N925L

Part: BRACKET — MISSING (RT WING)

DURING OP 16 MAINT CHECK, RT WING TE NEED INSTALL RIB ASSEMBLY OTBD OF CENTER FLAP HINGE ASSEMBLY AFTER FLAP BRACKET INSTALLED. INSTALLED RIB ASSEMBLY USING HI-LOCKS PER SRM 51-30-5 AND RIVETS PER SRM 51-30-2.

Part: BRACKET — DAMAGED (LT WING)

DURING OP 16 MAINT CHECK ON LT WING TE NEED INSTALL RIB ASSEMBLY OTBD OF CENTER, FLAP HINGE ASSEMBLY, AFTER FLAP HINGE BRACKET INSTALLED. REINSTALLED HI-LOCKS IN RIB ASSEMBLY PER SRM 51-30-5, PAGE 12 AND 13, PARAGRAPH 7 A AND B. REINSTALLED RIB PER SRM 51-30-2.

Part: BOLT — CORRODED (RT WING)

DURING OP 16 MAINT CHECK, FOUND ON RT WING TE, RUST EMITTING FROM TOP INBD BOLT OF CENTER FLAP HINGE CASTING AT REAR SPAR. ACCOM HIGH FREQ EDDY CURRENT OF HOLES AND AREA PER TWA NDT 51-00-03, PART 6, AND 2 EA CRACKS FOUND. INSTALLED 4 EA NEW STUDS AND ONE FLAP HINGE FITTING PER MM 57-40-1.

Part: BRACKET — CORRODED (LT WING)

DURING OP 16 MAINT CHECK, FOUND ON LT WING TE THE INBD FLAP HINGE SUPPORT BRACKET HAD RUST EMITTING FROM BETWEEN HINGE SUPPORT BRACKET TO ATTACH BOLT. ACCOMP HIGH FREQ EDDY CURRENT OF HOLES IN AREA PER TWA NDT 51-00-03 PART 6. INSTALLED NEW STUDS AND FLAP HINGE FITTING PER MM 57-40-1.

Part: HINGE — CORRODED (LT WING)

DURING OP 16 MAINT CHECK, FOUND ON LT WING, CENTER FLAP HINGE SUPPORTS HAD RUST EMITTING FROM HINGE TO REAR SPAR ATTACH BOLTS. ACCOMP HIGH FREQ EDDY CURRENT TO HOLES AND AREA PER TWA NDT 51-00-3, PART 6. INSTALLED NEW STUDS AND FLAP HINGE FITTING PER MM 57-40-1.

Part: FRAME — MISREPAIRED (BS 980)

DURING OP 16 MAINT CHECK, FOUND AN INCORRECT REPAIR ON FUSELAGE FRAME AT STA 980, BETWEEN LONGERON 14L AND 16L. CUT OLDER SECTION OF FORMER RING BETWEEN STA 10 AND 11, AND INSTALLED NEW RING PN 9958238-7. INSTALLED SPLICE FABRICATED FROM 0.063, 7075-0 HEAT TREAT TO T6 PER SRM 53-05, FIG 32, SHEET 2 AND 3.

Part: FRAME — MISREPAIRED (BS 980)

DURING OP 16 MAINT CHECK, FOUND IN RT LAV AT STA 980 FORMER RING BETWEEN LONGERON 15 AND 16 AN INCORRECT REPAIR INSTALLED. CUT FORMER RING BETWEEN STRINGER 10 AND 11 AND INSTALLED NEW BOEING RING PN 9958238-7. INSTALLED SPLICE PER SRM 53-03, FIG 32, SHEET 2 AND 3. DOUBLER MADE FROM 7075-O, 0.063 IN, HEAT TREATED TO T6. INSTALLED CLIPS PER MO 72J14H AT STRINGER 13, 14, 16, AND 17.

