N32725

Part: BATTERIES — DISCHARGED (R-1 DOOR)

THE R-1 DOOR INTERIOR OVERHEAD LIGHT WOULD NOT TEST. THE BATTERIES WERE REPLACED IAW MM 33-50-101 AND OPERATION CHECKED GOOD.

Part: CABLES — OUT OF ADJUST (NLG DOORS)

A LOUD EXTERNAL RUMBLE WAS HEARD ACCOMPANIED BY FLASHING GEAR WARNING LIGHTS WHILE CRUISING AT FL 290. THE AIRCRAFT WAS DIVERTED TO BWI WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NOSE GEAR DOORS OUT OF RIG. THE NOSE GEAR DOORS WERE ADJUSTED IAW MM 32-22-1.

Part: BEAM — CRACKED (LT WING)

INSPECTION FOUND A .5 INCH CRACK IN J BEAM AT CUTOUT AREA ABOVE NR 7 SPOILER. THE J BEAM WAS REPAIRED IAW ECRA 5780-02914.

Part: SKIN — DEBONDED (LT TE FOREFLAP)

INSPECTION FOUND LT INBOARD FOREFLAP DEBONDED ON LOWER SURFACE ABOVE NR 4 CARRIAGE. THE FOREFLAP WAS REMOVED AND REPLACED IAW MM 27-51-2.

Part: SKIN — CORRODED (BS 1166)

INSPECTION FOUND FUSELAGE SKIN CORRODED AT LT SIDE, STA 1166, TWO INCHES ABOVE TOP OF FLOORBEAM. THE CORRODED AREA WAS CUT OUT, A DOUBLER WAS INSTALLED IAW ECRA 5330-02699.

Part: BOTTLE PIN — CORRODED (RT WING BODY)

INSPECTION FOUND RT AFT BOTTLE PIN CORRODED. THE BOTTLE PIN AND FORWARD AND AFT BUSHINGS WERE REMOVED AND REPLACED, THEN SAFETIED AND SEALED IAW MM 57-41-1.

Part: ANGLE — CRACKED (LT WING)

INSPECTION FOUND LT WING INBOARD NR 7 SPOILER ACTUATOR SUPPORT FITTING LOWER ANGLES (TWO EACH) RIB PANEL SUPPORTS CRACKED. THE CRACKS WERE .5 INCH LONG. THE INBOARD AND OUTBOARD ANGLES WERE REMOVED AND NEW ANGLES WERE INSTALLED IAW SRM 51-10-1 AND 51-30-2.

Part: FITTING — CORRODED (HORIZ STAB)

INSPECTION FOUND LT AND RT HORIZONTAL STABILIZER ATTACH FITTING CORRODED. THE CORROSION WAS REMOVED BY BORING HOLES. NEW BUSHINGS AND BEARINGS WERE INSTALLED. THE BEARINGS WERE TORQUED AND SAFETIED IAW ECRA 5550-01033.

Part: RIB — CRACKED (RT AILERON)

INSPECTION FOUND A .5 INCH CRACK IN RT OUTBOARD AILERON LEADING EDGE RIB JUST OUTBOARD OF NR 3 HINGE. THE RIB WAS REMOVED AND REPLACED IAW SRM 51-10-1, PAGE 4.

Part: STIFFENER — CRACKED (BS 950)

INSPECTION FOUND A .5 INCH CRACK IN AFT CARGO STIFFENER AT STA 950A, LONGERON 29R. THE STIFFENER WAS REMOVED AND A NEW STIFFENER WAS INSTALLED IAW SRM 51-30-2, 51-10-1, 51-10-2.

Part: SKIN — DELAMINATED (RT ELEV TAB)

INSPECTION FOUND RT ELEVATOR CONTROL TAB INBOARD TRAILING EDGE DELAMINATED. THE ELEVATOR CONTROL TAB WAS REMOVED AND REPLACED IAW MM 27-30-11.

Part: CHANNEL — CRACKED (WING)

INSPECTION FOUND A 1.25 INCH CRACK IN CHANNEL INSIDE TRAILING EDGE AT UPPER SKIN OUTBOARD END OF AFT FALSE SPAR ABOVE NR 3 FLAP TRANSMISSION. A NEW CHANNEL WAS INSTALLED IAW SRM 51-30-2.

