N68059

Part: UNKNOWN — MALFUNCTIONED (FUEL TANK) · airframe 56,023 hrs · 26,659 cycles

ACFT LEFT AIRPORT WITH NR 1 TANK FUEL QTY DEFERRED. UPON ARRIVAL INTO ,CREW REPORTED THAT ON APPROACH THEY GOT THE NR 1 TANK FUEL QTY LOW FAULT. CHECKED NR 1 TANK FUEL LEVEL STICKS AND FOUND ONLY 1200 LBS IN TANK NR 1,14600LBS IN TANK NR 2 AND 9100 LBS IN TANK NR 3.APPROX 40 MINS AFTER ACFT WAS FUELED OVER 2000 LBS OF FUEL MIGRATED FROM NR 1 TANK INTO NR 2 TANK. NR 3 TANK QTY WAS NOT AFFECTED.AFTER COMMUNICATING WITH MOCC IT WAS DETERMINED THAT THE LEAK WILL REQUIRE TANK ENTRY . MOCC R FFC NOTIFIED, SHOULD BE ARRIVING APPROX 1600Z 26MAY10 TRYING TO LOCATE A COMPRESSOR AND A VENDER TO DEFUEL ACFT.

Part: WIRE — UNKNOWN (ENGINE) · airframe 54,586 hrs · 25,978 cycles

CLIMBOUT PASSING 1000 FT RECEIVED ENG 2 EXCEEDANCE ALERT. RETARDED THROTTLE & N1 NOT EXCEEDED BUT HAD LARGE FLUCTUATIONS. ENG 2 N2 EGT NORMAL. PASSING 3000 FT RECEIVED ENG 2 RPM HI ALERT. ACCOMPLISHED CHECKLIST & ABLE TO KEEP NI RPM IN LIMITS WITH THROTTLE IN IDLE. NR 2 RPM STILL ERRATIC. DURING DECENT NR 2 ENG N1 EXCEEDED REDLINE, PERFORMED NR 2 ENG SHUTDOWN INFLT. ON ROLLOUT WITH NR 2 ENG SHUTDOWN, N1 AGAIN SHOWED AN EXCEEDANCE FOR ABOUT 3 SECS. FOUND WIRE PULLED BACK ON S30-13 77SB, RESECURED. PERFORMED POWER ASSURANCE CHK PER JRH CH 7. AT 94% N2 INDICATION JUMPING TO 100% & BACK TO 94%. VIA NR 1 & 2 FAILED. R&R NR 1 VIA PER MM 31-43-01-4. PERFORMED NAV DATABASE CROSSLOAD PER MM 31-43-01-3. OPS CHK

Part: CABLE — INOPERATIVE (AUTOTHROTTLE) · airframe 53,852 hrs · 25,624 cycles

NR 2 THROTTLE STUCK DURING CRUISE. ENGINE SHUTDOWN DURING DESCENT. NR 2 THROTTLE MOVED BACK ON SHORT FINAL AFTER LANDING NR 2 THROTTLE COULD BE MOVED TO IDLE. CABLE COMING FROM OAK. REPLACED #2 THROTTLE CABLE PER MM 76-11-01-2, OP'S CHEKS NORMAL. PERFORMED NR 2 FCC AUTOTHROTTLE RTS.

Part: SKIN — FAILED (ZONE 100) · airframe 53,570 hrs · 25,466 cycles

DURING REPAIR ASSESSMENT AN EXISTING REPAIR WAS FOUND AT FUSELAGE SKIN REPLACED EXISTING REPAIR IAW SRM53-50-00 FIG 9 BECAUSE IT IS NOT IN COMPLIANCE WITH APPROVED DATA.

Part: DOOR FRAME — MISREPAIRED (ZONE 200) · airframe 53,570 hrs · 25,466 cycles

DURING REPAIR ASSESSMENT WAS FOUND AN EXISTING REPAIR AT CTR CARGO FUSELAGE DOOR JAMB REPAIR HAS BEEN REPLACED BECAUSE IT FOUND NOT IN CONFORMITY WITH APPROVED DATA.

