N360FE

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 87,191 hrs · 31,721 cycles

MAIN DECK STA 1900 RBL52 FLOOR SUPPORT WSP0711-552 UNDER NUTPLATE IS CORRODED REF PREVIOUS SDR #: 18-3003 REPAIRED FLOOR SUPPORT WSP0711-552 PER EA 8-5310-T0343200 P1 "FLOOR SUPPORT DOUBLER REPAIR AT STA 1895-1900" MAJOR REPAIR

Part: ENGINE — OVERTEMP (NR 1) · airframe 86,995 hrs · 31,585 cycles

PDIS 360 77-20 6391 09AUG19 MEM OPEN U LOGPAGES:2977480 APPROXIMATELY 500 FEET AFTER TAKEOFF. WE RECEIVED A LEVEL 1 ENG 1 EXEEDANCE. TEMP SHOWED 1010?, THROTTLE 1 WAS PULLED BACK AND TEMP DECREASED INTO A NORMAL RANGE. WAS OVERTEMP FOR APPROXIMATELY 2 SEC. ENGINE OPERATED NORMAL FOR THE REMAINDER OF FLIGHT WHILE WE RETURNED TO MEM REMOVED AND REPLACED THE EGT THERMOCOUPLE HARNESSES TO INCLUDE THE AFT, TOP RIGHT,FWD,TOP LEFT,BOTTOM RIGHT,BOTTOM LEFT THERMOCOUPLE HARNESS SECTIONS. AMM 77-21-01-2.ENGINES WERE RAN PER JRH, ALL ENGINES RAN WITH SIMILAR EGT TEMPS AND #1 ENGINE EGT WAS NORMAL

Part: ENGINE — FAILED (NR 1) · airframe 86,995 hrs · 31,585 cycles

APPROXIMATELY 500 FEET AFTER TAKEOFF. WE RECEIVED A LEVEL 1 ENG 1 EXEEDANCE. TEMP SHOWED 1010, THROTTLE 1 WAS PULLED BACK AND TEMP DECREASED INTO A NORMAL RANGE. WAS OVERTEMP FOR APPROXIMATELY 2 SEC. ENGINE OPERATED NORMAL FOR THE REMAINDER OF FLIGHT RETURNING TO DEPARTURE.

Part: SLAT SYSTEM — MALFUNCTIONED · airframe 86,283 hrs · 31,116 cycles

PDIS 360 27-80 5760 21DEC18 SAN FACT U LOGPAGES:3057986 ON APPROACH WITH FLAPS 50, FULLY COFIGURED AT 2000' A/C SLOWING ON SPEED TO 148KNTS, GOT STICK SHACKER WITH SUBSEQUENT SLAT DISSAGREE WARNING LIGHT. WENT AROUND AND AFTER TROUBLESHOOTING SYST. DID A NO SLAT / 22 DEGREES OF FLAPS LANDING AS PER QRH. WITH 190 KTS APPROACH SPEED. FACT 21DEC18 05:06 SAN U COMPLIED WITH FIM. 27-80-00 SLAT SYSTEM RTS. TEST IAW-MM22-00-00 ALL TEST PASSED. ALSO, PERFORMED FCC 1 & 2 RTS. ALL TEST PASSED IN ADDITION TO ANGLE OF ATTACK VANE, FLAP HANDLE TEST DURING THE FCC TEST. NO FAULTS FOUND. RTS. TESTS PASSED. ALSO, PERFORMED GVI, OF SLAT/FLAP SYSTEM, NO FAULTS FOUND.

Part: DOUBLER — CRACKED (LT WING) · airframe 86,089 hrs · 31,014 cycles

LT WING AT APPROX XORS 568, INTERNAL. WING BEADED DOUBLER HAS A 1" CRACK. REPAIRED REF SRM 57-10-00 VOL 1 FIG 71 PG 222. MAJOR REPAIR.

Part: ROLLER TRAY — CRACKED (BS 886-959) · airframe 86,089 hrs · 31,014 cycles

FWD CARGO BS 919, RT OTBD OMNI ROLLER TRAY HAD A 5 INCH CRACK. FABRICATED AND INSTALLED A NEW ROLLER TRAY IAW DWG ADJ7005, AND SRM 51-31-01, VOL 2.

Part: SKIN — DELAMINATED (LT SPOILER) · airframe 86,089 hrs · 31,014 cycles

LT WING NR 5 SPOILER, UPPER SKIN, PREVIOUS I/B REPAIR, HAS SMALL AREA DELAMINATION. REPAIRED NR 5 SPOILER PER SRM 57-10-00 VOL I AND SRM 51-71-00 VOL II.

Part: BRACKET — CRACKED (APU INLET) · airframe 86,089 hrs · 31,014 cycles

APU INLET DOOR, LT BRACKET AT SHAFT CRACKED. WELDED DAMAGED AREA AS PER AMM 20-90-00-8 AND DPS 10.225 SECTIONS 4.5 TO 4.5.6 AND GENERAL WELD PROCEDURES 5.3 TO 5.3.5.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

CENTER CARGO STA 1841 FLOOR BOARD SUPPORT HAS CORROSION. INSTALLED NEW SUPPORT AGA7170-5 PER SRM 51-31-01 VOL. 2 AND DAC DWG AGA7170.

Part: SKIN — DELAMINATED (RT SPOILER) · airframe 86,089 hrs · 31,014 cycles

RT WING NR 3 SPOILER UPPER SURFACE HAS SUSPECTED DELAMINATION AREA MARKED. REPAIRED DELAM AREA ON RT NR 3 SPOILER IAW SRM 51-71-00 VOL NR 2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 86,089 hrs · 31,014 cycles

MAIN DECK STA 1990 RBL 27 UNDER FLOOR HAS CORROSION AROUND NUT PLATE. MARKED NR 13 (ABOVE FLOOR) REMOVED DAMAGED FLOOR BOARD SUPPORT P/N WSP0711-554, FABRICATED FLOOR BOARD SUPPORT P/M WSP 0711-554 REF DWG WSP 0711, PROCESSED FLOOR BOARD SUPPORT P/N WSP 0711-554 REF DWG 0711, AND INSTALLED FLOOR BOARD SUPPORT P/N WSP 0711-554 REF SRM 51-31-01 VOL 2, SRM 51-3301 VOL2, AND SRM 51-35-01 VOL 2. MAJOR REPAIR

Part: FLOOR SUPPORT — WORN (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

MAIN DECK; STA. 440 26RBL FLOOR SUPPORT HAS UNDOCUMENTED MODIFICATION. DOT 47 REMOVED AND REPLACED AS REQUIRED FLOOR SUPPORT AT MAIN DECK; STA 440, RBL 19-26. REF. SRM 51-35-01 VOL 2 AND DWF: ABA8320 MAJOR REPAIR.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

MAIN DECK; STA. 485 - 490 15RBL SEAT TRACK DAMAGED 4" SECTION MISSING ON IB LEG. DOT 43 NEW SEAT TRACK INSTALLED AT LOCATION NOTED WORKED ON NR 501 REF SRM 51-31-01 VII MAJOR REPAIR.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

MAIN DECK - STA. 635 RBL 8. SEAT TRACK CRACKED LOWER FLANGE. NOTE: SEAT TRACK UNDER BALL MAT AREA. REPLACED DAMAGED SEAT TRACK FROM STA 635 TO STATION 615 REF SRM 53-70-00 FIG 1 VI, SRM 51-31-01 VOL, SRZ 10-53-002 DWG MAJOR REPAIR.

Part: SUPPORT — CRACKED (ZONE 100) · airframe 86,089 hrs · 31,014 cycles

FWD CARGO COMPT STA 795 FLOOR SUPPORT IS CRACKED. REMOVED AND REPLACED CRACKED FLOOR SUPPORT AS REQUIRED REF SRM51-35-01 VOL 2 AND DAC DWG ADA0235, NEW FLOOR SUPPORT PART NUMBER FXADA0235-3.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

MAIN DECK; STA. 485 75LBL SEAT TRACK DAMAGED - 4" OF MISSING MISSING OB LEG. DOT 42 NOTE: RCB AREA INSTALLED NEW SEAT TRACK @ NOTED LOCATION REF SRM 51-31-01 VOL II DWG WSP0826 REF NR500.

Part: FLOOR SUPPORT — CORRODED (BS 1900) · corrosion level 3 · airframe 86,089 hrs · 31,014 cycles

MAIN DECK, BS 1900, RBL 52 FLOOR SUPPORT WAS CORRODED. REPAIRED THE FLOOR SUPPORT IAW EA 8-5310-T0343200 P1. MAJOR REPAIR.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

MAIN DECK STA 427 LBL 79 LEFT SIDE LATERAL FLOOR SUPPORT ABA7339-1 DAMAGED AT CLIP NUT LOCATION. REMOVED DAMAGED FLOOR SUPPORT AND FAB NEW PER DRAWING ABA7339 AND SRM 51-33- 01 VOL 2. MAJOR REPAIR.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 3 · airframe 86,089 hrs · 31,014 cycles

MAIN DECK STA 1900 RBL52 FLOOR SUPPORT WSP0711-552 UNDER NUTPLATE IS CORRODED. REF SDR #: 19-2779 REPAIRED FLOOR SUPPORT WSP0711-552 PER EA 8-5310-T0343200 P1 FLOOR SUPPORT DOUBLER REPAIR AT STA 1895-1900" MAJOR REPAIR.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

STA 488 RBL 17 SEAT TRACK WSP0826-513, TRACK DAMAGED AT FASTENER HOLE REMOVED AND REPLACED NOTED SEAT TRACK RF SRM 51-31-01 VOL II, DAC DWG WSP0826 MAJOR REPAIR.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

STA 488 LBL 82 SEAT TRACK WSP0826-509, FLANGE DAMAGED AT SCREW HOLE. INSTALLED NEW SEAT TRACK @ NOTED LOCATION REF SRN 51-31-01 VOL II DWG WSP0826.

