N377FE

Part: LAMP — INOPERATIVE (L1 DOOR SLIDE) · airframe 97,453 hrs · 38,109 cycles

L1 DOOR SLIDE LIGHT WILL NOT TEST. REMOVED & RE LAMPED L1 DOOR SLIDE PRESS INDICATION LIGHT ASSEMBLY & REINSTALLED. OPERATIONS CHECK IS GOOD.

Part: SKIN — CRACKED (RT WING) · airframe 97,045 hrs · 37,866 cycles

RIGHT WING FOUND CRACK AT UPPER RT INBD CORNER OF TAI CUT OUT. FACTED IN ERROR WITH NO DEFECTS SEQ 225 WRI 57-10-4400. COMPLIED WITH EA 8-5720-T0310225 P1 BY REPAIRING USING SRM 57-40-01 FIG 201.

Part: SKIN — CRACKED (LT WING) · airframe 97,045 hrs · 37,866 cycles

EVIDENCE OF CRACKING AT UPPER INBD CORNER OF LT WING TAI DUCT CUT OUT ON THE FIXED LE SKIN. COMPLIED WITH EA 8-5720-T0310221 P1 BY REPAIRING USING SRM 57-40-01 FIG 201.

Part: SKIN — CRACKED (RT WING) · airframe 96,673 hrs · 37,668 cycles

POST FLIGHT WALK AROUND, FOUND POSSIBLE CRACK AT RT REFUELING DOOR INBD RADIUS ON WING. INSTALLED DOUBLER IAW SRM 57-10-00 & EA 8-5710-T0308147.

Part: SLIDE — FAULTY (L1 DOOR) · airframe 96,217 hrs · 37,418 cycles

L1 DOOR LOW BOTTLE PRESS INDICATOR LIGHT ILLUMINATED. REMOVED L1 DOOR SLIDE LOWER COVER & TROUBLESHOOT IAW ASM 25-61-0. FOUND CONTINUITY AT LIGHT ASSEMBLY JACK CONNECTOR. REPLACED L1 DOOR SLIDE IAW AMM 25-61-02-4.

Part: SENSOR — FAULTY (BLEED AIR SYS) · airframe 96,085 hrs · 37,344 cycles

ON CLIMB OUT LEVEL 3 BLED AIR 1 TEMP HI COMPLIED WITH QRH NO FURTHER INDICATION DURING RETURN. RELEASED FOR SERVICE IAW MEL 36-10-02-A. REMOVED AND REPLACED PNEU TEMP SENSOR B3-18 PER FIM 36-10-11 STEP K AND MM 36-22-01-2. NO FAULTS NOTED. TAXIED A/C TO RUN UP PAD PER JRH. RAN ENG UP TO 75%, N1 FOR FIVE MIN. NR 1 AND NR 3 ENG TEMPS CLIMBED TO 170. NO OVERHEAT. A/C OK TO CONTINUE.

Part: CHANNEL — CRACKED (NR 1 NACELLE) · airframe 95,963 hrs · 37,285 cycles

NR 1 PYLON, BRACKET BETWEEN LT AND RT LOWER SPARS CRACKED APPROXIMATELY 3 INCHES LONG. REMOVED CRACKED CHANNEL, FABRICATED NEW CHANNEL, IAW DWG AUB7009. INSTALLED CHANNEL IAW SRM 51-33-01, VOL II.

Part: SPAR — CORRODED (NR 1 PYLON) · airframe 95,963 hrs · 37,285 cycles

NR 1 PYLON UPPER SPAR CAP INBD LANDING IS CORRODED. CLEANED CORRISION AND BLENDED LANDING PER SRM 51-21-01 VOL II AND EA 8-5450-T0303216.

Part: BULKHEAD — CRACKED (NLG WW) · airframe 95,963 hrs · 37,285 cycles

NLG WHEEL WELL, RT BULKHEAD WEB CRACKED. ABOUT 3.5 INCHES LONG, AT BS 480, X= -6. INSTALLED FILLER SHIM AND DOUBLER IAW SRM 53-30-30 VOL.1 FIG.6.

Part: PROXIMITY SENSOR — MISINSTALLED (RT MLG) · airframe 95,279 hrs · 36,924 cycles

AFTER TAKEOFF, RAISED LANDING GEAR; RT MAIN INDICATED UNSAFE (RED) ON FWD PANEL AND SYNOPTIC. FOLLOWED QRH PROCEDURE, SLOWED AND CYCLED GEAR AFTER SECOND RETRACTION, ALL INDICATIONS WERE NORMAL. FOUND PROXIMITY SENSOR LINK LOWER BOLT NOT INSTALLED THROUGH BUSHING, INSTALLED BUSHING PROPERLY. ALSO ADJUSTED MLG UP AND DOOR LATCH PROXIMITY SENSOR REF AMM 32-61-15-5, ALL SENSOR TARGETS WITH IN LIMITS REF AMM32-61-15-5. GEAR SWING CHECK NORMAL. OK FOR SERVICE.

Part: WIRE — BURNED (ZONE 100) · airframe 95,277 hrs · 36,922 cycles

WIRE B9502-108-16 HAS BURN SIGNS, LOCATED BELOW THE RT OBSERVER CONSOLE THRU ACCESS PANEL ABN7643-139. REPAIRED WIRE B9502-108-16 IAW SWP 20-10-03, SECTION 7D. INSTALLED SPLICE: WDM 46-20-21. REPOSITIONED HARNESS TO PREVENT CHAFING.

Part: CONTROL UNIT — FAILED (ANTI SKID SYS) · airframe 95,233 hrs · 36,897 cycles

ANTI-SKID LT FAIL ALERT DURING PREFLIGHT CLEARED AFTER SUBSEQUENT SELF TEST. EXTENDED GEAR AND ANTI-SKID LT FAILED AGAIN. COMPLETED CHECKLIST AND DECLEARED EMERGENCY. LANDING AND BRAKING NORMAL. R & R ANTI-SKID CONTROL UNIT IAW MM 32-45-01-4. OPS CHECK IAW MM 32-45-01-5. OK FOR SERVICE. R & R ANTI-SKID CONTROL UNIT IAW MM 32-45-01-4. OPS CHECK IAW MM 32-45-01-5. OK FOR SERVICE.

