N717JL

Part: SIGN — DETACHED (ZONE 200) · airframe 59,197 hrs · 41,662 cycles

SHIP 9550 FA REPORTS EXIT SIGN AT FWD FIRST CLASS CABIN DETACHED. CORRECTIVE ACTION: RESECURED HARDWARE ON EXIT SIGN. (7585210)

Part: SIGN — DETACHED (ZONE 200) · airframe 59,197 hrs · 41,662 cycles

SHIP 9550 SIGN IN FIRST CLASS CABIN DETACHED FROM CEILING. CORRECTIVE ACTION: RE-ATTACHED EXIT SIGN AS REQUIRED. A/C OK FOR SVC (7585208)

Part: LIGHT — ARCED (ZONE 200) · airframe 57,301 hrs · 39,919 cycles

LIGHT PRODUCES AN ELECTRICAL ARC WHEN THE ATTACHMENT BOLT TOUCHES THE SCREW NEXT TO THE LIGHT ATTACHMENT SOCKET. MAINTENANCE REPLACED THE F/O LIGHT ASSEMBLY PER B717 AMM 33-16. THE OPERATIONAL CHECK WAS GOOD AND THERE WAS NO LONGER ANY ARCHING. (LP #6555658)

Part: TRANSDUCER — SHORTED (CPT CONTROL WHEE) · airframe 57,101 hrs · 39,741 cycles

SHIP 9550 -ATB/DE- THE FLIGHT CREW RETURNED THE AIRCRAFT TO CAE AND DECLARED AN EMERGENCY DUE TO "STICK PUSHER FAIL" MESSAGE WITH AN ASSOCIATED STALL WARNING LIGHT. CORRECTIVE ACTION: MAINTENANCE FOUND THAT THE CAPTAINS CONTROL WHEEL FORCE TRANSDUCER (T2-6080) CABLE WAS SHORTING TO GROUND. THE CAPTAINS CONTROL WHEEL TRANSDUCER WAS REPLACED. OPS CHECK GOOD. (LP #6552314)

Part: BULKHEAD — CRACKED (ZONE 100) · airframe 57,067 hrs · 39,701 cycles

-AD- ACCOMPLISH ER/A 619268-14AD REV A SECTION II - FUSELAGE MAIN FRAME BULKHEADS AT FS 1178, X=10 X=0.0. AFT WEB CRACKED & ELONGATED HOLE. ACCOMPLISH ER/A 619268-14AD REV A SECTION II FOR THE INSPECTION OF THE REAR CANTED BULKHEAD REPAIR. THIS IS AD RELATED. INSPECTIONS CANNOT BE PUSHED PAST 04DEC24. ASSOCIATED ER/A 14-619268 ADDED FOR AC 9550. COMPLIED WITH E/RA 619268-14AD SECTION #2 STEPS 1-12. NO CRACKS OR DEFECTS NOTED. CLOSED LOG AND REMOVED MONITOR INSP PER ALERT 24NOV24 AND LOG COMMENTS. (LP #0647095)

Part: BUSHING — CRACKED (ZONE 300) · airframe 56,878 hrs · 39,541 cycles

CRACK ON BUSHING WAS FOUND, PREVIOUSLY TO INSTALL NEW LOWER BRACKET ON LEADING EDGE AT VERTICAL STABILIZER. SUMMARY OF NRC 00927: CRACK ON BUSHING OF VERTICAL STABILIZER L.E. ZFS=46.300 TO ZFS=52.267 WAS REPAIRED PER ER/A 620945-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. TIME CONTROLLED ITEMS (DTE) MONITORED WITH LP 0613618. (LP #0614263)

Part: VANE — DENTED (ZONE 500 FLAP) · airframe 56,878 hrs · 39,541 cycles

DENTS ON LH WING INBOARD FIXED FLAP VANE INTRADOS BETWEEN XV1=119 AND XV1=119+11, XV1=211-24, XV1=211-26. SUMMARY OF NRC 00172: DENTS (16 EA) ON LH WING INBOARD FIXED FLAP VANE INTRADOS BETWEEN XV1=119 AND XV1=119+11, XV1=211-24, AND XV1=211-26 WERE EVALUATED AND FOUND WITHIN LIMITS PER B717-200 SRM 57-53-01-1A PROCEDURE 1 ALLOWABLE DAMAGE 1 PAR 3.A AND DENT #3 WAS REPAIRED B717-200 SRM 57-53-01-2R PROCEDURE 1 REPAIR 1 AND B717-200 SRM 51-70-02-0G PROCEDURE GENERAL. PERFORM A DVI AND TAP TEST FOR POSSIBLE DISBOND AT EVERY C-CHECK OR 3,000 CYCLES PER B717-200 SRM 57-53-01-1A, STEP 2.B FOR DENTS FOUND TO BE WITHIN ACCEPTABLE LIMITS. (LP #0582982)

Part: PAN — CRACKED (ZONE 100) · airframe 56,878 hrs · 39,541 cycles

CRACK ON INNER PAN FWD SIDE OF BEAM #4 AT AFT CARGO COMPARTMENT DOOR. SUMMARY OF NRC 00422: INNER PAN FWD SIDE OF BEAM #4 AT AFT CARGO COMPARTMENT DOOR WAS REPAIRED PER ERA 619283-14, REV ORIGINAL, SECTION I, PERMANENT REPAIR. (LP #0550050)

Part: CABLE — BROKEN (TAIL CONE) · airframe 56,878 hrs · 39,541 cycles

MAINTENANCE FOUND A BROKEN KEVLAR CABLE AT THE TAIL CONE SLIDE. THIS COULD PREVENT THE PROPER OPERATION OF THE ESCAPE PATH AND IT IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. SUMMARY OF NRC 00917: THE KEVLAR CABLE AT TAIL CONE SLIDE WAS REPLACED PER B717 AMM 53-52-01. (LP #0540955)

Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 56,878 hrs · 39,541 cycles

WEAR AND CORROSION ON HOLES OF LH FLAP HINGE FITTING #3. SUMMARY OF NRC 0885: CORROSION LEVEL 2. LH FLAP HINGE FITTING #3 WAS REPLACED BY A SERVICEABLE PER B717 AMM 57-55-25. (LP #0537751)

Part: CONTROL SYSTEM — OUT OF ADJUST (ZONE 300) · airframe 56,878 hrs · 39,541 cycles

-AD- AMDS 2740-01114-07 STEP 6: DUE RESULT OF THE STEP 6A "ADJUST THE HORIZONTAL STABILIZER TRIM SYSTEM AND SHUTOFF CONTROL SYSTEM AMM 27-40-00 820-801. SUMMARY NRC 00298: HORIZONTAL STABILIZER TRIM SYSTEM AND SHUTOFF CONTROL SYSTEM WAS ADJUSTED PER B717-200 AMM 27-40-00 820-801 AND RESULT OF THE STEP 6A IN AMDS 2740-01114-07 WAS CORRECTED. ASSOCIATED AA 2740-01114 ADDED FOR AC 9550. (LP #0532122)

Part: HINGE FITTING — CORRODED (LT TE FLAP) · corrosion level 2 · airframe 56,878 hrs · 39,541 cycles

CORROSION WAS FOUND ON THE LH FLAP INBOARD HINGE FITTING FASTENER HOLES (8 ATTACH POINT) IN REF NRC 258. SUMMARY OF NRC 00861: LEVEL CORROSION 2. LH FLAP INBOARD HINGE FITTING WAS REPLACED PER B717 AMM 57-55-25. (LP #0528717)

Part: BARREL NUT — CORRODED (ZONE 300) · airframe 56,878 hrs · 39,541 cycles

CORROSION ON THE BARREL NUT HOLES #26, #27, #28, AND #30, STA HX 6.625 RIGHT, STABILIZER CENTER BOX. SUMMARY OF NRC 00407: BARREL NUT HOLES #26, #27, #28, AND #30, STA HX 6.625 RIGHT, STABILIZER CENTER BOX WERE REPAIRED PER ER/A 619552-14 REV ORIGINAL. ASSOCIATED ER/A 14-619552 ADDED FOR AC 9550. (LP #0526275)

Part: CAP — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACK ON UPPER CAP STA Y=1022 AND LONGERON #7 LH AT CABIN PAX. SUMMARY OF NRC 000367: UPPER CAP STA Y=1022 AND LONGERON #7 LH AT CABIN PAX WAS REPAIRED PER PRI 619642-14 REV 1 AND ER/A 619642-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-619642 ADDED FOR AC 9550. (LP #0526995)

Part: DOOR FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,878 hrs · 39,541 cycles

AIRCRAFT 9550, CORROSION ON DOOR JAMB E/E STA Y=133 BTW LONG 29 RH TO 29 LH ALSO ON STA Y=160 FOUND PREVIUOS HOLE PLUGGED LIKE REPAIR AND NO DECAL FOUND. CORRECTIVE ACTION: CORROSION LEVEL 2 // DOOR JAMB E/E STA Y=133 BTW LONG 29 RH TO 29 LH ALSO ON STA Y=160 WAS REPAIRED PER PRI 619673-14 REV. 3 AND ER/A 619673-14 REV. ORIGINAL, SECTION I: PERMANENT REPAIR. ACCOMPLISH SECTION II: REPETITIVE INSPECTION WITHIN EVERY 3,000 CYCLES FROM TIME OR SECTION I REPAIR WAS PERFORMED. (LP 0523849)

