N976DL

Part: WIRE — SPARKS (WINDSHIELD) · airframe 74,130 hrs · 55,043 cycles

SPARKS FROM CAPTAINS WINDSHIELD, DID NOT TOUCH. NO TURBULENCE. RANDOM SPARKS. ON CAPT'S WINDSHIELD FOUND HEAT SINK WIRE TERMINAL CONTACTING HEAT SINK RETAINER SPRING. ADJUSTED FOR CLEARANCE. ALL CKS GOOD. (LP6193492)

Part: SPOILER — OUT OF ADJUST · airframe 74,090 hrs · 55,009 cycles

ON APPROACH, RECEIVED A GEAR WARNING WITH FLAPS SET TO 23DEGREES. WHEN FLAPS WERE EXTENDED FROM 23 TO 28 DEGREES AIRCRAFT EXPERIENCED AN ASSYMETRICAL ROLL. DURING TROUBLESHOOTING, FOUND SLAT FAIL LIGHT IN BOTH STALL WARNING COMPUTER HISTORY. FAULT AS SET UPON ARRIVAL. VISUALLY INSPECTED SPOILER HINGE FOR DAMAGE. NO DEFECTS. RAN RTS TEST IAW AMM 22-10. BOTH GO . RESET BOTH SWC & OPER FLAPS THRU SEVERAL CYCLES. FOUND RT FLT SPOILERS LWR THAN LEFT. ADJ SAME IAW MM 27-61-02. OPS CK GOOD. PERFORMED RII FOR LT & RT FLT SPOILERS ADJUSTMENTS PER MD88 AMM 27-61-02.

Part: WINDSHIELD — ARCED (COCKPIT) · airframe 73,484 hrs · 54,436 cycles

SPARKS/ SLIGHT ARCING CAPT SIDE WINDSHIELD. INSPECTED CAPT'S WINDOWS IAW AMM 30-41AND 56-10 FOUND NO EVIDENCE OF ARCING FROM AREA INDICATED. NO C/B POPPED RAW BOTH WINDOW ANTI-ICE AND ANTI-FOG. COULD NOT DUPLICATE PROBLEM ALL CKS GOOD AT THIS TIME. NO 30 DAY HISTORY. OK FOR SVC. (LP5822868)

Part: RUDDER — DAMAGED · airframe 72,937 hrs · 53,972 cycles

DURING PAINT VISIT, FOUND RUDDER TO HAVE DAMAGED/MISSING FLAME SPRAY COATING RUDDER P/N 5955501-1 S/N 581 STK NBR 88-5554-9-0001 FTN 8X2G08. REMOVED P/N 5955501-1 S/N 581 FTN 8X2G08 STK 88-5554-9-0001 FROM A/C 976 AND INSTALLED P/N 5955501-1 S/N 0164 FTN 3XL16A STK 88-5554-9-0001 ON A/C 976 PER AMDS WORK CARD 2720-4421 FORECAST NUMBER 88-0511-8-9010 RUDDER, MAIN TA OFF 88-5554-9-0001 00581 ON 88-5554-9-0001 00164. (LP1039486)

Part: TAB — DAMAGED (RUDDER) · airframe 72,937 hrs · 53,972 cycles

DURING PAINT VISIT, FOUND RUDDER TAB TO HAVE DAMAGED / MISSING FLAME SPRAY COATING RUDDER TAB P/N 5955545-503 S/N 551 STK NBR 88-5554-9-0002 FTN 29NJSK. REMOVED P/N 5955545-503 S/N 551 FTN 29NJSK STK 88-5554-9-0002 FROM A/C 976 AND INSTALLED P/N 5955545-503 S/N F271 FTN 8B6JEI STK 88-5554-9-0002 ON A/C 976 PER AMDS WORK CARD 2720-4421 FORECAST NUMBER 88-0511-8-9010 TAB, RUDDER; MD OFF 88-5554-9-0002 00551 ON 88-5554-9-0002 00271. (LP1039491)

Part: LANYARD — UNSECURE (TAILCONE) · airframe 72,806 hrs · 53,852 cycles

TAILCONE KEVLAR LANYARD LOOP NOT SECURED TO RELEASE CAM. REINSTALLED KEVLAR LANYARD LOOP TO RELEASE CAM PER AMM 53-53. VERIFIED LANYARD INSTALLED. (LP5741857)

Part: DOOR FRAME — CRACKED (RT MLG WW) · airframe 72,750 hrs · 53,804 cycles

INITIAL INSPECTION: CRACK ON FWD DOOR JAMB OF MLG RT SIDE. FWD DOOR JAMB OF MLG RT SIDE WAS REPAIRED PER ERA 576253-14 REV. ORIGINAL ( SECTION I TEMPORARY REPAIR) AND ETI-88-19-021 REV. 3. PERFORM SEC II PERMANENT REPAIR AT OR BEFORE 24 MONTHS AFTER INSTALLATION OF SECTION 1 UNDER LOG PAGE 0977605 PER ER/A 576253-14 REV ORIGINAL. (LP0977685)

Part: FITTING — CRACKED (NLG WW) · airframe 72,750 hrs · 53,804 cycles

INITIAL INSPECTION: CRACK ON SUPPORT WEB FITTING ON INTERNAL STRUCTURE OF WHEEL WELL NLG RT SIDE. REPAIRED PER ERA 576251-14 REV ORIG (SECTION I TEMPORARY REPAIR). LOGPAGE 0976320 CREATED FOR MONITOR OF TEMP REPAIR. (LP0977181)

Part: FITTING — CRACKED (NLG WW) · airframe 72,750 hrs · 53,804 cycles

INITIAL INSPECTION: CRACK ON SUPPORT WEB FITTING ON INTERNAL STRUCTURE OF WHEEL WELL NLG RT SIDE. SUPPORT WEB FITTING ON INTERNAL STRUCTURE OF WHEEL WELL NLG RT SIDE WAS REPAIRED PER ERA 576251-14 REV. ORIGINAL. ( SECTION I TEMPORARY REPAIR ) AND ETI-88-19-018 REV. 5. PERFORM SECTION II AT OR BEFORE 24 MONTHS AFTER INSTALLATION OF SECTION I PER ERA 576251-14 REV ORIGINAL. (LP0977482)

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,750 hrs · 53,804 cycles

AWR: DURING REPETITIVE INSPECTION PER ER/A 472700-14 REV. A SECTION III (LOGPAGE 1773168). CORROSION WAS FOUND ON EXTERNAL FUSELAGE SKIN BTW STA Y=1309-1322 LONG 19L-23L AROUND OF AFT LAVATORY SERVICE PANEL. (CORROSION LEVEL 2): ON EXTERNAL FUSELAGE SKIN BTW STA Y=1309-1322 LONG 19L-23L AROUND OF AFT LAVATORY SERVICE PANEL WAS REPAIRED PER ER/A 472700-14 REV B ((SECTION IV TIME-LIMITED REPAIR) (CCK AT QRO, MARCH-2019)) AND ETI 88-19-019-REV.3. PERFORM A GENERAL VISUAL INSPECTION AS DEFINED IN THE SRM 51-03 PAR. 5 TO THE SECTION IV REPAIR. WITHIN EVERY 3,000 CYCLES AFTER SECTION IV UNTIL SECTION VI IS COMPLETED. PER ER/A 472700-14 REV. B. (LP0973114)

Part: SKIN — GOUGED (FUSELAGE) · airframe 72,750 hrs · 53,804 cycles

FUSELAGE / SKIN / AFT LAV CUTOUT / GOUGE AND PUNCTURE REPAIR. ACCOMPLISH ER/A 472700-14 REV B SECTION V INSPECTION WITHIN EVERY 3000 CYCLES UNTIL ACCOMPLISHMENT OF SECTION VI REPAIR WITHIN 8000 CYCLES AFTER ACCOMPLISHMENT OF SECTION IV. (LP0972741)

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 72,750 hrs · 53,804 cycles

INITIAL INSPECTION: CRACK ON RT EXTERIOR SKIN AT VERTICAL STABILIZER, PROYECTION STA Y= 1420 APPROX. CRACK ON RT EXTERIOR SKIN AT VERTICAL STABILIZER, PROYECTION STA Y= 1420 APPROX WAS REPAIRED PER ER/A 575990-14AD REV. ORIGINAL (SECTION I PERMANENT REPAIR ) AND ETI-88-19-017 REV 2. REPAIR APPROVAL IS LIMITED TO 75,000 CYCLES ONLY. ADDITIONAL ENGINEERING AUTHORIZATION (ER/A REVISION ) IS REQUIRED FOR CONTINUED SERVICE BEYOND THIS LIMIT PER ER/A 575990-14AD REV. ORIGINAL UNDER LOG 0969525. (LP0969949)

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 72,750 hrs · 53,804 cycles

INITIAL INSPECTION: CRACK ON EXTERNAL REPAIR DOUBLER (AFT LOWER CORNER) AT FWD PASSENGER DOOR EXTERNAL AREA (L1). DAMAGED EXTERNAL REPAIR DOUBLER (AFT LOWER CORNER) AT FWD PASSENGER DOOR EXTERNAL AREA (L1) WAS REPLACED PER SRM 52-05 PAR 39 FIG 37. (LP0966722)

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,750 hrs · 53,804 cycles

CORROSION ON PREVIOUS REPAIR DOUBLER OF LOWER DOOR JAMB BEAM BTW STA Y=1155-1212 AT AFT CARGO COMPARTMENT. REPAIR DOUBLER OF LOWER DOOR JAMB BEAM BTW STA Y=1155-1212 AT AFT CARGO COMPARTMENT WAS REPLACED PER SRM 53-05 FIG. 123 AND SRM 51-30-5. (LP0962594)

Part: ACM — SEIZED (RIGHT) · airframe 72,370 hrs · 53,484 cycles

ON SHORT FINAL, AFT F/A SMELLED ELECTRICAL/RUBBER BURNING SMELL FROM TAILCONE. FIRE DEPT DID NOT DETECT ANT SIGN OF FIRE. FOUND RT ACM SEIZED REPLACED SAME PER MD88 AMM 21-51. RAN ACM TESTS OK. TURBINE, COOLIN OFF 88-2150-9-0002 23469. (LP4807634)

Part: SLIDE — DEFECTIVE (L1 DOOR) · airframe 72,251 hrs · 53,381 cycles

L1 DOOR SLIDE REMOVED. REPLACED SLIDE DUE TO PIN NOT ENGAGED. INSTALLED SLIDE L1 DOOR PER CARD 2561-4964.

Part: BATTERY — DISCHARGED (CABIN) · airframe 71,403 hrs · 52,626 cycles

THE AFT CABIN EMERGENCY LIGHTS ON THE CEILING ARE INOPERATIVE. MAINTENANCE FOUND THE BATTERY AT ROW 33E,D TO BE BAD. THE BATTERY WAS REPLACED PER AMM 33-53. ALL CEILING EMERGENCY LIGHTS NOW WORK PROPERLY.

Part: LINE — LEAKING (HYD SYSTEM) · airframe 71,142 hrs · 52,413 cycles

LEFT HYD QUANTITY DROPPED TO ZERO, FOLLOWED QRH 13.3, ABNORMAL PRESSURE 13.19. ACCORDING TO MCC ADVISORY MESSAGE, AN EMERGENCY LANDING WAS DECLARED. FOUND A LINE LEAKING, FWD SIDE OF LT ENGINE CASE DRAIN FILTER MODULE. REPLACED THE HYD LINE AND FILTERS IAW AMM 29-10. LEAK CHECKED GOOD. APU INLET CONTAMINATED.

Part: SKIN — WORN (VERTICAL STAB) · airframe 70,941 hrs · 52,249 cycles

WEAR WAS REPAIRED ON THE VERTICAL STABILIZER SKIN ZFS54.

Part: LIGHT — INOPERATIVE (ROWS 16 & 23) · airframe 68,459 hrs · 50,290 cycles

EMERGENCY LIGHTS AT ROWS 16 AND 23 INOPERATIVE. REPLACED THE EMERGENCY LIGHTS IAW 33-53-01. OPS CHECKED GOOD. OK FOR SERVICE.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 67,722 hrs · 49,747 cycles

RIGHT WING, CORROSION ON ACCESS PANEL 1409C. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A PAR. 6 CONDITION III.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 67,722 hrs · 49,747 cycles

CORROSION ON ACCESS PANELS 1303C AND 1404C. REPLACED THE ACCESS PANELS.

Part: HINGE — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 67,722 hrs · 49,747 cycles

CORRODED HINGE FACE ON VERTICAL STABILIZER. CORROSION REMOVED IAW SRM 55-02 PAR.24.A.

