Houston-George Bush-Intercontinental

During a dark night cross country in instrument meteorological conditions, the airplane was cleared for a VOR approach to runway 30. Due to unfavorable winds, the pilot elected to circle to land on runway 12. While on a right downwind, visual contact with the runway was lost and not reestablished. The pilot continued the descent on the base leg and impacted the terrain in a slight right turn.

The airplane broke up in flight while descending from FL240. The horizontal stabilizer, or top of the T-type tail, had separated from the fuselage before ground impact. Examination revealed that the 47 screw fasteners that would have attached the upper surface of the leading edge assembly for the left side of the horizontal stabilizer were missing. They had been removed the night before during scheduled maintenance. Investigation revealed that there was a lack of compliance with the FAA-approved general maintenance manual procedures by the mechanics, inspectors, and supervisors responsible for assuring the airworthiness of the airplane the night before the accident. In addition, routine surveillance of the continental express maintenance department by the FAA was inadequate and did not detect deficiencies, such as those that led to this accident. All 14 occupants were killed.

The passengers and witnesses reported that during takeoff, the aircraft yawed both left and right after lift-off. It then veered to the left and contacted the ground in a left wing low attitude between the runway and a parallel taxiway. An investigation revealed evidence that the left engine had sustained a partial loss of power due to a malfunctioning fuel pump. There were indications the power loss was not sufficient to trigger or allow completion of the autofeathering operation of the left propeller. Feathering of the left propeller had been manually initiated, but the propeller had not reached the feather position before impact. Manual feathering operation required the feathering pump button be held about 5 sec. 'V' speeds (kias) for this flight were: V1 92, VR 99, V2 110, normal VMCA (dead engine propeller feathered, flaps set for takeoff and aircraft out of ground effect) 101, VMCA (dead engine propeller unfeathered/windmilling and flaps set for takeoff) 127 knots. Exam of the actuators revealed the gear was retracted and the flaps were set for takeoff. Both pilots and a passenger who was seating on the jumpseat were killed.

The airplane was on a positioning flight and had two passengers along for the ride. The airplane was on base leg when the left engine sputtered. The pilot turned on the secondary boost pump and the engine operated normally until both engines flamed out. During the forced landing in a residential area, the airplane hit a powerline, trees, a house, a fireplug, a tree and a van, then another house. There was no smell of fuel in the entire area, and no usable fuel in the fuel system. All three occupants were seriously injured.

During landing, upon nose wheel contact with the runway, directional control was lost and the aircraft exited the runway hard surface and crossed a ditch collapsing the nose gear. The crew stated that full left rudder and differential braking would not stop the right drift, and that the aircraft was in grass uncontrollable by the time the steering tiller was reached. The nose wheel steering system was extensively damaged by the impact sequence when the nose wheel well aft bulkhead was forced into the steering assembly. The pilot stated that if he had been 'spring loaded to the tiller' that he could have possibly kept the aircraft off the grass.

The aircraft collided with power lines and trees while on final approach. The reported weather immediately following the accident was an indefinite ceiling zero, sky obscured, and visibility 1/16 of a mile in fog. No preimpact failures or malfunctions of the aircraft were found. The pilot had diverted from his intended destination due to fog. The pilot, sole on board, was killed.

Aircraft experienced a double engine failure. Pilot stated that immediately after the left engine failed, in climb to cruise, the aircraft rolled left, the stall warning activated, and the aircraft entered a left spiral. The right engine failed during the two-turn spiral. Pilot's attempts to restart the engines were unsuccessful. Pilot subsequently made a successful gear up emergency landing on a road, however, the aircraft was destroyed by post-crash fire. Investigation revealed that both engine fuel systems were contaminated with water and dissolved solids. Aircraft had just been refueled at a foreign airport. All seven occupants were uninjured.

Before takeoff, a pilot of XA-KUT was briefed that the Houston Hobby (HOU) weather was IFR with '. . . Indefinite ceiling zero sky obscured visibility's 1/16 of a mile and fog . . .' He was also advised IFR conditions were forecast until 0900 cst, gradually improving to marginal VFR by 1100 cst with 1,000 feet broken, 5 miles visibility and fog. The flight took off at 0900 cst. At HOU, arrival was delayed due to weather. The crew requested an ILS approach, with intentions of diverting if a missed approach was made. The RVR was variable. After being cleared for an ILS runway 04 approach, the pilot was advised the RVR had dropped to 1,400 feet. After changing to tower frequency, the flight was cleared to land and was told again the RVR was 1,400 feet. When the aircraft was on final approach, the pilots were advised of a low altitude alert. However, the aircraft continued below the decision height (dh), hit a 70 feet power line (approximately 6,500 feet short of the runway) and crashed. No preimpact malfunction of the aircraft or its systems was found. The ILS was flight checked, but only a minor discrepancy (concerning the outer marker width) was noted. The dh was 200 feet agl, minimum RVR for the approach was 2,400 feet. The copilot was killed and seven other occupants were injured, three seriously.