N971DL

Part: UNKNOWN — ODOR (CABIN) · airframe 73,864 hrs · 54,964 cycles

FA REPORTED FUMES AFTER T/O TRHU 10,000. FUMES DISSAPATED AFTER ABOUT 10 MINUTES. FLT CONTINUED. COMPLIED WITH NO GO ODI PREV. 2172 IAW AMDS CARD 2120-2367. NO OIL CONTAMINATION FROM EITHER ENG OR APU. APU INLET WAS DIRTY BUT NOT OIL CONTAMINATED. CLEANED APU INLET. PERFORMED FULL DUCT BURN OUT IAW AMDS CARD 7100-2619. CREW STATED SMELL WAS RUBBERY. NO SMELL NOTED ON DUCT BURNOUT. OK FOR SERVICE.

Part: FLUID — LEAKING (APU BAY) · airframe 73,335 hrs · 54,466 cycles

DURING INTIAL BOARDING NOTICED BURNING OIL ODOR ON FLT DECK, SHUT OFF PACKS ODOR DISSIPATED. SHUT APU DOWN AND FOUND OIL OR HYD FLUID BACK FLOWING OUT OF APU NON RAM DOOR. REVIEWED SMOKE/FUME QUESTIONNAIRE. PERFORMED TROUBLESHOOTING PER WORKCARD 2120-2367. PERFORMED DUCT BURNOUT PER WORKCARD 2120-2368. ALL NO GO ODI ITEM COMPLIED WITH PER NO GO ODI 21-72 ACFT OK FOR SERVICE. (LP5981696)

Part: ACM — ODOR (LEFT) · airframe 73,077 hrs · 54,221 cycles

ON APPROACH WE HAD A BURNING SMELL ON THE FLIGHT DECK AS WELL AS THE 2 LEFT DOOR. NO SMOKE. SMELL WENT AWAY AFTER 15 SEC. APU WAS OFF. PERFORMED INSPECTION PER W/C 2120-2367. FOUND LEFT ACM SEIZED. REMOVED AND REPLACED LEFT ACM PER AMM 21-51-01. OPS CHECK GOOD AT THIS TIME. C/W FULL DUCT BURNOUT PER W/C 7100-2619, NO ODER IN CABIN OR COCKPIT. NO GO ODI C/W REF LOG 5951001 TURBINE, COOLIN OFF 88-2150-9-0002 23462 ON 88-2150-9-0002 09015, (LP5773597)

Part: HOOK AND LOOP — WORN (EVAC SLIDE) · airframe 72,574 hrs · 53,772 cycles

TAILCONE SLIDE COVER HOOK AND LOOP IS WORN. REPLACED THE TAILCONE SLIDE ASSY. REF AMM 25-62-01. SLIDE OFF 88-2561-9-0003 01758 ON 88-2561-9-0006 01734 LOG-PAGE UPDATED @ 20MAY19 0300 UTC. (LP1082377)

Part: FRAME — CRACKED (FUSELAGE) · airframe 72,574 hrs · 53,772 cycles

CRACK WITH LOOSE MISSING FASTENERS AT CANTED FRAME 1485, LEFT SIDE, AFT OF UPPER VENT. REPAIRED IN REF TO SRM 53-03D, PARA 44, FIG.50. (LP1081922)

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,574 hrs · 53,772 cycles

AFT CARGO COMPARTMENT BILGE AREA:CORROSION AT STRINGER STA.1287, LONGERON 29LT. MKD. REPAIRED REF SRM 53-02 PARA 12 FIG 18. (LP1077190)

Part: COWLING — DENTED (NR 1 ENGINE) · airframe 72,574 hrs · 53,772 cycles

NR 1 ENG. NOSE COWL LIP HAS DENT AT APPROX. 2 O'CLOCK POSITION. REPLACED NR 1 ENGINE NOSE COWL, REF AMM 71-10-01. COWL, NOSE, LT OFF 88-7110-9-0001 99491 ON 88-7110-9-0001 00084. (LP1074461)

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 72,514 hrs · 53,719 cycles

DURING SVC CK, FOUND CEILING EMER LTS. FROM ROW 32-34 INOP. REMOVED AND REPLACED B5-107 POWER SUPPLY REF MD88 AMM 33-53. OPS CHECK GOOD. (LP3796407)

Part: UNKNOWN — ODOR (CABIN) · airframe 72,476 hrs · 53,688 cycles

RT AC TEMP HIGH ON OAP INTERMITENT DURING T/O. RT X-BLEED LEVER SEEMS STIFF. NO OAP MSG AFTER 1 MINUTE. FA REPORTED BURNING SMELL FOR A MINUTE OR TWO AFT. RAN LT AND RT ENGS TO T/O UNABLE TO DUPLICATE OAP MSG. C/W W/C 2120-2367 PER NO GO ODI 21-72. APU NOT CONTAMINATED REF LOG 1025898, CO CONTAMINATION IN THE LT OR RT PACK. RAN ENG PER NO GO ODI FIG 7, NO ODOR. RAN T/S 21-60 RT AC TEMP HIGH, AUG VALVE CKS GOOD, REPLACED AC PILOT PRESS REG PRECATIONARY. WASHED BELLY OF A/C AND APU DOORS WITH PRESS WASHER PRECATIONARY. C/W ALT DUCK BURN OUT PER W/C 4950-2215. ( BEFORE RUNNING ENGS FOUND LOOSE B-NUT AT AUG VLV AND ONE ON PRV, SECURED SAME). REPLACED WATER BAGS LEAK CK GOOD. LP3759672)

Part: BATTERY — DISCHARGED (CABIN) · airframe 72,197 hrs · 53,463 cycles

CABIN EMERGENCY LIGHTS OUT RELATED B5-105 AND B5-102. R/R BATTERIES FOR EMERGENCY LIGHTS BATTER PACKS B5-105 AND B5-102 IN REF TO AMM 33-53, OPS CHECK GOOD. (LP5758816)

Part: UNKNOWN — ODOR (COCKPIT) · airframe 71,769 hrs · 53,103 cycles

FA'S REPORT UNUSUAL ACRID SMELL THRU OUT CABIN. NO ABNORMAL INDICATIONS IN COCKPIT OR SMELL. FOLLOWED W.C. 2120-2367 REF FIG 6 AND FIG 7 - CHECKS GOOD - WORKING WC 7100-2619. DUCT BURN. C/W W/C 7100-2619. ALL CKS GOOD NO MORE SMELLS NOTED AT THE TIME. C/W NO GO ODI ATA 21-71. (LP4999450)

Part: FITTING — CRACKED (RT SPOILER) · airframe 70,715 hrs · 52,171 cycles

FOUND CRACKS ON TOP OF MOUNTING POINT OF RT GROUND SPOILER. REMOVED RT GROUND SPOILER. REMOVED CRACKED FITTING REF DWG 5936824. DRILLED NEW SPOILER FITTING REF DWG 5936824. INSTALLED NEW SPOILER FITTING REF DWG 5936824.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHTS) · airframe 70,294 hrs · 51,806 cycles

14 & 15 ED SEAT MOUNTED EMERGENCY LIGHTS INOPERATIVE. REPLACED THE LAMPS. OPS NORMAL.

Part: LIGHT — INOPERATIVE (COCKPIT) · airframe 69,586 hrs · 51,225 cycles

ON APPR WHEN LANDING GEAR DOWN, NO GREEN GEAR INDICATOR ON NOSE GEAR. RELAMPED NOSE GEAR DOWN INDICATION LAMPS. OPS CK NML. C/W NO GO ODI PREVENTION REF AMM 32-60-00-101 OK FOR SVC.

Part: CONTROL VALVE — FAILED (BRAKES) · airframe 68,219 hrs · 50,156 cycles

AFTER TAKEOFF FELT VIBRATION AND OBSERVED RT MAIN GEAR RED LIGHT, GEAR HANDLE UP AND GEAR DOOR LIGHT ILLUMINATED. SLIGHT BURNING RUBBER ODOR. AUTO SPOILER FAIL LIGHT ILLUMINATED. RAN QRH FOR LDING GEAR UNSAFE. GEAR HANDLE AND TIRE FAILURE QRH. GEAR PINS INSTALLED IAW AMM 32-11 AND 32-21. JACKED A/C AND RAN GEAR NUMEROUS TIMES, NO TROUBLE NOTED. LANDING GEAR ALTERNATE EXTEND CHECKED GOOD IAW AMM 32-31. FOUND LEVER ACTION ON RT WHEEL BRAKE CONTROL VALVE BAD. REPLACED IAW AMM 32-42. REMOVED AND STOWED GEAR PINS. OK FOR SERVICE.

Part: SUPPORT — CRACKED (LT WING) · airframe 67,506 hrs · 49,611 cycles

LT WING, CRACKED LWR MLG SUPPORT STA XCW 104, ALSO LOOSE FASTENERS. CRACKED LWR MLG SUPPORT STA XCW 104, ALSO LOOSE FASTENERS. (LW), WERE REPAIRED PER ETI -88-17-087 REV 6 & ERA 556328-14 REV ORIGINAL.

Part: DOOR FRAME — CRACKED (EMERGENCY EXIT) · airframe 67,506 hrs · 49,611 cycles

CRACK ON THE RT AFT EMERGENCY EXIT DOOR FRAME IN UPPER SECTION. THE DOOR FRAME WAS REPAIR IAW SRM 53-05, FIG. 32.

Part: FRAME — CRACKED (BS 1510) · airframe 67,506 hrs · 49,611 cycles

AFT ACCESORIES COMPARTMENT HAD A CRACKED FRAME BS 1510, BETWEEN 1 TO 2 HRS POSITION AND 5 HRS POSITION. THE FRAME WAS REPAIRED AT 1 HRS POSITION IAW ER/A 497316-14MA, REV ORIGINAL, AND SECTIONS WERE REPLACED BETWEEN 3 TO 6 HRS POSITION IAW SRM 51-30-1, 51-30-2, AND 51-30-5.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 67,506 hrs · 49,611 cycles

FUSELAGE INTERNAL DOUBLER LAV SERVICE PANEL STA 287 S-21L CORROSION REPAIR. REPAIR WAS ACCOMPLISHED PER ETI-88-17-086 REV ORIGINAL AND ER/A 493067-14 REV "B".

Part: SKIN — WORN (LT WING TE FLAP) · airframe 67,506 hrs · 49,611 cycles

LEFT WING HAS A WORN INBD FLAP INBD VANE SKIN. THE FLAP WAS REPAIRED IAW SRM 57-03D, PARAGRAPH 11, FIG 11.

Part: SKIN — CRACKED (LE SLAT) · airframe 67,506 hrs · 49,611 cycles

LT WING, CRACKED INNER SKIN OF SLAT PANEL NR 2 AT SLAT TRACK NR 7 RIB CUTOUT. SLAT PANEL NR 2 WAS REPLACED UNDER AMDS 2700-4224-LH-02 JOB 000-002 S/N: ON DL42, OFF DL32.

Part: SLEEVE — TORN (WIRE) · airframe 67,506 hrs · 49,611 cycles

TORN AUXILLARY HYD PUMP WIRING SLEEVE. SLEEVE WAS RAPAIRED PER MD88 SWPM 20-10-01 AND ER/A 467688-14MAAD. (LP2933936)

Part: FLAP SYSTEM — OUT OF RIG · airframe 67,506 hrs · 49,611 cycles

DURING ROTATION, THE AIRCRAFT ROLLED HARD TO THE LEFT. 2.5 UNITS OF AILERON TRIM WERE REQUIRED FOR LEVEL FLIGHT. MAINTENANCE FOUND THE FLAPS OUT OF RIG AT SETTING 11. THE FLAP BUSS CABLE ADJUSTMENT WAS PERFORMED AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 66,615 hrs · 48,985 cycles

ON SVC CK, EMER LT CK ROW 12 ED EMER LIGHT OUT. RELAMPED AS REQUIRED PER AMM 33-50 OPS CHECKS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 66,247 hrs · 48,702 cycles

SEAT MOUNTED EMERGENCY LIGHTS FROM ROW 1 THROUGH ROW 12 INOPERATIVE. REPLACED THE BATTERY PACK.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 65,844 hrs · 48,402 cycles

ROW 20 SEAT D EMERGENCY LIGHT INOPERATIVE. REMOVED AND REPLACED THE EMERGENCY LIGHT WIRE HARNESS IAW AMM 33-53, OPS CHECKED GOOD.

Part: PIN — PULLED (EVAC SLIDE) · airframe 65,773 hrs · 48,348 cycles

F/A REPORTS L1 SLIDE DOESN'T SEEM RIGHT. FOUND COVER PINS PULLED, REPLACED L1 SLIDE IAW AMM 25-62-00.

Part: SKIN — CORRODED · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

EXFOLIATION CORROSION ON LOWER INBD SKIN ON FIXED TRAILING PANEL AT STA XRS= 387.5 OF LT WING. REPAIR WAS PERFORMED IAW ERA NR 532526-14, REV ORIGINAL.

Part: SKIN — CRACKED · airframe 62,201 hrs · 45,832 cycles

CRACK ON FUSELAGE SKIN AT STA Y=586 BETWEEN LONGERON 20LT AND 21LT. HOLE OF REPAIR WAS DRILLED IAW SRM 53-04-2, PAR 3 C2, A, 1, A. PLUG OF REPAIR WAS INSTALLED IAW SRM 53-04-2, PAR 3C, 2, A,3. AREA WAS TREATED AND PAINTED IAW SRM 51-10-3, PAR 14 AND 21.

Part: HEATER BLANKET — CORRODED · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON HEATER BLANKET SURFACE AROUND ACCESS 1309C AT LT WING SETTLEMENT AREA OF SECONDARY ACCESS PANEL. LT HEATER BLANKET PANEL WAS REPLACED IAW AMM 30-80-02, PAGEBLOCK 401.

Part: HEATER BLANKET — CORRODED · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON HEATER BLANKET SURFACE AROUND ACCESS 1410C AT RT WING SETTLEMENT AREA OF SECONDARY ACCESS PANEL. RT HEATER BLANKET PANEL WAS REPLACED IAW AMM 30-30-02.

Part: SKIN — CRACKED · airframe 62,201 hrs · 45,832 cycles

CRACK ON FUSELAGE SKIN AT STA Y=586 BETWEEN LONGERON 20LT AND 21LT. HOLE OF REPAIR WAS DRILLED IAW SRM 53-04-2, PAR 3C, 2, A, 1, A. PLUG OF REPAIR WAS INSTALLED IAW SRM 53-04-2, PAR 3C, 2, A, 3. AREA WAS TREATED AND PAINTED IAW SRM 51-10-3 PAR 14 AND 21.

Part: SKIN — CORRODED · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON SEATING AREA OF RUBSTRIP ON STA Y= 1079 TO 1117 BETWEEN LONGERON 27LT TO 30. REWORKED AREA WAS TREATED AND PAINTED, CIC WAS APPLIED IAW SRM 51-30-5, 51-10-3, P 26, 21, 14, 38, 53-04 P.57 .

Part: LONGERON — CORRODED · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LONGERONS 24LT AND 25LT, STA Y=1174, Y=1193 AND Y=1212 AT AFT CARGO COMPARTMENT. CORROSION WAS ATTENDED IAW SRM 51-10-3, PAR 26 IS WITHIN LIMITS IAW SRM 53-02, PAR 13.

Part: RUB STRIP — CORRODED · airframe 62,201 hrs · 45,832 cycles

CORROSION ON SEATING AREA OF RUBSTRIP ON STA Y=1079 TO 1117 BETWEEN LONGERON 27LT TO 30. REWORKED AREA WAS TREATED AND PAINTED, CIC WAS APPLIED IAW SRM 51-30-5, 51-10-3, 21, 14, 38, 53-04.

Part: CHANNEL — CRACKED · airframe 62,201 hrs · 45,832 cycles

CRACK CHANNEL ON INBD FAIRING AT LT UPPER THRUST REVERSER DOOR. CHANNEL ON INBD FAIRING AT LT UPPER THRUST REVERSER DOOR WAS REPAIRED IAW ETI-88-15-090, REV ORIG AND ER/A 532544-14, REV ORIGINAL AS A PERMANENT REPAIR.

Part: SKIN — CORRODED · airframe 62,201 hrs · 45,832 cycles

PITTING CORROSION ON EXTERNAL FUSELAGE SKIN BENEATH RUBSTRIPS FILLET PANELS FROM STA Y=1079 TO Y=1136 BETWEEN LONGERON 24 AND 30 RT. AREA WAS BLENDED OUT, MEASURED, TREATED, AND PAINTED AND CIC WAS APPLIED IAW SRM 51-10-3 AND 53-04, PAR 57. MEASURE REWORKED AREA ORIGINAL THICKNESS 0.130" AND REMAINING THICKNESS 0.105" THEREFORE IT IS WITHIN LIMITS IAW SRM 53-04, PAR 57.

Part: SKIN — UNKNOWN · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

REPAIR DOUBLER BENEATH RUBSTRIPS AT FILLET PANELS AREA FROM STAY= 758 TO 778 BETWEEN LONGERONS 29RT AND 27RT. REPAIR DOUBLER WAS REPLACED IAW ER/A 330196-14, REV "C".

Part: STRUCTURE — CORRODED · airframe 62,201 hrs · 45,832 cycles

EXFOLIATION CORROSION ON SEATING AREA OF RUB STRIP ON STA Y=1117 TO 1136 AND BETWEEN LONGERON 26LT TO 27LT. CORROSION WAS REMOVED IAW SRM 51-10-3, PAR 26 AT STA Y=1117 TO 1136 BETWEEN LONGERON 26LT TO 27 LT. MEASURE REWORKED AREA: STA Y=1117 ORIGINAL THICKNESS 0.130" AND REMAINING THICKNESS 0.108, STA Y=1136, ORIGINAL THICKNESS 0.113" AND REMAINING THICKNESS 0.096", THEREFORE ARE THEY WITHIN LIMITS IAW SRM 53-04.

