N42836

Part: BULB — FAILED (CABIN) · airframe 41,892 hrs · 52,085 cycles

ON CLIMBOUT, CREW SMELLED BURNING ODOR, APPEARED TO BE COMING FROM WEMAC VENTS. MAINTENANCE INSPECTED THE ACFT LIGHTING SYSTEM AND FOUND THE LIGHT SOCKET ON ROW 5-AB LATERAL LIGHT BULB PINS TO BE ARCED TO SOCKET. MAINTENANCE R & R THE SOCKET AND LAMP IAW SPM CH 20-43-10.

Part: FITTING — FAILED (RT MLG) · airframe 41,392 hrs · 51,290 cycles

PILOT REPORTED WHEN THE GEAR WAS RETRACTED ON DEPARTURE THERE WAS AN UNUSUAL NOISE, GEAR WAS EXTENDED, THE WHOLE PLANE SHOOK & A LOUD NOISE CAME FROM THE RT SIDE. THE RT GEAR TOOK EXTREMELY LONG TO EXTEND. INSPECTED & FOUND THE EXTEND & RETRACT ACTUATOR TO FUSELAGE FITTING FAILED.

Part: FAN — DEFECTIVE (NR 2) · airframe 41,386 hrs · 51,281 cycles

PILOT REPORTED ON APPROACH TO LAND, RECIRCULATION FAN NR 2 FAULTED, BEFORE FAULT THERE WAS A UNIQUE SMELL. REMOVED & INSTALLED NR 2 RECIRCULATION FAN IAW 42 AMM JIC 21-22-21 RAI 10000. OPERATIONALLY TESTED GOOD IAW 21-22-21-OPT-00100. NO DISTINCTIVE SMELL NOTED AT THIS TIME.

Part: SPAR — CORRODED (RT WING) · airframe 40,855 hrs · 50,516 cycles

TEMPORARY REPAIR PERFORMED TO RT WING FWD SPAR LOWER CHORD IAW ENGINEERING STRUCTURAL REPAIR INSTRUCTION DT S-6990 14-23433 DATED NOV 18, 2014. ACFT WILL BE FERRIED WHERE IT WILL UNDERGO HEAVY CHECK & THE PERMANENT REPAIR WILL BE ACCOMPLISHED. SEE ATTACHED DOCUMENTATION FOR ENGINEERING.

Part: CONTROLLER — DIRTY (CABIN PRESSURE) · airframe 40,853 hrs · 50,513 cycles

EXCESS CABIN ALTITUDE, REPORTED THEY EXPERIENCED A CABIN DEPRESSURIZATION APPROXIMATELY 45 MILES AWAY FROM DESTINATION ON INITIAL DESCENT. THE CREW THEN DONNED O2 MASKS & FOLLOWED THE QRH & DECLARED AN EMER. LANDING WAS UNEVENTFUL. THE TOWER REPORTED THE CREW REQUESTED A LOWER ALTITUDE, ACFT WAS AT 3200 FEET & WAS ISSUED LOWER AT PILOT DISCRETION. REMOVED THE DIGITAL CONTROLLER, CLEANED CONNECTOR & PERFORMED OPERATIONS TEST IAW ATR 42 JIC 21-31-00 POT 10020.

Part: BATTERY — MALFUNCTIONED (MAIN) · airframe 40,682 hrs · 50,245 cycles

PILOT REPORTED MAIN BATTERY OFF LIGHT ILLUMINATED IN FLIGHT & NOTICED A BURNING SMELL IN COCKPIT. INSPECTED ALL ELEC POWER SYS. REMOVED & INSTALLED MAIN BATTERY, BATTERY CHARGE CONTACTOR, BATTERY PROTECTION UNIT & MAIN BATTERY CHARGE PUSH BUTTON SWITCH IAW AMM JIC 24-31-88, JIC 24-00-00 & JIC 24-31-35 AWM 24-31-04 P000.

Part: SYMBOL GENERATOR — FAULTED (NR 2) · airframe 40,671 hrs · 50,227 cycles

FIRST OFFICER`S SIDE EFIS & SGU FAIL FOLLOWED BY INTERMITTENT AHRS FAILURE. AHRS FAIL INCLUDED RADIO ATT GOING TO ZERO WITH GEAR NOT DOWN WARNING. BURNING SMELL BRIEFLY ACCOMPANIED ABNORMALITY. SMELL WAS BRIEF, 30 SEC & APPROX HALFWAY THROUGH ABNORMALITY. REMOVED & INSTALLED NR 2 SYMBOL GENERATOR, RE-RACKED AHRS IAW ATR 42 AMM JIC 34-71-82 EAI 10000. INSPECTED COCKPIT AREA & CANNOT DUPLICATE THE BURNING SMELL IAW AMM JIC 34-71-82.

Part: BATTERY — DEFECTIVE (MAIN) · airframe 40,393 hrs · 49,790 cycles

MAIN BATTERY CHARGE OFF LIGHT ILLUMINATED. MX PANEL MAIN BATTERY VOLTS SHOWED 18 VOLTS THEN READ 29. HOWEVER, LIGHT REMAINED ILLUMINATED UNTIL DESCENT 10000 FEET. STRONG BURNING SMELL IN FLIGHT DECK. MX REPLACED MAIN BATTERY. OPERATIONS TEST MAIN BATTERY PROTECTION UNIT & FOUND TO BE OK.

Part: POWER SUPPLY — DISCHARGED (EMERGENCY LIGHT) · airframe 39,058 hrs · 47,662 cycles

EMERGENCY EXIT LIGHTS DO NOT ALL ILLUMINATE DURING TEST. REPLACED POWER SUPPLY UNITS 3WL, 10WL, 15WL, 18WL, 29WL.

Part: WIRE — BROKEN (MLG) · airframe 38,831 hrs · 47,313 cycles

LANDING GEAR WOULD NOT EXTEND NORMALLY. THREE RED UNLOCKED INDICATORS REMAINED ILLUMINATED AFTER SELECTING GEAR DOWN. PERFORMED EMERGENCY LANDING GEAR EXTENSION. GEAR CAME DOWN NORMALLY AND 3 GREEN DOWN AND LOCKED INDICATION WITH NO RED UNLOCK LIGHTS ILLUMINATED. LANDED NORMALLY WITHOUT FURTHER INCIDENT. MX FOUND BROKEN WIRE AT FRAME 27 HYD PUMP BAY TO PIN B AT 13GA LANDING GEAR SELECTOR VALVE. REPAIRED BROKEN WIRE AND PERFORMED NORMAL EXTENSION AND RETRACTION AND EMERGENCY EXTENSION FUNCTION AND FOUND BOTH TO PERFORM NORMALLY.

Part: VENT LINE — CLOGGED (NR 5 BEARING) · airframe 38,756 hrs · 47,197 cycles

ON TAXI TO GATE, COCKPIT STARTED TO FILL WITH SMOKE. SELECTED BOTH BLEEDS AND BOTH PACKS TO OFF. INSPECTED NR 1 ENGINE NR 5 BEARING VENT TUBE. CLEANED CLOGGED VENT TUBE. PERFORMED ENGINE RUNUP AND FOUND TO OPERATE NORMALLY.

Part: ACCESS DOOR — DEPARTED (HYDRAULIC SYS) · airframe 37,883 hrs

PILOT REPORTED THAT WHILE CONDUCTING A POST FLIGHT REVIEW OF THE ACFT, THEY NOTED THAT THE HYD BAY ACCESS DOOR 195CL HAD DEPARTED THE ACFT IN FLIGHT. UPON MX INSPECTION, THE DOOR WAS REPLACED.

Part: SPAR CAP — CORRODED (LT WING) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK CORROSION ZL-532-GVI-10000, 572220-DVI-10000, SPOTS WERE FOUND ON LT WING AT AFT SPAR UPPER CAP VERTICAL FLANGE BETWEEN RIBS 24-26. CORROSION WAS REMOVED AND DAMAGES BLENDED IAW PREVIOUS SRI. REVIEWED REPAIRS AND ISSUED STRUCTURAL REPAIR APPROVAL SHEET (SRAS) DO/TS-3144/11...6529. REPAIRS WERE PERFORMED BY TECH SERVICES UNDER WO 17010, TASK 687. SUPPLEMENTARY INSP TASK REQUIRED: DVI OF BLENDED AREAS FOR NEW CORROSION DETECTION WITH THRESHOLD.

