N357FE

Part: CONTROL PANEL — FAILED (COCKPIT) · airframe 99,603 hrs · 34,851 cycles

NR 2 ENGINE WOULD NOT RESTART AFTER BEING SHUTDOWN FOR A FUNCTIONAL TEST. INITIALLY ATTEMPTED AT FL 240 AND 250 KNOTS LATER AT 12,000 AND 250 KNOTS. IN ALL CASES THE N, WAS NORMINAL, FUEL FLOW NORMAL AND N2 WAS "X" OUT. REMOVED AND REPLACED IGNITION CONTROL PANEL.

Part: CONTROL PANEL — FAILED (IGNITION SYS) · airframe 99,603 hrs · 34,851 cycles

NR 2 ENGINE WOULD NOT RESTART AFTER BEING SHUTDOWN FOR A FUNCTIONAL TEST, INITIALLY ATTEMPTED AT FL 240 AND 250 KNOTS LATER AT 12000 AND 250 KNOTS, IN ALL CASES THE N1 WAS NORMAL, FUEL FLOW NORMAL, AND N2 WAS X OUT. FOUND OVERRIDE IGNTION SYSTEM INOP, REMOVED AND REPLACE WITH SERVICABLE ENG IGNITION PANEL P4-5900. PERFORMED OPS CHECK, ALL CHECKS GOOD REF MM 74-30-01-2 AND 74-10-01/201.

Part: DISCHARGE TUBE — DIRTY (NR 1 ENGINE) · airframe 99,603 hrs · 34,851 cycles

DURING FUNCTIONAL CHECK OF NR 1 ENGINE. ENGINE WOULD NOT RESTART AFTER BEING INTENSIONALY SHUT DOWN. INITIALLY NOTED AT 250 KNOTS / 24,000. ATTEMPTED TO START SEVERAL MORE TIMES DOWN TO 12,000 NO HELP. N1 AND N2 NORMAL FUEL FLOW NORMAL, EGT NEVER SHOWED ANY RISE. USING FIM SUBTASK 80-11-00-810-005 FOUND CDP DISCHARGE PORT CLOGGED. UNCLOGGED DISCHARGE PORT AND PURGED LINE WITH NITROGEN. RECONNECTED LINE PER AMM 73-20-01-2 STEP 3 B(21). PERFORMED ENGINE RUNS ON GROUND PER JRH CHAPTERS 4 AND 5. ALL ENGINE PARAMETERS WITHIN LIMITS.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 3 · airframe 99,598 hrs · 34,848 cycles

FABRICATE NEW DOUBLER AND ADD ADDITIONAL FASTENERS. REMOVED AND REPLACED DOUBLER PER EA 5330-T0340491 P1 AT STA 2020 RT SIDE BETWEEN L29 & L31. COMPLIED WITH WORK CARD EA T 8-5330-70340491 P1.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 99,598 hrs · 34,848 cycles

NR 3 ACM COMPT CEILING AT STA 595 AND LONGERON 29 AIR LEAK FOUND DURING PRESSURIZATION. INSTALLED REPAIRED ANGLE IN REF TO SRM 53-40-00,VOL1 FIG 28 AT NR 3 ACM COMPT CEILING STA 595 AND LONGERON 29.

Part: HINGE FITTING — WORN (TE FLAP) · airframe 99,598 hrs · 34,848 cycles

3EA WEAR GOUGES ON INBOARD FLAP O/B HINGE WING ATTACHED HINGE. PERFORMED REPAIR FOR WEAR DAMAGE TO HINGE FITTING IAW SRM 57-20-00 FIG 17 V1.

Part: PANEL — CORRODED (FUSELAGE) · airframe 99,598 hrs · 34,848 cycles

MAIN DECK RT TOP AFT CENTER WING BOX PANEL HAS CORROSION AROUND FASTENER AT BS 1305, RBL 19, STRINGER 6 AT BUTT SPLICE. REPAIRED IN REF TO EA 8-5730-T0-340530, P1.

Part: PANEL — CORRODED (BS 1335) · corrosion level 2 · airframe 99,598 hrs · 34,848 cycles

MAIN DECK, LEFT TOP OF AFT SLANT PANEL WAS SHOWING EXFOLIATION CORROSION AROUND FASTERNER HEADS AT BS 1335, LBL 106, STRINGER 3. BLENDED AND REMOVED THE CORROSION. REPAIRED IAW EA 8-5730-T0340530, P1, & SRM 57-20-00, FIG 8A, SHEETS 1-2, VOL 1.

Part: PANEL — CORRODED (FUSELAGE) · airframe 99,598 hrs · 34,848 cycles

MAIN DECK, LT TOP OF AFT SLANT PANEL (CENTER WING BOX) IS SHOWING EXFOLIATION CORROSION AROUND FASTENER HEADS AT BS 1335, LBL 98, STRINGER 3. REF PREVIOUSLY GENERATED SNRM N00720. REPAIRED IN REFF TO EA 8-5730-T0340530, P1.

Part: PANEL — CORRODED (MAIN DECK) · airframe 99,598 hrs · 34,848 cycles

MAIN DECK, LT TOP OF AFT SLANT PANEL WAS SHOWING EXFOLIATION CORROSION AROUND FASTERNER HEADS AT BS 1346, LBL 106, STRINGER 2. REPAIRED IAW EA 8-5730-T0340530, P1, & SRM 57-20-00, FIG 8A, SHEETS 1 - 2, VOL 1.

Part: SEAT TRACK — DAMAGED (BS 758) · airframe 99,598 hrs · 34,848 cycles

MAIN CABIN SEAT TRACK AT BS 758 HAD BROKEN LOBES. REMOVED AND REPLACED THE SEAT TRACK SECTION IAW SRM 53-70-00, FIG 2, SHEETS 1-2, VOL 1.

Part: SPAR WEB — CRACKED (NR 3 PYLON) · airframe 99,598 hrs · 34,848 cycles

NR 3 PYLON UPPER SPAR WEB HAS 21 EA HOLES WITH CRACK INDICATIONS. REMOVED AND REPLACED THE UPPER WEB TO AN UPGRADED WEB, IN REF TO EA 8-5450- T0340262, PART 1 ON THE NR 3 ENGINE, AFT OF THE TOMB STONE.

Part: SKIN SPLICE — CORRODED (RT WING) · airframe 99,598 hrs · 34,848 cycles

UPPER AUX TANK SKIN PANEL AT WS 1305, LONGERON 6, RBL 57, SKIN BUTT SPLICE IS HEAVILY CORRODED AROUND FASTENER HEAD. REPAIRED IAW EA 8-5730-T0340530, P1, & SRM 57-20-00, FIG 8A, VOL 1.

Part: SKIN — CORRODED (FUEL TANK) · airframe 99,598 hrs · 34,848 cycles

MAIN DECK, STA 1315, RBL 98, TANK SURFACE, CORROSION, MARKED IN RED PENCIL. REPAIRED IN REF TO EA 8-5730-T0340530, P1.

Part: FLOOR SUPPORT — CORRODED (BS 1781-1860) · airframe 99,598 hrs · 34,848 cycles

AFT LOWER CARGO BAY FLOOR SUPPORT HAD SURFACE CORROSION BS 1781 - 1860 ADJACENT AND ABOVE LATCH SPOOLS. REMOVED THE CORROSION IAW SRM 51-21-01.

Part: TEE FITTING — CRACKED (BS 595 BULKHEAD) · airframe 99,598 hrs · 34,848 cycles

BS 595 BULKHEAD TEE VERTICAL LEG AT LONGERON 39R HAS A .300 INCH CRACK AT THE LOWER FASTENER. REPAIRED IAW DWG SR10530064-7013.

Part: BRACKET — CRACKED (ZONE 100) · airframe 99,598 hrs · 34,848 cycles

AFT CARGO DOOR SILL, FWD SPOOL SUPPORT BRACKET IS CRACKED. REMOVED AND REPLACED BRACKET IAW SRM 51-33-01 AND DWG AFA3150-501.

Part: FITTING — CRACKED (FUSELAGE) · airframe 99,598 hrs · 34,848 cycles

LT STA 1156 SUGAR SCOOP FITTING HAS A 2.0 IN CRACK BETWEEN LONG 38L-39L. REPAIRED SUGAR SCOOP FITTING CRACK REF SRM 53-40-00 FIG 8 VOL 1.

Part: ATTACH ANGLE — CRACKED (NR 3 PYLON) · airframe 99,598 hrs · 34,848 cycles

NR 3 PYLON INSIDE ACCESS PANEL488BL, LOOKING ACROSS AND AFT, ATTACH ANGLE TO TOMBSTONE FITTING TO PYLON SKIN IS CRACKED FIVE INCHES FROM TOP. WELDED DAMAGED AREA AS PER AMM 20-90-00-8 AND DPS 10.225 SECTIONS 4.8 TO 4.8.7 AND GENERAL WELD PROCEDURES 5.4 TO 5.5.6. INSTALLED ANGLE REPAIR DOUBLER REF EA 8-5410-T0340275 "NACELLES/PYLONS- NR 3 PYLON-CRACKED AUB7023-4 ANGLE REPAIR"

Part: WEB — CRACKED (NR 1 PYLON) · airframe 99,598 hrs · 34,848 cycles

NR 1 PYLON INSIDE ACCESS PANEL 437CL, LT SIDE, STA YN210, PYLON WEB SKIN IS CRACKED APPROX TWO INCHES. REPAIR CRACKED PYLON WEB REF SRM 54-20-00 VOL 1 FIG 5A PAGE 20 AND SRM 51-33-01 VOL 2.

Part: WEB — CRACKED (BS 547) · airframe 99,598 hrs · 34,848 cycles

NOSE WHEEL WELL, BS 500, -Z=40. JUST FWD OF THE NR 3 PACK WW CUT OUT OPENING. THERE IS APPROXIMATELY A .250 INCH CRACK EMINATING FROM A RIVET HOLE. REPAIRED THE CRACKED AREA IAW SRM 53-30-00, FIG 6, PAGE 26, VOL.1.

Part: DOUBLER — CRACKED (LE SLAT) · airframe 99,598 hrs · 34,848 cycles

RT WING INBOARD OF SLAT TRACK 9, PILLOW DOUBLER HAS CRACK. REPAIRED RT I/B SLAT TRACK 9 PILLOW DOUBLER CRACK PER SRM-57-10-00 FIG 71 VOL 1.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 99,598 hrs · 34,848 cycles

LT STA 595 BULKHEAD TEE CAP VERTICAL LEG AT LONG 39L HAS A .800 INCH CRACK AT THE LOWER FASTENER. REPAIRED LT TEE-CAP REF EA 8-5310-T0340063 P1/P2.

Part: DOUBLER — CRACKED (LE SLAT) · airframe 99,598 hrs · 34,848 cycles

RT WING INBOARD OF SLAT TRACK 9, PILLOW DOUBLER HAS CRACK. REPAIRED RT I/B SLAT TRACK 9 PILLOW DOUBLER CRACK PER SRM-57-10-00 FIG 71 VOL 1.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 99,598 hrs · 34,848 cycles

LT STA 595 BULKHEAD TEE CAP VERTICAL LEG AT LONG 43L HAS A .300 INCH CRACK AT THE LOWER FASTENER. REPAIRED LT TEE-CAP REF EA 8-5310-T0340063 P1/P2.

Part: SKIN — CRACKED (RT WING) · airframe 99,598 hrs · 34,848 cycles

RIGHT WING SKIN AT SLAT ANTI-ICE TELESCOPING DUCT CUTOUT, UPPER INBOARD CORNER HAD A .600 INCH CRACK AND UPPER OUTBOARD CORNER HAS A .300 IN. CRACK. REPAIRED IAW SRM 57-10-00, FIG 103, VOL 1.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 99,598 hrs · 34,848 cycles

MAIN DECK COMPARTMENT - SEAT TRACK AT STA 889 RBL 110 IS WORN. REMOVED AND REPLACED SECTION OF SEAT TRACK (PLUG) IN REF TO SRM 53-70-00 FIG 2 SHEETS 1-2, VOL 1 AND SRM 51-30-01 VOL 2.

