N18544

Part: UPLATCH MECH — OUT OF ADJUST (RT MLG)

THE RT MLG UNSAFE LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION LEAVING IAH. THE GEAR WAS CYCLED AND THE LIGHT EXTINGUISHED, BUT THE GEAR DOOR OPEN LIGHT REMAINED ON. THE AIRCRAFT WAS RETURNED TO IAH. BOTH THE LT AND RT MLG DOORS WERE DAMAGED ON LANDING. THE MLG DOORS WERE REMOVED AND REPLACED IAW MM 32-12-1. TROUBLESHOOTING FOUND THE RT MLG UPLATCH MECHANISM OUT OF ADJUSTMENT. THE UPLATCH MECHANISM WAS ADJUSTED IAW MM 32-31-4. A GEAR SWING WAS PERFORMED AND ALL OPERATION CHECKED GOOD.

Part: WIRE — BROKEN (RT MLG DOOR)

THE RT MLG UNSAFE LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION. THE GEAR WAS CYCLED AND THE LIGHT EXTINGUISHED, BUT THE GEAR DOOR OPEN LIGHT CAME ON. THE GEAR WAS CYCLED TO UP AND THE NOSE GEAR UNSAFE LIGHT ILLUMINATED. THE GEAR INDICATIONS WERE NORMAL AFTER CYCLING THE GEAR THE THIRD TIME. MAINTENANCE FOUND WIRES TO RT MLG DOOR UP SWITCH BROKEN. THE RT MLG DOOR UP SWITCH CANNON PLUG WAS REPLACED. THE NOSE GEAR POSITION SWITCH CANNON PLUG PINS WERE CLEANED. A GEAR SWING WAS PERFORMED AND ALL OPERATION AND INDICATIONS CHECKED GOOD.

Part: SKIN — DENTED (NR 1 LE SLAT)

INSPECTION FOUND LT LEADING EDGE SLAT NR 1 SKIN DENTED AT STA XIS 136 AND XIS 132. REPAIRED IAW SRM 57-09, FIGURE 10 AND 10A.

Part: SKIN — CORRODED (BS 680-756)

INSPECTION FOUND LT AND RT WHEEL WELL KEEL SKIN AREA CORRODED AT STA 680 TO 756. THE CORRODED SECTION OF KEEL SKIN WAS REMOVED IAW SRM 53-04, FIGURE 42. A NEW SECTION OF SKIN WAS FABRICATED AND INSTALLED IAW SRM 51-10-4, 51-10-3, 51-30-2, AND 53-04, FIGURE 42.

Part: SKIN — DENTED (WS 530)

INSPECTION FOUND A DENT IN LT LOWER WING SKIN AT XRS 530. THE AREA WAS REPAIRED IAW SRM 57-03, PAGE 23.

Part: SEAT TRACK — CORRODED (BS 237/803)

INSPECTION FOUND SEAT TRACKS CORRODED AT STA 237 RT O/B AND STA 803-845, LBL 48. THE CORRODED SECTIONS OF SEAT TRACKS WERE CUT OUT. NEW SEAT TRACKS, SPLICES, AND PLATES WERE FABRICATED AND INSTALLED IAW SRM 53-05, FIGURE 4F AND 51-30-1.

Part: FLOOR PANEL — DELAMINATED (BS 756-680)

INSPECTION FOUND FLOOR PANEL DELAMINATED AT STA 756 TO 680. A NEW FLOOR PANEL WAS FABRICATED AND INSTALLED IAW SRM 53-05 AND 51-10-3.

Part: SKIN — CRACKED (CARGO DOOR)

INSPECTION FOUND A 1 INCH CRACK COMING FROM RIVET HOLE IN FORWARD CARGO DOOR AT STA 425. THE CRACK WAS STOP DRILLED, A REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW SRM 52-03, 52-31-0 AND 51-70-2.

Part: SKIN — DAMAGED (BS 522)

INSPECTION FOUND LIGHTNING STRIKE DAMAGE TO SKIN BELOW FLOOR LINE AT WING SCAN LIGHT AT STA 522. A DOUBLER AND FINGER DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 53-04, FIGURE 38.