Part: BULKHEAD BEAM — CRACKED (BS 1183)

INSPECTION FOUND TWO 1.5 CRACKS IN AFT BULKHEAD VERTICAL SUPPORT BEAM AT AFT CARGO COMPARTMENT, BS 1183, RBL 46.93. THE CRACKS WERE STOP DRILLED IAW SRM 51-10-1. A REPAIR WAS INSTALLED IAW ECRA 5310-03758.

Part: BRACKET — CRACKED (LT TE FLAP ACT)

INSPECTION FOUND A .375 INCH CRACK IN SUPPORT BRACKET FOR LT WING NR 1 LEADING EDGE FLAP ACTUATOR. A NEW BRACKET WAS INSTALLED IAW SRM 51-10-1 AND 51-30-2.

Part: BOLT — CORRODED (NR 5 FLAP TRACK)

INSPECTION FOUND RT WING FLAP TRACK NR 5 CORRODED AT FORWARD ATTACH BOLT. THE NR 5 FLAP TRACK AND ATTACH BOLT WERE REMOVED AND REPLACED IAW MM 57-50-0.

Part: BRACKET — CRACKED (NR 2 LE SLAT ACT)

INSPECTION FOUND A .5 INCH CRACK IN SUPPORT BRACKET FOR LT WING NR 2 LEADING EDGE FLAP ACTUATOR. A NEW BRACKET WAS INSTALLED IAW SRM 51-30-2.

Part: SKIN — CRACKED (FUSELAGE)

INSPECTION FOUND A .25 INCH CRACK IN FUSELAGE SKIN JUST FORWARD OF CAPTAIN'S WINDSHIELD WIPER AREA. THE CRACKED AREA WAS CUT OUT IAW SRM 51-10-1. A DOUBLER, TRIPLER, AND FILLER WERE INSTALLED IAW SRM 51-30-2, 51-20-4, AND ECRA 5330-02698.

Part: SKIN — DEBONDED (LT AILERON TAB)

INSPECTION FOUND LT OUTBOARD AILERON TAB TRAILING EDGE DEBONDED 41.5 INCHES FROM INBOARD END. THE OUTBOARD AILERON TAB WAS REMOVED AND REPLACED IAW MM 27-10-41.

Part: SKIN — TORN (LT WING)

INSPECTION FOUND LEFT WING UPPER TRAILING EDGE SKIN TORN AT ALL THREE HINGES OF NR 6 SPOILER. THE TORN AREAS WERE CUT OUT IAW SRM 57-30-4. A DOUBLER WAS INSTALLED AT EACH OF THE THREE HINGES IAW SRM 57-30-4, FIGURE 10, SHEET 3.

Part: SKIN — DELAMINATED (RT TE AFT FLAP)

INSPECTION FOUND RT WING INBOARD AFT FLAP LOWER SURFACE DELAMINATED AT MID OUTBOARD AREA. THE AFT FLAP WAS REMOVED AND REPLACED IAW MM 27-51-10.

Part: RIB — CRACKED (NR 5 LE SLAT)

INSPECTION FOUND A 1 INCH CRACK IN NR 5 SLAT ACTUATOR INBOARD ATTACH RIB. THE CRACK WAS STOP DRILLED, A REPAIR WAS INSTALLED IAW SRM 51-30-2 AND 51-10-1.

Part: BEAM — CRACKED (RT WING)

INSPECTION FOUND A .75 INCH CRACK IN RT WING TRAILING EDGE J BEAM JUST ABOVE NR 8 SPOILER MOUNT. REPAIR PARTS WERE INSTALLED IAW ECRA 5720-01676.

Part: SKIN — DELAMINATED (LT AILERON)

INSPECTION FOUND AREAS OF DELAMINATED SKIN ON TOP AND BOTTOM OF LT WING OUTBOARD AILERON OUTBOARD TRAILING EDGE WEDGE PANEL. THE WEDGE PANEL WAS REMOVED AND REPAIRED IAW SRM 57-50-5. THE PANEL WAS REINSTALLED IAW SRM 51-10-1.

