N69736

Part: WEDGE — DELAMINATED (RT AILERON)

INSPECTION FOUND RT WING OUTBOARD AILERON TRAILING EDGE WEDGE DELAMINATED ON LOWER SURFACE AT OUTBOARD EDGE. THE TRAILING EDGE WEDGE WAS REMOVED, REPAIRED AND INSTALLED IAW SRM 51-30-2.

Part: SKIN — DEBONDED (LT TE FOREFLAP)

INSPECTION FOUND LT WING OUTBOARD FOREFLAP DEBONDED AT UPPER INBOARD TRAILING EDGE AREA. THE FOREFLAP WAS REMOVED AND REPLACED IAW MM 27-51-4.

Part: SKIN — DAMAGED (NR 2 ENGINE)

INSPECTION FOUND FASTENERS PULLING THROUGH SKIN FORWARD OF INLET GUIDE VANES AROUND CIRCUMFERENCE AT NR 2 ENGINE INLET. THE FASTENERS WERE REMOVED AND REPLACED IAW EA 5410-01328 AND SRM 51-30-2.

Part: SKIN — CORRODED (LT TE MIDFLAP)

INSPECTION FOUND CORROSION AND DEBONDING 65 INCHES FROM INBOARD END OF LT WING INBOARD MIDFLAP UPPER TRAILING EDGE. THE LT WING INBOARD MIDFLAP UPPER TRAILING WAS REMOVED, REPAIRED, AND REINSTALLED IAW SRM 51-30-2, 51-10-6, 51-10-1, AND 51-20-4.

Part: SKIN — DELAMINATED (RT TE FOREFLAP)

INSPECTION FOUND TWO AREAS OF DELAMINATION IN RT TRAILING EDGE INBOARD FOREFLAP UPPER SURFACE. THE DELAMINATION WAS LOCATED 90 INCHES FROM INBOARD EDGE AND 25 INCHES FROM OUTBOARD EDGE. THE FOREFLAP WAS REMOVED AND REPAIRED IAW SRM 57-50-02. THE FOREFLAP WAS REINSTALLED IAW MM 27-51-14.

Part: SKIN — CORRODED (RT TE MIDFLAP)

INSPECTION FOUND RT INBOARD MIDFLAP LOWER TRAILING EDGE CORRODED AND DISBONDED IN AFT FLAP COVE BETWEEN TEARDROP FAIRINGS. THE MIDFLAP LOWER TRAILING EDGE WAS REMOVED IAW SRM 51-30-2, TREATED AND PRIMED IAW SRM 51-10-2, AND INSTALLED IAW SRM 51-10-1 AND 51-20-4.

Part: BRACKET — CRACKED (NR 8 LE SLAT)

INSPECTION FOUND A 2 INCH CRACK IN NR 8 SLAT OUTBOARD UPSTOP BOLT BRACKET AND LOWER LEADING EDGE SKIN FLANGE BROKEN. THE BRACKET WAS REMOVED, A NEW BRACKET WAS FABRICATED AND INSTALLED IAW SRM 51-30-2.

Part: SKIN — DEBONDED (LT TE MIDFLAP)

INSPECTION FOUND LT WING OUTBOARD MIDFLAP LOWER TRAILING EDGE DEBONDED ON TOP 108 INCHES FROM INBOARD END AND ON BOTTOM 128 INCHES FROM INBOARD END. REMOVED MIDFLAP, REPAIRED AND INSTALLED IAW SRM 51-30-2, 51-10-2, 51-10-1, AND 51-20-4.

Part: SKIN — CORRODED (BS 620)

INSPECTION FOUND RT FUSELAGE SKIN CORRODED JUST BELOW CABIN WINDOW NR 11 AT STA 620. THE FASTENERS WERE REMOVED, THE CORROSION WAS CLEANED, AND FASTENERS WERE INSTALLED IAW SRM 51-30-2.

