N938AT

Part: MODULE — INOPERATIVE (FUEL QTY) · airframe 48,702 hrs · 35,153 cycles

DIVERTED TO MSN DUE TO FUEL QUANTITY INOPERATIVE. REPLACED ELECTRONIC MODULE. OPS CHECK NORMAL.(1301584)

Part: VALVE — BINDING · airframe 47,819 hrs · 34,370 cycles

SHIP 9561 -ATB- DUE TO CLT DUE TO SMOKE IN THE CABIN COMING FROM FWD GALLEY AREA. SMOKE DISSIPATED AND EMERGENCY WAS DECLARED. CORRECTIVE ACTION: FOUND BUFFER AIR VALVE BINDING. REPLACED SAME. OPS CHECKS GOOD.

Part: BATTERY PACK — INOPERATIVE (ZONE 200) · airframe 47,405 hrs · 34,006 cycles

EMERGENCY LIGHTS (3 EA) LOCATED AT CEILING PANEL IN FRONT OF FWD LAVATORY, EXIT SIGN AT TOP OF COW 1 AND ABOVE THE SERVICE DOOR DOES NOT OPERATE. THE POWER ASSEMBLY BATTERY PACK WAS REPLACED PER B717-200 AMM 33-51-04. TEST OK. (LP #6915838)

Part: SKIN — WORN (ZONE 100) · airframe 47,404 hrs · 34,005 cycles

WEAR ON SKIN BTW STA Y=994 L24R TO L26R (AFT EDGE CUT OUT) AT AFT CARGO DOOR. WORN SKIN BTW STA Y=994 L24R TO L26R (AFT EDGE CUT OUT) AT AFT CARGO DOOR WAS REPAIRED PER PRI 625059-14 REV 7 AND ER/A 625059-14 REV ORIGINAL SECTION I: PERMANENT REPAIR.

Part: DOUBLER — CRACKED (ZONE 100) · airframe 47,404 hrs · 34,005 cycles

CRACK FOUND ON INTERNAL DOUBLER AT STA Y=1178 CANT LONGERON 17RH AT AFT ACCESSORIES COMPARTMENT. SUMMARY OF NRC 00686: INTERNAL CAP DOUBLER AT STA Y=1178 CANT LONGERON 17RH AT AFT ACCESSORIES COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-00-00-2R PROCEDURE 1 REPAIR 1. (LP #0914552)

Part: LONGERON — CRACKED (ZONE 100) · airframe 47,404 hrs · 34,005 cycles

CRACK WAS FOUND BTW STA Y=1178 APPROX IN LONG 17R AT AFT FUSELAGE. SUMMARY OF NRC 00660: CRACK BTW STA Y=1178 APPROX IN LONG 17R AT AFT FUSELAGE WAS REPAIRED PER ERA 625404-14 REV ORIGINAL SECTION 1: PERMANENT REPAIR. ASSOCIATED ER/A 14-625404 ADDED FOR AC 9561. (LP #0908651)

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 47,404 hrs · 34,005 cycles

CORROSION OUT OF LIMITS ON COUNTERSINKS OF ACCESS PANELS: 520CB (3 HOLES), 520DB (4 HOLES), 520FT (6 HOLES), 620GB (3 HOLES), 620FT (2 HOLES), AND 620DT (3 HOLES) PER B717-200 SRM 57-10-01-2R PROCEDURE 2. SUMMARY OF NRC 00631: CORROSION LEVEL 2. ACCESS PANELS: 520DB, 520FT, 620GB, 620FT, AND 620DT WERE REPAIRED PER B717-200 SRM 57-10-01-2R REPAIR 2. ACCESS PANEL 520CB WAS REPLACED AND VERIFIED PER B717-200 IPC 57-23-01-01 AND INSTALLED UNDER AMDS 2040-0010. (LP #0908276)

Part: CARGO TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 47,404 hrs · 34,005 cycles

DUE TO CORRISION REWORK, (UT) THICKNESS MEASUREMENT WAS ACCOMPLISHED ON SIDE TIE TRACK BTW L27L TO L28L AND STA=900 LH TO STA=1022 LH AFT CARGO COMPARTMENT. WITH AN ORIGINAL THICKNESS OF 0.060IN, AND MINIMUN REMAINING THICKNESS OF 0.027IN. THE AREA REWORKED IS OUT OF LIMITS. SUMMARY OF NRC 00690: CORROSION LEVEL 2. NEW SIDE TIE TRACK WAS FABRICATED PER DGW 5936663-547 REV Y AND REPLACED PER B717-200 SRM 51-41-01-0G. (LP #0901443)

Part: SKIN — CORRODED (ZONE 300) · corrosion level 2 · airframe 47,404 hrs · 34,005 cycles

CORROSION ON BARREL NUT HOLE #28 AT HORIZONTAL STABILIZER UPPER SURFACE LH SIDE (CENTER SECTION). (EHV). SUMMARY OF NRC 00383: CORROSION LEVEL 2. BARREL NUT HOLE #28 AT HORIZONTAL STABILIZER UPPER SURFACE LH SIDE WAS REPAIRED PER PRI 624982-14 REV 1 & ER/A 624982-14 REV ORIGINAL. ASSOCIATED ER/A 14-624982 ADDED FOR AC 9561. (LP #0897224)

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 47,404 hrs · 34,005 cycles

CORROSION ON FRAME STA Y=870 L29L TO L29R. ORIGINAL THICKNESS IS 0.063IN AND MINIMUM REMAINING THICKNESS IS 0.029IN THEREFORE AREA IS OUT OF LIMITS PER B717-200 SRM 53-00-00-1A PAR 4C (2) FIG 103. SUMMARY OF NRC 00663: CORROSION LEVEL 2. FRAME STA Y=870 L29L TO L29R WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3. PERFORM VISUAL INSPECTION ON FRAME REPAIR PER B717 SRM 53-20-07 REPAIR 3, PAR 6 A TABLE 205, INITIAL 25,000 CYCLES AND REPETITIVE EVERY 6500 CYCLES. (LP #0897509)

Part: PAN — CORRODED (ZONE 100) · corrosion level 2 · airframe 47,404 hrs · 34,005 cycles

CORROSION AROUND DOOR JAMB PAN OF AFT CARGO COMPARMENT BTW L=25R/28R. SUMMARY OF NRC 00305: CORROSION LEVEL 2. DOOR JAMB PAN OF AFT CARGO COMPARMENT BTW L=25R/28R WAS REPLACED AND INSTALLED PER B717 SRM 53-20-15-2R-7 REPAIR 7. (LP #0896016)

Part: FRAME — CRACKED (ZONE 100) · airframe 47,404 hrs · 34,005 cycles

CRACK ON FRAME STA Y=465 BTW L-25R AND L-27R AT FWD CARGO COMPARTMENT. (CCD). SUMMARY OF NRC 00149: CRACK ON FRAME STA Y=465 BTW L-25R AND L-27R AT FWD CARGO COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-20 -07-2R PROCEDURE 3 REPAIR 3. PERFORM VISUAL INITIAL INSPECTION AT 25,000 CYCLES AND PERFORM REPETITIVE INSPECTION EVERY 6,500 CYCLES PER B717-200 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3 TABLE 205. THIS ENTRY IS TO CHANGE LIMIT TYPES; SUMMARY OF NRC 00149: CRACK ON FRAME STA Y=465 BTW L-25R AND L-27R AT FWD CARGO COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3. PERFORM VISUAL INITIAL INSPECTION AT 25,000 CYCLES AND PERFORM REPETITIVE INSPECTION EVERY 6,500 CYCLES PER B717-200 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3 TABLE 205. (LP #0893468)

