N372FE

Part: CLAMP — LEAKING (DUCT) · airframe 95,831 hrs · 40,294 cycles

AIR MANIFOLD NR 2 FAILED. AFTER TAKEOFF. AIR TURN BACK. REMOVED & REPLACED CLAMP ON DUCT ASSY IN LEFT WHEEL WELL IAW MM 36-14-02-4. NO LEAKS NOTED. PERFORMED DECAY CHECK WITH APU IAW 36-00-01-5 AND GAINED 4 SECONDS. TIME IS NOW WELL WITHIN LIMITS AT 22 SECONDS. ACFT OK FOR SERVICE.

Part: CLAMP — FAILED (BLEED AIR SYS) · airframe 95,831 hrs · 40,294 cycles

AIR MANF NR 2 FAIL. AFTER TAKEOFF. AIR TURN BACK. R&R CLAMP ASSY PER MM 36-14-02-4 IN LEFT WHEEL WELL JUST FWD OF BULKHEAD.

Part: SKIN — GOUGED (BS 1721) · airframe 95,831 hrs · 40,293 cycles

FOUND GOUGED ON LOWER BELLY NEAR BS 1721, LONGERON 47L. REPAIRED THE SKIN IAW SRM 53-20-00, FIG 6.

Part: SKIN — CRACKED (BS 1801) · airframe 95,831 hrs · 40,293 cycles

FOUND CRACK ON FUSELAGE JUST AFT OF CTR CARGO DOOR AROUND BS 1801 AND STRINGER 45L. REPAIRED THE SKIN IAW SRM 53-20-00, FIG 6.

Part: FIRE LOOP — FAILED (NR 1 NACELLE) · airframe 95,458 hrs · 40,080 cycles

DURING CLIMBOUT RECEIVED A LEVEL 2 ALERT FOR THE NR 1 ENGINE FIRE LOOP B AND TOOK THE APROPRIATE QRH ACTIONS (NO FIRE). TROUBLESHOT THE FIRE LOOP AND FOUND HIGH RESISTANCE TO GROUND. ALL OTHER 'B' LOOPS AND AIRCRAFT WIRING CHECK CLEAN. REMOVED AND REPLACED THE NR 1 PYLON FIRE LOOP B DETECTOR AND SECURED CONNECTOR P1-8692 IAW AMM 26-11-02-4. OPS CHECKED GOOD.

Part: STIFFENER — CRACKED (LT MLG WW) · airframe 94,239 hrs · 39,401 cycles

LEFT GEAR WELL OTBD SIDE TO FLAP WELL BULKHEAD, LOWER GUSSET REPAIR IS CRACKED AND RIVETS SHEARED. REMOVED EXISTING REPAIR AND TRIMMED OUT CRACKED AREA. FABRICATED NEW PARTS FOR REPAIR REF SRM 53-00-01, FIG 4 AND 8. INSTALLED REPAIR IAW SRM 53-00-01, VOL 1, FIG 4 AND 8.

Part: SKIN — CRACKED (TE FLAP) · airframe 94,239 hrs · 39,401 cycles

LEFT WING OTBD FLAP UPPER SURFACE CRACKED SKIN AT APPROXIMATELY XOFH 548, DEFECTIVE. INSTALLED DOUBLER AND FILLER IAW SRM 57-00-01, FIG 4, VOL 1. CLEANED AND PAINTED LT WING OTBD FLAP UPPER SURFACE IAW SRM 51-21-02, VOL 2.

Part: ACCESS PANEL — DELAMINATED (RT WING) · airframe 94,239 hrs · 39,401 cycles

RIGHT T/E ACCESS PANEL 641NB IS DELAMINATED IN MANY SPOTS. MARKED IN RED CIRCLES, REPAIRED RT T/E PANEL 641NB IAW SRM 51-71-00, VOL II.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

MAIN CABIN SEAT TRACK IS DAMAGED AT STA 630, RBL 8. REMOVED DAMAGED SECTION OF SEAT TRACK FROM STA 605-645, RBL 8. INSTALLED SEAT TRACK SPLICE REPAIR REF SRM 53-70-00, FIG 1.

Part: ACCESS DOOR — DELAMINATED (RT WING) · airframe 94,239 hrs · 39,401 cycles

RIGHT WING LOWER ACCESS DOOR, PN ARC0286-2, 641AB DELAMINATION. REPAIRED RT WING LOWER ACCESS DOOR ARC0286-2 IAW SRM 51-71-00, VOL NR 2.

Part: FITTING — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

STA 1159, RT SIDE CORNER. HAIRPIN FITTING CRACKED FROM UPPER INBD AFT FASTENER TO EDGE, 2016-06-17. REPAIRED FITTING AT BS 1159, RT SIDE IN REF TO SRM 53-30-00, VOL 1, FIG 7, A SHEET 1.

Part: SUPPORT ANGLE — CRACKED (R1 DOOR) · airframe 94,239 hrs · 39,401 cycles

R-1 DOOR SUPPORT ANGLE CRACKED ON UPPER FWD CORNER OF DOOR, ABOVE NR 8 BEAM, MARKED DOT 1, 2016-06-15. REMOVED SUPPORT ANGLE FROM R-1 DOOR, INSTALLED THE NEW PART.

Part: SKIN PANEL — DAMAGED (ZONE 400) · airframe 94,239 hrs · 39,401 cycles

RIGHT NR 2 ENGINE INLET DUCT PANEL 364JR, EXTERNAL SKIN HAS 1 LIGHTNING STRIKE REPAIRED AREA ON PANEL 364JR IAW SRM 51-71-00, VOL NR 2.

Part: PANEL — DELAMINATED (ZONE 400) · airframe 94,239 hrs · 39,401 cycles

NR 2 ENGINE PICKLE BARREL PANEL 364JR HAS DELAMINATED AT UPPER CENTER TOP SURFACE PANEL 364JR. REPAIRED DELAMINATION IAW SRM 51-71-00, VOL NR 2.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

RIGHT ACM COMPARTMENT, STA 595 BULKHEAD, HORIZONTAL STIFFENER, 3RD FROM BOTTOM, OTBD EDGE IS CRACKED. FABRICATED NEW STIFFENER NCA6044-58 IN REF TO DWG NCA6044.

Part: SKIN — DAMAGED (RT COWLING) · airframe 94,239 hrs · 39,401 cycles

NR 2 ENGINE RT FAN COWL LANDING HAS DAMAGE ON THE SKIN AT THE FWD END AT APPROXIMATELY 5:30 POSITION. REMOVED AND REPLACED DAMAGED SKIN IN REF TO SRMN 54-10-00 FIG 20, SHT 4.

Part: DOUBLER — CRACKED (VERTICAL STAB) · airframe 94,239 hrs · 39,401 cycles

LEFT LOWER VERTICAL AT FUSELAGE DRAG ANGLE REPAIR DOUBLER CRACKED. MARKED AT NR 2 BANJO FITTING 2016-06-09. REMOVED CRACKED ANGLE. INSTALLED NEW ANGLE IN REF TO SRM 55-20-00, FIG 3.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

RIGHT BS 595 BULKHEAD WEB LOWER FASTENER HOLE COMMON TO THE TEE CAP HAS A CRACK INDICATION.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

FORWARD CARGO COMPARTMENT BILGE SPACE, THERE ARE 2 AREAS OF CORROSION ALONG A LATERAL FLOORBEAM UPPER ANGLE UNDER 2 DIFFRENT ROLLER TRAYS AT AFT SIDE OF THE BS 879, FLOOR FRAME APPROXIMATE LBL 18 & LBL 30. FABRICATED ANGLE IAW DWG RAM1429.

Part: CAP — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

RIGHT BS 595 BULKHEAD TEE CAP VERTICAL LEG UPPER FASTENER HOLE AT LONGERON 39R HAS A CRACK INDICATION.

Part: FRAME — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

RIGHT NR 3 ACM COMPARTMENT, BS 555, APPROXIMATELY LONGERON 38, CRACKED FRAME. INSTALLED FABRICATED DOUBLER IN NR 3 ACM COMPARTMENT, STA 555 AT APPROXIMATELY LONGERON 38, REF SRM 53-00-01, VOL 1 AND SRM 51-33-01, VOL 2.

Part: FITTING — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

CAC STA 1159, RT SIDE CORNER, HAIRPIN FITTING CRACKED FROM UPPER INBD AFT FASTENER TO EDGE. REPAIRED FITTING AT BS 1159 IAW SRM 53-30-00, VOL 1, FIG 7, SHEET 1, 2.

Part: TEE FITTING — CRACKED (LT HORIZ STAB) · airframe 94,239 hrs · 39,401 cycles

LEFT HORIZONTAL LE, CTR INBD SECTION APPEARS TO BE CRACKED AT UPPER T. REMOVED & INSTALLED NEW T CAP. PN ALC7052-19, IAW DWG ALC7052 & SRM 51-31-00 VOL 2.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

MAIN CABIN CTR WING AREA, FLOORBEAM CRACKED AT STATION 1259, RBL 107, BELOW OTBD SEAT TRACK AREA. INSTALLED SR10530081 -15,-17,-19,-21, &-23 IAW DWG SR10530081.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

MAIN CABIN CTR WING AREA, FLOORBEAM CRACKED AT STATION 1259, LBL 107, AT OVERWING DOOR FWD FRAME AREA. REMOVED SECTION OF CRACKED FLOORBEAM AND REPLACED SECTION WITH KIT SB10530172-5 IAW SR10530081-7009.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

MAIN CABIN CTR WING AREA, FLOORBEAM CRACKED AT STATION 1293, RBL 107, BELOW OTBD SEAT TRACK. REMOVED DAMAGED SECTION OF FLOORBEAM AND REPLACED WITH KIT SB10530172-5 AND SR10530081-7009.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

RIGHT STATION 595 BULKHEAD, LONGERON 38R, T CAP AFT LEG HAS CRACK INDICATION FROM RADIUS TO END OF LEG SECTION. CRACK LOCATED 1.75" BELOW LONGERON 38R. R & R SECTION OF CRACKED TEE CAP FROM LONGERON 36R TO 44R AT STA 595, PN ACA7016-501 IN REF TO DWG SR10530064 AND EA 8-5310-T0325736.

Part: FITTING — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

BS 1159 RT SIDE CORNER, HAIR PIN FITTING CRACKED, FROM UPPER INBD AFT FASTENER TO EDGE.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

AIR CYCLE MACHINE COMPARTMENT NR 3, AT STATION 548, HAS A CRACKED INTERCOSTAL. STOP DRILLED CRACK, NDT VERIFIED NO CRACK BEYOND STOP DRILL AND INSTALLED REPAIR ANGLE TO RESTORE STRUCTURAL INTEGRITY IN REF TO SRM 53-00-01, FIG 8, VOL 1.

Part: SKIN — PUNCTURED (MLG DOOR) · airframe 94,239 hrs · 39,401 cycles

SMALL PUNCTURE IN THE CTR OF MLG DOOR. REPAIRED IAW SRM 51-71-00 VOL 2.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

FORWARD CARGO COMPARTMENT, BILGE AT STA 879, ANGLE ON AFT SIDE OF FRAME CORRODED LBL4-LBL40. REPAIRED ANGLE IAW DWG RAM 1429.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

MAIN CABIN SEAT TRACK AT STATION 1381, LBL 75 IS DAMAGED & GOUGED. SEAT TRACK DAMAGED BEYOND LIMITS. R & R SECTION FROM STATION 1371 - 1391 IAW SRM 53-70-00 FIG 1 VOL 1.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

FORWARD CARGO COMPARTMENT BILGE SPACE, THERE IS A LATERAL FLOORBEAM SUPPORT THAT IS CORRODED AT STATION 1059, NEAR BL 0. REMOVED AND REPLACED FLOOR SUPPORT BEAM IN REF TO SRM 51-35-01 VOL 2.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

AFT EMPENNAGE UPPER AFT FUSELAGE COMPARTMENT, STATION 2031 - 2035 RT 6TH LONGERON HAS 4 CRACKS UPPER & LOWER AREAS, TRANSITIONING THRU 2033 BULKHEAD DOT NR 4 ZONE 311 & 312 2016 05 20. R & R SECTION OF LONGERON IN REF TO SRM 53-10-00, FIG 3, VOL 1.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

FORWARD CARGO COMPARTMENT AT STATION 791, BETWEEN BL 0 - LBL 30, A LATERAL BEAM FLOOR SUPPORT ANGLE HAS CORROSION 2016 05 20. R & R FLOOR SUPPORT ANGLE AT STA 791, BL-0 TO LBL 30 IN REF TO SRM 51-35-01, VOL 2.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

AFT EMPENNAGE UPPER AFT FUSELAGE COMPARTMENT, STATION 2027 - 2037 RT 8TH LONGERON HAS 10 CRACKS UPPER & LOWER AREAS, TRANSITIONING THRU 2033 BULKHEAD DOT 5 ZONE 311 & 312 2016 05 20. R & R 8TH LONGERON STA 2007-2037. RT AFT UPPER EMPENNAGE COMPARTMENT IAW SRM 53-10-00, FIG 3.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

AFT EMPENNAGE UPPER AFT FUSELAGE COMPARTMENT, STATION 2030 - 2038 LT 7TH LONGERON HAS 8 CRACKS UPPER & LOWER AREAS, TRANSITIONING THRU 2033 BULKHEAD DOT 6 ZONE 311 & 312 2016 05 20. R & R LONGERON 10L FROM STA 2007-STA 2038 IAW SRM 53-10-00, FIG 3, SHT 1 THRU 5, PN: BAC1505-100900-9.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

FORWARD CARGO COMPARTMENT, BILGE AT STATION 879 FRAME FLOOR SUPPORT ANGLE, BETWEEN LONGERON 52 & LBL 24 IS CORRODED. R & R FLOOR SUPPORT IN REF TO SRM 51-31-01, VOL 2.

