N18833

Part: LONGERON — CORRODED (STA 160-170) · airframe 47,475 hrs · 22,897 cycles

INSPECTION FOUND LONGERON 30 CORRODED IN E&E COMPARTMENT AT STA 160-170. THE CORRODED SECTION OF LONGERON WAS REPLACED IAW SRM 53-02 AND 53-10-01.

Part: STRUT — LEAKING (NLG) · airframe 46,519 hrs · 22,417 cycles

THE NOSE GEAR RED UNSAFE LIGHT REMAINED ILLUMINATED AFTER TAKEOFF FROM MCO. THE GEAR WAS CYCLED, BUT THE HANDLE WOULD NOT RAISE PAST HALF WAY. THE AIRCRAFT WAS RETURNED TO MCO. MAINTENANCE FOUND THE NOSE STRUT DEFLATED DUE TO AN INTERNAL LEAK. A FULL NOSE STRUT REPACK WAS PERFORMED IAW MM 32-21-02. THE GEAR WAS CYCLED SEVERAL TIMES WITH NO DEFECTS NOTED.

Part: VALVE — DEFECTIVE (NOSE STRUT) · airframe 46,516 hrs · 22,415 cycles

THE NOSE GEAR DID NOT RETRACT AND WAS ACCOMPANIED BY THE RED GEAR UNSAFE LIGHT REMAINING ILLUMINATED AFTER TAKEOFF FROM MIA. THE GEAR WAS CYCLED, BUT THE HANDLE WOULD NOT COME UP. THE AIRCRAFT WAS DIVERTED TO MCO WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NOSE STRUT SCHRADER VALVE DEFECTIVE. THE SCHRADER VALVE WAS REMOVED AND REPLACED. THE NOSE GEAR WAS SWUNG SEVERAL TIMES WITH NO DEFECTS NOTED. A VISUAL INSPECTION OF THE GEAR FOUND NO OTHER DEFECTS.

Part: LONGERON — CORRODED (STA 1287) · airframe 45,729 hrs · 22,002 cycles

INSPECTION FOUND LONGERON 29R CORRODED AT STA 1287. THE CORRODED AREA OF LONGERON WAS REMOVED AND A NEW SECTION AND SPLICES WERE INSTALLED IAW SRM 53-02, FIGURE 18.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND SEAT TRACK CORRODED AT STA 1031 - 1136, LBL 54. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 51-30-2 AND 53-05, FIGURE 4F.

Part: SEAT TRACK — GOUGED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND SEAT TRACK GOUGED AT FS 1000 - 1025, LBL 54. THE SEAT TRACK WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW SRM 51-30-2 AND 53-05, FIGURE 4F.

Part: CABLE — OUT OF RIG (TAILCONE) · airframe 42,312 hrs · 20,123 cycles

THE FORCE REQUIRED TO RELEASE TAIL CONE EXCEEDED ALLOWABLE LIMIT. THE CABLES WERE CLEANED, LUBRICATED, AND ADJUSTED AND A FUNCTIONAL TEST CHECKED GOOD IAW MM 53-53-00 AND WORK CARD NR EA 5350-01063.

Part: CHANNEL — CORRODED (LAVATORY) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND FWD LAV FWD BULKHEAD LOWER SECTION WHERE IT TIES INTO FLOOR DELAMINATED AND CHANNEL HAD CORROSION. THE DELAMINATED AREA WAS REPAIRED BY APPLYING A FIBERGLASS OVERLAY REPAIR IAW SRM 51-70-1, PAGE 5. THE CORRODED CHANNEL WAS REMOVED AND REPLACED IAW SKETCH DHSK833-043, ECRA 2540-01313, AND SRM 51-40-3.

Part: SKIN — CRACKED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND A .5 INCH AND .375 INCH CRACK IN FUSELAGE SKIN AT STA 168, RBL 15 FORWARD OF R-1 SERVICE DOOR. THE INNER SKIN ACCESS PANEL FORWARD OF R-1 DOOR WAS REMOVED IAW SRM 51-30-1. THE CRACKED AREA WAS REMOVED. FILLER AND DOUBLER WERE INSTALLED IAW SKETCH DHSK233-507, SRM 51-30-2, AND 51-30-5. THE INNER SKIN ACCESS PANEL WAS REINSTALLED IAW SRM 51-30-1 AND ECRA 5330-02975.

Part: SKIN — DENTED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND AFT FUSELAGE EXTERNAL SKIN JUST FORWARD OF VENTRAL AIRSTAIR DENTED WITH A CREASE RUNNING HORIZONTAL AT STA 1361. THE DAMAGED AREA WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 53-01, FIGURE 4 AND 51-30-2.

