N058FE
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
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.
17 reports on file, 1998-04-29 – 2004-09-04.
Part: PANEL — DEBONDED (ZONE 500) · airframe 49,035 hrs · 23,532 cycles
FINGER DOUBLERS DISBONDED INSIDE LEFT WING TRAILING EDGE FAIRING BETWEEN XW 373 AND XORS 486, ACCESS THROUGH 641 MB. REMOVED ARC0584-1 SKIN FOR REPLACEMENT IAW DC10 SRM 51-35-01, 51-33-01 VOL II. FABRICATED NEW ARC0584-1 SKIN ASSEMBLY IAW DAC DWG 0584. INSTALLED NEW ARC0584 IAW DC10 SRM 51-33-24, 51-35-01 AND 51-38-01 VOL II AND EA 8-5710-77629. REMOVED PANEL P/N ARC0810-503 AND ARC0810-184 FOR ACCESS. REINSTALLED BOTH PANELS IAW DC10 SRM 51-31-01 VOL II. REFERENCE N/R N00544.
Part: SKIN — DAMAGED (ZONE 500) · airframe 49,035 hrs · 23,532 cycles
LEFT WING TRAILING EDGE SKIN AFT OF MAIN LANDING GEAR LOWER SURFACE REQUIRES FABRICATION. FABRICATED DOUBLER AND SKIN IAW DAC DWG ARC0468, BONDED SKIN AND DOUBLER IAW TPS 1001 REV E AND DAC DWG ARC0468 AND EA 9-5710-81448. ALODINED AND PRIMED CONTACT UPPER SURFACE IAW DC 10 SRM 51021-01 VOL II, MARKED FX ARC0468-9 FOR SKIN PART AND FX ARC0468 DOUBLER PART IAW FEDEX GMM 7-0-1001, REFERENCE N/R N01745.
Earlier reports · 1998–2001 · 15 reports
2001
Part: ENGINE — DAMAGED (NR 1)
PER ATC'S NOTIFICATION NR 1 ENGINE LOSING PARTS AND LOSS OF NR 1 EGT.
Part: THRESHOLD — CORRODED (FUSELAGE) · airframe 43,460 hrs · 21,049 cycles
CENTER CARGO DOOR AFT CORNER DOOR SILL THRESHOLD HAS HEAVY SURFACE CORROSION JUST AFT OF NR 5 SPOOL FITTING. *S/D* REMOVED AND REPLACED PER SRM 51-21-01, 51-31-01 VOL II.
Part: THRESHOLD — CORRODED (FUSELAGE) · airframe 43,460 hrs · 21,049 cycles
CENTER CARGO DOOR FWD CORNER DOOR SILL THRESHOLD HAS HEAVY SURFACE CORROSION FWD OF NR 1 SPOOL FITTING. *S/D* REMOVED AND REPLACED DOUBLER AND HI-LOKS PER EA 8-5310-56792.
Part: RIB — CRACKED (HORZ STAB) · airframe 43,460 hrs · 21,049 cycles
LT HORIZONTAL STAB INBD CTR L/E OTBD RIB LWR CHORD STRAP SUPPORT CRACKED. CRACK 6 INCHES LONG IN CHORD RADIUS AT STA XFS-241.28. *S/D* REMOVED AND REPLACED RIB CHORD PER SRM 51-00-01 & EA 8-5510-56793.
Part: ANGLE — CRACKED (HORZ STAB) · airframe 43,460 hrs · 21,049 cycles
RIGHT HORIZ STAB CTR L/E OUTBOARD SIDE UPPER ROW NUTPLATE RETAINER/LAND HAS 2 FT CRACK AT STA XFS 166. *S/D* REMOVED AND REPLACED CHORD ANGLE PER SRM 55-10-01.
Part: MANIFOLD — FAILED (PNEUMATIC SYS) · airframe 28,083 hrs · 14,025 cycles
WHEN APPLYING MAX PWR FOR T/O, RECEIVED NR 2 MANIFOLD FAILURE WITH PNEU MANIFOLD FAILURE ON OVERHEAD PNL.
Part: TRANSFER TUBE — FAULTY (NR 2 TANK)
APPROX 45 MIN AFT T/O FUEL QUANTITY IN NR 2 TANK STARTED TO INCREASE. UNABLE TO STOP TRANSFER FROM OUTBOARD INTO NR 2 TANK, AND UNABLE TO FEED FUEL FROM NR 2 TANK TO OUTBOARD ENG USING EITHER TRANSFER OR CROSSFEED. REMOVED AND REPLACED NR 2 TANK FUEL LT TRANSFER LINE ASSY PER MM 28-10-00. FUEL SYS OPS CK NORMAL.