Part: INTERCOSTAL — CRACKED (BS 996-1019)

INSPECTION FOUND TWO CRACKS IN INTERCOSTAL AT STA 996 TO 1019, RBL 20. THE CRACKS WERE STOP DRILLED, AN ANGLE STRAP WAS FABRICATED AND INSTALLED IAW SRM 53-01, 51-30-2, AND 51-30-0.

Part: SUPPORT — CRACKED (BS 294)

INSPECTION FOUND A .25 INCH CRACK IN FORWARD CARGO COMPARTMENT FLOOR SUPPORT AT STA 294, STRINGER 27R. THE FLOOR SUPPORT WAS REMOVED IAW SRM 51-30-2 AND THE CRACK WAS STOP DRILLED IAW ECRA 5320-01263. AN ANGLE REPAIR WAS FABRICATED AND INSTALLED IAW ECRA 5320-01263, SRM 51-10-3, 51-30-2, 51-30-5, AND 51-30-8.

Part: STRINGER — CORRODED (BS 598)

INSPECTION FOUND STRINGER/FRAME CORRODED AROUND FASTENERS AT KEEL BOX INTERIOR, STA 598, STRINGER 29R. THE KEEL BOX WEB WAS REMOVED. TWO REPAIR ANGLES WERE FABRICATED IAW SRM 53-01, FIGURE 2 AND 51-10-2A. THE ANGLES AND KEEL BOX PANEL WERE INSTALLED IAW SRM 51-10-4, 51-30-5, 53-01, FIGURE 2, AND 51-30-1.

Part: FLOOR PANEL — SEPARATED (BS 579-680)

INSPECTION FOUND FLOOR PANEL SKIN SEPARATING AT STA 579 TO 680. A NEW FLOOR PANEL WAS FABRICATED AND INSTALLED IAW SRM 53-21-0, PAGE 11 AND 53-05, PAGE 122B.

Part: FLOORBEAM — CORRODED (BS 980)

INSPECTION FOUND FLOORBEAM CORRODED AT STA 980, RBL 21 AND RBL 34. THE CORRODED AREAS WERE CUT OUT, AN ANGLE, FILLER, AND SHIM WERE FABRICATED AND INSTALLED IAW SRM 53-05, FIGURE 20A.

Part: ANGLE — CORRODED (BS 996)

INSPECTION FOUND FLOOR GILL LINING ATTACH ANGLE CORRODED IN AFT CARGO COMPARTMENT AT STA 996, BL 0 TO LBL 6. THE CORRODED SECTION OF ANGLE WAS CUT OUT. TWO L-ANGLES AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 53-01, FIGURE 2, 51-10-4, 51-10-3, AND 51-30-2.

Part: FLOORBEAM — CRACKED (BS 351)

INSPECTION FOUND A 4 INCH CRACK IN RADIUS OF FORWARD CARGO FLOORBEAM AT STA 351, BL 0. AN L-ANGLE WAS FABRICATED AND INSTALLED IAW SRM 53-05, FIGURE 78.

Part: FLOOR PANEL — CORRODED (BS 313-357)

INSPECTION FOUND FORWARD PIT FLOOR PANEL CORRODED AND DELAMINATED AT STA 313 TO 357. A NEW FLOOR PANEL WAS FABRICATED AND INSTALLED IAW ECRA 2551-01010.

Part: FLOOR PANEL — BROKEN (BS 522-579)

INSPECTION FOUND FLOOR PANEL BROKEN AT STA 522 TO 579. THE FLOOR PANEL WAS REMOVED IAW MM 53-20-0. A NEW FLOOR PANEL WAS FABRICATED AND INSTALLED IAW SRM 53-20-0 AND 53-21-0.

Part: ANGLE — CRACKED (DORSAL FIN)

INSPECTION FOUND A 2 INCH CRACK IN ATTACH ANGLE AT RT DORSAL FIN LOWER FORWARD ACCESS PANEL. THE ANGLE WAS REMOVED IAW SRM 51-30-2. A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-10-4 AND 51-30-2.

