N12507
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.
94 reports on file, 1995-01-16 – 2000-11-28.
Part: RELEASE SYSTEM — WORN (TAIL CONE) · airframe 57,550 hrs · 44,119 cycles
COMPLY WITH SB DC9-53-257 TAIL CONE EMERGENCY RELEASE MOD ON LEGEND AIRLINES EO DC9-53-00-025 & 026-COMPLIED WITH AS REQUIRED-REF AD97-22-05
Part: JACKSCREW — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 56,866 hrs · 43,871 cycles
DURING INSPECTION AT LEGEND AIRLINES FOUND THE HORIZONTAL JACK SCREW TO HAVE METAL SHAVINGS AND OUT OF LIMITS.
Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 56,487 hrs · 43,721 cycles
HOLE IN RADIUS OF FLOORBEAM AT STATION 297 BL 0. FAB AND INSTALLED NEW FLOOR SUPPORT.
Part: SEAT TRACK — WORN (COCKPIT) · airframe 56,487 hrs · 43,721 cycles
SEAT TRACK WORN BEYOND LIMITS. REMOVED AND REPLACED PILOTS SEAT TRACK.
Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
CORRODED AREA 18 BY 30 AT STATION 200 ON FLOOR PANEL SKIN. FABED NEW FLOOR PANEL.
Part: SEAT TRACK — WORN (COCKPIT) · airframe 56,487 hrs · 43,721 cycles
SEAT TRACK WORN BEYOND LIMITS, PILOTS. REMOVED AND REPLACED SEAT TRACK.
Part: PLATE — CORRODED (COCKPIT) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 4 BY 4 INCH AREA OF CORROSION ON PEDESTAL MOUNT FOR AIRSTAIR ROD FS 160 LBL 20. FABRICATED NEW PLATE AND INSTALLED.
Part: LONGERON — CRACKED (FUSELAGE) · airframe 56,487 hrs · 43,271 cycles
CRACK IN LONGERON NR 7 RT 1 INCH LONG. INSTALLED LONGERON REPAIR.
Part: ACCESS PANEL — CORRODED (TE FLAP ACCESS) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 13 X 20 INCH CORRODED AREA ON FLAP ACCESS PANEL 1648. REPLACED SKIN ON PANEL.
Part: ACCESS PANEL — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 13 INCH BY 20 INCH CORRODED AREA ON LT FLAP ACCESS PANEL 1548. REMOVED AND REPLACED SKIN ON PANEL 1548 LT.
Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 1 X 24 INCH CORRODED AREA AT RT OUTBOARD SEAT TRACK AT FS 642 - 666. REMOVED AND REPLACED TRACK.
Part: SEAT TRACK — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 1 X 15 INCH CORRODED AREA RT OUTBOARD SEAT TRACK FS 670 - 685. REMOVED AND REPLACED SEAT TRACK.
Part: FITTING — CRACKED (LT MLG WW) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK INSIDE LT WHEEL WELL DOOR FWD END AT FITTING. REMOVED AND FABRICATED NEW FITTING.
Part: SUPPORT BRACKET — CRACKED (NR 2 PYLON) · airframe 56,487 hrs · 43,721 cycles
A 3 INCH CRACK NR 2 PYLON HYD LINE AREA.
Part: WEB — CRACKED (CABIN) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK AT FS 598 - 610 LT SIDE CUSP WEB. FABRICATED DOUBLER REPAIR.
Part: ELBOW — CRACKED (APU EXHAUST) · airframe 56,487 hrs · 43,721 cycles
A 3 INCH CRACK ON APU EXHAUST ELBOW. WELDED REPAIR.
Part: SUPPORT BRACKET — CRACKED (APU BAY) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK AFT FUSELAGE ABOVE APU ENCLOSURE SUPPORT BRACKET. FABRICATED REPAIR ANGLE.
