N908FX

Part: FRAME — DENTED (FRM 19) · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK, MULTIPLE DENTS OVERLYING FRAME 19, BETWEEN STRINGER 13 - 15R. REPAIR IAW ES 2110 16 10293.

Part: FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK, LEFT WING OUTER BOX LOWER MIDDLE JUNCTION FITTING AT RIB 13 HAS CORROSION. REPAIR IAW SRAS CETS 2125 16 10261 ISSUE A.

Part: SPAR — CORRODED (LT WING) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK, LEFT WING FRONT SPAR LOWER CHORD HAS LEVEL 2 CORROSION BETWEEN RIBS 4 - 5. REPAIRED IAW SRAS DT S-909 14 8250 DATED 5 18 2016.

Part: PANEL — CORRODED (ZONE 300) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK, PANEL 323AL LE INNER SURFACE HAS AREAS OF CORROSION ON THE BOTTOM RIB. REPLACE PANEL WITH OEM PART.

Part: PANEL — CORRODED (ZONE 300) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK, PANEL 323AL LE INNER SURFACE HAS AREAS OF CORROSION ON THE 2ND FROM BOTTOM RIB. REPLACED PANEL WITH OEM PART.

Part: STRINGER — CORRODED (FRAMES 15-17) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK, STRINGER 3AR HAS AREAS OF CORROSION FRAMES 15 - 17. STRINGER SPLICE IAW SRM 530000-300-826-A01.

Part: STRINGER SPLICE — CRACKED (FRAMES 15-17) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

WO 157920 NR 200069 HEAVY CHECK COE & MAJOR REPAIR. STRINGER 2AR IS CRACKED AT FRAME 15 WITH AREAS OF LEVEL 2 CORROSION FRAMES 15 - 17. STRINGER SPLICE IAW SRM 530000-300-826-A01.

Part: SKIN — CORRODED (FRAME 14) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK, FWD CENTER FUSELAGE RT UPPER SKIN PANEL HAS LEVEL 2 CORROSION AT INSULATION STANDOFF, FRAME 14, STRINGER 7R - 8R. REPAIR IAW SRM 53-00-00-300-803-A01.

Part: STRINGER — CORRODED (FRAMES 14-17) · corrosion level 2 · airframe 34,246 hrs · 45,627 cycles

DURING HEAVY CHECK, STRINGER 5R HAS AREAS OF CORROSION AT FRAMES 14 - 17. REPAIR IAW SRM 530000-300-826-A01.

Part: STRINGER — CORRODED (FRAMES 14-15) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK, STRINGER 2AL HAS AREAS OF CORROSION BETWEEN FRAMES 14 - 15. STRINGER SPLICED IAW SRM 530000-300-826-A01.

Part: STRINGER SPLICE — CORRODED (FRAMES 15-17) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK. STRINGER 5AR HAS AREAS OF CORROSION FRAMES 15 - 17. REPLACED THE STRINGER SPLICE IAW SRM 530000-300-826-A01.

Part: STRINGER — CORRODED (FRAMES 15-17) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK, STRINGER 3R HAS AREAS OF CORROSION FRAMES 15 - 17. INSTALLED STRINGER SPLICE IAW SRM 530000-300-826-A01.

Part: DOUBLER — CORRODED (FRAMES 19-20) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK. CORROSION ON LOWER TCAS ANTENNA DOUBLER, FRAMES 19 - 20, STRINGER 21L - 21R. REPLACED DOUBLER WITH OEM PART.

Part: SKIN — DAMAGED (ZONE 200) · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK. SCRIBE LINES ON CROWN SKIN UNDER VHF 1 ANTENNA. REPAIRED IAW CETS 2055 16 1028.

Part: STRINGER — CORRODED (FRAMES 13-14) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK, STRINGER 9R HAS CORROSION FRAMES 13 - 14. REPAIRED STRINGER SPLICE IAW SRM 530000-300-826-A01.

Part: SKIN — CORRODED (FRAMES 20-21) · corrosion level 2 · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK, CORROSION ON SKIN UNDER ADF 1 ANTENNA. REPAIR IAW SRAS CETS 2126 16 10258 DATED 5 27 16.

Part: FLOOR SUPPORT — BROKEN (FRAMES 39-40) · airframe 34,246 hrs · 45,625 cycles

DURING HEAVY CHECK. LT LONGITUDINAL FLOOR SUPPORT, BETWEEN FRAMES 39 - 40 IS BROKEN. REPAIRED IAW EO 5315-01.

