N17533

Part: SKIN — GOUGED (NR 1 L/E SLAT)

INSPECTION FOUND LT WING NR 1 SLAT INNER SKIN GOUGED. THE FASTENERS AND DAMAGED AREA WERE REMOVED IAW SRM 57-09, PAGE 35. A NEW DOUBLER, FILLER AND STRAPS WERE INSTALLED IAW SRM 57-09 PAGE 35 AND 51-30-2 PAGE 2.

Part: SKIN — DENTED (LT T/E FLAP)

INSPECTION FOUND LT AFT FLAP DENTED. A REPAIR DOUBLER WAS INSTALLED IAW SRM 57-01, FIGURE 3 AND 51-10-3.

Part: SKIN — DENTED (LT T/E FOREFLAP)

INSPECTION FOUND LEFT WING LEFT O/B FOREFLAP DENTED ON LEADING EDGE. THE LEFT O/B FOREFLAP WAS REMOVED AND REPLACED IAW MM 27-51-3.

Part: SKIN — BULGED (RT AILERON)

INSPECTION FOUND RT AILERON BULGING. THE AILERON WAS REMOVED, REPAIRED, AND REINSTALLED IAW MM 27-10-31.

Part: SUPPORT — CRACKED (WS 171)

INSPECTION FOUND LT FLAP FIXED VANE SUPPORT WORN WITH A .25 INCH CRACK AT STA XFLS 171. THE FIXED SUPPORT WAS REPLACED IAW MM 27-51-3, PAGE 201.

Part: LONGERON — DAMAGED (BS 1060)

INSPECTION FOUND HEAT DAMAGE ON LONGERONS 12R AND 13R AT STA 1060. THE DAMAGED LONGERON SECTIONS WERE REMOVED AND NEW LONGERONS AND SPLICES WERE INSTALLED IAW SRM 53-01, FIGURE 18.

Part: FRAME — CRACKED (BS 1060)

INSPECTION FOUND A .5 INCH CRACK IN FUSELAGE FRAME AT STA 1060 AT LONGERON 12R-12R ATTACH POINT. THE CRACKED AREA OF FRAME WAS CUT OUT IAW SRM 53-03. A NEW FRAME AND SPLICES WERE INSTALLED IAW SRM 51-01-8 AND 51-01, PAGE 1.

Part: SKIN — CRACKED (PASSENGER DOOR)

INSPECTION FOUND A .5 CRACK IN L-1 DOOR EXTERIOR SKIN AT FORWARD LOWER CORNER. A REPAIR WAS INSTALLED IAW SRM 52-03-00, FIGURE 37, 51-10-3, AND 51-30-2.

Part: SKIN — CRACKED (FUSELAGE)

INSPECTION FOUND A .375 INCH CRACK AND LOOSE RIVETS IN FUSELAGE SKIN ABOVE LEFT AFT NOSE WHEEL WELL DOOR AFT HINGE AREA. THE CRACKED AREA AND RIVETS WERE REMOVED IAW SRM 51-30-2. A DOUBLER WAS INSTALLED IAW SRM 53-05-00, PAGE 169 AND 51-10-3, PAGE 1.

Part: RIB — CRACKED (WS 410)

INSPECTION FOUND A .25 INCH CRACK IN RT WING L/E RIB AT XFS 410 I/B OF NR 4 SLAT O/B HINGE. THE CRACK WAS STOP DRILLED IAW SRM 57-01, PAGE 9. AN ANGLE REPAIR WAS INSTALLED IAW SRM 57-30-2 AND 57-01, PAGE 9.

Part: SPAR CAP — CRACKED (WS 164)

INSPECTION FOUND A 1.875 INCH CRACK IN RT WING LOWER SPAR CAP, UNDER THE I/B FLAP HINGE FITTING AT STA XRS 164.0. A REPAIR WAS INSTALLED IAW DOUGLAS DRAWING NR 506271.

Part: VANE — DELAMINATED (RT TE FLAP)

INSPECTION FOUND RT WING FLAP O/B FIXED VANE I/B UPPER END DELAMINATED WITH CORROSION AT TOP AND BOTTOM AREAS. THE RT O/B VANE WAS REMOVED AND REPLACED IAW MM 27-51-3.

