Piper PA-60 Aerostar (Ted Smith 600)

Douglas A. Golike

JA Mach 3

On final approach to Wichita-Colonel James Jabara Airport, the pilot reported technical problems and elected to make an emergency landing. The aircraft crash landed in a field located about 3,5 km short of runway 18. The pilot escaped uninjured while the aircraft was damaged beyond repair.

Michael Stockton

Few minutes after takeoff from LaBelle Airport, the twin engine airplane crashed into trees located in a church garden located less than 2 km east of the airport. Apparently, the passenger survived while the pilot was killed. Engine failure was reported by the survivor.

Private Spanish

On Thursday, 20 February 2020, the Piper PA-60-602P aircraft, with registration EC-HRJ, took off from Sabadell Airport (LELL) bound for Pamplona Airport (LEPP). At 17:51:43 hours local time, when the aircraft was in the vicinity of the SURCO waypoint, a sudden change in course from 300º to 317º was observed on the aircraft's radar trace. Moments later, at 17:53:12, the pilot of the aircraft contacted the Madrid air control units to report problems with one of his engines, adding verbatim: “I’m not sure if I’ve lost the turbo”. In a subsequent communication with the same air traffic controller, at 17:57:22 h, the pilot stated: "I’ve lost an engine”. At 17:57:58 h, the pilot contacted the controller of the Pamplona control tower. The controller asked him if he required any assistance, and the pilot replied that he did not. At 18:16:15 h, the pilot told the control tower controller that he was on right base for runway 33. The controller cleared him to land and asked him to notify him when he was on final. At 18:19:40 h, the control tower controller alerted the airport Fire Extinguishing Service (SEI) when he saw the aircraft crash and a column of smoke coming from the wreckage area. The aircraft had impacted the ground during the final approach manoeuvre. As it fell, it hit and severed a power line. The pilot, who was the sole occupant of the aircraft, was killed during the accident. The impact and subsequent fire completely destroyed the aircraft.

Private Canadian

On 09 December 2019, a private Piper Aerostar PA-60-602P aircraft (registration C-FQYW, serial number 60-8265020), departed Cabo San Lucas International Airport (MMSL), Baja California Sur, Mexico, with 3 people on board, for a 2-day trip to Nanaimo Airport (CYCD), British Columbia (BC). As planned the aircraft stopped for an overnight rest at Chino Airport (KCNO), California, U.S. At 1142, on 10 December 2019, the aircraft departed KCNO on a visual flight rules (VFR) flight plan to Bishop Airport (KBIH), California, U.S., for a planned fuel stop. The aircraft departed KBIH at approximately 1425 on an instrument flight rules (IFR) flight plan to CYCD. On 10 December 2019, night started at 1654. At 1741, the Vancouver area control centre air traffic controller advised the pilot that an aerodrome special meteorological report (SPECI) had been issued for CYCD at 1731. The SPECI reported visibility as 2 ½ statute miles (SM) in light drizzle and mist, with an overcast ceiling of 400 feet above ground level (AGL). The pilot informed the controller that he would be conducting an instrument landing system (ILS) approach for Runway 16. At 1749, when the aircraft was approximately 32 nautical miles (NM) south of CYCD, the pilot contacted the controller to inquire about the weather conditions at Victoria International Airport (CYYJ), BC. The controller informed the pilot that a SPECI was issued for CYYJ at 1709 and it reported the visibility as 5 SM in mist, a broken ceiling at 600 feet AGL, and an overcast layer at 1200 feet AGL. The controller provided the occurrence flight with pilot observations from another aircraft that had landed at CYCD approximately 15 minutes before. That crew had reported being able to see the Runway 16 approach lights at minimums, i.e., at 373 feet AGL. Between 1753 and 1802, the controller provided vectors to the pilot in order to intercept the ILS localizer. At 1803, the controller observed that the aircraft had not intercepted the localizer for Runway 16. The aircraft had continued to the southwest, past the localizer, at an altitude of 2100 feet above sea level (ASL) and a ground speed of 140 knots. The controller queried the pilot to confirm that he was still planning to intercept the ILS for Runway 16. The pilot confirmed that he would be intercepting the ILS as planned. The aircraft made a heading correction and momentarily lined up with the localizer before beginning a turn to the west. At 1804:03, the pilot requested vectors from the controller and informed him that he “just had a fail.” The controller responded with instructions to “turn left heading zero nine zero, tight left turn.” The pilot asked the controller to repeat the heading. The controller responded with instructions to “…turn right heading three six zero.” The pilot acknowledged the heading; however, the aircraft continued turning right beyond the assigned heading while climbing to 2500 feet ASL and slowing to a ground speed of 80 knots. The aircraft then began to descend, picking up speed as it was losing altitude. At 1804:33, the aircraft descended to 1800 feet ASL and reached a ground speed of 160 knots. At 1804:40, the pilot informed the air traffic controller that the aircraft had lost its attitude indicator.Footnote6 At the same time, the aircraft was climbing into a 2nd right turn. At 1804:44, the air traffic controller asked the pilot what he needed from him; the pilot replied he needed a heading. The controller provided the pilot with a heading of three six zero. At 1804:47, the aircraft reached an altitude of 2700 feet ASL and a ground speed of 60 knots. The aircraft continued its right turn and began to lose altitude. The controller instructed the pilot to gain altitude if he was able to; however, the pilot did not acknowledge the instruction. The last encoded radar return for the aircraft was at 1805:26, when the aircraft was at 300 feet ASL and travelling at a ground speed of 120 knotsControl of the aircraft was lost. The aircraft collided with a power pole and trees in a wooded park area on Gabriola Island, BC, and then impacted the ground. The aircraft broke into pieces and caught fire. The 3 occupants on board received fatal injuries. As a result of being damaged in the accident, the emergency locator transmitter (Artex ME406, serial number 188-00293) did not activate.

