AA767, LLC

Part: SKIN PANEL — CORRODED (LT WING) · airframe 64,534 hrs · 28,018 cycles

LW SKIN CORRODED AT OVERWING FILL PORT.

Part: SKIN PANEL — CORRODED (RT WING) · airframe 64,534 hrs · 28,018 cycles

RW SKIN CORRODED AT OVERWING FILL PORT.

Part: RIB — CORRODED (LT WING) · corrosion level 2 · airframe 64,534 hrs · 28,018 cycles

LW AIRLOAD RIB CORRODED.

Part: SKIN PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 64,534 hrs · 28,018 cycles

LW UPPER SKIN PANEL CORRODED.

Part: LONGERON SPLICE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,534 hrs · 28,018 cycles

FUSELAGE EXTERNAL LONGERON SPLICE FITTING CORRODED.

Part: SKIN PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 64,534 hrs · 28,018 cycles

LW UPPER SKIN PANEL CORRODED.

Part: SKIN PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 64,534 hrs · 28,018 cycles

LW UPPER SKIN CORRODED.

Part: PANEL SUPPORT — CORRODED (LT WING) · corrosion level 2 · airframe 64,534 hrs · 28,018 cycles

LW TRAILING EDGE PANEL SUPPORT CORRODED.

Part: STRUCTURE — CORRODED (LT WING) · corrosion level 2 · airframe 64,534 hrs · 28,018 cycles

LW UPPER CHORD CORRODED AT TRAILING EDGE.

Part: ATTACH ANGLE — CORRODED (RT WING) · corrosion level 2 · airframe 64,534 hrs · 28,018 cycles

RW LOWER RIB ATTACH ANGLE ON WING TRAILING EDGE IS CORRODED.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 64,534 hrs · 28,018 cycles

UPPER CHORD ON FLOOR SUPPORT INTERCOSTAL CRACKED.

Part: SUPPORT — GOUGED (RT WING)

DEFECTS BEYOND SRM LIMITS FOUND IN FLAP SUPPORT HOLES FOR FLAP SUPPORTS 1, 7 & 8 WHILE ACCOMPLISHING SB 767-57A0131. HOLES WERE OVERSIZED, OVERSIZE BOLTS INSTALLED.

Part: LINKAGE — WORN (LT WING) · airframe 63,876 hrs · 27,788 cycles

FOUND LOOSE BUSHINGS IN FLAP SUPPORT LINKAGE 9 - 10 BEAM. BUSHINGS WERE REMOVED, HOLES IN LINKAGE OVERSIZED & OVERSIZED BUSHINGS WERE INSTALLED.

Part: SHAFT — BROKEN (INTERGRATER) · airframe 63,083 hrs · 27,548 cycles

DURING A-CHECK, OVERWING ESCAPE SLIDE FAILED TO OPEN WHILE PERFORMING OPS CHECK. FOUND BROKEN SHAFT ON INTEGRATER. REPLACED INTEGRATER. OPS CHECKED GOOD.

Part: DOOR FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 62,945 hrs · 27,501 cycles

DURING 'A' CHECK FOUND AFT LOWER CARGO DOOR JAMB AFT LOWER CORNER CORRODED. REPAIRED IAW AMES REA 47048REA02.

Part: SKIN — CRACKED (ZONE 200) · airframe 62,734 hrs · 27,441 cycles

DURING A ROUTINE SCHEDULED C2 INSPECTION, STA 1654 HAS 3 FUSELAGE SKIN CRACKS, ADJACENT TO S3 LENGTH 1.125, 2 BETWEEN S4 & S5 LENGTHS .175 AND .075. REPAIRED USING 0.032, 0.040, 0.063 7075 T6 REF SRM 53-80-01, FIG 201, REPAIR 4.

Part: SKIN — CRACKED (ZONE 200) · airframe 62,734 hrs · 27,441 cycles

DURING A ROUTINE C2 INSPECTION, FOUND CRACKS EMINATING FROM FASTENERS AT BS 1654.5 BETWEEN STR 3 RT AND STR 7 RT. FOUR CRACKS, THE LONGEST MEASURING .5". REPAIRED USING 0.032, 0.040, 0.063 7075 T6 REF SRM 53-80-01, FIG 201, REPAIR 4.

Part: BULKHEAD — DENTED (ZONE 100) · airframe 62,734 hrs · 27,441 cycles

DURING A ROUTINE SCHEDULED C2 INSPECTION,FOUND AFT PRESSURE BULKHEAD BS 1582 AFT SIDE DENT INBD OF RADIAL STIFFENER 16, ABOVE TEAR STRAP 3. CUT OUT DENT DAMAGE IN WEB AND LAYED OUT AND INSTALLED REPAIR REF SRM 53-80-03, AND EXTENDED FASTENER ROWS PAST RADIAL 16, TWO ROWS.

