N9305N

Part: VALVE — DEFECTIVE (NLG) · airframe 38,091 hrs · 32,463 cycles

NOSE GEAR STRUT FLAT NOT ALLOWING GEAR TO RETRACT. REMOVED AND REPLACED SCHRADER VALVE AND RESERVICED STRUT.

Part: SEAL — LOOSE (HEAT EXCHANGER) · airframe 38,062 hrs · 32,447 cycles

BOTH HEAT EXCHANGERS LEAKING NOT ALLOWING AIRCRAFT TO PRESSURIZE. TIGHTENED SEALS ON BOTH HEAT EXCHANGERS.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 37,604 hrs · 32,176 cycles

THE EGRESS LIGHTING BETWEEN ROWS 15 TO 21 WERE FLASHING ON AND OFF DURING FLIGHT. REPLACED THE POWER SUPPLY.

Part: FITTING — CRACKED (FUSELAGE) · airframe 37,080 hrs · 31,856 cycles

DURING CHECK-C MAINT THE FORMER FOOT WAS CRACKED AT STA 1361 BETWEEN LONGERON 23L AND 24L. FABRICATED AND INSTALLED NEW FORMER FOOT SECTION PER SPM 6-70-01, PAGE 2 AND 3, ITEM 4. FABRICATED AND INSTALLED PER SRM 51-30-02 AND 51-30-5.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 37,080 hrs · 31,856 cycles

DURING CHECK-C MAINT THE FLOOR BEAM CAP WAS GROUND BEYOND LIMITS AT STA 1322, LBL 34. REPAIRED FLOOR BEAM CAP PER SRM 53-05, FIG 20A.

Part: TIE CLIP — CRACKED (FUSELAGE) · airframe 37,080 hrs · 31,856 cycles

DURING CHECK-C CRACKED TIE CLIP AT STA 1437 VERT BULKHEAD TO LONG 3R. REPLACED TIE CLIP PER SPM 6-70-01.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 37,080 hrs · 31,856 cycles

DURING CHECK-C MAINT FOUND CORROSION IN LATERAL FLOOR BEAM AT STA 180, FROM RBL 8 TO RBL 43. FABRICATED AND INSTALLED FLOOR SUPPORT PER SRM 51-01, PAGE 1 ITEM C.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 37,080 hrs · 31,856 cycles

DURING CHECK-C MAINT STRINGER 3 LT WAS CRACKED AT STA 160, ABOVE ELECT PANEL. REPAIRED LONGERON 3 PER SRM 53-02, FIG 18.

Part: DOOR FRAME — CRACKED (R1 DOOR) · airframe 37,080 hrs · 31,856 cycles

DURING CHECK-C MAINT THE RT FWD GALLEY SERVICE DOOR HAD A CRACKED DOUBLER LOWER HINGE ARM. REPLACED WITH NEW FRAME PART PER SPM 6-70-01.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 37,080 hrs · 31,856 cycles

DURING CHECK-C MAINT THE NUMBER 4 LT LONGERON WAS CRACKED AT STA 160. REPLACED DAMAGED SECTION OF LONGERON PER SRM 53-02, FIG 18.

Part: WIRE — BROKEN (CABIN) · airframe 36,057 hrs · 31,220 cycles

DURING PREFLIGHT INSPECTION IT WAS NOTED THE RH MID ZONE EGRESS LIGHTS WERE INOP. REPAIRED BROKEN WIRE AT ROW 16 RH SIDE.

Part: WIRE — BROKEN (CABIN) · airframe 36,057 hrs · 31,220 cycles

DURING PREFLIGHT INSPECTION IT WAS NOTED THE RH MID ZONE EGRESS LIGHTS WERE INOP. REPAIRED BROKEN WIRE AT ROW 16 RT SIDE.

Part: BATTERY PACK · airframe 35,416 hrs · 30,874 cycles

THE CABIN OVERHEAD EMERGENCY LIGHTS ILLUMINATED WHEN POWER WAS REMOVED FROM THE AIRCRAFT. REPLACED THE BATTERY PACK. CHECK-C 5-7-01 STL. --CLOSED--

Part: LAMP · airframe 34,481 hrs · 30,411 cycles

DURING LANDING THE RIGHT MAIN LANDING GEAR LIGHT DID NOT ILLUMINATE, DUE TO BURNED OUT BULB. REPLACED LIGHT BULB P/N 387.LAST CHECK C 05/07/01 STL. --- CLOSED ---

