N125DL

Part: FAILSAFE — CRACKED (BS 859 FRAME) · airframe 83,839 hrs · 35,651 cycles

FUSELAGE, FRAME, STA 859.5, LT SIDE FAIL SAFE INNER CHORD/CRACK REPAIRED IAW ERA 532633-14.

Part: STRUCTURE — DAMAGED · airframe 83,839 hrs · 35,651 cycles

2 EACH HOLES DAMAGED ON INSIDE OF 1809 FWD CORD, COMMON TO THE SKIN ON LT SIDE BELOW LOWER DAMAGE.

Part: SUPPORT BEAM — DAMAGED · airframe 83,775 hrs · 35,632 cycles

NR 1 FLAP SUPPORT BEAM: HOLE DAMAGED ON INBD SIDE OF BEAM, AFT UPPER FASTENER OF SIDE BRACE MOUNT FITTING HOLE. C/W ERA 532696-01.

Part: SUPPORT BEAM — DAMAGED · airframe 83,775 hrs · 35,632 cycles

NR 1 FLAP SUPPORT BEAM 2 EA HOLES DAMAGED ON INBD SIDE, 2ND FROM AFT FASTENERS FWD OF LARGE BUSHING. C/W ERA 5326396-14.

Part: SUPPORT BEAM — CRACKED · airframe 83,775 hrs · 35,632 cycles

NR 8 FLAP SUPPORT BEAM "C" FASTENER HOLE INDICATE CRACKED C/W ERA 532817-14.

Part: BEAM — CRACKED · airframe 83,775 hrs · 35,632 cycles

BEAM CRACKED. REPAIRED IAW ERA 532683-14.

Part: SUPPORT BEAM — CRACKED (NR 7 FLAP) · airframe 83,775 hrs · 35,632 cycles

NR 7 FLAP SUPPORT BEAM CRACKED. REPAIRED IAW ERA 532683-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 83,775 hrs · 35,632 cycles

FUSELAGE SKIN IS CRACKED. EMANATING FROM UNDER AFT SCUFF PLATE OF L-1 DOOR AND PROGRESSING DOWN AND AFT. REPAIRED IAW SRM 53-10-01.

Part: SKIN — CRACKED (NR 1 NACELLE) · airframe 83,775 hrs · 35,632 cycles

NR 1 PYLON, OTBD SIDE STRUT ASSY. SKIN AT UPPER AFT CORNER OF 442AL ACCESS DOOR CUTOUT CRACKED. C/W PRI 532568-14.

Part: LIGHT — INOPERATIVE (COCKPIT) · airframe 79,832 hrs · 34,504 cycles

DURING SERVICE CHECK, FOUND COCKPIT EMERGENCY LIGHTS INOPERATIVE. MX REPLACED THE LIGHT ASSY AND BATTERIES. SYS OPERATION IS NORMAL.

Part: WIRE — DAMAGED (EMERGENCY LIGHT) · airframe 78,743 hrs · 34,185 cycles

SEAT 25 A/B RED AISLE EMERGENCY LIGHTS ARE INOPERATIVE. MX REPAIRED WIRES. SYS OPERATION IS NORMAL.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHT) · airframe 78,340 hrs · 34,078 cycles

EMERGENCY PATH LIGHTS AT ROW 41GF ARE INOPERATIVE. MX SECURED PATH LIGHT PLUG SYS OPERATION IS NORMAL.

Part: FITTING — DAMAGED (LONGERON) · airframe 77,745 hrs · 33,916 cycles

WHILE ACCOMPLISHING EA 01-499898-03 AD NEW LONGERON FITTING, WAS FOUND WITH SHORT EDGE MARGIN ON INBD FLANGE SIDE OF FITTING FASTENER HOLES. NEW REPLACEMENT LONGERON FITTING (PN 1114020-8) FABRICATED AND INSTALLED IAW PR1 509717-14 REV 0. DATED 19JAN13. REF NRC : 100-245 FINAL ER/A 509717-14AD DATED 07 FEB2013 STATEMENT OF COMPLIANCE WITH AIRWORTHYNESS STANDARDS STATES : THIS IS A CATAGORY B PERMANENT REPAIR AS DEFINED IN SRM 51-00-06 AND THIS REPAIR DOES NOT CHANGE ANY INSPECTION REQUIRMENT OF AD 2012-15-12.