Part: CUSP WEB — CORRODED · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON RT CUSP WEB PREVIOUS REPAIR DOUBLER BETWEEN STA Y=994-1000, X=-54 X=60 AT CABIN FLOOR STRUCTURE. DUE TO EXCESSIVE CORROSION, WEB WAS REPLACED IAW SRM 51-30-2, 51-30-5, 51-10-4, 51-10-3 P.21, 14, 38.

Part: NONE — NONE (NONE) · airframe 62,201 hrs · 45,832 cycles

PERFORM WEIGHT AND BALANCE OF RT ELEVATOR CONTROL TAB DUE TO OTHERS MAINTENANCE ACTIVITIES. RT ELEVATOR CONTROL TAB WERE PERFORMED WEIGHT AND BALANCED IAW SRM 55-20-2.

Part: BUSHING — WORN · airframe 62,201 hrs · 45,832 cycles

FREE-PLAY ON ATTACH POINT OF CONTROL TAB GEARED TAB AND ANTI-FLOAT TAB AT LT ELEVATOR REAR SPAR. ATTACH POINT OF CONTROL TAB GEARED TAB AND ANTI-FLOAT TAB AT LT ELEVATOR REAR SPAR WERE REPLACED BUSHINGS IAW CMM 27-30-1 AND FREE-PLAY WAS CORRECTLY.

Part: CUSP WEB — CORRODED · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON RT CUSP WEB UPPER AND LOWER SURFACES BETWEEN STA Y=965-984, X=-54 TO X=-60 AT CABIN FLOOR STRUCTURE. DUE TO EXCESSIVE CORROSION, WEB WAS REPLACED IAW SRM 51-30-2, 51-30-5, 51-10-4, 51-10-3.

Part: BRACKET — CORRODED · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON 6 PULLEY BRACKETS LOCATED Y=1338 AND RT LAVATORY FLOOR STRUCTURE. 6 PULLEY BRACKETS LOCATED Y=1338 AND RT LAVATORY FLOOR STRUCTURE WAS REPLACED IAW AMM 20-30-01-201. CONTROL CABLES WAS LOOSENED AND WAS RIGGING IAW AMM CHAPTER 27-20-00.

Part: SKIN — CORRODED · airframe 62,201 hrs · 45,832 cycles

CORROSION ON SEATING AREA OF RUBSTRIP BETWEEN STA Y= 750 TO 826, LONG 25LT TO 30. FASTENERS WAS REMOVE CORROSION WAS REMOVE, MEASURE, APPLY ALODINE, PRIMER AND CIC IAW SRM 51-30-5, 51-10-3 PAR 26, 21, 14 AND 38, 53-04, PAR 57. JOB COMPLETED.

Part: LONGERON — CORRODED · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

EXFOLIATION CORROSION ON LONGERON 23 LT AT STA Y=1155, 1174, 1193, 1212, 1231, 1240, 1252, 1259 AT AFT CARGO COMPARTMENT. SUPPORT AND SPLICE WERE REMOVED LONGERON STA Y=1146 TO 1201 WAS TRIMED AND REMOVED STRUT WAS REMOVED ON STA Y=1136. NEW LONGERON WAS DRILLED AND NEW HOLES WERE TREATED AND PAINTED. NEW LONGERON SECTION WAS INSTALLED IAW SRM 51-30-2, 51-30-5, 53-02, FIG 18 51-10-4, 53-02, 51-10-3 PARA 14 AND 21.

Part: TAB — DENTED · airframe 62,201 hrs · 45,832 cycles

DURING COMPLETE ELEVATOR INSTALLATION CHECK IAW AMDS 2730-4182, STEP 12, A DENT WAS FOUND ON RT ANTI-FLOAT TAB LOWER SKIN OTBD EDGE. A DENT WAS FOUND ON RT ANTI-FLOAT TAB LOWER SKIN OTBD EDGE AND WAS REMOVED RT ANTI-FLOAT TAB AND WAS REPAIRED IAW SRM 55-04, PAR 2 AND ACFT 0971 CARD 200-8149-09. WEIGHT AND BALANCED ON RT ANTI-FLOAT TAB WAS PERFORMED IAW SRM 55-20-2.

Part: SKIN — CORRODED · airframe 62,201 hrs · 45,832 cycles

PITTING CORROSION ON EXTERNAL FUSELAGE SKIN REPAIR DOUBLER BENEATH RUBSTRIPS AT FILLET PANELS AREA FROM STA Y= 758 -778 BETWEEN LONGERONS 29RT AND 27RT. REPAIR DOUBLER WAS REPLACED IAW ER/A 330196, REV "C".

Part: LONGERON — CORRODED · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

EXFOLIATION CORROSION ON LONG 22 LT ON STA 1136, 1155, 1174, 1193 AT AFT CARGO COMPARTMENT. DAMAGE AREA WAS REPAIRED IAW SRM 53-C2, FIG 18, SHEET 2 AND 51-10-3, PAR 14, 21 AND 38.

Part: BELLCRANK — CORRODED · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON BELLCRANK. BELLCRANK WAS REPLACED IAW CMM 27-20-33 AND WILL BE INSTALLED AND ADJUSTED.

Part: TRACK — CORRODED (UNKNOWN) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON RT TIE TRACK UPPER SURFACE AND LOWER SURFACE FROM STA Y=1005 UNTIL Y=1155. DUE TO EXCESSIVE CORROSION WILL BE TIE TRACK WAS REPLACED IAW SRM 51-10-4, 51-30-1 AND 51-30-02.

Part: STRUCTURE — CORRODED (DOOR FRAME) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

EXFOLIATION CORROSION ON UPPER DOOR JAM AFT CORNER AT AFT CARGO COMPARTMENT. DUE TO EXCESSIVE CORROSION, UPPER DOOR JAMB WAS REPLACED IAW SRM 51-30-2, 51-30-5, 51-10-4, 51-10-3 P.21-14.

Part: SKIN — CORRODED (BS 750-826) · airframe 62,201 hrs · 45,832 cycles

CORROSION FOUND ON EXTERNAL FUSELAGE SKIN BENEATH RUBSTRIPS FILLET PANELS BS 750 - 826 BETWEEN LONGERONS 26 - 30R. CORROSION REMOVED IAW SRM 51-10-2, PAR 26. ACCOMPLISHED NDT SPM 04-00-07, PAR 5, FIG 3 , SHEET 1 AND 2. SKIN WITHIN OF LIMITS IAW SRM 53-04, PAR 57. AREA TREATED AND PAINTED IAW SRM 51-10-3, PAR 14 AND 21.

Part: RUB STRIP — CORRODED (BS 1115) · airframe 62,201 hrs · 45,832 cycles

CORROSION ON SEATING AREA OF RUB STRIP ON BS 1115 BETWEEN LONGERON 26-28L. REPAIRED IAW SRM 53-04, PAR 57.

Part: WEB — CRACKED (BS 1463-1485) · airframe 62,201 hrs · 45,832 cycles

CRACKED WEB BETWEEN BS 1463 - 1485. DAMAGE WAS REPAIRED IAW SRM 53-01, 51-10-3, 51-30-2, 51-30-5

Part: ANGLE — CRACKED (BS 788) · airframe 62,201 hrs · 45,832 cycles

CRACKED ANGLE OF BS 788 X 38 Z -4. ANGLE REMOVED AND REPLACED IAW SRM 51-30-2. SRM 51-10-2, DWG5936628-61, ITEM REV: B5, SRM 51-10-3, PAR 14, 21, SRM 51-30-5.

Part: SKIN — CORRODED (BS 804-810) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON EXTERNAL FUSELAGE SKIN REPAIR DOUBLER BENEATH RUBSTRIPS AT FILLET PANELS AREA FROM BS 804 - 810 BETWEEN LONGERONS 29 - 30R. REPAIR DOUBLER WAS REPLACED IAW ERA 330196-14, REV "C".

Part: SKIN — UNKNOWN · airframe 62,201 hrs · 45,832 cycles

FUSELAGE RT SKIN WINDOW BELT FS 693-750 WAS REPAIRED WITH A DOUBLER. WINDOW BELL WAS REPAIRED IAW ETI-88-15-039, REV 2 AND ER/A 532428-14, REV ORIG.

Part: ANGLE — CRACKED (LT WING) · airframe 62,201 hrs · 45,832 cycles

CRACK ON ANGLE LOCATED LT WING INBD BUTTE DOOR XCW=58. BUTTE DOOR WAS REPLACED BY SERVICEABLE UNIT IAW SRM 51-30-1 AND 51-30-5.

Part: SUPPORT — DAMAGED (BS 1401) · airframe 62,201 hrs · 45,832 cycles

TOOL DAMAGE ON UPPER CHANNEL BETWEEN VENTRAL TUNNEL SUPPORT BS 1401. REPAIRED IAW SRM 53-01, FIG.2.

Part: FLOOR SUPPORT — CORRODED (BS 1322-1338) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON FLOOR SUPPORT BS 1322 - 1338. THE FLOOR SUPPORT WAS REPAIRED IAW ETI-88-15-053R2 AND ER/A 532505-14 REV ORIGINAL.

Part: FLOOR PANEL — DAMAGED · airframe 62,201 hrs · 45,832 cycles

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

Part: BEAM — CORRODED (BS 636-693) · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LOWER BEAM BETWEEN BS 636 - 693 AND LONGERON 27R. CORROSION WAS REMOVED, MEASURED, REWORKED AREAS WERE TREATED AND PAINTED IAW SRM 51-10-3 P-26, 21,14,38, 53-05, FIG 123.

Part: SKIN — DAMAGED (AILERON) · airframe 62,201 hrs · 45,832 cycles

BRACKET HINGE, WEAR ON INTERNAL SKIN, ALSO BENT AILERON, OTBD HINGE DOOR NR 3 AT LT WING, LOWER SURFACE. DOOR ASSY WAS REPLACED IAW SRM 51-30-2.

Part: INTERCOSTAL — CORRODED (BS 1212-1231) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON INTERCOSTAL BETWEEN BS 1212 - 1231 LONGERON 29L. THE INTERCOSTAL WAS REPLACED IAW SRM 51-14-3, 51-10-4, 51-10-3 P. 21-14, 51-30-5, AND 51-30-2.

Part: SEAT TRACK — CORRODED (BS 845-1079) · airframe 62,201 hrs · 45,832 cycles

CORROSION ON SEATING AREA OF RUB STRIP ON BS 845 - 1079 BETWEEN LONGERONS 18 - 19 LT. CORROSION WAS REMOVED, AREA REWORKED WITHIN LIMITS IAW SRM 53-04, PAR 57.

Part: FRAME — CRACKED (BS 1322) · airframe 62,201 hrs · 45,832 cycles

CRACKED FRAME BS 1322 AND LONGERON 17R. FRAME REPAIRED IAW ER/A 493697-14 MA, REV "B".

Part: FRAME — CRACKED (BS 1510) · airframe 62,201 hrs · 45,832 cycles

CRACKED FRAME BS 1510 AT 1 AND 7 HRS POSITION. FRAME WAS REMOVED, DRILLED, TREATED, PAINTED, AND INSTALLED IAW SRM 51-30-02, 51-10-04, AND 51-10-3 PAR 14 AND 21 AND DWG 9911843, REV AC.

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 62,201 hrs · 45,832 cycles

DELAMINATION BELOW RUB STRIP ON INBD UPPER SURFACE AT RT INBD FLAP OTBD GUIDE VANE. RT INBD FLAP OTBD GUIDE VANE WAS REPAIRED IAW SRM 57-03 PARR 11.

Part: DOOR — CRACKED (NLG) · airframe 62,201 hrs · 45,832 cycles

CRACK ON AFT NLG WHEEL WELL DOOR RT. NLG WHEEL WELL DOOR RT WAS REMOVED IAW AMM 32-22-01. NLG WHEEL DOOR RT SERVICIABLE WAS INSTALLED IAW AMM 32-22-01.

Part: SUPPORT — CRACKED (NLG WW) · airframe 62,201 hrs · 45,832 cycles

CRACKED ON RT SUPPORT AT NLG WHEEL WELL BETWEEN STA Y=38 AND X=-5. RT SUPPORT AT NLG WHEEL WELL BETWEEN STA Y: 38 AND X= -5 WAS REPLACED IAW SRM 53-14-1.

Part: SKIN — CRACKED (LT ELEVATOR) · airframe 62,201 hrs · 45,832 cycles

CRACK ON SKIN THE L/E AT ELEVATOR GEARED TAB LT IN HINGE INBD AREA. CRACK ON SKIN WAS REPAIRED IAW SRM 51-02 P7.

Part: EYEBOLT — DAMAGED (HORIZONTAL STAB) · airframe 62,201 hrs · 45,832 cycles

DAMAGE DUST COVER OF BEARINGS ON ATTACH POINT HINGE NR 2, 3, AND 5 REAR SPAR HORIZONTAL STABILIZER LT SIDE. EYEBOLTS ON ATTACH POINT HINGE NR 2, 3 AND 5 AT SPAR HORIZONTAL STABILIZER LT SIDE WERE REPLACED IAW CMM 27-30-2.

Part: FLOORBEAM — CORRODED (BS 522) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION AT FLOOR SUPPORT BS 522. THE FLOOR SUPPORT WAS REPAIRED IAW SRM 53-01, FIG 2, SHEET 4, 51-10-3, PAR 21 AND 14, AND 38 OTHER AREAS WAS REMOVED CORROSION IAW SRM 51-10-3, PAR 26.

Part: SKIN — DAMAGED (BS 446-484) · airframe 62,201 hrs · 45,832 cycles

LIGHTNING STRIKE ON LT EXTERNAL FUSELAGE SKIN BETWEEN BS 446-484 BETWEEN LONGERON 5 - 6L. REMOVE FASTENER STA Y=446. EVALUATED AND MEASURE MAX RADIAL DIMENTION R=0.063". THEREFORE IS WITHIN LIMITS IAW SRM 53-04-1 PAR 6C (2) CONDITION 2 WILL BE REPLACED FASTENER STA Y=484 IS OUT LIMITS IAW MEASURE THICKNESS ORIGINAL 0.050", REMAINING 0.036" WILL BE REPAIR IAW SRM 53-04-2, FIG 2. FABRICATE DOUBLER PAINT AND TREAT NEW DOUBLER INSTALL NEW DOUBLER IAW SRM 51-30-2.

Part: CUSP WEB — CORRODED (BS 1212-1231) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LT PAX CABIN FLOOR CUSP WEB BETWEEN X 54 AND X 60 FROM BS 1212 - 1231. CUSP WEB REPLACED IAW SRM 51-10-3, PARA 14, 21, 28, 51-30-2, 51-10-4 AND ETI 88-15-066, ER/A 532520-14.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 62,201 hrs · 45,832 cycles

CRACKED SKIN ON FLOOR PANEL 1003A. FLOOR PANEL REPLACED IAW SRM 51-10-4, 51-10-3 PAR 21 AND 14.

Part: SKIN — CORRODED · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON SKIN OF RT MAIN GEAR STRUT DOOR BELOW RUBSTRIP. DOOR WAS REMOVED IAW AMM 32-12-01. CORROSION OF RT MAIN GEAR STRUT DOOR WAS REMOVED IAW SRM 52-01. AREA WAS MEASURED IAW NDT SPM 04-00-07. ORIGINAL THICKNES 0.063 REMAINING THICKNESS 0.041. THEREFORE ITS OUT OF LIMITS IAW SRM 52-01 AND RT MAIN GEAR STRUT WAS REPLACED IAW AMM 32-12-01 AND WILL BE CHECKED AND ADJUSTED.

Part: SKIN — CRACKED (RT WING) · airframe 62,201 hrs · 45,832 cycles

CRACK LOWER SKIN XOS 240.081 AT RT SLAT PANEL NR 2. THIS REPAIR WAS ATTENDED IAW ERA 519116-14MA, REV ORIGINAL AND ETI-88-14-002.

Part: SKIN — CRACKED (RT WING) · airframe 62,201 hrs · 45,832 cycles

CRACKED LOWER SKIN XOS 136.421 AT RT SLAT PANEL NR 1. RT SLAT PANEL NR 1 WAS REPAIRED IAW ETI-88-15-034, REV ORIG AND ERA 531400-14, REV ORIGINAL.

Part: ANGLE — CRACKED (NLG WW) · airframe 62,201 hrs · 45,832 cycles

CRACKS ON RT/LT NLG WHEEL WELL ANGLES BETWEEN STA Y=38 AND X=17, X=-17. CRACKS ON RT/LT NLG WHEEL WELL ANGLES BETWEEN STA Y=30 AND X=17, X=-17 WERE REPLACE IAW SRM 53-14-1 FIG 4.

Part: DOOR FRAME — CRACKED (CARGO BAY) · airframe 62,201 hrs · 45,832 cycles

TWO CRACKS OF 1.375 AND 1.250 APPROXIMATELY WERE FOUND ON AFT LOWER DOOR FRAME CORNER INTERNAL DOUBLER AT C1. DAMAGED AREA WAS REPAIRED IAW SRM 53-05, FIG 105.

Part: FRAME — CRACKED (BS 1380) · airframe 62,201 hrs · 45,832 cycles

CRACKED FRAME ANGLE BS 1380, L15L. THE FRAME ANGLE WAS REMOVED, WITH NO CRACKS FOUND AND REINSTALLED IAW SRM 51-30-5.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE NR 1464C AT RT WING. DAMAGE ON ACCESS PLATE NR 1464C WAS REWORKED IAW SRM 51-22-2A, PAR 6, CONDITION II REWORKED AREA WAS MEASURED. DIAMETER 0.3235" AND COUNTERSINK 0.620" AND REPAIR BUSHING WAS FABRICATED AND INSTALLED WITH 0.D 0.324" AND COUNTERSINK .620" IAW SRM 51-22-2A PAR 6.