Part: FRAME — CORRODED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

AFT CARGO COMPT, STA 1901 FRAME UNDERSIDE CORROSION BY NUTPLATE. ACCOMPLISH CORROSION REPAIR PER SRM 53-00-01 FIG 9 VOL 1.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

FORWARD AVIONICS COMPARTMENT STA 449 4 INCHES LEFT OF CENTERLINE CLIP HAS CORROSION. REMOVED AND REPLACED INTERCOSTAL AS REQUIRED IN REF DWG ABA7882 AND SRM-51-31-01 VOL II.

Part: BRACKET — LOOSE (TE FLAP) · airframe 86,089 hrs · 31,014 cycles

RT WING TRAILING EDGE OUTBD FLAP, INBD HINGE, BULLET FAIRING (635EL) INTERNAL BRACKET HAS LOOSE FASTENERS. REMOVED AND REPLACED INTERNAL BRACKET ON FAIRING 635EL, RT WING T/E, O/B FLAP, I/B HINGE REF SRM 51-33-01 VOL 2.

Part: BRACKET — CRACKED (TE FLAP) · airframe 86,089 hrs · 31,014 cycles

RT WING TRAILING EDGE OUTBD FLAP, INBD HINGE, BULLET FAIRING (635EL ) INTERNAL BRACKET HAS LOOSE FASTENERS. FABRICATED NEW BRACKET AS REQ PER DWG ARC0504.

Part: BULKHEAD — DAMAGED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

CENTER CARGO COMPT STA1841 BULKHEAD SKIN DAMAGED (MARKED) REPLACED WEB AGA7170-3 AND AGA7170-4 PER SRM 51-31-01 VOL. 2. AND DAC DWG AGA7170.

Part: SKIN — WORN (TAILCONE) · airframe 86,089 hrs · 31,014 cycles

TAIL CONE FOREWARD UPPER LEFT SKIN EDGE HAS WEAR MARKS MARKED NR 5 REPAIRED THE DAMAGE AREA AS REQUIRED REF SRM 53-00-01 FIG. 4 SHEET. 2 VOL. 1.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

A/C COMPT, PACK BAY NR 1. APPROX STA 565 TO 588, JUST O/B OF EXHAUST DOOR. RUSTED /CORRODED FASTENERS AND FRAME AND SKIN STRUCTURE. REMOVED AND REPLACED WITH LONGERON ACA3353-3 WITH SPLICE FROM STATION 561 TO STATION 590 REF SRM 53-00-01 FIG 7 SHEETS 5-7 DETAIL 3 VOL 1.

Part: SKIN — CORRODED (LT WING) · airframe 86,089 hrs · 31,014 cycles

LT WING UPPER SURFACE AT APPROX XORS 264 STRINGER 12 CORROSION AROUND ONE (1) FASTENER. REMOVED CORROSION REF SRM 57-10-00 FIG 60 SHEET 1 VOL 1. MATERIAL REMOVED WAS APPROX .023 INCH MAX ALLOWED IS 0.017 INCH PER SRM 57-10-00 FIG 61 SHEET 4. AREA IS OUT OF LIMITS MSV MATERIAL REMOVED WAS .023 INCH, FOUND BLEND ACCEPTABLE PER NOTED INSTRUCTIONS AS A PERMANENT REPAIR EA 8-5710-T0343126.

Part: SKIN — CORRODED (RT WING) · airframe 86,089 hrs · 31,014 cycles

RT WING UPPER SURFACE AT APPROX XORS 264 STRINGER 13 CORROSION AROUND TWO (2) FASTENERS. REMOVED CORROSION REF SRM 57-10-00 FIG 60 SHEET 1 VOL 1. MATERIAL REMOVED WAS APPROX .022 INCH MAX ALLOWED IS 0.010 INCH PER SRM 57-10-00 FIG 64 SHEET 4. AREA IS OUT OF LIMITS MSV MATERIAL REMOVED WAS .022 INCH, FOUND BLEND ACCEPTABLE PER NOTED INSTRUCTIONS AS A PERMANENT REPAIR EA 8-5710-T0343126.

Part: SKIN — CORRODED (RT WING) · airframe 86,089 hrs · 31,014 cycles

RT WING UPPER SURFACE AT APPROX XORS 387 STRINGER 5 CORROSION AROUND TWO (2) FASTENERS. REMOVED CORROSION REF SRM 57-10-00 FIG 60 SHEET 1 VOL 1. MATERIAL REMOVED WAS APPROX. .034 INCH MAX ALLOWED IS 0.016 INCH PER SRM 57-10-00 FIG 61 SHEET 4 AREA IS OUT OF LIMITS MSV MATERIAL REMOVED WAS .034 INCH, FOUND BLEND ACCEPTABLE PER NOTED INSTRUCTIONS AS A PERMANENT REPAIR EA 8-5710-T0343126.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

MAIN DECK : SEAT TRACK RBL X= 107.25 NEAR STA 695 WORN MARKED REMOVED DAMAGE AND PLUGGED SEAT TRACK REF SRM 53-70-00 FIG 2 VOL. I MAJOR REPAIR.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

MAIN DECK SEAT TRACK LBL X= 47.50 NEAR STA 755 WORN. REPLACED DAMAGED SEAT TRACK REF SRM 53-70-00, FIG 1, VOL 1 & SRM 51-31-01, VOL 2. MAJOR REPAIR.

Part: SKIN — CORRODED (RT WING) · airframe 86,089 hrs · 31,014 cycles

RT WING UPPER SURFACE AT APPROX XORS 264 BETWEEN STRINGERS 9 AND 10, CORROSION AROUND ONE (1) FASTENER. REMOVED CORROSION REF SRM 57-10-00 FIG 60 SHEET 1 VOL 1. MATERIAL REMOVED WAS APPROX .035-.157 INCH MAX ALLOWED IS 0.012-0.019 INCH PER SRM 57-10-00 FIG 61 SHEET 4. AREA IS OUT OF LIMITS MSV MATERIAL REMOVED WAS .157 INCH, FOUND BLEND ACCEPTABLE PER NOTED INSTRUCTIONS AS A PERMANENT REPAIR EA 8-5710-T0343126.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 86,089 hrs · 31,014 cycles

MAIN DECK : SEAT TRACK RBL X= 8.50 NEAR STA 755 WORN MARKED INSTALLED NEW SEAT TRACK SPLICE REF SRM 53-70-00 FIG 1 VOL I MAJOR REPAIR.

Part: CONNECTOR — DEFECTIVE (MLG TRANSDUCER) · airframe 85,909 hrs · 30,884 cycles

UPON EXTENDING GEAR ON FINAL WE RECEIVED A LEVEL 2 ANTISKID L FAIL ALERT. REMOVED NR 1 MLG WHEEL TRANSDUCER ASSY, REF AMM 32-45-03-2. FOUND FULLY PUSHED PIN ON NR 1 MLG WHEEL TRANSDUCER PLUG P1-1695, WIRE G89A20BL, PIN 2. FURTHER T/S REQUIRED. REMOVED AND REPLACED NR 1 WHEEL SPEED TRANSDUCER CONNECTOR P1-1695 IAW SWPM 20-31-13 AND WDM 32-45-02. TRANSDUCER REQUIRES INSTALL AND OPS CHECK. INSTALLED WHEEL TRANSDUCER IAW MM 32-46-03-2 OPS CHECK GOOD A/C OK TO CONTINUE.

Part: CONTROL UNIT — FAILED (ANTI-SKID SYS) · airframe 85,907 hrs · 30,883 cycles

UPON PUTTING LANDING GEAR DOWN, GOT LEVEL 2 ANTI-SKID L FAIL ALERT. ON LAST LEG FAULTS FOUND ASCU INTERNAL FAULT CODE 324141. RTS FAILED. REMOVED AND REPLACED ANTI SKID CONTROL UNIT PER AMM 32-45-01-4, PERFORMED RETURN TO SERVICE TEST NO FAULTS NOTED. A/C OK FOR SVC. ANTI SKID CTL UNIT REMOVED PN 142-109 SN 179.

Part: PUMP — FAILED (NR 3 ENGINE) · airframe 85,285 hrs · 30,494 cycles

HYD 3 FAIL WHEN SELECTING GEAR DOWN. REMOVED AND REPLACED NR 3 ENGINE DRIVEN HYDRAULIC PUMPS LEFT AND RIGHT REF AMM 29-11-01-2. OPS AND LEAK CHECKS REQUIRED. REF AMM 29-12-02/201 REMOVED AND REPLACED NR 3 ENGINE HYDRAULIC PUMP PRESSURE LINE MANIFOLD FILTER ELEMENT. NR 3 ENG HYDRAULIC PUMP CASE DRAIN LINE MANIFOLD FILTER ELEMENT. NR 3 ENG HYDRAULIC SYSTEM RETURN FILTER ELEMENT. LEAK AND OPS CHECKS REQUIRED.

Part: LIGHT — MALFUNCTIONED (EMERGENCY SYS) · airframe 85,124 hrs · 30,400 cycles

EMERGENCY TEST FAILED, ALERT DISPLAYED IAW AMM 24-00-00-5-0, DOWN POWERED ACFT, REPOWERED. RESET THE LT EMERGENCY BUSS SENSE BREAKER. SYSTEM OPS CHECKED GOOD IAW AMM 24-00-00-5. SUSPECT COLD WEATHER. OK FOR SERVICE.