Part: CLAMP — BROKEN (RT MLG WW) · airframe 67,722 hrs · 49,747 cycles

RIGHT MLG AND WHEEL WELL AREA BROKEN ISULATION CLAMP AND TORN INSULATION OF HYD AUXILIAR PUMP CONECTOR. NEW CLAMP AND INSULATION ON CONNECTOR WERE REPLACED IAW SWPM 20-10-01, SWPM 20 31-20 AND ERA 467688-14 MAAD REV D.

Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 67,149 hrs · 49,331 cycles

TAILCONE UNSAFE LIGHT IN FLIGHT. INSERTED LOCKING CABLE IN RETAINING HOLE IN SUPPORT FITTING UNTIL SECURE PER AMM 53-53 PARAGRAPH 3 STEP 10.

Part: STRUCTURE — DAMAGED (VERTICAL STAB) · airframe 66,790 hrs · 49,029 cycles

DURING INSPECTION, FOUND ALL HOLES IN BOTH FASTENER ROWS BELOW ZFS 52.267 ELONGATED. REPAIRED ELONGATED HOLES IAW SECTION I, PERMANENT REPAIR OF ER/A 550371-14AD, REV ORIGINAL.

Part: STRUCTURE — DAMAGED (VERTICAL STAB) · airframe 66,790 hrs · 49,029 cycles

DURING INSPECTION, FOUND ALL HOLES IN BOTH FASTENER ROWS BELOW ZFS 52.267 ELONGATED. REPAIRED ELONGATED HOLES IAW SECTION I: PERMANENT REPAIR OF ER/A 550371-14AD, REV ORIGINAL.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHT) · airframe 66,786 hrs · 49,026 cycles

ROW 16DE EMERGENCY LIGHT INOPERATIVE. REPAIRED CONNECTION BETWEEN WIRES AND CONNECTOR IAW AMM 33-50.

Part: SKIN — CRACKED (RT HORIZ STAB) · airframe 66,298 hrs · 48,664 cycles

UPPER RT HORIZONTAL STABILIZER AFT SKIN HAS .2500" CRACK INDICATION. TRIMMED OUT CRACK WITH .75" MIN RADIUS, RLW 744338. ACCOMPLISHED CLOSE VISUAL OK TO TREAT AND PAINT. FABRICATED AND INSTALLED FILLER IAW STEP 8 AND 9 IAW DWG SR 09550028. REQUIRED INSPECTION COMPLETE.

Part: BUCKLE — BROKEN (TAILCONE) · airframe 66,212 hrs · 48,605 cycles

TAILCONE STRAP BUCKLE BROKEN. REINSTALLED BLIND THREADED SELF LOCKING INSERT.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,025 hrs · 48,456 cycles

THE FLIGHT CREW OF FLIGHT 1140 FOUND THAT THE EMERGENCY LIGHTS AT 2L OVERHEAD WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES FOR 2L EMERGENCY LIGHTS. THE LIGHTS CHECKS OK.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHT) · airframe 65,936 hrs · 48,380 cycles

MAINTENANCE FOUND THE EMERGENCY LIGHT AT SEAT 20ED INOPERATIVE. A NEW PIN WAS INSTALLED ON THE CONNECTOR AT SEAT 20ED. THE LIGHTS CHECKS OK.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 64,843 hrs · 47,648 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING AT THE EMERGENCY EXIT ROW IN THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE WIRE HARNESS AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 63,595 hrs · 46,785 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE AFT OVERWING EMERGENCY EXIT LIGHT TO BE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK AND THE OPS CHECK WAS GOOD.

Part: IRU — FAILED (NR 1) · airframe 62,724 hrs · 46,213 cycles

CREW DIVERTED AFTER THE NR 1 PRIMARY FLIGHT DISPLAY FAILED AND BOTH NAVIGATION DISPLAYS WERE DEEMED UNRELIABLE WITH EXCESSIVE HEADING DISCREPANCIES. MAINTENANCE REPLACED THE NR 1 IRU AND ALSO THE R2-47 EMERGENCY AC POWER TRANSFER RELAY AND R2-100 DFGC TRANSFER RELAY AS A PRECAUTION. NO OTHER DISCREPANCIES WERE NOTED AND A SUCCESSFUL RETURN TO SERVICE CHECK WAS PERFORMED ON BOTH DFGCS IAW AMM 22-01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PANEL 1371C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION WAS REMOVED AND FOUND OUT OF LIMITS IAW SRM 51-22-2A AND WAS REPLACED.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION IN RT WING ACCESS PANEL 1472C COUNTERSINKS. CORROSION WAS REMOVED, AND FOUND OUT OF LIMITS SRM 51-22-2A. THE ACCESS PANEL WAS REPLACED.

Part: ACCESS PANEL — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

SCRATCHES AND CORROSION ON HOLES AT MID ACCESS PANEL OF HORIZONTAL STABILIZER. DAMAGE REWORKED IAW ETI-88-14-301, REV 1 AND ER/A 531356-14 REV ORIG.

Part: INTERCOSTAL — CORRODED (BS 1155-1136) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON INTERCOSTAL BETWEEN BS 1155 - 1136 LONGERON 29 AND 30R. THE INTERCOSTAL WAS REPLACED IAW SRM 51-10-3, PAR 14 AND 21, 51-30-2, 51-30-5, 51-10-4.

Part: ANGLE — CORRODED (BS 1155) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FRAME ANGLE BS 1155 BETWEEN LONGERONS 29 AND 30R. THE ANGLE WAS REPLACED IAW SRM 51-30-2, 51-30-5, 51 -10-4 AND 51-10-3 PAR 14 AND 21.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PANEL 1335C AT COUNTERSINK HOLES AND SETTLEMENT AREAS. CORROSION WAS REMOVED IAW SRM 51-22-2 AND FOUND OUT OF LIMITS IAW SRM 51-22-2A. THE ACCESS PANEL WAS REPLACED.

Part: SPACER — CORRODED (DOOR FRAME) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON AFT LOWER CARGO DOOR SPACER BS 1154-1212. SPACER WAS REPLACED IAW SRM 53-05, FIG 123A.

Part: SKIN — DAMAGED (RUDDER TAB) · airframe 62,642 hrs · 46,156 cycles

FOUND DAMAGE METALIZED SKIN ON CONTROL RUDDER TAB. REPAIRED IAW SRM 51-70-1AD PAR 23.

Part: SKIN — CORRODED (BS 800) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

FUSELAGE SKIN WAS CORRODED BS 800 AND L28R. REPAIR DOUBLER WAS INSTALLED IAW ER/A 531371-14, REV ORIGINAL.

Part: INTERCOSTAL — CRACKED (BS 110) · airframe 62,642 hrs · 46,156 cycles

CRACK ON ENDS OF INTERCOSTAL BS 110, BETWEEN LONGERONS 27 -28L AND 27-28R AT NLG WHEEL WELL INTERNAL STRUCTURE. INTERCOSTAL WAS REPAIRED IAW SRM 51-30- 2,51-30-5,51-30-8,53-01 FIG 2 AND 51-10-3, PAR 14 AND 21.

Part: BULKHEAD — CORRODED (BS 1338) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON REPAIR DOUBLER ON THE PRESSURE BULKHEAD BS 1338 BETWEEN LONGERONS 28R - 28L. REPAIR DOUBLER WAS REPLACED IAW SRM 53-05, FIG 101.

Part: OUTFLOW VALVE — CORRODED · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON SUTTLEMENT AT CABIN AIR OUT FLOW BUTTERFLY VALVE. OUTFLOW BUTTERFLY VALVE WILL BE REPLACED UNDER NRC 2 DUE TO OUTFLOW BUTTERFLY VALVE WAS FOUND CRACKED.

Part: SKIN — CORRODED (BS 1118) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION OUT LIMITS ON FUSELAGE SKIN BS 1118 BETWEEN LONGERONS 27 - 28L. SKIN WAS REPAIRED IAW SRM 53-04, FIG 57 AND SRM 51-10-3, PAR 14, 21 SRM 51-30-5.

Part: SKIN — CORRODED (BS 779-783) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION OUT LIMITS ON FUSELAGE SKIN BS 779 BETWEEN LONGERONS 28 - 29L AND BS 783 BETWEEN LONGERONS 28 - 29L. DAMAGE WAS REPAIRED IAW SRM 53-04, PAR 57, FIG 57.

Part: INTERCOSTAL — CORRODED (BS 769-788) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON INTERCOSTAL BETWEEN BS 769 - 788 AND LONGERONS 27 - 28R. INTERCOSTAL REPLACED IAW DWG 991554, REV V AND SRM 51-10-3, PAR 14, 21.

Part: SKIN — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION AROUND LT HORIZONTAL STABILIZER BARREL NUT HOLES NR 17 AND 20. DAMAGE WAS REWORKED IAW ETI-88-14-292 REV ORIG AND ER/A 531348-14, REV ORIG.

Part: SUPPORT — CRACKED (BS 712) · airframe 62,642 hrs · 46,156 cycles

CRACKED RT SLANT SUPPORT BS 712 . SLANT SUPPORT WAS REPLACED IAW ER/A 413029-14MA, REV B.

Part: STRUCTURE — BENT (BS 383) · airframe 62,642 hrs · 46,156 cycles

BENT ON FWD CARGO DOOR LOWER CUT-OUT AREA AT BS 383. REPAIRED IAW ETI-88-15-0006 AND ER/A 531374-14.

Part: PAN — CRACKED (EMERGENCY EXIT) · airframe 62,642 hrs · 46,156 cycles

CRACK ON AFT LT OVERWING EMERGENCY EXIT DOOR PAN LOCATED AFT EDGE BETWEEN UPPER CHANNEL AND LOWER ZEE INTERNAL STRUCTURE. REPAIR DOUBLER WAS FABRICATED, PAINTED INSTALLED IAW SRM 5205D, FIG 51.

Part: CARGO TRACK — CORRODED (BS 1212-1320) · airframe 67,259 hrs · 49,418 cycles

CORROSION ON CARGO TRACK BS 1212 - 1320 IS OUT OF LIMITS. THE CARGO TRACK WAS REAPLACED.

Part: SPAR — OUT OF ALIGNMENT (HORIZONTAL STAB) · airframe 62,642 hrs · 46,156 cycles

MISALIGMENT UPPER REAR SPAR TO ATTACH HINGE 6 AT RT HORIZONTAL STABILIZER, RT SIDE. MISALIGMENT ON UPPER REAR SPAR TO ATTACH HINGE NR 6 WAS REPAIRED IAW ETI-88-15-002, REV 1 WITH A REPAIR BUSHING ON THE AFFECTED HOLE. ALSO IAW ER/A 531370-14 REV ORIGINAL. (LP1777587)

Part: SKIN — CORRODED (BS 1118) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION OUT LIMITS ON FUSELAGE SKIN BS 1118 BETWEEN LONGERONS 27 - 28L. SKIN WAS REPAIR IAW SRM 53-04 FIG 57 SRM 51-10-3, PAR 14, 21.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PANEL 1333C AT SETTLEMENT AREA. THE ACCESS PANEL WAS REPLACED IAW AMM 28-00-00.

Part: SKIN — CRACKED (BS 1418) · airframe 62,642 hrs · 46,156 cycles

CRACK ON FUSELAGE SKIN BS 1418. THE SKIN WAS REPAIRED IAW ER/A 530162-14 AD REV ORIGINAL.

Part: SPAR — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON UPPER REAR SPAR HOLE TO ATTACH HINGE 6 AT RT HORIZONTAL STABILIZER, RT SIDE. DAMAGE ON UPPER REAR SPAR HOLE TO ATTACH HINGE NR 6 WAS REPAIRED IAW ETI-88-15-002, REV 1 WITH A REPAIR BUSHING ON THE AFFECTED HOLE. ALSO, IAW ER/A 531370-14, REV ORIG.

Part: ANGLE — CRACKED (LT OVERWING EXIT) · airframe 62,642 hrs · 46,156 cycles

CRACKED ON AFT LEFT OVERWING EMERGENCY DOOR ANGLE. AN ANGLE WAS FABRICATED, TREATED, PAINTED AND INSTALLED IAW SRM 51-30-1, 51-30-2 , 51-30-5 AND DWG 9957735.

Part: SKIN — DAMAGED (RT WING TE FLAP) · airframe 62,642 hrs · 46,156 cycles

NICKS ON LOWER SKIN XW=42 TO XW=59 AT RT WING INBD FLAP. ON RT WING INBD FLAP SKIN STA XW=48 TO XW=59 AT WING INBD WAS REPAIRED IAW SRM 57-03 D, FIG 8. (LP1776313)

Part: DOUBLER — CORRODED (BS 1338 BULKHEAD) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON AFT PRESSURE BULKHEAD DOUBLER BS 1338 BETWEEN LONGERONS 28L - 29R. DOUBLER WAS FABRICATED IAW DWG 5910130-61, REV ET, TREATED AND PAINTED AND INSTALLED IAW SRM 51-10-3, PAR 14 AND 21, 51-30-5.

