N384FE

Part: LIGHT — INOPERATIVE (CABIN) · airframe 77,440 hrs · 31,423 cycles

EMERGENCY LIGHT FUNCTIONAL TEST FOUND INOPERATIVE.

Part: THROTTLE — BINDING (NR 1) · airframe 77,084 hrs · 31,223 cycles

AFTER LEVEL OFF, NR 1 THROTTLE STUCK AT CLIMB POWER. DISCONNECTED AUTO THROTTLES, NO HELP. AFTER 10 MIN, THROTTLE CAME FREE. CONTINUED WITH AUTO THROTTLE DISCONNECTED. THROTTLES WORKED NORMALLY THRU ENTIRE FLT. INSPECTED PUSH-PULL CABLE & PUSH-PULL CABLE AT ENGINE END HAD A STICKY CONTAMINANT. REMOVED CONTAMINANT WITH ALCOHOL. PURGED PUSH-PULL CABLE IAW MM76-11-02-2. NO FURTHER DEFECTS NOTED. PERFORMED PUSH-PULL CABLE FORCE & FORCE WAS APPROX 4 -4.5LBS. INSPECTED THROTTLE QUADRANT IN AVIONICS BAY & THROTTLE IDLER CRANK ON PYLON, NO DEFECTS NOTED. PERFORMED AUTOTHROTTLE TEST MM 22-00-00-5. ALL TESTS PASSED.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 77,018 hrs · 31,190 cycles

EMERGENCY LIGHT NR 1 BATTERY LOW, ILLUMINATED DURING EMERGENCY LIGHT TEST. R & R EMERGENCY LIGHT BATTERY POWER SUPPLY AND TESTED IAW AMM 33-51-01-4. ALL TESTED NORMAL. OK FOR SERVICE.

Part: LIGHT — MALFUNCTIONED (CABIN) · airframe 76,835 hrs · 31,098 cycles

EMERGENCY LIGHT 1 LOW DISPLAYED DURING EMERGENCY LIGHT TEST. RELEASED FOR SERVICE PER MEL: 33-50-02. COULD NOT DUPLICATE MALFUNCTION. OPERATIONAL TEST, OK IAW AMM 33-51-01-5. NO HISTORY FOR PAST 90 DAYS ITEM CLEARED. OK FOR SERVICE.

Part: CONNECTOR — DAMAGED (ANTI ICE SYS) · airframe 76,219 hrs · 30,786 cycles

AIR MANF 3 FAIL WHEN WING ANTI ICE PLACED ON FOR DESCENT. MAX TEMP INDICATE 190 C. BLEED AUTO SHUTDOWN. ONLY MANIFOLD LIGHT ON, NO TEMP HI LIGHT. FOUND RT WING PRESSURE SWITCH TRIPPED. RESET PRESSURE SWITCH. ACCESSED PSC-3 CURRENT FAULT SHOWS PRSOV LOW FAULT, FAULT CODE 361033. NR3 SYS PASSES PRESSURE DECAY CHECK IAW AMM 36-00-01-5. SHOWS NUMEROUS LEGS FAULTED FOR CODE 361033. FOUND P1-8096 BACKSHELL DAMAGED AND CONNECT OFF TO PRSOV BACKSHELL NEEDS TO BE REPLACED. ONE IN STOCK. REPLACED CONNECTOR PLUG P1-8096 IAW MM20-30-02-2-0. PERFORMED R-T-S ON PSC NR3, NO FAULTS. ACFT NEEDS RUN TO VERIFY MANIFOLD LIGHT IS NOT ON.

Part: PSEU — MALFUNCTIONED (MLG) · airframe 76,216 hrs · 30,784 cycles

GEAR RETRACTION UNSAFE INDICATION ON RT MAIN GEAR, BOTH PRIMARY AND SECONDARY INDICATIONS SHOWED UNSAFE. COMPLIED WITH QRH -CYCLED GEAR STILL UNSAFE INDICATION ON RETRACTION. RETURNED TO DEPARTURE, DECLARED EMERGENCY, LANDING UNEVENTFUL. NO CURRENT FAULTS. PSEU RTS PASSED AND ALL SENSOR READOUT VALUES WITH IN TOLERANCE. MLG UP & DOOR LATCH SENSOR, BRACKET & WIRING APPEAR NORMAL. R & R SENSOR D1-80 UPLOCK SENSOR AND PSEU IAW AMM. OPS CHECKED NORMAL.

Part: CONNECTOR — FAILED (ANTI ICE SYS) · airframe 76,219 hrs · 30,786 cycles

AIR MANF 3 FAIL WHEN WING ANTI ICE PLACED ON FOR DESCENT. MAX TEMP INDICATE 190 C. BLEED AUTO SHUTDOWN. ONLY MANIFOLD LIGHT ON, NO TEMP HI LIGHT. FOUND RT WING PRESSURE SWITCH TRIPPED. RESET PRESSURE SWITCH. ACCESSED PSC-3 CURRENT FAULT SHOWS PRSOV LOW FAULT, FAULT CODE 361033. NR3 SYS PASSES PRESSURE DECAY CHECK IAW AMM 36-00-01-5. PSC-3 SHOWS NUMEROUS LEGS FAULTED FOR CODE 361033. NR 3 SYSTEM PASSES PRESSURE DECAY CHECK PER AMM 36-00-01-5. PSC-3 SHOWS NUMEROUS LEGS FAULTED FOR CODE 361033. REPLACED CONNECTOR PLUG P1-8096 IAW MM 20-30-02-2-0. PERFORMED R-T-S ON PSC NR 3, NO FAULTS. RAN NR 3 ENG PER JRH CH 5 AND OPERATED WING ANTI ICE WITH BOTH ENG AND APU AIR AND NOT EXCEEDING GND LIMITS FOR OPERATION OF WING ANTI ICE.PER 11-02-2-0.OPS CHECKS GOOD NO MANIFOLD LIGHT. OK FOR SERVICE

Part: VALVE — LEAKING (HYD SYSTEM) · airframe 75,982 hrs · 30,656 cycles

SHORTLY AFTER LEVEL OFF, RECEIVED "HYD 3 ELEV OFF" WARNING, FLUID AT 4.9 CONTINUED TO SLOWLY LEAK, RECEIVED HYD 3 OFF 20 MINUTES LATER. FLUID TRAPPED AT 2.9. AFTER GEAR EXTENSION, RECEIVED "HYD 3 FAIL" FLUID DROPPED TO 1.2. SHUTDOWN 1 & 3 ENG, TOWED TO PARK. (FLUID 0.7) NEEDED ENG 2, NO APU. USED MANUAL GEAR EXTENSION ON SHORT FINAL. FOUND RT BRAKE MANIFOLD VLV LEAKING. REMOVED RT MANIFOLD IAW AMM 32-44-05-2 UP TO ITEM 3A(7).