Part: WIRE — BROKEN (CONNECTOR) · airframe 85,036 hrs · 30,353 cycles

PDIS 360 26-10 4655 13DEC17 MEM FACT U LOGPAGES:2734383 ENG #3 FIRE INDICATION ON CLIMB OUT. COMPLIED WITH QRH PROCEDURES, INCLUDING DISCHARGE OF AGT 2. FIRE INDICATIONS STOPPED. CRASH CREW REPORTED NO INDICATIONS OF FIRE VISIBLE. RETURNED #3 ENG FIRE DETECTORS TO NORMAL OPS PER MD10 MEL 26-11-01-01. EXAMINED #3 ENGINE FOR LOOSE DUCTS OF EVIDENCE OF A FIRE. NONE FOUND. WHILE SHAKING WIRE HARNESS FOR PYLON FIRE DETECTOR A&B RECIEVED INTERMITENT B LOOP FAULT. R/R B LOOP HARNESS AND A LOOP HARNESS FOR PYLON FIRE DETECTORS. IAW MD10 MM 20-30-02-2. PERFORMED FIRE TEST IAW MD10 MM 26-11-02-5. FIRE TEST PASSED. FOILED PNEUMATIC DUCTS IAW MD10 MM 36-00-00-0. PERFORMED HIGH PWER RUN FOR #3 ENG IAW MD10 JRH. 3 MIN INTO RUN RECIEVED #3 ENG B LOOP FAULT. FAULT WAS ON SOLID DURING RUN FOR 10 MIN. ON TAXI BACK TO GATE FAULT WAS INTERMITENT AND ON SOLID AGAIN BY THE TIME WE PARKED. REEXAMINED PYLON B LOOP HARNESS AND WAS ABLE TO MAKE FAULT COME AND GO BY SHAKING CONNECTOR AT THE PYLON JUNCTION BOX. EXAMINED ALL FOILED DUCTS NO LEAKS NOTED. SHGN 14DEC17 00:41 MEM U REF WDM 26-11-03 FOUND WIRES AT CONNECTORS R5-8024 AND R5-8025 BORKEN INSIDE CONNECTORS AT PINS A AND B OF PLUG 8025 AND A B AND C OF 8024. PERFORMED HIGH PWER RUN FOR #3 ENG NO DEFECTS NOTED SYSTEM CHECKS NORMAL.

Part: DUCT — LEAKING (9TH STAGE COOLIN) · airframe 84,503 hrs · 30,038 cycles

TWO HOURS INTO FLIGHT, HAD A QUICK FLASH ALERT LEVEL 2 FOR THE NR 2 ENGINE FIRE LOOP A, LASTED ONE SECOND AND WENT AWAY. 15 MINUTES LATER HAD STEADY LEVEL 2 ALERT FOR LOOP B. RAN QRH CHECKLIST, LOOP A TESTED GOOD. OPERATED IN LOOP A AT THAT POINT. ALL OTHER ENGINE INDICATIONS LOOKED NORMAL. NOT USING NR 2 PACK SO CLOSED THE NR 2 ENGINE BLEED AIR SWITCH AS A PRECAUTION. 10 MINUTES LATER RECEIVED A NR 2 ENGINE FIRE WARNING. RAN THE ENGINE FIRE CHECKLIST, SHUT DOWN THE NR 2 ENGINE, USED BOTH FIRE BOTTLES, FIRE WARNING REMAINED ON DIVERTED. R2D 9TH STAGE COOLING DUCT IAW AMM 70-00-00-2.

Part: ACTUATOR — INOPERATIVE (L1 DOOR) · airframe 84,098 hrs · 29,803 cycles

1L DOOR INOP. ELECTRIC DOOR ACTUATOR INOP. FOR EMERGENCY EGRESS, USE PNEUMATIC SYSTEM TO OPERATE DOOR. REPLACED L1 DOOR ACTUATOR ELECTRIC REF AMM 52-11-01-2. ADJUSTED CLUTCH CABLE REF AMM 52-11-00-5.

Part: SLIDE — INOPERATIVE (L1 DOOR) · airframe 83,446 hrs · 29,460 cycles

L1 DOOR SLIDE PRESSURE LIGHT ILLUMINATED. TROUBLE SHOT IAW FIM 25-61-00-2, TASK 25-61-00-810-802, PTT INDICATOR LIGHT DOESN`T GO OFF. CHECKED PLUG OUT OF JACK WITH OHM METER, READS ZERO. EVCUATION SLIDE IS INOPERATIVE. REMOVED AND REPLACED THE L1 DOOR SLIDE ASSY IAW AMM 25-61-02-4. L1 SLIDE ASSY REMOVED AND REPLACED.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 83,408 hrs · 29,444 cycles

LOWER FUSELAGE SKIN FOUND SURFACE CORROSION AT FWD DRAIN MAST LOCATION STA 665 APPROX. TRIMMED OUT SKIN DAMAGED, FABRICATED FILLER, DOUBLERS AND INSTALLED REF SRM 53-20-00 FIG 6 SHEET 7 VOL 1.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 83,408 hrs · 29,444 cycles

LT STA 595 BULKHEAD TEE CAP VERTICAL LEG HAS A .5 INCH CRACK THROUGH THE LOWER FASTENER AT LONGERON 39L. REMOVED AND REPLACED SECTION OF TEE CHORD BETWEEN LONGERONS 36L AND 40L IN REF TO DWG SR10530064 AND EA 8-5310-T0328457.

Part: BRACKET — CRACKED (BS 595) · airframe 83,408 hrs · 29,444 cycles

BS 595 BULKHEAD, BETWEEN STRINGERS 44 AND 45L AFT SIDE ANGLE CRACKED. REMOVED AND REPLACED THE BRACKET IAW SRM 51-33-01 VOL2 PAGE 1.

Part: SKIN — DAMAGED (LT WING) · airframe 83,408 hrs · 29,444 cycles

LT WING FUEL TANK LANDING 536CB HAS 1 BLOWN HOLE. REPAIRED PER EA 8-5710-T0328817, LT WING LOWER SURFACE-TANK ACCESS PANELS.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 83,408 hrs · 29,444 cycles

STA 595 BULKHEAD T CAP, LT FORWARD SIDE, HORIZONTAL LEG BETWEEN STR 38L AND STR 40L. 8 EA FASTENER HOLES SHOW CRACK INDICATION. REMOVED AND REPLACED SECTION OF TEE CHORD BETWEEN LONGERONS 36L AND 40L IN REF TO DWG SR10530064 AND EA 8-5310-T0328457.

Part: SKIN — DAMAGED (LT WING) · airframe 83,408 hrs · 29,444 cycles

LEFT WING FUEL TANK LANDING 538DB HAS 1 DAMAGED HOLES. REPAIRED IAW EA 8-5710-T0328817.

Part: SKIN — DAMAGED (LT WING) · airframe 83,408 hrs · 29,444 cycles

LEFT WING FUEL TANK LANDING 536BB HAS 2 DAMAGED HOLES. REPAIRED IAW EA 8-5710-T0328817.

Part: STRUCTURE — CRACKED (BS 595 BULKHEAD) · airframe 83,408 hrs · 29,444 cycles

BS 595 BULKHEAD TEE CAP AFT HORIZONTAL LEG HAS FOUR OPEN HOLES WITH CRACK INDICATIONS BETWEEN LONGERON 39 AND 40L. REMOVED AND REPLACED IAW DWG SR10530064 AND EA 8-5310-T0328457.

Part: SUPPORT FRAME — CORRODED (BS 380) · airframe 83,408 hrs · 29,444 cycles

LAVATORY SHROUD FRAME CORRODED. REMOVED THE CORROSION, TREATED AND PRIMED IAW SRM 51-21-01 VOL2.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 83,408 hrs · 29,444 cycles

MAIN DECK SEAT TRACK FROM STATION 715 TO 770, BUTTLINE 28 LBL DAMAGED. REPLACED DAMAGED SEAT TRACK, FROM STATION 715 TO 770, 28LBL REF SRM 53-70-00 FIG 1 VOL 1.

Part: DOOR — CORRODED (ZONE 100) · corrosion level 2 · airframe 83,408 hrs · 29,444 cycles

CENTER ACCESSORY BAY DOOR AFT LEDGE SHOWS SIGN OF CORROSION. REPAIRED IAW EA 8-5330-T0328525.

Part: CARGO TRACK — CORRODED (BS 1927) · corrosion level 2 · airframe 83,408 hrs · 29,444 cycles

AFT CARGO RT CARGO TRACK AT BS 1927 IS CORRODED. REMOVED AND REPLACED THE CARGO TRACK FROM BS 1841 TO 1964, RBL 45 IAW DRAWING AGA3855

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 83,408 hrs · 29,444 cycles

MAIN DECK SEAT TRACK STA 1621 X= 8.50 LT, GOUGED/WORN. REPAIR SEAT TRACK REF SRM 53-70-00 FIG 1 VOL 1.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 83,408 hrs · 29,444 cycles

STA 595 TEECAP, RT SIDE, ACM COMPARTMENT NR 3. CRACK FOUND ON FWD LEG OF TEE CAP BETWEEN LONGERON 38 AND 39. REMOVED AND REPLACED SMALL SECTION OF TEE CHORD BY SPLICING IN A NEW SECTION OF TEE CHORD, P/N ACA7016-501 BETWEEN LONGERONS 36R AND 44R IN REF TO DRAWING SR10530064 AND EA 8-5310-T0328290.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 83,408 hrs · 29,444 cycles

MAIN CABIN, JUST INBOARD OF L1 DOOR THRESHOLD, DELAMINATION FOUND AT FLOOR PANEL 225BF. REMOVED, FABRICATED NEW 225BF PANEL REF DRAWING SRZ-25-005, AND INSTALLED PANEL REF SRM 51-31-01 VOL2.

Part: SKIN — CRACKED (TE FLAP) · airframe 83,408 hrs · 29,444 cycles

RT WING OUTBD FLAP UPPER SURFACE XOF 565, CRACK IN SKIN APPROX 2.5" LONG. CONFIRMED WITH NDT HFEC. ENDS OF CRACK MARKED. REPAIRED RT WING O/B FLAP REF SRM 57-10-00 FIG 85 SHEET2 VOL 1.

