N991AT

Part: SPAR CAP — NONE (ZONE 600) · airframe 60,900 hrs · 44,029 cycles

RH WING / REAR SPAR / LOWER CAP / AFT FLANGE / XRS = 164 / CRITICAL HOLE INSPECTION. PRI 629860-14AD REQUIRES ACCOMPLISHMENT WHILE IN BHM. ACCOMPLISH PRI 629860-14AD WHILE IN BHM OCT-2025 MAINTENANCE VISIT. (1263856)

Part: NONE — NONE (NONE) · airframe 60,623 hrs · 43,754 cycles

ER/A 628630-14AD REV ORIGINAL REQUIRES SECTION II FOLLOW-ON INSPECTIONS FOR CONTINUED AIRCRAFT AIRWORTHINESS. UPDATE TERMINATING RESTRICTION IN TIME RESTRICTION BLOCK TO MATCH REQUIREMENT IN ER/A 628630-14AD REV ORIGINAL. (1174878)

Part: BATTERY PACK — MALFUNCTIONED (ZONE 200) · airframe 60,235 hrs · 43,350 cycles

FIRST CLASS OVERHEAD EMERGENCY LIGHT BLINKING. EMERGENCY EXIT LIGHT OVER 1R GALLEY DOOR BLINKING, AFT CABIN DOOR EMERGENCY LT BLINKING. REPLACED BATTERY AND CHARGER AT B5-260. (LP 6811967)

Part: WARNING MESSAGE — FALSE ACTIVATION · airframe 60,223 hrs · 43,342 cycles

SHIP 9529 -ATO- APPROX. 90KTS DUE TO FLAPS TAKEOFF CONFIGURATION WARNING. CORRECTIVE ACTION: PERFORMED TAKEOFF WARNING TEST, NO FAULTS FOUND. CHECKED FCC FLAP SENSOR READINGS, FLAP PHYSICAL MOVEMENT AND FLAP TRANSMITTERS. NO DISCREPANCIES NOTED. REPLACED VIA 1 AS PRECAUTION. OPS CHECK GOOD. (LP 6811954)

Part: DOOR — OUT OF ADJUST (ZONE 800) · airframe 58,909 hrs · 42,204 cycles

MAIN CABIN DOOR HARD TO OPEN AND CLOSE. F/O HAD TO OPEN DOOR ON ARRIVAL. THIS COULD PREVENT THE PROPER OPERATION OF THE ESCAPE PATH AND IT IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. MAINTENANCE FOUND L1 DOOR SETTING TOO HIGH IN ITS FRAME. HEIGHT WAS ADJUSTED REF B717 AMM 52-11. PRESSURIZED THE AIRCRAFT AND CHECKED FOR LEAKS. NO LEAKS WERE NOTED. REINSTALLED L1 SLIDE REF AMDS W/C 2561-9004. (LP #4005124)

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,901 hrs · 42,200 cycles

CORROSION ON FRAME STA Y=1022 INTERSECTION WITH LONG 30 AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00752: CORROSION LEVEL 2. CORROSION ON FRAME STA Y=1022 INTERSECTION WITH LONG 30 AT AFT CARGO COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3. PERFORM GVI WITH INITIAL 25,000 CYCLES AND AFTER EVERY 6,500 CYCLES PER B717 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3. (LP #0635252)

Part: WINDOW FRAME — CRACKED (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

CRACK ON CUTOUT (DRAIN AREA) OF LH SLIDING WINDOW AT FWD UPPER FUSELAGE. SUMMARY OF NRC 00047: CRACK ON CUTOUT (DRAIN AREA) OF LH SLIDING WINDOW AT FWD UPPER FUSELAGE WAS REPAIRED PER PRI 621091-14 REV 1 AND ER/A 621091-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-621091 ADDED FOR AC 9529. (LP #0626579)

Part: DOUBLER — CORRODED (SZONE 100) · corrosion level 2 · airframe 58,901 hrs · 42,200 cycles

EXFOLIATION ON UPPER DOUBLER ON INTERNAL CANTED KEEL STA Y=685 APROX BTW LONGERON 30-29R AT FUSELAGE (FUS). SUMMARY OF NRC 00523: CORROSION LEVEL 2. EXFOLIATION ON UPPER DOUBLER ON INTERNAL CANTED KEEL STA Y=685 APROX BTW LONGERON 30-29R AT FUSELAGE, WAS REPAIRED PER PRI 621188-14 REV 2 AND ER/A 621188-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-621188 ADDED FOR AC 9529. (LP #0622850)

Part: ANGLE — CORRODED (ZONE 200) · corrosion level 2 · airframe 58,901 hrs · 42,200 cycles

CORROSION ON RH CUSP ANGLE STA 198 X=-59 AT PAX CABIN. SUMMARY OF NRC 00387: CORROSION LEVEL 2. CORROSION ON RH CUSP ANGLE STA 198 X=-59 AT PAX CABIN WAS REPAIRED PER PRI 621192-14 REV 3 AND ER/A 621192-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-621192 ADDED FOR AC 9529. (LP #0622996)

Part: ACCESS PANEL — DAMAGED (ZONE 300) · airframe 58,901 hrs · 42,200 cycles

ELONGATED NUT HOLES ON OTBD ACTUATOR ACCESS PANEL AT RH ELEVATOR. SUMMARY OF NRC 00563: INTERNAL DOUBLER WAS FABRICATED PER B717-200 SRM 51-41-02-0G, AND DWG 9918480 REV BF, AND RIB PER DWG 9918471 REV B, AND INTERNAL DOUBLER AND RIB WERE REPLACED PER B717 SRM 51-41-08-0G PAR 7 AND 51-41-01-0G. (LP #0621179)

Part: FRAME — CRACKED (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

CRACK ON FRAME BTW STA Y=1037 AND LONG 14L AT AFT PAX CABIN. SUMMARY OF NRC 00289: FRAME BTW STA Y=1037 AND LONG 14L AT AFT PAX CABIN WAS REPAIRED PER ER/A 621344-14 REV ORIG SECTION I, PERMANENT REPAIR. ASSOCIATED ER/A 00-621344 ADDED FOR AC 9529. (LP #0621033)

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,901 hrs · 42,200 cycles

CORROSIONS ON FRAME STA Y=870 BTW L-29L AND L-29R AT AFT CARGO. SUMMARY OF NRC 00206: CORROSION LEVEL 2. CORROSION ON FRAME STA Y=870 BTW L-29L AND L-29R AT AFT CARGO WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3. PERFORM AN INITIAL INTERNAL AN EXTERNAL GVI TO THE REPAIR PERFORMED AT 25,000 FLIGHT CYCLES FROM NOW THAT THE REPAIR WAS INSTALLED AND PERFORM INTERNAL AND EXTERNAL REPETITIVE GVI EVERY 6,500 FLIGHT CYCLES PER B717 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3 PAR 6 TABLE 205. (LP #0615817)

Part: SKIN — DENTED (ZONE 500 FLAP) · airframe 58,901 hrs · 42,200 cycles

SEVERAL DENTS ON (UPPER AND LOWER) SKIN OF FWD MOVABLE VANE AT LH WING. SUMMARY OF NRC 00630: DENTS (9 LOCATIONS) ON LOWER SKIN OF FWD MOVABLE VANE AT LH WING WERE EVALUATED WITH THE FOLLOWING DIMENTIONS WERE: DENT #1 W=0.250" Y=0.003" W/Y=83.33, DENT #2 W=0.320" Y=0.017" W/Y=18.82, DENT #3 W=0.187" Y=0.001" W/Y=187, DENT #5 W=0.320" Y=0.008" W/Y=40, DENT #7 W=0.218" Y=0.007 W/Y=31.14, WERE MEASURED AND FOUND WITHIN LIMITS PER B717-200 SRM 57-53-01-1A-1 PAR 3. (ET) (HFEC) AND (UT) (TAP-TEST) INSPECTIONS WERE PERFORMED ON AREA OF DENTS (9 LOCATIONS) NO CRACK WERE FOUND, BUT DID FIND DISBOND ON DENTS #4, #6, #8, AND #9 PER DC-MD/BOEING NDTSPM PART 6, 06-10-01.001 AND PER DC-MD/BOEING NDTSPM PART 5, 05-10-02.001. DENTS #4, #6, #8, AND #9 WERE REPAIRED PER B717-200 SRM 57-53-01- 2R-1 PAR 4. FOR DENTS FOUND WITHIN LIMITS PERFORM A DVI INSPECTION AND TAP TEST FOR POSSIBLE DISBOND EVERY "C" CHECK PER B717-200 SRM 57-53 -01-1A PARAGRAPH 2.B. (LP #0615454)

Part: LONGERON — CRACKED (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

CRACK ON LONG=1 IN STA Y=794 AT PASSENGER CABIN. SUMMARY OF NRC 00324: LONG=1 IN STA Y=794 AT PASSENGER CABIN WAS REPAIRED PER B717-200 SRM 53-00-05-2R PROCEDURE 2 REPAIR 2. PERFORM A GVI INSPECTION PER B717-200 SRM 53-00-05-2R-2 STEP 7 A TABLE 202 EVERY "C" CHECK. (LP #0613839)