Part: SPAR CAP — CRACKED (HORIZONTAL STAB) · airframe 62,642 hrs · 46,156 cycles

CRACK ON UPPER REAR SPAR CAP OF HORIZONTAL STABILIZER RT SIDE. THE SPAR CAP WAS REPLACED IAW DWG SR09550030, REV C.

Part: SPAR — DAMAGED (HORIZONTAL STAB) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION AND SCRATCHES LOWER REAR SPAR AND CAP HOLES TO ATTACH HINGE 6 AT RT HORIZONTAL STABILIZER, RT SIDE. DAMAGES ON LOWER REAR SPAR CAP HOLES ATTACH HINGE 6 WERE REPAIRED IAW ETI 88-15-002, REV 1 WITH A REPAIR BUSHING AT THE HOLE. ALSO IAW ER/A 531370-14, REV ORIG.

Part: PANEL — CRACKED (BS 1231) · airframe 62,642 hrs · 46,156 cycles

CRACKED SLANT PANEL BS 1231 BETWEEN LONGERON 23 - 27R. THE SLANT PANEL WAS REPLACED IAW SRM 51-30-2, 51-10-4, 51-30-5, 51-10-3, PARR 14, 21 AND ER/A 413029-14MA, REV D.

Part: FRAME — CRACKED (BS 1474) · airframe 62,642 hrs · 46,156 cycles

CRACKED FRAME, BS 1474 . CRACK WAS STOP DRILLED IAW SRM 53-01, FIG 2, REPAIR DOUBLERS WERE FABRICATED IAW SRM 53-01, FIG 2, DOUBLERS WERE TREATED AND PAINT IAW SRM 51-10-3, PAR 14,21. REPAIR DOUBLERS WERE INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: CARGO TRACK — CORRODED (BS 1003-1155) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

SEVERAL CORROSION POINTS ON CARGO TRACK BS 1155 - 1003. THE CARGO TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-1 AND SRM 51-30-1.

Part: PANEL — CRACKED (BS 1287) · airframe 62,642 hrs · 46,156 cycles

CRACKED SLANT PANEL BS 1287 BETWEEN LONGERON 23 - 27L. THE SLANT PANEL WAS REPLACED IAW SRM 51-30-2, 51-10-4, 51-30-5, 51-10-3, PAR 14, 21 AND ER/A 413029-14MA REV D.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 72,750 hrs · 53,804 cycles

FUSELAGE SKIN & DOUBLER AT AFT LAV CUTOUT HAD 3 ENLARGED HOLES REQUIRING ENLARGEMENT OF THE EXISTING REPAIR DOUBLER. TERMINATES THE SECTION III INSPECTION. OK TO CLOSE THIS LP. ALL FOLLOW-ON WORK IS ON LP 0972741. (LP1773168)

Part: DOUBLER — CRACKED (BS 1193) · airframe 62,642 hrs · 46,156 cycles

CRACKED FUSELAGE SKIN DOUBLER BS 1193 AND LONGERON 26L. DOUBLER WAS REPLACED IAW FIG 12D, 51-30-2, 51-30-5.

Part: CARGO TRACK — CORRODED (BS 1003-1228) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

SEVERAL CORROSION POINTS ON CARGO TRACK BS 1228 - 1003. THE CARGO TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-1 AND 51-30-2, 51-10-4 AND 51-10-3, PAR 21 - 14 .

Part: CARGO TRACK — CORRODED (BS 1222-1320) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON LT CARGO TRACK BS 1222 - 1320. THE CARGO TRACK WAS REPLACED SRM 51-30-2, 51-30-1 AND 51-30-5.

Part: TEE FITTING — SCRATCHED (BS 1380) · airframe 62,642 hrs · 46,156 cycles

SCRATCHES ON TEE FITTING AT BS 1380, X 0 TO X 10, TEE FITTING WAS REMOVED AND REPLACED IAW ETI-88-14-295, REV ORIG AND SRM 51-30-2 AND 51-30-5 AND ERA 531350-14, REV ORIG.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 62,642 hrs · 46,156 cycles

DELAMINATED FLOUR PANEL. FLOOR PANEL FABRICATED IAW AMM 53-20-101-201.

Part: FLOOR SUPPORT — CRACKED (CABIN) · airframe 62,642 hrs · 46,156 cycles

FLOOR SUPPORT CRACKED. REPAIRED IAW SRM 53-05, FIG 131C, AND 51-10-3, PAR 21 - 14.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 62,642 hrs · 46,156 cycles

DELAMINATED FLOOR PANEL. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 62,642 hrs · 46,156 cycles

WORN REPAIR ON INBD FIXED GUIDE VANE AT LT WING OTBD FLAP. REPAIR WAS REPLACED IAW SRM 57-03D, PAR 11.

Part: CUSP WEB — CORRODED (BS 506-547) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON RT CUSP WEB X -60, BS 506-547. CORROSION REMOVED AND CUSP WEB REPLACED IAW SRM 51-30-2, 51-30-5, 51-30-1, 51-10-4, 51-10-3 PAR 14,21,26 AND 38, AND AMM 20-12-01.

Part: FRAME — CORRODED (BS 1250) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON FRAME BS 1250 BETWEEN LONGERONS 26L - 29 R. CORROSION REMOVED IAW SRM 53-03D, FIG 2A; 51-10-4; 51-30-2; 51-30-5, AND 51-10-3 P. 21, 14.

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FLOOR PANEL 160GT. FLOOR PANEL REPLACED IAW DWG 9957828, REV AB AND SRM 51-10-3 PAR 14, 21.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON ACCESS PANEL 1335C AT COUNTERSINK HOLES AND SETTLEMENT AREAS. CORROSION REMOVED IAW SRM 51-22-2 AND FOUND OUT OF LIMITS IAW SRM 51-22-2A.

Part: LONGERON — CRACKED (BS 1418) · airframe 62,642 hrs · 46,156 cycles

CRACKED LONGERON 2L BS 1418. LONGERON WAS REPAIRED IAW SRM 53-02 FIG 18.

Part: SUPPORT — CORRODED (BS 180-200) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON GIRT BAR FITTING SUPPORTS BETWEEN BS 180 - 200 AND X -60. SUPPORTS REPLACED IAW SRM 51-10-4 , 51-10-3 PAR 14, 21.

Part: SEAT TRACK — CORRODED (BS 448-720) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON LT SEAT TRACK X 22 BETWEEN BS 448-720. REPAIRED IAW SRM 53-05, FIG 4A SRM 51-10-3, PAR 14,21.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON ACCESS PANEL 1460C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION REMOVED AND FOUND OUT OF LIMITS IAW SRM 51-22-2. THE ACCESS PANEL WAS REPLACED.

Part: SEAT TRACK — CORRODED (BS 527-536) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON THE RT SEAT TRACK REPAIR PLUG X -54 BETWEEN BS 527 - 536. THE REPAIR PLUG WAS REPLACED IAW SRM 53-05, FIG 4A AND 53-30-1.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON ACCESS PANEL 1460C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION REMOVED AND FOUND OUT OF LIMITS IAW SRM 51-22-2. THE ACCESS PANEL WAS REPLACED.

Part: SEAT TRACK — CORRODED (BS 513-720) · airframe 67,259 hrs · 49,418 cycles

CORROSION ON LEFT SEAT TRACK X 22. BS 513 - 520 AND 717 - 720. THE AREA WAS REPAIRED.

Part: SEAT TRACK — CORRODED (BS 627) · airframe 67,259 hrs · 49,418 cycles

CORROSION ON RT SEAT TRACK X -54 BS 627. CORROSION WAS ATTENDED IAW SRM 53-05 FIG.4A.

Part: SUPPORT — CRACKED (BS 1136) · airframe 62,642 hrs · 46,156 cycles

CRACKED SLANT PANEL SUPPORT BS 1136 BETWEEN LONGERONS 24-28R. THE SUPPORT WAS REPLACED IAW SRM 51-30-2 AND ERA 413029-14MA AND 51-10-3 PARA 21 AND 14.

Part: SEAT TRACK — CORRODED (BS 702-720) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON LT SEAT TRACK X 22 BETWEEN BS 702-720. REPAIRED IAW SRM 53-05, FIG 4A 51-10-3 PAR 14,21.

Part: SPAR — CORRODED (LT NACELLE) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON LT ENGINE MOUNT FWD PYLON SPAR LOWER BORE. REPAIRED IAW SRM 54-04D, PAR 14.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PANEL NR 1462C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION WAS REMOVED AND WAS FOUND OUT OF LIMITS IAW SRM 51-22-2.

Part: SEAT TRACK — CORRODED (BS 449-450) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON THE RT SEAT TRACK X -22 BS 449 - 450 . CORROSION WAS REMOVED IAW SRM 53-05, FIG 4A, 51-03-3, PAR 14, 21 AND 38, AND 51-30-1.

Part: SUPPORT — CRACKED (BS 1041) · airframe 62,642 hrs · 46,156 cycles

CRACKED SLANT PANEL SUPPORT BS 1041 BETWEEN LONGERONS 24-28R. THE SUPPORT WAS REPLACED IAW SRM 51-30-5 AND ERA 413029-14MA AND SRM 51-10-3 PARA 21 AND 14. (LP1773428)

Part: SUPPORT — CRACKED (BS 1060) · airframe 62,642 hrs · 46,156 cycles

CRACKED SLANT PANEL SUPPORT BS 1060 BETWEEN LONGERONS 24 - 28L. SUPPORT WAS REPLACED IAW SRM 51-30-5 AND ERA 413029-14MA AND 51-10-3. (LP1773419)

Part: RIB — CORRODED (SLAT) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON RIB FWD BORE STA 286, INBD AND OUTBD RIB FWD/ AFT BORES STA 332.5 AND RIB FWD BORE STA XOS 380 AT LT SLAT PANEL NR 3 ON STA 332.5. AREAS WERE REWORKED AND MEASURE,THEREFORE OUT LIMITS IAW SRM 57-02, PAR.9C, 1, AND TABLE 1 WITH DIAMETER INBD HOLES 0.0938, 2 EA AND OTBD HOLES 0.0938", 2 EA. BUSHINGS WERE FABRICATED IAW SRM 57-02 PAR 9C, 2, AND STA 286 , STA 380 AREAS WERE REWORKED, MEASURED AND FABRICATED BUSHINGS IAW ETI-88-14-285 AND ER/A 530169-14, REV LP1770438.

Part: LONGERON — CRACKED (BS 1437) · airframe 62,642 hrs · 46,156 cycles

CRACKED LONGERON 16L BS 1437. LONGERON REMOVED IAW SRM 51-30-2 AND 51-30-5, AND A NEW LONGERON WAS DRILLED AND ADJUSTED IAW SRM 51-10-4, TREATED AND PAINTED IAW SRM 51-10-3 PAR 14 AND 21, AND INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: SERVICE PANEL — CRACKED (LAVATORY) · airframe 62,642 hrs · 46,156 cycles

CRACKED AFT LAVATORY SERVICE PANEL. AFT LAVATORY SERVICE PANEL WAS REPLACED SRM 51-30-2, 51-30-5, 51-10-4, 51-10-3 PAR 21 AND 14.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON RT FUEL ACCESS PANEL 1470C COUNTERSINK HOLES. CORROSION WAS REMOVED AND FOUND OUT LIMITS IAW SRM 51-22-2A. THE ACCESS PANEL WAS REPLACED.

Part: SUPPORT — CORRODED (BS 1136) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON TEE SUPPORT, BS 1136 LONGERON 18R. TEE SUPPORT WAS REPLACED IAW SRM 51-30-1, 51-30-5, SRM 51-10-3 PAR 14-21 SRM 51-10-4.

Part: SEAT TRACK — CORRODED (BS 879-881) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON LT SEAT TRACK X 22 BETWEEN BS 879-881. REPAIRED IAW SRM 53-05, FIG 4A SHEET 1, 51-10-3 PAR 26,14,21 AND 38.