Part: PANEL — DELAMINATED (LT WING) · airframe 99,598 hrs · 34,848 cycles

LT WING UPPER SURFACE INBD, TRAPEZOIDAL PANEL ARC0269. TOP SURFACE SHOWS SUSPECTED DELAMINATION AREA MARKED REPAIR PER SRM 57-71-00 VOL 2.

Part: SKIN — CRACKED (LT WING) · airframe 99,598 hrs · 34,848 cycles

LEFT WING SKIN AT THE SLAT ANTI-ICE TELESCOPING DUCT CUTOUT, UPPER INBOARD CORNER HAS A .900 INCH CRACK AND UPPER OUTBOARD CORNER HAS A .500 INCH CRACK. REPAIRED THE LT WING SKIN AT SLAT ANTI-ICE TELESCOPING DUCT CUTOUT IAW SRM 57-10-00 FIG 103 SHEETS 1-6 VOL 1

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 99,598 hrs · 34,848 cycles

FWD CARGO DOOR AFT LOWER CORNER DAMAGE. REPAIR DAMAGED LOWER CORNER REF SRM 52-10-00 FIG 17 VOL 1.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 99,598 hrs · 34,848 cycles

FWD CARGO DOOR BOTTOM EDGE FWD OF AFT CORNER DAMAGE. REPAIR DAMAGED BOTTOM EDGE REF SRM 52-10-00 FIG 17 VOL 1.

Part: VALVE — DAMAGED (FUEL TANK) · airframe 99,489 hrs · 34,774 cycles

DURING DESCENT FROM FL350 TO FL290, RECEIVED A TANK 3 TIP TRAPPED LEVEL 1 ALERT, WITH ASSOCIATED 5800 LBS UNUSABLE AND A TANK 3 PUMPS OFF ALERTS. PASSING 8000 FT, TRAPPED ALERT WENT AWAY, BUT THE NR 2 TANK KEPT FEEDING NR 3. INSPECTED TIP TANK TRANSFER SYSTEM AND FOUND THE NR 3 MAIN TANK OTBD TRANSFER FLOAT VALVE BROKEN AND INBD TRANSFER FLOAT VALVE STICKING. REMOVED AND REPLACED BOTH TRANSFER FLOAT VALVES. LEAK AND OPS CHECKED GOOD IAW FIM 28-14-04, TASK 28-14-00-810-803. AMM 28-00-00-2, AND AMM 28-21-10-2.

Part: FLOAT VALVE — FAILED (FUEL TANK 3) · airframe 99,281 hrs · 34,635 cycles

2.44 HRS INTO FLIGHT, RECEIVED A TANK 3 TIP TRAPPED LVL 1 ALERT. REMOVED & REPLACED INBD. TRANSFER FLOAT VALVE, NR 3 TANK IAW MM 28-21-10-2, & OPS. CHECKED NORMAL.

Part: POWER SUPPLY — NO TEST (EMERGENCY LIGHTS) · airframe 97,497 hrs · 33,630 cycles

EMERGENCY BATTERY 1 LOW, ALERT DURING EMERGENCY LIGHTS TEST ON PREFLIGHT. TEST FAILED FOR POWER SUPPLY ASSY. REMOVED AND REPLACED THE POWER SUPPLY IAW MM 33-51-01-4 AND TESTED IAW MM 33-51-00-5. TEST PASSED. ACFT OK FOR SERVICE.

Part: LANDING GEAR — MALFUNCTIONED · airframe 96,967 hrs · 33,356 cycles

LOWERED GEAR AT 220KTS TO AID IN DESCENT. WHEN GEAR WAS RAISED AT 220 KTS LEFT AND RIGHT MAIN GEAR INDICATED IN TRANSIT ON CONFIGURATION PAGE AND INDICATOR LIGHTS ABOVE GEAR HANDLE. RESEATED GEAR HANDLE WITH NO EFFECT. THERE WAS AIRFRAME VIBRATION AND ASSOCIATED NOISE THAT INDICATED GEAR WAS STILL DOWN OR DOORS WERE STILL OPEN. LOWERED GEAR AND RECEIVED 3 GREEN. PERFORMED GVI OF LT, RT AND NLG, NO DEFECTS NOTED. JACKED AND SWUNG GEARS IAW 32-30-00-5, 3 SUCCESSFUL CYCLES. OK FOR SERVICE.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 96,868 hrs · 33,300 cycles

EMERGENCY LIGHTS ARE INOPERATIVE, TROUBLESHOT, 115VAC PRESENT AT PIN 6 & 5 OF P1-1756A, NO 28VDC AT PIN 8 OF P1-1756A, NO 28VDC AT TERMINAL D2 OF SWITCH S1-346. GOOD 28VDC COMING OFF C/B B1-907 EMERGENCY LIGHTS ARM UNABLE TO TROUBLESHOOT FURTHER TO FIND OPEN IN WIRE B201-151-22 OR B203- 917-22 OR B213-1-22. EMERGENCY LIGHTS TEST PASSES AND LIGHTS COME ON WHEN PLACED TO ON, TRIED NUMEROUS TIMES WITH TIME INTERVALS, SYSTEM OK. SUSPECT LOW BATTERY ON LAST TEST FAILURE.

Part: MOTOR — FAILED (L1 DOOR) · airframe 96,859 hrs · 33,297 cycles

L-1 DOOR WILL NOT FREE FALL WHEN ENGAGED. REPLACED L-1 DOOR ELECTRIC DRIVE MOTOR IAW AMM 52-11-01-2. OPS CHECK GOOD, PN 6322A0001-04, SN 1744.

Part: WIRE — BROKEN (R1 DOOR) · airframe 96,714 hrs · 33,223 cycles

R1 DOOR EMER DOOR SLIDE TEST SWITCH INOPERATIVE ON PRE-FLIGHT. RELEASED FOR SERVICE IAW MEL 25-61-01, CATEGORY C, EXPIRATION 03 JUN 16. EVAC SLIDE REMOTE PRESS INDICATOR INOPERATIVE. VERIFY & RECORD IN THE AML, EVAC SLIDE SYS PRESS ONCE EACH FLIGHT DAY. FOUND R1 WIRE BROKEN AT BATTERY PACK. SYS VERIFIED IAW MEL 25-61-01. ACFT OK FOR SERVICE. CONTROL 7051045, EXP 03 JUNE 16, C 7051045 PART, 24 MAY 16 19:46. IDENTIFIED PARTS MPN 17528-2, CPN 2511426, QTY 1. R & R BATTERY PACK & LIGHT ASSEMBLY IAW 25-61-01-2-0. OPERATIONS CHECKED GOOD.

Part: PANEL — CORRODED (LT WING) · airframe 96,691 hrs · 33,212 cycles

LEFT WING LOWER SURFACE FUEL VLV PANEL, LAND HAS EXFOLIATED CORROSION. CLEANED CORROSION & FABRICATED REPAIR DOUBLERS & FILLERS IAW 57-10-00.

Part: LANDING — CRACKED (LT WING) · airframe 96,691 hrs · 33,212 cycles

CRACK ON LT ACFT STRUCTURE PANEL 519AB LANDING FWD END, JUST INBD OF FUEL ACCESS PANEL. FABRICATED REPLACEMENT DOUBLER IAW DWG ARB 1180.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 96,691 hrs · 33,212 cycles

CENTER WW FLOOR STIFFENER, CRACKED AT CTR LINE, APPROX STATION 1471. R & R IAW DWG AEA 0276-1 & SRM 51-31-01.

Part: SKIN — CRACKED (LT WING) · airframe 96,691 hrs · 33,212 cycles

LEFT WING FIXED LE ABOVE NR 1 PYLON, INBD OF SLAT NR 3 THERE IS A CRACK. INSTALLED FILLER & DOUBLER IAW SRM 57-00-01.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 96,691 hrs · 33,212 cycles

R3 DOOR FWD JAMB, UPPER CORNER CRACKED. REMOVED DOUBLER, STOPPED DRILLED CRACK & INSTALLED NEW DOUBLER.

Part: SKIN — DENTED (FUSELAGE) · airframe 96,691 hrs · 33,212 cycles

LOWER FUSELAGE, SEVERAL DENTS IN OUTER SKIN LOCATED JUST FWD OF LOWER FWD CARGO DOOR, APPROX STATION 879, BETWEEN LONGERON 35 - 36. INSTALLED REPAIR IAW SRM 53-20-00 FIG 6.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 96,691 hrs · 33,212 cycles

MAIN CABIN L3 DOOR, FWD DOOR JAMB, UPPER WEB CRACKED. REMOVED THE AEA 0530-19 DOUBLER & INSTALLED THE -7 REPAIR DOUBLER, STOP DRILLED CRACK IAW SRM 53-50-00 VOL I FIG 19 SHEET 1. FABRICATE NR 7 DOUBLER IAW SRM 53-50-00 FIG 19 7075-0 063 HEAT TREAT REQUIRED. HEAT TREATED IAW DPS 7.00-1 SEE ATTACHED. INSTALLED REPAIR -7 DOUBLER IAW SRM 53-50-00 FIG 19.

Part: SEAT TRACK — BROKEN (FUSELAGE) · airframe 96,691 hrs · 33,212 cycles

MAIN CABIN SEAT TRACK HAS BROKEN LUG AT LOCK POSITION AT STATION 755, LBL 47 SPLICE IN NEW SECTION OF SEAT TRACK IAW SRM 53-70-00.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 96,691 hrs · 33,212 cycles

MAIN CABIN RT SIDE R3 DOOR AFT DOOR JAMB, UPPER CORNER CRACKED AT WEB. DRILL STOP CRACK, INSTALLED NEW 14 DOUBLER IAW SRM 53-50-00 VOL I FIG 19 SHEET 2 05 11 16. NDT TO VERIFY CRACK. COMPLIED WITH HFEC REF NDTSPM PART 06. VERIFIED & MARKED END OF CRACK. FABRICATE 14 DOUBLER IAW SRM 53-50-00 FIG 19 7075-0 .063. HEAT TREATED IAW DPS 7.00-1. INSTALLED 14 DOUBLER IAW SRM 53-50-00 VOL I FIG 9 SHEET 2 05 04 16.

Part: STRUCTURE — CRACKED (LT WING) · airframe 96,691 hrs · 33,212 cycles

LEFT WING AT FIXED LE ABOVE NR 1 PYLON INBD OF SLAT, NR 3 THERE IS A CRACK. FABRICATED FILLER & DOUBLER IAW EA 8-5710-T0325356.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 96,691 hrs · 33,212 cycles

MAIN DECK, FROM STATION 1600 TO NEAR STATION 1661, RBL 8 SEAT TRACK DAMAGED. SPLICED IN NEW SECTION OF SEAT TRACK IAW SRM 53-70-00.

Part: SEAT TRACK — GOUGED (FUSELAGE) · airframe 96,691 hrs · 33,212 cycles

MAIN DECK STATION 1661, RBL 27 SEAT TRACK SHOWS GOUGES & WEAR MARKS. R & R DAMAGED SECTION OF SEAT TRACK SRM 53-70-00 VOL I.

Part: UNION — LEAKING (HYDRAULIC SYS) · airframe 96,275 hrs · 33,001 cycles

LEVEL 1 ALERT HYD 3 ELEV OFF AUTO PILOT 1 DISCONNECTED. FOUND MLG RETRACT CYLINDER PACKING THAT GOES AROUND RETAINER CUT. R & R UNION ASSEMBLY PN S4932412T8 & ASSOCIATED SEALS IAW IPC 32-34-05-01 ITEMS 525, 530 & 535. ADDED SUFFICIENT HYD FLUID TO PERFORM LEAK CHECK. PERFORMED LEAK CHECK IAW AMM 29-00-00-2-0.

