N980AT

Part: FUEL CELL — LEAKING (ZONE 500) · airframe 58,963 hrs · 41,333 cycles

FUEL LEAK FOUND DURING INSPECTION OF THE L/H WING AFT LWR SKIN DOUBLER AT XRS=164. CORRECTIVE ACTION: REPAIRED PER ER/A 14-621176. (1243963).

Part: SKIN — DAMAGED (ZONE 600) · airframe 58,938 hrs · 41,305 cycles

EXISTING REPAIR FOUND THAT IMPACTS INSPECTION ACCOMPLISHMENT. REPAIR INVESTIGATION REQUIRED BEFORE FURTHER FLIGHT. RH WING XRS 14- XRS 177. REF. EA 619064-14AD REV. B SECT II. DVI OF AFT SIDE OF SPAR CAP AT STOP DRILL SHOWS NO DISCREPANCY. (1199238)

Part: BATTERY PACK — INOPERATIVE (ZONE 200) · airframe 58,877 hrs · 41,242 cycles

EMERGENCY LIGHTS INOPERATIVE ABOVE OVER WINGS EXITS. REMOVED AND REPLACED BATTERY PACK B5-121 REF AMM 33-51 (7280198)

Part: SIGN — DETACHED (ZONE 200) · airframe 58,877 hrs · 41,242 cycles

EMERGENCY EXIT SIGN ON CEILING ABOVE ROW 1 DETACHING FROM CEILING. RESECURED EXIT SIGN PER B-717 AMM 33-51. (7354500)

Part: ELEC CONNECTOR — DIRTY (ZONE 200) · airframe 58,798 hrs · 41,169 cycles

AFT EMERGENCY LIGHT FLASHING. CLEANED CONNECTOR ON EMERGENCY LIGHT BATTERY PACK B5-260 AND OPS CHECKED IAW AMM 33-51, CHECKED GOOD (7280156).

Part: BATTERY PACK — NO TEST (ZONE 200) · airframe 58,776 hrs · 41,148 cycles

EMER LIGHT ABOVE AFT FA JUMPSEAT STAYS ILLUMINATED WHEN IN ARM. T/S REF WDM 33-51. FOUND EMER LIGHT BATTERY PACK B5-260 WATER DAMAGED. R&R'D BATTERY PACK & BATTERY REF B717 AMM 33-51. OPS CHECK GOOD. (7280148)

Part: SIGN — DETACHED (ZONE 200) · airframe 58,468 hrs · 40,861 cycles

SHIP 6546 EMERGENCY EXIT SIGN COVER HANGING LOOSE IN FIRST CLASS CABIN. CORRECTIVE ACTION: RE-SECURED EMERGENCY EXIT SIGN. OK FOR SVC (7552948)

Part: DOUBLER — LEAKING (ZONE 500) · airframe 58,440 hrs · 40,832 cycles

SHIP 9546 FUEL LEAK FOUND DURING INSPECTION OF LH WING AFT LOWER SKIN DOUBLER AT XRS=164. CORRECTIVE ACTION: FUEL LEAK REPAIRED ON ERA 621176-14AD REV C (1044305)

Part: ANGLE — NOT REPORTED (ZONE 500) · airframe 58,440 hrs · 40,832 cycles

SHIP 9546 C/W LH WING BULKHEAD CLIP XRS164 PART MANUFACTURE ERA 626984-14 REV ORIG. CORRECTIVE ACTION: COMPLIED WITH LH WING BULKHEAD CLIP XRS164 PART MANUFACTURE ER/A 626894-14 REV A. (1043812)

Part: REPAIR — NO DISCREPANCY (ZONE 600) · airframe 58,434 hrs · 40,825 cycles

EXISTING REPAIR FOUND. CONTACT LIASON ENGINEERING FOR REPAIR PROCEDURES PRIOR TO FURTHER FLIGHT (R/H WING). PER ENGINEERING C/W ERA 619064-14AD REV B SEC II STEP 3. NO ISSUES NOTED.

Part: SPAR CAP — DAMAGED (ZONE 500) · airframe 58,434 hrs · 40,825 cycles

C/W 621176-14AD REV B LH WING LOWER SPAR CAP LEAK REPAIR. DAMAGED AREA REPAIRED PER ERA 621176-14AD REV B PRI 621176-14AD (1043689).

Part: REPAIR — DAMAGED (NOT REPORTED) · airframe 58,434 hrs · 40,825 cycles

SHIP 9546 EXISTING REPAIR FOUND. CONTACT LIASON ENGINEERING FOR REPAIR PROCEDURES PRIOR TO FURTHER FLIGHT. REPAIRED PER ERA 6190064-14AD (0984966)

Part: REPAIR — NOT REPORTED · airframe 58,263 hrs · 40,674 cycles

-AD- EXISTING REPAIR FOUND, OK TO CONT THE WC INSP AS AUTHORIZED BY THE TIME CONT ITEMS STATEMENT FOR SEC I OF ERA 619064-14AD REV B. (LP #7184929)

Part: REPAIR — NOT REPORTED · airframe 58,263 hrs · 40,674 cycles

-AD- EXISTING REPAIR FOUND, CONTACT LIASON ENGINEERING FOR REPAIR PROCEDURES PRIOR TO FUTHER FLIGHT. FC 5720-01103-01A. OK TO CONT THE WC INSP AS AUTHORIZED BY THE TIME CONT ITEMS STATEMENT FOR SEC II OF ERA 621176-14AD REV A. (LP #7184928)

Part: FUEL CAP — LEAKING (ZONE 500) · airframe 58,151 hrs · 40,576 cycles

-AD- WORKING PRI 621176-14AD REV "O" B717-200 LH WING REAR SPAR LOWER CAP FUEL LEAK. SUMMARY SEE NRC 004-0001:5720-01103-01A/004 00004: CMOR - COMPLIED WITH ER/A 621176-14 REV A, PRI REV "0", "1", "2", "3", "4", "5", "6", AND "7" REPAIR INSTRUCTIONAL STEPS. ENSURE ALL ER/A 621176-14 REV A. PRI REV "0", "1", "2", "3", "4", "5", "6", AND "7" REPAIR INSTRUCTIONAL STEPS ARE COMPLETED AND MATCH FINAL. LH WING / REAR SPAR LOWER CAP FUEL LEAK. ER/A 621176-14 REV A SECTION III LEAK EVALUATION. (LP #0908480)

Part: NONE — NONE (NONE) · airframe 57,904 hrs · 40,344 cycles

IN REFERENCE NRC 00924: LEVEL AND SHORE AIRCRAFT IN ACORDANCE WITH AMM 07-11-00 AS WELL AS PER FIGURE 4 OF BOEING SERVICE SKETCH 3268E PER PRI 621176-14 REV 0 STEP 1 A) AND PERFORM DAILY CHECK UNTIL REMOVED. SUMMARY NRC 00981: SHORINGS WERE INSTALLED AND VERIFIED ON STA Y=218, STA Y=661.106, STA Y=813.000, STA XRS=69.000, STA XRS=267.000, AND STA XRS=477 PER PRI 621176-14 REV 0 STEP 1, ER/A 621176-14AD REV ORIGINAL. AND SHORINGS WERE REMOVED PER B717 AMM 07-20-01. ASSOCIATED ER/A 14-621176 ADDED FOR AC 9546. (LP #0807418)

Part: FITTING — DAMAGED (ZONE 500) · airframe 57,904 hrs · 40,344 cycles

PERFORM COLDWORK ON INBOARD BRACE FITTING DOUBLER XRS=164 AT LH WING. SUMMARY OF NRC 00924: INBOARD BRACE FITTING DOUBLER XRS=164 AT LH WING WAS REPAIRED PER PRI 621176-14 REV 10 AND ERA 621176-14AD REV ORIGINAL SECTION I: PERMANENT REPAIR. ALSO FAIRING WAS REWORKED PER PRI 623505-14 REV 1 AND ERA 623505-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. TIME CONTROLLED ITEMS SECTION DTE MONITORING UNDER LOG PAGE 0761182 PER ER/A 621176-14D REV ORIGINAL. ASSOCIATED ER/A 14-621176 ADDED FOR AC 9546. (LP #0807042)

Part: SPAR CAP — DAMAGED (ZONE 600) · airframe 57,904 hrs · 40,344 cycles

-AD- AWR, AA, AD, IN REF TO AMDS 5720-01103-01B STEP 7: REPAIR IN PROGRESS AT RIGHT WING LOWER REAR SPAR CAP THATS INCLUDES LOWER WING SKIN AND DOUBLER BTW STA XRS 150 AND XRS 177. SUMMARY OF NRC 00918: THIS REPAIR PROVIDED WITH FAA AMOC APPROVAL AND INCLUDES WITH REPETITIVE INSPECTIONS, THRESHOLD AND INTERVALS PER ERA 619064-14AD REV B UNDER LOG PAGE 0703165. ASSOCIATED ER/A 14-619064 ADDED FOR AC 9546. (LP #0802278)

Part: SPAR CAP — CRACKED (ZONE 600) · airframe 57,904 hrs · 40,344 cycles

CRACK ON RH WING LOWER REAR SPAR CAP AROUND SECOND FASTENER FROM FLAP HING FITTING STA XW=154 OUTBOARD TO INBOARD DIRECTION. SUMMARY OF NRC 00347: CRACK ON RH WING LOWER REAR SPAR CAP AROUND SECOND FASTENER FROM FLAP HING FITTING STA XW=154 OUTBOARD TO INBOARD DIRECTION WAS REPAIRED PER PRI 619064-14 REV 32 AND ERA 619064-14AD REV A, SECTION I: TIME LIMITED REPAIR ACCOMPLISHMENT OF SECTION II AND SECTION III WILL BE UNDER LOG PAGE #0703165. ASSOCIATED ER/A 14-619064 ADDED FOR AC 9546. (LP #0789388)

Part: UNKNOWN — NO DISCREPANCY (UNKNOWN) · airframe 57,904 hrs · 40,344 cycles

-AD RELATED- AMDS 5720-01103-01A: PERFORM STEP 13. SUMMARY NRC 00919: (ET) HFEC INSPECTION WAS PERFORMED. NO CRACKS WERE FOUND PER B717 CARD 5720-01103-01A, STEP 13 AND B717 DC/MD NDT SPM PART 6, 06-10-01.001. ASSOCIATED AA 5720-01103 ADDED FOR AC 9546. (LP #0576451)

Part: UNKNOWN — NO DISCREPANCY (UNKNOWN) · airframe 57,904 hrs · 40,344 cycles

-AD RELATED- AMDS 5720-01103-01A: PERFORM STEP 15 AND 16. SUMMARY NRC 00921: SEALANT WAS REMOVED AND APPLIED PER B717 AMM 20-60-01 PER AMDS 5720-01103-01A ALSO (ET) HFEC INSPECTION WAS PERFORMED. NO CRACKS WERE FOUND PER B717 CARD 5720-01103-01A, STEP 16 AND B717 DC/MD NDT SPM PART 6 06-10-01.001. ASSOCIATED AA 5720-01103 ADDED FOR AC 9546. (LP #0576448)

