N398FE

Part: BULKHEAD — CRACKED (LT MLG WW) · airframe 80,148 hrs · 27,932 cycles

SUSPECT CRACK IN LT MAIN GEAR WHEEL WELL BULKHEAD. REPAIRED LT WHEEL WELL WEB CRACK IN REF TO SRM 53-00-01, FIG 10, VOL I

Part: SPLICE — CRACKED (ZONE 200) · airframe 79,151 hrs · 27,380 cycles

MAIN DECK CROWN AT BS 1741, WEB SPLICE ANGLE CRACKED BETWEEN L13-14L. R & R SPLICE.

Part: FUSE — LEAKING (HYD SYSTEM) · airframe 78,946 hrs · 27,283 cycles

NR 3 HYD FAILED ON GEAR EXTENSION. R & R THE NR 3 HYD SYS TRIM CYCLINDER INTERLOCK FUSE, REF AMM 32-31-06-2.

Part: SENSOR — FAILED (NR 3 ENGINE) · airframe 78,816 hrs · 27,210 cycles

ON CLIMB OUT, NR 3 ENGINE EXCEEDENCE. RAN QRH, OIL PRESSURE MAINTAINED THROUGH OUT WINDMILL. ALL OTHER PERIMETERS WERE NORMAL. REMOVED AND REPLACED N1 FAN SPEED SENSOR IAW AMM 77-11-01.

Part: FAN — CONTAMINATED (E/E BAY) · airframe 78,191 hrs · 26,852 cycles

DURING LEFT WING DUMP VALVE OPS CHECK, SMOKE WAS NOTICED IN FWD LWR E&E BAY. INSPECTED COOLING FAN, FOUND DEBRIS. REMOVED DEBRIS PERFORMED OPS CHECK, ADJUSTMENT AND TEST. CHECKED GOOD, NO SMOKE, ACFT OK TO CONTINUE REF AMM 21-26-02-5-0.

Part: POWER SUPPLY — FAILED (EMERGENCY LIGHT) · airframe 77,966 hrs · 26,728 cycles

ON POST FLIGHT CHECK FOUND EMERGENCY LIGHTS INOPERATIVE. R & R EMERGENCY LIGHTING POWER SUPPLY IAW 33-51-01-4-0, CHECKED GOOD FOR SECURITY AND OPERATION.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT) · airframe 77,967 hrs · 26,729 cycles

ON POST FLIGHT CHECK FOUND EMERGENCY LIGHTS INOP. R & R EMERGENCY LIGHTING POWER SUPPLY IAW 33-51-01-4-0, CHECKS GOOD FOR SECURITY AND OPERATION. FINAL CLOSED.

Part: SKIN — CORRODED (BS 1853 S46-48R) · corrosion level 2 · airframe 76,862 hrs · 26,140 cycles

AFT CARGO COMPARTMENT-FLAKING CORROSION BOTH SIDES BELL FRAME BETWEEN 46R AND 48R,STA 1853.(MRK'D) CORROSION REMOVED, REPAIR INSTALLED IAW EA 8-5330-147781 REF FIG 1 AND SRM 53-20-00 FIG 13 SHT 11. EA 8-5330-147781 PART 2 WILL BE ACCOMPLISHED C7 CHECK MAY2013 PART 2 REPLACES REPAIR.

Part: SKIN — CORRODED (BS 1841 L45R) · corrosion level 2 · airframe 76,862 hrs · 26,140 cycles

FOUND SKIN BULGING AT FWD OF STA. 1841 L45R, 9 FASTENERS MARKED. CLEANED CORROSION, INSTALLED INTERIM REPAIR INSTALLED IAW EA 8-5330-147780 (SEQ 733). REPAIR WILL BE WILL INTEGRATED ADJACENT REPAIR ON C-7 CHECK.

Part: SKIN — DEFORMED (BS 1902) · airframe 76,862 hrs · 26,140 cycles

LOWER AFT FUSELAGE-SKIN DEFORMING AROUND RIVET HEADS AT STA 1902 BETWEEN STRINGERS 43R AND 46R.