Part: LONGERON — CORRODED (ZONE 100) · corrosion level 2 · airframe 47,404 hrs · 34,005 cycles

CORROSION OUT LIMITS, IN REFERENCE TO NRC 00163: CORROSION ON LONGERON BTW STA Y=956 TO STA Y=964 L30 AT AFT CARGO COMPARTMENT WITH ORIGINAL THICKNESS IS 0.125IN AND MINIMUM REMAINING THICKNESS IS 0.055IN, THEREFORE AREA IS OUT OF LIMITS PER B717-200 SRM 53-00-00-1A PAR. 4C (2) FIG. 103. SUMMARY OF NRC 00656: CORROSION LEVEL 2. LONGERON BTW STA Y=956 TO STA Y=964 L30 AT AFT CARGO COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-20-05-2R PROCEDURE 1 REPAIR 1 FIGURE 201. (LP #0893400)

Part: ANGLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 47,404 hrs · 34,005 cycles

CORROSION ON ANGLE OF AFT CARGO DOOR JAMB AREA BTW STA Y=956 AND LONGERON 27R AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00300: CORROSION LEVEL 2. ANGLE OF AFT CARGO DOOR JAMB AREA BTW STA Y=956 AND LONGERON 27R AT AFT CARGO COMPARTMENT WAS REPLACED AND INSTALLED PER B717-200 SRM 53-20-15-2R REPAIR 7, 51-41-06-0G PAR 7, AND 51-41-02-0G. (LP #0891909)

Part: STRAP — CRACKED (ZONE 200) · airframe 47,404 hrs · 34,005 cycles

CRACKED STRAP STA Y 1178 CANT UPPER CHORD, PROJECTION LONG 2 RH AT AFT ACCESORY COMPARTMENT. INITIAL INSPECTION: PERFORM DECAL CONDITION INSPECTION EVERY C-CHECK PER TOPP MANUAL 30-10-70 PAR I PAGE 14. LOG PAGE FOR CRACKED STRAP STA Y 1178 CANT UPPER CHORD, PROJECTION LONG 2 RH AT AFT ACCESORY COMPARTMENT DEFERRED TO DECAL CONDITION MONITOR PER TOPP 30-10-70. TO BE INSPECTED AT THE APPROPRIATE CHECK INTERVAL. (LP #0890786)

Part: SKIN — CRACKED (ZONE 200) · airframe 47,404 hrs · 34,005 cycles

CRACK ON SKIN AT STA Y=1076 AND LONG 14R ON AFT FUSELAGE. SUMMARY OF NRC 00035: CRACK ON SKIN AT STA Y=1076 AND LONG 14R ON AFT FUSELAGE WAS REPAIRED PER PRI 624820-14 REV 3 AND ER/A 624820-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. PERFORM GVI EVERY 24 MONTHS AFTER ACCOMPLISHED OF SECTION I: PERMANENT REPAIR PER ER/A 624820-14 REV ORIGINAL SECTION II. THIS ACTIVITY IS MONITORED UNDER LOGPAGE 0880701. ASSOCIATED ER/A 14-624820 ADDED FOR AC 9561. (LP #0883195)

Part: SKIN — CRACKED (ZONE 200) · airframe 47,404 hrs · 34,005 cycles

CRACK EVIDENCE ON FUSELAGE SKIN LOCATED AT Y=1087 AND L-14L. SUMMARY OF NRC 00444: CRACK EVIDENCE ON FUSELAGE SKIN LOCATED AT Y=1087 AND L-14L WAS REPAIRED PER PRI 625028-14 REV 1 AND ER/A 625028-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. PERFORM GENERAL VISUAL INSPECTION (DVI) PER NDTSP MANUAL PART 9, 09-00-06 TO MAKE SURE THE SECTION I REPAIR IS DAMAGE FREE PER ERA 625028-14 REV ORIGINAL SECTION II: REPETITIVE INSPECTIONS STEP 1 AND 2. ASSOCIATED ER/A 14-625028 ADDED FOR AC 9561. (LP #0883069)

Part: SKIN — DENTED (ZONE 500 FLAP) · airframe 47,404 hrs · 34,005 cycles

DENT ON UPPER MID AREA NEAR L/E AT LH WING FWD MOVABLE VANE. SUMMARY OF NRC 00554: AREA DAMAGE WAS REPAIRED ON UPPER MID AREA NEAR L/E AT LH WING FWD MOVABLE VANE PER B717-200 SRM 57-53-01-2R PROCEDURE 1 REPAIR 1 PAR 4. (LP #0873498)

Part: PAN — CRACKED (ZONE 800) · airframe 47,404 hrs · 34,005 cycles

CRACKED PAN ON AFT EDGE OF AFT CARGO COMPARMENT DOOR BTW BEAM 1-2. SUMMARY OF NRC 00096: PAN ON AFT EDGE OF AFT CARGO COMPARMENT DOOR BTW BEAM 1-2 WAS REPAIRED PER B717-200 SRM 52-30-02-2R REPAIR 8 FIGURE 202, 51-41-02-0G PROCEDURE GENERAL, AND 51-41-05-0G. (LP #0871872)

Part: PAN — CRACKED (ZONE 800) · airframe 47,404 hrs · 34,005 cycles

A CRACK WAS FOUND ON THE #2 INNER PAN AT AFT EDGE OF THE FWD CARGO COMPARMENT DOOR. SUMMARY OF NRC 00598: INNER PAN ON AFT EDGE BEAM #2 AT FWD CARGO COMPARTMENT DOOR WAS REPAIRED PER B717-200 SRM 52-30-02-2R-3 PROCEDURE 3 REPAIR 3. (LP #0871599)

Part: BEAM — CRACKED (ZONE 800) · airframe 47,404 hrs · 34,005 cycles

CRACK ON BEAM #8 AFT SIDE AT PASSENGER DOOR. SUMMARY OF NRC 00083: BEAM #8 AFT SIDE AT PASSENGER DOOR WAS REPAIRED PER B717-200 SRM 52-10-02-2R REPAIR 14 PAR 6. (LP #0871639)

Part: DOOR FRAME — CRACKED (ZONE 200) · airframe 47,404 hrs · 34,005 cycles

CRACK ON BEAM #1 AFT EDGE AT PASSENGER ENTRANCE DOOR (L1). SUMMARY OF NRC 00290: BEAM #1 AFT EDGE AT PASSENGER ENTRANCE DOOR WAS REPAIRED PER B717-200 SRM 52-10-02-2R PROCEDURE 7 REPAIR 7. (LP #0871550)

Part: FRAME — CRACKED (ZONE 200) · airframe 47,404 hrs · 34,005 cycles

CRACK OF 0.093 IN LENGTH WAS FOUND ON THE UPPER RADIUS OF FRAME TAB ON THE OVERWING FRAME AT STA Y=696.000 RH. (IN REF CARD 5310-01436-04D, JOB #090-0004, STEP 10). SUMMARY OF NRC 00281: FRAME TAB ON THE OVERWING FRAME AT STA Y= 696.000 RH WAS REPAIRED PER CARD 5310-01436-02B. ASSOCIATED AA 5310-01436 ADDED FOR AC 9561. (LP #0868948)

Part: CUSP WEB — CRACKED (ZONE 200) · airframe 47,404 hrs · 34,005 cycles

CRACK ON CUSP WEB BTW STA Y=655 TO STA Y=670 LH SIDE AT CABIN PASSENGER. SUMMARY OF NRC 00338: CRACK ON CUSP WEB BTW STA Y=655 TO STA Y=670 LH SIDE AT CABIN PASSENGER WAS REPAIRED PER B717-200 SRM 53- 00-55-2R PROCEDURE 4 REPAIR 4 FIGURE 203. (LP #0868343)