Part: SPAR — CRACKED (RT WING)

DURING OP 16 MAINT CHECK, FOUND ON RT WING 2 EA SURFACE CRACKS AT TOP OF REAR SPAR, INBD HOLE 3/8 IN LONG, OTBD HOLE .5 IN LONG, AT CENTER FLAP HINGE AREA. STOP DRILLED CRACKS PER DOUGLAS REPAIR DOCUMENT JO60272. REPAIRED CRACKS AT TOP OF REAR SPAR RT WING AT CENTER FLAP HINGE PER JO60272. SUBSTITUTED HL325-6 FOR HLT59-6 PER SRM 51-60-0, FIG 4, PARAGRAPH 33.

Part: SKIN — DAMAGED (TE FLAP)

DURING OP 16 MAINT CHECK, FOUND RT WING FLAP LOWER SKIN AND DOUBLER WITH BAD HOLES BY OTBD HINGE CASTING. FABRICATED SKIN AND DOUBLER PER SRM 57-50-9. REPLACED SKIN AND FILLER SECTION PER SRM 51-10-01.

Part: ANGLE — CORRODED (BS 216)

DURING OP 16 MAINT CHECK, FOUND CABIN ATTACH ANGLE AND MEMBRANE WITH CORROSION AT RBL 55 IN, STA 216. REMOVED AND REPLACED MEMBRANE AND FLOOR ATTACH ANGLE PER SPM 6-70-01, PART A AND B. ANGLE REPLACED ON SEPARATE NON ROUTINE.

Part: FLOOR PAN — CORRODED (BS 218)

DURING OP 16 MAINT CHECK, FOUND LIGHT CORROSION AT CABIN FLOOR PAN STA 218, LONGERON 18R. REMOVED AND REPLACED FLOOR PAN PER SPM 6-70-01, PART A AND B.

Part: ANGLE — CORRODED (BS 200)

DURING OP 16 MAINT CHECK, FOUND STA 200, RBL 0 TO 57 IN, WITH CORROSION ON CABIN FLOOR ATTACH ANGLE. REMOVED AND REPLACED FLOOR ATTACH ANGLE PER SPM 6-70-01, PART A AND B.

Part: SPAR — LIGHTNING STRIKE (ELEVATOR)

DURING OP 16 MAINT CHECK, FOUND LT ELEVATOR REAR SPAR LOWER SURFACE APPROX 14 IN FROM OTBD END WITH SKIN BURNED FROM LIGHTNING STRIKE. REMOVED DAMAGED AREA AND INSTALLED FILLER AND DOUBLER PER SRM 55-03, FIG 15 PAGE 32.

Part: SEAT TRACK — CORRODED (BS 200 - 229)

DURING OP 16 MAINT CHECK, FOUND CABIN FLOOR TRACK WITH CORROSION AT RBL 45 IN, STA 200 TO 229. REMOVED OLD PART OF TRACK AND INSTALLED NEW PIECE PER SRM 53-05, FIG 4.

Part: SPAR — CRACKED (ELEVATOR)

DURING OP 16 MAINT CHECK, FOUND RT ELEVATOR FRONT SPAR CRACKED APPROX 120 IN FROM INBD END. REPAIRED PER DWG 5934866-503.

Part: ANGLE — CRACKED (NR 2 PYLON) · airframe 75,588 hrs · 80,116 cycles

DURING OP 16 MAINT CHECK, NUMBER 2 PYLON FWD END OF CANNON PLUG CONNECTOR HOOK UP, IN PYLON FWD I/B ANGLE WAS CRACKED OUT BEYOND STOP DRILL. ADDITIONAL DAMAGE FOUND ON ANGLE. REMOVED AND REPLACED PER DRAWING 9958193. CANCELLED ARA 16323 WITH 16323A. REPLACEMENT OF PART PER SPM 6-70-01, 4A PAGE 2 AND 3.

Part: PANEL — GOUGED (BS 698)

DURING OP 16 MAINT CHECK, FOUND IN RT WHEEL WELL RT TRAPAZOIDAL PANEL AREA AT STR 20R, ABOVE RT TRAP PANEL, HAD 3.5 IN GOUGE BY 0.015 IN DEEP, STA 698. BLENDED GOUGE PER SRM 53-01, FIG 1 PAGE 6 LIMITS, AND 51-10-03 PROCESS. TREATED ON NON-ROUTINE CARD.

