N14335

Part: INTERCOSTAL — CRACKED (BS 294 S7L) · airframe 62,476 hrs · 32,014 cycles

BS 294.5 STRINGER 7L INTERCOSTAL WEB CRACKED AT IB FORWARD CORNER. REMOVED AND REPLACED PER ECRA 5310-04700.

Part: LINK — CORRODED (RT MLG) · airframe 62,476 hrs · 32,014 cycles

RT MAIN GEAR STABILIZER LINK HAS CORROSION AT END. REMOVED AND REPLACED RT MAIN GEAR STABILIZER LINK PER MM 57-15-00.

Part: ATTACH ANGLE — CRACKED (BS 350 S15L) · airframe 62,476 hrs · 32,014 cycles

ATTACH ANGLE CRACKED AT STA350 STRINGER 15L AFT SIDE OF L-1 DOOR. REMOVED AND REPLACED ANGLE PER SRM 51-40-02 AND EA 354-53-002 CAL REV 2.

Part: SEAT TRACK — CORRODED · airframe 62,476 hrs · 32,014 cycles

FOUND RBL 18 HAS SIGNS OF SURFACE CORROSION. REMOVED FLOORBOARDS FOR FOM IAW SRM 51-40-02. REMOVED AND REPLACED CORRODED SEAT TRACK SECTION IAW SRM 53-00-52 FIG 201 AND SRM 51-40-02. REINSTALLED FLOORBOARDS IAW SRM 51-40-02 SEALED FLOORBOARDS PER AMM 51-30-00.

Part: KEELBEAM — CORRODED (BS 500D-540) · airframe 55,720 hrs · 28,876 cycles

INSPECTION FOUND KEEL BEAM CORRODED AT STA 500D-540, S28R. THE CORRODED SECTION OF KEEL BEAM WAS CUT OUT AND A NEW SECTION OF KEEL BEAM WAS INSTALLED IAW ECRA 5311-01236.

Part: STRINGER — CORRODED (STA 867-887) · airframe 55,720 hrs · 28,876 cycles

INSPECTION FOUND STRINGER 25R IN THE AFT BAGGAGE BIN CORRODED AT STA 867-887, RBL 27. A SECTION OF STRINGER AND DOUBLERS WAS INSTALLED IAW SRM 53-00-03.

Part: FRAME — CRACKED (STA 616) · airframe 55,720 hrs · 28,876 cycles

INSPECTION FOUND A .5 INCH CRACK IN LT MAIN FRAME BELOW MAIN DECK FLOOR AT STA 616, S18L TO S19L. A FILLER AND ANGLE REPAIR WAS INSTALLED IAW ECRA 5311-01158, PAGE 1-9.

Part: SKIN — CRACKED (FUSELAGE) · airframe 54,803 hrs · 28,433 cycles

A 3 INCH CRACK WAS FOUND IN THE FUSELAGE SKIN DURING WALKAROUND. THE CRACK WAS LOCATED APPROXIMATELY 2.5 FEET FORWARD OF AFT CARGO DOOR AND 2.5 FEET BELOW WATER LINE AND BETWEEN STRINGERS 19R AND 20R (THREE FEET FORWARD OF STA 767). A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-00-01, FIGURE 229.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 52,764 hrs · 27,311 cycles

THE EMERGENCY LIGHTS IN FIRST CLASS CABIN AND AT FORWARD SERVICE ENTRY DOOR WERE FOUND INOPERATIVE. THE BATTERY CHARGER AT STA 338 WAS REPLACED IAW MM 33-51-51.

Part: SKIN — CRACKED (NR2 PYLON STRUT) · airframe 52,201 hrs · 27,027 cycles

INSPECTION FOUND A 0.75 INCH CRACK IN NR 2 PYLON STRUT SKIN AT ACCESS DOOR 5824R CUTOUT, TOP FORWARD CORNER. THE CRACK WAS STOP DRILLED AND A REPAIR DOUBLER AND FILLERS WERE INSTALLED IAW ECRA 5430-01204.

Part: SKIN — DELAMINATED (LT TE FLAP) · airframe 52,201 hrs · 27,027 cycles

INSPECTION FOUND THE NR 1 T/E FOREFLAP DELAMINATED BELOW NR 2 SPOILER PANEL, LT WING. THE FOREFLAP WAS REMOVED AND REPLACED IAW MM 27-51-37.

Part: SKIN — PUNCTURED (SPOILER) · airframe 52,201 hrs · 27,027 cycles

INSPECTION FOUND RT WING NR 6 FLIGHT SPOILER PANEL PUNCTURED IN CENTER SECTION. REPAIRED SPOILER PANEL IAW SRM 57-70-1.