Part: SKIN — DAMAGED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

AIRCRAFT 9550, LIGHTNING STRIKES ON SKIN STA Y=256, 229 AND BTW RH LONGERONS 15/16 AT EXTERNAL FUSELAGE. CORRECTIVE ACTION: SKIN STA Y=256, 229 AND BTW RH LONGERONS 15/16 AT EXTERNAL FUSELAGE WAS REPAIRED PER. PRI 619580-14 REV. 4 AND ER/A 619580-14AD REV. ORIGINAL SECTION I: PERMANENT REPAIR. (LP 0516030)

Part: PAN — CRACKED (ZONE 100) · airframe 56,878 hrs · 39,541 cycles

AIRCRAFT 9550, CRACK INNER PAN NEAR TO AFT STOP FITTING AND BEAM NBR 01. CORRECTIVE ACTION: INNER PAN NEAR TO AFT STOP FITTING AND BEAM NBR 01. WAS REPAIRED PER PRI 619304-14 REV. 3 AND ERA 619304-14 REV ORIGINAL SECTION I PERMANENT REPAIR ASSOCIATED ER/A 14-619304. (LP 0514338)

Part: PAN — CRACKED (ZONE 100) · airframe 56,878 hrs · 39,541 cycles

AIRCRAFT 9550, INITIAL INSPECTION: CRACK ON INNER PAN AFT SIDE ON BEAM NBR 3, NBR 4 AND NBR 5 AT AFT CARGO COMPARTMENT DOOR. CORRECTIVE ACTION: INNER PAN AFT SIDE ON BEAM NBR 3, NBR 4 AND NBR 5 AT AFT CARGO COMPARTMENT DOOR. WAS REPAIRED PER PRI 619298-14 REV. 3 AND ERA 619298-14 REV ORIGINAL SECTION I PERMANENT REPAIR. (LP 0514619)

Part: ANGLE — CRACKED (ZONE 100) · airframe 56,878 hrs · 39,541 cycles

AIRCRAFT 9550, INITIAL INSPECTION: CRACKS ON ANGLE OF CANTED KEEL STRUCTURE ON STA Y=716 AND PROJECT LONG 27L AT LOWER CTR FUSELAGE. CORRECTIVE ACTION: ANGLE OF CANTED KEEL STRUCTURE ON STA Y=716 AND PROJECT LONG 27L AT LOWER CTR FUSELAGE WAS REPAIRED PER PRI 619619-14 REV. 2 AND ER/A 619619-14 REV. ORIGINAL, SECTION I: PERMANENT REPAIR. (LP 511626)

Part: NUT — CORRODED (ZONE 300) · corrosion level 2 · airframe 56,878 hrs · 39,541 cycles

CORROSION ON NUTS INSIDE HOLES #26, #27, #28, AND #30 STA HX 6.625 RIGHT STABILIZER CENTER BOX. SUMMARY OF NRC 00494: NUTS INSIDE HOLES #26, #27, #28, AND #30 STA HX 6.625 RIGHT STABILIZER CENTER BOX WERE REPAIRED PER ER/A 619552-14 PRI REV 1. ASSOCIATED ER/A 14-619552 ADDED FOR AC 9550. (LP #0507790)

Part: FRAME — CRACKED (ZONE 100) · airframe 56,878 hrs · 39,541 cycles

CRACK ON WEB AND CRACK ON FRAME OF AFT ACCESSORY COMPARTMENT FROM STA 1178 CANT BTW LONG 1 TO LONG 3RH TO 3LH, APPROXIMATELY. SUMMARY OF NRC 00219: WEB AND FRAME OF AFT ACCESSORY COMPARTMENT FROM STA 1178 CANT BTW LONG 1 TO LONG 3RH TO 3LH WERE REPAIRED PER PRI 619268-14 REV. 4 AND ER/A 619268-14 REV. ORIGINAL, SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-619268 ADDED FOR AC 9550. (LP #0504605)

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,878 hrs · 39,541 cycles

CORROSION ON FRAME STA Y=1022 BTW LONGERON 28R/L30 AT AFT CARGO COMPARMENT. SUMMARY OF NRC 00833; CORROSION LEVEL 2. CORROSION ON FRAME STA Y=1022 BTW LONGERON 28R/L30 AT AFT CARGO COMPARMENT WAS REPAIRED PER B717-200 SRM 53-20-07-2R REPAIR 3, PAR 5, FIGURE 201. PERFORM A VISUAL INSPECTION (GVI) WITH INITIAL THRESHOLD: 25,000 CYCLES AND REPETITIVE INSPECTION: 6,500 CYCLES PER B717-200 SRM 53-20-07-2R REPAIR 3. PARAGRAPH 6.A (TABLE 205). (LP #0502484)

Part: WINDOW FRAME — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACK ON LH WINDOW FRAME (RETAINER POLISHED). SUMMARY OF NRC 00623: LH WINDOW FRAME WAS REPAIRED PER PRI 619398-14 REV 2 AND PER ER/A 619398-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-619398.

Part: SKIN — CORRODED (WING) · corrosion level 2 · airframe 56,878 hrs · 39,541 cycles

CORROSION ON SKIN UPPER EDGE OF LH AND RH WING REAR SPAR BTW XCW=0 TO XW=60 (THROUGH LH AND RH MLG (SPECIFICALLY XCW=30)). SUMMARY OF NRC 00169: CORROSION LEVEL 2. CORROSION ON SKIN UPPER EDGE OF LH AND RH WING REAR SPAR BTW XCW=0 TO XW=60 WAS REPAIRED PER PRI 619422-14 REV 2 AND ER/A 619422-14 REV ORIGINAL, SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-619422 ADDED FOR AC 9550. (LP #0499064)

Part: BEAM — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACKS ON BEAM #6 BTW STA 180-196 AT FWD PASSENGER DOOR. SUMMARY OF NRC 00117: BEAM #6 ON STA 196 AT FWD PASSENGER DOOR WAS REPAIRED PER B717-200 SRM 52-10-02-2R PROCEDURE 12 PAR 4 FIGURE 201. AND (ET) (HFEC) INSPECTION WAS ACCOMPLISHED ON BEAM #6 ON STA 180 AT FWD PASSENGER DOOR AND NO CRACKS WERE FOUND. (LP #0498549)

Part: STABILIZER — DISTORTED (VERTICAL STABILI) · airframe 56,878 hrs · 39,541 cycles

THE COUNTERSINK OF THE FASTENERS HOLES OF THE VERTICAL STABILIZER LEADING EDGE WERE NOTED WORN ALL AROUND EDGES BETWEEN ZFS 52.267 TO 153.938. SUMMARY OF NRC 00748: THE LEADING EDGE OF THE VERTICAL STABILIZER IS OUT OF LIMITS, AS REPAIRABLE HOLE LIMITS PER B717-200 SRM 55-30-01 REPAIR 6 AND 7 ARE EXCEEDED, THEREFORE VERTICAL STABILIZER LEADING EDGE IS REPLACED PER NRC 00775. (LP #0491654)

Part: CAP — CRACKED (STA Y=1022 AND L) · airframe 56,878 hrs · 39,541 cycles

CRACK ON UPPER CAP STA Y=1022 AND LONGERON #7 RH AT CABIN PAX. SUMMARY OF NRC 00816: UPPER CAP STA Y=1022 AND LONGERON #7 RH AT CABIN PAX WAS REPAIRED PER PRI 619643-14 REV 1 AND ER/A 619643-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-619643 ADDED FOR AC 9550. (LP #0491995)

Part: ANGLE — CORRODED (ZONE 200) · corrosion level 2 · airframe 56,878 hrs · 39,541 cycles

CORROSION ON RH CUSP ANGLE Y=200, Y=219-224 AT PAX CABIN (W1.) SUMMARY OF NRC 00467: CORROSION LEVEL 2. CUSP ANGLE Y=200, Y=219-224 AT PAX CABIN WAS REPAIRED PER PRI 619420-14 REV 2 AND ER/A 619420-14 REV ORIGINAL, SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-619420 ADDED FOR AC 9550. (LP #0488697)

Part: INTERCOSTAL — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,878 hrs · 39,541 cycles

CORROSION ON INTERCOSTAL 29R STA Y=1002 TO Y=1005 AT AFT CARGO COMPARTMENT (C2). SUMMARY OF NRC 00332: CORROSION LEVEL 2. INTERCOSTAL 29R STA Y=1002 TO Y=1005 AT AFT CARGO COMPARTMENT (C2) WAS REPLACED PER B717-200 SRM 51-41-05-0G. (LP #0487811)

Part: AUTOBRAKE SYS — INTERMITTENT · airframe 56,878 hrs · 39,541 cycles

CRACK ON FRAME CAP STA Y=1133 AND BTW LONG 2LH TO 3LH AT AFT ACCESSORY COMPARTMENT. SUMMARY OF NRC 00685: FRAME CAP (STIFFENER) STA Y=1133 AND BTW LONG 2LH TO 3LH AT AFT ACCESSORY COMPARTMENT WAS REPAIRED PER B717-200 SRM 51-70-11-2R PROCEDURE 1 REPAIR 1. (LP #0486708)

Part: SKIN — CRACKED (LH SIDE BTW LONG) · airframe 56,878 hrs · 39,541 cycles

CRACKS ON FUSELAGE SKIN LH SIDE BTW LONGERON 13L-14L AND STA 1022, 1037, 1087 AT AFT FUSELAGE. SUMMARY OF NRC 00046: (ET) HFEC INSPECTION WAS ACCOMPLISHED ON FUSELAGE SKIN LH SIDE BTW LONGERON 13L-14L AND STA 1037, 1087 AT AFT FUSELAGE ON STA 1037 THREE CRACKS WERE FOUND OF 0.300 IN, 1.950 IN, 200 IN AT THE OTHER STATION NO CRACKS WERE FOUND PER DC-MD/BOEING NDTSPM PART 6, 06-10-01.001. FUSELAGE SKIN LH SIDE BTW LONGERON 13L-14L AND STA 1037 AT AFT FUSELAGE WAS REPAIRED PER PRI 619241-14 REV 3 AND ER/A 619241-14 REV ORIGINAL, SECTION I: PERMANENT REPAIR. REPAIR APPROVAL IS LIMITED TO 24 MONTHS FROM 01AUG24. ADDITIONAL ENGINEERING AUTHORIZATION (ER/A REVISION) IS REQUIRED FOR CONTINUED SERVICE BEYOND THIS LIMIT UNDER LOG 0486241. ASSOCIATED ER/A 14-619241 ADDED FOR AC 9550. (LP #0486597)

