N70755

Part: WEB — CORRODED (BS 1110-1130)

DURING A C-CHECK, CORROSION WAS NOTED AT FS 1110 - FS 1130, UNDER SIDE OF CUSP WEB RBL 64.

Part: WEB — CORRODED (BS 1110-1130)

DURING A C-CHECK, CORROSION WAS NOTED AT FS 1110 - FS 1130 UNDERSIDE OF CUSP WEB RBL 64.

Part: SEAT TRACK — CORRODED (BS 1040-1070)

DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK INSIDE OF L-1 DOOR STA 1040-1070.

Part: BOTTLE PIN — CORRODED (FUSELAGE)

DURING A C-CHECK, CORROSION WAS NOTED ON RIGHT FRONT SPAR WING TO BODY BOTTLE PIN.

Part: BOTTLE PIN — CORRODED (FUSELAGE)

DURING A C-CHECK, CORROSION WAS NOTED ON LEFT FRONT SPAR WING TO BODY BOTTLE PIN.

Part: BOLT — CORRODED (STA 1183)

DURING A C-CHECK, CORRROSION NOTED ON LT AND RT BULKHEAD ATTACH FITTING STA 1183.

Part: BOLT — CORRODED (LT WING)

DURING A C-CHECK, CORROSION NOTED ON LEFT FORWARD WING BODY TERMINAL PIN BEARING LUG BOLT.

Part: SUPPORT — CORRODED (CABIN)

DURING A C-CHECK, CORROSION NOTED ON TOP AND BOTTOM OF FLOOR SUPPORT R1 DOOR.

Part: SEAT TRACK — CORRODED (BS 1110-1155)

DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK STA 1110 - STA 1155, LBL 24.5.

Part: BRACKET — CORRODED (CARGO BAY)

DURING A C-CHECK, CORROSION NOTED ON FORWARD PIT DOOR FRAME ATTACH BRACKET (STA 580).

Part: BOTTLE PIN — CORRODED (RT WING)

DURING A C-CHECK, CORROSION NOTED AT RT REAR SPAR BOTTLE PIN.

Part: SEAT TRACK — CORRODED (BS 1110)

DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK STA 1110RT.

Part: SUPPORT — CORRODED (CABIN)

DURING A C-CHECK, CORROSION NOTED ON TOP AND BOTTOM OF FLOOR SUPPORT L-1 DOOR.

Part: LINK — CORRODED (RT MLG)

DURING A C-CHECK, CORROSION NOTED ON RT MLG WALKING BEAM ACTUATOR BEAM SUPPORT LINK SHAFT.

Part: SUPPORT — CORRODED (BS 520)

DURING C-CHECK, CORROSION NOTED ON FORWARD BAY PIT FLOOR SUPPORT STA 520, LBL 5.

Part: SKIN — CORRODED (BS 680)

DURING C-CHECK, CORROSION NOTED IN FORWARD PIT BILGE STA 680 STR 28R ON SKIN.

Part: SPLICE — CORRODED (BS 680)

DURING C-CHECK, CORROSION NOTED AT STA 680 ON STR 27R SPLICE FITTING.

Part: SILL — CORRODED (BS 460)

DURING C-CHECK, CORROSION NOTED AT FLOOR LEVEL MAIN CABIN MOP SILL STA 460 RT.

Part: STRINGER — CORRODED (BS 1012)

INSPECTION FOUND STRINGER 29L CORRODED AT STA 1012. THE CORRODED AREA WAS CUT OUT, A SPLICE AND STRINGER WERE FABRICATED AND INSTALLED IAW SRM 53-10-3.

Part: PANEL — CRACKED (NLG WW)

INSPECTION FOUND CRACKS AROUND SEVEN FASTENERS IN TOP LEFT PANEL OF NLG WHEEL WELL. THE CRACKS MEASURED FROM .125 TO .5 INCH IN LENGTH. THE CRACKED AREA WAS CUT OUT, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-2.

Part: PANEL — CRACKED (NLG WW)

INSPECTION FOUND CRACK INDICATIONS AROUND SIX EACH FASTENERS IN TOP RIGHT PANEL OF NLG WHEEL WELL. THE CRACKED AREA WAS CUT OUT, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-2.

