N16808

Part: SKIN — DENTED (FUSELAGE) · airframe 52,251 hrs · 24,391 cycles

INSPECTION FOUND LT AFT FUSELAGE SKIN DENTED JUST AFT OF LOUVER. THE DENT WAS COLD WORKED AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38, SHEETS 11 AND 20, AND 51-30-2.

Part: SUPPORT — CRACKED (MLG WW)

INSPECTION FOUND A 1 INCH CRACK IN LT WHEEL WELL FORWARD JAMB SUPPORT. AN ANGLE AND FILLER REPAIR WAS INSTALLED IAW SRM 51-10-11, 51-10-03, AND 53-10-01, FIGURE 2.

Part: FITTING — CRACKED (BS 200)

INSPECTION FOUND A 1 INCH CRACK IN VERTICAL SUPPORT FITTING AT FS 200, LBL 50. THE VERTICAL SUPPORT FITTING WAS REPLACED IAW SRM 51-30-05.

Part: PAN — GOUGED (PAX DOOR)

INSPECTION FOUND R-1 DOORJAMB LOWER PAN AT SILL PLATE GOUGED. THE R-1 DOOR JAMB LOWER PAN WAS REMOVED AND REPLACED IAW SRM 53-05, FIGURE 55.

Part: SKIN — DENTED (HORIZ STAB)

INSPECTION FOUND RT HORIZONTAL STABILIZER DENTED EIGHT FEET AND NINE FEET FROM STABILIZER ROOT AT LEADING EDGE. THE AREA WAS REPAIRED IAW SRM 55-03, PAGE 6 AND 6A. A DIP WAS ISSUED TO REINSPECT THE REPAIR EVERY 125 FLIGHT HOURS AND TO INSTALL A PERMANENT REPAIR WITHIN 4000 FLIGHT HOURS.

Part: SKIN — DENTED (HORIZ STAB)

INSPECTION FOUND LEFT HORIZONTAL STABILIZER LEADING EDGE LOWER SURFACE DENTED AT XFS 71 TO XFS 77.50. A DOUBLER WAS INSTALLED IAW EA9-5513-2-AD577 AND ECRA 5510-01482.

Part: SEAT TRACK — CORRODED (BS 1040 - 1338)

INSPECTION FOUND LEFT I/B SEAT TRACK CORRODED BETWEEN STA 1040 AND 1338. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-1 AND 51-30-5.

Part: SUPPORT — CORRODED (BS 200)

INSPECTION FOUND FLOOR SUPPORT AT FS 200, BL 0 TO RBL 44 CORRODED. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-30-2.

Part: WEB — CRACKED (BS 1174)

INSPECTION FOUND CUSP WEB CRACKED AT FS 1174, LBL 43. THE CRACKED SECTION OF WEB WAS REMOVED AND A NEW SECTION AND DOUBLER WERE INSTALLED IAW SRM 51-30-5.

Part: BATTERY PACK — DISCHARGED (CABIN)

INSPECTION FOUND THE FIRST CLASS OVERHEAD EMERGENCY ESCAPE PATH LIGHTING INOPERATIVE. THE BATTERY PACK WAS REMOVED AND REPLACED AND OPERATION OF THE OVERHEAD LIGHTING CHECKED GOOD.

Part: STRUT — REQUIRED SERVICE (NLG)

THE NOSE GEAR DID NOT RETRACT AFTER TAKEOFF FROM ORD. THE CHECKLIST WAS PERFORMED AND WHEN THE GEAR WAS PUT DOWN IT EXTENDED WITH A BANG. THE AIRCRAFT WAS RETURNED TO ORD WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NOSE GEAR STRUT FLAT. A FULL SERVICE WAS PERFORMED ON THE NOSE STRUT IAW MM 32-21-02. STRUT LEAK CHECK WAS GOOD.

Part: CABLES — OUT OF ADJUST (TAIL CONE)

THE FORCE REQUIRED TO DROP TAILCONE USING THE INTERIOR RELEASE HANDLE AND THE AFT PASSENGER ENTRANCE DOOR HANDLE WAS EXCESSIVE. MAINTENANCE RIGGED THE TAILCONE IAW MM 53-53-00 AND OPERATION CHECKED GOOD. IN ADDITION, ONE LOCK LATCH PIN WAS REPLACED DUE TO WEAR.

Part: INTERCOSTAL — CRACKED (PAX DOOR)

INSPECTION FOUND A 1 CRACK IN MAIN CABIN DOOR INTERCOSTAL. THE CRACK WAS IN RADIUS AND LOCATED AFT OF HANDLE TORQUE SHAFT. THE INTERCOSTAL WAS REMOVED AND REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: JAMB — CORRODED (BAGGAGE COMPT)

INSPECTION FOUND DOOR JAMB BEAM OF MAIN BAGGAGE BIN CORRODED. A REPAIR WAS INSTALLED IAW SRM 53-05, FIGURE 63 AND ECRA 5310-03642.