Part: SEAT TRACK — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 1 BY 7 INCH CORRODED AREA RT OUTBOARD SEAT TRACK. REMOVED AND REPLACED SEAT TRACK.
Part: SKIN — CHAFED (RT LE FLAP) · airframe 56,487 hrs · 43,721 cycles
A 1 BY 1 INCH CHAFED AREA. REPAIRED WITH REPAIR DOUBLER ON RT WING FLAP LEADING EDGE.
Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
OUT OF LIMITS CORROSION ON FLOOR PANEL NR 13. REMOVED, FABBED AND INSTALLED PANEL.
Part: WEB — CRACKED (NR 1 PYLON) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK NR 1 PYLON ELEC COMP AFT O/B CORNER. FABED REPAIR ANGLE.
Part: SHROUD — CRACKED (LT APU BAY) · airframe 56,487 hrs · 43,721 cycles
CRACKED SHROUD LT SIDE OF APU COMPARTMENT. WELDED REPAIR.
Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
CORROSION ON WEB 12 BY 40 INCH LONG AREA. REMOVED AND FABED WEB.
Part: STIFFENER — CRACKED (APU BAY) · airframe 56,487 hrs · 43,721 cycles
1 INCH CRACK AFT FUSELAGE ABOVE APU ENCLOSURE STEP STIFFENER. FABRICATED REPAIR ANGLE.
Part: WEB — CRACKED (CABIN) · airframe 56,487 hrs · 43,721 cycles
A 2 INCH CRACK AT STATION 960 BL 50 RT. INSTALLED DOUBLER REPAIR.
Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 3 BY 11 INCH AREA OF CORROSION AT FS 996 BETWEEN LONGERON 17 LT AND 18 LT FRAME. INSTALLED FRAME SPLICE DOUBLER REPAIR.
Part: ATTACH ANGLE — CRACKED (APU BAY) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK AFT FUSELAGE ABOVE APU ENCLOSER STEP STRUCTURE. FABRICATED REPAIR ANGLE.
Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
CORROSION AROUND ALL FASTENER HOLES ON WING PANEL RT NUMBER 1242A. REMOVED AND REPLACED PANEL.
Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK FS 889 LONGERON 10 LT INTERCOSTAL. FABRICATED REPAIR DOUBLERS.
Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 1 INCH LONG CRACK ON SKIN AT FS 82 LONGERON 20 TO 21 RT. INSTALLED REPAIR DOUBLER.
Part: FLOOR PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
FLOOR PANEL CORROSION OUT OF LIMITS AT FS 200. FABRICATED NEW PANEL.
Part: STRUCTURE — CRACKED (APU BAY) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK TOP LT SIDE OF APU ENCLOSURE STEP. INSTALLED DOUBLER REPAIR.
Part: FLOOR PANEL — CRACKED (COCKPIT) · airframe 56,487 hrs · 43,721 cycles
CRACK AT FS 170 RBL 22 FLOOR WEB. FABRICATED REPAIR DOUBLER AND INSTALLED.
Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 56,487 hrs · 43,721 cycles
HOLE IN FLOOR PANEL AT FS 560 - 580. INSTALLED REPAIR DOUBLER.
Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
SURFACE CORROSION OUT OF LIMITS ON FLOOR PANEL NR 12. REMOVED, FABED AND INSTALLED NEW PANEL.
Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 4 BY 16 INCH AREA OF CORROSION AND CRACKS AT STATION 680 TO 756 BL 44 TO 56 LT FLOOR PANEL. REMOVED, FAB, INSTALLED NEW WEB.
Part: ANGLE — CRACKED (FUSELAGE) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK AFT PIT CEILING FS 990. FABRICATED REPAIR ANGLE.
Part: HINGE — CRACKED (LT FLAP) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK LT FLAP NR 2 HINGE FAIRING SKIN. INSTALLED DOUBLER REPAIR.