Part: UNKNOWN — NO DISCREPANCY (UNKNOWN) · airframe 57,904 hrs · 40,344 cycles

-AD RELATED- AMDS 5720-01103-01A: PERFORM STEP 14. SUMMARY NRC 00920: (ET) HFEC INSPECTION WAS PERFORMED. NO CRACKS WERE FOUND PER B717 CARD 5720-01103-01A, STEP 14 AND B717 DC/MD NDT SPM PART 6, 06-10-01.001. ASSOCIATED AA 5720-01103 ADDED FOR AC 9546. (LP #0576445)

Part: FASTENER — SHEARED (ZONE100 FRAME) · airframe 57,904 hrs · 40,344 cycles

FASTENER SHEARED OFF ON FRAME REAR SIDE STA Y=1152 AT AFT ACCESORY COMPARTMENT. SUMMARY OF NRC 00441: FRAME REAR SIDE STA Y=1152 AT AFT ACCESSORY COMPARTMENT WAS REPAIRED PER PRI 619773-14 REV 3 AND ERA 619773-14 REV ORIGINAL, SECTION I: PERMANENT REPAIR. ACCOMPLISH SECTION II, REPETITIVE INSPECTION, WITHIN 3,000 CYCLES FROM TIME OF REPAIR INSTALLATION FROM SEPTEMBER 06, 2024, AND REPEAT WITHIN EVERY 3,000 CYCLES THEREAFTER PER ERA 619773-14 REV ORIGINAL, LOG PAGE #0552880. (LP #0559771)

Part: FASTENER — SHEARED (ZONE 100 FRAME) · airframe 57,904 hrs · 40,344 cycles

FASTENER SHEARED OFF ON FRAME REAR SIDE STA Y=1152 AT AFT ACCESORY COMPARTMENT. SUMMARY OF NRC 00441: FRAME REAR SIDE STA Y=1152 AT AFT ACCESSORY COMPARTMENT WAS REPAIRED PER PRI 619773-14 REV 3 AND ERA 619773-14 REV ORIGINAL, SECTION I: PERMANENT REPAIR. ACCOMPLISH SECTION II, REPETITIVE INSPECTION, WITHIN 3,000 CYCLES FROM TIME OF REPAIR INSTALLATION FROM SEPTEMBER 06, 2024, AND REPEAT WITHIN EVERY 3,000 CYCLES THEREAFTER PER ERA 619773-14 REV ORIGINAL, LOG PAGE #0552880. (LP #0559779)

Part: LUG — CORRODED (LT FLAP HINGE) · corrosion level 2 · airframe 57,904 hrs · 40,344 cycles

CORROSION ON OUTER/INNER LUGS (INNER PART) AND BUSHING OF LH FLAP OUTBOARD HINGE. SUMMARY OF NRC 00657: CORROSION LEVEL 2. LH FLAP OUTBOARD HINGE WAS REPAIRED PER PRI 619369-14 REV 4 & ER/A 619369-14 REV ORIG. REPAIR APPROVAL IS LIMITED TO 24 MONTHS FROM 29AUG24. ADDITIONAL ENGINEERING AUTHORIZATION (ER/A REVISION) IS REQUIRED FOR CONTINUED SERVICE BEYOND THIS LIMIT. UNDER LOG 0537163 ASSOCIATED ER/A 14-639369 ADDED FOR AC 9546. (LP #0548101)

Part: FUEL CELL — CORRODED (ZONE 100) · corrosion level 2 · airframe 57,904 hrs · 40,344 cycles

AIRCRAFT 9546, CORROSION ON THE LOWER SKIN OF THE CENTRAL TANK APPROX. STA. Y=748 AND STA XCW=-25 AND Z=-29 IN THE FRONT WALL ON RH MLG WHEEL WELL. CORRECTIVE ACTION: LOWER SKIN OF THE CENTRAL TANK APPROX. STA. Y=748 AND STA XCW=-25 AND Z=-29 WAS REPAIRED PER PRI 619112-14 REV. 3 AND ERA 619112-14AD REV. ORIGINAL, SECTION I: PERMANENT REPAIR. REPAIR APPROVAL IS LIMITED TO 24 MONTHS FROM 16-AUG-2024. (LP 0517863)

Part: PAN — CRACKED (ZONE 100) · airframe 57,904 hrs · 40,344 cycles

CRACK (3 EA) ON OUTER PAN AT BEAM #3, #4, AND #5 INTERNAL STRUCTURE AT FWD CARGO COMPARTMENT DOOR. SUMMARY OF NRC-00141: OUTER PAN AT BEAM #3, #4, AND #5 INTERNAL STRUCTURE AT FWD CARGO COMPARTMENT DOOR WAS REPAIRED PER ERA 619498-14 REV ORIGINAL. ASSOCIATED ER/A 14-619498 ADDED FOR AC 9546. (LP #0502933)

Part: PAN — CRACKED (ZONE 100) · airframe 57,904 hrs · 40,344 cycles

CRACK ON INNER PAN WAS FOUND ON BEAM 4 FWD EDGE AT FWD CARGO COMPARTMENT DOOR. SUMMARY OF NRC 00674: INNER PAN ON BEAM 4 FWD EDGE AT FWD CARGO COMPARTMENT DOOR WAS REPAIRED PER ER/A 619393-14 REV ORIGINAL SECTION I: PERMANENT REPAIR AND PRI 619393-14 REV 3. ASSOCIATED ER/A 14-619393 ADDED FOR AC 9546. (LP #0504170)

Part: CAP — CORRODED (STA Y=1022) · corrosion level 2 · airframe 57,904 hrs · 40,344 cycles

CORROSION ON SEAT TRACK X=22 STA Y=197-225, -X=44.5 Y=200-237, AND FLOOR SUPPORT AT -X=54.5 Y=210. SUMMARY OF NRC 00719: CORROSION LEVEL 2. SEAT TRACK X=22 STA Y=197-225, AND SEAT TRACK -X=44.5 Y=200-237, WERE REPAIRED PER B717-200 SRM 53-20-52-2R PROCEDURE 5 REPAIR 5 FIG 201, AND FLOOR SUPPORT AT -X=54.5 Y=210. WAS REPAIRED PER B717-200 SRM 51-40- 08-0G. (LP #0492234)

Part: HOUSING — CRACKED (ZONE 800) · airframe 57,904 hrs · 40,344 cycles

CRACK AT SETTLEMENT AREA OF HANDLE HOUSING WAS FOUND WHILE HOUSING REMOTION DOOR L1. SUMMARY OF NRC 00708: EXTERNAL SKIN ON SETTLEMENT AREA OF HANDLE HOUSING AT PASSENGER DOOR L1 WAS REPAIRED PER ER/A 619355-14 REV ORIGINAL SECTION I: PERMANENT REPAIR AND PRI 619355-14 REV 1. ASSOCIATED ER/A 14-619355 ADDED FOR AC 9546. (LP #0493592)

Part: FRAME — CRACKED (ZONE 100) · airframe 57,904 hrs · 40,344 cycles

CRACK ON FRAME STA Y=694 LH SIDE AT CANTED KEEL INTERNAL STRUCTURE. SUMMARY OF NRC 00340: LH SIDE FRAME STA Y=694 INBOARD EDGE WAS REPAIRED PER B717-200 SRM 51-70-11-2R PROCEDURE 1 REPAIR 1 AND OUTBOARD EDGE WAS REPAIRED PER ERA 545683-14MA REV ORIGINAL. (LP #0487650)

Part: FRAME — CRACKED (ZONE 100) · airframe 57,904 hrs · 40,344 cycles

CRACK ON FRAME STA Y=694 LH SIDE AT CANTED KEEL INTERNAL STRUCTURE. SUMMARY OF NRC 00340: LH SIDE FRAME STA Y=694 INBOARD EDGE WAS REPAIRED PER B717-200 SRM 51-70-11-2R PROCEDURE 1 REPAIR 1 AND OUTBOARD EDGE WAS REPAIRED PER ERA 545683-14MA REV ORIGINAL. ASSOCIATED ER/A 14-545683 ADDED FOR AC 9546. (LP #0487654)

Part: CUSP WEB — CORRODED (STA 565 X) · corrosion level 2 · airframe 57,904 hrs · 40,344 cycles

CORROSION ON CUSP WEB MEMBRANE STA 565 X=- 59, STA 576 X=-58, STA 579-589 X=-60 AND X=-58 (UPPER AND UNDER), STA 589-617 X=-57 AND X=-59, STA 636 X=-49, STA 647 X=-58 AT PAX CAB. SUMMARY OF NRC 00491: CORROSION LEVEL 2. CUSP WEB MEMBRANE STA 565 X=-59, STA 579-589 X=-60 AND X=-58, STA 589-617 X=-57 AND X=-59, STA 636 X=-49, STA 647 X=-58 AT PAX CAB WERE REPAIRED PER B717-200 SRM 53-00-55-2R REPAIR 4, 53-00-55-2R- 4, FIG 209, 53-00-55-2R-4, FIG 203, CUSP WEB MEMBRANE STA 576 X=-58 WAS CLEANED PER DAL PS 900-1-2-1 NO 02, AND GENERAL VISUAL INSPECTION WAS PERFORMED, AFTER CLEANED UP AT AREA ON STA 576 X=-58 PER B717-200 SRM 51-00-06-0G PROCEDURE GENERAL STEP 5.A(2)(B) AND NO CORROSION WAS FOUND. (LP #0485715)

Part: CUSP WEB — CORRODED (ZONE 200) · corrosion level 2 · airframe 57,904 hrs · 40,344 cycles

CORROSION ON CUSP WEB MEMBRANE STA Y=794 TO Y=813, X=-44 X=-60, AND Y=832/Y=835 AND X=-57. ALSO, CORROSION ON THE REPAIR DOUBLER OF THE CUSP WEB MEMBRANE STA Y= 865 TO Y=870, X=-53 TO X=-60. CABIN PAX. SUMMARY OF NRC 00764: CORROSION LEVEL 2. CUSP WEB MEMBRANE STA Y=794 TO Y=813, X=-44 X=-60 WAS REPLACED PER B717-200 SRM 53-20-51-0I PROCEDURE 2; CUSP WEB MEMBRANE Y=832/Y=835 AND X=-57 WAS REPAIRED PER B717-200 SRM 53-00-55-2R PROC 4 REPAIR 4; REPAIR DOUBLER OF THE CUSP WEB MEMBRANE STA Y=865 TO Y=870, X=-53 TO X=-60 WAS REPLACED PER B717-200 SRM 53-00-55-2R PROCEDURE 4 REP 4; B717-200 SRM 51-41-02-0G AND B717-200 SRM 51-41-05-0G. (LP #0468406)

Part: FRAME — CRACKED (ZONE 100) · airframe 57,904 hrs · 40,344 cycles

CRACK ON FRAME STA Y=1037 AND STR 17 RH AT C PAX. SUMMARY OF NRC 00360: FRAME STA Y=1037 AND STR 17 RH WAS REPAIRED PER B717 SRM 53-20-07-2R REP 4. (LP #0466007)

Part: DOOR FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 57,904 hrs · 40,344 cycles

CORROSION ON DOOR JAMB BTW STA Y=387-408 AT FWD CARGO COMPARTMENT DOOR. SUMMARY OF NRC 00079: CORROSION LEVEL 2. DOOR JAMB BTW STA Y=387-408 AT FWD CARGO COMPARTMENT DOOR WAS REPAIRED PER B717-200 SRM 53-20-15-2R PROCEDURE 6 REPAIR 6. (LP #0462776)

