N7037E

Part: BEAM — CRACKED (ZONE 400) · airframe 36,135 hrs · 34,450 cycles

DURING MAINTENANCE A CRACK WAS DISCOVERED IN THE CHANNEL(P/N 5654107-15) THAT ATTACHES THE RT CROSSOVER BEAM(P/N 5654104-12) TO THE RT INBOARD ENGINE BEAM(P/N 5654109-7.) WHEN THIS CHANNEL WAS REMOVED FOR REPLACEMENT, A CRACK IN THE RH INBOARD ENGINE BEAM WAS DISCOVER. THIS CRACK MEASURES .228 IN LENGTH. THE CRACK IN THE ENGINE BEAM WAS NOT VISIBLE UNTIL THE CHANNEL WAS REMOVED. PICTURES OF A SIMILAR CRACK WERE POSTED ON HYIA20190605001.

Part: ANGLE — CORRODED (VERTICAL STAB) · airframe 35,958 hrs · 34,140 cycles

DURING MAINTENANCE SURFACE CORROSION WAS DISCOVERED ON THE RIGHT HAND AFT VERTICAL STABILIZER ANGLE (P/N: 5131007-6) BETWEEN APPROXIMATE W.L. 143.52-167.52. THE DEEPEST CORRODED AREA IN THIS SPAN MEASURES APPROXIMATELY .029" DEEP. THIS ANGLE WILL BE REMOVED AND REPLACED WITH NEW PARTS.

Part: ANGLE — CORRODED (VERTICAL STAB) · airframe 35,958 hrs · 34,140 cycles

DURING MAINTENANCE SURFACE CORROSION WAS DISCOVERED ON THE LEFT AFT ANGLE OF THE VERTICAL STABILIZER BETWEEN APPROXIMATE WL 143.52-167.52. THE DEEPEST CORRODED AREA IN THIS SPAN MEASURES APPROXIMATELY .031 DEEP. THIS ANGLE WILL BE REMOVED AND REPLACED WITH NEW PARTS.

Part: INDICATOR — FAILED (MLG) · airframe 35,691 hrs

PILOT REPORTED "RIGHT LANDING GEAR LIGHT BURNT OUT. REPLACED WITH BULB AND WHEN REPLACED, 3 GREEN APPEARED BUT THEN SPARKED AND WENT OUT." MAINTENANCE INSPECTED AND DETERMINE THE LANDING GEAR INDICATOR BLOCK TO BE AT FAULT. THE LANDING GEAR INDICATOR BLOCK WAS REPLACED.

Part: DIMMER — FAILED (INSTRUMENT LIGHT) · airframe 35,532 hrs

DURING CLIMB OUT, THE CAPTAIN'S FLIGHT INSTRUMENT ILLUMINATION FAILED. SHORTLY AFTER, SMELLED A BURNING ELECTRICAL AND LIGHT SMOKE. MAINTENANCE INSPECTED AND FOUND THE INSTRUMENT LIGHT DIMMER ASSEMBLY AT FAULT. REPLACED THE DIMMER AND TRANSISTOR Q4 WITH NO FURTHER DEFECTS NOTED.

Part: CHANNEL — CORRODED (NACELLE) · airframe 35,303 hrs · 32,879 cycles

WHILE PERFORMING A BORE SCOPE VISUAL INSPECTION OF THE THE NACELLE FITTINGS IAW AD2017-10-19, CORROSION WAS NOTED ON THE RT OUTBOARD NACELLE FITTING. DISASSEMBLE THE STACK UP AT THE BACK OF THE ENGINE BEAM CAP AND DOUBLERS, FOR FURTHER INSPECTION. NOTED THAT THE 5654111-2 CHANNEL WAS HEAVILY CORRODED AND WAS MISSING MOST OF IT'S PROTECTIVE COATING. THE FITTING AND CHANNEL WHERE REMOVED. NO OTHER DEFECTS WERE NOTED TO THE REMAINING ENGINE BEAM STRUCTURE. SEVERAL AREAS OF CORROSION WHERE NOTED ON ALL SURFACES OF THE FITTING AND IN THE MOUNTING HOLES TO THE CHANNEL. BELIEVE THAT WITH THE PROTECTIVE COATING WAS COMPROMISED ON THE CHANNEL, CORROSION BEGAN TO DEVELOP AND SPREAD TO THE NACELLE FITTING. BOTH THE NACELLE FITTING. BOTH THE FITTING AND CHANNEL WERE REPLACED WITH FACTORY NEW PARTS.

