N124DE

Part: SKIN — DAMAGED (NOT REPORTED) · airframe 75,967 hrs · 33,892 cycles

FUSELAGE SKIN DAMAGED. REPAIRED IAW ERA 528965-14.

Part: SKIN — DAMAGED (UNKNOWN) · airframe 75,967 hrs · 33,892 cycles

FUSELAGE SKIN GROUND DAMAGED. REPAIRED IAW ERA 528964-14.

Part: SKIN — DAMAGED (NOT REPORTED) · airframe 75,967 hrs · 33,892 cycles

FUSELAGE SKIN DAMAGED. REPAIRED IAW ERA 528966-14.

Part: STRINGER — CRACKED (BS 1530-1540) · airframe 75,967 hrs · 33,892 cycles

RT SIDE FUSELAGE STRINGER 30R CRACKED BS 1530-1540. REMOVED STRINGER IAW SRM 53-00-01,. PERFORMED HFEC FOR DAMAGE CONTAINMENT, NO FINDINGS.

Part: FLOORBEAM — CRACKED (BS 347) · airframe 71,849 hrs · 32,723 cycles

CABIN BS 347 FLOORBEAM UPPER TEE FOUND CRACKED AT RBL 2.0 AND RBL 8.0 & LBL 9.0. REPAIRED IAW 514023-14 (LP 0917476).

Part: FAILSAFE — CRACKED (BS 955) · airframe 71,849 hrs · 32,723 cycles

CRACK ON RT BULKHEAD FAIL SAFE STRAP AT BS 955. REPAIRED IAW PRI 514007-14AD, REV 0.

Part: STRINGER — CORRODED (BS 412-434) · corrosion level 2 · airframe 71,823 hrs · 32,717 cycles

FWD CARGO BS 412-434, STRINGER 34R CORRODED. REPAIR CARRIED OUT IAW SRM 53-00-03, FIG 201, REPAIR 2, REV 92.00.

Part: STRINGER — CORRODED (BS 412-434) · corrosion level 2 · airframe 71,823 hrs · 32,717 cycles

FWD CARGO BS 412-434, STRINGER 36R CORRODED. REPAIR CARRIED OUT IAW SRM 53-00-03, FIG 201, REPAIR 2, REV 92.00.

Part: STRINGER — CORRODED (BS 412-434) · corrosion level 2 · airframe 71,823 hrs · 32,717 cycles

FWD CARGO BS 412-434 STRINGER 27R CORRODED. REPAIR CARRIED OUT IAW SRM 53-00-03 FIG 201, REPAIR 2, REV 92.00.

Part: STRINGER — CORRODED (BS 412-434) · corrosion level 2 · airframe 71,823 hrs · 32,717 cycles

FWD CARGO BS 412-434 STRINGER 39R CORRODED. REPAIR CARRIED OUT IAW SRM 53-00-03, FIG 201, REPAIR 2, REV 92.00.

Part: STRINGER — CORRODED (BS 412-434) · corrosion level 2 · airframe 71,823 hrs · 32,717 cycles

FWD CARGO BS 412-434, STRINGER 35R CORRODED, REPAIR CARRIED OUT IAW SRM 53-00-03 FIG 201, REPAIR 2, REV 92.00.

Part: STRINGER — CORRODED (BS 412-434) · airframe 71,823 hrs · 32,717 cycles

FWD CARGO -BS 412-434, STRINGER 38R CORRODED. REPAIR CARRIED OUT IAW SRM 53-00-03, FIG 201, REPAIR 2, REV 92.00.

Part: FRAME — CRACKED (BS 1809) · airframe 71,823 hrs · 32,717 cycles

DURING HFEC INSPECTION ON BS 1809, BULKHEAD LT FORWARD OUTER FRAME S6-7L FOUND CRACKED. REPAIRED FRAME.

Part: STRUCTURE — CORRODED (BS 857-859) · corrosion level 2 · airframe 71,849 hrs · 32,723 cycles

WING CENTER SECTION UPPER SURFACE BETWEEN BS 857 AND 859, LBL 88. REWORKED IAW PRI 514634-14, REV 0, REV 1, REV 2, REV 3 AND REV 4.

Part: STRUCTURE — CORRODED (BS 927) · corrosion level 2 · airframe 71,849 hrs · 32,723 cycles

WING CENTER SECTION UPPER SURFACE AT BS 927, LBL 90. REPAIR CARRIED OUT IAW- PRI 514016-14, REV 0, REV 1, REV 2, REV 3, REV 4, REV 5 AND REV 6. AND COMPLIED WITH ER/A 514016-14, REV ORIGINAL.