Part: FLOORBOARD — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND RT FLOOR WEB OB OF OUTBOARD SEAT TRACK. CORRODED AT FS 900. THE CORRODED AREA WAS CUT OUT IAW SRM 53-01. A REPAIR WAS INSTALLED IAW SRM 53-01, FIGURE 2, 51-30-2, AND 51-10-3.

Part: WEB — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND LT CUSP WEB CORRODED AT FS 1022-1041. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 4 AND 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND CABIN FLOOR SUPPORT CORRODED AROUND FASTENER HOLES AT STA 160-200, RBL 42. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-30-1 AND 53-14-1, FIGURE 11.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND CABIN FLOOR SUPPORT CORRODED AROUND FASTENER HOLES AT STA 218, LBL 16 TO RBL 10. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-2, 53-14-01, FIGURE 11, AND 51-10-3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND CABIN FLOOR SUPPORT CORRODED AT STA 212, RBL 14. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-33-5, 53-14-1, AND 51-30-5.

Part: WEB — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND FORWARD CABIN SUBFLOOR WEB CORRODED AT STA 160 - 200, LBL 50. THE CORRODED AREA WAS REMOVED IAW SRM 51-30-2 AND 53-01, FIGURE 2. A FILLER AND DOUBLER WERE INSTALLED IAW SRM 53-12-1, FIGURE 11 AND 51-30-2.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND LONGERON 29L CORRODED IN AFT CARGO AREA AT STA 1287. THE CORRODED AREA WAS CUT OUT IAW SRM 53-02, FIGURE 18. REPAIR PARTS WERE INSTALLED IAW SRM 53-02, FIGURE 18, 51-30-1, AND 51-30-2.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND CARGO TRACK IN AFT CARGO PIT CORRODED AT STA 1322, LBL 26-28. REPAIR DOUBLERS WERE INSTALLED IAW 53-01 AND 51-10-0.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND CABIN THRESHOLD FLOOR SUPPORT CORRODED AT L-1 DOOR. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-2 AND 53-14-1, FIGURE 11.

Part: SEAT TRACK — CORRODED (FS 1180-1220) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND CABIN SEAT TRACKS CORRODED AT STA 1180, RBL 22 AND AT STA 1220, RBL 22. THE SEAT TRACKS WERE REMOVED AND NEW SEAT TRACKS WERE INSTALLED IAW SRM 51-30-2, 51-30-1, 53-05, FIGURE 4, AND 51-10-3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND FLOOR SUPPORTS CORRODED AT STA 200, LBL 4 - RBL 4 AND AT STA 224, RBL 14. THE FLOOR SUPPORTS WERE REMOVED AND NEW FLOOR SUPPORTS WERE INSTALLED IAW SRM 51-03-5, 51-30-5, 53-14-1, AND 51-30-2.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND CARGO TRACK IN AFT CARGO PIT CORRODED AT STA 1003 - 1155, RBL 24. THE CARGO TRACK WAS REMOVED AND A NEW TRACK WAS INSTALLED IAW SRM 51-30-1 AND 53-24.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND SEAT TRACK CORRODED AT STA 1136, LBL 22. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK SECTION WAS INSTALLED IAW SRM 53-05, FIGURE 4F.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND LEFT O/B SEAT TRACK CORRODED AT STA 1174 - 1236, LBL 56. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK AND SPLICE REPAIR WERE INSTALLED IAW SRM 53-05, FIGURE 4 AND 51-30-1.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND CABIN FLOOR SUPPORTS CORRODED AT STA 160 - 168, LBL 52 AND AT STA 165, LBL 8. THE FLOOR SUPPORTS WERE REMOVED AND NEW FLOOR SUPPORTS WERE INSTALLED IAW SRM 53-14-1, 51-10-1, 51-30-2, AND 51-30-1.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND SEAT TRACK CORRODED AT STA 860, RBL 54. THE CORRODED SECTION OF SEAT TRACK WAS CUT OUT AND A REPLACEMENT SEAT TRACK AND AFT SPLICE WERE INSTALLED IAW SRM 53-05, FIGURE 4F.

Part: ATTACH FITTING — CORRODED (SEAT TRACK) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND AFT CARGO SEAT TRACK ATTACH FITTING CORRODED AT STA 1174, LBL 54. THE FITTING WAS REMOVED AND REPLACED IAW SRM 51-10-03.

Part: WEB — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND UPPER SURFACE OF WEB CORRODED AT STA 201, RBL 48, JUST AFT OF RT SERVICE DOOR. A SPLICE DOUBLER WAS INSTALLED IAW SRM 51-04-2, FIGURE 5, 53-10-3, AND 51-30-2.

Part: FLANGE — CORRODED (CARGO DOOR) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND AFT CARGO DOOR SUPPORT UPPER FLANGE CORRODED AT STA 1211, RBL 6. THE SUPPORT WAS REMOVED AND A SUPPORT ANGLE WAS INSTALLED IAW SRM 51-3-0 AND DRAWING 69936660.