Part: WING ROOT — CORRODED (LH CENTER WING U) · corrosion level 2 · airframe 56,878 hrs · 39,541 cycles

CORROSION ON LH CENTER WING UPPER SURFACE (WING BOX) BTW STGR 6-5 AND STGR 5-4 PAX CABIN. SUMMARY OF NRC 00693: CORROSION LEVEL 2. CORROSION ON LH CENTER WING UPPER SURFACE (WING BOX) BTW STGR 6-5 AND STGR 5-4 PAX CABIN WAS REPAIRED PER PRI 619399-14 REV 3 AND ERA 619399-14 AD REV ORIGINAL SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-619399 ADDED FOR AC 9550. (LP #0486415)

Part: FRAME — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACK ON MAIN FRAME STA Y=1037 LONGERON 17L AT PAX CABIN. SUMMARY OF NRC 00354: MAIN FRAME STA Y=1037 LONGERON 17L AT PAX CABIN WAS REPAIRED PER PRI 619352-14 REV 1 AND ERA 619352-14 REV ORIGINAL, SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-619352 ADDED FOR AC 9550. (LP #0480784)

Part: SKIN — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACKS ON FUSELAGE SKIN RH SIDE BTW LONGERON 13R-14R AND STA 1116, 1144, LONGERON 7R AND STA 1022 AT AFT FUSELAGE. SUMMARY OF NRC 00047: FUSELAGE SKIN RH SIDE BTW LONGERON 13R-14R AND STA 1116, 1144, LONGERON 7R AND STA 1022 AT AFT FUSELAGE WAS REPAIRED PER PRI 619247-14 REV 3 AND ERA 619247-14 REV ORIGINAL, SECTION I: PERMANENT REPAIR. TIME CONTROLLED ITEM SECTION II ACCOMPLISH SECTION II: THRESHOLD INSPECTION 8,000 CYCLES AFTER ACCOMPLISHMENT OF SECTION I, REPETITIVE INSPECTION AT INTERVAL 8,000 CYCLES MONITORING UNDER LP 0479078. ASSOCIATED ER/A 14-619247 ADDED FOR AC 9550. (LP #0481310)

Part: LONGERON — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACKS ON LONGERONS 3, 4, 5, 6, AND 17 LH STA Y=1022 AT CABIN PAX. SUMMARY OF NRC 00371: LONGERON 3 BTW STA Y=1012 TO STA Y=1027 LH, LONGERON 4 BTW STA Y=1011 TO STA Y=1053 LH, LONGERON 5 BTW STA Y=1012 TO STA Y=1053 LH, LONGERON 6 BTW STA Y=1013 TO STA Y=1053 LH, AND LONGERON 17 BTW STA Y=1014 TO STA Y=1053 LH WERE REPAIRED PER B717-200 SRM 53-00-05-2R REPAIR 2. (LP #0480413)

Part: FRAME — DAMAGED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

NICKS ON FRAME STA Y=351 BTW LONGERON 17R / L18R. SUMMARY OF NRC 00711: FRAME'S STA Y=351 BTW LONGERON 17R / L18R WAS REPAIRED PER B717-200 SRM 53-00-07-2R PROCEDURE 1 REPAIR 1. (LP #0473575)

Part: LONGERON — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACKS ON LONGERONS 3, 4, 5, 6, AND 8 RH STA Y=1022 AT CABIN PAX. SUMMARY OF NRC 00370: LONGERONS 3, 4, 5, 6, AND 8 RH STA Y=1022 AT CABIN PAX WERE REPAIRED PER B717-200 SRM 53-00-05-2R REPAIR 2 FIG.201. (LP #0473110)

Part: CUSP WEB — CORRODED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACK ON CUSP WEB BTW STA Y=579/598 AND STA X=-45 AT PAX CABIN. SUMMARY OF NRC 00453: CUSP WEB BTW STA Y=579/598 AND STA X=-45 AT PAX CABIN WAS FABRICATED PER B717 SRM 53-00-55-2R-4 AND REPLACED PER B717 SRM 51-41-01-0G, 51-41-02-0G, AND 51-41-05-0G. (LP #0471152)

Part: CUSP WEB — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACK WAS FOUND AFTER REMOVED CUSP WEB BTW STA Y=218 TO STA Y=238, -X=56 TO -X=44 AT CABIN PAX. SUMMARY OF NRC 00820: CUSP WEB BTW STA Y=218 TO STA Y=238, -X=56 TO -X=44 AT CABIN PAX WAS REPAIRED PER B717-200 SRM 53-00-55-2R REPAIR 4 FIG 203. (LP #0468164)

Part: PAN — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,878 hrs · 39,541 cycles

CORROSION ON AFT CARGO COMPARTMENT LOWER DOOR JAMB PAN. SUMMARY OF NRC 00131: CORROSION LEVEL 2. LOWER DOOR JAMB PAN ON AFT CARGO COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-20-15-2R REPAIR 7. (LP #0467185)

Part: CUSP WEB — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACKS ON CUSP WEB BTW STA Y=579/598 AND BTW STA X=44/60 AT PAX CABIN. SUMMARY OF NRC 00443: CUSP WEB BTW STA Y=579/598 AND BTW STA X=44/60 AT PAX CABIN WAS REPAIRED PER B717 SRM 53-00-55-2R-4 AND 51-41-02-0G. (LP #0467746)

Part: CUSP WEB — DAMAGED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

TOOL MARK ON CUSP WEB (LOWER FACE) STA Y=614 AND STA X=-54 AT PAX CABIN. SUMMARY OF NRC 00452: CUSP WEB STA Y=614 AND STA X=-54 AT PAX CABIN WAS REPAIRED PER B717-200 SRM 53-00-55-2R REPAIR 4. (LP #0466500)

Part: VANE — DENTED (ZONE 500) · airframe 56,878 hrs · 39,541 cycles

DENTS ON LH WING LOWER MOVABLE FLAP VANE INTRADOS BETWEEN XF=69+8 AND XF=111-10. ADDL TIME RLTD MON 0464583 ADDED. SUMMARY OF NRC 00260: DENTS ON LH WING LOWER MOVABLE FLAP VANE INTRADOS BETWEEN XF=69+8 AND XF=111-10 WERE MEASURED AND EVALUATED AND ARE WITHIN LIMITS PER B717-200 SRM 57-53-01-1A PROCEDURE 1. ALLOWABLE DAMAGE 1. PAR. 3. A; AND DENTS LOCATED BETWEEN XF=69+16 AND XF=69+24: ARE OUT OF LIMITS PER B717-200 SRM 57-53-01-1A PROCEDURE 1. ALLOWABLE DAMAGE 1. PAR. 3. A. THEREFORE WERE REPAIRED PER B717- 200 SRM 51-70-02-0G PROCEDURE GENERAL IN REFERENCE TO B717-200 SRM 57-53-01-2R PROCEDURE 1 REPAIR 1 PAR. 4 DENTS WITHIN LIMITS PERFORM DVI AND TAP-TEST PER 57-53-01-1A PROCEDURE 1 ALLOWABLE DAMAGE 1 - FLAPS AND FLAP VANES DENT LIMITS EVERY C CHECK OR 3,000. (LP #0464590)

Part: CUSP WEB — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACKS ON CUSP WEB BTW STA Y=655/715 AND BTW STA X=44/60 AT PAX CABIN. SUMMARY OF NRC 00444: CUSP WEB BTW STA Y=655/715 AND BTW STA X=44/60 AT PAX CABIN WAS REPAIRED PER B717 SRM 53-00-55-2R-4. (LP #0464713)

Part: PAN — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,878 hrs · 39,541 cycles

CORROSION ON FWD CARGO COMPARTMENT PAN LOWER DOOR JAMB. SUMMARY OF NRC 00129: CORROSION LEVEL 2. FWD CARGO COMPARTMENT PAN LOWER DOOR JAMB WAS REPAIRED PER B717-200 SRM 53-20-15-2R REPAIR 6. (LP #0466095)

Part: VANE — DENTED (ZONE 500) · airframe 56,878 hrs · 39,541 cycles

DENTS ON LH WING LOWER MOVABLE FLAP VANE INTRADOS BETWEEN XF=69+8 AND XF=111-10. ADDL TIME RLTD MON 0464590 ADDED. SUMMARY OF NRC 00260: DENTS ON LH WING LOWER MOVABLE FLAP VANE INTRADOS BETWEEN XF=69+8 AND XF=111-10 WERE MEASURED AND EVALUATED AND ARE WITHIN LIMITS PER B717-200 SRM 57-53-01-1A PROCEDURE 1. ALLOWABLE DAMAGE 1. PAR. 3. A; AND DENTS LOCATED BETWEEN XF=69+ 16 AND XF=69+24 ARE OUT OF LIMITS PER B717-200 SRM 57-53-01-1A PROCEDURE 1. ALLOWABLE DAMAGE 1. PAR. 3. A. THEREFORE WERE REPAIRED PER B717-200 SRM 51-70-02-0G PROCEDURE GENERAL IN REFERENCE TO B717-200 SRM 57-53-01-2R PROCEDURE 1 REPAIR 1 PAR. 4 DENTS WITHIN LIMITS PER PERFORM DVI AND TAP-TEST PER 57-53-01-1A PROCEDURE 1 ALLOWABLE DAMAGE 1 - FLAPS AND FLAP VANES DENT LIMITS EVERY C CHECK OR 3,000. (LP #0464583)