Part: PRESSURE SWITCH — FAILED (BLEED AIR SYS) · airframe 96,259 hrs · 32,993 cycles

LEVEL 3 AIR MANIFOLD 1 FAIL AT FL 370. BLEED & PACK CONFIGURATION AT TIME OF FAILURE WAS NR 1 & 2 BLEEDS & PACKS ON. NR 3 BLEED & PACK OFF & 1 - 3 ISOL VLV OPEN. AFTER RUNNING QRH PROCEDURES THE NR 1 MANIFOLD SHOWED RED ON AIR SYNOPTIC FOR 10 - 15 MINUTES. FOUND LT WING DIFFERENTIAL PRESSURE SWITCH INDICATOR TRIPPED IN CAC. R & R LT WING DIFFERENTIAL PRESS SWITCH IAW MM 36-23-03-4. OPERATIONS TEST PERFORMED IAW 36-23-03-5. OPERATIONS CHECKED NORMAL. ACFT OK FOR SERVICE. IAW GMM 12-7-600 SDR PART INFO, WING MANIFOLD FAIL DET SWITCH.

Part: LAMP — INOPERATIVE (R1 DOOR) · airframe 96,162 hrs · 32,940 cycles

R1 DOOR REMOTE PRESSURE PRESS TO TEST INOPERATIVE. REPLACED THE LAM IAW MM 25-61-03-2 OPS CHECKS GOOD PER M/M 25-61-03-5 A/C OK FOR SERVICE.

Part: LAMP — INOPERATIVE (R1 DOOR) · airframe 96,163 hrs · 32,941 cycles

R1 DOOR REMOTE PRESSURE PRESS TO TEST INOPERATIVE. REPLACED THE LAMP. OPS CHECKED GOOD. OK FOR SERVICE.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 95,973 hrs · 32,833 cycles

LOAD CREW FOUND LOCK MISSING BETWEEN POSITIONS 7L & 8L. FOUND DAMAGE TO SEAT TRACK LOBE ONLY. SHEET METAL WILL REQUIRE 16 HOURS TO REPAIR SEAT TRACK. ALL PARTS NEEDED FOR REPAIR ON HAND. REMOVED LOADING SYS & FLOORBOARDS IAW AMM 25-52-00 & 53-21-01-2. CUT OUT DAMAGED TRACK SECTION & CUT NEW TRACK TO LENGTH, DRILLED UP & COUNTERSUNK PARTS IAW SRM 53-70-00 & SR10-53-002. INSTALLED NEW SEAT TRACK SECTION IAW SRM 53-70-00, NEED TO INSTALL FLOORBOARDS & LOADING SYS.

Part: CONTROL VALVE — INOPERATIVE (ANTI-SKID SYS) · airframe 957 hrs · 32,685 cycles

NUMBER 4 BRAKE FAILED BRAKE RELEASE TEST ON SYS 1. MEL 32-45-01-01-B ANTI-SKID CONTROL VLV INOPERATIVE. ONE WHEEL BRAKE INOPERATIVE. R&R IAW MD10-10 MM. OPS CHECKS GOOD NO FAULTS NOTED.

Part: INDICATOR — INOPERATIVE (R1 DOOR) · airframe 956 hrs · 32,630 cycles

R1 DOOR EVACUATION SLIDE REMOTE PRESSURE PRESS TO TEST INOPERATIVE. RELEASED FOR SERVICE IAW MEL 25-61-01, CATEGORY C EXPIRATION 14 AUG 15. EVAC SLIDE REMOTE PRESS INDICATOR INOPERATIVE. VERIFY & RECORD IN THE AML, EVAC SLIDE SYSTEM PRESS ONCE EACH FLIGHT DAY. PERFORMED SLIDE PRESSURE CHECK USING METHOD B. SLIDE PRESSURE IS IN GREEN BAND. AIRCRAFT OK TO CONTINUE. ITEM PLACED ON MEL.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 955 hrs · 32,580 cycles

LOCK AT POSITION 6L & 7L Q1262 CAME OUT OF TRACK. SEAT TRACK IS DAMAGED. RELEASED FOR SERVICE IAW MEL 25-57-02-A2 CATEGORY A, EXPIRATION 03 AUG1 5. REQUIRES SHEET METAL EVALUATION & REPAIR. REPLACED SEAT TRACK.

Part: SKIN — CRACKED (LT WING) · airframe 94,157 hrs · 31,771 cycles

CRACK IN LE AT NR 12 SLAT CUT OUT ON LT WING. HFEC INSPECTED LT WING AND VERIFIED CRACK. REPAIRED IAW EA8-5710-T0309287.

Part: STIFFENER — CRACKED (BS 1156 BULKHEAD) · airframe 94,046 hrs · 31,717 cycles

RIGHT BULKHEAD TEE AT BS 1156 CANTED VERTICAL LEG HAS CRACK INDICATIONS.

Part: STIFFENER — CRACKED (BS 1156 BULKHEAD) · airframe 94,046 hrs · 31,717 cycles

LEFT BULKHEAD TEE AT BS 1156, CANTED VERTICAL LEG HAS ONE CRACK APPROXIMATELY .5 INCHES.

Part: CONTROLLER — MALFUNCTIONED (HYD SYSTEM) · airframe 93,033 hrs · 31,173 cycles

AT LEVEL CRUISE 330. RECEIVED A HYD OFF (LEVEL 1 ALERT). SWITCH TO NR 1 AUTO PILOT AND CONSULTED QRH. HYD SYS TEMP CONTINUED TO INCREASE. IAW CONTINGENCY DIVERT. NORMAL OPS DURING APPROACH AND LANDING. R & R HYD SYS CONTROLLER & RTS GOOD IN REF WITH AMM 29-08-01-2.

Part: SLAT SYSTEM — MALFUNCTIONED · airframe 92,593 hrs · 30,915 cycles

EXTENDING FLAPS 35 FOR LANDING, RECEIVED A LEVEL 2 SLAT DISAGREE AND FLAP DISAGREE ALERTS. TRIED SECOND TIME. ON SECOND ATTEMPT, FLAPS AND SLATS EXTENDED NORMAL WITH NORMAL LANDING, INBOUND PILOT OPS CHECKED THE FLAP/SLAT SYS WITH NORMAL OPS ON SECOND TIME. PERFORMED FLAPS ADJUSTMENT AND TEST IAW MM 27-50-00-5-1, ITEM D FLAP HYD ACTUATION SYS OPERATED NORMAL. FCC SENSOR READOUT WITHIN TOLERANCE OF -2 DEGREES. ACFT OK FOR SERVICE.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 92,273 hrs · 30,740 cycles

DURING SERVICE CHECK, FOUND EMERGENCY LT BATTERY 1 LOW MESSAGE ON EAD. FOUND PWR SUPPLY AT FAULT. BATTERY POWER SUPPLY REMOVAL AND INSTALLATION C/O IAW AMM 33-51-01-4 AND OPS CHECKED, NO DESCREPANCIES NOTED IN THE SYS. ACFT OK FOR SERVICE.

Part: SKIN — DAMAGED (LT INBD) · airframe 91,699 hrs · 30,413 cycles

LT INBD FLAP LOWER SKIN HAS GRAVEL DAMAGE. REPAIRED LEFT INBD FLAP LOWER SKIN DAMAGE IAW SRM 57-10-00, 57-00-01, FIG 3 AND 51-31-01. MAJOR REPAIR.

Part: SKIN — MISREPAIRED (BS 1761) · airframe 91,699 hrs · 30,413 cycles

FUSELAGE SKIN AT 1761, L40L AND L41L MISREPAIRED. REPAIRED IAW SRM 53-20-00, FIG 6. MAJOR REPAIR.

Part: PULLEY — WORN (L1 DOOR) · airframe 91,699 hrs · 30,413 cycles

L1 UPPER AFT DOOR FRAME DRIVE CABLE PULLEY WORN REMOVED AND REPLACED PULLEY ASSY IAW SRM 51-31-01. NO RIG DISTURBED. OPS CHECKED GOOD IAW AMM 52-11-00-5. MINOR REPAIR.

Part: SKIN — MISREPAIRED (BS 635-655) · airframe 91,699 hrs · 30,413 cycles

SKIN AT BS 635 - 655, L49-52L, MISREPAIRED. REPAIRED IAW SRM 53-20-00 FIG 6. MAJOR REPAIR.

Part: SKIN — MISREPAIRED (BS 1851 L46-48L) · airframe 91,699 hrs · 30,413 cycles

SKIN BS 1851 , BETWEEN L46 & 48L MISREPAIRED. REPAIRED IAW SRM 51-31-01, HFEC INSPECTED CUT OUT IAW NTSPM 06-10-01 NO CRACK INDICATIONS NOTED.

Part: FRAME — CORRODED (BS 1964) · airframe 91,699 hrs · 30,413 cycles

AFT CARGO, AT BS 1964 ABOVE L48L UPPER SIDE OF FRAME IS CORRODED. REPAIRED UPPER SIDE OF FRAME IAW SRM 53-30-00 FIG 4. MAJOR REPAIR.

Part: SKIN — MISREPAIRED (BS 615-635) · airframe 91,699 hrs · 30,413 cycles

SKIN AT STA 615 - 635, L48-49L MISREPAIRED. REPAIRED IAW SRM 53-20-00.

Part: FRAME — CRACKED (BS 1159) · airframe 91,699 hrs · 30,413 cycles

FUSELAGE FRAME AT BS 1159 IS CRACKED AT THE LOWER INBD LEG. REPAIRED FRAME IAW SRM 53-30-00 FIG 7. MAJOR REPAIR.

Part: SKIN — MISREPAIRED (BS 1811, L50R) · airframe 91,699 hrs · 30,413 cycles

SKIN AT BS 1811, L50R, MISREPAIRED. REPAIRED IAW SRM 53-20-00, FIG 6.

Part: FRAME — CORRODED (BS 1997) · airframe 91,699 hrs · 30,413 cycles

AFT CARGO BILGE AT BS 1997, L51L TO 51R HAS SURFACE CORROSION ON FRAME. BLENDED CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-00-01. ORIGINAL MATERIAL 0.071 , MATERIAL LOSS 0.028 , MATERIAL AFTER REWORK 0.043. FABRICATED , TREATED AND PRIMED IAW SRM 51-21-01. INSTALLED REPAIR CHANNEL IAW SRM 51-33-01. APPLIED TOP COAT IAW SRM 51 21-02. MAJOR REPAIR

Part: SKIN — MISREPAIRED (BS 1009) · airframe 91,699 hrs · 30,413 cycles

SKIN AT BS 1009 MISREPAIRED. REPAIRED IAW SRM 53-20-00, FIG 6.

Part: FRAME — CRACKED (BS 1159) · airframe 91,699 hrs · 30,413 cycles

FUSELAGE FRAME AT BS 1159 IS CRACKED AT INBD LOWER LEG. REPAIRED IAW SRM 53-30-00 FIG 7. MAJOR REPAIR.

Part: PULLEY — WORN (L1 DOOR) · airframe 91,699 hrs · 30,413 cycles

L1 UPPER FWD DOOR FRAME DRIVE CABLE PULLEY IS WORN. R & R PULLEY ASSY IAW SRM 51-31-01. NO RIG DISTURBED. OPS CHECKED GOOD IAW AMM 52-11-00-5. MINOR REPAIR.

Part: SKIN — MISREPAIRED (BS 1781) · airframe 91,699 hrs · 30,413 cycles

LOWER FUSELAGE SKIN BS 1781 BETWEEN L48L TO L49L MISREPAIRED. REPAIRED IAW SRM53-20-00, FIG 6.

Part: PULLEY — WORN (R1 DOOR) · airframe 91,699 hrs · 30,413 cycles

R1 DOOR UPPER AFT DOOR FRAME PULLEY WORN. REPLACED PULLEY ASSY IAW SRM 51-31-01. OPS CHECKED GOOD IAW AMM 52-11-00-5. NO RIGGING DISTURBED. MINOR REPAIR. EES REPAIR.

Part: PULLEY — WORN (R1 DOOR) · airframe 91,699 hrs · 30,413 cycles

R1 DOOR UPPER FWD DOOR FRAME DRIVE CABLE PULLEY WORN REPLACED PULLEY ASSY IAW SRM 51-31-01. NO RIG DISTURBED. OPS CHECKED GOOD IAW AMM 52-11-00-5, MINOR REPAIR.