Part: PANEL — CRACKED (NLG WW)

INSPECTION FOUND CRACK INDICATIONS AROUND THREE EACH FASTENERS IN TOP CENTER PANEL OF NLG WHEEL WELL. THE CRACKED AREA WAS CUT OUT, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-2.

Part: SKIN — CRACKED (LT WING)

INSPECTION FOUND A .1875 INCH CRACK IN LT WING INBOARD UPPER LEADING EDGE SKIN. THE CRACK WAS LOCATED FORWARD OF FRONT SPAR AT SCREW 7.5 INCHES OUTBOARD OF FUSELAGE. THE CRACKED AREA WAS CUT OUT, FILLER AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 57-30-4.

Part: SKIN — CRACKED (L-1 DOORWAY)

INSPECTION FOUND A 1.25 INCH CRACK IN FUSELAGE SKIN JUST FORWARD OF LOWER HINGE OF L-1 DOOR. THE CRACKED AREA OF SKIN WAS CUT OUT, FILLER AND DOUBLER WERE FABRICATED AND INSTALLED IAW WORK CONTROL CARD M AND E NR 07-5310-1-0100.

Part: SHEAR TIE — CORRODED (BS 660)

INSPECTION FOUND SHEAR TIE CORRODED IN FORWARD CARGO COMPARTMENT AT STA 660, STRINGER 27R AND CIRCUMFERENTIAL AREA. THE SHEAR TIE WAS REMOVED, A REPLACEMENT WAS FABRICATED AND INSTALLED IAW SRM 51-40-4.

Part: SPLICE — CORRODED (BS 680)

INSPECTION FOUND STRINGER SPLICE IN FORWARD CARGO COMPARTMENT CORRODED AT STA 680, STRINGER 27L. THE CORRODED SECTION WAS REMOVED, REPLACEMENT PARTS WERE FABRICATED AND INSTALLED IAW SRM 53-10-3 AND 51-30-3.

Part: SKIN — CRACKED (NR 3 LE SLAT)

INSPECTION FOUND A .3125 INCH CRACK IN NR 3 SLAT LOWER TRAILING EDGE EXTERIOR SKIN AT RIVET BELOW ACTUATOR PISTON. THE CRACK WAS STOP DRILLED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-50-3.

Part: AUX SPAR CHORD — CRACKED (LT WING)

INSPECTION FOUND A 2 INCH CRACK IN LT WING AUX SPAR LOWER CHORD. THE CRACK WAS LOCATED AT INBOARD END FORWARD OF NR 7 SPOILER ACTUATOR SUPPORT FITTING. THE CRACKED SECTION OF CHORD WAS CUT OUT, A REPLACEMENT CHORD AND SPLICE WERE FABRICATED AND INSTALLED IAW ECRA 5720-01590.

Part: WEB — CRACKED (BS 290)

INSPECTION FOUND A .5 INCH CRACK IN NOSE GEAR WELL HORIZONTAL WEB ON RT SIDE AT STA 290. THE WEB WAS REMOVED, A REPLACEMENT WAS FABRICATED AND INSTALLED IAW SRM 51-10-1.

Part: SKIN — CORRODED (BS 1012)

INSPECTION FOUND FUSELAGE SKIN CORRODED AT STA 1012, STRINGER 29L. THE CORROSION WAS REMOVED, FILLER AND DOUBLER WERE INSTALLED IAW SRM 53-30-3.

Part: MOTOR — LEAKING (RT TE FLAP)

AIRCRAFT LOST THE 'A' HYDRAULIC SYSTEM FLUID QUANTITY WHILE EN ROUTE FROM EWR TO TPA. THE FLUID LOSS WAS ACCOMPANIED BY NR 1 ENGINE DRIVEN HYDRAULIC PUMP PRESSURE LOSS. THE AIRCRAFT LANDED AT TPA WITHOUT INCIDENT. MAINTENANCE FOUND THE RT OUTBOARD FLAP MOTOR SEAL BLOWN. THE FLAP MOTOR WAS REMOVED AND REPLACED. IN ADDITION, THE NR 1 ENGINE DRIVEN HYDRAULIC PUMP WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL. LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: FLOORBEAM — CORRODED (BS 1130)

INSPECTION FOUND LOWER SURFACE OF FLOOR BEAM CORRODED AT F.S. 1130. THE AREA WAS REPAIRED IAW ECRA 5310-03318.

