N967AT

Part: SIGN — DAMAGED (ZONE 200) · airframe 58,449 hrs · 41,578 cycles

SHIP 9526 FORWARD CENTER OVERHEAD EXIT SIGN DAMAGED. CORRECTIVE ACTION: R/R FWD ISLE EMERGENCY LIGHT SIGN IAW B717 AMM 33-51. OPS CHECK GOOD. (7608370)

Part: FAN — ODOR (ZONE 200) · airframe 57,857 hrs · 41,013 cycles

SMOKE & FUMES, THE CREW REPORTED ELECTRICAL SMELL IN THE CABIN DURING PUSHBACK AND START OF NR 2 ENGINE. MAINTENANCE REPLACED GASPER BOOSTER FAN.

Part: FUEL CELL — LEAKING (ZONE 600) · airframe 56,460 hrs · 39,797 cycles

-AD- FUEL LEAK FOUND DURING INSPECTION OF THE RH WING THROUGH FLAP FITTING BOLTS (4 EA WET LEAK) AT XRS=164 LOWER SURFACE (OUTB BOLTS). CONTACT LIAISON ENGINEERING FOR REPAIR PROCEDURES PRIOR TO FURTHER FLIGHT. SUMMARY OF NRC 00002: RH WING THROUGH FLAP FITTING AT XRS=164 LOWER SURFACE WAS REPAIRED PER ER/A 622406-14AD REV ORIGINAL SECTION I PERMANENT REPAIR. ASSOCIATED AA 5720-01103 ADDED FOR AC 9526. ASSOCIATED ER/A 14-622406 ADDED FOR AC 9526. (LP #0700428)

Part: REPAIR — UNKNOWN · airframe 56,322 hrs · 39,690 cycles

ERA 615468-14 SECTION I REPAIR REQUIRES DTE WITHIN 12 MONTHS OF AIRCRAFT RETURN TO SERVICE. ADDED FOR AC 9526. REDEFERRED LOG TO QC, ESTAB MON INSP. ER/A 615468-14 REV A, DTE STAGE 2 AND 3 ACCOMPLISHED ON 11DEC24. ER/A SECTION II FOLLOW-ON INSPECTIONS ARE REQUIRED AND ARE TRACKED ON NEW LOG PAGE 0704878. PLEASE CLOSE THIS LOG PAGE, 0179348. CLOSED LOG AND REMOVED MONITOR INSP (LP #0179348)

Part: SKIN — CRACKED (FUSELAGE RIGHT) · airframe 54,469 hrs · 37,988 cycles

CRACK AT FWD UPPER CORNER OF R1 DOOR ON FUSELAGE SKIN. REMOVED PAINT AND FASTENER FOR FURTHER EVALUATION PER B717 SRM 51-22-01 AND SRM 51-40-02-06. VERIFIED CRACK PER BHEC AND HFEC INSPECTION, NDTSPM PART 06-10-01.003 AND PART 06-10-01.001. TWO CRACKS MARKED AT 10 O'CLOCK AND 7 O'CLOCK. ENDS OF CRACK ARE MARKED. DISCREPANCY XFRD TO NR #1 OF HANGAR WORK PACKAGE. (LP #5395006)

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,301 hrs · 39,672 cycles

CORROSION ON FRAME CHANNEL BTW LONGS 29L / 29R STA Y=1037 AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00311: CORROSION LEVEL 2. FRAME CHANNEL BTW LONGS 29L / 29R STA Y=1037 AT AFT CARGO COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3 TABLE 204 FIGURE 201 SHEET 7. PERFORM DECAL CONDITION INSPECTION EVERY C-CHECK PER TOPP MANUAL 30-10-70 PAR I PAGE 14. DECAL IS IN GOOD CONDITION BUT DUE REPAIR PERFORMED ON FRAME BTW LONG 29L/29R STA 1037 PER B717-200 SRM 53-20-07-2R PROCEDURE 3 PAR 5 AND THE CORRECT MAINTENANCE REQUIREMENTS PERFORM VISUAL INSPECTION, INITIAL FROM THIS REPAIR AT 25,000 AND REPETITIVE EVERY 6,500 AS PER THE SAME REFERENCE B717-200 SRM 53-20-07-2R PROCEDURE PAR 6 TABLE 205 MAINTENANCE REQUIREMENT. PLEASE CHANGE ATA 5320 DUE THE VISUAL INSPECTION WAS PERFORMED IN THIS VISIT AND NO DAMAGE FOUND. (LP #2841275)

Part: UNKNOWN — UNKNOWN · airframe 52,500 hrs · 36,254 cycles

NLG WHEEL WELL AFT FRAME FOR GEAR DOOR CUTOUT DAMAGED 2 PLACES. (MARKED) SUMMARY SEE NRC 005-0003:3221-4001/002 00005: REPLACED NLG WHEEL WELL AFT FRAME FOR GEAR DOOR CUT OUT FRAME PER B717 SRM 53-10-15-2. AND DAC DWG 5913421. (LP #2665497)

Part: NONE — NONE · airframe 52,500 hrs · 36,254 cycles

LMLG FIXED STRUT O/B ATTACH FITTING WORN ON FWD AND AFT FACES. SUMMARY SEE NRC 008-0003:3211-4001/001 00006: REPAIRED PER CMM 57-40-1. (LP #2663943)

Part: NONE — NONE · airframe 52,500 hrs · 36,254 cycles

RMLG FIXED STRUT O/B ATTACH FITTING WORN ON FWD AND AFT FACES. SUMMARY SEE NRC 006-0003:3211-4004/001 00007: REPAIRED PER CMM 57-40-1. (LP #2663936)

Part: NOT ENTERED — NOT ENTERED (NOT ENTERED) · airframe 52,326 hrs · 36,097 cycles

MAINTENANCE FOUND THE R1 DOOR SLIDE PARTIALLY DEPLOYED. THIS COULD PREVENT PROPER OPERATION OF THE ESCAPE PATH AND IT IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. THE R1 DOOR SLIDE WAS REPLACED PER AMDS CARD 2561-9005. (LP #4153514)

Part: SKIN — DAMAGED · airframe 52,169 hrs · 35,972 cycles

LIGHTNING STRIKE ON FUSELAGE SKIN LEFT SIDE AT FS 325, STR 10L, BETWEEN 2 FASTNERS. REMOVED DAMAGED SKIN PER B717 SRM 53-03-01-2R-1 FIG 205 SHEET 5. FABRICATED & DRILLED EXTERNAL REPAIR DOUBLER IAW B717 SRM 53-03-01-2R-1 FIG 205 SHEET 5. TREATED, PRIMED, AND INSTALLED REPAIR IAW B717 SRM 53-03-01-2R-1 FIGURE 205, SHEET 5. PAINTED TOP COAT PER B717 SRM 53-03-01-0G. VISUAL INSPS DUE EVERY 3000 CYCLES. PERMENANT REPAIR DUE AT 8000 CYCLES IAW B717 SRM 53-03-01-0G, PARA. 5, D (1) ALL RII C/W. (LP #2567946)

Part: ANGLE — CORRODED · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

EXFOLATION CORROSION ON RH ANGLE CUSP STA 200 TO 206 AT CPAX (CFS). SUMMARY OF NRC 00441: CORROSION LEVEL 2. RH ANGLE CUSP STA 168 TO 218 WAS REPAIRED PER PRI 603031-14 PRI REV 3 AND ER/A 603031- 14 REV. ORIGINAL SECTION I: PERMANENT REPAIR ASSOCIATED ER/A 14-603031 ADDED FOR AC 9526. (LP #2500821)

Part: INTERCOSTAL — CORRODED (BS 1022-1037 L30) · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

CORROSION ON INTERCOSTAL OVER LONG 30 BTW STA Y=1022 AND Y=1037 AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00310: CORROSION LEVEL 2. INTERCOSTAL OVER LONG 30 BTW STA Y=1022 AND Y=1037 AT AFT CARGO COMPARTMENT WAS REPLACED PER B-717 200 SRM 51-41-02-0G PAR 4 (A), B717-200 SRM 51-41-05-0G PAR 8, AND DWG 9936718 REV. N. (LP #2499298)

Part: NONE — NONE · airframe 51,944 hrs · 35,776 cycles

FREEPLAY ON LH WING FLAP OUTBD HINGES PIVOT AREA (STA 331.1). SUMMARY OF NRC 00186: LH WING FLAP OUTBD HINGES PIVOT AREA WAS REPAIRED PER PRI 603178-14 REV 2 & ERA 603178-14 REV. ORIG. ASSOCIATED ER/A 14-603178 ADDED FOR AC 9526. (LP #2487822)

Part: NONE — NONE · airframe 51,944 hrs · 35,776 cycles

FREEPLAY ON RH WING FLAP OUTBD HINGES PIVOT AREA (STA 331.1). SUMMARY OF NRC 00188: RH WING FLAP OUTBD HINGES PIVOT AREA WAS REPAIRED PER PRI 603122-14 REV 3 & ER/A 603122-14 REV ORIG. (LP #2488108)