Part: SKIN — CORRODED (BS 1119) · airframe 91,485 hrs · 30,285 cycles

CORROSION FOUND ON FUSELAGE SKIN AT STA 1119. REPAIRED SKIN IAW SRM 53-20-00, FIG 6 SHEET 5 AND 6. MAJOR REPAIR.

Part: UNKNOWN — ODOR (COCKPIT) · airframe 90,987 hrs · 30,016 cycles

STRONG ODOR PRESENT ON ACFT. COULD SMELL IN COURIER COMPARTMENT AND COCKPIT. CALLED MX, COULD NOT ID CAUSE/SOURCE. ADHESIVE ODOR FROM REPLACING FUSELAGE INSULATION IN FWD AVIONICS COMPT, ODOR STRONGER WHEN WE SET T/O PWR (MAX) FOR TAKEOFF. SMELLED MORE LIKE KEROSENE. . UPON ENTERING FLT DECK NO NOTICABLE ODOR PRESENT. SPOKE WITH JUMPSEATER AND THEY ONLY NOTICED A SLIGHT ODOR UPON ENTERING ACFT. OPENED FWD AND W/W HATCHES FOR VENTILATION WHILE ON GRND. AS A PRECAUTION CHANGED NR 1,NR 2 & NR 3 PACK COALESCER BAGS IAW AMM 21-54-03-2. SECURED FWD AND W/W HATCHES AND REPLACED SECURITY TAPE IAW SMP.

Part: BATTERY — DISCHARGED (EMERGENCY LIGHTS) · airframe 90,353 hrs · 29,646 cycles

THE R1 DOOR LIGHT DOES NOT TEST. SUSPECT BATTERIES. INSTALLED NEW BATTERIES IN R1 DOOR, IAW SMP. R1 DOOR LIGHT OPS CHECK GOOD. ACFT OK TO CONTINUE. FINAL CLOSED

Part: FITTING — CRACKED (ZONE 200) · airframe 89,473 hrs · 29,178 cycles

NR 6 SPOOL FITTING LOCATION HAS CRACK INDICATIONS AT HOLES "A", "B", "C" AND "D". R & R NR 6 SPOOL FITTING IAW SRM 51-31-01, VOL I, SRM 53-50-00, FIG 17, VOL I AND EA 8-5310-123543 "FUSELAGE -JAMB LOWER SILL OVERSIZE HOLES AT NR 1 -NR 7 SPOOL FITTING LOCATIONS - REPAIR".

Part: FLOOR PANEL — DELAMINATED (CARGO BAY) · airframe 89,473 hrs · 29,178 cycles

FWD CARGO PIT FLOOR PANEL 123 TF IS DELAMINATED. FABRICATED NEW FWD CARGO PIT FLOOR PANEL 123 TF IAW FEDEX DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 HF IS DELAMINATED FROM STA 735 - 795; RBL 48. FABRICATED NEW FLOOR PANEL IAW DWG SRZ 25-005, REV "H".

Part: FRAME — CORRODED (BS 1791 BULKHEAD) · corrosion level 2 · airframe 89,473 hrs · 29,178 cycles

AFT CARGO COMPARTMENT UNDER FLOOR AREA; THE BULKHEAD LOWER CHORD DOUBLER IS CORRODED UNDER AND AROUND NUTPLATE AT FS 1791. BL 0. REMOVED DAMAGED SECTION AND DOUBLER ON FRAME REF SRM 53-00-01, VOL I. FABRICATED NEW FRAME SECTION & 2 EA SPLICE ANGLES REF DWG AFA 3878, REV "AS" & SRM 53-00-01, VOL I. ALODINED & PRIMED REF SRM 51-21-01, VOL II & INSTALLED REF SRM 53-00-01, VOL I. 1EA SPLICE DOUBLER ANGLE CRACKED. FABRICATED NEW ANGLE REF SRM 53-00-01, VOL I. ALODINED & PRIMED REF SRM 53-00-01, VOL I. INSTALLED REF SRM 53-00-01, VOL I.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 89,473 hrs · 29,178 cycles

AFT CARGO COMPARTMENT BILGE AREA AT FS 1841 L50-51R; FRAME LOWER SECTION IS CORRODED. REMOVED AFT CARGO COMPARTMENT BILGE AREA LOWER FRAME SECTION PER SRM 51-33-01, VOL II. FORMED SECTION AND 2 SPLICES REF DWG AGA 3789, REV "M" AND SRM 53-00-01, FIG 8, VOL I. FRAME LOWER SECTION FOUND TO HAVE 100% MATERIAL LOSS AND IS OUT OF LIMITS PER SRM 53-00-01, FIG 1-B, VOL I. FABRICATED, LOCATED AND DRILLED FRAME LOWER SECTION REPAIR SECTION AND 2 SPLICES PER SRM 53-00-01, FIG 8, VOL I. ALODINED IAW SRM 51-21-01, PARA 31, VOL II. PRIMED PER SRM 51-20-01, PARA 24, VOL II. INSTALLED PER SRM 51-33-01, VOL II. PAINTED PER SRM 51-21-02, VOL II.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 89,473 hrs · 29,178 cycles

CENTER PIT FLOOR PANEL 183 RF IS DELAMINATED. FABRICATED NEW FLOOR BOARD 183 RF IAW DWG SRZ 25-005, REV "H".

Part: LATCH — WORN (ACCESS PANEL) · airframe 89,473 hrs · 29,178 cycles

NR 2 ENGINE PYLON ACCESS PANEL, 457 CL ON LT SIDE HAS WORN LATCHES. LATCH LANDS FOUND TO BE OUT OF LIMITS IAW SRM 54-00-01, VOL I. FABRICATED NEW DOUBLER AND INSTALLED IAW DAC DWG AVB7332 AND SRM 51-33-01, VOL II.

Part: FITTING — UNKNOWN (ZONE 200) · airframe 89,473 hrs · 29,178 cycles

MCD NR 4 SPOOL FITTING REQUIRES REPLACEMENT. R & R NR 4 SPOOL FITTING IAW SRM 51-31-01, VOL II, SRM 51-10-00, VOL I.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · airframe 89,473 hrs · 29,178 cycles

LT OTBD FLAP; OTBD HINGE FITTING LOCATION NR3 OTBD BORE IS CORRODED. REPAIRED FLAP HINGE FITTING NR 3 OTBD BORE IAW EA NR 8-5740-136666.

Part: HINGE FITTING — CORRODED (ZONE 800) · corrosion level 2 · airframe 89,473 hrs · 29,178 cycles

CENTER CARGO DOOR HINGE IS CORRODED. REPLACED HINGE SECTION P/N ACA 0012-539 AND P/N ACA 0012-541 IAW SRM 51-31-01, VOL II. REMOVED CORROSION ON HINGE SECTION P/N ACA 0012-543 AND FOUND TO BE IN LIMITS IAW SRM 52-10-00, FIG 8, VOL I. REMOVED CORROSION ON HINGE SECTION P/N ACA 0012-545 AND FOUND TO BE IN LIMITS IAW SRM 52-10-00, FIG 8, VOL I. ALODINED AND PRIMED -543 AND -545 HINGE SECTIONS IAW SRM 51-21-01, VOL I. REMOVED AND REINSTALLED CENTER CARGO DOOR IAW AMM 52-32-04-2.

Part: SKIN — CHAFED (ZONE 500) · airframe 89,473 hrs · 29,178 cycles

LT WING LEADING EDGE SKIN IS CHAFED BY THE NR 5 SLAT BETWEEN THE INBD AND OUTBD TRACKS. BLENDED CHAFED AREA AND FOUND TO BE OUT OF LIMITS IAW SRM 57-10-00, FIG 37, VOL I. REMOVED FASTENERS IAW SRM 51-35-01, VOL II. FABRICATED DOUBLER IAW SRM 57-10-00, FIG 40, VOL I. ALODINED AND PRIMED IAW SRM 51-21-01, VOL II. INSTALLED REPAIR DOUBLER IAW SRM 57-10-00, FIG 40, VOL I.

Part: STIFFENER — CRACKED (RT WING) · airframe 89,473 hrs · 29,178 cycles

RT WING L/E STIFFENER IS CRACKED BETWEEN WING STATIONS XORS 560 AND XORS 565. ACCOMPLISHED HFEC IAW NTSPM 06-10-01.001 TO VERIFY AND OF CRACK. REPAIRED CRACKED STRINGER IAW EA 8-5710-136667.

Part: STIFFENER — CRACKED (RT WING) · airframe 89,473 hrs · 29,178 cycles

RT WING L/E STIFFENER IS CRACKED BETWEEN WING STATIONS XORS 560 AND XORS 565.

Part: FLOOR PANEL — DELAMINATED (BS 795-879) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 FF IS DELAMINATED FROM STA 795 TO 879, RBL 48. FABRICATED NEW FLOOR PANEL 123 FF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — GOUGED (BS 919-959) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 QF FROM STA 919 TO 959, LBL 24 IS GOUGED. FABRICATED NEW FLOOR PANEL 123 QF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 1601-1701) · airframe 89,473 hrs · 29,178 cycles

CTR PIT FLOOR PANEL 183 XF IS DELAMINATED FROM STA 1601 TO 1701, RBL 48. FABRICATED NEW FLOOR PANEL 183 XF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — GOUGED (BS 979-1059) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 JD FROM STA 979 TO 1059, LBL 48 IS GOUGED. FABRICATED NEW FLOOR PANEL 123 JD IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DAMAGED (BS 879-959) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 SF FROM STA 879 TO 959, LBL 12 HAS BROKEN INSERTS. FABRICATED NEW FLOOR PANEL 123 SF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 675-735) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 LF IS DELAMINATED FROM STA 675 TO 735, RBL 48. FABRICATED NEW FLOOR PANEL 123 LF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 1601-1701) · airframe 89,473 hrs · 29,178 cycles

CTR PIT FLOOR PANEL 183 BF IS DELAMINATED FROM STA 1601 TO 1701, LBL 48. FABRICATED NEW FLOOR PANEL 183 BF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 879-919) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 CD FROM STA 879 TO 919, RBL 48 IS DELAMINATED. FABRICATED NEW FLOOR PANEL 123 CD IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 879-959) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 XF FROM STA 879 TO 959, RBL 12 IS DELAMINATED. FABRICATED NEW FLOOR PANEL 123 XF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 959-979) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 KF IS DELAMINATED FROM STA 959 TO 979, LBL 48. FABRICATED NEW FLOOR PANEL 123 KF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 919-959) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 DD FROM STA 919 TO 959, RBL 48 IS DELAMINATED. FABRICATED NEW FWD PIT FLOORBOARD 123 DD IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 899-919) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 WF FROM STA 899 TO 919, BL 0 IS DELAMINATED. FABRICATED NEW FLOOR PANEL 123 WF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 879-899) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 UF FROM STA 879 TO 899, BL 0 IS DELAMINATED. FABRICATED NEW FLOOR PANEL 123 UF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — BROKEN (BS 959-979) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 BD FROM STA 959 TO 979, RBL 24 HAS A BROKEN CORNER. FABRICATED NEW FLOOR PANEL 123 BD IAW DWG SRZ 25-005, REV "H".

Part: FITTING — CRACKED (ZONE 200) · airframe 89,473 hrs · 29,178 cycles

MCD NR 2 SPOOL FITTING LOCATION HAS CRACK INDICATIONS AT HOLES "A", "B", "C" AND "D". R & R NR 2 SPOOL FITTING IAW SRM 51-31-01, VOL I, SRM 51-33-01, VOL II, SRM 53-50-00, FIG 17, VOL I, DAC DWG AFA7132, REV "B" AND EA 8-5310-123543.