Part: ANTI-SKID SYS — MALFUNCTIONED (MLG) · airframe 94,704 hrs · 36,631 cycles

LEFT ANTI-SKID FAIL GO AROUND, RAN QRH ON SECOND GEAR EXTENSION NO ANTI-SKID FAIL. PERFORMED RTS ON VIA 1 ALL CHECKS GOOD. PERFORMED BITE TEST ON ANTI SKID CONTROL UNIT IAW PLACARDED INSTRUCTIONS, ALL TESTS GOOD. PERFORMED OPS TEST OF ANTI SKID SYS IAW AMM 32-45-01-2. NO FAULT FOUND, OK TO CONTINUE.

Part: TEE FITTING — CRACKED (ZONE 100) · airframe 94,623 hrs · 36,586 cycles

LEFT SIDEWALL TO SPAR ATTACH TEE FITTING HAS A THREE INCH CRACK 1.5" DOWN FROM SPAR CAP. REMOVED TEE FITTING IAW SRM 51-35-01. FABRICATED PART APB 7078-1 IAW DWG APB 7078. INSTALLED TEE FITTING IAW STM 51-33-01. S

Part: SENSOR — FAILED (MLG DOWNLOCK) · airframe 94,070 hrs · 36,276 cycles

RIGHT MLG INTERMITTENT RED UNSAFE UP & LOCKED. BOTH PRIMARY & SECONDARY, QRH FOLLOWED. REMOVED RT MLG DOWNLOCK SENSOR D1-43. REPLACED PINS AND CONNECTOR ON NEW DOWN LOCK SENSOR PER MM 20-30-02-2-0. INSTALLED RT MAIN GEAR DOWN LOCK SENSOR 'A' PER MM 32-61-15-4. PSEU RETURNED TO SERVICE. PASSED AND SENSOR READ OUT IS OK.

Part: POWER SUPPLY — FAILED (EMERGENCY LIGHTS) · airframe 93,343 hrs · 35,880 cycles

WHILE PREPPING ACFT FOR DEPARTURE, EMERGENCY LIGHT TEST FAIL. INDICATED EMERGENY LIGHT BATTERY 1 LOW. FOUND EMERGENCY LIGHT BATTERY POWER SUPPLY FAULTY. R & R EMERGENCY LIGHT BATTERY POWER SUPPLY IAW MM 33-51-01-4. EMERGENCY LIGHTS, OPS CHECKED GOOD.

Part: BULB — WRONG PART (L1 DOOR SLIDE) · airframe 92,581 hrs · 35,480 cycles

L1 DOOR SLIDE PRESSURE, PRESS TO TEST LIGHT INOPERATIVE. FOUND WRONG BULBS INSTALLED IN LIGHT SOCKET, INSTALLED PROPER BULBS PER STANDARD MAINT. PRACTICES, OPS CHECKED GOOD.

Part: PRESSURE SWITCH — INOPERATIVE (ENG ANTI ICE) · airframe 92,409 hrs · 35,388 cycles

ON DESCENT TURNED ON ENG - WING ANTI-ICE RECEIVED "A WING A-ICE L DISAG ALERT SHORTLY AFTER RECEIVED AN AIR MANF 1 FAIL" COMPLIED WITH QRH AND DIVERTED, WITHOUT INCIDENT. R & R LT MANIFOLD FAILURE DETECTION PRESSURE SWITCH IAW MM 36-23-03-4. ALSO REPLACED NR1 ENGINE MANIFOLD FAILURE DELAY RELAY R2-5256. PERFORMED PNEUMATIC SYS PRESSURE DECAY TEST IAW MM 36-00-02-5. DECAY TIME IS IN LIMITS IAW TABLE 1. NO FURTHER DEFECTS NOTED, OK FOR SERVICE.

Part: FRAME — CRACKED (ZONE 200) · airframe 90,790 hrs · 34,541 cycles

MAIN CARGO STA 1721, RT LONGERON NR 13, FRAME CRACKED N1080 WAS GENERATED TO REPAIR ALL AFFECTED AREAS. THIS CRACKED FRAME SECTION AT THE ABOVE STA AND LONGERON WERE REMOVED WITH NEW SECTIONS AND SPLICES. THIS IS A CATEGORY "B" REPAIR AND REQUIRE A 12,000 CYCLE INITIAL INSP AND 8,000 CYCLE REPETITIVE INSP REFERENCE SRM 53-20-00 VOL: I, FIG 5.

Part: FRAME — CRACKED (ZONE 200) · airframe 90,790 hrs · 34,541 cycles

MAIN CARGO, STA 1741, RT, LONGERON NR 13, FRAME CRACKED N1079 WAS GENERATED TO REPAIR ALL AFFECTED AREAS. THIS CRACKED FRAME SECTION AT THE ABOVE STA AND LONGERON WERE REMOVED WITH NEW SECTIONS AND SPLICES. N THIS IS A CATEGORY "B" REPAIR AND REQUIRE A 12,000 CYCLE INITIAL INSP AND 8,000 CYCLE REPETITIVE INSP REFERENCE SRM 53-20-00 VOL: I, FIG 5.

Part: FRAME — CRACKED (ZONE 200) · airframe 90,790 hrs · 34,541 cycles

MAIN CARGO, STA NR 1761, LT LONGERON NR 13 FRAME CRACKED. N1076 WAS GENERATED TO REPAIR ALL AFFECTED AREAS. THIS CRACKED FRAME SECTION AT THE ABOVE STA AND LONGERON WERE REMOVED WITH NEW SECTIONS AND SPLICES. THIS IS A CATEGORY "B" REPAIR AND REQUIRE A 12,000 CYCLE INITIAL INSP AND 8,000 CYCLE REPETITIVE INSP REFERENCE SRM 53-20-00 VOL: I, FIG 5.

Part: FRAME — CRACKED (ZONE 200) · airframe 90,790 hrs · 34,541 cycles

MAIN CARGO, STA NR 1781, LT LONGERON NR 13, FRAME CRACKED N1078 WAS GENERATED TO REPAIR ALL AFFECTED AREAS. THIS CRACKED FRAME SECTION AT THE ABOVE STA AND LONGERON WERE REMOVED WITH NEW SECTIONS AND SPLICES. THIS IS A CATEGORY "B" REPAIR AND REQUIRE A 12,000 CYCLE INITIAL INSP AND 8,000 CYCLE REPETITIVE INSP SRM 53-20-00 VOL: I, FIG 5.

Part: NONE — NONE · airframe 88,798 hrs · 33,613 cycles

REJECTED TAKEOFF AT IND AT 100 KTS OAT 31C WEIGHT 386,200. REJECTED FOR PREDICITIVE WINDSHEAR ALERT. NO OBSERVED OR REPORTED WINDSHEAR. PERFORMED BRAKE INSPECTION PER AMM 32-57-00-6. NO DEFECTS NOTED. ACN RELEASED FOR SERVICE PER MEL/CDL: 34-41-01-01-A CATEGORY: C EXPIRATION: 15JUN08 "MEL 34-41-01-01-A: PREDICTIVE WINDSHEAR INOP. WAGS WINDSHEAR IS AVAILABLE." PERFORMED BRAKE INSPECTION PER AMM 32-57-00-6. NO DEFECTS NOTED.

