N391CM

Part: SMOKE DETECTOR — INOPERATIVE (ZONE 200) · airframe 59,424 hrs · 24,251 cycles

ON PRE-FLIGHT CHECK, FOUND MAIN CARGO SMOKE DETECTOR 3A INOP. REMOVED AND REPLACED MAIN CARGO SMOKE DETECTOR 3A PER MM 26-14-01-OPS CHKD OK. A/C REMAINS ETOPS 180. AIRCRAFT RETURNED TO SERVICE.

Part: A/C PACK — INOPERATIVE (ZONE 100) · airframe 59,074 hrs · 24,115 cycles

RT PACK INOP AT PUSH BACK. AIRCRAFT RETURNED TO BLOCKS (BTB). MAINTENANCE DEFERRED RT PACK IAW ABX-21-51-1-1. A/C RETURNED TO SERVICE.

Part: EXTINGUISHER — LOW PRESSURE (ZONE 200) · airframe 59,048 hrs · 24,100 cycles

DURING SERVICE CHECK FOUND COCKPIT PORTABLE FIRE EXTINGUISHER GETTING LOW REMOVED AND REPLACED PORTABLE FIRE EXTINGUISHER IAW B767 AMM 26-26-02-024-015-001/26-26-02-434-020-001. RETURNED AC TO SERVICE.

Part: WARNING LIGHT — ILLUMINATED (ZONE 800) · airframe 58,923 hrs · 24,046 cycles

DURING TAXI, MAIN CARGO DOOR LIGHT ILLUMINATED WHILE STARTING ENGINES. AIRCRAFT RETURNED TO BLOCKS. (BTB) MAINTENANCE DEFERRED IAW MEL C ABX-52-32-1-3. AIRCRAFT RETURNED TO SERVICE

Part: DOOR — NOT CLOSED (ZONE 800) · airframe 58,821 hrs · 24,007 cycles

DURING TAXI AFTER LEFT ENGINE START MASTER WARNING & MAIN CARGO DOOR LIGHT ILLUMINATED. A/C RETURNED TO THE GATE (BTB) AND MTX GROUNDED AC. FOUND MAIN CARGO DOOR WAS NOT COMPLETELY CLOSED CLOSED DOOR REMAINDER OF THE WAY LIGHT EXTINGUISHED IAW B767 AMM 52-32-00. MTX RETURNED AC TO SERVICE .

Part: FIRE DETECTOR — SHORTED (ZONE 500) · airframe 58,288 hrs · 23,800 cycles

LEFT ENGINE FIRE WARNING DURING TAXI OUT, A/C RETURNED TO GATE (BTB) AND MTX GROUNDED A/C. MTX TROUBLE SHOT AND REMOVED AND REPLACED AFT LOWER AND UPPER FIRE LOOPS ON #1 ENGINE AS PER AMM 26-11-02, SYSTEM CHECKS GOOD, GROUND ENGINE CHECKS GOOD, AIRCRAFT RELEASED NO ETOPS MTX RETURNED A/C TO SERVICE PN LOWER AFT 901907 SN 1608 TSI 36.0 TSO 36.0

Part: WARNING MESSAGE — ILLUMINATED (LT A/C PACK) · airframe 58,149 hrs · 23,740 cycles

DURING TAXI OUT, LT PACK TEMP CAUTION ON PACK. AIRCRAFT RETURNED TO BLOCKS. (BTB) DEFERRED LT PACK IAW MEL ABX 21-51-1-1. MAINTENANCE PROCEDURES C/W. AIRCRAFT RELEASED NO ETOPS. MBCB: 4/27/25. AIRCRAFT RETURNED TO SERVICE.

Part: STARTER — MALFUNCTIONED (ZONE 400) · airframe 57,633 hrs · 23,536 cycles

DURING TAXI WHILE STARTING #2 ENGINE EGT EXCEEDANCE OF 750 DEGREES DURING START WITH START SELECTOR IN BOTH, A/C RETURNED TO THE GATE (BTB) AND MTX GROUNDED AC . MTX PERFORMED VISUAL INSPECTION ON #2 ENGINE, NO DISCREPANCIES OR DAMAGE FOUND AND USED FIM (71-11 FAULT CODE DIAGRAM B. ENGINE OK PER AMM 71-00-00 PAGE 217, FIG 2106 71-00-00-99. AIRCRAFT REMAINS NO ETOPS.AND RETURNED AC TO SERVICE .