Part: FRAME — CRACKED (ZONE 100) · airframe 47,404 hrs · 34,005 cycles

CRACK ON FRAME STA Y=1037 LONG 17L AT PASSENGER CABIN. SUMMARY OF NRC 00360: CRACK ON FRAME STA Y=1037 LONG 17L AT PASSENGER CABIN WAS REPAIRED PER B717-200 53-20-07-2R REPAIR 4. (LP #0866910)

Part: CUSP WEB — DAMAGED (ZONE 200) · airframe 47,404 hrs · 34,005 cycles

ELONGATED HOLE ON CUSP WEB LH BTW STA Y=696 X=56 AT CABIN PASSENGER. SUMMARY OF NRC 00339: ELONGATED HOLE ON CUSP WEB LH BTW STA Y=696 X=56 AT CABIN PASSENGER WAS REPAIRED PER B717-200 SRM 53-00-55-2R-4 REP 4. (LP #0866724)

Part: CUSP WEB — CRACKED (ZONE 200) · airframe 47,404 hrs · 34,005 cycles

CRACK ON CUSP WEB RH SIDE BTW STA Y=674 X-56 AT CABIN PASSENGER. SUMMARY OF NRC 00330: CRACK ON CUSP WEB RH SIDE BTW STA Y=674 X-56 AT CABIN PASSENGER WAS REPAIRED PER B717-200 SRM 53-00-55-2R-4, PAR 5, FIG 223, AND FIG 226. (LP #0864855)

Part: FRAME — CRACKED (ZONE 100) · airframe 47,404 hrs · 34,005 cycles

CRACK ON FRAME STA Y=1037 LONG 17R AT PASSENGER CABIN. SUMMARY OF NRC 00361: FRAME STA Y=1037 LONG 17R AT PASSENGER CABIN WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 4 REPAIR 4. (LP #0861190)

Part: LONGERON — CRACKED (ZONE 200) · airframe 47,404 hrs · 34,005 cycles

CRACK ON INTERNAL AREA OF LONGERON 7R, 8R, 5R, STA Y=1022 AT PASSENGER CABIN. SUMMARY OF NRC 00363: LONGERON 8R, 5R, STA Y=1022 AT PASSENGER CABIN WERE REPAIRED PER B717-200 SRM 53-00-05-2R REPAIR 2 AND LONGERON 7R NO DAMAGE WAS FOUND PER DC-MD/BOEING NDTSPM PART 6, 06-10-01.001. PERFORM DECAL INSPECTION CONDITION EVERY "C" CHECK PER TOPP 30-10-70 PAGE 14 PAR I. LOG PAGE DEFERRED TO DECAL CONDITION MONITOR PER TOPP 30-10-70 TO BE INSPECTED AT THE APPROPRIATE CHECK INTERVAL. (LP #0858453)

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 47,404 hrs · 34,005 cycles

CORROSION ON RH SEAT TRACK STA Y=236-238 -X=22 AT PAX CABIN FLOOR STRUCTURE. SUMMARY OF NRC 00398: CORROSION LEVEL 2. CORROSION ON RH SEAT TRACK STA Y=236-238 -X=22 AT PAX CABIN FLOOR STRUCTURE WAS REPAIRED PER B717-200 SRM 53-20-52-2R. PROC 1, REPAIR 1. (LP #0858265)

Part: LONGERON — CRACKED (ZONE 200) · airframe 47,404 hrs · 34,005 cycles

CRACK ON INTERNAL AREA OF LONGERON 5L STA Y=1022 AT PASSENGER CABIN. SUMMARY OF NRC 00432: CRACK ON INTERNAL AREA OF LONGERON 5L STA Y=1022 AT PASSENGER CABIN WAS REPAIRED PER B717-200 SRM 53-00-05-2R PROCEDURE 2 REPAIR 2. (LP #0856135)

Part: COVER — MISSING (EMERGENCY LIGHT) · airframe 45,492 hrs · 32,303 cycles

THE CABIN CEILING EMERGENCY STANDBY LIGHT LENS COVER IS MISSING AT SEAT ROW 3. MAINTENANCE FORWARDED IT TO NEF 33-21-02. CABIN LIGHT LENS MISSING SEAT ROW 3. (LP #0309494)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 44,934 hrs · 31,814 cycles

THE EMERGENCY LIGHTS FROM ROW 1 TO ROW 13 CEILING LIGHTS ARE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY BATTERY PACK AT B5-227 PER B717 AMM 33-51. OPERATIONAL CHECK WAS GOOD. THE AIRCRAFT IS OK FOR SERVICE. (LP #5006827)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 44,463 hrs · 31,433 cycles

THE LOWER EMERGENCY LIGHTS ARE INOPERATIVE AT THE AFT EMERGENCY EXIT. MAINTENANCE REPLACED THE BATTERY (B5-119) PER B717 AMM 33-51-04. ALL EMERGENCY LIGHT OPERATIONAL CHECKS ARE GOOD. THE AIRCRAFT IS OK FOR SERVICE. (LP #4620011)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 43,770 hrs · 30,844 cycles

ON A SERVICE CHECK, THE SIDE PAX DOOR EMERGENCY EXIT LIGHT AND SERVICE DOOR SIDE EMERGENCY EXIT LIGHT WERE FOUND TO BE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT POWER SUPPLY B5-118 AND THE BATTERY ASSEMBLY IAW B717 AMM 33-51. (LP #4798653)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 43,546 hrs · 30,647 cycles

MAINTENANCE FOUND SEVERAL EMERGENCY LIGHTS IN THE CABIN AT STA 715-737R TO BE INOPERATIVE. THE EMERGENCY LIGHTS BATTERY SUPPLY (B5-230) WAS REPLACED. OPERATIONAL CHECK WAS GOOD. (LP #4774723)

Part: NONE — NONE · airframe 41,886 hrs · 29,206 cycles

AIRCRAFT 9561, EXIT LOCATOR SIGN FWD/AFT FACING DOES NOT ILLUMINATE. LIGHTED SIGN IS LOCATED ON CEILING OF CABIN BETWEEN OVER-WING EMERGENCY EXITS. CORECTIVE ACTION: REPLACED EMERGENCY LIGHTS BATTERY ASSY (LP 9147282)

Part: NONE — NONE · airframe 40,967 hrs · 28,359 cycles

EMERGENCY LIGHTS AT LOWER AFT OVERWING DOOR ARE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT BATTERY PACK PER B717 AMM 33-51. OPERATIONAL CHECK WAS GOOD. (LP #7883681)

Part: NONE — NONE · airframe 40,536 hrs · 27,975 cycles

HIDDEN DAMAGE DURING THE DOUBLER REMOVE PROCESS. WEB DAMAGE WAS FOUND ON LEFT HAND SIDE, LOCATED ON INTECECTION STA 674 AND STGR 18LH. SUMMARY OF NRC 00175: WEB ON STA 674 LH WAS REPAIRED PER B717 SRM 53-00-55-2R PROCEDURE 4. (LP #2071146)

Part: NONE — NONE · airframe 40,367 hrs · 27,817 cycles

THERE ARE MULTIPLE CABIN EMERGENCY ESCAPE LIGHTS INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT BATTERY PACK B5-121 IAW B717 AMM 33-51. OPERATIONAL CHECK WAS NORMAL. THE AIRCRAFT IS OK FOR SERVICE. (LP #8141196)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 39,372 hrs · 26,904 cycles

DURING A SERVICE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTS AT CEILING PANELS 11, 12, AND 13 WERE INOPERATIVE. THE BATTERY PACK, B5-231, WAS REPLACED, PER B717 WDM 33-51-12. OPERATIONAL CHECK WAS SATISFACTORY. THE AIRCRAFT IS OK FOR SERVICE.