Part: SEAT TRACK — WORN (BS 1530) · airframe 83,408 hrs · 29,444 cycles

MAIN DECK, SEAT TRACK IS DAMAGED AT RBL 51 BS 1510. CUT DAMAGED, FABRICATED AND INSTALLED SEAT TRACK IAW.SRM 53-70-00 FIG.1 VOL. 1

Part: SEAT TRACK — WORN (BS 1530) · airframe 83,408 hrs · 29,444 cycles

MAIN DECK, SEAT TRACK IS DAMAGED AT RBL 51 BS 1520. CUT DAMAGED, FABRICATED AND INSTALLED SEAT TRACK IAW.SRM 53-70-00 FIG.1 VOL. 1

Part: SEAT TRACK — DAMAGED (BS 1521) · airframe 83,408 hrs · 29,444 cycles

MAIN DECK: SEAT TRACK BS 1521,RBL 47.50 DAMAGED. CUT DAMAGED, FABRICATED AND INSTALLED SEAT TRACK IAW SRM 53-70-00 FIG.1 VOL. 1

Part: FRAME — CORRODED (BS 440) · airframe 83,408 hrs · 29,444 cycles

FUSELAGE LOWER SKIN AT BS 440 LONGERON 50R AT BELLFRAME, HAS ONE EACH BLIND FASTENER INSTALLED. INSIDE BETWEEN SKIN AND BELLFRAME IS A GAP , POSSIBLE CORROSION IN BETWEEN. CUT OUT CORROSION DAMAGE ON BELLFRAME REF: SRM 53-00-01 FIG 8 SHEET 1, LOCATED AND DRILLED OUT ANGLE AND FILLER REF: SRM 53-00-01 FIG 8 SHEET 1,A ND INSTALLED ANGLE AND FILLER REF: SRM 53-00-01 FIG 8 SHEET 1 VOL 1.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 83,408 hrs · 29,444 cycles

SEAT TRACK BS 1239 LBL 27.5 WORN. CUT SEAT TRACK BS 1209-1229 LBL 20, FABRICATED AND INSTALLED A NEW SEAT TRACK SECTION IAW SRM 53-70-00 FIG 1. VOL 1.

Part: TEE FITTING — CRACKED (BS 595 BULKHEAD) · airframe 83,408 hrs · 29,444 cycles

BS 595 BULKHEAD TEE CAP VERTICAL LEG HAS A .75 INCH CRACK THROUGH THE LOWER FASTENER AT LONGERON 43R. REMOVED AND REPLACED SECTION OF TEE FITTING IAW DRAWING SR10530064 AND EA 8-5310-T0328290.

Part: BULKHEAD WEB — CRACKED (BS 595) · airframe 83,408 hrs · 29,444 cycles

BS 595 BULKHEAD WEB HAS A CRACK INDICATION AT LONGERON 43R. REPAIRED IAW SRM 53-40-00 FIG 25, SHEET 2, VOL 1.

Part: VANE — DAMAGED (LT WING TE FLAP) · airframe 83,408 hrs · 29,444 cycles

LEFT INBD FLAP VANE, HAD A SMALL HOLE N BOTTOM SIDE LOCATED NEAR OTBD SIDE OF VANE. REPAIRED IAW SRM 51-00-01 VOL 1, FIG 4, PG 11.

Part: VANE — DAMAGED (LT WING TE FLAP) · airframe 83,408 hrs · 29,444 cycles

LEFT INBD FLAP VANE, HAD A SMALL HOLE ON BOTOM SIDE LOCATED NEAR CENTER OF THE VANE. REPAIRED IAW SRM 51-00-01 VOL 1, FIG 4, PG 11.

Part: VANE — DENTED (LT WING TE FLAP) · airframe 83,408 hrs · 29,444 cycles

LEFT INBD FLAP VANE TOP SIDE, OTBD SECTION HAD SEVERAL DENTS NOTED. REPAIRED IAW SRM 51-00-01 VOL 1, FIG 4, PG 11.

Part: PANEL — DELAMINATED (RT WING) · airframe 83,408 hrs · 29,444 cycles

RIGHT UNDER WING PANEL 641AL DELAMINATED ALONG ALL FOUR EDGES. REPAIRED THE WING PANEL IAW SRM 51-71-00 VOL 2, AND PAINTED PER SRM 51-21-02 VOL 2.

Part: PANEL — DELAMINATED (RT WING) · airframe 83,408 hrs · 29,444 cycles

RIGHT UNDER WING PANEL 641AL DELAMINATED ALONG ALL FOUR EDGES. REPAIRED THE WING PANEL IAW SRM 51-71-00 VOL 2 AND PAINTED PER SRM 51-21-02 VOL 2.

Part: LENS — UNKNOWN (L1 DOOR SLIDE) · airframe 83,188 hrs · 29,309 cycles

DURING PREFLIGHT, L1 DOOR PRESS TO TEST FOR SLIDE WILL NOT ILLUMINATE REMOVED AND REPLACED L1 DOOR SLIDE TEST LIGHT LENS ASSY IAW MM 25-61-03-2. ACFT OK TO CONTINUE.

Part: SENSOR — OUT OF ADJUST (LE SLAT) · airframe 82,672 hrs · 29,013 cycles

ON FINAL APPROACH GOT INTERMITTENT SLAT DISAGREE LVL 2 ALERT, ALERT WOULD COME ON FOR 1 OR 2 SECONDS THEN GO OUT. STICK SHAKER WOULD ACTIVATE WITH DISAGREE ALERT. RETRACTED GEAR & WENT TO FLAPS 15 170 KTS & DISAGREE ALERT STOPPED. RECONFIGURED & LANDED. NO ADVERSE PITCH OR ROLL NOTED WITH AUTOPILOT ON OR OFF. TROUBLE SHOT SLAT SYS IAW FIM 27-80-00-2. ALL FCC TESTS PASSED WITH NO FAIL INDICATIONS. PERFORMED AMM 27-84-00-5-0 ADJUSTMENT TEST OF SLAT POSITION SENSORS & FOUND SENSOR L2A INDUCTANCE READING OUT OF TOLERANCE. ADJUSTED SENSOR L2A AS REQUIRED & CYCLED SLATS TO FULLY EXTEND & RETRACT SEVERAL TIMES. ALL READINGS FALL WITHIN SPECIFIED TOLERANCE & NO SLAT DISAGREE ALERT DISPLAYED. SLAT & STICK SHAKER SYS TESTED NORMAL IAW AMM 27-84-00-5 & 27-35-02-2.

Part: CABLE — FAILED (FEEDBACK) · airframe 816 hrs · 28,417 cycles

PASSING FL 350 MULTIPLE COMPRESSOR STALLS ON NR 2 ENG, FOLLOWED BY A ROLL BACK. REDUCED THROTTLE TO IDLE & ENG STABILIZED. NO EXCEEDENCES NOTED. AT IDLE NR 2 ENG WAS N1 43% FF 400 LB HIGHER, N2 WAS ABOUT 2% HIGHER, COMPARED TO ENGS 1 & 3 AT IDLE. R & R VSV FEEDBACK CABLE IAW MM 75-31-01-2.

Part: SKIN — CRACKED (FUSELAGE) · airframe 816 hrs · 28,392 cycles

CRACK FOUND ON FUSELAGE SKIN AT UPPER AFT CORNER OF EXHAUST VLV CUT OUT. REPAIRED IAW SRM 53-20-00 FIG 2 WITH DEVIATIONS PROVIDED IN EA 8-5330-T0317819.

Part: ACTUATOR — FAILED (L1 DOOR) · airframe 814 hrs · 28,287 cycles

1L CABIN DOOR, ELECTRIC MOTOR THAT RAISES & LOWERS THE DOOR IS BEGINNING TO FAIL. OPERATES INTERMITTENTLY, AT TIMES THE DOOR WILL ONLY RAISE 10 TO 12 INCHES, OTHER TIMES OPERATES NORMALLY. CAN HEAR MOTOR DEVELOP HIGH PITCHED WHINE WHEN BEGINNING TO FAIL. REPLACED L1 DOOR ACTUATOR IAW MM 52-11-01-2. OPS CHECKED NORMAL. ACFT OK SERVICE.

Part: FIRE BOTTLE — INOPERATIVE (CARGO BAY) · airframe 81,000 hrs · 28,029 cycles

50MIN INTO FLIGHT GOT NR 2 LOWER AFT FLASHING DISCHARGE. DEPLOYED NR 2 BOTTLE, NR1 DEFERRED, FOLLOWED BY SMOKE RED INDICATION WHICH WENT OUT AFTER SEVERAL MINUTES. FIRE EXTINGUISHER CYLINDER NR 2 INOPERATIVE. ALL LOWER CARGO COMPARTMENTS MUST REMAIN EMPTY.

Part: FLOORBEAM — DENTED (BS 1741) · airframe 80,801 hrs · 27,913 cycles

FLOORBEAM IN THE CARGO BAY BS 1741, DOUBLER DENTED AT X=0. REPAIRED IAW SRM 53-00-01 VOL I FIGURE 10 AND EO 8-5100-7-5001 B3 PART 2. REPAIR CLASSIFIED MINOR IAW GMM 6-2-100.

Part: FLOORBEAM — MECHANIC ERROR (BS 735) · airframe 80,801 hrs · 27,913 cycles

REPAIR ON MAIN DECK FLOORBEAM UPPER TEE AT BS 735 X= 36. EVALUATED & FOUND NOT REPAIRED IAW APPROVED SRM REPAIR. REPAIRED IAW EA8-5310-T0311669 PART 1.

