N550FE

Part: SUPPORT — CORRODED (AFT CARGO) · corrosion level 2 · airframe 93,053 hrs · 38,862 cycles

AFT CARGO COMPARTMENT BILGE, CORROSION ON VERTICAL FRAME SUPPORT BELOW FLOOR AT FWD BULKHEAD STA 1781 L-52, MARKED NR 2, 2020-12-10. REMOVED AND REPLACED THE STANCHION, IAW SRM 53-15-01, FIG 9A VOL 3 & DWG AFA 3225.

Part: ATTACH ANGLE — CRACKED (ZONE 100) · airframe 93,053 hrs · 38,862 cycles

AT CAC BAY LT SIDE, A CRACK FOUND ON 'ATTACHMENT ANGLE' FOR SUGAR SCOOP FITTING (P/N-NYB6042-7) AT FUS STA-1156. REMOVED AND REPLACED SUGAR SCOOP ATTACHMENT ANGLE AS REQUIRED, PER DWG NYB6042.

Part: STOP FITTING — CRACKED (ZONE 200) · airframe 93,053 hrs · 38,862 cycles

L-1 DOOR UPPER FWD CORNER STOP APPEARS TO BE CRACKED. REMOVED DAMAGED ABA7191-506 STOP ASSEMBLY AND INSTALLED NEW PART REFERENCE DRAWING ABA7191 AND EA NR 8-5210-T0358597. REWORK FROM ABA7191-1.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 93,053 hrs · 38,862 cycles

LT HORIZ LEADING EDGE CENTER SECTION (INTERAL) MULTIPLE CRACKS AT BEADED DOUBLE, APPROXIMATELY 27" OUTBOARD OF INBOARD EDGE (BETWEEN FRAMES 5-6). CRACKS WERE CONFIRMED WITH NDT HFEC. REPAIRED PER EA 8-5510-T0358321.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 93,053 hrs · 38,862 cycles

AFT FUSELAGE, RT SIDE STA 2163 LONG 33 NUTPLATE HOLE CORRODED OUT OF LIMITS. CONFIRMED WITH NDT. COMPLIED WITH FUSELAGE SKIN REPAIR, PER MD-10 SRM 53-20-00 PG 197-205 FIG 22.

Part: STIFFENER — CRACKED (NR 3 NACELLE) · airframe 93,053 hrs · 38,862 cycles

REWORK NR 343 FABRICATED PART NOT ACCEPTED: NR 3 ENGINE PYLON INTERNAL STRUCTURE/BOX AFT ANGLE SUPPORT FOR ACCESS DOOR 488BL COMPLETELY BROKEN OFF AND CRACKED VIEWING THRU ACCESS DOOR 488BR. (DOT 9) REMOVED AND REPLACED ANGLE SUPPORT FX AUB7087-15, AS REQUIRED PER DAC DWG AUB7087.

Part: ACCESS PANEL — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 93,053 hrs · 38,862 cycles

RIGHT HAND LEADING EDGE INBOARD SIDE P/N ACL7051-2-401 HAS CORROSION UNDER STRINGERS AROUND ACCESS PANEL 341, AT MARKED NR 14 (REQ RDR SDR). REPLACED DOUBLER P/N ALC7273-11, PER DOUGLAS DRW ALC7273 AND MD10 SRM 51-31-01 VOL II.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 93,053 hrs · 38,862 cycles

RT HORIZONTAL STABILIZER, AFT BODY FAIRING, HAS THREE DAMAGED NUTPLATES, AREA MARKED. COMPLIED WITH DOUBLER REPAIR INSTALLATION AT FUSELAGE SKIN STA 2163 BETWEEN LONGERON 12 & 13 RT, REF MD-10 SRM 53-00-01 FIG 4 (SHEET 2) VOL 1.

Part: SUPPORT — CRACKED (FUEL LINE) · airframe 93,053 hrs · 38,862 cycles

RT WING NR 3 FUEL TANK REFUELING/DEFUELING T-LINE SUPPORT BRACKET CRACKED P/N ARL0501-44. FABRICATED NEW SUPPORT BRACKET, REF DAC DWG ARL0501.

Part: DRIVE CHAIN — BROKEN (L1 DOOR EMER) · airframe 93,053 hrs · 38,862 cycles

L1 DOOR EMERGENCY OPERATION CHECK FAILED FOUND DRIVE CHAIN BROKEN. REPLACED CHAIN, PER CMM 52-11-09 AND GMM 52-10-01-2. OPERATIONS CHECKED EMERGENCY DOOR, PER WORK CARD 52C1301.

Part: DOUBLER — CORRODED (HORIZONTAL STAB) · airframe 93,053 hrs · 38,862 cycles

LEFT HORIZONTAL LEADING EDGE INBOARD SECTION ALC7051-1-401 HAS EXTENSIVE CORROSION. INSIDE AND OUTSIDE SKIN IS SWOLLEN AROUND FASTENERS, MARKED NR 15 AND NR 16. FOUND CORROSION TO BE ON ACCESS PANEL DOUBLER P/N ALC7273-13. REPLACED DOUBLER AND INSTALLED NEW FASTENERS, REF SRM 51-31-01 VOL II DAC DRAWING ALC7273.

Part: FITTING — CRACKED (BS 1156) · airframe 93,053 hrs · 38,862 cycles

LT FUSELAGE STRUCTURE, STA 1156 L39, SUGER SCOOP FITTING (AYB 7000) CRACKED APPROX 1 INCH BEYOND PREVIOUS STOP DRILL, MARKED. REMOVED AND REPLACED SUGAR SCOOP FITTING AYB7000-1, REFERENCE DOUGLAS DRAWING NYB6042.

Part: FRAME — CORRODED (ZONE 100) · airframe 93,053 hrs · 38,862 cycles

CENTER CARGO BILGE-STR 52 STA 1641-CORROSION AT FRAME, LOWER ANGLE AFT. REPAIRED CENTER CARGO BILGE STR 52 STA 1641 FRAME, REF SRM 53-30-00 FIG 5 (SHEET 1) VOL 1. MAJOR REPAIR AMT NR JG3884010 11/13/20 RII BUY BACK QC NR 439384 11/13/20. SEE ATTACHMENTS FOR JPF.

Part: FRAME — CORRODED (BS 1921) · airframe 93,053 hrs · 38,862 cycles

AFT CARGO COMPT BILGE, CORROSION ON FRAME, LOWER HAT SECTION, AT STA 1921 L-52 (MARKED #10) STA 1921, FRAME AGA7130-11, LOWER HAT, BETWEEN LONG L51 TO R51 REMOVED CORROSION REF MD10-10 SRM 51-21-01 VOL 2. DUE TO BLENDOUT PAST 20 PERCENT OF ORIGINAL THICKNESS 0.080", REMAINING THICKNESS 0.058", PERFORMED NESTED REPAIR CHANNEL REF MD10-10 SRM 53-30-00 FIG 8 VOL 1.

Part: FRAME — CORRODED (BS 1853) · airframe 93,053 hrs · 38,862 cycles

AFT CARGO COMPT BILGE, CORROSION ON FRAME, LOWER HAT SECTION, AT STA 1853 L-52 (MARKED #7) REMOVED CORROSION ON FRAME AGA0016-3, LOWER HAT SECTION, AT STA 1853 BETWEEN LONG L51 TO R51 REF MD10-10 SRM 51-21-01 VOL 2. INSTALLED NESTED CHANNEL REPAIR REF MD10-10 SRM 51-33-01 VOL 2, DUE TO BLEND OUT PAST 20 PERCENT OF ORIGINAL THICKNESS 0.071", REMAINING THICKNESS 0.053" REF MD10-10 SRM 53-30-00 FIG 8 VOL 1. "MAJOR REPAIR"

Part: FRAME — CORRODED (BS 1841) · airframe 93,053 hrs · 38,862 cycles

AFT CARGO COMPT BILGE, CORROSION ON FRAME, LOWER HAT SECTION, AT STA 1841 L-52 (MARKED #11) CORROSION ON FORMER/FRAME (2 PIECE) LWR CHANNEL AT STA 1841, LONG 50L TO 50R IS ON A PREVIOUS SPLICE REPAIR. REMOVED PREVIOUS SPLICE REPAIR IAW MD10-10 SRM 51-33- 01 VOL 2, THEN PERFORMED CHANNEL SPLICE REPAIR ON LWR CHANNEL ONLY IAW MD10-10 SRM 53-30-00 FIG 5 VOL 1. (NOTE: MD10-10 SRM 53-30-00 FIG 8 NOTATES "FOR 2 PIECE FRAME, ONLY EXISTING CHANNEL REQUIRES SPLICING") *MAJOR REPAIR*

Part: FITTING — CRACKED (FRAME) · airframe 93,053 hrs · 38,862 cycles

RT FUSELAGE AT STA 1156, FRAME FITTING (SUGAR SCOOP) CRACKED (CRACK CONTINUE PROPOGATE FROM PREVIOUS STOP DRILL INBOARD, VIEW FROM OUTSIDE. INSTALLED NEW EXTERNAL REPAIR DOUBLER, FILLER AND SHIM, PER EA: T8-5310-T0357791 P1.

Part: SKIN — CRACKED (FUSELAGE) · airframe 93,053 hrs · 38,862 cycles

RT FUSELAGE APPROXIMATELY AT STA 1156 SKIN HAS A 3" CRACK, PROPAGATING FROM EXTERNAL DOUBLER FORWARD BETWEEN STRINGER 38 AND 37, INSTALLED NEW EXTERNAL REPAIR DOUBLER, FILLER AND SHIM, PER EA: T8-5310-T0357791.

Part: CAP — CRACKED (ZONE 100) · airframe 93,053 hrs · 38,862 cycles

LT WING, FUSELAGE STRUCTURE SEEN THROUGH WING BODY FAIRING 154AB, STA 1156 STRINGER 39, FITTING CRACKED, MARKED. REPAIRED AREA REFERENCE EA 8-5310-T0357883.

Part: STIFFENER — CRACKED (RT NACELLE) · airframe 93,053 hrs · 38,862 cycles

NR 3 ENGINE PYLON INTERNAL STRUCTURE/BOX AFT ANGLE SUPPORT FOR ACCESS DOOR 488BL COMPLETLY BROKEN OFF AND CRACKED WING THRU ACCESS DOOR 488BR. (DOT 9) REMOVED AND REPLACED STIFFENER AUB7087-505, REF DAC DWG AUB7300 AND SRM 51-31-01 VOL 2.

Part: SKIN — CRACKED (RT WING) · airframe 93,053 hrs · 38,862 cycles

RT WING FIXED LEADING EDGE, INNER SURFACE, PILLOW DOUBLER IS CRACKED AT STA XOS 669. INSTALLED REPAIR DOUBLER AS REQUIRED, REF SRM 57-10-00 VOL 1 FIG 71 AND SRM 51-31-01 VOL 2.

Part: DOUBLER — CRACKED (RT WING LE) · airframe 93,053 hrs · 38,862 cycles

RT WING FIXED LEADING EDGE, INNER UPPER SURFACE, PILLOW DOUBLER IS CRACKED AT STA XOS 697. REPAIRED CRACKED DOUBLER, PER SRM 57-10-00 FIG 71 VOL 1.

Part: STIFFENER — CRACKED (RT WING) · airframe 93,053 hrs · 38,862 cycles

RT WING FIXED LEADING, INNER SURFACE, SKIN STIFFENER IS CRACKED AT STA XOS 697. REPAIRED STIFFENER, PER EA 8-5710-T0357549 "WINGS-BASIC WING STRUCTURE-RT WING LEADING EDGE UPPER STRINGER CRACKED AT XOS 696-REPAIR".

Part: SKIN — DENTED (ZONE 100) · airframe 93,053 hrs · 38,862 cycles

RT FUSELAGE EXTERIOR APPROXIMATELY STA 1853 BETWEEN LONGERON 37R-38R DENT. ENTERED IN ERROR.

Part: DOUBLER — CRACKED (BS 1195) · airframe 93,053 hrs · 38,862 cycles

CENTER WHEEL WELL FWD BULKHEAD RT OUTBOARD SPOILER PUSH/PULL M.J RODS FEED THROUGH DOUBLER LOWER AFT CORNER CRACKED. P/N AEA0526. R & R THE DOUBLER (P/N-AEA0526U2) WITH HI-LOK, PER SRM 51-33-01 VOL-II.

Part: SKIN — CRACKED (ZONE 100) · airframe 93,053 hrs · 38,862 cycles

CENTER CARGO DOOR AFT SKIN CUT-OUT AT APPROXIMATELY STA 1787 BETWEEN LONGERON 39L-41L. REPAIR DOUBLERS DAMAGED AT CENTER CARGO DOOR LOWER AFT CORNER STA 1787 BETWEEN LONGERON 39L-41L. REMOVED DAMAGED DOUBLERS NR 1 & NR 2 AND MADE NEW REPLACEMENT DOUBLERS NR 1 & NR 2 AND INSTALLED COMPLETE, PER SRM VOL 1, 53-50-00 FIGURE 26.

Part: SKIN — DAMAGED (BS 959) · airframe 93,053 hrs · 38,862 cycles

FWD CARGO DOOR CUT-OUT SKIN AT APPROXIMATELY STA 959 BETWEEN LONGERONS 40-41-REPAIR DOUBLERS ARE DAMAGED. R & R REPAIR DOUBLERS AND FILLER, REF SRM 53-50-00 VOL I FIGURE 26 PG 175 AND DWG ADA0237.

Part: DOUBLER — CRACKED (RT WING LE) · airframe 93,053 hrs · 38,862 cycles

RT WING, FWD LOWER LEADING EDGE: CRACK ON INTERCOSTAL. OUTBOARD OF NR 12 SLAT TRACK, STA XOS 790. REMOVED AND REPLACED CRACKED ARB1249-28, REF SRM 51-33-01 VOL 2 AND SRM 51-35-01 PG 40 VOL. 2 AND DWG ARB1249.

