N364FE
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
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.
24 reports on file, 1998-08-18 – 2003-12-08.
Part: PRESSURE SWITCH — FAILED (PNEUMATIC SYS) · airframe 65,332 hrs · 26,146 cycles
RECEIVED NR 1 MANIFOLD FAIL ALERT AT FL350. COULD NOT MAINTAIN CABIN PRESSURE. RAN RED TABS AND DIVERTED TO DEN. FOUND LEFT WING PRESSURE SWITCH FAULT BALL NO LEAKS NOTED. PERFORMED DECAY CHECK PER MD-10 MM 36-00-01-5 DECAY CHECK WITHIN LIMITS. REMOVED AND REPLACED PNEUMATIC MANIFOLD FAULT INDICATOR IAW FIM 36-23. PER MOCC REQUEST, REMOVED AND REPLACED LOOP 1A D1-88 SENSING ELEMENT IAW MM 36-23-02-4. ACCOMPLISHED PNEUMATIC SYSTEM ADJUSTMENT AND TEST AS REQUIRED PER MM 36-00-03-5. OPS CHECKED NORMAL NO DEFECTS NOTED. NO MANIFOLD FAIL INDICATION. RAN ENGS NR 1, 2, 3 DURING CHECK PER MD-10 JRH.
Part: BULKHEAD — CRACKED (ZONE 200) · airframe 64,789 hrs · 25,865 cycles
COMPLY WITH E.A.8-5310-70387. FUSELAGE-MAINFRAME-REPAIR OF STA 1987 BULKHEAD P/N AJC7066-1. CLOSING ACTION ON 05-27-03 ON N/R C00019. COMPLIED WITH E.A.8-5310-70387.
Part: SKIN — CRACKED (ZONE 600) · airframe 64,789 hrs · 25,865 cycles
NR S 17 COMPLY WITH E.A.8-5710-70392.WINGS-RT-FIXED LEADING EDGE BEADED DOUBLER REPAIR ACB 1242. CLOSING ACTION ON 05/23/03. COMPLIED WITH E.A.8-5710-70392.
Part: CLIP — DAMAGED (ZONE 200) · airframe 64,789 hrs · 25,865 cycles
AFT FUSELAGE PENTHOUSE CANTED FRAME AT Y=2029.88. HAS REPAIRS, SHOULD BE REPLACED PER E.O.8-5310-7-5000.PT 1. CLOSING ACTION ON 02/22/03. REMOVED AND REPLACED CLIP IAW E.O.8-5310-7-5000.PT1 AND SRM 51-31/01.
Part: RUB STRIP — CRACKED (DOOR) · airframe 64,789 hrs · 25,865 cycles
LT PATIO DOOR UPPER STAINLESS STRIP CRACKED AND CRUSHED. CLOSING ACTION ON 05/24/03. REMOVED CLOSEOUT STRIP IAW SRM 51-31-01.FAB NEW RUB STRIP ON TRAVLER T2/33374, LOCATED AND DRILLED NEW PART IAW SRM 51-31-01.INSTALLED RUB STRIP IAW SRM 51-31-01
Part: CONTROL VALVE — FAILED (THRUST REVERSER) · airframe 64,789 hrs · 25,865 cycles
N 860 #2 O/B T/R FAILS TO AUTO-RESTOW CHECK. CLOSING ACTION ON 05/24/03. REMOVED AND REPLACED DIRECTI0NAL CONTROL VALVE IAW M/M 78-31-11-2, LEAK TO BE ACCOMPLISHED ON W/C 78X3501CMR.
Part: RIB — CRACKED (NR 3 NACELLE) · airframe 64,789 hrs · 25,865 cycles
NR 855 NR 3 ENGINE RTCORE COWL FWD RIB CRACKED AT UPPER L/E RADIUS. CLOSING ACTION ON 05/24/03. REMOVED FASTENERS FOR ACCESS IAW SRM 51-31-01. WELLED CRACK ON MAE TRAVELER T2/336399 IAW SRM 54-31-01. REINSTALLED FASTNERS IAW SRM 51-35-01, PAINTED TEFLON PAINT IAW SRM 51-21-01 INSTALLED CORE COWL IAW M/M 71-13-01-0.
