N963AT

Part: LATCH — FAULTED (ZONE 800) · airframe 59,090 hrs · 42,023 cycles

ATB, PERFORMED AN AIR TURN BACK DUE TO A RIGHT MAIN LANDING GEAR UNSAFE LIGHT. REPLACED RT GEAR DOOR LATCH. OPS CHECK NORMAL.(7841530).

Part: PAN — CRACKED (CARGO DOOR AREA) · airframe 56,009 hrs · 39,236 cycles

CRACKS ON INNER PAN (3 EA) NEAR BEAMS #5 & #3 FWD SIDE. ALSO NEAR BEAM #2 AFT SIDE AT FWD CARGO DOOR. ER/A 554100-14 REV. A SECTION I WAS ACCOMPLISHED. SUMMARY OF NRC 00097: FWD AND AFT INNER PAN BETWEEN BEAMS #1 AND BEAM #4 AT FWD CARGO DOOR WAS REPAIRED PER ER/A 554100-14 REV A SECTION I: PERMANENT REPAIR AND PRI 554100-14 REV 6. ALSO, FWD INNER PAN NEAR BEAM #5 AT FWD CARGO DOOR WAS REPAIRED PER B717-200 SRM 52-30-02-2R REPAIR 1. ASSOCIATED ER/A 14-554100 ADDED FOR AC 9522. (LP #0268224)

Part: HINGE — OBSTRUCTED (RT WING TE FLAP) · airframe 56,009 hrs · 39,236 cycles

INTERFERENCE BTW HEAD BOLT AND FWD OUTB FLAP HINGE AT RH WING. SUMMARY OF NRC 00808: FWD OUTB FLAP HINGE AT RH WING WAS REPAIRED PER ERA 616905-14 REV ORIGINAL SECTION I. ASSOCIATED ER/A 14-616905 ADDED FOR AC 9522. (LP #0268113)

Part: BULKHEAD WEB — CRACKED · airframe 56,007 hrs · 39,235 cycles

CRACK ON WEB LH AND RH SIDE, (PROJECTION OF UPPER HINGE) AT AFT CABIN PRESSURE BULKHEAD EMERGENCY EXIT DOOR. SUMMARY OF NRC 00558: WEB AT AFT CABIN PRESSURE BULKHEAD EMERGENCY EXIT DOOR WAS REPLACED PER B717-200 SRM 51-41-02-0G AND 51-41-05-0G. ALSO AFT CABIN BULKHEAD DOOR WAS REMOVED / INSTALLED / ADJUSTED PER B717-200 AMM 52-12-03. (LP #0260725)

Part: WEB — CORRODED (BS 200-208) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION ON WEB BTW Y=200 TO Y=208 X=56. SUMMARY OF NRC 00734: CORROSION LEVEL 2. CORROSION ON WEB BTW Y=200 TO Y=208 X=56 WAS REPAIRED PER PRI 616504-14 REV. 1 AND ERA 616504-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. ASSOCIATED ERA 14-616504 ADDED FOR AC 9522. (LP #0257752)

Part: AILERON — UNKNOWN (LEFT) · airframe 56,218 hrs · 39,434 cycles

-AD- PERFORM BALANCE PROCEDURE ON AILERON LH. SUMMARY OF NRC 00770: AILERON LH BALANCE PROCEDURE WAS PERFORMED PER B717-200 SRM 51-60-01-0G, ALSO AILERON LH WAS REMOVED / INSTALLED PER B717-200 AMM 27-10-01. ADJUSTMENT / TEST OK; AILERON CONTROL TAB L/H WAS REMOVED / INSTALLED PER B717-200 AMM 27-10-02. ADJUSTMENT / TEST OK; AND AILERON TRIM TAB L/H WAS INSTALLED PER B717-200 AMM 27-10-05. ADJUSTMENT / TEST OK. (LP #0257444)

Part: FRAME — CRACKED (BS 1037 L14-15R) · airframe 56,007 hrs · 39,235 cycles

CRACK ON FRAME STA Y=1037 BTW LONG 14 RH AND 15 RH AT CABIN PAX. SUMMARY OF NRC 00386: FRAME STA Y=1037 BTW LONG 14 RH AND 15 RH AT CABIN PAX WAS REPAIRED PER ERA 616076-14 REV ORIGINAL SECTION I: PERMANENT REPAIR AND PRI 616076-14 REV 3. (LP #0255676)

Part: SKIN — CORRODED (AIRSTAIR DOOR) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION ON INTERNAL SKIN AND CUT OUT OF FWD AIR STAIRWELL DOOR. SUMMARY OF NRC 00109: FWD AIR STAIRWELL DOOR WAS REPLACED PER B717-200 AMM 52-63-01. (LP #0255910)

Part: LONGERON — CORRODED (AFT CARGO) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION ON LONGERON END 25RH AT AFT CARGO COMPARTMENT C-2. SUMMARY OF NRC 00686: CORROSION LEVEL 2. LONGERON END 25RH AT AFT CARGO COMPARTMENT C-2 WAS REPLACED PER B717-200 SRM 51-41-05-0G. (LP #0252387)

Part: CUSP WEB — CORRODED (BS 200) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION AT CUSP ANGLE WAS FOUND ON STA Y=200 AND X=54 - 60. SUMMARY OF NRC 00713: CUSP ANGLE WAS ON STA Y=200 AND X=54 - 60 REPAIRED PER B717-200 SRM 53-00-55-2R PROCEDURE 3 REPAIR 3. (LP #0246718)

Part: SKIN — WORN (BS 994 L23-25L) · airframe 56,007 hrs · 39,235 cycles

WORN FUSELAGE SKIN AT STA Y=994 & LONG 23 - 25 (ADJACENT TO AFT DOOR JAMB). SUMMARY OF NRC 00013: FUSELAGE SKIN AT STA Y=994 & LONG 23 - 25 (ADJACENT TO AFT DOOR JAMB) WAS REPAIRED PER B717-200 SRM 53-20-15-2R PROCEDURE 10 REPAIR 10. PERFORM VISUAL INSPECTION AT 8,000 CYCLES AND REPETITIVE VISUAL INSPECTION EVERY 8,000 CYCLES PER B717 SRM 53-20-15-2R PROCEDURE 10 REPAIR 10 FIG 202 STEP 7. (LP #0244014)

Part: SKIN — WORN (BS 994 L23-25) · airframe 56,007 hrs · 39,235 cycles

WORN FUSELAGE SKIN AT STA Y=994 & LONG 23 - 25 (ADJACENT TO AFT DOOR JAMB). SUMMARY OF NRC 00013: FUSELAGE SKIN AT STA Y=994 & LONG 23 - 25 (ADJACENT TO AFT DOOR JAMB) WAS REPAIRED PER B717-200 SRM 53-20-15-2R PROCEDURE 10 REPAIR 10. (LP #0242390)

Part: FLOOR SUPPORT — CORRODED (BS 1022-1060) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION OUT OF LIMITS AT FLOOR SUPPORT BTW STA Y=1022 AND STA Y=1060, ON X=44. SUMMARY OF NRC 00696: CORROSION LEVEL 2. FLOOR SUPPORT BTW STA Y=1022 AND STA Y=1060, ON X=44 WAS REPLACED PER B717-200 SRM 51-41-01-0G. (LP #0239946)

Part: SKIN — DENTED (CARGO DOOR) · airframe 56,007 hrs · 39,235 cycles

SEVERAL DENTS BTW 1 THRU 3 BEAMS AT AFT CARGO DOOR SKIN AND ALSO WORN SKIN AT AFT LWR DOOR SKIN CORNER. SUMMARY OF NRC 00016: OUTER SKIN AT AFT CARGO COMPARTMENT DOOR WAS FABRICATED AND REPLACED PER DWG 5910157 REV CW AND B717-200 SRM 51-41-02-0G. (LP #0237570)