Part: BOLT — SHEARED (NR 3 PYLON) · airframe 87,954 hrs · 33,211 cycles

NR 3 PYLON, TOMBSTONE LOWER SPHERICAL BEARING ATTACH BOLT SHEARED AT 6 O'CLOCK POSITION, DOT NR 1. REMOVED AND REPLACED 6 BOLTS, P/N 77711-9-105, PLATE -P/N AUB7125-1, RETAINER P/N AUB7126-501 AND PLI WASHERS REF AMM 54-00-01-4.

Part: MEC — FAILED (NR 1 ENGINE) · airframe 87,329 hrs · 32,923 cycles

NR 1 ENGINE FLAMED OUT ON ROLLOUT. FIRST INDICATION WAS GEN 1 OFF FOLLOWED BY AIR SYS 1 LOW PRESS. REMOVED AND REPLACED FUEL PUMP AND MEC.

Part: SPAR — CORRODED (BS 1321-1381) · corrosion level 2 · airframe 85,141 hrs · 32,000 cycles

LT WHEEL WELL STA 1370 JUST ABOVE REAR SPAR, HAS AREA OF CORROSION. REMOVED CORROSION AT EDGE MEMBER, OUT OF LIMITS IAW DC10 SRM 51-21-01-VOL II AND DC10 SRM 53-00-01 FIG 1A VOL I. REMOVED AND REPLACED EDGE MEMBER, ANGLE SECTION, GASKET, RUB STRIP AND INSTALLED SLANT PANEL IAW DC10 SRM 51-35-01, 51-33-01 VOL II, DAC DWG AEA4401 REVA, FEDEX DWG SR10-53-508 REV A AND REMOVED AND INSTALLED FLOORBOARD AT STA 132-1381, LBLL8-107 IAW MD10 MM 53-21-01-2.

Part: DOUBLER — CRACKED (ZONE 500) · airframe 85,141 hrs · 32,000 cycles

LEFT OUTER WING TO CENTER WING LOWER SURFACE SPLICE DOUBLER HAS A CRACK STARTING AT FASTENER HOLE ON AFT END, XFS 145 AND FS 1370. REPAIRED IAW FEDEX EA 8-5710-96375- WINGS, CENTER WING BOX SPLICE PLATE CRACKED. FINGER REPAIR, MAJOR REPAIR.

Part: REPAIR — UNKNOWN (ZONE 100) · airframe 85,141 hrs · 32,000 cycles

REPAIR EVALUATION AGING AIRPLANE PROGRAM EXISTING REPAIR AT STA 304-328 LONGERON 26L-38L. OPS 1401/ T 8-5330-86848 COMPLIED WITH CARD T-8-5330-83848-FUSELAGE-REPAIR EVALUATION AGING AIRPLANE PROGRAM EXISTING REPAIR AT STA.304-328 LONGERON 26L-38L. MAJOR REPAIR

Part: VALVE — MALFUNCTIONED (LT PARKING BRAKE) · airframe 82,244 hrs · 30,744 cycles

AFTER GEAR EXTENSION, RECEIVED LVL 2 LT ANTI SKID FAIL. EXECUTED GO-AROUND, FOLLOWED QRH PROCEDURES. ALERT MOMENTARILY EXTINGUISHED AFTER CYCLING ANTI SKID SWITCH, BUT RE-APPEARED ON NEXT GEAR EXTENSION. HISTORY OF SAME PROBLEM. T/S PER FIM 32-40-08 & M/M 32-45-01-5. REMOVED AND REPLACED LEFT PARKING BRAKE VALVE ACTUATOR PER M/M 32-45-05-2.

Part: HINGE BRACKET — GOUGED (ZONE 300) · airframe 82,189 hrs · 30,715 cycles

VERTICAL STABILIZER REAR SPAR, UPPER RUDDER HINGE FITTING BENT AND GOUGED. REMOVED AND REPLACED UPPER RUDDER HINGE SUPPORT BRACKET IAW MD10-10 MM 55-53-01-2 AND EA 8- 5530-83844, STABILIZER- VERTICAL STABILIZER RUDDER HINGE BRACKET, REPAIR. REFERENCE NON-ROUTINE N01059.

Part: SKIN — DAMAGED (ZONE 100) · airframe 82,189 hrs · 30,715 cycles

AFT REPAIR AT STATION 966 TO 1001, LONGERON 37 RIGHT TO 42 RIGHT NEEDS EVALUATION TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVED DATA AND REPETITIVE INSPECTION REQUIREMENTS. REMOVED EXISTING DAMAGED PORTION OF SKIN IAW DC10 SRM 53-20-00 VOL 1. FABRICATED AND INSTALLED REPAIR IAW DC10 SRM 53-20-00 FIGURE 6.

Part: SKIN — DAMAGED (ZONE 100) · airframe 82,189 hrs · 30,715 cycles

REPAIR AT STATION 470-475 LONGERON 30 RIGHT TO 30 LEFT, NEEDS ENGINEERING EVALUATION TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVED DATA AND REPETITIVE INSPECTION REQUIREMENTS. REMOVED EXISTING REPAIR. REPLACED DOUBLER PER DC10 SRM 53-20-00 VOL 1, FIGURE 6, SHEET 15. REFERENCE NON-ROUTINE N01169.

Part: SKIN — DAMAGED (ZONE 100) · airframe 82,189 hrs · 30,715 cycles

REPAIR AT STATION 1942 LONGERON 50 RIGHT TO 51 RIGHT NEEDS ENGINEERING EVALUATION TO DETERMINE IF REPAIR IS MINOR OR MAJOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVED DATA AND REPETITIVE INSPECTION REQUIREMENT. REMOVED OLD REPAIR IAW DC10 SRM 51-35-01 VOL 2, FABRICATED AND INSTALLED DOUBLER REPAIR IAW DC10 SRM 53-20-00 VOL 1, 51-21-01 VOL 2 AND 51-35-01 VOL 2. REFERENCE NON-ROUTINE N01182

Part: SKIN — DAMAGED (FUSELAGE) · airframe 82,189 hrs · 30,715 cycles

REPAIR AT STATION 304 TO 328 LONGERON 26 LEFT AND 38 LEFT NEEDS ENGINEERING EVALUATION TO DETERMINE IF REPAIRS IS MAJOR OR MINOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVED DATA AND REPETITIVE REQUIREMENTS. EVALUATED REPAIR IAW FEDEX EA 8-5330-83848, FUSELAGE, REPAIR EVALUATION AGING AIRPLANE PROGRAM EXISTING REPAIR AT STATION 304-328 LONGERON 26L-38L- REPAIR. REPAIR IS MAJOR AND REPLACEMENT IS REQUIRED AT NEXT "C" CHECK IAW FEDEX EA 8-5330-83848. REFERENCE NON-ROUTINE N01166.