Part: SEAT TRACK — CORRODED (BS 200 - 229)

DURING OP 16 MAINT CHECK, FOUND LIGHT CORROSION ON CABIN FLOOR TRACK CLIP NUT ATTACH, STA 200 TO 229, LBL 45. REMOVED CORRODED TRACK FROM STA 200 TO 229, AND SPLICED IN NEW PER SRM 53-05, FIG 4F.

Part: FLOOR PANEL — CORRODED (BS 917 - 965)

DURING OP 16 MAINT CHECK, THE CABIN FLOOR MEMBRANE AND FORMER FOOT WAS CORRODED AT STA 929, APPROX RBL 58. REMOVED CORROSION AT FORMER FOOT AND ATTACH AREA SRM 51-10-3. REINSTALLED FORMER FOOT AND NEW FAB MEMBRANES PER SRM 51-30/51-10-4/53-05 FIG 97 AT STA 917 TO 965.

Part: RIB — CRACKED (RT WING)

DURING OP 16 MAINT CHECK, FOUND ON THE RT WING A CRACK APPROXIMATELY 1 IN LONG WAS FOUND IN REPAIR DOUBLER OF WING L.E. RIB, 13 IN OTBD OF INBD END OF NUMBER 4 SLAT. INSTALLED NEW DOUBLER AND SHIM PER SRM 57-06A, FIG 5, SHEET 1 AND 4.

Part: FLOOR PANEL — CORRODED (BS 917 - 965)

DURING OP 16 MAINT CHECK, FOUND THE CABIN FLOOR MEMBRANE AND FORMER FOOT AT LONGERON 18R, STA 945, APPROX RBL 58 WAS CORRODED. REMOVED CORROSION AT FORMER FOOT AND ATTACH AREA PER SRM 51-10-3. REINSTALLED FORMER FOOT AND NEW FAB MEMBRANE PER SRM 51-30/51-1-4/ AND 53-05, FIG 97, AT STA 917 TO 965.

Part: SKIN — CRACKED (BS 1221)

DURING OP 16 MAINT CHECK, FOUND THE LEFT AFT FUSELAGE SKIN AT STA 1221, OTBD AT FWD CORNER OF VERT LOUVERS THE FWD OTBD ATTACH CLIP ANGLE WAS CRACKED THROUGH ON THE FWD SIDE. REPLACED CLIP AT STA 1221 PER SRM 53-05, FIG 66. FABRICATED LOWER CLIP OUT OF 2024-O, 0.080, HEAT TREATED TO 2024T4 PER SPM 6-70-01, PAGE 2 AND 3. REPLACED CLIP PER SRM 53-05, FIG 66.

Part: ANGLE — CRACKED (NR 2 PYLON) · airframe 75,588 hrs · 80,116 cycles

DURING OP 16 MAINT CHECK, NUMBER 2 PYLON INTERIOR, O/B VERTICAL ANGLE WAS CRACKED AT BOTTOM, JUST AFT OF 13TH STAGE PNEUMATIC DUCT. DIRECTLY BELOW FIRE SPRAY TUBE. REPAIRED FLANGE USING 2 FABRICATED DOUBLERS OF 0.012 ALUMINUM PER SRM 53-01, PAGE 10 FIG 2, SHEET 4.

Part: WEB — CORRODED (BS 195 - 204)

DURING OP 16 MAINT CHECK, FOUND CORROSION ON LOWER AFT CORNER OF DOOR FRAME AND CABIN FLOOR WEB, APPROX STA 195 TO 204, LBL 59 IN. CUT OUT CORRODED SECTION PER SPM 6-80-01. REPLACED CUSP PER ARA 16316 FROM MIDDLE OF ENTRY DOOR TO STA 229. REPLACED MEMBRANE.