Part: FLOOR SUPPORT — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 1.5 INCH BY 20 INCH AREA CORRODED AT FS 160 BL 0 TO 20 LT. REMOVED AND REPLACED FLOOR SUPPORT.
Part: MOUNT BRACKET — CRACKED (APU) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK RT AFT STEP AFT ACCESSORY COMP ON TOP OF APU ENCLOSURE BRACKET. FABBED NEW BRACKET AND INSTALLED.
Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 5 BY 7 INCH CORRODED AREA AT STATION 579 LT SIDE CUSP WEB. FABRICATED DOUBLER REPAIR.
Part: SEAT TRACK — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 1 BY 7 INCH CORRODED AREA SEAT TRACK. REMOVED AND REPLACED TRACK.
Part: LONGERON — CRACKED (FUSELAGE) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK ON LONGERON 15 LT AT STATION 1059 AFT FUSELAGE. INSTALLED 2 DOUBLER REPAIRS.
Part: SKIN — CRACKED (LT ELEVATOR) · airframe 56,487 hrs · 43,721 cycles
SKIN CRACKED LT ELEVATOR LOWER T/E BY PANEL 3511A. REPAIRED AS PER SRM GROUND OUT CRACK.
Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 56,487 hrs · 43,721 cycles
CRACK AT HOLE IN INTERCOSTAL. REMOVED AND REPLACED INTERCOSTAL.
Part: FRAME — CRACKED (FUSELAGE) · airframe 56,487 hrs · 43,721 cycles
FRAME CRACKED AT FS 180 LT BELOW LONGERON 5L. FABRICATED REPAIR ANGLE.
Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK IN FLOORBEAM AT STATION 658. REMOVED AND REPLACED CRACKED FRAME.
Part: HINGE — CRACKED (LT FLAP) · airframe 56,487 hrs · 43,721 cycles
A 4 BY 1 INCH CRACK LT FLAP NR 2 HINGE FAIRING SKIN. INSTALLED DOUBLER REPAIR.
Part: SEAT TRACK — DAMAGED (COCKPIT) · airframe 56,487 hrs · 43,721 cycles
HOLES IN SEAT TRACK WORN BEYOND LIMITS, CO-PILOT. REMOVED AND REPLACED SEAT TRACK.
Part: FLOOR SUPPORT — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 1.5 INCH BY 8 INCH CORRODED AREA AT FS 200 BL 44 TO 50 RT FLOOR SUPPORT. REMOVED AND REPLACED WITH IDENTICAL PART.
Part: WEB — CORRODED (COCKPIT) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 40 INCH X 8 INCH AREA OF CORROSION STATION 160 TO 218 RBL 46 TO 52. FABRICATED FLOOR WEB.
Part: WEB — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
A 5 BY 5 INCH CORRODED AREA AT STATION 155 - 160 BL 25R SUBFLOOR WEB. REPAIRED, TREATED AND PRIMED.
Part: WEB — CRACKED (CABIN) · airframe 56,487 hrs · 43,721 cycles
A 3.5 INCH CRACKS AT FS 560 - 580 BL 0 TO 22 LT. FABRICATED WEB INSTALLED.
Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
SURFACE CORROSION 2 BY 8 INCH AREA ON FLOOR PANEL NUMBER 13 OUT OF LIMITS. FABBED NEW PANEL.
Part: ANGLE — CRACKED (NR 2 PYLON) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK NR 2 PYLON ELEC COMP FWD I/B CORNER. FABBED REPAIR DOUBLERS.
Part: FLOOR SUPPORT — CORRODED (CABIN) · corrosion level 2 · airframe 56,487 hrs · 43,721 cycles
CORROSION AND DOUBLE DRILLED HOLES AT FS 160. FABRICATED NEW FLOOR SUPPORT.
Part: FLOOR PANEL — CRACKED (CABIN) · airframe 56,487 hrs · 43,721 cycles
A 1 INCH CRACK ON FLOOR PANEL. INSTALLED DOUBLER REPAIR.