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 34,481 hrs · 30,411 cycles

DURING MAINTENANCE THE AFT FLOOR EGRESS LIGHTS WERE INOP DUE TO WEAR. REPLACED BATTERY PACK P/N5822-2 AND FEEDER JUMPER CABLE PER MM 33-51-01.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 34,743 hrs · 30,532 cycles

IN FLIGHT THE EGRESS LIGHTS AT ROWS 15 TO 22 ILLUMINATED. REPLACED THE BATTER PACK. CHECK-C 5-7-01 STL.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 34,669 hrs · 3,057 cycles

AN OVERWING EMERGENCY EXIT LIGHT REMAINED ON IN FLIGHT. REPLACED THE POWER SUPPLY. CHECK-C 5-7-01 STL.

Part: BATTERY — DISCHARGED (CABIN) · airframe 34,601 hrs · 30,472 cycles

THE EGRESS LIGHTING IN THE FIRST CLASS CABIN WAS INOPERATIVE. REPLACED THE BATTERIES IN THE BATTERY PACK. CHECK-C 5-7-01 STL.

Part: WIRE — BROKEN (CABIN) · airframe 42,836 hrs · 21,445 cycles

THE AFT CABIN EXIT IDENTIFIER FAILED TO ILLUMINATE. REPAIRED A BROKEN WIRE IN CEILING OF AFT LEFT LAVATORY. CHECK-C 2-5-01 JFK.

Part: FRAME — CRACKED (FAIRING) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, THE FAIRING SUPPORT FRAME WAS CRACKED AT STA 946, RBL 7 AND LBL 7. REPAIRED BOTH PER SRM 53-05, FIG 81, PAGE 267.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, THE FLOORBEAM WAS CORRODED AT STA 1323, LBL 22. REPAIRED FLOORBEAM PER SRM 53-05 PAGE 31 FIG 20A.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, FOUND CORROSION ON FLOORBEAM AT STA 1309, LOCATED 6 INCHES LEFT OF CENTER LINE. REMOVED AND REPLACED FLOOR SUPPORT. USED TWA (P/N 56-2789) TO FABRICATE PER SRM 53-14-3, PAGE 49, AND USED HI-LOKS PER SRM 51-30-5.

Part: SKIN — CORRODED (WING) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, THE SURFACE AT LE AT TELESCOPING ANTI-ICE DUCT, 0.045 IN MATERIAL WAS REMOVED FOR CORROSION REMOVAL. MATERIAL THICKNESS IS 0.250 IN PER SRM 57-31-1 FIG 1 CORROSION REMOVED ON NR 2-42 BLEND OUT OF CORROSION COMPLIES WITH THE 20 PER CENT LIMIT. FINISHED PER SRM 51-10-3 PARAGRAPH 23. ---CLOSED---

Part: ATTACH ANGLE — CRACKED (VERTICAL STAB) · airframe 31,850 hrs · 29,084 cycles

DURING CHECK-C MAINT, THE ATTACH ANGLE ON BOTTOM OF DORSAL FIN CRACKED THROUGH THE SCREW HOLE, LT SIDE APROX STA 1420. INSTALLED REPAIR ANGLE PER SRM 53-01 PAGE 0 WITH FASTENERS PER SRM 51-10-3.

Part: WEB — CORRODED (FUSELAGE) · airframe 31,850 hrs · 29,084 cycles

DURING CHECK-C MAINT, THE MEMBRANE AT LONGERON 18L BETWEEN STATION 218 TO 237, O/B OF CHAIR TRACK, WAS CORRODED. FABRICATED NEW PART PER DRAWING 5930544 AND 9930538, AND SRM 51-10-3. INSTALLED PER SRM 51-30 AND 51-10-4.

Part: FRAME — CORRODED (FUSELAGE) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, FOUND FORMER RING AT STA 1309 CORRODED BETWEEN LONGERONS 29L AND 29R. REMOVED CORROSION PER SPM 6-80-01. TRIMMED CORRODED AREA OVER LONGERON AND REPAIRED PER SRM 53-05, FIG 2A.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, FOUND INTERGRANULAR CORROSION ON NUMBER 4 CHAIR TRACK, RBL 22 INCHES, STA 1144. INSTALLED SPLICE REPAIR PER SRM 53-05, FIG 4F.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 31,850 hrs · 29,084 cycles

DURING CHECK-C MAINT, THE RT DORSAL FIN ATTACH ANGLE ON FUSELAGE STA 1420 WAS CRACKED. INSTALLED NEW ANGLE PER DOUGLAS DRAWING 174968, PER SPM 6-70-01 WITH FASTENERS PER SRM 51-10-3.