Part: SKIN — DEBONDED (NR 6 SPOILER)

INSPECTION FOUND THE LT WING NR 6 SPOILER LOWER SKIN DEBONDED AT FORWARD END. THE NR 6 SPOILER WAS REMOVED AND REPLACED IAW MM 57-00 AND 27-60-1.

Part: SKIN — CRACKED (NR 6 LE SLAT)

INSPECTION FOUND A .5 INCH CRACK IN RT WING NR 6 SLAT AT OUTBOARD HOOK. A REPAIR WAS ACCOMPLISHED IAW SRM 57-50-3, FIGURE 10.

Part: SKIN — DEBONDED (NR 4 SPOILER)

INSPECTION FOUND LT WING NR 4 SPOILER DEBONDED AT LOWER SKIN. THE NR 4 SPOILER WAS REMOVED AND REPLACED IAW MM 27-61-1.

Part: SKIN — CRACKED (LT TE FOREFLAP)

INSPECTION FOUND A .875 INCH AND .25 INCH CRACK IN LT OUTBOARD FOREFLAP LEADING EDGE CUTOUT ABOVE NR 1 FLAP TRACK. THE FLAP WAS REPAIRED IAW SRM 57-50-4, FIGURE 1.

Part: SIDEWALL — CRACKED (NLG WW)

INSPECTION FOUND A .125 INCH CRACK IN LEFT SIDEWALL OF NLG WHEEL WELL. THE CRACKED AREA WAS CUT OUT IAW SRM 51-20-1. DOUBLER AND FITTINGS WERE INSTALLED IAW ECRA 5310-03759.

Part: BOLTS — CORRODED (VERT STAB)

INSPECTION FOUND FOUR VERTICAL STABILIZER TENSION TIE BOLTS CORRODED AT TOP OF STABILIZER. THE FOUR BOLTS WERE REMOVED AND REPLACED IAW SRM 55-20-00.

Part: WEB — CORRODED (BS 1148-1183)

INSPECTION FOUND CORROSION ON TOP OF AFT CABIN FLOOR SUPPORT WEB AT BS 1148 TO 1183, RBL 25 TO LBL 25. THE CORRODED AREA WAS CUT OUT IAW SRM 51-40-2. A DOUBLER WAS INSTALLED IAW SRM 51-40-2, FIGURE 1.

Part: SKIN — CORRODED (CARGO DOORWAY)

INSPECTION FOUND FORWARD LOWER C-3 DOOR CUTOUT CORRODED IN AFT CARGO COMPARTMENT BETWEEN LONGERON 25R AND 26R. THE CORRODED AREA WAS REMOVED IAW SRM 51-30-2. A DOUBLER WAS INSTALLED IAW SRM 53-10-1, PAGE 5, FIGURE 1.

Part: BRACKET — CRACKED (BS 910)

INSPECTION FOUND A .0781 INCH CRACK AT UPPER FORWARD LEG OF LT GEAR UPLOCK SUPPORT BRACKET WHERE IT MOUNTS TO FUSELAGE BS 910 BETWEEN STRINGER 18A LEFT AND 18L. THE BRACKET WAS REMOVED AND REPLACED IAW SRM 51-10-1, PAGE 4.

Part: SUPPORT — CORRODED (LAVATORY)

INSPECTION FOUND LT AFT LAV AISLE SIDEWALL FLOOR SUPPORT CORRODED. THE FLOOR SUPPORT WAS REMOVED IAW SRM 51-10-1. A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-10-1, PAGE 4.

Part: STRINGER — CRACKED (VERT STAB)

INSPECTION FOUND A .5 INCH CRACK AT ATTACH BOLT IN STRINGER 9R AT VERTICAL STABILIZER INNER COMPARTMENT NR 9 RIB. THE CRACKED AREA WAS REMOVED IAW SRM 55-30-4. A REPAIR WAS INSTALLED IAW SRM 55-20-4, FIGURE 1, SHEET 5, AND SRM 51-10-2.