Part: ECU — FAULTY (NR 2 ENGINE) · airframe 34,165 hrs · 45,531 cycles

FLIGHT 0673 PDX & MFR AIR TURN BACK & DISCREPANCY. NR 2 ENG PARAMETERS & POWER FLUCTUATED IN FLIGHT. CREW COMPLIED WITH QRH. DE-SELECTED NR 2 ENG CONTROL UNIT. RETURNED, NO EMER DECLARED. NUMBER 2 ENG CONTROL UNIT FAULT, ISSUE DEFERRED. DEFERRAL CLEARED BY REPLACING NR 2 ENG CONTROL UNIT. ENG TRIM COMPLIED WITH IAW JIC 73-23-61 OPT 10040-001. OPERATIONS & PERFORMANCE CHECKED GOOD.

Part: RIVET — DAMAGED (RT WING) · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE, MAJOR REPAIR. RT WING, TWO DAMAGED RIVET HEADS AT RIB 13 - 14 AT STIFFENER NR 3 & NR 5 ON FITTING. REPAIR IAW SRAS S572R0325 8378 DATED 4/23/14. SEE AMOC ANM-116-14-266 DATED 4/25/14.

Part: FITTING — CORRODED (LT ELEVATOR) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

DURING HEAVY CHECK, LT ELEVATOR OTBD TE FITTING HAS CORROSION ON UPPER FLANGE MATING SURFACE. REPLACED WITH OEM PART.

Part: SKIN — DENTED (FUSELAGE) · airframe 33,352 hrs · 44,665 cycles

FUSELAGE UPPER CROWN SKIN AFT OF FRAME 22 BETWEEN STRINGER 1P & 1AP HAS DENT OUT OF LIMITS. REPAIR IAW SRM 53-31-21 ITEM 1.

Part: ATTACH ANGLE — CORRODED (STABILIZER) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

ATTACH ANGLE FOR PANEL 325DL HAS LEVEL 2 CORROSION. REPLACED WITH OEM.

Part: SKIN — DENTED (FUSELAGE) · airframe 33,352 hrs · 44,665 cycles

RIGHT TAIL SECTION SKIN HAS DENT. REPAIR IAW SRM 53-00-00 FIG 403.

Part: BUSHING — DAMAGED (ZONE 500) · airframe 33,352 hrs · 44,665 cycles

DURING HEAVY CHECK, LT FWD WING TO FUSELAGE FRAME FITTING BUSHING HAS DAMAGE. REPAIR IAW SRAS S535R00411555 DATED 3/27/2014.

Part: PANEL — DENTED (FUSELAGE) · airframe 33,352 hrs · 44,665 cycles

LEFT SIDE OF FUSELAGE UPPER CROWN PANEL HAS DENT. REPAIR IAW SRM 53-00-00 FIGURE 405.

Part: FRAME — DENTED (FUSELAGE) · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE MAJOR REPAIR. DENT DAMAGE AT FRAME 10 ABOVE STRINGER 19L. PATCH REPAIR IAW 53-00-00 FIG 408.

Part: SKIN — DENTED (FUSELAGE) · airframe 33,352 hrs · 44,665 cycles

DENT OUT OF LIMITS 10.5 INCHES ON SKIN FWD OF FRAME 19, 9.5 INCHES RT OF CTR. REPAIR IAW SRM 53-00-00 FIG 420.

Part: SKIN — DENTED (FUSELAGE) · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE MAJOR REPAIR. DENT IN FUSELAGE SKIN AT WL 2640 RT BETWEEN FRAMES 6 & 7. CLOSE PROXIMITY TO EXISTING REPAIR BETWEEN FRAMES 5 & 6. REPAIR IAW SRAS DTS 972 14 8280 DATED 3/11/2014.

Part: INTERCOSTAL — CRACKED (CARGO DOOR) · airframe 33,352 hrs · 44,665 cycles

WORK ORDER 132169 NR 200094 HEAVY CHECK COE MAJOR REPAIR. CRACK IN THE INTERCOSTAL AT STATION 7141 IN THE FWD CARGO DOOR. DOUBLER REPAIR IAW SRM 52-31-00.

Part: RIB — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

DURING HEAVY CHECK. LT OTBD FLAP RIB 14 HAS CORROSION ON INBD SIDE. REPLACED FLAP WITH SERVICEABLE FLAP.

Part: RETAINER SEAL — CORRODED (PANEL) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

RETAINER SEAL FOR PANEL HAS LEVEL 2 CORROSION. REPLACED WITH NEW PART IAW IPC 53-91-40 FIG 15 ITEM 80.