Part: STRAP — CORRODED (FUSELAGE) · airframe 52,201 hrs · 27,027 cycles

INSPECTION FOUND STRAP UNDER BEAM AT C-2 DOOR CUTOUT I/B SILL STRUCTURE CORRODED AT STA 800. THE STRAP WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: STRAP — CORRODED (FUSELAGE) · airframe 52,201 hrs · 27,027 cycles

INSPECTION FOUND STRAP I/B OF C-2 DOOR THRESHOLD CORRODED FROM STA 787 TO 847 IN AFT BAG BIN. REPLACED STRAP IAW SRM 51-40-02.

Part: ATTACH ANGLE — CRACKED (NR 2 PYLON) · airframe 52,201 hrs · 27,027 cycles

INSPECTION FOUND A .5 INCH CRACK IN ATTACH ANGLE I/B OF NR 2 PYLON JUST AFT OF MIDSPAR ATTACH BOLT. REPAIRED ANGLE IAW SRM 51-70-12.

Part: FAN — SEIZED (NR 2 ENGINE) · airframe 51,311 hrs · 26,522 cycles

THE NR 2 ENGINE GAVE OFF A LOUD BANG FOLLOWED BY VIBRATION AND THE ENGINE SPOOLED DOWN TO IDLE. THE ENGINE NEVER DID SHUTDOWN. CREW WAS UNABLE TO GET POWER ABOVE IDLE. THE AIRCRAFT WAS DIVERTED TO CLE WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE ENGINE FAN SEIZED. THE NR 2 ENGINE WAS REMOVED AND REPLACED. THE SDR WILL REMAIN OPEN FOR PART INFORMATION PENDING INVESTIGATION. INVESTIGATION REVEALED THAT THE PRIMARY CAUSE OF ENGINE FAILURE WAS DUE TO FAILURE OF NR 4 BEARING.

Part: SKIN — CRACKED (AFT OF EXH DCT) · airframe 49,708 hrs · 25,642 cycles

INSPECTION FOUND A 1/4" CRACK IN BELLY SKIN AFT OF EXHAUST DUCT. A REPAIR DOUBLER WAS INSTALLED IAW ECRA 5330-02894.

Part: PRESSURE PANEL — CRACKED (FUSELAGE) · airframe 49,708 hrs · 25,642 cycles

INSPECTION FOUND AN 8 INCH CRACK IN LT MAIN WHEEL WELL PRESSURE DECK WEB AT STA 664-675. THE AREA WAS REPAIRED IAW SRM 53-60-51.

Part: OVEN — MALFUNCTIONED (GALLEY) · airframe 49,592 hrs · 25,583 cycles

FLIGHT ATTENDANTS REPORTED SMOKE COMING FROM BEHIND OVENS IN AFT GALLEY WHILE AT CRUISE EN ROUTE TO CLE. ASSOCIATED CIRCUIT BREAKERS WERE PULLED AND THE SMOKE CEASED. THE FLIGHT WAS CONTINUED TO CLE WHERE IT LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE FOUND THE AFT GALLEY CENTER OVEN AT FAULT. THE OVEN WAS REMOVED AND REPLACED. OPERATIONAL CHECKS WERE GOOD.

Part: MEGAPHONE — WEAK (AFT CABIN) · airframe 49,174 hrs · 25,357 cycles

INSPECTION FOUND AFT PORTABLE MEGAPHONE WEAK. THE MEGAPHONE WAS REMOVED AND REPLACED.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 46,686 hrs · 24,060 cycles

FORWARD BAG BIN DOOR INNER SKIN PREVIOUS REPAIR DAMAGED / GOUGED. INSTALLED REPAIR DOUBLER PER EC/RA 5230-01633.

Part: WEB — DENTED (CARGO DOOR) · airframe 46,686 hrs · 24,060 cycles

FORWARD CARGO DOOR INNER SKIN LOWER CENTER DENT AT LIGHTENING HOLE. INSTALLED DOUBLER REPAIR PER EC/RA 5230-1631.

Part: SKIN — CRACKED (INNER DOOR SKIN) · airframe 46,686 hrs · 24,060 cycles

LIGHTING HOLES DAMAGED ABOVE COUNTER BALANCE CABLES AT A/B/B (1" CRACK). INSTALLED REPAIR AS PER EC/RA 5230-01632.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 46,686 hrs · 24,060 cycles

THIRD LIGHTENING HOLE FROM AFT END OF DOOR AND THIRD LIGHTENING HOLE FROM TOP OF DOOR HAS A CRACK. INSTALLED REPAIR PER EC/RA 5230-01630.