Part: WASHER — MIGRATED (FITTING BOLTS) · airframe 77,745 hrs · 33,916 cycles

WHILE ACCOMPLISHMENT OF EA 01-499890-03AD ME12 WORK CARD STEP 30, FOUND TENSION BOLT'S SELF AUGMENT WASHER RIDING ON RADIUS OF INTERNAL BATHTUB FITTING. INSTALLATION OF NEW REPLACEMENT LONGERON FITTING TENSION BOLTS CARRIED OUT IAW PRI 509717-14, REV 1, REF NRC'S AND CARDS : 100-037, 100-245 AND EA 01-499898-03AD OPN NR 1201.

Part: WEB — MISREPAIRED (NR 1 PYLON) · airframe 77,745 hrs · 33,916 cycles

NR 1 PYLON LT UPPER WEB FOUND EXISTING REPAIR IAW ERA 267062-14 NOT IAW SRM AND UPON NDT INSPECTION FOUND CRACK AT ANTI-ICE DUCT CUT-OUT ON WEB. NR 1 PYLON UPPER SPAR WEB CRACKED AREA REPAIRED IAW PRI 510604-14, REV O AND REV 1. (ERA 267062-14)

Part: FLOORBEAM — CORRODED (BS 325) · airframe 77,745 hrs · 33,916 cycles

BS 325, FLOORBEAM UPPER TEE AT RBL25 FOUND CORRODED. EXISTING T-CHORD REPAIR FROM RBL8 TO RBL93. AREA PREVIOUSLY REPAIR IAW SRM 53-00-51, FIG 201, REPAIR 1. EXISTING CORRODED REPAIR UPPER T CHORD, REMOVED AND FABRICATED NEW UPPER T-CHORD INSTALLED IAW SRM 53-00-51, FIG 201, REPAIR 1.

Part: SKIN — MISREPAIRED (NR 1 NACELLE) · airframe 77,745 hrs · 33,916 cycles

HMV2, DURING ACCOMPLISHMENT OF EA 01-487658, REV A MEO1. FOUND NR 1 PYLON NS 150-180 RT SIDE ACCESS DOOR CUT OUT EXISTING REPAIR NOT IAW THE SRM EXISTING REPAIR DOUBLER AT NR 1 PYLON NACELLE STRUT SKIN ASSY RT SIDE ACCESS DOOR CUT OUT EXTERIOR. REMOVED AND NEW REPAIR DOUBLER INSTALLED IAW PRI 510626-14 REV ORIGINAL AND ERA 510626-14, REV ORIGINAL.

Part: SUPPORT — CRACKED (BS 654-742) · airframe 77,745 hrs · 33,916 cycles

FWD CARGO BETWEEN BS 654 AND 742 LT SIDEWALL UPPER SUPPORT. (STABILIZATION ANGLE) FOUND DAMAGED. FWD CARGO LT SIDE STABILIZATION ANGLE, PN, 143T5401-82 DAMAGED PORTION CUT AND REMOVED BET STA 654-113 TO STA 736 AND REPAIRED IAW PRI ER/A 510619-14, REV O NRC 100-177. (NRC 100-177)

Part: SUPPORT — CRACKED (AFT CARGO) · airframe 77,745 hrs · 33,916 cycles

AFT CARGO BS 1105-1280 LT UPPER SUPPORT FOUND DAMAGED. AFT CARGO LT SIDE STABILIZATION ANGLE, DAMAGED PORTION CUT AND REMOVED AND REPAIRED IAW PRI ER/A 510625-14, REV O AND REV I.

Part: SKIN — CORRODED (FUSELAGE) · airframe 77,745 hrs · 33,916 cycles

AFT CARGO BS 1200-1219 STRINGER 36R CAP JOINT SKIN CORROSION. REPAIRED IAW ER/A 509718-14, REV 0.

Part: STRINGER — CORRODED (AFT CARGO) · airframe 77,745 hrs · 33,916 cycles

AFT CARGO BS 1313, STR 35L FOUND CORRODED. STRINGER REPAIRED IAW ER/A 510073-14, REV ORIG.

