N14834

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 41,068 hrs · 52,935 cycles

PILOT REPORTED EMER AISLE LIGHTS INOPERATIVE AT SEATS 10B, 11B, & 12B. R & R EMER POWER SUPPLY UNIT 30WL & OPERATIONS CHECKED GOOD AT THIS TIME IAW AMM JIC 33-51-21-RAI-10000-002.

Part: WIRE — SHORTED (CABIN) · airframe 40,994 hrs · 52,821 cycles

PILOT REPORTED BURNING SMELL SHORTLY AFTER TAKEOFF. MX INSPECTED & FOUND WIRE 216, BETWEEN 771VT & 71VC SHORTING TO GND. REPAIRED WIRE 216 IAW SPM 20-52-00 & AWM 33-21-06. OPERATIONS CHECKED GOOD & NO BURNING SMELL NOTED AT THIS TIME IAW AMM JIC 33-20-00 OPT 10000-001.

Part: FITTING — CRACKED (RT MLG) · airframe 40,966 hrs · 52,775 cycles

DURING INSPECTION FCD ATR-2016-32-001, RT MLG ACTUATOR FITTING WAS FOUND CRACKED AT LEVEL OF THE TWO LOWER ATTACHMENT HOLES.

Part: BEARING — DEFECTIVE (RUDDER) · airframe 40,498 hrs · 51,028 cycles

PILOT REPORTED THE RUDDER WAS STIFF & HARD TO MOVE IN FLIGHT. R & R TWO AFTER RUDDER QUADRANT BEARINGS PN MS27645-10 & MS27648-16 IAW AMM JIC 22-18-32 & RELEASED FOR A FUNCTIONAL FLIGHT CHECK. FLIGHT CHECK WAS SUCCESSFUL WITH NO FURTHER DEFECT NOTED.

Part: ECU — INOPERATIVE (NR 1) · airframe 40,281 hrs · 51,687 cycles

AFTER GO AROUND, ECU 1 FAULTED. ECU 1 WAS TURNED OFF IAW QRH. ON BASE TO FINAL, LT TORQUE WENT TO 100% & LT NP WENT INTO CAUTION, NR 1 ECU. CLEANED CONNECTOR, PERFORMED ENG RUN-UP & FOUND TO BE OK IAW MM JIC 73-23-61 RAI 10000. AFTER INITIAL DISCREPANCY CORRECTED, CREW STATED THEY MIGHT HAVE EXCEEDED EXTENSION LIMITS FOR LG & FLAPS. PERFORMED FLAP & LG EXTENSION OVER SPEED INSPECTIONS IAW MM. IAW DFDR DOWNLOAD IT WAS DISCOVERED NR 1 ENG HAD SUSTAINED AN OVER TORQUE OF 126.2% FOR 41 SECONDS. PERFORMED ENG & PROPELLER OVER TORQUE INSPECTIONS IAW MM. NO FURTHER DISCREPANCIES FOUND.

Part: BRAKE SYS — CONTAMINATED (MLG) · airframe 39,896 hrs · 51,073 cycles

PILOT REPORTED UPON PARKING, BRAKES WERE APPLIED TO THE STOP. ALMOST NEEDED TO USE THE EMER BRAKE. PCE PERFORMED FOUR BRAKE ASSEMBLY HIGH PRESSURE LINE BLEEDING IAW ATR 42 AMM & JIC 32-42-00 BUS10010 NO LEAK NOTED AT THIS TIME, OPERATIONAL TESTED GOOD.

Part: BOLT — LOOSE (LT AILERON) · airframe 39,400 hrs · 50,291 cycles

LEFT AILERON OTBD SHACKLE BOLT WAS FOUND LOOSE AFTER REPORTS OF SLIGHT VIBRATION IN FLIGHT FROM THE FLIGHT CREW. SECURED & RE-TORQUED SHACKLE BOLT NUT IAW AMM JIC 20-21-12. NO FURTHER DEFECTS FOUND.

Part: BOLT — LOOSE (LT AILERON) · airframe 39,400 hrs · 50,291 cycles

LEFT AILERON OTBD SHACKLE BOLT WAS FOUND LOOSE AFTER REPORTS OF SLIGHT VIBRATION IN FLIGHT FROM THE FLIGHT CREW. AILERON WAS R & R AT AN OUTSIDE VENDOR DURING 2014 HEAVY CHECK. SECURED & RE-TORQUED SHACKLE BOLT NUT IAW AMM JIC 20-21-12. NO FURTHER DEFECTS FOUND.

Part: PANEL — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

CORROSION ON THE LOWER SURFACE OF THE AFT KEEL BEAM PANEL AROUND BL 0 0 & FRAME STATION 27. DURING INSPECTION CORROSION WAS FOUND ON THE AFT KEEL PANEL SHOWN IN FIGURES 3 - 7. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS IAW EO ATR-53-30-2014.

Part: STRAP — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

REPAIR FOR THE INTERIOR MACHINED STRAP AT FRAME 40 BETWEEN FRAMES STRINGERS 1L & 1R. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND IN AREAS SHOWN IN FIGURE 4. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-38-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

REPAIR OF DOOR REINFORCEMENT BETWEEN FRAMES 45 & 46. DURING INSPECTION CORROSION WAS FOUND AROUND THE DOOR BETWEEN FRAME 45 & 46 BETWEEN STRINGER 17 LT & 18 LT & STRINGER 17 RT & 18 RT. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-40-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE SKIN SURROUNDING THE LT EMER EXIT LIGHT CORRODED. DURING INSPECTION CORROSION WAS FOUND ON THE FUSELAGE SKIN SURROUNDING THE LT EMER EXIT LIGHT AFT OF FRAME 20 BETWEEN STRINGERS 15L & 16L. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS IAW EO ATR-53-42-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

DURING INSPECTION CORROSION WAS FOUND ON THE EXTERIOR FUSELAGE SKIN BETWEEN FRAMES 33 & 35 BELOW STRINGER 16L. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-43-2014.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

SURFACE CORROSION FOUND ON THE FUSELAGE LT SIDE MLG FWD DOUBLER. UPON REMOVAL OF PAINT MINOR CORROSION WAS FOUND IN AREAS SHOWN IN FIGURE 3. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-51-2014.

Part: ATTACH FITTING — CORRODED (RT WING) · airframe 38,796 hrs · 49,380 cycles

REPAIR FOR THE RT INBD WING FLAP, CTR ATTACH FITTING SURFACE CORROSION. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND IN AREA. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS. THE MIN THICKNESS AFTER BLEND OUT IS 0.136”, WAS 0.157. IAW EO ATR-57-15-2014.

Part: HINGE — CORRODED (RT SPOILER) · airframe 38,796 hrs · 49,380 cycles

DURING INSPECTION, CORROSION WAS FOUND ON THE RT SPOILER HINGE FASTENER HOLES SHOWN IN FIGURES 5 - 7. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS. IAW EO ATR-57-20-2014.

Part: SKIN PANEL — DEFORMED (RT WING) · airframe 38,796 hrs · 49,380 cycles

RIGHT WING TE ASSEMBLY LOWER PANEL WAS FOUND TO HAVE AN AREA OF LAMINATE DEFLECTION FROM THE ORIGINAL CONTOUR OF UP TO .37” OVER THE LENGTH OF THE PANEL. ACCOMPLISH REPAIR, TE ASSEMBLY, WING RT PANEL NR 631BB. REPAIRED BY CUTTING BACK & POTTING IN DAMAGED AREAS, LAYING UP PLIES TO MATCH REMOVED AREAS & CURING PER MANUFACTURER'S INSTRUCTION. IAW EO ATR-57-21-2014.

Part: SKIN PANEL — CORRODED (RT WING) · airframe 38,796 hrs · 49,380 cycles

DURING INSPECTION, CORROSION WAS FOUND AROUND THE HOLES ON LOWER SURFACE OF THE RT WING PANEL. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-57-23-2014.

Part: SKIN — CORRODED (RT WING) · airframe 38,796 hrs · 49,380 cycles

CORROSION FOUND ON RT WING SKIN, BETWEEN ENG NACELLE RIB 12 & 16. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-57-24-2014.

Part: SKIN — CORRODED (LT WING) · airframe 38,796 hrs · 49,380 cycles

UPON REMOVAL OF PAINT, CORROSION WAS FOUND AT LT WING LOWER SKIN INBD CUT OUTS. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-57-26-2014.

Part: STRAP — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE FRAME 25 INTERNAL STRAP CORROSION AT STRINGER. CORRODED INTERNAL STRAP PORTION BLENDED OUT & INSPECTED WITHOUT ADDITIONAL FINDINGS FOLLOWING ATR INSTRUCTION IAW EO ATR-53-63-2014.