Part: SKIN — WORN (ZONE 600 FLAP) · airframe 58,901 hrs · 42,200 cycles

WEAR ON UPPER SURFACE OF UPPER FIXED GUIDE VANE STA XRS=140.000 RH WING. SUMMARY OF NRC 00010: UPPER SURFACE OF UPPER FIXED GUIDE VANE STA XRS=140.000 RH WING WAS REPAIRED PER B717-200 SRM 57-53-01-2R PROCEDURE 1 REPAIR 1 PAR 4 D AND 51-70-02-0G PROCEDURE GENERAL PAR 11. MAINTENANCE REQUIREMENTS WERE VERIFIED AND NO FURTHER ACTION ARE REQUIRED PER B717-200 SRM 57-53-01-2R PROCEDURE 1 REPAIR 1 PAR 4 D STEP 2 A (1) TABLE 201 DAMAGE TOLERANCE INSPECTION REQUIREMENTS METHOD, INITIAL, REPETITIVE, AND REPLACEMENT NOT APPLICABLE. (LP #0613087)

Part: VANE — WORN (ZONE 500 FLAP) · airframe 58,901 hrs · 42,200 cycles

WEAR ON LEADING EDGE OF AFT MOVABLE VANE LH WING. SUMMARY OF NRC 00770: WEAR ON LEADING EDGE OF AFT MOVABLE VANE LH WING WAS REPAIRED PER B717-200 SRM 57-53-01-2R PROCEDURE 1 REPAIR 1. (LP #0614293)

Part: DOOR FRAME — WORN (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

WEAR ON FUSELAGE CUTOUT STA Y=130 OF PASSENGER DOOR HOOK CAVITY ALSO VERIFY IF RADIUS MEET WITH SRM ON FWD LOWER CORNER. SUMMARY OF NRC 00048: WEAR ON FUSELAGE CUTOUT STA Y=130 OF PASSENGER DOOR HOOK CAVITY WAS REPAIRED PER B717-200 SRM 53-10-01-2R PROCEDURE 7, REPAIR 7 AND 51-40-05-0G AND 51-40-02-0G. (LP #0612898)

Part: VANE — DENTED (ZONE 600 FLAP) · airframe 58,901 hrs · 42,200 cycles

DENTS ON UPPER SURFACE OF AFT MOVABLE FLAP VANE ON RIGHT WING. SUMMARY OF NRC 00623: DENTS (9 LOCATIONS) ON UPPER SURFACE OF AFT MOVABLE FLAP VANE ON RIGHT WING WERE DENT #1 W=0.400" Y=0.001" W/Y=400 DENT #2 W=0.350" Y=0.001" W/Y=350 DENT #3 W=0.343" Y=0.001" W/Y=343 DENT #4 W=0.437" Y= 0.003" W/Y=87.4 DENT #5 W=0.375" Y=0.001" W/Y=375 ,DENT #8 W= 0.406" Y=0.004" W/Y=101.5 DENT #9 W=0.346" Y=0.003" W/Y=115.3 WERE MEASURED AND FOUND WITHIN LIMITS PER B717-200 SRM 57-53-01-1A-1 PAR 3. (ET) (HFEC) AND (UT) (TAP-TEST) INSPECTIONS WERE PERFORMED ON AREA OF DENTS (9 LOCATIONS) NO CRACKS WERE FOUND BUT WERE FOUND DISBOND ON DENTS #6 AND #7 PER DC-MD/BOEING NDTSPM PART 6, 06-10-01.001 AND PER DC-MD/BOEING NDTSPM PART 5, 05-10-02.001. DENTS #6 AND #7 WERE REPAIRED PER B717-200 SRM 57-53-01-2R-1 PAR 4. PERFORM A DETAILED VISUAL INSPECTION (DVI) AND TAP TEST FOR POSSIBLE DISBOND AT EVERY "C" CHECK OR 3,000 CYCLES ON DENTS WITHIN LIMITS PER B717-200 SRM 57-53-01-1A PROCEDURE 1, ALLOWABLE DAMAGE 1 PAR 2 B. (LP #0603743)

Part: VANE — DENTED (ZONE 600 FLAP) · airframe 58,901 hrs · 42,200 cycles

DENTS ON LWR SURFACE OF FWD MOVABLE FLAP VANE ON RIGHT WING. SUMMARY OF NRC 00624: DENTS (7 LOCATIONS) ON LWR SURFACE OF FWD MOVABLE FLAP VANE ON RIGHT WING (DENT #1 W=0.218" Y=0.005" W/Y=43.6, DENT #2 W=0.320" Y=0.012" W/Y=26.66, DENT #6 W=0.250" Y=0.008" W/Y=31.25, DENT #7 W=0.343" Y=0.012 W/Y=28.58), WERE MEASURED AND FOUND WITHIN LIMITS PER B717-200 SRM 57-53-01-1A-1 PAR 3. (ET) (HFEC) AND (UT) (TAP-TEST) INSPECTIONS WERE PERFORMED ON AREA OF DENTS (7 LOCATIONS) NO CRACKS WERE FOUND BUT DID FIND DISBOND ON DENTS #3, #4, AND #5 PER DC-MD/BOEING NDTSPM PART 6, 06-10-01.001 AND PER DC-MD/BOEING NDTSPM PART 5, 05-10-02.001. DENTS #3, #4, AND #5 WERE REPAIRED PER B717-200 SRM 57-53-01-2R-1 PAR. 4. PERFORM A DVI AND TAP TEST FOR POSIBLE DISBOUND AT EVERY "C" CHECK OR 3,000 CYCLES PER B717 SRM 57-53-01-1A PROCEDURE 1 ALLOWABLE DAMAGE 1. (LP #0603658)

Part: SKIN — CRACKED (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

CRACK NTERNAL SKIN UNDER CAP UPPER AFT SIDE OF LH SLIDING WINDOW CUTOUT AT FLIGHT COMPARTMENT. SUMMARY OF NRC 701: INTERNAL SKIN UNDER CAP UPPER AFT SIDE OF LH SLIDING WINDOW CUTOUT AT FLIGHT COMPARTMENT WAS REPAIRED PER B717-200 SRM 56-10-02-2R PROCEDURE 1 REPAIR 1. (LP #0602176)

Part: SKIN — CRACKED (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

CRACK INTERNAL SKIN UNDER CAP UPPER AFT SIDE OF RH SLIDING WINDOW CUTOUT AT FLIGHT COMPARTMENT. SUMMARY OF NRC 702: INTERNAL SKIN UNDER CAP UPPER AFT SIDE OF RH SLIDING WINDOW CUTOUT AT FLIGHT COMPARTMENT WAS REPAIRED PER B717-200 SRM 56-10-02-2R PROCEDURE 1 REPAIR 1. PERFORM AN EXTERNAL GVI OF THE COCKPIT WINDOW REPAIR RH SIDE EVERY C-CHECK PER B717 SRM 56-10-02-2R PROCEDURE 1 REPAIR 1 PAR 6.A TABLE 203 AS MAINTENANCE REQUIREMENTS. (LP #0602395)

Part: SKIN — CRACKED (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

CRACK NTERNAL SKIN UNDER CAP UPPER AFT SIDE OF LH SLIDING WINDOW CUTOUT AT FLIGHT COMPARTMENT. SUMMARY OF NRC 701: INTERNAL SKIN UNDER CAP UPPER AFT SIDE OF LH SLIDING WINDOW CUTOUT AT FLIGHT COMPARTMENT WAS REPAIRED PER B717-200 SRM 56-10-02-2R PROCEDURE 1 REPAIR 1. PERFORM AN EXTERNAL GVI OF THE COCKPIT WINDOW REPAIR LH SIDE EVERY C-CHECK PER B 717-200 SRM 56-10-02-2R PAR 6 A TABLE 203 AS MAINTENACE REQUIREMENT. (LP #0602271)

Part: SKIN — CRACKED (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

CRACK INTERNAL SKIN UNDER CAP UPPER AFT SIDE OF RH SLIDING WINDOW CUTOUT AT FLIGHT COMPARTMENT. SUMMARY OF NRC 702: INTERNAL SKIN UNDER CAP UPPER AFT SIDE OF RH SLIDING WINDOW CUTOUT AT FLIGHT COMPARTMENT WAS REPAIRED PER B717-200 SRM 56-10-02-2R PROCEDURE 1 REPAIR 1. (LP #0602192)

Part: CUSP WEB — CRACKED (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

CRACKS ON CUSP WEB STA 658 AND X=58, STA 516 AND X=49 AT PAX CABIN. SUMMARY OF NRC 00386: CUSP WEB STA 658 AND X=58, STA 516 AND X=49 AT PAX CABIN WERE REPAIRED PER B717-200 SRM 53-00-55-2R-4 FIGURE 203 AND 205. (LP #0599143)

Part: LONGERON — CRACKED (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

CRACKED LONGERON 2LH AT STA Y=1133 AT AFT ACCESSORIES COMPARTMENT. SUMMARY OF NRC 00408: LONGERON 2LH AT STA Y=1133 AT AFT ACCESSOIRES COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-00-05-2R PROCEDURE 2 REPAIR 2. (LP #0599134)

Part: LONGERON — CRACKED (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

CRACKS ON LONGERONS (3 EA), LONG 5L AND LONG 6L ON STA Y=1022. ALSO LONG 5R ON STA Y=1022 AT AFT PAX CABIN. SUMMARY OF NRC 00283: LONGERONS (3 EA), LONG 5L AND LONG 6L ON STA Y=1022 ALSO LONG 5R ON STA Y=1022 AT AFT PAX CABIN WERE REPAIRED PER B717-200 SRM 53-00-05-2R PROCEDURE 2 REPAIR 2, FIG 201. (LP #0597390)