Part: LONGERON — CORRODED (BS 1025) · corrosion level 2 · airframe 80,801 hrs · 27,913 cycles

EXISTING REPAIR ON LOWER FWD CARGO COMPARTMENT AT BS 1025 LONGERON 52. REPAIR DOUBLER CORRODED AROUND FASTENER HOLES. CORROSION REMOVED IAW SRM 51-21-00 VOL II AND FOUND OUT OF LIMITS IAW SRM 53-00-01 FIG. 1B VOL I. REPAIRED IAW SRM 53-10-00FIG. 2 VOL I AND DRAWING ADA7898 REV A.

Part: SKIN — CRACKED (RT WING) · airframe 80,801 hrs · 27,913 cycles

RIGHT WING FIXED LE SKIN FOUND CRACKED AT XOS 611 PANEL 619CB CUT OUT. REPAIRED IAW SRM 57-10-00 FIGURE 68 VOLUME I REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: SKIN — CRACKED (LT WING) · airframe 80,801 hrs · 27,913 cycles

REWORK REQUIRED LT WING LE INTERNAL STRUCTURE JUST OTBD OF NR 10 SLAT TRACK SKIN SPLICE CRACKED APPROX 4 INCHES STATION XOS 667.679. SKIN REMOVED IAW SRM 51-31-01 VOLUME II NEW DOUBLER FABRICATED AS PER DOUGLAS DRAWING ARB1249 REVISION AA AND INSTALLED IAW SRM 51-31-01 VOLUME II REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 80,801 hrs · 27,913 cycles

LOWER CTR CARGO COMPARTMENT AT STATION Y=1801, X=3 SHEAR CLIP FOUND CORROSION AFTER REMOVED FOR ACCESS. REMOVED AND REPLACED WITH FABRICATED SHEAR CLIP AS PER SRM 51-35-01 VOLUME II. SHEAR CLIP FABRICATED AS PER DRAWING AFA0053 REVISION N REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100

Part: REPAIR — DAMAGED (TE FLAP) · airframe 80,801 hrs · 27,913 cycles

AGEING ACFT EXISTING REPAIR DOUBLER ON UPPER SURFACE AT LT WING OTBD FLAP, STATION XOF 533. EXISTING BEARING STRIP ON UPPER SURFACE AT LEFT WING OUTBOARD FLAP, STATION XOF 533 EVALUATED AND FOUND DAMAGED. EXISTING REPAIR REMOVED AND REPLACED WITH NEW REPAIR AS PER SRM 57-10-00 FIG 7 VOL I EA#8-5750-T0311717 PART 1 TITLE: " WINGS - FLIGHT SURFACES - LT O/B FLAP HAS MANY BEARING STRIPS REPAIRS WITH LOOSE FASTENER HOLES - SECTIONAL SKIN REPLACEMENT AND SKIN SPLICES PER SRM AND ONE DOUBLER REPLACED AS PER SRM - RSC TRACKING" ACCOMPLISHED. REFER TO WRI#57501226 AND SNRM N00096 FOR DETAILS. EO#8-5100-7-5001 B3 PART 2 TITLE: Ï¿½STRUCTURES Ï¿½ REPAIR CATALOG Ï¿½ MD-10 REPAIR IDENTIFICATION, CLASSIFICATION AND TRACKING OF SMRÏ¿½S ON AIRCRAFT BEING INDUCTED INTO THE FEDEX MAINTENANCE SYSTEM 14 CFR 121.1105, 121.1107, 121.1109 AND 121.707Ï¿½ ACCOMPLISHED. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2- 100

Part: REPAIR — DAMAGED (TE FLAP) · airframe 80,801 hrs · 27,913 cycles

AGEING ACFT EXISTING BEARING STRIPS REPAIR 10 EACH AT LT WING OTBD FLAP. EXISTING BEARING STRIPS AT LEFT WING OUTBOARD FLAP BETWEEN STA XOF 511.260 - XOF 599.378 EVALUATED AND FOUND DAMAGE TO REPAIR STRIPS. EXISTING REPAIR REMOVED AND REPLACED WITH NEW REPAIR AS PER SRM 57-10-00 FIG. 7 VOL. I EA#8-5750-T0311717 PART 1 TITLE: " WINGS - FLIGHT SURFACES - LHW O/B FLAP HAS MANY BEARING STRIPS REPAIRS WITH LOOSE FASTENER HOLES - SECTIONAL SKIN REPLACEMENT AND SKIN SPLICES PER SRM AND ONE DOUBLER REPLACED AS PER SRM - RSC TRACKING" ACCOMPLISHED. REFER TO WRI#57501226 FOR DETAILS. EO#8-5100-7-5001 B3 PART 2 TITLE: Ï¿½STRUCTURES Ï¿½ REPAIR CATALOG Ï¿½ MD-10 REPAIR IDENTIFICATION, CLASSIFICATION AND TRACKING OF SMRÏ¿½S ON AIRCRAFT BEING INDUCTED INTO THE FEDEX MAINTENANCE SYSTEM 14 CFR 121.1105, 121.1107, 121.1109 AND 121.707Ï¿½ ACCOMPLISHED. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2- 100

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 80,801 hrs · 27,913 cycles

LOWER FWD CARGO COMPARTMENT BILGE AREA AT STATION Y=879, X=-5 SHEAR CLIP FOUND CORROSION. SHEAR CLIP REMOVED AND REPLACED WITH FABRICATED SHEAR CLIP AS PER SRM 51-35-01 VOLUME II. SHEAR CLIP FABRICATED AS PER DRAWING ADA0112 REVISION R. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100

Part: STANCHION — CORRODED (FUSELAGE) · corrosion level 2 · airframe 80,801 hrs · 27,913 cycles

LOWER AFT FUSELAGE WASTE COMPARTMENT AT STATION Y=1964, X=-25 STANCHION FOUND CORROSIONS MARKED. REMOVED AND REPLACED WITH NEW REWORKED STANCHION AS PER SRM 51-31-01 VOLUME II. NEW STANCHION REWORKED AS PER DRAWING AGA3224 REVISION S. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100

Part: STANCHION — CORRODED (FUSELAGE) · corrosion level 2 · airframe 80,801 hrs · 27,913 cycles

LOWER AFT FUSELAGE WASTE COMPARTMENT AT STATION Y=1964, X=0 STANCHION FOUND CORROSION AS MARKED. REMOVED AND REPLACED WITH NEW REWORKED STANCHION AS PER SRM 51-35-01 VOLUME II. NEW STANCHION REWORKED AS PER DRAWING AGA3224 REVISION S. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 NOTE: X=0 - CENTER POSITION

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 80,801 hrs · 27,913 cycles

MAIN DECK SEAT TRACK AT STATION 720, X=8.5 FOUND CORROSION AS MARKED. SEAT TRACK REPAIRED AS PER SRM 53-70-00 FIGURE 1 VOLUME I REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100

Part: WIRE — DAMAGED (ENG INDICATION) · airframe 80,439 hrs · 27,709 cycles

NR 2 ENGINE EGT 1018 DEGREES DURING CLIMB OUT. EGT STAYED HIGH AT REDUCED POWER SETTING. EGT HIGH ALERT, SHUTDOWN ENGINE. DUMPED 8500 LBS FUEL PRIOR TO LANDING. WIRE FOUND DAMAGED, WIRE REPLACED.

Part: SWITCH — INOPERATIVE (MLG) · airframe 79,402 hrs · 27,136 cycles

BOTH PRIMARY AND SECONDARY GEAR LIGHTS REMAINED ILLUMINATED WITH GEAR HANDLE UP. COMPLIED WITH QRH. REF FIM 32-30, FAULT CODE 32-30-01, STEP (B) (2)CHECK FOR CONTINUITY BETWEEN PIN A AND B WITH GEAR HANDLE UP POSITION, FOUND BAD GEAR HANDLE SWITCH S1-431 NO CONTINUITY BETWEEN A & B. CONFIRMED S1-431 AT FAULT. CONFIRMED THE FAULT IS ASSOCIATED WITH ALL THREE LANDING GEAR RED WARNING LIGHTS (BOTH CHANNELS). PULLED GEAR LEVEL BACK, HALFWAY THROUGH TRAVEL ALL THREE RED LIGHTS CAME ON, THEN WOULD RETURN TO GREEN WITH HANDLE PULLED. R & R SWITCH IAW MM 32-61-04-2. PERFORMED OPS CHECK OF GEAR HANDLE SWITCH IAW FIM 32-30, STEPS 5B 1-2 & C/W STEPS 1-5 OF MM 32-61-04-2 WITH NO DEFECTS NOTED, OPS CHECKED SATISFACTORY IAW MM 32-61-04-2,

Part: DUCT — LEAKING (BLEED AIR) · airframe 78,637 hrs · 26,720 cycles

ENG 3 FIRE INDICATION,ENG SHUTDOWN, ONE BOTTLE FIRED. INDICATION OF FIRE WAS VERY BRIEF WITH NO OTHER ABNORMAL INDICATIONS. INSPECTED ALL LOOPS, CHECKED LOOP B FOR SHORTS TO GROUND OR CASE, NO FAULTS NOTED. INSPECTED ALL LOOP B CONNECTORS FOR INTEGRITY, NO DEFECTS NOTED. FOUND FOIL WRAP MISSING ON 5 DUCTS, SECURED CLAMPS, REPLACED FOIL, AND RAN ENGINE.

Part: SHEAR TIE — CORRODED (BS 1964) · corrosion level 2 · airframe 78,395 hrs · 26,567 cycles

AFT CARGO BAY AT BS 1964 BETWEEN LONGERONS 50L AND 50R FRAME CLIP IS CORRODED. REMOVED AND REPLACED FRAME CLIP IAW SRM 51-31-01 VOL 2. HEAT TREATED CLIP IAW SRM 51-10-01. FABRICATED CLIP PER SRM 51-10-01 FIG. 7. MAJOR REPAIR.