Part: DOOR — CORRODED (ZONE 800) · airframe 38,796 hrs · 49,380 cycles

UPON REMOVAL OF PAINT, CORROSION WAS FOUND IN AREAS SHOWN IN FIGURE 4. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGE AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS. REFERENCE EO 52-09-2014.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

STINGER CLIP AT FRAME 36 STRINGER 15R CORRODED. REMOVED CORRODED STRINGER CLIP. FABRICATED & INSTALLED NEW CLIP. REFERENCE EO 53-23-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

REPAIR OF AFT SKIN LAP AT FRAME 45 STRINGER 17L. DURING INSPECTION CORROSION WAS FOUND AT THE AFT SKIN LAP AT FRAME 45 & STRINGER 17L. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-39-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE SKIN CORROSION AT SERVICE DOOR SURROUND. CORRODED SKIN AREAS BLENDED OUT & INSPECTED FOLLOWING ATR INSTRUCTION.

Part: SPAR — CORRODED (RT HORIZ STAB) · airframe 38,796 hrs · 49,380 cycles

CORROSION ON RT HORIZONTAL REAR SPAR UPPER CHORD. UPON REMOVAL OF PAINT MINOR CORROSION WAS FOUND IN RT HORIZONTAL REAR SPAR UPPER CHORD. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-55-01-2014.

Part: FITTING — CORRODED (RT ELEVATOR) · airframe 38,796 hrs · 49,380 cycles

SURFACE CORROSION ON RT ELEVATOR TE UPPER TIP FITTING. DURING INSPECTION CORROSION WAS FOUND ON THE RT ELEVATOR TE UPPER TIP FITTING & OTBD STATIC WICK BASE. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-55-02-2014.

Part: ATTACH ANGLE — CORRODED (ELEVATOR) · airframe 38,796 hrs · 49,380 cycles

CORROSION ON AN ATTACH ANGLE ON THE OTBD LT SIDE OF THE ELEVATOR. DURING INSPECTION CORROSION WAS FOUND AT MULTIPLE PLACES ALONG THE ATTACH ANGLE AS SHOWN IN FIGURES 2 - 12. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS. IAW EO ATR-55-03-2014.

Part: SKIN — CORRODED (LT ELEVATOR) · airframe 38,796 hrs · 49,380 cycles

CORROSION ON THE LT ELEVATOR TRAILING INBD EDGE UPPER TIP FITTING LOCATION. DURING INSPECTION CORROSION WAS FOUND ON THE LT ELEVATOR TRAILING INBD EDGE. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS. IAW EO ATR-55-04-2014.

Part: SKIN — CORRODED (LT WING) · airframe 38,796 hrs · 49,380 cycles

LANDING GEAR WING LOWER SKIN EXT CORROSION AT LE BETWEEN RIBS 19 & 20. CORROSION BLENDED IAW SRI DT S-1551 14-21619. IAW EO ATR-57-06-2014.

Part: DOOR — CORRODED (LAV SERVICE) · airframe 38,796 hrs · 49,380 cycles

DURING INSPECTION, CORROSION WAS FOUND ON THE INNER & OUTER SURFACES OF THE LAVATORY DRAIN DOOR. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGE AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS. THEN A DOUBLER WAS FABRICATED & INSTALLED TO REINFORCE EACH FWD & AFT LATCH LOCATIONS. REFERENCE EO 52-04-2014.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

STRINGER 21RT AT FRAME 18 HAS CORROSION. REMOVED CORROSION & FOUND STRINGER TO BE OUT OF LIMITS, CUT OUT DAMAGED SEGMENT & FABRICATED NEW SEGMENT, SPLICE & SHIM. INSTALLED REPAIR PARTS AFTER SURFACE PROTECTION APPLICATION. DAMAGED STRINGER WAS APPROX 14 INCHES IN LENGTH, CUT LINE APPROX 9 INCHES FWD OF FRAME 18 TO END OF STRINGER APPROX 5 INCHES AFT OF FRAME 18. REFERENCE EO 2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE LT SIDE INTERNAL PANEL SKIN SURFACE CORROSION AT STATION 46 STRINGER 17L. MINOR CORROSION WAS FOUND UPON REMOVAL OF PAINT. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECT IAW EO ATR-53-24-2014.

Part: SKIN — CORRODED (LT WING) · airframe 38,796 hrs · 49,380 cycles

UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND ON THE LT WING LOWER SKIN SURFACE TE BETWEEN RIBS 4 & 10. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS. IAW EO ATR-57-18-2014.

Part: SKIN — CORRODED (RT WING) · airframe 38,796 hrs · 49,380 cycles

UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND ON RT WING FRONT, LOWER CHORD, BETWEEN RIB 5 & 6, SURFACE CORROSION. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND. THE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-57-02-2014.

Part: SKIN — CORRODED (LE SLAT) · airframe 38,796 hrs · 49,380 cycles

UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND ON THE LT WING UPPER SLAT FRONT SPAR BETWEEN RIBS 5 & 6. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-57-12-2014.

Part: SKIN PANEL — DELAMINATED (RT WING) · airframe 38,796 hrs · 49,380 cycles

DURING INSPECTION, DELAMINATION WAS FOUND ON THE RT WING LE PANEL 611. REMOVED DAMAGED AREAS, APPLIED REPAIR PLIES & CURED PER INSTRUCTION. IAW EO ATR-57-25-2014.

Part: SKIN — CORRODED (LT WING) · airframe 38,796 hrs · 49,380 cycles

SURFACE CORROSION ON THE LT WING LOWER SKIN NACA AREA. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND AROUND PERIMETER OF LT WING LOWER SKIN NACA AREA FWD OF THE RAM AIR INLET. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-57-11-2014.

Part: SLAT — CORRODED (LT WING) · airframe 38,796 hrs · 49,380 cycles

LEFT WING FWD SPAR UPPER STRIP SLAT CORROSION AT RIB 19 PLUS BETWEEN RIBS 23 - 24 & 29 - 30. CORROSION REMOVED & DAMAGES BLENDED IAW SRI REF DT S-1559 14-21618 ISSUE B. IAW EO ATR-57-07-2014.

Part: CREASE BEAM — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

REPAIR FOR THE LT CREASE BEAM WEB BETWEEN FRAMES 17L & 18L. UPON REMOVAL OF PAINT CORROSION WAS FOUND IN AREAS SHOWN IN FIGURE 4. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-48-2014.

Part: FRAME — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE FRAME 28 CORROSION BETWEEN STRINGERS 21 LT & RT. CUT AWAY CORRODED FRAME PORTION & SPLICED IN NEW IAW ADAPTATION OF TSK-530000-300-840-A01 FOLLOWING ATR INSTRUCTION IAW EO ATR-53-57-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE LT LOWER SKIN AT ANTENNA BEACON SURFACE CORROSION. UPON REMOVAL OF PAINT MINOR CORROSION WAS FOUND IN AREAS SHOWN IN FIGURE 3. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-49-2014.

Part: SKIN PANEL — DEFORMED (RT WING) · airframe 38,796 hrs · 49,380 cycles

RIGHT WING TE ASSEMBLY LOWER PANEL WAS FOUND TO HAVE A 7.75” X 7.4” X 0.2” AREA OF LAMINATE DEFLECTION. THE DISCREPANT AREA IS LOCATED 6.1” FROM THE INBD EDGE & 4.9” FROM THE AFT EDGE. REMOVED DAMAGED AREAS, POTTED IN DAMAGED AREAS & CURED IAW MANUFACTURER'S INSTRUCTION. IAW EO ATR-57-22-2014.

Part: PAN — CORRODED (PAX DOOR) · airframe 38,796 hrs · 49,380 cycles

PASSENGER DOOR AFT UPPER CORNER PAN PRESSING CORROSION. INSPECTED & BLENDED CORROSION AS REQUIRED. REFERENCE EO 52-10-2014 FOR REPAIR.

Part: FAIRING — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

CORROSION DAMAGE ON LT MLG FAIRING AT FRAME 28A IAW FIGURES 2 & 3. THE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-52-2014.

Part: SKIN — CORRODED (RT WING) · airframe 38,796 hrs · 49,380 cycles

RIGHT WING LOWER SKIN, BETWEEN RIB 5 & 10, SURFACE CORROSION. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-57-14-2014.

Part: SPAR — CORRODED (RT WING) · airframe 38,796 hrs · 49,380 cycles

CORROSION FOUND ON RT WING REAR LOWER SPAR. UPON REMOVAL OF PAINT, MAJOR CORROSION WAS FOUND IN AREAS SHOWN IN FIGURE 5. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS. FURTHER ANALYSIS OF THE DAMAGED EXTRUSION DETERMINED THAT THE PART BE REPLACED ENTIRELY & SPLICED INTO THE EXISTING EXTRUSION BETWEEN RIB 19 & 23. IAW EO ATR-57-30-2014.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

REPAIR REQUIRED FOR THE BELLY FAIRING UPPER ATTACH ANGLE ON FAIRING 192HR. UPON REMOVAL OF PAINT, CORROSION WAS FOUND. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-29-2014.

Part: STRINGER — GOUGED (RT WING) · airframe 38,796 hrs · 49,380 cycles

RIGHT WING INNER LOWER STRINGER 7 INBD OF RIB 6, GOUGE DAMAGE. UPON INSPECTION, GOUGE SCRAPES WERE FOUND IN THE AREA SHOWN IN FIGURE 3. THE DAMAGE WAS BLENDED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-57-16-2014.

