N312AA

Part: WARNING MESSAGE — FALSE ACTIVATION (FUEL PUMP) · airframe 95,873 hrs · 25,232 cycles

DURING TAXI OUT R AFT FUEL PUMP EICAS MESSAGE APPEARED ,A/C RETURNED TO GATE AND MTX GROUNDED AC MTX THEN PERFORMED RH AFT PUMP OPERATIONAL TEST PER ABX-B767 AMM 28-22-00 NO FAULTS FOUND .AC REMAINS NO ETOPS . AND RETURNED A/C TO SERVICE.

Part: GENERATOR — FAULTED (RIGHT) · airframe 95,786 hrs · 25,190 cycles

DURING TAXI AND UPON NR 2 ENGINE START, RT GENERATOR CONT INDICATED OFF, RT AC BUSS INDICATED NO POWER, RT BUSS TIE INDICATED OFF AND FMC AND LOWER EICAS WENT DEAD. AIRCRAFT RETURNED TO BLOCKS (BTB). MAINTENANCE TESTED RT IDG IAW FIM 24-20-43 A1. OPS CHECKED GOOD. IDG OPS CHECKED IAW AMM 24-11-01. AIRCRAFT REMAINS NO ETOPS. AIRCRAFT RETURNED TO SERVICE.

Part: PROXIMITY SWITCH — DEFECTIVE (ZONE 100) · airframe 95,434 hrs · 25,029 cycles

DURING PUSH BACK AFTER ENGINE START  STATUS MSG OF LDG GEAR MONITOR CAME ON, AC RETURNED TO THE GATE (BTB), MTX GROUNDED AC AND TROUBLESHOT, USING B767 FIM 32-09. FT 803. REMOVED AND REPLACED PSEU, IAW B767 AMM 32-09-04. AND CLEANED SENSOR S234 AND S235. PERFORMED BITE CHECK OF PSEU OPS CHECK GOOD . MTX RETURNED AC TO SERVICE.

Part: WARNING MESSAGE — ACTIVATED · airframe 95,348 hrs · 25,002 cycles

DURING TAXI, AFTER ENGINE START, RIGHT HYD QTY DROPPED SIGNIFICANTLY AND REFILL INDICATION CAME ON. AIRCRAFT RETURNED TO BLOCKS. (BTB). ACCOMPLISHED WALKAROUND OF A/C, NO SIGNS OF LEAKS. SERVICED RH HYDRAULICS IAW B767 AMM 12-12-01. MONITORED ENGINE START, ALL INDICATIONS NORMAL. AIRCRAFT RETURNED TO SERVICE.

Part: SMOKE DETECTOR — DEFECTIVE (ZONE 100) · airframe 95,113 hrs · 24,923 cycles

BELOW 1000 FT ON FINAL APPROACH INTO CVG, RECEIVED A FWD EQPT SMOKE EICAS MESSAGE. LANDED WITHOUT INCIDENT. CALLED CFR. CFR VERIFIED THERE WAS NO SMOKE OR FIRE. MAINTENANCE T/S, DETERMINED INTERMITTENT SMOKE INDICATION FROM TS164, E/E SMOKE DETECTOR. REMOVED AND REPLACED SMOKE DETECTOR. CONDUCTED TEST PER IAI MM SUPP 21-58-00 AND AMM 21-58-00. OPS TEST OK. AIRCRAFT RETURNED TO SERVICE. A/C VERIFIED ETOPS 180.

Part: LINK — GOUGED (RT WING TE FLAP) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, THE RH WING OUTBD. FLAP, MAIN DRIVE LINK, SIDE LINK PIN (I I 3TI 307-8) WAS FOUND GOUGED ON THE EDGE OF THE LOWER FLANGE. THE DAMAGE WAS BLENDED PER SRM 51-10-02, WITH MATERIAL LOSS OF 0.035 INCHES. THE WIDTH OF THE FLANGE AT THIS LOCATION IS 0.605 INCHES. THE SRM CHAPTER DOES NOT PROVIDE ALLOWABLE DAMAGE OR REPAIR DATA FOR THE SUBJECT PART. THE CMM-27-51-97, REPAIR 4-1 PROVIDES REPAIR ON BUSHING ONLY. ACCOMPLISHED BLEND REPAIR PER HAECO REO-G24737 REV IR AND ABX-REA-2750-65182-00. ABX FORM M-287, M-289 AND FAA FORM 337

Part: SKIN PANEL — CORRODED (ZONE 600) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, MAINTENANCE REPORTED THAT THE RH OUTBOARD FLAP UPPER SKIN PANEL, LOWER SKIN IS DELAMINATED. AFTER REMOVING THE DIS-BONDED SKIN, THE SIZE OF THE DAMAGE IS 70.4-INCH BY 8.10 INCHES. THE SRM 57-53-01, REPAIR L DIRECTED TO SRM 51-70-10 GENERAL AND STATED THAT THE LARGEST REPAIRABLE DAMAGE SHOULD NOT BE MORE THAN 50% OF THE TOTAL LENGTH. IT WAS FOUND THE TOTAL LENGTH OF THE CUTOUT IS MORE THAN 50% OF THE LENGTH OF THE LOWER SKIN SUBJECT. REPAIRED R/H WING O/B FLAP T/E SKIN PANEL INNER SKIN BY REMOVING DAMAGED AREA OF INNER SKIN AND FABRICATING AND BONDING SKIN FILLER AND DOUBLER IAW B767-200 SRM 57-53-01, 51-70-10-2R-4, 51-70-10-2R-0 ,ABX-REA-5750-65179-00, REO-G24723 REV IR AND REO-G24723.

Part: WEB — NONE (ZONE 200) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, MAINTENANCE REPORTED A REPAIR DOUBLER WAS FOUND THAT HAVE NO RECORD OF ACCOMPLISHMENT ON THE STA 1582 AFT PRESSURE BULKHEAD. THE REPAIR FOR A BLEND TO THE 148T2610-100 WEB IS LOCATED AT FASTENERS COMMON TO RSLL, JUST INBOARD OF TS6. THE BLEND MEASURES 1.75 INCH BY 1.25 INCH AND HAS A MINIMUM REMAINING THICKNESS OF 0.024 INCH. ORIGINAL THICKNESS IS 0.032 PER 8767-200 SRM 53-80-08-ID, FIGURE 1 ITEM 2 AND THE MATERIAL LOSS EXCEEDS THE ALLOWABLE PER 8767-200 SRM 53-80-08-AD, FIGURE 101 DETAILS 2 AND 4. REPAIRED AFT PRESSURE BULKHEAD WEB IAW BAX REA-5380-65280-00 & HAECO REA-G24817 REV IR. ABX FORM M-287, M-289.AND FAA FORM 337

Part: SKIN PANEL — DAMAGED (ZONE 500) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, MAINTENANCE REPORTED CORROSION DAMAGE ON LH WING UPPER SKIN PANEL NO.1, APPROX. AT WBL105 (112T3101-5), STRINGER UL-U3. DAMAGE WAS REMOVED BY BLENDING AFFECTED AREA PER SRM 51-10-02 WITH MEASURED MATERIAL REMAINING OF 0.171 INCHES FROM INITIAL THICKNESS OF 0.210-INCH (UT MEASURED) WITH MATERIAL LOSS OF 0.039-INCH, FOUND TO BE OUT OF LIMITS PER SRM 57-20-01, ADL 1, TABLE I OF 0.030 INCHES (BASED ON 0.196-INCH UT READING)RESTORED/REPAIRED AREA IAW ABX-REA-5720-65238-00 AND HAECO REO-G24750 REV: IR. ABX FORM M-287, M-289 AND FAA FORM 337.

Part: FRAME — CRACKED (BULKHEAD) · airframe 93,302 hrs · 24,080 cycles

DATUM AIRCRAFT IS IN CPZ FOR C24 MAINTENANCE CHECK. CPZ WAS TASKED WITH ACCOMPLISHING INSPECTIONS OF THE STA 1809.5 DATUM AIRCRAFT IS IN CPZ FOR C24 MAINTENANCE CHECK. CPZ WAS TASKED WITH ACCOMPLISHING INSPECTIONS OF THE STA 1809.5 BULKHEAD OUTER CHORD (LH) AS PER ABX JC 5380-0001-002 (SB 767-53A0078 PART 1 INSTRUCTIONS AND FIGURE 2). DURING THIS ACCOMPLISHMENT, HOLE 51 WAS FOUND CRACKED AND PERMANENT REPAIR WAS ACCOMPLISHED PER ABX JC 5380-0001-002 (SB 767-53A0078 PART 1 AND PART 4), AT 148T2740-9 FORWARD FRAME. HOWEVER, A CRACK INDICATION WAS PRESENT AT HOLE # 49 AND WAS REAMED TO 0.281-INCH DIAMETER THRU 148T2740-3 WEB AND 148T2740-1 BULKHEAD. THE ABX JC 5380-0001-002 (SB 767-53A0078) STATES TO CONTACT BOEING FOR REPAIR.REPAIRED IAW ABX-REA-5380-65254-00 AND REO-G24801 REV IR ,BAC-REA-5380-65254 AND HAECO REO-G24801. (LH) AS PER ABX JC 5380-0001-002 (SB 767-53A0078 PART 1 INSTRUCTIONS AND FIGURE 2). DURING THIS ACCOMPLISHMENT, HOLE 51 WAS FOUND CRACKED AND PERMANENT REPAIR WAS ACCOMPLISHED PER ABX JC 5380-0001-002 (SB 767-53A0078 PART 1 AND PART 4), AT 148T2740-9 FORWARD FRAME. HOWEVER, A CRACK INDICATION WAS PRESENT AT HOLE # 49 AND WAS REAMED TO 0.281-INCH DIAMETER THRU 148T2740-3 WEB AND 148T2740-1 BULKHEAD. THE ABX JC 5380-0001-002 (SB 767-53A0078) STATES TO CONTACT BOEING FOR REPAIR.REPAIRED IAW ABX-REA-5380-65254-00 AND REO-G24801 REV IR ,BAC-REA-5380-65254 AND HAECO REO-G24801.

