N9306T

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 32,214 hrs · 26,238 cycles

THE EGRESS LIGHTS WERE INOPERATIVE AFT OF THE AFT GALLEY. REPLACED THE POWER PACK. CHECK-C 2-23-01 STL.

Part: PLUG — MISSING (ROW 21) · airframe 31,351 hrs · 25,770 cycles

THE EMERGENCY EXIT INDICATOR WAS MISSING AT ROW 21, RT SIDE OF CABIN. RE-INSTALLED INDICATOR. CHECK-C 5-10-00 MCI.

Part: HANDLE — CRACKED (CARGO DOOR) · airframe 29,799 hrs · 24,938 cycles

FWD CARGO DOOR, DOOR HANDLE CRACKED. NDT CONFIRMED. REMOVED AND REPLACED DOOR HANDLE AND SPRING PER MM 52-31-00. CK-C 05/07/00 MCI.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, FOUND CORROSION AT INTERCOSTAL DOUBLERS, STA 1212 TO 1231 AND STA 1212 AT LONGERON 229R. REMOVED FASTENERS AND DOUBLERS. REMOVED CORROSION BY SANDING PER SPM 6-80-01 PAGES 1 TO 3. TREATED AND PRIMED PER SRM 51-10-03.

Part: FRAME — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, STA 1231 FORMER RING HAD CORROSION FROM LONGERON 29L TO 29R. REMOVED CORROSION PER SPM 6-80-01. TREATED AND PRIMED AREA PER SRM 51-10-03.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, FOUND CORROSION ON TOP AND BOTTOM OF FLOOR BRACE AT STA 1212, BETWEEN LONGERON 29R AND 28L. REMOVED CORROSION PER SPM 6-80-01. TREATED AREA AND PRIMED PER SRM 51-10-03.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, FOUND LONGERON 30 HAD CORROSION AROUND RIVETS FROM STA 1231 TO 1271. REMOVED CORROSION PER SPM 6-80-01. TREATED AND PRIMED AREA PER SRM 51-10-03.

Part: FRAME — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, STA 1212 FORMER RING HAD CORROSION FROM LONGERON 28L TO 29R. REMOVED CORROSION PER SPM 6-80-01. TREATED AND PRIMED AREA PER SRM 51-10-03.

Part: SPLICE — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, LONGERON NUMBER 30 SPLICE WAS CORRODED AT FWD AND AFT ENDS, STA 1243 AND 1196. REPLACED NUMBER 30 LONGERON SPLICE AT STA 1243 AND 1196 PER DOUGLAS DRAWING 593667 AND FASTENER SUBSTITUTION PER SRM 51-60-00 FIG 4.

Part: STRUCTURE — CRACKED (MLG DOOR) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT AT THE LT MAIN LANDING GEAR, CORNER BRACKET RT FWD BETWEEN MLG DOORS, FWD I/B CORNER OF RT MLG DOOR IS CRACKED AT STA 937. INSTALLED NEW CORNER BRACKET PER SRM 51-30 -05.

Part: SKIN — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, FOUND CORROSION ON LOWER FUSELAGE SKIN, STA 770, STRINGER 12R. INSTALLED EXTERNAL DOUBLER PER SRM 53-04, FIG 12B.

Part: GALLEY TRACK — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, FOUND CORROSION ON TRACK NR 5 AT NUMBER 1 GALLEY, STA 200 TO 256. REPLACED SECTION OF NR 5 SEAT TRACT STA 200 TO 256. SPLICED AT STA 256 PER SRM 53-05-10G TO 53-05-10Q.

Part: PLATE — CORRODED (HORIZONTAL STAB) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, THE LT SIDE STABILIZER WRAP AROUND SEAL PLATE HAD SEVERAL SCREW HOLES WITH CORROSION. MADE DOUBLER PER SRM 53-01. REMOVED CORROSION BY SPOT FACING OUT HOLES PER SRM 53-01, PAGE 1B. INSTALLED DOUBLER OVER SPOT FACED AREA PER SRM 55-01, FIG 2 SHEET 2 PAGE 7.

Part: GALLEY TRACK — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, THE GALLEY TRACK NUMBER 6 AT FWD END OF STA 218 HAD CORROSION ON THE TRACK. CUT AND SPLICED TRACK TO REMOVE CORROSION PER SRM 53-05, FIG 4F.

Part: STRUCTURE — CRACKED (CARGO DOOR) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT THE FORWARD CARGO DOOR, WHERE FWD AND AFT LATCH CAMS COME THRU THE DOOR, FITTINGS ARE WORN AND LOCK BOLT REQUIRED WORK. REMOVED DAMAGED HUCKS AND INSTALLED WITH LIKE HL 326 HI-LOKS. BLENDED FITTING PER 52-01, FIG 1 SHEET 3.

Part: SKIN — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, FUSELAGE SKIN AND INTERIOR DOUBLER HAD LIGHT CORROSION BETWEEN THEM AT STA 1307, ABOVE STRINGER 22L. REMOVED LIGHT CORROSION ON SKIN AND INTERIOR DOUBLER AT STA 1307, STRINGER 11L, PER SPM 6-80-01 AND ARA 16966. PRIMED AND TREATED PER SRM 51-10-3 PARAGRAPH 47.