Part: ROLLER TRAY — CORRODED (CARGO BAY) · airframe 94,239 hrs · 39,401 cycles

FORWARD CARGO COMPARTMENT, ROLLER TRAY HAS CORROSION ON A LT FLOOR SUPPORT TANG, BETWEEN STATION 755 - 808 AT BL 0. REMOVED CORRODED ROLLER TRAY AND REPLACED WITH NEW ROLLER TRAY.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

FORWARD CARGO COMPARTMENT, STATION 735, BETWEEN BL 0 - LBL 30, HAS A LATERAL FRAME FLOOR SUPPORT BEAM ANGLE THAT IS CORRODED 2016 05 20. REMOVED MINOR CORROSION ON FLOOR SUPPORT, BETWEEN BL 0 & LBL 30 IAW SRM 51-21-01 VOL 2.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

AFT EMPENNAGE UPPER AFT FUSELAGE COMPARTMENT, STATION 2030 - 2039 RT 4TH LONGERON HAS 9 CRACKS UPPER & LOWER AREAS, TRANSITIONING THRU 2033 BULKHEAD DOT NR 2 ZONE 311 & 312 2016 05 20. R & R SECTION OF LONGERON FROM BS 2030 TO STA, GOING THROUGH THE 2033 BULKHEAD TO STA 2039, RT 4TH LONGERON IN REF TO SRM 53-10-00, FIG 3 OF VOL 1.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

AFT EMPENNAGE UPPER AFT FUSELAGE COMPARTMENT, STATION 2030 - 2036 RT 3RD LONGERON HAS 6 CRACKS UPPER & LOWER AREAS, TRANSITIONING THRU 2033 BULKHEAD DOT 1 ZONE 311 & 312 2016 05 20. R & R SECTION OF LONGERON FROM STA 2031 TO STA 20335 THAT GOES THROUGH THE 2033 BULKEAD, RT 3RD LONGERON IN REF TO SRM 53-10-00, FIG 3 OF VOL 1.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

AFT EMPENNAGE UPPER AFT FUSELAGE COMPARTMENT, STATION 2031- 2035 RT 5TH LONGERON HAS 4 CRACKS UPPER & LOWER AREAS, TRANSITIONING THRU 2033 BULKHEAD DOT NR 3 ZONE 311 & 312 2016 05 20. R & R SECTION OF LONGERON AT BS 2031 GOING THROUGH THE 2033 BULKHEAD TO STA 2035, RT 5TH LONGERON IN REF TO SRM 53-10-00, FIG 3.

Part: FRAME — CORRODED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

FORWARD CARGO COMPARTMENT, BILGE AT STATION 879, AFT SIDE OF FRAME AT RBL 36, HAS CORROSION UNDER ROLLER TRAY. REMOVED CORROSION FROM ANGLE, TREATED AND PRIMED IN REF TO SRM 51-21-01, VOL 2.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

LEFT STATION 595 BULKHEAD TEE CAP VERTICAL LEG AT LONGERON 36L, HAS A 2 INCH CRACK. R & R SECTION OF TEE CAP FROM LONGERON 36L TO 40L AT STA 595 WITH PN ACA7016-1 IN REF TO DWG SR10530064 AND EA 8-5310-T0325366.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

RIGHT STATION 595 BULKHEAD TEE CAP VERTICAL LEG AT LONGERON 43R, HAS A 2 INCH CRACK. REPAIRED THE 595 BULKHEAD AT LONGERON 43R BY SPLICING IN A NEW SECTION OF TEE CHORD IN REF TO SR DWG SR10530081 AND EA 8-5310-T0325736, PN OF THE TEE CHORD IS ACA7016-501.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 94,239 hrs · 39,401 cycles

LEFT STATION 595 BULKHEAD TEE CAP VERTICAL LEG AT LONGERON 39L HAS A 2 INCH CRACK. R & R SECTION OF TEE CAP FROM LONGERON 36L TO 40L AT STA 595 WITH PN ACA7016-1 IN REF TO DWG SR10530064 AND EA 8-5310-T0325366.

Part: TRIM PANEL — OUT OF POSITION (L1 DOOR) · airframe 93,489 hrs · 39,039 cycles

ON LANDING ROLL OUT, HAD THE CABIN DOOR 1L APPEAR. AFTER COMING TO A STOP ON THE TAXIWAY, INSPECTED DOOR & ALL WAS NORMAL, EXCEPT FOR ARMED TAB FOR GIRT BAR WENT OUT AFTER HOOKING UP TO THE TUG. INSPECTED THE ARMED TAB FOR GIRT BAR & FOUND THE WHITE DECORATIVE TRIM OUT OF ITS TRACK & OBSTRUCTING VIEW. RESEATED TRIM INTO TRACK & ARMED TAB IS NOW VISIBLE. RELEASED FOR SERVICE IAW MEL 52-40-01-01-A CATEGORY C, EXPIRATION 14 DEC 15. DOOR L1 ALERT SYS INOPERATIVE. VERIFY DOOR IS CLOSED, LOCKED & ARMED PRIOR TO BLOCK OUT. ROLLER ON SLIDING CEILING PANEL LOOSE & BINDING. TIGHTENED FASTENER & OPS OK IAW AMM 52-11-00-5.

Part: WIRE — BROKEN (CABIN DOOR) · airframe 931 hrs · 38,852 cycles

CABIN DOOR FWD LT WILL UNLOCK BUT WILL NOT OPEN ELECTRICALLY. HAD TO USE FWD RT DOOR TO EXIT. L1 ELECTRIC DOOR ACTUATOR INOPERATIVE FOR EMER EGRESS, USE PNEUMATIC SYS TO OPERATE DOOR. FOUND WIRE AT PIN 3 BROKEN AND C/P CORRODED. R&R C/P P1-3120 AND RETERM'D PINS 2 & 3 IAW MD10 WDM 52-11-01 & SWPM 20-31-00. DOOR APPEARS TO FUNCTION NORMALLY. OPS CHK REQ'D. L1 DOOR OPS TEST AND IND TEST NORMAL. PER MD-10-10 M/M 52-11-00-5

Part: CONNECTOR — DAMAGED (BRAKE) · airframe 931 hrs · 38,824 cycles

WHILE WORKING THE NR 5 BRAKE WORN, MX FOUND BRAKE TEMP SENSOR CONNECTOR P1-2337 DAMAGED. REMOVED & INSTALLED DAMAGED CP P1-2337 IAW WDM 32-46-01 & SWPM 20-31-00.

Part: SWITCH — DIRTY (ZONE 200) · airframe 926 hrs · 38,512 cycles

AFTER PUSHBACK, CABIN DOOR FWD LT ALERTED. CYCLED ARM SWITCH & DOOR SWITCH, WORKED TO REMOVE ALERT. FOUND AFT GIRT BAR ARMED SWITCH ROLLER ASSEMBLY FROZEN. CLEANED SWITCH ASSEMBLY & OPERATED DOOR ASSEMBLY, NO DEFECTS NOTED AT THIS TIME. INDICATION CHECKED NORMAL.

Part: PSEU — FAILED · airframe 92,251 hrs · 38,330 cycles

AFTER TAKEOFF LT MLG UNSAFE AT HANDLE & SYNOPTIC QRH PROCEDURE, RECYCLED GEAR, INDICATION NORMAL. REPEAT WRITE UP, AML 2441721 RED INDICATION IN DESCENT. CREW GAVE MORE INFO CONCERNING FAULTS, DURING TAKEOFF AFTER CLEANUP SPEED 230 GOT UNSAFE INDICATION SLOWED TO QRH PROCEDURES 210, AFTER A FEW CYCLES GOT SAFE INDICATION. DESCENDING AT 310 KNOTS & FL 10,500 RED UNSAFE INDICATION RETURNED & STAYED ON UNTIL GEAR WAS CYCLED DOWN. BOTH HANDLE & SYNOPTIC WERE RED FOR THE LT GEAR. FAILED OPERATIONS CHECK & REPLACED WITH SERVICEABLE UNIT. R & R PROXIMITY SWITCH ELECTRONICS UNIT IAW MM 31-71-01-2. ALL TEST PASSED AT THIS TIME.

Part: PROXIMITY SENSOR — MALFUNCTIONED (LT MLG) · airframe 92,252 hrs · 38,331 cycles

AFTER TAKEOFF LT MLG PRIMARY & SECONDARY LIGHTS WERE RED WITH THE GEAR HANDLE UP. RAN QRH CHECKLIST & ALL LIGHTS WENT OUT INDICATING SAFE RETRACTION. LIGHT CAME BACK ON DESCENT. INTERROGATED PSEU IN CFDS. FOUND TWO OCCURRENCES ON LAST FLIGHT LEG OF LG UP & LATCHED A/B SENSOR DISAGREE PROBABLE CAUSE SENSOR & TARGET RIGGING. TROUBLE SHOT IAW FIM 32-60/807. DURING RIG CHECK OF SENSOR IN UP & LOCKED POSITION, FOUND LT MLG UP & LOCKED SENSOR INDUCTANCE AN OUT OF RANGE IAW AMM 32-61-15-5. CHECKED ROLLER GAPS ON LT MLG DOOR LATCH MECHANISM. HOOK & ROLLER ALIGNED & GAPS OK IAW FIM-SENSOR AT FAULT. R & R LT MLG UPLOCK PROX SENSOR RTS PASSED. CHA & CHB INDUCTANCE IN LIMITS. ALL INDICATIONS NORMAL.

Part: DOUBLER — CHAFED (FUSELAGE) · airframe 91,706 hrs · 38,033 cycles

FORWARD CARGO DOOR CUT OUT AFT LOWER EDGE EXISTING REPAIR DOUBLER FOUND WITH CHAFED MARK FROM STATION 959 TO STATION 999, BETWEEN LONGERON 38 RIGHT AND LONGERON 42 RIGHT. DAMAGED EXISTING REPAIR DOUBLER FROM STATION 959 TO STATION 999, BETWEEN LONGERON 38 RIGHT AND LONGERON 42 RIGHT AT LOWER FORWARD CARGO DOOR CUTOUT AFT SIDE REMOVED AND REPLACED WITH NEW FABRICATED DOUBLER PER MD10 SRM 51-31-01 VOLUME II REVISION 101. DOUBLER FABRICATED AS PER MD10 SRM 53-20-00 FIGURE 6 VOLUME I CLASS I REPAIR REVISION 101. REPAIR CLASSIFIED MAJOR PER GMM 6-2-100 REVISION 122.

Part: HINGE — DAMAGED (TE FLAP) · airframe 91,706 hrs · 38,033 cycles

RIGHT WING INBD FLAP ASSEMBLY OTBD HINGE FOUND SURFACE DAMAGED. SURFACE DAMAGED AT RIGHT HAND WING - INBOARD FLAP ASSEMBLY OUTBOARD HINGE REWORKED PER MD10 SRM 57-20-00 VOLUME I REVISION 101. MATERIAL REMOVED: LENGTH 0.650 INCH X WIDTH 0.090 INCH X DEPTH 0.0195 INCH. REPAIR ACCOMPLISHED AS PER EA 8-5750-T0310004 REVISION B PART 1. TITLE: WINGS FLIGHT SURFACES - RT INBOARD FLAP - OUTBOARD HINGE - GOUGE BLEND OUT. REFER TO WRI: 57502984 FOR WORK DETAILS. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 122.

Part: ATTACH FITTING — CRACKED (LT WING) · airframe 91,706 hrs · 38,033 cycles

DURING HIGH FREQUENCY EDDY CURRENT INSPECTION AT LT WING TANK XORS 402 STRINGER 36 BUTTERFLY CLIP FOUND CRACK INDICATION APPROXIMATELY 0.3 INCHES IN LENGTH. REMOVED AND REPLACED IAW SRM 51-31-01 VOLUME II REVISION 101. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: STIFFENER — CRACKED (LT WING) · airframe 91,706 hrs · 38,033 cycles

LEFT WING LE COMPARTMENT FIXED LE STIFFENER AT XOS 665 FOUND CRACKED. REPAIRED IAW EA 8-5710-T0310202 PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: SEAT TRACK — CRACKED (BS 1247) · airframe 91,706 hrs · 38,033 cycles

MAIN DECK CARGO COMPARTMENT SEAT TRACK FLANGE AT BS 1247 X = - 76 FOUND CRACKED. TRIMMED OUT FROM BS 1235 - 1265 IAW SRM 53-70-00 FIGURE 1 VOLUME I REVISION 101. REPAIR FABRICATED AND INSTALLED IAW SRM 53-70-00 FIGURE 1 VOLUME I REVISION 101. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: SPAR CAP — CRACKED (RT WING) · airframe 91,706 hrs · 38,033 cycles

DURING HIGH FREQUENCY EDDY CURRENT INSPECTION OF RT WING, REAR SPAR LOWER CAP FOUND AROUND ONE FASTENER HOLE TO HAVE A CRACK INDICATION. REPAIRED IAW EA 8-5710-T0310288 REVISION A PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 123.

Part: STIFFENER — CRACKED (RT WING) · airframe 91,706 hrs · 38,033 cycles

RIGHT WING LE COMPARTMENT FIXED LE STIFFENER AT STATION XOS 666 FOUND CRACKED. REPAIRED IAW EA 8-5710-T0310204 REVISION A PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: SKIN — CRACKED (LT WING) · airframe 91,706 hrs · 38,033 cycles

LEFT WING LOWER FIXED LE AT NR 14 SLAT TRACK CUT OUT XOS 889 FOUND CRACKED. CRACKED SKIN REPAIRED IAW SRM 57-10-00 FIGURE 68 VOLUME I REVISION 101. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 122.

Part: ATTACH ANGLE — CRACKED (RT WING) · airframe 91,706 hrs · 38,033 cycles

RIGHT WING LE COMPARTMENT FIXED LE SUPPORT RIB AT XOS 584 OTBD ATTACHED ANGLE FOUND CRACKED. ATTACHED ANGLE REMOVED AND REPLACED IAW SRM 51-31-01 VOLUME II REVISION 101. NEW ANGLE FABRICATED IAW DRAWING ARB1162 REVISION S. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 122.

Part: RIB — CRACKED (RT WING) · airframe 91,706 hrs · 38,033 cycles

RIGHT WING LE COMPARTMENT FIXED LE SUPPORT RIB DOUBLER AT XOS 667 FOUND CRACKED. RIB DOUBLER REMOVED AND REPLACED IAW SRM 51-31-01 VOLUME II REVISION 101. NEW RIB DOUBLER FABRICATED IAW DRAWING ARB1249 REVISION AA. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 122.