Part: SKIN — CORRODED (ZONE 500) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, CORROSION DAMAGE WAS FOUND ON THE LH WING SKIN PANEL NO. 1, TRAILING EDGE OVERHANG AT APPROXIMATELY WS 230.00. THE DAMAGE WAS REMOVED BY BLENDING, HOWEVER, THE BLEND DEPTH WAS FOUND TO BE OUT OF THE B767-200 SRM 57-20-01 ALLOWABLE DAMAGE 1, TABLE 1 LIMITS AND THERE ARE NO APPLICABLE REPAIRS FOR THE DAMAGE LOCATION. REPAIRED SKIN PANEL PER HAECO REO-G24741 REV IR AND ABX-REA-5720-65185-00.

Part: SKIN PANEL — CORRODED (ZONE 100) · airframe 93,302 hrs · 24,080 cycles

MAINTENANCE CHECK. DURING ACCOMPLISHMENT OF SB-767-53A0100, FIGURE 37 (SPOT-FACING OF CORRODED SKIN)(REFERENCE AMES DOCUMENT 47008ORD10) REPAIR• FUSELAGE SECTION 45 - SKIN PANEL SPOTFACE REPAIR AT STA 955 RBL 97.S WL WAS FOUND THE MINIMUM MATERIAL READING IS 0.308 INCHES. PER REFERENCE 58-767-53A0100, FIGURE 37, STEP (G) (AMES DOCUMENT I47008ORD10 STEP 7.5), THE MINIMUM ALLOWABLE IS 0.324 INCHES (MINIMUM SKIN THICKNESS), FOR GROUP 1. REPAIRED PER ABX-REA-5355-65282-00 AND HAECO REO-G24836.

Part: SKIN PANEL — CORRODED (LT WING) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, MAINTENANCE REPORTED CORROSION DAMAGE ON LH WING UPPER SKIN PANEL NO.L, APPROX. AT WBL105 (112T3101-5), STRINGER U4-U5. DAMAGE WAS REMOVED BY BLENDING AFFECTED AREA PER SRM 51-10-02. PLANE XXXII, INITIAL 0.210" (UT, AVG.), MATERIAL. LOSS 0.038", (18.1%), REMAINING MATERIAL. 0.172" (UT). INITIAL THICKNESS, PER DRAWING 0.209". PLANE XXX, INITIAL 0.196" (UT, AVG.), MATERIAL LOSS 0.033", (16.9%), REMAINING MATERIAL. 0.163" (UT). INITIAL THICKNESS, PER DRAWING 0.192". BLEND OUTS ARE FOUND TO BE OUT OF LIMITS PER SRM 57-20-01, AOL 1, TABLE I OF 0.030 INCHES. RESTORED/REPAIRED AREA IAW ABX-REA-5720-65253-00 AND HAECO REO-G24759 REV: IR. ABX FORM M-287, M-289 AND FAA FORM 337

Part: LONGERON SPLICE — CORRODED (LT WING) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, CORROSION WAS DISCOVERED ON THE LEFT HAND OVERWING LONGERON SPLICE PLATE BETWEEN STA 930 TO STA 947. THE DAMAGE WAS REMOVED BY BLENDING AND FOUND TO BE BEYOND THE PUBLISHED LIMITS OF B767-200 SRM 53-50-05 FIGURE 101. THE AVERAGE MATERIAL LOSS WAS REPORTED AT 0.020-0.040-INCHES.ACCOMPLISHED BLEND REPAIR PER HAECO REO-G24747 REV IR AND ABX REA-5350-65240-00. ABX FORM M-287, M-289 AND FAA FORM 337

Part: DOUBLER — NONE (ZONE 200) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, MAINTENANCE REPORTED A REPAIR DOUBLER WAS FOUND THAT HAVE NO RECORD OF ACCOMPLISHMENT ON THE STA 1582 AFT PRESSURE BULKHEAD, APPROXIMATELY AT TS5 / RS11. THE 8767-200 SRM 53-80-08, REPAIR 7 CANNOT BE PERFORMED, AS THE DAMAGE IS LOCATED AT THE JUNCTION OF TEAR STRAP AND RADIAL STIFFENER. REPAIRED AFT PRESSURE BULKHEAD IAW ABX REA NO ABX-REA-5380-65281-00 AND HAECO REO-G24832. ABX FORMS M-287, M-289.AND FAA FORM 337

Part: BEAR STRAP — GOUGED (ZONE 100) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, GOUGE DAMAGE WAS FOUND ON THE CARGO DOOR CUTOUT, LOWER FORWARD COMER, INNER SURFACE BEARSTRAP AT APPROXIMATELY STA 547. POST BLEND MEASUREMENTS HAVE THE MINIMUM REMAINING MATERIAL THICKNESS AT 0.006-INCH FROM AN INITIAL MEASURED THICKNESS OF 0.180-INCH. NO SRM REPAIR IS AVAILABLE FOR THIS DAMAGE LOCATION AS B767-200 SRM 53-00-01, REPAIR L STATES THAT REPAIR SHOULD NOT BE WITHIN 22 INCHES FROM A DOOR CUTOUT. REPAIRED PER ABX-REA-5335-65181-00 AND HAECO REO-G24736 REV IR.

Part: SKIN PANEL — CORRODED (RT WING) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, CORROSION WAS REMOVED FROM THE RIGHT WING UPPER SKIN, PANEL NO. 1, UPPER SURFACE FROM AROUND THE FUEL PORT CUTOUT LOCATED AT APPROXIMATELY WS 785.2 AND BETWEEN STRINGERS U15-U16. ORIGINAL THICKNESS PER DRAWING 112T3101 SHEET 4 IS 0.431-INCH WHICH STEPS DOWN TO 0.251-INCH AT THE SKIN CUTOUT. THE MINIMUM REMAINING THICKNESS WITH THE BLEND AREA WAS FOUND TO BE 0.150-INCH. THERE ARE NO APPLICABLE REPAIRS FOR DAMAGE IN THIS AREA OF THE WING SKIN. POST RE-WORK OF THE BLENDED AREA TO PROVIDE A FLUSH AND PARALLEL SURFACE RESULTED IN A FINAL MINIMUM REMAINING THICKNESS OF 0.083-INCH. ACCOMPLISHED DOUBLER REPAIR PER HAECO REO-G24779 REV IR AND ABX-REA-5725-65248-00. M-287 & M-289 ATTACHED AND FAA FORM 337

Part: SKIN PANEL — CORRODED (LT WING) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, MAINTENANCE REPORTED CORROSION DAMAGE ON LH WING UPPER SKIN PANEL NO.L, APPROX. AT WBL105 (112T3101-5). DAMAGE WAS REMOVED BY BLENDING AFFECTED AREA PER SRM 51-10-02 WITH MEASURED MATERIAL REMAINING OF 0.159 INCHES FROM INITIAL THICKNESS OF 0.196-INCH (UT MEASURED) WITH MATERIAL LOSS OF 0.037-INCH, FOUND TO BE OUT OF LIMITS PER SRM 57-20-01, AOL 1, TABLE I OF 0.030 INCHES (BASED ON 0.196-INCH UT READING). THE THICKNESS PER DRAWING IS 0.192 INCHES . RESTORED/REPAIRED AREA IAW ABX-REA-5720-65239-00 AND HAECO REO-G24749 REV: IR. ABX FORM M-287, M-289, AND FAA FORM 337

Part: SKIN PANEL — CORRODED (LT WING) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, CORROSION WAS REMOVED FROM THE LEFT WING UPPER SKIN, PANEL NO. 1, UPPER SURFACE FROM AROUND THE FUEL PORT CUTOUT LOCATED AT APPROXIMATELY WS 785.2 AND BETWEEN STRINGERS U15-U16. ORIGINAL THICKNESS PER DRAWING 112T3101 SHEET 4 IS 0.431-INCH WHICH STEPS DOWN TO 0.251-INCH AT THE SKIN CUTOUT. THE MINIMUM REMAINING THICKNESS WITH THE BLEND AREA WAS FOUND TO BE 0.124-INCH. THERE ARE NO APPLICABLE REPAIRS FOR DAMAGE IN THIS AREA OF THE WING SKIN. POST RE-WORK OF THE BLENDED AREA TO PROVIDE A FLUSH AND PARALLEL SURFACE RESULTED IN A FINAL MINIMUM REMAINING THICKNESS OF 0.098-INCH. ACCOMPLISHED DOUBLER REPAIR PER HAECO REO-G24774 REV IR AND ABX-REA-5725-65247-00. M287 & M289 ATTACHED AND FAA FORM 337