Part: FLOORBEAM — DAMAGED (ZONE 100) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK FLOORBEAM FR13 WAS BEING REPLACED. DURING THE INSTALLATION THE OEM DESIGNED CONTROL CABLE GUIDE THROUGH-HLOES WERE ACCIDENTALLY DRILLED ON THE WRONG (OPPOSITE) SIDE OF THE BL0. REPAIRED IAW STS EA 09-2011-227. REPAIR PERFORMED BY TECH SERVICE UNDER W/O 17077.

Part: BEAM — CRACKED (ZONE 400) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK OVERSIZED HOLES FOUND IN NR1 ENGINE LOWER COWL BEAM AT OIL LINE SUPPORT BRACKET ATTACH POINT. IN ADDITION TO OVERSIZED AND ELONGATED HOLES, THE MATERAL BETWEEN HOLES WAS FOUND TO BE CRACKED, WITH CRACKS TERMINATING AT EACH HOLE. REPAIRED IAW STS EA 10-2011-141. REPAIR PERFORMED BY TECH SERVICES UNDER W/O 17077.

Part: PANEL — CRACKED (FUSELAGE) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK, TOILET COMPARTMENT PANEL NR261EW FOUND CRACKED IN 3 PLACES. PANEL REPAIRED IAW STS EA 12-2011-020. REPAIR PERFORMED BY COMPOSITE SHOP UNDER W/O 17010.

Part: STRUCTURE — DEBONDED (ZONE 900) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK THE TRANSVERSE LAVATORY WALL WAS FOUND WITH A LARGE AREA OF DISBOND. WALL REPAIRED IAW EA 14-2011-003. REPAIRS PERFORMED BY TECH SERVICE (MRO) COMPOSITE SHOP UNDER W/O 17010.

Part: SKIN — CORRODED (ZONE 100) · airframe 36,410 hrs · 43,608 cycles

CORROSION WAS FOUND ON LOWER SKIN AT FRAME 31. CORROSION WAS REMOVED IAW SRM 51-21-58 AND FOUND TO BE OUT OF LIMITS. REPAIRED IAW EA 12-2011-018. REPAIR PERFORMED BY TECH SERVICES UNDER W/O 17010. DTA EVALUATION TO BE ACCOMPLISHED WITH IN 12 MONTHS IAW AC 120-93.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK CORROSION FOUND ON EXTERIOR SURFACE OF LT FWD KEEL SKIN AT THE LT ECS CUT OUT. REMOVED CORROSION IAW SRM 51-21-58 AND FOUND TO BE OUT OF LIMITS. REPAIRED IAW STS ENGINEERING SOLUTIONS EA 12-2011-041. REPAIR PERFORMED UNDER W/O 17010.

Part: FRAME — CRACKED (ZONE 200) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK A CRACK WAS FOUND ON THE LT SIDE OF THE UPPER FRAME 28. THE DAMAGE CONSISTS OF A SINGLE CRACK THAT STARTS MIDWAY DOWN THE WEB RUNNING 1.6" THROUGH A .098" HOLE AND INTO THE AFT FACING FLANGE 0.6". REPAIRED IAW STS ENGINEERING SOLUTIONS EA 12-2011-010. REPAIR PERFORMED BY TECH SERVICE (MRO) UNDER W/O 17010.

Part: FRAME — DAMAGED (ZONE 100) · airframe 36,410 hrs · 43,601 cycles

DURING HEAVY CHECK, RT SPONSON FRAME WAS DAMAGED. SPONSON FRAME WAS REPAIRED IAW EA 09/2011-184. REPAIR PERFORMED BY TECH SERVICE (MRO) UNDER W/O 17077.

Part: SKIN — CORRODED (ZONE 100) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK CORROSION WAS FOUND ON LOWER SKIN AT FRAME 31. CORROSION WAS REMOVED IAW SRM 51-21-58 AND FOUND TO BE OUT OF LIMITS. REPAIRED IAW STS ENGINEERING SOLUTIONS EA 12-2011-018. REPAIR PERFORMED BY TECH SERVICE (MRO) UNDER W/O 17010.

Part: PANEL — CRACKED · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK SEVERAL CRACKS FOUND ON THE FACE OF INTERIOR PANEL NR261DW. PANEL WAS REPAIRED IAW STS EA 12-2011-019. REPAIR PERFORMED BY ACFT TECH SERVICES (MRO) COMPOSITE SHOP UNDER W/O 17010.

Part: COWLING — CRACKED (ZONE 400) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK A CRACK WAS FOUND ON A BEAM IN THE LT LOWER ENGINE COWLING. THE DAMAGE CONSISTS OF A SINGLE CRACK 1.8" LONG THAT RUNS BETWEEN 2 LIGHTNING HOLES IN THE BEAM. THE CRACK WAS REPAIRED IAW STS ENGINEERING SOLUTIONS EA 12-2011-013. REPAIR PERFORMED BY TECH SERVICES UNDER W/O 17010.

Part: TUBE — CHAFED (ZONE 400) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK, NR1 ENGINE NR7 MOUNT TUBE FOUND CHAFED. BLENDED IAW ATR 42-320, SRM 54-21-00. ORIGNAL THICKNESS OF TUBE IS .0632", THICKNESS AFTER BLENDING IS .0551" AND WITH IN LIMITS. WORK PERFORMED BY ACFT TECH SERVICE UNDER W/O 17010.

Part: PANEL — DEBONDED (ZONE 900) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK THE LONGITUDINAL LAVATORY WALL WAS FOUND WITH A LARGE AREA OF DISBOND. WALL REPAIRED IAW STS ENGINEERING SOLUTIONS EA 14-2011-003. REPAIRS PERFORMED BY TECH SERVICE (MRO)COMPOSITE SHOP UNDER W/O 17010.

Part: PANEL — DELAMINATED (FUSELAGE) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK NR1 OTBD LATERAL PANEL WAS FOUND TO HAVE A LARGE DELAMINATION OVER THE CORE. PANEL REPAIRED IAW STS ENGINEERING SOLUTIONS EA 12-2011-023. REPAIR PERFORMED BY COMPOSITE SHOP UNDER W/O 17010.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK CORROSION FOUND ON EXTERIOR SURFACE OF FORWARD KEEL SKIN AT RT ECS CUTOUT. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW SRM. REPAIR PREFORMED IAW STS ENGINEERING SOULTIONS EA 12-2011-43. REPAIR PERFORMED BY TECH SERVICES UNDER W/O 17010.

Part: FRAME — CRACKED (ZONE 200) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK A CRACK WAS FOUND ON THE LT SIDE OF UPPER FRAME 28. REPAIRED IAW EA 12-2011-010. REPAIR PERFORMED BY TECH SERVICES (MRO) UNDER W/O 17010. DTA EVALUATION TO BE ACCOMPLISHED WITHIN 12 MONTHS IAW AC120-93.

Part: SINK — CRACKED (LAVATORY) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK LAVATORY WASH BASIN WAS FOUND TO BE CRACKED. THE DAMAGE CONSISTS OF 4 CRACKS. DAMAGE REPAIRED IAW STS ENGINEERING SOLUTIONS EA 12-2011-022. REPAIR PERFORMED BY TECH SERVICE (MRO) UNDER W/O 17010.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK CORROSION WAS FOUND ON THE LOWER SKIN AT VHF2 ANTENNA LOCATION. THE CORROSION WAS REMOVED IAW SRM 51-21-58 AND FOUND TO BE OUT OF LIMITS. REPAIR DOUBLER FABRICATED AND INSTALLED IAW STS ENGINEERING SOLUTIONS EA 12-2011-012. REPAIR PERFORMED BY ACFT TECH SERVICES (MRO) UNDER W/O 17010..