Part: WEB — DAMAGED (BS 1841) · airframe 78,395 hrs · 26,567 cycles

AFT CARGO BAY AT BS 1841, FRAME SUPPORT WEB HAS MULTIPLE GOUGES AS MARKED. FOUND ALL GOUGES OUT OF LIMITS, REMOVED DAMAGE AREAS IAW SRM 53-00-01, SHEET 2, NDT VERIFIED NO CRACKS IAW NTSDM 06-10-01, FABRICATED REPAIRS PARTS WEB FROM 7075/T6, IAW SRM 53-00-01, FIG 4, INSTALLED 3 EA REPAIR DOUBLERS IAW SRM 51-31-01, REPAIR CLASSIFIED AS MAJOR.

Part: INTERCOSTAL — CORRODED (BS 1701-1710) · corrosion level 2 · airframe 78,395 hrs · 26,567 cycles

CENTER CARGO BAY LOWER BOX AREA BS 1701 TO 1710, LONGERON 45R AND INTERCOSTALS ARE CORRODED. REPAIRED IAW SRM 53-50-01, FIG 15A AND FIG 22.

Part: DOOR FRAME — CORRODED (CARGO DOORWAY) · airframe 78,395 hrs · 26,567 cycles

FWD CARGO COMPT. LOWER CARGO DOOR JAMB FORWARD END IS CORRODED. REPAIRED FWD CARGO LOWER FWD JAMB IAW SRM 53-50-00, FIG 22 AND SRM 53-00-01, FIG 10, VOL I, REPAIR IS CLASSIFIED AS MAJOR.

Part: SHEAR TIE — CORRODED (BS 871) · airframe 78,395 hrs · 26,567 cycles

AFT CARGO BAY AT STA. 1871 BETWEEN LONGERON 47L AND LONGERON 48L, FRAME CLIP CORRODED. R & R SHEAR CLIP IAW SRM 51-31-01, REPAIR PART FABRICATED ON STAM WITH TR 12/937190, REMOVED AND REINSTALLED 2 EA SPLICES AND 1EA SUPPORT IAW SRM 51-31-01 FOR ACCESS. REPAIR CLASSIFIED AS MAJOR.

Part: ANGLE — CORRODED (BS 975) · airframe 78,395 hrs · 26,567 cycles

FORWARD CARGO COMPT LOWER AFT DOOR JAMB IS CORRODED. REMOVED CORROSION IAW SRM 53-50-00, FIG 15, VOL 1, ORIGINAL MATERIAL THICKNESS IS 0.240", REMAINING MATERIAL LT IS 0.153" AND FOUND WITHIN LIMIT IAW SRM 53-50-00, FIG 15, SHEET 1 AND 2, REPAIR IS CLASSIFIED AS MAJOR.

Part: RIB — CRACKED (RT WING) · airframe 78,395 hrs · 26,567 cycles

RIGHT WING L/E CAVITY HAS CRACKED RIB OTBD SIDE OF PULLEY SUPPORT STRUCTURE BETWEEN SLAT TRACK 13 AND 14. REPAIRED CRACKED RIB IAW SRM 57-00-01, FIG 3.

Part: RIB — CRACKED (ZONE 600) · airframe 78,395 hrs · 26,567 cycles

RT WING L/E CAVITY HAS CRACKED RIB, INBD SIDE OF PULLEY SUPPORT STRUCTURE BETWEEN SLAT TRACK 13 AND 14. REPAIRED CRACKED RIB IAW SRM 57-00-01, FIG 3.

Part: CONTROLLER — FAILED (MANIFOLD) · airframe 77,585 hrs · 26,113 cycles

TURNED ON WING ANTI-ICE, LEVEL 3 ALERT MANIFOLD FAILURE. PRV BLEED AUTO CLOSED. OPERATED ENG AT IDLE. EMERGENCY LANDING. REMOVED AND REPLACED NR 1 MANIFOLD FAILURE CONTROLLER IAW AMM 36-23-01-4, OP'S CHECKED GOOD. OK FOR SERVICE.

Part: DOOR FRAME — CRACKED (ZONE 200) · airframe 75,901 hrs · 25,267 cycles

MAIN CARGO DOOR LOWER JAMB NR 1 SPOOL FITTING HOLES C AND D FOUND CRACKED INDICATION DURING HFEC OPEN HOLE INSPECTION. MAIN CARGO DOOR LOWER JAMB BEAM BORE HOLE COMMON TO NR 1 SPOOL FITTING HOLES C AND D REPAIRED AS PER E.A. 8-5310-132448, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 110.

Part: SPAR CAP — CRACKED (ZONE 600) · airframe 75,901 hrs · 25,267 cycles

DURING PERFORMING E.O. E8-5710-7-5007 PART 1, RIGHT HAND WING REAR SPAR LOWER CAP HFEC OPEN HOLE INSPECTION 01 EACH HOLE FOUND CRACKED INDICATION. RT WING REAR SPAR LOWER CAP 01 EACH FASTENER HOLE COLD WORKED REPAIRED TO FINAL HOLE SIZE PER STEP 7 OF E.O.8-5710-7-5007 PART 1, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100, REVISION 110.

Part: STRUCTURE — CORRODED (ZONE 200) · airframe 75,901 hrs · 25,267 cycles

CABIN CTR WING BOX UPPER SURFACE AT STA 1370 'X' = -30 FOUND CORRODED. CABIN CTR WING BOX UPPER SURFACE AT STA 1370 'X' = -30 REPAIRED IAW EA NR 8-5710-138579, TITLE: WINGS - BASIC WING STRUCTURE - CTR WING BOX UPPER SKIN CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: SPLICE PLATE — CORRODED (ZONE 200) · airframe 75,901 hrs · 25,267 cycles

CABIN CTR WING BOX UPPER SURFACE AT STA 1179, 'X' = -107 FOUND CORRODED. CABIN CTR WING BOX UPPER SURFACE AT STA 1179 'X' = -107 REPAIRED IAW EA NR 8-5710-138580, TITLE: FUSELAGE - MAIN FRAME - SURFACE CORROSION ON UPPER RT SPLICE PLATE PN ANB7011 BETWEEN STA 1176 TO 1278. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: SPLICE PLATE — CORRODED (ZONE 200) · airframe 75,901 hrs · 25,267 cycles

CABIN CTR WING BOX UPPER SURFACE AT STA 1295, 'X' = -107 FOUND CORRODED. CABIN CTR WING BOX UPPER SURFACE AT STA 1295 'X' = -107 REPAIRED IAW EA NR 8-5710-138580, TITLE: FUSELAGE - MAIN FRAME - SURFACE CORROSION ON UPPER RT SPLICE PLATE PN ANB7011 BETWEEN STA 1176 TO 1278. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: STRUCTURE — CORRODED (ZONE 200) · airframe 75,901 hrs · 25,267 cycles

CABIN CTR WING BOX UPPER SURFACE AT STA 1370, 'X' = -84 TO 'X' = -91 FOUND CORRODED. CABIN CTR WING BOX UPPER SURFACE AT STA 1370 'X' = -84 TO 'X' = -91 REPAIRED IAW EA NR 8-5710-138579, TITLE: WINGS - BASIC WING STRUCTURE - CTR WING BOX UPPER SKIN CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: SPLICE PLATE — CORRODED (ZONE 200) · airframe 75,901 hrs · 25,267 cycles

CABIN CTR WING UPPER SURFACE AT STA 1219, 'X' = -107 FOUND CORRODED. CABIN CTR WING UPPER SURFACE AT STA 1219 'X' = -107 REPAIRED IAW EA NR 8-5710-138580, TITLE: FUSELAGE - MAIN FRAME - SURFACE CORROSION ON UPPER RT SPLICE PLATE PN ANB7011 BETWEEN STA 1176 TO 1278. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: SPLICE PLATE — CORRODED (ZONE 200) · airframe 75,901 hrs · 25,267 cycles

CABIN CTR WING BOX UPPER SURFACE AT STA 1199, 'X' = -107 FOUND CORRODED. CABIN CTR WING BOX UPPER SURFACE AT STA 1199 'X' = -107 REPAIRED IAW EA NR 8-5710-138580, TITLE: FUSELAGE - MAIN FRAME - SURFACE CORROSION ON UPPER RT SPLICE PLATE PN ANB7011 BETWEEN STA 1176 TO 1278. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: SPLICE PLATE — CORRODED (ZONE 200) · airframe 75,901 hrs · 25,267 cycles

CABIN CENTER WING BOX UPPER SURFACE AT STA 1239, 'X' = -107 FOUND CORRODED. CABIN CENTER WING BOX UPPER SURFACE AT STA 1239 'X' = -107 REPAIRED IAW EA NR 8-5710-138580, TITLE: FUSELAGE - MAIN FRAME - SURFACE CORROSION ON UPPER RT SPLICE PLATE PN ANB7011 BETWEEN STA 1176 TO 1278. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: STRUCTURE — CORRODED (ZONE 200) · airframe 75,901 hrs · 25,267 cycles

CABIN CTR WING BOX UPPER SURFACE AT STA 1370 'X' = 80 FOUND CORRODED. CABIN CTR WING BOX UPPER SURFACE AT STA 1370 'X' = 80 REPAIRED IAW EA 8-5710-138579, TITLE: WINGS - BASIC WING STRUCTURE - CTR WING BOX UPPER SKIN CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: SPLICE PLATE — CORRODED (ZONE 200) · airframe 75,901 hrs · 25,267 cycles

CABIN CTR WING BOX UPPER SURFACE AT STA 1275, 'X' = -107 FOUND CORRODED. CABIN CTR WING BOX UPPER SURFACE AT STA 1275 'X' = -107 REPAIRED IAW EA NR 8-5710-138580, TITLE: FUSELAGE - MAIN FRAME - SURFACE CORROSION ON UPPER RT SPLICE PLATE PN ANB7011 BETWEEN STA 1176 TO 1278. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: SKIN — DENTED (ZONE 100) · airframe 75,901 hrs · 25,267 cycles

FUSELAGE EXTERIOR SKIN, LEFT HAND STA 1953 TO STA 1964 BETWEEN LONGERON 40 LEFT AND LONGERON 42 LEFT FOUND DENT. FUSELAGE EXTERIOR SKIN, LEFT HAND STA 1953 TO STA 1964 BETWEEN LONGERON 40 LEFT AND LONGERON 42 LEFT REPAIRED AS PER SRM 53-50-00 FIGURE 26, VOLUME I, REVISION 96. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 110.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 75,901 hrs · 25,267 cycles

CABIN: STA 1275, 'X' = -100 FLOORBEAM FOUND CRACKED. CABIN: STA 1275, 'X' = -100 FLOORBEAM REPAIRED AS PER E.A. 8-5310-132440, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 110.