Part: FRAME — CORRODED (BS 200)

DURING OP 16 MAINT CHECK, FOUND CORROSION AT STA 200, ON BOTH SIDES OF FORMER AT FLOOR LINE, FORWARD LEFT CABIN DOOR. CUT OUT CORRODED SECTION PER SPM 6-80-01. REMOVED AND REPLACED SUPPORT FROM MIDDLE OF FORWARD LEFT ENTRY DOOR TO STA 229, PER ARA 16316.

Part: FLOORBEAM — CORRODED (BS 200)

DURING OP 16 MAINT CHECK, FOUND STA 200 CABIN FLOORBEAM OUTER EDGE CORRODED LBL 52 TO 55. CUT OUT CORRODED SECTION PER SPM 6-80-01. REPAIRED BEAM CAP PER ARA 16316.

Part: CUSP — CORRODED (BS 165 - 185)

DURING OP 16 MAINT CHECK, FOUND LIGHT CORROSION ON LT FWD ENTRY DOOR FLOOR SILL ATTACH ANGLE AT SCREW HOLES APROX STA 165 TO 185, LBL 59. CUT OUT CORRODED DOOR SILL. REPLACED DOOR SILL CUSP FROM MIDDLE OF ENTRY DOOR TO STA 229, PER ARA 16316.

Part: ANGLE — CORRODED (BS 160)

DURING OP 16 MAINT CHECK, FOUND CORROSION ON CABIN FLOOR ATTACH ANGLE STA 160 TO 200, LBL 45. REMOVED AND REPLACED SUPPORT PER SPM 6-70-1, PAGE 3.

Part: SKIN — PUNCTURED (LE FLAP) · airframe 75,588 hrs · 80,116 cycles

DURING OP 16 MAINT CHECK, THE RT WING L/E HAD SMALL PUNCTURE HOLE AT L/E ON O/B END, AFT OF O/B END OF NUMBER 5 L/E SLAT. REMOVED WING TIP SUPPORT EXTENSION L/E PER SRM 51-30 AND 51-10-4. SENT PART TO WELDING SHOP TO BE WELDED PER DRAWING 5923349. CLEANED UP OR GROUND WELD PER DRAWING 5923349. PAINTED AND TREATED PER SRM 51-10-3. INSTALLED FASTENERS PER SRM 51-30.

Part: SPAR — CRACKED (LT WING)

DURING OP 16 MAINT CHECK, FOUND ON LT WING, 2 CRACKS AT TOP BOLT HOLES, OTBD APROX .375 IN LONG, INBD APPROX .25 IN LONG, ON REAR SPAR FACE AT CENTER FLAP HINGE SUPPORT, 1 O'CLOCK POSITION. STOP DRILLED CRACKS AROUND ATTACH BOLT HOLES PER SERVICE REWORK DRAWING JO60272. EDDY CURENT STOP DRILLED. REPAIRED DAMAGE TO REAR SPAR AT CENTER HINGE SUPPORT BOLT HOLES PER DRAWING JO602272.

Part: SKIN — WORN (BS 813)

DURING OP 16 MAINT CHECK, FOUND WING TO FUSELAGE PANEL HAD WORN DEEPLY INTO THE SKIN ON LEFT SIDE, STA 813, LONGERON 26L. ACCOMP NDT INSP AND FOUND TOP SKIN EQUALS 0.022 MATERIAL LOSS AND BOTTOM SKIN 0.030 MATERIAL LOSS. REPAIRED, INSTALLED DOUBLER PER SRM 53-04, FIG 53.

Part: WEB — CORRODED (BS 1038)

DURING OP 16 MAINT CHECK, FOUND AFT INTERIOR AREA OF AFT ACCESSORY COMPT, STA 1038, THE LT ENG MOUNT INTERNAL TAIL STRUCTURE WEB WITH A 4 INCH CRACK. REPAIRED CRACK IN WEB STRUCTURE. STOP DRILLED HOLE, REPLACED DOUBLER PER SRM 53-01, FIG 2 SHEET 3.

