N795AX

Part: CABLE — BINDING (LEFT ENGINE) · airframe 69,196 hrs · 48,743 cycles

LT ENG COMPRESSOR STALL (MODERATE) ALL ENG INDICATIONS NORMAL IN CLIMB THROUGH 35000'. FLIGHT CREW ELECTED TO DIVERT TO CVG. AIRCRAFT WAS GROUNDED BY MAINTENANCE. MAINTENANCE FOUND VSV CABLE BINDING.REMOVED OLD, THEN INSTALLED NEW L/H ENGINE VSV CABLE PER AMM 75-31-03. ENGINE WAS BORESCOPED AND NO DAMAGE FOUND. AIRCRAFT RETURNED TO SERVICE

Part: TRANSMITTER — FAULTY (TE FLAP SYS) · airframe 68,867 hrs · 48,644 cycles

AFTER TAKEOFF DURING CLIMB THE FOLLOWING LIGHTS ILLUMINATED; AMBER TE FLAP DISAGREE EICAS AMBER TRAILING EDGE DISCREET LIGHT PERFORMED NON-NORMAL PROCEDURE FOR TE FLAP DISAGREE AND LANDED BACK IN KILN WITH FLAPS 20 THE LIGHTS BEGAN ILLUMINATING WHILE FLAPS RETRACTING FROM 1 TO UP. AIRCRAFT WAS GROUNDED BY MAINTENANCE. TROUBLESHOT FLAP SYSTEM IAW B767 FIM 27-51 FAULT TREE 839 AND TREE 809. FOUND FLAP POSITION TRANSMITTERS #1 AND #8 FAULTY. REMOVED POSITION #1 AND #8 TRANSMITTERS IAW B767 AMM 27-51-45. OPERATIONAL CHECK SATISFACTORY. AICRAFT RETURNED TO SERVICE.

Part: TRANSMITTER — FAULTED (RT ELEVATOR) · airframe 68,583 hrs · 48,555 cycles

DURING CONTROL CHECK, RIGHT ELEVATOR FAILED TO MOVE FROM NEUTRAL POSITION. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE VERIFIED MOVEMENT OF RH ELEVATOR AND POSITION TRANSMITTER WAS AT FAULT.R/H POSITION INDICATOR DEFERRED IAW MEL 27-08-1. AIRCRAFT RETURNED TO SERVICE.

Part: CONTROL VALVE — INTERMITTENT (TEMP) · airframe 68,330 hrs · 48,473 cycles

CABIN ALT & CABIN ALTITUDE LIGHTS ILLUMINATED. EICAS MESSAGE CABIN ALTITUDE WAS DISPLAYED. UNABLE TO RESTORE CABIN PRESS. USING MANUAL MODE. DESCENDED TO FL 280 LIGHT WENT OUT. OXYGEN WAS USED. AICRAFT CONTINUED TO SCHEDULED ARRIVAL AIPORT. AIRCRAFT WAS GROUNDED BY MAINTENANCE UNTIL REPAIRS WERE MADE. RT PACK TEMP CONTROL VALVE WAS REPLACED IAW B767 AMM 21-51-12. RELAY K50 WAS REPLACED IAW SWPM 20-81-22 AIRCRAFT RETURNED TO SERVICE.

Part: START VALVE — FAULTED (LT ENGINE) · airframe 68,123 hrs · 48,404 cycles

DURING L ENG START, L ENG STARTER EICAS MSG. NO N2 ROTATION. AIRCRAFT RETURNED TO BLOCK AND GROUNDED BY MAINTENANCE. REMOVED AND REPLACED #1 ENG. START VALVE IAW B767 AMM 80-11-02. AIRCRAFT RELEASED FOR FLIGHT

Part: UNKNOWN — UNKNOWN (NLG STEERING) · airframe 67,978 hrs · 48,360 cycles

UPON ENTERING RUNWAY MAKING LEFT TURN NWS MAKING GRINDING SOUNDS AND BURNING RUBBER SMELLED. AIRCRAFT BTB. MAINTENANCE GROUNDED AIRCRAFT.INSPECTED NOSE WHEEL STEERING SYSTEM. NO FAULTS NOTED. GREASED STEERING ACTUATORS AND TORQUE LINKS IAW AMM 32-51-00. AIRCRAFT RELEASED.

Part: SHUTOFF VALVE — LEAKING (HYD FLAP/SLAT) · airframe 67,791 hrs · 48,300 cycles

THE CENTER HYDRAULIC QUANTITY EICAS MESSAGE DISPLAYED INDICATION. AN IN FLIGHT EMERGENCY WAS DECLARED. THE AIRCRAFT LANDED SAFELY WITH NO OTHER PROBLEMS. AIRCRAFT WAS THEN GROUNDED BY MAINTENANCE. A HYDRAULIC LEAK WAS FOUND ON THE CENTER FLAP/SLAT SHUT OFF VALVE MODULE. THE VALVE WAS REPLACED IAW AMM 27-51-48. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: WARNING LIGHT — ILLUMINATED (LT A/C PACK TEMP) · airframe 67,515 hrs · 48,212 cycles

L PACK TEMP EICAS MESSAGE ON TAXI OUT. ACCOMPLISHED QRH PROCEDURE. AFTER 5 MINUTES IN STBY N PACK INOP LIGHT REMAINED ILLUMINATED. AIRCRAFT BACK TO BLOCK. AIRCRAFT GROUNDED BY MAINTENANCE. LEFT PACK DEFERRED. AIRCRAFT RELEASED FOR FLIGHT.

Part: DOOR — UNLATCHED (MAIN CARGO) · airframe 67,302 hrs · 48,142 cycles

AFTER TAKE OFF, MX CARGO DOOR LIGHT ILLUMINATED.AIRCRAFT DECLARED AN EMERGENCY AND RETURNED TO ORIGIN. AIRCRAFT WAS GROUNDED BY MAINTENANCE. FOUND THE MCD DOOR DOOR NOT LATCHED LIGHT ON. OPERATED THE UNLOCK SWITCH UP, UNLOCKED DOOR AND POSITIONED THE CLOSED SWITCH DOWN. THE LIGHT EXTINGUISHED , OPERATED DOOR THRU ADDITIONAL CYCLES PER ABX MMS 52-32-00, NO FAULTS FOUND. PERFORMED OVERWEIGHT LANDING INSPECTION PER AMM 05-51-35 NO DAMAGE FOUND. AIRCRAFT RELEASED FOR FLIGHT.

Part: PCA — LEAKING (NR 1 SPOILER) · airframe 67,105 hrs · 48,055 cycles

L HYD QTY LOW EICAS MSG,FLIGHT CREW DECLARED AN EMERGENCY AND EXECUTED AN AIR TURN BACK AND LANDED UNEVENTFULLY. MAINTENANCE DETERMINED #1 SPOILER WAS LEAKING HYDRAULIC FLUID AND AIRCRAFT WAS GROUNDED. REMOVED AND REPLACED #1 SPOILER PCA OPS CHECK/RIG CHECK GOOD. NO FAULTS NOTED AT THIS TIME. IAW B767 AMM 27-61-02. AIRCRAFT RELEASED FOR SERVICE

Part: FSEU — FAULTED (TE FLAPS) · airframe 67,088 hrs · 48,042 cycles

TE FLAPS DISAGREE CAUTION MESSAGE RAN THE QRH IN-FLIGHT. TRAILING EDGE DISCREET LIGHT. EMERGENCY DECLARED. LANDING UNEVENTFUL. AIRCRAFT GROUNDED BY MAINTENANCE. BITE TESTED FSEU AS PER FIM 27-51 FT 809. EXTRACTED FAULT MSG NO. 27-51102 " L FLAP.STAB POS" PERFORMED CORRECTIVE ACTION AS PER TABLE A. TESTED EACH FSPM AS PER FIM 27-58-00/101. ALL GRD LIGHT ILLUMINATED NO AMBER LIGHT CAME ON . PHYSICALLY CHECKED ALL POS TRANSMITTERS, NO DIASCREANCIES. FOUND. OPS CHECKED GOOD. AIRCRAFT RELEASED.