Part: SKIN — CORRODED (BS 1895) · airframe 76,862 hrs · 26,140 cycles

AFT LOWER FUSELAGE SKIN AT APPROX STA 1895 BETWEEN LONGERONS R45 & R43 IS BULGING. SUSPECT CORROSION. DOT NR 2 AND MARKED IN RED.

Part: SKIN — MISREPAIRED (BS 1811 L47L) · corrosion level 2 · airframe 76,862 hrs · 26,140 cycles

FUSELAGE EXTERNAL SKIN STA 1811, 47L HAS BLIND FASTENERS THRU THE FUSELAGE. REMOVED BLIND FASTENERS PER SRM 51-00-01 AND FOUND CORROSION. CUT OUT CORRODED AREAS AND INSTALLED DOUBLER, TRIPLER, AND FINGER DOUBLERS IAW SRM 53-20-00 FIG. 6 SHEET 5 CLASS I REPAIR, CAT "A"

Part: CONTROL VALVE — INOPERATIVE (TE FLAPS) · airframe 75,554 hrs · 25,457 cycles

ON CLIMB OUT STARTED NORMAL FLAP RETRACTION-GOT A FLAP DISAG. FLAPS INDICATED 14- 17 IN AMBER BOXES ON CONFIG PAGE.PUT FLAP/SLAT HANDLE TO 15 DETENT,FLAPS THEN MOVED TO 10,THEN 4, FLAP HANDLE STILL AT 15. MOVED HANDLE TO 0 DEGS,FLAPS EVENTUALLY MOVED TO 0 DEGS.LANDED SLATS EXTENDED,FLAPS UP. WT APPROX 368,000 LBS ON TOUCHDOWN. LANDED WITHOUT INCIDENT. FACT, INSTALLED INBD FLAP CONTROL VALVE REF AMM 27-52-02-2. REPLACED BOTH RESTRICTORS AND ONE CHECK VALVE. CLEANED THE OTHER CHECK VALVE AS PRECAUTION. OPS CHECK AND LEAK CHECK GOOD.

Part: CABLE — FAILED (THROTTLE) · airframe 75,414 hrs · 25,378 cycles

NR 2 THROTTLE STUCK AT 93 PERCENT AT FL 340 LOWER ALTITUDE AND STARTING APU AIRBORNE DID NOT UNFREEZE THROTTLE. SHUT NR 2 DOWN IAW QRH WINDMILLED FOR 17 MINUTES. RAN NR 2 ENG FOR A MINIMUM OF 3 MINUTES TO OIL/LUBE BRGS, BECAUSE OF WIND MILLING DUE TO INFLT SHUTDOWN. IAW MM 72-00-00-4. REMOVED PUSH-PULL CABLE AND REINSTALLED NEW CABLE UP TO STEP B.9 OF MM 76-11-01-2. TURNOVER TO NEXT SHIFT. COMPLETED INSTALLATION IAW MM 76-11-01-2. PREMATURE REMOVAL/INSTALLATION.

Part: ANGLE — CORRODED (ZONE 100) · corrosion level 3 · airframe 74,474 hrs · 24,950 cycles

T WHEEL WELL FWD BULKHEAD BOTTOM EDGE OF SLANT PANEL THIRD FROM OTBD SHIM AREA HAS CORROSION. REMOVED AND INSTALLED REPAIR ANGLE USING REF SRM 53-40-00.

