N93738
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| CONTINENTAL AIRLINES INC | Operator | on 1976-05-25 | Operator named in NTSB report |
Accident & incident history
Operated by CONTINENTAL AIR LINES INC (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.
101 reports on file, 1995-01-02 – 1998-11-17.
Part: BEARING — WORN (NLG DOOR)
THE NOSE GEAR DOORS OPEN LIGHT ON BOTH THE FORWARD AND SECOND OFFICER'S PANELS WERE ILLUMINATED AFTER GEAR RETRACTION DEPARTING BWI. THE WARNING LIGHTS WERE ACCOMPANIED BY RUMBLING AIR NOISE. THE GEAR WAS CYCLED WITH NO CHANGE. THE AIRCRAFT WAS DIVERTED TO EWR AND THE GEAR EXTENDED NORMALLY FOR LANDING. MAINTENANCE FOUND THAT THE NLG FORWARD DOORS HAD WORN PARTS INCLUDING BEARING, BUSHINGS, SPACERS, 4H FITTING, AND BOLT. THE WORN PARTS WERE REPLACED. THE NOSE GEAR DOORS WERE ADJUSTED AND TESTED IAW MM 32-22-1, PAGE 501. A NOSE GEAR EXTENSION AND RETRACTION TEST WAS PERFORMED IAW MM 32-33-0, PAGE 501 AND OPERATION CHECKED GOOD.
Part: FITTING — CORRODED (RT TE FLAP)
INSPECTION FOUND RT WING NR 6 AND NR 8 FLAP TRACK ATTACH FITTINGS CORRODED. THE CORROSION WAS REMOVED AND THE FITTINGS WERE REPAIRED IAW ECRA 5740-01277.
Part: FITTING — CORRODED (RT TE FLAP)
INSPECTION FOUND THE NR 2 AND NR 3 FLAP TRACK FORWARD MOUNT FITTINGS CORRODED. THE FLAP TRACK FITTINGS WERE REPAIRED IAW ECRA 5740-01277.
Part: FITTING — CORRODED (BS 870)
RIGHT WING TO FUSELAGE AT BS 870 FACE AND BORE HAVE CORROSION. ACCOMPLISHED REPAIR BY OVERSIZE HOLE TO REMOVE CORROSION PER ECRA 5310-63775.
Part: SKIN — WORN (NR 8 SPOILER)
RT WING NR 8 SPOILER CENTER CHAFE PAD WORN AND TE WORN/MISSING. DENTS OUT OF LIMITS PER SRM 57-50-1 FIG 5. REMOVED SPOILER PANEL AND SENT OUT FOR REPAIR PER MM 27-62-1.
Part: FLOORBEAM — CORRODED (BS 1130)
FLOORBEAM TOP HAS SURFACE CORROSION FS 1130 RBL 12-12. REMOVED FASTENERS. CUT OUT ANGLE DAMAGE. FABRICATED NEW ANGLE, SPLICES. FABRICATED NEW FLOORBEAM TREATED AND INSTALLED PER SRM 51-10-2 AND 51-40-3.
Part: BOTTLE PIN — CORRODED (BS 870)
INSPECTION FOUND RT WING TO FUSELAGE BOTTLE PIN, BUSHING, AND RETAINING BOLT CORRODED AT BS 870. THE BOTTLE PIN, BUSHING, AND RETAINING BOLT WERE REMOVED AND REPLACED IAW MM 57-41-1, PAGE 403 AND 57-41-11, PAGE 404.
Part: AILERON TAB — DENTED (LT AILERON)
INSPECTION FOUND LT INBOARD AILERON TAB DENTED. THE AILERON TAB WAS REMOVED AND REPLACED IAW MM 27-10-31.
Part: SKIN — DELAMINATED (RT TE FOREFLAP)
INSPECTION FOUND RT INBOARD FOREFLAP SKIN DELAMINATED AT LOWER SURFACE INBOARD MOST END. THE FOREFLAP WAS REMOVED AND REPLACED IAW MM 27-51-11.
Part: SKIN — CORRODED (LT ELEVATOR)
INSPECTION FOUND CORROSION IN LT ELEVATOR UPPER TRAILING EDGE SKIN BETWEEN STATIC WICKS. THE CORROSION WAS REMOVED, DOUBLERS WERE INSTALLED IAW SRM 55-20-03.
Part: SEAT TRACK — CORRODED (BS 348)
INSPECTION FOUND SEAT TRACK CORRODED AT STA 348, LBL 24. THE SEAT TRACK WAS REMOVED AND A NEW TRACK WAS INSTALLED IAW SRM 53-10-5 AND 51-10-2.