Part: SKIN — CORRODED (ZONE 100) · airframe 364,100 hrs · 43,608 cycles

DURING HEAVY CHECK, CORROSION WAS FOUND ON LOWER SKIN AT FRAME 45. REPAIRED IAW STS EA 12-2011-017, REV A. REPAIR PERFORMED BY TECH SERVICES UNDER W/O 17010. DTA TO BE ACCOMPLISHED WITHIN 12 MONTHS IAW AC 120-93.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK, CORROSION WAS FOUND ON LOWER SKIN AT FRAME 45 BETWEEN STRINGERS 20R AND 20L. CORROSION WAS REMOVED IAW SRM 51-21-58 AND FOUND TO BE OUT OF LIMITS. DOUBLER FABRICATED AND INSTALLED IAW STS ENGINEERING SOLUTIONS EA 12-2011-017. REPAIR PERFORMED BY ACFT TECH SREVICES (MRO) UNDER W/O 17010.

Part: SKIN — CORRODED (ZONE 100) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK COROSION WAS FOUND ON THE LOWER SKIN AT VHF2 ANTENNA LOCATION. THE CORROSION WAS REMOVED IAW SRM 51-21-58 AND FOUND TO BE OUT OF LIMITS. REPAIR DOUBLER FABRICATED AND INSP IAW STS ENGINEERING SOLUTIONS EA 12-2011-012. REPAIRS PERFORMED BY TECH SERVICES UNDER W/O 17010. DTA EVALUATION TO BE ACCOMPLISHED IN 12 MONTHS IAW AC 120-93.

Part: SKIN — DAMAGED (ZONE 100) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, LT AND RT FUSELAGE SKIN WAS DAMAGED BY DRILL MARKS BETWEEN FRAMES 39 TO 42 BELOW STRINGER 14. DAMAGE EXCEED LIMITATIONS. SUBMITTED INFORMATION WHICH ISSUED S.R.I. DO/TS-5488/11-16116 FOR REPAIR SPECIFICATIONS. DAMAGED SKIN WAS CUT OUT NEW SKIN FABRICATED WITH DOUBLERS BY TECH SERVICES UNDER W/O 17010, TASK 965 ON BOTH THE LT AND RT FUSELAGE SKINS. REPAIRS SUBMITTED AND APPROVED UNDER STRUCTURAL REPAIR APPROVAL SHEET (SRAS) DO/TS-5488/11...6753. SUPPLEMENTARY INSPECTIONS TASK: DVI OF LT AND RT DOUBLER JOINTS FROM INSIDE AND OUTSIDE WITH THRESHOLD OF 24000 FLTS FROM REPAIR AND INTERVAL OF 18000 FLIGHTS THERE AFTER.

Part: FRAME — CORRODED (ZONE 100)

DURING HEAVY CHECK INSPECTION, CORROSION WAS FOUND ON MLG FAIRING RT WEB SEGMENT AT FRAME 29. CORROSION WAS OUT OF LIMITS PER THE SRM 51-21-58. CORRODED FRAME WAS CUT OUT AND NEW PORTION SPLICED IN.

Part: SPAR — CORRODED (LT WING) · airframe 36,410 hrs · 43,608 cycles

LT WING-AFT SPAR LOWER CAP HORIZ FLANGE CORROSION BETWEEN RIBS 18-19. DAMAGE BEYOND THE LIMITS IAW THE SRM. DAMAGED SPAR CAP REPLACED IAW REPAIR.

Part: FLOOR PANEL — PUNCTURED · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK, FLOOR PANEL 222CZ REMOVED FOR MX. FOUND IMPACT DAMAGE AND 2 PUNCTURES IN THE FLOOR PANEL. 1 WAS 0.5 " IN LENGTH AND SECOND 1.0" IN LENGTH. REPAIRED IAW EA 12-2011-021.

Part: SKIN — CRACKED (PAX DOOR) · airframe 36,410 hrs · 43,608 cycles

DURING MX, PASSENGER DOOR INTERIOR SKIN WAS FOUND CRACKED, APPROX 2.25" IN LENGTH RUNNING IN THE UP/DOWN DIRECTION. CRACK THRU INNER SKIN ONLY. REPAIRED IAW STS EA 10-2011-088.

Part: SKIN — CORRODED (EMERGENCY EXIT) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK, CORROSION WAS FOUND ON THE EMERGENCY HATCH INNER SKIN AFT OF FRAME 9 AT STA 5136, INBD OF STRINGER 2R. CORROSION REMOVED IAW SRM 51-21-58 AND EXCEEDED THE LIMITS OF THE SRM. THE DAMAGE CONSISTS OF A .50" DIA HOLE IN THE INNER SKIN. REPAIRED IAW STS EA 12-2011-011.

Part: PANEL — CRACKED (INTERIOR) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, LT BASEBOARD DADO PANELS 241DW WERE FOUND TO HAVE SMALL CRACKS ALONG THE BOTTOM AND MISSING MATERIAL THAT WERE BEYOND SRM LIMITS. REPAIRS WERE MADE TO THE PANELS UNDER EA 09-2011-257.

Part: PANEL — CRACKED (INTERIOR) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, RT BASEBOARD DADO PANELS 252CW, 252AW, AND 242EW WERE FOUND TO HAVE SMALL CRACK ALONG THE BOTTOM THAT WERE BEYOND SRM LIMITS. REPAIRS WERE MADE TO THE PANELS UNDER EA 09-2011-260.

Part: PANEL — CRACKED (INTERIOR) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, RT BASEBOARD DADO PANELS 232FW,232JW, AND 242AW WERE FOUND TO HAVE SMALL CRACK ALONG THE BOTTOM THAT WERE BEYOND SRM LIMITS. REPAIRS WERE MADE TO THE PANELS UNDER EA 09-2011-258.

Part: PANEL — CRACKED (CABIN) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, LT BASEBOARD DADO PANELS 231FW, AND 2231JW WERE FOUND TO HAVE SMALL CRACKS ALONG THE BOTTOM AND UPPER ANGLE THAT WERE BEYOND SRM LIMITS. REPAIRS WERE MADE TO THE PANELS UNDER EA 09-2011-259.

Part: PANEL — CRACKED (INTERIOR) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, LT BASEBOARD DADO PANELS 251AW, 251CW, AND 251EW WERE FOUND TO HAVE SMALL CRACK ALONG THE BOTTOM AND MISSING THAT WERE BEYOND SRM LIMITS. REQUEST FOR REPAIRS WERE SUBMITTED TO STS ENGINEERING SOLUTIONS. REPAIRS WERE MADE TO THE PANELS UNDER EA 09-2011-256. TECH SERVICES UNDER WO 17010, TASK 597.

Part: PANEL — CRACKED (FUSELAGE) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, RT BASEBOARD DADO PANELS 242DW AND 242AW WERE FOUND TO HAVE SMALL CRACK ALONG THE BOTTOM THAT WERE BEYOND SRM LIMITS. REQUEST FOR REPAIRS WERE SUBMITTED TO STS ENGINEERING SOLUTIONS. REPAIRS WERE MADE TO THE PANELS UNDER EA 09-2011-255 BY TECH SERVICES UNDER WO 17010, TASK 596.

Part: SPAR CAP — CORRODED (RT WING) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP RT WING AFT SPAR UPPER CAP WAS CORRODED REF:ZL-632-GVI-10000/572220-DVI-10000 BEYOND LIMITS IAW THE SRM 57-22-00. DAMAGE WAS SUBMITTED THEN ISSUED S.R.I. DO/TS-3027/11-15459. REPAIR WAS PERFORMED BY TECH SERVICES UNDER W/O 17010, TASK 674. REPAIRS WERE SUBMITTED AND APPROVED UNDER STRUCTURAL REPAIR APPROVAL SHEET (SRAS) D0/TS-3027/11...6532. SUPPLEMENTARY INSPECTION TASK: DVI OF BLENDED AREAS FOR NEW CORROSION DETECTION WITH THRESHOLD INTERVAL 2 YEARS.

