Idaho

After extending the gear for landing, the down-and-locked indication (green light) for the left main gear was not illuminated. The crew performed the emergency checklist procedures for abnormal gear extension with no success. The aircraft subsequently landed with the left main landing gear retracted. Inspection of the landing gear revealed that the pin (part number MY20248-001), which is part of the forward gear door lock, was corroded and cracked at the point of rotation, preventing proper movement of the gear door uplock.

Radar data indicated that the aircraft completed a figure-eight maneuver at about 3,000 feet AGL, with an estimated airspeed of 140 knots and approximate 40 degree bank angle before leveling out at the completion of the maneuver. The radar data then indicated level flight before a rapid descent. A witness reported observing the aircraft in visual conditions and flying at a high altitude and that it 'appeared fast.' The witness stated that he observed the aircraft make a wide, shallow left turn, then turn back the other way. The nose of the aircraft then started to gradually lower, and the airplane eventually came straight down and started to spin. The witness lost sight of the airplane behind hilly terrain and he did not see the impact. Postaccident examination of the wreckage indicated that the aircraft collided with the terrain in a slight nose-down attitude, located in a gully with approximate 30 degree bank angle. The aircraft then slid downhill to the right and came to rest with the fuselage upright and the empennage was twisted to the right and inverted. No evidence was found to indicate a mechanical failure or malfunction.

The DC-3C took off on runway 10L and immediately executed a right turn followed by a left turn back toward the airport declaring a fire aboard. Dark night visual meteorological conditions existed. Witnesses observed 'flames' or an 'orange glow' coming from the right engine. A small number of aluminum fragments identified from the aft edge of the right engine accessory cowling were found along the ground just short of the ground impact site. These fragments displayed signs of heat distress but no significant melting. An examination of the right engine and accessory section revealed no evidence of a preimpact fire, and sooting and metal splatter on the leading edge of the right horizontal stabilizer was minimal. Spectral analysis of radio transmissions revealed no evidence of significant divergence of engine RPM between the two engines. Postcrash propeller examination revealed approximate blade pitch angles of 18-19° and 30-32° for the right and left propellers respectively upon impact. Propeller slash mark dimensions associated with the right propeller resulted in propeller RPM of approximately 1,750 to 2,570 over a range of 68 to 100 knots respectively. The first officer advised the PIC (broadcasting over the tower frequency) 'we're gonna stall' approximately 10 seconds before the impact. The aircraft was in a left turn back toward runways 28 left and right when the right wing struck the ground and the aircraft cartwheeled to a stop. A postcrash fire destroyed the cockpit area and inboard right wing.

A Mitsubishi MU-2 departed Salt Lake City, Utah, and climbed to 16,000 feet MS on an IFR flight to Pocatello, Idaho. While in cruise flight, the MU-2 encountered structural icing conditions. According to radar data, the MU-2 began slowing from a cruise speed of about 190 knots with slight deviations from heading and altitude. The airspeed decreased to about 100 knots, and the flight crew declared an unspecified emergency, then radio contact was lost. The MU-2 began a right turn, then it entered a steep descent and crashed. The pilot of a Beech 1900 (about 12 minutes in trail of the MU-2), stated that he encountered moderate rime icing at 16,000 feet. The Beech pilot activated his deice boots (3 times) and descended to 12,000 feet to exit the icing conditions. The MU-2 flight manual warned that during flight in icing conditions, stall warning devices may not be accurate and should not be relied upon; and to minimize ice accumulation, maintain a minimum cruise speed of 180 knots or exit the icing conditions. An investigation determined that the captain of the MU-2 was aware of deficiencies in the timer for the deice boots, as well as other maintenance deficiencies. The captain's medical certificate was dated 11/17/94; he was providing executive transportation for compensation under an agreement for "contractual flights," under 14 CFR 91. Although icing conditions were forecast in the destination area, no icing was forecast for the en route portion of the flight.

The aircraft was VFR inbound to the Hailey airport when the pilot contacted the tower at 1247 and reported 10 miles south. During the next 7 minutes the pilot and controller communicated back and forth and the pilot never visually acquired the airport. A number of witnesses located north of the airport observed the aircraft flying northbound along the highway into upsloping, mountainous terrain at an estimated altitude of 400 feet above ground, and with the landing gear extended and the engines developing power. The aircraft was described as low and slow and was observed to dip its wings during a left turn and then descend steeply to the ground. The aircraft impacted terrain in a steep nose down attitude. There was no evidence of flight control or powerplant malfunctions. High density altitude conditions existed at the accident site. Toxicological examination revealed a finding of 0.068 ug/ml and 0.183 ug/ml of Chlorpheniramine (an over-the-counter antihistamine) in kidney and heart tissue respectively.