Part: STRAP — DAMAGED (NR 1 FLAP) · airframe 62,734 hrs · 27,441 cycles

DURING A ROUTINE SCHEDULED C2 INSPECTION, NR 1 FLAP SUPPORT FITTING OTBD STRAP UPPER COUNTERSUNK FASTENER, COUNTERSINK DAMAGED. THE OTBD SIDE HAS A THICKNESS OF 0.865. THE DAMAGE WAS REMOVED AND THE COUNTERSINK FASTENER HAD A MAXIMUM WIDTH OF 0.635 AND DEPTH OF 0.115. THE HOLE WAS REAMED TO THE NEXT HOLE SIZE (0.434-0.438 DIA) AND INSTALLED BACB30NW14K FASTENER WET WITH BMS 5-95 SEALANT. REWORK WAS ACCOMPLISHED IAW ENGINEERING DOCUEMENT 47023REA03 APPROVED.

Part: BULKHEAD — DENTED (ZONE 200) · airframe 62,734 hrs · 27,441 cycles

DURING A ROUTINE SCHEDULED C2 INSPECTION, DISCOVERED AFT PRESSURE BULKHEAD BS 1582 AFT SIDE HAS A DENT INBD OF RADIAL STRAP 17 BETWEEN TEAR STRAP 4 & TEAR STRAP 5. CUT OUT DAMAGE, FABRICATED REPAIR DOUBLER AND INSTALLED IAW SRM 53-80-08, FIG 201, REPAIR 2.

Part: SKIN — DENTED (ZONE 100) · airframe 62,734 hrs · 27,441 cycles

DURING A ROUTINE SCHEDULED C2 CHECK INSPECTION, A DENT WAS DISCOVERED AT BS 1619, BETWEEN S-33R AND S-32R. FOUND DENT TO BE OUT OF LIMITS IAW SRM 53-00-01, FIG 101, DETAIL III. REPAIRED DENT IAW SRM 53-00-01, REPAIR 14, FIG 201.

Part: STIFFENER — CORRODED (ZONE 100) · corrosion level 2 · airframe 61,332 hrs · 27,015 cycles

DURING THE PROCESS OF GAINING ACCESS TO THE FAIL-SAFE STRAP TRIM OUT AREA, IT WAS DETERMINED THAT THE INSTRUCTION IAW REV 1 OF THE SB WAS INSUFFICIENT TO REMOVE THE T-FITTINGS. MFG WAS CONTACTED VIA FIRST RESPONSE ON 6/9/09 AND THE SB ENGINEERING GROUP RESPONDED WITH THE INSTRUCTION REQUIRED VIA E-MAIL ON 6/10/09. THE SKIN STIFFENERS (T-FITTINGS) WERE REMOVED AND CORROSION WAS FOUND ON BOTH THE LT AND RT SKIN STIFFENERS (T-FITTINGS). IAW THE SENT INSTRUCTION, REV 2 OF THE SB, WHICH IS DUE OUT Q3 OF THIS YEAR, WILL INCLUDE THE DATA FOR T-FITTING REMOVAL AND INSTRUCTION TO CHANGE ANY CORRODED T-FITTINGS. CURRENTLY WE HAVE ORDERED AND RECEIVED BOTH OF THE T-FITTINGS FOR REPLACEMENT (PN 100T1440U3(LT) & 100T1440U4(RT). THE TRIM OUT PROCEDURE WAS COMPLIED WITH IAW THE SB 767-53A0100 FIGURE 15 ON 6/12/09. THE FINAL NDT TESTING WAS COMPLIED WITH ON 6/13/09 AND IT WAS VERIFIED THAT ALL CRACKS WERE REMOVED. CURRENTLY THE ACFT IS BEING RESTORED BACK TO THE USUAL CONDITION AND TERMINATING ACTION WILL BE COMPLETE IAW SB 767-53A0100. MFG DID INFORM AA767,LLC. THAT ALL TERMINATING ACTION IAW REV 1 OF THE SB WILL BE ACCEPTABLE AND THE UPCOMING REV 2 WILL HAVE NO FURTHER REQUIREMENTS.