Part: SKIN — DAMAGED (ZONE 100) · airframe 82,189 hrs · 30,715 cycles

EXTERNAL DOUBLER ON LEFT HAND LOWER FUSELAGE SKIN STATION 470 TO 475 BETWEEN LONGERON 30 LEFT AND 31 LEFT APPEARS NOT TO BE PER THE SRM. REMOVED OLD REPAIR IAW DC10 SRM 51-33-01 VOL 2. FABRICATED AND INSTALLED NEW DOUBLERS IAW DC10 SRM 53-20-00 VOL 1, FIGURE 6, 51-35-01 AND 51-33-01 V0L 2. REFERENCE NON-ROUTINE N01093.

Part: SKIN — DAMAGED (ZONE 100) · airframe 82,189 hrs · 30,715 cycles

REPAIR AT STATION 330 BETWEEN LONGERONS 37 RIGHT TO 38 RIGHT NEEDS ENGINEERING EVALUATION TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVED DATA AND REPETITIVE REQUIREMENTS. CUT OUT DAMAGED AREA OF SKIN, FABRICATED AND INSTALLED FILLER SHIMS, INNER AND OUTER DOUBLERS AND INTERNAL FINGER DOUBLERS IAW DC10 SRM 53-20-00 VOL 1 FIGURE 6, SHEET 5 AND 51-21-01 VOL 2.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 82,189 hrs · 30,715 cycles

REPAIR AT STATION 1957 TO 1993 LONGERON 49 LEFT TO 49 RIGHT NEED ENGINEERING EVALUATION TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF REPAIR IS IN ACCORDANCE WITH FAA APPROVE DATA AND REPETITIVE INSPECTION REQUIREMENT. CUT AND REMOVE SKIN IAW EA8-5330-83838. REMOVED CORROSION FROM LONGERON AND FOUND TO BE OUT OF LIMITS IAW DC10 SRM 53-10-01 VOL 1. FABRICATED AND INSTALLED SKIN, SPLICE, 2 EACH DOUBLERS, AND LONGERON SPLICE REPAIR FITTINGS IAW DC10 SRM 53-20-00 VOL 1, 51-31-01VOL 2, 51-35-01 VOL 2, AND FEDEX EA 8-5330-83838, FUSELAGE, SKIN SPLICE IN AREA OF ART LAV PAN, REPAIR. REFERENCE NON-ROUTINE N01183.

Part: ROLLER — WORN (ZONE 600) · airframe 82,189 hrs · 30,715 cycles

RIGHT WING LOWER AFT LOAD ROLLER HAS WORN BEARING SURFACE, CHROME WORN ON INBOARD FLAP TRACK ATTACHMENT AREA. REMOVED AND REPLACED RIGHT HAND INBOARD FLAP INBOARD TRACK AFT LARGE LOAD ROLLER IAW FEDEX EA 8- 5750-81513.

Part: PRESSURE BLKHD — DAMAGED (ZONE 100) · airframe 82,189 hrs · 30,715 cycles

REPAIR UNDER RADAR ON PRESSURE BULKHEAD NEEDS ENGINEERING EVALUATION TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF IS IN ACCORDANCE WITH FAA APPROVED DATA AND REPETITIVE INSPECTION REQUIREMENTS. PERFORMED FEDEX EA 8-5330-83949, FUSELAGE- REPAIR EVALUATION AGING AIRPLANE PROGRAM EXISTING REPAIR AT STATION 275, FORWARD PRESSURE BULKHEAD. OPENED AND CLOSED RADOME IAW MD10-10 MM 53-51-00-2.

Part: SKIN — DAMAGED (ZONE 100) · airframe 82,189 hrs · 30,715 cycles

REPAIR AT STATION 1140 TO 1151 AT LONGERON 39 LEFT TO 41 LEFT NEEDS ENGINEERING EVALUATION TO DETERMINE MAJOR OR MINOR AND IF DATA AND REPETITIVE INSPECTION REQUIREMENTS. REMOVED PANEL 153AB AND REMOVED DOUBLER IAW DC10 SRM 51-31-01 VOL 2 AND 51-35-01 VOL 2. FABRICATED AND INSTALLED DOUBLER AND FINGER DOUBLER IAW DC10 SRM 53-20-01 VOL 2. REINSTALLED PANEL 153AB IAW DC10 SRM 51-31-01 VOL 2.

Part: SKIN — DAMAGED (ZONE 100) · airframe 82,189 hrs · 30,715 cycles

REPAIR AT STATION 377 TO 413, LONGERON 50 RIGHT TO LONGERON 47 LEFT NEEDS ENGINEERING EVALUATION TO DETERMINE IF REPAIR ID MAJOR OR MINOR AND IF REPORT IS IN ACCORDANCE WITH FAA APPROVED DATA AND REPETITIVE INSPECTION REQUIREMENTS. EVALUATED REPAIR AT STATION 377 TO 413 LONGERON 50 RIGHT TO LONGERON 47 LEFT AND ACCOMPLISHED FEDEX EA 8-5330-83846, FUSELAGE- REPAIR EVALUATION AGING AIRPLANE PROGRAM EXISTING REPAIR AT STATION 377- 413 LONGERON 50 RIGHT TO LONGERON 47 LEFT.

Part: PANEL — DENTED (ZONE 500) · airframe 82,189 hrs · 30,715 cycles

LEFT HAND WING UPPER TRAILING EDGE PANEL JUST OUTBOARD OF MAIN LANDING GEAR UPPER SURFACE HAS SEVERAL DENTS. REPAIRED PANEL PART NUMBER ARC0263, BY FABRICATING AND BONDING NEW OUTER SKIN, INNER SKIN, DOUBLER AND CORE IAW RPS 1001 REV E, DAC PRINT ARC0263 AND FEDEX EA 8-5710-81525, WINGS- LEFT HAND UPPER WING PANEL ASSEMBLY AILERON TO MAIN LANDING GEAR REPAIR. REMOVED AND REINSTALLED SEALS, RETAINERS AND PANEL IAW DC10 SRM 51-31-01 VOL 2. REFERENCE NON-ROUTINE N00895.