Part: WEB — DENTED (NR 2 PYLON) · airframe 92,423 hrs · 38,508 cycles

#2 ENGINE AFT PYLON CENTER SECTION VERTICAL WEB R/H SIDE IS DENTED. FABRICATED/INSTALLED #2 ENG PYLON WEB USING DOUGLAS DRW AVB7318, AVB7023 & AVB7050 AS A REFERENCE.

Part: FIRE DETECTOR — MALFUNCTIONED (NR 2 ENGINE) · airframe 92,423 hrs · 38,508 cycles

DURING QRH FOR COMPRESSOR STALL WE RECEIVED LEVEL 2 ENG 2 LOOP A ALERT/ POSSIBLE ENGINE FIRE. THE QRH PROCEDURES SHOWED NO FIRE SO WE LEFT ENG 2 AT IDLE WITH ENG 2 LOOP SWITCH IN B POSITION. #2 ENGINE FIRE DETECT SYSTEM OPS CHECK GOOD IAW MD10-10 MM 26-11-02-5 & 26-10-00-5. 2 EA PYLON DETECTORS REPLACED : P/N FOR ALL 4 UNITS REMOVED & INSTALLED IS 3851-01- 1350/825-7. (LOOP A S/N OFF: 200641 ; S/N ON: 200357) (LOOB B S/N OFF: 200429 : S/N ON 200582) . FIRE DETECTORS MANUFACTURED BY MEGGITT. AFT FIRE BARRIER WAS ALSO REPLACED, P/N AUL7058-1 (NO S/N)

Part: FIRE WARNING — FALSE ACTIVATION (COCKPIT) · airframe 92,423 hrs · 38,508 cycles

DURING QRH FOR COMPRESSOR STALL WE RECEIVED LEVEL 2 ENG 2 LOOP A ALERT/ POSSIBLE ENGINE FIRE. THE QRH PROCEDURES SHOWED NO FIRE SO WE LEFT ENG 2 AT IDLE WITH ENG 2 LOOP SWITCH IN B POSITION.

Part: ENGINE — UNKNOWN (NR 2) · airframe 92,423 hrs · 38,508 cycles

CLIMBING THRU FL340 WITH ENGINES ALL AT CLIMB POWER WE FELT A BUMP LIKE MINOR TURBULENCE. THEN ANOTHER AND ANOTHER. WE SAW ENG 2 N1 FLUCTUATING SO WE SUSPECTED A COMPRESSOR STALL. AS WE WERE RUNNING THE QRH FOR ENG COMPRESSOR STALL WE RECEIVED LEVEL 2 ENG 2 LOOP A. WE THEN RAN ENG 2 LOOP A CHECKLIST BEFORE FINISHING THE COMPRESSOR STALL CHECKLIST. THE ENG LOOP CHECKLIST INDICATED NO FIRE. THE COMPRESSOR STALL CHECKLIST HAD US ADVANCE #2 ENG SLOWLY. ALL INDICATIONS WERE NORMAL SO WE ELECTED TO LEAVE #2 AT IDLE THRU LANDING ROLLOUT.

Part: ENGINE — MALFUNCTIONED (NR 2) · airframe 92,423 hrs · 38,508 cycles

CLIMBING THRU FL340 WITH ENGINES ALL AT CLIMB POWER WE FELT A BUMP LIKE MINOR TURBULENCE. THEN ANOTHER AND ANOTHER. WE SAW ENG 2 N1 FLUCTUATING SO WE SUSPECTED A COMPRESSOR STALL. AS WE WERE RUNNING THE QRH FOR ENG COMPRESSOR STALL WE RECEIVED LEVEL 2 ENG 2 LOOP A. WE THEN RAN ENG 2 LOOP A CHECKLIST BEFORE FINISHING THE COMPRESSOR STALL CHECKLIST. THE ENG LOOP CHECKLIST INDICATED NO FIRE. THE COMPRESSOR STALL CHECKLIST HAD US ADVANCE #2 ENG SLOWLY. ALL INDICATIONS WERE NORMAL SO WE ELECTED TO LEAVE #2 AT IDLE THRU LANDING ROLLOUT. #2 ENGINE REPLACED SHGN 17APR20 18:38 IND INSTALLED #2 ENGINE REF WORK CARD 71T1701 WORK STILL IN PROGRESS DOCUMENTED INSTALL ONLY FACT 19APR20 21:12 IND COMPLETED #2 ENGINE INSTALLATION W/C 71T1701 OF GE P/N CF6-6D MSN 451125.

Part: BRACKET — DAMAGED (L1 DOOR) · airframe 91,429 hrs · 37,844 cycles

MDIS 550 25-60 7274 27APR19 OAK OPEN U UPON ENTERING THROUGH L1 DOOR, FOUND GIRT BAR HANGING AND DISCOVERED FWD ATTACHED BRACKET INDEX PIN SHEARED. REPLACED GIRT BAR BRACKET (HOOK), AND PERFORMED ADJ/TEST REF AMM 52-11-00. ALL CHECKS OK. BRACKET P/N, ABA7931-1 S/N, N/A.

Part: SKIN — CRACKED (R1 DOOR) · airframe 91,116 hrs · 37,636 cycles

R1 DOOR FWD LOWER CORNER DENTED. REPLACED LOWER SKIN OF R1 DOOR REF. SRM 52-10-00 FIG. 4A PAGE 14A VOL. 1, AND RSC TRACKING EA # 8-5210-T0344731.

Part: LEAD — DEFECTIVE (NR 1 EGT) · airframe 90,885 hrs · 37,498 cycles

AS AUTO THROTTLES WENT TO CLIMB TRUST, NR 1 EGT WENT TO 1018' WITH "ENG 1 EXCEEDANCE" ALERT. C/W MTSI, R&R ALL NR 1 EGT THERMOCOUPLE PROBES AND FWD AND AFT LEADS I/R/T MM 77-21-01-2. RAN ENGINE NR 1 AND NR 3 FOR COMPARISON. ENGINE NR 1 START EGT 560, EGT 375 AT IDLE, FF 1130 N2 58.0 N1 22.3. COMPARED TO ENGINE NR 3 WITHIN 1 DEGREE OF START EGT, AND 16 DEGREES AT STABLIZED IDLE. REFER TO R&R OF PARTS ON MTSI 77-20/6781.

Part: SKIN — DENTED (R1 DOOR) · airframe 90,869 hrs · 37,482 cycles

R1 FORWARD PASSENGER / CREW DOOR HAS DENTS IN SKIN ACROSS 4 FRAME BAYS, COMPLIED WITH EA 8-5210-T0340776 AND IAW SRM 52-10-00 FIG 12B. SECTIONAL SKIN REPLACEMENT REPAIR. MAJOR REPAIR.

Part: SKIN — CORRODED (TE FLAP) · corrosion level 2 · airframe 90,869 hrs · 37,482 cycles

BULGING SKIN AT LT INBD FLAP LOWER SURFACE MID AREA 22" INBD OF FLAP HINGE ARM. CORROSION FOUND TO BE BEYOND LIMITS AT BULGING SKIN AT LT INBD FLAP LOWER SURFACE MID AREA 22" INBD OF FLAP HINGE ARM IAW SRM 57-00-01 FIG 1A. REMOVED AND REPLACED LOWER SKIN AND LOWER T-ANGLE IAW DC10 SRM 51-31-01. MAJOR REPAIR.

Part: ANGLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 90,869 hrs · 37,482 cycles

CENTER CARGO COMPT, FWD WALL LOWER SECTION, FWD OF LT END ATTACHMENT OF LT ROLLER TRAY ALONG STA 1521 HAS CORROSION. REMOVED CORROSION IAW SRM 51-21-01 AND SRM 53-00-01 VOL I. MATERIAL LOSS .100 OUT OF LIMITS IAW SRM 53-00-01 VOL 1. REMOVED AND REPLACED ANGLE (REPAIR) IAW SRM 53-00-01 VOL I AT STA 1521 MAJOR REPAIR.

Part: DOOR SILL — CORRODED (FUSELAGE) · airframe 90,869 hrs · 37,482 cycles

CORROSION ON WEB IN CENTER CARGO COMPT DOOR SILL AREA BS 1701 TO BS 1705 UNDER FLOOR LEVEL. REMOVED CORROSION IAW SRM 51-21-01. MATERIAL LOSS .098 FOUND OUT OF LIMITS IAW SRM 53-00-01 FIG 1A. REMOVED AND REPLACED WEB IAW SRM 53-31-01. MAJOR REPAIR.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 90,869 hrs · 37,482 cycles

CRACKED CABIN FLOORBEAM BELOW LT OVERWING DOOR STA 1301. REPAIRED CABIN FLOORBEAM AT LT STA 1301 IAW REPAIR DWG SR10530081-7003. PERFORM REPETITIVE NDI INSPECTION AT LANDING INTERVALS 5000 LANDINGS. IAW SRM 51-50-01 VOL II. MAJOR REPAIR

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 90,869 hrs · 37,482 cycles

MAIN DECK BS 1481, X75.50 SEAT TRACK FLANGE HAD CORROSION. REMOVED THE CORROSION AND FOUND OUT OF LIMITS IAW SRM 53-70-00. FABRICATED A NEW SEAT TRACK REPAIR SPLICE. INSTALLED THE REPAIR IAW SRM 53-70-00, PAGE3. MAJOR REPAIR.

Part: O-RING — DAMAGED (HYDRAULIC SYS) · airframe 90,752 hrs · 37,398 cycles

LEVEL ONE HYD 3 ELEV OFF W/ SLOW LEAK TO HYD 3 QTY LO LEVEL ONE ON DESCENT AND GEAR EXTENDED. ON TAXI IN LEVEL 2 HYD 3 FAIL. BLOCK IN QTY 1.2. QTY DECREASED THROUGHOUT REMAINDER OF FLIGHT, QRH PROCEDURES FOLLOWED. QTY NEVER DECREASED TO THE POINT OF ENG PUMP DISCONNECT. AT TOUCH DOWN QTY WAS 0.9. ENGINE PUMP INDICATIONS NORMAL THE ENTIRE TIME. ENGINE SHUT DOWN AFTER TOUCH DOWN. AT BLOCK IN QTY LEVEL 1.2 AND INCREASED TO 1.4. TAIL END OF THE AIRPLANE FROM THE ELEVATOR FWD TO THE LOWER BELLY IS COVERED IN HYD FLUID. FOUND HYD FLUID LEAKING FROM UPPER HORIZONTAL STAB PRIMARY CONTROL VALVE REGULATOR. REPLACED CUT O-RING ON REGULATOR FITTING. SERVICED NR 3 HYD TO PROPER LEVEL REF MM12-13-02-3. OPERATED HORIZONTAL STAB REF MM 27-40-00-2-0. NO LEAKS NOTED. OPS CKS NORMAL. A/C OK FOR SERVICE REGULATOR P/N FOR SDR REF 3U3141-2 O-RING P/N -NAS1612-8A IPC REF 27-43-15-01 ITEM 772.

Part: TORQUE TUBE — FAILED (CARGO DOOR) · airframe 90,286 hrs · 37,115 cycles

MAIN CARGO DOOR WOULD NOT LATCH, WHEN CLOSED. FOUND TORQUE TUBE CRACKED AND BROKEN. REMOVED THE MAIN CARGO DOOR TORQUE TUBE ON FWD SIDE OF DOOR IAW CMM 52-34-04. INSTALLED A NEW TORQUE TUBE IAW CMM 52-34-04.

Part: WARNING LIGHT — FALSE ACTIVATION (MLG) · airframe 89,270 hrs · 36,509 cycles

AFTER TAKEOFF, NOTICED THREE RED GEAR LIGHTS. LEVELED AT 5000 FT, SLOWED TO 200KTS, COMPLIED WITH QRH, CYCLED GEAR. LIGHTS WENT OUT WITH NO FURTHER PROBLEMS. TROUBLESHOT FAULT IAW FIM 32-30-00-2-0, TASK 32-30-00-810-801, NO CURENT PSEU FAULTS OR FAULT HISTORY. ALL VOLTAGES AND DISCRETES CHECKED GOOD. PSEU RETURNED TO SERVICE PASSED, NO FAULTS. NO 90 DAY HISTORY. COULD NOT VERIFY DISCREPANCY. ACFT OK FOR SERVICE.

Part: TRIM SYSTEM — MALFUNCTIONED (RUDDER) · airframe 88,701 hrs · 36,200 cycles

RUDDER TRIM WHEEL WILL NOT TURN PAST 1R OR 1L. INSPECTED CABLES AND PULLEYS NO DEFECTS NOTED. APPLIED ICE PREVENTION COMPOUND TO AFT PRESSURE SEALS. RAN RUDDER TRIM FULL TRAVEL LEFT AND RIGHT WITH NO BINDING. ALL WORK DONE IAW AMM 20-20-07-2-0.

Part: ACCESS PANEL — PUNCTURED (LT WING) · airframe 88,692 hrs · 36,196 cycles

LEFT WING, BOTTOM ACCESS PANEL 541EB HAS A DAMAGED CORNER AND A PUNCTURE. PREPPED AND BONDED THE ACCESS PANEL IAW SRM 57-71-00 VOL 2 PAGE 64 PARA .16 A2.