Part: SLEEVE — CRACKED (HORIZONTAL STAB) · airframe 75,496 hrs · 30,399 cycles

HORIZONTAL STAB CONSTANT SECTION BEARING: SLEEVE UNDER RT PIVOT BEARING SHAFT CRACKED 2 PLACES. NOTE:IPC REF 55-51-01-01 ITEM NR 270, MM REF:55-51-01-02. REMOVED AND REPLACED HORIZONTAL STABLIZER RT AFT PIVOT BEARING SLEEVE IAW AMM 55-51-01-2

Part: DOOR — DAMAGED (REFUEL) · airframe 75,411 hrs · 30,361 cycles

FOUND ON ARRIVAL. RT WING FUELING PANEL DOOR MISSING. FACT: INSTALLED RT WING FUELING PANEL DOOR IAW SMP. OPS AND FIT CHECK GOOD. ACFT OK FOR SERVICE.

Part: FUEL CONTROL — MALFUNCTIONED (NR 3 ENGINE) · airframe 73,227 hrs · 29,319 cycles

NR 3 ENGINE FLAMED OUT ON TAKEOFF ROLL. ENGINE ROLLED BACK TO ABOUT 8% N1; FF INTERMITTENT FROM 0-500. EGT LOWER THAN OTHER 2 AT IDLE. REPLACED THE FUEL CONTROL AND FUEL PUMP.

Part: FUEL CONTROL — FAILED (NR 3 ENGINE) · airframe 73,227 hrs · 29,319 cycles

NR 3 ENGINE FLAMED OUT ON TAKEOFF ROLL. ENGINE ROLLED BACK TO ABOUT 8 PERCENT N1; FF INTERMITTENT FROM 0-500. EGT LOWER THAN OTHER 2 AT IDLE. REPLACED THE FUEL CONTROL AND FUEL PUMP.

Part: CONTROL VALVE — MALFUNCTIONED (NR 2 FLOW) · airframe 72,466 hrs · 28,954 cycles

RECEIVED A LEVEL 1 PACK 2 FLOW DISAGREE ALERT IN FLIGHT 6 TIMES. REMOVED AND REPLACED PACK 2 FLOW CONTROL VALVE, REF MM 21-51-02-4. REMOVED AND REPLACED PACK 2 FLOW TRANSMITTER. REF MM 21-52-01-4. OPS AND LEAK CHECK OK.

Part: FLOW VALVE — FAILED (NR 2 A/C PACK) · airframe 72,466 hrs · 28,954 cycles

RECEIVED A LEVEL 1 PACK 2 FLOW DISAG ALERT IN FLIGHT 6 TIMES. REMOVED AND REPLACED PACK 2 FLOW CONT VALVE, REF MM 21-51-02-4. REMOVED AND REPLACED PACK 2 FLOW TRANSMITTER, REF MM 21-52-01-4. OPS AND LEAK CHECK OK.

Part: TRANSMITTER — FAILED (A/C PACK) · airframe 72,495 hrs · 28,969 cycles

RECEIVED A LEVEL 1 PACK 2 FLOW DISAG ALERT IN FLIGHT 6 TIMES. REMOVED AND REPLACED PACK 2 FLOW CONT VLV, REF MD10 MM 21-51-02-4. REMOVED AND REPLACED PACK 2 FLOW XMITER, REF MM 21-52-01-4. OPS AND LK CK OK.

Part: TRANSMITTER — FAILED (NR 1 PACK) · airframe 72,495 hrs · 28,969 cycles

RECEIVED A LEVEL 1 PACK 2 FLOW DISAG ALERT IN FLIGHT 6 TIMES. REMOVED AND REPLACED PACK 2 FLOW CONTROL VALVE, REF MM 21-51-02-4. REMOVED AND REPLACED PACK 2 FLOW TRANSMITTER, REF MM 21-52-01-4. OPS AND LEAK CHECK OK.

Part: SKIN — BULGED (FUSELAGE) · airframe 72,404 hrs · 28,926 cycles

BULGING ON THE EXTERIOR FUSELAGE SKIN; LEFT AT STA 515 TO 521; LONGERON 27L TO LONGERON 28L. REMOVED RIVETS IAW DC/MD-10 SRM 51-31-01; VOL II. FORMED SKIN IAW DC/MD-10 SRM 53-20-00; VOL II. INSTALLED RIVETS IAW DC/MD-10 SRM 51-31-10; VOL II. REMOVED AND REINSTALLED FLOOR PANELS; SIDEWALLS AND VENT PANELS IAW DC/MD-10-10 AMM 53-21-01- 2. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01; VOL II AND COMPLIED WITH FEDEX EA 8- 5330-118542 "FUSELAGE, FINGER DOUBLER REPAIR STA 517 AND LONGERON 27L.

Part: SKIN — WORN (FUSELAGE) · airframe 72,404 hrs · 28,926 cycles

STABILIZER JACKSCREW COMPARTMENT DOOR CUTOUT FOR PANEL 311 AB BETWEEN STA 2007 AND 2033 INNER SURFACE OF THE SKIN IS WORN FROM FRETTING ON THE DOOR LATCHES (4) PLACES LEFT AND RIGHT SIDES. COMPLIED WITH EA 8-5330-116971.

Part: PANEL — CRACKED (NR 3 NACELLE) · airframe 72,404 hrs · 28,926 cycles

NR 3 ENGINE PYLON PER-COOLER PANEL NR 487 DR HAS 2 CRACKS AT THE LOUVER OPENING. INSTALLED REPAIR DOUBLER IAW SRM 54-00-01 VOL I FIG 2-B SHEET 2. TOPCOATED IAW SRM 51-23-01 VOL II.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 72,404 hrs · 28,926 cycles

GOUGED/DENTED FORWARD LOWER CARGO DOOR SKIN AT THE FORWARD CORNER. COMPLIED WITH CARGO DOOR SKIN/PAN REPAIR IAW DC/MD-10 SRM 52-10-00; VOL I; FIG 17.

Part: HINGE — WORN (CARGO DOOR) · airframe 72,404 hrs · 28,926 cycles

LOWER FWD CARGO DOOR FWD HINGE SEGMENT LOBES ARE WORN BEYOND LIMITS PER FEDEX WORK CARD 52X3502. MACHINED 3 EACH REPAIR BUSHINGS IAW SRM 52-10-00 PG 23 VOL I. INSTALLED BUSHINGS IAW SRM 51-39-01 VOL II PG 3. MINOR REPAIR.