Part: SEAL — WORN (ZONE 500) · airframe 82,189 hrs · 30,715 cycles

LT HAND WING UPPER TRAILING EDGE HAS TORN SEAL AT OUTBOARD END OF NR 1 LEFT HAND SPOILER. REMOVED SEAL FROM SPOILER NR 1 LEFT WING IAW FEDES MD10-10 MM 20-50-02 PAGE 1. REPAIRED SEAL IAW FEDEX EA 8-2760-83941, REINSTALLED SEAL ON NR 1 LEFT WING SPOILER IAW FEDEX MD10-10 MM 20-50-02- 2 PAGE 1 AND FEDEX EA 8-2760-83941, FLIGHT CONTROL- NR 1 SPOILER, TRAILING EDGE WORN SEAL REPAIR.

Part: DOOR — DELAMINATED (ZONE 500) · airframe 82,189 hrs · 30,715 cycles

LEFT HAND WING REFUEL PANEL NEEDS REWORK DUE TO SHIFT OF INNER DOUBLER DURING AUTO-CLAVE CURE AND LACK OF TIMCO ROUTING SHEET BEING ASSIGNED. REPAIRED, REWORKED REFUEL PANEL PART NUMBER ARB1101-503 BY FABRICATING AND BONDING NEW OUTER SKIN AND INNER DOUBLER IAW TPS 10001 REV E AND DAC DWG ARB1101 AND FEDEX EA 8-5710-83944, WINGS- LEFT HAND WING, DOOR ASSEMBLY, REFUELING PANEL DISBOND- REPAIR. LOWER SKIN, CORE AND BLOCKS BONDED ON NON-ROUTINE N01203.

Part: BULKHEAD — DAMAGED (ZONE 200) · airframe 82,189 hrs · 30,715 cycles

REPAIR ON AFT SIDE OF PRESSURE BULKHEAD FORWARD WALL IN FORWARD CARGO COMPARTMENT FLOOR LEVEL ENGINEERING EVALUATION TO DETERMINE IF REPAIR IS MAJOR OR MINOR AND IF REPAIR DATA ARE REPETITIVE INSPECTIONS REQUIREMENTS. EVALUATED REPAIR ON AFT SIDE OF PRESSURE BULKHEAD FORWARD WALL IN FORWARD CARGO COMPARTMENT FLOOR LEVEL AND ACCOMPLISHED FEDEX EA 8-5310-83845.

Part: ROLLER — LOOSE (ZONE 600) · airframe 82,189 hrs · 30,715 cycles

RIGHT WING LOWER FORWARD INBOARD FLAP LOAD ROLLER HAS EXCESSIVE LATERAL PLAY. REMOVED AND REPLACED RIGHT HAND INBOARD FLAP INBOARD TRACK LOWER ROLLER IAW FEDEX EA 8-5750- 81513, WING- INBOARD FLAP- INBOARD ROLLER TORQUE REQUIREMENT- CLARIFICATION.

Part: PANEL — DELAMINATED (ZONE 600) · airframe 82,189 hrs · 30,715 cycles

RIGHT WING PANEL ARC0613-502, UPPER TRAILING EDGE PANEL AT INBOARD END OF OUTBOARD FLAP DELAMINATED. RIGHT WING PANEL ARC0613-502 REPAIRED BY FABRICATING AND BONDING NEW OUTER SKINS, DOUBLER AND CORE IAW TPS 1001 REV E, DAC DWG ARC0613 AND FEDEX EA 8-5710-81523, WINGS, RIGHT HAND UPPER WING PANEL ASSEMBLY. REPAIR, INSTALLED PANEL IAW DC10 SRM 51-31-01 VOL 2. REFERENCE NON-ROUTINE N00723.

Part: MANIFOLD — WORN (ZONE 400) · airframe 82,189 hrs · 30,715 cycles

NR 1 ENGINE OUTBOARD THRUST REVERSER UPPER COOLING DUCT IS CHAFED IN SEVERAL AREAS. REMOVED COOLING DUCT IAW DC10 SRM 51-31-01 VOL 2. WELD REPAIRED COOLING MANIFOLD IAW FEDEX EA 8-7830-81526, EXHAUST SYSTEM NR 1 OUTBOARD THRUST REVERSER COOLING DUCT MANIFOLD REPAIR. REINSTALLED COOLING MANIFOLD DUCT IAW MD10 SRM 51-31-01 VOL 2.

Part: PANEL — DELAMINATED (ZONE 200) · airframe 82,189 hrs · 30,715 cycles

RIGHT WING INBOARD FLAP AREA LEFT HAND FALSE SPAR CEILING PANEL INBOARD OF MAIN LANDING GEAR STRUT DELAMINATED/DENTED. REMOVED FILLET PANELS 152FT, 152ET AND SMALL PANEL OUTBOARD OF DAMAGED PANEL IAW DC10 SRM 51-31-01 VOL 2, TO FOM. REMOVED DELAMINATED PANEL IAW DC10 SRM 51-31-01 VOL 2. REPAIRED DELAMINATED PANEL IAW FEDEX EA 8-5710-81524, WING- RIGHT HAND UPPER WING PANEL ASSEMBLY MAIN LANDING GEAR FITTING TO FUSELAGE CENTER UPPER- REPAIR. REINSTALLED REPAIRED PANEL IAW DC10 SRM 51-31-01 VOL 2. REINSTALLED FILLET PANELS 152FT, 152ET AND SMALL PANEL OUTBOARD OF REPAIRED PANEL IAW DC10 SRM 51-31-01 VOL 2.

Part: PANEL — DELAMINATED (ZONE 500) · airframe 82,189 hrs · 30,715 cycles

LEFT WING PANEL OVER AFT TRUNNION HAS MANY AREAS OF DELAMINATION. REPAIRED AFT TRUNNION PANEL ARC0269-503 BY FABRICATING AND BONDING NEW SKINS, DOUBLERS AND CORE IAW TPS 1001 REV E, DAC GWG ARC0269 AND FEDEX EA 8-5710-83945, WINGS- LEFT HAND MAIN LANDING GEAR FITTING TO FUSELAGE AFT, UPPER TRAILING EDGE PANEL- REPAIR.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 82,189 hrs · 30,715 cycles

LEFT AND INBOARD FLAP OUTBOARD HINGE BOLT HOLE HAS AREA OF CORROSION. BOLT HOLE IS REPLACEMENT BOLT PART NUMBER 3D0031-8-90 STEP 23 OF FEDEX WIC E 8-5710-7-5005 PT1. REMOVED STOP FITTING IAW DAC DWG ARC0154, REMOVED OUTBOARD PANEL IAW MD10 SRM 51-31-01 VOL 2, REAMED HOLE TO .5273 INCH, OUT OF LIMITS IAW DAC DWG ARC0154 AND MD10 51-21-01 PAGE 1-8. ACCOMPLISHED FEDEX EA 8-5710-81535, WINGS- LEFT HAND, INBOARD FLAP, OUTBOARD HINGE BRACKET, UPSTOP MOUNTING HOLES- REPAIR.