Part: SPLICE PLATE — CORRODED (WING) · airframe 38,796 hrs · 49,380 cycles

WING UPPER SKIN REMOVABLE PANELS EXT SPLICE PLATE CORROSION AT RIB 0. CORROSION BLENDED IAW SRI DT S-2286-14-21888. IAW EO ATR-57-09-2014.

Part: SPAR — CORRODED (RT WING) · airframe 38,796 hrs · 49,380 cycles

RIGHT WING AFT SPAR UPPER CHORD CORROSION BETWEEN RIBS 23 - 30. CORROSION REMOVED & DAMAGES BLENDED IAW SRI REF DO TS-136 11-14754. AFT SPAR UPPER CAP REPLACED FROM RIB 16 TO 30 WITH SPLICES BETWEEN RIBS 16 - 17 & 23 - 24 IAW NEW REPAIR DWG REF 22S572R0331. IAW EO ATR-57-31-2014.

Part: SKIN — CORRODED (HORIZ STAB) · airframe 38,796 hrs · 49,380 cycles

CORROSION ON THE RT SIDE HORIZONTAL STABILIZER, UPPER & LOWER SKIN. DURING INSPECTION, CORROSION WAS FOUND AT MULTIPLE PLACES ALONG THE TRAILING SKIN. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS. IAW EO ATR-55-06-2014.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FRAME 1 BULKHEAD WEB, SURFACE CORROSION. DURING INSPECTION, MINOR CORROSION WAS FOUND IN AREAS SHOWN IN FIGURE 2. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGE AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS. REFERENCE EO 53-01-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

EXTERIOR SKIN CORRODED ALONG FRAME 41 BETWEEN STRINGERS 21L & 21R. UPON REMOVAL OF PAINT MINOR CORROSION WAS FOUND. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-44-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE SKIN CORROSION AT RT FWD MLG TRUNNION ATTACHMENT. BLENDED CORRODED SKIN & INSPECTED WITH NO ADDITIONAL FINDINGS FOLLOWING ATR INSTRUCTION IAW EO ATR-53-25-2014.

Part: BULKHEAD — CORRODED (RT MLG WW) · airframe 38,796 hrs · 49,380 cycles

UPON REMOVAL OF PAINT, THE TECHNICIAN FOUND CORROSION ON INTERIOR FUSELAGE RT MLG PRESS BULKHEAD WEB JUST AFT OF FRAME 26 FLOORBEAM ON THE RT OTBD CORNER. THE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGE AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF CRACK DEFECTS. REFERENCE EO 53-02-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE CGO DOOR SURROUND SKIN CORROSION AT LEVEL OF FRAME 14. BLENDED OUT CORRODED AREA & INSPECTED FOLLOWING ATR INSTRUCTION IAW EO ATR-53-58-2014.

Part: TRUSS — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

REPAIR REQUIRED FOR THE LT MLG TRUSS MEMBER AROUND LOCK FASTENERS AT ATTACH ANGLE. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-32-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

CORROSION ON THE EXTERNAL SKIN. DURING INSPECTION CORROSION WAS FOUND ON THE RT CROWN PANEL AT FRAME 44 & STRINGER 6R. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS IAW EO ATR-53-36-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

DURING INSPECTION CORROSION WAS FOUND ON THE LOWER EXTERIOR SKIN AT NR 2 DME ANTENNA MOUNT LOCATION FRAMES 8 TO 9 LBL 4.5. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-33-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

DURING INSPECTION CORROSION WAS FOUND ON THE EXTERIOR FUSELAGE SKIN BETWEEN FRAMES 31 & 33 BETWEEN STRINGERS 19L & 19R. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-50-2014.

Part: SKIN — CORRODED (LT WING) · airframe 38,796 hrs · 49,380 cycles

WING SKIN SURFACE CORROSION. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND AT LT WING LOWER SKIN BETWEEN RIBS 13 & 30. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS. IAW EO ATR-57-01-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE LT EMER EXIT SURROUND SKIN CORROSION. CORRODED AREA WAS BLENDED & INSPECTED FOLLOWING ATR INSTRUCTION IAW EO ATR-53-60-2014.

Part: FAIRING — OUT OF ALIGNMENT (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

REPAIR REQUIRED FOR THE MLG BELLY FAIRING PANEL 192FR PN S5247121200900. THE REPAIR IS NECESSARY DUE TO NUMEROUS AREAS OF GAPS & AERODYNAMIC MISMATCH WITH THE ADJACENT PANELS. IAW EO ATR-53-69-2014.

Part: SPAR — CORRODED (LT WING) · airframe 38,796 hrs · 49,380 cycles

LEFT HAND SPAR FRONT SLAT, BETWEEN RIB 5 & 10, SURFACE CORROSION. UPON INSPECTION CORROSION & CHAFE DAMAGE WAS DISCOVERED AT THE LT LOWER SLAT AT RIB 5 & 10. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-57-13-2014.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

CORROSION AT THE DC POWER RECEPTACLE BOX. DURING INSPECTION CORROSION WAS FOUND ON THE OUTER SURFACE OF DC RECEPTACLE POWER BOX. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS IAW EO ATR-53-27-2014.

Part: STRUCTURE — DAMAGED (COCKPIT) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE COCKPIT NODE 5 ELONGATED HOLES RT & LT. OVERSIZED HOLES INSPECTED & 2ND OVERSIZED FASTENERS INSTALLED FOLLOWING ATR INSTRUCTION IAW EO ATR-53-61-2014.

Part: SKIN PANEL — DAMAGED (RT WING) · airframe 38,796 hrs · 49,380 cycles

RIGHT WING UPPER SKIN REMOVABLE PANEL OVERSIZED HOLE BETWEEN RIBS 7 & 8 ST FWD LONGERON JUNCTION. HOLE ENLARGED & BUSHING INSTALLED IAW SRI DT S-2606 14-22016. IAW EO ATR-57-08-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE PAX DOOR SURROUND SKIN CORROSION. BLENDED OUT CORRODED AREAS & INSPECTED FOLLOWING ATR INSTRUCTION IAW EO ATR-53-59-2014.

Part: PAN — CORRODED (CARGO DOOR) · airframe 38,796 hrs · 49,380 cycles

DAMAGE ON FWD CARGO DOOR UPPER INTERNAL PAN. THE DAMAGED AREA WAS CUT OUT & REPLACED WITH A CUT OUT SECTION FROM A NEW DOOR FRAME. REFERENCE EO 52-08-2014 FOR FULL DETAILS.

Part: SKIN — CORRODED (VERTICAL STAB) · airframe 38,796 hrs · 49,380 cycles

UPON REMOVAL OF PAINT, SURFACE CORROSION LT SIDE OF THE VERTICAL STABILIZER. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-55-05-2014.

Part: SKIN — CORRODED (LT WING) · airframe 38,796 hrs · 49,380 cycles

MINOR SURFACE CORROSION FOUND ON LT WING LOWER SKIN. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND ON THE LE SURFACE OF THE LT LOWER SKIN BETWEEN RIBS 28 & 30. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS.

Part: PAN — CORRODED (EMERGENCY EXIT) · airframe 38,796 hrs · 49,380 cycles

DURING INSPECTION CORROSION WAS FOUND ON THE EMER EXIT DOOR LOWER PAN. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGE AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS. REFERENCE EO 52-06-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

UPPER FUSELAGE EXTERIOR SKIN AT ATC ANTENNA SURFACE CORROSION. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND IN AREAS SHOWN IN FIGURE 3. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-37-2014.

Part: SKIN — SCRATCHED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

DAMAGE TO FUSELAGE INTERNAL SKIN BETWEEN STRINGER 14L - 15L FRAME 40 - 42. UPON INITIAL WORK OF INTERNAL SKIN SCRATCHES OCCURRED BETWEEN STRINGER 14L - 15L FRAME 40 - 42. AFTER BLENDING WAS DONE NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-46-2014.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

CORROSION ON STRINGER 21R BETWEEN FRAMES 29 & 30 AFT OF A SPLICE. DURING INSPECTION CORROSION WAS FOUND ON THE STRINGER AS SHOWN IN FIGURE 5. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS IAW EO ATR-53-31-2014.

Part: FRAME — MECHANIC ERROR (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FOUR MIS DRILLED HOLES AT FRAME 23 BETWEEN STRINGER 16 & 18. ALL FOUR HOLES WERE OVERSIZED TO .281 INCH IN DIAMETER IN ORDER TO REMOVE THE DAMAGE. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR53-34-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE SKIN INTERNAL CORROSION BETWEEN FRAMES 03 - 04 AT LEVEL OF LT STATIC PORT. CORRODED SKIN AREA BLENDED OUT & INSPECTED FOLLOWING ATR INSTRUCTION IAW EO ATR-53-66-2014.

Part: SPAR — CORRODED (RT WING) · airframe 38,796 hrs · 49,380 cycles

DURING INSPECTION, CORROSION WAS FOUND ON THE RT WING LOWER SPAR FLANGE AT RIB 10. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-57-17-2014.

Part: ANGLE — CORRODED (RT WING) · airframe 38,796 hrs · 49,380 cycles

RIGHT WING UNDERWING BOX ANGLE AT RIB 10 MID AREA VERTICAL FLANGE CORROSION. CORROSION REMOVED & DAMAGE BLENDED IAW SRI RF DT S-1538 14-21620. IAW EO ATR-57-05-2014.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

CORROSION ON RT LOWER SIDE BOX BETWEEN FRAME 26 & 27, RBL 1225 MM 48.2. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-32-2014.

