N392FE

Part: BOTTLE — LOW PRESSURE (R1 DOOR) · airframe 84,045 hrs · 32,402 cycles

RIGHT ENTRY DOOR PNEUMATIC BOTTLE PRESSURE 0. FOUND DOOR R1 HANDLE IN THE EMERGENCY POSITION. RESET DOOR HANDLE & SERVICED DOOR ASSIST BOTTLE IAW MD10-10 MM 52-11-07-2, OPERATIONS NORMAL.

Part: FIRE DETECTOR — FALSE ACTIVATION (CARGO BAY) · airframe 83,554 hrs · 32,117 cycles

THIRTY MINUTES AFTER TAKEOFF, RECEIVED A LEVEL 3 ALERT, LOWER CARGO FWD FIRE. DISCHARGED FIRE AGENT IAW PHASE 1 PROCEDEURES, RAN RED TABS. DIVERTED, CRASHED. FIRE RESCUE INSPECTED ACFT AND FOUND NO INDICATION OF FIRE. INSPECTED FWD LOWER CARGO BAY FOR ANY INDICATIONS OF FIRE OR SMOKE. NO DISCREPANCIES NOTED. R & R CARGO FIRE CONTROL PANEL IAW MM 26-14-10-4. REPLACED FWD SMOKE DETECTORS IAW MM 26-14-01-4. GROUND OPS CHECKED OK.

Part: WINDSHIELD — FAILED (COCKPIT) · airframe 83,127 hrs · 31,905 cycles

ON FINAL APPROACH, MODERATE RIM ICE ACCUMULATATED ON F/O WINDSHIELD, ALMOST NO ICE ON CAPT SIDE. WINDSHIELD A/I HAD BEEN ON FOR ABOUT 10 MIN ON LOW ON BOTH SIDES. HIGH WAS THEN SELECTED AND WITHIN 30, " F/O WINDSHIELD CRACKED." REPAIRED IAW AMM 56-11-00-2

Part: RELAY — INTERMITTENT (MANIFOLD) · airframe 82,949 hrs · 31,807 cycles

AIR MANIFOLD NR 3 FAILED LEVEL 3 ALERT WHEN ANTI-ICE SELECTED ON DURING DESCENT. PERFORMED TEST OF THE PNEUMATIC PRESSURE SW IAW EA 8-3622-114705, SWITCH OPS NORMAL, BUR FOUND FAILED. RELAY R2-5257 INTERMITTENT, REPLACED RELAY AND PERFORMED TESTS IAW FIM 36-23 AND NR 3 PNEU. SYS OPS NORMAL.

Part: RELAY — FAILED (MANIFOLD DELAY) · airframe 82,949 hrs · 31,807 cycles

AIR MANIFOLD NR 3 FAILED LEVEL 3 ALERT WHEN ANTI-ICE SELECTED ON, DURING DESCENT. PERFORMED A GVI OF PNUEMATIC DUCTS AND VALVES IN WING AND PYLON AREA. PERFORMED PNEUMATIC DECAY TEST IAW AMM 36-00-01-5 WITH NO FAULTS. DURING SYS TESTS USING APU, FOUND THE MANIFOLD DELAY RELAY BAD, REPLACED RELAY AND SYS OPS CHECKED GOOD.

Part: SHAFT — SHEARED (ACM) · airframe 81,029 hrs · 30,732 cycles

NR1 ACM PACK RUNS ALMOST FULL HOT REGARDLESS OF RAM AIR DOOR AND PACK VALVE TRANSMITTER POSITIONS. REMOVED NR 1 ACM PACK, FOUND A BROKEN TURNBINE SHAFT. R & R AIR CYCLE MACHINE POSSITION NR 1.

Part: SPAR CAP — CRACKED (RT WING) · airframe 81,029 hrs · 30,732 cycles

RT WING REAR SPAR CAP HAS 2 HOLES WITH CRACK INDICATION. ACCOMPLISHED LIMITED REPAIR REF EA 8-5710-147784. PERMANENT REPAIR TO BE ACCOMPLISHED WITHIN 24 MONTHS.

Part: ANGLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 81,029 hrs · 30,732 cycles

AFT CARGO COMPARTMENT AT STA 1841 FLOOR AFT FRAME ANGLE FOUND CORRODED FROM UNDERNEATH AT NUT PLATE HOLES FROM LONGERON 42L TO 42R. FABRICATED NEW ANGLE WITH 7075-0 IAW WITH SRM 53-00-01 AND DWG AGA3874. PART HEAT TREATED TO T6. INSTALLED NEW ANGLE AT STA 1841 AFT FRAME IAW WITH SRM 51-35-01 AND 51-33-01, VOL 2.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 81,029 hrs · 30,732 cycles

CTR CARGO, AFT WALL FLOORBEAM ANGLE CORRODED ON AFT SIDE (AS VIEWED FROM AFT CARGO). R & R LT FLOORBEAM ANGLE SECTION, REF AFA3871, CLEANED AND TREATED CTR AND RT FLOORBEAM ANGLE SECTIONS, REF SRM 51-21-01, VOL II, LT FLOOR SUPPORT ANGLE 13 CORRODED BEYOND REPAIR, FABRICATED FLOORBEAM ANGLE IAW DWG AFA 3871.