Part: SKIN — CORRODED (ZONE 500) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, CORROSION WAS FOUND ON LT WING LOWER SKIN AT AFT SPAR NEAR RIBS 6-7. CORROSION WAS REMOVED AND BLENDED IAW SRI REF: DP/TS-3-3/11-15470 BY TECH SERVICES UNDER W/O 17010. APPROVED UNDER STRUCTURAL REPAIR APPROVAL SHEET (SRAS) DO/TS-30300/11...6528. SUPPLEMENTARY INSP TASK: DVI OF BLENDED AREA FOR NEW CORROSION WITH THRESHOLD.

Part: SKIN — CORRODED (ZONE 500) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSPECTION, CORROSION WAS FOUND ON LT WING LOWER SKIN AT AFT SPAR NEAR RIBS 4 AND 7. CORROSION WAS REMOVED AND BLENDED IAW SRI REF: DP/TS-3-3/11-15470 BY TECH SERVICES UNDER W/O 17010. APPROVED UNDER STRUCTURAL REPAIR APPROVAL SHEET (SRAS) DO/TS-30300/11...6527. SUPPLEMENTARY INSPECTION TASK: DVI OF BLENDED AREA FOR NEW CORROSION.

Part: SKIN — CORRODED (ZONE 100) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK, CORROSION WAS FOUND ON THE LOWER SKIN AT FRAME 27 AD BL 0.0 BETWEEN STRINGERS 21R AND 21L. THE CORRIOSION EXCEEDED THE LIMITS OF THE SRM. REPAIR DEFINITIONS WERE REQUESTED. ISSUED EA 12-2011-016 WHICH CALLED OUT FOR THE REMOVAL OF THE HFEC INSP AND OR A DYE PENETRANT INSPECTION. REPAIR OF THE AREA CONSISTED OF ADDING DOUBLER TO THE SKIN AS CALLED OUT BY THE EA ALL REPAIRS.

Part: SPAR CAP — CORRODED (ZONE 600) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP ZL-530/533-GVI-10000, 5722220-DVI-10000, CORROSION WAS FOUND ON RT WING AFT SPAR LOWER CAP VERTICAL FLANGE BETWEEN RIBS 24 AND 25. CORROSION WAS REMOVED, BLENDED AND INSPECTED USING UT INSP. REMAINING THICKNESS WAS SUBMITTED FOR EVAULUATION UNDER SRI DO/TS-4349/11-5786 AND FOUND TO BE WITHIN LIMITS. ISSUED STRUCTURAL REPAIR APPROVAL SHEET (SRAS) DO/TS-4349/11...6760. SUPPLEMENTARY INSP TASK: DVI OF BLENDED AREAS FOR NEW CORROSION DETECTION WITH THRESHOLD INTERVAL 2 YEARS.

Part: FRAME — CORRODED (ZONE 100) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, CORROSION WAS FOUND ON FUSELAGE FRAME 25 LOWER FLANGE AT STRINGER 20 THAT WAS BEYOND THE SRM LIMITS. REPAIRED IAW STRUCTURAL REPAIR APPROVAL SHEET (SRAS) SO/TS-2865/11...6640.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSPECTIONS ZL-261-GVI-10000, MULTIPLE CORROSION SPOTS WERE FOUND ON INNER SURFACE OF FUSELAGE SKIN BETWEEN FRAMES 40 TO 44 STRINGERS 5-13 LT SIDE. 4 CORRODED AREAS BLENDED OUT IAW INSTRUCTIONS DO/TS-4390/11-15789. 3 CORRODED SPOTS REPAIRED IAW SRM PRINCIPLES 53-00-00, FIG 401/402/403 AND TEN OTHERS SPOTS BLENDED OUT FOLLOWING INSTRUCTIONS DO/TS-4458/11.15789 AND EMAIL REF DATED AUG-01-2011. T3 LAST CORROSION SPOTS ON SECTION 18 CUT-OUT AND EXTERNAL DOUBLER INSTALLED IAW INSTRUCTIONS OITS-4727/11-15789. ALL REPAIRS CONFIRMED WITHOUT DEVIATION BY EMAIL REF. ANA/E/6404/20114-004, /E-005 AND/E-006. ISSUE C: PERFORATED MACHINED DOUBLER UNDER FRAME, 41 BTW STR 11-12 LTS BLEND-OUT AND INSPECTED FOLLOWING INSTRUCTION REF DT/S-359/11-16319 AS CONFIRMED BY EMAIL ANA REF. ANA/E/6404/20LL/E-010. ALL REPAIRS APPROVED BY ART UNDER SRAS DO/TS-4727/11...6639 AND PERFORMED USING ABOVE INSTRUCTIONS UNDER W/O 17077 TASKS 11-14, 16-18, 23-27, AND 29. SUPPLEMENTARY INSP TASK: INTERVAL DVI OF BLENDED AREA FOR NEW CORROSION WITH THRESHOLD INTERVAL 2 YEARS.

Part: SPLICE — DAMAGED (ZONE 200) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK, A NEW CENTER WING SPLICE PLATE WAS DROPPED AND THE AFT RT CORNER WAS DAMAGED BEYOND SRM LIMITS. REPAIR DAMAGE WAS SUBMITTED, AN EA WAS ISSUED TO REPAIR THE DAMAGED CORNER UNDER EA 09-2011-191. DAMAGE WAS REPAIRED UNDER WO 17010, TASK 913.

Part: BULKHEAD — DAMAGED (BS 2692) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, A DAMAGED NUT PLATE AND ELONGATED HOLE WAS FOUND ON THE FORWARD PRESSURE BULKHEAD AT STA 2692, LWR B.L 0.0, THE ELONGATE HOLE WENT THROUGH THE BULKHEAD WEB AND SPLICE. DAMAGE WAS OUT OF LIMITS IAW THE SRM, REPAIRED IAW EA 10-2011-089.

Part: SKIN — CORRODED (ZONE 100) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, CORROSION WAS FOUND OUT OF LIMITS IAW SRM ON THE FUSELAGE SKIN SURFACE LOCATED AFT OF STA 9510 AT BL0.0 BETWEEN STRINGERS 21L AND 21R. REPAIR CONSIDERATION WAS SUBMITTED, ISSUED EA 10-2011-087. CORROSION WAS REMOVED AND ALL REPAIRS WERE MADE.

Part: SPAR — CORRODED (LT WING) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, CORROSION WAS FOUND ON LT WING AFT SPAR UPPER HORIZ FLANGE AND UPPER SKIN AT RIP 29. THE CORROSION WAS REMOVED AND DAMAGE BLENDED IAW ATR S.R.I. DO/TS-3042/11-15468. THE REPAIR WAS PERFORMED BY TECH SERVICES UNDER WO 17010, TASK 323. APPROVED UNDER STRUCTURAL REPAIR APPROVAL SHEET (SRAS) DO/TS-3042/11...6531. SUPPLEMENTARY INSP TASK: DVI OF BLENDED AREAS FOR NEW CORROSION WITH THRESHOLD.

Part: SKIN — CORRODED (ZONE 100) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK, CORROSION WAS FOUND ON THE EXTERIOR SURFACE OF THE LOWER FUSELAGE SKIN BETWEEN FRAME 46 AND FRAME 47 BETWEEN STRINGERS 20L AND 20R. CORROSION WAS REMOVED IAW SRM 51-21-58 AND EXCEEDED THE LIMITS OF THE SRM. SKIN WAS FOUND TO BE WITHIN ACCEPTABLE LIMITS IAW STS EA 12-11-015-A. AREA WAS ALODINED, PRIMED AND FINISH PAINTED TO PROTECT THE AREA.

