N918FX

Part: FAN — FAILED (ZONE 100) · airframe 30,666 hrs · 38,893 cycles

ODOR OF SMOKE FOLLOWED BY RECIRC FAN #2 FAULTED IN FLIGHT.

Part: NONE — NONE · airframe 29,858 hrs · 38,064 cycles

PRIOR TO THE INITIAL DESCENT, IN CRUISE FLIGHT, THE CREW NOTICED A TRANSIENT OVER-TORQUE ON ENGINE #2, FOLLOWED BY A DECREASE IN NP. THE CREW ASSESSED THE SITUATION, SHUT DOWN AND SECURED ENGINE #2, AND DECLARED AN EMERGENCY. THE FLIGHT CONTINUED TO MIA, WHERE IT LANDED WITHOUT FURTHER INCIDENT.

Part: NONE — NONE · airframe 29,783 hrs · 37,969 cycles

PITCH TRIM ASYMMETRY IN FLIGHT. PITCH, ROLL, AND RUDDER TRIM INDICATOR INOP. TRIPPED CIRCUIT BREAKER. REMOVED AND RECONNECTED LEFT AND RIGHT ELECTRIC PITCH TRIM ACTUATOR CONNECTORS AFTER CLEANING WITH CONTACT CLEANING. REMOVED AND REPLACED CREW ALERTING COMPUTER. OPS CHECK GOOD.

Part: INDICATOR — FAULTED (PITCH TRIM) · airframe 29,308 hrs · 37,555 cycles

PITCH TRIM ASYMMETRY MASTER CAUTION IN FLIGHT. FOUND TRIM INDICATOR CIRCUIT BREAKER POPPED. INSPECTED AND CLEANED CANNON PLUGS FOR RIGHT AND LEFT ELEVATOR TRIM ACTUATOR. INSPECTED ASSOCIATED WIRING AND VARISTORS IN TAIL CONE FOR CORROSION. REPLACED TRIM INDICATOR. COMPLIED WITH ELEVATOR SURFACE PARAMETER TEST. NO DISCREPANCIES FOUND DURING THIS TEST.

Part: CIRCUIT BREAKER — TRIPPED (PITCH TRIM) · airframe 39,286 hrs · 37,543 cycles

PITCH TRIM ASYMMETRY IN CRUISE FLIGHT. FLIGHT CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT AT THE SCHEDULED ARRIVAL AIRPORT. MAINTENANCE FOUND TRIM INDICATOR CIRCUIT BREAKER TRIPPED. RESET CIRCUIT BREAKER AND SYSTEM OPERATIONALLY CHECKED GOOD. MAINTENANCE PERFORMED GENERAL VISUAL INSPECTION OF WIRING AND CONNECTIONS IN THE TAIL AND AT THE PITCH TRIM ACTUATORS WITH NO DISCREPANCIES FOUND.

Part: O-RING — LEAKING (PROP CONTROL) · airframe 29,147 hrs · 37,393 cycles

DURING CRUISE RT TORQUE UNCOMMENCED TORQUE INDICATED 120%, ACCOMPANIED AIRPLANE ASSEMETRY. MAINTENANCE FOUND PROPELLER CONTROL UNIT O-RING LEAKING AT REDUCTION GEAR BOX. REPLACED O-RING OPERATIONALLY CHECKS GOOD. PER PRATT & WHITNEY MM 05-50-00 OVERTORQUE WAS IN "AREA A", REQUIRING NO FURTHER MAINTENANCE ACTION.

Part: O-RING — LEAKING (PROP CONTROL) · airframe 29,146 hrs · 37,391 cycles

DURING CRUIS, RIGHT UNCOMMANDED TORQUE INDICATED 120%, ACCOMPANIED BY AIRPLANE ASYMMETRY. REPLACED #2 PROPELLER CONTROL UNIT O-RINGS, OPERATIONALLY CHECKS GOOD. UPON FOQA DOWNLOAD FOUND OVERTORQUE TO HAVE BEEN 146%. REPLACED RH PROPELLER ASSEMBLY FOR INSPECTION, PERFORMED ENGINE REDUCTION GEAR BOX CHIP DETECTOR AND OIL FILTER CHECKS, NO DISCREPANCIES WERE DISCOVERED.

