N329AM

ATA 6200

Part: TUBE — INTERFERENCE (COLLETIVE) · airframe 4,804 hrs · 15,183 cycles

CONTROL INTERFERENCE. CYCLIC DISPLACES IN LATERAL AXIS WHEN COLECTIVE IS MOVED. PILOT WAS MOVING THE AIRCRAFT FROM THE GRASS NEXT TO THE HELIPAD TO HELIPAD. WHILE PICKING THE AIRCRAFT UP INTO A HOVER HE NOTED THAT WHILE PULLING COLLECTIVE THE CYCLIC WAS MOVING LATERALLY. HE COULD OVER COME THIS ISSUE, HOWEVER IT MADE HANDLING THE AIRCRAFT AWKWARD. WE INSPECTED THE FLIGHT CONTROL SYSTEM, ADJUSTED THE FRICTION ON THE COLLECTIVE AND CYCLIC SYSTEMS. DISCOVERED THE CYCLIC BALANCING SPRING NEED ADJUSTING AND ADJUSTED IT. TEST FLEW THE AIRCRAFT AND IT STILL HAD THE SAME ISSUE. WE INSPECTED THE CONTROL MORE AND NOW WE PLAN TO CHECK THE AIRCRAFT FLIGHT CONTROL RIGGING.

ATA 5270

Part: WARNING LIGHT — FALSE ACTIVATION (DOOR) · airframe 4,723 hrs · 14,973 cycles

DOOR LIGHT ILLUMINATED. LANDED AT DESTINATION HOSPITAL, CALLED MECHANIC, AND MELED IAW AIRMETHODS' EC130 MEL DOCUMENT. PRECAUTION WHILE THE MEL IS IN EFFECT IS TO VISUALLY VERIFY ALL THE DOORS ARE SECURED PRIOR TO LIFT OFF.

ATA 5311

Part: FRAME — CRACKED (BS 2258) · airframe 3,469 hrs · 11,429 cycles

DAMAGE TO THE X2258 RH CROSSBEAM (PN: 350A21-4065.22) IN THE FORM OF A CRACK. THE CRACK WAS MEASURED TO BE APPROXIMATELY 1.20” IN LENGTH.

ATA 5320

Part: FLOOR SUPPORT — CRACKED · airframe 3,470 hrs · 11,429 cycles

DAMAGE TO THE AFT FUSELAGE FLOOR SUPPORT IN THE FORM OF CRACKS. THE FLOOR SUPPORT HAD A 0.50 INCH CRACK AND A 6.70 INCH CRACK. THE FLOOR SUPPORT HAD A 0.50” CRACK AND TWO CRACKS MEASURING 0.70 AND 0.80 IN LENGTH AT RIVET HOLES ALONG THE LENGTH OF THE BASE OF THE PART

ATA 5342

Part: ATTACH FITTING — CRACKED (HORIZONTAL STAB) · airframe 2,954 hrs · 9,922 cycles

TO COMPLETE INSPECTIONS OF THE TAIL BOOM AND HORIZONTAL STAB ASSEMBLY. THE HORIZONTAL WAS REMOVED AND IT WAS THEN FOUND DURING A VISUAL INSPECTION OF THE ATTACHMENT FITTINGS THAT THE UPPER LEFT HAND HAD CRACKED COMPLETELY IN HALF.

ATA 7200

Part: SEAL — SEPARATED (ENGINE) · airframe 1,654 hrs · 5,592 cycles

DURING TROUBLESHOOTING OF THE ENGINE ELECTRICAL INDICATION SYSTEMS FOR POSSIBLE CAUSE OF ENGINE POWER CHECK FAILURE, FOUND THAT THE INTAKE COMPRESSOR BLADES SUSTAINED DAMAGE. ON FURTHER INSPECTION AND REMOVAL OF THE INTAKE SHROUD AND THE INLET BARRIER FILTER IT WAS FOUND THAT THE AFT FILTER ELEMENT PLENUM SEAL WAS MISSING. THE SEAL ITSELF WAS APPROX 16.5" LONG AND APPROX .3750" WIDE. THE D-SEAL IS LOCATED ON THE DOWNSTREAM SIDE OF THE BARRIER FILTER AND IS 1 OF 4 D-SEAL STRIPS BONDED WITH RTV108 TO THE UPPER PLENUM HOUSING. THE AFT SEAL DISBONDED AND WAS INGESTED INTO THE ENGINE. SMALL RUBBER PARTICLES WERE FOUND IN THE CREVICES IN THE INTAKE SHROUD AND RUBBER TRANSFER MARKS WERE ALSO PRESENT ON THE INTAKE SHROUD. ENGINE AIR FILTER SYSTEM - EC130, PN 1130IN1-1, SN 0129.

ATA 3140

Part: DISPLAY — FAILED (COCKPIT) · airframe 1,654 hrs · 5,590 cycles

DISCOVERED BURNED ODOR IN CABIN WHILE RETURNING TO BASE. VERIFIED THAT HEATING AND DEMISTER WAS STILL OFF. FAILED MESSAGE AND PUSHED RESET AND FAILED AGAIN. ODOR HAD DISSIPATED AT THIS POINT, OVER AIRPORT AND LANDED UNEVENTFULLY. ON SHUTDOWN, FAILURE MESSAGE STATED CODE 39, KEYBOARD FAILURE/ SCREEN MODULE (LT AND RT). TROUBLESHOT IAW EC130B4, AMM 31-61-00, 1-1 AND FOUND VEMD HAD INTERNAL FAILURE.