Part: SKIN — CRACKED (ZONE 100) · airframe 57,904 hrs · 40,344 cycles

CRACK ON EDGE EXTERNAL FUSELAGE SKIN STA Y=991 BTW LONGERON 26-24R AT FUSELAGE. SUMMARY OF NRC 00075: CRACK ON EDGE EXTERNAL FUSELAGE SKIN STA Y=991 BTW LONGERON 26-24R AT FUSELAGE WAS REPAIRED PER B717 SRM 53-20-15-2R PROCEDURE 12. (LP #0461829)

Part: LONGERON — CRACKED (ZONE 200) · airframe 57,904 hrs · 40,344 cycles

CRACK ON RH LONGERONS 4 AND 6 STA Y=1022 AT C PAX. SUMMARY OF NRC 00363: CRACK ON RH LONGERONS 4 AND 6 STA Y=1022 AT C PAX WERE REPAIRED PER B 717-200 S.R.M. 53-00-05-2R REPAIR 2. (LP #0460780)

Part: CUSP WEB — CRACKED (ZONE 200) · airframe 57,904 hrs · 40,344 cycles

CRACK ON CUSP WEB MEMBRANE STA 403 X=-58 AT PAX CAB. SUMMARY OF NRC 00498: CUSP WEB MEMBRANE STA 403 X=-58 AT PAX CAB WAS REPAIRED PER B717-200 SRM 53-00-55-2R-4, REPAIR 4, FIGURE 212. (LP #0460928)

Part: CUSP WEB — CORRODED (ZONE 200) · corrosion level 2 · airframe 57,904 hrs · 40,344 cycles

CORROSION ON CUSP WEB MEMBRANE BTW STA Y=483 AND X=55 AT CPAX. SUMMARY OF NRC 00488: CORROSION LEVEL 2. CUSP WEB MEMBRANE BTW STA Y=483 AND X=55 AT CPAX WAS REPAIRED PER B717-200 SRM 53-00-55-2R-4 FIG 213. (LP #0457527)

Part: WEB — CORRODED (ZONE 200) · corrosion level 2 · airframe 57,904 hrs · 40,344 cycles

CORROSION ON WEB MEMBRANE STA Y=185-Y=200. SUMMARY OF NRC 00827: CORROSION LEVEL 2. WEB MEMBRANE STA Y=185-Y=200 WAS REPAIRED PER B717-200 SRM 51-70-10-2R PROCEDURE 2 REP 2. (LP #0456066)

Part: CUSP WEB — CORRODED (ZONE 200) · corrosion level 2 · airframe 57,904 hrs · 40,344 cycles

CORROSION OUT OF LIMITS ON RH CUSP WEB STA 896-904 X=-58 PER B717-200 SRM 53-00-55-1A PROCEDURE 1 ALLOWABLE DAMAGE 1 PAR 4.A. SUMMARY OF NRC S/N 00711: CORROSION LEVEL 2. RH CUSP WEB STA 896 -904 X=-58 WAS REPAIRED PER B717-200 SRM 53-00-55-2R REPAIR 4 FIGURE 215. (LP #0451714)

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 57,904 hrs · 40,344 cycles

CORROSION ON SEAT TRACK BTW STA Y=265-301 COORDINATE X=-22. SUMMARY OF NRC 00672: CORROSION LEVEL 2. SEAT TRACK BTW STA Y=265-301 COORDINATE X=-22 WAS REPAIRED PER B717-200 SRM 53-20-52-2R PROCEDURE 5, REPAIR 5, PAR 4, FIG 201. (LP #0451567)

Part: CUSP WEB — DAMAGED (ZONE 200) · airframe 57,904 hrs · 40,344 cycles

MISSING MATERIAL ON CUSP WEB MEMBRANE STA 527 X=-59 AT PAX CAB. SUMMARY OF NRC 00501: CUSP WEB MEMBRANE STA 527 X=-59 AT PAX CAB WAS REPAIRED PER B717-200 SRM 53-00-55-2R-4 FIG 215. (LP #0450942)

Part: BEAM — CRACKED (ZONE 200) · airframe 57,904 hrs · 40,344 cycles

CRACK ON DOOR BEAM 1 BETWEEN STA 170 AND STA 180 (UPPER AFT CORNER) AT FWD PASSENGER DOOR L1. SUMMARY OF NRC 00157: DOOR BEAM 1 BETWEEN STA 170 AND STA 180 (UPPER AFT CORNER) AT FWD PASSENGER DOOR L1 WAS REPAIRED PER B717-200 SRM 52-10-02-2R PROCEDURE 7. (LP #0447744)

Part: FRAME — CRACKED (FWD CARGO) · airframe 57,904 hrs · 40,344 cycles

CRACK ON UPPER EDGE FRAME, 2 FROM UPPER EDGE AND 38 FROM FWD EDGE AT FWD CARGO COMPARTMENT DOOR. SUMMARY OF NRC 00107: UPPER EDGE AND FWD EDGE AT FWD CARGO COMPARTMENT DOOR WAS REPAIRED PER B717-200 SRM 52-30-02-2R PROCEDURE 1 REPAIR 1.

Part: CUSP WEB — CRACKED (ZONE 200) · airframe 57,904 hrs · 40,344 cycles

CRACK ON CUSP WEB MEMBRANE STA 674 X=-46 AT PAX CAB. SUMMARY OF NRC 00499: CUSP WEB MEMBRANE STA 674 X=-46 AT PAX CAB WAS REPAIRED PER B717 SRM 53-00-55-2R PROCEDURE 4 REPAIR 4 FIG 219. (LP #0444565)

Part: LONGERON — CRACKED (ZONE 200) · airframe 57,904 hrs · 40,344 cycles

CRACK ON LH LONGERONS 4, 5 AND 6 STA Y=1022 AT C PAX. SUMMARY OF NRC 00362: LONGERONS 4, 5, AND 6 STA Y=1022 AT C PAX WERE REPAIRED PER B717-200 SRM 53-00-05-2R PROC 2 REPAIR 2 PAR 5 FIG 201. (LP #0444631)

Part: CUSP WEB — CRACKED · airframe 57,904 hrs · 40,344 cycles

THE CUSP WEB WAS FOUND CRACKED STA Y=218-220 / -X=44.5. SUMMARY OF NRC 00762: CUSP WEB STA Y=218-220 / -X=44.5. WAS REPAIRED PER B717-200 SRM 53-00-55-2R-4. (LP #0443614)

Part: FRAME — CRACKED (ZONE 100) · airframe 57,904 hrs · 40,344 cycles

CRACK ON FRAME STA Y=1037 AND STR 17 LH AT C. PAX. SUMMARY OF NRC 00361: FRAME AT STA Y=1037 AND STR 17 LH WAS REPAIRED PER B717-200 SRM 53-20-07-2R REPAIR 4 PAR 5 A. (LP #0444212)

Part: PAN — CRACKED (ZONE 100) · airframe 57,904 hrs · 40,344 cycles

AFT REMOVAL ANGLE CRACK ON INNER AND OUTER PAN WAS FOUND BTW BEAM 1-2 AND STA Y=954 AT AFT CARGO COMPARTMENT DOOR. SUMMARY OF NRC 00665: INNER AND OUTER PAN BTW BEAM 1 TO BEAM 2 AND STA Y=954 AT AFT CARGO COMPARTMENT DOOR WERE REPAIRED PER B717-200 SRM 52-30-02-2R PROCEDURE 8 REPAIR 8 FIGURE 204. (LP #0442225)

Part: BEARING — CORRODED (ZONE 300) · corrosion level 2 · airframe 58,151 hrs · 40,576 cycles

CORROSION ON BEARINGS (6 EA) AND BUSHINGS (2 EA), OF THE RH ELEVATOR TAB AND RH ELAVATOR GEARED TAB. ALSO CORROSION ON ALL HARDWARE OF THE RH ELEVATOR TAB AND RH ELAVATOR GEARED TAB. SUMMARY OF NRC 00658: CORROSION LEVEL 2. BEARINGS (6 EA) AND BUSHINGS (2 EA) OF THE RH ELEVATOR TAB AND RH ELAVATOR GEARED TAB WERE REPLACED PER P.S. 900-9-1 NO 06. ALL HARDWARE OF THE RH ELEVATOR TAB AND RH ELAVATOR GEARED TAB WAS VERIFIED AND REPLACED WITH NRC 00673 AND INSTALLED IN NRC 00639. (LP #0439935)

Part: SKIN — DAMAGED (RT ELEVATOR) · airframe 57,904 hrs · 40,344 cycles

LIGHTING STRIKE R/H O/B ELEVATOR. C/W REP CHK PER ERA 618187-14 REV A SECTION 2. NO FURTHER DAMAGE FOUND ON RIGHT ELEVATOR. OK TO CONT ON MON. TIME LIMITS FOR SECTION I: TIME LIMITED REPAIR EXTENDED FROM 24 DAYS TO 34 DAYS PER ER/A 618187-14 REV B. ASSOCIATED ER/A 00-618187 ADDED FOR AC 9546. SUMMARY: ELEVATOR RH WAS REPLACED BY SERVICEABLE PER AMDS 2730-4002 AND AMDS 2730-4004, ALSO PER ERA 618187-14 REV B SECTION III: PERMANENT REPAIR OPTION 2. PLEASE CLOSE THIS LOG. (LP #5937372)

Part: ENGINE — STALLED (NR 1) · airframe 57,837 hrs · 40,282 cycles

SHIP 9546 -DIV/IFSD/DE- THE FLIGHT CREW NOTED THAT THE #1 ENGINE STALLED MULTIPLE TIMES IN FLIGHT WHICH RESULTED IN A "LT ENG SYS FAIL" MESSAGE. FLIGHT CREW SHUT DOWN THE ENGINE PER THE QRH, THEY DECLARED EMERGENCY WITH ATC, AND DIVERTED THE AIRCRAFT TO LAND AT ORD. CORRECTIVE ACTION: ENGINE ENGINE WAS FOUND TO HAVE OUT-OF-LIMITS DAMAGE TO THE HIGH-PRESSURE COMPRESSOR AND WAS REPLACED. (LP #5937360)

Part: BATTERY PACK — FAULTED (EMERGENCY LIGHTS) · airframe 57,736 hrs · 40,191 cycles

AFT, CENTER EMERGENCY EXIT SIGN BECOMES ILLUMINATED THEN EXTIGUISHES INTERMITENTLY. REPLACED POWER SUPPLY ASSEMBLY AND BATTERY PACK AT B5-230 PER B717 AMM 33-51. ONCE BATTERY CHARGED, THE OPERATIONAL CHECK WAS GOOD. (LP #5822592)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 56,850 hrs · 39,446 cycles

CORROSION WAS FOUND ON THREADS OF ACME SCREW AT HORIZONTAL STAB PER AMDS 2740-01114-03, STEP # 2.C. CORRODED SCREW AT HORIZONTAL STAB WAS REPLACED BY SERVICEABLE SCREW AT HORIZONTAL STAB. (LP #0128653)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 56,834 hrs · 39,432 cycles