Part: FRAME — CRACKED (ZONE 100) · airframe 58,901 hrs · 42,200 cycles

CRACK ON FRAME BTW STA Y=1037 AND LONG 17R AT PAX CABIN RH SIDE. SUMMARY OF NRC 00287: FRAME BTW STA Y=1037 AND LONG 17R AT PAX CABIN RH SIDE WAS REPAIRED PER B717 SRM 53-20-07-2R-4. PERFORM A GENERAL VISUAL INSPECTION EVERY C-CHECK PER B717-200 SRM 53-20-07-2R PROCEDURE 4 REPAIR 4, STEP 6 TABLE 202. (LP #0593450)

Part: LONGERON — CRACKED (ZONE 200) · airframe 58,901 hrs · 42,200 cycles

CRACK ON LONGERON L10L STA Y=908 AT CPAX CABIN. SUMMARY OF NRC 00268: LONGERON L10L STA Y=908 AT CPAX CABIN WAS REPAIRED PER B717-200 SRM 53-00-05-2R PROCEDURE 2 REPAIR 2. PERFORM DECAL INSPECTION CONDITION EVERY "C" CHECK PER TOPP 30-10-70 PAGE 14 PAR I. (LP #0592598)

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 58,901 hrs · 42,200 cycles

CORROSION ON FLOOR SUPPORT X=-22 BTW STA Y=1022 TO STA Y=1053 WAS FOUND OUT LIMITS AT PASSENGER CABIN (W2). SUMMARY OF NRC 00715: CORROSION LEVEL 2. FLOOR SUPPORT X=-22 BTW STA Y=1022 TO STA Y=1053 AT PASSENGER CABIN (W2) WAS REPLACED AND INSTALLED PER B717-200 SRM 51-41-01-0G. (LP #0591817)

Part: FRAME — WORN (ZONE 100) · airframe 58,901 hrs · 42,200 cycles

WEAR ON PREVIOUS DOUBLER REPAIR ON INTERNAL LOWER FRAME AT AFT BULKHEAD DOOR. SUMMARY OF NRC 00363: REPAIR DOUBLER ON INTERNAL LOWER FRAME AT AFT BULKHEAD DOOR WAS FABRICATED AND REPLACED PER B717-200 SRM 52-10-02-2R PROCEDURE 16 REPAIR 16. (LP #0590940)

Part: DOOR FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,901 hrs · 42,200 cycles

CORROSION ON PREVIOUS REPAIR DOUBLER OF DOOR JAMB FWD SECTION AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00145: CORROSION LEVEL 2. PREVIOUS REPAIR DOUBLER OF DOOR JAMB FWD SECTION AT AFT CARGO COMPARTMENT WAS REPLACED PER B717-200 SRM 53-20-15-2R-7. (LP #0588555)

Part: LONGERON — CRACKED (ZONE 100) · airframe 58,901 hrs · 42,200 cycles

CRACKED LONGERON 17 RH AT STA Y=408 PAX CABIN. SUMMARY OF NRC 00259: LONGERON 17 RH AT STA Y=408 PAX CABIN WAS REPAIRED PER B717-200 SRM 53-00-05-2R PROCEDURE 2 REPAIR 2. PERFORM AN EXTERNAL GVI OF THE REPAIR EVERY C-CHECK PER B717 SRM 53-00-05-2R PROCEDURE 2 REPAIR 2 PAR 7.A. (LP #0579981)

Part: SIGN — MALFUNCTIONED (ZONE 200) · airframe 58,677 hrs · 41,989 cycles

AFT REAR LEFT EXIT SIGN FLASHING. DISCOVERED BOARDING AIRCRAFT. MAINTENANCE REPLACED THE AFT PASSENGER CABIN DROP CEILING EMERGENCY LIGHT BATTERY ASSY PER B717 AMM 33-51. (LP #6186958)

Part: SIGN — DETACHED (CABIN) · airframe 58,535 hrs · 41,864 cycles

THE CENTER ISLE FWD EXIT SIGN FELL DOWN. MAINTENANCE REATTACHED THE SIGN PER B717 AMM 33-51. OPERATIONAL CHECK WAS GOOD. (LP #6142766)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · corrosion level 2 · airframe 56,509 hrs · 40,154 cycles

CORROSION AROUND OF DOOR JAMB FROM STA Y=954 TO Y=990 BTW LONGS 26 RH TO 28 RH AT AFT CARGO COMPARMENT. SUMMARY OF NRC 00049: CORROSION LEVEL 2. DOOR JAMB LOWER PAN WAS REPAIRED PER B717 SRM 53-20-15-2R PROCEDURE 7, REPAIR 7 FIGURE 201. (LP #2928163)

Part: DISC — CRACKED (AIR SEAL F)

MULTIPLE MICRO CRACKS FOUND ON OUTER AIR SEAL F THE LONGEST ONE HAS A RADIAL LENGTH 0.021 INCHES.

Part: NONE — NONE · airframe 53,693 hrs · 37,662 cycles

THE TAIL COMPARTMENT EMERGENCY CEILING LIGHT AND TAILCONE SLIDE EMERGENCY LIGHTS ARE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT BATTERY B5-116 PER B717 AMM 33-51. (LP #8256528)

Part: ANTI-SKID SYS — FAULT MESSAGE · airframe 53,501 hrs · 37,475 cycles

SHIP 9529 - THE "ANTI-SKID FAIL" MESSAGE ILLUMINATED WHILE ON FINAL APPROACH. THE CREW DECLARED AN EMERGENCY WITH ATC AND LANDED NORMALLY. CORRECTIVE ACTION: MAINTENANCE REPLACED THE ANTI-SKID BRAKE CONTROL UNIT, BOTH INBOARD ANTI-SKID DUAL BRAKE CONTROL VALVES, AND BOTH LANDING GEAR INTERLOCK RELAYS. GEAR EXTENSION AND RETRACTION FUNCTIONAL TEST PASSED. THE AIRCRAFT HAS RETURNED TO SERVICE. (LP #8475286)

Part: LANYARD — MISROUTED (TAILCONE) · airframe 51,979 hrs · 36,152 cycles

THE KEVLAR TAILCONE DEPLOYMENT LANYARD IS IMPROPERLY ROUTED AT THE RELEASE CAM. THIS COULD PREVENT PROPER OPERATION OF THE ESCAPE PATH AND IT IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. SUMMARY SEE NRC 001-0134:2700-2002/001 00340: MAINTENANCE REROUTED THE LANYARD, CHECKED THE LOCK CABLE ADJUSTMENT, AND SAFETIED THE TURNBARREL REF B717 AMM 53-52-01. ADJUSTMENT CHECKED WITHIN LIMITS. (LP #1916461)

Part: DOOR FRAME — CRACKED (RT OVERWING) · airframe 51,979 hrs · 36,152 cycles

STA 715.000 RH OVERWING EXIT FRAME CRACKED (CONDITION 3) AT UPPER RADIUS OF FRAME TAB. REF STEP 13 OF 5310-01436-01D. SUMMARY SEE NRC 063-0004:5310-01436-01D/001 00171: REPLACED FRAME REF CARD 5310-01436-03B. (LP #1912105)

Part: WEB — DAMAGED (BS 696-715) · airframe 51,979 hrs · 36,152 cycles

SUBFLOOR CUT FROM STATION 696 TO STATION 715. SUMMARY SEE NRC 063-0004:5310-01436-01D/002 00310: REPAIRED SUBFLOOR PER B717 SRM 53-00-55-2R-4 FIG 223. (LP #1909352)

Part: SKIN — DAMAGED (AFT CARGO DOOR) · airframe 51,979 hrs · 36,152 cycles

THE AFT CARGO DOOR, FORWARD LOWER EDGE OF DOOR, SKIN IS KNIFE EDGE. THE DOOR WAS REPLACED ON NRC 144 AT C-2 CHECK IN ATLANTA. REPAIRED ON SHOP ORDER RO6476. (LP #1906584)

Part: BOLT — DAMAGED (RT MLG WW) · airframe 51,979 hrs · 36,152 cycles

UPON INSPECTION OF SLANT PANEL HARDWARE, FOUND TOP INBOARD BOLT SPINNING ON RH SLANT PANEL IN WHEEL WELL. SUMMARY SEE NRC 001-0197:5300-2005/001 00121: REPLACED DOME NUTS REF B717 SRM 51-40-02. (LP #1902094)

Part: STRUT — DAMAGED (LT MLG) · airframe 51,147 hrs · 35,449 cycles

THE LT MLG FIXED STRUT, OB FITTING HAS TOOLING DAMAGE. NRC 006-0003:3211-4003/010 00024: REWORKED AREA PER B717 CMM/OHM 57-40-1 PAGE 611.005 MATERIAL REMOVED TREATED AND PAINTED BLENDED AREA.

Part: THRESHOLD — CORRODED (AFT CARGO) · airframe 47,998 hrs · 32,839 cycles

NUMEROUS AREAS OF CORROSION WAS FOUND AT THE AFT CARGO THRESHOLD. REPLACED AFT CARGO DOOR THRESHOLD REF B717 SRM 53-20-15-2R.

Part: BUSHING — DAMAGED (ELEVATOR TAB) · airframe 47,998 hrs · 32,839 cycles

HALF BUSHING GROOVED AT 4TH FROM O/B GEARED TAB HINGE, I/B LEG. REPLACED THE BUSHINGS.