Part: AUTOTHROTTLE SYS — MALFUNCTIONED · airframe 66,418 hrs · 47,749 cycles

ON PUSH, AUTOTHROTTLES WENT INOPERABLE FOLLOWED BY LOSS OF THRUST SETTINGS BEING DELETED. WILL NOT TAKE ANY THRUST SETTINGS. AIRCRAFT BACK TO BLOCK. AIRCRAFT GROUNDED. ACCOMPLISHED OPERATIONS CHECK OF TMS DISPLAY AND TMC, REF AMM 22-31-01, C/W MCDP TESTS 02 AND 05-NO FAULTS, SYSTEM OPERATIONS CHECKS OK. PLACARDS REMOVED. A/C RELEASED, NO PARTS REPLACED.

Part: LINE — LEAKING (HYD SYSTEM) · airframe 66,351 hrs · 47,725 cycles

ON TAXI OUT, LT HYDRAULIC SYSTEM LOW QTY EICAS MESSAGE IN VIEW STATUS PAGE SHOWS ZERO QTY. AICRAFT BACK TO BLOCK AND GROUNDED. UPON INSPECTION FOUND LEAKING RETURN LINE FROM EDP IN THE LT PYLON. REMOVED LINE, REPAIRED HYD LINE WITH RYNGLOK, REF B767 MM 20-10-09, LINE LEAK CHECKS GOOD. REINSTALLED LINE, REF AMM 20-10-09. SYSTEM LEAK CHECKS GOOD. AIRCRAFT RELEASED.

Part: SEAT TRACK — CORRODED (BS 1307) · airframe 65,925 hrs · 47,561 cycles

CORROSION WAS FOUND ON THE INBOARD FLANGE OF AFT LOWER CARGO COMPARTMENT SEAT TRACK (P/N: 96FS667842-107) AT STA 1307, RBL 15.01. THE DAMAGE WAS REMOVED BY BLENDING. ORIGINAL FLANGE THICKNESS IS .080 AND MINIMUM REMAINING THICKNESS IN THE BLENDED AREA IS .033. THERE ARE NO REPAIRS FOR THE SPECIFIC LOCATION IN THE 767-200 SRM. THIS REA ACCOMPLISHES THE PERMANENT REPAIR OF THE AFT LOWER CARGO COMPARTMENT SEAT TRACK (ABX-REA-5043-64103-00).

Part: PANEL — GOUGED (LT PYLON STRUT) · airframe 65,925 hrs · 47,561 cycles

GOUGE DAMAGE WAS FOUND ON THE STRUT SKIN PANEL (P/N 311T1400-21) OF THE LT PYLON. THE GOUGE WAS REMOVED BY BLENDING, PER 767-200 SRM 51-10-02 EXCEEDING SRM LIMITS. ALL FASTENERS COMMON TO REWORKED AREAS, AS REQUIRED, WERE REMOVED AND HFEC OPEN-HOLE AND SURFACE SCAN INSPECTIONS WERE ACCOMPLISHED PER N767 NDT MANUAL PART 6, 51-00-00 WITH NO DEFECTS REPORTED. AN ULTRASONIC THICKNESS (UT) INSPECTION WAS ACCOMPLISHED AT REWORKED LOCATION, PER 767 NDT MANUAL PART 6 TO DETERMINE THE MINIMAL REMAINING MATERIAL THICKNESS AND RESULTS WERE RECORDED IN A 0.5” X 0.5” GRID PATTERN AS SHOWN IN FIGURE 2. THIS REA ACCOMPLISHES THE PERMANENT REPAIR OF THE STRUT SKIN.

Part: DOOR SILL — CORRODED (AFT CARGO BAY) · airframe 65,925 hrs · 47,561 cycles

DURING AIRCRAFT CURRENT CHECK AT AIRBORNE (TPA), CORROSION WAS FOUND ON THE AFT LOWER CARGO DOOR CUTOUT LOWER SILL FAIL SAFE STRAP (P/N 146T8048-3), BETWEEN STA 1241 AND STA 1263 AT STRINGER S-33R. THE CORROSION WAS REMOVED AND EVALUATED PER 767-200 53-00-15 AND FOUND TO BE OUT OF PUBLISHED LIMITS. AN ULTRASONIC THICKNESS (UT) INSPECTION WAS ACCOMPLISHED AND DETERMINED THE NOMINAL THICKNESS TO BE AT REWORKED LOCATION 0.260” AND THE MINIMUM REMAINING TO BE 0.210” (REMOVED 0.050”). ALL FASTENERS COMMON TO REWORKED AREA, AS REQUIRED, WERE REMOVED AND HFEC OPEN-HOLE AND SURFACE SCAN INSPECTIONS WERE ACCOMPLISHED PER N767 NDT MANUAL PART 6, 51-00-00 WITH NO DEFECTS REPORTED. THE FAIL SAFE STRAP (146T8048-3) IS FABRICATED FROM 7075-T651 ALUMINUM PLATE. THIS REA ACCOMPLISHES THE PERMANENT REPAIR OF THE FAIL-SAFE STRAP.

Part: SUPPORT FITTING — CORRODED (RT WING) · airframe 65,925 hrs · 47,561 cycles

DURING AIRCRAFT C-CHECK AT TAMPA, AIRBORNE MAINTENANCE WAS REQUIRED TO INSPECT THE NR 8 FLAP SUPPORT 1-3 BEAM ASSEMBLY PER ABX WORK CARD ABX-57-796-28-02. INSPECTION REVEALED CORROSION WITHIN A HOLE LOCATION. THE SUBJECT HOLE WAS REWORKED TO A CLEAN AND ROUND CONDITION FROM 0.6270” TO A FINAL DIAMETER OF 0.6680”. A SUBSEQUENT HFEC ROTARY SCAN WAS ACCOMPLISHED WITH NO FURTHER DEFECTS FOUND. REFERENCE FIGURE 1 FOR SUBJECT HOLE LOCATION. THIS REA ACCOMPLISHES THE PERMANENT REPAIR OF THE 1-3 BEAM (ABX-REA-2750-64094-00).

