N905TW

Part: COMPRESSOR — STALLED (RT ENGINE)

STL - AT FL280 RIGHT ENGINE COMPRESSOR STALLED. OPERATED ENGINE AT IDLE AND LANDED STL WITHOUT INCIDENT. REPLACED RIGHT HAND ENGINE. SYSTEM GROUND CHECKED NORMAL OPERATION.

Part: CONTACT — DIRTY (EMERGENCY LIGHT)

SFO - ENTRY EMERGENCY LIGHTS AT NUMBER ONE DOOR INOPERATIVE. CLEANED CONTACTS FOR POWER AND GROUND FOR LEFT NUMBER 1 ENTRY DOOR EMERGENCY LIGHTS. SYSTEM GROUND CHECKED NORMAL OPERATION.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 59,750 hrs · 31,400 cycles

THE EGRESS LIGHT AT ROW 7 AND THE EMERGENCY LIGHTS ABOVE THE L1 AND L2 DOORS WERE INOPERATIVE. REINSERTED THE LAMP INTO THE MODULE FOR THE EGRESS LIGHT, REPLACED THE LAMP ASSEMBLY PN L20191-9 ABOVE THE L2 CABIN DOOR, AND CLEANED THE CONTACTS AND REPLACED THE LAMP PN 1315 ABOVE THE L1 CABIN DOOR. CHECK-C 12-3-02 STL. --CLOSED--

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 59,750 hrs · 31,400 cycles

THE EMERGENCY LIGHTS AT BOTH AFT OVERWING EXITS, AND THE RT SIDEWALL EMERGENCY LIGHT IN THE TAILCONE, WERE INOPERATIVE. REPLACED THE BATTERY PN 408822101 IN THE BATTERY PACK FOR THE EXIT LIGHTS, AND REPLACED THE LAMP PN 1315 IN THE TAIL CONE. CHECK-C 12-03-2002 STL.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 59,409 hrs · 31,199 cycles

THE EGRESS LIGHTS WERE INOPERATIVE FROM ROW 25 THRU 31. REPLACED THE POWER SUPPLY. CHECK-C 12-3-02 STL.

Part: TRANSMITTER — MALFUNCTIONED (STALL WARNING) · airframe 58,793 hrs · 30,835 cycles

ON APPROACH WHEN FLAPS SELECTED TO 40 GOT SLAT DISAGREE LIGHT. SLOWED DESCEND RATE AND GOT STICK SHAKER. ACCOMPLISHED GO AROUND. SECOND APPROACH WAS NORMAL. REPLACED LEFT AOA TRANSMITTER AND PLUNGER ASSEMBLY FOR THE LEFT NUMBER 1 SLAT PROX SENSOR TARGET ASSY.

Part: WINDSHIELD · airframe 57,713 hrs · 30,164 cycles

CAPTAIN'S WINDSHIELD CRACKED AND SHATTERED SHORTLY AFTER TAKEOFF.R/R CRACKED WINDSHIELD (P/N 217-0332), OPS CHECK WINDOW HEAT AND OPERATION NORMAL. --CLOSED-- LAST CHECK-C MCI 10/9/01

Part: BLADE — FAILED (RT ENGINE) · airframe 57,159 hrs · 29,831 cycles

A LOUD BANG WAS HEARD FROM THE RIGHT ENGINE AND THE ENGINE SHUT ITSELF DOWN. THE FLIGHT RETURNED TO AIRPORT AND THE ENGINE WAS REPLACED. A FOURTH STAGE TURBINE BLADE HAD FAILED.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 56,416 hrs · 29,374 cycles

THE CABIN CEILING EMERGENCY LIGHTS WERE INOPERATIVE ROWS 12 TO 21 AND 28 TO 29, AND THE EGRESS LIGHTS WERE INOPERATIVE ROW 1 TO 14. REPLACED THE BATTERIES P/N 408822-101 IN THE BATTERY PACK FOR THE CEILING LIGHTS, AND REPLACED THE BATTERY PACK P/N 5822-2 FOR THE EGRESS LIGHTS.