Part: ACCESS PANEL — DENTED (ZONE 400) · airframe 72,404 hrs · 28,926 cycles

EMPENNAGE, LT INLET DUCT ACCESS PANEL 363 GL IS DENTED REPAIRED DENT DAMAGES ON LT LOWER VERT STAB FAIRING PNL 363 GL BY REMOVING DAMAGED AREAS, HOT BONDING SKIN PLUGS, DOUBLERS, AND FILL AND FAIR, AND REFINISHING IAW DC/MD-10 SRMS 55-33-01 VOL III, 51-71- 00 VOL II AND DAC DWG AJC 7074 PANEL REMOVED AND REINSTALLED IAW MD/DC10 SRM 51-31-01 VOL II PAGE 1.

Part: PANEL — CRACKED (NR 1 PYLON) · airframe 72,404 hrs · 28,926 cycles

NR 1 ENGINE PYLON PANEL NR 438CR IS CRACKED. WELD REPAIRED CRACKS IAW DAC DRWG AUB 7120; DPS 4.801 AND DPS 10.225.

Part: SKIN — DENTED (BS 278-323) · airframe 72,404 hrs · 28,926 cycles

EXTERNAL FUSELAGE SKIN JUST BELOW THE WINDSHIELD AND SLIDING WINDOW HAS A DENT BETWEEN STA 278 AND 323; RT SIDE. COMPLIED WITH EA 8-5330-118447.

Part: INTERCOSTAL — CRACKED (BS 806) · airframe 72,404 hrs · 28,926 cycles

FWD LOWER CARGO BILGE INTERCOSTAL STRUCTURE IS CRACKED AT BS 806; RBL 40.0 REMOVED INTERCOSTAL AND PLUGGED HOLES IAW DC/MD-10 SRM 51-31-01; VOL II; PGS 1 - 10 AND EA NR 8-5320-118449 "FUSELAGE MID LAV WASTE LINT SUPPORT BRACKET - REMOVAL".

Part: SUPPORT ANGLE — CORRODED (BS 1019-1039) · corrosion level 2 · airframe 72,404 hrs · 28,926 cycles

FWD CARGO COMPARTMENT BILGE AREA; FOUND CORROSION ON THE FUSELAGE SKIN DOME NUT SUPPORT ANGLE JUST OUTBD OF STR 52 FROM FS 1019 - 1039. REMOVED CORROSION IN REFERENCE WITH SRM 51-21-01; VOL II; PG 28. ORIGINAL THICKNESS IS .063 IAW DWG NDA 6014; REV A B. MATERIAL REMOVED IS .004; MATERIAL REMAINING IS .059. FOUND TO BE WITHIN LIMITS IAW SRM 53-00-01; VOL I; FIG 1B. ALODINED AND PRIMED TN REFERENCE WITH SRM 51-21-01; VOL II; PGS 21 AND 25. REMOVED AND REINSTALLED ANGLE IN REFERENCE WITH SRM 51-35-01; VOL II; PG 1.

Part: FLOORBEAM — CORRODED (BS 879) · airframe 72,404 hrs · 28,926 cycles

FWD CARGO COMPARTMENT BILGE AREA; FLOORBEAM WEB AFT FACE HAS TOOL MARKINGS ABOVE STR 47R; FS 879. BLENDED AREA IAW SRM 53-00-01; VOL I; FIG 8. ORIGINAL THICKNESS .062 IAW SRM 53-13-01; VOL III; FIG 6; PG 24B AND SRM 51-10-01; FIG 32. REMAINING THICKNESS .062; FOUND TO BE WITHIN LIMITS IAW SRM 53-00-01; VOL I; PG 8. ALODINED AND PRIMED IN REF TO SRM 51-21-01; VOL II; PGS 31 AND 24. APPLIED TOP COAT IN REF SRM 51-21-01; VOL II; PGI. REMOVED AND REPLACED FASTENERS IAW 51-31-01; VOL II; PG 1 - 10.

Part: STRINGER — CORRODED (BS 1019-1039) · corrosion level 2 · airframe 72,404 hrs · 28,926 cycles

FWD CARGO COMPARTMENT BILGE AREA; FOUND CORROSION ON STRINGER 52 OUTBD FACE; FROM FS 1019-1039. REMOVED CORROSION IN REFERENCE WITH SRM 51-21-01; VOL II; PG 28. ORIGINAL THICKNESS IS .090 IAW SRM 53-13-01; VOL III; ITEM 39. MATERIAL REMOVED IS .002. MATERIAL REMAINING IS .088. FOUND TO BE WITHIN LIMITS IAW SRM 53-00-01; VOL I; FIG 1B. ALODINED AND PRIMED IN REFERENCE WITH SRM 51-21-01; VOL II; PGS 21 AND 25.

Part: FRAME — CORRODED (BS 899) · corrosion level 2 · airframe 72,404 hrs · 28,926 cycles

FWD CARGO COMPARTMENT BILGE AREA; FS 899 FRAME LOWER FLANGE UPPER SURFACE HAS LIGHT CORROSION; STR 51R - 51L. REMOVED CORROSION IAW SRM 51-21-01; VOL II; PG 28 AT STA 899 STR 51R - 51L FRAME FLANGE. FOUND TO BE WITHIN LIMITS IAW SRM 53-00-01;FIG 1A. ORIGINAL THICKNESS IS .080. MATERIAL LOSS OS .010. REMAINING THICKNESS IS .070. ALODINED, PRIMED, AND TOP COATED IAW SRM 51-21-01; VOL II; PGS 19; 21 AND 24. INSTALLED FASTENERS 6 IAW SRM 51-33-01; VOL II; PG 1. MINOR REPAIR.