Part: SKIN — CORRODED (BS 1395-1417) · airframe 65,925 hrs · 47,561 cycles

WHILE PERFORMING THE SCRIBE LINE INSPECTION, PER ABX TASK CARD ABX-SCL-5330-0016-23145 REFERENCE AD 2010-06-16 AND BOEING SB 767-53A0193, CORROSION WAS FOUND ON THE FUSELAGE SKIN (P/N 146T3330-41 ASSY) IN ZONE A AT STRINGER S-17L BETWEEN STA 1395 AND STA 1417. CORROSION WAS REMOVED BY BLENDING, PER 767-200 SRM 51-10-02. ALL FASTENERS COMMON TO REWORKED AREAS, AS REQUIRED, WERE REMOVED AND HFEC OPEN-HOLE AND SURFACE SCAN INSPECTIONS WERE ACCOMPLISHED PER 767 NDT MANUAL PART 6 WITH NO DEFECTS REPORTED. AN ULTRASONIC THICKNESS (UT) INSPECTION WAS ACCOMPLISHED AT EACH LOCATION TO DETERMINE THE MINIMAL REMAINING MATERIAL THICKNESS AND RESULTS WERE RECORDED IN A 0.5” X 0.5” GRID PATTERN AS SHOWN IN FIGURE 2. THE SRM 53-00-01 ALLOWABLE DAMAGE 1, FIGURE 101 (SHEET 12 OF 17) STATES DAMAGE IN ZONE A IS NOT PERMITTED, CONTACT BOEING FOR THE ALLOWABLE LIMITS IN THIS AREA.

Part: WARNING MESSAGE — ILLUMINATED (LT STARTER) · airframe 65,774 hrs · 23,145 cycles

L ENG STARTER EICAS MESSAGE ILLUMINATED DURING ENGINE START. AIRCRAFT WAS GROUNDED.

Part: VALVE — MALFUNCTIONED (BLEED AIR SYS) · airframe 65,670 hrs · 47,433 cycles

LEFT BLEED AIR ISOLATION VALVE LIGHT STAYS ON. AIRCRAFT WAS GROUNDED.

Part: ESCAPE REEL — DEPLOYED (CABIN) · airframe 65,317 hrs · 47,276 cycles

INERTIAL ESCAPE REELS DEPLOYED. AIRCRAFT GROUNDED.

Part: ENGINE — MAKING METAL (RIGHT) · airframe 62,157 hrs · 46,084 cycles

ON CLIMB OUT AT APPROXIMATELY FLIGHT LEVEL 190, THE CREW HEARD A BOOM AND SMELLED A STRONG SMOKE ODOR. AT THE SAME TIME, THE AIRPLANE YAWED AND SHUTTERED. THE RIGHT ENGINE HAD HIGH EGT (1100 DEG) AND N2 INDICATION (113.1). THE RIGHT ENGINE WAS SHUT DOWN AND THE CREW DECLARED AN EMERGENCY. THE AIRPLANE WAS REMOVED FROM SERVICE (GROUNDED) AND METAL PARTICLES WERE FOUND IN THE TAIL PIPE. THE RIGHT ENGINE WAS REPLACED. THE CAUSE OF THE ENGINE FAILURE IS UNKNOWN.

Part: STRUCTURE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,974 hrs · 46,001 cycles

CORROSION ON OUTBOARD LONGERON CHORD AT BODY STATION 1047 TO 1051 IN THE LEFT WHEEL WELL. THE CHORD WAS REPAIRED. THE AIRPLANE WAS GROUNDED.

Part: STRINGER — CORRODED (LT HORIZ STAB) · corrosion level 2 · airframe 61,974 hrs · 46,001 cycles

CORROSION ON THE UPPER NR 8 STRINGER COMMON TO THE UPPER SURFACE OF THE LOWER HORIZONTAL FLANGE JUST OUTBOARD OF RIB 2 (LBL 41.5 - RSS 0.00) OF THE LEFT HORIZONTAL STABILIZER. THE STRINGER WAS REPAIRED. THE AIRPLANE WAS GROUNDED.

Part: KEELBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,974 hrs · 46,001 cycles

CORROSION ON KEEL BEAM LOWER INBOARD FLANGE AT BODY STATION 955 TO 1009. THE KEEL BEAM FLANGE WAS REPAIRED. THE AIRPLANE WAS GROUNDED.

Part: CARABINER — MISSING (FORWARD CABIN) · airframe 60,795 hrs · 45,537 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: CONTAINER — UNSECURE (ESCAPE ROPE) · airframe 60,497 hrs · 45,396 cycles

ON CLOSING THE L1 DOOR, TWO DESCENT DEVICES FELL OUT OF THE DESCENT DEVICE CONTAINER AND THEY UNWOUND TO THE FLOOR. WHILE THE AIRPLANE WAS GROUNDED, THE DESCENT DEVICES WERE REPLACED WITH SERVICEABLE DESCENT DEVICES. THE CAUSE FOR THE DESCENT DEVICES DROPPING TO THE FLOOR IS UNKNOWN.

Part: ESCAPE ROPE — DEFECTIVE · airframe 59,871 hrs · 45,192 cycles

WHILE THE AIRPLANE WAS REMOVED FROM SERVICE, TWO DESCENT DEVICES WERE FOUND PARTIALLY UNWOUND. THE DESCENT DEVICES WERE REPLACED. THE CAUSE FOR THE DESCENT DEVICES BECOMING UNWOUND IS UNKNOWN.

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHT) · airframe 58,854 hrs · 44,839 cycles

INTERIOR EMERGENCY LIGHTING SYSTEM INOPERATIVE. THE EMERGENCY LIGHT BATTERY PACK WAS REPLACED. THE CAUSE OF THE INOPERATIVE LIGHTS WAS A DISCHARGED BATTERY.

Part: SOCKET — INOPERATIVE (EMERGENCY LIGHT) · airframe 58,854 hrs · 44,839 cycles

EXTERIOR EMERGENCY LIGHTING SYSTEM INOPERATIVE. THE LAMP WAS REPLACED IN THE EMERGENCY LIGHT LAMPHOLDER ASSEMBLY. THE CAUSE OF THE INOPERATIVE LIGHT WAS A FAILED LAMP.

Part: BEAM — CORRODED (LT WING) · corrosion level 2 · airframe 58,311 hrs · 44,667 cycles

LEFT WING, T/E, STA WS 370, OTBD OF AFT CORNER OF PANEL 551XBX, FWD OF FLAP TRANSMISSION, MAJOR CORROSION. R & R BEAM, CHORD LT WING T/E STA WS 370 IAW SRM 51-40-02. CORRODED LEVEL 2, PN 113T1407-5, SPOILERS BEAM CHORD, EXACT FS/BS LOCATION ON ACFT FROM STR, WS 273 TO 431. ACFT WAS GROUNDED.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 58,311 hrs · 44,667 cycles

AFT SIDE STA 676, STR 8L CRACKED IN RADIUS IN UPPER HAT FLANGE APPROXIMATELY 2" FROM FORWARD END. STR 8L AT STA 676 IAW ENGINEERING SKETCH ES 02821. CRACKED 2.0", PN 143T3001-6, STR 8L, LOCATION AT STA TO 709, STR LOCATION S8L. ACFT WAS GROUNDED.

Part: ATTACH ANGLE — CORRODED (LT WING) · airframe 58,311 hrs · 44,667 cycles

CORRODED LOWER T/E PANEL ATTACH ANGLE AT WS 364 AFT OF PANEL 651XBX. BLENDED AREA WITH THICKNESS OF .110" REMAINS .076" OUT OF LIMITS IAW SRM 57-51-02. R & R LOWER T/E PANEL ATTACH ANGLE AT WS 364 IAW SRM 51-40-02, SEC 9. CORRODED, PN 113T1407-6, SPOILER BEAM CHORD FROM WS 220 TO 380. ACFT WAS GROUNDED.