Part: PRESSURE BLKHD — MISREPAIRED (ZONE 200) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT CPZ, MAINTENANCE REPORTED UNDOCUMENTED REPAIR AT AFT PRESSURE BULKHEAD RS 19 BETWEEN TSS AND TS6. THE EXISTING REPAIR WAS CAREFULLY REMOVED AND REVEALED A 1.20-INCH BY 1.0-INCH TRIM CUTOUT. THE B767-200 SRM 53-80-08, REPAIR 2 IS NOT APPLICABLE ON THIS AREA DUE TO PROXIMITY TO RADIAL STIFFENER (RS). NO REPAIR RECORD WAS FOUND. ACCOMPLISHED DOUBLER REPAIR PER HAECO REO-G24815 REV IR AND ABX-REA-5380-65278-00.

Part: PLATE — CORRODED (RT WING) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, AND DURING ACCOMPLISHMENT OF SB 767-53A0 I 00 REV 02, MAINTENANCE DISCOVERED CORROSION ON THE RIGHT-HAND BEARING PLATE PIN I I ITI008-1 AS SHOWN IN FIGURE I. THE CORROSION WAS MECHANICALLY REMOVED BY BLENDING PER 8767-200 SRM 51- I 0-02. THE MINIMUM REMAINING THICKNESS WAS FOUND TO BE 0.150-INCH. THERE ARE NO PUBLISHED LIMITS OR ??EPAIR FOR THIS PART. REPAIRED RH MLG WHEEL WELL CENTER WING REAR SPAR STA.955,RBL 80 IAW ABX-REA-5712-65178-00 REO-G24709 REV IR.

Part: RIB — GOUGED (RT WING) · airframe 93,302 hrs · 24,080 cycles

DURING C-24 MAINTENANCE CHECK AT HAECO AMERICAS, GOUGE DAMAGE WAS FOUND ON THE RH WING L/E RIB AT OFSS 427. THE POST-BLEND MEASUREMENT HAS MATERIAL REMAINING OF 0.025" AND 0.029" FROM INITIAL THICKNESS OF 0.060". THAT'S LESS THAN 50% REMAINING. THE ALLOWABLE PER B767-200 SRM 57-41-09, ADL IS 10%. THERE ARE NO AVAILABLE REPAIRS FOR THE DAMAGE. ACCOMPLISHED DOUBLER REPAIR PER HAECO REO-G24728 REV IR AND ABX-REA-5740-65180-00. ABX FORM M-289 AND FAA FORM 337

Part: PITOT TUBE — FAULTED (ZONE 200) · airframe 93,076 hrs · 23,975 cycles

F/O PITOT EICAS MESSAGE ON TAXI. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE REMOVED AND REPLACED FO'S PITOT PROBE IAW B767 AMM 34-11-01. PERFORMED HIGH RANGE PITOT/STATIC LEAK CHECK IAW AMM 34-11-00. A/S 0.2KT/MIN. STATIC 5KTS/MIN. LOW RANGE STATIC 7FT/MIN. OPS CHECK OF PITOT HEAT GOOD. A/C REMAINS RVSM. AIRCRAFT RETURNED TO SERVICE.

Part: MODULE — FAULTED (ZONE 100) · airframe 92,860 hrs · 23,891 cycles

AIRCRAFT SPOILER LIGHT ON WITH HYDS, NO EICAS MESSAGE NOTED. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE REMOVED AND REPLACE R1 SPOILER CONTROL MODULE (M533),SPOILER INDICATION SYSTEM AND OPS CHECKED GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: ACTUATOR — LEAKING (ZONE 300) · airframe 92,791 hrs · 23,867 cycles

RUDDER RATIO EICAS MESSAGE AFTER ENGINE START. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE REMOVED AND REPLACED RUDDER RATIO ACTUATOR ASSY. IAW B767 AMM CHAPT. 27-21-15. RAN HYD SYSTEMS, NO LEAKS NOTED. NO EICAS MESSAGE APPEARS. AIRCRAFT RETURNED TO SERVICE.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 92,546 hrs · 23,776 cycles

SPOILERS EICAS MESSAGE AND DISCRETE LIGHT ON WHILE DOING FLIGHT CONTROL CHECK. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANNCE TROUBLESHOT. FOUND "HYD PRESS SW FAULT BALL DISPLAYED ON STAB TRIM AILERON LOCK ASY. IN MODULE AND 1 MODULE FAULT BALL ON SPOILER CONTROL MODULE RESET, MESSAGE CLEARED. OPS CHECK SPOILER NO FAULTS DIPSLAYED REF B767 AMM 31-41-00 27-41-00. AIRCRAFT RETURNED TO SERVICE

Part: CIRCUIT BREAKER — TRIPPED (AILERON SYS) · airframe 92,216 hrs · 23,634 cycles

RT OUTBOARD AILERON NOT MOVING DURING CONTROLS CHECK. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE RESET RH AILERON LOCKOUT CB IAW AMM 20-60-01 VERIFIED MOVEMENT AND INDICATION OF AILERON IAW AMM 27-18-10 AND AMM 27-11-00 VERIFIED MEL MEL LOCK OUT PROCEDURES IAW MEL 27-11-2. AIRCRAFT RETURNED TO SERVICE.

Part: AILERON SYS — FAULTED · airframe 92,203 hrs · 23,631 cycles

AILERON LOCK OUT EICAS MSG DURING TAXI OUT. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE DEFERRED AILERON LOCKOUT EICAS MESSAGE PER MEL 27-11-2 MBCB 1-22-23 MAINTENANCE PROCEDURES C/W PLACARD INSTALLED. AIRCRAFT RETURNED TO SERVICE.

Part: MODULE — TRIPPED (AILERON LOCKOUT) · airframe 92,106 hrs · 23,592 cycles

AILERON LOCKOUT EICAS MESSAGE AND ANNUNCIATOR ON OVERHEAD PANEL. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE RESET AILERON LOCKOUT MODULE IAW FIM 27-11-FT804. AIRCRAFT RETURNRED TO SERVICE.

Part: NONE — NONE (NONE) · airframe 91,539 hrs · 23,376 cycles

AIRCRAFT DEPARTED GATE AND MAINTENANCE DISCOVERED THAT THE FAK HAD BEEN PLACED ON AIRCRAFT WITHOUT DOCUMENTATION. MAINTENANCE CONTACTED FLIGHT CREW AND HAD THEM RETURN TO GATE. MAINTENANCE GROUNDED AIRCRAFT UNTIL LOCATION AND WEIGHT OF FAK WAS VERIFIED. AIRCRAFT WAS RETURNED TO SERVICE.

Part: NONE — NONE · airframe 91,176 hrs · 23,227 cycles

APU FAILED DURING PUSHBACK, RETURNED TO GATE AND WAS GROUNDED BY MAINTENANCE. MAINTENANCE PERFORMED APU START IAW B767 AMM 49-11-01 OPS CHECK NORMAL AIRCRAFT REMAINS ETOPS 180. AIRCRAFT RETURNED TO SERVICE.

Part: NONE — NONE · airframe 91,021 hrs · 23,174 cycles

PERFORMING BEFORE T/O CHECKLIST FLT CONTROL CHECK, LEFT INBOARD AILERON WAS SLOW TO FOLLOW OUTBOARD. SPOILERS EICAS + DISCREET LIGHT, PERFORMED QRH, RETURNED TO BLOCKS. AIRCRAFT GROUNDED BY MAINTENANCE. MAINTENANCE PERFORMED RESET ON SCM PER 27-09 FT 808. RESET PCA RH FAULT BALL. PERFORMED OPS CHECK OPS CHECK GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: NONE — NONE · airframe 90,707 hrs · 23,035 cycles

CREW REPORTED LH T/R AMBER LIGHT AND TR NOT STOWED. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE FOUND W146-063-20 WIRE BORKEN AT TB 458. RE-TERMINATED NAMED WIRE IAW SWPM 20-10-11 AND WDM 78-34-11. LEFT T/R OPS CHECK GOOD IAW B767 AMM 78-31-00. AIRCRAFT RETURNED TO SERVICE.