Part: FITTING — CRACKED (LT MLG)

INSPECTION FOUND A .5 INCH CRACK AT FORWARD LUG OF LT MLG UPLOCK SUPPORT FITTING. THE SUPPORT FITTING WAS REMOVED AND REPLACED IAW SRM 51-10-1. A LANDING GEAR RETRACTION AND ROTATIONAL CHECK WAS ACCOMPLISHED AND ALL CHECKED GOOD.

Part: SKIN — CORRODED (E/E DOOR)

INSPECTION FOUND E AND E DOOR RT SIDE SKIN CORRODED. THE DOOR WAS REMOVED AND REPLACED IAW MM 52-40-11.

Part: SKIN — CRACKED (NR 6 LE SLAT)

INSPECTION FOUND A .125 AND .0937 INCH CRACK AT FASTENER OF NR 6 SLAT SKIN UPPER LEADING EDGE, IN FORWARD ROW OF FASTENERS 50 FROM INBOARD END. THE FASTENERS WERE REMOVED, THE CRACKS WERE STOP DRILLED IAW SRM 51-10-1. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-50-3, FIGURE 1.

Part: HYD LINE — LEAKING (AIR COND BAY)

THE A-SYSTEM HYDRAULIC QUANTITY DECREASED TO .5 GALLON WHILE EN ROUTE. THE NR 1 LED UNSAFE LIGHT WAS OBSERVED TO BE ILLUMINATED WITH FLAPS UP. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND HYDRAULIC LINE IN RIGHT AIR CONDITIONING BAY 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: POWER SUPPLY — INOPERATIVE (CABIN)

INSPECTION FOUND RT AFT OVERWING EMERGENCY EXIT LIGHT INOPERATIVE. BOTH RT OVERWING CHARGING PACKS WERE REPLACED.

Part: SKIN — CORRODED (BS 430)

INSPECTION LT FUSELAGE SKIN BULGED AT STA 430. THE BULGED AREA WAS CUT OUT, A REPAIR PLATE WAS FABRICATED AND INSTALLED IAW SRM 53-30-2.

Part: RIB — CRACKED (NR 3 LE SLAT)

INSPECTION FOUND NR 3 LEADING EDGE SLAT INBOARD END CLOSURE RIB CRACKED. THE RIB WAS REMOVED AND REPLACED IAW SRM 51-30-2.

Part: SKIN — CORRODED (BS 480-500)

INSPECTION FOUND CORROSION ON SKIN UNDER STRINGER 28L BETWEEN STA 480 AND 500. THE CORRODED AREA WAS CUT OUT, REPAIR DOUBLER AND FILLERS WERE FABRICATED AND INSTALLED IAW SRM 51-10-2, 53-30-2 AND 53-30-3.

Part: ANGLE — CORRODED (BS 620-630)

INSPECTION FOUND CORROSION ON BOTTOM SIDE OF SPLICE ANGLE ABOVE STRINGER 27R AT STA 620 TO 630. THE OLD SPLICE WAS REMOVED AND A NEW SPLICE WAS FABRICATED AND INSTALLED IAW SRM 51-40-4 AND 51-10-2.

Part: FLOOR BEAM — CORRODED (BS 1070)

INSPECTION FOUND LOWER HORIZONTAL LEG AT CABIN FLOORBEAM CORRODED FROM BL ZERO TO RBL 56, STA 1070 (AFT CARGO). A STRAP AND ANGLE REPAIR WERE FABRICATED AND INSTALLED IAW SRM 53-10-8.

Part: RIB — CRACKED (NR 5 LE SLAT)

INSPECTION FOUND LOWER FORWARD END OF NINE RIBS CRACKED AT INTERIOR OF NR 5 SLAT. THE CRACKS RANGED IN LENGTH FROM .1250 INCH TO 1 INCH. THE CRACKS WERE STOP DRILLED. REPAIRS WERE FABRICATED AND INSTALLED IAW SRM 57-50-3.