Part: STRINGER — CORRODED (RT HORIZ STAB) · corrosion level 2 · airframe 58,311 hrs · 44,667 cycles

HORIZONTAL STABILIZER BOX STR S-1U AFT HORIZONTAL LEG AT ATTACH POINT TO OTBD SIDE OF RIB 2R IS CORRODED, BLOWN OUT. REPAIRED STR 1 UPPER IN THE RT HORIZONTAL STABILIZER IAW REA B655-62090-MR. CORRODED LEVEL 2, PN: 182T3101-6, STRINGER, EXACT FS/BS LOCATION ON AC: RS STA 2.0 TO RS STA 6.0, EXACT STR/WS LOCATION ON AC: S1R TO S1R. ACFT WAS GROUNDED.

Part: STRINGER — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 58,311 hrs · 44,667 cycles

HORIZONTAL STABILIZER BOX STR S-5L FORWARD VERTICAL LEG AT ATTACH POINT TO INBD SIDE OF RIB 2L IS CORRODED, BLOWN OUT. REPAIRED STRINGER 5 LOWER IN THE HORIZONTAL STABILIZER CENTER BOX IAW REA B655-62086-MR. 181T4100-5, STR, CORRODED: LEVEL 2, EXACT FS/BS LOC ON AC: LBL 41.5 TO LBL 38.5 EXACT STR/WS LOCATION ON AC: S5 LOWER TO S5 LOWER. ACFT WAS GROUNDED.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 58,311 hrs · 44,667 cycles

AFT SIDE STA 676, STR 11L CRACKED APPROXIMATELY 1.5" AROUND FORWARD HI-LOCK IN LOWER HAT FLANGE. REPAIRED STR 11L IAW SRM 53-0-03 AND ES 02821. CRACKED 1.5", PN 143T3001-7, STR 11L, EXACT FS/BS LOCATION ON AC FROM S11L, STA 676. ACFT WAS GROUNDED.

Part: SPLICE PLATE — CORRODED (LT WING) · corrosion level 2 · airframe 58,311 hrs · 44,667 cycles

LEFT WING L/E LOWER SPLICE PLATE IS CORRODED AT STA 627. REMOVED CORROSION IAW SRM 57-41-01 ON LOWER SPLICE PLATE AT STA 627 AND FOUND TO BE OUT OF LIMITS. REPAIRED ON REA NR B657-62081. CORRODED, LEVEL 2, PN 114T0222-9, PART NAME: SPLICE PLATE, EXACT STR/WS LOCATION ON AC FROM 624 TO 629. ACFT WAS GROUNDED.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 58,311 hrs · 44,667 cycles

INNER CHORD AT STA 883.5, RBL89 HAS CRACK INDICATION. REPAIR COMPLETED ON EA 53000050-101. CRACKED, PN 145T1004-2, INNER CHORD, EXACT FS/BS LOCATION ON ACFT AT STA 883.5, EXACT STR, WS LOCATION ON ACFT AT RBL 89. ACFT WAS GROUNDED.

Part: CHANNEL — DAMAGED (LT WING) · corrosion level 2 · airframe 55,716 hrs · 43,372 cycles

WING TE PANEL ATTACH CHANNEL LOWER CHORD SPLIT ON EDGE AT WS 424.22 INCHES FROM REAR SPAR. INSTALLED NEW CHORD IAW REA B657-61210-MR & SRM 51-40-02. PANEL 552JB INSTALLED IAW SRM 51-40-02. SDR INFO PN 113T1407-1, PART NAME SPOILER BEAM CHORD, L2 CORROSION, EXACT STRINGER & WS LOCATION ON ACFT LW412. ACFT WAS GNDED.

Part: BUSHING — WORN (TE FLAP) · airframe 55,716 hrs · 43,372 cycles

LEFT WING NR 2 FLAP HINGE 9 - 10 BEAM HAS LOOSE BUSHINGS IN CTR OF THE BEAM. REPLACED BUSHINGS IAW REA C027-61235-MR. PN 113T1347-7, PART NAME BUSHING, WORN & LOOSE BUSHING, EXACT FS & BS LOCATION ON ACFT LT WING, EXACT WS LOCATION ON ACFT WS 616. ACFT WAS GNDED.

Part: BEARING — WORN (TE FLAP) · airframe 55,716 hrs · 43,372 cycles

RIGHT FLAP HINGE POINT 9 - 10 BEAM HAS A LOOSE BEARING & A LOOSE BUSHING. R & R BEARING ON 9 - 10 BEAM AT FLAP SUPPORT NR 7 IAW CMM 27-51-97. THE 9 - 10 BEAM WILL BE INSTALLED ON NR 0037, SEE REACO27-61234-MR. PN 60B00180-236, PART NAME BEARING, WORN & LOOSE BEARING, EXACT FS & BS LOCATION ON ACFT RT WING, EXACT WS LOC ON ACFT WS 616. ACFT WAS GNDED.

Part: KEELBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 55,716 hrs · 43,372 cycles

CORROSION FOUND BETWEEN STATION 999 & 1021 IN LT WW CTR BEAM. REMOVED CORROSION IAW SRM 53-50-12 & COMPLIED WITH REA NR B653-61251-MR. CORRODED L2, PN 145T8612-1, PART NAME KEEL WEB, SN N/A, LOCATION STATION 999 LBL TO 1021 LBL. ACFT WAS GNDED.

Part: SKIN — CRACKED (FUSELAGE) · airframe 55,716 hrs · 43,372 cycles

SKIN CRACKED AROUND RIVETS AT STATION 1654 ADJACENT TO STRINGERS 3L, 4L & 5L. REPAIRED SKIN IAW SRM 53-80-01 FIG 201 REPAIR 4. CRACKED, 0.6 INCHES, PART NAME SKIN, PN 148T3111, SN NSN, LOCATION FROM 1654 STRINGER & WS, LOCATION STRINGER 3L - 8L. ACFT WAS GNDED.

Part: BEAM — CRACKED (LT WING) · airframe 55,716 hrs · 43,372 cycles

LEFT WING NR 8 123 BEAM HAS 1 CRACK INDICATION. YOU CAN SEE THE DEFECT AT THE BOTTOM OF THE HOLE LOOKING FROM INBD OUT. REAMED HOLE CLEAN & ROUND IN 1/64TH INCREMENTS & COMPLIED WITH HFEC HOLE SCAN. REPAIRED NR 8 1-2-3 BEAM IAW REA CO57-61254-MR. ALSO REFERENCE NR 50700-0000-0033. PN 113T1313-8, PART NAME 1 - 3 BEAM, SN ABX V556, CRACKED .006, EXACT WS LOCATION ON ACFT 798.20 TO 810.00. ACFT WAS GNDED.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 55,716 hrs · 43,372 cycles

AT STRINGER 17L AT STATION 676 FOUND STRINGER CRACKED. REPAIR CRACKED STRINGER 17L STATION 676 UPPER CARGO AREA IAW ARM 53-00- 03 & REA NR B653-61203MR. CRACKED 2.0 INCHES, PN 143T3001-10, PART NAME STRINGER, LOCATION 675L TO 700L, STRINGER & WS LOCATION 17L. ACFT WAS GNDED.

Part: WEB — CRACKED (LT PYLON) · airframe 55,716 hrs · 43,372 cycles

AFT PYLON & STRUT AREA WHERE PANEL 437DB ATTACHES INSIDE LOWER ATTACH ANGLES ON LT & RT SIDES CRACKED. R & R IAW SRM 51-70-011 & SRM 51-20-01 MATERIAL 2024-T3- .071 OI-0050130. CRACKED 0.5, PN 313T1355-181, PART NAME WEB, SN NSN, NAC STATION 400.59 TO 410.59. ACFT WAS GNDED.