Part: FAIRING — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

CORROSION FOUND ON FRAME 24A LT & RT SIDES IN MLG FAIRING. UPON REMOVAL OF PAINT CORROSION WAS FOUND IN AREAS SHOWN IN SECTION 2.0. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-45-2014.

Part: HOUSING — CORRODED (WING) · airframe 38,796 hrs · 49,380 cycles

WING ACCESS DOORS 521 DT & 522 CT HOUSINGS CORROSION. CORROSION REMOVED & DAMAGE BLENDED IAW SRI REF DT S-2398 14-21886. IAW EO ATR-57-27-2014.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

INTERIOR CABIN STRINGER CLIP JUST BELOW FLOORBEAM 21 STRINGER 15L, CORRODED. REMOVED CLIP FOUND TO BE BEYOND LIMITS. FABRICATED & INSTALLED NEW STRINGER CLIP & APPLIED SURFACE PROTECTION. REFERENCE EO 53-04-2014.

Part: SPAR — CORRODED (RT WING) · airframe 38,796 hrs · 49,380 cycles

UPON REMOVAL OF PAINT, CORROSION WAS FOUND AT THE RT WING, UPPER SLAT REAR SPAR AT RIB 13. THIS PART IS A SHIM. AFTER CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA, NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS. IAW EO ATR-57-19-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

DURING INSPECTION CORROSION WAS FOUND ON THE LOWER EXTERIOR SKIN BETWEEN FRAME 14 & 15. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS IAW EO ATR-53-28-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

SKIN RT SIDE BETWEEN FRAMES 40 & 41 ALONG STRINGER 15. UPON REMOVAL OF PAINT CORROSION WAS FOUND IN AREAS SHOWN IN FIGURE 4. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-56-2014.

Part: SPAR — CORRODED (HORIZ STAB) · airframe 38,796 hrs · 49,380 cycles

CORROSION RT & LT HORIZONTAL REAR SPAR, LOWER CHORD. DURING INSPECTION CORROSION WAS FOUND ON THE RT & LT HORIZONTAL REAR SPAR, LOWER CHORD. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS. A .032 THICK 7075-T6 DOUBLER WILL BE SANDWICHED BETWEEN THE EXISTING COMPOSITE AERODYNAMIC FILLER & THE REAR SPAR LOWER CHORD. IAW EO ATR-55-07-2014.

Part: DOOR — CORRODED (CARGO BAY) · airframe 38,796 hrs · 49,380 cycles

DURING INSPECTION CORROSION WAS FOUND ON THE FWD CARGO DOOR. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGE AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS. REFERENCE WORK ORDER 133428, NON-ROUTINE 800005 EO 52-05-2014.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

REPAIR OF FUSELAGE FRAME 46 SHEAR TIE BETWEEN STRINGER 17R & 17L. DURING INSPECTION CORROSION WAS FOUND ON THE INTERNAL SHEAR TIE PN S53871204202. THE SURFACE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGE AREA. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINE THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-41-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

SURFACE CORROSION FUSELAGE LT SIDE INTERNAL PANEL SKIN AT STATION 46 STRINGER 17L. UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND IN AREAS SHOWN IN FIGURE 3. CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGE AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF DEFECTS IAW EO ATR-53-53-2014.

Part: FRAME — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE FRAME 24 CORROSION BETWEEN STRINGERS 19 - 20 RHS. CORRODED FRAME PORTION CUT AWAY & NEW PORTION SPLICED AT LEVEL OF STRINGERS 17 LT & RT IAW ADAPTATION OF SRM REPAIR IAW 53-00-00 FIG 435 FOLLOWING ATR INSTRUCTION. IAW EO ATR-53-68-2014.

Part: SKIN — CORRODED (RT WING) · airframe 38,796 hrs · 49,380 cycles

UPON REMOVAL OF PAINT, THE TECHNICIAN FOUND CORROSION ON RT OTBD WING LOWER SURFACE AT MULTIPLE LOCATIONS, BETWEEN RIBS 13 - 23. THE CORROSION WAS CLEANED AWAY & BLENDING WAS PERFORMED AT THE LOCAL DAMAGED AREAS. NDT WAS THEN PERFORMED TO RECORD MATERIAL LOSS & DETERMINED THAT THE PART WAS FREE OF CRACK DEFECTS. MINIMUM THICKNESS REMAINING AFTER CORROSION REMOVAL IS .074 INCHES. IAW EO ATR-57-2014.

Part: SKIN — CORRODED (FUSELAGE) · airframe 38,796 hrs · 49,380 cycles

FUSELAGE SKIN INTERNAL & EXTERNAL CORROSION AT LEVEL OF FRAME 24 BETWEEN STRINGERS 19 - 20 RHS. CORRODED SKIN AREAS BLENDED OUT & INSPECTED FOLLOWING ATR INSTRUCTION IAW EO ATR-53-67-2014.

Part: DOOR — CORRODED (ZONE 800) · airframe 38,796 hrs · 49,380 cycles

DURING HEAVY MAINTENANCE CHECK, UPON REMOVAL OF PAINT, MINOR CORROSION WAS FOUND AROUND PERIMETER OF AFT ACCESS DOOR 835, PN S538750001800, ON EXTERNAL PANEL PN S53875000248, INTERNAL & EXTERNAL SURFACES. WORK ORDER 133428 NON-ROUTINE 300024. ACCOMPLISH REPAIR OF AFT ACCESS DOOR 835 – SURFACE CORROSION IN ACCORDANCE WITH EO7019-300024 REVISION NC DATED 08 APR 2014.

Part: POWER SUPPLY — DISCHARGED (EMERGENCY LIGHTS) · airframe 38,251 hrs · 48,544 cycles

SEVERAL EMERGENCY EXIT LIGHTS DO NOT TEST. REPLACED POWER SUPPLIES. OPS CHECKED GOOD. CREW SUBSEQUENTLY REPORTED EMERGENCY LIGHTS LIGHTS ARE INOPERABLE WHEN EMERGENCY LIGHTS ARMED AND BOTH BATTERY AND EXTERNAL POWER OFF. FOUND BATTERY CHARGE LEVELS DEPLETED AND CHARGED BATTERIES. FOUND TO OPS CHECK GOOD.

Part: LINE — FAILED (HYDRAULIC SYS) · airframe 35,540 hrs · 44,379 cycles

AFTER TAKEOFF, CREW GOT GREEN HYD LOW PRESSURE AND LOW LEVEL LIGHTS. CREW DECLARED EMERGENCY AND COMPLETED AN AIR RETURNED TO SPN (PGSN). GEAR WAS BLOWN DOWN AND LANDED SAFELY. MX INSPECTED AND FOUND FAILED HYD LINE. AS PRECOUTIONARY MEASURE, MX R & R SUPPLY AND RETURN LINES ON BOTH MLG ACTUATORS. ACFT LANDING GEAR SYS WAS OPERATIONALLY CHECKED AND ACFT RETURNED TO SERVICE.

Part: CLAMP — LOOSE (CONTROL VALVE) · airframe 35,008 hrs · 43,543 cycles

CREW REPORTED AFTER TAKEOFF AND AFTER TURNING ON THE BLEED AIR, THEY OBSERVED A HIGHER THAN NORMAL NR1 DUCT TEMP ACCOMPANIED WITH A BURNING SMELL IN THE COCKPIT. AS A PRECAUTION, THEY RETURNED TO DEPARTURE AND REQUESTED MX TO INSPECT THE ACFT. MX INSPECTED ACFT, DEFERRED THE NR 1 BLEED SYS IAW MEL 36-2. UPON RETURN FLIGHT, MX RESECURED LOOSE TURBINE INLET CONTROL VALVE HOSE CLAMP. SYS CHECKED GOOD ON GROUND.

Part: FAIRING — MISINSTALLED (ZONE 200) · airframe 34,197 hrs · 42,313 cycles

ON APPROACH, THE ACFT STARTED TO EXPERIENCE ABNORMAL VIBRATIONS. WHEN VIBRATION STARTED THE AUTO PILOT WAS DISENGAGED AND THE ACFT WAS FLOWN MANUALLY. AS THE ACFT DESCENDED AND SLOWED DOWN, THE VIBRATION ALSO DECREASED. WHEN VIBRATION STARTED, THE F/A REPORTED A LOUD NOISE AND VIBRATION COULD BE FELT AFT OF THE WINGS. LANDING WAS UNEVENTFUL, AND NO PHYSICAL DAMAGE WAS EVIDENT ON THE ACFT. MX INSPECTED ENTIRE ACFT. MX FOUND WING TO FUSELAGE FAIRING (295DL) IMPROPERLY INSTALLED. REMOVED FAIRING AND REINSTALLED CORRECTLY. ACFT RELEASED FOR FUNCTIONAL CHECK FLIGHT. FLIGHT CHECK SATISFACTORY. ACFT RELEASED BACK TO SERVICE.