Part: FAIRING — WORN (BS 813 - 816)

DURING OP 16 MAINT CHECK, FOUND RT WING LOWER EDGE OF FAIRING WAS WORN INTO FUSELAGE, STA 813 TO 816, FAIRING NUMBER 2207A. METAL HAD THICKNESS IND OF 0.048 AT STA 813, LONGERON 26R. REMAINDER OF AREA WAS OK. INSTALLED DOUBLER PER SRM 53-04, FIG 53, SHEET 1.

Part: FLOORBEAM — CORRODED (BS 216 - 229)

DURING OP 16 MAINT CHECK, FOUND LIGHT CORROSION ON CABIN FLOOR SUPPORT ANGLE AT BL 0, STA 216 TO 229. REMOVED AND REPLACED FLOOR SUPPORT ANGLE PER SPM 6-70-01.

Part: PANEL — WORN (BS 160 - 200)

DURING OP 16 MAINT CHECK, FOUND CABIN FLOOR AT STA 160 TO 200, LBL 0 TO LBL44, FLOOR PANEL MEMBRANE WITH DEEP WORN AREAS FROM CHAFING FLOOR PANEL WORN ALMOST THROUGH IN 22 PLACES. REMOVED AND REPLACED MEMBRANES FROM STA 160 TO 200, BLB 0 TO LBL 44, PER STD PROCESSES MANUAL 6-70-01.

Part: FLOORBEAM — CORRODED (BS 160 - 220)

DURING OP 16 MAINT CHECK AT STA 160 TO 220 FOUND CABIN FLOOR PANEL ATTACH ANGLE WITH CORROSION. REMOVED AND REPLACED FLOOR SUPPORT PER SPM 6-70-01.

Part: FLOORBEAM — CORRODED (BS 160)

DURING OP 16 MAINT CHECK, FOUND CORROSION ON TOP OF CABIN FLOOR PANEL ATTACH ANGLE, STA 160, LBL 0 TO 13 IN. REMOVED AND REPLACED FLOOR SUPPORT PER SPM 6-70-01.

Part: FLOORBEAM — CORRODED (BS 180)

DURING OP 16 MAINT CHECK, FOUND CORROSION ON TOP OF CABIN FLOOR PANEL ATTACH ANGLE, STA 180, RBL 0 TO 44 IN. REMOVED CORROSION PER SPM 6-80-01. REINSTALLED SUPPORT PER SPM 6-30-07. TREATED PER SRM 51-10-3.

Part: FLOORBEAM — CORRODED (BS 160)

DURING OP 16 MAINT CHECK, FOUND CORROSION ON CABIN FLOOR ATTACH ANGLE, STA 160, RBL 0 TO 53 IN. REMOVED AND REPLACED FLOOR SUPPORT PER SPM 6-70-01.

Part: STIFFENER — WORN (NR 2 NACELLE)

DURING OP 16 MAINT CHECK ON NUMBER 2 PYLON, THE SIDE COWL PANEL VERTICAL STIFFENER HAD WORN THROUGH AT REPAIR AND METAL HAD NOT BEEN ROUTED OUT TO PREVENT FURTHER CRACKING. ACCOMP EDDY CURRENT INSPECTION PER NDT 51-00-03 AND FOUND CRACK CONTAINED. REPAIRED PER SRM 54-01, FIG 1. REPLACED DOUBLER.

Part: FLOOR PANEL — WORN (BS 160 - 200)

DURING OP 16 MAINT CHECK, FOUND CABIN FLOOR AT STA 160 TO 200, RBL 0 TO 50 IN, THE FLOOR PANEL MEMBRANE WITH A HEAVY WORN DEEP AREA IN MEMBRANE FROM FLOOR PANEL CHAFING WORN ALMOST THROUGH. REMOVED AND REPLACED MEMBRANE FROM STA 160 TO 200, RBL 0 TO 50, PER SPM 6-70-01.

Part: SUPPORT — CORRODED (BS 197)

DURING OP 16 MAINT CHECK, FOUND CABIN FLOOR AT STA 197, LBL 0 TO 57 IN WITH CORROSION ON FLOOR PANEL ATTACH ANGLES. REMOVED AND REPLACED FLOOR SUPPORT PER SPM 6-70-01.