Part: SKIN — DAMAGED (RT ELEVATOR TAB) · airframe 47,998 hrs · 32,839 cycles

COMPOSITE EXPOSED ON RIGHT ELEVATOR CONTROL TAB. REMOVED RT ELEVATOR CONTROL TAB REF B717 AMM 27-31-04 TAB ASSY, CONTR OFF 95-5525-9-0002 09529. INSTALLED R/H ELEVATOR CONTROL TAB. REF B-717 AMM 27-31-04 TAB ASSY, CONTR ON 95-5525-9-0002 00268. (LP1202039)

Part: SKIN — DAMAGED (LT ELEVATOR TAB) · airframe 47,998 hrs · 32,839 cycles

COMPOSITE EXPOSED ON LEFT ELEVATOR CONTROL TAB. REMOVE LT ELEVATOR CONTROL TAB, ROUTED TO SHOP FOR REPAIR REF B717 AMM 27-31-04 TAB ASSY, CONTR OFF 95-5525-9-0003 09529. INSTALLED L/H ELEVATOR CONTROL TAB. REF B-717 AMM 27-31-04 TAB ASSY, ON 95-5525-9-0003 55135.

Part: SKIN — DAMAGED (LT ELEVATOR TAB) · airframe 47,998 hrs · 32,839 cycles

COMPOSITE EXPOSED ON LEFT ELEVATOR ANTI-FLOAT TAB. REMOVED LT ELEVATOR GEARED TAB REF B717 AMM 27-31-05 TAB ASSY, GEARE OFF 92-5522-9-0007 00010. INSTALLED LT ELEVATOR GEARED TAB REF B717 AMM 27-31-05. NRC 132. TAB ASSY, GEAR ON 92-5522-9-0007 00129. (LP1202056)

Part: LENS — DAMAGED (EMERGENCY LIGHT) · airframe 44,038 hrs · 30,092 cycles

F/A REPORTED THAT THE AFT RIGHT EMERGENCY CEILING LIGHT LENS IS DAMAGED. MAINTENANCE REPLACED THE LIGHT ASSEMBLY IAW AMM 33-51. OPS CHECKED SATISFACTORY.

Part: SKIN — DELAMINATED (LT WING SPOILER)

DURING UNSCHEDULED NON ROUTINE CHECK FOUND UPPER SURFACE TO BE DELAMINATED AND MISSING SECTION OF SPOILER SKIN.

Part: STRUCTURE — CORRODED (COCKPIT) · corrosion level 2 · airframe 43,213 hrs · 29,522 cycles

CORROSION ON PRINTER ENCLOSURE IN THE COCKPIT. THE DAMAGED AREA FOR THE PRINTER ENCLOSURE WAS FABRICATED AND REPLACED IAW DWG 5991370, REV ORIGINAL, AND SRM 51-41-02.

Part: ANGLE — CRACKED (BS 1022) · airframe 43,213 hrs · 29,522 cycles

CRACKED ANGLE ON THE RH AFT ENGINE PYLON SUPPORT BULKHEAD BS 1022, LONGERON 7R. REPAIRED IAW ETI 17-17-164, REV ORIGINAL, AND ER/A 560925-14, REV ORIGINAL.

Part: SKIN — CRACKED (BS 1022) · airframe 43,213 hrs · 29,522 cycles

CRACKED FUSELAGE SKIN BS 1022, BETWEEN LONGERONS 13L TO 14L. REPAIRED IAW ETI-17-17-149, REV 2, AND ER/A 560891-14, REV ORIGINAL.

Part: SKIN — CRACKED (BS 1022) · airframe 43,213 hrs · 29,522 cycles

CRACKED FUSELAGE SKIN BS 1022, BETWEEN LONGERONS 13R TO 14R. REPAIRED IAW ETI-17-17-148, REV 2, AND ER/A 560890-14, REV ORIGINAL.

Part: LONGERON — CRACKED (BS 1152) · airframe 43,213 hrs · 29,522 cycles

CRACKED LONGERON 3R, BS 1152. HFEC WAS ACCOMPLISHED IAW NDT SPM 06-10-01.001. THE CRACKS WERE CONFIRMED ON THE LONGERON. TRIMMED OUT AND NO CRACKS WERE FOUND NDT SPM 06-10-01.001. LONGERON WAS REPAIRED IAW SRM 53-00-05, REP 2.

Part: FITTING — CRACKED (BS 663 BULKHEAD) · airframe 43,213 hrs · 29,522 cycles

CRACKED VERTICAL FITTING BS 663 RBL 22 Z=-12, THE FITTING WAS REPLACED IAW DWG 9910009-123, REV BB, AND SRM 51-41-05. LEAK CHECKED IAW AMM 28-00-00, NO LEAKS FOUND.

Part: FRAME ANGLE — CORRODED (BS 927) · corrosion level 2 · airframe 43,213 hrs · 29,522 cycles

CORROSION ON FRAME ANGLE BS 927, BETWEEN LONGERONS 29L - 30L IN THE AFT CARGO BAY. REPAIRED IAW SRM 53-00-06-2R, REP 2.

Part: FITTING — CRACKED (BS 661) · airframe 43,213 hrs · 29,522 cycles

CRACK ON MAIN FRAME WING TO FUSELAGE FITTING BS 661, LONGERON 22L. REPAIRED IAW ETI-17-17-155, REV ORIGINAL, AND ER/A 560940-14, REV ORIGINAL.

Part: DOOR FRAME — CORRODED (BS 200) · corrosion level 2 · airframe 43,213 hrs · 29,522 cycles

CORROSION ON DOOR FRAME WEB BS 200, LONGERON 18L. A REPAIR WAS ACCOMPLISHED IAW ETI-17-17-160, REV 3, AND ER/A 560920-14, REV ORIGINAL.

Part: LONGERON — CRACKED (BS 1133) · airframe 43,213 hrs · 29,522 cycles

CRACKED LONGERON 2R, BS 1133. THE LONGERON WAS REPAIRED IAW SRM 53-00-05-2R, PROCEDURE 2. HFEC INSPECTION WAS ACCOMPLISHED, NO CRACKS WERE FOUND IAW NDT SPM 06-10-01.

Part: TAB — WORN (RUDDER) · airframe 43,213 hrs · 29,522 cycles

WEAR ON UPPER CORNER AT RUDDER TAB. THE RUDDER TAB WAS REPAIRED IAW SRM 55-41-01-2R-1, REPAIR 1, AND JIC 5464417.

Part: TAB — STUCK (RUDDER) · airframe 43,213 hrs · 29,522 cycles

DURING RUDDER INSTALLATION, RUDDER CONTROL TAB WAS STRUCK ON RT SIDE.

Part: TAB — DEBONDED (AILERON TRIM) · airframe 43,213 hrs · 29,522 cycles

DEBONDED AILERON TRIM TAB UPPER SURFACE XAT=12 ON THE LT WING. TRIM TAB WAS REPAIRED IAW SRM 51-70-02-2R-3, REPAIR 3.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,213 hrs · 29,522 cycles

EXFOLIATED CORROSION ON PRODUCTION DOUBLER P/N 9915561-73 OF AFT PRESSURE BULKHEAD LWR AREA. CORROSION LEVEL 2. PRODUCTION DOUBLER P/N 9915561-73 WAS REPLACED PER SRM 51-41-02 AND SRM 51-41-05.

Part: FLOOR PANEL — CRACKED (COCKPIT) · airframe 43,213 hrs · 29,522 cycles

CRACKED COCKPIT FLOOR PANEL 211ANF. A NEW FLOOR PANEL WAS FABRICATED IAW SRM 53-20-50-2R, REP 3, AND INSTALLED IAW CARD 2040-0058.

Part: CUSP WEB — CRACKED (BS 889-908) · airframe 43,213 hrs · 29,522 cycles

CRACKED CUSP WEB BS 889 TO 908, BETWEEN LBL 56 AND 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-00-55 2R-4, FIG 226.

Part: FRAME ANGLE — CRACKED (BS 1022) · airframe 43,213 hrs · 29,522 cycles

CRACKED FRAME ANGLE BS 1022 BETWEEN LONGERONS 16 - 17L. THE FRAME ANGLE WAS REPLACED IAW SRM 51-41-02 AND SRM 51-41-05.

Part: FRAME — CRACKED (BS 679) · airframe 43,213 hrs · 29,522 cycles

CRACKED LH FRAMES STA Y=679, Y=694, AND Y=715 AT CANTED KEEL AREA. (FUS). NRC 00365: FRAMES WERE REPAIRED PER B717-200 SRM 51-70-11-2R. CRACKS WERE FOUND WITH FOLLOW DIMENTIONS: STA Y=679 1) 2.350"; STA Y=694 1) 1.370", 2) 1.350", 3) 0.800"; STA Y= 715 1) 0.700" HFEC INSPECTION WAS ACCOMPLISHED AND NO CRACKS WERE FOUND AFTER THE TRIM OUT PER DC-MD NDT SPM 06 -10-01.001 / EQUP. MENTOR N/C 1137 EXP. 18MAY18. (LP #0204506)

Part: FRAME ANGLE — CRACKED (BS 1022) · airframe 43,213 hrs · 29,522 cycles

CRACKED LT ANGLE AT BS 1022, BETWEEN LONGERONS 13 & 14L. THE FRAME ANGLE WAS REPLACED IAW DWG 9912243, REV JV, SRM 51-41-02-0G, AND SRM 51-41-02-0G.

Part: CUSP WEB — CRACKED (BS 674) · airframe 43,213 hrs · 29,522 cycles

CRACKED CUSP WEB BS 674, LBL 44. THE CUSP WEB WAS REPLACED IAW SRM 53-00-55-2R-4, FIG 226.

