N5832Y

HISTORY OF FLIGHT

On June 1, 1995, about 1230 eastern daylight time, a Piper PA-23-250, N5832Y, crashed shortly after takeoff from the Opa-Locka Airport, Opa-Locka, Florida, while on a 14 CFR Part 91 business flight. Visual meteorological conditions prevailed at the time and a visual flight rules flight plan was filed for the flight. The airplane was destroyed and a postcrash sire ensued, which was extinguished by the Metropolitan Dade County Fire Rescue Department. The commercial-rated pilot and private pilot-rated passenger were fatally injured. The flight was originating at the time of the accident. Damage to Florida Power and Light (FPL) property consisted of a damaged guy wire and heat damage to a power line pole.

The airplane had been parked for at least 16 days with the inboard fuel tanks about 1/3 full. At about 1040 on the day of the accident, the inboard fuel tanks were filled.

A mechanic stated that on the flight before the accident flight, the pilot returned and landed reporting that the flaps were not operational and the landing gear would not retract. According to the owner's handbook the landing gear and flaps are hydraulically operated and pressure is supplied from an engine- driven hydraulic pump mounted to the left engine. The mechanic stated that he inspected the left engine compartment, and reservoir for leaks; none were found. He then operated both engines and raised and lowered the flaps greater than 10 times to full extension noting that each time the flap selector handle returned to neutral; no discrepancies were noted. He asked the pilot if he had hydraulic pressure; to which the pilot responded he did not know. The owner's handbook indicates that after full extension of the flaps or landing gear, hydraulic pressure within the selector valve forces the flap or landing gear control lever to the neutral or off position. The owner's handbook also indicates that landing gear retraction occurs in about 10-12 seconds. The mechanic stated he then observed the pilot reload the nose baggage compartment and the airplane was positioned by a tug to a taxiway. The pilot was then observed to have difficulty starting each engine and after each engine was started, the pilot taxied to takeoff. The mechanic did not witness the accident. The airplane was not placed on jacks for an operational test of the landing gear.

The pilot taxied to runway 9L and according to recorded communications with the Opa-Locka Air Traffic Control Tower (ATCT), the flight was cleared to takeoff. Shortly after takeoff an occupant of the airplane advised the ATCT controller that the flight was returning due to a rough running engine. When the ATCT controller asked if the pilot needed assistance the occupant replied negative. The flight was then cleared to land on any runway and the pilot was advised that the wind was from 120 degrees at 12 knots. The ATCT controller inquired about the rough running engine but there was no reply.

A witness who is an FAA certificated airframe and powerplant mechanic stated he was working on an airplane inside a hangar which is east of the ATCT. He heard a "backfiring" sound, walked outside of the hangar and observed the accident airplane about abeam the ATCT. Calculations indicate that the tower is located about 5,202 feet down the 8,002-foot runway. He thought the backfiring was from the left engine of the accident airplane and observed it about tower height (141 feet) in a shallow climb. He thought the pilot was going to land and the airplane climbed no higher than 300 feet. He then observed the airplane in a left bank of about 30 degrees with both engines operating but one of the engines sounded as if it was not developing full power. The airplane then "spun" to the left, pitched nose down, and he heard the impact.

Another witness who is also a mechanic stated he was working with the above mentioned mechanic who alerted him to the accident airplane. He observed the airplane and heard "alot of backfiring" which he thought was associated with the left engine. He stated that the airplane was observed to bank to the left and descended losing 150-200 feet of altitude. The airplane was observed to regain the altitude then banked "sharply" to the left. The airplane then pitched nose down and impacted the ground. He estimated the airplane climbed to about 500 feet while over the runway and the flight was about just east of the ATCT. He also stated that he did not observe any smoke trailing the airplane. Calculations indicated that about 2,437 feet of runway remained when the witness first observed the airplane and heard an engine malfunction.

Another witness who was located about 60-80 yards north of the crash site stated that he observed the airplane fly over trees which were later determined to be about 60-feet tall. The airplane was then observed in a 45-60 degree right bank, descended, impacted the ground nose low, then exploded. No damage to the trees was noted.

