N391FE
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| FEDERAL EXPRESS CORPORATION (FDEA) | Operator | on 2006-07-28 | Operator named in NTSB report |
Accident & incident history
Operated by FEDERAL EXPRESS CORP (per NTSB report)
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
26 reports on file, 1997-07-30 – 2006-07-28.
Part: LANDING GEAR — COLLAPSED (LEFT) · airframe 73,283 hrs · 27,002 cycles
LEFT MAIN LANDING GEAR COLLAPSED ON LANDING AT MEM. NO WRITE UP AT THIS TIME. UNDER NTSB INVESTIGATION. AIRCRAFT DESTROYED, BEYOND ECONOMICAL REPAIR.
Part: LANDING GEAR — COLLAPSED (LEFT) · airframe 73,283 hrs · 27,002 cycles
LT MAIN LANDING GEAR COLLAPSED ON LANDING AT MEM. NO WRITE UP AT THIS TIME. UNDER NTSB INVESTIGATION.
Part: ENGINE — DAMAGED (NR 2) · airframe 72,242 hrs · 26,548 cycles
ON T/O ROLL AT ORD AT ABOUT 120KT, RECEIVED ENGINE FAIL ALERT ON NR 2 ENG, NOTED EGT EXCEEDANCE AT 1052DEG, REJECTED. CLEARED RUNWAY, QRH. SHUTDOWN NR 2 ENGINE ON TAXIWAY. RETURNED TO RAMP. DUE TO THE FOD DAMAGE DONE TO THE FAN AND METAL IN THE TAIL PIPE WITH A N1,N2, ROLLBACK AND EGT OF 1052. THIS ENGINE IS APPROVE FOR CHANGE. REPLACED THE NR 2 ENGINE, BOTH THRUST REVERSERS, THE INLET BELLMOUTH AND ADAPTER RING.
Earlier reports · 1997–2005 · 23 reports
2005
Part: TUBE — LOOSE (NR 2 ENGINE) · airframe 71,715 hrs · 26,329 cycles
DURING DESCENT THRU FL200, NOTICED NR 2 ENGINE WOULD NOT SPOOL UP FOR LEVEL OFF. N1 REMAINED AT LESS THAN 35 N1, N2 60 PERCENT. NR 2 THROTTLE HAD A VERY LIGHT TRAVEL FORCE AND FELT DISCONNECTED. ACCOMPLISHED RED TABS AND SHUT DOWN ENGINE DUE TO ENGINE BEING UNRESPONSIVE TO THROTTLE COMMANDS. T/S AND FOUND CDP LINE LOOSE AT MEC RETORQUED AND SAFETY LINE IAW SMP RAN NR 2 ENGINE AT HIGH POWER IAW JRH 4-5, NO DEFECTS NOTED. OK FOR SERVICE.
Part: BRACKET — BROKEN (ZONE 500) · airframe 71,282 hrs · 26,137 cycles
COMPLY WITH EA 8-2750-82100A FLIGHT CONTROL-FLAP-REPLACMENT OF FLAP CONTROL BRACKET. COMPLIED WITH EA 8-2750-82100A. FLIGHT CONTROL FLAP REPLACMENT OF LWR CONTROL BRACKET.
Part: SEAL — DAMAGED (PYLON FAIRING) · airframe 71,280 hrs · 26,134 cycles
COMPLY WITH EA 8-5410-82094. NACELLES/PYLON-REPLACEMENT OF DAMAGED PYLON FAIRING SEAL. CLOSING ACTION ON 06/27/05, ON N/R S00083.COMPLIED WITH EA8-5410-82094.
Part: ACCESS PANEL — CRACKED (NR 1 PYLON) · airframe 71,280 hrs · 26,134 cycles
NR 1 PYLON FUEL LINE INSIDE ACCESS PANEL 517CT HAS IMPROPER STOP DRILL INSIDE RADIUS OF WELD. CRACK APPEARS TO HAVE PROPAGATED ONTO THE WELD. REMOVED AND REINSTALLED AFTER REPAIR PER TRAVELER T5/522336 NR 1 PYLON FUEL LINE INSIDE ACCESS 517CT IAW MM 20-50-01-2. LEAK CHECK GOOD IAW MM 28-00-02-2.
Part: FUEL LINE — CRACKED (NR 3 ENGINE) · airframe 71,280 hrs · 26,134 cycles
NR 3 ENGINE FUEL LINE CRACKED ABOVE PYLON AT CONNECTING BRACKET UNDER PANEL 617CT. REMOVED AND REINSTALLED AFTER REPAIR PER TRAVLER T5/527309, NR 3 ENGINE PYLON. MAIN FUEL LINE AT PANEL 617CT IAW MM 20-50-01-2. LEAK CHECK GOOD IAW MM 28-00-02-2.