Part: FLOOR PANEL — BROKEN (BS 879-979) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 MF FROM STA 879 TO 979, LBL 36 EDGE IS BROKEN. FABRICATED NEW FLOOR PANEL 123 MF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 735-795) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 DF IS DELAMINATED FROM STA 735 TO 795, RBL 48. FABRICATED NEW FLOOR PANEL 123 DF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 1521-1601) · airframe 89,473 hrs · 29,178 cycles

CTR PIT FLOOR PANEL 183 WF IS DELAMINATED FROM STA 1521 TO 1601, RBL 48. FABRICATED NEW FLOOR PANEL 183 WF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 979-1059) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 UD FROM STA 979 TO 1059, RBL 48 IS DELAMINATED. FABRICATED NEW FLOOR PANEL 123 UD IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 899-919) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 VF FROM STA 899 TO 919, BL 0 IS DELAMINATED. FABRICATED NEW FLOOR PANEL 123 VF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 1521-1601) · airframe 89,473 hrs · 29,178 cycles

CTR PIT FLOOR PANEL 183 AF IS DELAMINATED FROM STA 1521 TO 1601, LBL 48. FABRICATED NEW FLOOR PANEL 183 AF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (BS 879-959) · airframe 89,473 hrs · 29,178 cycles

FWD PIT FLOOR PANEL 123 JF HAS A BROKEN CORNER FROM STA 879 TO 959, LBL 48. FABRICATED NEW FLOOR PANEL 123 JF IAW DWG SRZ 25-005, REV "H".

Part: SKIN — CRACKED (HORIZ STAB) · airframe 89,473 hrs · 29,178 cycles

REPAIRED HORIZ STAB UPPER LT AFT SKIN PLANK IAW EA 8-5510-123540.

Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 89,473 hrs · 29,178 cycles

LT OTBD FLAP; OTBD SIDE LOAD FITTING; ACFT SIDE; FWD HOLE IS CORRODED. BLENDED CORRODED AREA IAW SRM 51-21-01, VOL II. FOUND TO BE OUT OF LIMITS DUE TO EXFOLIATION. R &R SIDE LOAD FITING IAW SRM 51-33-01, VOL II AND DWG ARC 0501, REV "B4".

Part: FLOOR SUPPORT — CORRODED (BS 1871) · corrosion level 2 · airframe 89,473 hrs · 29,178 cycles

AFT CARGO COMPARTMENT FLOOR SUPPORT IS CORRODED TOP & BOTTOM FROM BS 1868 TO BS 1871; LBL 56. REMOVED CORROSION IAW SRM 51-21-01, PG 28A, VOL II. 100% MATERIAL LOSS - OUT OF LIMITS IAW SRM 53-00-01, FIG 1-B, VOL I. REMOVED FLOOR SUPPORT FROM FS 1853 TO 1902 LT, LBL 56 IAW SRM 51-31-01, PG 1, VOL II. DRILLED TO FIT NEW SUPPORT AND INSTALLED NEW SUPORT IAW SRM 51-31-01, PG 1, VOL II FROM FS 1853 TO 1902, LBL 56.

Part: PLATE — CRACKED (LT WING) · airframe 89,473 hrs · 29,178 cycles

LT WING L/E CAVITY UPPER JOINT PLATE IS CRACKED AT XFS 669. R & R JOINT PLATE AT LT WING L/E STA XFS 669 IAW SRM 51-33-01, VOL II AND SRM 51-35-01, VOL II.

Part: PANEL SUPPORT — CRACKED (LT WING) · airframe 89,473 hrs · 29,178 cycles

LT WING L/E LOWER PANEL SUPPORT IS CRACKED AT XORS 98. R & R PANEL SUPPORT AT XORS 98 IAW SRM 51-33-01 AND 51-35-01, VOL II.

Part: FITTING — CRACKED (FUSELAGE) · airframe 89,473 hrs · 29,178 cycles

NR 1 SPOOL FITTING LOCATION HAS CRACK INDICATIONS AT HOLES "A", "B", "C" AND "D". R & R NR 1 SPOOL FITTING IAW SRM 51-31-01, VOL I, SRM 51-33-01, VOL II, SRM 53-50-00, FIG 17, VOL I AND EA 8-5310-123543.

Part: FITTING — CRACKED (ZONE 200) · airframe 89,473 hrs · 29,178 cycles

MCD NR 7 SPOOL FITTING LOCATION HAS CRACK INDICATIONS AT HOLES "A", "B", "C", "D". R & R NR 7 SPOOL FITTING IAW SRM 51-31-01, VOL I, SRM 51-35-01, VOL II, SRM 51-10-00, VOL I, SRM 53-50-00, FIG 17, VOL I AND EA 8-5310-123543.

Part: FITTING — CRACKED (ZONE 200) · airframe 89,473 hrs · 29,178 cycles

NR 4 SPOOL FITTING LOCATION HAS CRACK INDICATIONS AT HOLES "A", AND "C". R & R NR 4 SPOOL FITTING IAW SRM 51-31-01, VOL I, SRM 53-50-00, FIG 17, VOL I AND EA 8-5310-123543.

Part: FITTING — CRACKED (FUSELAGE) · airframe 89,473 hrs · 29,178 cycles

NR 3 SPOOL FITTING LOCATION HAS CRACK INDICATIONS AT HOLES "C" AND "D". R & R NR 3 SPOOL FITTING IAW SRM 51-31-01, VOL I, SRM 51-33-01, VOL II, SRM 53-50-00, FIG 17, VOL I AND EA 8-5310-123543.

Part: FITTING — CRACKED (ZONE 200) · airframe 89,473 hrs · 29,178 cycles

NR 5 SPOOL FITTING LOCATION HAS CRACK INDICATIONS AT HOLES "C" AND "D". R & R NR 5 SPOOL FITTING IAW SRM 51-31-01, VOL I, SRM 51-10-00, VOL I, SRM 53-50-00, FIG 17, VOL I AND EA 8-5310-123543.

Part: RIB — CRACKED (LT WING) · airframe 89,473 hrs · 29,178 cycles

LT WING L/E RIB IS CRACKED AT XORS 270; UPPER FRONT SPAR AREA. REPAIRED CRACKED RIB IAW E.A. 8-5710-123546.

Part: SKIN — BENT (RT WING AILERON) · airframe 89,473 hrs · 29,178 cycles

RT WING OTBD AILERON LOWER SKIN INBD EDGE IS BENT. REMOVED FASTENERS AND REMOVED DAMAGE BY CUTOUT IAW SRM 57-10-00, FIG 56, VOL I. FABRICATED DOUBLER AND FILLER IAW SRM 57-10-00, FIG 56, VOL I. ALODINED AND PRIMED IAW SRM 51-21-01, VOL II. INSTALLED DOUBLER AND FILLER IAW SRM 57-10-00, FIG 56, VOL I.

Part: SKIN — CRACKED (LT WING) · airframe 89,473 hrs · 29,178 cycles

LT WING L/E CAVITY UPPER SKIN IS CRACKED AT AT XFS 672. FABRICATED DOUBLER IAW SRM 57-10-00, FIG 71, PG 222, VOL I. PRIMED DOUBLER IAW SRM 51-21-01, VOL II. INSTALLED DOUBLER IAW SRM 57-10-00, FIG 71, PG 222, VOL I.

Part: STIFFENER — CRACKED (RT WING) · airframe 89,473 hrs · 29,178 cycles

RT WING L/E LOWER PANEL SUPPORT STIFFENER IS CRACKED AT WING STA XORS 940, AFT SIDE. STOP DRILLED CRACK IN FORMER IAW SRM 57-00-01, FIG 3, SHEET 2, VOL I. FORMED REPAIR DOUBLERS IAW SRM 57-00-01, FIG 3, SHEET 2, VOL I. HEAT TREATED REPAIR DOUBLERS IAW SRM 57-00-01, FIG 3, SHEET 2, VOL I. FABRICATED REPAIR DOUBLERS IAW SRM 57-00-01, FIG 3, SHEET 2, VOL I. ALODINED AND PRIMED REPAIR DOUBLERS IAW SRM 51-21-01, VOL II. INSTALLED REPAIR DOUBLERS IAW SRM 51-31-01, VOL II. INSTALLED REPAIR DOUBLERS IAW SRM 51-31-01, VOL II SRM 57-00-01, FIG 3, SHEET 3, VOL 1.

Part: SKIN — CRACKED (RT WING) · airframe 89,473 hrs · 29,178 cycles

RT WING L/E INNER SKIN IS CRACKED AT WING STA XORS 560. RECEIVED MATERIAL ID 0.020 6AL-4Y TITANIUM AMD FABRICATED DOUBLER IAW SRM 57-10-00, PG 222, VOL I. PRIMED IAW SRM 51-21-01, VOL II. INSTALLED DOUBLER IAW SRM 57-10-00, PG 222, VOL I.

Part: RIB — CRACKED (RT WING) · airframe 89,473 hrs · 29,178 cycles

RT L/E RIB IS CRACKED AT WING STA XORS 560. R & R RIB DOUBLER IAW SRM 51-33-01, VOL II.

Part: RIB — CRACKED (RT WING) · airframe 89,473 hrs · 29,178 cycles

RT WING L/E RIB IS CRACKED AT WING STA XORS 725 UPPER AFT SIDE. REMOVED AND INSTALLED A NEW STRAP ON THE RIB IAW SRM 51-33-01, VOL II AND DWG ARB 1249, REV "Z". MATERIAL ID 7075-0 HEAT TREATED TO T6, PO 685178.1 IAW DWG ARB 1249, REV "Z". APPLIED ALODINE AND PRIMER IAW SRM 51-21-01, VOL II.

Part: STIFFENER — CRACKED (RT WING) · airframe 89,473 hrs · 29,178 cycles

RT WING L/E LOWER PANEL SUPPORT STIFFENER IS CRACKED AT WING STA XORS 855, AFT SIDE. REMOVED CRACKED FORMER/ SUPPORT STIFFENER IAW SRM 51-31-01, VOL II. REPLACED AND INSTALLED NEW RT WING L/E LOWER PANEL SUPPORT FORMED/ STIFFENER IAW DWG ARB 1164, REV "M" AND SRM 51-31-01, VOL II.

Part: PANEL SUPPORT — CRACKED (LT WING) · airframe 89,473 hrs · 29,178 cycles

LT WING L/E CAVITY LOWER PANEL SUPPORT IS CRACKED AT XFS 994. R & R PANEL SUPPORT IAW SRM 51-33-01 AND 51-35-01, VOL II.

Part: SKIN — DAMAGED (BS 859-879) · airframe 89,473 hrs · 29,178 cycles

LT PRIMARY STATIC PORT FAILS WAVINESS CHECK JUST FWD AND AFT OF THE STATIC PORT PLATE IN THE CONTROLLED AREA. R & R 16 HIGH FASTENERS IAW SRM 51-33-01, PG 34, VOL II. PERFORMED RVSM WAVINESS CHECK OF THE AFFECTED AREAS. AREAS ARE WITHIN LIMITS IAW SRM 53-00-02, VOL I AND AMM 34-11-01.

Part: SKIN — DAMAGED (TE FLAP) · airframe 89,473 hrs · 29,178 cycles

RT WING INBD FLAP LOWER SKIN HAS LIGHTENING DISCHARGE ON THE T/E AT WS XIFH 215. MATERIAL ID FOR THE REPAIR DOUBLER 2024-T3, 0.050, PO NR 680965.1 AND FOR THE FILLER 2024-T3 0.040, PO 668161.2. REMOVED DAMAGED AREA IAW SRM 57-10-00, FIG 85, VOL I. LOCATED AND DRILLED DOUBLER AND FILLER IAW SRM 57-10-00, FIG 85, VOL I ALODINED AND PRIMED IAW SRM 51-21-01, VOL II. INSTALLED DOUBLER AND FILLER IAW SRM 57-10-00, FIG 85, VOL I.

Part: WEDGE — CRACKED (AILERON) · airframe 89,473 hrs · 29,178 cycles

RT WING OTBD AILERON T/E WEDGE IS CRACKED AND PAINT IS CHIPPED FROM XW 760 TO XW 890. REMOVED T/E WEDGE SEC IAW SRM 57-20-00, FIG 10, VOL I. FABRICATED NEW T/E WEDGE AND "Z" ANGLE IAW SRM 57-20-00, FIG 10, VOL I. ALODINED AND PRIMED IAW SRM 51-21-01, VOL II. INSTALLED NEW T/E WEDGE AND "Z" ANGLE IAW SRM 57-20-00, FIG 10, VOL I. R & R BALANCE DATA PLATE AND ENGRAVED WITH NEW BALANCE CONDITION (67.2) IAW SRM 57-50-00, VOL II.

