N395FE

Part: INDICATOR — INOPERATIVE (ESCAPE SLIDE) · airframe 83,652 hrs · 35,148 cycles

DOOR EVACUATION SLIDE REMOTE PRESSURE PRESS TO TEST INDICATOR INOPERATIVE. REPLACED L1 DOOR REMOTE SLIDE PACK PRESSURE INDICATOR REF AMM 25-61-03-2. CHECKED OK NOW REF AMM 25-61-03-5.

Part: BULKHEAD WEB — CRACKED (MLG WW) · airframe 83,002 hrs · 34,800 cycles

CENTER LANDING GEAR WHEEL WELL SPACE HAS 3 CRACKS COMING FROM A PRODUCTION HOLE IN THE UPPER FWD CORNER OF THE LT WALL INNER SKIN. THE OUTER SKIN HAS ONE CRACK FROM THE SAME PRODUCTION HOLE THAT EXTENDS THROUGH A RIVET HOLE. ALL CRACKS WERE CHECKED USING HFEC. REPAIRED CRACKED WEB IN CENTER LANDING GEAR WHEEL WELL UPPER FWD CORNER OF LT WALL REF EA 8-5310-157336.

Part: SKIN — DELAMINATED (NR 1 SPOILER) · airframe 82,912 hrs · 34,750 cycles

LEFT WING UPPER SURFACE JUST FWD OF NR 1 SPOILER INBD END, PANEL IS DELAMINATED. REPAIR CLASSIFIED AS A MINOR REPAIR.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 82,912 hrs · 34,750 cycles

LEFT WING OTBD FLAP LOWER SURFACE SKIN BET X-467 AND X-478 HAS SEVERAL DENTS. FOUND DENTS OUT OF LIMITS IAW SRM 51-80-01, VOL II AND 57-10-00, VOL I. REPAIRED DAMAGED AREA IAW SRM 57-10-00, FIGURE 7. MAJOR REPAIR.

Part: STRUCTURE — CORRODED (BS 1772-1781) · corrosion level 2 · airframe 82,912 hrs · 34,750 cycles

CENTER CARGO LOWER BOX BS 1772 TO 1781 UNDER STRAP HAS HEAVY CORROSION. REMOVED CORROSION ORIGINAL MATERIAL .050 MATERIAL LOSS .025 OUT OF LIMITS IAW SRM 43-00-01 FIG1. CUT OUT DAMAGED SECTION IAW SRM 53-00-01. FABRICATED NEW SUPPORT. FABRICATED FILLER IAW SRM 53-00-01 FIG 10. INSTALLED SUPPORT AND FILLER IAW SRM 51-31-01. MAJOR REPAIR

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 80,295 hrs · 33,392 cycles

MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR1, NR2, NR3, NR4, NR5 AND NR6 HAS CRACKS EMANATING FROM MOUNT BOLT HOLES. R & R MAIN CARGO DOOR LOWER JAMB SUPPORT FITTINGS NR1, NR2, NR3, NR4, NR5 AND NR6 IAW DWG : ACA7224.

Part: PUSH-PULL CABLE — STUCK (NR 1 ENGINE) · airframe 78,646 hrs · 32,598 cycles

AT FL 360 IN CRUISE NR 1 AND NR 3 THROTTLES RAPIDLY CAME TO IDLE WHILE NR 2 STAYED AT ITS CRUISE SETTING (95.4). DISCONNECTED AUTO THROTTLES AND TRIED TO MARRY THROTTLES. NR 2 WAS FROZEN AND REMAINED FROZEN THROUGHOUT FLIGHT. IN DESCENT HAD TO SHUTDOWN ENG NR 2 DUE TO STUCK THROTTLE AT HIGH POWER SETTING. ALL OTHER ENGINE LIMITATIONS NORMAL. REMOVED AND REPLACED NR 2 ENGINE THROTTLE PUSH-PULL CABLE IAW AMM 76-11-01-2.