Part: STARTER — FAILED (LT ENGINE) · airframe 57,386 hrs · 23,426 cycles

ON TAXI OUT DURING LH ENGINE START LEFT ENGINE WOULD NOT START AC RETURNED TO GATE (BTB) AND MTX GROUNDED AC . MTX PERFORMED ENGINE START AF #1 ENGINE IAW 71-00-00. NO DEFECTS NOTED A/C REMAINS ETOPS 180 AC RETURNED TO SERVICE

Part: TRANSPONDER — FAULTED (ZONE 100) · airframe 57,328 hrs · 23,401 cycles

DURING TAXI OUT ATC WAS UNABLE TO RECEIVE TRANSPONDER . AC RETURNED TO THE GATE (BTB) AND MTX GROUNDED AC . MTX PERFORMED A SYSTEM TEST OF THE TCAS SYSTEM AND ATC WAS ABLE TO PICK UP THE IDENT, IAW B 767 AMM 34-45-00. NO FURTHER DEFECTS NOTETED . MTX RETURNED AC TO SERVICE .

Part: COMPUTER — MALFUNCTIONED (ZONE 100) · airframe 56,549 hrs · 23,077 cycles

DURING TAXI OUT ELEVATOR FEEL STATIS MESSAGE CAME ON ONCE HYDRAULIC PUMP TURNED ON . A/C RETURNED TO THE GATE AND MTX GROUNDED A/C . TROUBLE SHOT AND REMOVED AND REPLACED ELEVATOR FEEL COMPUTER IAW B767 AMM 27-31-19 OPS CHECK GOOD , MTX RETURNED A/C TO SERVICE .

Part: IRU — FAULTED (LEFT) · airframe 56,403 hrs · 23,019 cycles

DURING TAXI SPLIT IRS OPERATION (LEFT IRU , ILLUM. AC RETURED TO GATE AND MAINTENANCE GROUNDED AC .AND DEFERRED LH IRU IAW ABX-MEL 34-21-1-1-2A AND RETURNED AC TO SERVICE ,AC DEPARTED.

Part: SHUTOFF VALVE — INOPERATIVE (RT EINGINE) · airframe 56,114 hrs · 22,904 cycles

RT ENGINE HPSOV MSG DURING CRUISE FLIGHT. (REASON FOR DIVERSION TO IND: HPSOV MESSAGE (NO ICING)- ICING AT CVG/JFK) ACCOMPLISHED THUMB TEST ON HPSOV FROM CONTROLLER SIDE OF SENSE LINE, NO FAULTS PRESENT. REPLACED HPSOV IAW B767 AMM 36-11-07 AND RH BLEED CONTROL CARD IAW B767 AMM 36-11-12. LEAK CHECKS GOOD. ACCOMPLISHED ENGINE RUNS TO BLEED SHIFT LIGHT. BLEED SHIFT OPERATES NORMAL. BITE CHECKED AIR SUPPLY BITE MODULE, NO FAULTS PRESENT IAW B767 AMM 36-23-00. VERIFIED OPERATION OF RH THRUST REVERSER IAW B767 AMM 78-31-00. VERIFIED A/C RELEASED ETOPS ETOPS 180.