Part: PUMP — MALFUNCTIONED (RT ENGINE) · airframe 38,365 hrs · 26,000 cycles

ACCORDING TO THE AOS REPORT, EMERGENCY DECLARED - HYD R TEMP HI MESSAGE AFTER T/O. R&R RT ENG EDP PER B717 AMM 29-11. OPS AND LEAK CHK OK. ODI PAPERWORK C/W. PUMP, HYD, ENG 95-2911-9-0001 S/N 00019. (LP6906554)

Part: SKIN — DELAMINATED (RT WING SPOILER)

NON ROUTINE CHECK, UPPER AND LOWER SKINS OF THE RT WING SPOILER WAS DELAMINATED.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 44,957 hrs · 31,841 cycles

DENT INSPECTION RHS AFT MOVABLE VANE, UPPER SKIN - QTY 6. #5) APPROX 25" FROM O/B EDGE & 4.5" FROM T/E. 5) DENT DIMENSIONS WIDTH 1.3" X DEPTH 0.024" APPROX 25" FROM O/B EDGE & 4.5" FROM T/E. IAW B717 SRM 57-53-01 AD 1 ACCOMPLISH DVI AND TAP TEST FOR POSSIBLE DISBOND AT EVERY C CHECK OR 3,000 CYCLES. DENT ORIGINALLY DOCUMENTED, INSPECTED, MEASURED BY AIRTRAN/SWA DECAL COND MONITOR. REPAIRED AT C CHECK INTERVALS. DENT LAST INSPECTED 16,658 CYCLES. C/W DVI AND TAP TEST IAW B717 SRM 57-53-01 AD1. NO FURTHER DAMAGE FOUND. TAP-TEST ACCOMPLISHED ON DENTED AREA 27DEC21, DENT #5 WAS FOUND DISBOND OF LENGTH: 1.000IN X WIDTH:0.750IN, AND THE OTHERS DENTS NO DISBONDS WERE FOUND PER DC-MD/BOEING NDT SPM PART 5, 05-10-02.001. RH AFT MOVABLE VANE UPPER SKIN APPROX 25.00IN FROM O/B EDGE AND 4.500 IN FROM T/E WAS REPAIRED PER B717 SRM 51-70-02-0G. PROCEDURE GENERAL OF REFERENCE OF B717 SRM 57-53-01-2R-1 PAR 4 AND WAS ATTENDED WITH NRC 00156. (LP #1774883)

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,834 hrs · 25,587 cycles

FUSELAGE SKIN CORRODED INTERNALLY AT CUTOUT FOR DRAIN MAST IN FLOOR OF E/E COMPARTMENT. EXTERNAL FILLET SEALER AROUND MAST SHOWS CORROSION PROTRUSION ALSO. NRC 001-0223:2570-2002/002 00076: (CORROSION LEVEL 2), REPLACED DOUBLER REF BOEING DWG #9923686. (LP #1407393)

Part: COVER — MISSING (CABIN) · airframe 37,595 hrs · 25,397 cycles

THE CABIN CEILING EMERGENCY EXIT LIGHT IS MISSING AT ROW 22AB. FORWARDED TO MEL 33-51-01A AND THE PLACARD WAS INSTALLED. 06NOV19 LGA INSTALLED EMERGENCY EXIT LIGHT COVER AT ROW 22AB AS PER B717 AMM 33-51. CHECKS OK. MEL AND PLACARD REMOVED. (LP #5955947)

Part: DOOR — MISSING (GROUND AIR) · airframe 37,482 hrs · 25,312 cycles

PNEUMATIC AIR GROUND CONNECT DOOR MISSING. REPLACED BROKEN HINGE ON GROUND AIR DOOR PER AMM 52-47, REINSTALLED DOOR. (LP5416466)

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 33,679 hrs · 22,604 cycles

LEFT AND RIGHT OVERWING EMERGENCY EXIT LIGHTS ARE INOPERATIVE. MAINTENANCE REPLACED THE OVERWING EMERGENCY EXIT LIGHT POWER SUPPLY IAW AMM 33-51. OPS CHECKED GOOD.

Part: FASTENER — SHEARED (SKIN) · airframe 33,149 hrs · 22,253 cycles

SHEARED FASTENER ON LONGERON 2L, BS 1153 AT AFT ACCESSORY. REPAIRED IAW ER/A 566637-14, REV ORIGINAL, AND ETI-17-18-044 REV 1.

Part: TAB — DENTED (RUDDER) · airframe 33,205 hrs · 22,297 cycles

THE RUDER CONTROL TAB WAS DENTED ON TRAILING EDGE UPPER SECTION. THE RUDDER CONTROL TAB TRAILING EDGE UPPER SECTION WAS REPAIRED PER SRM 51-70-02-0G.

Part: BEAM — CRACKED (FUSELAGE) · airframe 33,149 hrs · 22,253 cycles

CRACKED BEAM 1 STA Y=170 AT FWD SERVICE DOOR. BEAM 1 WAS REPLACED PER SRM 51-41-02-0G AND DWG 9911579 REV L.

Part: ACCESS PANEL — CRACKED (RT WING) · airframe 33,149 hrs · 22,253 cycles

A CRACK WAS CONFIRMED IAW NDTSPM PART 6, 06-10-01.001 ON ACCESS PANEL 620EB, RT WING. THE ACCESS PANEL WAS REPLACED IAW AMM 28-00-00. A LEAK CHECK WAS PERFORMED IAW AMM 28-00-00. NO LEAKS FOUND.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA AT FUEL ACCESS PLATES 520GB. CORROSION LEVEL 2, DUE TO EXCESSIVE DAMAGE BY CORROSION ON FUEL ACCESS PLATE 520GB WAS REPLACED PER SRM 57-10-01 REPAIR 2 PAR 5 CONDITION II (A AND B) AND VERIFIED PER IPC 57-23-01-01 ITEM 345J.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA AT FUEL ACCESS PLATES 520CB. CORROSION LEVEL 2, DUE TO EXCESSIVE DAMAGE BY CORROSION FUEL ACCESS PLATE 520CB WAS REPLACED AND VERIFIED PER IPC 57-23-01-01 ITEM 465J.

Part: SKIN — CRACKED (BS 1087) · airframe 33,149 hrs · 22,253 cycles

CRACKED SKIN, BS 1087, BETWEEN LONGERONS 13 AND 14R. REPAIRED THE SKIN IAW ER/A 566384-14, REV ORIGINAL, AND ETI-17-014, REV 1.

Part: SKIN — CORRODED (FUEL TANK) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON CENTER FUEL TANK LOWER SKIN STA Y=747 X=-23 AT RT WHEEL WELL. CORROSION LEVEL 2, CORROSION WAS REWORKED PER ER/A 566336-14AD REV ORIGINAL AND ETI-17-18-018 REV 1. PER ER/A 566336-14AD REV ORIGINAL SECTION DTE.