Part: CLIP — CRACKED (WS 429)

INSPECTION FOUND RT WING LEADING EDGE RIB CLIP CRACKED JUST INBOARD OF WS XOS 429. THE CRACK WAS STOP DRILLED AND A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-10-2, 51-10-3, 51-10-4, AND 51-30-5.

Part: BRACKET — CRACKED (WS 332)

INSPECTION FOUND A .25 INCH CRACK AT BOLT HOLE OF LT WING SUPPORT BRACKET, XRS 332. THE BRACKET WAS REMOVED AND A NEW BRACKET WAS FABRICATED AND INSTALLED IAW SRM 51-30-1, 51-10-2, 51-10-2A, AND 51-10-3.

Part: CUSP — CORRODED (BS 986)

INSPECTION FOUND CUSP CORRODED AT FS 986, RBL 62. THE CORRODED AREA OF CUSP WAS CUT OUT. A REPAIR CUSP AND L-ANGLE WERE FABRICATED AND INSTALLED IAW SRM 53-05, 51-20-2, AND 51-10-30.

Part: FRAME — DAMAGED (WINDOW)

INSPECTION FOUND LIGHTNING STRIKE DAMAGE ON WINDOW FRAMES 28 TO 30R. REPAIRED IAW ECRA 5330-02683.

Part: END CAPS — CORRODED (BS 996)

INSPECTION FOUND LONGERON 20R AND 21R END CAPS CORRODED IN AFT CARGO COMPARTMENT AT STA 996. THE END CAPS WERE REMOVED IAW SRM 51-30-2. NEW END CAPS WERE FABRICATED AND INSTALLED IAW SRM 51-10-4 AND 51-30-2.

Part: WEB — CORRODED (BS 237)

INSPECTION FOUND WEB CORRODED AT CUSP LINE FORWARD AND AFT OF FRAME FITTING AT STA 237 ON LT SIDE. THE CORRODED AREA OF WEB WAS CUT OUT, A REPAIR WEB AND L-ANGLE WERE FABRICATED AND INSTALLED IAW SRM 51-30-2, 51-10-3, AND 53-01, PAGE 9.

Part: FLOOR PANEL — CRACKED (BS 427-522)

INSPECTION FOUND FORWARD CARGO PIT FLOOR PANEL CRACKED AT ST 427 TO 522. A NEW FLOOR PANEL WAS FABRICATED AND INSTALLED IAW ECRA 2551-01010.

Part: FLOOR PANEL — DELAMINATED (BS 218-313)

INSPECTION FOUND FORWARD PIT FLOOR PANEL DELAMINATED AT STA 218 TO 313. A NEW FLOOR PANEL WAS FABRICATED AND INSTALLED IAW ECRA 2551-01010.

Part: FLOOR — CORRODED (BS 945-965)

INSPECTION FOUND CABIN FLOOR PANEL CORRODED FORWARD OF RT AFT LAV AT STA 945 TO 965, RBL 44. THE FLOOR PANEL WAS REMOVED AND THE CORRODED SECTIONS WERE CUT OUT. REPAIRS WERE FABRICATED AND INSTALLED IAW SRM 53-05, FIGURE 1, 51-10-3, AND 51-30-2. THE FLOOR PANEL WAS REINSTALLED IAW SRM 51-30-1.

Part: LONGERON — CRACKED (BS 965)

INSPECTION FOUND LONGERON 16R CRACKED AT UPPER FLANGE AND LONGERON 16L CRACKED OUT OF UPPER AND LOWER ATTACH CLIP FASTENERS, STA 965. THE CRACKED AREAS OF LONGERONS WERE REMOVED IAW SRM 51-30-2. LONGERONS AND SPLICES WERE FABRICATED AND INSTALLED IAW SRM 53-02, FIGURE 18, 51-30-5, AND 51-10-3.

Part: FITTING — CRACKED (BS 756)

INSPECTION FOUND A 7 INCH CRACK IN KEEL BEAM FITTING AT BS 756, LONGERON 30. THE FITTING WAS REMOVED AND A NEW FITTING WAS FABRICATED AND INSTALLED IAW SRM 51-10-4, 51-30-5 AND 51-30-1, PAGE 6.

