LAX98FA048
LAX98FA048

HISTORY OF FLIGHT

On November 27, 1997, at 1235 hours Pacific standard time, a Piper PA-23-250, N6933Y, rolled inverted during the takeoff initial climb and impacted a hangar at the Carson City, Nevada, airport. The aircraft was destroyed and the commercial pilot and three passengers were fatally injured. Visual meteorological conditions prevailed for the personal flight. The flight was originating at the time and was destined for Nacadoches, Texas.

A private pilot witnessed the takeoff from near the midfield location adjacent to runway 27. The runway is 5,900 feet long and the airport elevation is 4,697 feet. The witness reported that the accident aircraft lifted off prior to reaching his location and passed in front of him at 30 - 50 feet agl. The nose gear had retracted and the main gear was in transit. The engines sounded normal. As the aircraft continued west over the runway, the witness sensed that something was wrong as the aircraft reached 150 - 200 feet agl, it yawed slightly, and appeared to mush. The nose pitched up and the aircraft rolled to the left, then the nose dropped and the aircraft disappeared behind a parked aircraft in a vertical dive and he heard the impact in the hangar. When the aircraft pitched up and rolled to the left, he had a view of the top of the aircraft from the rear and could see that the nose baggage door on the right side of the nose was open. As the aircraft continued to roll, the baggage door appeared to fold back over the nose in front of the windshield but it did not come off. He did not observe anything fall from the aircraft and the engine sound was normal except that there was what the witness termed a "Doppler shift" as the aircraft spun toward the ground.

Another witness, a commercial pilot who was on the midfield ramp about 200 feet south of the runway edge, also reported that the engines sounded normal as the aircraft passed midfield. His attention was attracted to the aircraft by its abnormally steep climb angle. However, this witness reported hearing a pop - pop sound which he attributed to one of the aircraft's engines immediately before the nose pitch up and "VMC roll".

Another pilot/witness observed the aircraft climbing out at a very steep angle and stated, "As we continued to watch the plane continued up on a steep angle, until the plane stalled. At the stall the plane nosed down to the left and went directly down into a [hangar]."

Still another witness reported that the aircraft appeared to climb normally to about 200 feet agl and then it "appeared to zoom upward at an excessive rate for about 100 ft. more and then nosed over in a dive straight for the ground."

Another commercial pilot, who did not witness the accident, reported landing at Carson City about 1130 behind the landing Aztec and taxiing behind the aircraft to the (unattended) self-fueling pumps. He said that there were two young men in the aircraft and he spoke to the one who was the pilot. The pilot said that he had rented the aircraft in Southern California and had flown to Santa Rosa to pick up his brother. They were now picking up his mother and girlfriend and going to Texas. While they were talking a car drove up with the two women. The other young man, who did not appear knowledgeable about airplanes, asked the pilot where to load the baggage. The pilot said to put the heavy bags up front and the second man loaded approximately two to four pieces of luggage in the nose baggage compartment. It appeared that the pilot fueled all the tanks of the accident aircraft to capacity. This pilot fueled his aircraft after the pilot of the accident aircraft fueled his and recalled clearing the pump which read about 109 gallons. (According to the facility operator, there is only one grade of fuel sold at the self-fueling facility, 100LL.) This pilot then took off about 1200 while the accident aircraft was still on the fueling ramp and returned to Stead Airport and reported no problem with the fuel.

A modest amount of burned luggage residue was found in the area of the nose baggage compartment at the accident site. Two separate foot searches of the runway environs failed to locate any items from the aircraft. The husband of the pilot's mother brought her to the airport and helped load luggage. He reported through a friend of the family that the group only had about 20 pounds of soft luggage. He reported that he only helped load the baggage and did not operate the baggage door.

No fuel sample was retained by the fuel pump operator (Texaco). However, refueling records for the time following the refueling of the accident aircraft (attached), show three other aircraft were fueled after the accident aircraft and no abnormalities were reported. The records show that the pilot added 119.6 gallons. The clock times on the record are erroneous.

PERSONNEL INFORMATION

The pilot was employed as a flight engineer at a supplemental air carrier. The pilot's logbook was located in the wreckage with fire damage. It indicated total flying time of 484 hours as of November 15, 1997. The pilot's multiengine airplane rating was issued June 26, 1997, after 7.2 hours of instruction and check ride in a Beech BE-95. On August 1, 1997, the pilot logged 1.9 hours in a Piper PA-34-200 and 2.3 hours in a Beech BE-58. On November 14 and 15, 1997, the pilot flew 8.6 hours during his checkout in the accident aircraft.