Part: SKIN — DENTED (BS 1958-1963) · airframe 75,901 hrs · 25,267 cycles

AFT CARGO DOOR AFT LOWER JAMB EXTERIOR SKIN STA 1958 TO 1963, BETWEEN LONGERON 40 LEFT AND LONGERON 42 LEFT FOUND DENT. AFT CARGO DOOR AFT LOWER JAMB EXTERIOR SKIN STA 1958 TO STA 1963 BETWEEN LONGERON 40 LEFT AND LONGERON 42 LEFT REPAIRED AS PER SRM 53-50-00 FIGURE 26, VOLUME I, REVISION 96. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 110.

Part: SKIN — DENTED (ZONE 100) · airframe 75,901 hrs · 25,267 cycles

FUSELAGE EXTERIOR SKIN, LEFT HAND STA 1953 TO STA 1964 BETWEEN LONGERON 38 LEFT AND LONGERON 40 LEFT FOUND DENT. FUSELAGE EXTERIOR SKIN, LEFT HAND STA 1953 TO STA 1964 BETWEEN LONGERON 38 LEFT AND LONGERON 40 LEFT REPAIRED AS PER SRM 53-50-00 FIGURE 26, VOLUME I, REVISION 96. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 110.

Part: SKIN — CRACKED (STA 495) · airframe 75,901 hrs · 25,267 cycles

FUSELAGE - NR 3 AIR CONDITION COMPARTMENT DOOR CUT OUT UPPER FORWARD CORNER EXTERIOR SKIN FOUND CRACKED. CRACK AT NR 3 AIRCON DOOR CUTOUT UPPER FWD CORNER REPAIR AS PER EA 8-5330-140384 REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REV110.

Part: SKIN — DENTED (RT ELEVATOR) · airframe 75,901 hrs · 25,267 cycles

RIGHT INBD DETACHABLE ELEVATOR UPPER SURFACE FOUND DENTED. REPAIRED AS PER SRM 55-10-01 FIGURE 8, VOLUME I, REVISION 96. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100, REVISION 110.

Part: LONGERON SPLICE — CRACKED (BS 1531 L2R) · airframe 75,901 hrs · 25,267 cycles

UPPER FUSELAGE - CRACK INDICATION APPROXIMATELY 1.5 INCHES FOUND AT STA 1531 LONGERON 2 RIGHT, AFT INBOARD SIDE OF LONGERON SPLICE FITTING. UPPER FUSELAGE - STA 1531 LONGERON 2 RIGHT, LONGERON SPLICE FITTING REMOVED AND REPLACED PER SRM 51-33-01 VOLUME II, REVISION 96. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 110.

Part: LONGERON — CORRODED (BS 1341-1361) · airframe 75,901 hrs · 25,267 cycles

CABIN - LONGERON 17 LT FROM STA 1341 TO STA 1361 CORRODED. R & R IAW SRM 51-31-01 VOLUME II, REVISION 96. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 110.

Part: LONGERON — CORRODED (BS 1381-1401) · corrosion level 2 · airframe 75,901 hrs · 25,267 cycles

CABIN - LONGERON 17 LT FROM STA 1381 TO STA 1401 CORRODED. R & R IAW SRM 51-31-01 VOLUME II, REVISION 96. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 110.

Part: LONGERON — CORRODED (BS 1441-1461) · corrosion level 2 · airframe 75,901 hrs · 25,267 cycles

CABIN - LONGERON 17 LT FROM STA 1441 TO STA 1461 CORRODED. REMOVED AND REPLACED AS PER SRM 51-31-01, VOLUME II. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 110.

Part: LONGERON — CORRODED (BS 1381-1401) · airframe 75,901 hrs · 25,267 cycles

CABIN - LONGERON 19 LT FROM STA 1381 TO STA 1401 CORRODED. R & R IAW SRM 51-31-01 VOLUME II, REVISION 96. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 110.

Part: LONGERON — CORRODED (BS 1501-1521) · corrosion level 2 · airframe 75,901 hrs · 25,267 cycles

LONGERON 17 LT FROM STA 1501 TO STA 1521 CORRODED. DAMAGE REMOVED AS PER SRM 51-31-01 VOL 2 REV 96. NEW LONGERON FABRICATED AS PER QWG AEA 0220 P/N AEA0220-1 REV R. NEW LONGERON INSTALLED AS PER SRM 51-31-01 VOL 2 REV 96. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REV 110.

Part: LONGERON — CORRODED (BS 1421-1441) · corrosion level 2 · airframe 75,901 hrs · 25,267 cycles

CABIN - LONGERON 17 LT FROM STA 1421 TO STA 1441 CORRODED. R & R IAW SRM 51-31-01 VOLUME II, REVISION 96. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 110.

Part: SPLICE — CORRODED (BS 1641 S47-49R) · airframe 75,901 hrs · 25,267 cycles

CENTER CARGO COMPARTMENT - SPLICE ANGLE AT STA 1641 BETWEEN LONGERON 47 RIGHT AND LONGERON 49 RIGHT FOUND CORROSION. CENTER CARGO COMPARTMENT - SPLICE ANGLE AT STA 1641 BETWEEN LONGERON 47 RIGHT AND LONGERON 49 RIGHT REMOVED AND REPLACED AS PER SRM 51-31-01 VOLUME II, REVISION 96. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100, REVISION 110.

Part: SKIN — CRACKED (ZONE 600) · airframe 75,901 hrs · 25,267 cycles

RT WING ANTI ICE TELESCOPIC DUCT DOOR CUT OUT SKIN FOUND CRACKED. RT WING ANTI ICE TELESCOPIC DUCT DOOR CUT OUT SKIN REPAIRED IAW EA NR 8-5710-132442, TITLE: WINGS - RT WING ANTI-ICING TELESCOPIC DUCT DOOR CUTOUT - REPAIR. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 110.

Part: SKIN — DEFORMED (RT WING TE FLAP) · airframe 75,901 hrs · 25,267 cycles

RT WING OTBD T/E FLAP INBD LOWER EDGE FOUND DEFORMED. RT WING OTBD T/E FLAP INBD LOWER EDGE REPAIRED IAW SRM 57-10-00, FIG 7, VOLUME I, REVISION 96. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 110 SKIN.

Part: SLAT TRACK — CHAFED (NR 6 SLAT) · airframe 75,901 hrs · 25,267 cycles

LT WING NR 6 SLAT TRACK CHAFING WITH OTBD ATTACHED RIB FITTING. R & R IAW SRM 51-31-01 VOLUME I, REV 96. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 110.

Part: SKIN — DAMAGED (ZONE 100) · airframe 75,901 hrs · 25,267 cycles

FUSELAGE - FD CARGO DOOR CUT-OUT AFT LOWER MID AREA EXTERIOR SKIN FOUND DAMAGED. FWD CARGO DOOR CUTOUT AFT LOWER MID DAMAGED AREA TRIMMED OUT AS PER SRM 53-50-00 FIG 26 VOL 1 REV. 96. TRIMMED OUT AREA IS 1" X 9.5". REPAIR DOUBLER AND FILLER FABRICATED AND INSTALLED AS PER SRM 53-50-00 FIG 26 VOL1 REV96. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REV 110. REPAIR CARRIED OUT BET LONGERON 38R AND 41R STA 959.

Part: ENGINE — FAILED (NR 1) · airframe 75,851 hrs · 25,249 cycles

NR 1 ENGINE FAILURE AT ROTATION. ACFT SHUTTERED. NO FIRE INDICATION TOWER ADVISED FIREBALL ON LT SIDE OF ACFT. AUS R IN WORK. AUS R PERFORMED VISUAL INSP OF INLET AND EXHAUST AREA(S). NO APPARENT DAMAGE NOTED IN INLET. METAL PARTICLES FOUND IN EXHAUST PIPE. OPENED FAN AND REVERSER COWLS TO INSPECT FOR OBVIOUS DAMAGE OR BLOWN DUCTS, NONE NOTED. FOUND AGENT 1 LO LIGHT ILLUMINATED IN COCKPIT AND NR 1 FIRE BOTTLE TO BE DISCHARGED. NO FUEL WAS DUMPED BY CREW DURING AIR TURNBACK, 49K STILL ON-BOARD AT BLOCK-IN. MC1 R DUE TO METAL IN THE TAIL PIPE. R & R NR 1 ENGINE IAW WORKCARDS 71T0201-1, WC 71T0101-1, WC 71T0701-1. PERFORMED ENGINE RUNS & LEAK CHECKS PER JRH CHAPTER 5 AND 7. AIRCRAFT OK FOR SERVICE.