Indiana Paging Network

The airline transport pilot arrived at the departure airport in the reciprocating engine-powered airplane where it was fueled with Jet A jet fuel by an airport employee/line service technician. A witness stated that she saw a "low flying" airplane flying from north to south. The airplane made a "sharp left turn" to the east. The left wing "dipped low" and she then lost sight of the airplane, but when she approached the intersection near the accident site, she saw the airplane on the ground. The airplane impacted a field that had dry, level, and hard features conducive for an off-airport landing, and the airplane was destroyed. The wreckage path length and impact damage to the airplane were consistent with an accelerated stall. Postaccident examination of the airplane found Jet A jet fuel in the airplane fuel system and evidence of detonation in both engines from the use of Jet A and not the required 100 low lead fuel. Use of Jet A rather than 100 low lead fuel in an engine would result in detonation in the cylinders and lead to damage and a catastrophic engine failure. According to the Airplane Flying Handbook, the pilot should witness refueling to ensure that the correct fuel and quantity is dispensed into the airplane and that any caps and cowls are properly secured after refueling.

Joe Robertson

The private pilot of the multiengine airplane was in cruise flight at 23,000 ft mean sea level (msl) in day visual meteorological conditions when he reported to air traffic control that the airplane was losing altitude due to a loss of engine power. The controller provided vectors to a nearby airport; about 7 minutes later, the pilot reported the airport in sight and stated that he would enter a downwind leg for runway 14. By this time, the airplane had descended to about 3,200 ft above ground level. Radar data indicated that the airplane proceeded toward the runway but that it was about 400 ft above ground level on short final. The airplane flew directly over the airport at a low altitude before entering a left turn to a close downwind for runway 21. Witnesses stated that the airplane's propellers were turning, but they could not estimate engine power. When the airplane reached the approach end of runway 21, it entered a steep left turn and was flying slowly before the left wing suddenly "stalled" and the airplane pitched nose-down toward the ground. Postaccident examination of the airplane and engines revealed no mechanical deficiencies that would have precluded normal operation at the time of impact. Examination of both propeller systems indicated power symmetry at the time of impact, with damage to both assemblies consistent with low or idle engine power. The onboard engine monitor recorded battery voltage, engine exhaust gas temperature, and cylinder head temperature for both engines. A review of the recorded data revealed that about 14 minutes before the accident, there was a jump followed by a decrease in exhaust gas temperature (EGT) and cylinder head temperature (CHT) for both engines. The temperatures decreased for about 9 minutes, during which time the right engine EGT data spiked twice. Both engines' EGT and CHT values then returned to normal, consistent with both engines producing power, for the remaining 5 minutes of data. It is possible that a fuel interruption may have caused the momentary increase in both engines' EGT and CHT values and prompted the pilot to report the engine power loss; however, the engine monitor did not record fuel pressure or fuel flow, and examination of the airplane's fuel system and engines did not reveal any mechanical anomalies. Therefore, the reason for the reported loss of engine power could not be determined. It is likely that the pilot's initial approach for landing was too high, and he attempted to circle over the airport to lose altitude. While doing so, he exceeded the airplane's critical angle of attack while in a left turn and the airplane entered an aerodynamic stall at an altitude too low for recovery.

Heliblack

The twin engine aircraft departed Santa Fe de Antioquia on a flight to Medellín, carrying one passenger and two pilots who were taking part to the production of the Tom Cruise movie 'Barry Seal - American Traffic'. While flying over mountainous terrain in IMC conditions, the airplane struck the slope of a hill with its right wing then crashed at the bottom of trees. A pilot was seriously injured and both other occupants were killed. The aircraft was destroyed.

Managed Aviation

The pilot receiving instruction conducted three full-stop landings without incident. After the fourth takeoff, the flight instructor simulated a prearranged left engine failure about 600 ft above ground level (agl). The pilot followed emergency procedures, used the checklist, and prepared to land. The pilot reported that, when the airplane was about 50 to 100 ft agl on final approach, he thought that it was a little too high, so he chose to initiate a go-around. He moved the throttle levers full forward, but neither engine responded. The flight instructor pushed the airplane's nose down, and the pilot continued the approach. On touchdown, the right main and nose landing gear collapsed. A postimpact fire ensued, which consumed most of the airplane. Postaccident examination of the landing gear revealed that it collapsed due to bending overload consistent with a hard landing. The reason for the failure of both engines to respond to power inputs could not be determined because of the postcrash fire damage.

AFIT

During the takeoff roll from runway 25 at Hildesheim Airport, the twin engine aircraft accelerated slowly and lifted off from the mid-runway only. After takeoff, the climb gradient was low then the airplane lost height and descended until it impacted a wall and crashed in an industrial area located about 900 metres from the runway end, bursting into flames. The aircraft was totally destroyed and the pilot, sole on board, was killed.