Part: NONE — NONE · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

CORROSION ON FRAME CHANNEL BTW LONGS 29L / 29R STA Y=1037 AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00311: CORROSION LEVEL 2. FRAME CHANNEL BTW LONGS 29L / 29R STA Y=1037 AT AFT CARGO COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3 TABLE 204 FIGURE 201 SHEET 7. PERFORM VISUAL INSPECTION INITIAL 25,000 AND REPETITIVE EVERY 6500 CICLE PER B717 SRM 53-20--07-2R PROCEDURE 3 PAR 6. (LP #2486285)

Part: NONE — NONE · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

CORROSION ON FRAME CHANNEL BTW LONGS 29L / 29R STA Y=1037 AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00311: CORROSION LEVEL 2. FRAME CHANNEL BTW LONGS 29L / 29R STA Y=1037 AT AFT CARGO COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3 TABLE 204 FIGURE 201 SHEET 7. PERFORM DECAL CONDITION INSPECTION EVERY C-CHECK PER TOPP MANUAL 30-10-70 PAR. I PAGE. 14. (LP #2485622)

Part: NONE — NONE · airframe 51,944 hrs · 35,776 cycles

CRACK ON BRACKET UPPER CORNER AFT SIDE OF CUT OUT AT RH SLIDING CLEARVIEW WINDOW COCKTPIT (CPIL) IN REF NRC 00019. SUMMARY OF NRC 00073: CORNER AFT SIDE OF CUT OUT AT RH SLIDING CLEARVIEW WINDOW WAS REPAIRED PER B717-200 SRM 56-10-02-2R PROCEDURE 1 REPAIR 1, PRI 603296-14 REV 3 AND ER/A 603296-14 REV ORIGINAL SECTION I PERMANENT REPAIR. ASSOCIATED ER/A 14-603296 ADDED FOR AC 9526. (LP #2485644)

Part: NONE — NONE · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

FOUND CORROSION ON FLOOR SUPPORTS STA Y=160-200 AND X=-53 AT CPAX (CFS)(W1)(IN REF NRC NBR 00468). SUMMARY OF NRC 00613: CORROSION LEVEL 2 IS OUT OF LIMITS. SUPPORTS BTW STA Y=160-200 AND X=-53 AT CPAX WERE REPLACED PER B717-200 SRM 51-41-01-0G. (LP #2482688)

Part: SEAT TRACK — CORRODED (BS 200-206) · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

EXFOLATION RH SEAT TRACK X=-22 STA 200 TO 206 AT CPAX (CFS). SUMMARY OF NRC 00446: CORROSION LEVEL 2. RH SEAT TRACK SECTION X=-22 BTW STA 200 TO STA 265 WAS REPLACED PER B717-200 SRM 51-41-01-0G AND B717-200 SRM 51-41-05-0G. (LP #2475977)

Part: WEB — CRACKED (BULKHEAD DOOR) · airframe 51,944 hrs · 35,776 cycles

CRACKS (2 PLACES) ON UPPER WEB OF AFT CABIN BULKHEAD DOOR. SUMMARY OF NRC 00063: UPPER WEB OF AFT CABIN BULKHEAD DOOR WAS REPLACED PER B717 SRM 51-41-05-0G PAR. 8 AND SRM 51-40-02-0G. (LP #2477471)

Part: ANGLE — CRACKED (AFT CABIN) · airframe 51,944 hrs · 35,776 cycles

CRACK ON CLIP ANGLE NEAR TO UPPER BELLCRANK OF AFT CABIN BULKHEAD DOOR. SUMMARY OF NRC 00065: CLIP ANGLE (FITTING ASSY) NEAR TO UPPER BELLCRANK OF AFT CABIN BULKHEAD DOOR WAS FABRICATED AND REPLACED PER DWG 3917863 REV B AND B717-200 SRM 51-41-05-0G. (LP #2477105)

Part: SEAT TRACK — CORRODED (BS 200-206) · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

AFTER RH SEAT TRACK REMOTION, CORROSION WAS FOUND ON DIAPHRAGM BTW Y=200 AND Y=206 X-22 IN REF NRC 00446. SUMMARY OF 00573: CORROSION LEVEL 2. DIAPHRAGM (WEB) BTW Y=200 AND Y=218 X-17 TO X-25 WAS REPAIRED PER B717-200 SRM 51-70-10-2R PROCEDURE 1. (LP #2474250)

Part: LONGERON — CORRODED (BS 908-927 L29L) · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

CORROSION ON LONG 29LH STA Y=908 TO 927 AT AFT CARGO COMPARTMENT (C2). SUMMARY OF NRC 00260: CORROSION LEVEL 2. LONG 29LH BTW STA Y=908 TO 927 AT AFT CARGO COMPARTMENT WAS REPAIRED PER B717-200 SRM 53 -20-05-2R-1, REPAIR 1 FIGURE 201 AND B717-200 SRM 53-00-06-2R REPAIR 2. (LP #2472340)

Part: NONE — NONE · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

CORROSION ON L1 DOOR JAMB SUPPORT STA Y=160-200 AT PAX CABIN (W1). SUMMARY OF NRC 00470: CORROSION LEVEL 2. L1 DOOR JAMB SUPPORTS, 2 EA, STA Y=160-200 AT PAX CABIN WAS REPLACED PER B717-200 SRM-51-41-05-0G. (LP #2469122)

Part: MEMBRANE — CORRODED · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

CORROSION ON CUSP MEMBRANES BTW X=-54-X=-60 AND BTW STA Y=408-427, 506, 525, 598. ORIGINAL THICKNESS IS 0.020 IN AND MINIMUM REMAINING THICKNESS IS 0.010 IN, THEREFORE THE AREA IS OUT OF LIMITS IN REF NRC 00453 AT PAX CABIN. SUMMARY OF NRC 00621: CORROSION LEVEL 2. CUSP MEMBRANES BTW X=-54-X=-60 AND BTW STA Y=408-427, 506, 525, 598 WERE REPAIRED PER B717-200 SRM 53-00-55-2R PROCEDURE 4. (LP #2465577)

Part: FLOOR SUPPORT — CORRODED · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

CORROSION ON FLOOR SUPPORT BTW STA Y=1024 TO Y=1054 RBL 56 AT RH LAVATORY AFT PASSENGER CABIN (W2). SUMMARY OF NRC 00491: CORROSION LEVEL 2. FLOOR SUPPORT BTW STA Y=1024 TO Y=1054 RBL 56 AT RH LAVATORY AFT PASSENGER CABIN WAS REPLACED PER B717-200 SRM 51-41-02-0G AND B717-200 SRM 51-41-05- 0G. (LP #2462557)

Part: FLOOR SUPPORT — CORRODED · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

CORROSION ON FLOOR SUPPORT STA Y=200 BTW X=-9 AND X=-46 (CAPX)(W1). SUMMARY OF NRC 00472: CORROSION LEVEL 2. FLOOR SUPPORT AT STA Y= 200 BTW X=-9 AND X=-46 WAS REPLACED PER B717-200 SRM 51-41-01-0G AND B717-200 SRM 51-41-05-0G. (LP #2462418)

Part: FLOOR SUPPORT — CORRODED · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

EXFOLATION ON FLOOR SUPPORT STA Y=160-200 X=-44 (CAPX)(W1). SUMMARY OF NRC 00482: CORROSION LEVEL 2. FLOOR SUPPORT STA Y=160- 200 X=-44 WAS REPLACED PER B717-200 SRM 51-41-01-0G AND B717-200 SRM 51-41-05-0G. (LP #2462423)

Part: FLOOR SUPPORT — CORRODED · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

CORROSION ON FLOOR SUPPORT BTW STA Y=1024 TO Y=1055 RBL 48 AT RH LAVATORY AFT PASSENGER CABIN (W2). SUMMARY OF NRC 00492: CORROSION LEVEL 2. FLOOR SUPPORT BTW STA Y=1024 TO Y=1055 RBL 48 AT RH LAVATORY AFT PASSENGER CABIN WAS REPLACED PER DWG 9981474-82 AND B717-200 SRM 51-41-05-0G. (LP #2462081)

Part: FLOOR SUPPORT — CORRODED · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

EXFOLATION ON FLOOR SUPPORT STA Y=180 BTW X=-9 - X=-43 (CAPX)(W1). SUMMARY OF NRC 00481: CORROSION LEVEL 2. SUPPORT STA Y=180 BTW X =-9 - X=-43 WAS REPLACED PER B717-200 SRM 51-41-02-0G AND B717- 200 SRM 51-41-05-0G. (LP #2461817)

Part: FLOORBEAM — CORRODED (BS 200) · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

AIRCRAFT 9526, INITIAL INSPECTION:CORROSION ON FLOOR SUPPORT STA Y=200 BTW X=9 AND X=13 (CAPX)(W1). CORRECTIVE ACTION: CORROSION LEVEL 2. FLOOR SUPPORT STA Y=200 BTW X=9 AND X=13 WAS REPLACED PER B717-200 SRM 51-41-05-0G PAR. 8. LP 2457059

Part: FLOORBEAM — CORRODED (BS 200) · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