Part: WEB — CORRODED (BS 1130)

INSPECTION FOUND LT LAV FLOOR WEB CORRODED AT STA 1130, LBL 27. THE CORRODED AREA WAS CUT OUT IAW SRM 51-40-2. A DOUBLER WAS INSTALLED IAW SRM 51-40-2, FIGURE 1, SHEET 6.

Part: SKIN — CRACKED (BS 680)

INSPECTION FOUND A 2 INCH CRACK IN LT FUSELAGE SKIN BETWEEN WINDOWS NR 16 AND NR 17 AT STA 680. THE CRACKED AREA WAS REPAIRED IAW SRM 51-40-00, 51-10-6, AND 51-10-2.

Part: PLATE — CRACKED (VERT STAB)

INSPECTION FOUND A 4 INCH CRACK IN VERTICAL STABILIZER INNER COMPARTMENT NR 1 RIB LOWER LT CORNER PLATE JUST AFT OF S-DUCT. THE RIVETS WERE REMOVED IAW SRM 51-30-2. A DOUBLER WAS INSTALLED IAW SRM 51-30-2.

Part: FITTING — CRACKED (RT TE MIDFLAP)

INSPECTION FOUND A 0.6 CRACK IN FITTING AT RT INBOARD MIDFLAP RIB LEADING EDGE JUST OUTBOARD OF NR 5 CARRIAGE. THE FITTING WAS REMOVED AND REPLACED IAW SRM 51-10-1, PAGE 4. FASTENERS WERE INSTALLED IAW SRM 51-30-2.

Part: STIFFENER — CRACKED (BS 950)

INSPECTION FOUND A 0.3 INCH CRACK IN AFT CARGO COMPARTMENT STIFFENER AT STA 950A, LONGERON 30R. THE STIFFENER WAS REMOVED AND REPLACED IAW SRM 51-30-2 AND 51-40-4.

Part: WEB — CRACKED (WS 171.5)

INSPECTION FOUND A .5 INCH CRACK IN WEB PANEL NEXT TO BOOST PUMP INSIDE NR 2 FUEL TANK AT LT WS 171.50. THE WEB PANEL WAS REPAIRED IAW SRM 51-40-2, FIGURE 1.

Part: STRINGER — CRACKED (VERT STAB)

INSPECTION FOUND A .5 INCH CRACK AT ATTACH BOLT IN NR 7 STRINGER OF RT VERTICAL STABILIZER INNER COMPARTMENT AT NR 4 RIB. THE CRACKED SECTION WAS REMOVED. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 55-30-4.

Part: CIRCUMFERENTIAL — CORRODED (BS 219)

INSPECTION FOUND CORROSION ON FORWARD AND AFT FACE OF CIRCUMFERENTIAL AT LOWER FORWARD NOSE COMPARTMENT, BS 219 BETWEEN STRINGER 24R AND 26R. THE CORRODED AREA WAS CUT OUT IAW SRM 51-40-2. A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-2, 51-10-2, AND 51-30-2.

Part: SEAT TRACK — CORRODED (BS 380-420)

INSPECTION FOUND SEAT TRACK CORRODED AT BS 380-420, RBL 24. THE SEAT TRACK WAS REMOVED AND A NEW TRACK WAS FABRICATED AND INSTALLED IAW SRM 53-10-5 AND 51-10-5.

Part: BRACKET — CRACKED (C2 DOOR)

INSPECTION FOUND A 1 INCH CRACK AT LOWER AFT END OF AFT CARGO C-2 DOOR FRAME SIDE BRACKET. THE DOOR FRAME BRACKET WAS REMOVED AND REPLACED IAW SRM 51-30-2.

Part: SKIN — CRACKED (LT TE MIDFLAP)

INSPECTION FOUND A .5 INCH CRACK IN LT INBOARD MIDFLAP LOWER TRAILING EDGE SKIN, 32 INCHES FROM INBOARD END. THE CRACK WAS STOP DRILLED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-6 AND 51-10-1.

Part: SKIN — CRACKED (LT TE FLAP)

INSPECTION FOUND A .5 INCH CRACK IN LT INBOARD FLAP AFT SEGMENT LEADING EDGE SKIN, 64 INCHES FROM OUTBOARD END. THE CRACKED AREA WAS REMOVED. A REPAIR ANGLE AND STRAP WERE FABRICATED AND INSTALLED IAW SRM 51-40-2 AND 51-10-6.