DENTS (8 LOCATIONS) ON UPPER SKIN OF AFT MOVABLE VANE BTW STA XRS=77 TO XRS=88 AT RH WING. SUMMARY OF NRC 00077: AFT MOVABLE VANE BTW STA XRS=77 TO XRS=88 OF RH WING WAS REPAIRED PER ER/A 614501-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-614501 ADDED FOR AC 9546. (LP #0127506)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · corrosion level 2 · airframe 56,834 hrs · 39,432 cycles

CORROSION ON LOWER DOOR JAMB BTW STA:946 TO 994 AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00033: CORROSION LEVEL 2. LOWER DOOR JAMB BTW STA:946 TO 994 AT AFT CARGO COMPARTMENT WAS REPAIRED PER B717 SRM 53-20-15-2R-7 REPAIR 7. (LP #0120705)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 56,834 hrs · 39,432 cycles

CRACK WAS FOUND ON WEB STA Y=670, X=-56 APROX AT CABIN PAX. SUMMARY OF NRC 00078: WEB STA Y=670, X=-56 WAS REPAIRED PER B717 SRM 53-00-55-2R-4. (LP #0114428)

Part: COVER — MISSING (LT ENGINE) · airframe 56,834 hrs · 39,432 cycles

MAINTENANCE FOUND THAT LEFT ENGINE FORWARD HOIST POINT COVER WAS MISSING FROM THE NOSE COWLING. THE DISCREPANCY WAS DEFERRED TO NEF 71-10-02 AND THE PLACARDS WERE INSTLALLED. COWL HOIST SCREW MPN AN565AC624H20 REF CMM 71-11-05 FIG 1 SHEET 4 ITEM 220 00-2500-3-0640. SUMMARY OF NRC 00096: NEW HOIST SCREW WAS INSTALLED ON LEFT ENG FWD HOIST POINT PER B717 AMM 71-12-01 400-801 STEP A TO E.(1)N. (LP #4278125)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 56,381 hrs · 39,032 cycles

THE AFT BULKHEAD DOOR EMERGENCY LIGHT EXIT SIGN IS NOT ILLUMINATING. RELAMPING IT DID NOT HELP. CHECKED FOR POWER AND DISCOVERED THERE WAS NO VOLTAGE. REPLACED THE B5-260 EMERGENCY LIGHT BATTERY PER B717 AMM 33-51. OPERATIONAL CHECK IS NOW NORMAL. (LP #4941969)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 56,201 hrs · 38,878 cycles

THE FLIGHT DECK OVERHEAD EMERGENCY LIGHT IS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY POWER PACK REF B717 AMM 33-51. OPERATIONAL CHECK WAS GOOD. (LP #9967944)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 55,903 hrs · 38,615 cycles

FOUND CRACK IN SKIN TO BE OUT OF LIMITS. COMPLIED WITH PRI 610480-14 AD REV 0. COMPLIED WITH PRI 610488-14AD REV 1 ALL INSTRUCTIONS ON PRI 610480-14AD REV 0 AND REV 1 ARE C/W AND MATCH FINAL ERA 610480-14 REV ORIGINAL. (LP #2866614)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 55,903 hrs · 38,615 cycles

1 CRACK INDICATION ON L/H VERTICAL (MARKED) WHILE PERFORMING AA 5530-01048 AND AD 2018-10-08 BHEC INSPECTION. REINSPECTED CRACK IN STEP 16 CRACK CONFIRMED IN SKIN LAYER OF L/H VERTICAL STAB (MARKED) REF CARD AA5530-01048 AND AD 2018-10-08. C/W ERA 610480-14AD REV ORIGINAL SECTION I, PERMANENT REPAIR. DISCREPANT HOLE OVERSIZED IN SKIN LAYER ONLY, INSTALLED INTERFERENCE FIT BUSHING, FINAL REAMED BUSHING, AND INSTALLED FASTNER IN DISCREPENT HOLE. (LP #4826378)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 55,594 hrs · 38,351 cycles

NOTED CRACK INDICATIONS IN 6 HOLES BELOW EXISTING REPAIR (MARKED). REF AA 5530-01048-02 STEP 8, AA 2018-10 -08. SEPARATED LAYERS REF STEP 9 OF AA CARD 5530-01048-02. CONFIRMED CRACKS ARE IN SKIN ONLY (7 EA). INSTALLED REPAIR DOUBLER PER ERA 609262-14 AD REV ORIG. ALL RII STEPS C/W. ASSOCIATED ER/A 14-609262 ADDED FOR AC 9546. (LP #4716715)

Part: LENS — DETACHED (EMERGENCY LIGHT) · airframe 54,446 hrs · 37,385 cycles

DURING CABIN WALK THROUGH, THE OVERHEAD EMERGENCY LIGHT COVER WAS NOTED AS MISSING. MAINTENANCE INSTALLED A NEW EMERGENCY LIGHT LENS & COVER ON AFT MOST RIGHT OVERHEAD EMERGENCY LIGHT PER AMM 33-51-08. NO FURTHER DEFECTS NOTED. (LP #9347261)

Part: NONE — NONE · airframe 53,949 hrs · 36,923 cycles

DURING PACK HEALTH CHECK AMT WENT TO AFT (DISARMED) DOOR TO WORK CARDS FOR HEALTH CHECK. AMT LOOKED DOWN CAT WALK AND NOTICED TAIL CONE SLIDE BUSSEL OPENED AND TAIL CONE SLIDE HALF WAY OPENED BUT NOT BLOWN. THIS COULD PREVENT PROPER OPERATION OF THE ESCAPE PATH AND IT IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. MAINTENANCE REPLACED THE TAIL CONE ESCAPE SLIDE PER B717 WORKCARD #2561-9006. (LP #2406635)

Part: NONE — NONE · airframe 53,526 hrs · 36,523 cycles

THE EMERGENCY CEILING LIGHT LENS IS MISSING AT ROW 25. MAINTENANCE INSTALLED THE CEILING LIGHT LENS COVER AT ROW 25 PER IPC 33-51-08-01, ITEM 35 40-45. (LP #8930838)

Part: NONE — NONE · airframe 53,526 hrs · 36,523 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND THE OVERHEAD FWD EXIT LIGHT AND FWD DROP CEILING LIGHTS WERE NOT OPPERATING WITH THE EMERGENCY LIGHT SWITCH ON. THE BATTERY AND CHARGER AT POSITION B5-259 WERE REPLACED IN REF TO B717 AMM 33-51. OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT RETURNED TO SERVICE. (LP #8930822)

Part: NONE — NONE · airframe 53,243 hrs · 36,273 cycles

THE FWD CEILING EMERGENCY LIGHTS ARE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK AT ROW 10. ALL LIGHTS NOW OPERATE NORMALLY. THE AIRCRAFT IS OK FOR SERVICE PER B717AMM 33-50. (LP #8919458)

Part: SKIN — CORRODED · corrosion level 2 · airframe 53,135 hrs · 36,175 cycles

CORROSION UPPER WING SURFACE AT STA266, STR 4 LEFT WING. REMOVED CORROSION BY BLENDING AT STA 266 STR 4. MAPPED AREA AFTER BLENDING USING A 1/2" GRID. AREA FOUND TO BE OUT OF LIMITS PER B717 SRM 51-10-04 AND B717 SRM 57-10-01-1A-1 FIG 113 SHEET 3. PERFORMED HFEC IAW MD-BOEING NDT 06-10-01.001 NO DEFECTS NOTED. PERFORMED UT MEASURE IAW MD-BOEING NDT SPM PART 4 04-10-01 COMPLIED WITH ER/A 598797-14 SECTION 1 TIME-LIMITED REPAIR. ASSOCIATED ER/A 14-598797 ADDED FOR AC 9546. (LP #2197930)

Part: SKIN — CORRODED · corrosion level 2 · airframe 53,135 hrs · 36,175 cycles

CORROSION UPPER WING SURFACE AT STA 266, R.S. LEFT WING. REMOVED CORROSION BY BLENDING AT STA 266, R.S.. MAPPED AREA AFTER BLENDING USING A 1/2" GRID. AREA FOUND TO BE OUT OF LIMITS PER B717 SRM 51-10-04 AND B717 SRM 57-10-01-1A-1 FIG 113 SHEET 3. PERFORMED HFEC IAW MD-BOEING NDT 06-10-01.001 NO DEFECTS NOTED. PERFORMED UT MEASURE IAW MD-BOEING NDT SPM PART 4 04-10-01. COMPLIED WITH ER/A 598797-14 SECTION 1 TIME-LIMITED REPAIR. ASSOCIATED ER/A 14-598797 ADDED FOR AC 9546. (LP #2197931)

Part: SKIN — CORRODED · corrosion level 2 · airframe 53,135 hrs · 36,175 cycles

CORROSION UPPER WING SURFACE AT STA 300, STR 2.5 RIGHT WING. REMOVED CORROSION BY BLENDING AT STA 266 STR 4. MAPPED AREA AFTER BLENDING USING A 1/2" GRID. AREA FOUND TO BE OUT OF LIMITS PER B717 SRM 51-10-04 AND B717 SRM 57-10-01-1A-1 FIG 113 SHEET 3. PERFORMED HFEC IAW MD-BOEING NDT 06-10-01.001 FOUND BLENDED FASTENER. NO OTHER DEFECTS NOTED. PERFORMED UT MEASURE IAW MD-BOEING NDT SPM PART 4 04-10-01. COMPLIED WITH ER/A 598797-14 SECTION 1 TIME-LIMITED REPAIR. (LP #2197933)

Part: NONE — NONE · airframe 52,950 hrs · 36,009 cycles

AT PUSHBACK, CATERING ATTEMPTED TO OPEN DOOR 1R WHILE ARMED. THE SLIDE FAILED TO DEPLOY. THIS IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. MAINTENANCE FOUND THE RELEASE LANYARD DETACHED. THE SLIDE REMAINED INTACT WITH NO DAMAGE. THE RELEASE LANYARD WAS REINSTALLED PER B717 25-61. AIRCRAFT IS OK FOR SERVICE. (LP #8748628)

Part: NONE — NONE · airframe 52,751 hrs · 35,840 cycles

FOUND LIGHTED EMERGENCY EXIT SIGNS ABOVE LEFT AND RIGHT FORWARD OVERWING EMERGENCY EXITS WILL NOT ILLUMINATE DURING TEST. BOTH LIGHTS ARE POWERED BY POWER SUPPLY B5-121. REPLACED EMERGENCY LIGHT BATTERY ASSEMBLY IN POWER SUPPLY B5-121 IN REF WITH B717 AMM 33- 51. OPERATIONAL TEST WAS GOOD. OK FOR SERVICE. (LP #8303514)

Part: NONE — NONE · airframe 52,493 hrs · 35,609 cycles

(LOG 2061219) DURING INSPECTION FOUND CRACKS ON HOLE #6 AND HOLE #7 BELOW STATION ZFS=52.267, ON RH SIDE VERTICAL STABILIZER LEADING EDGE FRONT SPAR CAP. RH SIDE VERTICAL STABILIZER LEADING EDGE FRONT SPAR CAP WAS REPAIRED PER ER/A 534685-14AD REV B SECTION IV AND ETI-17-21-043 REV 4.