Part: PROXIMITY SENSOR — OUT OF ADJUST (MLG) · airframe 77,551 hrs · 32,076 cycles

DURING DESCENT WHEN SPEED BRAKE DEPLOYED RIGHT MAIN GEAR UNSAFE LT, RED LT DISPLAYED. RED SHOWING ON SD TOO. NO ABNORMAL YAW FELT. GEAR EXT NORMAL ALL GREEN. SWUNG GEAR. FOUND WING DOOR NOT FAIRED (DN .25"). ADJ WING DOOR TO FAIRED. REF MM 32-14-01-2. CHECKED GEAR DOOR GAPS. GAPS OK. CHECKED HOOK AND ROLLER CLEARANCE. CLEARANCE OK. FOUND PROX SENSOR GAP AT .230 INCH RESHIMMED TO .180 INCH. SWUNG GEAR ALL IND AND CLEARANCES OK MD10 MM 32-34-03-2.

Part: DOOR — OUT OF ALIGNMENT (MLG) · airframe 77,545 hrs · 32,071 cycles

AFTER GEAR RETRACTION RT MAIN INDICATION REFLECTED UNSAFE (RED) INTERMITTANLY CYCLED GEAR REF QRG AND UNSAFE GEAR INDICATION REMAINED OUT ON SLOW DOWN FOR LANDING UNSAFE RT MAIN GEAR AT 200 KNOTS UNSAFE INDICATION ON PRI AND SEC SOURCES, SWUNG GEAR. FOUND WING DOOR NOT FAIRED (DN .25 INCH). ADJ WING DOOR TO FAIRED. REF MD10MM 32-14-01-2. CK'D GEAR DOOR GAPS. GAPS OK. CK'D HOOK AND ROLLER CLEARANCE. CLEARANCE OK. FOUND PROX SENSOR GAP AT .230 INCH RESHIMMED TO .180 INCH. SWUNG GEAR ALL IND AND CLEARANCES OK. REF MD10MM 32-34-03-2.

Part: SEAT TRACK — CHAFED (ZONE 200) · airframe 77,408 hrs · 31,993 cycles

MAIN CARGO COMPT SEAT TRACK HAS DAMAGED AREAS AT F/S 735-755 LBL8 EVALUATED AND FOUND OUT OF LIMITS. REMOVED FLOOR PANELS AND SEAT TRACK. FABED NEW TRACK AND SPLICE ON TRAVELERS T8/744729,T8/744769, T8/744782. INSTALLED NEW TRACK AND SPLICES AND REINSTALLED FLOOR PANELS ALL IAW SRM 51-31-01, 53-70-00 FIG 5. REPAIR IS CLASSIFIED AS A MAJOR REPAIR.

Part: PRESSURE PANEL — CORRODED (BS 1381) · airframe 74,950 hrs · 30,884 cycles

LT MAIN LANDING GEAR WHEEL WELL SEVERE CORROSION WITH EXFOLIATION ON TEE AND ANGLE OF SLANT PANEL AT STA 1381 FROM X=108 TO X=114. REMOVED LT SLANT PANEL IAW MM20-50-02-2. REMOVED CORROSION IAW SRM51-21-01 PAR 34 VOL2 AND REMAIN MAT IS WITHIN LIMITS IAW SRM53-40-00 VOL1 FIG11 SHT1. REMOVED CORROSION CUTOUT AREA IAW SRM 51-21-01 PAR 34 VOL2 AND REMAIN MAT IS WITHIN LIMITS IAW SRM57-20-00 VOL1 FIG 8A SHT2. DURING REWORK FOUND CORR UP SKIN STRAP. REMOVED BOLTS IAW MM 20-50-02-2. REMOVED CORR IAW SRM 51-21-01 PAR 28 VOL2 OUT OF LIMITS IAW SRM 57-00-01 FIG1A VOL1. INSP IAW NDTSPM 08, NO CORR FOUND. ACCOMPLISHED EA# 8-5320-103665. INSTALLED SLANT PANEL AND CLAMPS IAW MM20-50-02-2. INSTALLED NEW BOLTS IAW EA

Part: UNKNOWN — CRACKED (BS 595) · airframe 74,950 hrs · 30,884 cycles

LOWER FWD CARGO COMPT 2 CRACKS 1" LONG ON CAP AT L35 LT & AT L39 LT AT STA 595. ACCOMPLISHED EA NR 8-5310-96117.