Part: LONGERON — CRACKED (BS 945-980)

INSPECTION FOUND THREE CRACKS IN LONGERON 17R AT FRAME ATTACH HOLES FROM STA 945 TO 980. THE CRACKS WERE .5 TO 1 INCH LONG. THE CRACKED AREAS OF LONGERON WERE REMOVED IAW SRM 53-02, FIGURE 18. LONGERON REPAIRS WERE FABRICATED AND INSTALLED IAW SRM 53-02, FIGURE 18, 51-10-3, 51-30-1, 51-30-2, AND 51-30-5.

Part: FLOOR — CORRODED (BS 229-294)

INSPECTION FOUND FLOOR PANEL CORRODED AT STA 229 TO 294, BL 0. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS FABRICATED AND INSTALLED IAW SRM 53-21-0, 53-10-4, 51-20-2, 51-10-3, AND 51-30-2.

Part: DOUBLER — BULGED (BS 1019)

INSPECTION FOUND DOUBLER BULGED WITH FASTENERS PULLING THROUGH AT STA 1019, LONGERON 19L. THE DOUBLER WAS REMOVED IAW SRM 51-10-2. A NEW DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-2, 51-30-2, AND 53-04, FIGURE 12B.

Part: CHANNEL — CRACKED (BS 389)

INSPECTION FOUND A .5 INCH CRACK AROUND FASTENER HOLE IN CHANNEL AT FORWARD CARGO DOOR FRAME STA 389, S18R, RBL 52. THE CHANNEL WAS REMOVED IAW SRM 51-30-2 AND 51-30-5. A NEW CHANNEL WAS FABRICATED AND INSTALLED IAW SRM 51-10-4, 51-10-3, AND 51-30-2.

Part: SKIN — CORRODED (BS 945)

INSPECTION FOUND SKIN CORRODED AT AFT CARGO COMPARTMENT FRAME STA 945 BETWEEN LONGERON 25R AND 26R. THE CORRODED AREA WAS CUT OUT. A REPAIR DOUBLER, FINGER DOUBLER, AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 51-30-2, 51-10-3, AND 53-04, FIGURE 12, SHEET 6.

Part: FLOORBEAM — CORRODED (BS 965-996)

INSPECTION FOUND FLOORBEAM CORROSION AT STA 980, LBL 34, STA 996, LBL 27, AND STA 965, LBL 16. L-ANGLES AND FILLERS WERE FABRICATED AND INSTALLED AT EACH LOCATION IAW SRM 53-05, FIGURE 20A AND 51-10-3.

Part: FRAME — CRACKED (BS 256)

INSPECTION FOUND A .5 INCH CRACK IN RADIUS OF FORWARD CARGO COMPARTMENT FLOOR FRAME AT STA 256, S27L. THE CRACK WAS STOP DRILLED. AN L-ANGLE REPAIR WAS FABRICATED AND INSTALLED IAW ECRA 5320-01263 AND SRM 51-10-3.

Part: DOUBLER — CORRODED (BS 351)

INSPECTION FOUND DOUBLER CORRODED WITH FASTENERS PULLING THROUGH AT STA 351, LONGERON 30. A FINGER DOUBLER AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 51-10-2 AND 51-30-2.

Part: ANGLE — CRACKED (NR 2 PYLON)

INSPECTION FOUND NR 2 ENGINE PYLON INBOARD VERTICAL ATTACH ANGLE FORWARD OF WIRE BUNDLE CRACKED AT LOWER END. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-10-2, 51-10-3, 51-30-5, 54-04, FIGURE 10, AND MM 51-20-11.

Part: SUPPORT — CRACKED (BS 332)

INSPECTION FOUND A .5 INCH CRACK IN FORWARD CARGO COMPARTMENT FLOOR SUPPORT STRIP AT STA 332, S27L. THE CRACK WAS STOP DRILLED. AN L-ANGLE REPAIR WAS FABRICATED AND INSTALLED IAW ECRA 5320-01263.