Part: CUSP WEB — CORRODED (BS 986-1000) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION ON CUSP WEB BTW STA Y986 TO STA Y1000 X=-60 AT CPAX. STRUCTURE WAS MEASURED WITH AN ORIGINAL THICKNESS OF 0.020IN. REMAINING THICKNESS IS 0.005IN THEREFORE REWORKED AREA IS OUT OF LIMITS. SUMMARY OF NRC 00697: CORROSION LEVEL 2. CUSP WEB BTW STA Y986 TO STA Y1000 X=-60 AT CPAX WITH WAS REPAIRED PER B717-200 SRM-53-00-55-2R. (LP #0235916)

Part: CUSP WEB — CORRODED (BS 400) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION ON CUSP WEB BTW STA Y408 AND X=- 60 AT CPAX. SUMMARY OF NRC 00569: CORROSION LEVEL 2. CUSP WEB BTW STA Y408 AND X=-60 AT CPAX WAS REPAIRED PER B717-200 SRM 53-00-55-2R PROCEDURE 4 REPAIR 4. (LP #0235862)

Part: INTERCOSTAL — CORRODED (BS 635-353) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION ON INTERCOSTAL BTW STA 636 TO 653 AND BTW LONGERONS 27-L TO 28-L AT FWD CC. SUMMARY OF NRC 00316: CORROSION LEVEL 2. INTERCOSTAL ON BTW STA 636 TO 653 AND BTW LONGERONS 27-L TO 28-L AT FWD CC WAS REPLACED PER B717 SRM 51-40-02-0G. (LP #0234436)

Part: WEB — CORRODED (BS 198) · airframe 56,007 hrs · 39,235 cycles

CORROSION WAS FOUND AT DIAPHRAGM BEETWEN STA Y=198 AND X=54 (PASSENGER DOOR ENTRANCE). SUMMARY OF NRC 00616: CORROSION LEVEL 2. DIAPHRAGM BEETWEN STA Y=198 AND X=54 (PASSENGER DOOR ENTRANCE) WAS REPAIRED PER B717-200 SRM 51-70-10-2R PROCEDURE 2 REPAIR 2 PAR 4 FIGURE 201. (LP #0231988)

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 56,007 hrs · 39,235 cycles

CRACK ON INTERCOSTAL OF MECHANISM BTW BEAM #4 AND BEAM #5 OF L1 DOOR. SUMMARY OF NRC 00059: INTERCOSTAL OF MECHANISM BTW BEAM #4 AND BEAM #5 OF L1 DOOR WAS FABRICATED AND REPLACED PER DWG 9955763 REV L, B717-200 SRM 51-41-01-0G AND 51-41-02-0G. (LP #0229988)

Part: SKIN — CRACKED (CARGO DOOR) · airframe 56,007 hrs · 39,235 cycles

CRACK ON INTERNAL SKIN NEAR TO BEAM #3 FWD EDGE WAS FOUND AT FWD CARGO DOOR. SUMMARY OF NRC 00745: INTERNAL SKIN NEAR TO BEAM #3 FWD EDGE AT FWD CARGO DOOR WAS REPAIRED PER B717-200 SRM 52-30-02-2R PROCEDURE 3 REPAIR 3, FIGURE 201. (LP #0231760)

Part: TAB — DENTED (RUDDER) · airframe 56,007 hrs · 39,235 cycles

SEVERAL DENTS ON RH SIDE OF RUDDER CONTROL TAB. SUMMARY OF NRC 00081: SEVERAL DENTS ON RH SIDE OF RUDDER CONTROL TAB WERE MEASURED AND FOUND WITH NO DISBONDS AND ARE WITHIN LIMITS PER B717-200 SRM 55-41-01-1A PROCEDURE I ALLOWABLE DAMAGE I PAR 3,A,(4),(C), AND PAR 2.B. TAP-TEST FOR POSSIBLE DISBOND AT EVERY "C" CHECK OR 3,000 CYCLES, OR REPAIR PER B717-200 SRM 55-41-01-1A PROCEDURE 1 AD 1 PAR 2. B. (LP #0226068)

Part: CUSP WEB — CORRODED (BS 696) · airframe 56,007 hrs · 39,235 cycles

CRACK CUSP WEB RH LOWER AREA STA 696 CPAX. SUMMARY OF NRC 0547: CUSP WEB RH ON STA 655 TO STA 715 WAS REPAIRED PER B717-200 SRM 53-00-55-2R-4 REPAIR 4, 51-41-02-0G, AND 51-41-05-0G. PERFORM A GVI EVERY "C" CHECK PER B717-200 SRM 53-00-55-2R-4 REPAIR 4, PAR 6. (LP #0227143)

Part: FLOOR SUPPORT — CORRODED (BS 200) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION ON FLOOR SUPPORT ON STA Y=200 BTW X=-44 AND X=-55 AT PAX COMPARTMENT. (W1). SUMMARY OF NRC 00553: CORROSION LEVEL 2. DUE TO EXCESS CORROSION (EXFOLIATION), FLOOR SUPPORT ON STA Y=200 BTW X=-44 AND X=-55 AT PAX COMPARTMENT (W1) WAS REPLACED PER DWG 9936534 REV BW AND B717-200 SRM 51-41-02-0G. (LP #0226178)

Part: WEB — CORRODED (BS 201) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION ON MEMBRANE STA Y=201 BTW X=11 TO X=-44 AT PAX COMPARTMENT. (W1). CORROSION LEVEL 2. MEMBRANE STA Y=201 BTW X=11 TO X=-44 AT PAX COMPARTMENT WAS REPAIRED PER B717-200 SRM 51-70-10-2R, PROCEDURE 2 REPAIR 2. (LP #0225731)

Part: WEB — CORRODED (BS 178) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION ON MEMBRANE STA Y=178 AND BTW X=-2 AND X=-26 AT PASSENGER COMPARTMENT (W1). SUMMARY OF NRC 0551: CORROSION LEVEL 2. MEMBRANE STA Y=178 AND BTW X=-2 AND X=-26 AT PASSENGER COMPARTMENT (W1) WAS REPAIRED PER B717-200 SRM 51-70-10-2R REPAIR 2. (LP #0222570)

Part: CUSP WEB — CORRODED (BS 832-851) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION AT CUSP WEB BETWEN STA 832 AND STA 851 AND X=60 PAX CABIN. SUMMARY OF NRC 0395: CORROSION LEVEL 2. CORROSION AT CUSP WEB BETWEN STA 832 AND STA 851 AND X=60 PAX CABIN WAS REMOVED B717-200 SRM 51-10-04-0G PAR 26 C (1). (UT) THICKNESS MEASUREMENT WAS ACCOMPLISHED ON AT CUSP WEB BETWEN STA 832 AND STA 851 AND X=60 PAX CABIN. ORIGINAL THICKNESS IS 0.040IN REMAINING THICKNESS IS 0.017IN THEREFORE IT IS OUT OF LIMITS PER B717-200 SRM 53-00-00-1A ALLOWABLE DAMAGE PAR 4 C AND DC-MD/BOEING NDT SPM PART 4, 04-00-06 PAR 4 FIG 9. AREA OUT LIMITS WAS REPAIRED PER B717-200 SRM 53-00-55-2R-4 FIG 215. (LP #0222439)

Part: CUSP WEB — CRACKED (BS 1017-1020) · airframe 56,007 hrs · 39,235 cycles

CRACK ON CUSP WEB (LOWER AREA) BTW STA 1017 TO STA 1020 AND X=45 AT CPAX. SUMMARY OF NRC 00589: CUSP WEB (LOWER AREA) BTW STA 1017 TO STA 1020 AND X=45 AT CPAX WAS REPAIRED PER B717-200 SRM 53-00-55-2R PRCEDURE 4 REPAIR 4. (LP #0221152)

