED ILLUMINATED WHEN LANDING GEAR EXTENDED. MAIN GEAR DOWN AND LOCKED LIGHT WERE GREEN. A FLY-BY WAS CARRIED OUT WITH GROUND MAINT VERIFYING THAT THE NLG WAS INDEED ONLY HALF WAY DOWN WITH MAINS FULLY DOWN. AN EMERGENCY EXTENSION WAS ATTEMPTED AND FAILED TO EXTEND THE NLG. THE CREW 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) 1L72 3T4 T A14CE E4EA 6 CP15EA 20080520 CE 2008 5 20 CA080211019 120080104G282020282004500R SELECTOR CESSNA172 172M 2072418CE THIELTTAE125TAE12501 59300EU FUEL SYS MALFUNCTIONED W K NONE O OTHER ININSP/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 INSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEADER TANK. THE B-NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE WAS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REPLACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAKS WERE FOUND. THE OTHER (2) FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. (TC NR 20080211019) 1H71 3O3 BNT3A12 E00069EN 20080319002212008031900221EA 2008 3 19 CA080212001 120080212G5711C6WM10271 ADAPTER DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL SPAR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) UPON COMPLIANCE WITH SB 6/540 (WING-FRONT SPAR ADAPTER ASSEMBLY (P/N C6WM1027-1) INSPECTION FOR CRACKS) A CRACK WAS FOUND ON THE LT FRONT SPAR ADAPTER. REPLACED LT FRONT SPAR ADAPTER ASSY PN C6WM1027-1 WITH PN C6WM1027-3 IAW SB NR 61542. (TC NR 20080212001) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20081229 CE 2008 12 29 CA080212003 120080201G575355250007 SUPPORT CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE TE FLAP WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A CAMPAIGN NOTICE OF THE RT FLAP CENTER BRG INSTALLATION, BOTH OF THE AFT FLAP BEARINGS WERE FOUND LOOSE AND WORN DUE TO THE LOCATING PIN ON THE BEARINGS NOT INSTALLED INTO MATING HOLES OF FLAP RIB EXTENSIONS. FLAP ROLLER PN KJS 112603 AND BOTH CENTER AFT FLAP ROLLER SUPPORT BRGS P/N 5525000-79 WERE REPLACED.FLAPS FUNCTION CHECK SERVICEABLE AND ACFT RETURNED TO SERVICE. 1L72 4F4 F A22CE E1NE 20080319002232008031900223EA 2008 3 19 CA080212004 120080129G5411C6WM10271 ADAPTER DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL SPAR CRACKED W K NONE O OTHER ININSP/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) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20080319002272008031900227EA 2008 3 19 CA080212005 220080208G7320 LINK BENDIX HUGHES269 269C 4470504WP LYC O360 HIO360D1A 41514EA FUEL INJECTOR DISCONNECTED W R AUTOROTATION RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 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 THE ENGINE AND THE ENGINE RETURNED TO GROUND IDLE POWER. (TC NR 20080212005) 1G71 3O3 O 4H12 1E10 20080319002292008031900229EU 2008 3 19 CA080213001 120080208G2421729722C GENERATOR HONEYWELL AIRBUS310 A310 EU GE CF6 CF680C2A5 NE APU CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 3248819916 PP1269 (CAN) DURING TROUBLESHOOTING FOR HIGH OIL CONSUMPTION ON THE APU, FOUND A 7 INCHES CRACK ON THE GENERATOR HOUSING. THE IDG WAS REPLACED AND THE UNIT WAS SENT TO THE VENDOR FOR INVESTIGATION. (TC NR 20080213001) 2L72 4F4 FRTA35EU E13NE 20080520 CE 2008 5 20 CA080213002 120080211G3250MC09543022 TUBE CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL NLG STEERING STUCK W K NONE O OTHER ININSP/MAINT 1 CA 828 (CAN) PROBLEM WAS DISCOVERED DURING PRE-INSP RUN UP. WHEN FULL RUDDER DEFLECTION WAS APPLIED THE RUDDER MOVEMENT WAS RESTRICTED AND WOULD ONLY RELEASE WHEN ALTNATE RUDDER PRESSURE WAS APPLIED. (TC NR 20080213002) 1H71 3O3 ONT3A19 E223 5 NP50GL 20080319002312008031900231NM 2008 3 19 CA080213003 120080120G5610070303 WINDSHIELD DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE COCKPIT CRACKED W BI EMER. DESCENT CABIN DEPRESSURIZATION O OTHER CRCRUISE 1 CA (CAN) WHILE IN CRUISE FLIGHT, THE F/O HEATED WINDSHIELD SHATTERED WITH NO APPARENT WARNING. THE CREW DEPRESSURIZED THE CABIN AND DESCENDED IAW THEIR CHECKLISTS AND CONTINUED THE FLIGHT TO THEIR DESTINATION. THE AC WAS ON A NON REVENUE FLIGHT TO A MAINT FACILITY FOR THE COMPLETION OF A C-CHECK. THE WINDOW HAS BEEN REPLACED AND NO DEFINITIVE REASON FOR THE FAILURE 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) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080520 GL 2008 5 20 CA080213004 120080206G2133811441A010302 OUTFLOW VALVE BOMBDRBD100 BD1001A10 1390044GL HNYWL AS907 AS90711A 33908WP CABIN PRESSURE FAILED W B EMER. DESCENT J WARNING INDICATION CLCLIMB 1 CA 607 (CAN) DURING CLIMB, THROUGH FL270, CABIN ROC (RATE OF CLIMB) INCREASED TO 3000 FPM (FT PER MINUTE), CABIN ALTITUDE STARTED TO CLIMB. MANUAL PRESSURIZATION WAS SELECTED RESULTING IN AN INABILITY TO REDUCE CABIN ALTITUDE. AC DESCENDED, EICAS (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) 2L72 4F4 FRTT00005NYE00010LA 20080520 GL 2008 5 20 CA080213005 120080103G2133811441A010302 OUTFLOW VALVE BOMBDRBD100 BD1001A10 1390044GL HNYWL AS907 AS90711A 33908WP CABIN PRESSURE MALFUNCTIONED W B EMER. DESCENT O OTHER CRCRUISE 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 AND AN EMERGENCY DESCENT WAS CARRIED OUT. WAITING MORE INFO FROM CUSTOMER. THE MFG HAS INSPECTED THE VALVES AND THEY CONCLUDE THE VALVES WERE (NO FAULT FOUND). THE INVESTIGATION IS ONGOING. (TC NR 20080213005) 2L72 4F4 FRTT00005NYE00010LA 20080319002342008031900234NM 2008 3 19 CA080213006 120080122G3246314353 WHEEL DHAV DHC8 DHC8106 2809020NM PWA PW121 PW121 52124NE HAMSTD14SF 14SF7 NE LT MLG CRACKED W K NONE O OTHER ININSP/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 REMOVED AND SENT FOR INSP. INSP REVEALED THAT THE INNER RIM HALF WAS CRACKED AT THE FUSE PLUG AND FURTHER INSP REVEALED CRACKING 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) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081229 CE 2008 12 29 CA080213007 120080131G2910SEEDESCRIPTION HOSE CESSNA680 680CE 2076811CE PWC PW306 PW306C 52169NE HYD SYS LEAKING W K NONE K FLUID LOSS ININSP/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 FOLLOWING PN HOSES WERE REPLACED. AE1011925E0087, AE1011925E0094, AE1011925E0121, AE1011888E0132, AE1011924E0103, AE1011933E0086. 2L72 4F4 FRCT00012WIE35NE 20080520 EU 2008 5 20 CA080213008 120080208G2913 PUMP AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE HYD SYSTEM MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) SHORTLY AFTER DEPARTURE, THE CREW OBSERVED A LOW PRESSURE INDICATION ON THE BLUE HYDR SYS. THE AC RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINT REPLACED THE BLUE SYS PUMP AND THE AC WAS RETURNED TO SERVICE. (TC NR 20080213008) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20080520 NE 2008 5 20 CA080213010 320080209G6114 SEAL HAMSTD 54H60117 LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE PUMP HOUSING TORN W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 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 AFTER 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) 2H74 4T4 T A1SO E282 6 CP906 20080521 CE 2008 5 21 CA080213013 120080104G282320282004500R SELECTOR CESSNA172 172M 2072418CE THIELTTAE125TAE12502114 EU FUEL SYSTEM LEAKING W K NONE O OTHER ININSP/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 INSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEADER TANK. THE B NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE WAS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REPLACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAKS WERE FOUND. THE OTHER TWO FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. THIS IS THE SECOND PART. (TC1H71 3O3 BNT3A12 E00069EN 20080522 CE 2008 5 22 CA080213014 120080104G282320282004500R SELECTOR CESSNA172 172M 2072418CE THIELTTAE125TAE1250299 EU FUEL SYSTEM DAMAGED W K NONE O OTHER ININSP/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 INSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEADER TANK. THE B-NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE WAS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REPLACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAKS WERE FOUND. THE OTHER (2) FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. THIS IS THE THIRD PART. (TC 1H71 3O3 BNT3A12 E00069EN 20080319002372008031900237GL 2008 3 19 CA080214001 120080212G27202227271400 RUDDER PEDAL DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA COCKPIT CORRODED W O OTHER O OTHER TXTAXI/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 CONTINUOUSLY CORRODES TO THE POINT THAT IT AFFECTS THE POSITIONING OF THE RUDDER PEDALS. (TC NR 20080214001) 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20081104 SW 2008 11 4 CA080214002 120080213G7714 DRIVE SHAFT SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110U 01514WP HARTZLHCB3T HCB3TN5 GL TACH GENERATOR FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TROUBLESHOT NO RPM INDICATION. REMOVED TACH GENERATOR FROM RT ENGINE, DRIVE SHAFT WAS STILL STUCK IN THE ENGINE. IT 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) 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20080319002422008031900242CE 2008 3 19 CA080214005 120080214G27501013800005 DRIVE SHAFT BEECH 1900 1900D 1154162CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL FLAP DRIVE SEIZED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 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) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20080603 NM 2008 6 3 CA080214007 120080121G291082970009325 HYDRAULIC LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120 NE HAMSTD14SF 14SF7 NE HYDRAULIC SYS CRACKED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 34968 (CAN) WHILE ENROUTE THE "IB ROLL SPL HYD" AND NR 1 "HYD ISO VLV" CAUTION LIGHTS ILLUMINATED. CHECKED THE HYD QUANTITY AND 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 AND THE FITTING HAD EVIDENCE OF PITTING CORROSION. THE TUBE AND FITTING WERE BOTH REPLACED IAW THE AIRCRAFT MM AND SUBSEQUENTLY TESTED SERVICEABLE. (TC NR 20080214007) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080521 2008 5 21 CA080214008 420080213G25620010009C ELT CABIN CRACKED W O OTHER O OTHER NRNOT 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 120080114G3260 DOWNLOCK SWITCH CVAC 440 440 2422902WP ALLSN 501D 501D13D 03004GL ALLSN A6441 A6441FN606 GL MLG DEFECTIVE W L ABORTED APPROACH N FALSE WARNING DEDESCENT 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 LOCKED. FOR PRECAUTIONARY MEASURES IN THE COMPANY PROCEDURES AN EMERGENCY LANDING WAS DECLARED THAN PROCEEDED WITH NORMAL LANDING. FOLLOWING MAINT INVESTIGATION FOUND LT MLG DOWNLOCK SWITCH DEFECTIVE, THE SWITCH WAS REPLACED AND RIGGED IAW MM AND AC RETUNED TO SERVICE. (TC NR 20080214009) 2L72 4R4 T 6A6 E282 6 CP898 20080521 NE 2008 5 21 CA080214010 120080209G53403322203 ATTACH FITTING 3035941 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL SEATBELT FAILED W K NONE O OTHER ININSP/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 FAILURE OF THE ALUMINUM ATTACH FITTING. A DESIGN CHANGE IS REQUIRED TO PREVENT SIMILAR OCCURRENCES. I AM THE APPROVAL HOLDER 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 CONTACTED THE SEAT MFG REQUESTING ENGINEERING ASSISTANCE TO ADDRESS THIS DEFECT. (TC NR 20080214010) 1G72 3U3 U H1NE E1GL 20081230 CE 2008 12 30 CA080214011 120080124G251005142121 SEAT BACK CESSNA CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MCAULY1C235 1C235LFA GL COCKPIT SEAT BROKEN W O OTHER O OTHER CRCRUISE 1 CA 4056 (CAN) SEAT BACK FRAME BROKEN JUST ABOVE INSERT ON THE OTBD SIDE. NOTEWORTHY ITEM: THIS SEAT DID HAVE A STEAL BAR INSTALLED IAW AD 2007-05-10. WE DO NOT KNOW WHETHER THIS WAS A CONTRIBUTING CAUSE TO THE FAILURE. 1H71 3O3 ONT3A12 1E10 5 NP12EA 20080521 2008 5 21 CA080215001 420080207G23704954200001 VIDEO MONITOR BOEING767 7673Y0 NM PWA 4060 PW4060 52119NE CABIN FIRE W O OTHER AB FLAME/FIRE SMOKE/FUMES/ODORS/SPARKS LDLANDING 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 MELTED 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). 2L72 4F4 FRTA1NM E24NE 20081105 2008 11 5 CA080215002 420080214G31307013348931 DAU LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP MALFUNCTIONED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) THIS DAU WAS ORIGINALLY REMOVED FROM ANOTHER OPERATOR ACFT WITH THE FAULT, LOSS OF N1 AND N2 INDICATION. MFG TESTED THE UNIT AND RETURNED IT TO SERVICE WITH NO FAULT FOUND, WITH ALL THE APPROPRIATE CERTIFICATION. THE UNIT WAS INSTALLED ON OUR ACFT IN NR1 POSITION WITH THE PROPER FUNCTION CHECK CARRIED OUT. DURING ENGINES RUN, ALL ENGINES INDICATIONS WERE 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 THIS UNIT GET FINALLY REPAIRED. (TC NR 20080215002) 2L72 4F4 FRTT00008WIE6WE 20080320000112008032000011SO 2008 3 20 CA080215003 120080214G78209948200 MUFFLER PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA SNSNCH74D 74DM EA ENGINE DAMAGED W K NONE O OTHER ININSP/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 THE PAST WE WERE FINDING LARGE CRACKS IN BEHIND WHEN WE PRESSURE TESTED EVERY 200 HOURS WHICH YOU COULD NOT SEE VISUALLY SO WE BEGAN PRESSURE TESTING ALL THE TIME VERSUS VISUAL. ALSO FOUND THAT AFTER INSTALLATION OF NEW EXHAUST, PIN HOLES BEGAN 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 LATER. SO WE NOW PRESSURE TEST THE EXHAUST SYS EVERY 100 HRS COMMERCIAL AND ANNUALLY WITH PRIVATES. THIS HAS LOWER THE OV1L71 3O3 O 2A13 E274 5 NP88614 20080521 GL 2008 5 21 CA080215005 220080215G7230 CASE HALF BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL COMPRESSOR DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON SPLITTING THE COMPRESSOR CASE HALVES FOR AN INSPECTION, IT WAS NOTED THERE WERE AREAS OF THE PLASTIC COATING THAT WERE MISSING. CASES REPLACED. (TC NR 20080215005) 1G71 3U3 U H2SW E4CE 20080325000032008032500003SO 2008 3 25 CA080215007 120080209G5520486104 BOLT PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL ELEVATOR STOP BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A ROUTINE INSP OF THE ELEVATOR STOPS. WHEN THE DOWN STOP WAS PHYSICALLY TEST FOR SECURITY THE BOLT HEAD POPPED OFF. UPON CLOSER INSP THE BOLT WAS CRACKED AND WAS BEING HELD IN PLACE BY THE NORMAL ELEVATOR DOWN PRESSURE. NO OTHER DAMAGE WAS NOTED, BOLT REPLACED AC RETURNED TO SERVICE. (TC NR 20080215007) 1L72 3O3 O A20SO E14EA 5 CP33EA 20080521 EA 2008 5 21 CA080215008 220080209G7314RG9080J4A PUMP PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL FUEL SYSTEM ERRATIC W K NONE O OTHER ININSP/MAINT 1 CA 482 (CAN) RT ENGINE DRIVEN FUEL PUMP REPLACED DUE TO ERATIC PRESSURE INDICATIONS. (TC NR 20080215008) 1L72 3O3 O A20SO E14EA 5 CP33EA 20080521 WP 2008 5 21 CA080215009 120080111G2497 CONNECTOR CVAC 440 440 2422902WP ALLSN 501D 501D13 03004GL ALLSN A6441 A6441FN606 GL CONTROL PANEL DAMAGED W EF ENGINE SHUTDOWN ACTIVATE FIRE EXT. GJ MULTIPLE FAILURE WARNING INDICATION CLCLIMB 1 CA (CAN) ON CLIMBOUT, AT 5500FT, THE ADI, HSI AND VSI WENT UNSERVICEABLE AT THE SAME TIME, COMPLETE LOSS OF ELECTRICAL POWER, 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 AC CONTROL PANEL CONNECTOR DAMAGED AT PIN NR 10. BOTH THE AC CONTROL PANEL UNIT AND THE CONNECTOR WAS REPLACED AND TESTED SERVICEABLE. A FLEET CAMPAING WAS CARRIED OUT TO INSPECT ALL THE AC CONTROL PANEL CONNECTORS FOR CONDITION AND NO DEFECT DETECTED. (TC NR 20080215009) 2L72 4R4 T 6A6 E282 6 CP898 20080521 2008 5 21 CA080215010 420080214G22152R5310A SERVO EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE AUTOPILOT MALFUNCTIONED W O OTHER O OTHER NRNOT REPORTED 1 CA 5702 5702 (CAN) AUTOPILOT UNSERVICEABLE, EICAS MESSAGE (AP FAIL) ON FOR APPROX 3-5 SECONDS, THEN DISAPPEARS. AUTOPILOT AILERON SERVO FAILED. FAULT CODES 22110239PA1 AND 22110239PA2 RECORDED. (TC NR 20080215010) 2L72 4F4 FRTA56NM E00063EN 20080521 EA 2008 5 21 CA080215011 120080214G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS FAILED W O OTHER J WARNING INDICATION APAPPROACH 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 LUBRICATED IAW COMPANY POLICY. (TC NR 20080215011) 2L72 4F4 FRTA21EA E15NE 20080521 EU 2008 5 21 CA080215012 120080214G3150B19030W04 DISPLAY UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE MALFUNCTIONED W O OTHER N FALSE WARNING LDLANDING 1 CA 1874 1874 (CAN) THERE HAS BEEN REPORTS OF NUMEROUS SYS FAILURE REPORTS FROM THE VEMD SUCH AS NF/NR, MODULE, OVERLIMITS, LANE FAILURES 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) 1G72 3U3 UNCR0001RD E34NE 20081229 CE 2008 12 29 CA080215013 120080207G2810S51812 LINE CESSNA CESSNA425 425 2076018CE PWA PT6 PT6A112 52043NE MCAULY4HFR344HFR34C762 NE BLADDER VENT WORN W K NONE O OTHER ININSP/MAINT 1 CA 7218 (CAN) LT AND RT NACELLE FUEL BLADERS WERE FOUND COLLAPSED. GROUND HANDLER REPORTED AIR RUSHING INTO TANK AFTER FILLER CAP REMOVAL WHILE PREPARING TO FUEL ACFT. FUEL VENT LINES WITHIN INTEGERAL WING TANK WERE FOUND TO HAVE HARD/BRITTLE RUBBER 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. 1L72 3T3 TRTA7CE E4EA 6 C3PNE 20080521 EA 2008 5 21 CA080217002 120080211G5610NP13932111 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA COCKPIT BROKEN W A UNSCHED LANDING O OTHER CLCLIMB 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) 2L72 4F RTA21EA 20080521 EA 2008 5 21 CA080217003 120080211G5610NP13932111 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 12616 (CAN) ON ROTATION CAPTAINS WINDSHIELD CRACKED. FOLLOWED QRH AND RETURNED TO THE FIELD. WINDSHIELD IS A POST SB CONFIGURATION. (TC NR 20080217003) 2L72 4F RTA21EA 20080521 EA 2008 5 21 CA080218001 120080216G324190004433 CONTROL UNIT CNDAIRCL600 CL600* 1900302EA GE CF34 CF348C5 30050NE ANTI SKID SYS FAULTY W O OTHER J WARNING INDICATION LDLANDING 1 CA 8195 (CAN) ON LANDING, CREW RECEIVED IB ANTI-SKID CAUTION MESSAGE. AFTER TAXIING CLEAR OF ACTIVE RUNWAY IT WAS DETERMINED BOTH LT MAIN TIRES FLAT. MAINT FOUND MDC FAULT CODES INDICATED FAULTY ASCU. ASCU REPLACED, AXLE INSP. FOR OVERTEMP AND TIRES REPLACED. FUNCTION CHECKS C/O WITH NO FURTHER FAULTS. (TC NR 20080218001) 2L72 4F4 FRTA21EA E00063EN 200805141 200805141 EU 2008 5 14 CA080218002 120080218G71300292827110 HEAT SHIELD TMECA ARRIEL2B SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B 60037NE ENGINE CHAFED W K NONE O OTHER ININSP/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 OUTER LAYER OF THE HEAT SHIELD. (TC NR 20080218002) 1G71 3U3 U H9EU E00054EN 20081230 CE 2008 12 30 CA080218003 120080218G326030A01002203202 INDICATOR CESSNA206 T206H 2073303CE LYC O540 TIO540AJ1A EA HARTZLHCF3Y HCF3YR1 GL MLG FLOAT MISINSTALLED W K NONE W INADEQUATE Q C ININSP/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. 1H71 3O3 ORTA4CE E14EA 5 CP31EA 20081230 CE 2008 12 30 CA080218004 120080218G2820051338216 SELECTOR CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA FUEL SYS WORN W K NONE O OTHER ININSP/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 WITHOUT THE SELECTOR POSITIONING BALL AND SPRING HSG REACHING THE DETENT IN THE FUEL SELECTOR HSG. 1H71 3O3 ONT3A12 E274 20080521 EU 2008 5 21 CA080218005 120080218G7720955017820 THERMOCOUPLE SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B 60037NE ENGINE GROOVED W K NONE O OTHER ININSP/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) 1G71 3U3 U H9EU E00054EN 20080521 EU 2008 5 21 CA080218006 120080218G77229550178220 THERMOCOUPLE SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B 60037NE ENGINE GROOVED W K NONE O OTHER ININSP/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) 1G71 3U3 U H9EU E00054EN 20081113 EU 2008 11 13 CA080219002 120080208G6730 SERVO SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE FLLIGHT CONTROL MALFUNCTIONED W L ABORTED APPROACH EF VIBRATION/BUFFET FLT CONT AFFECTED APAPPROACH 1 CA 101282345 (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 CONCERN ABOUT LOSS OF CONTROL OF THE HELICOPTER. COLLECTIVE WAS INCREASED AND THE VIBRATION LEVEL RETURNED TO A NORMAL LEVEL. 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 REPLACED AND INSPECTIONS PERFORMED. THE VIBRATIONS WERE WITHIN LIMITS AND NEVER REACHED A LEVEL OF IMMEDIATE CONCEARN LIKE T1G71 3U3 U H9EU E19EU 20080603 NM 2008 6 3 CA080219004 120080218G327065715611 SKID BOEING727 727227 1384078NM PWA JT8 JT8D9A 52048NE TAIL SKID DEFECTIVE W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) UPON GEAR RETRACTION, TAIL SKID LIGHT REMAINED ILLUMINATED. A/C RETURNED TO STATION WHERE SKID TIP WAS REPLACED, SWITCH CONTACT CONFIRMED AND A/C RETURNED TO SERVICE. (TC NR 20080219004) 2L73 4F4 F A3WE E2EA 20080521 NM 2008 5 21 CA080219005 120080219G5320654659244 CHANNEL BOEING737 7374S3 1384711NM BS 790 CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FLOOR CHANNEL AT BS 790, RBL 8 AFT CARGO PIT CORRODED AND REPAIRED IAW CUSTOMER EA (TC NR 20080219005) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080219006 120080219G5321654659247 FLOOR PANEL BOEING737 7374S3 1384711NM AFT CARGO PIT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL CORRODED AT BS 767+6, LBL 3 AND REPAIRED IAW CUSTOMER EA. (TC NR 20080219006) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080219007 120080219G5320654659249 CHANNEL BOEING737 7374S3 1384711NM AFT CARGO PIT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 727+8, LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080219007) 2L72 4F RTA16WE 20080521 EA 2008 5 21 CA080220001 120080219G76033018024 ROD END DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL NR 2 THROTTLE BENT W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 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 NR 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 IAW MM. THE ENGINE WAS RECENTLY REPLACED AND HAS 3.4 HOURS SINCE LAST OVERHAUL. (TC NR 20080220001) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20080521 SW 2008 5 21 CA080220002 120080218G56102719442004 WINDSHIELD SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE COCKPIT DELAMINATED W O OTHER O OTHER CRCRUISE 1 CA 4902 (CAN) DURING THE CRUISE PORTION OF FLIGHT, THE CREW WITNESSED THE RT SIDE COCKPIT HEATED WINDSHIELD PHYSICALLY DELAMINATING . THE CREW INDICATED THE AC WAS OPERATING AT A 6.0 PSI DIFFERENTIAL WHICH IS WITHIN THE MAXIMUM 7.25 PSI DIFFERENTIAL FOR THE AC. NO ACTION WAS TAKEN BY THE CREW OR WAS DEEMED NECESSARY AND THE WINDOW DELAMINATION WAS MONITORED CLOSLY UNTIL LANDING. MAINT HAS REPLACED THE WINDSHIELD. (TC NR 20080220002) 2L72 4T4 TRTA8SW E4WE 5 CP10NE 20080521 2008 5 21 CA080220003 220080220G7414 BEARING MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 122 (CAN) MAG WAS RECEIVED FOR INSPECTION DUE TO ENGINE OVERSPEED. WHEN THE ROTATING MAGNET (ROTOR) WAS SPUN BY HAND THERE WAS 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 PRELOAD AND THE MAG WAS TESTED AND RETURNED TO SERVICE. THIS WAS A FACTORY NEW MAGNETO WITH ONLY 121.5 HOURS IN SERVICE. (TC NR 20080220003) 20080521 EA 2008 5 21 CA080220005 220080130G7200 ENGINE BEECH 1900 1900C 1154161CE PWA PT6 PT6* 52043EA HARTZLHCB4M HCB4MP3 GL MAKING METAL W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION DEDESCENT 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 CONTAMINATED WITH OIL. THE ENGINE HAS BEEN SENT FOR INVESTIGATION AND REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080220005) 2L72 4T3 TRTA24CE E2NE 6 CP56GL 200805141 200805141 NE 2008 5 14 CA080220006 220080206G7250 TURBINE BLADES PWA PW127 AEROSPATR72 ATR72212 8680945EU PWA PW120 PW127 NE ENGINE FRACTURED W EA ENGINE SHUTDOWN UNSCHED LANDING KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CLCLIMB 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 SHUTDOWN THE ENGINE AND RETURN TO POINT OF DEPARTURE. POST FLIGHT INSPECTION INDICATED FRACTURED POWER TURBINE BLADES AND EVIDENCE OF OIL LEAKAGE. THE ENGINE WILL BE RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE PROVIDED. (TC NR 20080220006) 2H72 4T4 TRTA53EU E20NE 20080521 NM 2008 5 21 CA080220007 120080115G7931 OIL SYSTEM DORNERDO32 DO328100 2996000NM PWA 119 PW119B NE ENGINE LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, THE OIL PRESSURE WAS NOTED TO DROP. THE CREW SHUTDOWN THE ENGINE AND PERFORMED A SINGLE ENGINE LANDING. ENGINE IS BEING SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080220007) 2H72 4T4 TRTA45NM E20NE 20080521 NE 2008 5 21 CA080220008 220080211G7200 ENGINE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE SEIZED W EA ENGINE SHUTDOWN UNSCHED LANDING RB PARTIAL RPM/PWR LOSS SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF, WHEN SELECTING BLEED AIR ON, THE CREW HEARD TWO (2) LOUD BANGS FOLLOWED BY SEEING SPARKS FROM THE EXHAUST. PILOT SECURED THE ENGINE AND RETURNED TO POINT OF DEPARTURE. POST FLIGHT INSP REVEALED A SEIZED PROP AND IMPACT DAMAGE INSIDE EXHAUST DUCT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080220008) 2L72 4T4 TRTA24CE E26NE 20080521 NM 2008 5 21 CA080220009 120080220G5320654659249 CHANNEL BOEING737 7374S3 1384711NM AFT CARGO PIT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+6, LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220009) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220010 120080220G5320654659247 CHANNEL BOEING737 7374S3 1384711NM AFT CARGO PIT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+6, LBL 8 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220010) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220011 120080220G5320654659249 CHANNEL BOEING737 7374S3 1384711NM AFT CARGO PIT CORRODED W K NONE O OTHER ININSP/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) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220012 120080220G5340650163312 STRINGER CLIP BOEING737 7374S3 1384711NM BS 294.5 S13L CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TIE CLIP AT BS 294.5, S13L CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220012) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220013 120080220G5310651768537 DOOR FRAME BOEING737 7374S3 1384711NM L1 DOOR GOUGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) L1 DOOR CUTOUT FRAME AT STA 349, WL 216 GOUGED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220013) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220014 120080220G4910656612115 SHROUD BOEING737 7374S3 1384711NM APU CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) APU UPPER SHROUD CRACKED FWD OF FWD LATCH REPAIRED IAW CUSTOMER EA. (TC NR 20080220014) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220015 120080220G531365617777 STRINGER SPLICE BOEING737 7374S3 1384711NM BS360 S15L CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) STRINGER SPLICE AT BS 360, STR 15L CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220015) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220016 120080220G532065465926 CHANNEL BOEING737 7374S3 1384711NM AFT CARGO PIT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS767+6, LBL11 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220016) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220017 120080220G5320654659247 CHANNEL BOEING737 7374S3 1384711NM AFT CARGO PIT CORRODED W K NONE O OTHER ININSP/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) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220018 120080220G5534655484221 SKATE ANGLE BOEING737 7374S3 1384711NM VERTICAL STAB CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) V STAB TO FUSELAGE SKATE ANGLE LT CHAFED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220018) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220019 120080220G53206546592503 CHANNEL BOEING737 7374S3 1384711NM AFT CARGO PIT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 727E+8, RBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220019) 2L72 4F RTA16WE 200805141 200805141 NM 2008 5 14 CA080220020 120080220G53206546592503 CHANNEL BOEING737 7374S3 1384711NM FUSELAGE CORRODED W K NONE O OTHER ININSP/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 20080220020) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220021 120080220G5320654659247 CHANNEL BOEING737 7374S3 1384711NM AFT CARGO PIT CORRODED W K NONE O OTHER ININSP/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) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080220022 120080220G5320654659247 CHANNEL BOEING737 7374S3 1384711NM AFT CARGO PIT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+4, LBL 8 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220022) 2L72 4F RTA16WE 20080521 EA 2008 5 21 CA080221001 120080212G2810CT2P10011 FUEL TANK DHAV DHC2 DHC2MK3 2800107EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL FORWARD DETERIORATED W K NONE O OTHER ININSP/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. THIS 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) 1H71 3T4 T A806 E4EA 6 CP15EA 20081230 CE 2008 12 30 CA080221002 120080208G7820PN04504003 MUFFLER CESSNA150 150L 2071826CE CONT O200 O200A 17020SO MCAULY1A101 1A101DCM GL EXHAUST SYS DAMAGED W K NONE O OTHER ININSP/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 AND WATER, 3 PIN HOLES SHOWED. 2 WERE IN OPEN BARE METAL SURFACE. ONE WAS IN THE LONGITUDINAL SEAM. ANOTHER EXPERIENCED AME WAS IN MY SHOP FOR OTHER REASONS. ASKED HIM TO VISUALLY INSPECT IAW CF90-03. EVEN THOUGH HE KNEW THERE WERE LEAKS, SO 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. 1H71 3O3 O 3A19 E252 5 NP918 20080521 EA 2008 5 21 CA080221003 120080220G2913601R751547 PUMP CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE HYD SYSTEM UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 8050 (CAN) CREW RECEIVED A GEAR DISAGREE MESSAGE AFTER TAKEOFF WITH AN APPLICABLE RED NOSE GEAR INDICATION AND 2 MAIN GEAR AMBER MESSAGES. CREW ACTIONED THEIR QRH AND DO AN ALTERNATE EXTENSION, A/C RETURNED. PSEU CODES RETRIEVED AND THE AC WAS ROUTED WHERE MAINT WILL INVESTIGATE FURTHER. NOSE GEAR OLEO SERVICED TO C/O AND 3A HYD PUMP TO BE REPLACED. MORE INFORMATION TO FOLLOW. (TC NR 20080221003) 2L72 4F4 FRTA21EA E15NE 20080603 SW 2008 6 3 CA080221004 120080209G6320PT6T3B GEARBOX BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE MAIN ROTOR MISMANUFACTURED W O OTHER J WARNING INDICATION HOHOVERING 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 DRAINED AND YET THE VISUAL INDICATION THERE WAS LOTS OF OIL. ON FEB. 9TH THE PWR SECTION WAS REMOVED DUE TO LOSS OF OIL PRESSURE. A TECH REP WAS BROUGHT TO THE BASE AND IT WAS NOTICED THAT THE LOWER HOLE INTO THE GEARBOX OF THE OIL LEVEL INDICATOR WAS NOT DRILLED INTO THE CASE. SINCE THE OIL COULD NOT DRAIN OUT OF THE VISUAL INDICATOR THE OIL LEVEL APPEARED FULL. (TC NR 20080221004) 1G71 4U4 U H4SW E22EA 20081104 SW 2008 11 4 CA080221005 120080216G5302206031327101 FITTING BELL 407 407 1182206SW ALLSN 250C 250C47B GL TAILBOOM CRACKED W K NONE O OTHER ININSP/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) 1G71 3U3 UO H2SW E1GL 20080603 NE 2008 6 3 CA080221007 220080208G7200PT6A68 ENGINE PWA PT6 PT6A68 NE MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING JEAWARNING INDICATION VIBRATION/BUFFET FLAME/FIRE NRNOT 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 220080213G7200 ENGINE DHAV DHC8 DHC8* NM PWA PW121 PW121 52124NE FLAMED OUT W O OTHER RX PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT APAPPROACH 1 CA (CAN) DURING APPROACH, ENGINE SHUTDOWN UNCOMMANDED AS FLAPS WERE BEING EXTENDED FOR LANDING. POST FLIGHT INSP REVEALED UNSTABLE FUEL FLOW AND LOW ITT AT IDLE POWER. FUEL PUMP AND FUEL CONTROL ARE BEING RETURNED FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221008) 2H72 4T4 TRTA13NM E20NE 20080521 NE 2008 5 21 CA080221009 220080214G7320 EEC AEROSPATR72 ATR72202 8680940EU PWA PW120 PW124B NE ENGINE FAULTED W A UNSCHED LANDING RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CRCRUISE 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 ESTABLISHED (TC NR 20080221009) 2H72 4T4 TRTA53EU E2ONE 20080521 NE 2008 5 21 CA080221010 220080214G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114 52043NE FAILED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, A LOUD NOISE WAS HEARD FOLLOWED BY REDUCTION IN ENGINE POWER TO ZERO. THE AC LANDED ON A PUBLIC ROAD. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221010) 1H71 3T3 T A37CE E4EA 20080603 2008 6 3 CA080221011 420080217G6122 GOVERNOR AEROSPATR72 ATR72 EU PWA PW120 PW127 NE PROPELLER LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 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 PROPELLER OVERSPEED GOVERNOR AREA. THE COMPONENT WAS REPLACED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221011) 2H72 4T4 TRT E20NE 200805141 200805141 NE 2008 5 14 CA080221012 220080214G7314LW15473 PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYSTEM LEAKING W O OTHER K FLUID LOSS NRNOT REPORTED 1 CA 936 (CAN) DURING THE PREFLIGHT CHECK THE ENGINE DRIVEN FUEL PUMP FOUND LEAKING OIL. (TC NR 20080221012) 1G71 3O3 O H11NM 1E4 20081104 2008 11 4 CA080221013 420080214G3416066030620010 ALTIMETER PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL COCKPIT INOPERATIVE W O OTHER J WARNING INDICATION NRNOT 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 20080221013) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20080521 NM 2008 5 21 CA080222001 120080219G3246L8121482629 BEARING DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF* NE MLG WHEEL DISINTEGRATED W K NONE O OTHER ININSP/MAINT 1 CA 19373233 (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 OBSERVED: BOTH WHEEL BRGS WERE DISINTEGRATED ALONG WITH DAMAGE TO THE WHEEL HUB AND BRAKE KEYS, BRAKE DISKS, WHEEL NUT AND MLG AXLE. FOLLOWING OBSERVATIONS WERE NOTICED DURING THE INITIAL INVESTIGATION: THE WHEEL NUT WAS IN PLACE AND SECURED 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. PN2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080521 SO 2008 5 21 CA080222002 220080221G8530655475A CYLINDER CONT O470 O470* 17026SO ENGINE UNSERVICEABLE W K NONE O OTHER ININSP/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 THROUGH MFG. (TC NR 20080222002) 3 O E273 20080521 EU 2008 5 21 CA080222003 120080220G2897 WIRE HARNESS AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE BOOST PUMP CHAFED W K NONE O OTHER ININSP/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) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20080521 NM 2008 5 21 CA080222004 120080215G2497284T3501315 ELECTRICAL BOX BOEING767 767333 1385301NM GE CF6 CF680C2B6F 30025NE CARGO HANDLING BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) WIRING DAMAGE FOUND IN FWD CARGO HANDLING ACCESS PANEL P35 DURING THE (XM) VISIT. 57 WIRES BURN, 3 WIRES MAJOR DAMAGED, 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) 2L72 4F4 FRTA1NM E13NE 20080521 EA 2008 5 21 CA080222005 120080222G32343620377 O-RING CNDAIRCL215 CL2151A10 1900320EA PWA R2800 R2800CA3 52026NE HAMSTD43E 43E60 NE MLG DETERIORATED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) O-RING LOCATED BEHIND INDICATED SCREW IN DIAGRAM, DETERIORATED CAUSING A HYDRAULIC LEAK. THERE ARE (6) LOCATIONS ON THE AC THAT INCORPORATES THIS VALVE. THIS LEAK WAS DISCOVERED ON THE NLG SELECTOR VALVE LOCATED UNDER CO-PILOTS SIDE. (TC NR 20080222005) 2H72 4R4 RRTA14EA 5E8 6 CP871 20080530 EA 2008 5 30 CA080222006 120080219G2910 LINE DHAV DHC2 DHC2MK3 2800107EA PWA PT6 PT6A27 52043EA HYD SYSTEM PUNCTURED W EF ENGINE SHUTDOWN ACTIVATE FIRE EXT. KA FLUID LOSS FLAME/FIRE TXTAXI/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 AT 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 FIRE, SUFFERED 1ST AND 2ND DEGREE BURNS TO HIS FACE AND RIGHT HAND. THE PASSENGER DID NOT RECEIVE ANY INJURIES AND WAS INSTRUMENTAL IN EXTINGUISHING THE PILOT, THE SYSTEM HAS BEEN IN THE ACFT SINCE MANUFACTURING, BUT DOES NOT MATCH ROUTING S1H71 3T4 T A806 E4EA 20080603 EU 2008 6 3 CA080222007 120080215G3211201660001010 BOLT AIRBUSA321 A321211 3930370EU CFMINTCFM56 CFM565B3P 13006NE MLG CORRODED W K NONE O OTHER ININSP/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 295 IS HEAVILY CORRODED. (TC NR 20080222007) 2L72 4F4 FRTA28NM E37NE 20080603 NM 2008 6 3 CA080222008 120080222G271019004209401 CONTROL CABLE EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE AILERON WORN W K NONE F FLT CONT AFFECTED ININSP/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 RIB 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) 2L72 4F4 FRTA57NM E00070EN 20080530 NM 2008 5 30 CA080222009 120080221G271017005825401 CONTROL CABLE EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE AILERON WORN W K NONE O OTHER ININSP/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. EMBRAER WILL ISSUE A SB END OF MARCH (TC# 20080222009) 2L72 4F4 FRTA56NM E00063EN 20080603 NM 2008 6 3 CA080222010 120080221G5315 FLOORBEAM EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE FUSELAGE CORRODED W K NONE O OTHER ININSP/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 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, 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) 2L72 4F4 FRTA56NM E00063EN 200805141 200805141 NE 2008 5 14 CA080225001 220080212G732178639114 HMU DHAV DHC8 DHC8* NM PWA PW121 PW121 52124NE NR 2 ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS APAPPROACH 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 WITH VERY SLOW ACCELERATION REPORTED AND LOW IDLE OF 60 PERCENT ONLY ACHIEVED - NP 168, FUEL FLOW 160, ITT 550 DEGREES. FOLLOWING COMMUNICATION OF THIS DATA WITH THE ENG MFG, IT WAS DETERMINED THAT THE MOST LIKELY CAUSE OF THE DEFECT WAS HYDRO MECHANICAL FCU (HMU) FUEL SCHEDULE. THE HMU AND FUEL PUMP ASSY WAS REPLACED IAW THE AC MM 72-01-40 AND SUBSEQUENTLY GR2H72 4T4 TRTA13NM E20NE 20080521 NM 2008 5 21 CA080225002 120080122G326083260024101 ROLLER DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE NLG SEIZED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA 8236 (CAN) AFTER RETRACTING LANDING GEAR ON TAKEOFF, NOSE GEAR AMBER DOOR LIGHT REMAINED ILLUMINATED. CONDUCTED CHECKS IAW QRH (LANDING GEAR DOOR MALFUNCTIONS) UNABLE TO RECTIFY PROBLEM, RETURNED TO BASE WITH LANDING GEAR EXTENDED FOR NORMAL APPROACH AND LANDING. INSP OF THE AC BY MAINT AFTER RETURN OF THE AC TO THE TERMINAL DETERMINED THAT THE NLG DOORS WERE CLOSED BUT THE CORRESPONDING INDICATION WAS OF AN UNSAFE CONDITION. FUNCTIONAL CHECK OF THE NLG DOORS AND INDICATING SYS CARRIED OUT. THE ALTERNATE RELEASE ROLLER TRIPPING ARM BRG WAS DISCOVERED TO BE SEIZED AND THE CLEARANCE BETWEEN THE ROLLER AND OB TOGGLE LINK OUT OF ADJUSTMENT. ROLLER PN 83260024-101 WAS REPLACED AND THE ALTERNATE RELEASE CABLE ADJUSTED IAW2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080521 NM 2008 5 21 CA080225003 120080219G29136617303 PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R320 CR3204123F1 GL NR 2 ENGINE SEPARATED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) NR 2 EDP FAILED IN FLIGHT WITH A BANG FOLLOWED SHORTLY AFTER BY NR1 HYD FLUID HOT CAUTION LIGHT ILLUMINATING, FOLLOWED BY THE 1 HYD ISO VALVE TO CLOSING. THE AC MADE A FLAPLESS EMERGENCY LANDING. INITIAL INVESTIGATION BY MAINT FOUND THAT THE NR2 HYD SYS HAD LOST ITS FLUID, THE NR2 EDP PORT CAP HAD SEPARATED FROM THE EDP PUMP BODY, THE PTU WAS INOPERATIVE (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 APPLICABLE HYDR LINES. (TC NR 20080225003) 2H72 4T4 TRTA13NM E00062EN6 CP5NE 20080521 EA 2008 5 21 CA080225005 120080222G2421731579 SHAFT CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF343A2 30067NE IDG BROKEN W H DEACTIVATE SYST/CIRCUITS O OTHER CLCLIMB 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) 2L72 4F4 FRTA21AE E15NE 20080603 GL 2008 6 3 CA080225006 320080221G6114 HUB HARTZL HCE4A3D PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL PROPELLER LEAKING W K NONE K FLUID LOSS CRCRUISE 1 CA 663 (CAN) PROPELLER REMOVED DUE TO EXCESSIVE GREASE LEAK FROM BLADE CLAMPS. (TC NR 20080225006) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20080603 2008 6 3 CA080225007 420080221G23306009580001 MONITOR BOEING757 75728A 1384976NM RROYCERB211 RB211535E43754555NE CABIN MALFUNCTIONED W O OTHER B SMOKE/FUMES/ODORS/SPARKS APAPPROACH 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) 2L72 4F4 FRTA2NM E12EU 20081230 CE 2008 12 30 CA080225009 120080221G27300510105125 CONTROL CABLE CESSNA180 180K 2072624CE CONT O470 O470* 17026SO MCAULY2A34C C2A34C204 GL ELEVATOR FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA 140, WHERE CABLE RIDES ON THE PHENOLIC BLOCK. 1H71 3O3 O 5A6 E273 5 CP3EA 20081230 CE 2008 12 30 CA080225010 120080204G27300510105125 CONTROL CABLE CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL ELEVATOR FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA140 AT PHENOLIC BLOCK. 1H71 3O3 O 3A24 E5CE 5 CP3EA 20081230 CE 2008 12 30 CA080225011 120080211G27300510105125 CONTROL CABLE CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C401 GL ELEVATOR FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA 140 AT THE PHENOLIC BLOCK. 1H71 3O3 O 3A24 E5CE 5 CP47GL 20080530 EA 2008 5 30 CA080225012 120080222G534319064104 FITTING CNDAIRCL604 CL604 1900301EA MLG CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 4481 DURING LANDING GEAR 96 MONTH DETAIL INSPECTION HEAVY PITTING CAUSED BY CORROSION. FOUND ON MAIN LANDING GEAR MAIN FITTING TRAILING ARM ATTACHMENT INBOARD LUG BUSHING AREA AND BORE, RESULTING CONSIDEABLE AMOUNT OF MATERIAL FROM AFFECTED LOCATION, LEADING MAIN FITTINGTO REDUCED LOAD CARRYING CAPACITY 2L72 4F RTA21EA 20090102 CE 2009 1 2 CA080225013 120080220G323026410148 SPRING CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL MLG WORN W K NONE O OTHER ININSP/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 COULD 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 MEASURED 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 N1H71 3T3 T A37CE E4EA 5 CP60GL 20080530 NM 2008 5 30 CA080225014 120080222G2750 CLUTCH BOEING737 737200 1384453NM PWA JT8 JT8D17A 52049NE TE FLAP DISENGAGED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 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 INSPECTED, THE CLUTCH BELLCRANK RESET AND THE SYSTEM FUNCTION CHECKED SERVICEABLE. (TC# 20080225014) 2L72 4F4 F A16WE E2EA 200805141 200805141 2008 5 14 CA080225015 220080225G7414 BEARING 106006169 MAGNETO EXCESS PLAY W K NONE O OTHER ININSP/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 .003 INCH. THE BRGS WERE INSPECTED, SHIMS WERE ADDED, THE REST OF THE 500 HOUR INSP WAS CARRIED OUT, AND THE MAG WAS RETURNED TO SERVICE. THE MAG HAD 473.8 HRS SINCE ITS PREVIOUS 500 HR INSP. (TC NR 20080225015) 20081104 EA 2008 11 4 CA080226001 220080222G7322 THROTTLE BODY PIPER PA18 PA18A135 7101822SO LYC O320 O320A2B 41508EA SNSNCH74DM M74DM EA CARBURETOR LOOSE W K NONE RJ PARTIAL RPM/PWR LOSS WARNING INDICATION ININSP/MAINT 1 CA 279 (CAN) DURING GROUND RUN UP PRIOR TO ANNUAL INSPECTION, ENGINE OBTAINED A MAXIMUM RPM OF 1900. INSPECTION FOUND CARBURETOR THROTTLE BODY SCREWS LOOSE AND FUEL STAINS ON BOWL. CARBURETOR REMOVED AND FORWARDED TO REPAIR FACILITY. (TC N 20080226001) 1H71 3O3 O 1A2 E274 5 NP88614 20090102 CE 2009 1 2 CA080226002 120080219G32450923150 TUBE CESSNA425 425 2076018CE PWA PT6 PT6A112 52043NE MCAULY4HFR344HFR34C762 NE NLG TIRE DESTROYED W O OTHER E VIBRATION/BUFFET LDLANDING 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. 1L72 3T3 TRTA7CE E4EA 6 C3PNE 20081104 EU 2008 11 4 CA080226003 120080224G3110 ANNUNCIATOR SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B 60037NE MALFUNCTIONED W O OTHER P NO WARNING INDICATION NRNOT REPORTED 1 CA 1403 (CAN) ON A ROUTINE CHECK FOLLOWING START, THE ANNUNCIATOR LIGHT FOR GOV FAILURE (RED) FAILED TO ILLUMINATE WHEN THE ENGINE GOV SWITCH WAS MOVED FROM AUTO TO MANUAL. OTHER FUNCTIONS ASSOCIATED WITH MOVING TO MANUAL (SOLENOID, VEMD FAILURE CODES) 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) 1G71 3U3 U H9EU E00054EN 20080521 SW 2008 5 21 CA080226004 120080222G2420ALX8403 ALTERNATOR GULSTM112 112 0144701SW LYC O360 IO360C1D6 41514EA HARTZLHCE2Y HCE2YR1BF GL ELECTRICAL UNSERVICEABLE W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA (CAN) ALTERNATOR FAILED, CAUSING MAIN BATTERY TO DRAIN RESULTING IN COMMUNICATION DIFFICULTIES WHICH CAUSED PILOT TO CONTACT TOWER BY CELL PHONE FOR CLEARANCE TO LAND. NEW UPGRADED ALTERNATOR INSTALLED PN ALX8521R (TC NR 20080226004) 1L71 3O3 O A12SO 1E10 5 CP9EA 20080521 EU 2008 5 21 CA080227001 120080131G2121 BEARING SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE ROTOL R389 R3894123F26 NE BLOWER MOTOR FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 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 THAT A FAILED BEARING IN THE ASSEMBLY IS THE CAUSE OF THE FAULT. (TC NR 20080227001) 2L72 4T4 TRTA52EU E8NE6 6 CP30NE 20080521 CE 2008 5 21 CA080227002 120080226G5210SL51043 SPINDLE CESSNA560 560XL 2076702CE PWA 545 PW545A NE MAIN CABIN DOOR WORN W K NONE O OTHER ININSP/MAINT 1 CA 1583 (CAN) CREW SNAGGED MAIN CABIN DOOR OUTER HANDLE AS BEING SLOPPY. DISASSEMBLED DOOR HANDLE AND FOUND OUTER DOOR HANDLE SPINDLE 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 WOULD FAIL SOON AND ALLOW THE HANDLE (OUTER) TO COME OFF AND POSSIBLY BE INGESTED BY THE LT ENGINE. (TC NR 20080227002) 2L72 4F4 FRTA22CE E00059EN 20080521 EA 2008 5 21 CA080227003 120080219G7931 OIL SYSTEM CNDAIRCL604 CL604 1900301EA GE CF34 CF343B 30069NE ENGINE LOW PRESSURE W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) LOW OIL PRESS WARNING ON NR 2 ENGINE APPROX 3 MINS AFTER TAKEOFF AT 6000FT MSL ON DEPARTURE CLIMBOUT. AFTER IDENTIFICATION OF FAULT AND CONFIRMATION THAT THE FAULT WAS NOT AN INDICATION PROBLEM NR 2 ENGINE WAS SHUTDOWN AND SECURED. RETURNED SAFELY. THE CAUSE HAS YET TO BE DETERMINED. (TC NR 20080227003) 2L72 4F4 FRTA21EA E15NE 20081104 SW 2008 11 4 CA080227004 120080201G531120631308015S FRAME BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL FUSELAGE CRACKED W K NONE O OTHER ININSP/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) 1G71 3U3 U H2SW E4CE 20080521 SW 2008 5 21 CA080227005 120080131G5320206031322003 STIFFENER BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL FUSELAGE CRACKED W K NONE O OTHER ININSP/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) 1G71 3U3 U H2SW E4CE 20080521 NE 2008 5 21 CA080227006 220080122G741410885435 CAM ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO BROKEN W K NONE O OTHER ININSP/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 TAPPED OFF SHAFT WITH BRASS PUNCH AND HAMMER. WHEN CAM CAME OFF SHAFT IT BROKE INTO 4 PIECES. (TC NR 20080227006) 1G71 3O3 O H11NM 1E4 20080530 GL 2008 5 30 CA080227007 220080227G72306898607 BEARING RACE BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL COMPRESSOR SPALLED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 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 AND THE FLIGHT CONTINUED. A FEW HOURS LATER ANOTHER CHIP LIGHT HAD ILLUMINATED. THE AIRCRAFT WAS RETURNED TO THE BASE VIA TRUCK AND TRAILER. FURTHER INVESTIGATION REVEALED FWD CHIP PLUG HAD METAL EVIDENT ON THE PLUG. THE COMPRESSOR WAS REMOVED 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) 1G71 3U3 U H2SW E4CE 20080530 SW 2008 5 30 CA080227008 120080227G632023034787 BEARING RACE BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL GEARBOX SPALLED W O OTHER J WARNING INDICATION CRCRUISE 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. 1G71 3U3 U H2SW E4CE 20080603 NM 2008 6 3 CA080228001 120080119G3230C247300016 UPLOCK AIRBUSA319 A319114 3930350NM GE CFM56 CFM565A 13802NE NLG FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 29460 AFTER TAKEOFF, THE CREW COULD NOT RETRACT THE NOSE GEAR. THE GEAR WAS RECYCLED WITH NO SUCCESS. THE CREW RETURNED TO LAND 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 LOCKING TEST. THE LOCK MECHANISM INSIDE THE UNIT FAILED TO LOCK THE HOOK. THE REPAIR FACILITY CONCLUDED THAT THE DRIED GREASE 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 2L72 4F4 FRTA28NM E29NE 200805141 200805141 NM 2008 5 14 CA080228002 120080222G531517003264001 FLOORBEAM EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE FUSELAGE CORRODED W K NONE O OTHER ININSP/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 PLATES 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 PROTECTION UNDERNEATH THE GALLEY NOT ADEQUATE. (TC NR 20080228002) 2L72 4F4 FRTA56NM E00063EN 20080521 NM 2008 5 21 CA080228003 120080215G215018279018 ACM DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE FAILED W GA O2 MASK DEPLOYED UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 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 TO THE MFG FOR REPAIR/OVERHAUL WITH A REQUEST TO PROVIDE A STRIP REPORT. (TC NR 20080228003) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080521 NM 2008 5 21 CA080228004 120080219G3230483025 SEQUENCE VALVE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R320 CR3204123F1 GL NLG FAILED W O OTHER J WARNING INDICATION CLCLIMB 1 CA 93 (CAN) AN OPERATOR COMPLETED AN EMERGENCY LANDING DUE TO NLG DOOR OPEN INDICATION AFTER SELECTING GEAR UP. UNSCHEDULED LANDING, CREW FOLLOWED THEIR QRH, PERFORMED ALTERNATE GEAR EXTENSION. NLG SOLENOID SEQUENCE VALVE REPLACED. (TC NT 20080228004) 2H72 4T4 TRTA13NM E00062EN6 CP5NE 20081104 SW 2008 11 4 CA080228007 120080124G3246206050297105 SKID BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 8330 (CAN) UPON INSTALLATION OF GROUND HANDLING WHEELS IT WAS DISCOVERED THAT THE MOUNTING LUGS ON THE FWD LT SIDE WAS DETACHED 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) 1G71 3U3 U H2SW E4CE 20080521 NM 2008 5 21 CA080228009 120080225G3260 SENSOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R320 CR3204123F1 GL MLG DOWNLOCK FAULTED W C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 CA (CAN) AFTER DEPARTURE, AN ABNORMAL GEAR INDICATION WAS OBSERVED. DECISION TO CONTINUE TO NEXT BASE IAW MCC AND OCM. ON ARRIVAL, 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 AND NORMAL DISEMBARKATION ON THE RUNWAY FOLLOWED. PSEU FAULT CODES AS FOLLOWS: LEG 00: LGDLK 1 PROX SENSOR OPEN, LGDLK 1 PROX SENSOR SHORT, PSEU CHANNEL D FAIL CHANNEL INOP, LGDLK1 UNREASONABLE NEAR, NLGLK2 UNREASONABLE NEAR, NLGLK1 UNREASONABLE NEAR, NGDRCL UNREASONABLE NEAR, NGWOFW2 UNREASONABLE NEAR NGWOFW1 UNREASONABLE NEAR, NGDN2 UNREASONABLE FAR, NGDN1 U2H72 4T4 TRTA13NM E00062EN6 CP5NE 20080521 NM 2008 5 21 CA080228010 120080225G2750734386B TORQUE TUBE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE TE FLAPS SHEARED W O OTHER J WARNING INDICATION APAPPROACH 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. THE A/C LANDED WITHOUT INCIDENT. MAINT INSP REVEALED THAT THE LT OB TORQUE TUBE WAS SHEARED OFF. AFTER FURTHER INSP, IT WAS DETERMINED THAT THE TORQUE TUBE WAS SHEARED OFF BY CLAMP INSTALLED ON A DRAIN LINE THAT HAD BEEN CHAFING. THE TORQUE TUBE WAS REPLACED, THE TORQUE SENSOR RIGGED AND THE FLAPS WERE FUNCTION CHECKED SERVICEABLE. (TC NR 20080228010) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080602 SW 2008 6 2 CA080228011 120080227G32302752003042 BELLCRANK SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE3311 01514WP MCAULY4HFR344HFR34C652 NE NLG MISSING W K NONE O OTHER ININSP/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) 2L72 4T3 TRTA8SW E3WE 6 C3PNE 20080602 SW 2008 6 2 CA080228012 120080220G3222MS171536 PIN FRCHLD SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE3311 01514WP MCAULY4HFR344HFR34C652 NE RH TORQUE KNEE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA PIVOT PIN FOR RT MAIN GEAR TORQUE KNEE WAS PROTRUDING FROM THE TORQUE KNEE. SPRING PIN REMOVED AND INSPECTED. NO DAMAGE FOUND. NEW SPRING PIN INSTALLED. NO FURTHER PROBLEMS SINCE REPLACEMENT OF SPRING PIN (TC NR 20080228012) 2L72 4T3 TRTA8SW E3WE 6 C3PNE 20080602 EA 2008 6 2 CA080229001 120080218G5610NP1393222 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT CRACKED W O OTHER O OTHER DEDESCENT 1 CA 10959 FLT NR 6671 - FIRST OFFICER SIDE WINDOW CRACKED ON DESCENT INTO PSP. WINDOW REPLACED (TC NR 20080229001) 2L72 4F4 FRTA21EA E15NE 20080602 NE 2008 6 2 CA080229002 220080221G72004129T17G04 ACTUATOR CNDAIRCL600 CL6002D24 1390016EA GE CF34 CF348C1 30049NE LT ENGINE CRACKED W O OTHER YJ ENGINE STOPPAGE WARNING INDICATION APAPPROACH 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 NO PROBLEMS WITH FUEL FLOW, ITT, OIL PRESSURE OR WARNINGS. CVR AND FDR CIRCUIT BREAKERS HAVE BEEN PULLED. AIRCRAFT VERIFIED NOT IMPOUNDED BY THE NTSB. CONTRACT MX INTERROGATE MDC. MDC REVEALED LH PS3 SENSE LINE, L FMU FAILED AND VG CMD\POSN 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 INSPECT2L72 4F4 FRTA21EA E00063EN 200805141 200805141 NM 2008 5 14 CA080229003 120080221G3260864202 PROXIMITY SENSOR DHAV DHC8 DHC8* NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NLG INTERMITTENT W D RETURN TO BLOCK N FALSE WARNING TXTAXI/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 OHMS. THE NLG DRAG STRUT SENSOR WAS REPLACED IAW THE AC MM 32-20-11. NLG RETRACTION AND EXTENSION CHECKS/ TESTS CARRIED OUT IAW AC MM 32-30-00, ALL INDICATIONS CHECKED SERVICEABLE. AC RETURNED TO SERVICE. (TC NR 20080229003) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080521 CE 2008 5 21 CA080229004 120080228G2420 PULLEY CESSNA210 210R 2073458CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL ALTERNATOR SEPARATED W K NONE J WARNING INDICATION ININSP/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. RETAINING 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) 1H71 3O3 ORT3A21 E5CE 5 CP47GL 20080521 CE 2008 5 21 CA080229005 120080229G57530512128 BRACKET CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL TE FLAPS BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 7402 (CAN) ON PREFLIGHT INSPECTION, PILOT FOUND WHEN FLAPS EXTENDED, LT FLAP HAD NO TENSION, AND COULD BE LIFTED TO THE RETRACT POSITION, POTENTIALLY CAUSING DISIMILAR LIFT WHEN ACTIVATED IN FLIGHT. INSPECTED AREA, AND FOUND LT BRACKET BROKEN AT F.S. 65.33, IB MOUNTING TABS BROKEN. SIMILAR OCCURANCE INSPECTED AREA EACH 100 HRS SINCE, NO INDICATION OF CRACKS PREVIOUSLY DETECTED. SUSPECT THAT FAILURE IS IMMEDIATE AS BREAKS LOOK NEW. POORLY DESIGNED PART FOR LOADS THAT ARE IMPOSED. (TC NR 20080229005) 1H71 3O3 O 3A24 E5CE 5 CP3EA 20080521 2008 5 21 CA080229007 420080220G2565416T28243 LEVER BOEING767 76735H 1385208NM GE CF6 CF680C2B6F 30025NE OVERWING SLIDE MISINSTALLED W K NONE W INADEQUATE Q C ININSP/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-DOWN. THIS APPEARS TO CAUSE THE LEVER TO BIND WITH THE FIRING PIN CLEVIS AND COULD PREVENT NORMAL DOOR OPENING ACTUATION IN 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) 2L72 4F4 FRTA1NM E13NE 20080521 GL 2008 5 21 CA080229008 220080206G7200 ENGINE BELL 407 407 1182206SW ALLSN 250C 250C47B GL VIBRATION W O OTHER E VIBRATION/BUFFET NRNOT REPORTED 1 CA (CAN) EXCESSIVE ENGINE NOISE AND HIGH VIBRATION FELT BY PILOT AT GROUND IDLE. VERFIED BY ENGINEER. COMPLETE ENGINE REMOVED AND SENT FOR INVESTIGATION. WILL FWD REPORT WHEN AVAILABLE. (TC NR 20080229008) 1G71 3U3 UO H2SW E1GL 20080521 GL 2008 5 21 CA080229010 220080227G7230 SCROLL ALLSN BELL 407 407 1182206SW ALLSN 250C 250C47B GL COMPRESSOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) COMPRESSOR 390.6 SINCE 2000 HOUR INSP. CRACK LOCATED BY ENGINEER DURING GROUND RUN UP FOLLOWING SCHEDULED INSP. LOCATED 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) 1G71 3U3 UO H2SW E1GL 20080521 SO 2008 5 21 CA080229011 120080226G81204091701 SHAFT PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL TURBOCHARGER SHEARED W A UNSCHED LANDING BR SMOKE/FUMES/ODORS/SPARKS PARTIAL RPM/PWR LOSS CRCRUISE 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. MAINT FOUND THE SHAFT THAT CONNECTS THE EXHAUST AND INTAKE TURBINE WHEELS ON THE TURBOCHARGER WAS BROKEN AT THE EXHAUST TURBINE WHEEL. NO REASON COULD BE FOUND FOR THE FAILURE. THE TURBOCHARGER HAD 2.7 HOURS SINCE OVERHAUL. (TC NR 20080229011) 1L72 3O3 O A20SO E14EA 5 CP33EA 20080521 EA 2008 5 21 CA080229012 220080229G8530LW12966 CYLINDER PIPER PA28 PA28140 7102802SO LYC O540 TIO540J2BD 41532EA ENGINE UNSERVICEABLE W BA EMER. DESCENT UNSCHED LANDING R PARTIAL RPM/PWR LOSS NRNOT 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 INSPECTION 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 ITSELF 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) 1L71 3O3 O 2A13 E14EA 20080521 NM 2008 5 21 CA080303001 120080228G5315 FLOORBEAM EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE FUSELAGE CORRODED W K NONE O OTHER ININSP/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 FLOORBEAM 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 PLATES 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 20080303001) 2L72 4F4 FRTA56NM E00063EN 20080602 NM 2008 6 2 CA080303002 120080228G271017005825401 CONTROL CABLE EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE AILERONS DAMAGED W K NONE O OTHER ININSP/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 BROKEN AT FAIRLEADS, LOCATED AT LT 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. EMBRAER HAVE BEEN ADVISED (TC NR 20080303002) 2L72 4F4 FRTA56NM E00063EN 20080603 SO 2008 6 3 CA080303003 120080229G2421 BEARING PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL ALTERNATOR FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CRCRUISE 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 HAD SEIZED AND BROKEN THE BELT. (TC NR 20080303003) 1L72 3O3 O A20SO E14EA 5 CP33EA 20081104 SW 2008 11 4 CA080303004 120080303G6510327211 DISC PACK BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL T/R DRIVE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2562 (CAN) DISC PAC WAS REMOVED FOR INSPECTION DURING A SCHEDULED 1200 HOUR INSPECTION. CRACKED DISC WAS DISCOVERED DURING DISASSEMBLY. ONE DISC OF TEN IN PAC WAS COMPLETELY CRACKED ON BOTH SIDES ON ATTACHEMENT BOLT HOLE SO THAT A PIECE OF THE DISC 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. 1G71 3U3 U H2SW E1GL 20080603 GL 2008 6 3 CA080303005 220080302G732223034702 FUEL CONTROL BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL ENGINE LEAKING W K NONE O OTHER ININSP/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 20080303005) 1G71 3U3 U H2SW E4CE 20090102 CE 2009 1 2 CA080303006 120080303G3411 STATIC PORT BEECH 23 B23 1151240CE LYC O360 O360A2G 41514EA SNSNCH76E M76EMMS EA RT OBSTRUCTED W K NONE O OTHER ININSP/MAINT 1 CA 2312 2312 (CAN) WHILE DOING A PRE-PURCHASE INSP, DISCOVERED A PIECE OF TAPE COVERING THE RT STATIC PORT. 1L71 3O3 ORTA1CE E286 5 NP4EA4 20081104 SW 2008 11 4 CA080303008 120080229G6520476400751 GEARBOX BELL 47 47G2 1181008SW LYC O435 VO435A1D 41516EA TAIL ROTOR MAKING METAL W K NONE O OTHER ININSP/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 GEARBOX WAS REMOVED FROM SERVICE AND OH ONE INSTALLED AND ACFT WAS RELEASED. MORE INFO WILL BE POSTED AS THE GEARBOX IS DISASSEMBLED. 1G71 3O3 O H1 E279 20080521 EA 2008 5 21 CA080303009 220080301G855077517 SUMP FOUND FBA FBA2C1 3640103EA LYC O540 IO540L1A5 41532EA HARTZLHCC3Y HCC3YR GL ENGINE OIL SYS UNSERVICEABLE W K NONE O OTHER ININSP/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 CONTAMINATION AND SERVICEABILITY. (TC NR 20080303009) 1H71 3O3 ONCA7EA 1E4 5 CP25EA 200805141 200805141 2008 5 14 CA080304001 420080204G3418543036B29 COMPUTER CNDAIRCL600 CL600* 1900302EA GE CF34 CF343A2 30067NE STALL WARNING FAULTY W O OTHER W INADEQUATE Q C NRNOT REPORTED 1 CA (CAN) IT TOOK (3) STALL WARNING COMPUTER BEFORE GETTING ONE THAT WAS SERVICEABLE , THEY ALL FAIL THE TEST IAW TEST PROCEDURE MM PSP601-2 CHAP 27-39-00 P 206 207 NB MFG PRODUCTS (TC NR 20080304001). 2L72 4F4 FRTA21EA E15NE 20080602 NM 2008 6 2 CA080304003 120080229G2497IN3311B DIODE BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU OPEN W O OTHER P NO WARNING INDICATION CRCRUISE 1 CA EN ROUTE, AFTER SHUTTING OFF CENTER TANK BOOST PUMPS, LEFT CENTER, LEFT AFT AND RIGHT FORWARD LOW PRESSURE LIGHTS DID NOT 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 PRESSURIZATION 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 THROUGH BRIGHT/DIM/TEST AND THE GEAR INDICATION RETURNED. THE AIRCRAFT WAS LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE WAS2L72 4F4 FRTA16WE E21EU 20080602 2008 6 2 CA080304004 420080303G34165035PP41 ENCODER ALTIMETER DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA WHEN RECEIVED FOUND WITH TIN BETWEEN CASE AND PIN ON CONNECTION RECEPTACLE. 20080602 EU 2008 6 2 CA080304005 120080227G2910A3248021101100 LINE AIRBUS310 A310304 3930339EU GE CF6 CF680C GL HYD SYSTEM SPLIT W K NONE K FLUID LOSS ININSP/MAINT 1 CA WHILE AIRCRAFT WAS UNDER MAINTENANCE IN THE HANGAR, THE HYDRAULIC RETURN LINE FOR YELLOW SYSTEM ALTERNATE BRAKE FAILED WITH A SPLIT IN THE TUBING APPROX 1.5 INCHES IN LENGTH. AT THE TIME OF THE FAILURE THERE WAS NO HYDRAULIC PRESSURE OR OPERATION OF THE SYSTEM. THE LINE WAS REPLACED AND SYSTEM TESTED SERVICEABLE. LINE WAS SENT TO AIRBUS FOR ANALYSIS. (TC NR 20080304005) 2L72 4F4 FRTA35EU E23EA 20080602 2008 6 2 CA080304006 120080304G8011 STARTER ENGINE FAILED W K NONE O OTHER ININSP/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 220080205G8500 ENGINE PIPER PA31 PA31310 7103103SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL MAKING METAL W K NONE O OTHER ININSP/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 WHICH INDICATES CAMSHAFT AND FOLLOWERS, ALTHOUGH THIS IS NOT AS YET SUBSTANTIATED. THE ENGINE HAS BEEN OPERATED FOR 88.1 HOURS 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) 1L71 3O3 ORTA20SO E14EA 5 CP33EA 20080521 WP 2008 5 21 CA080304009 220080303G73218978017 FUEL CONTROL SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL ENGINE FAILED W K NONE O OTHER ININSP/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 RESISTANCE, 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 SENT FOR REPAIR AND A TEARDOWN REPORT REQUESTED. (TC NR 20080304009) 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20080521 EA 2008 5 21 CA080304010 120080303G3230533407 SELECTOR VALVE CNDAIRCL600 CL6002C10 1390015EA GE CF700 CF7002D2 30010NE MLG FAILED W L ABORTED APPROACH J WARNING INDICATION APAPPROACH 1 CA (CAN) DISC LANDING GEAR WOULD NOT EXTEND. PERFORMED MANUAL/EMERGENCY EXTENTION. ENG HYDR PUMP PRESSURE WAS NORMAL. REMOVED 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) 2L72 4F4 FRTA21EA E7EA 20080521 CE 2008 5 21 CA080304011 120080118G323399101399 ACTUATOR CESSNA441 441 2076020CE GARRTTTPE331TPE3318 01514WP HARTZLHCB3T HCB3TN5 GL NLG FAILED W O OTHER Z SIGNIFICANT FAILURE REPORT LDLANDING 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 PULLED INTO THE DOWN AND LOCKED POSITION. INITIAL INSP OF THE GEAR SYS FOUND ALL TO BE IN WORKING ORDER, GEAR SWINGS PERFORMED NORMALLY. THE ACTUATOR`S INTEGRAL POSITION INDICATION SWITCH MALFUNCTIONED CAUSING THE HYD SYS PRESSURE TO THE NOSE GEAR ACTUATOR TO STOP PREMATURELY BEFORE THE NOSE GEAR WAS FULLY EXTENDED AND IN THE OVER CENTER POSITION. (TC NR 20080304011) 1L72 3T4 TRTA28CE E4WE 6 CP15EA 20081104 WP 2008 11 4 CA080304012 120080302G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA 289 (CAN) STARTER - COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BREAKING 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. 1G71 3O3 O H11NM 1E4 20081104 WP 2008 11 4 CA080304013 120080228G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 14 (CAN) STARTER -COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BREAKING 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) 1G71 3O3 O H11NM 1E4 20081104 WP 2008 11 4 CA080304014 120080217G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 62 (CAN) STARTER - COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BREAKING 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) 1G71 3O3 O H11NM 1E4 20080602 GL 2008 6 2 CA080305001 220080303G7261 PRESSURE SWITCH AIRBUS310 A310304 3930339EU GE CF6 CF680C GL ENGINE OIL MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 479931630 DURING CLIMB AT 18000 FEET, NR 1 ENGINE OIL FILTER CLOGGED LIGHT CAME ON. AS PER QRH, NR 1 ENGINE WAS SHUT DOWN. AIRCRAFT 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. 2L72 4F4 FRTA35EU E23EA 20080521 CE 2008 5 21 CA080305002 120080303G2121C4140070102 COOLING FAN CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL COCKPIT NOISY W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA (CAN) ON CLIMBOUT FLIGHT CREW HEARD A LOUD SQUEALING NOISE FROM THE AVIONICS COOLING FAN. IN COLD TEMPERATURES THIS IS TYPICAL OF THE COOLING FAN AND THE FLIGHT CREW DECIDED TO ALLOW THE FAN TO WARM UP. AFTER A COUPLE MINUTES THE FLIGHT CREW DECIDED TO RETURN. APPROX 5 MINUTES LATER DURING VECTORS BACK THE FLIGHT CREW BEGAN TO SMELL A BURNED SMELL IN THE COCKPIT AND PULLED THE AVIONICS FAN CIRCUIT BREAKER, THE SMELL STOPPED. AT THE TIME, THE FLIGHT CREW ALSO COMMENTED ON SMOKE 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) 1H71 3T3 T A37CE E4EA 5 CP60GL 20081104 NE 2008 11 4 CA080305003 220080228G7200 PIN SKRSKYS92 S92A NE GE CT7TS CT78A 30136NE ENGINE FOD W O OTHER CR F.O.D. PARTIAL RPM/PWR LOSS CRCRUISE 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 ARRIVAL AT AIRPORT AND DAMAGE IN ENGINE PARTICLE SEPARATOR WAS NOTICED. SMALL HANDLE. PIN FROM HINGE ASSY FOUND TO HAVE BECOME DETACHED FROM ASSY AND ENTERED THE ENGINE INTAKE RESULTING IN FOD DAMAGE TO ENGINE. 2G72 4U4 U R00024BOE8NE 200805141 200805141 NM 2008 5 14 CA080305004 120080221G381014C3308 COUPLER BOEING737 7378Q8 13844BXNM CFMINTCFM56 CFM567B26US NE POTABLE WATER CRACKED W BG EMER. DESCENT O2 MASK DEPLOYED ZS SIGNIFICANT FAILURE REPORTAFFECT SYSTEMS CRCRUISE 1 CA (CAN) DURING CRUISE, CREW NOTED CABIN ALTITUDE WARNING. UNABLE TO CLOSE OUTFLOW VALVE EITHER ELECTRICALLY OR MANUALLY. EMERGENCY 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 PORTABLE WATER LEAKING AT FITTING AND FITTING PARTLY SEPARATED WITH WIGGENS COUPLING OPEN. UPON INSP OF REMOVED COUPLING FOUND CRACKED. (TC NR 20080305004) 2L72 4F4 FRTA16WE E00055EN 20080521 EU 2008 5 21 CA080305008 120080225G2421ALU8521R ALTERNATOR ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA MUHBR MTV MTV9* EU FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CRCRUISE 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 ALTERNATOR CASE. THE FREE WIRE ENABLED A RAPID DISCHARGE OF THE BATTERY. (TC NR 20080305008) 1L71 3O3 O0 A76EU 1E10 5 CP24NE 20080521 SO 2008 5 21 CA080305011 120080305G2140CD21252 SWITCH PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2B NE HARTZLHCE3Y HCE3YR2A GL HEATER INTERMITTENT W O OTHER O OTHER CRCRUISE 1 CA 31 (CAN) THE PILOT REPORTED THAT THE HEATER DID NOT WORK. MAINT INVESTIGATED AND DETERMINED THAT THE CYCLING SWITCH WAS DEFECTIVE AND REPLACED THE SWITCH. THE CREW AGAIN REPORTED THAT THE HEATER DID NOT WORK PROPERLY. MAINT DID MORE TROUBLESHOOTING AND DETERMINED THAT THE CYCLING SWITCH FUNCTIONED PROPERLY INSIDE A HEATED HANGAR. HOWEVER WHEN LEFT OUTSIDE AT ABOUT -20 DEGREES CELSIUS THE SECOND SWITCH ALSO FAILED TO FUNCTION PROPERLY. THE HEATER WAS INSTALLED NEW ABOUT 218 HRS AGO AND THE FIRST CYCLING SWITCH FAILED AFTER 188.3 HRS. (TC NR 20080305011) 1L72 3O3 O A20SO E14EA 5 CP33EA 20080521 NE 2008 5 21 CA080305012 220080219G7320 EEC CESSNA560 560XL 2076702CE PWA 545 PW545A NE ENGINE MALFUNCTIONED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 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 AIRCRAFT RETURNED TO THE GATE. TROUBLESHOOTING IS ONGOING. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080305012) 2L72 4F4 FRTA22CE E00059EN 20080521 NE 2008 5 21 CA080305013 220080219G7200 ENGINE CESSNA500 550 2076604CE PWA 530 PW530A NE FLAMED OUT W D RETURN TO BLOCK XJ ENGINE FLAMEOUT WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) WHILE DEICING THE AC AND PERFORMING SYSTEMS CHECKS, THE ENGINE FLAMED OUT WHEN BROUGHT TO IDLE POWER. THE ENGINE FLAMED OUT (2) ADDITIONAL TIMES UNDER SIMILAR CIRCUMSTANCES DURING TROUBLESHOOTING. ATTENTION IS FOCUSING ON THE FUEL CONTROL AND AIRFRAME RIGGING. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080305013) 1L72 4F4 F A22CE E00053EN 200805141 200805141 NE 2008 5 14 CA080305016 220080301G7200 ENGINE PWC PW545B CESSNA560 560XL 2076702CE PWC 545 PW545B NE POWER LOSS W E ENGINE SHUTDOWN RFJPARTIAL RPM/PWR LOSS FLT CONT AFFECTED WARNING INDICATION DEDESCENT 1 CA (CAN) DESCENDING THROUGH FL370, THE ENGINE ELECTRONIC CONTROL REVERTED TO MANUAL AND ENGINE N2 SPEED REDUCED TO 41 PERCENT ASSOCIATED WITH VIBRATION. THE ENGINE DID NOT RESPOND TO THRUST LEVER INPUT AND THE CREW ELECTED TO SHUTDOWN THE ENGINE. TROUBLESHOOTING IS ONGOING. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080305016) 2L72 4F4 FRTA22CE E00059EN 20081104 WP 2008 11 4 CA080305017 120080220G6710369A7304 BRACKET HUGHES369 369A 4470503WP ALLSN 250C 250C20B 03013GL ROTOR CONTROL UNSERVICEABLE W K NONE O OTHER ININSP/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. 1G71 3U3 U H3WE E4CE 20080521 EU 2008 5 21 CA080306002 120080304G2910HTE400005 VALVE BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP ROTOL R333 R333482F12 GL HYD SYSTEM FAILED W O OTHER K FLUID LOSS CRCRUISE 1 CA (CAN) THE RT NON RETURN VALVE ASSEMBLY DOWNSTREAM OF THE RT HYDRAULIC PUMP FAILED. NON RETURN VALVE ASSEMBLY IS A UNIT THAT 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. TIME AND CYCLES ON PART ARE UNKNOWN BUT IT IS VERY LIKELY ORIGINAL EQUIPMENT. (TC NR 20080306002) 2L72 4T4 TRTBA15CAA E4WE 6 CP61GL 20081104 2008 11 4 CA080313002 420080312G3197 CONNECTOR SNIAS 350 AS350BA 8680817EU INSTRUMENT LIGHTBURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 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 THE UNIT IS UNSERVICABLE. (TC NR 20080313002) 1G71 3U NCH9EU 20080602 EU 2008 6 2 CA080313004 220080311G7200 ENGINE BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU ROTOL R4304 R2124304 EU NR 2 MALFUNCTIONED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION APAPPROACH 1 CA DURING APPROACH IN ICING CONDITIONS AND HEAVY PRECIPITATION, WHEN THE PILOT THROTTLED BACK, ENGINE NR 2 FLAMED OUT AND AUTO FEATHERED. THE PILOT DID NOT ATTEMPT TO RE-LIGHT AND LANDED WITH ONE ENGINE OPERATING. MAINTENANCE CHECKED THE OIL SCREEN, 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 DIRECTED TO THE FLIGHT CREWS TO "SWITCH ON THE ENGINE IGNITION SWITCHES WHEN MODERATE OR SEVERE ICING IS ENCOUNTERED". THE PILOT DID NOT HAVE THE ENGINE IGNITION SWITCHES SELECTED TO "ON" DURING THIS EVENT. THE PILOTS HAVE BEEN REMINDED OF THIS 2L72 3T4 T A24EU A196 6 CP899 20080521 EA 2008 5 21 CA080314001 120080206G5610NP1393225 WINDOW CNDAIRCL600 CL6002B19 1900309EA COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 7038 (CAN) FLT NR 3874 DISCREPANCY: (CAPT`S SIDE WINDOW FWD UPPER CORNER, MIDDLE PANE CRACKED DURING APPROACH) REQUESTED THE PN/SN, TSN/CSN INFORMATION. UPDATE 2/6: REPLACED THE WINDOW. (TC NR 20080314001) 2L72 4F RTA21EA 200805141 200805141 NE 2008 5 14 CA080314002 220080313G7200CF343B1 ENGINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE NR 2 FIRE W AFB UNSCHED LANDING ACTIVATE FIRE EXT. EMER. DESCENT BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CRCRUISE 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 220, 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 EMERGENCY 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 BRIGADE WENT INTO ACTION AND USED FIRE EXTINGUISHING AGENT, BUT DID NOT REPORT HAVING ACTUALLY SEEN FLAMES. (TC NR 2008032L72 4F4 FRTA21EA E15NE 20080521 NM 2008 5 21 CA080314003 120080307G532019093649001 BRACKET EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE FUSELAGE CRACKED W O OTHER O OTHER NRNOT 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 INFORMED OF THE FINDING, REPAIR SUGGESTED TO FLEET ENGINEERING. MORE INFO TO BE PROVIDED. (TC NR 20080314003) 2L72 4F4 FRTA57NM E00070EN 20081104 SW 2008 11 4 CA080314004 120080306G2510STCSH0631 INERTIA REEL BELL BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE COCKPIT SEAT BINDING W K NONE O OTHER ININSP/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. 1G71 4U4 U H4SW E22EA 20080521 EU 2008 5 21 CA080314005 120080311G3244542K694 TIRE AIRBUSA330 A330* EU RROYCERB211 RB211* 54555NE MLG FAILED W A UNSCHED LANDING O OTHER LDLANDING 1 CA (CAN)THE AC BLEW THE NR (4) MAIN TIRE ON DEPARTURE. THE FLIGHT CREW ELECTEDTO DIVERT, AND ULTIMATELY LANDED APPROXIMATELY 15000 KGS OVER THE MAXIMUM STRUCTURAL LANDING WEIGHT OF 185000KGS. DURING TAXI, THE NR (3), RT FWD IB MAIN TIRE DEFLATED 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) 2L72 4F4 FRTA46NM A12EU 20080521 NM 2008 5 21 CA080314006 120080312G215078279018 ACM DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3390523037 (CAN) WHILE CARRYING OUT WORK CARD TO REMOVE COMPONENT IT WAS DISCOVERED THERE WAS A 6 INCH CRACK ON THE INNER SIDE OF THE CHAMBER. (TC NR 20080314006) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080603 GL 2008 6 3 CA080314007 220080312G7261 ENGINE EMB 135 EMB135ER 3260203SO ALLSN AE300 AE3007A GL LEAKING W A UNSCHED LANDING KMYFLUID LOSS OVER TEMP ENGINE STOPPAGE CRCRUISE 1 CA OIL IMPENDING BYPASS INDICATION ILLUMINATED ALONG WITH OIL TEMPERATURE RISING TO 141 DEGREES. THE PILOT COMMANDED THE SHUT DOWN OF THE ENGINE DUE TO OIL TEMPERATURE AND QUANTITY INDICATING THREE QUARTS. AIRCRAFT RETURNED TO CMH WITHOUT INCIDENT. MAGNETIC INDICATING PLUGS WERE FOUND CLEAN. A SMALL PUDDLE OF OIL IN FAN SECTION AND A LOT OF OIL IN THE EXHAUST 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 TEARDOWN. (TC NR 20080314007) 2L72 4F4 FRTT00011ATTE6CH 20080603 NE 2008 6 3 CA080314008 220080313G7200 ENGINE AIRBUSA319 A319114 3930350NM GE CFM56 CFM565A 13802NE FAILED W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CLCLIMB 1 CA 3080414183 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. INVESTIGATION INTO CAUSE OF ENGINE FAILURE IS ON GOING AND SDR WILL UPDATED ACCORDINGLY. ENGINE HAS BEEN CHANGED. (TC NR 20080314008) 2L72 4F4 FRTA28NM E29NE 20080603 GL 2008 6 3 CA080314009 220080310G7230 BEARING EMB 145 EMB145LR 3260212SO ALLSN AE300 AE3007A GL NR 4 FAILED W K NONE BM SMOKE/FUMES/ODORS/SPARKS OVER TEMP ININSP/MAINT 1 CA ENGINE REMOVED FOR ITT EXCEEDANCE, AUTO IFSD, SMOKE IN COCKPIT/CABIN, OIL DEBRIS ON ALL CHIP DETECTORS. TEARDOWN OF ENGINE REVEAL NR 4 BEARING FAILURE AND ALSO NR 3 BEARING FAILURE. EXCESSIVE DAMAGE IN COMPRESSOR AREA DUE TO BOTH SUPPORTING BEARING FAILURE. FAILED COMPONENTS WILL BE SENT TO THE OEM FOR INVESTIGATION. (TC NR 20080314009) 2L72 4T4 FRTT00011ATTE6CH 20081219 CE 2008 12 19 CA080314010 120080306G3245G195X6758 TUBE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL TIRE FLAT W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) TIRE WENT FLAT SITTING IN HANGAR. CRACK FOUND IN TUBE AT BASE OF VALVE STEM. 1H71 3T3 T A37CE E4EA 5 CP60GL 20080603 CE 2008 6 3 CA080314011 120080306G8011200SGL119Q2 BRUSHES CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL STARTER FAILED W K NONE O OTHER ININSP/MAINT 1 CA 1181 SLOW SPOOLING OVER ENGINE, ENGINE STARTER BRUSHES WORN OUT (TC NR 20080314011) 1H71 3T3 T A37CE E4EA 5 CP60GL 20081104 NE 2008 11 4 CA080314012 120080310G792184300207 THERMOSTAT SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL OIL COOLER STUCK W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMPERATURE INCREASED TO RED LINE. (TC NR 20080314012) 1G72 3U3 U H1NE E1GL 20080521 SO 2008 5 21 CA080314013 220080307G8500TSIO520EB ENGINE CESSNA401 401 207590CCE CONT O520 TSIO520E 17040SO MCAULY3AF32C3AF32C* GL MAKING METAL W E ENGINE SHUTDOWN O OTHER APAPPROACH 1 CA 714 (CAN) ON FINAL APPROACH INTO AIRPORT THE RT ENGINE MANIFOLD PRESSURE STARTED CHANGING. THE PILOT THEN NOTICED THAT THE RT OIL PRESSURE HAD DROPPED TO THE RED LINE. THE RT PROP WAS FEATHERED AND THE ENGINE WAS SHUTDOWN. SMALL BITS OF METAL WERE FOUND UNDER THE OIL PRESSURE RELIEF VALVE. THE ENGINE WAS REMOVED AND SENT FOR WARRANTY. (TC NR 20080314013) 1L72 3O3 O A7CE E8CE 5 CP22EA 20081105 SW 2008 11 5 CA080314014 120080307G3246205050400063 CROSSTUBE BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE MLG BROKEN W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) HELICOPTER WORKING HELI-SKIING. THE PASSENGERS WERE LOADING INTO THE HELICOPTER. ALMOST ALL THE SEATS WERE OCCUPIED WHEN A SUDDEN SETTLING WITH A METALLIC NOISE ON THE REAR OF THE MACHINE OCCURRED. IT WAS NOTED THAT THE REAR CROSS TUBE WAS CRACKED ALL THE WAY AROUND OR BROKEN UNDERNEATH THE RIGHT HAND CROSS TUBE SADDLE. (ABOUT 1" INSIDE THE SADDLE AREA) 1G71 4U4 U H4SW E22EA 20081104 WP 2008 11 4 CA080314015 120080313G6320369D2512311 GEAR HUGHES369 369 4470702WP ALLSN 250C 250C20 03013GL M/R TRANSMISSIONBROKEN W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 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) 1G71 3U3 U H3WE E4CE 200805141 200805141 EU 2008 5 14 CA080314016 120080309G2751A275704050400 SWITCH AIRBUS310 A310300 3930305EU GE CF6 CF680C2* GL KRUEGER FLAP CONTAMINATED W D RETURN TO BLOCK N FALSE WARNING CLCLIMB 1 CA (CAN) DURING CLIMB, ECAM WARNING "FLAP KRUEGER NOT RETRACTED LIGHT" CAME ON. FLIGHT RETURNED TO THE STATION. SFCC INDICATED FAULT COMING FROM THE LT KRUEGER RETRACT SWITCH. MAINT FOUND THE SWITCH BACK SHELL CONTAMINATED WITH WATER. CONNECTOR AND SWITCH CLEANED OUT AND SYS TESTED SERVICEABLE. AC DEPARTED AND SAME SNAG REOCCURRED DURING CLIMB. THE AC RETURNED TO THE STATION AND WAS REMOVED FROM SERVICE FOR TROUBLESHOOTING. DURING INSP, FOUND SLIGHT DAMAGE ON WIRE, 2 INCHES FROM CONNECTOR. WIRE PROTECTION CARRIED OUT IAW ESPM 20-53-00 AND SWITCH ASSY REPLACED. SYS TESTED SERVICEABLE. AC WAS RETURN TO SERVICE WITH NO REOCCURRENCE. (TC NR 20080314016) 2L72 4F4 FRTA35EU E23EA 20080521 EA 2008 5 21 CA080314017 120080306G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS MALFUNCTIONED W O OTHER J WARNING INDICATION APAPPROACH 1 CA (CAN) FLAP FAIL MESSAGE SHORT FINAL WHEN CREW WERE SELECTING FROM FLAP 8 TO FLAP 20 POSITION, FLAPS REMAINED AT 8 DEGREES AND LANDED NORMAL. MAINT REPORTED THAT THE LIST OF FAULTS IN MDC ARE : 1- JAM 2- FECU 3- L MOTOR BRAKE THE FAULT CODES WERE RETRIEVED FROM THE FECU AND POINT TOWARDS POWER LOSS DUE TO THE SDS LT SKEW DETECTOR FLAGGED. MAINT RESET THE SDU AND FECU. RAN THE FLAPS UP AND DOWN 2 TIMES. THEN THE SDU FLAGGED THE LT SKEW DETECTOR AGAIN. DUMMY BOX INSTALLED, SYSTEM TESTED AND IT WAS CONFIRMED THE SKEW DETECTION IS AT FAULT. MAINT HAS CONFIRMED THAT THE SDU FECU POWER 1 AND 2 LIGHTS FLAGGED, AND THE LT OB PANEL SKEW L4 AND L3 LIGHTS FLAGGED. SKEW DETECT SYS BOUND AT FAULT. SKEW DETECT SYS DEACTIVAT2L72 4F4 FRTA21EA E15NE 20080521 EU 2008 5 21 CA080314018 120080307G32505325012004 BEARING PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL NLG STEERING UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA 8888 (CAN) FORK BEARING ON NOSE LANDING GEAR STEERING FOUND TWISTED. THIS DEFECT WAS FOUND ON NOSE LANDING GEAR SHOCK ABSORBER REPAIR AND SERVICE. (TC NR 20080314018) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20080521 GL 2008 5 21 CA080314019 220080304G72506871505 BEARING HILLERUH12 UH12E 4360122WP ALLSN 250C 250C20 03013GL NR 5 FAILED W K NONE O OTHER ININSP/MAINT 1 CA 169 (CAN) CHIP LIGHTS METAL CONTAMINATION ENGINE SHOP DETERMINED NR 5 BEARING FAILURE. (TC NR 20080314019) 1G71 3O3 U 4H11 E4CE 20080603 NE 2008 6 3 CA080314021 220080209G7200 ENGINE SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B 60037NE MAKING METAL W O OTHER EJ VIBRATION/BUFFET WARNING INDICATION TXTAXI/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 NOISE 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 LUCKY THIS DID NOT HAPPEN IN THE AIR AS WE WOULD BE LOOKING AT A TOTAL ENGINE FAILURE. (TC NR 20080314021) 1G71 3U3 U H9EU E00054EN 20080521 SO 2008 5 21 CA080314022 120080309G2400W23X1A1G40 CIRCUIT BREAKER PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL COCKPIT OPEN W O OTHER H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA (CAN) CIRCUIT BREAKER FOUND IN OPEN CIRCUIT AND ALSO FOUND ONE FAULTY WIRE WHICH WAS REPLACED. (TC NR 20080314022) 1L72 3O3 O A20SO E14EA 5 CP33EA 200805141 200805141 EU 2008 5 14 CA080317003 120080311G2435 COOLING FAN 160SG140Q UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE STARTER GEN SEPARATED W E ENGINE SHUTDOWN O OTHER TXTAXI/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 SEVERAL 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 WAS 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 DURIN1G72 3U3 UNCR0001RD E34NE 20080521 2008 5 21 CA080317004 420080214G8300 GEAR PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360EB 17025SO HARTZLHCC2Y BHCC2YF2 GL ACCESSORY G/B FAILED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 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 METAL CONTAMINANTS FOUND. PROP DID NOT TURN FREELY. ALTERNATOR PULLED OFF ON THE BACK OF THE ENGINE. GEAR FOUND LYING LOOSE IN ACCESSORY CASE WITH MULTIPLE BROKEN TEETH ON OTHER GEARS. (TC NR 20080317004) 1L72 3O3 O A7SO E9CE 5 CP920 20080521 EA 2008 5 21 CA080317005 220080304G8520 PISTON PIN CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL NR 1 CYLINDER WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ALUMINUM FOUND IN OIL FILTER DURING 100 HOUR INSP. CYLINDER BOROSCOPED, SUSPECT CYLINDER REMOVED, FWD PISTON PIN FOUND WORN ON NR 1 CYLINDER. (TC NR 20080317005) 1H71 3O3 ONT3A19 E223 5 NP50GL 20081222 EA 2008 12 22 CA080317006 220080222G8530 CYLINDER CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL ENGINE WORN W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) ALUMINUM FOUND IN OIL FILTER DURING 100 HR INSP. CYLINDER BOROSCOPED, SUSPECT CYLINDER REMOVED, FWD PISTON PIN FOUND WORN ON NR 1 CYLINDER. 