One of the two flight instructors who performed the checkout in the accident aircraft said that they do not normally simulate engine failures on takeoff or do Vmc demonstrations during checkout of a rated pilot. They did do slow flight, steep turns, and stalls, as well as a high altitude airport landing and takeoff. They also practiced engine out procedures by retarding the mixture control while in cruise flight. This instructor considered the pilot a "very good pilot" who flew well and kept the airplane under control.

There were no further entries in the pilot's logbook after November 15. The Safety Board investigator, using a DUATS, no wind, flight plan, estimated that the pilot flew an additional 3.1 hours in the accident aircraft while en route from Pomona, California, to Santa Rosa, California, to Carson City preceding the accident.

AIRCRAFT INFORMATION

The aircraft's weight and balance at the time of the accident was estimated by the Safety Board investigator using postaccident weights of the occupants provided by the Coroner's office, together with baggage and fuel weights reported from other sources. The initial calculation indicated that the takeoff center of gravity position was 100.32 inches aft of datum. However, a subsequent examination of the aircraft weighing record dated October 29, 1997, revealed an error in the calculation which caused the empty weight center of gravity position to be reported 2.4 inches aft of the true position. After compensating for this error, the calculation showed the takeoff weight of the accident aircraft was 4,730 pounds and the center of gravity was at 98.5 inches aft of datum. According to the weight and balance documents, the maximum takeoff weight is 5,200 pounds and the center of gravity limits (at 4,730 pounds) are 95.3 to 100.5 inches.

In the operator's "Flight Squawk Record" document, squawk number 2, dated September 15, 1997, is "door ajar lt inop." The corrective action, dated September 16, 1997, is "adjusted fwd baggage compartment door switch. Light works good." According to the operator, the door ajar light was located on the glareshield in front of the right seat passenger.

METEOROLOGICAL CONDITIONS

According to a deputy from the Carson City Sheriff's Department, weather at Carson City at the time of the accident was clear and sunny, calm wind, and temperature in the mid 40-degree Fahrenheit range.

WRECKAGE AND IMPACT INFORMATION

The aircraft impacted in the roof of a "Porta-Hangar" single aircraft, T-hangar located approximately 1,000 feet from the departure end of runway 27 and 200 feet south of the runway centerline. The hanger, in the center row of three rows of "Porta-Hangar's" was identified as B6 and is located at latitude 39 degrees 11.13 minutes north, and longitude 119 degrees 44.26 minutes west (GPS). There was a fire following impact with the ground and the entire aircraft was destroyed by the fire. Burned debris associated with the aircraft was found on the floor of the hangar approximately in the planform of the aircraft with the fuselage aligned approximately 300 degrees. A Cessna T210 aircraft was stored in the hangar and was also destroyed.

The fuselage was oriented with the nose in the northwest corner of the hangar and the skeletal remains of the empennage about 25 feet southeast near the center of the hangar door. The aluminum components of the fuselage were consumed by fire except for the area under the cabin floor in proximity of the wing center section structure. The instrument panel, switches, and radios were destroyed by impact damage and fire. The cabin area was identifiable by the steel tube truss cabin structure, seat frames, and lower fuselage in proximity of the wing center section. The cabin floor beneath the pilot's seat was buckled. The pilot's seat remained attached to the right rail and was detached from the left rail. The aft travel seat stop was in place on the left rail and the seat was positioned forward of the stop. The engine power levers were bent to the right side. The throttle and propeller controls were approximately in the mid-range position with the left-hand engine controls forward of the right hand engine.

The nose baggage door latch handle and recess assembly, and the latch operating shafts were located in the nose area of the wreckage. The handle was approximately 1/4-inch open at the locking end and solidified molten metal had filled the cavity between the handle and the recess fixture. The track for the nose baggage door hold-open rod was found crushed with the slot in the track.

The landing gear were in the retracted position. The flight controls were continuous from the cockpit to the empennage and the aileron cables outboard of the nacelles had been disturbed by rescue personnel. According to the representative from The New Piper Aircraft Company, the threads exposed on the trim tab actuators corresponded to neutral rudder trim and approximately 2 degrees nose down elevator trim. The flaps and flap actuator were destroyed by impact and fire damage.

The wing center section, engine nacelle structure, and engines remained attached to the fuselage. The wings were consumed by fire outboard of the engine nacelles; however, residue on the hangar floor associated with wing approximated the wing planform. The fuel selector valves in the nacelles were positioned to the outboard tank position and were heat damaged.