BDW Equipment Leasing

According to radar and Global Positioning System data, the pilot overflew the airport from the southwest and turned to the west to maneuver into position for landing on runway 9. Several witnesses observed the airplane to the west of the airport at a low altitude, appearing to enter a turn that was followed by a "rapid descent" and impact with the ground. The ground scars and damage to the airplane were consistent with a near-vertical descent and impact. An examination of the airplane and its systems revealed no preaccident anomalies. The moon was obscured by an overcast sky and dark night conditions were prevalent.

Midwestern Restaurants

The accident flight was the pilot's first 700 nm cross-country flight in the newly purchased airplane. Prior to departing he had the airplane refueled with the airplane on a slope. The individual who refueled the airplane estimated that the left wing tip was 12 to 14 inches lower than the right wing tip. He stated that the pilot was very concerned about getting as much fuel in the airplane as possible because of his up-coming flight. After climbing to his assigned cruising altitude of 21,000 feet and about two hours into the flight the pilot reported to ATC that he needed to divert. During the descent the pilot reported that he was experiencing a fuel problem and that one engine was sputtering. Two minutes later the pilot declared an emergency and reported that both engines were sputtering. The pilot reported at that time that he had 15 total gallons of fuel remaining A witness to the accident reported that he saw the airplane flying southbound and that the wings were rocking side-to-side. The airplane then rolled to the right before crashing into the citrus grove. Examination of the airframe revealed no pre-impact failure to any flight control surface or control system component. The power plant investigation did not disclose any pre-impact mechanical failure of any rotating or reciprocating component of the engine. Interviews with pilots who had flown with the accident pilot indicated that this was his first flight above 13,000 feet in the accident airplane, and was probably his longest distance attempted flight since he had purchased the airplane. According to information contained within the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual (VB-1190), "The full amount of usable fuel is based on the airplane sitting on a level ramp, laterally level, and longitudinally (approximately 1 1/2 degree nose up) with each tank fueled to 0.6 inches below filler neck. The wing tanks are extremely sensitive to attitude and if not level, they cannot be fueled to the full usable capacity." This information is also included in the FAA Type Certificate Data Sheet No. A17WE under the section Data Pertinent to All Models, Note 1.

John R. Martin

The pilot obtained a weather briefing from an Automated Flight Service Station (AFSS) and filed an IFR flight plan before departing on an IFR flight from Cornelia, Georgia, to Pensacola, Florida, on May 10, 2006.The flight service specialist provided information on a line of embedded thunderstorm activity along the route from Atlanta to Mobile including SIGMETs and advised that tops were forecasted to be at 41,000 to 50,000 feet. The specialist suggested that the pilot not depart immediately because of the weather, but said that it might be possible to land at an intermediate stop ahead of the weather, possibly in Pensacola or further north in the Crestview area. The pilot filed an IFR flight plan from Cornelia to Pensacola at 16,000 feet. The pilot called the AFSS again and requested an IFR clearance. The specialist responded that the clearance was on request, and that he would work on the void time and placed the pilot on hold. The specialist obtained the clearance from Atlanta Center and returned back to provide the clearance to the pilot. The pilot was not on the telephone line. The pilot departed Cornelia without an IFR clearance and contacted Atlanta Center. The controller informed the pilot on initial contact that he was not on his assigned heading, altitude, correct transponder code, and subsequently handed the pilot off to another controller. The flight was subsequently cleared direct to Panama City, Florida, and the pilot was instructed to climb to 16,000 feet. Atlanta Center broadcasted weather alerts over the radio frequency the pilot was on for Center Weather Advisory 101, SIGMETS 73C, 74C,and AIRMET Sierra between 0903 to 0913 CDT. The National Weather Service Storm Prediction Center, issued Severe Thunderstorm Watch 329 valid from 0635 CDT until 1300 CDT. The National Weather Service Aviation Weather Center issued Convective SIGMET 73C valid from 0855 CDT until 1055 CDT. The SIGMET was for a line of thunderstorms 40 nautical miles wide, and moving from 280 degrees at 35 knots. The tops of the thunderstorms were at 44,000 feet, with 2-inch hail, and possible wind gusts up to 60 knots. These weather alerts included the route of flight for the accident airplane. The controllers did not issue the pilot with severe radar-depicted weather information that was displayed on the controller's radar display. The airplane was observed on radar level at 16,000 feet at 09:19:48 CDT heading southwest. The airplane was observed to began a continuous left turn northwest bound at 15,700 feet at 09:20:38. The pilot called Atlanta center at 09:20:48 CDT and stated, "Aero Star six eight triple nine we're going to make a reverse." and there was no further radio contact with the pilot. The last radar return was at 09:20:59. The airplane was at 15, 600 feet. The wreckage was located on May 11, 2006. Examination of the wreckage revealed the right wing separated 9 feet 2 inches outboard of the wing root. The separated outboard section of the right wing was not recovered. The components were forwarded to the NTSB Laboratory for further examination. Examination of the components revealed the deformation patterns found on the fracture surfaces were consistent with upward bending overstress of the right wing.