1H71 3O3 ONT3A19 E223 5 NP50GL 20081222 CE 2008 12 22 CA080317009 120080302G272004115261 RUDDER BAR CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL COCKPIT CRACKED W K NONE O OTHER ININSP/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. 1H71 3O3 ONT3A19 E223 5 NP50GL 20081230 CE 2008 12 30 CA080318001 120080306G7160 BRACKET CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA CARB HEAT DETACHED W O OTHER O OTHER NRNOT 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. 1H71 3O3 ONT3A12 E274 20080603 EA 2008 6 3 CA080318002 220080226G8530 STUD CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA SNSNCH72C 72CK EA CYLINDER BROKEN W O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 CA 3495 DURING WALK AROUND, PILOT NOTICED ENGINE OIL COVERING LT SIDE OF FUSELAGE AND EMPENNAGE. MAINTENANCE INSPECTED ENGINE AND FOUND ON NR 2 CYLINDER, ONE BROKEN THROUGH STUD. OIL WAS RUNNING DOWN THROUGH STUD AND EXITING CYLINDER BASE WHERE ATTACH NUT USED TO BE. OIL LEAK WAS NOT DISCOVERED DURING OR AFTER PREVIOUS NIGHT FLIGHT. (TC NR 20080318002) 1H71 3O3 ONT3A19 E223 5 NP9045 20080521 EA 2008 5 21 CA080318008 220080317G7310252429710 SERVO PIPER PA28 PA28R180 7102809SO LYC O360 IO360B1E 41514EA HARTZLHCC2Y HCC2YK1 GL FUEL SYSTEM MALFUNCTIONED W K NONE O OTHER ININSP/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) 1L71 3O3 O 2A13 1E10 5 CP920 20080602 WP 2008 6 2 CA080319003 220080311G731331038294 NOZZLE GARRTTTPE331TPE33111U 01514WP FUEL DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 1791 THE A/C CAME INTO THE HANGER FOR A ROUTINE FUEL NOZZLE AND BOROSCOPE INSPECTION. DURING THE BOROSCOPE INSPECTION OUR NIGHT 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 120080307G531019093649001 SUPPORT EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE MLG WW CRACKED W K NONE O OTHER ININSP/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 GOES 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, 317, 318, 319, 320, 322, 323, 324, 326, 332 (TC NR 20080319004) 2L72 4F4 FRTA57NM E00070EN 20080602 2008 6 2 CA080319005 120080319G8011EBB131A DRIVE SYSTEM STARTER SEIZED W K NONE O OTHER ININSP/MAINT 1 CA 97 STARTER RECEIVED DUE TO DRIVE ASSEMBLY FAILURE. ENGINE COULD NOT BE STARTED BECAUSE DRIVE WOULD NOT ENGAGE. WHEN INSPECTED 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 120080306G3260EN516 SWITCH SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE331* 01514WP MCAULY4HFR344HFR34C652 NE LT MLG INTERMITTENT W L ABORTED APPROACH N FALSE WARNING APAPPROACH 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 20080319007) 2L72 4T3 TRTA8SW E2WE 6 C3PNE 20080602 NE 2008 6 2 CA080319008 220080306G7200 ENGINE PAC CRESCOCRESCO CE PWA PT6 PT6A34AG 52053NE POWER LOSS W C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA DURING TAKEOFF ROLL, A NOISE WAS HEARD ACCOMPANIED BY LOSS OF ENGINE POWER. THE TAKEOFF WAS ABORTED. INITIAL INSPECTION REVEALED FRAGMENTS SIMILAR TO COMPRESSOR BLADE MATERIAL DISTRIBUTED THROUGHOUT THE INLET. TEARS IN THE INLET SCREEN WERE NOTED. THE ENGINE HAS BEEN REMOVED AND WILL BE INVESTIGATE ROOT CAUSE ONCE ESTABLISHED. 1L71 4T4 TNTEXPA1L71E4EA 20080602 EA 2008 6 2 CA080320002 120080318G2797MS27473T20B4 CONNECTOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE FLUTTER DAMPER DAMAGED W O OTHER O OTHER NRNOT 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 TRANSMITTER SWITCHES. THIS TASK WAS CALLED UP DURING THE AIRCRAFT`S PLANNED HEAVY INSPECTION. T HERE WERE NO REPORTED FAILURES 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 DISCONNECTED. SEVERAL OTHER PINS WERE ALSO FOUND DISCOLORED. CONNECTOR P/N MS27497T20B41S, BACKSHELL P/N HEX41-AB90-21A9-1, CONNECTOR P/N MS27473T20B41P AND BACKSHELL P/N HEX41-AB00-21A9-1 WERE REPLACED AND SYSTEM FUNCTION CHECKED "SERVICEABLE".2L72 4F4 FRTA21EA E15NE 20080602 SW 2008 6 2 CA080320003 120080312G52302724050083 FRAME SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP CARGO DOOR CRACKED W K NONE O OTHER ININSP/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 (POSITIONS 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) 2L72 4T4 TRTA8SW E4WE 20080602 CE 2008 6 2 CA080320004 120080314G5320365533 GASKET CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA SERVO PLUG LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 1861 SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE. ENGINE REMANUFACTURE DATE OF JULY 14, 2004 DOES NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC NR 20080320004) 1H71 3O3 ONT3A12 1E10 20080602 EA 2008 6 2 CA080320005 220080314G7321365533 GASKET PRECISIONWND CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA FCU LOOSE W K NONE O OTHER ININSP/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 WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. RIGHT MAGNETO P-LEAD WIRE BROKEN. (TC NR 20080320005) 1H71 3O3 ONT3A12 1E10 20080602 EA 2008 6 2 CA080320006 220080314G7321365533 GASKET PRECISIONWND CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA FCU LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 1367 SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE. ENGINE REMANUFACTURE DATE OF AUG 18, 2005 AND THE FUEL SERVO WAS REPAIRED JULY 28, 2006 AND BOTH DO NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC NR 20080320006) 1H71 3O3 ONT3A12 1E10 20080602 EA 2008 6 2 CA080320007 220080314G7321365533 GASKET PRECISIONWND CESSNA182 182T 2072703CE LYC O540 IO540AB1A5 EA MCAULY3D36C B3D36C431 GL FCU LOOSE W K NONE O OTHER ININSP/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 NR 20080320007) 1H71 3O3 ONT3A13 1E4 5 C 20080602 CE 2008 6 2 CA080320010 120080307G2750S16612 SWITCH CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA TE FLAPS BROKEN W O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 CA INTERNAL RETURN SPRING OF SWITCH BROKEN. TOGGLE NOT RETURNING TO NEUTRAL POSITION. SWITCH REPLACED WITH NEW. (TC NR 20080320010) 1H71 3O3 ONT3A12 E274 20081105 EU 2008 11 5 CA080320011 120080320G6230350A37118322 LOCK SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE MAIN ROTOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACKED MAIN ROTOR MAST LOCK. 1G71 3U3 UNCH9EU E19EU 20081105 WP 2008 11 5 CA080320012 120080312G6310C1883 CROSS TIE ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE SPRAG CLUTCH CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 911 (CAN) DURING A IN-HOUSE 1000 HR CLUTCH INSPECTION THE SPRAG CLUTCH CAGE CROSSBAR WAS FOUND CRACKED. NEW PARTS WERE INSTALLED. 1G71 3O3 O H11NM 1E4 20080602 CE 2008 6 2 CA080320013 120080319G3245891250 TUBE CESSNA208 208 2073702CE PWA PT6 PT6A114A 52043NE TIRE FAILED W D RETURN TO BLOCK O OTHER TXTAXI/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. TIRE ASSY WAS DISASSEMBLED AND TUBE WAS FOUND BLOWN WITH ABOUT A FOUR INCH SPLIT IN IT. THE TUBE WAS ALSO FUSED TO THE INSIDE 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. TALKING TO OTHER OPERATORS HAS INDICATED THAT OTHERS ARE HAVING THE SAME PROBLEM. I HAVE BEEN TOLD BY A TIRE COMPANY THAT THE BUTYL RUBBER TUBES ARE NOT WORKING WELL IN OUR COLDER CLIMATE. (TC NR 20080320013) 1H71 3T3 TNTA37CE E4EA 20080521 2008 5 21 CA080324001 120080324G3245600X6 TUBE TIRE DEFECTIVE W K NONE O OTHER ININSP/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 120080312G531212127071 BULKHEAD CESSNA206 U206E 2073350CE CONT O520 IO520F 17032SO HARTZLHCC3Y HCC3YF1 GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BULKHEAD CRACK 1.25 IN LONG AT RT SIDE FROM LIGHTNING HOLE. NEAR STAB ATTACH POINT. (TC NR 20080325006) 1H71 3O3 O A4CE E5CE 5 CP25EA 20080521 NM 2008 5 21 CA080325008 120080325G5315654681163 FLOORBEAM BOEING737 737490 1384715NM BS 986 RBL43 CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FLOORBEAM FOUND CORRODED DURING VISUAL INSP AND REPAIRED WITH REPAIR PART IAW EA AND SRM. (TC NR 20080325008) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080325009 120080325G5315654681179 FLOORBEAM BOEING737 737490 1384715NM BS 986 RBL 35-40CORRODED W K NONE O OTHER ININSP/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) 2L72 4F RTA16WE 20080521 NM 2008 5 21 CA080325010 120080325G5315654681179 FLOORBEAM BOEING737 737490 1384715NM BS 986 RBL 27 CORRODED W K NONE O OTHER ININSP/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) 2L72 4F RTA16WE 20080521 2008 5 21 CA080325011 120080325G2410ALV9510R ROTOR ALTERNATOR MISMANUFACTURED W K NONE O OTHER ININSP/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. ALSO THE O-RING BETWEEN THE SPACER AND WASHER UNDER THE DRIVE HUB WAS FOUND TO BE TOO BIG TO ALLOW THE WASHER TO SEAT AGAINST 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 220080320G725023038136 SHAFT ALLSN 250C 250C47B GL TURBINE CRACKED W K NONE O OTHER ININSP/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 POWER 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 120080304G5100 UNKNOWN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE UNKNOWN W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 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 DECELERATION AND IMMEDIATE LOW ROTOR HORN. THE PILOT DROPPED THE COLLECTIVE & CONDUCTED EMERGENCY RUN-ON LANDING IN A FIELD SOUTH OF THE HANGAR. UPON SAFE LANDING, THE ENGINE WAS STILL RUNNING AND ACCELERATING AND ROTOR RPM WAS AT 90% AND RISING. AFTER 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 FURTHER INCIDENT. AT THE TIME OF THIS INCIDENT, THIS ACFT HAD THE DART COLD WEATHER BAFFLES INSTALLED. WE HAVE IMPLEMENTED A 1G71 3O3 O H11NM 1E4 20081105 SW 2008 11 5 CA080326001 120080325G8097 WIRE BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE STARTER CHAFED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC TXTAXI/GRND HDL 1 CA (CAN) DURING START UP THE STARTER RELAY CIRCUIT BREAKER WAS POPPING NOT ALLOWING THE STARTER TO START. IT WAS FOUND THAT 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. 1G71 4U4 U H1SW E17EA 20080521 SW 2008 5 21 CA080326002 120080324G78103101582 EXHAUST DUCT SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL ENGINE CRACKED W K NONE O OTHER ININSP/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 NEAR THE EGT PROBE BOSSES. IT APPEARED TO BE ON A PREVIOUS WELD. REMOVED AND REPLACED THE DUCT. (TC NR 20080326002) 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20080521 CE 2008 5 21 CA080326003 120080324G2161 COUPLING CESSNA650 650 2076802CE GARRTTTPE731TFE7313C WP TEMP CONTROL MISINSTALLED W O OTHER O OTHER CRCRUISE 1 CA (CAN) CREW WROTE UP, CABIN PAC STUCK ON FULL COLD. TROUBLESHOOTING CARRIED OUT AND FOUND THAT THE COUPLING FOR CABIN TEMP CONTROL HAD DISCONNECTED FROM THE ENVIROMENTAL CONTROL UNIT. BOTH CLAMPS AND THE COUPLING WERE INTACT HOWEVER THE COUPLING HAD BEEN INSTALLED INCORRECTLY. COUPLING WAS REINSTALLED AND LEAK CHECKED SERVICEABLE. (TC NR 20080326003) 2L72 4F4 F A9NM E6WE 20081105 WP 2008 11 5 CA080326004 120080304G2435 ARMATURE ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE STARTER GEN DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 543 (CAN) HOLES MELTED THROUGH ARMATURE CASE IN STARTER. 1G71 3O3 O H11NM 1E4 20081105 WP 2008 11 5 CA080327005 120080317G2435 GEAR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE STARTER GEN DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 27 (CAN) STARTER AND RING GEAR TEETH FOUND DAMAGED DURING A DI 1G71 3O3 O H11NM 1E4 20081105 WP 2008 11 5 CA080327006 120080304G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE INTERMITTENT W O OTHER O OTHER NRNOT REPORTED 1 CA 203 (CAN) STARTER INTERMITTENT 1G71 3O3 O H11NM 1E4 20081105 WP 2008 11 5 CA080327007 120080307G6520C0211 GEARBOX ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE TAIL ROTOR LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 4 (CAN) TAILROTOR GEARBOX FOUND LEAKING FROM THE INPUT SEAL DURING DI 1G71 3O3 O H11NM 1E4 20080521 NE 2008 5 21 CA080328001 220080320G7250310703301 BEARING RACE PWA PW120 PW123 NE NR 15 MAKING METAL W K NONE O OTHER ININSP/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 220080309G8530399353 CYLINDER HEAD DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE NR 2 SEPARATED W A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 CA 5 HEAD SEPERATED FROM NR 2 CYLINDER AFTER 4.9 HRS AIRTIME. CYLINDER HEAD SEPARATION OCCURRED DURING CRUISE FLIGHT. UNEVENTFUL LANDING CARRIED OUT. REPLACEMENT CYLINDER HEAD INSTALLED AND AIRCRAFT COMPLETED ITS MISSION. (TC NR 20080328002) 1H71 3R3 RRCA806 5E1 20080603 CE 2008 6 3 CA080328003 120080319G551412326231 BRACKET CESSNA210 210J 2073439CE CONT O520 IO520J 17032SO HORIZONTAL STAB CRACKED W O OTHER O OTHER NRNOT 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 BOLT 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) 1H71 3O3 O 3A21 E5CE 20080603 CE 2008 6 3 CA080328004 120080319G531212120031 DOUBLER CESSNA210 210J 2073439CE CONT O520 IO520J 17032SO BULKHEAD CRACKED W O OTHER O OTHER NRNOT 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 PLATE, THIS BRACKET IS ATTACHED TO THE REAR FRAME AT STN 209, P/N 12120402-3. AFFECTED PART REPLACED. (TC NR 20080328004) 1H71 3O3 O 3A21 E5CE 20080603 2008 6 3 CA080328005 220080328G741410357586 DISTRIBUTOR GEAR MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 2000 MAG WAS RECEIVED TIME EXPIRED FOR OVERHAUL. WHEN DISASSEMBLED THE WASHER THAT RETAINS THE NYLON GEAR ON THE SHAFT WAS FOUND 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 WASHER 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 220080328G741410357586 DISTRIBUTOR GEAR MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 2000 MAG WAS RECEIVED TIME EXPIRED FOR OVERHAUL. WHEN DISASSEMBLED THE WASHER THAT RETAINS THE NYLON GEAR ON THE SHAFT WAS FOUND 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 WASHER 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 120080327G5280150450018 ARM CESSNA401 401B 207590ECE CONT O520 TSIO520EB 17040SO MLG DOOR BROKEN W K NONE O OTHER ININSP/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) 1L72 3O3 O A7CE E8CE 20081105 WP 2008 11 5 CA080328008 120080308G2410 BRUSHES KELLY ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ALTERNATOR WORN W K NONE O OTHER ININSP/MAINT 1 CA 847 (CAN) DURING A POST FLIGHT DI THE ALTERNATOR BELT WAS FOUND DAMAGED. CARRIED OUT AN INSPECTION OF THE ALTERNATOR AND FOUND THE BRUSHES AND SLIP RINGS WORN. 1G71 3O3 O H11NM 1E4 20080521 EA 2008 5 21 CA080328010 120080327G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE TE FLAP FAILED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 2931729317 (CAN) ON APPROACH WHEN MAKING INITIAL FLAP SELECTION CREW RECEIVED FLAP FAULT MESSAGE, FLAPS FAILED TO OPERATE. CREW PERFORMED FLAP (0) LANDING. CREW ADVISE OAT WAS -57 TO -59 FOR ABOUT AN HOUR AT FLIGHT LEVEL 260 PRIOR TO COMMENCING DESCENT. ON GROUND FLAPS POSITIONED TO 8 DEG AND AC FERRIED WITH FLAPS AT 8 DEG TO MAINT BASE FOR CORRECTIVE ACTION. FLAP FAULT 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) 2L72 4F4 FRTA21EA E15NE 20080521 NM 2008 5 21 CA080328011 120080328G7500 DUCT BOEING727 727200 138407ENM PWA JT8 JT8D9A 52048NE BLEED AIR LEAKING W A UNSCHED LANDING N FALSE WARNING CLCLIMB 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 SLEEVE CAUSING A DUCT LEAK. THE DUCT WAS REPAIRED AND LEAK CHECKED SERVICEABLE. (TC NR 20080328011) 2L73 4F4 FRTA3WE E2EA 20080521 EA 2008 5 21 CA080331001 120080317G571121531062212 FRAME CNDAIRCL215 CL2151A10 1900320EA PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE FS 434.80 CRACKED W K NONE O OTHER ININSP/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 DETECTED 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 DURING WINTER MAINT AT A/F 2530.8 AND 9521 WATER DROPS. APPROVED REPAIRS WILL BE CARRIED OUT AND THE AC RELEASED FOR SERVICE. (TC NR 20080331001) 2H72 4R3 RRTA14EA ATC14 6 CP871 20080521 CE 2008 5 21 CA080331002 120080312G2510505530401 CABLE ASSY CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL SEAT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSTALLATION OF SERVICE KIT SK210-175 - SECONDARY SEAT STOP, IT WAS FOUND THAT THE THREADS ON THE HOUSING FOR THE ADJUSTMENT CABLE WERE CRACKED. (TC NR 20080331002) 1H71 3O3 ONT3A12 E274 5 NP910 20080521 EA 2008 5 21 CA080331003 120080317G57112151003268 SPAR CAP CNDAIRCL215 CL2151A10 1900320EA PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE WING CRACKED W K NONE O OTHER ININSP/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 REAR SPAR CAPS. VISUAL INSPECTIONS WERE CARRIED OUT AND CRACKS DISCOVERED ON BOTH SPAR CAPS AT WS 51.00 FS 434.80. THIS AD 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 DROPS 9521. THE AC MFG WAS CONTACTED AND APPROVED DRAWINGS SENT SHOWING REPAIRS. (TC NR 20080331003) 2H72 4R3 RRTA14EA ATC14 6 CP871 20081105 NE 2008 11 5 CA080331004 220080319G7314C8187B PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE AUX FUEL NOISY W K NONE O OTHER ININSP/MAINT 1 CA 860 (CAN) AUX FUEL PUMP HAD EXCESSIVE NOISE THE PUMP WAS REPLACED. (TC NR 20080331004) 1G71 3O3 O H11NM 1E4 20080521 EA 2008 5 21 CA080331006 120080328G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 2522625226 (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) 2L72 4F4 FRTA21EA E15NE 20080521 NM 2008 5 21 CA080331007 120080327G575317039312001 FLAP TRACK EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE TE FLAPS GOUGED W K NONE O OTHER ININSP/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 FACE 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 (STRUCTURAL REPAIR MANUAL) , ALL C/A CARRIED OUT IAW MFG INSTRUCTION. REF: IC2007-17005998C, IC2008-17002015A, IC2008-17002163. (TC NR 20080331007) 2L72 4F4 FRTA56NM E00063EN 20080521 EU 2008 5 21 CA080331008 120080325G3600 B-NUT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL CRACKED FAILED W O OTHER O OTHER CLCLIMB 1 CA 7625 (CAN) FOLLOWING AN ANNUAL INSP AND A SATCOM AVIONICS UPGRADE IN THE INITIAL CLIMB PHASE OF A TEST FLIGHT , CABIN PRESSURE 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 SLIGHT TUG , NUT SEPARATED COMPLETLY AND LINE COULD BE PULLED COMPLETLY FROM FITTING. A NEW LINE WAS INSTALLED , SUBSEQUENT GROUND RUNS AND TEST FLIGHT PROVED SATISFACTORY. SOME OF THE WIRING NECESSARY FOR THE PROJECTS LEADING UP TO THIS INCIDENT WAS CARRIED OUT IN THIS AREA (UPPER FIREWALL). IT IS BELIEVED THAT THE LINE MAY HAVE BEEN DISTURBED IE TYWRAPS, PERHA1L71 3T4 TRTA78EU E26NE 5 CP210NE 20080521 EA 2008 5 21 CA080331009 220080320G8530LW12966 CYLINDER PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL ENGINE CRACKED W K NONE O OTHER ININSP/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 AND 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) 1L72 3O3 O A20SO E14EA 5 CP33EA 20080521 EA 2008 5 21 CA080401001 120080327G7830W31G1120 WIRE CNDAIRCL600 CL6002B19 1900309EA THRUST REVERSER BROKEN W E ENGINE SHUTDOWN O OTHER CRCRUISE 1 CA (CAN) ABOUT 20 MINUTES BEFORE EXPECTED ARRIVAL , RECEIVED THAT THERE WAS REV UNLOCKED MESSAGE ON EICAS IN FLIGHT, THE CREW ACCORDING TOOK QUICK CHECKLIST OPERATION, SHUTDOWN THE LT ENGINE MANUALLY, DID SINGLE ENGINE LANDING PROCEDURES. STARTED THE TROUBLESHOOTING. CHECKED THE PDU, ETC. FINALLY, FOUND THE PROBLEM, THE WIRE OF THE W31G/1/1-20 OF THROTTLE LOCKOUT THROTTLE LOCKOUT WAS BROKEN, THE BROKEN WIRE WAS TOO SHORT, (ALL THE WIRE SHOULD HAVE THE SAME LENGTH NORMALLY) THEY 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 EVERY2L72 4F RTA21EA 20080521 NE 2008 5 21 CA080401002 220080313G7230806101 BLADE BOEING727 72722C 138400FNM PWA JT8 JT8D7B 52053NE COMPRESSOR DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 186512963 (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 AND REPLACED. THE AC WAS INSPECTED IAW MFG ABNORMAL OCCURRENCE "BIRD STRIKE". NO FAULTS WERE FOUND. IT HAD BEEN OBSERVED 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 AIRFRAME ABNORMALITIES DURING THE FLIGHT AND THE PROCEEDING DAILY INSP HAD NOT REVEALED THE DAMAGE. (TC NR 20080401002) 2L73 4F4 F A3WE E2EA 20080602 EA 2008 6 2 CA080401004 220080326G7200 ENGINE DHAV DHC6 DHC6200 2802620EA PWA PT6 PT6A20 52043EA LEFT POWER LOSS W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 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) 1H72 3T3 TRTA9EA E4EA 20080602 NM 2008 6 2 CA080401005 120080401G3222 PIN EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE NLG MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA DURING INSPECTION, FOUND NUT ON LOWER DRAG BRACE ATTACHEMENT HINGE PIN NOT SAFETIED WITH CUTTER PIN AND PRC ADRIFT SEE ATTACHEMENT. NO EVIDENCE OF WORK PREVIOUS ACCOMPLISHED ON THE NOSE GEAR. 2L72 4F4 FRTA56NM E00063EN 20080602 NM 2008 6 2 CA080401008 120080313G32132821A000003 STRUT EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE LT MLG LEAKING W K NONE O OTHER ININSP/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 PER EMBRAER, TO FIX THE PROBLEM THE MAIN GEAR AS TO BE CHANGE AIR CANADA FLEET AS BEEN ADVISED AND SEEMS TO BE A KNOWN CONDITION (TC NR 20080401008). 2L72 4F4 FRTA57NM E00070EN 20080602 NM 2008 6 2 CA080401010 120080401G323265C330325 ARM BOEING737 737490 1384715NM MLG ACTUATOR CRACKED W K NONE O OTHER ININSP/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 ACTUATOR BEAM ARM IS CRACKED CYCLES/TSN ARE AIRFRAME. NO EVIDENCE THAT THIS PART HAS BEEN REPLACED SINCE A/C MANUFACTURE. (TC NR 20080401010) 2L72 4F RTA16WE 20080602 EA 2008 6 2 CA080402001 120080331G3040 HEATER DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE WINDSHIELD SMOKE W HA DEACTIVATE SYST/CIRCUITSUNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) DURING CLIMB, THE CREW OBSERVED SMOKE IN THE COCKPIT AND QUICKLY NOTICED THAT THE SMOKE WAS COMING FROM THE LT WINDSHIELD 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 TERMINAL 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) 2H72 4T4 TRTA13NM E20NE 20080602 NE 2008 6 2 CA080402002 220080305G7532 BLEED VALVE CESSNA560 560XL 2076702CE PWA 545 PW545A NE COMPRESSOR MALFUNCTIONED W E ENGINE SHUTDOWN EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 CA THE CREW EXPERIENCED ENGINE VIBRATIONS, FOLLOWED BY AN EEC MANUAL LIGHT. ENGINE POWER INCREASED AS EXPECTED, BUT THE CREW 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 SERVICE. THE COMPONENT WILL BE INVESTIGATED AND RESULTS FORWARDED FOR REVIEW. (TC NR 20080402002) 2L72 4F4 FRTA22CE E00059EN 20080602 NE 2008 6 2 CA080402005 220080314G7261 TANK AEROSPATR42 ATR42* 8680900EU PWA 120 PW120 NE ENGINE OIL LEAKING W E ENGINE SHUTDOWN KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION DEDESCENT 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) 2H72 4T4 TRTA53EU E20NE 20080602 EA 2008 6 2 CA080402006 220080328G853072877 TAPPET PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA NR 1 CYLINDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1490 WHEN REPLACING NR 1 CYLINDER THE HYDRAULIC TAPPET BODY WAS FOUND CRACKED IN TWO PLACES. (TC NR 20080402006) 1L72 3O3 O A20SO E14EA 20080602 EA 2008 6 2 CA080402007 120080402G3150 WARNING LIGHT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE ILLUMINATED W BE EMER. DESCENT ENGINE SHUTDOWN J WARNING INDICATION DEDESCENT 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 BY THE LOW OIL PRES INDICATION. ALL OTHER PARAMETERS NORMAL. CREW THEN ACTIONED EMERGENCY PROCEDURES AND SHUT DOWN LT ENG AND LANDED. (TC NR 20080402007) 2L72 4F4 FRTA21EA E15NE 20080602 EA 2008 6 2 CA080402008 120080314G2435 BRUSHES DHAV DHC2 DHC2MK3 2800107EA PWA PT6 PT6A34 52043EA STARTER/GEN WORN W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 379 STARTER WOULD NOT OPERATE TO START ENGINE. (TC NR 20080402008) 1H71 3T4 T A806 E4EA 20080602 NE 2008 6 2 CA080402010 220080316G7320 EEC AEROSPATR72 ATR72 EU PWA PW120 PW124B NE ENGINE MALFUNCTIONED W C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA DURING TAKEOFF ROLL, THE ENGINE TORQUE INDICATED 75 PERCENT. THE TAKEOFF WAS ABORTED AND AIRCRAFT TAXIED BACK TO THE RAMP. THE EEC WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. THE REMOVED UNIT WILL BE RETURNED FOR INVESTIGATION AND UPDATES PROVIDED TO TC. (TC NR 20080402010) 2H72 4T4 TRT E2ONE 20080603 EA 2008 6 3 CA080402011 220080304G7200 ENGINE EMB 312 EMB312 SO PWA PT6 PT6* 52043EA POWER LOSS W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CA DURING TRAINING MANEUVERS, THE PILOT REPORTED A LOSS OF ENGINE POWER. PILOT ATTEMPTED TO RECOVER WITHOUT SUCCESS, AND EJECTED SAFELY. AIRCRAFT CRASHED IN AN EMPTY FIELD. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L71 4T3 TRT E2NE 20080602 NE 2008 6 2 CA080402014 220080321G7200 ENGINE AEROSPATR72 ATR72 EU PWA PW120 PW127 NE POWER LOSS W EA ENGINE SHUTDOWN UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA DURING CLIMB, ENGINE POWER WAS LOST ACCOMPANIED BY A LOUD NOISE. THE ENGINE WAS SECURED AND THE AIRCRAFT RETURNED TO BASE. 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) 2H72 4T4 TRT E20NE 20080602 NE 2008 6 2 CA080402017 220080327G7200 ENGINE AEROSPATR72 ATR72201 8680943EU PWA PW120 PW124B NE MAKING METAL W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CLCLIMB 1 CA THE OIL PRESSURE INDICATION REDUCED TO ZERO FOLLOWED BY A LOUD NOISE, OIL MIST AND ODOR IN THE CABIN. THE ENGINE THEN FLAMED 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. 2H72 4T4 TRTA53EU E2ONE 20080602 2008 6 2 CA080402018 420080317G6122 GOVERNOR BEECH 1900 1900C 1154161CE PWA PT6 PT6A67B 52043NE PROPELLOR MISRIGGED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CA TAKEOFF WAS ABORTED WHEN THE ENGINE WOULD NOT PRODUCE FULL POWER. INVESTIGATION REVEALED IMPROPER RIGGING OF THE PROP GOVERNOR. 2L72 4T4 TRTA24CE E26NE 20080602 NE 2008 6 2 CA080402019 220080401G7200 ENGINE AEROSPATR72 ATR72 EU PWA PW120 PW127 NE DAMAGED W EA ENGINE SHUTDOWN UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CLCLIMB 1 CA THE CREW HEARD A LOUD NOISE ACCOMPANIED BY AN AIRCRAFT YAW. UPON POWER REDUCTION, THE ENGINE SHUT DOWN BY ITSELF. INITIAL INVESTIGATION REVEALS SEVERE INTERNAL ENGINE DAMAGE. THE ENGINE WILL BE INVESTIGATED AND UPDATES WILL BE PROVIDED. (TC NR 20080402019) 2H72 4T4 TRT E20NE 20080602 EA 2008 6 2 CA080403002 120080331G2750855D1009 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE MALFUNCTIONED W L ABORTED APPROACH FJ FLT CONT AFFECTED WARNING INDICATION APAPPROACH 1 CA 24045 THE POST MAINTENANCE TEST FLIGHT WAS UNSUCCESSFUL. THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE ON APPROACH WHEN THE FLAPS WERE SELECTED FROM 0 TO 8 DEGREES. THE FLAP ELECTRONIC CONTROL UNIT (FECU) CODES WERE RETRIEVED. THE RT BRAKE AND POSITION SENSOR UNIT (BPSU) WAS REPLACED AND RIGGED, THE LT BPSU WAS RE-RIGGED AND THE FECU WAS REPLACED FOR TROUBLESHOOTING. 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 20080403002) 2L72 4F4 FRTA21EA E15NE 20080602 WP 2008 6 2 CA080403003 220080331G73108945682 TUBE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP ENGINE CRACKED W A UNSCHED LANDING RK PARTIAL RPM/PWR LOSS FLUID LOSS CLCLIMB 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 FLOW INDICATION FOR THAT ENGINE WAS ERRATIC. THE LANDING WAS UNEVENTFUL. ONCE ON THE GROUND THE AIRCRAFT WAS INSPECTED BY MAINTENANCE AND THEY DETERMINED THE LINE FROM THE FUEL FLOW TRANSMITTER TO THE FUEL FLOW DIVIDER HAD SPLIT AT A BEND RADIUS IN THE TUBE CAUSING A SOMEWHAT LARGE FUEL LEAK. THE LEAK WAS ENOUGH TO AFFECT ENGINE PERFORMANCE. THE LINE WAS FOUND 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. 2L72 4T4 TRTA8SW E4WE 20080602 SW 2008 6 2 CA080403005 120080331G56102621126905 WINDSHIELD SWRNGNSA226 SA226T 8780122SW GARRTTTPE331TPE33110U 01514WP COCKPIT CRACKED W BA EMER. DESCENT UNSCHED LANDING W INADEQUATE Q C CRCRUISE 1 CA 1986 IN LEVEL CRUISE AT FLIGHT LEVEL 220 APPROXIMATELY 25 MINUTES AFTER DEPARTURE, THE LEFT HEATED WINDSHIELD SUDDENLY SHATTERED. ATC WAS ADVISED AND DESCENT REQUESTED FOLLOWED BY REQUEST FOR RETURN TO CYWG. AFTER ESTABLISHING THE RETURN COURSE AND LEVELING AT 9000 FEET, THE PASSENGERS WERE BRIEFED AND THE AIRCRAFT PROCEEDED BACK AT REDUCED CRUISE SPEED AND COMPLETED A NORMAL LANDING. UPON WINDOW REMOVAL NO DISCREPANCIES WERE NOTED WITH THE PREVIOUS INSTALLATION, ALL ATTACHING HARDWARE WAS CORRECT. 2L72 4T4 TRTA5SW E4WE 20080602 EU 2008 6 2 CA080403007 120080319G2121 BEARING AIRBUSA319 A319112 3930323EU CFMINTCFM565CFM565B6 13802NE RECIRC FAN OVERHEATED W B EMER. DESCENT MBJOVER TEMP SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CLCLIMB 1 CA 19565 NEAR TOP OF CLIMB, COCKPIT ODOR OF ACRID BURNING SMELL NOTICED. NO ECAM OR VISUAL CUES. DURING CRUISE CHECK NOTICED FAN IN AMBER DISPLAYED ON COND PAGE. RECYCLED CAB FAN AND SMELL REOCCURRED IMMEDIATELY. RETURNED TO AIRPORT. THE SHOP REPORT INDICATED THAT THE REAR BEARING SEIZED, THE FRONT BEARING WAS DRY, THE FAN OVERHEATED BUT THE STATOR WAS ELECTRICALLY NORMAL. THE FAN WAS DIRTY AND SMELLED OVERHEATING. 2L72 4F4 FRTA28NM E37NE 20080602 NE 2008 6 2 CA080403008 220080401G8550100243 SHAFT CNDAIRCL215 CL2151A10 1900320EA PWA R2800 CA3 52026NE HAMSTD43E 43E60 NE ENGINE OIL SHEARED W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION LDLANDING 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 GALLONS, SO THE RT ENGINE WAS SHUT DOWN. MAINTENANCE DISCOVERED THAT THE SCAVENGE PUMP HAD INGESTED A PIECE OF A CASTLE NUT WHICH HAD BROKEN OFF ONE OF THE NUTS P/N 542 FROM ONE OF THE REDUCTION PINION GEAR SHAFTS. THIS HAD CAUSED THE FAILURE OF THE GEAR/SHAFT P/N 100243 IN THE ACCESSORY DRIVE CASE. 2H72 4R4 RRTA14EA E231 6 CP871 20080602 NE 2008 6 2 CA080403009 220080116G8520128495 MAIN BEARING DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD22D 22D30 NE MASTER ROD BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 1474 DURING INSPECTION METAL PIECES FOUND IN ENGINE SUMP. INVESTIGATION DETERMINED THEM TO BE PART OF FLANGE OF MASTER ROD BEARING. ENGINE REMOVED FOR OVERHAUL. 1H71 3R3 RRCA806 5E1 5 CP736 20080602 GL 2008 6 2 CA080404001 120080303G5310C2TP63ND SPAR DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA WHEN REPLACING FRONT CENTER SPAR DUE CRACK. REAR CENTER SPAR DISCOVERED CORRODED BEHIND CENTER MOUNT BRACKET. SPAR REPLACED. THIS CORROSION WAS NOT VISABLE UNTIL ACCESS TO INSIDE OF TAILPLANE WAS GAINED (TC NR 20080404001) 1H71 3R3 RRCA806 5E1 20080602 SW 2008 6 2 CA080404002 120080326G2913 SHAFT SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HYD PUMP FAILED W K NONE O OTHER ININSP/MAINT 1 CA 1155 DURING A ROUTINE INSPECTION OF THE HYDRAULIC PUMP, THE RETAINING BOLT WHICH HOLDS THE SPLINE DRIVE INTO THE HYDRAULIC PUMP HAD SHEARED. 2L72 4T4 TRTA8SW E4WE 20080602 NM 2008 6 2 CA080404004 120080402G29136617303 PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA HYDRAULIC SYS FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 1339 DURING CRUISE FL 120, NR 2 ENG HYD PRES CAUTION LIGHT ILLUMINATED. HYD NR 2 PRESS - 0 PSI - AFTER PERFORMING ABNORMAL CHECKLIST WITH PTU ON, PRESS 3000 PSI. UNEVENTFUL LANDING. MAINTENANCE CREW REPLACED THE NR 2 ENGINE DRIVEN HYDRAULIC PUMP. 2H72 4T4 TRTA13NM E00062EN 20080602 EA 2008 6 2 CA080404005 120080331G282339423091 SHUTOFF VALVE DHAV DHC3 DHC3 2800202EA GARRTTTPE331TPE33110R 0517 WP FUEL SYSTEM UNSERVICEABLE W O OTHER O OTHER NRNOT 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. AIRCRAFT RETURNED TO SERVICE. 1H71 3R4 T A815 E4WE 20080602 NM 2008 6 2 CA080404006 120080331G24201701320 GENERATOR EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE APU FAULTED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS NRNOT 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 GENERATOR. APU GENERATOR WAS REPLACED. 2L72 4F4 FRTA57NM E00070EN 20080602 SO 2008 6 2 CA080404007 120080329G4990GTCP36150G APU GULSTMG1159 GIV 3980115SO RROYCETAY TAYMK6118 NE LEAKING W O OTHER K FLUID LOSS TXTAXI/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. REPLACED 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. LOANER APU INSTALLATION IN PROGRESS, MORE INFO WILL BE GIVEN WHEN REPORT OF REPAIR SHOP WILL BE GIVEN. 2L72 4F4 FRTA12EA A25NE 20080602 CE 2008 6 2 CA080404009 120080404G2510 CABLE CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL PILOT SEAT OUT OF ADJUST W O OTHER O OTHER TXTAXI/GRND HDL 1 CA FLIGHT CREW DISCREPANCY, PILOTS SEAT DOES NOT SLIDE BACK INTERMITTENTLY. SEAT REMOVED AND VISUALLY INSPECTED. REEL ASSEMBLY 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. 1H71 3O3 ONT3A12 E274 5 NP910 20080602 NE 2008 6 2 CA080406001 220080331G73210301037950 LINE SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE FUEL CONTROL BROKEN W K NONE O OTHER ININSP/MAINT 1 CA TUBE WAS DISCOVERED CRACKED AND SEPARATED FROM FLARE AT P2 TAP END DURING ROUTINE INSPECTION. ORIGINALLY, BLACK DEPOSITS WERE NOTICED AT B-NUT AND WHEN DISASSEMBLED, FOUND COMPLETE FAILURE OF TUBE FROM FLARE END. CLOSE TOLERANCE FIT OF TUBE PROBABLY PROHIBITED ANOMALY FROM BEING NOTICED EARLIER. 1G71 3U3 UNCH9EU E19EU 20081105 NE 2008 11 5 CA080407001 220080404G7200C632A2116102 HOUSING UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE ENGINE CRACKED W K NONE O OTHER ININSP/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. 1G72 3U3 UNCR0001RD E34NE 20080602 2008 6 2 CA080407002 120080331G3297472011 WIRE HARNESS NLG WOW MISINSTALLED W O OTHER O OTHER NRNOT 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 HARNESSES PULLED FROM STOCK WERE MISS WIRED. ON CONNECTOR 3261-P32 PINS A-B AND D-E WERE WIRED REVERSED. HARNESSES APPROPRIATELY 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 120080406G2752852D1001921 ACTUATOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE FLAP UNSERVICEABLE W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION DEDESCENT 1 CA ON APPROACH AT 4000 FT SELECTING FLAPS FROM 0 - 8 DEG, FLAP FAIL MSG APPEARED IMMEDIATELY WITH NO MOVEMENT OF FLAPS. AIRSPEED 215 AT THE TIME. A/C WAS AT -57 DEG FOR 1 HR IN CRUISE, GND -4. FECU INTERGRADED AND FOLLOWING FAULT CODES DISPLAYED 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 AND 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 PAPERWORK COMPLETED. A/C FERRIED. TROUBLESHOOTING GOING ON, ACTION PLAN TO INSPECT AND LUBE ALL DRIVES AND CHANGE ALL FLAP ACTUATORS WITH NEWLY OVERHAULED UNITS SENT. INFORMATION WILL BE UPDATED WHEN AVAILABLE. 2L72 4F4 FRTA21EA E15NE 20080602 GL 2008 6 2 CA080407004 120080404G32341760A000004 LEVER BOMBDRBD100 BD1001A10 1390044GL HNYWL AS907 AS90711A 33908WP MLG LOOSE W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA AFTER TAKEOFF, IT WAS REPORTED THAT THE CREW WERE UNABLE TO RETRACT THE FLAPS FROM THE 10 DEGREE POSITION TO THE 0 DEGREE POSITION. PRELIMINARY REPORT STATES THAT A LOOSE SCREW WAS FOUND INSIDE THE FLAP LEVER GUARD. THE FORWARD RIGHT SCREW LOCATED INSIDE THE GUARD WAS FOUND TO BE PROTRUDING SUFFICIENTLY TO PREVENT THE LEVER FROM MOVING FROM THE 10 DEGREE POSITION 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 SHOW ANY SIGNS OF LOOSENESS (REFER TO FIGURE1). PLEASE REPORT ANY ANOMALIES FOUND DURING THIS INSPECTION. 2L72 4F4 FRTT00005NYE00010LA 20080602 EA 2008 6 2 CA080407005 220080403G7200PT6A20 ENGINE DHAV DHC6 DHC6100 2802610EA PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL STOPPED W A UNSCHED LANDING Y ENGINE STOPPAGE CLCLIMB 1 CA 117864634 AFTER A NORMAL TAKEOFF, THE CREW WENT THROUGH POWER 1, FLAPS UP AND POWER 2 AND AFTER SETTING POWER 2 PRIOR TO CLIMB CHECKS, 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. 1H72 3T3 TRTA9EA E4EA 6 CP15EA 20081105 EU 2008 11 5 CA080407006 120080405G2913A5026780 PUMP SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B 60037NE HYDRAULIC SYS MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 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 LIGHT OBSERVED, NOTICE CHANGE OF FEEL TO THE CYCLIC CONTROL (ACCUMULATORS ACTIVATED) CHECKED THAT BOTH HYD SWITCHES HAD NOT 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 POSITION FOR A SECOND APPROACH AND LANDED HELICOPTER WITHOUT INCIDENT THE HYDR PUMP WAS REPLACED AFTER AND ACFT WAS TEST F1G71 3U3 U H9EU E00054EN 20080602 SW 2008 6 2 CA080407007 120080405G6322R476204971 GEAR SET BELL 4762060025 BELL 47 47G4 1181030SW LYC O540 VO540B1B3 41532EA COOLING FAN SHEARED W A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 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 OF THE DRIVE SHAFT WAS MISSING. WE ARE SENDING IN REMAINING SHAFT SEGMENT WHERE IT SHEARED FOR METALLURGICAL ANALYSIS. 1G71 3O3 O 2H3 E304 20080602 EA 2008 6 2 CA080407010 120080402G3250 CABLE DHAV DHC6 DHC6200 2802620EA PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL STEERING BROKEN W D RETURN TO BLOCK S AFFECT SYSTEMS TXTAXI/GRND HDL 1 CA STEERING CABLE BROKE ON TAXI WHILE THE AIRCRAFT WAS PREPARING FOR TAKEOFF. 1H72 3T3 TRTA9EA E4EA 6 CP15EA 20080602 EU 2008 6 2 CA080408001 120080408G25204030082SRS ATTACH FITTING PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL PAX SEAT CRACKED W K NONE O OTHER ININSP/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. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20080602 EA 2008 6 2 CA080408002 120080329G275070745 CONTROL UNIT CNDAIRCL600 CL600* 1900302EA GE CF34 CF348C5 30050NE TE FLAP MOTOR FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA 8989 8989 PRIOR TO DEPARTURE FLIGHT CREW COMPLETED A STAB TRIM RESET. SHORTLY AFTER FLAP RETRACTION ON TAKEOFF, FLIGHT CREW RECEIVED AN AP TRIM IS ND ASSOCIATED WITH AN AP PITCH TRIM ‘CAUTION MESSAGE. SUBSEQUENTLY CREW RECEIVED A ELEVATOR SPLIT’ CAUTION MESSAGE. CREW FOLLOWED QRH, CIRCLED TO BURN OFF FUEL AND LANDED BACK AT DEPARTURE AIRPORT WITHOUT INCIDENT. MAINTENANCE 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 OF THE MOTOR CONTROL UNIT CHANNEL 2 INTERNAL HOLD ON RELAY. MOTOR CONTROL UNIT REPLACED. OPERATIONAL TESTS OF THE SSCU,2L72 4F4 FRTA21EA E00063EN 20080602 NM 2008 6 2 CA080408003 120080404G2130 CABIN PRESSURE BOEING757 75728A 1384976NM RROYCERB211 RB211535E43754555NE MALFUNCTIONED W A UNSCHED LANDING G MULTIPLE FAILURE CLCLIMB 1 CA AIRCRAFT C-GTDX DEPARTING FROM YYZ ON APRIL 4TH 2008, AROUND 7000 FT AN EICAS MSG AUTO PRESSURIZATION SYS 1 AND 2, AIRCRAFT RETURNED BACK TO YYZ AND REQUESTED FIRE TRUCKS ON ARRIVAL DUE TO OVERWEIGHT LANDING. TROUBLESHOOTING CARRIED OUT, BOTH PRESSURIZATION CONTROL UNITS AND STBY ALTIMETER REPLACED AS PRECAUTIONARY MEASURE. FLIGHT TEST CARRIED OUT SUCCESSFULLY. INVESTIGATION IS ON GOING. 2L72 4F4 FRTA2NM E12EU 20080602 EA 2008 6 2 CA080408004 120080330G3230101655 UPLOCK ROLLER DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE RH MLG SEIZED W O OTHER J WARNING INDICATION APAPPROACH 1 CA 3589520079 RT MLG FAILED TO EXTEND ON LANDING GEAR SELECTION, CREW PERFORMED GO-AROUND AND USED ALTERNATE GEAR EXTENSION. ALL LANDING GEAR EXTENDED AND NORMAL LANDING CARRIED OUT. MAINTENANCE INSPECTION FOUND RT MLG UPLOCK ROLLER SEIZED, ROLLER REPLACED, GEAR SWINGS COMPLETED AND AIRCRAFT RETURNED TO SERVICE. TIMES PROVIDED ARE SHOCK STRUT TIMES, ROLLER IS NOT SERIALIZED AND NOT TRACKED FOR ACTUAL TIMES. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080602 EU 2008 6 2 CA080409001 120080325G259740900011 WIRE AIRBUS310 A310304 3930339EU GE CF6 CF680C2* GL COFFEEMAKER BURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 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 DAMAGE ON THE COFFEE MAKER. COFFEE MAKER REPLACED AND ROUTED TO SHOP FOR REPAIR. 2L72 4F4 FRTA35EU E23EA 20080602 EU 2008 6 2 CA080409003 120080407G2133 OUTFLOW VALVE AIRBUS310 A310300 3930305EU GE CF6 CF680C2* GL CABIN PRESSURE MALFUNCTIONED W B EMER. DESCENT J WARNING INDICATION CRCRUISE 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 MANUAL. EMERGENCY DESCENT AND QAR PROCEDURES FOLLOWED. PAX MASK SYSTEM ACTIVATED IN AUTO. FLIGHT RETURNED TO STATION AT FL 10,000 FT. ACFT WAS REMOVED FROM SERVICE FOR INVESTIGATION. 2L72 4F4 FRTA35EU E23EA 20080602 EA 2008 6 2 CA080409004 120080330G3040601R3303313 CONTROLLER CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE WINDSHIELD TEMP OVERTEMP W O OTHER J WARNING INDICATION DEDESCENT 1 CA 1432514325 ON DESCENT THROUGH 21000 FEET INTO ARRIVAL AIRPORT, CAPTAIN’S LT WINDSCREEN SHATTERED. CREW DONNED OXYGEN MASKS AS A PRECAUTION. 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 TEMPERATURE CONTROLLER. MAINTENANCE ALSO REPLACED THE LT WINDSHIELD TEMPERATURE CONTROLLER SUSPECTING THAT IT HAS CAUSED AN OVERHEAT CONDITION. 2L72 4F4 FRTA21EA E15NE 20081105 SW 2008 11 5 CA080409005 120080409G2450MS2207375 CIRCUIT BREAKER BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE OVERHEAD PANEL INOPERATIVE W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) WHILE DOING A PREFLIGHT CHECK DURING FLIGHT TRAINING IT WAS NOTED THAT THE LT BOOST PUMP CIRCUIT BREAKER WAS NOT ABLE TO BE CYCLED. THE CIRCUIT BREAKER WAS REMOVED AND REPLACED. AFTER GOING THROUGH THE REST OF THE CIRCUIT BREAKER PANEL IS WAS NOTED THAT IN EXCESS OF 20 BREAKERS WERE DIFFICULT TO OR UNABLE TO BE CYCLED. REQUIRED CIRCUIT BREAKERS WERE REPLACED. INSPECTION CRITERIA TO NOW INCLUDE CYCLING BREAKERS AT INTERVALS TO REDUCE THE CHANCE OF A BREAKER NOT POPPING WHEN REQUIRED AND CAUSING FURTHER PROBLEMS/DAMAGE. (TC NR 20080409005) 1G71 4U4 U H1SW E17EA 20080602 EA 2008 6 2 CA080409006 220080330G7230 BLADES BELL 412 412 1182202SW PWA PT6T PT6T3 52045EA COMPRESSOR TURB FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION APAPPROACH 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. 1G72 4U4 U H4SW E22EA 20080602 EA 2008 6 2 CA080409008 120080409G521033130131 PISTON CNDAIRCL215 CL2151A10 1900320EA ACTUATOR CRACKED W K NONE O OTHER ININSP/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. 2H72 4R RTA14EA 20081105 NE 2008 11 5 CA080410004 220080401G7314LW15473 PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/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 20080410004) 1G71 3O3 O H11NM 1E4 20080602 EA 2008 6 2 CA080410005 120080408G2750855D1009 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE RT FLAP SYS UNSERVICEABLE W O OTHER J WARNING INDICATION DEDESCENT 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 REPLACED, FLAP SYSTEM RIGGED AND FUNCTION CHECKED SERVICEABLE. THE A/C RETURNED TO SERVICE WITH NO FURTHER FAULTS. 2L72 4F4 FRTA21EA E15NE 20081105 WP 2008 11 5 CA080410006 120080409G6310 SHAFT ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE CLUTCH WORN W K NONE O OTHER ININSP/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 TO INTERNAL WEAR OF THE SHAFT, HSG AND SPRAG. THE SPRAG CAGE CROSSBAR WAS CRACKED, PEANUT INNER EARS WERE BROKEN OFF, WEAR ON THE INNER SURFACE OF THE PEANUTS (POSSIBLE SLIPPAGE) AND EXCESSIVE CAGE WINDOW WEAR. 1G71 3O3 O H11NM 1E4 20080602 SO 2008 6 2 CA080410009 220080312G8530AEC631397SN2B22 CYLINDER HEAD CESSNA414 414 2075908CE CONT O520 TSIO520N 17040SO MCAULY3AF32C3AF32C505 GL ENGINE CRACKED W A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 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. 1L72 3O3 ORTA7CE E8CE 5 CP22EA 20081105 EU 2008 11 5 CA080411001 120080220G6700D107610E ACTUATOR BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL TRIM SYS FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ACTUATOR FAILED, (WOULD NOT RETRACT) ON PRESTART TEST. FAILED IN THE EXTEN POSITION (CYCLIC FULL FWD) (TC NR 20080411001) 1G72 3U3 U H3EU E4CE 20080602 2008 6 2 CA080411002 420080409G6122210332 PILOT VALVE WOODWARD GOVERNOR DAMAGED W O OTHER X ENGINE FLAMEOUT NRNOT REPORTED 1 CA 97 THE GOVERNOR WAS MANUFACTURED BY ONTIC, ONTIC HAS THE MANUFACTURING RIGHTS TO THE FORMER WOODWARD GOVERNOR COMPANY PISTON 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 FROM 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 120080220G670010513142 ROD END BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL BEARING DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ROD END HAS TEFLON MISSING WITH METAL TO METAL CONTACT (TC NR 20080411003) 1G72 3U3 U H3EU E4CE 20080602 NM 2008 6 2 CA080411004 120080408G29106517840330 LINE BOEING727 727223 1384074NM PWA JT8 JT8D15 52051NE HYD SYSTEM LEAKING W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION NRNOT 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 LOWERED HOWEVER FLIGHT CREW WAS UNABLE TO MANUALLY LOWER THE LT GEAR. TWO ATTEMPTS WERE MADE AND THEN THE FLIGHT CREW SELECTED ON ONE "A" SYSTEM HYDRAULIC PUMP TO GET THE LT GEAR DOWN AND LOCKED. THE PUMP WAS THEN TURNED OFF AGAIN. THE AIRCRAFT LANDED SUCCESSFULLY WITH NO ADDITIONAL FAULTS. MAINTENANCE PERSONNEL FOUND A PIN HOLE LEAK ON THE A SYSTEM HYDRAULIC RETURN LINE RETURNING FROM THE A SYSTEM HEAT EXCHANGER. A PERMANENT REPAIR WAS CARRIED OUT BY THE INSTALLATION OF A P2L73 4F4 F A3WE E2EA 20080602 GL 2008 6 2 CA080411006 220080409G725023063354 TURBINE BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE DAMAGED W A UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 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 EXHAUST 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,1G71 3U3 UO H2SW E1GL 20080602 CE 2008 6 2 CA080411007 120080407G32450923150 TUBE CESSNA425 425 2076018CE PWA PT6 PT6A112 52043NE MCAULY4HFR344HFR34C762 NE NLG WHEEL LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 62 NOSE TIRE FOUND LOW ON POST FLIGHT INSPECTION BY 10 PSI. NOSE WHEEL ASSY REMOVED FOR TEAR DOWN AND INVESTIGATION. SPARE BUILT-UP WHEEL ASSY INSTALLED. TEAR DOWN SHOWED INNER TUBE HAD PIN HOLE IN OUTER CIRCUMFERENCE AT ONE END OF A FOLD MARK. NO OTHER FAULTS FOUND WITH TIRE OR TUBE. 1L72 3T3 TRTA7CE E4EA 6 C3PNE 20080603 GL 2008 6 3 CA080414001 120080407G5711 SPAR DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE WING CRACKED W K NONE O OTHER ININSP/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. 1H71 3R3 RRCA806 5E1 5 CP206 20080603 WP 2008 6 3 CA080414003 120080410G2435 GEAR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE STARTER GEN WORN W K NONE O OTHER ININSP/MAINT 1 CA 58 UPON POST FLIGHT INSPECTION, STARTER TEETH FOUND WORN, REMOVED AND INSTALLED NEW STARTER. 1G71 3O3 O H11NM 1E4 20080603 WP 2008 6 3 CA080414004 120080410G6310 CLUTCH ACTUATOR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAIN ROTOR MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA 1552 UPON INSPECTION, CARRIED OUT METHOD 2 AND THE ACTUATOR KEPT RUNNING . 1G71 3O3 O H11NM 1E4 20080603 EA 2008 6 3 CA080414005 220080411G72303012060 DUCT PWA PT6 PT6A27 52043EA DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA METAL SWARF FOUND INSIDE COOLING PASSAGES OF DUCT ASSY. 4 T E4EA 20080603 2008 6 3 CA080414006 420080407G221008071 STATIC LINE AIRTRCAT802 AT802A 0390308SW PWA PT6 PT6A67A 52043NE HARTZLHCB5M HCB5MA3 GL AUTO PILOT SYS DETERIORATED W K NONE O OTHER ININSP/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 FLEET WILL BE INSPECTED FOR SERVICEABILITY. 1L71 3T4 TNCA19SW E26NE 6 CP44GL 20080603 NM 2008 6 3 CA080414008 120080328G3242 BRAKE DISC BFGOODRICH DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE MLG BRAKE ASSY WARPED W O OTHER MJ OVER TEMP WARNING INDICATION TXTAXI/GRND HDL 1 CA 395056254 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. MAINTENANCE REPLACED THE NR 3 BRAKE UNIT AND THE NR 3 AND 4 MAIN WHEEL ASSEMBLIES. TAXI AND FUNCTION CHECKS OF THE BRAKING 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080603 2008 6 3 CA080414009 120080414G31107003652631 DISPLAY COCKPIT INOPERATIVE W K NONE O OTHER ININSP/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 120080408G2750Z4243130000 CONTROL CABLE ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA TE FLAPS FRAYED W K NONE O OTHER ININSP/MAINT 1 CA FLAP CENTER CABLE WAS FOUND FRAYED DURING REGULARLY SCHEDULED MAINTENANCE. 1L71 3O3 O0 A76EU 1E10 20080603 SW 2008 6 3 CA080415005 120080412G56102719442004 WINDSHIELD SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP COCKPIT CRACKED W B EMER. DESCENT O OTHER CRCRUISE 1 CA 1233 DURING THE RETURN LEG TO MAIN BASE THE AIRCRAFT EXPERIENCED A RT HEATED WINDSHIELD CRACK IN A SPIDER WEB FASHION. THE AIRCRAFT 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. 2L72 4T4 TRTA8SW E4WE 20080603 NE 2008 6 3 CA080415006 220080411G7250 BLADE TMECA ARRIELARRIEL1B 6OO30NE TURBINE WHEEL DAMAGED W K NONE O OTHER ININSP/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-CONDUCTOR OF THE IGNITER, P/N 9550175400, THAT DISLODGED ITSELF FROM THE HOUSING. THIS WAS FOUND DURING A SCHEDULED 100/150 HR ENGINE INSPECTION. THE AFFECTED MO3 HAS BEEN SEND TO MANUFACTURER FOR FUTURE INVESTIGATION. SUBSEQUENTLY ALL OTHER ENGINE IGNITER WHERE INSPECTED AND REMOVED FROM SERVICE DO TO LOOSENESS OF THE SEMI-CONDUCTOR. PICTURES WERE TAKEN AND SEND TO MANUFACTURER. 3 U E19EU 20080521 WP 2008 5 21 CA080415007 120080411G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 79 (CAN) AFTER FIRST GROUND RUN, STARTER CRACKED, REPLACED STARTER (TC NR 20080415007) 1G71 3O3 O H11NM 1E4 20080521 EU 2008 5 21 CA080416001 120080414G5302V40GT3911AA SPRING BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL TAIL BOOM BROKEN W K NONE O OTHER ININSP/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 PROBLEM HAPPENED STATICALLY ON THE GROUND. THESE EJECTION SPRINGS WERE ORDERED NEW FROM MFG, BATCH NR S0000243616 COMING FROM 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) 1G72 3U3 U H3EU E4CE 20080521 NE 2008 5 21 CA080416002 220080416G7414 COIL BL6006163 ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO LOOSE W K NONE O OTHER ININSP/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 DISASSEMBLY THE OIL SEAL WAS FOUND TO BE LEAKING. THE COIL WAS LOOSE IN THE HOUSING UNDER THE COIL CLAMPS. THE COIL HAD DARK 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 THE CASTING AND A NEW CONTINENTAL ALPHA SYS DATAPLATE. THIS MAG WAS REBUILT IN JANUARY OF 2007. THE MAG WAS RETURNED TO MFG FOR WARRANTY PURPOSES. (TC NR 20080416002) 1G71 3O3 O H11NM 1E4 20080521 2008 5 21 CA080416003 420080416G2562ELT10 ELT BBAVIA7 7GCAA 21101N8SW LYC O320 O320A2B 41508EA INOPERATIVE W K NONE O OTHER ININSP/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) 1H71 3O3 O A759 E274 20080521 WP 2008 5 21 CA080417003 120080413G7920 PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE OIL LEAKING W K NONE O OTHER ININSP/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 THE SEALS AND THIS ALLOWS ENGINE OIL TO BYPASS AND FLOW OUT OF THE DRAIN. PUMP WAS REPLACED AND AIRCRAFT RETURN TO SERVICE. DATE CODE ON THE PUMP IS 4105. (TCNR 20080417003) 1G71 3O3 O H11NM 1E4 20080521 EU 2008 5 21 CA080417010 120080221G5610 SEAL SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE CHIN BUBBLE DEPARTED W A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 CA (CAN) CHIN BUBBLE WINDOW AND SEAL DEPARTED THE AIRCRAFT IN CRUISE FLIGHT. AIRCRAFT WAS LANDED AND CHECKED FOR DAMAGE, NOT FOUND. REVIEW INDCATED THAT THE WINDOW WAS REMOVED FOR MAINT BEFORE THE OCCURANCE. WILL FOLLOW UP FOR SPECIFIC PN (TC NR 20080417010) 1G71 3U3 UNCH9EU E19EU 20080521 2008 5 21 CA080418001 120080416G3310REE75R RHEOSTAT VIKING 72510090005 PWA PT6 PT6A50 52043EA HAMSTD24PF 24PF305 GL RESISTANCE COILSMELTED W K NONE O OTHER ININSP/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 THE 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 HAS A SLIGHT GLOW) AND DISSIPATING MAXIMUM WATTAGE. THE HEAT IS TRANSFERRED THROUGH THE RHEOSTAT SHAFT CAUSING KNOB PN MS91528-1C1-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 CP1NE 20080521 NM 2008 5 21 CA080418002 120080417G2612 FIRE DETECTOR BOEING727 727247 138408FNM PWA JT8 JT8D15 52051NE NR 1 NACELLE FALSE INDICATIONW F ACTIVATE FIRE EXT. N FALSE WARNING CLCLIMB 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 WITHOUT FURTHER INCIDENT. THERE WAS NO EVIDENCE OF A FIRE. MAINT FOUND THE FAULT IN THE NR 1 FIRE DETECTION B SYS. (TC NR 20080418002) 2L73 4F4 F A3WE E2EA 20080521 2008 5 21 CA080418003 120080318G3245302120402 TUBE MLG TIRE FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) MULTIPLE FAILURES OF INNER TUBES ON VARIETY OF COMPANY C-208 MAIN WHEELS. TUBES FAIL IN DIFFERENT WAYS FROM PIN HOLES TO 18 INCH SPLITS. THERE HAVE BEEN NO FOREIGN OBJECTS FOUND IN THE AFFECTED TIRES AND ASSY PRACTICES HAVE BEEN OBSERVED TO ENSURE CORRECT PROCEDURES ARE BEING FOLLOWED. TUBES ARE PURCHASED FROM A VARIETY OF SUPPLIERS AND ORIGINATE IN DIFFERENT COUNTRIES. (TC NR 20080418003) 20080521 2008 5 21 CA080418004 420080417G6113VT2E16231 PLATE DHAV DHC2 DHC2MK3 2800107EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL PROP SPINNER DAMAGED W K NONE O OTHER ININSP/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-FOEU. THIS DAMAGE IS THE RESULT OF OUR INSTALLATION OF OUR PROP POSITION TRANSMITTER MOD STCSA 98-46, VT2E 1623. IDENTIFIED 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 O1H71 3T4 T A806 E4EA 6 CP15EA 20080521 SO 2008 5 21 CA080421001 120080408G3210424052 COTTER PIN PIPER 7872331 PIPER PA44 PA44180 7104402SO LYC O360 LO360E1A6 41514EA HARTZLHCC2Y HCC2YR2 GL TORQUE LINK MISSING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) COTTER PIN MISSING ON LT MLG TORQUE LINK DURING WALK AROUND. BOLT REMOVED AND FOUND DRY OF LUBRICATION, WHICH COULD HAVE CAUSE NUT TO TURN AND SHEARING OF COTTER PIN. NEW BOLT INSTALLED AND LUBRICATED ON BOTH MAIN GEAR TORK LINKS. (TC NR 20080421001) 1L72 3O3 O A19S0 E286 5 CP920 20080521 NE 2008 5 21 CA080422002 220080417G72503053094CL BLADE BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE HARTZLHCB3T HCB3TN3 GL ENGINE DEFORMED W K NONE O OTHER ININSP/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 HAD DEFORMED AND THE CT BLADES HAD RUBBED AGAINST THE SEGMENTS CAUSING EXCESSIVE CLEARANCES. THIS WORK HAD BEEN DONE BY MFG. THE HOT SECTION WAS SENT BACK FOR WARRANTY CONSIDERATION . (TC NR 20080422002) 1L72 4T4 T A24CE E4EA 6 CP15EA 20080522 2008 5 22 CA080422003 420080420G8300 COUPLER LKHEED188 188A 5262602WP ALLSN 501D 501D13 03004GL ALLSN A6441 A6441FN606 GL ENG/GEARBOX UNKNOWN W K NONE O OTHER ININSP/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) 2L74 4T4 TRT4A22 E282 6 CP898 20080522 NE 2008 5 22 CA080423003 220080421G73201520KDC0501 EEC BOMBDRBD700 BD7001A10 1390006GL RROYCEBR700 BR700710A22009500NE ENGINE UNSERVICEABLE W O OTHER O OTHER CRCRUISE 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 ENGINE. EICAS MESSAGE (L FADEC FAULT) (CYAN) POSTED. CREW REQUESTED LOWER FLIGHT LEVEL AND LEVELED OFF AT FL370. APU WAS 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 RETURNED TO NORMAL OPERATING CONDITIONS. CREW DIVERTED, AS A PRECAUTIONARY MEASURE, IN ORDER TO HAVE THE AC EVALUATED AND REP2L72 4F4 FRTT00003NYE00061EN 20080521 NM 2008 5 21 CA080423004 120080416G56105893543130 WINDSCREEN BOEING727 727260 138408KNM PWA JT8 JT8D17 52049NE COCKPIT BURNED W H DEACTIVATE SYST/CIRCUITS AB FLAME/FIRE SMOKE/FUMES/ODORS/SPARKS ININSP/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 PRECAUTION. THE AC WAS RETURNED TO SERVICE. (TC NR 20080423004) 2L73 4F4 FRTA3WE E2EA 20080521 NE 2008 5 21 CA080423011 220080330G7200 ENGINE CESSNA500 500CESSNA 2076602CE PWA JD15 JT15D1A NE MALFUNCTIONED W A UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 CA (CAN) THE CREW REPORTED VIBRATIONS SHORTLY AFTER TAKEOFF AND WAS ATTEMPTING TO RETURN TO POINT OF DEPARTURE. THE AC CRASHED. ALL ON BOARD WERE FATALLY INJURED. BOTH ENGINES SHOWED INDICATIONS CHARACTERISTIC OF THE ENGINES PRODUCING LOW POWER 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 20080423011) 1L72 4F4 F A22CE E25EA 20080521 NE 2008 5 21 CA080423012 220080417G7261 OIL SYSTEM AMD FALC50FALCON2000 2730170NM PWC PW306 PW306C 52169NE ENGINE LEAKING W A UNSCHED LANDING KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF, THE CREW NOTED OIL SMELL FOLLOWED BY VISIBLE VAPOR IN THE CABIN AIR AND OIL PRESSURE GAUGE FLUCTUATIONS. 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 ESTABLISHED. (TC NR 20080423012) 2L72 4F4 FRTA50NM E35NE 20080521 EA 2008 5 21 CA080423013 220080328G7321 FUEL CONTROL BEECH 90 E90 1152914CE PWA PT6 PT6A28 EA ENGINE MALFUNCTIONED W O OTHER X ENGINE FLAMEOUT APAPPROACH 1 CA (CAN) DURING APPROACH, UPON RETARDING THE POWER LEVER TO IDLE, THE ENGINE ACCELERATED TO 90 PERCENT NG WITH AN ASSOCIATED TEMPERATURE OF 800 DEGREES. THE PILOT ELECTED TO SHUTDOWN THE ENGINE AND FEATHER THE PROP. THE FUEL CONTROL WAS SUBSEQUENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20080423013) 1L72 3T4 T 3A20 E4EA 20080521 CE 2008 5 21 CA080423014 120080417G7500 LINE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA ENGINE FRACTURED W E ENGINE SHUTDOWN J WARNING INDICATION NRNOT 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) 2L72 4T4 TRTA24CE E4EA 20080522 NM 2008 5 22 CA080424001 120080418G2910AE2463510E0124 FLEX LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD SYSTEM LEAKING W A UNSCHED LANDING KF FLUID LOSS FLT CONT AFFECTED CRCRUISE 1 CA (CAN) AFTER TAKEOFF WITH GEAR RETRACTON NR 2 HYD SYS QUANTIY DROPPED TO 2 QUARTS, THE CREW ELECTED TO RETURN TO THE AIRFIELD. DURING LANDING THE NR 2 HYD ISOLATION LIGHT CAME ON AND THE AC LOST THE OB SPOILERS, AND STEERING. THE AC WAS TOWED 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) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080522 SO 2008 5 22 CA080424003 220080423G741410160844 BRUSHES BENDIX BL3492205 CESSNA340 340A 2076405CE CONT O520 TSIO520NB 17040SO MCAULY3AF32C3AF32C93 GL MAGNETO MISSING W K NONE O OTHER ININSP/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 SPRING REMNANTS FOUND INSIDE OF MAGNETO. MAGNETO RE-ASSEMBLED WITH NEW BRUSH, BENCH TESTED IAW BENDIX OVERHAUL MANUAL X42000-1. MAGNETO RE-INSTALLED ON ENGINE, ENGINE STARTS NORMAL. (TC NR 20080424003) 1L72 3O3 O 3A25 E8CE 5 CP22EA 20080522 NE 2008 5 22 CA080424005 220080423G742090591507 IGNITION LEAD CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE LT ENGINE DEFECTIVE W K NONE O OTHER ININSP/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 LEAD, FOUND THE LEAD`S CENTER ELECTRICAL POST LOOSE AT IGNITER END. APPROX ONE INCH OF THE CENTER POST OF LEAD FEEL OUT WITH CERAMIC INSULATOR AND NOTED BURNING MARKS AROUND WHERE THE CENTER CORE HAD BROKEN AWAY. LEAD REPLACED WITH NEW UNIT. (TC NR 20080424005) 2L72 4F4 FRTA22CE E00053EN 20080522 NM 2008 5 22 CA080425002 120080421G274032EN614 WARNING SWITCH BOEING727 72722C 138400FNM PWA JT8 JT8D7B 52053NE LOWER STABILIZERCLOSED W C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 CA (CAN) WHILE ATTEMPTING TAKEOFF, TAKEOFF WARNING INTERMITTENT, HORN SOUNDED UPON POWER LEVER ADVANCEMENT. TAKEOFF WAS ABORTED 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 EXAMINATION 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 RETURNED TO SERVICE. (TC NR 20080425002) 2L73 4F4 F A3WE E2EA 20080522 NM 2008 5 22 CA080425006 120080425G5311654653969 FRAME BOEING737 737490 1384715NM BS 616 CRACKED W K NONE O OTHER ININSP/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 20080425006) 2L72 4F RTA16WE 20080522 NM 2008 5 22 CA080426001 120080423G8120310440001 TURBOCHARGER DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NR 1 ENGINE LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 4484718251 (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 OUTLET 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 COMPRESSOR FOUND TO BE BEYOND LIMITS, ENGINE CHANGE TO BE C/O. TEARDOWN REPORT TO FOLLOW WHEN AVAILABLE. (TC NR 20080426001) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080522 NM 2008 5 22 CA080428001 120080424G2761 CASE SMITHSIND DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ACTUATOR RUPTURED W D RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION TXTAXI/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 SPOILER ACTUATOR CASING HAD RUPTURED AND CAUSED THE LEAK. THE ACTUATOR WAS REPLACED, ADJUSTED, LEAK CHECKED AND TESTED SERVICEABLE. THE AC WAS RELEASED AND RETURNED INTO SERVICE. TSR: 1657:43 CSR: 1678 (TC NR 20080428001) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20080522 EA 2008 5 22 CA080428002 220080425G853005K21104 CYLINDER HEAD MOONEYM20 M20C 5870208SW LYC O360 O360A1D 41514EA MCAULY2D34C 2D34C53 GL ENGINE CRACKED W A UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 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 COMPLETED AND IT WAS FOUND THAT NR3 CYL NO COMPRESSION. CYL WAS REMOVED FROM ENGINE. FOUND THAT THERE WAS A HOLE BURNED UNDER THE EXHAUST VALVE SEAT AND THERE WAS A PART OF THE EXHAUST VALVE MISSING. RECORDS INDICATE THAT AT ENGINE OVERHAUL THE EXHAUST VALVES AND SEATS WERE REPLACED. AME WONDERS IF WHEN THEY CHANGED THE SEAT THAT THEY MAY HAVE CRACKED THE CYL ALLOWING THE EXHAUST GASES TO BURN THROUGH THE CYL UNDER THE SEAT. (TC NR 20080428002) 1L71 3O3 O 2A3 E286 5 CP7EA 20080522 NM 2008 5 22 CA080428005 120080421G324629685 BEARING BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R320 CR3204123F1 GL WHEEL ASSY FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/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. THE 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 AND THE AC RETURNED TO SERVICE. (TC NR 20080428005) 2H72 4T4 TRTA13NM E00062EN6 CP5NE 20081105 EU 2008 11 5 CA080507004 120080430G6420 FORK BOLKMS117 BK117B2 5626013EU LYC LTS101LTS101750B1 41560NE TAIL ROTOR BINDING W CR ABORTED TAKEOFF AUTOROTATION F FLT CONT AFFECTED APAPPROACH 1 CA 65 (CAN) ACFT WAS UNDERGOING A TEST FLIGHT FOR RADAR ALTIMETER TROUBLESHOOTING. 5 MINUTES INTO CRUISE FLIGHT, A SUDDEN VIBRATION WAS INDUCED INTO AIRFRAME AND ALL FLIGHT CONTROLS. PILOT IMMEDIATELY RETURNED TO BASE FOR AN UNSCHEDULED LANDING WITHOUT 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 INDICATED ABRASION MARKS ON THE INSIIDE WHERE THE DISLODGED BUSHING HAD COME INTO CONTACT. SUSPECT ACFT VIBRATION A RESULT1G72 3U3 UNCH13EU E5NE10 20081105 EU 2008 11 5 CA080508007 120080506G5610350A25904320 WINDSHIELD UROCOPEC130 EC130B4 8680989EU TMECA ARRIELARRIEL2B1 60056NE COCKPIT CRACKED W K NONE O OTHER ININSP/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 IS 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. 1G72 3U3 U H9EU E00054EN 20081105 WP 2008 11 5 CA080508020 120080428G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE INOPERATIVE W K NONE O OTHER ININSP/MAINT 1 CA 392 (CAN) ON START ACFT STARTER GEN DID NOT ENGAGE. 1G71 3O3 O H11NM 1E4 20081105 NM 2008 11 5 CA080510002 120080102G6220 BEARING ROBSIN ROBSINR22 R22BETAII 7640110NM M/R HEAD WORN W K NONE E VIBRATION/BUFFET ININSP/MAINT 1 CA 2169 (CAN) PILOT REPORTED A LATERAL VIBRATION HAD BEEN PROGRESSIVELY GETTING WORSE OVER THE PAST WEEK. UPON VISUAL INSP OF THE MAIN ROTOR HEAD THERE WAS A BLACK PASTE (SMOKING) AROUND ONE OF THE TEETER HINGE BEARINGS. AFTER REMOVING MAIN ROTOR HEAR 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) 1G71 3O H10WE 20081105 EU 2008 11 5 CA080513007 120080506G6320332A3210073P TRANSMISSION SNIAS AS332 AS332L 8680809EU TMECA MAKILAMAKILA1A 60040EU MAIN ROTOR MAKING METAL W A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 CA 2581 (CAN) TRANSMISSION CHIP LIGHT ILLUMINATION. FERROUS METAL CHIPS, WHISKERS AND FLAKES FOUND IN FILTER AND SUMP AND ON CHIP DETECTOR. 2G72 4U4 U H4EU E12NE 20081105 WP 2008 11 5 CA080513008 120080506G6730D2121 SERVO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE HYDRAULIC SYS LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1064 (CAN) DURING INSPECTION FOUND THE LT FWD SERVO LEAKING. (TC NR 20080513008) 1G71 3O3 O H11NM 1E4 20081105 WP 2008 11 5 CA080514007 120080508G6510 SHAFT ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA COOLING FAN DAMAGED W K NONE O OTHER ININSP/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) 1G71 3O3 O H11NM E295 20081105 SW 2008 11 5 CA080515002 120080515G6710 CYCLIC CONTROL BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA OBSTRUCTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFTER INSTALLATION OF THE VERTICAL REFERENCE SEAT KIT LISTED ABOVE, IT WAS DISCOVERED DURING FLIGHT CONTROL CLEARANCE CHECKS THAT THE SEAT IN VARIOUS PLACEMENTS OF IT`S RANGE OF TRAVEL INTERFERED WITH THE FULL MOVEMENT OF THE CYCLIC FLIGHT CONTROL. INCLUDED WITH THIS REPORT IS A DOCUMENT WITH SOME PRELIMIARY APPROXIMATE VALUES AND PICTURES OF THE CLEARANCE AND INTERFERANCE THAT EXISTS. INSTALLATION OF THE SEAT KIT AS IAW AAL-292-035-001, UNDER STC APPROVAL NR SH 06-31 1G71 4U4 U H4SW E22EA 20081105 SW 2008 11 5 CA080516003 120080513G6520212040004103 GEARBOX BELL 412 412EP 1182205SW PWA PT6T PT6T3 52045EA TAIL ROTOR LEAKING W O OTHER K FLUID LOSS LDLANDING 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 THE HOURMETER),THE OIL LEVEL WAS CHECKED IN THE 90 DEGREE AND FOUND TO BE EMPTY, WITH OIL SPLASHED ALL OVER THE GEARBOX. THE 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. 1G72 4U4 U H4SW E22EA 20081105 EU 2008 11 5 CA080516013 120080515G6220350A37116200 STOP SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE MAIN ROTOR BROKEN W K NONE O OTHER ININSP/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 COULD BE FATAL SINCE ONLY (2) OUT OF (3) WAS KEEPING THE RING CENTERED. (TC NR 20080516013) 1G71 3U3 U H9EU E19EU 20081105 SW 2008 11 5 CA080521002 120080513G6410 BEARING BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL T/R BLADE CRACKED W K NONE O OTHER ININSP/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. CRACK 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 SEEMS TO HAVE RESURFACED. 1G71 3U3 U H2SW E1GL 20081105 SW 2008 11 5 CA080521007 120080516G6310206040270 CLUTCH BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL FREEWHEEL UNIT MALFUNCTIONED W K NONE O OTHER ININSP/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. 1G71 3U3 U H2SW E4CE 20081105 SW 2008 11 5 CA080523002 120080522G6220AN17420 BOLT BELL 205 205A1 1181414SW LYC T53 T5317BLYC 41616NE STAB BAR DAMPER BROKEN W K NONE O OTHER ININSP/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 CONTRIBUTING 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 POSSIBLE INTERNAL FAILURE/SEIZURE WHICH MIGHT HAVE CONTRIBUTED TO SUBJECT BOLT FAILURE. STAB BAR DAMPER TUBE RIGGING FOR 1G71 4U4 U H1SW E17EA 20081105 2008 11 5 CA080523005 420080516G2311TK760HG TRANSCEIVER SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE UHF SYSTEM INOPERATIVE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RADIO WOULD NOT TRANSMIT, REMOVED AND INSTALLED SERVICABLE RADIO. 1G71 3U3 UNCH9EU E19EU 20081105 WP 2008 11 5 CA080523006 120080518G2432RG2415 BATTERY ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MASTER LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 73 (CAN) DURING DI FOUND THE BATTERY LEAKING, REPLACED WITH A NEW ONE. 1G71 3O3 O H11NM 1E4 20081105 GL 2008 11 5 CA080527002 220080521G723023057142 STATOR ALLSN BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL 6TH STAGE MISSING W K NONE O OTHER ININSP/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, WITH 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 THIS 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) 1G71 3U3 U H2SW E4CE 20081105 SW 2008 11 5 CA080528003 120080523G5302206032400027S RING BELL BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL TAIL BOOM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK FOUND ON TAIL BOOM RING DURING ROUTINE INSPECTION. 1G71 3U3 U H2SW E1GL 20081105 SW 2008 11 5 CA080528004 120080523G5300206031337003 FITTING BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK DETECTED ON FITTING DURING ROUTINE INSPECTION. 1G71 3U3 U H2SW E1GL 20081105 SW 2008 11 5 CA080528007 120080525G5100427065125111 SHROUD BELL 427 427 1182207SW PWC PW207 PW207D NE FUSELAGE CHAFED W K NONE O OTHER ININSP/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. 1G71 3U3 U R00001RCE42NE 20081105 2008 11 5 CA080528010 420080417G830023068295 GEARSHAFT ALLSN SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL GEARBOX CRACKED W K NONE O OTHER ININSP/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 CG119988. (TC NR 20080528010) 1G72 3U3 U H1NE E1GL 20081105 WP 2008 11 5 CA080528014 120080522G2822D8187B PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYSTEM UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA 609 (CAN) AUX FUEL PUMP UNSERVICEABLE, CHANGED OUT FUEL PUMP WITH A SERVICABLE ONE. (TC NR 20080528014) 1G71 3O3 O H11NM 1E4 20081105 NE 2008 11 5 CA080530001 120080529G6730S156520421041 SERVO SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE MAIN ROTOR LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 4694 1156 (CAN) DURING A POST-FLIGHT INSP, MECHANIC FOUND MOVEMENT BETWEEN THE FORK AND PISTON. THE PRIMARY SERVO WAS REPLACED. AFTER DISASSEMBLY AT REPAIR STATION, IT WAS DISCOVERED THAT THE MOVEMENT WAS CAUSED BY THE BREAKDOWN OF A LAMINATED REPAIR SHIM INSTALLED BETWEEN THE FORK AND PISTON ROD, CAUSING THE LOSS OF TORQUE BETWEEN THE SERVO FORK AND PISTON ROD. SUBMITTING THIS SDR IAW OUR REPAIR STATION CANADIAN SUPPLEMENT. AN ASB 64B29-8 WAS RELEASED BY THE MFG, ON MAY 24, 2008 (TC NR 20080530001) 2G72 4U4 U H4EA E15EA 20081106 EU 2008 11 6 CA080530003 120080528G6730SC5083 SERVO SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE FLT CONTROLS WORN W A UNSCHED LANDING F FLT CONT AFFECTED HOHOVERING 1 CA 2895 2895 (CAN) STIFF FLIGHT CONTROLS IN ALL RANGE OF TRAVEL, IN HOVER, CRUISE, LANDING. 1G71 3U3 U H9EU E19EU 20081229 NE 2008 12 29 CA080601001 220080521G720070BM035420 MODULE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE ENGINE NOISY W E ENGINE SHUTDOWN O OTHER TXTAXI/GRND HDL 1 CA 2955 2955 (CAN) SQEALING NOISE COMING FROM ENGINE. SHUTDOWN AFTER FLIGHT, SUSPECT TURBINE BLADE RUB. MODULE 2 AND MODULE 3 REMOVED AND SENT TO MFG. 1G71 3U3 U H9EU E19EU 20081106 2008 11 6 CA080602005 120080516G78103031988 EXHAUST DUCT PWA PT6 PT6A27 52043EA ENGINE CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA 135771220 (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 220080602G7314 PUMP HUGHES369 369E 4470707WP ALLSN 250C 250C20R2 GL FUEL MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) REINFORCED PAPER WIPERS LEFT IN THE FUEL TANK AFTER WORK CARRIED OUT. DURING A 300 HOUR INSP, THERE WAS SIGNIFICANT FUZZ LIKE DEBRIS FOUND IN THE ENGINE DRIVEN FUEL PUMP FILTER THAT WAS A BLUISH COLOR. WHEN PICKING UP THE HELICOPTER 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 VERIFIED 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 DOIN1G71 3U3 U H3WE E4CE 20081106 2008 11 6 CA080603006 120080528G574400100018273 HINGE BRACKET RT WING WORN W I CABIN DEPRESSURIZATION O OTHER ININSP/MAINT 1 CA 1191 (CAN) REAR SPAR, RT LOWER WING AILERON, HINGE BRACKET INNER OUTER SHELL BECOMING LOOSE IN BEARING (REPLACED WITH NEW) (TC NR 20080603006) 20081106 CE 2008 11 6 CA080604005 120080530G29104529101067001 LINE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP HYDRAULIC SYS CRACKED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 2614 (CAN) DURING CRUISE, THE ACFT EXPERIENCED A HYDRAULIC FAILURE. THE CREW DECLARED AN EMERGENCY, LANDING WITHOUT FLAPS. INVESTIGATION REVEALED A KINK IN A HYDRAULIC SUPPLY LINE IN THE PYLON AREA OF THE LT ENGINE. A CRACK HAD FORMED IN THE KINKED AREA AND THE FLUID WAS RELEASED FROM THE PRESSURIZED LINE. 2L72 4F4 FRTT00008WIE6WE 20081106 SW 2008 11 6 CA080604011 120080528G5340 ATTACH FITTING BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE LIFT LINK CRACKED W K NONE O OTHER ININSP/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 BEAM IS UNKNOWN AT THIS TIME. CRACK WAS FOUND ON THE AFT EAR OF LUG RT SIDE. 1G71 4U4 U H1SW E17EA 20081106 NE 2008 11 6 CA080604013 220080603G7200 ENGINE CNDAIRCL604 CL604 1900301EA GE CF34 CF343B 30069NE FLAMED OUT W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) ACFT TOOKOFF AND ENGINE FLAMED OUT AT 41000 FT, ENGINE RESTARTED AT 25 000 FT AND LANDED SAFELY. ENG MFG WAS CALLED AND OPERATOR INSTRUCTED TO DO POWER ASSURANCE. AT THE TIME ARCRAFT WAS AT IMC SOME 17NM OFF TRACK DIVERTING AROUND SOME MODERATE INTENSITY RADAR RETURNS. RADAR PICTURE GAVE NO CAUSE FOR CONCERN WITH THE PATH WHICH WAS CHOSEN AND INDICATED 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 AFTER2L72 4F4 FRTA21EA E15NE 20081106 EA 2008 11 6 CA080604016 120080602G5280 ROD CNDAIRCL604 CL604 1900301EA GE CF34 CF343B 30069NE MLG DOOR OUT OF RIG W A UNSCHED LANDING ED VIBRATION/BUFFET INFLIGHT SEPARATION CLCLIMB 1 CA (CAN) UPON GEAR RETRACTION DURING TAKEOFF A RHYTHMIC THUMPING SOUND WAS HEARD COMING FROM THE NOSE AREA. A RETURN TO FIELD WAS REQUESTED AND AN EMERGENCY DECLARED. NO EICAS MESSAGE WAS POSTED AND NOISE STOPPED WHEN GEAR SELECTED DOWN. LANDING DONE WITHOUT ANY ISSUE. ACFT WAS PUT IN QUARANTINE FOR TEST ON GROUND AND FINDING OF THE ROOT CAUSE. AFTER TROUBLESHOOTING NOISE SUSPECTED TO BE COMING THE NOSE LANDING GEAR DOOR FUNCTIONAL TEST PROCEDURE FTP S604-323001 R RECHECKED FOR -DOOR MECHANISM RIGGING PARA 5.1.2 -GEAR MANUAL RELEASE PARA5.6.4 -LANDING GEAR FUNCTIONAL CHECK PARA 5.8 MINOR ADJUSTMENT DONE TO R/H NOSE DOOR ACTUATING ROD SYS WAS CHECKED AND FOUND OK AND ACFT WAS RELEASED FOR FLIGHT TEST. 2L72 4F4 FRTA21EA E15NE 20081106 SW 2008 11 6 CA080606002 120080603G6410212010750113 BLADE BELL 205 205B SW LYC T53 T5313B 41549NE TAIL ROTOR CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA 573 (CAN) PILOT REPORTED PEDAL VIBRATIONS THROUGHOUT THE DAYS FLYING. AD-2008-10-03 CLEAN AND INSPECT T/R BLADES WAS SCHEDULED 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 APROX .333 OF BLADE LENGTH OUT FROM THE ROOT. THE DEFECT IS APROX 2 INCHES IN LENGTH. T/R BLADE REPLACED WITH SERVICEABLE UNIT AND SENT FOR FURTHER INSP. THERE HAVE BEEN NO DAMAGE OR ABNORMAL INCIDENTS NOTED TO HAVE AFFECTED THE BLADE, AND THERE ARE NO INDICATIONS OF ANY IMPACT OR OTHER DAMAGE IN THE SUSPECT AREA. WILL SEND ADDITIONAL INFO AFTER INSPECT THE BLA1G71 4U4 U H1SW E17EA 20081106 SW 2008 11 6 CA080606004 120080604G2740C200G3R SWITCH FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE STAB TRIM INTERMITTENT W A UNSCHED LANDING F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) LT SAS FAILED AND ALL STAB TRIM FUNCTIONS FAILED. MASTER DISCONNECT SWITCH REPLACED AND TEST FLIGHT CARRIED OUT SERVICIBLE. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081106 SW 2008 11 6 CA080606005 120080516G3246LM29749 BEARING FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33110UG 01514WP MCAULY4HFR344HFR34C652 NE LH NOSE WHEEL LACK OF LUBE W D RETURN TO BLOCK W INADEQUATE Q C TXTAXI/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. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081229 NE 2008 12 29 CA080606008 220080530G7321350A57147620 CONTROL LEVER SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE FCU INCORRECT W K NONE O OTHER ININSP/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 CONFIRMATION WITH MFG THIS WAS CONFIMED. AS THIS ACFT CAME TO US, ON B2 S/N 1685 WE ASSUMED THAT THE INSTALLATION WAS CORRECT. THE RIGGIN WAS WAY OUT AND WE COULD NOT REACH THE REQUIRED RPM. LEVER WAS REPLACED, RIGING WAS CARRIED OUT AND THE ACFT WAS RETURNED TO SERVICE. 1G71 3U3 U H9EU E19EU 20081106 EU 2008 11 6 CA080608003 120080603G2752 NUT TALLEY 1251T100 BNORM BN2 BN2A26 1520226EU LYC O540 O540E4C5 41532EA HARTZLHCC2Y HCC2YK2 GL FLAP ACTUATOR STRIPPED W C ABORTED TAKEOFF O OTHER CLCLIMB 1 CA (CAN) DURING A TRAINING FLIGHT, ON OVERSHOOT FROM A ABORTED LANDING, FLAPS RETRACTED UN-COMMANDED. PILOT REDUCED POWER AND WAS ABLE TO LAND STRAIGHT AHEAD ON REMAINING RUNWAY. INSPECTION FOUND THE FLAP ACTUATOR STRIPED. ACTUATOR WAS REMOVED AND SENT FOR OVERHAUL. OVERHAUL FACILITY REPORT THAT THE STRIPPED BRASS NUT WAS MADE OF A SOFTER THAN STANDARD MATERIAL. THERE WAS IN EVIDENCE IN THE AVAILABLE LOGS OF THE TIME IN SERVICE SINCE NEW OR OVERHAULED. OVERHAULED ACTUATOR WAS RE-INSTALLED IN ACFT. 1H72 3O3 O A17EU E295 5 CP920 20081106 SW 2008 11 6 CA080609004 120080603G2742DL5040M6 ACTUATOR SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE PITCH TRIM UNRESPONSIVE W A UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 CA 6486 (CAN) SHORTLY AFTER DEPARTING, AND ACCELERATING THROUGH 200KTS, THE PITCH TRIM STOPPED RESPONDING. TRIM SONALERT WAS SOUNDING 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 POWER TO MAKE CONTROLLING THE A/C EASIER AND USED THEIR KNEES TO KEEP THE ACFT LEVEL AND CONTINUED. AS THE ACFT SLOWED FOR ARRIVAL, THROUGH ABOUT 180 KTS, THE TRIM BEGAN RESPONDING AGAIN. THE ACFT LANDED NORMALLY AND MAINT WAS INFORMED. MAINT REPLACED THE PITCH TRIM ACTUATOR AND THE PROBLEM HAS NOT REOCCURRED. THE ACTUATOR WILL BE SENT FOR REPAIR/OVERHAUL AN2L72 4T4 TRTA8SW E4WE 5 CP10NE 20081105 SW 2008 11 5 CA080609005 120080605G750027621009 TUBE SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP BLEED AIR LEAKING W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 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 SHIELD AND UPON CUTTING AWAY THE SHIELD TO INSPECT THE BELLOWS IT WAS DISCOVERED THAT THE LEAK WAS ORIGINATING FROM THE SEAM 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. 2L72 4T4 TRTA8SW E4WE 20081106 SW 2008 11 6 CA080609006 120080531G21202784142007 DUCT SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE BLEED AIR CRACKED W K NONE O OTHER ININSP/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 MACHINE HAD CRACKED 2 INCHES, ABOUT ONE THIRD THE CIRCUMFERENCE OF THE TUBE. 2L72 4T4 TRTA8SW E4WE 5 CP10NE 20081106 EA 2008 11 6 CA080609007 120080606G2751601R590141 DETECTOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS FALSE ACTIVATIONW O OTHER N FALSE WARNING APAPPROACH 1 CA 9197 9197 (CAN) ON APPROACH CREW RECEIVED `FLAPS DEGRADED` MESSAGE ON EICAS, WHEN FLAPS SELECTED TO 45DEG, FLAPS CONTINUED TO SELECTED 45DEG POSITION. AFTER LANDING WHEN SELECTING FLAPS UP, CREW RECEIVED `FLAP FAIL’ MESSAGE AND FLAPS REMAINED AT 43DEG. MAINT OBTAINED FAULT CODES INDICATING SKEW DETECTION ISSUE. FLAPS RESET AND ACFT FERRIED TO MAINT BASE. MAINT INSP FOUND 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. 