Part: FLOOR PANEL — CRACKED (BS 598)

DURING OP 16 MAINT CHECK, FOUND CABIN FLOOR MEMBRANE AT STA 598, APPROX RBL 55 IN, WAS CRACKED. STOP DRILLED CRACK AND INSTALLED REPAIR DOUBLER PER SRM 53-01, FIG 4, SHEET 3, PAGE 19.

Part: WINDOW FRAME — CRACKED (BS 794)

DURING OP 16 MAINT CHECK, FOUND IN LT CABIN STA 794 UPPER AFT CORNER OF WINDOW FRAME WITH A CRACK AT A FASTENER. REMOVED CRACKED AREA OF WINDOW PAN AND INSTALLED C ANGLE REPAIR PER SSRM 53-10-114.

Part: LONGERON — CRACKED (BS 200)

DURING OP 16 MAINT CHECK, FOUND LONGERON 2 LEFT CRACKED AT TIE BOLTS, STA 200. REMOVED AND REPLACED WITH NEW LONGERON FROM STA 148 TO APPROX STA 230 PER TWA SPM 6-70-01.

Part: FLOORBEAM — WORN (BS 408)

DURING OP 16 MAINT CHECK, FOUND AT STA 408, FLOORBEAM TOP CHORD WORN AT LBL 0-10 IN. BLENDED OUT WEAR MARKS PER SRM 53-05, FIG 20. INSTALLED 0.025 S/S WEAR STRIP PER SRM 53-05.

Part: FLOORBEAM — WORN (BS 427)

DURING OP 16 MAINT CHECK, FOUND AT STA 427, THE FLOORBEAM TOP CHORD WAS WORN AT LBL 0-10 IN. BLENDED OUT WEAR MARKS PER SRM 53-05, FIG 20. INSTALLED 0.025 S.S WEAR STRIP PER SRM 5305.

Part: BULKHEAD — CORRODED (BS 1019)

DURING OP 16 MAINT CHECK, FOUND CORROSION ON THE AFT PRESSURE BULKHEAD, STA 1019 LT SIDE JUST BELOW APU POWER LINE FEED THROUGH. REMOVED CORROSION PER SPM 6-80-01.

Part: ANGLE — CRACKED (BS 610)

DURING OP 16 MAINT CHECK, FOUND FUSELAGE TO WING ATTACH ANGLE CRACKED INBD OF LE OF LT WING, STA 610. REPLACED ANGLE WITH MFG PN 5910006-43. REINSTALLED HI-LOCKS PER SRM 51-30-5. INSTALLED BOLTS, NUTS AND WASHERS PER TWA SPM 6-30-07.

Part: SKIN — GOUGED (BS 503)

DURING OP 16 MAINT CHECK, FOUND A 2 INCH BY 2 1/2 INCH GOUGE AND TEAR IN THE FUSELAGE SKIN AT STA 503, LONGERON 20R. CUT OUT DAMAGED SKIN AND REPAIRED PER SRM 53-04, FIG 12B, SHEET 5.

Part: BULKHEAD — CORRODED (BS 1017)

DURING OP 16 MAINT CHECK, FOUND CORROSION AROUND THE AFT PRESSURE BULKHEAD. CORROSION WAS ON THE FINGER DOUBLER ON BULKHEAD AT STA 1017, LBL 25 INCHES. REMOVED CORROSION PER SPM 6-80-01.

Part: STIFFENER — CRACKED (BS 69)

DURING OP 16 MAINT CHECK, FOUND TOP FOOT OF VERTICAL STIFFENER CRACKED AT STA 69, RBL X-10. CRACK IS .25 IN LONG AND IN AFT END OF FOOT RADIUS. REMOVED AND REPLACED CRACKED STIFFENER PER SPM 6-70-01. INSTALLED HILOCKS PER SRM 51-30-05.

Part: FRAME — CRACKED (BS 83.5)

DURING OP 16 MAINT CHECK, FOUND INTERNAL STRUCTURE INBD OF WINDSHIELD WIPER MOTOR ACCESS WITH MFG PN 9911505-7 FRAME WITH 1 1/2 INCH LONG CRACK IN RADIUS AT X=+1, STA 83.5. REMOVED AND REPLACED FRAME PER MO 72N37.