Part: SKIN — CORRODED (BS 1725) · airframe 74,950 hrs · 30,884 cycles

EXT FUSELAGE, DEEP CORROSION WITH EXFOLIATION ON SKIN AT STA 1725 L52 C/L. REMOVED EXISTING ANTENNA, AND PARTS IAW SRM51-35-01 VOL 2. CUT OUT ALL SKIN EXFOLIATED IAW SRM53-00-01 FIG1B. FOUND INTERCOSTAL MODERATE CORROSION. REMOVED CORROSION MECHANICALLY AND SAND BLASTING METHOD IAW SRM 51-21-01 VOL 2 PAR 34A- B. REMAINING MAT THK IS WITHIN LIMITS IAW SRM53-00-01FIG 1B VOL1. REPROTECT AREA IAW SRM51-21-01 VOL2. REPAIRED AREA IAW CRITERIA OF SR10530034 DWG AND SRM 53-20-00 FIG6 SHT3. REMOVED FOR ACCESS IAW SRM 51-35-01 VOL2. SEALED AREA PER SRM 51-41-02 VOL 2. FAB PARTS IAW PARTS TRAVELER NR I020903-3 FILLER, I020903-7 DOUBLER, I020903-17 OUT EXT DOUBLER AND I020903-19 INNER EXT DOUBLER IAW DWGSR105300

Part: PRESSURE PANEL — CORRODED (BS 1381) · airframe 74,950 hrs · 30,884 cycles

RT MLG W/W ON STRUCTURE SLANT PANEL AT STA 1381 X-115 ON TEE FOUND SEVERE CORROSION WITH EXFOLIATION. REM SLANT PNL IAW MM20-50-02. AFTER REM SLANT PNL FOUND SEAL BROKEN AND QTY17 P/N AEA0476-505 CLAMP QTY4 P/N AEA0476-509, QTY3 P/N AEA0476-507, QTY1 P/N AEA0481-2 CLAMP WORN. REMOVED CORROSION IAW SRM 51-21-01PAR34 VOL1 ORIG MAT THK IS .260" IAW SRM 53-40-00 PAGE 55. MAT REM .088" REMAIN THK .172", MAT REM 33.8 PERCENT IS WITHIN LIMITS IAW SRM53-40-00 VOL1 FIG 11 SHT 1 IAW SRM 51-21-01 VOL2 PAR 22. PROTECTED AREA IAW RM53-40-00 VOL1 FIG11. INSTALLED SLANT PNL EXCEPT 3EA CLAMP IAW DWG AEA0441. INSTALL SLANT PANEL, FOUND QTY 1 P/N AEA0481-2 AND QTY2 P/N AEA0476-509 CLAMP WORN. REPLACED CLAMPS IAW DWG A

Part: RIB — CRACKED (RT WING) · airframe 74,950 hrs · 30,884 cycles

RT WING AT XORS 346 RIB LOWER CAP LUG IS CRACKED BTWN STR NR 43 AND 44. ALL FUEL PIPES REMOVED FOR ACCESS IAW MM 28-24-01-2. REPAIR TEE INSTALLED IAW SRM 57-20-00 FIG 27 VOL 1 SHT 2, FUEL PIPES REINSTALLED IAW MM 28-24-01-2. FABRICATED PART IAW DETAIL PART TRAVELER N00426/I020426 AND SRM 57-20-00 FIG 27 VOL 1 SHT 2 AND 4.

Part: SEAT TRACK — CORRODED (BS 1381-1521) · airframe 74,950 hrs · 30,884 cycles

MAIN CABIN COMPT FOUND CORROSION WITH EXFOLIATION ON SEAT TRACK FROM STA 1381 TO STA 1521 AT X = 107 LT SIDE. CUT REMOVED CORRODED SECTION OF TRACK, INSTALLED NEW SECTION TRACK AND SPLICE -7A IAW SRM 53-70-00 FIG 1 SHT 1/3 VOL 1. FABRICATED PARTS IAW DETAIL PARTS TRAVELER N00289 AND IAW SRM 53-70-00 FIG 1 SHT 4 VOL 1.