Part: STRUCTURE — CORRODED (LT WING) · corrosion level 2 · airframe 55,716 hrs · 433,372 cycles

REAR SPAR TO WING TE RIB AT WS 433 UPPER CHORD CORRODED AROUND NUTPLATES ON INBD SIDE. R & R CHORD IAW SRM 51-40-02. L2 CORROSION, PN 113T1510-33, PART NAME UPPER CHORD, SN NSN, LOCATION FROM 433 TO 433. ACFT WAS GNDED.

Part: CHANNEL — CORRODED (LT WING) · corrosion level 2 · airframe 55,716 hrs · 43,372 cycles

WING TE PANEL ATTACH CHANNEL LOWER CHORD SPLIT ON EDGE AT WS 1050. R & R DAMAGED CHORD IAW SRM 51-40-02. CORRODED L2 PN 113T1912-29, PART NAME BEAM, STRINGER & WS LOCATION WS 1040 TO 1060. ACFT WAS GNDED.

Part: CHANNEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 55,716 hrs · 43,372 cycles

KEEL BEAM PANEL 139DL ATTACHED CROSS MEMBER CORRODED AROUND NUTPLATES. CLEANED UP CORRODED AREAS & FOUND TO BE OUT OF LIMITS IAW SRM 53-30-12 FIG 101. REPLACED WITH NEW PART & DRILLED HOLES IAW SRM 51-40-08 & INSTALLED NUTPLATES IAW SRM 51-40-02. APPLIED IAW AMM 51-21-00 & APPLIED CORBAN IAW AMM 51-00-59-2. CORRODED L2, PN 145T8629-3, PART NAME CHANNEL, SN NA, FS & BS LOCATION FROM STATION 940 TO 940. ACFT WAS GNDED.

Part: FITTING — CORRODED (FUSELAGE) · airframe 53,224 hrs · 42,092 cycles

STA 1809.5 RIGHT STRINGER 10 END FITTING HAS CORROSION IN (1/2") ATTACH BOLT HOLES. REMOVED AND REPLACED S10R END CAP FWD OF STA 1809.5 IAW REA B653-60437-MR. ACFT WAS GROUNDED.

Part: FITTING — CORRODED (FUSELAGE) · airframe 53,224 hrs · 42,092 cycles

STA 1809.5 LEFT STRINGER 4 (1/2") END FITTING INBOARD HOLE HAS CORROSION INBOARD AND OUTBOARD HOLES THRU WEB AND CHORD. ALSO HAVE CORROSION. REMOVED AND REPLACED S4L END CAP FWD OF STA 1809.5 IAW REA B653-60437-MR, ACFT WAS GROUNDED.

Part: FITTING — CORRODED (FUSELAGE) · airframe 53,224 hrs · 42,092 cycles

STA 1809.5 LEFT STRINGER 3 (1/2") END FITTING THRU HOLES HAVE CORROSION INCLUDING WEB AND CHORD. REMOVED AND REPLACED S3L STA 1809.5 FWD SECTION END CAP IAW REA B653-60437-MR AND ON REA B653-60437-MR, ACFT WAS GROUNDED.

Part: FITTING — CORRODED (FUSELAGE) · airframe 53,224 hrs · 42,092 cycles

STA 1809.5 LEFT STRINGER 8 AND FITTING (1/2") BOLT HOLES THRU FITTING AND CHORD HAVE CORROSION. REMOVED AND REPLACED S8L END CAP FORWARD OF STA 1809.5 IAW REA B653-60437-MR AND REA B653-60437-MR, ACFT WAS GROUNDED.

Part: WEB — DAMAGED (HORIZ STAB) · airframe 53,224 hrs · 42,092 cycles

FASTENER HOLE NR 40 ON THE LEFT SIDE OF THE 1809.5 BULKHEAD OF DRWG 624T0020 FLAG NOTE 1 IS ELONGATED AT THE FUSELAGE, THE FITTING, AND AT THE HORIZONAL STAB. COULD NOT GET AN ACCURATE HFEC SCAN. FAB'D NEW REPAIR WEB IAW ENGINE APPROVAL & BOEING DWG #148T2740, SRM 51-20-01, AMES PROC STND'S. REMOVED & REINSTALLED VERT/HORIZ STIFFNERS, COLLAR, UPPER TENSION FITTING IAW 767 SRM 51-40-02. RMVD & REPL UPPR CHORD SEC. & CHORD BULKHEAD SPLICE FITTING IAW 767 SRM 51-40-02 & S/B 53A0078, INSTALLED & REMOVED STAB JACK EQUIP IAW 767 MM 55-17-51-4. ACFT WAS GROUNDED. S/N: NSN, ATA : 53, LOC: RT SD 1809.5

Part: FITTING — DAMAGED (FUSELAGE) · airframe 53,224 hrs · 42,092 cycles

STA 1809.5 UPPER OUTBOARD CORD LOWER FORWARD TENSION FITTING INNER SURFACE HAS TOOLING MARKS. REMOVED AND REPLACED RIGHT TENSION FITTING AND TORQUED TENSION BOLT TO 358 FT. LBS IAW B767 SRM 51-40-02 AND B767 SB 767-53A0078. ACFT WAS GROUNDED.

Part: RIB — DAMAGED (LT WING) · airframe 53,224 hrs · 42,092 cycles

LEFT WING RIB 8 STA 375 AT FWD SPAR OUTBOARD SIDE HAS TOOLING MARKS. REPAIRED IAW REA B657-60430-MR. ACFT WAS GROUNDED.

Part: RIB — DAMAGED (RT WING) · airframe 53,224 hrs · 42,092 cycles

RIGHT WING RIB 8 AT FORWARD SPAR INBOARD AND OUTBOARD IN ENGINE DRY BAY HAS TOOLING MARKS. REPAIR IAW REA B657-60431-MR. ACFT WAS GROUNDED.

Part: SPAR — CORRODED (LT WING) · airframe 53,224 hrs · 42,092 cycles

WING STATION 974 LW REAR SPAR UPPER SURFACE TRAILING EDGE PANEL SKIN BULGING SUSPECT CORROSION MARKED. REPAIRED LEFT WING REAR SPAR UPPER SKIN SURFACE WS 974 IAW REA B657-60401-MR. ACFT WAS GROUNDED.

Part: SILL — CORRODED (FUSELAGE) · airframe 53,224 hrs · 42,092 cycles

BULK CARGO DOOR SILL DOUBLER CORROSION ON UPPER SURFACE FUSELAGE STATION 1147 AND STRINGER 33 LEFT FORWARD END OF SILL PLATE. REMOVED AND REPLACED BULK CARGO DOOR SILL PLATE IAW B767 SRM 51-40-02 PARA 4, PARA 5 AND PARA 7. ACFT WAS GROUNDED.

Part: STRUCTURE — CORRODED (TAILCONE) · airframe 53,224 hrs · 42,092 cycles

TAIL CONE RIGHT LOWER OUTER CHORD LOWER TENSION BOLT HOLE HAS CORROSION. REMOVED AND REPLACED CHORD SECTION IAW B767-200 SRM 51-40-02 & BOEING DWG 624T0020. ACFT WAS GROUNDED.

