N933AT

Part: SENSOR — FAULTED (ZONE 100) · airframe 57,285 hrs · 41,681 cycles

ON THE GROUND ON APU POWER WHEN RT PACK TURNED ON, DID NOT COME ON. SMELLED SMOKE & THEN GOT PACK R FLO DISAG. TURNED SWITCH OFF AND SMELL WENT AWAY. R & R RT AIRFLOW SENSOR REF AMM 21-52. OPS CHK NML NO FAULTS, GOOD AIRFLOW. MEL/PLAC REMOVED. REVERSED M PROC. (7343272)

Part: NOT REPORTED — NO DISCREPANCY (ZONE 100) · airframe 56,979 hrs · 41,411 cycles

WORKING REP CK RH MLG DOOR KEEL BEAM . C/W REP CK PER ER/A 621720-14 (9858048)

Part: STRUT — DISCHARGED (ZONE 700) · airframe 56,956 hrs · 41,387 cycles

ATB/GEAR- RETURNED ATL DUE TO PSEU FAIL MESSAGE WITH LANDING GEAR INDICATION INCORRECT. GEAR HANDLE UP AND INDICATION SHOWS DOWN. FAULT CLEARED WITH CORRECT INDICATION. RETURNED ATL PRECAUTIONARY. SERVICED NLG STRUT. REPLACED GEAR INDICATION BULBS. OPS NORMAL.(9858076)

Part: DEFOG SYSTEM — FAULTED (ZONE 200) · airframe 56,107 hrs · 40,594 cycles

WHEN COCKPIT CREW TURNED ON THE WINSHIELD ANTI-FOG SWITCH, WHILE AT CRUISE, A SHOWER OF SPARKS SHOT OUT OF THE UPPER EDGE OF FIRST OFFICER'S FORWARD FACING WINDOW. THE CREW PULLED CIRCUIT BREAKER X26 10592. MAINTENANCE PERFORMED A VISUAL INSPECTION OF FIRST OFFICER'S WINDSCREEN AND FOUND THAT THE ANTI-FOG SENSOR RING TERMINALS WERE MISSING INSULATION AND MAKING CONTACT WITH EACH OTHER. RETERMINATED SENSOR WIRES PER B717 SWPM 20-20-01, PERFORMED OPERATIONAL CHECK OF WINDOW ANTI-FOG AND HEAT SYSTEM IAW B717 AMM 30-42-01. ALL CHECKS WERE GOOD. REFER TO LOG PAGE #0884126 FOR NO-GO ODI PREVENTION. NO OTHER DAMAGE NOTED. AC OK FOR SERVICE. (LP #7236638)

Part: LENS — MISSING (ZONE 200) · airframe 55,742 hrs · 40,276 cycles

THE FIRST EMERGENCY LIGHT ON CATWALK IN EMPENNAGE IS MISSING THE LENS COVER. MAINTENANCE REPLACED THE EMERGENCY LIGHT ASSEMBLY. OPERATIONAL CHECK WAS GOOD. (LP #0803705)

Part: LENS — MISSING (EMERGENCY LIGHT) · airframe 53,960 hrs · 38,717 cycles

EMERGENCY LENS COVER AT 17CDE MISSING. MAINTENANCE INSTALLED NEW EMERGENCY LENS COVER AT 17CDE PER B717 AMM 33-51. (LP #5874313)

Part: UNION — LEAKING (HYD SYSTEM) · airframe 53,932 hrs · 38,691 cycles

AN EMERGENCY WAS DECLARED WITH ATC DUE TO THE RIGHT HYDRAULIC FLUID QUANTITY DECREASING. MAINTENANCE REPLACED THE RIGHT MAIN LANDING GEAR DOWN TEE ASSEMBLY. OPERATIONAL AND LEAK CHECKS WERE BOTH GOOD. THE AIRCRAFT HAS RETURNED TO SERVICE. (LP #5300792)

Part: SKIN — DAMAGED (AFT CARGO DOOR) · airframe 53,693 hrs · 38,492 cycles

BOTTOM FWD CORNER OF AFT CARGO DOOR SKIN DAMAGED. REMOVED CARGO (AFT CARGO) PER B717 AMM 52-31. CUT OUT DAMAGE PER B717 SRM 52-00-01-2R. PERFORMED HFEC INSP OF CUT OUT REPAIR AREA PER B717 SRM 52-00-01-2R. NO CRACK INDICATION NOTED. COMPLETED REPAIR PER B717 SRM 52-00-01-2R. FOUND AFT HINGE, AFT ATTACH DOUBLER WORN. FABRICATED AND INSTALLED A NEW DOUBLER PER BOEING DWG 9919628 AND B717 AMM 52-31. CKS GOOD.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 53,635 hrs · 38,435 cycles

A.D. RUST IN BARREL NUT AND CORROSION IN BARREL NUT HOLE (HSTAB SKIN) WAS FOUND IN NUT #11 AT RH HSTAB UPPER SIDE, IN REFERENCE NRC 438. SUMMARY OF NRC 00727: HORIZONTAL STABILIZER RH UPPER BARREL NUT HOLE #11 AND LOWER BARREL NUT HOLE #29 WERE REPAIRED PER PRI 615196-14 REV 2 AND ERA 615196-14AD REV ORIGINAL SECTION I: PERMANENT REPAIR. MAINTENANCE REQUIREMENTS WERE VERIFIED ON FOLLOWING ACTIONS AS NEEDED: REPAIR APPROVAL IS LIMITED TO 24 MONTHS ONLY AFTER 07-FEB-2024. ADDITIONAL ENGINEERING AUTHORIZATION (ERA REVISION) IS REQUIRED FOR CONTINUED SERVICE BEYOND THIS LIMIT. NOTE TO ENGINEER: DAMAGE TOLERANCE ANALYSIS (DTA) STAGE II/III IS REQUIRED IN ACCORDANCE WITH PROCEDURES ESTABLISHED IN FACC AC 120-93. UNDER LOG PAGE #0202232. ASSOCIATED ERA 14-615196 ADDED FOR AC 9566. (LP #0209462)

Part: BEAM — CRACKED (L1 DOOR AREA) · airframe 53,635 hrs · 38,435 cycles

CRACKS ON BEAM #1 FWD AND AFT EDGE (INTERNAL STRUCTURE) AT PASSENGER DOOR (L1). SUMMARY OF NRC 00083: BEAM #1 FWD AND AFT EDGE (INTERNAL STRUCTURE) AT PASSENGER DOOR (L1) WAS REPAIRED PER B717-200 SRM 52-10-02-2R PROCEDURE 7, REPAIR 7. (LP #0201880)

Part: UNKNOWN — DAMAGED (RUDDER) · airframe 53,635 hrs · 38,435 cycles

ELONGATED HOLES ON AREA TO ATTACH ANCHOR NUT ON SETTLEMENT AREAS OF ACCESS 370CR AT RUDDER LOWER AREA. SUMMARY OF NRC 00455: AREA TO ATTACH ANCHOR NUT ON SETTLEMENT AREAS OF ACCESS 370CR AT RUDDER LOWER AREA WAS REPAIRED PER ERA 615547-14, REV ORIGINAL. MAINTENANCE REQUIREMENTS WERE VERIFIED AND NO FURTHER ACTION ARE REQUIRED. ASSOCIATED ERA 14-615547 ADDED FOR AC 9566. (LP #0200986)

Part: PAN — WORN (AFT CARGO DOOR) · airframe 53,635 hrs · 38,435 cycles

WEAR ON EXTERNAL PAN UPPER FWD/AFT CORNERS AT AFT CARGO DOOR. SUMMARY OF NRC 00116: EXTERNAL PAN UPPER FWD CORNER AT AFT CARGO DOOR WAS BLENDED OUT AND MEASURED AS FOLLOW: ORIGINAL THICKNESS OF 0.050" REMAINING THICKNESS.0.048" THEREFORE IT IS WITHIN THE ALLOWED LIMITS PER B717-200 SRM 52-00-00-1A PAR 4 C FIGURE 103. EXTERNAL PAN UPPER AFT CORNER WAS REPAIRED PER ERA 615583-14, REV ORIGINAL. ASSOCIATED ERA 14-615583 ADDED FOR AC 9566. (LP #0200807)

Part: ANGLE — CRACKED (BS 710-715) · airframe 53,635 hrs · 38,435 cycles

CRACK ANGLE STA 710-715 X=-43 AT CENTER TANK WING UPPER SURFACE AT PAX CABIN (WINGBOX AREA). SUMMARY OF NRC 00320: ANGLE STA 710-715 X=-43 AT CENTER TANK WING UPPER SURFACE AT PAXCABIN WAS REPAIRED PER PRI 615191-14 REV 4 AND ERA 615191-14 REV ORIGINAL, SECTION I: PERMANENT REPAIR. ASSOCIATED ERA 14-615191 ADDED FOR AC 9566. (LP #0202011)