Part: BRACKET — CRACKED (FUSELAGE) · airframe 56,346 hrs · 29,330 cycles

DURING CHECK-C MAINT FOUND BRACKET CRACKED AT STA 1485, 18 INCHES RBL, JUST FWD OF RUDDER TRIM CABLE SPOOL BRACKET. FABRICATED AND INSTALLED REPLACEMENT BRACKET PER SRM 53-14-4.

Part: LIGHT — INOPERATIVE (EMPENNAGE) · airframe 56,246 hrs · 29,268 cycles

THE AFT TAIL CONE AREA EMERGENCY CAT WALK LIGHT, AND THE AFT TAIL CONE AREA EMERGENCY LIGHT, WERE INOPERATIVE. REPLACED THE LIGHT ASSEMBLY P/N 0200335-001 FOR THE CAT WALK LIGHT, AND REPLACED THE LIGHT ASSEMBLIES P/N 0200333-002 AND 0200333-001 FOR THE EMERGENCY LIGHT. CHECK-C 4-12-01 MCI.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 56,246 hrs · 29,268 cycles

THE EMERGENCY EXIT SIGN AT THE LT OVERWING EXIT, AND THE EMERGENCY CEILING LIGHT BETWEEN NUMBER 4 GALLEY AND THE AFT AIRSTAIR DOOR, WERE INOPERATIVE. REPLACED THE LAMP PN 1315 FOR THE OVERWING EXIT, AND REPLACED THE POWER SUPPLY PN 5822-2 FOR THE CEILING LIGHT.

Part: WIRE — CHAFED (PA SYSTEM) · airframe 55,553 hrs · 28,874 cycles

CREW REPORTED THE PA SYSTEM WAS INOPERATIVE FROM THE AFT FLIGHT ATTENDANT POSITION. FOUND SEVERAL WIRES HAD SHORTED AND BURNED FROM RUBBING ON A LIGHTENING HOLE. A COUPLE OF THE WIRES HAD BURNED THRU. DEACTIVATED AFFECTED SYSTEMS, CAPPED WIRES, AND MAINTENANCE FERRIED THE AIRCRAFT TO MCI, WHERE ALL DAMAGED WIRES WERE REPAIRED. THE LIGHTENING HOLE GROMMET WAS ALSO REPLACED. CHECK-C 4-12-01 MCI.

Part: FITTING — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND STRINGER TIE FITTING HAD CORROSION AT STA 1338, STRINGER 21R. REPLACED STRINGER 21R TIE FITTING PER SRM 51-30-05.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CORROSION ON LONGERON 26R, BETWEEN STA 1338 AND 1322. INSTALLED NEW LONGERON AND SPLICE PER SRM 53-02, PAGE 49 AND ARA 17645, STA 1297 TO 1338.

Part: SKIN — DENTED (FUSELAGE) · airframe 55,078 hrs · 78,621 cycles

DURING CHECK-C MAINT FOUND DENT IN FUSELAGE FROM STA 229 TO 234, BETWEEN LONGERON 24L AND 25L. DENT WAS 5 INCHES BY 1.750 BY 0.020 DEEP. REPAIRED DENT IN FUSELAGE PER SRM 53-04, PAGE 37 FIG 12B.

Part: SKIN — DENTED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND DENT IN FUSLEAGE AT STA 237, BETWEEN LONGERON 24L AND 25L. DENT WAS 1 INCH BY 2 IN BY 0.050 DEEP. REPAIRED DENT PER 53-04, PAGE 37 FIG 12B.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CORROSION ON PRESSURE BULKHEAD AT STA 1338, BETWEEN STRINGER 25R AND 26R. REMOVED AND REPLACED TIE FITTING. INSTALLED FASTENERS PER DRAWING 5911429.

Part: SKIN — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CORROSION ON STA 1338 AFT PRESSURE BULKHEAD LOWER TEE. REPLACED FUSELAGE SKIN STA 1311 TO 1338, LONGERON 21R TO 26R, PER ARA 17647 AND SRM 53-04 FIG 12C.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT THE LOWER Y CHORD SECTION AT STA 1338, STRINGER 24R TO 24L, HAD CORROSION. INSTALLED Y-CHORD PER SRM 53-03 FIG 37A, AND ARA 17647A, STRINGER 23R TO 23L.