Part: SUPPORT — CRACKED (BS 294)

INSPECTION FOUND A .25 INCH CRACK IN FLOOR SUPPORT AT STA 294, S28R, FORWARD CARGO COMPARTMENT. THE CRACK WAS STOP DRILLED. AN L-ANGLE WAS FABRICATED AND INSTALLED IAW ECRA 5320-01263.

Part: RIB — CRACKED (WS 516)

INSPECTION FOUND A 3.5 INCH CRACK IN LT WING LEADING EDGE RIB AT HI-LOK IN UNDERSIDE OF LEADING EDGE AT XOS 516. THE RIB WAS REMOVED IAW SRM 51-30-2. A REPAIR ANGLE WAS FABRICATED AND INSTALLED ON RIB IAW SRM 57-02, FIGURE 6 AND 51-10-3. THE RIB WAS REINSTALLED IAW SRM 51-30-2.

Part: SHEAR TIE — CRACKED (BS 945)

INSPECTION FOUND A .5 INCH CRACK IN SHEAR TIE ON MAIN FRAME AT FS 945 BETWEEN LONGERON 14R AND 15R. THE SHEAR TIE WAS REMOVED AND A NEW SHEAR TIE WAS FABRICATED AND INSTALLED IAW SRM 53-11-3, 51-10-4, AND 51-10-3.

Part: SKIN — CRACKED (BS 935)

INSPECTION FOUND A 1 CRACK IN FUSELAGE SKIN AT STA 935, LONGERON 25R, AFT OF CARGO DOOR OPENING. THE CRACKED AREA WAS REMOVED IAW SRM 53-05, FIGURE 80. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-4, 53-05, FIGURE 80, 51-10-3, 51-30-2, AND 51-30-5.

Part: SUPPORT — CRACKED (BS 313)

INSPECTION FOUND A 2 INCH CRACK EXTENDING FROM RADIUS TO FASTENER HOLE IN CABIN FLOOR SUPPORT AT STA 3113, BL 0. THE CRACK WAS STOP DRILLED. AN ANGLE REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-01, FIGURE 2, 51-10-4, 51-10-3, AND 51-30-2.

Part: FLOOR — CORRODED (BS 960-965)

INSPECTION FOUND CABIN FLOOR PANEL CORRODED AND PUNCTURED AT STA 960-965, BL 0 TO RBL 21.5. A NEW FLOOR PANEL WAS FABRICATED AND INSTALLED IAW SRM 51-70-1 AND 53-05, PAGE 122B.

Part: SKIN — CRACKED (BS 560)

INSPECTION FOUND A 1.25 CRACK IN FUSELAGE SKIN AT STA 560, STRINGER 18L. THE CRACKED SKIN WAS REMOVED AND A DOUBLER REPAIR WAS INSTALLED IAW ECRA 5330-02481.

Part: SUPPORT — CRACKED (BS 294)

INSPECTION FOUND TWO .5 INCH CRACKS IN FLOOR SUPPORT IN FORWARD CARGO COMPARTMENT AT STA 294, STRINGER 27L. THE CRACKS WERE STOP DRILLED IAW ECRA 5320-01263. A DOUBLER WAS FABRICATED AND INSTALLED IAW ECRA 5320-01263.

Part: BRACKETS — CRACKED (LT WING)

INSPECTION FOUND LT WING LEADING EDGE FRAMES HAD CRACKED BRACKETS BETWEEN STA 383 AND 370, BETWEEN STA 414 AND 426, STA 506, AND STA 551. THE CRACKS WERE .25 TO .5 INCH LONG. THE CRACKED BRACKETS WERE REMOVED AND NEW BRACKETS WERE FABRICATED AND INSTALLED IAW SRM 51-30-2, 51-30-3, 51-30-5, 51-10-2, AND 51-10-3.

Part: INTERCOSTAL — CRACKED (BS 448)

INSPECTION FOUND A 1.5 INCHCRACK IN INTERCOSTAL IN FORWARD CARGO PIT AT STA 448, LONGERON 29R. THE INTERCOSTAL WAS REMOVED AND REPLACED IAW SRM 51-30-5.