Part: FLOORBEAM — CORRODED (BS 347) · airframe 77,745 hrs · 33,916 cycles

CABIN FLOORBEAM UPPER TEE AT BS 347 BET RBL 25 TO RBL 31. FOUND CORROSION. AREA OF FLOORBEAM IS PREVIOUSLY SECTIONAL CUT-OUT AT RBL3102 AND LBL 3102 AND REPAIRED IAW ER/A 458406-14 (REF: ACTS PP NO B767-53-27165). EXISTING REPAIRED CORRODED FLOORBEAM SECTION BET RBL 31.2 TO LBL 31.2 AT STA 347. REMOVED AND NEW FABRICATED REPAIR FLOORBEAM SECTION INSTALLED IAW ER/A 458406-14, REV ORIG REF: ACTS PP NR: B767-53-27165 DOCUMENT.

Part: FLOORBEAM — CORRODED (BS 347) · airframe 77,745 hrs · 33,916 cycles

CABIN FLOORBEAM UPPER TEE AT BS 347, RBL 25 TO 31 FOUND CORRODED. FLOORBEAM SECTION REMOVED AND NEW FABRICATED REPAIR FLOORBEAM SECTION INSTALLED IAW ER/A 458406-14, REV ORIG.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 75,271 hrs · 33,198 cycles

EMERGENCY EXIT LIGHT AFT R3 ARE INOPERATIVE. MAINTENANCE REPLACED BATTERY PACK. SYSTEM OPERATION IS NORMAL.

Part: FAILSAFE — CRACKED (FS 966) · airframe 73,796 hrs · 32,794 cycles

A CRACK WAS FOUND DURING INSPECTION OF THE FAILSAFE FITTING IN THE RT AND LT MAIN LANDING GEAR WHEEL WELL. REPAIR IAW 479305-14.

Part: WIRE — BROKEN (CABIN) · airframe 72,205 hrs · 32,372 cycles

EMERGENCY LIGHTS RED ON LAVATORY L2 ARE INOPERATIVE. MAINTENANCE FOUND WIRE BROKEN AT FLOOR LEVEL AND REPAIRED. SYSTEM OPERATION IS NORMAL.

Part: LIGHT — INOPERATIVE (SEAT 5C) · airframe 69,818 hrs · 31,742 cycles

PASSENGER SEAT 05C EMERGENCY LIGHTING FLOOR LIGHTS INOP. RESET SYS. OPS CK OK.

Part: FAILSAFE — CRACKED (BS 955) · airframe 68,704 hrs · 31,455 cycles

AT PSV INSPECTIONS PRE SI 01-086393-12AD FOUND THE FAILSAFE CRACKED BOTH LT AND RT SIDES AND REQUIRED TRIMMING IAW SB 767-53-0100 REV 1. UPON REMOVAL OF THE CUT SECTIONS CORROSION WAS NOTED ON THE FUSALAGE SKIN COMMON TO THE AREA TRIMMED NOTE THAT THE 2 LOWER FASTERNER HOLES REQUIRED SPOTFACING WITH A REPORTED DEPTHS OF 0.030" ERA 479079-14AD ISSUED.

Part: FAILSAFE — CRACKED (FUSELAGE) · airframe 68,704 hrs · 31,455 cycles

INSPECTIONS SI 01-086393-12AD FOUND CORROSION IN THE RT AND LT FAILSAFE STRAPS WHICH REQUIRED TRIMMING IAW SB INSTRUCTIONS UPON REMOVAL OF THE CUT SECTIONS CORROSIONS WAS NOTED ON THE FUSALAGE SKIN COMMON TO THE AREA TRIMMED OUT. PLEASE NOTE THAT THE DEPTH WAS 0.025" ERA 479080-14AD REV "O" IS ISSUED.