Part: FRAME — CRACKED (BS 83.5)

DURING OP 16 MAINT CHECK, FOUND RT NOSE SECTION INTERNAL STRUCTURE, AS VIEWED INSIDE WINDSHIELD WIPER MOTOR ACCESS, HAD MFG PN 9911505-7 FRAME CRACKED AT X=-10, 1 1/2 INCHES LONG IN RADIUS AND 1 1/2 IN LONG BETWEEN 3 RIVETS AT STA 83.5. TWO EACH PLACES. REMOVED AND REPLACED FRAME PER MO 72N37.

Part: FRAME — CRACKED (BS 83)

DURING OP 16 MAINT CHECK AT STA 83 FORMER CRACKED AT LBL 10. STOP DRILLED CRACK. HFEC STOP DRILL PER TWA NDT PART 6-51-00-03, CRACK CONTAINED. REPAIRED CRACK PER SRM 53-03, FIG 34.

Part: ANGLE — CRACKED (BS 63)

DURING OP 16 MAINT CHECK, FOUND T ANGLE CRACKED, FORWARD SIDE OF STA 63, RBL 13. REMOVED AND REPLACED PART PER TWA STANDARD PROCESSES MANUAL 6-70-01.

Part: ANGLE — CRACKED (BS 69)

DURING OP 16 MAINT CHECK, FOUND ANGLE CRACKED, AFT SIDE OF STA 69, LBL 13. REMOVED AND REPLACED PART PER TWA STANDARD PRACTICES MANUAL 6-70-01.

Part: FRAME — CRACKED (BS 83)

DURING OP 16 MAINT CHECK AT STA 83 FORMER WAS CRACKED AT RBL 10. STOP DRILLED CRACK AND HIGH FREQ EDDY CURRENT STOP DRILL PER NDT PART 6. CRACK CONTAINED PER 51-00-03. CRACK REPAIRED PER SRM 53-03, FIG 34.

Part: CLIP — BROKEN (NR 2 PYLON)

DURING OP 16 MAINT CHECK AT STA 944, THE LOWER SIDE OF NUMBER 2 PYLON DOUBLER ANGLE CLIP WAS BROKEN. REPLACED DOUBLER PER SPM 6-70-01.

Part: LONGERON — CRACKED (BS 699)

FOUND LONGERON 6R CRACKED AT BELT RING STA 699. REPAIRED LONGERON PER SRM 53-02, FIG 18. CHECK-C 2-12-99 STL.

Part: LONGERON — CRACKED (BS 718)

USING LOW FREQ EDDY CURRENT, FOUND CRACK INDICATION AT STA 718, LONGERON 4L. CUT OUT AND REPLACED LONGERON SECTION AND INSTALLED SPLICE SECTION PER SRM 53-02, FIG 18. CHECK C 2-12-99 STL.

Part: FRAME — CRACKED (SERVICE DOORWAY)

DURING CHECK-C MAINT, FOUND LOWER AFT CORNER OF SERVICE DOOR FRAME, OUTSIDE SKIN, WITH 1 INCH CRACK FROM FASTENER HOLE EDGE OF FRAME TO HOLE AND COMES OUT OF HOLE SRO207, 4 INCH UP FROM LONGERON 18R. STARTS AT EDGE OF FRAME. REPAIRED CRACK PER ARA 15866.