Part: FRAME — CRACKED (BS 694) · airframe 43,213 hrs · 29,522 cycles

CRACKED RH FRAMES STA Y=679, Y=694, AND Y=715 AT CANTED KEEL AREA. (FUS). NRC 00364: FRAMES WERE REPAIRED PER B717-200 SRM 51-70-11-2R. CRACKS WERE FOUND WITH FOLLOW DIMENTIONS: STA Y=679 1) 2.350", 2) 2.500"; STA Y=694 1) 2.750"; STA Y= 715 1) 1.650", 2) 0.750". HFEC INSPECTION WAS ACCOMPLISHED AND NO CRACKS WERE FOUND AFTER THE TRIM OUT PER DC-MD NDT SPM 06 -10-01.001 / EQUP. MENTOR N/C 1137 EXP. 18MAY18. (LP #0204513)

Part: FRAME ANGLE — CRACKED (BS 1022) · airframe 43,213 hrs · 29,522 cycles

CRACKED FRAME ANGLE BS 1022 BETWEEN LONGERON 13 - 14R. THE FRAME ANGLE WAS REPLACED IAW DWG 9912243 REV JS, SRM 51-41-05, AND SRM 51-41-02.

Part: ANGLE — CORRODED (BS 137-157) · corrosion level 2 · airframe 43,213 hrs · 29,522 cycles

CORROSION ON THE ANGLE OF THE RT CONSOLE FROM BS 137 TO 157 BETWEEN RBL 44 TO 54. NEW ANGLE WAS REPLACED PER B-717-200 DWG #9936533 REV. CM, SRM 51-41-01 AND SRM 51-41-02. (LP #0203440)

Part: FITTING — CRACKED (BS 1063) · airframe 43,213 hrs · 29,522 cycles

CRACKED LEFT FITTING BS 1063, LBL 17, Z=20. IN THE AFT CABIN PRESSURE BULKHEAD EMERGENCY EXIT DOOR FRAME. A NEW FITTING WAS INSTALLED IAW SRM 51-41-05, 51-41-02, AND 51-40-08.

Part: DOOR FRAME — CRACKED (NLG) · airframe 43,213 hrs · 29,522 cycles

CRACK ON THE RT NLG DOOR FRAME. NLG DOOR FRAME WAS REPAIRED IAW SRM 53-10-14-2R, REP 2.

Part: DOOR FRAME — CRACKED (NLG) · airframe 43,213 hrs · 29,522 cycles

CRACK ON Y=42 LT SIDE OF NLG DOOR FRAME. THE NLG DOOR FRAME WAS REPAIRED IAW SRM 53-10-14-2R, REP 2.

Part: HINGE — WORN (CARGO DOOR) · airframe 43,213 hrs · 29,522 cycles

FREE PLAY ON BOTH HINGES AT FWD CARGO DOOR. THE FWD & AFT HINGES WERE REPAIRED IAW ER/A 559577-14MA, REV ORIGINAL.

Part: FITTING — CRACKED (BS 715) · airframe 43,213 hrs · 29,522 cycles

CRACKED FITTING, BS 715, RBL 44, Z=-8. THE FITTING WAS REPLACED IAW SRM 51-41-02, 51-41-05, AND 51-40-08.

Part: ANGLE — CRACKED (EMERGENCY EXIT) · airframe 43,213 hrs · 29,522 cycles

CRACKED INTERNAL ANGLE. UPPER AFT CORNER AT THE RT FWD EMERGENCY EXIT DOOR. THE ANGLE WAS REPLACED IAW SRM 51-41-02, 51-41-05, AND DWG 9957735, REV. G.

Part: DOUBLER — DAMAGED (F/A SEAT AREA) · airframe 43,213 hrs · 29,522 cycles

WEAR ON DOUBLER AT FLIGHT ATTENDANT SEAT ENCLOSURE OF AFT VENTRAL DOOR. THE WEAR WAS BLENDED IAW SRM 52-10-02-1A-2. NDT WAS ACCOMPLISHED IAW SPM 04-00-07, PAR 5, FIG 3, SHEET 1 AND 2, FOUND TO BE OUT OF LIMITS IAW SRM 52-10-02-1A-2. REPAIRED IAW SRM 52-10-02-2R, REPAIR 16.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · airframe 43,213 hrs · 29,522 cycles

CORROSION ON FUEL TANK ACCESS PLATE 620JB. THE ACCESS PANEL WAS REPLACED.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · airframe 43,213 hrs · 29,522 cycles

CORROSION ON FUEL TANK ACCESS PANEL 620DT OUT OF ALLOWABLE LIMITS, THE ACCESS PANEL WAS REPLACED IAW SRM 57-10-01, PAR 5, REPAIR 2.

Part: ACCESS PANEL — CORRODED (WING) · airframe 43,213 hrs · 29,522 cycles

CORROSION ON FUEL TANK ACCESS PLATES #520CT AND 620CT (AMDS 5720-2001) (AI) (AD). NRC 00472: THE UPPER WING ACCESS DOOR 520CT AND 620CT WERE REPLACED PER B-717 SRM 57-10-01 REPAIR 2 PAR. 5 CONDITION III AND PART NUMBERS WERE VERIFIED PER B-717 AIPC 57-22-01-01. (LP #0201823)

Part: ACCESS PANEL — DAMAGED (WING) · airframe 43,213 hrs · 29,522 cycles

ELONGATED HOLES ON FUEL TANK ACCESS PLATES #520CB, 520FT, AND 520EB (AI). NRC 00471: FUEL ACCESS PLATES #520CB, 520FT, AND 520EB WERE REPAIRED PER B-717 SRM 57-10-01 REPAIR 2 PAR. 5 CONDITION II. (LP #0201639)

Part: ANGLE — CRACKED (EMERGENCY EXIT) · airframe 43,213 hrs · 29,522 cycles

CRACKED INTERNAL ANGLE ON UPPER AFT AND FWD CORNER OF THE RT AFT EMERGENCY EXIT DOOR. REPLACED IAW SRM 51-41-02, 51-41-05, AND DWG 9957735, REV G.

Part: PAN — CRACKED (CARGO DOOR) · airframe 43,213 hrs · 29,522 cycles

CRACK ON INNER PAN BETWEEN BEAMS 1 AND 2 AFT EDGE AT FWD CARGO COMPARTMENT DOOR. HFEC INSPECTION WAS ACCOMPLISHED IAW NDT SPM PART 6, 06-10-01.001 AND ONE CRACK WAS DELIMTED OF 2.000" LENGHT. REPARIED IAW SRM 52-30-02-2R-4. FIGURE 201.

Part: ANGLE — CRACKED (EMERGENCY EXIT) · airframe 43,213 hrs · 29,522 cycles

CRACKED INTERNAL ANGLE, UPPER FWD CORNER AT THE LT AFT & LT FWD EMERGENCY EXIT DOORS THE ANGLES WERE REPLACED IAW SRM 51-41-02, 51-41-05, AND DWG 9957735, REV G.

Part: CHANNEL — CRACKED · airframe 43,213 hrs · 29,522 cycles

CRACKED CHANNELS ON FLOOR PANELS #221NF, 221SF, 221TF, 221XF, 222AQF, 222EF, 222SF, 222AF, 222XF, AND 222AFF AT CABIN PAX (CPAX). NRC 00338: HFEC INSPECTION WAS ACCOMPLISHED ON CHANNELS ON FLOOR PANELS #221NF, 221TF, 221XF, 222AQF, AND 222SF AND NO CRACKS WERE FOUND PER DC-MD/BOEING NDT SPM 06-10-01.001 EQUIPMENT: PHASEC 2D C/N: 925 EXP. DATE: 09MAY18. CRACKED CHANNELS ON FLOOR PANELS #222AF, 222XF, 221SF, 222AFF, AND 222EF WERE REPAIR PER B 717-200 SRM 53-20-50-2R-5 REPAIR 5 FIG. 201. (LP #0196537)

Part: BEAM — CRACKED (L1 DOOR) · airframe 43,213 hrs · 29,522 cycles

CRACKED BEAM 1 ON AFT EDGE BS 200 ON THE L1 DOOR. THE BEAM WAS REPAIRED IAW SRM 52-10-02-2R, REPAIR 7, FIG .201.

Part: WEB — CRACKED (BS 218) · airframe 43,213 hrs · 29,522 cycles

CRACK FOUND ON WEB, BS 218, RBL 45. THE WEB WAS REPAIRED IAW SRM 53-00-55-2R-4.

Part: BEARING — CORRODED (NLG) · airframe 43,213 hrs · 29,522 cycles

CORROSION ON THRUST WASHER BEARING OF NOSE LANDING GEAR. NRC 00120: THRUST WASHER BEARING OF NOSE LANDING GEAR WAS REPLACED IAW CMM 32-21-13.

Part: ANGLE — CORRODED (BS 954-994) · airframe 43,213 hrs · 29,522 cycles

CORROSION ON ANGLES AT LOWER DOOR FRAME BS 954 TO 994 IN THE AFT CARGO BAY. THE ANGLES WERE REMOVED AND FABRICATED NEW ANGLES AND INSTALLED IAW SRM 53-20-15-2R-10, REP 10, FIG 201.