Part: NONE — NONE · corrosion level 2 · airframe 52,490 hrs · 35,608 cycles

CORROSION ON AFT AND FWD DOUBLERS OF FORWARD CARGO COMPARTMENT DOOR JAMB. SUMMARY OF NRC 00116: CORROSION LEVEL 2, AFT AND FWD DOUBLERS OF FORWARD CARGO COMPARTMENT DOOR JAMB WERE REPLACED PER B717 SRM 53-20-15-2R REPAIR 6. (LP #2052502)

Part: SPAR CAP — DAMAGED (VERTICAL STAB) · airframe 51,948 hrs · 35,117 cycles

ERA 585576-14AD SECTION I ISSUED FOR DEVIATION TO WC5530-01048 / SB B717-55A0012 INSPECTION TO VERT STAB LEADING EDGE AND SPAR CAP ERA REVISED TO REV 'A' FOLLOWING DTE. REFER TO LP #1505142. FOLLOW ON ACTION REQUIRED. ACCOMPLISH SECTION II INSPECTION EVERY 3000 FLIGHT CYCLES FOLLOWING SECTION I ACCOMPLISHMENT ON 25FEB20. (LP #1929998)

Part: SKIN — DAMAGED (ZONE 200) · airframe 57,904 hrs · 40,344 cycles

EVIDENCE OF LIGHTNING STRIKE 7 INCHES AFT OF STA 332 AT STRINGER 15 L REF LOG 8010442. REMOVED DAMAGED FASTENER AND INSTALLED TEMPORARY FASTENER PER B717 SRM 53-02-01-2R PARA 5 B (2) REPAIR 1. REQUIRES INITIAL VISUAL INSPECTION AT 3000 CYCLES. REPETITIVE INSPECTION EVERY 3000 CYCLES AND REPLACEMENT AT 8000 CYCLES. **REDEFERRED LOG TO QC, ESTAB MON INSP. COMPLY WITH REP INSP OF TEMPORARY FASTENER PER B717 SRM 53-02-01-2R PARA 5 B (2) REPAIR 1. NO CHANGE IN CONDITION. OK TO REMAIN ON MON. SUMMARY: TEMPORAL BLINF FASTENER WAS REPLACED BY SOLID FASTENER PER B717-200 SRM 53-02-01-2R-1 PAR 5.B.(2)(C) AND THE ORIGINAL PRODUCTION DRAWING ON 01AUG24. PLEASE CLOSE THIS LOG. (LP #8010455)

Part: SKIN — DAMAGED (ZONE 200) · airframe 57,904 hrs · 40,344 cycles

EVIDENCE OF LIGHTNING STRIKE5 FWD OF STA 332 AT STRINGER 15L REF LOG 8010441. REMOVED DAMAGED FASTENER AND INSTALLED TEMPORARY FASTENER PER B717 SRM 53-02-01-2R PARA 5 B (2) REPAIR 1. REQUIRES INITIAL VISUAL INSPECTION AT 3000 CYCLES, REPETITIVE INSPECTION EVERY 3000 CYCLES AND REPLACEMENT AT 8000 CYCLES. C/W REP INSP OF TEMPORARY FASTENER PER B717 SRM 53-02-01-2R PARA 5 B (2) REPAIR 1. NO CHANGE IN CONDITION. OK TO REMAIN ON MON (00858895 03APR23 03:08 UTC). SUMMARY: BLIND FASTENER WAS REMOVED PER B717-200 SRM 57-41-03-06 AND B717-200 SRM 53-02-01-2R-1 PAR.5B (2)(C)1. HFEC OPEN HOLE INSPECTION WAS PERFORMED, NO CRACKS FOUND AT HOLE PER B717-200 SRM 53-02-01-2R-1 PAR.5B (2)(C) 2 AND DC-MD/BOEING NDTSPM PAR.6, 06-10-01-003. (EQ: NORTEC 600D C/N: 3400 EXP:03/NOV/24). SOLID FASTENER WAS INSTALLED PER B717-200 SRM 51-41-02-06 AND B717-200 SRM 53-02-01-2R-1 PAR.5B (7)(C).3. INSPECTOR STAMP TECHOPS A.K.A.R 201955000. (LP #8010454)

Part: OIL SYSTEM — LEAKING (APU) · airframe 50,014 hrs · 33,528 cycles

DURING CUSTOMER BOARDING, THE CABIN CREW NOTICED SMOKE IN THE CABIN. THE AIRCRAFT WAS DEPLANED NORMALLY THROUGH THE MAIN CABIN DOOR AND JET BRIDGE. CORRECTIVE ACTION: MAINTENANCE FOUND THAT THE APU WAS LEAKING OIL AND REPLACED THE APU. A DUCT BURNOUT WAS ACCOMPLISHED. THE AIRCRAFT HAS RETURNED TO SERVICE.

Part: BATTERY PACK — NO TEST (EMERGENCY LIGHTS) · airframe 49,678 hrs · 33,212 cycles

DURING EMERGENCY LIGHT TEST, FOUND THE OVERHEAD EMERGENCY LIGHTS ROW 24-29 INOPERATIVE. REPLACED B5-231 BATTERY IAW B717 AMM 33-51, OPERATIONAL CHECK WAS GOOD. (LP #6468795)

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 49,051 hrs · 32,636 cycles

THE REMOVEABLE VERTICAL LEADING EDGE HAS 15 HOLES OUT OF TOLERANCE IN THE AD SIGNIFICANT AREA - FORWARD CROWN SIDE. MAINTENANCE OPENED UP 65 HOLES PER DWG #SG95550001. BOLT HOLE EDDY CURRENT PER SRM 06-10-01.003 - NO DEFECTS NOTED (QC1969 ). INSTALLED BUSHING PER DWG #SG95550001. 13 OF THE 3/16 HOLES ARE OVER MAXIMUM DIAMETER ALLOWED. HOLES ARE .531 INCH. TREATED, PRIMED, & INSTALLED REPAIR DOUBLER PER 5530-01048-03 AND DWG #SG95550001-7003. SEALED AND PAINTED DOUBLER PER PRI 585576-14AD, REV. ORIG. (LP#1505615)

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 51,948 hrs · 35,117 cycles

VERT STABILIZER / UPPER REMOVABLE / LE SKIN / ZFS-52 / OS HOLES / AD RELATED. ERA 585576-14 ISSUED AND IS CURRENT. AD RELATED, FOLLOW ON ACTION REQUIRED. SECTION II TO BE ACCOMPLISHED WITHIN 24 MONTHS AFTER SECT.I. SECT.II IS PENDING DAMAGE TOLERANCE ANALYSIS (DTA). ENG APPROVAL (ERA REV) IS REQUIRED FOR SERVICE PAST 24 MONTHS. ASSOCIATED ER/A 00-585576 ADDED FOR AC 9546. ASSOCIATED ER/A CHANGED FROM 00-585576 TO 14-585576 FOR AC 9546. ERA REVISED TO REV 'A'. STAGE III DTE COMPLETE. LOGPAGE 1929998 TRACKS SECTION II FOLLOW ON ACTION REQUIREMENTS. THIS LOG CAN BE CLOSED. TERMINATED LOG PER LINE 4 COMMENTS. (LP #1505142)

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 49,040 hrs · 32,631 cycles

THE COCKPIT EMERGENCY LIGHTS ARE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT PWR SUPPLY [B5-123] REF B-717 AMM 33-51. OPERATIONAL TEST WAS GOOD. OK FOR SERVICE. (LP #1499012)

Part: HINGE FITTING — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 46,835 hrs · 31,019 cycles

THE I/B LUG FACE OF RH FLAP O/B IDLER HINGE IS CORRODED. MAINTENANCE REMOVED ALL OF THE CORROSION AND FABRICATED AN OVERSIZED BUSHING AND WASHER TO FILL THE VOID CAUSED BY THE REMOVED CORROSION. COMPLIED WITH FINAL ER/A 577251-14 REV. 0. (LP #1037065)

Part: FRAME — CRACKED (BS 696) · airframe 46,835 hrs · 31,019 cycles

CRACK NOTED AT UPPER RADIUS OF THE FRAME TAB OF THE OVER WING FRAME STA 696 RH, CONDITION 3 GREATER THAN 0.125 INCH. NRC 057-0004:5310-01436-01D/001 00056: REPLACED FRAME ON AMDS 5310-01436-03B.

Part: TAPE — TORN (RT WING) · airframe 46,835 hrs · 31,019 cycles

RIGHT WING UPPER SURFACE TAPE WORN. SURFACE IS ALSO CORRODED JUST FORWARD OF O/B SPOILER O/B END. NRC 001-0282:5720-2003/001 00081: REPAIRED COMPLIED WITH PER ER/A 576976-14 REV 0. (LP #1027898)

Part: CAM — OUT OF POSITION (TAILCONE RELEASE) · airframe 46,835 hrs · 31,019 cycles

THE VERY AFT END OF 48 SECTION: TAILCONE RELEASE LANYARD CAM ASSEMBLY IS CLOCKED INCORRECTLY. NRC 001-0251:5300-2004/002 00198: ADJUSTED CAM REF B717 AMM 53-52-03.

Part: LANYARD — BROKEN (GIRT BAR) · airframe 46,590 hrs · 30,842 cycles

THE GIRT BAR CABLE ON DOOR 1R WAS FOUND TO BE BROKEN. MAINTENANCE REPLACED THE LANYARD ASSEMBLY, IPC REF 25-61-03-01 ITEM 085. INSTALLED PER AMM 25-61-03. RII ACCOMPLISHED. OK FOR SERVICE. (LP #5070232)

Part: BATTERY — DISCHARGED (CABIN) · airframe 46,299 hrs · 30,654 cycles

THE OVERWING EXIT EMERGENCY LIGHT WAS FOUND TO BE INOPERATIVE. MAINTENANCE REPLACED THE FORWARD EMERGENCY BATTERY AND REPLACED THE AFT EMERGENCY POWER SUPPLY PER AMM 33-51. OPERATIONAL CHECK WAS GOOD. (LP #4289937)

Part: CONNECTOR — LOOSE (EMERGENCY LIGHT) · airframe 44,640 hrs · 29,483 cycles

THE AFT BULKHEAD EMERGENCY LIGHT EXIT SIGN WOULD NOT ILLUMINATE DURING TEST. FOUND A LOOSE CONNECTION ON LIGHT L2-938, AND POWER SUPPLY AND BATTERY PACK B5-260 FUSES BAD, TIGHTENED CONNECTION AT LIGHT L2-938 AND REPLACED EMERGENCY POWER SUPPLY AND BATTERY PACK B5-260. OPERATIONAL CHECK IS GOOD PER B-717 WDM 33-51-13 AND AMM 33-51.

Part: LIGHT — SHORTED (TAILCONE) · airframe 44,431 hrs · 29,341 cycles

THE EMERGENCY LIGHTS INTERMITTENTLY CAME ON & OFF DURING FLIGHT. WATER WAS FOUND IN THE EXIT SIGN AT THE TAILCONE. REPLACED IAW WDM 33-51. THE EMERGENCY LIGHTS NOW OPERATE NORMALLY. ALSO REMOVED CONDENSATION ABOVE AFT DROP CEILING PANEL.