Part: ANGLE — CRACKED (BS 720)

INSPECTION FOUND A HOLE BROKEN THROUGH CAP ANGLE OF CABIN FLOOR INTERCOSTAL BETWEEN STA 720 AND 720A, BL ZERO. THE CAP WAS REMOVED AND A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-10-1.

Part: SUPPORT — CORRODED (BS 1140)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 1140, LBL 12. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-30-2.

Part: SUB FLOOR — CORRODED (BS 1134-1140)

INSPECTION FOUND RT AFT LAV SUBFLOOR CORRODED AT STA 1134 TO 1140, RBL 19. THE CORROSION WAS REMOVED AND A DOUBLER WAS INSTALLED IAW SRM 51-40-2.

Part: FLOORBEAM — CORRODED (BS 1070)

INSPECTION FOUND FLOORBEAM CORRODED AT STA 1070, RBL 48 TO 57. THE CORROSION WAS REMOVED AND A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-8.

Part: ANGLE — CRACKED (BS 760.95)

INSPECTION FOUND A 2.25 INCH CRACK ON INBOARD FLANGE, JUST BELOW CABIN FLOORBOARD ATTACH ANGLE, OF LEFT FRAME AT BS 760.95. THE AREA WAS REPAIRED IAW BOEING DRAWING NR 65C36279-1.

Part: STRINGER — CRACKED (BS 686.50)

INSPECTION FOUND LT WING FUEL TANK STRINGER CRACKED AT STA 686.50. THE CRACK WAS STOP DRILLED, A REPAIR WAS FABRICATED AND INSTALLED IAW EA 5762-01050.

Part: SUPPORT — CORRODED (BS 1130-1142)

FLOOR SUPPORT AND INTERCOSTAL CORRODED AT STATION 1130 TO 1142 RBL 12 TO 16. REMOVED AND REPLACED FLOOR SUPPORT AND INTERCOSTAL IAW SRM 51-10-1 AND 51-10-2.

Part: FLOOR BEAM — CORRODED (BS 1130)

INSPECTION FOUND EXFOLIATION CORROSION ON FLOORBEAM AT STA 1130, LBL 18. THE CORROSION WAS REMOVED IAW SRM 51-10-6. REPAIR STRAPS WERE INSTALLED IAW SRM'S 51-10-2, 51-30, 51-40-5, AND 53-30-4.

Part: ANGLE — CORRODED (BS 1067)

INSPECTION FOUND FLOOR SUPPORT CORRODED BETWEEN RBL 24 AND RBL 48 AT STA 1067. THE FLOOR SUPPORT ANGLE WAS REMOVED AND REPLACED IAW SRM'S 51-10-1, 51-10-2, AND 51-30-2.

Part: ANGLE — CORRODED (BS 1034)

INSPECTION FOUND FLOOR SUPPORT ANGLE CORRODED AT LBL 35, STA 1034. THE FLOOR SUPPORT ANGLE WAS REMOVED AND REPLACED IAW SRM'S 51-10-1, 51-30-2, 51-10-2, AND 51-40-5.

Part: FITTING — CRACKED (RT TE MID FLAP)

INSPECTION FOUND A .75 INCH CRACK IN CHORD FITTING AT AFT UPPER INBOARD CORNER OF RT WING INBOARD MID FLAP REAR SPAR, WBL 124.2. THE FITTING WAS REMOVED AND REPLACED IAW SRM 51-30-2.

Part: RIB — CRACKED (RT TE MID FLAP)

INSPECTION FOUND A .75 INCH CRACK IN LOWER AFT END OF INBOARD RIB OF RT OUTBOARD MID FLAP. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM'S 51-10-0, 51-10-2, AND 51-40-3.

Part: FLOORBEAM — CORRODED (BS 344)

INSPECTION FOUND CORROSION AT NUTPLATE HOLES OF FLOORBEAM FLANGE AT STA 344, LBL 40. THE FLANGE WAS CUT OFF AND REPLACED IAW SRM 53-10-8.