Part: DOUBLER — GOUGED (#2 PYLON) · airframe 46,686 hrs · 24,060 cycles

#2 ENGINE PYLON UPPER LEFT SIDE OF PYLON ACCESS PANEL 5827 SUPPORT FOR PANEL HAS DEEP GOUGES. BLENDED AREA. INSTALLED DOUBLER PER EC/RA 5430-01230.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND RT TIE DOWN CHANNEL CORRODED AROUND FASTENERS AT STA 500A-500D IN FORWARD BAGGAGE BIN. THE TIE DOWN CHANNEL WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND A 2 INCH CRACK COMING FROM HI-LOC HOLE IN BOTH THE RT AND LT O/B FLOOR TRACKS AT STA 727B. BOTH FLOOR TRACKS WERE REPAIRED IAW ECRA 5310-04202.

Part: SILL — CORRODED (STA 767-787) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND AFT BAGGAGE BIN FORWARD LOWER SILL CORRODED AT STA 767-787, S26R. THE SILL WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND SKIN DOUBLER TORN IN TWO LOCATIONS AT EXHAUST DUCT ATTACH POINT IN E&E COMPARTMENT BELLY OF AIRCRAFT. THE DOUBLER WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: FLOORBEAM — CORRODED (STA 294) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND FLOORBEAM CORRODED ON UPPER SURFACE AT STA 294, RBL 53. THE FLOORBEAM UPPER SURFACE WAS REPAIRED IAW SRM 53-10-51.

Part: FLOORBEAM — CORRODED (STA 947.5) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND FLOORBEAM UPPER CAP CORRODED AT STA 947.5, LBL 6 TO RBL 6. THE FLOORBEAM UPPER CAP WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: ANGLE — CORRODED (STA 302-306) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND FWD LAV WALL MOUNT L-ANGLES ON HAT SECTION CORRODED AT STA 302, LBL 36-56 AND AT STA 306, LBL12-43. NEW ANGLES WERE INSTALLED IAW SRM 51-40-02.

Part: FITTING — CORRODED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND GALLEY MOUNT FITTINGS ON FLOORBEAM CORRODED AT STA 270-294, RBL 43 AND AT STA 294, RBL 12. THE TWO GALLEY MOUNT FITTINGS WERE REMOVED AND REPLACED IAW SRM 51-40-02.

Part: SEAT TRACK — CORRODED (STA 360-380) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND L/H O/B SEAT TRACK CORRODED AT STA 360-380. THE SEAT TRACK WAS REPLACED IAW SRM 53-00-52.

Part: STIFFENER — CRACKED (#6 FLAP TRK) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND AN 8" CRACK IN STIFFENER LOCATED JUST FORWARD OF HORSE COLLAR IN #6 FLAP TRACK FAIRING. THE STIFFENER WAS REPLACED IAW SRM 51-10-02.

Part: SPLICE — CRACKED (#3 FLAP TRK) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND A 5" CRACK IN #3 FLAP TRACK FAIRING SPLICE. THE #3 FAIRING SPLICE WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: CHANNEL — CORRODED (STA 312-344) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND U-CHANNEL UNDER L-1 DOOR THRESHOLD CORRODED AT STA 312-344. THE CHANNEL WAS REPLACED IAW SRM 51-40-00.

Part: FITTING — CORRODED (STA 344) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND L-1 DOOR GIRT BAR LATCH ATTACH FITTING CORRODED AT STA 344. THE ATTACH FITTING WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: STIFFENER — CRACKED (#3 FLAP TRK) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND A 5" CRACK IN ANGLE STIFFENER INSIDE #3 FLAP TRACK FAIRING. THE ANGLE STIFFENER WAS REMOVED AND REPLACED IAW SRM 51-10-2.

Part: CHANNEL — CORRODED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND FWD LAV WALL HAT SECTION CORRODED AT STA 306, LBL 36-56. THE HAT SECTION WAS REPLACED IAW SRM 51-40-02.

Part: ANGLE — CORRODED (STA 312-344) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND L-1 DOORWAY ANGLE CORRODED AT STA 312-344, LBL 60. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: ANGLE — CORRODED (STA 298-328) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND ANGLE BELOW SCUFF PLATE AREA OF R-1 DOOR JAMB CORRODED AT STA 298-328. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: SKIN — CRACKED (WINDOW POST) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND A 1.125" CRACK AT UPPER R/H CORNER I/B SIDE OF CO-PILOT'S R/H WINDOW POST SKIN AND GUSSET. THE CRACKED AREA WAS ROUTED OUT AND FILLER AND DOUBLER WERE INSTALLED IAW SRM 53-10-1, FIGURE 210.