Part: SPAR WEB — CRACKED (RT WING)

INSPECTION FOUND A .25 INCH CRACK IN SECOND FROM AFT VERTICAL WEB AT RT WING FRONT SPAR CHORD INBOARD AREA JUST FORWARD OF BOTTLE PIN. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-3 AND 51-10-2.

Part: SKIN — CRACKED (RT TE MIDFLAP)

INSPECTION FOUND A .75 INCH CRACK IN RT WING INBOARD MIDFLAP LOWER CUTOUT FOR INBOARD ACTUATING ROD. THE CRACK WAS STOP DRILLED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-2.

Part: ANGLE — CORRODED (RT LAVATORY)

INSPECTION FOUND RT AFT LAV FLOOR ANGLE CORRODED OUTBOARD OF DUMP CHUTE AREA. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-10-6, 51-10-1, 51-30-2, AND 51-10-2.

Part: FLOOR — CORRODED (BS 1129-1176)

INSPECTION FOUND RT AFT LAV FIXED FLOOR CORRODED INCLUDING AROUND DUMP CHUTE AT BS 1129-1176, RBL 25-63. THE CORROSION WAS REMOVED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-30-2, 51-10-2, 51-40-5, AND 51-10-6.

Part: ANGLE — CRACKED (WS 150)

INSPECTION FOUND A .5 INCH CRACK IN FORWARD ANGLE AT RT WING LEADING EDGE FLAP WELL LOWER STIFFENER, FS 150. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-2.

Part: ANGLE — CRACKED (LT WING)

INSPECTION FOUND A .15625 CRACK IN SUPPORT ANGLE FOR LT WING TRAILING EDGE PANEL FORWARD OF OUTBOARD AILERON, OUTBOARD OF AILERON LOCKOUT. THE CRACKED AREA WAS ROUTED OUT. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 57-40-1 AND 51-10-2.

Part: ANGLE — CRACKED (BS 970-990)

INSPECTION FOUND A .5 INCH CRACK IN INTERCOSTAL WEB TOP ANGLE AT FORWARD SCREW HOLE BETWEEN FLOORBEAMS AT BS 970-990, BL 0. THE TOP ANGLE WAS REMOVED. A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-10-6 AND 51-40-3.

Part: HAT CHANNEL — CORRODED (BS 320)

INSPECTION FOUND FLOOR SUPPORT HAT CHANNEL CORRODED AT FORWARD LAV AREA, BS 320, RBL 15. THE HAT CHANNEL WAS REMOVED AND A NEW SECTION WAS FABRICATED AND INSTALLED IAW SRM 51-10-2 AND 51-40-4.

Part: CLIP — CRACKED (BS 1183)

INSPECTION FOUND A 1 INCH CRACK IN TIE CLIP IN AFT CARGO COMPARTMENT AT STA 1183, 36 INCHES BELOW LBL 9 BULKHEAD FITTING. THE TIE CLIP WAS REMOVED, A NEW TIE CLIP WAS FABRICATED AND INSTALLED IAW SRM 51-10-1.

Part: FLOORBEAM — CORRODED (BS 344)

INSPECTION FOUND CORROSION ON TOP OF FLOORBEAM AT BS 344, LBL 41-53. THE CORRODED AREA WAS CUT OUT. NEW PARTS WERE FABRICATED AND INSTALLED IAW SRM 53-10-8 AND 51-10-2.

Part: WEB — CORRODED (BS 1175)

INSPECTION FOUND FLOOR WEB CORRODED AT BS 1175, RBL 65, OUTBOARD OF RT AFT LAV DUMP CHUTE FLANGE. THE CORRODED AREA WAS CUT OUT. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-6 AND 51-30-2.

Part: ANGLE — CORRODED (BS 1129-1176)

INSPECTION FOUND ANGLE AT LT AFT LAV FIXED FLOOR CORRODED AT BS 1129 TO 1176, RBL 25 TO 63. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-30-2.