Part: STRUCTURE — DAMAGED (FUSELAGE) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, FOUND CLASS 3 REPAIR AT STA 200 TO 225, LONGERON 4L TO 6L. REPAIRED PER SRM 53-04 FIG 12B, SHEETS 9 AND 10. MESSAGE SENT TO ENGINEERING PER GP&P MANUAL.

Part: FLOORBOARD — CORRODED (CABIN) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, FOUND CORROSION ON CABIN FLOOR PANEL SUPPORT AT STA 200, BL 0 TO RBL 50. REMOVED CORROSION PER SPM 6-80-1. REPLACED SUPPORT EXTRUSION PER DWG 5930545 AND SPM 6-70-01. TREATED PER SRM 51-10-3.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, NUMBER 3 CHAIR TRACK FROM STA 1031 TO 1309 HAD CORROSION BEYOND LIMITS. REPLACED NUMBER 3 CHAIR TRACK PER IPC 53-40-00 FIG 19B AND SRM 53-05 FIG 4F AND SRM 51-60-0. FIFTEEN FEET 9 INCHES OF TRACK REPLACED WITH TRACK SPLICE AT THE AFT END OF 12 FOOT SECTION.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,925 hrs · 29,140 cycles

DURING CHECK-C MAINT, CABIN STA 1155 LRL 47 HAD CORROSION ON TRACK NUMBER 2. REPLACED TRACK SECTION PER SRM 53-05, FIG 4F.

Part: SPAR — CORRODED (RT WING) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT ON THE RT WING, CORROSION WAS FOUND ON THE REAR SPAR BETWEEN CENTER AND O/B AILERON HINGE. FABRICATED ACCORDING TO SRM 59-09 FIG 5. FABRICATED, FINISHED, AND INSTALLED FILLER SHIM AND DOUBLER PER SRM 57-09 FIG 5 AND SRM 57-01 PARAGRAPH 3B. SUBSTITUTED HLT 336-6, HLT 436 AND 54931920-6 FASTENERS PER 20-00 PAGE 36 FIG 4.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, FOUND CORROSION ON CABIN FLOORBEAM, LEFT AFT LAV STA 1338, 20 INCH LBL AND 30 IN LBL. CORROSION REMOVED PER SPM 6-80-01 PAGE 31 TO 42, AND SRM 51-10-3 PARAGRAPH 23. REPAIRED DAMAGED AREA PER SSRM 53-00-101 PAGE 201.

Part: FRAME — CORRODED (FUSELAGE) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, THE AFT CARGO BIN HAD CORROSION ON FORMER RING AT STA 1271, LONGERON 30. AT STA 1271 ON FORMER RING AT LONGERON 30 REMOVED CORROSION PER SPM 6-80-01. CUT OUT DAMAGED PORTION OF FORMER RING AND REPAIRED WITH SPLICE PER SRM 53-03, FIG 2A CONFIG 7005.

Part: BRACKET — CRACKED (FUSELAGE) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, A FUSELAGE ANGLE BRACKET WAS CRACKED AT STA 946, LBL 7 INSIDE KEEL BEAM LOWER FWD CORNER. FABRICATED PART FROM 7075-T6 PER SPM AND PRINT 9936368, SHEET 1 PART 101.

Part: SEAT TRACK — WORN (COCKPIT) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, THE FIRST OFFICER''S RT FWD CHAIR TRACK WAS WORN ON UPPER AND LOWER SURFACES. REPLACED FLOOR TRACK PER MM 53-40-01 PAGE 203.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT AT CABIN STA 1155, LBL 33, FOUND CORROSION ON FLOOR SUPPORT BETWEEN NUMBER 2 AND 3 TRACKS. FABRICATED AND INSTALLED NEW SUPPORT PER SRM 53-14-3, FIG 12 AND SPM 6-70-01 PAGE 3. PROTECTIVE TREATMENT OF SUPPORT PER SRM 51-10-3. INSTALLED WITH ORIGINAL TYPE FASTENERS PER SRM 51-30-0.