Part: FITTING — CORRODED (NACELLE) · airframe 35,303 hrs · 32,879 cycles

WHILE PERFORMING A BORE SCOPE VISUAL INSPECTION OF THE THE NACELLE FITTINGS IAW AD2017-10-19, CORROSION WAS NOTED ON THE RT OUTBOARD NACELLE FITTING. DISASSEMBLE THE STACK UP AT THE BACK OF THE ENGINE BEAM CAP AND DOUBLERS, FOR FURTHER INSPECTION. NOTED THAT THE 5654111-2 CHANNEL WAS HEAVILY CORRODED AND WAS MISSING MOST OF IT'S PROTECTIVE COATING. THE FITTING AND CHANNEL WHERE REMOVED. NO OTHER DEFECTS WERE NOTED TO THE REMAINING ENGINE BEAM STRUCTURE. SEVERAL AREAS OF CORROSION WHERE NOTED ON ALL SURFACES OF THE FITTING AND IN THE MOUNTING HOLES TO THE CHANNEL. BELIEVE THAT WITH THE PROTECTIVE COATING WAS COMPROMISED ON THE CHANNEL, CORROSION BEGAN TO DEVELOP AND SPREAD TO THE NACELLE FITTING. BOTH THE FITTING AND CHANNEL WERE REPLACED.

Part: SPAR CAP — CRACKED · airframe 35,167 hrs · 32,605 cycles

DURING ROUTINE INSPECTION, A CRACK WAS FOUND IN THE RIGHT HAND SIDE LOWER FORWARD CARRY THROUGH SPAR CAP; IN THE VICINITY OF THE LOWER WING ATTACH FITTING (B.L. 47.25). THE CRACK EXTENDS THROUGH THE BULK SECTION OF THE SPAR CAP. CORRECTIVE ACTION WILL BE TO INSTALL NEW SPAR CAP. UPON DISASSEMBLY THE DAMAGED SPAR CAP WILL BE ROUTED FOR ANALYSIS OF FAILURE. IF RELEVANT- ANALYSIS OF FAILURE WILL BE ADDED TO THIS SDR RECORD.

Part: RIB — CRACKED (RT WING) · airframe 34,842 hrs · 31,889 cycles

DURING A ROUTINE INSPECTION, A CRACK WAS LOCATED AT RIB AT RT WS 106.79. THE CRACK ORIGINATED FROM A LOCK FASTENER. REPAIRED IAW MAINTENANCE MANUAL.

Part: FAN — BURNED OUT (CABIN) · airframe 34,510 hrs · 31,142 cycles

PILOT REPORTED AN ODOR OF SMOKE IN THE CABIN. MAINTENANCE INSPECTED AND FOUND CABIN FAN BURNED OUT. REMOVED AND REPLACED CABIN FAN IAW MM 21-20-00.

Part: DRAG BRACE — CRACKED (NLG) · airframe 32,385 hrs

AT SCHEDULED INSPECTION, NLG DRAG BRACE, OEM PN 5142002-5, WAS FOUND TO BE CRACKED IN THE AREA OF NLG ACTUATOR ATTACH POINT. METHOD OF INSPECTION WAS DYE PENETRANT. THIS CRACK WAS FOUND TO BE BEYOND LIMIT ALLOWABLE. THIS UNIT HAS BEEN SCRAPPED & A REPLACEMENT DRAG BRACE HAS BEEN INSTALLED IN ACFT.