Part: DOUBLER — CRACKED (RT WING) · airframe 91,706 hrs · 38,033 cycles

RIGHT WING LE COMPARTMENT BEADED DOUBLER AT XOS 554 FOUND CRACKED. NEW DOUBLER FABRICATED AND INSTALLED IAW SRM 57-10-00 FIGURE 71, VOLUME I, REVISION 101. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 122.

Part: DOUBLER — CRACKED (RT WING) · airframe 91,706 hrs · 38,033 cycles

RIGHT LE COMPARTMENT BEADED DOUBLER AT STATION XOS 586 FOUND CRACKED. DOUBLER FABRICATED AND INSTALLED IAW SRM 57-10-00 FIGURE 71, VOLUME I, REVISION 101. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 122.

Part: DOUBLER — CRACKED (RT WING) · airframe 91,706 hrs · 38,033 cycles

RIGHT WING LE COMPARTMENT BEADED DOUBLER AT XOS 666 FOUND CRACKED. DOUBLER FABRICATED AND INSTALLED IAW SRM 57-10-00, FIGURE 71, VOLUME I, REVISION 101. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: TEE FITTING — CRACKED (BS 1156) · airframe 91,706 hrs · 38,033 cycles

CRACK FOUND PROPAGATED APPROXIMATELY .125 INCH IN LENGTH FROM THE STOP DRILL HOLE OF TEE FITTING. FOUND DURING HIGH FREQUENCY EDDY CURRENT INSPECTION INSIDE CTR ACCESSORY BAY AT BS 1156 BETWEEN LONGERONS 38 - 39R. TEE FITTING REPAIRED IAW EA 8-5310-T0309914 REVISION B PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: SKIN — CRACKED (BS 1160) · airframe 91,706 hrs · 38,033 cycles

FUSELAGE SKIN CRACKED APPROXIMATELY TWO INCHES IN LENGTH. FOUND DURING HIGH FREQUENCY EDDY CURRENT INSPECTION INSIDE CTR ACCESSORY BAY AT BS 1160 BETWEEN LONGERON 37 - 38R. SKIN REPAIRED IAW EA 8-5310-T0309914 REVISION B PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: FORMER — CRACKED (LT WING) · airframe 91,706 hrs · 38,033 cycles

LEFT WING LE PANEL SUPPORT FORMER AT XOS 543 FOUND CRACKED. FORMER REMOVED AND REPLACED IAW SRM 51-31-01 VOLUME II REVISION 101. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: STIFFENER — CRACKED (BS 1159 BULKHEAD) · airframe 91,706 hrs · 38,033 cycles

CENTER ACCESSORY COMPARTMENT FWD BULKHEAD ONE STIFFENER FOUND CRACKED AT BS 1159 X = 24. STIFFENER REMOVED AND REPLACED IAW SRM 51-31-01, VOLUME II, REVISION 101. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: DOUBLER — CRACKED (LT WING) · airframe 91,706 hrs · 38,033 cycles

LEFT WING LE BEADED DOUBLER AT XOS 586 FOUND CRACKED. REPAIR DOUBLER FABRICATED AND INSTALLED IAW SRM 57-10-00 FIGURE 71 VOLUME I REVISION 101. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: DOUBLER — CRACKED (LT WING) · airframe 91,706 hrs · 38,033 cycles

LEFT WING LE BEADED DOUBLER AT XOS 645 FOUND CRACKED. REPAIR DOUBLER FABRICATED AND INSTALLED IAW SRM 57-10-00 FIGURE 71 VOLUME I REVISION 101. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: SKIN — CRACKED (LT WING) · airframe 91,706 hrs · 38,033 cycles

LEFT WING LOWER FIXED LE AT REFUELING ACCESS DOOR CUT OUT OTBD FWD CORNER AT XOS 643 FOUND CRACKED. REPAIRED IAW SRM 57-10-00, FIGURE 68 VOLUME I, REVISION 101. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: ATTACH ANGLE — CRACKED (LT WING) · airframe 91,706 hrs · 38,033 cycles

LEFT WING LE FIXED LE SUPPORT RIB AT XOS 584 OTBD ATTACHED ANGLE FOUND CRACKED. RIB ATTACH ANGLE REMOVED AND REPLACED AS PER SRM 51-31-01 VOLUME II REVISION 101. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: DOUBLER — CRACKED (LT WING) · airframe 91,706 hrs · 38,033 cycles

LEFT WING LE BEADED DOUBLER AT XOS 770 FOUND CRACKED. REPAIR DOUBLER FABRICATED AND INSTALLED IAW SRM 57-10-00 FIGURE 71 VOLUME I, REVISION 101. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: SKIN PANEL — DENTED (FUSELAGE) · airframe 91,706 hrs · 38,033 cycles

LOWER FUSELAGE PLATE & SKIN WITH REPAIR DENT AT STATION 1831 BETWEEN LONGERON 37 RT & LONGERON 38 RT IAW 8-5330-160630. REPAIR DENT AT STATION 1831 BETWEEN LONGERON 37 RIGHT AND 38 RIGHT. PERFORM REPETITIVE INSPECTION BY 125 FLIGHT HOURS OR AT EVERY A-CHECK NOT TO EXCEED 90 DAYS UNTIL C-10 CHECK WHICHEVER COMES FIRST. TO PERFORM PERMANENT REPAIR WITHIN 730 DAYS. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 122.

Part: POWER SUPPLY — NO TEST (EMERGENCY LIGHTS) · airframe 91,594 hrs · 37,983 cycles

EMERGENCY LIGHT BATTERY 1 LOW ILLUMINATED DURING TEST. REMOVED AND REPLACED EMERGENCY LIGHT POWER SUPPLY IAW AMM 33-51-01-4

Part: SKIN — CRACKED (LT WING) · airframe 91,443 hrs · 37,917 cycles

ON POST FLIGHT WALK AROUND FOUND CRACK LT WING SLAT TRACK CUT OUT OTBD OF REFUELING PANEL. COMPLIED WITH HFEC INSPECTION & VERIFIED CRACK TO BE 1.1" IN LENGTH. REMOVED PANEL 579DB FOM & PLACED IN CREW AREA. IAW SRM MD10 57-10-00 MATERIAL ID 6AL4V .063 TITANIUM EXTERNAL DOUBLER MP 64228 & FILLER 7075 T6 .090 MP 1681501. REMOVED FASTENERS IAW SRM MD10 51-31-01 VOL 2 & REMOVED DAMAGE IAW SRM MD10 57-10-00 REQUIRES HFEC INSPECTION. VERIFIED DAMAGE, REMOVED BY HFEC INSPECTION. NO OTHER ANOMALIES NOTED IAW NTM 20-30-00 PT6. FABRICATED REPAIR DOUBLER, TREATED & PRIMED MATING SURFACES IAW SRM57-10-00. OK TO INSTALL, INSTALLED REPAIR DOUBLER IAW SRM.

Part: SKIN — CRACKED (RT WING LE) · airframe 91,404 hrs · 37,898 cycles

FOUND RT WING FIXED LE PANEL CRACKED AT INBD FWD SIDE OF FIRE EXTINGUISHER DOOR. FABRICATED DOUBLER, DRILLED & COUNTERSUNK, AND FABRICATED FILLER IAW SRM 57-10-00 FIG 68 SHEET 2. REPAIRED RT FIXED LE IAW EA 8-5730-T0307712 PART 1. MAJOR REPAIR.

Part: SOCKET — BURNED (CARGO LIGHT) · airframe 89,718 hrs · 37,018 cycles

LOAD CREW REPORTED BURNING ODOR. FOUND AFT OVERHEAD LIGHT LAMP HOLDER BURNED. REPLACED LIGHT ASSY IAW MM 33-31-01-2.

Part: FRAME — CORRODED (BS 1841) · airframe 89,211 hrs · 36,740 cycles

AFT CARGO BAY BS 1841 FRAME CORRODED. REMOVED DAMAGED AREA. FABRICATED, DRILLED, DEBURRED, ALODINED & PRIMED REPAIR ANGLE & SPLICE & FILLER IAW SRM53-30-00. FRAME REPAIRED IAW SRM.53-30-00, VOL I AND ER 12-03855.

Part: SKIN — DENTED (BS 1831) · airframe 89,211 hrs · 36,740 cycles

LOWER FUSELAGE SKIN AFT OF CENTER CARGO DOOR SHOWING DENT APPROX 3 INCHES LONG. INSTALLED DOUBLER IAW EA 8-5330-160630 & SRM 53-20-00, FIG 3, SHEET 8.

Part: FLOORBEAM — CORRODED (BS 1841) · corrosion level 2 · airframe 89,211 hrs · 36,740 cycles

AFT CARGO BAY BS 1841 FLOORBEAM CORRODED AT SEVERAL FLOORBOARD NUTPLATE HOLES. REMOVED AND REPLACED CORRODED FLOORBEAM IAW DWG AGA 3874 AND SRM 51-35-01 VOL. 2.

Part: ANGLE — CRACKED (BS 575-595) · airframe 89,211 hrs · 36,740 cycles

AIR CONDITIONING COMPARTMENT NR 3 - BETWEEN BS 575 - 595 AT L30. CAL ANGLE IS CRACKED APPROX 8.00". REPAIRED IAW SRM.

Part: ANGLE — CRACKED (BS 555-575) · airframe 89,211 hrs · 36,740 cycles

AIR CONDITIONING COMPARTMENT NR 3 - BETWEEN BS 555-575 AT L30. ANGLE IS CRACKED APROX 8".

Part: BUTTON — INOPERATIVE (L2 DOOR SLIDE) · airframe 89,170 hrs · 36,720 cycles

ON WALK AROUND, FOUND LT ENTRY DOOR SLIDE PRESS TO TEST LIGHT INOPERATIVE. REPLACED BATTERIES, NO HELP, REPLACED TEST BUTTON WITH R1 LIGHT BUTTON CHECKED GOOD. REMOVED AND REPLACED L1 DOOR SLIDE PRESSURE PTT ASSEMBLY REF AMM 25-61-03-2. OPS CHECKED GOOD.

Part: DIMMER — BURNED (INSTRUMENT LIGHT) · airframe 88,713 hrs · 36,471 cycles

NOTED SLIGHT ELECTRICAL OVERHEAT ODOR IN COCKPIT. R & R OVERHEAD INSTRUMENT LIGHTING DIMMER IAW MM 33-11-03-2-0. OK FOR SVC. PREMATURE REMOVAL/INSTALLATION.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 88,297 hrs · 36,240 cycles

ACFT SKIN AND RIVETS ARE DAMAGED 6 IN TO THE LT OF THE LOWER BEACON. REPAIRED IAW EA 8-5330-155553.

Part: SKIN — CRACKED (ZONE 100) · corrosion level 2 · airframe 88,297 hrs · 36,240 cycles

ACFT SKIN AND RIVETS ARE DAMAGED 6 INCHES TO THE LT OF THE LWR BEACON. REPAIRED SKIN IAW EA8-5330-155553. REF; SERVICE REQUEST 1-2004950126, SRM 53-20-00, FIG 6.

Part: WIRE — DAMAGED (MLG) · airframe 87,999 hrs · 36,061 cycles

AFTER T/O GEAR RETRACTION RECEIVED 3 RED (UNSAFE) ON FWD PANEL & 3 RED ON CONFIG PAGE. COMPLIED WITH QRH. SAME RESULT. RETURNED TO DEPARTURE FOR UNEVENTFUL LANDING. FOUND NO CONTINUITY BETWEEN PINS A AND B OF THE GEAR HANDLE SWITCH. R & R GEAR HANDLE SWITCH. TEST GOOD. FINAL CLOSED.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

LT WING SIDE OTBD FLAP, OTBD HINGE, BARREL NUT LOWER BORE HOLE FOUND CORRODED AFTER BUSHING REMOVED. LT WING SIDE OUTBOARD FLAP OUTBOARD HINGE BARREL NUT LOWER BORE HOLE REWORKED AS PER EA 8-5740-132487, BUSHING FABRICATED AND INSTALLED AS PER EA 8-5740-132487. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REVISION 110.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

LT WING SIDE OTBD FLAP INBD HINGE BARREL NUT LOWER BORE HOLE FOUND CORRODED AFTER BUSHING REMOVED. REWORKED AS PER EA 8-5740-132489, BUSHING FABRICATED AND INSTALLED AS PER EA 8-5740-132489. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REVISION 110.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

RT WING SIDE OTBD FLAP INBD HINGE AFTER PIVOT POINT BUSHING REMOVED, BORE FOUND CORRODED. BORE FOUND CORRODED RT WING SIDE OTBD FLAP INBD HINGE PIVOT POINT REWORKED IAW EA 8-5740-132488, REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100 REV 110.

Part: STIFFENER — CRACKED (BS 1160-1169) · airframe 86,815 hrs · 35,442 cycles

CABIN STA 1160 TO 1169 XCW=0 CTR WING TANK UPPER SURFACE STIFFENER FOUND CRACKED. REMOVED AND REPLACED PER SRM 51-31-01 VOLUME II REVISION 96. NEW STIFFENER REWORKED FROM S1325739S TEE EXTRUSION 7075-0-0-094" AS PER DRAWING NPB 6072 REVISION AL. REPAIR CLASSIFIED MINOR PER GMM 6-2-100 REVISION 110.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 86,815 hrs · 35,442 cycles

LT WING OTBD FLAP OTBD HINGE BARREL NUT SURFACE FOUND CORRODED. LT WING SIDE OTBD FLAP, OTBD HINGE BARREL NUT SURFACE REWORKED IAW EA 8-5740-132487, MATERIAL REMOVED 0.008", REMAINING THICKNESS 0.418". REPAIR EVALUATED AND FOUND REMAINING THICKNESS 0.394"(UPPER) AND 0.418"(LOWER) ACCEPTED IAW EA NR8-5740-132487. SHIM FABRICATED AND INSTALLED IAW EA8-5740-132487. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

LT WING SIDE OTBD FLAP, OTBD HINGE, BARREL NUT BORE FOUND CORRODED AFTER BUSHING REMOVED. LT WING SIDE OTBD FLAP, OTBD HINGE BARREL NUT BORE HOLE REWORKED IAW EA 8-5740-132487, BUSHING FABRICATED AND INSTALLED IAW EA 8-5740-132487. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

RT WING SIDE OTBD FLAP, INBD HINGE, BARREL NUT UPPER BUSHING FOUND CORRODED. BUSHING REMOVED AND FOUND BORE EXCEED LIMIT IAW CMM 57-44-08 REV 50. EXISTING BORE DIAMETER 0.494", MAXIMUM BORE DIA 0.490". BUSHING FABRICATED AND INSTALLED IAW EA 8-5740-132488. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100 REV 110.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

LT WING SIDE OTBD FLAP INBD HINGE PIVOT POINT BORE HOLE FOUND CORRODED AFTER BUSHING REMOVED. REWORKED AS PER EA 8-5740-132489, BUSHING FABRICATED AND INSTALLED AS PER EA 8-5740-132489. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REVISION 110.