Part: SKIN — CRACKED (RT WING) · airframe 88,692 hrs · 36,196 cycles

RIGHT WING UPPER SKIN HAS CRACKS. INSTALLED A REPAIR DOUBLER IAW SRM 57-10-00 FIG 55

Part: SPAR CAP — CRACKED (RT WING) · airframe 88,692 hrs · 36,196 cycles

RIGHT WING, LOWER REAR SPAR CAP AFT EDGE AT STA. XORS 404 HAS A .150 IN. CRACK PROPAGATING UP FROM THE LOWER EDGE. REPAIR IAW EA. 8-5710-T0329826

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 88,692 hrs · 36,196 cycles

CRACKED FRAME WEB AT LBL 105 STA 1146 FOUND DURING INSPECTION WORK CARD. REPLACED WEB PER SRM REF 51-35-01 VOL II WITH FABRICATED MATERIAL PER DWG AEA0259- 47 MATERIAL .040 2024.T3 MP3045884.

Part: SEAT TRACK — WORN (BS 1730) · airframe 88,692 hrs · 36,196 cycles

MAIN CABIN BS 1730, RBL 48 SEAT TRACK WORN. REPAIRED IAW SRM 53-70-00 FIG. 1A.

Part: SEAT TRACK — DAMAGED (BS 1380-1385) · airframe 88,692 hrs · 36,196 cycles

MAIN CABIN BS 1380 - 1385, RBL 72 SEAT TRACK MISSING LOBES. REPAIRED IAW SRM 53-70-00.

Part: SEAT TRACK — DAMAGED (BS 1640-1652) · airframe 88,692 hrs · 36,196 cycles

MAIN CABIN BS 1640 - 1652, LBL 48 SEAT TRACK DAMAGED. REPAIRED IAW SRM 53-70-00.

Part: SEAT TRACK — DAMAGED (BS 1624-1630) · airframe 88,692 hrs · 36,196 cycles

MAIN CABIN BS 1624 - 1630, LBL 12 SEAT TRACK LOBES DAMAGED. REPAIRED IAW SRM 53-70-00.

Part: RIB — CRACKED (LT WING) · airframe 88,692 hrs · 36,196 cycles

LT WING FIXED LEADING EDGE INT RIB CRACKED AT UPR AFT END. MRKD 30 IN. O/B OF NR 13 TRACK NEXT TO SECOND CRACK THAT HAS BEEN STOP DRILLED. REPAIRED L/H WING FIXED LEADING EDGE FORMER REF SRM 57-20-00 FIG 1 VOL 1.

Part: WEB — CRACKED (ACM BAY) · airframe 88,692 hrs · 36,196 cycles

NR 3 ACM BAY WEB CRACKED AT LONGERON 35R BS 615, 512, AND 1818, REPAIRED THE WEB IAW SRM 53-30-00 FIG 4 PG 13 VOL I.

Part: CONTROLLER — MALFUNCTIONED (HYDRAULIC SYS) · airframe 88,100 hrs · 35,867 cycles

HYD 1 OFF ALERT ILLUMINATED IN FLIGHT. QTY REMAINED ABOVE 7.1 FOR DURATION OF FLIGHT. PSI WAS 0, NO FAULTS FOUND ON ARRIVAL. TROUBLE SHOT IAW FIM 29-10-00-2. R & R HYD SYS CONTROLLER PN REMOVED 4059021-903 & SN 97080460 IAW AMM 29-08-01-2. RTS SATISFACTORY, ENG RUN PERFORMED WITH NO DEFECTS NOTED. ACFT OK TO CONTINUE.

Part: BOLT — UNKNOWN (L1 DOOR) · airframe 872 hrs · 35,455 cycles

DOOR 1L SLIDE ARMING HANDLE NOW DOES NOT GO INTO, SLIDE ARMED, POSITION & THE LEVEL ONE, DOOR OPEN, ANNUNCIATOR WILL NOT EXTINGUISH. INSTALLED BOLT IN AFT POWER ROLLER IAW MM 52-11-03-02.

Part: GIRT BAR — DIRTY (L1 DOOR) · airframe 868 hrs · 35,256 cycles

THE L1 ESCAPE SLIDE WAS DIFFICULT TO ARM, HAD TO OPEN & CLOSE THE L1 DOOR TWICE BEFORE THE SLIDE COULD BE COMPLETELY ARMED. CLEANED & LUBED GIRT BAR & GIRT BAR ROLLOVER LATCHES IAW MM 12-21-05-3-1. OPERATIONS CHECKED DOOR ARMING IAW MM 52-11-00-5-0. DOOR CHECKED NORMAL.

Part: ARMING LEVER — MALFUNCTIONED (ENTRY DOOR) · airframe 868 hrs · 35,201 cycles

LEFT CREW ENTRANCE DOOR ARMING LEVER DOES NOT MOVE COMPLETELY TO ARMED POSITION WITHOUT SEVERAL ATTEMPTS WHILE CYCLING THE DOOR OPEN & CLOSED. CLEANED & LUBRICATED L1 DOOR INTERIOR CONTROL MECHANISM. OPS CHECK OF ARMING LEVER WAS SATISFACTORY. IAW AMM 52-11-00-5.

Part: COVER — DAMAGED (R1 DOOR) · airframe 864 hrs · 34,962 cycles

R1 SLIDE COVER DAMAGED, SLIDE OK & SERVICEABLE, DOES NOT AFFECT DOOR OR SLIDE OPERATION. NO RESTRICTION, ITEM DEFERRED IAW THE NEF PROGRAM.

Part: CABLE — BROKEN (R1 DOOR) · airframe 864 hrs · 34,962 cycles

R1 DOOR CABLE SNAPPED AT LT SIDE OR AFT LOOKING FROM OUTSIDE. RELEASED FOR SERVICE IAW MEL 52-10-02-01.

Part: COWLING — WORN (NR 3 ENGINE) · airframe 85,977 hrs · 34,716 cycles

NUMBER 3 ENG LT FAN COWL AFT EDGE AT 10:00 HAS BEEN DAMAGED, WORN THROUGH TO HONEYCOMB. DAMAGE APPEARS TO HAVE BEEN CAUSED BY RIDING CONDITION WITH STRUCTURE. REPAIRED IAW SRM 51-71-00 VOL II & PAINTED IAW SRM 51-21-02 VOL II.

Part: SKIN — DAMAGED (RT WING) · airframe 85,977 hrs · 34,716 cycles

RIGHT WING LE AREA BLENDED APPROX 0.450 ABOVE & OTBD OF SLAT TRACK NR 3 DOT NR 17. REPAIR IAW SRM 57-40-01 REPAIR 10 & EA 8-5730-T0308613A PT3.

Part: SUPPORT — CRACKED (LT MLG WW) · airframe 85,977 hrs · 34,716 cycles

LEFT WW, WHEEL SUPPORT STRUCTURE ON AFT SECTION OF LOWER WW, OTBD SECTION, HAS LOWER T WITH A CRACK. R & R LT WW SUPPORT STRUCTURE IAW DWG ANB7203.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 85,977 hrs · 34,716 cycles

ACM BAY 1 STATION 595 THERE IS A CRACK AT STATION 595 BULKHEAD WEB. REPAIRED CRACK AT STATION 595 IN WEB IAW SRM 53-40-00 FIG 25 SHEET 1 & EA 8-5310-T0312644.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 85,977 hrs · 34,716 cycles

INTERCOSTAL PN ACA3819-503 CRACKED AT STATION 588 - 595 NG 4L. FABRICATED NEW INTERCOSTAL IAW ACA3353 & INSTALLED IAW SRM 51-35-01 VOL 2.

Part: PANEL — DELAMINATED (ZONE 600) · airframe 85,977 hrs · 34,716 cycles

RIGHT WING, INBD FLAP, HINGE PANEL 641AR, IS DELAMINATED IN TWO AREAS. REPAIRED PANEL IAW SRM 51-71-01 VOL II & PAINTED IAW SRM 51-21-02 VOL II.

Part: FITTING — CRACKED (FUSELAGE) · airframe 85,977 hrs · 34,716 cycles

CAC STATION 1156 RT FRAME BULKHEAD FITTING AT FLOORBEAM TIE IN FITTING CRACKED. REPAIRED IAW SRM 53-30-00 FIG 7 V 1.

Part: PANEL — DELAMINATED (VERTICAL STAB) · airframe 85,977 hrs · 34,716 cycles

VERTICAL STAB HINGE PANEL 374FL HAS DELAMINATION. REPAIRED PANEL 374FL IAW SRM 51-71-00 VOL II & PAINTED IAW SRM 51-21-02 VOL II.

Part: SKIN PANEL — DELAMINATED (LT WING) · airframe 85,977 hrs · 34,716 cycles

LEFT WING TAKEOFF, TE PANEL TOP SKIN PANEL ARC0728-501 DELAMINATED AROUND FASTENERS. REPAIRED LT WING TE PANEL ARC0728-501 IAW SRM 51-71-00 VOL II & PAINTED IAW SRM 51-21-02 VOL II.

Part: PANEL — DELAMINATED (VERTICAL STAB) · airframe 85,977 hrs · 34,716 cycles

VERTICAL STAB HINGE PANEL 374EL HAS DELAMINATION. REPAIRED IAW SRM 51-71-00 VOL II .

Part: WIRE HARNESS — DAMAGED (GENERATOR) · airframe 85,977 hrs · 34,716 cycles

STEEL BRAIDED CONDUIT FOR NR 3 ENGINE GENERATOR PMG & FIELD HARNESS IS DAMAGED AT RT LE ROOT FEED THRU AREA P3-XZB JUST ABOVE THE POWER FEEDER CABLES. REMOVED AND REPLICED TWISTED WIREBUNDLE IAW WDM 24-21- 31,SWPM 20-10-01 PAGE 298.77.

Part: PANEL — DELAMINATED (TE FLAP) · airframe 85,977 hrs · 34,716 cycles

LEFT WING OTBD FLAP HINGE PANEL 535BR IS DELAMINATED. REPAIRED PANEL 535BR IAW SRM 51-71-00 VOL II & PAINTED IAW SRM 51-21-02 VOL II.

Part: PANEL — DELAMINATED (VERTICAL STAB) · airframe 85,977 hrs · 34,716 cycles

VERTICAL STAB FWD OF LOWER RUDDERS, HINGED PANEL 374CL HAS DELAMINATION. REPAIRED PANEL 374CL IAW SRM 51-71-00 & PAINTED IAW SRM 51-21-02 VOL II.

Part: SKIN — CRACKED (RT WING) · airframe 85,977 hrs · 34,716 cycles

RIGHT WING OTBD FIXED LE, BOTTOM PANEL LAND CRACKED JUST INBD FROM FUEL FILL VLV ACCESS PANEL, MARKED, APPROX AT STATION XORS 885. INSTALLED REPAIR DOUBLER IAW SRM VOLUME I CHAPTER 57-10-00 FIGURE 49.

Part: BEAM — CRACKED (ZONE 100) · airframe 85,977 hrs · 34,716 cycles

AFT SIDE OF PRESSURE BULKHEAD AT BS 595 SUPPORT BEAM NCA 6044-29 CRACKED ON UPPER & LOWER FLANGE LT & RT OF CTR LINE 4 EACH. REPAIRED BEAM NCA 6044-29 IAW SRM 53-40-00 VOL 1 FIG 36.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 85,977 hrs · 34,716 cycles

AFT FUSELAGE WASTE TANK AREA STATION 1967 L52 AT FRAME CAP INTERCOSTAL CRACKED. INSTALLED REPAIR ANGLE IAW SRM 53-30-00 V1.

Part: SKIN — BUCKLED (FUSELAGE) · airframe 85,977 hrs · 34,716 cycles

LEFT UPPER FUSELAGE SKIN AT STATION 285, SKIN IS BUCKLED. REPAIR INSTALLED IAW SRM 53-20-00 FIG 13 SHEET 14.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 85,977 hrs · 34,716 cycles

NUMBER 1 ACM COMPARTMENT AFT BULKHEAD STATION 595, INBD UPPER, RT BELOW OF CEILING, SHOWING CRACK 4 INCHES LONG, MARKED. SUSPECT THE CRACK DUE TO EXCESSIVE AIR LEAKING DURING FUSELAGE DECAY CHECK. DID DVI OF AREA, FOUND TWO MISSING FASTENERS. INSTALLED NEW FASTENERS IAW SRM 51-33-01 VOL 2. NDT REQUESTED TO CHECK FOR CRACK. COMPLIED WITH HFEC OF NR 1 ACM AFT BULKHEAD WEB IAW NDT SPM PART 06, NO DEFECT NOTED.

Part: WINDOW FRAME — CRACKED (COCKPIT) · airframe 85,977 hrs · 34,716 cycles

UPPER FUSELAGE, COCKPIT WINDSHIELD CTR POST, A CRACK WAS FOUND AT RT MID-SECTION. BLENDED DAMAGED AREA IAW SRM 53-30-00, P. 41, PARAGRAPH 13 C, VOL. 1. COMPLIED WITH HFEC PER NDT-SPM 06. NO CRACK INDICATION NOTED.

Part: TEE FITTING — CRACKED (BS 595 BULKHEAD) · airframe 85,977 hrs · 34,716 cycles

NR 1 ACM BAY AFT BULKHEAD BS 595, TED FITTING SHOWING CRACKS ALONG BULKHEAD. REPAIRED IAW SRM 53-40-00 FIG. 25 SHEET 1 VOL. 1 AND EA 8-5310-T03126644

Part: FRAME — CRACKED (COCKPIT) · airframe 85,977 hrs · 34,716 cycles

UPPER FUSELAGE, COCKPIT WINDSHIELD CENTER POST, A CRACK WAS FOUND AT UPPER LT SIDE. BLENDED DAMAGE IAW SRM 53-30-00 PARAGRAPH 13C VOL.1. COMPLIED WITH HFEC PER NDT-SPM 06. NO CRACK INDICATION NOTED.