Part: DOOR — CRACKED (NR 8 SLAT TRACK) · airframe 71,280 hrs · 26,134 cycles
RT WING NR 8 SLAT TRACK DOOR HAS CRACK AND WORN. REMOVED AND REPLACED NR 8 SLAT TRACK DOOR IAW MM 57-21-01--2 AND OPS CHECKED GOOD IAW MM 27-80-01-4.
Part: SUPPORT FITTING — CORRODED (ZONE 600) · airframe 71,280 hrs · 26,134 cycles
COMPLY WITH EA 8-5750-55487, WINGS - FLAP VANE SUPPORT CORROSION REWORK (RIGHT OUTBOARD FLAP). COMPLIED WITH EA 8-5750-55487.
Part: STIFFENER — GOUGED (NR 1 STRUT) · airframe 71,280 hrs · 26,134 cycles
COMPLY WITH EA 8-7254-89506 ENGINE - TURBINE - TMF STRUT NR 1 STIFFENER GOUGE REPAIR. COMPLIED WITH EA 8-7254-89506.
2004
Part: PROXIMITY SENSOR — OUT OF ADJUST (LT MLG) · airframe 70,375 hrs · 25,748 cycles
AFTER T/O RAISED LANDING GEAR, BOTH PRI AND SEC IND SHOWED LT GEAR NOT UP AND LOCKED. NOTED NO UNUSUAL VIB OR CONT INPUT. C/W QRH AND LOWERED THEN RAISED LANDING GEAR. ALL IND WERE LEFT MAIN GEAR NOT UP AND LOCKED. DECIDED TO RETURN TO RAMP. CTR GAVE US A RT TURN AND ALL IND SHOWED UP AND LOCKED. JACKED A/C IN REF TO MD10-10 M/M 07-10-00-0. FOUND GAP AT LT MLG UPLOCK LATCH PROX TO TARGET NOT WITHIN LIMITS. ADJ SHIMS AS REQ TO OBTAIN GAP REF MD-10-10 AMM 32-61-15-4. AS PRECAUTION REMOVED AND REPLACED PSEU IN REF MD-10-10 AMM 31-71-01-2. PERF ADJ TEST OF PROX TARGETS AND TARGETS REF MM 32-61-15-5. ALL TEST PASSED. COMPLETED SEVERAL NORMAL GEAR RETRACTIONS WITH NO DEFECTS NOTED.
Part: CONTROL UNIT — MALFUNCTIONED (BATTERY) · airframe 69,613 hrs · 25,424 cycles
IN CRUISE FLIGHT RECEIVED BATTERY DISCHARGING ALERT, BATTERY VOLTAGE WAS 29V. DIVERTED TO TPA. AFTER LANDING GOT: BATTERY CHARGER INOP ALERT. FACT: TROUBLESHOT PER FIM 24-30-01. REMOVED AND REPLACED EPCU PER MM 24-08-01-4. PERFORMED RTS PER MM 24-08-01-5. REMOVED AND REPLACED RELAY R2-5784 PER SMP AS PRECAUTIONARY.
Part: FLAP — MALFUNCTIONED (WING) · airframe 69,158 hrs · 25,186 cycles
ON FLAP RETRACTION AFTER T/O, GOT A FLAP DISAGREE LEVEL 2 ALERT. CONFIG PAGE SHOWED FLAPS STILL AT 18 DEG T/O SETTING. ACCOMPLISHED QRH PROCEDURES WITH RESULTS OF INABILITY TO RAISE OR LOWER FLAPS AT ALL. LANDED AT FLAPS 18 DEG/ EXT. CONFIG PAGE SHOWED FLAPS AT 19/21 & 20/19. FLAP HANDLE DURING TROUBLESHOOTING WAS RAISED TO 0 DEG/EXT AND LOWERED TO 35/EXT WITH NO CHANGE. FOUND DIAL-A-FLAP OUT OF SEQUENCE. RESET FLAP AND SLAT HANDLES REF MM 27-50-00-5. OPS CHECK NUMEROUS TIMES ALL NORMAL OPERATION.