2L72 4F4 FRTA21EA E15NE 20081106 EU 2008 11 6 CA080609009 120080604G575313760B462 ATTACH FITTING BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP ROTOL R333 R333482F12 GL FLAP SYSTEM CRACKED W K NONE O OTHER ININSP/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. 2L72 4T4 TRTBA15CAA E4WE 6 CP61GL 20081106 SW 2008 11 6 CA080610001 120080609G6230206010467105 LEVER BELL 206 206B 1181511SW SWASHPLATE MISMARKED W K NONE W INADEQUATE Q C ININSP/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. 1G71 3U H2SW 20081106 2008 11 6 CA080610003 120080609G575125W181001501 SKIN LT AILERON DELAMINATED W O OTHER O OTHER DEDESCENT 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 POST 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 120080524G2997M2750012MW3U00 WIRE CNDAIRCL600 CL600* 1900302EA HYD SYSTEM DAMAGED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) WHILE RUNNING ACFT HYDRAULIC SYS IN HANGAR FOR CONTROL SYS FUNCTIONAL CHECKS, AN AUDIBLE BANG WAS HEARD FROM THE BACK 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. WIRES 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 TRIPLE TWISTED SOOT ON THE WIRE INSULATION WIRES CABLE P/N M27500-12MW3U00 IS KAPTON WIRE. 2L72 4F RTA21EA 20081106 SW 2008 11 6 CA080611002 120080318G6220C807382 BEARING RACE BELL 206 206L4 1182110SW ALLSN 250C 250C30P 03013GL PUSH-PULL FRACTURED W K NONE O OTHER ININSP/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. 1G71 3U3 UNCH2SW E1GL 20081106 SW 2008 11 6 CA080611003 120080606G2820412061634105 VENT LINE BELL 412 412 1182202SW FUEL SYSTEM CHAFED W K NONE O OTHER ININSP/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 PANEL. CUT MADE WITH SHARP EDGE OF BOTTOM FOOT DOOR. 1G72 4U H4SW 20081106 GL 2008 11 6 CA080611005 120080609G5551BSFS159160 ATTACH BRACKET DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN1 52008NE HORIZONTAL STAB WORN W K NONE O OTHER ININSP/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 THAT THE FUSELAGE FITTING WAS WEARING INTO THE HORIZONTAL STABILIZER ATTACH FITTING (PN BSFS-159/160). 1H71 3R3 RRCA806 5E1 20081230 NE 2008 12 30 CA080611006 220080525G72000292005220 ENGINE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE MAKING METAL W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA 8428 (CAN) WHILE DOING AIRBORNE SURVEY WORK (BIRD TOWING), ENGINE CHIP LIGHT ILLUMINATED. HELICOPTER DESCENDED TO VALLEY BOTTOM 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 AMOUNT OF METAL CHIPS ON THE ENGINE CHIP PLUGS. ENGINE REMOVED AND SENT TO MFG FOR FURTHER INVESTIGATION. 1G71 3U3 U H9EU E19EU 20081106 WP 2008 11 6 CA080611007 220080610G720031080981 BEARING FRCHLDSA227 SA227CC 3377522SW GARRTTTPE331TPE33110 01514WP MCAULY4HFR344HFR34C652 NE ENGINE SPALLED W K NONE O OTHER ININSP/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 SOUND THAT WAS NOTICED BY LINE MAINT. ANOTHER REAR TURBINE BEARING FAILED ON ENGINE P44436C INSTALLED ON AC. THE BEARING ONLY 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 IN REGARDS OT THE SITUATION POINTING TOWARDS BAD BATCH. MFG IS RESEARCHING THE PROBLEM. ALL CONTACTED TO ASSIST IN PROBL2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081106 SW 2008 11 6 CA080611009 120080605G324631418A BEARING SEAL FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE NLG WHEEL DISPLACED W K NONE O OTHER ININSP/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 DISPLACED 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 THAT THE BEARING ROLLERS WERE VISIBLE. NOSE WHEEL ASSY REPLACED AND ACFT RETURNED TO SERVICE. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081106 SW 2008 11 6 CA080611010 120080610G3246LM299710 BEARING RACE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE3311 01514WP MCAULY4HFR344HFR34C652 NE NOSE WHEEL DAMAGED W K NONE O OTHER ININSP/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. 2L72 4T3 TRTA8SW E3WE 6 C3PNE 20081106 EA 2008 11 6 CA080612001 120080611G5753600143023 VANE BOMBDR CNDAIRCL600 CL600* 1900302EA GE CF34 CF348E5A1 30062NE TE FLAP CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A DAILY INSPECTION, THE LT INBD FLAP VANE WAS FOUND CRACKED ON THE UPPER SURFACE. THE CRACK IS APPROXIMATELY 2 INCHES LONG. FLAP TO BE REMOVED AND SENT OUT FOR FLAP VANE REPLACEMENT. LOANER FLAP TO BE INSTALLED. 2L72 4F4 FRTA21EA E00063EN 20081113 NE 2008 11 13 CA080612002 220080605G7200 ENGINE PWC PW615 PW615FA 52282NE MALFUNCTIONED W E ENGINE SHUTDOWN J WARNING INDICATION LDLANDING 1 CA (CAN) DURING LANDING TOUCHDOWN AND BRAKING, BOTH ENGINES REPORTEDLY INCREASED UNCOMMANDED TO FULL POWER. CREW ABORTED LANDING AND PERFORMED A GO-AROUND. DURING BASE LEG, TO CONTAIN AIRSPEED CREW SHUT DOWN RT ENGINE AND AT THIS TIME THE LT ENGINE 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 QUADRANT. THE CAS MSGS AND EVENTS REPORTED BY THE FLIGHT CREW WERE DUPLICATED DURING SIMULATION TESTING. THE NTSB HAS RETAINED 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 120080612G2820C6PF1034105 LINE DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA FUEL SYSTEM MISMANUFACTURED W K NONE W INADEQUATE Q C ININSP/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. 1H72 3T4 TRTA9EA E4EA 20081106 EA 2008 11 6 CA080612004 120080612G2820C6PF103479 LINE DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA FUEL SYS MISMANUFACTURED W K NONE W INADEQUATE Q C ININSP/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 INSTALLER FOUND THE TUBE ASSY TO BE ONE INCH TOO LONG FOR THE LOCATION. 1H72 3T4 TRTA9EA E4EA 20081106 NE 2008 11 6 CA080612005 220080612G7414 BEARING ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO LOOSE W K NONE W INADEQUATE Q C ININSP/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 NEW MAG. MFG REQUIRES 0.0005 TO 0.0015 INCH END PLAY AT ASSY. THE MAG BEARINGS WERE INSPECTED FOR DAMAGE AND NONE WAS FOUND. THE BEARINGS WERE PROPERLY SHIMMED DURING THE 500 HOUR INSP AND THE MAG WAS RETURNED TO SERVICE. 1G71 3O3 O H11NM 1E4 20081106 NE 2008 11 6 CA080612006 220080612G7414 BEARING BENDIX ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO LOOSE W K NONE W INADEQUATE Q C ININSP/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 NONE WAS FOUND. THE BEARINGS WERE PROPERLY SHIMMED DURING THE 500 HOUR INSPECTION AND THE MAG WAS RETURNED TO SERVICE. 1G71 3O3 O H11NM 1E4 20081106 2008 11 6 CA080612007 220080612G7414 BEARING MAGNETO LOOSE W K NONE W INADEQUATE Q C ININSP/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 120080605G3250AN310A BOLT CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA COCKPIT MISINSTALLED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LEFT RUDDER PEDAL SYSTEM INSPECTED TO VERIFY CLEARANCE BETWEEN THE BOLT AND NUT HOLDING THE BRAKE BELLCRANK LOCATED BESIDE THE RIGHT RUDDER PEDAL ARM BAR ON THE PILOT SIDE AND THE NOSE GEAR STEERING ARM TUBE ATTACHMENT. BOLT WASHER AND NUT REPOSITIONED TO ALLOW CLEARANCE. MINOR INTERFERENCE NOTED PRIOR TO REPOSITIONING. INSPECTION CARRIED OUT AFTER FINDINGS AS DESCRIBED IN SDR 20080613002 (TC# 20080613004) 1H71 3O3 ONT3A12 E274 20081106 CE 2008 11 6 CA080613005 120080604G2720AN310A BOLT CESSNA CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160CTM GL RUDDER PEDAL MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) LT RUDDER PEDAL SYS INSPECTED TO VERIFY CLEARANCE BETWEEN THE BOLT AND NUT HOLDING THE BRAKE BELLCRANK LOCATED BESIDE THE RT RUDDER PEDAL ARM BAR ON THE PILOT SIDE AND THE NOSE GEAR STEERING ARM TUBE ATTACHMENT. BOLT WASHER AND NUT REPOSITIONED TO ALLOW CLEARANCE. MINOR INTERFERENCE NOTED PRIOR TO REPOSITIONING. INSP CARRIED OUT AFTER FINDINGS AS DESCRIBED IN SDR 20080613002. 1H71 3O3 ONT3A12 E274 5 NP910 20081106 SW 2008 11 6 CA080613007 120080605G30002719156003 TRANSDUCER FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP DE ICE SYSTEM DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 6918 (CAN) PILOT REPORTED DEICE PRESSURE GAUGE UNSERVICEABLE. DURING TROUBLESHOOTING MAINT FOUND THE DEICE PRESSURE TRANSDUCER CONTAMINATED WITH WATER. 2L72 4T4 TRTA18SW E4WE 20081106 WP 2008 11 6 CA080613009 120080603G2435BC3151004 STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE INTERMITTENT W O OTHER O OTHER NRNOT REPORTED 1 CA 824 (CAN) STARTER INTERMITTENT. 1G71 3O3 O H11NM 1E4 20081106 CE 2008 11 6 CA080613010 120080611G6120A3495 LOCK PLATE MTSBSIMU2 MU2B60 5780460CE GARRTTTPE331TPE33110 01514WP HARTZLHCB4T HCB4TN5 GL PROPELLER WORN W K NONE O OTHER ININSP/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 COULD JAM THE PIN. THIS COULD PREVENT IN FIGHT ENGINE START. 1H72 3T4 TRTA10SW E4WE 6 CP40EA 20081106 SW 2008 11 6 CA080614001 120080612G2910 LINE BELL 205 205A1 1181414SW LYC T53 T5317BLYC 41616NE HYD SYSTEM LEAKING W A UNSCHED LANDING KF FLUID LOSS FLT CONT AFFECTED HOHOVERING 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 HYDRAULIC LINE HAD CHAFED THROUGH CREATING A HOLE. MORE DETAILS ARE COMING. 1G71 4U4 U H1SW E17EA 20081106 NE 2008 11 6 CA080616001 220080611G7250 TURBINE PWA PW120 PW123 NE ENGINE OUT OF BALANCE W O OTHER E VIBRATION/BUFFET TXTAXI/GRND HDL 1 CA 1866710033 (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 120080611G28205282412189 LINE PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE FUEL SYS CORRODED W O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 CA (CAN) MX FOUND FUEL LEAKING FROM CENTER BELLY PANEL AND DURING INVESTIGATION FOUND A CORRODED FUEL LINE. 1L71 3T4 TRTA78EU E26NE 20081106 CE 2008 11 6 CA080616003 120080611G261224418922 FIRE LOOP CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL NACELLE LOOSE W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA 1398713987 (CAN) ENGINE FIRE WARNING INDICATION CAME ON IN FLIGHT. THE ENGINE WAS REPLACED THE PREVIOUS DAY AND THE FIRE WIRE MAY HAVE BEEN DISTURBED AT THAT TIME. THE PILOT LANDED AND THE FIRE WIRE WAS REPLACED AND CHECKED SERVICEABLE. 1H71 3T3 T A37CE E4EA 5 CP60GL 20081106 EA 2008 11 6 CA080616004 120080615G2750860D10018 FCU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE FLAP SYSTEM UNSERVICEABLE W A UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION CLCLIMB 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 CHECK 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. 2L72 4F4 FRTA21EA E15NE 20081106 EU 2008 11 6 CA080616005 120080611G2731Z4244170000 CONTROL CABLE ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA ELEVATOR TAB FRAYED W K NONE O OTHER ININSP/MAINT 1 CA 3800 (CAN) AFT ELEVATOR TRIM CABLE WAS DISCOVERED FRAYED DURING REGULARLY SCHEDULED MAINT. IT WAS SURMISED THAT FURTHER OPERATION OF THE TRIM SYS WOULD HAVE LED TO SYS FAILURE BEFORE THE NEXT SCHEDULED INSPECTION. 1L71 3O3 O0 A76EU 1E10 20081106 CE 2008 11 6 CA080617001 120080610G5720 SUPPORT CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE SPEED BRAKES DAMAGED W K NONE O OTHER ININSP/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 UPPER OTBD AILERON CABLE PASSES THROUGH ON BOTH THE LT AND RT WING. THE AILERON CABLES WERE WORN AND HAD WORN INTO THE AFT SIDE OF THE HOLE IN THE TRUNNION SUPPORTS. REPAIR S-550-0699/04RD WAS ISSUED TO BLEND THE TRUNNION SUPPORT AND THE AILERON CABLES WERE REPLACED. 1L72 4F4 F A22CE E1NE 20081106 CE 2008 11 6 CA080617002 120080418G534305430161 FITTING CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA NLG BROKEN W O OTHER O OTHER NRNOT 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 FOUND 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. 1H71 3O3 ONT3A12 1E10 20081106 NE 2008 11 6 CA080617003 220080607G8530 EXHAUST VALVE CNDAIRCL215 CL2151A10 1900320EA PWA R2800 R2800CA3 52026NE HAMSTD43E 43E60 NE NR 9 CYLINDER FAILED W E ENGINE SHUTDOWN O OTHER CRCRUISE 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 ACFT WAS RETURNED TO SERVICE. 2H72 4R4 RRTA14EA 5E8 6 CP871 20081106 EU 2008 11 6 CA080617004 120080616G3040 SHAFT AIRBUS310 A310300 3930305EU GE CF6 CF680C2* GL WINDSHIELD WIPERSHEARED W O OTHER O OTHER LDLANDING 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 WAS FOUND IN TAXIWAY. CONVERTER ASSY REPLACED. 2L72 4F4 FRTA35EU E23EA 20081106 NM 2008 11 6 CA080618001 120080615G3233AS11510K0330 HOSE BOEING757 75728A 1384976NM RROYCERB211 RB211535E43754555NE MLG ACTUATOR LEAKING W O OTHER K FLUID LOSS NRNOT REPORTED 1 CA (CAN) LT TRUCK TILT ACTUATOR RETURN LINE FOUND LEAKING. 2L72 4F4 FRTA2NM E12EU 20081230 SW 2008 12 30 CA080618002 120080616G2510AAL292030001 SEAT FRAME BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA COCKPIT SEAT INTERFERENCE W O OTHER O OTHER NRNOT 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 INSTALLATION. 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. 1G71 4U4 U H4SW E22EA 20081106 NE 2008 11 6 CA080618003 220080602G7261 SEAL PWA PT6 PT6A60 52043NE NR 1 BEARING LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) DURING ENG COMPRESSOR RECOVERY WASH, ENGINE OIL LOSS FROM NR 1 BEARING SEAL. MULTIPLE ENGINE SPOOLS ARE REQUIRED TO 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 SUCSESSFULLY 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 DURING 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 120080613G5210BACS12ER06K6 SCREW BOEING737 737* NM GE CFM56 CFM567B24 NE PAX DOOR ARM MISSING W K NONE O OTHER ININSP/MAINT 1 CA 1713417134 (CAN) L1 MAIN CABIN ENTRANCE DOOR WAS FOUND TO HAVE RESTRICTED OPERATION FOR OPENING AND CLOSING UPON ARRIVAL AT THE GATE. 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 COMPLETED WITHIN 90 DAYS OF THE CAMPAIGN DETAILS BEING FINALIZED. 2L72 4F4 FRTA16WE E00055EN 20081106 NE 2008 11 6 CA080618005 220080616G72006018T30P14 BLADE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE ENGINE FAN BENT W O OTHER C F.O.D. NRNOT 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 OF SERVICE FOR A FAN BLADE REPLACEMENT. THIS WAS REPORTED BY THE CREW PICKING UP THE ACFT FOR THE NEXT FLIGHT, AFTER THEIR 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 REPLACEMENT IN PROGRESS. 2L72 4F4 FRTA21EA E15NE 20081105 EA 2008 11 5 CA080618006 220080508G8530LW16740 VALVE LYC LYC O540 TIO540A2C 41532EA VALVE STEM ELONGATED W K NONE O OTHER ININSP/MAINT 1 CA 2700 (CAN) VALVE STREACHED TO 6 THOU AND MANUFACTURES LIMITATION IS 2 THOU. CONCERN IS VALVE IS SODIUM FILLED AND WILL DISINTIGRATE IF THE STREACH IS BEYOND MANUFACTURES RECOMMENDATIONS. THE MAIN CONCERN IS THIS ENGINE IS ON CONDITION AND THE CYLINDERS 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 220080602G8530LW16703 CYLINDER LYC O235 O235L2C 41505EA ENGINE CRACKED W O OTHER E VIBRATION/BUFFET NRNOT 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 OF ANY CRACKS. THIS ENGINE HAD BEEN OVERHAULED 225 HOURS PREVIOUSLY AND THE CYLINDERS WERE OVERHAULED AS WELL. THE RECORDS SHOWED THAT THE CYLINDERS WERE OVERHAULED AS PER MANUFACTURERS SPECIFICATIONS. WE WILL CONTINUE TO MONITOR THE OTHER CYLINDERS AND WILL REPORT ANY FUTURE ISSUES REGARDING THESE CYLINDERS. 3 O E223 20081105 EA 2008 11 5 CA080618008 220080604G7314A10014044 PUMP PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA FUEL SYSTEM INOPERATIVE W K NONE L NO TEST ININSP/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. 1L72 3O3 O A20SO E14EA 20081106 SO 2008 11 6 CA080618009 120080604G8120 BOLT KELLY PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL TURBOCHARGER MISSING W K NONE O OTHER ININSP/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 TURBO 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. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081106 EA 2008 11 6 CA080618010 120080602G5610NP13932212 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C5 30050NE COCKPIT FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RT COCKPIT SIDE WINDOW SHATTERED WHILE SITTING AT THE GATE. REMOVED AND REPLACED THE RT COCKPIT SIDE WINDOW. 2L72 4F4 FRTA21EA E00063EN 20081106 NM 2008 11 6 CA080619001 120080618G3220 BUSHING EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE NLG MIGRATED W K NONE O OTHER ININSP/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). 2L72 4F4 FRTA57NM E00070EN 20081106 2008 11 6 CA080619002 420080617G2565101651303 SLIDE LOOSE W K NONE O OTHER ININSP/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 LWR INFLATION TUBES. IT APPEARS THAT THE SLIDE UNITS, AS THEY AGE BEYOND 20 YEARS FROM DATE OF MFG, HAVE EXPONENTIALLY INCREASING 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 120080618G5343AN35A BOLT CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE TRUNNION DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CARRIED OUT VISUAL INSPECTION AS PER CAMPAIGN FOUND 4 BOLTS INSTALLED AND WASHERS AND NUTS. REMOVED HARDWARE INSTALLED 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. 1L72 4F4 F A22CE E1NE 20081106 2008 11 6 CA080619004 420080418G6122F624L GOVERNOR PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2A GL PROPELLER MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 6 (CAN) AFTER INSTALLATION OF THE OVERHAULED GOVERNOR, THE TEST FLIGHT WAS CARRIED OUT AND THE ENGINE WAS OVER SPED. THE GOVERNOR WAS SENT BACK TO THE REPAIR FACILITY, THE FACILITY REPORTS NOTHING ABNORMAL. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081106 2008 11 6 CA080619005 420080619G8300310625801 BEVEL GEAR PWA 120 PW120A NE ASSY GEARBOX MISMANUFACTURED W O OTHER W INADEQUATE Q C NRNOT 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 120080323G81204091709001 TURBOCHARGER PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2A GL ENGINE FAILED W A UNSCHED LANDING ERJVIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA 1 (CAN) AN OVERHAULED ENGINE COMPLETE WITH NEW TURBOCHARGER WAS INSTALLED. AFTER THE FIRST HOUR OF THE FLIGHT THE TURBOCHARGER COMPLETELY FAILED. MAINT INSTALLED A NEW TURBOCHARGER AND ACFT RETURNED TO SERVICE. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081106 CE 2008 11 6 CA080619007 120080617G575350160018 FLAP TRACK BEECH 100 A100A CE PWA PT6 PT6A28 EA MCAULY4HFR344HFR34C762 NE TE FLAPS CRACKED W K NONE O OTHER ININSP/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. 1L72 3T4 T A14CE E4EA 6 C3PNE 20081106 EU 2008 11 6 CA080619008 120080506G2822P94B12203C PUMP SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE FUEL BOOST INOPERATIVE W O OTHER J WARNING INDICATION CRCRUISE 1 CA 221 (CAN) BOOST PUMP FAILED IN FLIGHT, MOTOR STILL TURNING BUT NOT CREATING PRESSURE. SUSPECT SHEARED SHAFT OR DRIVE. 1G71 3U3 UNCH9EU E19EU 20081106 WP 2008 11 6 CA080620002 120080615G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA 139 (CAN) STARTER WOULD NOT TURN OVER THE ENGINE, TROUBLESHOOTING REVEALED THE STARTER WOULD NOT ROTATE THE STARTER GEAR. 1G71 3O3 O H11NM 1E4 20081106 GL 2008 11 6 CA080620004 120080618G5541 SPAR DHAV DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FRONT SPAR WAS FOUND CRACKED AFTER THE RUDDER WAS REMOVED FOR REPLACEMENT OF UPPER HINGE BEARING. FRETTING WAS NOTICED 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. 1H71 3R3 RRCA806 5E1 20081106 GL 2008 11 6 CA080621001 220080611G72406870992 COMBUST CHAMBER ALLSN 250C 250C20B 03013GL ENGINE CRACKED W K NONE MJ OVER TEMP WARNING INDICATION ININSP/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 120080618G3230750005000 SELECTOR VALVE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE MLG FAILED W O OTHER J WARNING INDICATION APAPPROACH 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 WAS ALL READY DOWN. NO EMERGENCY WAS DECLARED.) CONTACTED REPAIR STATION TO PIN THE LANDING GEAR, AND MAKE READY FOR THE FERRY FLIGHT. A/C TO FERRY FOR REPAIRS. REMOVED AND REPLACED THE MAIN LANDING SELECTOR VALVE. 2L72 4F4 FRTA21EA E15NE 20081106 NM 2008 11 6 CA080623001 120080424G325069355174 ROD END BOEING737 737* NM PWA JT8 JT8D17 52049NE STEERING TILLER WORN W O OTHER E VIBRATION/BUFFET TXTAXI/GRND HDL 1 CA 18425 (CAN) MINOR BUT PERSISTENT VIBRATION COULD BE FELT IN THE STEERING TILLER DURING TAXI, PARTICULARLY AT HIGHER SPEEDS. 2L72 4F4 FRTA16WE E2EA 20081106 CE 2008 11 6 CA080623002 120080619G3230AA5C MOTOR MTSBSIMU2 MU2B60 5780460CE GARRTTTPE331TPE33110 01514WP HARTZLHCB4T HCB4TN5 GL MLG INOPERATIVE W O OTHER J WARNING INDICATION LDLANDING 1 CA 954 954 (CAN) PILOT SELECTED GEAR DOWN THE DOOR MOTOR CIRCUIT BREAKER POPPED. MANUAL GEAR EXTENSION COMPLETED AND ACFT LANDED WITHOUT INCIDENT. MECHANIC DISPATCHED AND FOUND THE GEAR DOOR ACTUATOR/MOTOR UNSERVICEABLE. ACFT FERRIED TO MAINTENANCE BASE, DOOR ACTUATOR/MOTOR REPLACED AND GEAR SWING COMPLETED. ACFT RETURNED TO SERVICE. 1H72 3T4 TRTA10SW E4WE 6 CP40EA 20081106 EA 2008 11 6 CA080623003 220080514G8520LW15628 SEAL PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2A GL CRANKCASE LEAKING W K NONE K FLUID LOSS ININSP/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 STILL UNDER WARRENTY AND IT WAS DECIDED TO REMOVE THE ENGINE FROM SERVICE AND INSTALL A NEW ONE. THE ENGINE OVERHAUL FACILITY WAS REQUESTED TO PROVIDE A TEARDOWN REPORT AS A FOLLOW UP. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081106 EA 2008 11 6 CA080623004 120080620G5200215260522 SHAFT CNDAIRCL215 CL2151A10 1900320EA PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE DOOR BROKEN W O OTHER J WARNING INDICATION TXTAXI/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 RETURNED TO BASE IAW COMPANY SOPS. MAINT FOUND THAT THE BOMB DOOR CLOSING JACK MOUNTING SPIGOT WAS SHEARED AND THAT THE ACTUATOR WAS HANGING FROM ITS HYDRAULIC LINES. NO OTHER DAMAGE WAS FOUND, THE SPIGOT WAS REPLACED, THE SYS FUNCTION-TESTED AIRWORTHY,AND THE ACFT RETURNED TO SERVICE. 2H72 4R3 RRTA14EA ATC14 6 CP871 20081114 EA 2008 11 14 CA080623005 120080620G5240601R387271 UPLOCK CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE SERVICE DOOR CRACKED W O OTHER J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) PILOT REPORTED THAT THE SERVICE DOOR MESSAGE WAS DISPLAYED. MAINT WAS CALLED TO INVESTIGATE THE PROBLEM AND THEY WERE TOLD BY THE CREW THAT THE ENGINEER COULD NOT OPEN THE DOOR AND THEY START REMOVING THE DOOR LINER. ONCE REMOVED, THEY FOUND THAT THE SERVICE DOOR UP-LOCK MECHANISM HAD BROKEN COMPLETELY. BY LOOKING AT THE MATERIAL INSIDE THE CRACK IT WAS NOTICED THERE WERE SIGNS OF DIRT ACCUMULATION IN DIFFERENT AREAS MEANING THAT A CRACK DEVELOPED FOR QUITE SOME TIME. 2L72 4F4 FRTA21EA E15NE 20081106 EA 2008 11 6 CA080623006 120080620G3070304310 HEAT TAPE CNDAIRCL604 CL604 1900301EA GE CF34 CF343B 30069NE WATER LINE BURNED W K NONE O OTHER ININSP/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 AFFECTED PIPING WAS DEEPLY BURNED. THE BREAKER NEVER POPPED DURING THIS INCIDENT. 2L72 4F4 FRTA21EA E15NE 20081106 EU 2008 11 6 CA080623007 120080623G3030 HEATER PILATS PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL PITOT TUBE INOPERATIVE W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 7257 (CAN) ACFT RETURNED WHEN PITOT STATIC HEAT FAIL LIGHT CAME ON. FOUND RT PITOT TUBE NOT HEATING, REPLACED TUBE TESTED SYSTEM AND PERFORMED LEAK TEST ACFT RETURNED TO SERVICE. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081106 EU 2008 11 6 CA080623008 120080618G53115331412041 FRAME PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 17784 (CAN) CORROSION WAS FOUND ON THE TOP SURFACE OF FUSELAGE FRAMES 21 AND 24 BETWEEN ALL 4 SEAT RAILS. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081106 EU 2008 11 6 CA080623009 120080621G53115331412041 FRAME PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 14225 (CAN) CORROSION FOUND ON TOP SURFACE OF FUSELAGE FRAMES 21 AND 24 BETWEEN ALL 4 SEAT RAILS. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081106 SW 2008 11 6 CA080623010 120080622G3260 BULB GULSTM690TP 690 0141720SW GARRTTTPE331TPE3315251K NM MLG INDICATOR INOPERATIVE W O OTHER P NO WARNING INDICATION APAPPROACH 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 LIGHT FOR THE LT MAIN. GEAR APPEARED TO BE IN THE NORMAL DOWN POSITION, GEAR UNSAFE LIGHT WAS NOT ILLUMINATED, AND THE HYDRAULIC PRESSURE WAS NORMAL. MX WAS PHONED TO DISCUSS THE ISSUE, AND CONCLUDED THAT IT WAS PROBABLY A DEFECTIVE LIGHT. CYMM RADIO WAS CONTACTED TO HAVE EMERGENCY VEHICLES ALERTED. ACFT CIRCLED WEST OF CYMM UNTIL EMERGENCY VEHICLES ARRIVED AND THEN PROCEEDED TO LAND WITH NO FURTHER PROBLEMS. AFTER LANDING IT WAS DETERMINED THAT THE LT GEAR LIGHT BULB WAS BURNED OUT. LT MAIN GEAR LIGHT BULB REPLACED. 1H72 3T4 T 2A4 E2WE 20081106 2008 11 6 CA080623011 420080623G2562 G SWITCH DORNEMARGLN ELT FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHEN PERFORMING THE ANNUAL TESTS REQUIRED BY CAR 571 APPENDIX G FOUND G SWITCH WOULD NOT ACTIVATE. ELT REPLACED WITH SERVICEABLE UNIT. 20081106 2008 11 6 CA080623012 420080620G61224U1827 GOVERNOR CNDAIRCL215 CL2151A10 1900320EA PWA R2800 CA3 52026NE HAMSTD43E 43E60 NE PROPELLER FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION APAPPROACH 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 OVERSPEED PROCEDURE WAS FOLLOWED AND THE ENGINE RESPONDED TO THROTTLE REDUCTION BUT WOULD NOT FEATHER. THE ENGINE AND PROP REMAINED STABLE AND LANDING WAS UNEVENTFUL. THE PROP GOVERNOR WAS CHANGED AND THE ACFT WAS RETURNED TO SERVICE. DUE TO THE TSO AND TYPE OF FAILURE THIS GOVERNOR WILL BE SENT OUT FOR A TEAR DOWN REPORT. A FOLLOW UP REPORT WILL BE GENERATED UPON RECEIPT OF THE TEAR DOWN REPORT. 2H72 4R4 RRTA14EA E231 6 CP871 20081106 EA 2008 11 6 CA080624001 220080624G7230 COMPRESSOR PWA PT6 PT6A21 52043EA ENGINE FAILED W O OTHER O OTHER NRNOT 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 WERE INSTALLED "NEW" AT PRIOR OVERHAUL (TSO 465 HOURS). TIE RODS WERE FOUND TO BE WITHIN ALLOWABLE HARDNESS RANGE. ENGINE 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 120080610G5345D2010104 ARM DART ROBSINR44 R44 7640120WP MIRROR SEPARATED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) DART HAS RECEIVED REPORTS FROM CUSTOMERS THAT UNDER CERTAIN CIRCUMSTANCES ON D044-715-011 AND D022-716-011 CARGO MIRROR INSTALLATIONS AT CHG001 THE D2010-104 ARM MAY CRACK DURING FLIGHT CAUSING THE D2011-101 MIRROR TO SEPARATE FROM THE ASSEMBLY. DART SERVICE BULLETIN SB08-2 IS BEING ISSUED TO ALL CUSTOMERS WHO HAVE PURCHASED THESE ASSEMBLIES FROM DART. 1G71 3O H11NM 20081106 NM 2008 11 6 CA080624003 120080624G7933 INDICATOR BOEING727 727225 1384077NM PWA JT8 JT8D15 52051NE OIL TEMP MALFUNCTIONED W E ENGINE SHUTDOWN N FALSE WARNING CLCLIMB 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 NR 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 RETURNED FOR LANDING. MX REPLACED THE OIL TEMP INDICATOR AND BULB WHICH RECTIFIED THE PROBLEM. 2L73 4F4 F A3WE E2EA 20081106 EU 2008 11 6 CA080624004 120080618G3397 WIRE UROCOPEC130 EC130B4 8680989EU TMECA ARRIELARRIEL2B1 60056NE NAV LIGHT CHAFED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 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). 1G72 3U3 U H9EU E00054EN 20081114 CE 2008 11 14 CA080625001 120080606G29106317003136 LINE CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL HYDRAULIC SYS RUPTURED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA 2115 2115 (CAN) ACFT DEPARTED AND EXPERIENCED COMPLETE HYDR FLUID LOSS. ACFT GEAR ALTERNATE EXTENDED AND RETURNED TO AIRPORT. TROUBLESHOOTING REVEALED RUPTURED HYDR PRESSURE LINE INBD OF SERVICE QUICK CONNECT. LINE REPLACED WITH NEW, AND SYS BLED. ACFT 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. 1L72 4F4 FRTA1WI E3GL 20081114 SO 2008 11 14 CA080625002 120080429G2997 CONNECTOR PIPER PA23 PA23250 7102308SO LYC O540 TIO540C1A 41532EA HARTZLHCE2Y HCE2YR2 GL HYD POWERPACK LOOSE W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 CA (CAN) HYDR FLUID NOTED LEAKING FROM MANUAL HYDR HAND PUMP UPON POST-TAKEOFF GEAR RETRACTION. ATTEMPT TO RE-EXTEND GEAR WITH STANDARD SYS OR MANUAL HAND PUMP FAILED. CO2 EMERGENCY DEPLOYED, GEAR EXTENSION UNSUCCESSFUL. S-PIN ON BACK OF PRIORITY VALVE REMOVED BY OTHER CREW MEMBER ONBOARD (WITH GUIDANCE FROM AME ON GROUND VIA RADIO). PIN FOUND DIFFICULT TO REMOVE, TOOLS AND CONSIDREABLE FORCE REQUIRED. GEAR IMMEDIATELY EXTENDED WITH NORMAL INDICATIONS ONCE PIN WAS REMOVED, SUCCESSFUL LANDING EXECUTED. 1L72 3O3 O 1A10 E14EA 5 CP9EA 20081114 EU 2008 11 14 CA080625003 120080620G75007275031504 PIPE SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE ROTOL R389 R3894123F26 NE HP BLEEDAIR CRACKED W C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 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. THE CREW REDUCED ENGINE POWER AND AT THIS TIME THEY DID HAVE A STEADY DECREASE IN ENGINE TEMP. THE ACFT RETURNED TO THE RAMP 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. 2L72 4T4 TRTA52EU E8NE6 6 CP30NE 20081114 SW 2008 11 14 CA080625004 120080618G2910 LINE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 29073NE MCAULY4HFR344HFR34C652 NE HYD SYSTEM CRACKED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION APAPPROACH 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 LANDING 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 THE LEAK. LINE WAS REPLACED WITH NEW, FUNCTION, OPERATION, AND LEAK CHECKS COMPLETED AND THE ACFT RETURNED TO SERVICE. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20081114 SW 2008 11 14 CA080625005 120080612G6210206015001119 BLADE BELL 206 206L 1181522SW ALLSN 250C 250C20R2 GL MAIN ROTOR DELAMINATED W K NONE O OTHER ININSP/MAINT 1 CA 753 (CAN) DELAMINATION AT ROOT OF BLADE ON UPPER SURFACE OF THE GIP PLATE FINGER. VISUAL SEPARATION NOTED ON DAILY INSP. 1G71 3U3 U H2SW E4CE 20081118 SO 2008 11 18 CA080625006 120080622G2823 SCREW PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA SNSNCH76E 76EM8S5 EA FUEL SELECTOR IMPROPER PART W D RETURN TO BLOCK WS INADEQUATE Q C AFFECT SYSTEMS TXTAXI/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 WITH 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 IN1L71 3O3 O 2A13 E286 5 NP4EA 20081118 CE 2008 11 18 CA080625007 120080624G53121014302851 BULKHEAD BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL FUSELAGE CRACKED W K NONE O OTHER ININSP/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. 2L72 4T4 T A24CE E4EA 6 CP56GL 20081118 EA 2008 11 18 CA080625008 120080612G27426009230167 ACTUATOR CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF348E5A1 30062NE HORIZ STAB MALFUNCTIONED W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION NRNOT 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 TRIM ACTUATOR BRAKE COIL OPEN. HORIZ STAB TRIM ACTUATOR (P/N 600-92301-67/21207-008 S/N Y2003) WAS REPLACED WITH A REPAIRED 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 AFTER THAT THE PILOT REPORTED CHANNEL NR1 AND NR2 INOP LIGHT ON. AFTER ATTEMPTING TO RESET THE TRIM SYS BY THE AFM RECOMMENDATION AND FAILED TO RESET, THE PILOT RETURNED TO BASED WITH THE ACTUATOR TRIM FROZEN TO THE LAST SET FLIGHT POSITION. T2L72 4F4 FRTA21AE E00063EN 20081230 NE 2008 12 30 CA080626001 220080619G7314LW15473 PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYS LEAKING W K NONE O OTHER ININSP/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, REMOVED FUEL VENT FITTING, FOUND VENT CHAMBER FULL OF ENGINE OIL. REPLACED WITH NEW PUMP. 1G71 3O3 O H11NM 1E4 20081118 EA 2008 11 18 CA080626002 220080624G8520982C9HE2 MAIN BEARING WRIGHTR1820 982C9HE2 67020EA HAMSTD43D 43D51 NE NR 1 ENGINE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 460 (CAN) ACFT WAS IN CRUISE FLIGHT WHEN PILOT NOTICED OIL TEMP ON NR1 ENGINE INCREASING. A PRECAUTIONARY SHUTDOWN WAS INITIATED ENGINE FEATHERED ACFT RETURNED AND LANDED WITH NO EVENT. INVESTIGATION FOUND THE MAIN OIL SCREENS CONTAMINATED (SUSPECT MAIN BRG FAILURE) ENGINE IS BEING REMOVED AND REPLACEMENT ENGINE INSTALLED ACFT WILL BE RETURNED TO SERVICE. 4 R E259 6 CP8879 20081118 WP 2008 11 18 CA080627001 120080623G243514924HTH HOUSING ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE STARTER-GEN CRACKED W K NONE O OTHER NRNOT REPORTED 1 CA 24 (CAN) STARTER WAS GRINDING ON STARTUP, UPON FURTHER INVESTIGATION AND REMOVAL OF THE STARTER IT WAS FOUND TO HAVE A CRACKED HSG. 1G71 3O3 O H11NM 1E4 20081118 NE 2008 11 18 CA080627002 220080624G7200LTS100750B ENGINE BOLKMS117 BK117B2 5626013EU LYC LTS101LTS101750B1 41560NE NR 2 FLAMED OUT W O OTHER X ENGINE FLAMEOUT TXTAXI/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 GENERATOR, 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 THE NR2 ENGINE WERE INSPECTED AND FOUND NO FAULTS. ALL AIR LINES WERE REMOVED AND VISUALLY INSPECTED AND CAPPED LEAK CHECKED AROUND THE FLARES AND NO FAULTS WERE DETECTED. AIR LINES WERE REINSTALLED AND NR2 ENGINE ASSY WAS LEAK CHECKED IAW MM NO FAULTS DETECTED. THE NR2 ENG WAS GROUND RUNNED AND LEAK CHECKED NO FAULTS WERE FOUND. ACFT WAS RETURNED TO SERVICE 1G72 3U3 UNCH13EU E5NE10 20081118 2008 11 18 CA080627003 120080625G2910MS21926J4 FITTING GULSTM GARRTTTFE731TFE73140 29001NE NLG LOOSE W K NONE KJ FLUID LOSS WARNING INDICATION DEDESCENT 1 CA 1175 (CAN) ON DESCENT THE LT AND RT HYDR PUMP LIGHTS FLICKERED ON AND OFF. LOW HYD RESERVOIR ALSO ILLUMINATED. ALL SYS FUNCTIONED 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, AFTER 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 120080622G5610NP13932112 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT CRACKED W K NONE O OTHER CRCRUISE 1 CA 2651 (CAN)"THE FO’S WINDSHIELD SHATTERED IN FLIGHT. THE OUTTER PANE IS BROKE". REMOVED AND REPLACED THE WINDSHIELD. WINDSHIELD, (RT) NP-139321-12 03017H4489 TSO: 2651.2/CSO: 2069. 2L72 4F4 FRTA21EA E15NE 20081119 NE 2008 11 19 CA080630001 220080522G7200 ENGINE BOEING737 737217 1384464NM PWA JT8 JT8D17A 52049NE NR 2 FAILED W E ENGINE SHUTDOWN E VIBRATION/BUFFET APAPPROACH 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 "POPS" AND THEN A LOUD "BANG" AT WHICH TIME THE NR 2 ENGINE LOST THRUST. NR 2 ENG TEMP CLIMBED BUT THERE WAS NO ENG OVERHEAT OR FIRE WARNING. ATC ADVISED OF EMERGENCY, AFTER LANDING, THE ACFT WAS BROUGHT TO A FULL STOP IN THE MIDDLE OF THE RUNWAY AND THE ENGINE WAS SHUT DOWN. C.F.R. APPROACHED THE ACFT AND NOTICED "SMOKE" AND A "GLOW" FROM THE NR 2 ENGINE. THERMAL 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 2L72 4F4 F A16WE E2EA 20081118 CE 2008 11 18 CA080630002 120080623G270107118505 CONTROL COLUMN CESSNA185 A185F 2072821CE LYC O540 IO540* 41532EA MCAULYD3A34 D3A34C401 GL CORRODED W K NONE O OTHER ININSP/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 HISTORY SHOWED FRESH WATER SUBMERSION IN 1982. 1H71 3O3 O 3A24 1E4 5 CP47GL 20081118 SO 2008 11 18 CA080630003 120080425G8011149NLR STARTER PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2A GL ENGINE FAILED W K NONE O OTHER ININSP/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 STARTER 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. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081118 WP 2008 11 18 CA080630004 120080627G8010A1294BBT SWITCH CVAC 440 440 2422902WP ALLSN 501D 501D13D 03004GL ALLSN A6441 A6441FN606 GL COCKPIT SHORTED W E ENGINE SHUTDOWN O OTHER ININSP/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 AND ATTEMPTING TO START NR2 ENG. NR 1 ENGINE START SWITCH FOUND SHORTING INTERMITTENTLY INTERNALLY WHEN START BUTTON IS ROCKED SIDE TO SIDE. 2L72 4R4 T 6A6 E282 6 CP898 20081107 EA 2008 11 7 CA080630005 120080629G3230555406 SELECTOR VALVE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE NLG UNSERVICEABLE W L ABORTED APPROACH J WARNING INDICATION APAPPROACH 1 CA 223268866 (CAN) GEAR DISAGREE MSG ON GEAR DOWN SELECTION, MAINS INDICATING GREEN AND THE NOSE INDICATING WHITE. CREW CYCLED GEAR WITH SAME RESULT. THEY THEN DID AN ALTERNATE EXTENSION AND GOT THE 3 GREEN INDICATION AND LANDED WITH NO PROBLEM. (LANDING GEAR RETRACTION SYSTEM) MX T/S REVEALED THE NLG DOOR SELECTOR VALVE TO BE AT FAULT. THE SELECTOR VALVE WAS REPLACED AND GEAR SWINGS WERE C/O AND THE ACFT WAS CHECKED SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20081110 EA 2008 11 10 CA080701003 120080630G5751 SKIN BOMBDR DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE AILERON DAMAGED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) DEPARTING AND DURING CLIMB OUT THE ACFT WAS STRUCK BY LIGHTNING CAUSING DAMAGE TO LT AILERON TIP. DECISION WAS MADE TO RETURN THE ACFT TO AIRPORT FOR INSPECTION. INSPECTION COMPLETED PER AMM 05-50-31 AND DAMAGE WAS FOUND AT THE LT AILERON 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. 2H72 4T4 TRTA13NM E20NE 20081110 CE 2008 11 10 CA080701004 120080627G52105043003211 HOOK BEECH BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA PAX DOOR OUT OF ADJUST W B EMER. DESCENT O OTHER CRCRUISE 1 CA (CAN) ACFT DEPRESSURIZED AT 20000 FEET. ACFT DESCENDED TO 10000 FEET AND LANDED WITHOUT INCIDENT MX FOUND THE UPPER FORWARD DOOR HOOK WAS NOT LATCHING PROPERLY THAT CAUSED THE DOOR SEAL TO BLOW OUT CAUSING THE DECOMPRESSION. DOOR HOOK ADJUSTED AND THE DOOR SEAL WAS SECURED. 1L72 3T4 T A14CE E4EA 20081110 EA 2008 11 10 CA080702001 120080629G5610NP1393226 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT CRACKED W K NONE O OTHER TXTAXI/GRND HDL 1 CA (CAN) THE FIRST OFFICERS SIDE WINDOW INNER PANE IS CRACKED. FERRIED THE PLANE. SLC REPLACED THE FIRST OFFICERS SIDE WINDOW. OPS CHECKS GOOD. 2L72 4F4 FRTA21EA E15NE 20081110 2008 11 10 CA080702003 420080701G22974986 FUSE STEC 012980201 PIPER PA46 PA46500TP 7104622SO PWA PT6 PT6A42 52043NE A/P COMPUTER FAILED W K NONE O OTHER ININSP/MAINT 1 CA 500 500 (CAN) MANUAL ELECTRIC & AUTO TRIM UNSERVICEABLE - REPLACED FUSE F2 IN ACCORDANCE WITH S-TEC SERVICE BULLETIN SB08-004. 1L71 3O4 TRTA25SO E4EA 20081110 NE 2008 11 10 CA080702004 220080602G7250 TURBINE BLADES BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE ENGINE DAMAGED W C ABORTED TAKEOFF O OTHER TOTAKEOFF 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 ROOT CAUSE ONCE ESTABLISHED. 2L72 4T4 TRTA24CE E26NE 20081118 NE 2008 11 18 CA080702005 220080626G7250 TURBINE BELL 205 205B SW LYC T53 T5313B 41549NE ENGINE DAMAGED W R AUTOROTATION Y ENGINE STOPPAGE APAPPROACH 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 SUSTAINED 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 SCATTER DAMAGE. INSPECTION OF THE TAILPIPE AREA REVEALED EXTENSIVE DAMAGE TO ALL WHEEL AND DISC ASSEMBLIES. ACFT INSPECTED AS UN-AIRWORTHY. 1G71 4U4 U H1SW E17EA 20081118 NE 2008 11 18 CA080702006 220080612G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MALFUNCTIONED W A UNSCHED LANDING ZJ SIGNIFICANT FAILURE REPORTWARNING INDICATION CLCLIMB 1 CA (CAN) THE PILOT REPORTED WHILE AT 3000FT AGL, 2-3 MINUTES AFTER TAKEOFF, HE HEARD A LOUD BANG AND OBSERVED THE PROP TORQUE 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. 1H71 3T3 T A37CE E4EA 20081118 CE 2008 11 18 CA080702007 120080624G27200510105207 CONTROL CABLE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160CTM GL RUDDER WORN W K NONE O OTHER ININSP/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 GALVANIZED STEEL CABLES. 1H71 3O3 ONT3A12 E274 5 NP910 20081118 NE 2008 11 18 CA080702008 220080308G7200 BEARING CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE DISTRESSED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) WHILE AT CRUISE AT FL70, THE ENGINE TORQUE DROPPED BELOW 600FT-LB WITH ASSOCIATED COCKPIT WARNING LIGHT. THE FLIGHT WAS DIVERTED FROM ITS INTENDED DESTINATION AND AN UNEVENTFUL LANDING WAS MADE. THE ENGINE WAS FWD WHERE DISASSEMBLY SHOWED A DISTRESSED NR 1 BEARING. THE BEARING WAS FWDED TO MFG FOR INVESTIGATION. THE EXTENT OF DAMAGE TO THE BEARING PREVENTED ASSESSMENT OF THE ROOT CAUSE FOR ITS DISTRESS. 1H71 3T3 T A37CE E4EA 20081118 EA 2008 11 18 CA080702009 220080422G7314 DRIVE SHAFT EMB 110 EMB110* SO PWA PT6 PT6A34 52043EA FUEL PUMP DISTRESSED W A UNSCHED LANDING Y ENGINE STOPPAGE NRNOT 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 EXCURSION 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 PRESENT AROUND THE AREA. 1L72 4T4 TRTA21SO E4EA 20081118 2008 11 18 CA080702010 420080630G3197EC130B4 WIRE UROCOPEC130 EC130B4 8680989EU TMECA ARRIELARRIEL2B1 60056NE WARNING SYSTEM MISREPAIRED W O OTHER O OTHER ININSP/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 THE RED WARNING LIGHTS ILLUMINATING ON THE CAUTION LIGHT WARNING PANEL. THE GONG WAS PRESENT BUT VERY LOW AND MAY NOT HAVE BEEN HEARD BY THE PILOT IN CASE OF A RED WARNING INDICATION. WIRE SPLICE TO THE ASU CARD NR1 WAS FOUND TO HAVE AN INTERMITTENT CONNECTION. WIRE WAS REPAIRED AND GONG WARNING WAS RETURNED TO THE PROPER LEVEL. 1G72 3U3 U H9EU E00054EN 20081118 EU 2008 11 18 CA080702011 120080627G2121EVAC2423H COOLING FAN AEROSPATR42 ATR42320 8680930EU PWA PW121 PW121 52124NE HAMSTD14SF 14SF5 NE NR 2 FAILED W O OTHER JB WARNING INDICATION SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) WHILE TAXIING FOR DEPARTURE (FAB 820) THE CREW OBSERVED A NR2 PACK VALVE FAULT. THE FAULT RECURRED AFTER RESET ACCOMPANIED BY AN AFT SMOKE INDICATION. THE F/A CONFIRMED THE PRESENCE OF SMOKE/HAZE IN THE AFT LAV. WHILE CONDUCTING THE CHECK LIST THE SMOKE INDICATION EXTINGUISHED BUT THE ASSOCIATED ODOR REMAINED EVIDENT. MAINT REPLACED THE NR2 GROUND COOLING FAN AND THE ACFT WAS RETURNED TO SERVICE. THE SMELL AND HAZE WAS ATTRIBUTED TO THE DUCT OVERHEAT CONDITION RESULTANT FROM THE FAN FAILURE. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20081118 EU 2008 11 18 CA080702012 120080702G6720ASSB3510127 TUBE 10543079 BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL TAIL ROTOR CHAFED W K NONE O OTHER ININSP/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 LOOKING FWD FROM THE AFT OF THE ACFT. CHAFED AREA TO BE CLEANED UP AND ALODINE APPLIED, AND ON REINSTALLATION OF THE PROTECTIVE BOOT ENSURE NO CONTACT WITH THE CONTROL ROD IS PRESENT. 1G72 3U3 U H3EU E4CE 20081118 2008 11 18 CA080702013 420080630G6122 VALVE CVAC ALLSN 501D 501D13H 03004GL ALLSN A6441 A6441FN606 GL PITCH LOCK VALVEFAILED W O OTHER F FLT CONT AFFECTED LDLANDING 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 CP898 20081118 EA 2008 11 18 CA080703001 220080702G7414M3975 COIL SLICK 4370 CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL MAGNETO WORN W O OTHER W INADEQUATE Q C ININSP/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 DISTRIBUTOR ROTOR HAS A SPRING-LOADED CARBON BRUSH THAT RIDES ON THIS TAB, AND IF THE TAB IS NOT PERPENDICULAR TO THE ROTOR SHAFT, L THE BRUSH IS THRUST SIDEWAYS IN THE ROTOR SHAFT BORE, WEARING THE SIDES OF THE BRUSH AND CUTTING A HALF-MOON DEPRESSION IN THE COIL TAB. THIS TAB WAS SLIGHTLY OFF-LEVEL AND WAS WORN AS DESCRIBED. THE BRUSH WAS ALSO SOMEWHAT WORN ON ITS SIDES. 1H71 3O3 ONT3A12 E274 5 NP910 20081105 CE 2008 11 5 CA080703002 120080703G531205120151 BULKHEAD CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL FUSELAGE CRACKED W K NONE O OTHER ININSP/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 BULKHEAD AT STATION 108 (IMMEDIATELY INSIDE THE BAGGAGE DOOR), JUST ABOVE FLOOR LEVEL. THIS AREA IS NORMALLY COVERED BY PLASTIC INTERIOR PANELS. IT WAS DISCOVERED DURING A 200-HOUR INSPECTION, WHICH REQUIRES REMOVAL OF INTERIOR PANELS AND UPHOLSTERY. 1H71 3O3 ONT3A12 E274 5 NP910 20081105 EU 2008 11 5 CA080703004 120080702G2720 CLEVIS PIN STBROSSC7 SC72 8100510EU RUDDER CONTROL DETACHED W A UNSCHED LANDING DF INFLIGHT SEPARATION FLT CONT AFFECTED CLCLIMB 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 INCIDENT. 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. 1H72 3T A15EU 20081105 EA 2008 11 5 CA080704002 120080702G5753 ROD DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA TE FLAPS WORN W K NONE O OTHER ININSP/MAINT 1 CA CFTFX173 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 OTHER ROD. A NEW SPAN-WISE ROD WAS INSTALLED. DURING INSTALLATION IT WAS NOTED THAT THE BELL CRANK SUPPORT STRUCTURE WAS POSSIBLY 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 PROVIDED WHEN THIS IS DETERMINED. 1H72 3T4 TRTA9EA E4EA 20081105 2008 11 5 CA080704003 420080703G23973042865102 ELECTRICAL BOX BOEING737 737* NM CFMINTCFM567CFM567B22 13802NE ROW 8 DEF ODOR W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 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. 2L72 4F4 FRTA16WE E00055EN 20081105 2008 11 5 CA080704004 120080704G3246 BEARING MLG WHEEL LACK OF LUBE W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) EXCESSIVE WHEEL BEARING NOISE WAS NOTED FROM LANDING GEAR DURING TAXIING. INVESTIGATION REVEALED THAT WHEEL BEARING GREASE HAD WASHED OUT OF THE BEARING AND ONTO THE WHEEL HALF. WATER HAD PERMEATED THE GREASE AND CAUSED EXCESSIVE CORROSION 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 120080705G2751 INDICATOR BOEING727 727225 1384077NM PWA JT8 JT8D15A 52051NE FLAP SYSTEM BROKEN W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) AFTER TAKE-OFF WHEN RETRACTING FLAPS THE INBD FLAPS STUCK AT APPROXIMATELY 5 DEGREES WITH AN ASYMMETRY. THE ACFT DECLARED 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 ASSEMBLY WAS FOUND TO BE AT FAULT, AND THE TRANSMITTER ASSEMBLY SPRING TENSION HAD FAILED. THE FLAP POSITION TRANSMITTER ASSEMBLY WAS REPLACED AND THE FLAP ADJUSTMENT/TEST PROCEDURES WERE CARRIED OUT WITH NO FURTHER FAULTS. THE ACFT WAS RETURNED TO SERVICE. 2L73 4F4 F A3WE E2EA 20081105 GL 2008 11 5 CA080707003 220080706G732123065104 BEARING HONEYWELL BELL 206 206B3 1181506SW ALLSN 250C 250C20B 03013GL FCU DRIVESHAFT FAILED W B EMER. DESCENT XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 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 CONTINUED 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 CORROSION NOTED. REPLACEMENT FCU INSTALLED AND ACFT WAS RUN UP. ACFT DEPARTED BACK TO BASE WITH NO FURTHER ISSUES. 1G71 3U3 U H2SW E4CE 20081105 CE 2008 11 5 CA080707004 120080526G561099144111 WINDSHIELD CESSNA680 680CE 2076811CE PWC PW306 PW306C 52169NE COCKPIT CRACKED W O OTHER O OTHER DEDESCENT 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 WINDSHIELD WAS REPLACED. 2L72 4F4 FRCT00012WIE35NE 20081113 CE 2008 11 13 CA080707005 120080407G322012436351 TORQUE LINK CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE CARRING INP ON UPPER TORQUE LINK IAW CONTINUED AIRWORTHINESS PROGRAM 32-50-02 THE TORQUE LINK WAS FOUND CRACKED. A NEW LINK WAS INSTALLED WITH NEW BOLTS. 1H71 3O3 O A4CE E5CE 5 CP47GL 20081113 SW 2008 11 13 CA080707006 120080616G6510407040416103 SHAFT BELL 407 407 1182206SW ALLSN 250C 250C47B GL TAIL ROTOR CORRODED W K NONE O OTHER ININSP/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 THE 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. 1G71 3U3 UO H2SW E1GL 20081113 CE 2008 11 13 CA080707007 120080422G2730 BEARING CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL CONTROL TUBE WORN W K NONE O OTHER ININSP/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 OFF, IT WAS NOTICED THAT THE BEARINGS HAD WORN THE TUBE TO ITS LIMITS. THE CONTROL TUBE AND THE BEARINGS WERE CHANGED. 1H71 3O3 O A4CE E5CE 5 CP47GL 20081113 2008 11 13 CA080707008 420080407G6113TCB43940008 SPINNER PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL LT PROP CRACKED W K NONE O OTHER ININSP/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. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081113 NE 2008 11 13 CA080707009 220080703G72300292208260 DIFFUSER AEROSPAS355 AS355* EU TMECA ARRIELARRIEL1D1 60053NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING MAINT FOR REPLACEMENT OF THE T2 BLADES AND WHEEL, AFTER REMOVING OUTER CASING OF THE M03 THE OUTSIDE SURFACE 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. 1G72 3U3 U H11EU E19EU 20081113 SO 2008 11 13 CA080707010 120080516G2750 WORM GEAR CALCO PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL FLAP XMSN WORN W K NONE O OTHER ININSP/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. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081113 CE 2008 11 13 CA080707011 120080528G3020 BUSHING BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE HARTZLHCB3T HCB3TN3 GL ICE VANE LINK WORN W K NONE O OTHER ININSP/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 VANE LIGHT TO COME ON. 1L72 4T4 T A24CE E4EA 6 CP15EA 20081113 EU 2008 11 13 CA080707012 120080629G5302 SKIN AEROSPAS355 AS355* EU TMECA ARRIELARRIEL1D1 60053NE TAILBOOM DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) THE HELICOPTER EXPERIENCED A HARD LANDING AFTER BEING PUSHED SIDEWAYS BY A GUST OF WIND. THE RT SKID CAUGHT THE GROUND FIRST AND THE HELICOPTER STARTED TO YAW SEVERLY, PILOT DROPPED COLLECTIVE AND LANDED THE HELICOPTER IMMEDIATELY. THE TAILBOOM SUSTAINED DAMAGE CAUSED BY THE SUDDEN YAW, SERVICEABLE TAILBOOM AND HARD LANDING INSP C/W IAW MM AND RETURNED TO SERVICE. 1G72 3U3 U H11EU E19EU 20081113 NE 2008 11 13 CA080707013 220080627G7210310830601 SLEEVE PWA PT6 PT6A67D NE NR 5 BRG JOURNALDISLODGED W K NONE O OTHER ININSP/MAINT 1 CA 175267040 (CAN) THE ASSEMBLY HAD ACCUMULATED IN EXCESS OF 7000 HOURS SINCE THE SLEEVE WAS INSTALLED ON THE NR 5 BEARING JOURNAL, AND THE POWER SECTION WAS BEING RETURNED TO THE SHOP FOR A SCHEDULED OVERHAUL. DURING INSPECTION OF THE 2ND STAGE REDUCTION CARRIER IAW OHM 3038337, SEC.72-10-00 INSPECTION, PARA.6AM IT WAS FOUND THAT THE NR 5 BEARING JOURNAL SLEEVE HAD MOVED 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 120080606G323042042000 ARM PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA LT MLG RETRACT BROKEN W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING TAKEOFF, COULDN`T GET GEAR UP, LT GREEN LIGHT STAYS ON. UPON INSP AFTER LANDING, LT RETRACTION ARM WAS FOUND BROKEN. CRACK WAS ORIGINATED FROM ONE OF THE BOLT HOLES. NEW PART WAS ORDERED. 1L72 3O3 O A20SO E14EA 20081113 SW 2008 11 13 CA080708001 120080622G2820S0310015HT O-RING GULSTM GULSTM690TP 690D 3970405SW GARRTTTPE331TPE3315 01514WP ROTOL R306 R306382F7 GL COUPLING WORN W O OTHER K FLUID LOSS NRNOT 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 ACFT RETURNED TO SERVICE. 1H72 3T4 T 2A4 E4WE 6 CP8EU 20081113 EA 2008 11 13 CA080708002 120080706G2750855D1009 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE RT TE FLAP UNSERVICEABLE W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) ACFT WAS SET UP IN LANDING CONFIGURATION WITH FLAPS AT 45 DEGREES. ON SHORT FINAL, CREW RECEIVED A FLAP FAILURE INDICATION. 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. 2L72 4F4 FRTA21EA E15NE 20081113 CE 2008 11 13 CA080708004 120080626G3230PDLM60 CIRCUIT BREAKER BEECH BEECH 100 100BEECH 1152916CE GARRTTTPE331TPE3316252B 01514WP HARTZLHCB4T HCB4TN5 GL LANDING GEAR FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) ACFT DEPARTED, OR AFTER SCHEDULED MAINT WAS COMPLETED. IN THE CLIMB OUT IT WAS NOTICED BY THE CREW THAT THE LANDING GEAR FAILED TO RETRACT. THE ACFT LANDED WITHOUT INCIDENT. UPON INSP IT WAS FOUND THAT THE CIRCUIT BREAKER HAD FAILED BUT HAD NOT ACTUALLY POPPED. THE BREAKER WAS BENCH TEST AND CONTINUED TO NOT ALLOW POWER THOUGH DESPITE BEING PROPERLY DEPRESSED. THE BREAKER WAS REPLACED WITH A NEW ONE AND THE SYS FUNCTION TESTED NORMAL. 1L72 3T4 T A14CE E2WE 6 CP40EA 20081113 CE 2008 11 13 CA080708005 120080708G273155657562 WHEEL CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ELEVATOR TRIM DAMAGED W K NONE O OTHER ININSP/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 ITS GROOVE. INSPECTION FOUND THAT THE GROOVES WERE NOT WORN AND THE SYSTEM LOOKED NORMAL BUT WHEN THE WHEEL WAS ROTATED WITH 1 FINGER APPLYING PRESSURE TO THE SIDE OF THE WHEEL IT WOBBLED AND ALLOWED THE PIN RIDING IN THE GROOVE TO BECOME DISENGAGED. PINCHING THE WHEEL WITH A THUMB AND FINGER OR TURNING THE WHEEL WITH THE PALM OF THE HAND ON THE TOP DID NOT ALLOW THE PIN TO DISENGAGE. 1L72 4F4 F A22CE E1NE 20081113 NE 2008 11 13 CA080708006 220080621G7314LW15473 PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYS LEAKING W O OTHER O OTHER NRNOT REPORTED 1 CA 98 (CAN) DURING A GROUND RUN OF THE ACFT THE ENGINE FUEL PUMP WAS LEAKING. 1G71 3O3 O H11NM 1E4 20081113 WP 2008 11 13 CA080708007 120080630G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE INOPERATIVE W O OTHER O OTHER NRNOT REPORTED 1 CA 344 (CAN) STARTER BENDIX IS NOT FUNCTIONING/STARTER WOULD NOT ENGAGE THE RING GEAR. 1G71 3O3 O H11NM 1E4 20081113 WP 2008 11 13 CA080708008 120080629G6310C0511 ACTUATOR ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA CLUTCH LOOSE W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) THE CLUTCH ACTUATOR LOWER MOTOR HSG FLANGE TO WORM GEAR FOUND LOOSE. 1G71 3O3 O H11NM E295 20081113 SO 2008 11 13 CA080708009 120080620G8011 STARTER PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL ENGINE UNSERVICEABLE W O OTHER O OTHER NRNOT REPORTED 1 CA 641 (CAN) THE STARTER WOULD NOT ENGAGE, REPLACED WITH A SERVICABLE STARTER. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081113 2008 11 13 CA080708010 420080708G3452 TRANSPONDER CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA ATC INTERMITTENT W K NONE O OTHER ININSP/MAINT 1 CA (CAN) MODE C ALTITUDE REPORTING INTERMITTENTLY REPORTS FALSE ALTITUDES. VISUAL INSP FOUND A CHAFED MODE C A1 CODE WIRE IN THE ALTITUDE ENCODER WIRING. WIRE WAS CHAFFING (DUE TO VIBRATION) ON THE THROTTLE CABLE DIRECTLY BEHIND THE CENTER RADIO PANEL. WIRE WAS REPAIRED AND CHAFE PROTECTION WAS ADDED TO THE WIRE HARNESS. MODE C DATA INTEGRATION CHECK WAS PERFORMED IAW CARS STD 571 APPENDIX F, ITEM K. 1H71 3O3 ONT3A12 1E10 20081113 NM 2008 11 13 CA080708011 120080708G2497 WIRE BOEING737 737400 138449ANM COCKPIT CHAFED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT 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 GALLEY POWER MODULE. INSPECTION REVEALED NO AFFECT TO ACFT STRUCTURE, BUT 6 WIRES WERE FOUND CHAFFED REVEALING THEIR RESPECTIVE 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. W036-650-22, 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 242L72 4F RTA16WE 20081113 NE 2008 11 13 CA080709001 220080706G73207982133007 EEC DHAV DHC8 DHC8315 2809010NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE ENGINE MALFUNCTIONED W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CLCLIMB 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 RUNS 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 UNIT (EECU) WAS REPLACED THE ENGINES WERE GROUND RUN AND NO FAULTS WERE FOUND. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081113 EU 2008 11 13 CA080709002 120080708G32205322012289 DRAG LINK PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL NLG CRACKED W K NONE O OTHER ININSP/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. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081113 NM 2008 11 13 CA080709003 120080709G2710 CONTROL CABLE EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE AILERONS MISINSTALLED W K NONE W INADEQUATE Q C ININSP/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 2L72 4F4 FRTA57NM E00070EN 20081113 NM 2008 11 13 CA080709004 120080709G575319092001405 CARRIAGE EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE LT TE FLAP GROOVED W K NONE O OTHER ININSP/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. ENGINEERING ADVISED THE ROOT CAUSE OF THE DAMAGE OF THE FLAP CARRIAGE IS CAUSE BY THE FLAP TRACK MECHANISM LOOSE BOLT. 2L72 4F4 FRTA57NM E00070EN 20081113 EU 2008 11 13 CA080709005 120080706G2720RS87 RETAINING RING BRAERO BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP ROTOL R333 R333482F12 GL RUDDER PEDAL MISSING W D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA 500 (CAN) RUDDER PEDAL BECAME DISENGAGED FROM PEDAL SPIGOT, RS87 RETAINING RING CAME OUT OF RETAINING SLOT. RETAINING RING SEEMED TO HAVE INSUFFICIENT TENSION TO STAY IN SLOT. NEW RING INSTALLED AND NO FURTHER PROBLEMS. FLEETWIDE INSPECTION CARRIED OUT AND NO SIMILAR PROBLEMS FOUND. 2L72 4T4 TRTBA15CAA E4WE 6 CP61GL 20081113 NM 2008 11 13 CA080709006 120080703G271019005549401 CONTROL CABLE EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE AILERONS BROKEN W K NONE O OTHER ININSP/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 FAIRLEAD. EMBRAER CAME UP WITH 2 SERVICES BULLETIN: SB190-27-0017 EMBRAER FLIGHT CONTROLS - AILERON - CABLES WEAR SB170-27-0028 EMBRAER FLIGHT CONTROLS - AILERON - CABLES WEAR 2L72 4F4 FRTA57NM E00070EN 20081113 NM 2008 11 13 CA080709007 120080709G322019070150404 BUSHING EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE NLG MIGRATED W K NONE O OTHER ININSP/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 INVESTIGATION FOUND NO CLEARANCE FIT, EMBRAER HAS BEEN ADVISED OF THE PROBLEM. THIS PROBLEM HAS BEEN ALREADY FOUND ON NUMEROUS ACFT 2L72 4F4 FRTA57NM E00070EN 20081113 EA 2008 11 13 CA080709008 220080704G8530 EXHAUST VALVE LYC O540 O540* 41532EA ENGINE SEIZED W O OTHER E VIBRATION/BUFFET DEDESCENT 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 VIBRATION 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 320080703G6111SFA13N1ROA1D BLADE CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE PROP ASSY LEAKING W K NONE K FLUID LOSS ININSP/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. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20081113 NE 2008 11 13 CA080709010 220080706G8550 SCAVENGE PUMP DOUG DC6 DC6B 3021712WP PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE ENGINE FAILED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CRCRUISE 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 LANDING CARRIED OUT WITHOUT FURTHER INCIDENT. 2L74 4R3 R 6A4 ATC14 6 CP871 20081113 GL 2008 11 13 CA080709011 320080709G6111A1851B BEARING RACE HARTZLHCB3R HCB3R304 GL PROPELLER FRACTURED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PROPELLER WAS RECEIVED IN SHOP FOR REMOVAL OF A BROKEN OFF GREASE NIPPLE IN BLADE CLAMP. BLADE CLAMP REQUIRED REMOVAL 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 NORMAL CONDITION FOR THIS PROP TYPE. BEARING WAS REPLACED AND PROPELLER RETURNED TO SERVICE. 5 CP28EA 20081113 SW 2008 11 13 CA080710001 120080708G5620412670101 WINDOW BELL 412 412EP 1182205SW PWA PT6T PT6T3 52045EA PAX DOOR MISSING W O OTHER O OTHER DEDESCENT 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 FLIGHT AT 138 KNOTS. 1G72 4U4 U H4SW E22EA 20081113 SW 2008 11 13 CA080710002 120080618G255026801500 CABLE BELL 427 427 1182207SW PWC PW207 PW207D NE CARGO HOOK ASSY BROKEN W O OTHER O OTHER CRCRUISE 1 CA 284 (CAN) MANUAL RELEASE CABLE BROKE AT CARGO HOOK FITTING CAUSING HOOK TO RELEASE INFLIGHT. 1G71 3U3 U R00001RCE42NE 20081113 EU 2008 11 13 CA080710003 120080704G2822045004B145A SWITCH SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B1 60056NE FUEL PUMP FAILED W H DEACTIVATE SYST/CIRCUITS O OTHER TXTAXI/GRND HDL 1 CA 435 (CAN) FUEL PUMP WOULD NOT TURN ON 1G71 3U3 U H9EU E00054EN 20081113 CE 2008 11 13 CA080710004 120080709G7120J124532 MOUNT CESSNA210 210R 2073458CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL ENGINE DEFORMED W K NONE O OTHER ININSP/MAINT 1 CA 1863 (CAN) DURING ENGINE INSPECTION NOTED THAT THE LT AND RT FORWARD ENGINE MOUNTS WERE SAGGING TO THE POINT THAT DURING TAKEOFF POWER ON ENGINE AND INTAKE PIPE HOSE CLAMP MADE CONTACT WITH THE UPPER PORTION OF ENGINE MOUNT. THE LORD MOUNT APPEARED TO BE SAGGING/DROOPING BUT NOT SEPERATED ANYWHERE. BOTH FRONT ENGINE MOUNTS REPLACED WITH NEW. 1H71 3O3 ORT3A21 E5CE 5 CP47GL 20081113 NE 2008 11 13 CA080710005 220080708G8530 EXHAUST VALVE PWA R985 R985AN14B 52008NE ENGINE DAMAGED W O OTHER RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CRCRUISE 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 THROTTLING 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 OVERHAULED AT LAST ENGINE OVERHAUL. 3 R 5E1 20081113 SW 2008 11 13 CA080710006 120080709G5410205030195030 BEAM BELL 205 205A1 1181414SW LYC T53 T5317BLYC 41616NE LT NACELLE CRACKED W K NONE O OTHER ININSP/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 WAS GROUNDED. THE AIRFRAME TIME 15185 HOURS. THE TIME ON THE MAIN BEAM CAP IS UNKNOWN. 1G71 4U4 U H1SW E17EA 20081113 EU 2008 11 13 CA080711001 120080708G2121BC112A2 FAN SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE ROTOL R389 R3894123F26 NE CABIN OVERHEATED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 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 THAT WHEN THE FLIGHT DECK RECIRCULATION FAN WAS SELECTED THE CONTROL BREAKER POPPED. THE CENTER ISLE FLOOR BOARDS WERE REMOVED 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. 2L72 4T4 TRTA52EU E8NE6 6 CP30NE 20081113 2008 11 13 CA080711002 420080709G34516221234013 INDICATOR SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE DME BURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS APAPPROACH 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 CREW SHUT DOWN ALL NON-ESSENTIAL AVIONICS AND CONTINUED WITHOUT INCIDENT. THE ACFT WAS THEN POSITIONED AT THE HANGAR WHERE MX REMOVED AND CARRIED OUT AN INSPECTION ON THE DME INDICATOR. UPON A CLOSER LOOK IT WAS NOTICED THAT THE CAPACITOR HAD FAILED. IT WAS DETERMINED THAT THE INDICATOR WAS THE SOURCE OF THE PROBLEM. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20081113 EA 2008 11 13 CA080711003 120080704G28102156400212 FUEL CELL CNDAIRCL215 CL2156B11215 EA LEAKING W K NONE K FLUID LOSS ININSP/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 CENT. NOTE: WE’VE HAD SO MANY PROBLEMS WITH THESE CELLS THAT WE MADE AN INTERNAL PROCEDURE TO TEST THEM BEFORE INSTALLATION 2H72 4T RTA14EA 20081113 GL 2008 11 13 CA080711004 120080627G2150347074 BEARING BOMBDRBD100 BD1001A10 1390044GL HNYWL AS907 AS90711A 33908WP ACM IMPELLER DRAGGING W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS TXTAXI/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 VENTS. THE CABIN FILLED UP QUICKLY ENOUGH THEY WERE STARTING TO HAVE TROUBLE BREATHING. ONLY THING THEY MANAGED TO DO WAS SHUT 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 DEPARTMENT. FD USED THERMAL IMAGING TO DETERMINE THERE WAS NO FIRE AND LEFT. NO EMERGENCY WAS DECLARED. 2L72 4F4 FRTT00005NYE00010LA 20081113 SO 2008 11 13 CA080711005 220080620G8530AEC646263 PISTON CESSNA182 182K 2072724CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL SKIRT BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 517 (CAN) A PIECE OF NR 2 PISTON SKIRT WAS BROKEN OFF AT THE OIL CONTROL RING GROOVE. 1H71 3O3 ONT3A13 E273 5 CP3EA 20081113 NE 2008 11 13 CA080711006 220080701G7230 BLADES PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE COMPRESSOR DAMAGED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE AT FL200, THE PILOT NOTED THE ENGINE TEMPERATURE RAPIDLY RAISING TO 850°C WITH POWER TURBINE SPEED DECREASING. HE ELECTED TO SHUT THE ENGINE DOWN AND PERFORMED A SUCCESSFUL DEAD STICK LANDING. POST FLIGHT ENGINE EXAMINATION REVEALED HEAVY RUBBING DAMAGE IN THE COMPRESSOR SECTION. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L71 3T4 TRTA78EU E26NE 20081113 CE 2008 11 13 CA080711007 120080626G793230B385103 SENSOR CESSNA680 680CE 2076811CE PWC PW306 PW306C 52169NE RT ENGINE LEAKING W K NONE K FLUID LOSS ININSP/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. FURTHER 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. 2L72 4F4 FRCT00012WIE35NE 20081113 EA 2008 11 13 CA080711008 120080706G3240AE87996E LINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE NR 2 BRAKE ASSY DISCONNECTED W O OTHER B SMOKE/FUMES/ODORS/SPARKS LDLANDING 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. 2L72 4F4 FRTA21EA E15NE 20081113 NE 2008 11 13 CA080711009 220080629G7261 ENGINE CESSNA560 560XL 2076702CE PWC 545 PW545B NE OIL CONSUMPTION W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 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 QUARTS IN 10 MIN. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4F4 FRTA22CE E00059EN 20081113 EU 2008 11 13 CA080711010 120080705G7797 CONNECTOR BAG ATP ATP EU PWA PW120 PW126A NE ENGINE CONTAMINATED W O OTHER RX PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT CRCRUISE 1 CA (CAN) DURING FLIGHT, THE ENGINE TORQUE STARTED TO FLUCTUATE BETWEEN 60% TO 120% AND THE ENGINE SHUT ITSELF DOWN. TROUBLESHOOTING 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. 2L72 4T4 TRTA27NM E2ONE 20081113 NE 2008 11 13 CA080711011 220080706G8530399354 CYLINDER HEAD DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE ENGINE SEPARATED W A UNSCHED LANDING ERJVIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 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 1H71 3R3 RRCA806 5E1 20081113 SO 2008 11 13 CA080711012 120080705G8011MHB4016R STARTER PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA INOPERATIVE W K NONE O OTHER ININSP/MAINT 1 CA 48 (CAN) THE STARTER WOULD NOT WORK AT ALL, REPLACED WITH A SERVICEABLE STARTER. 1L72 3O3 O A20SO E14EA 20081113 EA 2008 11 13 CA080712001 120080711G32402604141 HOUSING CNDAIRCL215 CL2151A10 1900320EA PWA R2800 CA3 52026NE BRAKE PISTON CRACKED W K NONE O OTHER ININSP/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. 2H72 4R4 RRTA14EA E231 20081113 CE 2008 11 13 CA080714001 120080708G5343 TRUNNION CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE MISINSTALLED W K NONE O OTHER ININSP/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 UNDER 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). 1L72 4F4 F A22CE E1NE 20081113 SO 2008 11 13 CA080714003 120080714G81204091709001 TURBOCHARGER PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA ENGINE FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 800 (CAN) RT TURBOCHARGER FAILED SHORTLY AFTER T/O. ENGINE SHUTDOWN AND ACFT RETURNED TO AIRPORT FOR AN UNEVENTFUL LANDING. 1L72 3O3 O A20SO E14EA 20081113 NM 2008 11 13 CA080714004 120080712G8097 WIRE AIRBUSA319 A319114 3930350NM CFMINTCFM56 CFM565A1 NE START VALVE DAMAGED W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CLCLIMB 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 POWER 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. 2L72 4F4 FRTA28NM E29NE 20081113 EA 2008 11 13 CA080714005 120080708G1400TBC6EM106727 BOLT DHAV DHC6 DHC6 2802606EA DRAIN VALVE MISMANUFACTURED W O OTHER O OTHER NRNOT 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 PURCHASED 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 COMPARED TO TBAL DRAWINGS. THE LOCK WIRE HOLE WAS CLOSER TO THE EDGE OF THE HEAD ON THE TBAL PART WHEN COMPARED AGAINST THE OEM. 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.1H72 3T RTA9EA 20081118 2008 11 18 CA080714006 420080714G2565 LINE BFGOODRICH ESCAPE SLIDE MISROUTED W K NONE W INADEQUATE Q C ININSP/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 DISCOVERED 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 220080711G72509362M43P02 TURBINE WHEEL GE CF6 CF680C2* GL ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 4522213716 (CAN) DURING SHOP INSPECTION CRACKS FOUND ON FWD DOVETAIL SEPARATIONS IN EXCESS OF MANUAL LIMITS. 4 F E23EA 20081110 EA 2008 11 10 CA080714008 120080710G2820 SLEEVE GE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE WORN W E ENGINE SHUTDOWN J WARNING INDICATION CLCLIMB 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 DOWN CARRIED OUT. RECTIFICATION: AFTER INVESTIGATION, FOUND A COUPLING DISCONNECTED ON MAIN LT ENGINE FUEL FEED LINE LOCATED IN THE CENTER TANK. REASON WHY THE CENTER TANK WAS @ 1600 LBS AND CAUSED AN IMBALANCE. FOUND SLEEVE/COUPLING DAMAGED. NEW COUPLING ASSEMBLY REINSTALLED PROPERLY ON ENGINE FUEL FEED LINE, ENGINE RUNS, LEAK CHECK CARRIED OUT AND ACFT BACK IN SERVICE 2L72 4F4 FRTA21EA E15NE 20081110 NM 2008 11 10 CA080715001 120080625G29136617303 PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA HYDRAULIC SYS FAILED W O OTHER J WARNING INDICATION CRCRUISE 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 IN CASE DRAIN FILTER. EDP REPLACED AND ACFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E00062EN 20081110 CE 2008 11 10 CA080715002 120080715G534204310093 ATTACH FITTING CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 11005 (CAN) LT ATTACH FITTING CRACKED AT LOWER OUTSIDE RADIUS ADJACENT TO AN 4-6A ATTACH BOLT. 1H71 3O3 ONT3A19 E223 5 NP50GL 20081112 CE 2008 11 12 CA080715003 120080702G2421 COMMUTATOR KELLY CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO ALTERNATOR FAILED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC DEDESCENT 1 CA 289 (CAN) FLIGHT CREW NOTICED THE ALTERNATOR WAS NOT CHARGING ON DESCENT. UPON CLOSER INSPECTION IT WAS FOUND THAT THE COMMUTATOR 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. 1H71 3O3 O A4CE E5CE 20081112 EU 2008 11 12 CA080715004 120080714G242131342001 SHAFT SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE ROTOL R389 R3894123F25 NE GENERATOR SHEARED W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CRCRUISE 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. 2L72 4T4 TRTA52EU E8NE6 6 CP30NE 20081112 EU 2008 11 12 CA080715005 120080711G5415417157001 BRACKET SNIAS 350 AS350BA 8680817EU LYC LTS101LTS101* NE FUEL FILTER CRACKED W K NONE O OTHER ININSP/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 SUPPORT, 1 AT THE TOP AND 1 AT THE BOTTOM ASSEMBLY HOLDING HOLES GOING FROM EACH HOLE TO THE EDGE OF SUPPORT. 1G71 3U3 UNCH9EU E5NE 20081112 SO 2008 11 12 CA080715006 220080708G8530 STUD SUPERIOR CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO CYLINDER HEAD FAILED W A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 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. 1H71 3O3 O A4CE E5CE 20081112 SW 2008 11 12 CA080715007 120080715G6410206011809005 PITCH HORN BELL BELL 206 206B 1181511SW ALLSN 25OC 250C20R GL T/R HUB DAMAGED W O OTHER O OTHER NRNOT 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. 1G71 3U3 U H2SW E4CE 20081112 CE 2008 11 12 CA080716001 120080715G212199101133 COOLING FAN CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE NOISY W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FLOOD COOLING FAN NOISY. FUNCTIONAL CHECK CONFIRMED SNAG, UNIT REMOVED FROM ACFT AND REPLACED WITH OVERHAULED UNIT. 1L72 4F4 F A22CE E1NE 20081112 EA 2008 11 12 CA080716002 120080710G2810K215T640024 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE NR 4 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) FUEL LEAK FROM RT WING. CHANGED NR4 RT PN-K215 T64002-4 SN 89306. 2H72 4T4 TRTA14EA E20NE 20081112 EU 2008 11 12 CA080716003 120080714G5415417157001 BRACKET SNIAS 350 AS350BA 8680817EU LYC LTS101LTS101* NE FUEL FILTER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 790 (CAN) CRACK DISCOVERED DURING ENGINE VISUAL INSPECTION ON THE HIGH PRESSURE FUEL ASSEMBLY SUPPORT, CRACK ON THE TOP HOLDING HOLE, FROM HOLE TO THE EDGE OF SUPPORT. 1G71 3U3 UNCH9EU E5NE 20081112 EU 2008 11 12 CA080716004 120080624G6220350A31182703 FREQ ADAPTER SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE MAIN ROTOR HEAD WORN W O OTHER O OTHER NRNOT REPORTED 1 CA 5299 (CAN) WORN TO SERVICEABLE LIMITS, RUBBER DEBONDING FROM ITS METHC SURFACE. REPLACED WITH A NEW SET. 1G71 3U3 U H9EU E19EU 20081112 EU 2008 11 12 CA080716007 120080707G5350 FAIRING AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE FUSELAGE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FIRST AIR HAS OBSERVED SEVERAL OCCURRENCES OF DEGRADATION IN THE SURFACE PROTECTION COATING ON THE ACFT LOWER CENTER 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 HOUSED WITHIN THE LANDING GEAR BAY AREA WHICH IS FAIRED IN BY THE AFFECTED PANELS. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20081112 NM 2008 11 12 CA080716008 120080714G2781H1010271 POSITION SWITCH BOEING727 727243 138408DNM PWA JT8 JT8D9A 52048NE NR 6 L/E SLAT MALFUNCTIONED W L ABORTED APPROACH N FALSE WARNING APAPPROACH 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 SLAT POSITION SWITCH WAS UNSERVICEABLE. THE SWITCH WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE. 2L73 4F4 FRTA3WE E2EA 20081112 2008 11 12 CA080716009 420080716G2562E01G G SWITCH ELT STICKING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ANNUAL BENCH RECERTIFICATION OF ELT, THE OPS OF THE G-SWITCH WAS TESTED AND FOUND TO BE STICKING INTERMITTENTLY. THE G- SWITCH WAS REPLACED AND OPS WAS TESTED SEVERAL TIMES TO ENSURE NEW G SWITCH IS OPERATING CORRECTLY. NO FURTHER PROBLEMS NOTED 20081112 GL 2008 11 12 CA080717001 220080705G732323076061 GOVERNOR BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL TURBINE MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA 246 (CAN) DURING GROUND RUN THE GOVERNOR WOULD NOT MAINTAIN ENGINE RPM. REMOVED AND SERVICEABLE GOVERNOR INSTALLED. 1G71 3U3 U H2SW E4CE 20081112 WP 2008 11 12 CA080717002 120080714G6310C0512REVU ACTUATOR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE CLUTCH INOPERATIVE W O OTHER O OTHER NRNOT REPORTED 1 CA 1067 (CAN) THE CLUTCH WOULD NOT ENGAGE, FERRY FLIGHT PERMIT APPROVED AND ACFT RETURNED TO BASE. THE MICROSWITCH WAS FOUND FAULTY, CLUTCH ACTUATOR R&R WITH A SERVICEABLE ACTUATOR 1G71 3O3 O H11NM 1E4 20081112 NM 2008 11 12 CA080717003 120080716G534717003263001 SEAT TRACK EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE FUSELAGE CORRODED W K NONE O OTHER ININSP/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 FOUND 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 2L72 4F4 FRTA56NM E00063EN 20081112 EU 2008 11 12 CA080717005 120080715G6730SC5083SN2353 SERVO SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE MALFUNCTIONED W O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 CA 2017 (CAN) ON A EUROCOPTER AS350 B2 DURING HYDRAULIC TEST PROCEDURES FOR FIRST FLIGHT OF THE DAY THE PILOT ENCOUNTERED THE CYCLIC 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 REPAIR. 1G71 3U3 U H9EU E19EU 20081112 SW 2008 11 12 CA080718001 120080713G6230 BEARING BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE M/R MAST DAMAGED W A UNSCHED LANDING J WARNING INDICATION HOHOVERING 1 CA 6478 17 (CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPS, UPON DESCENT WITH AN EXTERNAL LOAD, THE MASTER CAUTION WARNING INDICATION 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 NORMALLY IN AN ADJACENT CUT BLOCK. A POST-SHUTDOWN INSPECTION BY THE AME REVEALED AN ABUNDANCE OF ALUMINUM METAL SHAVINGS IN 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 REMO1G71 4U4 U H1SW E17EA 20081112 EU 2008 11 12 CA080718002 120080715G32225322012289 DRAG LINK PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL TAIL GEAR CRACKED W K NONE O OTHER ININSP/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. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081112 EA 2008 11 12 CA080718003 120080712G5610NP139322001 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA (CAN) FLT NR 5820, CAPTAINS SIDE WINDSHIELD CRACKED. WINDOW CRACKED FROM LOWER LT CORNER TO UPPER RT CORNER. CALLED AMERICAN EAGLE AND THEY DETERMINED IT WAS THE INNER PLY. ACFT TO FERRY IN THE MORNING TO COS. CAPTAIN SIDE WINDSHIELD R&R. 2L72 4F4 FRTA21EA E15NE 20081112 EU 2008 11 12 CA080718004 120080717G3251176SF2DT102W0162POTENTIOMETER DORNERDO228 DO228202 2992030EU GARRTTTPE331TPE331* 01514WP STEERING MALFUNCTIONED W C ABORTED TAKEOFF H ELECT. POWER LOSS-50 PC TOTAKEOFF 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 CONFIRMED THAT THE NOSE GEAR STEERING WAS ALL THE WAY TO THE LT. ACFT LANDED SAFELY UPON NOSE TOUCHED DOWN IT CENTERED ITSELF AND WAS TAXIED BACK USING ENGINE DIFFERENTIAL POWER. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE STEERING POTENTIOMETER 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. 2H72 4T3 TRTA16EU E2WE 20081112 EA 2008 11 12 CA080718005 220080714G731491380003 PUMP BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA FUEL SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/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. 1L72 4T4 T A24CE E4EA 20081112 NE 2008 11 12 CA080718006 220080714G8530127951 WASHER CNDAIRCL215 CL2151A10 1900320EA PWA R2800 CA3 52026NE INTAKE VALVE BROKEN W K NONE K FLUID LOSS ININSP/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 CRACKED. CAP WAS REMOVED AND FOUND THAT 1/3 OF THE INTAKE VALVE UPPER WASHER WAS BROKEN OFF AND THE PIECE WAS LAYING IN THE ROCKER BOX AREA. INSPECTION REVEALED THAT THE WASHER PIECE HAD BEEN PUSHED AROUND THE ROCKER BOX AREA, CRACKING THE ROCKER 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 CYLINDER WAS REPLACED WITH AN OVERHAULED UNIT. ACFT RUN UP, ENGINES CHECKED FOR POWER AND LEAKS, AND ACFT WAS RETURNED TO S2H72 4R4 RRTA14EA E231 20081112 SW 2008 11 12 CA080718007 120080717G6320206040184001 PUMP BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL TRANSMISSION DISLODGED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION HOHOVERING 1 CA 28 (CAN) THE SEAL FOR THE TRANSMISSION OIL PUMP BECAME DISLODGED, AND LOSS OF OIL OCCURRED. 1G71 3U3 U H2SW E4CE 20081112 CE 2008 11 12 CA080721001 120080714G4997 WIRE LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE APU CHAFED W F ACTIVATE FIRE EXT. N FALSE WARNING TXTAXI/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 SHUTDOWN 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. 2L72 4F4 FRTA10CE E35NE 20081112 CE 2008 11 12 CA080721003 120080721G555226340231 FITTING CESSNA CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE BEARING SUPPORT DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE MOVEMENT OF THE ELEVATOR WAS NOTED AS NOT BEING `SMOOTH`. ON INVESTIGATION IT WAS FOUND THAT THE BEARING IN THE SUPPORT BRACKET WAS SEIZED AND THAT THE SUPPORT BRACKET ALSO HAD CORROSION. THE BRACKET (AND BEARING) WILL BE REPLACED WITH NEW BEFORE NEXT FLIGHT. 1H71 3T3 T A37CE E4EA 20081112 WP 2008 11 12 CA080721005 120080721G6310C0511 ACTUATOR ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA CLUTCH DAMAGED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) DURING 100 INSPECTION AND ACTUATOR FUNCTION TEST, 1 OF THE COLUMN SPRINGS SWITCH DID NOT RESPOND. FANWHEEL ASSY REMOVED AND SWITCHES CHECKED MANUALLY AND FOUND SERVICEABLE. IT SEEMS LIKE THE SPRINGS ON 1 SIDE DID NOT PUSH THE SWITCH COMPLETELY AND THERE WAS ONLY 1 SWITCH ACTIVE. ACTUATOR ASSEMBLY SENT TO R.H.C. 1G71 3O3 O H11NM E295 20081112 SW 2008 11 12 CA080722001 120080713G6320 BEARING BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE M/R MAST DAMAGED W A UNSCHED LANDING J WARNING INDICATION HOHOVERING 1 CA 6478 17 (CAN) UPON DESCENT WITH AN EXTERNAL LOAD, MASTER CAUTION WARNING INDICATION ILLUMINATED. THE PIC CHECKED THE CAUTION PANEL TO FIND A TRANSMISSION OIL PRESSURE CAUTION LIGHT ILLUMINATED, TRANSMISSION OIL PRESSURE GAUGE INDICATING ZERO PRESSURE. 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. DURING 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 GROO1G71 4U4 U H1SW E17EA 20081112 EU 2008 11 12 CA080722002 120080707G2731EM40112 ACTUATOR PIAGIO PIAGIOP180 P180 6960204EU PWA PT6 PT6A66 52043NE HARTZLHCE5N HCE5N3 GL ELEVATOR TRIM MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 CA 605 (CAN) THE HORIZONTAL STABILIZER PRIMARY TRIM FAILED IN THE DOWN MODE ONLY. THE ACFT THEN PROCEEDED TO THE NEAREST AIRPORT. MAINT CONFIRMED THE SNAG ON THE GROUND. AFTER REPLACING THE HORIZONTAL TRIM ACTUATOR THE SYS FUNCTIONED NORMAL. 1H72 3O4 TRTA59EU E26NE 5 CPZONE 20081112 EU 2008 11 12 CA080722003 120080716G6310350A351069 GIMBAL PIN SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE DAMAGED W K NONE O OTHER ININSP/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. GIMBAL PINS (ALL 4 OF THEM) WERE SENT ALONG WITH OTHER PARTS FOR NDT (NO REQUIREMENT TO CHECK THE GIMBAL PINS AFTER AN INCIDENT), 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 TO BE REASSEMBLED TO FLIGHT CONDITION). 