Part: NONE — NONE · airframe 90,325 hrs · 22,869 cycles

SPOILERS DISCRETE AND EICAS MESSAGE CAME ON DURING PUSHBACK. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE PERFORMED OPERATIONAL TEST IAW B767 AMM 27-61-00. OPS CHECK GOOD.AIRCRAFT RETURNED TO SERVICE

Part: STRINGER — CRACKED (ZONE 200) · airframe 90,256 hrs · 22,843 cycles

DURING C CHECK IT WAS FOUND THAT MAIN CABIN, UPPER ANGLE OF STRINGER 9L CRACKED AFT OF FRAME STA676. REMOVED STR 9L SECTION AND REPAIR PARTS AS REQ IAW B767-200 SRM 53-00-03 REPAIR 1 FIG 201, VERIFIED MAT ID FOR STR SECTION BAC1498.205, RC0699402 IAW B767-200 SRM 53-00-03, REPAIR 1, LOCATED AND DRILLED NEW STR SECTION FROM STA 680 TO 708 IAW B767-200 SRM 53-00-03, REPAIR 1 , TREATED AND PRIMED NEW STR SECTION IAW B767-200 SRM 51-21-01, INSTALLED STR SECTION AND REPAIR PARTS AS REQ IAW B767-200 SRM 53-00-03 REPAIR 1 PER E502821

Part: GEARBOX — OUT OF ADJUST (RT AILERON) · airframe 90,286 hrs · 22,857 cycles

RIGHT AILERON DID NOT DROOP WITH FLAPS SET TO 15. AICRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE FOUND R/H DROOP ANGLE GEAR BOX OUT OF ADJUSTMENT. ADJUSTED ITEM PER AMM 27-51-40, THEN CONDUCTED IN BOARD AILERON DROOP TEST PER AMM 27-11-00. DROOP SYSTEM TEST OK. NO FURTHER ACTION REQUIRED. AIRCRAFT RELEASED BACK IN SERVICE.

Part: PIN — WORN (MAIN CARGO DOOR) · airframe 90,256 hrs · 22,843 cycles

WHILE IN C-CHECK IT WAS DISCOVERED THAT MAIN CARGO DOOR LATCH CAM PINS WERE WORN BEYOND LIMITS. PINS #2,7,11 AND 12 WERE REPLACED IAW B767-200 MMS 52-32-11

Part: STRINGER — CRACKED (ZONE 200) · airframe 90,256 hrs · 22,843 cycles

DURING C CHECK AT AMES TAMPAIT WAS FOUND THAT MAIN CABIN, UPPER ANGLE OF STRINGER 9L CRACKED AFT OF FRAME STA676. REMOVED STR 9L SECTION AND REPAIR PARTS AS REQ IAW B767-200 SRM 53-00-03 REPAIR 1 FIG 201, VERIFIED MAT ID FOR STR SECTION BAC1498.205, RC0699402 IAW B767-200 SRM 53-00-03, REPAIR 1, LOCATED AND DRILLED NEW STR SECTION FROM STA 680 TO 708 IAW B767-200 SRM 53-00-03, REPAIR 1 , TREATED AND PRIMED NEW STR SECTION IAW B767-200 SRM 51-21-01, INSTALLED STR SECTION AND REPAIR PARTS AS REQ IAW B767-200 SRM 53-00-03 REPAIR 1 PER E502821

Part: WARNING MESSAGE — FALSE ACTIVATION (FUEL VALVE) · airframe 90,163 hrs · 22,804 cycles

RT. ENG FUEL VALVE EICAS MSG APPEARS DURING ENGINE START. AICRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE PERFORMED OPS CHECK OF FUEL CONDITION MOTOR IAW B767 AMM 76-11-00 OPS CHECK NORMAL A/C REMAINS ETOPS 180. AICRAFT RETURNED TO SERVICE.

Part: LOCK — OUT OF ADJUST (CARGO DOOR) · airframe 89,957 hrs · 22,727 cycles

MAIN CARGO WARNING DURING PUSHBACK. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. ADJUSTED MCD LOCK BAR IAW B767 AMM 52-32-00, OPS CHECK GOOD. DOOR VERIFIED LOCKED RII FORM ACCOMPLISHED. AIRCRAFT RELEASED FOR FLIGHT.

Part: PNEUMATIC SYSTEM — BINDING (LT ENGINE) · airframe 88,603 hrs · 22,206 cycles

LT ENG BLEED VALVE OFF LIGHT WITH ASSOCIATED LEFT ENGINE BLEED AND LEFT PACK OFF LIGHT. AIRCRAFT BACK TO GATE. AIRCRAFT GROUNDED. VERIFIED PRSOV WON'T OPEN, REMOVED AND REPLACED LT ENG PRSOV. OPERATIONS CHECKED GOOD, IAW B767 MM 36-11-18. REMAIN ETOPS 180.

Part: WARNING MESSAGE — ILLUMINATED (COCKPIT WINDOW) · airframe 88,304 hrs · 22,089 cycles

L FWD WINDOW EICAS MESSAGE ON CLIMB OUT.CONTINUED TO DESTINATION. AIRCRAFT WAS GROUNDED

Part: WARNING MESSAGE — ILLUMINATED (WINDOW HEAT) · airframe 88,304 hrs · 22,089 cycles

L FWD WINDOW EICAS ON CLIMB OUT. AIRCRAFT WAS GROUNDED.

Part: SPEAKER — ABNORMAL (COCKPIT) · airframe 88,164 hrs · 22,032 cycles

LOUD SQUEAL COMING FROM CAPTAIN`S. SPEAKER, UNABLE TO CONTROL. AIRCRAFT WAS GROUNDED.

Part: ESCAPE REEL — DISLODGED (CABIN) · airframe 87,080 hrs · 21,587 cycles

TWO EMERGENCY DESCENT DEVICES WERE DISLODGED FROM THEIR STORAGE CONTAINER LOCATED IN THE SUPERNUMERARY COMPARTMENT CEILING. THE AIRPLANE WAS REMOVED FROM SERVICE (GROUNDED) AND THE TWO DESCENT DEVICES WERE REPLACED WITH SERVICEABLE DESCENT DEVICES. THE CAUSE FOR THE DESCENT DEVICES BECOMING DISLODGED IS UNKNOWN.

Part: ESCAPE REEL — DETACHED (CABIN) · airframe 87,014 hrs · 21,562 cycles

ONE DESCENT DEVICE WAS FOUND DISLODGED FROM ITS STORAGE CONTAINER LOCATED IN THE SUPERNUMERARY COMPARTMENT CEILING. THE AIRPLANE WAS REMOVED FROM SERVICE (GROUNDED) AND THE DESCENT DEVICE WAS REPLACED WITH SERVICEABLE DESCENT DEVICE. THE CAUSE FOR THE DESCENT DEVICE BECOMING DISLODGED IS UNKNOWN.

Part: STRINGER — CRACKED (BS 676) · airframe 87,011 hrs · 21,559 cycles

CRACK IN OUTBOARD SURFACE OF STRINGER 23L AT FUSELAGE STATION 676. THE STRINGER WAS REPAIRED. THE AIRPLANE WAS GROUNDED.

Part: STRUCTURE — GOUGED (RT PLYON) · airframe 87,011 hrs · 21,559 cycles

GOUGE IN THE RIGHT PYLON AFT FAIRING CHORD BELOW THE LATCH PIN. THE CHORD WAS REPAIRED. THE AIRPLANE WAS GROUNDED.

Part: STRINGER — CRACKED (BS 676) · airframe 87,011 hrs · 21,559 cycles

CRACK IN OUTBOARD SURFACE OF STRINGER 25L AT FUSELAGE STATION 676+6. THE STRINGER WAS REPAIRED. THE AIRPLANE WAS GROUNDED.

Part: SKIN — CRACKED (RT NACELLE) · airframe 87,011 hrs · 21,559 cycles

CRACK IN RIGHT ENGINE OUTBOARD CORE COWL LOWER LONGERON AT SECOND FROM AFT LATCH. THE CORE COWL WAS REPLACED. THE AIRPLANE WAS GROUNDED.

Part: STRINGER SPLICE — CORRODED (BS 786) · airframe 87,011 hrs · 21,559 cycles

CORROSION ON THE SPLICE FITTING AT FUSELAGE STATION 786, STRINGER 39L. THE SPLICE FITTING WAS REPLACED. THE AIRPLANE WAS GROUNDED.

Part: ATTACH ANGLE — CORRODED (BS 786) · airframe 87,011 hrs · 21,559 cycles

CORROSION ON THE ATTACH ANGLE AT FUSELAGE STATION 786, RIGHT BUTT LINE 4, KEEL BEAM AREA. THE ATTACH ANGLE WAS REPAIRED. THE AIRPLANE WAS GROUNDED.

Part: STRINGER — CRACKED (BS 676) · airframe 87,011 hrs · 21,559 cycles

CRACK IN OUTBOARD SURFACE OF STRINGER 24L AT FUSELAGE STATION 676+7.75. THE STRINGER WAS REPAIRED. THE AIRPLANE WAS GROUNDED.

Part: KEELBEAM — CORRODED (BS 820) · corrosion level 2 · airframe 87,011 hrs · 21,559 cycles

CORROSION ON THE KEEL BEAM FLANGE UPPER SURFACE AT FUSELAGE STATION 820. THE KEEL BEAM WAS REPAIRED. THE AIRPLANE WAS GROUNDED.