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 53,635 hrs · 38,435 cycles

DENTS ON RH FWD MOVABLE FLAP. SUMMARY OF NRC 00381: DENTS (10 LOCATIONS) ON RH FWD MOVABLE FLAP, #2, #3, #5, #6, #8, #9, & # 10 WERE EVALUATED AND FOUND TO BE WITHIN LIMTS PER B717-200 SRM 57-53-01-1A-1 PAR 3 A (1)(2)(4). DENT #1: O/B=18 IN, T/E=6.700 IN, L=1.150 IN, W=0.900 IN, Y=0.029 IN, W/Y=31; (DISTANCE BTW DENTS #1 TO #4 IS 2.750 IN.) DENT #4: O/B=20.600 IN, T/E=6.100 IN, L=0.800 IN, W=0.700 IN, Y=0.035 IN, W/Y=20; DENT #7: O/B=22 IN, T/E=6.900 IN, L=0.800 IN, W=0.700 IN, Y=0.025 IN, W/Y=28; (DISTANCE BTW DENTS #4 TO #7 IS 0.800 IN.) WITH A SEPARATION OF LESS THAN 3" THESE DENTS ARE OUT LIMITS PER B717-200 SRM 57-53-01-1A-1 PAR 3 A (1) TO (3). DENTS #1, #4, & #7 WERE REPAIRED PER B717-200 SRM 51-70-02-0G PROCEDURE GENERAL WITH REFERENCE TO B717-200 SRM 57-53-01-2R REPAIR 1 PAR 4 D. DENTS #2, #3, #5, #6, & #8 WERE UNDER REPAIR OF DOUBLER. DENTS #9 & #10 WERE ATTENDED UNDER MON/9566/1354431. PERFORM DECAL CONDITION INSPECTION EVERY C CHECK PER TOPP MANUAL 30-10-70 PAR I PAGE 14. (LP #0194382)

Part: FRAME — CRACKED (BS 1037 L14R) · airframe 53,635 hrs · 38,435 cycles

CRACK ON RH FRAME STA 1037 LONG 14RH AT PAX CABIN. SUMMARY OF NRC 00296: CRACK ON RH FRAME STA 1037 LONG 14RH AT PAX CABIN WAS REPAIRED PER PRI 614871-14 REV 2 AND ERA 614871-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-614871 ADDED FOR AC 9566. (LP #0193395)

Part: CAP — CRACKED (BS 1022 L1) · airframe 53,635 hrs · 38,435 cycles

CRACK ON CAP STA 1022 AND LONG 1. SUMMARY OF NRC 00351: CAP STA 1022 AND LONG 1 WAS REPAIRED PER PRI 615124-14 REV 0 AND ERA 615124-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. ASSOCIATED ERA 14-615124 ADDED FOR AC 9566. (LP #0192767)

Part: SKIN — CRACKED (BS 1076-1087) · airframe 53,635 hrs · 38,435 cycles

CRACKS (2 EA) ON FUSELAGE SKIN BTW STA Y=1076 AND STA Y=1087 BTW LONG 13R AND LONG 14R AT AFT FUSELAGE. SUMMARY OF NRC 0514: CRACKS (2 EA) ON FUSELAGE SKIN BTW STA Y=1076 AND STA Y=1087 BTW LONG 13R AND LONG 14R AT AFT FUSELAGE. WERE REPAIRED PER PRI 614977-14 REV 1 AND ERA 614977-14 REV ORIGINAL, SECTION I: PERMANENT REPAIR. ACCOMPLISH REPETITIVE INSPECTIONS WITHIN EVERY 24 MONTHS AFTER ACCOMPLISHMENT OF SECTION I: PERMANENT REPAIR, UNDER LOG PAGE #0189745. ASSOCIATED ERA 14-614977 ADDED FOR AC 9566. (LP #0192083)

Part: SKIN — CRACKED (BS 1087 L13-14L) · airframe 53,635 hrs · 38,435 cycles

CRACK ON FUSELAGE SKIN ON STA Y=1087 BTW LONG 13L AND LONG 14L AT AFT FUSELAGE. SUMMARY OF NRC 00513: FUSELAGE SKIN ON STA Y=1087 BTW LONG 13L AND LONG 14L AT AFT FUSELAGE WAS REPAIRED PER PRI 614985-14 REV 3 AND ERA 614985-14 REV ORIGINAL SECTION I: PERMANENT REPAIR. ACCOMPLISH REPETITIVE INSPECTIONS WITHIN EVERY 24 MONTHS AFTER ACCOMPLISHMENT OF SECTION I: PERMANENT REPAIR, UNDER LOG PAGE #0191192. ASSOCIATED ERA 14-614985 ADDED FOR AC 9566. (LP #0191896)

Part: FRAME — CRACKED (BS 660) · airframe 53,635 hrs · 38,435 cycles

CRACK ON FRAMES 2 EA, STA Y=660 AND 675 OUTBOARD EDGE LH SIDE OF KEEL BEAM AREA. SUMMARY OF NRC 0807: FRAME STA=660 AND FRAME STA=675 OUTBOARD EDGE LH SIDE OF KEEL BEAM AREA WERE REPAIRED PER B717-200 SRM 51-41-05-0G, 51-41-02-0G, AND 51-70-11-2R PROC 1 REPAIR 1. MAINTENANCE REQUIREMENTS: PERFORM A GVI ON FRAMES (2 EA) STA Y=660 AND 675 OUTBOARD EDGE LH SIDE OF KEEL BEAM AREA EVERY C CHECK PER B717-200 SRM 51-70-11-2R PROC 1 REPAIR 1. (LP #0188975)

Part: FRAME — CRACKED (BS 1200 S17) · airframe 53,635 hrs · 38,435 cycles

CRACK ON CANTED FRAME INTERNAL STRUCTURE Y=1200 REF STGR 17 APROX. SUMMARY OF NRC 00257: CANTED FRAME INTERNAL STRUCTURE Y=1200 REF STGR 17 APROX WAS REPAIRED PER PRI 614980-14 REV 1 AND ERA 614980-14 REV ORIGINAL.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 53,635 hrs · 38,435 cycles

CRACK ON INTERNAL DOUBLER AFT EDGE BTW BEAM #1 AND #2 AT FWD CARGO DOOR. SUMMARY OF NRC 00104: INTERNAL DOUBLER (WEB) AFT EDGE BTW BEAM #1 AND #2 AT FWD CARGO DOOR WAS FABRICATED AND REPLACED PER BOEING DWG 9957664 REV "N", B717-200 SRM 51-41-01-0G, 51-41-02-0G, AND 51-41-05-0G. (LP #0186063)

Part: PAN — CRACKED (FUSELAGE) · airframe 53,635 hrs · 38,435 cycles

CRACK ON INTERNAL PAN FWD EDGE ON BEAM #1 AT FWD CARGO DOOR. SUMMARY OF NRC 00103: INTERNAL PAN FWD EDGE ON BEAM #1 AT FWD CARGO DOOR WAS REPAIRED PER B717-200 SRM 52-30-02-2R REPAIR 1. (LP #0187095)

Part: PAN — CRACKED (FUSELAGE) · airframe 53,635 hrs · 38,435 cycles

CRACK ON LOWER EDGE OF EXTERNAL PAN AT FWD CARGO DOOR WAS FOUND IN REF NRC 00098. SUMMARY OF NRC 00788P: LOWER EDGE OF EXTERNAL PAN AT FWD CARGO DOOR WAS REPAIRED PER B717-200 SRM 52-30-02-2R REPAIR 1. (LP #0185876)

Part: FRAME — CRACKED (BS 696) · airframe 53,635 hrs · 38,435 cycles

CRACK ON UPPER RADIUS OF THE FRAME TAB OF THE OVERWING FRAME STA 696 RH AT PAX CABIN. SUMMARY OF NRC 00462: CRACKED FRAME TAB OF THE OVERWING FRAME STA 696 RH AT PAX CABIN WAS REPLACED PER B-717-200 SRM 51-41-05-0G AND 51-41-02-0G IN REFERENCE CARD 5310-01436-03B JOB 100-0002. ASSOCIATED AA 5310-01436 ADDED FOR AC 9566. (LP #0185725)

Part: DRAG BRACE — CORRODED (NLG) · corrosion level 2 · airframe 53,635 hrs · 38,435 cycles

CORROSION ON DRAG BRACE BORE (LH TAPER PIN HOLE) AND CORROSION ON LH / RH (2 EA) TAPER PIN AT NLG. DRAG BRACE WAS REMOVED PER B717-200 AMM 32-22-05 000-802. SUMMARY OF NRC 00250: NLG DRAG BRACE ASSY WAS REPLACED PER B717-200 AMM 32-22-05. OPERATIONAL TEST OK. (LP #0185561)

Part: INTERCOSTAL — CRACKED (BS 180) · airframe 53,635 hrs · 38,435 cycles

CRACK ON INTERCOSTAL BTW BEAMS 4 AND 5 STA Y=180 AT PASSENGER DOOR (L1). SUMMARY OF NRC 00087: INTERCOSTAL BTW BEAMS 4 AND 5 STA Y=180 AT PASSENGER DOOR (L1) WAS FABRICATED AND REPLACED PER DWG 9955763 REV K, B717-200 SRM 51-41-01-0G AND 51-41- 02-0G. (LP #0185484)