Part: BLADE — CRACKED (PROPELLER)

MAINTENANCE REPORTED POSSIBLE CRACK OF PROPELLER BLADE LEADING EDGE SHEATH. REMOVED AND REPLACED BLADE AS A PRECAUTION.

Part: BLADE — CRACKED (PROPELLER)

MAINTENANCE REPORTED POSSIBLE CRACK OF PROPELLER BLADE LEADING EDGE SHEATH. REMOVED AND REPLACED BLADE AS A PRECAUTION.

Part: ENGINE — CONTAMINATED · airframe 31,779 hrs · 38,521 cycles

DURING CLIMB-OUT, CREW REPORTED "ODD" ODOR IN THE COCKPIT. CREW ELECTED TO PERFORM PRECAUTIONARY AIR RETURN, LANDING UNEVENTFUL. MX INSPECTED ACFT FOR FLUID LEAKS, ALL RESERVOIR LEVELS CHECKED OK, NO LEAKS NOTED. PERFORMED GENERAL INSPECTION OF FLIGHT COMPARTMENT AND CABIN FOR SIGNS OF SMOKE, NONE NOTED. MAINTENANCE SUSPECT RESIDUAL COMPRESSOR CLEANING/RINSE FLUID AS CAUSE OF ODOR WHEN FLUID EVAPORATED DURING ENGINE RUNNING. MAINTENANCE PERFORMED ENGINE GROUND RUNS, NO UNUSUAL SMELLS OR FUMES ASSOCIATED WITH ENGINE RUNS. AIRCRAFT RELEASED BACK TO SERVICE.

Part: LIGHT — FAILED (CABIN) · airframe 30,309 hrs · 36,119 cycles

FLOOD LIGHT FOR EMERGENCY LIGHT AT PASSENGER/CREW DOOR IN OPERATIVE. REMOVED AND INSTALLED SERVICEABLE EMERGENCY FLOOD LIGHT ASSEMBLY. OPERATIONALLY CHECKED GOOD.

Part: POWER SUPPLY — FAILED (EMERGENCY LIGHTS) · airframe 29,813 hrs · 35,290 cycles

EMREGENCY AISLE PATH AND LOWER EXIT SIGNS FOR THE PASSENGER AND SERVICE DOORS ILLUMINATE DIMMLY WHEN EMERGENCY EXIT LIGHTS ARE ARMED. REMOVED AND INSTALLED EMER. LIGHT POWER SUPPLY THERE WERE NO ENGINE SHUTDOWNS, NO PROPELLER FEATHERINGS, NO DELAYS AND NO CANCELLATIONS DUE TO THIS PROBLEM.

Part: POWER SUPPLY — WEAK (EMERGENCY LIGHTS) · airframe 29,813 hrs · 35,240 cycles

EMERGENCY AISLE PATH AND LOWER EXIT SIGNS FOR PASSENGER AND SERVICE DOORS ILLUMINATE DIMLY WHEN EMERGENCY EXIT LIGHTS ARE ARMED AISLE PATH LIGHTS ARE ON ONLY AFT OF ROW 10. MAINTENANCE REMOVED AND INSTALLED EMERGENCY LIGHTING POWER SUPPLY. OPERATIONALLY TESTED GOOD.

Part: FACEPLATE — CRACKED (RT WING) · airframe 29,747 hrs · 35,225 cycles

RIGHT WIING BOX FACE PLATE CRACKED AT FRAME 29. REMOVED AND REPLACED THE FACE PLATE IN ACCORDANCE WITH SRM 51-25-01.

Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

RUDDER SPRING TAB LEVER SUPPORT ASSEMBLY CORRODED. CORROSION WAS FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED IN ACCORDANCE WITH SRM.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

FOUND FLOORBEAM AT FRAME 13 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REPAIRED FLOORBEAM WITH SPLICE IN ACCORDANCE WITH SRM 53-00-00 FIGURE 435.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

RIGHT INBOARD SEAT TRACK BETWEEN FRAMES 13 AND 23 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM 51-25-04.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

LEFT SEAT TRACK BETWEEN FRAMES 39 AND 41 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM 51-25-04.

Part: STIFFENER — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

AFT PRESSURE BULKHEAD STIFFENER, BETWEEN STRINGERS LEFT 21 AND RIGHT 21, CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND INSTALLED STIFFENER IN ACCORDANCE WITH SRM 51-25-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

LEFT INBOARD SEAT TRACK BETWEEN FRAMES 23 AND 29 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM 51-25-04.

Part: RETAINER SEAL — CRACKED · airframe 29,747 hrs · 35,225 cycles

UPPER WING DECK PRESSURE SEAL RETAINER CRACKED. SEAL RETAINER REPAIRED IN ACCORDANCE WITH AIRCRAFT MANUFACTURES STRUCTURAL REPAIR INSTRUCTIONS DO/TS3909/01-9238.

Part: FRAME — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

FOUND FRAME 44 BETWEEN STRINGERS LEFT AND RIGHT 21 CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. FRAME 44 REPAIRED IN ACCORDANCE WITH SRM 53-81-40 FIGURE 403.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

SEAT TRACK RIGHT SIDE BETWEEN FRAMES 36 AND 39 CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. SEAT TRACK WAS REMOVED AND REPLACED IN ACCORDANCE WITH SRM 51-25-04.

Part: STIFFENER — CORRODED (BULKHEAD) · airframe 29,747 hrs · 35,225 cycles

FORWARD PRESSURE BULKHEAD LEFTHAND OUT BOARD STIFFNER CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND INSTALLED STIFNER IN ACCORDANCE WITH SRM 5125-01 AND 51-25-04.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

RIGHT STRINGER 20 BETWEEN FRAMES 13 AND 25 CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED AS PER SRM 53-00-00 FIGURE 428.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

RIGHT SEAT TRACK BETWEEN FRAMES 39 AND 40 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM 51-25-04.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

FOUND SEAT TRACK LEFT SIDE BETWEEN FRAMES 36 AND 39 CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. SEAT TRACK WAS REMOVED AND REPLACED IN ACCORDANCE WITH SRM 51-25-04.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

RIGHT STRINGER 21 BETWEEN FRAMES 13 AND 25 CORRODED. REMOVED CORROSION AND FOUND TO BE BEYOND MANUFACTURER LIMITS. REMOVED AND REPLACED IN ACCORDANCE WITH SRM 53-31-00 FIGURE 301.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

RIGHT OUTBOARD SEAT TRACK BETWEEN FRAMES 23 AND 29 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM 51-25-04.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

RIGHT SEAT TRACK BETWEEN FRAMES 41 AND 44 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM 51-25-04.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

FOUND FLOORBEAM AT FRAME 39 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED FLOORBEAM IN ACCORDANCE WITH 51-25-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

LEFT ZEE FLOOR BETWEEN FRAMES 39 AND 40 CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMIT. REMOVED AND REPLACED AS PER SRM 51-25-03.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

LEFT OUTBOARD SEAT TRACK BETWEEN FRAMES 23 AND 29 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM 51-25-04.

Part: THRESHOLD — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

RIGHT THRESHOLD BETWEEN FRAMES 36 AND 39 CORRODED. CORROSION WAS REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED THRESHOLD IN ACCORDANCE WITH SRM 51-25-01.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

FOUND FLOORBEAM AT FRAME 36 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED FLOORBEAM IN ACCORDANCE WITH 51-25-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

LEFT SEAT TRACK BETWEEN FRAMES 41 AND 44 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM 51-25-04.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

LEFT OUTBOARD SEAT TRACK BETWEEN FRAMES 13 AND 23 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM 51-25-04.

Part: THRESHOLD — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

LEFT THRESHOLD BETWEEN FRAMES 36 AND 39 CORRODED. CORROSION WAS REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED THRESHOLD IN ACCORDANCE WITH SRM 51-25-01.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

FOUND UPPER FLOORBEAM 41 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND INSTALLED FLOORBEAM IN ACCORDANCE WITH SRM 51-25-01.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

FOUND FLOORBEAM 38 IS CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS ALLOWABLE LIMITS. REMOVED AND REPLACED FLOORBEAM 38 IN ACCORDANCE WITH SRM 51-25-01.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

FOUND FLOORBEAM 40 IS CORRODED. REMOVED CORROSION AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED FLOORBEAM IN ACCORDANCE WITH SRM 51-25-01.

Part: SEAT TRACK — CORRODED (FUSELAGE)

SEAT TRACK RIGHT OUTBOARD BETWEEN FRAMES 29 AND 36 CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM 51-25-04.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

SEAT TRACK RIGHT INBOARD BETWEEN FRAMES 29 AND 36 CORRODED. CORROSION REMOVED AND FOUND TO BE BEYOND MANUFACTURERS LIMITS. REMOVED AND REPLACED SEAT TRACK IN ACCORDANCE WITH SRM 51-25-04.