Part: FITTING — CORRODED (RT TE FLAP)
INSPECTION FOUND FITTING CORRODED WHERE RT WING NR 5 FLAP TRACK MOUNTS. THE FITTING AND BUSHING WERE REMOVED AND REPLACED IAW MM 32-11-51, PAGE 401 TO 403 AND MM 20-70-7.
Part: FLOORBEAM — CORRODED (BS 400)
INSPECTION FOUND FLOORBEAM CORRODED AROUND MOUNT HOLES AT STA 400, RBL 30. THE CORRODED AREA WAS CUT OUT IAW SRM 53-10-8. A REPAIR WAS INSTALLED IAW SRM 51-10-2 AND 53-10-8.
Part: PANEL — CRACKED (RT WING)
INSPECTION FOUND A .5 INCH CRACK IN RT WING UPPER PANEL FORWARD OF NR 7 SPOILER. THE CRACK WAS STOP DRILLED IAW SRM 51-10-1. DOUBLERS WERE INSTALLED IAW SRM 57-30-4, FIGURE 10, 51-10-2 AND 51-30-2.
Part: CHANNEL — CORRODED (BS 1140)
INSPECTION FOUND RT AFT LAV FLOOR WAS HAT CHANNEL CORRODED AT FS 1140, RBL 24 TO 60. THE HAT CHANNEL WAS REMOVED AND A NEW CHANNEL WAS INSTALLED IAW SRM 51-10-2, 51-30-1, AND 51-20-1.
Part: ANGLE — CRACKED (VERT STAB)
INSPECTION FOUND A .25 INCH CRACK IN VERTICAL STABILIZER FORWARD RT DORSAL FIN ATTACH ANGLE. THE ANGLE WAS REMOVED AND REPLACED IAW EA 5340-01012.
Part: SKIN — CORRODED (LT ELEVATOR)
INSPECTION FOUND LT ELEVATOR SKIN UPPER SURFACE CORRODED AROUND STATIC WICK BASE. THE CORRODED AREA WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 55-20-03.
Part: ANGLE — CRACKED (NR 2 LE SLAT)
INSPECTION FOUND A .375 INCH CRACK IN NR 2 SLAT PANEL ATTACH ANGLE BY ANTI-ICE DUCT. THE CRACK WAS STOP DRILLED IAW SRM 51-10-1. A REPAIR ANGLE WAS INSTALLED IAW SRM 51-40-4, FIGURE 4.
Part: PAD — CORRODED (RT TE FLAP)
INSPECTION FOUND CORROSION AT RT WING AFT FALSE SPAR PAD WHERE NR 5 AND NR 6 FLAP TRACKS MOUNT. THE FLAP TRACK MOUNT PADS WERE REMOVED IAW SRM 51-30-2. NEW MOUNT PADS WERE INSTALLED IAW SRM 51-10-6, 51-10-1, AND 51-30-2.
Part: ANGLE — CRACKED (NR 3 LE SLAT)
INSPECTION FOUND A .375 INCH CRACK IN NR 3 SLAT LOWER ATTACH ANGLE FOR PANELS AT ACTUATOR ATTACH AREA. THE CRACK WAS ROUTED OUT. AN ANGLE DOUBLER WAS INSTALLED IAW SRM 51-40-4, FIGURE 3.
Part: CHANNEL — CORRODED (BS 1140-1170)
INSPECTION FOUND AFT LAV FLOOR HAT CHANNEL CORRODED AT FS 1140-1170, RBL 24. THE HAT CHANNEL WAS REMOVED AND A NEW CHANNEL WAS INSTALLED IAW SRM 51-30-2, PAGE 2, 51-10-2, AND 51-40-5.
Part: PANEL — CRACKED (RT WING)
INSPECTION FOUND A .375 INCH CRACK IN RT WING UPPER PANEL FORWARD OF NR 12 SPOILER INBOARD HINGE AREA. THE CRACK WAS STOP DRILLED IAW SRM 51-10-1. DOUBLERS WERE INSTALLED IAW SRM 57-30-4 AND 51-30-2.
Part: SKIN — CRACKED (RT TE FOREFLAP)
INSPECTION FOUND A .3125 INCH CRACK AT RT OUTBOARD FOREFLAP LOWER LEADING EDGE SKIN ABOVE NR 7 FLAP TRACK AREA, 54 INCHES FROM INBOARD END. A DOUBLER WAS INSTALLED IAW SRM 57-50-4, FIGURE 1, 51-10-6, AND 51-10-2.
Part: ANGLE — CRACKED (RT TE MIDFLAP)
INSPECTION FOUND A 1 INCH CRACK IN ANGLE AT RT INBOARD MIDFLAP JUST OUTBOARD OF NR 5 FLAP CARRIAGE. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-10-1.