Aquila Air

On 18 January 2005 at approximately 1340Z, the pilot accompanied by 4 passengers, took off on a private flight from FAWB (Wonderboom Aerodrome) to FAHS (Harrismith aerodrome). However, the pilot advised the FAWB ATC (Wonderboom Air Traffic Controller) that the intended destination was Springs via Delmas. Sometime after 1455Z the aircraft impacted the ground at a high descent rate and high forward speed on a heading of 260°M in a 15° nose-down and 30° right-wing low attitude, whilst the nose of the aircraft was facing in a direction of 211°M, near Cornelia. Partly cloudy weather conditions, with isolated thundershowers prevailed at the time of the accident. Although there were no eyewitnesses to the accident, local inhabitants reported a severe storm in the vicinity of the accident site at the estimated time of the accident. The five occupants were fatally injured and the aircraft destroyed on impact.

Pablo Valencia Iragorri

The twin engine aircraft was completing a flight from Guaymaral to Popayán with an intermediate stop in Girardot, carrying four passengers and one pilot. The aircraft departed Girardot-Santiago Vila Airport at 1523LT. The pilot contacted Bogotá Control and reported his altitude at 4,200 feet bound to the west. At 1537LT, he received the QNH pressure. Two minutes later, while cruising in clouds, the aircraft collided with trees and crashed on the slope of a mountain, bursting into flames. The wreckage was found on Mt San Isidro five days later. The aircraft was destroyed by impact forces and a post crash fire and all five occupants were killed.

Poke Aire

The pilot attempted an ILS approach during night, instrument meteorological conditions. The inbound course was 322 degrees magnetic, and the glideslope outer marker crossing altitude was 3,333 feet msl. The decision altitude was 2,370 feet msl and the airport elevation was 2,143 feet msl. A wreckage path, about 370 feet in length, along a track 320 degrees magnetic, commenced with a tree strike about 300 feet southeast of the outer marker, at an elevation of about 2,200 feet msl. Examination of the airplane revealed no mechanical anomalies.

Grand Aire Express - Executive Aire Express

The airplane was destroyed by impact forces and fire after it impacted the intersection of runway 23 and 32 while attempting a missed-approach. The pilot's crew day started at 1300 and the 14 hour duty limit was 0300 the following morning. The second leg of the flight was delayed 1 hour and 36 minutes due to a freight delay. The operator reported the pilot exceeded his 14 hour crew day by 45 minutes as a result of the freight delay. The flight was cleared for the runway 23 ILS instrument approach. A witness, who was monitoring the Unicom radio frequency, reported that he heard clicking sounds on the Unicom frequency (to bring up the runway light intensity), but the pilot did not make any radio transmissions. The witness reported the ground fog was very thick. Two witnesses reported they heard the airplane's engines. They then heard the engines go to "full power," and then they heard the airplane impact the ground. They saw an initial flash, but could not see the airplane on fire from 2,500 feet away. FAR 135.213 requires that, "Weather observations made and furnished to pilots to conduct IFR operations at an airport must be made at the airport where those IFR operations are conducted." The destination did not have authorized weather reporting, and the operator's Operating Specifications did not list an alternate weather reporting source. At 0253, the observed weather 20 miles to the north, indicated the following: winds 190 at 4 knots, 1/4 statute mile visibility, fog, indefinite ceilings 100 feet, temperature 22 degrees C, dew point 22 degrees C, altimeter 30.00. From the initial point of impact (POI), the wreckage path continued for about 210 feet on a heading of about 180 degrees. The outboard section of the left wing outboard of the nacelle was found on runway 32, about 85 feet from the POI. Separated, unburned, portions of the left aileron and left flap were also found on the runway. The remaining pieces of the left wing were located with the main wreckage. The right wing was located with the main wreckage and the entire span of the right wing from the wing root to the wingtip exhibited continuity. The inspection of the airplane revealed no preexisting anomalies.

Roeder-Johnson Corporation

The airplane had just taken off and was climbing through 9,000 feet when the pilot heard "a very loud explosive sound" that came from the right side of the aircraft. He returned to the airport and landed. When the airplane touched down, it began veered to the right and the pilot attempted to correct. The airplane departed the right side of the runway and the right main landing gear collapsed, driving it through the top of the wing. Half of the right main tire (30 hours total time in service) and most of its inner tube (with a round section blown out) were found at the point of touch down. Missing was the valve stem. Continuous S-shaped marks indicated the tire came off the rim.

Skyline Ranch Investment Company

The Piper Aerostar 602P aircraft, registration N88AT, serial number 62P08628165003, with the pilot, who was also the owner, three passengers, and two dogs on board, took off from the Salt Lake City Airport, Utah, on an instrument flight rules flight to Penticton, British Columbia. At 1149 Pacific standard time, the Kamloops/Castlegar sector controller of Vancouver Centre passed N88AT a special weather observation for Penticton: Awinds calm; visibility : mile in snow; sky obscured; vertical visibility 700 feet; remarks snow eight [8/8 of the sky covered]; temperature zero; 1900 [1100 Pacific standard time] altimeter [email protected] When approaching Penticton, the pilot requested the localizer distance-measuring equipment B (LOC DME-B) approach to runway 16. When the pilot confirmed that he could complete the procedure turn within 13 miles of the Penticton airport, the controller issued an approach clearance for the LOC DME-B approach, with a restriction to complete the procedure turn within 13 miles of the Penticton airport. This restriction was to prevent possible conflicts between N88AT and aircraft taking off or carrying out missed approaches from runway 15 at Kelowna. The pilot reported to the Penticton Flight Service Station at 1203 Pacific standard time that he was by the Penticton non-directional beacon (NDB) outbound on the localizer, and he was given the latest runway condition report. When the aircraft then failed to respond to numerous radio calls from the Penticton Flight Service Station and Vancouver Centre, search and rescue staff were notified and a search initiated. The wreckage was found two days later, near the summit of Okanagan Mountain, in a wooded area, at an elevation of about 5100 feet above sea level. There were no survivors. The aircraft was destroyed but did not catch fire.