Part: STRUCTURE — MISREPAIRED (BS 1250-1256) · airframe 53,570 hrs · 25,466 cycles

DURING REPAIR ASSESSMENT WAS FOUND AN EXISTING REPAIR AT CENTER FUSELAGE DOOR JAMB LT SIDE REPAIR HAS BEEN REPLACED BECAUSE IT FOUND NOT IN CONFORMITY WITH APPROVED DATA.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 53,570 hrs · 25,466 cycles

DURING DC10 CARGO MODIFICATION TO ACF DURING INSPECTION FOUND ON THE CENTER LOWER CARGO DOOR LATERAL SKIN DAMAGE. REPAIRED CENTER CARGO DOOR PAN ASSEMBLY FOR SRM 52-10-00 FIG 3 VOL 1.

Part: SKIN — DAMAGED (ZONE 600) · airframe 53,570 hrs · 25,466 cycles

EXISTING EXTERNAL REPAIR DOUBLER AT FIXED L/E STA XIS 150 REMOVE REPAIR AND ACCOMPLISH A NEW IAW SRM 57-10-00 FIG 40 BECAUSE REPAIR DETECTED WAS FOUND WITH A SIGNIFICANT LOSS OF MATERIAL DUE TO A LIP CONTACT.

Part: SKIN — DAMAGED (ZONE 100) · airframe 53,570 hrs · 25,466 cycles

DURING REPAIR ASSESSMENT WAS FOUND AN EXISTING EXTERNAL REPAIR AT FUSELAGE SKIN STA 1019, LONG NR 37R REPAIR FOUND NOT IN CONFORMITY WITH APPROVED DATA AND HAS BEEN REPLACED WITH A NEW IAW SRM 53-20-00 FIG 6 SH 3 AND 4.

Part: WEB — CRACKED (ZONE 200) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE AT STA 1305 JAMB DOOR L3 FOUND CRACK 0.5 INCH LONG ON THE WEB UPPER SIDE. PERFORMED REPAIR FOR SRM 53-50-00 FIG 19 VOL. I

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE ON SEAT TRACK X -107 STA 1581 TO 1661 FOUND SEVERAL POINT OF CORROSION. REPAIRED FOR SRM 53-70-00 FIG 1 VOL I.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE AT STA 1305 JAMB DOOR R3 FOUND CRACK 0.5 INCH LONG ON THE WEB. REPAIRED FOR SRM 53-50-00 FIG 19 VOL I.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE ON SEAT TRACK AT STA 502 X= 63, FOUND CORROSION AND SCREW BROKEN. REPLACED TRACK AFA7789-521 FOR DWG AND SRM 53-70-00 FIG 1 VOL I.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE AT STA 1256 JAMB DOOR R3 FOUND CRACK 0.5" LONG ON THE WEB UPPER SIDE REPAIRED FOR SRM 53-50-00 FIG 19 VOL I.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION ON UPPER FUSELAGE AT STA 1256 JAMB DOOR R3 FOUND N2 CRACK TO 2 INCH LONG ON THE WEB LOWER SIDE. REPAIRED FOR SRM 53-50-00 FIG 19 VOL I AND REPLACED CHANNEL P/N AEA0210-40.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE ON SEAT TRACK STA 635- 615 X -28, FOUND USURED AND MISSING MATERIAL REPAIRED FOR SRM 53-70-00 FIG 1 VOL I.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE AT STA 1273 AND X -47.250 FOUND MISSING MATERIAL ON SEAT TRACK. REPAIRED SEAT TRACK FOR SRM 53-10-00 FIG 1 VOL I.