Part: FORMER — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CORROSION ON FORMER AT STA 1308 AT LONGERON 28L TO 28R. CUT OUT CORROSION. INSTALLED NEW FORMER SECTION LONGERON 28L TO 28R AND REPAIRS PER SRM 53-03, PAGE 4A. PAINTED AND TREATED PER SRM 51-10-3.

Part: FORMER — DAMAGED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND AIR SUPPLY VALVE HAD WORN HOLE INTO FORMER RING AT STA 1380, BELOW LONGERON 5L AND 6L. INSTALLED DOUBLER PER SRM 53-01 FIG 4. REINSTALLED LT TEMP CONTROL VALVE PER MM 20-10-11. LEAK CHECKED.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CORROSION ON LONGERON 29L, STA 1287 TO 1308. REMOVED CORROSION BY REPLACING PART. INSTALLED NEW LONGERON PER SRM 53-14-3, PAGE 21. INSTALLED FASTENERS PER SRM 51-30-02 AND 51-30-5.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CORROSION ON BOTTOM OF LONGERON 20R AT INTERSECTION WITH STA 1338 AND TIE CLIP AT END OF LONGERON. REMOVED CORRODED EXTRUSION SECTION AND INSTALLED EXTRUSION AND REPAIR SPLICE FROM STA 1314 TO 1338 PER SRM 53-02 FIG 18.

Part: FORMER — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CORROSION ON FORMER 1338, 4 INCHES ABOVE LONGERON 18L, AFT OF LAV TANK HOLD DOWN CLIP, BETWEEN CLIP AND FORMER. REPAIRED PER SRM 53-03 FIG 14. TREATED METAL PER SRM 51-10-03.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND TOP OF FLOOR SUPPORT CORRODED IN SEVERAL PLACES AT STA 1155, BETWEEN LBL 15 AND RBL 07. INSTALLED NEW SUPPORT REF IPC 25-52-00 FIG 3L. SRM 51-30-2 RIVET INSTALLATION.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND FLOOR SUPPORT CORRODED AT SEVERAL PLACES STA 1136 TO 1212, RBL 8 INCHES. INSTALLED NEW SUPPORT PER DRAWING 5936660. INSTALLED BOLTS, WASHERS AND NUTS PER SRM 51-30-1.

Part: FORMER — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND FORMER WITH CORROSION AT STA 1338, 5 INCHES ABOVE LONGERON 18R AT ATTACH POINT FOR LAV TANK HOLD DOWN CABLE. REPAIRED FORMER PER SRM 53-03 FIG 14 PAGE 37. TREATED BARE METAL PER 51-10-3. ALL REPAIR PARTS PRE PAINTED.

Part: SPLICE — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CORROSION ON LONGERON SPLICE AT STA 1193, LONGERON 29L. REMOVED CORROSION BY REPLACEMENT OF PART. INSTALLED FABRICATED PART MANUFACTURED PER DRAWING 3914677 AND INTERSHOP TAG 892670. INSTALLED FASTENERS PER SRM 51-30-5.

Part: BRACKET — CORRODED (AFT CARGO BAY) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND BRACKETS CORRODED AT FWD CARGO DOOR STA 1155 LOWER AFT CORNER OF ENTRY SILL AREA, AND STA 1212 LOWER FWD CORNER OF ENTRY SILL AREA. INSTALLED NEW BRACKETS PER SRM 51-30-5. PART MANUFACTURED PER DRAWING 5936070.

Part: FRAME — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND FORMER CORRODED AT STA 1212, LONGERON 26 TO 27L. REMOVED CORROSION BY REPLACEMENT OF PART. INSTALLED NEW FRAME PER PRINT 9936073.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND FORMER FOOT CRACKED AT STA 1309, BETWEEN LONGERON 13 AND 14. REPLACED CRACKED FORMER FOOT. SPLICED PER SRM 53-03 FIG 3. INSTALLED PER SRM 51-30-02/05. PRIMED AND TREATED PER SRM 51-10-03.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT IN FWD CARGO COMPT FOUND CORROSION ON BOTTOM OF FLOOR SUPPORT AT STA 138, AT INTERSECTION WITH LONGERON 18R, CORROSION ON REAR OF BULKHEAD AT STA 1338 APPROX 18 INCHES INBD OF LONGERON 18R, AND CORROSION AT STA 1338 EXTREME UPPER RT FWD CORNER OF BULKHEAD JUST BELOW LONGERON 18R. ABOVE 3 WRITE-UPS ARE ON THE SAME FLOORBEAM. REPAIRED PER SRM 53-05 FIG 108. ALL PARTS PRE-PAINTED.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND 4 INCH J-ANGLE FLOOR SUPPORT CORRODED AT STA 1155, RBL 13 INCHES. REPLACED ANGLE WITH NEW. INSTALLED HI-LOKS PER SRM 51-30-5.