AIRCRAFT 9526, INITIAL INSPECTION:CORROSION ON FLOOR SUPPORT STA Y=200 BTW X=5 AND X=-5 (CAPX)(W1). CORRECTIVE ACTION: CORROSION LEVEL 2. FLOOR SUPPORT STA Y=200 BTW X=5 AND X=-5 WAS REPLACED PER B717-200 SRM 51-41-05-0G PAR. 8. LP 2457001

Part: CUSP WEB — CORRODED (BS 446-465) · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

AIRCRAFT 9526, INITIAL INSPECTION : CORROSION ON PREVIOUSLY REPAIR DOUBLER RH CUSP WEB BTW X=-54 - X=-60 AND STA Y=446-465. CORRECTIVE ACTION: DOUBLER RH CUSP WEB BTW X=-54 - X=-60 AND STA Y=446-465 WAS REPLACED PER B717-200 SRM 53-00-55-2R-4 REPAIR 4 FIGURE 209. LP 2454517

Part: HINGE — DAMAGED (BULKHEAD DOOR) · airframe 51,944 hrs · 35,776 cycles

AIRCRAFT 9526, INITIAL INSPECTION. WEAR ON INTERNAL DOUBLER BTW LOWER HINGE AND LOWER PAN OF AFT CABIN BULKHEAD DOOR. CORECTIVE ACTION: PAN OF AFT CABIN BULKHEAD DOOR WAS REPAIRED PER B-717 SRM 52-10-02-2R PROCEDURE 16, REPAIR 16, PAR 4. A. LP 2450898

Part: LONGERON SPLICE — CORRODED (BS 889-908) · corrosion level 2 · airframe 51,944 hrs · 35,776 cycles

AIRCRAFT 9526, INITIAL INSPECTION:CORROSION ON LONG SPLICE 30 BTW STA Y=889-908 AT AFT CARGO COMPARTMENT (C2). CORRECTIVE ACTION: LONG SPLICE 30 BTW STA Y=889-908 AT AFT CARGO COMPARTMENT WAS REPLACED PER B717-200 SRM 51-41-01-0G PAR. 6 & 51-41-05-0G PAR. 8. LP 2449561

Part: SLIDE — NO TEST (R1 DOOR) · airframe 50,579 hrs · 34,712 cycles

THE R1 DOOR SLIDE FAILED THE DEPLOYMENT TEST PER AMDS CARD #2561-9002 FORECAST #95-0525-8-0121. MAINTENANCE REMOVED AND INSTALLED A NEW SERVICEABLE R1 DOOR SLIDE REF AMDS CARD #2561-9005. ICR HAS BEEN SUBMITTED USING DOC/WORKCARD #2560-9352 -95 (QC5126/376046). (LP #5745100)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 50,152 hrs · 34,383 cycles

THE EXIT SIGN ABOVE THE AFT BULKHEAD DOOR IS INOPERATIVE (EMERGENCY LIGHT). MAINTENANCE REPLACED THE EMERGENCY LIGHT BATTERY IAW B717 AMM 33-57-03. OPERATIONAL CHECK WAS GOOD. (LP #5759650)

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 48,223 hrs · 33,027 cycles

THE FORWARD EMERGENCY EXIT SIGN IS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK B5-235 REF AMM 33-51. OPERATIONAL CHECK WAS GOOD. (LP #3914354)

Part: DOOR FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 48,145 hrs · 32,973 cycles

CORROSION WAS FOUND ON THE FORWARD CARGO DOOR JAMB. REPLACED DOOR JAMB IN STEPS 1 THRU 5 REF SRM 53-20-15-2R PROC 6.

Part: MECHANISM — OUT OF ADJUST (TAILCONE) · airframe 48,145 hrs · 32,973 cycles

TAILCONE RELEASE CAM MECHANISM IS CLOCKED WRONG. CHECKED CLOCKING AND ADJUSTED, REF BAC DWG 5961568 & AMM 53-52-03.

Part: LENS — MISSING (EMERGENCY LIGHT) · airframe 48,045 hrs · 32,915 cycles

THE FLIGHT ATTENDANT DISCOVERED THE OVERWING EXIT EMERGENCY SIGN COVER WAS MISSING. MAINTENANCE REPLACED THE LENS ASSEMBLY AND THE AIRCRAFT RETURNED TO SERVICE.

Part: POWER SUPPLY — CONTAMINATED (EMERGENCY LIGHTS) · airframe 47,316 hrs · 32,409 cycles

THE EMERGENCY EXIT LIGHTS WOULD NOT TURN OFF. MAINTENANCE FOUND THE POWER SUPPLY ABOVE THE AFT F/A SEAT TO BE SATURATED WITH WATER. MAINTENANCE REPLACED POWER SUPPLY AND BATTERY IAW AMM 33-51. OPS CHECKED NORMAL.

Part: BATTERY PACK — MALFUNCTIONED (EMERGENCY LIGHTS) · airframe 47,215 hrs · 32,335 cycles

UPPER AFT CABIN EXIT DOOR SIGN FLASHING WHEN IN ARM POSITION. MAINTENANCE REPLACED LIGHT POWER SUPPLY AND BATTERY ABOVE AFT DOOR CEILING PANEL IAW AMM 33-51. OPERATIONAL CHECK IS NOW NORMAL. AIRCRAFT OK FOR SERVICE.

Part: SMOKE DETECTOR — FALSE ACTIVATION (FWD CARGO BAY) · airframe 46,867 hrs · 32,102 cycles

WHILE ON APPROACH FOR LANDING, THE FORWARD CARGO SMOKE INDICATION ILLUMINATED. THE QRH WAS COMPLIED WITH, DISCHARGED BOTH CARGO FIRE BOTTLES TO MAKE THE INDICATION EXTINGUISH. MAINTENANCE INSPECTED WIRE BUNDLES AND ALL COMPONENTS TESTED GOOD. THE CARGO SMOKE DETECTORS WERE REPLACED. NO EVIDENCE OF ANY SCORCHING, DAMAGE, NOR FIRE WAS FOUND.

Part: SIGN — DETACHED (EMERGENCY LIGHTS) · airframe 45,949 hrs · 31,462 cycles

EMERGENCY EXIT SIGN COVER LOOSE. THE LIGHT WAS HANGING BY WIRES. SECURED THE EXIT SIGN.

Part: SIGN — LOOSE (EMERGENCY LIGHTS) · airframe 45,580 hrs · 31,221 cycles

CREW REPORTED THE CEILING EXIT SIGN AT ROW 1 WAS LOOSE. SECURED THE SIGN.

Part: LIGHT — INTERMITTENT (CABIN) · airframe 45,380 hrs · 31,081 cycles

AFT EMERGENCY EXIT SIGN FLICKERED. PERFORMED EMERGENCY EXIT LIGHT TEST IAW B717 AMM 33-51. NO FAULTS NOTED. OPERATION IS NORMAL.

Part: FIRE WARNING — FALSE ACTIVATION (NR 1 NACELLE) · airframe 45,280 hrs · 31,013 cycles

THE COCKPIT CREW RECEIVED A NR 1 ENGINE FIRE WARNING INDICATION WHILE IN CRUISE FLIGHT. IAW QRH, BOTH FIRE BOTTLES WERE DISCHARGED AND THE NR 1 ENGINE WAS SHUTDOWN. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT AT THE SCHEDULE DESTINATION. MAINTENANCE DID NOT FIND ANY EVIDENCE OF AN ACTUAL ENGINE FIRE. REPLACED THE GEAR BOX FIRE LOOP, LOWER SPLITTER FAIRING FIRE LOOP (AT 6 O'CLOCK POSITION), UPPER SPLITTER FAIRING FIRE LOOP, LOWER COWL EXHAUST VENT FIRE DETECTOR, AND THE ENGINE CORE FIRE DETECTOR. PERFORMED OPERATIONAL CHECK OF THE NR 1 & 2 ENGINE FIRE DETECTION SYSTEMS AND ALL CHECKS WERE GOOD.

Part: UNKNOWN — MALFUNCTIONED (CABIN) · airframe 44,983 hrs · 30,795 cycles

AFT EXIT SIGN ILLUMINATED WHILE EMERG LIGHT SWITCH IN ARM POSITION. PERFORMED EMERGENCY LIGHTS TEST PER AMM 33-51. CYCLED EMERGENCY LIGHTS SWITCH SEVERAL TIMES. AFT EXIT SIGN DID NOT ILLUMINATE IN THE ARMED POSITION. SYSTEM CHECKS GOOD. A/C OK FOR SVC.

Part: LENS — MISSING (EMERGENCY LIGHT) · airframe 44,346 hrs · 30,349 cycles

EMERGENCY LIGHT LENS MISSING, IN THE OVERHEAD ABOVE ROW 1. REPLACED THE LENS, CHECKED GOOD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 43,273 hrs · 29,581 cycles

CRACKED FUSELAGE SKIN Y=1076 LONG 14 RT. REPAIR WAS ACCOMPLISHED PER ETI-17-16-123 REV 1 & ER/A 550326-14 REV ORIGINAL. LEAK TEST OF AIR CONDITION PNEUMATIC DUCT WAS ACCOMPLISHED PER AMM 21-00-00 790-801 AND NO LEAKS WERE FOUND. ACCOMPLISH SECTION II REPETITIVE INSPECTIONS EVERY 3,000 FLIGHT CYCLES AFTER ACCOMPLISHMENT OF SECTION I PERMANENT REPAIR PER LOG 2730787.