Part: SPAR CAP — CORRODED (RT WING) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSPECTION CORRIOSON WAS FOUND ON THE RT WING AT THE AFT SPAR UPPER CAP VERTICAL FLANGE BETWEEN RIBS 27-30. CORROSION WAS FOUND TO BE OUT OF THE LIMITS OF THE SRM AND REQUEST FOR STRUCTURAL REPAIR INSTRUCTION WAS SUBMITTED. CORROSION WAS REMOVED AND DAMAGES BLENDED USING SRI DO/TS-3407/11-15469 ISSUE A AND SUBMITTED FOR APPROVAL. STRUCTURAL REPAIR APPROVAL SHEET (SRAS) DO/TS-3407/11...6533 WAS ISSUED. ALL WORK COMPLETED BY TECH SERVICES UNDER WO 17010, TASK 220. SUPPLEMENTARY INSP TASK: DVI OF BLENDED AREAS FOR NEW CORROSION DETECTION WITH THRESHOLD INTERVAL OF 2 YEARS.

Part: RIB — CORRODED (VERTICAL STAB) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP FOUND VERTICAL STABILIZER LOWER RIB FLANGE IN CORRESPONDENCE TO THE 3 SPAR FITTINGS, WERE CORRODED BEYOND LIMITS. INSPECTION REF:ZL-324-GVI-10000/553601-DVI-10000 BEYOND LIMITS IAW SRM 57-36-00. DAMAGE WAS SUBMITTED THEN ISSUED S.R.I. DO/TS-2953/11-15435. REPAIR WAS PERFORMED BY TECH SERVICES UNDER W/O 17010, TASK 675. REPAIRS WERE SUBMITTED AND APPROVED UNDER STRUCTURAL REPAIR APPROVAL SHEET (SRAS) D0/TS-2953/11...6641.

Part: WINDOW FRAME — DAMAGED (ZONE 200) · airframe 36,410 hrs · 43,608 cycles

DURING HEAVY CHECK INSP, FUSELAGE WINDSHIELD NODE 5 LT AND RT SILL FITTINGS AND WINDOW FRAME WERE FOUND DAMAGED AND CORRODED DURING ZONAL INSPECTIONS ZL-211-GVI-10000/10100/10020/10030. DAMAGE WAS OUT OF LIMITS AND SUBMITTED. DAMAGE WAS BLENDED OUT BY TECH SERVICES UNDER W/O 17077, TASK 61. REPAIRS WERE SUBMITTED AND APPROVED UNDER STRUCTURAL REPAIR APPROVAL SHEET (SRAS) D0/TS-2908/11...6746 DATED 21 OCT 2011.

Part: FITTING — CORRODED (TE FLAP) · airframe 31,410 hrs · 35,687 cycles

LEFT OUTBOARD FLAP FORWARD PICK UP FITTING AT FLAP RIB 18 VERTICAL WEB EDGE CORROSION. REPAIRED PER ATR STRUCTURAL REPAIR INSTRUCTIONS.

Part: FRAME — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

CORROSION AND BARE METAL FOUND AT BELLY FRAME 28. CORROSION REMOVED FROM BELLY FRAME 28 RIGHT AND LEFT WEB. BELLY FRAME 28 LEFT AND RIGHT WEBS REPLACED IN ACCORDANCE WITH SRM.

Part: STIFFENER — CRACKED (NLG DOOR) · airframe 31,410 hrs · 35,687 cycles

STIFFENER BROKEN ON FORWARD LEFT SIDE OF NOSE LANDING GEAR DOOR. LEFT AFT NOSE LANDING GEAR DOOR STIFFENER REPLACED IN ACCORDANCE WITH SRM.

Part: SKIN — CORRODED (PAX DOOR) · airframe 31,410 hrs · 35,687 cycles

PASSENGER DOOR INNER SKIN CORRODED AT TOP AFT CORNER. PASSENGER DOOR INNER SKIN REPAIRED AT TOP AFT CORNER AND CORROSION REMOVED.

Part: FRAME SPLICE — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

CORROSION FOUND ON BELLY FRAME 27. CORROSION REMOVED, FRAME REPAIRED IN ACCORDANCE WITH SRM.

Part: PAN — CORRODED (PAX DOOR) · airframe 31,410 hrs · 35,687 cycles

PASSENGER DOOR UPPER PAN CORRODED NEAR BONDING STRIP. PASSENGER DOOR UPPER PAN CORROSION REMOVED AND REPAIRED IN ACCORDANCE WITH SRM.

Part: ARM — CORRODED (TE FLAP) · airframe 31,410 hrs · 35,687 cycles

LEFT OUTBOARD FLAP ARM CORRODED AT RIB 18. CORROSION REMOVED FROM LEFT OUTBOARD FLAP ARM RIB 18 IAW SRM. PERFORMED EDDY CURRENT, NO CRACKS FOUND. LEFT OUTBOARD FLAP ARM AT RIB 18 REPAIRED IN ACCORDANCE WITH ATR STRUCTURAL REPAIR INSTRUCTIONS.

Part: PAN — CRACKED (CARGO DOOR) · airframe 31,410 hrs · 35,687 cycles

THE LOWER FORWARD CARGO DOOR PAN CRACKED. REPAIRED IN ACCORDANCE WITH ATR DRAWING NR 13S523R0028.

Part: SUPPORT FITTING — CRACKED (CARGO DOOR) · airframe 31,410 hrs · 35,687 cycles

CARGO DOOR PAN CRACKED AT STRUT SUPPORT FITTING LOCATION. CARGO DOOR PAN AT STRUT FITTING LOCATION REPAIRED IN ACCORDANCE WITH SRM.

Part: ARM — CORRODED (TE FLAP) · airframe 31,410 hrs · 35,687 cycles

RIGHT INBOARD FLAP ARM CORRODED AT RIB 5. REMOVED CORROSION AND PERFORMED EDDY CURRENT INSPECTION, NO CRACKS FOUND. REPAIRED FLAP ARM IN ACCORDANCE WITH ATR STRUCTURAL REPAIR INSTRUCTIONS.

Part: FRAME — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

FRAME 44 AFT FACE CORRODED AT JUNCTION OF LEFT AND RIGHT SEAT TRACK, FOUND TO BE OUT OF LIMITS. NEW FRAME SEGMENT WAS SPLICED IN, IN ACCORDANCE WITH SRM.

Part: STIFFENER — CORRODED (AFT BULKHEAD) · airframe 31,410 hrs · 35,687 cycles

AFT PRESSURE BULKHEAD FORWARD FACE (3) LOWER STIFFENERS CORRODED. CORROSION REMOVED, 2 STIFFENERS FOUND TO BE WITHIN LIMITS, 1 REMOVED AND REPLACED IN ACCORDANCE WITH SRM.

Part: SKIN — CRACKED (SERVICE DOOR) · airframe 31,410 hrs · 35,687 cycles

SERVICE DOOR EXTERNAL SKIN CRACKED AT FORWARD LOWER CORNER. SERVICE DOOR SKIN REPAIRED IN ACCORDANCE WITH SRM.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

RIGHT BETWEEN FRAMES 41 AND 44 UPPER CHORD CORRODED. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED CHORD IN ACCORDANCE WITH SRM.

Part: HINGE FITTING — CORRODED (TE FLAP) · airframe 31,410 hrs · 35,687 cycles

LEFT OUTBOARD FLAP, HINGE ARE AT FLAP RIB 18 UPPER AFT LUG CORROSION. REPAIRED PER ATR STRUCTURAL REPAIR INSTRUCTIONS.

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 31,410 hrs · 35,687 cycles

EMERGENCY LIGHT POWER SUPPLY BATTERY FAILED CAPACITY CHECK. REMOVED AND REPLACED BATTERY.

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 31,410 hrs · 35,687 cycles

EMERGENCY LIGHT POWER SUPPLY BATTERY FAILED CAPACITY CHECK. REMOVED AND REPLACED BATTERY.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

RIGHT SIDE BETWEEN FRAMES 39 AND 41 ZEE FLOOR SUPPORT CORRODED. CORROSION FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED ZEE FLOOR SUPPORT IN ACCORDANCE WITH SRM.

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 31,410 hrs · 35,687 cycles

EMERGENCY LIGHT POWER SUPPLY BATTERY FAILED CAPACITY CHECK. REMOVED AND REPLACED BATTERY.

Part: SKIN PANEL — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

EXTERNAL SKIN UNDER TCAS ANTENNA TOP OF FRAME 16-17 HAS CORROSION. CORROSION REMOVED AND FOUND TO BE WITHIN LIMITS IN ACCORDANCE WITH SRM.