Part: SKIN — DENTED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND DENT 2.7 BY 3.6 BY 0.093 DEEP IN SKIN OF AFT CARGO DOOR. CUT OUT 2 .6875 ROUND PLUG FROM SKIN 0.050. INSTALLED 2024-T3 PLUG WITH A BACK UP PLATE 301 .25 H, 0.032 PER SRM 52-05, PAGE 4 FIG 3.

Part: FRAME — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT IN THE AFT CARGO COMPT, CORROSION WAS FOUND ON FORMER AT STA 1271, LONGERON 28R TO 28L. REMOVED CORROSION. INSTALLED NEW J-ANGLE. PAINTED REMOVED PARTS WHITE AND INSTALLED REPAIR PER SRM 53-03, FIG 2.

Part: WEB — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND FLOOR MEMBRANE CORRODED AT STA 163, LBL 16 INCHES. REMOVED CORROSION PER SPM 6-80-01. TREATED AREA PER SRM 51-10-3. FABRICATED DOUBLERS AND INSTALLED PER SRM 53-01, FIG 4 SHEET 3.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CRACK AT FORMER FOOT (SHEAR TIE) STA 1429, BETWEEN LONGERON 1 AND 2R. REPLACED FORMER FOOR PER DRAWING 9911840-112. INSTALLED PER 51-30-02/05.

Part: WEB — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND HEAVY CORROSION ON MEMBRANE AT LBL 54 INCHES, BETWEEN STA 160 AND 190. REMOVED CORRODED AREA. FABRICATED DOUBLER AND INSTALLED PER SRM 53-01 FIG 4 SHEET 3. TREATED PER SRM 51-10-3.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT AT LBL 54, STA 1309, FOUND CORROSION ON CABIN CHAIR TRACK FLANGE. REMOVED CORROSION PER SPM 6-80-01. REMOVED DAMAGED TRACK PER DRAWING 5930966. INSTALLED PER SPM 6-70-01 AND SRM 51-30-1.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CORROSION IN CABIN ON SEAT TRACK, AT LBL 54 INCHES, STA 1252 AND STA 1283 TO 1280. REMOVED DAMAGED TRACK AT BOTH LOCATIONS. INSTALLED NEW PER DRAWING 5930566, SPM 6-70-01 AND SRM 51-30-1.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CABIN FLOOR TRACK AT LBL 54, THE NUMBER 1 TRACK WAS GROUND BEYOND LIMITS AT STA 1237 AND 1303. REMOVED DAMAGED TRACK STA 1174 TO 1303. MADE NEW PER DRAWING 5930966. INSTALLED PER SPM 6-70-01 AND SRM 51-30-1.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CORRODED FLOOR PANEL SUPPORT AT STA 200, RBL 4 INCHES TO LBL 4 INCHES. REMOVED CORRODED SUPPORT. FABRICATED NEW SUPPORT FROM STOCK AND TREATED PER SRM 51-10-3. INSTALLED PER SRM 51-30-2 AND 51-20-0.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CORRODED FLOOR SUPPORT AT RBL 44 INCHES, STA 160 TO 200. REMOVED CORRODED SUPPORT AND FABRICATED NEW SUPPORT. INSTALLED PER SRM 51-30-2. TREATED PER SRM 51-10-3.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT, FOUND LONGERON 12L CRACKED AT ATTACH POINT TO 1287 FORMER RING. REMOVED CRACKED LONGERON FOR REPAIR PER SRM 53-02 FIG 18.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT, FOUND CORROSION AT LBL 36 INCHES, STA 1138 TO 1110. REPLACED TRACK. FABRICATED NEW TRACK FROM STOCK AND INSTALLED PER SRM 51-30-01. PRIMED PER SRM 51-10-3. PAINTED PER SRM 51-10-3.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT, FOUND INTERCOSTAL CORRODED, ATOP FLOORBEAM AT STA 1250, LBL 23 TO 46. REPLACED CORRODED FLOORBEAM SUPPORT AND INSTALLED FASTENERS PER SRM 51-30-05.