Part: PLUG — INSTALLED (HPC CONNECTOR) · airframe 55,983 hrs · 22,859 cycles

DURING PUSH BACK ,L ENG HPSOV EICAS STATUS MESSAGE L ENG BLEED LIGHT, L+R DUCT LEAK LIGHTS ALL ILLUMINATED AFTER ENGINE WERE STARTED PACKS + BLEEDS TURNED OFF PER QRH + LIGHTS STAYED ILLUMINATED ENGINES SHUT.AC RETURNED TO GATE AND MAINTENANCE GROUNDED AC , T/S AND FOUND HPC SHORTING PLUG INSTALLED ON HPC CONNECTOR. REMOVED AND STOWED SAME PER MEL MPM 36-11-2. CONDUCTED ENGINE RUNS PER AMM 71-00-00. PNEUMATICS SYSTEM OK. CONDUCTED WING/BODY DUCT LEAK OPERATIONAL TEST PER AMM 26-18-00. TEST OK A/C VERIFIED ETOPS 180. RETURENED AC TO SERVICE . AND DEPARTED

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 55,208 hrs · 22,593 cycles

" LOCK AT STATION 1190,RBL 33.00, MISSING ROLLER, POSITION LIMITED TO D11 7299 AND POS D12 6987 DEFERRED LOCK IAW MEL ABX-25-58-1A . AC LEFT BLOCKS AND WAS CALLED BACK FOR PAPERWORK ISSUES. CORRECTED PAPERWORK AND AC RETURNED TO SERVICE .

Part: SOLENOID — DEFECTIVE (RIGHT ENGINE) · airframe 54,035 hrs · 22,143 cycles

UPON INIATING THE START OF THE RIGHT ENGINE, THE RT ENGINE FUEL VALVE LIGHT ILLUMINATED AT APPROXIMATELY PASSING 10%. DISCONTINUED START. FUEL CONTROL SWITCH NEVER LEFT CUTOFF. POS. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE RAN #2 ENGINE VERIFIED THE PROBLEM. R+R #2 ENGINE FUEL SHUT OFF SOLENOID VALVE PER AMM 73-21-14. RUN #2 ENG PER AMM 71-00-00 OPS CHECK AND LEAK CHECK OK. #2 ENG SHUT DOWN NORMAL. AMM 71-00-00. A/C RETURNED TO SERVICE.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 53,532 hrs · 21,964 cycles

CAPTAIN ALTIMETER OFF FLAG APPEARED DURING TAXI. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE REMOVED AND RESEATED CAPT ALTIMETER CANNON PLUG OPS NORMAL OF CAPT ALTIMETER PER B767 AMM 34-13-01 NO DEFECTS AC IS RVSM COMPLIANT. AIRCRAFT RETURNED TO SERVICE.

Part: NONE — NONE (NONE) · airframe 52,721 hrs · 21,721 cycles

RABBIT STRIKE ON T/O ABORTED 120KTS. AIRCRFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. INSPECTION C/O IAW AMM 05-41-01 NO DEBRIS FOUND, NO DAMAGE. SATISFACTORY. AIRCRAFT RETURNED TO SERVICE

Part: CONTROL MODULE — FAULTY (STAB TRIM) · airframe 52,388 hrs · 21,629 cycles

DURING TAXI OUT STAB TRIM CAUTION MSG AND STAB TRIM STATUS MSG CAME ON. AIRCRAFT BACK TO BLOCK AND MESSAGES DISAPPEARED AFTER LEFT ENGINE WAS SHUTDOWN. AIRCRAFT GROUNDED BY MAINTENANCE. MAINTENANCE PERF MCDP TEST 65 TEST PASSED. PERF MCDP 30/40 FAULT RETURNED, FAULT ON SAM FOR R FSPM . REMOVED AND REPLACED R FSPM OPS CK GOOD TRANSFERRED TO MEL 27-41-2A, MBCB 11/05/22 MX PROCEDURES 27-41-2 C/W PLACARDS INSTALLED ALL PER AMM 27-58-01/ AMM 22-00-02. AIRCRAFT RETURNED TO SERVICE.

Part: NONE — NONE · airframe 52,308 hrs · 21,599 cycles

DURING AICRAFT PUSHBACK A HYDRAULIC LEAK WAS NOTICED OVER RIGHT MAIN GEAR. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE FOUND "O" RING LEAKING ON ANTISKID VALVE. MAINTENANCE REMOVED AND REPLACED O-RING ON ANTISKID VALVE IAW AMM 20-10-19 LEAK CHECK GOOD. LEAK CODE 600-9-B. AIRCRAFT RETURNED TO SERVICE.