1G71 3U3 U H9EU E19EU 20081112 NE 2008 11 12 CA080722004 220080718G7314 SEAL CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL FUEL PUMP LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 4973 (CAN) ON DAILY INSP, FUEL WAS DISCOVERED IN THE OIL SEAL DRAIN COLLECTOR CAN. FURTHER INVESTIGATION FOUND FUEL LEAKING FROM THE SEAL ON THE FUEL HIGH PRESSURE PUMP. THERE WAS NO INDICATION OF GREASE WASH OUT OF THE FCU BRG. THE FUEL PUMP WAS REPLACED WITH A SERVICEABLE UNIT. 1H71 3T3 T A37CE E4EA 5 CP60GL 20081230 EU 2008 12 30 CA080722005 120080716G6230350A37122021 STOP TMECA SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE M/R SHAFT CRACKED W O OTHER O OTHER NRNOT 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 OF 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 NOTIFIED OF THE DEFECT AND THE PART WAS REPLACED. 1G71 3U3 U H9EU E19EU 20081112 EA 2008 11 12 CA080722007 120080718G5700C6FSM244335 BUSHING DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL WING LUG MISSING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BUSHINGS MISSING FROM WING PICKUP LUGS ON ORIGINAL FRAMES INSTALLED IN ACFT. 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20081112 2008 11 12 CA080722008 220080722G7414M3548 ROTOR MAGNETO BROKEN W K NONE P NO WARNING INDICATION ININSP/MAINT 1 CA 364 (CAN) MAGNETO INSPECTED FOR SB 2-08/3-08 COMPLIANCE. DISTRIBUTOR GEAR FAILED, ROTOR GEAR FAILED, CARBON BRUSH FAILED. DURING 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 120080722G7603S6130620173 THROTTLE PLATE SKRSKYS61 S61A 814210CNE FAILED W K NONE O OTHER ININSP/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 VENDOR 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 BRITTLE AS IT FAILED INSTANTLY UNDER MINIMAL PRESSURE WITHOUT BENDING. SUSPECTED BOGUS PARTS. 2G72 4U H2EA 20081112 NM 2008 11 12 CA080723001 120080720G32607002537 CONTROL UNIT DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE MLG MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING LDLANDING 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081112 NE 2008 11 12 CA080723002 220080708G7261 RETAINING NUT PWC PW308 PW308C 52182NE OIL PUMP ASSY DISLODGED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA 791 (CAN) THE LOW OIL PRESSURE WARNING ACTIVATED DURING TAKEOFF ROLL AND TAKEOFF WAS ABORTED. SUBSEQUENT INSP REVEALED THE OIL 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 320080718G6111 SEALANT AIRTRCAT802 AT802 0390305SW PWA PT6 PT6A67A 52043NE HARTZLHCB5M HCB5MA3 GL BLADE CLAMP FAILED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB OUT PILOT EXPERIENCED A BUILD UP OF GREASE ON WINDSHIELD. PILOT ABORTED LOAD IN DESIGNATED AREA AND RETURNED TO BASE. UPON INSP GREASE APPEARED TO BE COMING FROM 1 OR 2 BLADE CLAMPS. BLADE CLAMP SEALS WERE REPLACED IN BOTH UNITS. NO OBVIOUS DAMAGE WAS FOUND ON REMOVED SEALS OR PROP ASSY. SEALANT MAY HAVE FAILED. ACFT WAS RETURNED TO SERVICE AFTER GROUND FUNCTION CHECKS. 1L71 3T4 TNCA19SW E26NE 6 CP44GL 20081112 EU 2008 11 12 CA080723004 120080527G6710350A27134320 STOP AEROSPAS355 AS355F2 8680812EU ALLSN 250C 250C20B 03013GL COLLECTIVE DAMAGED W O OTHER W INADEQUATE Q C NRNOT 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 POINT 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 PLATE ON THE UPPER PART OF THE COLLECTIVE QUADRANT. POSITIONING THIS STOP PLATE (P/N 350A27-1343-20) IAW INSTRUCTIONS PROVIDED 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 1G72 3U3 U H11EU E4CE 20081112 EU 2008 11 12 CA080723005 120080722G2730Z4244120000 CABLE ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA MUHBR MTV MTV9* EU ELEV TRIM TAB FRAYED W K NONE O OTHER ININSP/MAINT 1 CA 1899 (CAN) CABLE WAS DISCOVERED FRAYED DURING REGULARY SCHEDULED MAINT. 1L71 3O3 O0 A76EU 1E10 5 CP24NE 20081112 CE 2008 11 12 CA080723006 120080721G2421 ALTERNATOR CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL FAILED W O OTHER H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA (CAN) DURING CRUISE, PILOT NOTICED KX155 NAV/COM FLASHING ITS DISPLAY AND VOR NEEDLE ERATIC. PILOT DECLARED NORDO AND LANDED SAFELY WITHOUT FURTHER INCIDENCE. MAINT ATTEPTED TO START ACFT AND DISCOVERED BATTERY ALMOST DEAD. ACFT CHARGING SYS 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 RED 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. 1H71 3O3 ONT3A19 E223 5 NP50GL 20081112 WP 2008 11 12 CA080724001 120080707G2822C81878 PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL BOOST FAILED W O OTHER J WARNING INDICATION CRCRUISE 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. 1G71 3O3 O H11NM 1E4 20081112 WP 2008 11 12 CA080724003 220080717G723031037081 BEARING SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33110UG 01514WP MCAULY4HFR344HFR34C652 NE COMPRESSOR SPALLED W K NONE O OTHER ININSP/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 DISSASEMBLY OF THE ENGINE GEAR BOX IT WAS FOUND THAT THE COMPRESSOR BALL BEARING WAS STARTING TO HAVE METAL SPAWLING COMING FROM THE INNER RACE. THE ENGINE WAS REPAIRED ON WING AND WITH A NEW COMPRESSOR BEARING ALL METAL FLUSHED FROM ENGINE AND THE A/C WAS RETURNED TO SERVICE WITH NO MORE ISSUES. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20081112 CE 2008 11 12 CA080724004 120080721G7720 INDICATOR BEECH 100 100BEECH 1152916CE GARRTTTPE331TPE3316252B 01514WP HARTZLHCB4T HCB4TN5 GL ITT MALFUNCTIONED W O OTHER N FALSE WARNING CRCRUISE 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. UPON RETURN TO BASE, MAINT TROUBLESHOT THE ITT SYS AND DISCOVERED THAT THE ITT HARNESS HAS 3000 OHMS TO GROUND WHERE THE MINIMUM LIMITS ARE 100000 OHMS. A NEW HARNESS HAS BEEN ORDERED AND WILL BE INSTALLED. THIS SDR HAS BEEN REPORTED PREVIOUSLY UNDER SDR’S 20080103005 AND 20070223002. SUPPLEMENTARY SDR TO FOLLOW WITH ASSY AND PART FAILURE INFORMATION. 1L72 3T4 T A14CE E2WE 6 CP40EA 20081112 NE 2008 11 12 CA080724006 220080717G73210164548250 FUEL CONTROL TMECA ARRIELARRIEL1D1 60053NE ENGINE FAILED W K NONE O OTHER ININSP/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 ADJUST 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 120080722G3411 PITOT SYSTEM DOUG DC6 DC6B 3021712WP PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE NR 2 CLOGGED W C ABORTED TAKEOFF G MULTIPLE FAILURE TOTAKEOFF 1 CA (CAN) BOTH NR 1 AND NR 2 PITOT SYS INDICATED NO AIRSPEED ON TAKEOFF RUN. TAKEOFF WAS ABORTED. BUGS AND SIMILAR DEBRIS FOUND IN BOTH PITOT SYS. APAR LINES BLOWN OUT, PITOT SYS FUNCTION CHECKED SERVICEABLE. 2L74 4R3 R 6A4 ATC14 6 CP871 20081113 2008 11 13 CA080724008 420080628G61221219310 PLUG WOODWARD DIAMONDA40 DA40 2990002GL HARTZLHCC2Y HCC2YR1 GL PROP GOVERNOR FAILED W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CLCLIMB 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 SOMETHING 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. THE LANDING WAS ACCOMPLISHED WITHOUT ANY PROBLEMS AND NO FURTHER DAMAGE WAS SUSTAINED TO THE ACFT. BEGAN THE INVESTIGATION INTO WHAT CAUSED THE FAILURE. AFTER ELIMINATING SOME OTHER PROBABLE CAUSES WE CAME TO THE PROPELLER GOVERNOR. IT LOOKS AS IF A SCREW PLUG BACKED OUT OF AN INTERNAL PASSAGE WITHIN THE GOVERNOR, DUMPING THE OIL PRESSURE AND CAUSING THE PR1L71 3O NTA47CE 5 CP920 20081112 CE 2008 11 12 CA080725001 120080709G246070002450 CIRCUIT BREAKER CESSNA560 560XL 2076702CE PWC 545 PW545B NE LT POWER FEED TRIPPED W O OTHER O OTHER CRCRUISE 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. 2L72 4F4 FRTA22CE E00059EN 20081112 NE 2008 11 12 CA080725002 120080716G291366WAP2001 BOLT SKRSKYS61 S61N 8142104NE GE CT58 CT581401 30011NE HYD PUMP BROKEN W K NONE O OTHER ININSP/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. 2G72 4U4 U 1H15 1E3 20090102 EU 2009 1 2 CA080725003 120080720G2910 HYDRAULIC SYSTEM UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE MALFUNCTIONED W K NONE F FLT CONT AFFECTED NRNOT REPORTED 1 CA (CAN) AT GROUND IDLE, THE NORMAL PROCEDURE IS TO TEST ACCUMULATORS BY PUSHING THE ACCUMULATORS BUTTON ON, AND THE HYD LIGHT ILLUMINATES , AND PROCEED TO TEST THE ACTUATORS BY MOVING THE CYCLIC FWD AND AFT, ABOUT 4-5 INCHES TRAVEL, EIGHT TIMES, 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. THE 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 RESIS1G72 3U3 UNCR0001RD E34NE 20081112 NM 2008 11 12 CA080728001 120080723G243220412 BATTERY DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF* NE MASTER OVERTEMP W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 14134594 (CAN) DURING CRUISE THE CREW RECEIVED A MAIN BATTERY HOT WARNING MESSAGE. THE HIGH TEMP WAS CONFIRMED ON THE BATTERY TEMP 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 BEEN RETURNED TO THE COMPANY IN-HOUSE COMPONENT SHOP TO DETERMINE THE CAUSE OF THE THERMAL RUN-AWAY. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081112 NM 2008 11 12 CA080728003 120080725G2710 PCU BOEING727 727243 138408DNM PWA JT8 JT8D9A 52048NE AILERONS FAILED W O OTHER KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) ENROUTE, CREW NOTICED HYD SYS (A) QUANTITY DECREASING RAPIDLY. SYS (A) HYDR WERE SHUTOFF AND EMERGENCY DECLARED. UPON ARRIVAL AT DESTINATION, A/C REQUIRED TOWING TO RAMP WHERE MAINT DISCOVERED THE AILERON PCU HAD FAILED. THE AILERON PCU WAS REPLACED AND A/C RETURNED TO SERVICE. 2L73 4F4 FRTA3WE E2EA 20081112 EU 2008 11 12 CA080728004 120080708G25308001060000LH OVEN AIRBUS310 A310304 3930339EU DIRTY W A UNSCHED LANDING WB INADEQUATE Q C SMOKE/FUMES/ODORS/SPARKS NRNOT 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 OVENS 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. 2L72 4F RTA35EU 20081112 EU 2008 11 12 CA080728005 120080721G2897NSA931322100 CIRCUIT BREAKER AIRBUS310 A310300 3930305EU GE CF6 CF680C2A5 NE FUEL PUMP BURNED W O OTHER H ELECT. POWER LOSS-50 PC TXTAXI/GRND HDL 1 CA (CAN) DURING TROUBLESHOOTING OF THE INOPERATIVE LT OUTER TANK FUEL PUMP (DEACTIVATED IAW MEL) THE CIRCUIT BREAKER 3QA WAS FOUND BURNED, BODY CRACKED AND ONE LEG MISSING. CIRCUIT BREAKER WAS REPLACED AND SYS TESTED SERVICEABLE. A DETAILED VISUAL INSPECTION CAMPAIN WAS INITIATED TO INSPECT ALL CIRCUIT BREAKERS IN THE 101VU ELECTRICAL PANEL. 2L72 4F4 FRTA35EU E13NE 20081112 NM 2008 11 12 CA080728006 120080725G2897F759857SC WIRE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF* NE SWITCH CHAFED W O OTHER N FALSE WARNING TXTAXI/GRND HDL 1 CA 4050140501 (CAN) DURING TAXI, NR2 TANK FUEL LOW LEVEL CAUTION LIGHT ILLUMINATED. MAINT GROUND RUN AND NR2 TANK LOW LEVEL LIGHT INTERMITTENT. ACFT DISPATCHED UNDER MEL FOR FUEL LOW LEVEL INDICATION. LATER MAINT INSP DURING SWITCH REPLACEMENT, FOUND SWITCH WIRE CHAFED ON CONDUIT. SWITCH ASSY REPLACED. (NOTE: PART IS CONSIDERED AN EXPENDABLE AND PART TIMES NOT TRACKED. TIME PROVIDED ARE ACFT TIMES). 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081112 SW 2008 11 12 CA080728007 120080722G5280 STRUCTURE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE MLG DOOR BENT W O OTHER J WARNING INDICATION APAPPROACH 1 CA (CAN) ON APPROACH PILOT EXTENDED GEAR AND HAD GREEN INDICATION FOR NOSE AND LT MAIN GEAR ONLY, INTRANSIT LIGHT WAS ON FOR 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 FRONT EDGE OF THE GEAR DOOR AND WAS BENT WHEN THE GEAR WAS SELECTED DOWN. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20081112 2008 11 12 CA080728008 420080722G612231039391 FITTING SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE PROP GOVERNOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON INSPECTION, IT WAS DISCOVERED THAT THERE WAS AN OIL LEAK AROUND THE RT ENGINE PROP GOVERNOR. UPON FURTHER INSPECTION IT WAS FOUND THAT THE FITTING WAS CRACKED HALF WAY AROUND THE FITTING. FITTING REPLACED AND ACFT RETURNED TO SERVICE. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20081112 EU 2008 11 12 CA080728009 120080719G6410355A12004008 BLADE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE TAIL ROTOR CRACKED W K NONE O OTHER ININSP/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 MFG. 1G71 3U3 U H9EU E19EU 20081112 SW 2008 11 12 CA080728010 120080704G6730212076005011 PILOT VALVE BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA LT CYCLIC CHATTERING W A UNSCHED LANDING EF VIBRATION/BUFFET FLT CONT AFFECTED CRCRUISE 1 CA (CAN) ACFT ENCOUNTERED VIBRATION, FELT THROUGH FLIGHT CONTROLS. VIBRATION WORSENED RAPIDLY DURING RETURN TO BASE. UPON ARRIVAL TO BASE, ENGINEER INSPECTED ACFT AND FOUND LT CYCLIC SERVO PILOT VALVE TO BE CHATTERING EXCESSIVELY, CAUSING UNCOMMANDED 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. 1G71 4U4 U H4SW E22EA 20081112 EU 2008 11 12 CA080729001 120080718G2120 GUARD PILATSPC12 PC1247 7090552EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL REEFER PACK CUT W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/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 STOP THE BELT FROM GOING OUT OF THE GEAR IS WORN OUT ALSO, CHAFING THE BELT PLASTIC GUARD. THE GUARD IS CUT. 1L71 4T4 TRTA78EU E26NE 5 CP210NE 20081112 SO 2008 11 12 CA080729003 120080724G5310MS212505 BOLT LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE FUSELAGE FAILED W A UNSCHED LANDING O OTHER CRCRUISE 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 THAT AN APPARENT FASTENER FAILURE COMMON TO THE STA 577 BEAM AND THE DRAG ANGLE GENERATED THE GAP. THE ACFT WAS REPOSITIONED UNDER PERMIT WHERE FURTHER ASSESSMENT IS ONGOING. 2H74 4T4 T A1SO E282 6 CP906 20081113 EU 2008 11 13 CA080729006 120080727G2913AIR29804 COVER LKHEED BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU HYDRAULIC PUMP LEAKING W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 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 NR OF TIMES. EMERGENCY U/C ACTUATION WAS NOT REQUIRED. UNDER INSPECTION THE RT HYDRAULIC PUMP WAS FOUND TO BE LEAKING. THE 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. 2L72 3T4 T A24EU A196 20081112 GL 2008 11 12 CA080729007 120080725G5730 SKIN DIAMONDA40 DA40 2990002GL WING DEBONDED W K NONE O OTHER ININSP/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 SAFETY ISSUE BUT ARE WORKING QUICKLY AND DILIGENTLY TO GET TO ROOT CAUSE AND CORRECTIVE ACTION. 1L71 3O NTA47CE 20081112 NE 2008 11 12 CA080730001 220080623G72204037T84P03 NUT GE CF34 CF343B1 30070NE ENGINE MISSING W K NONE O OTHER ININSP/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 120080730G2611774001 SMOKE DETECTOR BOEING727 727225 1384077NM PWA JT8 JT8D15 52051NE NR 6 FAILED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 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. 2L73 4F4 F A3WE E2EA 20081112 SO 2008 11 12 CA080730003 220080730G8530 SPRING ECI CONT O520 IO520F 17032SO EXHAUST VALVE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 13 (CAN) CYLINDER WAS PULLED DUE TO LOW COMPRESSION. WHEN THE ROCKER COVER WAS REMOVED IT WAS DISCOVERED THAT BOTH THE INNER AND OUTER EXHAUST VALVE SPRINGS WERE BROKEN INTO MANY PIECES. 3 O E5CE 20081112 EA 2008 11 12 CA080730004 120080714G552285520056 SKIN DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4061940619 (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 DAMAGE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081112 NE 2008 11 12 CA080730005 220080728G73210164548540 FUEL CONTROL SNIAS 350 AS350* EU TMECA ARRIELARRIEL1B 6OO30NE ENGINE FAILED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) FLUCTUATION OF NG (+/- 2 PERCENT) IN CRUISE FLIGHT. ACFT LANDED AT THE BASE NORMALLY. ENGINE INSPECTED. RUN-UP CARRIED OUT, NG FLUCTUATION CONFIRMED ON THE GROUND (82.5 TO 84.5 PERCENT), NR FLUCTUATION ON THE GROUND (374 - 380). FCU REPLACED (PART REMOVED WAS 1369.6 HOURS TSO). TEST FLIGHT CONDUCTED AFTER FCU REPLACEMENT AND FOUND SATISFACTORY. 1G71 3U3 U H9EU E19EU 20081112 EA 2008 11 12 CA080730006 220080713G7200 ENGINE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA FAILED W E ENGINE SHUTDOWN J WARNING INDICATION CLCLIMB 1 CA (CAN) 10 MINUTES AFTER TAKEOFF, THE ENGINE OIL PRESSURE AND TORQUE INDICATION DECREASED BELOW ALLOWABLE LIMITS. THE ENGINE WAS SHUTDOWN AND SECURED BY THE FLIGHT CREW. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA13NM E00062EN 20081112 EA 2008 11 12 CA080730007 220080706G7250 ENGINE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NR 1 ERRATIC W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA (CAN) DURING TAKEOFF ROLL THE NR 1 ITT DROPPED TO 230 DEGREES AND WAS ERRATIC. THE PILOT ELECTED TO ABORT THE TAKEOFF AND RETURNED TO THE GATE. TROUBLESHOOTING DISCLOSED FAULT CODE (FC) 973 T6 OPEN CIRCUIT. FURTHER INTERROGATION OF FC CONFIRMED 973 PRESENT ON BOTH A&B CHANNELS. THE T6 HARNESS WAS REPLACED AND THE ACFT RETURNED TO SERVICE. ERRATIC ITT INDICATION WAS NOTED BY THE CREW DURING THE PREVIOUS FLIGHT. 2H72 4T4 TRTA13NM E00062EN 20081112 NE 2008 11 12 CA080730008 220080503G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE POWER LOSS W BA EMER. DESCENT UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB AT APPROX 3,000 FEET ABOVE GROUND LEVEL, PILOT HEARD A LOUD BANG AND EXPERIENCED COMPLETE LOSS OF POWER . PILOT DECLARED EMERGENCY AND PERFORMED A DEAD STICK LANDING. AN UNEVENTFUL LANDING WAS ACCOMPLISHED. POST INSP REVEALED CT BLADE DISTRESS. ENGINE WAS REMOVED AND SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1H71 3T3 T A37CE E4EA 20081112 CE 2008 11 12 CA080730009 120080424G7930 OIL SYSTEM CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE ENGINE LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/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 TEMPERATURE. THE PILOT IMMEDIATELY SHUTDOWN THE ENGINE. ON-GROUND INSP, REVEALED METAL IN OIL FILTER AND ON THE CHIP DETECTOR. THE ENGINE WAS REMOVED AND SHIPPED FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1H71 3T3 T A37CE E4EA 20081112 SW 2008 11 12 CA080731001 120080727G322255010011 DRAG BRACE SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL MLG CRACKED W K NONE O OTHER ININSP/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 FOUND CRACKED IN HALF AND SEPARATED FROM THE DRAG BRACE. REPLACED WITH A SERVICEABLE DRAG BRACE, RIGGED AND ADJUSTED WITH NO FURTHER ISSUES. 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20081112 SW 2008 11 12 CA080731002 120080729G6320212040143001 BEARING BELL BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE TRANSMISSION ROUGH W K NONE O OTHER ININSP/MAINT 1 CA 875 (CAN) UPON A SCHEDULED INSPECTION OF THE TRANSMISSION WAFFER FILTER AN EXCESSIVE AMOUNT OF FERROUS METAL WAS FOUND. THERE 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 IN THE HYDRAULIC PUMP AND TACHOMETER DRIVE ASSEMBLY OFFSET QUILL WAS FOUND TO BE ROUGH. 1G71 4U4 U H1SW E17EA 20081112 EU 2008 11 12 CA080801001 120080726G2910 FLEX LINE BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU ROTOL R4304 R2124304 EU HYD SYSTEM CHAFED W O OTHER KJ FLUID LOSS WARNING INDICATION APAPPROACH 1 CA (CAN) ON APPROACH, THE CREW OBSERVED A LOSS OF HYDRAULIC PRESS AFTER GEAR WAS SELECTED DOWN. THE ACFT LANDED WITHOUT FURTHER INCIDENT. MAINT IDENTIFIED THE HYDRAULIC LINE FROM THE PUMP THE HIGH PRESSURE FILTER AS THE SOURCE OF THE LEAK. THE LINE WAS REPLACED AND THE ACFT RETURNED TO SERVICE. 2L72 3T4 T A24EU A196 6 CP899 20081112 EU 2008 11 12 CA080801002 120080728G2460SM400D30 CONTACT AEROSPATR42 ATR42320 8680930EU PWA PW121 PW121 52124NE HAMSTD14SF 14SF5 NE DC BUSS FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 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. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20081112 NE 2008 11 12 CA080801003 220080728G7200 ENGINE BOEING727 727233 138408ANM PWA JT8 JT8D15 52051NE POWER LOSS W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 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. THE ACFT FERRIED FOR ENGINE REPLACEMENT. 2L73 4F4 FRTA3WE E2EA 20081112 EU 2008 11 12 CA080801004 120080723G5754A5724853200000 ACCESS PANEL AIRBUS310 A310300 3930305EU GE CF6 CF680C2* GL SLAT TRACK MISSING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON ARRIVAL, LEADING EDGE SLAT TRACK ACCESS PANEL 512HB FOUND MISSING. ADJACENT PANEL 512JB ALSO FOUND DAMAGED. LOST IN FLIGHT. PANEL 512HB REPLACED AND PANEL 512JB REPAIRED IAW SRM. 2L72 4F4 FRTA35EU E23EA 20081112 CE 2008 11 12 CA080801005 120080729G2750C1452501 MOTOR CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL TE FLAPS UNSERVICEABLE W O OTHER F FLT CONT AFFECTED CLCLIMB 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. 1H71 3T3 T A37CE E4EA 5 CP60GL 20081112 NE 2008 11 12 CA080801007 220080801G7414 BEARING ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO WORN W K NONE O OTHER ININSP/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 ALLOWABLE 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 HOUSING. THE REST OF THE 500 HOUR INSP WAS CARRIED OUT AND THE MAG WAS RETURNED TO SERVICE. 1G71 3O3 O H11NM 1E4 20081112 NE 2008 11 12 CA080801008 220080801G7414 COIL ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO LOOSE W K NONE O OTHER ININSP/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 COIL CLAMPS WERE REPLACED AND THE COIL WAS NO LONGER LOOSE IN THE HOUSING. THE REST OF THE 500 HOUR INSP WAS CARRIED OUT AND THE MAG WAS RETURNED TO SERVICE. 1G71 3O3 O H11NM 1E4 20081112 EU 2008 11 12 CA080804001 120080731G3340RG1007AA03 FLASHER AIRBUS310 A310304 3930339EU GE CF6 CF680C2A5 NE EXTERIOR LIGHT BURNED W K NONE O OTHER ININSP/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. 2L72 4F4 FRTA35EU E13NE 20081112 EU 2008 11 12 CA080804002 120080801G2131 CONTROLLER AIRBUS330 A330342 EU RROYCERB211 RB211TRENT77 NE CABIN PRESSURE MALFUNCTIONED W O OTHER O OTHER CRCRUISE 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 TESTED SERVICEABLE. AFTER RETURN FLIGHT TO BASE, BOTH SAFETY VALVES WERE REPLACED AS PRECAUTIONARY. 1L72 4F4 FRTA46NM E39NE 20081112 CE 2008 11 12 CA080804003 120080718G7931 OIL SYSTEM CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ENGINE LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 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 LANDING FOLLOWED. TROUBLESHOOTING COULD NOT IDENTIFY THE PROBLEM AND THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L72 4F4 F A22CE E1NE 20081113 GL 2008 11 13 CA080805001 120080707G3246 FLOAT AMTR TUNDRATUNDRA 05607NZGL LEFT NOSE BROKEN W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) ON RETRACTING LANDING GEAR AFTER TAKEOFF IT WAS NOTICED THAT THE LT NOSE GEAR ONLY PARTIALLY RETRACTED. GEAR WAS CYCLED 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 FLOAT COMPANY, THE MANUFACTURER WILL SUPPLY 2 NEW RODS 7/16" THICK - OLD RODS 3/8" THICK. 1H71 3O NTEXPA1H71 20081113 EA 2008 11 13 CA080805002 220080728G7313311991901 SLEEVE BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA FUEL NOZZLE WRONG PART W K NONE W INADEQUATE Q C ININSP/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 CORRECT PART NR WERE INSTALLED AND THE ENGINE RETURNED TO SERVICE. 1L72 3T4 TRT3A20 E4EA 20081112 SW 2008 11 12 CA080805003 120080803G5302 SKIN BELL 407 407 1182206SW ALLSN 250C 250C47B GL TAILBOOM CRACKED W K NONE O OTHER ININSP/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. 1G71 3U3 UO H2SW E1GL 20081119 NM 2008 11 19 CA080805005 120080731G3231483025 SEQUENCE VALVE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU MLG DOOR INOPERATIVE W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 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. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081119 NM 2008 11 19 CA080805006 120080801G29136617303 PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA HYD SYSTEM DAMAGED W A UNSCHED LANDING J WARNING INDICATION APAPPROACH 1 CA (CAN) DURING APPROACH, NR 2 HYD PUMP CAUTION LIGHT ILLUMINATED. PTU WAS SELECTED ON SO ALL SYSTEMS OPERATED NORMAL FOR ROUTINE LANDING. EDP CASE HALVES LOOSE AND PUMP NOT MAKING PRESSURE. PUMP REPLACED. 2H72 4T4 TRTA13NM E00062EN 20081119 EA 2008 11 19 CA080805007 220080801G853065678 BOLT CURTIS GRUMANTS2 TS2ACALFORST3951102WP WRIGHTR1820 982C9HE2 67020EA EXAUST ROCKER SHEARED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CRCRUISE 1 CA (CAN) IN CRUISE FLIGHT, THE NR 1 ENGINE LOST POWER AND BEGAN TO BACKFIRE. ENGINE SHUT DOWN AND FEATHERED. UPON INSPECTION OF ENGINE NR 9 CYLINDER EXHAUST ROCKER BOLT FOUND SHEARED AT NUT AND BOLT HAD DISENGAGED FROM CYLINDER EAR ASSEMBLY. NEW BOLT AND NUT ASSEMBLY INSTALLED, VALVE CLEARENCES ADJUSTED, MAIN OIL SCREEN AND NO CONTAMINATION FOUND. ENGINE GROUND RUN SERVICEABLE AND RETURNED TO SERVICE. 2H72 4R4 R A25WE E259 20081119 NE 2008 11 19 CA080805008 220080805G7414106006169 MAGNETO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE INOPERATIVE W K NONE O OTHER ININSP/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 (0.0015 INCH IS MAX. ALLOWABLE). WHEN DISASSEMBLED THE WASHER THAT RETAINS THE DISTRIBUTOR GEAR ON THE SHAFT WAS SLIGHTLY LOOSE. 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 CLAMP SCREWS WERE REMOVED TO INSPECT THIS THE SCREWS WERE FOUND TO BE NOT VERY TIGHT. THE ROTOR BEARINGS WERE RESHIMMED, THE DIST. GEAR SHAFT WAS REFLARED, AND THE COIL CLAMP SCREWS WERE TIGHTENED. THE REST OF THE 500 HOUR INSP. WAS CARRIED OU1G71 3O3 O H11NM 1E4 20081119 NE 2008 11 19 CA080805009 220080805G741410160858 HOUSING ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO CRACKED W K NONE O OTHER ININSP/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 HSG NEXT TO THE BRG AREA. WE HAVE NOTICED A HIGHER NR OF THESE NEW STYLE HSGS CRACKING AT THIS LOCATION. OLDER CASTINGS WOULD OCCASIONALLY CRACK IF THE MOUNTING NUTS WERE OVERTORQUED, WHEREAS THESE NEW ONES SEEM TO BE WEAKER AND CRACK MORE OFTEN. THE MAG WAS REMOVED FROM SERVICE. 1G71 3O3 O H11NM 1E4 20081119 NM 2008 11 19 CA080805010 120080802G3060 HEATER HAMSTD DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE PROP BLADE BURNED W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA 1031610316 (CAN) THE CREW OBSERVED SPARKS COMING FROM THE FRONT OF THE RT ENGINE. THE CREW SHUTDOWN THE ENGINE IN FLIGHT AND DECLARED 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 BLADE ANTI-ICING SYS TESTED AND THE ACFT RETURNED INTO SERVICE. THE BLADE WAS SENT TO AN EXTERNAL SHOP FOR REPAIR. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081119 GL 2008 11 19 CA080805011 220080801G72303896888M SCROLL BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL COMPRESSOR CRACKED W K NONE O OTHER ININSP/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 NEAR THE RT ELBOW. ACFT WAS GROUNDED. COMPRESSOR ASSY IS AN ON-CONDITION ITEM BUT THERE IS AN INSP EVERY 2000 HOURS. AS YOU CAN SEE THIS SCROLL WAS VERY HIGH TIME. SINCE LAST 2000 HOUR INSP 374.8 HOURS. TO THE 2000 HR INSP INVOLVES INSPECTING THE SPUR ADAPTER GEAR AND ITS MATING GEAR. BELIEVE THAT THE SCROLL IS THE SAME TIME AS THE COMPRESSOR ASSY. 1G71 3U3 U H2SW E1GL 20081117 CE 2008 11 17 CA080805012 120080730G32341013841377 SELECTOR BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE LANDING GEAR DEFECTIVE W O OTHER J WARNING INDICATION APAPPROACH 1 CA (CAN) UPON APPROACH THE CREW WAS UNABLE TO EXTEND THE GEAR NORMALLY AND HAD TO PERFORM AN EMERGENCY EXTENSION. A SUCCESSFUL LANDING WAS CARRIED. UPON INVESTIGATION, IT WAS DETERMINED THE PROBLEM WAS IN THE LANDING GEAR SELECTOR ASSY. THE PIVOT 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, WHEN THE CREW SELECTED GEAR DOWN THE SWITCHES WERE NOT RELEASED AND THE GEAR REMAINED IN THE RETRACTED POSITION. THREAD LOCKING COMPOUND WAS APPLIED TO THE PIVOT SCREW AND THE SCREW WAS TIGHTENED. SEVERAL GEAR SWINGS WERE SUCCESSFULLY COMPLET1L72 4T4 T A24CE E4EA 20081117 2008 11 17 CA080805013 420080805G611335323012 BULKHEAD PIPER PA28 PA28151 7102805SO LYC O320 O320E3D 41508EA SNSNCH74D 74DM EA SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ANNUAL INSP FWD SPINNER BULKHEAD WAS FOUND TO BE CRACKED AT SCREW ATTACHMENT HOLE. NEW PART WAS ORDERED FROM MFG IAW APPLICABLE PARTS CATALOGUE. NEW PART RECEIVED WAS STAMPED WITH CORRECT PN AS ORDERED, BUT WAS PHYSICALLY DIFFERENT IN DEPTH AND WOULD NOT FIT. MFG WAS CONTACTED (VIA AVIATION UNLIMITED AND A SECOND SPINNER BACK PLATE IS BEING SHIPPED). 1L71 3O3 O 2A13 E274 5 NP88614 20081117 SO 2008 11 17 CA080805014 220080709G8530 CAMSHAFT CESSNA185 A185F 2072821CE CONT O550 IO550D 17042SO MCAULYD3A34 D3A34C401 GL ENGINE CORRODED W K NONE O OTHER ININSP/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 TSOH. UPON TEARDOWN, CRANKSHAFT HAD CORROSION, AND THE OIL PUMP WAS DAMAGED DUE TO METAL CONTAMINATION IN ENGINE, AND MORE 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. 1H71 3O3 O 3A24 E3SO 5 CP47GL 20081117 NE 2008 11 17 CA080806001 220080723G7321 FUEL CONTROL BEECH 200 200CBEECH 1152926CE PWA PT6 PT642A NE ENGINE MALFUNCTIONED W O OTHER F FLT CONT AFFECTED LDLANDING 1 CA (CAN) DURING LANDING, THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION WHICH CAUSED THE PILOT TO HAVE DIFFICULTY CONTROLLING THE ACFT, CAUSING IT TO SKID IN THE GRASS AND MUD AT THE SIDE OF THE RUNWAY. THE FUEL CONTROL WAS REPLACED AND THE RIGGING WAS ADJUSTED. THE FUEL CONTROL WILL BE INVESTIGATED AND UPDATES PROVIDED. 1L72 4T4 T A24CE E4EA 20081117 2008 11 17 CA080806002 420080729G31608221577012 DISPLAY BOMBDRBD100 BD1001A10 1390044GL HNYWL AS907 AS90711A 33908WP COCKPIT MALFUNCTIONED W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS TXTAXI/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. 2L72 4F4 FRTT00005NYE00010LA 20081117 EA 2008 11 17 CA080806003 220080726G7260 GEARBOX BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA ENGINE DISCONNECTED W O OTHER X ENGINE FLAMEOUT APAPPROACH 1 CA (CAN) DURING FINAL APPROACH, THE ENGINE FLAMED OUT. RELIGHT ATTEMPT WAS UNSUCCESSFUL. AN UNEVENTFUL SINGLE ENGINE LANDING 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. 2L72 4T4 TRTA24CE E4EA 20081117 NE 2008 11 17 CA080806004 220080729G7200 ENGINE PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE MALFUNCTIONED W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION TOTAKEOFF 1 CA (CAN) DURING T/O, THE ENGINE STARTED TO SURGE FOLLOWED BY A RISE IN INDICATED TEMPERATURE. THE PILOT ELECTED TO RETURN TO HIS POINT OF DEPARTURE, WHERE A SAFE LANDING WAS PERFORMED. THE ENGINE TEMP REACHED 970°C FOR ONE MINUTE. THE ENGINE WILL BE REMOVED AND FWDED FOR INVESTIGATION AND REPAIR. 1L71 3T4 TRTA78EU E26NE 20081117 CE 2008 11 17 CA080806005 120080801G8120 TURBOCHARGER BEECH 60 B60 1153605CE LYC O541 TIO541E1C4 41536EA HARTZLHCF3Y HCF3YR2 GL LT ENGINE MALFUNCTIONED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 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. 1L72 3O3 O A12CE E10EA 5 CP31EA 20081117 EA 2008 11 17 CA080806006 120080804G7110 COWLING CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE NR 2 ENGINE DEPARTED W K NONE P NO WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) AS INDICATED BY MAINT CONTROL, ACFT DEPARTED. MISSING COWLING FROM NR2 ENGINE WAS DISCOVERED DURING WALKAROUND INSP BY GROUND MAINT. IT WAS ALSO APPARENT THAT PORTIONS OF THE COWLING THAT DEPARTED ENGINE, STRUCK THE LEADING EDGES OF THE LT AND RT HORIZONTAL STAB. CREW DID NOT HAVE ANY ABNORMAL INDICATIONS DURING FLIGHT, IAW MAINT CONTROL COMMENT TO FSR. PLEASE REFER TO ADR RRAD-C08-21754681. 2L72 4F4 FRTA21EA E15NE 20081117 NE 2008 11 17 CA080806007 220080805G7260 GEARBOX CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF348E5A1 30062NE NR 1 ENGINE DEFECTIVE W EA ENGINE SHUTDOWN UNSCHED LANDING K FLUID LOSS CRCRUISE 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, THEY REMOVED THE DRAIN MAST AND INSTALL PLASTIC BAG TO THE DIFFERENT DRAIN LINES. AFTER STARTING THE ENGINE, THE PLASTIC BAG FOR THE ACCESSORY GEAR BOX DRAIN WAS FULL OF OIL. SHUTDOWN THE ENGINE, THEY ARE NOW WAITING FOR THE MRP TO CHANGE THE AGB. 2L72 4F4 FRTA21AE E00063EN 20081117 NM 2008 11 17 CA080806008 120080730G213388060B010003 OUTFLOW VALVE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU CABIN PRESSURE FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) ACFT RETURNED DUE TO DEPRESSURIZATION AND BURNING ODOR IN THE COCKPIT. ATC CALLED LOCAL STANDBY, NO PAN/MAYDAY DECLARED. ACFT LANDED SAFELY AND WITHOUT INCIDENT. MAINT INTEROGATEED THE CDS, THE FOLLOWING CODES IDENTIFIED: AFT OUTFLOW VALVE FAIL CPC/OFF VALVE DATA FAIL. AFT OUTFLOW VALVE REPLACED. FUNCTION CHECKS OF ECS SYSTEM CARRIED OUT COULD NOT IDENTIFY ANY ODORS. AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081117 EA 2008 11 17 CA080806009 120080718G2730C6CTM102827 DRIVE ASSY DHAV C6CT10103 DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA ELEVATOR STRIPPED W A UNSCHED LANDING ZE SIGNIFICANT FAILURE REPORTVIBRATION/BUFFET CLCLIMB 1 CA (CAN) DURING CLIMB OUT AT 800 FEET ALTITUDE THE ACFT SUDDENLY STARTED TO SHAKE VIOLENTLY. THE PILOT ABORTED THE CLIMB, PROCEEDED STRAIGHT AHEAD FOR 4 MILES TO A LANDING STRIP AND LANDED SAFELY WITH NO INJURIES TO PERSONS ON BOARD. UPON INVESTIGATION 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 FLUTTER WHICH IN TURN CAUSED THE ELEVATOR TO FLUTTER INDUCING A VIOLENT SHAKING OF THE ACFT. 1H72 3T4 TRTA9EA E4EA 20081117 EA 2008 11 17 CA080806010 120080705G760374491147 CABLE ASSY CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE THROTLE BROKEN W EA ENGINE SHUTDOWN UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 CA 18500 (CAN) WHILE ATTEMPTING TO REDUCE RT ENGINE PWR AFTER TAKEOFF AND CLIMB, FLT CREW REPORTED THAT THE RT ENG WOULD NOT RESPOND TO THROTTLE LEVER INPUTS. THE RT ENGT WAS SHUTDOWN VIA FIRE PUSH SWITCH/LIGHT, ACFT DIVERTED TO IAD AND LANDED WITHOUT FURTHER INCIDENT. PRIOR TO TAKEOFF (ON TAXI OUT), THE FLT CREW NOTICED THAT THE RT THROTTLE LEVER WAS VERY STIFF THAT THEY ATTRIBUTED TO FRICTION LOCKS. UPON ADDING POWER FOR TAKEOFF, THEY NOTICED THAT THE THROTTLE LEVERS WERE VERY STIFF 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 RESPO2L72 4F4 FRTA21EA E15NE 20081117 CE 2008 11 17 CA080806011 120080716G2550D2010103 ARM DART D500560041 DART G G 2700102CE CARGO BAY CRACKED W O OTHER O OTHER UKUNKNOWN 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 ISSUED TO ALL CUSTOMERS WHO HAVE PURCHASED ASSEMBLIES. 1L71 3R TC674 20081117 EA 2008 11 17 CA080806012 220080801G8530SL360000WA20P CYLINDER HEAD BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL ENGINE CRACKED W A UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 CA 1854 (CAN) DURING CLIMB OUT WITH GLIDER IN TOW, THE PILOT REPORTED AN ENGINE VIBRATION. THEY IMMEDIATELY INSTRUCTED THE GLIDER TO RELEASE AND THEN PREFORMED A DOWN WIND LANDING AND RETURN TO HANGER. UPON SHUTDOWN AND INSP IT WAS FOUND THAT CYL NR1 HEAD HAD CRACKED AND SEPARATED FROM THE REMAINDER OF THE CYL. 1H71 3O3 O A21CE E286 5 NP874 20081117 SW 2008 11 17 CA080806013 120080728G3244280250 TIRE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL TAIL WHEEL DAMAGED W O OTHER O OTHER TXTAXI/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 THE TUBE. TIRE, BATCH NR WAS EITHER 0321672 OR 0422043. 1H71 3O3 O A21CE E286 5 NP874 20081117 SW 2008 11 17 CA080806014 120080727G3244280250 TIRE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL TAIL WHEEL DAMAGED W O OTHER O OTHER TXTAXI/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 THE TUBE. TIRE, BATCH NR WAS EITHER 0321672 OR 0422043. 1H71 3O3 O A21CE E286 5 NP874 20081117 SW 2008 11 17 CA080806015 120080728G3244280250 TIRE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2A 41514EA MCAULY1A200 1A200* GL TAIL WHEEL DAMAGED W O OTHER O OTHER TXTAXI/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 CUT THE TUBE. 1H71 3O3 O A21CE E286 5 NP874 20081117 SW 2008 11 17 CA080806016 120080625G571131692 SPAR BBAVIA8 8GCBC 1220803SW WING CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA 976 (CAN) PART FOUND CORRODED AT SPAR ATTACHMENT BOLT HOLE. 1H71 3O A21CE 20081117 SW 2008 11 17 CA080806017 120080625G571131692 SPAR BBAVIA8 8GCBC 1220803SW WING CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA 976 (CAN) PART FOUND CORODED AT SPAR ATTACHMENT BOLT HOLE. 1H71 3O A21CE 20081117 NM 2008 11 17 CA080807001 120080729G25205045802158003 SEAT BELT EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE CABIN FRAYED W K NONE O OTHER ININSP/MAINT 1 CA 3059 (CAN) F/A SEAT LAP BELTS AT DOOR LT NR1 AND DOOR RT NR2 FRAYED SEVERAL PLACES. 2L72 4F4 FRTA57NM E00070EN 20081117 NM 2008 11 17 CA080807002 120080806G25205045802158003 SEAT BELT 5045804078 EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE CABIN FRAYED W K NONE O OTHER ININSP/MAINT 1 CA 5704 (CAN) F/A SEAT LAP BELT AT DOOR LT NR1, NR2 AND DOOR RT NT2 FRAYED SEVERAL PLACES. 2L72 4F4 FRTA57NM E00070EN 20081119 NE 2008 11 19 CA080807003 320080718G61107149A0 THRUST WASHER HAMSTD HAMSTD23E 23E50 NE BLADE SHANK CRACKED W O OTHER E VIBRATION/BUFFET CRCRUISE 1 CA 471 (CAN) THE CRACKED BLADE RING IS PART OF THE BLADE ASSEMBLY. A CRACKED RING TYPICALLY RESTRICTS BLADE ROTATION AND CAN SET UP A VIBRATION. PROPELLER WAS REMOVED AND AFTER TEAR DOWN AND INSPECTION A CRACKED BLADE RING (THRUST WASHER) WAS DETERMINED AND OTHER DAMAGE TO THE BARREL ASSEMBLY. REPLACED BLADE THAT HAD THE BROKEN BLADE RING AND OTHER DAMAGED PARTS. PROPELLER ASSEMBLED BALANCED AND RETURNED TO SERVICE. 6 CP603 20081119 NM 2008 11 19 CA080807004 120080806G2761 HOUSING SMITHSIND DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ACTUATOR FRACTURED W D RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION TXTAXI/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 CAUTION 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081117 EA 2008 11 17 CA080807005 120080807G5520C6TEM101229 HINGE FITTING DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA ELEVATOR MISMANUFACTURED W O OTHER W INADEQUATE Q C ININSP/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. ADDITIONALLY TO MAKE THE TAB BOND PROPERLY TO THE ARM PAINT WAS REMOVED FROM THE ASSY AND NOT REFINISHED. THE AREA THIS PART IS INSTALLED IN IS EXPOSED TO THE ENGINE GAS PATH THEREBY MAKING IT A HIGH CORROSION AREA. ALSO UPON FURTHER EXAMINATION THE BONDING TAB WAS FOUND LOOSE DUE TO THE COUNTER SINK(S) SIZE. THIS PART HAS BEEN SENT BACK TO THE OEM FOR REPLACEMENT. 1H72 3T4 TRTA9EA E4EA 20081117 EU 2008 11 17 CA080807006 120080701G71601350P5103 SEAL SNIAS 350 AS350BA 8680817EU LYC LTS101LTS101750A1 41560NE ENGINE DAMAGED W E ENGINE SHUTDOWN X ENGINE FLAMEOUT ININSP/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. 1G71 3U3 UNCH9EU E5NE 20081117 2008 11 17 CA080807007 420080805G6113C4383 SUPPORT CESSNA180 180C 2072608CE CONT O470 O470K 17026SO MCAULY2A34C 2A34C203 GL SPINNER BROKEN W C ABORTED TAKEOFF E VIBRATION/BUFFET TOTAKEOFF 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. 1H71 3O3 O 5A6 E273 5 CP3EA 20081117 EU 2008 11 17 CA080808001 120080807G3233A5341130500200 ATTACH FITTING AIRBUS310 A310304 3930339EU GE CF6 CF680C2* GL NLG ACTUATOR BROKEN W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 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 INSTALLED. 2L72 4F4 FRTA35EU E23EA 20081117 CE 2008 11 17 CA080808002 120080731G8011534685 BEARING CONT 643259A18 CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HARTZLHCJ3Y PHCJ3YF1 GL STARTER WORN W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 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 SEAL 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. 1H71 3O3 O A4CE E5CE 5 CP36EA 20081119 2008 11 19 CA080808004 120080722G291025W711008171 LINE GARRTTTFE731TFE73140 29001NE HYD SYSTEM CRACKED W O OTHER KJ FLUID LOSS WARNING INDICATION APAPPROACH 1 CA 1219 (CAN) ON APPROACH INTO TORONTO PEARSON THE CREW NOTICED THAT THE AUX HYDRAULIC LOW PRESSURE ANNUNCIATOR AND FLUID LOW LEVEL LIGHT ILLUMINATED ON THE ACFT. AFTER STABILIZING THEIR APPROACH, ALL LIGHTS WENT OUT. AFTER LANDING THE LOW LEVEL LIGHT 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, THAT 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 220080805G7321 VALVE WOODWARD SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL FUEL CONTROL INOPERATIVE W O OTHER F FLT CONT AFFECTED TXTAXI/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 FOR REPAIR. 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20081117 SO 2008 11 17 CA080811001 120080729G24342CM353C1H ALTERNATOR LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE NR 2 FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION APAPPROACH 1 CA (CAN) ON DESCENT, CREW OBSERVED THE NR 2 GENERATOR FAIL WAS ILLUMINATED. THE NR2 ENGINE WAS SHUTDOWN AND THE ACFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINT REPLACED THE NR2 GENERATOR AND THE ACFT WAS RETURNED TO SERVICE. 2H74 4T4 T A1SO E282 6 CP906 20081117 NE 2008 11 17 CA080811002 220080806G8530 CYLINDER CNDAIRCL215 CL2151A10 1900320EA PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE NR 1 ENGINE DAMAGED W E ENGINE SHUTDOWN Z SIGNIFICANT FAILURE REPORT CRCRUISE 1 CA (CAN) NR 1 ENGINE BACKFIRED IN FLIGHT. ENGINE WAS SHUTDOWN AND PROP FEATHERED. NR 2 CYLINDER EXHAUST EAR WAS FOUND CRACKED. CYLINDER WAS REPLACED AND ENGINE GROUND RUNS SERVICEABLE. 2H72 4R3 RRTA14EA ATC14 6 CP871 20081117 NM 2008 11 17 CA080811003 120080810G3242214664 BRAKE ASSY 214664 DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE LANDING GEAR DAMAGED W O OTHER O OTHER TXTAXI/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 DAMAGE WAS NOTICED. THE BRAKE UNIT WAS REPLACED WITH A SERVICEABLE UNIT AND THE ACFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081117 SW 2008 11 17 CA080811004 120080808G2910205076302001 TUNING UNIT BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE HYDRAULIC SYS CRACKED W HA DEACTIVATE SYST/CIRCUITSUNSCHED LANDING KF FLUID LOSS FLT CONT AFFECTED CRCRUISE 1 CA 13967 (CAN) TUBE ASSY WAS REPLACED EARLIER IN APRIL 2008 DURING WINTER MAINT. SINCE SINGLE HYDR SYS PARTS ARE HARD TO FIND ITEMS, SERVICEABLE PART WAS INSTALLED WITH APPROPRIATE CERTIFICATION. VISUAL INSP DIDN`T REVEALED ANY DAMAGE AND NO LEAK WAS NOTICED AT THIS TIME. PART HAD 79 HRS SINCE INSTALLATION WHEN FAILED. 1G71 4U4 U H1SW E17EA 20081119 SW 2008 11 19 CA080811006 120080807G76032761000009 ROD END SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP RT POWER LEVER WORN W O OTHER O OTHER NRNOT 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 END. (SOME WORSE THAN OTHERS) THE PART APPEARS TO BE FINE AT INSPECTION THEN FAILS SUDDENLY. AT A CERTAIN POINT IN THE LAST FEW YEARS THE PART CHANGED, THE NR IS THE SAME BUT THE PART WAS PHYSICALLY DIFFERENT. THE NEWER ONES ARE THE PROBLEM 2L72 4T4 TRTA8SW E4WE 20081118 EA 2008 11 18 CA080811007 220080807G7322383493 PLUG 25245009 PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2A GL FUEL SERVO LOOSE W K NONE O OTHER ININSP/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. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081117 CE 2008 11 17 CA080812001 120080716G3340S21601 SWITCH CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA STROBE LIGHT FAULTY W A UNSCHED LANDING BB SMOKE/FUMES/ODORS/SPARKS SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) ON JULY 16, 2008 AT APPROX. 13:00, PILOT REPORTED SMOKE IN COCKPIT AND PLASTIC BURNING SMELL. ACFT ELECTRONICS WERE SHUTDOWN AND SMOKE DISSIPATED. DURING POST FLIGHT INSP, MAINT DISCOVERED A FAULTY STROBE LIGHT SWITCH, AND REPLACED THE DEFECTIVE SWITCH. ACFT SYS TESTED WITH NO FURTHER DEFECTS FOUND. 1H71 3O3 ONT3A12 E274 20081117 CE 2008 11 17 CA080812002 120080808G325222430211 CLEVIS CESSNA 24421141 CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA MCAULY2D34C B2D34C220 GL SHIMMY DAMPER BROKEN W D RETURN TO BLOCK E VIBRATION/BUFFET TXTAXI/GRND HDL 1 CA 9102 (CAN) DAMPER SHAFT CLEVIS BROKE AT NOSE STRUT ATTACHMENT ALLOWING UNRESTRAINED MOTION OF SHIMMY DAMPER. 1H71 3O3 O 3A17 E286 5 CP7EA 20081117 EA 2008 11 17 CA080812003 220080808G8530LW13623 PISTON CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL ENGINE DAMAGED W D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS ININSP/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. 1H71 3O3 ONT3A19 E223 5 NP50GL 20081124 NE 2008 11 24 CA080812004 220080721G7261MS920807 BOLT DHAV DHC8 DHC8314 NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE ENGINE OIL LINE LOOSE W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF, THE NR 1 ENGINE LOST OIL PRESSURE AND WAS SUBSEQUENTLY SHUTDOWN. THE ACFT RETURNED TO THE AIRPORT FOR AN APPROACH, HOWEVER, THE VISIBILITY WAS TOO LOW, A MISSED APPROACH WAS EXECUTED FOLLOWED BY A NR OF HOLDS UNTIL THE WEATHER WAS APPROPRIATE TO TRY A SECOND APPROACH. THE ACFT LANDED SAFELY AFTER A SECOND APPROACH. FURTHER INSPECTION FOUND THE OIL LINE FLANGE BOLTS LOOSE ON THE NR 1 ENGINE, ALLOWING ALL THE OIL TO BE PUMPED OUT OF THE ENGINE. THESE BOLTS ARE NOT DRILLED AND THEREFORE CANNOT BE SAFETY WIRED. PRATT SB 21178 REPLACES THE INSERTS WITH SELF LOCKING INSERTS. THE BOLTS WERE RETORQUED, OIL REPLENISHED AND THE ACFT WAS RETURNED TO SERVICE. 2H72 4T4 TRT E20NE 6 CP7NE 20081117 NE 2008 11 17 CA080812005 220080803G853071167 EXHAUST VALVE PWA 399359 DHAV DHC3 DHC3 2800202EA PWA R1340 R1340* 52016NE HAMSTD23D 23D40 NE CYLINDER BROKEN W A UNSCHED LANDING E VIBRATION/BUFFET NRNOT 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. 1H71 3R3 R A815 5E2 6 CP719 20081119 SW 2008 11 19 CA080813002 120080813G6410206011809109 PITCH HORN BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL TAIL ROTOR LOOSE W O OTHER E VIBRATION/BUFFET NRNOT 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. THE 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. 1G71 3U3 U H2SW E4CE 20081117 EA 2008 11 17 CA080813003 120080812G2910AE4760H0592055 HYDRAULIC LINE CNDAIRCL601 CL6013A 8070802EA GE CF34 CF343A2 30067NE HYDRAULIC SYS BURST W O OTHER KJ FLUID LOSS WARNING INDICATION NRNOT 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 PRESSURE HOSE IN RT NACELLE. 2L72 4F4 FRTA21EA E15NE 20081117 CE 2008 11 17 CA080813004 120080806G325055656195 ARM CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE NLG STEERING DAMAGED W K NONE O OTHER UKUNKNOWN 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 MS27039-1-07 AND NIL WASHERS ARE CALLED FOR IN THE MFG IPC. THE LENGTH OF THE INSTALLED SCREWS WERE SUCH THAT WHEN FULL NOSE WHEEL DEFLECTION WAS ACHIEVED THERE WAS INTERFERENCE BETWEEN THE SCREW AND THE STEERING ARM CAUSING THE DAMAGE. STEERING ARM P/N 5565619-5 REPAIRED IAW ASEO 851-32-50-0212 BLEND REPAIR. CORRECT HARDWARE (MS27039-1-07 SCREWS AND MS21042-3 NUTS) INSTALLED ON CHANNEL-TRUNION BRACE. 1L72 4F4 F A22CE E1NE 20081117 EA 2008 11 17 CA080813005 120080812G2751756158 TORQUE SENSOR DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE TE FLAP INOPERATIVE W D RETURN TO BLOCK J WARNING INDICATION CRCRUISE 1 CA (CAN) FLAP DRIVE CAUTION LIGHT IN CRUISE. ELECTED TO RETURN A/C TO DEPARTURE FOR REPAIR. CONFIRMED FAULT TO TORQUE SENSOR ASSY S/N:0570 (ROGUE UNIT). WHEN LT SWITCH IS COLD SPRAYED "FLAP DRIVE" CAUTION LIGHT COMES ON WITH TQ SENSOR CENTERED. 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081119 EA 2008 11 19 CA080813006 220080801G8520SL18840 CAMSHAFT CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA ENGINE WORN W K NONE R PARTIAL RPM/PWR LOSS ININSP/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. 1H71 3O3 ONT3A12 E274 20081117 EU 2008 11 17 CA080813007 120080812G55445554012215 COVER PLATE 5554012038 PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL RUDDER DAMAGED W O OTHER F FLT CONT AFFECTED TOTAKEOFF 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 ACFT REVEALS THAT THIS COVER PLATE CAN RUB ON THE RUDDER STOP OVER TIME AND MAY BE THE BEGINNING OF THE CAUSE OF THIS PROBLEM. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081117 CE 2008 11 17 CA080813008 120080813G3097 WIRE CESSNA208 208 2073702CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL DEICE SYS CHAFED W K NONE N FALSE WARNING NRNOT REPORTED 1 CA (CAN) PILOT REPORTED INTERMITTENT "DE-ICE PRESSURE" ANNUNCIATOR ILLUMINATION WHEN DE-ICE WAS NOT SELECTED. ON INVESTIGATION 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. 1H71 3T3 TNTA37CE E4EA 5 CP60GL 20081118 SW 2008 11 18 CA080813009 120080320G6420212011701 BELLCRANK BELL 212011701 BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE TAIL ROTOR IMPROPER PART W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING T/R RIGGING CHECK, IT WAS NOTED THAT WHEN FULL LT PEDAL WAS APPLIED, THE COUNTERWEIGHT LINK TO COUNTER WEIGHT ARM HARDWARE WOULD CONTACT T/R CROSSHEAD ASSY. UPON INVESTIGATION THE WRONG P/N OF COUNTERWEIGHT BELLCRANK ASSY`S WERE 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. 1G71 4U4 U H4SW E22EA 20081118 SW 2008 11 18 CA080813011 120080526G6410 BLADE BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE TIAL ROTOR UNKNOWN W K NONE O OTHER ININSP/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/ROOT. T/R BLADES REMOVED AND DRESSED OUT TO PROVIDE .010" CLEARANCE BETWEEN YOKE AND BLADES (IAW PSE). YOKE INSPECTED FOR DAMAGE, NONE FOUND. 1G71 4U4 U H4SW E22EA 20081119 NE 2008 11 19 CA080813012 220080811G7250 TURBINE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE ENGINE FAILED W BR EMER. DESCENT AUTOROTATION KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CRCRUISE 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 DEVELOPING 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 EXPLAIN INTENSE SMOKE OBSERVED COMING FROM ENGINE DURING AUTOROTATION & LANDING. RUBBING NOISES CAN BE HEARD WHEN TURNING C1G71 3U3 U H9EU E19EU 20081118 NE 2008 11 18 CA080814001 220080703G7200 ENGINE BAG ATP ATP EU PWA PW120 PW126A NE FLAMED OUT W K NONE XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) THE ENGINE FLAMED OUT AND THEN RELIT (AUTO RELIGHT) WITHIN 2 SEC. THE OCCURRENCE HAPPENED APPROXIMATELY 10 MIN. AFTER ENCOUNTERING SEVERE WEATHER INCLUDING HAIL AND MODERATE TURBULENCE. THE FLIGHT CONTINUED TO DESTINATION WITHOUT FURTHER PROBLEMS. POST FLIGHT INSPECTION SHOWED NO DAMAGE AND THE A/C CONTINUED IN SERVICE. 2L72 4T4 TRTA27NM E2ONE 20081118 NE 2008 11 18 CA080814002 220080428G7200 PLANETARY GEAR CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE ENGINE DISTRESSED W A UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER T/O, THE PILOT NOTED ENGINE VIBRATION FOLLOWED BY AN OIL PRESSURE DROP. HE RETURNED TO THE POINT OF DEPARTURE WHERE AN UNEVENTFUL LANDING WAS PERFORMED UNDER POWER. THE ENGINE WAS FWDED TO MFG WHERE 1ST STAGE PLANET GEAR DISTRESS 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. 1H71 3T3 T A37CE E4EA 20081118 NE 2008 11 18 CA080814003 220080730G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE FOD W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 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. 1H71 3T3 T A37CE E4EA 20081119 NE 2008 11 19 CA080814004 220080809G7261 LINE BOEING767 7673Y0 NM GE CF6 CF680C2B6F 30025NE ENGINE OIL SYS CRACKED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 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 FEED 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. 2L72 4F4 FRTA1NM E13NE 20081118 NE 2008 11 18 CA080814005 220080730G7200 ENGINE CESSNA680 680CE 2076811CE PWC PW306 PW306C 52169NE LEFT POWER LOSS W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CA (CAN) DURING TAKE-OFF, THE LT ENGINE POWER ROLLED BACK ABOUT 8-10 PERCENT. WHILE ON CLIMB AND WHILE LEVELING-OFF AT 6,000 FT, SEVERAL OTHER ROLL-BACKS WERE NOTED. ACCORDING TO THE PIC, THESE SEEMED TO OCCUR AFTER A TLA ADJUSTMENT. CREW STABILIZED ACFT AT 6,000 FT AND DECIDED TO DIVERT. AN UNEVENTFUL DUAL ENGINE LANDING WAS ACCOMPLISHED. TROUBLESHOOTING REVEALED POSSIBLE ISSUE WITH LT ENGINE FCU. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4F4 FRCT00012WIE35NE 20081118 EA 2008 11 18 CA080814006 120080812G77326233M30A TRANSDUCER CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE VIBRATION ANLYZRUNSERVICEABLE W C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 CA (CAN) ON THE TAKE-OFF ROLL AT APRX 60KTS, THE FLIGHT CREW REJECTED TAKE-OFF DUE TO AN N2 ENGINE VIBRATION CAUTION MESSAGE. 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 RUNS CARRIED OUT AND VIBE INDICATIONS ALL CHECK OK. SYSTEM CHECKED SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20081118 EU 2008 11 18 CA080814007 120080814G3246Z0DN6068757295 WHEEL HALF PARKER40270 SOCATATBM TBM700 8682000EU RT MLG CRACKED W O OTHER O OTHER LDLANDING 1 CA (CAN) DURING LANDING ROLL, PILOT NOTICED ABNORMAL "FEEL" OF ACFT AND STEERING. DISCOVERED FLAT TIRE ON RT MAIN WHEEL. ACFT RECOVERED FROM RUNWAY. DISASSEMBLED WHEEL AND PERFORMED DYE PENETRANT INSP ON WHEEL HALVES. CRACK INDICATION VERY EVIDENT IN INNER BEAD RADIUS OF OUTER WHEEL HALF SUB-ASSEMBLY, AND ALSO VISIBLE ON OUTER SURFACE. PART IS SUBJECT TO REPETITIVE NDT INSPECTIONS. WHEEL HALF SUB-ASSEMBLY REPLACED. 1L71 3T RTA60EU 20081118 NE 2008 11 18 CA080814008 220080802G7200 ENGINE CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE LEFT MALFUNCTIONED W K NONE Y ENGINE STOPPAGE APAPPROACH 1 CA (CAN) WHILE ON APPROACH, THE LT ENGINE ROLLED BACK AND WOULD NOT RESPOND TO THROTTLE MOVEMENTS. WHILE CREW WAS PERFORMING EMERGENCY CHECKLIST FOR ENGINE SHUTDOWN. THE LT ENGINE SHUTDOWN ON ITS OWN. ACFT LANDED WITHOUT INCIDENT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4F4 FRTA22CE E00053EN 20081118 NE 2008 11 18 CA080814009 220080804G7200 ENGINE EMB 120 EMB120 3260201SO PWA PW118 PW118B NE MALFUNCTIONED W EC ENGINE SHUTDOWN ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA (CAN) WHILE ON INITIAL TAKEOFF ROLL PHASE, PILOT APPLIED POWER ON BOTH ENGINES BUT NOTICED FUEL AND OIL PRESSURE DECREASING 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. 2L72 4T4 TRTA31SO E20NE 20081118 NE 2008 11 18 CA080814010 220080804G7200 ENGINE CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE NR 1 SHUTDOWN W A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 CA (CAN) THE ACFT WAS ON A FIREFIGHTING MISSION. JUST AFTER A WATER DROP, AS THE PILOT APPLIED FOR POWER, THE NR1 ENGINE WENT INTO AUTOFEATHER AND SHUTDOWN BY ITSELF. THE PILOT FOLLOWED PROCEDURES AND RESTARTED THE ENGINE. THE ACFT LANDED SAFELY. TROUBLESHOOTING IS FOCUSING ON ELECTRICAL HARNESS AND POSSIBLE OVERTORQUE. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA14EA E20NE 20081119 NM 2008 11 19 CA080814011 120080806G5330 LAP JOINT EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE FUSELAGE LEAKING W K NONE O OTHER ININSP/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). 2L72 4F4 FRTA56NM E00063EN 20081119 NE 2008 11 19 CA080814012 220080804G7200 ENGINE LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE MALFUNCTIONED W C ABORTED TAKEOFF MBJOVER TEMP SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TOTAKEOFF 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 SISTER ENGINE AFTER SHUTDOWN AND A BURNED ODOR WAS NOTICED, WITH SOME SMOKE COMING FROM THE EXHAUST. ENGINE IS BEING REMOVED AND SENT FOR INVESTIGATION. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4F4 FRTA10CE E35NE 20081119 EA 2008 11 19 CA080814013 220080812G7200 ENGINE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA LEFT FAILED W C ABORTED TAKEOFF EJ VIBRATION/BUFFET WARNING INDICATION TOTAKEOFF 1 CA (CAN) DURING TAKE OFF ROLL AT AROUND 60 KNOTS, LT ENGINE ITT ENGINE WARNING ILLUMINATED AND CREW FELT THE ACFT YAW. ENGINE 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 ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA13NM E00062EN 20081119 WP 2008 11 19 CA080815001 220080811G7321 FUEL CONTROL DORNERDO228 DO228202 2992030EU GARRTTTPE331TPE3315 01514WP NR 1 ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN F FLT CONT AFFECTED NRNOT 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 SHUT 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 LEVER CONTROLS WERE CHECKED AND FOUND THAT THE LEVER ON THE FCU WAS OVERCENTERING CAUSING THE JAMMING OF THE CONTROLS. ENG2H72 4T4 TRTA16EU E4WE 20081119 NM 2008 11 19 CA080815002 120080813G24324011769 BATTERY DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE MASTER OVERHEATED W HA DEACTIVATE SYST/CIRCUITSUNSCHED LANDING MJ OVER TEMP WARNING INDICATION CLCLIMB 1 CA 21080478 (CAN) DURING CLIMB OUT FROM YWK, THE CREW RECEIVED A "MAIN BAT HOT" RED WARNING MSG ASSOCIATED WITH A HIGH TEMPERATURE ON THE BATTERY TEMPERATURE MONITOR. THE ACFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. MX CONFIRMED THE BATTERY SUFFERED FROM A THERMAL RUN-AWAY. THE MAIN BATTERY WAS REPLACED AND THE ACFT RETURNED INTO SERVICE. THE BATTERY TEMPERATURE WAS NOT RECORDED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081119 NE 2008 11 19 CA080815004 220080812G7200 ENGINE CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE RIGHT FIRE W A UNSCHED LANDING A FLAME/FIRE NRNOT REPORTED 1 CA (CAN) DURING A FIRE FIGHTING MISSION, RT ENGINE WAS SHUT DOWN DUE TO A FIRE WARNING. AN EMERGENCY WAS DECLARED, ACFT DIVERTED 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. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA14EA E20NE 20081119 EA 2008 11 19 CA080815005 220080803G7314 SPLINE BEECH STC STC90BEECH PWA PT6 PT6A20 52043EA FUEL PUMP WORN W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT 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 REVEALED LT ENGINE WITH SEVERELY WORN FUEL PUMP SPLINE. ENGINES WILL BE FORWARDED TO MANUFACTURER MONTREAL FOR INVESTIGATION. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L72 3O3 T 3A20 E4EA 20081119 EA 2008 11 19 CA080815006 220080713G8520LW15288 CONNECTING ROD PIPER PA44 PA44180 7104402SO LYC O360 LO360E1A6 41514EA NR 4 CYLINDER BROKEN W O OTHER O OTHER NRNOT 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 1L72 3O3 O A19S0 E286 20081112 NM 2008 11 12 CA080815009 120080117G3240 BRAKE EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE MLG CHATTERING W O OTHER S AFFECT SYSTEMS TXTAXI/GRND HDL 1 CA (CAN) AS REPORTED BY FLIGHT CREW: LT BRAKE CHATTERS WHEN PRESSED, VERY PRONOUNCED AT TIMES CARBON DISK FAILURE CONFIRMED. 2L72 4F4 FRTA56NM E00063EN 20081112 NM 2008 11 12 CA080818001 120080814G2913661733 PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU HYD SYSTEM LEAKING W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 4815 (CAN) DURING CRUISE OPERATION FLIGHT CREW OBSERVED NR 1 HYDR SYS CAUTION LIGHT ON, FLIGHT DIVERTED TO BASE. CREW CONFIRMED NO PRESSURE FROM NR 1 EDP SELECTED SPU CONFIRMED PRESSURE 3000 PSI AND NO QUANTITY LOSS. ON GROUND TROUBLESHOOTING REVEALED EDP HAD 5 PUNCTURES THROUGH CASING & SOURCE OF SMALL AMOUNT OF HYDR FLUID LOSS. NR 1 ENGINE DRIVEN PUMP REPLACED. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081113 CE 2008 11 13 CA080818002 120080707G2730 CONTROLLER BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL ELEVATOR FROZEN W O OTHER F FLT CONT AFFECTED CRCRUISE 1 CA (CAN) APPROXIMATELY 50 MIN OUT, AUTOPILOT BEGAN TO CLIMB, THE A/P WAS DISCONNECTED AND ACFT MANUALLY BROUGHT BACK TO ALTITUDE. A/P WAS REENGAGED AND THEN BEGAN TO DESCEND FOLLOWED BY THE AP TRIM FAIL ANN. A/P DISCONNECTED, ELECTRIC TRIM CHECK 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 POSITION. 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 L2L72 4T4 TRTA24CE E4EA 6 CP56GL 20081113 EU 2008 11 13 CA080818003 120080806G750032156281 O-RING ISRAEL1125 ASTRASPX 4500205EU GARRTTTFE731TFE73140 29001NE BLEED SYSTEM FAILED W A UNSCHED LANDING MJ OVER TEMP WARNING INDICATION CLCLIMB 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 POWER 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 SUBSEQUENT ACTIVATION OF BLEED LEAK WARNING ILLUMINATION AT 250 DEG F. BOTH VALVES REPLACED O-RING NOT FIELD REPLACEABLE. 2L72 4F4 FRTA16NM E1NM 20081113 CE 2008 11 13 CA080819001 120080814G25105055301401 CABLE ASSY CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA SEAT BROKEN W K NONE O OTHER ININSP/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 TO ALLOW THE SEAT TO MOVE. THE CABLE HAD BROKEN IMMEDIATELY AFTER THE SWAGED END. 1H71 3O3 ONT3A12 E274 20081113 EA 2008 11 13 CA080819002 120080715G5610NP1393226 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CLCLIMB 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. 2L72 4F4 FRTA21EA E15NE 20081113 EA 2008 11 13 CA080819003 120080715G5610NP1393226 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) "F/O WINDSHIELD SHATTERED ENROUTE, DIVERTED ". REMOVED AND REPLACED THE F/O`S WINDSHIELD. 2L72 4F4 FRTA21EA E15NE 20081113 EA 2008 11 13 CA080819004 120080815G5610NP1393215 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C5 30050NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 14795 (CAN) "DISC - AFTER TAKEOFF CAPTAIN`S WINDSHIELD CRACKED. NO OTHER PROBLEMS NOTED. REMOVED AND REPLACED PILOTS WINDSHIELD. 2L72 4F4 FRTA21EA E00063EN 20081113 EA 2008 11 13 CA080819005 120080816G5610NP13932210 WINDOW CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C5 30050NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 12265 (CAN) DISC - IN CRUISE FLIGHT, F/O SIDE WINDSHIELD CRACKED AND WINDSHIELD HEAT ON RT SIDE FAILED.. ACFT RETURNED. NO PRESS PROBLEM. ALL OTHER SYS NORMAL. REMOVED AND REPLACED F/O SIDE WINDOW. 2L72 4F4 FRTA21EA E00063EN 20081113 NM 2008 11 13 CA080819006 120080818G29135116403 PUMP EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE HYD SYSTEM FAILED W O OTHER K FLUID LOSS CRCRUISE 1 CA (CAN) WHILE ENROUTE, THE NR 1 HYD SYS FAILED. AFTER CONSULTATION WITH MAINT, FLIGHT CONTINUED AND LANDED WITHOUT INCIDENT. 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. 2L72 4F4 FRTA57NM E00070EN 20081118 EU 2008 11 18 CA080819008 120080805G6230 NUT BOLKMS117 BK117B2 5626013EU LYC LTS101LTS101750B1 41560NE MAIN ROTOR LOOSE W A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA (CAN) VIBRATION NOTICEABLE ON COLLECTIVE CONTROL PWR CHANGES. FURTHER INVESTIGATION REVEALED THAT THE MAIN ROTOR MAST HAD .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. 1G72 3U3 UNCH13EU E5NE10 20081118 GL 2008 11 18 CA080819009 120080815G323417C17616A3 VALVE BOMBDRBD100 BD1001A10 1390044GL HNYWL AS907 AS90711A 33908WP LANDING GEAR UNKNOWN W O OTHER J WARNING INDICATION APAPPROACH 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. AGAIN THE GEAR DID NOT MOVE. HE THEN GRABBED THE QRH AND CARRIED OUT THE EMER PROCEDURES TO DEPLOY THE GEAR. WHEN THE EMER LG HANDLE WAS PULLED THE GEAR DEPLOYED AND ACHIEVED 3 GREEN IN A FEW SECONDS. THE LANDING WENT SMOOTHLY. 2L72 4F4 FRTT00005NYE00010LA 20081118 SW 2008 11 18 CA080819010 120080808G243523079010 STARTER GEN FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR 29081NE MCAULY4HFR344HFR34C652 NE RIGHT FAILED W K NONE J WARNING INDICATION DEDESCENT 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 DESTROYED. UNIT REPLACED AND ACFT CHECKED SERVICEABLE. INVESTIGATION INTO FAILURE PENDING. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081124 SW 2008 11 24 CA080819011 120080810G75008943825 TUBE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE3311 01514WP MCAULY4HFR344HFR34C652 NE LT ENGINE BLEED FRACTURED W O OTHER J WARNING INDICATION TOTAKEOFF 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. UNIT WAS REPLACED AND ACFT RETURNED TO SERVICE. 2L72 4T3 TRTA8SW E3WE 6 C3PNE 20081118 EU 2008 11 18 CA080819012 120080817G2750945020220 DRIVE SHAFT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL TE FLAP SHEARED W K NONE F FLT CONT AFFECTED APAPPROACH 1 CA 6330 (CAN) LT INBD FLAP FLEXABLE DRIVE SHAFT SHEARED AT INBD DRIVE END. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081120 2008 11 20 CA080819013 420080812G612210185 COTTER PIN DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HARTZLHCB3R HCB3R304 GL GOVERNOR MISSING W K NONE O OTHER ININSP/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 MISSING. 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 OF GOVERNOR BASE AND BREAK OFF. ONCE THIS HAPPENS, THE SHORT END OF COTTER PIN CAN ROTATE AND ALSO CONTACT THE INSIDE OF 1H71 3R3 RRCA806 5E1 5 CP28EA 20081118 EA 2008 11 18 CA080820001 220080817G7261766859C SCAVENGE PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NR 2 ENGINE LOOSE W E ENGINE SHUTDOWN J WARNING INDICATION DEDESCENT 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 WITH THE NR 2 OIL PRESS WARNING AND CHIME. CREW IMMEDIATELY SHUT DOWN THE NR 2 ENG, TAKING ABOUT 5 TO 10 SECONDS TO COMPLETE MEMORY ITEMS. AFTER ENGINE/PROP FEATHERED, THERE SEEMED TO BE NO OTHER PROBLEMS. CASTELLATED NUT ON THE OIL SCAVENGE PUMP FOUND LOOSE. WITH INPUT SHAFT ROTATING THE SPUR GEAR WAS NOT ROTATING WHICH WAS DRIVE FOR THE ADJACENT SHAFT. RGB SCAVENGE IS LOCATED ON THIS SHAFT WHICH WAS NOT ROTATING. OIL SCAVENGE PUMP BEING REPLACED. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081118 2008 11 18 CA080820002 420080815G5301 RELEASE MECH BELL 407 407 1182206SW ALLSN 250C 250C47B GL MALFUNCTIONED W O OTHER O OTHER HOHOVERING 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 PILOT PULLED INTO AN HOVER AND THEN THE CABLE RELEASED WITHOUT ANY ACTION FROM THE PILOT. HE LANDED IMMEDIATELY. FURTHER INVESTIGATION FOUND THE MANUAL RELEASE CABLE SNAG ON THE OUTSIDE OF THE HOLE CENTER FRAME P/N D2796 STATION 115.75 WHICH PREVENTED THE HOOK TO CLOSE SECURELY. MFG HAS BEEN INFORMED ABOUT THE INCIDENT AND PICTURES WERE FORWARDED AS WELL. 1G71 3U3 UO H2SW E1GL 20081118 NM 2008 11 18 CA080821001 120080215G3242900005831PR BRAKE EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE NR 1 BRAKE MALFUNCTIONED W K NONE J WARNING INDICATION LDLANDING 1 CA (CAN) NUMEROUS LANDING GEAR NO DISPATCH AND EMERGENCY BRAKE FAULT MESSAGES AFTER TOUCHDOWN NR1 BRAKE REPLACED. CONSIDERED SERVICEABLE. 2L72 4F4 FRTA56NM E00063EN 20081118 NM 2008 11 18 CA080821002 120080704G3242900005832PR DISK EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE NR 4 BRAKE DETERIORATED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) NR 4 MAIN WHEEL BRAKE CARBON DISK BADLY DETERIORATED. 2L72 4F4 FRTA56NM E00063EN 20081118 NM 2008 11 18 CA080821003 120080714G3242900005832PR BRAKE EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE NR 1 DAMAGED W O OTHER O OTHER ININSP/MAINT 1 CA (CAN) BRAKE ASSY BREAKING UP. 2L72 4F4 FRTA56NM E00063EN 20081118 NM 2008 11 18 CA080821004 120080719G3242900005831PR BRAKE ASSY EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE NR 4 FAILED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) ON PUSHBACK REPORT OF NR 4 BRAKE ASSY FAILURE, AS REPORTED BY STATION SERVICES CREW BRAKE ASSY REPLACED. 2L72 4F4 FRTA56NM E00063EN 20081118 NM 2008 11 18 CA080821005 120080802G3242900005831PR BRAKE ASSY EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE NR 2 FAILED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/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) 2L72 4F4 FRTA56NM E00063EN 20081118 CE 2008 11 18 CA080821006 120080818G3221030A311201 ATTACH FITTING MTSBSIMU2 MU2B60 5780460CE GARRTTTPE331TPE33110 29053NE HARTZLHCB4T HCB4TN5 GL NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1594915949 (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. 1H72 3T4 TRTA10SW E4WE 6 CP40EA 20081118 NM 2008 11 18 CA080821007 120080809G3242900005831PR BRAKE EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE LT MLG DEFECTIVE W O OTHER O OTHER LDLANDING 1 CA (CAN) LT MAIN BRAKE TEMPS OB 365/IB149, RT BRAKES IB 148/OB130, BRAKES FELT SOFT, BRAKES REPLACED. CAUSE: CARBON OXIDATION. 2L72 4F4 FRTA56NM E00063EN 20081120 SW 2008 11 20 CA080821008 120080820G5311 FRAME BELL 206 206L4 1182110SW ALLSN 250C 250C30P 03013GL FUSELAGE CHAFED W K NONE O OTHER ININSP/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. 1G71 3U3 UNCH2SW E1GL 20081118 NM 2008 11 18 CA080821009 120080809G324290000582WT BRAKE EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE NR 1 DISINTEGRATED W K NONE J WARNING INDICATION LDLANDING 1 CA (CAN) BRAKE NR 1 DISINTEGRATED AND M/W CHANGED DUE TO BRAKE STUCK IN TIRE. BRAKE NR 1 CHANGED. 2L72 4F4 FRTA56NM E00063EN 20081118 EU 2008 11 18 CA080821010 120080821G3040320570 SPLICE PILATSPC12 PC1247 7090552EU PWA PT6 PT6A67 52043NE HARTZLHCE4A HCE4A3D GL WINDSHIELD HEAT BURNED W O OTHER MW OVER TEMP INADEQUATE Q C ININSP/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 WAS 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 WINDSHIELD HEAT WIRING WAS COMPLETED AND NO FAULTS FOUND. THE WIRES 1H83A12,1H85A12,1H80B12,1H81A12 AND SPLICES WERE ALL REPLACE1L71 4T4 TRTA78EU E26NE 5 CP210NE 20081118 SW 2008 11 18 CA080821011 120080215G6210206010200133 BALANCE WEIGHT 206010200133BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL BLADE DEBONDED W O OTHER E VIBRATION/BUFFET APAPPROACH 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 OCCURRED. 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 FLUNG 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 AT 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 BL1G71 3U3 U H2SW E4CE 20081118 CE 2008 11 18 CA080821012 120080817G561066561000010 WINDSHIELD LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP COCKPIT BROKEN W O OTHER Z SIGNIFICANT FAILURE REPORT CRCRUISE 1 CA (CAN) WHILE IN CRUISE AT FLT 400 ENROUTE, THE RT WINDSHIELD OUTTER PLY SHATTERED, CAUSING A LOUD BANG. NO DEPRESSURISATION OCCUR, RT WINDSHILED HEAT BECAME INOPERATIVE. RT WINDSHIELD REPLACED WITH NEW ONE. ACFT RETURN TO SERVICE. 2L72 4F4 FRTT00008WIE6WE 20081118 2008 11 18 CA080821013 420080818G3416066030620010 ALTIMETER PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL DEFECTIVE W O OTHER O OTHER DEDESCENT 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. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081118 WP 2008 11 18 CA080822001 120080728G6310C0511 ACTUATOR ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA CLUTCH FAILED W K NONE O OTHER UKUNKNOWN 1 CA 788 (CAN) THE CLUTCH ACTUATOR WOULD NOT FULLY ENGAGE, SERVICABLE ACTUATOR INSTALLED. 1G71 3O3 O H11NM E295 20081118 NE 2008 11 18 CA080822002 220080731G732225766304 SERVO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYSTEM UNSERVICEABLE W K NONE O OTHER NRNOT REPORTED 1 CA 1595 (CAN) THE ENGINE HAD ROUGH IDLING, TROUBLESHOOTING REVEALED AN EXCESSIVE AMOUNT OF FUEL WAS BEING INJECTED OUT OF THE FUEL INJECTORS. INSTALLED A SERVICABLE FUEL SERVO. 1G71 3O3 O H11NM 1E4 20081118 WP 2008 11 18 CA080822003 120080803G6310C0511 ACTUATOR ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA CLUTCH FAILED W K NONE O OTHER TXTAXI/GRND HDL 1 CA (CAN) THE CLUTCH WOULD NOT ENGAGE DURING ACFT START. REPLACED CLUTCH ACTUATOR. 1G71 3O3 O H11NM E295 20081118 WP 2008 11 18 CA080822004 120080804G2435BC3151004 STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE INOPERATIVE W K NONE O OTHER TXTAXI/GRND HDL 1 CA 372 (CAN) THE STARTER WOULD NOT ENGAGE, REPLACED WITH SERVICABLE STARTER. 1G71 3O3 O H11NM 1E4 20081118 SW 2008 11 18 CA080822005 120080805G2432RG206 BATTERY BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL MAIN DISCHARGED W K NONE O OTHER TXTAXI/GRND HDL 1 CA 157 (CAN) DURING ACFT START, THE BATTERY WAS FOUND WITH NO CHARGE, BATTERY REPLACED. 1G71 3U3 U H2SW E4CE 20081118 WP 2008 11 18 CA080822006 120080715G6310C0512 CLUTCH ACTUATOR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FAILED W K NONE O OTHER NRNOT REPORTED 1 CA 667 (CAN) CLUTCH WOULD NOT ENGAGE, SERVICABLE CLUTCH ACTUATOR INSTALLED. 1G71 3O3 O H11NM 1E4 20081118 WP 2008 11 18 CA080822007 120080730G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FAILED W K NONE O OTHER NRNOT REPORTED 1 CA 623 (CAN) THE STARTER WAS GRINDING DURING START, STARTER REPLACED. 1G71 3O3 O H11NM 1E4 20081118 WP 2008 11 18 CA080822008 120080729G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FAILED W K NONE O OTHER UKUNKNOWN 1 CA (CAN) THER STARTER WOULD NOT START. 1G71 3O3 O H11NM 1E4 20081118 WP 2008 11 18 CA080822009 120080727G2435BC3151004 STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FAILED W K NONE O OTHER TXTAXI/GRND HDL 1 CA 687 (CAN) STARTER FAILED ON START UP, STARTER REPLACED. 1G71 3O3 O H11NM 1E4 20081118 NE 2008 11 18 CA080822010 220080714G732225766304 FCU ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE INOPERATIVE W K NONE O OTHER NRNOT REPORTED 1 CA 1996 (CAN) THE ENGINE WAS RUNNING TOO RICH, TROUBLESHOOTING REVEALED COULD NOT ADJUST FUEL INJECTOR SERVO, REPLACED FCU. 1G71 3O3 O H11NM 1E4 20081118 SO 2008 11 18 CA080822011 120080725G3710441CC7 PUMP PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL VACUUM SYS SEIZED W K NONE O OTHER ININSP/MAINT 1 CA 452 (CAN) DURING INSPECTION THE LT ENGINE VACUUM PUMP FOUND SEIZED, REPLACED. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081118 WP 2008 11 18 CA080822012 120080718G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE DAMAGED W K NONE O OTHER UKUNKNOWN 1 CA 55 (CAN) THE STARTER WAS INTERMITTENT, ON INSPECTION WAS FOUND TO HAVE TEETH MISSING. 1G71 3O3 O H11NM 1E4 20081118 NE 2008 11 18 CA080822013 220080703G732225766304 FCU ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION THE MIXTURE CONTROL FOUND TO BE BINDING IN THE RICH POSITION, REMOVED DUE TO STIFF MIXTURE LEVER. 1G71 3O3 O H11NM 1E4 20081118 GL 2008 11 18 CA080822014 220080707G7261 LABYRINTH SEAL BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL ENGINE LEAKING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION, OIL WAS FOUND POOLING IN EXHAUST COLLECTOR, SUSPECT NR 5 LAB SEAL. 1G71 3U3 U H2SW E4CE 20081124 CE 2008 11 24 CA080822015 120080822G3060 WIRE CESSNA441 441 2076020CE GARRTTTPE331TPE33110N 29062NE MCAULY4HFR344HFR34C660 NE PROP DE-ICE BOOTSHORTED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA (CAN) AFTER LANDING, THE ACFT EXPERIENCED A SMALL AMOUNT OF SMOKE IN THE COCKPIT, FOLLOWED IMMEDIATELY BY THE SWITCH CIRCUIT BREAKER POPPING. THE AMMETER FOR THE PROP DE-ICE WAS PEGGED TO THE FULL RT, ONCE THE SYSTEM WAS SWITCHED OFF THE METER STILL INDICATED IN THE GREEN. MX INSPECTION REVEALED THE WIRE LEAD OFF THE PROP DE-ICE BOOT WAS TOO LONG AND WAS RUBBING AGAINST THE INSIDE OF THE SPINNE. THE SHORT TO GROUND WENT THROUGH THE BRUSH BLOCK ASSEMBLY TO THE AMMETER IN THE COCKPIT. 1L72 3T4 TRTA28CE E4WE 5 C3PNE 20081118 2008 11 18 CA080822016 420080820G34211013800803 GYRO BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL ATTITUDE FAILED W O OTHER I FLT. ATTITUDE INST. UKUNKNOWN 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 HAVE 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. 2L72 4T4 T A24CE E4EA 6 CP56GL 20081118 NM 2008 11 18 CA080825001 120080825G6120666000459 CONTROL UNIT BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NR 2 ENGINE SHORTED W E ENGINE SHUTDOWN F FLT CONT AFFECTED DEDESCENT 1 CA (CAN) DURING FLIGHT THE PROP SPEED SHOWED 1070 RPM IN DESCENT WITH PEC CAUTION. CREW PREFORMED NR2 ENGINE IFSD AND RETURNED TO BASE. MAINT REVIEWED CDS AND FOUND FC 160 CH A&B. FIM TASK FOLLOWED AND FOUND MPU SHORTED TO GROUND. MPU REPLACED AND EGR C/O SATIS. ACFT RELEASED FOR SERVICE. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081118 EU 2008 11 18 CA080825002 120080822G2913993378 PUMP VICKERS PPEV3008EA PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL HYDRAULIC SYS CRACKED W K NONE K FLUID LOSS APAPPROACH 1 CA 2220 2220 (CAN) ON LANDING, HYDR PUMP CONTINUED TO CYCLE, AFTER LANDING WHEN ACFT PARKED, HYDR FLUID DRIPPING FROM FUSELAGE NEAR HYDR PUMP LOCATION. WHEN PUMP OPERATED FLUID SPRAYED FROM CRACK IN END PLATE OF PUMP, PUMP ASSY REPLACED WITH SERVICABLE UNIT. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081120 SO 2008 11 20 CA080825003 120080814G2750487084 SOLENOID 4018542 PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2A GL TE FLAP FAILED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) FLIGHT CREW REPORTED DURING SHORT FINAL, SELECTING THE FLAPS FROM 25 DEGREES TO 40 DEGREES, THE ACFT YAWED SEVERELY. VISUAL CHECK OF THE FLAP REVEALED THE LT FLAP AT FULL DOWN AND THE RT FLAP AT APPROX 25 DEGREES. THE ACFT LANDED WITHOUT FURTHER INCIDENT. MAINT CONFIRMED THE ASYMMETRIC CONDITION AND FOUND THE LT FLAP DRIVING PAST THE "DOWN" LIMIT SWITCH ACTUATION POINT AND THE LT FLAP L/E ALSO BUCKLED AT THE MID-FLAP TRACK AREA. LT AND RT FLAP TRANSMISSIONS, MOTOR AND DRIVE CABLES WERE INSPECTED. SUSPECT THE ASYMMETRIC CONDITION DUE TO LT FLAP DRIVING PAST THE DOWN LIMIT AND THE EXCESSIVE DRIVING TORQUE CAUSED THE INTERNAL DRIVE CABLE SPLINES TO SKIP CAUSING THE SPLIT FLAP CONDITION. THE FOLLOWING MAINT 1L72 3O3 O A20SO E14EA 5 CP33EA 20081118 SO 2008 11 18 CA080825004 120080820G24604817102 CLAMP PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2A GL FAULTY W O OTHER G MULTIPLE FAILURE ININSP/MAINT 1 CA (CAN) FLIGHT CREW REPORTED ALL FLIGHT CONTROL TRIM AND BOTH ENGINE COWL FLAP INDICATORS INOP. MAINT INVESTIGATION ISOLATED 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. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081201 CE 2008 12 1 CA080826001 120080812G32603086070843004 LIGHT BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL MLG INDICATOR INOPERATIVE W O OTHER P NO WARNING INDICATION DEDESCENT 1 CA (CAN) LANDING GEAR MOTOR CONTROL CIRCUIT BREAKER FOUND POPPED WHEN THE GEAR WAS SELECTED DOWN FOR LANDING. GEAR WAS LOWERED BY EMERGENCY EXTENSION INDICATING (3) GREEN BUT THE IN TRANSIT LIGHT WAS STILL ON. ACFT EXPERIENCED A NOSE GEAR COLLAPSE 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 INDICATION OF THE NOSE NOT LOCKED. 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20081118 EA 2008 11 18 CA080826002 220080824G7321252444057 FCU BEECH 99 99 1154002CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL LT ENGINE FAILED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 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 ENGINE A REPLACEMENT FCU WAS INSTALLED. ENG RUNS AND FLIGHTS WERE COMPLETED WITH NO FURTHER PROBLEMS. 1L72 3T4 T A14CE E4EA 6 CP15EA 20081124 EU 2008 11 24 CA080826003 120080815G2440 UNKNOWN SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE GROUND POWER UNKNOWN W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) GPU VOLTAGE SPIKED WHILE PROVIDING POWER FOR ENGINE START. GROUND POWER WAS SHUT OFF AND ENGINES STARTED USING INTERNAL BATTERIES. BOTH ESSENTIAL DC ELECTRICAL CBS FOUND TRIPPED WHILE PERFORMING TAXI CHECK LIST. RETURNED TO GATE. 2L72 4T4 TRTA52EU E8NE6 20081118 EU 2008 11 18 CA080826004 120080819G3213 STRUT SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE LT MLG CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF CHECKS COMPLETED AND CONDITION LEVER RETARDED, RESULTING IN CONFIG WARNING AND OAT LIGHT ILLUMINATING. THIRD OCCURANCE. UNSCHEDULED LANDING MADE. (FUEL BURNED OFF TO ACCOMODATE LANDING WEIGHT) THE LT MLG WAS NOT FULLY EXTENDED DUE TO AIR REMAINING IN THE OLEO. THE LG SERVICING WAS REPEATED USING A POWER SERVICING CART, NO FURTHER FAULTS FOUND ON SUBSEQUENT GEAR SWINGS. 2L72 4T4 TRTA52EU E8NE6 20081120 EU 2008 11 20 CA080826005 120080818G3260 SQUAT SWITCH SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE LANDING GEAR OUT OF RIG W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF CHECKS WERE COMPLETED AND CONDITION LEVERS RETARDED, CONFIG WARNING AND OAT LIGHT CAME ON. UNSCHEDULED 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 THE 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. 2L72 4T4 TRTA52EU E8NE6 20081118 2008 11 18 CA080826006 120080825G541485410587 SKIN PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE LT NACELLE CRACKED W K NONE O OTHER ININSP/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 BEING 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 CP7NE 20081120 CE 2008 11 20 CA080826007 120080826G793126060154RX INDICATOR CESSNA208 208 2073702CE PWA PT6 PT6A114 52043NE HARTZLHCB3T HCB3TN3 GL OIL PRESSURE DEFECTIVE W O OTHER O OTHER NRNOT REPORTED 1 CA 107 (CAN) OIL PRESSURE NEEDLE INDICATES HIGH OIL PRESSURE WHEN ENGINE IS OPERATING (100- 105 PSI) READS OFF OF ZERO WHEN ENGINE IS NOT OPERATING (10-15 PSI) 106.5 HRS SINCE OVERHAUL. 