Part: DOOR FRAME — CORRODED (AFT CARGO) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

EXFOLIATION CORROSION AT AFT CARGO LWR DOOR JAMB FROM STA Y=954 TO Y=996. SUMMARY OF NRC 00020: CORROSION LEVEL 2. AFT CARGO LWR DOOR JAMB FROM STA Y=954 TO Y=996 WAS REPLACED PER B717 SRM 53-20-15-2R REPAIR 7, 51-41-02-0G, AND 51-41-04-0G. (LP #0218389)

Part: LONGERON — CORRODED (BS 130 L30L) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION AT STA 130 APROX AND L30 COMPARTMENT E&E. SUMMARY OF NRC 00225: CORROSION LEVEL 2. LONGERON 30 STA Y=110 TO Y=130 WAS REPLACED PER DWG 5411401 REV DT AND B717-200 SRM 51-41-02-0G. (LP #0217998)

Part: FLOORBEAM — CORRODED (BS 1053) · corrosion level 2 · airframe 56,007 hrs · 39,235 cycles

CORROSION ON ANGLE OF FLOOR STRUCTURE STA Y=1053 X=20 AT CABIN PAX. SUMMARY OF NRC 00374: CORROSION LEVEL 2. ANGLE OF FLOOR STRUCTURE STA Y=1053 X=20 WAS REPLACED PER B717-200 SRM 51-41-05-0G. (LP #0212052)

Part: FRAME — CRACKED (BS 717 S27-28L) · airframe 56,007 hrs · 39,235 cycles

CRACKED FRAME ON STA Y=715 BTW S-27L AND S-28L AT CANTED KEEL BEAM AREA. (FUS) SUMMARY OF NRC 0549: CRACKED FRAME ON STA Y=715 BTW S-27L AND S-28L AT CANTED KEEL BEAM AREA WAS REPAIRED PER B-717-200 SRM 51-70-11-2R PROCEDURE 1 REPAIR 1. PERFORM AN EXTERNAL GVI OF THE REPAIRED FRAME AT STA Y=715 BTW S-27L AND S-28L ON CANTED KEEL AREA EVERY C-CHECK PER B717-200 SRM 51-70-11-2R PROCEDURE 1 REPAIR 1 PAR 2 A TABLE 201. (LP #0209507)

Part: FLOOR SUPPORT — CRACKED (BS 636) · airframe 56,007 hrs · 39,235 cycles

CRACK ON FLOOR SUPPORT STA 636 X=0 AND Z=-2 AT FWD CC. SUMMARY OF NRC 00309: FLOOR SUPPORT (INTERCOSTAL) STA 636 X=0 AND Z=-2 AT FWD CARGO WAS REPAIRED PER B717 SRM 51-70-11-2R PROCEDURE 1 REPAIR 1. (LP #0205320)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 55,042 hrs · 38,386 cycles

THE CENTER AISLE OVERHEAD RED EXIT SIGN IS BROKEN AND MISSING THE BACK HALF OF THE SIGN. MAINTENANCE REPLACED THE SIGNAGE. OPERATIONAL CHECK OF THE SIGN WAS NORMAL. THE AIRCRAFT IS OK FOR SERVICE. (LP #4398332)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 54,630 hrs · 38,027 cycles

SHIP 9522 -MISC/DE- DURING APPROACH FOR LANDING, THE "BUS DC R OFF" INDICATION ILLUMINATED. WHICH WAS FOLLOWED BY 15 OTHER DISCREPANCY INDICATIONS. THE QRH WAS COMPLIED WITH AND THE CREW DECLARED EMERGENCY DUE TO THE IMPENDING NO FLAP AND NO SLAT LANDING. A HOT BRAKE CONDITION EXISTED AFTER THE LANDING. CORRECTIVE ACTION: MAINTENANCE FOUND THAT THE RIGHT PCDU CIRCUIT BREAKER HAD TRIPPED. THE PDCU WAS REPLACED AND THE CONTACTORS WERE CLEANED, THE DC BUS FEED C/B WAS REPLACED, AND THE MESSAGES WERE ALL CLEARED. A HIGH-ENERGY STOP INSPECTION RESULTED IN NO FINDINGS AND THE AIRCRAFT WAS RETURNED TO SERVICE. (LP #4716304)

Part: NONE — NONE · airframe 52,774 hrs · 36,358 cycles

SHIP 9522 -HYD/GEAR- THE AIRCRAFT EXPERIENCED A BIRD STRIKE WHICH DAMAGED HYDRAULIC LINES AND DUE TO THAT DAMAGE, LOSS FLUID OUT OF THE RIGHT HYDRAULIC SYSTEM. AN ALTERNATE GEAR EXTENSION WAS REQUIRED TO LOWER THE LANDING GEAR. AN EMERGENCY WAS DECLARED FOR THE APPROACH AND OTHERWISE UNEVENTFUL LANDING IN ATL. CORRECTIVE ACTION: MAINTENANCE FOUND THE RIGHT MLG BRAKE HOSES DAMAGED AS WELL AS DAMAGE TO THE MAIN LANDING GEAR DOORS. THE HOSES AND BOTH LANDING GEAR DOORS WERE ALL REPLACED. THE AIRCRAFT HAS RETURNED TO SERVICE. (LP #7278215)

Part: LIGHT — UNSERVICEABLE · airframe 52,299 hrs · 35,911 cycles

THE EVACUATION EXTERIOR EMERGENCY LIGHTS ON BOTH SIDES ARE INOPERATIVE. TRANSFER TO MEL 33-51-02A. NEEDS BATTERY. REPLACED OVERWING EMERGENCY LIGHT AND POWER SUPPLY BATTERY PER B717 AMM 33-51-06. NO HELP. REPLACED OVERWING EMERGENCY LIGHT POWER RELAY R2-273 PER B717 SWPM 20-20- 03. NO HELP. VERIFIED THAT BOTH BULBS ARE GOOD BUT NO POWER AT LIGHT ASSY PER B717 WDM 33-51-13. PER MCC OK TO CONT ON MEL REQUIRES FURTHER TS. CONTROL NUMBER ISSUED. (LP #6536435)

Part: SKIN — CRACKED · airframe 52,299 hrs · 35,911 cycles

CRACKS ON EXTERNAL FUSELAGE SKIN STA Y=1022 BTW LONG 13RH-14 RH (FUS). SUMMARY OF NRC 00029: FUSELAGE SKIN STA Y=1022 WAS REPAIRED PER PRI 599215-14 REV. 2 AND ER/A 599215-14 REV ORIGINAL SECTION I: PERMANENET REPAIR. ACCOMPLISH REPETITIVE INSPECTION WITHIN EVERY 24 MONTH INTERVAL AFTER 19MAY22 PER ER/A 599215-14 REV ORIG. SEC II. (LP #2243616)

Part: FRAME — CORRODED · corrosion level 2 · airframe 52,296 hrs · 35,910 cycles

CORROSION ON FRAME CLIP STA Y=927 BTW LONG 27LH TO 28RH AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00191: CORROSION LEVEL 2, FRAME CLIP STA Y=927 BTW LONG 27LH TO 28RH AT AFT CARGO COMPARTMENT WAS REPLACED PER B717 SRM 51-41-02-0G, SRM 51-41-05-0G. (LP #2242428)

Part: TRACK — CORRODED · corrosion level 2 · airframe 52,296 hrs · 35,910 cycles

CORROSION ON RH TIE TRACK BTW STA Y=896-954 AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00098: CORROSION LEVEL 2, TIE TRACK WAS REPLACED PER B717 SRM 51-41-01-0G BECAUSE IT IS OUT OF LIMITS PER B717 SRM-53-20-52-1A-2 PAR 4 FIG 101 AND B717 DC-MD/BOEING NDT MANUAL 04-00-06 PART 4. (LP #2242009)