Part: SUPPORT — CRACKED (BS 1120)
INSPECTION FOUND A 1 INCH CRACK IN FLOOR SUPPORT INTERCOSTAL AT FS 1120, BL 0. THE TOP FLANGE WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW SRM 51-30-2, 51-10-2, AND 51-20-1 FIGURE 7.
Part: SKIN — CRACKED (RT TE MIDFLAP)
INSPECTION FOUND A .75 INCH AND .1093 INCH CRACK IN RT WING LOWER TRAILING EDGE OF INBOARD MIDFLAP, 34 INCHES FROM INBOARD END. THE CRACKS WERE STOP DRILLED IAW SRM 51-10-1. A REPAIR DOUBLER WAS INSTALLED IAW SRM 51-10-2 AND 57-50-4, FIGURE 1.
Part: INTERCOSTAL — CRACKED (BS 970)
INSPECTION FOUND A .5 INCH CRACK AT TOP FLANGE OF INTERCOSTAL THREE INCHES AFT OF FLOOR FRAME FS 970, BL 0. THE TOP FLANGE WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW SRM 51-30-2 AND 51-20-1.
Part: TRACK — CORRODED (NR 4 FLAP)
INSPECTION FOUND NR 4 FLAP TRACK FORWARD CLEVIS CORRODED ON BOTH SIDES. THE FLAP TRACK ASSEMBLY WAS REPLACED IAW MM 57-40-00.
Part: STRINGER — CORRODED (BS 683-688)
INSPECTION FOUND STRINGER 26R CORRODED IN FORWARD CARGO COMPARTMENT AT STA 683 TO 688. THE CORROSION WAS REMOVED IAW SRM 51-10-6. THE CORRODED AREA WAS CUT OUT IAW SRM 53-30-3, FIGURE 6. A REPAIR WAS INSTALLED IAW SRM 53-30-3, FIGURE 6 AND 51-10-2.
Part: SUPPORT — CORRODED (BS 1034)
INSPECTION FOUND CABIN FLOOR SUPPORT CORRODED AT FS 1034, RBL 12-24. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 53-00 AND 51-10-2.
Part: SUPPORT — CORRODED (BS 1034)
INSPECTION FOUND FLOOR SUPPORT CORRODED AT FS 1034, RBL 45-65. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-30-2.
Part: SKIN — DENTED (FUSELAGE)
INSPECTION FOUND FUSELAGE SKIN AND RIB DENTED JUST AFT OF NLG AFT DOOR. THE RIB AND SKIN WERE REMOVED AND REPLACED IAW SRM 51-10-1.
Part: CARRIAGE — CORRODED (NR 7 TE FLAP)
INSPECTION FOUND NR 7 FLAP OUTBOARD FLAP INBOARD CARRIAGE CORRODED. THE FLAP CARRIAGE WAS REMOVED AND REPLACED IAW MM 57-53-2.
Part: ANGLE — CRACKED (RT WING)
INSPECTION FOUND A 4 INCH CRACK IN ANGLE AND DOUBLER AT RT WING FIXED LEADING EDGE RIB AT SLAT STA 0. THE DOUBLER WAS REMOVED IAW SRM 51-30-2. THE CRACK WAS STOP DRILLED IAW SRM 51-10-1. AN ANGLE REPAIR WAS INSTALLED IAW SRM 51-30-2, 51-10-2, AND 51-40-3, FIGURE 1.
Part: TRACK — CORRODED (NR 8 TE FLAP)
INSPECTION FOUND RT WING NR 8 FLAP TRACK FORWARD ATTACH LUG AREA CORRODED. THE FLAP TRACK ASSEMBLY WAS REPLACED IAW MM 57-40-00.
Part: HAT CHANNEL — CORRODED (BS 1150)
INSPECTION FOUND HAT CHANNEL CORRODED AT FS 1150, LBL 24. THE HAT CHANNEL WAS REMOVED AND A NEW CHANNEL WAS INSTALLED IAW SRM 51-10-1 AND 51-10-2.
Part: BRACKET — CRACKED (NR 5 LE FLAP ACT)
INSPECTION FOUND A .5 INCH CRACK IN OUTBOARD BRACKET WHERE RT WING NR 5 LEADING EDGE FLAP ACTUATOR MOUNTS. THE BRACKET WAS REMOVED AND A NEW BRACKET WAS INSTALLED IAW SRM 51-10-2 AND 51-30-2.
Part: SKIN — CORRODED (RT ELEVATOR)
INSPECTION FOUND RT ELEVATOR SKIN LOWER SURFACE CORRODED. THE CORRODED AREA WAS CUT OUT AND A NEW FITTING AND DOUBLER WERE INSTALLED IAW SRM 55-20-3, FIGURE 2, PAGE 2, 51-10-2, AND 51-40-5.