Part: FRAME — CRACKED (ZONE 100) · airframe 53,570 hrs · 25,466 cycles

DURING MODIFICATION IN CENTER ACCESSORY COMPARTMENT AT STA 1099 FROM LONGERON 49 TO LONGERON 48 RT SIDE FOUND LIGHT CORROSION AND CRACK LONG 0.5" ON CAP FRAME. REMOVED CORROSION FOR SRM 51-21-01 VOL II AND PERFORMED FRAME CAP REPAIR FOR SRM 53-30-00 FIG 8 VOL I.

Part: RIB — DAMAGED (ZONE 600) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION ON SLAT NR 3 RT WING FOUND RIB P/N ARB1666-502 WITH HOLE OVALIZED REPLACED RIB FOR SRM 51-35-01 VOL II AND DWG NRB6027.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE FROM STA 1099 TO STA 1159 ON SEAT TRACK FOUND HOLES OVALIZED REPAIRED FROM SRM 53-70-00 FIG 1 VOL I.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE AT STA 1341 X = -75.250 FOUND SEAT TRACK WITH CRACK .5" LONG REPAIRED FOR SRM 53-70-00 FIG 1 VOL I.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE AT STA 1209 X= 47.250 SEAT TRACK WITH MISSING MATERIAL. REPAIRED FOR SRM 53-70-00 FIG 1 VOL I.

Part: RIB — DAMAGED (ZONE 500) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION ON WING LT SIDE OUTBOARD SLAT NR 3 FOUND RIB P/N ARB1666-501 WITH EA 7 HOLES OVALIZED. REPLACED RIB FOR SRM 51-35-01 VOL II AND DWG ARB1666.

Part: SKIN — DENTED (ZONE 200) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION ON LOWER FUSELAGE EXTERNAL FOUND DENT 0.047" BY 2" BY 1.5 INCH LONG ON EXTERNAL SKIN STA 1049 RT SIDE LONGERON 46 TO LONGERON 47. REPAIRED FOR SRM 53-20-00 FIG 6 VOL I.

Part: FRAME — CRACKED (ZONE 100) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 MODIFICATION TO ACF IN AVIONIC COMPARTMENT RT SIDE STA 469 X =-61 FOUND FRAME WITH CRACK 1 INCH REPAIRED FOR SRM 53-30-00 FIG 11 VOL I.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE AT STA.939 X -47.50 FOUND SEAT TRACK WITH HOLE OVALIZED REPAIRED FOR SRM 53-70-00 FIG 1 VOL I.

Part: FLOORBEAM — DAMAGED (ZONE 100) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 MODIFICATION ACF FOUND IN AFT CARGO COMPT STA 1857 AT X 30 BEAM FLOOR WITH DOUBLE HOLE. REPAIRED FOR SRM 53-60-01 FIG 3 VOL I.

Part: SKIN PANEL — DELAMINATED (HORIZONTAL STAB) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION ON HORIZONTAL STABILIZER RT SIDE FOUND DISBONDING THE UPPER SKIN TIP OUTBOARD ELEVATOR REPLACED SKIN ASSY FOR SRM 51-35-01 AND DWG ALC7347,ALC7348, ALC7602.

Part: SKIN — CRACKED (BS 1305) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION FOUND ON UPPER FUSELAGE AT STA 1305 JAMB DOOR R NR 3 NUMBER 2 CRACK 2 INCHES LONG ON THE WEB IN POSITION LOWER REPAIRED FOR SRM 53-50-00 FIG 19 VOL I.

Part: FRAME — CRACKED (ZONE 200) · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION ON UPPER FUSELAGE AT STA 1781 LT STRINGER 13 FOUND FRAME WITH CRACK 5 INCHES LONG. REPAIRED FOR SRM 53-30-00 FIG 5 SECT.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 53,570 hrs · 25,466 cycles

DURING REPAIR ASSESSMENT AN EXISTING REPAIR AT FUSELAGE SKIN WAS FOUND NOT IN CONFORMITY WITH APPROVED DATA REPAIR HAS BEEN REPLACED WITH A NEW IAW SRM 53-20-00 FIG 6, SH 3/4.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 53,570 hrs · 25,466 cycles

DURING REPAIR ASSESSMENT AN EXISTING REPAIR AT FUSELAGE SKIN WAS FOUND NOT IN CONFORMITY WITH APPROVED DATA REPAIR HAS BEEN REPLACED WITH A NEW IAW SRM 53-50-00 FIG 26, VOL I.