Part: STRINGER — CORRODED (BS 809 S52L) · corrosion level 2 · airframe 72,404 hrs · 28,926 cycles

FWD CARGO PIT BILGE; STRINGER 52 IS CORRODED AT BS 809. REMOVED CORROSION IAW SRM 51-21-01; VOL II; PG 26. WITHIN LIMITS IAW SRM 53-00-01; VOL I; FIG 1A. ORIGINAL THICKNESS IS .071. MATERIAL LOSS IS .006. REMAINING THICKNESS IS .065. ALODINED; PRIMED AND TOP COATED IAW SRM 51-21-01; VOL II; PGS 19; 21 AND 24. MINOR REPAIR

Part: SHEAR TIE — CORRODED (BS 824) · corrosion level 2 · airframe 72,404 hrs · 28,926 cycles

FWD LOWER CARGO PIT BILGE SHEAR TIE IS CORRODED AT BS 824 BETWEEN STR 51L AND STR 52L. REMOVED CORROSION IAW SRM 51-21-01; VOL II; PG 28. ORIGINAL THICKNESS .071 IAW SRM 53-13-01; VOL III; FIG 8A AND SRM 51-10-02; VOL II. REMAINING THICKNESS .068; FOUND TO BE WITHIN LIMITS IAW SRM 53-00-01; FIG 1; PG 4B. UT GAUGE NR 78224Q. ALODINED AND PRIMED IAW SRM 51-21-01; VOL II; PGS 21 AND 24. APPLIED TOP COAT IAW SRM 51-21-02; VOL II; PG 1. MINOR REPAIR.

Part: WEDGE — CRACKED (NR 2 FAIRING) · airframe 72,404 hrs · 28,926 cycles

NR 2 ENGINE AFT FAIRING T/E WEDGE IS CRACKED AT LOWER END IN WORK.

Part: SUPPORT — CORRODED (BS 959) · corrosion level 2 · airframe 72,404 hrs · 28,926 cycles

FWD CARGO PIT BILGE AREA; DRAIN PAN SUPPORT ANGLE LOWER SURFACE AND NUT PLATES HAVE CORROSION ABOVE FRAME AT FS 959, S49-51L. REMOVED CORROSION IAW SRM 51-21-01; VOL II; PG 28. THE ORIGINAL THICKNESS IS .040 IAW DWG ADA0145 REV J; THE MATERIAL REMOVED IS .002; MATERIAL REMAINING IS .038. FOUND TO BE WITHIN LIMITS IAW SRM 53-00-01; VOL II; FIG 1B. TREAT AND PRIMED IAW SRM 53-21-01; VOL II; PGS 21 AND 24; THEN INSTALLED NUT PLATES IAW SRM 51-33-01; VOL II; PG 2.

Part: FAIRING — BROKEN (NR 2 ENGINE) · airframe 72,404 hrs · 28,926 cycles

NR 2 ENGINE AFT FAIRING (BEAVER TAIL), LOWER AFT CORNER, (INNER PAN) IS BROKEN OUT.

Part: SILL — GOUGED (BS 715) · airframe 72,404 hrs · 28,926 cycles

CARGO DOOR CUT-OUT LOWER JAMB INBOARD ANGLE AT NR 5 LATCH SPOOL AREA HAS 2 GOUGES; .065 AND .085. CLEANED UP GOUGES AREA IN REF TO SRM 53-00-01; VOL I; FIG 1A WITHIN LIMITS; MAINTAINED 2D EDGE DISTANCE IN REF TO SRM 53-00-01;VOL I; FIG 1A. ALODINED AND PRIMED AREA IN REF TO SRM 51-21-01; VOL II; PGS 21 AND 25.

Part: SHEAR TIE — CORRODED (FUELAGE) · corrosion level 2 · airframe 72,404 hrs · 28,926 cycles

FWD LOWER CARGO PIT BILGE SHEAR TIE IS CORRODED AT BS 824 BETWEEN STR 51R AND STR 52R. REMOVED CORROSION IAW SRM 51-21-01; VOL II; PG 28. ORIGINAL THICKNESS .071 IAW SRM 53-13-01; VOL III; FIG 8A AND SRM 51-10-02; VOL II. REMAINING THICKNESS .068; FOUND TO BE WITHIN LIMITS IAW SRM 53-00-01; FIG 1A; PG 4B. UT GAUGE NR T8224Q. ALODINED AND PRIMED IN REF TO SRM 51-21-01; VOL II; PG'S 21 AND 24. APPLIED TOPCOAT IAW SRM 51-21-02; VOL II; PG 1. MINOR REPAIR.

Part: SUPPORT — CORRODED (BS 939) · corrosion level 2 · airframe 72,404 hrs · 28,926 cycles

FWD CARGO PIT BILGE AREA FOUND CORROSION ON THE DRAIN PAN SUPPORT ANGLE AROUND THE NUT PLATES ABOVE THE FRAME AT FS 939; STR 49L/R. REMOVED CORROSION IAW SRM 51 21-01; VOL II; PG 28. THE ORIGINAL THICKNESS IS .040 IAW DWG ADA 0145 REV J. THE MATERIAL REMOVED IS .003. THE MATERIAL REMAINING IS .037. FOUND TO BE WITHIN LIMITS IAW SRM 53-00-01; VOL II; FIG 1B. TREAT AND PRIMED IAW SRM 53-21-01; VOL II; PGS 21 AND 24; THEN INSTALLED THE NUT PLATES IAW SRM 51-35-01; VOL II; PG 2.

Part: SUPPORT — CORRODED (BS 959) · corrosion level 2 · airframe 72,404 hrs · 28,926 cycles

FWD CARGO PIT BILGE AREA; DRAIN PAN SUPPORT LOWER SURFACE AND NUT PLATES HAVE CORROSION ABOVE FRAME FS 959 FROM S49-51R. REMOVED CORROSION IAW SRM 51-21-01; VOL II; PG 28. THE ORIGINAL THICKNESS IS .040 IAW DWG ADA0145 REV J. THE MATERIAL REMOVED IS .002; MATERIAL REMAINING IS .038. FOUND TO BE IN LIMITS IAW SRM 53-00-01; VOL II; FIG 1B. TREAT AND PRIMED IAW SRM 51-21-01; VOL II; PGS 21 AND 24; THEN INSTALLED NUT PLATES IAW SRM 51-35-01; VOL II PG 2. MINOR REPAIR.

Part: CHANNEL — CORRODED (BS 824) · corrosion level 2 · airframe 72,404 hrs · 28,926 cycles

FWD LOWER CARGO PIT BILGE FRAME J-CHANNEL IS CORRODED AT BS 824 S51R. REMOVED CORROSION IAW SRM 51-21-01; VOL II; PG 28. ORIGINAL THICKNESS .071 IAW SRM 53-13-01; VOL III; FIG 8A AND SRM 51-10-02; VOL II. REMAINING THICKNESS .069; FOUND TO BE WITHIN LIMITS IAW SRM 53-00-01; VOL II; FIG 1A; PG 4B. UT GAUGE NR T8224Q. ALODINED AND PRIMED IN REF TO SRM 51-21-01; VOL II; PGS 21 AND 24. APPLIED TOP COAT IN REF TO SRM 51-21-02; VOL II; PG 1. MINOR REPAIR.