Part: PAD — CORRODED (NR 3 FLAP TRACK)
INSPECTION FOUND BOTTOM SURFACE OF SPOILER BEAM PAD CORRODED WHERE NR 3 FLAP TRACK MOUNTS. THE FLAP TRACK MOUNT PAD WAS REMOVED AND REPLACED IAW SRM 51-10-2, PAGE 1 AND 51-30-2, PAGE 14.
Part: BRACKET — CRACKED (LE FLAP ACT)
INSPECTION FOUND A .5 INCH CRACK IN BRACKET WHERE RT WING NR 6 LEADING EDGE FLAP ACTUATOR MOUNTS. THE BRACKET WAS REMOVED AND A NEW BRACKET WAS INSTALLED IAW SRM 51-40-3, 51-30-2, AND 51-10-2.
Part: TRACK — CORRODED (NR 5 TE FLAP)
INSPECTION FOUND RT WING NR 5 FLAP TRACK FORWARD LUG AREA CORRODED. THE FLAP TRACK ASSEMBLY WAS REPLACED IAW MM 57-40-00.
Part: RIB — CRACKED (LT TE MIDFLAP)
INSPECTION FOUND A 1.5 INCH CRACK IN LT O/B MIDFLAP O/B END RIB FORWARD OF MID SPAR. THE CRACK WAS STOP DRILLED. A DOUBLER ANGLE WAS INSTALLED IAW SRM 51-30-2, PAGE 4.
Part: DOUBLER — CRACKED (LT I/B FLAP)
INSPECTION FOUND A .5 INCH CRACK IN DOUBLER INSIDE LT INBOARD FLAP AT AFT END OF INBOARD FLAP TRACK CARRIAGE SPINDLE CUTOUT. THE DOUBLER WAS REMOVED AND A NEW DOUBLER WAS INSTALLED IAW SRM 51-10-1 AND 51-30-2.
Part: SUPPORT — CORRODED (BS 1130-1150)
INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 1130-1150, RBL 12. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-10-6 AND 51-10-2.
Part: SUPPORT — CORRODED (BS 1067)
INSPECTION FOUND FLOOR SUPPORTS CORRODED AT FS 1067, RBL 12-24 AND RBL 45-65. THE FLOOR SUPPORTS WERE REMOVED AND A NEW SUPPORTS WERE INSTALLED IAW SRM 51-30-1AND 51-10-2.
Part: RIB — CRACKED (LT WING TIP)
INSPECTION FOUND A 1.5 INCH CRACK IN LT WING TIP RIB UPPER FLANGE BY INBOARD AFT CORNER OF FUEL VENT OUTLET. THE CRACK WAS STOP DRILLED IAW SRM 51-30-2. AN ANGLE REPAIR WAS INSTALLED IAW SRM 51-30-2, FIGURE 1.
Part: FLOORBEAM — CORRODED (BS 1050)
INSPECTION FOUND FLOORBEAM CORRODED AT TOP FLANGE SCREW HOLE FS 1050, RBL 35. THE CORRODED AREA WAS REMOVED AND A NEW SECTION OF FLOORBEAM WAS INSTALLED IAW SRM 51-10-1, 51-10-2, AND 53-10-5, FIGURE 7.
Part: SUPPORT — CORRODED (LAVATORY)
INSPECTION FOUND FORWARD LAV INBOARD WALL FLOOR SUPPORT CORRODED. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-10-1, PAGE 4.
Part: SPINDLE — CORRODED (NR 8 TE FLAP)
INSPECTION FOUND NR 8 FLAP CARRIAGE AFT SPINDLE CORRODED. THE NR 8 FLAP CARRIAGE ASSEMBLY WAS REMOVED AND REPLACED IAW MM 57-50-00.
Part: FLOOR — CORRODED (BS 1178-1183)
INSPECTION FOUND FLOOR WEB WITH CORROSION RUNNING INTO SPLICE AT FS 1178-1183, RBL 16. THE CORRODED AREA WAS CUT OUT AND A DOUBLER REPAIR WAS INSTALLED IAW SRM 51-40-2, FIGURE 1, 51-10-2, AND 51-30-2, PARAGRAPH 7.
Part: SUPPORT — CORRODED (BS 1140)
INSPECTION FOUND FLOOR SUPPORT CORRODED AT FS 1140, LBL 12. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-10-2, 51-10-1, AND 51-30-2.
Part: FLOORBEAM — CORRODED (BS 344)
INSPECTION FOUND FLOORBEAM CORRODED AT STA 344, LBL 22.5 TO 24.5. THE CORRODED SECTION OF FLOORBEAM WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW SRM 53-10-8 AND 51-30-2.