Part: FLOORBEAM — CORRODED (BS 344)

INSPECTION FOUND FORWARD FLANGE OF FLOORBEAM AT STA 344 AND LBL 21 CORRODED. THE FLANGE WAS REMOVED AND A NEW FLANGE WAS FABRICATED AND INSTALLED IAW SRM 53-10-8.

Part: FLOORBEAM — CRACKED (BS 344)

INSPECTION FOUND A 1 INCH CRACK THROUGH NUTPLATE HOLE ON TOP AFT FLANGE OF STA 344 FLOORBEAM AT LBL 26. THE UPPER FLANGE WAS CUT OFF AND A REPLACEMENT FLANGE WAS INSTALLED IAW SRM 53-10-8.

Part: WEB — CRACKED (LT WING TIP)

INSPECTION FOUND LATERAL WEB CRACKED AT UPPER AND LOWER RADIUS INSIDE LEFT WING TIP, FORWARD OF FLUX VALVE COMPARTMENT. THE WEB WAS REMOVED AND REPLACED IAW SRM 51-10-1 AND 51-40-5.

Part: FLOOR BEAM — CORRODED (BS 1130)

INSPECTION FOUND THE AFT CARGO HORIZONTAL FLOORBEAM CORRODED AT STA 1130, RBL 30 TO RBL 53.

Part: SUPPORT — CRACKED (BS 580-600)

INSPECTION FOUND CENTER SUPPORT FOR FLOORBOARD IN FORWARD CARGO COMPARTMENT CRACKED AT STA 580 TO 600. ALSO, THE WEB BELOW WAS CRACKED. THE CRACKS WERE STOP DRILLED, REPAIRS WERE FABRICATED AND INSTALLED IAW SRM 51-40-2 AND 51-40-3.

Part: RIB — GROOVED (NR 5 LE SLAT)

INSPECTION FOUND OUTBOARD RIB OF NR 5 SLAT DEEPLY GROOVED. THE RIB WAS REMOVED AND REPLACED IAW SRM 51-10-1.

Part: FLOORBEAM — CORRODED (BS 1110)

INSPECTION FOUND AFT CARGO COMPARTMENT FLOORBEAM CORRODED AT STA 1110, RBL 16 TO RBL 52. THE CORROSION WAS REMOVED AND A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-8.

Part: STRINGER — CORRODED (BS 580)

INSPECTION FOUND STRINGER 26L IN FORWARD CARGO COMPARTMENT CORRODED AT STA 580. THE CORROSION WAS REMOVED AND THE STRINGER WAS REPAIRED IAW SRM 53-10-3.

Part: SUPPORT — CORRODED (BS 480-720)

INSPECTION FOUND FLOORBOARD SUPPORT CORRODED ON UPPER AND LOWER SURFACES IN FORWARD CARGO COMPARTMENT ABOVE STRINGER 26L FROM STA 480 TO 720D. THE CORROSION WAS REMOVED, REPLACEMENT SECTIONS WERE FABRICATED AND INSTALLED IAW SRM 51-40-5, 51-10-0, 51-10-2 AND 51-10-6.

Part: SUPPORT — CORRODED (BS 720)

INSPECTION FOUND FLOORBOARD SUPPORT CORRODED IF FORWARD CARGO COMPARTMENT AT STA 720D, STRINGER 26L. THE CORRODED AREA WAS CUT OUT, A FILLER AND DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-2.

Part: ANGLE — CRACKED (BS 580)

INSPECTION FOUND A CRACK PROTRUDING PAST STOP DRILL IN ANGLE BELOW FLOOR SUPPORT AT STA 580 ABOVE STRINGER 28L. THE CRACK WAS STOP DRILLED, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-3.