1H71 3T3 TNTA37CE E4EA 6 CP15EA 20081120 CE 2008 11 20 CA080826008 120080825G32406119 CYLINDER PN9122 CESSNA172 172K 2072430CE LYC O320 O320E2D 41508EA MLG CORRODED W K NONE O OTHER ININSP/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). 1H71 3O3 ONT3A12 E274 20081120 SO 2008 11 20 CA080827001 120080827G521012030027001 SHIM 1454101760 EMB 145 EMB145LR 3260212SO PAX DOOR CORRODED W O OTHER O OTHER ININSP/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 FOUND HEAVELY CORRODED. DUE TO THE EXPENSION PRODUCE BY THE CORROSION, SOME BRACKET FASTENER WAS BROKEN AND THE ATTACHED FRAME P/N: 145-25299-001 WAS DEFORMED. (TC NR 20080827001) 2L72 4T RTT00011AT 20081120 NM 2008 11 20 CA080828001 120080826G7920AE7077093 FLEX LINE DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE NR 2 ENGINE DAMAGED W E ENGINE SHUTDOWN K FLUID LOSS CRCRUISE 1 CA (CAN) AN ACFT EXPERIENCED AN IN-FLIGHT ENGINE INCIDENT. THE CREW OBSERVED SUDDENLY THE OIL PRESSURE INDICATOR DROPPED TO "0" ASSOCIATED WITH THE ENG NR 2 LOW PRESS CAUTION LIGHT AND MASTER WARNING LIGHT. FLIGHT CREW SHUT DOWN THE ENGINE NR2 IAW QRH PROCEDURES, ACFT MADE A SATISFACTORY SINGLE ENGINE LANDING. ON GROUND, MAINT PERFORMED EXTERNAL VISUAL INSP AROUND 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081120 EA 2008 11 20 CA080828002 120080818G5610NP13932112 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 10871 (CAN) BEGIN QUOTE "DISC - WINDOW SHATTERED INFLIGHT WHEN FLYING C/A - RAR FOS WINDOW" END QUOTE. 2L72 4F RTA21EA 20081120 EA 2008 11 20 CA080828003 120080820G2910601R752863 HYDRAULIC LINE CNDAIRCL600 CL6002B19 1900309EA HYDRAULIC SYS CRACKED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 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 ELBOW WERE REPLACED , ACFT BACK TO SERVICE. 2L72 4F RTA21EA 20081124 EU 2008 11 24 CA080828004 120080828G2720137312E401 FITTING BAG JETSTMJETSTM3112 1500220EU GARRTTTPE331TPE33110UGR 29069NE RUDDER WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TAPER PINS PN SP28N14 FOUND SLIGHTLY LOOSE AT SPRING END FITTING ASSY. 2L72 4T4 TRTBA15CAA E4WE 20081120 NE 2008 11 20 CA080828005 220080827G726031070371 SPUR GEAR GARRTTTPE331TPE33110UGR 29069NE MCAULY4HFR344HFR34C652 NE GEARBOX DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FRONT GEAR CASE ON ENG REMOVED FOR TORQUE RING REPLACEMENT. PITTING FOUND ON SPUR AND HELICAL GEAR ASSY. CONSULTATION WITH ENGINE OVERHAUL FACILITY IS ON GOING. 4 T E4WE 6 C3PNE 20081120 CE 2008 11 20 CA080828006 120080827G7197 WIRE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL OUT OF POSITION W E ENGINE SHUTDOWN F FLT CONT AFFECTED DEDESCENT 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 WITH TORQUE INCREASE ON FWD MOVEMENT, NORMAL OPERATION. PWR LEVER WAS MOVED FWD TO HIGHER POWER SETTING AND ENG RESPONDED. STILL, WHEN RETARDING PWR LEVER TO FLIGHT IDLE, TORQUE REMAINED AT 1600 FT/LBS. CREW THEN DETERMINED THAT IT WAS CONSIDERED A RUNAWAY TORQUE SITUATION, DECLARED AN EMERGENCY, THEN SHUTDOWN AND SECURED THE RT ENG. A SAFE LANDING WAS CARRIED OUT AT THE DESTINATION AIRPORT STOPPING 3/4 DOWN THE RUNWAY. EMERGENCY CREWS MET THE ACFT AND ALL PASSENGERS AND CREW1L72 4T4 T A24CE E4EA 6 CP15EA 20081120 NE 2008 11 20 CA080829001 220080827G7421REM40E SPARK PLUG DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE ENGINE DEFECTIVE W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS ININSP/MAINT 1 CA (CAN) ON TROUBLESHOOTING LT MAG DROP (100 RPM), REAR SPARK PLUGS WERE REPLACED WITH NEW SPARK PLUGS OBTAINED FROM RELIABLE SOURCE WITH CERTIFICATION. ENG WAS GROUND RUN AND MAG CHECK CONDUCTED AND RPM DROP ON LT MAG WAS 150RPM. AFTER INSPECTING 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. 1H71 3R3 RRCA806 5E1 20081120 NM 2008 11 20 CA080829002 120080805G249791252ZC7C4001 CONTACTOR BOEING737 737232 1384475NM PWA JT8 JT8D17 52049NE ELECTRICAL SYS FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC TOTAKEOFF 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 CONTACTOR 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) 2L72 4F4 FRTA16WE E2EA 20081120 EU 2008 11 20 CA080829003 120080829G2841SIC6734 MODULE GE SIC505911 AIRBUSA319 A319112 3930323EU CFMINTCFM56 CFM565B6P 13018NE FUEL SYSTEM IMPROPER PART W K NONE O OTHER ININSP/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 RECEIVED WITH -04 CPU BOARDS, WHICH IS NOT CONSIDERED A PROPER CONFIGURATION. ACFT WAS UNDER A "N" (USA) REGISTRATION WHEN THE COMPUTER WAS FITTED TO THE ACFT. 2L72 4F4 FRTA28NM 20081120 EA 2008 11 20 CA080829004 220080826G7314200F5002R PUMP PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA FUEL SYSTEM LEAKING W O OTHER K FLUID LOSS ININSP/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. 1L72 3O3 O A20SO E14EA 20081126 EA 2008 11 26 CA080829005 220080829G74146350 MAGNETO GROB 120 G120A 1660208EU LYC O540 AEIO540D4D5 EA HARTZLHCC3Y HCC3YR GL ENGINE FAILED W D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TXTAXI/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 STUDENT 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 MAGNETO 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 SHORT1L71 3O3 ORTA49CE 1E4 5 CP25EA 20081120 SO 2008 11 20 CA080829006 120080829G27204004009 TORQUE TUBE 4004638 PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2A GL RUDDER CORRODED W K NONE O OTHER ININSP/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 FOUND ON LOWER INTERNAL SURFACES. PART REMOVED FROM SERVICE UNSERVICEABLEV. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081120 CE 2008 11 20 CA080829007 120080828G3240420001263 VALVE 99123682 CESSNA525 525B 2076616CE RESERVOIR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 361 (CAN) DURING DAILY INSP, THE PRESSURE WAS FOUND LOW ON THE EMERGENCY GEAR/BRAKE RESERVOIR. BOTTLE WAS REMOVED, VALVE AND FITTINGS WERE LEAK CHECKED WITH SNOOP AND CRACK WAS FOUND IN BOTTOM OF VALVE NEAR GAUGE BOSS. 1L72 4F RTA1WI 20081120 CE 2008 11 20 CA080902001 120080806G27100510105364 CONTROL CABLE CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL AILERON FRAYED W K NONE F FLT CONT AFFECTED ININSP/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 AT WS 71.125 RESULTING IN SEVERE DAMAGE TO THE CABLE. CABLE REPLACED. UNFORTUNATELY THE CABLE HAD BEEN REMOVED BEFORE PICTURES WERE TAKEN OF THE WORN CABLE. UWN1 AND 3 SIMULATE THE CABLE OVER THE CHAFE STRIP USING THE NEW CABLE, AND UWN2 SHOWS THE DAMAGED OLD CABLE. 1H71 3O3 ONT3A12 1E10 5 NP857 20081120 CE 2008 11 20 CA080902002 120080827G24324076 BATTERY MTSBSIMU2 MU2B60 5780460CE GARRTTTPE331TPE33110 29053NE HARTZLHCB4T HCB4TN5 GL THERMAL RUNAWAY W H DEACTIVATE SYST/CIRCUITS M OVER TEMP ININSP/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 BATTERY 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. 1H72 3T4 TRTA10SW E4WE 6 CP40EA 20081124 EU 2008 11 24 CA080902003 120080826G2750978732000 CONTROL SYSTEM PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL FLAP SYS MALFUNCTIONED W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION CLCLIMB 1 CA 6586 (CAN) CREW REPORTED FLAPS MOVED ONLY A FEW DEGREES UP AFTER SELECTING "0" FROM TAKEOFF POSITION "15" IN THE INITIAL CLIMB PHASE. "FLAP" CAUTION ILLUMINATED. ACFT RETURNED TO BASE, TROUBLESHOOTING REVEALED POWER DRIVE UNIT AT FAULT. PDU REPLACED, FUNCTION CHECKS SATISFACTORY. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081120 CE 2008 11 20 CA080902004 120080816G32331FA1004323 BARREL 1143800411 BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL MLG ACTUATOR CRACKED W O OTHER K FLUID LOSS ININSP/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 32-3870 WHICH CALLS FOR NDT OF THE END CAP. 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20081120 SO 2008 11 20 CA080902005 120080831G321315200 HOUSING ERAM 110P241021 EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL NLG STRUT BROKEN W K NONE O OTHER ININSP/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 ACFT PITCHED RT AND FULL LT BRAKE WAS USED TO KEEP THE ACFT ON THE RUNWAY. THE ACFT MOMENTARILY LT THE RT SIDE OF THE RUNWAY 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. 1L72 4T4 T A21SO E4EA 6 CP15EA 20081120 EU 2008 11 20 CA080902006 120080813G6123 AUTOFEATHER SYS AEROSPATR72 ATR72 EU PWA PW120 PW127 NE NR 2 ENGINE MALFUNCTIONED W C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 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 ENGINE AFU WAS REPLACED AND THE ACFT RELEASED FOR SERVICE. 2H72 4T4 TRT E20NE 20081120 NE 2008 11 20 CA080902007 220080815G7250 TURBINE AEROSPATR72 ATR72 EU PWA PW120 PW127 NE ENGINE DAMAGED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE AT 10000 FEET, THE OIL PRESSURE DROPPED TO THE RED BAND ACCOMPANIED BY A LOW OIL PRESSURE WARNING. THE ENGINE WAS SHUT DOWN. POST EVENT EXAMINATION OF THE ENG SHOWED DAMAGE IN THE POWER TURBINES. THE ENGINE WILL BE REMOVED AND SENT FOR REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRT E20NE 20081120 NE 2008 11 20 CA080902008 220080819G7200 ENGINE CESSNA560 560XL 2076702CE PWC 545 PW545B NE FLAMED OUT W D RETURN TO BLOCK X ENGINE FLAMEOUT TXTAXI/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. 2L72 4F4 FRTA22CE E00059EN 20081120 EU 2008 11 20 CA080902009 120080809G6123 AUTOFEATHER SYS AEROSPATR72 ATR72 EU PWA PW120 PW127 NE RT ENGINE UNKNOWN W EA ENGINE SHUTDOWN UNSCHED LANDING FR FLT CONT AFFECTED PARTIAL RPM/PWR LOSS CLCLIMB 1 CA (CAN) DURING CLIMB THE RT ENGINE PROPELLER FEATHERED UNCOMMANDED. PILOT SHUTDOWN THE ENGINE AND RETURNED TO AIRPORT, WHERE AN UNEVENTFUL SINGLE ENGINE LANDING TOOK PLACE. THE AFU IS SUSPECT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRT E20NE 20081120 NE 2008 11 20 CA080902010 220080805G7321 FUEL CONTROL FOKKERF27 F27MK50 EU PWA PWA120PW125B NE LT ENGINE UNKNOWN W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE THE LT ENGINE EXPERIENCED A SUDDEN TORQUE AND ITT INCREASE. THE CREW RETARDED THE POWER LEVER BUT THE 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. 2H72 4T4 TRTA817 E20NE 20081126 NE 2008 11 26 CA080902011 220080902G7414BL600646201 MAGNETO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE CONTAMINATED W O OTHER W INADEQUATE Q C ININSP/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 PROTRUDING ABOVE MAG HSG PARTING SURFACE. THE COIL TAB SHOULD BE LEVEL + OR - 5 DEGREES, THIS TAB WAS BENT APPROXIMATELY 10 DEGREES UP. TAB HAD CONTACTED THE METAL WASHER ON THE DISTRIBUTOR GEAR AND HAD STARTED TO WEAR THE TAB AND WASHER. THE COIL 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. 1G71 3O3 O H11NM 1E4 20081120 CE 2008 11 20 CA080903001 120080902G8011149NL STARTER CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL ENGINE MALFUNCTIONED W K NONE O OTHER ININSP/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 SUSPECTED TO NOT COMPLETELY ENGAGE RING GEAR. STARTER WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. 1H71 3O3 ONT3A12 1E10 5 NP857 20081120 SO 2008 11 20 CA080903004 120080801G7920SA00402SE HOUSING SA00402SE PIPER PA30 PA30 7103002SO LYC O320 IO320B1A 41508EA HARTZLHCE2Y HCE2YL2 GL OIL FILTER CRACKED W O OTHER K FLUID LOSS NRNOT 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 REMAINED IN THE FILTER HSG. RT REMOTE FILTER HSG THREADED STUD FOUND TO HAVE 0.020" WALL THICKNESS AT THE NON-THREADED PORTION. 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 THICKNESS. 1L72 3O3 O A1EA 1E12 5 CP9EA 20081120 WP 2008 11 20 CA080903005 120080813G243514924HT MOUNT ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE STARTER CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) STARTER MOUNT PAD CRACKED THROUGH BY FRONT MOUNTING HOLES. 1G71 3O3 O H11NM 1E4 20081120 EA 2008 11 20 CA080903006 120080831G3230NAS16128 O-RING CNDAIRCL604 CL604 1900301EA GE CF34 CF343B 30069NE LANDING GEAR DETERIORATED W D RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 5135 (CAN) DEPARTING, EN ROUTE, NR3 HYDR SYS LO PRESS. LIGHT CAME (ON) AND QTY READ 2 PERCENT. ACFT RETURNED TO BASE. INVESTIGATION SHOWED A (BLOWN) SEAL ON PRIORITY VALVE IN THE LANDING GEAR WHEEL WELL. O-RING FOUND DETERIORATED. REPLACED O-RING, FUNCTION TESTED AND RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20081120 NM 2008 11 20 CA080903007 120080208G5320HL10878 COLLAR BOEING777 777222 1385219NM FASTENER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 40041 (CAN) FOUND DURING INSP, SEVERAL HI-LOCK COLLARS CRACKED. ALL HI-LOCK COLLARS REPLACED IAW SRM 51-40-02. 2L72 4F RTT0001SE 20081120 SW 2008 11 20 CA080903008 120080828G56102719442003 WINDSHIELD SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE COCKPIT CRACKED W I CABIN DEPRESSURIZATION O OTHER DEDESCENT 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 FAILURE. THE TREND OF PREMATURE FAILURES OF THESE WINDOWS FOR THIS OPERATOR CONTINUES AS IS LIKEY CAUSED DUE TO SUBSTANDARD PARTS. 2L72 4T4 TRTA8SW E4WE 5 CP10NE 20081120 2008 11 20 CA080903009 120080903G3411 FITTING GARRTTTFE731TFE73140 29001NE PITOT/STATIC SYSLEAKING W K NONE O OTHER ININSP/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. AN EXCESSIVE LEAK RATE WAS NOTICED ON THE NR1 SIDE AND ISOLATED TO THE FLEX LINE AT THE NR1 ADC STATIC FITTING. UPON FINDING 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 120080828G56102719442003 WINDSHIELD SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE COCKPIT CRACKED W I CABIN DEPRESSURIZATION O OTHER DEDESCENT 1 CA (CAN) ON DESCENT AT APPROX 13000FT THE LT HEATED WINDSHIELD CRACKED. MAINT REPLACED THE WINDSHEILD AND NO PREXISTING DAMAGE WAS FOUND WHICH WOULD HAVE CONTRIBUTED TO THE WINDOW CRACKING. PREMATURE FAILURE OF THESE WINDOWS IS NOT UNCOMMON. 2L72 4T4 TRTA8SW E4WE 5 CP10NE 20081120 NM 2008 11 20 CA080903011 120080903G29136617303 SHAFT BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU HYDRAULIC PUMP SHEARED W O OTHER J WARNING INDICATION DEDESCENT 1 CA (CAN) DURING DESCENT ENGINE THE NR2 HYDR PUMP CAUTION LIGHT CAME ON ACFT CONTINUE NORMAL LANDING. NR2 HYDR PRESS BEING MAINTAINED BY PTU MAINT. FOUND EDP SHAFT SHEARED. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081120 EA 2008 11 20 CA080903012 120080827G2810215640014 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE LT WING LEAKING W O OTHER K FLUID LOSS ININSP/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. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20081118 EA 2008 11 18 CA080903013 120080827G2810215640024 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE LT WING LEAKING W K NONE K FLUID LOSS ININSP/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 SYSTEM LEAK CHECKED AND FOUND SERVICEABLE. 2H72 4T4 TRTA14EA E20NE 20081118 EA 2008 11 18 CA080903014 120080827G2810K215T6400212 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE LT WING LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) FUEL LEAKING FROM LT WING. FUEL CELLS REMOVED LEAK CHECKED. FUEL CELL NR 4 FAILED LEAK CHECK. NEW CELL INSTALLED SYSTEM LEAK CHECKED AND FOUND SERVICEABLE. 2H72 4T4 TRTA14EA E20NE 20081118 WP 2008 11 18 CA080903015 120080816G2435 GEAR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE STARTER GEN WORN W K NONE O OTHER ININSP/MAINT 1 CA 277 (CAN) STARTER TEETH FOUND WORN, REPLACED WITH A SERVICEABLE STARTER. 1G71 3O3 O H11NM 1E4 20081118 2008 11 18 CA080903016 220080903G7414 ROTOR SLICK MAGNETO BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 135 (CAN) CUSTOMER RETURNED MAG FOR WARRANTY PURPOSES. MAG ROTOR SHAFT WAS BROKEN BETWEEN THE DRIVE END BEARING AND THE MAGNET 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 UNDER THE DRIVE GEAR AS PER TCM SB03-7. THE HUB WAS INSPECTED AS PER SLICK SB1-07 AND NO CRACKING WAS FOUND. MAG WAS RETURNED TO MANUFACTURER FOR FURTHER INVESTIGATION. 20081118 2008 11 18 CA080904001 420080902G2562 BATTERY ELT LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) ELT WAS FUNCTION TESTED DURING ROUTINE SCHEDULED INSPECTION AND WOULD NOT TRANSMIT. SUBSEQUENT INSPECTION AT AVIONICS SHOP REVEALED LEAKING BATTERY. 20081118 CE 2008 11 18 CA080904002 120080826G3060 BOOT CESSNA206 T206H 2073303CE LYC O540 TIO540AJ1A EA MCAULY3D36C B3D36C432 GL PROP DEICE SEPARATED W K NONE O OTHER ININSP/MAINT 1 CA 523 (CAN) DEICE BOOT RETAINING STRAP SEPARATING FROM NR 3 BLADE, DISCOVERED DURING ANNUAL INSP. (AT ELECTRICAL LEAD AREA). NR 3 DEICE BOOT REPLACED. MCCAULEY SL2006-5 PERFORMED ON ALL 3 BOOTS. 1H71 3O3 ORTA4CE E14EA 5 CP58GL 20081219 WP 2008 12 19 CA080904003 120080901G6310C1883 SPRAG CLUTCH ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAIN ROTOR DAMAGED W C ABORTED TAKEOFF O OTHER TOTAKEOFF 1 CA 3773 1921 (CAN) UNTIL THE OFFICIAL REPORT ARRIVES, THIS IS WHAT IS DETERMINED HAPPENED. DURING TAKEOFF THE PILOT EXPERIENCED A LOUD NOISE AND THEN ACFT YAWED SLIGHTLY. THE ACFT LANDED WITHOUT INCIDENT. THE CLUTCH WAS REPLACED AND ACFT RETURNED TO SERVICE. DETAILS WILL BE BROUGHT FORWARD ONCE THE CLUTCH IS DISASSEMBLED AND A TEAR DOWN REPORT IS AVAILABLE. 1G71 3O3 O H11NM 1E4 20081118 EU 2008 11 18 CA080904004 120080903G32109321921210 BOLT PILATS PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL PIVOT PIN BROKEN W A UNSCHED LANDING N FALSE WARNING CLCLIMB 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 WEIGHT 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 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081118 EA 2008 11 18 CA080904006 220080904G7414 COIL BENDIX PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA MAGNETO DAMAGED W K NONE O OTHER ININSP/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 TOUCHING THE INSULATION COVERING THE COIL (APPROX. 10 DEGREES). THE CARBON BRUSH HAD WORN THE EXTERNAL EDGE ONLY. THIS TAB IS SUPPOSED TO BE LEVEL + OR - 5 DEGREES. THE TAB WAS BENT BACK UP DURING THE 500 HOUR INSPECTION AND RETURNED TO SERVICE. 1L72 3O3 O A20SO E14EA 20081119 2008 11 19 CA080905001 120080903G32469595601143 GROMMET BFGOODRICH MLG WHEEL MISMARKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) VALVE STEM GROMMET SEAL PN TRRG30 WAS CROSS REFERENCED THEN ORDERED FROM AN ACFT MANUFACTURE SUPPLIER USING THE CROSS 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 VISUAL 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 TRRG30 (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 120080902G2497M275008SP3U00 WIRE HARNESS HAMFLU 761339D CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE ADG BROKEN W K NONE O OTHER ININSP/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 CORROSION AND BREAK IN SEVERAL STRANDS OF THE WIRES. ALL 3 WIRES WERE REPLACED AS AN ASSEMBLY P/N M27500-8SP3U00. 2L72 4F4 FRTA21EA E15NE 20081119 NE 2008 11 19 CA080905003 220080903G7530658385 CONTROLLER BOEING727 727260 138408KNM PWA JT8 JT8D17 52049NE BLEED SYSTEM MALFUNCTIONED W O OTHER EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 CA (CAN) AT FL300, TOP OF DESCENT, AS THRUST REDUCTION COMMENCED, LARGE BANG WAS EXPERIENCED BY THE FLIGHT CREW WITH FLUCTUATIONS IN NR 2 ENGINE PARAMETERS. ENGINE WAS IDLED FOR THE REMAINDER OF THE FLIGHT AND SHUT DOWN UPON LANDING. MX PERSONNEL CARRIED OUT TROUBLESHOOTING AND THE PRESSURE RATIO BLEED CONTROLLER WAS REPLACED. THE PRBC HAS BEEN SENT TO AN OVERHAUL FACILITY AND AWAITING COMPLETE STRIP REPORT TO VERIFY DEFECTIVE PRBC. 2L73 4F4 FRTA3WE E2EA 20081119 SW 2008 11 19 CA080905004 120080904G2497 WIRE FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR 29081NE MCAULY4HFR344HFR34C652 NE MASTER SWITCH BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/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. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081119 NE 2008 11 19 CA080905005 220080824G7250 TURBINE BLADES CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE ENGINE FRACTURED W BA EMER. DESCENT UNSCHED LANDING YA ENGINE STOPPAGE FLAME/FIRE CRCRUISE 1 CA (CAN) APPROX 45 MINUTES INTO THE FLIGHT PILOT REPORTED ENGINE TROUBLE AND WAS ATTEMPTING AN EMERGENCY LANDING. CONTROL OF THE ACFT WAS LOST DURING LANDING AND THERE WAS A POST CRASH FIRE. EXAMINATION OF THE ENGINE REVEALED FRACTURED COMPRESSOR TURBINE (CT) BLADES. CT BLADES ARE ORIGINAL TO ENGINE MFG. MFG HAS REQUESTED COMPRESSOR TURBINE DISK AND BLADES TO BE RETURNED FOR ANALYSIS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1H71 3T3 T A37CE E4EA 20081222 NE 2008 12 22 CA080905006 220080904G7323B2475 GOVERNOR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE FAILED W O OTHER O OTHER LDLANDING 1 CA 1557 (CAN) PILOT WAS LANDING THE ACFT AND THE RPM DROPPED DUE TO THE GOVERNOR NOT HOLDING THE REQUIRED RPM, GOVERNOR REPLACED. 1G71 3O3 O H11NM 1E4 20081119 CE 2008 11 19 CA080905007 120080904G5220 TAB BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA EMERGENCY EXIT BENT W K NONE O OTHER ININSP/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 MANNER. 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 PROTRUDING 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 EXISTED SINCE MANUFACTURE. AN INSPECTION OF THE REMAINDER OF OUR FLEET FOR THIS CONDITION REVEALED NO OTHER FAULTS. 1L72 3T4 TRT3A20 E4EA 20081119 SW 2008 11 19 CA080905008 120080902G215020475546 A/C PACK FRCHLDSA227 SA227CC 3377522SW GARRTTTPE331TPE33111U 29073NE MCAULY4HFR344HFR34C652 NE LT DAMAGED W O OTHER B SMOKE/FUMES/ODORS/SPARKS APAPPROACH 1 CA (CAN) ON APPROACH, THE PILOT NOTICED SMOKE COMING OUT OF FRESH AIR VENTS AND MOMENTS LATER LT WING OVERHEAT LIGHT CAME ON. ACFT LANDED WITHOUT INCIDENT. MX WENT TO LOOK AND FOUND THAT THE LT COOLING TURBINE HAD A CATASTROPHIC FAILURE. THE LT BLEED SYSTEM WAS MEL`D AND DISABLED. NUMEROUS RUNS WERE COMPLETED WITH NO FURTHER SMOKE COMING INTO CABIN. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081119 SO 2008 11 19 CA080908001 120080829G71206666200 MOUNT PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 7948 (CAN) CRACKS WHERE TUBES ARE WELDED TO NOSE STRUT. CHAFING WHERE AERO DUCT HOSE TOUCHED MOUNT. 1L71 3O3 O 2A13 E274 20081119 EA 2008 11 19 CA080908002 220080827G7414K3975 COIL SLICK CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MAGNETO OPEN W D RETURN TO BLOCK RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA 1895 (CAN) PILOTS NOTED A DEAD LT MAGNETO WHEN PERFORMING PRE FLIGHT RUNUP. MAGNETO WAS REMOVED AND DISASSEMBLED AND FOUND THAT THE COIL SECONDARY WINDING WAS OPEN CIRCUIT (SHOULD BE BETWEEN 1500-20,000) - MANGETO WAS REPLACED. 1H71 3O3 ONT3A12 1E10 20081119 CE 2008 11 19 CA080908003 120080902G28101183810021 FLOAT VALVE BEECH 200 B200 1152922CE PWA PT6 PT642A NE FUEL CELL DISLODGED W O OTHER O OTHER NRNOT 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. 1L72 4T4 T A24CE E4EA 20081119 NM 2008 11 19 CA080908004 120080902G27222334003001 ACTUATOR DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE RUDDER BYPASSING W O OTHER FG FLT CONT AFFECTED MULTIPLE FAILURE NRNOT REPORTED 1 CA 4180141801 (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 APPEARED THEY WERE CROSS CONTROLLING THE ACFT WITH THE TRIMS. MX DISCOVERED THAT BOTH THE NR 1 AND 2 SYSTEM RUDDER ACTUATORS WERE 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, FUNCTIONAL AND LEAK CHECKS COMPLETED. RUDDER CABLES TENSIONED. ACFT TEST FLOWN SATISFACTORILY AND RETURNED TO SERVICE. NOTE:MX TA2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081119 EU 2008 11 19 CA080908005 120080908G5753Z4243300014 SPRING ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA FLAP SPRING BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FLAP SPRING LOCK WAS DISCOVERED CRACKED DURING SCHEDULED MX. SPRING BROKE COMPLETELY DURING REMOVAL. 1L71 3O3 O0 A76EU 1E10 20081119 SW 2008 11 19 CA080908006 120080507G6320430040003 TRANSMISSION BELL 430 430 1182150SW MAIN ROTOR DAMAGED W BA EMER. DESCENT UNSCHED LANDING CJ F.O.D. WARNING INDICATION CRCRUISE 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 LOUD RUMBLING SOUND. THE COCKPIT INDICATION SHOWED THAT THE ACFT HAS A TRANSMISSION CHIP AND A CHIP SUMP CAUTION. THE PILOT DESCENDED DOWN TO APPROXIMATELY 400 FEET READY TO PREPARE FOR DITCHING. AFTER APPROXIMATELY 1 1/2 TO 2 MINUTES, THE RUMBLING STOPPED AND THE ACFT NOISE WENT BACK TO NORMAL. THE PILOT PROCEEDED TO LAND WITHOUT EVENT AND SHUT DOWN THE HELICOPTER. 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 1G72 3U RTH9SW 20081119 SO 2008 11 19 CA080908007 220080828G853007502385AWL RISER CESSNA185 A185E 2072818CE CONT O520 IO520F 17032SO NR 5 CYLINDER CRACKED W K NONE O OTHER ININSP/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 0750161-31. 1H71 3O3 O 3A24 E5CE 20081119 EA 2008 11 19 CA080908008 220080906G8530AEL85099 CYLINDER CESSNA172 172N 2072434CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL NR 1 SEPARATED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 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 CYLINDER 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 AND 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. 1H71 3O3 ONT3A12 E274 5 NP910 20081124 CE 2008 11 24 CA080908009 120080908G551112326212 SPAR CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/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. 1H71 3O3 O A4CE E5CE 20081124 CE 2008 11 24 CA080908010 120080808G5312071111229 BULKHEAD CESSNA185 A185F 2072821CE CONT O550 IO550D 17042SO FUSELAGE CRACKED W K NONE O OTHER ININSP/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. 1H71 3O3 O 3A24 E3SO 20081124 CE 2008 11 24 CA080909001 120080907G2435 COOLING FAN TRW BEECH 99 99 1154002CE PWA PT6 PT6A28 EA STARTER GEN BROKEN W K NONE O OTHER ININSP/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 BETWEEN THE GENERATOR AND THE CASE. 1L72 3T4 T A14CE E4EA 20081124 2008 11 24 CA080909003 220080909G7414M3611 CAM SLICK MAGNETO WORN W K NONE O OTHER ININSP/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. THE 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 RETURNED TO UNISON/SLICK FOR INSPECTION. 20081124 2008 11 24 CA080909004 220080909G7414M3611 CAM SLICK LOBES WORN W K NONE O OTHER ININSP/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. 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 RETURNED TO UNISON/SLICK FOR INSPECTION. 20081124 EA 2008 11 24 CA080909005 120080819G27501104SD1201 SHAFT CNDAIRCL600 CL6002B19 1900309EA TE FLAPS BROKEN W O OTHER F FLT CONT AFFECTED TXTAXI/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 GATE 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. 2L72 4F RTA21EA 20081124 CE 2008 11 24 CA080910001 120080903G7160155212914 INTAKE DUCT CESSNA337 337F 2075725CE CONT O360 IO360C 17025SO MCAULY2AF34CD2AF34C306 GL CRACKED W O OTHER E VIBRATION/BUFFET APAPPROACH 1 CA 2712 (CAN) DURING A ROUTINE PATROL FLIGHT THE PILOT EXPERIENCED A VIBRATION IN THE AREA OF THE REAR ENGINE. HE ELECTED TO RETURN TO THE AIRPORT AND MADE AN UNSCHEDULED LANDING WITHOUT INCIDENT. UPON INSPECTION BY THE MX CREW, IT WAS DISCOVERED THAT THE FWD EDGE OF THE INNER & OUTER SECTIONS OF THE AIR COOLING DUCT HAD PARTIALLY SEPARATED FROM THE NOSE CAP. THIS ALLOWED ROM AIR TO FLOW BETWEEN THE INNER & OUTER SECTIONS AND CAUSED THE INNER DUCT TO VIBRATE AND SUBSEQUENTLY CRACK & BREAK. 1H72 3O3 O A6CE E1CE 5 CP5EA 20081124 WP 2008 11 24 CA080910002 120080818G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE INOPERATIVE W O OTHER O OTHER NRNOT REPORTED 1 CA 345 (CAN) THE STARTER WAS NOT CRANKING OVER ENGINE, STARTER REPLACED. 1G71 3O3 O H11NM 1E4 20081124 SO 2008 11 24 CA080910003 220080715G8520 COTTER PIN CONT CONT O200 O200A 17020SO CONNECTING ROD MISSING W K NONE O OTHER ININSP/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 220080909G7530 SWITCH EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE NR 2 FAULTY W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 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 FLIGHT WAS NOT OVERWEIGHT FOR LANDING AND THERE WAS NO EMERGENCY DECLARED. BLEED NR1 FAULT CODE HAS BEEN TROUBLESHOT. BLEED O/P SWITCH NR2 REPLACED IAW AMM. TORQUE MOTOR LINES TO VALVE CHECKED OK. 2L72 4F4 FRTA57NM E00070EN 20081119 SW 2008 11 19 CA080910005 120080709G6510407340340103 DISC PACK BELL 407 407 1182206SW ALLSN 250C 250C47B GL T/R DRIVESHAFT CRACKED W O OTHER Z SIGNIFICANT FAILURE REPORT ININSP/MAINT 1 CA (CAN) FOUND (3) DISCS CRACKED AND ALL DISCS CORRODED ON THE FWD NR 1 POSITION. 1G71 3U3 UO H2SW E1GL 20081119 NE 2008 11 19 CA080910006 220080820G7314C8187B PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYSTEM MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA 993 (CAN) FUEL PUMP ELECTRICALLY MALFUNCTIONING, REPLACED FUEL PUMP. 1G71 3O3 O H11NM 1E4 20081126 SO 2008 11 26 CA080911001 120080908G812089682002 SHROUD PIPER PA46 PA46350P 7104602SO LYC O540 TIO540AE2A 41532EA AIR PUMP LOOSE W O OTHER F FLT CONT AFFECTED CRCRUISE 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 ROTATION OCCURRED DURING FULL POWER, THIS TRAPPED THE LINKAGE ON THE TURBO CONTROLLER IN THE CLIMB POWER POSITION. THE LOWER AIRPUMP COOLING SHROUD ASSEMBLY(P/N 89682-002), ROD(P/N 89682-008), HOSE (P/N 89684-002), AND CLAMP(P/N 5544-896) WERE 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 SATISFACTORILY1L71 3O3 ORTA25SO E14EA 20081119 EA 2008 11 19 CA080911002 120080909G5610601R330339 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT CRACKED W K NONE Z SIGNIFICANT FAILURE REPORT DEDESCENT 1 CA 1823818238 (CAN) ON DESCENT THE LT WINDSHIELD CRACKED AT FL370 AND THE LT WINDSCREEN HEAT CAUTION CAME ON. AN EMERGENCY WAS DECLARED, BUT THE A/C LANDED WITHOUT INCIDENT. THIS WINDSHIELD HAD OVER 18,000 HRS AND WAS WELL ABOVE THE AVERAGE FOR NORMAL FAILURE RATES. 2L72 4F4 FRTA21EA E15NE 20081119 NM 2008 11 19 CA080911003 120080905G27821U1110 ACTUATOR BOEING727 727225 1384077NM PWA JT8 JT8D9A 52048NE KRUEGER FLAP FAILED W A UNSCHED LANDING K FLUID LOSS CLCLIMB 1 CA (CAN) DURING CLIMB THROUGH APPROX 2,000 FT NR1 ENGINE LOW HYDR PRESSURE LIGHT ILLUMINATED, SYS `A` HYDRAULIC OIL AND PRESSURE LOSS. ACFT RETURNED TO DEPARTURE. NR5 KRUGER FLAP ACTUATOR FOUND FAILED AND ATTACH BRACKET DAMAGED. REPLACED ACTUATOR AND TESTED IAW AMM 29-11-00 AND 27-81-22. KRUEGER FLAP ATTACH BRACKET REPAIRED IAW SRM 51-10-2. ACFT RETURNED TO SERVICE. 2L73 4F4 F A3WE E2EA 20081119 EU 2008 11 19 CA080911004 120080908G32205322012165 BARREL NUT PILATS 532001203 PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL NLG CORRODED W O OTHER O OTHER NRNOT 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 RUBBER 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. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081126 NM 2008 11 26 CA080911005 120080911G7920443330 O-RING BOEING727 727247 138408FNM PWA JT8 JT8D15 52051NE GEARBOX OIL LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) WHILE CLIMBING OUT, NOTICED ENG NR 1 OIL QUANTITY INDICATOR SLOWLY DECREASING, QUANTITY WAS 1 GALLON AT TOP OF CLIMB. 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 ENG, 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 CHECK, SIGNIFICANT OIL LEAK FROM GEARBOX TO OIL COOLER TUBE. FOUND OIL LINE HAD TENSION ON IT WHEN REMOVING TUBE. SEAL SPLIT AND REAR PIECE MISSING. PROCURED SEAL P/N 443330 (REV.A). CPN 0043234 INSTALLED SEAL AND REPOSITIONED TUBE, REMOVE2L73 4F4 F A3WE E2EA 20081119 NE 2008 11 19 CA080911006 220080904G7200JT8D9A ENGINE BOEING727 727227 1384078NM PWA JT8 JT8D9A 52048NE NR 2 FAILED W AE UNSCHED LANDING ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA 544691313 (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. 2L73 4F4 F A3WE E2EA 20081119 NE 2008 11 19 CA080912001 220080825G7321 ECU PWA PW121 PW121 52124NE NR 1 ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN JX WARNING INDICATION ENGINE FLAMEOUT CRCRUISE 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 220080826G7320 HMU BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE LT ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CRCRUISE 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. 2H72 4F4 FRTA16SW E25EA 20081119 EA 2008 11 19 CA080912003 220080902G8530SL11625 PLUG CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL ENGINE WORN W K NONE O OTHER ININSP/MAINT 1 CA 1300 (CAN) THE PISTON PIN PLUGS IN TWO CYLINDERS ON THE ENGINE WORE UNUSUALLY AND CAUSED ALUMINUM METAL CONTAMINATION THROUGHOUT THE ENGINE. 1H71 3O3 ONT3A19 E223 5 NP50GL 20081119 CE 2008 11 19 CA080912004 120080912G57533516505030 HINGE BRACKET BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL TE FLAP DAMAGED W K NONE O OTHER ININSP/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 HINGE OTBD BRACKET WITH DAMAGE CAUSED BY THE ROLLER BEARING FLANGE APROX 0.025 DEEP. DECIDED TO PERFORM DVI OF ALL REMAINING FLAP ROLLER ASSY AND REMOVE THE RT OTBD FLAP. FOUND THE SAME DAMAGE ON THE RT OTBD FLAP INBD HINGE OTBD BRACKET. INVESTIGATION SHOWED THAT THE BEARINGS AND FLAPS WERE INSTALLED CORRECTLY. BRACKETS ARE BEING REPLACED. 2L72 4T4 T A24CE E4EA 6 CP56GL 20081120 CE 2008 11 20 CA080912005 120080911G249710936102247 WIRE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL LT NACELLE BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) LT ENGINE FAILED TO ROTATE ON START UP. MAINT DISCOVERED LT STARTER GEN WIRE FEED THRU ASSY (CONSISTS OF 3 PARALLEL HEAVY GUAGE WIRES) TERMINAL ENDS BURNED OFF AT START CONTROL PANEL TERMINAL. NEW WIRE FEED THRU ASSY ON ORDER. START CONTROL PANEL ON ORDER. WILL CARRY OUT A FLEET WIDE INSP OF LT AND RT NACELLES FOR WIRE FEED THRU TERMINAL ENDS FOR CONDITION. 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20081120 SW 2008 11 20 CA080912006 120080908G7920991930811 TUBE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 29073NE MCAULY4HFR344HFR34C652 NE OIL SYSTEM CRACKED W K NONE K FLUID LOSS ININSP/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 OF 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. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20081120 2008 11 20 CA080912007 120080817G5210 ATTACH FITTING BRAERO 1371008C409 GARRTTTPE331TPE33110UGR 29069NE PAX DOOR CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SEVERE CORROSION NOTED AT MAIN CABIN DOOR ATTACH FITTINGS. CORROSION ALSO NOTED UNDER SEVERAL DOOR SEAL CLIPS. DOOR DEEMED BEYOND ECOMONICAL REPAIR AND REPLACED WITH SERVICEABLE UNIT. 4 T E4WE 20081120 2008 11 20 CA080912008 120080912G5210 FITTING BRAERO 1371008C409 GARRTTTPE331TPE33110UGR 29069NE PAX DOOR CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THIS DOOR WAS INSTALLED AS A REPLACEMENT DUE TO SEVERE CORROSION FOUND ON ORIGINAL DOOR. REPLACEMENT DOOR INSPECTED AND CORROSION DISCOVERED UNDER SEVERAL DOOR INFLATION SEAL CLIPS. CLIPS REMOVED AND CORROSION REMOVED AND SURFACES TREATED. CLIPS REINSTALLED. 4 T E4WE 20081126 GL 2008 11 26 CA080915006 120080826G3260 WARNING LIGHT BOMBDRBD700 BD7001A10 1390006GL HNYWL AS907 AS90711A 33908WP MLG ILLUMINATED W A UNSCHED LANDING J WARNING INDICATION APAPPROACH 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 LANDING GEAR EXTENSION PROCEDURE WAS CARRIED OUT IAW AFM. ON APPROACH, ACFT DESCENDED TO AN ALTITUDE OF 500 FEET WHEN ENHANCED GROUND PROXIMITY WARNING SYSTEM "TOO LOW GEAR" UN-MUTABLE AURAL WARNING SOUNDED, WHICH PROMPTED PILOT TO GO AROUND AND 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 ENGIN2L72 4F4 FRTT00003NYE00010LA 20081120 WP 2008 11 20 CA080915007 120080816G2822D7431 PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYSTEM FAULTY W K NONE O OTHER NRNOT REPORTED 1 CA 267 (CAN) THE AUX FUEL PUMP LIGHT WOULD NOT EXTINGUISH, AUX PUMP REPLACED. 1G71 3O3 O H11NM 1E4 20081120 EU 2008 11 20 CA080916001 120080911G323372MEF20151 SWIVEL FITTING SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE ROTOL R389 R3894123F25 NE RT MLG SHEARED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKE-OFF, DURING GEAR RETRACTION, THE RT MLG DOWNLOCK ACTUATOR SWIVEL FITTING LOCATED ON THE DRAG BRAC, FAILED. THIS CAUSED A SUBSTANTIAL LOSS OF FLUID. AN EMERGENCY GEAR EXTENSION WAS CARRIED OUT AND THE ACFT RETURNED TO BASE WITH NO FURTHER PROBLEMS. 2L72 4T4 TRTA52EU E8NE6 6 CP30NE 20081120 CE 2008 11 20 CA080916002 120080806G2752 ROLL PIN CESSNA C1450046RX CESSNA208 208 2073702CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL TE FLAP SHEARED W O OTHER FP FLT CONT AFFECTED NO WARNING INDICATION ININSP/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 INSPECTION. IN THIS INSTANCE PRIMARY FLAP OPS WERE NOT AFFECTED. 1H71 3T3 TNTA37CE E4EA 5 CP60GL 20081120 EU 2008 11 20 CA080916004 120080915G4940 CONTROL BOX AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE73131C 01518NE COCKPIT DEFECTIVE W K NONE B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 12101 (CAN) PILOTS HAVE BEEN REPORTING INTERMITTENT SULPHUR SMELL IN THE ACFT. WHILE TROUBLESHOOTING, THE MECHANIC NOTICED THAT THE APU DOOR WAS OPEN AND APU MASTER AS OFF. WHEN THE APU SWITCH WAS CYCLED TO CLOSE THE DOOR, SPARKS STARTED TO APPEAR 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. 2L73 4F4 F A46EU E6WE 20081126 2008 11 26 CA080916005 420080830G3457GNS530430W GPS MALFUNCTIONED W O OTHER GH MULTIPLE FAILURE ELECT. POWER LOSS-50 PC CRCRUISE 1 CA (CAN) GNS530W AND GNS430W SIMULTANEOUSLY LOOSE SATELLITE RECEPTION. SATELLITES ARE REAQUIRED BETWEEN 2 AND 20 MINUTES LATER. 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 PROBLEM WITH THE GNS SOFTWARE AND THE ALASKA WAAS GROUND STATION. THE WAAS ENGINE IN THE GNS NAVIGATOR MUST BE SHUT OFF IN THAT AUXILLARY MENU SETUP PAGE TO PREVENT SATELLITE LOSS IN NORTHERN LATTITUDES. THIS INFORMATION IS NOT READILLY AVAILABLE TO OPERATORS AND OWNERS. 20081222 CE 2008 12 22 CA080916006 120080912G555104320049 ATTACH BRACKET CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA SNSNCH72C 72CK EA VERTICAL STAB CRACKED W K NONE O OTHER ININSP/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 WAS CRACKED AROUND A RIVET HOLE FOR THE PREVIOUSLY INSTALLED NUT PLATES. AD PREVIOUSLY ALLOWED REMOVAL OF NUT PLATES. THIS OPERATOR HAS SEEN AT LEAST TWO OTHER FAILURES OF THIS PART. A/C TT IS ~22,950 HOURS OPERATING IN AN FTU. REPLACED PART WITH A USED, INSPECTED SERVICEABLE PART DUE TO NO PARTS SUPPORT FROM MFG. NOTE: NO PICTURE, NOT ABLE TO TAKE A PICTURE FROM THE INSIDE OF THE BRACKET. 1H71 3O3 ONT3A19 E223 5 NP9045 20081120 CE 2008 11 20 CA080916007 120080728G2436C6110040101 VOLT REGULATOR CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO ELECTRICAL SYS SHORTED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA (CAN) ACFT WAS IN CRUISE FLIGHT WHEN THE PILOT NOTICED THE ELECTRICAL SYSTEM WAS DRAINING THE BATTERY. THE ACFT LANDED AND 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 AND A NEW ALTERNATOR WAS ALSO INSTALLED AS A PRECAUTIONARY MEASURE. THE ACFT WAS GROUND RUN & ELECTRICAL SYSTEM CHECKED SERVICEABLE. 1H71 3O3 O A4CE E5CE 20081120 2008 11 20 CA080916008 120080913G3040 MOTOR GARRTTTPE331TPE3312201A WP WINDSHIELD MALFUNCTIONED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) SKYVAN EN ROUTE WITH 2 CREW ,1 PASSENGER ON BOARD ADVISED ARCTIC RADIO THEY HAD SMOKE IN COCKPIT, CREW REQUESTED EMERGENCY VEHICLES, ACFT LANDED SAFELY, CREW AND PASSENGER WERE CHECKED AT LOCAL NURSING STATION AND RELEASED. FURTHER INVESTIGATING PROBLEM, IT WAS FOUND THAT THE WINDSHIELD WIPER MOTOR HAD BURNT OUT. WIPER MOTOR WAS REPLACED WITH A SERVICEABLE UNIT , FUNCTION CHECKED AND RELEASED BACK TO SERVICE. TOTAL TIME ON WIPER MOTOR UNKNOWN. 4 T E3WE 20081120 2008 11 20 CA080917001 120080826G28203014884 TUBE PWA PT6T PT6T3B 52045NE FUEL SYSTEM CRACKED W K NONE K FLUID LOSS ININSP/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 120080911G32138A04000021 SUPPORT 8000FLOATS DHAV DHC3 DHC3 2800202EA PWA PT6 PT6A34 52043EA MLG AXLE CRACKED W K NONE O OTHER ININSP/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. 1H71 3R4 T A815 E4EA 20081126 NM 2008 11 26 CA080917003 120080916G21333964401 SHUTOFF VALVE BOEING727 727247 138408FNM PWA JT8 JT8D15A 52051NE A/C PACK FAILED W JA DUMP FUEL UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMBOUT, SEPT 16 2008, PRESSURIZATION FAILED TO OPERATE NORMALLY. WHEN CLIMBING THROUGH 23,000 FT, CABIN ALTITUDE EXCEEDED 10000 FT. FUEL DUMP CARRIED OUT IN ORDER FOR ACFT TO RETURN TO DEPARTURE. CABIN PRESSURIZATION LEAK CHECK CARRIED OUT, NO FAULTS. PRESSURIZATION CONTROLLER AND PRESSURIZATION CONTROL PANEL REPLACED. GROUND PRESSURIZATION CHECKS CARRIED OUT WITH NO FAULTS DETECTED. ON SEPT 17, 2008, ACFT WAS DEPARTED. AS THE ACFT CLIMBED THROUGH 25000 FT, CABIN PRESSURIZATION FAILED TO OPERATE NORMALLY WITH MINIMAL CONTROL. ACFT RETURNED TO DEPARTURE FOR FURTHER TROUBLESHOOTING. TROUBLESHOOTING REVEALED NO PROBLEMS WITH THE PRESSURIZATION SYS BUT HAS REVEALED THAT THE RT PACK FLOW CONTROL AND 2L73 4F4 F A3WE E2EA 20081120 CE 2008 11 20 CA080917004 120080907G2750C3010010211 COUPLING CESSNA208 208 2073702CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL TE FLAP FAILED W O OTHER F FLT CONT AFFECTED ININSP/MAINT 1 CA (CAN) FLAP COUPLING FAILED DURING NORMAL LANDING PROCEDURES. UPON FAILING, THE PART BROKE INTO 2 PIECES, DISCONNECTING THE FLAP MOTOR FROM THE ACTUATOR ASSEMBLY. THIS RESULTED IN THE FLAPS STOPPING WHILE PARTIALLY EXTENDED. THE FLAPS WERE LEFT PARTIALLY EXTENDED FOR LANDING. THE CREW ELECTED NOT TO USE THE STANDBY FLAP MOTOR TO AVOID THE POTENTIAL FOR FURTHER DAMAGE TO THE FLAP ACTUATOR ASSEMBLY. 1H71 3T3 TNTA37CE E4EA 5 CP60GL 20081124 NE 2008 11 24 CA080917005 220080910G720090623 ENGINE BOEING777 777* UTILUSENM GE GE90 GE90115B 30048NE NR 1 VIBRATION W A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA 889 (CAN) IN CRUISE, THE FLIGHT EXPERIENCED A NR 1 ENGINE VIBRATION. THE ENGINE CONTINUED OPERATING NORMALLY BUT WITH VIBRATION. THE FLIGHT DIVERTED TO FAIRBANKS, ALASKA. AN ENGINE HAS BEEN SCHEDULED AND TOOLS, PARTS AND MANPOWER ARE CURRENTLY BEING SHIPPED TO ALASKA. ACFT IS OUT OF SERVICE. \ETQ INVESTIGATION NR 2917 INITIATED. 2L72 4F4 FRTT00001SEE00049EN 20081120 2008 11 20 CA080917006 420080902G6122 GOVERNOR CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE PROPELLER OUT OF ADJUST W EC ENGINE SHUTDOWN ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) DURING TAXI ROLL IN PREPARATION FOR TAKE-OFF, THE COMPRESSOR TURBINE SPEED (NG) DROPPED BY APPROX 2%. PILOT ADVANCED POWER LEVER AND ITT ROSE TO 740 DEG C WITH NO INCREASE IN NG. THE LOW OIL PRESSURE ANNUNCIATED AND PILOT OBSERVED ZERO OIL PRESSURE. THE PROPELLER FEATHERED UNCOMMANDED AND THE PILOT SHUT THE ENGINE DOWN. THE PROP GOVERNOR WAS ADJUSTED AND THE ACFT RETURNED TO SERVICE. 1H71 3T3 T A37CE E4EA 20081120 EA 2008 11 20 CA080917007 220080823G7200 ENGINE DHAV DHC8 DHC8* NM PWC 150 PW150A EA MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB PASSING THRU FL15, THE LOW OIL PRESSURE WARNING WAS ACTIVATED AND THE COCKPIT INDICATION WAS SEEN FALLING. THE CREW SHUT THE ENGINE DOWN AND THE ACFT RETURNED TO THE POINT OF DEPARTURE. NO TROUBLESHOOTING WAS DONE BY THE 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. 2H72 4T4 TRTA13NM E00062EN 20081120 CE 2008 11 20 CA080917008 120080808G5312071111210 BULKHEAD CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO FUSELAGE CRACKED W K NONE O OTHER ININSP/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 PREVIOUSLY REPAIRED AND HAS CRACKED AGAIN. 1H71 3O3 O 3A24 E5CE 20081120 NE 2008 11 20 CA080917009 220080904G7200 ENGINE LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE SHUTDOWN W D RETURN TO BLOCK RX PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT TXTAXI/GRND HDL 1 CA (CAN) PILOT REPORTED THAT DURING TAXI THE ENGINE EXPERIENCED UNCOMMANDED ROLL BACK AND SHUTDOWN. TROUBLESHOOTING INDICATED THAT THE ENGINE MAY HAVE ALSO EXPERIENCED AN OVERTEMP CONDITION AND WAS REMOVED FROM SERVICE FOR INSPECTION. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4F4 FRTA10CE E35NE 20081120 CE 2008 11 20 CA080917010 120080808G5312071111229 BULKHEAD CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO FUSELAGE CRACKED W K NONE O OTHER ININSP/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. 1H71 3O3 O 3A24 E5CE 20081120 CE 2008 11 20 CA080917011 120080808G5312071111229 BULKHEAD CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A NON-ROUTINE INSPECTION AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER LT AND RT CORNERS AT REAR FLOAT FITTINGS. 1H71 3O3 O 3A24 E5CE 20081120 NE 2008 11 20 CA080917012 220080907G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MALFUNCTIONED W BA EMER. DESCENT UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA (CAN) DURING A 5 MIN. RE-POSITIONING FLIGHT, THE ENGINE LOST POWER AND AN EMERGENCY LANDING WAS ATTEMPTED. THE ENGINE WILL BE RETURNED TO P&WC FOR INVESTIGATION. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1H71 3T3 T A37CE E4EA 20081120 NE 2008 11 20 CA080917013 220080908G7200 ENGINE BEECH B300 B300 1159232CE PWA PT6 PT6A60A 52043NE RIGHT MALFUNCTIONED W E ENGINE SHUTDOWN KJBFLUID LOSS WARNING INDICATION SMOKE/FUMES/ODORS/SPARKS CRCRUISE 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 ENGINE TORQUE WAS FLUCTUATING BETWEEN APPROXIMATELY 20% TO 40% WITH THE TEMPERATURE INDICATION RISING TO APPROXIMATELY 820 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 LEAKING FROM THE COWLING. THE ENGINE WILL BE REMOVED. 2L72 4T4 TRTA24CE E4EA 20081120 NE 2008 11 20 CA080917014 220080901G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE DEFECTIVE W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF, THE ENGINE LOST OIL PRESSURE. AN AIR TURNBACK WAS INITIATED AND THE ACFT LANDED AT THE POINT OF DEPARTURE WITH THE ENGINE RUNNING. POST FLIGHT INSPECTION FOUND OIL LEAKING AROUND THE ENGINE INTAKE AREA. THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIR. P&WC WILL CLOSELY MONITOR THE INVESTIGATION RESULTS AND ISSUE UPDATES TO TC. 1H71 3T3 T A37CE E4EA 20081120 NE 2008 11 20 CA080917015 220080905G7250 TURBINE BLADES AEROSPATR42 ATR42* 8680900EU PWA PW121 PW121 52124NE ENGINE DISTRESSED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 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 DISTRESS. 2H72 4T4 TRTA53EU E20NE 20081120 NE 2008 11 20 CA080917016 220080908G7200 ENGINE BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE MALFUNCTIONED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING A RE-POSITIONING FLIGHT, THE PILOT NOTED LOW AND FLUCTUATING OIL PRESSURE. THE ENGINE WAS SHUT DOWN AND SECURED AND A SINGLE ENGINE LANDING WAS PERFORMED. GROUND INSPECTION FOUND CONTAMINATION IN THE OIL FILTER AND FILTER BOWL. THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIR. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4F4 FRTA16SW E25EA 20081126 SW 2008 11 26 CA080917017 120080911G2597 CONNECTOR ARTEX BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL ELT MISINSTALLED W K NONE O OTHER ININSP/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 FULLY INSTALLED SO THE ELT ACTIVATION WAS NOT NOTICED. HAVE SINCE SPOKE WITH THE MFG AND FOUND THAT THIS IS A COMMON PROBLEM WITH THE INSTALLATION OF THE CONNECTOR NOT BEING INSERTED EXACTLY STRAIGHT, CAUSING THE PINS TO GROUND AND ACTIVATE ELT. 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. 1G71 3U3 U H2SW E4CE 20081124 2008 11 24 CA080917018 420080911G8300 GEARBOX PWC PW610 PW610FA 52267NE ENGINE DAMAGED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 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 PILOT COULD NOT RESTART THE ENGINE. INITIAL TROUBLESHOOTING MAY HAVE INDICATED DAMAGE TO THE ACCESSORY GEARBOX AND THE ENGINE 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 220080913G7220 INLET GUIDE VANE AMD FALC50FALCON2000 2730170NM PWC PW308 PW308C 52182NE NR 1 ENGINE MALFUNCTIONED W K NONE YJ ENGINE STOPPAGE WARNING INDICATION APAPPROACH 1 CA (CAN) IT IS REPORTED THAT 10 MINUTES BEFORE LANDING, ENGINE NR 1 SHUTDOWN BY ITSELF FOLLOWED BY A "NO DISPATCH" MSG ON THE COCKPIT DISPLAY. TROUBLESHOOTING SHOWED THAT THE IGV POSITION DID NOT MATCH THE REQUESTED VALUE. THE VIGV WAS REPLACED AND THE FAULT CLEARED. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4F4 FRTA50NM E00065EN 20081120 EU 2008 11 20 CA080918002 120080912G5753S5751202320 A/C PACK SNIAS S57512007004AEROSPATR72 ATR72212 8680945EU TE FLAP BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING C-CHECK INSPECTION (1C, 2C, 4C, CPCP2, A8), WHILE PERFORMING A DVI INSPECTION ON THE L INBD FLAP, THE INSPECTION REVEALED THAT THE FWD PICK-UP FITTING INBD LOG AT RIB 5 WAS BROKEN IN HALF. THE FITTING LOT NR IS P4110. THE BROKEN OFF PIECE WAS FOUND IN THE FLAP FAIRINGS. 2H72 4T RTA53EU 20081120 CE 2008 11 20 CA080918003 120080917G243400317 ALTERNATOR CESSNA337 337G 2075730CE CONT O360 IO360G 17025SO MCAULY2AF34CD2AF34C306 GL FWD ENGINE DAMAGED W K NONE J WARNING INDICATION CRCRUISE 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 ALTERNATOR, IT WAS DISCOVERED THAT THE DRIVE SHAFT HAD BEEN SHEARED OFF. THE DRIVE GEAR IN THE ENGINE WAS INSPECTED AND FOUND 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. 1H72 3O3 O A6CE E1CE 5 CP5EA 20081125 SW 2008 11 25 CA080918004 120080914G2913 HOUSING VICKERS SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HYDRAULIC PUMP SEPARATED W D RETURN TO BLOCK K FLUID LOSS TXTAXI/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 AND 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 TO HAVE PULLED OUT OF THE THREADS ALLOWING THE PUMP HALVES TO SEPARATE TO THE POINT OF PUMP FAILURE. THE COMPANY WILL SEND THE PUMP FOR WARRANTY REPAIR. 2L72 4T4 TRTA8SW E4WE 20081125 SW 2008 11 25 CA080918005 120080914G76032543161 SPRING BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL THROTTLE RETURN BROKEN W C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA 101 (CAN) DURING TAKEOFF THE LOW ROTOR HORN SOUNDED. THE PILOT ABORTED THE TAKEOFF, SHUT DOWN THE ENGINE AND CALLED MX. WHEN THE ENGINE COWL WAS OPENED THE FCU THROTTLE RETURN SPRING WAS FOUND IN THE BOTTOM OF THE ENGINE PAN. 1G71 3U3 U H2SW E4CE 20081125 CE 2008 11 25 CA080918006 120080909G273112601491 ACTUATOR CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO ELEVATOR TRIM CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION A AME FOUND HEAVY CORROSION (LEVEL 3) ON THE ACTUATOR. HE R&R THE PART. 1H71 3O3 O A4CE E5CE 20081126 2008 11 26 CA080919001 420080917G2562 MOUNT BRACKET PIPER PA28 PA28180 7102808SO LYC O360 O360A4A 41514EA ELT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE EXISTING ELT MOUNTING BRACKET WAS INSPECTED PRIOR TO REPLACEMENT OF THE VHF ELT WITH A 406 MHZ ELT. UPON REMOVING THE NARCO ELT10 MOUNTING TRAY, IT WAS DISCOVERED THAT ACFT ELT MOUNTING BRACKET WAS CRACKED AT EACH MOUNTING TRAY SCREW HOLE LOCATION. THE NARCO ELT TRAY WAS FOUND TO BE MOUNTED TO THE BRACKET USING ACCEPTABLE AN SCREWS AND SELF-CAPTIVE 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 INSTALLED. 1L71 3O3 O 2A13 E286 20081125 WP 2008 11 25 CA080919002 120080916G2421ALX8521RS ALTERNATOR ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 128 (CAN) ALTERNATOR HAS STRIPPED HOUSING 1G71 3O3 O H11NM E295 20081125 WP 2008 11 25 CA080919003 120080910G6310C0512 ACTUATOR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE CLUTCH DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 712 (CAN) CLUTCH ACTUATOR FOUND U/S DURING INSPECTION, SERVICEABLE ACTUATOR INSTALLED. 1G71 3O3 O H11NM 1E4 20081126 EA 2008 11 26 CA080919004 220080916G7261 NUT 766859C BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU OIL PUMP LOOSE W E ENGINE SHUTDOWN J WARNING INDICATION DEDESCENT 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. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081125 WP 2008 11 25 CA080919005 120080908G6310C0183 CLUTCH ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAIN ROTOR DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA 1920 (CAN) LOUD BANGING NOISE IN ACFT. CLUTCH REMOVED FOR TEARDOWN INSPECTION, SERVICEABLE CLUTCH INSTALLED. 1G71 3O3 O H11NM 1E4 20081125 WP 2008 11 25 CA080919006 120080826G6310C0512 CLUTCH ACTUATOR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAIN ROTOR DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA 1747 (CAN) DRIVE BELTS SLIPPING, SERVICEABLE ACTUATOR INSTALLED. 1G71 3O3 O H11NM 1E4 20081126 EU 2008 11 26 CA080919007 120080917G2110139312 SUPERCHARGER BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU ROTOL R4304 R2124304 EU CABIN PRESSURE INOPERATIVE W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 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 INSPECTED 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 CABIN SUPERCHARGERS REPLACED. GROUND RUNS AND FLIGHT TEST WERE COMPLETED, THE ACFT WAS FOUND SERVICEABLE AND RELEASED FOR SERVICE. 2L72 3T4 T A24EU A196 6 CP899 20081125 CE 2008 11 25 CA080919008 120080825G8011149NL STARTER CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA FAILED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 98 (CAN) STARTER FAILS TO ENGAGE, SERVICEABLE STARTER INSTALLED. 1H71 3O3 ONT3A12 1E10 20081125 2008 11 25 CA080919009 220080918G7414 ROTOR MAGNETO BROKEN W O OTHER R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 CA (CAN) CUSTOMER COMPLAINED ABOUT DEAD MAG. TIME IN SERVICE IS UNKNOWN. MAG WAS OPENED AND INSPECTED. THE ROTOR GEAR VANE SHOWED INDICATIONS OF RUBBING ON THE HALL EFFECT SENSOR AND HAD CONTACTED THE SENSOR. THIS STOPPED THE ROTOR GEAR WHICH 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 220080908G741410600646201 MAGNETO ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA ENGINE MALFUNCTIONED W O OTHER O OTHER NRNOT REPORTED 1 CA 331 (CAN) REMOVED DUE TO ERRATIC ENGINE RPM. 1G71 3O3 O H11NM E295 20081126 NE 2008 11 26 CA080919011 220080918G7414 BEARING BL6006163 ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO EXCESS PLAY W O OTHER W INADEQUATE Q C ININSP/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 500 HR INSP WAS CARRIED OUT AND THE MAG WAS RETURNED TO SERVICE. 1G71 3O3 O H11NM 1E4 20081201 CE 2008 12 1 CA080921001 120080919G3220AN17621A BOLT CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HARTZLHCJ3Y PHCJ3YF1 GL NLG CRACKED W K NONE O OTHER ININSP/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 CRACKS. 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 REQUIREMENTS. 1H71 3O3 O A4CE E5CE 5 CP36EA 20081201 NM 2008 12 1 CA080922001 120080917G3244DR0231T TIRE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NR 3 FAILED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 255 (CAN) PASSENGER REPORTED NR 3 TIRE BURST DURING TAKE OFF. CREW EXTENDED GEAR AND FA CONFIRMED TIRE WAS BLOWN. ACFT RETURNED 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. INSPECTION COMPLETED AND TIRE REPLACED, 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081201 EA 2008 12 1 CA080922002 220080822G7414 IMPULSE COUPLING CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL MAGNETO MISMANUFACTURED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA CGGPE (CAN) ENGINE WAS OVERHAULED AND STORED UNTIL AUGUST 2008. DURING INSTALLATION ON AUG. 22, 2008, IT WAS NOTICED THAT THERE 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 MAGNETOS WOULD NOT ENGAGE PROPERLY OR AT ALL. IT APPEARED THAT THE IMPULSE COUPLINGS HAD BEEN ASSEMBLED INCORRECTLY. 1H71 3O3 ONT3A19 E223 5 NP50GL 20081125 NE 2008 11 25 CA080922003 220080915G7313301114521 ADAPTER CESSNA208 208 2073702CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL REAR FUEL NOZZLECRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 400 (CAN) DURING LEAK TEST AFTER CLEANING LEAKAGE NOTED AT THE HEAD FUEL NOZZLE ADAPTER. 1H71 3T3 TNTA37CE E4EA 5 CP60GL 20081128 SW 2008 11 28 CA080922005 120080909G29102781032273 LINE FRCHLDSA227 SA227CC 3377522SW GARRTTTPE331TPE33111U 29073NE MCAULY4HFR344HFR34C652 NE HYDRAULIC SYS CRACKED W K NONE K FLUID LOSS ININSP/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. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081128 EA 2008 11 28 CA080922006 120080915G215078279015 ACM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE LEFT ODOR W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS APAPPROACH 1 CA 1324413244 (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. 2L72 4F4 FRTA21EA E15NE 20081128 EA 2008 11 28 CA080923002 120080922G56106003303021 WINDOW CNDAIRCL604 CL604 1900301EA GE CF34 CF343B 30069NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 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 SOUTHBOUND WHEN THE FAILURE OCCURRED. 2L72 4F4 FRTA21EA E15NE 20081128 EU 2008 11 28 CA080923003 120080912G539752802800 WIRE BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL CARGO HOOK BROKEN W K NONE O OTHER ININSP/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. 1G72 3U3 U H3EU E4CE 20081125 SW 2008 11 25 CA080923004 120080922G7933 OIL SYSTEM BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL ENGINE OVERTEMP W A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) ENGINE OIL TEMPERATURE INCREASED TO 100 DEG. C. 1G71 3U3 U H2SW E4CE 20081128 NE 2008 11 28 CA080923006 220080806G72503022312 TURBINE WHEEL BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE ENGINE DISINTEGRATED W C ABORTED TAKEOFF XJ ENGINE FLAMEOUT WARNING INDICATION TOTAKEOFF 1 CA 10566 (CAN) WHILE HOVERING DURING TAKEOFF, NR1 PWR SECTION LOST POWER (PILOT REPORTED HEARING LOUD BANG). ACFT PUT DOWN WITHOUT FURTHER INCIDENT, NR2 POWER SECTION SHUTDOWN. POWER SECTION REPLACED. ACFT RETURNED TO SERVICE. PRELIMINARY INSP REVEALED FAILURE OF THE PT DISK. PARTIAL BLADE SEPARATION AND FOD TO EXHAUST DUCT. 1G71 4U4 U H4SW E22EA 20081128 NM 2008 11 28 CA080924001 120080920G3240900005831PR BRAKE ASSY EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE NR 3 FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/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, INSPECTED 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. 2L72 4F4 FRTA56NM E00063EN 20081125 SW 2008 11 25 CA080924002 120080924G5302205001731101 SUPPORT BELL 412 412 1182202SW PWA PT6T PT6T3 52045EA TAIL ROTOR SERVOCRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2322 (CAN) CRACKS FOUND IN SUPPORT CASTING NEAR UPPER ATTACHMENT TO AIRFRAME. 1G72 4U4 U H4SW E22EA 20081125 SW 2008 11 25 CA080924003 120080924G5302205001731101 SUPPORT BELL 412 412 1182202SW PWA PT6T PT6T3 52045EA TAIL ROTOR SERVOCRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2322 (CAN) CRACKS FOUND IN SUPPORT CASTING NEAR UPPER ATTACHMENT TO AIRFRAME. 1G72 4U4 U H4SW E22EA 20081125 SW 2008 11 25 CA080924004 120080924G5302205001731001 SUPPORT BELL 412 412 1182202SW PWA PT6T PT6T3 52045EA TAIL ROTOR SERVOCRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2322 (CAN) TAIL ROTOR SERVO SUPPORT FOUND CRACKED NEAR UPPER ATTACHMENT FLANGES. 1G72 4U4 U H4SW E22EA 20081128 SW 2008 11 28 CA080924005 120080918G561036004314SS WINDSHIELD GULSTM690TP 690D 3970405SW GARRTTTPE331TPE3315 01514WP ROTOL R306 R306382F7 GL COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 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 SLAP. THEY COULD SEE THEN THAT THE RT WINDSHIELD WAS CRACKED. ACFT RETURNED WITHOUT FURTHER INCIDENT. INSP FOUND THE WINDSHIELD OUTER PANEL HAD SHATTERED. WINDSHIELD IS BEING RETURNED FOR INSP AND WARRANTY CONSIDERATION. WINDSHIELD REMOVED FROM ACFT AND STRUCTURE INSPECTED. NO DEFECTS FOUND. 1H72 3T4 T 2A4 E4WE 6 CP8EU 20081128 2008 11 28 CA080924007 120080924G2820 LINE GARRTTTFE731TFE73140 29001NE FUEL SYSTEM CHAFED W K NONE O OTHER ININSP/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 120080924G282025W653120634 LINE GARRTTTFE731TFE73140 29001NE FUEL SYSTEM CHAFED W K NONE O OTHER NRNOT 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 QTY PROBE MOUNTING BRACKET. THE LINE WAS REPLACED. 4 F E1NM 20081128 EA 2008 11 28 CA080924009 120080924G3210C6UM11104 ATTACH FITTING DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL MLG CRACKED W K NONE O OTHER ININSP/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. 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20081128 NE 2008 11 28 CA080924011 220080922G7200 TORQUE SHAFT AEROSPATR72 ATR72 EU PWA PW120 PW127 NE NR 1 ENGINE CRACKED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE TORQUE WAS LOST ON NR 1 ENGINE, SUBSEQUENTLY THE ENGINE WAS SHUTDOWN BY THE CREW. POST FLIGHT INSPECTION 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. 2H72 4T4 TRT E20NE 20081128 NE 2008 11 28 CA080924012 220080815G7200 ENGINE BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE LEFT FAILED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION HOHOVERING 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. 1G71 4U4 U H4SW E22EA 20081128 NE 2008 11 28 CA080924013 220080922G7200 ENGINE DORNERDO32 DO328100 2996000NM PWA 119 PW119B NE FLUCTUATES W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) AT ABOUT 50 METERS FROM THE ARRIVAL GATE, THE ENG PARAMETERS STARTED FLUCTUATING. PILOT SHUTDOWN THE ENG. NO REPORTED DAMAGE. TROUBLESHOOTING IN PROGRESS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA45NM E20NE 20081128 NM 2008 11 28 CA080925001 120080914G561080260008 WINDOW BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 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. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081128 CE 2008 11 28 CA080925002 120080924G5511053200198 SPAR CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA HORIZONTAL STAB CRACKED W A UNSCHED LANDING CA F.O.D. FLAME/FIRE NRNOT REPORTED 1 CA 9629 (CAN) DURING THE 100 HRS/ANNUAL INSP, IT WAS DISCOVERED THAT THE HORIZONTAL STABILIZER FRONT SPAR ASSY (PN 0532001-98) AND THE RE-INFORCEMENT SPAR (PN 0531037-1) HAVE CRACKS AT 2 PLACES, ABOUT .5 INCH IN LENGTH, RADIATING FROM THE CENTER LIGHTENING HOLE BETWEEN BOLT ATTACHMENT AREA. 1H71 3O3 ONT3A12 E274 20081128 EA 2008 11 28 CA080925003 220080919G7414BL600646201 MAGNETO ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA ENGINE FAILED W O OTHER X ENGINE FLAMEOUT DEDESCENT 1 CA 151 (CAN) PILOT SNAGGED THERE WAS A HIGH ENGINE RPM RISE. MAGNETO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. 1G71 3O3 O H11NM E295 20081128 EA 2008 11 28 CA080925004 220080919G7414BL600646201 MAGNETO ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA ENGINE FAILED W O OTHER X ENGINE FLAMEOUT APAPPROACH 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. 1G71 3O3 O H11NM E295 20081201 NE 2008 12 1 CA080925006 220080908G7200 ENGINE SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE NR 2 MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION DEDESCENT 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 LOW RPM AUDIO HORN SOUNDED ALONG WITH ILLUMINATION OF NR 2 ENGINE LOW OIL PRESSURE LIGHT. A SCAN OF THE ENGINE GAUGES REVEALED 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 SERVICE 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 TH2G72 4U4 U H4EA E15EA 20081202 NE 2008 12 2 CA080925007 220080908G7321 FUEL CONTROL SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING RMJPARTIAL RPM/PWR LOSS OVER TEMP WARNING INDICATION NRNOT 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 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 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 AFTER A COMPLETE GROUND CHECK ACFT WAS RETURNED TO SERVICE. THE ENG, FREE TURBINE AND FCU WERE RETURNED TO MFG FOR AN OVER TEMP INSP AND EVALUATION AS TO A POSSIBLE CAUSE OF THE ROLL BACK. 2G72 4U4 U H4EA E15EA 20081128 SW 2008 11 28 CA080925009 120080804G243523032027 STARTER GEN BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) STARTER WAS SNAGGED BY PILOT WHICH MOTORED UNDER ITS OWN POWER. EXCESSIVE ROTATION CAUSED INTERNAL DAMAGE. STARTER WAS REPLACED AND NO ISSUES WERE NOTED. 1G71 3U3 U H2SW E4CE 20081128 WP 2008 11 28 CA080925012 120080924G6310C1883 SPRAG CLUTCH ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAIN ROTOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1781 (CAN) CLUTCH WAS REMOVED FROM ACFT FOR VISUAL INSP DUE TO ISSUES WITH CLUTCH ASSY`S. TEARDOWN REVEALED THE FOLLOWING: CAGE CRACKED AT 1 CROSSBAR, SHAFT C166-4 WORN UNDERSIZE, HSG C167-3 WORN OVERSIZE AND OIL WAS VERY BLACK. 1G71 3O3 O H11NM 1E4 20081202 GL 2008 12 2 CA080925013 120080918G2421ALU8521LS ALTERNATOR DIAMONDA40 DA40 2990002GL INTERMITTENT W A UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CLCLIMB 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 TERMINAL THAT IS CRIMPED TO THE BRUSH LEAD IS SLIGHTLY LARGER THAN THE HEAD OF THE TERMINAL BOLT. IT IS ACTUALLY THE RING TERMINAL THAT TOUCHES THE HSG. THIS TRIPS THE VOLTAGE REGULATOR OFF LINE. THE ALTERNATOR SWITCH NEEDS TO BE CYCLED TO RESET THE REGULATOR. 1L71 3O NTA47CE 20081128 WP 2008 11 28 CA080925014 120080923G6310C1883 SPRAG CLUTCH ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAIN ROTOR CHIPPED W O OTHER O OTHER LDLANDING 1 CA 596 (CAN) PILOT HEARD POSSIBLE NOISE WITH SLIPPAGE OF DRIVE TRAIN. CLUTCH WAS REMOVED TO VERIFY NO INTERNAL DAMAGE. THE FOLLOWING WAS FOUND DURING A TEARDOWN: 1 PEANUT INNER EAR CHIPPED, SHAFT PN C166-4 WORN UNDERSIZE, HSG C167-3 WORN OVERSIZE AND OIL VERY BLACK. 1G71 3O3 O H11NM 1E4 20081128 NE 2008 11 28 CA080926001 220080925G7414103571651 COIL ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO WORN W K NONE O OTHER ININSP/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 HOUSING 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. 1G71 3O3 O H11NM 1E4 20081128 NM 2008 11 28 CA080926002 120080926G291082920010227 PIPE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE HYD SYSTEM DAMAGED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/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 DISCOVERED 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 RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081128 SW 2008 11 28 CA080926003 120080914G272027720065 ARM SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL RUDDER PEDAL CRACKED W K NONE O OTHER ININSP/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 ATTACHES 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. 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20081128 CE 2008 11 28 CA080926004 120080922G2840S38521 RESISTOR CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL FUEL INDICATOR WORN W K NONE N FALSE WARNING ININSP/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 ENOUGH 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 AROUND 350 OHNS WHEN THE FLOAT ARM WAS WIGGLED. UNIT WAS REPLACED AND NO FURTHER ISSUES WERE NOTED. 1H71 3O3 ONT3A12 1E10 5 NP857 20081201 EU 2008 12 1 CA080926005 120080925G2597E0111241057 CONNECTOR AIRBUS310 A310 EU GE CF6 CF680 30025NE GALLEY POWER DAMAGED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) DURING STATION TRANSIT, CABIN CREW REPORTED SMOKE COMING FROM AFT GALLEY, WITH SMOKE WARNING, WHEN GALLEY ELECTRICAL PWR WAS PUT ON. GALLEY POWER WAS REMOVED FROM THE AFT GALLEY. DURING MX INVESTIGATION, THE GALLEY CONNECTOR 38 MC WAS FOUND DAMAGED WITH PINS AND SOCKET BURNED. CONNECTOR WAS REPLACED AND CAMPAIGN WAS INITIATED TO INSPECT ACFT EQUIPMENT WITH THE SAME TYPE OF INSTALLATION. 2L72 4F4 FRTA35EU E13NE 20081202 EA 2008 12 2 CA080927001 220080926G8520130L119 PISTON RING ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA ENGINE BROKEN W A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 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 REPLACED. ACFT RETURNED TO SERVICE. 1G71 3O3 O H11NM E295 20081202 NE 2008 12 2 CA080929003 220080918G73218237002 FUEL CONTROL CESSNA560 560XL 2076702CE PWA 545 PW545A NE ENGINE FAILED W L ABORTED APPROACH XJ ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 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. 2L72 4F4 FRTA22CE E00059EN 20081209 SW 2008 12 9 CA080929005 120080924G6720369X2172313 PITCH LINK DOUG 500N MD500N 3030001SW ALLSN 250C 250C20B 03013GL TAIL ROTOR SEPARATED W K NONE O OTHER ININSP/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 ROTOR 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. 1G71 3U3 UNCH3WE E4CE 20081202 WP 2008 12 2 CA080929006 120080929G6310C0183 CLUTCH ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAIN ROTOR INOPERATIVE W K NONE O OTHER ININSP/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. 1G71 3O3 O H11NM 1E4 20081202 CE 2008 12 2 CA080929007 120080920G284338522 INDICATOR CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170* GL FUEL QTY INOPERATIVE W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FUEL QUANTITY SENDER FOUND ELECTRICALLY UNSERVICEABLE, READING EMPTY WHEN TANKS WERE FULL. SERVICEABLE FUEL SENDER INSTALLED. 1H71 3O3 ONT3A12 1E10 5 NP857 20081202 EA 2008 12 2 CA080930001 120080928G5280CC670105202003 DOOR CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 30049NE LT MLG MISSING W O OTHER D INFLIGHT SEPARATION APAPPROACH 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 ATTACHMENT POINT. LAST STRUCTURAL INSPECTION IAW AD CF2003-23 DONE 12 SEPT 2008. 2L72 4F4 FRTA21EA E00063EN 20081202 GL 2008 12 2 CA080930002 320080914G6110 PROPELLER FOUND FBA FBA2C 3640102EA LYC O540 O540A1C5 41532EA HARTZLHC92Z HC92ZK1 GL VIBRATION W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) PROPELLER REMOVED FOR EVALUATION DUE TO SMALL VIBRATION. NOT CONSIDERED SERIOUS. 1H71 3O3 O A7EA E295 5 CP892 20081202 NE 2008 12 2 CA080930003 220080831G7261 SEAL BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE ENGINE OIL LEAKING W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, THE OIL PRESSURE STARTED TO FLUCTUATE FOLLOWED BY A DROP TO ZERO, WHICH WAS ACCOMPANIED BY A GEARBOX 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 AND GEARBOX TC2523 WILL BE REMOVED AND FORWARDED FOR REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1G71 4U4 U H4SW E22EA 20081202 CE 2008 12 2 CA080930004 120080929G273005117821 YOKE CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C401 GL ELEV CONTROL CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) ASSEMBLY WAS FOUND CORRODED WHEN INSPECTED IAW SEB01-3. 1H71 3O3 O 3A24 E5CE 5 CP47GL 20081202 CE 2008 12 2 CA080930005 120080929G53400512128 BRACKET CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO FLAP PULLEY BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT FLAPS HAVE EXCESSIVE PLAY WHEN DEPLOYED. SYSTEM INVESTIGATED AND LT SIDE FLAP PULLEY BRACKET FOUND BROKEN. 1H71 3O3 O 3A24 E5CE 20081202 CE 2008 12 2 CA080930006 120080723G32464040A WHEEL CESSNA401 401 207590CCE CONT O520 TSIO520E 17040SO MCAULY3AF32C3AF32C505 GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RT MAIN WHEEL ASSY BEAD AREA FOUND CRACKED. WHEEL REPLACED WITH SERVICEABLE UNIT. 1L72 3O3 O A7CE E8CE 5 CP22EA 20081202 CE 2008 12 2 CA080930007 120080930G321024410071 SPACER LEAR 35 35A 5170602CE GARRTTTFE731TFE73122B 01518WP LT MLG ACTUATOR CRACKED W K NONE O OTHER ININSP/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, WAS FOUND CRACKED. RT ACTUATOR REMOVED, SPACER VISUALLY INSPECTED. NO CRACK INDICATIONS. BOTH ACTUATOR PILLARS REMOVED, CLEANED 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. 2L72 4F4 F A10CE E6WE 20081202 SO 2008 12 2 CA080930008 120080929G8120 SEAL PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL TURBOCHARGER LEAKING W O OTHER K FLUID LOSS LDLANDING 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 FLIGHTS. 1L72 3O3 O A20SO E14EA 5 CP33EA 20081202 CE 2008 12 2 CA080930009 120080920G29101013880175 LINE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL HYDRAULIC SYS RUPTURED W K NONE K FLUID LOSS ININSP/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 LINE. THE LINE HAD RUPTURED ABOUT 1 INCH FROM THE END FITTING RESULTING IN A SUBSTANTIAL FLUID LOSS. THE LINE WAS REPLACED WITH NO FURTHER ISSUES. 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20081202 NM 2008 12 2 CA081001001 120080916G7920 PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ENGINE OIL LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION DEDESCENT 1 CA (CAN) DURING DESCENT, THE LOW OIL PRESSURE WARNING FOR THE NR 2 ENGINE SOUNDED. THE PILOT ELECTED TO SHUTDOWN AND SECURE 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 THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA13NM E00062EN 20081202 EU 2008 12 2 CA081001002 120080930G2440 TERMINAL SAAB SF340 340B 7860101EU EXTERNAL POWER MELTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ACFT ARRIVED FROM CUSTOMER WITH EXTERNAL POWER INOP (MEL). AFTER INVESTIGATION, FOUND THE + TERMINAL MELTED AT THEN EXT PWR CONNECTOR. SHEET METAL REPAIR WAS PREVIOUSLY DONE AT THE EXT PWR CONNECTOR ATTACHMENT. BOTH TERMINALS WERE CRACKED HALF WAY. 2L72 4T RTA52EU 20081202 CE 2008 12 2 CA081001003 120080919G5751122005211 SKIN CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL AILERON CRACKED W K NONE O OTHER ININSP/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. 1H71 3O3 O A4CE E5CE 5 CP47GL 20081202 SW 2008 12 2 CA081001004 120080927G5302206031329103S FITTING BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL TAILBOOM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) UPPER LT TAILBOOM ATTACHMENT FITTING ON THE FUSELAGE SIDE FOUND CRACKED FROM THE RIVET HOLES. 1G71 3U3 U H2SW E1GL 20081202 2008 12 2 CA081001006 420080924G2397GNS430 WIRE UROCOPEC130 EC130B4 8680989EU TMECA ARRIELARRIEL2B1 60056NE COMM 1 SHORTED W O OTHER H ELECT. POWER LOSS-50 PC TXTAXI/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. 1G72 3U3 U H9EU E00054EN 20081202 SW 2008 12 2 CA081001007 120081001G2821ZT2CV06A08B CHECK VALVE BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL FUEL SYSTEM DIRTY W K NONE O OTHER ININSP/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 IN THE FUEL SYS. DURING THIS 2 MINUTE GROUND RUN THE ENG FLAMED OUT AFTER APP 90 SECONDS INDICATING AN AIR LEAK. FUEL SYS INSPECTED AND THE INLINE FUEL/CHECK VALVE WAS FOUND STUCK IN THE OPEN POSITION. WHEN THIS VALVE IS STUCK OPEN AIR CAN BE SUCKED FROM THE FRONT FUEL TANKS IF THEY ARE EMPTY. CHECK VALVES CLEANED AND HELICOPTER WAS GROUND RUN SATISFACTORILY. THIS WAS POSSIBLY CAUSED BY FUELING FROM DRUMS FOR AN EXTENDED PERIOD OF TIME AND A SMALL QUANTITY OF DIRT ENTERED THE FUEL SYS. 1G71 3U3 U H2SW E1GL 20081202 NM 2008 12 2 CA081001008 120080814G3000XD4N RELAY DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF* NE DEICE SYSTEM FAILED W O OTHER J WARNING INDICATION DEDESCENT 1 CA 4093540935 (CAN) DURING DESCENT FROM FL250, AS POWER WAS REDUCED BELOW 30 PERCENT TORQUE. WHEN DESCENDING THROUGH 23000` CABIN STARTED TO CLIMB RAPIDLY. DE-ICE PRESSURE CAUTION LIGHT ILLUMINATED. NO LOUD NOISES OR SQUEALS. MX INVESTIGATION FOUND RELAY 2121-K6 AT FAULT. RELAY REPLACED, ACFT RETURNED TO SERVICE. (NOTE: PART IS CONSIDERED AN EXPENDABLE AND TIMES NOT TRACKED, TIMES PROVIDED ARE AIRFRAME TIMES) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081202 CE 2008 12 2 CA081002001 120081002G3260SA24SDX111 SWITCH CESSNA340 340A 2076405CE CONT O520 TSIO520NB 17040SO MCAULY3AF32C3AF32C505 GL MLG INTERMITTENT W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) LANDING GEAR INTERMITTENTLY WOULD NOT RETRACT. FOUND ANNUNCIATOR PRESS TO TEST SWITCH INTERMITTENT. 1L72 3O3 O 3A25 E8CE 5 CP22EA 20081202 CE 2008 12 2 CA081002002 120081002G32301002573 PISTON CESSNA206 T206H 2073303CE LYC O540 TIO540AJ1A EA HARTZLHCF3Y HCF3YR1 GL MLG SEPARATED W O OTHER O OTHER NRNOT REPORTED 1 CA 51 (CAN) RT MLG FAILED TO RETRACT. FOUND HYDRAULIC CYLINDER PISTON HAD SEPARATED FROM CYLINDER RAM. 1H71 3O3 ORTA4CE E14EA 5 CP31EA 20081202 CE 2008 12 2 CA081002003 120080929G8120407809001 TURBINE WHEEL CESSNA340 340CESSNA 2076404CE CONT O520 TSIO520C 17040SO MCAULY3AF32C3AF32C87 GL TURBOCHARGER SEIZED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA 774 (CAN) TURBINE WHEEL SEIZED. TURBOCHARGER REMOVED, OVERHAULED TURBOCHARGER INSTALLED. 1L72 3O3 O 3A25 E8CE 5 CP22EA 20081202 NM 2008 12 2 CA081002004 120081001G2432 BATTERY BOEING737 737275C 13844ASNM PWA JT8 JT8D17 52049NE MASTER OVERHEATED W O OTHER BM SMOKE/FUMES/ODORS/SPARKS OVER TEMP TXTAXI/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. CAPTAIN WENT TO THE E&E BAY TO RESET THE APU BOX. APU START ATTEMPTED AGAIN, SAME RESULT. PILOT AGAIN RESET THE APU CONTROL 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 BATTERY CHARGING CIRCUIT WAS TESTED IAW WORKCARD. NO FAULTS WERE NOTICED, ACFT WAS RELEASED BACK INTO SERVICE. 2L72 4F4 FRTA16WE E2EA 20081126 CE 2008 11 26 CA081002005 120080929G282010192000015 LINE BEECH 200 B200C 1152924CE PWA PT6 PT642A NE HARTZLHCB3T HCB3TN3 GL FUEL SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) DURING DAILY INSP, WITH POWER ON A FEW MOMENTS, NOTICED FUEL LEAKING FROM LT GEAR WELL. POWER TURNED OFF, NOTED FUEL 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 NOT ALLOWED FUEL TO FLOW BACK FROM THE NACELLE TANK. PILOT HAD LEFT THE AUX FUEL TRANSFER OVERRIDE SWITCH IN THE MANUAL PO1L72 4T4 T A24CE E4EA 6 CP15EA 20081120 2008 11 20 CA081002006 120080926G5200 ACTUATOR CNDAIR 215T752204 PWA PW120 PW123 NE DOOR LEAKING W O OTHER K FLUID LOSS ININSP/MAINT 1 CA 129 129 (CAN) FOUND LEAKING AT THE PREES LINE CONNECTION, TSO129HRS, TOTAL DROPS 398 FOUND LEAKING DURING AN INSPECTION BY THE TECHNICAL ENGINEER. 4 T E20NE 20081120 CE 2008 11 20 CA081002007 120080924G555304311481 FITTING CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA VERTICAL STAB FRACTURED W C ABORTED TAKEOFF F FLT CONT AFFECTED NRNOT REPORTED 1 CA (CAN) ACFT BROUGHT TO MX DUE TO ACFT NOT RESPONDING CORRECTLY, VERTICAL STABILATOR WAS INSPECTED AND A FRACTURE WAS FOUND IN THE BRACKET. IT APPEARED TO BE A STRESS FRACTURE IN THE FITTING. WE WOULD LIKE ALL CESSNA OWNERS TO UNDERSTAND THAT IF THE TAIL HITS THE GROUND OR IT RUBS THE GROUND IN ANY WAY THAT IT SHOULD BE INSPECTED. THIS ACFT HAD BEEN INSPECTED APPROX 50 HOURS PRIOR AND THERE WAS NO FRACTURE AT THAT TIME. ALL OF THE FITTINGS AND BOLTS RELATED TO THE ATTACH POINT OF THE VERTICAL FIN WERE REPLACED AND THE FIN WAS INSPECTED FOR ANY DAMAGE. WE ARE GOING TO CONTINUE TO MONITOR THESE FITTINGS ON ALL 152`S AND IF FURTHER INFORMATION ABOUT THIS ISSUE BECOMES APPARENT TO US WE WILL UP DATE. 1H71 3O3 ONT3A19 E223 20081120 2008 11 20 CA081002008 220080925G741410357584 DISTRIBUTOR GEARCONT 106006141 MAGNETO DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) MAGNETO RECEIVED WITH TEETH BROKEN OFF THE DISTRIBUTOR GEAR. 20081120 EA 2008 11 20 CA081003001 120080926G5610NP13932211 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT CRACKED W K NONE O OTHER CRCRUISE 1 CA (CAN) CAPTAINS SIDE WINDOW CENTER PANE SHATTERED ENROUTE. MX CHANGED THE WINDOW. 2L72 4F4 FRTA21EA E15NE 20081120 NE 2008 11 20 CA081003002 220081001G73971710101 WIRE HARNESS EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE FADEC DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 6526 (CAN) FADEC WIRING HARNESS DAMAGED (WHICH REQUIRED REPLACEMENT) DUE TO THE LOWER SEAL ON THE PYLON PRE-COOLER LEAKING (NO LEAK/HEAT DETECTION IN THIS AREA). ATTACHED ARE PICTURES. BELOW ARE THE FIN`S AFFECTED WITH TIMES AND CYCLES. ACFT INDUCTED FOR THE FREEZE PROTECTION MOD. 2L72 4F4 FRTA56NM E00063EN 20081120 2008 11 20 CA081003003 120080925G8011149NL HOUSING STARTER LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 43 (CAN) REAR HOUSING DISCOVERED LOOSE DURING SCHEDULED MX. 20081120 2008 11 20 CA081003004 120080912G8011149NL HOUSING STARTER LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 207 (CAN) REAR HOUSING DISCOVERED LOOSE DURING SCHEDULED MX. 20081120 2008 11 20 CA081003005 120080924G8011 ATTACH BOLT 149NL STARTER LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 655 (CAN) MOTOR TO HOUSING ATTACH BOLTS LOOSE. 