Part: WIRE HARNESS — DAMAGED · airframe 74,011 hrs · 24,331 cycles

ON CLIMB-OUT OF MEM RCVD LVL 3"MANF 2 FAIL" COMPLIED WITH QRH AND RETURNED MEM. RELEASED FOR SERVICE PER MEL/CDL: 36-23-01-02. NR 2 MANIFOLD FAIL DETECTION LOOP, INOP. MX MUST CLEAR ALERT PRIOR TO EACH DISPATCH. DO NOT PRESSURIZE PNEUMATIC SYS NR 2 EXCEPT FOR ENG START. DECAY TEST PASSED PER MM 36-00-01-5. FOUND LOOP D1-28 (C) AT FAULT. REMOVED AND INSTALLED NEW LOOP PER AMM 36-23-02-4. FOUND LOOP D1-28 (C) (UPPER SECTION) AT FAULT. REMOVED AND INSTALLED NEW LOOP IAW AMM 36-23-02-4, TESTED IAW MM 36-23-01 AND MM 36-23-00. CKS GOOD. CLOSED ALL ACCESS PANELS ON VERTICAL STAB.

Part: PRESSURE SWITCH — MALFUNCTIONED (LT WING) · airframe 71,253 hrs · 23,015 cycles

PDIS: ENROUTE AFW-LAX WITHIN 10 SECONDS AFTER TURNING WING ANTI-ICE ON, RECEIVED LEVEL 3 AIR MANIFOLD 1 FAILURE. DIVERT TO BOI. CHECKED MANIFOLD FAIL INDICATION PANEL IN CAC FOUND PRESS SWITCH FAULT BALL SET FOR LEFT WING. RESET FAULT INDICATION PANEL. PERFORMED DECAY CHECK ON NR 1 MANIFOLD PER MM. TEST OK. INSPECTED SLATS FOR LEAKS WITH PRESSURE APPLIED. FOUND LT WING ANTI ICE VLV O/B CLAMP LEAKING. REPOSITIONED CLAMP AND RESECURED. LEAK CK NORMAL. MEL WING ANTI ICE AS PRECAUTION. LAX/29 REACTIVATED WAI. FUNCTIONAL CHECK NORMAL.

Part: SPAR — CRACKED (RT WING) · airframe 70,707 hrs · 22,753 cycles

RIGHT WING REAR SPAR IS CRACKED AT NR 3 AFT FUEL BOOST PUMP, REMOVED PARTS. FABRICATED REPAIR DOUBLER AND INSTALLED REPAIR PARTS IAW SRM 57-10-00, FIG 52, VOL I.

Part: SKIN — DENTED (ZONE 100) · airframe 70,707 hrs · 22,753 cycles

FOUND FUSELAGE SKIN DENT AT LE OF RT STATIC PORT (PRIMARY) CREATING A GAP BETWEEN SKIN AND COMPENSATOR PLATE REPAIRED STATIC PORT REGION IAW SRM VOL I 53-20-00 FIG 9. CLASS "B" REPAIR REQUIRES REINSPECTION AND FOLLOWUP INSPECTIONS. INITIAL INSPECTION AT 34,000 AND REPETITIVE AT 23,000 IAW SRM VOL I 53-20-00 FIG 9.

Part: CONTROLLER — FAILED (BLEED AIR) · airframe 68,946 hrs · 22,007 cycles

DURING CRUISE FLIGHT, AIR MANIFOLD 2 FAIL, LEVEL ONE AIR SYSTEM 2 OFF. MANIFOLD RED LIGHT ON OVERHEAD MEL, RELEASED FOR SERVICE PER MEL/CDL: 36-23-01-02. NR 2 MANIFOLD FAIL DETECTION LOOP INOPERATIVE. TROUBLESHOT PER FIM 36-23-01, 36-23-04, AND 36-23-09. CLEARED AIU1 MX PREFLIGHT AND RAN AIR SYSTEM TEST. TEST FAILED AND AIU 1 CURRENT FAULT SHOWED "314211 NO LOOP 2 INPUT RECEIVED DURING PREFLT TEST-P (FIM FAULT CODE 36-23-09)." R & R NR 2 MANIFOLD FAILURE DETECTION CONTROLLER M/M 36-23-01-4. OPS CHECK SYSTEM DURING ENGINE RUN PER MD10 JRH, NO PROBLEMS NOTED. AIRCRAFT OK FOR SERVICE.

Part: CONTROLLER — MALFUNCTIONED (MANIFOLD) · airframe 68,772 hrs · 21,927 cycles

ON T/O CLIMBING OUT AT 5000FT, MASTER WARNING ILLUMINATED WITH -AIR MANF 2 FAIL- ALERT DISPLAYED AIR SYSTEM SHOWED NR 2 INDICATING RED WITH NR 2 BLEED OFF AND PACK 2 & 3 OFF. SYNOPTIC WARNED NOT TO PRESSURIZE MANIFOLD NR 2 RED -MANF- DISPLAYED ON OVERHEAD PANEL. RETURNED TO IND. PERFORMED AIR SYS TEST AND FAILED. AIU 1 CURRENT FAULTS WERE ALL 3 SYSTEMS TRIED NEW MANIFOLD FAULT DETECTION CONTROLLER AND WORKED NORMAL. COULD GET NR 2 MANIFOLD FAIL LIGHT WITH OR WITHOUT AIR APPLIED. PERFORMED NR 2 DECAY CHECK WITH ENG AIR PER MM SUPP. PERFORMED NR 2 DECAY CHECK WITH APU AIR PER MM SUPP. A/C OK FOR SERVICE.

Part: ANGLE — CORRODED · airframe 67,776 hrs · 21,479 cycles

CORROSION FOUND ON LEFT REAR SPAR CAP ANGLE APB 7080-1. REPAIRED IN ACCORDANCE WITH FEDEX EA 8-5340-84036 LT SLANT PANEL TEE ANGLE CORROSION REPAIR .

Part: SKIN — DENTED (FUSELAGE) · airframe 67,776 hrs · 21,479 cycles

LWR FUSELAGE EXT SKIN APPROX STA 1830 AT BL 0 AT THRESHOLD OF AFT BULK PIT DOOR HAS A CREASE WITH DENT APPROX 36 INCHES IN LENGTH.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 62,909 hrs · 19,190 cycles

BARE METAL AT CIRCUMFERENTIAL STRAP BETW. L40L & L41L FS 1871. REMOVED CORROSION,FABRICATED AND INSTALLED SHIM,DOUBLER,TRIPLER AND FINGER DOUBLERS IAW DC10-10/MD10-10 SRM 51-21-01 VOL I & II,53-20-00 VOL I PG.73 FIG. 6 SHT. 3 ,53- 20-00 VOL.I PG. 74 FIG. 6 SHT.4 AND 51-41-01 VOL II. MAJOR REPAIR

Part: CONNECTOR — FROZEN (FLAP TRANSMITTER) · airframe 66,448 hrs · 20,920 cycles

AFTER T/O THE UPPER FOOT CAME DOWN AND A/T'S WENT TO IDLE, THEN BTM FOOT CAME UP AND THROTTLES CLAMPED AND WENT TO MAX. DISC THROTTLES AND THEN FOOT CAME UP AND THROTTLES CAME TO MAX, CLAMP AGAIN. UPPER AND LOWER FOOT CYCLED INTO THE AIRSP CAUSING THROTTLES TO ALTERNATLEY GO FROM MAX TO IDLE. IT APPEARED THAT ACFT ONLY THOUGHT IT WAS TOO FAST. AIRSPEED WAS NEVER TOO FAST OR TOO SLOW FOR THE CONFIG. CHKD WIRING TO ROB FLAP TRANSMITTER FROM NR 1 FCC, NO FAULTS NOTED. FOUND CONNECTOR AT ROB TRANSMITTER ICED UP. REMOVED ICE AND DRIED PLUG REFER TO WRI 27- 50/2130 FOR CURRENT DEFERRAL PROCEDURE. USED ALTERNATE PROCEDURE FOR DEFERRAL WHICH REMOVES WIRE B502-1231 -22 FROM S3625.

Part: FRAME — CRACKED (FUSELAGE) · airframe 64,982 hrs · 20,226 cycles

UPPER AFT FUSELAGE FRAME CRACKED CANT STA 2092. REMOVED AND REPLACED FRAME IAW SRM 51-35-01 AND SRM 51-33-01 AT MAE ON N/R N00317 W/O 25240.

Part: BRACKET — CORRODED (LT WING FLAP) · airframe 64,982 hrs · 20,226 cycles

COMPLY WITH EA 8-5740-73884 WINGS - LT OUTBOARD FLAP, OUTBOAD HINGE BRACKET CORROSION REPAIR (P/N ARC0503). COMPLIED WITH EA 8-5740-73884 WINGS - LT OUTBOARD FLAP, OUTBOARD HINGE BRACKET CORROSION REPAIR (P/N ARC0503) AT MAE.

Part: BRACKET — CORRODED (FUSELAGE) · airframe 64,982 hrs · 20,226 cycles

COMPLY WITH EA 8-5740-73888 WINGS - RIGHT OUTBOARD FLAP, OUTBOARD HINGE, REWORK OF ACTUATOR LUG. COMPLIED WITH EA 8-5740-73888 WINGS - RIGHT OUTBOARD FLAP, OUTBOARD HINGE, REWORK OF ACTUATOR LUG AT MAE.

Part: FRAME — CRACKED (FUSELAGE) · airframe 64,982 hrs · 20,226 cycles

UPPER AFT FUSELAGE FRAME CRACKED CANT STA 2069. REMOVED AND REPLACED FRAME IAW SRM 51-35-02 AND SRM 51-33-01 AT MAE ON N/R N00320 W/O 25240.

Part: FRAME — CRACKED (FUSELAGE) · airframe 64,982 hrs · 20,226 cycles

UPPER AFT FUSELAGE FRAME CRACKED CANT STA 2046. REMOVED AND REPLACED FRAME IAW SRM 51-35-02 AND SRM 51-33-01 AT MAE ON N/R N00321 W/O 25240.