Part: BEAM — CRACKED (L1 DOOR) · airframe 53,635 hrs · 38,435 cycles

CRACK BEAM NBR 6 (MID SECTION) ON PASSENGER DOOR (L1). SUMMARY OF NRC 00174: BEAM NBR 6 (MID SECTION) ON PASSENGER DOOR (L1) WAS REPAIRED PER B717-200 SRM 51-70-11-2R, PROCEDURE 1, REPAIR 1. (LP #0182665)

Part: FITTING — CRACKED (BS 1053 BULKHEAD) · airframe 53,635 hrs · 38,435 cycles

CRACK ON VERTICAL FITTING ON AFT PRESSURE BULKHEAD STA 1053 LONGERON #1 (ABOVE DOOR CUT OUT) AT PAX CABIN. SUMMARY OF NRC 00522: SPRING OF THE ARM ASSEMBLY WAS REMOVED AND INSTALLED PER B717-200 AMM 53-52-02-020-801 AND 53-52-02- 420-801, VERTICAL FITTING ON AFT PRESSURE BULKHEAD STA 1053 LONGERON #1 (ABOVE DOOR CUT OUT) AT PAX CABIN WAS REPLACED PER B717-200 SRM 51-41-05-0G AND 51-41-02-0G. (LP #0171298)

Part: FRAME — CRACKED (BS 1037 S17L) · airframe 53,635 hrs · 38,435 cycles

CRACK ON LH FRAME STA 1037 LONG 17LH AT PAX CABIN. SUMMARY OF NRC 00294: LH FRAME STA 1037 LONG 17LH AT PAX CABIN WAS REPAIRED PER B717-200 SRM 53-20-07-2R. (LP #0170333)

Part: CUSP WEB — CORRODED (BS 610-660) · corrosion level 2 · airframe 53,635 hrs · 38,435 cycles

CORROSION ON CUSP WEB (RH) BTW STA Y=610 TO STA Y=660 APROX AT PAX CABIN. SUMMARY OF NRC 00510: CORROSION LEVEL 2. AREA ON CUSP WEB (RH) BTW STA Y=610 TO STA Y=660 APROX AT PAX CABIN WAS REPAIRED PER B-717-200 SRM 53-00-55-2R. (LP #0170434)

Part: CUSP WEB — CORRODED (BS 389-400) · corrosion level 2 · airframe 53,635 hrs · 38,435 cycles

CORROSION ON DOUBLER OF LH CUSP WEB UPPER BTW STA Y=389 TO Y=408 AT PAX CAB. SUMMARY OF NRC 00477: CORROSION LEVEL 2. DOUBLER OF REPAIR ON LH CUSP WEB UPPER BTW STA Y=389 TO Y=408 AT PAX CAB WAS REPLACED PER B-717-200 SRM 53-00-55-2R. (LP #0171752)

Part: CUSP WEB — CRACKED (BS 715-728) · airframe 53,635 hrs · 38,435 cycles

CRACKS ON CUSP WEB (BELOW) BTW STA Y=715 TO STA Y=728 AT PASSENGER CABIN. SUMMARY OF NRC 00376: CUSP WEB (BELOW) BTW STA Y=715 TO STA Y=728 AT PASSENGER CABIN WAS REPAIRED PER B717-200 SRM 51-41-02-0G AND 53-00-55-2R PROCEDURE 4 REPAIR 4. (LP #0160778)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · corrosion level 2 · airframe 53,635 hrs · 38,435 cycles

CORROSION ON REPAIR PLUG ON OUTB SEAT TRACK X=56 LH IN STA Y= 547 AND 610 (2 EA). SUMMARY OF NRC 00604: CORROSION LEVEL 2. PLUG ON OUTB SEAT TRACK X=56 LH IN STA Y=547 AND 610 (2 EA) WERE REPLACED PER B-717-200 SRM 51-41-01-0G AND 53-20-52-2R-1 REPAIR 1. (LP #0145840)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 53,635 hrs · 38,435 cycles

-AD- A SKIN LAYER CRACK WAS FOUND ON THE LEADING-EDGE SKIN ON THE RHS OF THE VERTICAL STABILIZER OF A B717-200. THE CRACK WAS REPAIRED PER ER/A 613198-14. THIS ER/A REQUIRES FOLLOW ON INSPECTION. UPDATED MONITOR LOG THRESHOLD TO ACCOUNT FOR TIME FLOWN SINCE SECTION I: PERMANENT REPAIR WAS ACCOMPLISHED. SECTION II: REPETITIVE INSPECTIONS INITIALLY DUE AT 4,600 FC FROM REPAIR ACCOMPLISHMENT (4,500 FC FROM CURRENT FC). ASSOCIATED ER/A CHANGED FROM 00-613198 TO 14-613198 FOR AC 9566. (LP #0078171)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 53,424 hrs · 38,270 cycles

ALL TAIL COMPARTMENT EMERGENCY PATHWAY LIGHTS ARE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT BATTERY PACKS B5-260 & B5-116 PER B717 AMM 33-51. OPERATIONAL CHECK WAS GOOD. THE AIRCRAFT IS OK FOR SERVICE. (LP #4368053)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 53,322 hrs · 38,188 cycles

FOUR (4) CRACK INDICATIONS NOTED ON RT VERT STAB (MARKED) REF STEP 12 OF AMDS CARD 5530-01048-02 (AD2018-10-08). AFTER SEPERATION OF LAYERS PER AMDS 5530-01048-02, BHEC INSP SHOWS UPPER 3 HOLES OK AND LOWER MARKED HOLE HAS CRACK IN SKIN LAYER ONLY (QC 4031). C/W ER/A 613198-14AD REV ORIGINAL. VERIFIED PRI REV 0-2 MATCH FINAL ER/A (QC 5284). (LP #4861679)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 53,478 hrs · 38,309 cycles

AD RELATED. DTE ERA 613198-14 REV ORIGINAL. ERA ISSUED FOR VERT STAB FRONT SPAR REPAIR AT ZFS=43.000, RHS. DAMAGE TOLERANCE EVALUATION REQUIRED ADDL TIME RLTD MON #0078171. DAMAGE TOLERANCE EVALUATION REQUIRED. DTE LOG #0040724 NO LONGER LIMITED TO 30 DAYS. ERA 613198-14AD REV A RELEASED WITH SECTION II: REPETITIVE INSPECTIONS ADDED FOR INSPECTION OF PERMANENT REPAIR. REFERENCE LOG #0078171 FOR TRACKING OF REPETITIVE INSPECTIONS. ASSOCIATED ERA CHANGED FROM 00-613198 TO 14-613198 FOR AC 9566. (LP #0040724)

Part: UNKNOWN — UNKNOWN · airframe 51,656 hrs · 36,723 cycles

AFT LOWER CARGO COMPARTMENT LINERS METAL TRANSITION STRIP BENT UP. MCC FCP DEFERRAL TO MEL 25-50-01, FLIGHT CREW PLACARD INSTALLED. LOWER COMPARTMENT LINERS BINS 3-4. INSTALLED SIDEWALL PANELS PUSHED OUT. FOUND PNL 181HF BENT UP AND WILL NEED REPLACED REF IPC 25-58-15-02 ITEM #100. ALSO PNL 181AF HAS DAMAGE WITH SHARP EDGES POINTING UPWARDS. REPLACED AFT CARGO PANEL 181 AF & RESECURE PANEL 181 HF PER B717 AMM 25-25-01. PLACARD REMOVED & MEL CLOSED. (LP #2617255)

Part: LIGHT — INOPERATIVE · airframe 51,453 hrs · 36,541 cycles

THE EXTERIOR EMERGENCY LIGHTS WERE ON IN THE ARM POSITION AT WAKE UP. MAINTENANCE REPLACED THE EMERGENCY LIGHTS RACK PER B717 AMM 33-51. OPERATIONAL CHECK IS OK. (LP #9624134)

Part: SLIDE — FAILED (L1 DOOR) · airframe 51,199 hrs · 36,340 cycles

CATERING ATTEMPTED TO OPEN 1L WITHOUT VISUAL CONFIRMATION FROM LEAD FA, AFTER JET WAY PULLED AND DOORS ARMED. THE RAFT FELL AND DID NOT INFLATE. THIS COULD PREVENT PROPER OPERATION OF THE ESCAPE PATH AND IT IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. THE SLIDE WAS DETACHED FROM GIRT BAR. THE SLIDE WAS REMOVED FROM THE AIRCRAFT. A NEW SERVICE DOOR EMERGENCY SLIDE WAS INSTALLED IAW AMDS W/C 2561-9005.