Gardner Aircraft Sales

Start-up, taxi and take-off were apparently normal with an IFR clearance for a noise abatement right turn-out on track towards the Talla VOR beacon. Soon afterwards the pilot was given clearance to join controlled airspace on track towards Talla at FL 140 and to expect the flight planned level of FL 200 when cleared by Scottish Radar. As the aircraft was climbing through FL 120 the Talla sector controller first cleared the pilot to climb to FL140 and then almost immediately re-cleared him to climb to FL 200. The pilot replied "ER NEGATIVE I WOULD LIKE TO MAINTAIN ONE FOUR ZERO FOR THE TIME BEING" and the controller granted his request. At 16:21 hrs the pilot transmitted "SCOTTISH NOVEMBER SIX FOUR SEVEN ONE NINE ER REQUESTING HIGHER TO GET OUT OF SOME ICING". Initially the controller offered FL 160 but the pilot replied "IF POSSIBLE TWO ZERO ZERO". Immediately he was given clearance to climb to FL 205, the correct quadrantal cruising altitude. Recorded radar data showed that for the next six minutes, the aircraft's rate of climb and airspeed were erratic. The pilot made one brief transmission of "SCOTTISH" at about 16:30 hrs but nothing more was said by him or the controller for another 20 seconds. Then the controller said "NOVEMBER SIX FOUR SEVEN ONE NINE ER I SEE YOU'RE IN THE TURN DO YOU HAVE A PROBLEM". There was no reply and so the controller repeated his message, eventually receiving the reply "YES I HAVE ER AN EMERGENCY". The controller asked the pilot to "SQUAWK SEVEN SEVEN ZERO ZERO" but the pilot replied "HANG ON". By this time the aircraft was descending rapidly in a gentle right turn. The controller twice asked the pilot for the nature of his problem but the pilot asked the controller to 'HANG ON FOR A MOMENT". The controller could see the aircraft was near high ground and losing altitude rapidly. He twice passed messages to this effect to the pilot but he did not receive an immediate reply. At 16:33 hrs the pilot transmitted "CAN YOU GET ME ER SOMEWHERE WHERE I CAN LAND I CAN'T MAINTAIN ALTITUDE AT ALL". Immediately the controller instructed the pilot to take up an easterly heading and gave him the aircraft's position relative to the airport at Perth. The controller then asked the pilot for his flight conditions (twice) to which the pilot eventually replied "I'M COMING OUT OF ER THE CLOUDS NOW" followed by "JUST BREAKING OUT". The controller then said "ROGER DO YOU HAVE ANY POWER AT ALL OR HAVE YOU LOST THE ENGINE". The pilot replied "I GOT POWER AGAIN BUT I HAVE NO CONTROL". That was his last recorded RTF transmission made at 16:34:40 hrs. The final radar return placed the aircraft at an altitude of 3,150 feet overhead Drummond Hill which is on the north bank of Loch Tay, near the village of Fortingall, and rises to 1,500 feet amsl.

Private German

After landing on runway 12/30 which is 632 metres long, the twin engine aircraft was unable to stop within the remaining distance. It overran, lost its left wing and came to rest, bursting into flames. The pilot, sole on board, was slightly injured.

Sandgar

The pilot had submitted a flight plan nominating a charter category, single pilot, Instrument Flight Rules flight, from Darwin to Port Keats and return. The Piper Aerostar 600A aircraft, with 6 Passengers on board, departed Darwin at 2014 Central Standard Time and arrived at Port Keats at 2106 hours after an uneventful flight. The passengers disembarked at Port Keats and the pilot prepared to return to Darwin alone. At 2119 hours the pilot reported taxying for runway 34 to Brisbane Flight Service. That was the last radio contact with the aircraft. Witnesses noted nothing unusual as the aircraft taxied and then took off from runway 34. As a departure report was not received, a distress phase was declared and subsequently a search was instigated. The following morning a number of major structural components of the aircraft, including the outer left wing, were located at a position 24 km north-east of Port Keats aerodrome and close to the aircraft's flight planned track. The main portion of wreckage was found four days later, destroyed by ground impact. The impact crater was located a considerable distance from the previously located structural components and indicated that an inflight breakup had occurred. The accident was not survivable.

Biodata

The twin engine aircraft departed Aschaffenburg Airport on a training flight to Hahn with two pilots on board, one instructor and one pilot under supervision who was completing his type rating qualification. On approach to Hahn Airport runway 03 in marginal weather conditions, at an altitude of 4,350 feet and at a speed of 150 knots, the aircraft entered an uncontrolled descent. The rate of descent was up to 2,800 feet during the last four seconds before the aircraft crashed in an almost vertical position in a wooded area located about 9 km short of runway. The aircraft disintegrated on impact and both occupants were killed. At the time of the accident, weather conditions were as follow: overcast with few clouds at 200 feet, light rain possible on approach, moderate icing conditions possible in clouds, visibility one km and RVR runway 03 1,300 metres.