Part: SKIN — CRACKED (BS 687) · airframe 79,053 hrs · 34,779 cycles

CRACK AT BS 687, STRINGER 36R AT CARRY THOUGH HOLE, RT AIRFONE BLANKING PLATE, 1/8TH INCH CRACK.

Part: SKIN — CRACKED (FUSELAGE) · airframe 71,463 hrs · 32,608 cycles

SKIN CRACKED ONE EIGTH INCH CRACK RT AIRFONE BLANKING PLATE INST STA 687 STR 36R AT CARRY THRU HOLE LOC MARKED REF ERA 389647-14 REV A. REPAIRED PER SRM B767-300 53-00-01 REPAIR 12.

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 67,264 hrs · 31,432 cycles

RT WING OTBD FLAP LWR SURFACE MID INSPAR PANEL SKIN DELAMINATED AT APPROX 66"FROM INBD AND 24" FRM BOTTOM; CA: REPAIR DOUBLER AND FILLER FABRICATED IAW SRM 57-53-01 OTIS. REPAIR PARTS BONDED IAW SRM 51-70-10 OTIS. DECAL INSTALLED ADJ TO REPAIR IAW PS 900-5-1, NR4.

Part: WEDGE — DELAMINATED (LT WING NR2 SLAT) · airframe 67,264 hrs · 31,432 cycles

LT WING L/E NR2 SLAT WEDGE UPPER SURFACE FOUND DELAMINATED; CA: LT WING L/E NR2 SLAT WEDGE UPPER SURFACE, REPAIR FILLER AND DOUBLER FABRICATED IAW 51-70-10 OTIS. DECAL INSTALLED ADJ TO REPAIR IAW DELTA PS 900-5-1, NR 4.

Part: SKIN — DENTED (VERTICAL STAB) · airframe 67,264 hrs · 31,432 cycles

LT V-STAB EXTERIOR AROUND FS STA 270.784 FOUND DENT DURING HMV INSP AT SIN; C/A-DENTED SURFACE TRIMMED OFF. REPAIR PART FABRICATED IAW SRM 51-70-01, FIG 201, OT IS REPAIR PARTS BONDS IAW SRM 51-71-10.

Part: INDICATOR — MALFUNCTIONED (AIRSPEED) · airframe 62,859 hrs · 29,828 cycles

AFTER TO, F/O AIRSPEED INDICATOR BECAME UNREADABLE AND ROSE STEADILY TO 400 KTS. NO FLAGS OR OTHER INDICATIONS, OTHER THAN OVERSPEED WARNING. ACTUAL AIRSPEED ON CAPTS IND NORMAL. FOUND QUICK DISCONNECT DAMAGED ON PITOT PRESS ON RT ADC. REPLACED SAME. LEAK CHECKED PITOT/STATIC SYSTEM CHECKED GOOD. PERFORMED MCDP TEST 30 TEST PASSED. ADC LEFT AND RIGHT BITE CHECKED GOOD.

Part: TRUNNION — CORRODED (NLG) · airframe 62,858 hrs · 29,827 cycles

LT AND RT NOSE LANDING GEAR TRUNNION FITTINGS CORRODED IN THE INNER DIAMETER. CORROSION CLEANED UP AND OVERSIZED BUSHINGS WERE INSTALLED.

Part: MEC — MALFUNCTIONED (NR 2 ENGINE) · airframe 62,176 hrs · 29,617 cycles

RTO DUE TO RT ENGINE WOULD NOT MAKE TAKEOFF POWER. REPLACED RT ENGINE MEC. AFTER RUNUP ENGINE MAKES TAKEOFF POWER.

Part: CHARGER — MISSING (EMERGENCY LIGHTS) · airframe 61,273 hrs · 29,350 cycles

EMERGENCY LIGHT EXIT SIGN INOP AT L1 AND R1 DOOR. INSTALLED NEW BATTERY AND CHARGER TRA, FOUND TRAY AND BATTERY PACK ASSY MISSING AT L1 POSITION.

Part: FLOORBEAM — CORRODED (BS 287 RBL 51) · airframe 59,363 hrs · 28,566 cycles

CABIN FLOORBEAM UPPER CHORD STA 287 CORRODED AT RBL 51 TO RBL 62 AND ALSO EXISTING SPLICE PLATE CORRODED AT RBL 10 TO RBL 15. REPAIRED PER SRM 53-00-51D FIGURE 201, AMM 32-41-00.