2000
Part: WEB — CRACKED (TORQUE BOX) · airframe 41,889 hrs · 20,420 cycles
LWR TORQUE BOX (Y) 2122.8 (X) -40, WEB HAS CRACK IND ADJACENT TO FASTENER COLLAR AT UPPER EDGE JUST I/B OF RIGHT HORIZ STAB PIVOT SUPPORT INSIDE DOOR 316BB. *S/D* REMOVED AND REPLACED PER EA 8-5310-49669.
Part: FASTENER — BROKEN (HORIZONTAL STAB) · airframe 41,889 hrs · 20,420 cycles
RT HORIZ STAB PIVOT SUPPORT, LOWER HALF, HAS 2 BROKEN FASTENERS WHERE PRIMARY AND SECONDARY ATTACH TO UPPER EDGE OF LOWER TORQUE BOX. (Y) 2122.8 (X) -41.7 INSIDE DOOR 316BB. *S/D* REMOVED AND REPLACED FASTENERS PER SRM 53-00-01.
1999
Part: SEAL — FAILED (RT WING)
NR 3 PNEUMATIC MANIFOLD FAIL LIGHT CAME ON, WING ANTI-ICE WAS USED. FOUND MASSIVE LEAK BETWEEN SLATS R4 AND R5. REPLACED PERISEAL ON CONNECTOR SLEEVE. PRESS NR 3 MAN AND RAN NR 3 PACK TO LEAK CK DUCTS, CK NORM. ACCOMPLISHED TEST OF WING ANTI-ICE SYS PER MM 30-11-00-2.
1998
Part: CASTING — CORRODED (RT TE FLAP)
N/R N00434 STA-LAX: RT WING INBD FLAP, INBD FLAP DRIVE MOUNT HOLE (INBD) HAS DEEP CORROSION AROUND SECTION OF BUSHING. REMOVED CORROSION REF SRM 51-21-01. C/W HFEC REQUIRED BY ENGINEERING NO CRACK INDICATION FOUND. REF: EA 8-5750-38590.
Part: ACTUATOR — DAMAGED (RT ELEVATOR)
SNRM N00048 STS-LAX: Rt I/B ELEVATOR ACTUATOR. X-RAY FILM EXHIBITS IRREGULAR GEOMETRIC PATTERNS OF DIFFERENT DENSITIES THROUGHOUT PISTON WALL (PRIMARY PATH). REMOVED AND REPLACED RT INBD ELEVATOR ACTUATOR. CLOSED 7/16/98.
Part: COWL — CRACKED (NR 2 ENGINE)
STA-LAX NR 2 ENGINE NOSE COWL INLET L/E HAD A 25 INCH CRACK AT 2:30 O'CLOCK POSITION. *S/D* REMOVED AND REPLACED NOSE COWL PER M/M 54-22-01-2.
Part: ANGLE — CORRODED (BS 1110)
FWD LOWER BELLY BS 1110 MOUNTING STRUCTURE FOR LINEAR ACCELEROMETERS ARE BADLY CORRODED, LOWER FACE. *S/D* REMOVED AND REPLACED FWD AND AFT SUPPORT STRUCTURE FOR LINEAR ACCELEROMETERS AS PER SRM 51-0-00 AND DAC DRAWING NR AAN7081. REF N/R'S 00641 AND N00642. LINEAR ACCELEROMETERS REINSTALLED AND REALINED BY BOEING A/C. REF SNRM NR 00533.
Part: SWITCH — FAILED (LT MLG)
98-0109, PILOTS PANEL RED LEFT GEAR LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION. S/O PANEL LEFT GEAR LIGHT EXTINGUISHED. PERFORMED RECYCLE OF GEAR AND LIGHT REMAINED ILLUMINATED ON PILOTS PANEL FOR LEFT GEAR. FEF1 32-30 AF-L.T/S AND FOUND LT MLG DOOR UPLATCH PROX SWITCH BAD 274911. WIRED PROX SWITCH AT TERMINAL STRIP EMPLOYEE NR 44389 OPS CHECK LMLG DOOR UPLOCK PROX SWITCH M/M 32-61-03 STEPS 13 A,B,C CHECKS GOOD. EMPLOY NR 31716 VERIFIED INSTALLATION EMPLOY NR 300892 PER 31-61-03.