Part: FITTING — CORRODED (BS 955) · airframe 68,704 hrs · 31,455 cycles

WHILE ACCOMPLISHING INSPECTIONS OF THE FS 955 REAR SPAR BULKHEAD AND FAILSAFE STRAPS FOR CORROSION AND FATIGUE CRACKS IAW DAL SI01-086393-12AD CORROSION WAS FOUND ON THE RT SIDE BRACE FITTING AND FAILSAFE STRAPS BOTH SIDE BRACE AND FAILSAFE WERE REPLACED ON THE RT SIDE DUE TO CORROSION. ERA 478790-14AD WAS ISSUED TO COVER THE REPLACEMENT ON THE RT SIDE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 62,677 hrs · 29,402 cycles

MINOR SKIN BLENDS AT FS 1219-1270 ALONG S-21R TO S-26R.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 62,671 hrs · 29,399 cycles

SKIN BLENDS FS 1444 AND S-39R, AND FS 1448 AND S-38L. REPAIRED PER ER/A 459236-14 REV A.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 62,671 hrs · 29,399 cycles

MINOR SKIN BLENDS AT FS 1438 TO 1540, ALONG S-19L TO S-26L. REPAIRED PER ER/A 459229-14ADREVA.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 62,532 hrs · 29,338 cycles

FUSELAGE SKIN BLENDS, FS 1285, AND STR 36R. REPAIRED PER ER/A 459263-14 REV A.

Part: SKIN — DAMAGED (FS 1286 S32L) · airframe 62,490 hrs · 29,321 cycles

FUSELAGE SKIN BLENDS AT FS 1286.5 AND 32L DUE TO GROUND DAMAGE PER ER/A 459209-14 REV A.

Part: FITTING — CORRODED (BS 276) · airframe 61,029 hrs · 28,864 cycles

RT NLG TRUNNION BORE CORRODED AND TOOLING DAMAGE FOUND ON WEB. BORE OVERSIZED AND AN OVERSIZED BUSHING INSTALLED. TOOLING DAMAGE OVERSIZED AND A BUSHING INSTALLED.

Part: STARTER — INOPERATIVE (APU) · airframe 60,205 hrs · 28,576 cycles

STRONG SMELL NOTICED BOTH INSIDE AND OUTSIDE AIRCRAFT SMELL STARTED AFTER POWER TRANSFER TO APU AND PACKS WERE TURNED ON. GROUND PERSONNEL ALSO REPORTED STRONG SMELL AND REPORTED SMOKE COMING OUT OF AN APU VENT. INSP APU AREA FOUND STARTER MOTOR W/STRONG BURNT ELEC ODOR. REPLACED STARTER ALSO FOUND RELAY STUCK CLOSED K197 REPLACED K19 AND K117 RELAYS. ALSO, REPLACED APU BATT. RAN APU, OPS CK OK. REMOVED MCO/PLAC.

Part: SKIN — LIGHTNING STRIKE (FUSELAGE) · airframe 59,538 hrs · 28,292 cycles

AT HMV, LIGHTNING STRIKES WERE FOUND JUST AFT OF FS 347 AND ABOVE S33R AND REPAIRED PER SRM 53-00-01, FIGURE 201, REPAIR 14. THIS REPAIR IS LOCATED JUST ABOVE AND AFT OF A REPAIR INSTALLED PER ERA 387247-14. THE REPAIRS ARE LOCATED 13" APART. ERA 459155-14 DOCUMENTS THE PROXIMITY AND SETS UP ON GOING INSPECTIONS.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 59,533 hrs · 28,290 cycles

FIVE CRACKS WERE FOUND IN THE FS 347 FLOORBEAM UPPER CAP. THREE OF THE CRACKS EXTENDED INTO THE WEB. THE DAMAGE WAS FOUND AT HMV AND REPAIRED PER ERA 458406-14.

Part: SKIN — NICKED (FUSELAGE) · airframe 59,533 hrs · 28,290 cycles

AT HMV, SIX NICKS TO THE FUSELAGE SKIN WERE FOUND AND BLENDED PER SRM. THE RESULTING BLENDS EXCEEDED SRM ALLOWABLE LIMITS. ERA 459158-14 ACCOMPLISHED REPAIR.

Part: SKIN — NICKED (FUSELAGE) · airframe 59,533 hrs · 28,290 cycles

AT HMV, TWO NICKS WERE NOTED IN THE FUSELAGE SKIN AT FS 654 +4-+9 BETWEEN STR 35L AND 36L. THE RESULTING BLENDS EXCEEDED THE SRM ALLOWABLE DAMAGE REQUIREMENTS. ERA 459156-14 WAS ISSUED TO REPAIR THE DAMAGE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 59,533 hrs · 28,290 cycles

DAMAGE WAS DISCOVERED IN THE FUSELAGE SKIN AT FS 654 +22 TO +66 AND STR 3R - 4R THAT RESULTED IN TWO SRM REPAIRS 4.875" APART. A DTA WAS ACCOMPLISHED AND THE INSPECTION REQUIREMENTS WERE IMPLEMENTED PER ERA 459157-14.