Walter L. Cecil

The pilot/owner was performing a post maintenance check flight about 20 miles off shore. He was receiving visual flight advisories from a terminal radar approach facility while in level flight about 4,900 feet msl. Subsequently, the airplane started slowing then descending in a right spiral, and radar contact was lost about 1,000 feet msl. The pilot's body was recovered from the ocean. According to the autopsy report, the pilot had experienced sudden cardiac death secondary to an acute myocardial infarction due to atherosclerotic coronary artery disease. Tramadol, a painkiller not approved by the FAA for flight, was detected in a drug screen and may have masked the chest pain.

Alpha Beta Aviation

During the takeoff roll and initial climb both engines were producing normal power. As the airplane climbed through 150 feet, the left engine lost power. The pilot reported that he feathered the left propeller. He further stated that following the securing of the left engine, the right engine began to 'power down.' The pilot reported that he was unable to maintain a climb attitude and was forced to land on the airport in a grassy area. The subsequent examination of the cockpit disclosed that the left engine throttle was in the full forward position, and the right throttle lever was in the mid-range position. Both propeller levers were found full forward. The left engine mixture lever was in the full forward position, and the right mixture lever full aft, or lean, position. The functional check of both engines was conducted. Initially the left engine would not start, but after troubleshooting the fuel system, the left fuel boost pump was determined to have been defective. The 'loss of engine power after liftoff' checklist requires that the pilot identify the inoperative engine and to feather the propeller for the inoperative engine.

Aircraft Guaranty Corporation Trustee

On May 3, 1999, at an unknown time before 2300 Bangkok, Thailand, local time, a Piper PA-60-602P, N602PK, crashed on an air rally flight between Calcutta, India, and Bangkok. The German national pilot was confirmed to have been fatally injured, and his German national passenger was reported missing at the accident scene. The crash site was at the Srinakarin Reservoir, Tambon Tha Chalab, Srisawat district in Kanchanaburi province, west of Bangkok. The airplane was reported to have been due to land at Bangkok's Don Muang airport at 2300 local time on May 3. Adverse weather was reported in the vicinity at the time of the accident. There was no report of an ELT actuation.

Henry K. Sagel

After takeoff while over the departure end of the runway, deep gray colored smoke was observed by the tower controller trailing the right engine. The pilot was alerted of this and advised the controller the flight was returning. Witnesses reported seeing smoke trailing the right engine and that the airplane rolled to the left, pitched nose down, impacted trees, and then the ground. A fatigue crack was detected in the exhaust aft of the No. 6 cylinder of the right engine; and incomplete fusion of a weld repair was also noted. Heat damaged components from the right engine were replaced and the engine was started and found to operate normally. A foreign object of undetermined origin was found in the intake area of the No. 3 cylinder. Analysis of the voice tape revealed both engines/propellers were operating near full rated rpm when the pilot acknowledged the transmission that smoke was trailing the right engine, one engine/propeller rpm then decreased to about 2,160 rpm. Examination of the flight controls revealed no evidence of preimpact failure or malfunction. Flap positions at impact could not be determined. Calculations indicate that the airplane was approximately 55 pounds over the maximum certificated takeoff weight at takeoff.

David C. Blessing

The airplane departed at night after maintenance was performed on the left engine. The pilot attempted to return to the airport and while on base leg struck the ground inverted and nose down. The left engine propeller was found feathered. On the left engine, the # 5 cylinder was off the engine and the # 5 piston with the connecting rod still attached were found nearby. Interviews revealed that during maintenance, the # 1,3,5,and 6 cylinders had been removed and reinstalled; however, the # 5 cylinder had not been tightened. Several people had worked on the airplane at various stages of the work. The maintenance facility did not have a system to pass down what had been accomplished, and the FAA did not require the tracking of work accomplished in other than 14 CFR Part 121, or 14 CFR Part 145 facilities.

Maine Flight Center

The twin-engine Aerostar departed on Runway 1. While on initial climb, after take-off, witnesses observed the airplane roll to the left until it became inverted, after which the nose dropped and the airplane impacted the ground in a near vertical nose down attitude. The fuselage was consumed with a post crash fire. On-site examination revealed the wing flaps and landing gear were retracted. No evidence of a mechanical failure or malfunction was found relating to the airplane, engines, or propellers. The investigation revealed that both propellers were rotating and absorbing power at the time of impact. The winds were reported from 360 degrees at 17 knots, with gusts to 25 knots.

Pilot und Flugzeug

The twin engine airplane crashed in unknown circumstances while approaching Erfurt-Weimar Airport. The wreckage was found 3 km from the airport. All four occupants were killed, three Swiss and one German.

James H. Doering

The airplane was over gross weight at takeoff but within Weight and Balance at the time of the accident. Witnesses observed the airplane flying low with the landing gear retracted over a wooded area then observed the airplane bank to the left and pitch down. The airplane then pitched nose up and entered what was described as a flat spin to the left. The airplane descended and impacted the ground upright with the landing gear retracted and the flaps symmetrically extended 6 degrees. Examination of the flight control systems, and engines revealed no evidence of preimpact failure or malfunction. A cabin door ajar indicating light was not illuminated at impact but the gear warning light was illuminated at impact. The pilot recently purchased the aircraft and only accumulated a total of 1 hour 23 minutes during 6 training flights. He accumulated an additional 3 hours 37 minutes after completion of the training flights while flying with other qualified pilots. The accident flight was the first flight in the make and model while flying with no other multiengine-rated pilot aboard.