Part: SKIN — CORRODED (RT ELEVATOR)
INSPECTION FOUND CORROSION IN RT ELEVATOR SKIN UNDER OUTBOARD MOST STATIC WICK BASE. THE CORRODED AREA WAS CUT OUT. A NEW DOUBLER AND FITTING WERE INSTALLED IAW SRM 55-20-3, FIGURE 2, PAGE 2.
Part: TRACK — CORRODED (NR 3 TE FLAP)
INSPECTION FOUND CORROSION IN BORE WHERE BUSHINGS MOUNT ON LT AND RT SIDES OF NR 3 FLAP TRACK FORWARD CLEVIS. THE FLAP TRACK ASSEMBLY WAS REMOVED AND REPLACED IAW MM 57-40-00.
Part: SUPPORT — CORRODED (BS 1034)
INSPECTION FOUND FLOOR SUPPORT CORRODED AT FS 1034, RBL 24-45. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-10-1, 51-10-2, AND 51-30-2.
Part: FLAP TRACK — CORRODED (NR 6 TE FLAP)
INSPECTION FOUND RT WING NR 6 FLAP TRACK CORRODED AROUND FORWARD MOUNT HOLES. THE FLAP TRACK ASSEMBLY WAS REPLACED IAW MM 57-40-00.
Part: TRACK — CORRODED (NR 1 TE FLAP)
INSPECTION FOUND NR 1 FLAP TRACK PAD MOUNT CENTER HOLE CORRODED. THE FLAP TRACK ASSEMBLY WAS REMOVED AND REPLACED IAW MM 57-40-00.
Part: ANGLE — CRACKED (BS 950)
INSPECTION FOUND A .375 CRACK IN ANGLE AT INTERCOSTAL AT BS 950A-950B, BL 0. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-40-3, FIGURE 1 AND 51-30-2.
Part: WEB — CORRODED (BS 1122)
INSPECTION FOUND RT WEB CORRODED AT FS 1122, RBL 65. THE CORRODED AREA WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 51-10-2, 51-10-1, PAGE 4, AND 51-30-2.
Part: MOUNT — CORRODED (BS 312-344)
INSPECTION FOUND FORWARD LAV FLOORBOARD MOUNT FRAME AT STA 312-344 HAD CORROSION AROUND MOUNTING HOLES. THE MOUNT FRAME WAS REMOVED AND A NEW FRAME WAS INSTALLED IAW SRM 53-10-8.
Part: STRINGER — CRACKED (BS 720)
INSPECTION FOUND A 1 INCH CRACK IN STRINGER 15L AND 15R AT STA 720B. REPAIRS WERE INSTALLED IAW SRM 53-10-3 AND 51-10-2.
Part: SKIN — DENTED (LT AILERON TAB)
INSPECTION FOUND LT OUTBOARD AILERON TAB DENTED ON UPPER SURFACE WITH THE TRAILING EDGE BENT. THE AILERON TAB WAS REMOVED AND REPLACED IAW MM 27-10-41.
Part: PRESSURE PANEL — CRACKED (BS 930)
INSPECTION FOUND A .9375 INCH CRACK IN LT MLG WHEEL WELL CEILING PRESSURE PANEL JUST FORWARD OF WHEEL WELL LIGHT AT STA 930, LBL 48. THE CRACK WAS STOP DRILLED IAW BOEING DRAWING 65-89360. A DOUBLER WAS INSTALLED IAW BOEING DRAWING 65-89360.
Part: TRACK — CORRODED (NR 7 TE FLAP)
INSPECTION FOUND RT WING NR 7 FLAP TRACK ROLLER SURFACES CORRODED. THE FLAP TRACK ASSEMBLY WAS REMOVED AND REPLACED IAW MM 57-40-00.
Part: CARRIAGE — CORRODED (NR 5 TE FLAP)
INSPECTION FOUND RT WING NR 5 FLAP CARRIAGE SPINDLE CORRODED AT FORWARD AREA. THE NR 5 FLAP CARRIAGE ASSEMBLY WAS REPLACED IAW MM 57-50-00.
Part: RIB — CRACKED (RT TE MIDFLAP)
INSPECTION FOUND A 1 INCH CRACK IN RT WING INBOARD MIDFLAP RIB OUTBOARD OF INBOARD CARRIAGE SPINDLE MOUNT. THE CRACK WAS STOP DRILLED IAW SRM 51-10-1. A DOUBLER REPAIR WAS INSTALLED IAW SRM 57-10-5, FIGURE 1.
Part: RIB — CRACKED (RT WINGTIP)
INSPECTION FOUND A 2.75 AND 1 INCH CRACK IN RIB INSIDE RT WINGTIP, ACCESSED THROUGH PANEL NR 8811. THE CRACKS WERE STOP DRILLED IAW SRM 51-10-1. ANGLE REPAIRS WERE INSTALLED IAW SRM 51-40-3, FIGURE 1 AND 51-30-2.