Part: HINGE BRACKET — CORRODED (LT WING) · airframe 86,815 hrs · 35,442 cycles

LT WING SIDE OTBD FLAP INBD HINGE BARREL NUT UPPER BORE HOLE FOUND CORRODED AFTER BUSHING REMOVED. REWORKED AS PER EA 8-5740-132489, BUSHING FABRICATED AND INSTALLED AS PER EA 8-5740-132489. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REVISION 110.

Part: HINGE BRACKET — CORRODED (LT WING) · airframe 86,815 hrs · 35,442 cycles

LEFT WING SIDE OTBD FLAP INBD HINGE FWD MOUNT OTBD BORE HOLE FOUND CORRODED AFTER BUSHING REMOVED. LT WING SIDE OUTBOARD FLAP INBOARD HINGE FORWARD MOUNT OUTBOARD BORE HOLE REWORKED AS PER EA 8-5740-132489, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REVISION 110.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

LT WING SIDE OTBD FLAP INBD HINGE BARREL NUT UPPER BUSHING FOUND CORRODED. BUSHING REMOVED AND F0UND BORE EXCEED LIMIT AS PER CMM 57-44-08 REVISION 50. EXISTING BORE DIAMETER 0.5045", MAXIMUM BORE DIAMETER 0.490". REPAIRED AND INSTALLED BUSHING AS PER EA 8-5740-132489, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REVISION 110.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

LT WING OTBD FLAP, OTBD HINGE, BARREL NUT UPPER BORE HOLE FOUND CORRODED AFTER BUSHING REMOVED. REWORKED IAW EA NR 8-5740-132487, REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

RT WING SIDE OTBD FLAP INBD HINGE BARREL NUT SURFACE FOUND CORRODED. RT WING SIDE OTBD FLAP INBD HINGE BARREL NUT SURFACE REWORKED IAW EA 8-5740-132488, REPAIR CLASSIFIED AS MINOR IAWGMM 6-2-100, REV 110.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

LT WING SIDE OTBD FLAP INBD HINGE BARREL NUT SURFACE FOUND CORRODED. HINGE BARREL NUT SURFACE REWORKED AS PER EA 8-5740-132489, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REVISION 110.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

LT WING SIDE OTBD FLAP INBD HINGE BARREL NUT LOWER BUSHING FOUND CORRODED. LOWER BUSHING REMOVED AND F0UND BORE EXCEED LIMIT AS PER CMM 57-44-08 REVISION 50. EXISTING BORE DIAMETER 0.502", MAXIMUM BORE DIAMETER 0.490". REPAIRED AND INSTALLED BUSHING AS PER EA 8-5740-132489, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REVISION 110.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

LT WING SIDE OTBD FLAP INBD HINGE FWD MOUNT OTBD BUSHING FOUND CORRODED. BUSHING REMOVED AND FOUND BORE EXCEED LIMIT AS PER CMM 57-44-08 REVISION 50. EXISTING BORE DIAMETER 1.259", MAXIMUM BORE DIAMETER 1.254". REPAIRED AND INSTALLED BUSHING AS PER EA 8-5740-132489, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REVISION 110.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

RT WING SIDE OTBD FLAP INBD HINGE BARREL NUT LOWER BUSHING FOUND CORRODED. BUSHING REMOVED AND FOUND BORE EXCEED LIMIT IAW CMM 57-44-08 REV 50. EXISTING BORE DIA 0.4965", MAXIMUM BORE DIAMETER 0.490". BUSHING FABRICATED AND INSTALLED IAW EA NR 8-5740-132488, REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

RT WING SIDE OTBD FLAP, INBD HINGE UPPER MOUNT FWD FACE FOUND CORRODED. REWORKED IAW EA 8-5740-132488, REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100 REV 110.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

RT WING SIDE OTBD FLAP OTBD HINGE BARREL NUT FOUND SURFACE CORROSION. REWORKED IAW EA NR 8-5740-132486, SHIM FABRICATED AND INSTALLED IAW EA NR8-5740-132486. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: HINGE — CORRODED (RT WING TE FLAP) · airframe 86,815 hrs · 35,442 cycles

RT WING OTBD FLAP INBD HINGE PIVOT POINT INBD BORE HOLE FOUND CORRODED. REWORKED IAW EA NR 8-5750-132465, REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: FRAME — CRACKED (BS 1781 S11R) · airframe 86,815 hrs · 35,442 cycles

CABIN RT STA 1781, STR 11R, FRAME FOUND CRACKED. REPAIRED IAW SRM 53-30-00, FIG 5 (SHEET 1) VOL I, REV 96. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 110. INITIAL INSP TO BE CARRIED OUT ON 12,000 FLIGHT CYCLES AND REPETITIVE INSP ON 8,000 FLIGHT CYCLES.

Part: SKIN — CRACKED (NR 3 SLAT) · airframe 86,815 hrs · 35,442 cycles

DURING WALK AROUND CHECK LT WING ADJACENT TO NR 3 SLAT L/E TELESCOPIC DUCT CUT-OUT UPPER SECTION FOUND CRACKED. REPAIR ACCOMPLISHED PER EA 8-5710-140449. REPAIRED CLASSIFIED AS MAJOR PER GMM 6-2-100 REV 110.

Part: SKIN — CRACKED (RT WING) · airframe 86,815 hrs · 35,442 cycles

DURING WALKAROUND CHECK, RT WING ADJACENT TO NR 3 SLAT L/E TELESCOPIC DUCT CUT-OUT UPPER SECTION FOUND CRACKED.

Part: CONNECTOR — LOOSE (DOOR WARNING) · airframe 86,347 hrs · 35,202 cycles

CAD DOOR ALERT PASSING 26,000 FT DESCENDED TO 8000 FT DUMPED 10,000 GAL FUEL. UNEVENTFUL LANDING. NO PRESSURIZATION PROBLEM. FOUND CONNECTOR PLUG LOOSE ON CAC DOOR SWITCH. REINSTALLED CONNECTOR PLUG IAW SMP. OPS CHECK NORMAL. ACFT OK FOR SERVICE. CLOSED

Part: FILTER — FOULED (NR 2 ACM) · airframe 84,838 hrs · 34,444 cycles

APPROX 20 MINUTES AFTER TAKEOFF, SMOKE AND FUMES WERE DETECTED IN THE COCKPIT. APPEARED TO BE ELECTRICAL IN ORIGIN. PREVIOUS TO THIS, NR 1 PACK WAS INDICATING -21F AND GETTING COLDER. NR 2 PACK WAS OFF AND WAS TURNED BACK ON. THEN NR 1 PACK WAS TURNED OFF. QRH PROCEDURE FOR SMOKE/FUMES COMPLETED, DIVERTED. INSPECTED BOTH FWD AVIONICS BAY & CAC FOR EVIDENCE OF SMOKE. NONE FOUND. INSPECTED BEHIND FLT DECK C/B PANELS FOR EVIDENCE OF SMOKE. NONE FOUND. INSPECTED COALESCER BAGS & FOUND NR 2 ACM FILTER FOULED. UNABLE TO GET TURBINE BYPASS VALVE FUNCTIONING ON NR 1 PACK. PLACED NR 1 & 2 PACK ON MEL. REPLACED COALESCER BAGS, NR1 PACK TURBINE BYPASS VALVE AND RAM AIR INLET DOOR ACTUATOR.

Part: RIB — CRACKED (NR 2 NACELLE) · airframe 83,901 hrs · 34,003 cycles

NR 2 ENG BEAVER TAIL NR 2 AND NR 3 RIB CRACKED OR MISSING AT TRAILING EDGE. REMOVED DAMAGED RIB AND INSTALLED NEW RIBS REFERENCE DC/MD-10 SRM 51-35-01; VOL II AND 51-31-01; VOL II.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

RIGHT WING INBD FLAP LOWER SKIN SURFACE HAS AREAS OF DENTS. FABRICATED A NEW SKIN PANEL ASSEMBLY IAW EA NR 8-5750-118534.

Part: SUPPORT BRACKET — GOUGED (NR 1 PYLON) · airframe 83,901 hrs · 34,003 cycles

NR 1 ENGINE PYLON, THROTTLE INTERLOCK ACTUATOR AFT SUPPORT BRACKET IS GOUGED. REMOVED DIRECTIONAL PILOT VALVE PUSH ROD IAW MD-10-10 AMM 76-10-03-02. REMOVED, FABRICATED AND INSTALLED AUL 7047-7 SUPPORT IN REF TO DAC DWG AUL 7047, REF "F". ALODINED AND PRIMED IN REF TO DC/MD-10 SRM 51-21-01; VOL II. INSTALLED THE PUSH ROD IAW FEDEX MD-10-10 AMM 76-10-03-02.

Part: RIB — CRACKED (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

NR 1 PYLON ATTACH FLANGE FOR PANEL 438 GL IS CRACKED. REMOVED AND REPLACED RIB NR AUB 7107-39, PO 625780.4 IAW DAC DWG AUB 7107, REV "P" AND DC/MD-10 SRM 51-35-01, VOL II.

Part: PANEL — CORRODED (ZONE 600) · airframe 83,901 hrs · 34,003 cycles

RIGHT WING FUEL PANEL 636 BB IS PITTING ON THE MATING SURFACES. FABRICATED A NEW FUEL PANEL IAW SRM 57-10-00; VOL I AND DWG ARB 0975-536, REV AY.

Part: SKIN — CHAFED (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

NR 2 ENGINE BEAVER TAIL LEFT SIDE SKIN IS CHAFED UNDER NR 2 AND 3 RIBS. REMOVED DAMAGE IAW DC/MD-10 SRM 54-20-00; VOL I, FIG 9. FABRICATED REPAIR IAW DC/MD-10 SRM 54-20-00; VOL I; FIG 9. INSTALLED IAW DC/MD-10 SRM 51-31-01; VOL II.

Part: FITTING — WORN (ZONE 100) · airframe 83,901 hrs · 34,003 cycles

MAIN CARGO DOOR JAMB AT SPOOL FITTING NR 4; HOLE "D" IS OVERSIZED TO 0.519. VERIFIED HOLE "D" TO BE .5192 MEASURED WITH TOOL NR T8723K; MATERIAL ID FOR 3 EA FREEZE PLUGS FOR 4-"D" IS 7075-T6 AC BAR, PO 529774.6. FABRICATED AND LOCATED HOLE IAW SRM 53-50-00, VOL I, PG 81. FINAL HOLE SIZE 0.453.5.

Part: FITTING — DAMAGED (DOOR FRAME) · airframe 83,901 hrs · 34,003 cycles

MAIN CARGO DOOR JAMB AT SPOOL FITTING NR 2, HOLE "D" IS OVERSIZED TO 0.545 INCH. REMOVED WEB AND STRUCTURE IN REF TO DC/MD-10 SRM 51-33-01; VOL II AND 51-35-01; VOL II. REMOVED BACK UP FITTING IN REF TO DC/MD-10 SRM 51-33-01; VOL II. LOCATED AND DRILLED THE BACK UP FITTING IN REF TO DAC DWG AFA 7132; REV "B". INSTALLED BACK UP FITTING, REF TO DC/MD-10 SRM 51-33-01; VOL II. INSTALLED BUSHING ON THE BEAM IN REF TO EA 8-5310-117003 "FUSELAGE, MAIN DECK CARGO DOOR JAMB LOWER SEAL OVERSIZED HOLES AT THE NR 1 AND NR 2 SPOOL FITTINGS REPAIR".

Part: SUPPORT FITTING — DAMAGED (ZONE 200) · airframe 83,901 hrs · 34,003 cycles

MAIN CARGO DOOR JAMB AT SPOOL FITTING NR 6; HOLE "A" HAS A CRACK INDICATION IN THE BACK UP FITTING, (HOLE IS 0.574 INCH DIA.) REMOVED SUBSTRUCTURE AND WEB TO GAIN ACCESS TO THE NR 6 SPOOL BACK UP FITTING IAW SRM 51-33-01; VOL II. LOCATED AND DRILLED NEW BACK UP FITTING IAW 51-33-01; VOL II. INSTALLED NEW BACK UP FITTING AFA 7132-1 IAW SRM 51-33-01; VOL II. RE-INSTALLED SUB STRUCTURE AND WEB IAW SRM 51-33-01; VOL II. INSTALLED BUSHING IAW SRM 53-50-11; VOL I.

Part: FITTING — DAMAGED (DOOR FRAME) · airframe 83,901 hrs · 34,003 cycles

MAIN CARGO DOOR JAMB AT SPOOL FITTING NR 1, HOLE "A" IS OVERSIZED TO 0.536 INCH. REMOVED SUB STRUCTURE AND WEB TO GAIN ACCESS TO THE NR 1 SPOOL BACK UP FITING IAW SRM 51-31-01;VOL II. LOCATED AND DRILLED NEW BACK UP FITTING AFA 7135-1IAW SRM 51-31-01; VOL II. INSTALLED NEW BACK UP FITTING IAW SRM 51-33-01; VOL II. INSTALLED SNU STRUCTURE AND WEB IAW SRM 51-33-01; VOL II. INSTALLED BUSHING IAW SRM 53-50-00, VOL I.