Part: BATTERY — INOPERATIVE · airframe 50,944 hrs · 36,102 cycles

DURING THE SERVICE CHECK, MAINTENANCE FOUND THE EXTERIOR EMERGENCY LIGHTS TO NOT BE TESTING PROPERLY. THE OVERWING EMERGENCY EVACUATION BATTERY WAS REPLACED PER B717 AMM 33-51. (LP #9586900)

Part: NONE — NONE · airframe 50,591 hrs · 35,758 cycles

ON WALKAROUND FOUND MISSING PANEL ON UNDERSIDE OF LEFT HAND ELEVATOR. MAINTENANCE INSTALLED A NEW PANEL PER AMM 06-33 B717. (LP #9236464)

Part: FRAME — CORRODED · corrosion level 2 · airframe 49,977 hrs · 35,195 cycles

CORROSION ON FRAME CHANNEL STA Y=889 BTW LONG 29LH AND 29 RH AT AFT CARGO COMPARTMENT IN REF NRC 00107. SUMMARY OF NRC 00214: CORROSION LEVEL 2, FRAME WAS REPAIRED PER B717 SRM 53-20-07-2R, REPAIR 3. PERFORM A VISUAL INSPECTION, INITIAL AT 25,000 FH AND REPETITIVES EVERY 6500 FH PER B717 SRM 53-20-07-2R-3 PAR 6. UPDATE DETAILS PER PREVOUS COMMENTS ON LINE 03: PERFORM A VISUAL INSPECTION, INITIAL AT 25,000 FH AND REPETITIVES EVERY 6500 FH PER B717 SRM 53-20-07-2R-3 PAR 6. (LP #2228013)

Part: SKIN PANEL — CRACKED · airframe 49,977 hrs · 35,195 cycles

CRACKED UPPER SKIN PANEL TRAILING EDGE STA XRS 111.500 AT LH WING (LW). SUMMARY OF NRC 00030: CRACKED UPPER SKIN PANEL TRAILING EDGE STA XRS 111.500 AT LH WING WAS REPAIRED PER. PRI 599039-14 REV. 0 AND ER/A 599039-14, REV. ORIGINAL, SECTION I: PERMANENT REPAIR. ASSOCIATED ER/A 14-559039 ADDED FOR AC 9566. (LP #2224039)

Part: CHANNEL — CORRODED · corrosion level 2 · airframe 49,977 hrs · 35,195 cycles

CORROSION ON FRAME CHANNEL STA Y=180 STR=30 AT E/E COMPARTMENT. SUMMARY OF NRC 00113: CORROSION LEVEL 2, FRAME CHANNEL STA Y=180 STR=30 AT E/E COMPARTMENT, WAS REPAIRED PER B717-200 SRM 53-20-07-2R, REPAIR 3. (LP #2223147)

Part: DOOR TRACK — CORRODED · corrosion level 2 · airframe 49,977 hrs · 35,195 cycles

CORROSION ON LOWER DOOR JAMB PAN AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00019: CORROSION LEVEL 2, LOWER DOOR JAMB PAN AT AFT CARGO COMPARTMENT WAS REPAIRED PER B717 SRM 53-20-15-2R REPAIR 7. (LP #2222868)

Part: SKIN — CRACKED · airframe 49,977 hrs · 35,195 cycles

CRACK ON FUSELAGE SKIN STA Y=1155 BTW LONGERON 28L TO 29L. SUMMARY OF NRC 00225: FUSELAGE SKIN STA Y=1155 BTW LONGERON 28L TO 29L WAS REPAIRED PER B717-200 SRM 53-00-00-2R. (LP #2222777)

Part: LONGERON — CORRODED · corrosion level 2 · airframe 49,977 hrs · 35,195 cycles

CORROSION ON LONGERON 29L BTW STA Y:907 TO 964 AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00112: CORROSION LEVEL 2, SECTION LONGERON 29L BTW STA 898 TO 964 WAS REPLACED PER B717 SRM 51-41-02-0G. (LP #2220090)

Part: LONGERON — CORRODED · corrosion level 2 · airframe 49,977 hrs · 35,195 cycles

CORROSION ON LONGERON 30 BTW STA Y:908 TO Y:956 AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00117: CORROSION LEVEL 2, SECTION LONGERON 30 BTW STA 898 TO 964 WAS REPLACED PER B717 SRM 51-41-02-0G. (LP #2220258)

Part: SPAR — WORN · airframe 49,977 hrs · 35,195 cycles

DISCOVERED WEAR ON THE PREVIOUS REPAIR AT THE RIGHT WING FIXED LEADING EDGE STA XIS 117. SUMMARY OF NRC 00055: WING FIXED LEADING EDGE STA XIS 117 WAS REPAIRED PER ER/A 599011-14 REV. ORIGINAL, SECTION I. PERMANENT REPAIR AND PER PRI 599011-14 REV 0. ASSOCIATED ER/A 14-599011 ADDED FOR AC 9566. (LP #2218000)

Part: DOUBLER — WORN · airframe 49,977 hrs · 35,195 cycles

FOUND WEAR ON THE FIXED LEADING EDGE REPAIR DOUBLER STA XOS 329 TO 335 AT LH WING (LW). SUMMARY OF NRC 00033: FIXED LEADING EDGE REPAIR DOUBLER STA XOS 329 TO 335 AT LH WING WAS REPLACED PER ER/A 551840-14 REV. ORIGINAL SECTION I. PERMANENT REPAIR. (LP #2218445)

Part: NONE — NONE · corrosion level 2 · airframe 49,977 hrs · 35,195 cycles

AFTER REMOVAL OF FLOOR PANEL 221AF, SEVERAL PLACES OF CORROSION WERE FOUND ON THE FLOOR SUPPORT BTW STA 157 AND 170 IN THE PASSENGER CABIN. SUMMARY OF NRC 00053: CORROSION LEVEL 2, FLOOR SUPPORT WAS REPLACED PER B717 SRM SRM 51-41-05-0G. (LP #2214987)

Part: STRUCTURE — DAMAGED (VERTICAL STAB LE) · airframe 49,401 hrs · 34,717 cycles

RHS VERTICAL STAB LEADING EDGE THREE FASTENER HOLES BELOW ZF 52 SPLICE SHOW CRACK INDICATION. CRACK IS NOT IN SKIN. ALL DAMAGED COMPLETE ON PRI 583922-14AD REV 2. INSTALLED VERTICAL LEADING EDGE PER B717 AMM 55-32-01 400-802. LEAK TEST OF RUDDER LIMITER GOOD PER B717 AMM 34-11-00-790-807 AND RETURN TO SERVICE OF MULTIMODE RECEIVER GOOD PER B717 AMM 34-35-01-741-801. SEALED L/E AND ALL PANELS ALL WORK ACCOMPLISHED PER ER/A 583922-14AD REV. ORIG SEC I PERMANENT REPAIR. (LP #1410190)

Part: BATTERY — DISCHARGED (CABIN) · airframe 47,409 hrs · 33,305 cycles

ON THE SERVICE CHECK, THE AFT CABIN OVERHEAD EMERGENCY LIGHT B5-260 WAS FOUND TO BE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY ONLY ON POWER SUPPLY B5-260 PER AMM 33-51-03. OPERATIONAL CHECK WAS NORMAL. OK FOR SERVICE. (LP #5838604)

Part: FRAME — CRACKED (FUSELAGE) · airframe 46,851 hrs · 32,926 cycles

LEFT OVER WING FRAME AT STA Y=696.00 IS CRACKED. CRACK IS CONDITION 3, EQUAL OR GREATER THAN 0.125. REPLACED FRAME REF 5310-01436-03A.

Part: CAM — OUT OF POSITION (TAILCONE) · airframe 46,851 hrs · 32,926 cycles

THE TAIL CONE RELEASE CAM WAS FOUND TO BE CLOCKED INCORRECTLY. MAINTENANCE RE-CLOCKED THE TAIL CONE RELEASE CAM REF AMM 53-52-03.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 42,478 hrs · 29,850 cycles

FWD UPPER EMERGENCY EXIT LIGHT IS INOPERATIVE. REPLACED THE BATTERY PACK IAW AMM 33-51. OPS CHECKED GOOD. ACFT OK FOR SERVICE.

Part: FASTENER — LOOSE (VERTICAL STAB) · airframe 41,869 hrs · 29,424 cycles

LT VERTICAL STAB L/E SKIN BELOW ZFS 52.267 HAS 10 LOOSE SCREWS IN UPPER ROW BELOW SPLICE AND 2 LOOSE FASTENERS IN LWR ROW BELOW SPLICE REF AA WORK CARD 5530-01048-01 STEP 3. REPAIRED DAMAGED AREA IAW ER/A 551841-14AD REV O.

Part: SKIN — CRACKED (FUSELAGE) · airframe 41,869 hrs · 29,424 cycles

FUSELAGE STA 1134 ON LT SIDE OF VERTICAL HAS SKIN CRACKED AROUND RIVET REQUEST VERIFICATION WITH HFEC MARKED. REPLACED DAMAGED AREA IAW ER/A 551837-14AD REV O.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,870 hrs · 29,425 cycles

ALC LONGERON 30 HAS CORROSION IN MULTIPLE AREAS FROM FUSELAGE FRAME STA 986 TO STA 1037. REPAIRED L30 FROM STA 899-1053 IAW SRM 53-20-05 REP 1.

Part: RIVET — LEAKING (RT WING) · airframe 41,869 hrs · 29,424 cycles

RIGHT WING UPPER SURFACE, LE WING XRS 115.500. RIVET SEEPING FUEL. REPAIRED IAW ER/A PR551844-14, SRM 51-40-02.