Part: SKIN — CRACKED (FUSELAGE) · corrosion level 2 · airframe 61,332 hrs · 27,015 cycles

DURING REMOVAL OF THE RT LWR AFT BODY FAIRING, ZONE 198, A CRACK WAS DISCOVERED IN THE FUSELAGE SKIN BETWEEN BS 1197 AND 1199, .5 INCH ABOVE STRINGER S-32R. THE CRACK IS APPROXIMATELY 1.625 INCHES IN LENGTH AND RUNS PARALLEL TO THE STRINGER. THE CRACK IS A RESULT OF LOCAL, LEVEL 2 CORROSION BEHIND THE AFT CARGO BIN SIDEWALL.

Part: FAILSAFE — CRACKED (FUSELAGE) · corrosion level 2 · airframe 61,332 hrs · 27,015 cycles

ON 5-13-09 AT 1600 HRS. NOTIFIED THAT WHILE COMPLYING WITH SB 767-53A0100 IAW AD 2004-19-06: ULTRASONIC TESTING OF THE LT AND RT STA 955 REAR BULKHEAD SIDE FITTING FAIL-SAFE STRAPS SHOWED POSSIBLE CRACKING OF BOTH FAIL-SAFE STRAPS AND RECEIVING THE NDT REPORT THE FOLLOWING DAY. UPON RECEIVING THE REPORT, THE INSTRUCTION OF THE SB WAS REVIEWED AND MFG WAS CONSULTED FOR VERIFICATION OF OUR NEXT COURSE OF ACTION. IT WAS DETERMINED THAT AN OPEN HOLE HFEC WAS NEEDED TO VERIFY THE THE EARLIER FINDINGS. ON 5-18-09 BOTH LT AND RT HOLES HAD HFEC TESTING DONE TO CONFIRM OUR FINDINGS. IT WAS DETERMINED THAT THE LT FAIL-SAFE STRAP LOWER BOLT HOLE HAD A CRACK INDICATION ON THE FWD EDGE OF THE HOLE. THE RT FAIL-SAFE STRAP INSP ALSO CONFIRMED A CRACK ON THE AFT EDGE OF THE HOLE WITH SIGNS OF CORROSION. WE RECEIVED THE FINAL NDT REPORT ON 5-19-09. WE ARE CURRENTLY PLANNING TO DO THE TERMINATING ACTION IAW SB 767-53A0100 (R1) STEP 3. B.

Part: WINDSHIELD — DELAMINATED (COCKPIT) · airframe 61,250 hrs · 26,981 cycles

RT NR1 WINDSHIELD FAILURE.

Part: WIRE — MISINSTALLED (ESCAPE SLIDE)

WHILE ACFT WAS ON GROUND, WITH JUST APU RUNNING, THE LT OVERWING SLIDE DEPLOYED. THE ESCAPE HATCH WAS NOT DISTURBED. THIS TOOK PLACE IN LFPB. THE ONLY THING DONE PRIOR TO DEPLOYMENT WAS THAT THE LEAD F/A PUSHED THE EMERGENCY LIGHTING TEST SWITCH AT THE L1 CONTROL PANEL LOCATED ON THE F/A JUMP SEAT. THE TEST FUNCTIONED CORRECTLY, AND APPROX. 5 MIN. AFTER THE TEST, THE SLIDE DEPLOYED. THE SLIDE COMPONENTS REMOVED WERE SLIDE RAMP ASSY P/N 101630-305 S/NPG0261, INITIATOR ACTUATOR P/N 6023100-2,S/N 0263, LATCH ACTUATOR P/N 3125400-11,S/N 266, ACTUATOR P/N 526-2100, S/N 1171, BOTTLE P/N 130104-237, S/N IZ4603, EMERGENCY BATTERY CHARGER P/N 2012-1 AND BATTERY PACK P/N 2013-1A. THE BATTERY WAS FOUND TO HAVE A VOLTAGE OF 1.8 VOLTS. INSTALLED O/H SLIDE RAMP ASSY P/N 101630-305, S/N PG0192, O/H BOTTLE P/N 130104-237, S/N IZ5570, NEXT O/H DATE OF 01/11/2012, INITIATOR ACTUATOR P/N 6023100-2 S/N DL3, ACTUATOR P/N 5262100 S/N 2870, ACTUATOR P/N 3125400-11, S/N 2622, BATTERY CHARGER P/N 2012-1 S/N 2214 AND BATTERY PACK ASSY P/N 2013-1A, S/N 95660, AND ACTUATOR P/N 5262100, S/N 2872.THE SYSTEM FAILED DUE TO STC WIRING INSTALLED TO BATTERY PACK AFTER EXTENSIVE INVESTIGATION AT A CERTIFIED REPAIR STATION IN THE US.