Part: HINGE — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 64,789 hrs · 25,865 cycles
S 16 COMPLY WITH E.A.8-5740-70384. WINGS INBD FLAP OUTBD HINGE SUPPORT FITTING TO WING ATTACH HOLES REWORK. CLOSING ACTION ON 05/19/03. COMPLIED WITH E.A.8-5740-70384.
Part: HINGE — CORRODED (TE FLAPS) · corrosion level 2 · airframe 64,789 hrs · 25,865 cycles
S 14 C/W E.A.8-5740-70390. WINGS-RT INBD FLAP HINGE ASSY CORROSION REWORK. CLOSING ACTION ON 05/17/03. COMPLIED WITH E.A.8-5740-70390.WINGS R/H INBD FLAP HINGE ASSY CORROSION REWORK.
Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 64,789 hrs · 25,865 cycles
NR 200 RT PATIO DOOR NR 10 FRAME CRACKED AS MARKED. STOPPED DRILL CRACK IAW MD-10 SRM 53-30-00. FAB ANGLE REPAIR IAW MAE TRAVLER T2/333232. LOCATED AND DRILLED ANGLE IAW MD-10 SRM 53-30-00, INSTALLED ANGLE REPAIR IAW SRM 51-31-01, 51-33-01.
Part: PROXIMITY SWITCH — INOPERATIVE (MLG) · airframe 64,498 hrs · 25,723 cycles
WHEN GEARS WERE LOWERED, ALL 3 GEAR INDICATED UNSAFE ON MAIN GEAR INDICATORS AND CONFIGURATION PAGE. NO ABNORMAL YAW OR NOISE. RECYCLED GEAR AND GOT 3 GOOD DOWN INDICATIONS. REMOVED AND REPLACED PROXIMITY SWITCH ELECTRONICS UNIT IN REF TO MD1 0-10 M/M 31-71-01-2. JACKED AIRCRAFT IAW MD10-10 M/M 07-11-00-2 AND CYCLED GEAR SEVERAL TIMES IAW MD10-10 M/M 32-30-00-5 ALL INDICATIONS NORMAL.
Earlier reports · 1998–2002 · 13 reports
2002
Part: DETECTOR — INOPERATIVE (PNEUMATIC SYS) · airframe 63,145 hrs · 25,032 cycles
ON CLIMBOUT NR 2 MANIFOLD FAIL ILLUM'D. NR 2 MANIFOLD FAIL DET LOOP INOP, DO NOT PRESS PNEU SYS NR 2 EXCEPT FOR ENG START.
2001
Part: VANE — GOUGED (T/E FLAP) · airframe 62,589 hrs · 24,717 cycles
LEFT HAND OUTBOARD FLAP VANE HAS GOUGE. REMOVED AND REPLACED FLAP PER SRM 51-71-00.
Part: SKIN — CRACKED (T/E FLAP) · airframe 62,589 hrs · 24,717 cycles
LEFT HAND INBOARD FLAP OUTER SKIN HAS .5 INCH CRACK. REMOVED AND REPLACED SKIN PER SRM 57-00-01.
Part: SPLICE — CRACKED (FUSELAGE) · airframe 62,589 hrs · 24,717 cycles
CTR CARGO BILGE AREA LEFT LONGERON 46 BETWEEN BS 1744 & 1761 LONGERON SPLICE CRACKED. REMOVED AND REPLACED SPLICE PER SRM 51-21-01, 51-35-01.
Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 62,589 hrs · 24,717 cycles
IN CTR CARGO AT BS 1521 BILGE AREA BETWEEN LONGERONS R44 & R46 CRACK IN BULKHEAD ATTACH ANGLE. REMOVED AND REPLACED TEE CHORD PER SRM & AEA0453-1 & SRM 51-39-01.