Part: FRAME — CRACKED (BS 903) · airframe 59,363 hrs · 28,566 cycles

FUSELAGE STATION 903.5 FRAME INNER CHORD FOUND CRACKED. ON BOTH LT AND RT AT TRANSITION BETWEEN CHORD FLANGES. AREA TRIMMED AND REPAIR INSTALLED.

Part: FLOORBEAM — CRACKED (BS 325 LBL 32) · airframe 59,363 hrs · 28,566 cycles

CABIN FLOORBEAM AT STA 325 LBL 32 UPPER STRUCTURE BENT AND CRACKED IN RADIUS AS MARKED. REPAIRED PER SRM 53-00-51D FIGURE 201.

Part: RIB — CORRODED (RT WING) · airframe 59,363 hrs · 28,566 cycles

RT WING RIB NR 8, LOWER OUTBOARD HOLE WAS FOUND WITH CORROSION PITTING. DAMAGE WAS REMOVED BY OVERSIZED HOLE, BUSHING INSTALLATION.

Part: FITTING — FATIGUED (NR 1 ENGINE) · airframe 59,363 hrs · 28,566 cycles

CRACK INDICATIONS WERE FOUND AT THE FORWARD OUTBOARD BOLT HOLE LOCATION OF THE AFT PITCH LOAD FITTING, NR 1 PYLON. CRACK IS IN LOWER WING SKIN ALSO, AND REQUIRED SUBJECT HOLE TO BE OVERSIZED AND BUSHED BACK TO DIAMETER.

Part: FITTING — FATIGUED (PYLON) · airframe 59,363 hrs · 28,566 cycles

DURING REWORK OF THE FORWARD UPPER SPAR FITTING PER SIP EO, CRACKING INDICATIONS WERE FOUND AT AFT OUTBOARD FASTENER LOCATIONS COMMON TO MIDSTRUT BULKHEAD FITTING ON EACH PYLON. HOLES WERE OVERSIZED AND BUSHED BACK TO DIAMETER.

Part: LINKAGE — MISINSTALLED (EVAC SLIDE) · airframe 59,363 hrs · 28,565 cycles

DURING INSPECTION OF THE LT OFF WING ESCAPE SLIDE PER JIC 6075 THE TECHNICIAN FOUND THAT THE INTEGRATOR LOCK HANDLE HAD TO BE FORCED INTO THE SAFETY POSITION. UPON FURTHER INVESTIGATION IT WAS DETERMINED THAT SLIDE DOOR OPENING ACTUATOR LINKAGE LEVER WAS INSTALLED UPSIDE DOWN CAUSING BINDING BETWEEN THE LEVER AND LINKAGE CLEVIS. SUBSEQUENT INSPECTION OF THE RH SLIDE FOUND THE SAME CONDITION. REFERENCE: ON ROUTINE JOBCARDS N613, N619 & JIC 6075, IPC 25-65-51-01

Part: SKIN — LIGHTNING STRIKE (FUSELAGE) · airframe 58,544 hrs · 28,307 cycles

FUSELAGE SKIN WAS STRUCK BY LIGHTNING BETWEEN BS 257 AND 277 BELOW S-11L. THE DAMAGED SKIN WAS REMOVED AND A DOUBLER WAS INSTALLED.

Part: BOLT — MISSING (NR 2 SLAT) · airframe 57,871 hrs · 27,997 cycles

NR 2 SLAT I/B ACTUATOR COVER DAMAGED. REINSTALLED MISSING HARDWARE, RAN SLATS, ALL OK.

Part: SKIN — CRACKED (STA STR3L) · airframe 50,148 hrs · 24,331 cycles

MECHANIC FOUND 2 INCH CRACK IN FUSELAGE SKIN RT SIDE STA 1654.5 STR 3R. ALSO, FOUND STRINGER 3R AND 3L CRACKED AT SAME LOCATION. REPAIRED CRACK.

Part: SKIN — DENTED (FS 290, S-37R) · airframe 47,619 hrs · 23,083 cycles

FUSELAGE / SKIN / FS 287-303 / STRG. 37R : DENT REPAIR THE FUSELAGE SKIN WAS DENTED AT THE STRINGER 37R SKIN LAP JOINT BETWEEN FS 287 & 303. THE LAPJOINT WAS CUTOUT IN THE AREA TO REMOVE THE DENT. THE CUTOUT WAS REPAIRED WITH 2 ALUMINUM EXTERNAL DOUBLERS PER ER/A 383469-14.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 47,209 hrs · 22,883 cycles

OVERHEAD AISLE LIGHTS FIRST CLASS LEFT SIDE INOP. REPLACED BATTERY PACK AND RACK.