Part: SKIN — CRACKED (NR 2 SLAT) · airframe 43,273 hrs · 29,581 cycles

CRACKED SLAT PANEL NR 2 INBD FACE XOS 238 RT WING. THE SLAT PANEL WAS REMOVED IAW AMM 27-80-01 000-806, HFEC INSPECTION WAS ACCOMPLISHED AND ONE CRACK WAS FOUND IAW NDT SPM 06-10-01. THE SLAT PANEL WAS REPAIRED IAW SRM 57-00-00 FIG. 201 AND INSTALLED IAW AMM 27-80-01 400-805 STEP E5 AND F.

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 43,273 hrs · 29,581 cycles

DISTRESS AT VERTICAL STABILIZER LEADING EDGE STRUCTURE SPLICE. BHEC INSPECTION WAS ACCOMPLISHED, NO CRACKS WERE FOUND IAW DWG SG 95550001 REV.B, BUSHINGS WERE FABRICATED AND INSTALLED IAW DPS 4.710-3 AND DWG SG95550001 REV. B.

Part: PAN — CRACKED (FUSELAGE) · airframe 43,273 hrs · 29,581 cycles

CRACK ON LOWER FWD CORNER AT AFT CARGO COMPARTMENT DOOR PAN. REPAIR WAS ACCOMPLISHED PER ER/A 550336-14 REV ORIGINAL AND ETI-17-16-127 REV 3.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 43,273 hrs · 29,581 cycles

CRACKED LONGERON 2R ON STA 1133 AT AFT ACCESSORIES AREA. LONGERON SECTION WAS REPLACED PER SRM 51-41-05, 51-40-08, 51-10-04 PAR 15 AND 21, AND SRM 51-41-01.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 43,273 hrs · 29,581 cycles

CRACK ON DOOR JAMB STA Y=954 AT AFT CARGO COMPARTMENT C2 (SM) (S/N 00135). DOOR JAMB WAS REPLACE PER SRM 51-41-02 AND 51-41-05. PERFORM DECAL VISUAL INSPECTION EVERY C CHECK PER TOPP 30-10-70 PAR I PG 14.

Part: FRAME — CRACKED (BS 1022) · airframe 43,273 hrs · 29,581 cycles

CRACKED FRAME ANGLE ON BULKHEAD PYLON SUPPORT AT BS 1022 LONGERON 7L. REPAIRED IAW ETI-17-16-130 REV. ORIGINAL AND ER/A 550341-14 REV. ORIGINAL.

Part: CUSP WEB — CORRODED (BS 550) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

CORROSION ON THE RT CUSP WEB BS 550. DAMAGED AREA WAS TRIMMED OUT IAW SRM 53-00-55. HFEC INSPECTION WAS ACCOMPLISHED AFTER TRIM OUT AND NO CRACKS WERE FOUND IAW NDT SPM 06-10-01. REPAIRED IAW SRM 53-00-55 FIG. 215, 51-10-4 PAR 15, 21, 51-41-02, AND 51-10-04 PAR. 37.

Part: CUSP WEB — CRACKED (FUSELAGE) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

EXCESSIVE CORROSION ON RT CUSP WEB ON STA Y=550 IN REF CARD 00393. CRACK WAS FOUND WITH NEXT DIMENSION L=.320" DAMAGED AREA WAS TRIMMED OUT PER SRM 53-00-55. HFEC INSPECTION WAS ACCOMPLISHED ON RT CUSP WEB ON STA Y=550 AFTER TRIM OUT AND NO CRACKS WERE FOUND PER NDT SPM 06-10-01 .001. AREA WAS REPAIRED PER SRM 53-00-55 FIG 215, 51-10-4 PAR 15,21, 51-41-02 AND 51-10-04 PAR 37.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,725 hrs · 29,902 cycles

EXCESSIVE CORROSION ON RT CUSP WEB ON STA Y=550 IN REF CARD 00393. CRACK WAS FOUND WITH NEXT DIMENSION L=.320" DAMAGED AREA WAS TRIMMED OUT PER SRM 53-00-55. HFEC INSPECTION WAS ACCOMPLISHED ON RT CUSP WEB ON STA Y=550 AFTER TRIM OUT AND NO CRACKS WERE FOUND PER NDT SPM 06-10-01 .001 EQUIPMENT: MENTOR C/N: 1205 EXP DATE 24AUG17, AREA WAS REPAIRED PER SRM 53-00-55 FIG 215, 51-10-4 PAR 15,21, 51-41-02 AND 51-10-04 PAR 37.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

EXCESSIVE CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE 620CB AND 620AT AT RT WING. PLATES 620AT AND 620CB WERE REWORKED AND WERE FOUND OUT LIMITS, THEREFORE FUEL ACCESS PLATES WERE REPLACED AND THE APPLICABILITY WAS VERIFIED PER IPC 57-22-01-01 AND 57-23-01-01.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

CORROSION OUT OF LIMITS ON LONGERON 30 BTW STA Y= 974 TO 1005 AT AFT CARGO COMPARTMENT. LONGERON 30 BTW STA Y=974 TO Y=1005 WAS REPAIRED PER SRM 53-00-05 FIG 201 REPAIR 3.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 43,273 hrs · 29,581 cycles

CRACKED RT NLG DOOR JAMB. (00434) LENGTH ORIGINAL CRACK LONG 1.300" AND WIDTH 0.750". DAMAGED AREA WAS REMOVED, CUT WAS CHECKED PER HFEC INSP, AND NO CRACKS FOUND. AREA WAS REPAIRED PER SRM 53-10-14 FIG 201 REPAIR 2.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 43,273 hrs · 29,581 cycles

CRACKED LT NLG DOOR JAMB (00435). LENGTH ORIGINAL CRACK LONG 1.125" AND WIDTH 0.750", DAMAGED AREA WAS REMOVED, CUT WAS CHECKED PER HFEC INSP, AND NO CRACKS FOUND. AREA WAS REPAIRED PER SRM 53-10-14 FIG 201 REPAIR 2.

Part: CUSP WEB — CRACKED (BS 663) · airframe 43,273 hrs · 29,581 cycles

CRACK ON CUSP WEB BS 663 BTW LBL 54 TO 60. HFEC WAS ACCOMPLISHED AND A CRACK WAS CONFIRMED OF 1.900" LENGTH IAW NDT SPM 06-10-01 .001: THE CRACK WAS STOPPED DRILL IAW SRM 51-00-07 PAR 5. HFEC WAS ACCOMPLISHED IAW NDT SPM 06-10-01 .001 AND NO CRACKS WERE FOUND AFTER STOP DRILL. THE CUSP WEB WAS REPAIRED IAW SRM 53-00-55 REPAIR 4.

Part: CHANNEL — CRACKED (BS 757) · airframe 43,273 hrs · 29,581 cycles

CRACKED RT MLG DOOR FRAME CHANNEL AT BS 757. THE CHANNEL WAS REPLACED IAW SRM 51-41-02 AND 51-41-05.

Part: FRAME — CRACKED (BS 907) · airframe 43,273 hrs · 29,581 cycles

CRACKED FRAME 907 BETWEEN LONGERONS 26-28R, REPAIRED IAW SRM 51-41-02 AND 51-41-05.

Part: ANGLE — CRACKED (BS 1022 BULKHEAD) · airframe 43,273 hrs · 29,581 cycles

CRACK ON BULKHEAD ANGLE BS 1022 BETWEEN LONGERONS 16-17L. A NEW FRAME ANGLE WAS MANUFACTURED IAW DRAWING 9912243-189 AND SRM 51-20-09. TREATED AND PAINTED IAW SRM 51-10-04 PAR 15 AND 21, AND INSTALLED IAW SRM 51-41-05.

Part: ANGLE — CRACKED (BS 1022 BULKHEAD) · airframe 43,273 hrs · 29,581 cycles

CRACK ON BULKHEAD ANGLE BS 1022 BETWEEN LONGERONS 13-14R. A NEW ANGLE WAS MANUFACTURED IAW DRAWING 9912243-198 AND SRM 51-20-09, TREATED AND PAINTED IAW SRM 51-10-04 PAR 21 AND 15, AND INSTALLED IAW SRM 51-41-02 AND 51-41-05.

Part: CUSP WEB — CRACKED (BS 365) · airframe 43,273 hrs · 29,581 cycles

CRACK FOUND ON THE RT CUSP WEB BS 365 X45. HFEC INSPECTION WAS ACCOMPLISHED ON THE CUSP WEB AND A CRACK WAS CONFIRMED IAW NDT SPM 06-10-01 .001. THE DAMAGE WAS REMOVED PER B-717 SRM 55-00-55 REPAIR 4 AND ANOTHER HFEC INSPECTION WAS ACCOMPLISHED AND NO CRACKS WERE FOUND IAW NDT SPM 06-10-01 .00.