Part: SKIN PANEL — CORRODED (FUSELAGE) · airframe 59,533 hrs · 28,290 cycles

CORROSION WAS FOUND AT FS 1585 AND STR 38R-39R, 148T3251-4 SKIN PANEL. THE CORROSION WAS FOUND AT HMV AND WAS REPAIRED PER ERA 458836-14.

Part: FRAME — CRACKED (FUSELAGE) · airframe 59,531 hrs · 28,289 cycles

A CRACK WAS FOUND ON THE INNER CHORD OF THE STA 903.5 FRAME. THE CRACK WAS TRIMMED OUT AND A REPAIR ANGLE WAS INSTALLED.

Part: FRAME — CRACKED (FUSELAGE) · airframe 59,531 hrs · 28,289 cycles

A CRACK WAS FOUND IN THE INNER CHORD OF THE STA 883.5 FRAME AT WL 190 ON THE RT SIDE. THE CRACK WAS TRIMMED OUT AND A REPAIR ANGLE WAS INSTALLED.

Part: WEB — CRACKED (NR 1 NACELLE) · airframe 59,531 hrs · 28,289 cycles

THE NR 1 STRUT MIDSPAR WEB WAS FOUND CRACKED. THE CRACKED WEB REINFORCED WITH A DOUBLER.

Part: SWITCH — OVERHEATED (MODULE) · airframe 52,387 hrs · 25,240 cycles

ON DESCENT STARTED TO DETECTED A SLIGHT BURNING ODOR, ELECTRICAL ODOR. CREW DECLARED AN EMERGENCY. FOUND GPWS MODULE OVERHEATED. REMOVED MODULE AND FORWARDED TO MCO AND PLACARD.

Part: SKIN — TOOL DAMAGE (FUSELAGE) · airframe 43,032 hrs · 20,669 cycles

DURING ACCOMPLISHMENT OF A SRM SKIN REPAIR, TOOLING DAMAGE OCCURRED TO STR 39L. THIS DOCUMENT PROVIDES A REPAIR OF BOTH THE STRINGER AND SKIN. THE DAMAGE IS LOCATED AT STA 355. CORRECTIVE ACTION: ER/A 397313-14

Part: SKIN — DAMAGED (FUSELAGE) · airframe 43,032 hrs · 20,669 cycles

AN EXISTING TIME LIMITED REPAIR WAS REMOVED AT STA 325 AND S-34R. THE TIME LIMITED REPAIR IS REPLACED AT THIS TIME WITH A PERMANENT REPAIR. ER/A 397247-14.

Part: WEB — CRACKED (CENTER WING) · airframe 43,032 hrs · 20,669 cycles

DAMAGE FOUND IN WEB OF THE LBL VERTICAL STIFFENER ON THE CENTER SECTION FRONT SPAR AT THE OVERWING FLOORBEAM TO VERTICAL STIFFENER JOINT. CRACKED PORTION OF WEB WILL BE REMOVED AND REPAIRED BY SPLICING IN NEW SECTION OF STIFFENER. ER/A 397281-14.

Part: FIRE DETECTOR — CHAFED (NR 1 ENGINE) · airframe 40,625 hrs · 19,509 cycles

AFTER TAKEOFF, RECEIVED LT ENG FIRE LOOP 1 EICAS MSG FOLLOWED BY LT ENG FIRE WARNING. REPLACED UPPER AFT LOOP AND REPAIRED CHAFED WIRING.

