N108LN

Part: UNKNOWN — ODOR (CABIN) · airframe 8,237 hrs · 26,643 cycles

DURING TAKE-OFF AND CLIMB THERE WAS A STRONG ODOR THROUGHOUT THE CABIN. THE BEST WAY TO DESCRIBE IT, IS THAT IT SMELLS LIKE PROPANE. THIS HAS BEEN AN ONGOING ISSUE WITH THE AIRCRAFT. THE CREW DID NOT FEEL COMFORTABLE FLYING IN THE AIRCRAFT UNTIL FIXED, SO THE AIRCRAFT WAS LEFT AT NORTHWEST HOSPITAL INTUCSON UNTIL MAINTENANCE CAN TAKE A LOOK AT IT. CHECKED 30R PANEL AND BEHIND INSTRUMENT PANEL. COULD NOT DUPLICATE.

Part: FLOOR PANEL — CORRODED (ZONE 200) · airframe 8,057 hrs · 25,794 cycles

THERE IS CORROSION DAMAGE TO THE CABIN FLOOR EDGING (PN: 350A21-1359-20/21).

Part: SUPPORT — DAMAGED (ZONE 200) · airframe 8,057 hrs · 25,794 cycles

DAMAGE TO THE RH BI-DIRECTIONAL SUPPORT FITTING (P/N: 350A211232.23) AND SUPPORT BEAM (P/N: 350A211293.20) IN THE FORM OF CHAFING CAUSED DUE TO CABLE. THE CHAFE DAMAGE AT SUPPORT BEAM MEASURED TO BE APPROXIMATELY 0.30” X 0.20” X 0.015”. THE CHAFE DAMAGE AT BI-DIRECTIONAL SUPPORT FITTING MEASURED TO BE APPROXIMATELY 0.25” X 0.20” X 0.010

Part: BULKHEAD WEB — CHAFED (ZONE 200) · airframe 8,057 hrs · 25,794 cycles

DAMAGE TO THE 15° BULKHEAD LH WEB (PN: 350A21-1032.86) IN THE FORM OF SEVERAL CHAFES. THE CHAFES WERE REPORTED TO BE 0.20” X 0.10” AND 0.004” DEEP, AS WELL AS 0.20” X 0.30” AND 0.010” DEEP

Part: STRUCTURE — GOUGED (ZONE 200) · airframe 8,057 hrs · 25,794 cycles

DAMAGE TO THE LH UPPER CARGO EDGING (P/N: 350A211041.22) IN THE FORM OF A GOUGE CAUSED WHILE INSTALLING BLIND FASTENER. THE GOUGE DAMAGE NEAR AFT SIDE OF THE LH EDGING AND WAS MEASURED TO BE APPROXIMATELY 0.40” X 0.15” X 0.02”.

Part: STIFFENER — WORN (ZONE 100) · airframe 8,057 hrs · 25,794 cycles

DAMAGE TO THE LH STA2700 STIFFENER (LH PN: 350A21-1071.22; RH PN: 350A211071.23) IN THE FORM OF WEAR CAUSED BY A NEARBY BOLT HEAD.

Part: STRUCTURE — GOUGED (ZONE 100) · airframe 8,057 hrs · 25,794 cycles

GOUGE AT THE OUTBOARD FLANGE RIVNUT LOCATION IN THE FORM OF SHEAR OUT. THE GOUGE WAS MEASURED TO BE APPROXIMATELY 0.1” X 0.1285”X 0.060”.

Part: UNKNOWN — UNSERVICEABLE (INSTRUMENT PANEL) · airframe 7,600 hrs · 24,012 cycles

FUMES AND SMOKE APPARENTLY COMING FROM GNS530 AFTER START UP. MECHANIC MEL'D GNS530 DISABLED AND COLLARED CIRCUIT BREAKER. SUSPECT MALFUNCTIONING GNS530 OR WIRING LEADING TO GNS 530.

Part: FRAME — CHAFED (ZONE 200) · airframe 7,005 hrs · 22,201 cycles

THE LH X-FRAME HAS ONE CHAFED AREA LOCATED ON ITS OBD BEADED FACE AFT UPPER SIDE MEASURING 0.3” X 0.3” X 0.035” DEEP.