Part: DOOR — DELAMINATED (ZONE 500) · airframe 82,189 hrs · 30,715 cycles

LEFT WING REFUEL PANEL, DELAMINATED ON EDGES ADJACENT TO HINGE, AS MARKED. LOWER SKIN, CORE AND BLOCKS BONDED IAW TPS 1001 REV E, DAC DWG ARB1011 AND FEDEX EA 8- 5710-83944, AND DC10 SRM 51-70-00 VOL 2.

Part: ROLLER — WORN (ZONE 600) · airframe 82,189 hrs · 30,715 cycles

RIGHT WING INBOARD FLAP UPPER LOAD ROLLER HAS CHROME WORN AWAY ON BEARING SURFACE OF ROLLER. REMOVED AND REPLACED RIGHT HAND INBOARD FLAP INBOARD TRACK FORWARD UPPER LOAD ROLLER IAW FEDEX EA 8-5750-81513, WING - INBOARD ROLLER TORQUE REQUIREMENT - CLARIFICATION. REFERENCE NON-ROUTINE N00589.

Part: ROLLER — CORRODED (T/E FLAP) · airframe 82,189 hrs · 30,715 cycles

LEFT INBOARD FLAP INBOARD FLAP TRACK AREA, LOWER FORWARD LARGE ROLLER CORRODED ON OUTBOARD SIDE. REMOVED AND REPLACED LEFT INBOARD FLAP INBOARD TRACK LOWER FORWARD LARGE ROLLER IAW FEDEX EA 8-5750-81513. REFERENCE NON-ROUTINE N00604.

Part: ROLLER — WORN (T/E FLAP) · airframe 82,189 hrs · 30,715 cycles

LEFT WING INBOARD FLAP INBOARD FLAP ROLLERS MOST FORWARD UPPER LARGE ROLLER WORN. REMOVED AND REPLACED LEFT INBOARD FLAP INBOARD TRACK FORWARD UPPER LARGE ROLLER IAW FEDEX EA 8- 5750-81513, WINGS, INBOARD FLAP, INBOARD ROLLER TORQUE REQUIREMENTS, CLARIFICATION. REFERENCE NON-ROUTINE N00603.

Part: ROLLER — WORN (T/E FLAP) · airframe 82,189 hrs · 30,715 cycles

LEFT HAND INBOARD FLAP INBOARD FLAP TRACK AREA, LOWER FORWARD SMALL ROLLER PLATING WORN. REMOVED AND REPLACED LEFT HAND INBOARD FLAP INBOARD TRACK LOWER FORWARD SMALL ROLLER IAW FEDEX EA 8-5750-8513, WING INBOARD FLAP INBOARD ROLLER TORQUE REQUIREMENT, CLARIFICATION. REFERENCE NON-ROUTINE N00605.

Part: PANEL — DELAMINATED (ZONE 600) · airframe 82,189 hrs · 30,715 cycles

PANEL NR 641 LB, RIGHT WING INBOARD TRAILING EDGE HAS DELAMINATION IN NUMEROUS AREAS. REPAIRED PANEL NR 641LB BY FABRICATING AND BONDING NEW SKINS, DOUBLER AND CORE IAW TPS 1001 REV E AND DAC DWG ARC0357 ANF FEDEX EA 8-5710-81521, WINGS, RIGHT HAND LOWER AILERON CLOSURE, LOWER TRAILING EDGE FAIRING PANEL. REFERENCE NON-ROUTINE N00919.

Part: LONGERON — WORN (ZONE 400) · airframe 82,189 hrs · 30,715 cycles

NR 1 ENGINE INBOARD CORE COWL UPPER LONGERON IS CRACKED AFT OF CENTER HINGE. REPAIRED IAW FEDEX EA 8-5410-81514, NACELLES/PYLON, NR 1 ENGINE RIGHT HAND CORE COWL UPPER LONGERON, REPAIR. REFERENCE NON-ROUTINE N00166.

Part: HINGE FITTING — CORRODED (ZONE 600) · airframe 82,189 hrs · 30,715 cycles

RIGHT WING OUTBOARD FLAP INBOARD SUPPORT PIVOT ATTACH POINT INBOARD BUSHING GALLED. MEASURED BORE DIAMETER AT 1.1725, FOUND TO BE BEYOND DAC MD10 CMM 57-52-02 LIMITS OF 1.150. FABRICATED, INSTALL AND FINAL HONE REPAIR BUSHING IAW DAC CMM 57-52-02 AND EA 8-5750-81509, WING RIGHT HAND OUTBOARD FLAP INBOARD HINGE FITTING PIVOT BORE-REPAIR. REFERENCE NON-ROUTINE N00184.

Part: LONGERON — WORN (ZONE 400) · airframe 82,189 hrs · 30,715 cycles

NR 3 ENGINE OUTBOARD CORE COWL UPPER LONGERON WORN AFT OF CENTER HINGE. REMOVED DAMAGED AREA IAW FEDEX EA 8-5410-81518, FABRICATED AND INSTALLED REPAIR DOUBLER IAW FEDEX EA 8-5410-81518, NACELLES/PYLON, NR 3 ENGINE RIGHT HAND CORE COWL UPPER LONGERON REPAIR. REFERENCE NON-ROUTINE N00176.

Part: ROLLER — CHIPPED (ZONE 500) · airframe 82,189 hrs · 30,715 cycles

LEFT WING INBOARD FLAP INBOARD TRACK AREA LOWER AFT LARGE ROLLER PLATING WORN ON SIDE OF ROLLER. REMOVED AND REPLACED LEFT HAND INBOARD FLAP INBOARD TRACK LOWER AFT LARGE ROLLER IAW FEDEX EA 8-5750-81513, WING, INBOARD FLAP, INBOARD ROLLER TORQUE REQUIREMENT, CLARIFICATION. REFERENCE NON-ROUTINE N00606.