Part: ROLLER TRAY — CORRODED (ZONE 100) · corrosion level 2 · airframe 81,029 hrs · 30,732 cycles

4 ROLLER TRAYS HAVE CORROSION, CENTER PIT BETWEEN STA 1700 TO 1781 CLEANED SURFACE CORROSION ON 3 TRAYS IAW SRM 51-21-01, VOL III. FABRICATED ONE ROLLER TRAY IAW DWG AFJ 7001. INSTALLED NEW TRAY IAW DWG AFJ7001.

Part: SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 81,029 hrs · 30,732 cycles

CENTER CARGO AFT WALL, CORROSION ON VERTICAL SUPPORT BEAM JUST RIGHT OF CTR AND JUST ABOVE FLOOR LINE. INSTALLED NEW VERTICAL SUPPORT BEAM AT STA 1781 IAW DWG AFA3225 AND SRM 51-35-01, VOL II.

Part: RELIEF VALVE — LEAKING (HYD SYSTEM) · airframe 79,700 hrs · 30,067 cycles

ON CLIMBOUT, GOT HYD 3 ELEV OFF ALERT WITH DECREASING HYD 3 QTY. FOLLOW ON ALERTS HYD 3 OFF AND ON FINAL APPROACH BACK TO DEPARTURE GOT HYD 3 FAIL. LOST ALL HYD 3 QTY. ALTN GEAR EXTENSION USED. LDG WT 343,500LBS. AIRPORT CRASH FIRE RESCUE REPORTED SMOKE COMING OFF RT GEAR AND SPRAYED IT. FOUND SOURCE OF HYD FLUID LOSS TO BE THE RT GEAR TRIM CYL PRESSURE RELIEF VALVE. REPLACED SAME. SERVICED AND BLED HYD SYS 3. EXCERCISED ALL FLIGHT CONTROLS AND GEAR. CLEANED RIGHT GEAR WELL. ITEM OK FOR SERVICE. RESET ALT GEAR EXTENSION REF AMM'S 12-13-02-3, 12-22-02-7 & 32-37-03-2.

Part: PRESSURE SWITCH — FAILED (MANIFOLD FAILURE) · airframe 79,463 hrs · 29,956 cycles

AT CRUISE ALTITUDE, RECEIVED LEVEL 3 MANIFOLD NR 1 FAIL ALERT. AIR SYS ISOLATED PROPERLY AND ALERT WENT AWAY. DIVERTED AND LANDED WITHOUT INCIDENT. R & R LT WING MANIFOLD FAILURE DETECTION PRESSURE SWITCH IAW. MM36-23-03-4. PERFORMED TEST IAW 36-23-03. R & R (2)EA CLAMPS ON LT WING ANTI ICE VALVE IAW MM 30-11-02-2 PERFORMED LEAK CHECK AND OP'S IAW 30-11-00-5 NO LEAKS NOTED. AS A PRECAUTION R & R MANIFOLD FAILURE DETECTION THERMAL SWITCH AT SLAT TRACK NR 3 ON LT WING IAW MM 36-23-04-2 PERFORMED ADJUST AND TEST IAW ABOVE REF AND 36-10-02/501 ACFT OK FOR SERVICE.

Part: TRANSDUCER — MALFUNCTIONED (MLB BRAKES) · airframe 79,254 hrs · 29,834 cycles

ANTI-SKID R FAIL ON LANDING CYCLED AND NO CHANGE,ON 2ND. ATTEMPT TO LAND CAME ON AGAIN THEN WENT OUT, FLAPS 50 LANDING 4L CKED CFDS FOUND MSG. 324355, NR 7 WHEEL SPEED TRANSDUCER FAIL, NEEDS CPN 3215531, ORDERED PART. REMOVED NR 7 TRANSDUCER, INSPECTED CONNECTOR PLUG FOUND OK, TRANSDUCER IS REMOVED AND PARTS ARE IN MX OFFICE WAITING FOR PARTS. C/B'S PULLED IAW AMM 32-45-03-2 STEP 3A. FOUND CFDS FAULT REF NR 7 WHEEL SPEED TRANSDUCER INOP. R & R NR 7 WHEEL SPEED TRANSDUCER IAW MM 32-45-03-2. OPS CKS NORMAL. PREMATURE REMOVAL/INSTALLATION.

Part: ANTI-SKID SYS — FAILED (MLG) · airframe 79,076 hrs · 29,759 cycles

LEVEL 2 ANTI-SKID R FAIL ON FINAL W/GEAR DOWN. ANTI-SKID WOULD NOT TEST W/GEAR UP AFTER GO AROUND. DID TEST AND FAIL ONCE GEAR DOWN. R & R NR 7 WHEEL SPEED TRANSDUCER IN REF TO AMM32-45-03-2, SPIN CKD GOOD AND NO FAULTS SHOWN ON ASCU. REACTIVATED NR 7 MLG BRAKE AND STOWED BRAKE INOP KIT. SWUNG MLG 6 TIMES AND PERFORMED ANTISKID TEST WITH GEAR UP AND DOWN AND ANTISKID TEST PASSED EACH TIME. PERFORMED R-T-S OF ASCU AND PASSED AND NO CURRENT FAULTS IN REF TO AMM 32-45-00-5,32-45-01-5. ACFT OK FOR SERVICE.