Part: FITTING — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION MAIN CARGO DOOR COVER JAM SUPPORT FITTING AFTER INSPECTION FOUND BORE "B" OF FITTING NR 3 WITH CORROSION (DIAMETER .58") (REF EO FEDEX 8-5230-117635). PERFORMED REWORK HOLE FOR SRM 53-50-00 FIG 17, PERFORMED NDI AND INSTALLED BUSHING FOR SRM 53-50-00 FIG 17 VOL I.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION IN UPPER FUSELAGE AT STA 1099 BETWEEN SEAT TRACK X= -78 AND X=-81 FOUND CORROSION ON FLOOR SUPPORT REMOVED CORROSION IS OUT LIMIT THE REWORK. REPLACED SUPPORT FOR DWG ADA3615 AND SRM 51-35-01 VOL II.

Part: FITTING — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION MAIN CARGO DOOR LOWER JAM SUPPORT FITTING AFTER INSPECTION FOUND BORE "C" OF FITTING NR 1 WITH CORROSION (DIAMETER .456"), REF EO FEDEX 8-5230-117635. PERFORMED REWORK HOLE FOR SRM 53-50-00 FIG 17, PERFORMED NDI AND INSTALLED BUSHING FOR SRM 53-50-00 FIG 17 VOL I.

Part: FITTING — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION MAIN CARGO DOOR LOWER JAM SUPPORT FITTING AFTER INSPECTION FOUND BORE "B", "A" AND "D" OF FITTING NR 4 WITH CORROSION (DIAMETER .456") (REF EO FEDEX 8-5230-117635. PERFORMED REWORK HOLE FOR SRM 53-50-00 FIG 17, PERFORMED NDI AND INSTALLED BUSHING FOR SRM 53-50-00 FIG 17 VOL. I

Part: FITTING — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION MAIN CARGO DOOR LOWER JAM SUPPORT FITTING AFTER INSPECTION FOUND BORE "B", "C" AND "D" OF FITTING NR 7 WITH CORROSION DIAMETER .456 INCH (REF.E.O. FEDEX 8-5230-117635). PERFORMED REWORK HOLE FOR SRM 53-50-00 FIG 17, PERFORMED NDI AND INSTALLED BUSHING FOR SRM 53-50-00 FIG 17 VOL I.

Part: HINGE BRACKET — CORRODED (T/E FLAP) · corrosion level 2 · airframe 53,570 hrs · 25,466 cycles

DURING MODIFICATION MD10 ACF RT OUTBOARD FLAP INBOARD HINGE WITH RUST, BUSHING WITH PLAY AND SHIM WITH OXIDE. REPLACED HINGE FLAP P/N ARC0502-501 FOR DWG ARC0504.

Part: HINGE BRACKET — CORRODED (T/E FLAP) · corrosion level 2 · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION FOUND RT OUTBOARD FLAP, OUTBOARD HINGE WITH RUT AND CORROSION. REPLACED BRACKET ASSY OUT FLAP FOR DWG ARC0503-502

Part: HINGE BRACKET — CORRODED (T/E FLAP) · corrosion level 2 · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION, FOUND LT OUTBOARD INBOARD FLAP HINGE WITH ATTACH POINT (FWD) RUST AND BUSHING WITH PLAY. REPLACED BRACKET ASSY FOR DWG ARC0504.