Part: ATTACH FITTING — CORRODED (ZONE 500) · airframe 31,646 hrs

DURING A SCHEDULED MAINTENANCE EVENT, AT REMOVAL OF LT WING TO FACILITATE OTHER MX, THE LT AFT LOWER FUSELAGE FITTING WAS FOUND TO BE SEVERELY CORRODED. FITTING, PN IS 5011024-2, ASSUMED TO BE ORIGINAL FROM ACFT MFG WITH 31,645.5 HOURS TT IN SERVICE. REMOVEED AND INSTALLED NEW FITTING AND PERFORMED DETAILED VISUAL INSPECTION OF SURROUNDING STRUCTURE PRIOR TO REASSEMBLY.

Part: STRAP — CORRODED (WING SPAR) · airframe 31,646 hrs

DURING A REGULARLY SCHEDULED MAINTENANCE EVENT, THE LEFT LOWER NACELLE SKIN (PN 5654100-30) AND ASSOCIATED HEAT SHIELD WERE REMOVED FOR OTHER MAINTENANCE. AFTER REMOVAL, SEVERE CORROSION WAS FOUND AT LEFT SPAR STRAP INCLUDING SPAR CAP FASTENER FAILURE. VISUAL INSPECTION OF THIS AREA WOULD NOT HAVE BEEN REGULARLY POSSIBLE WITHOUT REMOVAL OF SKIN ASSEMBLY AND OUTBOART NACELLE HEAT SHIELD. REPAIR DECISION IS REMOVAL AND REPLACEMENT OF SPAR STRAP ASSEMBLY ALONG WITH A DETAILED INSPECTION OF THE SURROUNDING AREAS. OPEN

Part: FLOORBEAM — CRACKED (ZONE 100) · airframe 31,592 hrs

DURING SCDEDULED INSPECTION, MX FOUND AFT CARRY THROUGH SPAR FLOORBEAM FLANGE CRACKED.

Part: TIRE — FLAT (ZONE 700) · airframe 31,540 hrs

DURING THE LANDING ROLLOUT, THE PILOT NOTICED A FLAT LT MAIN TIRE. THE ACFT MAINTAINED CONTROL AND WAS STOPPED CLEAR OF THE ACTIVE RUNWAY. UPON INSPECTION BY MX THE TIRE WAS FOUND TO BE FLAT SPOTTED. THE LT MAIN WHEEL ASSEY WAS SUBSEQUENTLY REPLACED.

Part: AXLE — CRACKED (RT MLG) · airframe 30,200 hrs

PILOT REPORTED, ON COMPLETION OF FLIGHT 1033, WHILE PARKING AIRCRAFT, RIGHT MAIN GEAR LOCKED UP. MAINTENANCE INSPECTED AIRCRAFT, FOUND RIGHT MAIN LANDING GEAR AXLE CRACKED. MAINTENANCE REMOVED AND REPLACED LOWER BARREL AND AXLE ASSEMBLY. AIRCRAFT RELEASED BACK TO SERVICE.

Part: CIRCUIT BREAKER — FAILED (AVIONICS)

AVIONIC CIRCUIT BREAKER/SWITCH FAILED IN FLIGHT CAUSING COMPLETE AVIONIC FAILURE CREW UTILIZED EMERGENCY AVIONIC BUS SWITCH AND LANDED WITHOUT INCIDENT. SEVERAL SUCH FAILURES RECORDED RECENTLY. THIS SWITCH HAS A HIGH UTILIZATION FACTOR.(K)

Part: POTENTIOMETER — FAILED (DIMMER BOARD)

AN ODOR OF ELECTRICAL SMOKE FILLED THE CABIN. AIRCRAFT LANDED WITHOUT INCIDENCE. FOUND THE DIMMER BOARD AT FAULT. DIMMER ASSY REPLACED AND AIRCRAFT RETURNED TO SERVICE.

Part: SWITCH — FAILED (AVIONICS MASTER)

AFTER TAKEOFF, AIRCRAFT EXPERIENCED COMPLETE AVIONICS ELECTRICAL FAILURE DUE TO AVIONICS MASTER SWITCH FAILURE. EMERGENCY AVIONICS BUS WAS ACTIVATED AND POWER WAS RESTORED.