Part: LONGERON SPLICE — CORRODED (BS 898) · airframe 43,273 hrs · 29,581 cycles

CORROSION ON LONGERON SPLICE 18R, BS 898. THE SPLICE WAS REMOVED IAW SRM 51-41-05. SPLICE WAS FABRICATED IAW SRM 53-20-01 FIG 1 AND 51-20-09. THE SPLICE AND AREA WAS TREATED AND PAINTED IAW SRM 51-10-04 PAR. 15/21. THE SPLICE WAS INSTALLED IAW SRM 51-41-05.

Part: PAN — CRACKED (BS 427) · airframe 43,273 hrs · 29,581 cycles

CRACK ON PAN BS 427 BETWEEN BEAM 1 AND BEAM 2 AT FWD CARGO DOOR. HFEC INSPECTION WAS ACCOMPLISHED AND CRACKS WERE FOUND IAW NDT SPM 06-10-01 .001. CRACKS ON PAN WERE STOP DRILLED IAW SRM 52-30-02 FIG 201, HFEC WAS ACCOMPLISHED ON PAN AND NO CRACKS WERE FOUND AFTER STOP DRILL IAW NDT SPM 06-10-01.001.

Part: SUPPORT — CRACKED (BS 715) · airframe 43,273 hrs · 29,581 cycles

CRACKED SUPPORT UNDER SEAT TRACK X 44.5 ON BS 715. THE SUPPORT WAS REPLACED IAW DWG 9923417 REV. B AND SRM 51-41-05.

Part: CUSP WEB — CORRODED (BS 455) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

EXCESSIVE CORROSION ON RT CUSP WEB BS 455. DAMAGE WAS REMOVED, A REPAIR WAS MANUFACTURED, AND INSTALLED IAW SRM 53-00-55 REPAIR 4. HFEC WAS ACCOMPLISHED IAW NDT SPM 06-10-01.001 AND NO CRACKS WERE FOUND AFTER CUT OUT.

Part: SEAT TRACK — CRACKED (BS 715) · airframe 43,273 hrs · 29,581 cycles

CRACKED SUPPORT UNDER SEAT TRACK X -44.5 AT BS 715. THE SUPPORT WAS REMOVED IAW SRM 51-41-05 AND 51-41-02. A NEW SUPPORT WAS DRILLED IAW DWG 9923417 REV. B AND SRM 51-40-08. TREATED AND PAINTED IAW SRM 51-10-04 PAR. 21 AND 15. AND INSTALLED IAW DWG 9923417 AND SRM 51-41-05.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

EXCESIVE CORROSION ON COUNTERSINK OF FUEL ACCESS PANEL 520CB LT WING. THE ACCESS PANEL WAS DETERMINED TO BE OUT OF LIMITS AND WAS REPLACED IAW SRM 57-10-01 PAR. 5.

Part: CUSP WEB — CORRODED (BS 294) · airframe 43,273 hrs · 29,581 cycles

PUNCTURE ON LT CUSP WEB BS 294 BETWEEN X 44 TO 54. DAMAGE WAS REMOVED, HFEC INSPECTION ACCOMPLISHED, NO CRACKS WERE FOUND IAW NDT SPM 06-10-01 .001. DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-00-55 AND SRM 51-41-02.

Part: CUSP WEB — CORRODED (BS 856) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

EXCESSIVE CORROSION ON LT CUSP WEB BS 856. DAMAGE WAS REMOVED, DOUBLER FABRICATED, AND INSTALLED IAW SRM 53-00-55 AND 51-41-02, HFEC INSPECTION WAS ACCOMPLISHED IAW NDT SPM 06-10-01.001.

Part: CUSP WEB — CORRODED (BS 513) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

EXCESSIVE CORROSION ON RT CUSP WEB ON BS 513. DAMAGE ON AREA WAS TRIMMED OUT IAW SRM 53-00-55. HFEC INSPECTION WAS ACCOMPLISHED AND NO CRACKS WERE FOUND IAW NDT SPM 06-10-01.001. REPAIR FABRICATED IAW SRM 53-00-55 REPAIR 4 FIG. 215 AND INSTALLED IAW SRM 51-41-02.

Part: ACCESS PANEL — DAMAGED (RT WING) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

ELONGATED HOLES ON FUEL ACCESS PANEL 141AR ON THE RT WING. THE ACCESS PANEL WAS REWORKED IAW SRM 57-10-01 CONDITION II AND FOUND TO BE OUT OF LIMITS. REPLACED IAW SRM 57-10-01.

Part: CUSP WEB — CRACKED (BS 218) · airframe 43,273 hrs · 29,581 cycles

CRACK ON RT CUSP WEB BS 218 X=45 AT CABIN PAX RH. CRACK WAS STOP DRILL IAW SRM 53-00-55 REPAIR 4, HFEC INSPECTION WAS ACCOMPLISHED IAW NDT SPM 06-10-01.001, NO CRACKS WERE FOUND AFTER STOP DRILL. REPAIR DOUBLER WAS FABRICATED IAW SRM 53-00-55. AREA DRILLED WAS TREATED AND PAINTED IAW SRM 51-10-04 PAR 21 AND 15. REPAIR INSTALLED IAW SRM 53-00-55 REPAIR 4. C

Part: CUSP WEB — CORRODED (BS 489) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

EXCESSIVE CORROSION ON RT CUSP WEB ON BS 489 IAW CARD 00393. DAMAGE WAS REMOVED IAW SRM 53-00-55 FIG. 215. HFEC INSPECTION WAS ACCOMPLISHED AFTER TRIM OUT AND NO CRACKS WERE FOUND IAW NDT SPM 06-10-01.001. REPAIR FABRICATED IAW SRM 53-00-55. REPAIR INSTALLED SRM 51-41-02.

Part: ACCESS PANEL — DAMAGED (LT WING) · airframe 43,273 hrs · 29,581 cycles

ELONGATED HOLES ON FUEL ACCESS PANEL 141AL ON THE LT WING. THE FUEL ACCESS PANEL WAS REPAIRED SRM 57-10-01 CONDITION II.

Part: FRAME — CRACKED (BS 1116) · airframe 43,273 hrs · 29,581 cycles

CRACKED FRAME ANGEL BS 1116 BETWEEN LONGERONS 15 -16 BOTH SIDES. THE ANGLS WERE REPLACED IAW SRM 51-41-05.

Part: CUSP WEB — CORRODED (BS 836) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

CORROSION FOUND ON THE LT CUSP WEB BS 836. DAMAGE WAS REMOVED IAW SRM 53-00-55 REPAIR 4. DOUBLER WAS FABRICATED IAW SRM 53-00-55 REPAIR 4. HFEC INSPECTION WAS ACCOMPLISHED AFTER TRIM OUT, AND NO CRACKS WERE FOUND IAW NDT SPM 06-10-01.THE DOUBLER WAS INSTALLED IAW SRM 53-00-55 REPAIR 4.

Part: CUSP WEB — PUNCTURED (BS 169) · airframe 43,273 hrs · 29,581 cycles

PUNCTURE ON CUSP WEB BS 169 AND X 50. HFEC INSPECTION WAS ACCOMPLISHED AFTER TRIM OUT, AND NO CRACKS WERE FOUND IAW NDT SPM 06-10-01. REPAIRED IAW SRM 51-70-10 REPAIR 2 FIG. 201.

Part: CUSP WEB — PUNCTURED (BS 813) · airframe 43,273 hrs · 29,581 cycles

PUNCTURE ON RT CUSP WEB BS 813 BETWEEN X40 TO 44). THE DAMAGE WAS REMOVED IAW SRM 53-00-55 REPAIR 4 FIG. 219, HFEC INSPECTION WAS ACCOMPLISHED AFTER TRIM OUT, AND NO CRACKS WERE FOUND IAW NDT SPM 06-10-01.001. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 55- 00-55 FIG 219,51-41-02.

Part: PAN — CRACKED (BS 370) · airframe 43,273 hrs · 29,581 cycles

CRACK ON INNER PAN BS 370, BEAM 5 AT FWD CARGO COMPARTMENT DOOR. REPAIRED IAW SRM 52-30-02 REPAIR 1 FIG. 201.

Part: FLOORBEAM — CORRODED (BS 200) · corrosion level 2 · airframe 43,292 hrs · 29,599 cycles

SEVERAL CORROSION POINTS ON FLOORBEAM BS 200 FROM X-13 TO X-44 . CORROSION WAS REMOVED IAW SRM 51-10-04 PAR 26, THE FLOORBEAM WAS REPAIRED IAW SRM 51-41-02. AND 51-41-05.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 43,273 hrs · 29,581 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PANEL 520CT ON LT WING. FOUND TO BE OUT OF LIMITS IAW SRM 57-10-01. THE ACCESS PANEL WAS REPLACED IAW SRM 57-10-01.

Part: PAN — CRACKED (BS 870-889) · airframe 43,273 hrs · 29,581 cycles

CRACK ON LT FWD LOWER CORNER ON RING PAN OF WINDOW, BETWEEN BS 870 AND 889. DAMAGE WAS REMOVED IAW SRM 56-20-02 REP 1. HFEC WAS ACCOMPLISHED ALONG THE TRIM LINE, NO CRACKS WERE FOUND IAW 06-10-01.001. CRACK RING PAN WAS REPAIRED IAW SRM 56-20-02 REP 1.