Part: PAN — CRACKED (ZONE 100) · airframe 56,878 hrs · 39,541 cycles

CRACK ON INNER PAN ON BEAM 3 FWD SIDE AT FWD CARGO COMPARTMENT DOOR. SUMMARY OF NRC: 00104, PERMANENT REPAIR, INNER PAN ON BEAM 3 FWD SIDE AT FWD CARGO COMPARTMENT DOOR WAS REPAIRED PER B717-200 SRM 52-30-02-2R PROCEDURE 1 REPAIR 1. (LP #0464129)

Part: FRAME — CRACKED (ZONE 100) · airframe 56,878 hrs · 39,541 cycles

CRACK ON MAIN FRAME STA Y=1037 LONG 17RH AT CPAX. SUMMARY OF NRC 00622: MAIN FRAME STA Y=1037 LONG 17RH AT CPAX WAS REPAIRED PER B717-200 SRM 53-20-07-2R-4 REPAIR 4 PAR 5 A. (LP #0460601)

Part: CUSP WEB — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACKS ON CUSP WEB STA 715 TO 756 BTW X=44 AND X=60 WERE FOUND DURING INSPECTION OF REMOVED COMPONENTS ON NRC 693. CUSP WEB STA 715 TO 756 BTW X=44 AND X=60 WAS REPAIRED PER B717-200 SRM 53-00-55-2R REPAIR 4, FIG 203.

Part: PAN — CRACKED (ZONE 100) · airframe 56,878 hrs · 39,541 cycles

CRACK ON OUTER PAN ON AFT UPPER CORNER AT FWD CARGO COMPARTMENT DOOR. SUMMARY OF NRC 00100: OUTER PAN ON AFT UPPER CORNER AT FWD CARGO COMPARTMENT DOOR WAS REPAIRED PER B717-200 SRM 52-30-02-2R-1. (LP #0454678)

Part: SUPPORT — CRACKED (ZONE 100) · airframe 56,878 hrs · 39,541 cycles

CRACK ON FAIRING SUPPORT STA Y=617 AND BTW LONGERONS LH 24/25 AT EXTERNAL FUSELAGE. SUMMARY OF NRC 00381: FAIRING SUPPORT STA Y=617 AND BTW LONGERONS LH 24/25 AT EXTERNAL FUSELAGE WAS REPAIRED PER B717-200 SRM 51-70-11-2R REPAIR 1. (LP #0453173)

Part: SKIN — CRACKED (RT NACELLE) · airframe 56,878 hrs · 39,541 cycles

CRACK ON EXTERNAL SKIN AT APRON, FIVE INCHES FWD OF LOWER AFT CORNER APROX RH ENGINE. SUMMARY OF NRC 00268: EXTERNAL SKIN AT APRON, FIVE INCHES FWD OF LOWER AFT CORNER APROX RH ENGINE WAS REPAIRED PER B717-200 SRM 54-50-01-2R PRCEDURE 2, REPAIR 2. (LP #0449618)

Part: CUSP WEB — CRACKED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

CRACKS ON CUSP WEB STA Y=656, 715, AND STA X=-45 AT PAX CABIN. SUMMARY OF NRC 00451: CUSP WEB STA Y=656, 715, AND STA X=-45 AT PAX CABIN WERE REPAIRED PER B717-200 SRM 53-00-55-2R REPAIR 4, FIG 203 AND FIG 211. (LP #0449560)

Part: CUSP WEB — WORN (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

WEAR ON CUSP WEB STA Y=256, 275, AND BTW STA X=44/54 (UPPER FACE) AT PAX CABIN. SUMMARY 00441: CUSP WEB STA Y=256, 275, AND BTW STA X=44/54 (UPPER FACE) AT PAX CABIN WAS REPAIRED PER B717-200 SRM 53-00-55-2R-4. (LP #0442199)

Part: JACKSCREW — DAMAGED (HORIZONTAL STAB) · airframe 56,385 hrs · 39,117 cycles

AD - DURING HORIZONTAL STABILIZOR JACKSCREW INSPECTION FOUND NICKS ON THE JACKSCREW THREADS. REPLACED JACKSCREW REF TO AMDS CARD #2740-01114-05 AND B717 AMM 27-41-04-401. OK TO INSTALL P/A BY QC5363, INSTALL BUY OFF OF HORIZONTAL STABILIZER ACTUATOR P/A BY QC2099, VERIFIED GIMBAL NUT ORIENTATION P/A BY QC5307. ALL RII STEPS COMPLIED WITH ON AMDS 2740-01114-05. (LP #0281171)

Part: FASTENER — LOOSE (VERTICAL STAB) · airframe 56,141 hrs · 38,918 cycles

AD. FOUND 5 FASTENERS LOOSE AT THE RH VERTICAL STABILIZER LEADING EDGE STRUCTURE SPLICE (STA ZFS=52.267) REFERENCE AA 5530-01048 & AD 2018-10-08. CHECKED FASTENER HOLES REF SERVICE GENERAL DRAWING SG 95550001 AND FOUND HOLES TO BE OK REF AMDS CARD 5530-01048-02 STEP 5 B (1). (LP #0227478)

Part: FASTENER — LOOSE (VERTICAL STAB) · airframe 56,141 hrs · 38,918 cycles

AD. FOUND 24 FASTENERS LOOSE AT THE LH VERTICAL STABILIZER LEADING EDGE STRUCTURE SPLICE. (STA ZFS=52.267) REFERENCE AA 5530-01048 AND AD 2018-10-08. CHECKED FASTENER HOLES REF SERVICE GENERAL DRAWING SG9550001 AND FOUND HOLES TO BE OK REF AMDS CARD 5530-01048-02 STEP 5 B (1). (LP #0227464)

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 55,953 hrs · 38,732 cycles

MAINTENANCE FOUND THE L-1 ENTRY EMERGENCY EXIT SIGN TO BE INOPERATIVE. THE POWER SUPPLY FOR THE EMERGENCY LIGHT BATTERY WAS REPLACED IAW B717 AMM 33-51-03. OPERATIONAL CHECK WAS GOOD. THE AIRCRAFT IS OK FOR SERVICE. (LP #4369370)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 55,514 hrs · 38,378 cycles

SHIP 9550 -MISC/DE- THE FLIGHT CREW NOTICED THE FUEL TO BE TRENDING LOW AND A 1000LB IMBALANCE. THE TANKS WERE RE-BALANCED, BUT THE IMBALANCE RETURNED. FUEL QUANTITY WAS ALSO LOWER THAN PLANNED. THE QRH WAS COMPLIED WITH AND THE FUEL LEAK CHECKLIST WAS FOLLOWED, BUT THE LEAK CONTINUED. THE CREW DECLARED AN EMERGENCY WITH ATC AND REQUESTED ARFF TO MEET THEM ON ARRIVAL. THE LANDING WAS UNEVENTFUL BUT THEY EXITED THE RUNWAY AT HIGHSPEED FOR ARFF INSPECTION. A FUEL LEAK WAS NOTED AND IT DECREASED AFTER THE #2 ENGINE WAS SHUTDOWN. NORMAL TAXI TO GATE WHERE THE AIRCRAFT WAS MET BY MAINTENANCE WHO CONFIRMED THE FUEL LEAK. THE #2 ENGINE FUEL FILTER HOUSING O-RING WAS ONE CAUSE OF THE LEAK AND WAS REPLACED. THE BY-PASS VENT VALVE WAS ALSO FOUND TO BE LEAKING, SO IT WAS REPLACED. THE AIRCRAFT HAS RETURNED TO SERVICE. (LP #4996420)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 55,481 hrs · 38,350 cycles

DURING SERVICE CHECK, FOUND EMERGENCY EXIT LOWER DOOR LIGHTS INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHTS BATTERY POWER SUPPLY PER B717 AMM 33-51. OPERATIONAL CHECK WAS GOOD. (LP #4996416)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 55,217 hrs · 38,130 cycles

SHIP 9550 -DE- THE CREW RETURNED THE AIRCRAFT TO THE GATE DUE TO AN ENGINE FIRE INDICATION ON THE #1 ENGINE DURING TAXI OUT. CORRECTIVE ACTION: MAINTENANCE CONFIRMED IT TO BE AN INDICATION ONLY. NO FIRE. THE #1 ENGINE FDCU WAS REPLACED, THE #1 ENGINE EXHAUST VENT LOOPS A & B WERE REPLACED, AND THE GEARBOX LOOPS A & B WERE REPLACED. ENGINE RUNS SUCCESSFUL. (LP #4610148)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 54,350 hrs · 37,386 cycles

COMPLY WITH PRI 609042-14 AD REV O., ENSURE FINAL ERA 609042-14 AD REV O MATCHES PRI 609042-14 AD REV O. COMPLIED WITH PRI 609042-14 AD REV O., FINAL ERA 609042-14 AD REV O MATCHES PRI 609042-14 AD REV O. CORRECT NUT INSTALLATION AND WASHER INSTALLATION ON WORK CARD 000-0002:2750-4003. (LP #2785849)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · corrosion level 2 · airframe 54,336 hrs · 37,372 cycles

AFT CARGO DOOR LOWER SILL: SIGNS OF CORROSION AND METAL BULGING FROM UNDER AFT SIDE OF CENTER DOOR STOP FITTING -MARKED-. SUMMARY SEE NRC 001-0311:5231-2002/009 00237: REPLACED AFT CARGO DOOR JAMB PAN REF B717 SRM 53-20-15-2R-7. (LP #2774207)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · corrosion level 2 · airframe 54,336 hrs · 37,372 cycles

FWD CARGO DOOR SILL/JAMB, EVIDENCE OF CORROSION AROUND FASTNERS IN THE SILL AREA. (MARKED). SUMMARY SEE NRC 001-0312:5231-2003/007 00134: REPLACED FWD CARGO DOOR LOWER JAMB PAN REF B717 SRM 53-20-15-2R-6. (LP #2774676)

Part: LENS — MISSING (EMERGENCY LIGHT) · airframe 53,344 hrs · 36,535 cycles

THE EXIT SIGN IS MISSING AT THE FRONT OF FIRST CLASS. MAINTENANCE INSTALLED A NEW FIRST CLASS EMERGENCY EXIT LIGHT LENS PER B717 AMM 33-51. OK FOR SERVICE.