Part: FLOOR SUPPORT — CRACKED (BS 1022-1041) · airframe 62,201 hrs · 45,832 cycles

CRACKS ON BEAM SUPPORT THE FLOORBEAM, BETWEEN STA Y=1022 TO Y=1041, X=0, CENTER AREA. NEW BEAM SUPPORT WAS REPLACED IAW SRM 51-30-5 AND 51-30-2, 51-10-3 PARA 14 AND 21.

Part: WEB — CORRODED (BS 363-370) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON WEB BETWEEN BS 363 - 370, LONGERON 24-26R. REPAIRED IAW ER/A 5325-19-14, REV ORIGINAL

Part: SKIN — CORRODED · airframe 62,201 hrs · 45,832 cycles

CORROSION ON SEATING AREA OF RUBSTRIP BETWEEN STA Y=750 TO 826, LONGERON 25LT TO 30. FASTENERS WAS REMOVE CORROSION WAS REMOVE, MEASURE, APPLY ALODINE, PRIMER AND CIC IAW SRM 51-30-5, 51-10-3, PAR 26, 21, 14 AND 38, 53-04, PAR 57.

Part: WEB — CORRODED (BS 427-434) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON WEB BS 427 - 434 LONGERON 24 - 27R. REPAIRED IAW ERA 511165-14 MA, REV B.

Part: RIB — CORRODED (WING) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON RIB XOS 380.229-481.438. DAMAGED RIB FOUND OUT OF LIMITS OF DBP. BUSHINGS WERE FABRICATED AND INSTALLED IAW SRM 57-02, PAR 9. DAMAGE ON RIB INBD WERE REWORKED IAW ETI-88-15-032, REV 1AND ER/A 531398-14, REV ORIG.

Part: SKIN — DENTED (ELEVATOR) · airframe 62,201 hrs · 45,832 cycles

DENT ON LOWER SKIN AT LT ANTI-FLOAT TAB. LT ANTI-FLOAT TAB WAS REPAIRED IAW SRM 55-04, PAR 2 AND OPEN 1031A.

Part: CUSP WEB — CRACKED (BS 1098-1117) · airframe 62,201 hrs · 45,832 cycles

CRACKED RT CUSP WEB BETWEEN BS 1098-1117 X -54 X -60. CUSP WEB REPAIRED IAW SRM 53-05, FIG 131A-7.

Part: CHANNEL — CORRODED (LAVATORY PAN) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION AND WEAR ON CHANNELS AT LT AFT LAVATORY PAN. CHANNELS REMOVED. NEW CHANELS WERE TRIMMED, DRILLED, TREATED, PAINTED AND WERE INSTALLED IAW SRM 53-24-0, 51-20-0, 51-10-3 PAR 21,14.

Part: SKIN — CORRODED (BS 1003-1136) · airframe 62,201 hrs · 45,832 cycles

CORROSION ON EXTERNAL FUSELAGE SKIN BENEATH RUB STRIPS FILLET PANELS FROM STA Y=1136 TO Y=1003 BETWEEN LONGERON 24 AND 18 RT. REMOVE CORROSION TREAT AND PAINT AREA MEASURE THICKNESS ORIGINAL 0.080" REMAINING THICKNESS 0.070" THEREFORE IT'S WITHIN LIMITS IAW SRM 53-04, PAR 57, 51-10-3, PAR 26, 51-10-3, PAR 14 AND 21.

Part: RIB — CORRODED (WING) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION FOUND ON RIB XOS=240.081. DAMAGE REWORKED, AND REAMED AND FOUND OUT OF LIMITS. REPAIR BUSHINGS WERE FABRICATED AND INSTALLED IAW SRM 57-02, PAR 9.

Part: SKIN — CORRODED (BS 886-1003) · airframe 62,201 hrs · 45,832 cycles

CORROSION ON EXTRNAL FUSELAGE SKIN BENEATH RUB STRIPS FILLET PANELS FROM BS 886-1003 LONGERON 18R. REMOVED CORROSION AND FOUND WITHIN LIMITS IAW SRM 53-04, PAR 57 51-10-3, PAR 26 51-10-3, PAR 14 AND 21.

Part: STIFFENER — CRACKED (BS 1338) · airframe 62,201 hrs · 45,832 cycles

CRACKED STIFFENER, BS 1338, 12 HRS POSITION AT AFT CABIN FUSELAGE. REMOVED STIFFENER. FABRCATED NEW STIFFENER. TREATED AND PAINTED NEW STIFFENER. INSTALL NEW STIFFENER IAW SRM 51-30-5 AND 51-30-2, DWG 9915562, REV ET 51-10-3 PAR 14 AND 21.

Part: TAB — DENTED (ELEVATOR) · airframe 62,201 hrs · 45,832 cycles

DENTS ON UPPER AND LOWER SKIN AT LT GEARED TAB. LEFT GEARED TAB WAS REPAIRED IAW SRM 55-04, PAR 2.

Part: CUSP WEB — CORRODED (BS 580-586) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON REPAIR DOUBLER CUSP WEB AT BS 580 - 586 AND X -54 TO X -60. REPLACED IAW SRM 51-10-3, PARA 14, 21, 38, 51-30-2.

Part: LONGERON — CRACKED (BS 1309) · airframe 62,201 hrs · 45,832 cycles

CRACK ON LONGERON 4L BS 1309. LONGERON REPAIRED IAW SRM 53-02, P12, FIG 18.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 62,201 hrs · 45,832 cycles

CRACKED FLOOR PANEL CHANNEL. FLOOR PANELS WERE REPAIRED IAW SRM 53-05, FIG 131C.

Part: CUSP WEB — CORRODED (BS 1153) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON RT CUSP WEB BS 1153, X -54 TO X -60. CUSP WEB REPAIRED IAW SRM 53-05, FIG 131A-10, 51-10-3 PAR 21-14, 51-30-2, 51-30-5.

Part: INTERCOSTAL — CRACKED (BS 1307-1322) · airframe 62,201 hrs · 45,832 cycles

CRACKED ON INTERCOSTAL X 0 BETWEEN BS 1307 TO 1322. INTERCOSTAL REPAIRED IAW SRM 53-01, FIG 2.

Part: FITTING — CORRODED (RT MLG) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON BUSHING BORE OF RT MAIN GEAR FITTING. RT GEAR RETRACT ACTUATOR SUPPORT FITTING BUSHINGS WAS REPAIR IN REF WITH IAW DWG SR09570087 FLAG NOTE 11 AREA OF BUSHING WERE MEASURED THICKNESS INBD 2.473" AND BUSHING 2.476.

Part: SUPPORT — CRACKED (BS 1212) · airframe 62,201 hrs · 45,832 cycles

CRACKED LT SLAT SUPPORT BS 1212, LONGERON 25L. SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-30-2, 51-10-3, PAR 14 AND 21 AND ER/A 413029-14 MA, REV D.

Part: SKIN — DAMAGED (BS 446-484) · airframe 62,201 hrs · 45,832 cycles

LIGHTNING STRIKE ON LT EXTERNAL FUSELAGE SKIN BETWEEN BS 446-484 BETWEEN LONGERONS 5 AND 6L. OUT OF LIMITS, REPAIRED IAW SRM 53-04-2, FIG 2.

Part: CUSP WEB — CORRODED (BS 550-567) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LT CUSP WEB BETWEEN BS 550-567 AND X 54 TO X 60E. DAMAGE WAS REMOVED, REPAIR FABRICATED, TREATED AND PAINTED, INSTALLED AND CIC WAS APPLIED IAW SRM 51-30-1, 53-05, FIG 131, 51-10-3 IAW 14, 21, 38.

Part: DEFLECTOR — CORRODED (BS 1338) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON WATER DEFLECTOR BS 1338. REMOVE AND REPLACED THE DEFLECTOR IAW SRM 51-30-1, 51-10-4, 51-10-3, PAR 14 AND 21.

Part: RIB — CRACKED (VERTICAL STAB) · airframe 62,201 hrs · 45,832 cycles

CRACKED LT RIB ON VERTICAL STABILIZER FIXED L/E STA ZFS STA ZFS 49.6. RIB WAS REPAIRED IAW SRM 55-02, FIG 27.

Part: FRAME — CRACKED (BS 1455) · airframe 62,201 hrs · 45,832 cycles

CRACKED FRAME BS 1455, LONGERON 1. FRAME REMOVED AND REPLACED IAW SRM 51-30-2 AND 51-30-5 AND DWG 9911860.

Part: CUSP WEB — CRACKED (BS 881-885) · airframe 62,201 hrs · 45,832 cycles

CRACKED RT CUSP WEB BETWEEN BS 881-885 , X -54 - X -60. CUSP WEB REPLACED IAW SRM 51-10-3 PARA 14, 21, 38, 51-10-4, 51-30-2.

Part: SKIN — CORRODED (BS 731-750) · airframe 62,201 hrs · 45,832 cycles

CORROSION ON EXTERNAL FUSELAGE SKIN BENEATH RUB STRIPS FILLET PANELS FROM STA Y=731 TO 750 BETWEEN LONGERON 18 AND 21 RT. CORROSION WAS REMOVED, MEASURE, TREAT, PAINT AND APPLIED CIC IAW SRM 51-10-3, PARAGRAPH 26, 21, 14 AND 38, AND 53-04, PARAGRAPH 57.

Part: CUSP WEB — DAMAGED (BS 1134) · airframe 62,201 hrs · 45,832 cycles

RT CUSP WEB BS 1134 X -60 DAMAGED. DAMAGE REMOVED, REPAIR REFABRICATED, INSTALLED, TREATED AND PAINTED AND CIC WAS APPLIED IAW SRM 51-30-5, 53-05. FIG 131A-9, 51-10-3 PAR 14, 21 AND 38.

Part: CUSP WEB — CORRODED (BS 1008) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LT CUSP WEB ANGLE BETWEEN X 59 AND BS 1008. CORROSION WAS REMOVED. DAMAGE WAS REMOVED. REPAIR FABRICATED. TREATED, PAINTED AND INSTALLED IAW SRM 51-10-3, PAR 14, 21, 26, 38, 51-30-2, 53-05 FIG 131A, AND ERA 511165-14MA REV B.

Part: LONGERON — CRACKED (BS 927) · airframe 62,201 hrs · 45,832 cycles

CRACKED LONGERON 7L BS 927 AT PAX CABIN. LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18.

Part: CUSP WEB — CORRODED (BS 895-905) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LT CUSP WEB BETWEEN BS 895 TO 905 AND X 56 TO X 59. REPAIRED IAW SRM 51-30-2, 51-10-3, PAR 26 AND 53-01, 53-05, FIG 131A-4.

Part: FRAME SPLICE — CRACKED (RT WING) · airframe 62,201 hrs · 45,832 cycles

CRACKED L/E SPLICE STA XRS 164 AT RT WING SPLICE WAS REMOVED, SPLICE WAS FABRICATED, TREATED, PAINTED AND INSTALLED IAW SRM 51-30-2, SRM 51-30-5.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON SETTLING AREA OF FUEL ACCESS PANEL LT WING. CORROSION WAS REMOVED, WITHIN LIMITS IAW 80DT SPM SRM 51-22-2A.

Part: FORMER — CRACKED · airframe 62,201 hrs · 45,832 cycles

CRACKED FORMER ON VENTRAL PANEL SUPPORT PROJECTION STAIR TUBE TORQUE BEAM. FORMER WAS REMOVED, REPLACED, OPEN NEW HOLES TREATED AND PAINTED, AND INSTALLED IAW SRM 51-30-2, 51-10-4, 51-10-3 PAR 14 AND 21 AND 51-30-5 AND IAW DWG 9911953.

Part: CUSP WEB — CRACKED (BS 808) · airframe 62,201 hrs · 45,832 cycles

CRACK ON LT CABIN FLOOR CUSP WEB ON BS 808 AND X 55. REMOVED DOUBLER, REMOVED DAMAGE. FABRICATED REPAIR PARTS. TREATED AND PAINTED NEW DOUBLER. INSTALLED NEW DOUBLER IAW SRM 51-30-2, 53-05 FIG 131, 51-10-3, PAR 21 AND 14 AND 38.

Part: RIB — CORRODED (NR 3 SLAT) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION BORE ON OTBD, MID INBD RIB XOS 286.963, XOS 332.588 XOS 380.229 AT RT SLAT PANEL NR 3. DAMAGES ON RIB MID, INBD AND OTBD WERE REWORKED, REAMED, WITH FINAL DIMENSION, RIB MID ID 0.938" ON 4 HOLES; THEREFORE OUT LIMITS OF BLUE PRINT HOLE DIAMETER. BUSHINGS WERE FABRICATED AND INSTALLED IAW SRM 57-02, PAR 9. DAMAGES ON RIB INBD AND OTBD WERE REWORKED IAW ETI-88-15-027 AND ER/A 531394-14, REV ORIGINAL.

Part: SKIN — CORRODED (BS 731-847) · airframe 62,201 hrs · 45,832 cycles

CORROSION ON EXTERNAL FUSELAGE SKIN BENEATH RUB STRIPS FILLET PANELS FROM BS 731-847 LONGERON 16 - 18R. CORROSION REMOVED, REWORKED AREAS FOUND WITHIN LIMITS AND AREAS WAS TREATED AND PAINTED IAW SRM 51-10-3, PAR 26, 21 AND 14 AND 53-04, PAR 57.

Part: CUSP WEB — CRACKED (BS 1076) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RT CUSP WEB BS 1076 X -54 TO X -60. DAMAGE AREA WAS OUT IAW SRM 53-05, FIG 131A-14. REPAIR PARTS WERE FABRICATED IAW SRM 53-05, FIG 131A-14. REPAIR PARTS WERE TREATED AND PAINTED IAW SRM 51-10-3, PAR 14/21. DOUBLER AND FILLER NEW INSTALLED IAW SRM 51-30-02, 53-05, FIG 131A-14.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON COUNTERSINK AREA OF FUEL ACCESS PLATES NR 1303C, 1379C, 1409C, 1307C, 1355C, 1311C, 1373C, 1367C, 1363C, 1357C, 1361C, 1335C AND 1365C AT LT WING. ACCESS 1409C CORROSION NO WAS NECESSARY THE REMETION BECAUSE NOT PERMITED BLEND. ACCESS 1303C A OUT ON SETTLEMENT AREA IAW SRM 51-22-2A COND 3 THEREFORE, WERE REPLACED UNDER CARD 25 ZONE 71. ACCESS PLATE NR 1379C-1363C-1373C-1367C AND 1361C WILL BE PERFORMER UNDER CARD 33, ZONE 71.

Part: SKIN — DAMAGED (BS 237-256) · airframe 62,201 hrs · 45,832 cycles

LIGHTING STRIKE ON FUSELAGE SKIN BETWEEN BS 237-256 LONGERONS 6-7L. REPAIR INSTALLED IAW SRM 53-04-2, FIG 1.

Part: CUSP WEB — CORRODED (BS 803) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LT CUSP WEB BS 803 BETWEEN X=55 TO X=60. CUT OUT DAMAGE FABRICATED REPAIR DOUBLER. TREATED AND PAINTED NEW DOUBLER. INSTALLED NEW DOUBLER. APPLIED CIC IAW SRM 53-05, FIG 131A-1, 51-10-3 PAR 21 AND 14 AND 38.

Part: RIB — CORRODED (RT WING) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON INBD, MID OTBD RIB XOS 530.834, - 610.311 AT RT SLAT PANEL NR 5. REPAIRED IAW SRM 57-02, PAR 9C (2), SRM 51-10-3, P 14 AND 21, SRM 51-30-10, P 7, SRM 51-30-30, 51-30-2, 51-10-4, 51-10-3, PAR 14/21, SRM 51-30-8 AND 51-30-2.

Part: SHEAR TIE — CRACKED (BS 1338) · airframe 62,201 hrs · 45,832 cycles

CRACK ON SHEAR TIE BS 1338, BETWEEN LONGERON 14R AND AFT PRESSURE BULKHEAD. REMOVED AND REPLACED IAW SRM 51-30-5, 51-10-3 AND DWG 99115558.

Part: STRAP — CRACKED (DOOR FRAME) · airframe 62,201 hrs · 45,832 cycles

CRACKED STRAP OF JOINT AFT LOWER SECTION DOOR JAMB WITH FLOOR SUPPORT BS 427 LONGERON 28R. STRAP OF JOINT WAS REMOVED, FABRICATED, TREATED, PAINTED AND INSTALLED IAW SRM 51-30-2, 51-30-5, REMOVED AND INSTALLED 51-10-3, PAR 21 AND 14, TREATED AND PAINTED, DWG 5936587, REV CC, FABRICATED.

Part: INTERCOSTAL — CRACKED (BS 237) · airframe 62,201 hrs · 45,832 cycles

CRACKED INTERCOSTAL ANGLE, BS 237 BETWEEN LONGERON L27 - 28L. INTERCOSTAL ANGLE REMOVED AND REPLACED IAW SRM 51-30-2, 51-30-2 , 51-30-5 AND DWG 9915554-REV U51-10-3, PAR 21 AND 14.

Part: CUSP WEB — CORRODED (BS 744) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION WAS REMOVED ON LIGHTNING HOLE, AND FOUND OUT LIMITS ON CUSP WEB BS 744, BETWEEN X 56, TO X 60. REMOVED DAMAGE AND FABRICATED REPAIR IAW SRM 51-30-2, 53-05, FIG 131, A 51-103, PAR 14 AND 21 AND 38.

Part: LONGERON — CRACKED (BS 1338) · airframe 62,201 hrs · 45,832 cycles

CRACKED LONGERON 1, BS 1338. REPLACED THE LONGERON IAW SRM 51-30-2 AND 51-30-5.