Part: SKIN — CRACKED (FUSELAGE) · airframe 46,830 hrs · 22,698 cycles

WHILE ACCOMPLISHING THE FS 1809.5 BULKHEAD OUTER CHORD MOD PER BAC S/B 767-53-0078 AND AD 2001-09-13, A CRACK WAS FOUND IN THE SKIN COMMON TO A FASTENER HOLE FOR THE OUTER CHORD ON THE LT SIDE. THE HOLE WAS OVERSIZED IN THE SKIN ASSY ONLY AND A BUSHING INSTALLED. THE WORK WAS ACCOMPLISHED PER ER/A 382872-14, REV A.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 45,865 hrs · 22,225 cycles

LEFT FORWARD OVERHEAD EMERGENCY LIGHTS INOP IN CABIN. REMOVED AND REPLACED BATTERY PACK FOR LEFT FORWARD OVERHEAD EMERGENCY LIGHTS, CHECKS GOOD.

Part: ENGINE — UNSERVICEABLE (#2 ENGINE) · airframe 45,312 hrs · 21,945 cycles

ON CLIMB OUT RIGHT ENGINE STALLED. ACCOMPLISHED POM "ENGINE SURGE OR STALL" PROCEDURE. THROTTLE REDUCED TO IDLE. ENGINE SHUT DOWN AFTER LANDING. EGT MAX 895 FOR 1.4 SECONDS. FOUND METAL IN EXHAUST. REPLACED ENGINE.

Part: PROBE — MALFUNCTIONED (LT NOSE AREA) · airframe 43,704 hrs · 21,198 cycles

RTB FOR INSP. DUE TO SMOKE COMING FROM LT NOSE AREA OVER RADOME. J/C VISUAL INSPECTION OF NLG AREA, FWD AND MAIN E/E COMPARTMENTS. ALSO VISUALLY INSPECTED OF LT / RT ACM AREAS AND RADAR ANTENNA AREA. NO ANOMALIES NOTED-ALL HYD QTYS NORMAL, NO HYD LEAKS FOUND. REPLACED TAT PROBE AS PRECAUTION PER M/M. PERF CADC BITE TEST. NO ABNORMAL CONDITIONS NOTED. RAN BOTH ACMS AND PNEU.SYS, ALL CK NORMAL

Part: FRAME — CORRODED (FUSELAGE) · airframe 43,377 hrs · 21,021 cycles

CORROSION WAS FOUND ON THE FWD FRAME AT THE CUTOUT FOR THE FWD LT PASSENGER DOOR. THE CORROSION WAS LOCATED ON THE AFT SURFACE OF THE FRAME WEB SURROUNDING THE GIRT BAR HOLE (JUST ABOVE CABIN FLOOR LEVEL). REPAIRED DAMAGE PER ER/A 396699-14.

Part: SKIN — DENTED (FUSELAGE) · airframe 43,377 hrs · 21,021 cycles

FUSELAGE SKIN WAS DENTED DUE TO NOSE TIRE BLOWOUT. THE DENTS WERE APPROVED FOR INTERIM SERVICE PER ER/A 269377-14. THE DAMAGE WAS PERMANENTLY REPAIRED PER ER/A 269377-14 AT OVERHAUL MTC VISIT. REPAIRED DAMAGE PER ER/A 269377-14.

Part: LIGHT — INOP (CABIN)

FOUR AISLE EMERGENCY LIGHTS INOP AFT RIGHT SIDE. REPLACED POWER SUPPLY, SYSTEM CHECKS NORMAL.

Part: MASK — FELL (CABIN)

THE O2 MASK ZONE C HANGING DOWN. REINSTALLED MASK AND SECURED PANEL.

Part: SKIN — CORRODED (CENTER WING)

CORROSION WAS FOUND ON THE WING CENTER SECTION. DAMAGE LOCATED ON AFT SKIN PANEL, FWD EDGE ON THE LT OUTBD END. REPAIRED PER ERA 331990-14.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

ON L/O, FOUND ZONE EMERGENCY TRACK LIGHTS INOP BOTH AISLES. REPLACED PWR SUPPLY M9010. LIGHTS OPS NML.

Part: SKIN — DELAMINATED (NR 9 LE SLAT)

THE NR 9 LE SLAT TRAILING EDGE WEDGE WAS FOUND TO HAVE A 3.5 DIAMETER SECTION OF THE UPPER SKIN DELAMINATED. THE DAMAGE IS LOCATED IN THE CENTER OF THE SLAT WEDGE FWD/ AFT AND INB'D/OUTB'D. THE DAMAGED SECTION WAS REPAIRED PER B767 SRM 57-43-02, FIGURE 201.