Part: ANGLE — CORRODED (BS 1130-1148)

INSPECTION FOUND FLOOR PANEL SUPPORT ANGLE CORRODED AT BS 1130-1148, RBL 12. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-40-4, 51-10-2, AND 51-40-5.

Part: SIDEWALL — CRACKED (NLG WW)

INSPECTION FOUND A 0.3 CRACK IN TOP LT PANEL OF NLG WHEEL WELL. THE AREA WAS REPAIRED IAW SRM 51-40-2.

Part: SIDEWALL — CRACKED (NLG WW)

INSPECTION FOUND A .5 INCH CRACK IN RT SIDEWALL OF NLG WHEEL WELL. THE CRACKED AREA WAS CUT OUT, A DOUBLER AND FITTING WERE FABRICATED AND INSTALLED IAW SRM 53-10-1.

Part: SEAT TRACK — CORRODED (BS 1030-1120)

INSPECTION FOUND CORROSION AT INBOARD AND OUTBOARD LEGS OF SEAT TRACK AT BS 1030-1120, LBL 45. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-2.

Part: PANEL — CRACKED (NLG WW)

INSPECTION FOUND THREE .5 INCH CRACKS IN TOP CENTER PANEL OF NLG WHEEL WELL. THE AREA WAS REPAIRED IAW SRM 51-40-2.

Part: SEAT TRACK — CORRODED (BS 380-420)

INSPECTION FOUND SEAT TRACK CORRODED AT INBOARD AND OUTBOARD LEGS AND ALONG TOP AT BS 380 TO 420, RBL 45. THE SEAT TRACK WAS REMOVED AND A NEW ONE WAS FABRICATED AND INSTALLED IAW SRM 53-10-5.

Part: SEQUENCE VALVE — LEAKING (RT MLG)

THE A HYDRAULIC SYSTEM PRESSURE AND FLUID WAS LOST AFTER GEAR WAS RETRACTED DEPARTING IAH. FUEL WAS DUMPED AND THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE RT MLG LOCK SEQUENCE VALVE LEAKING. THE VALVE WAS REMOVED AND REPLACED IAW MM 32-32-31. LEAK AND OPERATIONAL CHECKS WERE GOOD IAW MM 32-32-0.

Part: TURBINE — FAILED (NR 3 ENGINE)

THE NR 3 ENGINE OIL PRESSURE WENT TO ZERO ACCOMPANIED BY ILLUMINATION OF THE LOW OIL PRESSURE LIGHT WHILE EN ROUTE FROM RSW TO EWR. THE NR 3 ENGINE WAS SHUT DOWN AND THE AIRCRAFT WAS DIVERTED TO MCO WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED THE NR 3 ENGINE. EXAMINATION REVEALED TURBINE FAILURE ATTRIBUTED TO FUEL NOZZLE STREAKING. THE ENGINE EXITED THE FLEET WITHOUT A TEARDOWN.

Part: CONTROL MODULE — LEAKING (AILERON)

THE A-SYSTEM HYDRAULIC OVERHEAT LIGHT ILLUMINATED AFTER TAKEOFF WHILE CLIMBING THROUGH 6000 FEET. A MINUTE LATER, THE A-HYDRAULIC SYSTEM QUANTITY WENT TO ZERO. THE HYDRAULIC FAILURE CHECKLIST WAS PERFORMED, FUEL WAS DUMPED, AND THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND AILERON CONTROL MODULE LEAKING. THE AILERON CONTROL MODULE WAS REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED. LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: SWITCH — MALFUNCTIONED (NLG DOOR)

THE AIRCRAFT HAD A BRIEF HISTORY OF THE NOSE GEAR DOOR LIGHT ILLUMINATING AT BOTH THE FORWARD PANEL AND SECOND OFFICER'S PANEL WHILE IN FLIGHT. BOTH NOSE GEAR DOOR UP SWITCHES WERE REMOVED AND REPLACED IAW MM 32-62-11. IN ADDITION, BOTH NOSE GEAR DOOR CABLES WERE ADJUSTED IAW MM 32-22-01. OPERATION AND INDICATIONS CHECKED GOOD.