Part: HINGE — BROKEN (LE FLAP) · airframe 31,410 hrs · 35,687 cycles

LEADING EDGE 511 HINGE BROKEN. REMOVED AND REPLACED HINGE IAW SRM.

Part: BATTERY — FAILED (EMERGENCY LIGHT) · airframe 31,410 hrs · 35,687 cycles

EMERGENCY LIGHT POWER SUPPLY BATTERY FAILED CAPACITY CHECK. REMOVED AND REPLACED BATTERY.

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 31,410 hrs · 35,687 cycles

EMERGENCY LIGHT POWER SUPPLY BATTERY FAILED CAPACITY CHECK. REMOVED AND REPLACED BATTERY.

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 31,410 hrs · 35,687 cycles

EMERGENCY LIGHT POWER SUPPLY BATTERY FAILED CAPACITY CHECK. REMOVED AND REPLACED BATTERY.

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 31,410 hrs · 35,687 cycles

EMERGENCY LIGHT POWER SUPPLY BATTERY FAILED CAPACITY CHECK. REMOVED AND REPLACED BATTERY.

Part: LIGHT — FAILED (CABIN) · airframe 31,410 hrs · 35,687 cycles

EMERGENCY LIGHT ON PAX DOOR NOT WORKING. REMOVED AND REPLACED EMERGENCY LIGHT.

Part: CREASE BEAM — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

LEFT CREASE BEAM INNER CHORD BETWEEN FRAME 17 AND 20 CORRODED. CORROSION REMOVED AND FOUND TO BE WITHIN LIMITS CREASE BEAM INNER CHORD REPAIRED PER SRM.

Part: CREASE BEAM — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

FORWARD CARGO RIGHT CREASE BEAM INNER CHORD ANGLE BETWEEN FRAMES 13 AND 23, STRINGER RIGHT 14 CORRODED. CORROSION REMOVED AND FOUND TO BE WITHIN LIMITS CREASE BEAM CHORD REPAIRED PER SRM.

Part: SEAL DEPRESSOR — CRACKED (SERVICE DOOR) · airframe 31,410 hrs · 35,687 cycles

SERVICE DOOR LOWER FORWARD CORNER SEAL DEPRESSOR CRACKED. SEAL DEPRESSOR REMOVED AND REPLACED PER SRM.

Part: DOOR — OUT OF TOLERANCE (L EMER EXIT) · airframe 31,410 hrs · 35,687 cycles

LEFT EMERGENCY EXIT DOOR LATCH HANDLE FOUND HARD TO OPEN AND OPENING WEIGHT OUT OF LIMITS. LUBRICATED AND FUNCTIONALLY TESTED AND FOUND TO BE IN SERVICEABLE CONDITION.

Part: SEAL DEPRESSOR — CRACKED (SERVICE DOOR) · airframe 31,410 hrs · 35,687 cycles

SERVICE DOOR AFT LOWER CORNER SEAL DEPRESSOR CRACKED. REPLACED SERVICE DOOR SEAL DEPRESSOR IN ACCORDANCE WITH SRM.

Part: SPAR — CORRODED (WING) · airframe 31,410 hrs · 35,687 cycles

RIGHT FRONT SPAR AT RIB 12 INBOARD, AND LEFT FRONT SPAR AT RIB 10, BOLTS FOUND CORRODED. REMOVED AND REPLACED BOLTS AT RIB 10 AND 12.

Part: SHIM — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

SHIM BETWEEN STRINGER 15 AND SKIN AT FRAME 41 CORRODED. REMOVED AND FABRICATED SHIM IN ACCORDANCE WITH SRM.

Part: SEAL DEPRESSOR — CRACKED (CARGO DOOR) · airframe 31,510 hrs · 35,687 cycles

CARGO DOOR LOWER AFT SEAL DEPRESSOR CRACKED. REMOVED AND REPLACED IN ACCORDANCE WITH SRM.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

FOUND FLOORBEAM FRAME 40 CORRODED. CORROSION REMOVED AND FOUND TO BE OUT OF LIMITS. REPAIRED FLOORBEAM IN ACCORDANCE WITH SRM.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

FLOORBEAM AT FRAME 40 CORRODED. CORROSION REMOVED AND FOUND TO BE OUT OF LIMITS. FLOORBEAM REPAIRED IN ACCORDANCE WITH SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

CORROSION FOUND ON SEAT TRACK RIGHT SIDE BETWEEN FRAMES 36 AND 39. CORROSION OUT OF LIMITS, FABRICATED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

CORROSION FOUND ON SEAT TRACK LEFT SIDE BETWEEN FRAMES 39 TO 41. CORROSION FOUND TO BE OUT OF LIMITS. FABRICATED SEAT TRACK AND REPLACED PER SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

CORROSION FOUND ON SEAT TRACK LEFT OUTBOARD SIDE BETWEEN FRAMES 13 AND 23. CORROSION REMOVED AND FOUND TO BE OUT OF LIMITS. SEAT TRACK REPLACED PER SRM.

Part: INTERCOSTAL — CRACKED (PAX DOOR) · airframe 31,410 hrs · 35,687 cycles

PASSENGER DOOR SPRING ATTACH POINT LOWER INTERCOSTAL CRACKED. REMOVED AND REPLACED INTERCOSTAL.

Part: BOLT — CHIPPED (SERVICE DOOR) · airframe 31,410 hrs · 35,687 cycles

SERVICE DOOR LOWER AFT SHOOT BOLT CHIPPED. SERVICE DOOR LOWER SHOOT BOLT REPLACED IN ACCORDANCE WITH AMM.

Part: ATTACH FITTING — CRACKED (EMERGENCY EXIT) · airframe 31,410 hrs · 35,687 cycles

RIGHT EMERGENCY EXIT, FORWARD ATTACHMENT POINT CRACKED. REMOVED AND REPLACED EMERGENCY EXIT FORWARD ATTACHMENT POINT IN ACCORDANCE WITH SRM.

Part: SEAT TRACK — CORRODED (FUELAGE) · airframe 31,410 hrs · 35,687 cycles

CORROSION FOUND ON SEAT TRACK RIGHT BETWEEN FRAMES 39 AND 40. CORROSION FOUND TO BE OUT OF LIMITS. FABRICATED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

CORROSION FOUND ON SEAT TRACK RIGHT SIDE OUTBOARD SIDE BETWEEN FRAMES 13 AND 23. CORROSION REMOVED AND FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM.

Part: THRESHOLD — CORRODED (FUELAGE) · airframe 31,410 hrs · 35,687 cycles

RIGHT THRESHOLD BETWEEN FRAMES 36 AND 39 CORRODED. CORROSION REMOVED AND FOUND TO BE OUT OF LIMITS. FABRICATED AND INSTALLED THRESHOLD.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

CORROSION FOUND ON SEAT TRACK LEFT OUTBOARD SIDE BETWEEN FRAME 29 TO 36. CORROSION FOUND TO BE OUT OF LIMITS SEAT TRACK REPLACED PER SRM.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 31,410 hrs · 35,687 cycles

FLOORBEAM FRAME 39 CORRODED. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS. FABRICATED AND REPAIRED FLOORBEAM FLANGE IN ACCORDANCE WITH SRM.

Part: LINE — LEAKING (HYDRAULIC SYS) · airframe 31,287 hrs · 35,525 cycles

WHEN COMMING IN FOR LANDING ON FLIGHT NR 9596 LANDING GEAR DID NOT EXTEND WHEN SELECTED DOWN. GEAR EXTENSION WAS ACCOMPLISHED WITH THE EMERGENCY GEAR EXTENSION HANDLE WITH NORMAL RESULTS. AIRCRAFT LANDED SAFELY WITH NO FURHTER INCIDENTS. AIRCRAFT WAS FERRY FLOWN TO MAINTENANCE BASE IAW SFP NR 2007-003. CORRECTIVE ACTION WAS REPAIR OF EXTENSION HYDRAULIC PRESSURE LINE AND AS A PRECAUTIONARY MEASURE, REMOVAL AND INSTALLING OF THE NOSE LANDING GEAR ACTUATOR. THERE WAS NO SHUTDOWN OF ENGINES OR FEATHERING OF PROPELLERS. NO DELAYS WITH 10 CANCELATIONS.

