United States of America

The aircraft collided with a tree and a pole short of the runway during a night VFR approach to land. The pilot changed from runway 18 to 36 during the approach. He was seen low and fast on downwind which ended in a steep descending turn to ground contact. The tower had overied the pilot during the initial approach because of his speed and high altitude. The pilot replied that he would be down and requested a change of runway. The wind was reported as from 150° at 7 knots. Both occupants were killed.

At 2045 the military flight, Dixie 06, contacted Birmingham approach and obtained clearance for a low approach followed by a full-stop landing on runway 05. At 2053, Dixie 06 reported a 4 mile final for a low approach to the local controller. At 2054:19, the local controller cleared ABX74, N19T, '...taxi position and hold five.' ABX74 was awaiting takeoff instructions on runway 05 when the collision occurred. Investigation revealed the local controller forgot ABX74. She became preoccupied with other traffic using runway 36. The local controller termed the traffic as busier than normal for a night operation. At the time of the accident, the tower was staffed with two air traffic controllers and an air traffic assistant. No supervisor or coordinator was available in the cab to detect controller overload and offer assistance. The pilot, sole on board, was killed. The military aircraft involved in the collision was a USAF Douglas RF-4C Phantom II registered 64-1032 with two pilots on board. They escaped uninjured.

The amphibious aircraft crashed as the pilot was landing on glassy water at the inlet of Nerka Lake. Subsequently, it sank and came to rest inverted in clear water on the bottom of wood river with the gear retracted and the flaps extended. Moderate rain was falling when the pilot was landing. All three occupants escaped with minor injuries.

As the aircraft was climbing thru 14,800 feet for 19,000 feet, the pilot reported a rapid decompression. Two minutes later, he reported that he has lost the tail. Aircraft impacted in an inverted flat spin and the tail and a section of empennage were found about 3/4 mile away from main wreckage. Investigation revealed that a skin seam had split open along a 54' span in an area where 2 pieces of 'l' shaped channel had been riveted together to form a stringer. Normally the stringer would be made using a single piece of 't' shaped channel. The non-standard stringer had been fabricated during repairs made on the aircraft following a gear up landing 7 years prior to this accident. Analysis revealed that the rivets holding the 'l' channels together and failed in fatigue due to tensile cyclic loading whenever the aircraft was pressurized. Aircraft had a history of pressurization problems following the repair that was not properly performed or inspected. The pi1lot, sole on board, was killed.

The copilot begun takeoff with 2,700 rpm and 52 to 53.5' of manifold pressure (mp). Water injection was not used although 12 gallons was available. At 150 to 250 feet agl, the left engine lost power and the left propeller auto feathered. The captain took control and took action to verify left engine feathering. Neither pilot moved any of the other engine controls. A turn was initiated to return to the airport, but the aircraft began losing speed and altitude. Subsequently, it crash landed in a partly wooded area short of an open field and burned until firefighting personnel arrived. The impeller was demolished by fire, but evidence of debris from the impeller was found in the left engine intake and on top of its #3 and # 11 piston. The company's stated policy was to use water (wet takeoff), except when precluded by mechanical malfunction or lack of additional fluid; however, 4 dissimilar power charts were found in the aircraft. Takeoff weight was 38,670 lbs. Performance manual showed aircraft capable of 420 fpm climb with 12° of flaps, one prop feathered, landing gear up, dry power (no water). Max power setting was 2,700 rpm and 56' mp for dry takeoff; 2,800 rpm and 59.5' mp for wet takeoff. Both pilots were seriously injured.

Ground witnesses observed the aircraft enter low clouds going south, then emerge from clouds going went. Aircraft collided with mountain in wings-level and powered attitude. Mountains were reported to be obscured by clouds and fog. All eight occupants were killed.

The pilot, executing an ILS approach, observed a primary hydraulic pressure drop and declared his intent to land without the use of flaps, speed brakes, reversers or nose wheel steering. The aircraft ran off the end of the runway during landing, traveled approximately 1,300 feet and came to rest on a golf course after striking two vehicles and a chain link fence. Post accident investigation revealed 0.8 quarts of hydraulic fluid (skydrol) in the reservoir. Reservoir capacity is 1.28 u.s. gallon. The pilot stated he pumped the brakes on approach to build pressure in the emergency brake system. The pilot announced he had no braked after touchdown. The Jet Commander 1121 operator's manual cautions against this practice. A functional check of the thrust reversers by on-scene investigators produced two complete cycles of operation. Two persons located in a ground vehicle were injured during the overrun landing.

Pilot filed IFR for two flight legs; Baltimore, MD to Teterboro, NJ and Teterboro to Montgomery, NY (Orange County Airport). The pilot received a preflight weather briefing and was advised that the forecast for Stewart, NY, about 10 miles from Montgomery was sky partially obscured 4,000 feet, 500 feet scattered and 4 miles in fog. While enroute to Teterboro, at 0134 hrs, the pilot radioed Stewart airport and was advised of weather there as sky partially obscured with 4 miles in fog and haze. The aircraft landed at Teterboro at 0152 hours and departed VFR at 0200 hours. At 0211 hours the pilot radioed another aircraft and in part stated that he was at Orange County Airport and was attempting to land, however the weather was going down. At 0211 hours the pilot radioed Stewart and was advised that weather there was the same as reported at 0134 hours. The pilot acknowledged. There was no further transmission from the pilot. At 0215 hours a witness near the accident site heard a crash. He reported weather as 400 feet in fog. The aircraft crashed two miles south of runway 03. The landing gear and flaps were down. Examination of the aircraft did not disclose evidence of malfunction. Both occupants were killed.

The flight departed and proceeded en route without incident. Radar and radio contact was maintained until the flight proceeded over Lake Erie. The flight did not arrive at its destination. The aircraft is presumed to have crashed in Lake Erie. One identifiable 3 feet x 4 feet section of floor panel was located. Two smaller pieces of wreckage were also found which may have been portions of C-FFLC.

The aircraft was being operated as general aviation flight 115 and was departing on a routine night flight. During takeoff/initial climb, the left engine lost power. The flight crew attempted to control the climb-out, but following the application of water-methanol, the pilot lost directional control. Subsequently, the aircraft banked to the left, entered a descent and impacted between the parallel runway. An investigation disclosed that the left propeller's blade angle was 21°. No preimpact system malfunction or failure was found. The cockpit voice recording indicated that the flight crew did not complete all of the items on the before taxi/takeoff checklist. One of the items (presumably not completed) was a check of the h.p. cock levers. The checklist required that the h.p. cock levers be in 'cruise lockout' for takeoff. The left h.p. cock lever was found between the 'fuel off' and 'feather' positions. Movement to this position would have deactivated the auto-feather sys and shut down the left engine. Both pilots were killed.