Part: LATCH — CRACKED (CARGO DOOR) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, THE FWD CARGO DOOR, AFT SIDE OF DOOR, HAD CRACK AT LATCH CAM ON BOTH INSIDE AND OUTSIDE PAN. INSTALLED DOUBLER PER 52-05, FIG 50 ON INSIDE CRACK. INSTALLED DOUBLER PER 52-05, FIG 26A ON OUTSIDE CRACK.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, AT STA 1322, RBL 17 TO RBL 51, LEVEL 2 CORROSION ON TOP OF FLOOR BEAM. REPAIRED AS INSTRUCTED ON ARA 16962. REMOVED CORROSION PER SPM 6-80-01. CORROSION TREATMENT PER ARA. TREATED PER SRM 51-10-3, PARAGRAPH 47.

Part: RIB — CRACKED (LT WING) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, TIE CLIP WAS CRACKED AT LT WING FRONT SPAR TO RIB AT UPPER T/E, 9 INCHES I/B OF NUMBER 7 TRACK, AFT OF NR 2 L/E SLAT. REPLACED CLIP. RIB FOUND TO BE CRACKED UNDER THE CLIP. STOP DRILLED THE UPPER CRACK AND ROUTED OUT THE LOWER CRACK.

Part: STRUCTURE — CRACKED (CARGO DOOR) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, THE AFT CARGO DOOR HAD CRACKS UNDER DOOR SEAL, TOP AFT SIDE OF DOOR LATCH. REPAIRED CRACKS UNDER DOOR SEAL ON AFT CARGO DOOR PER SRM 52-05, FIG 26A AND 52-03 FIG 8.

Part: SKIN — DENTED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, FOUND FUSELAGE SKIN DENT AT STA 446, 0.027 DEEP, .0312 INCH FROM EDGE OF ALTERNATE STATIC PORT LOWER AFT PERIMETER. REPAIRED PER BOEING MESSAGE TWA-MCI-00-00473H DATED 4-14-00. REINSTALLED INTERNAL PLATE PER DRAWING 5911412. TEMPORARY REPAIR AUTHORIZED BY BOEING.

Part: FRAME — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING C CHECK, STA 1308 FORMER RING HAD CORROSION FROM STRINGER 24 LT, TO 24 RT, AFT SIDE. REMOVED CORROSION PER SRM 51-10-3 AND SPM 6-80-1. INSTALLED REPAIR PER SRM 53-03 FIG 2A. ---CLOSED---

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING C CHECK, FOUND CRACK IN MEMBRANE AT STA 1280, AND 1296 TO 1309, LONGER 18 LT. STOP DRILLED CRACKS. INSTALLED REPAIR DOUBLER OVER CRACKED MEMBRANE AND INSTALLED FASTENERS PER SRM 53-05, PAGE 349 AND 359. ---CLOSED---

Part: ANGLE — CRACKED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING C CHECK, MAINT FOUND A CRACK AT DOUBLER ANGLE FWD SIDE OF REAR BULKHEAD, BELOW LONGERON 1. STOP DRILLED TO QUARTER INCH. REPAIRED WITH 2 EA 0.025 THICK DOUBLERS PER SRM 53-01 PAGE 10. REINSTALLED ANGLE. ---CLOSED---

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING C CHECK, MAINT CABIN FLOOR MEMBRANE LOWER SURFACE, AT STA 200 AFT SIDE OF FLOORBEAM, AT BL 0 WAS CORRODED. REMOVED CORRODED FLOOR MEMBRANE AT STA 200 TO 218, LBL 25 TO RBL 26. INSTALLED NEW SECTION OF MEMBRANE 0.025. REF SRM 53-14-1 PAGE 27. ---CLOSED---

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 29,799 hrs · 24,938 cycles

DURING C CHECK, MAINT CABIN FLOOR MEMBRANE LOWER SURFACE AT AFT SIDE OF STA 200 FLOORBEAM, RBL 22, WAS CORRODED. REMOVED CORRODED MEMBRANE AT STA 200 TO 218, LBL 25 TO RBL 26. INSTALLED NEW SECTION OF MEMBRANE 0.025 7075-T6 REF SRM 53-14-1 PAGE 27. ---CLOSED---

Part: ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT AT STA 434 FOUND LEVEL 2 CORROSION ON T ANGLE FWD END OF INTERCOSTAL, LONGERON 29R. INSTALLED NEW T ANGLE (P/N 491258-501). SECURED TO STRUCTURE WITH HI-LOK 326 PER SRM 51-30-5.

Part: TIE CLIP — CRACKED (RT WING) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT ON THE RT WING, THE TIE CLIP FROM RIB TO FRONT SPAR WAS CRACKED AT UPPER T/E 26 INCHES O/B OF NR 11 L/E TRACK. CONFIRMED BY NDT. REPLACED RIB PER SPM 6-70-01 PAGE 3, AND INSTALLATION DRAWING 9919329.