Part: FITTING — GOUGED (RT WING) · airframe 53,224 hrs · 42,092 cycles

RIGHT WING ENGINE BACKUP FITTING BETWEEN RIB 8 AND 9 AT FWD SPAR HAS A GOUGE ON INBOARD LOWER SIDE. BLENDED GOUGE IAW B767 SRM 51-10-02. REMOVED .025" MATERIAL. COMPLIED WITH REA B657-60383-MR. FOUND NO DEFECTS ON AREA OF FITTING. GOUGE DIA 1.4" X .025". ACFT WAS GROUNDED.

Part: SKIN — GOUGED (LT WING) · airframe 53,224 hrs · 42,092 cycles

LEFT WING LOWER SKIN IN ENGINE DRY BAY HAS TOOLING MARKS AT WING STATION 389 JUST AFT OF LOWER SPAR CAP MARKED. BLENDED AREA IAW B767 SRM 51-20-01. MAX MATERIAL REMOVED .046. ACFT WAS GROUNDED.

Part: TEE FITTING — CORRODED (LT HORIZ STAB) · airframe 53,224 hrs · 42,092 cycles

LEFT HORIZONTAL STAB TIP UPPER PANEL ATTACH NUT PLATE T-CAP CORRODED AROUND NUT PLATES ON EDGE AND LOWER T-CAP SPLIT ON EDGE ADJACENT TO FORWARD NUT PLATE. REPAIRED LEFT HOIZONTAL STAB TIP UPPER PANEL ATTACHED NUT PLATE T-CAP IAW B767 SRM 51-40-02, PRIMED AND PAINTED AREAS OF REMOVED PAINT ON LEFT HORZ STAB TIP IAW B767 MM 51-21-10-307-802. ACFT WAS GROUNDED.

Part: STIFFENER — CORRODED (LE SLAT) · airframe 53,224 hrs · 42,092 cycles

NR 11 SLAT HAS CORROSION ON STIFFENER INSIDE 625CB COVE PANEL. REMOVED AND REPLACED CORD SPLICE P/N 114T4122-55. INSTALLED WITH HI-LOCKS IAW B767 SRM 51-40-02 PARA 7. ACFT WAS GROUNDED.

Part: SKIN — CORRODED (RT WING) · airframe 53,224 hrs · 42,092 cycles

SKIN BULGING AND POSSIBLE CORROSION AT RT WS 1025 UPPER SURFACE ABOVE OUTBOARD. AILERON, OUTBOARD OF PCA. REMOVED CORROSION AND REPAIRED AREA IAW REA B657-60384-MR. ACFT WAS GROUNDED.

Part: SUPPORT ANGLE — CRACKED (VERTICAL STAB) · airframe 53,224 hrs · 42,092 cycles

LEFT AND RIGHT OUTBOARD WEB SUPPORT ANGLES AT THE BOTTOM OF THE VERTICAL STABILIZER HAS 2 INCH CRACK ON EACH ANGLE. VIEWED THRU PANELS 324LL. REMOVED AND REPLACED ANGLES IAW 51-40-02 SRM, ACFT WAS GROUNDED.

Part: SPLICE — UNKNOWN (FUSELAGE) · airframe 53,224 hrs · 42,092 cycles

UPPER LEFT WEB SPLICE REQUIRES REPLACEMENT AT STA 1809 FABRICATED NEW SPLICE IAW REA B653-60391. INSTALLED IAW BOEING DWG 148T2740 B767 SRM CH 51-40-02 PG 7. ACFT WAS GROUNDED.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 53,244 hrs · 42,092 cycles

INTERCOSTAL STA 1562-1582 BETWEEN LEFT LONGERONS 1-2 FOUND CRACKED ON END. REMOVED DAMAGE ON INTERCOSTAL STA 1562-1562. FABRICATED & INSTALLED REPAIR IAW B767 SRM CH 51-70-11 FIG 1 & CH 51-40-02. ACFT WAS GROUNDED.

Part: STRUT — CRACKED (WING) · airframe 53,224 hrs · 42,092 cycles

NUMBER 5 SLAT OUTBOARD AUX TRACK OUTBOARD LOWER PANEL ATTACH STRUT SPLIT UNDER FORWARD NUT PLATE ON EDGE. REMOVED AND REPLACED NR 5 SLAT O/B AUX TRACK OUTBOARD LOWER PANEL ATTACH STRUT RIB IAW B767 SRM 51-40-02. ACFT WAS GROUNDED.

Part: STRUT — CORRODED (LT WING) · airframe 53,224 hrs · 42,092 cycles

NUMBER 2 SLAT OUTBOARD AUX INBOARD LOWER PANEL ATTACH STRUT CORRODED ADJACENT TO FORWARD HI-LOC. REMOVED AND REPLACED LWR STRUCTURE P/N IAW B767 SRM 51-40-02 PARA 7. ACFT WAS GROUNDED.

Part: STRUT — CRACKED (LT WING) · airframe 53,224 hrs · 42,092 cycles

NUMBER 3 SLAT INBOARD AUX TRACK OUTBOARD LOWER PANEL ATTACH STRUT SPLIT AT AFT END ON EDGE. INSTALLED NEW STRUT P/N IAW BOEING 767-200 SRM 51-40-02. ACFT WAS GROUNDED.

Part: RIB — CRACKED (VERTICAL STAB) · airframe 53,224 hrs · 42,092 cycles

VERTICAL STABILIZER LEADING EDGE PANEL 321C HAS A CRACKED SUPPORT RIB. SUPPORT RIB WAS REPAIR IAW B767-200 SRM 55-30-09. ACFT WAS GROUNDED.

Part: SKIN — DAMAGED (LT ELEVATOR) · airframe 53,224 hrs · 42,092 cycles

LEFT INBOARD ELEVATOR UPPER AND LOWER SKINS DAMAGED AT TRAILING EDGE APPROX 8 INCHES FROM OUTBOARD END. REPAIRED ELEVATOR IAW REA B627-60371-MR AND B767 SRM 55-20-01. ACFT WAS GROUNDED.

Part: WEB — CRACKED (VERTICAL STAB) · airframe 53,224 hrs · 42,092 cycles

WEB STIFFENER FORWARD OF STA 1755 ON BOTTOM WEB OF VERTICAL STABILIZER IS CRACKED IN BOTH INBOARD AND OUTBOARD OF CORNERS. REMOVED AND REPLACED WEB STIFFENER IAW B767 SRM 54-40-02. ACFT WAS GROUNDED.

Part: SUPPORT BEAM — CORRODED (LT WING) · airframe 53,244 hrs · 42,092 cycles

LEFT WING TRAILING EDGE PANEL SUPPORT BEAM ABOVE LEFT WHEEL WELL JUST AFT OF LANDING GEAR BEAM ASSY. CORROSION AROUND NUT PLATES. FABRICATED SUPPORT BEAM PER BOEING DWG 113T1633 MATERIAL BAC 1506-23-7075T6511 P/O 407827679. ACFT WAS GROUNDED.

Part: SUPPORT BEAM — CORRODED (LT WING) · airframe 53,224 hrs · 42,092 cycles

LEFT WING TRAILING EDGE PANEL SUPPORT BEAM ABOVE LEFT WHEEL WELL JUST AFT OF LANDING GEAR BEAM ASSY. CORROSION AROUND NUT PLATES. FABRICATED SUPPORT BEAM PER BOEING DWG 113T1633 MATERIAL BAC 1506-23-7075T6511 P/O 407827679. ACFT WAS GROUNDED.