Part: LONGERON — WORN (ZONE 400) · airframe 82,189 hrs · 30,715 cycles

NR 1 ENGINE RIGHT HAND CORE COWL UPPER LONGERON HAS 2 EACH GOUGES UNDER AFT HINGE. REMOVED AFT FITTING IAW DC10 SRM 51-31-01 VOL II. CUT OUT DAMAGED AREA IAW FEDEX EA 8-5410- 81531, NACELLES/PYLON, NR 1 ENGINE RIGHT HAND CORE COWL UPPER LONGERON, REPAIR. REINSTALLED AFT FITTING IAW DC10 SRM 51-31-01 VOL II.

Part: ACCESS PANEL — DELAMINATED (ZONE 500) · airframe 82,189 hrs · 30,715 cycles

LEFT WING ACCESS PANEL NR 541JB HAS 4 EACH DENTS ON LOWER SURFACE. REPAIRED LEFT HAND WING ACCESS PANEL P/N ARC0585, BY FABRICATING AND BONDING NEW INNER AND OUTER SKINS, DOUBLER AND CORE IAW FEDEX EA 8-5710-81522 AND TPS 1001 REV E AND DAC PRINT ARC0585. REFERENCE NONROUTINE N00990.

Part: CHAIN — CRACKED (HORIZ STAB) · airframe 78,797 hrs · 28,991 cycles

FOUND HAIRLINE CRACK ON CHAIN LINK SLEEVE OF HORIZONTAL STAB LOWER LT CHAIN. REMOVED AND REPLACED LT LOWER CHAIN MASTER LINK, SECURED, NEEDS REPOSITION & TENSION. REMOVED AND REPLACED UPPER AND LOWER LT CHAINS FOR LT ACME SCREW PER MM 27-44-02-2-1.

Part: DOOR — CORRODED (L1) · airframe 77,882 hrs · 28,525 cycles

BS 415 L1 DOOR CORROSION ON FWD LWR LEG. REMOVED AND REPLACED DOOR PER SRM 53-20-00.

Part: SLAT TRACK — DAMAGED (LT WING) · airframe 77,882 hrs · 28,525 cycles

LEFT WING UPPER L/E INBOARD SLAT TRACK NR 1. REMOVED AND REPLACED PER IAW EA 8-5410-56154 & SRM 57-20-00.

Part: SKIN — CRACKED (#2 ENG INLET) · airframe 77,882 hrs · 28,526 cycles

N 192 & N 351 #2 ENG INLET, AFT SIDE CRACK IN SKIN. R&R SKIN PER SRM 54-10-00 & 55-31-01 & EA 8-5410-56140.

Part: FAIRING — DELAMINATED (NR 2 PYLON) · airframe 77,882 hrs · 28,526 cycles

PYLON NR 2 AFT FAIRING EDGE LT SIDE IS DISBONDED AND MISSING RIVETS. REMOVED AND REPLACED TRAILING EDGE PER EA 8-5410-56153 & SRM 54-12-02.

Part: BRACKET — CRACKED (WING) · airframe 77,882 hrs · 28,525 cycles

CRACK AT TOP OF CORNER ANGLE BRACKET. REMOVED AND REPLACED BRACKET PER EA 8-5710-56175 & S/B 57-88.

Part: DOOR FRAME — DAMAGED (FUSELAGE) · airframe 77,882 hrs · 28,525 cycles

F/S 963 LONG 39R TO 40R AFT FRAME FWD CARGO DOOR FRAME WORN THRU BOTH LAYERS OF SKIN. R&R FRAME PER SRM & EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 77,882 hrs · 28,525 cycles

CTR CARGO LT BS 1701 CRACK IN FRAME AT L27. REMOVED AND REPLACED FRAME PER SRM & IAW.

Part: DOOR FRAME — WORN (FUSELAGE) · airframe 77,882 hrs · 28,525 cycles

N 33 FS 960, LONG 40R TO 41R, FWD CARGO DOOR FRAME, AFT FRAME SKIN WORN. R&R FRAME PER SRM & EA.

Part: SKIN — DENTED (CARGO DOOR) · airframe 77,882 hrs · 28,525 cycles

F/S 559 LONG 39R TO 40R 6 EA DENTS AFT OF FWD CARGO DOOR. R&R DOOR PER EA & SRM.

Part: PRESSURE PANEL — CORRODED (FUSELAGE) · airframe 77,882 hrs · 28,525 cycles

CORROSION ON CAPT & F/O'S SIDE COCKPIT FLOOR BETWEEN BS 295-322. R&R COCKPIT FLOOR PER SRM & EA.

Part: DOOR FRAME — WORN (FUSELAGE) · airframe 77,882 hrs · 28,525 cycles

F/S 960 LONG 40R TO 41R FWD CARGO DOOR AFT FRAME WORN. R&R PER IAW & SRM.

Part: FRAME — CRACKED · airframe 77,882 hrs · 28,525 cycles

N 240 THERE IS CRACK ON FRAME AT Y=459, X=18 AT FRAME SPLICE INCLUDE IS A PREVIOUS REPAIR FROM X=18 TO X=18. R&R FRAME PER IAW EA & SRM.

Part: SKIN — CRACKED (AFT SIDE) · airframe 77,882 hrs · 28,525 cycles

N 351 #2 ENGINE INLET AFT SIDE HAS CRACK. R&R PER IAW EA & SRM REQ.

Part: SKIN — CORRODED (AILERON) · airframe 76,862 hrs · 28,021 cycles

LEFT WING O/B AILERON LWR SKIN IS CORRODED AFT OF CENTER HINGE POINT. *S/D* REMOVED AND REPLACED PER SRM 51-00-01.

Part: SKIN — CORRODED (AILERON) · airframe 76,862 hrs · 28,021 cycles

SKIN BULGING AROUND FASTENERS ON LWR SURFACE OF RT O/B AILERON. FOUND CORROSION BETWEEN SKIN AND FINGER DOUBLER. *S/D* REMOVED AND REPLACED LWR SURFACE SKIN OF RT O/B AILERON REF SRM 51-00-01.

Part: SPAR — GOUGE (RT WING)

RIGHT WING AFT SPAR AFT TANG HAS A GOUGE ACROSS THE FLANGE AT XROS 414. COMPLIED WITH EA 8-5710-42395 RT REAR SPAR DEVIATION FROM EO 8-5710-7-30041.

Part: SWITCH — INOP (LT MLG DOOR)

98-309 - LT MAIN GR IND ON BOTH PNLS WAS IND UNSAFE UP. COMPLETE RED TAB PROC, REMAIN UNSAFE UP. DIVERT TO OAK. REMOVED AND REPLACED LEFT MAIN LAND GEAR DOOR PROXIMITY SWITCH TARGET SUPPORT. NOSE AND RIGHT LAND GEAR PINS INSTALL. POS AND WARNING OPS NORM. GEAR PINS REMOVED.