Part: DOOR FRAME — CRACKED (CARGO DOORWAY) · airframe 72,404 hrs · 28,926 cycles

MCD LOWER JAMB AT SPOOL LOCATION NUMBER 5 SHOWED EVIDENCE OF CRACK IN HOLES A,B,C,D IN WORK

Part: SKIN — BULGED (BS 1909) · airframe 72,404 hrs · 28,926 cycles

BULGING AT EXTERNAL FUSELAGE SKIN; RT STA 1909; LONGERON 41R TO 42 R. FOUND TO BE OUT OF LIMITS IAW SRM 53-20-00; VOL I; PG 116. DRILLED OUT BULGED AREA AT .250 & REPAIRED IAW SRM 53-20-00; FIG 13; SHEET 1; VOL I.

Part: SUPPORT FITTING — CORRODED (CARGO DOORWAY) · airframe 72,404 hrs · 28,926 cycles

MAIN CARGO DOOR LOWER JAMB AND SUPPORT FITTING HAD CORROSION IN HOLES B, C, D AT FITTING LOCATION NR 6.

Part: FITTING — CRACKED (CARGO DOORWAY) · airframe 72,404 hrs · 28,926 cycles

MCD LOWER JAMB AT SPOOL FITTING LOCATION NUMBER 7 SHOWED EVIDENCE OF CRACKS IN HOLES A, B, C, D.

Part: SKIN — DENTED (BS 1789-1796) · airframe 72,404 hrs · 28,926 cycles

DENTED EXTERNAL FUSELAGE SKIN FROM STA 1789 TO 1796.5; BETWEEN LONGERON 29R AND 30R. BLENDED GOUGED AREA. FOUND TO BE OUT OF LIMITS IAW SRM 53-20-00 VOL I PG 116 FIG 6. GENERATED RFTS N384FE-7-23178. REMOVED DAMAGED AREA IAW SRM 53-20-00 VOL I PG 73 FIG 6. LOCATED, DRILLED & TRIMED IAW SRM 53-20-00 VOL I FIG 6. ALODINED & PRIMED IAW SRM 51-21-01 VOL II. INSTALLED REPAIR IAW SRM 51- 33-01 VOL II. HFEC OF DENT IAW NDT 60-10-001.

Part: PANEL — CRACKED (ZONE 400) · airframe 72,404 hrs · 28,926 cycles

NR 3 PYLON PANEL 488CL IS CRACKED AT THE CUTOUT. WELD REPAIRED CRACKS IAW DWG AUB 7120 & DPS 4.801 & DPS 10.225.

Part: FITTING — CRACKED (CARGO DOORWAY) · airframe 72,404 hrs · 28,926 cycles

MCD LOWER JAMB AT SPOOL FITTING LOCATION NUMBER 4 SHOWED EVIDENCE OF CRACKS IN HOLES A, B, C, D.

Part: SKIN — DENTED (BS 1801-1802) · airframe 72,404 hrs · 28,926 cycles

DENTED EXTERNAL FUSELAGE SKIN FROM STA 1801 TO STA 1802.5; BETWEEN LONGERON 29R TO 30R. BLENDED GOUGED AREA. FOUND TO BE OUT OF LIMITS IAW SRM 53-20-11 VOL I PG 116. REMOVED DAMAGE IAW SRM 53-20-00 VOL I. GENERATED RFTS N384FE-6-23179. FABRICATED REPAIR IAW SRM 53-20-00 VOL I FIG 6. ALODINED & PRIMED IAW SRM 51-21-01 VOL II. INSTALLED REPAIR IAW SRM 51-33-01 VOL II. HFEC IAW NDT 06-10-001.

Part: TEE FITTING — CRACKED (HORIZONTAL STAB) · airframe 72,404 hrs · 28,926 cycles

2ND FROM INBD LEADING EDGE SECTION AT THE RT HORIZONTAL STABILIZER; "UPPER OUTBD ATTACH ANGLE" IS CRACKED. REMOVED RACKED TEE ANGLE IAW SRM 51-31-01 VOL II PG 1. FORMED NEW TEE CAP IAW DWG ALC 07052 REV G. LOCATED, DRILLED & DEBURRED NEW TEE CAP IAW SRM 51-31-01 VOL II PG 1. ALODINED & PRIMED NEW TEE CAP IAW SRM 51-21-01 VOL II PG 18. PART MARKED TEE CAP IAW GMM 7-0-100 PGS 1-2. INSTALLED TEE CAP IAW SRM 51-33-01 PG 1 & 51-35-01 VOL II PG 1.

Part: FITTING — CRACKED (CARGO DOORWAY) · airframe 72,404 hrs · 28,926 cycles

MCD LOWER JAMB AT SPOOL FITTING LOCATION NUMBER 2 SHOWED EVIDENCE OF CRACK IN HOLES A, B, C, D.

Part: SUPPORT FITTING — CRACKED (CARGO DOORWAY) · airframe 72,404 hrs · 28,926 cycles

MCD LWR JAMB, NR 1 LATCH SPOOL LWR JAMB SUPPORT FITTING (THRU LIGHTENING HOLE) FWD I/B LEG, CRACKED AND MK'D.

Part: FAIRING — CRACKED (NR 1 PYLON) · airframe 72,404 hrs · 28,926 cycles

NR 1 PYLON PANEL 438CL IS CRACKED. REPAIRED CRACKS IAW DRAWING AIB7120-501.

Part: FITTING — CRACKED (CARGO DOORWAY) · airframe 72,404 hrs · 28,926 cycles

MCD LOWER JAMB AT SPOOL FITTING LOCATION NUMBER 3 SHOWED EVIDENCE OF CRACKS IN HOLES A, B, C, D.

Part: PANEL — CRACKED (NR 3 NACELLE) · airframe 72,404 hrs · 28,926 cycles

NR 3 PYLON PANEL 488CL IS CRACKED AT THE CUTOUT. WELD REPAIRED CRACKS IAW DWG AUB 7120 AND DPS 4.801 AND DPS 10.225.

Part: DRAIN — CHAFED (NR 1 NACELLE) · airframe 72,404 hrs · 28,926 cycles

NR 1 ENGINE PYLON AFT FAIRING LOWER PANEL 438EL HAS A CHAFED DRAIN TUBE. WELDED CHAFED AREA IAW DPS 10.225. MINOR REPAIR.