Part: INTERCOSTAL — CRACKED (CARGO DOOR) · airframe 33,352 hrs · 44,665 cycles

WORK ORDER 132169 NR 200090 HEAVY CHECK COE MAJOR REPAIR. CRACK IN THE INTERCOSTAL AT STATION 7065 IN THE FWD CARGO DOOR. DOUBLER REPAIR IAW SRM 52-31-00 FIG 405.

Part: PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE MINOR REPAIR. PANEL 533BB HAS LEVEL 2 CORROSION. REPLACED WITH OEM PANEL.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE MINOR REPAIR. FWD CARGO DOOR AFT LATCH INNER FITTING HAS LEVEL 2 CORROSION IN BOLT HOLES. REPLACED WITH NEW OEM PART.

Part: HINGE FITTING — CORRODED (TE FLAP) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK MINOR REPAIR. RT OTBD FLAP INBD HINGE ARM ATTACHED TO FLAP HAS LEVEL 2 CORROSION. REPLACED WITH OEM PART.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE MINOR REPAIR. FWD CARGO DOOR AFT LATCH FITTING HAS LEVEL 2 CORROSION IN BOLT HOLES. REPLACED FITTING WITH NEW OEM PART.

Part: SPAR — CORRODED (LT WING) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

LEFT WING FRONT SPAR LOWER STRIP SLAT HAS FRETTING CORROSION LEVEL 2 DAMAGE. REPAIR IAW SRAS DT S-909 14 8250 DATED 2/27/14.

Part: ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE. DORSAL PANEL MOUNTING ANGLES ARE CORRODED, FWD OF PANEL 321AL. BOTH ANGLES WERE REPLACED WITH NEW PARTS IAW ATR42 SRM.

Part: SKIN PANEL — CHAFED (FUSELAGE) · airframe 33,352 hrs · 44,665 cycles

LEFT FWD CTR SKIN PANEL UNDER ICE SHIELD HAS CHAFING DAMAGE. REPAIR IAW SRAS DT S-976 14 8246 DATED 3/10/2014.

Part: HINGE — CORRODED (LT WING) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

DROP DOWN PANEL 531AB MOUNT HINGE IS EXFOLIATED. REPLACED WITH NEW PART.

Part: ANGLE — CORRODED (RT ELEVATOR) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE MAJOR REPAIR. RT ELEVATOR AFT INBD CORNER L ANGLE HAS LEVEL 2 CORROSION. FABRICATION OF ANGLE DWG 38S55275004.

Part: FITTING — CORRODED (RT ELEVATOR) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

WORK ORDER 132169 NR 300033 HEAVY CHECK COE MINOR REPAIR. RT ELEVATOR HORN HEAT FITTING HAS AREAS OF BARE METAL WITH LEVEL 2 CORROSION. REPLACED WITH OEM PART.

Part: ATTACH ANGLE — CORRODED (RT WING) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

RIGHT WING REAR SPAR HINGE ATTACH ANGLE FOR PANEL 631AB RIB 5 & 6 HAS LEVEL 2 CORROSION. REPLACED PART BY FABRICATION IAW SRM 57-12-20 FIG 102 ITEM 50.

Part: FITTING — CORRODED (ZONE 300) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

DURING HEAVY CHECK, LT ELEVATOR HORN HEAT FITTING HAS AREAS OF CORROSION. REPLACED WITH OEM PART.

Part: ANGLE — CORRODED (LT ELEVATOR) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

LT ELEVATOR, AFT INBD CORNER, L ANGLE IS CORRODED. REPAIRED BY PART REPLACEMENT.

Part: ATTACH ANGLE — CORRODED (RT WING) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

RIGHT WING REAR SPAR HINGE ATTACH ANGLE FOR PANEL 631AB HAS LEVEL 2 CORROSION. REPLACED BY FABRICATION IAW SRM 57-12-20 FIG 102 ITEM 65.

Part: SPAR — DAMAGED (LT ELEVATOR) · airframe 33,352 hrs · 44,665 cycles

DURING HEAVY CHECK. LT ELEVATOR REAR SPAR, EXISTING PLUGGED HOLES UNDER BRACKET & 1ST PLY DAMAGED. REPAIR ACCOMPLISHED IAW ATR STRUCTURAL REPAIR APPROVAL SHEET IAW DT S 1490 14 8307 ISSUE A.

Part: ATTACH ANGLE — CORRODED (RT WING) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

RIGHT WING REAR SPAR HINGE ATTACH ANGLE FOR PANEL 631AB BETWEEN RT WING RIB 6 & 7 HAS LEVEL 2 CORROSION. REPLACED BY FABRICATION IAW SRM 57-12-20 FIG 102 ITEM 45.