Part: PAN — CRACKED (BS 889-908) · airframe 43,273 hrs · 29,581 cycles

CRACKED RING PAN ON AFT UPPER CORNER BETWEEN BS 889 AND 908. DAMAGE WAS REMOVED IAW SRM 56-20-02 REP 1. HFEC INSPECTION WAS ACCOMPLISHED ALONG THE TRIM LINE, NO CRACKS WERE FOUND 06-10-01.001. THE RING PAN WAS REPAIRED IAW SRM 56-20-02 REP 1.

Part: PAN — CRACKED (BS 756-775) · airframe 43,273 hrs · 29,581 cycles

CRACKED RING PAN ON FWD UPPER CORNER BETWEEN BS 756 AND 775. DAMAGE WAS REMOVED IAW SRM 56-20-02 REP 1. HFEC INSPECTION WAS ACCOMPLISHED ALONG THE TRIM LINE, NO CRACKS WERE FOUND IAW 06-10-01.001. RING PAN WAS REPAIRED IAW SRM 56-20-02 REP 1.

Part: PAN — CRACKED (BS 617-636) · airframe 43,273 hrs · 29,581 cycles

CRACK ON LT FWD LOWER CORNER ON RING PAN OF WINDOW BETWEEN BS 617 AND 636. DAMAGE WAS REMOVED IAW SRM 56-20-02 REP 1. HFEC INSPECTION WAS ACCOMPLISHED ALONG THE TRIM LINE, NO CRACKS WERE FOUND IAW 06-10-01.001. CRACK RING PAN WAS REPAIRED IAW SRM 56-20-02 REP 1.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 42,227 hrs · 28,720 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LOWER INTERIOR LIGHTS AT THE OVERWING HATCHES WERE INOPERATIVE IN 4 POSITIONS. MAINTENANCE REPLACED THE BATTERY PACKS FOR THE NOTED LIGHTED AREAS AND THE OPS CHECK WAS GOOD.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 41,789 hrs · 28,350 cycles

R1 DOOR EMERGENCY EXIT SIGN ABOVE DOOR WILL NOT ILLUMINATE. MAINTENANCE R & R B5-123 POWER SUPPLY AND BATTERY IAW AMM 33-51, LP 7203501.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 40,084 hrs · 26,975 cycles

DURING LINE CHECK, FOUND EMERGENCY LIGHTS AT CEILING PANEL 20CD AND 22CDE INOPERATIVE. REPLACED POWER SUPPLY AT ROW 20CD IAW AMM 33-51-03.

Part: FITTING — CRACKED (LE SLAT) · airframe 384,090 hrs · 25,668 cycles

LEFT WING NR 5 SLAT END FITTING CRACKED AT LOWER FASTENER HOLE ATTACHING SEAL. R & R FITTING IAW SRM & DWG.

Part: SIGN — CRACKED (CABIN) · airframe 384,090 hrs · 25,668 cycles

PLASTIC EXIT SIGN CRACKED AT PULL HANDLE IN TAIL COMPARTMENT. R & R SIGN IAW MM.

Part: LENS — CRACKED (CABIN) · airframe 384,090 hrs · 25,668 cycles

R1 DOOR OVERHEAD EMER EXIT LIGHT LENS CRACKED. R & R LENS IAW AMM.

Part: SIGN — CRACKED (CABIN) · airframe 37,950 hrs · 25,355 cycles

R1 DOOR EMER EXIT SIGN LIGHT ASSEMBLY CRACKED. R & R SIGN ASSEMBLY IAW AMM.

Part: DOOR — CRACKED (LE SLAT) · airframe 37,950 hrs · 25,355 cycles

LEFT WING NR 1 SLAT OTBD TRACK LE DOOR ASSEMBLY CRACKED. R & R DOOR ASSEMBLY IAW DWG.

Part: FITTING — CORRODED (GIRT BAR) · airframe 37,950 hrs · 25,355 cycles

GIRT BAR FITTING CORRODED AT BS 172, BL 0. R & R FITTING IAW SRM & DWG.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 37,950 hrs · 25,355 cycles

CABIN FLOORBOARD SUPPORT ANGLE CORRODED AT BS 200 BL 0. REPAIRED ANGLE IAW SRM & DWG.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 37,950 hrs · 25,355 cycles

STRINGER CORRODED AT BS 129 STRINGER 29R. R & R STRINGER IAW SRM.

Part: DOOR — CRACKED (RT WING) · airframe 37,950 hrs · 25,355 cycles

RIGHT WING INBD BUTTE DOOR AT INBD END OF AFT PIANO HINGE, DOOR CRACKED IN THE CORNER. REPAIRED DOOR IAW EA.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 37,950 hrs · 25,355 cycles

ATTACH CLIP CORRODED AT BS 1087, LONGERON 24R. R & R CLIP IAW SRM & DWG.

Part: ENGINE — FAILED (RIGHT) · airframe 36,797 hrs · 24,619 cycles

DECLARED EMERGENCY, SEVERAL COMPRESSOR STALLS ON DESCENT RAW CHECK LIST. COMPRESSOR STALL ON FINAL APPROACH WITH THROTTLE AT IDLE RT ENGINE ONLY. R & R NR 2 ENGINE IAW MT.

Part: COMPRESSOR — STALLED (NR 2 ENGINE) · airframe 4,595 hrs · 2,960 cycles

AIR TURNBACK - AFTER TAKEOFF NR 2 ENGINE COMPRESSOR STALL. REMOVED AND REPLACED NR 2 ENGINE PER TC AND MM.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

INTERCOSTAL AT BL 0 STA 617-636 HAS A CRACK AT THE AFT VERTICAL LEG. REMOVED CRACKED FLANGE OF INTERCOSTAL AT STA 636 BL 0 IAW B717 SRM 51-10-04, FABRICATED REPAIR ANGLE FROM 224-T3.040 PO 90015069 IAW BOEING DRW 993658 + SRM 51-70-11 REPAIR 1 A

Part: RUB STRIP — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

WING TO BODY PANEL CHAFE STRIP CRACKED AND PEELING AT LEFT UPPER WING STA 715. REMOVED AND REPLACED STRIP IAW SRM AND BOEING.

Part: RUB STRIP — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

WING TO BODY PANEL CHAFE STRIP CRACKED & PEEL AT RIGHT UPPER WING STA 674 TO 699. REMOVED AND REPLACED STRIP IAW MM AND BOEING.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

RIGHT CUSP WEB AT STA 655 TO 675 CRACKED. REMOVED AND REPLACED WEB IAW SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

LEFT CUSP WEB AT STA 668 TO 679 FOUND CRACKED. REMOVED AND REPLACED WEB IAW SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

LEFT CUSP WEB AT STA 655 CRACKED. REMOVED AND REPLACED WEB IAW SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

RIGHT CUSP WEB AT STA 677 CRACKED. REMOVED AND REPLACED WEB IAW SRM.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

LONGERON CRACKED AT BS 1114, LONG 2R. REMOVED AND REPLACED LONGERON IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

OVERWING FRAME LT STA 674 CRACKED ON THE UPPER RADIUS OF THE TAB. REMOVED AND REPLACED WINDOW IAW SRM DWG. REMOVED AND REPLACED LEFT FRAME 674 IAW B717 SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

RIGHT OVERWING FRAME CRACKED AT STA 696, ON THE UPPER RADIUS OF THE TAB. REPAIRED FRAME IAW BOEING DWG.

Part: BRACKET — CRACKED (RT MLG WW) · airframe 34,150 hrs · 22,953 cycles

RIGHT WHEEL WELL - FWD I/B OF DOOR CUTOUT BRACKET CRACKED. REMOVED AND REPLACED BRACKETS AT RIGHT W/W FWD I/B OF DOOR CUTOUT IAW B717 SRM 51-40-02, 51-40-08 AND 51-41-05.

Part: SKIN — CORRODED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

BELLY SKIN CORRODED AT STA 598 TO 617, BETWEEN L-30 L-29. REMOVED AND REPLACED SKIN IAW SRM AND DWG.

Part: BRACKET — CRACKED (LT MLG WW) · airframe 34,150 hrs · 22,953 cycles

LEFT WHEEL WELL - FWD DOOR CUTOUT - I/B BRACKET CRACKED. REMOVED AND REPLACED BRACKET AT LEFT W/W FWD DOOR CUTOUT IAW B717 SRM 51-41-05, 51-40-08 AND 51-40-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

RIGHT FS 715 FRAME CRACKED AT LONGERON 18R. REMOVED AND REPLACED FRAME IAW SRM.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

MAIN CABIN SEAT TRACK SUPPORT HINGE AT FS 737 LBL 45.5 CRACKED AT LOWER LEG. REMOVED AND REPLACED PANEL IAW AMM.

Part: ANGLE — CRACKED (CENTER WING) · airframe 34,150 hrs · 22,953 cycles

WING CENTER SECTION FRONT SPAR AT FS 660, RBL 24.5 CRACKED ANGLE. REMOVED AND REPLACED ANGLE IAW SRM.