Part: WEB — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND UPPER SURFACE OF O/B LEFT CABIN FLOOR WEB LIGHTENING HOLE CORRODED AT FS 1231-1236. THE CORRODED AREA WAS REMOVED, A DOUBLER AND FILLER WERE INSTALLED IAW SRM 53-14-3, 51-10-2, AND 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AROUND SEVERAL FASTENER HOLES AT STA 160 - 200, RBL 8. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-1, 51-30-5, 53-14-1, FIGURE 27.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND CABIN FLOOR SUPPORTS CORRODED AT STA 180, RBL 10 - RBL 46 AND AT STA 200, RBL 10 - RBL 52. THE FLOOR SUPPORTS WERE REMOVED AND NEW FLOOR SUPPORTS WERE INSTALLED IAW SRM 51-30-2 AND 53-14-1, FIGURE 11.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,312 hrs · 20,123 cycles

INSPECTION FOUND CABIN SEAT TRACKS CORRODED AT FS 1136 - 1174, LBL 44 AND AT FS 1174 - 1190, LBL 22. THE SEAT TRACKS WERE REMOVED AND NEW SEAT TRACKS WERE INSTALLED IAW SRM 51-30-1, 51-30-2, 53-05, FIGURE 4, AND 51-60-0.

Part: FEEDER CABLE — SHORTED (BS 218)

INSPECTION FOUND APU POWER FEEDER CABLE NR 2 SHORTED ON STANDOFF ANGLE CLIP LOCATED IN TAIL COMPARTMENT AT SUPPORT CLAMP BETWEEN AFT PRESSURE BULKHEAD AND TERMINAL BLOCK. THE APU POWER FEEDER CABLE WAS REPLACED FROM T-STRIP STA 218 TO APU T-STRIP IN TAIL COMPARTMENT.

Part: TIEDOWN RAIL — CORRODED (BS 1007-1155)

INSPECTION FOUND RIGHT TIE DOWN RAIL CORRODED IN AFT CARGO BIN AT STA 1007 TO 1155. THE TIE DOWN RAIL WAS REMOVED AND THE CORROSION WAS REMOVED IAW SRM 51-30-3. A REPAIR DOUBLER WAS INSTALLED IAW ECRA 5320-01519.

Part: ANGLE — CRACKED (LT VERT STAB)

INSPECTION FOUND SEVERAL .75 INCH CRACKS IN LT VERTICAL STABILIZER ATTACH ANGLE ABOVE CANTED STA 1463. THE CRACKED AREAS WERE CUT OUT, A REPAIR DOUBLER AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 53-05, FIGURE 23.

Part: LONGERON — CORRODED (BS 580)

INSPECTION FOUND LONGERON 29R CORRODED AT STA 580. A SPLICE WAS INSTALLED IAW SRM 51-10-5.

Part: CABLES — OUT OF ADJUST (TAIL CONE)

EXCESSIVE FORCE WAS REQUIRED TO RELEASE TAILCONE USING AFT CABIN DOOR AND THE INTERIOR RELEASE HANDLE. THE CABLES AND LATCHES WERE ADJUSTED IAW MM 53-53-00.

Part: SKIN — CRACKED (CARGO DOOR)

INSPECTION FOUND A .5 INCH CRACK WITH DENT AT LOWER AFT CORNER OF FORWARD MAIN CABIN DOOR SKIN. A REPAIR WAS INSTALLED IAW SRM 52-05, FIGURE 37.

Part: BEAM — CRACKED (PAX DOOR)

INSPECTION FOUND A 1 CRACK AT BOTH ENDS OF MAIN CABIN DOOR NR 1 BEAM. A NEW BEAM WAS INSTALLED IAW SRM 51-10-3.

Part: BEAM — CRACKED (SERVICE DOOR)

INSPECTION FOUND A .5 INCH CRACK AT FORWARD END OF FORWARD SERVICE DOOR NR 1 BEAM. THE BEAM WAS REMOVED AND REPLACED IAW SRM 51-30-2.

Part: ANGLE — CORRODED (CARGO DOOR JAMB)

INSPECTION FOUND CORROSION ON FORWARD FACE OF MAIN BAGGAGE BIN LOWER DOOR JAMB Z-ANGLE. A REPAIR WAS INSTALLED IAW SRM 53-05, FIGURE 63.

Part: TIEDOWN RAIL — CORRODED (BS 1007-1231)

INSPECTION FOUND CORROSION ON LT TIE DOWN RAILS AT STA 1007-1174 AND STA 1212-1231. NEW TIE DOWN RAILS WERE INSTALLED IAW SRM 51-30-01.