Part: SKIN — CRACKED (LT WING) · airframe 41,869 hrs · 29,424 cycles

LEFT WING, LWR SURFACE, LE, XOS 332.558 CRACKED. REPAIR IAW SRM 57-40-01 REPAIR 7. FABRICATED AND INSTALLED INTERNAL/EXTERNAL DOUBLERS WITH FILLERS IAW ER/A 551840-14 REV ORIGINAL.

Part: DOOR FRAME — CORRODED · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

DOOR FRAME LOWER HALF INCLUDING PAN AND SEAL SPLICES HAS MULTIPLE AREAS OF CORROSION. BLEND AND CHECK LIMITS. REPLACED THE DOOR FRAME IAW SRM 51-41-02.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 41,870 hrs · 29,425 cycles

RT CARGO SEAT TRACK IS CORRODED JUST FWD OF DOOR JAMB FWD LOWER CORNER. BLENDED CORROSION ON LWR RT CARGO SEAT TRACK AFTER EVALUATION OF BLEND FLANGE THICKNESS FOUND TO BE .040 ALLOWABLE MINIMUM FLANGE THICKNESS IS .060 THIS IS OUT OF LIMITS PER SRM 53-20-52 AD 2 VERIFIED. FABRICATED CARGO SEAT TRACK VERIFIED BY DRAWING 5936663. SEAT TRACK WAS THEN TREATED, PRIMED, AND PAINTED IAW 51-10-04. TRACK INSTALLED IN AFT CARGO RT SIDE IAW SRM 51-41-05.

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

CORROSION ON FORWARD SIDE OF ALC FRAME AND SHEAR TIES AT STA 1022.091 BETWEEN LONGERONS 29L AND 29R (MARKED IN RED). BLENDED CORROSION ON SHEAR TIE AT STA 1022 L29L -L29R. NOMINAL THICKNESS .050 REMAINING THICKNESS .038 REPAIRED SHEAR TIE IAW SRM 53-20-06 REPAIR 2 NO CORROSION NOTED ON FORWARD SIDE OF FRAME AT STA 1022.

Part: STRUCTURE — CRACKED (NR 5 SLAT) · airframe 41,869 hrs · 29,424 cycles

LEFT WING, LE NR 5 SLAT, OTBD L SURFACE CRACKED. REPAIRED IAW SRM 51-41-02 AND 51-41-08.

Part: CUSP WEB — CRACKED (FUSELAGE) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

UPPER FUSELAGE, CABIN RT CUSP WEB STA 458-503 BL54 5R CORROSION MARKED "CORROSION". REPLACED CUSP WEB RT STA 389-503 IAW SRM 51-41-02, 51-41-05. WORK COMPLETED ON OUTSIDE REPAIR NON-ROUTINE CARD 74117-0200-0257.

Part: SEAT TRACK — CORRODED (BS 197-256) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

CORROSION ON THE RIGHT INBD SEAT TRACK RBL 22, BS 197 TO 256. REPLACED THE SEAT TRACK IAW SRM 53-20-52 REPAIR 5.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 41,870 hrs · 29,425 cycles

CORROSION ON THE RIGHT CENTER SEAT TRACK (RBL44.5), FROM STA 197 TO STA 256. REPLACED RIGHT CENTER SEAT TRACK AT RBL 44.5 FROM STA 197-256 IAW AMM 53-22-01-400-800 SEE PARTIAL WS PG 1 AND 2. MATERIAL ID IAW SRM 53-20-52 LOCATED AND DRILLED NEW SEAT TRACK SECTION IAW SRM 53-20-52.

Part: SEAT TRACK — DAMAGED (BS 756-813) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

RT OTBD SEAT TRACK, BS 756 - 813 RBL 56 GOUGED AND CORRODED. REPLACED THE SEAT TRACK IAW SRM 53-20-52 (FIG 201) REPAIR 5.

Part: SEAT TRACK — CORRODED (BS 870-898) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

RBL 56 OTBD SEAT TRACK BS 870 - 898 FOUND SEVERAL SPOTS OF CORROSION. REPLACED THE SEAT TRACK IAW SRM 53-20-52 (FIG 201) REPAIR 5.

Part: SEAT TRACK — CORRODED (BS 927-986) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

RBL 56 OTBD SEAT TRACK BS 927 - 986, FOUND SEVERAL SPOTS OF CORROSION. BLENDED AREAS OF CORROSION IAW SRM 53-00-00 FIG 103 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-20-52 FIG 101. REPAIRED IAW SRM 53-20-52 REPAIR 1.

Part: FORMER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

CORROSION ON FORMER STA 954 L29L-L30. BLENDED CORROSION ON FORMER AT STA 954 IAW SRM 53-00-00 FIG 103 .037 REMAINING OF .063 FOUND TO BE OUT OF LIMITS IAW SRM 53-00-00 FIG 103 (6784). REPAIRED OUT OF LIMITS AREA IAW SRM 53-00-06 REPAIR 2.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,870 hrs · 29,425 cycles

UPPER FUSELAGE, CABIN RT CUSP WEB STA 389-427 BL54.5R CORROSION MARKED "CORROSION". BLENDED CORROSION AND FOUND TO BE OUT OF LIMITS ORG 0.020 REMAINING 0.007" REPLACED CUSP WEB WITH NEW CUSP WEB. NEW CUSP WEB IAW DWG #9430538475 AND 51-41-02, 51-41-05.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 41,869 hrs · 29,424 cycles

RT CUSP WEB CRACK AT STA 318 RBL 44. REPAIRED CRACKED RT CUSP WEB AT STA 318 RBL 44 IAW SRM 53-00-55 FIG 221 .032.

Part: SEAT TRACK — CORRODED (BS 465-503) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

CORROSION ON THE LEFT INBD SEAT TRACK LBL 22, BS 465 - 503. CUT OUT DAMAGE AND INSTALLED 3 LUG REPAIR IAW SRM 53-20-52 REPAIR 1 FIG 201.

Part: CUSP WEB — CRACKED (BS 503) · airframe 41,869 hrs · 29,424 cycles

RIGHT CUSP WEB CRACKED AT RBL 54.5, BS 503. REPAIRED THE CUSP WEB IAW SRM 53-00-55 REPAIR 4.

Part: CUSP WEB — CORRODED (BS 562-617) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

SURFACE CORROSION ON RIGHT SIDE CUSP WEB AT BS 562, 582, 598-617. REPAIRED CUSP WEB IAW SRM 53-00-55 2R-4.

Part: CUSP WEB — CORRODED (BS 598-617) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

SURFACE CORROSION ON RT CUSP WEB AT BS 598-617. REPAIRED THE CUSP WEB IAW SRM 53-00-55 2R-4.

Part: FRAME — CORRODED (BS 313) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

FRAME BS 313 HAS CORROSION AROUND FASTENERS AT ATTACH POINT FOR STR 30. BLENDED CORROSION ON FRAME AT STA 313 STR 30 AND FOUND TO BE OUT OF LIMITS ORG 0.050" REMAINING .039" WITHOUT TOOL TAG 6785 REPAIRED FRAME STA 313 STR 30 IAW B717 SRM 53-00-00 FIG 103 AND 53-20-07 REP 3 FIG 201. (LP #2820014)

Part: SUPPORT BRACKET — CRACKED (BS 737) · airframe 41,869 hrs · 29,424 cycles

UPPER CABIN SEAT TRACK SUPPORT BRACKET AT BS 737 RBL 44 IS CRACKED. REPLACED THE SUPPORT BRACKET IAW SRM 51-41-05.

Part: SEAT TRACK — CORRODED (BS 488) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

LEFT OTBD SEAT TRACK LBL 56 BS 488 CORRODED OUT OF LIMITS. REPAIRED THE SEAT TRACK IAW SRM 53-20-52-2R-1.

Part: SUPPORT BRACKET — CRACKED (BS 715) · airframe 41,869 hrs · 29,424 cycles

UPPER CABIN SEAT TRACK SUPPORT BRACKET AT BS 715 LBL 44 IS CRACKED. REMOVED THE SEAT TRACK SUPPORT BRACKET AND INSTALLED A NEW BRACKET IAW SRM 51-41-05.

Part: SEAT TRACK — CORRODED (BS 1010-1022) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

LEFT OTBD SEAT TRACK LBL 56 BS 1010-1022 CORRODED. BLENDED THE CORROSION AND FOUND OUT OF LIMITS IAW SRM 53-20-52 REPAIR 1.

Part: STRUCTURE — CORRODED (BS 172-178) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

FOUND AFTER REMOVAL OF FLOOR SUPPORT AT BS 172 TO 178 SUBFLOOR CORRODED. TRIMMED CORRODED SUBFLOOR IAW SRM 51-70-10 REPAIR 1, FABRICATED REPAIR DOUBLER AND FILLER IAW SRM 51-70-10 REPAIR 1, AND SRM 53-10-51, INSTALLED THE REPAIR IAW SRM 51-70-10 REPAIR 1.