Part: INTERCOSTAL — DAMAGED (BS 1021) · airframe 84,642 hrs · 20,645 cycles

EVIDENCE OF BURN DAMAGE ON AN INTERCOSTAL ASSEMBLY AND TWO OF THE THREE APU GENERATOR FEEDER WIRES FROM CONTACT WITH THE INTERCOSTAL AT BS 1021, RBL 35.

Part: KEELBEAM — CORRODED (BS 1007-1017) · corrosion level 2 · airframe 84,093 hrs · 20,373 cycles

CORROSION ON UPPER SURFACE OF LOWER INBOARD HORIZONTAL FLANGE OF THE LEFT KEEL BEAM AT BS 1007 - 1014. THE KEEL BEAM WAS REPAIRED. AIRPLANE WAS GROUNDED.

Part: STRUCTURE — CORRODED (LT WING) · corrosion level 2 · airframe 84,093 hrs · 20,373 cycles

CORROSION AROUND NUTPLATES AND STIFFENERS ON THE CHORD AT THE LEFT WING REAR SPAR TO TRAILING EDGE UPPER PANEL. THE CHORD WAS REPLACED. AIRPLANE WAS GROUNDED.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 84,093 hrs · 20,373 cycles

CRACK IN AFT LOWER SIDE OF STRINGER 13L AT SPLICE. THE STRINGER WAS REPAIRED. AIRPLANE WAS GROUNDED.

Part: FRAME — CRACKED (FUSELAGE) · airframe 84,093 hrs · 20,373 cycles

DURING ULTRASONIC INSPECTION REQUIRED BY AD 2012-22-17, A CRACK WAS FOUND IN THE INNER CHORD OF THE RIGHT SIDE FRAME BELOW FLOOR LEVEL OF THE UPPER CARGO COMPARTMENT. THE CHORD WAS REPAIRED. AIRPLANE WAS GROUNDED.

Part: FITTING — CRACKED (FUSELAGE) · airframe 84,093 hrs · 20,373 cycles

CRACK IN PRESSURE DECK FITTING (PYLON FITTING) AT FUSELAGE STATION 1062. THE FITTING WAS REPLACED. AIRPLANE WAS GROUNDED.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 84,093 hrs · 20,373 cycles

CORROSION ON THE ATTACH ANGLE FOR PANEL 196BR IN THE RIGHT WHEEL WELL. THE ANGLE WAS REPLACED. AIRPLANE WAS GROUNDED.

Part: CARABINER — MISSING (FORWARD CABIN) · airframe 84,086 hrs · 20,369 cycles

THREE EMERGENCY DESCENT SAFETY HARNESS CARABINERS WERE MISSING FROM THEIR STOWAGE POUCH. WHILE THE AIRPLANE WAS REMOVED FROM SERVICE (GROUNDED), THREE NEW SAFETY HARNESS CARABINERS WERE INSTALLED INTO THE STOWAGE POUCH. THE CAUSE OF THE MISSING CARABINERS IS UNKNOWN.

Part: ESCAPE ROPE — DEFECTIVE (COCKPIT) · airframe 83,238 hrs · 19,962 cycles

TWO DESCENT DEVICES WERE FOUND NOT PROPERLY STOWED. THE AIRPLANE WAS REMOVED FROM SERVICE. THE DESCENT DEVICES WERE REPLACED WITH SERVICEABLE DESCENT DEVICES. THE CAUSE FOR THE DESCENT DEVICES BECOMING UNSTOWED IS UNKNOWN.

Part: ESCAPE ROPE — UNWANTED DEPLOY · airframe 82,558 hrs · 19,657 cycles

AFTER NORMAL LANDING, THE CREW FOUND TWO INERTIAL REEL HANDLES DANGLING TO THE FLOOR OF THE SUPERNUMERARY COMPARTMENT. THE AIRPLANE WAS REMOVED FROM SERVICE (GROUNDED) UNTIL ONE OF THE DESCENT DEVICES WAS REWOUND, RESEALED, AND RESTOWED. THE OTHER INERTIAL REEL WAS DEFERRED UNTIL IT CAN BE REPLACED WHILE THE AIRPLANE IS GROUNDED.

Part: SUPPORT — CORRODED (TE FLAP) · airframe 82,480 hrs · 19,633 cycles

NUMBER ONE FLAP SUPPORT GOUGED AND SIGNS OF CORROSION. REPAIRED IAW REA B657-62231-MR AND JC 57500006-001. AIRCRAFT WAS GROUNDED.

Part: ESCAPE REEL — UNWANTED DEPLOY (CABIN) · airframe 82,411 hrs · 19,611 cycles

TWO DESCENT DEVICES WERE FOUND NOT PROPERLY STOWED. THE AIRPLANE WAS REMOVED FROM SERVICE (GROUNDED) UNTIL THE DESCENT DEVICES WERE REPLACED WITH SERVICEABLE DESCENT DEVICES. THE CAUSE FOR THE DESCENT DEVICE BECOMING UNSTOWED IS UNKNOWN.

Part: STRUCTURE — CORRODED (LT WING) · airframe 80,952 hrs · 19,073 cycles

LEFT WING ACCESS PANEL 552AB HAS CORROSION ON AFT INBD FLANGE UPPER SIDE. GAINED ACCESS & REMOVED LOWER TE CHORD AT WS 157 - 228. INSTALLED NEW CHORD PN 654T0391-35 & REINSTALLED PANELS IAW DWG 113T1400 & SRM CH51-40-02-PAR 7. CORRODED, PART NAME CHORD, PN 654T0391-35, SN NSN, STRINGER & WS LOCATION FROM 157 - 282. ACFT WAS GROUNDED.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 80,952 hrs · 19,073 cycles

CORROSION WHERE STRINGER 35L MEETS FUSELAGE SKIN AT FS 412, FOUND CORROSION ON STRINGER 35L, STATION 412, OUT OF LIMITS. FABRICATED STRINGER IAW SRM 53-00-03 FIG 201 REPAIR 2. CORRODED, PN 144T3001, PART NAME STRINGER, SN NSN, FS & BS LOCATION 412, STRINGER & WS LOCATION 35L. ACFT WAS GROUNDED.

Part: SKIN — CRACKED (R1 DOOR) · airframe 80,952 hrs · 19,073 cycles

FORWARD LOWER CORNER OF R1 DOOR HAS AN EXTERNAL HFEC CRACK INDICATION, APPROX 3/8" LONG. INSTALLED REPAIR TO FWD LOWER CORNER OF R1 DOOR CUT OUT IAW SRM 53-10-01. PN 141T3330, PART NAME SKIN, CRACKED 3/8", EXACT FS LOCATION ON ACFT 287. ACFT WAS GROUNDED.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 80,952 hrs · 19,073 cycles

AFT LOWER CARGO FLOORBEAM, UPPER CHORD STATION 1153 WAS CORRODED BEYOND LIMITS & WAS REPLACED IAW DWG 146T1204. PN 146T1204-7, SN NSN, PART NAME UPPER CHORD, CORRODED LEVEL 2, EXACT FS & BS LOCATION ON ACFT STATION 1153, EXACT STRINGER & WS LOCATION ON ACFT LBL 48 TO RBL 48. ACFT WAS GROUNDED.

Part: ATTACH FITTING — CORRODED (RT WING) · corrosion level 2 · airframe 80,952 hrs · 19,073 cycles

REAR SPAR TO WING TE PANEL ATTACH BEAM, LOWER CHORD CORRODED ABOVE WIRE BUNDLE RACE WAY AT WS 250, INBD & OTBD SIDES AS SEEN IN RT WW. FOUND ATTACH BEAM CORRODED BEYOND LIMITS. REPAIRED ATTACH BEAM IAW SRM 51-70-12 FIG 1 DETAIL III. CORRODED L2, PN 113T1621-58, SN NSN, PART NAME ATTACH BEAM, FS & BS LOCATION ON ACFT WS 250. ACFT WAS GNDED.

Part: ATTACH FITTING — CORRODED (RT WING) · corrosion level 2 · airframe 80,952 hrs · 19,073 cycles

REAR SPAR TO TE, UPPER PANEL ATTACH BEAM, UPPER CHORD CORRODED AROUND NUTPLATES AT WS 290 AS SEEN IN RT WW. FOUND ATTACH BEAM TO BE CORRODED OUT OF LIMITS IAW SRM 51-10-00. R & R ATTACH BEAM IAW SRM 51-40-2 & 51-40-5. CORRODED LEVEL 2, PN 113T1622-125, PART NAME CHORD, SN NSN, STRINGER & WS LOCATION WS 290. ACFT WAS GROUNDED.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 80,952 hrs · 19,073 cycles

AFT LOWER CARGO ON UNDER SIDE, CORRODED STATION 1219, LBL 24 - 34. R & R SUPPORT ANGLE 451T2409-2 IAW DWG 451T2402. CORRODED LEVEL 2, PN 451T2409-2, PART NAME SUPPORT ANGLE, SN N/A, FS & BS LOCATION STATION 1219, STRINGER & WS LOCATION LBL 24 TO LBL 34. ACFT WAS GROUNDED.