Part: ANGLE — CRACKED (STA 380-400) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND A 2" CRACK IN INTERCOSTAL UPPER ANGLE AT STA 380-400, BL 0. A NEW ANGLE WAS INSTALLED IAW SRM 51-40-02.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND A 1 INCH CRACK IN FLOOR SUPPORT AT STA 967-986.5, LBL 18. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: STRINGER — CRACKED (STA 338) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND A 6" CRACK IN STRINGER 10R AT STA 338. A NEW STRINGER WAS INSTALLED IAW SRM 51-40-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AROUND FASTENER HOLES AT STA 312-328. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND UPPER SURFACE OF FLOORBEAM CORRODED AT STA 312, LBL 20 - RBL 20. THE FLOORBEAM CHORD WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND A .5 INCH CRACK IN FLOOR SUPPORT AT STA 540 BETWEEN RT I/B AND O/B SEAT TRACKS. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND A .5 INCH CRACK IN FLOOR SUPPORT AT STA 540, LEFT OF BL 0 FLEX JOINT. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: STRINGER — CRACKED (STA 500C-500D) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND A 1/2" CRACK IN STRINGER 16L BETWEEN STA 500C AND 500D. REPAIRED IAW SRM 53-00-03, FIGURE 201, SHEET 6.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND UPPER SURFACE OF FLOOR SUPPORT CORRODED AT STA 294-312, LBL 12. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-40-02 AND 51-10-02.

Part: SPLICE — CRACKED (FUSELAGE) · airframe 46,687 hrs · 24,060 cycles

INSPECTION FOUND A 2 INCH CRACK IN STRINGER SPLICE AT STA 907, S4R. A NEW SPLICE WAS INSTALLED IAW SRM 53-40-3.

Part: BATTERY — DISCHARGED (BS 960)

L2 EXTERIOR EMERGENCY EXIT LIGHT INOP. REPLACED BATERY PACK PER WD 33-51-21.

Part: FLOORBEAM — CORRODED (BS 967)

INSPECTION FOUND FLOORBEAM CLIP NUT HOLES CORRODED AT STA 967L, WL 208. A NEW UPPER T-CAP WAS INSTALLED IAW ECRA 5310-03588.

Part: FLOORBEAM — CORRODED (BS 312)

INSPECTION FOUND FLOORBEAM UPPER CHORD CORRODED AT STA 312. THE FLOORBEAM WAS REMOVED AND REPLACED IAW SRM 51-10-51.

Part: STRINGER — CRACKED (BS 294.5)

INSPECTION FOUND A 1 CRACK IN STRINGER 26L LOCATED JUST OUTBOARD OF LEFT TRUNNION BEARING AT STA 294.5. THE CRACKED AREA WAS REMOVED AND A REPAIR ANGLE WAS INSTALLED IAW ECRA 5310-03590.

Part: FLAP — DELAMINATED (LT TE FOREFLAP)

INSPECTION FOUND UPPER SURFACE OF LT OUTBOARD FOREFLAP DELAMINATED. THE FLAP WAS REMOVED AND REPAIRED IAW ECRA 5750-01450.

Part: BATTERY PACK — DISCHARGED (CABIN)

THE CABIN EMERGENCY LIGHTING ON OVERHEAD BINS AT ROW 3L, 5R, 14R, 16R, 20L, 21R, AND 24L FAILED THE 10 MINUTE DURATION TEST. THE EMERGENCY LIGHT BATTERIES WERE REMOVED AND REPLACED.

Part: SKIN — DENTED (BS 927)

INSPECTION FOUND A DENT IN FUSELAGE SKIN BELOW AND FORWARD OF R-2 DOOR AT LAP JOINT AND BUTT SPLICE, BS 927, STRINGER 21R. THE SKIN WAS REPAIRED IAW SRM 53-00-01, FIGURE 210.

Part: FLAP — DELAMINATED (RT TE FLAP)

INSPECTION FOUND DELAMINATION ON AFT INBOARD EDGE OF RT OUTBOARD AFT FLAP. THE FLAP WAS REMOVED AND REPAIRED IAW ECRA 5750-02787.

Part: FLOORBEAM — CORRODED (BS 986.5)

INSPECTION FOUND FLOORBEAM CORRODED AT STA 986.5 LEFT TO RIGHT. THE CORRODED SECTION WAS REMOVED AND A NEW SECTION OF FLOORBEAM WAS FABRICATED AND INSTALLED IAW ECRA 5310-03450.