Part: FRAME — CRACKED (FUSELAGE) · airframe 33,149 hrs · 22,253 cycles

CRACK ON FRAME STA Y=1022 LONG 7R AT PASSENGER CABIN. DAMAGE AREA WAS REPAIRED PER ER/A 566385-14 REV ORIGINAL AND ETI-17-18-015 REV ORIGINAL. HFEC INSPECTION WAS ACCOMPLISHED ON FRAME STA Y=1022 LONG 7R AT PASSENGER CABIN AND 2EA CRACKS WERE DELIMITED WITH FOLLOWING DIMENSION: 1)LENGTH=2IN; 2) LENGTH=0.500IN PER NDT SPM 06-10-01.001.

Part: FITTING — CRACKED (FUSELAGE) · airframe 33,149 hrs · 22,253 cycles

CRACKED INTERNAL FITTING STA Y=994 BEAM 4, ALSO INTERNAL FITTING Y=954 BEAM 2 AT AFT CARGO COMPARTMENT DOOR. FITTINGS STA Y=994 AND Y=954 WERE REPLACED PER SRM 51-41-01-0G, 51-41-05-0G, AND DWG 9957665 REV R.

Part: FLOOR SUPPORT — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON THE FLOOR SUPPORT. THE FLOOR SUPPORT WAS REPLACED IAW DWG #9957828, REV Y.

Part: PAN — CORRODED (CARGO DOORWAY) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON LOWER PAN OF THE LOWER DOOR FRAME IN THE AFT CARGO BAY, THE PAN WAS REPLACED IAW SRM 51-41-02-0G, 51-41-05-0G, AND SRM 53-20-15-2R-7.

Part: BEAM — CRACKED (CARGO DOOR) · airframe 33,149 hrs · 22,253 cycles

CRACK ON INNER PAN IN BEAM NR 1 STA Y=427 AT FWD CARGO COMPARTMENT DOOR (PTAS). INNER PAN IN BEAM NR 1 STA Y=427 WAS REPAIRED PER SRM 52-30-02-2R-1 FIG 201.

Part: MEMBRANE — CRACKED (FUSELAGE) · airframe 33,149 hrs · 22,253 cycles

CRACK ON MEMBRANE STA Y=674 X=-54 AT PASSENGER CABIN. DAMAGE AREA WAS REPAIRED PER SRM 53-00-55-2R FIG 223 (ET) HFEC INSPECTION WAS ACCOMPLISHED ON MEMBRANE STA Y=674 X=-54 AT PASSENGER CABIN AND NO CRACKS WERE FOUND AFTER TRIM OUT PER NDT SPM 06-10-01.001. EQUIPMENT PHASEC 3D C/N 1381 EXP 20DEC18.

Part: BEAM — CRACKED (CARGO DOOR) · airframe 33,149 hrs · 22,253 cycles

CRACK ON INNER PAN IN BEAM NR 3 STA Y=370 AT FWD CARGO COMPARTMENT DOOR (PTAS). INNER PAN IN BEAM NR 3 STA Y=370 WAS REPAIRED PER SRM 52-30-02-2R-1 FIG 201.

Part: BEAM — CRACKED (CARGO DOOR) · airframe 33,149 hrs · 22,253 cycles

CRACK ON INNER PAN IN BEAM NR 1 STA Y=370 AT FWD CARGO COMPARTMENT DOOR (PTAS). PAN IN BEAM NR 1 STA Y=370 WAS REPAIRED PER SRM 52-30-02-2R-1 FIG 201.

Part: TEE FITTING — CRACKED (CARGO DOOR) · airframe 33,149 hrs · 22,253 cycles

CRACK ON INTERNAL FITTING "T" STA Y=389 (LOWER EDGE) AT FWD CARGO COMPARTMENT DOOR (PTAS). FITTING "T" STA Y=389 WAS REPLACED PER SRM 51-41-01, 51-41-02, 51-41-05, AND DWG 3926046 REV D.

Part: BEAM — CRACKED (CARGO DOOR) · airframe 33,149 hrs · 22,253 cycles

CRACK ON INNER PAN IN BEAM NR 5 STA Y=427 AT FWD CARGO COMPARTMENT DOOR (PTAS). PAN IN BEAM NR 5 STA Y=427 WAS REPAIRED PER SRM 52-30-02-2R-1 FIG 201.

Part: BEAM — CRACKED (CARGO DOOR) · airframe 33,149 hrs · 22,253 cycles

CRACK ON INNER PAN IN BEAM NR 5 STA Y=370 AT FWD CARGO COMPARTMENT DOOR (PTAS). PAN IN BEAM NR 5 STA Y=370 WAS REPAIRED PER SRM 52-30-02-2R-1 FIG 201.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 33,149 hrs · 22,253 cycles

CRACKED CHANNELS ON FLOOR PANELS #221XF, 221TF, 222AFF, AND 222AJF AT PAX CABIN (CPAX). NRC 00438: CRACKED CHANNELS ON FLOOR PANELS #221XF, 221TF, 222AFF AT PAX CABIN WERE REPAIRED PER B717 SRM 53-00-00-1A FIG 101. AND CRACKED CHANNEL ON FLOOR PANEL 222AJF WAS REPAIRED PER B-717 SRM 53-20-50-2R-5. (ET)(HFEC) WAS ACCOMPLISHED AT CHANNELS ON FLOOR PANELS #221XF, 221TF, 22AJF, AND 222AFF AT PAX CABIN. AFTER DAMAGE REMOVED AND NO CRACKS WERE FOUND PER DC MD NDT SPM PART 6. 06-10-01.001 EQUIP. (PHASEC 3D N/C 1381 EXP. 20DEC18). (LP #0443358)

Part: DOOR FRAME — CRACKED (NLG WW) · airframe 33,149 hrs · 22,253 cycles

CRACKS FOUND ON THE LT & RT DOOR FRAME BS 46 AT NLG WHEEL WELL. THE DOOR FRAME WAS REPAIRED IAW SRM 53-10-14 R2, FIG 201. HFEC INSPECTION WAS ACCOMPLISHED, AND NO CRACKS WERE FOUND AFTER CUT OUT IAW NDT SPM 06-10-01.001.

Part: CUSP WEB — CORRODED (BS 487-491) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON CUSP WEB BS 487 - 491, BETWEEN RBL 54 TO RBL 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-00-55-2R, FIG 215.

Part: FITTING — CRACKED (FUSELAGE) · airframe 33,149 hrs · 22,253 cycles

CRACK FRAME CLIPS BTW LONG 13L AND 14L STA Y=1022 AND LONG 13R TO 14R. FRAME CLIP REPLACED PER DWG 9912243 REV HG. HFEC INSPECTION WAS ACCOMPLISHED ON FRAME CLIPS BTW LONG 13L AND 14L AND LONG 13R TO 14R STA Y=1022. CRACK OF 0.375" LENGTH ON FRAME CLIP BTW LONG 13R TO 14R. ON FRAME CLIP BTW LONG 13L AND 14L NO CRACKS WERE FOUND PER NDT SPM 06-10-01.001.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA AT FUEL ACCESS PLATES 620CT. CORROSION LEVEL 2, FUEL ACCESS PLATE 620CT WAS REPLACED AND VERIFIED PER IPC 57-22-01. INSTALLATION IS ATTENDED WITH CARD 2040-0012.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 33,149 hrs · 22,253 cycles

CRACKED INTERCOSTAL IN X=O BTW STA Y=1002-1022 AT PAX CABIN. INTERCOSTAL IN X=O BTW STA Y=1002-1022 AT PAX CABIN WAS REPLACED PER SRM 51-41-02-0G AND SRM 51-41-05-0G.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA AT FUEL ACCESS PLATES 520CT. CORROSION LEVEL 2, FUEL ACCESS PLATE 520CT WAS REPLACED AND VERIFIED PER IPC 57-22-01. INSTALLATION IS ATTENDED WITH CARD 2040-0010.