Part: FITTING — DAMAGED (ZONE 200) · airframe 83,901 hrs · 34,003 cycles

MAIN CARGO DOOR JAMB SPOOL FITTING NR 7 HAS A CRACK INDICATION IN THE BACK UP FITTING AT HOLE "A". HOLE "A" HOLE DIS IS 0.519". REMOVED SUBSTRUCTURE AND WEB TO GAIN ACCESS TO THE NR 7 SPOOL BACK UP FITTING IAW SRM 51-33-01; VOL II. LOCATED AND DRILLED NEW BACK UP FITTING IAW 51-33-01; VOL II. INSTALLED NEW BACK UP FITTING AFA 7132-1 IAW SRM 51-33-01; VOL II. RE-INSTALLED SUB STRUCTURE AND WEB IAW SRM 51-33-01; VOL II. INSTALLED BUSHING IAW SRM 53-50-11; VOL I.

Part: SKIN — DELAMINATED (NR 2 SPOILER) · airframe 83,901 hrs · 34,003 cycles

THE RIGHT WING NR 2 SPOILER IS DELAMINATED ON THE LOWER SURFACE AT THE OUTBOARD CORNER. REMOVED NR 2 RT WING SPOILER IAW AMM 27-60-01-4. REPAIRED BY REMOVING DELAMINATED LOWER SKIN; DOUBLER & CORE. FABRICATED & BONDED A NEW LOWER SKIN; DOUBLER & CORE IAW SRM 57-10-00; VOL I & DWG ARC 1347. INSTALLED THE HARDWARE & SEALS IAW SRM 51-31-01 & 57-10-00; VOL I. SEALED & PAINTED SPOILER IAW SRM 51-41-01; VOL II & SRM 51-21-02; VOL II. RE-INSTALLED NR 2 RT WING SPOILER PER AMM 27-60-01-4. GAP & OPS CHECKS GOOD PER AMM 27-60-01-4 & 27-60-01-6.

Part: SKIN — DELAMINATED (NR 2 SPOILER) · airframe 83,901 hrs · 34,003 cycles

LEFT WING SPOILER NR 2 IS DELAMINATED ON THE LOWER SURFACE AT THE INBD CORNER.

Part: SKIN — DELAMINATED (NR 3 SPOILER) · airframe 83,901 hrs · 34,003 cycles

THE RIGHT WING NR 3 SPOILER IS DELAMINATED ON THE LOWER SURFACE AT THE INBD CORNER. REPLACED THE LOWER SKIN; DOUBLER & PARTIAL CORE. BONDED REPAIR IAW SRM 57-10-00; VOL I & SRM 51-71-00; VOL II. PRIMED & SEALED SPOILER IAW SRM 51-21-01; VOL II. REMOVED; RE-INSTALLED & THE GAP & OPS CHECKS ARE GOOD IAW MD-10 AMM 67-60-01-4 & 27-60-01-1.

Part: SKIN — CRACKED (RT WING) · airframe 83,901 hrs · 34,003 cycles

RIGHT WING L/E PANEL 615 DB IS CRACKED AT A FASTENER HOLE. FABRICATED A NEW REPAIR DOUBLER & LOCATED THE HOLES IAW SRM 57-00-01 & 57-10-00 VOL I PG 12-A FIG 4. ALODINED & PRIMED IAW SRM 51-21-01; VOL II. INSTALLED IAW SRM 51-31-01 VOL II.

Part: PANEL — WORN (ZONE 500) · airframe 83,901 hrs · 34,003 cycles

LEFT WING INBD L/E PANEL 516 HB IS WORN ON THE EDGE OF THE PANEL. BLENDED PANEL 516 NB AND FOUND TO BE OUT OF LIMITS IAW SRM 57-00-01; VOL I. FABRICATED DOUBLER IAW SRM 57-00-01; VOL I. ALODINED AND PRIMED IAW SRM 51-21-01; VOL II. PAINTED DOUBLER IAW SRM 51-21-02; VIL II. INSTALLED DOUBLER IAW SRM 51-35-01; VOL II AND 57-00-01; VOL I.

Part: SKIN — DELAMINATED (NR 2 SPOILER) · airframe 83,901 hrs · 34,003 cycles

THE LEFT WING NR 2 SPOILER IS DELAMINATED ON THE LOWER SURFACE AT THE OUTBD CORNER. REMOVED & REPLACED THE NR 2 LT WING SPOILER PER AMM 27-60-01-4. OPS & GAP CHECKS ARE GOOD PER AMM 27-60-01-4 & 27-60-01-6.

Part: SKIN — DELAMINATED (NR 2 SPOILER) · airframe 83,901 hrs · 34,003 cycles

THE RIGHT WING NR 2 SPOILER SKIN IS DELAMINATED ON THE LOWER SURFACE AT THE INBD CORNER. THE REPAIR OF THE INBD LOWER CORNER OF THE RT WING NR 2 SPOILER WAS ACCOMPLISHED ON NON-ROUTINE N00269.

Part: SKIN — DELAMINATED (NR 5 SPOILER) · airframe 83,901 hrs · 34,003 cycles

THE LEFT WING NR 5 SPOILER IS DELAMINATED ON THE LOWER SURFACE AT THE INBD CORNER. REMOVED LEFT NR 5 SPOILER IAW MD-10 AMM 27-60-01-4. REPAIRED THE LEFT NR 5 SPOILER BY REMOVING THE DELAMINATED LOWER SKIN DOUBLER, CORE SECTION AND END RIB. FABRICATED AND BONDED A NEW CORE SECTION, LOWER SKIN; DOUBLER AND END RIB IAW DC/MD-10 SRM57-10-00; VOL I AND DAC DWG ACA 1347. INSTALLED SEALS AND HARDWARE IAW DC/MD-10 SRM 51-31-01, VOL II. PAINTED SPOILER IAW DC/MD-10 SRM 51-21-01; VOL II.

Part: SKIN — DELAMINATED (RT WING SPOILER) · airframe 83,901 hrs · 34,003 cycles

THE RIGHT WING NR 3 SPOILER IS DELAMINATED ON THE LOWER SURFACE AT THE OUTBD CORNER. REPLACED THE LOWER SKIN, DOUBLER AND PARTIAL CORE THEN BONDED IT IAW DC/MD-10 SRM 57-10-00, VOL I AND SRM 51-71-00, VOL II. PRIMED AND SEALED IAW DC/MD-10 SRM 51-21-01, VOL II. ACCOMPLISHED ALL WORK ON W/O 3283309 AND NON-ROUTINE NR N00270.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

RIGHT WING INBD FLAP LOWER SURFACE SKIN HAS MULTIPLE DENTS INBD OF THE SPRING CARTRIDGE. CHECKED DENTS AND FOUND TO BE OUT OF LIMITS IAW SRM 57-10-00; VOL I; FIG 48 AT STA XIFH 250 AT 254. REMOVED THE LOWER SKIN WEDGE SKIN IAW SRM 51-35-02; VOL II. RECEIVED NEW SKIN ASSY. FABRICATED ON N01033. LOCATED; DRILLED AND INSTALLED NEW SKIN ASSY IAW SRM 51-31-01; 51-35-01; VOL II AND DWG ARC 2735, REV S. ALODINED AND PRIMED IAW SRM 51-21-01; VOL II.

Part: SKIN — DELAMINATED (ZONE 500) · airframe 83,901 hrs · 34,003 cycles

PANEL, LEFT WING LOWER SURFACE, FWD OF THE MLG WELL IS DELAMINATED. REMOVED AND REPLACED THE LEFT WING T/E PANEL P/N ARC 0280-503, PO 627171.3 IAW DWG ARC 0448, REV "BG" AND SRM 51-31-01; VOL II.

Part: RUB STRIP — WORN (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

NR 3 PYLON PANEL 487 CL HAS BOTH FLANGES WORN. BLENDED RUB STRIPS. ORIGINAL MATERIAL 0.063. MATERIAL REMOVED 0.040. MATERIAL REMAINING 0.023. FOUND TO BE OUT OF LIMITS IAW SRM 54-00-01; VOL I AND 54-31-01; VOL II. PRIMED RUB STRIPE IAW SRM 51-21-01; VOL II. INSTALLED RUB STRIPS IAW SRM 51-31-01; VOL II AND DWG AUB 7038, REV AC. FABRICATED RUB STRIPS IAW DWG AUB 7038, REV AC.

Part: PANEL — WORN (NR 3 NACELLE) · airframe 83,901 hrs · 34,003 cycles

NR 3 PYLON PANEL 437 DL HAS ELONGATED HOLES. REPAIRED PANEL 437 DL IN REF TO EA 8-5480-116998 P/N AUB 7038-7.

Part: SKIN — CHAFED (NACELLE DOOR) · airframe 83,901 hrs · 34,003 cycles

NR 1 PYLON PANEL 437 LL IS CHAFED AT THE FASTENER HOLES. BLENDED AREA IAW DC/MD-10 SRM 54-00-01, VOL I, FIG 1-A. ORIGINAL MATERIAL THICKNESS 0.071 IAW DC/MD-10 SRM 54-51-0 AND FOUND TO BE OUT OF LIMITS 54-00-01, VOL I, FIG 1-A. UT GAUGE USED IS T8225P. MATERIAL ID THE PANEL IS 7075-T6, 0.071, PO 623403.4 AND THE FILLER IS 2024-T3, 0.016, PO 346313.2 IN REF TO DAC DWG AUB 7108, REV AN. FABRICATED THE PANEL AND FILLER IAW DAC DWG AUB 7108, REV AN. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01, VOL II, PGS 21-24. ASSEMBLED PANEL IAW DAC DWG AUB 7108, REV AN. PART MARKED PANEL IAW FEDEX GMM 7-0-1001.

Part: PANEL — CRACKED (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

NR 1 PYLON PANEL 437 DR INNER SKIN IS CRACKED. RECEIVED NEW PRECOOLER VENTILATOR ASSEMBLY P/N AUB 7054-501, PO 626793.1. LOCATED AND DRILLED IN REF TO DC/MD-10 SRM 51-31-01; VOL II AND DAC DWG AUB 7054; REF "J".

Part: FAIRING — WORN (NR 3 PYLON) · airframe 83,901 hrs · 34,003 cycles

NR 3 PYLON PANEL 488 CR IS WORN AT THE FASTENER HOLES. BLENDED WORN AREA OUT OF LIMITS. ORIGINAL MATERIAL 0.050. MATERIAL REMOVED IS 0.011. MATERIAL REMAINING IS 0.039 REF DC/MD-10 SRM 54-00-01, VOL I. FABBED REPAIR DOUBLER AND INSTALLED DOUBLER REF DC/MD-10 SRM 54-00-01, VOL I AND SRM 51-33-01, VOL II.

Part: RIB — CHAFED (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

NR 3 PYLON PANEL 487 CL HAS A CHAFED RIB. BLENDED RIB IAW SRM 54-00-01; VOL I. FOUND TO BE OUT OF LIMITS IAW SRM 54-00-01; VOL I. LOCATED AND DRILLED HOLES IAW DWG AUB 7080; REV A. ALODINED AND PRIMED IAW SRM 51-21-01; VOL II. MARKED PART AUB 7080-3 IAW GMM 7-0-1001. INSTALLED AUB 7080-3 IAW DWG AUB 7080, REV A.

Part: SUPPORT ANGLE — CRACKED (ZONE 100) · airframe 83,901 hrs · 34,003 cycles

MID CARGO CEILING WEB PANEL IS CRACKED AT THE DOOR MOTOR AREA. REMOVED CEILING SUPPORT ANGLE AT FS 1741 - 1761, BL 95. FABRICATED NEW SUPPORT ANGLE IAW DAC DWG AFA 0161, REV AV. MATERIAL ID 2024-0, 0.040, PO 548001.2. HEAT TREAT ANGLE IAW TPS 1003, REV A. LOCATED AND DRILLED ANGLE IAW DAC DWG AFA 0161, REV AV. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01, VOL III. INSTALLED SUPPORT ANGLE IAW DC/MD-10 SRM 51-31- 01, VOL II.

Part: SKIN — CRACKED (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

NR 1 PYLON PANEL 437 DOOR SKIN IS CRACKED AT A FASTENER HOLE. 3 1 PYLON PANEL 437 DOOR WAS REPLACED ON N/R N00808. SEE SDR TRACKING NR 08-3031 FOR THE DETAILED INFORMATION.

Part: PANEL — CHAFED (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

NR 3 PYLON PANEL 488 AL IS CHAFED. FABRICATED DOUBLER AND FILLER IAW SRM 51-21-01;VOL II; FIG 2-B. ALODINED AND PRIMED FILLERS IAW SRM 51-21-01; VOL II. INSTALLED REPAIR PARTS IAW SRM 54-00-01; VOL I; FIG 2-B AND EA 8-5480-123601.

Part: PANEL — CHAFED (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

NR 1 PYLON PANEL 438 OL IS CHAFED IN 2 PLACES. FABRICATED DOUBLER AND FILLER IAW SRM 51-21-01; VOL II; FIG 2-B. ALODINED AND PRIMED FILLERS IAW SRM 51-21-01; VOL II. INSTALLED REPAIR PARTS IAW SRM 54-00-01; VOL I; FIG 2-B AND EA 8-5480-123601.

Part: PANEL — CHAFED (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

NR 1 PYLON PANEL 437 FR IS CHAFED AT FASTENER HOLES. NR 1 PYLON PANEL 437 FR WAS CHAFED BEYOND ALLOWABLE LIMITS REQUIRED SRM REPAIR IAW DC/MD-10 SRM 54-00-01, VOL I. MATERIAL ID FOR SRM REPAIR 2024-T3, 0.071, PO 614899.4 IAW DC/MD-10 SRM 54-51-02, VOL III. FABRICATED REPAIR IAW DC/MD-10 SRM 54-00- 01, VOL I. ALODINE AND PRIMED REPAIR DOUBLER IAW DC/MD-10 DRM 51-21-01, VOL II. INSTALLED REPAIR IAW DC/MD-10 SRM 51-31-01, VOL II. UT GAUGE USED T8225P.