Part: HYD LINE — LEAKING (PRESS MODULE)

AIRCRAFT LOST THE A-SYSTEM HYDRAULIC QUANTITY WHILE EN ROUTE. THE LOSS WAS ACCOMPANIED BY ILLUMINATION OF THE NR 1 A-PUMP PRESSURE LIGHT. THE HYDRAULIC QUANTITY LOSS AND HYDRAULIC SYSTEM FAILURE CHECKLISTS WERE ACCOMPLISHED AND THE AIRCRAFT LANDED AT IAH WITHOUT INCIDENT. MAINTENANCE FOUND HYDRAULIC PRESSURE LINE AT A-SYSTEM PRESSURE MODULE LEAKING. THE LINE WAS REPLACED USING FLEX LINE AND A DIP WAS ISSUED TO REPLACE THE FLEX LINE WITHIN 1200 HOURS OR 500 FLIGHTS.

Part: ACTUATOR — BROKEN (NR 2 LE SLAT)

IAH - FLT 0525 - THE A-SYSTEM HYDRAULIC QUANTITY WENT TO ZERO UPON FLAP RETRACTION AFTER TAKEOFF FROM IAH. FUEL WAS DUMPED AND THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE FRONT END OF NR 2 LEADING EDGE SLAT ACTUATOR BROKEN. THE NR 2 SLAT ACTUATOR WAS REMOVED AND REPLACED PER MM 27-81-32. THE HYDRAULIC SYSTEM WAS SERVICED AND THE ENGINE PUMPS WERE RUN. OPERATION OF THE PUMPS AND SLAT ACTUATOR CHECKED GOOD. (X)

Part: CHORD — CORRODED (BS 1176.9)

GSO - THE MAIN CABIN BS 1183 BULKHEAD REINFORCEMENT CHORD AT BS 1176.9 AT RT CUSP TO AFT ENTRY DOOR CUTOUT HAD CORROSION AND BLUE WATER STAINS. THE REINFORCEMENT CHORD WAS REMOVED AND REPLACED IAW SRM 51-10-1. (M)

Part: WEB — CRACKED (RT TE MID FLAP)

GSO - INSPECTION FOUND THE RT OUTBOARD MID-FLAP INBOARD END WEB CRACKED AT TWO PLACES. BOTH CRACKS WERE .5 INCH LONG. REPAIR PARTS WERE FABRICATED AND INSTALLED IAW SRM 51-40-2 AND 51-30-2. (M)

Part: FLOORBEAM BRACE — CRACKED (FORWARD LAV)

GSO - INSPECTION FOUND A 1.3 INCH CRACK IN FORWARD LAVATORY FLOORBEAM BRACE. A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-21 AND 51-30-2. (M)

Part: SKIN — CRACKED (RT WING LE)

GSO - INSPECTION FOUND A .75 INCH CRACK IN RT WING FIXED LEADING EDGE ABOVE CUTOUT FOR NR 6 SLAT OUTBOARD TRACK. THE CRACK WAS STOP DRILLED. A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW ECRA 5762-01020. (M)

Part: LE STRUCTURE — CRACKED (LT WING)

GSO - INSPECTION FOUND THE LEFT WING LEADING EDGE CAVITY NR 1 SLAT ACTUATOR INBOARD ATTACH AREA CRACKED AT MOUNT BOLT. THE CRACK WAS .5 INCH LONG. A SUPPORT RIB REPAIR WAS INSTALLED IAW ECRA 557C187. (M)

Part: FRAME — CRACKED (BS 990)

GSO - INSPECTION FOUND A 1 INCH CRACK IN FRAME AT UPPER LIP IN AFT CARGO HOLD STATION 990, BETWEEN S27L AND S28L. THE CRACKED AREA WAS REMOVED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-4 AND 51-30-3. (M)