Part: CARGO TRACK — CORRODED (BS 1098-1155) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LT CARGO TRACK BS 1098-1155. THE CARGO TRACK WAS REPLACED IAW SRM 51-30-1 AND 51-30-2.

Part: CUSP WEB — CORRODED (BS 624-651) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON CUSP WEB BS 624 - 651 X -54 TO X -60. A REPAIR WAS INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: FLOORBEAM — CORRODED (BS 1338) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION FOUND ON FLOORBEAM BS 1338 BETWEEN X -17 TO X -60. THE FLOORBEAM WAS REMOVED AND REPLACED IAW SRM 51-30-2, 51-30-5 51-10-3 PARA 14 AND 21 AND 51-10-4 AND DWG 9915561.

Part: CUSP WEB — CORRODED (BS 1055-1204) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON RT CUSP WEB BETWEEN BS 1055-1204, X -54 - X -60. CORROSION REMOVED, REWORKED AREA WERE MEASURE, TREATED, PAINTED AND CIC WAS APPLIED IAW SRM 51-10-3, PARG 14, 21, 26, 38.

Part: SKIN — DAMAGED (BS 275) · airframe 62,201 hrs · 45,832 cycles

LIGHTNING STRIKE ON FASTENERS HEAD AT BS 275 BETWEEN LONGERONS 2-8L. REPAIRED IAW SRM 53-04-2, FIG 2.

Part: HOUSING — CORRODED (RUDDER YOKE) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON HOUSING OF RUDDER YOKE BEARING. REPLACED HOUSING IAW SRM 51-30-1 AND 51-30-2.

Part: ANGLE — CRACKED (NACELLE) · airframe 62,201 hrs · 45,832 cycles

CRACK ON ACCESS PANEL ANGLE. ANGLE REPLACED IAW DWG 9935747, REV SRM 51-10-3, P-21-14, 51-30-2.

Part: ANGLE — CRACKED (LT NACELLE) · airframe 62,201 hrs · 45,832 cycles

CRACK ON ACCESS PANEL ANGLE. ANGLE WAS REPLACED IAW DWG 9935747, REV SRM 51-10-3, PAR 21-14, SRM 51-30-2.

Part: CUSP WEB — CORRODED (BS 713-722) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON CUSP WEB OUT OF LIMITS BS 713-722 BETWEEN X 56 AND X 60. REPAIRED, TREATED AND PAINTED IAW SRM 53-05, FIG 131A- 6.

Part: TAB — DAMAGED (RUDDER) · airframe 62,201 hrs · 45,832 cycles

DAMAGE FLAME SPRAY ON RUDDER CONTROL TAB. FLAME SPRAY ON RUDDER CONTROL TAB WAS REPAIRED AND PAINTED IAW SRM 51-70-1AD PAR 23 AND 51-10-3B.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON COUNTERSINK AREA OF FUEL ACCESS PANLE RT WING. OUT OF LIMITS IAW SRM 51-22-2A WAS REPLACED.

Part: CHANNEL — CRACKED (VERTICAL STAB) · airframe 62,201 hrs · 45,832 cycles

CRACKED Z CHANNEL ON VERTICAL STABILIZER T/E BETWEEN ZRS 38.2 AND ZRS 57.7. Z-CHANNEL REPAIRED IAW SRM 55-01, FIG 2.

Part: RIB — DAMAGED (NR 5 SLAT) · airframe 62,201 hrs · 45,832 cycles

ELONGATED HOLE OF ECCENTRIC RETAINER ATTACH ON RT SLAT PANEL NR 5 STA XOS=530. RIB ON STA XOS= 530 AND INTERNAL STRUCTURE, LOWER SKIN WERE REMOVED IAW SRM 51-30-8, AND SRM 51-30-2. NEW RIB ON STA=530 WAS DRILLED IAW SRM 51-10-4. HOLES WERE TREATED AND PAINTED IAW SRM 51-10-3, PAR 14 AND 21. NEW RIB STA XOS=530 AND INTERNAL STRUCTURE LOWER SKIN WERE INSTALLED IAW SRM 51-30-08 AND 51-30-2.

Part: ANGLE — CRACKED (BS 1388) · airframe 62,201 hrs · 45,832 cycles

CRACKED ANGLE BEHIND BS 1388. CRACKED ANGLE REPLACED IAW DWG 5937954 AND SRM 10-4, 51-30-5.

Part: FRAME — CRACKED (BS 1380) · airframe 62,201 hrs · 45,832 cycles

CRACKED FRAME ANGLE BS 1380 LONGERON 15R . FRAME ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-2, 51-30-5, 53-14-4, FIG 1, AND 51-10-3, PAR 14-21.

Part: CUSP WEB — CORRODED (BS 693-705) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION FOUND ON THE LT CUSP WEB BETWEEN BS 693-705 AND X 54 TO X 60. THE CUSP WEB WAS REPLACED IAW SRM 51-30-2, 51-30-5, 51-10-3 PARA 14, 21, 38, 51-30-5.

Part: SUPPORT — CRACKED (SLAT TRACK DOOR) · airframe 62,201 hrs · 45,832 cycles

CRACKED SLAT TRACK DOOR SUPPORT. BRACKET REMOVED AND REPLACED IAW SRM 51-30-1, SRM 51-10-2 AND DWG 9937467, SRM 51-10-3 P 14/21, AND SRM 51-30-1.

Part: ANGLE — CRACKED (BS 197) · airframe 62,201 hrs · 45,832 cycles

CRACKED ANGLE ON BEAM END NR 1, BS 197. THE ANGLE WAS REMOVED AND REPLACED IAW DWG 9955752, REV M AND SRM 51-30-2 AND 51-30-5.

Part: FLOOR SUPPORT — CORRODED (BS 160-195) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON FLOOR SUPPORT BETWEEN BS 160 - 195, LBL 54. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW 31-30-2, 51-30-5, 53-14-1, FIG 1, 51-10-4, 51-10-3, PAR 21 AND 18 AND PAR 38.

Part: INTERCOSTAL — CRACKED (BS 1338) · airframe 62,201 hrs · 45,832 cycles

CRACKED INTERCOSTAL, BS 1338 AND LONGERON 3R. THE INTERCOSTAL WAS REMOVED AND REPLACED IAW SRM 51-30-2, SRM 51-10-4 AND SRM 51-30-2 AND 51-30-5.

Part: SUPPORT — CRACKED (SLAT TRACK DOOR) · airframe 62,201 hrs · 45,832 cycles

CRACKED SUPPORT OF SLAT TRACK DOOR. SUPPORT REMOVED AND REPLACED IAW SRM 51-10-2, DWG 9954156, SRM 51-10-3, P 14/21, AND SRM 51-30-1.

Part: CUSP WEB — CORRODED (BS 479) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION FOUND ON THE RT CUSP WEB X -60 BS 479. THE CUSP WEB WAS REPAIRED IAW SRM 51-30-2, 51-30-5, 53-05, FIG 13A, 51-10-3 PARA 14,21,38.

Part: BRACKET — CORRODED (DOOR LATCH) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON BRACKET TO ATTACH ROD OF FWD AIRSTAIR DOOR LATCH MECHANISM CABIN CONTROL. BRACKET UNSERVICEABLE DUE TO EXCESSIVE CORROSION BRACKET WAS REPLACED FOR NEW BRACKET IAW AMM 20-30-01-201.

Part: FLOOR SUPPORT — CORRODED (BS 313-807) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION AND WEAR ON FLOOR SUPPORT BETWEEN STA X= 22 AND X=-22 AND Y= 313, 389, 465, 541, 579, 693, 807 AT PAX CABIN. CORROSION WAS REMOVED, AREAS WITHIN LIMITS WERE MEASURED, TREATED, PAINTED AND CIC WAS APPLIED. OUT OF LIMITS SUPPORTS WERE REMOVED, AND NEW FLOOR SUPPORTS WERE DRILLED, ADJUSTED, TREATED, PAINTED, INSTALLED, AND CIC WAS APPLIED IAW SRM 53-01, FIG 1, 51-10-3, PARA 21, 14, 30 AND 51-30-5, 51-10-4.

Part: PAN — DAMAGED (SERVICE DOOR) · airframe 62,201 hrs · 45,832 cycles

CRACKED PAN BETWEEN BEAMS 3 AND 4 IN LOWER HINGE AT FWD SERVICE DOOR. INNER SKIN, FITTINGS, RUBSTRIPS AND CLIP WERE REMOVED IAW SRM 51-30-5, 51-30-4 AND 51-30-1. REPAIR WAS MANUFACTURED IAW SRM 52-03D, FIG. 3. FABRICATED PARTS AND REPAIR WERE INSTALLED IAW SRM 51-30-5, 51-30-4 AND 51-30-1. INNER SKIN, FITTINGS, RUBSTRIP AND CLIP WERE INSTALLED IAW SRM 51-30-5, 51-30-4 AND 51-30-1.

Part: FLOORBEAM — BROKEN (BS 965) · airframe 62,201 hrs · 45,832 cycles

BROKEN FLOORBEAM ANGLE BS 965, BETWEEN X 0 TO X -18. THE FLOORBEAM ANGLE WAS REPLACED IAW SRM 53-14-3, 51-10-4, 51-30-5, AND 51-10-3, P 21, 14, 38.

Part: ANGLE — CRACKED (LT WING) · airframe 62,201 hrs · 45,832 cycles

CRACKED ANGLE RIB OF FWD SPAR XRS=189.00 AT LT WING. CLIP WAS REPLACED IAW DWG NR 9937586, REV D AND SRM 51-30-1 AND 51-30-5.

Part: SKIN — CRACKED (LT WING) · airframe 62,201 hrs · 45,832 cycles

CRACKED ON L/E LOWER SURFACE STA XRS 267 AT LT WING. L/E LOWER SURFACE WAS REPAIRED IAW SRM 57-06B, FIG14.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION FOUND ON ACCESS PANEL. THE ACCESS PANEL WAS REPLACED.

Part: SKIN — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON HORIZONTAL STABILIZER LT UPPER PANEL STA XH=27.2. DAMAGE WAS REWORKED AND FOUND OUT OF LIMITS. REPAIR BUSHINGS WERE FABRICATED AND INSTALLED IAW SRM 55-03D, PAR 30. OTHER DAMAGE REWORKED IAW ETI-88-15-029, REV ORIGINAL AND ER/A 531396-14, REV ORIGINAL.

Part: ANGLE — CRACKED (DOOR FRAME) · airframe 62,201 hrs · 45,832 cycles

CRACKED ANGLE ON UPPER CHANNEL BELOW STOP FITTING NR 12 AT RT/ FWD EMERGENCY EXIT. NEW ANGLE WAS FABRICATED IAW SRM 51-10-2 AND DWG 9957735, REV 6, SRM 51-10-3 PAR 14/21. ANGLE WAS INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: HOUSING — WORN (CARGO DOOR) · airframe 62,201 hrs · 45,832 cycles

WEAR ON HANDLE HOUSING OF MID CARGO DOOR. MECHANISM ON HANDLE OF MID CARGO COMPARTMENT DOOR WAS R & R HOUSING IAW AMM 52-30-1. DUE TO WEAR EXCESSIVE ON HOUSING WAS R & R IAW SRM 51-30-2 AND 51-30-5.

Part: CUSP WEB — CORRODED (BS 582-590) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LT CUSP WEB REPAIR DOUBLER BETWEEN BS 582-590 AND X=54 TO X=60 AT CABIN FLOOR STRUCTURE. CORROSION WAS ATTENDED ON WEB DOUBLER IAW SRM 53-05, FIG 131 A-6 AND 51-10-3, PAR 26, 14, 21 AND 38.

Part: STRUCTURE — WORN (RT WING TE FLAP) · airframe 62,201 hrs · 45,832 cycles

WEAR ON INBD SEAL OF RT OTBD FLAP. OTBD FLAP FIXED VANE INBD SIDE WAS REPAIRED IAW ER/A 521199-14 MA.

Part: ACCESS PANEL — DAMAGED (WING) · airframe 62,201 hrs · 45,832 cycles

ELONGATED HOLES ON CENTRAL FUEL ACCESS PANEL 2302C. THE ACCESS PANEL WAS REPLACED.

Part: FITTING — CRACKED (LT WING) · airframe 62,201 hrs · 45,832 cycles

CRACKED FITTING ON FRONT SPAR TO ATTACH LINK OF INTI-ICE DUCT STA XRS=69 AT LT WING. REMOVE FITTING TREAT AND PAINT NEW FITTING AJUST AND DRILL NEW FITTING. INSTALLED NEW FITTING IAW SRM 51-30-5 AND 51-10-3, PAR 14 AND 21, DWG 9930529, REV F 5.

Part: EXHAUST DUCT — CRACKED (APU) · airframe 62,201 hrs · 45,832 cycles

CRACKED APU EXHAUST DUCT . EXHAUST DUCT APU WAS REPAIRED, AND WELDED, IAW ER/A 473221-14 MA RE, ORIGINAL.

Part: SKIN — CRACKED (BS 1380) · airframe 62,201 hrs · 45,832 cycles

A CRACK WAS FOUND ON THE FUSELAGE SKIN BETWEEN BS 1380 LONGERON 14L. THE SKIN WAS REPAIRED IAW SRM 53-04 FIG.18.

Part: BULKHEAD WEB — CRACKED · airframe 62,201 hrs · 45,832 cycles

THE FS 1437 BULKHEAD WEB WAS SPLICED FROM L1R-L4R TO REMOVE A CRACK. CRACK ON FRAME WAS REPAIRED IAW ER/A 532506-14, REV ORIGINAL.

Part: ANGLE — CRACKED (BS 1174) · airframe 62,201 hrs · 45,832 cycles

CRACK ON ANGLE BETWEEN LOWER EDGE AND BEAM, NR 1 BS 1174 OF AFT CARGO COMPARTMENT DOOR. ANGLE CRACK WAS REMOVED IAW SRM 51-30-2. ANGLE WAS INSTALL IAW SRM 51-30-2.

Part: STOP FITTING — CRACKED (CARGO DOOR) · airframe 62,201 hrs · 45,832 cycles

CRACKED STOP FITTING AT FWD CARGO DOOR FWD EDGE. A NEW STOP FITTING DRILLED IAW SRM 51-10-4 AND INSTALLED IAW SRM 51-30-1 AND 51-30-2.

Part: CUSP WEB — CORRODED (BS 523-530) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LT CABIN FLOOR CUSP WEB REPAIR DOUBLER BETWEEN BS 523 - 530 AND X=55 TO Y=60. REPAIR DOUBLER WAS REMOVED, REPAIR PARTS WERE FABRICATED WAS TREATED AND PAINTED, NEW DOUBLER WAS INSTALLED, CIC WAS APPLIED IAW SRM 51-30-5, 53-05 FIG 131A-13, 51-10-3 PAR 14 AND 21 PAR 38.

Part: PAN — CRACKED (CARGO DOORWAY) · airframe 62,201 hrs · 45,832 cycles

CRACKED DOOR PAN ON AFT STOP NR 1 AT MID CARGO DOOR IN REF DAMAGE AREA WAS REWORKED IAW SRM 52-03, PAR 6, FIG 1.

Part: ANGLE — CRACKED (PAX DOOR) · airframe 62,201 hrs · 45,832 cycles

WORN AND CRACKED RT ANGLE BETWEEN BEAM 4 TO LOWER CHANNEL AT PASSENGER AFT ENTRANCE STAIRWELL DOOR. ANGLE WAS REPAIRED IAW SRM 52-01, FIG 4.

Part: SKIN — CRACKED (BS 1380) · airframe 62,201 hrs · 45,832 cycles

CRACK ON FUSELAGE SKIN BS 1380, BETWEEN LONGERONS 13 - 14R. REPAIRED IAW SRM 53-04, FIG 18, 51-10-3, P 21-14, 51-30-2, AND 51-30-5.

Part: DOUBLER — CORRODED (BS 1338) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON INNER PRODUCTION DOUBLER STA Y=1338 BETWEEN LONGERON 28L-28R. THE DOUBLER WAS REPLACED IAW DWG 9915561, REV AND SRM 51-10-4.

Part: TEE FITTING — DAMAGED (BS 1338) · airframe 62,201 hrs · 45,832 cycles

TOOL DAMAGE ON TEE FITTING BS 1338 AFT PRESSURE BULKHEAD. . FABRICATE REPAIR, TREAT, PAINT, AND INSTALLED IAW SRM 51-30-5, 51-30-2, 51-30-1 AND 51-20-0 AND 53-05, FIG 37.

Part: INTERCOSTAL — CRACKED (BS 886) · airframe 62,201 hrs · 45,832 cycles

CRACK ON AFT UPPER HORIZONTAL INTERCOSTAL BS 886 BETWEEN BEAM 1 AND 2 AT FWD LT EMERGENCY EXIT OVERWING DOOR. INTERCOSTAL WAS REMOVED IAW SRM 51-30-2. INSTALLED IAW SRM 51-30-2.

Part: FLOOR SUPPORT — CORRODED (BS 1117-1155) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON FLOOR SUPPORT BS 1117 - 1155 LONGERON 28R. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-1, 51-10-3, PAR 14 AND 21 AND 51-10-4.

Part: PAN — CRACKED (CARGO DOOR) · airframe 62,201 hrs · 45,832 cycles

CRACK ON INNER PAN LOCATED BEAM NR 5, BEHIND STOP FITTING AT FWD CARGO DOOR AFT EDGE. CRACK WAS STOPPED AND NEW DOUBLER WAS FABRICATED IAW SRM 52-03, D FIG 8. NEW DOUBLER WAS INSTALLED IAW SRM 52-03, FIG 8 AND 51-30-5.

Part: BUSHING — DAMAGED (LT ELEVATOR) · airframe 62,201 hrs · 45,832 cycles

SCRATCHES ON BUSHINGS OF ATTACH POINTS, XE: 49-103-157-204-225 AT LT ELEVATOR FWD SPAR. BUSHINGS REPLACED IAW CMM.-27-301.