Part: SKIN — CRACKED (FUSELAGE) · airframe 53,224 hrs · 42,092 cycles

A CRACK WAS INDICATED DURING AN HFEC OF THE PASSENGER ENTRY DOOR (L1) AT THE LWR AFT CORNER OF THE CUTOUT ON THE FUSELAGE SKIN, B STA 337.0, S-20L. REPAIRED CRACK IAW SRM 53-10-01. REPAIR MATERIAL: 2024 T3. ACFT WAS GROUNDED.

Part: ATTACH FITTING — CRACKED (TE FLAP) · airframe 53,136 hrs · 42,050 cycles

LOUD POPPING NOISE HEARD WHEN LEFT FLAP WAS EXTENDED OR RETRACTED. AT AFT WING SPAR STATION 908 FOUND REAR SPAR DEFLECTION CONTROL TRACK SUPPORT FOR OUTBOARD TRAILING EDGE FLAP BROKEN OFF AT SPAR SIDE LOWER LOBE ATTACH FITTING. REMOVED AND REPLACED OUTBOARD FLAP OUTBOARD TRACK ATTACH FITTING ON LEFT WING IAW B767 SRM 51-40-02, ACFT WAS GROUNDED.

Part: PBE — UNSERVICEABLE (CABIN) · airframe 50,797 hrs · 41,095 cycles

PBE LOST VACUUM SEAL. DEF DI 68682 CODE 27 DEFERRED IAW GMM & B767-2A PLACARD INSTALLED.

Part: HARNESS — MISSING (CABIN) · airframe 50,668 hrs · 41,056 cycles

ONE EACH DESCENT HARNESS MISSING AT THE SUPERNUMARY AREA. DEF # 68451. DEFERRED 1 EACH DESCENT HARNESS AT THE SUPERNUMARY AREA PER MEL 25-16-1-2. PLACARD INSTALLED MBCB 4/19/11. AIRCRAFT WAS NOT GROUNDED.

Part: INERTIA REEL — DEFECTIVE (CABIN) · airframe 50,562 hrs · 41,027 cycles

INERTIA REELS NOT PROPERLY STOWED. REPLACED INERTIA REELS FROM LOCATION 1 & 4 IAW B767 MM 25-61-03-4.

Part: INERTIA REEL — DEFECTIVE (CABIN) · airframe 50,555 hrs · 41,025 cycles

INERTIA REELS NOT PROPERLY STOWED. REPLACED 3 INERTIA REELS PER B767 AMM 25-61-03-4 IN SUPERNUMERARY AREA. AIRCRAFT WAS NOT GROUNDED.

Part: SMOKE GOGGLES — MISSING (COCKPIT) · airframe 50,465 hrs · 41,001 cycles

SECOND OBSERVER SEAT SMOKE GOGGLES MISSING. DEFERRED 2ND OBSERVER SEAT IAW ABX B767 MEL 25-11-2-1-2 CAT D, CODE 14, PLACARD INSTALLED. REPLACED 2ND OBSERVER SEAT SMOKE GOGGLES. PLACARDS REMOVED. AIRCRAFT WAS NOT GROUNDED.

Part: WARNING SYSTEM — MALFUNCTIONED (CARGO DOOR) · airframe 48,951 hrs · 3,757 cycles

ON INITIAL CLIMBOUT MAIN CARGO DOOR LIGHT WITH AUDIO WARNING ACTIVATED. NOTE: LIGHT WENT OUT ON LANDING. DEFERRED MAIN CARGO DOOR LIGHT IAW B767 MEL 52-71-1-2. VERIFIED MAIN CARGO DOOR CLOSED AND LOCKED. PLACARD INSTALLED.

Part: STRUCTURE — CRACKED (NLG WW) · airframe 48,716 hrs · 40,422 cycles

RBL 25 NOSE WHEEL WELL VERTICAL CHORD IS CRACKED. REPAIRED VERTICAL CHORD AT RBL 25 IAW 767 SRM 51-70-12 FIG 1 SH 4.

Part: STRUCTURE — CRACKED (NLG WW) · airframe 48,716 hrs · 40,422 cycles

LBL 25 NOSE WHEEL WELL VERTICAL CHORD AT STA 287 IS CRACKED. REPLACED LBL 25 VERTICAL CHORD AT STA 287 IAW 767 SRM 51-70-12 FIG 1 SH 4.

Part: FAILSAFE — CRACKED (FUSELAGE) · airframe 48,716 hrs · 40,422 cycles

LT FAIL SAFE STRAP CRACKED HORIZONTALLY AT LWR THRU BOLT OF INSP AREA. FAIL SAFE STRAP REPAIRED IAW REA B653-5868MR.

Part: FAILSAFE — CRACKED (FUSELAGE) · airframe 48,716 hrs · 40,422 cycles

RT FAIL SAFE STRAP CRACKED HORIZONTALLY AT LWR THRU BOLT OF INSP AREA. CRACK REPAIRED IAW REA B65-58685MR.

Part: FLASHLIGHT — DEFECTIVE (COCKPIT) · airframe 48,085 hrs · 40,117 cycles

COCKPIT EMERGENCY FLASHLIGHT IS DIM. REMOVED & REPLACED COCKPIT EMERGENCY FLASHLIGHT, OPS CHECKED GOOD.

Part: PIN — DAMAGED (LT BOGIE PIVOT) · airframe 46,013 hrs · 39,133 cycles

DURING COMPLIANCE WITH AD 2006-07-14, AMENDMENT 39-14541, ABX JOB CARD JEA32100002-001, THE LEFT MAIN LANDING GEAR BOGIE PIVOT PIN WAS FOUND TO HAVE BRONZE TRANSFER. REMOVED AND REPLACED LEFT MAIN LANDING GEAR BOGIE PIVOT PIN IAW B767 MM.

Part: CIRCUIT CARD — MALFUNCTIONED (WARNING SYSTEM) · airframe 44,553 hrs · 38,594 cycles

FIRE DETECTION BELL COMES ON INTERMITTENTLY ON ITS OWN, AND THEN WOULD NOT COME ON WHEN TESTED, VERIFIED. REMOVED AND RESEATED BELL CHIME CARD (M1000) IN P51 PANEL IAW B767 AMM 26-10-00 PERFORMED BITE PROCEDURE 26-16-00-10, NO PROBLEMS AT THIS TIME. FIRE WARNING SELF TESTED NORMAL AT THIS TIME. PER MAINT CONTROL DUE TO REPAIR HISTORY OF AURAL WARNING MODULE SERV NR 121, REPLACE MODULE PN 285T0385-5.

Part: ODOR — DETECTED (COCKPIT) · airframe 43,745 hrs · 38,286 cycles

FORWARD EQUIPMENT COOLING EICAS MESSAGE DISPLAYED AS WELL AS NO COOLING LIGHT. ACRID SMELL IN COCKPIT ABOUT 5 MINUTES BEFORE LIGHTS DISPLAYED. CREW REPORTED THIS HAPPENED JUST BEFORE LANDING. EQUIPMENT COOLING WAS IN OVERRIDE. DUE TO CONFIGURATION, THIS CONDITION MAY OCCUR. INSPECTED FORWARD EQUIPMENT COOLING AREA, UNABLE TO RECREATE DISCREPANCY.

Part: DRAG BRACE — CRACKED (RT MLG) · airframe 43,340 hrs · 38,134 cycles

RIGHT MAIN LANDING GEAR DRAG BRACE LUG HAD CRACK INDICATION REF: EA 32110006-001. REPLACED RIGHT MAIN LANDING GEAR IAW DC-9 MM.