Part: STRUCTURE — DAMAGED (RT ELEVATOR) · airframe 56,487 hrs · 43,721 cycles
SECTION MISSING FROM T/E OUTBOARD RT ELEVATOR. FABRICATED TIP END.
Earlier reports · 1995–1999 · 36 reports
1999
Part: SKIN — DENTED (BS 940)
INSPECTION FOUND LT FUSELAGE SKIN DENTED AT STA 940, LONGERON 23. THE DENTED AREA WAS CUT OUT AND A DOUBLER AND FILLER WERE INSTALLED IAW SRM 51-30-2, PAGE 4.
Part: FLOORBEAM — CHAFED (BS 465)
CABIN FS 465 FLOORBEAM UPPER FLANGE IS CHFED BETWEEN RBL 12 AND LDL 12. BLENDED FLOOR BEAM UPPER FLANGE. DIMENSIONS OUT OF LIMITS. REPAIRED FLOORBEAM SUPPORT PER EAC 531155-01055.
Part: FLOORBEAM — CORRODED (BS 908)
AFT CARGO PIT UPPER SIDE OF FLOORBEAM LBL 22 STA 980 IS CORRODED. FABRICATED AND INSTALLED REPAIR PER SRM 51-10-3, 53-10 FIG 10, 53-05 FIG 20A, 51-10-4, AND 51-30-5.
Part: FLOORBEAM — CHAFED (BS 408)
CABIN FS 408 FLOORBEAM UPPER FLANGE IS CHAFED BETWEEN RBL 12 AND LBL 12. FABRICATED AND INSTALLED REPAIR DOUBLER PER SRM 53-30, 53-05, 51-10-4, AND 51-30-5.
Part: FITTING — CORRODED (BS 996)
AFT LAV FRAME SUPPORT OUTBOARD FITTING FS 996 STR 18L IS CORRODED. REPAIRED PER SRM 53-05 FIG 20 AND FIG 72.
Part: FLOORBEAM — GOUGED (BS 313)
CABIN FS 313 FLOORBEAM UPPER FLANGE IS GOUGED BETWEEN RBL 12A AND LBL 12A. AFTER BLEND OUT OF GOUGED, FOUND OUT OF LIMITS. FABRICATED TREATED, PRIMED AND INSTALLED REPAIR ANGLE AND FILLERS PER SRM 53-05 FIG 20A, 53-01-01, 53-10-4 AND 53-05 FIG 20.
1998
Part: BATTERY — DISCHARGED (AFT BAGGAGE)
LEFT EXTERIOR EMERGENCY LIGHT DOES NOT ILLUMINATE WHEN EMERGENCY LIGHTS TURNED ON. REMOVED AND REPLACED AFT BATTERY PACK IN AFT BAG BIN OVERHEAD PER MM 33-53-0.
Part: LATCH MECH — WORN (LT MLG DOOR)
THE LT GEAR UNSAFE LIGHT REMAINED ILLUMINATED ATER GEAR RETRACTION (REPEAT PROBLEM - LANDING GEAR SWITCH PREVIOUSLY CHANGED). THE CHECKLIST WAS COMPLETED WITH NO CHANGE. THE FLIGHT WAS CONTINUED TO CLE WHERE THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE LT MLG DOOR LATCH MECHANISM LINKAGE WORN. THE LATCH MECHANISM WAS REMOVED, REPLACED AND RIGGED IAW MM 32-31-4, PAGES 201-210. LANDING GEAR OPERATION AND INDICATIONS CHECKED NORMAL.