Part: HINGE BRACKET — CORRODED (T/E FLAP) · corrosion level 2 · airframe 53,570 hrs · 25,466 cycles

DURING MD10 ACF MODIFICATION, FOUND LT OUTBOARD FLAP OUTBOARD HINGE WITH ATTACH POINTS WITH OXIDE. REPLACED BRACKET ASSY P/N ARC0503-501 FOR DWG ARC0505.

Part: FRAME — CRACKED (FUSELAGE) · airframe 53,570 hrs · 25,466 cycles

DURING MODIFICATION DC10 CARGO TO MD10 ACF, AT REMOVAL BRACKET IS NOTED CRACK 1.5 INCH LONG ON FRAME STA 1851 RT SIDE LONGERON 10 TO 11. PERFORMED REPAIR FOR EA FEDEX 8-5310-111515.

Part: BRACKET — DAMAGED (NR 3 NACELLE) · airframe 53,570 hrs · 25,466 cycles

FOUND ON PYLON NR 3 ON STA YN=240 THE BRACKET WITH DAMAGED AND DO NOT INSTALLED FOR DWG REPLACE WEB FOR SRM 51-33-01 VOL II AND DWG AUB7027.

Part: FITTING — CRACKED (ZONE 100) · airframe 53,570 hrs · 25,466 cycles

DURING MODIFICATION DC10 FREIGHTER TO MD10 ACF, FOUND IN AIR CONDITION COMPARTMENT NR 3 RT SIDE STA 555 X= -96 Z=-37,50 THE END FITTING FRAME WITH CRACK. INSPECTED AREA AND REPLACED SUPPORT P/N ACA3137-1.

Part: UNKNOWN — UNKNOWN (ZONE 200) · airframe 51,586 hrs · 24,440 cycles

REPAIR DOUBLER STA 620 FWD LOWER CORNER MAIN CARGO DOOR CUT-OUT MARKED NR 73. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. COMPLIED WITH FEDEX EA 8-5330-100785, FUSELAGE, MAIN CARGO DOOR OPENING SKIN HAS DAMAGE REPAIR.

Part: BOLT — SHEARED (T/E FLAP) · airframe 51,586 hrs · 24,440 cycles

RIGHT WING TRAILING EDGE INTERIOR STRUCTURE, OUTBOARD FLAP INBOARD TRACK SUPPORT FITTING LOWER OUTBOARD ATTACH BOLT SHEARED AT AFT SPAR. COMPLIED WITH E8-5710-100781 PT 1, LOWER ATTACH STUD BOLT REPLACED. MAJOR REPAIR.

Part: DOUBLER — UNKNOWN (ZONE 100) · corrosion level 2 · airframe 51,586 hrs · 24,440 cycles

REPAIR DOUBLER STA 870 LONG 28R-30R, MARKED NR 8. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. VISUALLY INSPECTED AND FOUND TO BE ACCEPTABLE IAW EA 8-5330-102789. FUSELAGE SKIN HAS EXISTING REPAIR NEAR LOWER FORWARD CARGO DOOR EVALUATE. MAJOR REPAIR.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 51,586 hrs · 24,440 cycles

FOUND REPAIR DOUBLER LOCATED AT STA 1125 L48L. REPAIR REQUIRES EVALUATION FOR MAJOR / MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. VISUALLY INSPECTED REPAIR DOUBLER LOCATED AT STA 1125 L48L FOUND EXISTING REPAIR NOT PER DC10 SRM. REMOVED EXISTING REPAIR AND REPLACED WITH NEW REPAIR IAW DC10 SRM 53-20-00 VOL I FIG 6 SHEETS 5 AND 16. MAJOR REPAIR.

Part: DOUBLER — UNKNOWN (ZONE 100) · airframe 51,586 hrs · 24,440 cycles

FOUND REPAIR DOUBLER LOCATED AT STA 1139 L48R -L48R. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REMOVED, FABBED AND INSTALLED DOUBLER AND TRIPLER IAW DC10 SRM 53-20-00 VOL I FIG 6. MAJOR REPAIR.