Part: PANEL — DENTED (RT WING) · airframe 72,404 hrs · 28,926 cycles

RT MLG AREA PANEL ABOVE THE MLG ACTUATOR IS DENTED. REMOVED DAMAGED AREA, PREPPED AREA FOR BONDING, FABRICARED REPAIR CORE PLUG & DOUBLERS. LAYED UP & BONDED IAW SRM 51-31-01 VOL III FIG 1 & 51-71-00 VOL II PG 1. SEALED, PRIMED & PAINTED IAW SRM 51-31-01 VOL II. PANEL 152 ET INSTALLED ON W/C 53P10.048B.

Part: PANEL — PUNCTURED (RT WING) · airframe 72,404 hrs · 28,926 cycles

RT WING, INBD UPPER T/E FIXED PANEL P/N ARC0269-502 HAS A PUNCTURE ON THE LOWER SIDE. REMOVED DAMAGE FROM THE AREA; PREPPED AREA FOR BONDING; FABRICATED REPAIR CORE PLUG & DOUBLERS; LAYED UP AND BONDED IAW SRM 51-31-01 VOL III FIG 4 & SRM 51-71-00 VOL II PG 1. SEALED, PRIMED & PAINTED IAW SRM 51-70-00; VOL II CH 17C. MINOR REPAIR.

Part: SEAT TRACK — WORN (BS 685-768) · airframe 72,404 hrs · 28,926 cycles

FOUND CABIN FLOOR DECK SEAT TRACK HAS SEVERAL WEAR MARKS FROM STA 685 - STA 768 RBL 9 IN WORK.

Part: SKIN — CHAFED (HORIZONTAL STAB) · airframe 72,404 hrs · 28,926 cycles

LEFT HORIZONTAL SATBILIZER REAR SPAR PANEL 334 SB IS CHAFED ON THE INTERIOR SKIN FAYING SURFACE XE 306. REMOVED FINISH AT INTERIOR OF PANEL IAW SRM 51-21-01, VOL I. CHAFED AREA FOUND TO BE WITHIN LIMITS OF FIGURE 1-A. SRM 55-00-01 VOL I. APPLIED SURFACE PROTECTOR IAW SRM 51-21-01 VOL II. APPLIED SURFACE FINISH IAW SRM 51-21-01 VOL II. MINOR REPAIR.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 72,404 hrs · 28,926 cycles

RT HORIZONTAL STABILIZER; UPPER INBOARD SKIN PLANK SHOWS EVIDENCE OF A CRACK FROM INBOARD TO FORWARD, APPROXIMATELY 1 INCH, AFT PLANK. COMPLIED WITH EA 8-5510-116961.

Part: PANEL — CHAFED (HORIZONTAL STAB) · airframe 72,404 hrs · 28,926 cycles

RT HORIZONTAL STABILIZER REAR SPAR HINGE PANEL BELOW THE INBD DAMPER IS CHAFED ON THE INTERIOR SKIN, OUTBD ELEVATOR. REMOVED PANEL TO FOM. IAW SRM 51-31-01 VOL II. REMOVED DAMAGE AND PREPARED SURFACES FOR BONDNG IAW SRM 51-71-00 VOL II. FABRICATED REPAIR FILLER, DOUBLER, BONDED & CURED IAW SRM 51-71-00 VOL II. APPLIED SEALANT IAW SRM 51-71-00 VOL II. PAINTED AREA IAW SRM 51-21-01 VOL II. RE-INSTALLED PANEL IAW SRM 51-31-01 VOL II PG 1.

Part: ACCESS PANEL — DENTED (NR 2 NACELLE) · airframe 72,404 hrs · 28,926 cycles

NR 2 ENGINE PYLON ACCESS PANEL NR 362 DR HAS A DENT. REPAIRED PANEL BY FABRICATING SKINS, CORE, LAYED UP & BONDED IAW TPS 1001 REV E & EA 8-5530-116967 "RT VERTICAL STABILIZER PICKLE BARREL PANEL". PANEL REMOVED & REINSTALLED TO FACILITATE MAINTENANCE IAW SRM 51-31-01 VOL II PG 1.

Part: LINER — CRACKED (CARGO DOOR) · airframe 72,404 hrs · 28,926 cycles

LOWER FWD CARGO DOOR LINER IS CRACKED IN THE AFT UPPER AREA.

Part: SKIN — DELAMINATED (NR 5 SPOILER) · airframe 72,404 hrs · 28,926 cycles

LT WING SPOILER NR 5 UPPER EXTERIOR INBD SIDE IS DELAMINATED (2 PLACES). TAP TESTED MARKED AREAS IAW DC/MD-10 SRM 51-61-01; VOL II. NO DELAMINATION NOTED AT THIS TIME. REINSTALLED LT NR 5 SPOILER IAW MD-10-10 AMM 27-60-01-4. CLEARANCE AND OPS CHECKS GOOD IAW MD-10-10 AMM 27-60-01-4 AND MD-10-10 AMM 27-60-01-4.

Part: PANEL — DAMAGED (LT WING) · airframe 72,404 hrs · 28,926 cycles

LT WING MOST INBD LOWER T/E PANEL AT THE FUEL TANK SUMP PANEL HAS DENTS AND THE REPAIR DOUBLER IS MISSING. REPLACED MISSING DOUBLER IAW SRM 51-71-11 VOL II. REFINISHED REPAIR IAW SRM 51-71-00 VOL II & SRM 51-21-01 VOL II.

Part: SKIN — DELAMINATED (NR 4 SPOILER) · airframe 72,404 hrs · 28,926 cycles

LT WING SPOILER NR 4 UPPER EXTERIOR IS DELAMINATED (3 PLACES). TAP TESTED MARKED AREAS IAW DC/MD-10 SRM 51-61-01; VOL II. NO DELAMINATION NOTED AT THIS TIME. REINSTALLED LT NR 4 SPOILER IAW MD-10-10 AMM 27-60-01-4. CLEARANCE AND OPS CHECKS GOOD IAW MD-10-10 AMM 27-60-01-6 AND MD-10-10 AMM 27-60-01-4.

Part: LINER — CRACKED (CARGO DOOR) · airframe 72,404 hrs · 28,926 cycles

CENTER CARGO DOOR LINER IS CRACKED AND DISBONDED AT THE AFT END. REPAIRED THE CENTER CARGO DOOR LINER BY REMOVING THE DAMAGE, CLEANED, & PREPARED FOR A WET LAY-UP TO THE INTERIOR & EXTERIOR SURFACES. APPLIED, CURED, & SANDED THE WET LAY-UP ON THE INTERIOR & EXTERIOR SURFACES IAW SRM 51-43-01. MINOR REPAIR.