Part: CHANNEL — CRACKED (ZONE 100) · airframe 71,392 hrs · 23,469 cycles

STA 1787 LOWER "J" CHANNEL AT FRAME TO LONGERON CRACKED. FABBED NEW "J" SECTION FROM LONGERON 43R-49R IAW DAC DWG AFA 3907 REV C. ALODINED AND PRIMERED IAW MD/DC 10 SRM 51-21-01 VOL.II. INSTALLATION ON SNRM N00581 (SEE SDR NR 07-2225)

Part: FRAME — CRACKED (ZONE 100) · airframe 71,392 hrs · 23,469 cycles

LOWER CENTER CARGO COMPARTMENT, FLOORBEAM AT FRAME 1741 CRACKED AT LBL 1"-5" AND RBL 2.5"-4" ON UPPER FLANGE. REPAIRED BY CUTTING OUT DAMAGE AND FABRICATING AND INSTALLING FILLER AND REPAIR ANGLES IAW MD/DC 10 SRM 53-00-01 FIG 9 VOL I. ALODINED AND PRIMERED AREA AND PARTS IAW MD/DC 10 SRM 51-21-01 VOL II. THIS IS A MAJOR REPAIR.

Part: SKIN — DENTED (ZONE 100) · airframe 71,392 hrs · 23,469 cycles

RIGHT FUSELAGE SKIN HAS A DENT WITHIN 12 INCHES OF PRIMARY STATIC PORT. REPAIRED DENT BY CUTOUT AND EXTERNAL DOUBLER IAW MD/DC10 SRM 53-20-00 FIG 9 VOL I. REPAIR DOUBLER IS ACCEPTABLE FOR RVSM OPERATION IAW MD/DC 10 SRM 53-00-02 FIG1 SHEET 2 VOL I. THIS IS A CATAGORY B REPAIR INITIAL INSPECTION IS 34,000 AND REPETITIVE AT 24,000.

Part: LONGERON — CORRODED (BS 1781) · corrosion level 2 · airframe 71,392 hrs · 23,469 cycles

CENTER LOWER CARGO COMPTMENT, LONGERON 46R IS CORRODED OUT OF LIMITS AT FS 1781 AFTER CLEAN UP. [07-27-07] REPAIRED LONGERON 46R IAW FEDEX EA 8-5310-112950. REMOVED AND REINSTALLED SUBSTRUCTURE AS REQUIRED FOR ACCESS IAW DC/MC 10 SRM 51-31-01, 51-33-01 AND 51-35-01 VOL II. THIS IS A MAJOR REPAIR.

Part: SHUTOFF VALVE — MALFUNCTIONED (ANTI ICE SYSTEM) · airframe 70,274 hrs · 22,997 cycles

DECENT,ENG & WING A/I ON,RT WING A/IVLV DISAG, NR 1 MAN ALERT.PERF QRH , NR 1 THROTTLE IDLE,SECURED ENG AND WING A/I,DEP ICING,CLIMBED TO 280. 20 MIN LATER #1 MANI ALERT EXTINGUISHED RETURNED THROTTLE TO NORMAL POWER. CKD MAN FAIL DET UNIT, LEFT WING PRESS SW FAULT. ACP PNEU DECAY CHECK PER MM 36- 00-02 ALL THREE SYSTEM PASSED. DROPPED L/E SLATS, PUT AIR ON THE WINGS OPENED WING A/I FOUND NO PRESS DROP 28PSI. ALSO ACP INSPECTION ON WING L/E FOR ANY DUCT LEAKS AND CHECKED TELESCOPING TUBE ON BOTH WINGS. NO LEAKS. R/R RIGHT WING ANTI-ICE SHUTOFF VALVE PER M/M 30-11-02-2, OPS & LEAK CHECKS NORM. R/R NR 1 MAN FAILURE DETECTION PRESS SW M/M 36-23-03-4, OPS CHECKS NORM.

