N796AX

Part: BOLT — MISSING (TRUNNION) · airframe 47,428 hrs · 39,209 cycles

LT MAIN LANDING GEAR TRUNNION DOOR FITTING ON TOP OF STRUT MISSING AFT BOLT AND ATTACHING HARDWARE. INSTALLED CORRECT HARDWARE PER IPC 32-12-01-5, SHEET 2 AND AMM 32-12-06. (BOLTS 2 EA-BACB30LJ6U15). (S)

Part: LIGHT — INOPERATIVE (CABIN) · airframe 46,948 hrs · 38,973 cycles

MAINTENANCE AT ILN FOUND MAIN ENTRY DOOR EMERGENCY ESCAPE LIGHT LENS CRACKED AND LIGHT INOP. REMOVED AND REPLACED MAIN ENTRY DOOR EMERGENCY ESCAPE LIGHT ASSEMBLY IAW B767 AMM 33-51-06-2.

Part: DOOR FRAME — CORRODED (FWD CARGO DOOR) · airframe 46,878 hrs · 38,931 cycles

FORWARD LOWER CARGO DOOR FRAME UNDER VENT DOORS CORRODED IN SEVERAL PLACES. REMOVED AND REPLACED FORWARD LOWER CARGO DOOR FRAME IAW B767 SRM.

Part: BEAM — CORRODED (AFT CARGO DOOR) · airframe 46,878 hrs · 38,931 cycles

I-BEAM DIRECTLY BELOW DEPRESSURIZATION VENTS ON AFT LOWER CARGO DOOR HEAVILY CORRODED. REMOVED AND REPLACED BEAM IAW B767 SRM 51-40-2.

Part: STRAP — CORRODED (RT WING) · corrosion level 2 · airframe 45,187 hrs · 38,046 cycles

UPPER SPAR CAP STRAP AT RT WING STA 792 HAD INTERGRANULAR CORROSION. REPAIRED AREA IAW REA B657-54341.

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,187 hrs · 38,046 cycles

FRAME CORRODED AT STA 1219 BETWEEN S38-47R. REMOVED AND REPLACED SHEAR TIE IAW B767 SRM 51-40-02.

Part: MODULE — LEAKING (HYD SYSTEM) · airframe 41,262 hrs · 36,598 cycles

CENTER HYDRAULIC QUANTITY DECREASED TO .13, SYSTEM DEPRESSURIZED AND LEAK CONTINUED. ON APPROACH, COMPLETE LOSS OF CENTER HYDRAULICS. FOUND FLAP/SLAT SHUTOFF VALVE MODULE ASSEMBLY LEAKING AT FILTER HOUSING. REPLACED FLAP/SLAT SHUTOFF VALVE MODULE ASSEMBLY IAW B767 AMM 27-51-48-2. LEAK AND OPS CHECKED GOOD. SERVICED CENTER HYDRAULIC SYSTEM TO 1.12.

Part: DUCT — OUT OF ADJUST (AIR CONDITIONER) · airframe 40,464 hrs · 36,319 cycles

MAINTENANCE COULD NOT OPEN R-2 WINDOW. FOUND WINDOW BINDING ON LOWER AC DUCT. ADJUSTED AND SECURED AC DUCT. WINDOW OPENED NORMALLY.

Part: FITTING — ELONGATED (NACELLE) · airframe 40,254 hrs · 36,237 cycles

DURING INSPECTION, ON LEFT STRUT FORWARD UPPER SPAR FITTING, FOUND FOUR BOLT HOLES SHOULD BE .4375 INCH ARE ALREADY OVERSIZED TO 0.515 INCH AND BACB 30 MT8X ARE INSTALLED. SB GIVES A MAXIMUM OVERSIZE OF 4692 INCH FOR THOSE HOLES. REWORKED AREA IAW REA B654-46255MR.

Part: STRUT — GOUGED (MLG) · airframe 40,254 hrs · 36,237 cycles

DURING INSPECTION, TWO GOUGES WERE FOUND ON NR 2 ENGINE STRUT RIGHT SKIN PANEL NEAR ACCESS DOOR CUT OUT. MAXIMUM DEPTH OF BLENDED OUT REQUIRED TO COMPLETELY REMOVE DAMAGE, 0.025 INCH. REPAIRED AREA IAW REA .