Part: FITTING — CORRODED (RT ELEVATOR) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE MINOR REPAIR. RT ELEVATOR TE FITTING UPPER HALF. REPLACED WITH OEM PART.

Part: FITTING — CORRODED (RT ELEVATOR) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK MINOR REPAIR. RT ELEVATOR TE FITTING LOWER HALF HAS LEVEL 2 CORROSION. REPLACED WITH OEM PART.

Part: ATTACH ANGLE — CORRODED (RT WING) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

RIGHT WING REAR SPAR HINGE ATTACH ANGLE FOR PANEL 631AB RIB 7 & 8 HAS LEVEL 2 CORROSION. REPLACED BY FABRICATION IAW SRM 57-12-20 FIGURE 102 ITEM 40.

Part: TEE FITTING — CORRODED (RT AILERON) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE. RT AILERON, INTERNAL TEE FITTING, ON AFT SIDE OF FRONT SPAR IS CORRODED. REPAIRED BY REPLACEMENT WITH SERVICEABLE AILERON.

Part: RIB — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

DURING HEAVY CHECK. RT OTBD FLAP CORROSION ON INTERNAL FLANGES OF RIB 20 & RIB 12. REPLACED WITH SERVICEABLE FLAP.

Part: HINGE FITTING — CORRODED (LT AILERON) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

DURING HEAVY CHECK, LT INBD AILERON HINGE FITTING AT RIB 24 HAS CORROSION. REPLACED WITH OEM PART.

Part: SPAR — CORRODED (RT WING) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE MAJOR REPAIR. RT WING REAR SPAR UPPER STRIP SLAT HAS FRETTING DAMAGE, LEVEL 2 CORROSION AT RIB 17. REPAIR IAW SRAS S572R0323 8242.

Part: WINDOW FRAME — CRACKED (COCKPIT) · airframe 33,352 hrs · 44,665 cycles

CRACK INDICATION IN PREVIOUS REPAIR BLEND ON LT WINDSHIELD FRAME AT NODE 5. REPAIR IAW SRAS DT S-863 14 8237 DATED 2/28/2014.

Part: SKIN PANEL — CRACKED (FUSELAGE) · airframe 33,352 hrs · 44,665 cycles

DENT WITH CRACK IN LT UPPER SKIN PANEL APPROXIMATELY 14 INCHES AFT OF FRAME 18, 2 INCHES ABOVE STRINGER 6. FUSELAGE SKIN REPAIR IAW ATR42 SRM 53-00-00 REPAIR 403.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

HEAVY CHECK COE MAJOR REPAIR. LEVEL 2 CORROSION ON EXTERIOR FUSELAGE SKIN AROUND AFT CARGO AFT LOWER CORNER. REPAIR IAW SRAS ASI E 36440 99 1635 DATED 3/14/2014.

Part: FITTING — CORRODED (LT AILERON) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

DURING HEAVY CHECK. CORROSION FOUND ON LT AILERON, INTERNAL FITTING ON AFT SIDE OF FRONT SPAR. AILERON REPLACED WITH SERVICEABLE AILERON.

Part: SKIN — CORRODED (LT WING) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

LEFT LOWER WING SKIN AT APPROXIMATELY RIB 7 HAS LEVEL 2 CORROSION JUST FWD OF DROP DOWN PANEL 531AB. REPAIR IAW SRAS DT S-809 14 8235 DATED 2/24/2014.

Part: SKIN — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 33,352 hrs · 44,665 cycles

DURING HEAVY CHECK, LT HORIZONTAL STAB LE PANEL 331 HAS CORROSION ON SKIN. REPLACED LE OEM PART.

Part: CONTROL UNIT — FAULTY (ANTI-SKID SYS) · airframe 32,548 hrs · 43,811 cycles

MAIN BRAKES FAILED TO OPERATE WHEN ATTEMPTING TO STOP AIRCRAFT FOR PARKING WITH NR 2 ENGINE SHUT DOWN. REMOVED AND REPLACED ANTI-SKID CONTROL UNIT. AIRCRAFT RETURNED TO SERVICE.

Part: SKIN — DAMAGED (ZONE 200) · airframe 32,460 hrs · 43,685 cycles

HEAVY CHECK, FOUND OPEN HOLES BENEATH AFT CARGO DOOR FWD AND AFT UPPER HINGE HALVES BETWEEN FRAMES 37 AND 39 AND BETWEEN STRINGERS 5L AND 6L. FOUND WHILE ACCOMPLISHING M7 SB ATR42-53-030 & EO 5344-05) REPAIRED PER M7 DRAWING, PERFORMED STEP 1 THRU 6 OF DRAWING 42-470000 SFO-3.