Part: STRUCTURE — CRACKED (NR 2 NACELLE) · airframe 74,950 hrs · 30,884 cycles

PYLON NR 2 AT STA YID 453.322 UPPER SURFACE ON HORIZ WEB STRUCTURE FOUND CRACK 2.5" LONG. REMOVED AFT PYLON UPPER FAIRING (RIF SRM 54-52-02 VOL 3). PERFORMED REPAIR IAW EA# 8-5450-103662. REINSTALLED FAIRING IAW SRM 54-52-02 VOL 3.

Part: DOOR FRAME — CRACKED (BS 1256) · airframe 74,950 hrs · 30,884 cycles

MAIN CABIN COMPT ON UPPER FAUND WEB JAMB NR 3 LT DOOR AT 1256 1 CRACK .50" LONG. REPAIRED DOOR JAMB WEB IAW SRM 53-50-00 FIG 19 SHT 11 VOL 1. FABRICATED PARTS IAW DETAIL PARTS TRAVELLER N00285 AND IAW SRM 53-50-00 FIG 19 SHT 1.4 VOL 1.

Part: BULKHEAD — CRACKED (BS 478) · airframe 74,950 hrs · 30,884 cycles

RT AIR COND COMPT CRACK 2.5" LONG ON BULKHEAD AT STA 478 X = -24 Z = -39. TRIMMED CRACK AND INSTALLED FILLER AND 2 DOUBLERS IAW SRM 53-00-01 FIG 10 SHT 5 VOL 1. FABRICATED PARTS IAW DETAIL PARTS TRAVELER NR I020585/N00585 AND SRM 53-00-01 VOL 1 AND TOUCH UP IAW SRM 51-21-01 VOL 2. REINSTALLED AIR CONDITION, CHECK VLV IAW MM 20-50-02-2.

Part: UNKNOWN — UNKNOWN · airframe 74,950 hrs · 30,884 cycles

DURING U/S INSPECTION ON CONSTANT AND OUTER SEC STB, FOUND CRACKS WHEN SHOWN AN ATTACHED SHEET. REMOVED PANEL ALC7206-1 IAW SB 55-16 GROUP 1, CLEANED BOLTS AND INSPECTED IAW SB 55-16 PAGE 28 STEP K. PANEL INSTALLED NEW P/N ALC7206-1 IAW SB 55-16 GROUP 1 AND EA#8-5510-96109.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 74,950 hrs · 30,884 cycles

LOWER FUSELAGE FWD CARGO COMPT AT STA 755 X = 47 Z = -18 ON SEAT TRACK FOUND CRACK 3" LONG. REMOVED AND REPLACED CRACKED SECTION OF SEAT TRACK IAW SRM 53-70-00 FIG 1 VOL 1. REMOVED AND REPLACED DAMAGED FLOOR PANELS IAW SRM 53-60-00 VOL 1 PAGE 26. FABRICATED PARTS IAW DETAIL PARTS TRAVELER N/R N00246 AND SRM 53-70-00 FIG 1 VOL 1 AND SRM 53-60-00 VOL 1 PAGE 26 AND REF EO NR 8-5321-7-3000.

Part: SKIN — CORRODED (RT WING) · airframe 74,950 hrs · 30,884 cycles

RT WING L/E DROOP FOUND CORROSION WITH EXF ON EXT SKIN. REMOVED SEAL IAW SRM 51-31-01 VOL 2 PAGE 36/41. REMOVED RUB STRIP IAW SRM 51-31-01 VOL 2 PAGE 36/41. REMOVED EXISTING REPAIR IAW SRM 51-31-01 VOL 2 PAGE 1/13. CLEANED AREA IAW SRM 51-21-01 VOL 2 PAR 22. TRIMMED OUT DAMAGED SKIN IAW SRM 57-00-01 VOL 1 FIG 4 SHT 2. PARTS ARRIVED WRONG FROM BACK-SHOP. INSTALLED REPAIR PART IAW SRM 57-00-01 VOL 1 FIG 4 SHT 2. REINSTALLED RUB STRIP AND SEAL IAW SRM 51-31-01 VOL 2 PAG 36/41. FABRICATED PARTS IAW DETAIL PARTS TRAVELER# I020236/N00236-3A REPAIR DOUBLER AND I020236-5A FILLER IAW SRM 57-00-01FIG 4 SHT 2 VOL 1.