Part: GIRT BAR — CONTAMINATED (ESCAPE SLIDE) · airframe 42,119 hrs · 37,686 cycles

DOOR SLIDING ARMING HANDLE DIFFICULT TO ARM. REMOVED DEBRIS AND DIRT FROM GIRT BAR CAM ENGAGEMENT PINS AND MECHANISM. CLEANED AREA AND OPERATED DOOR THROUGH SEVERAL CYCLES. OPS CHECKED GOOD IAW B767 AMM 52.

Part: CLAMP — MISALIGNED (A/C SYSTEM) · airframe 40,716 hrs · 37,168 cycles

WITH EQUIPMENT COOLING SELECTED TO OVERRIDE, COULD NOT MAINTAIN CABIN PRESSURIZATION IN AUTO OR MANUAL. WHEN EQUIP COOLING SELECTED BACK TO AUTO ALL SYSTEMS CHECKED OK. THE CREW DESCENDED THE AIRCRAFT AND WENT ON OXYGEN FOR A SHORT PERIOD OF TIME. FOUND LEFT HAND AC EXT CONNECTION ELBOW CLAMP MISALIGNED. REALIGNED CLAMP. LEFT HAND PNEUMATIC SUPPLY CHECK VALVE ABOVE EXT CONNECTION HAD A BLOWN GASKET. REPLACED GASKET. CLAMP AND GASKET LEAK CHECKED GOOD. FORWARD EQUIPMENT CHECKED GOOD IAW 21-58-00-5. AUTO CABIN PRESSURIZATION CHECKED GOOD IAW B 767 MM FIM 21-30-00.

Part: TUBE — WORN (FUSELAGE) · airframe 39,554 hrs · 36,768 cycles

FORWARD CARGO LOWER LOBE, BETWEEN STA. 325 - 347, LT BUTT LINE 21, LT BUTT LINE 48.65 AND RT BUTT LINE 44.45, 6 EACH TUBES WORN OUT. DAMAGED TUBES REMOVED AND NEW TUBES INSTALLED IAW SRM.

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

FORWARD CARGO LOWER LOBE BETWEEN STA 577 - 610, LBL - RBL 15, CORRODED SHEAR PANEL. CORRODED SHEAR PANEL REMOVED, NEW SHEAR PANEL INSTALLED IAW SRM 51-40-02.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 39,554 hrs · 36,768 cycles

FORWARD CARGO LOWER LOBE EXISTING REPAIRS ON UPPER CHORD OF BEAM AT STA 588, BL 45, FOUND DAMAGE. DAMAGED CHORD REMOVED AND NEW FRAME INSTALLED IAW SRM.

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

FORWARD CARGO LOWER LOBE, CORRODED SHEAR TIE AT STA 412, BETWEEN STRINGERS 39 LEFT - 39 RIGHT. CORRODED SHEAR TIE REMOVED AND INSTALLED NEW SHEAR TIE IAW SRM.

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

FORWARD CARGO LOWER LOBE, STA. 742, CORRODED SHEAR TIE, BETWEEN STR 38 - 39 LEFT. CORRODED SHEAR TIE REMOVED, NEW SHEAR TIE INSTALLED IAW SRM.

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

FORWARD CARGO LOWER LOBE, CORRODED SHEAR PANEL, BETWEEN STA 544-610, LBL 20 - 30 AND CRACKED. CORRODED AND CRACKED SHEAR PANEL. REMOVED AND REPLACED SHEAR PANEL IAW SRM.

Part: PANEL — SCRATCHED (FUSELAGE) · airframe 39,554 hrs · 36,768 cycles

FORWARD CARGO LOWER LOBE, DEEP SCRATCHES ON SHEAR PANEL BETWEEN STA 610 - 632, LBL 45. DAMAGED SHEAR PANEL REMOVED AND NEW SHEAR PANEL INSTALLED IAW SRM.

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

FORWARD CARGO LOWER LOBE CORRODED SHEAR TIES AT STA 434, BETWEEN LONG 36-37 LEFT AND RIGHT. CORRODED SHEAR TIE REPLACED WITH NEW SHEAR TIE IAW SRM.

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

FORWARD CARGO LOWER LOBE STA 742, CORRODED SHEAR TIE, BETWEEN STRINGER 39 LEFT - 39 RIGHT. CORRODED SHEAR TIE REMOVED, NEW SHEAR TIE INSTALLED IAW SRM.

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

FORWARD CARGO LOWER LOBE, CORRODED SHEAR TIE AT STA 742, BETWEEN STRINGERS 36 - 37 LEFT. CORRODED SHEAR TIE REMOVED, NEW SHEAR TIE INSTALLED IAW SRM.

Part: SKIN — CORRODED (LT WING SLAT) · corrosion level 2 · airframe 39,554 hrs · 36,768 cycles

LT WING SLAT NR 3 OSS 756.50, LE SKIN FOUND CORRODED ON FASTENER HEAD ATTACHING SKIN TO FORMER. REPAIRED AREA IAW REA B657-45505MR.

Part: SKIN — CORRODED (LT WING) · corrosion level 2 · airframe 39,554 hrs · 36,768 cycles

LT WING UPPER SKIN PANEL NR 1 AFT OF REAR SPAR ATTACHMENT, WHERE THE TRAILING EDGE PANELS ARE INSTALLED, FOUND CORROSION AT WING STATIONS 534.27 & 554, 811.20 & 852. REPAIRED AREA IAW REA B657-45500MR.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 39,554 hrs · 36,768 cycles

FORWARD FUSELAGE CABIN RIGHT SIDE, WL 251.8, STA 287, FOUND CRACK ON TEE CONNECT TO FRAME. CRACKED TEE REMOVED AND INSTALLED NEW TEE. REF SRM 53-10-16, FIGURE 1 AND BAC DWG NR 141T8330/-6 INSTALLATION.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 39,554 hrs · 36,768 cycles

DURING CHECK, 0.5 INCH LONG CRACK WAS FOUND AT SEC. 43 RT, STR. 17 RT, STA. 434. THE CRACK ORIGINATED AT THE FORWARD FASTENER HOLE IN STR. VERTICAL FLANGE. REPAIRED AREA IAW REA B653-45486MR.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 39,554 hrs · 36,768 cycles

FORWARD FUSELAGE CABIN LEFT SIDE, WL 251.8, STA 287. FOUND CRACK ON TEE CONNECT TO FRAME. CRACKED TEE REMOVED AND INSTALLED NEW TEE, FASTENERS IAW SRM, INSTALLATION.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 39,554 hrs · 36,768 cycles

STRINGER 19L, BETWEEN STA 632 AND STA 654, AFT SIDE OF EXISTING LAMP HAD CRACKS ON STRINGER. THE CRACKS LENGTH WERE APPROXIMATELY .5 INCHES FROM THE EDGE OF STRINGER. PERFORMED STRINGER REPAIR IAW SRM 53-30-03 AND SRM 53-00-03, FIGURE 201. PART OF STRINGER WITH CRACKS REMOVED AND THE AREA PROTECTED IAW SRM 51-10-02. THE PARTS INSTALLED IAW SRM 51-40-02.

Part: SKIN — GOUGED (FAIRING) · airframe 39,554 hrs · 36,768 cycles

NR 1 ENGINE STRUT UNDER WING FAIRING FOUND DEEP GOUGE ON SKIN AT NAC STATION 258 RT SIDE. REPAIRED AREA IAW REA B654-45455MR.