Part: NONE — NONE · airframe 52,296 hrs · 35,910 cycles

CRACKS ON EXTERNAL FUSELAGE SKIN STA Y=1076 AND Y=1087 BTW LONG 13RH-14RH (FUS). SUMMARY OF NRC 00030: EXTERNAL FUSELAGE SKIN STA Y=1076 AND Y=1087 BTW LONG 13RH-14RH WAS REPAIRED PER ER/A 599216-14 REV. ORIGINAL SECTION L: PERMANENT REPAIR AND PRI 599216-14 REV. 1 TIME CONTROLLED ITEMS. ACCOMPLISH REPETITIVE INSPECTION WITHIN EVERY 24 MONTH INTERVAL AFTER 17MAY22 LOG PAGE #2240770. ASSOCIATED ER/A 14-599216 ADDED FOR AC 9522. (LP #2241250)

Part: BATTERY PACK — INOPERATIVE · airframe 52,296 hrs · 35,910 cycles

ER/A 599216-14, FUSELAGE SKIN AT Y=1076 AND Y=1087, L-13R TO L-14R HAS CRACKS. SUBJECT REPAIR REQUIRES FOLLOW-ON REPETITIVE INSPECTIONS. ACCOMPLISH ER/A 599216-14, SECTION II REPETITIVE INSPECTION WITHIN EVERY 24 MONTH INTERVAL AFTER 17MAY22. ASSOCIATED ER/A 14-599216 ADDED FOR AC 9522. PLACED ON MONITOR. WIP. (LP #2240770)

Part: SKIN — DEBONDED · airframe 52,296 hrs · 35,910 cycles

DISBOND (0.700 IN LENGTH X 0.700 IN WIDTH) ON RHS I/B FIXED VANE, UPPER SKIN 60.5 IN FROM I/B END AND 5.5 IN FROM T/E. SUMMARY OF NRC 00317: INBOARD FIXED VANE, UPPER SKIN AT RH WING WAS REPAIRED PER B-717-200 SRM 51-70-02-0G PROCEDURE GENERAL IN REFERENCE OF B-717 SRM 57-53-01-2R-1. (LP #2238650)

Part: NONE — NONE · corrosion level 2 · airframe 52,296 hrs · 35,910 cycles

CORROSION ON FRAME CLIP STA Y=908 BTW LONG 28LH TO 28 RH AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00190: LEVEL CORROSION 2, FRAME CLIP STA Y=908 BTW LONG 28LH TO 28 RH AT AFT CARGO COMPARTMENT WAS REPLACED PER B717 SRM 51-41-02-0G. (LP #2239592)

Part: SKIN — DEBONDED · airframe 52,296 hrs · 35,910 cycles

IN REF NRC 00116: ONE DISBOND WAS FOUND ON DENT STA XV1=143 OF 1.500 IN X 1.100 IN LENGTH / WIDTH ON INBOARD FIXED VANE UPPER SKIN AT LH WING. SUMMARY OF NRC 00311: INBOARD FIXED VANE UPPER SKIN AT LH WING WAS REPAIRED PER B-717-200 SRM 51-70-02-0G PROCEDURE GENERAL IN REFERENCE OF B-717 SRM 57-53-01-2R-1. (LP #2238637)

Part: NONE — NONE · airframe 52,296 hrs · 35,910 cycles

CRACK ON BEAM #1 STA=160 AT PASSENGER ENTRANCE DOOR (L1). SUMMARY OF NRC 00089: BEAM #1, STA=160 AT PASSENGER ENTRANCE DOOR (L1) WAS REPAIRED PER B-717 SRM 52-10-02-2R REPAIR 7. (LP #2237275)

Part: NONE — NONE · corrosion level 2 · airframe 52,296 hrs · 35,910 cycles

CORROSION ON DOUBLER STA Y=1053 IN FRONT BULKHEAD LONG 30 AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00210: CORROSION LEVEL 2, DOUBLER STA Y=1053 IN FRONT BULKHEAD LONG 30 AT AFT CARGO COMPARTMENT WAS REPLACED PER B717 DWG 5910130-61 REV. ET AND SRM 51-41-05-0G. (LP #2235751)

Part: DOUBLER — CORRODED · corrosion level 2 · airframe 52,296 hrs · 35,910 cycles

CORROSION ON DOUBLERS ON FWD AND AFT CUT OUT AT FWD CARGO COMPARTMENT. SUMMARY OF NRC 00016: CORROSION LEVEL 2, DOUBLERS ON FWD AND AFT CUT OUT AT FWD CARGO COMPARMENT WERE REPLACED PER B717 SRM 53- 20-15-2R-6 FIG. 201. (LP #2229744)

Part: BATTERY — DISCHARGED (CABIN) · airframe 51,843 hrs · 35,577 cycles

THE EXTERNAL OVERWING EMERGENCY LIGHTS FAILED TO ILLUMINATE. MAINTENANCE REPLACED THE BATTERY AND POWER SUPPLY PER AMM 33-51. OPERATIONAL CHECK WAS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 51,161 hrs · 35,059 cycles

THE TAIL COMPARTMENT EMERGENCY WALKWAY LIGHTS ARE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY AND BATTERY PACK B5-260 PER B717 AMM 33-51. OPERATIONAL CHECK IS GOOD. (LP #6411951)

Part: SKIN PANEL — DELAMINATED (LT SPOILER)

INITIAL INSPECTION, DELAMINATED AREAS ON EXTERNAL WING SPOILER PANEL, UPPER AND LOWER SURFACE.

Part: FRAME — CRACKED (FUSELAGE) · airframe 49,231 hrs · 33,696 cycles

HFEC INSPECTION OF RH OVERWING EXIT FRAME STA Y=715.000 SHOWS CRACK INDICATION GREATER THAN 0.125" AT THE UPPER RADIUS OF THE FRAME TAB REF STEP 13 OF 5310-01436-01D. REPLACED FRAME PER WORK CARD 000-0001:5310-01436-03B AND NRC 37. (LP #0906405)

Part: THRESHOLD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,231 hrs · 33,696 cycles

LIGHT CORROSION FOUND AT AFT CARGO DOOR THRESHOLD. REF NRC 0058: REPLACED AFT CARGO DOOR JAMB PAN REF SRM 53-20-15-2R-7. (LP #0902258)

Part: CHARGER — INOPERATIVE (EMERGENCY LIGHTS) · airframe 48,309 hrs · 33,075 cycles

DURING A SERVICE CHECK, MAINTENANCE FOUND THAT THE TAIL COMPARTMENT EMERGENCY LIGHTS WERE INOPERATIVE. MAINTENANCE REPLACED THE CHARGER AND BATTERY B5-260 IAW IAW AMM 33-51-03. OPS CHECKED GOOD.

Part: ACCESS PANEL — DAMAGED (LT ELEVATOR) · airframe 47,862 hrs · 32,762 cycles

FOUND DAMAGED ACCESS PANEL ON LT ELEVATOR INBD. MANUFACTURED NEW ACCESS PANEL PER DRAWING 5910412. TREATED AND PAINTED PER SRM 51-22-01-0G. OKAY FOR SVC.

Part: FRAME — CORRODED (BS 889) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

AFT CARGO BAY HAS CORROSION OUT OF LIMITS ON FRAME BS 889, LONGERON 30. REPAIRED IAW ETI-17-17-015 AND ER/A 554106-14 REV. ORIGINAL.

Part: SKIN — DAMAGED (BS 947) · airframe 44,348 hrs · 30,358 cycles

ELONGATED HOLES IN FUSELAGE SKIN BS 947 LONGERON 26L. THE DAMAGE WAS REPAIRED IAW ERA 554117-14, REV ORIGINAL, SECTION II.