Part: NONE — NONE · airframe 51,969 hrs · 35,230 cycles

WORKING MEL LOG 2202663 FOUND DAMAGE RUDDER STOP LIMITING SPRING BRACKET. REMOVED BRACKET. INTERCOSTAL SENT TO ATL TO HAVE FABRICATED. REPLACED INTERCOSTAL AND BRACKET PER SRM 51-40. (LP #8488457)

Part: NONE — NONE · airframe 51,815 hrs · 35,101 cycles

THE AFT OVERWING EMERGENCY EXIT SIGN WILL NOT LIGHT UP. MAINTENANCE REPLACED THE EMERGENCY EXIT POWER SUPPLY BATTERY IAW B717 AMM 24-34. OPERATIONAL CHECK WAS GOOD. (LP #8758756)

Part: NONE — NONE · airframe 51,493 hrs · 34,822 cycles

CEILING PANEL 1 EMERCENCY LIGHT IS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY IN THE EMERGENCY LIGHT POWER SUPPLY B5-235. OPERATIONAL CHECK WAS GOOD REF B717 AMM 33-51. (LP #8405291)

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 50,453 hrs · 33,898 cycles

ROW 19CDE LOWER EMERGENCY SIGN IS INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT BATTERY POWER SUPPLY PER B717 AMM 33-51. OPERATIONAL CHECK WAS GOOD, OK FOR SERVICE. (LP #8004127)

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 50,332 hrs · 33,780 cycles

THE AFT EMERGENCY EXIT SIGN IS INOPERATIVE. MAINTENANCE REPLACED THE AFT EMERGENCY BATTTEY POWER PACK PER B717 AMM 33-51. THE OPERATIONAL CHECK WAS GOOD. (LP #7081659)

Part: WEB — DAMAGED (FUELING PANEL) · airframe 49,983 hrs · 33,491 cycles

I/B FUELING PANEL O/B SIDE PREVIOUS DAMAGE TO WEB WHERE AFT HINGE PIN MADE CONTACT. MARKED. NRC 001-0356:5740-2002/003 00119: REPAIRED PER ER/A 591558-14 REV A. CLOSING REQUIREMENTS RII: INSPECTOR 00450401. (LP #1815751 )

Part: SPAR CAP — CRACKED (VERTICAL STAB) · airframe 49,970 hrs · 33,478 cycles

DURING CRACK CONFIRMATION STEP 10 OF 5530-01048-02 VERIFIED CRACK INDICATIONS IN LH VERTICAL STAB FRONT SPAR CAP FORWARD FLANGE AT HOLES 1,2,3,4, AND 7 BELOW ZFS=52.267. HOLES ARE NUMBERED FROM TOP TO BOTTOM REF AA 5530-01048-02 STEP 10 AND AD 2018-10-08. COMPLIED WITH ER/A 591513-14AD REV A. REFERENCE NRC 264. ASSOCIATED ER/A 14-591513 ADDED FOR AC 9550. (LP #1814015)

Part: FRAME — CORRODED (BS 974 S28L-29R) · corrosion level 2 · airframe 49,970 hrs · 33,478 cycles

AFT PIT AT STA 974 BETWEEN STRINGER 29R AND 28L FRAME HAS CORROSION. REPAIRED REF B717 SRM 53-20-07-2R-3. (LP #1812173)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 54,193 hrs · 37,248 cycles

ER/A 591513-14AD ISSUED FOR 5 CRACKED FASTENER HOLES IN THE FRONT SPAR CAP ON THE LH VERTICAL STABILIZER. FOLLOW ON ACTION IS REQUIRED. ASSOCIATED ER/A 95-591513 ADDED FOR AC 9550. ER/A 591513-14AD IS NOW AT REVISION A. LOG PAGE 1810936 TRACKING IS UNAFFECTED AT THIS REVISION. SEE ER/A 591513-14AD REV A. UPDATED MASK LOG-PAGE UPDATED @ 26MAY21 1356 UTC 06 DFRD BY GROSS MSP 17APR23 RII: N ERA 591513-14AD REV B IS CURRENT, THIS LP MAY BE CLOSED. TERMINATED LOG PER COMMENTS FROM ENGINEER GROSS. (LP #1810936)

Part: STRINGER SPLICE — CORRODED (BS 927-946 S30) · corrosion level 2 · airframe 49,970 hrs · 33,478 cycles

CORROSION ON STRINGER SPLICE STR 30 BETWEEN FR 927 & 946. MARKED. REMOVED & REINSTALLED SPLICE PER B717 SRM 51-40-02. BLENDED AND CHECKED WITHIN LIMITS PER B717 SRM 53-00-00-1A. (LP #1804433)

Part: SKIN — DAMAGED (ZONE 200) · airframe 56,878 hrs · 39,541 cycles

-AD- LIGHTNING STRIKE DAMAGE TO THE UPPER FWD CORNER OF THE RH #19 WINDOW (RHS STA 579-598). SECTION I: TIME-LIMITED REPAIR ACCOMPLISHMENT PER ER/A 554700-14 REV ORIG. REQUIRED PRIOR TO DEPARTURE FROM EWR. PERMANENT REPAIR ACCOMPLISHMENT PER THIS ER/A REQUIRED WITHIN 14553 FLIGHT CYCLES. ASSOCIATED ER/A 95-554700 ADDED FOR AC 9550. C/W ERA-554700-14 ORIGINAL SECTION 1 ACCOMPLISHED. SECTION 2 TO BE ACCOMPLISHED WITHIN 14553 FLT CYCLES RH BELT WINDOW 19. SUMMARY: RH WINDOW BELT, UPPER FWD CORNER OF WINDOW #19 WAS REPAIRED PER ERA 554700-14AD REV B SECTION II: TEMPORARY REPAIR AND NRC 00110. CLOSED LOG AND REMOVED MONITOR INSP PER ALERT 13AUG24 AND LOG COMMENTS. (LP #2861451)

Part: FAIRING — MISSING (RT ELEVATOR TRIM) · airframe 49,278 hrs · 32,936 cycles

THE RIGHT SIDE ELEVATOR TRIM TAB OUTBOARD FAIRING WAS MISSING ON WALK AROUND INSPECTION. MAINTENANCE INSTALLED A NEW FAIRING AND NEW FASTENERS, PER B717 AMM 27-30. NO FURTHER DAMAGE WAS NOTED.

Part: PANEL — MISSING (THRUST REVERSER) · airframe 48,902 hrs · 32,614 cycles

THE INBOARD SIDE NR 1 ENGINE THRUST REVERSER PANEL MISSING. MAINTENANCE INSTALLED A NEW PANEL USING NEW HARDWARE. PERFORMED AN OPERATIONAL AND LEAK CHECK OF THE THRUST REVERSER, PER B717 AMM 78-30. AIRCRAFT OK FOR SERVICE.

Part: ROD END — BROKEN (SLAT ACTUATOR) · airframe 48,681 hrs · 32,402 cycles

SHIP 9550, THE AIRCRAFT ROLLED AGGRESSIVELY TO THE RIGHT UPON SLAT DEPLOYMENT DURING APPROACH FOR LANDING. THE ROLL REACHED 10-20 DEGREES OF BANK AND THEN WAS CORRECT BACK TO WINGS LEVEL BY THE AUTOPILOT. NO OTHER FAULT MESSAGES OR INDICATIONS WERE OBSERVED. CORRECTIVE ACTIONS: MAINTENANCE FOUND THE SLAT DRUM INBOARD ACTUATOR ROD END BROKEN IN HALF AND THE ACTUATOR OFF THE SLAT DRUM. A NEW LEFT WING INBOARD SLAT DRIVE ACTUATOR WAS INSTALLED. FUNCTIONAL CHECK WAS GOOD, PER B717 AMM 27-90-00 720-801.

Part: DOOR FRAME — DAMAGED (AFT CARGO) · airframe 49,970 hrs · 33,478 cycles

ON WALKAROUND, FOUND DAMAGE TO AFT CARGO DOOR JAMB, AFT SIDE. REMOVED EXISTING DAMAGE PER PRI 587222-14, REV 0, STEPS 1 THROUGH 5. COMPLETED STEPS 6 THROUGH 10 OF R.I. ASSOCIATED ER/A 587222-14 ADDED FOR AC 9550. COMPLIED WITH ER/A 587222-14 REV. C. SECTION V PERMANENT REPAIR. (LP #1583771)

Part: ROD END — BROKEN (RT WING SLAT) · airframe 48,446 hrs · 32,199 cycles

SLAT DISAGREE CAUTION ILLUMINATED AFTER EXTENDING SLATS. RT WING SLAT DRIVE ACTUATOR ROD-END BROKEN. REPLACED ROD-END TO SLAT ACTUATOR. OPS OK . NO FURHER SLAT DISAGREE MSGS NOTED.