Robert L. Kovach

After making a localizer runway 08 approach, the pilot landed over halfway down the 4,422 feet wet runway. He then decided to abort the landing, added power, and when airborne, retracted the landing gear. He said he asked the right front seat (non-rated) passenger to reset the flaps (to 20°). The pilot saw trees ahead, and realized the airplane was not going to clear the obstacles, though full power was applied. Just before impact, he pulled back on the elevator control to soften the impact, rather than hitting the trees nose first. After the accident, the wing flaps were found in the retracted position. A passenger was killed and three other occupants were seriously injured.

New Creations

The airplane was on a positioning flight at night, cruising at 6,000 feet. Also, the pilot was operating on an IFR flight plan and was on his 6th flight after reporting for duty at 1530 est. During a frequency change and radio check at 0207 est, the pilot's response was normal. Radar data revealed that about 16 minutes later, the airplane entered a right turn, then disappeared from radar at about 0222 est after about 255° of turn. It impacted the ground in a steep nose down descent; debris from the airplane was found down to 6 feet below the surface. During the final 15 minutes of flight, there were no radio transmissions on the assigned frequency. No preimpact mechanical failure or malfunction was found. The propeller blades had s-curves or were bent forward; they also had leading edge impact damage and Rotational scoring. The pilot had flown in excess of 120 hours (110 hrs at night) in the preceding 30 days. There was evidence that he may have lacked crew rest during the day(s) before the accident.

FCF-Bowers

As the airplane approached 22,000 feet, the pilot reported that both engines stopped running within seconds of each other. During the emergency landing approach the airplane collided with trees. Onscene investigation revealed no mechanical anomalies with the engines. The fuel system was empty, other than traces of fuel found in the left and right engine's fuel injector servos and flow dividers. Both wing fuel tank caps o-rings were hardened and had flat spots on them. The caps' opening tabs were able to be opened at 8 and 3 lbs of force, respectively. The company holding the airplane's type certificate states an opening force of 16 lbs of force is required. The company's annual inspection checklist requires that the tabs be checked. No record of this being accomplished was found in the airframe logbook. The pilot operating handbook states that the fuel cap tab tension must be checked during the preflight inspection.

Clifford Botway

During an aborted takeoff, the airplane overran the 4,451 foot long runway, went down a hill, and struck a fence. According to the pilot, 'during the takeoff roll, the indicated airspeed needle climbed to approximately 60 knots, but then would go no further... My attempts to dislodge it by tapping on the face of the gauge were futile...I pulled back the throttles and applied full brakes...' The pilot reported that based on the existing conditions 'the airplane can accelerate from rest to rotation speed and back to rest in less than 3,500 feet.' The examination of the airplane revealed the pitot tube was internally obstructed with an insect and mud.

Cherokee Express Air Cargo

The flight had been cleared for the VOR-A approach, with instructions to circle to a right downwind and land on runway 14. The tower controller observed the airplane emerge from the overcast over runway 23 abeam the VOR, then make a tight right turn onto the downwind leg, parallel to runway 14 and close in. When the airplane was abeam the runway 14 threshold, she observed the nose pitch up, and the airplane did what she described as a wing over. It then dove and impacted the runway near the threshold. The controller stated that the pilot made this round trip every day, and she had seen him do this maneuver on several occasions. The pilot, sole on board, was killed.

Potomac Imaging Associates

During a VOR runway 22 approach, the instrument rated pilot sighted the runway and cancelled his IFR flight plan. As he was circling to land, the airplane stalled and collided with terrain. Witnesses stated that the airplane made a steep left banking turn about 250 feet above the ground. According to witnesses, upon roll out of the turn, the airplane's wings rocked back and forth, the nose and right wing dropped below the horizon, and the airplane fell to the ground. Instrument meteorological conditions existed at the time of the accident and witnesses stated that the ceiling was about 400 to 500 feet above the ground. Weather facilities in the area were forecasting about 1,000 foot ceilings throughout the area. All three occupants were killed.

Zero One Tango

During the takeoff ground run, witnesses observed the airplane at a slow speed, using the full length of the 4,102-ft runway before it became airborne briefly. The left wing dipped, struck some power lines, and the airplane crashed on a highway striking a car. Metallurgical teardown examinations of the two left engine turbochargers disclosed evidence of extreme wear in the bearings from the turbine wheel shafts which resulted in obstructed oil ports. Both occupants were injured.

English Aero Services

The pilot was on a personal trip that he had flown many times. On the day of the accident, additional fuel was not available at the departure airport. As he neared his destination, the pilot left one of his engines in a fuel crossfeed configuration causing a partial power loss. The airplane has the capability to climb at more than 500 feet per minute using only one engine. After declaring his emergency to the control tower, radio contact was lost. The aircraft was observed flying 90° to the ILS final approach course at very low altitude banking side to side. The airplane crashed in a 70° nose down position. Heavy snow had started falling just before the accident. A post crash fire destroyed much of the airplane. Both occupants were killed.

Jimmy M. Franklin

While departing on a cross country flight the aircraft was observed to have an abnormally long takeoff roll and to rotate abruptly to a higher than normal nose attitude. Initial climb was followed by settling with a high nose attitude and the aircraft crashed approximately one mile beyond the departure end of the runway. The main cabin door was found in the unlocked position and the lower half was found near the beginning of the wreckage path with impact damage. The top half was found further down the wreckage path and had sustained fire damage. The Aerostar has an observed drag and pitch performance degradation if the cabin door opens during takeoff run. A passenger was seriously injured while two other occupants were killed.