Part: SEAT TRACK — CORRODED (BS 1021-1031) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON LT SEAT TRACK X 22 BETWEEN BS 1021 - 1031. SEAT TRACK REPAIRED IAW SRM 53-05, FIG 4F, 51-10-3 PAR 14, 21 AND 38.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PANEL 1410C COUNTERSINK HOLES AND SETTLEMENT AREAS. CORROSION REMOVED IAW SRM 51-10-3 AND FOUND OUT OF LIMITS IAW SRM 51-22-2. THE ACCESS PANEL WAS REPLACED.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PANEL 1307C COUNTESINK HOLES AND SETTLEMENT AREAS. CORROSION REWORKED IAW SRM 51-1-3 AND WAS FOUND OUT OF LIMITS IAW SRM 51-22-2. THE ACCESS PANEL WAS REPLACED.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON ACCESS PANEL 1414C AT COUNTERSINK HOLES AND SETTLEMENT AREA. THE CORROSION WAS REMOVED, FOUND OUT OF LIMITS IAW SRM 51-22-2, AND WAS REPLACED.

Part: CUSP WEB — CORRODED (BS 829-841) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON REPAIR DOUBLER X -55 - X -60 BS 829-841 CUSP WEB. REPAIR REMOVED, AND A NEW WAS FABRICATED AND INSTALLED, TREAT, AND PAINTED IAW SRM 53-05, FIG 131A -14 51-10-3, PAR 14 AND 21 AND 38.

Part: PAN — CRACKED (EMERGENCY EXIT) · airframe 62,642 hrs · 46,156 cycles

CRACKED AFT EMERGENCY EXIT PAN BS 916 BETWEEN LONGERONS 11 AND 12R. REPAIRED IAW SRM 53-05, FIG 32.

Part: CUSP WEB — DAMAGED (BS 1155) · airframe 62,642 hrs · 46,156 cycles

CUSP WEB BS 1155, X 53 DAMAGED. CUSP WEB REPAIRED IAW SRM 53-01 FIG 2, SRM 51-10-3, PAR 14,21, SRM 51-30-5.

Part: SKIN — DENTED (BS 1418) · airframe 62,868 hrs · 46,311 cycles

A 0.093" LONG CRACK WAS FOUND ON THE FUSELAGE SKIN AT BS 1418 BETWEEN LONGERONS 2-3R. SKIN REPAIRED IAW ER/A 530162-14AD, REV ORIGINAL.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PANEL 1410C COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION WAS REMOVED IAW SRM 51-10-3 AND FOUND OUT OF LIMITS IAW SRM 51-22-2 AND A NEW ACCESS PANEL INSTALLED.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PANEL 1361C COUNTERSINK HOLES AND SETTLEMENT AREAS. CORROSION REMOVED IAW SRM 51-10-3 AND FOUND OUT OF LIMITS IAW SRM 51-22-2. THE ACCESS PANEL WAS REPLACED.

Part: PAN — CRACKED (DOOR FRAME) · airframe 62,642 hrs · 46,156 cycles

CRACKED FWD EMERGENCY EXIT PAN BS 875 BETWEEN LONGERONS 11 AND 12R. REPAIRED IAW SRM 53-05, FIG 32.

Part: SKIN — CORRODED (BS 886-1065) · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUSELAGE SKIN BS 886 - 1065 LONGERON 18L. CORROSION REMOVED AND FOUND WITHIN LIMITS. TREATED AND PAINTED IAW SRM 51-10-3, PAR 26, 21 AND 14 AND 53-04, PAR 57.

Part: CUSP WEB — CORRODED (BS 1235) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON THE RT CUSP WEB BS 1235 BETWEEN X -54 TO X -60. DAMAGE WAS REMOVED AND REPAIR PART FABRICATED. AREA AND DOUBLER WERE TREATED, PAINTED, AND INSTALLED IAW SRM 53-05, FIG 131A-14, 51-30-5,51-10-3 PARA 14, 21, 38.

Part: FRAME — CORRODED (BS 1250) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FRAME ANGLE BS 1250 BETWEEN LONGERONS 29 AND 30R. FOUND OUT OF LIMITS AND THE FRAME SECTION WAS REPLACED IAW SRM 53-03 D, FIG 3.

Part: HINGE FITTING — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION RT INBD AND OTBD HINGE BORE FITTINGS ON HORIZONTAL STABILIZER PIVOT POINT ZRS 173. REMOVED AND REPAIRED IAW SRM 55-02 D, PAR 24.

Part: SKIN — DENTED (CARGO DOOR) · airframe 62,642 hrs · 46,156 cycles

DENTS ON MID CARGO DOOR SKIN BETWEEN BEAMS 3-4, 1EA, AND BETWEEN BEAMS 4-5, 6 EAS. DENTS WERE MEASURED, DUE TO WERE FOUND MANY DENTS OUT OF LIMITS DOOR SKIN WILL BE R & R. OUTER SKIN AND DOUBLERS AND HOUSING WERE REMOVED IAW SRM 51-30-2 AND 51-30-5 AND 51-30-1. OUTER SKIN WAS FABRICATED AND DRILLED IAW DWG 5910141, REV FE AND SRM 51-10-4. NEW SKIN WAS TREATED AND PAINTED IAW SRM 51-10-3 PAR 21 AND 14 NEW SKIN AND DOUBLERS AND HOUSING WERE INSTALLED IAW SRM 51-30-2 AND 51-30-5 AND 51-30-1.

Part: RIB — CORRODED (LT WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON INBD AND OTBD RIBS INNER FACES XOS 580 - 610 LT SLAT PANEL NR 5. RIB REMOVED IAW SRM 51-30-1 AND 51-30-2. A NEW RIB WAS DRILLED IAW SRM 51-10-4, AND PAINTED IAW SRM 51-10-3 PAR 14. INSTALLED IAW SRM 51-30-1 AND 51-30-2.

Part: CUSP WEB — CORRODED (BS 552-559) · airframe 67,259 hrs · 49,418 cycles

CORROSION ON REPAIR DOUBLER OF THE CUSP WEB BETWEEN BS 552-559 AND X 54 TO 60. THE CUSP WEB WAS REPLACED.

Part: RIB — CORRODED (LT WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON RIB FWD & AFT BORES XOS 380 LT SLAT PANEL NR 4. REPAIRED IAW ETI-88-14-286 AND ER/A 530170-14, REV ORIG.

Part: TEE FITTING — CORRODED (BS 655-674) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON MID CARGO DOOR TEE BS 655 - 674 BETWEEN BEAM NR 1 AND LWR EDGE. TEE REPLACED IAW SRM 51-30-2, 51-10-4.

Part: SEAT TRACK — CORRODED (BS 1191-1196) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON RT SEAT TRACK REPAIR PLUG X -22 BETWEEN BS 1191-1196. THE REPAIR PLUG WAS REPLACED IAW SRM 53-05 FIG 4A AND 51-10-3.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 62,642 hrs · 46,156 cycles

DELAMINATED FLOOR PANEL. A NEW FLOOR PANEL WAS FABRICATED IAW AMM 53-20-01-201.

Part: CUSP WEB — CORRODED (BS 850-862) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON RT CUSP WEB, X -54 TO -60, BS 850 - 862. REPAIRED IAW SRM 51-10-3, PAR 14, 21 & 26, SRM 51-30-2, SRM 51-30-5 AND SRM 53-05, FIG 131A-14.

Part: PAN — CRACKED (CARGO DOOR) · airframe 62,642 hrs · 46,156 cycles

CRACKED OUTER PAN AFT SIDE AND BEAM NR 1 AT FWD CARGO DOOR. STOP FITTING WAS REMOVED IAW SRM 51-30-1 AND 51-30-5, CRACK WAS STOPPED DRILLED IAW SRM 51-01 PAR 21. A DOUBLER WAS FABRICATED IAW SRM 52-05D FIG 50, REPAIR PAINTED IAW SRM 51-10-3, PAR 21 AND 14, REPAIR INSTALLED AIW SRM 51-30-2.

Part: LONGERON — CRACKED (BS 1309) · airframe 62,642 hrs · 46,156 cycles

CRACK ON LONGERON 8R AT BS 1309. LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 62,642 hrs · 46,156 cycles

ELONGATED HOLE OF FLOOR PANEL 927A IN PAX CABIN. FLOOR PANEL REPAIRED IAW FIG 1, SRM 51-10-3, PAR 14 & 21, SRM 51-30-2, 53-05.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON FUEL ACCESS PANEL 1373C COUNTERSINK HOLES AND SETTLEMENT AREAS. CORROSION REMOVED IAW SRM 51-22-2A. FOUND OUT OF LIMITS IAW SRM 51-22-2A. NEW ACCESS PANEL INSTALLED.

Part: FRAME — CRACKED (BS 1418) · airframe 65,847 hrs · 48,315 cycles

CRACKED FRAME BS 1418, LONGERON 2 RT. THE FRAME WAS REPAIRED IAW SRM 53-03D FIG 31A, AND 51-10-3, PAR 21 AND 14, 51-3-5, AND 51-3-2.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 62,642 hrs · 46,156 cycles

DELAMINATED FLOOR PANEL. A NEW FLOOR PANEL WAS FABRICATED IAW AMM 53-20-01-201.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 62,642 hrs · 46,156 cycles

DELAMINATED FLOOR PANEL. A NEW FLOOR PANEL WAS FABRICATED IAW AMM 53-20-01-201.

Part: SKIN — WORN (FUSELAGE) · airframe 62,642 hrs · 46,156 cycles

WORN OUT FWD & AFT REPAIR DOUBLERS AT FWD CARGO BAY OUTER SKIN. DOUBLERS WERE REMOVED IAW SRM 51-30-2 DOUBLERS WERE FABRICATED IAW SRM 52-05D, FIG 806D. DOUBLERS WERE TREATED AND PAINTED IAW SRM 51-10-3, PAR 21 AND 14 DOUBLERS WERE INSTALLED IAW SRM 51-3-2.

Part: FLOOR SUPPORT — CORRODED (BS 168-194) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FLOOR SUPPORT AT X 54 BETWEEN BS 168 - 194. FLOOR SUPPORT REPLACED IAW SRM 53-14-1, 51-10-3 P. 21, 14, 38, AND 51-10-4.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PLATE NR 1456C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION ON ACCESS PLATE WAS R & R UNDER JIC 2800-0390, JOB 001-0393.

Part: INTERCOSTAL — CRACKED (PAX DOOR) · airframe 62,642 hrs · 46,156 cycles

CRACKED AFT INTERCOSTAL BETWEEN BEAM NR 4 AND 5 OF FORWARD PASSENGER ENTRY DOOR MID SECTION L1. NEW INTERCOSTAL WAS INSTALLED IAW SRM 51-30-2.

Part: SEAT TRACK — CORRODED (BS 1128-1131) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON RT SEAT TRACK X -54 BETWEEN BS 1128 - 1131. SEAT TRACK WAS REPAIRED IAW SRM 53-05, FIG 4A AND 51-10-3, PAR 14, 21.

Part: SEAT TRACK — CORRODED (BS 822-829) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON REPAIR PLUG OF RT SEAT TRACK X -22, BS 822 - 829. REPAIR REPLACED IAW SRM 51-30-01 AND 53-05, FIG 4A.

Part: SKIN — WORN (L1 DOOR) · airframe 62,642 hrs · 46,156 cycles

SKIN OF FORWARD L1 DOOR LOWER EDGE WORN. DOUBLER REMOVED IAW SRM 51-30-2. A NEW DOUBLER FABRICATED IAW SRM 52-05, FIG. 37, TREATED AND PAINTED IAW SRM 51-10-3, PAR 14/21 AND INSTALLED IAW SRM 51-30-2.

Part: SEAT TRACK — CORRODED (BS 1096-1101) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON RT SEAT TRACK X -22 BS 1096-1101. SEAT TRACK REPAIRED IAW SRM 53-05, FIG 4A AND 51-10-3, PAR 14, 21.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PLATE NR 1464C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION ON FUEL ACCESS AT COUNTERSINK HOLES AND SETTLEMENT AREA WAS R & R.

Part: CUSP WEB — CORRODED (BS 889-902) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON DOUBLER REPAIR X -53 TO -60 BS 889-902 CUSP WEB. CUSP WEB WAS REPLACED IAW SRM 53-05, FIG 131, A-6, TREATED AND PAINTED IAW SRM 51-10-3, PAR 14 AND 21, AND CIC APPLIED IAW SRM 51-10-3, PAR 38.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PANEL 1436C COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION WAS REMOVED AND FOUND OUT OF LIMITS IAW SRM 51-22-2. THE ACCESS PANEL WAS REPLACED.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PLATE, NR 1311C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION ON FUEL ACCESS AT COUNTERSINK HOLES AND SETTLEMENT AREA WAS R & R AND WILL BE INSTALLED.