Part: SUPPORT — CORRODED (BS 480-720D)

INSPECTION FOUND FLOORBOARD SUPPORT CORRODED ON UPPER AND LOWER SURFACES IN FORWARD CARGO COMPARTMENT ABOVE STRINGER 26R FROM STA 480-720D. THE FLOOR SUPPORT WAS REMOVED AND THE CORROSION WAS CLEANED, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-10-6, 51-10-1, 51-30-2 AND 51-10-2.

Part: FLOORBEAM — CORRODED (BS 1068)

INSPECTION FOUND CORROSION ON CABIN FLOORBEAM AT STA 1068, RBL 48. THE FLOORBEAM WAS REMOVED AND A NEW PART WAS FABRICATED AND INSTALLED IAW SRM 51-30-1.

Part: ANGLE — CRACKED (BS 332)

INSPECTION FOUND A .50 INCH CRACK BETWEEN BOLTS OF UPPER RIB CAP ANGLE AT RT WING LEADING EDGE, STA 332. A REPLACEMENT ANGLE WAS FABRICATED AND INSTALLED IAW SRM'S 51-40-3, 51-8-0, AND 51-30-2.

Part: FLOOR BEAM — CORRODED (BS 1130)

INSPECTION FOUND HORIZONTAL LEG OF AFT CARGO FLOORBEAM CORRODED AT STA 1130, RBL ZERO TO RBL 56. THE CORROSION WAS REMOVED IAW SRM 51-10-6. THE FLOORBEAM WAS REPAIRED IAW ECRA 5330-03333.

Part: STRINGER — CORRODED (BS 480-500)

INSPECTION FOUND STRINGER 28L CORRODED IN FORWARD CARGO COMPARTMENT BETWEEN BS 480 AND 500. THE CORRODED AREA WAS CUT OUT, A STRINGER AND SPLICE WERE FABRICATED AND INSTALLED IAW 51-20-2.

Part: BRACKET — CRACKED (BS 940)

INSPECTION FOUND A CRACK ON ANGLE BRACKET IN LT MLG WHEEL WELL AT STA 940, STRINGER 18A. THE BRACKET WAS REMOVED AND REPLACED IAW SRM 51-10-1 AND 51-30-2.

Part: SUPPORT — CRACKED (BS 480)

INSPECTION FOUND FORWARD CARGO COMPARTMENT FLOORBOARD SUPPORT CRACKED AT STA 480. THE CRACKED AREA WAS CUT OUT, A FILLER AND DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-3.

Part: BRACKET — CRACKED (BS 940)

INSPECTION FOUND BRACKET CRACKED IN RT MLG WHEEL WELL AT STA 940, STRINGER 18A. THE BRACKET WAS REMOVED AND REPLACED IAW SRM 51-10-2, 51-40-5 AND 51-10-6.

Part: ANGLE — CRACKED (BS 480)

INSPECTION FOUND LOWER ANGLE OF FORWARD CARGO FORWARD BULKHEAD PANEL CRACKED AT STA 480 ABOVE STRINGER 27. THE ANGLE WAS REMOVED AND THE CRACK WAS STOP DRILLED, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-3 AND THE ANGLE WAS REINSTALLED.

Part: ANGLE — CRACKED (WS 338)

INSPECTION FOUND A 1.5 INCH CRACK IN UPPER ANGLE JUST FORWARD OF FRONT SPAR AT LT WING LEADING EDGE RIB, STA 338. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-40-3.

Part: STOP PLATE — CORRODED (CARGO DOOR)

INSPECTION FOUND RIVETS PULLING THROUGH AND BULGING UNDER STOP PLATE INSIDE C-2 DOOR AT AFT PRESSURE RELIEF DOOR. THE STOP PLATE WAS REMOVED AND REPLACED IAW SRM 51-30-2, 51-10-1 AND 51-10-6.

Part: STOP PLATE — CORRODED (CARGO DOOR)

INSPECTION FOUND RIVET PULLING THROUGH AND SLIGHT BULGING UNDER STOP PLATE INSIDE C-2 DOOR AT FORWARD PRESSURE RELIEF DOOR. THE STOP PLATE WAS REMOVED AND REPLACED IAW SRM 51-40-1.