Part: SUPPORT — CRACKED (BS 236)

INSPECTION FOUND A 1 INCH CRACK IN FLOOR SUPPORT IN FORWARD CARGO COMPARTMENT AT STA 236, STRINGER 27R. THE CRACK WAS STOP DRILLED IAW ECRA 5320-01263. AN ANGLE WAS FABRICATED AND INSTALLED IAW ECRA 5320-01263.

Part: LONGERON — CRACKED (BS 945)

INSPECTION FOUND LONGERON 17L CRACKED OUT OF UPPER AND LOWER FRAME ATTACH HOLES AT FS 945. THE LONGERON WAS REMOVED IAW SRM 51-10-2. A NEW LONGERON WAS FABRICATED AND INSTALLED IAW SRM 53-02, FIGURE 18, 51-10-4, 51-10-3, AND 51-30-5.

Part: VENT BOX — LEAKING (LT WING TIP)

THE CREW OBSERVED FUEL LEAKING FROM LT WING OUTBOARD OF AILERON WHILE EN ROUTE. THE AIRCRAFT WAS RETURNED TO CLE WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND FUEL LEAKING AT LT WING TIP ON FORWARD SPAR BY VENT BOX. THE VENT BOX AND AREA WERE RESEALED IAW SRM 51-23-00. LEAK CHECKS WERE GOOD.

Part: CKT BREAKER — FAILED (LEFT AC BUS)

THE B-PHASE CIRCUIT BREAKER ON LEFT AC BUS POPPED FOLLOWED BY ALL FORWARD LT, RT AND CENTER FUEL BOOST PUMP CB. THE A-PHASE CIRCUIT BREAKER ON RADIO RACK COOLING FAN POPPED AND LIGHTS ON RT SIDE IN CABIN WENT OUT AS WELL AS CAPT'S INSTRUMENT LIGHTS, VOR AND RADIOS. THE AIRCRAFT WAS RETURNED TO CLE. A CHECK OF ALL BOOST PUMPS, RADIO RACK COOLING FAN AND ALL MISC LIGHTS/EQUIPMENT POWERED BY LT AC BUS WAS PERFORMED AND NO DEFECTS WERE NOTED. A CHECK OF ALL GENERATORS PERFORMED WITH NO PROBLEMS. MAINTENANCE FOUND THE LT AC BUS B-PHASE CB AT FAULT. THE B-PHASE CB WAS REMOVED AND REPLACED. ALL AC DISTRIBUTION CHECKED GOOD.

Part: INTERCOSTAL — CRACKED (BS 148-160)

INSPECTION FOUND A 1 INCH CRACK IN INTERCOSTAL BETWEEN STA 148-160, LONGERON 11R. THE INTERCOSTAL WAS REPAIRED IAW SRM 53-05, FIGURE 100.

Part: LONGERON — CRACKED (BS 658)

INSPECTION FOUND A CRACK IN LONGERON 6L AT STA 658. A NEW LONGERON WAS INSTALLED IAW SRM 53-02.

Part: LONGERON — CRACKED (BS 160-200)

INSPECTION FOUND FOUR 1.25 INCH CRACKS IN LONGERON 4L FROM STA 160-200. THE CRACKED AREAS WERE CUT OUT AND A NEW SECTION OF LONGERON WAS SPLICED IN IAW SRM 53-02, FIGURE 2.

Part: LONGERON — CRACKED (BS 160)

INSPECTION FOUND TWO 1.25 INCH CRACKS IN LONGERON 3L AT STA 160. THE CRACKED SECTION OF LONGERON WAS REMOVED AND A NEW SECTION WAS SPLICED IN IAW SRM 53-02, FIGURE 2.

Part: LONGERON — CRACKED (BS 200)

INSPECTION FOUND TWO 1.25 INCH CRACKS IN LONGERON 2L AT STA 200. THE CRACKED SECTION OF LONGERON WAS REMOVED AND A NEW SECTION WAS SPLICED IN IAW SRM 53-02, FIGURE 2.