Part: FLOOR SUPPORT — CORRODED (BS 200) · airframe 67,259 hrs · 49,418 cycles

FLOOR SUPPORT WEB CORRODED BS 200 X -51, BS 213-217 X -52. WEB SECTION REPLACED.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PANEL 1363C AT COUNTERSINK HOLES AND SETTLEMENT AREA. THE CORROSION WAS REMOVED IAW SRM 51-10-03 AND FOUND OUT OF LIMITS. THE ACCESS PANEL WAS REPLACED

Part: STRUCTURE — CORRODED (RT WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON OTBD FITTING AND BORES XOS=286 AT SLAT 2 RT. OTBD FITTING WAS REMOVED IAW SRM 51-30-2 AND 51-30-8 NEW OTBD FITTING WAS DRILLED IAW SRM 51-10-4, NEW OTBD FITTING WAS TREATED AND PAINTED IAW SRM 51-10-3 P 14, 21.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PLATE 1365C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION ON FUEL ACCESS AT COUNTERSINK HOLES AND SETTLEMENT END AREA WAS R & R.

Part: BUSHING — CORRODED (HORIZONTAL STAB) · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON BOLTS, AND BUSHINGS, TO ATTACH JACKSCREW AND HORIZONTAL STABILIZER. BUSHINGS REMOVED IAW AMM 20-10-02 AND NEW WERE INSTALLED IAW DPS 1.33 AND DWG 9911846. BOLTS WERE REPLACED IAW AMM 55-10-00.

Part: CUSP WEB — CORRODED (BS 622-633) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON DOUBLER REPAIR X-56 TO X-60 BS =622-633 ON CUSP WEB. DOUBLER WAS REPLACED IAW SRM 53-05, 51-30-5 51-10-3 PAR 14,21, 51-30-5.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PANEL 1355C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION REMOVED IAW SRM 51-10-3, AND FOUND OUT OF LIMITS, THE ACCESS PANEL WAS REPLACED.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON FUEL ACCESS PANEL 1357C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION ON ACCESS PANEL REMOVED IAW SRM 51-10-03 AND FOUND OUT OF LIMITS, THE ACCESS PANEL WAS REPLACED.

Part: PAN — CRACKED (RIGHT) · airframe 62,642 hrs · 46,156 cycles

CRACK ON RT RING PAN AFT UPPER CORNER STA Y=484-503 FUSELAGE STRUCTURE. RING PAN AFT UPPER CORNER ON STA Y=484 TO 503 WAS REPAIRED IAW SRM 53-05, FIG 122.

Part: FLOOR SUPPORT — CORRODED (BS 148-200) · airframe 67,259 hrs · 49,418 cycles

CORROSION ON FLOOR SUPPORT BS 148.5 - 200, X=7 AND X=-7. THE FLOOR SUPPORT WAS REPLACED.

Part: PAN — CRACKED (CARGO DOOR) · airframe 62,642 hrs · 46,156 cycles

CRACKED FWD CARGO DOOR INNER PAN AFT END AND BEAM NR 5. RETAINER WAS REMOVED IAW SRM 51-30-1, CRACK DRILL STOPPED IAW SRM 52-03, FIG 8 AND 51-01 PAR 21 A, DOUBLER WAS FABRICATED IAW SRM 52-30D, FIG 8, DOUBLER WAS TREATED AND PAINTED IAW SRM 51-10-3 PAR 21 AND 14 DOUBLER WAS INSTALLED IAW SRM 51-30-2. RETAINER WAS INSTALLED IAW SRM 51-30-1.

Part: CUSP WEB — CORRODED (BS 608) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON RT CUSP WEB X -56 TO X -60 AND BS 608. REPAIRED IAW SRM 53-05, FIG 131A-13 53-10-3, PAR 14121.

Part: SKIN — DENTED (CARGO DOOR) · airframe 62,642 hrs · 46,156 cycles

DENTS ON AFT CARGO DOOR OUTER SKIN PREVIOUS REPAIR DOUBLERS, 5EA. SKIN WAS REPLACED IAW SRM 51-30-1, 51-30-2, 51-30-5.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 62,642 hrs · 46,156 cycles

DELAMINATED FLOOR PANEL. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: DOUBLER — CORRODED (BS 883) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON DOUBLER BETWEEN BS 883, X 54 - 60 . DOUBLER REPLACED IAW SRM 51-30-2, SRM 51-30-5, SRM 53-05, FIG 131A-6 AND SRM 51-10-3 PAR 14 Y 21.

Part: FRAME — CORRODED (BS 1271) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FRAME, BS 1271 BETWEEN LONGERONS 28 LT AND 28 RT. REPAIRED IAW SRM 53-03D, FIG 2A, 51-30-2, 51-30-5 AND 51-10-4.

Part: STOP FITTING — CRACKED (CARGO DOOR) · airframe 62,642 hrs · 46,156 cycles

CRACKED STOP FITTINGS NR 2, 3 AND 5 ON FWD SIDE AND STOP FITTING NR 5 AFT SIDE AT FWD CARGO DOOR. STOP FITTING WERE REMOVED. STOP FITTING WERE INSTALLED IAW SRM 51-30-5.

Part: FITTING — CORRODED (HORIZONTAL STAB) · airframe 62,642 hrs · 46,156 cycles

RUSTED LT INBD AND OTBD HINGE BORE FITTING ON HORIZONTAL STABILIZER PIVOT POINT STA ZRS 173. INBD AND OTBD HINGE BORE FITTING WERE REWORKED WITH FINAL DIMENSION, D 1.434". THEN 4 BUSHINGS WERE FABRICATED, D 1.4345 AND WERE INSTALLED IAW SRM 55-02 D, PAR 24.

Part: CUSP WEB — CORRODED (BS 638-664) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON DOUBLER REPAIR X-54, X-58 BS 638-664 CUSP WEB. DOUBLER WAS REPLACED IAW 53-05, FIG 131A-12 AND SRM 51-30-5 SRM 51-10-3, PAR 14, 21.

Part: FLOOR SUPPORT — CORRODED (BS 1157) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FLOOR SUPPORT BS 1157 BETWEEN SEAT TRACK 22 AND 44. DUE TO EXCESSIVE DAMAGE SUPPORT WAS REPLACED AND DRILLED. ADJUSTED NEW SUPPORT WAS TREATED AND PAINTED AND INSTALLED IAW SRM 51-30-5, D/DWG 5930544, REV DD, 51-10-4, 51-10-3, PARA 21, 14.

Part: CHANNEL — CRACKED (FLOOR PANEL) · airframe 62,642 hrs · 46,156 cycles

CRACKED CHANNEL AND SPACER ON FLOOR PANEL. REPLACED THE CHANNEL AND SPACER IAW DWG 9936639, REV "P".

Part: SPAR CAP — CORRODED (HORIZONAL STAB) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON HORIZONTAL STABILIZER LOWER REAR SPAR CAP. DAMAGE REPAIRED IAW SRM 55-03 D PAR 30.

Part: DOUBLER — CORRODED (BS 1309 FRAME) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON REPAIR DOUBLER ON FRAME BS 1309 BETWEEN LONGERONS 29LT AND 29RT. DOUBLER WAS REMOVED, AND A NEW DOUBLER WAS FABRICATED, TREATED, PAINTED, AND INSTALLED IAW SRM 51-30-2, 51-10-3 PAR 14 AND 21, 53-03D FIG 2A, 51-30-5.

Part: FRAME — CORRODED (BS 1309) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FRAME ANGLE BS 1309 BETWEEN LONGERON 29 AND 30RT. REPAIRED IAW SRM 53-03D, FIG 3 AND SRM 51-10-3, PAR 14, 21 SRM 51-30-2.

Part: SKIN — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON RT HORIZONTAL STABILIZER SKIN. REPAIRED IAW SRM 55-03, PARAGRAPH 30D.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 62,642 hrs · 46,156 cycles

DELAMINATED FLOOR PANEL. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: SUPPORT — DAMAGED (BS 693-712) · airframe 62,642 hrs · 46,156 cycles

ELONGATED HOLE IN CEILING SUPPORT BS 693 - 712 BETWEEN LONGERONS 4 - 5R. SUPPORT REPLACED IAW DWG 3353004, REV F, SRM 51-60-0, FIG 1, AND SRM 51- 10-3, PAR 21, 14.

Part: STIFFENER — CRACKED (BS 1338 BULKHEAD) · airframe 62,642 hrs · 46,156 cycles

CRACK ON BULKHEAD STIFFENER LONGERON 14R, BS 1338. STIFFENER REPLACED IAW SRM 51-3-5, 51-10-4 AND 51-10-3, PAR 14 AND 21.

Part: CUSP WEB — CORRODED (BS 993-1000) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON CUSP WEB BETWEEN BS 993-1000 AND X 54 - 60. CORROSION WAS REMOVED, MEASURE, REPAIRED, TREATED, AND PAINTED IAW SRM 51-10-3, 53-05, FIG 131A-14. NDT SPM 04-00-07, FIG 3, SHEET 1 AND 2 ORIGINAL

Part: SUPPORT — DAMAGED (BS 750-769) · airframe 62,642 hrs · 46,156 cycles

ELONGATED HOLE ON CEILING SUPPORT BS 750-769 BETWEEN LONGERONS 4 - 5R. SUPPORT REPLACED IAW DW6 3353004, REV F, SRM 51-60-0, FIG 1, AND SRM 51-10-3, PAR 21 AND 14.

Part: DOUBLER — CORRODED (BS 638-644) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON REPARATION DOUBLER BETWEEN BS 638-644 AND X 54-60. DOUBLER WAS REPLACED IAW SRM 51-30-5, 53-05, FIG 131A-13 AND 51-10-3, PAR 14 AND 21.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PLATE NR 1379C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CARD 90, ZONE 00. CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA WAS REMOVED, IAW SRM 51-10-3 AND COUNTERSINK HOLES WERE MEASURED, MAX DIAMETER ALLOWABLE IS 0.532" AND MAX. DIAMETER MEASURED IS 0.540" IN 7 ADJACENT HOLES THEREFORE WAS FOUND OUT OF LIMITS. THE ACCESS DOOR 1379C WAS REPLACED AND WILL BE INSTALLED IAW SRM 51-22-2.

Part: SEAT TRACK — CORRODED (BS 512-515) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON RT SEAT TRACK, REPAIR X -22, BS 512 - 515. REPAIR WAS REPLACED IAW SRM 53-05, FIG 4A, 51-30-1.

Part: PAN — CRACKED (CARGO DOOR) · airframe 62,642 hrs · 46,156 cycles

CRACKED AFT CARGO DOOR OUTER PAN AT AFT END OF BEAM NR 3. REPAIR WAS ACCOMPLISHED ON CRACKED AFT CARGO DOOR OUTER PAN IAW SRM 52-03, D FIG 8.

Part: FLOOR SUPPORT — CORRODED (BS 160-200) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FLOOR SUPPORT BETWEEN BS 160 - 200 X -44. FLOOR SUPPORT REPLACED IAW SRM 53-14-1, 51-10-4, 51-30-2, 51-10-3 PAR 21-14 AND 51-30-5.

Part: SEAT TRACK — CORRODED (BS 529-532) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON RT SEAT TRACK REPAIRE X -54, BS 529- 532. REPAIR WAS REPLACED IAW SRM 53-05, FIG 4A, 151-30-1.

Part: SEAT TRACK — CORRODED (BS 406-408) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON REPAIR ON SEAT TRACK X 22 BETWEEN BS 406 - 408. REPAIR WAS REPLACED IAW SRM 53-05, FIG 4A AND SRM 51-10-3, PAR 14-21, SRM 51-30-1.

Part: FLOOR SUPPORT — CORRODED (BS 1141-1170) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FLOOR SUPPORT BETWEEN BS 1141 - 1170 X 54. REPAIRED IAW SRM 51-30-5, 51-10-3, PAR 26, DWG 9930612, REV CG, 57-01, FIG 1, 51-10-3.

Part: SKIN — CORRODED (RT SLAT) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON BORES AND INTERIOR SIDES OF FITTING AT RT SLAT NO .0 STA XIS=40. AREAS WERE REWORKED AND MEASURED THEREFORE OUT LIMITS IAW SRM 57-02, PAR 9C(1) AND TABLE 1 WITH DIAMETER FWD HOLE 0.9385" AND AT HOLE 0.9385" BUSHINGS WERE FABRICATED IAW SRM 57-02, PAR 9 C(2).