Part: ATTACH ANGLE — CRACKED (ZONE 100) · airframe 83,901 hrs · 34,003 cycles

AFT CARGO STA 1967 GILL LINER ATTACH ANGLE AT THE CARGO FLOOR AND ACROSS CEILING ATTACH ANGLE HAS CORROSION ON THE BACKSIDE AROUND CAMLOCK RECEPTICLES. REMOVED CAMLOKS FROM THE CEILING RETAINER TO FOM, CORROSION REMOVAL REF DC/MD-10 SRM 51-35-01; VOL II. REMOVED CORROSION REF DC/MD-10 SRM 51-21-01, VOL II. ORIGINAL THICKNESS 0.040 RF DAC DWG AGA 3228. MATERIAL REMOVED 0.002 (UT GAUGE T8253B). MATERIAL REMAINING 0.038 AND FOUND TO BE WITHIN LIMITS REF DC/MD-10 SRM 53-00-01; VOL I. ALODINED, PRIMED AND REPLACED CAMLOKS REF DC/MD-10 SRM 51-21-01 AND 51-35-01; VOL II. LOWER GILL LINER ATTACH ANGLE FOUND TO BE CRACKED. REMOVED AND REPLACED ANGLE REF DAC DWG AGA 3228, REV AB AND SRM 51-21-01.

Part: PANEL — WORN (RT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

RIGHT WING OUTBOARD FLAP PANEL 636 AR HAS SEVERAL DENTS. REMOVED THE SKIN AND CORE IN THE DAMAGED AREA. MATERIAL ID'D; CLEANED AND PREPPED FOR CORE BOND; BONDED CORE; CLEANED AND PREPPED DOUBLER FOR BOND. FABRICATED AND BONDED DOUBLER, SEALED DOUBLER EDGE BOND LINES, RESTORED FINISH IAW SRM 51-71-00, VOL II, PARA 17.

Part: FAIRING — CHAFED (LT WING) · airframe 83,901 hrs · 34,003 cycles

LEFT WING INBD FAIRING PANEL 535 DL IS CHAFED. REPAIRED THE LT WING INBD FLAP FAIRING PANEL 535 P/N ARC 0740-501 BY FABRICATING & BONDING THE SKINS; CORE; DOUBLERS; PHENOLIC FILLERS & INSTALLED HARDWARE IAW EA 8-5750-116997; DWG ARC 0740 & TPS - 1001; REV E.

Part: SKIN — DAMAGED (ZONE 100) · airframe 83,901 hrs · 34,003 cycles

FUSELAGE EXTERNAL SKIN HAS A BULGING AREA AT FS 1781 AND LONGERON 49 L. THE BULGR HAS A CREASE AND IS OUT OF LIMITS PER SRM 53-20-00; FIG 13; SHEET 2; VOL I, PARA 1-B. CUT OUT THE DAMAGE AND FABRICATED A REPAIR DOUBLER; TRIPLER AND FINGER DOUBLERS PER SRM 53-20-00; FIG 6; SHEET 5; VOL I. INSTALLED THE REPAIR DOUBLER; TRIPLER AND FINGER DOUBLERS PER SRM 53-20-00; FIG 6; SHEET 5; VOL I.

Part: PANEL — WORN (ZONE 500) · airframe 83,901 hrs · 34,003 cycles

LEFT WING T/E PANEL 541 BB IS WORN. BLENDED PANEL 541 BB IAW DC/MD-10 SRM 57-00-01; FIG 1-A; VOL I. FOUND TO BE OUT OF LIMITS IAW DC/MD-10 SRM 57-00-01; FIG 1-A; VOL I AND SRM 57-32-01; VOL I. LOCATED AND DRILLED HOLES IAW DC/MD-10 SRM 51-31-01, VOL II.

Part: SUPPORT ANGLE — DAMAGED (ZONE 100) · airframe 83,901 hrs · 34,003 cycles

CENTER PIT CEILING SUPPORT AT STA 1761, FROM BL 80R TO BL 110R P/N AFA0161-115 IS SMASHED. REMOVED CEILING SUPPORT ANGLE AT FS 1761 FROM BL 80R TO BL 110R. MATERIAL ID FOR THE ANGLE IS 2024-T3, 0.040, PO 614877.2. FABRICATED, LOCATED AND DRILLED ANGLE IAW DAC DWG AFA0161, REV AV. ALODINED AND PRIMED ANGLE IAW DC/MD-10 SRM 51-21-01, VOL II. INSTALLED ANGLE IAW DC/MD-10 SRM 51-31-01, VOL I.

Part: PANEL — CORRODED (ZONE 600) · corrosion level 2 · airframe 83,901 hrs · 34,003 cycles

RIGHT WING T/E PANEL 641 BB HAS CORROSION AROUND FASTENER HOLES. REMOVED THE CORROSION IAW SRM 51-21-01; PG 28; VOL II. ORIGINAL MATERIAL 0.032 IAW SRM 57-32-01; FIG 2; VOL III. MATERIAL LOSS 0.010. REMAINING MATERIAL 0.022. FOUND TO BE OUT OF LIMITS IAW SRM 57-00-01; FIG 1-A; VOL I. LOCATED AND DRILLED THE NEW PANEL P/N ARC 0267-504, PO 627171.2 IAW SRM 51-31-01; VOL II.

Part: BRACKET — WORN (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

NR 1 ENGINE INBD FAN COWL INTERIOR SURFACE BRACKET IS WORN AT APPROX THE 3 O'CLOCK POSITION. REMOVED BRACKET IAW SRM 51-31-01, VOL II. FOUND TO BE OUT OF LIMITS IAW SRM 54-00-01, VOL I AND DAC DWG PLWSPO959, REV H. MATERIAL ID 2024-T3, 0.032 IAW DAC DWG PLWSP0959, REV H. FABRICATED A BRACKET IAW DWG PLWSP0959, REV H. ALODINED AND PRIMED IAW SRM 51-21-01, VOL II. PART MARKED BRACKET FX WSP0959-13 IAW GMM 7-0-1000. INSTALLED BRACKET IAW SRM 51-31-01, VOL II.

Part: ATTACH ANGLE — CHAFED (TAILCONE) · airframe 83,901 hrs · 34,003 cycles

TAILCONE ACCESS PANEL, CUT OUT, FWD EDGE LATCHING POSITIONS ARE MISSING MATERIAL IN 2 PLACES. FABRICATED A NEW ATTACH ANGLE IAW DC/MD-10 SRM 53-52-01, VOL III AND DAC DWG NRC 6022. ALODINED AND PRIMED ANGLE IAW DC/MD-10 SRM 51-21/01, VOL II. REMOVED AND INSTALLED ANGLE IAW DC/MD-10 SRM 51-35-01, VOL II.

Part: INTERCOSTAL — BENT (ZONE 100) · airframe 83,901 hrs · 34,003 cycles

FWD PIT STA 775, LONGERON 33R INTERCOSTAL IS BENT. REMOVED INTERCOSTAL REF DC/MD-10 SRM 51-35-01, VOL II. FAB MATERIAL ID S2929627 ALUM, FORMED SECTION 2027-T3, PO 469828.2 REF DC/MD-10 SRM 53-13-01, VOL III, PG 38. LOCATED FASTENER HOLES IN INTERCOSTAL REF DC/MD-10 SRM 51-31-01, VOL II. ALODINE, PRIME AND TOP COAT REF DC/MD-10 SRM 51-21-01, VOL II. PART MARKED INTERCOSTAL REF FEDEX GMM 7-0-1000, FRX 2929627T TOMCO - GSO JULY 17 2008.

Part: PANEL — CHAFED (ZONE 500) · airframe 83,901 hrs · 34,003 cycles

LEFT WING L/E PANEL 518 FB IS CHAFED. REPAIRED THE LT WING INBD L/E PANEL 518 FB BY REMOVING THE DAMAGED AREA AND BONDED A FILLER AND DOUBLER IAW SRM 51-71-00; VOL II. PRIMED AND PAINTED IAW SRM 51-21-02; VOL II.

Part: PANEL — DENTED (ZONE 500) · airframe 83,901 hrs · 34,003 cycles

LEFT WING FAIRING PANEL 535BL HAS NUMEROUS DENTS. REPAIRED DENTS IN THE LEFT WING FAIRING PANEL 535 BL WITH REPAIR DOUBLERS IAW SRM 51-71-00; VOL II.

Part: PANEL — DENTED (ZONE 500) · airframe 83,901 hrs · 34,003 cycles

LEFT WING FAIRING PANEL 536 BL HAS DENTS. REPAIRED THE DENTS ON THE LT WING OUTBD FAIRING PANEL 536 BL WITH REPAIR DOUBLERS IAW SRM 51-71-00; VOL II.

Part: PANEL — DENTED (LT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

LEFT WING OUTBD FLAP PANEL 535 AR HAS SEVERAL DENTS. REPAIRED DENTS IN THE LT WING OUTBD PANEL 535 AR WITH REPAIR DOUBLERS IAW SRM 51-71-00; VOL II.

Part: SKIN — DENTED (ZONE 100) · airframe 83,901 hrs · 34,003 cycles

FUSELAGE EXTERNAL SKIN HAS A DENT BETWEEN LONGERONS 45-L AND 46-L AND FS 1761 AND 1741. MEASURED THE MINOR AXIS OF THE DENT (D) D=3.5. MEASURED DEPTH (Y) Y = .085, D/Y = 41, DENT IS CREASED AND FOUND TO BE OUT OF LIMITS IAW DC/MD-10 SRM 53-20-00, FIG 13, SHEET 2, VOL I, PARA 1-B. CUTOUT DAMAGE AND FABRICATED A REPAIR DOUBLER, TRIPLER, FINGER DOUBLERS AND INSTALLED THE REPAIR IAW DC/MD-10 SRM 53-20-00, FIG 6, VOL I. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01, VOL II.

Part: PANEL — DELAMINATED (ZONE 500) · airframe 83,901 hrs · 34,003 cycles

LEFT WING T/E PANEL 541 IB IS GOUGED. REMOVED DAMAGE. FABRICATED REPAIR DOUBLERS AND FILLERS. PREPARED FOR BONDING. BONDED AND CURED REPAIR DOUBLERS AND FILLERS IAW DC/MD-10 SRM 51-71-00; VOL II. APPLIED SEALANT AND PRIMER IAW DC/MD-10 SRM 51-71-00; VOL II.

Part: SKIN — DAMAGED (RT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

RIGHT WING INBD FLAP T/E LOWER SURFACE SKIN HAS LIGHTNING STRIKE DAMAGE 4 FEET FROM THE OUTBD EDGE. REPLACED SKIN P/N ARC 2736-4. THIS WAS ACCOMPLISHED ON N/R N00285, FOR DETAILS SEE SDR TRACKING NUMBER 08-3079.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

LEFT WING INBD FLAP LOWER SURFACE HAS DENTS. CHECKED DENT AND FOUND TO BE OUT OF LIMITS IAW DC/MD-10 SRM 57-10-00, VOL I, FIG 48. REMOVED DAMAGE AND FABRICATED A REPAIR DOUBLER IAW DC/MD-10 SRM 57-10-00, VOL I, FIG 85. ALODINED AND PRIMED REPAIR DOUBLER IAW DC/MD-10 SRM 51-21-01, VOL II. INSTALLED THE REPAIR DOUBLER IAW DC/MD-10 SRM 57-10-00, VOL I, FIG 85.

Part: SKIN — CHAFED (LT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

LEFT WING INBD FLAP LOWER SKIN IS DENTED. CHECKED DENT AND FOUND TO BE OUT OF LIMITS IAW SRM 57-10-00; VOL I, FIG 48. REMOVED DAMAGE AND FABRICATED A REPAIR DOUBLER IAW SRM 57-10-00, VOL I, FIG 85. ALODINED AND PRIMED REPAIR DOUBLER IAW SRM 51-21-01, VOL II. INSTALLED THE REPAIR DOUBLER IAW SRM 57-10-00, VOL I, FIG 85.

Part: SHEAR TIE — CORRODED (ZONE 100) · corrosion level 2 · airframe 83,901 hrs · 34,003 cycles

FWD PIT, ATTACH ANGLE ON LONGERON 52 IS CORRODED, BL O AT STA 959. CUT OUT DAMAGED SECTION OF ATTACH ANGLE (SHEAR TIE). FABRICATED A NEW SHEAR TIE SECTION AND 2 SPLICES IAW DC/MD-10 SRM 53-30-00, VOL I, FIG 9 AND 10. ALODINED, PRIMED AND PAINTED SHEAR TIE SECTION AND SPLICES IAW DC/MD-10 SRM 51-21-01, VOL II, PGS 21 - 24 AND SRM 51-21-02, PG 8, VOL II. INSTALLED THE NEW SHEAR TIE SECTION AND SPLICES IAW DC/MD-10 SRM 51-33-01, VOL II, PG 34 AND SRM 51-35-01, VOL II, PG 1.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

RIGHT WING OUTBD FLAP LOWER SURFACE, OUTBD EDGE AREA SKIN HAS 6 EA DENTS. CHECKED DENTS AND FOUND THEM TO BE OUT OF LIMITS IN 2 PLACES FROM STA XOFH 773 - 778, IAW DC/MD-10 SRM 57-10-00, FIG 48, VOL I. CUT OUT DAMAGED AREAS. MATERIAL ID FOR THE DOUBLER IS 2024-T3, 0.050, PO 623403.1. FABRICATED DOUBLER IAW DC/MD-10 SRM 57-10-00, FIG 48, 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: SKIN — DENTED (RT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

RIGHT WING OUTBD FLAP LOWER SURFACE SKIN HAS A DENT 29 INCH OUTBD OF THE SPRING CARTRIDGE. CHECKED THE DENT AND FOUND IT TO BE OUT OF LIMITS IAW DC/MD-10 SRM 57-10-00, FIG 48, VOL I. CUT OUT THE DAMAGED AREA. MATERIAL ID FOR THE DOUBLER IS 2024-T3, 0.050, PO 623408.1. FABRICATED DOUBLER IAW DC/MD-10 SRM 57-10-00, FIG 85, VOL I. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01, VOL II, PGS 21-24, VOL II. INSTALLED IAW DC/MD-10 SRM 51-35-02, VOL II. THE NON-ROUTINE NUMBER DOCUMENTED ON THIS SDR IS INCORRECT. PLEASE CORRECT THE NON-ROUTINE NUMBER TO N00293.

Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

LEFT WING OUTBD FLAP, INBD LOWER SKIN HAS TWO CREASES BETWEEN RIBS 3 AND 4 FROM THE INBD SIDE. REMOVED DAMAGED AREA IAW SRM 57-10-00, VOL I, FIG 85. FABRICATED A REPAIR DOUBLER IAW SRM 57-10-00, VOL I, FIG 85. ALODINE AND PRIMED REPAIR DOUBLER IAW SRM 51-21-01, VOL II. INSTALLED REPAIR DOUBLER IAW SRM 57-10-00, VOL I, FIG 85.

Part: BEAM — CRACKED (L1 DOOR) · airframe 83,901 hrs · 34,003 cycles

L-1 DOOR INTERIOR, NR 3 BEAM IS CRACKED AT THE UPPER FLANGE AFT SIDE. REPAIRED THE L-1 DOOR NR 3 BEAM USING 0.032, 7075-T6, PO 577146.6; 0.050, 7075-T6, PO 565544.1 IAW DC/MD-10 SRM 52-00-01; VOL I.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

RIGHT WING OUTBD FLAP SURFACE SKIN HAS 6 DENTS IN THE INBD EDGE AREA. CHECKED DENTS AND FOUND TO BE OUT OF LIMITS AT STA XOFH 478 AND 503 IAW DC/MD-10 SRM 57-10-00, FIG 48, VOL I. CUT OUT DAMAGED AREAS. MATERIAL ID FOR DOUBLERS 2024-T3, 0.050, PO 623403.1, FILLERS 2024-T3, 0.046, PO 600955.2. FABRICATED IAW DC MD 10 SRM 57-10-00, FIG 85; VOL I AND SRM 57-52-01, FIG 8, VOL III. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01, VOL II, PGS 21-24. INSTALLED IAW DC/MD-10 SRM 51-35-02, VOL II.

Part: RIB — CRACKED (LT WING) · airframe 83,901 hrs · 34,003 cycles

LEFT WING L/E INTERIOR RIB IS CRACKED AT STA XFS 580. REMOVED CRACKED RIB IAW DC/MD-10 SRM 51-35-01, 51-33-01; VOL II. MATERIAL ID FOR THE RIB IS 7075-0, 0.063, PO 613435.3. FABRICATED IAW DAC DWG ARB 1162, REV "S". ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01; PGS 21 - 24; VOL II. INSTALLED IAW DAC DWG ARB 11621, REV "S" AND DC/MD-10 SRM 51-33-01; VOL II.

Part: RIB — CRACKED (LT WING LE) · airframe 83,901 hrs · 34,003 cycles

LEFT WING L/E INTERIOR RIB IS CRACKED AT THE STOP DRILL AT APPROX WING STA 683 (INBD OF THE NR 5 SLAT CENTER TRACK).

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

RIGHT WNG OUTBD FLAP LOWER SURFACE SKIN HAS A DENT, 1 FOOT OUTBD OF THE SPRING CARTRIDGE. CHECKED THE DENT AND FOUND IT TO BE OUT OF LIMITS IAW DC/MD-10 SRM 57-10-00, FIG 48, VOL I. CUT OUT THE DAMAGED AREA. MATERIAL ID FOR THE DOUBLER IS 2024-T3, 0.050, PO 623408.1. FABRICATED DOUBLER IAW DC/MD-10 SRM 57-10-00, FIG 85, VOL I. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01, VOL II, PGS 21-24, VOL II. INSTALLED IAW DC/MD-10 SRM 51-35-02, VOL II.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 83,901 hrs · 34,003 cycles

RIGHT WING INBD LOWER SURFACE SKIN HAS MULTIPLE DENTS JUST INBD OF THE OUTBD HINGE. CHECKED DENTS AND FOUND 2 OUT OF LIMITS IAW SRM 57-10-00, VOL I, FIG 48 AT STA XIFH 250 AND XIFH 254. REMOVED DAMAGED AREAS AND FABRICATED 2 REPAIR DOUBLERS IAW SRM 57-10-00, VOL I, FIG 85. ALODINED AND PRIMED 2 REPAIR DOUBLERS IAW SRM 51-21-01, VOL II. INSTALLED 2 REPAIR DOUBLERS IAW SRM 57-10-00, FIG 85.

Part: SKIN — DENTED (ZONE 600) · airframe 83,901 hrs · 34,003 cycles

RIGHT WING TIP, LOWER SURFACE HAS 2 DENTS, CENTER AREA. CHECKED WING TIP LOWER SURFACE, NOTED CREASES. FOUND TO BE OUT OF LIMITS IAW DC/MD-10 SRM 51-80-01, PARA 2-C, VOL II. CUT OUT DAMAGED AREA. MATERIAL ID FOR THE DOUBLER IS 2024-T3, 0.063, PO 614988.3. FABRICATED DOUBLER IAW DC/MD-10 SRM 57-00-01, FIG 4, VOL III. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-71-01, PGS 21 - 24, VOL II. INSTALLED DOUBLER IAW DC/MD-10 SRM 51-35-01, VOL II.

Part: SKIN — GOUGED (ZONE 100) · airframe 83,901 hrs · 34,003 cycles

DENT AND GOUGE ON THE FUSELAGE SKIN APPROX FS 840 AT LONGERON 38 L. BLENDED OUT GOUGE PER SRM 53-00-01; FIG 1-A; SHEET 3; VOL I. ORIGINAL THICKNESS 0.068 PER SRM 53-33-01; FIG 1; VOL III. REMAINING THICKNESS IS 0.045. MAT REMOVED 0.023. AREA IS OUT OF LIMITS PER SRM 53-00-01; FIG 1-A; SHEET 3; VOL I. REMOVED DAMAGED AREA IAW SRM 53-20-00; FIG 6; VOL I. INSTALLED REPAIR PARTS REF SRM 53-20-00; VOL I; PGS 84 A, B, C.

Part: FRAME — GOUGED (ZONE 100) · airframe 83,901 hrs · 34,003 cycles

IN CAC FUSELAGE FRAME LOWER ANGLE IS GOUGED/DENTED ON THE AFT SIDE AT STA 1119 FROM LONGERON 36R TO 40R. FUSELAGE FRAME IN THE CAC, LOWER ANGLE GOUGE/DENT AT STA 1119, LONGERON 36R TO LONGERON 40R. FOUND TO BE OUT OF LIMITS. REMOVED "J" CHANNEL AS PART OF THE "J" CHANNEL REPAIR ACCOMPLISHED ON N/R N00967.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 83,901 hrs · 34,003 cycles

IN THE CAC, THE FUSELAGE FRAME LOWER ANGLE IS CORRODED ON THE AFT SIDE AT STA 1119 FROM LONGERON 40R TO 41 R. FUSELAGE FRAME IN THE CAC, LOWER ANGLE CORROSION AT STA 1119, LONGERON 40R TO LONGERON 41R. FOUND TO BE OUT OF LIMITS. REMOVED "J" CHANNEL AS PART OF THE "J" CHANNEL REPAIR ACCOMPLISHED ON N/R N00967.

Part: LONGERON — CRACKED (ZONE 100) · airframe 83,901 hrs · 34,003 cycles

CENTER CARGO PIT, LONGERON 30 L END FITTING IS CRACKED IN THE UPPER LEG AT STA 1756. MACHINED LONGERON END FITTING P/N AFA 3044-1. MATERIAL ID 7075-T651, PO 626147.1 IAW DAC DWG AFA 3044. HEAT TREATED TO T-73. LOAD NR HT092208-1 AND PERFORMED DIMENSIONAL CHECK IAW EA 8-5310-116996 "FUSELAGE - LONGERON SPLICE FITTING HEAT TREAT REQUIREMENTS". PART MARKED IAW FEDEX GMM 7-0-1000. REMOVED OLD FITTING AND INSTALLED NEW FITTING IAW DC/MD-10 SRM 51-31-01; PG 1; VOL II.

Part: SKIN — DENTED (ZONE 100) · airframe 83,901 hrs · 34,003 cycles

FUSELAGE EXTERNAL SKIN HAS 2 DENTS BETWEEN LONGERONS 41R AND 42R AT FS 1821. INSPECTED THE AREA AND FOUND IT TO BE GOOD IAW EA 8-5330-123604; TITLED "FUSELAGE - SKIN AT STA 1825 AND L-40R - DENTS".

Part: SKIN — DENTED (ZONE 100) · corrosion level 2 · airframe 83,901 hrs · 34,003 cycles

CENTER WHEEL WELL/SPACE, INTERIOR AFT BULKHEAD, FWD FACE, MID LOWER SECTION SKIN HAS CORROSION IN MULTIPLE SPOTS AROUND FASTENER HEADS AND RUNNING UNDER A HORIZONTAL STIFFENER, LBL 15, FS 1521. REMOVED CORROSION IAW DC/MD-10 SRM 53-00-01, VOL I. FOUND TO BE WITHIN ALLOWABLE LIMITS. ORIGINAL MATERIAL IS 0.063. MATERIAL LOSS 0.003. MATERIAL REMAINING 0.060 IAW DC/MD-10 SRM 53-14-01, VOL III. USED UT GAUGE T8225P. ALODINED AND PRIMED AREAS IAW DC/MD-10 SRM 51-21-01, VOL II.

Part: SKIN — CRACKED (ZONE 200) · airframe 83,901 hrs · 34,003 cycles

LEFT WING FIXED L/E IS CRACKED AT THE INBD OF SLAT DRIVE MECHANISM ACCESS PANEL. CUT OUT CRACKED AREA AND FABRICATED A DOUBLER AND FILLER IAW SRM 57-10-00; FIG 68; VOL I. ALODINED AND PRIMED THE DOUBLER AND FILLER IAW SRM 51-21-01; VOL II; PGS 21-24. INSTALLED THE DOUBLER AND FILLER IAW SRM 51-33-01; VOL II.

Part: SUPPORT — CRACKED (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

LEFT WING OUTBD FLAP, INBD HINGE, FAIRING ATTACH BRACKET IS CRACKED AFT OF THE FLAP TRANSMITTER IN THREE LOCATIONS. REMOVED FAIRING TO FOM REF DC/MD-10 SRM 51-31-01; VOL II. REMOVED THE -1 TEE, -19 CLIP, -51 CLIP AND -1 CRACKED BRACKET REF DC/MD-10 SRM 51-31-01, VOL II. LOCATED AND DRILLED NEW STRUCTURE AND INSTALLED A NEW STRUCTURE REF DC/MD-10 SRM 51-31-01, VOL II. REINSTALLED FAIRING REF DC/MD-10 SRM 51-31-01, VOL II.

Part: SKIN — CRACKED (ZONE 500) · airframe 83,901 hrs · 34,003 cycles

LEFT WING OUTBD FLAP UPPER SKIN SURFACE IS CRACKED BETWEEN THE SECOND AND THIRD FLAP VANE TRACK. REMOVED DAMAGED AREA IAW DC/MD-10 SRM 57-10-00; VOL I, FIG 85. FABRICATED REPAIR DOUBLER AND FILLER IAW DCMD-10 SRM 57-10-00, VOL I, FIG 85. ALODINED AND PRIMED REPAIR DOUBLER AND FILLER IAW DC/MD-10 SRM 51-21-01, VOL II. INSTALLED DOUBLER AND FILLER IAW DC/MD-10 SRM 57-10-00, VOL I, FIG 85.

Part: BEAM — CRACKED (R3 DOOR) · airframe 83,901 hrs · 34,003 cycles

R3 DOOR NR 1 DOOR BEAM, AFT STOP LUG IS CRACKED. REMOVED & REPLACED THE R3 DOOR IAW EA 8-5210-116995.

Part: SKIN — UNKNOWN (LT ELEVATOR) · airframe 83,901 hrs · 34,003 cycles

LEFT OUTBD ELEVATOR LOWER SURFACE HAS A LIGHTNING STRIKE AT STA XE 474.

Part: ADAPTER — WORN (ZONE 400) · airframe 83,901 hrs · 34,003 cycles

NR 1 ENGINE LEFT CORE COWL LEADING EDGE IS WORN. ADAPTER REMOVED AND REPLACED PER DC/MD-10 SRM 51-31-01.

Part: SKIN — CRACKED (ZONE 500) · airframe 83,901 hrs · 34,003 cycles

LEFT WING FIXED L/E INTERNAL STA XFS 664 AT THE RIB, TOP STRAP IS CRACKED. REMOVED RIB TO FOM, REMOVED DOUBLER SPLICE. MATERIAL ID FOR A DOUBLER SPLICE 7075-0, 0.071, PO 620987.4 IAW DAC DWG ARB 1249; REV AA. FABRICATED A NEW DOUBLER SPLICE IAW DAC DWG 1249-11. HT IAW TPS 1003, REV A, LOAD NR HT071408.1. LOCATED AND DRILLED HOLES IAW DC/MD-10 SRM 51-33-01, VOL II. ALODINED AND PRIMED IAW DC/MD-10 SRM 51-21-01, PGS 21 AND 24, VOL II. INSTALLED NEW DOUBLER SPLICE AND RIB IAW DC/MD-10 SRM 51-33-01, VOL II. PART MARKED IAW FEDEX GMM 7-0-1001.

Part: FRAME — CRACKED (BS 1841) · airframe 81,558 hrs · 32,917 cycles

COMPLY WITH EA8-5310-102019, FUSELAGE FRAME CRACK AT STA1841 BETWEEN L9 AND L10 COMPLIED WITH EA8-5310-102019.

Part: SPAR — CRACKED (LT WING) · airframe 81,558 hrs · 32,917 cycles

C/W EA 8-5710-102021 WING LT WING REAR SPAR WEB CRACK AT XORS 217 COMPLIED WITH EA 8-5710-102021 IAW SRM 57-10-00 FIG 52.