Part: ANTI-SKID SYS — FAILED (MLG) · airframe 79,071 hrs · 29,756 cycles

GOT LEVEL 2 ANTI SKID FAIL ON FINAL. EXECUTED GA RAN QRH. UNEVENTFUL LANDING. HAD FIRE TRUCK LOOK AT BRAKES WITH INFARED. THEY STATED BRAKES WERE WARM NOT HOT. IAW RTS FOUND ASCU HAD INTERNAL FAULT. R & R ASCU IAW AMM 32-45-01-04. ACCOMPLISHED RTS IAW AMM 32-45-01-5. RTS PASSED NO FAULTS NOTED AT THIS TIME. ACFT OK FOR SERVICE. PREMATURE REMOVAL/INSTALLATION.

Part: ANTI-SKID SYS — FAILED (MLG) · airframe 79,058 hrs · 29,746 cycles

WHILE CONDUCTING ILS APPROACH TO RWY 36R AT MEM RECEIVED LVL 2 ALERT ANTI SKID RT FAIL EXECUTED MISSED APPROCH, RAN QRH. FAILED MANUAL ANTI-SKID CHECK WERE VECTOR FOR ANOTHER APPROACH AND ANTI-SKID APPEARED TO WORK. REMOVED AND REPLACED ASCU IAW MM 32-45-01-4. OPS CHECKS NORMAL AT THIS TIME. ACFT OK FOR CONT SERVICE.

Part: FITTING — CRACKED (NR 2 SLAT) · airframe 78,329 hrs · 29,391 cycles

RIGHT WING NR 2 SLAT FOUND CRACKED AT INBOARD FITTING. REMOVED AND REPLACED RT WING NR 2 SLAT AND ADJUSTED IAW AMM 27-80-01-4.

Part: WEB — CRACKED (NR 3 PYLON) · airframe 78,329 hrs · 29,391 cycles

N/R206- 5 IN CRACK ON UPPER WEB INBD SIDE NR 3 PYLON APPROX 12 IN. FROM AFT PYLON MOUNT. REMOVED UPPER WEB ATNR 3 PYLON REF SRM 51-00-01. FABRICATED NEW WEB REF DRAWING AUB7031. INSTALLED NEW WEB REF 51-00-01 VOL 1, E.O. 5-5410-7-4311 P2 AND EO 8-5410-7-4311 P1.

Part: PRESSURE PANEL — CRACKED (LT MLG WW) · airframe 77,802 hrs · 29,134 cycles

LT MLG WHEEL WELL INBD WALL UPPER AFT CORNER HAS CRACK FROM STIFFENER GOING FWD TOWARD PREVIOUS REPAIR, VERIFIED AND MARKED USING ET, LOCATED ABOVE NR 1 HYD SYSTEM RESERVOIR COMPLIED WITH EA 8-5310-123830 TITLE, FUSELAGE-MAIN FRAME- KEEL STRUCTURE/UNDERWING BARREL/WEB REPAIR. CUT OUT DAMAGE AND INSTALLED DOUBLER IN THE AREA.

Part: SKIN — BULGED (ZONE 600) · airframe 73,514 hrs · 27,124 cycles

FOUND CENTER PIT STA 1731 ABOVE L45R TORQUE BOX WEB (SILL AREA) SKIN BULGE AND SHEARED RIVET. ENTERED IN ERROR WRONG AIRCRAFT, NO NON-ROUTINE N00200 FOR AIRCRAFT N392FE.

Part: REPAIR — UNKNOWN (FUSELAGE) · airframe 73,514 hrs · 27,124 cycles

RT FUSELAGE EXTERNAL REPAIR IS IN CRITICAL AREA OF PRIMARY STATIC PORT. REWORKED REPAIR IAW FEDX EA 8-5330-96383 FUSELAGE - SKIN AT FORWARD CARGO DOOR HAS REPAIR THAT WAS REMOVED - REWORK. MAJOR REPAIR.

Part: SENSOR — OUT OF ADJUST (SLATS) · airframe 73,344 hrs · 27,044 cycles

ON APPROACH TO KSMF AT FLAPS 22, SLAT EXTEND SELECTION OF FLAPS 35 CAUSE A SLAT DISAGREE. RAN QRH LANDED FLAPS 22/SLATEXT. FOUND SENSOR GAP BEYOND MAX LIMIT. ADJUST SENSORS L4A AND L4B. RETENSIONED LT WING O/B SLATS AND SAFETIED PER M/M 27-80-00-5-2 CLOSED AND SECURED OPEN PANEL OPS CK GOOD.