Part: SKIN — DENTED (BS 1796) · airframe 74,950 hrs · 30,884 cycles

LWR EXT FUSELAGE FOUND 2 DEEP DENTS ON SKIN, ONE 5" BY 1.50" DEEP .07" BTWN LONG NR 44 AND LONG NR 45 AT STA 1796 LT. TWO 5.50" BY 1" DEEP .03" BTWN LONG NR 44 AND LONG NR 43 FROM STA 1761 AND 1781 LT. PERFORMED DENT IAW SRM 51-70-00 VOL 2 PAR 2. PERFORMED EDDY CURRENT INSP IAW NDT SPM 06, NO CRACK FOUND. INSTALLED NEW REPAIR DOUBLERS IAW SRM 53-20-00 VOL 1 FIG 6 SHT 3-6.

Part: WEB — MISREPAIRED (BS 1156) · airframe 74,950 hrs · 30,884 cycles

INTERNAL FUSELAGE CAC COMPARTMENT AT STA 1156 BETWEEN X = 75 AND X = 50 EXISTING WEB REPAIR. PERFORMED INSPECTION OF REPAIR AND FOUND NOT INCOMPLIANCE WITH CRITERIA REQUEST BY EO NR 8-5100-7-5001 P1 BECAUSE FOUND 2 RIVETS WITH HEADS BROKEN. REMOVED FASTENERS IAW SRM 51-31-00 VOL 2. PERFORMED INSPECTION IAW NDI SPM 06 NO CRACK FOUND. INSTALLED RIVETS IAW SRM 53-40-00 FIG 4 VOL 1.

Part: WEB — MISREPAIRED (BS 1156) · airframe 74,950 hrs · 30,884 cycles

INTERNAL FUSELAGE CAC COMPARTMENT AT STA 1156 BETWEEN X = -75 AND X = -50, EXISTING WEB REPAIR. PERFORMED INSPECTION OF REPAIR AND FOUND NOT IN COMPLIANCE WITH CRITERIA REQUEST BY EO NR 8-5100-7-5001 P1 BECAUSE FOUND NR 5 RIVETS WITH HEADS BROKEN. REMOVED FASTENERS IAW SRM 51-35-01 VOL 2. PERFORMED INSP IAW NDI SPM 06, NO CRACK FOUND. REINSTALLED RIVETS IAW SRM 53-40-00 VOL 1 PAGE 4.

Part: COMPUTER — MALFUNCTIONED (NR 2) · airframe 72,693 hrs · 29,731 cycles

ON ROTATION THE FIRST OFFICERS ALTIMETER DESCENDED TWO THOUSAND FEET (-2000). ALTIMETER REMAINED 2000 FT BELOW THE CAPT'S ALT AND STANDBY ALT REMAINDER OF FLIGHT. SWITCHED CADC'S, NO CHANGE - ALT STATIC SOURCE NO CHANGE. REMOVED AND REPLACED NR 2 AIR DATA COMPUTER IAW DC10-10 AMM 34-16-01-2. NR 2 ALTIMETER SYSTEM OPERATIONAL CHECKS NORMAL, NO DISCREPANCIES NOTED. PREMATURE REMOVAL/INSTALLATION, OFF MFG HG280D4, POS P2 SRL 465, TAG A03096, ON MFG HG280D80 SRL 115, TAG 590682.

Part: ALTIMETER — READS LOW (COCKPIT) · airframe 72,684 hrs · 29,727 cycles

F/O ALTIMETER FAILED IN FLIGHT. READS 450FT LOW AND FLUCTUATES /- 30 FT AT FL280. NOT RVSM CAPABLE. REPLACED F/O'S ALTIMETER PER 34-12-01-2 1. OPS CK NORMAL.