Part: SKIN — CRACKED (APU DOOR) · airframe 80,952 hrs · 19,073 cycles

APU DOOR 316AL EXTERIOR SKIN, LOWER EDGE BENT IN SEVERAL PLACES. FWD CORNER HAD 2 CRACKS .2 INCHES DEEP, OUT OF LIMITS IAW SRM 52-40-01 FIG 101 DETAIL III. ROUTED OUT 2 CRACKS AT EDGE OF PANEL WITHIN LIMITS IAW SRM 52-40-01 FIG 101 DETAIL III. STOP DRILLED CRACKS, FABRICATED REPAIR & INSTALLED REPAIR IAW SRM 52-40-01 REPAIR 5 STEPS 1 - 12. CRACKED .2, PN 148T6551, PART NAME, SN NSN, FS & BS LOCATION 1832 STATION, STRINGER & WS LOCATION FWD LOWER CORNER. ACFT WAS GNDED.

Part: STRUCTURE — DAMAGED (ZONE 500) · airframe 79,510 hrs · 18,404 cycles

LOWER SURFACE OF LT WING FUEL TANK HAS HOLE DAMAGED IN THE CENTER AT WING STA 128. REPAIRED DAMAGE IAW ATI 57-767-4910 & DWG 57-13075-2, HOLE DIA .3750". ACFT WAS GROUNDED.

Part: MOUNT — CORRODED (RT ENGINE) · airframe 79,510 hrs · 18,404 cycles

RT ENGINE AFT MOUNT IS BLEEDING RUST FROM THE BEARING AND THE POCKETS IN MULTIPLE AREAS. R & R AFT ENGINE MOUNT IAW AMM 71-21-01, ACFT WAS GROUNDED.

Part: STIFFENER — CRACKED (ZONE 400) · airframe 79,510 hrs · 18,404 cycles

LEFT PYLON OTBD HORIZONTAL STIFFENER IS CRACKED. R & R OTBD STIFFENER IAW SRM 51-40-02. ACFT WAS GROUNDED.

Part: VERTICAL SUPPORT — CRACKED (ZONE 100) · airframe 79,510 hrs · 18,404 cycles

NOSE WHEEL WELL AFT BULKHEAD AT STA. 287, LT SIDE ANGLE 10" FROM TOP CRACKED. REPAIRED LEFT AFT VERTICAL NOSE WELL WHELL CORD IAW SRM 51-70-12, ACFT WAS GROUNDED.

Part: VALVE — DAMAGED (LT WING) · airframe 78,717 hrs · 18,090 cycles

ON POST FLIGHT INSPECTION, FOUND HOLE IN LOWER LT WING SURFACE (LT CENTER FUEL TANK). UPON INSP, INSIDE LT CENTER FUEL TANK, DAMAGE WAS FOUND TO THE FUEL TANK VENT VALVE AND ON THE L5 STRINGER. TEMPORARY REPAIR ACCOMPLISHED TO LOWER LT WING SURFACE IAW DWG 57-13075-1 WITH FAA FORM 8110-3 APPROVAL DATED FEB 10, 2013. REINSPECT EVERY 25 CYCLES. CURRENT TAC IS 18090. R & R LT CENTER TANK VENT VALVE IAW AMM 28-13-01 AND BLENDED DAMAGE ON L5 STRINGER IAW SRM 57-00-03. BLENDED .1250" DEEP AND .3750" LONG TO SMOOTH CONTOUR. TOUCHED UP PRIMER IAW SRM 51-20-01. PERMENANT REPAIR TO FOLLOW.

Part: ESCAPE REEL — DAMAGED (EMERGENCY EQUIP) · airframe 78,493 hrs · 18,011 cycles

DURING DAILY CHECK, EMERGENCY DESCENT DEVICE CABLE FOUND EXTENDED. R & R EMERGENCY DESCENT DEVICE IAW AMM 25-61-03. DEVICE INSPECTION DUE DATE IS 09/15/2016.

Part: FUEL CELL — LEAKING (FUSELAGE) · airframe 78,133 hrs · 17,857 cycles

DURING TAKEOFF ROLL, WITH AIR CONDITIONING PACKS TURNED OFF, THERE WAS A STRONG JET FUEL ODOR IN FLIGHT DECK. ODOR DISSIPATED WHEN PACKS WERE SWITCHED ON. FOUND CENTER FUEL TANK RIB "O" CENTER MEMBER AND LT MAIN TANK RIB 4 AFT SKIN JOINT LEAKING. ALL WORK PERFORMED IAW AMM 28-11-00-796-111 AND IAW AMM 28-11-00.

Part: SKIN — DAMAGED (APU DOORS) · airframe 78,053 hrs · 17,827 cycles

ON POST FLIGHT WALK AROUND FOUND EVIDENCE OF A TAIL STRIKE. SKIN DAMAGE WAS FOUND TO THE APU DOORS AND AFT FROM BS 1898.4 TO 1923. FRAME DAMAGE WAS FOUND FROM BS 1898.45 TO 1923.5.

Part: SEAL — BROKEN (DESCENT DEVICE) · airframe 77,791 hrs · 17,725 cycles

DURING A-CHECK FOUND POSITION NR 1 EMERGENCY DESCENT DEVICE SEAL BROKEN. R & R EMERGENCY DESCENT DEVICE IAW AMM 25-61-00.

Part: PRESSURE BLKHD — DENTED (ZONE 200) · airframe 77,627 hrs · 17,677 cycles

DURING C18 CHECK INSPECTION, DAMAGE WAS OBSERVED AT THE AFT PRESSURE BULKHEAD, BS 1582 ON THE DOME WEB BETWEEN RS 19 AND RS 20. CREASE SIGNS ARE SEEN AT THE CENTER OF THE AFFECTED AREA. CUT OUT THE DAMAGED WEB PORTION AT BS 1582 BETWEEN RS 19 AND RS 20. PERFORMED HFEC INSP OF THE WEB AT THE CUTOUT AND 3 INCHES AROUND TO INSURE A CRACK FREE CONDITION IAW NDT PART 6. TOUCHED UP THE EXPOSED EDGE OF WEB CUTOUT AND ANY BARE AREA OF THE SURROUNDING STRUCTURE WITH CHEMICAL CONVERSION COATING IAW SRM 51-20-01 AND 1 COAT OF EPOXY PRIMER IAW SOPM 20-41-02. INSTALLED THE REPAIR PARTS IAW FIG 3 OF IAI REPAIR EA MF00852R0007, SRM 53-80-08, FIG 201 REPAIR NR 2 AND MESSAGE IAI-TIN-12-0001-05C/-06B.

Part: STRINGER — CRACKED (ZONE 800) · airframe 77,627 hrs · 17,677 cycles

DURING C18 CHECK INSPECTION, A CRACK WAS OBSERVED AT STRINGER S8L END, BS 676 POINTING AFT. THE DAMAGE IS LOCATED AT THE STRINGER WEB EXTENDING FOR ABOUT 2 INCHES. THE AFFECTED STRINGER SPLICES TO THE MAIN DECK CARGO DOOR SURROUND STRUCTURE. TRIMMED OUT DAMAGED PORTION OF STRINGER BETWEEN BS 698 AND BS 720. PERFORMED HFEC INSPECTION OF TRIM OUT AND 3 INCHES AROUND IT TO INSURE A CRACK FREE CONDITION IAW NDT PART 6. TOUCHED UP EXPOSED EDGES OF STRINGER TRIM OUT AND ANY BARE AREA OF THE SURROUNDING STRUCTURE WITH CHEMICAL COATING IAW SRM 51-20-01. INSTALLED REPAIR PARTS AS SHOWN IN FIG 3 OF IAI REPAIR EA MF00852R0001. THIS IS A CATEGORY B REPAIR IAW SRM 51-00-06.

Part: STRINGER — CRACKED (ZONE 200) · airframe 77,627 hrs · 17,677 cycles

DURING C18 CHECK INSPECTION, A CRACK WAS OBSERVED AT STRINGER S18L END, BS 676 POINTING AFT. THE DAMAGE IS LOCATED AT THE STRINGER WEB EXTENDING ABOUT 1 INCH. THE AFFECTED STRINGER SPLICES TO THE MAIN DECK CARGO DOOR SURROUND STRUCTURE. TRIMMED OUT THE DAMAGED PORTION OF THE AFFECTED STRINGER BETWEEN BS 698 AND 720. PERFORMED HFEC INSP OF TRIM OUT AND 3 INCHES AROUND IT TO INSURE A CRACK FREE CONDITION PER B767 NDT PART 6. TOUCHED UP EXPOSED EDGE OF STRINGER TRIM OUT AND ANY BARE AREA OF THE SURROUNDING STRUCTURE WITH CHEMICAL CONVERSION COATING IAW SRM 51-20-01. INSTALLED REPAIR PARTS AS SHOWN IN FIG 3 OF IAI REPAIR EA MF00852R0003. THIS IS A CATEGORY B REPAIR IAW SRM 51-00-06.