Part: COMPUTER — MALFUNCTIONED (ZONE 200) · airframe 70,770 hrs · 26,063 cycles

DURING APPROACH TO RWY 35R AT MCO GOT TOO LOW TERRAIN WARNING. AT 400 FEET ON GLIDE SLOPE AND LOC EXECUTED MISSED APPROACH AND RETURNED TO SAME RWY. THE SAME THING HAPPENED ON SECOND APPROACH. TOO LOW TERRAIN, WARNING CONTINUED TO TOUCHDOWN. REMOVED & REPLACED ENHANCED GROUND PROXIMITY WARNING COMPUTER.

Part: ROLLER — WORN (ZONE 600) · airframe 70,219 hrs · 25,826 cycles

RT WING FLAP SIDE LOAD ROLLER FITTING LOWER LUG FLAT SPOTTED AND HOLES HAVE EVIDENCE OF PITTING. REMOVED PITTING AND CORROSION FROM LUG AND BORE. FABBED AND INSTALLED 2 EACH REPAIR BUSHINGS IAW SRM 57-20-00 VOL. I PAGE 16. BLENDED FLAT SPOTTED AREA IAW EA8-5750-81494. ORIGINAL LUG THICKNESS WAS 1.015 INCH FINAL LUG THICKNESS .990 INCH. SEE NR N01176

Part: FITTING — WORN (ZONE 500) · airframe 70,219 hrs · 25,826 cycles

LT WING FLAP SIDE LOAD ROLLER FITTING LOWER LUG FLAT SPOTTED AND ALL HOLES HAVE EVIDENCE OF PITTING. REMOVED CORROSION AND PITTING FROM LUG AND BORES. FABBED AND INSTALLED 2 EACH REPAIR BUSHINGS IAW SRM57-20-00 VOL.I PAGE 16. INSTALLED BUSHINGS ON NR N01175. BLENDED FLAT SPOTS IAW EA 8-5750-81495. SEE N/R N01174.

Part: LAVATORY — NOT SEATED (ZONE 200) · airframe 70,219 hrs · 25,826 cycles

LAVATORY PAPER AND WASTE RECEPTACLE DOES NOT SEAL CORRECTLY. RESEALED LAVATORY PAPER AND WASTE RECEPTALE IAW MD10-10 SRM 51-41-01 VOL II AND EA 8-2540- 82478, SEALING OF FORWARD LAVATORY TRASH SHOUT.

Part: FRAME — CRACKED (ZONE 400) · airframe 70,219 hrs · 25,826 cycles

NR 2 ENGINE RT THRUST REVERSER TRAILING EDGE AFT FLANGE CRACKED APPROXIMATELY 6 INCHES FROM BOTTOM. COMPLIED WITH MFG EA 8-7830-81496

Part: PANEL — MISALIGNED (ZONE 400) · airframe 70,219 hrs · 25,826 cycles

NR 1 PYLON PRECOOLER VENTILATOR PANEL ASSY PN AUB7054-501 FASTENER HOLES DO NOT ALIGN TO PYLON STRUCTURE. COMPLIED WITH EA 8-5480-81485 REV. A, NR 1 ENGINE VENTILATOR PANEL REPAIR.

Part: HINGE FITTING — CORRODED (ZONE 600) · airframe 70,219 hrs · 25,826 cycles

RIGHT HAND INBOARD FLAP PIVOT ATTACH POINT, OUTBOARD LUG FACE, OUTER SURFACE CORRODED. REMOVED CORROSION FROM LUG FACE, FOUND TO BE OUT OF LIMITS IAW DC10 CMM 57-52-01. COMPLIED WITH FEDEX EA 8-5750-81475, WINGS, RIGHT HAND INBOARD FLAP OUTBOARD HINGE PIVOT OVERSIZE BORE REPAIR. REFERENCE NON-ROUTINE N00985.

Part: HINGE — CORRODED (ZONE 500) · airframe 70,219 hrs · 25,826 cycles

LEFT WING OUTBOARD FLAP INBOARD HINGE, LOCATION NR 4 BORE CORRODED. REMOVED CORROSION IAW DACCMM 57-44-08, INSPECTED IAW DACCMM 57-44-08 AND 20-11-02. PEENED IAW DACCMM 57-44-08 AND 20-11-01. PRIMED IAW DC10 SRM 51-21-01 VOL. II. FABBED BUSHING IAW DACCMM 57-44-08 AND EA 8-5750-81470. CAD PLATED BUSHING IAW DACCMM 57-44-08 AND 20-10-01. INSTALLED AND HONED BUSHING IAW DACCMM 57-44-08. BEGINNING BORE 2.300 INCH FINAL BORE 2.3414 INCH MATERIAL REMOVED .0414 INCH IAW DACCMM 57-44-08.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 70,219 hrs · 25,826 cycles

RIGHT HAND PRIMARY STATIC PORT FAILS RVSM INSPECTION FOR EXTERNAL DOUBLER MISMATCH RATIO IAW DC10 SRM 53-00-02 NOTE 2 (FIG 1 SHEET 2). REMOVED EXISTING FUSELAGE SKIN REPAIR ON FORWARD EDGE OF FORWARD CARGO DOOR CUTOUT DOUBLERS, FABRICATED NEW EXTERNAL DOUBLER, INTERIOR DOUBLER AND FILLER IAW EA8-5330-81482 AND FEDEX DC10/MD11 SRM 53-50-10 FIGURE 20. ALODINED AND PRIMED PARTS IAW DC10 SRM 51-20-01 VOLUME II. INSTALLED REPAIR IAW EA8-5330-81482 AND FEDEX DC10/MD11 SRM 53-33-01 VOLUME II. SEE NR N00531.