Part: SKIN — DAMAGED (RT WING) · airframe 85,513 hrs · 34,458 cycles

RT WING AROUND LOWER CUT OUT OF NR 9 SLAT TRACK ON PREVIOUS REPAIR PARTIALLY PULLED RIVETS WITH CURLED HEADS DUE TO SLAT RUB. CUT OUT DAMAGE IAW SRM 57-10-00. PERFORMED HFEC OF CUT OUT FOR DAMAGE REMOVAL IAW NTSPM 06-10-01 010, NO DEFECTS NOTED. REPAIRED IAW SRM 57-10-00 VOL 1, FIGURE 68 SHEET 2.

Part: SKIN — DAMAGED (LT WING) · airframe 85,513 hrs · 34,458 cycles

FOUND REPAIR DOUBLER LOOSE AT LT WING 9 SLAT TRACK. REMOVED PREVIOUS REPAIR IAW SRM 51-31-01 VOL II. REMOVED CRACKED AREA AT SLAT TRACK 9. REMOVED CRACKED AREA AT CORNER OF FUEL PANEL DOOR. IAW SRM 57-10-00 FIG 68. PERFORMED HFEC OF CUT OUT AREA IAW NTSPM 06-10-01.010, NO DEFECTS NOTED. REPAIRED IAW EA 8-5730-T0308730.

Part: SKIN — DAMAGED (RT WING) · airframe 85,513 hrs · 34,458 cycles

WHILE COMPLIED WITH FCD 8-5710-F0308207 FOUND APPROX 3/8 HOLE IN FIXED LE SKIN BETWEEN NR 1 & NR 2 SLAT. CLEANED & ROUTED DAMAGED AREA IAW SRM 53-00-01. APPROX FINAL BLENDED AREA IS FOUND TO BE 13/32 INCH WIDE & 1 1/2 INCHES LONG. SUBMITTED ERS 14-03583. COMPLIED WITH EA 8-5730-T0308613 PART 1. CLEANED & ROUTED DAMAGED AREA IAW SRM 53-00-01.

Part: SKIN — CRACKED (RT WING) · airframe 85,513 hrs · 34,458 cycles

FOUND RT WING 8 SLAT TRACK REPAIR LOOSE & WITH SMOKING RIVETS. CUT OUT DAMAGE AT UPPER & LOWER SKINS. IAW SRM 57-10-00 FIG 68. PERFORMED HFEC OF CUT OUT AREA IAW NTSPM 06-10-01.010, NO DEFECTS NOTED. REPAIRED IAW EA 8-5730-T0308755.

Part: SKIN — CRACKED (RT WING) · airframe 85,513 hrs · 34,458 cycles

RIGHT WING LE SKIN CRACKED AT ANTI-ICE DUCT CUT OUT UPPER INBD & OTBD CORNER, BETWEEN SLAT TRACKS 6 & 7. REPAIRED IAW SRM 57-40-01 FIG 201 AND EA 8-5710-T0308711.

Part: SKIN — CRACKED (LT WING) · airframe 85,513 hrs · 34,458 cycles

POSSIBLE CRACK ON LT WING FIRE BOTTLE DOOR INBD. CRACK VERIFIED IN LT WING LE FIRE BOTTLE ACCESS DOOR IAW NDT SPM PT 6. INSTALLED REPAIR FILLER AND DOUBLER IAW SRM 57-10-00 VOL 1 FIG 68 AND EA 8-5730-T0308636.

Part: SKIN — WORN (LT WING) · airframe 85,513 hrs · 34,458 cycles

DISCOVERED WORN AREAS ON FIXED LE SKIN INBD & OTBD OF LT NR 15 SLAT TRACK. BLENDED WORN AREASIAW SRM 57-10-00 FIG 37.

Part: SKIN — CRACKED (LT WING) · airframe 85,513 hrs · 34,458 cycles

POSSIBLE CRACK LT WING T DUCT CUT OUT UPPER INBD CORNER. PERFORMED HFEC TO VERIFY SUSPECTED CRACK. FOUND POSITIVE INDICATION IAW NTM 23-30-00 PART 6. INSTALLED DOUBLER AND FILLER AND EDGE SEALED IAW EA 8-5710-T0308710 P1 AND SRM 57-40-01 REPAIR 10 FIG.201 SHEET 2.

Part: SKIN — CRACKED (LT WING) · airframe 85,513 hrs · 34,458 cycles

LEFT WING REFUELING DOOR OTBD DOOR LAND CRACKED. PERFORMED HFEC TO VERIFY SUSPECTED CRACK. FOUND POSITIVE INDICATION IAW NTM 23-30-00 PART 6. FABRICATED NEW LOWER SECTION OF INNER RIB PER DRAWING ARB 1187. INSTALLED REPAIR PARTS IAW EA 8-5710-T0308715 PART 1 AND SRM 53-00-01 FIG 10.

Part: SKIN — CRACKED (LT WING) · airframe 85,513 hrs · 34,458 cycles

LEFT WING POSSIBLE SKIN CRACKED NR 10 TRACK CUT OUT LWR SURFACE. PERFORMED HFEC TO VERIFY SUSPECTED CRACK. FOUND POSITIVE INDICATION IAW NTM 23-30-00 PART 6. INSTALLED REPAIR DOUBLER AND FILLER IAW EA 8-5710-T0308676.

Part: PITOT LINE — CLOGGED (PITOT/STATIC SYS) · airframe 84,962 hrs · 34,152 cycles

NOTICED "IAS" DISPARITY SHOWN ON PFD. CAPTAIN`S AIRSPEED 204KTS, STANDBY AIRSPEED & FIRST OFFICER’S AIRSPEED WAS 224KTS. AP & AT KICKED OFF. RAN AIRSPEED LOST, SUSPECT OR ERRATIC FROM QRH. SEL ELEV FEEL MAN, SEL FLAP LIM OVRD LEVEL 2 ALERTS. FOUND CAPTAIN'S PITOT TUBE CLOGGED. REMOVED PITOT TUBE & BLEW OUT LINE IAW MD-10 MM 34-11-02-2. CHANGED CAPTAIN'S ADM AS A PRECAUTION IAW MD-10 MM 34-16-01-4. ADM NEEDS OPERATIONS CHECK & NEW PITOT TUBE NEEDS INSTALLED.

Part: CONTROL CABLE — FAILED (L1 DOOR) · airframe 84,925 hrs · 34,129 cycles

L1 DOOR OFF TRACK WHEN OPENED. R & R ALL L1 FWD PAX DOOR SEQUENCE CONTROL CABLES IAW MD10-10MM 52-11-12-2. PERFORMED ADJUSTMENT TEST IAW MD10-10MM 52-11-00-5. SERVICED L1 PASSENGER DOOR AIR RESERVOIR IAW MD10-10MM 52-11-07-2. DOOR OPERATIONS CHECKED NORMAL, ACFT OK FOR SERVICE.

Part: WIRE HARNESS — FAILED (ENGINE TEMP) · airframe 84,291 hrs · 33,796 cycles

ENROUTE AT FL 350, RECEIVED LEVEL 2, ENGINE 2 HIGH EGT. EGT PEAKED AT 994 DEGREES, FOLLOWED QRH AND RETARDED NR 2 THROTTLE. APROXIMATELY TWO MINUTES LATER NR 2 EGT SWUG UP TO 1098 DEGREES. SHUT ENGINE 2 DOWN. FUEL FLOW WAS STEADY AND EGT WAS AT 1098 APPROXIMATELY TWO MINUTES. PERFORMED GVI OF NR 2 ENGINE INLET AND EXHAUST AND NO DEFECTS NOTED. PERFORMED RESISTANCE CHECK OF UPPER LT/RT AND LOWER LT/RT EGT THERMOCOUPLE HARNESS SEGMENTS, FOUND ALL FOUR TO BE OUT OF LIMITS, REF AMM 77-21-01. R & R RT FWD LEAD, UPPER RT, AND LOWER RT THERMOCOUPLE HARNESS SEGMENTS, REF AMM 77-21-01. R & R LEAD AFT THERMOCOUPLE. R & R BOTTOM LEFT THERMOCOUPLE, R & R TOP LEFT THERMOCOUPLE, MM 77-21-01-2. PERFORMED ENGINE RUN PER JRH. OPS CHECKED NORMAL. ALL INDICATIONS WERE IN LIMITS, ACFT OK FOR SERVICE.

Part: DISPLAY — FAILED (COCKIT) · airframe 83,558 hrs · 33,416 cycles

CRUISE FLIGHT AT 340, NR 2 MCDU WENT BLANK. STRONG BURNING ELECTRIC ODOR APPARENT WITH SOME SMOKE IN AREA OF MCDU NR 2. PULLED CIRCUIT BREAKER AFTER LANDING. REMOVED NR 2 MCDU AND FOUND EVIDENCE OF INTERNAL ELECTRICAL FAILURE. NO OTHER DAMAGE FOUND TO AREA EXTERNAL OF MCDU OR CONNECTOR PLUGS. REPLACED NR 2 MCDU IAW 31-65-01-4. OPERATES NORMAL.

Part: SPAR CAP — CRACKED (ZONE 600) · airframe 83,471 hrs · 33,362 cycles

WHILE PERFORMING A HFEC INSPECTION OF RT WING REAR SPAR LWR CAP FOUND OTBD AFT HOLE CRACKED. REPAIR ACCOMPLISHED IAW EA 8-5710-163706. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 1521) · airframe 83,471 hrs · 33,362 cycles

CENTER CARGO COMPT FLOORBEAM COMPLETELY CORRODED THROUGH 2 ATTACH POINTS AS VIEWED FROM UNDER SURFACE STA 1521, LBL-3 TO RBL-3. REPAIRED CORRODED CENTER CARGO COMPT FLOORBEAM AT STA 1521, LBL-3 TO RBL-3 AS REQ IAW SRM 53-00-01, FIG 8, MAJOR REPAIR.

Part: FRAME — CRACKED (BS 1159) · airframe 83,471 hrs · 33,362 cycles

DURING THE INSPECTION OF EO 8-5100-7-5001, PT 2, FOUND FUSELAGE FRAME BS 1159 LT CRACKED ON THE LOWER INBD LEG. REPAIRED CRACKED FRAME IAW SRM 53-30-00, FIG 7, SHEETS 1-6, MAJOR REPAIR.

Part: BULKHEAD — CRACKED (NR 2 NACELLE) · airframe 83,471 hrs · 33,362 cycles

CRACKED BULKHEAD WEB AT NR 2 ENGINE INLET DUCT LT SIDE ACCESS THROUGHT PANEL 363EL. CRACKED BULKHEAD WEB REPAIRED IAW SRM 55-00-01, FIG 9, VOL I, CLASSIFED AS MAJOR.

Part: SKIN — GOUGED (BS 959) · airframe 83,471 hrs · 33,362 cycles

SKIN AT BS 959 ON L40 TO 41R, FOUND THE FORWARD EDGE TO BE GOUGED. REWORKED GOUGED AREA IAW SRM 53-5000, FIG 26. FOUND TO BE OUT OF LIMITS IAW SRM 53-50-00 FIG 26. FABRICATED DOUBLERS, & FILLER IAW SRM 53-50-00, FIG 26. INSTALLED DOUBLERS AND FILLER IAW SRM 53-50-00, FIG 26. MAJOR REPAIR.

Part: BATTERY — FAILED (EMERGENCY LIGHTS) · airframe 83,374 hrs · 33,301 cycles

EMERGENCY LIGHT TEST FAILED, OPS CHECK SHOWS LOW BATTERY. R & R EMERGENCY LIGHT BATTERY POWER SUPPLY IAW MM REF 33-51-01-4. OPS CHECKED GOOD, ACFT OK FOR CONTINUE SERVICE.

Part: O-RING — FAILED (HYD SYSTEM) · airframe 83,231 hrs · 33,213 cycles

HYDRAULIC SYSTEM 1 LOST QUANTITY INITIALLY 0 BUT AFTER LANDING RECOVERED TO 2.2 GAL. ACFT STILL HAD 3.7 GAL OF HYDRAULIC FLUID IN NR 1 SYS. TROUBLESHOOTING FOUND NR 1 SYS BRAKE ACCUMILATOR HAS A BLOWN O-RING. REPLACED O-RING IAW SMP, SERVICED ACCUMILATOR IAW MM 32-12-01-3, LEAK CHECKED GOOD. RAN NR 1 ENGINE IAW JRH. NO AIR IN SYS FOUND. OK FOR SERVICE.

Part: WIRE — CHAFED (FIRE DETECTOR) · airframe 83,082 hrs · 33,130 cycles

PRIOR TAKEOFF, RECEIVED NR 2 ENG FIRE ALERT, QRH COMPLIED WITH, FIRE TEST SATISFACTORY AFTER NR 1 BOTTLE FIRED, NO FIRE INDICATION, FIRE DEPT REPORTED NO HEAT SIGNATURE/FIRE IN AREA OF NR 2 ENG. FIRE INDICATION REAPPEARED AFTER A FEW MINUTES. NO FIRE PRESENT. FOUND WIRE SDW108A18 WAS CHAFING TO BONDING WIRE INSIDE AFT JUNCTION BOX. REPAIRED WIRE IAW SWPM 20-10-03. NR 2 ENG FIRE DETECTION SYS OPS CHECK NORMAL IAW 26-10-00-5. FINAL CLOSED.

Part: ANTI-SKID SYS — FAILED (MLG) · airframe 82,196 hrs · 32,640 cycles

ON APPROACH, FLAPS 35 FULLY CONFIGURED, GOT LEVEL 2 ANTI SKID FAIL ALERT. NORMAL GO AROUND RAN QRH. SECOND APPROACH DID FLAPS 50. ALERT DID NOT RETURN. R & R THE ASCU IAW AMM 32-45-01-4. PERFORMED ASCU RTS. OPS CK GOOD. NO DEFECTS NOTED. FINAL CLOSED.