Part: SLIDE — UNSERVICEABLE (L1 DOOR) · airframe 34,150 hrs · 22,953 cycles

UPON REMOVAL OF L1 DOOR SLIDE FOUND SLIDE TO BE PACKED INCORRECTLY AND MISSING A SAFETY PIN. REMOVED AND REPLACED LEFT DOOR SLIDE ASSY IAW B717 MM 25-61-01.

Part: LINK ASSY — CORRODED (RT ELEVATOR) · airframe 34,150 hrs · 22,953 cycles

RIGHT ELEV DOC BONE BEARING RUSTED (DAMPER ROD). REMOVED & REPLACED DAMPER LINK ASSY IAW B717 AMM 20-50-01 AND 27-31-09

Part: BRACKET — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

LEFT VENT LOWER BOX CRACKED BRACKET ON FRAME STA 1200. REMOVED AND REPLACED BRACKET IAW SRM.

Part: SPOILER — DELAMINATED (RT WING) · airframe 34,150 hrs · 22,953 cycles

RIGHT WING FLAP VANE SIDE OF I/B SPOILER DELAMINATED. REPAIRED IAW M/M.

Part: FAIRING — CRACKED (TE FLAP) · airframe 34,150 hrs · 22,953 cycles

RIGHT WING FLAP - NR 3 HINGE LWR FAIRING - LWR END CRACKED. SANDED CLEANED PREPARED & PAINTED RIGHT WING FLAP NR 3 HINGE LWR FAIRING AS REQUIRED IAW B717 AMM 51-10-00.

Part: STOP FITTING — CRACKED (LE SLAT) · airframe 34,150 hrs · 22,953 cycles

LEFT WING L/E SLAT TRACK NR 8 DOOR, DOOR STOP IS CRACKED LOCATED INSIDE ACCESS 510ABB. REMOVED & REPLACED LEFT WING L/E SLAT TRACK NR 8 DOOR STOP IAW B717 SRM 51-41-02.

Part: GUSSET — CRACKED (LT WING) · airframe 34,150 hrs · 22,953 cycles

LEFT WING ROOT STA 65.5, GUSSETT I/B OF FLAP TRACK ROLLERS CRACKED. REPAIRED ROLLERS IAW SRM.

Part: STRAP — CRACKED (RT WING) · airframe 34,150 hrs · 22,953 cycles

RIGHT WING LEADING EDGE - AT STA XCW 58.500 STRAP CRACKED. REMOVED AND REPLACED STRAPS IAW SRM AND BOEING DWG.

Part: FAIRING — CRACKED (LT AILERON) · airframe 34,150 hrs · 22,953 cycles

LEFT WING AILERON TRIM CONTROL ROD FAIRING IS CRACKED 55-41. REPLACED LEFT WING AILERON TRIM CONTROL ROD FAIRING IAW B717 SRM 51-40-08, 51-10-04 AND AMM 51-10-00.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL #222AVF IS DELAMINATED. REMOVED PANEL 222AVF. FABRICATED NEW PANEL P/N B227002 TYPE3 P/O 79019957 DIM: 21" X 65". INSTALLED PANEL IAW B717 SRM 53-20-50 & 51-41-01 AND AMM 53-21-01.

Part: SKIN — CRACKED (NLG DOOR) · airframe 34,150 hrs · 22,953 cycles

LEFT NLG STRUT DOOR SKIN CRACKED. REPAIRED SKIN IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 221WF IS DELAMINATED. REMOVED PANELS 221WF, FABRICATED NEW PANEL P/N B227002TYPE3 P/O 79019957 DIM 21" X 76". INSTALLED NEW PANEL ALL IAW B717 SRM 53-20-50 & 51-41-01 AND AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222FF IS DELAMINATED. REMOVED PANEL 222FF. FABRICATED NEW PANEL P/N B227002TYPE P/O 79019957 DIM 21" X 39". NSTALLED NEW PANEL ALL IAW B717 SRM 53-20-50 & 51-41-01 AND AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222VF IS DELAMINATED. REMOVED PANEL 222RF. FABRICATED NEW PANEL P/M B227002TY PE3, PO 49019957 DIM: 21" X 57". INSTALLED FLOOR PANEL ALL IAW B717 53-21-01, SRM 53-20-50 & 51-41-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222ACF IS DELAMINATED. REMOVED PANEL 222ACF. FABRICATED NEW PANEL P/N B227002TYPE P/O 79019957 DIM 21" X 41". INSTALLED PANEL 222ACF ALL IAW B717 AMM 53-21-01 SRM 53-20-50 & 51-41-01.

Part: STRIP — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

CRACKED CHAFE STRIP WING TO BODY FILLET STA 898 BETWEEN L21R - L22R. REMOVED AND REPLACED CHAFE STRIP ON WING TO BODY FILLET AT STA 898 WITH NEW SERVICEABLE PART IAW B717 SRM 53-53-01.

Part: SKIN — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

RT NLG STRUT DOOR AFT CUT OUT HAS CRACKED SKIN, NDT VERIFIED, ENDS MARKED. REMOVED FASTENERS IN REPAIR AREA AT RT AFT WLG DOOR IAW SRM 51-40-02, STOP DRILLED CRACK IAW B717 SRM 53-10-01 REPAIR 6. HFEC VERIFIED CRACK STOP DRILL.

Part: PANEL — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

LEFT SIDE OF FUSELAGE, VENT LOUVER AT FS 1200 CRACKED ANGLE. REMOVED AND REPLACED PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222LF IS DELAMINATED. REMOVED PANEL 222LF. FABRICATED PANEL P/N B224002TYPE3 P/O 79019957 DIM 21" X 76'. INSTALLED PANEL ALL IAW B717 SRM 53-20-50 & 51-41-01 AND B717 AMM 53-21-01

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222AMF IS DELAMINATED. REMOVED FLOOR PANEL 222AMF FABRICATED NEW PANEL P/N B227002TYPE3 P/O 790191470 DIM. 21" X 76". INSTALLED NEW PANEL ALL IAW B717 AMM 53-21-01, 53-20-50 & 51-41-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222RF IS DELAMINATED. REMOVED PANEL 22RF, FABRICATED PANEL P/N B224002TYPE PO 79019957 DIM 21" X 76", INSTALLED PANEL ALL SRM 53-20-30, 51-41-01 AND AMM 53-21-01

Part: BOLT — CORRODED (AILERON TAB) · airframe 34,150 hrs · 22,953 cycles

RIGHT WING - AILERON TABS HINGES 5 EA HAS CORRODED HWD. REMOVED & REPLACED RIGHT WING AILERON TABS 5 EACH HINGE BOLTS.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

RIGHT SIDE OF FUSELAGE, VENT LOUVER AT FS 1200 CRACKED ANGLE. REMOVED AND REPLACED ANGLE IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222ABF IS DELAMINATED. REMOVED PANEL 222ABF FABRICATED NEW PANEL P/N B227002TYPE3 P/O 79019957 DIM 21" X 22". INSTALLED NEW PANEL ALL IAW B717 SRM 53-20-50 & 51-41-01 AND AMM 53-21-0.1

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222AEF IS DELAMINATED. REMOVED PANEL 222AGF. FABRICATED NEW PANEL P/N B227002TYPE3 P/O 79019957 DIM 21" X 46". INSTALLED NEW PANEL IAW AMM 53-21-01, SRM 53-20-50 & 51-10-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222PF IS DELAMINATED. REMOVED PANEL 222PF. FABRICATED NEW PANEL P/N B227002TY PE 3 P/O 790191470 DIM 21" X 76". INSTALLED PANEL ALL IAW B717 AMM 53-21-01 SRM 53-20-50 & 51-41-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222AAF IS DELAMINATED. REMOVED PANEL 222AAF. FABRICATED NEW PANEL P/N B227002TYPE3 P/O 49019957 DIM: 21" X 22". INSTALLED PANEL ALL IAW B717 AMM 53-21-01 SRM 53-20-50 & 51-41-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222APF IS DELAMINATED. REMOVED PANEL 222APF. FABRICATED NEW PANEL P/N B227002 TYPE3 P/O 79019957 DIM: 21" X 76" CLOSED PANEL IAW B717 SRM 53-20-50 & 51-41-01 AND AMM 53-21-01.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,150 hrs · 22,953 cycles

CABIN FLOOR PANEL 222AEF IS DELAMINATED. REMOVED PANEL 222AEF. FABRICATED NEW PANEL P/N B227002 TYPE3 P/O 79019957 DIM: 21" X 41" CLOSED PANEL 222AEF IAW B717 SRM 53-20-50 & 51-41-01 AND AMM 53-21-01.

Part: SEAL — LOOSE (EMERGENCY EXIT) · airframe 34,150 hrs · 22,953 cycles

RIGHT AFT EMERGENCY EXIT DOOR JAMB - LWR SEAL LOOSE. SECURED RIGHT AFT EMERGENCY EXIT DOOR SEAL IAW B717 MM 20-60-21.

Part: FITTING — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

RT FWD EMERGENCY EXIT DOOR JAMB - AFT SIDE, UPPER AND LWR CHAFE CLIPS CRACKED. REMOVED AND REPLACED UPPER AND LOWER CLIPS AFT SIDE OF RT FWD EMERGENCY EXIT DOOR JAMB AS PER B717 SRM 51-41-08.