Part: SPAR WEB — CRACKED (WS 240)

STA-VCE - SEVERAL CRACKS WERE FOUND COMMON TO LT REAR SPAR AFT WEB AT XRS = 240. MAJOR REPAIR PERFORMED IAW EA 8-5711-38429 A. FABRICATED PARTS IAW DETAIL PART TRAVELER F008593/N2593. (26 JUNE 1998).

Part: SKIN — DAMAGED (WS 826)

RT WING LOWER WING SKIN, STA X0RS 826.00 THERE IS DAMAGE TO THE LOWER SKIN (WIDTH: 0.250, DEPTH: 0.065, DISTANCE TO NEAREST FASTENER: 0.5). CENTER TO CENTER. MAJOR REPAIR PERFORMED IAW EA 8-5732-38431, ENCLOSED. (22 JUNE 1998)

Part: BULKHEAD FITTING — CRACKED (BS 1156)

STA-VCE: DURING REMOVAL AND REPLACEMENT OF P/N AYB 7000-2 (Y=1156 BLKHD CORNER FITTING) A GAP WAS FOUND BETWEEN AYB 7000-2 WEB AND P/N NYB6054-25, NOT COVERED BY SRM STANDARDS. REF NRC NR N1341. MAJOR REPAIR PERFORMED IAW EA 8-5314-34489B. (29 JUNE 1998).

Part: WEB — CRACKED (BS 2007)

STA-VCE LOWER AFTER FUSELAGE COMPARTMENT STA 2007 FOUND CRACK ON WEB CORNER. MAJOR REPAIR PERFORMED IAW EA 8-5317-38443 9-JULY 1998.

Part: SKIN — CORRODED (CENTER WING)

CENTER WING TAPERED FWD LWR SKIN (P/N APB 7002-1) HAS CORROSION AT STRINGERS 44 AND 45 BETWEEN XCW STATIONS 4.0 TO 14.5. MAJOR REPAIR PERFORMED IAW EA 8-5734-38427. REMOVED FASTENERS ADJACENT TO CORROSION AND INSPECTED HOLES PER SRM 57-20-00. REMOVED CORROSION AND CHECKED VALUES PER SRM 57-20-00, FOUND OUT OF LIMITS. INSTALLED OVERSIZED FASTENERS PER SRM 51-31-00 AND COMPLETED REWORK PER SRM 57-20-00, FIGURE 8, SHEET 1. (13 JUNE 1998)

Part: SKIN — CORRODED (BS 1236)

N2203 STA-VCE: AFTER REMOVAL OF CORROSION ON LOWER SKIN BETWEEN STA 1236 AND STA 1521, LONGERON NR 48 RT TO LONGERON NR 48 LT, MATERIAL REMOVED IS OUT OF LIMITS. MAJOR REPAIR PERFORMED IAW EA 8-5334-38436. (08 JULY 1998).

Part: LONGERON — DAMAGED (BS 1521-1541)

STA-VCE LONGERON NR 45, BETWEEN STA 1521 AND 1541 PRESENTS A PUNCHING DAMAGE NEAR THE 4TH HOLE IN THE MIDDLE ROW. MAJOR REPAIR PERFORMED IAW EA 8-5315-38441.

Part: BULKHEAD FITTING — CRACKED (BS 1156)

STA-VCE: RT FRONT SPAR TO Y=1156 BULKHEAD TEE FITTING WAS FOUND CRACKED. CRACK IS .450. MAJOR REPAIR PERFORMED IAW EA 8-5314-34480 B. (29 JUNE 1998).

Part: FAIRING — WORN (RT TE FLAP)

WEAR DAMAGE FOUND ON FITTING AND ACTUATOR FAIRING INBOARD FLAP RT AT STA XIF 265. MAJOR REPAIR PERFORMED IAW EA 8-5710-38425. BLENDED OUT WEAR ON FAIRING IAW SRM 57-00-01. TREATED AREA WITH ALODINE/PRIMER IAW SRM 51-21-01 (13 JUNE 1998).

Part: SKIN — CORRODED (WS 130-164)

STA-VCE NR 2 LEFT FUEL TANK LEAKS, FOUND DURING POSITIVE PRESSURE CHECK ON LOWER SURFACE XORS 130-164 STRINGER 16. MAJOR REPAIR PERFORMED IAW EA 8-5732-38428A. REMOVED AND REPLACED FASTENERS IAW SRM 51-31-01. REMOVED AND REPLACED DOUBLER IAW SRM 51-31-01 AND SRM 53-40-00 AND PER INSTRUCTION GIVEN ON EA 8-5732-38428A. REMOVED AND REINSTALLED COMPENSATOR PROBE NR 2 LEFT, REPLACED SEALANT DAMAGED AND REPLACED PACKING AND SHIM IAW M/M 28-41-01.

Part: RIB — WORN (LT WING)

DEEP WEAR ON NR 6 SLAT TRACK SUPPORT O/B SIDE, LT WING. MAJOR REPAIR PERFOMED IAW EA 8-5710-38424 BLENDED OUT AREA ON SLAT TRACK SUPPORT WITH 1.0 RAD MIN. PROTECTED AREA WITH ALODINE AND PRIMER IAW SRM 51-21-01. (10 MARCH 1998).

Part: ANGLE — CRACKED (AFT ENG INTAKE)

STA-VCE: AFT ENGINE AIR INTAKE DUCT: FOUND 1 CRACK 7 INCHES LONG AT 8 HOURS ON INTERNAL STEEL ANGLE, INTERNAL SIDE (CLOSE TO ACCESS PANEL 361BZ). MAJOR REPAIR PERFORMED IAW EA 8-5400-39555. TRIMMED OUT CRACK. NSTALLED FILLER IN THE TRIMMED AREA. INSTALLED REPAIR ANGLE.

Part: ANGLE — CRACKED (NR 2 ENGINE)

AFT ENGINE AIR INTAKE DUCT FOUND 1 CRACK 8 INCHES LONG AT 8 HOURS ON EXTERNAL STEEL ANGLE, INTERNAL SIDE, CLOSE TO ACCESS PANEL NR 3618Z. MAJOR REPAIR PERFORMED IAW EA 8-5400-39555. TRIMMED OUT CRACK, INSTALLED FILLER IN THE TRIMMED OUT AREA, INSTALLED REPAIR ANGLE. (16 JUNE 1998)