Part: UNKNOWN — UNKNOWN · airframe 52,194 hrs · 21,562 cycles

AIRCRAFT OVERBURNED BY 4000+ LBS ENROUTE.AIRCRAFT DIVERTED TO BOS. AIRCRAFT WAS GROUNDED BY MAINTENANCE. MAINTENANCE PERFORMED VISUAL INSPT, NO LEAKS. COMPLIED WITH FUEL QUANTITY BITE TEST PER FIM 28-41 FAULT TREE 841. AIRCRAFT RELEASED NO ETOPS, BITE TEST GOOD, AIRCRAFT RETURNED TO SERVICE.

Part: THRUST REVERSER — CORRODED · corrosion level 3 · airframe 51,520 hrs · 21,336 cycles

ENG #1 , R/H SIDE, THRUST REVERSER - BEAVERTAIL, NAC STA 232; DURING MAINTENANCE INSPECTION AT IAI, AN EXISTING DEEP CORROSION DAMAGE WAS FOUND ON THE THRUST REVERSER - BEAVERTAIL.

Part: REPAIR — DISCOVERED · airframe 51,520 hrs · 21,336 cycles

LEADING EDGE SKIN, RIGHT HORIZONTAL STABILIZER, LES 342.677 TO 346.177 AND LES 401.577 TO 405.07: DURING CONVERSION PROCESS, DISCOVERED (2 EA) EXISTING (UNDOCUMENTED 3.5” DIAMETER CIRCULAR) LEADING EDGE REPAIRS LOCATED ON THE RIGHT HORIZONTAL STABILIZER BETWEEN APPROXIMATE LES 342.677 TO 346.177 AND LES 401.577 TO 405.07. A REVIEW OF THE PREVIOUS OPERATOR’S RECORDS WAS ACCOMPLISHED FOR REPAIR INSTALLATION AND APPROVAL DOCUMENTATION WITHOUT SUCCESS. BOTH REPAIRS WERE REMOVED AND THE UNDERLYING/EXPOSED HONEYCOMB WAS INSPECTED FOR DEFECTS AND A “T-A-P-TEST” WAS ACCOMPLISHED FOR DELAMINATION AT EACH AREA WITH NO DEFECTS REPORTED. THE LEADING EDGE ASSY (P/N 184T1008-2) IS CONSTRUCTED OF A 2024-T3 (0.090”) ALUMINUM CLAD SHEET SKIN (QQ-A-250/5) WITH ALUMINUM HONECOMB CORE (BMS4-6 CLASSII, TYPE 6.0-37, FORM B, 0.50 THICK) WITH A 2024-T3 BARE SHEET (0.016”) INNER FACE SHEET (QQ-A-250/4).

Part: SKIN — DENTED · airframe 51,520 hrs · 21,336 cycles

DURING MAINTENANCE INSPECTION AT IAI, DOCUMENTED DENT (CUSTOMER FAIL NO: 81-78-ET148) WAS FOUND ON ENG #1 EXHAUST EXTERNAL SKIN BETWEEN 8 TO 9 O’CLOCK AT NAC STA 348.246. THE DENT WAS MEASURED AND FOUND BEYOND SRM 54-42-30 ALLOWABLE DAMAGE 1 NOTE “N” LIMITS.

Part: NONE — NONE · airframe 51,520 hrs · 21,336 cycles

DURING MAINTENANCE INSPECTION AT IAI, UNDOCUMENTED WELDING PATCH REPAIR WAS FOUND ON ENG #2 EXHAUST EXTERNAL SKIN AT 8 O’CLOCK BETWEEN NAC STA 318 TO 320. THE PATCH DIAMETER WAS MEASURED AND FOUND 2.3”.

Part: ACOUSTIC PANEL — DENTED · airframe 51,520 hrs · 21,336 cycles

DURING MAINTENANCE INSPECTION AT IAI, TWO (2) ADJACENT DENTS WERE FOUND ON ENG #2 INLET COWL ACOUSTIC PANEL PERFORATED SKIN BETWEEN 8 TO 9 O’CLOCK.