Part: VANE — DELAMINATED (LT TE FLAP)

INSPECTION FOUND LT WING FLAP I/B FIXED VANE DELAMINATED ON LOWER SURFACE. THE LEFT I/B VANE WAS REMOVED AND REPLACED IAW MM 27-51-3.

Part: SUPPORT — CORRODED (BS 160)

INSPECTION FOUND FLOOR SUPPORT ANGLE CORRODED AT LT FORWARD ENTRY STA 160, LBL 54. THE FASTENERS WERE REMOVED FROM FLOOR SUPPORT ANGLE IAW SRM 51-30-2. A NEW ANGLE WAS INSTALLED IAW SRM 51-30-2, 51-30-3, AND 53-02-00.

Part: FRAME — CRACKED (AIRSTAIR DOORWAY)

AIRSTAIR DOOR CUTOUT LEFT SUPPORT FRAME CRACKED .75 BELOW AIRSTAIR OPEN/CLOSE FORWARD BRACKET ATTACH LEG, APPROX FS 1090. CUT DAMAGED AREA, FABRICATED, ALODINED, PRIMED AND INSTALLED REPAIR DOUBLER PER SRM 53-01.

Part: FITTING — CRACKED (CARGO DOOR)

FOUND INTERCOSTAL ANGLE FITTING UNDER UPPER FWD DOOR STOP CRACKED .5 INCH. REMOVED ANGLE, FABRICATED, TREATED, PRIMED AND INSTALLED PER SRM 51-10-2, 51-10-3 AND 51-30-2.

Part: SKIN — CORRODED (BS 332)

FUSELAGE LOWER SKIN AT APPROX STA 332 AT RT LONGERON 29 AREA HAS ONE POPPED RIVET AND BULGED. FABRICATED, TREATED, PRIMED, AND INSTALLED NEW FINGER DOUBLER PER SRM 51-00-00.

Part: SKIN — BENT (AFT CARGO DOOR)

AFT CARGO COMPARTMENT DOOR LOWER EXTERIOR SKIN EDGE BENT. CUT OUT BENT AREA AT AFT CARGO DOOR LOWER EDGE EXTERIOR SKIN AND INSTALLED DOUBLER REPAIR PER SRM 52-01.

Part: SWITCH — INOPERATIVE (LT MLG)

WHEN GEAR WAS EXTENDED FOR LANDING, NO GREEN LIGHTS WERE INDICATED FOR LT MLG. THE GEAR WAS CYCLED AND NORMAL INDICATIONS WERE RECEIVED. THE LT MLG DOWNLOCK SWITCH WAS REPLACED. OPERATION CHECKED GOOD WITH BOTH GREEN LIGHTS FOR LT GEAR ILLUMINATED.

Part: JAMB — CORRODED (CARGO DOOR)

INSPECTION FOUND BOTTOM SECTION OF FORWARD BAGGAGE BIN DOOR JAMB PAN CORRODED. A NEW DOOR JAMB PAN WAS INSTALLED IAW SRM 51-10-3, 51-30-2, AND 51-30-5.

Part: SKIN — CORRODED (BS 580)

INSPECTION FOUND INNER SKIN OF FUSELAGE CORRODED AT STA 580, LONGERON 29R. THE OUTER DOUBLER AND INNER DOUBLER WERE REMOVED AND REPLACED IAW SRM 51-30-0.

Part: SKIN — DENTED (BS 300)

INSPECTION FOUND A DENT IN FUSELAGE SKIN AT STA 300 BETWEEN LONGERON 26 TO 27R. A REPAIR WAS PERFORMED IAW SRM 53-04, FIGURE 12B.

Part: FITTING — CRACKED (CARGO DOOR)

INSPECTION FOUND AFT BAGGAGE BIN DOOR FITTING CRACKED IN TWO AREAS AT FORWARD EDGE OF DOOR, 5TH FRAME FROM TOP. THE CRACKS WERE .25 INCH LONG. THE FITTING WAS REMOVED AND REPLACED IAW SRM 51-30-5.

Part: FITTING — CRACKED (CARGO DOOR)

INSPECTION FOUND A .25 INCH CRACK IN AFT BAGGAGE BIN DOOR FITTING AT FORWARD EDGE OF DOOR SECOND FRAME FROM TOP. THE FITTING WAS REMOVED AND REPLACED IAW SRM 51-30-5.