Part: RIB — CORRODED (LT WING SLAT) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON OTBD/INBD RIBS AFT BORES STA XIS 186.3, LT SLAT PANEL NR 1. AREAS WERE REWORKED AND MEASURED INBD HOLE 0.938" OTBD HOLE 0.938" THEREFORE OUT LIMITS IAW SRM 57-02, PAR 9 C(1). BUSHINGS WERE FABRICATED AND INSTALLED IAW SRM 57-02, PAR 9C (2) 51-10-3, PAR 21, 51-30-10, PAR 7, 8.

Part: RIB — CORRODED (LT WING SLAT) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON INBD/ OTBD RIBS, FWD BORES, STA XOS 429 AT LT SLAT PANEL NR 4. AREAS WERE REWORKED AND MEASURED INBD HOLE 0.9375" OTBD HOLE 0.9375" THEREFORE LIMITS IAW SRM 57-02, PAR 9 C, 1, BUSHINGS WERE FABRICATED AND INSTALLED IAW SRM 57-02, PAR 9C (2) 51-10-3 PAR 21, 51-30-10 PAR 7/8.

Part: FLOOR PANEL — DELAMINATED (CABIN) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

DELAMINATED FLOOR PANEL. FLOOR PANEL FABRICATED IAW AMM 53-20-201-201.

Part: CUSP WEB — CORRODED (BS 1060-1071) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON REPAIR OF CUSP WEB, BS 1060 - 1071, X -54 TO -60. REPAIRED IAW SRM 51-30-5, SRM 53-05 FIG. 131A-6, SRM 53-05, FIG 131A-6, AND SRM 53-05, FIG 131A-6.

Part: DOUBLER — WORN (CARGO DOOR) · airframe 62,642 hrs · 46,156 cycles

WORN OUT REPAIR DOUBLER AFT CARGO DOOR OUTER PAN AT AFT UPPER CORNER. REPAIR WAS REPLACED IAW SRM 51-30-2 52-01, FIG 2.

Part: DOUBLER — CORRODED (BS 1167) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON DOUBLER BS 1167 AND X 44 TO 54. DOUBLER WAS REPLACED IAW SRM 51-30-5, 53-05 TIG 131A-19 SHEET 2, 51-10-3, PAIR 21,14.

Part: STRUCTURE — CORRODED (NR 2 SLAT) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON UPPER BORES AND INBD FACES OF INBD/OTBD LUGS OF INBD FITTING XOS 196 AT SLAT 2 RT. AREAS WERE REWORKED AND FOUND OUT LIMITS IAW SRM 57-02, PAR 9 C (1). BUSHINGS FABRICATED IAW SRM 57-02, PAR 9 C.

Part: RIB — CORRODED (LT WING SLAT) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON INBD AND OTBD RIBS FWD BORES STA XIS 136 AT LT SLAT PANEL NR 1. AREAS WERE REWORKED AND MEASURED INBD HOLE 0.938", OTBD HOLE 0.938". THEREFORE OUT OF LIMITS IAW SRM 57-02, PAR 9C (1). BUSHINGS WERE FABRICATED AND INSTALLED IAW SRM 57-02, PAR 9C (2) 51-10-3, PAR 21, 51-30-10 PAR 7,8.

Part: STRUCTURE — CORRODED (NR 1 SLAT) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FWD BORE OF INBD LUG OF OTBD FITTING STA XIS=186 AT SLAT 1 RT. AREAS WERE REWORKED AND MEASURED THEREFORE OUT LIMITS IAW SRM 57-02, PAR 9 C (1) TABLE 1 WITH DIAMETER 0.938". BUSHING WAS FABRICATED AND INSTALLED IAW SRM 57-02, PAR 9 C 2, LP1749542.

Part: SKIN — CORRODED (NR 5 SLAT) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON INBD AND OTBD RIBS FWD/AFT BORES XOS 530.6 AT LT SLAT PANEL NR 5. AREAS WERE REWORKED AND FOUND OUT LIMITS IAW SRM 57-02, PAR 9 C(1) AND TABLE 1. BUSHINGS WERE FABRICATED IAW SRM 57-02, PAR 9 C 2.

Part: FRAME — CRACKED (BS 1380) · airframe 62,642 hrs · 46,156 cycles

CRACKED FRAME BS 1380 LONGERON 14L . FRAME REMOVED IAW SRM 51-30-2 AND 51-30-5 AND A NEW FRAME WAS INSTALLED IAW SRM 51-10-2, 51-14-4 FIG 1, 51-30-2 AND 51-30-5.

Part: FLOOR SUPPORT — BROKEN (BS 769-788) · airframe 62,642 hrs · 46,156 cycles

BROKEN FLOOR SUPPORT BETWEEN BS 769 - 788 X 0. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-2, 51-30-5, 51-10-4 AND 51-10-3 PAR 14, 21.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PLATE NR 1454C AT COUNTERSINK HOLES AND SETTLEMENT. CORROSION AT COUNTERSINK HOLES AND SETTLEMENT AREA WAS REMOVED IAW SRM 51-22-2A. COUNTERSINK HOLES WERE MEASURED MAX DIAMETER ALLOWABLE IS .532" AND MAX DIAMETER MEASURED IS .590 IN (2) HOLES. SETTLEMENT AREA WAS MEASURED. ORIGINAL THICKNESS IS .150" AND MAX MATERIAL REMOVED IS .052" THEREFORE WAS FOUND OUT OF LIMITS IAW SRM 51-22-2A. ACCESS PLATE NBI 1454C WAS REPLACED IAW IPC 57-30-00-05B AND WILL BE INSTALLED.

Part: PAN — CRACKED (BS 750) · airframe 62,642 hrs · 46,156 cycles

CRACKED LT RING PAN BS 750 UPPER/FWD CORNER. RING PAN WAS REPAIRED IAW SRM 53-05, FIG 122, SRM 51-10-3, PAR 14,21, SRM 51-30-5 AND ER/A 487747-14 MA REV ORIGINAL.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PLATE NR 1476C AT COUNTERSINK HOLES AND SETTLEMENT AREA. CORROSION AT COUNTERSINK HOLES AND SETTLEMENT AREA WAS REMOVED IAW SRM 51-22-2.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PLATE NR 1303C AT COUNTERSINK HOLES AND SETTLEMENT AREA. BLEND OUT REPAIR IS NOT PERMITTED ON THE UPPER WING ACCESS DOOR, PN 3912757. DUE TO REDUCE AREA OF THE CONDUCTIVE. INTERFACE AND ACCESS PLATE 1303C WAS REPLACED AND WILL BE INSTALLED.

Part: PAN — CRACKED (BS 1136) · airframe 62,642 hrs · 46,156 cycles

CRACKED RT RING PAN BS 1136, UPPER/AFT CORNER. RING PAN WAS REPAIRED IAW SRM 53-05, FIG 122, SRM 51-10-3, PAR. 14.21, SRM 51-30-5 AND ER/A 487747-14 MA REV ORIGINAL.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON FUEL ACCESS PLATE NR 1409C AT COUNTERSINK HOLES AND SETTLEMENT AREA. FUEL ACCES PLATE NR 1409C WAS REPLACED.

Part: PAN — CRACKED (BS 750) · airframe 62,642 hrs · 46,156 cycles

CRACKED RT RING PAN BS 750 LOWER AFT CORNER. RING PAN WAS REPAIRED IAW SRM 53-05 FIG 122, SRM 51-10-3, PAR 14-21, SRM 51-30-2 AND ER/A 487747-14, MA REV ORIGINAL.

Part: PAN — CRACKED (BS 788) · airframe 62,642 hrs · 46,156 cycles

CRACKED LT RING PAN, BS 788 UPPER/FWD CORNER. RING PAN WAS REPAIRED IAW SRM 53-05, FIG. 122, SRM 51-10-3, PAR 14.21, SRM 51-30-5 AND ER/A 487747-14 MA REV ORIGINAL.

Part: CUSP WEB — CORRODED (BS 701-703) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON CUSP WEB BETWEEN BS 701-703 AND X 54 - 60. REPAIRED IAW SRM 53-05, FIG 131A-7, SRM 51-10-3, SRM 51-30-2, AND SRM 51-30-5.

Part: PAN — CRACKED (BS 946) · airframe 62,642 hrs · 46,156 cycles

CRACKED LT RING PAN BS 946 LOWER/FWD CORNER. RING PAN WAS REPAIRED IAW SRM 53-05, FIG 122, SRM 51-10-3, PAR 14.21, SRM 51-30-5 AND ER/A 487747-14MA, REV ORIGINAL.

Part: DOUBLER — CORRODED (BS 845) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON DOUBLER BETWEEN BS 845 X 54 - 60. THE DOUBLER WAS REMOVED AND A REPAIR WAS FABRICATED, TREATED, PAINTED AND INSTALLED IAW SRM 51-30-2 AND 53-05, FIG 131, A-13.

Part: SEAT TRACK — CORRODED (BS 823-827) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION FOUND ON RT SEAT TRACK X -54, BS 823-827. REMOVED AND REPLACED IAW SRM 51-30-1 AND 53-05, FIG 4B-1.

Part: SEAT TRACK — CORRODED (BS 268-272) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON RT SEAT TRACK X -54, BS 268-272 . SEAT TRACK REPLACED IAW SRM 53-05, FIG 4A.

Part: SEAT TRACK — CORRODED (BS 967-970) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON RT SEAT TRACK X -22 BS 967-970. SEAT TRACK REMOVED AND REPLACED IAW SRM 53-05, FIG 4A, SHEET 1 AND SRM 51-10-3, PAR 38.

Part: SEAT TRACK — CORRODED (BS 1085-1087) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON SEAT TRACK REPAIR BETWEEN BS 1085 - 1087 X 54. NEW REPAIR WAS INSTALLED IAW SRM 53-05, FIG 4.

Part: CUSP WEB — CORRODED (BS 674-685) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON CUSP WEB BETWEEN BS 674 - 685 AND X 54 - 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131, SRM 51-10-3, PAR 14, 21, SRM 51-30-2, AND SRM 51-30-5.

Part: LONGERON — CRACKED (BS 1437) · airframe 62,642 hrs · 46,156 cycles

CRACKED LONGERON 12L BS 1437. REMOVED AND REPLACED IAW SRM 51-30-2, 51-30-5, SRM 53-02, FIG 18, & 51-10-4.

Part: BEAM — CORRODED (CARGO DOORWAY) · corrosion level 2 · airframe 62,642 hrs · 46,156 cycles

CORROSION ON MID CARGO DOOR BEAM TEE AND BEAM WEB FROM BS 636 - 693. CORROSION WAS REMOVED IAW SRM 51-10-3 PAR 26, AND FOUND OUT LIMITS BUT THE BEAM WEB FOUND WITHIN LIMITS. BEAM WEB WAS TREATED AND PAINTED IAW SRM 51-10-3, PAR 21 AND 14. BEAM TEE WAS REPLACED IAW SRM 51-30-2 AND 51-30-5 AND DWG PL9957663, REV W.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHTS) · airframe 62,069 hrs · 45,742 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT SEVERAL OF THE EMERGENCY LIGHTS IN THE CABIN WERE INOPERATIVE. MAINTENANCE REPAIRED CONNECTORS AND RELAMPED WHERE NEEDED. THE SYSTEM WAS OPERATIONALLY CHECKED AS FUNCTIONAL.

Part: STRUCTURE — CRACKED (VERTICAL STAB) · airframe 59,114 hrs · 43,707 cycles

DURING SCHEDULED INSPECTION, SEVEN FASTENER HOLES EXHIBITED CRACK INDICATIONS ON THE LT SIDE OF THE VERTICAL STABILIZER IAW AD 2011-15-01. REPAIRS ACCOMPLISHED IAW ER/A 516705-14AD.

Part: RIB — CRACKED (VERTICAL STAB) · airframe 62,428 hrs · 46,006 cycles

VERTICAL STAB INTERNAL RIB, CRACKED STA 50. INSTALLED NEW RIB IAW SRM 51-01, SRM 51-30 AND DWG 9911881.

Part: RIB — CRACKED (VERTICAL STAB) · airframe 62,428 hrs · 46,006 cycles

VERTICAL STABILIZER INTERNAL RIB, PN 9911881-9 CRACKED STA 50-AFT LOWER END BAR CODE: HK2RIH, WO: 10976-69, NR CARD SERIAL: 273: POS: AF TASK HRS: 0004.0, TASK ELAPSE TIME, HRS: 0004.0, RII: Y DRILLED NEW RIB, PN 9911881-9 TO SIZE, DEBURRED & PRIMED. OK TO INSTALL. INSTALLED RIB IAW DWG 9911881-9, SRM'S 51-01 & 51-30.