Part: FLOOR PANEL — BROKEN (COCKPIT) · airframe 33,149 hrs · 22,253 cycles

BROKEN FLOOR PANEL NR 211ANF OF COCKPIT. FLOOR PANEL 211ANF WAS FABRICATED, REPLACED. AND IDENTIFIED PER SRM 53-20-50-2R PROCEDURE 3. AND WAS INSTALLED WITH THE CARD JIC 2040-0058.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA AT FUEL ACCESS PLATES 620CB. CORROSION LEVEL 2, FUEL ACCESS PLATE 620CB WAS REPLACED AND VERIFIED PER IPC 57-23-01. INSTALLATION IS ATTENDED WITH CARD 2040-0012.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA AT FUEL ACCESS PLATES 520DT. CORROSION LEVEL 2, FUEL ACCESS PLATE 520DT WAS REPLACED AND VERIFIED PER IPC 57-23-01. INSTALLATION IS ATTENDED WITH CARD 2040-0010.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 33,149 hrs · 22,253 cycles

PUNCTURED AND BROKEN ON FLOOR PANELS 211AQF, 211ALF, 221AF, 221BF, 221CF, 221EF, 221JF, AND 222PF AT PAX CABIN / COCKPIT. NRC 00473: FERRULES DAMAGES ON FLOOR PANEL 221EF, 222PF, 221BF, 221AF, AND 221JF WERE REPLACED PER B-717 SRM 53-20-50-2R PROCEDURE 3. FLOOR PANEL 221CF WAS ATTENDED WITH NRC 00472. FLOOR PANEL #211ALF WAS FABRICATED, REPLACED, AND IDENTIFIED PER B-717 SRM 53-20-50-2R-3. FLOOR PANEL 211AQF WAS CLEANED PER P.S. 900-1-2-2 NO. 2 AND NO DAMAGE WAS FOUND. (LP #0440260)

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA AT FUEL ACCESS PLATES 620DT. CORROSION LEVEL 2, FUEL ACCESS PLATE 620DT WAS REPLACED AND VERIFIED PER IPC 57-23-01. INSTALLATION IS ATTENDED WITH CARD 2040-0012.

Part: FLOORBEAM — CORRODED (BS 200) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON THE FLOORBEAM ANGLE BS 200 BETWEEN RBL 22 TO 44 AND BTW RBL 44 TO 56. THE FLOORBEAM ANGLE WAS REPLACED IAW SRM 51-41-02-0G, AND 51-41-05-0G.

Part: RIB — CRACKED (LE SLAT) · airframe 33,149 hrs · 22,253 cycles

CRACK ON SLAT NR 5 CORNER EXTERNAL LOWER SIDE STA XW 536.861 APPROX AT LT WING. CRACKED RIB ON SLAT NR 5 WAS REPLACED PER SRM 51-41-02 AND 51-41-08.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,149 hrs · 22,253 cycles

CRACKED FORMER LT/RT SIDE STA Y=694 AT CANTED KEEL INTERNAL STRUCTURE. FORMER LT/RT SIDE STA Y=694 AT CANTED KEEL INTERNAL STRUCTURE WAS REPAIRED PER SRM 51-70-11 REPAIR 1.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,149 hrs · 22,253 cycles

CRACKED FORMER LT/RT SIDE STA Y=679 AT CANTED KEEL INTERNAL STRUCTURE. FORMER LT/RT SIDE STA Y=679 AT CANTED KEEL INTERNAL STRUCTURE WAS REPAIRED PER SRM 51-70-11 REPAIR 1.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA AT FUEL ACCESS PANEL 520HB. THE ACCESS PANEL WAS REPAIRED IAW SRM 57-10-01, REPAIR 2, PAR. 5, CONDITION II.

Part: FORMER — CRACKED (FUSELAGE) · airframe 33,149 hrs · 22,253 cycles

CRACKED FORMER RT SIDE STA Y=715 AT CANTED KEEL INTERNAL STRUCTURE. FORMER RT SIDE STA Y=715 AT CANTED KEEL INTERNAL STRUCTURE WAS REPAIRED PER SRM 51-70-11 REPAIR 1.

Part: RETAINER — WORN (CARGO BAY) · airframe 33,149 hrs · 22,253 cycles

WEAR ON LOWER RETAINER (FWD AND AFT SECTION) AT FWD CARGO DOOR BARRIER. LOWER RETAINER FWD AND AFT SECTION WAS REPAIRED PER ER/A NR 559579-14MA REV ORIGINAL.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA AT FUEL ACCESS PLATES 520DB. CORROSION LEVEL 2, FUEL ACCESS PLATE 520DB WAS REPLACED FOR NEW ACCESS PLATE PER SRM 57-10-01 REPAIR 2 PAR 5.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA AT FUEL ACCESS PLATES 520EB. CORROSION LEVEL 2, DUE TO EXCESSIVE DAMAGE BY CORROSION ON COUNTERSINK AREAS, ACCESS PLATE 520EB WAS REPAIRED PER SRM 57-10-01 REPAIR 2 PAR 5 CONDITION II.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON COUNTERSINK HOLES AND SETTLEMENT AREA AT FUEL ACCESS PLATES 620AT. CORROSION LEVEL 2, FUEL ACCESS PLATE 620AT WAS REPLACED FOR NEW ACCESS PLATE PER SRM 57-10-01 REPAIR 2 PAR 5.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON CUSP WEB FROM STA Y=449-457 BTW X=-54 TO X=-60 AT PAX CABIN IN REF NRC 00324 (5300-2020). CORROSION LEVEL 2, CUSP WEB FROM STA Y=449-457 BTW X=-54 TO X=-60 AT PAX CABIN WAS REPAIRED PER SRM 53-00-55-2R.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON CUSP WEB FROM STA Y=515-519 BTW X=-54 TO X=-60 AT PAX CABIN IN REF NRC 00325 (5300-2020). CORROSION LEVEL 2, CUSP WEB FROM STA Y=515-519 BTW X=-54 TO X=-60 AT PAX CABIN WAS REPAIRED PER SRM 53-00-55-2R.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON CUSP WEB FROM STA Y=467-475 BTW X=-54 TO X=-60 AT PAX CABIN IN REF NRC 00324 (5300-2020). CORROSION LEVEL 2, CORROSION ON CUSP WEB FROM STA Y=467-475 BTW X=-54 TO X=-60 AT PAX CABIN WAS REPAIRED PER SRM 53-00-55-2R.

Part: CUSP WEB — CORRODED (BS 160-200) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORRODED CUSP WEB RBL 43 AND 54, BS 160 - 200. THE CUSP WEB WAS REPAIRED IAW SRM 53-00-00-2R-2.

Part: DIAPHRAGM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON DIAPHRAGM BTW STA Y=200-205 AND BTW X=-40 TO X=-50 AT PAX CABIN IN REF NRTC 00316 (5300-2010). CORROSION LEVEL 2, DIAPHRAGM BTW STA Y=200-205 AND BTW X=-40 TO X=-50 AT PAX CABIN WAS REPAIRED PER SRM 53-00-00-2R FIG 201.

Part: FLOORBEAM — CORRODED (BS 198) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON FLOORBEAM BS 198 BTW X=16 TO X=44 . REPLACED PER B717 SRM 51-41-02-0G.

Part: DOOR FRAME — CORRODED (BS 200-202) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION WAS FOUND ON THE DOOR FRAME WEB BS 200 - 202, LONGERON 18L. REPAIRED IAW SRM 53-00-00, REP 2.