Part: LONGERON — DAMAGED (BS 947) · airframe 44,348 hrs · 30,358 cycles

AFT CARGO BAY HAS AN ELONGATED HOLE ON LONGERON 26L, BS 947. REPAIRED IAW ER/A 554117-14, REV ORIGINAL, SECTION II.

Part: CARGO TRACK — CORRODED (CARGO BAY) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

AFT CARGO COMPARTMENT HAS CORROSION OUT OF LIMITS ON LT TIE TRACK BTW STA Y=898 TO 1022 (AMDS 5331-2001) (REF CARD 00286) (CCT). DUE TO EXCESSIVE CORROSION TIE TRACK WAS REPLACED BTW STA Y=898 TO Y=1022 PER SRM 51-41-01, 51-41-02, 51-41-05, AND DWG 5936663 REV W PL REV Y.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 44,348 hrs · 30,358 cycles

CRACKED LT ANGLE AT UPPER SURFACE CENTER WING STA Y=715, X=44, Z=-9. (CPAX). REPAIR PARTS WERE INSTALLED PER ETI-17-17-006 R2 & ER/A 554082-14 REV ORIGINAL.

Part: FASTENER — SHEARED (VERTICAL STAB) · airframe 44,348 hrs · 30,358 cycles

SHEARED FASTENER ON DORSAL FIN ANGLE STA Y=1152 BTW LONGS: 2-3 (STA). REPAIR WAS ACCOMPLISHED PER ETI-17-17-005 R2 AND ER/A 554078-14 REV ORIGINAL.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

CORROSION ON FUEL TANK ACCESS PANEL 520GB. THE ACCESS PANEL WAS REPLACED IAW SRM 57-10-01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

CORROSION ON ACCESS PANEL 520CB. THE ACCESS PANEL WAS REPLACED IAW SRM 57-10-01.

Part: SUPPORT — CORRODED (BS 832) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

CORROSION ON PANEL SUPPORT BS 832, LONGERONS 24 - 30L. REPAIRED IAW SRM 51-70-11 REP. 1.

Part: TAB — CRACKED (RUDDER) · airframe 44,348 hrs · 30,358 cycles

VERTICAL STABILIZER IS BENT AND CRACKED ON UPPER CORNER OF RUDDER TAB. RUDDER CONTROL TAB WAS REPAIRED IN ACCORDING CAR 2000-8149-02 JOB 000-0006 AND SRM 55-41-01 REPAIR 1 AND RUDDER CONTROL TAB BALANCE WAS ACCOMPLISHED.

Part: PAN — CRACKED (CARGO DOOR) · airframe 44,348 hrs · 30,358 cycles

FWD CARGO COMPARTMENT DOOR HAS A CRACK ON INNER PAN STA Y=427 BTW BEAM 4 AND 2. PAN WAS REPAIRED PER SRM 52-30-02 REP 1 FIG 201, 51-41-02, AND 51-41-05, CRACK .281", .781" AND 1".

Part: TEE FITTING — CRACKED (BS 954) · airframe 44,348 hrs · 30,358 cycles

AFT CARGO DOOR FRAME HAD A CRACKED TEE FITTING BS 954 IN BEAM 4. THE TEE FITTING WAS REPLACED IAW SRM 51-41-01 AND 51-41-05.

Part: TEE FITTING — CRACKED (BS 994) · airframe 44,348 hrs · 30,358 cycles

AFT CARGO DOOR OPENING HAD A CRACKED TEE FITTING BS 994 IN BEAM 2. THE TEE FITTING WAS REPLACED PER B717 SRM 51-41-05 AND 51-41-02 AND DWG #9957665 REV R.

Part: FLOOR PANEL — BROKEN (CABIN) · airframe 44,348 hrs · 30,358 cycles

PAX CABIN FLOOR PANEL 223BF IN REF CARD 2040-0024 IS BROKEN. FLOOR PANEL 223BF WAS REPLACED PER SRM 53-20-50.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 44,736 hrs · 30,628 cycles

CORROSION ON UPPER SKIN AFT EDGE AT X 13, X 28, X 31, X 32 TO 36, AND X 40 TO 60 RIGHT. A REPAIR WAS ACCOMPLISHED IAW ER/A 554092-14, REV ORIGINAL, AND ETI-17-17-008, REV 1.

Part: FRAME — CRACKED (BS 47) · airframe 44,348 hrs · 30,358 cycles

CRACK ON NLG FRAME AT BS 47. THE FRAME WAS REPAIRED IAW SRM 53-10-14 FIG. 201 REPAIR 2.

Part: LONGERON — CRACKED (BS 1152) · airframe 44,348 hrs · 30,358 cycles

AFT ACCESSORY COMPARTMENT HAS A CRACKED LONGERON 3R, BS 1152. THE LONGERON WAS REPAIRED IAW SRM 53-00-05 FIG. 201 REPAIR 2.

Part: CUSP WEB — CRACKED (BS 825) · airframe 44,348 hrs · 30,358 cycles

CRACK ON LEFT CUSP WEB LBL 45, BS 825. THE CUSP WEB WAS REPLACED IAW SRM 51-41-02 AND 51-41-05.

Part: SKIN — PUNCTURED (LT WING TE FLAP) · airframe 44,348 hrs · 30,358 cycles

PUNCTURED LOWER SKIN OF AFT MOVABLE FLAP VANE. REPAIRED IAW SRM 57-53-01 REPAIR 1 FIG. 201.

Part: DOUBLER — CORRODED · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

SEVERAL CORROSION POINTS ON WEB UNDER FLOOR PANEL 211ANF. A DOUBLER WAS FABRICATED IAW DWG 9936533 REV CM. A NEW SUPPORT WAS INSTALLED IAW SRM 51-41-02, 51-41-05, AND 51-41-01.

Part: DOUBLER — CRACKED (BS 176) · airframe 44,348 hrs · 30,358 cycles

CRACKED DOUBLER BETWEEN BEAMS 3 & 4 ON FWD SERVICE DOOR BS 176.5. REPLACED IAW SRM 51-41-02, 51-41-05, AND DWG 9911582 REV T.

Part: WEB — CRACKED · airframe 44,348 hrs · 30,358 cycles

CRACKED WEB BELOW CAP PLATE. THE WEB WAS REMOVED AND REPLACED IAW SRM 51-41-02, 51-41-05 AND DWG 5910084 REV EM.

Part: BEAM — CRACKED (SERVICE DOOR) · airframe 44,348 hrs · 30,358 cycles

CRACKED FWD EDGE OF BEAM NR 4 AT FWD SERVICE DOOR. THE BEAM WAS REPLACED IAW DWG 9911582 REV T AND SRM 51-41-01, 51-41-02, AND 51-41-05.

Part: KEELBEAM — CRACKED (BS 680-696) · airframe 44,348 hrs · 30,358 cycles

LH KEEL BEAM INTERNAL STRUCTURE CRACKED AT BS 680 - 696, LONGERONS 25 - 29L. REPAIRED IAW SRM 51-70-11 REP 1.

Part: CUSP WEB — CORRODED (BS 389-408) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

CORROSION ON RIGHT CUSP WEB DOUBLER BETWEEN BS 408 - 389. REPAIR AND REPLACED IAW SRM 53-00-55 REP 4 FIG 210.

Part: KEELBEAM — CRACKED (BS 680-716) · airframe 44,348 hrs · 30,358 cycles

RIGHT KEEL BEAM INTERNAL STRUCTURE CRACKED BS 680, 696, AND 716, LONGERONS 25 - 29R. REPAIRED IAW SRM 51-70-11 REP 1.

Part: SEAT TRACK — CORRODED (BS 940) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

EXCESSIVE CORROSION ON RT SEAT TRACK RBL 22 AND BS 940. THE DAMAGE WAS REMOVED IAW SRM 53-20-52 REP.1. PLUG AND CHANNEL WERE INSTALLED IAW SRM 53-20-52 REP.1 AND SRM 51-41-01.