Part: HINGE FITTING — CORRODED (ZONE 500) · airframe 70,219 hrs · 25,826 cycles

LEFT WING INBOARD FLAP OUTBOARD SUPPORT PIVOT ATTACH POINT INBOARD BORE GOUGED. REMOVED DAMAGE IAW DACCMM 57-52-01, BORE FOUND OUT OF LIMITS, GENERATED RFTS, RECEIVED FEDEX EA8-5750-81492, REPAIRED BORE IAW DACCMM 57-52-01 AND FEDEX EA8-5750-81492. SEE NR N00416.

Part: HINGE FITTING — CORRODED (ZONE 600) · airframe 70,219 hrs · 25,826 cycles

RIGHT HAND INBOARD FLAP PIVOT ATTACH POINT INBOARD BORE CORRODED. REMOVED CORROSION BEGINNING BORE 1.1875 INCH FINAL 1.2583 INCH MATERIAL REMOVED .0708 INCH IAW DACCMM 57-52-01. FABBED REPAIR BUSHING IAW DACCMM 57-52-01 AND EA8-5750-81475. PERFORMED MPI IAW DPS 4.704. CAD PLATED, INSTALLED AND HONED REPAIR IAW DACCMM 57-52-01.

Part: SUPPORT — CORRODED (ZONE 600) · airframe 70,219 hrs · 25,826 cycles

RIGHT WING INBOARD FLAP OUTBOARD HINGE AT LOCATION NR 1 INBOARD AND OUTBOARD LUG HAS CORROSION. REMOVED CORROSION IAW DACCMM 57-44-07. FOUND TO BE STRUCTURALLY ACCEPTABLE IAW FEDEX EA8-5750-81474. ALODINED AND PRIMED LUG FACES IAW DC10 SRM 51-21-01 VOLUME II. BEGINNING SURFACE 1.255 INCH. FINAL INBOARD 1.2400 INCH OUTBOARD 1.2360 INCH. MATERIAL REMOVED INBOARD .015 INCH OUTBOARD .019 INCH FOUND OUT OF LIMITS IAW DACCMM 57-44-07. SEE NR N00962.

Part: HINGE — CORRODED (ZONE 500) · airframe 70,219 hrs · 25,826 cycles

LT IB FLAP OB HINGE PIVOT BORE FACE PITTED AND GOUGED (AIRFRAME SIDE) LOCATION NR 3. REMOVED BUSHING, REMOVED CORROSION, AND COMPLIED WITH EA 8-5750-81473 REF NR N00295.

Part: SUPPORT — CORRODED (ZONE 600) · corrosion level 2 · airframe 70,219 hrs · 25,826 cycles

RIGHT WING INBOARD FLAP OUTBOARD HINGE LOCATION NR 1 INBOARD AND OUTBOARD LUG HAS CORROSION. REMOVED CORROSION IAW DACCMM 57-44-07. FOUND TO BE STRUCTURALLY ACCEPTABLE IAW EA8-8750-81474. ALODINED AND PRIMED LUG FACES IAW DC10 SRM 51-21-01 VOLUME II. BEGINNING SURFACE 1.255 INCH INBOARD FINAL 1.2400 INCH OUTBOARD 1.2360 INCH. MATERIAL REMOVED INBOARD .015 INCH OUTBOARD .019 INCH FOUND OUT OF LIMITS IAW DACCMM 57-44-07.

Part: FITTING — DAMAGED (ZONE 600) · airframe 70,219 hrs · 25,826 cycles

RIGHT HAND INBD FLAP PIVOT POINT OUTBOARD BORE HAS GROOVE MARK. REMOVED CORROSION IAW DAC CMM 57-52-01. BEGINNING DIAMETER 1.1875 INCH FINAL 1.2552 INCH . FABBED REPAIR BUSHING IAW DACCMM 57-52-01 AND EA8-5750-81475 MPI IAW DACCMM 5752-01 AND DPS 4.704 CAD PLATED, INSTALLED AND HONED BUSHING IAW DACCMM 57-52-01.

Part: SUPPORT — CORRODED (ZONE 500) · airframe 70,219 hrs · 25,826 cycles

LEFT WING INBOARD FLAP OUTBOARD HINGE AT LOCATION NR 3 HAS CORROSION IN BORE. REMOVED CORROSION IAW DACCMM 57-44-07. BEGINNING BORE 2.5850 INCH FINAL 2.626 INCH MATERIAL. REMOVED .041 INCH. FABRICATED BUSHING IAW DACCMM 57-44-07 AND EA8-5750-81473. ACCOMPLISHED MPI IAW DPS 4.704. CAD PLATED BUSHING IAW DACCMM 57-44-07. ALODINED AND PRIMED BORE IAW DC10 SRM 51-21-01 VOLUME II. INSTALLED AND HONED BUSHING IAW DACCMM 57-44-07.