Both engines remained attached to their respective engine mounts and remained aligned with the fuselage. The engine sumps and induction systems of both engines were destroyed by impact and fire. The right engine fuel servo assembly was destroyed by fire. The throttle valve in the left servo assembly, although damaged by impact and fire, was near the closed position. The fuel distribution manifold was intact on the top of the engines, however, no fuel was present. The engine fuel supply lines and engine mounted fuel pumps were destroyed by fire. The exhaust systems were destroyed by impact. The magnetos and ignition harness wires on both engines were damaged by fire.

Both propellers remained attached to their respective engines and were in the feathered position. The actuator arms of both propeller governors, however, were in the low pitch position. The blades of the left propeller were free to rotate in the hub and the blades of the right propeller would not rotate in the hub.

The blades of the right propeller were bent aft approximately 15 degrees about 12 inches inboard of the blade tip. The R1 blade of the right propeller exhibited one gouge in the leading edge approximately 1/4 inch and no chordwise striations. Approximately 20 percent of the R2 blade tip was consumed by fire. The leading edge inboard of the melted portion contained three gouges of approximately 1/4 inch and light chordwise and diagonal striations.

The L1 blade of the left propeller was bent aft about 90 degrees between the root and the midspan location. The blade had two gouges in the leading edge, one approximately 1/4 inch and the other of approximately 3/8 inch. The L2 blade was bent forward approximately 60 degrees and 12 inches inboard of the tip. The blade had one gouge on the face side of the leading edge near the tip and approximately 1 to 2 inches of the blade tip trailing edge was absent.

According to a deputy of the Washoe County Sheriff's Department who was present when the occupants were removed from the aircraft, the pilot's mother and brother were seated in the number 5 and 6 seats, respectively. The number 3 and 4 seats were empty and the other female passenger was in the right front seat. There was a modest amount of personal belongings in the nose area and, in the cabin, only a pillow and a jacket were found.

The engines were disassembled and inspected by the Safety Board at the facilities of Textron Lycoming on January 21 and 22, 1998. The sumps were consumed by fire on both engines and the data plates were absent. The engines were identified by metal tags affixed at the accident site. The fuel, induction air, ignition, and exhaust systems could not be examined due to impact and fire damage. The engines were mechanically continuous, the valves functioned and accessory case gears rotated when the crankshaft was turned. The oil pump gears were intact. The internal mechanical components of the engines were in place and undamaged except for the effects of heat generated by the postaccident fire. The crankcase and connecting rod bearings were gray and unscored, although tin plating on some of the bearings had melted and run in localized areas of high temperature. The connecting rod journals were smooth, shiny, and unscored, although several journals exhibited a blue appearance in areas of high temperature. The spark plugs were clean and gray except for the number 1, 3, and 5 cylinder plugs on the left engine which were covered with shiny black oil. The fuel injectors were clear except the number 1 injector on the left engine and the number 2 injector on the right engine which were blocked. The number 4 and 6 injectors on the right engine were partially blocked. The oil filters were opened and the elements were charred. There were no metal particles in the filter elements. The propeller governors, when removed from the engine, turned freely and pumped oil.

The propellers were disassembled and inspected by the Safety Board at Hartzell Propeller Company on January 23, 1998. The dome and piston of the right propeller were absent. The pitch control rod of the right propeller was broken approximately midway between the piston and the yolk. The fracture was elliptical and an area of displaced metal on the forward face of the hub conformed to the fracture shape of the rod. According to a Hartzell representative, the position of the rod failure relative to the forward face of the hub corresponds approximately to a low pitch blade position at the time the mark was transferred. A mark transferred from the R2 blade root to the adjacent preload plate corresponded to a 21-degree blade position at the time the mark was transferred, according to the same Hartzell representative. The blade root pin of the R1 blade was bent approximately 5 degrees toward the low pitch direction and the pin on the R2 blade was bent a like amount in the high pitch direction.

The pitch control rod of the left propeller was broken in the threaded area on both sides of the yolk assembly. The remaining portion of the rod aft of the yolk was bent at mid-length. According to the Hartzell representative, if the bent rod was positioned so that the bent portion was between the yolk and the last point of support for the rod on the aft face of the hub cavity, the blade position corresponded to approximately the low pitch position when the rod was bent. Transfer marks on the preload plate of the L2 blade corresponded to blade angles of 40, 78, and 88 degrees, according to the Hartzell representative. The pitch change pins on the root of both blades of the this propeller were bent approximately 5 degrees toward the high pitch position.

ADDITIONAL INFORMATION

An autopsy was performed on the pilot by the Washoe County Medical Examiner/Coroner and a toxicology analysis was performed by the FAA Civil Aeromedical Institute.

The aircraft wreckage was released to Mr. Ernest Despain, insurance adjuster for Kern and Wooley, LLP, on February 11, 1998.

Use your browsers 'back' function to return to synopsis
Return to Query Page