Part: ACCESS PANEL — CORRODED · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

CORROSION ON FUEL TANK ACCESS PANEL 620CT. THE ACCESS PANEL WAS REPLACED IAW SRM 57-10-01.

Part: SPLICE — CORRODED (BS 636-655) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

CORROSION ON RT LOWER ANGLE CUSP SPLICES BETWEEN BS 636 - 655. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-00 FIG. 1. REPLACED THE SPLICE IAW SRM 51-41-05.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

RT WING CORROSION ON FUEL TANK ACCESS PANEL 520CT. THE ACCESS PANEL WAS REPLACED IAW SRM 57-10-01.

Part: PAN — CRACKED (SERVICE DOOR) · airframe 44,348 hrs · 30,358 cycles

CRACKED FWD PAN ON BEAM NR 4 AREA AT FWD SERVICE DOOR. REPAIRED IAW SRM 52-00-00 FIG. 202.

Part: FLOORBEAM — CRACKED (BS 655) · airframe 44,348 hrs · 30,358 cycles

CRACK ON FLOOR SUPPORT BS 655, LBL 22 - RBL 22. THE FLOORBEAM WAS REMOVED AND REPLACED IAW SRM 51-41-02, SRM 53-20-51 FIGURE 1, SRM 51-10-04 PAR 15 AND 21, AND SRM 51-41-02.

Part: FLOOR PANEL — DELAMINATED (NOT REPORTED) · airframe 44,348 hrs · 30,358 cycles

DELAMINATION ON FLOOR PANEL. FABRICATED A NEW FLOOR PANEL SRM 53-20-50 REPAIR 3.

Part: FLOOR SUPPORT — CORRODED (BS 160-200) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

CORROSION ON FLOOR SUPPORT BETWEEN BS 160 - 200 LBL 54. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-40-08, SRM 51-41-02, AND SRM 51-41-05.

Part: CUSP WEB — CORRODED (BS 512) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

CORROSION ON LT CUSP WEB BS 512 BTW LBL 54-60 . REPAIRED IAW SRM 53-00-55 FIG. 215 REPAIR 4.

Part: CUSP WEB — CRACKED (BS 835) · airframe 44,348 hrs · 30,358 cycles

CRACKED LT CUSP WEB BS 835, LBL 53. THE CUSP WEB WAS REPAIRED IAW SRM 53-00-55 REP 4.

Part: FLOOR SUPPORT — CORRODED (BS 1022-1053) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

CORROSION ON FLOOR SUPPORT LBL 54, BS 1022 - 1053. THE SUPPORT WAS REMOVED IAW SRM 51-41-05 AND A NEW FLOOR SUPPORT PREPAIRED IAW SRM 51-20-08 AND INSTALLED IAW SRM 51-41-05.

Part: CUSP WEB — CORRODED (BS 569) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

CORROSION ON LT CUSP WEB BS 569 BTW LBL 54 AND 60 AT PAX CABIN . REPAIRED IAW SRM 51-41-05 AND 53-00-55 REPAIR 4.

Part: CUSP WEB — CORRODED (BS 494) · corrosion level 2 · airframe 44,348 hrs · 30,358 cycles

CORROSION ON LT CUSP WEB BS 494 BTW LBL 54-60. REPAIRED IAW SRM 53-00-55 REPAIR 4, SRM 51-41-02, AND SRM 51-41-05.

Part: PAN — CRACKED (BS 561-599) · airframe 44,348 hrs · 30,358 cycles

CRACKS ON THE LT FWD LOWER RING PAN BS 561 - 599. REPAIRED IAW SRM 56-20-02.

Part: PAN — CRACKED (BS 758) · airframe 44,348 hrs · 30,358 cycles

CRACK ON RT UPPER FWD CORNER OF RING PAN AT BS 758. WINDOW RING PAN WAS REPAIRED IAW SRM 56-20-02.

Part: ANGLE — CRACKED (SERVICE DOOR) · airframe 44,348 hrs · 30,358 cycles

CRACKED ANGLE ON BEAM AT FWD SERVICE DOOR. THE ANGLE WAS REPLACED IAW SRM 51-41-02.

Part: BEAM — CRACKED (PAX DOOR) · airframe 44,348 hrs · 30,358 cycles

CRACKED FWD EDGE OF BEAM AT FWD ENTRY DOOR. REPAIRED IAW SRM 52-10-02 FIG. 202.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 41,688 hrs · 28,289 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHTING EXIT SIGN IN MID-CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACKS FOR THE NOTED LIGHTED AREAS AND THE OPS CHECK WAS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 41,620 hrs · 28,229 cycles

DURING LINE CHECK, NOTED EMERGENCY LIGHTS WERE INOPERATIVE FROM ROWS 1-19. REPLACED APPLICABLE BATTERY PACKS AND OPERATION CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 40,776 hrs · 27,535 cycles

DURING LINE CHECK, NOTED EMERGENCY LIGHTS IN AFT ACCESSORY COMPARTMENT WERE INOPERATIVE. REPLACED BATTERY PACK AND OPS NORMAL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 38,438 hrs · 25,814 cycles

EXTERIOR OVERWING EMERGENCY EVACUATION LIGHTS INOPERATIVE. R & R BATTERY PACK IAW AMM.

Part: SIGN — DAMAGED (CABIN) · airframe 36,738 hrs · 24,714 cycles

FORWARD CABIN CEILING EXIT SIGN DAMAGED. R&R SIGN IAW AMM.

Part: BATTERY — DISCHARGED (FLASHLIGHT) · airframe 36,782 hrs · 24,737 cycles

AFT FLASHLIGHT POSITION INOPERATIVE. R&R BATTERY IAW SIP.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED AT BS 617, RBL 56. REPAIRED WEB IAW SRM.

Part: FRAME — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

FRAME CORRODED AT BS 927, BETWEEN LONGERON 29L TO LONGERON 29R. REPAIRED FRAME IAW SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

LEFT CUSP WEB CRACKED AT STATION 674, LBL 45. REPAIRED WEB IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

FRAME CRACKED AT STA 674, LONGERON 18R. REMOVED AND REPLACED FRAME IAW SRM.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

FORWARD CARGO PIT AFT BULKHEAD FWD FACE OF RIGHT CENTER FUEL CELL CRACKED STIFFENER. REMOVED AND REPLACED STIFFENER IAW SRM AND DWG.

Part: FRAME — CORRODED (FUSELAGE) · airframe 35,888 hrs · 24,196 cycles

FRAME CORRODED AT BS 927, BETWEEN LONGERON 29L TO LONGERON 29R. REPAIRED FRAME IAW SRM.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

AFT PRESSURE BULKHEAD CORRODED AT BS 1053, BETWEEN LONGERON 28R AND 29R. REMOVED AND REPLACED DOUBLER IAW SRM AND DWG.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

LONGERON CRACKED AT BS 1133, LONGERON 2L. REPAIRED LONGERON IAW SRM AND DWG.

Part: PAN — CRACKED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

WINDOW FRAME RING PAN CRACKED AT STA 638, ABOVE 45L. REMOVED AND REPLACED WINDOW RING PAN IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED AT BS 532, RBL 56.0. REMOVED AND REPLACED WEB IAW SRM.