Part: HINGE — CORRODED (ZONE 600) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

HEAVY CHECK, ON INSTALLATION OF RT AILERON MOVEABLE TAB, FOUND INBD HINGE BRACKET EXFOLIATED (LENGTH .75", WIDTH 1", DEPTH .50"). FABRICATED AND INSTALLED HINGE IAW SRM.

Part: BULKHEAD — CORRODED (ZONE 100) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

HEAVY CHECK, FWD SIDE OF FWD PRESSURE BULKHEAD, RT LOWER BONDING POINT FOR RADOME HAS LEVEL 2 CORROSION. FABRICATED AND INSTALLED DOUBLER, SHIM AND PLUG IAW SRM.

Part: HINGE — CORRODED (ZONE 600) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

HEAVY CHECK, ON INSTALLATION OF RT AILERON MOVEABLE TAB FOUND INBD HINGE BRACKET EXFOLIATED (LENGTH .75", WIDTH 1", DEPTH .50"). FABRICATED AND INSTALLED HINGE IAW SRM.

Part: SPLICE — CORRODED (AILERON) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

HEAVY CHECK, MAJOR REPAIR, LEVEL 2 CORROSION ON RT AILERON FIXED TAB MOUNT FLANGE LOWER SIDE ON ENTIRE MATING SURFACE (LENGTH 48", WIDTH 1", DEPTH .023"). FABRICATED AND INSTALLED NEW FIXED TAB MOUNT TO AILERON.

Part: BULKHEAD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

HEAVY CK / MAJOR REPAIR / LEVEL 2 CORROSION, FWD SIDE OF FWD PRESSURE BULKHEAD, LT OUTBOARD MOST LOWER BONDING POINT FOR RADOME HAS LEVEL 2 CORROSION (LENGTH 1", WIDTH 1", DEPTH .05"). REMOVED CORROSION, FABRICATED AND INSTALLED REPAIR DOUBLER, SHIM AND PLUG PER SRM.

Part: SKIN — CORRODED (ZONE 600) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

HEAVY CHECK, ON REMOVAL OF DE-ICE BOOT FROM PANEL 614 FOUND LEVEL 2 CORROSION ON SKIN (LENGTH 12", WIDTH 2", DEPTH .025"). REMOVED CORROSION, REMOVED & INSTALLED NEW LEADING EDGE PANEL 614.

Part: BULKHEAD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

HEAVY CK / MAJOR REPAIR / LEVEL 2 CORROSION, FWD SIDE OF FWD PRESSURE BULKHEAD, RT OUTBOARD MOST MID LOWER BONDING POINT FOR RADOME HAS LEVEL 2 CORROSION (LENGTH 1", WIDTH 1", DEPTH .01"). SUBMITTED TO ATR FOR STRUCTURAL REPAIR INSTRUCTIONS.

Part: FITTING — CORRODED (ESCAPE HATCH) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

HEAVY CK / LEVEL 2 CORROSION: OVERHEAD HATCH HAS A MACHINED INTERCOSTAL WITH DAMAGE NEXT TO A BAD RIVET BY THE PROX SENSOR. (LENGTH .5", WIDTH .25", DEPTH .025"). REMOVED CORROSION, REPLACED FITTING/ INTERCOSTAL OVERHEAD HATCH.

Part: SKIN — CORRODED (ESCAPE HATCH) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

HEAVY CK / LEVEL 2 CORROSION: OVERHEAD HATCH HAS A MACHINED INTERCOSTAL WITH DAMAGE NEXT TO A BAD RIVET BY THE PROX SENSOR. (LENGTH 1", WIDTH .75", DEPTH .004"). REMOVED CORROSION, REPLACED OUTER SKIN.

Part: SUPPORT BEAM — CHAFED (TE FLAP) · airframe 32,460 hrs · 43,685 cycles

WO 110032 NR 500017 HEAVY CK / MAJOR REPAIR: LT OUTBOARD FLAP CENTER HINGE LOWER SUPPORT BEAM BEARING LOBE IS CHAFED. SUBMITTED TO ATR FOR STRUCTURAL REPAIR INSTRUCTIONS.

Part: SKIN PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

WO 110032 NR 200016 HEAVY CK / MAJOR REPAIR / LEVEL 2 CORROSION: LT INTERNAL AND EXTERNAL SURFACES FUSELAGE SKIN HAS CORROSION AFT OF FRAME 27 BETWEEN STRINGERS 5L AND 6L AT HYDRAULIC LINE PASS THROUGH.(LENGTH 3. ", WIDTH 2.5", DEPTH .015"). BLEND PER SRM AND SUBMIT TO ATR FOR STRUCTURAL REPAIR INSTRUCTIONS.