Part: SUPPORT FITTING — GOUGED (ZONE 400) · airframe 63,702 hrs · 19,598 cycles

NR 1 PYLON, STATION YN256, MOUNT BRACKET FOR LEFT AND RIGHT THRUST REVERSER ACTUATORS, OPEN/CLOSE BEARING WORN AND GOUGED. COMPLIED WITH FEDEX EA 8-5450-83973, NACELLES/PYLON - NR 1 PYLON FAN REVERSER JACK SCREW SUPPORT FITTING GOUGED - REPAIR, REMOVED AND REPLACED LEFT HAND AND RIGHT HAND BEARING IAW BOEING SOPM 20-50-03.

Part: HINGE — CORRODED (ZONE 600) · airframe 72,547 hrs · 29,650 cycles

RIGHT WING INBOARD FLAP HINGE INBOARD PIVOT BUSHING GALLED AND PITTED. MEASURED BORE DIAMATER, FOUND TO BE OUT OF LIMITS IAW DAC CMM 57-52-01. ALODINE AND PRIMED BORE IAW DC10-10 SRM 51-21-01 VOL 2, FABRICATED, INSTALLED AND HONED BUSHING TO A FINAL INSIDE DIAMETER OF .9995-1.0005 IAW DAC CMM 57-52-01 AND FEDEX EA 8-5750-83955, RIGHT HAND INBOARD FLAP, OUTBOARD HINGE BRACKET OVERSIZE PIVOT BORE- REPAIR, REFERENCE NON-ROUTINE N00386.

Part: FRAME — DENTED (ZONE 100) · airframe 72,547 hrs · 29,650 cycles

STATION 322 ON LEFT SIDE OF NOSE FUSELAGE JUST BELOW COCKPIT FLOOR FRAME IS DENTED. REFERENCE NON-ROUTINE N01203. COMPLIED WITH FEDEX EA 8-5310-83962,

Part: HINGE — CORRODED (ZONE 600) · airframe 72,547 hrs · 29,650 cycles

RIGHT WING INBOARD FLAP HINGE OUTBOARD PIVOT BUSHING GALLED AND PITTED. MEASURED BORE DIAMETER, FOUND TO BE OUT OF LIMITS IAW CMM 57-52-01, ALODINE AND PRIMED BORE IAW DC10-10 SRM 51-21-01. FABRICATED, INSTALLED AND HONED BUSHING TO A FINAL INSIDE DIAMETER OF .9995 - 1.0005 IAW DAC CMM 57-52-01 AND FEDEX EA 8-5750-83995, RT INBOARD FLAP, OUTBOARD HINGE BRACKET OVERSIZE PIVOT BORE - REPAIR. REFERENCE NON-ROUTINE N00385.

Part: SKIN — DENTED (ZONE 100) · airframe 72,547 hrs · 29,650 cycles

FIRST OFFICERS PRIMARY STATIC PORT HAS EXTERNAL DOUBLER REPAIR WITHIN REDUCED VERTICAL SEPARATIONS. MINIMUN CONTROLLED AREA AT THE 9 TO 10 O'CLOCK POSITION PREVENTING REDUCED VERTICAL SEPARATION OPERATION UNDER FEDEX DC10-10 SRM 53-00-00. REPAIR WAS ACCOMPLISHED PER FEDEX EA 8-5330-83961.

Part: HINGE — CORRODED (ZONE 500) · airframe 72,547 hrs · 29,650 cycles

LEFT WING INBOARD FLAP HINGE INBOARD PIVOT BUSHING GALLED AND PITTED. MEASURED BORE DIAMETER, FOUND TO BE OUT OF LIMITS IAW DAC CMM 57-52-01, ALODINE AND PRIMED BORE IAW DC10-10 SRM 51-21-01 VOL 2, FABRICATED, INSTALLED AND HONED BUSHING TO A FINAL INSIDE DIAMETER OF .9995 - 1.0005 IAW DAC CMM 57-52-01 AND FEDEX EA 8-5750-83956, WINGS, LEFT HAND INBOARD FLAP, OUTBOARD HINGE BRACKET, OVERSIZED PIVOT BORE REPAIR, REFERENCE NON-ROUTINE; N00390.