Part: STRUCTURE — CRACKED (VERTICAL STAB) · airframe 59,114 hrs · 43,707 cycles

DURING SCHEDULED INSPECTION, THREE FASTENER HOLES EXHIBITED CRACK INDICATIONS ON THE RT SIDE OF THE VERTICAL STABILIZER IAW AD 2011-15-01. REPAIRS ACCOMPLISHED IAW ER/A 516705-14AD.

Part: DOOR FRAME — CRACKED (BS 886) · airframe 59,110 hrs · 43,704 cycles

OVERWING FRAME BS 886 LT CRACKED, IN UPPER RADIUS OF FRAME TAB. REPAIRS COMPLETED.

Part: BRACKET — WORN (TAILCONE) · airframe 59,110 hrs · 43,704 cycles

MX DISCOVERED THAT THE TAILCONE LT AND RT SPRING BRACKETS ARE WORN FROM THE SPRING. THE BRACKETS WERE REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS. THE RII STEPS WERE COMPLETED AND THE FUNCTIONAL CHECK WAS COMPLETED SATISFACTORILY.

Part: CAM — WORN (TAILCONE RELEASE) · airframe 59,110 hrs · 43,704 cycles

MX DISCOVERED THAT THE TAILCONE RELEASE MECHANISM CAM BASE WAS WORN OUT OF ALLOWABLE LIMITS. THE CAM BASE WAS REPLACED AND THE SYS WAS RIGGED TO SPECIFICATIONS. THE RII WAS SATISFACTORY.

Part: DOOR SILL — CORRODED (CARGO BAY) · corrosion level 2 · airframe 62,428 hrs · 46,006 cycles

LOWER DOOR SILL BS 636-693 HAS CORROSION AT THE CARGO DOORWAY. REPAIRED IAW SRM 53-05, FIG 123.

Part: LATCH — WORN (TAILCONE RELEASE) · airframe 59,110 hrs · 43,704 cycles

MX DISCOVERED THAT THE TAILCONE RELEASE SPADE LATCH RECEPTACLES WERE WORN OUT OF ALLOWABLE LIMITS. THE RECEPTACLES WERE REPLACED AND THE SYS WAS RIGGED TO SPECIFICATIONS. THE FUNCTIONAL CHECK WAS COMPLETED SATISFACTORILY.

Part: SKIN — CRACKED (BS 1380) · airframe 59,110 hrs · 43,704 cycles

SKIN CRACKED APPROX .2500" LONG AT RIVET, BS 1380, 2" ABOVE LONGERON 14 RT. REMOVED FASTENERS IN AREA, CUT OUT SKIN IAW SRM 53-04, FIG 1B. 1" DIAMETER CUTOUT. ACCOMPLISHED HFEC. CONTAINMENT 06-10-001 NO CRACKS FOUND. FABRICATED FILLER AND DOUBLER AND INSTALLED REPAIR WET WITH SEALANT IAW SRM 53-04, FIG 18 AND PROCESS STANDARD 900-5-1-NR 4.

Part: CABLE — FRAYED (TAILCONE RELEASE) · airframe 59,110 hrs · 43,704 cycles

MX DISCOVERED THAT THE TAILCONE RELEASE CABLE WAS FRAYED BEYOND ALLOWABLE LIMITS. THE CABLE WAS REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS. THE RII STEPS WERE COMPLETED.

Part: SKIN — DAMAGED (HORIZONTAL STAB) · airframe 59,110 hrs · 43,704 cycles

HORIZONTAL STAB UPPER CENTER SKIN PANEL DAMAGED. REPAIRED IAW AA 5510-01086.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 58,345 hrs · 43,122 cycles

DURING SERVICE CHECK, COCKPIT EMERGENCY LIGHTS WERE FOUND TO BE INOPERATIVE. TROUBLESHOOTING INDICATED NO VOLTAGE AT THE EMERGENCY LIGHT BATTERY PACK. REPLACED BATTERY PACK POWER SUPPLY IAW AMM 33-55 AND OPERATION CHECKED GOOD.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 57,237 hrs · 42,311 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 29Ï¿½31 OF THE CABIN WERE INOPERATIVE. MX REPLACED THE BATTERY PACK POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 55,650 hrs · 41,245 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE FIRST CLASS SECTION OF THE CABIN HAD FAILED. MAINTENANCE REPLACED THE BATTERY CHARGER AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 55,378 hrs · 41,059 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT ROW 35D IN THE CABIN, WAS INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 55,303 hrs · 41,011 cycles

FORWARD GALLEY TRACK CORROSION AT STA 196 LBL 44. REPAIRED BY SEAT TRACK REPLACEMENT SPLICE AT STA 221 PER ERA 498864-14 (NRC 142).

Part: OIL CAP — LEAKING (APU) · airframe 55,180 hrs · 40,923 cycles

FLIGHT ATTENDANT REPORTED SMOKE IN THE CABIN WITH THE LAV SMOKE DETECTORS SOUNDING AT TAKEOFF. MAINTENANCE FOUND THE APU HAD INJESTED OIL. THE OIL CAP WAS REPLACED. APU INLET CLEANING WAS ACCOMPLISHED AND LEAK CHECK WAS GOOD.

Part: CONNECTOR — BROKEN (CABIN) · airframe 54,018 hrs · 40,067 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY LIGHTS AT SEAT 24DE INOPERATIVE. MAINTENANCE REPLACED BROKEN CONNECTOR TO LIGHT ASSEMBLY. OPERATION OF LIGHTS NOW CHECKS OK.

Part: SKIN PANEL — DAMAGED (VERTICAL STAB) · airframe 53,471 hrs · 39,698 cycles

WHILE IN LTR CK IN ATL MULTIPLE HOLES LOCATIONS WERE FOUND DAMAGED ON LT & RT EDGES OF VERTICAL STAB L/E UPPER REMOVABLE PANEL SKIN, 26 DAMAGED HOLES ON RT & 59 DAMAGED HOLES ON THE LT SIDE.

Part: SPAR — CRACKED (WING) · airframe 53,477 hrs · 39,702 cycles

WING REAR SPAR CRACKED AT XRS 164. REPAIRED IAW AA 5710-01110.

Part: PANEL — MISSING (RT AILERON) · airframe 51,938 hrs · 38,701 cycles

PANEL MISSING ONTOP OF RT AILERON CA-INSTALLED RT WING PANEL TOP OF RT AILERON. OK FOR SVC.

Part: LONGERON — CRACKED (FS 994) · airframe 48,241 hrs · 36,267 cycles

LONGERON NR 20 DRAG ANGLE, LT AND RT, WERE FOUND CRACKED IN THE VERTICAL LEG NEAR FS 994. THREE CRACKS WERE TRIMMED OUT, THE LONGEST CRACK BEING 1.75 INCHES. EACH DRAG ANGLE WAS REPAIRED WITH A DOUBLER ANGLE AND A TRIPLER ANGLE.

Part: DOOR FRAME — CORRODED (AFT PAX DOOR) · airframe 48,241 hrs · 36,267 cycles

DURING HMV AT GDL, CORROSION WAS FOUND IN THE AFT PASSENGER DOOR JAMB AT THE BOTTOM OF THE DOOR FRAME. THE CORROSION WAS TRIMMED OUT AND A REPAIR WAS INSTALLED PER BOEING INSTRUCTIONS.

Part: LONGERON — DAMAGED (FUSELAGE) · airframe 48,241 hrs · 36,267 cycles

WHILE PERFORMING PREVENTATIVE MOD ON LONGERONS AT STA Y=160, INADEQUATELY DRILLED HOLES WERE FOUND ON LONGERON LT 22 AND SKIN. FASTENERS WERE INSTALLED CORRECTLY IAW SRM 51-30-5 AND SRM 51-30-1.

Part: BULKHEAD — DENTED (FUSELAGE) · airframe 48,241 hrs · 36,267 cycles

HIDDEN DAMAGE, DENT, ON AFT P DOME. REMOVED DAMAGE IAW SRM 53-05 FIG 115. REPAIR PARTS INSTALLED IAW EA 09-086680-12 ME 06.

Part: SKIN — DAMAGED (RUDDER) · airframe 48,241 hrs · 36,267 cycles

DAMAGED METALLIZED AND PAINT COAT OF RUDDER SURFACE. DAMAGE REMOVED IAW SRM 51-70-1A PAR 23 (A). ONE PLY OF STYLE 120 GLASS FABRIC AND LAMINATE ASTRO STRIKE (AC28 SCREEN) IMPREGNATED WITH EA956 A/B RESIN WAS APPLIED AND CURED IAW SRM 51-70-1A PAR 23 (2,3,4,5,6,7,AND 8). RUDDER PAINTED IAW SRM 51-10-3B. CHECKED BALANCE IAW SRM 51-40-1D PAR 20.

Part: LATCH — WORN (TAILCONE RELEASE) · airframe 48,241 hrs · 36,267 cycles

WORN UPPER RT LATCH ON TAILCONE RELEASE SYSTEM. REPLACED LATCH IAW AMM 20-30-01. OPS CHECK WILL BE PERFORMED IAW OPN 7915 CARD 986.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 48,241 hrs · 36,267 cycles

EXFOLIATION CORROSION ON LOWER DOOR JAMB BTW STA Y=370 TO 427 AT FWD CARGO COMP. REMOVED CORROSION IAW SRM 51-10-3 PAR 35. FOUND OUT OF LIMITS IAW SRM 53-01 FIG 1. INSTALLED REPAIR PARTS IAW SRM 53-05D.

Part: TUBE — WORN (BS 1510) · airframe 48,241 hrs · 36,267 cycles

WORN CABLE GUIDE TUBE ON FRAME Y=1510 CANT LOWER SECTION. REPLACED CABLE GUIDE TUBE IAW AMM 20-30-01-201.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 48,241 hrs · 36,267 cycles

CRACK ON EXTERNAL SURFACE OF OVERWING LONG 20 AT AFT END OF THE LT TRAPEZOID PANEL STA Y=994.5. DAMAGE REMOVED AND NO CRACKS FOUND IAW NDT SPM 06-10-01 001. REPAIR PARTS WERE INSTALLED IAW ERA 472714-14 REV ORIG.

Part: CABLE — CORRODED (TAILCONE RELEASE) · airframe 48,241 hrs · 36,267 cycles

RUSTED CABLE TERMINALS ON TAILCONE RELEASE SYSTEM. CABLE WAS REPLACED IAW AMM 53-53-00-501. FUNCTIONAL CHECK WILL BE PERFORMED ON OPN 6908AD CARDS 1162 AND 1163.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 48,241 hrs · 36,267 cycles

EXFOLIATION CORROSION ON AFT P-DOME SKIN AT LOWER AREA. RELACED DAMAGED PARTS IAW SRM 53-05 FIG 101.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 48,241 hrs · 36,267 cycles

CRACK ON LONGERON 20 RT BTW STA Y=993 AND Y=998. DAMAGE CUT OUT. NO CRACKS FOUND IAW NDT SPM 06-10-01 001. REPAIR PARTS INSTALLED IAW ERA 472714-14 REV ORIG.

Part: BEAM — CORRODED (DOOR FRAME) · airframe 48,241 hrs · 36,267 cycles

EXFOLIATION CORROSION ON LOWER BEAM OF AFT CARGO DOOR. CORROSION WAS REMOVED AND FOUND TO BE OUT OF LIMITS IAW SRM 53-01 FIG 1. REPAIR PARTS INSTALLED IAW SRM 53-05 FIG 12B.

Part: TAB — DENTED (RT ELEVATOR) · airframe 48,241 hrs · 36,267 cycles

DENT ON RT ELEVATOR CONTROL TAB TRAILING EDGE. THIS ITEM WAS WORKED ON OPN 1031 CARDS 1254 TO 1262. REPAIR WAS IDENTIFIED IAW PS 900-5-1 NO 4. TAD WAS BALANCED IAW SRM 55-20-2D.

Part: SKIN — DENTED (LT WING LE SLAT) · airframe 48,241 hrs · 36,267 cycles

FOUND BY ACS DENT IN LEADING EDGE SLAT LT WING 8 FEET OTBD OF FUSELAGE. THIS NR WAS ACCOMPLISHED WITH NR T0130985.

Part: CHARGER — FAILED (E&E BAY) · airframe 46,567 hrs · 35,164 cycles

BATTERY CHARGER FAILED - UPON SHOP EXAMINATION, FOUND C9 DAMAGED BY HEAT FROM R6. NOTE: THIS CHARGER HAS HAD SB 203BC102-24-06 COMPLIED WITH (MOVED R6 TO BASE OF C9 ASSEMBLY). THE DAMAGE TO C9 APPEARED TO BE ALMOST TO THE POINT OF CAUSING C9 TO IGNITE AND CAUSE A BATTERY CHARGER FIRE.