Part: ANGLE — CRACKED (WS 118)

GSO - A .25 INCH CRACK WAS FOUND IN THE RT WING LEADING EDGE CAVITY AT STATION 118 WEB LOWER ATTACH ANGLE. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-3 AND 51-30-2. (M)

Part: ANGLE — CRACKED (BS 720)

GSO - A .80 INCH CRACK WAS FOUND IN THE LOWER FUSELAGE INTERCOSTAL SUPPORT ANGLE AT BS 720. THE CRACK WAS STOP DRILLED. A REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-40-3, 51-30-2, AND 51-20-4. (M)

Part: SKIN — CORRODED (BS 720)

GSO - INSPECTION FOUND ACTUATOR ACCESS PANEL AND LOWER FUSELAGE BL 0, BS 720 SKIN CORRODED AT RT RAM AIR SCOOP. A REPAIR DOUBLER AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 51-30-2. THE ACCESS PANEL WAS REPLACED WITH A NEW PANEL IAW SRM 51-10-1. (M)

Part: ANGLE — CRACKED (WS 119)

GSO - INSPECTION FOUND A .5 INCH CRACK IN WEB LOWER ATTACH ANGLE OF RT WING LEADING EDGE CAVITY AT STATION 119. A REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-40-3 AND 51-30-2. (M)

Part: STRINGER — CRACKED (WS 656.5)

GOS - INSPECTION FOUND A .5 INCH CRACK IN LEFT WING UPPER STRINGER S10 AT WS 656.50. THE STRINGER WAS REPAIRED IAW EA 5762-01050. (M)

Part: FLOORBEAM — CORRODED (FS 1110)

GSO - INSPECTION FOUND THE FLOORBEAM CORRODED AT FS 1110, RBL 20-RBL 60. THE CORRODED SECTION OF FLOORBEAM WAS CUTOUT IAW ECRA 5310-01102. A SPLICE T-CHORD, FOUR ANGLE SPLICES, AND FILLER WERE FABRICATED AND INSTALLED IAW ECRA 5310-01102 AND SRM 51-30-2. (M)

Part: STRINGER — CORRODED (BS 570)

GSO - INSPECTION FOUND STRINGER 28L CORRODED UNDER FLOOR SUPPORT IN FORWARD PIT AT STATION 570. THE CORRODED AREA OF STRINGER WAS CUT OUT IAW SRM 53-10-3. REPAIR PARTS WERE FABRICATED AND INSTALLED IAW SRM 53-10-2 AND 51-30-2. (M)

Part: FLOOR — CORRODED (BS 1130-1140)

GSO - THE FLOORBOARD SUPPORTS, FLOORBEAM, AND ATTACHING WEB IN AFT GALLEY AREA AT STATION 1130-1140 WERE FOUND CORRODED. THE CORRODED SECTIONS WERE REMOVED IAW ECRA 5310-01508. REPAIR WAS FABRICATED AND INSTALLED IAW ECRA 5310-01508 AND SRM 51-30-2. (M)

Part: SKIN — CRACKED (WS 90 LE)

GSO - INSPECTION FOUND RT WING LEADING EDGE CAVITY INTERIOR OF LEADING EDGE SKIN CRACKED AT RIVET HOLES AT STATION 90. THE CRACK WAS .25 INCH LONG. THE CRACK WAS STOP DRILLED. REPAIR DOUBLERS WERE FABRICATED AND INSTALLED PER ECRA 5720-01064. (M)

Part: O-RING — LEAKING (SPOILER)

EWR - FLT 0432 - THE A-SYSTEM HYDRAULIC QUANTITY DROPPED TO ZERO IN FLIGHT. THE AIRCRAFT LANDED AT EWR WITHOUT INCIDENT. MAINTENANCE FOUND THE GROUND SPOILER CONTROL VALVE IN THE LT WHEELWELL LEAKING AT FITTING. THE O-RING AND REDUCER WERE REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL AND LEAK CHECKS WERE GOOD. (X)