Part: FLOOR SUPPORT — BROKEN (FRAMES 31-32) · airframe 28,201 hrs · 36,156 cycles

LEFT FLOOR SUPPORT BROKEN BETWEEN FRAMES 31 AND 32.

Part: ENGINE — SHUTDOWN (NR 2) · airframe 28,200 hrs · 36,155 cycles

DURING LEVEL-OFF AT 10,000 FEET FOR CRUISE FLIGHT, A POP SOUND WAS HEARD, FOLLOWED BY A LACK OF RESPONSE FROM THE NR 2 CONDITION LEVER AND COMPLETE SHUTDOWN OF THE NR 2 ENGINE. THE CREW DECLARED AN EMERGENCY, AND THE AIRCRAFT RETURNED TO FIELD WITHOUT INCIDENT. THE NR 2 PROPELLER WOULD ALSO NOT FEATHER UNTIL THE FIRE HANDLE WAS PULLED. CHANGEE THE NR 2 ENGINE.

Part: SMOKE WARNING — ACTIVATED · airframe 28,067 hrs · 36,038 cycles

DURING CLIMB AND PART OF CRUISE, THE AFT SMOKE INDICATION ON THE CREW ADVISORY PANEL CAME ON ALONG WITH A WARNING LIGHT AND REPETITIVE CHIME. AIRCRAFT RETURNED TO FIELD WITHOUT INCIDENT.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 27,282 hrs · 35,166 cycles

MAIN CARGO DOOR FITTINGS ATTACHED TO FUSELAGE DISCOVERED TO HAVE OVERSIZED HOLES. APPLIED SERVICE BULLETIN 42-52-0076 & HOLES REMAINED OVERSIZE IAW ATR EMAIL IAW DT S-5011/14-22727 DATED 8/22/2014 & 8/25/2014. APPROVED DATA IS SRAS DT S-5011 14 8665 ISSUE A DATED 8/26/2014.

Part: PAN — DENTED (CARGO DOOR) · airframe 27,088 hrs · 34,940 cycles

AFT CARGO DOOR HAS THREE DENTS THAT ARE OUT OF LIMITS ON LOWER PAN. REPAIRED LOWER DOOR PAN IAW M-7 DWG NR 42R47000-09 REV. I/R.

Part: FLOOR PANEL — CORRODED (ZONE 100) · airframe 27,088 hrs · 34,940 cycles

FOUND CORROSION ON FLOOR PANEL 214BF, OUT OF LIMITS. REPLACED FLOOR PANEL IAW SRM.

Part: COMPUTER — OUT OF ADJUST · airframe 26,526 hrs · 34,291 cycles

DURING DESCENT, ACFT EXPERIENCED AN MC LIGHT AND SINGLE CHIME, IMMEDIATELY FOLLOWED BY THE AUTOPILOT DISCONNECT WARNING. FLT CONTROL CAUTION WAS ILLUMINATED ON CAP, AND A LOCAL PITCH TRIM ASYM LIGHT WAS NOTED ON THE INSTRUMENT PANEL. THE MC AND LOCAL ALERTS FLASHED SEVERAL TIMES, GIVING AN AURAL SINGLE CHIME ALERT EACH TIME, BEFORE ILLUMINATING FOR GOOD. NOTIFIED ATC THAT AIRCRAFT HAD A COMPLETE PITCH TRIM FAILURE, AN EMERGENCY WAS DECLARED. AN UNEVENTFUL, VISUAL APPROACH, BACKED UP WITH ILS COUPLED FD AND LANDING ACCOMPLISHED. AFTER TROUBLESHOOTING THE MECHANIC REPLACED THE CREW ALERTING COMPUTER AND CHECKED PITCH TRIM CONTROLS WITH A SYNCHRO READER. THE SYSTEM CHECKED GOOD IAW JIC 27-32-00FUT-10004. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: WARNING SYSTEM — MULTIPLE IND · airframe 26,526 hrs · 34,291 cycles

DURING DESCENT, ACFT EXPERIENCED A MC LIGHT AND SINGLE CHIME, IMMEDIATELY FOLLOWED BY THE AUTOPILOT DISCONNECT WARNING. FLT CONTROL CAUTION WAS ILLUMINATED ON THE CAP, AND A LOCAL PITCH TRIM ASYM LIGHT WAS NOTED ON THE INSTRUMENT PANEL. THE MC AND LOCAL ALERTS FLASHED SEVERAL TIMES, GIVING AN AURAL SC ALERT EACH TIME, BEFORE FINALLY ILLUMINATING FOR GOOD. NOTIFIED ATC THAT ACFT HAD A COMPLETE PITCH TRIM FAILURE, AN EMERGENCY WAS DECLARED. AN UNEVENFUL, VISUAL APROACH (BACKED UP WITH ILS COUPLED FD) AND LANDING WAS ACCOMPLISHED.

