Fresno

The captain reported that, while returning to the departure airport following an uneventful aerial drop, he noticed that the hydraulic pressure gauge indicated 0. The first officer subsequently verified that the sight gauge for the main hydraulic fluid reservoir was empty. The flight crew began performing the emergency gear extension checklist and verified that the nosewheel landing gear was extended. The captain stated that the first officer then installed the pin in the nosewheel landing gear as part of the emergency checklist. As the flight crewmembers diverted to a nearby airport because it had a longer runway and emergency resources, they briefed the no-flap landing. The first officer extended the main landing gear using the emergency gear release, which resulted in three down-and-locked landing gear indications. Subsequently, the airplane landed normally; however, during the landing roll, the nosewheel landing gear collapsed, and the airplane then came to rest nose low. Postaccident examination of the airplane revealed that the nosewheel landing gear pin was disengaged from the nosewheel jury strut, and the pin was not located. The disengagement of the pin allowed the nosewheel landing gear to collapse on landing. It could not be determined when or how the pin became disengaged from the jury strut. Installation of the pin would have required the first officer to maneuver in a small area and install the pin while the nose landing gear door was open and the gear extended. Further, the pin had a red flag attached to it. When inserted during flight, the flag encounters a high amount of airflow that causes it to vibrate; this could have resulted in the pin becoming disengaged after it was installed. Evidence of a hydraulic fluid leak was observed around the right engine cowling drain. The right engine hydraulic pump case was found cracked, and the backup ring was partially extruded, which is consistent with hydraulic system overpressurization. The reason for the overpressurization of the hydraulic system could not be determined during postaccident examination.

At about 1146 pst, Learjet 35A, N521PA, operating as a public use aircraft, crashed in Fresno, CA. Operating with call sign Dart 21, the flightcrew had declared an emergency inbound to Fresno Air Terminal due to engine fire indications. They flew the airplane toward a right base for their requested runway, but the airplane continued past the airport. The flightcrew was heard on tower frequency attempting to diagnose the emergency conditions and control the airplane until it crashed, with landing gear down, on an avenue in fresno. Both pilots were fatally injured. Twenty-one persons on the ground were injured, and 12 apartment units in 2 buildings were destroyed or substantially damaged by impact or fire. Investigation revealed that special mission wiring was not installed properly, leading to a lack of overload current protection. The in-flight fire most likely originated with a short of the special mission power supply wires in an area unprotected by current limiters. The fire resulted in false engine fire warning indications to the pilots that led them to a shutdown of the left engine. An intense fire burned through the aft engine support beam, damaging the airplane structure and systems in the aft fuselage and may have precluded a successful emergency landing.

The emergency medical service (EMS/medevac) flight was dispatched to transport a patient in response to a medical emergency. During arrival to the destination, the pilot contacted the airport unicom for advisories and was advised to land on runway 25. Runway 25 had a 2.2 percent uphill grade and was restricted to landings only. After landing, the airplane was refueled and the patient was put on board. The pilot back-taxied on runway 25 and proceeded to take off uphill with the airplane near its maximum gross weight. According to ground witnesses, there was a tailwind, which they estimated was between 4 and 15 knots. The temperature was about 100 degrees, and the density altitude was about 3,200 feet. After the airplane became airborne, the pilot started an immediate left turn to avoid rising terrain. However, the left tip tank contacted the ground, and the airplane cartwheeled. It came to rest about 711 feet from the departure end of the runway. The flaps and landing gear were found fully extended; the published configuration for takeoff data in the flight manual was for 'wing flaps - up.' The airport had no signs to indicate runway use restrictions; however, the restrictions were published in the airport facility directory.

The engine lost oil pressure while climbing through 6,000 feet, and the pilot requested to return to his departure airport. ATC informed the pilot of a closer airport. The pilot secured the engine, feathered the prop, and made a power-off descent to the airport. The pilot elected to make a downwind approach to runway 12L due to his altitude. The airplane overflew the runway and touched down past the departure end. It penetrated the airport perimeter fence, struck several trees, a sign post, a light pole, and an auto before coming to rest in a residential area. Examination of the wreckage revealed the loss of pressure was due to oil leaking. The oil filler cap was found improperly adjusted after the original installation. The maintenance manual does not approve any field repairs on the oil filler cap engaging mechanisms. The airplane's flaps were found at a 7° intermediate setting.

During the night cross country flight at FL250, the pilot elected to leave the cockpit area and move to the rear of the aircraft to attend to physiological needs. Although oxygen was available in the cockpit, supplemental oxygen was not available in the rear. The aircraft was operated with a known pressurization system deficiency which limited the airplane to flight to 17,000 feet msl while maintaining a cabin altitude of 10,000 feet. After 2 hours and 10 minutes, atc declared the flight to be 'no radio'. At 3 hours and 57 minutes after departure, the airplane was plotted on radar in a descending left turn to ground impact. Fuel starvation resulted in power loss to the left engine. Propeller signatures indicated power on the right propeller at impact. The pilot's body was found in the aft cabin area on the aft cabin bulkhead.

Just after liftoff from runway 29R, the aircraft began to pitch up. As the pitch up progressed, the pilot applied right aileron and full right rudder. The aircraft responded by rolling to the right with the nose falling thru. Subsequently, the pilot was able to pull out before the aircraft hit the ground. It collided with a 6 feet wire fence which tore off the engines and caused the aircraft to rotate clockwise on the ground. Cargo in the aircraft was thrown thru the side of the fuselage. The pilot exited the aircraft without injury. The aircraft immediately burst into flames and the fuselage was badly burned. An investigation revealed that 2,989 lbs of freight plus a 359 lb motorcycle were being carried between bulkheads 5 & 11. The bulkhead loads were limited to 450 lbs (5-8) and 300 lbs (8-10). The max gross weight at takeoff was estimated to be 10,310 lbs. The pilot reported that none of the freight was tied down.

After takeoff from Ashland-Parker Airport, the twin engine airplane encountered difficulties to maintain a positive rate of climb and crashed on a hill. The pilot was killed while four other occupants were injured.

After liftoff, the right engine lost power. The airplane encountered difficulties to gain height, struck tree tops and crashed near the runway end. All six occupants were injured, four of them seriously. The aircraft was destroyed.

On final approach to Oakland Airport by night, the left engine failed. The pilot lost control of the airplane that lost height, hit wires/poles and crashed short of runway. The pilot, sole on board, was killed.