Part: CLIP — CORRODED (AIRSTAIR) · airframe 29,799 hrs · 24,938 cycles

DURING CHECK-C MAINT, FOUND DELAMINATION CORROSION PART OF CLIP/RETAINERS FOR SEAL BOTTOM OF AIRSTAIR DOOR. INSTALLED 2 NEW PRE-FABRICATED L ANGLES FROM 7075-T6 PER SAMPLE 2.4 INCHES LONG BY 1 INCH WIDE BY 0.60 HIGH. SECURED TO DOOR FRAME WITH HI-SHEAR BLIND BOLTS PER SRM 51-30-4.

Part: ENGINE — FAILED (RIGHT)

THE RIGHT ENGINE FAILED AT 12,000 FEET IN CLIMB WITH A LOUD BANG. ENGINE WAS SHUT DOWN AND FLIGHT RETURNED TO STL. FOUND TURBINE HAD FAILED WITH ENGINE CASE PENETRATION. REPLACED THE ENGINE. CHECK-C 3-12-99 STL.

Part: LAMP — FAILED (ROW 33)

THE AFT STAIR EMERGENCY LIGHT AND THE EGRESS LIGHT AT ROW 33 WERE INOPERATIVE. RELAMPED THE TWO AFT STAIR LIGHTS, AND RECONNECTED THE EGRESS STRIP AT ROW 33. CHECK-C 3-12-99 STL.

Part: TIRE — FAILED (LT MLG)

DURING TAKEOFF AT SJC, THE NUMBER 1 TIRE COMPLETELY SEPARATED FROM THE WHEEL, CAUSING FAILURE OF THE RH HYDRAULIC SYSTEM. DURING THE LANDING AT SFO THE NUMBER 2 TIRE SEPARATED FROM THE WHEEL. INSPECTION OF THE AIRCRAFT FOUND OTHER DAMAGE CAUSED BY THE TIRE FAILURES, INCLUDING THE LT ENGINE FAN, NOSE COWL, AND ENGINE CASE. BOTH TIRES WERE REPLACED AND THE DAMAGE CORRECTED. CHECK-C 3-12-99 STL.

Part: SAFETY STRAP — OUT OF POSITION (PAX DOOR)

ON CLIMB-OUT, R1 DOOR HAD AN AIR NOISE. SAFETY STRAP CAUGHT IN DOOR. STRAP WAS STOWED. CHECK-C1.

Part: FUSE — FAILED (RT HYD SYST)

THE RT HYD SYSTEM FAILED DURING GEAR RETRACTION AFTER TAKEOFF. COMPLETE FLUID LOSS FROM RT SIDE. RT HYD PUMP LATER FAILED. FLT RETURNED TO STL. REPLACED NR 3 BRAKE HYD FUSE LIMITER AS INITIAL CAUSE. CHECK-C 3-16-98 MCI.

Part: SUPPORT — CRACKED (FUSELAGE)

MCI - DURING CHECK-C, MAINTENANCE FOUND AFT END OF LT MLG DOOR HINGE AND ABOVE DOORWAY FRAME SUPPORT BRACE WITH ID CRACKED. REPLACED SUPPORT BRADE PER SRM 51-01, PG 1 ITEM C, AND TWA STD PRACT. (X)

Part: VANE — DAMAGED (LT ENGINE)

LAX - FLT 467 - AT APPROX 2000 FT LEFT ENGINE FAILED. RETURNED LAX. MADE SMOOTH OVERWEIGHT LANDING. FOUND TURBINE FAILURE INCLUDING LOSS OF TAIL CONE. CHANGED ENGINE. CHECK-C 3-15-97. EXAMINATION OF ENGINE FOUND ONE T2 VANE FRETTED THROUGH INNER SHROUD AND RUBBED ON T3 BLADES UNTIL ONE BLADE FAILED. THE DAMAGE WAS REPAIRED. (M)

Part: CLAMP — LOOSE (LT AUG VALVE)

STL - FLT 118 - DURING CLIMB, THE TAIL COMPARTMENT HIGH TEMPERATURE LIGHT ILLUMINATED. TIGHTENED CLAMPS ON THE LEFT HAND AUGMENTATION VALVE. OPERATIONAL CHECK NORMAL. CHECK C - 3-15-97 - JFK. (X)

Part: SPRAY DEFLECTOR — LOOSE (NLG)

STL - FLT 121 - DURING CLIMB, NOSE GEAR UNSAFE LIGHT ILLUMINATED. TIGHTENED AND RESAFTIED AFT BOLTS ON NOSE GEAR SPRAY DEFLECTOR AND CLEANED AND LUBRICATED GEAR EMERGENCY RELEASE HANDLE. OPERATIONAL CHECK NORMAL. (M)

Part: HYD PUMP — FAILED (LT ENGINE)

STL - FLT 134 - DURING CRUISE, LEFT ENGINE HYDRAULIC PUMP FAILED. AIRCRAFT RETURNED TO AIRPORT. REMOVED AND REPLACED LEFT ENGINE HYDRAULIC PUMP DUE TO A SHEARED SHAFT, MFG PN 566411L5666. OPERATIONAL CHECK NORMAL. OP-16 - 4-8-96 - TUS.