Part: TAT PROBE — FAILED (N/A) · airframe 88,331 hrs · 28,600 cycles

JUST AFTER T/O GOT LEVEL ONE "TAT PROBE HEAT" ALERT. C/B HAD POPPED. CONSULT WITH MX, RESET C/B DUE TO THUNDERSTORMS AND LOW VISIBILITY AT DESTINATION. REMOVED AND REPLACED TOTAL AIR TEMP PROBE. OPS CHECK GOOD, REF AMM 34-16-02-2.

Part: RIB — GOUGED (ZONE 300) · airframe 86,545 hrs · 27,715 cycles

RIGHT STABILIZER INBD ELEVATOR UPPER SURFACE IS GOUGED IN 2 PLACES. REPAIRED 2 EA GOUGES IAW DC/MD-10 SRM 55-10-00; VOL I; FIG 8 AND DC/MD-10 SRM 55-00-01; VOL I; FIG 3; SHEET 2. REPAIRED THE DAMAGED RIB CAP IAW DC/MD-10 SRM 55-00-01; VOL I; FIG 6. WEIGHT AND BALANCE NOT REQUIRED IAW DC/MD-SRM 55-10-00; VOL I; FIG 8; NOTE II.

Part: STRUCTURE — CRACKED (LT WING AILERON) · airframe 86,545 hrs · 27,715 cycles

LEFT WING OUTBD AILERON T/E IS CRACKED AND DETERIORATING. REMOVED T/E SECTION IAW DC/MD-10 SRM 51-35-01; VOL II. MATERIAL ID FOR T/E SECTION IS 3913181-72, PO 621834.1 AND "Z" CHANNELS 2024-T3, 0.032, PO 473755.1. FABRICATED IAW DC/MD-10 SRM 57-20-01; FIG 10; VOL I. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01; PGS 21 - 24; VOL II. INSTALLED IAW DC/MD-10 SRM 51-35-02; VOL II.

Part: SEAL — CRACKED (NR 3 PYLON) · airframe 86,545 hrs · 27,715 cycles

NR 3 PYLON LEFT SKIRT FAIRING METAL SEALS ARE WORN. REMOVED AND REPLACED P/N AUB 7078-17 SEAL AND AUB 7037-17 SEAL IAW DC/MD-10 SRM 51-35-01; VOL II. MATERIAL ID GAL-4V063 TITANIUM, 0.063 IAW DC/MD-10 SRM 54-00-01; FIG 2B; VOL I. FABRICATED A DOUBLER AND DRILLED HOLES IAW DC/MD-10 SRM 54-00-01, FIG 2B; VOL I.

Part: WEDGE — DELAMINATED (ZONE 300) · airframe 86,545 hrs · 27,715 cycles

RIGHT STABILIZER; OUTBD ELEVATOR, INBD SIDE T/E AREA IS DELAMINATED. REMOVED AND REPLACED WEDGE IAW DC/MD-10 SRM 51-35-01; VOL II.

Part: RUB STRIP — WORN (ZONE 400) · airframe 86,545 hrs · 27,715 cycles

THE NR 2 ENGINE RIGHT FAN COWL; THE RUB STRIP IS WORN. RUB STRIP WAS FOUND TO BE OUT OF LIMITS IAW MD-10-10 AMM 71-13-02-2. REMOVED THE RUB STRIP AND FWD LOWER FIRE SHIELD IAW DC/MD-10 SRM 51-35-01; VOL II. LOCATED; DRILLED AND DEBURRED RUB STRIP IAW DAC DWG ATL0022. INSTALLED NEW RUB STRIP AND FWD LOWER FIRE SHIELD IAW DC/MD-10 SRM 51-35-01; VOL II.

Part: RING — CHAFED (ZONE 400) · airframe 86,545 hrs · 27,715 cycles

ON THE NR 2 ENGINE AT THE 5 O'CLOCK POSITION; THE COWL RING COVERING THE NR 2 ENGINE ADAPTER RING IS CHAFED THROUGH BY THE RIGHT FAN COWL. REMOVED COWL RING PANEL IAW DC/MD-10 SRM 51-35-01; VOL II. MATERIAL ID FOR A NEW COWL RING PANEL IS 2024-T3, 0.063 IAW DC/MD-10 SRM 55-35-01; PGS 49 AND 50. ALODINED AND PRIMED THE NEW COWL RING PANEL IAW DC/MD-10 SRM 51-21-01; VOL II. PART MARKED THE NEW COWL RING PANEL IAW FEDEX GMM 7-0-1001. INSTALLED THE NEW COWL RING PANEL IAW DC/MD-10 SRM 51-35-01; VOL II. PAINTED THE NEW COWL RING PANEL IAW DC/MD-10 SRM 51-21-02; VOL II.

Part: STRUCTURE — LOOSE (NR 1 PYLON) · airframe 86,545 hrs · 27,715 cycles

NR 1 PYLON, AFT LOWER RIGHT SIDE HAS NUMEROUS RIVETS LOOSE.

Part: MOUNT — LOOSE (NR 1 PYLON) · airframe 86,545 hrs · 27,715 cycles

NR 1 PYLON LOWER AFT END (AT THE PYLON MOUNT) BRACKET IS LOOSE AND CRACKED AT THE BOTTOM, (FASTENERS ARE WORKING).

Part: PANEL — CHAFED (ZONE 400) · airframe 86,545 hrs · 27,715 cycles

ON THE NR 2 ENGINE ABOUT 7 O'CLOCK POSITION THE COWL RING COVERING THE NR 2 ENGINE ADAPTER RING IS CHAFED BY THE LEFT FAN COWL. REMOVED COWL RING PANEL FROM THE NR 2 ENGINE IAW DC/MD-10 SRM 51-31-01; VOL II. MATERIAL ID FOR THE NEW PANEL IS CLAD 2024-T6, 0.063 IAW DC/MD-10 SRM 55-31-01; VOL I; PGS 49 AND 50. FABRICATED A NEW PANEL IAW DC/MD-10 SRM 55-31-01; VOL I; PGS 49 AND 50. ALODINED AND PRIMED THE NEW PANEL IAW DC/MD-10 SRM 51-21-01; VOL II. PART MARKED THE NEW PANEL FX-AJC-7415-95 IAW FEDEX GMM 7-0-1000. INSTALLED THE NEW PANEL IAW DC/MD-10 SRM 51-31-01; VOL II.

Part: PANEL — CRACKED (ZONE 400) · airframe 86,545 hrs · 27,715 cycles

NR 3 PYLON PANEL 487 FL IS CHAFFED IN THE INNER SURFACE. BLENDED AREA AND FOUND A CRACK ON THE OUTBD ATTACH FLANGE. BLENDED THE AREA AND FOUND A CRACK ON THE ATTACH FLANGE. ORIGINAL MATERIAL THICKNESS 0.071 IAW DC/MD-10 SRM 54-51-01; VOL III. MATERIAL REMAINING 0.064 USING UT GAUGE T8225P. FOUND TO BE WITHIN LIMITS IAW DC/MD-10 SRM 54-00-01; VOL I; FIG 1-A; SHEET 3. MATERIAL ID 2024-T30.071, PO 618569.1 IAW DC/MD-10 SRM 54-00-01; VOL I; FIG 2-B, SHEET 2 AND DC/MD-10 SRM 54-51-01; VOL III. FABRICATED REPAIR PARTS IAW DC/MD-10 SRM 54- 00-01; VOL I; FIG 2-B; SHEET 2. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01; VOL II. INSTALLED DOUBLER IAW DC/MD-10 SRM 51-35-01; VOL II.

Part: SUPPORT — CRACKED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

THE CENTER LANDING GEAR WELL/SPACE INTERIOR, FWD BULKHEAD RIGHT UPPER CORNER AREA HAS A HYDRAULIC LINE SUPPORT BRACKET THAT IS CRACKED. REMOVED THE SUPPORT BRACKET IAW DC/MD-10 SRM 51-35-01; VOL II. MATERIAL ID 6061-T6, 0.063 IAW DC/MD-10 DWG AYK7014, REV BF. FABRICATED A NEW SUPPORT BRACKET IAW DC/MD-10 DWG AK7014, REV BF. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01; VOL II. INSTALLED THE SUPPORT BRACKET IAW DC/MD-10 SRM 51-33-01; VOL II.

Part: STIFFENER — CRACKED (ZONE 400) · airframe 86,545 hrs · 27,715 cycles

NR 3 PYLON PANEL NR 487 EL HAS A CRACKED STIFFENER. REMOVED AND REPLACED THE CRACKED STIFFENER IAW DC/MD-10 SRM 51-31-01; VOL II ON PANEL 487 EL ON THE NR 3 PYLON.

Part: BRACKET — BROKEN (SLAT TRACK) · airframe 86,545 hrs · 27,715 cycles

RIGHT WING NR 7 SLAT TRACK CLOSE OUT PANEL HAS A BROKEN BRACKET.

Part: PANEL — CHAFED (NR 3 PYLON) · airframe 86,545 hrs · 27,715 cycles

NR 3 PYLON PANEL 488 GL IS CHAFED ON THE INNER SKIN.

Part: SKIN — DENTED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

FUSELAGE EXTERNAL SKIN HAS A DENT ON THE LEFT SIDE AT APPROX FS 632 BETWEEN STRINGERS 39L AND 40L. REPAIRED DAMAGE AT THE LEFT SIDE FUSELAGE APPROX STA 632 BETWEEN L39L AND L40L IAW DC/MD-10 SRM 53-20-00; VOL I; FIG 6; SHEET 3.

Part: SEAT TRACK — DAMAGED (BS 1481-1884) · airframe 86,545 hrs · 27,715 cycles

ON THE MAIN CARGO DECK FLOOR, THE SEAT TRACK FROM BS 1481 TO BS 1884; LBL 48L HAS MINOR NICKS AND SCRATCHES.

Part: BRACKET — CRACKED (NR 1 PYLON) · airframe 86,545 hrs · 27,715 cycles

NR 1 PYLON THRU PANEL 438 AR; STAND OFF BRACKET FOR THE FIREX LINE IS CRACKED.

Part: STRUCTURE — GOUGED (NR 1 NACELLE) · airframe 86,545 hrs · 27,715 cycles

NR 1 ENGINE RIGHT FAN COWL INTERIOR IS GOUGED JUST FWD OF THE GENERATOR EXHAUST DUCT.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 86,545 hrs · 27,715 cycles

UPPER CARGO COMP SEAT TRACK HAS PITTING CORROSION IN THE BOTTOM OF THE TRACK LOCATED AT FS 760; LBL 9. REMOVED AND REPLACED THE SEAT TRACK IAW DC/MD-10 SRM 51-31-01. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01; VOL II. FABRICATED NEW SEAT TRACK IAW DC/MD-10 SRM 53-70-00, VOL I; FIG 2; SHEET 2.

Part: PANEL — CHAFED (ZONE 400) · airframe 86,545 hrs · 27,715 cycles

NR 1 PYLON PANEL 438 GL HOLE IS CHAFED. FABRICATED A NEW AUB 7036-27 SKIN IN REF TO FEDEX EA 8-5480-116987 AND REASSEMBLED THE PANEL IN REF TO FEDEX EA 8-5480-116987 "NACELLES/PYLONS - NR 1 PYLON AFT "V" FAIRING PANEL DAMAGED - REPAIR".