Part: CONNECTOR — FAILED (HYDRAULIC PUMP)

STL - AFTER REPLACEMENT OF THE AUXILIARY HYDRAULIC PUMP, DURING CHECK-OUT, A FIRE IGNITED AT THE PUMP. FIRE WAS QUICKLY EXTINGUISHED WITH GROUND FIRE BOTTLE. PASSENGERS WERE DEPLANED THROUGH JETWAY. FOUND SHORT IN AUXILIARY PUMP HARNESS CONNECTOR. REPLACED AUXILIARY HYDRAULIC PUMP, PUMP HARNESS, CONNECTOR, AND CIRCUIT BREAKER. CHECK-C 10-23-97 STL. (X)

Part: AIR DISTRIBUTION — ODOR (CABIN)

MKE - FLT 656 - WHILE TAXIING, AFT CABIN SMELLED HOT OIL FUMES. RAN APU WITH BOTH PACKS FOUND NO OIL SMELL OR OIL LEAKS. (M)

Part: LINE — LEAKING (CABIN)

STL - FLT 694 - DURING CRUISE AND APPROACH, AN AIR LEAK WAS HEARD COMING FROM THE PASSENGER OXYGEN BOTTLE RELIEF LINE. REPLACED THE PASSENGER THERMAL OVERBOARD RELIEF LINE. (M)

Part: BULB — FAILED (NLG)

STL - FLT 570 - DURING CLIMB, NOSE GEAR GREEN LIGHT REMAIN ON AFTER GEAR RETRACTION DUE TO FAULTY LIGHT BULB. REMOVED AND REPLACED LIGHT BULB, MFG P/N GE1864, MANUFACTURED BY GENERAL ELECTRIC INC. OPERATIONAL CHECK NORMAL. (M)

Part: POWER SUPPLY — WEAK (CABIN)

STL - FLT 200 - DURING CRUISE, EGRESS LIGHTS FROM SEAT ROW 20 TO AFT STAIR DOOR ILLUMINATED AND WOULD NOT EXTINGUISH. FOUND POWER SUPPLY WEAK, MFG P/N 5822-2. REPLACED POWER SUPPLY AND EGRESS LIGHT OPERATION CHECKED NORMAL. CHECK C-12 - 1-11-95 - STL.

Part: COFFEEMAKER — MALFUNCTIONED (GALLEY)

STL - FLT 247 - AFTER TAKEOFF, GALLEY COFFEEMAKER EMITTED SMOKE AND NOXIOUS FUMES. TURNED OFF GALLEY. FOUND COFFEEMAKER SOLENOID MALFUNCTIONING. REPLACED COFFEEMAKER, MFG P/N 50198A. GALLEY AND COFFEEMAKER OPERATION CHECK NORMAL. CHECK C - 8-21-96 - STL.

Part: FUEL CONTROL — FAILED (RT ENGINE)

ATL - FLT 605 - DURING LANDING TOUCHDOWN LEFT AND RIGHT ENGINES, 2164-L, 2146-R, SPOOLED DOWN. COMPLETED LANDING PROCEDURES. REPLACED LEFT ENGINE FUEL CONTROL, MFG PN 243602-4, AND RIGHT ENGINE FUEL CONTROL, MFG PN 243602-3. ENGINE OPERATION AND PERFORMANCE CHECKED NORMAL. LEFT ENGINE S/N 2164 - TOTAL TIME: 51,272 HOURS, CYCLES, 60,004. RIGHT ENGINE S/N 2146 - TOTAL TIME: 56,299 HOURS, CYCLES, 66,976. CHECK C-5-14-95 - STL. REFERENCE OPERATOR CONTROL NR 96ZZZX223.

Part: FUEL CONTROL — FAILED (LT ENGINE)

ATL - FLT 605 - DURING LANDING TOUCHDOWN LEFT AND RIGHT ENGINES, 2164-L, 2146-R, SPOOLED DOWN. COMPLETED LANDING PROCEDURES. REPLACED LEFT ENGINE FUEL CONTROL, MFG PN 243602-4, AND RIGHT ENGINE FUEL CONTROL, MFG PN 243602-3. ENGINE OPERATION AND PERFORMANCE CHECKED NORMAL. LEFT ENGINE S/N 2164 - TOTAL TIME: 51,272 HOURS, CYCLES, 60,004. RIGHT ENGINE S/N 2146 - TOTAL TIME: 56,299 HOURS, CYCLES, 66,976. CHECK C-5-14-95 - STL. REFERENCE OPERATOR CONTROL NR 96ZZZX224.