Part: SKIN — CORRODED (ZONE 100) · airframe 51,586 hrs · 24,440 cycles

FWD LWR CARGO STA 1019 TO 1029, LONG 52 CORROSION ON ATTACHING DOUBLER AT SKIN. REMOVED CORROSION, ALODINED AND PRIMED WITHIN LIMITS IAW DC10 SRM 53-00-01 FIG 1B, 51-21-01. REPAIRED SKIN DOUBLER IAW DC10 SRM 53-20-00 FIG7 SHT 1AND 2, PAGE 85. REMOVED AND REPLACED FWD ADF ANTENNA, OPS CHECK GOOD IAW DC10 MM 34-53-01-2. MECH 2676 QC002.

Part: DOUBLER — UNKNOWN (ZONE 100) · airframe 51,586 hrs · 24,440 cycles

REPAIR DOUBLER NR 3 A/C PACK DOOR UPPER EDGE. MARKED NR 7 REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED FAA APPROVED DATA. REMOVED, FABRICATED AND INSTALLED DOUBLER REPAIR IAW DC10 SRM 52-10-00 VOL I FIG 2. MAJOR REPAIR.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 51,586 hrs · 24,440 cycles

FWD LWR CARGO STA 1019 TO 1029, LONG 52 CORROSION ON ATTACHING DOUBLER AT SKIN. N00642

Part: SKIN — CORRODED (FUSELAGE) · airframe 51,586 hrs · 24,440 cycles

UPON REMOVAL OF LOWER ADF (AFT) ANTENNA FOR NON-ROUTINE N00520 FOUND SKIN UNDER ANTENNA CORRODED. REPAIRED SKIN IN REFERENCE TO DC-10 SRM 53-20-00,VOL 1 FIG 7 SHEET 1 AND 2. REF SNRM N00909 / WORK ORDER 00032742.

Part: INVERTER — FAILED (ZONE 100) · airframe 51,199 hrs · 24,225 cycles

ON TAXI-OUT GOT DC 2 BUS OFF LIGHT WHICH RESET ITSELF AFTER 3 SECONDS. AFTER CONFIGURING THE A/C FOR T/O, THE BATT BUS OFF LIGHT CAME ON & STICK SHAKER/TAKEOFF WARNING CAME ON. GOT ELEV FEEL & FLAP LIMIT LIGHTS ON. LOST FRONT PANEL GEAR INDICATIONS. SMELLED SMOKE FUMES AS WE'RE TAXIING INTO CHOCKS. REMOVED AND REPLACED STATIC INVERTER AS PER MM 24-24-01-2. CYCLED BATT DIR AND LEFT EMER DC FEED C/B. ALL POWER RESTORED TO NORMAL CONFIG. RAN ALL 3 ENG PER JRH CHPT 5, PERFORMED PREFERENTIAL GEN CHECKS. RAN A/C ON GROUND PWR, ENG PWR, APU PWR, EMERGENCY PWR. ALL CHECKS NORMAL.

Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 49,124 hrs · 23,207 cycles

FUSELAGE, ATTACH FITTINGS INBD FLAP SUPPORT STRUCTURE FITTING CRACK REPAIR. COMPLIED WITH EA 8-5310-55417.

Part: SUPPORT — CORRODED (LT FLAP VANE) · airframe 49,124 hrs · 23,207 cycles

WING D-LT OUTBD FLAP-FLAP VANE SUPPORT CORROSION REWORK. COMPLIED WITH EA 8-5750-55416.

Part: ANGLE — CRACKED (ZONE 300) · airframe 49,124 hrs · 23,207 cycles

COMPLY WITH EA 8-5530-82462 INSPECTION AND REPLACEMENT OF UPPER VERTICAL STABILIZER RESPAR BASE ANGLE SB DC10-55-019R3. CLOSING ACTION ON 11/15/04, ON N/R S00005. COMPLIED WITH EA 8-5530-82462.