Part: RIB — CORRODED (TE FLAP) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

WO 110032 NR 500048 HEAVY CK / MAJOR REPAIR / LEVEL 2 CORROSION: LT OUTBOARD FLAP RIB 15 CAM GUIDE MOUNT HAS CORROSION OUT OF LIMITS (LENGTH 1", WIDTH 1", DEPTH .03"). SUBMIT TO ATR AND REPAIR PER STRUCTURAL REPAIR INSTRUCTIONS.

Part: STIFFENER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 32,460 hrs · 43,685 cycles

WO 110032 NR 200022 HEAVY CK / LEVEL 2 CORROSION: FWD SIDE OF FWD PRESSURE BULKHEAD HAS A RIVET WITH A CORRODED BUCKTAIL ON RT SIDE OF CENTER STIFFENER BEHIND WX RADAR ANTENNA (LENGTH 3", WIDTH .650", DEPTH .016"). REMOVED AND REPLACED PER SRM WITH OEM PART.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 32,460 hrs · 43,685 cycles

WO 110032 NR 100008 HEAVY CK COE / MAJOR REPAIR: LEFT O/B LONGITUDINAL FLOORBEAM HAS APPROX 1/2 INCH CRACK AFT OF FRAME 20. FABRICATED AND INSTALLED NEW LONGITUDINAL FLOORBEAM PER EMPIRE'S ENGINEERING ORDER.

Part: SKIN — DELAMINATED (HORIZ STAB) · airframe 32,460 hrs · 43,685 cycles

WO 110032 NR 300003 HEAVY CK COE / MAJOR REPAIR: DELAMINATION ON LT HORIZONTAL STABILIZER UPPER SKIN 8.2 INCHES FROM VERTICAL STABILIZER AND 16.5 INCHES FROM LEADING EDGE SPAR. SUBMIT TO ATR FOR STRUCTURAL REPAIR INSTRUCTIONS.

Part: TRANSCEIVER — FAILED (RADAR) · airframe 31,802 hrs · 42,977 cycles

EN ROUTE FROM RAP TO FSD ON FLIGHT NUMBER 7584: RADAR FAILED AFTER TAKEOFF. SEVERE WEATHER EN ROUTE. PILOTS ELECTED TO RETURN TO RAP. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED RADAR RT. AIRCRAFT RETURNED TO SERVICE.

Part: CREASE BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,636 hrs · 42,787 cycles

HEAVY CHECK COE; MAJOR REPAIR; LEVEL 2 CORROSION: RT CREASE BEAM WEB BETWEEN FRAMES 34 AND 35 HAS TWO AREAS OF LEVEL 2 CORROSION. FABRICATED NEW PART AND REPLACED CREASE BEAM WEB BETWEEN FRAMES 34 AND 35 PER SRM.

Part: PUMP — FAILED (BLUE HYD SYS) · airframe 31,243 hrs · 42,208 cycles

AIR TURN BACK. DURING LANDING GEAR RETRACTION, THE CREW RECEIVED A HYDR WARNING LIGHT FOR THE BLUE HYDR SYS. THEY ALSO OBSERVED THE SYS INDICATED '0' PRESSURE. AFTER RETURNING TO THE AIRPORT THE CREW DISCOVERED THE CIRCUIT BREAKER POPPED. MAINT FOUND THE BLUE SYS PUMP CAUSED THE CIRCUIT BREAKER TO POP. BLUE HYD SYS, PUMP REPLACED.

Part: WIRE — SHORTED (WINDSHIELD HEAT)

RETURN TO BLOCKS. AS THE ACFT WAS TAXIING INTO THE DEICE AREA THE PILOT NOTICED A FLASH OF LIGHT FOLLOWED BY SPARKS FALLING NEAR THE COPILOTS FEET. ELECTRICAL POWER AND THE MAINT INDICATOR ON THE MAINT PANEL WAS POPPED. WIRE HARNESS WIRES SHORTED TO EACH OTHER AND TO THE BACK SHELL, WHERE THE HARNESS CONNECTS TO THE BACK SHELL ON THE CONNECTOR TO THE LT WINDSHIELD HEAT TEMP CONTROLLER. CUT ALL WIRES BACK IN HARNESS PAST DAMAGED AREA, REPAIRED THE WIRES AND REPLACED THE CONNECTOR TO THE LT WINDSHIELD HEAT TEMPERATURE CONTROLLER. (K)

Part: RELEASE CABLE — LACK OF LUBE (FWD CARGO DOOR)