20081124 NE 2008 11 24 CA081003006 220080930G7322 FLOAT BENDIX DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE CARBURETOR DAMAGED W O OTHER YJ ENGINE STOPPAGE WARNING INDICATION DEDESCENT 1 CA (CAN) FLIGHT CREW REPORTS THAT THE ENGINE FALTERED ON SHORT FINAL AND QUIT COMPLETELY AS THE FLOATPLANE CAME OFF THE STEP. AFTER BEING TOWED TO THE DOCK, FUEL WAS OBSERVED POURING OUT OF THE CARBURETOR. THE FLOAT VALVE APPEARED TO BE STUCK IN THE FULL OPEN POSITION. CARBURETOR WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE. THE CARBURETOR HAD BEEN INSTALLED 2 HOURS PREVIOUS FROM OVERHAUL. 1H71 3R3 RRCA806 5E1 20081124 SW 2008 11 24 CA081003007 120080925G3233LA11C2110 ACTUATOR MOONEYM20 M20F 5870214SW LYC O360 IO360LYC* 41514EA MLG FAILED W O OTHER J WARNING INDICATION APAPPROACH 1 CA (CAN) LANDING GEAR FAILED TO EXTEND ELECTRICALLY. ACTUATOR TEAR DOWN REVEALED THE MOTOR HAD FAILED. 1L71 3O3 O 2A3 1E10 20081124 SO 2008 11 24 CA081003009 220081001G8530652420902 THRU BOLT CONT O360 IO360KB 17025SO NR 6 CYLINDER BROKEN W K NONE O OTHER ININSP/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 WASHER 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 BOLTS IN THE AREA WERE TORQUE CHECKED AND FOUND SERVICEABLE. NO OTHER DEFECTS WERE NOTED. 3 O E1CE 20081124 CE 2008 11 24 CA081004001 120081001G3245302247400 TUBE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL NLG FOD W O OTHER C F.O.D. NRNOT REPORTED 1 CA (CAN) TUBE HAD A HOLE CHAFED IN IT - NO EVIDENCE OF FOD INSIDE TIRE FROM INITIAL ASSY TO CAUSE WEAR HOLE. 1H71 3T3 T A37CE E4EA 5 CP60GL 20081126 CE 2008 11 26 CA081006001 120081002G325005430223 STEERING SYS CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA INOPERATIVE W O OTHER F FLT CONT AFFECTED TOTAKEOFF 1 CA (CAN) INSTRUCTOR WITH A STUDENT PILOT ON BOARD REPORTED THAT ALTHOUGH RUDDER PEDAL TRAVEL APPEARED TO BE NORMAL DURING TAXI, AT THE POINT OF LIFT OFF RUDDER PEDAL MOVEMENT WAS RESTRICTED TO RT RUDDER ONLY. RUDDER COULD NOT BE MOVED TO THE LT. 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 SOLID ROD, WHERE AFTER LIFT OFF WITH THE NOSE OLEO EXTENDED AND THE NOSE WHEEL LOCKED IN THE CENTER POSITION, IT WOULD HAVE 1H71 3O3 ONT3A19 E223 20081124 GL 2008 11 24 CA081006002 120080929G24201707580A CONVERTER BOMBDRBD700 BD7001A10 1390006GL DAMAGED W O OTHER MBGOVER TEMP SMOKE/FUMES/ODORS/SPARKS MULTIPLE FAILURE TXTAXI/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 BURNED TRACE. THE MICROPROCESSOR CARD LOCATED ABOVE THE AC/DC CONVERTER CARD HAD A SMALL AMOUNT OF SOOT BUT NO VISIBLE DAMAGE. THE PRIMARY LOGIC CARD WAS SOOTY AND , WHEN THE SOOT WAS WASHED OFF, A SMALL AREA ABOUT 3 SQUARE INCHES WAS DISCOLORED. AC POWER CENTER REPLACED TO DISPATCH THE ACFT. 2L72 4F RTT00003NY 20081124 NM 2008 11 24 CA081006003 120081001G3231 CONTROL ROD DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE NLG DOOR BROKEN W A UNSCHED LANDING ED VIBRATION/BUFFET INFLIGHT SEPARATION CLCLIMB 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 GROUND CREW NOTED THAT THE RT NLG DOOR WAS OPEN AND THAT THE DOOR CONTROL ROD AND TENSION SPRING (PN 83232010-105) FOR THE RT DOOR WAS BROKEN. THERE WAS NO DAMAGE TO THE SURROUNDING STRUCTURE. THE CONTROL ROD WAS SHEARED AT THE UPPER PERMASWAGE ON THE ROD. GEAR INDICATION WAS NORMAL TO THE CREW. THE BARTS WHERE REPLACED AND THE ACFT RELEASED BACK TO SERVICE. 2H72 4T4 TRTA13NM E20NE 20081120 SO 2008 11 20 CA081006004 120081003G7160434179 GROMMET 86245041 PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6D 42305EA CARB HEAT BOX MISSING W K NONE O OTHER ININSP/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 MISSING ON THE LT ENGINE CARB HEAT BOX. THIS GROMMET SUPPORTS THE SHAFT IN THE CARB HEAT BOX. THIS PROMPTED THE INSP OF THIS ACFT, WHICH FOUND THE BOTTOM GROMMET AND BUSHING MISSING FROM ITS LT ENGINE. 1L72 3O3 O A19S0 E286 20081124 EA 2008 11 24 CA081007001 220081003G7320312240015 FADEC BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NR 2 ENGINE MALFUNCTIONED W D RETURN TO BLOCK YJ ENGINE STOPPAGE WARNING INDICATION TXTAXI/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 SHUTDOWN WITH AN ASSOCIATED NR 2 ENG FADEC FAIL WARNING LIGHT AND POWERPLANT MSG. INTERROGATION OF THE CDS REVEALED THE FOLLOWING 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. 2H72 4T4 TRTA13NM E00062EN 20081124 NE 2008 11 24 CA081007002 220080906G7200 ENGINE SKRSKYS92 S92A NE GE CT7TS CT78A 30136NE MALFUNCTIONED W E ENGINE SHUTDOWN J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) POST LANDING AND TAXI. ACFT WAS STATIONARY WITH BOTH ENGINES IN THE GROUND IDLE POSITION WITH ROTORS TURNING. PILOT 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 SPIKED TO 1100 DEGREES C FOR A PERIOD OF 3 SECONDS BEFORE THE AUTOMATED PROTECTIVE CIRCUITS OF THE FADEC SHUT THE ENGINE DOW2G72 4U4 U R00024BOE8NE 20081124 NM 2008 11 24 CA081007003 120081006G5754NAS86034NAS86 SCREW BOMBDRCL600 CL6002D15 NM GE CF34 CF348C5 30050NE SLAT LOOSE W K NONE O OTHER ININSP/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 BEYOND THE WING SURFACE CAUSING MINOR DAMAGE TO THE UNDER SKING SURFACE OF THE SLAT. ALL SCREWS WERE TIGHTENED BACK. 2L72 4F4 FRTA21EA E00063EN 20081124 NM 2008 11 24 CA081007004 120080929G213010010602 CIRCUIT CARD EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE CABIN PRESSURE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER DEPARTURE AT APPROX 1500`, BLEED NR 1 AND NR 2 FAILED EICAS MSGS APPEARED, AND QRH CARRIED OUT (RESET) BUT UNSUCCESSFUL. ACFT DID NOT PRESSURIZE, AND RETURNED TO BNA FOR MX. OTHER PNS AND SNS AFFECTED: 2L72 4F4 FRTA56NM E00063EN 20081120 2008 11 20 CA081007005 420081007G3160071015980301 CONTROLLER PILATSPC12 PC1247 7090552EU PWA PT6 PT6A67 52043NE MFD FAILED W O OTHER O OTHER TXTAXI/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 THE MFG APEX SYS. THE JOYSTICK FAILS TO MOVE THE CURSOR TO THE RT AS DISPLAYED ON THE MFD SCREEN. THE CONTROLLER WAS REPLACED WITH A NEW ITEM THAT CLEARED THE PROBLEM THIS IS THE SECOND REPLACEMENT ON THIS ACFT SINCE NEW 150 HRS TT. 1L71 4T4 TRTA78EU E26NE 20081126 EU 2008 11 26 CA081007006 120081007G2910MS287786 O-RING BAG JETSTMJETSTM3112 1500220EU GARRTTTPE331TPE33110 29053NE ROTOL R333 R333482F12 GL COUPLING FAILED W O OTHER KJ FLUID LOSS WARNING INDICATION APAPPROACH 1 CA (CAN) DURING GEAR DOWN LANDING CHECKS, ONLY NOSE GEAR LOCKED, BOTH MLG UNSAFE. REQUESTED LOW AND OVER-CYMM FSS CONFIRMED 3 GEAR DOWN. RE-POSITIONED TO A SAFE AREA AND PERFORMED ITEMS LISTED ON QRH. PUMPED GEAR DOWN MANUALLY, GEAR WAS CONFIRMED 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 COUPLING BASE O-RING HAD FAILED, CAUSING EXCESSIVE FLUID LOSS. REMOVED AND REPLACED DEFECTIVE O-RING WITH NEW. HYD SYS REPLENISHED GEAR, FLAP, STEERING, BRAKE SYSTEMS BLED, GEAR SWINGS C/O AND SYS F/C C/O SYS SERVICED AND L/C C/W. 2L72 4T4 TRTBA15CAA E4WE 6 CP61GL 20081124 EU 2008 11 24 CA081007007 120080929G5310350A38101832 CROSSBEAM SNIAS 350 AS350BA 8680817EU ALLSN 250C 250C30 03013GL FUSELAGE CRACKED W K NONE O OTHER ININSP/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. 1G71 3U3 UNCH9EU E1GL 20081124 CE 2008 11 24 CA081007008 120081007G3340CM358910 SWITCH CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA TAXI LIGHT INOPERATIVE W O OTHER P NO WARNING INDICATION NRNOT 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. 1H71 3O3 ONT3A12 1E10 20081124 CE 2008 11 24 CA081007009 120081001G3397903641241 C/BREAKER PANEL BEECH 200 B200 1152922CE PWA PT6 PT642A NE COCKPIT BURNED W BA EMER. DESCENT UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 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 HEAT HAD BURNED PART WAY THROUGH THE EDGE LIGHTED PANEL AND STARTED TO HEAT THE OVER LYING CIRCUIT BREAKER PANEL. NO FURTHER DAMAGE WAS NOTED. THIS EDGE LIGHTED PANEL WAS PREVIOUSLY INSPECTED AS PER THE MM ABOUT 565 HOURS AGO. 1L72 4T4 T A24CE E4EA 20081124 SW 2008 11 24 CA081007010 120081002G32405011639 DISC SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 29073NE MCAULY4HFR344HFR34C652 NE BRAKE WORN W K NONE O OTHER ININSP/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 LUGS 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. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20081126 CE 2008 11 26 CA081008001 120080818G3220 FORK CESSNA172 172N 2072434CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL NLG CRACKED W K NONE O OTHER ININSP/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 DEFLECTION IN THE SUSPECTED AREA. SUBSEQUENTLY THE INSP WAS CONDUCTED ON THE OPPOSITE SIDE OF THE NLG FORK WITH THE SAME RESULTS. ADDITIONALLY FPI WAS ALSO DONE TO SHOW VISUALLY UNDER BLACK LIGHT. CRACKS WERE CLEARLY VISIBLE ON BOTH SIDES OF THE FORK UNDER THE BLACK LIGHT. THE ACFT WAS REMOVED FROM SERVICE AND A NEW NLG FORK ASSY WAS ORDERED FROM MFG AND INSTALLED UPON ARRIVAL. 1H71 3O3 ONT3A12 E274 5 NP910 20081124 GL 2008 11 24 CA081008002 120080923G24102224121400 BRACKET DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO ALTERNATOR CRACKED W K NONE O OTHER ININSP/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 FOUND ON THIS ACFT AND BOTH CRACKS HAVE BEEN LOCATED IN THE IDENTICAL LOCATIONS. 1L71 3O3 ONTTA4CH E7SO 20081124 GL 2008 11 24 CA081008003 120080923G24102224121400 BRACKET DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO ALTERNATOR CRACKED W K NONE O OTHER ININSP/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. 1L71 3O3 ONTTA4CH E7SO 20081124 SW 2008 11 24 CA081008006 120081007G5210205D10282 WINDOW FRAME BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE JUMP DOOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) 10 INCH CRACK FOUND AT UPPER LT CORNER OF WINDOW FRAME. 1G71 4U4 U H4SW E22EA 20081124 NM 2008 11 24 CA081008007 120081008G5210SB003T0023 PANEL DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE COCKPIT DOOR MISALIGNED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FLEX IN LAV WALL IS CAUSING SIGNIFICANT IN-SERVICE MISALIGNMENT OF PONS INSTALLED IN LATCH HOUSING USING TTF-SB-03T002-001. REFER TO PROTECTED "A" AD CF-2008-26R1 AND STC SA03-70, SB TTF-SB-03T002-001 REV "D". 2H72 4T4 TRTA13NM E20NE 20081124 EA 2008 11 24 CA081009001 120081002G38105000120701 WATER HEATER CNDAIRCL601 CL6013A 8070802EA FWD GALLEY DAMAGED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) ON CLIMB OUT SMOKE WAS OBSERVED COMING OUT OF THE FUEL CONTROL PANEL IN THE FORWARD GALLEY. THE WATER HEATER INSULATION BLANKET IN THE FORWARD GALLEY HAD EVIDENCE OF HEAT DAMAGE. INSTALLATION OF THIS PART IN THE FORWARD GALLEY OF THE ACFT IS A PART OF SUPPLEMENTAL TYPE CERTIFICATE ST09049SC. THE PART IN QUESTION HAS BEEN FORWARDED TO THE TSB. 2L72 4F RTA21EA 20081124 CE 2008 11 24 CA081009002 120080918G5753S16612 SWITCH CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA TE FLAP DAMAGED W O OTHER F FLT CONT AFFECTED APAPPROACH 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. 1H71 3O3 ONT3A12 E274 20081124 GL 2008 11 24 CA081009003 220081002G732323065123 GOVERNOR BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL TURBINE INOPERATIVE W O OTHER O OTHER NRNOT REPORTED 1 CA 1234 (CAN) BENDIX KING GOVERNOR NOT RESPONDING WHEN BEEPED, 1G71 3U3 U H2SW E4CE 20081124 NM 2008 11 24 CA081009004 120081003G2421ALX8521R ALTERNATOR ROBSINR22 R22BETA 7640110NM LYC O360 O360J2A 41514EA INOPERATIVE W O OTHER O OTHER NRNOT REPORTED 1 CA 331 (CAN) ALTERNATOR LIGHT ILLUMINATED IN FLIGHT, ALTERNATOR CHECKED AND NOT CHARGING. 1G71 3O3 O H10WE E286 20081124 NE 2008 11 24 CA081009005 220080929G741410600646201 MAGNETO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MALFUNCTIONED W O OTHER O OTHER NRNOT REPORTED 1 CA 90 (CAN) ENGINE TACH FLUCTUATING, MAGNETO REPLACED. 1G71 3O3 O H11NM 1E4 20081124 WP 2008 11 24 CA081009006 120080930G2435BC3151004 STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MALFUNCTIONED W O OTHER O OTHER NRNOT REPORTED 1 CA 359 (CAN) STARTER NOT ENGAGING. 1G71 3O3 O H11NM 1E4 20081124 NM 2008 11 24 CA081009007 120081009G2781651781823 SWITCH DECOTO BOEING727 727247 138408FNM PWA JT8 JT8D15 52051NE SLAT ACTUATOR FAILED W JA DUMP FUEL UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA 47 (CAN) JUST AFTER DEPARTURE FROM YYZ, THE PILOTS NOTICED WHEN SELECTING FLAPS 5 TO FLAPS 2, THE LEADING EDGE FLAP INDICATOR ON THE FORWARD PANEL WENT MOMENTARILY GREEN THEN BACK TO AMBER. THE LEADING EDGE INDICATOR ON THE REAR PANEL INDICATED THE NR 1 LEADING EDGE IN TRANSIT. FUEL WAS DUMPED IN ORDER TO REDUCE LANDING WEIGHT OF THE ACFT AND THE ACFT RETURNED TO YYZ. MX TROUBLESHOT THE SYSTEM AND INSTALLED A JUMPER CABLE ON THE SLAT ACTUATOR TO ENABLE THE ACFT TO DEPART. 2L73 4F4 F A3WE E2EA 20081124 NM 2008 11 24 CA081009008 120081008G2497 WIRE BOMBDRCL600 CL6002D15 NM GE CF34 CF348C5 30050NE CHAFED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA (CAN) FLIGHT ATTENDANT REPORTED A BURNING ODOR IN THE CABIN. THE ACFT LANDED UNEVENTFULLY. THE CAUSE OF THE ODOR WAS TRACED TO CHAFED WIRE ABOVE THE FORWARD LAVATORY. 2L72 4F4 FRTA21EA E00063EN 20081124 GL 2008 11 24 CA081009009 120080927G2497 WIRE KELLY DIAMONDA40 DA40 2990002GL CONT IO360 IO360* 17025CE ALTERNATOR BROKEN W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) A+ TERMINAL MELTED OFF ALTERNATOR AND LOOSE. PROBLEM CAUSED BY BROKEN TERMINAL ON A+ WIRE GOING TO ALTERNATOR. WIRE WAS ORIGINALLY VERY TIGHT CAUSING THE BREAKAGE, THEN IT ARCED CAUSING HEAT AND EVENTUAL FAILURE. 1L71 3O3 ONTA47CE E1CE 20081126 NE 2008 11 26 CA081009010 220080929G7532PN1422010 CLEVIS EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE BLEED VALVE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) (ENGINE INTAKE VARIABLE BLEED VALVE ACTUATOR) INTERFERENCE HAS OCCURRED BETWEEN THE SUBJECT CLEVIS LUG AND ADJACENT 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) 2L72 4F4 FRTA57NM E00070EN 20081126 GL 2008 11 26 CA081009011 120081007G27202227271100 RUDDER PEDAL DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA COCKPIT WORN W K NONE O OTHER ININSP/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 CABLE 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 OVERLOO1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20081126 NM 2008 11 26 CA081010001 120080927G2820 LINE BOEING717 717200 1383700NM RROYCEBR700 BR700715A130 NE FUEL SYSTEM CRACKED W O OTHER KE FLUID LOSS VIBRATION/BUFFET APAPPROACH 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 FROM UNDER THE LT ENGINE. MAINT FOUND THAT PIPE WAS CRACKED AGAIN. SEVERAL FIRE LOOP BRACKETS WERE ALSO FOUND CRACKED. THE 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, CSI 35 CYCLES. HIGH VISIBILITY EVENT BY THE FAA DUE TO FUEL LEAK. ENG 13243 IN FOR INVESTIGATION. TEST BED RUN CONFIRMED HIGH VIBRATION EMANATING FROM ACCY GEARBOX, WHEN ENGINE POWERED UP AN OIL LEAK EMANATED FROM THE GEARBOX AT FUEL PUMP LOC2L72 4F4 FTRA6WE E00061EN 20081124 NE 2008 11 24 CA081010002 220081009G731063E951 HOUSING GRIMES CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE FUEL FILTER LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) MX DISCOVERED NR 1 ENGINE FUEL FILTER ASSEMBLY LEAKING FROM THE TOP OF THE FILTER HOUSING. HOUSING IS EITHER CRACKED 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 2L72 4F4 FRTA21EA E15NE 20081124 EA 2008 11 24 CA081010003 120081010G2750855D10011 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE RT WING TE FLAP UNSERVICEABLE W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION APAPPROACH 1 CA 1010010100 (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 RECEIVED. 2L72 4F4 FRTA21EA E15NE 20081124 SW 2008 11 24 CA081010004 120081003G3040 HEATER GULSTM680 680 0141602SW PWC PW306 PW306C 52169NE WINDSHIELD SMOKE W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA 613 (CAN) SMOKE DETECTED IN COCKPIT ON ENGINE STARTUP. PROBLEM ISOLATED TO LT WINDSHIELD. RECTIFIED BY REPLACEMENT OF PART. 1H72 3O4 F 2A4 E35NE 20081124 EA 2008 11 24 CA081010005 120081002G5343VALTBS112091 ATTACH FITTING DHAV DHC2 DHC2MK3 2800107EA PWA PT6 PT6A27 52043EA WING/MLG CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION A AME FOUND THE WING GEAR/STRUT ATTACH FITTING TO BE CORRODED (LEVEL 3). 1H71 3T4 T A806 E4EA 20081124 EA 2008 11 24 CA081010006 120081002G2731C2T29A TORQUE TUBE DHAV DHC2 DHC2MK3 2800107EA PWA PT6 PT6A27 52043EA ELEVATOR TRIM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A ROUTINE 100 HOUR INSPECTION A AME FOUND THE ELEVATOR TRIM TORQUE TUBE TO BE CRACKED, PART WAS REPLACED AND CUSTOMER WAS ADVISED. 1H71 3T4 T A806 E4EA 20081124 EA 2008 11 24 CA081010007 120081002G3246VALBVS12601 FITTING DHAV DHC2 DHC2MK3 2800107EA PWA PT6 PT6A27 52043EA MLG FLOAT SPLIT W K NONE O OTHER ININSP/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. 1H71 3T4 T A806 E4EA 20081124 EA 2008 11 24 CA081010008 220081003G74144371 MAGNETO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MALFUNCTIONED W O OTHER O OTHER NRNOT REPORTED 1 CA 156 (CAN) POOR MAG DROP, TIMING LIGHT FLICKERING BEFORE 25 DEGREES. MAGNETO REPLACED WITH A SERVICEABLE MAGNETO. 1H71 3O3 ONT3A12 1E10 20081124 EA 2008 11 24 CA081010009 220081003G74144371 MAGNETO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA 156 (CAN) POOR MAG DROP. TIMING LIGHT FLICKERING BEFORE 25 DEGREES. REPLACED WITH SERVICEABLE MAGNETO. 1H71 3O3 ONT3A12 1E10 20081124 EA 2008 11 24 CA081010010 220081002G7321 SCREW DHAV DHC2 DHC2MK3 2800107EA PWA PT6 PT6A27 52043EA FCU CORRODED W K NONE O OTHER ININSP/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. 1H71 3T4 T A806 E4EA 20081124 SW 2008 11 24 CA081010011 120081010G3500AS4857D01 TEE FITTING GULSTM680 680 0141602SW PWC PW306 PW306C 52169NE OXYGEN SYSTEM CRACKED W K NONE O OTHER ININSP/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. 1H72 3O4 F 2A4 E35NE 20081124 2008 11 24 CA081014001 120081010G6100 SHAFT PWA 118 PW118 NE PROPELLER CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) EIR PW100-0477 CRACKED PROPELLER SHAFT. 4 T E20NE 20081124 CE 2008 11 24 CA081014002 120081008G273007606861 CONTROL TUBE CESSNA182 182Q 2072732CE CONT O470 O470U 17026SO MCAULY2A34C C2A34C204 GL LT ELEVATOR GOUGED W O OTHER W INADEQUATE Q C NRNOT 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 AND 0.250 WIDE. 1H71 3O3 ONT3A13 E273 5 CP3EA 20081124 CE 2008 11 24 CA081014003 120081009G2731071250012 ACTUATOR CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL HORIZ STAB TRIM SEPARATED W O OTHER F FLT CONT AFFECTED LDLANDING 1 CA 100 (CAN) ACFT HORIZONTAL STAB TRIM JAM ON LANDING. ELEVATOR CONTROLS BECAME LIGHT. ACFT LANDED WITHOUT INCIDENT. UPON INSPECTION AT THE DOCK, THE PILOT FOUND THE HORIZONTAL STAB WAS COMPLETELY LOOSE, STAB COULD BE MOVED FULL TRAVEL UP AND DOWN WITH NO RESISTANCE FROM THE TRIM JACKS. MX FOUND THE TRIM JACK BARREL COULD BE SLID ON TO THE SCREW OF THE SCREW JACK 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 REPLACED AND CESSNA DISTRIBUTOR CONTACTED DUE TO THE ACTUATORS IN QUESTION WERE ONLY 3 MONTHS OLD AND 100HRS. SINCE NEW TIME IN1H71 3O3 O 3A24 E5CE 5 CP3EA 20081124 NM 2008 11 24 CA081014004 120080917G52101700375200 SEAL EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE PAX DOOR GOUGED W K NONE O OTHER ININSP/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 PICTURES FOR DETAILS, TYPICAL DAMAGE SEEN TO THE PAX/SERVICE DOOR CUTOUT SEAL RESTS. EMB HAS ISSUED A “TYPICAL” IC APPROVAL THAT PERMITS PERMANENT BLENDING OF UP TO 20% THICKNESS. 2L72 4F4 FRTA57NM E00070EN 20081124 NE 2008 11 24 CA081014005 220081006G732287327003 ARM PIPER PIPER PA44 PA44180 7104402SO LYC O360 LO360A1H6 42294NE CARB HEAT SEPARATED W D RETURN TO BLOCK O OTHER TXTAXI/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 ACTUATOR ARM ONTO THE CARB AIR DOOR HAD BROKEN CAUSING THE ARM TO SEPARATE FROM THE SHAFT. THE WELD APPEARED TOO THIN IN COMPARISON TO THE LT ENGINE CARB AIR DOOR ASSY. 1L72 3O3 O A19S0 E286 20081124 SO 2008 11 24 CA081014006 120081006G7160434179 GROMMET PIPER PIPER PA44 PA44180 7104402SO LYC O360 LO360A1H6 42294NE AIR BOX MISSING W O OTHER O OTHER NRNOT 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. 1L72 3O3 O A19S0 E286 20081126 CE 2008 11 26 CA081014007 120081001G32461368520629 BEARING BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE WHEEL FAILED W O OTHER S AFFECT SYSTEMS TXTAXI/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 NUT 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 RESULTED IN A BEARING BURN WHICH IS NOT SEVERE IN MATTER BUT IS AN INDICATION OF HOW FAR THE INITIAL FAILURE EXTENDED. DAMAGE REQUIRED REMOVAL OF THE LT GEAR LEG AND INSTALLATION OF A SERVICEABLE GEAR LEG. BOTH MAIN WHEEL ASSEMBLIES AFFECTED WERE REPLACED. ACFT WAS THEN RETURNED TO SERVICE. ONE WHEEL ASSY WAS DESTROYED AND THE OTHER SENT OUT FOR TESTING. BEA2L72 4T4 TRTA24CE E26NE 20081126 SW 2008 11 26 CA081014009 120080904G3397 WIRE BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL AT NAV LIGHT CHAFED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 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 THE HEATER AND IN A FEW SECONDS SEES A MIST COMING FROM OVERHEAD PANEL. HEATER IS SWITCHED OFF THEN PILOT REALIZES ITS SMOKE FROM HOT WIRES. BATTERY, GENERATOR IS SWITCHED OFF AND ACFT RETURNS UNEVENTFUL TO THE TAKEOFF AREA. UPON INVESTIGATION, 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 BREAKE1G71 3U3 U H2SW E4CE 20081124 CE 2008 11 24 CA081015001 120081006G29106000100184 LINE LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE HYD SYSTEM CRACKED W K NONE K FLUID LOSS ININSP/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 AUXILIARY PUMP INLINE FILTER. 2L72 4F4 FRTA10CE E35NE 20081124 EA 2008 11 24 CA081015002 220081006G8530AEL11795 SPRING BNORM BN2 BN2B27 7080227EU LYC O540 O540E4C5 41532EA HARTZLHCC2Y HCC2YK2 GL INTAKE VALVE BROKEN W O OTHER O OTHER NRNOT REPORTED 1 CA 333 (CAN) DURING INSPECTION OF LYCOMING SB 388C FOUND BROKEN INNER SPRING PART NR AEL11795 ON INTAKE AND EXHAUST VALVE. 1H72 3O3 O A17EU E295 5 CP920 20081124 NE 2008 11 24 CA081015003 220081015G7497BL60064620 WIRE ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO MISROUTED W O OTHER O OTHER NRNOT REPORTED 1 CA 1287 (CAN) TACH WIRE CHAFING ON TACH POINT CONNECTOR TACH WIRES INCORRECTLY ROUTED. TCM SB663A NOT COMPLIED WITH FOR WIRE ROUTING. LAST MX ON MAGNETO WAS PRO AERO. MAGNETO WAS REMOVED DUE TO ENGINE/ACFT OVERSPEED. 1G71 3O3 O H11NM 1E4 20081124 NE 2008 11 24 CA081015004 220081015G749710400586 WIRE ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE TACH MISROUTED W O OTHER O OTHER NRNOT 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. 1G71 3O3 O H11NM 1E4 20081124 NE 2008 11 24 CA081015005 220081015G749710400586 WIRE ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE TACH PINCHED W O OTHER O OTHER NRNOT 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 . 1G71 3O3 O H11NM 1E4 20081124 EA 2008 11 24 CA081015006 220081015G749710400586 WIRE ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA TACH CHAFED W O OTHER O OTHER NRNOT REPORTED 1 CA 151 (CAN) TACH WIRES CHAFED THROUGH AND GROUNDING TO THE COIL PRIMARY CONNECTOR. TACH WIRES INCORRECTLY ROUTED TCM SB663A NOT COMPLIED WITH FOR WIRE ROUTING. VERY HIGH RESISTANCE FOUND BETWEEN THE TERMINALS OF THE TACH POINTS, WHEN CLOSED 1200-1500 OHMS, PROBLEM IS BLACK COATING ON TACH POINT ARM CAUSING A HIGH RESISTANCE. MAGNETO REMOVED FROM ACFT BECAUSE IT WANTED TO OVERSPEED. 1G71 3O3 O H11NM E295 20081124 NM 2008 11 24 CA081016001 120081010G27811702286A SENSOR EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE FLAP SKEW INOPERATIVE W O OTHER J WARNING INDICATION APAPPROACH 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. 2L72 4F4 FRTA56NM E00063EN 20081124 NM 2008 11 24 CA081016002 120081006G27811702286A SENSOR EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE SLAT SKEW FAILED W O OTHER J WARNING INDICATION APAPPROACH 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. 2L72 4F4 FRTA57NM E00070EN 20081126 EA 2008 11 26 CA081016003 120081010G4930MS29513021 O-RING CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF348E5A1 30062NE EMI FILTER FAILED W K NONE J WARNING INDICATION ININSP/MAINT 1 CA 2790 (CAN) ACFT, PRIOR TO ENG START APU HAD AN UNCOMMANDED SHUTDOWN. WHILE CARRYING OUT COCKPIT TROUBLESHOOTING PILOTS OBSERVED APU BOOST PUMP FAIL LIGHT WAS ILLUMINATED. APU BOOST PUMP WAS SUSPECT BECAUSE IT HAD JUST BEEN CHANGED THE PREVIOUS DAY 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 FUEL TO DEGRADE THE INSULATION MATERIAL TO THE POINT WERE THE PINS SHORTED OUT. A NEW EMI FILTER HARNESS AND BOOST PUMP WERE INSTALLED AND ACFT RETURNED TO SERVICE. FYI THE APU BOOST PUMP FUEL IS USED TO COOL. APU LUBRICATING OIL. WITH NO F2L72 4F4 FRTA21AE E00063EN 20081124 NE 2008 11 24 CA081016004 220081008G731010608486 HOSE BOEING727 727225 1384077NM PWA JT8 JT8D15 52051NE FUEL SYSTEM LEAKING W D RETURN TO BLOCK K FLUID LOSS TXTAXI/GRND HDL 1 CA (CAN) DURING DEPARTURE OF THE ACFT PRIOR TO ENGINE START, FUEL WAS NOTICED LEAKING FROM NR 3 ENGINE. MX REQUESTED NORMAL ENGINE START TO VERIFY FUEL LEAK. ENGINE WAS SHUT DOWN, AND ACFT TOWED BACK TO GATE FOR FURTHER INVESTIGATION. THE FUEL HOSE ASSEMBLY WAS R&R WITH A SERVICEABLE ASSEMBLY. ENGINE GROUND RUN WAS CARRIED OUT AND LEAK CHECKED WITH NO FURTHER LEAKS OBSERVED. THE ACFT WAS RETURNED TO SERVICE. 2L73 4F4 F A3WE E2EA 20081124 EA 2008 11 24 CA081016005 120081014G2751601R930301 TRANSMITTER CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE FLAP POSITION FAILED W O OTHER O OTHER CLCLIMB 1 CA (CAN) CLIMBING THROUGH 12000 FT AT 250 KIAS ACFT NOSED OVER AS FLAPS WENT TO AT LEAST 25 DEGREES AND AUTOPILOT KICKED OFF. ACFT SLOWED TO 200 KIAS WHILE RETURNING TO DEPARTURE AIRPORT. FLAPS CONTINUOUSLY CYCLED FROM 0 TO 12 DEGREES. CIRCUIT 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. 2L72 4F4 FRTA21EA E15NE 20081126 NM 2008 11 26 CA081016006 120081008G27821703911 ACTUATOR EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE NR 4 SLAT MALFUNCTIONED W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION APAPPROACH 1 CA 4135 (CAN) SLAT FAIL ON APPROACH CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT. T/S IAW FIM, SLAT INHIBIT CLEARED, OPS 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: 3665. 2L72 4F4 FRTA57NM E00070EN 20081126 2008 11 26 CA081016007 220081015G7414D6RN3200 MAGNETO RT ENGINE INOPERATIVE W O OTHER R PARTIAL RPM/PWR LOSS TXTAXI/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 120081003G783065378786 SWITCH BOEING727 7272Q6 138407VNM PWA JT8 JT8D17 52049NE THRUST REVERSER INOPERATIVE W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) ON CLIMB OUT, NR 3 ENGINE THRUST REVERSER OPERATING LIGHT ILLUMINATED THROUGH 5000 FT. THE ACFT RETURNED TO THE AIRPORT. 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. THE DEFERRAL WAS CLEARED AND THE ACFT WAS RETURNED TO SERVICE. 2L73 4F4 FRTA3WE E2EA 20081126 NM 2008 11 26 CA081016009 120081010G279719019566401 WIRE HARNESS EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE LE SLAT DEFECTIVE W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION APAPPROACH 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 MESSAGES. 2L72 4F4 FRTA57NM E00070EN 20081126 CE 2008 11 26 CA081016011 120081010G27201295240823 TORQUE TUBE BEECH 1295240821 BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE RUDDER CONTROL BROKEN W O OTHER F FLT CONT AFFECTED TXTAXI/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 FROM 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 IN AN AREA NOT VISIBLE UNTIL UNIT IS DISMANTLED. ONCE FAILURE PROGRESSED TO COMPROMISE THE TORSION ABILITY OF THE SHAFT IT WOULD SPREAD RAPIDLY TO COMPLETE FAILURE. COMPLETE RUDDER AND STEERING SYS WAS INSPECTED TO DETERMINE IF RELATED SYS 2L72 4T4 TRTA24CE E26NE 20081124 EA 2008 11 24 CA081016012 220080925G7230 COMPRESSOR BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA ENGINE SEIZED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 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 ENGINE LANDING. POST FLIGHT INSPECTION REVEALED A SEIZED COMPRESSOR AND OIL FILTER CONTAMINATION. THE ENGINE WILL BE REMOVED AND FORWARDED TO STANDARD AERO FOR INVESTIGATION AND REPAIR. 2L72 4T4 TRTA24CE E4EA 20081124 NE 2008 11 24 CA081016014 220081002G7321 FUEL CONTROL GULSTM200 200 4500308NM PWC PW306 PW306A 52165NE ENGINE MALFUNCTIONED W D RETURN TO BLOCK XJ ENGINE FLAMEOUT WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) 2 TO 3 MINUTES AFTER ENGINE START, IT FLAMED OUT UNCOMMANDED. NO FAULT CODES WERE RECORDED ON THE FADEC. INSPECTION FOUND THE FAN FREE TO ROTATE WITH NO EVIDENCE OF INGESTION. THE PILOT MOTORED THE ENGINE AND THEN PERFORMED AN ENGINE 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. 2L72 4F4 FRTA53NM E35NE 20081124 NE 2008 11 24 CA081016015 220081002G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE FIRE W EFB ENGINE SHUTDOWN ACTIVATE FIRE EXT. EMER. DESCENT ARJFLAME/FIRE PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING FLIGHT, THE PILOT SAW FLAMES COMING OUT OF THE ENGINE EXHAUST BEFORE LOSING POWER. HE DECLARED EMERGENCY AND DIVERTED THE FLIGHT TOWARDS A NEARBY AIRPORT. HE WAS NOT ABLE TO MAKE THE AIRPORT AND HE WAS FORCED TO LAND ON A ROAD. THE PILOT WAS NOT INJURED AND THE ACFT SUFFERED NO DAMAGE. THE ACFT WAS LATER TOWED TO THE AIRPORT WHERE FAA IS INVESTIGATING. THE ENGINE WILL BE REMOVED AND FORWARDED TO STANDARD AERO FOR INVESTIGATION. 1H71 3T3 T A37CE E4EA 20081106 2008 11 6 CA081017001 420081012G83003022375 SEAL BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA ACCESSORY G/B FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 7524 7524 (CAN) PILOTS SHUT DOWN NR 1 ENGINE, DUE TO OIL PRESSURE FLUCTUATION AND OIL PRESS. ANNUNCIATOR ILLUMINATION. ACFT RETURNED TO YXS MX BASE. OIL LOSS WAS FOUND TO BE COMING FROM THE HP PUMP DRAIN. OIL SEAL REPLACED, OIL CONSUMPTION ELIMINATED. EXPLORATORY WORK COMPLETED AS PER PRATT AND WHITNEY MX MANUAL. ACFT RELEASED AS PER PRATT AND WHITNEY MX MANUAL PUTTING IN PLACE BOTH OIL FILTER/SCREEN AND CHIP DETECTOR INSPECTIONS. 2L72 4T4 TRTA24CE E4EA 20081106 EA 2008 11 6 CA081017002 120081007G61208210004 CSU DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL RT ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN H ELECT. POWER LOSS-50 PC CRCRUISE 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 POWER WAS BROUGHT BACK THE PROPELLER STOPPED FEATHERING. A PRECAUTIONARY ENGINE SHUTDOWN WAS PERFORMED AND THE ACFT RETURNED TO BASE WITHOUT FURTHER INCIDENT. THE ENGINE AND ASSOCIATED SYSTEMS WERE TROUBLESHOT, WHICH DETERMINED THAT THE PROPELLER GOVERNOR WAS AT FAULT. THE GOVERNOR WAS CHANGED, A GROUND RUN AND A TEST FLIGHT WERE PERFORMED WITH NO FURTHER PROBLEMS. 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20081106 NM 2008 11 6 CA081017003 120081007G5720190933321001 FAIRLEAD EMB ERJ190ERJ190100IGW3260408NM DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT WING AILERON FAIRLEAD BRACKETS. REMOVAL OF THE PLASTIC FAIRLEADS FOUND THAT THE CABLES DID NOT SIT ROUGHLY IN THE 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 REFERENCE. 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). 2L72 4F RTA57NM 20081106 WP 2008 11 6 CA081017004 220081017G723031081822 BLADE NORMALAIR GARRTTTPE331TPE33110UA 01514WP IMPELLER DAMAGED W D RETURN TO BLOCK E VIBRATION/BUFFET TXTAXI/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 ENGINE. THE ENGINE WAS REMOVED AND FORWARDED TO THE ENGINE SHOP FOR EVALUATION. UPON DISASSEMBLY THE NR 1 IMPELLER WAS FOUND TO HAVE A PIECE OF THE BLADE MISSING. THE NR 1 IMPELLER HAS NO OTHER DAMAGE EXCEPT WHERE THE BLADE PIECE IS MISSING. THE NR 1 IMPELLER WILL BE FORWARDED TO A METALURGY FACILITY FOR EVALUATION TO DETERMINE WHY THE BLADE PIECE BROKE OFF. THERE WAS SUBSTANTIAL DAMAGE TO THE ENGINE FROM THE IMPELLER BLADE PIECE. 4 T E4WE 20081106 EA 2008 11 6 CA081017005 120081017G2910AE4760H0592055 LINE CNDAIRCL600 CL600* 1900302EA GE CF34 CF343A2 30067NE NR 2 EDP BURST W O OTHER KS FLUID LOSS AFFECT SYSTEMS CRCRUISE 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 HIS NR 1 AND NR 3 HYD SYSTEM. ACFT LANDED SAFELY WITHOUT ANY EMERGENCY REQUEST. NR 2 ENGINE HYD PUMP OUTLET LINE FOUND BUSTED, LINE REPLACED. NR 2 HYD PUMP CHANGED AS MTCE PREVENTIVE AND NR 2 HYD FILTER CHECKED FOR FOD. NOTHING WAS FOUND. 2L72 4F4 FRTA21EA E15NE 20081106 SW 2008 11 6 CA081017006 120080925G5302214001920101 HORN BELL 214 214B1 1182105SW LYC T55 T5508D 41555NE ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2034 (CAN) BOTH `EARS` (LT & RT) OF THE HORN TO WHICH THE ELEVATORS ATTACH CRACKED. COMMON PROBLEM WITH THESE HELICOPTERS. SENT A PREVIOUSLY CRACKED HORN TO BELL HELICOPTER FOR ENGINEERING ANALYSIS, BUT HAVE NOT HEARD ANY RESULTS YET. 2G71 4U4 U H6SW E4NE 20081106 GL 2008 11 6 CA081017007 220081017G732323065123 GOVERNOR BELL 206 206L 1181522SW ALLSN 250C 250C20R2 GL ENGINE MALFUNCTIONED W O OTHER O OTHER NRNOT 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 DRIVE GEAR FOR THE GOVERNOR. THERE WAS DIFFICULTY GETTING FULL RANGE OF THE GOVERNOR, COULD NOT ADJUST FOR 100 PERCENT ON THE 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. 1G71 3U3 U H2SW E4CE 20081106 SW 2008 11 6 CA081017008 120081003G5302204032806079A LONGERON BELL 204 204B 1181404SW LYC T53 T5311B 41549NE TAILBOOM CRACKED W K NONE O OTHER ININSP/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 AFT OF THE TAILBOOM ATTACHMENT FITTING. ACFT GROUNDED FOR REPAIRS. 1G71 4U4 U H1SW E1EA 20081106 CE 2008 11 6 CA081020001 120081003G5551 MOUNT CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL RUDDER CONTROL MISINSTALLED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) METAL FILINGS WERE FOUND UNDER THE RUDDER SERVO DUE TO THE MOUNTING STRUCTURE HAVING BEEN INSTALLED OFFSET FROM THE FACTORY. THIS CAUSED THE RUDDER CABLE TO EXIT THE DRUM ON AN ANGLE AND RUB THE CAPSTAN. THE SERVO WAS REPLACED AND A PERMANENT FIX IS SCHEDULED FOR MAR. 09 AT CESSNA CITATION SERVICE CENTER. PICTURES ARE AVAILABLE. 1L72 4F4 FRTA1WI E3GL 20081106 CE 2008 11 6 CA081020002 120081011G3213 TORQUE LINK BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA MLG CRACKED W K NONE O OTHER ININSP/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. 1L72 3T4 T A14CE E4EA 20081106 CE 2008 11 6 CA081020003 120081019G8011MMU6001 STARTER CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL ENGINE BROKEN W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) SNAG REPORTED THAT ACFT WOULD NOT START. UPON INVESTIGATING IT WAS NOTED THAT THE STARTER HOUSING WHERE IT ATTACHES TO ENGINE WAS BROKEN. ALSO NOTED THAT THE BENDIX DRIVE TEETH WERE MISSING/SHEARED OFF. ENGINE CASE INSPECTED FOR DAMAGE, NONE FOUND NEW STARTER INSTALLED AND FUNCTION CHECKED SERVICEABLE. A CHECK ON STARTER SOLENOID SHOWED NO FAULTS. SUSPECT STARTER WAS RE-ENGAGED BY PILOT AFTER ENGINE WAS RUNNING. 1H71 3O3 ONT3A19 E223 5 NP50GL 20081222 EU 2008 12 22 CA081020004 120081002G6720350A21136324 BRACKET SNIAS 350 AS350* EU TAIL ROTOR CRACKED W K NONE O OTHER ININSP/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. 1G71 3U H9EU 20081106 GL 2008 11 6 CA081020005 320081017G6114HCD4N3C SEAL BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL PROPELLER WORN W K NONE K FLUID LOSS ININSP/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 PROP 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 C1L72 3T4 T A14CE E4EA 5 CSTC 20081106 SW 2008 11 6 CA081020006 120081019G3230KRP5064 BEARING FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE MLG DAMAGED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) UPON TAKEOFF THE CREW REPORTED THAT THE RT GEAR WOULD NOT REMAIN LOCKED. ACFT RETURNED TO BASE AND UPON MX INSPECTION IT WAS FOUND THAT THE UP-LOCK HOOK BEARING AND ATTACHING HARDWARE WERE MISSING. IT WAS ALSO NOTED THAT THE UP-LOCK HOOK 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. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081106 2008 11 6 CA081020007 420081019G23303042865102 ELECTRICAL BOX BOEING737 737* NM GE CFM56 CFM567B24 NE SEAT ROW 16ABC ODOR W HA DEACTIVATE SYST/CIRCUITSUNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) FLIGHT ATTENDANTS NOTICED ELECTRICAL ODOR AT ROW 16 AND SHORTLY AFTER THE ROW 16ABC MALFUNCTIONED. LIVETV SYSTEM SHUT OFF IN FLIGHT DECK AND FLIGHT ATTENDANT STATION. THE SEB P/N 3042865-102 S/N 1792 WAS REMOVED. THIS SDR WILL BE UPDATED WHEN SEB TEARDOWN INFORMATION IS AVAILABLE. 2L72 4F4 FRTA16WE E00055EN 20081219 SW 2008 12 19 CA081020008 120081009G56102621126005 WINDSHIELD SWRNGNSA226 SA226T 8780122SW GARRTTTPE331TPE3311 01514WP COCKPIT CRACKED W B EMER. DESCENT O OTHER CRCRUISE 1 CA 177 (CAN) DURING CRUISE FLIGHT THE LT COCKPIT WINDSHIELD GLASS CRACKED WITH AN EXPLOSIVE BANG. THE CREW IMMEDIATELY DESCENDED AND REDUCED CABIN PRESSURE TO AVOID THE POSSIBILITY OF THE WINDOW GLASS BLOWING OUT. THE WINDOW WAS INSTALLED ON APRIL 11, 2006 AND HAD A TOTAL OF 177 HOURS SINCE OVERHAUL AND INSTALLATION. THE ACFT WAS IN THE USA AT THE TIME OF THE OCCURRENCE 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. 2L72 4T3 TRTA5SW E3WE 20081229 SW 2008 12 29 CA081020009 120081007G3244196K089 TIRE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33110U 29066NE MCAULY4HFR344HFR34C652 NE MLG SEPARATED W O OTHER C F.O.D. TXTAXI/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 MISSING. THIS TIRE WAS A RECAPPED TIRE RECEIVED FROM A CERTIFIED FAA REPAIR STATION. THE TIRE WHEN IT SHREDDED CAUSED DAMAGE TO THE ACFT FLAP AND SURROUNDING WW WHICH REQUIRED REPLACEMENT OF THE FLAP AND REPAIR OF THE WW AREA. MAINT REPAIRED THE ACFT AND REPLACED THE TIRE. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20081106 SO 2008 11 6 CA081020010 120081015G7930 FITTING PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A135 52043NE HARTZLHCB3T HCB3TN3 GL OIL PRESS LINE FAILED W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION TXTAXI/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 SHUTDOWN THE LT ENGINE AND TAXIED THE ACFT USING 1 ENGINE BACK TO THE HANGER. AFTER INSPECTION, IT WAS FOUND THAT THE HOSE ASSEMBLY 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 DETECTOR AND ENGINE FILTER WAS INSPECTED WITH NO FAULTS FOUND. THE WAS SERVICED WITH OIL AND SATISFACTORY OPS AND LEAK CHECKS WHERE CARRIED OUT WITH NO FAULTS FOUND. THE HOSE ASSEMBLY WAS REPLACED PRIOR BECAUSE THE HOSE ASSEMBLY TIME LIMIT WAS 1L72 3T4 TRTA8EA E4EA 6 CP15EA 20081107 WP 2008 11 7 CA081020011 120081016G7714 TACHOMETER ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) DURING DESCENT FROM ALTITUDE TO BEGIN LOW LEVEL FLIGHT FOR PIPE LINE SURVEILLANCE AT APPROX. 75 KNOTS INDICATED AIRSPEED AND VSI AT APPROX. 500 FPM, THE ENGINE RPM TACH INDICATED ENGINE OVERSPEED WELL ABOVE 110%. ALL OTHER ENGINE PARAMETERS REGISTERED WITHIN LIMITS, INCLUDING THE ROTOR RPM TACH. NO WARNING OR CAUTION LIGHTS. THE THROTTLE WAS LOWERED TO MAINTAIN NR RPM WHEN LOW ROTOR RPM HORN SOUNDED. A POWER ON LANDING PERFORMED WHILE ATTEMPTING TO MAINTAIN ENGINE TACH 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 ON1G71 3O3 O H11NM 1E4 20081107 NE 2008 11 7 CA081020012 220081019G8530 VALVE ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE STUCK W A UNSCHED LANDING E VIBRATION/BUFFET NRNOT REPORTED 1 CA (CAN) DURING STRAIGHT AND LEVEL CRUISE FLIGHT, THE PILOT NOTICED A SUDDEN INCREASE IN VIBRATION, THOUGHT TO BE COMING FROM THE ENGINE, AND AN INCREASE IN MANIFOLD PRESSURE. HE OPTED TO TURN AROUND AND LAND AT A NEARBY CAMP. DURING HIS DESCENT, THE VIBRATION STOPPED AND ENGINE PERFORMANCE RETURNED TO NORMAL. A COMPRESSION CHECK WAS FOUND NORMAL ON ALL CYLINDERS. A WIGGLE CHECK ON THE EXHAUST VALVES WAS FOUND SATISFACTORY, HOWEVER, 1 OF THE VALVES WAS AT 0.014 WHILE ALL THE OTHERS WERE AT 0.020 OR BETTER. IT IS SUSPECTED THAT THIS EXHAUST VALVE BECAME STUCK AND THEN CAME FREE AGAIN. 1G71 3O3 O H11NM 1E4 20081107 CE 2008 11 7 CA081021001 120081001G3220NAS150A48 BOLT BEECH BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE NLG LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BOLT WAS FOUND LOOSE ON RT SIDE OF NLG. THE COTTER PIN AND NUT WERE MISSING. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20081107 NM 2008 11 7 CA081021002 120081018G3260401020101 SENSOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NLG DOOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4571 (CAN) ON INSPECTION FOUND NOSE GEAR DOOR CLOSED SENSOR CRACKED. SENSOR REPLACED IAW AMM 32-61-06-04 2H72 4T4 TRTA13NM E00062EN 20081107 2008 11 7 CA081021003 420081019G312049712631 PRINTER CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE ACARS SMOKE W G O2 MASK DEPLOYED B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA 5044 5044 (CAN) DURING DESCENT TO YOW, CREW NOTICED SMOKE COMING FROM THE ACARS PRINTER, ELECTRICAL CIRCUIT BREAKER POPPED AND SMOKE STOPPED. NO EMERGENCY DECLARED AND THE ACFT LANDED WITHOUT FURTHER INCIDENT. ACARS PRINTER DIFFERED IAW MEL 23-22-0 AND CIRCUIT BREAKER SECURED. 2L72 4F4 FRTA21EA E15NE 20081107 NM 2008 11 7 CA081021004 120081019G3260 SENSOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NLG DOOR OUT OF RIG W A UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA (CAN) NOSE GEAR DOOR LIGHT FLICKERING ON AND OFF IN FLIGHT. RIGGED NOSE GEAR DOOR PROXIMITY SENSOR IAW AMM 32-61-06. CYCLED NOSE GEAR DOORS AND NO OTHER FAULTS FOUND. 2H72 4T4 TRTA13NM E00062EN 20081107 GL 2008 11 7 CA081021005 220081020G732323065121 GOVERNOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE MALFUNCTIONED W O OTHER J WARNING INDICATION CRCRUISE 1 CA 1329 (CAN) PILOT REPORTED ROTOR SPEED HUNTING IN CRUISE SO THE GOVERNOR WAS REMOVED TO CLEAN THE ORIFICES. ONCE REMOVED IT WAS NOTICED THAT THE EPOXY BOND ON THE END OF THE DRIVESHAFT WAS MISSING AND THE SPLINE DRIVE WAS LOOSE ON THE GOVERNOR DRIVESHAFT. IF LEFT THIS WOULD LIKELY TURN INTO WHAT WAS REPORTED IN SDR 20071015004 AND COULD LEAD TO AN ENGINE DECEL OR SHUT DOWN. 1G71 3U3 U H3WE E4CE 20081107 EU 2008 11 7 CA081021006 120081020G2730258CT29115A JACKSCREW HAWKER BRAERODH125 BAE125800A 1500285EU GARRTTTFE731TFE7315R 01518WP TRIM ACTUATOR FROZEN W K NONE O OTHER ININSP/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. 2L72 4F4 FRTA3EU E6WE 20081107 NM 2008 11 7 CA081021007 120081017G792128E997 OIL COOLER DHAV DHC8 DHC8106 2809020NM PWA PW121 PW121 52124NE NR 1 ENGINE LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 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 FOUND AN OIL LEAK FROM THE NR 1 ENGINE OIL COOLER. 2H72 4T4 TRTA13NM E20NE 20081107 CE 2008 11 7 CA081022001 120081021G5343AN35A BOLT CESSNA CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE MLG TRUNNION WRONG PART W O OTHER W INADEQUATE Q C NRNOT REPORTED 1 CA (CAN) CARRY OUT INSPECTION AS PER CAMPAIGN 851-53-11-047 CESSNA 550 CHANNEL-TRUNION BRACE. FOUND INCORRECT HARDWARE INSTALLED. NO VISUAL DAMAGE TO STEERING ARM. REPLACED HARDWARE AS PER CAMPAIGN. NO RESTRICTED TRAVEL FOUND. 1L72 4F4 F A22CE E1NE 20081107 NM 2008 11 7 CA081022002 120081014G324014209114 CONTROL MODULE EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE RT BRAKES FAILED W O OTHER J WARNING INDICATION LDLANDING 1 CA 3089 (CAN) AFTER LANDING, DURING DECELERATION ON RUNWAY AT APPROX 80 KTS, LT AND RT BRAKE FAULT MSG APPEARED ON EICAS ACCOMPANIED BY COMPLETE LOSS OF BRAKING. AFTER APPROX 8 SECONDS BRAKING RETURNED TO NORMAL AND EICAS MSG DISAPPEARED. SERVICE NEWS 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 2L72 4F4 FRTA57NM E00070EN 20081230 CE 2008 12 30 CA081022003 120081020G5240H1721050100 LATCH LEAR 35 31A 5170531CE GARRTTTFE731TFE73123B WP SERVICE DOOR UNSERVICEABLE W O OTHER E VIBRATION/BUFFET DEDESCENT 1 CA (CAN) SINGLE POINT FUEL DOOR LATCH OPENED IN FLIGHT. 2L72 4F4 FRTA10CE E6WE 20081107 EU 2008 11 7 CA081022004 120081015G2421200322 GENERATOR AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE NR 1 FAILED W O OTHER J WARNING INDICATION CRCRUISE 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. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20081107 NM 2008 11 7 CA081022005 120081021G3260401020101 PROXIMITY SENSOR DHAV DHC8 DHC8* NM PWC 150 PW150A EA RT MLG OUT OF RIG W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) RT MLG FAILED TO RETRACT NORMAL, AMBER DOOR LIGHT, HANDLE LIGHT AND RED DISAGREEMENT LIGHT ILLUMINATED. RT MLG PROXIMITY SENSOR FOR UPLOCK INDICATION RIGGED AS PER AMM 32-61-06-400-802. GAP SET TO .045, MH 8.621 2H72 4T4 TRTA13NM E00062EN 20081107 WP 2008 11 7 CA081022006 220081019G7261 CARBON SEAL DORNERDO228 DO228202 2992030EU GARRTTTPE331TPE3315 01514WP NR 1 ENGINE LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION NRNOT 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 TESTING AT ENGINE SHOP. 2H72 4T4 TRTA16EU E4WE 20081230 GL 2008 12 30 CA081022008 120081021G2710AN2412 CLEVIS BOLT DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD22D 22D30 NE CONTROL CABLE WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING AN AILERON CABLE (IN WING) REPLACEMENT THE CLEVIS BOLTS WERE FOUND TO BE WORN MORE THAT 30 PERCENT, REPLACED WITH NEW AN 24-12 CLEVIS BOLTS. 1H71 3R3 RRCA806 5E1 5 CP736 20081107 NE 2008 11 7 CA081022009 220081007G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE DAMAGED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 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 CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1H71 3T3 T A37CE E4EA 20081230 CE 2008 12 30 CA081022010 120081002G2752503801537 DRIVE ASSY BEECH BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE FLAP ACTUATOR SHEARED W L ABORTED APPROACH F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) ON APPROACH THE FLAPS WERE SELECTED TO 17 DEG BUT FAILED TO EXTEND PAST 10 DEG. THE FLIGHT CREW INITIATED AN OVERSHOOT TO TROUBLESHOOT THE PROBLEM, THEY WERE UNABLE TO FIX THE BROKEN FLAPS AND RETURNED TO BASE. MX REPLACED THE FLAP DRIVE AND NO FURTHER FAULTS WITH SYS FOUND. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20081230 NM 2008 12 30 CA081023001 120081023G2710 BEARING DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE CABLE PULLEY SEIZED W K NONE O OTHER ININSP/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 REMAINING BEFORE COMPLETION OF TASK 2710/02 (11000 HRS). 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 NM 2008 12 30 CA081023002 120081013G291019071270901 RESTRICTOR VALVE EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE HYDRAULIC SYS CRACKED W O OTHER K FLUID LOSS TXTAXI/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 CLOSE INSP, FOUND A VERTICAL CRACK IN THE THREADED PORTION OF THE VALVE UNDER THE B-NUT (BOTH RESTRICTOR VALVES). THESE FINDINGS RAISED THE CONCERNS OF ATTACHING A STAINLESS STEEL LINE AND B-NUT TO THE LIGHTER ALUMINUM RESTRICTOR VALVE. A 1.1250 IN WRENCH IS REQUIRED TO TIGHTEN THE "B" NUT. NOTE, WE ALSO REPLACED THE HYD LINE ASSY. 2L72 4F4 FRTA57NM E00070EN 20081107 NM 2008 11 7 CA081023003 120081019G279719019564401 WIRE HARNESS EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE SLAT SYSTEM DAMAGED W A UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION CLCLIMB 1 CA (CAN) ON FLAP RETRACTION AFTER T/O. SLAT FAIL EICAS MSG DISPLAYED. CARRIED OUT QRH FOR SLAT FAIL. DID NOT RECTIFY PROBLEM. 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. 2L72 4F4 FRTA57NM E00070EN 20081230 NE 2008 12 30 CA081023004 120081016G792228E251 THERMOSTAT SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL NR 2 OIL COOLERUNSERVICEABLE W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMP 8 EXCEEDED RED LINE LIMIT. 1G72 3U3 U H1NE E1GL 20081222 SW 2008 12 22 CA081023005 120080727G5302205032807003 FITTING BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE TAILBOOM CRACKED W K NONE O OTHER ININSP/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. 1G71 4U4 U H1SW E17EA 20081222 SO 2008 12 22 CA081024001 120081024G53436705403 TRUNNION PIPER PA32 PA32R300 7103213SO LYC 0540 IO540K1G5D 41532SO HARTZLHCC3Y HCC3YR GL NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4771 (CAN) FOUND GREASE LEAKING FROM TOP PORTION OF THE LWR BRG SUPPORT. CLEANED AREA AND RE GREASED TRUNNION. GREASE WAS FOUND COMING OUT OF CRACK. THE CRACK IS APPROXIMATELY ONE INCH LONG, HORIZONTAL. THIS CRACK INDICATION DOES APPEAR TO BE CAUSED BY IMPROPER GROUND HANDLING. STEPS ARE BEING TAKEN TO REPLACE PART AT THIS TIME. 1L71 3O3 O A3SO 1E4 5 CP25EA 20081230 NE 2008 12 30 CA081024002 120081021G29109265004900101 HEAT EXCHANGER SKRSKYS92 S92A NE GE CT7TS CT78A 30136NE HYD SYSTEM CRACKED W O OTHER K FLUID LOSS CRCRUISE 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/CAUTION 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 CHECKLIST 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 2G72 4U4 U R00024BOE8NE 20081107 WP 2008 11 7 CA081024003 120081015G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE INOPERATIVE W O OTHER O OTHER NRNOT REPORTED 1 CA 413 (CAN) STARTER GEN WOULD NOT ENGAGE ENGINE, REPLACED WITH SERVICEABLE STARTER GEN. 1G71 3O3 O H11NM 1E4 20081107 WP 2008 11 7 CA081024004 120081011G6730D2121 SERVO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE PILOT VALVE LEAKING W O OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 CA 1690 (CAN) SERVO LEAKING FROM PILOT VALVE 1G71 3O3 O H11NM 1E4 20081107 WP 2008 11 7 CA081024005 120081011G6730D2121 SERVO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE PILOT VALVE LEAKING W O OTHER K FLUID LOSS NRNOT REPORTED 1 CA (CAN) SERVO LEAKING FROM PILOT VALVE 1G71 3O3 O H11NM 1E4 20081230 2008 12 30 CA081024006 420081010G2216 GROUND WIRE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP TRIM SYS OPEN W O OTHER F FLT CONT AFFECTED LDLANDING 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. 2L72 4F4 FRTT00008WIE6WE 20081107 NE 2008 11 7 CA081025001 220081024G7530BRH10211MS3215 PIN BOEING717 717200 1383700NM RROYCEBR700 BR700715A130 NE LINKAGE MISSING W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 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 MALFUNCTION. IT HAS BEEN REPORTED BY OPERATOR THAT BVV LEVER WAS NOT OPERATING PROPERLY. ENGINE AT ROLLS ROYCE CANADA FOR REPAIR TO DETERMINE THE ROOT CAUSE OF MECHANISM MALFUNCTION. STRIP WAS CARRIED OUT TO EXPOSE THE BOOSTER BLEED VALVE MECHANISM AND IT WAS NOTED THAT PIN AND RETAINING RING WERE MISSING. THIS PIN IS THE JUNCTION BETWEEN THE BELL CRANK LEVER 2L72 4F4 FTRA6WE E00061EN 20081107 NE 2008 11 7 CA081025002 220081010G7320251818 BRACKET BOEING717 717200 1383700NM RROYCEBR700 BR700715A130 NE ENGINE BROKEN W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA 22738 (CAN) ENGINE AUTO IFSD, ACFT DIVERTED TO ATL UNEVENTFUL LANDING. FSO CABLE RELEASE, PIECES FOUND IN THE TAILPIPE. LPT3 SCUFFED AND NICKED CONSISTENT WITH CABLE DAMAGE. NO EVIDENCE OF A TURBINE FAILURE. LP SYSTEM FREE TO TURN SMOOTHLY. ENGINE IN RRC FOR INVESTIGATION. FURTHER DETAIL WILL BE SUBMITTED. 2L72 4F4 FTRA6WE E00061EN 20081107 CE 2008 11 7 CA081027001 120081023G61208930861 SHAFT MTSBSIMU2 MU2B36 5780412CE GARRTTTPE331TPE33110 01514WP HARTZLHCB3T HCB3TN5 GL PROPELLER BINDING W O OTHER F FLT CONT AFFECTED DEDESCENT 1 CA 255085965 (CAN) PROP OVERSEED DURING DESCENT. FOUND ENGINE INNER CONCENTRIC SHAFT TO BE BINDING ON OUTER CONCENTRIC SHAFT. AS POWER LEVER IS RETARDED, INNER CONCENTRIC SHAFT ROTATES SLIGHTLY CLOCKWISE INCREASING PROP GOVERNOR HIGH SETTING. THERE IS NO PROVISION FOR LUBRICATION IN THIS AREA AND IT ONLY RELIES ON SPRING FORCE TO RETURN THE PROP GOVERNOR TO A LOWER SETTING. INNER SHAFT REMOVED, CLEANED, LUBRICATED AND REINSTALLED 1H72 3T4 TRTA10SW E4WE 6 CP15EA 20081230 EA 2008 12 30 CA081027002 120080910G243523048016 STARTER GEN DHAV DHC3 DHC3 2800202EA PWA PT6 PT6A135 52043NE HARTZLHCB3T HCB3TN3 GL WORN W K NONE O OTHER ININSP/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. 1H71 3R4 T A815 E4EA 6 CP15EA 20081230 EA 2008 12 30 CA081027003 220081025G7321 SHAFT BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL FCU THROTTLE STIFF W E ENGINE SHUTDOWN F FLT CONT AFFECTED APAPPROACH 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 APPROACH 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 ACFT RETURNED TO SERVICE. 1L72 3T4 T A14CE E4EA 5 CSTC 20081222 EA 2008 12 22 CA081027004 120081024G5280491184 BRACKET CNDAIRCL600 CL600* 1900302EA GE CF34 CF348C5 30050NE RT MLG DOOR LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) INBD MLG RT DOOR ATTACHMENT BRACKET ON STRUT FOUND LOOSE DURING HEAVY MAINT VISIT. REFERENCE: CMM 32-11-05, FIGURE 1, PAGE 1019, ITEM 290. IT IS WORTH NOTING THAT THIS IS THE 2ND TIME, IN THE MONTH OF OCTOBER 2008, THAT THIS ISSUE HAS 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. 2L72 4F4 FRTA21EA E00063EN 20081229 CE 2008 12 29 CA081027005 120081022G3233ADI79990038 FORK ADI7999003 BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCD4N3HCD4N3A GL ACTUATOR BROKEN W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF THE PILOT SELECTED GEAR UP, RT MLG FAILED TO RETRACT. GEAR WAS CYCLED WITH NO SUCCESS. GEAR WAS RETURNED TO DOWN POSITION AND THERE WERE 3 GREEN LIGHTS. DISPATCH AND MX WERE CONTACTED AND IT WAS DECIDED TO RETURN TO BASE. LANDING WAS UNEVENTFUL. UPON INSP BY MX, THE RT MLG ACTUATOR FORK END THAT ATTACHES TO THE UPPER DRAG BRACE WAS SHEARED 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 REPLACED WITH NEW PARTS. CYCLES OR HRS ON BROKEN FORK END IS UNKNOWN. THE GEAR WAS INSPECTED FURTHER AND NO OTHER DEFECTS FO1L72 4T4 T A24CE E4EA 5 CSTC 20081230 EU 2008 12 30 CA081027006 120081023G2130 BUTTERFLY VALVE AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE CABIN PRESSURE STICKING W A UNSCHED LANDING O OTHER CLCLIMB 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. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20081230 CE 2008 12 30 CA081028001 120081001G249770002405D CIRCUIT BREAKER CESSNA680 680CE 2076811CE PWC PW306 PW306C 52169NE LT POWER FEED TRIPPED W O OTHER J WARNING INDICATION CRCRUISE 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. 2L72 4F4 FRCT00012WIE35NE 20081222 SW 2008 12 22 CA081028003 120081024G6320407040035101 BEVEL GEAR BELL BELL 407 407 1182206SW ALLSN 250C 250C47B GL TRANSMISSION DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 6089 1122 (CAN) TRANSMISSION CHIP LIGHT ILLUMINATED. MECHANIC FOUND SMALL DEBRIS ON THE LWR CHIP PLUG. UPON INSP BY THE OVERAUL SHOP, THEY DISCOVERED THE BEVEL GEAR DAMAGED. A SMALL PIECE OF GEAR TOOTH APPROX. .360X.073 HAD BROKEN OFF THE GEAR ASSY AND DISCOVERED THE BEVEL GEAR CRACKED AT THE DAMAGED GEAR TOOTH ARED. 1G71 3U3 UO H2SW E1GL 20081230 GL 2008 12 30 CA081028004 120081021G27202227271200 TUBE DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA RUDDER CONTROL WORN W K NONE O OTHER ININSP/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. 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20081230 WP 2008 12 30 CA081028005 120081022G243514924HTH STARTER GEN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE DISENGAGED W O OTHER O OTHER NRNOT REPORTED 1 CA 201 (CAN) STARTER WOULD NOT ENGAGE THE RING GEAR. 1G71 3O3 O H11NM 1E4 20090102 WP 2009 1 2 CA081028006 120081024G6310C0183 BAR ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA SPRAG CLUTCH CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA 930 (CAN) DURING AN AES MIDLIFE INSP FOUND: SPRAG CAGE CRACKED (2) CROSSBARS SHAFT WORN UNDERSIZE HOUSING WORN OVERSIZE. 1G71 3O3 O H11NM E295 20090102 GL 2009 1 2 CA081028007 120081020G5320C2CE329A BRACKET DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD22D 22D30 NE FIREWALL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSP, AN AME FOUND A CRACK IN RADIUS OF MIXTURE CONTROL BRACKET ATTACHED TO FIREWALL, BRACKET WAS REMOVED, REPAIRED AND REINSTALLED. 1H71 3R3 RRCA806 5E1 5 CP736 20090102 EA 2009 1 2 CA081029001 120081027G2820 TUBE CNDAIRCL604 CL604 1900301EA FUEL SYS DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) WHILE TROUBLESHOOTING A FUEL TRANSFER PROBLEM ON THE CHALLENGER 604, SERIAL NR 5320, WE FOUND 3 DAMAGED FUEL TUBES IN THE CENTER FUEL TANKS, 2 IN THE RT SIDE AND 1 IN THE LT SIDE. ALL 3 FUEL TUBES WERE REPLACED. 2L72 4F RTA21EA 20090102 SO 2009 1 2 CA081029002 120081027G77211020007 PROBE PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL CYLINDER HEAD MALFUNCTIONED W E ENGINE SHUTDOWN N FALSE WARNING CRCRUISE 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 WHEN ENGINE WAS COLD. CHANGED THE PROBE TO P/N AN5546-1 IAW IPC. THE PROBE REMOVED IS AN FAA/PMA ALTERNATE TO THE REQUIRED P/N IN THE IPC. 1L72 3O3 O A20SO E14EA 5 CP33EA 20090102 NM 2009 1 2 CA081029003 120081024G612030005000024 SIGNAL COND UNIT DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF* NE PROPELLER INOPERATIVE W E ENGINE SHUTDOWN F FLT CONT AFFECTED CLCLIMB 1 CA 3523635236 (CAN) JUST AFTER TAKEOFF, NR 2 ENGINE WENT TO FEATHER. AUTO FEATHER WAS ARMED/CREW HAD NOT COMMANDED AN ENG FEATHER. CREW COMPLETED SHUT DOWN OF NR2 ENG, DECLARED AN EMERGENCY AND RETURNED TO ORIGINATING AIRPORT. NO OTHER INCIDENTS DURING LANDING. MAINT INTERROGATION OF FDR RECORD SHOWS ELECTRONIC FEATHER SIGNAL WAS GENERATED BY THE TSCU AND SYSTEMS RESPONDED 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 (TSCU SUSPECTED) REPLACED FOR TROUBLESHOOTING. ENGINE OVER TORQUE INSPECTIONS COMPLETED AND ALLOWED TO CONTINUE IN SERVICE2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090102 EA 2009 1 2 CA081029004 120081026G27508004301 CONTROL UNIT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS UNSERVICEABLE W O OTHER F FLT CONT AFFECTED DEDESCENT 1 CA (CAN) ON DECENT CREW SELECTED FLAPS DOWN AND FLAPS STOPPED AT 3 DEGREES. CREW ELECTED TO DO A GO AROUND AND PERFORMED THEIR 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 UNIT REPLACED AND SYS CHECKED SERVICABLE. 2L72 4F4 FRTA21EA E15NE 20090105 NE 2009 1 5 CA081029005 220080915G7261 OIL SYSTEM STBROSSD3 SD360 8100606EU PWA PT6 PT6A65AR 52043NE ENGINE LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 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 INSPECTION REVEALED OIL LEAKING FROM GAS GENERATOR CASE AND EXHAUST AREA. THE ENG WAS REMOVED AND SENT FOR INVESTIGATION WHERE TEARDOWN REVEALED A NR 1 BEARING DISTRESS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 T A41EU E4EA 20090102 NE 2009 1 2 CA081029006 220081016G7250 TURBINE AEROSPATR72 ATR72201 8680943EU PWA PW120 PW124B NE LT ENGINE SEIZED W C ABORTED TAKEOFF XJ ENGINE FLAMEOUT WARNING INDICATION TOTAKEOFF 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. REVIEW 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 AND THE TMM CHIP DETECTOR WERE INSPECTED AND FOUND CONTAMINATED. THE STARTER GEN WAS REMOVED IN ORDER TO ROTATE THE HP SHAFT BUT THE HP TURBINE WAS SEIZED. BORESCOPE INSP PERFORMED AND CONFIRMED THAT THE HP TURBINE WAS NOT ROTATING. SUSPECTING DISTRESS IN THE TOWERSHAFT AREA, THE COVER OF THE AGB DRIVE WAS REMOVED. INSP SHOWED A TOWERSHAFT WITH SIGNIFICANT RAD2H72 4T4 TRTA53EU E2ONE 20090102 CE 2009 1 2 CA081030001 120081012G2160HYLZ503361 CONTROLLER BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCD4N3HCD4N3A GL A/C SYSTEM SMOKE W O OTHER B SMOKE/FUMES/ODORS/SPARKS LDLANDING 1 CA (CAN) THE FLIGHT CREW REPORTED SMOKE IN THE CABIN, THE ACFT LANDED SAFELY. MX INSPECTED AND SMOKE WAS THOUGHT TO BE COMING FROM THE VENT BLOWER, THE BLOWER WAS REPLACED, GROUND RUN-UP CHECK WAS CARRIED OUT AND NO SMOKE WAS EVIDENT COMING FROM AIR CONDITIONING SYS. DURING TEST FLIGHT, THERE WAS NO HEATING CONTROL IN AUTO MODE. THE SYS WAS SWITCHED TO MANUAL AND HEAT CONTROLLING WAS POSSIBLE. WHEN THE SYS WAS SWITCHED BACK TO AUTO, A SLIGHT BURNING SMELL WAS NOTICED BUT THERE WAS NO SMOKE IN THE CABIN. THE SYS WAS TURNED OFF AND THE ACFT RETURNED TO BASE. THE CABIN TEMP CONTROLLER WAS REMOVED AND INSPECTED. THERE WAS EVIDENCE OF DAMAGE AND ARCING ON THE UNIT AND IT WAS REPLACED AND THE ACFT RETURNED TO SERVICE. 1L72 4T4 T A24CE E4EA 5 CSTC 20081230 EA 2008 12 30 CA081030002 120081024G3246472439473232 SEAL CLEVELANDPNU DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL WHEEL WRONG PART W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THIS PROBLEM WAS IDENTIFIED WHILE CARRYING OUT ROUTING MX ON AMPHIBIAN FLOAT MAIN WHEELS. THE MFG PARTS BOOK SPECIFIED 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 FLOATS ONLY HAVE 32 HOURS TSN, MFG FAILED TO INFORM THEIR CUSTOMERS OF THIS PROBLEM WITH THE SIZE OF THE GREASE SEAL. 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20081230 NM 2008 12 30 CA081030003 120081016G27511817392 TRANSMITTER BOEING737 737201 1384454NM PWA JT8 JT8D17 52049NE LT FLAP POSITIONFAILED W L ABORTED APPROACH F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) DURING FINAL APPROACH, WHEN THE PILOTS SELECTED FLAPS 25, THE FLAPS STOPPED SLIGHTLY PAST FLAPS 15. THE PILOTS SELECTED 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 THE FLAPS DOWN. ON THE SECOND TRY, THE FLAPS OPERATED NORMALLY. MX INSPECTED AND FUNCTIONED THE FLAP SYS A SECOND TIME AN2L72 4F4 F A16WE E2EA 20081230 WP 2008 12 30 CA081030004 120080313G7810C1693 EXHAUST DUCT ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE DEFORMED W O OTHER S AFFECT SYSTEMS NRNOT REPORTED 1 CA (CAN) VISUAL INSP (CF90-03R2) FOUND DEFORMATION AND CRACK IN MUFFLER ASSY AT THE BASE OF THE EXHAUST PIPE WITH SUBSEQUENT LEAK OF EXHAUST GASES INTO CABIN HEAT SYS, NO CO WARNING LIGHTS OR PILOT REPORTS POSTED. PART REPLACED AS REQ`D. 1G71 3O3 O H11NM 1E4 20081230 SW 2008 12 30 CA081031001 120081031G6510327211 COUPLING BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL T/R DRIVE SHAFT CRACKED W K NONE O OTHER ININSP/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 SERVICE AND REPLACED NEW. THE AFT COUPLING WAS ALSO INSPECTED FUTHER WITH NO DAMAGE NOTED. 1G71 3U3 U H2SW E1GL 20081230 SW 2008 12 30 CA081031002 120081029G3210ESI2440 HOUSING GULSTM690TP 690A 0141722SW GARRTTTPE331TPE33110T 29065NE HARTZLHCB3T HCB3TN5 GL MLG CRACKED W K NONE O OTHER ININSP/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 .040". THIS WAS THE FIRST OVERHAUL OF THIS LANDING GEAR BY THE OPERATOR SINCE PURCHASE 3 YEARS AGO. 1H72 3T4 T 2A4 E4WE 6 CP15EA 20081230 SW 2008 12 30 CA081031004 120081031G2710 ROLL PIN AIRTRCAT802 AT802A 0390308SW PWA PT6 PT6A67A 52043NE AILERON PUSHROD MISSING W K NONE O OTHER ININSP/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 MISSING PIN HOLE. 1L71 3T4 TNCA19SW E26NE 20081230 2008 12 30 CA081103001 420081016G2300 DISPLAY BOMBDRBD100 BD1001A10 1390044GL HNYWL AS907 AS90711A 33908WP FAILED W O OTHER H ELECT. POWER LOSS-50 PC DEDESCENT 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 REVERSIONARY PANEL AND TURNING THE TUNE KNOB TO THE COMM1 121.5 SELECTION. LANDING WAS UNEVENTFUL. AFTER LANDING 20 MINUTES 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 FAULTS. PLEASE SEE ATTACHED PIC`S BELOW FOR FAULTS AND THE B3 CODES. CREW THEN DID A COMPLETE POWER DOWN ACFT AND WAIT A FEW2L72 4F4 FRTT00005NYE00010LA 20081230 NM 2008 12 30 CA081103002 120080716G3320BR63031023 SOCKET DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE CABIN LIGHTS MELTED W K NONE O OTHER ININSP/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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 EA 2008 12 30 CA081103003 120081102G291082970009325 LINE DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE HYD SYSTEM CHAFED W A UNSCHED LANDING K FLUID LOSS CRCRUISE 1 CA 3829438294 (CAN) DURING CRUISE FLIGHT, THE ACFT REPORTED LOSING NR1 HYD SYS FLUID AND ACTIVATION OF NR1 ISO VALVE. COMMERCIAL DECISION 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 2008 12 30 CA081103004 420081008G8300310186401 BEARING CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL ACCESSORY G/B FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 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. 1H71 3T3 T A37CE E4EA 5 CP60GL 20081230 SW 2008 12 30 CA081103005 120081030G800031057463 IGNITION SWITCH SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 29073NE MCAULY4HFR344HFR34C652 NE ENGINE CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) OIL LEAK ON THE ENG FROM LWR ENG COWL FOUND. TROUBLESHOOTING REVEALED THE PROBLEM AS A AUTO IGNITION PRESSURE SWITCH LEAKING AT THE BASE WELD. INSP WITH A MAGNIFYING GLASS FOUND A CRACK APR .7500 AROUND THE CIRCUMFERENCE OF THE WELD. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20081230 EU 2008 12 30 CA081104001 120081028G3231 HOSE BRAERODH125 BAE125800A 1500285EU GARRTTTFE731TFE7315R 01518WP DOOR ACTUATOR LEAKING W O OTHER KJ FLUID LOSS WARNING INDICATION TXTAXI/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 AIDED IN ALLOWING THE B-NUT TO BACK OFF CAUSING THE HYDR LEAK IN THE RT GEAR WELL. AREA CLEANED UP. THE LINE WAS INSPECTED 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 CY2L72 4F4 FRTA3EU E6WE 20081222 NE 2008 12 22 CA081104002 220081031G7230 COMPRESSOR DOUG DC3 DC3C 3021457WP PWA PT6 PT6A67R 52043NE HARTZLHCB5M HCB5MA3 GL RT EINGE SEIZED W A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 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. 2L72 4R4 T A669 E26NE 6 CP44GL 20081222 GL 2008 12 22 CA081104003 120080927G241007A19474 BRACKET DIAMONDA40 DA40 2990002GL LYC O360 IO360M1A NE MUHBR MTV MTV3BC EU ALTERNATOR BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 805 (CAN) DURING A ROUTINE INSP, THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE BROKEN ACROSS THE WIDTH OF THE BRACKET ADJACENT ONE OF THE MOUNTING HOLES. (REAR MOUNTING BOLT THAT IS USED TO ATTACH THE BRACKET TO THE ENGINE). 1L71 3O3 ONTA47CE 1E10 5 CUSSR 20081222 NM 2008 12 22 CA081104004 120081031G555417063073405 FITTING EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE RUDDER BROKEN W O OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 CA 6515 (CAN) ON PUSHBACK, RECEIVED FLIGHT CONTROL- NO DISPATCH MESSAGE. INVESTIGATION FOUND THE RUDDER UPPER FTG LUG BROKEN. RUDDER 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 CUT/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 INSTALLED, SITS INSIDE THE FLANGED BUSHING, AND PREVENTS SIDE LOADS FROM BEING APPLIED ON THE LUGS WHEN THE ATTACH BOLT IS TO2L72 4F4 FRTA56NM E00063EN 20081222 EU 2008 12 22 CA081105001 120081105G2822D107318D1 PUMP BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL FUEL BOOST MISINSTALLED W K NONE W INADEQUATE Q C ININSP/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 THE 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. 1G72 3U3 U H3EU E4CE 20081222 NE 2008 12 22 CA081105002 220080908G7200 ENGINE SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE OVERTEMP W EA ENGINE SHUTDOWN UNSCHED LANDING RMJPARTIAL RPM/PWR LOSS OVER TEMP WARNING INDICATION DEDESCENT 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 ENG HAD LOW N1 RPM WITH A CLIMBING T5 TEMP. FLT CREW IDENTIFIED PROBLEM AS AN ENG ROLL BACK AND SHUTDOWN OF NR 2 ENGINE CARRIED OUT. ACFT THEN RETURNED TO LANDING AREA AND MADE AN SINGLE ENG LANDING. A POST FLT INSP OF T5 RECORDING SYS REVEALED ENGINE TEMP HAD REACHED 798 DEGREES C. ENGINE, FREE TURBINE ASSEMBLY AND FUEL CONTROL UNIT REPLACED AND AFTER A COMPLETE GROUND CHECK ACFT RETURNED TO SERVICE. ENGINE, FREE TURBINE AND FUEL CONTROL UNIT WERE RETURNED FOR AN OVER TEMP I2G72 4U4 U H4EA E15EA 20081222 EU 2008 12 22 CA081105003 120081102G32505322012040 LANDING GEAR PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL NOSE MALFUNCTIONED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) WHILE TAXING FOR TAKEOFF, THE NOSE STEERING BECAME VERY STIFF. PILOT RETURNED TO THE RAMP AND MAINT DISCOVERED THAT 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. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081222 NM 2008 12 22 CA081105004 120081103G2910 LINE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU HYD SYSTEM RUPTURED W O OTHER KJ FLUID LOSS WARNING INDICATION CRCRUISE 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 TECHNICIANS DISCOVERED RUPTURED HYD LINE IN NR 1 MLG GEAR BAY. LINE HAD BEEN CHAFED FROM A BONDING CLAMP (AN735C4). TECH REPORTED BONDING CLAMP WAS LOOSE, AND APPEARED TO BE INSTALLED WITHOUT SEALANT. RUPTURED HYD LINE WAS FOR THE NR 1 MLG DOWNLOCK ACTUATOR. LINE REPAIRED WITH A PERMASWAGED SPLICE SECTION, AND A/C RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081219 NM 2008 12 19 CA081105005 120081103G291082974351003 LINE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA HYD SYSTEM LEAKING W O OTHER KJ FLUID LOSS WARNING INDICATION CRCRUISE 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 ALTERNATE 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 LINE, WHERE IT HAD BEEN CHAFFING ON THE FWD JET PIPE SHROUD DAMAGED LINE WAS PART OF MLG `NR 2 GEAR UP` PIPING, P/N 82974351-003. LINE TO BE REPLACED. 2H72 4T4 TRTA13NM E00062EN 20081222 NE 2008 12 22 CA081105006 220081028G7200 ENGINE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF* NE NR 2 MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 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 ACCOMPLISHED. TROUBLESHOOTING LED TO THE REPLACEMENT OF THE TORQUE SIGNAL CONDITIONER UNIT AND THE TORQUE SENSOR. MM REQUIREMENTS 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 NE 2008 12 30 CA081105007 220081029G7200 ENGINE PWA PT6 PT6A68 NE MAKING METAL W BA EMER. DESCENT UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CA (CAN) DURING FLIGHT TEST, THE ENG HAD A PARTIAL FEATHERING OF THE PROPELLER LEADING TO A PARTIAL LOST OF THRUST. THE ENGINE "CHIP LIGHT" CAME APPROX 20 SECONDS AFTER LOST OF THRUST. THE PILOT REDUCED POWER TO FLIGHT IDLE AND RETURNED TO BASE. POST FLIGHT INSP REVEALED METALLIC DEBRIS ON THE CHIP DETECTOR AND MAIN OIL FILTER. THE ENGINE WILL BE RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE PROVIDED IN DUE COURSE. 4 T E26NE 20081229 NE 2008 12 29 CA081105008 220081031G7261 CARBON SEAL AMD FALC50FALCON2000 2730170NM PWC PW308 PW308C 52182NE ENGINE CRACKED W C ABORTED TAKEOFF KJ FLUID LOSS WARNING INDICATION TOTAKEOFF 1 CA (CAN) DURING TAKEOFF ROLL, AT 90 KNOTS, THE OIL PRESSURE DROPPED TO ZERO AND THE LOW OIL PRESSURE WARNING ANNUNCIATED. THE CREW RETARDED THE POWER TO IDLE, ABORTED THE T/O AND RETURNED TO THE RAMP. TROUBLESHOOTING FOUND AN OIL LEAK FROM A CRACKED CARBON SEAL ON THE FRONT HYD PUMP DRIVE PAD. THE ACFT WAS RETURNED TO SERVICE FOLLOWING ITS REPLACEMENT. 2L72 4F4 FRTA50NM E00065EN 20081222 NE 2008 12 22 CA081105009 220081101G7200 ENGINE CESSNA500 550 2076604CE PWA 530 PW530A NE NR 2 FLAMED OUT W A UNSCHED LANDING RXJPARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE AT FL270, THE PILOT NOTICED A POWER ROLL BACK ON NR 2 ENGINE. HE IMMEDIATELY DIVERTED THE ACFT TO AN ALTERNATE AIRPORT. THE ENGINE THEN FLAMED OUT AND THE PILOT MADE A SINGLE ENGINE LANDING. THE FUEL CONTROL WAS REPLACED AND THE ACFT RELEASED TO SERVICE. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L72 4F4 F A22CE E00053EN 20081222 WP 2008 12 22 CA081105010 120081105G5340C8303 ANGLE ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ELT MOUNT CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA 2149 (CAN) FOUND CRACKED ANGLE DURING INSPECTION OF ELT MOUNT. 1G71 3O3 O H11NM 1E4 20081229 EA 2008 12 29 CA081105011 120080924G524033130131 PISTON CNDAIRCL215 CL2151A10 1900320EA PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE ACTUATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 256 (CAN) DURING ANNUAL INSP, WATER DOOR UNLATCHING JACKS WERE REMOVED FOR INSPECTION. THE PISTONS OF THE JACKS WERE INSPECTED USING LIQUID PENETRANT INSPECTION FOR PRECAUTIONARY REASONS. BOTH PISTONS OF THE ACTUATORS WERE FOUND TO HAVE INDICATIONS 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 PISTONS CRACKING. BOTH OF THESE ACTUATORS HAD BEEN THROUGH OUR OVERHAUL SHOP. ONE ACTUATOR WAS REPAIRED, THE OTHER WAS OVERHAULED. IN BOTH CASES, THE ACTUATORS HAD NEW PISTONS INSTALLED AND ACCUMULATED. 2H72 4R3 RRTA14EA ATC14 6 CP871 20081229 EA 2008 12 29 CA081105012 120081020G2751601R930303 TRANSMITTER CNDAIRCL600 CL6002B19 1900309EA MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 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 DEGRADED (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 STARTED THEIR DEVIATION, THE ACFT NOSED OVER BRIEFLY WITH ABOUT A 500 FT LOSS IN ALTITUDE BUT INSTANTLY RECOVERED BACK TO2L72 4F RTA21EA 20081229 2008 12 29 CA081106001 420081104G2562E01 ELT INOPERATIVE W K NONE L NO TEST ININSP/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 420081104G2562E01 ELT MALFUNCTIONED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) DURING THE ANNUAL BENCH RECERTIFICATION INSP OF AN ELT THE VALUE OF MEASURED CURRENT DRAW WAS OBSERVED TO EXCEED THE MFG SPECIFICATION BY 50MA. THE UNIT WAS STILL UNDER THE MFG WARRANTY AND IT WAS BELIEVED THIS INSP WAS THE FIRST CHECK COMPLETED SINCE BEING PUT INTO SERVICE. THE ELT WAS RETURNED TO THE MFG FOR REPAIR. 20081229 EA 2008 12 29 CA081106003 220081030G8520 CASE CESSNA150 152 2071835CE LYC O235 O235N2C 41505EA SNSNCH72C 72CK EA ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINT (OIL CHANGE) OIL WAS DISCOVERED LEAKING FROM THE UPPER ENGINE CRANK CASE. FUTHER INSP CONFIRMED A CRACK 3 INCHES LONG BETWEEN CYLINDER NR 2 AND 4. ENGINE WAS REMOVED FOR REPAIR. 1H71 3O3 ONT3A19 E223 5 NP9045 20081229 GL 2008 12 29 CA081106004 120081010G2840 FLOAT GE DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE FUEL TRANSMITTERDETACHED W O OTHER N FALSE WARNING NRNOT REPORTED 1 CA (CAN) GENERAL ELECTRIC FUEL TRANSMITTER MODEL NR 56949-248, TYPE TJ-13. FUEL GAUGE READINGS WERE STUCK AT 22 GAL, INDICATING ON CENTER FUEL CELL. INVESTIGATION REVEALED THAT THE FUEL TRANSMITTER. FLOAT HAD BECOME DETACHED FROM THE FUEL TRANSMITTER. FUEL TRANSMITTER REMOVED, REPAIRED, TESTED AND REINSTALLED. 1H71 3R3 RRCA806 5E1 5 CP206 20081229 SO 2008 12 29 CA081106005 120081031G7820 BAFFLE PIPER PA28 PA28180 7102808SO LYC O360 O360A4A 41514EA SNSNCH76E 76EM8S5 EA MUFFLER FAILED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CA (CAN) POWER LOSS ON TAKEOFF DUE TO BAFFLE FAILURE INSIDE MUFFLER WHICH RESTRICTED EXHAUST OF ENGINE CAUSING PARTIAL POWER LOSS. 1L71 3O3 O 2A13 E286 5 NP4EA 20081229 GL 2008 12 29 CA081106006 120081105G3220 ARM DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA NLG WHEEL FORK CRACKED W K NONE O OTHER ININSP/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 ARMS ARE CRACKED THRU THE LOWER PORTION AND A .25 INCH CRACK HAS STARTED ON THE UPPER SIDE OF THE ARMS. 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20081229 EA 2008 12 29 CA081106007 120081103G2440671GA01Y00 POWER UNIT CNDAIRCL600 CL600* 1900302EA GE CF34 CF348C5 30050NE APU BURNED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 CA (CAN) NOT ACCEPTING AC EXTERNAL OR APU GEN AC. MX DETECT A BURNED CONTACTOR. CURRENTLY ACFT EXTERNAL AVAILABLE LIGHT IS ON. ACFT ONLY MAINTAINS POWER FOR 3 SECONDS, AND KICKS OFF. MFG HAS ISSUED A CONCESSION SL STATING NO OBJECTION TO FERRY PROVIDED THE FOLLOWING MTC PROCEDURES BE ACCOMPLISHED. DISCONNECT CONNECTORS K119-S4 AND K119-S3 2. CAP AND STOW CONNECTORS 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. 2L72 4F4 FRTA21EA E00063EN 20081222 NM 2008 12 22 CA081107001 120081104G6322B1741 MOUNT ROBSINR22 R22BETAII 7640110NM FAN WHEEL ASSY CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 162 (CAN) AT REINSTALLATION OF FANWHEEL ASSEMBLY, FOUND TAPERED MOUNTING FLANGE COMPLETELY CRACKED LONGITUDINALLY. UNIT SENT TO MANUFACTURER FOR WARRANTY EXCHANGE. 1G71 3O H10WE 20081222 WP 2008 12 22 CA081107002 120081104G5340C8303 ANGLE ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ELT MOUNT SHEARED W K NONE O OTHER ININSP/MAINT 1 CA 2197 (CAN) THE ANGLE USED AS PART OF ELT INSTALLATION WAS FOUND SHEARED DURING 2200 HR OVERHAUL TEARDOWN. 1G71 3O3 O H11NM 1E4 20081229 CE 2008 12 29 CA081107003 120081103G5347MC07106582 SEAT TRACK CESSNA182 182J 2072722CE CONT O470 O470R 17026SO LT PILOTS/LTPAS CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2250 (CAN) 3 CRACKS LT PAS RAIL, 1 CRACK LT PILOTS RAIL, SEAT RAILS SOME WEAR, WEAR WITHIN LIMITS. 1H71 3O3 ONT3A13 E273 20081222 NE 2008 12 22 CA081107004 220081026G7414106006169 MAGNETO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE INTERMITTENT W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) MAGNETO INTERMITTENT. 1G71 3O3 O H11NM 1E4 20081222 NE 2008 12 22 CA081107005 220081026G74141060064620 MAGNETO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE INTERMITTENT W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) MAGNETO INTERMITTENT. 1G71 3O3 O H11NM 1E4 20081222 WP 2008 12 22 CA081107006 120081029G6310C0511 ACTUATOR ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA CLUTCH MALFUNCTIONED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) CLUTCH ACTUATOR REMOVED DUE TO FAULTY SWITCHES. 1G71 3O3 O H11NM E295 20081229 GL 2008 12 29 CA081107007 220081030G732323076061 DRIVE SHAFT BELL 206 206B1 1181503SW ALLSN 250C 250C20B 03013GL TURBINE GOVERNORFAILED W K NONE O OTHER ININSP/MAINT 1 CA 2021 2021 (CAN) DURING REMOVAL OF THE GOVERNOR FOR SCHEDULED OVERHAUL, AT REMOVAL FROM ENGINE GEARBOX, THE CLIP THAT RETAINS THE DRIVEGEAR ON THE PT SHAFT WAS NOT LOCATED IN THE GROOVE ON THE SHAFT, AND THE WASHERS THAT ARE RETAINED BY THE CLIP AND SET AGAINST THE DRIVE GEAR, WERE FOUND SITTING IN THE MALE SPLINE OF THE GEARBOX DRIVE. IT APPEARS AS THOUGH THE END OF THE DRIVESHAFT WAS WORN DOWN TO ALLOW THE CIRCLIP TO BECOME DISLODGED FROM THE GROOVE AND WORK IT`S WAY OFF THE SHAFT, HOWEVER THE DAMAGE TO THE SHAFT COULD HAVE BEEN DUE TO THE DISLODGED WASHERS SITTING IN THE DRIVE SPLINE. THE ONLY ITEM FOUND RETAINING THE DRIVEGEAR WAS THE SPRING ON THE BACK SIDE OF IT. THE ENGINEER INSPECTED THE GEARBOX DRIVE BUT WAS UNAB1G71 3U3 U H2SW E4CE 20081229 EU 2008 12 29 CA081107008 120081104G6220117775P BALL JOINT SNIAS 350 AS350* EU LYC LTS101LTS101* NE STARFLEX DEFECTIVE W O OTHER O OTHER NRNOT 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 IT WAS MISALIGNED FROM ITS ORIGINAL POSITION. 1G71 3U3 U H9EU E5NE 20081222 2008 12 22 CA081110001 420081101G2562C362042702 BATTERY DHAV DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ULB INCORRECT W K NONE WL INADEQUATE Q C NO TEST ININSP/MAINT 1 CA (CAN) WRONG BATTERY INSTALLED IN UNIT. CORRECT BATTERY INSTALLED INTO ULB. REF WO NR 214939 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081222 CE 2008 12 22 CA081110002 120081105G32601003810061 SWITCH BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA NLG INTERMITTENT W L ABORTED APPROACH N FALSE WARNING APAPPROACH 1 CA (CAN) AFTER PILOT SELECTED GEAR DOWN, THERE WAS NO INDICATION THE NOSE GEAR WAS DOWN AND LOCKED, ACFT DIVERTED BACK TO MX BASE. ON ROUTE NOSE GEAR INDICATION CAME ON. ACFT LANDED WITHOUT INCIDENT. MX REPLACED NOSE GEAR DOWN LOCK INDICATOR SWITCH AND RETURNED TO SERVICE. 1L72 3T4 T A14CE E4EA 20081229 GL 2008 12 29 CA081110003 120081106G5311 SPAR DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO FUSELAGE DELAMINATED W K NONE O OTHER ININSP/MAINT 1 CA 5972 (CAN) DURING THE 6000 HOUR INSP DELAMINATIONS AND CRACKS WERE DISCOVERED ON THE SPAR BRIDGE. THE DELAMINATIONS AND CRACKS WERE FOUND ON THE RT SIDE ON THE AFT UPPER CORNER AT THE FILLET FROM BRIDGE TO SKIN INSIDE OF THE FUESLAGE AS VIEWED FROM 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. 