Part: BALANCE WEIGHT — CORRODED (ZONE 600) · airframe 72,547 hrs · 29,650 cycles

RIGHT WING OUTBOARD AILERON 1 EACH BALANCE WEIGHT HAS CORROSION OUTBOARD SIDE OF ACTUATOR. REMOVED AND REPLACED RIGHT WING OUTBOARD AILERON BALANCE WEIGHT, BALANCE WITHIN LIMITS IAW FEDEX EA 8-5751-83957, WINGS REPLACEMENT OF CORRODED RIGHT HAND OUTBOARD AILERON BALANCE WEIGHT.

Part: BALANCE WEIGHT — CORRODED (ZONE 500) · corrosion level 2 · airframe 72,547 hrs · 29,650 cycles

LEFT WING OUTBOARD AILERON INBOARD BALANCE WEIGHT CORRODED. REMOVED AND REPLACED LEFT WING OUTBOARD AILERON INBOARD BALANCE WEIGHT IAW FEDEX EA 8-5751- 83958, WINGS-REPLACEMENT OF CORRODED LEFT HAND, OUTBOARD AILERON BALANCE WEIGHT.

Part: HINGE — CORRODED (ZONE 500) · airframe 72,547 hrs · 29,650 cycles

LEFT WING INBOARD FLAP HINGE OUTBOARD PIVOT BUSHING GALLED AND PITTED. MEASURED BORE DIAMETER, FOUND TO BE OUT OF LIMITS IAW DAC CMM 57-52-01, ON NON-ROUTINE N00390. FABRICATED, INSTALLED AND HONED BUSHING TO A FINAL INNER DIAMETER OF .9995-1.0005 INCHES IAW DAC CMM 57-52-01 AND FEDEX EA 8-5750-83956, WINGS- LEFT HAND INBOARD FLAP, OUTBOARD HINGE BRACKET OVERSIZED PIVOT BORE- REPAIR.

Part: BALANCE WEIGHT — CORRODED (ZONE 500) · corrosion level 2 · airframe 72,547 hrs · 29,650 cycles

LEFT WING OUTBOARD AILERON CENTER BALANCE WEIGHT CORRODED.

Part: SPAR — CRACKED (ZONE 300) · airframe 72,547 hrs · 29,650 cycles

VERTICAL STABILIZER AFT CENTER SPAR HAS CRACK STATION ZFR 328, YV237.628. REMOVED PANEL AND WEB IAW DC10 SRM 51-35-01 VOL 2. REPAIRED CENTER SPAR DOUBLER IAW FEDEX EA 8-5530-83960, STABILIZER - VERTICAL AFT CENTER SPAR DOUBLER CRACK-REPAIR. REINSTALLED PANEL AND WEB IAW DC10 SRM 51-35-01 VOL 2.

Part: FITTING — CRACKED (FUSELAGE) · airframe 72,547 hrs · 29,650 cycles

CENTER ACCESSORY COMPARTMENT AT FUSELAGE STATION 1156 LT WING BOX FITTING IS CRACKED. REMOVED INNER ATTACHED ANGLE IAW DC10 SRM 51-33-01 VIL 2, FABRICATED REPAIR PARTS AND INSTALLED REPAIR PARTS IAW DC10 SRM 51-21-01 VOL 2 AND 53-30-00 VOL 1. REINSTALLED INNER ATTACH ANGLE IAW D10 SRM 51-33-01 VOL 2. REFERENCE NON-ROUTINE N00184

Part: FITTING — CRACKED (FUSELAGE) · airframe 72,547 hrs · 29,650 cycles

CENTER ACCESSORY COMPARTMENT FUSELAGE STATION 1156 RIGHT HAND WING BOX FITTING IS CRACKED AT APPROX LONGERON 27 RIGHT. REMOVED INNER ATTACHED ANGLE IAW DC10 SRM 51-33-01 VOL 2, FABRICATED AND INSTALLED SPLICED ANLES AND FILLERS IAW DC10 SRM 53-30-00 VOL 1 FIGURE 7. REINSTALLED INNER ATTACH ANGLE IAW DC10 SRM 51- 33-01 VOL 2. REFERENCE NON-ROUTINE N00185.