Part: SKIN — CORRODED (RT ELEVATOR)
INSPECTION FOUND CORROSION IN RT ELEVATOR SKIN UNDER OUTBOARD CENTER STATIC WICK BASE. THE CORRODED AREA WAS CUT OUT, A DOUBLER AND FITTING WERE INSTALLED IAW SRM 55-20-3 FIGURE 2 PAGE 2.
Part: CARRIAGE — CORRODED (NR 2 LE FLAP)
INSPECTION FOUND NR 2 FLAP CARRIAGE AFT SPINDLE BUSHING CORRODED. THE NR 2 FLAP CARRIAGE ASSEMBLY WAS REMOVED AND REPLACED IAW MM 57-50-00.
Earlier reports · 1995–1997 · 32 reports
1997
Part: SKIN — CRACKED (NR 2 ENG INLET)
INSPECTION FOUND A 2 INCH CRACK BETWEEN TWO RIVETS OF NR 2 ENGINE LT S-DUCT EXTERIOR SKIN PANEL JUST BELOW AND AFT OF ENGINE INLET AREA. A DOUBLER REPAIR WAS INSTALLED IAW SRM 54-10-3.
Part: RIB — CRACKED (LT WING)
INSPECTION FOUND A 6 INCH CRACK IN RIB AT OUTBOARD SIDE OF LT WING FLUX VALVE CUTOUT. THE CRACK WAS CUT OUT. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-3 AND 51-10-2.
Part: WIRE — BROKEN (CABIN)
INSPECTION FOUND LT OVERWING EXTERIOR EMERGENCY EXIT LIGHT INOPERATIVE. MAINTENANCE FOUND A BROKEN WIRE AT LIGHT ASSEMBLY. THE WIRE WAS REPAIRED AND THE BATTERY WAS RECHARGED, OPERATION CHECKED GOOD IAW MM 33-50-0.
Part: SKIN — CRACKED (LT WING)
INSPECTION FOUND A .75 INCH CRACK IN LT WING UPPER TRAILING EDGE SKIN PANEL AT SECOND FROM INBOARD HINGE CUTOUT FOR NR 4 SPOILER. THE FASTENERS WERE REMOVED AND THE CRACK WAS STOP DRILLED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-30-04.
Part: FRAME — CRACKED (BS 1275)
INSPECTION FOUND A 1.5 INCH CRACK IN RT TORQUE BOX FRAME AT FS 1275. THE CRACK WAS LOCATED AT INBOARD END BELOW HORIZONTAL WEB. THE INBOARD WEB WAS REMOVED. TWO ANGLES WERE REMOVED. A FRAME REPAIR WAS FABRICATED IAW SRM 53-10-4. THE FRAME REPAIR AND WEB WERE INSTALLED IAW SRM 51-30-2, FIGURE 2 AND 51-10-6.
Part: SKIN — CRACKED (RT WING)
INSPECTION FOUND A 2 INCH CRACK IN LOWER SKIN OF RT WING TIP JUST OUTBOARD OF NR 8 SLAT. THE CRACK WAS STOP DRILLED IAW SRM 51-10-01. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-2 AND 51-20-4.
Part: SKIN — DENTED (LT TE MIDFLAP)
INSPECTION FOUND LT WING OUTBOARD MIDFLAP LEADING EDGE DENTED APPROXIMATELY 32 INCHES FROM INBOARD END. THE DENTED AREA WAS REMOVED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-50-4 AND 51-10-2.
Part: FITTING — BROKEN (CARGO DOOR)
INSPECTION FOUND AFT CARGO C-3 DOOR FORWARD LOWER STOP FITTING BROKEN OFF. THE FITTING WAS REMOVED AND REPLACED IAW SRM 51-10-1.
Part: SKIN — CRACKED (NR 4 LE SLAT)
INSPECTION FOUND A .5 INCH CRACK IN LOWER SURFACE OF LT WING NR 4 SLAT SKIN, OUTBOARD OF INBOARD TRACK. THE CRACK WAS STOP DRILLED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-30-5, 51-40-2, AND 51-10-2.
Part: SKIN — CRACKED (LT WING)
INSPECTION FOUND A 1 INCH CRACK IN LT WING FIXED LEADING EDGE AT CUTOUT ABOVE NR 3 SLAT OUTBOARD TRACK. THE CRACKED AREA WAS ROUTED OUT, DOUBLER AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 57-30-4.
Part: BATTERY PACK — DISCHARGED (CABIN)
INSPECTION FOUND AFT ENTRY EMERGENCY EXIT LIGHT INOPERATIVE. THE BATTERY PACK WAS REMOVED AND REPLACED.