Part: PANEL — GOUGED (NR 1 NACELLE) · airframe 40,254 hrs · 36,237 cycles

DURING INSPECTION, TWO GOUGES WERE FOUND ON NR 1 ENGINE STRUT RIGHT SKIN PANEL NEAR AN ACCESS DOOR CUTOUT. MAXIMUM DEPTH OF BLEND OUT REQUIRED TO COMPLETELY REMOVE DAMAGE WAS 0.035 INCH. REPAIRED AREA IAW REA B654-46243MR.

Part: FRAME — DAMAGED (NACELLE) · airframe 40,254 hrs · 36,237 cycles

NR 2 ENGINE RIGHT CORE COWL FRAME NAS STA. 304.60 AND NAC WL 73, DAMAGE WAS FOUND ON FRAME P/N 314T1210-333. REPAIRED AREA IAW REA B671-46254MR.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 40,254 hrs · 36,237 cycles

CARGO DOOR GOUGE WAS FOUND IN THE PART AT BULK CARGO DOOR INNER SKIN, STA. 1439, WL 131, P/N 146T6334-1, GOUGE ON INNER SKIN. REPAIRED AREA IAW REA MR.

Part: DOOR FRAME — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 40,254 hrs · 36,237 cycles

AFT CARGO DOOR BEAM NR 5, CORROSION WAS FOUND ON THE INNER CHORD P/N 140T2605-3 UNDERNEATH PUMP. AFTER CORROSION REMOVED MINIMUM REMAINING THICKNESS WAS 0.082, WHILE ORIGINAL THICKNESS WAS 0.125 INCH.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,254 hrs · 36,237 cycles

RIGHT STA. 883.5 FRAME SEGMENT P/N 145T1003-2 FAIL SAFE FRAME AT STR. 18 RIGHT WAS FOUND CORRODED. THE ORIGINAL THICKNESS OF FRAME WAS 0.200 INCH AFTER BLENDED OUT CORROSION THE REMAINING THICKNESS WAS 0.170 INCH. REPAIRED AREA IAW REA B653-46282, REV. 'A'.

Part: STRINGER — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 40,254 hrs · 36,237 cycles

RIGHT HORIZONTAL STAB. LOWER STRINGER NO. 10 LOWER HORZ. FLANGE RBL 56, P/N 181T4110-4, FOUND CORROSION DURING INSPECTION ON STRINGER P/N 181T4110-4 COMMON TO SKIN PANEL REMAIN THICKNESS MATERIAL OF 0.135 INCH ORIGINAL THICKNESS WAS 0.165 INCH. THE TOTAL BLENDED AREA WAS APPROXIMATELY 2.5 INCH AND 1 INCH WIDE. REPAIRED AREA IAW REA B655-46297MR.

Part: SUPPORT FITTING — DAMAGED (RT WING) · corrosion level 2 · airframe 40,254 hrs · 36,237 cycles

RIGHT WING TRAILING EDGE 113T1647-6 PANEL SUPPORT FITTING ASSEMBLY DAMAGED DOUBLE HOLE AND BLENDED AREA STA 1051 RIGHT BUTTLINE 97.4. REPAIRED AREA IAW REA B657-46309MR.

Part: WIRE — DAMAGED (APU) · airframe 40,254 hrs · 36,237 cycles

APU GENERATOR FEEDER WIRE DAMAGE, CAUSED SHORT CIRCUIT TO GROUND, RESULTING ARCHING TO WIRE AND CLAMP AT STA 1788 RIGHT. REPLACED THE FEEDER WIRE FROM THE NEARBY SPLICE TO APU SHROUD CONNECTOR D 4016J, AND CLAMP. OPS CHECKED GOOD IAW B767 MM.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 39,554 hrs · 36,768 cycles

CABIN RIGHT SIDE STA 287 FLOORBEAM, RBL 73, FOUND CORROSION ON UPPER FLANGE OF FLOORBEAM, WL 199.5. PERFORMED FLOORBEAM UPPER CHORD REPAIR IAW SRM 53-00-51, FIGURE 201, REF SRM 53-10-51 AND DWG NR 141T5111. INSTALLED IAW SRM 51-40-02.