Part: SUPPORT — CORRODED (ZONE 500) · airframe 70,219 hrs · 25,826 cycles

LEFT WING INBOARD FLAP OUTBOARD HINGE AT LOCATION NR 1 INBOARD AND OUTBOARD LUGS HAVE CORROSION. REMOVED CORROSION FROM LOCATION NR 1 MOUNTING SURFACE IAW DACCMM 57-44-07 AND FEDEX EA8-5750-81473. PRIMED LUGS IAW DC109 SRM 57-21-01 VOLUME II. BEGINNING BORE 1.255 INCH REMOVED .0200 INCH FINAL 1.2360 INCH. FOUND TO BE WITHIN LIMITS IAW DACCMM 57-44-07.

Part: SUPPORT — CORRODED (ZONE 500) · airframe 70,219 hrs · 25,826 cycles

LEFT WING INBOARD FLAP OUTBOARD HINGE AT LOCATION NR 1 INBOARD AND OUTBOARD LUGS HAVE CORROSION. REMOVED CORROSION FROM LOCATION NR 1 MOUNTING SURFACE IAW DACCMM 57-44-07 AND FEDEX EA8-5750- 81473. PRIMED LUGS IAW DC10 SRM 57-21-01 VOLUME I, BEGINNING BORE 1.255 INCH REMOVED .0200 INCH FINAL 1.2360 INCH FOUND TO BE WITHIN LIMITS IAW DACCMM 57-44-07.

Part: SUPPORT — CORRODED (ZONE 600) · airframe 70,219 hrs · 25,826 cycles

BORE CORRODED RIGHT WING INBOARD FLAP OUTBOARD HINGE LOWER SWIVEL BEARING. REMOVED CORROSION IAW DACCMM 57-44-07. ORIGINAL BORE 2.530 INCH FINAL 2.543 INCH MATERIAL LOSS .013 INCH. FABBED BUSHING IAW DACCMM 57-44-07 AND EA8-5750-81474. PERFORMED MPI IAW DPS 4.704. CAD PLATED BUSHING IAW DACCMM 57-44-07. ALODINED AND PRIMED BORE IAW DC10 SRM 51-201 VOLUME II. INSTALLED AND HONED BUSHING IAW DACCMM 57-44-07.

Part: SUPPORT — CORRODED (ZONE 600) · airframe 70,219 hrs · 25,826 cycles

RIGHT HAND OUTBOARD FLAP INBOARD SUPPORT PIVOT ATTACH POINT INBOARD BORE CORRODED (INBOARD SUPPORT). REMOVED CORROSION IAW DACCMM 57-52-02. ETCHED AND PEENED IAW DACCMM PERCENT &-52-02 AND 20-11-02. FABBED BUSHING IAW DACCMM 57-52-02 AND EA8-5750-81472. CAD PLATED BUSHING IAW QQ-P- 416TC AT BY OUTSIDE VENDOR PO NR 460364, THEN INSTALLED IAW DACCMM 57-52-02 FINAL HONED BUSHING TO A BORE OF .8752 IAW DACCMM 57-52-02 USING TOOL TWS8725 DATE 6-18-05.

Part: SKIN — CORRODED (ZONE 500) · airframe 70,219 hrs · 25,826 cycles

LEFT WING SKIN LOWER SURFACE IS CORRODED, STATION XORS 799 APPROX 19 INCHES AFT OF FORWARD SPAR CAP. SKIN HAS SMALL AMOUNTS OF PITTING. REMOVED CORROSION AND FOUND TO BE WITHIN LIMITS IAW EA 8-5710-81493. ORIGINAL MATERIAL THICKNESS IS .096 INCH, REMOVED .028 INCH AT FORWARD SPOT LEAVING .068 INCH, REMOVED .024 INCH AT AFT SPOT LEAVING .072 INCH REMAINING. FLAP PEENED AREAS IAW MD10 CMM 20-11-01. ALODINE AND PRIMED IAW DC10 SRM 51-21- 01 VOL II. REINSTALLED FASTENERS IAW DC10 SRM 51-33-01 VOL II. LEAKED CHECKED IAW MD10 MM 28-00-02-2 WITH NO LEAKS NOTED. REFERENCE NON-ROUTINE N00687.