AIR TURNBACK, FLT NR 7304. UPON ROTATION, THE CARGO DOOR UNLOCK LIGHT ILLUMINATED. CREW ELECTED TO RETURNED. AIR CRAFT MADE A SAFE AND NORMAL LANDING. DOOR LOCK RELEASE CABLE WAS LUBRICATED AND AC RETURNED TO SERVICE. AS A PRECAUTION FWD CARGO DOOR LOCK RELEASE CABLE TO BE REPLACED AT NEXT SCHEDULED MAINTENANCE EVENT. (K)

Part: CONNECTOR — DEFECTIVE (RADAR ALTIMETER)

AIR TURN BACK, FLT 8788 - ON CLIMB-OUT AT CPR, THE CREW RECEIVED MULTIPLE RADAR ALTIMETER WARNINGS AS WELL AS GROUND PROXIMITY WARNING SYSTEM AND TERRAIN AHEAD WARNING SYSTEM ERRORS. PILOT ELECTED TO RETURN TO CPR. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED THE COAX CABLE CONNECTOR TO THE TRANSMISSION ANTENNA. (M)

Part: ANTENNA — CORRODED (RADAR ALTIMETER)

AIR TURN BACK, FLT 8813 - ON CLIMB-OUT AT CPR, THE RADAR ALTIMETER WAS VERY ERRATIC WITH MULTIPLE TERRAIN AHEAD WARNINGS. PILOT ELECTED TO RETURN TO CPR. AIRCRAFT LANDED WITHOUT INCIDENT. (M)

Part: PANEL — DENTED (FUSLEAGE)

DENT FOUND ON LT FUSELAGE 1 INCH BELOW STRINGER 14 AND 5 INCHES FORWARD OF FRAME 35. REMOVED DAMAGE. FABRICATED DOUBLER AND INSTALLED ON AIRCRAFT IAW ATR SRM. (M)

Part: PANEL — SCRATCHED (BS 11660)

SCRATCHES FOUND ON RIGHT EXTERNAL FUSELAGE LOWER SKIN AT STRINGER 14R 2 INCHES FORWARD OF FR 25 CLOSE TO STATION 11660. REMOVED EXISTING REPAIR DOUBLER AND INSTALLED A STEEL DOUBLER, EXTENDED TO COVER CORRODED SKIN CUT OUT AT FRAME 25 STRINGER 14 RT FOLLOWING REPAIR DWG 15S535R0211 ISSUE B IAW SRI DOTS-4103/06-7439. REF SRAS S535R0206...2734. (M)

Part: PANEL — DAMAGED (FUSELAGE)

TOOLING MARKS FOUND BEHIND ANGLE BRACKET AT FS 29 TO FR 30 AND STR 5L TO STR 6L ON SKIN OF LT LATERAL UPPER PANEL. FABRICATED AND REPAIRED DOUBLER. INSTALLED AND COMPLETED REPAIR SCHEME IAW ATR SRM. (M)

Part: FRAME — DAMAGED (FUSELAGE)

GOUGE LOCATED ON THE VERTICAL WEB OF FRAME 7 AT BL 0 IN THE NLG WELL. DAMAGE CUTOUT AND FABRICATED DOUBLER INSTALLED PER DO/TS-3265/06-7477 AND DO/TS-3926/06-7477. REF SRAS DO/TS03265/06...3787. (M)

Part: PANEL — DAMAGED (RT NACELLE)

FRETTING DAMAGE FOUND ON RT NACELLE REBATE FLANGE COMMON TO PANEL 486AL AND 486AR. REPLACED FABRICATED REBATE PANELS IAW ATR SRM. (M)

Part: FLANGE — DAMAGED (LT ENG NACELLE)

FRETTING DAMAGE FOUND ON LEFT NACELLE REBATE FLANGE COMMON TO PANEL 476AR. REMOVED REBATE PANEL. FABRICATED AND INSTALLED NEW REBATEPANEL IAW ATR SRM. (M)

Part: PANEL — DENTED (FUSELAGE)

DENT FOUND ON EXTERNAL LT LATERAL UPPER SKIN PANEL AT STRINGER 10L ABD 3 INCHES FORWARD OF FRAME 40. REMOVED DAMAGE. FABRICATED DOUBLER AND FILLER AND INSTALLED ON AC IAW ATR42 SRM. (M)

Part: SKIN — DENTED (FUSELAGE)