PERSONNEL INFORMATION

Information pertaining to the pilot-in-command seated in the left front seat is contained in the NTSB Factual Report-Aviation. Review of his pilot logbook dated from 1981 to the last entry dated November 5, 1994, revealed he logged about 28 hours in 1987, in the accident make and model airplane. There was no other similar make and model entries in his logbook. The last entry logged was a 2 hour 51 minute flight in a single engine airplane which took place on November 5, 1994. The last entry logged in a multiengine airplane took place on October 21, 1992, in an Aero Commander 500 airplane. Information pertaining to the private pilot-rated right front seat passenger is contained in Supplement E.

AIRCRAFT INFORMATION

Information pertaining to the airplane is contained in the NTSB Factual Report-Aviation and Supplements A and B. Additionally, an optional engine driven hydraulic pump was not installed to the right engine. According to a mechanic, work began on May 24, 1995, and ended on May 26, 1995, in which deteriorated left engine hydraulic hoses were removed and replaced, and the hydraulic reservoir was serviced. The airplane was then placed on jacks and using the hand pump at the power pak assembly and a hydraulic mule, the landing gear and flaps were retracted and extended about 13 times. The maintenance work was not documented in the aircraft logbooks.

METEOROLOGICAL INFORMATION

Information pertaining to the weather is contained in the NTSB Factual Report-Aviation.

WRECKAGE AND IMPACT

The airplane crashed on a road in a residential and industrial area and it was observed to be upright on a magnetic heading of about 295 degrees. All components necessary to sustain flight were attached to the airframe and the cockpit, and both wings were fire damaged. A cargo net was not installed and the cargo, which consisted in part of frozen food, was found shifted in the airplane. During recovery of the airplane it was noted that the main and nose landing gears were collapsed. The crash site was located about 045 degrees and .94 nautical mile from the Opa-Locka Airport.

Examination of the aileron, elevator, and rudder flight controls revealed no evidence of preimpact failure or malfunction. The landing gear and flap selector handles were in the down position. Weight calculations indicate that the airplane was about 268 pounds under gross weight. Rust like contaminant was found in the left engine fuel strainer. No rust like contaminant was found in the right engine fuel strainer. The crossfeed valve was determined to be in the "on" position and using water finding paste, water was detected on a drain plug. Both engines were removed for further examination.

Visual examination of the left engine revealed that the propeller was still connected to the crankshaft. Crankshaft, camshaft, and valve train continuity was verified. Cold differential compression of cylinder Nos. 1-6 revealed the following results respectively; 52/80; 75/80; 67/80; 70/80; 53/80; 65/80. Heat damage to the servo fuel injector which was found separated, and both magnetos which were tight against the accessory case, precluded testing. Examination of the servo fuel injector revealed that the fuel inlet screen was clean and the stem of the fuel diaphragm was intact. The flexible fuel supply line was found separated at the servo fuel injector but the opposite end was determined to be tightly secured at the fuel manifold assembly. All tube assemblies-fuel manifold to nozzle, exhibited minimal damage and their fittings were tight at each fitting at the fuel manifold valve and each nozzle, injection. Water was detected at the fuel injector nozzles of cylinder Nos. 1 and 2. Water was also detected at the outlet of the fuel manifold assembly for cylinder Nos. 1, 2, 4, and 5. Blockage of the No. 3 cylinder fuel injector nozzle was noted. The propeller was removed for further examination.

Examination of the left propeller revealed that the No. 2 blade exhibited about a 10-degree forward bend about 25 inches from the butt end of the blade and about a 90-degree aft bend about 11 inches from the butt end of the blade. The No. 1 blade was heat damaged but intact. Disassembly of the propeller revealed that the pitch change knob of the No. 2 blade was failed. Examination of the fracture surface revealed evidence of overload failure. Additionally, the auto high pitch stops were determined to be engaged but the auto high pitch stop assembly was intact. The blade angle of the No. 2 blade was determined to be about 13 degrees. The propeller manufacturer indicates that the low pitch stop is 14.5 degrees plus or minus .1 degree.

Visual examination of the right engine revealed that the propeller was separated and the crankshaft was failed about 1 3/4 inches aft of the forward side of the crankshaft flange. Examination of...