Part: DOUBLER — WORN (FWD CARGO BAY) · airframe 62,201 hrs · 45,832 cycles

WEAR ON DOUBLERS LOCATED FWD CARGO OUTER SKIN FWD AND AFT LOWER CORNERS. DAMAGE DOUBLERS WERE REMOVED IAW SRM 51-30-2. NEW DOUBLERS WERE FABRICATED IAW SRM 52-05, A FIG 806D. NEW DOUBLERS WERE TREATED AND PAINTED IAW SRM 51-10-3, PAR 14 AND 21.

Part: SKIN — DAMAGED (RT WING) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION AND CRACKS ON RT WING LOWER ACCESS CUTOUT BETWEEN XRS=189.0-214.0 AND STRINGERS 12-15-RT. BOLT HOLE WAS REMOVED IAW SRM 51-22-2A, BUSHING WAS FABRICATED AND INSTALLED IAW SRM 51-22-2A, PAR 7B 2, 51-10-3 PAR 21, 51-30-10 AND 51-10-4.

Part: CUSP WEB — CORRODED (BS 886-894) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON RT CUSP WEB, BS 886-894, X -54 - X -60. THE CUSP WEB WAS REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: FLOORBEAM — CORRODED (BS 1322) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON FLOORBEAM BS 1322, BETWEEN LBL 27 - 28. DAMAGE WAS REMOVED, FILLER WAS FABRICATED, DOUBLER WAS TRIMED. REPAIR TREATED, PAINTED, AND INSTALLED IAW SRM 51-10-3 PAR 21, 14, 38, 53-05 FIG 20.

Part: DOUBLER — WORN · airframe 62,201 hrs · 45,832 cycles

WEAR ON PRODUCTION DOUBLER BETWEEN BEAM 4 TO LOWER CHANNEL AT PASSENGER AFT ENTRANCE STAIRWELL DOOR. DAMAGE ANGLE WAS REMOVED, DUE TO EXCESSIVE DAMAGE ANGLE. FABRICATED, AND NEW ANGLE WAS TREATED, PAINTED AND INSTALLED IAW SRM 51-30-2, 51-30-4, 51-30-5, 51-10-3 PAR 14/21, 51-10-2 AND DWG 9929480, REV BW.

Part: BEAM — CRACKED (R1 DOOR) · airframe 62,201 hrs · 45,832 cycles

CRACKED BEAM NR 1 FWD SECTION OF FWD SERVICE DOOR, R1, CUP PLATE, INNER SKIN, 2 INTERCOSTAL, 2 SUPPORTS, 2 CLIPS, 6 RETAINERS, SEAL AND BEAM WERE REMOVED IAW SRM 51-30-1, 51-30-2 AND 51-30-5. BEAM WAS DRILLED IAW SRM 51-10-4. BEAM HOLES WERE TREATED AND PAINTED IAW SRM 51-10-3. NEW BEAM WAS INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: WEB — PUNCTURED (BS 348) · airframe 62,201 hrs · 45,832 cycles

PUNCTURED WEB BELOW SEAT TRACK X.-54 BS 348. DAMAGE AREA WAS REPAIRED IAW SRM 53-05, FIG 131A-5.

Part: INTERCOSTAL — CRACKED (BS 1338) · airframe 62,201 hrs · 45,832 cycles

CRACK ON INTERCOSTAL BEHIND PULLEY BRACKET BS 1338 . REPAIRED IAW SRM 53-01, FIG 2 AND 51-30-5, 51-30-2 AND DWG 9915540, ID:2, REV, AH.

Part: STRUCTURE — CORRODED (BS 786-807) · airframe 62,201 hrs · 45,832 cycles

CORROSION ON SEATING AREA OF RUBSTRIP ON BS 786 - 807 BETWEEN LONGERON 16 TO 18L. CORROSION WAS REMOVED AND REWORKED AREA, TREATED AND PAINTED IAW SRM 51-10-3 PAR 26,21 AND 14 AND 53-04, PAR 57.

Part: PAN — CRACKED (EMERGENCY EXIT) · airframe 62,201 hrs · 45,832 cycles

CRACKED PAN ON RT AFT EMERGENCY EXIT DOOR BELOW STOP FITTING NR 1. STOP FITTING, WEB AND CLIP WERE REMOVED IAW SRM 51-30-2 AND 51-30-5. CRACK WAS FOUND OF 1.250" OF LENGTH IAW NDT SRM 06-01-10.001, CRACKED WAS STOPED IAW SRM 51-01. DOUBLER WAS FABRICATED IAW 51-10-2 AND 52-05D, FIG. 51, DOUBLER WAS PAINTED IAW SRM 51-10-3, PAR 21, DOUBLER WAS FABRICATED IAW SRM 51-10-3, REPAIR DOUBLER WAS INSTALLED IAW SRM 51-30-2, SHIMS WERE FABRICATED IAW SRM 52-05 IAW SRM 51-10-3 PAR 14, CLIP , WEB, SHIMS AND STOP FITTING WERE INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: ANGLE — CRACKED · airframe 62,201 hrs · 45,832 cycles

CRACKED ANGLE BELOW BEAM NR 1 AFT SECTION OF FWD SERVICE DOOR. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-1 AND 51-30-5 PAR 7/8 CLIP WAS MANUFACTURED IAW DWG 9911579 REV L ANGLE WAS TREATED AND PAINTED IAW SRM 51-10-3. NEW ANGLE AFT WAS INSTALLED IAW SRM 51-30-1 AND 51-30-5.

Part: SKIN — CRACKED (RT ELEVATOR) · airframe 62,201 hrs · 45,832 cycles

CRACKED LOWER SKIN XE=2 ON RT ELEVATOR. REMOVED THE DAMAGED SKIN. FABRICATED NEW DOUBLER DWG AND TRIM. INSTALLED THE NEW DOUBLER IAW SRM 51-30-2, 55, 22-0, FIG 3, 51-10-4 AND 51-10-3 PAR 1 AND 21.

Part: SKIN — CRACKED (LT ELEVATOR) · airframe 62,201 hrs · 45,832 cycles

CRACK ON LOWER SKIN STA XE=2 OF LT ELEVATOR. REMOVED DAMAGE SKIN. FABRICATED A DOUBLER, DRILLED AND TRIMED. TREATED AND PAINTED THE DOUBLER AND INSTALLED IAW SRM 51-30-2, 55-22-0, FIG 3, 51-10-4, 51-10-3, PAR 14 AND 21.

Part: SKIN — CORRODED (BS 1338) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON WEB BS 1338 LONGERON 28L. REPAIRED IAW SRM 51-70-4.

Part: DOUBLER — CORRODED (BS 1338 BULKHEAD) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON PRESSURE DOME SKIN INTERNAL PRODUCTION DOUBLER AT STA Y=1338 AND PROTECTION OF LONGERON 30. REMOVE PRODUCTION DOUBLER. FABRICATE NEW DOUBLER. TREAT/ PAINT NEW DOUBLER. INSTALL NEW DOBLER IAW SRM 51-30-5, DWG 5910130, REV ET, 51-10-4, AND 51-10-3, PARA 21 AND 14.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 62,201 hrs · 45,832 cycles

BENT AND CRACKED DOUBLER AROUND OTBD LATCH OF FWD PASSENGER DOOR. DAMAGE DOUBLER WAS REMOVED IAW SRM 52-05, FIG 20A, HOLD OPEN HOOK WAS REMOVED IAW IAW AMM 52-11-04-201. AREA AND DOUBLER WERE TREATED AND PAINTED IAW SRM 51-10-3, PAR 14 AND 21 DOUBLER WERE TREATED AND PAINTED IAE SRM 51-10-3 PAR 14 AND 21. DOUBLER WAS INSTALLED IAW SRM 51-30-2 AND 52-05- FIG.20A. HOLD OPEN HOOK WAS INSTALLED IAW AMM 52-11-04-201.

Part: FLOOR SUPPORT — CORRODED (BS 160-200) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION WAS FOUND ON THE FLOOR SUPPORT BETWEEN BS 160 - 200, LBL 8. THE CORROSION WAS REMOVED IAW SRM 51-10-3 PAR 26, 14, 21 AND 38 AND 51-30-1.

Part: DIAPHRAGM — PUNCTURED (BS 200) · airframe 62,201 hrs · 45,832 cycles

PUNCTURED DIAPHRAGM, BS 200, LBL 37. DAMAGE WAS CUTOUT. REPAIR FABRICATED, TREATED, PAINTED, AND INSTALLED IAW SRM 51-30-2, 51-70-4, FIG 2, 51-10-3 PAR 21, 14.

Part: RIB — CRACKED (LT WING) · airframe 62,201 hrs · 45,832 cycles

CRACKED RIB ON LT WING L/E XRS=164. RIB WAS REPLACED IAW DWG 9937517 AND SRM 51-30-2 AND 51-30-5.

Part: FLOORBEAM — CORRODED (BS 256) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON FLOORBEAM BS 256, BETWEEN X=22 AND X=-22. THE FLOORBEAM WAS REMOVED AND REPLACED IAW SRM 51-30-5, PARA 8 FIG 16, SRM 51-10-4, 53-14-2 FIG 4, SHEET 1 AND 2, SRM 51-10-3 AND SRM 51-30-5 PAR 7.

Part: SKIN — CRACKED (BS 1380) · airframe 62,201 hrs · 45,832 cycles

CRACK ON FUSELAGE SKIN AT BS 1380 BETWEEN LONGERONS 13 AND 14R. THE DAMAGE WAS REMOVED AND AREA WAS REPAIRED IAW ER/A 505302-14, REV ORIG.

Part: DOUBLER — CRACKED (LT WING) · airframe 62,201 hrs · 45,832 cycles

CRACKED INNER DOUBLER REPAIR OF LT WING L/E XRS 164 . INNER DOUBLER WAS REPLACED IAW SRM 57-32-1, FIG 1.

Part: FLOOR SUPPORT — CORRODED (BS 195-200) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION WAS FOUND ON THE FLOOR SUPPORT BETWEEN BS 195 - 200, LBL 54. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW 51-30-2, 51-30-5, 51-14-1 FIG.11, SRM 51-10-3 PAR 21 AND 14 AND PAGE 38.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 62,201 hrs · 45,832 cycles

CRACKED ANGLE BELOW BEAM NR 1 FWD SECTION OF FWD SERVICE DOOR. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-1 AND 51-30-5, PAR 7/8.

Part: ANGLE — CRACKED (BS 186) · airframe 62,201 hrs · 45,832 cycles

CRACKED ANGLE BS 186 BETWEEN BEAM NR 4 TO 5. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-10-4, 51-10-3 PAR 14 AND 21.

Part: FLOORBEAM — CORRODED (BS 200) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON FLOORBEAM AT BS 200 BETWEEN LBL 9 - 13. CORROSION WAS REMOVED IAW SRM 51-10-3, PAR 21, 14, 38, 26, AND 51-30-2, 53, 14-1, FIG 11.

Part: PAN — CRACKED (EMERGENCY EXIT) · airframe 62,201 hrs · 45,832 cycles

CRACKED PAN ON RT AFT EMERGENCY EXIT DOOR BELOW STOP FITTING NR 12, DOUBLER WAS FABRICATED IAW 51-10-2 AND 52-05D, FIG 51. DOUBLER WAS INSTALLED IAW SRM 51-30-2, WEB, CLIP, SHIMS AND STOP FITTING WERE INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: FLOORBEAM — CORRODED (BS 200) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON FLOORBEAM BETWEEN BS 200, RBL 46 - 56. CORROSION WAS REMOVED IAW SRM 51-10-3, PAR 14, 21, 26 AND 38, 51-30-2, 53-01, FIG 1 AND 53-14-1 FIG 11, SHEET 1 AND 2.

Part: FLOOR SUPPORT — CORRODED (BS 185-195) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON FLOOR SUPPORT BETWEEN BS 185 - 195, X -51 LT. CORROSION REMOVED IAW SRM 51-30-2, 53, 01, FIG 1, 53-14-1, FIG 11, SHEET 1 AND 2 AND 51-10-3, PAR 26, 14, 21 AND 38.

Part: RIB — DAMAGED (NR 5 SLAT) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION AND SCRATCHED ON AFT RIB BORE STA XOS 530.834 OF LT SLAT NR 5. DAMAGES ON AFT RIB BORE XOS=530.834 WERE REWORKED. BUSHINGS WERE FABRICATED AND INSTALLED IAW SRM 57-02, PAR 9.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 62,201 hrs · 45,832 cycles

CRACK ANGLE BETWEEN BEAM 1 AND AFT SECTION DOOR PAN AT LT AFT EMERGENCY EXIT. THE ANGLE WAS REMOVED IAW SRM 51-30-2 AND 51-30-5. AND A NEW ANGLE WAS FABRICATED IAW SRM 51-10-2/ DWG NR 9957735, REV 6. THE ANGLE WAS INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: SKIN — SCRATCHED (FUSELAGE) · airframe 62,201 hrs · 45,832 cycles

SCRATCH ON WINDOW BELT AFT MID SECTION CUT OUT WINDOW BTA STA 946-965 RT. SCRATCH WAS BLEND OUT, MEASURED, REWORKED AREA WAS TREATED IAW SRM 53-05, FIG 111, 51-10-3 PAR 21.

Part: PANEL — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON HORIZONTAL STABILIZER RT UPPER PANEL STA XH= 27.2. DAMAGE WAS REWORKED, REAMED AND FOUND OUT OF LIMITS. REPAIR BUSHINGS WERE FABRICATED AND INSTALLED IAW SRM 55-03D, PAR 30.

Part: CUSP WEB — CRACKED (BS 237-258) · airframe 62,201 hrs · 45,832 cycles

CRACK ON CABIN FLOOR CUSP WEB BETWEEN BS 237 - 258 AND RBL 54 - 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-13, 51-30-2, 51-10-3 PAR 14, 21 AND 38, AND 51-30-5.

Part: SEAT TRACK — CORRODED (BS 530-534) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION FOUND ON REPAIR PLUG IN THE SEAT TRACK BETWEEN BS 530-534, X 54. THE REPAIR PLUG WAS REPLACED IAW SRM 53-05, FIG 4A.

Part: SEAT TRACK — CORRODED (BS 343-347) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON SEAT TRACK REPAIR PLUG BETWEEN BS 343 - 347, X -54, REPAIR WAS REPLACED IAW SRM 53-05, FIG 4A.

Part: PAN — CRACKED (BS 617) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RING PAN AT CORNER UP FWD ON BS 617. FATSENERS WERE REMOVED. DAMAGE ARE WAS REMOVED. REPAIR PARTS WERE FABRICATED, TREATED AND PAINTED. ANGLE WAS INSTALLED IAW SRM 51-30-2, 51-30-3, 53-05 FOG. 122, 51-10-3 PAR 21 AND 14. ER/A 593648-14 MA REV, ORIG AND 487747-14MA, REV ORIG.

Part: LONGERON — CRACKED (BS 1437) · airframe 62,201 hrs · 45,832 cycles

CRACKED LONGERON 16L BS 1437 . LONGERON WAS REMOVED AND A NEW LONGERON WAS WAS DRILLED. THE NEW LONGERON WAS TREATED AND PAINTED AND WAS INSTALLED IAW AMM AND SRM 54-20-00, 51-30-5, 51-10-4 AND 51-10-3 PAR 14-21.

Part: RIB — CORRODED (NR 1 SLAT) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON FWD RIB BORE OF LT SLAT NR 1 STA XIS 136.421. CORROSION ON FWD RIB BORE WERE REMOVED, HOLES WERE MEASURED WITH ID 0.938", 2 EA, THEREFORE OUT LIMITS BLUE PRINT HOLE DIAMETER, REPAIR BUSHINGS WERE FABRICATED AND INSTALLED IAW SRM 57-02, PAR.9 C, 1,2.

Part: RIB — CORRODED (NR 1 SLAT) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION BORE ON RIB STA=XOS 136.421 AT RT SLAT PANEL NR 1. CORROSION ON RIB STA=XOS 136.421 WERE REMOVED, HOLES WERE MEASURED WITH FINAL I.D. 0.938", 4 EA, THEREFORE OUT LIMITS BLUE PRINT HOLE DIAMETER REPAIR BUSHINGS WERE FABRICATED AND INSTALLED IAW SRM 57-02, PAR 9.

Part: RIB — CORRODED (NR 3 SLAT) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON FWD RIB BORE OF LT SLAT 3 XOS 288.693. CORROSION ON FWD RIB BORE WAS REMOVED AND FOUND OUT LIMITS. A REPAIR BUSHING WAS FABRICATED AND INSTALLED IAW SRM 57-02, PAR.9, 1, 2.

Part: FLOORBEAM — CORRODED (BS 101) · airframe 62,201 hrs · 45,832 cycles

CRACK ON FLOORBEAM ANGLE AT BS 101.550 X -34 AND X 34. THE FLOORBEAM ANGLE REMOVED, FABRICATED, AND INSTALLED IAW SRM 51-30-2, 51-30-1, 51-10-3, 51-10-4 AND DWG 9957820, REV GN.

Part: PAN — CRACKED (BS 1211) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RING PAN AT CORNER UP AFT BS 1211 RT SIDE. RING PAN WAS REPAIRED IAW SRM 53-05, FIG-122, 51-10-2 51-10-3, PAR 21 AND 14.

Part: PAN — CRACKED (BS 1079) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RING PAN AT CORNER LOWER FWD BS 1079, RT SIDE. RING PAN AT CORNER LOWER FWD WAS REPAIRED IAW SRM 53-05, FIG 122, 51-10-2, 51-10-3 PAR 21 AND 14.