Part: BEAM — CRACKED (SERVICE DOOR)

INSPECTION FOUND A .75 CRACK IN FORWARD LOWER CORNER OF FORWARD SERVICE DOOR LOWER BEAM. A NEW BEAM WAS INSTALLED IAW SRM 51-30-02, 51-30-04, AND 51-30-05.

Part: RADIO PANEL — CHAFED WIRE (COCKPIT)

THE OBSERVER'S RADIO PANEL STARTED TO SMOKE WHILE EN ROUTE. THE PANEL WAS REMOVED, THE CONNECTOR PLUGS WERE DISCONNECTED, AND THE SMOKE CEASED. THE FLIGHT CONTINUED TO MIA WHERE IT LANDED WITHOUT FURTHER PROBLEM. A CHAFED WIRE WAS FOUND BEHIND THE PANEL. THE WIRE WAS REPAIRED AND THE PANEL WAS REPLACED.

Part: GROUND SHIFT ROD — BROKEN (NLG)

THE AIR/GROUND SHIFT MECHANISM WOULD NOT COME OUT OF GROUND MODE AFTER TAKEOFF FROM IAH. THE AIRCRAFT WAS RETURNED TO IAH. MAINTENANCE FOUND GROUND SHIFT ROD ON NOSE GEAR BROKEN. THE GROUND SHIFT ROD WAS REMOVED AND REPLACED.

Part: SKIN — DELAMINATED (RT WING TE)

MIA - INSPECTION FOUND RIGHT WING CENTER SPAR TRAILING EDGE LOWER PANEL BELOW INBOARD AND OUTBOARD ANTI-SKID VALVES DELAMINATED. THE DELAMINATED AREA WAS CUT OUT. A NEW CORE WAS INSTALLED AND FIBERGLASS OVERLAY WAS APPLIED IAW SRM 51-70-2. (M)

Part: SUPPORT — CORRODED (BS 570-695)

MIA - INSPECTION FOUND CORROSION ON FLOOR SUPPORT TRACK IN CENTER CARGO COMPARTMENT BETWEEN BS 570-695, LBL 20. THE CORRODED AREA WAS CUT OUT AND A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-1-0. (M)

Part: BULKHEAD — CRACKED (FS 1490)

MIA - INSPECTION FOUND A .5 INCH CRACK IN CANTED BULKHEAD WEB JUST FORWARD OF RUDDER TRIM ACTUATOR DRUM AT FS 1490, RIGHT SIDE. THE CRACKED WEB WAS REMOVED AND A BRACKET WAS FABRICATED AND INSTALLED IAW SRM 51-30-02. (M)

Part: SUPPORT — CORRODED (BS 1165)

MIA - INSPECTION FOUND FLOOR BOARD SUPPORT HAT CHANNEL CORRODED IN MAIN CABIN AT STATION 1165. A NEW FLOOR BOARD SUPPORT HAT CHANNEL WAS FABRICATED AND INSTALLED IAW SRM 51-30-1. (M)

Part: ANGLE — CRACKED (BS 1401-1429)

MIA - INSPECTION FOUND A .5 INCH CRACK IN LEFT AND RIGHT VERTICAL STABILIZER TO FUSELAGE EXTERNAL ATTACH ANGLES LOCATED BETWEEN BS 1401 TO 1429. THE ANGLES WERE REMOVED AND REPLACED IAW SRM 51-30-2. (M)

Part: SKIN — DELAMINATED (RT SPOILER)

MIA - INSPECTION FOUND RIGHT WING INBOARD SPOILER UPPER SKIN DELAMINATED AT FORWARD INBOARD AREA. THE DAMAGED CORE WAS CUT OUT AND A HOT BOND REPAIR WAS DONE IAW SRM 51-70-1A. (M)

Part: FLOOR WEB — CRACKED (BS 1300)

MIA - INSPECTION FOUND AN 8 INCH CRACK IN SUB FLOOR WEB ON RIGHT SIDE, STATION 1300, STRINGER 18. A NEW DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-01, FIGURE 2. (M)

Part: VANE — GOUGED (RT TE FLAP)

MIA - INSPECTION FOUND TOP INBOARD END OF RIGHT WING 5TH FOREFLAP VANE HAD GOUGES. THE DAMAGED AREA WAS CUT OUT AND A HOT BOND REPAIR WAS INSTALLED IAW SRM 51-1-9A. (M)

Part: SKIN — CHAFED (LT TE FLAP)

MIA - INSPECTION FOUND LEFT WING INBOARD FLAP UPPER SURFACE CHAFED INTO TWENTY INCHES FROM OUTBOARD END. THE CHAFED AREA WAS CUT OUT. AN INTERNAL DOUBLER AND FILLER WERE FABRICATED IAW SRM 51-01, FIGURE 4 AND INSTALLED IAW SRM 51-30-0. (M)