Part: BULKHEAD TEE — CRACKED (BS 996)

AFT PRESSURE BULKHEAD T-CAP CRACKED STATION 996 LONG 1 TO 6 LEFT 20 RIGHT SIDE 19. REPLACED DAMAGED T-CAP SECTION PER EC/RA 5310-03531.

Part: CENTER TUBE — FRACTURED (NR 2 ENGINE)

THE NR 2 ENGINE LOST POWER AT FL 330 WHILE EN ROUTE. THE POWER LOSS WAS ACCOMPANIED BY A DROP IN OIL QUANTITY, VIBRATION, AND ODOR IN THE CABIN. THE AIRCRAFT WAS DIVERTED TO DFW WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE PRESSURE RATIO BLEED CONTROL VALVE LINE CRACKED, THE ENGINE OIL TANK EMPTY, AND METAL IN THE OIL FILTER. THE NR 2 ENGINE WAS REMOVED AND REPLACED. *S/D* SHOP FINDINGS REVEALED HPC CENTER TUBE FRACTURED AND BLEW OPEN. C9 DISC HAD SEVERE DAMAGE AND DEFORMATION DUE TO VERY HIGH TEMP. LPT SHAFT HAD SEVERE SCORING AT THE CENTER TUBE LOCATION.

Part: LONGERON — CRACKED (BS 980)

HOU - INSPECTION FOUND A .25 INCH CRACK IN LONGERON 17 AT RIGHT AFT LAV, STA 980. THE CRACKED SECTION OF LONGERON WAS REMOVED AND REPLACED IAW SRM 53-02, FIGURE 2A, SRM 51-30-2, AND SRM 51-30-5. (X)

Part: BLKHD ANGLE — CRACKED (AFT PRESS BLKHD)

HOU - INSPECTION FOUND A .50 INCH CRACK IN OUTBOARD AFT PRESSURE BULKHEAD FORMER ATTACH ANGLE AT TEE CAP. THE CRACK WAS STOP DRILLED. A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-01, FIGURE 2. (X)

Part: LONGERON — CRACKED (BS 965)

HOU - INSPECTION FOUND A .50 INCH CRACK IN LONGERON 14L AT STA 965 BULKHEAD. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIGURE 2. (X)

Part: FLOOR BEAM — CRACKED (BS 617)

HOU - INSPECTION FOUND A 1 INCH CRACK IN RIGHT SIDE FLOOR BEAM WEB AT STA 617. THE END OF WEB WAS CUT OFF AND A NEW WEB WAS SPLICED IAW SRM 53-01, FIGURE 4. (X)

Part: BLKHD STIFFENER — CRACKED (FWD BULKHEAD)

HOU - INSPECTION FOUND A 1 INCH CRACK ON FORWARD BULKHEAD VERTICAL STIFFENER. THE CRACK WAS STOP DRILLED. A DOUBLER REPAIR WAS INSTALLED IAW SRM 53-01, FIGURE 2, SHEET 4. (X)

Part: SKIN — CRACKED (FUSELAGE)

HOU - INSPECTION FOUND A .25 INCH CRACK IN FUSELAGE SKIN AT FORWARD SERVICE DOOR JAMB UPPER FORWARD CORNER AND A .25 INCH CRACK AT THE LOWER AFT CORNER. DOUBLER REPAIRS WERE INSTALLED IAW SRM 53-05, FIGURE 38. (X)

Part: ANGLE — CORRODED (BS 160-200)

HOU - INSPECTION FOUND FLOOR SUPPORT ANGLE CORRODED AT STA 160 - STA 200. A NEW FLOOR SUPPORT ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-10-1. (X)

Part: BELT FRAME — CRACKED (BS 1109)

HOU - INSPECTION FOUND A .75 INCH CRACK IN BELT FRAME AT STA 1109, LONGERON 1. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-11-4, FIGURE 4. (X)

Part: LONGERON — CRACKED (BS 1076)

HOU - INSPECTION FOUND A 1.25 INCH CRACK AT FORWARD END OF LONGERON 13R. A NEW SPLICE AND LONGERON WAS INSTALLED IAW SRM 51-10-3. (X)