Part: LINER — DEBONDED (CARGO DOOR) · airframe 72,404 hrs · 28,926 cycles

THE AFT CARGO DOOR LINER REPAIR PATCH IS DISBONDED. REPAIRED THE AFT CARGO DOOR LINER BY REMOVING THE DAMAGE; CLEANED & PREPARED FOR WET LAY-UP TO THE INTERIOR AND EXTERIOR SURFACES. APPLIED, CURED, AND SANDED WET LAY-UP ON THE INTERIOR AND EXTERIOR SURFACES IAW SRM 51-43-01. MINOR REPAIR.

Part: PANEL — DELAMINATED (LT WING) · airframe 72,404 hrs · 28,926 cycles

LT WING PANEL 541GB IS DELAMINATED ON THE BACK SIDE. REPAIRED PANEL 541GB LT WING PANEL BY FABRICATING AND BONDING A SKIN DOUBLER & REPAIR PARTS IAW SRM 51-71-00; VOL II CH 17 & ARC0264 DWG. MINOR REPAIR

Part: SEALANT — DETERIORATED (ELEVATOR) · airframe 72,404 hrs · 28,926 cycles

LT HORIZONTAL STAB, OUTBD ELEVATOR T/E WEDGE IS DELAMINATED IN 2 PLACES AT BEAMS. AFTER FURTHER INVESTIGATION FOUND SEALANT DETERIORATED AT THE SEAMS WITH NO DELAMINATION NOTED. RESEALED SEAMS IAW SRM 51-41-01; VOL II; PAGE 1. MINOR REPAIR

Part: SKIN — DELAMINATED (WING) · airframe 72,404 hrs · 28,926 cycles

FOUND DELAMINATION ON PANEL NR 535HL EXTERIOR SKIN. REMOVED DAMAGE & REPAIRED PANEL IAW SRM 51-21-01; VOL II. ALODINED & PRIMED REPAIR AREA IAW SRM 51-21-01 VOL II. PAINTED PANEL IAW SRM 51-21-01; VOL II. MINOR REPAIR

Part: SEAT TRACK — GOUGED (BS 1145) · airframe 72,404 hrs · 28,926 cycles

FOUND SEAT TRACK IS GOUGED AT BS 1145, RBL 75. BLENDED DAMAGED AREA. MATERIAL REMAINING .085. FOUND OUT OF LIMITS IAW SRM 53-70-00 VOL I. REMOVED AND REINSTALLED 4 FLOOR PANELS IAW AMM 53-21-08-2 . REMOVED DAMAGED TRACK AND INSTALLED NEW SECTION OF TRACK IAW SRM 51-31-01; VOL II; PG 1. FABBED NEW SECTION AND SPLICE HAT & PLATE IAW SRM 53-70-00; VOL I; PGS 3 & 4. ALODINED & PRIMED NEW SECTION IAW SRM 51-21-01; VOL II; PGS 21 & 24. MAJOR REPAIR.

Part: SKIN — GOUGED (RT WING) · airframe 72,404 hrs · 28,926 cycles

RT WING PANEL 641LB INTERIOR SKIN IS GOUGED (2 PLACES). REPAIRED THE TWO GOUGED AREAS BY REMOVING THE DAMAGE. FABRICATING A NEW CORE PLUG, FILLER & DOUBLERS USING BONDING REPAIRS IAW SRM 51-71-00; VOL II. ALODINED, PRIMED, SEALED AND PAINTED IAW SRM 51-21-02; VOL II. MINOR REPAIR

Part: ACCESS PANEL — DELAMINATED (LT WING) · airframe 72,404 hrs · 28,926 cycles

LT WING PANEL 541BB IS DELAMINATED ON THE BACK SIDE. REPAIRED LT WING CONTROL ACCESS PANEL 541 BB BY FABRICATING & BONDING NEW INNER & OUTER SKINS, DOUBLERS & CORE IAW EA 8-5710-116968;

Part: LINER — CRACKED (CARGO DOOR) · airframe 72,404 hrs · 28,926 cycles

LOWER FWD CARGO DOOR LINER IS CRACKED IN THE AFT UPPER AREA. REPAIRED FWD CARGO DOOR LINER CRACK WITH A WET LAY-UP IAW DC/MD-10 SRM 51-43-01. VOL II. MINOR REPAIR.

Part: PANEL — DELAMINATED (LT WING) · airframe 72,404 hrs · 28,926 cycles

FOUND DELAMINATION ON PANEL NR 535BR AT EXTERNAL SKIN. REPAIRED THE DELAMINATED AREA BY REMOVING DAMAGED AREA, & BY FABRICATING & BONDING A FILLER & DOUBLER IAW SRM 51-71-00 VOL II. RESTORED FINISH IAW SRM 51-71-00; VOL II.

Part: PANEL — DAMAGED (WING TO FUSELAGE) · airframe 72,404 hrs · 28,926 cycles

RT FUSELAGE, TO WING FILLET PANEL 152GT HAS A CHUNK OUT OF THE LOWER EDGE. REMOVED DAMAGED, CLEANED & PREPPED REPAIR. APPLIED REPAIR PLYS & VAC BAGGED. CURED & SANDED. APPLIED FIBERGLASS SEALER, CURED & SANDED SMOOTH IAW SRM 51-43-01 VOL II PARA 16-A (4) & 16-A (10). APPLIED REFINISH IAW SRM 51-21-02; VOL II. MINOR REPAIR

Part: PANEL — PUNCTURED (LT WING) · airframe 72,404 hrs · 28,926 cycles

LT WING PANEL 541CR IS PUNCTURED AND DELAMINATED ON THE LOWER SIDE. REMOVED THE DAMAGE AND REPAIRED PANEL IAW SRM 51-71-00; VOL II. ALODINED AND PRIMED THE REPAIR AREA IAW SRM 51-21-01; VOL II. MINOR REPAIR.

Part: VANE — DELAMINATED (RT WING TE FLAP) · airframe 72,404 hrs · 28,926 cycles

RT WING INBD FLAP VANE INBD SIDE LOWER EXTERNAL SURFACE IS DELAMINATED AND DENTED AT THE L/E AREA. REMOVED & REPLACED RT I/B FLAP VANE IAW MM 27-50-03-2.