Part: FLOORBEAM — CORRODED (BS 312/344)

INSPECTION FOUND FLOORBEAM CORRODED STA 312 AND 344. THE CORRODED AREAS OF FLOORBEAM WERE CUT OUT. FLOORBEAM SECTIONS AND REPAIR ANGLES WERE FABRICATED AND INSTALLED IAW SRM 53-10-51.

Part: SKIN — SCRATCHED (BS 374-390)

INSPECTION FOUND A SCRATCH IN FUSELAGE SKIN AT STA 374-390, S14L TO S15L. THE SCRATCH WAS CUT OUT IAW SRM 53-00-01, FIGURE 201. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-00-01.

Part: SKIN — DENTED (BS 380)

INSPECTION FOUND FUSELAGE SKIN DENTED AT STA 380 BELOW S23L. A REPAIR WAS INSTALLED IAW SRM 53-00-01.

Part: TRANSMISSION — FAILED (NR 8 TE FLAP)

THE FLAPS WOULD NOT EXTEND USING NORMAL SYSTEMS ON APPROACH. WHEN THE ALTERNATE FLAP SYSTEM WAS USED, THE LEADING EDGE DEVICES EXTENDED, BUT THE FLAPS SHOWED .5 DEGREE AND THEN FROZE. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 8 FLAP TRANSMISSION AT FAULT. THE FLAP TRANSMISSION WAS REMOVED AND REPLACED, OPERATIONAL CHECK OF FLAPS WAS GOOD.

Part: CONNECTOR — CORRODED (NR 1 ENGINE)

DFW - FLT 0624 - THE NR 1 ENGINE OVERHEAT ANNUNCIATOR LIGHT ILLUMINATED IN CRUISE FLIGHT, BUT EXTINGUISHED AFTER 10 SECONDS. WHEN LIGHT CAME ON 2ND TIME, CREW DISENGAGED AUTOTHROTTLES AND SPLIT THROTTLE 74 PERCENT N1 AND 92 PERCENT N2. LIGHT CONTINUED TO GO OFF AND ON INTERMITTENTLY. NR 1 ENG WAS SHUT DOWN AND ACFT DIVERTED TO DFW WHERE IT LANDED WITHOUT INCIDENT. MX FND NR 1 ENGINE CORE FIRE LOOP CONNECTORS CORRODED. WIRE SIDE OF BOTH A AND B CONNECTORS CLEANED. UPPER AND LOWER LOOPS TESTED NORMAL. IN ADDITION, AFT CORE FIRE DETECTION LOOP A AND B WAS REMOVED ADN REPLACED. OPERATIONAL AND FUNCTIONAL CHECKS WERE GOOD. (X)

Part: FIRE DET MODULE — INOPERATIVE (E/E COMPT)

FLT NR 0118 - IAH - THE APU FIRE WARNING LIGHT ILLUMINATED WHILE CRANKING APU ON SHORT FINAL. THE APU FIRE WARNING HANDLE WAS PULLED, BUT THE LIGHT REMAINED ON. THE APU FIRE BOTTLE WAS DISCHARGED AND THE LIGHT EXTINGUISHED. THE APU AND REAR OF AIRCRAFT WERE INSPECTED WITH NO EVIDENCE OF FIRE FOUND. THE APU WAS RUN AND NO DISCREPANCIES WERE OBSERVED. THE FIRE DETECTION CONTROL MODULE FAILED SYSTEM TEST PER MM 26-15-00. THE FIRE DETECTION MODULE WAS REMOVED AND REPLACED. THE MODULE TESTED GOOD AND THE APU WAS RUN WITHOUT FAULT. IN ADDITION, THE APU FIRE BOTTLE WAS REMOVED AND REPLACED. (M)

Part: SKIN — CRACKED (NR 1 ENG PYLON)

HOU - INSPECTION FOUND A 1 INCH CRACK IN OUTER SKIN AT INBOARD SIDE OF PYLON OF NR 1 ENGINE PYLON ACCESS CUT OUT. A REPAIR WAS INSTALLED IAW ECRA 5430-01204. (X)

Part: SHEAR TIE — BROKEN (BS 460)

HOU - THE SKIN SHEAR TIE AT STA 460 BETWEEN S27R AND S28R WAS FOUND BROKEN DUE TO GROUND DAMAGE. A REPAIR WAS ACCOMPLISHED PER SRM 53-00-07, FIGURE 205, SHEET 2. (X)

Part: SKIN — CRACKED (RT WING LE)

HOU - INSPECTION FOUND A .5625 INCH CRACK IN RT WING LOWER LEADING EDGE SKIN AT PYLON OUTBOARD MID-SPAR FITTING. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-70-13. (X)