Part: CUSP WEB — CRACKED (BS 674) · airframe 43,213 hrs · 29,522 cycles

CRACKED CUSP WEB, BS 674, RBL 44. THE CUSP WEB WAS REPAIRED IAW SRM 53-00-55-2R-4, FIG 219.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 43,213 hrs · 29,522 cycles

DELAMINATED FLOOR PANELS #221JF, 221KF, 221LF, 221DF, 221FF, 221CF, 221BF, 221AF, AND 223GF AT PAX CABIN. NRC 00433: FLOOR PANEL #221JF, 221KF, AND 221CF WERE REPLACED AND IDENTIFIED PER B-717 SRM 53-20-50-2R REP 3. FLOOR PANEL #221DF, 221FF, 221AF, AND 221BF WERE REPLACED FERRULS AND NO DELAMINATION WAS FOUND PER B-717 SRM 53-20-50-2R REP 3. FLOOR PANELS #221LF AND 223GF WERE CLEANED PER PS 900-1-2-2 N 02 AND NO DELAMINATION WAS FOUND. (LP #0194884)

Part: BEAM — CRACKED (L1 DOOR) · airframe 43,213 hrs · 29,522 cycles

CRACKED BEAM 7 ON AFT EDGE BS 200 AT THE L1 DOOR. THE BEAM WAS REPAIRED IAW SRM 52-10-02-0G, FIG. 201.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 43,213 hrs · 29,522 cycles

CORROSION ON FLOOR SUPPORT STA Y=200 BTW X=9 TO X=14 AT PAX CABIN W1 IN REF NRTC 00386. SUPPORT WAS REMOVED AND NEW FLOOR SUPPORT WAS INSTALLED PER SRM 51-41-02.

Part: PAN — CRACKED (WINDOW) · airframe 43,213 hrs · 29,522 cycles

CRACKS ON RING PAN AT CAB PAX LT WINDOWS LWR CORNERS AT STA Y=656, Y= 831, Y=852 (CPAX). REPAIR WAS ACCOMPLISHED PER SRM 56-20-02-2R PROCEDURE 1.

Part: PAN — CRACKED (WINDOW) · airframe 43,213 hrs · 29,522 cycles

CRACKS ON RING PAN AT CAB PAX RT WINDOWS LWR CORNERS AT STA Y=833, Y= 581 (CPAX). REPAIR WAS ACCOMPLISHED PER SRM 56-20-02-2R PROCEDURE 1.

Part: UNKNOWN — BURNED (CABIN) · airframe 42,587 hrs · 29,074 cycles

FLIGHT ATTENDANTS REPORT ODOR NEAR ROW 23 TWO DIFFERENT TIMES. BOTH TIMES IT WENT AWAY. NO VISIBLE SMOKE OBSERVED. DROPPED CEILING PANELS ON 19CDE, 23 CDE REMOVED COVER FOR EMER LITE BATTERY PACK AT 20CD. RAN UPPER BEACON & EMER LIGHTS - NO UNUSUAL SMELL. INSPECTED UPPER CEILING LIGHTS, WIRE BUNDLES, EMER LIGHT PACKS AROUND ROW 19-26 - NTF. INSP PED PLUGS ROW 19-26, FOUND SEAT 23E PED BURNT/DISCOLORED. REPLACED SAME PER AMM 24-58, CKS GOOD. C/W NO GO ODI PROCEDURES, RPLD BAGS. RAN BOTH ENGS W/ PACKS ON 85% N1 FOR SEVERAL MINUTES, NO SMELL NOTED. A/C OK FOR SVC.

Part: FAN — FAILED (GASPER) · airframe 42,439 hrs · 28,968 cycles

F/A REPORTED STRONG ODOR IN AFT CABIN DURING APPROACH. FOUND GASPER VENT FAN INOPERATIVE AND CAUSING A BURNING ODOR. COMPLIED WITH NO GO ODI PREV. 2172. CABIN ODOR WAS DETERMINED TO BE ELECTRICAL NOT APU, PERFORMED A DUCT BURNOUT & REPLACED THE COALESCER BAGS IAW AMM 21-54. PERFORMED A VERIFICATION FLIGHT IAW 9800204. NO DEFECTS NOTED THRU ALL PHASES OF FLIGHT.

Part: SKIN — DELAMINATED (LT WING SPOILER)

DURING ROUTINE MAINTENANCE LT SPOILER FOUND WITH DELAMINATION ALONG THE UPPER AND LOWER SURFACE.

Part: SKIN — DELAMINATED (RT SPOILER)

DURING NON-ROUTINE UNSCHEDULED CHECK, RT WING INBD SPOILER FOUND DELAMINATED.

Part: SKIN — DELAMINATED (SPOILER)

DURING NON-ROUTINE LINE UNSCHEDULED CHECK, LT INBD SPOILER FOUND DELAMINATED.

Part: SKIN — DELAMINATED (SPOILER)

DURING NON ROUTINE UNSCHEDULED CHECK DELAMINATION WAS FOUND ON THE RT OTBD SPOILER.

Part: SLIDE — DAMAGED (L1 DOOR) · airframe 38,900 hrs · 26,285 cycles

INSPECTION DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE AT 1L DOOR WAS NO LONGER IN AN ACCEPTABLE CONFIGURATION. THE SLIDE LACING WAS DAMAGED WHICH COULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SYSTEM. THE SLIDE WAS REPLACED AND THE RII WAS COMPLETED SATISFACTORILY.

Part: DOOR SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,068 hrs · 28,006 cycles

AFT CARGO DOOR SILL HAS CORROSION. C-CHECK NR 31, AFT CARGO DOOR JAMB PAN REPLACED PER DRAWING J060228.

Part: CUSP WEB — DAMAGED (BS 160-200) · airframe 38,900 hrs · 26,285 cycles

TOOLING DAMAGE TO CUSP MEMBRANE BS 160-200 L1 ENTRY DOOR. ACCOMPLISHED REPAIR IAW PRI 542148-14, REV 0, JOB COMPLETE PENDING FINAL ER/A.

Part: SKIN — CRACKED (BS 1087) · airframe 38,900 hrs · 26,285 cycles

FUSELAGE SKIN CRACKED AT FASTENER ON RT SIDE ABOVE PYLON, BS 1087. REPAIR WAS ACCOMPLISHED IAW PRI 542147-14, REV 0 AND COMPLIED WITH ER/A 542147-14 REV ORIGINAL. LOG PAGE 2262164 FOR RESTRICTED REPAIR INSTRUCTIONS.

Part: SKIN — CRACKED (BS 1076) · airframe 38,900 hrs · 26,285 cycles

ER/A 542146-14 ISSUED FOR FUSELAGE CRACK AT BS 1076 ON L14R. FOLLOW ON ACTION IS REQUIRED. THIS IS A MAJOR REPAIR. ACCOMPLISH SECTION II NTE 12 MONTHS FROM ACCOMPLISMENT OF SECTION I REPAIR. ASSOCIATED ER/A 95-542146 ADDED FOR AC 9529. ACCOMPLISHED REPAIR IAW PRI 542146-14, REV 0 AND ER/A 542146-14, SECTION 1 REV ORIGINAL.

Part: SKIN — CRACKED (BS 1087) · airframe 38,900 hrs · 26,285 cycles

ER/A 542147-14 ISSUED FOR FUSELAGE CRACK AT BS 1087 ON L14R. FOLLOW ON ACTION IS REQUIRED. THIS IS A MAJOR REPAIR. ACCOMPLISH SECTION II NTE 12 MONTHS FROM ACCOMPLISHMENT OF SECTION I REPAIR. ASSOCIATED ER/A 95-542147 ADDED FOR AC 9529.

Part: FLOOR SUPPORT — CORRODED (BS 160-200) · corrosion level 2 · airframe 38,900 hrs · 26,285 cycles

FWD CABIN FLOOR PANEL 221EF BS 160-200, OTBD SUPPORT UPPER SURFACE CORRODED. BLENDED CORROSION, FOUND TO BE OUT OF LIMITS IAW SRM 53-00-00, FIG 103. FABRICATED NEW FILLER FROM 2024T3 .100" IAW DWG 9957828-11. TREATED PRIMED AND PAINTED. REMOVED CORROSSION FROM VERTICLE FLANGE ORIGINAL THICKNESS .040" WITH .003" REMOVED WITHIN LIMITS. TREATED PRIMED AND PAINTED. LEVEL 2 CORROSION.

Part: PIN — OUT OF POSITION (L1 DOOR SLIDE) · airframe 35,017 hrs · 23,115 cycles

DURING LINE CHECK, NOTED THE L1 DOOR SLIDE PARACHUTE PIN WAS OUT OF POSITION. REPLACED THE L1 DOOR SLIDE AND PERFORMED THE REQUIRED INSPECTION.

Part: TAIL CONE — NO TEST · airframe 34,527 hrs · 22,663 cycles

DURING ROUTINE TAILCONE DROP IAW TASK 95-0552-8-0001, THE TAILCONE WOULD NOT DEPLOY. COMPLIED WITH REPAIRS IAW ER/A 95-522520-14 AND THE TAIL CONE LOCK MECHANISIM WORKED CORRECTLY WHILE ACCOMPLISHING TAIL CONE OPS CHECK.

Part: LENS — CRACKED (EXIT SIGN) · airframe 34,355 hrs · 22,514 cycles

EMERGENCY EXIT SIGN CRACKED AT ROW 1. R & R LENS IAW AMM.

Part: LENS — MISSING (CABIN) · airframe 34,355 hrs · 22,514 cycles

TAIL CONE EMERGENCY EXIT WALKWAY LIGHT LENSES MISSING. INSTALLED LENS IAW MM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 34,355 hrs · 22,514 cycles

EMERGENCY EXIT CEILING LIGHTS INOPERATIVE. RELAMPED LIGHT IAW AMM.

Part: LIGHT — CRACKED (CABIN) · airframe 34,355 hrs · 22,514 cycles

R1 DOOR EMERGENCY EXIT LIGHT CRACKED. R & R LIGHT IAW MM.