Part: PANEL — CHAFED (ZONE 500) · airframe 86,545 hrs · 27,715 cycles

LEFT WING INBD LOWER L/E PANEL 516 HB IS CHAFED. BLENDED AREA IAW DC/MD-10 SRM 57-00-01; VOL I; FIG 1-A. ORIGINAL MATERIAL THICKNESS IS 0.090 IAW DC/MD-10 SRM 57-31-01; VOL III; FIG 1. MATERIAL LOSS IS 0.028. REMAINING THICKNESS IS 0.062. FOUND TO BE OUT OF LIMITS IAW DC/MD-10 SRM 57-00-01; VOL I; FIG 1- A. USED UT GAUGE T8225P. MATERIAL ID IS 7075-T6, .100; PO 342278.3. FOR THE FILLER 7075-T6, 0.090, PO 603413.5 IAW DC/MD-10 SRM 57-00-01 AND 57-31-01; VOL III. FABRICATED DOUBLER AND FILLER IAW DC/MD-10 SRM 57-00-01; VOL I; FIG 4; VOL I. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01; VOL II; PGS 21-26. INSTALLED DOUBLER 7 FILLER IAE DC/MD-10 SRM 51-35-01; VOL II.

Part: INTERCOSTAL — CRACKED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

CENTER LOWER CARGO DOOR INTERIOR INTERCOSTAL JUST FWD OF THE UNLOCK ACTUATOR IS CORRODED. REMOVED THE INTERCOSTAL AND CRACKED BRACKET PER MD-10 SRM 51-35-01; VOL II. REMOVED THE DAMAGE FROM THE INTERCOSTAL. ORIGINAL MATERIAL 0.040; MATERIAL REMOVED .005; REMAINING MATERIAL .035. FOUND TO BE WITHIN LIMITS PER MD-10 SRM 57-00-01; PG 5; VOL I. VERIFIED CRACKED BRACKET TO BE OUT OF LIMITS PER MD-10 SRM 52-00-01; FIG 2; VOL I. MATERIAL ID 7075-T6, .050 FOR THE BRACKET PER DAC DWG ADA3791; REV M. FABBED A NEW BRACKET PER DAC DWG ADA3791; REV M. ALODINED AND PRIMED THE INTERCOSTAL AND NEW BRACKET PER MD-10 SRM 51-21-01; VOL II. INSTALLED BRACKET.

Part: PANEL — CHAFED (ZONE 500) · airframe 86,545 hrs · 27,715 cycles

LEFT WING INBD LOWER L/E PANEL 516 DB IS CHAFED AT THE CONTACT SURFACE. REMOVED PANEL. BLENDED OUT CHAFFED AREA. FABRICATED; PRIMED & BONDED THE REPAIR DOUBLER IAW SRM 57-00-01 VOL II PG 31 & EA 8-5720-118511. EDGE SEALED, PRIMED & PAINTED IAW SRM 51-71-00 VOL II & EA 8-5720-118511. INSTALLED PANEL IAW SRM 51-31-01 VOL II & EA 8-5720-118511.

Part: PANEL — CHAFED (ZONE 400) · airframe 86,545 hrs · 27,715 cycles

NR 3 PYLON PANEL NR 487 HR IS CHAFED AT THE INNER SURFACE. BLENDED CHAFED AREA AND FOUND TO BE OUT OF LIMITS REF DC/MD-10 SRM 54-00-01; VOL I. FABRICATED A NEW PANEL REF DAC DWG NR AUB7108; REV J. ALODINED AND PRIMED REF DC/MD-10 SRM 51-21-01; VOL II. INSTALLED THE SEALS REF DC/MD-10 SRM 51-31-01; VOL II. PARTS MARKED REF FEDEX GMM 7-0-1000.

Part: ANGLE — WORN (TE FLAP) · airframe 86,545 hrs · 27,715 cycles

LEFT WING LOWER TRAILING EDGE OUTBD FLAP; AT THE OUTBD SIDE OF THE HINGE FAIRING (XORS 500) ANGLE IS FRETTING FROM CONTACT WITH THE INBD SIDE OF PANEL NR 551 BB. CHECKED ANGLE AND FOUND TO BE OUT OF LIMITS IAW DC/MD-10 SRM 57-00-01; VOL I; FIG 1- A. ORIGINAL THICKNESS 0.080. MATERIAL REMAINING 0.042. MATERIAL REMOVED 0.039. UT GAUGE USED E2579A IAW DC/MD-10 SRM 51-31-01; VOL II. REMOVED ARC0744-15 ANGLE IAW DC/MD-10 SRM 51-31-01; VOL II. FABRICATED A NEW ANGLE IAW DAC DWG ARC0744, REV P. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01; VOL II. PART MARKED IAW FEDX GMM 7-0-1000. INSTALLED NEW ANGLE IAW DC/MD-10 SRM 51-31-01; VOL II. INSTALLED PANEL 536 BL IAW DC/MD-10 SRM 51-31-01;

Part: CHANNEL — CRACKED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

CENTER LANDING GEAR WELL/SPACE INTERIOR; HYDRAULIC MODULE UPPER CHANNEL HAS A CRACK STARTING AT THE MOUNT BOLT HOLE JUST FWD OF THE HYDRAULIC PUMPS. REMOVED SUPPORT CHANNEL IAW DC/MD-10 SRM 51-31-10; VOL II. MATERIAL ID 7275-0, 0.040 IAW DAC DWG AEA 0161, REV CR. FABRICATED THE SUPPORT CHANNEL IAW DAC DWG AEA 0161, REV CR. HEAT TREATED 7075-0 TO T6 IAW TPS 1003, REV A. HT 0603081 USED. ALODINED AND PRIMED THE SUPPORT CHANNEL IAW DC/MD-10 SRM 51-21-01; VOL II. PART MARKED THE SUPPORT CHANNEL FX AEA-016-289A IAW FEDEX GMM 7-0-1000. INSTALLED THE SUPPORT CHANNEL IAW DC/MD-10 SRM 51-35-01; VOL II

Part: ANGLE — DAMAGED (ZONE 500) · airframe 86,545 hrs · 27,715 cycles

LEFT WING INBD UPPER L/E PANEL 516 DT HAS A BROKEN ANGLE. REMOVED THE BROKEN ANGLE ON THE LEFT WING L/E PANEL 516 DT IAW DC/MD-10 SRM 51-31-01; VOL II. RECEIVE MATERIAL ID 7075-0, 0.050, PO 606256.5 IAW DAC DWG ARB 1261, REV IFOR THE FAB OF A NEW ANGLE. HEAT TREATED ANGLE IAW TPS 1003, REV A. ALODINED AND PRIMED THE NEW ANGLE IAW DC/MD-10 SRM 51-21-01; VOL II. PART MARKED THE ANGLE IAW DAC DWG ARB 1261, REV I AND FEDEX GMM 7-0-1000. INSTALLED THE NEW ANGLE IAW DC/MD-10 SRM 51-31-01; VOL II.

Part: PANEL — WORN (TE FLAP) · airframe 86,545 hrs · 27,715 cycles

RIGHT WING INBD FLAP HINGE PANEL 641 BR IS WORN. REPAIRED RIGHT WING INBD FLAP HINGE PANEL 641 BR BY REMOVING DAMAGED AREA AND BONDING A FILLER AND DOUBLER REPAIR IAW DC/MD-10 SRM 51-71-00; VOL II. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-2-01; VOL II AND SEALED IAW DC/MD-10 SRM 51-41-01; VOL II.

Part: PANEL — CHAFED (ZONE 400) · airframe 86,545 hrs · 27,715 cycles

LEFT WING INBD LOWER L/E PANEL 518 FB IS CHAFING AROUND THE CONTACT SURFACE. REPAIRED LEFT WING INBD LOWER PANEL ARB 1268-23 BY FABRICATING AND BONDING THE PAN DOUBLER IAW FEDEX EA 8-5720-116990; TIMCO TPS - 1001, REV E, AND DAC DWG ARB 1268. FEDEX EA 8-5720-116990 TITLED " WINGS - LT WING LEADING EDGE LOWER ACCESS PANEL 518 FB - REPAIR".

Part: PANEL — WORN (ZONE 400) · airframe 86,545 hrs · 27,715 cycles

LEFT WING LOWER TRAILING EDGE PANEL NR 551 BB INBD UPPER EDGE IS WORN FROM FRETTING. REPAIRED LEFT WING T/E PANEL NR 551 BB BY REMOVING THE DAMAGED AREA, FABRICATING A NEW FILLER AND DOUBLER. PERFORMED BONDING, CURE AND SEALING IAW DC/MD-10 SRM 51-71-00; VOL II. PAINTED AND RESTORED FINISH IAW DC/MD-10 SRM 51-21-01; VOL II.

Part: SKIN — WORN (ZONE 400) · airframe 86,545 hrs · 27,715 cycles

LEFT WING INBD FLAP HINGE PANEL 541 BR HAS A WORN AREA. REPAIRED BLENDED AREA BY REMOVING FINISH ON INNER SKIN AREA OF LEFT WING INBD FLAP HINGE PANEL 541 BR; FABBING A DOUBLER; HOT BONDING THE DOUBLER IN PLACE AND REFINISHING IAW DC/MD-10 SRM 51-71-00; VOL II AND DAC DWG ARC0166.

Part: STIFFENER — CRACKED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

LEFT MLG WHEEL WELL; LEFT WING INBD WEB; 4TH ANGLE AFT OF THE MLG CUTOUT IS CRACKED. THIS SDR WAS GENERATED IN ERROR. FOR DETAILS OF THIS DISCREPANCY SEE NON-ROUTINE NR N00205 AND SDR TRACKING NUMBER 08-2066.

Part: STIFFENER — CRACKED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

LEFT MLG WHEEL WELL; AFT OUTBD CORNER HORIZONTAL FRAME SUPPORT, INBD ANGLE IS CRACKED AT THE BOTTOM. REMOVED ACCESS PANELS IAW DC/MD-10 SRM 51-31-01; VOL II AND ANGLE IAW DC/MD-10 SRM 51-35-01; 51-33-01; VOL II. MATERIAL ID FOR THE ANGLE IS 7075-0, 0.063; PO 609289.3 IAW ASTME 1476. FABRICATED ANGLE IAW AS THE 1476; SRM 51-10-00 AND 51-33-01; VOL II. ALODINED; PRIMED AND PAINTED IAW SRM 51-21-01; PGS 21-24; 51-21-02; VOL II. INSTALLED IAW SRM 51-33-01; VOL II. INSTALLED PANELS IAW DC/MD-10 SRM 51-31-01; VOL II.

Part: SKIN — WORN (MLG DOOR) · airframe 86,545 hrs · 27,715 cycles

LEFT MLG DOOR SKIN A THE OUTBD T/E IS WORN AND BENT. BLENDED OUT DAMAGE. ORIGINAL MATERIAL 0.063 IAW DC/MD-10 SRM 52-80-01; VOL III. MATERIAL REMOVED 0.013. MATERIAL REMAINING 0.050. FOUND TO BE OUT OF LIMITS IAW DC/MD-10 SRM 52-00-01; VOL I; VOL I. WTG NR T8225P DOUBLER REPAIR IAW DC/MD-10 SRM 52-10-00; VOL I. LOCATED AND DRILLED DOUBLER IAW DC/MD-10 SRM 51-31-01; VOL II. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01; PGS 24 AND 21; VOL II. INSTALLED DOUBLER REPAIR IAW DC/MD-10 ARM 51-31-01; VOL II. PAINTED IAW DC/MD-10 SRM 51-21-02; VOL II AND DOUBLER REPAIR SR1052000-3-15, PO 621189.1.

Part: STIFFENER — CRACKED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

LEFT MLG WHEEL WELL; LEFT WING INBD WEB; 4TH ANGLE AFT OF THE MLG CUTOUT IS CRACKED. REMOVED STIFFENER IAW DC/MD-10 SRM 51-35-01 AND 51-33-01; VOL II. MATERIAL ID FOR THE STIFFENER 7075-0, 0.040 PO 606256.4. FABRICATED STIFFENER IAW DAC DWG ANB 7203, REV "BA". ALODINED; PRIMER AND PAINTED IAW DC/MD-10 SRM 51-21-01, PGS 21-24 AND 51-21-02; VOL II. INSTALLED STIFFENER IAE DC/MD-10 SRM 51-35-01; AND 51-33-01; VOL II.