Part: SKIN — INADEQUATE · airframe 51,520 hrs · 21,366 cycles

STA 1870.45 – STA 1875.45, 16 INCH LEFT FROM BL 0.0: DURING MAINTENANCE INSPECTION AT IAI, AN EXISTING UNDOCUMENTED REPAIR WAS FOUND ON THE EXTERNAL FUSELAGE SKIN AT DATUM LOCATION. SEE RFTA 02815-0227 FOR MORE INFORMATION.

Part: THRUST REVERSER — DAMAGED · airframe 51,520 hrs · 21,336 cycles

ENGINE # 2, OUTBD THRUST REVERSER, NAC STA 249.5, 5 O’CLOCK: DURING MAINTENANCE INSPECTION AT IAI, AN EXISTING EDGE REPAIR WAS FOUND, ON THE AFT EDGE OF THE DATUM THRUST REVERSER.

Part: FAIRING — INADEQUATE · airframe 51,520 hrs · 21,336 cycles

ENGINE # 1, OUTBD & INB THRUST REVERSERS, UPPER & LOWER FAIRINGS: DURING MAINTENANCE INSPECTION AT IAI, MULTIPLE EXISTING UNDOCUMENTED REPAIRS WERE FOUND ON THE UPPER AND LOWER FAIRINGS OF BOTH THRUST REVERSERS.

Part: COWLING — INADEQUATE · airframe 51,520 hrs · 21,336 cycles

ENGINE #1, INBD CORE COWL, EXISTING REPAIR: DURING MAINTENANCE INSPECTION AT IAI, AN EXISTING UNDOCUMENTED REPAIR WAS FOUND. THE REPAIR WAS REMOVED AND AREA WAS INSPECTED.

Part: FAIRING — INADEQUATE · airframe 51,520 hrs · 21,336 cycles

ENGINE #2, OUTBD & INBD THRUST REVERSERS, UPPER AND LOWER FAIRINGS, EXISTING REPAIRS: DURING MAINTENANCE INSPECTION AT IAI, SEVERAL EXISTING UNDOCUMENTED REPAIRS WERE FOUND ON BOTH THRUST REVERSERS INSTALLED ON ENGINE # 2. IAI NRC: M0203 L/H STA 206.5-210.5; M0204 L/H STA 241-246; M0212 R/H STA 206.5-210.5; M0213 R/H 241.5-246.5 M0214 L/H STA 205-209; M0215 L/H STA 201.2-214.2.

Part: SKIN — INADEQUATE · airframe 51,520 hrs · 21,336 cycles

: FUSELAGE SKIN BETWEEN STA 246 AND STA 266.5 AND BETWEEN STR 25L AND STR 28L: DURING CONVERSION AT IAI, SHOP FOUND AN EXISTING REPAIR IN FUSELAGE SKIN AT STA 250, S-26L, COMMON TO LAP SPLICE AND 4 INCHES AWAY FROM BUTT SPLICE. EXISTING REPAIR SIZE: 6.0” X 4.0”.

Part: ACOUSTIC PANEL — DENTED · airframe 51,520 hrs · 21,336 cycles

ENGINE # 2, INLET COWL ACOUSTIC PANEL, PERFORATED SKIN: DURING MAINTENANCE INSPECTION AT IAI, DENT WAS FOUND WITH NICK ON THE INNER BARREL ACOUSTIC PANEL OF INLET COWL #2 ENG LOCATED AT 3 TO 4 CLOCKWISE AND 4” FROM EDGE PANEL.

Part: COWLING — INADEQUATE · airframe 51,520 hrs · 21,336 cycles

ENGINE #2, OUTBD & INBD CORE COWLS, EXISTING REPAIRS: DURING MAINTENANCE INSPECTION AT IAI, THERE UNDOCUMENTED REPAIRS WERE FOUND. ALL REPAIRS WERE REMOVED AND THE AREAS WERE INSPECTED.STA 246 TO STA 251 12" O'CLOCK ; NAS STA 299.7 TO STA 304.5 BT 2-3 CLOCWISE; NAS 301.6 TO STA 304.5