Part: FLYING DOOR — CRACKED (RT MLG)

INSPECTION FOUND RT MLG FLYING DOOR CRACKED AT AFT SECTION LOWER CORNER NEXT TO SEAL RETAINER. THE CRACK WAS STOP DRILLED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-4.

Part: SKIN — DENTED (RT TE FLAP)

INSPECTION FOUND TWO DENTS ON LOWER SURFACE OF RT OUTBOARD FLAP AFT SEGMENT. THE DENTED AREAS WERE CUT OUT. FILLERS AND CORE WERE FABRICATED AND A HOT BOND REPAIR WAS ACCOMPLISHED IAW SRM 51-40-6.

Part: RIB — CRACKED (RT WING)

INSPECTION FOUND A .50 INCH CRACK IN BOTTOM OF RIB INSIDE OF RIGHT NAV LIGHT COMPARTMENT (RT WING TIP). THE RIB WAS REMOVED . A NEW RIB WAS FABRICATED AND INSTALLED IAW SRM'S 51-10-1 AND 51-40-2. A DOUBLER WAS ALSO INSTALLED TO REPAIR CRACKED WEB IN SAME AREA.

Part: SKIN — CRACKED (RT HORIZ STAB)

INSPECTION FOUND INBOARD LEADING EDGE OF RT HORIZONTAL STABILIZER DENTED. A HFEC INSPECTION FOUND A .5 INCH CRACK. THE CRACKED AND DENTED AREA WAS CUT OUT, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 55-10-3.

Part: SKIN — DENTED (BS 1313)

INSPECTION FOUND RT FUSELAGE SKIN DENTED JUST ABOVE ANTI- HIJACK VANE AT STA 1313. THE DENTED AREA WAS CUT OUT AND A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.

Part: SKIN — CRACKED (RT ELEVATOR)

INSPECTION FOUND CONNECTING CRACKS COVERING AN AREA OF APPROXIMATELY 4 BY 8 IN LOWER INBOARD SKIN OF RT ELEVATOR. THE SKIN PANEL WAS REMOVED, A REPAIR DOUBLER WAS INSTALLED IAW SRM 55-20-3, FIGURE 5 AND THE PANEL WAS REINSTALLED.

Part: BRACKET — CRACKED (NR 6 LE FLAP)

INSPECTION FOUND LOWER OUTBOARD RADIUS OF NR 6 KRUGER FLAP ACTUATOR MOUNT BRACKET CRACKED.

Part: SKIN — BENT (RT SERVICE DR)

INSPECTION FOUND RT SERVICE DOOR SKIN BENT AT BOTH HINGES. THE SKIN AT UPPER HINGE CUTOUT WAS STRAIGHTENED AND NO CRACKS WERE FOUND. THE LOWER HINGE CUTOUT WAS CRACKED AND THE CRACK WAS ROUTED OUT. A FILLER AND DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 52-00-3, FIGURE 3.

Part: SKIN — SEPARATING (RT ELEVATOR)

INSPECTION FOUND RT ELEVATOR SEPARATING JUST OUTBOARD OF TAB TRAILING EDGE. THE AREA WAS SMOOTHED AND A BONDING REPAIR WAS INSTALLED IAW SRM 51-20-3.

Part: SKIN — DENTED (BS 1000)

INSPECTION FOUND LT FUSELAGE SKIN DENTED AT STA 1000, BETWEEN STRINGER 17 AND 18. THE DENTED AREA WAS CUT OUT, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.