Part: SEAT TRACK — CORRODED (BS 465) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

UPPER CABIN LEFT INBD SEAT TRACK LBL 22 BS 465 CORRODED OUT OF LIMITS. CUT OUT DAMAGE AND INSTALLED A REPAIR IAW SRM 53-20-52 REPAIR 1.

Part: SKIN — DAMAGED (RUDDER) · airframe 41,869 hrs · 29,424 cycles

RUDDER LOWER LEFT SIDE EXTERNAL SKIN IS BENT AT EDGE. REPAIRED IAW SRM 51-70-13 FIG 202

Part: FLOOR SUPPORT — CORRODED · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

FLOOR SUPPORT HAS CORROSION ON UNDERSIDE. REPLACED THE FLOOR SUPPORT IAW SRM 51-41-05 PG 17 STEP 8 AND SRM 51-41-02 PG 3 PAR F. ORIGINAL .

Part: SEAT TRACK — DAMAGED (BS 488-581) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

LEFT OUTBD SEAT TRACK LBL 56 BS 488-581 HAS CORROSION, AND NICKS. BLENDED CORROSION AND FOUND OUT OF LIMITS IAW SRM 53-20-52. REPAIRED IAW SRM 53-20-52 REPAIR 1.

Part: SEAT TRACK — CORRODED (BS 608-703) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

LEFT OTBD SEAT TRACK LBL 56, BS 608-703 HAS CORROSION. BLENDED CORROSION . REPAIRED IAW SRM 53-20-52 REPAIR 1.

Part: SEAT TRACK — CORRODED (BS 726-826) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

LEFT OTBD SEAT TRACK LBL 56, BS 726-826 HAS CORROSION, AND SCRATCHES. REPAIRED IAW SRM 53-20-52-2R-1.

Part: FLOOR SUPPORT — CORRODED (BS 160-200) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

MAIN ENTRANCE DOOR THRESHOLD FLOOR SUPPORT BS 160 - 200, LBL 62 CORRODED. BLENDED AND FOUND TO BE OUT OF LIMITS. REPLACED THE FLOOR SUPPORT IAW SRM 51-41-02, 51-41-05, 51-41-08, AND DRAWING 52929169.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 41,869 hrs · 29,424 cycles

RT CUSP WEB AT STA 679 IS CRACKED. MARKED IN RED. REPAIRED CRACK CUSP WEB AT STA 679 RT IAW 53-00-55 REPAIR NR 4.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

UPPER FUSELAGE CABIN RT SEAT TRACK STA 356-456 BL 22R CORRODED AND GOUGED METAL. MARKED. RT INBD SEAT TRACK GOUGED AND CORRODED BLENDED TRACK AT STA 356-395 ORG THICKNESS .100 REMOVED .027 ALLOWED .040, BLENDED STA 405-456 ORG THICKNESS .100 REMOVED .025 ALLOWED .040 BLEND FOUND TO BE WITHIN LIMITS IAW B717 SRM 51-30-07. BLEND AT STA 400 FOUND TO BE OUT OF LIMITS ORG THICKNESS 11.5 REMOVED .027 ALLOWED .020 REPAIR OUT OF LIMITS AREA IAW SRM 53-20-52 REPAIR 1 (FIG 201).

Part: LONGERON — DAMAGED (FUSELAGE) · airframe 41,869 hrs · 29,424 cycles

LONGERON 29L IS CORRODED FROM STA 930 TO STA 954. CLEANED UP CORROSION ON L29L FS 930-954 IAW SRM 51-10-04 PAR 35. ORIGINAL THICKNESS .125" REMAINING .121 WITHIN ALLOWABLE LIMITS IAW SRM 53-00-00 FIG 103. FOUND ELONGATE HOLE AT 943 REPAIRED LONGERON AT FS 943 IAW SRM 53-00-05-2R REPAIR 3.

Part: FLOOR PANEL — CORRODED (FWD CARGO) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

FORWARD CARGO FLOOR PANEL CORRODED. BLENDED THE FLOOR PANEL IAW SRM 53-00-00 SHEET 1. FOUND TO BE OUT OF LIMITS. FABRICATED A NEW FLOOR PANEL IAW AMM 25-58-01-350-801 C1 AND C2.

Part: ACCESS PANEL — DAMAGED (LT WING) · airframe 41,869 hrs · 29,424 cycles

LEFT WING ACCESS PANEL 520EB HAS DAMAGE. REPLACED THE ACCESS PANEL IAW AMM 28-00-00-410.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

CORROSION ON PANEL SUPPORTS UNDER CABIN FLOOR PANEL 221AF. REMOVED DAMAGE FLOOR SUPPORT UNDER PANEL 221AF IAW SRM 51-41-02 FABRICATED REPLACEMENT FLOOR SUPPORT TAG 1725328 IAW SRM 53-10-51 DWG 9936534. INSTALLED REPLACEMENT FLOOR SUPPORT IAW SRM 51-41-02, 51-41-08.

Part: CUSP WEB — CRACKED (BS 715) · airframe 41,869 hrs · 29,424 cycles

BS 715 BETWEEN LBL 56-44 CUSP WEB IS CRACKED. INSTALLED A REPAIR IAW SRM 53-00-55-R4.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 41,869 hrs · 29,424 cycles

LEFT CENTER SEAT TRACK STA 737 LBL 44.5 CRACKED AT AFT LOWER RIVETS MARKED. REPLACED WITH NEW SEAT TRACK SUPPORT BRACKET AT FS 737 LBL 44.5 IAW SRM 51-41-05.

Part: CUSP WEB — CORRODED (BS 389-408) · corrosion level 2 · airframe 41,869 hrs · 29,424 cycles

CORROSION ON LT CUSP WEB NEAR ATTACH ANGLE TO FUSE AND AT NUT PLATE BETWEEN LBL 56-44 BS 389-408. FOUND TO BE OUT OF LIMITS. REPAIRED THE CUSP WEB IAW SRM 53-00-55 REPAIR 4.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 41,869 hrs · 29,424 cycles

AFT CARGO STA. 851, BL 0 AFT ANGLE ON INTERCOSTAL IS CRACKED. AFT CARGO STA 851, BL0 AFT ANGLE ON FLOOR SUPPORT INTERCOSTAL CRACKED, REPAIRED IAW SRM 53-00-00 FIG 203, DOUBLER MATERIAL 0.040 7075-T6.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 41,869 hrs · 29,424 cycles

FORWARD CARGO CEILING STRUCTURE INTERCOSTAL CRACKED AT STA 636 BL 0. REPAIRED CRACKED INTERCOSTAL AT STA 636 BL 0 IAW SRM 53-00-00 REP 1 FIG 201.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 41,353 hrs · 29,069 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHTING AT SEAT 32 WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACKS AND THE OPS CHECKED GOOD.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,624 hrs · 29,256 cycles

AIRCELL ANTENNA ATTACH STRUCTURE HAS CORROSION. REMOVED CORROSION AND CHECKED LIMITS PER SRM 53-00-00 FIG 103. FOUND OUT OF LIMITS. REPLACED THE DOUBLER PER DWG D12441-2005.

Part: DOOR FRAME — CORRODED (AFT CARGO) · corrosion level 2 · airframe 39,313 hrs · 27,453 cycles

AFT CARGO, ENTRY LOWER JAMB CORRODED. REPAIRED IAW SRM 53-20-15, REPAIR NR 7.

Part: LONGERON — CRACKED (BS 1116) · airframe 39,313 hrs · 27,453 cycles

LONGERON 2R IS CRACKED AT BS 1116, AFT SIDE. REPAIRED IAW SRM 53-00-05, REPAIR 2.

Part: GROUND WIRE — BROKEN (EMERGENCY LIGHT) · airframe 38,443 hrs · 26,810 cycles

FLIGHT CREW REPORTED AN EMERGENCY EXIT LIGHT ABOVE FWD F/A PANEL IS DIM WHEN ENTRY LIGHT IS TURNED ON. FOUND BROKEN GROUND WIRE AT ATTACH LUG. REPAIRED THE WIRE.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 37,981 hrs · 26,420 cycles

F/A REPORTED EMERGENCY FLOOR LIGHTING DAMAGED OR INOPERATIVE. REPLACED EMERGENCY FLOOR LIGHTING AT LT OVERWING EMERGENCY EXIT.

Part: WEB — DAMAGED (BS 664) · airframe 36,868 hrs · 25,504 cycles

DURING SCHEDULED INSPECTION, FOUND DAMAGE TO FLOOR WEB AT BS 664, APPROXIMATELY 12 INCHES FROM OUTER WALL. REPAIRED SRM 53-00-55, FIG 219.

Part: CUSP WEB — CRACKED (BS 636-655) · airframe 36,868 hrs · 25,504 cycles

DURING SCHEDULED INSPECTION IN MSP, FOUND LT SIDE CUSP WEB BS 636 TO 655 IS CRACKED. REPLACED WEB IAW SRM 51-40-02.

Part: DOOR FRAME — CRACKED (BS 674) · airframe 36,868 hrs · 25,504 cycles

DURING INSPECTION, FOUND LT OVERWING FRAME AT BS 674 CRACKED. R & R LT OVERWING FRAME IAW AMDS WC NR 5310-01436-03A.