Part: WEB — CRACKED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT, FOUND MEMBRANE WITH 3 INCH CRACK AT LBL 50, STA 1022, BETWEEN NUMBER 1 AND 2 FLOOR TRACKS. REPAIRED CRACK AT LBL 50 INCHES, STA 1022 MEMBRANE PER SRM 53-01, FIG 2, SHEET 3 AND PAGE 9. TREATED AND PRIMED AREA PER SRM 51-10-2.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT FOUND CHAIR TRACK WITH HEAVY CORROSION AT STA 1130 TO 1322, LBL 22 INCHES. REMOVED AND REPLACED TRACK PER SPM 6-70-01. INSTALLED FASTENERS PER SRM 51-30-01, STA 1307 TO 1028. TRACK PREPAINTED.

Part: PAN — CORRODED (CABIN FLOOR) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT, FOUND CORROSION ON FLOOR PAN AT STA 150, LBL 8 INCHES AND RBL 8 INCHES. REPAIRED PER SRM 53-01 PAGE 18. TREATED AND PAINTED PER SRM 51-10-3.

Part: WEB — CORRODED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT, FOUND CORROSION ON FLOOR MEMBRANE AT STA 1250, LBL 49. CUT OUT CORRODED AREA AND INSTALLED WEB REPAIR PER SRM 51-70-4.

Part: CLIP — CRACKED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT, FOUND CLIP CRACKED AT STA 236, LT SIDE BETWEEN STRINGER 28 AND 27 UNDER LT TRACK. REMOVED CRACKED ANGLE AND FABRICATED NEW ANGLE PER SPM 6-70-01, AND DOUGLAS DRAWING 9915554, ANGLE ITEM -7, AND REINSTALLED.

Part: CLIP — CRACKED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT AT STA 236, BETWEEN STRINGER 28 AND 27, A CLIP FOR FLOOR SUPPORT WAS CRACKED UNDER RT FLOOR TRACK. MADE AND INSTALLED NEW PART PER DRAWING 9915554 AND SRM 51-30-5.

Part: DOUBLER — CRACKED (LT WING) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT, FOUND DOUBLER AND TIE ANGLE CRACK AT PREVIOUS REPAIR BETWEEN NUMBER 5 AND 6 LE TRACK AT LT WING LEADING EDGE SKIN, AT PRODUCTION BREAK. FABRICATED DOUBLER PER SRM 57-32-1 ITEM 4. FABRICATED NEW ANGLE PER DRAWING 9937517. REF SRM 51-30-2 FOR RIVET INSTALLATION. SRM 51-30-5 FOR HI-LOK INSTALLATION.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT, FOUND CRACKED FLOOR SUPPORT AT STA 948, LBL 6. FABRICATED NEW SUPPORT PER DRAWING 5930560-61. INSTALLED PER SPM 6-70-01 AND SRM 51-01. TYPE FASTENERS PER SRM 51-30-2. PRIMED PER SRM 51-10-3.

Part: DOOR — CRACKED (LT MLG) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT, THE LT WHEEL WELL GEAR DOOR HAD APPROX .75 INCH CRACK IN INNER PAN RADIUS, IN AFT, OUTBOARD CORNER. CONFIRMED BY EDDY CURRENT. REPLACED CORNER ON GEAR DOOR USING FASTENERS PER SRM 51-30-5 AND SRM 51-30-2.

Part: STRUCTURE — CRACKED (CARGO DOOR) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT, THE FWD CARGO DOOR T/E WAS CRACKED AT AFT SIDE BETWEEN STRINGER 24R AND 25R. ACCOMP HIGH FREQ EDDY CURRENT PER 51-00-03 PART 6 AND NO CRACKS FOUND. REMOVED DAMAGED AREA AND INSTALLED DOUBLER PER SRM 52-05. INSTALLED FASTENERS PER SRM 51-30-02.