Part: STIFFENER — CRACKED (FAIRING) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT AT STA 996 BODY FAIRING STIFFENER BOTTOM CORD HAD A 6.5 INCH CRACK AND THE REPAIR ANGLE HAD 1.5 INCH CRACK. STOP DRILLED CRACKS PER SRM 53-00. ACCOMP NDT HIGH FREQ EDDY CURRENT ON STIFFENER PER 51-00-03 PART 6. FABRICATED NEW ANGLE AND INSTALLED PER SRM 53-01 PAGE 10 FIG 2.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, FOUND CABIN MEMBRANE CORRODED AT STA 503 TO 522, LONGERON 18L. REMOVED CORRODED AREA AND INSTALLED DOUBLER PER SRM 53-01, PAGE 9.

Part: STRAP — CORRODED (SPOILER) · airframe 31,935 hrs · 29,140 cycles

DURING CHECK-C MAINT, THE RT WING UPPER O/B SPOILER, O/B END, TRAILING EDGE SUPPORT STRAP HAD CORROSION. REMOVED DAMAGED SUPPORT STRAP AND REPLACED WITH NEW PART PER SRM 51-01 ITEM C.

Part: BATTERY — DISCHARGED (ROW 28L)

DURING PREFLIGHT, FOUND OVERHEAD EMERGENCY LIGHTS INOP AT ROWS 28L AND 28R THROUGH ROWS 26L AND R AND 5 EACH INOP IN THE TAIL SECTION. REPLACED BATTERY. AC01 9-14-99 JFK.

Part: COALESCER BAG — DIRTY (LT & RT)

STRONG ODOR WITH SMOKY HAZE IN COCKPIT AND CABIN AFTER TAKEOFF. FLT RETURNED TO SFO. CHECKED ALL ACFT COMPARTMENTS, CHECKED APU CHECK VALVE, AND ACM OUTLETS FOR OIL. NO SIGN OF OIL. CHANGED BOTH WATER SEPARATORS. ALSO ACCOMP ENG RUN AND PACK BURN OUT PROCEDURE. CHECK-C 8-7-98 MCI.

Part: COALESCER — DIRTY (CABIN)

LGA - FLT 293 - AFTER TAKEOFF SMOKE FILLED CABIN AND COCKPIT WITH ODOR AND LIGHT HAZY SMOKE. FLIGHT RETURNED TO LGA. FOUND AIR COND PACK COALESCER BAGS CLOGGED BY DEBRIS FROM BIRD INJESTION. PERFORMED PACK BURNOUT AND REPLACED BOTH COALESCER BAGS. PERFORMED ECS HEALTH CHECK. (M)

Part: SKIN — GOUGED (BS 1211-1338)

MCI - DURING C-CHECK MAINTENANCE FOUND A DEEP GOUGE ON LEFT SIDE OF FUSELAGE, LONGERON 18 TO 26, STATION 1211 TO 1338. REPLACED SKIN PANEL, LONGERON 18 TO 26, STATION 1211 TO 1338, PER SRM 51-10-0, PAGE 1. (M)

Part: SKIN — GOUGED (BS 1211-1117)

MCI - DURING OP 16 MAINTENANCE CHECK, FOUND GOUGE IN SKIN PANEL AT LONGERON 22, STATION 1211 TO 1117. REPAIRED SKIN PANEL PER SRM 53-04, FIG 12B. (M)

Part: SKIN — DAMAGED (FUSELAGE)

STL - DURING SPECIAL CHECK, FOUND DAMAGE ON LEFT AFT FUSELAGE, AFT OF FLAP. REPAIRED PER ARA 11135A AND SRM 53-04. (M)

Part: SCHRADER VLV — FAILED (NLG)

MSY - AFTER TAKEOFF WHEN LANDING GEAR WAS RETRACTED, NOSE LANDING GEAR DID NOT RETRACT. FOLOWED ORH PROCEDURES. FOUND NOSE LANDING GEAR STRUT DEFLATED AND A DEFECTIVE SCHRADER VALVE. SERVICED NOSE LANDING GEAR STRUT WITH HYDRAULIC FLUID AND REPLACED SCHRADER VALVE, MFG P/N B050762, AND DRY NITROGEN. NOSE LANDING GEAR OPERATION THEN CHECKED NORMAL.

Part: COALESCER BAG — DIRTY (CABIN)

MCI - FLT 667 - DURING CLIMB WHEN ENGINE ANTI-ICE WAS TURNED ON, A BURNING ODOR WAS NOTICED IN THE CABIN. TURNED OFF ENGINE ANTI-ICE. FOUND DIRTY COALESCER, MFG PN 21D10-1. REPLACED BOTH COALESCERS. AIR CONDITIONING SYSTEM THEN CHECKED NORMAL. OP-16 - 2-16-96 - TUS.