Part: PAN — CRACKED (BS 712) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RING PAN AT CORNER LOWER AFT BS 712 RT SIDE. RING PAN WAS REPAIRED IAW SRM 53-05, FIG 122, 51-10-2, 51-10-3 PAR 14 AND 21.

Part: PAN — CRACKED (BS 1174) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RING PAN AT CORNER UP AFT BS 1174 RT SIDE. RING PAN REPAIRED IAW SRM 53-03, FIG-122, 51-10-2, 51-10-3, PAR 21 AND 14.

Part: PAN — CRACKED (BS 1041-1060) · airframe 62,201 hrs · 45,832 cycles

CRACKED RT WINDOW RING PAN BETWEEN BS 1041 AND 1060 AFT LOWER CORNER. RING PAN WAS REPAIRED IAW SRM 53-05, FIG 122, 51-10-2, 51-10-3, PAR 21 AND 14.

Part: PAN — CRACKED (BS 845) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RING PAN AT CORNER UP FWD BS 845 RT SIDE. RING PAN AT CORNER UP WAS REPAIRED IAW SRM 53-05, FIG 122, 51-10-2, 51-10-3 PAR 21 AND 14.

Part: PAN — CRACKED (BS 1136) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RING PAN AT CORNER UP AFT BS 1136 RT SIDE. RING PAN REPAIRED IAW SRM 53-05, FIG 122, 51-10-2, 51-10-3 PAR 21 AND 14.

Part: PAN — CRACKED (BS 1003-1250) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RT WINDOW RING PAN AFT UPPER CORNER STA Y=1003-1022, 1231-1250 AT PAX CABIN STRUCTURE. RING PAN WERE REPAIRED IAW SRM 53-05, FIG 122 AND ERA 487747-14MA, REV ORIG, ERA 493648-14MA, REV ORIG.

Part: PAN — CRACKED (BS 886-946) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RT WINDOW RING PAN FWD UPPER CORNER STA Y=886-905, Y= 927-946 AT PAX CABIN STRUCTURE. RING PAN WERE REPAIRED IAW SRM 53-05, FIG 122 AND ERA 487747-14MA REV ORIG 493648-14MA REV ORIGINAL.

Part: PAN — CRACKED (BS 484-503) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RT WINDOW RING PAN AFT LOWER CORNER STA Y=484-503. THE RING PAN WAS REPAIRED IAW SRM 53-05, FIG 122 AND ERA 487747-14MA, REV ORIG AND ERA 493648-14MA, REV ORIGINAL.

Part: PAN — CRACKED (BS 579-826) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RT WINDOW RING PAN FWD UPPER CORNER STA Y=579-598, Y= 712-731, Y=807-826 AT PAX CABIN STRUCTURE. RING PAN WERE REPAIRED IAW SRM 53-05, FIG 122 AND ERA 487747-14MA, REV ORIG AND 493648-14, MA REV ORIG.

Part: PAN — CRACKED (BS 655-1155) · airframe 62,201 hrs · 45,832 cycles

CRACK ON RT WINDOW RING PAN AFT LOWER CORNER STA Y=655-1155 AT PAX CABIN STRUCTURE. RING PAN WERE REPAIRED IAW SRM 53-05, FIG 122 AND ERA 487747-14MA, REV ORIG, 493648-14MA, REV ORIG.

Part: PAN — CRACKED (BS 1212) · airframe 62,201 hrs · 45,832 cycles

CRACK ON WINDOW RING PAN AFTER UPPER CORNER BS 1212. RING PAN WAS REPAIRED IAW SRM 53-05, FIG 122 AND ERA 487747-14MA, REV ORIG, ERA 493648-14MA, REV ORIG.

Part: PAN — CRACKED (BS 807) · airframe 62,201 hrs · 45,832 cycles

CRACK ON LT WINDOW RING PAN FWD UPPER CORNER BS 807. RING PAN WAS REPAIRED IAW SRM 53-05, FIG 122 AND ERA 487747-14MA, REV ORIG, ERA 4936-48-14MA REV. ORIG.

Part: CUSP WEB — CORRODED (BS 639-660) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LT CUSP WEB BETWEEN BS 639-660 AND X 54 TO X 60. REPLACED.

Part: CUSP WEB — CORRODED (BS 663-680) · corrosion level 2 · airframe 62,201 hrs · 45,832 cycles

CORROSION ON LT CUSP WEB BETWEEN BS 663-680, AND X 54 TO X 60. CUSP WEB REPLACED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 61,710 hrs · 45,510 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE OVERHEAD EMERGENCY LIGHTS AT ROWS 17-20 WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK AND THE OPS CHECKED GOOD.

Part: CABLE — BROKEN (GIRT BAR) · airframe 61,058 hrs · 45,012 cycles

FOUND L1 DOOR SLIDE GIRT BAR CABLE TO BE BROKEN. R & R GIRT BAR LANYARD IAW AMM 25-60.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 60,495 hrs · 44,602 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHTS IN ROWS 18, 24, & 25 INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACKS AND THE OPS CHECKED GOOD.

Part: SKIN — CRACKED (NR 2 SLAT) · airframe 65,179 hrs · 47,921 cycles

CRACK OTBD OF NR 2 SLAT CENTER CUTOUT. NDT END OF CRACK. CRACK APPROXIMATELY 4.25" IN LENGTH. VERIFIED CRACK LENGTH AT 4.0" AND STOP DRILLED IAW ER/A 380953-14MA, REV ORIGINAL STEPS 1 AND 2. C/W ER/A 380953-14MA, REV ORIG STEP 3 CRACK IS CONTAINED. FABRICATED REPAIR PARTS AND INSTALLED TIME LIMITED REPAIR IAW ER/A 380953-14MA, REV ORIGINAL PERMANENT REPAIR DUE AT NEXT HMV. REDEFERRED LOG TO QC, ESTABILISH MONITOR INSPECTION, 00-0557-8-7985, SN 971 L/L SEC I. ASSOCIATED ER/A 00-532432 ADDED FOR AC 0971. TIME LIMITED REPAIR DOUBLER AND REPAIR STRAP WERE REMOVED IAW ER/A 380953-14MA, REV "A". INSPECTION WAS PERFORMED ON PREVIUS STOP DRILL HOLE NO CRACKS FOUND. INSPECTION WAS PERFORMED ON EXISTENT DRILL HOLES NO CRACKS WERE FOUND IAW NDT SPM 06-10-01-003 & ER/A 380953-14MA. AREA WAS IDENTIFIED WITH LOG 5281196 IAW PS 900-5-1, NR 4. THIS MONITOR WAS ATTENDED WITH ERA 532432-4 REV, CLOSED LOG AND REMOVED MONITOR INSP 00-0557-8-7985, SN 00971 L/L.

Part: SKIN — DAMAGED (BS 207-265) · airframe 59,007 hrs · 43,555 cycles

FUSELAGE SKIN DAMAGED, REPAIRED IAW ER/A 473338-14

Part: SKIN — DENTED (BS 207-265) · airframe 59,007 hrs · 43,555 cycles

DENT NOTED 38 INCHES AFT OF THE FWD ENTRY DOOR AT FLOOR LEVEL. REPAIRED IAW ER/A 518965-14, SECT 2.

Part: DOOR — CORRODED (LAV SERVICE) · corrosion level 2 · airframe 58,701 hrs · 43,336 cycles

DURING SCHEDULED INSPECTION, CORROSION WAS NOTED AT THE FWD LAVATORY SERVICE DOOR AREA ON THE LT SIDE OF THE FUSELAGE. CORROSION REPAIRED IAW ER/A 493067-14 AND THE REQUIRED INSPECTION WAS COMPLETED.

Part: FRAME — BENT (TAILCONE) · airframe 58,695 hrs · 43,333 cycles

DURING INSPECTION, TAILCONE L-FRAME WAS NOTED TO BE BENT AT THE 3:00 POSITION BETWEEN THE TAILCONE ALIGNMENT RECEPTICALS. NEW FRAME SECTION INSTALLED IAW SRM 51-01 AND DWG 9911957 AND THE REQUIRED INSPECTION WAS COMPLETED.

Part: VANE — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 58,695 hrs · 43,333 cycles

DURING ROUTINE INSPECTION, THE LT WING OTBD T/E FLAP FIXED VANE WAS NOTED TO HAVE EXFOLLIATION CORROSION ON THE LOWER SURFACE. THE FLAP VANE WAS REPLACED IAW AMM 27-51-03-501 AND THE REQUIRED INSPECTIONS WERE COMPLETED.

Part: FASTENER — LOOSE (VERTICAL STAB) · airframe 58,695 hrs · 43,333 cycles

DURING SCHEDULED INSPECTION, SEVERAL FASTENERS WERE FOUND TO BE LOOSE ON THE LT VERTICAL STABILIZER L/E AT ZFS 52.267. FASTENERS WERE REMOVED, THE HOLES WERE CLEANED AND HOLE MEASUREMENTS WERE FOUND TO BE WITHIN LIMITS. NEW FASTENERS WERE INSTALLED.

Part: PIN — WORN (TAILCONE RELEASE) · airframe 58,695 hrs · 43,333 cycles

DURING SCHEDULED INSPECTION IN MSP, THE TAIL CONE RELEASE CABLE T-PIN WAS NOTED TO BE WORN. THE T-PIN AND ASSOCIATED BUSHINGS WERE REPLACED IAW AMM 53-53, FIG 403 AND THE REQUIRED INSPECTION WAS COMPLETED.

Part: FASTENER — LOOSE (VERTICAL STAB) · airframe 58,695 hrs · 43,333 cycles

DURING SCHEDULED INSPECTION, SEVERAL FASTENERS WERE FOUND TO BE LOOSE ON THE RT VERTICAL STABILIZER L/E AT ZFS 52.267. FASTENERS WERE REMOVED, THE HOLES WERE CLEANED AND HOLE MEASUREMENTS WERE FOUND TO BE WITHIN LIMITS. NEW FASTENERS WERE INSTALLED.

Part: SCOOP — CRACKED (RAM AIR) · airframe 65,179 hrs · 47,921 cycles

RAM AIR SCOOP CRACKED VERT. LT. SIDE. TRANSFERRED STEP 1 FROM PRI 517410-14, REMOVED DAMAGED AREA WITH A 4" X 8.5" X 2" CUTOUT. STEP 2, HFEC COMPLETED. ALL INFO TRANSFERED FROM PRI NR 552071. ACCOMPLISED BNEC IAW SPM06-10-01.003, NO CRACKS QC 2021. TRANSFERED STEP 4 FROM PRI 517410-14 FORM FILLER FROM 6 061-0, .050". HEAT TREAT IAW PS 900-4-1, NR 1 CONDUCTIVITY TEST PERFORMED ON REPAIR FILLER IAW PS 900-4-NR 1 FOUND TO BE 45 PERCENT IACS. REF.PRI 517410-14, REV ORIGINAL. TRANSFERED FROM PRI 517410-14. WELDED REPAIR IAW SRM 55-05, ACCOMPLISHED FPI IAW PSM-900-6-1, 2, NO CRACKS-QC. REDEFERRED LOG TO QC, ESTABILISHED MONITOR INSPECTION 10-0553-8-7369, SN 971, REP SEC I. REPAIR LIMIT TO 4000 FH OR 547 DAYS, RESTRICTION REVISED ACCORDINGLY ASSOCIATED ER/A 00-420329 ADDED FOR AC 0971. DVI WAS PERFORMED AND CRACK WAS FOUND. REPAIR WAS ACCOMPLISHED IAW ER/A 420329-14MA REVISION "C" TIME LIMITED INSTRUCTIONS SRM 55-05, PAR 4. PERFORM REPETITIVE VISUAL INSPECTION WITHIN EVERY "C" CHECK LIMIT, 4000 FLIGHT HOURS OR 547 DAYS IAW ER/A NR 420329-14MA, REV "C" SECTION 1.

Part: BRACKET — WORN (TAILCONE RELEASE) · airframe 58,695 hrs · 43,333 cycles

DURING SCHEDULED INSPECTION IN MSP, THE TAIL CONE EVACUATION KEVLAR CABLE SPRING BRACKETS WERE FOUND TO BE WORN. NEW SPRING BRACKETS WERE INSTALLED AND THE REQUIRED INSPECTION WAS COMPLETED.

Part: RECEPTACLE — WORN (TAILCONE RELEASE) · airframe 58,695 hrs · 43,333 cycles

DURING SCHEDULED INSPECTION, THE TAIL CONE ALIGNMENT PIN RECEPTICALS WERE FOUND TO BE WORN. THE RECEPTICALS WERE REPLACED IAW SRM 51-30 ON THE LT SIDE. THE RT RECEPTICALS WERE REPLACED ON A SEPARATE NON-ROUTINE CARD DUE TO A CORRESPONDING RT FRAME REPLACEMENT. THE REQUIRED INSPECTION WAS COMPLETED.

Part: CLAMP — LOOSE (TAILCONE RELEASE) · airframe 58,695 hrs · 43,333 cycles

DURING SCHEDULED INSPECTION, THE TAIL CONE CABLE CONDUIT CLAMPS WERE FOUND TO BE LOOSE, WORN AND OUT OF POSITION. THE CABLE CONDUIT CLAMPS WERE REPLACED IN THE CORRECT POSITIONS AND THE REQUIRED INSPECTION WAS COMPLETED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 58,331 hrs · 43,083 cycles

DURING LINE CHECK, MX FOUND THAT THE OVERHEAD EMERGENCY PATHWAY LIGHTING AT ROWS 11-15 OF THE CABIN WERE INOPERATIVE. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: LENS — WRONG PART (EMERGENCY LIGHT) · airframe 58,011 hrs · 42,868 cycles

INSPECTOR FOUND AN INCORRECT LENS ON AN EMERGENCY EXIT LIGHT FOR THE OVERWING EXIT - LEFT SIDE. MX REPLACED THE EMERGENCY EXIT LIGHT IAW IPC 33-51 & INSTALLED CONNECTOR IAW AMM 20-50. SYS WAS CHECKED GOOD IAW AMM 33-53.

Part: UNKNOWN — ODOR (CABIN) · airframe 54,446 hrs · 40,387 cycles

FAINT ELECTRICAL SMELL IN GALLEY. DISSIPATED AFTER TURNING OFF GALLEY POWER. FLIGHT CONTINUED TO BDL AND LANDED WITHOUT INCIDENT. FORWARD GALLEY CHECKED OK AT ALL POSITIONS. NO TROUBLE/ODOR FOUND.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 53,852 hrs · 39,959 cycles

DURING LINE CHECK MAINTENANCE FOUND OVERHEAD EMERGENCY LIGHTS INOPERATIVE OVER SEATS 17-19. MAINTENANCE REPLACED BATTERY FROM BATTERY PACK. OPERATION OF LIGHTS NOW CHECKS OK.

Part: DISPLAY — FAULTY (COCKPIT) · airframe 53,291 hrs · 39,586 cycles

ELECTRICAL FUMES SMELL IN COCKPIT AT CRUISE ALTITUDE WITH WEATHER RADAR DISPLAY INOPERATIVE AT SAME TIME. MAINTENANCE FOUND PIN 30 ON WEATHER RADAR DISPLAY BURNED IN HALF AND ELECTRICAL SMELL ORIGINATING FROM THE DISPLAY. REPLACED WEATHER RADAR DISPLAY AND PERFORMED OP 5088.

Part: SKIN — CORRODED (FUSELAGE) · airframe 53,145 hrs · 39,489 cycles

DURING PSV VISIT IN MSP, MTC NOTED CORROSION COMMON TO THE INTERNAL DOUBLER SURROUNDING THE FWD LAV SERVICE PANEL AT STA 287, S-21L. REPAIRED PER ER/A 493067-14 REV 2.

Part: SKIN — CRACKED (FUSELAGE) · airframe 53,145 hrs · 39,489 cycles

THE UPPER FUSELAGE SKIN AT STATION 1418 OTBD OF LONGERON 2R WAS FOUND TO BE CRACKED. REPAIRED AREA PER ER/A 493101-14.

Part: LIGHT — INOPERATIVE (SEAT 24D) · airframe 52,546 hrs · 39,089 cycles

DURING LINE CHECK MX, FOUND EMERGENCY LIGHT AT 24D INOPERATIVE. MX REPLACED THE LAMINATOR AND OPERATION OF THE LIGHT NOW CHECKS OK.

Part: CABIN PRESSURE — MALFUNCTIONED (CABIN) · airframe 49,071 hrs · 36,730 cycles

AIRCRAFT WILL NOT PRESSURIZE. MTC IN PROGRESS. INSP 2L GALLEY DOOR SEAL, CHECKS GOOD. INSP ALL A/C DOOR SEALS, ALL OK, PSI A/C TO 6 PSI. CHECKED ALL DOORS FOR LEAKS, ALL OK. INSP PNU DUCTS AFT TAIL COMPT FOR LEAKS, CHECK OK. INSP OUTFLOW VALVE FOR OBSTRUCTIONS AND OPS RAN FULL OPEN/CLOSE CHECK OK. A/C OK FOR SERVICE.

Part: OIL SYSTEM — LEAKING (APU) · airframe 47,872 hrs · 35,962 cycles

DURING CLIMB-OUT LAVATORY SMOKE DETECTORS HEARD, ODOR AND HAZE NOTED IN CABIN. FOUND OIL FROM APU LEAKING INTO INTAKE. REMOVED AND REPLACED APU PER AMM 49-10-00.

Part: VANE — DAMAGED (WING) · airframe 47,872 hrs · 35,961 cycles

LT WING OTBD FLAP IB FIXED VANE HAD 2 GOUGES TO THE SKIN AND PENETRATED INTO THE INTERNAL DOUBLER. DAMAGE WAS NEAR XV1=211 AT THE AFT INBOARD CORNER. DAMAGE WAS CLEANED UP AND AN SRM 51-70-2 PARAGRAPH 18B HOT BOND REPAIR WAS INSTALLED. REPAIR WAS PERMANENT.