Part: SEAT TRACK — CORRODED (FUSELAGE)

RIGHT INBOARD SEAT TRACK BETWEEN FRAMES 23 AND 29 CORRODED. CORROSION WAS REMOVED AND TRACK WAS FOUND TO BE OUT OF LIMITS PER MANUFACTURES STRUCTURAL REPAIR MANUAL. SEAT TRACK WAS REPLACED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

LEFT INBOARD SEAT TRACK BETWEEN FRAMES 13 AND 23 CORRODED. CORROSION WAS REMOVED AND TRACK WAS FOUND TO BE OUT OF LIMITS PER MANUFACTURES STRUCTURAL REPAIR MANUAL. SEAT TRACK WAS REPLACED.

Part: ROD — CORRODED (LT AILERON) · airframe 29,747 hrs · 35,225 cycles

LEFT AILERON TRIM TAB CONTROL ROD WAS FOUND TO BE CORRODED. CORROSION WAS FOUND TO BE BEYOND MANUFACTURERS LIMITS. ROD WAS REMOVED AND REPLACED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

RIGHT OUTBOARD SEAT TRACK BETWEEN FRAMES 13 AND 23 CORRODED. CORROSION WAS REMOVED AND TRACK WAS FOUND TO BE OUT OF LIMITS PER MANUFACTURES STRUCTUAL REPAIR MANUAL. SEAT TRACK WAS REPLACED.

Part: SMOKE DETECTOR — FAILED (CARGO ABY) · airframe 29,747 hrs · 35,225 cycles

AFT CARGO SMOKE LIGHT REMAINED OFF DURING SMOKE DETECTION TEST. REMOVED AND REPLACED SMOKE DETECTOR.

Part: BATTERY PACK — DEFECTIVE (EMERGENCY LIGHTS) · airframe 29,747 hrs · 35,225 cycles

EMERGENCY LIGHTING BATTERY PACK UNIT FOUND DEFFECTIVE DURING CAP CHECK. BATTERY PACK UNIT REMOVED AND REPLACED PER CMM 33-51-21.

Part: BATTERY PACK — DEFECTIVE (EMERGENCY LIGHTS) · airframe 29,747 hrs · 35,225 cycles

EMERGENCY LIGHTING BATTERY PCK UNIT FOUND DEFECTIVE DURING CAP CHECK. BATTERY PACK UNIT REMOVED AND REPLACED PER CMM 33-51-21.

Part: BATTERY PACK — DEFECTIVE (EMERGENCY LIGHTS) · airframe 29,747 hrs · 35,225 cycles

EMERGENCY LIGHTING BATTERY PACK UNIT FOUND DEFECTIVE DURING CAP CHECK. BATTERY PACK UNIT REMOVED AND REPLACED PER CMM 33-51-21.

Part: BATTERY PACK — DAMAGED (EMERGENCY LIGHTS) · airframe 29,747 hrs · 35,225 cycles

EMERGENCY LIGHTING BATTERY PACK UNIT FOUND DAMAGED DURING CAP CHECK. BATTERY PACK AND TRAY NEED TO BE REPLACED. BATTERY PACK (P/N 30-1180) AND TRAY (301-1066) WERE REMOVED AND REPLACED IN ACCORDANCE WITH CMM 33-51-21.

Part: BATTERY PACK — DAMAGED (EMERGENCY LIGHTS) · airframe 29,747 hrs · 35,225 cycles

EMERGENCY LIGHTING BATTERY PACK UNIT FOUND DAMAGED DURING CAP CHECK. BATTERY AND TRAY NEED TO BE REPLACED. BATTERY PACK (P/N 301-1180) AND TRAY (301-1066) WERE REMOVED AND REPLACED IN ACCORDANCE WITH CMM 33-51-21.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 29,747 hrs · 35,225 cycles

LEFT INTERCOSTAL BETWEEN FRAMES 36 AND FRAME 38 CORROSION AROUND ANCHOR NUTS. OUT OF LIMITS PER SRM 63-61-00 FIG 301, MATERIAL THICKNESS .080, MATERIAL REMOVED .025. SEE WC NR 2000-24 FOR FABRICATION. REPLACED LEFT INTERCOSTAL BETWEEN FRAMES 36 AND 38 PER SRM 51-25-01.

Part: BATTERY PACK — DEFECTIVE (EMERGENCY LIGHTS) · airframe 29,747 hrs · 35,225 cycles

EMERGENCY LIGHTING BATTERY PACK UNIT FOUND DEFECTIVE DURING CAP CHECK. BATTERY PACK UNIT REMOVED AND REPLACED PER CMM 33-51-21.

Part: MOUNT — CHAFED (NR 2 ENGINE) · airframe 29,747 hrs · 35,225 cycles

NR 2 ENGINE "Z" MOUNT TUBE 7 CHAFED. REPAIRED BY BLENDING AND FOUND TO BE WITHIN LIMITS PER ATR SRI DO/TS-3777/07-9189.

Part: MOUNT — CHAFED (NR 2 ENGINE) · airframe 29,747 hrs · 35,225 cycles

NR 2 ENGINE AFT "Z" MOUNT TUB NR 2 CHAFED. CHAFE REPAIRED BY BLENDING OUT IN ACCORDANCE WITH ATR SRT DO/TS-3777/07-9189 SRAS 4238. BLEND OUT WITHIN LIMITS.

Part: BEAM — CORRODED (T/E FLAP) · airframe 29,747 hrs · 35,225 cycles

CORROSION ON LEFT WING FLAP BEAM AT RIB 8, FOUND TO BE BEYOND LIMITS. LEFT WING FLAP BEAM RIB 8 REPLACED.

Part: FITTING — CORRODED (TE FLAP) · airframe 29,747 hrs · 35,225 cycles

RIGHT INBOARD FLAP, FLAP ARM AND FLAP BEAM CORRODED AT FLAP RIB 5. RIGHT INBOARD FLAP BEAM, FLAP, FLAP ARM REPLACED AT RIB 5.

Part: SKIN — PUNCTURED · airframe 29,747 hrs · 35,225 cycles

PASSENGER DOOR EXTERNAL SKIN PUNCTURED. EXTERNAL SKIN REPAIRED PER SRM 52-00-00.

Part: TAB HINGE — CORRODED (RT AILERON) · airframe 29,747 hrs · 35,225 cycles

RT AILERON INBOARD TAB HINGE CORRODED. REMOVED AND REPLACED INBOARD HINGE.

Part: BRACKET — CORRODED (RT WING) · airframe 29,747 hrs · 35,225 cycles

RIGHT WING AT RIB 17 OF LOWER REAR SPAR SIDE STAY BRACKET CORRODED. REMOVED AND REPLACED FITTING IN ACCORDANCE WITH SRM 51-25-04.

Part: STRUCTURE — CRACKED (SERVICE DOOR) · airframe 29,747 hrs · 35,225 cycles

LOWER FORWARD CORNER OF SURROUND STRUCTURE ON RIGHT SERVICE DOOR CRACKED. REMOVED AND REPLACED STRUCTURE IN ACCORDANCE WITH SRM 51-25-01.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 29,747 hrs · 35,225 cycles

ALL EMERGENCY LIGHTING DID NOT WORK IN THE ARM POSITION. REMOVED AND REPLACED EMERGENCY BATTERY PACK. EMERGENCY LIGHTING TESTED SATISFACTORY.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 29,747 hrs · 35,225 cycles

ALL EMERGENCY LIGHTING DID NOT WORK IN THE ARM POSITION. REMOVED AND REPLACED EMERGENCY BATTERY PACK. EMERGENCY LIGHTING TESTED SATISFACTORY

Part: SPAR — CORRODED (RT WING) · corrosion level 2 · airframe 29,747 hrs · 35,225 cycles

CORROSION ON RIGHT WING REAR SPAR LOWER HORIZONTAL FLANGE BETWEEN THE WING RIBS 16 AND 19.

Part: FITTING — CORRODED (T/E FLAP) · airframe 29,747 hrs · 35,225 cycles

LEFT WING INBOARD FLAP RIB 9 ARM CORRODED. REMOVED AND REPLACED LEFT INBOARD FLAP ARM AT RIB 9.

Part: FITTING — CORRODED (T/E FLAP) · airframe 29,747 hrs · 35,225 cycles

LEFT WING OUTBOARD FLAP RIB 1O ARM CORRODED. REMOVED AND REPLACED LEFT WING OUTBOARD FLAP ARM AT RIB 10.

Part: FITTING — CORRODED (T/E FLAP) · airframe 29,747 hrs · 35,225 cycles

FOUND LEFT WING FLAP ARM AT RIB 23 IS CORRODED. REPLACED LEFT WING FLAP ARM AT RIB 23.

Part: FITTING — CORRODED (T/E FLAP) · airframe 29,747 hrs · 35,225 cycles

RIGHT WING OUTBOARD FLAP ARM RIB 14 CORRODED. REPLACED RIGHT WING OUTBOARD FLAP ARM AT RIB 14.

Part: FIRE LOOP — MALFUNCTIONED (NR 2 NACELLE) · airframe 28,931 hrs · 33,920 cycles

NR 2 ENGINE FIRE LOOP A MEL'D, JUST PRIOR TO LANDING, CREW REPORTED NR 2 ENGINE FIRE WARNING. CREW VERIFIED NO FIRE, THIS SAME PROBLEM OCCURRED ON PREVIOUS FLIGHT. MX REMOVED AND REPLACED LOOP A HARNESS, REPOSITIONED LOOP B HARNESS CLAMP CUSHIONS, MEL RESTORED.