Part: SPAR — CRACKED (ZONE 500) · airframe 81,558 hrs · 32,917 cycles

ON FRAME STA 1841 LEFT SIDE STRINGER 9L FOUND CRACK FROM ONE FASTNER HOLE THRU THE SECOND FASTENER HOLE (APROX 2"). REMOVED DOUBLER 2 CLIPS AND 2 INTERCOASTALS. RECEIVED FROM FAB ON T7/661087 AND T7/661086 2 DOUBLERS 7075T6 .080 T20631,193413. FAB 2 CLIPS FROM 60-19980 7075T6 8877871. LOCATED DRILLED REMOVED CRACK, TREATED AND PRIMED. INSTALLED 2 DOUBLERS, 2 CLIPS AND 2 INTERCOASTALS IAW EA8-5310-102019.

Part: BATTERY — MALFUNCTIONED (E/E BAY) · airframe 80,793 hrs · 32,561 cycles

BATTERY DISCHARGE ALERT INFLIGHT. PERFORMED BATTERY CHARGER TEST PER M/M 24-30-00-0 02, CHECKS NORMAL. PERFORMED BATTERY DISCHARGING ALERT OPS CHECK PER M/M 24-00-0106. CHECKS NORMAL. REPLACED BOTH SHIPS BATTERIES PER M/M 24-34-01-2, CHECKS NORMAL.

Part: MOUNT — CHAFED (ENGINE) · airframe 79,351 hrs · 31,928 cycles

COMPLY WITH EA8-7220-92342 ENGINE-FORWARD MOUNT CHAFE REPAIR, NR 3 ENGINE. COMPLIED WITH EA 8-7220-92342. MINOR REPAIR ENGINE FWD MOUNT CHAFE REPAIR.

Part: REPAIR — UNKNOWN (RT WING) · airframe 79,329 hrs · 31,912 cycles

"WINGS BASIC EXTISTING EXTERNAL DOUBLER ON RT WING UPPER SKIN. COMPLIED WITH EA8-5710-92352 WINGS BASIC EXISTING EXTERNAL DOUBLER ON RT WING UPPER SKIN.

Part: HEAT EXCHANGER — CRACKED (ZONE 100) · airframe 79,329 hrs · 31,912 cycles

AIR CONDITIONING, NR 1 AC PACK HEAT EXCHANGE FLANGE REPAIR. COMPLIED WITH EA 8-2150-92346. WELD REPAIR OF HEAT EXCHANGER FLANGE AREA.

Part: DOOR — MISSING (NR 2 NACELLE) · airframe 78,586 hrs · 31,591 cycles

PORTION OF NR 2 ENG FAN COWLING MISSING. CENTER ADVISED METAL WAS FOUND ON DEPARTURE PATH FROM OAK. PASSING 15,000 FEET THE A/C WAS JOLTED BUT NO OTHER INDICATIONS WERE NOTED. INSTALLED LEFT HAND FAN COWL FWD, CTR AND AFT HINGE BRACKETS. INSTALLED LEFT HAND FAN COWL. REFERENCE DWG AVB7050 AND EA 8-5410-89203. SECURED AND CLOSED FAN COWL AND PATIO. RETURNED TO SERVICE.

Part: SKIN — CORRODED (ZONE 100) · airframe 78,435 hrs · 31,523 cycles

FOUND INDICATIONS OF CORROSION SUCH AS DIMPLED FASTENER HEADS AND SKIN BULGING AT FS 1139 AND STRINGERS 45 LEFT TO 47 LEFT. REPAIRED WITH A SKIN DOUBLER.

Part: CONTROL UNIT — MALFUNCTIONED (SLATS) · airframe 77,904 hrs · 31,285 cycles

ON FINAL RECEIVED SLAT DISAGREE ALERT, WENT AROUND. BEGAN QRH PROCEDURE. RECOVERED LANDING SLAT, ELECTED TO LEAVE A/C CONFIGURED, UNEVENTFUL APPROACH AND LANDING. CYCLED C/B D-8 AUTO SLAT EXTEND AND E-8 AUTO SLAT EXTEND CONTROL PERFORMED R-T-S FCC-1 AND FCC-2 NO FAULT DISPLAYED OPERATED SLATS/FLAPS SEVERAL TIMES. ALERT CLEARED DID NOT RETURN. OPS CHECK NORMAL PER SMP. AIRCRAFT OK FOR SERVICE.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 77,608 hrs · 31,155 cycles

ON DEPARTURE OUT OF ONT AT APPROX 1000 AGL GOT A TAIL WINDSHEAR ALERT. WENT TO FIREWALL. NO OVERSPEED. DUMPED FUEL. DIVERT TO LAX. NO ENGINE EXCEEDANCE'S REPORT ON ACARS NOR AIU'S PERFORMED POSSIBLE TAIL STRIKE INSPECTION AND FLIGHT CONTROL INSPECTION. PULLED FLIGHT RECORDER AND VOICE RECORDER PER FLIGHT SAFETY. PERFORMED INSPECTION 05-51-12-6 PART 2 A-CHECK AND HARD LANDING SECTION A AND B WITH NO DEFECTS NOTED. FLIGHT CONTROL CHECK PER MM 27-00-0-2. ALL CHECK PASSED AS REQUIRED. REMOVED AND REPLACED FLIGHT DATA RECORDER PER FLT SAFETY. SYSTEM OPS CHECK GOOD. RETURNED TO SERVICE.

Part: BLEED VALVE — INOPERATIVE (ENGINE) · airframe 77,608 hrs · 31,155 cycles

ON TAKEOFF AT1000' AGL GOT LEVEL 3"AIR MANF 1 FAIL. COMPLIED WITH QRH, RETURNED TO AN UNEVENTFUL LANDING. PERFORMED DECAY CHECK FOR PNEUMATIC SYS 1 PER MM. CHECKED NORMAL. WHILE T/S FOUND AIU 3 INTERNAL FAULT FAILED TEST. REMOVED AND REPLACED AIU. NO FAULT LIGHTS ON MANIFOLD FAULT INDICATOR. R/R`D MANIFOLD RELAY R2-8962. R/R`D MANIFOLD FAILURE DETECTION PRESSURE SWITCH PER MM 36-23-03-4. R/R`D MANIFOLD FAILURE DETECT CONTROLLER. HIGH PRESSURE VALVE ON NR 1 ENG NEVER MOVES STAYS IN THE CLOSED POSITION THROUGHOUT ENGINE RUN. INSTALLED SERVICABLE HIGH PRESSURE BLEED VALVE. RAN NR 1 ENGINE I/A/W JRH. HP VALVE OPERATED NORMALLY. PERFORMED HIGH POWER RUN WITH WING ANTI-ICE SELECTED.

Part: STRIP — TORN (RT WING LE) · airframe 76,536 hrs · 30,650 cycles

RIGHT WING DLE CHAFE STRIP TORN WITH MISSING SECTION. REMOVED, FABRICATED CHAFE STRIP AND INSTALLED IAW DPS 4.710 & SRM 51-31-01 AT MAE.

Part: SPAR CAP — CORRODED (LT WING) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH FEDEX EA 8-5710-77344 WINGS BASIC LEFT WINGS, LOWER AFT SPAR CAP REPAIR. COMPLIED WITH EA 8-5710-77344 WINGS - BASIC LEFT WING, LOWER AFT SPAR CAP REPAIR.

Part: SPAR CAP — CORRODED (ZONE 600) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH FEDEX EA 8-5710-77344 WINGS BASIC LT WINGS, LOWER AFT SPAR CAP REPAIR. COMPLIED WITH EA 8-5710-77344 WINGS BASIC LT WING, LOWER AFT SPAR CAP REPAIR.

Part: HINGE — CORRODED (RT WING) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 8-5740-77340 WINGS RT OUTBD FLAP FLAP INBD HINGE. CORROSION REPAIR (P/N ARC0502-502), COMPLIED WITH EA 8-5740-77340 WINGS RT OUT'BD FLAP FLAP INBD HINGE CORROSION REPAIR P/N ARC 0502-502.

Part: HINGE — CORRODED (ZONE 600) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 8-5740-77340 WINGS RT OUTBOARD FLAP, FLAP INBOARD HINGE CORROSION REPAIR (P/N ARC0502-502). COMPLIED WITH EA 8-5740-77340 WINGS RT OUTBOARD FLAP, FLAP INBOARD HINGE CORROSION REPAIR P/N ARC 0502-502.

Part: SUPPORT — CORRODED (LT OB FLAP) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 8-5740-77338 WINGS - OUTBOARD FLAP, REWORK OF CARRIAGE SUPPORT ARM ARC2177. COMPLIED WITH EA 8-5740-77338 WINGS - OUTBOARD FLAP, REWORK OF CARRIAGE SUPPORT ARM ARC 2177 AT MAE.

Part: HINGE — CORRODED (RT IB FLAP) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 8-5750-75128 WINGS - RIGHT INBOARD FLAP - FLAP MOUNTED HINGE PIVOT BORE CORROSION REPAIR {P/N ARC2 512}. COMPLIED WITH EA 8-5750-75128, WINGS RIGHT INBOARD FLAP - FLAP MOUNTED HINGE PIVOT BORE CORROSION REPAIR (P/N ARC2512) AT MAE.

Part: HINGE — CORRODED (LT OB FLAP) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 8-5750-77339 WINGS - LEFT O/B, I/B FWD HINGE ASSY (P/N ARC 0502) FWD CLEVIS REWORK. COMPLIED WITH EA 8-5750-77339 WINGS - LEFT O/B FLAP, I/B FWD HINGE ASSY (P/N ARC0502) FWD CLEVIS REWORK.

Part: BRACKET — CORRODED (LT OB FLAP) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 5740-77336A WINGS - LT OUTBOARD FLAP - FWD CLEVIS BRACKET ASSY CORROSION REPAIR (P/N ARC0538-501). COMPLIED WITH EA 8-5740-77336A WINGS - LT OUTBOARD FLAP - FWD CLEVIS BRACKET ASSY CORROSION REPAIR (P/N ARC053 8-501) AT MAE.

Part: BRACKET — CORRODED (LT OB FLAP) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 8-5740-77341 WINGS - LEFT OUTBOARD FLAP - FLAP INBOARD HINGE CORROSION REPAIR (P/N ARC0502-501). COMPLIED WITH EA 8-5740-77341 WINGS - LEFT OUTBOARD FLAP - FLAP INBOARD HINGE CORROSION REPAIR (P/N ARC0502-501) AT MAE.

Part: CLEVIS — CORRODED (ZONE 600) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 8-5750-75133 WINGS - RT OUTBOARD FLAP, OUTBOARD HINGE, REWORK OF FWD CLEVIS ARC0538. COMPLIED WITH EA 8-5750-75123 WINGS RIGHT OUTBOARD FLAP OUTBOARD HINGE REWORK OF FWD CLEVIS.

Part: HINGE — CORRODED (ZONE 600) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 8-5740-75134 WINGS RIGHT INBOARD FLAP, HINGE ASSY ATTACH LUG REWORK. COMPLIED WITH EA 8-5740-75134.

Part: BRACE — CORRODED (ZONE 600) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 8-5740-75132 WINGS - RIGHT OUTBD FLAP - SIDE BRACE SUPPORT FITTING CORROSION REPAIR P/N ARB0 029-2. COMPLIED WITH EA 8-5740-75132 WINGS - RIGHT OUTBOARD FLAPS IDE BRACE SUPPORT CORROSION REPAIR P/N ARB0029-2.

Part: HINGE — CORRODED (ZONE 500) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 8-5750-75130 WINGS - LEFT OUTBOAD FLAP - FLAP MOUNTED HINGE POSITION INDICATOR HOLE REPAIR (P/N ARC1984). COMPLIED WITH EA 8-5750-75130 - WINGS - LEFT OUTBOARD FLAP - FLAP MOUNTED HINGE POSITION INDICATOR HOLE REPAIR P/N ARC 1984.

Part: BRACKET — CORRODED (LT O/B AILERON) · airframe 76,536 hrs · 30,650 cycles

COMPLY WITH EA 8-5740-75129 WINGS - OUTBOARD AILERON, BACKUP ACTUATOR BRACKET HOLE REWORK. COMPLIED WITH ENT BY: 484466 RPT BY: 484466.

Part: BOLT — OUT OF ADJUST (LT MLG) · airframe 74,783 hrs · 29,763 cycles

ON GEAR RETRACTION LEFT MAIN GEAR LIGHT REMAINED RED. SECONDARY LEFT MAIN GEAR LIGHT REMAINED RED ALSO. RAN CHECKLIST FOR MAIN GEAR NOT UP AND LOCKED, LOWERED GEAR IAW CHECKLIST AND RETURNED FOR LANDING. FOUND DOOR LATCH ROLLER LINK PIVOT WITH EXCESSIVE TIGHTNESS, SPRINGS WOULD NOT RETURN LINK TO STOP. LOOSENED PIVOT BOLT AND RESAFTIED, MM. DOOR LATCH ROLLER LINK NOW RETURNS PROPERLY. OK FOR SERVICE.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT) · airframe 74,165 hrs · 29,446 cycles

ALL IND NORMAL EXCEPT OIL STRAINER CLOG LIGHT CAME ON. SHUTDOWN ENG LIGHT STAYED ON.

Part: BRACKET — INOPERATIVE (LT MLG)

LT MLG REMAIN RED AFT GEAR RETRACTION. INSTALLED TARGET SUPPORT. REPLACED DOOR TARGETS AND BRACKET PER DC-10 MM 32-61-03-2. PERF ADJ & TEST PER SAME REF. OPS CK NORMAL.

Part: SENSOR — INOPERATIVE (AOA SYSTEM)

DURING SLAT RETRACTION ON T/O, SLAT DISAGREE LIGHT ILLUM AND STICK SHAKER ACTUATED. REMOVED AND REPLACED RT AOA SENSOR PER DCN -10 MM 22-33-01. PERFORMED STALL WARN TEST PER DC1010 MM 22-33-00, TEST OK. REMOVED AND REPLACED FLAP HANDLE POS TRANSMIT TER PER DC 1010.