Part: VANE — DINGED (LT TE FLAP)

MIA - INSPECTION FOUND LOWER SURFACE OF INBOARD LEFT FLAP VANE DINGED AND ERODED DUE TO IMPACT DAMAGE CAUSED BY TIRE DEBRIS. A HOT BOND REPAIR WAS PERFORMED IAW SRM 51-1-9A. (M)

Part: SKIN — DELAMINATED (LT WING TE)

MIA - INSPECTION FOUND LEFT WING LOWER TRAILING EDGE SKIN PANEL DELAMINATED AROUND MOUNT SCREWS FOR INBOARD AND OUTBOARD ANTI-SKID VALVES. THE PANEL WAS REPAIRED WITH FIBERGLASS OVERLAY IAW SRM 51-70-1. (M)

Part: VANE — CHAFED (LT TE FLAP)

MIA - INSPECTION FOUND LEFT WING OUTBOARD FLAP OUTBOARD VANE SEGMENT CHAFED WITH METAL CURLED AT INBOARD UPPER END. THE CHAFED AREA WAS CUT OUT. FILLER AND DOUBLER WERE FABRICATED AND HOT BONDED IAW SRM 51-1-40A. (M)

Part: BATTERY PACK — DISCHARGED (AFT GALLEY)

MIA - INSPECTION FOUND THE AISLE OVERHEAD EMERGENCY LIGHT AT AFT GALLEY TO LAV INOPERATIVE. THE BATTERIES FOR THE EMERGENCY LIGHT WERE REMOVED, CHARGED, AND REINSTALLED. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

MIA - INSPECTION FOUND THE FORWARD ENTRY EMERGENCY LIGHT DIM. THE BATTERIES FOR THE EMERGENCY LIGHT WERE REMOVED, RECHARGED, AND REINSTALLED. (M)

Part: BATTERY — DISCHARGED (AFT GALLEY)

MIA - INSPECTION FOUND AFT GALLEY EMEREGNCY LIGHT DIM. THE BATTERIES FOR THE LIGHT WERE REMOVED, CHARGED AND REINSTALLED. (M)

Part: BATTERY PACK — DISCHARGED (FWD GALLEY)

MIA - INSPECTION FOUND FORWARD GALLEY EMERGENCY LIGHT DIM. THE BATTERY PACK WAS REPLACED AND A LAMP WAS INSTALLED PER MM 33-50-0. (M)

Part: CLAMP — BROKEN (NR 2 ENGINE)

FLT 1263 - CLE - THE NR 2 ENG FIRE WARN LIGHT ILLUMINATED DURING CLIMB-OUT OF CLE. THE FIRE LIGHT WENT OUT FOR ABOUT 1 MIN AFTER LEVELING OFF, AND CAME ON AGAIN FOR ABOUT 15 SEC. THE FIRE WARN WAS ACCOMPANIED BY NR 2 ENG OIL QTY LOSS AND THE CABIN WOULD NOT PRESS. THE A/C WAS RETURNED TO CLE, LANDED W/O INCIDENT. MX FOUND NO EVIDENCE OF FIRE. THE NR 2 ENG 13TH STAGE DUCT CLAMP WAS FOUND BROKEN WITH RESULTANT DAMAGE TO THE NR 2 ENG NOSE COWL AND UPPER COWL, AND THE 13TH STAGE DUCT WAS DENTED. THE NR 2 ENG LOW OIL PRESS SWITCH WAS ALSO DAMAGED AND LEAKING. THE CLAMP, DUCT, NOSE COWL, UPPER COWL, AND OIL PRESS SWITCH WERE R/R. ENG WAS SERVICED WITH OIL AND LK CK WAS GOOD. FIRE DET SYS CHECKED GOOD. (M)

Part: GEN CONTL PNL — INOPERATIVE (RT SYSTEM)

GSO - FLT 0402 - THE RIGHT CSD OIL TEMP WENT OFF SCALE HIGH AFTER TAKEOFF FROM MCO. THE CSD WAS DISCONNECTED AND THE APU WAS STARTED TO POWER THE RIGHT AC BUS. THE APU GENERATOR FREQUENCY STARTED FLUCTUATING FULL SCALE DEFLECTION BOTH WAYS. THE APU GENERATOR WAS SHUT DOWN WHILE CLIMBING THROUGH 27,000 FEET. THE AIRCRAFT WAS DIVERTED TO GSO WHERE IT LANDED WITHOUT INCIDENT. THE APU GENERATOR CONTROL PANEL WAS REPLACED AND OPERATION CHECKED GOOD. IN ADDITION, THE RIGHT CSD, GENERATOR, AND CSD OIL COOLER WERE REPLACED DUE TO THE CSD FAILURE. (X)