Part: STRINGER — CRACKED (ZONE 200) · airframe 77,627 hrs · 17,677 cycles

DURING C18 CHECK INSPECTION, A CRACK WAS OBSERVED AT STRINGER S24L END, BS 676 POINTING AFT. THE DAMAGE IS LOCATED AT THE STRINGER WEB EXTENDING ABOUT 2 INCHES. THE AFFECTED STRINGER SPLICES TO THE MAIN DECK CARGO DOOR SURROUND STRUCTURE. TRIMMED OUT THE DAMAGED PORTION OF THE AFFECTED STRINGER BETWEEN BS 698 AND 720. PERFORMED HFEC INSPECTION OF TRIM OUT AND 3 INCHES AROUND IT TO INSURE A CRACK FREE CONDITION IAW NDT PART 6. TOUCHED UP EXPOSED EDGE OF STRINGER TRIM OUT AND ANY BARE AREA OF THE SURROUNDING STRUCTURE WITH CHEMICAL CONVERSION COATING IAW SRM 51-20-01. INSTALLED REPAIR PARTS AS SHOWN IN FIGURE 3 OF IAI REPAIR EA MF00852R0005. THIS IS A CATEGORY A REPAIR IAW SRM 51-00-06.

Part: STRINGER — CRACKED (ZONE 800) · airframe 77,627 hrs · 17,677 cycles

DURING C18 CHECK INSPECTION, FOUND A CRACK AT STRINGER S25L END, BS 676, POINTING AFT. DAMAGE IS LOCATED AT THE STRINGER WEB EXTENDING FOR ABOUT 5 INCHES. TRIMMED OUT DAMAGED. PERFORMED HFEC INSPECTION OF TRIM OUT AND 3 INCHES AROUND INSURE CRACK FREE IAW NDT PART 6. TOUCHED UP EXPOSED EDGE OF STRINGER TRIM OUT AND ANY BARE AREA OF THE SURROUNDING STRUCTURE WITH CHEMICAL CONVERSION COATING IAW SRM 51-20-01. INSTALLED REPAIR PARTS AS SHOWN IN FIG 3 OF REPAIR EA MF00852R0006.

Part: STRINGER — CRACKED (ZONE 200) · airframe 77,627 hrs · 17,677 cycles

DURING C18 CHECK INSPECTION, A CRACK WAS OBSERVED AT STRINGER S-17L END, BSTA 676 POINTING AFT. THE DAMAGE IS LOCATED AT THE STRINGER WEB EXTENDING ABOUT 3 IN. THE AFFECTED STRINGER SPLICES TO THE MAIN DECK CARGO DOOR SURROUND STRUCTURE. TRIMMED OUT THE DAMAGED PORTION OF THE AFFECTED STRINGER BETWEEN BSTA 698 AND BSTA 720. PERFORMED HFEC INSP OF TRIM OUT AND 3 IN AROUND IT TO INSURE A CRACK FREE CONDITION IAW NDT PART 6. TOUCHED UP EXPOSED EDGE OF STRINGER TRIM OUT AND ANY BARE AREA OF THE SURROUNDING STRUCTURE WITH CHEMICAL CONVERSION COATING IAW SRM 51-20-01. INSTALLED REPAIR PARTS AS SHOWN IN FIG 3 OF IAI REPAIR EA MF00852R0002. THIS IS A CATEGORY B REPAIR IAW SRM 51-00-06.

Part: STRINGER — CRACKED (ZONE 200) · airframe 77,627 hrs · 17,677 cycles

DURING C18 CHECK INSPECTION, A CRACK WAS OBSERVED AT STRINGER S19L END, BS 676 POINTING AFT. THE DAMAGE IS LOCATED AT THE STRINGER WEB EXTENDING ABOUT 1.5 IN. THE AFFECTED STRINGER SPLICES TO THE MAIN DECK CARGO DOOR SURROUND STRUCTURE. TRIMMED OUT THE DAMAGED PORTION OF THE AFFECTED STRINGER BETWEEN BS 698 AND 720. PERFORMED HFEC INSP OF TRIM OUT AND 3 INCHES AROUND IT TO INSURE A CRACK FREE CONDITION IAW NDT PART 6. TOUCHED UP EXPOSED EDGE OF STRINGER TRIM OUT AND ANY BARE AREA OF THE SURROUNDING STRUCTURE WITH CHEMICAL CONVERSION COATING PER SRM 51-20-01. INSTALLED REPAIR PARTS AS SHOWN IN FIG 3 OF IAI REPAIR EA MF00852R0004. THIS IS A CATEGORY B REPAIR IAW SRM 51-00-06.

Part: FUEL TANK — LEAKING (LT WING ROOT)

DURING TAKEOFF, THE CREW SMELLED A STRONG FUEL ODOR IN COKPIT WITH PACKS OFF. THEY CONTINUED ON WITH THE FLIGHT AND LANDED WITHOUT FURTHER INCIDENT. MX TROUBLESHOT SYS AND FOUND FUEL LEAK AT INBD LT WING OVER WING ROOT. THEY CLEANED, RESEALED, LEAK CHECKED GOOD IAW AMM 28-11-00. ACFT WAS RETURNED TO SERVICE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 76,202 hrs · 17,120 cycles

LIGHTNING STRIKE DAMAGE AT BS 148 - BS 157. DAMAGE ENCOMPASSES UNDERLYING CHORD AT S27L. REPAIRED IAW B767 SRM 53-00-01 FIG 201 REPAIR 1. SKIN REPAIR DIMENSION ARE 18" X 9.5" EXTENDING FROM BS 143 TO BS 161.5 USING .090 2024 T3 DOUBLER. CUT OUT DAMAGE AT S27L STA 148.75 TO 157 CUTOUT DIMENSIONS ARE 1.5" X 8.26 ". DOUBLER ATTACHED WITH BACR30CE8D REPAIR RIVETS AND EXISTING RIVETS.

Part: WIRE — DAMAGED (CABIN)

LAX - DURING OVERNIGHT MAINTENANCE, EMERGENCY ESCAPE PATH LIGHTING WAS OBSERVED TO BE INOPERATIVE IN THE AFT CABIN. REPAIRED ELECTRICAL WIRE CONNECTION. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: LIGHT — DISCONNECTED (CABIN)

JFK - DURING OVERNIGHT MAINTENANCE, EMERGENCY LIGHTS AT SEAT 29H INOPERATIVE. RECONNECT EMERGENCY EXIT LIGHT ASSEMBLY TO HARNESS AT SEAT 29H. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: WIRE — DAMAGED (CABIN)

LAX - DURING OVERNIGHT MAINTENANCE, RIGHT EMERGENCY LIGHT BY FORWARD GALLEY INOPERATIVE. REPAIRED WIRE AT EMERGENCY EXIT LIGHT AT FORWARD GALLEY. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: LIGHT — DAMAGED (CABIN)

LAX - DURING OVERNIGHT MAINTENANCE, LEFT AFT GALLEY UNDER FLIGHT ATTENDANT SET B1 DIRECTIONAL EMERGENCY EXIT LIGHT DAMAGED. REPLACED LEFT AFT GALLEY B1 DIRECTIONAL EMERGENCY EXIT LIGHT ASSEMBLY. (M)

Part: WIRE — DAMAGED (CABIN)

LAX - DURING OVERNIGHT MAINTENANCE, TWO FIRST CLASS FLOOR LEVEL EMERGENCY EXIT LIGHTS INOPERATIVE. REPAIRED FIRST CLASS FLOOR LEVEL EMERGENCY EXIT LIGHTS WIRE UNDER GALLEY FLOOR. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: CONNECTOR — BROKEN (CABIN)

SFO - DURING OVERNIGHT MAINTENANCE, FOUND EMERGENCY PATH LIGHTING AT SEAT 28H INOPERATIVE. REMOVED AND REPLACED BROKEN CONNECTOR AT LOWER SIDEWALL. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: SOCKET — DEFECTIVE (CABIN)

LAX - DURING OVERNIGHT MAINTENANCE, EMERGENCY EXIT LIGHT AT SEAT 32HJ INOPERATIVE. REPLACED EMERGENCY EXIT LIGHT SOCKET AT SEAT 32HJ. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: LIGHT — INOPERATIVE (EXTERIOR)

SFO - DURING OVERNIGHT MAINTENANCE, R1 DOOR EMERGENCY EXIT EXTERIOR LIGHT ASSEMBLY INOPERATIVE. UNABLE TO ACCESS LIGHT ASSEMBLY WITHOUT REMOVING GALLEY. AWAITING MAINTENANCE SCHEDULING. (M)

Part: WIRE — BROKEN (CABIN)

BOS - DURING OVERNIGHT MAINTENANCE, EMERGENCY EXIT ESCAPE PATH LIGHT AT SEAT 33A INOPERATIVE. REPAIRED WIRE AT SEAT 33A. SYSTEM GROUND CHECK NORMAL OPERATION. (M)

Part: SKIN — CORRODED (WING BOX)