Part: BRACKET — CORRODED (ZONE 600) · airframe 49,124 hrs · 23,207 cycles

WINGS, RT INBD FLAP REWORK OF TRACK/DRIVER BRACKET P/N ARC2761. CLOSING ACTION ON 11/27/04 ON N/R S00018. COMPLIED WITH EA 8-5754-55412.

Part: VANE — CHAFED (ZONE 500) · airframe 49,124 hrs · 23,207 cycles

WINGS, LT INBD FLAP REWORK OF CHAFED AREA ON VANE TE EXTRUSION. CLOSING ACTION ON 11/26/04, ON N/R S00022. COMPLIED WITH EA 8-5710-55415.

Part: MECHANISM — DIRTY (MLG HANDLE) · airframe 48,428 hrs · 22,876 cycles

GEAR HANDLE DOWN AND IN RED LIGHTS AT BOTH PANELS. UNABLE TO CHECK ANTI-SKID TEST. QRH COMPLETED. RECYCLED GEAR ALL LIGHTS GREEN ANTI-SKID TEST NORMAL. TWR VISUAL CK GEAR DOWN. PER CAPTAIN DEBRIEF, WHEN RED LIGHTS WERE ILLUMINATED, THE HANDLE WAS SLIGHTLY JIGGLED AND ALL SAFE LIGHTS ILLUMINATED. THE CREW THEN CYCLED THE GEAR AND ALL INDICATIONS WERE NORMAL. PERFORMED THE LANDING GEAR CONTROL MECHANISM CLEANING AND LUBE PER M/M 32-31-02-7. INDICATIONS NORMAL. ANTI-SKID TEST NORMAL PER M/M 32-45-01-2. A/C OKAY FOR SERVICE.

Part: LANDING GEAR — MALFUNCTIONED (MAINS) · airframe 47,709 hrs · 22,553 cycles

ON INITIAL GEAR EXTENSION GEAR WOULD NOT COME DOWN AND LOCK. RECYCLED GEAR, EXTENSION NORMAL, ALL 3 DOWN AND LOCKED. INSPECTED GEAR, COULD NOT FIND ANY DEFECTS. A/C OK FOR SERVICE PER M/M 32-31-01 AND TAFI 32-30.

Part: VALVE — LEAKING (RT MLG) · airframe 47,614 hrs · 22,516 cycles

RECEIVED MASTER CAUTION LIGHT & THEN HYD SYSTEM 3 PRESS LO LIGHTS. LOST 2 GAL HYD FLUID ON SYSTEM 3, STOPPED AT 6 GAL WHEN S/O TURNED PUMPS (SYST 3) OFF. RAN PHASE 1 RED TABS, DECLARED EMERGENCY. GEAR AND FLAPS WERE ALREADY SET AT THE TIME. LANDED UNEVENTFULLY. CRASH CREW REPORTED MASSIVE LEAK AT RIGHT MAIN GEAR TRUCK INSTALLED NEW VALVE PER MM 32-31-06.

Part: SKIN — CORRODED (FUSELAGE) · airframe 46,639 hrs · 22,092 cycles

MAIN CARGO CORROSION FOUND AT BS 1371, LBL 85 AT REAR SPAR TOP OF FUEL TANK WILL NEED TO HAVE FASTENERS REMOVED. R/R SKIN PER E.A. 8-5710-69306.

Part: SKIN — CORRODED (CENTER WING) · airframe 46,639 hrs · 22,092 cycles

MAIN CARGO-CORROSION FOUND AT STA 1371 LBL 85 AT REAR SPAR TOP OF FUEL TANK. WILL NEED TO HAVE FASTENERS REMOVED. ** S/D ** CLOSING ACTION: ACCOMPLISHED REPAIR - CENTER WING - UPPER SKIN CORROSION - PER EA 8-5710-69306.