Part: WARNING LIGHT — FALSE ACTIVATION (SLAT SYSTEM) · airframe 48,446 hrs · 32,199 cycles

SLAT DISAGREE CAUTION LIGHT CAME ON AFTER EXTENDING FLAPS, SLATS RETRACTED FINE. PERFORMED NO GO ODI 2785. TESTED SLATS IAW AMM 27-80 SLATS/FLAPS OPERATE NORMAL. A/C OKAY FOR SERVICE.

Part: BATTERY — FAILED (EMERGENCY LIGHT) · airframe 47,232 hrs · 31,207 cycles

WHILE PERFORMING WC #3351-2001, MAINTENANCE FOUND ONE EMERGENCY LIGHT BATTERY TO BE BAD FROM STOCK. INSTALLED ORIGINAL EMERGENCY LIGHT BATTERY (B5-227) IAW B717 AMM 33-51. DEFERRED FOR 40 FLIGHT HOURS. 28NOV19 DTW - THE EMERGENCY LIGHT BATTERY PACK (B5-227) WAS REPLACED PER WC #3351-2001. OPERATIONAL CHECK WAS GOOD. (LP #6404530)

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 46,692 hrs · 30,822 cycles

SEVERAL EMERGENCY EXIT LIGHTS ARE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK. OPERATIONAL CHECKS ARE GOOD REF AMM 33-51-03. (LP #5995456)

Part: COMPUTER — MALFUNCTIONED (COCKPIT) · airframe 44,481 hrs · 29,329 cycles

SHIP 9550 - THE CREW PERFORMED A MISSED APPROACH AND DECLARED EMERGENCY DUE TO THE STICK SHAKER CONTINUOUSLY ACTIVATING ON FINAL APPROACH. CORRECTIVE ACTION: MAINTENANCE REPLACED THE NR 1 FCC, AND ALL FOLLOW UP RETURN TO SERVICE CHECKS WERE SUCCESSFUL. (LP 4878102)

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 44,129 hrs · 29,108 cycles

VERTICAL STAB SKIN CRACKED IN 5TH FASTENER HOLE BELOW ZFS52.267. COMPLIED WITH ER/A 536162-14AD REV B SEC IV.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 42,012 hrs · 27,604 cycles

LOWER EMERGENCY EXIT DOOR LIGHTS ARE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT POWER SUPPLY AT B5-119. OPS CHECKED GOOD.

Part: SKIN — DELAMINATED (LT SPOILER)

DURING AN UNSCHEDULED MAINTENANCE CHECK OF THE LT, OTBD SPOILER, FOUND DELAMINATION ON THE UPPER SURFACE.

Part: SKIN — DELAMINATED (RT SPOILER)

DURING UNSCHEDULED MAINTENANCE CHECK, THE RT INBD SPOILER WAS FOUND TO BE DELAMINATED ON THE UPPER SURFACE.

Part: BEAM — CRACKED (R1 DOOR) · airframe 40,986 hrs · 26,885 cycles

CRACKED BEAM NR 4 FWD EDGE ON R1 DOOR (PTAS). BEAM NR 4 WAS REPLACED PER SRM VOL II 51-30-02 AND 51-30-05.

Part: DOOR FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,984 hrs · 26,884 cycles

CORROSION ON LWR DOOR JAMB BTW STA Y=954 TO Y=994 ON AFT CARGO COMPARTMENT IN REF AMDS 5300-2007)(SM)(C2). PERMANENT REPAIR ON LOWER DOOR JAMB WAS ACCOMPLISHED PER SRM 53-20-15-2R, 51-10-04 PAR 15, 21, 37, AND 51-41-01, 51-41-02, 51-41-05.

Part: FRAME — CRACKED (FUSELAGE) · airframe 40,984 hrs · 26,884 cycles

CRACKED RT OVERWING FRAME STA Y=674 PROJECTION LONG 18R CPAX. RT OVERWING FRAME STA Y=674 WAS REPLACED WITH TASK CARD NUMBER:107-0002:5310-01436-03B.

Part: FLOOR SUPPORT — CORRODED (BS 157-190) · corrosion level 2 · airframe 40,984 hrs · 26,884 cycles

CORROSION ON FLOOR SUPPORT BS 157 TO 190, LBL 58. THE FLOOR SUPPORT WAS REPLACED IAW DWG 9910078, REV JC, SRM 51-41-02 AND 51-41-05.

Part: FLOOR PANEL — DELAMINATED (NOT REPORTED) · airframe 40,984 hrs · 26,884 cycles

DELAMINATED FLOOR PANEL. THE FLOOR PANEL WAS REPAIRD IAW SRM 53-20-50, REP 3.

Part: CARGO TRACK — CRACKED (BS 937) · airframe 40,984 hrs · 26,884 cycles

CRACKED CARGO TRACK AT BS 937 IN THE AFT CARGO BAY. THE CARGO TRACK WAS REPLACED IAW SRM 53-20-51-0I. FIG.1, 51-41-01, 51-41-02 ,51-41-05, AND 51-10-04, PAR 15, AND 21.

Part: BEAM — CRACKED (NLG WW) · airframe 40,984 hrs · 26,884 cycles

CRACK ON RIGHT DOOR JAMB BEAM STA Y=46 APPROX AT NOSE GEAR WHEEL WELL. CRACK ON RIGHT DOOR JAMB BEAM STA Y=46 WAS REPAIRED PER SRM 53-10-14-2R-2.

Part: INTERCOSTAL — CRACKED (BS 636) · airframe 40,984 hrs · 26,884 cycles

CRACK ON INTERCOSTAL BS 636 Z=-3 X=0 FWD CARGO COMPARMENT. THE INTERCOSTAL WAS REPAIRED IAW SRM 53-00-00-2R, FIG 201.

Part: PAN — CRACKED (CARGO DOOR) · airframe 40,984 hrs · 26,884 cycles

CRACKED INNER PAN ON FWD EDGE AND BEAM NR 1 BS 370 AT FWD CARGO DOOR. REPAIRED IAW SRM 52-30-02 -2R, PROCEDURE 1, REPAIR 1, TABLE 201.

Part: LONGERON — CRACKED (BS 1133) · airframe 40,984 hrs · 26,884 cycles

CRACKED LONGERON 2L, BS 1133 IN THE AFT ACCESORY COMPARTMENT. THE LONGERON WAS REPAIRED IAW SRM 53-00-05.

Part: FRAME — CRACKED (BS 1225) · airframe 40,984 hrs · 26,884 cycles

CRACKED FRAME BS 1225 BETWEEN 5 - 6 HRS, AND 8 - 9 HRS. FRAME WAS REPLACED IAW SRM 51-41-02.

Part: PAN — CRACKED (CARGO DOORWAY) · airframe 40,984 hrs · 26,884 cycles

CRACK ON FWD EDGE OUTER PAN BETWEEN BEAMS 1 AND 2 IN THE AFT CARGO DOOR. FWD EDGE OUTER PAN WAS REPAIRED IAW SRM 52-30-02-2R, PROCEDURE 4, REPAIR 4.

Part: ACCESS DOOR — CORRODED (WING) · corrosion level 2 · airframe 40,984 hrs · 26,884 cycles

CORROSION ON COUNTERSINK OF FUEL ACCESS DOOR 141AR. ACCESS PLATE 141AR WAS MEASURED COUNTERSINK 0.745" AND HOLE 0.315" THEREFORE OUT OF LIMITS THEREFORE FUEL ACCESS WAS REPLACED PER SRM 57-10-01-2R-2 CONDITION I 1(A) AND PART NUMBER WAS VERIFIED PER IPC 57-22-01-01.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,984 hrs · 26,884 cycles

CORROSION ON PREVIOUS DOUBLER REPAIR LOWER SURFACE RT SIDE STA Y=894 TO Y=903 BTW X=-54 AND X=-60 AT PAX CABIN (CPAX). DAMAGE PRODUCTION DOUBLER LOWER SURFACE RT SIDE STA Y=894 TO Y=903 BTW X=-54 AND X=-60 WAS REPLACED PER SRM 53-20-51 AND 51-41-05.

Part: CUSP WEB — CRACKED (BS 600) · airframe 40,984 hrs · 26,884 cycles

CRACK ON RT CUSP WEB BS 600 BETWEEN RBL 54 AND 60. THE CUSP WEB WAS REPAIRED SRM 53-00-55, 51-10-04, 51-41-05, AND 51-41-02.

Part: FLOOR SUPPORT — CORRODED (BS 120-148) · corrosion level 2 · airframe 40,984 hrs · 26,884 cycles

CORROSION ON FLOOR SUPPORT BS 120 TO 148, RBL 54. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-41-02, 51-10-04 PAR 15 AND 16, AND DRAWING 9936533, REV CM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,984 hrs · 26,884 cycles

CORROSION OUT OF LIMITS ON SEAT TRACK X=-22 RT AT STA Y=427 TO Y=430. SEAT TRACK WAS REPAIRED PER SRM 53-20-52-2R-1, 51-10-04 PAR. 21, 15, 51-41-01.

Part: CUSP WEB — CRACKED (BS 250) · airframe 40,984 hrs · 26,884 cycles

CRACK ON CUSP WEB BS 250 RBL 58. THE CUSP WEB WAS REPAIRED IAW SRM 53-00-55-2R-4, FIG 215, SRM 51-41-02, AND SRM 51-10-04 PAR 15, 21, 38.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 40,984 hrs · 26,884 cycles

CRACK ON RT CUSP WEB STA Y=715 BTW X=- 44 AND X=-54 AT PAX CABIN. CUSP WEB WAS REPAIRED PER SRM 53-00-55, 51-10-04, AND 51-41-02.