Part: ANGLE — CORRODED (NLG WW)

CORROSION ON CHORD ANGLE AT RIGHT SIDE OF NOSE WHEEL WELL BELOW HORIZONTAL BEAM AREA. REMOVED AND REPLACED CHORD ANGLE PER SRM 51-30-2.

Part: WEB — CRACKED (RT MLG WW)

CRACK IN VERTICAL WEB AT FWD END OF APU CUTOUT IN RIGHT MLG WHEEL WELL STA 870. CUTOUT CRACKED AREA. FABRICATED AND INSTALLED REPAIR PER EC/RA 5310-03586.

Part: SKIN — DISBONDED (LT TE FOREFLAP)

LEFT WING INBOARD FORE FLAP HAS SMALL DISBOND AREA AND DINGS INBOARD LOWER SURFACE. REMOVED REPAIRED AND REINSTALLED FOREFLAP PER SRM 51-40-6.

Part: ANGLE — CRACKED (BS 870)

CRACK ON APU AFT LEFT CIRCUM WEB AT STA 870, 3:30 O'CLOCK. REMOVED AND REPLACED CRACKED ANGLE PER SRM 51-30-2.

Part: WEB — CRACKED (LT MLG WW)

CRACK IN VERTICAL WEB AT FORWARD END OF APU CUT OUT IN LEFT MLG WHEEL WELL STA 870. CUTOUT CRACKED AREA. FABRICATED AND INSTALLED REPAIR PER ECRA 5310-03587.

Part: DOUBLER — CRACKED (LT TE MIDFLAP)

LEFT WING INBOARD MID FLAP UPPER SKIN DOUBLER CRACKED AT UPPER ACCESS CUT OUT AT INBOARD CARRAIGE SPINDLE. REMOVED AND REPLACED DOUBLER PER SRM 51-10-2 AND 51-30-2.

Part: SKIN — BISBOND (LT TE FOREFLAP)

LEFT TRAILING EDGE OUTBOARD FORE FLAP UPPER SURFACE APPROX 5 FOOT FROM INBOARD EDGE HAS DISBOND. HOT BOND REPAIR ACCOMPLISHED PER SRM 51-40-6.

Part: SKIN — DISBONDED (RT TE FLAP)

RIGHT TRAILING INBOARD FLAP UPPER SURFACE CENTER HAS DISBOND. CUT OUT DISBOND AREA. FABRICATED FILLER AND DOUBLER. HOT BOND REPAIR PER SRM 51-40-6.

Part: SKIN — DISBONDED (RT TE FLAP)

RIGHT WING INBOARD FLAP OUTBOARD UPPER TRAILING EDGE HAS AREA OF DISBOND. CUT OUT DEBONDED AREA. FABRICATED FILLER AND DOUBLER. PERFORMED HOT BOND REPAIR PER SRM 51-40-6.

Part: SKIN — CRACKED (RT TE FOREFLAP)

APPROX 3 CRACK AT RIGHT WING OUTBOARD FORE FLAP LEADING EDGE ABOVE NR 8 TRACK AREA. HOT BOND DOUBLER REPAIR ACCOMPLISHED PER SRM 51-40-6

Part: SKIN — CORRODED (BS 680)

FUSELAGE LOWER SKIN AT APPROX STATION 680 AND RT STR 27 AREA BULGED. CUT OUT CORRODED SKIN. FABRICATED AND INSTALLED REPAIR PER SRM 53-10-3.

Part: SKIN — CRACKED (LT WING)

LEFT WING LEADING EDGE AT NR 3 SLAT OUTBOARD HOOK SEAL CUTOUT CRACK IN AFT OUTBOARD CORNER. STOP DRILLED CRACK. FABRICATED AND INSTALLED DOUBLER PER SRM 57-30-4.

Part: BRACKET — CRACKED (NR 5 LE FLAP ACT)

RIGHT WING NR 5 LEADING EDGE FLAP ACTUATOR MOUNT CRACKED AT OUTBOARD UPPER CORNER AREA. FABRICATED AND INSTALLED REPLACEMENT MOUNT BRACKETS PER SRM 51-10-1 AND 51-40-4.