DENT WITH TOOLING MARKS FOUND ON PREVIOUS TEMPORARY REPAIR ON RT FUSELAGE 1 INCH BELOW STRINGER 12 AND 5 INCHES AFT OF FRAME 23. DAMAGE REMOVED. FABRICATED DOUBLER AND INSTALLED ON AIRCRAFT IAW ATR42 SRM. (M)

Part: PANEL — DAMAGED (LT NACELLE)

FRETTING DAMAGE ON LT NACELLE REBATE FLANGE COMMON TO PANEL 475AL. REBATE PANEL REMOVED. FABRICATED AND INSTALLED NEW REBATE PANEL IAW ATR42 SRM. (M)

Part: FRAME — CRACKED (FUSELAGE)

CRACK FOUND ON FUSELAGE FRAME 5 LOWER FLANGE CLOSE TO LT NLG WHEEL WELL. CRACK REMOVED AND REINFORCING ANGLE INSTALLED PER ATR REPAIR INSTRUCTIONS DO/TS-3825/06-7654. REF SRAS DO/TS-3825/06...3816. (M)

Part: PANEL — GOUGED (FUSELAGE)

GOUGES DETECTED ON FUSELAGE SECTION 15RT FRAME 25 ON MLG STRUT ATTACHMENT FITTING HOLES. BUSHINGS INSTALLED ON FRAMES, NEW BUSHINGS INSTALLED ON SKIN AND STRAP AT FS 11RT MLG FITTING UPPER FORWARD HOLE PER SRI DO/TS-5448/06-8109, REF SRAS A/C MSN 023...614. (M)

Part: PANEL — DAMAGED (STR 14)

TOOLING DAMAGE FOUND ON RIGHT FUSELAGE LATERAL LOWER SKIN PANEL BELOW STRINGER 14R FROM FR 29 TO FR 30. DAMAGE REMOVED. FABRICATED REPAIR DOUBLER AND INSTALLED ON AIRCRAFT IAW ATR 42 SRM. (M)

Part: FRAME — DAMAGED (FUSELAGE)

TOOLING DAMAGE TO UPPER FUSELAGE FRAME 25 AFT FLANGE BETWEEN STRINGER 4-5 LT. DAMAGE BLENDED OUT PER SRAS DO/TS-3859/06-7653 REPAIR INSTRUCTIONS. REF SRAS DO/TS-3859/06...3772 ISSUE B FOR REPETITIVE INSPECTION. (M)

Part: STRINGER — CORRODED (FUSELAGE)

FOUND LEVEL 2 CORROSION ON STRINGER 16L 3 INCHES FORWARD OF FS 25. STRINGER 16L WAS REMOVED. STRINGER 16L WAS FABRICATED, HEAT TREATED AND INSTALLED ON AIRCRAFT IAW ATR SRM. (M)

Part: PANEL — CRACKED (FUSELAGE)

FOUND CRACK AND DENT ON EXTERNAL FUSELAGE SKIN BETWEEN FR 22 AND FR 23 AND BETWEEN STRINGER 15R AND 16R. DAMAGE REMOVED FROM EXTERNAL FUSELAGE SKIN. FABRICATED AND INSTALLED NEW REPAIR DOUBLER IAW ATR SRM. (M)

Part: ATTACH ANGLE — CORRODED (FUSELAGE)

CORROSION FOUND BETWEEN FS 46 AND FS 47 UPPER AFT WEB COMMON TO QUADRANT INTERCOSTALS. REMOVED QUADRANT INTERCOSTALS. FABRICATED AND INSTALLED INTERCOSTAL ATTACH ANGLES IAW ATR42 SRM. (M)

Part: FRAME — GOUGED (FUSLEAGE)

GOUGE LOCATED ON THE INBOARD AFT RADIUS OF FR 13 LOCATED 3 INCHES UP FROM FLOOR. DAMAGE BLENDED OUT AND REINFORCING DOUBLER INSTALLED PER DO/TS-2986-06-7405 REPAIR INSTRUCTIONS. REF SRAS DO/TS-2986/06..3782. (M)

Part: PANEL — CORRODED (RT WING)

CORROSION FOUND ON RT WING LOWER SURFACE OF LOWER SKIN PANEL AT RIB 10 AROUND AND UNDERNEATH NACELLE FITTING P/N 54310211206. CORROSION EVALUATED TO BE LEVEL 3. CORROSION REMOVED, DAMAGES BLENDED. FABRICATED AND INSTALLED DOUBLER REFERENCE TO SRAS ASI/E/38039/00... 1857 AND S571R0122...3665. (M)

Part: BRACKET — CRACKED (RT FLAP)

BRACKET CRACKED FROM CORRODED FOUND DURING C CHECK INSPECTION. UNIT REPLACED WITH NEW PART.