Part: SUPPORT — WORN (TE FLAP) · airframe 46,639 hrs · 22,092 cycles

LEFT INBOARD FLAP - INBOARD ACTUATOR LEVER ARM, SUPPORT STRUCTURE HAS DEEP WEAR/CHAFING AT PREVIOUS REPAIR. REQUEST ENGR EVALUATION. COMPLIED WITH EA-85750-67549 HINGE BRACKET SHIM INSTALL ALSO COMPLIED WITH EA- 8-5310-66485 WING- LT I/B T/E FLAP SUPPORT PANEL DAMAGE REPAIR. (REF. ITEM CHANGED PER ENGINEERING REQUEST FLAP CONTROL VALVE, RESTRICTROS, I/B & O/B ACTUATORS AND FLAP BUS CABLES.

Part: SEAT — SHORTED (COCKPIT) · airframe 44,738 hrs · 21,277 cycles

AT FL330 SMOKE IN COCKPIT, PERFORMED RED TAB PROCEDURES ORIGIN OF SMOKE APPEARED TO BE FROM SECOND OFFICER'S SEAT. PULLED SECOND OFFICERS SEAT CIRCUIT BREAKERS AND DIVERTED TO KSLC. C/B'S REMAIN PULLED, AND ELECTRICAL CONNECTOR TO SEA CONTROLS IS DISCONNECTED FOR PRECAUTIONARY REASONS. REMOVED AND REPLACED F/E'S CREW SEAT IAW MM 25-11-03-4. OFF MFG 1057D25-10-06 SRL 1143 ON MFG 1057D25-10-06 SRL 1087RW

Part: BOLTS — LOOSE (NR 1 PYLON)

DISCREPANCY: NR 4110, WHILE INSPECTING NR 1 PYLON FORWARD MOUNT BULKHEAD LT AND RT FORWARD MOUNT TRUSS FITTING, FOUND 1 EA TRUSS MOUNT BOLT LOOSE ON LT LOWER SPAR CAP, FOUND MORE MOUNT BOLTS LOOSE, PYLON STA YN 222-227. BOLTS REMOVED, HOLES INSPECTED AND FOUND OK. BOLTS REPLACED IAW SB 54-95.

Part: BULKHEAD — CRACKED (BS 31.8)

NR 2 ENGINE INTAKE FWD BULKHEAD STA 31.8 HAS SEVERAL CRACKS AT THE FOLLOWING POS; 5 O'CLOCK, 5:45, 6:15, 8:30 AND 9 O'CLOCK POSITION. REMOVED AND REPLACED LEFT AND LOWER WEB SECTIONS PER SRM 54-10-00.

Part: STRUT — REQD SERVICE (NLG)

ON TAKEOFF, GEAR OVERRIDE WAS USED TO RETRACT LT GEAR PER CHECKLIST. ON EXTENSION, DOWN AND LOCK IND NORMAL, INTERMITTENT WARNING HORN SOUNDED UNTIL FLAPS RETRACTED TO 22 DEGREES, THEN HORN SILENCED. SUSPECT NOSE STRUT NOT EXTENDING FULLY, RESULTING IN GROUND SENSING STILL HOLDING LATCH. DISASSEMBLED PER 32-21-03, SERVICED AND LEAK CHECKED OK.

Part: GEAR HANDLE — LACK OF LUBE (LANDING GEAR)

RED GEAR LIGHTS REMAINED ILLUMINATED AFTER SELECTING GEAR DOWN AND GEAR SHOULD HAVE BEEN DOWN. RECYCLED, AND SAME THING HAPPENED, THEN GREEN LIGHTS SUDDENLY CAME ON. A/C LANDED MEM WITHOUT INCIDENT. MAINTENANCE FOUND GEAR HANDLE GUMMED UP. CLEANED GEAR HANDLE AND RELUBED, OPS CHECKED GOOD. OK FOR SERVICE.