Part: AIR FILTER — OVERSERVICED · airframe 6,296 hrs · 19,954 cycles

A PRECAUTIONARY LANDING WAS MADE AFTER AN UNIDENTIFIED ODOR CAME INTO THE CABIN FROM THE ENGINE COMPARTMENT. IT WAS THEN DISCOVERED THAT THE AIR FILTER WAS OVERSERVICED AND THE OIL WAS DRIPPING ONTO THE HOT ENGINE. THE ENGINE WAS CLEANED AND THE EXCESS OIL WAS WIPED OFF OF THE ENGINE DECK, THEN AN ENGINE RUN-UP WAS PERFORMED TO ENSURE THIS WAS INDEED THE SOURCE OF THE STRANGE SMELL. THEN ENGINE WAS CHECKED AGAIN AND A SMALLER AMOUNT OF OIL WAS DETECTED. THE OIL WAS CLEANED OFF OF THE ENGINE. THE AIRCRAFT WAS THEN RETURNED TO SERVICE.

Part: SUPPORT FRAME — CHAFED (FUSELAGE) · airframe 5,279 hrs · 16,398 cycles

THE TRANSMISSION SUPPORT FRAME, PN 350A21-1041-143, HAS CHAFING DAMAGE ON THE LOWER FLANGE, FROM AN UNSECURED CABLE, PN 704A34-1302-23. PN 350A38-1040-20 ATTACHES TO PN 350A21-1041-143.

Part: DOOR — DELAMINATED (CARGO BAY) · airframe 5,045 hrs · 15,070 cycles

RIGHT LATERAL CARGO HOLD DOOR HAS DELAMINATION.

Part: ADAPTER — CRACKED (MAIN ROTOR) · airframe 4,792 hrs · 13,603 cycles

FREQUENCY ADAPTER IS CRACKED ON THE RED BLADE.

Part: UNKNOWN — ODOR · airframe 4,686 hrs · 13,022 cycles

STRONG ODOR OF FUEL PROMPTED PRECAUTIONARY LANDING. POST FLIGHT INSPECTION DID NOT REVEAL ANY FUEL LEAKS.

Part: CONNECTOR — CONTAMINATED (FIRE WARNING) · airframe 3,890 hrs

DURING TAKEOFF, HAD A FLICKERING ENGINE FIRE LIGHT. REMOVED CONNECTOR ON ENGINE DECK, CLEANED WITH CONTACT CLEANER, SUSPECT MOISTURE, APPLIED STABILANT TO CONNECTOR REINSTALLED CONNECTOR. FIRE LIGHT FLICKED 2-3 TIMES AGAIN. APPLIED STABILANT TO CONNECTOR. FOUND MOISTURE AGAIN IN CONNECTOR PLUG ON ENGINE DECK. CLEANED, PERFORMED CHECK FLIGHT, NO DEFECTS NOTED. ACFT RELOCATED TO AIRPORT AND PILOT AGAIN REPORTED FIRE LIGHT ON START UP. CLEANED ALL TERMINALS AT FIRE DETECTORS, CHECKED CONTINUITY OF FIRE DETECTORS NO DEFECTS NOTED PERFORMED GROUND RUN AND CHECK FLIGHT, NO DEFECTS NOTED PILOT RETURNED AND CONFIRMED THE PILOT HAD RETURNED TO BASE WITH NO FIRE LIGHT REPORTED.

Part: COIL — FAILED (ACM) · airframe 3,858 hrs

AIR CONDITIONER COMPRESSOR FAILED IN-FLIGHT RESULTING IN SMOKE/FUMES IN THE COCKPIT. VISUAL INSPECTED AND FOUND AIR CONDITIONING BELT SLIGHTLY LOOSE, BELT TIGHTENED, BUT NO OTHER DEFECTS NOTED DURING INSPECTION OF SYS. GROUND RUN REVEALED AIR CONDITIONER COMPRESSOR CLUTCH NOT ENGAGING FULLY. RETURNED ACFT TO SERVICE FOR FLIGHT TO MX FACILITY. AT MX FACILITY DETAILED TROUBLESHOOTING FOUND AIR CONDITIONING COMPRESSOR CLUTCH COIL FAILURE WAS CAUSE OF CLUTCH NOT ENGAGING FULLY AND CAUSE OF SMOKE AND FUMES. COMPRESSOR ASSY REPLACED.

Part: DRIVE SHAFT — SHEARED (STARTER GEN) · airframe 3,406 hrs · 8,373 cycles

THE PILOT REPORTED A GENERATOR LIGHT DURING ENGINE START. HE ATTEMPTED TO RESET THE GENERATOR WITH NO SUCCESS. DURING SUBSEQUENT TROUBLESHOOTING THE MECHANIC FOUND THE STARTER/GENERATOR DRIVESHAFT SHEARED. THE STARTED/GENERATOR WAS REPLACED WITH A SERVICEABLE STARTER/GENERATOR.