Part: SKIN — DISBONDED (RT TE MIDFLAP)

RIGHT OUTBOARD MID FLAP UPPER TRAILING EDGE HAS DISBOND AREA 73 FROM OUTBOARD END. CUT OUT DELAMINATED AREA AND ACCOMPLISHED HOT BOND REPAIR PER SRM 51-40-6.

Part: AILERON — DISBONDED (RT WING)

RIGHT OUTBOARD AILERON OUTBOARD TRAILING EDGE SECTION INBOARD UPPER SURFACE DISBONDED. REMOVED DAMAGED AREA. FABRICATED NEW CORE AND SKIN. ACCOMPLISHED HOT BOND REPAIR PER SRM 51-40-6.

Part: SKIN — CRACKED (LT WING)

LEFT WING OUTBOARD CUTOUT FOR NR 4 SPOILER. TWO CRACKS IN WING SKIN. STOP DRILLED CRACKS. FABRICATED AND INSTALLED DOUBLERS PER SRM 51-30-04.

Part: LIGHT — INOPERATIVE (CABIN)

AFT ENTRY LIGHT PACK IS INOP. REMOVED AND REPLACED LIGHT PACK.

Part: SKIN — CRACKED (NR 6 LE FLAP)

TWO SMALL CRACKS AT RIGHT WING NR 6 SLAT AT UPPER TRAILING EDGE SKIN FROM AFT SCREW HOLE WHER INBOARD HOOK MOUNTS. FABRICATED AND INSTALLED DOUBLER PER SRM 57-50-3.

Part: BRACKET — CRACKED (NR 6 LE FLAP ACT)

RIGHT WING NR 6 LEADING EDGE FLAP ACTUATOR MOUNT CRACKED AT INBOARD AND OUTBOARD BRACKET AREAS. FABRICATED AND INSTALLED MOUNT BRACKETS PER SRM 51-10-1 AND 51-40-4.

Part: SUPPORT — CRACKED (NR 4 LE FLAP ACT)

LEFT WING NR 4 LEADING EDGE SLAT ACTUATOR ROD END SUPPORT WEB CRACKED AT FORWARD EDGE. STOP DRILLED CRACK. FABRICATED AND INSTALLED DOUBLER PER SRM 51-40-2.

Part: SKIN — CRACKED (LT WING)

LEFT WING LEADING EDGE CUTOUT FOR NR 3 SLAT INBOARD TRACK CRACK AT TOP EDGE. STOP DRILLED CRACK. FABRICATED AND INSTALLED DOUBLER PER SRM 57-30-4.

Part: ANGLE — CRACKED (RT WING)

ANGLE CRACKED THROUGH 7 FASTENERS INSIDE AT BOTOM OF RIGHT WING LEADING EDGE RIB AT WBL 92.0 INBOARD AND AFT OF NR 4 LEADING EDGE FLAP AREA. FABRICATED AND INSTALLED REPLACEMENT ANGLE PER SRM 51-10-6 AND 51-10-1.

Part: SKIN — CRACKED (NR 6 LE FLAP)

.25 PREVIOUSLY STOP DRILLED CRACK AT INBOARD LEADING EDGE OF RIGHT WING NR 6 SLAT. FABRICATED AND INSTALLED DOUBLER PER SRM 57-50-3.

Part: BULKHEAD WEB — CRACKED (RT MLG WW)

.5 INCH CRACK AT APU OAD CONTROL VALVE CUT OUT IN RIGHT WHEEL WELL AT FWD BULKHEAD. FABRICATED AND INSTALLED DOUBLER REPAIR PER EC/RA 5310-01544.

Part: SKIN — CORRODED (FWD LAV PANEL)

FUSELAGE SKIN AT FWD LAVATORY SERVICE PANEL HAS CORROSION. CUTOUT CORRODED AREA. FABRICATED AND INSTALLED FILLER AND DOUBLER PER EC/RA 5330-02584.

Part: FITTING — CRACKED (R-2 DOOR)

IAH - INSPECTION FOUND A 1.5 INCH CRACK IN R-2 DOOR UPPER HINGE FITTING. THE FITTING WAS REMOVED AND REPLACED IAW SRM 51-10-1. (X)