Part: FLOORBEAM — CORRODED (BS 200) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON FLOORBEAM BS 200. LBL 14 TO 9. REPLACED IAW SRM 51-41-02-0G.

Part: LONGERON — CRACKED (BS 1022) · airframe 33,149 hrs · 22,253 cycles

CRACK LONGERON 6R, BS 1022. THE LONGERON WAS REPAIRED IAW SRM 53-00-05-2R.

Part: PAN — CRACKED (BS 889) · airframe 33,149 hrs · 22,253 cycles

CRACK RING PAN ON LWR CORNER BS 889. THE RING PAN WAS REPAIRED IAW SRM 56-20-02-2R, FIG 202.

Part: STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON STRAP FRONT OF DOOR JAMB WEB STA Y=200 X=54 (5310-2005). LEVEL CORROSION 2, STRAP WAS REPLACED PER DWG 9910078 REV JC.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,149 hrs · 22,253 cycles

CORROSION ON FLOOR SUPPORT BTW STA Y=200-218 IN X=56 AT PAX CABIN (W1) (AMDS 5300-2010). CORROSION LEVEL 2, FLOOR SUPPORT BTW STA Y=200-218 IN X=56 WAS FABRICATED PER DWG 9936535 REV CS, AND IT WAS INSTALLED PER SRM 51-41-05 AND 51-41-08-OG.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 31,939 hrs · 21,502 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND L2 MAIN EXIT SIGN AND RIGHT FORWARD SERVICE DOOR EMERGENCY EXIT SIGN INOPERATIVE. THE EMERGENCY EXIT SIGN LIGHT BATTERY WAS REPLACED PER B717 AMM 33-51. NO HELP. THEN THE POWER SUPPLY FOR THE CABIN EMERGENCY EXIT SIGN WAS REPLACED. OPERATIONAL CHECK IS NOW NORMAL. AIRCRAFT IS OK FOR SERVICE. (LP #3350793)

Part: LENS — MISSING (EMERGENCY LIGHT) · airframe 31,790 hrs · 21,390 cycles

EMERGENCY EXIT LENS COVER MISSING ABOVE R1 DOOR. INSTALLED EXIT SIGN COVER. LP#3350712

Part: LONGERON — CRACKED (FUSELAGE) · airframe 30,149 hrs · 20,263 cycles

TAIL INTERIOR COMPARTMENT LONGERON 2L CRACKED AT END FITTING STA 1133. SEE NR FOR ADDITIONAL INFORMATION 001-0230:5300-2004/001 00092. REPAIRED PER SRM 53-00-05 REPAIR 2.

Part: STRINGER — CORRODED (BS 898-964) · airframe 32,819 hrs · 22,046 cycles

CORROSION ON STRINGER 30 AT MULTIPLE LOCATIONS BETWEEN BS 898 - 964.

Part: LONGERON — CORRODED (BS 934-964) · corrosion level 2 · airframe 28,043 hrs · 18,629 cycles

EVIDENCE OF CORROSION ON LONGERON 30, BS 934 TO 964. BLENDED CORRODED AREAS OF LONGERON NR 30 IAW SRM 53-00-00. REMAIN THICKNESS 0.026". REF NDT SPM PART 4-04-00-03. DAMAGE FOUND TO BE OUT OF LIMITS IAW SRM 53-00-00, FIGURE 103. BLEND AREA UT REMAINING THICKNESS .75" REF MDDC SPM PART 4-04-00-03. OK TO CONTINUE REPAIR. REMOVED FASTENERS FROM STR 30, BS 944 TO BS 970 IAW SRM 51-41-02. REMOVED CORROSION FROM STR NR 30, BS 944 TO BS 970 IAW SRM 51-10-04. NDT. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-00. MATERIAL LOSS IS MORE THAN 20 PERCENT BUT LESS THAN 50 PERCENT. REPAIR 3 REQUIRED, ALL WORK DONE IAW SRM 53-00-00. LOCATED & DRILLED REPAIR U-CHANEL IAW SRM 53-00-05, REPAIR NR 3. OK TO TREAT & PRIME. TREATED AND PRIMED IAW SRM 51-10-4. OK TO INSTALL. INSTALLED REPAIR IAW SRM 53-00-05, REPAIR 3 AND SRM 51-40-05. REQUIRED RII INSPECTION ITEM COMPLETED.

Part: STRAP — CORRODED (BS 946-954) · corrosion level 2 · airframe 29,867 hrs · 20,073 cycles

CARGO TRACK STRAP FITTING CORRODED BS 946 - 954, STRINGER 30R, RBL 3. REMOVED AND REPLACED THE STRAP FITTING IAW SRM 51-41-05, 51-41-02.

Part: FRAME — CRACKED (BS 696) · airframe 26,368 hrs · 17,295 cycles

DURING SCHEDULED INSPECTION FOR OVERWING FRAME CRACKS, THE LT OVERWING FRAME AT FS 696 WAS FOUND TO BE CRACKED. FRAME WAS REPLACED IAW AMDS WC 5310-01436-03A.

Part: INTERCOSTAL — DAMAGED (BS 713) · airframe 26,366 hrs · 17,294 cycles

DURING THE SCHEDULED OVERWING FRAME INSPECTION, THE INTERCOSTAL AT LONGERON 11L, BS 713 WAS FOUND DAMAGED. NEW INTERCOSTAL WAS FABRICATED AND INSTALLED IAW WC 5310-01436-03A.

Part: CUSP WEB — CRACKED (BS 674) · airframe 26,366 hrs · 17,294 cycles

DURING OVERWING FRAME INSPECTION, FOUND CUSP MEMBRANE WEB CRACKED AT FS 674, LBL 44. REPAIRED IAW SRM 53-00-55, REPAIR 4.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 26,363 hrs · 17,293 cycles

DURING LINE CHECK, FOUND OVERWING, EXTERNAL, EMERGENCY LIGHTS LT AND RT INOPERATIVE. REPLACED OVERWING EMERGENCY EVACUATION BATTERY POWER SUPPLY & BATTERY PACK IAW AMM 33-51. CHECKED GOOD.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 26,206 hrs · 17,186 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EXTERIOR EMERGENCY LIGHTING WAS INOPERATIVE. MAINTENANCE REPLACED THE AFT POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATING CONDITION.

Part: HOLDER — CRACKED (R1 DOOR) · airframe 24,429 hrs · 15,902 cycles

R1 DOOR EMER EVAC SLIDE GIRT BAR STOW HOLDER CRACKED. R & R HOLDER IAW SRM.

Part: SUPPORT FITTING — CRACKED (LT MLG WW) · airframe 24,429 hrs · 15,902 cycles

LEFT WW FWD DOOR CUT OUT INBD SUPPORT FITTING CRACKED. R & R BRACKET IAW SRM.

Part: COVER — MISSING (CABIN) · airframe 24,805 hrs · 16,163 cycles

EMERGENCY LIGHT COVER MISSING AT ROW 21. INSTALLED COVER IAW AMM.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 23,448 hrs · 15,249 cycles

LT VENT LOUVER BOX & VERTICAL ANGLE CRACKED AT UPPER AFT CORNER. R & R ANGLE IAW SRM & DRAWING.

Part: FITTING — CORRODED (GIRT BAR) · airframe 23,448 hrs · 15,249 cycles

R1 DOOR EMERGENCY EVAC SLIDE AFT GIRT BAR FITTING CORRODED AT BS 199, RBL 53. REPAIRED FITTING IAW SRM & DRAWING.