Part: SKIN — STUCK · airframe 51,520 hrs · 21,336 cycles

STA 1542 STR-39L, STA1461 STR-38L, STA1654.5 STR-36R, STA 1197+110 STR-36R: DURING MAINTENANCE INSPECTION MULTIPLE LIGHTNING STRIKES WERE FOUND ON EXTERNAL FUSELAGE SKINS AT DATUM LOCATIONS. THE DAMAGES WERE BLENDED OUT AS REQUIRED, AND NDT HAS PERFORMED REMAINING MATERIAL THICKNESS MEASUREMENTS AND NO LOSSES WERE DETECTED. HOWEVER, THE BLEND OUTS ARE AMONG THE FASTENERS AREAS THAT PRIHIBITED PER SRM 53-00-01, AD1, DETAIL II.

Part: NONE — NONE · airframe 51,520 hrs · 21,336 cycles

STA 132.5 – STA 172.5, ABOVE STR-21L: DURING MAINTENANCE INSPECTION AT IAI, MULTIPLE EXISTING UNDOCUMENTED BLEND OUTS WERE FOUND ON THE EXTERNAL FUSELAGE SKIN. ALSO, A GOUGE WAS FOUND ON THE EDGE OF THE DATUM SKIN, STA 132.5.

Part: NONE — NONE · airframe 51,520 hrs · 21,336 cycles

ENGINE # 1 LH CORE COWL HAT FRAME NAC STA 303.75, MID LOWER AREA: DURING THE MAINTENANCE INSPECTION AT IAI, A 1.2 INCH CRACK WAS FOUND ON THE ENG # 1 L/H CORE COWL AFT HAT FRAME P/N 224-2318. THE AFT HAT FRAME FALLS UNDER ZONE CC2 AS PER TABLE 101 B767-300 SRM 54-45-01 ALLOWABLE DAMAGE 1 WHICH HAS NO ALLOWABLE DAMAGE FOR CRACKS. WE WANTED TO APPLY B767-300 SRM 54-45-01 REPAIR 4 ALUMINIUM HAT FRAME REPAIR, HOWEVER DUE TO THE CRACK END BEING LESS THAN 0.65 INCH FROM THE RADIUS OF THE FRAME MOUNTING FLANGE, AS MENTIONED IN APPLICABILITY NOTE A AND SECTION A-A FIGURE 201, THIS REPAIR IS NOT APPLICABLE FOR THIS DAMAGE.

Part: NONE — NONE · airframe 51,520 hrs · 21,336 cycles

EXTERNAL FUSELAGE SKINS, STA 390, STR-24R; STA 396, STR-22R; STA 1420, STR-31L – STR-32L; STA 1351, STR-31R: DURING MAINTENANCE INSPECTION AT IAI, A FEW BLENED OUTS WERE FOUND ON FUSELAGE SKINS 141T3330, 146T3230, 146T3530 AT LOCATIONS AS MENTIONED ABOVE. SEE RFTA 02815-0205 FOR MORE INFORMATION.

Part: NONE — NONE · airframe 51,520 hrs · 21,336 cycles

EXTERNAL FUSELAGE SKIN, SECTION 41, STA 168, BELOW STR-21R; 141T3211: DURING MAINTENANCE INSPECTION AT IAI, AN EXISTING BLEND OUT WAS FOUND ON THE EXTERNAL FUSELAGE SKINS AT STA 168, BELOW STR-21R. THE AFFECTED FASTENER IN THE BLEND OUT AREA WAS REMOVED. AFTER INSPECTION IT WAS FOUND THE DEPTH OF BLEND OUT IS WITHIN SRM 53-00-01, AD1 LIMITS, LESS THAN 15% MAX OF LOSS, HOWEVER, THERE ARE FASTENERS ARE IN THE BLEND OUT AREA, THAT PROHIBITED PER SRM 53-00-01, AD1, DETAIL II. THE SKIN MADE OF 2024-T3 X 0.080-INCH THICKNESS ALUMINUM CLAD SHEET AS PER SRM 53-60-01, IDENT 1.