Part: SKIN — CRACKED (BS 1038)

INSPECTION FOUND A 3 INCH CRACK IN FUSELAGE SKIN AT STA 1038, LT SIDE, ABOVE PYLON. THE AREA WAS REPAIRED IAW SRM 53-04.

Part: PAN — CRACKED (PAX DOOR)

INSPECTION FOUND A 1 INCH CRACK IN MAIN CABIN DOOR PAN AT LOWER HINGE AREA. A DOUBLER WAS FABRICATED AND INSTALLED IAW ECRA 5210-01262.

Part: BULKHEAD CLIPS — CRACKED (BS 996)

INSPECTION FOUND UPPER AND LOWER AFT PRESSURE BULKHEAD CLIPS CRACKED ON BOTH LT AND RT SIDES AT Z= 24, STA 996. THE CLIPS WERE REMOVED AND REPLACED IAW DOUGLAS DRAWING 9915558.

Part: CLIPS — CRACKED (BS 996)

INSPECTION FOUND THE UPPER AND LOWER AFT PRESSURE BULKHEAD CLIPS CRACKED ON BOTH THE LT AND RT SIDES AT Z= 14, STA 996. THE CLIPS WERE REMOVED AND REPLACED IAW DOUGLAS DRAWING 9915558.

Part: BULKHEAD CLIP — CRACKED (BS 996)

INSPECTION FOUND A .50 INCH CRACK IN THE LOWER AFT PRESSURE BULKHEAD CLIP ON RT SIDE AT Z= 48.5, STA 996. THE CLIP WAS REMOVED AND REPLACED IAW DOUGLAS DRAWING 9915558.

Part: CLIPS — CRACKED (BS 996)

INSPECTION FOUND UPPER AND LOWER AFT PRESSURE BULKHEAD CLIPS ON BOTH THE LT AND RT SIDES CRACKED AT Z= 34, STA 996. THE CLIPS WERE REMOVED AND REPLACED IAW SRM 51-60-0 AND DOUGLAS DRAWING 9915558.

Part: BULKHEAD CLIPS — CRACKED (BS 996)

INSPECTION FOUND UPPER AND LOWER AFT PRESSURE BULKHEAD CLIPS CRACKED ON LT SIDE AT Z= 48, STA 996. THE CLIPS WERE REMOVED AND REPLACED IAW DOUGLAS DRAWING 9915558.

Part: FITTING — CRACKED (PAX DOOR JAMB)

INSPECTION FOUND A 1.125 INCH CRACK IN MAIN CABIN DOOR JAMB INTERNAL FITTING FOR DOOR STOP. THE FITTING WAS REMOVED AND REPLACED IAW SRM 51-30-00.

Part: SUPPORT — CORRODED (CABIN)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT FORWARD SERVICE DOOR. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-10-03.

Part: KEEL BEAM — CRACKED (BS 622)

INSPECTION FOUND A CRACK IN RT SIDE OF KEEL BEAM AT STA 622. A DOUBLER WAS INSTALLED IAW SRM 53-05.

Part: FLR SUPPORT — CORRODED (CABIN)

INSPECTION FOUND FORWARD ENTRY FLOOR SUPPORT AT PANEL NR 12 AND NR 13 CORRODED. THE FLOOR SUPPORT WAS REPLACED IAW SRM 53-01.

Part: WEB — CORRODED (BS 935)

INSPECTION FOUND WEB CORRODED AT FORWARD SIDE OF AFT BAGGAGE BIN DOOR CUT OUT, STA 935. THE CORRODED AREA OF WEB WAS CUT OUT AND A DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 4.

Part: FLR SUPPORT — CORRODED (CABIN)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT FORWARD SIDE OF PANEL NR 7A, FORWARD ENTRY. A NEW FLOOR SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 51-30-0.

Part: LONGERON — CRACKED (BS 699)

INSPECTION FOUND A .1250 INCH CRACK IN LONGERON 5R AT STA 699. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIGURE 2.