Part: FITTING — CRACKED (ZONE 100) · airframe 70,219 hrs · 25,826 cycles

CRACKED LONGERON END FITTING, AFT OF RIGHT HAND AIR CONDITIONING DOOR CUTOUT, LONGERON 35R, STA 535. REMOVED END FITTING IAW FEDEX SRM 51-35-01 VOLUME II PAGE 1, AREA ALODINED AND TREATED IAW FEDEX DC10 SRM 51-21-01 VOLUME II PAGE 1, RECEIVED NEW END FITTING P/N ACA3039-511CLIP LONG END; PO 462215.1;LOCATED AND DRILLED HOLES IAW FEDEX DC10 SRM51-35-01 VOLUME II PAGE 1. INSTALLED NEW END FITTING IAW FEDEX DC10 SRM 51-35-01 VOLUME II PAGE 1 AND 51-33-01 VOLUME II PAGE 1.

Part: LONGERON — WORN (ZONE 400) · airframe 70,219 hrs · 25,826 cycles

NR 1 ENGINE LEFT HAND CORE COWL UPPER CHAFE STRIP WORN. FABRICATED DOUBLER, FILLERS, AND STRAP FOR LONGERON REPAIR IAW FEDEX EA8-7110-81487. INSTALLED LONGERON REPAIR IAW DC10 SRM 51-35-01 VOLUME II. FABRICATED RUB STRIP IAW DAC DWG NSL6016. INSTALLED RUB STRIP IAW DC10 SRM 51-35-01 VOLUME II. SEE NR N00192.

Part: HINGE — CORRODED (ZONE 500) · airframe 70,219 hrs · 25,826 cycles

LT WING OB FLAP IB HINGE, LOCATION NR 6, OB BORE IS CORRODED. REMOVED CORROSION, BEGINNING BORE DIAMETER 1.240, FINAL 1.266, MATERIAL LOSS 0.026 IAW DAC CMM 57-44-08, ETCH INSPECTED IAW DAC CMM 57-44-08 AND 20-11-02. PEENED IAW DAC CMM 57-44-08 AND 20-11-01.PRIMED IAW SRM 57-21-01 VOL II, FABBED BUSHING IAW DAC CMM 57-44-08 EA 8-5750-81470. CAD PLATED BUSHING IAW CMM 57-44-08 AND 20-10-01. INSTALLED AND HONED BUSHING IAW CMM 57-44-08. REF NON-ROUTINE NR N00564

Part: VENTILATOR PANEL — CRACKED (ZONE 400) · airframe 70,219 hrs · 25,826 cycles

NUMBER 3 PYLON PRECOOLER PANEL CRACKED AT WELD CORNER. WELD REPAIRED IN NEW PIECE OF MATERIAL IAW FEDEX EA 8-5480-81477 NACELLE/PYLONS NR 3 ENGINE VENTILATOR PANELS REPAIR. REFERENCE NON-ROUTINE NR N00798.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 70,219 hrs · 25,826 cycles

FORWARD PIT DOOR, LOWER AFT CORNER OF DOOR IS DENTED AND GOUGED. ACCOMPLISHED EA 8-5230-81484, TO FORWARD CARGO DOOR SKIN BLEND OUT ON LOWER AFT CORNER. REFERENCE NON-ROUTINE NR N00253

Part: COVER — PUNCTURED (FUSELAGE) · airframe 70,219 hrs · 25,826 cycles

PUNCTURE/GOUGES ON AFT PIT LOWER AFT TORQUE BOX COVER. WELD REPAIRED IAW FEDEX EA 8-5320-81483. REFERENCE NON-ROUTINE NR N00990.

Part: SMOKE DETECTOR — INOPERATIVE (CARGO BAY) · airframe 68,053 hrs · 24,736 cycles

LOWER AFT CARGO FIRE INDICATION, BOTTLE DISCHARGED, LANDED TUL WITHOUT INCIDENT. 1L EMERGENCY SLIDE DEPLOYED. ACN RELEASED FOR SERVICE PER MEL/CDL: 26-17-01-02-B "MEL 26-17-01-02-B: ALL LWR CENTER/AFT CARGO COMPT SMOKE DETECTORS - INOP. CENTER/AFT CARGO COMPT MUST REMAIN EMPTY." ALSO SEE AMLS 26-20-5060 ,52-10-5059 , AND 26-20-5061. 01MAY03 MEM MX R/R'D NR 4 SMOKE DETECTOR WITH KNOWN GOOD UNIT. OPS OK I.A.W. AMM 26-14-01-5.

Part: SMOKE DETECTOR — DAMAGED (CARGO BAY) · airframe 67,972 hrs · 24,677 cycles

PASSING 5,000 FT IN CLIMB GOT LEVEL 3 CARGO FIRE LWR ALERT. DISCHARGED AGENT IAW CHECKLIST AND RETURNED TO LAND AT KMEM. WHEN LEVEL 3 ALERT CAME ON AGAIN, DISCHARGED OTHER BOTTLE. CARGO FIRE LWR ALERT CAME ON AGAIN 2 MORE TIMES, DURING TAXI IN. CHECKED WIRING, REPAIRED GND ON AFT DET. REMOVED AND REPLACED ALL FOUR SMOKE DETECTORS IAW MM 26-14-01-4 SAFETIED ALL CONNCTOR PLUGS. PERFORMED ALL RETURN TO SERVICE CHECKS , PERFORMED THEM SEVERAL TIMES. OK FOR SERVICE.