Part: BOOST PUMP — LEAKING (LT MAIN TANK)
WHILE AT CRUISE, THE CREW ATTEMPTED TO BALANCE WING FUEL LOAD BY CROSSFEEDING FROM LEFT MAIN FUEL TANK TO RIGHT ENGINE. THE RIGHT ENGINE HESITATED (N1,N2,FF, AND EPR DECREASED) WITH FUEL CROSSFEED OPEN. THE RIGHT INLET FUEL PRESSURE LIGHT AND MASTER CAUTION LIGHT WERE FLICKERING. THE AIRCRAFT LANDED AT EWR WITHOUT INCIDENT. MAINTENANCE FOUND THE LT MAIN TANK AFT BOOST PUMP LEAKING INTERNALLY. THE AFT BOOST PUMP WAS REMOVED AND REPLACED. THE PACKINGS ON LT MAIN TANK FORWARD BOOST PUMP WERE REPLACED DUE TO LEAKAGE. THE FUEL CROSSFEED VALVE WAS REMOVED AND REPLACED AS A PRECAUTIONARY MEASURE. THE RIGHT ENGINE WAS RUN AT TAKEOFF FOR FIVE MINUTES AND OPERATION CHECKED GOOD.
1997
Part: CONNECTOR — LOOSE (RT MLG)
THE RT MLG RED LIGHT REMAINED ILLUMINATED AFTER GEAR WAS RETRACTED. THE GEAR WAS CYCLED AND THE LIGHT EXTINGUISHED. THE AMBER GEAR DOOR OPEN LIGHT ILLUMINATED UPON UPLATCH CHECK, BUT WENT OUT A SHORT TIME LATER. MAINTENANCE FOUND THE RT MLG UPLOCK SWITCH CANNON PLUG LOOSE. THE CANNON PLUG WAS CLEANED AND SECURED. A TEST OF THE MAIN GEAR DOOR LATCH MECHANISM WAS PERFORMED AND OPERATION CHECKED GOOD.
Part: RETRACT MECH — MALFUNCTIONED (LT/RT MLG)
WHEN GEAR WAS EXTENDED FOR LANDING ON APPROACH TO IAH THE R/H MLG GREEN LIGHT WOULD NOT ILLUMINATE. THE BULBS WERE REPLACED AND A TOWER FLY-BY WAS PERFORMED, BUT STILL COULD NOT GET THREE GREEN. AN ALTERNATE GEAR EXTENSION WAS PERFORMED. THE LEFT AND RIGHT MLG DOORS WERE DAMAGED ON LANDING. AN EXTENSION AND RETRACTION TEST WAS PERFORMED IAW MM 32-30-01AND ALL INDICATIONS WERE NORMAL WITH NO FAULTS NOTED. THE FAILURE COULD NOT BE DUPLICATED. BOTH THE LEFT AND RIGHT MLG INBOARD DOORS WERE REMOVED AND REPLACED IAW MM 32-12-1. THE DOORS WERE RIGGED IAW MM 32-10-0 AND 32-31-4 AND OPERATIONAL CHECKS WERE GOOD.
Part: VALVE — CRACKED (RUDDER HYD SOV)
AIRCRAFT LOST RT HYDRAULIC SYSTEM WHILE ENROUTE TO IAH. THE RIGHT GAUGE SHOWED ZERO PRESSURE AND THE LOW PRESSURE LIGHT ILLUMINATED. THE AIRCRAFT LANDED AT IAH WITHOUT INCIDENT. MAINTENANCE FOUND THE RUDDER HYDRAULIC POWER SHUTOFF VALVE CRACKED AT CASING. IN ADDITION,THE NR 2 ENGINE DRIVEN HYDRAULIC PUMP WAS REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD.
Part: ANGLE — CRACKED (BS 945)
INSPECTION FOUND A .25 INCH CRACK IN ANGLE AT STA 945, LONGERON 15R. A NEW ANGLE WAS INSTALLED IAW SRM 51-30-2.
Part: ANGLE — CRACKED (BS 964)
INSPECTION FOUND A .25 INCH CRACK IN ANGLE AT STA 964, LONGERON 16L. THE ANGLE WAS REPLACED IAW SRM 51-10-4.