Part: COMPRESSOR — DIRTY (NR 2 ENGINE)

ACRID SMOKE SMELL WITH SMOKE DETECTORS GOING OFF ON TAKEOFF TO WT 314,000 LAND WEIGHT 310,000, OVERWEIGHT LANDING, DETECTORS SOUNDED APPROX THIRTY SECONDS THEN OFF. A/C RETURNED TO GATE. NO VISIBLE SMOKE IN CABIN OR COCKPIT. SMELL DETERMINED COMING FROM BOTHS ENGINES DUE TO COMPRESSOR WASHES. RAN BOTH ENGINES TWENTY MINUTES WITH PACKS ON, NO SMELL OR ODOR NOTICED, NO DETECTORS SOUNDED, NO OVERHEAT INDICATIONS, ALL A/C SYSTEMS OPERATE NORMAL

Part: PROX TARGET — MISSING (NR 12 LE SLAT)

ON APPROACH WHEN FLAPS 15 SELECTED GOT LEADING EDGE LIGHT WITH L/E SLAT ASSYM EICAS MSG. LANDED WITH FLAPS 20 USING ALT FLAP POSITION/SELECTOR. DUE TO LDG FLAPS 20 AT 170K, LT MAIN GEAR BRAKE TEMP WAS 5 AND RT MAIN GEAR WAS 6. LDG WT 290K LBS. HAD BDL EMERG TRUCKS CALLED OUT FOR HOT LDG, POS WHEEL/BRAKE FIRES. NOT NEEDED. PERF HIGH ENERGY STOP/HEAT DMG INSP, NO DAMAGE FOUND. FOUND MID EXTEND PROX TARGET FOR NR 12 SLAT SW S300 MISSING REF IPC 27-81-02-01 FIG 1, SHT 3, DETAIL D. REPLACED TARGET.

Part: WEDGE — DELAMINATED (NR 1 LE SLAT)

DELAMINATION WAS FOUND ON THE NR 1 L/E SLAT TRAILING EDGE WEDGE NEAR THE INB'D END. DELAM WAS APPROX 3 BY 6. REPAIRED PER ERA 364501-14AD.

Part: SKIN — DELAMINATED (NR 8 LE SLAT)

THE NR 8 SLAT WAS FOUND TO HAVE THE UPPER SKIN DELAMINATED. THE DELAMINATION IS A 3 INCH DIA CIRCLE, APPROX 4 FROM THE AFT EDGE OF THE TRAILING EDGE WEDGE. THE WEDGE IS MANUFACTURED WITH 0.016 5052-H38 FACE SHEETS WITH A METALLIC HONEYCOMB CORE PER BMS 4-6, TYPE 4.1-25.

Part: CONNECTOR — DIRTY (R1 DOOR)

EXTERIOR EMERGENCY LIGHT AFT OF R-1 DOOR INOP. RELAMPED. RIGHT OVERWING EXTERIOR EMERGENCY LIGHT INOP. CLEANED LIGHT CONTACT.

Part: APU — MALFUNCTIONED (AFT FUSELAGE)

ON TAXI OUT, TOWER NOTIFIED OF APU FIRE, NO COCKPIT INDICATION. DISCHARGED BOTTLE, INSPECTED APU AREA AND EXHAUST FOR DAMAGE AND SMOKE, NONE FOUND. INSPECTED TAIL SECTION AREA FOR DAMAGE, NONE FOUND. APU DEFFERED PER MEL 49-11-01A. SUSPECT TAIL PIPE FIRE, FERRIED TO LAX. REPLACED APU, ROUTED TO SHOP.

Part: BATTERY PACK — DISCHARGED (CABIN)

NR 1 DOOR LEFT AND RIGHT EXIT EMERGENCY LIGHTS ARE INOPERATIVE. REPLACED BATTERY PACK, CHECKS GOOD.

Part: SKIN — DELAMINATION (RT TE FLAP)

FOUND ON I-2 LTR CK, DELAMINATION ON RT O/B FLAP LOWER SURFACE. REPAIRED PER SRM 57-53-01.

Part: TE WEDGE — DAMAGED (TE FLAP)

FOUND ON I-2 LETTER CHECK, 2 HOLES BOTTOM OF T/E WEDGE FLAP. REPAIRED PER SRM 57-53-01.

Part: SKIN — DENTED (LT TE FLAP)

DURING HMV, LT I/B T/E FLAP WAS FOUND TO HAVE TEMPORARY REPAIRS 12 INCHES TO 37 INCHES, AND 88 INCHES TO 94 INCHES FROM I/B END. MADE BONDED REPAIRS PER B767 SRM 57-53-01.