N845KH

Part: ENGINE — SHUTDOWN (NR 2) · airframe 36,270 hrs · 45,577 cycles

ON LANDING ROLLOUT, NR 2 ENG SHUTDOWN AUTOMATICALLY. POWER LEVERS WERE INTO SLIGHT REVERSE WHEN NR 2 ENG FAILED. FOLLOWED FAULT ISOLATION MANUAL 71-00-00, VISUALLY INSPECTED NR 2 ENG INLET FOR OBSTRUCTION & IGV RING & ACTUATING LINKAGE ASSEMBLY FOR DAMAGE. PERFORMED NR 2 ENG HIGH POWER RUN & OPERATED ENG IN REVERSE. NR 2 ENG FOUND TO BE OPERATING NORMALLY.

Part: ENGINE — FLAMED OUT (NR 2) · airframe 36,270 hrs · 45,362 cycles

NUMBER 2 ENG FLAMED OUT AFTER POWER LEVER WAS BROUGHT TO FLIGHT IDLE UPON LANDING. CREW TAXIED CLEAR OF RNWY & COMPLETED ALL APPLICABLE CHECKLISTS & TAXIED TO PARKING WITHOUT INCIDENT. INSPECTED NR 2 ENG FOR FUEL LEAK, BUT NO FUEL LEAK NOTED. OPERATED NR 2 ENG IAW AMM 71-00-00-05, OPERATION CHECKED NORMAL.

Part: FLAP — MALFUNCTIONED (WING) · airframe 35,147 hrs · 43,408 cycles

FLIGHT KH1104, ON APPROACH FLAPS WOULD NOT EXTEND. ACFT DECLARED AN EMERGENCY & LANDED IN A NO-FLAP CONDITION. ACFT LANDED UNEVENTFULLY & TAXIED BACK TO PARKING AREA.

Part: FITTING — CHAFED (MAIN ENTRY DOOR) · airframe 34,995 hrs · 43,182 cycles

MAIN ENTRY DOOR LOCK PIN FITTING CHAFED. NO LIMITS STATED IN SRM. BLENDED CHAFE AND INSPECTED FOR DAMAGE. RESTORED PROECTIVE FINISH IAW SRM 51-20. AFTER BLENDING, DAMAGE ACCEPTED FOR CONTINUDED OPERATION IAW REPAIR STATEMENT 340SDS034517.

Part: SKIN — PUNCTURED (CARGO DOOR) · airframe 34,998 hrs · 43,183 cycles

CARGO DOOR OUTER SKIN LOWER EDGE PUNCTURED FROM FOREIGN OBJECT CONTACT. DAMAGE INSPECTED FOR CRACKS, FILLED, AND SEALED IAW 340 SRM, CH 51-20-56; ACCEPTED FOR CONTINUED OPERATION IAW REPAIR STATEMENT 340SDS034488.

Part: DOOR — CRACKED (RT MLG)

RT MLG INBD DOOR INNER SKIN CRACKED ALONG LOWER EDGE OF COMPOSITE. DAMAGE FOUND TO BE BEYOND LIMITS OF SRM; SUBMITTED TO MFG FOR REPAIR APPROVAL. PERFORMED COMPOSITE REPAIR IAW SRM, CHS. 51-70 AND 52-80 IAW REPAIR STATEMENT 340SDS034475.

Part: SKIN — DAMAGED (BS 258)

FUSELAGE LT SKIN EDGE, EXTERNAL, GOUGED AT FS 258.0, WL 80, FWD EDGE OF MAIN DOOR OPENING. DAMAGE DETERMINED TO BE BEYOND SRM LIMITS. DAMAGE REPAIRED BY TRIMMING, INSPECTING AND RESTORING PROTECTIVE FINISH IAW SRM, CH 51-20 IAW REPAIR STATEMENT 340SDS034517.

Part: FITTING — CHAFED (DOOR LOCK PIN)

MAIN ENTRY DOOR LOCK PIN FITTING CHAFED; NO LIMITS STATED IN SRM. BLENDED CHAFE AND INSPECTED FOR FURTHER DAMAGE; SUBMITTED DAMAGE TO MFG FOR EVALUATION. RESTORED PROTECTIVE FINISH IAW 340SRM, CH 51-20. AFTER BLENDING, DAMAGE ACCEPTED FOR CONTINUED OPERATION IAW REPAIR STATEMENT 340SDS034517.

Part: STRUCTURE — CRACKED (EXHAUST) · airframe 34,995 hrs · 43,182 cycles

RT UPPER SHROUD CRACKED AT FWD CIRCUMFERENTIAL FLANGE BEYOND LIMITS. REPAIRED IAW REPAIR STATEMENT 340SDS034475.