After departure from Boise-Gowen Field, en route to Peterson AFB in Colorado Springs, the crew encountered technical problems with the engine n°2. The crew declared an emergency and elected to divert to Mountain Home AFB. About 20 minutes into the flight, the engine n°2 compressor disintegrated. The aircraft entered an uncontrolled descent and crashed 12 miles north of Bliss. All six crew members were killed.
Crew:
Lt Col Robert Buckout, Commander
1st Lt Lance Daugherty, pilot,
Cpt Geoffery Boyd, navigator,
CMSgt Jimmy Vail, flight engineer,
M/Sgt Jay Kemp, loadmaster,
S/Sgt Michael Scheideman, loadmaster.

The pilot had been charged with 'lewd and lascivious conduct with a minor.' He was jailed on Friday and released on bond on Saturday. During a meeting with a friend in the pilot's car on Sunday evening, he was drinking beer. The friend said the pilot made comments referring to intentionally crashing the aircraft and that 'he didn't want to die, but didn't know of any other way.' He had a gun in the car and told the friend 'don't call the police or I'll kill myself sooner.' The pilot departed Twin Falls at about 2230 on Sunday night in his PA-46. He flew to Boise, ID (via Ely, NV) before turning back toward Twin Falls. After passing over Boise, intermittent radio contact was made between the airplane and approach control. Radar vectors and descent were issued. Radar contact was lost during descent and pilot announced descending thru 11,000 feet; 38 seconds later, he reported at 6,000 feet. Ground impact was at 4,650 feet. Toxicology tests of the pilot's lung and muscle tissue showed an alcohol level of 175 & 117 mg/dl (0.175% & 0.117%). No preimpact failure of the aircraft was found.

Because of the failure of the thrust reverser relay circuit board, the thrust reversers failed to deploy when selected by the pilot. Because the reversers failed to deploy, the 'reversers in transition' lights, and the 'reversers deployed' lights did not illuminate. Even though the aircraft flight manual warns against moving the reverser throttle levers into the power range without the illumination of these lights, the pilot did so anyway. The pilot continued to select reverse power even after the activation of the throttle mismatch warning horn, resulting in an increase in forward thrust while attempting to stop. During this sequence of events the second-in-command moved the parking brake lever to full override, locking the main wheel brakes and overriding the antiskid system.

Left seat pilot was receiving a flight check for ATP and CV-240 type rating; right seat pilot was FAA OPS inspector. Following a simulated single-engine approach the airplane landed wheels up. Left seat pilot had received a total of 1.4 hrs left seat training in CV-240 prior to this flight; log book not endorsed.

On Friday afternoon, July 16, 1993, at 1405 mountain daylight time, a Beech B-60, N75CX, registered to the pilot, overran the end of the runway and impacted terrain while landing at the Camas County Airport, Fairfield, Idaho. An IFR flight plan was filed for the business flight, conducted under 14 CFR 91, which departed Hermiston, Oregon at 1244, July 16, 1993. Visual meteorological conditions prevailed in the area. The private certificated pilot and passenger Peter W. VanKomen were seriously injured. Passenger Chris A. Carrow suffered minor injuries in the accident. The aircraft was destroyed in the mishap. There was no fire. Witnesses reported the pilot landed on runway 7, near the center of the 2950 feet long gravel airstrip and was unable to stop on the runway. The aircraft skidded off the east end of the runway where it impacted a ditch and dirt embankment. The Camas County Sheriff reported he examined the aircraft tire marks on the runway, which according to his measurement, started 1400 feet from the west end of the runway (See Sheriff Report). The sheriff indicated in his report that a witness, Bill Simon, stated in an interview that the pilot landed in downwind conditions, estimated to be 15 to 20 knots. Witness David Coffin, a private pilot, reported the two wind socks on the strip were fully extended, indicating the wind was blowing from west to east at a velocity in excess of 25 MPH, and gusting 30 to 35 MPH. The surface aviation weather observation, taken at Hailey, Idaho, 24 miles northeast of the accident site at 1350 MDT, July 16, 1993, was recorded as 3000 feet scattered clouds, visibility 30 miles, temperature 65 degrees F., dew point 29 degrees F., wind 210 degrees at 10 knots and altimeter 30.05 inches Hg. The density altitude at the Camas County Airport was calculated to be 6488 feet. The airport facility directory indicates the Camas County Airport has a single 2950 by 40 feet dirt runway, oriented 070 and 250 degrees. The elevation at the airport is 5058 feet above mean sea level.