Part: COMPUTER — MALFUNCTIONED (FCC) · airframe 69,726 hrs · 22,743 cycles

DURING FIRST ATTEMPT, AT APPROX. 95 KNOTS, GOT AURAL WARNING "STABILIZER." AFTER RTO, STAB WAS SHOWING 5.9 (VERSUS THE PREVIOUSLY SET 5.7) ON SECOND TRY, BY 30 KNOTS STAB HAD ALREADY ADJUSTED ITSELF TO 5.5. ON EACH OCCASION OF STAB MOVEMENT, THE UNCOMMANDED CHANGE WAS IN THE SAME DIRECTION THAT WAS USED TO SET THE STAB PREVIOUSLY. REMOVED AND REPLACED NR 1 FCC PER MM 22-01-03-4. NR 1 FCC RTS PER MM 22-00-00-5. INSPECTED STAB TRIM VALVE OPERATION WITH NOT FAULTS FOUND. NR 2 FCC RTS PER MM 22-00-00-5. NO CURRENT/FAULT HISTORY LOGGED IN NR 1 OR NR 2 FCC PRIOR TO REPLACEMENT OF COMPONENTS.

Part: FLAP SYSTEM — MALFUNCTIONED (TE FLAPS) · airframe 69,686 hrs · 22,725 cycles

AT FLAP RETRACTION, BOXED AMBER FLAP DISAGREE LIGHT AND FLAPS SHOWED 3 AND 4 DEGREES ON BOTH SIDES IAW QRH, EXTENDED AND RETRACTED AGAIN. FLAPS AGAIN SHOWED 3 AND 4 DEGREES ON BOTH SIDES, FLAPS WOULD NOT EXTEND BEYOND 3 TO 4 DEGREES. CKD FLAP CABLES, F/U CABLES, AND FLAP DRUMS FROM COCKPIT TO W/W WITH NO DEFECTS. CHECKED FLAP VANES AND TRACKS FOUND NO BINDING. PERFORMED TEST OF FLAP LIMITER, TEST PASSED. CHECKED FLAP POSITION X-MITTER THRU FCC 1 AND FCC 2 ALL WITHIN LIMITS. RAN FLAPS THRU AT LEAST 10 TIMES WITH NO FAULTS OR BINDING NOTED IAW MM 27-50-00-5. RAN FLAPS THRU APPROX 10 TIMES AND CHECKED LT AND RT FLAP ACTUATORS FOR BYPASSING AND OVERHEATING NONE NOTED AT THIS TIME IAW MM 27-50-00.

Part: PROXIMITY SWITCH — MALFUNCTIONED (SLATS) · airframe 69,293 hrs · 22,551 cycles

AT 1200' AGL ILS26L ONT, GEAR DN, FLAPS 35, LEVEL 2 AMBER SLAT DISAGREE LIGHT GO AROUND, NORMAL INDICATION NS ON SECOND APPROACH. IN WORK, PSEU SHOWS NO CURRENT FAULTS. ALSO SHOWS NO PREVIOUS LEG FAULTS. ALSO SHOWS NO SENSORS WITH MARGINAL RIGGING. PSEU RTS GOOD. ACARS LAST SEG SHOWS SLAT DISAGREE ON APPROACH. RT WING SENSOR 4B WAS '0' WITH ALL OTHERS '1'. ALSO FLAP HANDLE POSITION WAS 'TAKEOFF', SHOULD BE 'LAND'. REMOVED AND REPLACED ELECT PROX SWITCHING UNIT PER M/M 31-71-01-2. OPS CHECKED GOOD. REMOVED AND REPLACED SLAT PROXIMITY SENSOR R4B PER MM 27-84-03-4.

Part: NOSE COWL — BIRD STRIKE (LEFT) · airframe 68,284 hrs · 22,126 cycles

AT ROTATION NOTICED BIRD FLOCK LEFT OF NOSE LEVEL AT 2000 FT NOTICED VIBRATION, CONTINUED TO CLIMB VIBRATION WAS NOTICED IN NR 1 START LEVER AND THROTTLE. AT 17000 NR 1 RED REV U/L APPEARS. RAN RED TABS, SHUT DOWN NR 1 ENGINE, RETURNED TO AFW. INSPECTED NR 1 ENGINE AND FOUND SEVERAL CUTS AND GOUGES BETWEEN 1/4" TO 3.5" LONG. NOSE COWL ON ORDER.