Part: PRESSURE SWITCH — INOPERATIVE (L1 DOOR SLIDE) · airframe 82,078 hrs · 32,577 cycles

L1 DOOR EVACUATION SLIDE REMOTE PRESSURE PRESS TO TEST LIGHT SWITCH INOP. RELAMPED L1 LIGHT CAPSULE IAW CH 33 SMP'S. L1 DOOR EVACUATION REMOTE PRESSURE PRESS TO TEST LIGHT SWITCH NOW TEST PROPERLY. OK FOR SERVICE.

Part: SENSOR — MALFUNCTIONED (BLEED AIR SYS) · airframe 81,974 hrs · 32,521 cycles

ON CLIMBOUT LEVEL ONE "AIR SYS 2 OFF" CAME ON. 30 SECONDS LATER LEVEL 3 "AIR MANF 2 FAIL" CAME ON. STAYED ON FOR 10 SECONDS WENT OUT THEN CAME ON AGAIN FOR 15 SECONDS. COMPLIED WITH QRH RETURNED TO DEPARTURE AND LANDED WITHOUT INCIDENT. R & R NR 2 MANIFOLD SENSING ELEMENT D1-49, LOCATED IN AFT CARGO COMPARTMENT BEHIND LT SIDEWALL NEAR CEILING, AIR SYS TEST PASSES NORMALLY, HOOKED UP MANIFOLD FAIL TEST BOX INLINE WITH MANIFOLD DETECT CONTROLLER AND ALL TESTS PASS, SYS RETURNED TO NORMAL CONFIGURATION, SYS NOW OPERATES NORMALLY, REF AMM 36-23-01, AMM 36-23-02.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 81,146 hrs · 32,092 cycles

R1 DOOR AFT EMERGENCY LIGHT INOPERATIVE. RELAMPED IAW AMM 33-52-04-2-0. ALL OPS CHECKS NORMAL.

Part: TEE FITTING — CRACKED (BS 595) · airframe 80,965 hrs · 31,991 cycles

PRESSURE BULKHEAD BS 595, FOUND RT TEE CAP, FWD HORIZONTAL LEG CRACKED AT STA X=58.000 APPROXIMATE LENGTH OF CRACK IS APPROX 2.5" LONG. ALSO FOUND CRACK ON INTERNAL DOUBLER BETWEEN TEE CAP AND OUTER SKIN. LENGTH OF CRACK IS APPROX 2" LONG. INSTALLED REPAIRS TO A/C FUSELAGE SKIN IAW EA 8-5310-142555 AND INSTALLED REPAIRS TO TEE CAP AT STATION 595, IAW E.A. 5310-142555

Part: SENSOR — MALFUNCTIONED (CABIN) · airframe 80,509 hrs · 31,758 cycles

AFTER LANDING RECEIVED CABIN SMOKE ALERT. NO SMOKE OR FUMES SEEN. EVACUATED THE ACFT AFTER BLOWING L1 SLIDE. AFTER APPLYING ELECTRICAL POWER THERE WAS NO CABIN SMOKE INDICATION ON OVERHEAD SMOKE DETECTION PANEL. ACCESSED VIA AND AIU NO FAULTS IN CURRENT FAULTS OR FAULT REVIEW. TESTED ALL FIRE SYS, SYS CK GOOD. SMOKE DETECTION FAULT NEVER RETURNED. HUB CHECK CANS DURING OFF LOAD NOTHING ABNORMAL FOUND. RAN AIR SYS TEST, TEST PASSED. MSC RTS GOOD. R & R MSC IAW MM 31-42-01-4 AND ADJUSTMENT TEST 31-42-01-5. OPS CHECK NORMAL. ALSO R & R NR 3 ACU IAW MM. OPS CHECK NORMAL.

Part: CLAMP — FAILED (THRUST REVERSER) · airframe 78,252 hrs · 30,674 cycles

AFTER TAKEOFF AT 500 FT, FELT A LOUD "THUMP" LIKE A BIRDSTRIKE. THIS WAS FOLLOWED BY AN INDICATION OF NR 3 BLEED CLOSED (VALVE WAS SELECTED OPEN). THIS WAS FOLLOWED BY A "REV 3 PRESS FAULT". T/R WAS 'NOT' UNLOCKED. ALL OTHER ENGINE INDICATIONS WERE NORMAL. THRUST REVERSER OPERATED NORMALLY ON LANDING. REV 3 PRESS FAULT REMAINED AFTER T/R WAS STOWED. WHILE PARKING ACFT, NOTICED BLOWOUT DOOR ON THE BOTTOM OF THE NR 3 ENGINE OPEN. FOUND BAND CLAMP FAILED BETWEEN PRESSURE REGULATOR VALVE AND HSV. NR 3 LT THRUST REVERSER DAMAGED BY PRESSURE REGULATOR VALVE. NEEDS THRUST REVERSER, HSV, PRV, DUCTS AND SENSE LINES. REMOVED AND REPLACED NR 3 ENG. HP BLEED CONTROL VALVE PER MM 36-11-02-4, AND REG PNEU PRESS VALVE PER MM 36-12-01-4.BOTH VALVE NEEDS OPS CHECK AND RTS CHECK. REMOVED AND REPLACED PWR PLANT BLEED DUCT,WING PYLON PNEU DUCT ,AND ACF COR WIRE HARNESS.DUCTS NEEDS LEAK CHECK.

Part: SKIN — DENTED (ZONE 200) · airframe 77,899 hrs · 30,510 cycles

RIGHT FUSELAGE EXTERIOR SKIN ID DENTED AT BS 499 LONGERON 14R. BLENDED GOUGES; OUT OF LIMITS IAW SRM 53-32-01. NO CRACKS NOTED PER NTSPM 06-10-01.001. FABRICATED DOUBLER IAW SRM 53-20-00. ALODINED & PRIMED OUTSIDE SKIN IAW SRM 51-21-01. PRIMED DOUBLER IAW SRM 51-21-01. INSTALLED DOUBLER IAW SRM 53-20-00. COMPLIED WITH E.A. 8-5330-123633.

Part: FAIRING — DAMAGED (LT WING TE FLAP) · airframe 77,883 hrs · 30,502 cycles

LEFT WING OUTBD FLAP INBD HINGE LOWER BULLET ASSY LOWER SURFACE IS DENTED. REPAIRED LEFT WING OUTBD FLAP HINGE LOWER BULLET ASSY IAW EA 8-5750-123660.

Part: SPLICE — CORRODED (ZONE 600) · corrosion level 2 · airframe 77,883 hrs · 30,502 cycles

RIGHT WING INBD T/E AT THE MAIN LANDING SUPPORT LOWER FWD AUX SPLICE HAS CORROSION. REPLACED 2 SPLICES P/N ARC 0634-2 & P/N ARB 0636-1 IAW DWG ARC 0621.

Part: CHANNEL — CRACKED (LT WING) · airframe 77,883 hrs · 30,502 cycles

LEFT WING UPPER L/E PANEL 517 CT HAS A CRACKED CHANNEL. REMOVED CRACKED CHANNEL IAW DC/MD-10 SRM 51-35-01; VOL II. MATERIAL ID 7075-0, 0.063; PO 629531.1 & FABRICATED IAW DAC DWG ARB 2407; REV G. ALODINED & PRIMED IAW DC/MD-10 SRM 51-21-01; VOL II; PG 21 - 24. INSTALLED IAW DC/MD-10 SRM 51-35-01 VOL II.

Part: PANEL — DELAMINATED (LT WING) · airframe 77,883 hrs · 30,502 cycles

LEFT WING LOWER T/E PANEL NR 541 HB DELAMINATED AROUND EDGE. REPAIRED BY REMOVING; FABRICATING & BONDING A NEW OUTER SKIN, INNER DOUBLER, HONEYCOMB CORE AND INNER SKIN IAW E.A. 8-5720-123638 AND TPS 1001; REV " E ". PRIMED; SEALED & PAINTED PANEL IAW E.A. 8-5720-123638 & SRM 51-21-02.

Part: SPAR — CORRODED (RT WING) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING INBD T/E AT THE MAIN LANDING GEAR SUPPORT, LOWER FWD AUX SPAR SPLICE HAS CORROSION. REPLACED SPLICES IAW DWG ARB 0621 AT THE RIGHT WING INBD TRAILING EDGE AT THE MLG LOWER FWD & AFT SPAR SPLICES.

Part: FAIRING — CRACKED (ZONE 400) · airframe 77,883 hrs · 30,502 cycles

NR 2 ENGINE PYLON LEFT SIDE APRON AT THE RAMP FAIRING IS CRACKED APPROX 10 INCHES. THIS SDR WAS GENERATED TO CORRECT BLOCK 7 ON SDR TRACKING NR 08-3899.

Part: RIB — CHAFED (NR 3 PYLON) · airframe 77,883 hrs · 30,502 cycles

NR 3 PYLON PANEL 489 AL FWD RIB IS CHAFED. REMOVED & REPLACED RIB IAW DWG AUB 7107 & SRM 51-35-01.

Part: RIB — CHAFED (ZONE 400) · airframe 77,883 hrs · 30,502 cycles

NR 1 PYLON PANEL 439 AL FWD RIB IS CHAFED THROUGH. REMOVED RIB IAW ARM 51-35-01; VOL II. LOCATED AND DRILLED THE NEW RIB P/N AUB 7107-39, PO 631193.2 IAW DWG AUB 7107; REV "P". INSTALLED NEW RIB IAW SRM 51-35-01; VOL II.

Part: SKIN — DENTED (ZONE 100) · airframe 77,883 hrs · 30,502 cycles

THE EXTERIOR SKIN HAS 2 SCRATCHES 0.750 LONG AND A DENT THAT IS 0.020 LONG AND 0.100 DEEP LOCATED 52 INCHES AFT OF THE LOWER FWD CARGO DOOR AND APPROX 36 INCHES ABOVE THE WHITE LINE. SEQUENCE NR 000830, WRI NR 53105938. REPAIRED THE DAMAGED AREA IAW DC/MD-10 SRM 53-20-00, FIG 6, SHEET 3, VOL I.

Part: WEDGE — CRACKED (LT TE FLAP) · airframe 77,883 hrs · 30,502 cycles

LEFT INBD FLAP, INBD TRAILING EDGE IS CRACKED. REMOVED TRAILING EDGE SECTION IAW SRM 51-35-02. FABRICATED IAW SRM 57-20-00. ALODINED & PRIMED IAW SRM 51-21-01. INSTALLED IAW SRM 51-35-02.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 77,883 hrs · 30,502 cycles

LEFT HORIZONTAL STAB UPPER SKIN AND APPROX XE 72, STRINGER NR 6 IS CRACKED. REPAIRED SKIN PER EA 8-5510-123649.

Part: SKIN — CRACKED (LT ELEVATOR) · airframe 77,883 hrs · 30,502 cycles

LEFT STAB DROOP ELEVATOR LOWER SURFACE IS CRACKED. CHECKED THE LIMITS ON THE DENT. DEEPEST POINT 0.065 IAW DEPTH GAUGE T8492C DUE 10-25-08 AND FOUND TO BE OUT OF LIMITS IAW DC/MD-10 SRM 51-80-01; VOL II; NOTE K. CUT OUT DAMAGE IAW DC/MD-10 SRM 55-10-00; VOL I. MATERIAL ID FOR THE REPAIR DOUBLER 2024-T3, 0.040 IAW DC/MD-10 SRM 55-10-00; VOL I. FABRICATED THE REPAIR DOUBLER IAW DC/MD-10 SRM 55-10-00; VOL I. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01; VOL II. INSTALLED THE REPAIR DOUBLER IAW DC/MD-10 SRM 55-10-00; VOL I.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 77,883 hrs · 30,502 cycles

MAIN CABIN SEAT TRACK AT STA 1385; LBL 75 IS WORN. REMOVED DAMAGED AREA IAW SRM 51-31-01; VOL II. MATERIAL ID FOR THE NEW TRACK S4929405 IAW SRM 53-42-01; VOL III. FABRICATED A NEW SEAT TRACK CHANNEL AND PLATE IAW SRM 53-70-00; VOL I. ALODINED, PRIMED AND PAINTED IAW SRM 51-21-02; VOL II. INSTALLED THE NEW SEAT TRACK IAW SRM 51-31-02; VOL II.

Part: PANEL — WORN (ZONE 500) · airframe 77,883 hrs · 30,502 cycles

LEFT WING OUTBD L/E PANEL 527 AB IS WORN AT THE LATCH. FABBED DOUBLER REF SRM 57-00-01; VOL I. BLENDED WORN AREA AND FOUND OUT OF LIMITS REF SRM 57-00-01; VOL I. ALODINED AND PRIMED REF SRM 51-21-01, VOL II. INSTALLED DOUBLER REF SRM 51-35-01; VOL II.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 77,883 hrs · 30,502 cycles

LEFT HORIZONTAL STAB UPPER SKIN AT APPROX XE 72, STRINGER NR 11 IS CRACKED. REPAIRED SKIN PER EA 8-5510-123649.

Part: PANEL — CHAFED (ZONE 600) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING LOWER L/E PANEL 616 HB IS CHAFED. BLENDED AREA IAW SRM 57-00-01; VOL I; FIG 1-A. ORIGINAL MATERIAL THICKNESS 0.090 IAW SRM 57-31-01; VOL III. MATERIAL LOSS 0.022. REMAINING THICKNESS 0.068 AND FOUND OUT OF LIMITS IAW SRM 57-00-01; VOL I. CUT OUT THE DAMAGE IAW SRM 57-00-01; VOL I. FABRICATED THE FILLER AND DOUBLER IAW SRM 57-00-01; VOL I AND SRM 57-31-01; VOL III. ALODINED AND PRIMED IAW SRM 51-21-01; VOL II; PGS 21 - 24.