Part: CUSP WEB — DELAMINATED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB DELAMINATED AT STA 400, RBL 56. REMOVED AND REPLACED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED AT BS 266, RBL 56.0. REMOVED AND REPLACED CUSP WEB IAW SRM.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CENTER SECTION SUPPORT CRACKED AT STA 737, RBL 44. REMOVED AND REPLACED SUPPORT IAW SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CRACKED BETWEEN STA 655 TO STA 674, RBL 56. REPAIRED WEB IAW SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

SEAT TRACK CORRODED BETWEEN BS 899 TO BS 970, LBL 44.5. REMOVED AND REPLACED TRACK IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED BETWEEN BS 541 TO BS 560, RBL 56.0. REPAIRED WEB IAW SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

SEAT TRACK CORRODED BETWEEN BS 515 TO BS 579, RBL 44.5. REMOVED AND REPLACED TRACK IAW SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

SEAT TRACK CORRODED BETWEEN BS 607 TO BS 640, RBL 44.5. REMOVED AND REPLACED TRACK IAW SRM.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

METAL FLOOR PANEL CORRODED BETWEEN BS 775 AND BS 800, LBL 44.5. REPAIRED PANEL IAW SRM.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CENTER SECTION SUPPORT CRACKED AT SEAT TRACK STA 737, LBL 44. REMOVED AND REPLACED SUPPORT IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED AT STA 338, RBL 56. REMOVED AND REPLACED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED AT STA 380, RBL 56. REPAIRED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED BETWEEN STA 832 TO STA 851, RBL 56.0. REMOVED AND REPLACED WEB IAW SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

SEAT TRACK CORRODED BETWEEN STA 607 TO STA 640, RBL 22.5.78. REMOVED AND REPLACED TRACK IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED BETWEEN STA 408 TO STA 427, RBL 56. REMOVED AND REPLACED WEB IAW SRM.

Part: DOUBLER — CRACKED (LT PYLON) · airframe 35,347 hrs · 23,868 cycles

NR 1 PYLON SKIRT FAIRING CRACKED AT LOWER ENGINE COWL, 2ND FROM FWD HINGE ATTACH POINT. REMOVED AND REPLACED DOUBLER IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED BETWEEN STA 304 TO STA 313, RBL 56. REMOVED AND REPLACED WEB IAW SRM.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

LONGERON CRACKED AT BS 1133, LONGERON 2R. REPAIRED LONGERON IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED BS 480, RBL 56. REMOVED AND REPLACED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED BETWEEN STA 598 TO STA 617, RBL 56. REMOVED AND REPLACED WEB IAW SRM.

Part: BONDING STRAP — CRACKED (RT WING) · airframe 35,347 hrs · 23,868 cycles

RIGHT WING LEADING EDGE AT ROOT WING BONDING STRAP CRACKED AT BOTTOM SIDE. REMOVED AND REPLACED STRAPS IAW SRM.

Part: PIN — LOOSE (R1 DOOR) · airframe 35,347 hrs · 23,868 cycles

R1 DOOR EMERGENCY EVAC SLIDE LOWER CONTAINMENT PIN LOOSE. SECURED PIN IAW AMM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED BETWEEN STA 655 TO STA 675, LBL 56. REMOVED AND REPLACED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED AT STA 704, LBL 56. REMOVED AND REPLACED WEB IAW SRM.

Part: WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED BETWEEN STA 598 TO STA 617, LBL 56. REMOVED AND REPLACED CUSP WEB IAW SRM.

Part: FRAME — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

FRAME CORRODED AT BS 908, LONGERON 28LTO LONGERON 29R. REPAIRED FRAME IAW SRM.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB DOUBLER CORRODED AT BS 589, LBL 56. REMOVED AND REPLACED ANGLE IAW SRM AND DWG.

Part: FRAME — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

FRAME CORRODED BETWEEN BS 927 TO BS 954, LONGERON 29L. REMOVED AND REPLACED FRAME SECTION IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 35,347 hrs · 23,868 cycles

MAIN CABIN FLOOR PANEL 222PF DELAMINATED. REMOVED AND REPLACED PANEL IAW SRM.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

SUPPORT ANGLE CORRODED AT STA 935, LONG 30. REMOVED AND REPLACED ANGLE IAW SRM AND DWG.

Part: GUSSET — CRACKED (CARGO BAY) · airframe 35,347 hrs · 23,868 cycles

C-2 DOOR CARGO BARRIER UPPER HINGE FORWARD ATTACH GUSSET CRACKED AT FASTENERS. REMOVED AND REPLACED GUSSET IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED BETWEEN BS 522 TO BS 541, LBL 56. REMOVED AND REPLACED CUSP WEB IAW SRM AND AMM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 35,347 hrs · 23,868 cycles

MAIN CABIN FLOOR PANEL 222AAF DELAMINATED. REMOVED AND REPLACED PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 35,347 hrs · 23,868 cycles

MAIN CABIN FLOOR PANEL 222AMF DELAMINATED. REPAIRED PANEL IAW SRM.

Part: GUSSET — CRACKED (CARGO BAY) · airframe 35,347 hrs · 23,868 cycles

C-2 DOOR CARGO BARRIER UPPER HINGE, AFT ATTACH GUSSET CRACKED AT FASTENERS. REMOVED AND REPLACED GUSSET IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 35,347 hrs · 23,868 cycles

MAIN CABIN FLOOR PANEL 222ATF DELAMINATED. REPAIRED PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 35,347 hrs · 23,868 cycles

MAIN CABIN FLOOR PANEL 222ACF DELAMINATED. REPAIRED PANEL IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

CUSP WEB CORRODED AT BS 727, LBL 56. REMOVED AND REPLACED WEB IAW SRM.

Part: FORMER — CRACKED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

AFT FUSELAGE FORMER CRACKED AT FWD SIDE OF FS 1022 BULKHEAD, BETWEEN L-15L AND L-14L. REMOVED AND REPLACED FORMERS IAW SRM.

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 35,347 hrs · 23,868 cycles

MAIN CABIN FLOOR PANEL 222 AVF DELAMINATED. REPAIRED PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 35,347 hrs · 23,868 cycles

MAIN CABIN FLOOR PANEL 222ABF DELAMINATED. REPAIRED PANEL IAW SRM.

Part: FRAME — CORRODED (FUSELAGE) · airframe 35,888 hrs · 24,196 cycles

FRAME CORRODED AT BS 908, LONGERON 28LTO LONGERON 28R. REPAIRED FRAME IAW SRM.

Part: DOUBLER — CRACKED (NLG WW) · airframe 35,347 hrs · 23,868 cycles

NLG STRUT DOOR AFT HINGE CUTOUT RIGHT CRACKED. REMOVED AND REPLACED DOUBLER IAW AMM AND SRM.

Part: PAN — CORRODED (FUSELAGE) · airframe 35,888 hrs · 24,196 cycles

AFT CARGO COMPARTMENT DOOR LOWER JAMB PAN CORRODED. REMOVED AND REPLACED JAMB PAN IAW SRM.

Part: PAN — CORRODED (CARGO DOOR) · airframe 35,347 hrs · 23,868 cycles

FWD CARGO COMP C-1 DOOR PAN CORRODED. REPAIRED PAN IAW SRM.

Part: LIGHT — BROKEN (CABIN) · airframe 35,347 hrs · 23,868 cycles

RIGHT EMERGENCY LIGHT FIXTURE BROKEN ON LOWER INBD CORNER AT ROW 17. REMOVED AND REPLACED LIGHT IAW MM.

Part: DOUBLER — CRACKED (NLG WW) · airframe 35,347 hrs · 23,868 cycles

NLG STRUT DOOR AFT HINGE CUTOUT LEFT CRACKED. REMOVED AND REPLACED DOUBLER IAW AMM AND SRM.

Part: PAN — CORRODED (CARGO DOOR) · airframe 35,347 hrs · 23,868 cycles

AFT CARGO COMPARTMENT C-2 DOOR PAN CORRODED. REMOVED AND REPLACED PAN IAW SRM.

Part: LENS — MISSING (CABIN) · airframe 34,822 hrs · 23,526 cycles

LANS COVER MISSING FOR ONE EMERGENCY ESCAPE PATH LIGHT ASSY ON SEAT 2D. INSTALLED LENS REF AMM.

Part: FLASHLIGHT — INOPERATIVE (CABIN) · airframe 33,590 hrs · 22,678 cycles

AFT EMERGENCY FLASHLIGHT INOP. REMOVED AND REPLACED FLASHLIGHT PER AMM.