Part: STRUCTURE — DELAMINATED (FS 756-768.5) · airframe 34,995 hrs · 43,182 cycles

COMPOSITE DAMAGE NOTED ON FUESLAGE RT VENTRAL FIN OTBD FACE, SEVERAL LOCATIONS BETWEEN FS 756 AND 768.5. DAMAGE DETERMINED TO BE BEYOND LIMITS. DAMAGE REPAIRED IAW SRM CH 53-90-10 IAW REPAIR STATEMENT 340SDS034517.

Part: SKIN — PUNCTURED (CARGO DOOR)

CARGO DOOR OUTER SKIN LOWER EDGE PUNCTURED FROM FOREIGN OBJECT CONTACT. DAMAGE INSPECTED FOR CRACKS, FILLED AND SEALED IAW 340 SRM, CH 51-20-56; ACCEPTED FOR CONTINUED OPERATION IAW REPAIR STATEMENT 340SDS034488.

Part: STRUCTURE — DAMAGED

COMPOSITE DAMAGE NOTED ON FUSELAGE RT VENTRAL FIN OTBD FACE, SEVERAL LOCATIONS BETWEEN FS 756.0 AND 768.5. DAMAGE DETERMINED TO BE BEYOND SRM LIMITS. DAMAGE REPAIRED IAW PRINCIPLES OF SRM, CH 53-90-10 IAW REPAIR STATEMENT 340SDS034517.

Part: SKIN — GOUGED (BS 258) · airframe 34,995 hrs · 43,182 cycles

FUSELAGE SKIN GOUGED AT FS 258, WL 80. DAMAGE DETERMINED TO BE BEYOND LIMITS. DAMAGE REPAIRED BY TRIMMING, INSPECTING AND RESTORING PROTECTIVE FINISH IAW SRM 51-20.

Part: SKIN — DENTED (BS 739-749)

FUSELAGE LT AFT SKIN, EXTERNAL, DENTED BETWEEN FS 739 AND 749, ABOVE LT VENTRAL FIN; ALSO, 4 RIVETS INSTALLED IN CHEM-MILLED POCKET. DAMAGE DETERMINED TO BE BEYOND 340 SRM LIMITS. DAMAGE INSPECTED AND SUBMITTED TO MFG FOR EVALUATION. DENTS AND RIVET LOCATIONS FOUND TO ACCEPTABLE FOR CONTINUED SERVICE IAW REPAIR STATEMENT 340SDS034517.

Part: SHROUD — CRACKED (RT NACELLE)

RT UPPER EDUCTOR SHROUD CRACKED AT FORWARD CIRCUMFERENTIAL FLANGE; BEYOND LIMITS IAW SRM. REPAIRED IAW REPAIR STATEMENT 340SDS034475.

Part: SKIN — CORRODED (BS 339) · airframe 34,998 hrs · 43,183 cycles

CORROSION NOTED ON FUSELAGE RT LOWER SKIN AT FS 339 DAMAGE DETERMINED TO BE BEYOND MFG LIMITS AFTER BLENDING TO REMOVE CORROSION. REPLACED DAMAGED FASTENERS AND INSPECTED TO ENSURE ALL DAMAGE WAS REMOVED. RESTORED PROTECTION FINISH IAW SRM 51-20.

Part: SKIN — DENTED (BS 739-749) · airframe 34,995 hrs · 43,182 cycles

FUSELAGE LT AFT SKIN DENTED BETWEEN FS 739 AND 749, ABOVE LT VENTRAL FIN. DAMAGE DETERMINED TO BE BEYOND LIMITS. DAMAGE INSPECTED, FOUND TO BE ACCEPTABLE FOR CONINTUED SERVICE IAW REPAIR STATEMENT 340SDS034517.

Part: SKIN — CORRODED (BS 339)

CORROSION NOTED ON FUSELAGE RT LOWER SKIN, EXTERNAL, AT FS 339.0, BELOW STRINGER SL 1622. DAMAGE DETERMINED TO BE BEYOND SRM LIMITS AFTER BLENDING TO REMOVE CORROSION. REMAINING MATERIAL THICKNESS SENT TO MFG FOR EVALUATION. REPLACED DAMAGED FASTENERS AND INSPECTED TO ENSURE ALL DAMAGE WAS REMOVED. RESTORED PROTECTION FINISH IAW SRM, CH 51-20; DAMAGE ACCEPTED FOR CONTINUED OPERATION IAW REPAIR STATEMENT 340SDS034517.