Part: VANE — DAMAGED (L WING OB FLAP) · airframe 47,872 hrs · 35,961 cycles

LT WING OTBD FLAP VANE AFT INBD CORNER OF SKIN HAD A GOUGE PENETRATING INTO THE INTERNAL DOUBLER. A SRM 51-70-2 PAR 18B HOT BOND REPAIR WAS INSTALLED THAT EXTENDED AROUND THE VANE LEADING EDGE. THIS REPAIR WAS APPROVED BY BOEING.

Part: FRAME — CRACKED (BS 1485) · airframe 47,872 hrs · 35,961 cycles

THE FUSELAGE STATION 1485 BULKHEAD RT FRAME INBD TERMINATING END AT X=-17.5 WAS FOUND CRACKED IN THE TYPICAL LOCATION. A PREVIOUS REPAIR NECESSITATED AN EXPANDED REPAIR ANGLE MAKE FROM 0.032" TI-6AL-4V PER BOEING APPROVED DATA.

Part: STRAP — CORRODED (FS 1212) · airframe 47,872 hrs · 35,961 cycles

THE AFT CARGO DOOR LOWER JAMB MAIN FRAME STRAP AT FS 1212 WAS CORRODED IN SEVERAL LOCATIONS. A 0.063 INCH 7075-T6 REPAIR STRAP WAS INSTALLED OVER SEVERAL BLENDS ON THE LOWER END. THE UPPER PART OF THE PRODUCTION STRAP WAS SPLICED WITH 0.25 INCH 7075-T6 MATERIAL.

Part: SKIN — WORN (FS 1019) · airframe 47,872 hrs · 35,961 cycles

THE CROWN SKIN AT FS 1019 HAD ELONGATED NUTPLATE HOLES BETWEEN L-1 AND L-2R. DAMAGE WAS CUTOUT TO A 1 INCH HOLE DIAMETER. A 0.063 INCH REPAIR DOUBLER AND TRIPLER, WITH AN 0.100 INCH STRUCTURAL SHIM WAS INSTALLED.

Part: ACCESS PANEL — CORRODED (LT WING UPPER) · airframe 47,872 hrs · 35,961 cycles

ACCESS PANEL 1303C CORRODED.

Part: SKIN — DAMAGED (FS 204) · airframe 47,872 hrs · 35,961 cycles

SKIN AND R1 DOOR DOUBLER TRIMMED OUT 3 BY 2 INCHES AT FS 204 BETWEEN L-17R AND L-18R. THE SKIN WAS SPLICED BETWEEN L-16R AND L-17R. THE DOOR DOUBLER WAS REPAIRED LOCALLY WITHIN INTERNAL REPAIR DOUBLER.

Part: CUSP WEB — CORRODED (BS 1174-1250) · airframe 47,872 hrs · 35,961 cycles

CUSP MEMBRANE CORRODED/PREVIOUS REPAIRS STA 1174-1250 RT SIDE. REPLACED CUSP MEMBRANE STA 1174-1250 RT SIDE PER SRM 51-30-01/51-30-04 ON ATS CARD 01466.

Part: FRAME — CRACKED (BS 1174 L6L) · airframe 47,872 hrs · 35,961 cycles

CRACKED FRAME AT STA1174 AND LONG 6 LEFT. REPAIRED PER ERA 473063-14 ON ATS CARD 00538.

Part: ACCESS PANEL — CORRODED (LT WING) · airframe 47,872 hrs · 35,961 cycles

FLANGE CORRODED ON LEFT WING LWR FUEL TANK ACCESS PANEL 1379C. REPLACED PANEL ON ATS CARD 01720.

Part: WEB — CORRODED (BS 1165) · airframe 47,872 hrs · 35,961 cycles

LOWER SILL WEB CORRODED STA 1165. REPLACED PER SRM 51-30-02/DRW NR 9930612 ON ATS CARD 01377.

Part: SKIN — CRACKED (EMPENNAGE) · airframe 47,872 hrs · 35,961 cycles

3/4 INCH CRACK IN EMPENNAGE SKIN 8 IN AFT OF ELEV ACCUM ACCESS DOOR. REPAIRED PER ER 09-1190 AND ERA 471520-14 ON ATS CARD 00229.

Part: BEAM — CORRODED (BS 598) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON C2 CARGO DOOR THRESHOLD BEAM STA693 X=+20. REPLACED PER SRM 51-30-05 ON ATS CARD 00450

Part: SKIN — CORRODED (FUSELAGE) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON LWR SILL OF AFT CARGO DOOR CUTOUT BETWEEN SKIN AND SILL LIP. REMOVED CORROSION AND INSTALLED DOUBLER PER ERA 422907-14 AND ER 09-1352 ON ATS CARD 01552.

Part: ACCESS PANEL — CORRODED (LT WING) · airframe 47,872 hrs · 35,961 cycles

FLANGE CORRODED ON FUEL TANK ACCESS PANEL 1363C LT LWR WING. REPLACED PANEL ON ATS CARD 01721.

Part: CUSP WEB — CRACKED (BS 905) · airframe 47,872 hrs · 35,961 cycles

CUSP MEMBRANE CRACKED STA905 X -54 Z=0. REPAIRED PER ERA 472901-14 ON ATS CARD 01375.

Part: SUPPORT BEAM — CRACKED (BS 1494) · airframe 47,872 hrs · 35,961 cycles

SUPPORT BEAM CRACKED AFT SIDE OF AIR STAIR CUTOUT, STA 1494. REPAIRED PER SRM 51-30-02 ON ATS CARD 01481.

Part: SKIN — GOUGED (BS 1172 L19L) · airframe 47,872 hrs · 35,961 cycles

FUSELAGE SKIN GOUGED STA 1172 3IN BELOW LONGERON 19L. INSTALLED DOUBLER PER ER09-1192 AND ERA 471514-14 ON ATS CARD 00146.

Part: FAIRING — CRACKED (HORIZONTAL STAB) · airframe 47,872 hrs · 35,961 cycles

RT LWR HORIZ STAB FAIRING CRACKED MIDDLE LWR SIDE. REPAIRED PER SRM 55-01 ON ATS CARD 01845.

Part: FITTING — CORRODED (R1 DOOR GIRT BAR) · airframe 47,872 hrs · 35,961 cycles

GIRT BAR FITTING CORRODED R1 DOOR. REPLACED FITTING PER SRM53-05/51-10-04 ON ATS CARD 01835.

Part: SPLICE — CORRODED (BS 1211-1231) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON CARGO TRACK AND SPLICE FLANGES BETWEEN STA 1211 AND 1231 X-16 Z-44. REPAIRED PER SRM 51-10-02 ON ATS CARD 01053.

Part: CUSP WEB — DAMAGED (BS 1098-1174) · airframe 47,872 hrs · 35,961 cycles

CUSP MEMBRANE DAMAGED/PREVIOUS REPAIRS STA 1098-1174 RT. REPLACED CUSP MEMBRANE STA 1098-1174 PER SRM 51-30-01/51-30-04 ON ATS CARD 01465.

Part: DOUBLER — CORRODED (BS 1194) · airframe 47,872 hrs · 35,961 cycles

THE AFT CARGO LWR THRESHOLD DOOR SURROUND DOUBLER HAD CORROSION ALONG THE UPPER EDGE. THE SKIN WAS BLENDED TO 0.023 INCH AT FS 1194 AND WAS TRIMMED OUT. THE SKIN WAS BLENDED TO 0.044 INCH AT FS 1175 AND WAS LEFT AS IS. A REPAIR DOUBLER WAS INSTALLED FROM 1169 TO 1199 FOR BOTH DAMAGE LOCATIONS.

Part: ACCESS PANEL — CORRODED (LT WING) · airframe 47,872 hrs · 35,961 cycles

ACCESS PANEL CORRODED ON FLANGE.

Part: ACCESS PANEL — CORRODED (LT WING) · airframe 47,872 hrs · 35,961 cycles

ACCESS PANEL FLANGE CORRODED.

Part: FITTING — CORRODED (MLG) · airframe 47,872 hrs · 35,961 cycles

THE LT AND RT MLG SUPPORT FITTING BORES WERE CORRODED. THE INBD BORE DIAMETERS EXCEEDED THE LIMITS OF AD 2004-25-14. PER BAC RECOMMENDATION AND AN FAA AMOC APPROVAL LETTER, THE BORES WERE BORED OVERSIZE, AND OVERSIZED BUSHINGS WERE INSTALLED, OTHERWISE PER THE AD REQUIREMENTS.

Part: CUSP WEB — CORRODED (BS 1174-1212) · airframe 47,872 hrs · 35,961 cycles

THE FUSELAGE CABIN FLOOR LT CUSP WEB WAS CORRODED BETWEEN FS 1174 AND 1212. THE CORROSION WAS TRIMMED OUT AND A REPAIR DOUBLER WAS INSTALLED.

Part: BEAM — DAMAGED (DOOR FRAME) · airframe 47,872 hrs · 35,961 cycles

DURING HMV, THE AFT CARGO DOOR JAMB BEAM WAS CORRODED AND HAD TO BE REPLACED. THE REPLACEMENT BEAM WAS DAMAGED IN SHIPPING. A BOEING-APPROVED REPAIR WAS MADE TO THE REPLACEMENT BEAM TO MAKE IT STRUCTURALLY ACCEPTABLE.

Part: FRAME — CRACKED (BS 1174 L6L) · airframe 47,872 hrs · 35,961 cycles

FS 1174 FRAME TO EACH SIDE OF LONGERON 6L WAS FOUND CRACKED IN 2 PLACES, APPROXIMATELY 1.5 INCH EACH. THE DAMAGE WAS TRIMMED OUT AND A REPAIR ANGLE WAS INSTALLED.

Part: BULKHEAD — CORRODED (BS 1348) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON PRESSURE BULKHEAD WEB DOUBLER STA 1348, +1X, -40Z. REPLACED DOUBLER PER SRM 51-30-01/51-10-03 ON ATS CARD 00771.

Part: CUSP WEB — CORRODED (BS 655-674) · airframe 47,872 hrs · 35,961 cycles

DURING HMV AT PAE, AN EXISTING REPAIR OF THE SUBFLOOR CUSP WEB WAS FOUND WITH ADDITIONAL CORROSION DAMAGE. THE REPAIR WAS REMOVED AND A MORE EXTENSIVE REPAIR WAS INSTALLED PER BOEING REPAIR INSTRUCTIONS.

Part: SUPPORT — CRACKED (BS 522 L23L) · airframe 47,872 hrs · 35,961 cycles

CRACKED RADIUS ON SUPPORT STA 522 LONGERON 23 LEFT MID CARGO COMPARTMENT FWD BULKHEAD. REPLACED SUPPORT PER SRM 51-10-02/51-30-02 ON ATS CARD 00368.

Part: SKIN — GOUGED (BS 1172 S19L) · airframe 47,872 hrs · 35,961 cycles

DURING HMV AT PAE, A GOUGE WAS FOUND IN THE FUSELAGE SKIN AT STA 1172 BELOW S-19L. THE GOUGE WAS CUT OUT AND REPAIRED PER BOEING REPAIR INSTRUCTIONS.

Part: INTERCOSTAL — CORRODED (BS 1309-1319) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON INTERCOSTAL AT NUTPLATE HOLES STA 1309-1319 BETWEEN LONGERON 27L-28L. REPLACED INTERCOSTAL PER SRM 51-30-02 ON ATS CARD 01702.

Part: KEELBEAM — CRACKED (BS 946) · airframe 47,872 hrs · 35,961 cycles

SUPPORT CORRODED IN KEEL BEAM AT STATION 946 BETWEEN LANDING GEAR DOOR ACTUATOR AND KEEL BEAM. REPAIRED BY REPLACEMENT ON STA NR 00512.

Part: ANGLE — CRACKED (BS 1418) · airframe 47,872 hrs · 35,961 cycles

ANGLE CRACKED AT STATION 1418 AT LONGERON 2R. REPAIRED BY REPLACEMENT ON ATS NR 01726.

Part: CUSP WEB — CORRODED (BS 826) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON MAIN CABIN FLOOR CUSP AT STATION 826 Z=0X=-62. REPAIRED BY REPLACEMENT ON ATS NR 06144.

Part: FLOORBEAM — CORRODED (BS 1155) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON FLOOR SUPPORT STATION 1155 +13 -5X -44Z IN AFT CARGO. REPAIRED BY REPLACEMENT ON ATS 00426.

Part: WEB — CORRODED (BS 212) · airframe 47,872 hrs · 35,961 cycles

CORROSION WEB AT STATION 212, X=46, Y=0. REPAIRED PER ATS ER09-1297 AND ERA 473067-14 REV ORG ON ATS 01438.

Part: INTERCOSTAL — CORRODED (BS 1136) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON INTERCOSTAL AT STA 1136 AT LONGERON 28R TO 29R. REPAIRED BY REPLACEMENT ON ATS 01553.

Part: FLOORBEAM — CORRODED (BS 946) · airframe 47,872 hrs · 35,961 cycles

FLOOR SUPPORT CORRODED AT STATION 946, X=+19 Z=0. REPAIRED BY REPLACEMENT ON ATS NR 01151.

Part: ANGLE — CORRODED (LT MLG DOOR) · airframe 47,872 hrs · 35,961 cycles

LEFT MAIN LANDING GEAR DOOR BODY ZEE ANGLE CRACKED AT FWD UPPER OUTBOARD END. REPAIRED BY REPLACEMENT IAW 51-30-2 ON ATS NR 00354.

Part: ANGLE — CORRODED (BS 1494) · airframe 47,872 hrs · 35,961 cycles

CAP ANGLE CORRODED AT STATION 1494 X=28. REPAIRED BY REPLACEMENT ON ATS NR 01656.

Part: SUPPORT — CORRODED (BS 1645) · airframe 47,872 hrs · 35,961 cycles

SUPPORT CORRODED AT BS 1645 RBL 56. REPAIRED BY REPLACEMENT ON NRC 01545.

Part: PRESSURE PANEL — CRACKED (NLG WW) · airframe 47,872 hrs · 35,961 cycles

FOUND HORIZONTAL WEB AT BOTTOM OF CLIPS TO BE CRACKED IN BOTH LEFT AND RIGHT CORNERS ON AFT SIDE OF FWD NOSE WHEEL WELL BULKHEAD. REMOVED AND REPLACED HORIZONTAL WEB.

Part: BRACKET — CORRODED (GIRT BAR) · airframe 47,872 hrs · 35,961 cycles

AFT SERVICE DOOR GRIT BAR FITTING BRACKET CORRODED. INSTALLED NEW BRACKET ON AFT GRIT BAR FITTING ON ATS 01366.

Part: SEAT TRACK — CORRODED (BS 788-1030) · airframe 47,872 hrs · 35,961 cycles

SEAT TRACK CORRODED AT STATION 788 TO STATION 1030 AT RIGHT OUTBOARD TRACK. REPLACED ON ATS 00924.

Part: FLOORBEAM — CORRODED (BS 427) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON FLOORBEAM AT BS 427, LONGERON 27L TO 27 R. REPAIRED BY REPLACEMENT ON ATS 01078.

Part: FINGER DOUBLER — DAMAGED (BS 1309 L18R) · airframe 47,872 hrs · 35,961 cycles

FINGER DOUBLER ON PREVIOUS REPAIR CORRODED AND OUT SIDE OF REPAIR DAMAGED AT STATION 1309 RT LONGERON 18. REPAIRED BY REPLACING REPAIR. INSTALLED REPAIR PER 53-04 FIG 12B.

Part: SEAT TRACK — CORRODED (BS 1174-1309) · airframe 47,872 hrs · 35,961 cycles

FOUND BS 1174-1309 SEAT TRACK CORRODED. REPLACEMENTON NR 00928.

Part: FRAME — CRACKED (BS 927) · airframe 47,872 hrs · 35,961 cycles

FOUND CRACK AT FRAME 927 AT X=+65. REPLACED FRAME ON NR 01124.

Part: BRACKET — CORRODED (FUSELAGE) · airframe 47,872 hrs · 35,961 cycles

CORROSION FWD CABIN FLOOR STRUCTURE AT STA 179 ON FLOOR SUPPORT BRACKET. REMOVED, FABRICATED AND INSTALLED NEW BRACKET PER SRM 51-30-5 AND SRM 51-10-4.

Part: ANGLE — CRACKED (NOSE W/W) · airframe 47,872 hrs · 35,961 cycles

STA Y=75.5 CRACKED UPPER FASTENER HOLES. REMOVED ANGLE, FABRICATED AND INSTALLED NEW ANGLE IAW DWG 9910088 AND SRM 51-101.

Part: LONGERON — CORRODED (AFT CARGO) · airframe 47,872 hrs · 35,961 cycles

AFT CARGO BAY LONGERON 22LT CORRODED FROM Y1271 TO Y1320. REMOVED CORRODED SECTION OF LONGERON AND SPLICED IN NEW LONGERON IAW SRM 53-02, SRM 51-10-04, SRM 51-30-01.

Part: CUSP WEB — CORRODED (BS 1203) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON CUSP MEMBRANE AT STA 1203. REMOVED CORROSION AND FOUND OUT OF LIMITS. EXISTING REPAIR IN AREA CAUSED REPLACEMENT OF CUSP. DISCREPANCY NOTED ON ATS NR 01178 AND REPLACEMENT OF CUSP ON ATS NR 01466.

Part: CUSP WEB — CORRODED (BS 598-579) · airframe 47,872 hrs · 35,961 cycles

MAIN CABIN FLOOR LT SIDE WEB BETWEEN STA 598 AND 579 CORRODED. REMOVED DAMAGED AREA AND REPAIRED PER DRD 53-05D.