Part: DOOR — DAMAGED (LE SLAT TRACK) · airframe 44,748 hrs · 29,565 cycles

LEFT NR 1 SLAT OUTBOARD TRACK DOOR DAMAGED. REMOVED DOOR AND FORWARD TO CDL 57-47-01. MCC NOTIFIED. MCC PLACARD INSTALLED. EA 5929781-2.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 43,039 hrs · 28,419 cycles

FOUND AFT EXIT DOOR EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED THE BATTERY PACK IAW AMM 24-34. OPS CHECKED GOOD.

Part: LIGHT — MALFUNCTIONED (AFT EXIT) · airframe 42,821 hrs · 28,274 cycles

EXIT LIGHT OVER AFTL EXIT, FLICKERED SEVERAL TIMES IN-FLIGHT THEN REMAINED ON. ALL OTHER CABIN EMERGENCY LIGHTS REMAINED OFF. F/A TRIED RESET, BUT WAS UNSUCCESSFUL. COULD NOT DUPLICATE, INSPECTED AND TESTED EMERGENCY LIGHTS IAW AMM 33-51, NO DEFECTS NOTED . NO 30 DAY HISTORY. OK FOR SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 42,347 hrs · 27,950 cycles

EXTERIOR EMERGENCY ILLUMINATION SYSTEM MALFUNCTIONED. ON ARRIVAL FOUND OVERWING EMERGENCY LIGHTS ON. REPLACED BATTERY PACK AND POWER SUPPLY, B5-125, IAW AMM 33-51-06. EMERGENCY LIGHT SYS OPS NORMAL.

Part: SPAR — CRACKED (RT WING) · airframe 42,149 hrs · 27,811 cycles

DURING REMOVAL OF OUTBD FLIGHT SPOILER LOCKED TOOL ONE CRACK WAS MADE TO RT WING AFT SPAR MEMBRANE BTW STA XRS=350 AND XRS=355. RT WING AFT SPAR MEMBRANE BTW STA XRS=350 AND XRS=355 WAS REPAIRED PER ETI -17-17-097 REV 2 AND ER/A 559526-14 REV ORIG.

Part: SKIN — CORRODED (RT WING) · airframe 42,149 hrs · 27,811 cycles

CORROSION ON RT WING UPPER SKIN XRS 375. ONE INCH FROM FRONT SPAR. THE SKIN WAS REPAIRED IAW ETI-17-17-094, REV 1, AND ER/A 559516-14, REV ORIG.

Part: BELLCRANK — WORN (SLAT DRIVE) · airframe 42,149 hrs · 27,811 cycles

WEAR ON BELLCRANK AT THE RT SLAT DRIVE MECHANISM. THE BELLCRANK WAS REPAIRED IAW ETI-17-17-075, REV 1, AND ER/A 559492-14, REV ORIG.

Part: FITTING — CORRODED (DOOR FRAME) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON FWD STAIRWAY DOOR MECHANISM FITTING. THE DAMAGED FITTING WAS REPLACED IAW AMM 20-50-01-201.

Part: CARGO TRACK — CORRODED (BS 813-1022) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION OUT OF LIMITS ON THE LT CARGO TRACK BETWEEN BS 813 - 1022 IN THE AFT CARGO BAY. THE CARGO TRACK WAS REPLACED IAW SRM 53-20-51-01-7, AND 51-41-01.

Part: CARGO TRACK — CORRODED (BS 892-1022) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION OUT OF LIMITS ON THE RT CARGO TRACK BETWEEN BS 892 & 1022 IN THE AFT CARGO BAY. THE CARGO TRACK WAS REPLACED IAW SRM 53-20-51-01-7, AND 51-41-01.

Part: FRAME — CORRODED (BS 927) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON FRAME ANGLE BS 927 BETWEEN LONGERONS 29L AND 29R. REPAIRED IAW SRM 53-00-06-2R, FIG 201, AND 53-20-07-01.

Part: SKIN — CORRODED (BS 737-751) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON WING BOX UPPER SKIN BETWEEN BS 737 - 751 RBL 22 - 60. REPAIRED IAW ETI-17-17-079, REV 1 AND ER/A 559498-14, REV ORIGINAL.

Part: ACCESS PANEL — DAMAGED (WING) · airframe 42,149 hrs · 27,811 cycles

ELONGATED HOLES ON FUEL ACCESS PANEL 620MB. THE ACCESS PANEL WAS REPLACED IAW SRM 57-10-01-2R, PROCEDURE 2, REPAIR 2, FIGURE 201, SHEET 1.

Part: PANEL — OUT OF LIMITS (VERTICAL STAB) · airframe 42,149 hrs · 27,811 cycles

SEVERAL COUNTERSINK OUT OF LIMITS ON REMOVABLE LEADING EDGE AT VERTICAL STABILIZER (EHV). REMOVABLE LEADING EDGE AT VERTICAL STABILIZER (EHV) WAS REPAIRED IAW DRAWING SG95550001, REV ORIGINAL, AND JIC CARD 5530-01048-03.

Part: FLOOR PANEL — CRACKED · airframe 42,149 hrs · 27,811 cycles

CRACK FLOOR PANEL 121NF. THE FLOOR PANEL WAS REPAIRED IAW SRM 53-00-00-2R.

Part: PANEL — CORRODED (VERTICAL STAB) · airframe 42,149 hrs · 27,811 cycles

SEVERAL COUNTERSINKS OUT OF LIMITS ON REMOVABLE LEADING EDGE AT VERTICAL STABILIZER. REPAIRED IAW SERVICE GENERAL REPAIR DRAWING SG 95550001 REV ORIGINAL.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON COUNTERSINK HOLES ON FUEL ACCESS PANEL. REPLACED THE ACCESS PANEL IAW SRM 57-10-01, PAR 5, CONDITION II.

Part: ACCESS PANEL — CORRODED · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON SETTLEMENT AREA AT FUEL ACCESS PANEL. THE FUEL ACCESS PANEL WAS REPLACED IAW SRM 57-10-01, REPAIR 2.

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 42,149 hrs · 27,811 cycles

LOOSE FASTENERS ON LT/RT SIDE AT VERTICAL STABILIZER LEADING EDGE STRUCTURE (REPAIR DOUBLER) AND REMOVABLE LEADING EDGE, STA ZFS=52.267. SEVERAL COUNTERSINK ON REMOVABLE LEADING EDGE STRUCTURE WERE MEASURED ABOVE 0.540" WERE LIMIT IS 0.517" AND ABOVE 0.420" WERE LIMIT IS 0.396" THEREFORE IT IS OUT OF LIMITS PER SG95550001 REV B.

Part: SKIN — CRACKED (FUSELAGE) · airframe 42,149 hrs · 27,811 cycles

CRACK ON FUSELAGE SKIN Y=1087 BTW LONG 13L-14L. FUSELAGE SKIN WAS REPAIRED PER ETI -17-17-072 REV 2 AND ER/A 558145-14 REV ORIG.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON ANGLE THAT ATTACH FUSELAGE TO CUSP ANGLE BTW LONGS 18L-19L, BTW STA Y=889-908. ANGLE WAS REPLACED PER SRM 53-20-51-01 AND DWG 9910151 ITEM -117. MEASURED (UT) WAS ACCOMPLISHED PER NDT SPM 04-00-07 PAR 5 FIG 3 SHEET 1 AND 2. THE ORIGINAL THICKNESS ON CUSP ANGLE LT IS .080" AND REMAINING THICKNESS .054 ",THEREFORE OUTSIDE LIMITS PER SRM 53-00-00-1A FIG 103 SHEET 1.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON CUSP WEB MEMBRANE UPPER LWR SURFACE BTW X=-54 TO X=-60 AND STAY=552 TO STAY=553 AT CAB PAX RT SIDE. DAMAGE WAS REMOVED PER SRM 53-00-55-2R REPAIR 4. HFEC WAS ACCOMPLISHED ON EDGES OF TRIMMED AREA, NO CRACKS WERE FOUND PER NDTSPM PART 6, 06-10-01.001. REPAIR PARTS WERE FABRICATED PER SRM 53-00-55-2R-4- FIG 209, REPAIR PARTS WERE INSTALLED PER SRM 53-00-55-2R-4- FIG 209 AND SRM 51-41-02-OG, CIC WAS APPLIED PER SRM 51-10-04 PAR 37.

Part: SKIN — DAMAGED (RT WING TE FLAP) · airframe 42,149 hrs · 27,811 cycles

PROTUBERANCE ON LOWER SKIN FOR THE RT WING AFT FLAP MOVEABLE VANE. THE SKIN WAS REPAIRED IAW SRM 57-53-01.

Part: SKIN — CRACKED (BS 1087) · airframe 42,149 hrs · 27,811 cycles

CRACK ON EXTERNAL SKIN, BS 1087 BETWEEN LONGERONS 13 AND 14R. THE SKIN WAS REPAIRED IAW ETI -17-17-074, REV ORIGINAL AND ER/A 558173-14, REV ORIGINAL,

Part: BEAM — CRACKED (SERVICE DOOR) · airframe 42,149 hrs · 27,811 cycles

CRACK ON FWD LOWER CORNER RETAINER AT THE FWD RT SERVICE DOOR. THE NR 4 BEAM WAS REPLACED IAW SRM 51-41-02, AND 51-41-05.

Part: FORMER — CRACKED (BS 694) · airframe 42,149 hrs · 27,811 cycles

CRACK ON FORMER BS 694, RBL 34. THE FORMER WAS REPAIRED IAW SRM 51-70-11-2R, 51-70-11, 51-41-02-0G, AND 51-41-05-0G.

Part: CUSP WEB — CORRODED (BS 622-630) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON CUSP WEB UPPER & LOWER SURFACES BETWEEN RBL 54 TO 60, BS 622 TO 624 AND BS 629 TO 630. THE DAMAGE WAS REMOVED IAW SRM 53-00-55-2R, FIG 216. HFEC INSPECTION WAS ACCOMPLISHED AND NO CRACKS WERE FOUND AFTER THE DAMAGED WAS REMOVED IAW NDT SPM 06-10-01.001. THE CUSP WEB WAS REPAIRED SRM 53-00-55-2R-4, FIG 216, SHEET 1.

Part: FLOOR SUPPORT — CORRODED (CABIN) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION AND CRACKED FLOOR PANEL 221AG. THE FLOOR SUPPORT WAS REPLACED IAW DWG 9957828, REV Y.

Part: CHANNEL — CRACKED (FLOOR PANEL) · airframe 42,149 hrs · 27,811 cycles

CRACKS ON CHANNEL OF PAX CABIN FLOOR PANEL 222ADF. THE CHANNEL WAS REPLACED IAW SRM 51-41-01-0G.

Part: TEE FITTING — CRACKED (CARGO DOOR) · airframe 42,149 hrs · 27,811 cycles

CRACKED TEE FITTING ON THE AFT LOWER STOP OF THE FWD CARGO DOOR. THE FITTING WAS REPLACED IAW SRM 51-41-01-0G, 51-41-02-0G, 51-41-05-0G, AND DRAWING 3926046, REV. B.

Part: MEMBRANE — CORRODED (BS 200) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON MEMBRANE BS 200 BETWEEN LONGERONS 17 &18L. THE MEMBRANE WAS REPAIRED IAW SRM 51-70-10-2R, FIG 201.