Part: SUPPORT FITTING — NICKED (RT WING MLG) · airframe 55,078 hrs · 28,621 cycles

DURING CHECK-C MAINT ON RT WING ON STRUT OF MAIN LANDING GEAR SUPPORT FITTING, THE FWD END OF HYD VALVES HAD A NICK IN THE FITTING. BLENDED OUT NICK PER SRM 53-01 FIG 1 SHEET 1.

Part: LIGHT — INOPERATIVE (CABIN)

DURING PREFLIGHT CHECKS, FIRST CLASS EGRESS LIGHTS WERE FOUND INOPERATIVE. MOISTURE WAS FOUND IN THE LIGHTING TRACK. MOISTURE WAS DRIED FROM THE TRACK AND CONNECTORS AND LIGHTS OPERATED NORMALLY. CHECKS WERE MADE FOR NORMAL OPERATION. CHECK-C 12-15-98 STL.

Part: BLADE — FRACTURED (TURBINE)

CLIMBING THROUGH 12,000 FEET A LOUD BOOM WAS HEARD FROM THE LT ENGINE. THERE WAS NO THROTTLE RESPONSE. SHUT DOWN THE ENGINE AND RETURNED TO SEA. FOUND SIGNIFICANT DAMAGE TO THE COMPRESSOR AND TURBINE. CHANGED THE ENGINE. CHECK-C 12-15-98 STL. *S/D* FOUND A FOURTH STAGE TURBINE BLADE FRACTURED DUE TO FATIGUE AND BLADE TIP RUB, CAUSING THE FRACTURE OF ALL OTHER FOURTH STAGE BLADES AND DAMAGE TO THIRD AND SECOND STAGE INNER SHROUDS.

Part: SOCKET — WORN (CABIN)

ELECTRICAL SMELL FIRST TWO ROWS OF COACH. LOWER SIDE WALL AND UPPER SIDE WALL LIGHTS WERE TURNED OFF AND ODOR WENT AWAY. FOUND EVIDENCE OF ARCING ON CABIN ROW 5A UPPER SIDE WALL LIGHT. REPLACED SOCKET. CHECK-C 12-16-97 MCI.

Part: INTERCOSTAL — CORRODED (FUSELAGE)

MCI - DURING OP-16, FOUND INTERCOSTAL CORROSION. REPLACED PART PER SRM 51-00 AND STANDARD PRACTICES. (M)

Part: GALLEY TRACK — CORRODED (BS 1174-1322)

MCI - DURING OP-16, FOUND CORROSION AROUND TIE HOLES OF OUTBOARD GALLEY TIE TRACK, LBL 54, FS 1174, 1210, 1238, 1295. REPLACED TRACK FROM 1174 TO 1322 PER MM 53-10-01. (M)

Part: INTERCOSTAL — CORRODED (BS 1231)

MCI - DURING OP-16, FOUND CORROSION ON INTERCOSTAL AFT OF STATION 1231 FRAME AT LONGERON 25L. REMOVED CORROSION PER SRM 51-10-3 AND STANDARD PRACTICES. (M)

Part: SUPPORT — CORRODED (CABIN FLOOR)

MCI - DURING OP-16, FOUND CORROSION ON CABIN FLOOR SUPPORT INBOARD OF FORWARD GALLEY DOOR. REPLACED PART PER SRM 51-10-3. (M)

Part: FLOOR TRACK — CORRODED (BS 1022-1155)

MCI - DURING OP-16, FOUND CORROSION ON CARGO FLOOR TRACK, LONGERON 27R-28R, FS 1022-1155. REPLACED PART PER SRM 51-01. (M)

Part: FORMER — CORRODED (BS 1271)

MCI - DURING OP-16, FOUND CORROSION ON FORMER, STATION 1271 AT LONGERONS 28L AND 29R. REMOVED CORROSION PER SRM 51-10-01 AND REPAIRED PER SRM 53-03, FIGURE 2A. (M)

Part: SUPPORT — CORRODED (BS 1320)

MCI - DURING OP-16, FOUND CORROSION ON FLOOR SUPPORT, LONGERON 26L TO 26R, STATION 1320. REPAIRED PER SRM 53-01, FIGURE 1. (M)