1L71 3O3 ONTTA4CH E7SO 20081222 EA 2008 12 22 CA081110004 120081109G5751 CONTROL CABLE DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE AILERONS DISLODGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) RT WING FWD AILERON CONTROL CABLE FOUND SITTING BEHIND THE AILERON INPUT ROD QUADRANT GUARD. CABLE MOVED OUT OF ITS LOCATION WITH SLIGHT FINGER ACTION. CABLE HAS LIGHT RUBBING MARK BUT ALUMINUM QUADRANT GUARD FOUND BADLY GROOVED. WINGS CONTROL CABLE TENSION TOOK ON BOTH SIDE. LT SIDE MEASURED AT 30 LBS AND RT SIDE AT 20 LBS. RIGGING TENSION IS BETWEEN 55 AND 65 LBS AT 20 DEGREES CELSIUS. TENSION TOOK WITH CABLE MISROUTED AND AT PROPER PLACE, NO SIGNIFICANT TENSION DIFFERENCE AT 2-3 LBS. LT SIDE CABLE SECTION INSPECTED AT SAME LOCATION, CABLE FOUND ROUTED PROPERLY. 2H72 4T4 TRTA13NM E20NE 20081229 GL 2008 12 29 CA081110005 120081109G3220203220080 FORK DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO NOSE GEAR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1541 (CAN) ON PREFLIGHT OF ACFT, PILOT DISCOVERED CRACKS IN NOSE WHEEL FORKS APPROXIMENTLY 1 INCH FROM AXLE AT RADUS OF MACHINING (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 BEEN REPORTED. ACFT INSPECTED, NO OTHER DAMAGE DETECTED. MFG HAS ASKED FOR PARTS TO BE RETURNED FOR ENGINEERING EVALUATI1L71 3O3 ONTTA4CH E7SO 20081222 WP 2008 12 22 CA081110006 120081030G2432B4151 RELAY ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA BATTERY FAILED W O OTHER H ELECT. POWER LOSS-50 PC TXTAXI/GRND HDL 1 CA 386 (CAN) BATTERY WOULD NOT COME ONLINE ALTHOUGH FULL BATTERY VOLTAGE WAS OBSERVED AT BATTERY CONNECTIONS. BATTERY RELAY WAS REPLACED AND ACFT RETURNED TO SERVICE. 1G71 3O3 O H11NM E295 20081222 NM 2008 12 22 CA081110007 120081110G531087140011001 STRUCTURE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE FUSELAGE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 51173 (CAN) BIRD STRIKE JUST UNDER NOSE AREA. FOUND NR 2 LOWER COWL WITH INTERNAL CONE DAMAGE, LOWER COWL REMOVED. ENGINE BOROSCOPED WITH MINIMAL DEBRIS FOUND INSIDE ENGINE. NO DAMAGE NOTED NO DEBRIS FOUND ON LP COMPRESSOR. AIRFRAME INSPECTION 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081229 EA 2008 12 29 CA081111001 120081107G21508084402 BYPASS VALVE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE NR 1 ACM STUCK W O OTHER BGMSMOKE/FUMES/ODORS/SPARKS MULTIPLE FAILURE OVER TEMP TXTAXI/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 BYPASS VALVE STUCK IN THE FULL HOT POSITION. NR 1 ACM WAS ALSO FOUND SEIZED (P/N 782790-15, S/N 930930. TSN 28517 HOURS, CYCLES 14277, TSO 878735). IN ADDITION COMPRESSOR OUTLET OVERTEMP SWITCHES (P/N 750659-16. RATED TO 415°F) WERE FOUND INSTALLED 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 ACF2L72 4F4 FRTA21EA E15NE 20081230 EA 2008 12 30 CA081111002 120081028G2612 FIRE WARNING CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE ILLUMINATED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA EXPERIENCED AN EMERGENCY EVACUATION A/P ON TAXIWAY (M), DUE SMALL FIRE EMITTING FROM ENG WHILE TAXIING. LOCAL ARRF RESPONDED, 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 DETERMINE IF THERE WAS FLAME AS WELL AS SMOKE, ASSUMED FIRE REPORTED RESTRICTED TO ONE OR BOTH ENG JETPIPES. REPORT MENTIONS "LT ENGINE FLAMES/FIRE". 2L72 4F4 FRTA21EA E15NE 20081222 NM 2008 12 22 CA081111003 120081107G56108SC0043014 WINDSHIELD DHAV DHC8 DHC8106 2809020NM PWA PW121 PW121 52124NE HAMSTD14SF 14SF7 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 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 WINDSHIELD. NO CAUSE AS TO THE FAILURE COULD BE DETERMINED, OTHER THAN IT APPEARS TO HAVE ORIGINATED AT THE EDGE OF THE WINDOW AT A HEATING ELEMENT. THE TOTAL TIME ON THIS WINDSHIELD COULD NOT BE DETERMINED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081222 EA 2008 12 22 CA081111004 120081110G2750 CONTROL UNIT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE TE FLAPS MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 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. 2L72 4F4 FRTA21EA E15NE 20081229 NM 2008 12 29 CA081111005 120081104G3230483003 SELECTOR VALVE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU MLG SHORTED W O OTHER J WARNING INDICATION CLCLIMB 1 CA (CAN) CREW REPORTED A NOSE STEERING CAUTION ON TAKEOFF. UPON LANDING, ALL 3 GEARS SHOW RED WITH GEAR DOWN SELECTION. ALTERNATE EXTENSION USED IAW QRH. ALL GREEN WITH ALT EXTENSION. FAULT CODES HAVE BEEN RETRIEVED AND ENTERED INTO THERE COMPUTER SYS. MX FOUND A SHORT TO GROUND IN THE UP SOLENOID OF THE LANDING GEAR SELECTOR VALVE. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081229 EA 2008 12 29 CA081111006 120081020G29169604501 RESERVOIR CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C5B1 30052NE HYD SYSTEM LEAKING W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) NR3 HYD SYS LOW PRESSURE CAUTION MESSAGE DURING CLIMB. INBD SPOILERS CAUTION MESSAGE ALSO PRESENT DUE TO HYD LOW PRESSURE. 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 RETURNED 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". 2L72 4F4 FRTA21EA E00063EN 20081229 NM 2008 12 29 CA081112001 120081110G3260401020101 PROXIMITY SENSOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU LT MLG UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 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 CONFIRMED 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. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081229 NM 2008 12 29 CA081112002 120080529G571485730800002 SHROUD BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA WING BOX MISMANUFACTURED W O OTHER O OTHER CRCRUISE 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 DISCREPANCY 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 REPAIR WAS MADE IAW WDM 20-16-00. A SMS/SRS WAS RAISED. 2H72 4T4 TRTA13NM E00062EN 20081229 EU 2008 12 29 CA081112003 120081030G75009550170290 PRESSURE SWITCH UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE ENGINE FAILED W E ENGINE SHUTDOWN XJ ENGINE FLAMEOUT WARNING INDICATION LDLANDING 1 CA AFTER A LANDING AND COOLDOWN THE PILOT PRESSED THE START/DETENT SWITCH TO MOVE THE TWIST GRIP TO CUTOFF. THE ENGINE IMMEDIATELY FLAMED OUT WHEN THE SWITCH WAS DEPRESSED (TWIST GRIP WAS NOT TURNED). THEN ATTEMPTED TO RECREATE THIS PROBLEM AND IT HAPPENED AT ALL ENGINE SPEEDS. AFTER TROUBLESHOOTING IT WAS DETERMINED THAT THE P3 PRESSURE SWITCH WAS THE PROBLEM. 1G72 3U3 UNCR0001RD E34NE 20081229 GL 2008 12 29 CA081112004 120081110G5755GT41501009 SPOILER SYS BOMBDRBD700 BD7001A10 1390006GL RROYCEBR700 BR700710A22009500NE MALFUNCTIONED W A UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF AND DURING CLIMB, A LATERAL CONTROL MOVEMENT TO THE LT WAS NOTICED . ONE SPOILERON DEPLOYED ON THE LT WING (2 PAIR OF MULTI-FUNCTION SPOILER (MFS) IAW WING ON THIS ACFT). THE LT NR 2 MFS WAS AMBER LINE ON THE FLIGHT CONTROL SYNOPTIC PAGE. SEVERAL EXTRACT AND RETRACT ACTIONS ON THE SPOILERS SYS PERFOMED, WITHOUT SUCCESS AND AILERON TRIM WAS ADJUSTED TO CORRECT THE ACFT LEVELING. CREW DECIDED TO ABORT THE FLIGHT AND LAND TO THE AIRPORT DEPARTURE . AFTER LANDING ,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) 2L72 4F4 FRTT00003NYE00061EN 20081229 NM 2008 12 29 CA081112005 120081107G2697FRF6E12S3S CONNECTOR BOEING727 727247 138408FNM PWA JT8 JT8D15A 52051NE FIRE WARNING SYSDAMAGED W F ACTIVATE FIRE EXT. N FALSE WARNING CLCLIMB 1 CA (CAN) AT APPROX 700 FT, AGL T/O YHZ FIRE WARNING LIGHTS ON GLARE SHIELD WERE DIMMLY ILLUMINATED. NO AURAL WARNING. APU FIRE HANDLE ILLUMINATED. SWITCH PULLED AND BOTTLE DISCHARED. ACFT RETURNED TO DEPARTURE. RECTIFICATION AFTER TROUBLESHOOTING FOUND APU FIRE SENSOR/RESPONDER CONNECTOR D1428 SEVERELY CORRODED. INTERIOR OF CONNECTOR FOUND PACKED WITH GREENISH REDIDUE. BOTH ENDS OF CONNECTOR (SOCKETS AND PINS) CLEANED AND INSPECTED. APU FIRE DETECTION SYS TESTED IAW AMM 26-15-00 FOLLOWUP: REF: WRI 26-11/3077 APU FIRE SENSOR/RESPONDER CONNECTOR D1428 TO BE REPLACE. FOUND CONNECTOR WEATHER GASKET DAMMAGED CAUSING CORRROSION IN SOCKETS. 2L73 4F4 F A3WE E2EA 20081222 SO 2008 12 22 CA081112006 120081106G324540140 TUBE PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA MLG TIRE FLAT W O OTHER O OTHER TXTAXI/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 ACTUAL CAUSE OF THE PROBLEM. 1L72 3O3 O A20SO E14EA 20081222 NE 2008 12 22 CA081112007 220081031G7200 ENGINE PIAGIOP180 P180 6960204EU PWA PT6 PT6A66 52043NE MAKING METAL W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CA (CAN) DURING FLIGHT, THE ENGINE LOST TORQUE AND OIL PRESSURE. THE PILOT SHUT IT DOWN AND PERFORMED A SINGLE ENGINE LANDING. POST FLIGHT INSPECTION FOUND THE PROPELLER SEIZED AND METAL DEBRIS IN THE EXHAUST. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1H72 3O4 TRTA59EU E26NE 20081229 CE 2008 12 29 CA081112008 120081112G3210130909B19 BOLT BEECH BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE SUPPORT BROKEN W K NONE O OTHER ININSP/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 BOLT SHANK AND CAPTURE NUT. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20081229 EA 2008 12 29 CA081112009 220081031G7200 ENGINE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA NR 2 FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE AT FL180, THE CREW FELT A STRONG JOLT AND VIBRATIONS THROUGH THE AIRFRAME. A QUICK REVIEW OF THE GAGES SHOWED A POWER LOSS ON NR 2 ENG. THE ENG WAS SECURED AND THE CREW PERFORMED A SINGLE ENGINE LANDING. GROUND INSP FOUND 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 INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4T4 TRTA24CE E4EA 20081229 NE 2008 12 29 CA081112010 220081104G7532 BLEED VALVE PWA 305 PW305B 52128NE ENGINE MALFUNCTIONED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION LDLANDING 1 CA (CAN) DURING LANDING, THE ENGINE FLAMED OUT. RE-START ATTEMPT WAS UNSUCCESSFUL. TROUBLESHOOTING LED TO THE REPLACEMENT OF 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 120081031G2421 GENERATOR DOUG DC3 DC3C 3021457WP PWA PT6 PT6A67R 52043NE HARTZLHCB5M HCB5MA3 GL NR 2 INOPERATIVE W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 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 FORWARDED FOR INVESTIGATION AND REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4R4 T A669 E26NE 6 CP44GL 20081229 EU 2008 12 29 CA081112012 120081111G32305322012289 DRAG LINK PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG BROKEN W K NONE O OTHER ININSP/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 GEAR AND GEAR BAY AND FOUND NOTHING UNUSUAL. THE DESISON WAS MADE TO RETURN TO DEPARTURE WITH THE GEAR EXTENDED. MX WAS THERE TO MEET THE ACFT WHEN IT RETURNED. THE ACFT WAS HANGERED AND PLACED ON JACKS. MX THEN DID A GEAR SWING AND THE NOSE1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081229 2008 12 29 CA081113001 420081113G34600710159803 CONTROLLER PILATSPC12 PC1247 7090552EU PWA PT6 PT6A67 52043NE MFD FAILED W K NONE O OTHER ININSP/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 CURSOR MOVEMENT ON THE FLIGHT SCREENS AND DOES NOT ALLOW FLIGHT CREWS TO ENTER OR MODIFY ROUTING IN FLIGHT. THE REPLACEMENT UNIT CLEARED PROBLEM FOR NOW. HAVE BEEN TOLD MFG IS LOOKING INTO THE PROBLEM AS WE ARE NOT THE ONLY CUSTOMER HAVING THIS ISSUE. 1L71 4T4 TRTA78EU E26NE 20081229 2008 12 29 CA081113002 220081113G7497 WIRE MAGNETO CHAFED W K NONE O OTHER ININSP/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 220081022G7414K3822 DISTRIBUTOR GEAR MAGNETO LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DISTRIBUTOR FINGER LOOSE ON GEAR ASSY. 20081229 NM 2008 12 29 CA081113004 120081112G7500ZZ84M46P01 DUCT EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE BLEED AIR SYS SPLIT W K NONE O OTHER ININSP/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 SPLIT SEAM HAS CAUSED DAMAGE TO THE THRUST REVERSER HEAT SHIELD. T/R FIRE BLANKET PN 104M1031-22, SN6011203-013 THIS HAS ALSO OCCURRED ON ACFT FIN 317 C-FHKI SN 190-0052 AND FIN 342.C-FNAP SN 190-00142. 2L72 4F4 FRTA57NM E00070EN 20081229 EA 2008 12 29 CA081113005 120081112G27518004301 DETECTION SYS CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE FLAP SYSTEM FAILED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 18700 (CAN) FLAP FAIL, SELECTED 20, FAILED AT 8 DEGREES. ON APPROACH, CREW UNAWARE OF OAT DUE TO WORK LOAD. FLAP SKEW DETECTION UNIT REPLACED IAW AMM 27-51-15, PG 401. FLAPS CHECKED SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20081230 SO 2008 12 30 CA081113006 120081107G324606104700 WHEEL PIPER PA34 PA34200 7103405SO LYC O360 IO360C1E6 41514EA HARTZLHCC2Y HCC2YK2 GL MLG CRACKED W K NONE O OTHER ININSP/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 FINDING IS RATHER UNUSUAL AT THE AMO. NO HARD OR UNUSUAL LANDINGS WERE REPORTED. THE WHEEL HALF WAS REPLACED, AND THE ACFT RETURNED TO SERVICE. 1L72 3O3 O A7SO 1E10 5 CP920 20081230 SW 2008 12 30 CA081113007 120081104G6420407012108101 BUSHING BELL 407 407 1182206SW PITCH HORN ASSY DEFORMED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WASHER BETWEEN THE T/R PITCH HORN AND PITCH LINK FOUND DEFORMED. 1G71 3U O H2SW 20081230 SW 2008 12 30 CA081113008 120081016G6210206010200133 TAB BELL 206 206B 1181511SW ROTOR BLADE DEFORMED W O OTHER E VIBRATION/BUFFET CRCRUISE 1 CA 11 (CAN) LOUD BANG WAS NOTED WITHING 10 MINUTES OF FLIGHT. LEVEL OF VIBRATION DID NOT INCREASE. INSP AFTER LANDING FOUND THAT THE TRIM TAB WAS DEFORMED (UPPER SIDE WAS BENT UPWARD AND LOWER SIDE BENT DOWNWARD). PEEL-PLY HAS BEEN LEFT ON THE TRIM TAB. 1G71 3U H2SW 20081230 NM 2008 12 30 CA081114001 120081113G3297464605 WIRE HARNESS BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU PROXIMITY SWITCHSHORTED W A UNSCHED LANDING J WARNING INDICATION APAPPROACH 1 CA (CAN) CREW SELECTED GEAR DOWN AND GOT 3 GREENS AND LT MLG DOOR AMBER LIGHT. ALTERNATE EXTENSION C/O AND CREW OBSERVED ALTERNATE INDICATION SHOWED LT MLG (UNSAFE). CREW DECLARED EMERGENCY AND LANDED. PAX DEPLANED ON RUNWAY AND AFTER GEARS WERE 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. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081230 2008 12 30 CA081114002 420081111G34134067644901 INDICATOR DHAV DHC8 DHC8106 2809020NM PWA PW121 PW121 52124NE HAMSTD14SF 14SF7 NE IVSI FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CLCLIMB 1 CA (CAN) AFTER TAKOFF, CAPTAINS SIDE IVSI FAILED, ACFT RETURNED TO AIRPORT - IVSI REPLACED AND FUNCTION CHECK SERVICEABLE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 GL 2008 12 30 CA081114003 120081112G27202227271300 PEDAL DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3313 (CAN) DURING ROUTINE INSP THE RUDDER PEDAL WAS FOUND CRACKED. 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20081230 NE 2008 12 30 CA081114004 120081103G6320S613522032001 GEARBOX SKRSKYS61 S61N 8142104NE MAIN ROTOR MAKING METAL W K NONE O OTHER ININSP/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: S6135-22032-001 THE CAUSE OF THE METAL CONTAMINATION WAS FROM THE UPPER BRG SUPPORT NUT. 2G72 4U 1H15 20081230 NE 2008 12 30 CA081114005 220081104G72308934825 IMPELLER SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 29073NE COMPRESSOR CRACKED W K NONE O OTHER ININSP/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 IMPELLER 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. 2L72 4T4 TRTA8SW E4WE 20081230 2008 12 30 CA081114006 220081113G7200SB3208A1 BEARING ENGINE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RECEIVED NEW BEARING FROM WHS 290 WITH CORROSION ON BEARING JOURNAL AND ROLLERS. CURE DATE ON PACKAGE IS 0206, BEARING 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 120081114G571085720013006 STRUCTURE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF* NE RT WING LE DAMAGED W O OTHER C F.O.D. LDLANDING 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 EA 2008 12 30 CA081114008 120081113G5714 FASTENER DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL WING BOX LOOSE W K NONE O OTHER ININSP/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 TOTAL OF 160 RIVETS NEEDING REPLACEMENT. THE RIVETS WERE REPLACED AND THE ACFT RETURNED TO SERVICE. 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20081230 NM 2008 12 30 CA081114009 120081112G5310 STRUCTURE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE FUSELAGE DAMAGED W O OTHER C F.O.D. DEDESCENT 1 CA (CAN) FLT ENCOUNTERED MULTIPLE BIRD STRIKES AT 4000 FT, DURING AN APPROACH FOR LANDING INTO AIRPORT. CREW CONTINUED ON DESCENT 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 BEING JUST ABOVE LT ENGINE INTAKE. GOOSE HAD SUBSEQUENTLY ENTERED INTAKE AND EXITED THROUGH THE OPEN ENG INTAKE BYPASS DOOR THAT WAS DAMAGED AS WELL. ACFT INSPECTED IN AIRPORT. RADOME REPLACED AND ACFT WAS THEN FERRIED TO MX BASE, UNDER A FERRY FLT PERMIT. RADOME REMOVED AGAIN TO FACILITATE REPAIRS TO BULKHEAD ON NOSE BEHIND RADOME. WEATHER RADAR ALSO REPLACE2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 2008 12 30 CA081115001 420081112G2312G340ENI CONTROL HEAD CVAC 340 340CVAC 242270AWP ALLSN 501D 501D13D 03004GL ALLSN A6441 A6441FN606 GL COCKPIT CONTAMINATED W O OTHER H ELECT. POWER LOSS-50 PC APAPPROACH 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. 2L72 4R4 T 6A6 E282 6 CP898 20081230 EA 2008 12 30 CA081117002 120081114G2750865D1007 DRIVE SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED APAPPROACH 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. 2L72 4F4 FRTA21EA E15NE 20081230 SW 2008 12 30 CA081117003 120081113G801231057463 IGNITION SWITCH SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE3311 01514WP MCAULY4HFR344HFR34C652 NE COCKPIT CRACKED W A UNSCHED LANDING BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CLCLIMB 1 CA (CAN) ACFT DEPARTED AIRPORT AND CREW NOTICED SMOKE IN THE CABIN. THE CREW TURNED THE TEMP CONTROLLER OFF - THE BLEEDS WERE 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 INCIDENT. 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. 2L72 4T3 TRTA8SW E3WE 6 C3PNE 20081230 EU 2008 12 30 CA081117004 120081114G6700ASNA013735E2 BEARING RACE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE INNER R ACE CRACKED W K NONE O OTHER ININSP/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 ASSY. THE CRACKS ORIGNALLY STARTED FROM THE RIVET HOLES. THE BEARING ASSY/SUPPORT ATTACH THE INNER RACE OF BEARING BY 4 RIVETS 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. 1G71 3U3 U H9EU E19EU 20081230 2008 12 30 CA081117005 420081113G2210103791101 CIRCUIT BOARD BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE HARTZLHCE4N HCE4N3 NE AUTOPILOT INTERMITTENT W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CLCLIMB 1 CA 428 (CAN) ACFT IN NORMAL CLIMB CONFIGURATION WITH FCS DISPLAYING CLIMB (GREEN) AND ALT ARM (WHITE.) THE VERTICAL MODE DISPLAY 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. INTERNAL PRINTED CIRCUIT BOARD IDENTIFIED AS THE PROBLEM SOURCE AND SUBSEQUENTLY REPLACED. 1L72 4T4 T A24CE E4EA 5 CP10NE 20081230 EA 2008 12 30 CA081117006 120080926G7160CT2EC10221 YOKE DHAV DHC2 DHC2MK3 2800107EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL INTAKE BROKEN W K NONE O OTHER ININSP/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. 1H71 3T4 T A806 E4EA 6 CP15EA 20081230 SO 2008 12 30 CA081117007 220081115G8530 CYLINDER CONT O300 O300C 17022SO NR 3 CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) NR 3 CYLINDER ASSY WAS FOUND CRACKED BETWEEN THE CYLINDER HEAD AND THE BARREL, APPROX .7500 AROUND THE CICUMFERENCE OF THE ASSY. THIS RESULTED IN LOSS OF COMPRESSION AND ENGINE VIBRATION. 3 O E253 20081230 CE 2008 12 30 CA081118001 120081115G3040MS24166DI RELAY BEECH BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL WINDSHIELD HEAT UNSERVICEABLE W H DEACTIVATE SYST/CIRCUITS MJ OVER TEMP WARNING INDICATION NRNOT REPORTED 1 CA (CAN) CREW DEFECT PILOT WINDSHIELD HEAT NOT WORKING, TROUBLESHOOT TO LOW HEAT RELAY, TERMINAL A2 MELTED OFF THE RELAY ASSY, DAMAGING WIRES ATTACHED TO THE TERMINAL APPROX 3 INCHES BACK THE WIRE COVER MELTED OFF. RELAY WAS REPLACED AND SYS OPERATES PROPERLY. 2L72 4T4 T A24CE E4EA 6 CP56GL 20081230 SW 2008 12 30 CA081118003 120081103G7603701981 LOCK TAB AIRTRC AIRTRCAT500 AT502B 0390307SW PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL POWER LEVER CRACKED W O OTHER F FLT CONT AFFECTED TXTAXI/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. 1L71 3T4 TNCA17SW E4EA 6 CP15EA 20081230 NM 2008 12 30 CA081118004 120081116G291082970009325 LINE DHAV DHC8 DHC8201 2809001NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE NR 2 HYD SYS CRACKED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION APAPPROACH 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 DRIVEN 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 GL 2008 12 30 CA081118005 120081117G2720 TUBE DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA RUDDER PEDAL WORN W K NONE O OTHER ININSP/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. 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20081230 NM 2008 12 30 CA081118006 120081114G322082253 TUBE MESSIER 8200103 DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE NLG BROKEN W O OTHER O OTHER LDLANDING 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 FLYBY 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 WAS 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 CE 2008 12 30 CA081118008 120081115G33101015245001 PANEL BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL COCKPIT SMOKE W O OTHER B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA 1488214882 (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 PANEL AT THE CO-PILOTS CLOCK WAS AT FAULT. THE LIGHTING WAS DISABLED AND DEFERRED IAW THE MEL UNTIL REPLACEMENT PARTS ARRIVE. THE AREA WAS INSPECTED AND ADJACENT SYS TESTED WITH NO ADDITIONAL FAULTS NOTED AND THE ACFT RELEASED. 1L72 4T4 T A24CE E4EA 6 CP15EA 20081230 SW 2008 12 30 CA081118010 120081118G71205082119 MOUNT AIRTRCAT602 AT602 0390309SW PWA PT6 PT6A65AG 52043NE HARTZLHCB5M HCB5MP3 GL ENGINE CRACKED W K NONE O OTHER ININSP/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 CRACK 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. 1L71 3T4 TNCA19SW E4EA 6 CP44GL 20081230 NM 2008 12 30 CA081119001 120081119G5330 SKIN EMB ERJ170ERJ170100SE 3260406NM FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACKS WERE SUSPECTED AFTER GVI AND CONFIRM BY NDT RADIATING FROM ONE FASTENER HOLE IN LT FUSELAGE SKIN PANEL AT FRAME 94 STR 03 AND 04 LT AND SAME AT FRAME 94 STR 03 AND 04 RT. 2L72 4F RTA56NM 20081230 EA 2008 12 30 CA081119002 120081118G2751800440304 PROXIMITY SENSOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS FAILED W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION APAPPROACH 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 FURTHER INCIDENT AND STOPPED ON RUNWAY FOR FIRE CREWS TO DO A WALK AROUND AND THEN TAXIED TO THE GATE. MX TROUBLESHOOTING IAW 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. 2L72 4F4 FRTA21EA E15NE 20081230 NE 2008 12 30 CA081119003 220081118G72610292507350 BEARING SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1B 6OO30NE ENGINE BLOCKED W K NONE O OTHER ININSP/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. 1G71 3U3 U H9EU E19EU 20081230 NM 2008 12 30 CA081119004 120081118G2750MS391130Z MOTOR BOEING727 727225 1384077NM PWA JT8 JT8D9A 52048NE TE FLAPS FAILED W O OTHER K FLUID LOSS CRCRUISE 1 CA (CAN) ENROUTE, SYS A HYD QTY DROPPED TO ZERO. MX FOUND OTBD FLAP HYD MOTOR FAILED. MOTOR REPLACED AND SYS CHECKED SERVICABLE. 2L73 4F4 F A3WE E2EA 20081230 EU 2008 12 30 CA081120001 120081119G2560SL12 BUCKLE GROB GROB G115 G115C 1660303EU LYC O320 O320D1A 41508EA SEAT BELT ASSY UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA 437 (CAN) BUCKLE WOULD NOT RELEASE. 1L71 3O3 ONTA57EU E274 20081230 CE 2008 12 30 CA081120002 120081118G2840 MONITOR BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA MCAULY4HFR344HFR34C762 NE FUEL QTY FAULTY W K NONE O OTHER ININSP/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 SERVICEABLE UNIT FROM AN OTHER ACFT (FLTS) TO CONFIRMED TROUBLESHOOTING. IT TAKES 3 DIFFERENT UNIT TO FINALLY FIXED THE PROBLEM. 1L72 3T4 T A14CE E4EA 6 C3PNE 20081230 NM 2008 12 30 CA081120003 120081107G3240900005831PR BRAKE SYS EMB ERJ170ERJ170200SU NIR NM GE CF34 CF348E5A1 30062NE MLG DISINTEGRATED W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) DURING PUSHBACK, GRND PERSONNEL REPORTED SMOKING BRAKES. FOUND NR3 BRAKE ROTORS HAD FAILED. REPLACED BOTH NR3 WHEEL AND BRAKE ASSY IAW AMM 32-49-05 AND 32-49-11. S/N OF THE BRAKE IS JAN05-0530. 2L72 4F4 FRTA56NM E00063EN 20081230 SW 2008 12 30 CA081120004 120081116G6220K974004107 MOUNT KAMAN K1200 K1200 05625F6SW LYC T53 T5317A 41549NE M/R HEAD CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK DISCOVERED ON LT FWD STRUT MOUNT FITTING. 1G71 4F4 UNTTR7BO E17EA 20090102 NE 2009 1 2 CA081120005 220081106G7532BRH10211 BLEED VALVE BOEING717 717200 1383700NM RROYCEBR700 BR700715A130 NE ENGINE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) IT HAS BEEN REPORTED BY OPERATOR THAT BVV LEVER WAS NOT OPERATING PROPERLY. ENG WAS REMOVED IN UNSERVICEABLE CONDITION DUE TO BOOSTER BLEED VALVE MECHANISM MALFUNCTION. ENG IN RRC FOR REPAIR. DURING INITIAL INSP, IT WAS CONFIRMED THAT BOOSTER BLEED VALVE RING ASSY (ATA 72-38-19 01-400) WAS NOT OPERATING PROPERLY. STRIP WAS CARRIED OUT TO EXPOSE THE BOOSTER 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 BOOSTER BLEED VALVE RING ASSY (ATA 72-38-19 01-409) AT TOP DEAD CENTER POSITION (ACTUATING ROD POSITION). (6) REMAINING PINS 2L72 4F4 FTRA6WE E00061EN 20081230 EU 2008 12 30 CA081120006 120081119G6220350A37116200 STOP SNIAS 350 AS350B2 8680813EU LYC LTS101LTS101* NE MAIN ROTOR CRACKED W K NONE O OTHER ININSP/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 SECOND RADIUS FROM THE TOP, AND WERE NOT VISIBLE TO THE NAKED EYE. 1G71 3U3 U H9EU E5NE 20081230 EU 2008 12 30 CA081120007 120081119G6220350A37116200 STOP SNIAS SNIAS 350 AS350B1 8680811EU ROTOR SHAFT CRACKED W K NONE O OTHER ININSP/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 TECHNICAL PUBLICATIONS TO NDT THESE PARTS). CRACK NOTED IN THE SECOND RADIUS FROM THE TOP. 1G71 3U H9EU 20081230 2008 12 30 CA081121001 420081120G34207004544314 SYMBOL GENERATOR DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE NR 1 FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 30171458 (CAN) SHORTLY AFTER TAKEOFF, THE CAPT`S PRIMARY FLIGHT DISPLAYS WERE MALFUNCTIONING, CAPTS EADI AND EHSI ARE BLANKING OUT INTERMITTENTLY , CREW ELECTED TO RETURN TO ORIGINATING AIRPORT. MX REPLACED NR 1 SYMBOL GENERATOR AND ACFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 EA 2008 12 30 CA081121002 120081120G2750855D1009 CONTROL UNIT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE TE FLAPS FAILED W D RETURN TO BLOCK FJ FLT CONT AFFECTED WARNING INDICATION TXTAXI/GRND HDL 1 CA 2777027770 (CAN) DURING PUSH BACK FROM THE GATE, FLAP LEVER WAS MOVED TO 8 DEGREES BY THE FLIGHT CREW BUT THE FLAP DIDN`T EXTEND AND "FLAP FAIL" CAUTION MESSAGE APPEARED ON THE ENGINE INDICATION AND CREW ALERTING SYS (EICAS). THE ACFT WAS TOWED BACK TO 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. 2L72 4F4 FRTA21EA E15NE 20081230 NM 2008 12 30 CA081121003 120081119G21508209063 ACM BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU RIGHT ODOR W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 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 CAUTION LIGHT WENT OUT. WE THEN LANDED AND COMPLETED THE FLIGHT NORMALLY. ON-SITE LINE MX INVESTIGATION IDENTIFIED THE RT (CABIN) 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. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081230 EU 2008 12 30 CA081121004 120081121G5751 SEAL PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL LT AILERON SPLIT W K NONE O OTHER ININSP/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 THE LT AILERON WHICH ATTACHES BETWEEN THE WING AND THE AILERON BALANCE WEIGHT ATTACHMENT. WHEN THE MS35207-XXX SCREWS WERE 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. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20081230 CE 2008 12 30 CA081121005 120081119G243523080023A STARTER GEN LEAR 35 31A 5170531CE GARRTTTFE731TFE73123B WP NR 1 FAILED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA 235 (CAN) GENERATOR FELL OFF, INE AND A SLIGHT VIBRATION WAS FELT. 2L72 4F4 FRTA10CE E6WE 20081230 GL 2008 12 30 CA081121006 120081120G27202227271200 TUBE DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA RUDDER PEDAL WORN W K NONE O OTHER ININSP/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 ALONG THE SLIDE TUBE ASSY. CLOSER INSPECTION BY MAINT REVEALED THAT THE RT OTBD FWD RUDDER CABLE HAD WORN THROUGH THE S-TUBE THAT IS WELDED TO THE PEDAL ASSY. CABLE WAS EXPOSED THROUGH THE LOWER BEND OF THE S-TUBE TO A POINT WHERE IT WAS JAMMED IN ITS WEAR HOLE THUS RESRICTING THE SLIDE ACTION OF THE PEDAL ASSY. THE DEFECTIVE PARTS ARE BEING REMOVED FOR REPLACEMENT WITH NEW. 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20081230 GL 2008 12 30 CA081121007 120081107G29101005354226007 LINE BOMBDRBD100 BD1001A10 1390044GL HYDRAULIC SYS CHAFED W O OTHER K FLUID LOSS CRCRUISE 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. 2L72 4F RTT00005NY 20081230 GL 2008 12 30 CA081121009 120080711G29101005354226007 LINE BOMBDRBD100 BD1001A10 1390044GL HYDRAULIC SYS CHAFED W O OTHER KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 5162 (CAN) DURING CRUISE FLIGHT, THE AMBER (R HYD PRESS LOW) CAS MESSAGE ILLUMINATED. PILOT OBSERVED THE HYD SYNOPTIC PAGE AND 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 FAIRLEAD BLOCK. 2L72 4F RTT00005NY 20081230 2008 12 30 CA081121010 120081119G341120131421B STATIC LINE PITOT/STATIC SY UNBONDED W O OTHER O OTHER NRNOT 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 120081120G3230656021132 ACCESSORY UNIT BOEING727 727227 1384078NM PWA JT8 JT8D9A 52048NE MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) JUST AFTER TAKEOFF, THE CREW ATTEMPTED TO SELECT GEAR UP, THE GEAR HANDLE WOULD NOT GO PAST THE OFF POSITION. ACFT RETURNED TO WHERE MAINT REPLACED THE LANDING GEAR ACCY UNIT. A/C RETURNED TO SERVICE. 2L73 4F4 F A3WE E2EA 20081230 EU 2008 12 30 CA081121012 120081120G2913S40 COUPLING SLEEVE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE HYD PUMP WORN W K NONE O OTHER ININSP/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. 1G71 3U3 U H9EU E19EU 20081230 NM 2008 12 30 CA081122001 120080929G5312 BULKHEAD BOEING727 727225 1384077NM PWA JT8 JT8D9A 52048NE FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING WALK-AROUND INSP, FOUND BELTFRAME AT 9G BULKHEAD CRACKED BY LT CARGO CAN CUTOUT. TEMPORARY REPAIR CARRIED OUT. A/C FERRIED. PERMANENT REPAIR CARRIED OUT. ACFT RETURNED TO SERVICE. 2L73 4F4 F A3WE E2EA 20081230 EA 2008 12 30 CA081122002 120081117G2752852D10021 ACTUATOR CNDAIRCL600 CL6002B19 1900309EA TE FLAPS FAILED W O OTHER J WARNING INDICATION APAPPROACH 1 CA 2078 (CAN) FLAP FAIL IN APPROACH WHEN SELECTED FROM 0 DEGREE. FLAP FAILED AT 0 DEGREE. 2L72 4F RTA21EA 20081230 EA 2008 12 30 CA081122003 120081117G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) DECENDING THROUGHT 10,000 FT, FLT CREW REPORTED FLAP FAIL MSG WITH FLAPS AT 0 DEG, AIRSPEED WAS 250 KTS. QRH FOLLOWED 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. 2L72 4F RTA21EA 20081230 EA 2008 12 30 CA081122004 120081116G2742AV67023105 ACTUATOR CNDAIRCL600 CL6002C10 1390015EA HORIZONTAL STAB LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AV670-23105-003 (LT) AND -004 (RT) DURING ROUTINE MX ON THE HORIZONTAL STAB TRIM ACTUATOR (HSTA), LOOSE BOLTS (ITEMS 24 AND 35) WERE FOUND IN THE UPPER BOLT LOCATIONS OF THE RT AND LT HSTA UPPER ATTACHMENT FITTING ASSY ITEM 33). 2L72 4F RTA21EA 20081230 EA 2008 12 30 CA081122005 120081111G2120 UNKNOWN CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE SMOKE W C ABORTED TAKEOFF BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TOTAKEOFF 1 CA (CAN) "A08C0232: AS FLIGHT WAS ON THE TAKEOFF RUN, WHEN THE CREW RECEIVED A CAUTION MESSAGE FOR SMOKE IN THE LAVATORY. THE TAKEOFF WAS REJECTED AT 60 KTS AND ARFF WAS CALLED OUT. THE FLIGHT RETURNED TO THE APRON, PASSENGERS WERE DEPLANED, AND MX INSPECTED THE AIR CONDITIONING PACKS AND THE ACFT WAS RETURNED TO SERVICE. AFTER DE-ICING AGAIN, ANOTHER TAKEOFF WAS ATTEMPTED, BUT WAS REJECTED AT 100 KTS WHEN THE SMOKE IN THE LAVATORY CAUTION MESSAGE OCCURRED AGAIN. THE ACFT WAS INSPECTED AND FERRIED, WHERE MX IS CHANGING THE RT ENGINE (GE CF34-3B1). 2L72 4F4 FRTA21EA E15NE 20081230 EA 2008 12 30 CA081122006 120081110G5610NP13922001 WINDOW CNDAIRCL600 CL6002B19 1900309EA COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 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 INCH AT THE WINDOW EDGE. CALLED TO VERIFY THE CRACKED PLY. ACFT TO FERRY UNPRESSURIZED FOR REPAIRS". 2L72 4F RTA21EA 20081230 WP 2008 12 30 CA081124001 120081006G3246 BUNGEE FEDERAL DOUG DC3 DC3CS4C4G 3021460WP PWA PT6 PT6A67R 52043NE SKI MISMARKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) DURING AERIAL WORK WITH SKIS INSTALLED THE RT MAIN GEAR DID NOT EXTEND FULLY. WITH THE ASSISTANCE OF A BELLY MOUNTED CAMERA THE CAUSE WAS DETERMINED TO BE THE SKI FWD LIMIT CABLE ASSY. THE LANDING GEAR WAS CYCLED AND EXTENDED SUCCESSFULLY. 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 NOT ALLOWING THE LANDING GEAR TO EXTEND FULLY. THE PROPER LENGTH BUNGEE WOULD NOT ALLOW THE CABLES TO BE LOCATED IN THAT AREA. THE ORIGINALLY INSTALLED BUNGEE ASSEMBLIES WERE UNITS SUPPLIED BY THE ACFT STC HOLDER, WHO HAS BEEN NOTIFIED OF THE2L72 4R4 T A669 E26NE 20081230 EA 2008 12 30 CA081124002 120081123G2497D3899920MJ43SN CONNECTOR CNDAIRCL600 CL6002D24 1390016EA BURNED W O OTHER H ELECT. POWER LOSS-50 PC CRCRUISE 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 NOISE 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, AND 2G3 BRAKE PRESS IND FOUND TO BE POPPED. DUE TO ELECTRICAL FAILURE AND NO INDICATIONS OF BRAKE PRESSURE, EMERGENCY DECLARED AND EMERGENCY VEHICLES REQUESTED FOR LANDING. AFTER LDG, ACPC CB`S FOR HYD PUMP 1B, 2B, 3A POPPED. 2L72 4F RTA21EA 20081230 SW 2008 12 30 CA081124003 120081121G3260MS243314 SWITCH SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE MLG FAILED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) AFTER TAKEOFF CREW WAS UNABLE TO RETRACT THE ACFT LANDING GEAR. THE CREW ELECTED TO RETURN TO AIRPORT OF ORIGIN AND 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 FUNCTIONED CHECKED SERVICEABLE. TOTAL TIME ON THE SWITCH COULD NOT BE DETERMINED. 2L72 4T4 TRTA8SW E4WE 5 CP10NE 20081230 SW 2008 12 30 CA081124004 120081117G3260MS243314 SWITCH SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110U 29066NE HARTZLHCE4N HCE4N3 NE INTERNAL FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING AN ATTEMPTED ENGINE START THE CREW WAS UNABLE TO GET ENGINE ROTATION OR LIGHT OFF. MX INVESTIGATED AND DETERMINED THE MLG SAFETY MICROSWITCH WHICH CONTROLS THE AIR/GROUND PORTION OF THE ENGINE START CONTROL SYS TO BE INOPERATIVE. MX REPLACED THE SWITCH AND RETURNED THE ACFT TO SERVICE. 2L72 4T4 TRTA8SW E4WE 5 CP10NE 20081230 SW 2008 12 30 CA081124005 120081120G32601EN516 SWITCH SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE NLG FAILED W O OTHER N FALSE WARNING APAPPROACH 1 CA (CAN) THE CREW COULD NOT GET A NOSE GEAR DOWN AND LOCKED INDICATION AFTER SEVERAL DOZEN GEAR POSITION CYCLES OR WITH MANUAL GEAR EXTENSION. WITH THE LAST ATTEMPT IT ILLUMINATED WITH ELECTRICAL SELECTION. EMERGENCY SERVICES AT AIRPORT WERE ON STANDBY. THE ACFT LANDED AND MX DISCOVERED THAT ONE OR BOTH OF THE NOSE LANDING GEAR DOWNLOCK SWITCHES WAS INOPERATIVE. MX REPLACED BOTH SWITCHES AS A PRECAUTION AND GEAR FUNCTIONAL CHECKS COMPLETED. NO FURTHER PROBLEMS WITH THE LANDING GEAR SYS HAVE OCCURED. 2L72 4T4 TRTA8SW E4WE 5 CP10NE 20081230 SW 2008 12 30 CA081124006 120081121G32601EN516 SWITCH SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE NLG FAILED W O OTHER N FALSE WARNING APAPPROACH 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 GEAR 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 LANDING GEAR DOWNLOCK MICRO SWITCH. BOTH DOWNLOCK MICROSWITCHES WERE REPLACED AS A PRECAUTION AND THE LANDING GEAR FUNCTION TESTED. THERE HAS BEEN NO FURTHER RECURRANCE OF THIS ISSUE. 2L72 4T4 TRTA8SW E4WE 5 CP10NE 20081230 NM 2008 12 30 CA081124007 120081121G5751 SUPPORT BRACKET DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF* NE AILERONS CRACKED W K NONE O OTHER ININSP/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 INSPECT THE AFOREMENTIONED ASSEMBLIES ON THE DHC8-300 SERIES ACFT. REFERENCE IPC 27-12-00, FIGURE 10, PAGE 0, ITEM 130. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 NM 2008 12 30 CA081125001 120081125G2497 WIRE HARNESS BOEING757 75728A 1384976NM RROYCERB211 RB211535E43754555NE CHAFED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) IN FLIGHT CREW NOTICED SMOKE AND FLASHES ABOVE ROW 4DEF. MX FOUND WIRING HARNESS CHAFED BY CEILING PANEL RESULTING IN EXPOSED WIRES ARCHING. 2L72 4F4 FRTA2NM E12EU 20081230 NM 2008 12 30 CA081125002 120081125G2910DSC252A40272 FLEX LINE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE HYD SYSTEM BROKEN W O OTHER K FLUID LOSS TXTAXI/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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081230 NM 2008 12 30 CA081125003 120081118G561080260008 WINDSHIELD BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU COCKPIT FAILED W O OTHER O OTHER APAPPROACH 1 CA 568 (CAN) AT ABOUT 500 FT ON FINAL APPROACH TO THE AIRPORT THE RT WINDSHIELD SHATTERED. THE FLIGHT CREWS INITIAL REACTION WAS 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 WINDSHIELD IAW AMM TASKS 56-10-01-000-801, 56-10-01-400-801 AND 30-41-00-710-802. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20081230 SO 2008 12 30 CA081125004 220081112G8500IO360KB ENGINE CESSNA172 R172K 2072431CE CONT O360 IO360KB 17025SO MCAULY2A34C 2A34C203 GL MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 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. 1H71 3O3 O 3A17 E1CE 5 CP3EA 20081230 SW 2008 12 30 CA081125005 120081124G65001400191 WASHER BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL PITCH CHANGE CRACKED W K NONE O OTHER ININSP/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 OUTSIDE PERIMETER OF THE WASHER. THE WASHERS P/N 140-019-1 WERE REPLACED AND THE FIN RE-INSTALLED. IT IS NOT KNOWN IF THIS CONDITION IS DUE TO OVERTIGHTENING OF THE FASTENER, OR THE INCREASE IN TORQUE VALUE FOLLOWING ISSUANCE OF ASB 206-06-107. 1G71 3U3 U H2SW E4CE 20081230 NE 2008 12 30 CA081125006 220081111G7200 ENGINE CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE FLAMED OUT W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION LDLANDING 1 CA (CAN) DURING SHORT FINAL, UPON REDUCING THE POWER TO IDLE, THE ENGINE FLAMED OUT. THE EVENT OCCURRED AT AN ALTITUDE OF APPROX. 100 FEET AND THE CREW LANDED THE ACFT SINGLE ENGINE. NOV. 12 2008: ENGINE FLAME-OUT EVENT OCCURRED WHILE DEPLOYING 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. 2L72 4F4 FRTA22CE E25EA 20081230 NE 2008 12 30 CA081125007 220081104G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE VIBRATION W O OTHER ERJVIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 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 SMOKE WAS OBSERVED COMING OUT OF THE ENGINE. THE ENG WILL BE REMOVED AND FWD FOR INVESTIGATION. UPDATES WILL BE PROVIDED TO TC. 1H71 3T3 T A37CE E4EA 20081230 NE 2008 12 30 CA081125008 220081112G7200 ENGINE PWA PW120 PW127 NE NR 2 MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CLCLIMB 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. THE 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 220081017G7323 GOVERNOR AEROSPATR42 ATR42300 8680920EU PWA PW121 PW121 52124NE OVERSPEED LEAKING W E ENGINE SHUTDOWN J WARNING INDICATION CLCLIMB 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 BEFORE THE CREW ELECTED TO SHUT IT DOWN. THE PROP HOWEVER DID NOT FEATHER AND THE ACFT FLEW FOR 60 MINUTES WITH THE ENGINE 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 ESTABLIS2H72 4T4 TRTA53EU E20NE 20081230 NE 2008 12 30 CA081125010 220081113G7200 OIL SYSTEM BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE ENGINE LEAKING W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 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 INLET AND COMPRESSOR BLEED VALVE. WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4T4 T A24CE E4EA 20081230 2008 12 30 CA081125011 120081113G6100 SLEEVE PWA PT6 PT6A68 NE PROP TRANSFER DAMAGED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS APAPPROACH 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 SLEEVE REVEALED BLUING. THE ENGINE IS TO BE REMOVED AND REPLACED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 4 T E26NE 20081230 NE 2008 12 30 CA081125012 220081116G7200 ENGINE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE LEFT FAILED W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, WITH NO WARNING THE LT ENG SHUTDOWN ACCOMPANIED WITH A LOUD NOISE. THE FIRE WARNING FOLLOWED AND THE CREW DISCHARGED BOTH FIRE BOTTLES BEFORE DIVERTING THE FLIGHT WHERE A SINGLE ENGINE LANDING WAS ACCOMPLISHED. POST FLIGHT INSP REVEALED THAT THE PROPELLER WAS HARD TO ROTATE AND DEBRIS WERE FOUND IN THE ENG TAILPIPE. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA13NM E20NE 20081230 NE 2008 12 30 CA081125013 220081115G7321 EEC AEROSPATR72 ATR72 EU PWA PW120 PW127 NE LT ENGINE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 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 DEPARTURE. SHORTLY AFTER, VIBRATIONS WERE FELT AND THE CREW SHUT THE ENGINE DOWN. A SINGLE ENGINE LANDING FOLLOWED. TROUBLESHOOTING LED TO THE REPLACEMENT OF THE ENGINE ELECTRONIC CONTROL BEFORE THE ACFT WAS RETURNED TO SERVICE. 2H72 4T4 TRT E20NE 20090102 EA 2009 1 2 CA081125014 120081011G2822RR12830 PUMP DHAV DHC6 DHC6100 2802610EA PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL FUEL BOOST DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 6 (CAN) OVERHAULED FUEL BOOST PUMP MAKING GRINDING NOSE WHEN TURNED ON. PUMP REMOVED AND REPLACED WITH OVERHAULED BOOST PUMP. FAILED PUMP HAD ONLY 6.1 HOURS TIME IN SERVICE SINCE OVERHAUL AND 5 FLIGHT CYCLES. FAILED PUMP RETURNED TO INSTALLER. 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20090102 NE 2009 1 2 CA081125015 220081115G7200 ENGINE UROCOPEC135 EC135P1 8680990EU PWA PW206 PW206B 0 NE NR 1 MAKING METAL W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE FLIGHT, THE NR 1 ENG CHIP DETECTOR LIGHT ILLUMINATED. THE PILOT "BURNED" THE CHIP DETECTOR AND THE LIGHT WENT OUT. SHORTLY AFTER THE LIGHT CAME ON AGAIN AND THE PILOT BURNED AGAIN AND THE LIGHT WENT OUT. HE DECIDED TO ABORT 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 FRACTURED POWER TURBINE BLADES. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1G72 3U3 UO H88EU E42NE 20090102 NE 2009 1 2 CA081125016 220081117G7200 ENGINE LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE SHUTDOWN W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 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 ESTABLISHED. 2L72 4F4 FRTA10CE E35NE 20090102 EA 2009 1 2 CA081125017 220081107G7230 BLADES PWA PT6 PT6A28 EA COMPRESSOR FRACTURED W A UNSCHED LANDING RXJPARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE AT FL170, THE LT ENG LOST POWER AND THE TEMP INCREASED TO 850 DEGREES C. (1) PASSENGER SAW FLAMES OUT THE EXHAUST. THE ENG WAS SHUTDOWN AND A SINGLE ENGINE LANDING FOLLOWED. POST FLIGHT INSP FOUND FRACTURED COMPRESSOR TURBINE 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 220081116G7250 BLADES PWA PT6 PT6A6 52043EA POWER TURBINE FAILED W O OTHER E VIBRATION/BUFFET NRNOT 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 220081119G7261 OIL SYSTEM LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE RT ENGINE LEAKING W B EMER. DESCENT KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS DEDESCENT 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 BLEED AIR DUCTS. THE ENG IS BEING REMOVED. 2L72 4F4 FRTA10CE E35NE 20090102 NE 2009 1 2 CA081125020 220081121G7200 ENGINE AGUSTAA109 A109E 0260119EU PWC PW206CPW206C NE NR 2 MAKING METAL W EA ENGINE SHUTDOWN UNSCHED LANDING RR PARTIAL RPM/PWR LOSS PARTIAL RPM/PWR LOSS CLCLIMB 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 ALERTED. NR 1 ENG WENT TO 124 PERCENT TORQUE AFTER NR 2 ENG POWER LOSS. SUCCESSFUL RUN-ON LANDING WAS ACCOMPLISHED AND ACFT WAS GROUND-TAXIED TO PARKING AREA. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1G72 3U3 URTH7EU E42NE 20090102 NM 2009 1 2 CA081126001 120081120G27203985001007 CONTROL UNIT BOMBDRDHC8 DHC8402 1390042NM PWC 150 PW150A EA RUDDER FAILED W K NONE L NO TEST ININSP/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 PASSED THE TEST. THE FCECU WAS TESTED IAW AMM 27-00-01. 2H72 4T4 TRTA13NM E00062EN 20090102 NM 2009 1 2 CA081126002 120081116G5230 DOOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA CARGO NOT CLOSED W A UNSCHED LANDING WJ INADEQUATE Q C WARNING INDICATION CLCLIMB 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 FUNCTIONED AND CLOSED AND LOCKED. SUSPECT THAT THE GROUND CREW DID NOT FULLY PUSH THE HANDLE INTO THE CORRECT POSITION. 2H72 4T4 TRTA13NM E00062EN 20090102 NM 2009 1 2 CA081126003 120081124G5270 SENSOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA DOOR LOCK OUT OF RIG W A UNSCHED LANDING N FALSE WARNING CLCLIMB 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. 2H72 4T4 TRTA13NM E00062EN 20090102 2009 1 2 CA081126005 420081104G3457S67157520 ANTENNA CESSNA750 750 2076810CE ALLSN AE3007AE3007C 03047GL NR 2 GPS MALFUNCTIONED W O OTHER H ELECT. POWER LOSS-50 PC LDLANDING 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. 2L72 4J4 FRTT00007WITE6CH 20090102 NM 2009 1 2 CA081126006 120081010G291082920010263 LINE DHAV DHC8 DHC8103 1386005NM PWA PW121 PW121 52124NE HAMSTD14SF 14SF7 NE HYDRAULIC SYS CRACKED W O OTHER K FLUID LOSS CRCRUISE 1 CA 6726 (CAN) DURING CRUISE FLIGHT SEVERAL DROPS OF HYD FLUID WERE DISCOVERED COMING FROM THE RT OVERHEAD CEILING. SOME FLUID FELL 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090102 2009 1 2 CA081126007 420081021G31007014300901 DISPLAY CESSNA750 750 2076810CE ALLSN AE3007AE3007C 03047GL NR 4 FAILED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC CLCLIMB 1 CA (CAN) RE-OCCURRING DEFECT 2008/10/21 -FLIGHT CREW REPORTED NR 4 DISPLAY UNIT FLICKED ON START-UP. FAULT COULD NOT BE DUPLICATED 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 INTERMITTENT 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. 2L72 4J4 FRTT00007WITE6CH 20090102 WP 2009 1 2 CA081126008 120081121G243514924HTH CASE ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE STARTER GEN CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA 41 (CAN) STARTER CASING CRACKED. 1G71 3O3 O H11NM 1E4 20090102 NE 2009 1 2 CA081127001 120081103G6320S613520670043 HOUSING SKRSKYS61 S61N 8142104NE M/R GEARBOX CRACKED W O OTHER O OTHER NRNOT 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 AREA OF THE HSG IS ALWAYS HIGHLY SCRUTANIZED DURING NDT. 2G72 4U 1H15 20090102 NE 2009 1 2 CA081127002 120081103G6230 BEARING SKRSKYS61 S61A 814210CNE MAST FAILED W O OTHER O OTHER NRNOT 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. 2G72 4U H2EA 20090102 NE 2009 1 2 CA081127003 120081030G6230 GUIDE SKRSKYS76 S76A 8143006NE SWASHPLATE MISMANUFACTURED W K NONE O OTHER ININSP/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 ABOVE 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 HAS 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 LOG CARDS) MOST LIKELY MACHINED INCORRECTLY DURING MFG PROCESS. SQID NR 08-07896. 1G72 3U H1NE 20090102 NE 2009 1 2 CA081127004 120080911G6230SB3354102 CONE SKRSKYS76 S76 8143010NE M/R GEARBOX BRG DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) INSPECTION OF CAGE SHAKE ON TAPERED ROLLER BRGS PN: SB3354-102 WAS DIMENSIONALLY INSPECTED IAW (SA4047-76-7-8 CHANGE 9, 31/MARCH/2006 IAW PARA. 2-52A) AND DETERMINED TO EXCEED AVERAGE MAXIMUM ALLOWABLE CAGE SHAKE LIMITS (.017 INCH) PRIOR TO INSTALLATION ON MGB PN: 76351-09600-044 SN:A231-00184. RETURN TO VENDOR FOR WARRANTY. UNSERVICEABLE BRG CONE RETURNED TO VENDOR AWAITING WARRANTY RMA NR. (COMPANY SQID NR 08-06654) 1G72 3U H1NE 20090102 NE 2009 1 2 CA081127005 320081112G6114E6468 HUB BEECH 56 56TC 1152736CE HARTZLHCE4A HCE4A3A NE PROPELLER WORN W O OTHER O OTHER NRNOT REPORTED 1 CA 2209 (CAN) PROPELLER CAME IN FOR SHIFTED PRELOAD PLATES. HUB DID NOT SEEM TO SEAL (MATE) PROPERLY. THERE WERE HEAVY WEAR MARKS ON THE CENTER SECTION OF THE MATING SURFACES ONLY. TEFLON WAS WORN THROUGH ON ALL (4) BLADES. ONE OTBD BRG RACE WAS BADLY CHIPPED AND SHOWED SIGNS OF CRACKING. 1L72 3O 3A16 5 CP10NE 20090102 NE 2009 1 2 CA081127007 120080708G63207635109626 SHAFT SKRSKYS76 S76 8143010NE M/R GEARBOX CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) MGB PN:76351-09600-044 SN:A231-00044 IN FOR OVERHAUL. FOLLOWING CLEANING AND INSP OF NEW SPLINE SHAFT, CORROSION WAS 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. 1G72 3U H1NE 20090102 NE 2009 1 2 CA081127008 120080620G63207635109058102 PINION GEAR SKRSKYS76 S76 8143010NE M/R GEARBOX CORRODED W K NONE O OTHER ININSP/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. 1G72 3U H1NE 20090102 NE 2009 1 2 CA081127009 120080611G63207635109028105 SHAFT SKRSKYS76 S76 8143010NE M/R GEARBOX CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CORROSION FOUND ON NEW QUILL SHAFT MAIN GEARBOX O/H PN:76351-09500-044, SN:A081-00110 FOLLOWING CLEANING AND INSPECTION OF NEW QUILL SHAFT (P/N,S/N LISTED BELOW), MULTIPLE CORROSION PITTING CLUSTERS FOUND ON INTERNAL SPLINES AND ID OF PART. 1G72 3U H1NE 20090102 2009 1 2 CA081127010 120080611G63207635109028105 SHAFT M/R GEARBOX CORRODED W K NONE O OTHER ININSP/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 AND 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 COMPANY SQID NR 08-04306. 20090102 NE 2009 1 2 CA081127011 120080606G6320SB3202A2 BEARING SKRSKYS76 S76A 8143006NE M/R GEARBOX FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PERFORMED CAGE SHAKE ON NEW BRGS IAW MFG ACFT ENGINEERING INSTRUCTION EI NR E76-702-35-1601. RESULTS FAILED INSP RETURN TO VENDOR FOR WARRANTY. UNSERVICEABLE BRG RETURN TO VENDOR AWAITING WARRANTY RMA NR COMPANY SQID NR 08-04194. 1G72 3U H1NE 20090102 NE 2009 1 2 CA081127012 120080417G63207635109008056 HOUSING SKRSKYS76 S76A 8143006NE M/R GEARBOX CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) GEARBOX REMOVED FOR EXCESSIVE CORROSION AROUND OIL FILTER HSG FITTING. MAIN GEARBOX RECEIVED AT HELI-ONE FOR REPAIR AT TT:10961:18 HRS. TSO:2969:48 HRS. FLUID ADAPTER (FITTING) REMOVED FROM LWR HSG OIL FILTER AREA AND CORROSION WAS CLEANED/REMOVED TO ALLOW FOR INSPECTION. EXTENSIVE CORROSION WAS FOUND AT FLUID ADAPTER PORT AND LOCK RING AREA BEYOND MAXIMUM 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 INSUFFICIENT SURFACE PROTECTION AT DAMAGED AREA. 1G72 3U H1NE 20090102 NE 2009 1 2 CA081127013 120080320G6320SB2151107 BEARING SKRSKYS76 S76A 8143006NE UNSERVICEABLE W K NONE O OTHER ININSP/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 BE BREAKING UP AT OUTER RACE ROLLER PATHWAY. FOLLOWING COMPLETION OF GB INSP THIS BRG WAS CONSIDERED AS THE SOURCE FOR THE METAL CONTAMINATION. REPLACE BRG DURING OVERHAUL. 1G72 3U H1NE 20090102 NE 2009 1 2 CA081128001 220081125G7250PW120A TURBINE DHAV DHC8 DHC8101 2809002NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NR 2 ENGINE FAILED W L ABORTED APPROACH O OTHER APAPPROACH 1 CA 2784617199 (CAN) PRIOR TO TAKEOFF, THE CREW FELT A THUD AND GRINDING NOISE FROM THE NR 2 ENGINE AT 70 PERCENT TORQUE. THE ENGINE WAS 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 TURBINE WERE FOUND IN THE TAIL EXHAUST PIPE. ALL PARAMETERS OF BOTH ENGINES WERE WITHIN LIMIT. AS SOON AS THE TAKEOFF ROLL 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 TORQU2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090102 NE 2009 1 2 CA081128002 120081103G6320S613723053102 BEVEL GEAR SKRSKYS61 S61A 814210CNE M/R GEARBOX UNSERVICEABLE W O OTHER O OTHER ININSP/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: E128-00271. COMPANY SQID NR 08-08045. 2G72 4U H2EA 20090102 NE 2009 1 2 CA081128003 120081127G6320 GEARBOX SKRSKYS76 S76 8143010NE MAIN ROTOR FAILED W K NONE O OTHER ININSP/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 NR 08-8606. 1G72 3U H1NE 20090102 NE 2009 1 2 CA081128004 120081127G6320SB2151107 BEARING SKRSKYS76 S76 8143010NE M/R GEARBOX DAMAGED W K NONE O OTHER ININSP/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. FOLLOWING DISASSY AND INSP OF MGB THE RT OUTPUT ALIGNMENT BRG WAS FOUND TO BE THE CAUSE FOR THE METAL GENERATION WITH HEAVY SPALLING AT ROLLER PATHWAY OF BRG OUTER RACE. ADDITIONAL BRS INDICATE INITIAL STAGES OF SPALLING. REPLACE WITH SERVICEABLE BRS. COMPANY SQID NR 08-08605. 1G72 3U H1NE 20090102 2009 1 2 CA081128005 420081127G3120285T08551 FDAS CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE COCKPIT ODOR W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) ON CRUISE THE F/A REPORTED A STRONG ODOR IN THE CABIN, PILOT CONFIRMED THE STRONG SMELL AND DIVERTED FLIGHT TO BASE AND DECLARE AN EMERGENCY LANDING. AFTER MX INVESTIGATION, FOUND THE FDAS "FLIGHT DECK ACCESS SYS" AT FAULT. ELECTRICAL ODOR COMING FROM THIS COMPONENT. 2L72 4F4 FRTA21EA E15NE 20090102 EA 2009 1 2 CA081128006 220081126G8530 VALVE SEAT PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL ENGINE WORN W O OTHER O OTHER NRNOT REPORTED 1 CA 1452 (CAN) INTAKE VALVE STAYING OPEN, INTAKE VALVE AND SEAT WORN. 1L72 3O3 O A20SO E14EA 5 CP33EA 20090102 EA 2009 1 2 CA081129001 120081125G5610NP1393229 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 9278 (CAN) IN FLIGHT LT SIDE WINDOW SHATTERED. FLIGHT DIVERTED MX REPLACED SIDE WINDOW. 2L72 4F4 FRTA21EA E15NE 20090102 EA 2009 1 2 CA081129003 120081122G3260 WARNING LIGHT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE MLG ILLUMINATED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF, LANDING GEAR DID NOT RETRACT WHEN SELECTED UP. LANDING GEAR LIGHT REMAINED GREEN. FLT CREW ALSO REPORTED INBD ANTI-SKID (C) AND PARK BRAKE SOV (C) MSG. ALL MSGS CLEARED WHEN GEAR SELECTED DOWN. ACFT RETURNED TO DEPARTURE AIRPORT AND LANDED WITHOUT FURTHER INCIDENT. 2L72 4F4 FRTA21EA E15NE 20090102 EA 2009 1 2 CA081129005 120081116G2150GG670950093 ACM CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C5B1 30052NE LEFT SEIZED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/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 RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E00063EN 20090102 NM 2009 1 2 CA081201001 120081128G2510412310416 SEAT BACK EMB ERJ190ERJ190100IGW3260408NM GE CF34 CF3410E5A1 30022NE COCKPIT LOOSE W K NONE O OTHER ININSP/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 PAGE 10044 FIGURE 7 ITEMS 5 & 10. CHAIR PN ARE414140003-105, 41414003-111,41414003-113,41404003-103 & 41404003-105. 2L72 4F4 FRTA57NM E00070EN 20090102 CE 2009 1 2 CA081201002 120081201G33400713035 SWITCH CESSNA172 172K 2072430CE LYC O320 O320E2D 41508EA LANDING LIGHT OVERHEATED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LANDING LIGHT SWITCH MAY BE ORIGINAL (8865 HRS) DETENTS BECAME "STICKY" AND NOT AS POSITIVE AS NORMAL. SWITCH FUNCTION DID NOT FAIL. INSP REVEALED PWR SUPPLY WIRE END AND LUG ON SWITCH OVERHEATED. DISASSY SHOWED LUG CONTACT RIVET DETERIORATED 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 TO CARRY MORE CURRENT SHOULD BE INSPECTED VISUALLY ANNUALLY TO DETERMINE IF OVERHEATING IS AN ISSUE. 1H71 3O3 ONT3A12 E274 20090203 CE 2009 2 3 CA081201003 120081009G3597P108 CONNECTOR LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE731* 01518WP O2 SYSTEM MISINSTALLED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) PASSENGER O2 MASK WOULD NOT DEPLOY WHEN TESTED. SYSTEM TROUBLESHOT AND FOUND CONNECTOR P108 WAS NOT INSTALLED CORRECTLY. CONNECTOR REMOVED, INSPECTED AND REINSTALLED .O2 MASK FUNCTION CHECKED SERVICEABLE IAW AMM 35. 2L72 4F4 FRTT00008WIE6WE 20090102 2009 1 2 CA081201004 120081201G8011 BOLT STARTER MISSING W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/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 BENDIX HSG DURING STARTER OPERATION. 20090102 WP 2009 1 2 CA081201005 220081130G720031037505 GASKET GARRTTTPE331TPE33110UA 01514WP ENGINE LEAKING W K NONE O OTHER ININSP/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 TO 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 UPGRADED 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 120081201G5310NAS1473A3K DOME NUT CESSNA750 750 2076810CE ALLSN AE3007AE3007C 03047GL WINDSHIELD POST CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE REPLACEMENT OF THE RT WINDSHIELD, DUE TO A BROKEN OUTER PANE, HEAVY CORROSION WAS NOTED COMING OUT OF THE DOME NUTS. THE WINDSHIELD IS INSTALLED FROM THE OUTSIDE AND THE SCREWS ARE HELD IN PLACE BY THESE DOME NUTS THAT RIVETED IN PLACE AROUND THE PERIMETER OF THE FRAME. EACH DOME NUT WAS BOROSCOPED AND FOUND THAT A MAJORITY WERE SPLIT OR CRUMBLED DUE TO CORROSION. ALL DOME NUTS WERE REPLACED AND THE WINDSHIELD RE-INSTALLED. 2L72 4J4 FRTT00007WITE6CH 20090102 CE 2009 1 2 CA081201007 120081128G272004115264 RUDDER BAR CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA SNSNCH72C 72CK EA RT RUDDER CHAFED W K NONE O OTHER ININSP/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 RUDDER PEDAL TORQUE TUBE. 1H71 3O3 ONT3A19 E223 5 NP9045 20090102 NM 2009 1 2 CA081201008 120080919G6320B7936S CHIP DETECTOR DOUG 600N 600N 3027377NM ALLSN 250C 250C47M 03013GL TRANSMISSION CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 800 (CAN) BOTH TEDESCO B7936S CHIP DETECTOR BASES FOUND CRACKED AT BASE OF O-RING FLANGE. CAUSED BY OVERTORQUE DURING AN EARLIER INSTALLATION. CRACKS NOT VISIBLE UNTIL CHIP DETECTORS WERE REMOVED TO DRAIN TRANSMISSION OIL. 1G71 3U3 UNCH3WE E1GL 20090102 NM 2009 1 2 CA081201009 120081128G5302500N34247 ANGLE DOUG 600N 600N 3027377NM ALLSN 250C 250C47M 03013GL TAILBOOM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 800 (CAN) FUSELAGE ANGLE FOUND CRACKED DURING A TAILBOOM INSPECTION. PART IS NOT READILY VISIBLE OR A PLACE OF INTEREST DURING INSPECTIONS AND MAY HAVE GONE SOME TIME AS CRACKED. PART IS TO BE REPLACED BEFORE FURTHER FLIGHT. 1G71 3U3 UNCH3WE E1GL 20090203 SW 2009 2 3 CA081201010 120080901G2910 HOSE BELL 206 206B 1181511SW HYD SYSTEM CHAFED W K NONE K FLUID LOSS ININSP/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. 1G71 3U H2SW 20090204 SW 2009 2 4 CA081201011 120081001G6320206031554003 SPINDLE BELL BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL TRANSMISSION WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TRANSMISSION MOUNTS REMOVED DUE TO BEARING WEAR. UPON FURTHER INSP, SPINDLE ALSO FOUND DAMAGED IN LOCATION OF WASHER 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. 1G71 3U3 U H2SW E4CE 20090102 NM 2009 1 2 CA081201012 120081129G3251651781412 ACTUATOR BOEING727 727225 1384077NM PWA JT8 JT8D9A 52048NE STEERING UNIT WORN W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) A "CLUNK" IN THE NOSE WHEEL STEERING TILLER WAS REPORTED. BOTH STEERING ACTUATOR ROD ENDS WERE FOUND PULLING OUT OF THE PISTONS. BOTH STEERING ACTUATORS WERE REPLACED. A/C RETURNED TO SERVICE. 2L73 4F4 F A3WE E2EA 20090102 2009 1 2 CA081202001 120081201G3244301003530 TIRE MLG BULGED W O OTHER O OTHER NRNOT 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 120081129G3250C247360011 STEERING SYS AIRBUSA319 A319114 3930350NM CFMINTCFM56 CFM565A1 NE NLG MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 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 CENTERLINE. STEERING CONTROL UNIT 6GC REPLACED IAW MM S/N H0714. 2L72 4F4 FRTA28NM E29NE 20090102 NE 2009 1 2 CA081202003 220081106G7250311074102 RETAINING RING PWA PT6 PT6A114A 52043NE TURBINE SECTION DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 2760 2760 (CAN) ENGINE WAS RECEIVED FOR INVESTIGATION/REPAIR DUE TO SHIFTING OF CT SHROUD SEGMENTS. THE CT SHROUD SEGMENT-RETAINING 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 WAS 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 INCH, 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 120081113G6710350A27035106 CONTROL TUBE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE COLLECTIVE FAILED W K NONE O OTHER ININSP/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). 1G71 3U3 U H9EU E19EU 20090102 CE 2009 1 2 CA081203001 120081120G2840100380006119 PROBE BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL RT AUX TANK SEPARATED W K NONE N FALSE WARNING ININSP/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. THE RT FUEL TANK READING WAS 300 LBS LOW. MAINT INSPECTED SYS AND ISOLATED THE PROBLEM TO THE RT AUX FUEL TANK PROBE. UPON 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. 2L72 4T4 T A24CE E4EA 6 CP56GL 20090106 NE 2009 1 6 CA081203002 220081125G7200 ENGINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE RIGHT MALFUNCTIONED W C ABORTED TAKEOFF O OTHER TOTAKEOFF 1 CA (CAN) ON TAKEOFF ROLL WITH PASSENGERS ON BOARD POWER WAS ADVANCED THROUGH 70 PERCENT TORQUE. A THUD AND GRINDING NOISE WAS HEARD FROM THE RT SIDE. TAKEOFF WAS ABORTED AND AC RETURNED TO THE GATE. ENG TO BE REMOVED AND SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA13NM E20NE 20090106 EA 2009 1 6 CA081203003 220081125G7200 ENGINE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA MALFUNCTIONED W BA EMER. DESCENT UNSCHED LANDING KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) SHORTLY AFTER TAKE OFF OIL MIST IN CABIN WAS DETECTED. THE ACFT IMMEDIATELY TURNED BACK, DECLARED AN EMERGENCY, AND 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 COMPONENTS. EMU DATA REQUESTED. ENGINE BEING REMOVED FOR INVESTIGATION AT MFG. UPDATES WILL BE PROVIDED. 2H72 4T4 TRTA13NM E00062EN 20090106 2009 1 6 CA081203004 120081118G6420S611033406101 SPINDLE S61TRH TAIL ROTOR UNSERVICEABLE W O OTHER O OTHER NRNOT 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 220080502G7250 TURBINE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA RT ENGINE DAMAGED W O OTHER R PARTIAL RPM/PWR LOSS NRNOT 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 WAS EQUIPPED WITH A FDR AND CVR. EXAMINATION OF ENGINES, REVEALED THE LT ENGINE DISPLAYED ROTATIONAL SIGNATURES CHARACTERISTIC 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 PROTRUDING CT BLADE SHROUD SEGMENT. THE CT DISK, VANE AND SHROUD ASSY WAS REQUESTED TO BE RETURNED TO MFG FOR DETAILED EX2L72 4T4 TRTA24CE E4EA 20090106 2009 1 6 CA081203006 120081202G6420S611033406 SPINDLE TAIL ROTOR UNSERVICEABLE W O OTHER O OTHER NRNOT 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 220081126G7200 ENGINE EMB 120 EMB120 3260201SO PWA 118 PW118 NE MAKING METAL W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB AT FL60, THE CREW NOTICED A LOW ENGINE OIL PRESSURE LIGHT, FOLLOWED BY A POPPING NOISE. THE ENG WAS SHUTDOWN AND THE ACFT WAS DIVERTED BACK TO BASE. GROUND INSP FOUND THE TURBOMACHINE CHIP DETECTOR COVERED WITH METAL SHAVINGS AND THE LP AND HP ROTORS INCAPABLE OF ROTATION. THE ENG HAD RECENTLY UNDERGONE A HOT SECTION INSP. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4T4 TRTA31SO E20NE 20090102 NE 2009 1 2 CA081203008 220081128G7323 GASKET FOKKERF27 F27MK50 EU PWA PWA120PW125B NE OVRSPD GOVERNOR TORN W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AT TOP OF CLIMB, OIL PRESSURE FLUCTUATION WAS REPORTED FOLLOWED BY LOW OIL PRESSURE INDICATION. THE ENGINE WAS SHUTDOWN BY THE PILOT. ON RETURN TO GATE, THE ENG COWL WAS FOUND COVERED WITH OIL. OVERSPEED GOVERNOR GASKET FOUND DETERIORATED. GASKET WAS REPLACED. 2H72 4T4 TRTA817 E20NE 20090102 NE 2009 1 2 CA081203009 220081125G73217898422009L6 EEC DHAV DHC8 DHC8* NM PWA 120 PW120A NE ENGINE MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) PILOT REPORTED SHUTTING ENGINE DOWN IN FLIGHT DUE TO EXCESSIVE TORQUE FLUCTUATIONS. EEC WAS REPLACED AND DEFECT RECTIFIED. THE SUSPECT EEC HAS BEEN SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA13NM E20NE 20090102 NE 2009 1 2 CA081203010 220081027G7297 WIRE HARNESS AEROSPATR42 ATR42* 8680900EU PWA PW120 PW127 NE ENGINE DAMAGED W E ENGINE SHUTDOWN RF PARTIAL RPM/PWR LOSS FLT CONT AFFECTED CRCRUISE 1 CA (CAN) THE ENG EXPERIENCED REPEATED EVENTS OF TORQUE FLUCTUATIONS BETWEEN THE 20TH AND 24TH OF OCTOBER FOR WHICH TROUBLESHOOTING 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 TROUBLESHOOTING LED TO THE REPLACEMENT OF THE FUEL CONTROL AND ENGINE WIRING HARNESS, WHICH HAVE BEEN SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA53EU E20NE 20090102 NM 2009 1 2 CA081203011 120081202G271085711569001 BRACKET DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF* NE AILERON CONTROL CRACKED W K NONE O OTHER ININSP/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 QUADRANT BRACKET TO BE INSTALLED. NEW BRACKET IS IN SHEET METAL SHOP. REMOVED AND REPLACED NEW LT AILERON QUADRANT BRACKET IAW SB 8-57-27. LT WING AILERON TERMINAL QUADRANT, PREVIOUSLY REMOVED FOR SHEET METAL ACCESS, INSTALLATION COMPLETED AS IAW AMM 27-12-31 TOTHE END OF STEP 12. INDEPENDENT INSP CARRIED OUT ON DEFECT 814228. M7109 FUNCTION TEST 1.C. COMPLETED FOR THOSE PORTIONS OF THE SYS THAT HAVE BEEN DISTURBED AND FOUND TO WORK NORMALLY M7128. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090102 WP 2009 1 2 CA081203012 120081126G61206506196 VALVE CVAC 580 580 2422806WP PROP PITCH LOCK FAILED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION APAPPROACH 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. 2L72 4T RT 20090102 EA 2009 1 2 CA081204001 120081202G2820CN6273003001 PIPE CNDAIRCL600 CL600* 1900302EA GE CF34 CF348C5 30050NE FUEL FLOW CHAFED W K NONE K FLUID LOSS ININSP/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. 2L72 4F4 FRTA21EA E00063EN 20090102 NM 2009 1 2 CA081204002 120081108G2497 WIRE DHAV DHC8 DHC8201 2809001NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ALTERNATOR DAMAGED W D RETURN TO BLOCK H ELECT. POWER LOSS-50 PC TXTAXI/GRND HDL 1 CA (CAN) NR1 AND NR2 AC GEN ANNUNCIATIONS ILLUMINATED DURING TAXI. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE FOLLOWING 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090102 EU 2009 1 2 CA081204003 120081204G271004820203 SENSOR AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE LT AILERON UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FDR CORRELATION CHECK REVEALED LT AILERON ROLL SENSOR UNSERVICEABLE. SENSOR INSPECTED. OPERATING CABLE FRAYED AND BINDING. SENSOR REPLACED. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20090102 NE 2009 1 2 CA081204005 320081204G6111SFA13MIROASK112 BLADE AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 6717 (CAN) LEADING EDGE NICKEL SHEATH VISUALLY INSPECTED AND A CRACK NOTED. IF PRESSURE APPLIED TO BLADED CRACK BECAME MORE NOTICEABLE. BLADE REMOVED FROM SERVICE. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20090102 NM 2009 1 2 CA081204006 120081203G3397 WIRE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF* NE CABIN LIGHT SHORTED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/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 CONFIRM SHORTING OF THE FORE/AFT WIRES TO THE AFT JUNCTION BOX. WIRING REPAIRED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090204 EA 2009 2 4 CA081204007 120081202G3234 SHAFT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE MLG HANDLE WORN W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) DURING MX OPERATION OF THE LANDING GEAR MANUAL RELEASE HANDLE IT STUCK IN THE RELEASE POSITION. MX TROUBLESHOOTING FOUND THE RELEASE HANDLE SHAFT BINDING DUE TO INTERNAL WEAR AND SLIGHTLY BENT. RELEASE HANDLE ASSY WAS REPLACED IAW AMM 32-34-01. ACF TT 14745 HOURS, 123110 CYCLES. 2L72 4F4 FRTA21EA E15NE 20081229 SW 2008 12 29 CA081204008 120081127G52104744 HINGE PIN BBAVIA8 8GCBC 1220803SW LYC O360 O360C2A 41514EA MCAULY1A200 1A200* GL PAX DOOR RUSTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AN ATTEMPT TO REMOVE THE ENTRANCE DOOR USING THE EMERGENCY EXIT HANDLE FOUND THAT THE SYS HAD BECOME SEIZED. UPON 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 SYS. THE MM DOES NOT CALL FOR LUBBING OR FUNCTION CHECKING THIS SYS. IT HAS BEEN APPROXIMATELY 2000 HRS SINCE THE LAST RECORDED REMOVAL OF THE DOOR. 1H71 3O3 O A21CE E286 5 NP874 20081219 CE 2008 12 19 CA081204009 120081201G7820175400125 MUFFLER CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ENGINE LEAKING W K NONE O OTHER ININSP/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 BODY. THIS IS A COMMON PLACE FOR THESE MUFFLERS TO FAIL. 1H71 3O3 ONT3A12 E274 5 NP910 20081219 CE 2008 12 19 CA081204010 120081201G7820175400122 MUFFLER CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ENGINE CRACKED W K NONE O OTHER ININSP/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 CRACK 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. 1H71 3O3 ONT3A12 E274 5 NP910 20081222 NM 2008 12 22 CA081204011 120081129G29317G773 PRESSURE SWITCH DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYDRAULIC SYS MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 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 INDICATOR, BUT THE NR 2 EDP AMBER CAUTION LIGHT IS ON. TR128. CONNECTOR ON PRESSURE SWITCH CLEANED. NR 2 SYSTEM HYD PRESSURE SWITCH REPLACED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090204 EA 2009 2 4 CA081204012 120081202G5610NP139321003 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA COCKPIT BROKEN W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) DURING CRUISE, RT (F/O) WINDSHIELD SHATTERED, WITH NO LOSS OF PRESSURIZATION. CAPTAIN DESCENDED AND DECLARED AN EMERGENCY LANDING RT WINDSHIELD (P/N OFF: NP139321-003) CHANGED IAW AMM 56-11-01. 2L72 4F RTA21EA 20090204 NE 2009 2 4 CA081204013 220081127G7261GE6087T04P0 SCREEN CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE SCAV PUMP OBSTRUCTED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA 21013 (CAN) IFSD EN ROUTE FROM PHL - PIT. LOSS OF ENGINE OIL PRESSURE AT FLIGHT FL340. LEFT ENGINE RED OIL PRESSURE CAS MESSAGE ILLUMINATED. OIL PRESSURE READ 23 PSI PRIOR TO ENGINE SHUTDOWN. OIL TEMP WAS NORMAL PRIOR TO ENGINE SHUTDOWN. AIRCRAFT WAS DIVERTED MADE AN UNEVENTFUL LANDING AT PIT. INSPECTION BY MAINTENANCE REVEALED COKING AROUND THE SCREEN. LUBE PUMP WAS REMOVED AND REPLACED IAW TO 70-21-01. AIRCRAFT RETURNED TO SERVICE WITH NORMAL OPERATION. (TC NR 20081204013) 2L72 4F4 FRTA21EA E15NE 20081219 NE 2008 12 19 CA081205001 220080723G7200 ENGINE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE NR 2 DAMAGED W A UNSCHED LANDING Y ENGINE STOPPAGE CLCLIMB 1 CA 9400 (CAN) AN ACFT RETURNED TO BASE DUE TO ENGINE NR 2 FIRE WARNING LIGHT ILLUMINATE. ENGINE FOUND DAMAGED AND REMOVED FOR INVESTIGATION. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081229 2008 12 29 CA081205002 420081123G34008221577202 DISPLAY CNDAIRCL604 CL604 1900301EA GE CF34 CF343B 30069NE MFD 1 INOPERATIVE W O OTHER H ELECT. POWER LOSS-50 PC DEDESCENT 1 CA (CAN) 30 MINUTES PRIOR TO LANDING, THE PILOT PRIMARY FLIGHT DISPLAY(PFD 1) WENT BLANK. THEN IAW AFM (SECTION 05-15-1) THE 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 AMM 31-61-00. THE MFD 1 (P/N: 822-1917-202 S/N: 2NKRG) WAS ALSO REPLACED BUT A PRECAUTIONARY MEASURE . ACFT RETUNED TO SE2L72 4F4 FRTA21EA E15NE 20081222 EA 2008 12 22 CA081205003 120081204G5720 SUPPORT BRACKET DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE AILERONS CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT AND RT WING AILERON INPUT QUADRANT SUPPORT BRACKETS AT YW414.00 CRACKED. QUADRANT SUPPORT BRACKETS REPLACED. 2H72 4T4 TRTA13NM E20NE 20090203 SW 2009 2 3 CA081205004 120081126G7603C8102415 CONTROL CABLE SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP POWER LEVER BROKEN W C ABORTED TAKEOFF F FLT CONT AFFECTED TOTAKEOFF 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 SLOWLY REDUCED POWER TO FLIGHT IDLE. LT ENGINE DID NOT RESPOND TO FURTHER POSITIVE POWER LEVER INPUTS BUT WOULD RESPOND WHEN 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 PROPER ROUTING OF CABLE REQUIRES A SIGNIFICANT BEND IN CABLE ASSY. CABLE REPLACED & ACFT RETURNED TO SERVICE. 2L72 4T4 TRTA8SW E4WE 20081229 NM 2008 12 29 CA081205006 120081202G3240244300 STATOR BFGOODRICH BOEING727 727223 1384074NM PWA JT8 JT8D15 52051NE BRAKE ASSY BROKEN W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) DURING PUSHBACK ON C-FCJF EXCESSIVE FORCE WAS REQUIRED TO MOVE ACFT AND DETERMINED NR2 MAIN WHEEL WAS DEFLATED. ACFT PULLED BACK TO GATE FOR INVESTIGATION. MAINT WAS UNABLE TO REMOVE NR2 WHEEL. AFTER SEVERAL EFFORTS WITHOUT SUCCESS IT WAS DECIDED THE TIRE AND POSSIBLY THE WHEEL WOULD HAVE TO BE CUTOFF. AFTER CUTTING A SECTION OF THE TIRE OFF IT WAS DETERMINED A PIECE OF THE BRAKE STATOR HAD BROKEN OFF AND PENETRATED THE WHEEL HUB AS THE ACFT WAS TOWED DEFLATING THE TIRE 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. 2L73 4F4 F A3WE E2EA 20081222 CE 2008 12 22 CA081205007 120081204G37105100106377 LINE CESSNA414 414A 2075907CE CONT O520 TSIO520NB 17040SO MCAULY3AF32C3AF32C505 GL VACUUM SYS CORRODED W O OTHER O OTHER CRCRUISE 1 CA 5291 (CAN) UPON REACHING CRUISE FLIGHT AND ACTIVATING AIRFRAME PNEUMATIC DE-ICE SYSTEM, THE BOOTS WOULD REMAIN PARTIALLY TO MOSTLY INFLATED. THIS PROBLEM WOULD NOT DUPLICATE ON A GROUND RUN. THE VACUUM LINE TO THE FLOW VALVES WAS INSPECTED AND A LINE ASSEMBLY TO THE TAIL FLOW VALVE WAS FOUND CORRODED WHERE IT PASSED OVER AN ENVIRONMENTAL DUCT AT APPROX. MID CABIN. THE LINE ASSEMBLY WAS REPAIRED. THE ACFT WAS GROUND RUN AND FLOWN TO CRUISE ALTITUDE TO MAX. CABIN PRESSURE DIFFERENTIAL, AND THE PNEUMATIC DE-ICE SYSTEM FUNCTIONED PROPERLY. 1L72 3O3 O A7CE E8CE 5 CP22EA 20081229 SW 2008 12 29 CA081205008 120081204G5610HYLZ88821 WINDSHIELD FRCHLDSA227 SA227CC 3377522SW GARRTTTPE331TPE33111U 29073NE MCAULY4HFR344HFR34C652 NE COCKPIT FAILED W O OTHER O OTHER APAPPROACH 1 CA (CAN) ON APPROACH THE LT WINDSHIELD SHATTERED. MX WAS DISPATCHED TO REPLACE THE WINDSHIELD. THE TEMP CONTROLLER WAS FOUND TO BE DEFECTIVE ALSO. TEMP CONTROLLER REPLACED ALONG WITH WINDSHIELD AND ACFT RETURNED TO SERVICE. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20081219 EA 2008 12 19 CA081207001 220081202G7414106006169 MAGNETO LYC O540 O540F1B5 41532EA ENGINE FAILED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS TXTAXI/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 BREAKER POINT WIRES HAD VIBRATED OFF. WIRES REPAIRED AND REINSTALLED. 3 O E295 20081219 CE 2008 12 19 CA081208001 120081119G3222SK1759 FORK CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL NOSE GEAR CRACKED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 1514615146 (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. 1H71 3O3 ONT3A12 E274 5 NP910 20081222 NM 2008 12 22 CA081208002 120081207G3231483023 SEQUENCE VALVE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA LT MLG DOOR MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 1398 (CAN) FLIGHT CREW REPORT: LT MAIN AMBER GEAR DOOR LIGHT FAILED TO EXTINGUISH ON GEAR RETRACTION (VISUALLY OPEN). ALT EXTENSION PERFORMED. REPLACED LT MLG SSV IAW 32-31-41 2H72 4T4 TRTA13NM E00062EN 20081222 SO 2008 12 22 CA081208005 120081208G8120 BEARING PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA TURBOCHARGER FAILED W AD UNSCHED LANDING RETURN TO BLOCK ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 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 THEN RETURNED TO THE AIRPORT WITH NO PROBLEMS ENROUTE. MX FOUND THE TURBO CHARGER SHAFT BEARING HAD FAILED. THE TURBO CHARGER WAS REPLACED, OIL SUMP CLEANED, OIL FILTER REPLACED AND GROUND RUN ACCEPTABLE. 1L72 3O3 O A20SO E14EA 20090204 EU 2009 2 4 CA081208007 120081201G243523085024 STARTER GEN PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL NR 1 MALFUNCTIONED W O OTHER O OTHER NRNOT 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 GENERATOR REPLACED AND GROUND RUN PERFORMED, ALL FOUND SATISFACTORY. (TC NR 20081208007) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20090205 CE 2009 2 5 CA081208008 120081208G2435200SGL119Q2 STARTER GEN CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA 110 (CAN) GENERATOR FAILED IN FLIGHT 12 MILES FROM YWG ENROUTE TO YQT. AIRCRAFT RETURNED TO YWG (TC NR 20081208008). 1H71 3T3 T A37CE E4EA 5 CP60GL 20090205 NM 2009 2 5 CA081208009 120081201G5751 BRACKET DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE AILERONS CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING MAINTENANCE INSPECTION BOTH THE LT AND RT AILERON QUADRANT SUPPORT BRACKETS WERE FOUND CRACKED. PART NUMBERS INCLUDED, LT END PIECE P/N 85711570-101, RT END PIECE P/N 85711570-102, LT BOTTOM PLATE P/N 85711572-101, RT BOTTOM PLATE 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 CRACKED BRACKETS WERE REPLACED. (TC NR 20081208009) 2H72 4T4 TRTA13NM E20NE 20081222 2008 12 22 CA081208011 120081126G78309007M60G46 COWLING GE CF6 CF650C2 30018NE THRUST REVERSER DELAMINATED W E ENGINE SHUTDOWN ED VIBRATION/BUFFET INFLIGHT SEPARATION DEDESCENT 1 CA (CAN) ON DESCENT INTO YYC, WITH POWER LEVERS AT IDLE, THE ACFT SHUDDERED MOMENTARILY. THE NR 2 THRUST REVERSER UNLOCK LIGHT ILLUMINATED AND IN-FLIGHT SHUT DOWN OF NR 2 ENGINE WAS CARRIED OUT. THE ACFT LANDED WITHOUT INCIDENT AND AN INSPECTION WAS CARRIED OUT ON NR 2 ENGINE. NR 2 ENGINE RT TRANSLATING COWL WAS FOUND DELAMINATED WITH A SECTION OF THE COWL MISSING. THE COWL WAS REPLACED, FUNCTION CHECKED AND THE ACFT RETURNED TO SERVICE. 4 F E23EA 20090203 EA 2009 2 3 CA081209005 120081208G5711215003268 SPAR CAP CNDAIRCL215 CL2151A10 1900320EA WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4895 (CAN) WHILE PERFORMING AD 92-26R1 NO DEFECTS WERE FOUND DURING ULTRASONIC INSPECTION OF REQUIRED INSPECTION AREA. DUE TO 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. 2H72 4R RTA14EA 20081222 SW 2008 12 22 CA081209006 120080611G6300206040015103 DRIVE SHAFT BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL M/R DRIVE FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA (CAN) ON DESCENT PILOT SMELLED BURNING GREASE. AFTER LANDING AND POST FLIGHT INSPECTION FOUND GREASE THROWN FROM DRIVESHAFT COUPLING. DRIVESHAFT WAS REPLACED AND FOUND ISOLATION MOUNT TO BE WEAK. REPLACED ISOLATION MOUNT AND PROBLEM WENT AWAY. 1G71 3U3 U H2SW E4CE 20081222 CE 2008 12 22 CA081210001 120081108G32455005 TUBE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MLG TIRE TORN W O OTHER O OTHER TXTAXI/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. 1H71 3O3 ONT3A12 E274 20081222 CE 2008 12 22 CA081210002 120081208G32455005 TUBE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA NLG TIRE TORN W O OTHER O OTHER TXTAXI/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 REPORTED. 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. 1H71 3O3 ONT3A12 E274 20081222 SO 2008 12 22 CA081210003 120081208G32455005 TUBE PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA NLG TIRE TORN W O OTHER O OTHER NRNOT 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. THE NOSE TIRE WAS INSP, NO DEFECTS FOUND. 