Part: SKIN — GOUGED (WING) · airframe 72,404 hrs · 28,926 cycles

GOUGED INTERNAL SKIN ON PANEL 535GL, ON THE PARTS RACK. REPAIRED INTERNAL SKIN PANEL 535 GL BY REMOVING THE DAMAGE & BLENDING & REMOVING BURRS. FABRICATED REPAIR DOUBLER & BONDED DOUBLER TO THE PANEL. VACUUMED COMPLETING CURE OF BOND & REMOVING EXCESS ADHESIVE FLASH. APPLYING SEALANT TO THE DOUBLER EDGES AND CURING. REAPPLIED FR PRIMER FINISH TO REPAIR AREA AND CURING IAW SRM 51-21-01. MINOR REPAIR.

Part: HINGE — CORRODED (CARGO DOOR) · airframe 72,404 hrs · 28,926 cycles

AFT CARGO DOOR, INTERIOR SIDE OF THE HINGE IS RUSTED. AFTER REMOVING THE CORROSION FOUND HINGE P/N AFA3953-525 OUT OF LIMITS IAW SRM 52-10-00 FIG 8 VOL I. REMOVED (TO GAIN ACCESS TO REMOVE THE HINGE) AND REINSTALLED FASTENERS ON PARTIAL INTERNAL SKIN, GUARD ASSEMBLY AFA 7384-39. GUARD SUPPORTS (2 EA) AFA7384-9 & -15 AND HANDLE VENT DOOR SPRING BRACKET IAW SRM 51-31-01 VOL II. REMOVED AND INSTALLED NEW HINGE P/N AFA3953-525 IAW SRM 51-31-01; VOL II; 51-38-01; VOL II; PG 12 & DWG AFA3953.

Part: SUPPORT BEAM — CORRODED (LT WING ROOT) · airframe 70,536 hrs · 28,116 cycles

LT WING ROOT UPPER TE MLG SUPPORT BEAM UPPER SURFACE IS FRETTED AT WING PNL INTERFACE BS 938-944, SEE SNRM N00178. BLENDED AREA REF SRM 51-10-03 FIG ITEM 7. TREATED AND PRIMED, AND TEFLON PAINTED AREA REF WRI 32108492 AND EA NR 7-32-7-107630.

Part: WIRE HARNESS — LOOSE (FUSELAGE)

WIRE BUNDLE 9102/AFT RIDING ON FWD RELAY PANEL OUTBOURD FRAME TOP RIGHT CORNER ,REF DWG SP10240263 FRAME 4 OF 4,G-G (31) REPOSITIONED AND SECURED WIRE BUNDLE AS PER EA.8-2400-84061 ON FWD RELAY PANEL. (WIRE INSTALATION FWD&AFT RELAY PANEL HARNESS ADJUST.

Part: SKIN — WARPED (NR 5 SLAT) · airframe 66,821 hrs · 26,451 cycles

LEFT WING, NR 5 SLAT LEADING EDGE SURFACE IS EXCESSIVELY WARPED THE ENTIRE WIDTH DUE TO TOO MUCH HEAT. LT WING NR 5 SLAT REMOVED AND REPLACED.

Part: BLOCK — WORN (TE FLAP TRACK) · airframe 66,262 hrs · 26,207 cycles

ON TAKEOFF AT 200 FT GOT STALL WARNING AND SLAT DISAGREE. CLEANED UP PER CHECK LIST. KEPT GETTING PSEU FAIL LEVEL 1 AND SLAT DISAGREE LEVEL 2. ALERT IN CLEAN CONFIG. DIVERT TO MEM. DUMPED 19K LBS OF FUEL NORTH MEM. FOUND NR 4 SLAT, NR 10 TRACK WITH EXCESSIVE PLAY SIDE TO SIDE. FOUND RUB BLOCKS ON NR 10 TRACK WORN ALLOWING DIFFERENT READINGS ON PROX SENSORS. REMOVED AND REPLACED 6 (SIX) BLOCKS FOR NR 10 TRACK. ALSO ADJUSTED NR 2 SENSOR L2A REF MD10-10 MM 27-84-02-4. ALL CHECKS GOOD. PERFORMED SLAT POSITION SENSORS ADJUSTMENT/TEST PER MD10-10 27-84-0 2-5. ALL READINGS CHECK GOOD. PERFORMED RETURN TO SERVICE CHECK ON AOA IN FCC1 AND FCC2. ALL CHECKS GOOD.

Part: HINGE BRACKET — GOUGED (ZONE 500) · airframe 65,827 hrs · 25,994 cycles

LEFT INBOARD FLAP OUTBOARD HINGE BRACKET P/N ARC0157-501 GOUGED UPPER HOLE. BUSHING REPAIRED IAW FEDEX EA 8-5710-70157.

Part: ENGINE — FAILED (NR 1) · airframe 63,988 hrs · 25,093 cycles

SETTING STANDARD POWER ON EWR 4L, WIND 3309, AIRCRAFT BEGAN TO ROLL, AND IMMEDIATELY AND EXPLOSION OCCURRED, PULLING THE AIRCRAFT HARD LEFT. AIRCRAFT EXITED THE RUNWAY WITH TORCHING FROM LEFT ENGINE REPORTED BY TRAILING AIRCRAFT. NR 1 ENGINE SHUTDOWN ACCOMPLISHED AFTER FIRE REPORTED. TOWER ASKED IF EMERGENCY TRUCKS REQUIRED. WE ACCEPTED BECAUSE THERE WAS NO FIRE INDICATION IN COCKPIT. IDLE POWER ON NR 1 NORMAL DURING ABORT. INSPECTED ENGINE, FOUND DAMAGE TO NR 7 COMPONENT TRAILING EDGE NR 8 AND NR 9 COMPONENT SECTION BLADES WERE MISSING. S/D COMING.

Part: SUPPORT — CRACKED (RT WING) · airframe 63,676 hrs · 24,920 cycles

FOUND HFEC DISCONTINUITY IND ON MLG RETRACT CYLINDER SUPPORT FRAME. R/R FRAME PER E.O. 8-5740-7-4312C PART 4 (REF N 6 SEQ 0009).

Part: INDICATOR — INOPERATIVE (HYD SYSTEM)

00-342 NR 1 HYD SYSTEM QTY WENT TO ZERO ON SHORT FINAL AT DTW. ** S/D ** COMING

Part: DOWNLOCK TARGET — INOPERATIVE (MLG DOOR)

AFT DEPARTURE LEFT GEAR UNSAFE RED LIGHT REMAIN ILLUM. RED TABS DIRECTED RECYCLING OF GEAR. REMOVED AND REPLACED RT MLG DOOR TARGET COMPLIED WITH EO 8-3260-7-3304 REV A PART 4. OPS CHECK GOOD.