Avjet Corporation

Operated by AVJET CORP (per NTSB report)

the flight crew's operation of the airplane below the minimum descent altitude without an appropriate visual reference for the runway. Contributing to the cause of the accident were the Federal Aviation Administration's (FAA) unclear wording of the March 27, 2001, Notice to Airmen regarding the nighttime restriction for the VOR/DME-C approach to the airport and the FAA's failure to communicate this restriction to the Aspen tower; the inability of the flight crew to adequately see the mountainous terrain because of the darkness and the weather conditions; and the pressure on the captain to land from the charter customer and because of the airplane's delayed departure and the airport's nighttime landing restriction.

Operated by AVJET (per NTSB report)

THE PIC'S FAILURE TO FOLLOW APPROVED PROCEDURES AND DIRECTIVES; THE PIC'S FAILURE TO ATTAIN/MAINTAIN DIRECTION CONTROL OF THE AIRPLANE, THE PIC'S FAILURE TO ABORT THE TAKEOFF IN A TIMELY MANNER; AND THE PIC'S FAILURE TO FOLLOW PROPER ABORTED TAKEOFF PROCEDURES.

Part: LEG ASSY — BROKEN (NLG) · airframe 8,922 hrs · 5,895 cycles

THE NOSE GEAR ACTUATOR ATTACH POINT ON THE NOSE STRUT BROKE OFF DURING GEAR RETRACTION AFTER TAKEOFF. THIS WAS NOTICED BY A THUD AND THE GEAR POSITION WARNING LIGHT ILLUMINATED WHEN THE GEAR WAS RETRACTED FOLLOWING TAKEOFF. THE GEAR WAS SELECTED "DOWN" AND AN EMERGENCY WAS DECLARED TO LAND BECAUSE THE STEERING TILLER WAS NOT CENTERED. AFTER AN UNEVENTFUL LANDING AND IT WAS DISCOVERED THAT THE NOSE LANDING GEAR ACTUATOR ATTACH POINT CASTING ON THE NOSE GEAR STRUT HAD BROKEN OFF. UPON REMOVAL OF THE LANDING GEAR ACTUATOR, THE BEARING ON THE STRUT ATTACH END WAS ALSO NOTED AS BEING SEIZED.

Part: STARTER GEN — FAILED (RT ENGINE)

NR 2 ENGINE STARTER/GENERATOR HAD A CATASTROPHIC BEARING FAILURE, ON THE FRONT SHAFT MOUNT OF THE STARTER/GENERATOR. THIS CAUSED A PRONOUNCED ENGINE VIBRATION ON THE NR 2 ENGINE, PROMPTING THE FLIGHT CREW TO SHUT THE ENGINE DOWN IN FLIGHT. COMPONENT WAS O/H, WO R11-03791.

Part: CONTROL VALVE — FAILED (ANTI SKID SYSTEM)

ANTI-SKID CONTROL VALVE FAILED WITHOUT ANY COCKPIT INDICATION. NR 1 LEFT MAIN GEAR TIRE BLEW ON LANDING, EXCESSIVE RESULTING HEAT CAUSED NR 2 LT MLG TIRE TO BLOW ON ROLL-OUT. TROUBLESHOOTING INDICATED THE ANTI-SKID CONTROL VALVE SOLENOID WAS FUNCTIONING, HOWEVER, THE VALVE WAS NOT OPENING. (X)

Part: INLET COUPLING — FAILED (HEAT EXCHANGER)

DURING CLIMB-OUT, CREW NOTICED THE CABIN WAS NOT PRESSURIZING (CABIN WAS CLIMBING WITH AIRCRAFT). THE AIRCRAFT THEN RETURNED TO TAKEOFF POINT. INVESTIGATION OF THE AIRCRAFT REVEALED THE INLET COUPLING ON THE PRIMARY HAT EXCHANGER FAILED RESULTING IN NO AIR TO THE CABIN FOR PRESSURIZATION OR AIR CONDITIONING. ACTT: 8,216.5. HOURS. ACTC: 5,365.