Part: PANEL — MISSING (NR 2 NACELLE) · airframe 71,494 hrs · 29,091 cycles

ON ARRIVAL WALKAROUND CHECK FOUND NR 2 ENGINE LEFT FWD LOWER PICKLE BARREL PANEL MISSING. RECEIVED PANEL AJC7077-1, PRE-DRILLED HOLES DO NOT LINE UP WITH STRUCTURES HOLES. COMPLIED WITH EA 8-5410-76625 PART 1. FLEW A/C TO IND FOR PERMANENT REPAIR. COMPLIED WITH EA 8-5410-76625 PART 2 AS REQUIRED. PNL 363AL UPPER HINGE HALF HAS ELONGATED HOLES, PERFORMED PERMANENT REPAIR TO HINGE HALF. CONNECTED TO PANEL. REPAIR REF EA 8-5410-76625.

Part: SLEEVE — BROKEN (MLG) · airframe 70,085 hrs · 28,393 cycles

LT MLG TRUCK BEAM OUTBOARD PIVOT BORE SLEEVE IS BROKEN AS VIEWED IN FWD AND AFT OUTBOARD BEAM ASSY. BORES. 05/29/03 A.M.M. 32-12-01-2 - SHOWS WASHER BETWEEN FLANGE BUSHINGS, WASHER AND MATING SURFACE AS BUSHING IS WHAT APPEAR TO BE A CHANK ON BUSHING. NO CRACK CONDITION EXIST.

Part: PIVOT ASSY — SEIZED (RT HORIZ STAB) · airframe 70,085 hrs · 28,393 cycles

HORIZ STAB CONSTANT SECTION BEARINGS - SUSPECTS R/H PIVOT BEARING IS FROZEN. PIVOT BEARING SHAFT HEAD MOVED INTO SUPPORT RETAINER. PREFORMED PIVOT BOLT LUBRICATION PER W/C 27C2116, FUNCTIONED ENTIRE HORIZONTAL STAB TO FULL ANUG AS WELL AS FULL A N D PER W/C27C4602. NO BINDING OR POPPING NOISE NOTED. 5/16/03.

Part: SHUTOFF VALVE — FAILED (HYD SYSTEM) · airframe 61,502 hrs · 24,226 cycles

00-349 AC EXPIRENCED HYD SYS 3 ELEVATOR OFF LIGHT. 3-2 NON-REVERSIBLE MOTOR PUMP SHUT OFF VALVE FAILED. R&R VALVE ASSY IAW MM 27-26-03-2 & EA 8-2910-55728. OPS CK GOOD.

Part: CONTROLLER — INOPERATIVE (PITOT HEAT)

DURING ROTATION MASTER CAUTON PITOT HEAT INOP LIGHT CAME ON. CONTINUE RED TAB. PITOT HEAT INOP. INSTALL PITOT HEAT CONTROL MONITOR AND TAT PROBE PER MM 30-30-00-2, 34-16-02-2.

Part: INDICATOR — FAILED (NR 2 ENGINE)

NR 2 ENGINE FAILED INFLT. FAILURE WAS PRECEEDED BY INTERMITTENT BLINKING OF THE RT AFT FUEL PUMP LOW PRESS LIGHT. NO FUEL PRESSURE IND. *S/D* REMOVED AND REPLACED 5 PLUG RECEPTICALS AND LT WIRING HARNESS AND LT NR 2 TANK MJP. REFUELED TANK AND TEST NORMAL.

Part: BEARING — FAILED (RAM AIR VALVE)

DURING D-CK INSP, FOUND VALVE ASSY EXHAUST, RAM AIR BEARING (P/N DT16A) DAMAGED. DURING BEARING REMOVAL I/B FLANGE WERE DAMAGED. FLANGE REPAIRED INSTALLING BUSHING IAW FEDEX EA NR 8-2160-45652.

Part: DOUBLER — DENTED (CARGO DOOR)

DURING A/C P-F CONV AT AERONAVALI, INSP FOUND SEV DENTS AFFECTING THE FWD CARGO DOOR DOUBLER AT Y=996 BETWEEN LONGERONS 45R-46R. REMOVED AND REPLACED SECTION OF DOUBLER (P/N ADA3024-1) AND INSTALLED SPLICE IAW FEDEX EA 8-5333-45543.