Part: JAMB — CORRODED (BAGGAGE DOOR)

INSPECTION FOUND FORWARD BAGGAGE BIN DOOR JAMB PAN CORRODED. THE CORRODED AREA OF DOOR PAN WAS CUT OUT. A REPAIR PAN WAS INSTALLED IAW SRM 53-05, FIGURE 44, SHEET 1.

Part: SKIN — DAMAGED (BS 237)

TEMP AIRPHONE REPAIR AT STA 237 BETWEEN L30 AND L29. INSTALLED DOUBLER PER SRM 53-04 FIG 38.

Part: SKIN — DENTED (BS 256)

FUSELAGE DENTED STA 256 L 18. INSTALLED DOUBLER REPAIR PER EC/RA 5330-02664.

Part: SKIN — DAMAGED (BS 383)

TEMP AIRPHONE REPAIR AT STA 383 BETWEEN L 30 AND L 29. INSTALLED DOUBLER PER SRM 53-04 FIG 38.

Part: BEAM — CRACKED (NR 4)

F/S/D NR 4 BEAM IS CRACKED (1) AT FWD END. REMOVED AND REPLACED BEAM PER 51-30-2.

Part: BOOST PUMP — INOPERATIVE (CTR FUEL TANK)

THE MASTER CAUTION LIGHT AND RIGHT INLET FUEL PRESSURE LOW LIGHT BEGAN TO BLINK WHILE IN FLIGHT. THE LEFT MAIN TANK WAS AT 8,700 AND THE RIGHT MAIN TANK WAS AT 8750. THE MAIN TANKS DROPPED TO 8650 WITH ALL MAIN BOOST PUMPS OFF AND CENTER TANKS ON. THE AIRCRAFT WAS DIVERTED TO MSY WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED BOTH CENTER TANK FUEL BOOST PUMPS IAW MM 28-20-07, LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: FCU — INOPERATIVE (APU)

THE APU WOULD NOT START WHILE ON DESCENT. MAINTENANCE FOUND THE APU FUEL CONTROL UNIT AT FAULT. THE APU FCU WAS REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE PERFORMED WITH NO FAULTS NOTED. THE APU OPERATED NORMALLY.

Part: STATOR SUPP — BROKEN (8TH STAGE)

THE NR 1 ENGINE GAVE A LOUD BANG AND SPOOLED DOWN SHORTLY AFTER TAKEOFF AT 1800 FEET. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. THE NR 1 ENGINE WAS REMOVED AND REPLACED. *S/D* SHOP FINDINGS REVEALED 8TH STAGE STATOR SUPPORT FAILURE.

Part: SUPPORT — CORRODED (BS 1155)

INSPECTION FOUND FLOOR SUPPORT CORRODED BETWEEN CENTER AND INBOARD SEAT TRACK AT STA 1155. A NEW FLOOR SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 51-10-3 AND 51-30-5.

Part: RIB — CRACKED (WS 276)

INSPECTION FOUND A .50 INCH CRACK AT LOWER RADIUS OF LEADING EDGE RIB OF LT WING AT STA XRS 276. A DOUBLER REPAIR WAS INSTALLED IAW ECRA 5720-01521.

Part: RIB — CRACKED (WS 289)

INSPECTION FOUND A .5 INCH CRACK IN LT WING RIB AT XRS 289. A DOUBLER WAS INSTALLED IAW ECRA 5720-01521.

Part: SUPPORT — CORRODED (BS 196)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 196. A NEW SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 51-30-2.

Part: CLIPS — OUT OF ADJUST (TAIL CONE)

THE TAIL CONE INTERIOR HANDLE PULL FROM CLIPS WAS 10 POUNDS. THE CLIPS WERE ADJUSTED IAW MM 53-53-00.

Part: SKIN — CRACKED (BS 100)

INSPECTION FOUND A .3125 INCH CRACK IN FUSELAGE SKIN AT NOSE WHEEL WELL RIGHT AFT DOOR AFT HINGE CUTOUT, STA 100. THE CRACK WAS STOPPED DRILLED AND A DOUBLER WAS INSTALLED IAW SRM 53-05, FIGURE 62.

Part: AUDIO SELECT PNL — FAILED (NR 3)

FLT NR 0730 - DCA - THE NR 3 AUDIO SELECT PANEL BEGAN TO SMOKE IN FLIGHT. THE SMOKE CEASED AFTER THE CIRCUIT BREAKERS WERE PULLED AND THE UNIT WAS REMOVED FROM OVERHEAD PANEL. THE NR 3 AUDIO SELECT PANEL WAS REMOVED AND REPLACED. OPERATIONAL CHECKS WERE GOOD. AN INSPECTION OF THE INSIDE OF THE REMOVED UNIT FOUND A BURNED CIRCUIT BOARD. (M)