2003
Part: ATTACH FITTING — CRACKED (T/E FLAP) · airframe 68,411 hrs · 24,833 cycles
REMOVE I/B FLAP ACTUATOR CYLINDER ATTACH FITTING STEP'S 1 THRU 8 LEFT SIDE. REMOVED AND INSTALLED FLAP ACTUATOR IAW MM 25-52-01-2 AND ACCOMPLISHED EO 8-5720- 7-2302 STEP NR 1 THRU NR 8 LEFT SIDE FLAP ACTUATOR CYLINDER ATTACH FITTING REPLACEMENT.
Part: ATTACH FITTING — CRACKED (T/E FLAP) · airframe 68,411 hrs · 24,833 cycles
REMOVE I/B FLAP ACTUATOR CYLINDER ATTACH FITTING STEP'S 1 THRU 8 RIGHT SIDE. REMOVED FLAP ACTUATOR AND INSTALLED IAW MM 27-52-01-2 AND ACCOMPLISHED EO 8-5720- 7-2302 STEP NR 1 THRU NR 8 RIGHT SIDE I/B FLAP ACTUATOR CYLINDER ATTACH FITTING REPLACEMENT.
Part: SPAR CAP — DAMAGED (HORIZ STAB) · airframe 68,411 hrs · 24,833 cycles
NR S 15 COMPLY WITH EA8-5510-73851. STABILIZER HORIZONTAL ELONGATED HOLE IN HORIZONTAL STAB UPPER REAR SPAR CAP AD 52-22-10. COMPLIED WITH EA8-5510-73851.
Part: STRUCTURE — CORRODED (CARGO DOOR) · airframe 68,411 hrs · 24,833 cycles
COMPLY WITH EA 8-5310-73850 FUSELAGE - CORROSION ON LWR AFT CARGO DOOR LWR RAIL EXTENSION. CLOSING ACTION ON 11/17/03, ON N/R S00011. COMPLIED WITH EA 8-5310-73850.
2001
Part: ENGINE — SHUTDOWN (NR 2)
INFLT SHUTDOWN OF NR 2 ENG IN DESCENT THROTTLES RETARDED.
Part: ARM — CRACKED (RUDDER PEDAL) · airframe 65,695 hrs · 23,489 cycles
CAPT'S RUDDER PEDAL TORQUE TUBE ARM ASSY CRACKED AT I/B SIDE INPUT ROD ATTACH POINT RT RUDDER PEDAL. *S/D* REMOVED AND REPLACED RT ARM ASSY PER DAC CMM 27-21-02.
2000
Part: FASTENER — CORRODED (WS 264)
SNRM #N00581 - RIGHT WING LWR SKIN SURFACE DOUBLER STRAP AT BS XOR & 264 & INNER REAR SPAR APPROX. HAS A CORRODED SHEARED FASTENER. ** S/D ** REMOVED FASTENER, EDDY CURRENTED SURFACE INSP WAS COMPLIED WITH. INSTALL & TORQUED BOLT PER DPS 3.67-60 & MM 20-50-2.
1999
Part: SPAR WEB — CRACKED (RT WING)
NR 129 - RT WING REAR SPAR WEB HAS CRACK EMANATING INBD FROM RADIUS OF APU FUEL PUMP HOLE. CRACK APPROX 2.5 INCHES IN LENGTH VER BY NDT. STOP DRILLED CRACK AND PLUG HOLE IAW SRM 51-00-02 AND 53-00-01 WEB DOUBLER INSTALL PER EA 8-5710-40417.
1998
Part: FRAME — CRACKED (BS 459)
STA 459 Z=-78, X=-63 A CRACK WAS FOUND ON THE FRAME LT SIDE. REF NRC NR N 2064. REPAIRED FRAME IAW SRM 53-30-00 FIG 5.
Part: FRAME — CRACKED (BS 459)
VCE: N2103 - AT STA NR 459 Z= -78, X = - 63 A CRACK WAS FOUND ON THE FRAME (RT SIDE). REF NRC NR N2064. REPAIRED FRAME IAW SRM 53-30-00, FIG 5.
1997
Part: CLIP — CRACKED (WS 402)
AT STA XORS - 402, STRINGER NR 37, FOUND CLIP CRACKED ON RIGHT WING LOWER SURFACE. *S/D* REMOVED AND REPLACED CLIP (REF DWG ARB 0807), PER SRM 51-31-01.
Part: CLIP — CRACKED (WS 402)
AT XORS - 402, STRINGER NR 36, FOUND CLIP CRACKED ON RIGHT WING LOWER SURFACE. *S/D* REMOVED AND REPLACED CLIP (REF DWG ARB 0807), PER SRM 51-31-01.