Part: FAIRING — CRACKED (ZONE 400) · airframe 77,883 hrs · 30,502 cycles

NR 2 ENGINE PYLON LEFT SIDE APRON AT THE RAMP FAIRING IS CRACKED APPROXIMATELY 10 INCH. REMOVED APPRON IAW SRM 51-31-01. FORMED NEW APPRON IAW SRM 51-10-00 & AMM 7-0-1-104. ALODINED & PRIMED IAW SRM 51-21-01. INSTALLED APPRON IAW SRM 51-31-01.

Part: HEAT SHIELD — WORN (ZONE 400) · airframe 77,883 hrs · 30,502 cycles

NR 2 ENGINE LEFT FAN COWL LOWER FWD INSIDE CORNER CHAFFING PLATE IS WORN AND TORN. REMOVED LOWER FWD HEAT SHIELD. FABRICATED REPAIR FOR HEAT SHIELD AND INSTALLED DC/MD-10 DAC DWG ATL OO55 AND SRM 51-31-01; VOL II.

Part: SKIN — WORN (ZONE 500) · airframe 77,883 hrs · 30,502 cycles

LEFT WING INBD LOWER TE PANEL 545 BB IS WORN. PANEL FOUND TO BE OUT OF LIMITS IAW SRM 57-00-01. FABRICATED IAW DWG ARC 1283. HEAT TREATED IAW TPS 1003. ALODINED & PRIMED IAW SRM 51-21-01. PAINTED IAW SRM 51-21-02. PART MARKED IAW GMM 7-0-1001.

Part: SKIN — DENTED (RT ELEVATOR) · airframe 77,883 hrs · 30,502 cycles

RIGHT STABILIZER INBD ELEVATOR UPPER SKIN IS DENTED. CHECKED LIMITS ON THE DENT DEEPEST POINT 0.095 WITH DEPTH GAUGE T8492C DUE 10/25/08. FOUND TO BE OUT OF LIMITS IAW SRM 51-80-01; VOL II; PG 2; NOTE "K". CUT OUT DAMAGE IAW SRM 55-10-00; VOL I; FIG 8. ALODINED AND PRIMED IAW SRM 51-21-01; VOL II. INSTALLED REPAIR DOUBLER IAW SRM 55-10-00; VOL I; FIG 8. PAINTED IAW SRM 51-21-01; VOL II.

Part: PANEL — CHAFED (ZONE 400) · airframe 77,883 hrs · 30,502 cycles

NR 3 PYLON PANEL 487 HR IS CHAFED AND HAS BARE METAL. BLENDED AREA IAW SRM 54-00-01; VOL I. ORIGINAL MATERIAL THICKNESS, 0.071 IAW SRM 54-51-01; VOL III. MATERIAL LOSS 0.020. REMAINING THICKNESS 0.051. FOUND TO BE OUT OF LIMITS IAW SRM 54-00-01;VOL I. FABRICATED PANEL IAW DWG AUB 7108; REV "A" ALODINED AND PRIMED IAW SRM 51-21-01; VOL II. PAINTED IAW SRM 51-21-01; VOL II. MARKED PANEL IAW GMM 7-0-1001.

Part: PANEL — CHAFED (NR 1 PYLON) · airframe 77,883 hrs · 30,502 cycles

NR 1 PYLON PANEL 738 GL IS CHAFED AT THE MATING SURFACE. FABBED REPAIR PARTS IAW EA 8-5480-123637 & SRM 54-00-01. ALODINED & PRIMED FILLERS IAW SRM 51-21-01. INSTALLED REPAIR PARTS PER EA 8-5480-123637 & SRM 54-00-01.

Part: STRINGER — GOUGED (ZONE 600) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING OUTER FUEL TANK UPPER STRINGER 3 - 4 AT XORS 965 (639 BB ACCESS OPENING) HAS A GOUGED EDGE. TRIMMED THE EDGE OF THE STRINGER. ORIGINAL THICKNESS OF THE LEG IS 1.080. MATERIAL REMOVED 0.020. REMAINING WIDTH OF THE LEG IA 1.060 AND FOUND TO BE WITHIN LIMITS IAW DC/MD-10 SRM 57-00-01, FIG 1-A,VOL II. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01, VOL II.

Part: TIE ROD — BROKEN (ZONE 100) · airframe 77,883 hrs · 30,502 cycles

CENTER PIT CARGO SYSTEM HAS 2 BROKEN TIE ROD SUPPORTS AT STA 1765, (P/N AWJ 7322-1). REMOVED AND REPLACED P/N AWJ 7322-1 (2) IAW SRM 51-31-01; VOL II.

Part: RETAINER — CRACKED (TE FLAP FAIRING) · airframe 77,883 hrs · 30,502 cycles

LEFT WING OUTBD FLAP INBD FAIRING OUTBD SIDE PANEL 535 DL HAS A CRACK SEAL RETAINER. REMOVED SEAL RETAINER IAW SRM 51-31-01. FORMED A NEW SEAL RETAINER IAW SRM 51-10-00. ALODINED & PRIMED THE SEAL RETAINER IAW SRM 51-31-01. DRILLED UP THE NEW SEAL RETAINER & INSTALLED IAW SRM 51-31-01.

Part: BRACKET — WORN (ZONE 600) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING UPPER FUEL TANK AT ACCESS OPENING 634 AT HAS A MOUNT BRACKET (A/C SIDE) WITH ELONGATED HOLES AT THE FUEL CHECK FLAPPER VALVE, WING STA XORS 402, AFT AND INBD OF THE OPENING. REMOVED THE HINGE ASSEMBLY. FABRICATED A NEW HINGE ASSEMBLY AND INSTALLED THE NEW HINGE ASSEMBLY IAW DWG ARB 2369; REV "C" AND SRM 51-33-01; VOL II. ALODINED AND PRIMED IAW SRM 51-21-01, VOL II. PART MARKED HINGE ASSEMBLY IAW GMM 7-0-1001.

Part: ATTACH BRACKET — CRACKED (ZONE 500) · airframe 77,883 hrs · 30,502 cycles

LEFT WING FUEL TANK FWD FUEL LINE CLAMP ATTACH BRACKET IS CRACKED AT XORS 714; ACCESS OPENING 536 BB. REMOVED & INSTALLED INTERCOSTAL IN REF TO SRM 51-31-01 VOL II. FABRICATED INTERCOSTAL P/N ARL 0500-7 IN REF TO DWG ARL 0500; REV "BU". ALODINED IN REF TO SRM 51-21-01 VOL II. PART MARKED IX ARL 0500-7 IN REF TO GMM 7-0-1000.

Part: DOUBLER — CRACKED (LT WING) · airframe 77,883 hrs · 30,502 cycles

LT WING NR 2 TANK INBD COMP PROBE PANEL LAND HAS A CRACK AT THE ATTACH BOLT HOLE. REMOVED & REPLACED NR 8 STRINGER IN REF TO EA 8-5720-117035 LEAK CHECK COMPLIED WITH ON NON-ROUTINE N00534 / 41534.

Part: ATTACH BRACKET — CRACKED (ZONE 600) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING OUTBD FUEL TANK OPENING 634 BT, FWD MOST FUEL LINE HAS A CRACKED CLAMP ATTACH BRACKET. XORS 480 OUTBD AND FWD OF THE OPENING. REMOVED THE BRACKET. FABRICATED A NEW BRACKET AND INSTALLED THE NEW BRACKET IAW DAC DWG ARL 0501; REV "AU" AND DC/MD-10 SRM 51-31-01; VOL II. ALODINED IAW DC/MD-10 SRM 51-21-01; VOL II. PART MARKED IAW FEDEX GMM 7-0-1001.

Part: LINE — CRACKED (ZONE 600) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING OUTBD FUEL TANK OPENING 635 AT, FWD MOST FUEL LINE HAS A CRACKED, CLAMP ATTACH BRACKET. XORS 593 OUTBD AND FWD OF THE OPENING. REMOVED THE BRACKET. FABRICATED A NEW BRACKET AND INSTALLED THE NEW BRACKET IAW DWG ARL 0500, REV "BM" AND SRM 51-31-01, VOL II. ALODINED IAW SRM 51-21-01; VOL II. PART MARKED IAW GMM 7-0-1001.

Part: ATTACH BRACKET — CRACKED (ZONE 500) · airframe 77,883 hrs · 30,502 cycles

LEFT WING FUEL TANK FUEL LINE ATTACH BRACKET IS CRACKED AT XORS 538; ACCESS OPENING 534 CT. REMOVED & INSTALLED INTERCOSTAL IN REF TO SRM 51-31-01; VOL II. FABRICATED INTERCOSTAL IN REF TO DWG ARL 0501 REV "BU". ALODINED IN REF TO SRM 51-21-01 VOL II. PART MARKED IN REF TO GMM 7-0-1000.

Part: CHANNEL — CRACKED (ZONE 600) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING OUTBD UPPER FUEL TANK ACCESS OPENING 634 CT HAS FUEL LINE CLAMP ATTACH BRACKET IS CRACKED XORS 538; FWD AND OUTBD OF ACCESS OPENING. REMOVED & INSTALLED THE INTERCOSTAL IN REF TO SRM 51-31-01; VOL II. FABRICATED INTERCOSTAL P/N ARL 0501-44 IN REF TO DWG ARL 0501; REV "AY". ALODINED IN REF TO SRM 51-21-01; VOL II. PART MARKED ARL 0501-44 IN REF TO GMM 7-0-1000.

Part: ATTACH BRACKET — CRACKED (ZONE 500) · airframe 77,883 hrs · 30,502 cycles

LEFT WING FUEL TANK FWD MOST FUEL LINE CLAMP ATTACH BEACKET IS CRACKED AT XORS 683; ACCESS 536 AB. REMOVED & INSTALLED THE INTERCOSTAL IN REF TO SRM 51-31-01; VOL II. FABRICATED INTERCOSTAL P/N ARL 0500-21IN REF TO DWG ARL 0500, REV "BU". ALODINED IN REF TO SRM 51-21-01; VOL II. PART MARKED IAW GMM 7-0-1000.

Part: ATTACH BRACKET — CRACKED (ZONE 600) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING UPPER FUEL TANK OPENING 634 BT, AT XORS 455 HAS A FUEL LINE CLAMP ATTACH BRACKET CRACKED INBD AND FWD OF THE OPENING. REMOVED THE BRACKET. FABRICATED A NEW BRACKET AND INSTALLED THE NEW BRACKET IAW DWG ARL 0501; REV "AU" AND SRM 51-31-01; VOL II. ALODINED IAW SRM 51-21-01;VOL II. PART MARKED IAW GMM 7-0-1001.

Part: HINGE — WORN (FUEL DOOR) · airframe 77,883 hrs · 30,502 cycles

LEFT WING FUEL TANK FUEL FLAPPER VALVE AT XORS 402; 534 AT ACCESS OPENING; HAD ELONGATED MOUNT HOLES (A/C SIDE) AT THE ATTACH BRACKET. REMOVED THE FLAPPER DOOR AND HINGE ASSEMBLY IAW SRM 51-31-01, VOL II. FABRICATED A NEW HINGE ASSEMBLY AND INSTALLED THE NEW HINGE ASSEMBLY IAW DWG ARB 2369; REV "C" AND SRM 51-33-01;VOL II. ALODINED AND PRIMED IAW SRM 51-21-01; VOL II. RE-INSTALLED THE FLAPPER DOOR IAW SRM 51-31-01; VOL II. PART MARKED HINGE ASSEMBLY IAW GMM 7-0-1001.

Part: DOUBLER — CRACKED (RT WING) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING COMP PROBE PANEL LAND IS CRACKED; NR 2 TANK. REMOVED & REPLACED NR 8 STRINGER IN REF TO EA 8-5720-117035. LEAK CHECK COMPLIED WITH ON NON-ROUTINE N00533 / 41533.

Part: ATTACH BRACKET — CRACKED (ZONE 500) · airframe 77,883 hrs · 30,502 cycles

LEFT WING FUEL TANK FWD FUEL LINE CLAMP ATTACH BRACKET IS CRACKED AT XORS 738; ACCESS OPENING 536 CB. REMOVED & INSTALLED INTERCOSTAL IN REF TO SRM 51-31-01; VOL II. FABRICATED INTERCOSTAL P/N ARL 0500-7 IN REF TO DWG ARL 0500; REV "BU". ALODINED IN REF TO SRM 51-21-01; VOL II. PART MARKED IN REF TO GMM 7-0-1000.

Part: ATTACH BRACKET — CRACKED (ZONE 500) · airframe 77,883 hrs · 30,502 cycles

LEFT WING FUEL TANK UPPER ACCESS 534 BT FWD MOST FUEL LINE CLAMP ATTACH BRACKET IS CRACKED AT XORS 455. REMOVED THE BRACKET. FABRICATED A NEW BRACKET AND INSTALLED THE NEW BRACKET IAW DAC DWG ARL 0501; REV "AU" AND DC/MD-10 SRM 51-31-01; VOL II. ALODINED IAW DC/MD-10 SRM 51-21-01; VOL II. PART MARKED IAW FEDEX GMM 7-0-1001.

Part: ATTACH BRACKET — WORN (ZONE 500) · airframe 77,883 hrs · 30,502 cycles

LEFT WING UPPER FUEL TANK ACCESS 533 AT, FUEL LINE ATTACH BRACKET WORN AND LOOSE AFT AND OUTBD OF THE OPENING AT THE RIB (XORS 316.9). REMOVED BRACKET ASSEMBLY -41 AND -37. FABRICATED A NEW BRACKET ASSEMBLY -41 AND -37. INSTALLED THE NEW BRACKET ASSEMBLIES -41 AND -37 IAW DAC DWG ARL 0531, REV "AA" AND DC/MD-10 SRM 51-31-01; VOL II. ALODINED IAW DC/MD-10 SRM 51-21-01, VOL II. PART MARKED IAW FEDEX GMM 7-0-1001.