Part: FITTING — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

LEFT AFT EMERGENCY EXIT DOOR JAMB - UPPER FWD AND AFT SIDES, CHAFE CLIPS CRACKED. REMOVED & REPLACED UPPER FWD AND AFT CLIPS ON LEFT AFT EMERGENCY EXIT DOOR JAMB AS PER B717 SRM 51-41-08.

Part: ATTACH FITTING — CRACKED (LT WING) · airframe 34,150 hrs · 22,953 cycles

CRACKED CLIP ATTACH TO LEFT WING ROOT TO FUSELAGE STA 636. REPAIRED STRAPS IAW SRM AND DWG.

Part: SEAL — LOOSE (EMERGENCY EXIT) · airframe 34,150 hrs · 22,953 cycles

RIGHT FWD EMERGENCY EXIT DOOR JAMB - LWR SEAL LOOSE. SECURED SEAL ON RIGHT FWD EMERGENCY EXIT DOOR IAW B717 MM 20-60-21.

Part: FITTING — CRACKED (FUSELAGE) · airframe 34,150 hrs · 22,953 cycles

LEFT FWD EMERGENCY EXIT DOOR JAMB - UPPER AFT CHAFE CLIP CRACKED. REMOVED & REPLACED UPPER AFT CLIP ON LT FWD EXIT DOOR JAMB AS PER B717 SRM 51-41-08.

Part: TAB — DELAMINATED (ELEVATOR) · airframe 32,122 hrs · 21,628 cycles

LT ELEVATOR CONTROL TAB T/E DELAMINATED. REMOVED AND REPLACED CONTROL TAB PER MM.

Part: HANDSET — DEFECTIVE (CABIN)

AFT HAND SET AT AFT F/A STATION FELT VERY HOT, WAS SMOKING WHEN AFT FA MADE CROSS ANNOUNCEMENT. UPON INITIAL ENTRY INTO THE ACFT DID NOT SMELL ANY STRANGE ODORS ,THE AFT F/A HAND SET HAD ELECTRICAL SMELL AND VISUAL DAMAGE, DISCONNECT HANDSET FROM SYSTEM REF; AMM 23-41-07. NO OTHER ODORS WERE NOTED. PLACED AFT FA HAND SET ON MEL. ADV CHIEF INSP FOR APPROVAL TO RETURN ACFT TO SERVICE.

Part: HOUSING — CRACKED (CABIN)

EMERGENCY FLOOR LIGHT ON SEAT 22D IS HANGING OFF THE SEAT, (HOUSING CRACKED). REMOVED AND REPLACED END FAIRING AT 22D, OK TO CONTINUE SERVICE, CMM AVIO 25-24-93.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY CEILING LIGHTS IN FWD CABIN INOP. REMOVED AND REPLACED EMERGENCY BATTERY ASSY AT STATION 39B IAW B717- / MM-33-51. OPS CHECK GOOD.

Part: GASPER FAN — MALFUNCTIONED (AC BAY)

ACCOMPLISH CHECK OF AIRCRAFT DUE TO SMELL IN CABIN. UPON ENTERING AIRCRAFT CHECK CIRCUIT BREAKERS AND ALL OTHER COMPONENTS PER SP8115. FOUND GASPER FAN SMOKING IN TAIL CONE COMPARTMENT. MTC TO NOTIFY CHIEF INSPECTOR.

Part: INTERCOSTAL — CORRODED (BS 1022-1037)

AFT CARGO COMPARTMENT INTERCOSTAL SECTION, STA 1022 TO 1037, LONG L30, CORROSION. ACCOMPLISHED INTERCOSTAL SECTION REPLACEMENT PER B717 SRM 51-41-02.

Part: STRUCTURE — CRACKED (LT PYLON)

LEFT PYLON APRON LOWER AFT HINGE CUTOUT, CRACKED. ACCOMPLISHED AFT HINGE CUTOUT DOUBLER REPAIR PER TRA 17-54-TR00129.

Part: STRUCTURE — CRACKED (LT PYLON)

LEFT PYLON APRON LOWER NR 2 HINGE CUTOUT AREA, CRACKED. ACCOMPLISHED NR 2 HINGE CUTOUT AREA DOUBLER REPAIR PER TRA 17-54-TR00129.

Part: STRUCTURE — CRACKED (LT PYLON)

LEFT PYLON APRON UPPER AFT HINGE CUTOUT, CRACKED. ACCOMPLISHED AFT HINGE CUTOUT DOUBLER REPAIR PER TRA 17-54-TR00129.

Part: ATTACH FITTING — CORRODED (GIRT BAR)

GALLEY ENTRANCE FWD AND AFT GIRT BAR ATTACH FITTINGS, CORROSION. ACCOMPLISHED GIRT BAR ATTACH FITTINGS REPLACEMENT PER B717 SRM 51-41-01 AND B717 SRM 51-41-02.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 237, RBL 22, CORROSION. ACCOMPLISHED SEAT TRACK SPLICE REPAIR PER BOEING DWG SR09530085.

Part: LONGERON — CORRODED (FUSELAGE)

E/E COMPARTMENT LONGERON SECTION, STA 125, LONG L30, CORROSION. ACCOMPLISHED LONGERON SECTION REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 160 TO 200, RBL 53, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 179, LBL 15 TO LBL 37, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 200, RBL 8 TO RBL 45, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 148 TO 200, RBL 7, CORROSION. ACCOMPLISHED SEAT TRACK REPLACEMENT PER B717 SRM 51-41-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 200 TO 256, LBL 15, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 200, LBL 5 TO RBL 5, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 148 TO 200, LBL 7, CORROSION. ACCOMPLISHED SEAT TRACK REPLACEMENT PER B717 SRM 51-41-01.

Part: COMPRESSOR — STALLED (LT ENGINE)

LEFT ENGINE COMPRESSOR STALL. REMOVED AND REPLACED NR 1 ENGINE S/N 13321 WITH ENGINE S/N 13133.

Part: PAN — CORRODED (FUSELAGE)

FWD CARGO DOOR PAN CORRODED BEYOND USABLE LIMITS. CUT OUT CORRODED AREA AT LOWER PAN, INSTALLED NEW PAN & SPLICE PER B717 SRM 53-20-15.

Part: STRUCTURE — DAMAGED (FUSELAGE)

MDDR 121944T DAMAGE AT LT STA 196 TO 229 L15 & 16. CUT OUT DAMAGED AREA, INSTALLED DOUBLER PER B717 SRM 53-06-01 REPAIR 6.

Part: FRAME — CRACKED (FUSELAGE)

CABIN - FWD ENTRY AFT FRAME WEB CRACKED AT STR 15 LT STA 200. FABRICATED WEB REPAIR PER B717 SRM 51-70-10 FIG 201.

Part: PAN — CORRODED (FUSELAGE)

AFT CARGO DOOR PAN CORRODED BEYOND LIMITS. CUT OUT CORRODED SECTION & REPLACED WITH SPLICE REPAIR PER B717 SRM 53-20-15 REPAIR 7.

Part: SKIN — DAMAGED (FUSELAGE)

DAMAGE DONE TO AIRCRAFT BY BELT LOADER UNDERSIDE OF TAIL SECTION BY AFT CARGO DOOR. REMOVED DAMAGED SKIN AND INSTALLED NEW SKIN SECTION FROM STA 980-1053 L26LTO L26R IAW B717 SRM 53-00-01 FIG 201 AND DWG 5919707 ON AAR W/O 28493 NRWC 6468 FOR COMPLETE DETAILS.

Part: PAN — CRACKED (AFT CARGO DOOR)

AFT CARGO DOOR FWD CAM CUTOUT CRACK. INSTALLED ANGLE REPAIR 2024T3 .063 X 30 X 7.0 PER B717 SRM 52-30-02 FIG 201 REPAIR 4.

Part: SKIN — DENTED (AFT CARGO DOOR)

DENT ON AFT CARGO DOOR CENTER OF DOOR. INSTALLED FLUSH REPAIR PER SRM 52-00-01 FIG 204, PERFORMED NDT NO CRACK NOTED.

Part: SKIN — DAMAGED (L1 DOOR)

L1 DOOR LOWER FWD CORNER OUTER SKIN DAMAGED. INSTALLED DOULBER REPAIR PER SRM 52-10-01 FIG 201, 14" X 2 1/7" 2024T3. 050.

Part: EEC — INOPERATIVE (NR 2 ENGINE)

ENGINE RIGHT SYSTEM FAIL AND REVERSER RIGHT FAIL IN CLIMB. HAD NO THROTTLE RESPONSE TRIED ALTN FADEC, NO RESPONSE SHUTDOWN ENGINE NECESSARY TO DESCEND AND LAND. REMOVED AND REPLACED NR 2 ENG EEC PER AMM 73-21-01. C/W RTS, RTS GOOD. C/W SPECIAL INSP OF LPC OGV LEADING EDGE, TRAILING EDGE, AND CONCAVED SURFACES PER AMM 72-00-00. CHIP DETECTOR INSPECTION C/W. PERFORMED ENGINE POWER ASSURANCE CK IAW 71-00-13, OPS CHECK OK.