Part: LONGERON — CRACKED (BS 699)

INSPECTION FOUND A .25 INCH CRACK IN LONGERON 1L AT STA 699. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIGURE 4.

Part: SUPPORT — CRACKED (BS 370)

INSPECTION FOUND A 1 INCH CRACK IN FLOOR SUPPORT AT STA 370, LONGERON 26L. THE FLOOR SUPPORT WAS REPAIRED IAW SRM 51-10-02.

Part: LONGERON — CRACKED (BS 699)

INSPECTION FOUND LONGERON 5L CRACKED AT STA 699. THE LONGERON WAS REPAIRED IAW SRM 53-02.

Part: FLR SUPPORT — CRACKED (BS 446)

INSPECTION FOUND A 1 INCH CRACK IN FORWARD BAGGAGE BIN FLOOR SUPPORT AT STA 446, LONGERON 29R. A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-2.

Part: LONGERON — CRACKED (BS 639)

INSPECTION FOUND A CRACK IN LONGERON 6L AT STA 639. A NEW LONGERON WAS INSTALLED IAW SRM 53-02.

Part: LONGERON — CRACKED (BS 756)

INSPECTION FOUND A CRACK IN LONGERON 2L AT STA 756. THE CRACKED SECTION OF LONGERON WAS REMOVED AND A NEW SECTION WAS SPLICED IN IAW SRM 53-02, FIGURE 2.

Part: LONGERON — CRACKED (BS 699)

INSPECTION FOUND A CRACK IN LONGERON 6L AT STA 699. A NEW LONGERON WAS INSTALLED IAW SRM 53-02.

Part: LATCH — OUT OF RIG (TAILCONE)

THE TAILCONE EXTERIOR RELEASE HANDLE PULLED LOW AT 20 POUNDS. TAILCONE LATCH ADJUSTMENT WAS PERFORMED AND PULL WAS WITHIN SPECIFICATIONS PER MM 53-50-3.

Part: LATCH — OUT OF ADJUST (TAILCONE)

THE TAILCONE EXTERIOR RELEASE HANDLE PULLED LOW AT 20 POUNDS. TAILCONE LATCH WAS ADJUSTED AND THE EXTERIOR RELEASE HANDLE PULL TESTED WITHIN SPECIFICATIONS AT 34 POUNDS PER MM 53-50-3.

Part: TIRE — CAP SEPARATED (RT MLG)

THE RT HYDRAULIC QUANTITY WENT TO ZERO IN FLIGHT AND THE PRESSURE STARTED DROPPING. THE RIGHT ENGINE PUMP WAS TURNED OFF. THE PRESSURE STAYED AT ZERO AND RIGHT QUANTITY ROSE TO 6. THE GEAR AND FLAPS WERE LOWERED USING THE LEFT SYSTEM AND THE AIRCRAFT LANDED NORMALLY. MAINTENANCE FOUND THE NR 3 TIRE CAP HAD SEPARATED RESULTING IN DAMAGE TO FOUR HYDRAULIC LINES. THE NR 3 TIRE AND HYDRAULIC LINES WERE REMOVED AND REPLACED. THE NR 3 AND NR 4 BRAKE LIMITERS WHICH THE DAMAGED HYDRAULIC LINES WENT TO WERE REPLACED AS A PRECAUTIONARY MEASURE. THE HYDRAULIC SYSTEM WAS SERVICED AND LEAK CHECKS WERE GOOD.

Part: ANTI-RETRACT LVR — OUT OF RIG (NLG)

FLT NR 9873 - STA 31J - THE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF FROM 31J (AERO CORP). THERE WAS NO GROUND SHIFT TO AIRBORNE. THE AIRCRAFT WAS RETURNED TO 31J WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE RE-RIGGED THE GROUND SENSE AND ANTI-RETRACTION LEVER IAW MM 32-23-1 AND OPERATION CHECKED GOOD. IN ADDITION, THE NLG POSITION INTERLOCK SWITCH WAS REMOVED AND REPLACED. A GEAR SWING WAS PERFORMED IAW MM 32-30 AND OPERATION CHECKED GOOD. (M)