Part: HYD LINE — LEAKING (LE FLAPS)

THE A-SYSTEM HYDRAULIC FLUID QUANTITY DROPPED TO ZERO ON FINAL APPROACH TO EWR. THE FLUID LOSS WAS ACCOMPANIED BY ILLUMINATION OF HYDRAULIC SYSTEM LOW PRESSURE LIGHTS. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND A LEAK IN THE LEADING EDGE SLAT HYDRAULIC PRESSURE LINE LOCATED IN AC BAY SIDE OF FORWARD WHEELWELL. A FLEX LINE REPAIR WAS INSTALLED PER CONTINENTAL AIRLINES GENERAL MAINTENANCE MANUAL 10-799-78, PAGE 14. A DIP WAS ISSUED TO INSTALL A PERMANENT LINE WITHIN 1200 HOURS OR 500 FLIGHTS, WHICHEVER COMES FIRST.

Part: MOTOR — LEAKING (FLAP ACTUATOR)

THE A-SYSTEM HYDRAULIC QUANTITY DROPPED TO ZERO WHILE EN ROUTE. THE LOSS WAS ACCOMPANIED BY ILLUMINATION OF THE LOW PRESSURE LIGHT AND LEADING EDGE FLAP AMBER LIGHT. THE NR 1 KREUGER FLAP WAS SHOWING UNLOCKED ON AUX PANEL. MAINTENANCE FOUND THE OUTBOARD HYDRAULIC FLAP ACTUATOR MOTOR LEAKING. THE FLAP ACTUATOR MOTOR WAS REMOVED AND REPLACED, LEAK AND OPERATIONAL CHECKS WERE GOOD. IN ADDITION, BOTH THE NR 1 AND NR 2 HYDRAULIC ENGINE DRIVEN PUMPS WERE REMOVED AND REPLACED AS A PRECAUTIONARY MEASURE.

Part: FRAME — WORN (BS 1352.46)

INSPECTION FOUND WORN AREAS IN FRAME OUTER CHORD ON RT SIDE OF B.S. 1352.46. THE FRAME CHORD WAS REPAIRED IAW ECRA 5310-03270 AND SRM 51-10-2.

Part: LIGHT MODULE — SHORTED (COCKPIT)

FLT NR 1422 - ATL - THE NOSE GEAR DOOR LIGHT ON SECOND OFFICERS PANEL AND THE DOOR LIGHT ON FORWARD PANEL REMAINED ILLUMINATED AFTER GEAR RETRACTION. THE GEAR WAS CYCLED, BUT THE LIGHT REMAINED ON. THE AIRCRAFT WAS RETURNED TO ATL WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE COCKPIT 'DOORS' LIGHT MODULE SHORTED. THE LIGHT MODULE WAS REMOVED AND REPLACED. A DOOR WARNING SYSTEM TEST WAS PERFORMED IAW MM 32-62-0 AND OPERATION CHECKED GOOD. (M)

Part: SEQUENCE VALVE — LEAKING (RT MLG)

EWR - FLT 0358 - THE RT MLG DOOR WOULD OPEN WHEN GEAR HANDLE WAS PLACED FROM UP TO OFF. MAINTENANCE FOUND THE RT MLG LOCK OPERATED SEQUENCE VALVE LEAKING. THE VALVE WAS REMOVED AND REPLACED IAW MM 32-32-41, PAGES 401-403. (X)

Part: DOOR ACTUATOR — INOPERATIVE (RT MLG)

FLT NR 475 - MCO - THE RIGHT GEAR DOOR LIGHT, ON SECOND OFFICERS PANEL AND RED GEAR DOORS LIGHT ON FORWARD PANEL, ILLUMINATED WHEN MOVING THE LANDING GEAR HANDLE FROM UP TO OFF AFTER TAKEOFF. WHEN MOVING THE HANDLE BACK TO UP THE LIGHT EXTINGUISHED AND THE SOUND OF A DOOR CLOSING COULD BE HEARD. MAINTENANCE FOUND THE RIGHT MLG DOOR ACTUATOR AT FAULT. THE DOOR ACTUATOR WAS REMOVED AND REPLACED IAW MM 32-32-81. OPERATIONAL AND LEAK CHECKS WERE GOOD. (M)