Part: RUB STRIP — CORRODED (BS 769-788)

MCI - DURING OP-16, FOUND CORROSION IN THE FAIRING RUB STRIP AREA OF RT FORWARD FILLET, BETWEEN FS 769 TO FS 788, AND FROM LONGERON 28R TO 29R. REPAIRED PER SRM 53-04, FIGURE 53. (M)

Part: FITTING — CORRODED (BS 1338)

MCI - DURING OP-16, FOUND CORROSION ON CORNER FITTING AT LEFT STATION 1338. REPLACED GUSSET PER SRM 51-1, PAGE 1. (M)

Part: RUB STRIP — CORRODED (BS 788-807)

MCI - DURING OP-16, FOUND CORROSION UNDER FAIRING RUB STRIP OF RT FORWARD FILLET AREA, BETWEEN FS 788-807, LONGERON 28R AND 29R. REMOVED CORROSION AND REPAIRED PER SRM 53-04, FIG 53. (M)

Part: RUB STRIP — CORRODED (BS 807-826)

MCI - DURING OP-16, FOUND CORROSION UNDER FAIRING RUB STRIP OF RT FORWARD FILLET AREA, LOONGEON 29L TO LONGERON 29R, BETWEEN FS 807 AND 826. REPAIRED PER ATA 10902. (M)

Part: PAN — CRACKED (BS 1287-1307)

MCI - DURING OP-16, FOND DIAPHRAM PAN CRACKED 12 INCHES OUTBOARD OF NR 6 CHAIR TRACK, LONGERON 18R, STATION 1287-1307. STOP DRILLED CRACK PER SRM 51-10-00 AND REPAIRED PER SRM 53-00-09, PAGE 347. (M)

Part: RUB STRIP — CORRODED (BS 750-769)

MCI - DURING OP-16, FOUND CORROSION IN THE FAIRING RUB STRIP AREA OF RT FORWARD FILLET, LONGERON 26R TO LONGERON 28R, BETWEEN FS 750 TO FS 769. REPAIRED PER SRM 53-04, FIGURE 53. (M)

Part: FLOOR TRACK — CORRODED (BS 1126-1222)

MCI - DURING OP-16, FOUND CORROSION ON NR 2 FLOOR TRACK AT LEFT AFT SERVICE DOOR, LBL 44. INSTALLED NEW FLOOR TRACK FS 1126 TO 1222, PER SRM 53-05, PAGE 10G. (M)

Part: PAN — CRACKED (BS 1271-1287)

MCI - DURING OP-16, FOUND DIAPHRAM PAN CRACKED 2.5 INCHES OUTBOARD OF NR 6 CHAIR TRACK, LONGERON 18R, STATION 1271-1287. STOP DRILLED CRACK PER SRM 51-10-00 AND REPAIRED PER SRM 53-00-09, PGE 347. (M)

Part: FORMER — CORRODED (BS 1309)

MCI - DURING OP-16, FOUND FORMER CORROSION, LONGERON 20L TO 20R, FS 1309. REPLACED PART PER SRM 53-10-01. (M)

Part: AIR DATA COMP — FAILED (E/E COMPT)

JFK - DURING TAKEOFF THE CENTRAL AIR DATA COMPUTER FAILED. AIRCRAFT RETURNED TO JFK. REMOVED AND REPLACED THE CADC, MFG P/N HG280D80. SELF TEST AND LEAK CHECK NORMAL. (M)

Part: CSD — FAILED (NR 2)

JFK - DURING CRUISE, THE NR 2 CONSTANT SPEED DRIVE FAILED. REMOVED AND REPLACED NR 2 CSD. OPERATIONAL CHECK NORMAL. (M)

Part: ANTI-ICE — CABIN SMOKE (ENGINE)

STL - FLT 269 - DURING APPROACH WITH ANTI-ICE ON, A LIGHT SMOKE APPEARED IN CABIN. TURNED ANTI-ICE OFF, SMOKE DISSIPATED. PERFORMED ENGINE HIGH POWER RUN, NO SMOKE OR ODOR DETECTED, AND LEAK CHECKED DUCTING. CHECK C-1D - 9-14-94 - MCI.