Part: SUPPORT FITTING — CRACKED (BS 946) · airframe 47,872 hrs · 35,961 cycles

SUPPORT FITTING BETWEEN LANDING GEAR DOOR ACTUATOR AND KEEL BEAM SUPPORT FITTING CRACKED AT STA 946 RT. REMOVED AND REPLACED FITTING PER SRM 51-30-5.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,872 hrs · 35,961 cycles

MID CARGO BAY FLOOR SUPPORT AT STA 693 IS CORRODED AROUND NUT CLIP HOLES. REMOVED AND REPLACED FLOOR SUPPORT PER SRM 51-30-02.

Part: ANGLE — CRACKED (BS 1429) · airframe 47,872 hrs · 35,961 cycles

ANGLE CRACKED AT STA 1429 LONGERON 5L. REMOVED AND REPLACED CRACKED ANGLE IAW SRM 51-30-5

Part: SUPPORT — CRACKED (AFT CARGO) · airframe 47,872 hrs · 35,961 cycles

BULKHEAD LINER SUPPORT CRACKED AT X-31, Y-1003. REMOVED DAMAGED SUPPORT, FABRICATED AND INTALLED NEW SUPPORT IAW SRM 51-30-2, SRM 51-10-2 ON ATS NRC 00970.

Part: STRUCTURE — CORRODED (BS 1380) · airframe 47,872 hrs · 35,961 cycles

CORROSION AFT OF APU COMP AFT SIDE OF STA 1380. REMOVED AND REPLACED 1380 CHORD IAW SRM 51-30-05 ON ATS NR 01385.

Part: BRACKET — CORRODED (GIRT BAR) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON AFT SERVICE DOOR FWD GIRT BAR FITTING BRACKET, REMOVED AND REPLACED GIRT BAR FITTING BRACKET IAW DWG 9930612 AND SRM 51-10-4 ON ATS NR 01390.

Part: FLOORBEAM — CORRODED (BS 256) · airframe 47,872 hrs · 35,961 cycles

CORROSION FWD CABIN FLOOR STRUCTURE STA 256. REMOVED DAMAGED FLOOR STRUCTURE, FABRICATED AND INSTALLED NEW FLOOR SUPPORT STRUCTURE IAW SRM 51-30-05.

Part: SEAT TRACK — CORRODED (BS 788) · airframe 47,872 hrs · 35,961 cycles

LT INBD SEAT TRACK HAS SEVERAL AREAS OF GOUGING AND CORROSION FROM FACTORY SPLICE STA 788 TO FACTORY SPLICE 1030. REMOVED AND REPLACED SEAT TRACK SECTION PER SRM 51-30-01.

Part: CUSP WEB — CORRODED (FS 655-674) · airframe 47,872 hrs · 35,961 cycles

PREVIOUS REPAIR CORRODED FS 655-674 CUSP WEB, RT SIDE ABOVE MID CARGO DOOR. REPAIRED PER ER/A 471521-14.

Part: FRAME — CORRODED (BS 427 L26R) · airframe 47,872 hrs · 35,961 cycles

CORROSION AT FWD CARGO DOORWAY FRAME BS 427 AND LONGERON 26 RT. DISCREPANCY NOTED ON ATS NR 00999 AND FRAME REPLACED ON ATS NR 00198.

Part: GUSSET — CORRODED (BS 598) · airframe 47,872 hrs · 35,961 cycles

MID CARGO DOORWAY LINER SILL GUSSET AT STA 598 CORRODED. REMOVED, FABRICATED AND INSTALLED NEW GUSSETT PER DRAWING 2913044.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,872 hrs · 35,961 cycles

FOUND CORROSION OF FWD CABIN FLOOR SUPPORT STA 179. REPAIRED BY REPLACEMENT IAW SRM 51-30-02.

Part: FRAME — CORRODED (BS 1250 L27-30L) · airframe 47,872 hrs · 35,961 cycles

AFT CARGO FRAME STA 1250 CORRODED ON BACK SIDE BETWEEN LONGERON 27L AND 30. REMOVED CORROSION AND REPAIRED FRAME IAW SRM 53.

Part: FRAME — CORRODED (BS 1098) · airframe 47,872 hrs · 35,961 cycles

FRAME AT STA 1098 CORRODED. REMOVED AND REPLACED LOWER FLANGE OF FRAME.

Part: CUSP WEB — CRACKED (BS 220) · airframe 47,872 hrs · 35,961 cycles

CUSP MEMBRANE CRACKED AT STA 220. REPAIRED BE REPLACEMENT PER SRM 51-30-02.

Part: CUSP WEB — CORRODED (BS 1053) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON CUSP WEB AT STA 1053. REPAIRED ON ATS NR 1470.

Part: CUSP WEB — CORRODED (BS 1094) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON CUSP MEMBRANE AT STA 1094. REPAIRED ON ATS NRC 1477.

Part: CUSP WEB — CORRODED (BS 1032-1098) · airframe 47,872 hrs · 35,961 cycles

CUSP MEMBRANE DAMAGED DUE TO SEVERAL CORRODED AREAS. REPAIRED ON ATS NRC 1477.

Part: CUSP WEB — CORRODED (FS 997) · airframe 47,872 hrs · 35,961 cycles

CUSP MEMBRANE CORRODED AT FS 997 X-62 Z-0. REPAIRED IAW DRD 53-05D.

Part: CUSP WEB — CRACKED (FS 905) · airframe 47,872 hrs · 35,961 cycles

CUSP MEMBRANE CRACKED AT STA 905 REPAIRED PER ER/A 472901-14.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,872 hrs · 35,961 cycles

CORROSION FWD CABIN FLOOR SUPPORT BRACKET AT STA 169 TO 200. REPAIRED BY REPLACEMENT PER SRM 51-30-2.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 47,872 hrs · 35,961 cycles

TANK ACCESS PLATE CORRODED AT FASTENER HOLE.

Part: FRAME — CRACKED (FS 886) · airframe 47,872 hrs · 35,961 cycles

MAIN CABIN RIGHT SIDE OVERWING FRAME CRACKED AT FLOOR LEVEL FS 886. REPLACED FRAME IAW EA 09-460094-12AD.

Part: FRAME — CORRODED (FS 1098) · airframe 47,872 hrs · 35,961 cycles

CORROSION ON FRAME FS 1098, LONGERON 30. REPAIRED BY REPLACING IAW SRM 51-30-03, 51-30-05.

Part: FRAME — CORRODED (FS 788) · airframe 47,872 hrs · 35,961 cycles

FRAME CORRODED AT FS 788.

Part: FRAME — CRACKED (BS 1463) · airframe 47,101 hrs · 35,428 cycles

FUSELAGE STA 1463 CANTED FRAME OUTER CHORD FOUND CRACKED OUTBOARD OF L2L AND L2R AND BETWEEN L13R AND 14R. INNER SKIN DOUBLERS ALSO FOUND CRACKED ON BOTH SIDES OF BULKHEAD. INNER SKIN PANEL WEB FOUND CRACKED. INNER SKIN PANEL WEB AND BOTH SKIN DOUBLERS WERE REPLACED. CRACKED CHORD SECTIONS WERE CUTOUT AND REPAIR STRAPS WERE INSTALLED.

Part: BALLAST — BURNED OUT (CABIN LIGHTS) · airframe 46,088 hrs · 34,857 cycles

FLIGHT ATTENDANT REPORTED SMELLING SMOKE IN THE MID CABIN. OVERHEAD LIGHT AT 20ABC FLICKERED THEN WENT OUT FOLLOWED BY ODOR. DISCOVERED BALLAST AT 20ABC HOT. PULLED AND COLLARED C/B FOR LT O/H LIGHTS. C/W OPN 5088. FWD LIGHT TO MCO/PLAC PER MEL 33-00-02. REPLACED BALLAST CKS, OK MCO/PLAC REMOVED.

Part: TARGET — MISSING (LT MLG DOOR) · airframe 40,904 hrs · 31,396 cycles

GEAR DOOR OPEN LIGHT REMAINED ILLUMINATED WITH GEAR HANDLE DOWN AND 3 GREEN DOWNLOCK LIGHTS ILLUMINATED. REPLACED MISSING PROX TARGET.

Part: PRESSURE PANEL — LEAKING (LT MLG WW) · airframe 38,589 hrs · 29,730 cycles

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

Part: SLIDE — UNSERVICEABLE (L2) · airframe 36,977 hrs · 28,603 cycles

L2 DOOR SLIDE FELL OUT OF DOOR PACK AND LANYARD PULLED FROM BUSSLE PACK. REPLACED SLIDE PACK L2 DOOR.

Part: ODOR — DETECTED (GALLEY) · airframe 36,726 hrs · 28,419 cycles

ELECTRICAL ODOR REPORTED IN COCKPIT/CABIN DIDN'T DISPERSE BY SHUTTING OFF GALLEY POWER OR CABIN LIGHTS. ODOR DISSIPATED AFTER 10 MIN, ACFT DIVERTED TO IND. PERFORMED DUCT BURNOUT PROCEDURE AND INSPECTED/RAN AIRCRAFT SYSTEMS. UNABLE TO DUPLICATE.

Part: STARTER — FAILED (APU) · airframe 35,933 hrs · 27,861 cycles

ELECTRICAL ODOR THROUGHOUT AIRCRAFT. REPLACED APU.

Part: REDUCER — LEAKING (NR 1 ENGINE) · airframe 31,358 hrs · 24,682 cycles

LEFT HYD WENT TO ZERO LEFT HYD PRESS FAIL. LEFT REVERSER CONTROL VALVE LEAKING AT LOWER OUTBOARD B/NUT. REPLACED REDUCER AND O-RING, RESECURED HYD LINE. NO FLUID CONTAMINATION IN APU INLET. CLEANED TAIL COMPT OF RESIDUAL FULID, LEAK CHECKS GOOD.

Part: HYDRAULIC LINE — LOOSE (HYD SYSTEM) · airframe 31,107 hrs · 24,493 cycles

RETURNED ACFT TO GATE DUE TO SMOKE INSIDE CABIN AND COCKPIT. FOUND LOOSE HYDRAULIC LINE ON THRUST REVERSER CONTROL VALVE. TIGHTENED SAME, PERFORMED DUCT BURNOUT.

Part: STRUT — LEAKING (NLG) · airframe 28,338 hrs · 22,442 cycles

AFTER TAKEOFF GEAR UNSAFE LIGHT ILLUMINATED (RED NOSE GEAR LIGHT). FOUND NOSE STRUT HAD LEAKED DOWN. REPACKED AND SERVICED STRUT.

Part: VALVE — UNSERVICEABLE (NOSE GEAR) · airframe 27,830 hrs · 22,069 cycles

NOSE GEAR UNSAFE UP INDICATION AFTER TAKEOFF. CYCLED GEAR STILL UNSAFE UP INDICATED. MUCH NOISE FROM NOSE GEAR WHEEL WELL INDICATING DOORS STILL OPEN. GEAR EXTENDED NORMALLY WITH ALL DAWN AND GEAR DOORS CLOSED. AUTO GROUND SPIOLERS INOP LIGHT ON OAP. NORMAL LANDING./// JACKED A/C SWUNG NOSE GEAR. FOUND NOSE GEAR SCHRADER VALVE DEFFECTIVE R/R VLV SERVICED NOSE STRUT PER M/M SWUNG NOSE GEAR UP & LOCKED CK PROX BOX INDUCATION NML LOWER GEAR CK PROX BOX CK GD. A/C OK FOR SERVICE.

Part: ENGINE — FAILED (NR 2) · airframe 27,491 hrs · 21,823 cycles

RIGHT ENGINE HAD NO EGT RISE USING NORMAL START. RAN ENGINE >20SEC THEN TRIED START W/BOTH IGNITIONS. HAD RAPID EGT RISE TO 510 C MOMENTARILY. STOPPED START AGAIN. TOWER MENTIONED FLAMES ON SECOND START ATTEMPED. EMERGENCY EQUIP SUMMONED. FIRE MARSHALL DIRECTED US TO FIRE AIRCRAFT HALON BOTTLE. GROUND FIRE CREW ALSO USED HALON. RETURNED TO GATE. REPLACED NR 2 FIRE BOTTLE IAW M/M. INSPECTED ENG VISUAL ENGINE START RUN NORMAL, REF M/M 72-00-00-05.

Part: CHIP DETECTOR — LEAKING (APU) · airframe 26,374 hrs · 20,973 cycles

AFTER TAKEOFF AT ELP BOTH AFT LAV SMOKE DETECTORS WENT OFF. FLIGHT ATTENDANT REPORTED UNIDENTIFIABLE SMELL. OPENED LAV DOORS AND ALARM SILENCED AFTER 1 TO 2 MINUTES. FOUND APU CHIP DETECTOR O-RING LEAKING. REPLACED SAME AND PERFORMED DUCT BURNOUT.

Part: GENERATOR — FAILED (NR 2 ENGINE)

RT ENG CSD EXCEEDED HI TEMP LIMITS. DISCONNECTED IN FLT. ELECT SMOKE OR FUMES REPORTED IN AFT CABIN. REPLACED CSD AND GENERATOR.

Part: LINE — LOOSE (LT TR ISO VALVE)

ON CLIMBOUT, HOT BURNED AIR SMELL CAME IN COCKPIT AND CABIN W/ ENG ANTI-ICE IN USE. F/A REPORTED THIN MIST/SMOKE INAFT CABIN AND SMOKE ALARM ACTIVATION IN AFT LAV. SMELL DISIPATED, SMOKE CLEARED AND SMOKE ALARM STOPPED WHEN ENG ANTI-ICE SECURED. FOUND LEFT THRUST REV ISOLATION VLV RETURN LINE LEAKING TIGHTENED B-NUT, LK CK GOOD. CLEANED TAIL COMP, RAN ENG TO T/O PWR WITH PACKS ON. NO FUMES OR SMOKE NOTED WITH ENG ANTI-ICE ON.

Part: TIRE — FAILED (NR 1 MLG)

BETWEEN VR AND V2 EXPERIENCED POPPING NOISES AND AIRFRAME SHUDDER. CONTINUED T/O AND NO 1 ENG ROLLED BACK TO 1.3 EPR AND OTHER GAUGES FLUCTUATED AS COMPRESSOR STALLS CONTINUED. ON RETURN MTC FOUND NR 1 MAIN TIRE CAME APART AND CAUSED SEVERE FOD DAMAGE TO NR 1 ENG AND DAMAGE TO LT I/B FLAP. REPLACED TIRES, NR 1 ENG. REPAIRED FLAP AND OTHER MINOR DAMAGE.

Part: SKIN — DENTED (BS 237)

THE FUSELAGE SKIN WAS FOUND TO HAVE A DENT AT FS 237 BETWEEN STRINGERS 18L AND 20L. THE DENT WAS CUT OUT WITH DIMENSIONS OF 9 FWD /AFT BY 12.75 UP/DOWN. THE SKIN IN THIS AREA IS MANUFACTURED FROM 0.050 CLAD 2024-T3 SHEET. (1) 0.063 2024-T3 CLAD SHT EXTERNAL DOUBLER; INTERNAL FINGER DOUBLERS; (1) 0.050 2024-T3 CLAD SHT SKIN FILLER.

Part: SKIN — GOUGED (BS 1303)

THE FUSELAGE SKIN AT FS 1303 AND STR 19R WAS FOUND GOUGED AND CLEANED UP OUT OF LIMITS. THE SKIN WAS CUT OUT MEASUREING 1.5 UP/DOWN BY .75 FWD / AFT. THE SKIN IN THIS AREA IS MANUFACTURED FROM 0.063 2024-T3. FABRICATE 1 0.071 2024-T3 CLAD DOUBLER (EXTERNAL), FABRICATED FINGER DOUBLERS FOR THE LOWER SIDE.

Part: SKIN — CORROSION (FS 759)

CORROSION WAS FOUND UNDER THE RIGHT RUB STRIP IN SEVERAL LOCATIONS BETWEEN 759 TO 807, BETWEEN STR 27R AND 29R. THE RUB STRIP IS LOCATED WHERE THE WING TO BODY FAIRING MEETS THE FUSELAGE. THE SKIN IS MANUFACTURED FROM 0.160 7075-T76 CLAD SHT AT FS 817 AND TAPERS DOWN TO 0.080 AT FS 759. INSTALLED TWO 0.063 7075-T6 CLAD REPAIR DOUBLERS.

Part: FRAME — CRACKED (BS 1418)

MAINTENANCE FOUND A 1.5 INCH CRACK AT FS 1418, L-2R AT THE TYPICAL LOCATIONS COVERED BY EO 9-63538-03. THE A/C COVERED IN THIS ER/A IS NOT COVERED BY THE REFERENCE EO (A/C 901-963), BUT AS A REPAIR AND PREVENTION OF FUTURE FATIGUE, THE EO WOULD BE PERFORMED ON THIS A/C. PERFORM EO 9-63538-03, OPN 0104 ON A/C 971 WITH THE FOLLOWING EXCEPTION: RETAIN AND USE THE EXITING AFT STIFFENER (DAC P/N 5913595-81) WITH REPAIR KIT. DO NOT USE THE KIT SUPPLIED REPAIR AFT STIFFENER (DAC P/N SR09530003-39).

Part: FRAME — CRACKED (LT MLG WW)

FOUND DURING E-1 LETTER CHECK, CRACK AT WHEEL WELL FWD FRAME O/B, LT WHEEL WELL. REPAIRED PER SRM 53-05 FIG 78A.

Part: RIB — CRACKED (KEEL BEAM)

FOUND DURING E-1 LETTER CHECK, CRACK AT KEEL BEAM CROSSOVER RIB. REPAIRED PER SRM 53-05 FIG 101.

Part: HYD LINE — LEAKING (RT FIREWALL)

DURING CLIMB THROUGH FL270 LOST RIGHT SYSTEM FLUID AND PRESSURE. LANDED ATL. FOUND RIGHT ENGINE PRESSURE LINE THROUGH FIRE WALL LEAKING. REPLACED LINE OPERATION NORMAL.