Part: SIGN — INOPERATIVE (CABIN)

R1 OVHD EXIT SIGN NOT LIT. RELAMPED, OPS CHECK GOOD.

Part: GALLEY — CORRODED (CABIN)

GALLEY COFFEEMAKER COMPARTMENTS 102, 103 AND 106 LOWER SURFACE, CORROSION. ACCOMPLISHED LOWER SURFACE REPLACEMENT PER EA 17-25-03222IR.

Part: VANE — DENTED (TE FLAP)

RIGHT AFT MOVEABLE VANE, DENTED. ACCOMPLISHED MOVEABLE VANE FILLER AND DOUBLER REPAIR PER B717 SRM 57-53-01 REPAIR 1 AND B717 SRM 51-70-02 REPAIR 3.

Part: PANEL — CORRODED (FUSELAGE)

GALLEY ENTRANCE DOOR JAMB GAP PANEL, CORROSION. ACCOMPLISHED DOOR JAMB GAP PANEL REPLACEMENT PER B717 SRM 51-41-01.

Part: PANEL — CORRODED (FUSELAGE)

GALLEY ENTRANCE STRAP PANEL, CORROSION. ACCOMPLISHED STRAP PANEL REPLACEMENT PER B717 SRM 51-41-02.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 237, RBL 44.5, CORROSION. ACCOMPLISHED SEAT TRACK SPLICE REPAIR PER B717 SRM 53-20-52 AND BOEING DWG SR09530085.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 188, RBL 44, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 237, RBL22, CORROSION. ACCOMPLISHED SEAT TRACK SPLICE REPAIR PER B717 SRM 53-20-52 AND BOEING DWG SR09530085.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 237, LBL 15 TO RBL 15, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02 AND B717 SRM 51-41-05.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 188, LBL 5 TO RBL 5, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: WEB — CORRODED (FUSELAGE)

CABIN FLOOR WEB, STA 200, RBL 22, CORROSION. ACCOMPLISHED FLOOR WEB DOUBLER REPAIR PER B717 SRM 51-70-10 FIG 201 REPAIR 2.

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 170, RBL 7 TO RBL 44, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02 AND B717 SRM 51-41-05.

Part: FINGER DOUBLER — CRACKED (FUSELAGE)

CABIN LONGERON FINGER DOUBLER, STA 209, LONG L15L, CRACKED. ACCOMPLISHED LONGERON FINGER DOUBLER FILLER AND DOUBLER REPAIR PER B717 SRM 51-70-10 FIG 201 REPAIR 2 AND B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 200, RBL 9 TO RBL 45, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: RIB — CRACKED (RT WING)

RT WING L/E AT STA XRS 264 RIB CRACKED. REMOVED AND REPLACED RIB ON RT WING L/E AT STA XRS 264 PER B717 SRM 51-41-02, 51-41-05.

Part: LENS — MISSING (CABIN)

EMERGENCY LIGHT LENS MISSING AT SEAT 29-D. INSTALL A NEW LIGHT LENS AT SEAT 29-D IAW B-717 CMM 33-51, OPS CHECK GOOD.

Part: PAN — CORRODED (FUSELAGE)

FWD CARGO DOOR SILL LOWER PAN CORRODED BEYOND LIMITS. REPLACED PAN PER B717 SRM 53-20-15.

Part: SKIN — CRACKED (FUSELAGE)

FUSELAGE SKIN HAS 2.5 INCH CRACK THROUGH LAP SEAM RIVETS AT STA 1022 LONG 14L. REPAIRED PER AIRTRAN EA 17-53-01127IR.

Part: PAN — CORRODED (FUSELAGE)

AFT CARGO DOOR LOWER PAN CORRODED BEYOND LIMITS. REPLACED PAN PER B717 SRM 53-20-15.

Part: PAN — CRACKED (CARGO BAY)

AFT CARGO DOOR PAN CRACKED FWD EDGE AT LOCKING CAM. INSTALLED DOUBLER REPAIR AT AFT CARGO PAN IAW B717 SRM 52-30-2 FIG 201. MATERIAL USED FOR OUT PAN 7075 0.050, HEAT TREATED TO 7075T6. PER AVBORNE SPEC 98PMS.247PS-01, SIZE 7.5" X 2" X 3.25 LONG AND FOR INNER PAN 2024T3.063 6.75" LONG.

Part: PAN — CRACKED (AFT CARGO DOOR)

AFT CARGO DOOR PAN CRACKED FWD EDGE AT LOCKING CAM. INSTALLED DOUBLER REPAIR AT AFT CARGO PAN IAW B717 SRM 52-30-2 FIG 201. MATERIAL USED FOR OUT PAN 7075 0.050, HEAT TREAT TO 7075T6 PER AVBORNE SPEC 98PMS.247PS-01, SIZE 7.5" X 2" X 3.25" LONG AND FOR INNER PAN 2024T3.063, 6.75" LONG.

Part: PSU — INOPERATIVE (ROW 30 DEF)

DURING MAINT, FOUND OXYGEN GENERATOR AT ROW 30DEF FIRED. OXYGEN MASKS IMPROPERLY STOWED. REMOVED AND REPLACED OXYGEN GENERATOR AND PSU.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS)

EMERGENCY LIGHTS AT BUSINESS SEATS AND FRONT ROW COACH INOPERATIVE. FOUND WRONG LAMPS INSTALLED SEAT ROWS 1-10. RELAMPED EPL ROWS 1-10. REMOVED AND REPLACED EMERGENCY BATTERY ASSEMBLY B5-118. ALSO REPAIRED LOOSE CONNECTION AT ROW 10, EMERGENCY LIGHTS OPS CHECK NORMAL REF WDM 33-51-141, 33-51-144, MM 33-51.

Part: ATTACH FITTING — CRACKED (FUSELAGE)

RIGHT LOUVER ATTACH FITTING ON RIGHT SIDE OF TAIL COMPARTMENT CRACKED. INSTALLED DOUBLER REPAIR AT RIGHT HAND LOUVER IAW AIRTRAN T/C 17-5320-2023 FIG 1.

Part: FITTING — CRACKED (TAIL)

RIGHT LOUVER ATTACH FITTING ON RIGHT SIDE OF TAIL COMPARTMENT CRACKED. INSTALLED DOUBLER REPAIR AT RIGHT LOUVER IAW AIRTRAN T/C 17-5320-2023.

Part: SKIN — DENTED (FUSELAGE)

DENT FOUND AT FS 229 AND STRINGER L-18 ON LT SIDE OF FUSELAGE JUST AFT OF L-1 DOOR - 2 INCH WIDE BY 4.35 INCHES LONG MAX DEPTH OF DENT .091. INSTALLED DOUBLER REPAIR AT STA 229 TO STA 245.5 BETWEEN L-16 TO L-18 IAW B717 SRM 53-00-01 REP 6. MATERIAL USED FILLER 2024 T3 .050 SIZE 16.75" X 14.125". DOUBLER 2024 T3.063 23.5" X 4", FINGER DOUBLER 2024T3.063 32.5" X 5.75".

Part: SKIN — DENTED (BS 229 S18L)

DENT FOUND AT FS 229 AND STRINGER L-18 ON LT SIDE OF FUSELAGE JUST AFT OF L-1 DOOR - 2 INCH WIDE BY 4.35 INCHES LONG MAX DEPTH OF DENT .091. INSTALLED DOUBLER REPAIR AT STA 229 TO STA 245.5 BETWEEN L-16 TO L-18 IAW B717 STM 53-00-01 REPAIR 6. MATERIAL USED FILLER 2024 T3 .050 SIZE 16.75" X 14.125". DOULBER 2024 T3.063, 23.5" X 4", FINGER DOUBLER 2024T3.063 32.5" X 5.75".