Part: LONGERON — CRACKED (BS 965)
INSPECTION FOUND A .25 INCH CRACK IN LONGERON 16R AT STA 965. A NEW SECTION WAS SPLICED IN IAW SRM 53-02, FIGURE 2.
Part: ANGLE — CRACKED (BS 964)
INSPECTION FOUND A .25 INCH CRACK IN ANGLE AT STA 964, LONGERON 17R. A NEW ANGLE WAS INSTALLED IAW SRM 51-30-0.
Part: LONGERON — CRACKED (BS 965)
INSPECTION FOUND FOUR .25 INCH CRACKS IN LONGERON 17L BETWEEN STA 965 AND 980. A NEW LONGERON WAS SPLICED IN IAW SRM 53-02, FIGURE 2.
Part: LONGERON — CRACKED (BS 965)
INSPECTION FOUND A .25 INCH CRACK IN LONGERON 17R AT STA 965. A NEW SECTION WAS SPLICED IN IAW SRM 53-02, FIGURE 2.
Part: SHEAR CLIP — CRACKED (BS 980)
INSPECTION FOUND A .25 INCH CRACK IN SHEAR CLIP AT STA 980, LONGERON 14L. THE CRACK WAS STOP DRILLED AND A DOUBLER WAS INSTALLED IAW SRM 53-03.
Part: FITTING — CRACKED (RT MLG)
INSPECTION FOUND A 1 INCH CRACK IN RT MLG ATTACH FITTING AFT COUNTERBORE. REPAIRED IAW ECRA 5740-01767.
Part: FRAME — CRACKED (BS 1038.868)
INSPECTION FOUND A 2 INCH CRACK IN FRAME WEB AT STA 1038.868, LONGERON 9L. REPAIRED IAW SRM 53-01, FIGURE 2.
Part: FRAME — CRACKED (BS 1132.604)
INSPECTION FOUND A 1.5 INCH CRACK IN CANTED FRAME AT STA 1132.604, LONGERON 2R. REPAIRED IAW SRM 53-03, FIGURE 18.
Part: FITTING — CRACKED (KEEL BEAM)
INSPECTION FOUND A .5 INCH CRACK IN LT KEEL BEAM FITTING. DOUBLERS AND FILLERS WERE INSTALLED IAW SRM 53-03, FIGURE 11.
Part: SKIN — CRACKED (RT WING)
INSPECTION FOUND FOUR .25 INCH CRACKS IN RT WING LOWER SKIN AT FUEL BAY SERVICE DOOR LATCHES. THE CRACKED AREA OF SKIN WAS CUT OUT, A DOUBLER AND FILLER REPAIR WAS INSTALLED IAW ECRA 5730-01126.
Part: ANGLE — CRACKED (AFT CABIN DOOR)
INSPECTION FOUND A 2 INCH CRACK IN AFT CABIN DOOR ANGLE AT RIGHT CENTER STOP. A NEW ANGLE WAS INSTALLED IAW SRM 51-30-0.
Part: WEB — CRACKED (NR 2 PYLON)
INSPECTION FOUND A 2 INCH CRACK AT LOWER END OF WEB JUST FORWARD OF AFT ENGINE MOUNT, NR 2 PYLON. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 54-01, FIGURE 2.
Part: FRAME — CRACKED (MAIN CABIN DOOR)
INSPECTION FOUND A .5 INCH CRACK IN SECOND DOOR FRAME FROM TOP OF MAIN CABIN DOOR. REPAIRED IAW SRM 52-05, FIGURE 31.