Part: CUSP WEB — CORRODED (BS 487-490) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON CUSP WEB RBL 54 TO 60, BS 487 TO 490. THE DAMAGE WAS REMOVED IAW SRM 53-00-55 2R, REPAIR 4, FIG 215. HFEC INSPECTION WAS ACCOMPLISHED AFTER DAMAGE REMOVED AND NO CRACK INDICATIONS WERE FOUND IAW NDT SPM 06-10-01.001. THE REPAIR WAS FABRICATED IAW SRM 53-00-55-2R-4, FIG. 215.

Part: BEAM — CRACKED (CARGO DOORWAY) · airframe 42,149 hrs · 27,811 cycles

CRACK ON BELOW DOOR STOP PAN AFT EDGE BEAM 3 OF FWD CARGO DOORWAY. REPAIRED IAW SRM 52-30-02, REPAIR 3.

Part: CUSP WEB — CORRODED (BS 602-603) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON LT CUSP WEB BETWEEN BS 602 - 603, LBL 54 TO 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-00-55-2R-4, FIG. 216.

Part: CUSP WEB — CORRODED (BS 655-663) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON CUSP WEB BETWEEN RBL 54 TO 60 OUT OF LIMITS AT BS 655 - 663. THE CUSP WEB WAS REPAIRED IAW SRM 53-00-55-2R.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON SEAT TRACK X=-44.5 STA Y=429-430 AT CAB PAX. SEAT TRACK X=-44.5 STA Y=429-430 AT CAB PAX WAS REPAIR PER SRM 53-20-52-2R REPAIR 1.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON FLOOR SUPPORT BTW STA Y=148 TO Y=168 AND X=-6 AT COCKPIT. FLOOR SUPPORT BTW STA Y=148 TO Y=168 AND X=-6 AT COCKPIT WAS REPLACED PER SRM 51-40-08-0G AND 51-41-01.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON LT CUSP WEB STA Y-855 BTW X54 TO X60 AT PAX CABIN IN REF NRC 198. REPAIR PART WAS FABRICATED AND INSTALLED PER SRM 53-00-55-2R FIG 215 AND 51-41-02. CIC WAS APPLIED PER SRM 51-10-04 PAR 37.

Part: RETAINING CLIP — WORN (CABIN DOOR) · airframe 42,149 hrs · 27,811 cycles

WORN ON LOWER LT DOUBLER RETAINER CLIP AT AFT CABIN BULKHEAD DOOR (DOORS). LT LOWER DOUBLER RETAINER CLIP WAS REPLACED PER SRM 51-41-01 AND 51-41-02.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON CUSP WEB BTW STA Y=544 TO Y=555 X54 TO X60 AT PAX CABIN IN REF NRC 195. DAMAGE WAS REMOVED PER SRM 53-00-55-2R-4 FIG 216 HFEC INSPECTION WAS ACCOMPLISHED ON CUSP WEB BTW STA Y=544 TO Y=555 X54 TO X60 AT PAX CABIN NO CRACKS WERE FOUND AFTER DAMAGE REMOVE PER NDTSPM 06-10-01.001. REPAIR PARTS WERE FABRICATED PER SRM 53-00-55-2R-4- FIG 216, REPAIR PARTS WERE INSTALLED PER SRM 53-00-55-2R-4- FIG. 216 AND 51-41-02, CIC WAS APPLIED PER SRM 51-10-04 PAR 37.

Part: FLOORBEAM — CORRODED (BS 200) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON FLOOR BEAM BS 200 BETWEEN RBL 54 TO 44 IN THE PAX CABIN. THE FLOORBEAM WAS REPLACED SRM 51-41-02, 51-10-4, PAR 26, AND 51-40-08.

Part: PAN — CRACKED (CABIN) · airframe 42,149 hrs · 27,811 cycles

CRACKED RING PAN ON STA Y=832 AND Y=870 AFT UPPER CORNER ALSO ON STA Y=579 LOWER FWD CORNER AT PAX CABIN LT SIDE. RING PAN WERE REPAIRED PER SRM 56-20-02-2R FIG 202 TYPE B.

Part: PAN — CRACKED (CABIN) · airframe 42,149 hrs · 27,811 cycles

CRACKED RING PAN ON STA Y=908 AFT LOWER CORNER AT PAX CABIN RT SIDE. RING PAN WERE REPAIRED PER SRM 56-20-02-2R FIG 202 TYPE B.

Part: FLOORBEAM — CORRODED (BS 200) · corrosion level 2 · airframe 42,149 hrs · 27,811 cycles

CORROSION ON FLOORBEAM BS 200 LBL 6 TO RBL 6. THE FLOORBEAM WAS REPLACED IAW SRM 51-41-02.

Part: POWER SUPPLY — NO TEST (EMERGENCY LIGHTS) · airframe 41,702 hrs · 27,480 cycles

DURING CHECK, FOUND SEVERAL OVERHEAD EMERGENCY LIGHTS INOPERATIVE. REPLACED THE POWER SUPPLY AND BATTERY IAW AMM 33-51. OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMEGENCY LIGHT) · airframe 40,520 hrs · 26,696 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT SIGNS AT BOTH OF THE AFT OVERWING HATCHES WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 35,746 hrs · 23,020 cycles

CEILING EMER LIGHTS INOPERATIVE. R & R CHARGER IAW AMM.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 35,746 hrs · 23,020 cycles

RIGHT AFT UPPER OVERWING EMER EXIT SIGN INOPERATIVE. R & R CHARGER ASSEMBLY IAW AMM.

Part: MEMBRANE — CORRODED (FUSELAGE) · airframe 35,746 hrs · 23,020 cycles

WEB MEMBRANE CORRODED BETWEEN BS 200 TO 218, BETWEEN RBL 35 TO RBL 56. R & R WEB IAW SRM & DWG.

Part: LENS — CRACKED (CABIN) · airframe 35,746 hrs · 23,020 cycles

OVERHEAD CEILING EMER EXIT LIGHT LENS CRACKED. R & R LENS IAW AMM.

Part: FITTING — CORRODED (R1 DOOR) · airframe 35,746 hrs · 23,020 cycles

R1 DOOR CUT OUT FWD & AFT SUB FLOOR GIRT BAR FITTINGS CORRODED. R & R FITTING IAW DWG.

Part: FLOOR PANEL — CRACKED (BS 150-207) · airframe 35,746 hrs · 23,020 cycles

MAIN CABIN SUB FLOOR PANEL CRACKED AT BS 150 - 207, RIGHT SIDE. R & R THE FLOOR PANEL IAW SRM AND DRAWING.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 35,746 hrs · 23,020 cycles

MAIN CABIN FLOOR SUPPORT CORRODED BETWEEN BS 160 TO 200, RBL 44. R & R SUPPORT IAW DWG.

Part: FITTING — CRACKED (RT MLG WW) · airframe 35,746 hrs · 23,020 cycles

RIGHT WW DOOR FWD LOWER CLIP FITTING CRACKED. R & R CLIP IAW SRM & DWG.

Part: CUSP WEB — CRACKED (BS 655-715) · airframe 35,746 hrs · 23,020 cycles

LEFT CUSP WEB WAS FOUND CRACKED AT BS 655 - 715. REPAIRED THE CUSP WEB IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 35,746 hrs · 23,020 cycles

LEFT FRAME CRACKED AT BS 674. R & R FRAME IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 35,746 hrs · 23,020 cycles

LEFT FRAME CRACKED AT BS 715. R & R FRAME IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 37,402 hrs · 24,159 cycles

FUSELAGE MAIN FRAME CRACKED AT STATION 674 LT SIDE. R & R FRAME ASSEMBLY IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 37,402 hrs · 24,159 cycles

FUSELAGE MAIN FRAME CRACKED AT STATION 715 LT SIDE. R & R FRAME ASSEMBLY IAW SRM.

Part: TAIL CONE — DELAMINATED (FUSELAGE) · airframe 35,746 hrs · 23,020 cycles

TAIL CONE DELAMINATED. R & R TAIL CONE AMM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 36,034 hrs · 23,218 cycles

RIGHT OVERHEAD EMER EXIT LIGHT INOPERATIVE. RELAMPED LIGHT IAW AMM.

Part: STRAP — CORRODED (VERTICAL STAB) · airframe 33,237 hrs · 21,392 cycles

VERTICAL STABILIZER SPLICE STRAP CORRODED. R &R STRAP IAW DRAWING & SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

SEAT TRACK SECTION CORRODED BETWEEN BS 265 TO BS 588 RBL 22. R &R PANEL IAW SRM.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 33,237 hrs · 21,392 cycles

CABIN FLOOR PANEL 221XF CORRODED AT BS 325 RBL45. R & R PANEL IAW SRM.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

FORMER CRACKED AT BD 674 LT SIDE. R & R FORMER IAW SRM.

Part: STRAP — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

RT UPPER LINER HORIZONTAL STRAP CRACKED BETWEEN BS 813 TO BS 832 BETWEEN BL0 TO RBL 48. R & R STRAP IAW SRM & DRAWING.

Part: STRAP — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

RT LOWER LINER HORIZONTAL STRAP CRACKED BETWEEN BS 813 TO BS 832 BETWEEN BL0 TO RBL 48. R & R STRAP IAW SRM & DRAWING.

Part: STRAP — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

LT UPPER LINER HORIZONTAL STRAP CRACKED BETWEEN BS 813 TO BS 832, BETWEEN BL0 & LBL 48. R & R STRAP IAW SRM & DRAWING.

Part: STRAP — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

LT LOWER LINER HORIZONTAL STRAP CRACKED BETWEEN BS 813 TO BS 832 BETWEEN BL0 TO LBL 48. R & R STRAP IAW SRM & DRAWING.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

LT CUSP WEB CORRODED BETWEEN BS 446 TO BS 465. REPAIRED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

RT CUSP WEB CORRODED BETWEEN BS 541 TO BS 560. REPAIRED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

RT CUSP WEB CORRODED BETWEEN BS 851 TO BS 870. REPAIRED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

RT CUSP WEB CORRODED BETWEEN BS 678 TO BS 685. REPAIRED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

LT CUSP WEB CORRODED BETWEEN BS 503 TO BS 522. REPAIRED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

RT CUSP WEB CORRODED BETWEEN BS 598 TO BS 617. REPAIRED WEB IAW SRM.

Part: ATTACH BRACKET — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN CENTER WING BOX ATTACH BRACKET CRACKED AT FS 663 LBL 22. R & R STIFFENER IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

LT CUSP WEB CORRODED BETWEEN BS 408 TO BS 427. R & R WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

RT CUSP WEB CORRODED BETWEEN BS 427 TO BS 446. R & R WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

RT CUSP WEB CORRODED BETWEEN BS 503 TO BS 522. R & R WEB IAW SRM.

Part: PAN — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

LT WINDOW PAN CRACKED LOWER FWD CORNER FLANGE BETWEEN BS 851 TO BS 570. REPAIRED ANGLE IAW SRM & DRAWING.