Part: SUPPORT — CORRODED (BS 217) · corrosion level 2 · airframe 40,984 hrs · 26,884 cycles

CORROSION ON PAX CABIN GALLEY SUPPORT AT BS 217, RBL 11. THE SUPPORT WAS REPLACED IAW SRM 51-40-08, 51-41-01, 51-41-02, AND 51-41-05.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 40,984 hrs · 26,884 cycles

CORROSION ON SETTLEMENT AREA AND COUNTERSINK OF FUEL ACCESS DOOR 520CT AND 620CT. THE ACCESS PANELS WERE REPLACED IAW SRM 57-10-01, REPAIR 2.

Part: PAN — CRACKED (BS 813-832) · airframe 40,984 hrs · 26,884 cycles

CRACKED AFT UPPER CORNER ON RING PAN BTW BS 813 - 832 IN PASSENGER CABIN. THE RING PAN WAS REPAIRED IAW SRM 56-20-02.

Part: SKIN PANEL — DAMAGED (FUSELAGE) · airframe 40,096 hrs · 26,249 cycles

LIGHTNING STRIKE DAMAGE ON WINDOW PANEL 15R. REMOVED WINDOW PANEL PER SRM 51-40-02. PREPARED NEW PANEL FOR INSTALLATION PER SRM 51-40-02 AND 51-40-08. INSTALLED NEW PANEL PER SRM 51-40-02. RII COMPLIED WITH.

Part: PROXIMITY SENSOR — OUT OF LIMITS (MLG) · airframe 37,189 hrs · 24,082 cycles

WHILE ON APPROACH, ALL 3 GEAR INDICATIONS WERE RED "UNSAFE". THE CREW PERFORMED A MANUAL GEAR EXTENSION AND LANDED WITHOUT FURTHER INCIDENT, OTHER THAN THE GEAR DOORS BEING OPEN ON LANDING. MAINTENANCE FOUND ALL POSITION/WARNING SENSORS AND THE DIMENSIONAL LIMITS OF THE PROXIMITY SENSORS WERE WITHIN AMM LIMITS. THE GEAR WAS SWUNG WITH NO DEFECTS. MAINTENANCE REPLACED THE PSEU.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 36,092 hrs · 23,308 cycles

THE AFT LEFT OVERWING EMERGENCY LIGHT WAS FOUND INOPERATIVE. REPLACED THE LAMP IAW MM.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 36,092 hrs · 23,308 cycles

AFT F/A STATION LOWER EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. REPLACED THE LAMP IAW MM.

Part: LAMP — INOPERATIVE (EMEGENCY LIGHT) · airframe 36,092 hrs · 23,308 cycles

TAIL COMPARTMENT THIRD EMERGENCY LIGHT WAS FOUND INOPERATIVE. REPLACE THE LAMP IAW MM.

Part: LIGHT — BROKEN (CABIN) · airframe 36,092 hrs · 23,308 cycles

CENTER AISLE EMER LIGHT BRACKET BROKEN AT ROW 1. R & R LIGHT IAW AMM.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 36,092 hrs · 23,308 cycles

LEFT FWD OVERWING EMERGENCY EXIT LIGHT HAS A BULB INOPERATIVE. REPLACED THE BULB IAW MM.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 36,092 hrs · 23,308 cycles

TAIL COMPARTMENT FIRST EMERGENCY LIGHT WAS FOUND INOPERATIVE. REPLACED THE LAMP IAW MM.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 36,092 hrs · 23,308 cycles

THE RIGHT FWD OVERWING EMERGENCY EXIT LIGHT HAS A BULB INOPERATIVE. REPLACED THE BULB IAW MM.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 34,552 hrs · 22,267 cycles

MAIN CABIN FLOOR SUPPORT CRACKED AT BS 237, BETWEEN LBL 22 TO RBL 12. R & R SUPPORT IAW SRM & DWG.

Part: WEB — CRACKED (FUSELAGE) · airframe 34,552 hrs · 22,267 cycles

L1 DOOR AFT CUT OUT TORQUE BOX WEB CRACKED AFT OF ROLLER FITTING. R & R WEB IAW SRM & DWG.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 34,552 hrs · 22,267 cycles

CUSP WEB CRACKED AT BS 908, LBL 54. R & R CUSP WEB IAW SRM & DWG.

Part: FITTING — DAMAGED (R1 DOOR) · airframe 34,552 hrs · 22,267 cycles

R1 DOOR EMER EVAC SLIDE, BOTH GIRT BAR FITTINGS DAMAGED. R & R FITTINGS IAW SRM.

Part: ROLLER — CORRODED (TE FLAP) · airframe 34,552 hrs · 22,267 cycles

RIGHT WING BELOW FLAP CTR MOVABLE VANE INBD TRACK ROLLER ON TRACK CORRODED, R & R ROLLER IAW SRM.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 34,552 hrs · 22,267 cycles

MAIN CABIN FLOOR SUPPORT CORRODED BETWEEN BS 160 - 200, RBL 54. R & R FLOOR SUPPORT IAW SRM & DWG.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 34,552 hrs · 22,267 cycles

MAIN CABIN FLOOR SUPPORT CORRODED AT BS 200, BETWEEN RBL 43 - 7. R & R SUPPORT IAW SRM & DWG.

Part: ATTACH ANGLE — CRACKED (LT WING) · airframe 34,552 hrs · 22,267 cycles

LEFT WING AILERON OTBD HINGE FITTING INBD ATTACH ANGLE CRACKED. R & R ANGLE IAW SRM & DWG.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 34,552 hrs · 22,267 cycles

MAIN CABIN FLOOR SUPPORT CORRODED AT BS 200, BETWEEN RBL 44 - 55. R & R SUPPORT IAW SRM & DWG.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 34,552 hrs · 22,267 cycles

MAIN CABIN CUSP WEB CRACKED AT BS 674, LBL 45. REPAIRED WEB IAW SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 34,552 hrs · 22,267 cycles

MAIN CABIN CUSP WEB CRACKED AT BS 441, RBL 60. REPAIRED CUSP WEB IAW SRM.

Part: SIGN — LOOSE (CABIN) · airframe 35,824 hrs · 23,126 cycles

FORWARD CEILING MOUNTED EMER EXIT SIGN LOOSE. SECURED SIGN IAW SIP.

Part: LANYARD — LOOSE (R1 DOOR) · airframe 34,798 hrs · 22,428 cycles

R1 DOOR EMER EVAC SLIDE LANYARD LOOSE. SECURED LANYARD IAW MT.

Part: SIGN — LOOSE (CABIN) · airframe 34,742 hrs · 22,390 cycles

FORWARD OVERHEAD CTR EMERGENCY EXIT SIGN LOOSE AT ROW 1. SECURED SIGN IAW SIP.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

LT CUSP WEB CRACKED AT BS 636 LBL 54. REPAIRED CUSP WEB IAW SRM.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

RT WING TO BODY FAIRING ANGLE CRACKED AT BS 813 LONGERON 23R. R & R ANGLE IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

RT CUSP WEB CORRODED BETWEEN BS 527 TO BS 537. R & R CUSP WEB IAW SRM.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

CABIN WINDOW 33 LT PANE FRAME AFT LOWER CORNER CRACKED BETWEEN BS 832 TO BS 851. REPAIRED FRAME IAW SRM & DRAWING.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

CABIN WINDOW 33 RT PANE FRAME AFT UPPER CORNER CRACKED BETWEEN BS 832 TO BS 851. REPAIRED FRAME IAW SRM & DRAWING.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

CABIN WINDOW NR 36 LT PANE FRAME AFT LOWER CORNER CRACKED BETWEEN BS 889 TO BS 908. REPAIRED FRAME IAW SRM & DRAWING.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

SUPPORT FITTING CRACKED AT BS 732 RBL 44. R & R FITTING IAW SRM & DRAWING.

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

LT FLOOR PANEL 222PF DELAMINATED BETWEEN BS 541 TO BS 617. R & R PANEL IAW SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

SEAT TRACK SECTION CORRODED BETWEEN BS 898 TO BS 1022 RBL 44. REPAIRED SEAT TRACK IAW SRM.

Part: DOOR — CRACKED (RT WING) · airframe 33,582 hrs · 21,633 cycles

RT WING INBD BUTE DOOR INBD END CRACKED. REMOVED DOOR IAW MM.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

CABIN WINDOW 34 RT PANE FRAME AFT LOWER CORNER CRACKED BETWEEN BS 851 TO BS 870. REPAIRED FRAME IAW SRM & DRAWING.