Part: WIRE — BROKEN (CABIN)

IAH- WHILE PERFORMING A 1A CHECK INSPECTION IT WAS NOTED THAT THE EMERGENCY LIGHT BATTERY HAS LOW VOLTAGE. IAH-MAINTENANCE TROUBLESHOT THE SYSTEM AND FOUND THAT THERE WAS NO POWER TO THE EMERGENCY LIGHTS IN THE BATTERY MODE. MAINTENANCE REPAIRED A BROKEN WIRE TO 29WL PIN F AND G, AND PERFORMED A OPERATIONAL CHECK OF THE EMERGENCY LIGHTING SYSTEM, NO DEFECTS NOTED, AND, THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: BATTERY — DISCHARGED (CABIN)

IAH- WHILE PERFORMING A LINE CHECK THE MECHANIC NOTED THAT WHEN TESTING THE EMERGENCY LIGHTING, SOME OF THE LIGHTS FAILED TO ILLUMINATE. IAH- MAINTENANCE REMOVED AND REPLACED THE EMERGENCY BATTERY AT LOCATION 15WL, PERFORMED A OPERATIONAL CHECK, NO DEFECTS NOTED, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: SENSOR — FAULTY (COCKPIT)

FLT 2937, CREW REPORTED THAT THE AUTOFEATHER LIGHT DID NOT ILLUMINATE AND NUMBER 2 ENGINE WAS LOSING POWER DURING TAKEOFF ROLL. THE CREW ABORTED TAKEOFF AND RETURNED TO THE GATE. MAINTENANCE INSPECTED AND FOUND THE NR 2 GCU MAGNETIC INDICATOR TO BE POPPED. FURTHER TROUBLESHOOTING INDICATED THAT THE NR 2 DC GENERATOR HALL EFFECTS SENSOR TO BE FAULTY. THE AFFECTED HALL EFFECTS SENSOR WAS REMOVED AND REPLACED. THE AIRCRAFT WAS THEN APPROVED FOR RETURN TO SERVICE.

Part: FUSE — BLOWN (CABIN)

IAH - DURING MAINTENANCE INSPECTION, THE EMERGENCY FLOOR LIGHTING AT SEAT 2B WAS FOUND TO BE INOPERATIVE, MAINTENANCE REMOVED AND REPLACED THE AFFECTED EMERGENCY LIGHT POWER SUPPLY FUSE, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: ENGINE — DETERIORATED (NR 2 ENGINE)

CRP - DURING POST-FLIGHT INSPECTION, THE CREW REPORTED THAT THE NUMBER TWO ENGINE PROPELLER SHAFT APPEARED TO BE LOOSE. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE NUMBER TWO PROP SHAFT TO BE LOOSE AND THE REDUCTION GEAR BOX CHIP DETECTOR TO BE CONTAMINATED. MAINTENANCE REMOVED AND REPLACED THE AFFECTED ENGINE, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: POWER SUPPLY — DISCHARGED (CABIN)

EFD - DURING MAINTENANCE INSPECTION, THE EMERGENCY LIGHT PAD WAS FOUND TO BE INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE AFFECTED EMERGENCY LIGHT POWER SUPPLY, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: FAN — SHORTED (CARGO BAY)

IAH- DURING FLIGHT THE CREW NOTED THE PAX VENT POWER SUPPLY CIRCUIT BREAKER POPPED; WHEN THE CIRCUIT BREAKER WAS RESET A STRONG ELECTRIC BURNING SMELL WAS PRESENT. THE CREW PULLED THE CIRCUIT BREAKER AND THE SMELL DISSIPATED. IAH- MAINTENANCE REMOVED AND REPLACED THE PAX VENT FAN, AND PERFORMED AN OPERATIONAL CHECK OF THE FAN WITH NO DEFECTS NOTED. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: LIGHT — INOPERATIVE (PAX DOOR)

IAH - DURING MAINTENANCE INSPECTION, THE PASSENGER DOOR EMERGENCY EXIT LIGHT WAS FOUND TO BE INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE PAX DOOR LIGHT ASSEMBLY, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: COOLING FAN — MALFUNCTIONED (FUSELAGE)

CLE FLIGHT 3116 THE CREW REPORTED A LIGHT HAZE AND ELECTRICAL BURNING SMELL IN COCKPIT DURING TAXI. THE AIRCRAFT RETURNED TO THE GATE WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTED AND REPLACED THE LEFT GROUND COOLING FAN. OPERATIONAL CHECKS WERE GOOD. MAINTENANCE ALSO INSPECTED THE NR 1 AND NR 2 ENGINES. NO DEFECTS WERE NOTED. THE AIRCRAFT WAS RELEASED FOR SERVICE.

Part: SPEAKER — SPARKS (CABIN)

CLE FLIGHT 3813 THE CREW REPORTED THE F/A SAW SPARKS COMING FROM THE SPEAKER GRILL WHILE TAXIING. THE AIRCRAFT RETURNED TO THE GATE WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTED BY REMOVING THE GRILL OF THE SPEAKER AND LOOKING AT ASSOCIATED COMPONENTS. THERE WAS NO EVIDENCE OF SPARKS OR BURNING NOTED. THE COVER WAS REINSTALLED AND THE AIRCRAFT WAS RELEASED FOR SERVICE.

Part: LIGHT — MALFUNCTIONED (FUSELAGE)

DURING LINE/WEEKLY CHECK MX FOUND THE EMERGENCY EXIT LIGHT AT SERVICE DOOR DIM.. REMOVED AND REPLACED EXIT INDICATOR LIGHT IAW ATR MM JIC 32-51-24 AND OPS CHECKED GOOD.

Part: LIGHT — INOPERATIVE (PAX DOOR)

IAH - DURING PREFLIGHT INSPECTION, THE CREW REPORTED THAT THE PASSENGER DOOR EMERGENCY EXIT LIGHT WAS INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE AFFECTED LAMP, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: BULB — FAILED (PAX DOORWAY)

IAH - DURING 2A INSPECTION, THE PASSENGER DOOR EMERGENCY LIGHT WAS FOUND TO BE INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE AFFECTED LIGHT BULB, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

IAH - DURING 2A INSPECTION, THE EMERGENCY LIGHT BATTERY LIGHT BATTERY AT 10WL WAS FOUND TO HAVE LOW VOLTAGE. MAINTENANCE REMOVED AND REPLACED THE AFFECTED BATTERY PACK IAW ATR42-320 MM 33-50-00, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: ENGINE — FAILED (RIGHT)

BPT - FLT 404 - DURING A TRAINING FIGHT, THE PILOT REPORTE THAT THE NR 2 ENGINE PRODUCED 4 LOUD BANGS, ASSOCIATED WITH A FIRE INDICATION. THE CREW DISCHARGED THE ENGINE FIRE BOTTLES AND LANDED AT BPT WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE ENGINE TO HAVE SUFFERED INTERNAL DAMAGE, CAUSING DAMAGE TO ADJACENT COMPONENTS. MAINTENANCE REMOVED AND REPLACED THE ENGINE AND AFFECTED COMPONENTS AND THE AIRCRAFT WAS RETURNED TO SERVICE. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

EFD - DURING MAINTENANCE INSPECTION, THE CENTER AISLE PATH EMERGENCY LIGHTS WERE FOUND TO BE INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE AFFECTED EMERGENCY LIGHT BATTERY PACK IAW ATR42-320 JIC 33-51-21, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: MOUNT — CORRODED (GALLEY)

IAH - DURING C-CHECK INSPECTION, THE INBOARD FORWARD GALLEY FLOOR MOUNT WAS FOUND CORRODED. MAINTENANCE REMOVED AND REPLACED THE AFFECTED MOUNT, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. ACFT TT: 20,370.2 HOURS. CYCLES: 21,341. (X)