Part: COVER — OUT OF POSITION (CABIN) · airframe 33,958 hrs · 22,271 cycles

RT EEPLS COVER OUT OF POSITION AT STATION 392. REPOSITIONED COVER IAW MM.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FRAME ATTACH ANGLE CRACKED AT STATION 1033, LONGERON 2L. R & R ANGLE IAW DRAWING & SRM.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FRAME ATTACH ANGLE CRACKED AT STATION 1033, LONGERON 2R. R & R ANGLE IAW DRAWING & SRM.

Part: PAN — CORRODED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FWD CARGO COMPARTMENT LOWER DOOR SILL FRAME WEB CORRODED BETWEEN STATION 375 TO STATION 381. R & R PAN IAW SRM.

Part: ATTACH FITTING — CRACKED (CARGO DOOR) · airframe 33,958 hrs · 22,271 cycles

FWD CARGO COMPARTMENT DOOR INTERNAL STRUCTURE AFT LOWER STOP ASSEMBLY ATTACH FITTING CRACKED. R & R FITTING IAW SRM.

Part: SPLICE — CORRODED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

AFT PIT CARGO DOOR CUTOUT AT FUSELAGE FRAME BOTH LOWER DOOR CUTOUT PAN SPLICES CORRODED AT BS 954, BETWEEN LONGERON 27R TO LONGERON 26R. R & R SPLICE IAW SRM.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

RT FWD INNER VERTICAL LE SUPPORT ANGLE CRACKED JUST FWD OF STATION 1144. R & R ANGLE IAW SRM.

Part: COVER — CRACKED (EXIT SIGN) · airframe 33,958 hrs · 22,271 cycles

R1 UPPER DOOR LINER EMERGENCY EXIT SIGN COVER CRACKED. R & R COVER IAW MM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

CUSP WEB CRACKED AT STATION 655, LONGERON 18L. R & R WEB IAW SRM & DRAWING.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

RT CUSP WEB CORRODED BETWEEN STATION 465 TO STATION 484. REPAIRED CUSP WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

RT CUSP WEB CORRODED BETWEEN STATION 503 TO STATION 522. REPAIRED CUSP WEB IAW SRM.

Part: PANEL — CORRODED (LT WING) · airframe 33,958 hrs · 22,271 cycles

LT WING FUEL PANEL NR 520LB INTERIOR MATING SURFACE CORRODED. R & R PANEL IAW SRM.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

LT PYLON SUPPORT BULKHEAD ANGLE CRACKED AT STATION 1022, LONGERON 6L. REPAIRED SUPPORT IAW EA.

Part: PANEL — CORRODED (LT WING) · airframe 33,958 hrs · 22,271 cycles

LT WING FUEL PANEL NR 520DB INTERIOR MATING SURFACE CORRODED. R & R PANEL IAW SRM.

Part: FRAME — CORRODED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FUSELAGE FRAME CORRODED AT BS 427, BETWEEN LONGERONS 25R & 26R. REPAIRED LONGERON IAW SRM.

Part: BRACKET — CRACKED (RT WING) · airframe 33,958 hrs · 22,271 cycles

RT WING LE NEXT TO FS WING TO RIB BRACKET CRACKED. R & R STRAP IAW DRAWING.

Part: BRACKET — CRACKED (LT WING) · airframe 33,958 hrs · 22,271 cycles

LT WING LE WING TO RIB BRACKET CRACKED. R & R BRACKET IAW DRAWING & SRM.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FLOOR SUPPORT ''Z'' ANGLE CORRODED AT BS 1059, RBL 16. R & R "Z" ANGLE IAW SRM & DRAWING.

Part: FITTING — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FRAME FITTING CRACKED AT STATION 636, LONGERON 18L. R & R FITTING IAW SRM & DRAWING.

Part: TRAY — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

WINDOW FRAME TRAY CRACKED BETWEEN STATION 794 & STATION 813, LONGERON 14R. REPAIRED TRAY IAW SRM & DRAWING.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

CREASE BEAM CUSP WEB CORRODED BETWEEN STATION 737 TO STATION 756, LONGERON 18R. REPAIRED WEB IAW SRM.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 33,958 hrs · 22,271 cycles

CABIN FLOOR PANEL 221SF CORRODED AT INBD EDGE FASTENERS RT SIDE BETWEEN STATION 256 TO STATION 313. R & R PANEL IAW SRM & DRAWING.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

RT CUSP WEB CORRODED BETWEEN STATION 541 TO STATION 560, STRINGER 18R. R & R CUSP WEB IAW SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

CUSP WEB CRACKED BETWEEN STATION 655 TO STATION 674, STRINGER 18R. R & R WEB IAW SRM.

Part: TRAY — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

WINDOW FRAME TRAY CRACKED IN LOWER AFT CORNER BETWEEN STATION 851 & 870, LONGERON 14R. R & R FRAME TRAY IAW DRAWING & SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

CUSP WEB CRACKED AT STATION 655, LONGERON 18R. R & R CUSP WEB IAW SRM.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

VERTICAL SEAT TRACK WHITE SUPPORT FITTING LOWER END CRACKED AT BS 737 LBL 45. R & R FITTING IAW SRM & DRAWING.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

VERTICAL SEAT TRACK WHITE SUPPORT FITTING LOWER END CRACKED AT BS 737 LBL 45. R & R FITTING IAW SRM & DRAWING.

Part: FRAME — CORRODED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FWD CARGO COMPARTMENT FRAME CORRODED AT STATION 332, LONGERON 30. REPAIRED FRAME IAW SRM.

Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FWD CARGO COMPARTMENT, BILGE, FWD SIDE OF FRAME STATION 237, BELOW RT CARGO TIE DOWN TRACK, ATTACH CLIP COMMON TO INTERCOSTAL & FRAME CLIP CRACKED. R & R CLIP IAW SRM & DRAWING.

Part: STRAP — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FWD BULKHEAD PANEL ATTACH STRAP CRACKED AT BS 817, BL 0 TO 23 RBL. R & R STRAP IAW SRM & DRAWING.

Part: STRAP — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FWD BULKHEAD PANEL ATTACH STRAP CRACKED AT BS 817, BL 0 TO LBL 0. R & R STRAP IAW SRM & DRAWING.

Part: STRAP — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FWD BULKHEAD CRACKED AT BS 817, BL 0 TO LBL 20. REPAIRED STRAP IAW SRM & DRAWING.

Part: STRAP — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

FWD BULKHEAD PANEL ATTACH STRAP CRACKED AT BS 817, BL 0 TO RBL 30. R & R STRAP IAW SRM & DRAWING.

Part: PANEL — CRACKED (VERTICAL STAB) · airframe 33,958 hrs · 22,271 cycles

VERTICAL STABILIZER TIP TOP FORWARD ACCESS PANEL UPPER LE CRACKED. REPAIRED PANEL IAW SRM.

Part: PANEL — CRACKED (LT WING) · airframe 33,958 hrs · 22,271 cycles

LT WING PANEL 530HA CRACKED. REPAIRED PANEL IAW EA.

Part: INLET — CRACKED (VERTICAL STAB) · airframe 33,958 hrs · 22,271 cycles

VERTICAL STABILIZER RAM AIR INLET RT SIDE CRACKED. REPAIRED INLET IAW SRM & DRAWING.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 33,958 hrs · 22,271 cycles

EXTERNAL FUSELAGE TAIL COMPARTMENT RT LOUVER VENT BOX SHROUD AFT UPPER CORNER ANGLE CRACKED. R & R VENT IAW SRM & DRAWING.

Part: COVER — OUT OF POSITION (R1 DOOR) · airframe 32,885 hrs · 21,606 cycles

R1 DOOR SLIDE COVER OUT OF POSITION. REMOVED AND REPLACED COVER ASSY PER MM.

Part: COVER — OUT OF POSITION (R1 DOOR) · airframe 32,885 hrs · 21,606 cycles

R1 DOOR SLIDE COVER IS OUT OF PLACE. REMOVED AND REPLACED COVER ASSY PER MM.

Part: RETAINER — BROKEN (R1 DOOR) · airframe 32,870 hrs · 21,598 cycles

R1 DOOR GIRT BAR RETAINER BROKEN. REMOVED AND REPLACED COVER ASSY PER AMM.

Part: GIRT BAR — DIRTY (R1 DOOR) · airframe 31,709 hrs · 20,882 cycles

R1 DOOR EMERGENCY EVAC SLIDE GIRT BAR STUCK. CLEANED AND LUBED GIRT BAR PER MM.

Part: TIRE — FAILED (RT MLG) · airframe 31,312 hrs · 20,609 cycles

SUPPLEMENTAL INFORMATION: DECLARED EMERGENCY. DURING TAKEOFF AT ROTATION THE RT MAIN OUTBOARD TIRE FAILED. DURING CLIMBOUT "HYD R QUANTITY LO" ALERT APPEARED ON EAD AND HYD QUANTITY SHOWED 2.6 AND THEN 0.0. COMPLIED WITH QRH, DECLARED EMERGENCY. DID AN EMERGENCY GEAR EXTENSION AND LANDED. REMOVED AND REPLACED DOWN HYDRAULIC LINE ON MLG BUNGEE CYLINDER PER MM. TRUNCATED AND QA

Part: FASTENER — SHEARED (FUSELAGE)

FASTENER, STA 1152, SHEARED. ACCOMPLISHED FASTENER PLUGGED PER EA 17-53-03498IR.