Part: WIRE HARNESS — FAILED (NR 1 ENGINE) · airframe 68,264 hrs · 22,115 cycles

ENGINE NR 1 EGT EXCEEDING 937 DEGREES ON TAKEOFF ALSO NOTED N1 FLUCTUATION SAME TIME. SHUT DOWN ENGINE AND DUMPED FUEL 22,000 LBS, RETURNED TO SEA. REMOVED AND REPLACED NR 1 ENG EGT THERMOCOUPLE HARNESS PER MD-10-10 AMM 77-21-01-2. OPS CHECKED NORMAL.

Part: DUCT — LEAKING (NR 2 ENGINE) · airframe 66,244 hrs · 21,243 cycles

DURING CLIMB-OUT LEVEL1 ENG 2 ANTI-ICE DISAGREE OCCURRED 3-4 TIMES. EN ROUTE AT FL310 AIR MANF 2 FAIL LEVEL 3 DUMPED 10K, LANDED AT KDEN AS PER RED TABS. AIR SYS CONTROLLER SHUTOFF BLEED AND PACK AT ALTITUDE NR 2 MANIF FAILED PRESSURE DECAY TEST PER MM 36-00-01-5. FOUND NR 2 ENG AIR DUCT AAM7414-1 IN FWD LEFT SIDE OF CTR CARGO COMPT LEAKING. REMOVED AND REPLACED HYD CLAMPS AND AIR LINE CLAMPS ON TWO VERTICAL BRACES NEXT TO AFT END OF DAMAGED DUCT. ALSO, REMOVED TOP AND BOTTOM FASTENERS ON TWO BRACES TO ALLOW R/R`D OF MANIFOLD DUCT. INSTALLED NEW DUCT PERFORMED PNEUMATIC SYS NR 2 DECAY, TEST IAW MD-10-10 M/M SUPP 36-00-02-5 AND WING ANTI-ICE SYS TEST IAW MD-10-10 M/M 30-11-00-5. BOTH TESTS PASSED.

Part: SHROUD — GOUGED (NR 2 ENGINE) · airframe 66,011 hrs · 21,130 cycles

AT C-CHECK AT BFM N/R N00504 WAS WRITTEN FOR THE NR 2 ENGINE LT SHROUD FAN COWL LAND BEING GOUGED. REMOVE AND REPLACE THE SHROUD IAW SRM 51-31-01. THE SHROUD PANEL WAS FABBED ON MAE TRAVELER T/4-442977.

Part: VANE — CORRODED (ZONE 600) · airframe 66,011 hrs · 21,130 cycles

COMPLY WITH EA 8-5750-79552 WINGS FLAP VANE SUPPORT CORROSION REWORK (RT OUTBOARD FLAP). COMPLIED WITH EA 8-5750-79552 WINGS FLAP VANE SUPPORT CORROSION REWORK, RIGHT O/B FLAP.

Part: FITTING — WORN (RT WING IB FLAP) · airframe 66,011 hrs · 21,130 cycles

RIGHT WING I/B FLAP I/B TRACK FAIRING AFT MOUNT WORN. REMOVED AND REPLACED MOUNT IAW SRM 51-33-01 AT MAE.

Part: BRACKET — CRACKED (TAIL CONE) · airframe 66,011 hrs · 21,130 cycles

TAIL CONE RIGHT FWD FRAME MIDDLE GUIDE PIN BRACKET IS CRACKED. REMOVED AND REPLACED GUIDE PIN BRACKET IAW SRM 51-31-01 & SRM 51-35-01 AT MAE.

Part: VANE — CORRODED (LT O/B FLAP) · corrosion level 2 · airframe 66,011 hrs · 21,130 cycles

COMPLY WITH EA 8-5750-79551 WINGS FLAP VANE SUPPORT CORROSION REWORK (LT OUTBD FLAP). COMPLIED WITH EA 8-5750-79551 WINGS FLAP VANE SUPPORT CORROSION REWORK (LT OUTBD FLAP) AT MAE.