Part: BONDING STRAP — CRACKED (RT WING) · airframe 33,582 hrs · 21,633 cycles

RT WING FIXED LE INBD SIDE BONDING STRAP CRACKED. R & R STRAP IAW SRM & DRAWING.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

RT CUSP WEB CORRODED BETWEEN BS 579 TO BS 617 RBL 57. R & R CUSP WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

RT CUSP WEB CORRODED BETWEEN BS 408 TO BS 412 RBL 57. R & R CUSP WEB IAW SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

RT CUSP WEB CRACKED BETWEEN BS 674 TO BS 775. REPAIRED CUSP WEB IAW SRM.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

CABIN WINDOW 34 LT PANE FRAME CORNER CUTOUT CRACKED BETWEEN BS 851 TO BS 870. REPAIRED FRAME IAW SRM & DRAWING.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

SUPPORT FITTING CRACKED AT BS 737 LBL 44. R & R FITTING IAW SRM & DAC DRAWING.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

CHORD DOUBLER CORRODED AT BS 130, LONGERON 30L. R & R DOUBLER IAW SRM & DRAWING.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

LONGERON CRACKED AT BS 1116 LONGERON 2R. R & R LONGERON IAW SRM.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

LT WW FWD DOOR CUTOUT INBD SUPPORT ANGLE CRACKED. R & R ANGLE IAW SRM & DRAWING.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

FORMER CRACKED AT BS 1152 LONGERON 2L. R & R FORMER IAW SRM & DAC DRAWING.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

FORMER CRACKED AT BS 1152 LONGERON 2R. R & R FORMER IAW SRM & DAC DRAWING.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

FORMER CRACKED AT BS 674 RBL 38. R & R FORMER IAW SRM & DRAWING.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

FORMER CRACKED AT BS 674 LBL 38. R & R FORMER IAW SRM & DRAWING.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

FORMER CRACKED AT BS 715 RBL 24. REPAIRED FORMER IAW SRM.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

LT SIDE SUPPORT ANGLE CRACKED AT BS 1178. REPAIRED ANGLE IAW SRM & DRAWING.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

FORMER CRACKED AT BS 715 LBL 24. REPAIRED FORMER IAW SRM & DRAWING.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

FORMER CRACKED AT BS 696 RBL 30. R & R FORMER IAW SRM & DRAWING.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

FORMER CRACKED AT BS 696 LBL 30. REPAIRED FORMER IAW SRM & DRAWING.

Part: FRAME — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

FRAME CRACKED AT BS 715 LONGERON 9R TO LONGERON 19R. R & R FRAME IAW SRM.

Part: FITTING — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

LT MAIN FRAME WING TO FUSELAGE FITTING CRACKED AT BS 661 LONGERON 22L. R & R FITTING IAW SRM & DAC DRAWING.

Part: BONDING STRAP — CRACKED (LT WING) · airframe 33,582 hrs · 21,633 cycles

LT WING LE BONDING STRAP CRACKED. R & R STRAP IAW SRM & DRAWING.

Part: FITTING — CRACKED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

RT MAIN FRAME WING TO FUSELAGE FITTING CRACKED AT BS 661 LONGERON 22R. R & R FITTING IAW SRM & DAC DRAWING.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 33,582 hrs · 21,633 cycles

AFT CARGO DOOR JAMB LOWER AREA CORRODED BETWEEN BS 994 TO BS 1022 LONGERON 28R. R & R JAMB IAW SRM.

Part: INTERCOSTAL — CRACKED (L1 DOOR) · airframe 33,582 hrs · 21,633 cycles

L1 DOOR INTERCOSTAL INSIDE HANDLE BOX CRACKED. R & R INTERCOSTAL IAW SRM.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 34,009 hrs · 21,918 cycles

AFT CARGO DOOR JAMB LOWER AREA CORRODED. REPAIRED JAMB IAW SRM.

Part: ACCESS PANEL — LOOSE (RT WING) · airframe 32,454 hrs · 20,889 cycles

FUEL SEEPING FROM TOP OF RT WING OUT OF INBOARD FUEL TANK ACCESS PANEL. TORQUED FUEL TANK ACCESS PANEL IAW TRA17-28-TR00148.

Part: BATTERY — FAULTY (CABIN) · airframe 31,150 hrs · 20,090 cycles

"EMERGENCY LIGHTS" WERE ON WHEN WE CAME TO AIRCRAFT. (THE SWITCHES WERE ALL OFF). REMOVED AND REPLACED EMERGENCY LIGHT BATTERIES. PER T/C #340 ON W/O #278454.

Part: SLIDE — OUT OF POSITION (L1 DOOR) · airframe 30,772 hrs · 19,857 cycles

L1 DOOR SLIDE PACK FELL OUT WHEN DOOR OPENED. INSTALLED L1 DOOR SLIDE PER 717 AMM 25-61.

Part: LENS — MISSING (CABIN) · airframe 29,741 hrs · 19,195 cycles

RIGHT EEPLS LENS MISSING AT ROW 3. INSTALLED LENS PER AMM.

Part: LIGHT — MISSING (CABIN) · airframe 29,741 hrs · 19,195 cycles

RIGHT EEPLS BULBS MISSING AT ROW 3. INSTALLED BULBS PER AMM.

Part: SKIN — DENTED (FUSELAGE)

LEFT SIDE FUSELAGE SKIN, STA 522 TO 541, LONG 26L, DENTED. ACCOMPLISHED FUSELAGE SKIN DOUBLER AND FILLER REPAIR PER B717 SRM 53-00-01 REP 6, 53-00-06 REP 2, 51-10-04. SEE NR 24724.

Part: ENGINE — FAILED (RIGHT)

ON CLIMBOUT 18500 FT LOUD EXPLOSION RT ENG FAILURE OCCURRED SEVERE DAMAGE NOTED. REMOVED AND REPLACED NR 2 ENGINE PER TASK CARD 603 RUN AND LEAK CHECK GOOD OK FOR SERVICE.

Part: SIGN — MISSING (CABIN)

FWD EMERGENCY EXIT SIGN IN BUSINESS CLASS IS MISSING. FOUND AND INSTALLED 'EXIT' SIGN ON O/H AS REQUIRED.

Part: WINDOW — DAMAGED (EVAC SLIDE)

TAIL CONE SLIDE ENCLOSURE VIEWING WINDOW HAS A HOLE IN IT AS WELL AS / SEVERAL CRACKS. REMOVED AND REPLACED AFT TAIL CONE SLIDE AS PER AMM 25-61-02.

Part: LENS — MISSING (CABIN)

THE 3 EPL LENSES MISSING. INSTALLED LENS AS REQUIRED.

Part: SKIN — DENTED (FUSELAGE)

FWD CAPTAIN'S WINDOW AREA DENTED FROM BIRD STRIKE. ACCOMPLISHED CLASS II DOUBLER REPAIR PER B717 DRAWING SG9530002 AND EA17-53-02505IR. REF NR2865.

Part: SKIN — DAMAGED (ELEVATOR)

LIGHTNING STRIKE DAMAGE TO LT TOP AFT SURFACE OF LT ELEVATOR. LIGHTNING STRIKE DAMAGE REPAIRED IAW B717 SRM 51-70-13 REPAIR 1. CALCULATED WEIGHT AND BALANCE MOMENT CHANGE IS 0.336 IN LBS PER SRM 51-60-02 NO CHANGE TO DATA TAG REQUIRED WITHIN LIMITS AT -695.5 IN LBSLTW WATCH REQUIRED FOR VISUAL INSPECTION EVERY 3000 CYCLES FOR DAMAGE TOLERANCE MAINTENANCE REQUIREMENTS AREA PRIMED AND PAINTED AS REQUIRED. OK FOR SERVICE.

Part: FRAME — DAMAGED (FUSELAGE)

AFT RIGHT STA 1178 CANTED FRAME INSPECTION IDENTIFIED CONFIGURATION 2 CONDITION 4. ACCOMPLISHED REPAIR TO AFT FUSELAGE FRAME CAP, CANTED STA 1178.225, RIGHT SIDE IAW AIRTRAN TASK CARD 17-5310-2989.

Part: FRAME — DAMAGED (FUSELAGE)

AFT LEFT STA 1178 CANTED FRAME INSPECTION IDENTIFIED CONFIGURATION 1 CONDITION 3. ACCOMPLISHED REPAIR TO AFT FUSELAGE FRAME CAP, CANTED STA 1178.225, LEFT SIDE IAW AIRTRAN TASK CARD 17-5310-2975.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 160 TO 200, RBL 7, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 200, LBL 7 TO RBL 7, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: WEB — CORRODED (FUSELAGE)

CABIN FLOOR WEB, STA 160 TO 200, LBL 7 TO RBL 7 CORROSION. ACCOMPLISHED FLOOR WEB DOUBLER AND FILLER REPAIR PER B717 SRM 51-70-10.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 160 TO 200, RBL 7, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-01 AND B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 160, LBL 6 TO RBL 6, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 148, RBL 32 TO RBL 44, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 200, RBL 7 TO RBL 44, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (CABIN)

CABIN FLOOR SUPPORT, STA 200, LBL 9 TO LBL 14, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02. .

Part: FLOOR PANEL — CORRODED (CABIN)

GALLEY ENTRANCE FLOOR FILLER PANEL, STA 160 TO 200, RBL 54, CORROSION. ACCOMPLISHED FLOOR FILLER PANEL REPLACEMENT PER B717 SRM 51-41-01.

Part: SLIDE — LOW PRESSURE (L1 DOOR)

L1 DOOR ESCAPE SLIDE PRESSURE NEEDLE GAUGE IS IN THE RED. REMOVED AND REPLACED L1 DOOR SLIDE REF 25-61.

Part: BATTERY PACK — DEFECTIVE (CABIN)

EMERGENCY LIGHTS ON SEATS 1 - 10 INOPERATIVE. OVERHEAD LIGHTS IN AREA OKAY. FOUND LAMPS AT SEAT 30 DAMAGED. SUSPECT DAMAGED LAMPS CAUSED ON OUTPUT AT B5-118 BATTERY PACK TO BLOW FUSE. REMOVED AND REPLACED BATTERY SUPPLY ASSY IAW EM CMM 33-50-02. OPS CHECK OK.

Part: SKIN — DAMAGED (T/E FLAP)

LEFT FLAP DAMAGE DUE TO FOD. INSTALLED TWO DOUBLER REPAIR AT LEFT INBOARD AREA IAW AIRTRAN RES 06-05-19. MATERIAL USED 0.063 7075T6. SIZE 7" X 7.5" AND 6" X 8".