Part: SKIN — CRACKED (FUSELAGE)

IAH - DURING C-CHECK INSPECTION, THE SKIN PANEL UNDER THE LEFT HAND AFT WING TO FUSELAGE ATTACH FITTING WAS FOUND CRACKED. MAINTENANCE REPAIRED THE HOLE IAW CONTINENTAL EXPRESS ENGINEERING CHANGE AND REPAIR AUTHORIZATION EC5340-01038, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. ACFT TT: 20,370.2 HOURS. CYCLES: 21,341. (X)

Part: PLATE — CORRODED (RT COCKPIT)

IAH - DURING C-CHECK INSPECTION, THE FIRST OFFICER'S SEAT ATTACH PLATE WAS FOUND CORRODED. MAINTENANCE REMOVED AND REPLACED THE AFFECTED PLATE IAW ATR 42-320 SRM 51-25-02, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. ACFT TT: 20,370.2 HOURS. CYCLES: 21,341. (X)

Part: SEAT — CRACKED (RT COCKPIT)

IAH - DURING C-CHECK INSPECTION, THE FIRST OFFICER'S SEAT RIGHT HAND AFT STRUCTURE WAS FOUND CORRODED. MAINTENANCE STOP DRILLED THE CRACK AND INSTALLED REPAIR DOUBLER IAW ATR 42-320 SRM 51-25-03, AND SRM 51-70-00, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (X)

Part: FLOORBEAM — CORRODED (FRAME 38)

IAH - DURING C-CHECK INSPECTION, THE FLOORBEAM AT FRAME 38 WAS FOUND CORRODED. MAINTENANCE REMOVED AND REPLACED THE AFFECTED FLOORBEAM IAW ATR 42-320 SRM 51-21-28, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. ACFT TT: 20,370.2 HOURS. CYCLES: 21,341. (X)

Part: MOUNT — CORRODED (GALLEY)

IAH - DURING C-CHECK INSPECTION, THE INBOARD AFT GALLEY FLOOR MOUNT WAS FOUND CORRODED. MAINTENANCE REMOVED AND REPLACED THE AFFECTED MOUNT, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. ACFT TT: 20,370.2 HOURS. CYCLES: 21,341. (X)

Part: MLG — MALFUNCTIONED (LEFT)

CREW REPORTED LEFT MAIN GEAR WOULD NOT RETRACT. MAINTENANCE PERFORMED LANDING RETRACTION AND EXTENSION CHECK AND FOUND NO DEFECTS NOTED. OPERATIONALLY CHECKED GOOD. (M)

Part: BULB — FAILED (CABIN)

EWR - FLT 3685 - ARRIVED NEWARK, REPORTING THAT BOTH THE EMERGENCY LIGHT ON THE MAIN CABIN DOOR STEP AND THE EMERGENCY LIGHT FOR THE SERVICE DOOR WERE INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE MAIN DOOR STEP BULB AND THE SERVICE DOOR EMERGENCY LIGHT BULB, AND OPERATIONALLY CHECKED THE SYSTEM GOOD. (M)

Part: PIN — WORN (GALLEY DOOR)

IAH - INSPECTION CHECK 2C - DURING A ROUTINE STRUCTURAL INSPECTION, THE GALLEY SERVICE DOOR AFT UPPER SHOOT BOLT WAS FOUND TO BE WORN BEYOND LIMITS. MAINTENANCE REMOVED AND REPLACED THE SHOOT BOLT AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: PIN — WORN (GALLEY DOOR)

IAH - INSPECTION CHECK 2C - DURING A ROUTINE STRUCTURAL INSPECTION, THE GALLEY SERVICE DOOR FORWARD MIDDLE SHOOT BOLT WAS FOUND TO BE WORN BEYOND LIMITS. MAINTENANCE REPLACED THE SHOOT BOLT AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: FRAME — CORRODED (FUSELAGE)

IAH - INSPECTION CHECK 2C - DURING A ROUTINE STRUCTURAL INSPECTION, FUSELAGE FRAME NR 37 WAS FOUND TO BE CORRODED BEYOND LIMITS AT AREA OF STRINGER NR 14 RIGHT. MAINTENANCE REMOVED DAMAGED PORTION OF FRAME AND PERFORMED REPAIR PER COEX EC 5310-01013. AIRCRAFT WAS LATER APPROVED FOR RETURN TO SERVICE. (M)

Part: PIN — WORN (PAX DOOR)

IAH - DURING INSPECTION 2C, DURING A ROUTINE STRUCTURAL INSPECTION, THE PASSENGER/CREW DOOR AFT LOWER (DOOR OPEN) SHOOT BOLT WAS FOUND TO BE WORN BEYOND LIMITS. MAINTENANCE REMOVED AND REPLACED THE SHOOT BOLT AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: FITTING — CRACKED (FA SEAT)

IAH - INSPECTION CHECK 2C, DURING A ROUTINE STRUCTURAL INSPECTION, THE FLIGHT ATTENDANT SEAT ASSEMBLY RIGHT ATTACHMENT FITTING WAS FOUND TO BE CRACKED. MAINTENANCE REPLACED THE RIGHT ATTACH FITTING AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: FITTING — CRACKED (FA SEAT)

IAH - INSPECTION CHECK 2C - DURING A ROUTINE STRUCTURAL INSPECTION, THE FLIGHT ATTENDANT SEAT ASSEMBLY LEFT ATTACHMENT FITTING WAS FOUND TO BE CRACKED. MAINTENANCE REPLACED THE LEFT ATTACHMENT FITTING AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: BATTERY — DISCHARGED (CABIN)

BTV - DURING 4A INSPECTION, FOUND ROW NR 1 BOTH LEFT AND RIGHT UPPER EMERGENCY EXIT LIGHTS INOPERATIVE WITH SWITCH IN ARM AND C/B. PULLED, REMOVED AND REPLACED NR 2 EMERGENCY LIGHT POWER SUPPLY BATTERY. OPERATIONALLY CHECKED GOOD. (M)

Part: SELECTOR VALVE — FAILED (LANDING GEAR)

IAH - FLT 3865 - ON APPROACH TO IAH, LANDING GEAR WOULD NOT EXTEND. CREW FOLLOWED EMERGENCY EXTENSION PROCEDURES AND THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE LANDING GEAR SELECTOR VALVE AND PERFORMED OPERATIONAL CHECKS PER ATR-42 MM PROCEDURES, ALL SYSTEM CHECKS NORMAL. AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (X)

Part: SEAT TRACK — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, LEFT AND RT FLIGHT ATTENDANT SEAT TRACKS FOUND TO HAVE CORROSION BEYOND LIMITS. MX REMOVED FABRICATED AND INSTALLED NEW TRACKS, FRAMES 36 TO FRAME 39. (M)

Part: COMPRESSOR — FAILED (LT ENGINE)

IAH - FLT 2597 - AFTER TAKEOFF FROM IAH, COCKPIT STARTED TO FILL WITH SMOKE. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED NR 1 ENGINE. AIRCRAFT WAS TEST FLOWN AFTER ENGINE REPLACEMENT WITH NO DISCREPANCIES. AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (REF JIC 72-00-00) AND COEX TEST FLIGHT FORM M-630. ENGINE CHECKED IN SHOP AND FOUND EXCESSIVE OIL IN COMPRESSOR SECTION. (X)

Part: PASSENGER DOOR — CORRODED (FUSELAGE)

IAH - DURING A 6C INSPECTION, THE PASSENGER/CREW DOOR WAS FOUND CORRODED IN SEVERAL AREAS BEYOND LIMITS. MAINTENANCE REMOVED AND REPLACED THE DOOR, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (X)

Part: ANGLE OF ATTACK — MALFUNCTIONED (RT FUSELAGE)

FLT NR 3724 - EWR- STICK PUSHER/SHAKER FAULT IN FLIGHT. AIR RETURNED TO EWR. MAINTENANCE REMOVED AND REPLACED RIGHT AOA PROBE. AIRCRAFT WENT ON A SATISFACTORY TEST FLIGHT AND RETURNED TO SERVICE. (W)