Part: FIRE LOOP — MALFUNCTIONED (NR 2 NACELLE) · airframe 28,930 hrs · 33,919 cycles

JUST PRIOR TO LANDING, CREW RECEIVED NR 2 ENGINE FIRE WARNING ON FIRE HANDLE AND CONDITION LEVER. CREW VERIFIED NO FIRE, SHUT DOWN AFTER LANDING AS A PRECAUTION. MX FOUND NR 2 ENGINE LOOP A FAULT AT 40 PERCENT POWER. MEL NR 2 LOOP A AND RELEASED AIRCRAFT BACK TO SERVICE.

Part: FIRE LOOP — MALFUNCTIONED (NR 2 NACELLE) · airframe 28,931 hrs · 33,920 cycles

NR 2 ENGINE FIRE LOOP MEL'D, JUST PRIOR TO LANDING, CREW REPORTED NR 2 ENGINE FIRE WARNING. CREW VERIFIED NO FIRE, THIS SAME PROBLEM OCCURRED ON PREVIOUS FLIGHT.

Part: WIRE — BROKEN (CABIN)

IAH- DURING 1A CHECKIT WAS NOTED THAT THE AFT SERVICE DOOR EMERGENCY LIGHTON BOTTOM OUT. IAH- MAINTENANCE REPAIRED WIRE NUMBER3351-106 ON EXIT SIGN, PERFORMED A OPERATIONAL CHECK OF THE EMERGENCY LIGHTING SYSTEM, NO DEFECTS NOTED, AND, THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: BEARING — FAILED (MLG WHEEL)

FLIGHT 3992, THE CREW REPORTED THAT THE NOSE GEAR HAD A BAD SHIMMY AFTER TOUCH DOWN AND DURING TAXI. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THAT THE NUMBER FOUR MAIN WHEEL ASSEMBLY HAD SHIFTED OUTBOARD. MAINTENANCE REMOVED AND REPLACED THE RIGHT HAND MAIN LANDING GEAR SWINGING LEVER ASSY, NR 4 BRAKE ASSY, NR 3 & 4 MAIN WHEEL ASSY'S, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: PSEU — INOPERATIVE (80 VU RACK RIGHT)

IAH- DURING FLIGHT 3889, THE CREW NOTED THAT THE LANDING GEAR SYSTEM #2(OVERHEAD) RIGHT MAIN INDICATES DOWN IN FLIGHT. IAH- MAINTENANCE REMOVED AND REPLACEDTHE PSEU, PERFORMED A OPERATIONAL CHECK OF THE LANDING GEAR SYSTEM,VERIFIEDNORMAL GEAR INDICATION, NO DEFECTS NOTED, AND, THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: PSEU — FALSE INDICATION (90 VU RACK)

IAH - FLT 3695 - Crew reported that the number 2 gear system showed a down indication. The aircraft landed at IAH where mainetanance removed and replaced the proximity switch electronic unit. Gear swings were acvcomplished and the aircraft was approved for return to service.

Part: LIGHT — INOPERATIVE (CABIN)

IAH- WHILE PERFORMING A LINE/WEEKLY CHECK IT WAS NOTED THAT THE GALLEY FLOOR LEVEL EXIT LIGHT FAILED TO ILLUMINATE. MAINTENANCE REMOVED AND REPLACED THE GALLEY FLOOR LEVEL EXIT LIGHT, PERFORMED A OPERATIONAL CHECK OF THE EMERGENCY LIGHTING SYSTEM, NO DEFECTS NOTED, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: CONNECTOR — DIRTY (LT MLG)

SHV FLIGHT 3340 - CREW REPORTED THAT THERE WAS NOT ANY GEAR INDICATION FOR SYSTEM 2. THE AIRCRAFT LANDED AT SHV WITHOUT INCIDENT WHERE MAINTENANCE CLEANED THE LEFT MLG DOWNLOCK CANNON PLUG AND PERFORMED AN OPERATIONAL CHECK OF THE GEAR INDICATION SYSTEM. THE AIRCRAFT OPERATIONALLY CHECKED GOOD AND WAS APPROVED FOR RETURN TO SERVICE.

Part: ENGINE — OVERSERVICED (NR 1 ENGINE)

CLE FLIGHT 3176 THE CREW REPORTED THAT ON STARTUP OF NR 1 ENGINE THERE WAS SMOKE IN THE COCKPIT. THE CREW SHUTDOWN THE ENGINE. MAINTENANCE INSPECTED AND FOUND THE NR 1 ENGINE WAS OVERSERVICED WITH OIL. MAINTENANCE SERVICED THE NR 1 ENGINE TO PROPER LEVEL. OPERATIONAL CHECKS WERE GOOD. THE AIRCRAFT WAS RELEASED FOR SERVICE.

Part: SMOKE — DETECTED (COCKPIT)

CLE FLIGHT 3147 THE CREW REPORTED A BURNING SMELL AND SMOKE IN COCKPIT AFTER STARTING NR 1 ENGINE AND GOING TO MAX RPM. THE ENGINE WAS SHUT DOWN. MAINTENANCE INSPECTED AND STARTED THE NR 1 ENGINE AND RAN NR 1 PACK BOTH FULL HOT AND COLD WITH ENGINE AT MAX RPM. NO SMOKE OR BURNING SMELL WAS NOTED. THE AIRCRAFT WAS RELEASED FOR SERVICE.

Part: RELAY — INOPERATIVE (COCKPIT)

IAH - FLIGHT 2990, THE CREW REPORTED A SMOKE DETECTION WARNING DURING TAXI. THE AIRCRAFT RETURNED TO THE GATE WITHOUT INCIDENT WHERE MAINTENANCE PLACED THE NUMBER ONE PACK ON MEL 21-50-01 CONTROL NUMBER 004868, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. THE AIRCRAFT RETURNED TO IAH ON FLIGHT 3556 ON 01/23/01 WHERE MAINTENANCE REMOVED AND REPLACED THE AVIONICS VENT FAN RELAY, REMOVE MEL 21-50-01 CONTROL NR 004868, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.

Part: CHANNEL — CORRODED (BS 38-39)

DURING C-CHECK, FOUND CORROSION ON PASSENGER DOOR THRESHOLD SUPPORT CHANNEL BETWEEN FRAMES 38 AND 39. REMOVED AND REPLACED SUPPORT CHANNEL IAW SRM 51-24-01 AND SRM 51-25-02. AIRCRAFT APPROVED FOR RETURN TO SERVICE. ACTT: 20,664.9 HOURS. ACTC: 23,807. (X)

Part: ANGLE — CORRODED (BS 38-39)

DURING C-CHECK, FOUND CORROSION ON PASSENGER DOOR THRESHOLD SUPPORT ANGLE BETWEEN FRAMES 36 AND 38. REMOVED AND REPLACED ANGLE IAW SRM 51-25-02. AIRCRAFT APPROVED FOR RETURN TO SERVICE. ACTT: 20,664.9 HOURS. ACTC: 23,807. (X)

Part: FLOORBEAM — CORRODED (BS 40)

DURING C-CHECK, FOUND CORROSION ON FLOORBEAM AT FRAME 40, RBL 13. REMOVED CORROSION, FABRICATED AND INSTALLED REPAIR STRAPS IAW SRM 51-21-42 AND EC5310-01037. AIRCRAFT APPROVED FOR RETURN TO SERVICE. ACTT: 20,664.9 HOURS. ACTC: 23,807. (X)

Part: BULB — FAILED (FUSELAGE)

BTV - FLT 3680 - MAINTENANCE FOUND EMERGENCY EXIT AISLE PATH LIGHT INOPERATIVE. REMOVED AND REPLACED LIGHT BULB AND OPS CHECKED SYSTEM GOOD. (M)

Part: POWER SUPPLY — INOPERATIVE (ROW 3WL)

BTV - DURING LINE CHECK ON RON BTV, FOUND FORWARD EMERGENCY FLOOR TRACK LIGHTS INOPERATIVE (EVERY OTHER ONE). REMOVED AND REPLACED POWER SUPPLY UNIT AT 3 WL, OPS CHECKED GOOD. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

LOWER RIGHT EMERGENCY SIGN INOP AT REAR OF THE CABIN. REMOVED AND REPLACED EMERGENCY POWER SUPPLY BATTERY PACK, OPS CHECKED GOOD. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

LEFT AND RIGHT EMERGENCY EXIT SIGNS WILL NOT ILLUMINATE. REMOVED AND REPLACED BATTERY PACK AT FUSELAGE POSITION 3WL, OPS CHECKED GOOD. (M)

Part: POWER SUPPLY — INOPERATIVE (FUSELAGE)

UPPER EMERGENCY EXIT LIGHTS INOPERATIVE. REMOVED AND REPLACED POWER SUPPLY AT 3WL. (M)

Part: DOUBLER — CORRODED (FUSELAGE)

IAH - DURING C-CHECK INSPECTION, FOUND VHF ANTENNA DOUBLER CORRODED. MAINTENANCE REMOVED AND REPLACED THE DOUBLER IAW ATR SRM 51-25-02. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: ATTACH PLATE — CORRODED (COCKPIT)