Part: HYDRAULIC SYSTEM — LOW (RIGHT) · airframe 40,525 hrs · 31,161 cycles

RIGHT HYD SYSTEMS QUANTITY DECREASED TO 5 QTS INFLIGHT. ACCOMPLISHED HYD QUANTITY DECREASING CHECKLIST. QUANTITY SHOWED 19 QTS INFLIGHT AND 7 QTS AFTER LANDING OPERATIONS NORMAL. INSP AIRCRAFT FOR HYD LEAKS, NONE FOUND. SERVICED HYD TO CORRECT LEVEL PER M/M AND CYCLED FLT CONTROLS AND LANDING GEAR THROUGH SEVERAL CYCLES WITH LANDING GEAR PINS INSTALLED. OPERATIONS AND INDICATIONS NOW NORMAL.

Part: BALLAST — OVERHEATED (ROW 22 LEFT BIN) · airframe 37,756 hrs · 29,198 cycles

AT GATE WHILE BOARDING, A PAX NOTICED SMOKE FROM ROW 22 LEFT OVERHEAD BIN. INSPECTED AREA AND FOUND SIDEWALL LIGHT BALLAST OVERHEATED. REPLACED SAME.

Part: PRESSURE PANEL — DAMAGED (MLG WW) · airframe 37,049 hrs · 28,689 cycles

FUSELAGE - MLG WHEEL WELL - SLANT PRESSURE PANEL REPAIR IAW 09-085387-12. C/W 09-085387-12 ME01.

Part: GENERATOR — INOPERATIVE (#1 ENGINE) · airframe 35,360 hrs · 27,501 cycles

ON TAKEOFF ROLL AFTER AUTO THROTTLES ENGAGED LEFT GENERATOR CAUSED ELECTRICS TO FLUCUATE AND DISENGAGE AUTO THROTTLES ABORT AT 20-30 KNOTS ACCOMPLISHED. WORKING MCO LEFT CSD LOW PRESSURE LIGHT. RAN ENGINE AND FOUND LEFT CSD BAD. CHANGED MEL TO 24-00-01A. CSD DISC LOW LIGHT GOOD AND NO VOLTS OR FREQS. RECONNECTED CANNON PLUG.

Part: SENSOR — DIRTY (LT MLG) · airframe 34,955 hrs · 27,236 cycles

LT MAIN LDG GEAR LIGHT REMAINED ON WITH GEAR DOOR OPEN LIGHT ILLUM AFTER T/O. REFERRED TO POM AND CYCLED GEAR. WHEN LIGHT EXTINGUISHED MAIN GEAR DOOR EXT BEFORE LT MAIN LDG GEAR LIGHT. CLEANED LT MLG DOOR PROX SENSOR. RAN GEAR DOOR. IND NORMAL. NO FAULTS ON PSEU.

Part: LIGHT — INOPERATIVE (COCKPIT) · airframe 34,124 hrs · 26,673 cycles

RIGHT MAIN GEAR BULB BURNT OUT. RELAMPED RIGHT MAIN GEAR BULBS PER MM, CHECKS OK.

Part: TAIL CONE — DEPARTED (FUSELAGE) · airframe 31,332 hrs · 24,674 cycles

AT PUSHBACK GOT TAIL CONE UNSAFE MESSAGE WITH ASSOCIATED TAILCONE SEPARATED FROM A/C AND LYING ON GROUND BEHIND THE ACA. INSTALLED NEW TAILCONE PER M/M AND REMOVED AND INSTALLED NEW SLIDE PACK.

Part: SWITCH — MALFUNCTIONED (NLG) · airframe 30,149 hrs · 23,752 cycles

ON FINAL APPROACH GREEN NOSE GEAR LT DID NOT ILLUMINATE, NO RED LIGHT GEAR WAS CYCLED IAW POM CKLIST WITH SAME RESULT. NOSE GEAR PIN ON THROTTLE QUADRANT INDICATED THE NOSE GEAR WAS DOWN. ON NEXT APPROACH WHEN GEAR WAS LOWERED ALL INDICATIONS (LTS AND PIN) WERE NORMAL. REPLACED NOSE GEAR LOCKED PROX SW D1-32 AND NOSE GEAR POS INTERLOCK SW S1-412. RAN NOSE GEAR SEVERAL TIMES. ALL INDS NORMAL. OP CHECKS GOOD PER MM.

Part: SLIDE — FAILED (TAIL CONE) · airframe 29,588 hrs · 23,322 cycles

ATC ORDERED AIRCRAFT TO LAND ASAP FOR SECURITY CONCERNS. RAMP PERSONNEL PULLED OUTSIDE EMERGENCY HANDLE AND DEPLOYED THE TAIL CONE. HOWEVER THE EMERGENCY SLIDE DID NOT DEPLOY. MTC INSTALLED TAIL CONE AND AIRCRAFT WAS FERRIED TO ATL. SLIDE WAS REPLACED IN ATL DPN 259001305.

Part: APU — LEAKING (APU BAY) · airframe 28,251 hrs · 22,327 cycles

PASSING FL 220 WE GOT A RT ICE PROT TEMP HIGH LIGHT WE CLOSED THE RT CROSSFEED VALVE THEN GOT A RT AIR COND TEMP HILIGHT FOLLOWED BY SMOKE IN THE CABIN AND COCKPIT FOLLOWED CK LIST SMOKE STOPPED. FOUND APU OIL LEAKING INTO APU INLET C/W OPN 5088 UNABLE TO FIND SOURCE OF APU OIL LEAK UNABLE TO CLEAN APU INLET THIS STA T/S PACK SYS RAN ADJUST/TEST AND AUGMENTATION VALVE CK PER M/M AND PFHB ALL CKS NORMAL. APU FWD TO MCO/PLAC FOR OIL CONTAMINATION.

Part: RADOME — BIRD STRIKE (NOSE) · airframe 26,791 hrs · 21,263 cycles

BIRD STRIKE AT 500 FT DEPARTIANG CVG. RETURNED TO CVG. SMELL INDICATED INGESTION INTO ENGINE BUT NO ENGINE PARAMETERS CHANGED OR GAVE ANY ABNORMAL INDICATION. SMELL SUBSIDED IN 5 MINUTES. PERFORMED BIRD STRIKE CONDITION CHK PER M/M 05-51-08-6. ALL NORMAL. RAN BOTH ENGINES, NO ODORS FOUND. REMOVED BIRD RESIDUE FROM RADOME.

Part: HARNESS — BROKEN (SEAT 24) · airframe 26,568 hrs · 21,105 cycles

SOME EMERGENCY TRACK LIGHTS INOP. FOUND 4CD 10ED AND 38ED HAVE BAD SOCKETS. REPLACED SAME. FOUND 12ED AND 24ED WITH BAD SEAT HARNESS. REPLACED SAME. BLEW FUSE IN F/C PWR SUPPLY WHILE T/S. REPLACED SAME ABOVE 4CD, EMERGENCY LIGHT SYS CKS NORMAL.

Part: APU — LEAKING (AFT) · airframe 26,533 hrs · 21,081 cycles

RETURN TO BDL. SMOKE IN REAR OF CABIN. AFT SMOKE DET SOUNDING, SMOKE CLEARED CABIN PRIOR TO LANDING. FOUND APU LEAKING OIL INTERNALLY. PERFORMED DUCT AND PACK BURN OUT PROCEDURES. REPLACED LEFT AND RIGHT COALESCER BAGS. RAN BOTH ENGINES TO TAKEOFF POWER, WITH BOTH PACKS ON. NO SMOKE NOTED. INSPECTED ALL PNEUMATIC DUCTS, NO CONTAMINATION FOUND.

Part: WIRE — BROKEN (ROW 3CD)

SEAT 3CD EMERGENCY TRACK LIGHT INOP. REPLACED LIGHT.

Part: LINE — LEAKING (RT ENGINE)

AT FLT LEVEL 220, JUST AFTER LIFT OFF, MASTER CAUTION LIGHT ILLUMINATED WITH RIGHT HYD PRESS LOW MSG. RIGHT HYD PRESS AND QTY SHOWED ZERO. RIGHT HYD SYS FAILURE CHECKLIST RUN. MAIN LANDING GEAR DOORS CONTACTED THE RUNWAY RUNWAY ABOUT 70 KNOTS. FOUND HYD HOSE FROM RIGHT ENGINE PRESS FILTER TO SOILD LINE ON SIDE OF FUSELAGE LEAKING. MADE APPROVED REPAIR. HYD RESERVIOR STILL HAD FLUID INDICATING AT THE RESERVIOR, SERVICED FULL RAN ENGINE LEAK CKS OK.

Part: GENERATOR — FAILED (NR 1 ENGINE)

LT CSD OIL LOW PRESS LIGHT ILLUMINATED IN FLT. TEMP RAPIDLY RISING, GEN CYCLING ON AND OFF. CSD DISCONNECTED. APU ON MCO AND PLAC FOR NOT STARTING. REPAIRED APU AND REMOVED MCO AND PLAC PLACED LT GEN ON MCO AND PLAC PER MEL 24-00-01A.

Part: SKIN — DENTED (BS 237)

FUSELAGE SKIN WAS FOUND DENTED AT APPROX STA 237 L18L TO 19L. REPAIRED PER ERA 331011-14.

Part: SKIN — DENTED (BS 237)

FUSELAGE SKIN FOUND DENTED AT STA 237 AT L17L-L18L. REPAIRED PER ERA 331010-14.

Part: SKIN — DENTED (LT TE FLAP)

DENT WAS FOUND IN THE LT SIDE OUTBOARD FLAP LWR SURFACE AT APPROX XFLS-294. REPAIRED PER ERA 331007-14.

Part: SKIN — CORRODED (BS 783)

CORROSION WAS FOUND UNDER THE RT RUB STRIP AT FS 779 TO 787 BETWEEN L28L AND L29R. REPAIRED PER ERA 330991-14.

Part: PANEL — LEAKING (LT WING)

FUEL LEAKING IN-FLIGHT FROM PANEL ON TOP OF LT WING. RE-TORQUED FUEL ACCESS PANEL ON LT WING.

Part: STRUT — REQD SERVICE (NLG)

NOSE GEAR FAILED TO RETRACT. SERVICED STRUT AND JACKED A/C. RETRACTED NOSE GEAR SEVERAL TIMES, OPERATION NORMAL.

Part: RETRACT MECH — MALFUNCTIONED (NLG)

AIR TURN-BACK. UNSAFE NOSE GEAR INDICATION WITH LOUD AIR NOISE. PROCEDURE ACCOMPLISHED. ALL NORMAL GEAR DOWN. INDICATED NORMAL FOR LANDING.

Part: STRUT — REQD SERVICE (NLG)

AFTER T/O, NOSE GEAR WOULD NOT RETRACT, HAD RED NOSE LIGHT. MAIN GEAR OPERATED NORMAL. SERVICED NOSE STRUT.

Part: BATTERY CHARGER — FAILED (E/E COMP)

ON PREDEPARTURE SAW SMOKE COMING FROM 2 VENTS BELOW E AND E COMPARTMENT. REPLACED BATTERIES AND CHARGER, OPS NORMAL. SHOP INSPECTION DETERMINED CHARGER FAILED. PROVIDED CONTINUOUS FULL CHARGE, OVERHEATING THE BATTERY.

Part: SKIN — DENTED (FS 484)

THE FUSELAGE SKIN AT FS 484 BETWEEN STR 27 AND 28R WAS DAMAGED REQUIRING A CUTOUT MEASURING APPROX 3 INCH BY 4.5 INCH. ACCOMPLISHED REPAIRS PER DL ERA 27245-14.

Part: STARTER — OIL LEAK (APU)

ON CLIMBOUT F/A REPORTED SMOKE ODOR IN CABIN, TURNED RT PACK OFF, SMOKE SEEMED TO DISSIPATE, RETURNED FLT TO PHL. FOUND OIL LEAK ON APU STARTER. ITEM WAS DEFFERRED PER MEL, ROR RETURN TO SERVICE, LATER STARTER WAS REPLACED, OPERATION NORMAL.

Part: ATTACH ANGLE. — CRACKED (LT ENG PYLON)

FOUND ON D-2 LETTER CHECK, CRACK AT LEFT ENG PYLON TO FUSELAGE ATTACH ANGLE. REPAIRED PER SRM 54-04A FIG 4.

Part: SKIN — CRACKED (R/H NLG WW)

FOUND ON D-2 LETTER CHECK, .375 INCH CRACK AT RT NLG WHEEL WELL AFT DOOR HINGE CUTOUT. REPAIRED PER SRM 53-05 FIG 62A.