Part: CONTROLLER — INOPERATIVE (FIRE EXTING) · airframe 67,972 hrs · 24,676 cycles

IN CRUISE (FL330) RECIEVED CARGO FIRE INDICATION WITH MASTER WARNING AND AFT 1 FLASHING DISCHARGE LIGHT. COMPLIED W/ APPROPRIATE PROCEDURES. DIVERT TO STL. ONLY FIRED BOTTLE NR 1. REPLACED LOWER CARGO COMP FIRE EXT CONTAINER NR 1, DISCHARGE HEADS AND DISCHARGE CARTRIDGES. R & R MISC. SYS. CONTROLLER PRECAUTIONARY PER MD10 MM 31-42-01. R&R CARGO FIRE CONTROL PANEL PER MD10 AMM 26-14-10-4 PANEL OPS CK OK, PER MD10 AMM 26-14-01 PG501. PERFORMED FIRE EXTINGUISHER CIRCUITS TEST PER M/M 26-22-01. PERFORMED OPS CHECK ON MSC PER M/M 31-42-01. CARGO FIRE TEST OPS CHECKS GOOD PER M/M 26-14-01. OK FOR SERVICE.

Part: CAP — CRACKED (LT WING) · airframe 67,943 hrs · 24,657 cycles

DURING "C" CHECK, LT WING UPPER CAP AT RIB STATION XORS 402 CRACKED. THE CRACK WAS ALL THE WAY THRU THE CAP AND WAS LOCATED IMMEDIATELY FWD OF STRINGER 15.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 67,943 hrs · 24,657 cycles

DURING "C" CHECK, ON RT HORZ STAB UPPER REAR SKIN PANEL FOUND CRACK ONE INCH LONG. REPAIRED PER IAW DOUGLAS SB 55-18 R1 FIG 2 (REF FEDEX NRC N 381).

Part: BULKHEAD — CORRODED · airframe 66,681 hrs · 24,042 cycles

SNRM 539 RMLG W/W FWD BULKHEAD & CTR TANK UPR AFT CHORD WITH PANEL CORRODED. ** S/D ** COMING

Part: CONTROL VALVE — CRACKED (HORIZ STAB)

HORIZONTAL STABILIZER UPPER TRIM CONTROL VALVE HAD CRACKED IND INSIDE FLOW CONTROL VALVE BORE APPROX .5 INCH. *S/D* REMOVED AND REPLACED HORIZONTAL STABILIZER PER M/M 27-43-03-4 OPS AND LEAK CK OK.

Part: CLIP — CRACKED (WS 402)

VCE: N 1617, AT STA XORS 402, STRINGER NR 36, FOUND CLIP CRACKED ON LEFT WING LOWER SURFACE.

Part: CABLES — RUSTED (RT AILERON)

N0735, AILERON LOCKOUT CONTROL CABLE RUN NUMBER 91B. RUSTED AND WEAR OFF LIMITS.

Part: CABLES — RUSTED (RT AILERON)

N0738, SPOILER CONTROL CABLES RUN NUMBER 15 A-B-C-D-E-F, 16 A-B-C-D-E-F, 17 A-B-C-D, 18 A-B-C-D. RUST AND WEAR OFF LIMITS.

Part: CABLES — RUSTED (RT AILERON TRIM)

N0736, AILERON TRIM CONTROL CABLE RUN NUMBER 24A. RUSTED AND WEAR OFF LIMITS.

Part: CABLES — RUSTED (RT AILERON)

N0737, FLAP FOLLOW UP CONTROL CABLES RUN NUMBER 165A, 165B, 166A, 166B, 167A, 167B, 168A, 168B. RUSTED AND WEAR OFF LIMITS.

Part: CABLES — RUSTED (RT AILERON)

N0739, AILERON CONTROL CABLES RUN NUMBER 9 E-F-G, 10 E-F-G. RUSTED AND WEAR OFF LIMITS.

Part: FAN — FAILED (NR 1 PACK)

VCE: N0317 FAN DIFFUSER ASSEMBLY, PACK NR 1, FOUND ACM COUPLING FLANGE BURNT. INSTALLED NEW PLENUM, COOLING ASSY P/N 2201968-2 IAW M/M 21-53-01. REPLACED REFRIG PACK FAN P/N 204943-2 IAW M/M 21-53-02.

Part: BULKHEAD PLATE — MISINSTALLED (NR 3 PYLON)

VCE: N0151. NR 3 PYLON FRONT SPAR BULKHEAD LOWER PLUG PLATE P/N AUB7125-1 INCORRECTLY INSTALLED - BEVELED SIDE FACING FORWARD INSTEAD OF AFTWARD. *** S/D *** COMING.

Part: BULKHEAD PLATE — MISINSTALLED (NR 1 PYLON)

VCE: N0150. NR 1 PYLON FRONT SPAR BULKHEAD LOWER PLUG PLATE P/N AUB7125-1 INCORRECTLY INSTALLED - BEVELED SIDE FACING FORWARD INSTEAD OF AFTWARD. *** S/D *** COMING.