Part: PAN — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

LT WINDOW PAN AFT UPPER FLANGE CRACKED BETWEEN BS 832 TO BS 851. REPAIRED ANGLE IAW DRAWING & SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 221WF DELAMINATED. R & R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222APF DELAMINATED. R & R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222JF DELAMINATED. R & R PANEL IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

RT FRAME CRACKED AT BS 674. R & R FRAME IAW DRAWING & SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 223DF DELAMINATED. R & R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 221UF DELAMINATED. R & R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222LF DELAMINATED. R & R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222 ATF DELAMINATED. R &R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR AGF DELAMINATED. R & R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222PF DELAMINATED. R & R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222AHF DELAMINATED. R & R PANEL IAW SRM.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

AFT BULKHEAD EXIT DOOR JAM STRUCTURE LT SIDE "T" FITTING CRACKED AT FWD ATTACH FASTENERS AREA. R & R "T" FITTING IAW SRM & DRAWING.

Part: COVER — BROKEN (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR NR 222YF BROKEN METER COVER. R & R COVER IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222ACF DELAMINATED. R & R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222FF DELAMINATED. R & R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222RF DELAMINATED. R & R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222AVF DELAMINATED. R & R PANEL IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

RT FRAME CRACKED AT BS 715. R & R FRAME IAW DRAWING & SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222BF DELAMINATED. R &R PANEL IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 33,237 hrs · 21,392 cycles

MAIN CABIN FLOOR PANEL NR 222 AMF DELAMINATED. R & R PANEL IAW SRM.

Part: LONGERON — BROKEN (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

LONGERON BROKEN AT BS 1133 LONGERON 2L. R & R LONGERON IAW SRM & DRAWING.

Part: SKIN — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

SKIN CORRODED AT BS 974 UNDER THRESHOLD PLATE. REPAIRED SKIN IAW SRM A& EA.

Part: SKIN — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

RT NLG STRUT DOOR AFT HINGE CUTOUT CRACKED. REPAIRED DOUBLER IAW SRM.

Part: SKIN — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

LT NLG STRUT DOOR AFT HINGE CUTOUT CRACKED. REPAIRED DOUBLER IAW SRM.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

FORMER CRACKED AT BS 1152 BETWEEN LONGERON 1R TO LONGERON 2R. R & R FORMER IAW SRM & DRAWING.

Part: SKIN — CORRODED (FUSELAGE) · airframe 34,381 hrs · 22,136 cycles

C2 DOOR CUTOUT AT BS 974 SKIN CORRODED UNDER THRESHOLD PLATE. REPAIRED DOUBLER IAW EA.

Part: ESCAPE ROPE — CORRODED (COCKPIT) · airframe 33,237 hrs · 21,392 cycles

FIRST OFFICERS EMERGENCY ESCAPE ROPES CORRODED. R & R ROPE IAW AMM.

Part: PAN — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

AFT CARGO DOOR CUTOUT LOWER PAN CORRODED. R & R PAN IAW SRM.

Part: ESCAPE ROPE — CORRODED (COCKPIT) · airframe 33,237 hrs · 21,392 cycles

CAPTAINS EMERGENCY ESCAPE ROPES CORRODED. R & R ROPE IAW AMM.

Part: PAN — CORRODED (FUSELAGE) · airframe 33,237 hrs · 21,392 cycles

FWD CARGO DOOR CUTOUT LOWER PAN CORRODED. REPAIRED PAN IAW SRM.

Part: PAN — CORRODED (FUSELAGE) · airframe 34,381 hrs · 22,136 cycles

C2 DOOR JAMB LOWER PAN CORRODED. REPAIRED PAN IAW SRM.

Part: LENS — DEFECTIVE (CABIN) · airframe 32,174 hrs · 20,732 cycles

OVERHEAD EXIT SIGN BETWEEN 2C AND 2D WILL NOT STAY ON. REMOVED AND REPLACED EXIT SIGN LENS ROW 2C AND 2D.

Part: SLIDE — LOOSE (L1 DOOR) · airframe 31,320 hrs · 20,175 cycles

L1 DOOR EMERGENCY EVAC SLIDE LOOSE. SECURED SLIDE PER AMM.

Part: BATTERY — DISCHARGED (CABIN) · airframe 30,962 hrs · 19,941 cycles

RIGHT EEPLS INOP BETWEEN ROWS 1 TO ROW 3. REMOVED AND REPLACED BATTERY IAW AMM.

Part: HOUSING — CORRODED (NLG WW) · airframe 30,599 hrs · 19,687 cycles

NOSE GEAR HOUSING UPPER BEARING BORE CHAMFER AND LOWER BEARING FACE CORRODED. REPAIRED NLG HOUSING ASSY PER AT EA.

Part: BATTERY — DISCHARGED (CABIN) · airframe 30,699 hrs · 19,755 cycles

TAIL COMPARTMENT CEILING FWD WALKWAY EMERGENCY LIGHT INOP. REMOVED AND REPLACED BATTERY IAW AMM.

Part: PIN — WORN (FUSELAGE)

TAIL CONE ALIGNMENT PIN AND RECEPTACLE, WORN AND MISSING HARDWARE. ACCOMPLISHED TAIL CONE ALIGNMENT PIN AND RECEPTACLE ANGLE REPAIR PER B717 SRM 51-70-11 AND EA 17-53-02391A.

Part: SKIN — DENTED (FUSELAGE)

FUSELAGE SKIN, STA 237, LONG 17L, DENTED. ACCOMPLISHED SKIN DOUBLER REPAIR PER B717 SRM 53-00-01.

Part: SEAT TRACK — CORRODED (FUSELAGE)

SEAT TRACK, STA 237, RBL 22, CORROSION. ACCOMPLISHED SEAT TRACK REPLACEMENT PER B717 SRM 53-20-52.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT ANGLE, STA 202, RBL 57, CORROSION. ACCOMPLISHED FLOOR SUPPORT ANGLE REPLACEMENT PER B717 SRM 51-41-02 AND 51-41-05.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

FLOOR SUPPORT, STA 200, LBL 9 TO LBL 13, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

FLOOR SUPPORT, STA 148, RBL 31 TO RBL 44, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 175 TO 187, LBL 55, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-10-04, 53-00-00 AND 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

FLOOR SUPPORT, STA 168 TO 200, RBL 56, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-10-04, 53-00-00 AND 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

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

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

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

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

FLOOR SUPPORT, STA 237, BL 0, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-10-04 AND 51-41-05.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

FLOOR SUPPORT, STA 148 TO 200, RBL 7, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-10-04, 53-00-00 AND 51-41-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

FLOOR SUPPORT, STA 148 TO 200, LBL 7, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-10-04, 53-00-00 AND 51-41-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

FLOOR SUPPORT, STA 200, RBL 8 TO RBL 45, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-10-04, 53-00-00 AND 51-41-02.

Part: SLIDE — LOW PRESSURE (R1 DOOR)

R1 DOOR SLIDE HAS LOW PRESSURE. REMOVED AND REPLACED R1 DOOR SLIDE IAW AMM 25-61. OK FOR SERVICE.

Part: UNKNOWN — ODOR (CABIN)

LEVEL AT 32,0 FLIGHT ATTENDANTS SMELLED A BURNED RUBBER SMELL AT ROWS 18-22. UPON ARRIVAL TO AIRCRAFT, INITIAL EVALUATION FOUND NO UNUSUAL SMELLS OR SMOKE. NO CIRCUIT BREAKERS FOUND POPPED, INSPECTED O/H BINS, SEAT POCKETS, CABIN LIGHTS, LAV AND GALLEY AREAS, COFFEEMAKERS, E&E BAYS AND CARGO COMPARTMENTS. RAN ENGINES WITH EACH AND BOTH PACKS OPERATING REF FIM 21-22. NO SMELLS OR VISIBLE EVIDENCE OF SMOKE EXISTS. NOTIFIED ACTING CHIEF INSPECTOR FINDINGS, AND HE HAS RELEASED AIRCRAFT FOR SERVICE REF GMM 8115.

Part: BATTERY — DISCHARGED (CABIN)

3 EACH TAIL CONE SLIDE, 1 EACH TAIL CONE RELEASE HANDLE, AND 2 EACH TAIL COMPARTMENT OVERHEAD EMERGENCY LIGHTS INOP. REMOVED AND REPLACED EMERGENCY LIGHTS BATTERY AND POWER SUPPLY/CHARGER EQ B5-116 AT STATION 1043R IAW AMM 33-51-03 OPS/FUNCTIONAL CHECK NORMAL.

Part: BATTERY PACK — DISCHARGED (CABIN)

TAIL CONE SLIDE (2 OF 3) EMERGENCY LIGHTS INOPERATIVE. REPLACED EMERGENCY LIGHT BATTERY POWER SUPPLY AND BATTERY ASSEMBLY IAW AMM 33-51-03. OPS CHECK NORMAL IAW AMM 33-51-00.

Part: SLIDE — LOW PRESSURE (L1 DOOR)

L1 DOOR SLIDE PACK PRESSURE LOW. REMOVED AND REPLACED SLIDE PER AMM 25-61.

Part: STRUCTURE — DAMAGED (FUSELAGE)

RIGHT FUSELAGE, STA 200 TO 218, LONG L19R TO L20R, TEMPORARY REPAIR. ACCOMPLISHED FUSELAGE PERMANENT DOUBLER REPAIR PER B717 SRM 53-00-01 AND EA 17-53-02135IR. SEE NR 3002 AND 1980.

Part: FRAME — DAMAGED (FUSELAGE)

EO 17-5310-2937 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 TASK CARD 17-5310-2975.

Part: BATTERY PACK — DISCHARGED (CABIN)

EXTERIOR EMERGENCY LIGHT ON WITH SWITCH IN "ARM" POSITION. REMOVED AND REPLACED EMERGENCY BATTERY PACK IAW M/M 33-51-06. OK FOR SERVICE.

Part: BOLT — MISSING (UPLOCK TARGET)

RIGHT MAIN GEAR UNSAFE INDICATION WITH GEAR HANDLE IN UP POSITION. FOUND RIGHT MAIN LANDING GEAR INBOARD DOOR UPLOCK SWITCH TARGET BOLT MISSING. REPLACED BOLT AND OPERATED LANDING GEAR UP AND DOWN 5 TIMES. CHECKS GOOD IAW REF AMM 32-10.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT)

SEVERAL BATTERY PACKS HAVE FAILED THE EMERGENCY BATTERY PACK CAPACITY FUNCTIONAL CHECK TC 33-055-00-01. REMOVED AND REPLACED EMERGENCY BATTERY PACKS M1670, M1674, M1675, M1669, M672, M673 IAW AMM 33-51-06. FUNCTIONAL CHECK GOOD.

Part: FRAME — DAMAGED (FUSELAGE)

EO 17-5310-2895 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: BATTERY PACK — DISCHARGED (CABIN)

AFT ACCESSORY COMPT O/H EMERGENCY LIGHTS INOP. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY & SUPPLY AT RIGHT AFT LAV REF MM 33-51. OP'S CHECK NORMAL.

Part: ENGINE — SURGES (LEFT)

LT ENGINE SURGED IN FLIGHT. ENGINE SHUT DOWN AS IT CONTINUED TO SURGE.

Part: STRUCTURE — GROUND DAMAGE (FS 207)

CATERING TRUCK STRUCK AIRCRAFT ON RIGHT SIDE NEAR R-1 DOOR. INSTALLED REPAIR CLASS 3 PAGE 219-226 LONGERON 19R-20R STA 210-200 AS PER B717 SRM 53-00-01 AND RES 04-0289 WO 24177 AND N/R 3052 AVBORNE.