N918FX
Registered owner: FEDERAL EXPRESS CORP, TN (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
DURING PREFLIGHT OF AIRCRAFT FOR FLIGHT 8120 BQN-AUA, THE CAPTAINS SIDE O2 MASK WOULD NOT TEST. BQN MAINTENANCE REPLACED THE CAPTAINS SIDE MASK AND FLIGHT 8120 DEPARTED
ODOR OF SMOKE FOLLOWED BY RECIRC FAN #2 FAULTED IN FLIGHT.
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.
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.
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.
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.
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.
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.
LEFT FLOOR SUPPORT BROKEN BETWEEN FRAMES 31 AND 32.
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.
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.
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.
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.
FOUND CORROSION ON FLOOR PANEL 214BF, OUT OF LIMITS. REPLACED FLOOR PANEL IAW SRM.
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.
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.
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.
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)
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.
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.
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.
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.