1996
Part: ACTUATOR — LEAKING (NR 5 LE FLAP)
THE A-HYDRAULIC SYSTEM WAS LOST WHILE EN ROUTE FROM IAH TO AUS. THE LOSS WAS ACCOMPANIED BY ILLUMINATION OF PUMP LOW PRESSURE LIGHTS 1 AND 2. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 5 L/E FLAP ACTUATOR SEALS BLOWN. THE ACTUATOR WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL. LEAK AND OPERATIONAL CHECKS WERE GOOD. PART TOTAL CYCLES, 31,400.
Part: DUCT — BLOWN (NR 3 ENGINE)
THE NR 3 ENGINE FIRE WARNING LIGHT ILLUMINATED AFTER TAKEOFF. THE EMERGENCY CHECKLIST WAS COMPLIED WITH AND THE WARNING LIGHT WENT OUT. THE AIRCRAFT WAS RETURNED TO PHX WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 3 ENGINE 13TH STAGE BLEED AIR DUCT TO EJECTOR VALVE BLOWN. THE DUCT WAS REPLACED, THE ENGINE WAS RUN AND ALL CHECKS WERE GOOD.
Part: FUSES — BLOWN (CABIN)
INSPECTION FOUND THE EMERGENCY AISLE PATH LIGHTING INOPERATIVE IN FIRST CLASS CABIN. THE FORWARD BATTERY PACK FUSES WERE REPLACED AND OPERATION OF THE LIGHTS WAS RESTORED.
Part: SKIN — CRACKED (FWD FUSELAGE)
INSPECTION FOUND A 3 INCH CRACK IN FUSELAGE SKIN AFT OF RADOME AT 12 O'CLOCK POSITION. THE SKIN PANEL WAS REMOVED AND A NEW SKIN PANEL WAS FABRICATED AND INSTALLED IAW SRM 51-30-2.
Part: INTERCOSTAL — CRACKED (BS 1128)
INSPECTION FOUND A .75 INCH CRACK IN THE UPPER AFT RADIUS OF CABIN FLOOR INTERCOSTAL AT B.S. 1128, BL ZERO. A REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-40-3 AND SRM 51-30-2.
Part: STRINGER — CRACKED (WS 656.50)
INSPECTION FOUND NR 1 FUEL TANK STRINGER CRACKED ON HORIZONTAL FLANGE AT WS 656.50. THE CRACK WAS STOP DRILLED IAW SB 727-57A159. A REPAIR WAS FABRICATED AND INSTALLED IAW SB 727-57A159 AND EA 5762-01050, REV J.
Part: FLOORBEAM — CORRODED (BS 1130)
INSPECTION FOUND FLOOR BEAM LOWER CHORD CORRODED AT STA 1130, RBL 1 TO RBL 40. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-04, FIGURE 1 AND SRM 51-30-2.
Part: RUDDER — CHAFED (VERT STAB)
INSPECTION FOUND LOWER LEFT LEADING EDGE OF UPPER RUDDER CHAFED. THE ACCESS PANELS WERE REMOVED, THE AREA WAS CLEANED AND THE FASTENERS WERE REMOVED IAW SRM 51-30-2. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 55-40-3, FIGURE 1. THE ACCESS PANELS WERE REINSTALLED IAW SRM 51-30-2.
Part: TAB — DELAMINATED (LT ELEVATOR)
INSPECTION FOUND LT ELEVATOR TAB DELAMINATED ALONG TRAILING EDGE. THE ELEVATOR TAB WAS REPAIRED IAW SRM 51-40-6 AND 51-40-10. THE ELEVATOR TAB WAS REBALANCED IAW SRM 51-80-9.
Part: FITTING — CORRODED (BS 1183)
INSPECTION FOUND STRINGER 22L ATTACH FITTING CORRODED AT STA 1183. THE FITTING WAS REMOVED AND REPLACED IAW SRM 53-10-3, 51-10-1, AND 51-30-2.
Part: SKIN — CORRODED (BS 1183)
INSPECTION FOUND FUSELAGE SKIN CORRODED AROUND AFT LAV SERVICE PANEL AT STA 1183, STRINGER 20L TO 23L. THE CORRODED AREA OF SKIN AND STRINGER WERE REMOVED, SKIN AND STRINGER WERE FABRICATED AND INSTALLED IAW SRM 53-30-3, FIGURE 12 AND SRM 53-10-3, FIGURE 1.
Part: SKIN — WORN (NR 3 PYLON)
INSPECTION FOUND NR 3 ENGINE PYLON TOP PORTION OF APRON INBOARD CENTER SECTION WORN THROUGH. THE WORN SKIN AND LONGERON WERE REMOVED. REPLACEMENT SKIN AND LONGERON WERE FABRICATED AND INSTALLED IAW SRM 54-30-2, FIGURE 1 AND 51-30-2.