IAH - DURING C-CHECK INSPECTION, FOUND CAPTAINS SIDE SEAT, FLOOR ATTACH PLATE CORRODED. MAINTENANCE REMOVED AND REPLACED THE ATTACH PLATE IAW ATR-42 SRM 51-25-02. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: SEAT TRACK — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, FOUND RIGHT INBOARD AFT SEAT TRACK CORRODED. MAINTENANCE REMOVED AND REPLACED THE SEAT TRACK IAW ATR SRM 51-70-00. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: FLOORBEAM — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, FOUND FLOORBEAM 39 CORRODED. MAINTENANCE REMOVED ALL CORROSION AND INSTALLED 4 DOUBLERS, IAW CONTINENTAL EXPRESS ENGINEERING CHANGE/REPAIR AUTHORIZATION (ECRA) EC5310-01037. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: CREASE BEAM — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, FOUND LEFT SIDE CREASE BEAM PLATE CORRODED BETWEEN FRAME SUPPORT AND FRAME 39. MAINTENANCE REMOVED AND REPLACED THE CREASE BEAM PLTE IAW ATR-42 SRM 51-25-02. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: SEAT TRACK — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, FOUND RIGHT OUTBOARD AFT SEAT TRACK CORRODED. MAINTENANCE REMOVED AND REPLACED THE SEAT TRACK, IAW ATR SRM 51-70-00. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: BULB — FAILED (CABIN)

DURING LINE CHECK, FOUND MAIN CABIN ENTRY DOOR EMERGENCY EXIT LIGHT INOP. RELAMPED ENTRY DOOR EXIT LIGHT. OPS CHECK GOOD. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

BTV - DURING 1A INSPECTION, FOUND EMERGENCY LIGHTS FAILED TO OPERATE PROPERLY DURING TEST OF SYSTEM. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY PACK. OPS CHECK OF SYSTEM GOOD. (M)

Part: CONTACTS — DIRTY (CABIN)

BTV - DURING 3A INSPECTION, FOUND NR 1, NR 3, AND NR 5 FLOOR LIGHT (EMERGENCY LIGHTS) INOPERATIVE. CLEANED CONTACTS ON NR 1 POWER SUPPLY BATTERY PACK. OPS CHECKED SYSTEM GOOD. (M)

Part: BATTERY — DISCHARGED (CABIN)

BTV - DURING 2A INSPECTION, FOUND EMERGENCY LIGHTS FAILED TEST. MAINTENANCE REMOVED AND REPLACED EMERGENCY POWER SUPPLY BATTERY AT 29WL. EMERGENCY LIGHTING SYSTEM OPERATIONAL CHECKED GOOD. (M)

Part: SEAT TRACK — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, THE LEFT FLIGHT ATTENDANT SEAT TRACK WAS FOUND TO BE CORRODED. MAINTENANCE REMOVED AND REPLACED THE SEAT TRACK AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: CLIP — CORRODED (FRAME 40)

IAH - DURING C-CHECK INSPECTION, THE STRINGER CLIP AT FRAME 40 ON STRINGER 15 WAS FOUND TO BE CORRODED. MAINTENANCE REMOVED THE CORRODED CLIP, FABRICATED AND INSTALLED A SERVICEABLE CLIP PER ATR42 SRM 53-00-00 AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: FLOOR BEAM — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, THE FLOOR SUPPORT BEAM AT FRAME 36 WAS FOUND TO BE CORRODED. MAINTENANCE REMOVED AND REPLACED THE SUPPORT BEAM AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: ANTENNA — CORRODED (FUSELAGE)

IAH - DURING C-CHECK INSPECTION, THE NR 1 DME ANTENNA WAS FOUND TO BE CORRODED. MAINTENANCE REMOVED AND REPLACED THE ANTENNA AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: SEAT TRACK — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, THE RIGHT FLIGHT ATTENDANT SEAT TRACK WAS FOUND TO BE CORRODED. MAINTENANCE REMOVED AND REPLACED THE SEAT TRACK AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: STRINGER — CORRODED (FUSELAGE)

IAH - DURING C-CHECK INSPECTION, STRINGER 15RT WAS FOUND TO BE CORRODED BETWEEN FRAMES 39 AND 40. MAINTENANCE REMOVED THE DAMAGED SECTION OF STRINGER AND FABRICATED AND INSTALLED A SERVICEABLE SECTION PER ATR 42 SRM 53-00-00. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: SEAT TRACK — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, THE AFT SEAT TRACK ON THE RIGHT SIDE FRAME 39-40, WAS FOUND TO BE CORRODED. MAINTENANCE REMOVED AND REPLACED THE SEAT TRACK AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: FITTING — CHAFED (PAX DOOR)

IAH - DURING C-CHECK INSPECTION, THE UPPER FORWARD PAX DOOR SHOOT BOLT ROLLER FITTING WAS FOUND TO BE CHAFED. MAINTENANCE REMOVED AND REPLACED THE FITTING AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: STEP — CRACKED (PAX DOOR)

IAH - DURING C-CHECK INSPECTION, THE PAX DOOR TOP STEP INTERNAL LEFT SIDE WAS FOUND TO BE CRACKED. MAINTENANCE INSTALLED A DOUBLER REPAIR PER ATR SRM 51-25-02 AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: RIB — CRACKED (RIGHT WING)

IAH - DURING C-CHECK INSPECTION, RIB 30 ON THE RIGHT WING WAS FOUND TO BE CRACKED AT ATTACHMENT FOR PANELS 615 AND 616AR. MAINTENANCE STOP DRILLED THE CRACK AND INSTALLED A DOUBLER REPAIR PER ATR SRM 51-70-00 AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: SHOOT BOLT — CHIPPED (GALLEY DOOR)

IAH - DURING C-CHECK INSPECTION, THE FORWARD SHOOT BOLT ON THE GALLEY SERVICE DOOR WAS FOUND TO BE CHIPPED. MAINTENANCE REMOVED AND REPLACED THE SHOOT BOLT AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: SEAT TRACK — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, THE LEFT FLIGHT ATTENDANT SEAT TRACK WAS FOUND TO BE CORRODED. MAINTENANCE REMOVED AND REPLACED THE SEAT TRACK AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: SHOOT BOLT — CHIPPED (GALLEY DOOR)

IAH - DURING C-CHECK INSPECTION, THE AFT SHOOT BOLT ON THE GALLEY SERVICE DOOR WAS FOUND TO BE CHIPPED. MAINTENANCE REMOVED AND REPLACED THE SHOOT BOLT AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: SEAT TRACK — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, THE RIGHT CENTER SEAT TRACK WAS FOUND TO BE CORRODED AT FRAME 36 ATTACHMENT. MAINTENANCE REMOVED THE DAMAGED SECTION AND PERFORMED A SPLICE REPAIR PER ATR SRM 53-53-00 AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: SKIN — CRACKED (CARGO DOOR)

IAH - DURING C-CHECK INSPECTION, THE INTERNAL SKIN PANEL ON THE CARGO DOOR WAS FOUND TO BE CRACKED. MAINTENANCE PERFORMED A DOUBLER REPAIR PER ATR42 SRM 51-70-00 AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: FLOORBEAM — CORRODED (CABIN)

IAH - DURING C-CHECK INSPECTION, THE FLOOR SUPPORT BEAM AT FRAME 38 WAS FOUND TO BE CORRODED. MAINTENANCE REMOVED AND REPLACED THE FLOORBEAM. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: FITTING — CHAFED (PAX DOOR WAY)

IAH - DURING C-CHECK INSPECTION, THE UPPER AFT PAX DOOR SHOOT BOLT ROLLER FITTING WAS FOUND TO BE CHAFFED. MAINTENANCE REMOVED AND REPLACED THE FITTING AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (M)

Part: EEL BATTERY — DISCHARGED (CABIN)

IAH - DURING AN A-CHECK INSPECTION, SEVERAL AISLE PATH LIGHTS WERE FOUND TO BE INOPERATIVE. MAINTENANCE REMOVED AND REPLACED EMERGENCY LIGHT BATTERY PACKS. THE EMERGENCY LIGHTS OPERATIONAL CHECKED GOOD, AND THE AIRCRAFT WAS RETURNED TO SERVICE. (W)

Part: BEARING — RUSTED (ELEVATOR)

IAH - DURING C-CHECK INSPECTION, FOUND ELEVATOR TORQUE TUBE, LT OUTER PITCH UNCOUPLING MECHANISM BEARING RUSTED. MAINTENANCE REMOVED AND REPLACED THE BEARING IAW ATR 42 MM 27-31-42 RAI-10000-005. A/C TT 9,267.5. CYC. 11,818. (X)

Part: RIVET — MISSING (FRAME 22)

IAH - DURING C-CHECK INSPECTION, FOUND ONE MISSING RIVET ON STR 18, RT SIDE, JUST BELOW FRAME 22. MAINTENANCE PERFORMED AN INTERIM REPAIR BY PROTECTING AND SEALING VACANT HOLE PER CONTINENTAL EXPRESS ENGINEERING CHANGE/REPAIR AUTHORIZATION EC5330-01073. TT 9,267.5. CYC. - 11,818. (X).