Part: BRACKET — BROKEN (NLG) · airframe 66,011 hrs · 21,130 cycles

HYD CLAMP SUPPORT BRACKET IS BROKEN AT LOWER MOUNT OF THE MAINT PLATFORM ON THE NOSE GEAR STRUT. REMOVED AND REPLACED BRACKET IAW MM 20-50-02-2 AT MAE.

Part: TRUSS FITTING — CORRODED (ZONE 600) · airframe 66,011 hrs · 21,130 cycles

COMPLY WITH EA 8-5420-7-79546B NACELLE/PYLON NR 1 ENGINE FWD TRUSS FITTING CORROSION REPAIR P/N AUB7000-501. COMPLIED WITH EA 8-5420-7-79546B.

Part: HINGE — CORRODED (ZONE 600) · airframe 66,011 hrs · 21,130 cycles

COMPLY WITH EA 8-5750-79542, WINGS RIGHT INBOARD FLAP - FLAP MOUNTED HINGE PIVOT BORE CORROSION REPAIR P/N ARC2512. COMPLIED WITH EA 8-5750-79542.

Part: SEAT TRACK — CORRODED (ZONE 100) · airframe 66,011 hrs · 21,130 cycles

AFT LWR CARGO COMPT, RT CARGO TRACK HAS SEVERAL NICKS AND DINGS ON UPPER SURFACE AND CORROSION INSIDE TRACK LOBES. REMOVED CORROSION IAW SRM 51-21-01 VOL 1 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-70-00 FIG 5 VOL 1. REMOVED AND REPLACED SEAT TRACK SEGMENT IAW SRM 53-70-00 FIG 1 VOL 1.

Part: FITTING — CORRODED (ZONE 400) · airframe 66,011 hrs · 21,130 cycles

COMPLY WITH EA8 -5420-79546 NR 1 PYLON FWD TRUSS FITTING CORROSION. COMPLIED WITH EA 8-5410-79546.

Part: RIB — GOUGED (ZONE 600) · airframe 66,011 hrs · 21,130 cycles

COMPLY WITH EA 8-5750-79543 WINGS RT FIXED LEADING EDGE SLAT RIB TRACK RIB GOUGE REPAIR XOS 427.4. COMPLIED WITH EA 8-5740-79543.

Part: SUPPORT ANGLE — CRACKED (RT WING SLAT) · airframe 66,011 hrs · 21,130 cycles

RIGHT WING SLAT TRACK NR 16 LOWER FAIRING PANEL INBOARD SUPPORT ANGLE IS CRACKED. REMOVED AND REPLACED CLIP IAW SRM 51-31-01 AT MAE.

Part: FITTING — DAMAGED (APU DOOR) · airframe 66,011 hrs · 21,130 cycles

APU COMPT ACCESS DOOR SNUBBER ROD ATTACH POINT ANGLE HOLE IS ELONGATED. REMOVED AND REPLACED FITTING IAW SRM 51-31-01 AT MAE.

Part: GUIDE — BROKEN (THRUST REVERSER) · airframe 66,011 hrs · 21,130 cycles

NR 3 ENGINE LEFT T/R UPPER GUIDE IS BROKEN. REMOVED AND REPLACED NR 3 ENGINE LEFT T/R UPPER GUIDE IAW SRM 51-33-01 AT MAE.

Part: CHANNEL — CRACKED (LT MLG DOOR) · airframe 66,011 hrs · 21,130 cycles

LEFT MLG DOOR AFT Z-CHANNEL APPEARS CRACKED. REMOVED AND REPLACED PAN IAW SRM 51-31-01 AT MAE.

Part: CONTROL CABLE — BROKEN (L/E SLAT) · airframe 61,952 hrs · 19,120 cycles

NR 7 RIGHT SLAT RETRACT CABLE HAS BROKEN STRANDS. REMOVED AND REPLACED CABLE AND CONTROL PULLEY PER MM 27-89-13, 27-80-00.