Part: NONE — NONE · airframe 51,520 hrs · 21,336 cycles

EXTERNAL FUSELAGE SKIN - STA 1261.5, STR 28R-STR 29R:DURING MAINTENANCE INSPECTION AT IAI, AN EXISTING BLEND OUT WAS FOUND , COMMON TO THE FASTENER, THAT IS NOT ALLOWED PER B767-300 SRM 53-00-01, AD1.

Part: NONE — NONE · airframe 51,520 hrs · 21,336 cycles

L/H WING, OUTBD TRAILING EDGE FLAP (P/N: 113T3100-95G, S/N: 000251): DURING MAINTENANCE INSPECTION AT IAI, AN UNDOCUMENTED REPAIR WITH LIGHT CORROSION WAS FOUND ON THE LOWER SKIN PANEL OF THE FLAP AT APPROXIMATELY OTEF 300.88. AFTER THE REPAIR WAS DIMANTLED, A BLEND OUT WAS FOUND ON THE LOWER SKIN PANEL AND ITS MINIMUM REMAINING THICKNESS WAS FOUND 0.092” (0.008”, 8% REMOVED). SEE RFTA 02815-0225 FOR THICKNESS GRID PERFORMED BY NDT. BLEND OUT SIZE: 8” X 1.5”.

Part: NONE — NONE · airframe 51,520 hrs · 21,336 cycles

TAILCONE ASSY, STA 1943.50 TO STA 1952.00: DURING MAINTENANCE INSPECTION MULTIPLE LIGHTING STRIKES WERE FOUND ON TAILCONE ASSY 148T8301-1 (148T8301-1 7 -2 SKINS). THE DAMAGES WERE BLENDED OUT AS REQUIRED, AND NDT HAS PERFORMED REMAINING MATERIAL THICKNESS AND NO LOSSES WERE DETECTED. REFER TO RFTA 02815-0245.

Part: NONE — NONE · airframe 51,520 hrs · 21,336 cycles

EXTERNAL FUSELAGE SKIN, SECTION 46, STA 1485, STR-37R; 146T3240: DURING MAINTENANCE INSPECTION AT IAI, AN EXISTING BLEND OUT WAS FOUND ON THE EXTERNAL FUSELAGE SKINS AT STA 1485, STR-37R. THE AFFECTED FASTENER IN THE BLEND OUT AREA WAS REMOVED. AFTER INSPECTION IT WAS FOUND THE DEPTH OF BLEND OUT IS WITHIN SRM 53-00-01, AD1 LIMITS, LESS THAN 15% MAX OF LOSS, HOWEVER, THERE ARE FASTENERS ARE IN THE BLEND OUT AREA, THAT PROHIBITED PER SRM 53-00-01, AD1, DETAIL II. THE SKIN MADE OF 2024-T3 X 0.160-INCH THICKNESS ALUMINUM CLAD SHEET CHEM – MILLED OR MACHINED TO 0.056 INCH AS PER 767-300 SRM 53-60-01, IDENT 1.

Part: NONE — NONE · corrosion level 2 · airframe 51,520 hrs · 21,336 cycles

HORIZONTAL STABILIZER, CENTER SECTION, UPPER SKIN, RBL 28.33, STR-U10: DURING MAINTENANCE INSPECTION, CORROSION DAMAGE WAS FOUND AT DATUM LOCATION AS MENTIONED ABOVE. THE CORROSION WAS REMOVED AND REMAINING MATERIAL THICKNESS MEASUREMENT WAS PERFORMED.SEE RFTA 02815-0244. THERE IS A LOSS OF 29% IN THICKNESS, 0.099 INCH OF 0.140 INCH AS MENTIONED.

Part: NONE — NONE · airframe 51,520 hrs · 21,336 cycles

FUSELAGE FRAME, STA 1461, STR-4R – STR-5R: DURING MAINTENANCE INSPECTION AT IAI, CRACKS WERE FOUND AT DATUM LOCATION. SEE RFTA 02815-0223. THE DAMAGE WAS REMOVED PER J/C MF02815R0223-01 INSTRUCTIONS. THE CUTOUT IS ABOVE 1.99X0.73 INCH.