AFW - WING BOX UPPER SKIN HAS CORROSION ON UPPER SURFACE. REMOVED FASTENERS, HFEC THE BLENDED AREA, SHOT/FLAP PEEN THE AFFECTED AREA PER SRM. APPLY ALODINE AND 2 COATS OF PRIMER TO AREA. REWORK EXISTING COUNTERSINK PER 767SRM 51-40-08 PER REF /C/. INSTALL REPLACEMENT BACB30NW12K OR EQUIVALENT FASTENER. (M)

Part: WIRE — BROKEN (ROWS 8 AND 34)

LHR - DURING ROUTINE MAINTENANCE, EMERGENCY EXIT SEAT LIGHTS AT SEATS 8HJ AND 34H INOPERATIVE. REPAIRED EMERGENCY EXIT SEAT LIGHT WIRING AT SEATS 8HJ AND 34H. SYSTEM GROUND CHECKED, NORMAL OPERATION. (X)

Part: WIRE — BROKEN (CABIN)

SFO - DURING OVERNIGHT MAINTENANCE, FORWARD GALLEY BIDIRECTIONAL EMERGENCY FLOOR PATH LIGHTS INOPERATIVE. REPAIRED BROKEN WIRE AT FORWARD GALLEY BIDIRECTIONAL EMERGENCY FLOOR PATH LIGHTS. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: LIGHT — INOPERATIVE (CABIN)

SFO - DURING OVERNIGHT MAINTENANCE, EMERGENCY CEILING LIGHT AT SEAT ROW 7 RIGHT SIDE WOULD NOT ILLUMINATE. REPLACED EMERGENCY CEILING LIGHT ASSEMBLY AT SEAT ROW 7 RIGHT SIDE. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: BEAM — CORRODED (LT MLG)

AFW - FOUND CORROSION IN THE BORE FOR THE AFT MLG TRUNNION BUSHING. THE BORE WAS HONED OUT TO A DIA OF 8.272 INCH, AFTER HONING SOME LOCAL PITTING REMAINED WHICH WAS BLENDED AND THE PITTING WAS IN THE 1R O'CLOCK AREA. (M)

Part: CONNECTOR — DEFECTIVE (CABIN)

SFO - DURING OVERNIGHT MAINTENANCE, EMERGENCY EXIT LIGHT AT SEAT ROW 30HJ WOULD NOT ILLUMINATE. REPLACED EMERGENCY EXIT LIGHT CONNECTOR AT SEAT ROW 30 HJ. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: WIRE — BROKEN (CABIN)

SFO - DURING OVERNIGHT CHECK, EMERGENCY FLOOR LIGHTS AT MID-GALLEY INOPERATIVE. REPLACED BROKEN EMERGENCY FLOOR LIGHT WIRE BY MID-GALLEY LIGHT L9027. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: IDG — FAILED (LT ENGINE)

BOS - LEFT ONE LIGHT ILLUMINATED AND GEN DISCONNECTED. CONFIRMED DELTA P FILTER BUTTON POPPED. REPLACED LEFT IDG. NEW IDG DEFECTIVE FROM STOCK AS UNABLE TO RESET FIELD, S/N CO105 DFW. NEEDS ANOTHER IDG. NIS BOS. PLACARDED LEFT IDG INOP PER MEL REF 2401 AUTH 07-158DC-B. BOTH IDGS SERVICED FULL ENTERED IN MIC. REPLACED LEFT ENGINE IDG PER MM. ALL CHECKS TEST GOOD. REMOVED PLACARD MEL 7-158DC-B. CLEARED MIC. (M)

Part: IDG — FAILED (RT ENGINE)

LGW - FLT 0174 - RIGHT GENERATOR DRIVE LIGHT AND GENERATOR OFF LIGHT ILLUMINATED AT FL 100 ABOVE GRD DURING APPROACH. REPEAT ITEM ACCOMPLISHED OM PROCEDURE. DISCONNECTED IDG. CHECKED RT IDG SCAVENGE FILTER. NO DEBRIS FOUND. SERVICED LT IDG TO FULL. CHECKED APU OIL LEVEL, FULL. DUE TO HISTORY, DEF TO MICS PER MEL. ALL PROCEDURES FOR MPM 24-01 ACCOMPLISHED. ER RESTRICTED TO 120 MINS. VERIFIED RT IDG DISCONNECTED, BPCU BITE SHOWED LOW OIL PRESSURE, UNDER FREQ TRIP, IDG PMG WIRING. PERFORMED CONTINUITY CHECKS OF WIRING BETWEEN GCU AND IDG TEMP BULB, PMG WIRING. NO FAULTS NOTED. REPLACED RT GCU PER MM. OPS CHECKS GOOD. MIC SHEET AND MEL CLEARED. (X)

Part: IDG — FAILED (RT ENGINE)

BRU - FLT 0088 - RIGHT GENERATOR DRIVE EICAS MESSAGE WITH ASSOCIATED RT GEN OFF LIGHT. REPLACED SCAVENGE FILTER (SMALL CHIPS FROM NORMAL WEAR). LOW OIL PRESSURE+UNDERFREQ TRIP+IDG/PMG WIRING ON BPCU BIT. IDG REMAINS DISCONNECTED. IDG SERVICED. APU SERVICED. ETOPS LESS THAN 120 MINS ALLOWED. MIC SHEET ENTERED. REMOVED AND REPLACED ENG DRIVEN GENERATOR. SYSTEM LEAK CHECKED AND OPERATIONALLY CHECKED DURING ENG RUN AND FULL LOAD. SYSTEM OPS CKD NORMAL. CLEARED MEL. REF: 24-01 AUTH 12-443DC-B. CLEARED MIC. (X)

Part: HOUSING — DEFECTIVE (CABIN)

SFO - DURING OVERNIGHT CHECK, EMERGENCY EXIT LIGHT AT PAX SEAT 3H INOPERATIVE. REPLACED EMERGENCY EXIT LIGHT HOUSING AT PAX SEAT 3H. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: FLOOR BEAM — CORRODED (BS 347)

AFW - FLOOR BEAM HAS CORROSION BEYOND SRM LIMITS. FABRICATE REPAIR DOUBLER FROM 0.050 CRES AND INSTALLED WET WITH BMS 5-95 SEALANT PER ENGINEERING MRB 767-1028. (M)

Part: FLOOR BEAM — CORRODED (BS 303)

AFW - FLOOR BEAM HAS CORROSION BEYOND SRM LIMITS. FABRICATED REPAIR DOUBLER FROM .050 STAINLESS STEEL INSTALLED WET WITH BMS 5-95 SEALANT PER ENGINEERING MRB 767-1026. (M)

Part: STRINGER — CORRODED (BS 1472)

AFW - REMOVED STRINGER SECTION, CORRODED BEYOND SRM LIMITS. FABRICATE LONGER SPLICE FROM SAME MATERIAL TYPE AND SHAPE PER ENGINEERING MRB 767-1032. (M)

Part: FLOOR BEAM — CORRODED (BS 325)

AFW - FLOOR BEAM HAS CORROSION BEYOND LIMITS. FABRICATED REPAIR DOUBLER FROM 0.050 CRES STEEL AND INSTALL WET WITH BMS 5-95 SEALANT PER ENGINEERING MRB 767-1030. (M)

Part: FAIL/SAFE STRAP — CORRODED (BS 747)

AFW - FORWARD CARGO DOOR FAIL/SAFE STRAP HAD CORROSION BEYOND SRM LIMITS. REMOVED CORROSION AND REPLACED FASTENERS PER ENGINEERING MRB 767-1023. (M)

Part: FITTING — DAMAGED (WING)

AFW - EDGE DAMAGE BEYOND SRM 57-20-90-1 FIG 101 DETAIL V LIMITS. BLENDED DAMAGED AREA, NDT INSPECT, FLAP PEEN AND RESTORE FINISH PER ENGINEERING MRB 767-1034. (M)

Part: SKIN — CORRODED (WS 995)

AFW - WING BOX SKIN HAS CORROSION BEYOND SRM LIMITS. BLENDED AND APPROVED FOR CONTINUED SERVICE PER ENGINEERING MRB 767-1029. (M)

Part: FLOOR BEAM — CORRODED (BS 266)

AFW - FOUND FLOOR BEAM HAS CORROSION BEYOND LIMITS. ALODINED, FILLED WITH BMS 5-92 SEALANT. INSTALLED REPAIR STRAP WET WITH BMS 5095 SEALANT, PRIMED AND PAINTED PER ENGINEERING MRB 767-1025. (M)

Part: FLOOR BEAM — CORRODED (BS 287)

AFW - FLOOR BEAM HAS CORROSION BEYOND SRM LIMTS. FABRICATE REPAIR STRAP FROM 0.050 THK CRES AND INSTALL WET PER ENGINEERING MRB 767-1027. (M)

Part: FLOOR BEAM — CORRODED (BS 852)

AFW - FOUND CORRODED BEYOND LIMITS. CUT OUT DAMAGED FLOOR BEAM AND INSTALLED REPAIR SPLICE PER ENGINEERING MRB 767-1031. (M)