1L71 3O3 O 2A13 E274 20090203 GL 2009 2 3 CA081210004 120081209G2421A3579101 GENERATOR BOMBDRBD100 BD1001A10 1390044GL HNYWL AS907 AS90711A 33908WP APU FIRE W O OTHER ABJFLAME/FIRE SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION DEDESCENT 1 CA (CAN) AFTER APU START AT FL100 JUST BEFORE APU GEN ON LINE APU FIRE CAS MESSAGE POSTED. PILOTS ARM APU BOTTLE MESSAGE DISAPPEARED. 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. 2L72 4F4 FRTT00005NYE00010LA 20081222 NM 2008 12 22 CA081210005 120081209G3213654611635 CYLINDER BOEING737 737232 1384475NM PWA JT8 JT8D17 52049NE STRUT WORN W O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 CA 3795216636 (CAN) RT MLG LOST FLUID. DURING ATTEMPTED SEAL CHANGE, THE INNER CYLINDER OF THE GEAR HAD A 6" BY 2" PIECE OF CHROME MISSING FROM THE INNER CYLINDER. 2L72 4F4 FRTA16WE E2EA 20090203 CE 2009 2 3 CA081210006 120081208G5220115430100661A SKIN BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE EMERGENCY EXIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 9902 (CAN) WHEN COMPLYING WITH SPECIAL INSPECTION "ESCAPE HATCHES AND ASSOCIATED AREAS", A CRACK WAS FOUND AT THE LOWER FORWARD CORNER OF THE BONDED RT EMERGENCY EXIT DOOR SKIN, EXACTLY AS PICTURED IN THE MAINTENANCE MANUAL. REPLACED SKIN ASSEMBLY WITH NEW. CRACKS ARE DIFFICULT TO DETECT DUE TO FILLER USED BY THE MANUFACTURER TO BLEND THE RADIUS AFTER FITTING THE 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. 2L72 4T4 T A24CE E4EA 20081229 NE 2008 12 29 CA081210008 220081204G7250FW45914 TURBINE BLADES BOEING717 717200 1383700NM RROYCEBR700 BR700715A130 NE ENGINE FAILED W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA 5094 (CAN) SURGE/IFSD/ENGINE SHUTDOWN IN FLIGHT WITH TGT CLIMBING THROUGH 1100 C. BOROSCOPE OF ENGINE 13299 TODAY FOUND THAT 2 OFF HPT STAGE 1 BLADES SUFFERED FROM A BELOW-PLATFORM FAILURE. THE 2 FAILED BLADES ARE SEPARATED BY 28 BLADES. THE AIRFOILS ON ALL OF THE REMAINING BLADES HAVE BEEN KNOCKED OFF ABOVE THE PLATFORM. 2L72 4F4 FTRA6WE E00061EN 20081222 NE 2008 12 22 CA081210009 220081201G7200 ENGINE AEROSPATR42 ATR42* 8680900EU PWA 120 PW120 NE ODOR W E ENGINE SHUTDOWN BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, THE PILOTS NOTICED OIL ODOR AND MIST IN THE CABIN. THEY TURNED THE AIR BLEED FROM THE ENGINE OFF AND THE MIST AND ODOR DISAPPEARED. SOON AFTER, OIL PRESSURE FLUCTUATIONS AND THEN A DROP IN PRESSURE OCCURRED. THE PILOTS SHUT DOWN THE ENGINE AND PERFORMED A SINGLE ENGINE LANDING. GROUND INSPECTION FOUND LOW OIL LEVEL, BOROSCOPE INSPECTION 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. 2H72 4T4 TRTA53EU E20NE 20081229 NE 2008 12 29 CA081210010 220081127G7200 ENGINE FOKKERF27 F27MK50 EU PWA PWA120PW125B NE POWER LOSS W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB AFTER T/O, ENGINE POWER LOSS OCCURRED (AT APPROX 300 FT ALTITUDE). THE ENGINE WAS SECURED AND A TURNBACK INITIATED. THE ACFT MADE A SINGLE ENGINE LANDING. POST EVENT INSP FOUND FRACTURED HP BLADES. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA817 E20NE 20090203 EA 2009 2 3 CA081210011 220081210G7200 ENGINE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA NR 1 SHUTDOWN W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA (CAN) NR 1 ENGINE SHUTDOWN CARRIED OUT AFTER TAKEOFF. HERE IS THE DEFECT ENTERED BY THE FLIGHT CREW "LT PROP RPM ONLY GOES TO 1500 RPM ON TAKEOFF AS POWER REDUCED RPM DROPS". THE INCIDENT IS UNDER INVESTIGATION. 2L72 4T4 TRTA24CE E4EA 20090203 EU 2009 2 3 CA081210012 120081208G5530313108 BRACKET ISRAEL1124 1124 4500102EU GARRTTTFE731TFE73131G 29003NE VERTICAL STAB CRACKED W K NONE O OTHER ININSP/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 CRACKS EXTEND FROM THE RIGHT OUTBOARD ATTACHMENT BOLT HOLE. THE ATTACHING BOLTS RUNS HORIZONTALLY FWD AND AFT THROUGH THE RUDDER 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. 2M72 4F4 F A2SW E6WE 20081222 NE 2008 12 22 CA081210013 220081128G7414BL600646201 MAGNETO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE UNSERVICEABLE W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) MAGNETO FOUND U/S. 1G71 3O3 O H11NM 1E4 20081229 EA 2008 12 29 CA081211002 320080116G6111W69EK763 PROPELLER DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA TIP OF BLADE CRACKED W K NONE O OTHER ININSP/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 THE PROPELLER BLADE LEADING EDGE TIPS HAD AN INDICATION OF POSSIBLE ROCK CHIP DAMAGE OF APPROXIMATELY .2500 INCH IN LENGTH AND LESS THAN A .0625 INCH IN DEPTH. IT SHOULD ALSO BE NOTED THAT THE PREVIOUS CREW HAD REPORTED A SLIGHT ENGINE VIBRATION 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 EXTENDED INWARD APPROX 2 INCHES. BY APPLYING PRESSURE TO EITHER OPPOSING SIDES OF THE BLADE TIP THE CRACK BECAME VERY APPA1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20081229 EA 2008 12 29 CA081211003 320081110G6111W69EK763T PROPELLER DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA TIP OF BLADE CRACKED W K NONE O OTHER ININSP/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 TOWARDS THE ROOT. AN AME CONDUCTED A VISUAL INSPECTION UNDER 10X MAGNIFICATION AND VERIFIED THAT A CRACK EXISTED FROM THE CENTER OF THE NR1 BLADE TIP AND EXTENDED APPROX 2 INCHES INWARD TRAVELLING TOWARDS THE BLADE ROOT. THE AIRCRAFT WAS IMMEDIATELY REMOVED FROM SERVICE WHERE A NEW PROPELLER ASSEMBLY WAS INSTALLED. 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20090203 NM 2009 2 3 CA081211004 120081203G531085312397101 BRACKET DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE WINDOW CRACKED W O OTHER O OTHER NRNOT 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090206 EA 2009 2 6 CA081211005 120081204G533021530023 SKIN CNDAIRCL215 CL2156B11215 EA FUSELAGE CRACKED W K NONE O OTHER ININSP/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 53-30-00-103 REV A. 2H72 4T RTA14EA 20081222 CE 2008 12 22 CA081212002 120081205G2421 BEARING CESSNA421 421B 2076014CE CONT O520 GTSIO520H 17032SO ALTERNATOR FAILED W H DEACTIVATE SYST/CIRCUITS BH SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC CRCRUISE 1 CA 16 (CAN) IN CRUISE PILOT NOTICED SPARKS COMING FROM RT ENGINE. UPON EXAMINATION ON GROUND BY MX, ALTERNATOR OUTER BRG. FAILED. SHAFT DEFORMED FROM HEAT. FAILURE OF CRANKSHAFT ALTERNATOR DRIVE GEAR CAUSED MAJOR INTERNAL ENGINE DAMAGE. 1L72 3O3 O A7CE E7CE 20090203 NE 2009 2 3 CA081212003 220081212G7320J2009P03 PLUG CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE MFC LOOSE W K NONE K FLUID LOSS ININSP/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 OUT 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 IN THIS AREA. THIS PLUG IS NORMALLY NOT TOUCHED IN SERVICE, IT WOULD NORMALLY ONLY BE LOOKED AT DURING OVERHAUL OR BENCH CHECK. 2L72 4F4 FRTA21EA E15NE 20090203 CE 2009 2 3 CA081212004 120081209G3244301401311 TIRE CESSNA441 441 2076020CE GARRTTTPE331TPE33110N 29062NE MLG DEFECTIVE W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 184 (CAN) DEFECT IN SIDEWALL CAUSED SIGNIFCANT LOSS OF PRESSURE. 1L72 3T4 TRTA28CE E4WE 20090203 NE 2009 2 3 CA081212005 320081212G61116607122666 BLADE SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE ROTOL R389 R3894123F25 NE NR 2 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 389844641 (CAN) THE PROP IN QUESTION WAS REMOVED FOR DISASSEMBLY TO BE SENT FOR DELAMINATION BEYOND LIMITS TO THE MANUFACTURER. WHEN THE PROP ASSEMBLY WAS DISASSEMBLED, A RADIAL CRACK WAS DISCOVERED IN NR 2 BLADE MEASURING IN EXCESS OF 6 INCHES IN THE HUB OF THE BLADE S/N: SF340-132/234. IT WAS DISCOVERED VISUALLY AND HAS SUBSEQUENTLY BEEN SENT FOR REPAIR TO THE MANUFACTURER. 2L72 4T4 TRTA52EU E8NE6 6 CP30NE 20090203 NE 2009 2 3 CA081212006 220081209G7210310838801 WASHER PWC DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE NR 9 BEARING CRACKED W K NONE O OTHER ININSP/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 TAB. IN CONSULTATION WITH MANUFACTURER THE COMPONENT WAS GIVEN A 10 HOUR REINSPECT, .10 HOUR, REINSPECT COMPLETED WITH NO FURTHER ANOMALIES. 2H72 4T4 TRTA13NM E20NE 20090203 2009 2 3 CA081212007 220081027G74144372 STOP PIN MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 764 (CAN) EXCESSIVE WEAR WAS NOTED ON IMPULSE COUPLING STOP PIN. 20090206 2009 2 6 CA081212008 220081212G74144372 STOP PIN MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 328 (CAN) EXCESSIVE WEAR WAS NOTED ON IMPULSE COUPLING STOP PIN. 20090203 CE 2009 2 3 CA081212010 120081209G3260 WARNING LIGHT BEECH 200 200BEECH 1152920CE MLG UNKNOWN W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) ON DEC 9TH, RETURNING FROM KGEG TO CYYC - ON TAKEOFF, WHEN THE GEAR WAS RETRACTED, THE FLIGHT CREW NOTICED THE "RED" 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 FLIGHT CREW DID A VISUAL INSPECTION OF EACH MAIN GEAR WHEEL AND CONFIRMED THAT THE MAIN WHEELS WERE INDEED UP. AT ALTITUDE, THE FLIGHT CREW CYCLED THE GEAR ONCE MORE AND THE LIGHTS WENT OUT INTERMITTENTLY, BUT SHORTLY AFTER STARTED TO COME ON AGAIN. THE FLIGHT CREW MAINTAINED THE GEAR EXTENSION SPEED OF 181KTS FOR THE REMAINDER OF THE FLIGHT. OTHER THAN HAV1L72 4T A24CE 20090203 CE 2009 2 3 CA081212011 120081204G8000C2925010105 SWITCH CESSNA150 150M 2071830CE CONT O200 O200A 17020SO MCAULY1A102 1A102OCM GL STARTER UNSERVICEABLE W O OTHER MBHOVER TEMP SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC NRNOT 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 REMAIN ENGAGED UNTIL IT SMOKED. REPLACED SWITCH WITH NEW, ALL CORRECT. 1H71 3O3 O 3A19 E252 5 NP918 20090203 EU 2009 2 3 CA081212013 220081006G7210 SPLINE ROTAX ROTAX 912 ROTAX912F3 EU PROP SHAFT CHIPPED W K NONE O OTHER ININSP/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 HALF. IF RING HALF WAS INSTALLED WITH THIS STEP RESTING ON THE RING SURFACE IT COULD CAUSE A STRESS POINT. THERE IS A SLIGHT 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 420081117G256297A256000000 ELT CABIN MALFUNCTIONED W O OTHER O OTHER NRNOT 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 120081213G28208SC0764 CHECK VALVE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA FUEL SYSTEM FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) DURING THE UNSCHEDULED REMOVAL OF THE NR 2 ENGINE FUEL FLOW TRANSMITTER, RESIDUAL AIRFRAME FUEL WOULD NOT STOP FLOWING. 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. 2H72 4T4 TRTA13NM E00062EN 20090203 2009 2 3 CA081215003 420081209G611305503214 SPINNER CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 148 (CAN) CRACKS PERPENDICULAR TO TOP OF PROP BOLT HOLES BARELY VISIBLE TO THE NAKED EYE, CONFIRMED WITH LPI. 1H71 3O3 ONT3A12 E274 5 NP910 20090203 EA 2009 2 3 CA081215009 120081210G2750855D10011 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 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 INDICATING 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 AIRCRAFT LANDED BACK WITHOUT INCIDENT. MAINTENANCE PULLED FECU CODES (SEE ATTACHED) WHICH INDICATED R BPSU OR WIRING. TH2L72 4F4 FRTA21EA E15NE 20090203 SW 2009 2 3 CA081216001 120081110G5311206033107117 FRAME BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL FUSELAGE CRACKED W K NONE O OTHER ININSP/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. 1G71 3U3 U H2SW E1GL 20090203 SW 2009 2 3 CA081216002 120081110G5311206033302031 FRAME BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL FUSELAGE CRACKED W K NONE O OTHER ININSP/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. 1G71 3U3 U H2SW E1GL 20090203 EA 2009 2 3 CA081216003 220081211G7200 ENGINE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA MAKING METAL W K NONE O OTHER ININSP/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 CONFIRMED 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 WINNIPEG FOR FURTHER INVESTIGATION AND REPAIR. TSO 3823.0, CSO 2033 (TTSN AND TCSN UNAVAILABLE AS LOG BOOKS ARE AT OVERHAUL FACILITY). 1L72 4T4 T A24CE E4EA 20090203 SW 2009 2 3 CA081216004 120081214G56102719442004 WINDSHIELD SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP COCKPIT CRACKED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA 3686 (CAN) DURING TAXI AS THE CREW TURNED INTO A 35 KNOT HEADWIND THE FIRST OFFICER WINDSHIELD SHATTERED. THE WINDSHEILD HEAT WAS SELECTED TO LOW AND THE OUTSIDE AIR TEMPERATURE WAS -36 DEGREES CELCIUS. MAINTENANCE REPLACED THE WINDSHIELD IN ACCORDANCE WITH THE AMM AND WAS RELEASED TO SERVICE. 2L72 4T4 TRTA8SW E4WE 20090203 EA 2009 2 3 CA081216005 120081212G2750 FCU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) FLAPS FAILED AT 3 DEGREES ON APPROACH. NORMAL LANDING FOLLOWED. CREW ABLE TO RESET SYSTEM ON THE GROUND AND FLIGHT CONTINUED UNDER MEL. SECOND FLAP FAILURE ON AIRCRAFT 107 IN AS MANY FLIGHTS. FLAPS FAILED AT 23 DEGREES INBOUND. NORMAL LANDING OCCURRED. MX RECTIFICATION TO FOLLOW ALL ACTUATORS REPLACED, RT BPSU REPLACED, LT NR 3 FLAP FLEX DRIVE REPLACED, RT NR 1AND NR 4 FLAP FLEX DRIVES REPLACED. A/C THEN HAD TEST FLIGHT AND HAD ANOTHER FAILURE AT 38 DEGREES EXTENSION. FLAP ELECTRONIC CONTROL UNIT AND FLAP PDU REPLACED AND A/C TEST FLIGHT WAS SUCCESSFUL. A/C RETURNED TO SERVICE DEC 18,2008. 2L72 4F4 FRTA21EA E15NE 20090203 NE 2009 2 3 CA081217001 220081213G7230 COMPRESSOR BOEING737 737201 1384454NM PWA JT8 JT8D17 52049NE NR 2 ENGINE FOD W C ABORTED TAKEOFF CA F.O.D. FLAME/FIRE TOTAKEOFF 1 CA CFJLB43057 (CAN) AIRCRAFT WAS ON TAKEOFF ROLL WHEN THE PILOTS HEARD A LOUD BANG FROM ENGINE NR 2 & EXPERIENCED A YAW TO THE RIGHT AS THEY APPROACHED 110 KNOTS. THE PILOTS THROTTLED BACK, ABORTED THE TAKEOFF, TAXIED BACK TO THE RAMP AND SHUTDOWN THE ENGINES. PASSENGERS OBSERVED FLAMES EXPEL FROM NR 2 ENGINE INLET AND EXHAUST WHEN THE BANG OCCURRED. CONDUCTED AN INITIAL VISUAL INSPECTION AND FOUND PART OF A RUBBER SEAL MISSING AND DETACHED FROM THE C2 INLET GUIDE VANE. THERE IS NO DAMAGE 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. 2L72 4F4 F A16WE E2EA 20090203 EA 2009 2 3 CA081217002 120081216G3230 LANDING GEAR CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C5 30050NE LEFT INOPERATIVE W O OTHER J WARNING INDICATION LDLANDING 1 CA (CAN) LANDED WITHOUT LT MLG NOT FULLY EXTENDED. THE FLT CREW ATTEMPTED TO EXTEND GEAR, BUT NEVER GOT A LT MLG GREEN DOWN 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. 2L72 4F4 FRTA21EA E00063EN 20090203 EA 2009 2 3 CA081217003 120081216G2120601R95655 DUCT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE CABIN AIR FAILED W B EMER. DESCENT J WARNING INDICATION CRCRUISE 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 OXYGEN 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 BEHIND THE APU INTO THE AFT PRESSURE BULKHEAD BLOWN. THEY ARE ORDERING PARTS AND WILL REPAIR ACCORDINGLY 17- O2 GENERATORS WERE ACTIVATED. 2L72 4F4 FRTA21EA E15NE 20090203 EA 2009 2 3 CA081217004 120081213G3260 PROXIMITY SENSOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE MLG OUT OF ADJUST W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA 19856 (CAN) ON TAKEOFF WHEN THE LANDING GEAR WAS SELECTED UP, THE EICAS DISPLAYED "GEAR DISAGREE" MSG FOLLOWED BY "NOSE GEAR DOOR" 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 THEN FERRIED WITH GEAR DOWN AND PINNED. MAINTENANCE READJUSTED THE PROX SENSOR TARGET FOR PROX SENSOR PS14GA (NOSE GEAR EXTEND/CENTER PROX SENSOR) AND THE SYSTEM CHECKED NORMAL. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20090203 NE 2009 2 3 CA081217005 220081210G7261 SCREEN CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE RT ENG OIL CONTAMINATED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 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 COKED UP CAUSING RESTRICTION. CLEANED SCREENS IN ACCORDANCE WITH EO 8/016/479 AND REINSTALLED PUMP IN ACCORDANCE WITH AMM 79-21-01. OPS CHECKS CARRIED OUT AND NO FURTHER DEFECTS NOTED. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20090203 CE 2009 2 3 CA081217006 120081215G324061702935 CONTROL CABLE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE PARKING BREAK FAILED W K NONE O OTHER ININSP/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 PARK BRAKE TO NOT RELEASE. THIS CABLE IS POST SB 550-32-50. 1L72 4F4 F A22CE E1NE 20090203 CE 2009 2 3 CA081217007 120081206G2750MS250261 LIMIT SWITCH BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA TE FLAPS FAILED W GA O2 MASK DEPLOYED UNSCHED LANDING BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB, JUST BEFORE 10000 FT, CREW NOTICED ODOR OF ELECTRICAL SMOKE IN COCKPIT. AS ACFT LEVELED OFF AT 10000 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 WOULDN`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 THE FLAPS WERE NOT ALL THE WAY UP. MOTOR OVERHEATED BEFORE TRIPPING THE CIRCUIT BREAKER, CAUSING THE ELECTRICAL SMOKE O1L72 3T4 T A14CE E4EA 20090203 SW 2009 2 3 CA081217008 120081201G5302206020113215A TAIL BOOM BELL 407 407 1182206SW DAMAGED W K NONE O OTHER ININSP/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. 1G71 3U O H2SW 20090203 NM 2009 2 3 CA081217011 120081215G5610NP15790113 WINDSHIELD DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 16661 (CAN) DURING CLIMB LT WINDSHIELD CRACKED. AIRCRAFT RETURNED TO DESTINATION AIRPORT. UNEVENTFUL LANDING. MAINTENANCE REPLACED THE DAMAGED WINDSHIELD AND THE AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090203 EU 2009 2 3 CA081217012 120081217G32134321012188 BEARING PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG STRUT WORN W K NONE O OTHER ININSP/MAINT 1 CA 6340 (CAN) RIGHT MAIN LANDING GEAR SHOCK ABSORBER STRUT LOWER BEARING WORN AND LOOSE INTERNALLY. REPLACED WITH NEW. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20090203 EU 2009 2 3 CA081217013 120081208G7930 OIL SYSTEM AEROSPATR72 ATR72 EU PWA PW120 PW127 NE ENGINE LOW PRESSURE W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF, THE PILOT NOTICED A LOW OIL PRESSURE INDICATION. THE ENGINE WAS SHUTDOWN AND THE FLIGHT RETURNED 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. 2H72 4T4 TRT E20NE 20090203 NE 2009 2 3 CA081217014 220081208G7200 ENGINE FOKKERF27 F27MK500 4990629EU PWA PWA120PW125B NE MAKING METAL W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 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 POINT OF DEPARTURE FOR AN UNEVENTFUL SINGLE LANDING. GROUND INSPECTION SHOWED OIL FILTER BYPASS INDICATORS ACTIVATED AND METAL WAS FOUND ON THE CHIP DETECTORS. A RECOMMENDATION TO REMOVE THE ENGINE HAS BEEN MADE. 2H72 4T4 T A817 E20NE 20090203 SW 2009 2 3 CA081217015 120081210G6320 HOUSING BELL 412 412EP 1182205SW PWA PT6T PT6T3 52045EA M/R GEARBOX CRACKED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, OIL PRESSURE WAS LOST ON THE COMBINING GEARBOX AND THE PILOT PERFORMED AN UNSCHEDULED LANDING OFF BASE. 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 PROVIDED IN DUE COURSE. 1G72 4U4 U H4SW E22EA 20090203 SW 2009 2 3 CA081217016 120081212G2435M2040AC2 BEARING BFGOODRICH SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP STARTER GEN FAILED W O OTHER J WARNING INDICATION CRCRUISE 1 CA 822 (CAN) STARTER GENERATOR FAILED IN FLIGHT CAUSING THE RT GEN FAIL LIGHT TO ILLUMINATE. UPON LANDING AND INSPECTION BY MAINTENANCE THE GENERATOR WAS FOUND TO HAVE DAMAGE RELATED TO COMPONENT FAILURE. THE GENERATOR WAS REPLACED AND SENT TO PERIMETER`S OVERHAUL FACILITY. THE TEARDOWN REPORT INDICATES FAILURE OF BOTH GENERATOR BEARINGS (PN M2040AC-2). GENERATOR WAS LAST INSPECTED AT 487.6 HOURS IN ACCORDANCE WITH THE MANUFACTURERS CMM SINCE LAST OVERHAUL AND PASSED THE INSPECTION AND WAS RETURNED TO SERVICE. AT 822.4 THE BEARINGS FAILED CAUSING THE GENERATOR SYSTEM FAILURE. BOTH THE STATOR AND ARMATURE ASSY WERE DAMAGED BEYOND REPAIR. NO DEFINITIVE CAUSE CAN BE DETERMINED. 2L72 4T4 TRTA8SW E4WE 20090203 GL 2009 2 3 CA081218001 120081208G5512 SKIN DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912F3 EU HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/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 SHOP (XU AVIATION) FOR FURTHER EVALUATION AND REPAIR. 1L71 3O3 ONTTA4CH E00051EN 20090203 2009 2 3 CA081218003 420081216G31608221917202 DISPLAY CNDAIRCL604 CL604 1900301EA GE CF34 CF343B 30069NE COCKPIT MALFUNCTIONED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CRCRUISE 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 (PPOS, 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 CHANGING ON THEIR OWN, SOMETIMES THE FREQUENCIES WOULD BE GREEN OR AMBER ON BOTH CDUS TUNING PAGE AND MFDS RADIO MENUS. THE 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 C2L72 4F4 FRTA21EA E15NE 20090203 SO 2009 2 3 CA081218004 120081201G3245 TUBE PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA TIRE FAILED W O OTHER E VIBRATION/BUFFET LDLANDING 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 COMPANY IS INSTALLING A PROCEDURE FOR INSPECTING NEW TUBES BEFORE INSTALL AS WELL AS PROPER WHEEL BUILD UP PROCEDURES. THE COMPANY IS ALSO IMPLEMENTING A 12 MONTH INSPECTION AND REPLACEMENT SCHEDULE FOR THE NOSEWHEELS ON THE NAVAJO AIRCRAFT. 1L72 3O3 O A20SO E14EA 20090203 EA 2009 2 3 CA081218005 120081217G2752 ACTUATOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) FLAP FAIL ON APPROACH. WHEN FLAPS SELECTED THE FLAPS DID NOT MOVE FROM ZERO DEGREES. FLAPLESS APPROACH AND LANDING 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 CLEANED AND RELUBED. LT NR 1 FLAP DRIVE FOUND WITH MOISTURE CONTAMINATION-CLEANED AND RELUBED. LT NR 5 FLAP DRIVE DEFORMED BEYOND LIMITS. REPLACED FLAP POWER DRIVE UNIT. ACFT TEST FLOWN SUCCESSFULLY AND RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20090203 SW 2009 2 3 CA081218006 120081217G79318974072 BYPASS VALVE SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP OIL FILTER LEAKING W O OTHER K FLUID LOSS TXTAXI/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 EVENTUALLY DETERMINED BY MAINTENANCE STAFF TO BE THE OIL FILTER BYPASS PIN. THE PIN POPS OUT IF THE OIL SYSTEM BECOMES CONTAMINATED. 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 THE LEAK FROM THE BYPASS PIN AREA. PRELIMINARY REPORT, THE DEFECT IS BEING REPAIRED NOW. UNKNOWN TSO ON THE PART, HOWEV2L72 4T4 TRTA8SW E4WE 20090203 2009 2 3 CA081222007 420081219G2350164ZS01Y AUDIO PANEL AMD FALC10FALCON10 2730101EU GARRTTTFE731TFE7312 01518WP COCKPIT MALFUNCTIONED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA 6069 6069 (CAN) DURING THE BASIC INSPECTION WITH AIRCRAFT POWER ON, FUMES AND LIGHT SMOKE WHERE NOTICED IN THE COCKPIT. AFTER INSPECTION 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. 2L72 4F4 F A33EU E6WE 20090203 SW 2009 2 3 CA081222008 120081208G6730222382001101 SERVO BELL 222 222U 1182140SW LYC LTS101LTS101750C1 41560NE UNKNOWN W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) SOLID RESISTANCE FELT WITH AFT CYCLIC MOVEMENT DURING OPERATIONS WITH FORCE TRIM ON & UTILIZING CYCLIC TRIM RELEASE SWITCH. ON FIRST OCCURRENCE RESISTANCE RELEASED WITH A FIRM BUMP & FAULTY LT CYCLIC TRIM RELEASE SWITCH SUSPECTED HOWEVER WITH SECOND OCCURRENCE SWITCHING FORCE TRIM OFF HAD NO EFFECT & RESISTANCE ONCE AGAIN RELEASED WITH A FIRM BUMP AFTER SEVERAL SECONDS. ALL THE MAIN ROTOR CONTROLS WERE INSPECTED FOR FREEDOM OF MOVEMENT & TRAVEL, NO DEFECTS NOTED. A GPU 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 1G72 3U3 U H9SW E5NE 20090203 NM 2009 2 3 CA081222009 120081218G242131708001A GENERATOR DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NR 1 AC MALFUNCTIONED W A UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CLCLIMB 1 CA 260711768 (CAN) SHORTLY AFTER TAKE OFF, THE FLIGHT CREW RECEIVED "NR 1 AC GEN" AND "NR 2 AC GEN" CAUTION LIGHTS. SYSTEMS WERE RESET 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. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090203 CE 2009 2 3 CA081222010 120081221G561010138402523 WINDSHIELD BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 4500 (CAN) WINDSHIELD CRACKED AFTER TAKEOFF, CRACKS EMANATED VERTICALLY FROM THE BOTTOM INBOARD EDGE. UNIT TTSN 4500 HOURS. 2L72 4T4 T A24CE E4EA 20090203 NE 2009 2 3 CA081223001 220081219G7230311194301 BEARING PWA 118 PW118 NE NR 3 FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) NR 3 BEARING FAILURE FOUND AT DISASSEMBLY. 4 T E20NE 20090203 NE 2009 2 3 CA081223002 220081217G7200MS945226 BEARING PWA PW120 PW123 NE ENGINE SEIZED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) ENGINE BEARING SEIZED. 4 T E20NE 20090203 2009 2 3 CA081223004 420081221G34604082499902 COMPUTER BOEING737 737800* NM FLIGHT CONTROL MALFUNCTIONED W L ABORTED APPROACH F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) CREW REPORT STABILIZER LIGHT CAME ON. ATC INFORMED AND CREW BROKE OFF APPROACH AND DETERMINED THAT THERE WAS NO STABILIZER TRIM. AIRCRAFT RETURNED TO AIRPORT AND CONDUCTED A SAFE LANDING. MAINTENANCE TROUBLESHOT REPORTED SNAG AND FOUND FAULT APPEARED TO LIE WITH THE FLIGHT CONTROL COMPUTER. UNIT REPLACED AND SYSTEM CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE. 2L72 4F RTA16WE 20090203 EA 2009 2 3 CA081223005 120081208G5531215221182 RIB CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE VERTICAL STAB CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) CRACK 35 MM LONG ON RIB OF VERTICAL STAB AT WL 396. 2H72 4T4 TRTA14EA E20NE 20090203 GL 2009 2 3 CA081223007 120081123G7921AE7010101H0114 HOSE DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO OIL COOLER LEAKING W K NONE K FLUID LOSS ININSP/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 INSPECTED MY MAINTENANCE, IT WAS DETERMINED THAT THERE WAS A SIGNIFICANT OIL LEAK. FURTHER INVESTIGATION REVEALED THAT THE 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, TESTED AND RETURNED TO THE MANUFACTURER FOR ANALYSIS. 1L71 3O3 ONTTA4CH E7SO 20090203 NE 2009 2 3 CA081223008 220081223G741422021081806 BEARING ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO LACK OF LUBE W K NONE O OTHER ININSP/MAINT 1 CA 474 (CAN) MAG RECEIVED FOR 500 HR INSPECTION, ROTATING MAGNET SHAFT SPUN BEFORE DISASSEMBLY TO INSPECT BEARING CONDITION & PRELOAD. NO END PLAY OR ROUGHNESS FELT, WHEN MAG WAS DISASSEMBLED, DISCOVERED THAT AT O/H IN SEPT 2007. NO GREASE HAD BEEN PACKED INTO BEARINGS. BEARINGS WERE LUBRICATED BY OIL THAT EACH BEARING IS PACKAGED WITH WHEN NEW. ONLY OTHER SOURCE OF LUBRICATION WAS A SMALL AMOUNT OF OIL THAT HAD LEAKED INTO MAG PAST OIL SEAL. LACK OF LUBRICATION COULD CAUSE MAGNETO & ENGINE FAILURE, EVEN THOUGH BEARINGS DID NOT APPEAR DAMAGED THEY WERE REPLACED, MAG WAS RETURNED TO SERVICE. 1G71 3O3 O H11NM 1E4 20090203 EA 2009 2 3 CA081229001 120081225G561004093H1031 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 1057510575 (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 INSPECTION OF THE WINDSHIELD INDICATES THAT THE EXTERNAL AND INTERNAL LAYERS ARE CRACKED. 2L72 4F4 FRTA21EA E15NE 20090203 GL 2009 2 3 CA081229003 220081224G732323070101 GOVERNOR BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL ENGINE FAILED W BA EMER. DESCENT UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CLCLIMB 1 CA 1419 (CAN) PILOT ENCOUNTERED HIGH SIDE GOVERNOR FAILURE. TORQUE INCREASED FROM 85 TO 100 PERCENT DURING CLIMB WITH NO COLLECTIVE 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. REPLACEMENT OF GOVERNOR CURED PROBLEM AFTER TROUBLESHOOTING IN ACCORDANCE WITH ROLLS ROYCE 250 C30P MM. REMOVED GOVERNOR WILL BE SENT TO REPAIR STATION FOR INSPECTION. 1G71 3U3 U H2SW E1GL 20090203 EA 2009 2 3 CA081229004 120081226G5210601R317047 HANDLE CNDAIRCL600 CL600* 1900302EA GE CF34 CF348C5 30050NE PAX DOOR BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 1081110811 (CAN) WHEN GROUND CREW ATTEMPTED TO OPEN AIRCRAFT FOR MORNING DEPARTURE, OUTER DOOR HANDLE SNAPPED OFF IN HIS HAND. MAINTENANCE INSPECTED AND REPLACED MAIN CABIN DOOR HANDLE ASSEMBLY AND FUNCTION CHECKED AS PER MANUFACTURERS MAINTENANCE MANUAL. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E00063EN 20090203 NE 2009 2 3 CA081231001 220081229G7200 ENGINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NR 1 OVERTORQUED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB THE CREW OBSERVED AN OVERTORQUE ON THE NR 1 ENGINE, THE POWER LEVER WAS REDUCED AND THE ENGINE STABILIZED AROUND 93 PERCENT OF TORQUE BEFORE RAISING AGAIN. DECISION WAS MADE TO PERFORM AN INFLIGHT SHUTDOWN. THE CREW DECLARED AN EMERGENCY, RETURNED TO THE AIRPORT AND LANDED WITHOUT FURTHER INCIDENT. IT IS UNKNOWN AT THIS TIME WHAT HAS CAUSED THE ENGINE OVERTORQUE. THE ENGINE IS BEING REPLACED AND WILL BE SHIPPED TO AN OVERHAUL FACILITY. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090203 NE 2009 2 3 CA081231002 220081231G7414GE5298 DRIVE GEAR BOSCH PWA R985 R985AN14B 52008NE MAGNETO WORN W D RETURN TO BLOCK RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/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 EXCESSIVE WEAR ON KY11-14 - KEY WOODRUFF FOR DRIVE GEAR. 3 R 5E1 20090203 CE 2009 2 3 CA081231003 120081221G561010138402524 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) WINDSHIELD CRACKED AS AIRCRAFT CLIMBED OUT OF YYC. AIRCRAFT RETURNED TO YYC. MAINTENANCE REPLACED WINDSHIELD AND RETURNED AIRCRAFT TO SERVICE. 1L72 4T4 T A24CE E4EA 20090203 CE 2009 2 3 CA081231004 120081221G561010138402523 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA COCKPIT CRACKED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) AFTER START PILOT NOTED THAT THE WINDSHEILD WAS CRACKED. ENGINES WERE SHUT DOWN AND MAINTENANCE REPLACED THE WINDSHEILD AND RETURNED THE AIRCRAFT TO SERVICE. 1L72 4T4 T A24CE E4EA 20090203 EA 2009 2 3 CA090102002 120081224G2750 FLAP SYSTEM CNDAIRCL604 CL604 1900301EA GE CF34 CF343B 30069NE TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) ON APPROACH THE FLAP FAILED TO EXTEND AND THE AIRCRAFT DIVERTED WHERE THEY LANDED WITH THE FLAPS UP. UPON INSPECTION 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. 2L72 4F4 FRTA21EA E15NE 20090203 CE 2009 2 3 CA090102004 120081231G531097430000149 DOOR FRAME BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE BS 201 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 6727 (CAN) WHILE CARRYING OUT SPECIAL INSPECTION, INSPECT ESCAPE HATCHES AND ASSOCIATED CLOSURE AREA. FOUND THE RT AFT EMERGENCY 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 FIRST 1000 LANDING REPETITIVE INSPECTION AFTER THE INITIAL 5000 LANDING INSPECTION. PART WILL BE REPLACED WITH FACTORY NEW PART. 2L72 4T4 T A24CE E4EA 20090203 CE 2009 2 3 CA090105001 120081208G3210 STRUCTURE CESSNA172 172M 2072418CE LYC O360 O360A4M 41514EA MLG WORN W O OTHER O OTHER NRNOT REPORTED 1 CA 15 (CAN) WORN ATTACH HOLE, CAUSING FORE AND AFT MOVEMENT OF THE WHEEL. 1H71 3O3 ONT3A12 E286 20090203 CE 2009 2 3 CA090105002 120081224G561050420066103 WINDOW BEECH 100 100BEECH 1152916CE PWA PT6 PT6A34 52043EA HARTZLHCB4T HCB4TN3 GL COCKPIT FAILED W BG EMER. DESCENT O2 MASK DEPLOYED O OTHER CRCRUISE 1 CA 15865 (CAN) AT 16000 FT LEVEL CRUISE, WINDOW FAILURE OCCURRED, COMPLETE WINDOW FAILED LEAVING ONLY APPROX 2 INCHES OF WINDOW ATTACHED TO AIRFRAME WINDOW SEAL STAYED ATTACHED TO AIRFRAME. CRAZING, PITS AND SCRATCHES REMOVED FROM WINDOW FEB 10, 2000, WINDOW MEASURED AFTER REPAIR. .304-.321, COMPLETED BY AVGLASS USA. 1L72 3T4 T A14CE E4EA 6 CP40EA 20090203 EA 2009 2 3 CA090105006 120081231G2750865D1007 DRIVE UNIT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE TE FLAPS FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA 1496314963 (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 DUE 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. 2L72 4F4 FRTA21EA E15NE 20090203 NM 2009 2 3 CA090105007 120081220G6120699018002 PCU BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NO 1 ENGINE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) POWERPLANT INDICATION ON ED NR 1 TRU AND AC GEN ZERO INDICATION WHILE TAXIING. ACTION TAKEN AT MNL, RETRIEVE FAULT 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. 2H72 4T4 TRTA13NM E00062EN 20090203 CE 2009 2 3 CA090105008 120081224G5540 ATTACH BRACKET CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160CTM GL RUDDER WEIGHT BROKEN W K NONE O OTHER ININSP/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 BALANCE 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. 1H71 3O3 ONT3A12 E274 5 NP910 20090203 EA 2009 2 3 CA090105009 120081229G2752852D10019 ACTUATOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE TE FLAPS MALFUNCTIONED W D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/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 COMPLETED, RIGGING AND FUNCTION CHECKS COMPLETED, AND A/C SUCCESSFULLY TEST FLOWN AND RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20090203 EA 2009 2 3 CA090105012 220081210G7200 ENGINE BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA COKED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING FLIGHT, THE CREW OBSERVED A RAPID RISE IN ENGINE TEMPERATURE AND TORQUE WITH FLAMES COMING OUT THE RIGHT ENGINE 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 VANE, CT BLADES HEAVILY ERODED AND HEAVY CARBON DEPOSITS ON THE COMBUSTION LINER. WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L72 3T4 T A14CE E4EA 20090204 2009 2 4 CA090105014 120081217G6123 AUTOFEATHER SYS PWA PW120 PW124B NE MALFUNCTIONED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB THE ENGINE TORQUE DROPPED TO 22 PERCENT AND THEN ZERO. THE ENGINE WAS SECURED AND THE A/C RETURNED TO THE POINT OF DEPARTURE, WHERE A SINGLE ENGINE LANDING WAS PERFORMED. POST FLIGHT TROUBLESHOOTING LED TO THE REPLACEMENT OF THE AUTO FEATHER UNIT BEFORE THE ACFT WAS RETURNED TO SERVICE. WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 4 T E2ONE 20090204 WP 2009 2 4 CA090106002 120081223G3260 DOWNLOCK SWITCH CVAC 340 340CVAC 242270AWP ALLSN 501D 501D13D 03004GL MLG OUT OF ADJUST W L ABORTED APPROACH N FALSE WARNING APAPPROACH 1 CA (CAN) ON APPROACH, CREW EXPERIENCED A LT GEAR UNSAFE LIGHT. AFTER DETERMINING THE GEAR TO BE DOWN, ACFT LANDED UNEVENTFULLY. MAINTENANCE ADJUSTED THE DOWN LOCK SWITCH AND ACFT WAS RETURNED TO SERVICE 2L72 4R4 T 6A6 E282 20090206 SO 2009 2 6 CA090107004 120081223G57124042306 RIB PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA LT WING CRACKED W K NONE O OTHER ININSP/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 COINCIDED WITH THE RIB CRACK. 1L72 3O3 O A20SO E14EA 20090206 EA 2009 2 6 CA090107006 120081229G5610 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 13762 (CAN) CAPTAINS SIDE WINDOW SHATTERED IN FLIGHT. FOLLOWED QRH, DIVERTED TO NEAREST AIRPORT AND LANDED WITHOUT FURTHER INCIDENT. R&R CAPTAINS SIDE WINDSHIELD IAW AMM 56-11-01 AND CARRIED OUT LEAK CHECKS. ACFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20090206 2009 2 6 CA090107008 420081226G34178220372445 ADC CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE NR 1 MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 4396 (CAN) JUST AFTER TAKEOFF, THE CREW RECEIVED RED FLAGS FOR THE CAPTAINS AIRSPEED, ALTIMETER AND VSI MOMENTARILY. INDICATIONS 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. 2L72 4F4 FRTA21EA E15NE 20090206 EA 2009 2 6 CA090107009 120081222G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED APAPPROACH 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. 2L72 4F4 FRTA21EA E15NE 20090206 EA 2009 2 6 CA090107011 120081219G2750855D1009 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) EXPERIENCED FLAP FAILURE. REPLACED BPSU. 2L72 4F4 FRTA21EA E15NE 20090203 EA 2009 2 3 CA090107014 120081216G30205399001 ANTI-ICE VALVE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE FAILED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 12356 (CAN) FLT CREW REPORTED RIGHT COWL ANTI-ICE MESSAGE IN FLIGHT WITH ANTI-ICE SELECTED ON. COMPLETED QRH AND MESSAGE PERSISTED. DIVERTED AND LANDED WITHOUT FURTHER INCIDENT. REMOVED AND REPLACED RIGHT COWL ANTI-ICE VALVE AND OPS CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE. ANTI-ICE VALVE 5399-00-1 0186A FAILED RIGHT COWL 13148/12356 (VALVE TIMES). 2L72 4F4 FRTA21EA E15NE 20090203 EA 2009 2 3 CA090107015 120081215G4930600970249 LINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE APU FUEL SYSTEM CHAFED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 19855 (CAN) WHILE SERVICING APU MAINTENANCE NOTICED A FUEL SMELL. OPENED PANEL AND RAN APU. FOUND APU INLET BELLOWS RETAINING 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 RETURNED TO SERVICE. FUEL LINE 600-97024-9 N/A CHAFED APU COMPARTMENT 20830/19855. 2L72 4F4 FRTA21EA E15NE 20090203 EA 2009 2 3 CA090107016 120081022G492038004883 APU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 30070NE SMOKE W O OTHER B SMOKE/FUMES/ODORS/SPARKS LDLANDING 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). 2L72 4F4 FRTA21EA E15NE 20090203 EU 2009 2 3 CA090108002 120081229G3260A254210012 UPLOCK AIRBUS310 A310304 3930339EU GE CF6 CF680C2* GL NLG FAILED W O OTHER N FALSE WARNING DEDESCENT 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 GEAR DOOR SEQUENCE VALVE WERE REPLACED. 2L72 4F4 FRTA35EU E23EA 20090203 SW 2009 2 3 CA090108003 120081226G5310 DOOR FRAME BBAVIA7 7AC 2110102SW FUSELAGE CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA 2508 (CAN) DOOR TUBE RUSTED THROUGH LOWER END, REPLACED. 1H71 3O A759 20090203 NM 2009 2 3 CA090109002 120081214G79308D1437 PRESSURE SWITCH DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA (CAN) NR 1 ENG OIL PRESS WARNING LIGHT ILLUMINATION IN FLIGHT, ENGINE SHUTDOWN IN ACCORDANCE WITH QRH/AFM, AIRCRAFT RETURNED TO DEPARTURE AIRPORT AND LANDED SAFELY. MAINTENANCE DETERMINED NR 1 OIL PRESSURE SWITCH FAILED. SWITCH REMOVED AND REPLACED. ENGINE RUNS CARRIED OUT, OPERATION SATISFACTORY. AIRCRAFT RETURNED TO SERVICE. SWITCH MANUFACTURER (CUSTOM CONTROL SENSORS) NOT IN THE DROP DOWN LIST. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090204 CE 2009 2 4 CA090112004 120081214G2823C2915030101 SELECTOR CESSNA206 U206D 2073342CE CONT O520 IO520F 17032SO MCAULY2A34C D2A34C58 GL FUEL SYSTEM LEAKING W O OTHER O OTHER NRNOT REPORTED 1 CA 1085110851 (CAN) FUEL SELECTOR CLOSED DUE TO FLEX HOSES IN ENGINE COMPARTMENT BEING REPLACED. AFTER HOSES INSTALLATION FUEL SELECTOR 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 20090112004) 1H71 3O3 O A4CE E5CE 5 CP3EA 20090205 SO 2009 2 5 CA090112008 220081031G7414 GASKET BENDIX PIPER PA28 PA28R201T 7102813SO CONT O360 TSIO360FB 17025SO MAGNETO LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 23 (CAN) ENGINE INSPECTED FOR OIL LEAK AT REAR ACCESSORY SECTION, FOUND OIL COMING FROM RIGHT MAGNETO ATTACH GASKET. MAGNETO REMOVED, GASKET AND ENGINE MATING SURFACE INSPECTED OK. MOUNTING FLANGE ON MAGNETO INSPECTED AND FOUND CRACKED IN AREA WHERE BOTH HOLD DOWN CLAMPS MAKE CONTACT, FLANGE WAS ON THE VERGE OF BREAKING OFF COMPLETELY WHICH WOULD RESULT IN MAGNETO 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 FLANGES IS FROM OVERTORQUING HOLD DOWN CLAMP NUTS. (TC NR 20090112008) 1L71 3O3 O 2A13 E9CE 20090206 CE 2009 2 6 CA090116004 120081229G7500 MOTOR CESSNA500 560CESSNA 2076750CE PWC 545 PW545B NE HBV TORQUE FAILED W E ENGINE SHUTDOWN EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 CA 654577883 (CAN) THE CREW REPORTED VIBRATION ON RT ENGINE AND THE EEC REVERTED TO MANUAL MODE. THEY OBSERVED A SUDDEN RISE IN ENGINE 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. 2L72 4F4 FRTA22CE E00059EN 20090206 NE 2009 2 6 CA090116006 220081224G7250 TURBINE BLADES DHAV DHC8 DHC8301 1386003NM PWA 120 PW123D 52152NE ENGINE FRACTURED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 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 AND POWER TURBINE BLADES WERE FRACTURED. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA13NM E20NE 20090206 NE 2009 2 6 CA090116007 220081222G7200 ENGINE AEROSPATR72 ATR72 EU PWA PW120 PW127 NE POWER LOSS W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 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 WILL BE REMOVED AND INVESTIGATED. 2H72 4T4 TRT E20NE 20090206 NE 2009 2 6 CA090116008 220081229G7200 ENGINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE MAKING METAL W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 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 LANDING WAS MADE AT THE POINT OF DEPARTURE. GROUND INSPECTION FOUND METAL PARTICLES IN THE OIL TANK. THE ENGINE WILL BE REMOVED. WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20090206 GL 2009 2 6 CA090119011 120081228G2421A3579101 GENERATOR BOMBDRBD100 BD1001A10 1390044GL HNYWL AS907 AS90711A 33908WP FAULTED W O OTHER H ELECT. POWER LOSS-50 PC LDLANDING 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) 2L72 4F4 FRTT00005NYE00010LA 20080325000602008032500060NM 2008 3 25 CO1Y200800001 120080307G5340ARB71701 SUPPORT FITTING DOUG MD11 MD11F 3023600NM MLG DOOR CORRODED B CO1YK NONE O OTHER ININSP/MAINT 1 EA33725BC 48503 AT LT MLG AND DOORS, FOUND BOLTS LOWER AND UPPER WITH PLI LOOSE ON LT FRAME SUPPORT. 2L73 4F RTA22WE 20080414000152008041400015NM 2008 4 14 CO1Y200800002 120080327G5510 STRUCTURE DOUG MD11 MD11F 3023600NM ZONE 400 CORRODED B CO1YK NONE O OTHER ININSP/MAINT 1 EA33725BC 48503 AT HORIZONTAL STABILIZER CTR SECTION, FOUND CORROSION INSIDE BARREL NUT HOLE NR 36 LT HORIZ STAB. 2L73 4F RTA22WE 20080428003182008042800318NM 2008 4 28 CO1Y200800003 120080114G5755ARC44231 HINGE BRACKET DOUG MD11 MD11 3023602NM LT SPOILER WORN B CO1YK NONE O OTHER ININSP/MAINT 1 EA33725BC 48503 LT SPOILER NR1 FOUND WITH PLAY. 2L73 4F RTA22WE 20080225000082008022500008NE 2008 2 25 CRSCW1R075K 120080221G64107610105017045 SPAR SKRSKY SKRSKYS76 S76B 8143007NE PWA PT6 PT6* 52043EA T/R BLADE CRACKED B K NONE O OTHER ININSP/MAINT 1 EA11780P 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, SPAR 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. 1G72 4U3 T H1NE E2NE 20080204001042008020400104CE 2008 2 4 CWQR200801 120080129G5330651201026 SKIN CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE FUSELAGE CRACKED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05839QS 5600690 DURING A PHASE 1-4 INSPECTION THE TECHNICIAN NOTICED A SMALL CRACK IN THE PAINT UNDER THE RT ENGINE PYLON. REMOVED THE PAINT 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. SUBMITTED TO MFG ENGINEERING FOR REPAIR. 2L72 4F4 FRTA22CE E00053EN 20080909 CE 2008 9 9 CWQR200808 120080821G5320661503517 SUPPORT BRACKET CESSNA560 560XL 2076702CE FUSELAGE CRACKED B CWQRK NONE O OTHER ININSP/MAINT 1 GL05679QS 5605279 DURING A PHASE 1-4 INSP, FOUND THE SUPPORT BRACKET CRACKED, CRACK IS LOCATED IN THE SUPPORT BRACKET FOR THE ECU, THE CRACK INTERSECTS A HOLE FOR THE NUTPLATE THAT ATTACHES ONE OF THE ECU MOUNTING BOLTS. SERVICE CONDITION REPORT HAS BEEN FILED WITH MFG UNDER SCR# 376154. 2L72 4F RTA22CE 20081001 CE 2008 10 1 CWQR200809 120080821G5320661503515 SUPPORT BRACKET CESSNA560 560XL 2076702CE FUSELAGE CRACKED B CWQRK NONE O OTHER ININSP/MAINT 1 GL05679QS 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) 2L72 4F RTA22CE 20080313000482008031300048SO 2008 3 13 DAL26220220 120080218G49101159AC30551103 DUCT GULSTMG1159 GIV 3980115SO APU INLET CRACKED E CLWAK NONE O OTHER ININSP/MAINT 1 SW05589HM6464 1153 A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM). 2L72 4F RTA12EA 20080317002522008031700252EU 2008 3 17 DJSR20080125 120080125G361032156321 PRESSURE VALVE AMD FALC20FALCON20C5 2730107EU GARRTTTFE731TFE731* 01518WP BLEED AIR SYS MALFUNCTIONED B DJSAA UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL23531FL15 113 NR 1 BLEED OVERHEAT LIGHT ILLUMINATED PASSING 15,000 WITH CORRESPONDING CABIN PRESSURE FLUCTUATIONS. 2L72 4F4 FRTA7EU E6WE 20080310003432008031000343EU 2008 3 10 DJSR20080205 120080205G5610MY20268109 WINDSHIELD AMD FALCONFALCON20 2730103EU GARRTTTFE731TFE731* 01518WP COCKPIT CRAZED D DJSRA UNSCHED LANDING O OTHER CLCLIMB 1 GL23541FL3 48 F/O`S WINDSHIELD OUTER PANE CRAZED OBSTRUCTING F/O`S VISION. (K) 2L72 4F4 FRTA7EU E6WE 20080320000212008032000021EU 2008 3 20 DJSR20080226 120080226G3231 MECHANISM AMD FALC20FALCON 2720302EU GARRTTTFE731TFE731* 01518WP NLG DOOR ICED B DJSAA UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION CLCLIMB 1 GL23521FL15493 68 NOSE GEAR DOOR WOULD NOT CLOSE IN FLIGHT. 2L72 4F4 F A7EU E6WE 20080428003442008042800344 2008 4 28 DJSR20080417 420080417G3417065008206 AIR DATA MODULE AMD FALC20FALCON20C5 2730107EU GARRTTTFE731TFE731* 01518WP COCKPIT MALFUNCTIONED B DJSAA UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 GL23511FL 68 122 ALTIMETER SYSTEMS SHOWING MISCOMPARE (EXCEEDING 50 FT AT 5000 FT). 2L72 4F4 FRTA7EU E6WE 20080122000892008012200089WP 2008 1 22 DSC4331DL6292 220080110G721031022811 RETAINER SEAL GARRTTTPE331TPE33110R 0517 WP ENGINE CRACKED B K NONE L NO TEST ININSP/MAINT 1 SO15 P37369C NO GEARCASE NEGATIVE PRESSURE INDICATED DURING ENGINE TEST STAND FUNCTIONAL TESTING. TROUBLESHOOTING FOUND CRACKS IN SEAL RETAINER. SUBJECT RETAINER IS MADE WITH ALUMINUM. OLDER PN 693905-10 IS MADE WITH STEEL. SB 72-0224 AUTHORIZED INSTALLATION OF ALUMINUM RETAINER. 4 T E4WE 20080603 EU 2008 6 3 DT1R200800001 120080508G27001090020477 LEVER AGUSTAA109 A109S 0260103EU YAW TRIM SYSTEM DAMAGED B K NONE O OTHER ININSP/MAINT 1 EA17167JC40 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. 1G71 3U RTH7EU 20080828 NM 2008 8 28 DU4R2008238 120080822G5322 SHEAR TIE DOUG MD80 MD83 3023681NM FS 148 L22L DAMAGED B DU4RO OTHER O OTHER NRNOT REPORTED 1 SO15874GA 49643 ACFT ARRIVED, WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE. (S) 2L72 4F RT 20080828 NM 2008 8 28 DU4R2008238A 120080822G5330 SKIN DOUG MD80 MD83 3023681NM FS 148 L22L DAMAGED B DU4RO OTHER W INADEQUATE Q C NRNOT REPORTED 1 SO15874GA 49643 ACFT ARRIVED, WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE. (S) 2L72 4F RT 20081201 NM 2008 12 1 DU4R2008263 120081124G531536726 FLOORBEAM BOEING737 7378Q8 13844BXNM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15171LF 30637 FOUND CORROSION IN AFT PIT ON TOP SURFACE OF FLOORBEAM AT BS 787 TO BS 847 RBL 16. 2L72 4F RTA16WE 20090105 NM 2009 1 5 DU4R2008273 120081213G5314 KEELBEAM BOEING757 75723APF 1384966NM BS 956 CORRODED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION AT TIMCO-LCQ, LAKE CITY, FL FOUND KEEL BEAM LOWER SURFACE CORSS BRACE HAS CORROSION AT BS 956S/O 318002 N/R #35360 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008274 120081213G5314 KEELBEAM BOEING757 75723APF 1384966NM BS 1040 CORRODED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND KEELBEAM LOWER SURFACE CROSS BRACE HAS CORROSION AT BS 1040. 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008275 120081216G5730 SKIN BOEING757 75723APF 1384966NM LT WING CORRODED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND LT WING HAD CORROSION IN UPPER SKIN AT ALL VORTEX GENERATORS 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008276 120081216G5330 SKIN BOEING757 75723APF 1384966NM BS 600-612 DENTED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND 3 EA. DENTS IN LOWER FWD FUSELAGE BELOW MLG DOOR SCUFF PLATE BS 600-612. 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008277 120081216G5330 SKIN BOEING757 75723APF 1384966NM BS 1125 DENTED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND DENT IN EXT. FUSELAGE SKIN BS 1125, S-10L LAP SEAM. 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008278 120081216G5330 SKIN BOEING757 75723APF 1384966NM BS 1364-1410 DAMAGED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND NUMEROUS CREASES IN EXT. FUSELAGE SKIN BS 1364 - 1410, S-26L TO S-26R 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008279 120081217G5711 SPAR BOEING757 75723APF 1384966NM LT WING CORRODED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION ON LT WING REAR SPAR BELOW LEFT AFT BOOST PUMP RSS 185. 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008280 120081217G5314 KEELBEAM BOEING757 75723APF 1384966NM BS 996 CORRODED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION ON KEELBEAM LOWER SURFACE CROSS BRACE AT BS 996. 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008281 120081216G5330 SKIN BOEING757 75723APF 1384966NM BS 1932-1936 CORRODED B R AUTOROTATION O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION ON EXT SKIN AROUND APU OIL FUEL DRAIN MAST RT APD ACCESS DOOR. 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008282 120081217G5320 SUPPORT BOEING757 75723APF 1384966NM BS 1098 CORRODED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION ON WING TO BODY FAIRING SUPPORT ABOVE RT WING AT BS 1098. 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008283 120081210G5320148N31388000 STRAP BOEING757 75723APF 1384966NM ZONE 300 CORRODED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND HEAVY CORROSION ON 2 EA. SUPPORT STRAPS REMOVED FROM BS 1825, B/O 0, RT SIDE TO HORIZ STAB. 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008284 120081217G5711112N100217 SPAR BOEING757 75723APF 1384966NM ZONE 500 CORRODED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION ON WEB, LT WING REAR SPAR, ABOVE LT AFT BOOST PUMP WS 188 2L72 4F RTA2NM 20090105 NM 2009 1 5 DU4R2008285 120081228G5512 SKIN BOEING757 75723APF 1384966NM ZONE 900 CORRODED B K NONE O OTHER ININSP/MAINT 1 SO15868AN 24868 DURING SCHEDULED INSPECTION, FOUND CORROSION IN SEVERAL AREAS OF UPPER SURFACE SKINS ON LT HORIZONTAL STABILIZER. 2L72 4F RTA2NM 20080828 NM 2008 8 28 DUR42008238B 120080822G5313 LONGERON DOUG MD80 MD83 3023681NM FS 148 L22L DAMAGED B DU4RO OTHER O OTHER NRNOT REPORTED 1 SO15874GA 49643 ACFT ARRIVED WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE. (S) 2L72 4F RT 20080508000972008050800097NM 2008 5 8 DXTA200803018 120080424G2613RP16100 SENSOR AMD FALC50FALCON2000 2730170NM PWC PW308 PW308C 52182NE BLEED AIR SYS INOPERATIVE E DXTAA UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL07223QS430 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 2L72 4F4 FRTA50NM E00065EN 20080715 CE 2008 7 15 E812008F00000 120080213G532050430043619 CHANNEL BEECH B300 B300 1159232CE FUSELAGE CRACKED B E81RK NONE O OTHER ININSP/MAINT 1 GL0337TD 6102 FL25 INVESTIGATED PILOT COMPLAINT OF LOOSE FUSELAGE SKIN RIVETS AT CABIN DOOR HINGE AREA. FOUND FUSELAGE DOOR FRAME CHANNEL CRACKED. CABIN DOOR DAMPER ACTION ALSO REPORTED AND FOUND TO BE WEAK. SUSPECT CAUSED BY CABIN DOOR "BOTTOMING OUT" EXCESSIVELY HARD OR EXCESSIVE WEIGHT ON DOOR OVER REPEATED CYCLES. TECH/ INSPECTORS SHOULD CHECK DOOR DAMPNER OPERATION AT SCHEDULED PHASE INSPECTIONS AND CORRECT IF WEAK OPERATION NOTED. EVIDENCE OF LOOSE HINGE AREA RIVETS SHOULD ALSO BE INVESTIGATED FOR POSSIBLE CRACKED STRUCTURE UNDER THRESHOLD. (K) 2L72 4T RTA24CE 20080508000912008050800091NE 2008 5 8 EY2R080424001 320080424G61117826761 BEARING EMB 120 EMB120 3260201SO HAMSTD14RF 14RF9 NE BLADE CRACKED B EY2RK NONE O OTHER ININSP/MAINT 1 GL03 (0087319) CRACKED RACE. 2L72 4T RTA31SO 6 CP11NE 20080114000412008011400041EA 2008 1 14 FAA010808001 220080108G7200MILH60001 BREATHER TUBE AYRES S2 S2RT15NORMAL0970105SO PWA PT6 PT6* 52043EA ENGINE COLLAPSED D K NONE O OTHER ININSP/MAINT 1 SO072281A7940 T15034 ENGINE BREATHER HOSE SWELLED ON INSIDE FROM THE ORIGINAL 1INCH DIAMETER TO .3750 INCH DIAMETER FROM HOT OIL FUMES. THRUSH 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. 1L71 3T3 T A3SW E2NE 20080131000072008013100007EU 2008 1 31 FAA011808001 220080104G7321CASC514 FUEL CONTROL GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU ENGINE INOPERATIVE C O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 EA25396U 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 ADVANCED FORWARD THE RT ENGINE DID NOT RESPOND TO THROTTLE MOVEMENT. 2L72 4F4 FRTA12EA E25NE 20080131000082008013100008SO 2008 1 31 FAA011808002 120080110G7930 OIL SYSTEM GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU ENGINE LOW PRESSURE D O OTHER J WARNING INDICATION CLCLIMB 1 EA17396U 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. 2L72 4F4 FRTA12EA E25NE 20080131002982008013100298CE 2008 1 31 FAA012408001 120080124G2710556536118 CABLE CESSNA500 550 2076604CE AILERON WORN B N81RK NONE O OTHER ININSP/MAINT 1 GL09338B 5501132 DURING A PHASE 5 IT WAS FOUND THAT THE AILERON CABLES WERE LOCATED IN THE WRONG GROVES OF THE FUSELAGE SECTOR, CAUSING GROOVES 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. 1L72 4F A22CE 20080312000032008031200003CE 2008 3 12 FAA021208001 120080212G2810 FUEL CAP CESSNA172 172 2072402CE DAMAGED D K NONE O OTHER ININSP/MAINT 1 GL15 4413 LEFT 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 SENDING UNIT LOCKING IT AT A 10 GAL. INDICATION. 1H71 3O NT3A12 20080414000012008041400001 2008 4 14 FAA030408001 120080304G4990 PUMP APU ENGINE FAILED B O OTHER J WARNING INDICATION NRNOT REPORTED 1 SW99 135991468 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 WAS NOTED. DISASSEMBLY OF THE OIL PUMP REVEALED PORT 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. 20080414000032008041400003CE 2008 4 14 FAA031008001 120080310G2497 WIRE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE COCKPIT ARCED B BA EMER. DESCENT UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 SW1743SA 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 ASSURE 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 PILOTS CONTROL COLUMN TO THE OB LT FWD AILERON CABLE. THE WIRE WAS NOT PROPERLY ROUTED OR SECURED. THE WIRE LAYS UNDERNEATH 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/1L72 4F4 F A22CE E1NE 20080403000422008040300042CE 2008 4 3 FAA08222001 120080222G25203037091BS SEAT RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE731* 01518WP MISINSTALLED B K NONE W INADEQUATE Q C ININSP/MAINT 1 CE01800RC 258660 DURING PRE-FLIGHT INSPECTION IT WAS NOTED THAT NR2 RT SEATBACK WOULD NOT BREAK OVER AND FOLD FWD IAW PLACARD TO REMOVE ESCAPE HATCH. THIS CONDITION PREVENTS ESCAPE HATCH FROM BEING EASILY REMOVED. FURTHER INVESTIGATION REVEALED THAT THE NR2 RT SEAT HAD BEEN SWAPPED WITH THE NR1 LT SEAT. SEATS ARE A DIFFERENT PN. THIS APPARENTLY HAPPENED AT LAST MAJOR MAINT, 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 TIME TO TIME. ACCOMPLISH AN IMMEDIATE INSP TO VERIFY THAT THE CORRECT PN SEAT IS IN THE NR2 RT POSITION AND CORRECT ANY2L72 4F4 FRTA3EU E6WE 20080129000112008012900011CE 2008 1 29 FAA20080118 120080118G2752505212234 ACTUATOR BEECH 90 C90 1152913CE PWA PT6 PT6A21 52043EA ZONE 600 CRACKED B K NONE O OTHER ININSP/MAINT 1 NM0985TB LJ833 RT OB FLAP ACTUATOR ASSY, PISTON TUBE CRACKED 100 PERCENT IN DEPTH, 100 PERCENT ENTIRE LENGTH OF TUBE. CRACK RUNS PARALLEL TO TUBE . 1L72 3T4 T 3A20 E4EA 20080402000272008040200027CE 2008 4 2 FAA2008123001 120080123G61205221220F PILOT VALVE WOODWARD BEECH 58 58 1152740CE CONT O550 IO550* SO PROP GOVERNOR BROKEN B E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 EA63401BC 697 00066 TH1668 PROPELLER WENT TO FEATHER IN FLIGHT AND WAS UNABLE TO UNFEATHER. AFTER RECEIVING THE GOVERNOR FOR INSPECTION IT WAS DISCOVERED THAT THE BOTTOM END OF THE PILOT VALVE (P/N 5221-220) HAD BROKEN OFF AND WAS MISSING. IT WAS PRESUMED THAT IT EXITED THE BOTTOM END OF THE DRIVE GEAR AND ENTERED THE ENGINE SUMP. THE OPERATOR WAS NOTIFIED AND THE MISSING PIECE WAS RETRIEVED. 1L72 3O3 O 3A16 E3SO 20081217 CE 2008 12 17 H51R08001 120081203G26202MD31AX287G SWITCH LEAR 35 31A 5170531CE EXTINGUISHERS STICKING B H51RK NONE L NO TEST ININSP/MAINT 1 NM03420LJ3052 111 FAILURE OF SWITCH IN THE ENGINE FIRE PULL SWITCH ASSY. AFTER ACCESSING THE FIRE PULL SWITCH ASSEMBLY TO VERIFY AIRWORTHINESS DIRECTIVE 95-21-03, AMENDMENT 39-9388, APPLICABILITY, THE S4 MICROSWITCH FAILED IN THE CLOSED POSITION. THE AIRWORTHINESS DIRECTIVE WAS ISSUED FOR THIS PROBLEM, BUT WAS NOT APPLICABLE TO THIS SWITCH BY S/N, SUSPECT ADDITIONAL LOTS MAY 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 POSITION. 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 2322L72 4F RTA10CE 20080402000372008040200037 2008 4 2 HN8R200800001 420080122G61226602263 CONTROL CABLE MOONEYM20 M20J 5870219SW LYC O360 IO360A1A 41514EA PROP GOVERNOR BROKEN B HN8RK NONE L NO TEST ININSP/MAINT 1 CE0558102298 243008 PROPELLER GOVERNOR CONTROL CABLE BROKE WHILE AIRCRAFT WAS ON GROUND. 1L71 3O3 O 2A3 1E10 20080404000032008040400003NM 2008 4 4 IU6R232726 120080306G2710654484515 MANIFOLD BOEING737 737 UTILSYSNM BROKEN B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 71885 FILTER BOWL BORE OF MANIFOLD BROKE OFF AT THE THREADS. 2L72 4F RTA16WE 20080522 2008 5 22 LJER050608 220080506G741410357424 BUSHING S4LSC200 ROBSINR22 R22BETA 7640110NM MAGNETO LOOSE B LJERK NONE O OTHER ININSP/MAINT 1 NM097155W531 531 E07DA122R 2759 ROTOR BUSHING DEBONDED AND LOOSE, CAUSED ROTOR AND GEAR PLAY. MAGNETO FAILED. 1G71 3O H10WE 20080508000252008050800025CE 2008 5 8 LJER210408 120080421G323312810016 HOUSING CESSNA172 172RG 2072438CE LYC O360 O360* 41514EA LT MLG ACTUATOR CRACKED B LJERA UNSCHED LANDING O OTHER CLCLIMB 1 NM099877B594 172RG1066 LANDING GEAR FAILED TO RETRACT. LT MAIN ACTUATOR HOUSING CRACKED AT MOUNTING HOLE. 1H71 3O3 O 3A17 E286 20080715 CE 2008 7 15 MT9R00000040 120080530G7603SL60061 POWER LEVER CESSNA208 208B 2073701CE PWA PT6 PT6* 52043EA ENGINE CONTROL BROKEN B MT9RO OTHER O OTHER NRNOT REPORTED 1 SW051324G 208B0777 ENGINE CONTROL QUADRANT POWER LEVER SPRING STOP BROKEN. (K) 1H71 3T3 T A37CE E2NE 20080410002372008041000237GL 2008 4 10 MV1R200808061 220080402G72106898785 SHAFT ALLSN SKRSKYS76 S76 8143010NE ALLSN 250C 250C30S 03013GL NR1 PTO GEAR CRACKED B MV1RK NONE K FLUID LOSS ININSP/MAINT 1 EA1738 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 AND LEAK CHECK GOOD. AFTER FLIGHT OIL LEAK RETURNED. ON GROUND RUN NO LEAK UNTIL ROTOR WAS RELEASED. OIL LEAK WAS AT OUTPUT SHAFT. FOUND PTO OUTPUT SHAFT CRACKED. REMOVED ENGINE SENT TO ENGINE SHOP FOR INSPECTION AND REPAIR. 1G72 3U3 U H1NE E1GL 20080520 CE 2008 5 20 MV1R200808136 120080429G21211013841761 BLOWER BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA ZONE 100 BURNED OUT B MV1RBGHAEMER. DESCENT O2 MASK DEPLOYED DEACTIVATE SYST/CIRCUITSUNSCHED LANDING BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CRCRUISE 1 EA1735 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. 1L72 4T4 T A24CE E4EA 20090106 NE 2009 1 6 MV1R200808429 120081217G62107615009100053 BLADE SKRSKYS76 S76A 8143006NE MAIN ROTOR DELAMINATED B K NONE O OTHER ININSP/MAINT 1 EA1738 213 S760087 DURING 3 YEAR MAIN ROTOR BLADE INSP FOUND DELAMINATION IN BLACK MAIN ROTOR BLADE ROOT END. DATA SENT TO MFG FOR EVALUATION. TOTAL DELAMINATED AREA IS 1.472 SQUARE INCHES. 1G72 3U H1NE 20080717 CE 2008 7 17 N772AF 120080602G554010164001423 HINGE BEECH 200 B200 1152922CE RUDDER CORRODED B VIBRK NONE F FLT CONT AFFECTED ININSP/MAINT 1 SO13772AF5763 BB1001 CENTER RUDDER HINGE FOUND TO HAVE EXCESSIVE CORROSION. 1L72 4T A24CE 20080508000422008050800042CE 2008 5 8 O7TR200800001 120080311G812046C22924E TURBOCHARGER CESSNA182 T182T 2072738CE ENGINE FAILED B O7TRK NONE O OTHER ININSP/MAINT 1 WP17 MAJOR TURBO FAILURE DUE TO SEPARATION OF TURBINE WHEEL HEAD FROM SHAFT. 1H71 3O NT3A13 20081210 CE 2008 12 10 OMKR2008-0002 120081124G5100 UNKNOWN CESSNA206 T206H 2073303CE LYC O540 TIO540AJ1A EA UNKNOWN B OMKRO OTHER O OTHER ININSP/MAINT 1 NM036197S 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 THEY HAD TO CHANGE LYCOMING'S LIST BECAUSE IT WAS IN ERROR. LYCOMING CONTACTED WITH NO REPLY YET. STRAIGHT FLIGHT PMI BROUGHT INTO LOOP, AND WANTED SDR FILLED OUT. PMI WILL ALSO ACTION. VERY SERIOUS IN NATURE AS LYCOMING SAYS THEY CHANGED 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 LISTS1H71 3O3 ORTA4CE E14EA 20081210 CE 2008 12 10 OMKR2008-0003 120081124G5100 NONE CESSNA208 208B 2073701CE NONE B OMKRK NONE O OTHER ININSP/MAINT 1 NM0322430 208B2011 NEW ACFT FROM FACTORY. PERFORMED AD SEARCH DUE TO EXPORT REQUIREMENT DURING ANNUAL. FOUND NUMEROUS ADS SIGNED OFF AS COMPLIED WITH THAT WERE N/A TO ACFT. MANY LISTED PARTS THAT WERE SUPPOSEDLY CHANGED. CONTACTED CESSNA. WAS ASKED WHY WITH SO MANY NEW ACFT BEING RELEASED, NO ONE ELSE WAS COMPLAINING. AFTER SEVERAL PHONE CONVERSATIONS AND SEVERAL CORRECTED LISTS, FINALLY HAD AN ACCEPTABLE LIST. 2 ADS WERE NOT ACCOUNTED FOR AND HAD BEEN ISSUED PRIOR TO THE ACFT BORN-ON DATE. 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. 1H71 3T A37CE 20080204001012008020400101EU 2008 2 4 PAI52008S4818 120080130G5540 STRUCTURE PIAGIOP180 P180 6960204EU RUDDER CHAFED B PAI5K NONE O OTHER ININSP/MAINT 1 SO05134SL2797 1100 DURING D-CHECK INSPECTION, FOUND RUDDER TORQUE CHAFED BY AFT FAIRING P/N 80-561004-401. 1H72 3O RTA59EU 20080225000092008022500009EU 2008 2 25 PAI52008S4858 120080212G5512 SKIN PIAGIOP180 P180 6960204EU PWA PT6 PT6* 52043EA HORIZONTAL STAB CRACKED B PAI5K NONE O OTHER ININSP/MAINT 1 SO05138SL 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. 1H72 3O3 TRTA59EU E2NE 20080328001022008032800102CE 2008 3 28 PAI52008S4877 120080209G322007436062 SUPPORT FITTING CESSNA182 182T 2072703CE NLG BROKEN B PAI5K NONE O OTHER ININSP/MAINT 1 SO05470P 719 18281290 PILOT COMPLAINED OF NOSE WHEEL SHIMMY. INSPECTION FOUND RIGHT-HAND SIDE OF NOSE GEAR LOWER SUPPORT FITTING BROKEN. 1H71 3O NT3A13 20080602 NE 2008 6 2 PJ6G20080147 220080414G7200310718501 GAS GENERATOR AIRTRCAT802 AT802 0390305SW PWC PT6 PT6A67AG 52211NE HARTZLHCB5M HCB5MA3 GL ENGINE ERODED D PJ6GO OTHER P NO WARNING INDICATION AGAGRICULTURE 1 SW11627JP566 566 8020238 PCERD0147 'C' FLANGE EROSION AT SCAVENGE TUBE OIL COUPLING WITH ASSOCIATED PARTIALLY SEVERED 'T' BOLT. 1L71 3T4 TNCA19SW E26NE 6 CP44GL 20090114 NM 2009 1 14 R5KB20081220001 120081220G5320 WEB BOEING727 727212 138407GNM BS 1213 CORRODED B K NONE O OTHER ININSP/MAINT 1 SO33727NK 21945 WEB CORRODED AT BS 1213 WL 177 RBL 5. 2L73 4F A3WE 20080131003052008013100305 2008 1 31 RC2R130L 420080123G61225221220F PILOT VALVE B210800REVJ BEECH 58 58 1152740CE CONT O520 IO520CB 17032SO GOVERNOR BROKEN B O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 NE03401BC 697 00066 TH1668 PROPELLER WENT TO FEATHER IN FLIGHT AND WAS UNABLE TO UNFEATHER. AFTER RECEIVING THE GOVERNOR FOR INSPECTION IT WAS DISCOVERED THAT THE BOTTOM END OF THE PILOT VALVE (P/N 5221-220) HAD BROKEN OFF AND WAS MISSING. IT WAS PRESUMED THAT IT EXITED THE BOTTOM END OF THE DRIVE GEAR AND ENTERED THE ENGINE SUMP. THE OPERATOR WAS NOTIFIED AND THE MISSING PIECE WAS RETRIEVED. 1L72 3O3 O 3A16 E5CE 20080414000402008041400040NM 2008 4 14 RI3R200800001 120080331G2840403501 TSU BOEING737 737* NM INTERNAL CONTAMINATED B RI3RK NONE J WARNING INDICATION ININSP/MAINT 1 SO15 WHILE PERFORMING TROUBLESHOOTING AND REPAIR OF 4035-01 SERIES TRANSIENT SUPPRESSION UNITS (TSU) IAW COMPONENT MM 28-44-64, 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 QUARANTINE. IMMEDIATELY NOTIFIED THE ORIGINAL EQUIPMENT MFG AND PRODUCTION AUTHORITY HOLDER, OF THE FINDINGS. COORDINATING WITH ENGINEERING AND QUALITY REPRESENTATIVES ON FURTHER ACTION AND FINAL DISPOSITION. AFFECTED UNITS TO REMAIN IN QUARANTINE UNTIL GUIDANCE IS RECEIVED. CONSULTED WITH FSDO, PMI. RECOMMENDED ACTION: SUBMIT SDR IAW 14 CFR PART 145.221 AND R2L72 4F RTA16WE 20080414001032008041400103NM 2008 4 14 RI3R200800002 120080409G2840403501 TSU BOEING737 737* NM CONTAMINATED B RI3RO OTHER O OTHER NRNOT REPORTED 1 SO15 WHILE PERFORMING PRELIMINARY INSPECTION AND TROUBLESHOOTING OF THE TRANSIENT SUPPRESSION UNIT (TSU) 4035-01, S/N 1308, IT WAS DISCOVERED THAT THE UNIT SHOWED EVIDENCE OF INTERNAL CONTAMINATION. THE CONTAMINATION APPEARS TO BE CAUSED BY MOISTURE INGRESS INTO THE UNIT. THE UNIT HAS BEEN PLACED IN QUARANTINE, AND PAH/OEM HAS BEEN NOTIFIED OF THE FINDING. 2L72 4F RTA16WE 20080404000082008040400008GL 2008 4 4 SJ3R025859 320080314G6110D495 FORK PILATSPC12 PC12 7090550EU PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3D GL PROPELLER ASSY CRACKED B SJ3RK NONE O OTHER ININSP/MAINT 1 GL05 2185 1361 HJ494 CRACK INDICATIONS FOUND DURING MAG PARTICLE INSPECTION. CRACKS ARE LOCATED ON THE THIN SIDE OF ALL (4) FORK SLOTS RADI. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20080402000352008040200035NE 2008 4 2 SJ3R080124001 320080124G6110B6545 CAM FOLLOWER BEECH 1900 1900D 1154162CE PWC PT6 PT6A42A 52043NE HARTZLHCE4A HCE4A3I NE PROP BLADE BROKEN B SJ3RK NONE E VIBRATION/BUFFET ININSP/MAINT 1 GL05 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 FOLLOWER. THIS PART WAS INSTALLED NEW AT OVERHAUL AND FAILED ON FIRST GROUND RUN. 2L72 4T4 TRTA24CE E4EA 5 CP10NE 20080423001682008042300168NM 2008 4 23 SROM2008001 120080406G5350654869089 SUPPORT BOEING737 737205 1384456NM LT MLG WW GOUGED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA39285 23466 LEFT HAND MAIN LANDING GEAR WHEEL WELL FAIRING SUPPORT GOUGED AT AFT OUTBOARD SIDE. REPAIRED LT MLG WHEEL WELL SUPPORT AT 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. 2L72 4F RTA16WE 20080423001762008042300176NM 2008 4 23 SROM2008002 120080406G5315 FLOORBEAM BOEING737 737205 1384456NM FUSELAGE CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 CORROSION ON AFT GALLEY FLOORBEAM AT STA BS 980 RBL 4. BLENDED AND FOUND CORROSION ON AFT GALLEY FLOORBEAM AT STA BS 980 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. 2L72 4F RTA16WE 20080714 NE 2008 7 14 SROM20080023 220080523G7200JT8D17A ENGINE BOEING737 737205 1384456NM PWA JT8 JT8D17A 52049NE NR 1 BIRD INGESTION C SROMEL ENGINE SHUTDOWN ABORTED APPROACH CJRF.O.D. WARNING INDICATION PARTIAL RPM/PWR LOSS APAPPROACH 1 AL03736BP366992561 23465 709500 INGESTED LARGE BIRD ON APPROACH TO AKU, SHUT-DOWN ENGINE AND COMPLETED MISSED APPROACH. DIVERTED TO SCC AND MADE UNEVENTFUL LANDING. REMOVED AND REPLACED NR 1 ENGINE. 2L72 4F4 FRTA16WE E2EA 20081126 2008 11 26 SROM20080024 420080926G2565D31355440 SLIDE BOEING737 737205 1384456NM R2 DOOR INOPERATIVE I SROMK NONE L NO TEST ININSP/MAINT 1 AL03733PA 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. 2L72 4F RTA16WE 20080423001862008042300186NM 2008 4 23 SROM2008003 120080406G5315 FLOORBEAM BOEING737 737205 1384456NM FUSELAGE CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 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 STA 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. 2L72 4F RTA16WE 20080423001712008042300171NM 2008 4 23 SROM2008004 120080406G5315 FLOORBEAM BOEING737 737205 1384456NM FUSELAGE CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 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, FIGURE 1. FLOORBEAM REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-04, FIGURE 1. REFERENCE NON-ROUTINE CARD 19, DATED 03/04/08. 2L72 4F RTA16WE 20080423001332008042300133NM 2008 4 23 SROM2008005 120080406G5320 TORQUE BOX BOEING737 737205 1384456NM FUSELAGE CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 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 STRUCTURAL REPAIR MANUAL (SRM), 51-10-06. ORIGINAL MATERIAL 0.063, AMOUNT OF REMOVED MATERIAL 0.025, OUT OF LIMITS IN ACCORDANCE 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. 2L72 4F RTA16WE 20080423001782008042300178NM 2008 4 23 SROM2008006 120080406G5330 SKIN BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 CRACK IN FUSELAGE SKIN AT STA BS 760 STR 19L, (NDT CONFIRMED CRACK). REPAIRED FUSELAGE SKIN AT STA BS 760 STR 19L IN ACCORDANCE 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. 2L72 4F RTA16WE 20080423001772008042300177NM 2008 4 23 SROM2008007 120080406G252043100001 BAR 87513 BOEING737 737205 1384456NM SEAT CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 REPAIR CRACKED SPREADER BARS ON PASSENGER SEATS. REPAIRED CRACKED SPREADER BARS ON PASSENGER SEATS IN ACCORDANCE WITH CPAI 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. 2L72 4F RTA16WE 20080423001882008042300188NM 2008 4 23 SROM2008008 120080406G5314 KEELBEAM BOEING737 737205 1384456NM FUSELAGE CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 LOWER CHORDS OF KEEL BEAM IN MAIN LANDING GEAR HAS CORROSION AT LOWER FLANGE IN SEVERAL AREAS UPPER & LOWER SURFACES FROM 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 WITH BOEING MESSAGE 1-789220434-4, DATED MARCH 28, 2008. FASTENERS INSTALLED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-2. REFERENCE NON-ROUTINE CARD 570, DATED 03/04/08. 2L72 4F RTA16WE 20080423001722008042300172NM 2008 4 23 SROM2008009 120080406G5320 FITTING BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 CLIP CRACKED AT STA BS 1006 STR 21L. REPLACED CLIP AT STA BS 1006 STR 21L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-01 AND 51-30-02. REFERENCE NON-ROUTINE CARD 578, DATED 03/04/08. 2L72 4F RTA16WE 20080423001732008042300173NM 2008 4 23 SROM2008010 120080406G5320 FITTING BOEING737 737205 1384456NM FUSELAGE CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 STRINGER TO FRAME CLIP REQUIRES BLENDING AT STA BS 907 STR 25L (REAR CARGO PIT). INSTALLED NEW CLIP AT STA BS 907 STR 25L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-03. REFERENCE NON-ROUTINE CARD 586, DATED 03/04/08. 2L72 4F RTA16WE 20080423001692008042300169NM 2008 4 23 SROM2008011 120080406G5340 STRINGER CLIP BOEING737 737205 1384456NM FUSELAGE DAMAGED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 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, DATED 03/04/08. 2L72 4F RTA16WE 20080423001812008042300181NM 2008 4 23 SROM2008012 120080406G5330 SKIN BOEING737 737205 1384456NM FUSELAGE DAMAGED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 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. 2L72 4F RTA16WE 20080423001342008042300134NM 2008 4 23 SROM2008013 120080406G5320 ATTACH FITTING BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 CRACK IN INTERCOSTAL ATTACH CLIP AT STA BS 360 STR 11L. REPLACED INTERCOSTAL ATTACH CLIP AT STA BS 360 STR 11L IN ACCORDANCE 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. 2L72 4F RTA16WE 20080423001702008042300170NM 2008 4 23 SROM2008014 120080406G5320 ATTACH FITTING BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 CRACK IN INTERCOSTAL ATTACH CLIP STA BS 294.5 STR 11L. REPLACED INTERCOSTAL ATTACH CLIP STA BS 294.5 STR 11L IN ACCORDANCE 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. 2L72 4F RTA16WE 20080423001352008042300135NM 2008 4 23 SROM2008015 120080406G5311 FRAME BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 CRACK ON BODY FRAME INNER CHORD STA BS 616 LEFT HAND AT STUB BEAM LOWER CHORD. REPAIRED BODY FRAME INNER CHORD STA BS 616 LT AT STUB BEAM LOWER CHORD IN ACCORDANCE WITH BOEING SB 737-53A-1254. REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CARD 672, DATED 03/05/08. 2L72 4F RTA16WE 20080423001672008042300167NM 2008 4 23 SROM2008016 120080406G5514 BUSHING BOEING737 737205 1384456NM HORIZ STAB LOOSE C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 LOOSE BUSHING ON STABILIZER SCREW JACK LOWER RIGHT HAND MOUNTING STRUCTURE (P/N 6-37464-1). REPLACED BUSHING ON STABILIZER SCREW JACK LOWER RT MOUNTING STRUCTURE IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 078-1236-08-473 AND ASI SOLUTIONS DRAWING 5340473-1, REV IR, DATED MARCH 14, 2008. REFERENCE NON-ROUTINE CARD 740, DATED 03/06/08. 2L72 4F RTA16WE 20080423001742008042300174NM 2008 4 23 SROM2008017 120080406G783065MK781031 BRACKET BOEING737 737205 1384456NM PWA JT8 JT8D17A 52049NE NR 1 ENGINE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA39277 23466 709507 LEFT HAND ENGINE TAILPIPE CRACKED AT BRACKET MOUNT (3 O'CLOCK POSITION). REPAIRED LEFT HAND ENGINE TAILPIPE BRACKET MOUNT (3 O'CLOCK POSITION) IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 073-1236-08-477 AND ASI SOLUTIONS DRAWING 7830477-1, REV IR, DATED MARCH 18, 2008. REFERENCE NON-ROUTINE CARD 826, DATED 03/11/08. 2L72 4F4 FRTA16WE E2EA 20080423001752008042300175NM 2008 4 23 SROM2008018 120080406G5315 FLOORBEAM BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 LOWER LONGITUDINAL FLOORBEAM CHORD CRACKED AT LBL 24.5 STA BS 663. REPLACED LOWER LONGITUDINAL FLOORBEAM CHORD AT LBL 24.5 STA BS 663 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-01 AND BOEING DRAWING 65-45410. REFERENCE NON-ROUTINE CARD 843, DATED 03/18/08. 2L72 4F RTA16WE 20080423001832008042300183NM 2008 4 23 SROM2008019 120080406G5315 FLOORBEAM BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 LOWER LONGITUDINAL FLOORBEAM CHORD CRACKED AT RBL 24.5 STA BS 663. REPLACED LOWER LONGITUDINAL FLOORBEAM CHORD AT RBL 24.5 STA BS 663 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-01 AND BOEING DRAWING 65-45410. REFERENCE NON-ROUTINE CARD 844, DATED 03/18/08. 2L72 4F RTA16WE 20080423001892008042300189NM 2008 4 23 SROM2008020 120080406G5315 FLOORBEAM BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 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 ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-9, FIGURE 5. REFERENCE NON-ROUTINE CARD 858, DATED 03/25/08. 2L72 4F RTA16WE 20080423001952008042300195NM 2008 4 23 SROM2008021 120080406G5320 TORQUE BOX BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 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, FIGURE 23, PART 6 ON A CUT-OUT ON THE APU TORQUE BOX, STA BS 1115. NO DEFECTS EVIDENT (NDT08-0461). APU TORQUE BOX WEB AT STA BS 1115 RBL 2 REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-01, FIGURE 1 AND INSTALLED 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. 2L72 4F RTA16WE 20080423001842008042300184NM 2008 4 23 SROM2008022 120080405G5314 KEELBEAM BOEING737 737205 1384456NM FUSELAGE CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 LOWER CHORD OF KEEL BEAM IN MLG HAS CORROSION ON VERTICAL AND HORIZONTAL FLANGES IN SEVERAL AREAS FROM STA BS 663-727 LBL 615. REPAIRED LOWER CHORD OF KEEL BEAM ON LT SIDE BETWEEN STA BS 663 THRU 727 IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 095-1236-08-483 AND ASI SOLUTIONS DRAWING 5310483-1, REV IR, DATED APRIL 4, 2008. CORROSION BLENDED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-06 AND FAIRED AT A 10:1 RATIO IN ACCORDANCE WITH SRM 51-10-06. ALL PARTS TREATED AND PROTECTED IN ACCORDANCE WITH SRM 51-10-2. ALL FASTENERS INSTALLED IN ACCORDANCE WITH SRM 51-30-2. REFERENCE NON-ROUTINE CARD 876, DATED 03/31/08. 2L72 4F RTA16WE 20080410001632008041000163 2008 4 10 STS004 420080402G25641218FASA6311701 LIFE RAFT EMB 135 EMB135KL 3260302SO MISINSTALLED B K NONE O OTHER ININSP/MAINT 1 SO15WL7R 2 THE CONFIGURATION BETWEEN THE FIRING HEAD BELL HOUSING AND THE LINK VALVE ARE NOT LOCATED PROPERLY. THE 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. 2L72 4F RTT00011AT 200805141 200805141 NE 2008 5 14 SWDG08RD0113 220080508G72103030988 SEAL PWC AIRTRCAT802 AT802A 0390308SW PWC PT6 PT6A67AG 52211NE HARTZLHCB5M HCB5MA3 GL RGB DEFORMED D SWDGK NONE K FLUID LOSS ININSP/MAINT 1 SW11804DG738 PCERD0113 802A0089 PCERD0113 EXCESSIVE OIL LEAKAGE AROUND PROP SHAFT. FOUND FELT SEAL MISALIGNED AND INTERFERING WITH THE SHAFT SEAL. 1L71 3T4 TNCA19SW E26NE 6 CP44GL 200805141 200805141 2008 5 14 SWDG20085569 420080414G6122311849703 GOVERNOR AIRTRCAT802 AT802A 0390308SW PWC PT6 PT6A67AG 52211NE HARTZLHCB5M HCB5MA3 GL PROPELLER LEAKING D SWDGA UNSCHED LANDING KR FLUID LOSS PARTIAL RPM/PWR LOSS AGAGRICULTURE 1 SW11804DG721 721 802A0089 PCERD0113 HBA1298 GOVERNOR HAS EXCESSIVE BETA VALVE OIL LEAKAGE AND ERRATIC TORQUE FLUCTUATION. PART REMOVED AND SENT TO REPAIR STATION FOR EVALVUATION. 1L71 3T4 TNCA19SW E26NE 6 CP44GL 20080225000072008022500007CE 2008 2 25 TIMR20080001 120080213G3233993880081 ACTUATOR BEECH 99 C99 1154006CE PWA PT6 PT6A36 52043NE MLG LEAKING B TIMAO OTHER J WARNING INDICATION CLCLIMB 1 NM07239AL 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. 1L72 3T4 T A14CE E4EA 20080111003072008011100307EA 2008 1 11 UE5R010208001 220080102G73133013635 NOZZLE DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A28 EA ENGINE SHEARED B UE5RK NONE O OTHER ININSP/MAINT 1 EA61 WHEN INSTALLING NOZZLE PN 3013635 ONTO NOZZLE ADAPTER ASSEMBLY USING SPECIFIED OHM TORQUE, NOZZLE SHEARED OFF COMPLETELY AT BASE OF THREADS. 1H72 3T4 TRTA9EA E4EA 20080410002582008041000258CE 2008 4 10 VIB8368K 120080320G3220 BRACE BEECH 100 B100 1152919CE NLG CORRODED B K NONE O OTHER ININSP/MAINT 1 SO1397WD 7178 BE97 DISASSEMBLED NLG DURING SCHEDULED MAINT AND FOUND SIGNIFICANT CORROSION OVER MOST OF THE NOSE LANDING GEAR V BRACE, PN 50-820204. WE ALSO FOUND A CRACK OF 0.008 INCH IN THE NOSE BARREL, PN 99-820100-5, WHERE IT LOOKED LIKE IT HAD BEEN REPAIRED 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. 1L72 4T A14CE 20081126 EA 2008 11 26 VJ1R20081118001 120081107G3810500120701 WATER HEATER CNDAIRCL600 CL6002B16 1900305EA ZONE 900 OVERTEMP B VJ1RBAH EMER. DESCENT UNSCHED LANDING DEACTIVATE SYST/CIRCUITS MB OVER TEMP SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 SW05CGQWI 5016 ACFT AT CRUISING ALTITUDE WHEN A PASSENGER ADVISED THE CREW THAT THEY COULD ODOR SOMETHING BURNING IN THE CABIN AREA. THE 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 CIRCUIT 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 INSTALLATIONS. THERE ARE POSSIBLY (2) PER INTERIOR ONE LOCATED BEHIND THE GALLEY AND ONE LOCATED BEHIND THE LAVATORY VANITY. A C2L72 4F RTA21EA 20080414000412008041400041 2008 4 14 WL7R040208001 420080402G2564 HOUSING EMB 135 EMB135KL 3260302SO LIFE RAFT MISINSTALLED B WL7RK NONE W INADEQUATE Q C ININSP/MAINT 1 SO15 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. 2L72 4F RTT00011AT 20080404000072008040400007SO 2008 4 4 WS9R030608001 220080306G8530AEC631397 CYLINDER BEECH 36 A36 1151604CE CONT O550 IO550B SO ENGINE CRACKED B WS9RK NONE O OTHER ININSP/MAINT 1 NM07 205 814500 CRACK BETWEEN 3RD AND 4TH CYLINDER HEAD, COOLING FIN. 1L71 3O3 O 3A15 E3SO 20080404000112008040400011SO 2008 4 4 WS9R031108001 220080311G8530 CYLINDER HEAD CESSNA180 180C 2072608CE CONT O470 O470L 17026SO ENGINE CRACKED B WS9RK NONE O OTHER ININSP/MAINT 1 NM07001 069693R VISUAL INSPECTION OF THE CYLINDER AS IT WAS RECEIVED FROM THE MFG, REVEALED CRACKED FINS NEAR THE FUEL INJECTOR NOZZLE. 1H71 3O3 O 5A6 E273 20080404000122008040400012EA 2008 4 4 WS9R031908001 220080319G8530AEL14995 RETAINER PIPER PA28 PA28* SO LYC O360 O360A4M 41514EA CYLINDER BROKEN B WS9RK NONE K FLUID LOSS ININSP/MAINT 1 NM07 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. 1L71 3O3 O 2A13 E286 20080401001202008040100120NM 2008 4 1 Y5CR200700003 120080122G6200369D25351 SPRAG CLUTCH DOUG MD500 MD500E 3027372NM MAIN ROTOR BROKEN B Y5CRK NONE O OTHER ININSP/MAINT 1 WP05 760 DURING A 300HR. INSPECTION ON THE O/R CLUTH THE CUSTOMER FOUND A BROKEN SPRAG CLIP ON THE SPRAG ASSY. 1G72 3U NC 20080520 NM 2008 5 20 Y5CR200700004 120080501G6320369D2512311 BEVEL GEAR DOUG DOUG MD500 MD500E 3027372NM M/R TRANSMISSIONBROKEN B Y5CRK NONE O OTHER ININSP/MAINT 1 WP05 616 3668 M/R TRANSMISSION GEAR HAS BROKEN TOOTH. 1G72 3U NC 20080403000442008040300044WP 2008 4 3 YZ4R200800001 120080222G26203260007 EXTINGUISHER DOUG DC3 DC3CR183090C3021466WP PWA PT6 PT6* 52043EA INOPERATIVE B YZ4RO OTHER O OTHER NRNOT REPORTED 1 EA39300BF 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 DISCHARGE 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 COMPRESSION. THE HOUSING ASSY IS MFG WITH VARIOUS MACHINED GROOVES AND IS DESIGNED FOR THE COMPRESSIVE FORCES. WHEN THE CA2L72 4R3 T A669 E2NE 20080122000612008012200061CE 2008 1 22 ZB0R20080001 120080111G2842S35942 SENSOR CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA FUEL QTY INTERMITTENT B ZB0RO OTHER N FALSE WARNING CRCRUISE 1 EA39272RP420 40 172S8405 RT FUEL QUANTITY INTERMITTENT AT HIGH FUEL LEVELS. 1H71 3O3 ONT3A12 1E10 20080122000562008012200056CE 2008 1 22 ZB0R20080002 120080111G2842S35942 SENSOR CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA FUEL QTY INTERMITTENT B ZB0RO OTHER N FALSE WARNING CRCRUISE 1 EA39963AC226 45 172S8259 RT FUEL QUANTITY INTERMITTENT AT HIGH FUEL LEVELS. 1H71 3O3 ONT3A12 1E10