Part: WEB — CORRODED (FUSELAGE) · airframe 23,448 hrs · 15,249 cycles

FWD ENTRY WEB CORRODED AT BS 200, BL 0. REPAIRED WEB IAW SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 23,448 hrs · 15,249 cycles

SEAT TRACK CORRODED AT BS 207, RBL 44. REPAIRED SEAT TRACK IAW SRM.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 23,448 hrs · 15,249 cycles

RT VENT LOUVER UPPER AFT CLIP ANGLE CRACKED. R & R ANGLE IAW SRM & DRAWING.

Part: SKIN — LOOSE (VERTICAL STAB) · airframe 23,448 hrs · 15,249 cycles

VERTICAL STABILIZER LE SKIN IAW EA. REPAIRED SKIN IAW EA & DRAWING.

Part: PANEL — CRACKED (RT WING) · airframe 23,448 hrs · 15,249 cycles

RT WING INBD BUTT DOOR AFT HINGE FWD PANEL INBD END CRACKED. REPAIRED PANEL IAW EA.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 23,448 hrs · 15,249 cycles

FWD CARGO COMPARTMENT DOOR CUTOUT LOWER DOOR JAMB CORRODED. REPAIRED JAMB IAW SRM.

Part: PANEL — CRACKED (RT WING) · airframe 23,448 hrs · 15,249 cycles

RT WING INBD BUTTE DOOR PANEL FWD HINGE FWD WING PANEL CRACKED. REPAIRED PANEL IAW SRM.

Part: SKIN — DELAMINATED (RT SPOILER) · airframe 23,448 hrs · 15,249 cycles

RT WING OTBD SPOILER UPPER SURFACE DELAMINATED. REPAIRED SPOILER IAW SRM.

Part: PANEL — CRACKED (LT WING) · airframe 23,448 hrs · 15,249 cycles

LT WING INBD BUTT DOOR FWD PANEL CRACKED. REPAIRED PANEL IAW SRM.

Part: VANE — DAMAGED (TE FLAP) · airframe 23,448 hrs · 15,249 cycles

LT WING INBD FLAP MOVABLE VANE SPRING CABLE AROUND PULLEY INSULATION DAMAGED. R & R VANE IAW DRAWING.

Part: SIGN — BROKEN (CABIN) · airframe 22,863 hrs · 14,849 cycles

L1 DOOR EMERGENCY EXIT PATHWAY SIGN ASSEMBLY BROKEN. R&R LIGHT ASSEMBLY IAW MM.

Part: PCU — FAULTY (ELECTRICAL SYS) · airframe 20,918 hrs · 13,604 cycles

AFTER TAKEOFF DURING CLIMB AT APPROXIMATELY 1200 FT THE BATTERY CHARGER FAIL LEVEL 1 ALERT ILLUMINATED FOR APPROXIMATELY THREE MINS. BATTERY VOLTS WERE NORMAL. REPLACED ELECT POWER CONTROL UNIT EPCU AND EMERGENCY POWER RELAY R2 - 636 AND OPS CHECK

Part: BATTERY — DISCHARGED (FLASHLIGHT) · airframe 20,911 hrs · 13,599 cycles

AFT F/A FLASHLIGHT INOP. REMOVED AND REPLACED THE AFT FLASHLIGHT BATTERY, OPS CHECK GOOD PER B717 MM.

Part: CHARGER — FAILED (E&E BAY) · airframe 20,854 hrs · 13,566 cycles

AIR RETURN - BATTERY CHARGER FAIL ALERT AND ACRID SMELL IN COCKPIT AND CABIN. REMOVED AND REPLACED BATTERY. CHARGER PAR MM.

Part: BATTERY — DISCHARGED (FLASHLIGHT) · airframe 20,566 hrs · 13,383 cycles

ONE AFT CABIN EMERGENCY FLASH LIGHT INOP. REMOVED AND REPLACED BATTERY ASSY REF AMM.

Part: BATTERY — UNSECURE (FLASHLIGHT) · airframe 20,919 hrs · 13,718 cycles

FORWARD FLIGHT ATTENDANT SEAT UPPER FLASHLIGHT INDICATOR INOP. SECURED BATTERY IAW MM.

Part: SKIN — DENTED (FUSELAGE)

LEFT SIDE AFT OF L1 DOOR FUSELAGE SKIN, STA 237, LONG L17L, DENT. ACCOMPLISHED FUSELAGE SKIN DOUBLER REPAIR PER B717 SRM 53-00-01, 53-20-01 AND 51-10-04. SEE NR 24906 AND 24981.

Part: DOOR FRAME — CRACKED (FUSELAGE)

AFT CARGO DOOR CUTOUT STUB FRAME, CRACKED. ACCOMPLISHED STUB FRAME REPLACEMENT PER B717 SRM 51-40-02, 51-40-08 AND 51-10-04. SEE NR 24962.

Part: STRUCTURE — DAMAGED (CARGO DOOR)

C2 DOOR FORWARD SIDE LATCH CUTOUT, DAMAGED. ACCOMPLISHED LATCH CUTOUT DOUBLER AND FILLER REPAIR PER B717 SRM 52-30-02, 51-10-02 AND 51-40-02. SEE NR 24894.

Part: THRESHOLD — CORRODED (FUSELAGE)

C-2 CARGO DOOR THRESHOLD (JAMB), CORROSION. ACCOMPLISHED LOWER PAN SECTION REPLACEMENT PER B717 SRM 53-20-15.

Part: ENGINE — MALFUNCTIONED (LEFT)

LT ENGINE SHUT DOWN DUE TO OIL PRESS "0". REMOVED AND REPLACED LEFT ENG REF TASK CARD# 603 BR 700-715.

Part: BATTERY — DISCHARGED (CARGO BAY)

RT AND LT OVERWING EMERGENCY EVACUATION LIGHT INOP. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY ASSY IN AFT CARGO IAW B717 AMM 33-51 OPS CHECK GOOD.

Part: LIGHT — BROKEN (CABIN)

FIRST EMERGENCY LIGHT ACROSS FROM FWD LAV FRAME IS BROKEN. RE-SECURED LIGHT FRAME REF MM 25 28.

Part: LIGHT — UNSECURE (CABIN)

ESCAPE PATH LIGHTING FWD GALLEY FALL DOWN. SECURED FWD SCAPE PATH LIGHTING.

Part: PIN — MISSING (EVAC SLIDE)

PIN MISSING ON L-1 DOOR EVACUATION SYSTEM. REMOVED AND REPLACED L-1 DOOR EVAC SLIDE. REF MM 25-61.

Part: LIGHT — MISSING (CABIN)

BULB AND COVER, ESCAPE LIGHTING AT 1D MISSING. REPLACED COVER AND BULBS AT SEAT 1D, CHECKS GOOD. REF MM 33-51.

Part: BATTERY — DISCHARGED (CABIN)

PER T/C 340, COCKPIT EMERGENCY LIGHTS WILL NOT ILLUMINATE DURING EMERGENCY LIGHTING SYSTEM TEST. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY SUPPLY ASSY. OPERATIONAL TEST OF EMERGENCY LIGHTING SYSTEM PERFORMED IAW AMM 33-51. FOUND GOOD.

Part: LIGHT — INOPERATIVE (CATWALK)

EMERGENCY EXIT LIGHT IN AFT COMPARTMENT CATWALK INOP. REMOVED AND REPLACED AFT COMPARTMENT OVERHEAD BULB. OPS CHECK EMERGENCY LIGHT AND OPS NORMAL.