Part: SPLICE — CORRODED (ZONE 200) · corrosion level 3 · airframe 24,819 hrs · 32,848 cycles

DURING A 4 YEAR INSP FOUND A CORRODED SPLICE PLATE AT FRAME 42. REMOVED AND INSTALLED A NEW DOUBLER IAW THE SRM, CH. 51-25-01, 51-25-02 AND 51-21-27.

Part: ATTACH ANGLE — CORRODED (LT WING SKIN)

DURING THE YEARLY INSPECTION FOUND EXFOLIATION CORROSIOIN LEVEL 2. THE CORROSION WAS ON LT LOWER WING SKIN ATTACH ANGLE THAT ATTCHES THE WING SKIN TO THE LT OUTBOARD NACELLE SKIN AT RIB 12. REPAIRED IAW ATR 42 SRM 51-21-42, 51-21-58, 51-22-02 AND ATR REPAIR INSTRUCTION DO/TS-3056/08-10463. (A)

Part: TEE FITTING — CORRODED (AILERON) · airframe 23,945 hrs · 23,198 cycles

DURING INSPECTION, LEVEL 2, CORROSION WAS FOUND ON THE (T-FITTINGS) ATTACHING THE RIBS TO THE SPAR. THE FITTINGS AFFECTED ARE LOCATED AT RT IB, CENTER, AND OB HINGE FITTINGS. THE PROBABLE CAUSE IS DISSIMILAR MATERIALS (STEEL BOLTS IN ALUMINUM ALLOYED FITTINGS). THE FITTINGS WERE REPLACED AT RIBS 4, 11/12, AND 19. REFERENCE ATR42 SRM 57-61-10 FIG 101 RT AILERON.

Part: FITTING — CORRODED (AILERON) · airframe 23,945 hrs · 23,198 cycles

DURING INSPECTION, LEVEL 2 CORROSION WAS FOUND ON THE (T- FITTINGS) ATTACHING THE RIBS TO THE SPAR. THE FITTINGS AFFECTED ARE LOCATED AT THE IB, CENTER, AND OB HINGE FITTINGS. THE PROBABLE CAUSE IS DISSIMILAR MATERIALS (STEEL BOLTS IN ALUMINUM ALLOYED FITTINGS). THE FITTINGS WERE REPLACED AT RIBS 4, 11/12, AND 19. REFERENCE ATR42 SRM 57-61-10 FIG 101.

Part: POWER LEVER — LACK OF LUBE (NR 2) · airframe 23,838 hrs · 32,104 cycles

IN CRUISE FLIGHT AT FL220 THE NR 2 POWER LEVER APPEARED TO BE FROZEN AT ITS POWER SETTING. AFTER DESCENT TO 12,000 FT THE NR 2 POWER LEVER BECAME FREE AND THE POWER COULD THEN BE CHANGED. SERVICE BULLETIN ATR42-76-0009 HAD PREVIOUSLY BEEN ACCOMPLISHED. PANELS WERE REMOVED TO GAIN ACCESS, THE FLEXIBLE CONTROLS WERE LUBED AND THE REMOVED PANELS WERE RESEALED. OPERATIONAL CHECKS WERE ACCOMPLISHED WITH NO DISCREPANCIES FOUND. THE A/C WAS RETURNED TO SERVICE WITH NO FURTHER DISCREPANCIES TO THE NR 2 ENGINE CONTROLS.

Part: GCU — OPEN · airframe 23,510 hrs · 31,773 cycles

NR 1 GENERATOR FAILED IN FLIGHT. ELECTRICAL SMOKE IN COCKPIT PRECEDED GENERATOR FAILURE. NO RESET WAS ATTEMPTED. THERE WAS NO EVIDENCE OF FIRE OR HEAT DAMAGE. THE PROBLEM WAS TRACED TO A GENERATOR CONTACTOR.