Part: DOOR FRAME — CRACKED (BS 674) · airframe 36,868 hrs · 25,504 cycles

DURING OVERWING FRAME INSPECTION IAW AD 14-05-22/SB 717-53A0034, THE LT OVERWING FRAME WAS FOUND TO BE CRACKED AND REQUIRED REPLACEMENT. DURING REMOVAL OF THE FRAME, IT WAS FOUND THAT LONGERON 11L AFT MOST END INTERFERES WITH REMOVAL OF THE STA 674 LT FRAME, AND MUST BE CUT IAW SRM 53-00-05, FIG 201, 6 ROWS OF FASTENERS MUST BE INSTALLED ON EACH SIDE OF THE CUTLINE. AS SHOWN IN ER/A 530384-14, FIG 1, THERE IS EXCESSIVE FACTORY SPACING COMMON TO THE SKIN FLANGE OF THE LONGERON WHICH DOES NOT ALLOW FOR STANDARD 4D-6D CENTER TO CENTER SPACING. INSTALLED PERMANENT REPAIR IAW ER/A 530384-14.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 36,868 hrs · 25,504 cycles

FUSELAGE, SEVERAL CRACKS ALONG CUSP MEMBRANE, STA 655-715.

Part: FLOORBEAM — CRACKED (BS 737) · airframe 36,868 hrs · 25,504 cycles

DURING SCHEDULED INSPECTION, FOUND LT SIDE FLOORBEAM CRACKED AT BS 737. REPAIRED IAW ER/A 530405-14, SECT 1.

Part: RELEASE CABLE — MISROUTED (TAILCONE) · airframe 36,868 hrs · 25,504 cycles

DURING LINE CHECK, MAINTENCE NOTED THE TAILCONE EXTERNAL RELEASE HANDLE CABLE WAS NOT ROUTED CORRECTLY. PROPERLY ROUTED IAW AMM 53-52-01.

Part: LIGHT — UNSECURE (CABIN) · airframe 35,692 hrs · 24,513 cycles

PILOT REPORTED THE EMERGENCY LIGHT AT ROW 19ABC UNSECURE. SECURED THE LIGHT.

Part: FASTENER — LOOSE (BATTERY PACK) · airframe 34,885 hrs · 23,804 cycles

DURING INSPECTION, NOTED EMERGENCY BATTERY PACK COVER SCREWS LOOSE IN OVERHEAD. CLEANED ALL FASTENERS AND INSTALLED EMERGENCY BATTERY PACK COVERS. ALL FASTENERS NOW SECURE.

Part: WIRE — MISROUTED (EMERGENCY LIGHTS) · airframe 34,885 hrs · 23,804 cycles

EMERGENCY CEILING LIGHT WIRE ROUTED INCORRECTLY ABOVE TAILCONE CATWALK. SECURED WIRING TO EMERGENCY LIGHT IN CEILING ABOVE TAILCONE CATWALK.

Part: CABLE — MISROUTED (TAILCONE SLIDE) · airframe 34,885 hrs · 23,804 cycles

TAILCONE SLIDE CABLE NOT ROUTED THROUGH AFT GROMMET COVER. SECURED CABLE THROUGH AFT GROMMET ON TAILCONE SLIDE AMM 25-61.

Part: BATTERY — DISCHARGED (CABIN) · airframe 34,865 hrs · 23,787 cycles

FWD OVERWING EMERGENCY EXIT DOORS LIGHTS INOPERATIVE. R & R BATTERY IAW MM.

Part: WEB — CORRODED (FUSELAGE) · airframe 34,842 hrs · 23,773 cycles

FLOOR WEB PAN CORRODED AT BS 160 TO BS 200, BL 0 TO RBL 58. R & R WEB IAW DRAWING.

Part: LENS — BROKEN (CABIN) · airframe 34,842 hrs · 23,773 cycles

G2 DOOR SURROUND PANEL EMERGENCY EXIT LIGHT LENS BROKEN. R & R LENS IAW AMM.

Part: ACCESS PANEL — CORRODED (FUSELAGE) · airframe 34,842 hrs · 23,773 cycles

ACCESS PANEL CENTER KEEL BEAM BETWEEN MLG DOORS CORRODED. R &R PANEL IAW SRM & DRAWING.

Part: HOLDER — BROKEN (FLASHLIGHT) · airframe 34,842 hrs · 23,773 cycles

FWD FLASHLIGHT HOLDER BOTTOM END BROKEN. R & R HOLDER IAW SRM.

Part: FITTING — CRACKED (LT MLG WW) · airframe 34,842 hrs · 23,773 cycles

LT MLG WW FWD INBD CORNER OF WW CUTOUT T FITTING CRACKED IN LOWER RADIUS AREA. R & R PANEL IAW SRM & DRAWING.

Part: BRACKET — CORRODED (FUSELAGE) · airframe 34,842 hrs · 23,773 cycles

NLG WW FWD ACCESSORY COMPARTMENT DOOR CORRODED AROUND RIVETS ON HINGE FLANGE. R & R BRACKETS IAW SRM & DRAWING.

Part: CABLE — LOOSE (L1 DOOR) · airframe 34,048 hrs · 23,259 cycles

L1 DOOR EMERGENCY EVAC SLIDE CABLE LOOSE. SECURED CABLE IAW AMM.

Part: BATTERY — DISCHARGED (CABIN) · airframe 33,872 hrs · 23,144 cycles

RIGHT EMERGENCY LIGHTS INOP AT ROW 2. REMOVED AND REPLACED BATTERY IAW AMM.

Part: RUB STRIP — DELAMINATED (TE FLAP) · airframe 30,919 hrs · 21,201 cycles

LEFT WING REQUIRED EXCESSIVE AILERON TRIM, NOTICED WHEN AUTOPILOT WAS DISCONNECTED AT APPROACH. FOUND RIGHT WING FLAP L/E UPPER RUB STRIP DELAMINATED. REPAIRED FLAP PER MM.

Part: PAN — CORRODED (FUSELAGE)

AFT CARGO COMPARTMENT LOWER DOOR JAMB PAN, CORROSION. ACCOMPLISHED JAMB PAN REPLACEMENT PER B717 SRM 53-20-15, 51-40-08 AND 53-00-15. SEE NR 23688.

Part: SHEAR TIE — CORRODED (FUSELAGE)

AFT PIT SHEAR TIE, STA 927, LONG 30 TO 29L, CORROSION. ACCOMPLISHED SHEAR TIE DOUBLER REPAIR AND REPLACEMENT PER B717 SRM 51-41-02, 53-00-06, 51-40-08 AND 51-40-02. SEE NR 23700.

Part: SKIN — CRACKED (FUSELAGE)

FUSELAGE SKIN, STA 200, LONG 24L, CRACKED. ACCOMPLISHED FUSELAGE SKIN DOUBLER REPAIR PER B717 SRM 53-03-01, 57-10-04, 51-41-10.

Part: SKIN — DEBONDED (LT SPOILER)

LEFT INBOARD FWD GROUND SPOILER EDGE SURFACE, DISBONDED. ACCOMPLISHED GROUND SPOILER EDGE SURFACE HOT BONDING REPAIR PER B717 SRM 51-70-02. SEE NR 23750.

Part: SIGN — MISSING (CABIN)

F/A REPORTED EMERGENCY EXIT SIGN IS MISSING ON TAXI OUT. F/A NOW REPORTS RED SEAT LENS MISSING, MM 33-50, INSTALLED SAME.

Part: SLIDE — UNSERVICEABLE (TAILCONE)

AFT TAIL CONE SLIDE NEED REPLACED PRESSURE NOT IN GREEN BAND (LOW). REMOVED AND REPLACED TAIL CONE SLIDE IAW AMM 25-61.

Part: COVER — MISSING (CABIN)

THE 21DEF LENS COVER FOR EMERGENCY EXIT LIGHT MISSING ON AFT SIDE OF SEAT. INSTALLED MISSING LENS COVER IAW B717 AMM 33-51.

Part: LIGHT — MISSING (CABIN)

THE 3DEF EMERGENCY EXIT LIGHT LENS COVER MISSING AND 2 EACH BULBS MISSING. INSTALLED 2 EACH MISSING BULBS AND MISSING LENS COVER ON SEAT 3D IAW B717 AMM 33-51, OPS CHECK GOOD.

Part: PIN — MISSING (EVAC SLIDE)

L1 DOOR SECONDARY PULL TAB PIN MISSING (SLIDE). REMOVED AND REPLACED DOOR SLIDE L1 IAW M/M 25-61-01.

Part: LENS — MISSING (CABIN)

EPL LENSES MISSING AT ROW 22DEF. INSTALLED LENSES AS REQUIRED.