Part: ATTACH BRACKET — CRACKED (ZONE 500) · airframe 77,883 hrs · 30,502 cycles

LEFT WING OUTBD FUEL TANK FUEL LINE CLAMP ATTACH BRACKET IS CRACKED AT XORS 653; FWD & OUTBD OF ACCESS OPENING 535 BT. REMOVED & INSTALLED INTERCOSTAL IN REF TO SRM 51-31-01; VOL II. FABRICATED INTERCOSTAL P/N ARL 0500-29 IN REF TO DAC DWG ARL 0500; REV "BU". ALODINED IN REF TO SRM 51-21-01; VOL II. PART MARKED IN REF TO GMM 7-0-1000.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 77,883 hrs · 30,502 cycles

LEFT HORIZONTAL STAB SKIN PANEL AFT SECTION (UPPER) SHOWS A CRACK INDICATION BETWEEN THE 2 BLACK DOTS APPROX 0.430 LONG AND 0.875 OFF THE AFT EDGE OF THE SKIN PANEL. REPAIRED SKIN PANEL PER EA 8-5510-123505.

Part: SKIN — CRACKED (RT WING) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING L/E SKIN IS CRACKED AT THE NR 3 SLAT CENTER TRACK CUT-OUT. REMOVED 2 EA PANELS TO FOM IAW SRM 51-31-01. REMOVED OLD REPAIR DOUBLER IAW SRM 51-35-02. CUT PUT DAMAGED AREAS. FABRICATED IAW SRM 57-10-00. ALODINED & PRIMED IAW SRM 51-21-01. INSTALLED DOUBLER, FILLER & ACCESS PANELS IAW SRM 51-33-01 & 51-31-01.

Part: FRAME — CRACKED (ZONE 100) · airframe 77,883 hrs · 30,502 cycles

THE SUB-FRAME AT STA 755 HAS A CRACK BELOW THE MCD AT LONGERON 29L. MATERIAL ID FOR DOUBLER 7075-T6511, PO 568806.2; SHIM 7075-T6 0.100, PO 584757.3 AND THE FILLER 7075-T6 0.071 PO 629996.2 IAW DAC DWG NR ACA 7230 AND DC/MD-10 SRM 51-10-01; VOL III. REMOVED DAMAGED AREA AND FABRICATED AND LOCATED HOLES IAW DC/MD-10 SRM 53-00-01;VOL I. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01; VOL II. INSTALLED DOUBLER, SHIM AND FILLER IAW DC/MD-10 SRM 51-33-01; VOL II.

Part: ANGLE — CRACKED (BS 1505) · airframe 77,883 hrs · 30,502 cycles

RIGHT MLG WHEEL WELL STA 1505; AFT SHELF AREA, FWD WEB, LOWER ANGLE IS CRACKED. REMOVED & RE-INSTALLED PANEL 144 AZ IAW SRM 51-31-01; VOL II. REMOVED CRACKED ANGLE IAW SRM 51-31-01. HEAT TREATED 7075-0 TO T6 IAW TPS 1003; REV " A ". HRD 88-89, NT09210801. AODINED; PRIMED & PAINTED ANGLE IAW SRM 51-21-01. MARKED IAW FEDEX GMM 7-0-1001.

Part: SKIN — CRACKED (RT WING) · airframe 77,883 hrs · 30,502 cycles

A CRACK IS PROPAGATING FROM UNDER THE REPAIR DOUBLER AT THE RIGHT WING L/E SLAT DRIVE MECHANISM INBD CORNER. WORK WAS ACCOMPLISHED ON NON-ROUTINE N00802.

Part: FITTING — CRACKED (ZONE 100) · airframe 77,883 hrs · 30,502 cycles

NR 6 SPOOL BACK UP FITTING HOLE "B" HAS A CRACK INDICATION. INSTALLED BUSHINGS IN THE NR 6 BACK UP FITTING HOLE "B" AND REAMED UP TO SIZE (.453) IAW SRM 53-50-00; VOL II.

Part: ANGLE — WORN (LT WING) · airframe 77,883 hrs · 30,502 cycles

LT WING LOWER T/E PANEL MATING SURFACE IS WORN OUT BY THE OUTBOARD FLAP; INBOARD HINGE FITTING. REMOVED ANGLE & ATTACH ANGLE IAW SRM 51-31-01 VOL II. FABRICATED A NEW ANGLE IAW DWG ARG 0744; REV "J ". ALODINED IAW SRM 51-21-01 VOL II. PRIMED IAW SRM 51-21-01; VOL II. TOP COATED IAW SRM 51-21-01 VOL II. INSTALLED ANGLE IAW SRM 51-21-01 VOL II. INSTALLED PANEL IAW SRM 51-31-01 VOL II.

Part: FITTING — CRACKED (ZONE 100) · airframe 77,883 hrs · 30,502 cycles

NR 2 SPOOL BACK UP FITTING HOLES C & D HAVE CRACK INDICATIONS IN THE BACK UP FITTING. REQUIRES REMOVAL. REMOVED & REPLACED BACK UP FITTING NR 2 IAW SRM 51-33-01 VOL II.

Part: CAP — WORN (LT WING) · airframe 77,883 hrs · 30,502 cycles

LEFT WING LOWER T/E STRUCTURE IS WORN APPROXIMATELY 48" INBD OF THE OUTBD AILERON ACTUATOR. UPON FURTHER INVESTIGATIONDAC DWG ARC 0824; REV "H" ALLOWS THE TRIMMING OF THE FLANGE IN THE WORN ARE. TRIMMED AREA FLANGE IAW DWG ARC 0724; REV "H"; E.O. SHEET 2. ALODINED, PRIMED, & PAINTED AREA IAW DC/MD-10 SRM 51-21-01; VOL II.

Part: BRACKET — CRACKED (BS 1361) · airframe 77,883 hrs · 30,502 cycles

THERE IS A CRACKED BRACKET AT STA 1361 BETWEEN LONGERONS 31L & 32L. REMOVED ANGLE IAW SRM 51-31-01 VOL II. HEAT TREATED IAW TPS 1003; REV " A ". ALODINED & PRIMED IAW SRM 51-21-01 PGS 21 & 24 VOL II. INSTALLED IAW SRM 51-31-01; VOL II.

Part: PANEL — CRACKED (NR 1 PYLON) · airframe 77,883 hrs · 30,502 cycles

NR 1 PYLON PANEL 438 CL IS CRACKED. FABBED A REPAIR DOUBLER & INSTALLED DOUBLER REF SRM 54-00-01 VOL I.

Part: BRACKET — CRACKED (BS 1341) · airframe 77,883 hrs · 30,502 cycles

THERE IS A CRACKED BRACKET AT THE LEFT OVERWING TO BODY FAIRING PANEL SUPPORT AT STA 1341; BELOW LONGERON 31L. REMOVED ANGLE IAW SRM 51-31-01 VOL II. HEAT TREATED IAW TPS 1003; REV " A ". ALODINED & PRIMED IAW SRM 51-21-01 PGS 21 & 24 VOL II. INSTALLED IAW SRM 51-31-01 VOL II.

Part: WEB — PUNCTURED (BS 1473) · airframe 77,883 hrs · 30,502 cycles

THERE ARE PUNCTURES (2 PLACES) ON THE FAIRING SUPPORT WEB AFT OF THE RT MLG STRUT CUTOUT AT STA 1473. REMOVED WEB & ANGLE IN REF TO SRM 51-35-01 VOL II. FABRICATED ANGLE IN REF TO DWG ANB 7203; REV " BA ". ALODINED & PRIMED IN REF TO SRM 51-21-01; VOL II. INSTALLED WEB & ANGLE IN REF TO SRM 51-35-01 VOL II.

Part: CHANNEL — CRACKED (LT WING) · airframe 77,883 hrs · 30,502 cycles

LEFT WING INBOARD UPPER L/E PANEL 517 CT HAS A CRACKED CHANNEL. REMOVED STIFFENER IAW SRM 51-35-01 VOL II. FABRICATED STIFFENER IAW DWG ARB 2407; REV "G". ALODINED & PRIMED IAW SRM 51-21-01 VOL II PGS 21-24. INSTALLED IAW SRM 51-35-01 VOL II.

Part: ANGLE — CRACKED (W-B FAIRING) · airframe 77,883 hrs · 30,502 cycles

THERE IS A CRACKED ANGLE AT THE RT WING TO BODY FAIRING SUPPORT AT BS 1581 BOTTOM EDGE. HEAT TREATED IAW TPS 1003; REV A. FABRICATED THE REPAIR IAW SRM 53-00-01 FIG 2 VOL I. ALODINED & PRIMED IAW SRM 51-21-01 VOL II. INSTALLED THE REPAIR IAW SRM 51-35-01; VOL II. REMOVED & RE-INSTALLED FLOOR BOARD PANEL 183WF IAW AMM 53-21-01-2.

Part: BRACKET — CRACKED (BS 1401 S31-32L) · airframe 77,883 hrs · 30,502 cycles

THERE IS A CRACKED BRACKET AT THE LEFT OVERWING TO BODY FAIRING SUPPORT BETWEEN LONGERON 31L & 32L AT STA 1401. REMOVED ANGLE IAW SRM 51-33-01 VOL II. FABRICATED A NEW ANGLE, HEAT TREAT IAW TPS 1003, REV " A ". ALODINED & PRIMED IAW SRM 51-21-01 PGS 21 & 24 VOL II. INSTALLED IAW SRM 51-33-01 & 51-35-01 VOL II.

Part: ANGLE — BROKEN (LT WING) · airframe 77,883 hrs · 30,502 cycles

LEFT WING INBOARD UPPER L/E PANEL 516 DT HAS A BROKEN ANGLE. ANGLE FABRICATED IAW DWG ARB 1261. HEAT TREATED IAW TPS 1003, REV "A". PRIMED IAW SRM 51-21-01; VOL II. INSTALLED IAW SRM 51-31-01 VOL II.

Part: TEE FITTING — CRACKED (BS 1441) · airframe 77,883 hrs · 30,502 cycles

THERE IS A CRACKED VERTICAL ANGLE AT THE RT OVERWING TO BODY FAIRING SUPPORT AT STA 1441. REMOVED TEE ANGLE IAW SRM 51-31-01 VOL II. IAW DWG ANB 7049 REV E. ANNEALED IAW TPS 1003 REV A. FORMED NEW TEE IAW ANB 7049 REV E. LOCATED & DRILLED IAW SRM 51-31-01 VOL II. ALODINED & PRIMED IAW SRM 51-21-01 PGS 21 & 24 VOL II. INSTALLED IAW SRM 51-31-01 VOL II. PART MARKED IAW GMM 7-0-1001.

Part: FAIRING — CHAFED (NR 1 PYLON) · airframe 77,883 hrs · 30,502 cycles

NR 1 PYLON PANEL 438 FL IS CHAFED AT THE FWD END. REMOVED DAMAGE IAW SRM 54-00-01; VOL I.

Part: ANGLE — BROKEN (BS 1421) · airframe 77,883 hrs · 30,502 cycles

THERE IS A BROKEN VERTICAL ANGLE AT THE LEFT WING TO BODY FAIRING SUPPORT AT STA 1421; ABOVE THE LEFT WING. REMOVED & REPLACED ANGLE ANB 7051-3 IAW SRM 51-31-01; VOL II.

Part: ANGLE — CRACKED (BS 1421) · airframe 77,883 hrs · 30,502 cycles

THERE IS A CRACKED VERTICAL ANGLE AT THE RIGHT OVERWING TO BODY FAIRING SUPPORT AT STA 1421. REMOVED ANGLE IAW SRM 51-31-01 VOL II. FABRICATED IAW DWG AUB 7051; REV " C ". HEAT TREATED IAW TPS 1003 REV " A ". LOCATED & DRILLED HOLES IAW SRM 51-31-01 VOL II. ALODINED & PRIMED IAW SRM 51-21-01 PGS 21 & 24 VOL II. INSTALLED NEW ANGLE IAW SRM 51-31-01; VOL II.

Part: BRACKET — CRACKED (BS 1421 L32L) · airframe 77,883 hrs · 30,502 cycles

THERE IS A CRACKED BRACKET AT THE LEFT OVERWING TO BODY FAIRING SUPPORT STRUCTURE AT STA 1421 & LONGERON 32L. REMOVED ANGLE IAW SRM 51-33-01 & SRM 51-31-01 VOL II. HEAT TREATED IAW TPS 1003; REV " A ". ALODINED & PRIMED IAW SRM 51-21-01 PGS 21 & 24 VOL II. INSTALLED IAW SRM 51-33-01 & SRM 51-31-01 VOL II.

Part: PANEL — CHAFED (NR 3 PYLON) · airframe 77,883 hrs · 30,502 cycles

NR 3 PYLON PANEL 488 GL IS CHAFED AT & AROUND THE FASTENER HOLES. BLENDED CHAFED AREAS, FOUND TO BE OUT OF LIMITS IAW SRM 54-00-01. FABRICATED IAW EA 8-5480-123637 & DWG AUB 7036 EV W.

Part: STIFFENER — CRACKED (RT WING) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING INBOARD UPPER L/E PANEL 617 CT HAS 2 CRACKED CHANNELS. REMOVED 2 EA STIFFENERS IAW SRM 51-35-01 VOL II. FABRICARED IAW DWG ARB 2407; REV " G " (-13 & -9). ALODINED & PRIMED IAW SRM 51-21-01 VOL II PGS 21-24 AND INSTALLED IAW SRM 51-35-01 VOL II.