Part: STRUCTURE — CRACKED (NACELLE)

LEFT ENGINE LOWER COWLING NR 4 HINGE CUTOUT, CRACKED. ACCOMPLISHED LOWER COWLING NR 4 HINGE CUTOUT REPAIR PER B717 SRM 54-50-02.

Part: STRUCTURE — CRACKED (NACELLE)

LEFT ENGINE LOWER COWLING NR 2 HINGE CUTOUT, CRACKED. ACCOMPLISHED LOWER COWLING NR 2 HINGE CUTOUT REPAIR PER B717 SRM 54-50-02.

Part: SEAT TRACK — CORRODED (FUSELAGE)

AFT CARGO COMPARTMENT LEFT SEAT TRACK, CORROSION. ACCOMPLISHED LEFT SEAT TRACK SPLICE REPAIR PER B717 SRM 51-10-04, 53-00-00, 53-20-52 AND REF 11-1583.

Part: STRUCTURE — CRACKED (NACELLE)

LEFT ENGINE UPPER COWLING NR 2 HINGE CUTOUT, CRACKED. ACCOMPLISHED UPPER COWLING NR 2 HINGE CUTOUT REPAIR PER B717 SRM 54-50-02.

Part: ATTACH ANGLE — CRACKED (RT PYLON)

RIGHT ENGINE LOWER APRON NR 1 LATCH ANGLE, CRACKED. ACCOMPLISHED LOWER APRON NR 1 LATCH ANGLE REPLACEMENT PER B717 SRM 54-50-02 AND TRA 17-54-TR00129.

Part: SKIN — DENTED (FUSELAGE)

FUSELAGE SKIN, STA 229 TO 256, LONG L162 TO L181, DENTED. ACCOMPLISHED SKIN DOUBLER REPAIR PER B717 SRM 53-00-01 AND EA 17-53-03135IR.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR SUPPORT Z-ANGLE, STA 202, LBL 55, CORROSION. ACCOMPLISHED FLOOR SUPPORT Z-ANGLE REPLACEMENT PER B717 SRM 51-10-04, 53-00-00, 51-32-01, 51-41-02 AND 51-41-05.

Part: PLATE — CORRODED (FUSELAGE)

MAIN CABIN FLOOR COVER PLATE, STA 195 TO 210, RBL 58, CORROSION. ACCOMPLISHED FLOOR COVER PLATE REPLACEMENT PER B717 SRM 53-00-00 AND 51-40-02.

Part: SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR VENT GRILL SUPPORT, STA 210, LBL55, CORROSION. ACCOMPLISHED FLOOR VENT GRILL SUPPORT DOUBLER REPAIR PER B717 SRM 51-10-04, 53-00-00, 51-70-10 AND 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR SUPPORT WEB, STA 160 TO 200, RBL 55, CORROSION. ACCOMPLISHED FLOOR SUPPORT WEB REPLACEMENT PER B717 SRM 51-41-01 AND 51-40-08.

Part: DOOR FRAME — CRACKED (FUSELAGE)

MAIN CABIN DOOR AFT ENTRY DOOR JAMB, STA 208, LONG S15L, CRACKED. ACCOMPLISHED AFT ENTRY DOOR JAMB DOUBLER REPAIR PER B717 SRM 51-70-10.

Part: SEAT TRACK — CORRODED (FUSELAGE)

MAIN CABIN SEAT TRACK, STA 200 TO 236, RBL 22, CORROSION. ACCOMPLISHED SEAT TRACK REPLACEMENT PER B717 SRM 53-20-52, 53-20-62 AND 51-40-08.

Part: VANE — DENTED (TE FLAP)

RIGHT WING LOWER MOVEABLE FLAP VANE, DENTED. ACCOMPLISHED LOWER MOVEABLE FLAP VANE DOUBLER REPAIR PER B717 SRM 57-53-01 AND 51-70-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR SUPPORT, STA 160, LBL 22 TO LBL 25, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 53-00-00, 51-42-02 AND 51-41-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR SUPPORT, STA 148 TO 200, RBL 7, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-10-04, 53-00-00, 51-41-01 AND 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR SUPPORT, STA 200 TO 260, LBL 15, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-40-08, 51-41-01 AND 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR SUPPORT, STA 160 TO 200, RBL 44, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 53-00-00 AND 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR SUPPORT, STA 180, RBL 9 TO RBL 43, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-10-04, 53-00-00, 51-41-01 AND 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR SUPPORT STA 197, RBL 52 TO RBL 47, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-10-04 AND 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR SUPPORT, STA 200, LBL 8 TO RBL 8, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 53-00-00 AND 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR SUPPORT, STA 200, RBL 9 TO RBL 46, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-10-04 AND 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN FLOOR SUPPORT, STA 197, LBL 15 TO LBL 42, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: MANIFOLD — DISCONNECTED (FUEL SYSTEM)

DURING CLIMBOUT ON FLIGHT 981, STARTED TO GET A FUEL IMBALANCE, AT FIRST IT WAS 200 LBS, AND GRADUALLY CONTINUED TO 9400 LBS LEFT, 0 LBS RIGHT, 2350 LBS CENTER. ENGINE LEFT FUEL PRESSURE LOW LIGHT CAME ON DURING ATTEMPTED CROSSFEED, AS WELL AS RIGHT ENGINE LOW PRESSURE LIGHT DURING CROSSFEED. DIVERTED BACK TO MCO AND LANDED AT 104,800 LBS. FOUND LEFT TANK FUEL MANIFOLD DISCONNECTED. CONNECTED FUEL MANIFOLD AND PERFORMED REFUEL OF LEFT WING AND OPERATED BOTH ENGINES USING LEFT FUEL BOOST PUMPS WITH CROSSFEED OPEN. NO LEFT OR RIGHT ENGINE LOW PRESSURE LIGHTS ILLUMINATED AND NO UNWANTED FUEL TRANSFER.

Part: FRAME — DAMAGED (FUSELAGE)

EO 17-5310-2937 AFT LEFT STA 1178 CANTED FRAME INSPECTION IDENTIFIED CONFIGURATION 2 CONDITION 5. ACCOMPLISHED REPAIR TO AFT FUSELAGE FRAME CAP, CANTED STA 1178.225, LEFT SIDE IAW AIRTRAN TASK CARD 17-5310-2980.

Part: DOOR FRAME — CORRODED (FUSELAGE)

AFT CARGO DOOR JAMB CUTOUT AREA HAS CORROSION STA FROM 954 TO 994. INSTALLED AFT CARGO COMPARTMENT DOOR JAMB LOWER SPLICE REPAIR PER B717 SRM 53-20-15 REPAIR 7 FIGURE 201. SEE NR 3797, 3829 AND 2382.

Part: FRAME — DAMAGED (FUSELAGE)

EO 17-5310-2895 AFT RIGHT STA 1178 CANTED FRAME INSPECTION IDENTIFIED CONFIGURATION 2 CONDITION 5. ACCOMPLISHED REPAIR TO AFT FUSELAGE FRAME CAP, CANTED STA 1178.225, RIGHT SIDE IAW AIRTRAN TASK CARD 17-5310-2990.

Part: RELEASE MECH — MISINSTALLED (TAILCONE)

FOUND TAIL CONE RELEASE CAM ASSEMBLY AND LANYARD IMPROPERLY STOWED. PERFORMED T/C 414A, 415, 417, 418 & 419 FOR TAIL CONE OPERATIONAL CHECK & PROPER ROUTING OF TAIL CONE LANYARD. OK TO RETURN TO SERVICE.

Part: SLIDE — UNSECURE (L1 DOOR)

L1 SLIDE PACK NOT SECURE. A/C FERRIED TO ATL FOR REPLACEMENT. REMOVED AND REPLACED SLIDE PACK AS OUTLINED IN B717 AMM 25-61.

Part: POWER SUPPLY — DISCHARGED (CABIN)

EMERGENCY EXIT LIGHTS ON SEATS ROWS 1-2-3 & 10 INOP. REMOVED AND REPLACED BATTERY PACK POWER SUPPLY FOR SEAT ROWS 1-2-3 & 10 PER MM 33-51-03.

Part: CABLE — MISROUTED (TAILCONE)

TAIL CONE UNLOCK LIGHT ILLUMINATED. FOUND EXTERNAL HANDLE FOR TAIL CONE RELEASE, CABLE MIS-ROUTED IN BLOCK. REINSTALLED CABLE PER B717 AMM 53-52-01. TAIL CONE WARNING LIGHT OPERATIONALLY CHECKED GOOD.

Part: SLIDE — FAILED (R1 DOOR)

R-1 DOOR SLIDE FAILED TO DEPLOY DURING MAINT CHECK. REPLACED DOOR SLIDE ASSY.

Part: DOOR FRAME — CORRODED (FUSELAGE)

FWD CARGO DOOR JAMB HAS SEVERAL AREAS OF CORROSION BEYOND LIMITS. INSTALLED FWD CARGO DOOR LOWER JAMB PAN CORROSION SPLICE REPAIR BETWEEN STA 427.00 AND 370.00.

Part: BATTERY PACK — DISCHARGED (CABIN)

EMERGENCY LIGHT INOP ON BUSINESS CLASS AND 1ST ROW OF COACH SEAT. REPLACED EMERGENCY LIGHT BATTERY PACK B5-118 AND OPS CHECKED, REF AMM 33-51.

Part: ENGINE — STALLED (NR 1)

LT OIL PRESSURE ZERO AND XXED OUT ON DISPLAY UNIT, COMPRESSOR STALL ENGINE SHUTDOWN. REMOVED AND REPLACED NR 1 ENGINE.