Part: SKIN — CRACKED (VERT STAB)
INSPECTION FOUND A 2 INCH CRACK IN RT SIDE VERTICAL STABILIZER EXTERNAL SKIN AT FIN STA 180, STRINGER 7. THE CRACKED SECTION OF SKIN WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 55-30-3, FIGURE 1.
Part: COVER PLATE — CRACKED (BS 1090)
INSPECTION FOUND A .25 INCH CRACK IN C-3 DOOR FORWARD FRAME COVER PLATE AT B.S. 1090, STRINGER 27. THE FRAME COVER PLATE WAS REPAIRED IAW SRM 51-40-2 AND 51-30-0.
Part: SKIN — CRACKED (VERT STAB)
INSPECTION FOUND A .25 INCH CRACK AT FASTENER HOLE OF LEFT SIDE VERTICAL STABILIZER EXTERNAL SKIN AT FIN STA 157 BETWEEN STRINGER S 4 AND 5. THE CRACKED SECTION OF SKIN WAS REMOVED IAW SRM 55-30-3. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 55-30-3 AND SRM 51-30-2.
Part: SKIN — CRACKED (VERT STAB)
INSPECTION FOUND TWO .25 INCH CRACKS AT FASTENER HOLES IN RIGHT SIDE VERTICAL STABILIZER EXTERNAL SKIN JUST BELOW PANEL 9516. THE PANEL WAS REMOVED FOR ACCESS. THE CRACKED SKIN WAS CUT OUT IAW SRM 54-30-3. REPAIR DOUBLER AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 54-30-3, FIGURE 6 AND SRM 51-30-2. THE PANEL WAS REINSTALLED.
Part: POWER SUPPLY — INOPERATIVE (CABIN)
DEN - EMERGENCY AISLE LIGHT ROW 23 AND AFT INOPERATIVE. REPLACED AFT BATTERY CHARGER AND REPAIRED SPLICE AT SERVICE DOOR, CHECKS GOOD. (M)
Part: TURB BLADE — BROKEN (NR 2 ENGINE)
EWR - FLT 2000 - THE NR 2 ENGINE GAVE OFF A LOUD BANG ON CLIMB-OUT OF EWR. ENGINE POWER WAS REDUCED AND THE AIRCRAFT WAS RETURNED TO EWR. MAINTENANCE FOUND METAL IN THE NR 2 ENGINE TAILPIPE. THE NR 2 ENGINE WAS REMOVED AND REPLACED. THE SDR WILL REMAIN OPEN FOR PART INFORMATION PENDING INVESTIGATION. SUPPLEMENT - THE ENGINE FAILED DUE TO A BROKEN FIRST STAGE TURBINE BLADE. THE BLADE BROKE NEAR THE ROOT AND INVESTIGATION INDICATED THE FAILURE INITIATED AT THE TRAILING EDGE. (X)
1995
Part: CARRIAGE — BROKEN (MIDFLAP, I/B)
EWR - MAINTENANCE FOUND LT MID-FLAP INBOARD CARRIAGE BROKEN. THE LT MID-FLAP INBOARD CARRIAGE WAS REMOVED AND REPLACED IAW MM 27-51-3 AND OPERATION CHECKED GOOD. (X)
Part: HYD PUMP — LEAKING (NR 1 ENGINE)
EWR - FLT 0376 - AIRCRAFT LOST A-SYSTEM HYDRUALIC QUANTITY WHILE EN ROUTE TO EWR. AIRCRAFT LANDED AT EWR WITHOUT INCIDENT. MAINTENANCE FOUND A-SYSTEM NR 1 ENGINE DRIVEN HYDRAULIC PUMP LEAKING. THE PUMP WAS REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD. (X)
Part: 8TH STAGE DUCT — RUPTURED (NR 3 ENG)
FLT NR 680 - MCO - THE NR 3 ENGINE FIRE WARNING LIGHT ILLUMINATED SHORTLY AFTER TAKEOFF FROM MLG. THE NR 3 ENGINE THROTTLE WAS REDUCED TO IDLE AND THE FIRE LIGHT EXTINGUISHED. THE AIRCRAFT WAS DIVERTED TO MCO, AS A PRECAUTIONARY MEASURE, WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND NO EVIDENCE OF FIRE. THE NR 3 ENGINE 8TH STAGE SADDLE DUCT WAS FOUND RUPTURED. THE 8TH STAGE DUCT WAS REMOVED AND REPLACED. THE ENGINE WAS RUN AND OPERATION CHECKED GOOD. (M)