Part: DOOR FRAME — DENTED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

THE CENTER CARGO DOOR AFT JAMB HAS A 2 INCH DENT AT THE LOWER AFT CORNER. REMOVED BULKHEAD PANEL 183 GA TO FOM PER MD-10-10 AMM 25-52-36-2; REMOVED DAMAGED ANGLE P/N AFA 3871-117 PER DC/MD-10 SRM 51-35-01; VOL II; PG 1. CUT OUT DAMAGE AND FABBED A REPAIR ANGLE AND FILLER PER DC/MD-10 SRM 53-00-01; FIG 8; SHEET 1; VOL I. INSTALLED REPAIR ANGLE; FILLER AND AFA 3871-117 ANGLE PER DC/MD-10 SRM 53-00- 01; FIG 8; SHEET 1; VOL I. INSTALLED AFA 3871-117 ANGLE PER DC/MD-10 SRM 51-35-01; VOL II AND DC/MD-10 SRM 51-33-01; VOL II. INSTALLED BULKHEAD PANEL 183 GA PER DC-10-10 AMM 25-52-36-02.

Part: STIFFENER — CRACKED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

LEFT MLG WHEEL WELL; LEFT WING INBD WEB 2ND AFT ANGLE AFT OF THE MLG CUTOUT IS CRACKED. REMOVED STIFFENER IAW DC/MD-10 SRM 51-35-01 AND 51-33-01; VOL II. MATERIAL ID FOR THE STIFFENER 7075-0, 0.040. FABRICATED STIFFENER IAW DAC DWG ANB 7208, REV "AB". ALODINED; PRIMED AND PAINTED IAW DC/MD-10 SRM 51-21-01; PGS 21-24 AND 51-21-02; VOL II. INSTALLED THE STIFFENER IAW DC/MD-10 SRM 51-35-01 AND 51-33-01; VOL II.

Part: STIFFENER — CRACKED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

LEFT MLG WHEEL WELL LEFT WING INBD WEB AFT OF THE MLG GEAR CUTOUT; THE FIRST ANGLE IS CRACKED AT THE BOTTOM. REMOVED COVERS IAW DC/MD-10 SRM 51-31-01; VOL II AND STIFFENER IAW DC/MD-10 SRM 51-31-01 AND 51-33-01 VOL II. MATERIAL ID FOR STIFFENER 7075-0, 0.063 PO 613534.3. FABRICATED STIFFENER IAW DAC DWG ANB7203, REV "BA". ALODINED; PRIMED AND PAINTED IAW DC/MD-10 SRM 51-21-01; PGS 21-24 AND 51-21-02; VOL II. INSTALLED STIFFENER IAW DC/MD-10 SRM 51-33-01; VOL II AND 51-21-02; VOL II.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

AFT PIT FLOOR PANEL 187 HF REQUIRES FAB NEW. FABRICATED NEW FLOOR PANEL 187 HF; POTTED EDGES; COMPLETED CURE AND SANDED EDGES; INSTALLED INSERTS; FABRICATED TOP SHEET; LAYED UP UNDER VAC BAG; COMPLETED CURE; BACK DRILLED AND COUNTERSUNK HOLES; APPLIED NON-SKID AND PART MARKED PANEL IAW FEDEX DWG SRZ 25-005, REV F AND 25-011, REV C.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

AFT PIT FLOOR PANEL 187 JF REQUIRES FAB NEW. FABRICATED NEW FLOOR PANEL 187 JF; POTTED EDGES; COMPLETED CURE AND SANDED EDGES; INSTALLED INSERTS; FABRICATED TOP SHEET; LAYED UP UNDER VAC BAG; COMPLETED CURE; BACK DRILLED AND COUNTERSUNK HOLES; APPLIED NON-SKID AND PART MARKED PANEL IAW FEDEX DWG SRZ 25-005, REV F AND 25-011, REV C.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

AFT PIT FLOOR PANEL 187 KF REQUIRES FAB NEW. FABRICATED A NEW PANEL 187 KF; POTTED EDGES; COMPLETED CURE AND SANDED EDGE POTTING; INSTALLED INSERTS; FABRICATED THE TOP SHEET; LAYED UP TOP SHEET UNDER A VAC BAG AND COMPLETED CURE; BACK DRILLED AND COUNTER SUNK HOLES; APPLIED NON-SKID AND PART MARKED PANEL IAW FEDEX DWG SRZ 25-005 REV F AND 25-011 REC C.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

AFT PIT FLOOR PANEL 187 DF REQUIRES FAB NEW. FABRICATED NEW FLOOR PANEL 187 DF; POTTED EDGES; COMPLETED CURE AND SANDED THE EDGE POTTING; INSTALLED INSERTS; FABRICATED TOP SHEET; LAYED UP UNDER VAC BAG; COMPLETED CURE; BACK DRILLED AND COUNTERSUNK HOLES; APPLIED NON-SKID AND PART MARKED PANEL IAW FEDEX DWG SRZ 25-005, REV F AND 25-011, REV C.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

AFT PIT FLOOR PANEL 187 AF REQUIRES FAB NEW. FABRICATED A NEW FLOOR PANEL 187 AF; POTTED EDGES; COMPLETED CURE AND SANDED EDGES; INSTALLED INSERTS; FABBED TOP SHEET; LAYED UP UNDER A VAC BAG; COMPLETED CURE; BACK DRILLED AND COUNTERSUNK HOLES; APPLIED NON-SKID AND PART MARKED THE PANEL IAW FEDEX DWG SRZ 25-005, REV F AND 25-011, REV C.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

AFT PIT FLOOR PANEL 187 BF REQUIRES FAB NEW. FABRICATED NEW FLOOR PANEL 187 BF; POTTED EDGES; COMPLETED CURE AND SANDED EDGE POTTING; INSTALLED INSERTS; FABRICATED TOP SHEET; LAYED-UP TOP SHEET UNDER A VAC BAG; COMPLETED CURE; BACK DRILLED AND COUNTERSUNK HOLES; APPLIED NON-SKID AND PART MARKED PANEL IAW FEDEX DWG SRZ 25-005, REV F AND 25-011, REV C.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

AFT PIT FLOOR PANEL 187 EF REQUIRES FAB NEW. FABRICATED NEW FLOOR PANEL 187 EF; POTTED EDGES; COMPLETED CURE AND SANDED EDGES; INSTALLED INSERTS; FABRICATED TOP SHEET; LAYED UP UNDER VAC BAG; COMPLETED CURE; BACK DRILLED AND COUNTERSUNK HOLES; APPLIED NON-SKID AND PART MARKED PANEL IAW FEDEX DWG SRX 25-005, REV F AND 25-011, REV C.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

AFT PIT FLOOR PANEL 187 CF REQUIRES FAB NEW. FABRICATED NEW FLOOR PANEL 187 CF; 187 CF; POTTED EDGES; COMPLETED CURE; INSTALLED INSERTS; FABRICATED TOP SHEET; LAYED UP UNDER VAC BAG; COMPLETED CURE; BACK DRILLED AND COUNTERSUNK HOLES; APPLIED NON-SKID AND PART MARKED PANEL IAW FEDEX DWG SRZ 25-005, REV F AND 25-011, REV C.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

AFT PIT FLOOR PANEL 187 FF REQUIRES FAB NEW. FABRICATED NEW FLOOR PANEL 187 FF; POTTED EDGES; COMPLETED CURE AND SANDED EDGE POTTING; INSTALLED INSERTS; FABRICATED TOP SHEET; LAYED UP UNDER A VAC BAG; BACK DRILLED AND COUNTERSUNK HOLES; APPLIED NON-SKID AND PART MARKED PANEL IAW FEDEX DWG SRZ 25-005, REV F AND 25-011, REV C.

Part: SKIN — BENT (CARGO DOOR) · airframe 86,545 hrs · 27,715 cycles

FWD LOWER CARGO DOOR EXTERIOR IS BENT ON THE LEFT SIDE OF THE DOOR. CUTOUT DAMAGE AND FABRICATED REPAIR DOUBLER, FILLER AND REPAIR ANGLE PER DC/MD-10 SRM 52-10-00, FIG 17; SHEET 1; VOL I. ALODINED AND PRIMED PER DC/MD-10 SRM 51-21-01; PGS 21 AND 25; VOL II. INSTALLED REPAIR DOUBLER, FILLER AND REPAIR ANGLE PER DC/MD-10 SRM 52-10-00, FIG 17, SHEET 1, VOL I.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 86,545 hrs · 27,715 cycles

AFT PIT FLOOR PANEL 187 GF REQUIRES FAB NEW. FABRICATED NEW FLOOR PANEL 187 GF; POTTED EDGES; COMPLETED CURE AND SANDED EDGE POTTING; INSTALLED INSERTS; FABRICATED TOP SHEET; LAYED UP UNDER A VAC BAG; COMPLETED CURE; BACK DRILLED AND COUNTERSUNK HOLES; APPLIED NON-SKID AND PART MARKED PANEL IAW FEDEX DWG SRZ 25-005, REV F AND 25-011, REV C.

Part: CONNECTOR — LOOSE (MLG) · airframe 81,597 hrs · 25,472 cycles

LANDING GEAR INDICATED UNSAFE ON BOTH THE CONFIG PAGE AND GEAR LIGHTS AFTER RETRACTION. RECYCLED IAW CFM PROCEDURE AND ALL INDICATIONS NORMAL. TOWER STATED GEAR "APPEARED" RETRACTED WHILE HAD UNSAFE INDICATIONS. REMOVED AND REPLACED LANDING GEAR CONTROL MECHANISM DURING REPLACEMENT OF THE LANDING GEAR CONTROL HANDLE AND MECH. IT WAS DISCOVERED SWITCH S1-431 CONNECTORS WERE VERY LOOSE AND SWITCH WAS REPLACED. JACKED AIRCRAFT. SWUNG ALL GEAR SEVERAL TIMES. ALL LIGHTS WORKED NORMAL.

Part: WIRE HARNESS — FAILED (FIRE LOOP) · airframe 81,554 hrs · 25,452 cycles

AFTER TAKEOFF ON CLIMB-OUT AT 17,000 FEET, GOT INTERMITTENT NR 2 ENG FIRE INDICATION, 1ST IN FUEL LVR THEN PASSING 18,000 GOT FIRE WARNING, ALL INDICATION NR 2 ENG, LIGHTS, BELL FOLLOWED QRH, SHUTDOWN NR 2 ENG. LANDED ASAP AT KATL. FIRED BOTH BOTTLES AND STILL HAD INTERMITTENT INDICATIONS NR 2 ENG REPLACED THE NR 2 RT FIRE BOTTLE PER M/NM 26-21-01-4. REPLACED HARNESS ASSY'S P1-8224 TO P1-8694 AND ASSY. P1-8225 TO P1-8693 REMOVED AND REPLACED THE NR 1 FIRE EXTINGUSHING BOTTLE FOR THE NR 2 ENG.

Part: WARNING LIGHT — FALSE ACTIVATION (MLG) · airframe 81,449 hrs · 25,408 cycles

UNSAFE GEAR-UP IND DURING GEAR RETRACT ON TAKEOFF. BOTH PRI AND SEC IND SHOWERED OR UNSAFE. LOWERED GEAR IAW RED-TAB PROC AND ALL IND GREEN. RAISED GEAR AGAIN AND GOT A GOOD GEAR UP IND. GEAR RETRACT SOUNDED NORM AND CAME UP AS USUAL BUT HANDLE MECH INSIDE OR BEHIND PANEL FEELS SLACK OR LOOSE. PERFORMED VISUAL CHK OF L/G CONTROL MECHANISM, NO FAULTS NOTED. OPERATED HANDLE THRU FULL MOTION, ALL GEAR LIGHTS OPERATED AS DESIGNED. PERFORMED INSPECT OF PROX SENSORS AND TARGETS (32-61-1 5-4) CHECKED NORMAL. INSPECTED GEAR AND DOORS FOR OBVIOUS IRREGS, NONE NOTED. NO FAULTS DISPLAYED FOR PREV FLIGHT OR CURRENT. PERFORMED PSEU RTS (31-71-01-2). (OPEN)