Texas

The DC-9 arrived at Carswell AFB at 01:12 CST after a flight from Kelly AFB. The aircraft was off-loaded and re-loaded with cargo by USAF personnel. The engines were then started at 02:04. The crew received taxi instructions for runway 17 and took off from this runway at 02:09. At (or immediately after) rotation, the main cargo door opened. An emergency was declared and the crew climbed to 2500 feet msl before entering a right turn. When about 5nm north of the airport the captain began a shallow turn to the right (for base leg). The aircraft crossed the extended centreline and the captain tightened the turn to establish their position relative to the runway threshold. In doing so, the air load on the door probably caused it to rapidly move to its full open over the top position. A sudden opening of the door would also have produced an unexpected change in the yawing and rolling moments. The captain, possibly partially disoriented, may not have sensed the increasing roll and nose tuck and thus failed to correct a changing attitude until a critical bank angle and loss of altitude had occurred. The DC-9 struck the ground in an inverted, nose down, left wing low attitude and disintegrated. It appeared that the first officer, when closing the main cargo door, didn't hold the door control valve 'T' handle in the closed position long enough for the latching hooks to move into place over the door sill spools. External latched and locked indicators were applied incorrectly, so the first officer thought the door was latched properly when the handle was pointed more toward the 'locked' than the 'unlocked' chevron. It also appeared that one of the two open door warning light switches was malfunctioning. Because of their wiring, this malfunction made the entire door warning system ineffective.

The airplane had made one approach, followed by a missed approach during a dark night with low ceilings and low visibility. During the next approach the airplane was high on the glide slope and touched down fast and long. The airplane hit the terrain 300 feet past the end of the runway, hit a second time 115 feet further down, then flew into the ils localizer. Part of the left wing burned. There were no indications of an attempted go-around.

Shortly after liftoff from runway 16 at Dyess AFB, while climbing to a height of about 60-100 feet, the aircraft banked right, causing the right wing to struck the ground. Out of control, the aircraft crashed in a huge explosion and was totally destroyed by impact forces and a post crash fire. All 19 occupants were killed, among them army officer and family members including spouses and children.

The pilot stated that during takeoff from runway 35L, the copilot on the flight controls reduced left propeller and right engine power at an altitude of less than 100 feet agl. He attempted to restore takeoff power while applying forward pressure on the control yoke, but lost control of the aircraft and impacted the terrain adjacent to the departure runway. He further stated that the cargo may have shifted to the rear of the aircraft during takeoff. The aircraft was destroyed and both pilots were seriously injured.

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.

The 70 years old pilot was flying a Douglas A-20 in a flight of 3 aircraft at an airshow (Confederate Air Force 'Airshow 88'). Afterflying on a southerly heading, the flight entered a procedure turn which involved a 90° left turn to the east followed by a 270° right turn back northbound. While maneuvering, the A-20 entered a right descending turn and subsequently crashed on level terrain in a relatively wings level descent. The main wreckage came to rest about 225 feet from the initial impact point. According to a pathological report, the pilot had severe coronary arteriosclerosis and suffered a heart attack.

Flight DL1141 (Jackson - Dallas - Salt Lake City) left Gate 15 at 08:30 and was instructed to taxi to runway 18L. When first in line for takeoff (at 08:59) the flight was cleared for takeoff. The takeoff was uneventful until the airplane reached the rotation phase (at 154 knots, 6017 feet down the runway). As the main gear wheels left the ground, the airplane began to roll violently, causing the right wingtip to contact the runway (1033 feet after lift-off), followed by compressor surges. The plane continued and struck the ILS localizer antenna array 1000 feet past the end of runway 18L. After impacting the antenna installation, the airplane remained airborne for an additional 400 feet, then struck the ground, traversed a ground depression and slid sideways until it came to rest near the airport perimeter fence, 3200 feet from the runway end. Parts of the aircraft had separated in the slide and a fire had erupted in the right wing area, quickly engulfing the rear, right side of the airplane after it came to rest. Twelve passengers and two crew members were killed. The aircraft was destroyed.

The pilot in the right seat had hired the pilot in the left seat to ferry the airplane to Germany, then to Turkey. A four tank ferry fuel system was installed but a weight and balance check was not made. During the tkof, the aircraft would not climb. Afterward the airplane was computed to have been overweight and the cg was aft of the rear limit. The left wing hit trees and the right wing hit two fences. After colliding with the terrain, the airplane burned. Both occupants were killed.

A rejected takeoff was attempted when the slat disagree light illuminated and the takeoff warning horn sounded at 166 knots (V1). The pilot aborted the takeoff, but the aircraft accelerated to 178 knots ground speed before it began to decelerate. The deceleration was normal until 130 knots where an unexpected rapid decay in the deceleration occurred. The aircraft ran off the end of the runway at 95 knots, the nose gear collapsed, and the aircraft came to a stop 1,100 feet beyond the end of the runway. Eight of the ten brake sets failed. Post-accident exam of the brakes revealed that excessive brake wear occurred during the rejected takeoff. Testing showed that dc-10 worn brakes have a much greater wear rate during an rto. The faa does not require worn brake testing. Douglas did not use brake wear data from rto certification tests to set more conservative brake wear replacement limits. New brakes were used for those tests. All 254 occupants were evacuated, among them eight were injured, two seriously. The aircraft was damaged beyond repair.