Part: SPLICE — CRACKED (FUSELAGE) · airframe 62,589 hrs · 24,717 cycles
CTR CARGO BILGE AREA L47 BETWEEN BS 1741 & 1761 LONGERON SPLICE CRACKED. REMOVED AND REPLACED SPLICE PER SRM 51-23-01, 51-00-00.
Part: SPLICE — CRACKED (FUSELAGE) · airframe 62,589 hrs · 24,717 cycles
IN CTR CARGO BILGE AREA BETWEEN BS 1701 & 1721 CRACK ON LONGERON SPLICE 51L. REMOVED AND REPLACED LONGERON SPLICE PER SRM 51-23-01 & 51-00-00.
Part: AILERON — CORRODED (RT WING) · airframe 62,589 hrs · 24,717 cycles
SIX SEPARATE AREAS ON RT OUTBOARD AILERON LWR CORRODED. REMOVED AND REPLACED AILERON PER IAW AMM 27-10-02-4.
2000
Part: WEB — CRACKED (RT MLG WW)
DURING MAINTENANCE, 3.0 INCH CRACK WAS FOUND ON RIGHT/CENTER WHEELWELL WEB. CRACK AFFECTED UPPER SPLICE WEB, P/N AEA0161-1, RT SIDE, AND AEA0501-1. (X)
1999
Part: BOLT — CORRODED (BS 275)
N2764, DURING A/C P-F CONV AT AERONAVALI, A SUSPECTED BOLT FAILURE WAS FOUND AT STA Y=275 FOR ATTACH P/N ABA7003-2, ABA7023-1, NBA6044-15 AND ABA7171. REPAIR WAS ACCOMPLISHED IAW EA NR 8-5311-44057 AND IT WAS APPROVED PER FEDEX 8110-3 DATED 29 APR 99. THE APPROVAL IS FOR 18 FLTS OR UPON REACHING LONG BEACH WHICHEVER COMES FIRST.
1998
Part: SPAR — CRACKED (HORIZ STAB)
N2420 - DURING A/C PF CONVERSION AT AERONAVALI AND ACCOMPLISHMENT OF DAC SB 55-17, R3, AD 88-03-08, A CRACK WAS FOUND ON THE HORIZONTAL STAB. REPAIR ATTEMPS TO REMOVE CRACK DAMAGE BY LOCAL BLENDING AND PERF HFEC TO QUAN DAMAGE. B/P EQUIVALENT BOLT IS REINSTALLED WITH SEALANT IAW EA NR 8-5510-41811.
Part: WEB — CRACKED (BS 2017)
N0527 - DURING AC P-F CONV AT AERONAVALI, A CRACK 0.87 IN LONG WAS FOUND ON WEB OF UPPER TORQUE BOX PLANE AT Y=2017 AND RBL = 20. SRM 53-00-01, FIG 4 SHEET 2 WEB REPAIR COULD NOT BE ACCOMPLISHED. REPAIR TO STOP DRILL CRACK AND VERIFY CONTAINMENT. THEN INSTALL TITANIUM REPAIR DOUBLER AND STIFFENER ANGLES IAW EA NR 8-5317-41822.
Part: DOUBLER — CORRODED (WS 264)
N0235 - DURING A/C P-F CONV AT AERONAVALI, CORROSION WAS FOUND ON LT UPPER WING AND MLG DOUBLER, TYPICAL PER DC10 SRM 57-00-01, FIG 8. THE AMOUNT OF DAMAGE FOUND ON PN ARB0866-1 IS NOT COVERED BY SRM. REPAIR REMOVES ALL CORROSION BY CUTTING OUT DAMAGE AND THEN VERIFIES CONTAINMENT PRIOR TO INSTALLING FILLERS AND EXT DOUBLERS PER EA NR 8-5710-39523.