Part: PAD — DAMAGED (FUSELAGE)

TAIL JACK PAD FUSELAGE STRUCTURE, DAMAGED. ACCOMPLISHED FUSELAGE STRUCTURE DOUBLER AND FILLER REPAIR PER BOEING DWG SG09530002.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

GALLEY ENTRANCE FLOOR SUPPORT ANGLE, CORROSION. ACCOMPLISHED FLOOR SUPPORT ANGLE REPLACEMENT PER B717 SRM 51-41-01.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 590 TO 756, RBL 56, CORROSION. ACCOMPLISHED SEAT TRACK SPLICE REPAIR PER B717 SRM 53-20-52 FIG 3.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 775 TO 898, RBL 56, CORROSION. ACCOMPLISHED SEAT TRACK SPLICE REPAIR PER B717 SRM 53-20-52 FIG 3.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 256 TO 590, RBL 56, CORROSION. ACCOMPLISHED SEAT TRACK SPLICE REPAIR PER B717 SRM 53-20-52 FIG 3.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 896 TO 1022, RBL 56, CORROSION. ACCOMPLISHED SEAT TRACK SPLICE REPAIR PER B717 SRM 53-20-52 FIG 3.

Part: ATTACH FITTING — CORRODED (CABIN)

GALLEY ENTRANCE GIRT BAR ATTACH FITTINGS, STA 200, CORROSION. ACCOMPLISHED GIRT BAR ATTACH FITTINGS REPLACEMENT PER B717 SRM 51-41-01.

Part: ATTACH FITTING — CORRODED (GIRT BAR)

GALLEY ENTRANCE GIRT BAR ATTACH FITTINGS, STA 200, CORROSION. ACCOMPLISHED GIRT BAR ATTACH FITTINGS REPLACEMENT PER B717 SRM 51-41-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT ANGLE, STA 200, RBL 55, CORROSION. ACCOMPLISHED FLOOR SUPPORT ANGLE REPLACEMENT PER B717 SRM 51-41-02.

Part: STRAP — CORRODED (FUSELAGE)

LEFT EXTERIOR WING TO BODY SUPPORT STRAP, STA 851, CORROSION. ACCOMPLISHED EXTERIOR WING TO BODY SUPPORT STRAP REPLACEMENT PER B717 SRM 51-41-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT ANGLE, STA 200, RBL 10 TO RBL 44, CORROSION. ACCOMPLISHED FLOOR SUPPORT ANGLE REPLACEMENT PER B717 SRM 51-41-02 AND B717 SRM 51-41-05.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN CABIN ENTRANCE FLOOR SUPPORT BEAM, STA 160 TO 200, LBL 44, CORROSION. ACCOMPLISHED FLOOR SUPPORT BEAM REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

COCKPIT FLOOR SUPPORT BEAM, STA 149, RBL 11, CORROSION. ACCOMPLISHED FLOOR SUPPORT BEAM REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT BEAM, STA 200, LBL 5 TO RBL 5, CORROSION. ACCOMPLISHED FLOOR SUPPORT BEAM REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT BEAM, STA 200, LBL 11, CORROSION. ACCOMPLISHED FLOOR SUPPORT BEAM REPLACEMENT PER B717 SRM 51-41-02.

Part: CUSP WEB — CORRODED (FUSELAGE)

RIGHT CABIN CUSP WEB, STA 484 TO 503, LONG 18R, CORROSION. ACCOMPLISHED CABIN CUSP WEB DOUBLER REPAIR PER B717 SRM 51-41-02 AND BOEING DWG SG09530003.

Part: HOUSING — LEAKING (NR 1 ENGINE)

FUEL IMBALANCE EN ROUTE. LT TANK LOW FUEL, LEAKING FROM LEFT ENGINE COWL. REPLACED FUEL FILTER, FUEL FILTER HOUSING, O-RING, AND CAP HARDWARE PER AMM 73-11-01 AND EA 17-73-02088IR SECTION 1. NO LEAKS NOTED.

Part: STRUCTURE — DAMAGED (FUSELAGE)

DENT IN FUSELAGE AT STA 229 BETWEEN STRINGERS 16L AND 17L. DRILLED .1562 INCH HOLE, ACCOMPLISHED HFEC INSPECTION AND FILLED HOLE WITH FASTENER PER EA17-53-0217IR.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY LIGHTS FROM ROW 20-24 INOP. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY CHARGER AND EMERGENCY LIGHT BATTERY PER AMM 33-51-03. OPS CHECK GOOD.

Part: CONTROLLER — INOPERATIVE (CABIN PRESSURE)

DURING CLIMB THROUGH APPROX FL300, LEVEL 3 CABIN ALTITUDE ALERT APPEARED. CONDUCTED EMERGENCY DESCENT PROCEDURE AS PER QRH & LEVELED OFF AT 10,000FT, CABIN ALTITUDE NEVER EXCEEDED APPROX 10,500FT ALTHOUGH CABIN RATE ALERT APPEARED SEVERAL TIMES DURING DESCENT. REPLACED CABIN PRESSURE CONTROL PANEL, REF AMM 21-31-03. OPS CHECK GOOD. REMOVED AND REPLACED CABIN AIR OUTFLOW VALVE ACTUATOR AS PRECAUTIONARY, REF AMM 21-31, OPS CHECK GOOD.

Part: WEB — CORRODED (BS 157-218)

FOUND CORROSION AT MAIN CABIN SUB FLOOR BETWEEN STA 157 AND 218 AT SEVERAL PLACES. REMOVED WEB AND FLOOR SUPPORT, FABRICATED WEB AND FLOOR SUPPORT, AND INSTALLED FABRICATED WEB AND FLOOR SUPPORT BETWEEN STA 157 AND 218 IAW B717 SRM 51-70-10.

Part: LENS — IMPROPER PART (CABIN)

FAA FOUND ROW 21 EMERGENCY EXIT ROW HAS A WHITE LENS, RATHER THAN A RED LENSE COVER IAW MM 33-51. REPLACED WHITE LENS COVER IN ROW 21 WITH A RED LENS COVER.

Part: ACTUATOR — FAILED (RT MLG)

RIGHT HYD SYS QTY WENT TO "0" ON DESCENT. QRH PROCEDURES FOLLOWED, TOWED TO GATE. REMOVED AND REPLACED RIGHT MLG RETRACT CYC AND GLAND ASSY IAW AMM 32-33-01 AND C/W EA 17-32-009211R, OPS CHECKS GOOD. NO LEAKS NOTED C/W BOEING SERVICE BULLETIN 717-31-0013.

Part: PAN — CORRODED (FUSELAGE)

FWD CARGO COMP LOWER DOOR JAMB HAS CORROSION IN SEVERAL SPOTS. INSTALLED FWD CARGO DOOR LOWER JAMB PAN CORROSION SPLICE REPAIR PER B717 SRM 53-20-15 FIG 201. MAT USED 2024-D .050 SIZE 5 X 4.75 INCHES.

Part: FITTING — CORRODED (FUSELAGE)

VHF ANTENNA MOUNT FITTING CORRODED BETWEEN STA 906 AND 927 AT 6 O'CLOCK. REMOVED AND REPLACED VHF ANTENNA MOUNT FITTING PER B717 SRM 51-41-02.

Part: PAN — CORRODED (FUSELAGE)

AFT CARGO COMPARTMENT LOWER DOOR JAMB EXTERNAL SURFACE CORROSION IN SEVERAL SPOTS. INSTALLED AFT CARGO DOOR JAMB PAN CORROSION SPLICES REPAIR AS PER B717 SRM 53-20-15 MAT USED 7075-0 .040 SPLICE 5 X 4.75 LONG.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT)

EMERGENCY LIGHTS FROM GALLEY TO ROW 10 INOPERATIVE. REMOVED AND REPLACED BATTERY SUPPLY EMERGENCY LIGHT PER AMM 33-51-03, TESTED OPS GOOD AT THIS TIME.

Part: ENGINE — INOPERATIVE (RIGHT)

RT ENG COMP STALL ON CLIMB-OUT, ENG SHUT DOWN, HIGH TGT. REMOVED AND REPLACED RT ENG ASSY. LEAK AND OPS CK NORMAL. OK FOR SVC.

Part: POWER SUPPLY — INOPERATIVE (STA 312)

FIRST CLASS SEAT EMERGENCY LIGHTS INOPERATIVE. REMOVED AND REPLACED EMERGENCY LIGHT POWER SUPPLY AND BATTERY PACKS AT STA 312 IAW MM 33-51. OPS CK GOOD.

Part: DISPLAY — LOCKED (COCKPIT)

MCDU NR 1 AND NR 2 LOCKED UP IN FLIGHT. NO FLIGHT PLAN INFO, NO AUTOPILOT RESET. RESET ITSELF AFTER 30 MINUTES. PERFORMED RTS OF BOTH VIA'S AND AUTOPILOT SYSTEM PERFORMED AUTOLAND RTS. REINSTALLED VIA SOFTWARE AND PERFORMED RTS. SYSTEMS OPS CHECK GOOD. CLEANED COOLING HOLES ON MCDU'S.

Part: LIGHT — SMOKE (CABIN)

WHEN TESTING EMERGENCY LIGHTS, AISLE PATH LIGHTS STARTED TO SMOKE. TURNED OFF LIGHTS AND SMOKE STOPPED. RELAMPED EMERGENCY EXIT LIGHTS AT 20D, OPS CHECKED GOOD IAW 33-51.