Part: COMPRESSOR — FAILED (NR 2 ENGINE)
THE NR 2 ENGINE INDICATIONS WENT TO ZERO DURING CLIMBOUT. THE ENGINE WAS SHUTDOWN AND CLE TOWER REPORTED THAT ENGINE WAS SMOKING. BOTH FIRE BOTTLES WERE DISCHARGED AND THE AIRCRAFT WAS RETURNED TO CLE WHERE IT LANDED SAFELY. MAINTENANCE IS IN PROCESS OF REMOVING AND REPLACING THE NR 2 ENGINE. *S/D* INVESTIGATION REVEALED HIGH PRESSURE COMPRESSOR FAILURE DUE TO UNIDENTIFIED FOD AT THE 8TH STAGE.
1996
Part: SKIN — CRACKED (BS 200)
INSPECTION FOUND A .8750 INCH CRACK IN SKIN COMING FROM FASTENER HOLE AT STA 200, FOUR INCHES ABOVE L21L. A .1250 INCH CRACK WAS ALSO FOUND IN SKIN AT STA 200, APPROXIMATELY FOUR INCHES ABOVE L20L. THE CRACKS WERE STOP DRILLED AND A REPAIR DOUBLER WAS INSTALLED IAW ECRA 5330-02458 AND SRM 53-05, FIGURE 57.
Part: SKIN — CORRODED (BS 794)
HOU - INSPECTION FOUND SKIN CORRODED IN AFT BAGGAGE BIN AT STA 794, LONGERON 30R. THE SKIN WAS REPAIRED IAW SRM 53-04, FIGURE 12B. (X)
Part: INTERCOSTAL — CORRODED (BS 465-484)
HOU - INSPECTION FOUND INTERCOSTAL CORRODED FROM STA 465 TO STA 484 BETWEEN STR 29 AND STR 30L. THE INTERCOSTAL WAS REMOVED AND A NEW INTERCOSTAL WAS INSTALLED IAW SRM 51-30-2 AND SRM 51-60-0. (X)
Part: LE SPLICE — CRACKED (WS 198)
HOU - INSPECTION FOUND A 1 INCH CRACK IN RT WING LEADING EDGE SPLICE AT STA XFS 198 BETWEEN NR 3 AND NR 4 SLAT TRACK. THE AREA WAS REPAIRED IAW ECRA 5710-01726. (X)
Part: CABLES — OUT OF ADJUST (TAILCONE)
HOU - THE TAILCONE INTERIOR AND EXTERIOR RELEASE SYSTEM PULLED LOW. THE TAILCONE RELEASE SYSTEM CABLES WERE ADJUSTED IAW MM 53-50-3, ITEM B, STEPS 1-17. (X)
Part: UPLOCK SWITCH — INOPERATIVE (NLG)
FLT NR 1147 - CLE - THE NLG WARNING LIGHTS DID NOT INDICATE GREEN OR RED WHEN GEAR WAS EXTENDED ON APPROACH TO CLE. THE GEAR WAS RECYCLED DURING A GO-AROUND AND THE NOSE GEAR INDICATIONS WERE NORMAL. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NOSE GEAR UPLOCK SWITCH AT FAULT. THE SWITCH WAS REMOVED AND REPLACED. GEAR OPERATION AND INDICATIONS CHECKED GOOD. (M)
1995
Part: CHANNEL — CRACKED (NR 1 PYLON)
IAH - INSPECTION FOUND TWO 'Z' CHANNELS CRACKED AT TOP OF CANNON PLUG COMPARTMENT OF NR 1 ENGINE PYLON. THERE WERE THREE CRACKS MEASURING 4.125 INCHES, 1.5 INCHES AND 1.25 INCHES LONG. TWO NEW 'A' CHANNELS WERE FABRICATED AND INSTALLED IAW SRM 54-10-0, PAGE 2, FIGURE 1. (M)
Part: SLIDE — LOW PRESSURE (GALLEY DOOR)
FLT NR 1524 - MSY - THE R-1 GALLEY DOOR SLIDE WAS FOUND WITH LOW PRESSURE DURING A PREFLIGHT CHECK. THE R-1 GALLEY DOOR SLIDE WAS REMOVED AND REPLACED. (Z)