Part: BRACKET — CRACKED (BS 1421 S32R) · airframe 77,883 hrs · 30,502 cycles

THERE IS A CRACKED BRACKET AT THE RT OVERWING TO BODY FAIRING SUPPORT AT BS 1421 L32R. REMOVED ANGLE IAW SRM 51-31-01 VOL II. FABRICATED IAW DWG ANB 7051 REV C . HEAT TREATED IAW TPS 1003 REV A. ALODINED & PRIMED IAW SRM 51-21-01 PGS 21 & 24 VOL II. INSTALLED IAW SRM 51-31-01 VOL II. PART MARKED IAW GMM 7-0-1001.

Part: PANEL — CRACKED (NR 3 PYLON) · airframe 77,883 hrs · 30,502 cycles

NR 3 PYLON PANEL 488 DL IS CRACKED. FABRICATED THE REPAIR DOUBLER IAW SRM 54-00-1 VOL I. INSTALLED DOUBLER IAW SRM 51-31-01 VOL II & SRM 54-00-01 VOL I.

Part: SKIN — GOUGED (THRUST REVERSER) · airframe 77,883 hrs · 30,502 cycles

NR 3 ENGINE INBD THRUST REVERSER OUTER SKIN IS GOUGED. 2 SPOTS CHECKED LIMITS & FOUND 1 DENT WITHIN LIMITS AND 1 OUT OF LIMITS IAW MM 78-32-01. REMOVED THE DAMAGED AREA. FABRICATED FILLER, BONDED FILLER. CURED & SANDED FLUSH IAW MM 78-32-01. CLEANED PRIMED & PAIMTED SRM 51-21-01 & SRM 51-21-01 VOL II.

Part: PANEL — GOUGED (RT WING TE FLAP) · airframe 77,883 hrs · 30,502 cycles

RIGHT WING OUTBOARD FLAP FAIRING INBOARD SIDE PANEL 635 GL HAS A GOUGE. BLENDED GOUGE; FOUND TO BE OUT OF LIMITS IAW DC/MD-10 SRM 57-52-01; VOL III & SRM 57-00-01; VOL I. PREPPED SURFACE; TREATED & PRIMED; FABRICATED DOUBLER; LAYED UP HOT BOND REPAIR & CURED. SEALED EDGES & APPLIED PRIMER COAT.

Part: PANEL — CHAFED (LT WING TE FLAP) · airframe 77,883 hrs · 30,502 cycles

LEFT WING OUTBOARD FLAP; INBOARD FAIRING; OUTBOARD SIDE PANEL 535 DL IS CHAFED ON THE INNER SKIN. BLENDED GOUGE; FOUND TO BE OUT OF LIMITS; PREPPED AREA FOR REPAIR; TREATED 7 PRIMED; FABRICATED DOUBLER; LATED UP HOT BOND REPAIR & CURED; SEALED EDGES & PRIMED AREA IAW DC/MD-10 SRM 57-00-01; VOL I & SRM 51-71-00; VOL II.

Part: FITTING — CRACKED (ZONE 100) · airframe 77,883 hrs · 30,502 cycles

NR 5 SPOOL BACK UP FITTING "HOLE C" HAS A CRACK INDICATION. BACK UP FITTING REQUIRES REMOVAL. REMOVED WEB ASSEMBLY AT FS 695 - 735 AND THE INTERCOSTAL AT FS 695 - 710 TO FOM IAW SRM 51-33-01; VOL II. INSTALLED BUSHINGS IN THE MCD LOWER JAMB BEAM AS REQUIRED. REMOVED AND REPLACED THE SPOOL BACK UP FITTING IAW SRM 53-50- 00; VOL I; FIG 17. RE-INSTALLED THE WEB ASSEMBLY AT FS 695 - 735 AND THE INTERCOSTAL AT FS 695 - 710 IAW SRM 51-33-01; VOL II.

Part: FITTING — CRACKED (ZONE 100) · airframe 77,883 hrs · 30,502 cycles

NR 1 SPOOL BACK UP FITTING "HOLE D" HAS A CRACK INDICATION IN THE BACK UP FITTING. FITTING REQUIRES REMOVAL. REMOVED AND REPLACED THE FITTING IAW SRM 53-33-01; VOL II AND EO 9-5230-7-5000 PT 2.

Part: RIB — CRACKED (ZONE 500) · airframe 77,883 hrs · 30,502 cycles

LEFT WING T/E STRUCTURE VERTICAL WEB IS CRACKED AT THE INBOARD FWD CORNER OF THE INBOARD FLAP. REMOVED & REPLACED THE CRACKED WEB (ANGLE) IN REF TO DC/MD-10 SRM 51-35-01; VOL II & IN REF TO DAC DWG AUB 7203; REV "BA".

Part: FITTING — CRACKED (ZONE 100) · airframe 77,883 hrs · 30,502 cycles

NR 4 SPOOL BACK UP FITTING "HOLE A" HAS A CRACK INDICATION. BACK UP FITTING REQUIRES REMOVAL. REMOVED WEB ASSEMBLY AT FS 675 - 695 AND THE INTERCOSTAL AT FS 675 - 690 TO FOM IAW SRM 51-33-01; VOL II. INSTALLED BUSHINGS IN THE MCD LOWER JAMB BEAM AS REQUIRED. REMOVED AND REPLACED THE SPOOL BACK UP FITTING AND THE INTERCOSTAL AT FS 675 - 690 IAW SRM 51-33-01; VOL II.

Part: SKIN — CRACKED (ZONE 500) · airframe 77,883 hrs · 30,502 cycles

LEFT WING OUTBD TRAILING EDGE PANEL 525 AT INNER SKIN IS CRACKED. CRACKED SKIN ON THE LEADING EDGE OF PANEL 525 AT REQUIRES AN SRM DOUBLER. FABRICATED THE DOUBLER IAW SRM 57-10-00 VOL I. INSTALLED DOUBLER IAW SRM 51-31-01 VOL II & SRM 57-10-00 VOL I. APPLIED PRIMER ON THE DOUBLER IAW SRM 51-21-01 VOL II.

Part: FITTING — CRACKED (ZONE 100) · airframe 77,883 hrs · 30,502 cycles

NR 7 SPOOL BACK UP FITTING "HOLES A; B AND D" HAVE A CRACK INDICATION. BACK UP FITTING REQUIRES REMOVAL. REMOVED AND REPLACED THE BACK UP FITTING IAW SRM 53-50-00; VOL I AND EO 9-5230-7-5000 PT2.

Part: SKIN — DENTED (NR 1 PACK DOOR) · airframe 77,883 hrs · 30,502 cycles

DENTS JUST BELOW THE NR 1 PACK DOOR HANDLE, FOUND DURING INCOMING INSPECTION. REMOVED THE DAMAGED AREA BELOW THE NR 1 PACK DOOR HANDLE PER DC/MD-10 SRM 52-10-00; FIG 2; VOL I. FABBED, LOCATED AND DRILLED THE FILLER; INTERNAL AND EXTERNAL DOUBLERS PER DC/MD-10 SRM 52-10-00; FIG 2; VOL 1. ALODINED PER DC/MD-10 SRM 51-21-01; PARA 31; VOL II. PRIMED PER DC/MD-10 SRM 51-21-01; PARA 24; VOL II. INSTALLED PER DC/MD-10 SRM; FIG 2; VOL I.

Part: ATTACH ANGLE — CRACKED (ZONE 600) · airframe 75,522 hrs · 29,339 cycles

THE "SUGAR SCOOP", P/N NYB6042-8, IS CRACKED AT THE UPPER OUTB'D CORNER. REMOVED RT "SUGAR SCOOP" (ATTACHMENT ANGLE) FROM CAC BULKHEAD 1154 PER SRM 51-00-01. INSTALLED NEW ATTACHMENT ANGLE, P/N NYB6042-8, AND SEALED PER SRM 53-40-00.

Part: BRACKET — CRACKED (TE FLAPS) · airframe 72,845 hrs · 28,175 cycles

RT INBD FLAP, OTBD HINGE ASSY UPPER AFT SUPPORT BRACKET WAS FOUND CRACKED. REMOVED FAB AND REPLACED BRACKET IAW SRM 51-35-01, 51-33-01, MINOR REPAIR IAW FEDEX GMM.

Part: CYLINDER — LEAKING (LANDING GEAR) · airframe 72,385 hrs · 27,970 cycles

LANDING GEAR WOULD NOT RETRACT ON T/O COMPLIED WITH QRH PROCEDURES COULD NOT RETRACT RETURNED TO EWR. PLACED FUSE BYPASS LEVER IN BYPASS POSITION, FOUND TRIM CYLINDER RELIEF VALVE LEAKING. REPLACED TRIM CYLINDER RELIEF VALVE IAW M/M 32-37-03-2, LEAK CHECK GOOD.

Part: CONTROL UNIT — MALFUNCTIONED (NR 2 MANIFOLD) · airframe 70,708 hrs · 27,227 cycles

NR 2 MANIFOLD FAIL ALERT ILLUMINATED IN FLIGHT. DIVERTED TO STL PER THE QRH, ACN RELEASED FOR SERVICE PER MEL/CDL: 36-23-01-02 CATEGORY: C EXPIRATION: 18JUL04. 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. REMOVED AND REPLACED MANIFOLD FAILURE DETECTION CONTROL UNIT PER M/M 36-23-01-4, ALL SYSTEM TESTS PASS.

Part: BOLT — UNDERTORQUED (ZONE 500) · airframe 70,116 hrs · 26,945 cycles

BOLT FAILED TORQUE CHECK ON POS 556JT LT OUTBOARD FLAP VANE. MX TORQUED PER FCD REQUIREMENTS.

Part: BOLT — UNDERTORQUED (ZONE 600) · airframe 70,116 hrs · 26,945 cycles

BOLT FAILED TORQUE CHECK ON POS 656GT RT OUTBOARD FLAP VANE. *S/D* MX TORQUED PER FCD REQUIREMENTS.

Part: BOLT — UNDERTORQUED (ZONE 500) · airframe 70,116 hrs · 26,945 cycles

BOLT FAILED TORQUES CHECK AT POSN 556GT LT OUTBOARD FLAP VANE. MX TORQUED PER FCD REQUIREMENTS.

Part: CARRIAGE — CORRODED (ZONE 600) · airframe 69,978 hrs · 26,881 cycles

COMPLY WITH EA 8-5750-73878. WINGS - OUTBD FLAP SPINDLE CARRIAGE FITTING CORROSION REPAIR P/N ARC2177. CLOSING ACTION ON 02-01-04. ON N/R S00014. COMPLIED WITH EA 8-5750-73875.

Part: SCREEN — DAMAGED (APU INTAKE) · airframe 69,978 hrs · 26,881 cycles

COMPLY WITH EA 8-4917-75549. APU - INLET SCREEN FRAME STUD REPAIR. CLOSING ACTION ON 01-31-04. ON N/R S00016. COMPLIED WITH EA 8-4917-75549.

Part: MANIFOLD — FAILED (NR 2 AIR SYS) · airframe 69,585 hrs · 26,694 cycles

AIR SYSTEM 2 MANIFOLD FAIL AFTER TAKEOFF. RETURNED TO AUS AS PER CHECKLIST. RELEASED FOR SERVICE PER MEL/CDL: 36-10-02-A CATEGORY: C EXPIRATION: 26OCT03 MEL 36-10-02-A: PNEUMATIC SYS NR 2 - INOP.

Part: MANIFOLD — FAILED (PNEU SYS) · airframe 69,313 hrs · 26,540 cycles

ABOUT 1 50 2FO FLT AT FL370 LEVEL 3 23 MANIFOLD FAIL OCCURRED. SECURED 232 ENG TO IDLE PER LIST WITH 232 BLEED OFF DIVERTED KDEN. AACN RELEASED FOR SERVICE PER MEL 2 FCDL 36-23-01-02 CATEGORY 3 AC EXPIRATION 3A 18AUG 03 FACT: CHECKED ELEMENTS_D1-50, D1-29 AND D1-27 ALL CHECKED NORMAL. FOUND D1-28 SHORTED TO GROUND PER MD10 WDM 36-23-02 AND CHAP 20 STANDARD MAINTENANCE PRACTICES. REPLACED ELEMENT D1-28 SYSTEM GND TEST NORMAL PER M/M 36-26 2 MANIFOLD FAIL CHECKED OK ON RUN.

Part: STRUCTURE — CORRODED (HORIZ STAB) · airframe 67,856 hrs · 25,807 cycles

RUST EMITTING FROM 40 EACH BARREL NUT HOLES ON RT AND LT HORIZ STAB LWR PLANK ATTACHMENT TO CENTER TORQUE BOX. R&R RUSTY BARREL NUTS & CLEANED HOLES MID PLANK AND BOLTS WITH PLI WASHERS PER MM 52-22-02-1.

Part: SPAR CAP — CRACKED (HORIZ STAB) · airframe 67,856 hrs · 25,807 cycles

HORIZONTAL STAB, CONSTANT SECTION, REAR SPAR UPPER CAP HAS A 2.5 INCH CRACK IN RT END OF VERTICAL TANG CRACK IS VERTICAL. REMOVED AND REPLACED PER EO 8-5510-7-4318.

Part: WINDOW — CRACKED (COCKPIT) · airframe 65,919 hrs · 24,694 cycles

CAPT'S WINDSCREEN OUTER PANEL SHATTERED. REMOVED AND REPLACED CAPT'S L1 WINDOW PER MM 56-11-00-2.

Part: CYLINDER — FAULTY (MLG)

ON T/O, GEAR HANDLE WOULD NOT RAISE NORMALLY. RECYCLED GEAR HANDLE, ALL GEAR RETRACTED. REMOVED AND REPLACED THE MAIN LANDING GEAR INTERLOCK FUSE AND THE MLG TRIM INTERLOCK CYLINDER, LAND GEAR OPS CK NORMAL.