Lawrence R. Edwards

The pilot of the multi-engine aircraft reported that his right engine was losing oil as he was climbing to cruise altitude. He secured the engine, feathered the propeller, and maneuvered to return to the airport. The pilot trimmed the aircraft for single engine operation and extended the main landing gear. During the approach, the operating left engine would not develop full power and the pilot reported to atc that he could not make the airport. The aircraft continued its emergency descent, impacted trees, and descended uncontrolled through a densely wooded area. A fuel tank ruptured during the uncontrolled descent through the trees and a fire/explosion occurred. The aircraft continued to burn after ground impact. Both engines were disassembled and numerous mechanical anomalies were found. They had been recently overhauled. This was the first flight of the aircraft since the engine overhauls. The pilot/owner was en route to sell the aircraft when the accident occurred. The pilot, sole on board, was killed.

Federal Armored Service

A Piper PA-28, N55354, had departed Plymouth, MI and was climbing from 1,300 feet msl on a course of about 282° with a ground speed of 80 knots. At about the same time, a Piper PA-60, N8060J, was cruising at 2,100 feet msl on a flight from Detroit to Jackson, MI, on a course of about 258° with a ground speed of 165 knots. Subsequently, the 2 aircraft converged and collided at 2,100 feet msl. Both aircraft then plunged to the ground and crashed. Radar data and wreckage exam revealed the PA-60 had converged from the right rear of the PA-28; the PA-28 converged on the PA-60 from its lower, left, forward area. The PA-28 was on an instrument training flight with a rated private pilot and an instructor pilot (cfi) aboard. The investigation did not reveal which seat the cfi was occupying. No flight plan had been filed for either flight, nor was there any indication that either flight crew had obtained ATC/radar assistance. The pilot, sole on board, was killed.

Walter V. Wicker Jr.

On January 16, 1989, Machen nacelle mounted induction air intercoolers were installed on N6894Y. On December 14, 1989, an annual inspection was performed, and a Machen superstar i-680 kit was installed. On December 21, 1989, N6894Y was at 6,000 feet when the pilot reported a problem with the right engine. The pilot reported a fire in the right engine. A couple of minutes later, he radioed he could not shut down the right engine. At 1034:37 the pilot advised his 'right engine just tore off' and that he was 'in a spin heading down.' The exhaust tailpipe of the left turbocharger on the right engine was found to have separated. Metallurgical examination revealed the tailpipe failed due to fatigue cracking. Records showed that part I of piper service bulletin 920 (engine tailpipe inspection) had been completed, while part II (addition of fire detection system) had not been accomplished due to the lack of available kits. The pilot, sole on board, was killed.

Cherokee Express Air Cargo

The air taxi aircraft departed Shreveport, LA, at approximately 0500 cst on an unscheduled, domestic, cargo flight. At about 0815 est, the pilot reported on company frequency that he was approximately 30 minutes from the destination (Orlando, FL). Subsequently, the aircraft crashed in the northwest part of Lake Apopka, approximately 15 to 20 miles west-northwest of the destination airport. A witness heard it crash, then saw parts from the aircraft, but did not see the actual impact. There was evidence the aircraft impacted in a shallow descent, while in a slight left wing low attitude, traveling at a relatively high speed. No preimpact part failure or malfunction of the aircraft or engine was found, though the aircraft was extensively damaged and some of the wreckage was not recovered from the lake. The Orlando weather was in part: 2,500 feet scattered, visibility 6 miles with fog and haze, wind from 350° at 4 knots. Both occupants were killed.

Top Flight Air Service

During arrival, the pilot was cleared for an ILS runway 07 approach. Also, he was advised of a DC-9 that was 4 miles ahead and was told to use caution for wake turbulence. As the aircraft was on final approach, it descended below the ILS glide slope and subsequently hit trees and crashed about 1.8 mile short of the runway. No preimpact part failure or malfunction of the aircraft or engines was found that would have resulted in an accident. Also, there were no reported problems with the ILS system and it tested normal after the accident. The pilot held a commercial pilot certificate which was good for single engine land aircraft; his multi-engine privileges were authorized as a private pilot, only. An NTSB performance study showed the aircraft was 2 minutes and 57 seconds behind the DC-9. Radar data indicated the aircraft did not exceed a bank angle of 32° and no excessive g-values were evident during the approach. The pilot, sole on board, was killed.

Albert T. Gianchiglia

The aircraft was on final approach to runway 30 at Somerset airport, Somerville, New Jersey when there was a loss of power of the right engine. The pilot raised the landing gear and flaps, and the aircraft rolled to the right, descended toward the ground and crashed. The fuel selector valve to the right wing tank was in the closed position. The right engine magnetos were defective. All four occupants were injured, two seriously.

Richard L. Bird

Flight entered near vertical descent while flying in area of level 1 and 2 thunderstorms just after pilot had called requesting permission to deviate around rain showers. A level 5 thunderstorm was present 8 miles west. The aircraft descended at rates up to 13,800 feet per minute. Witnesses saw aircraft exit bottom of clouds at approximately 4,000 feet in a near flat attitude and rotating around the yaw axis to the left. Engine sounds increased and decreased as the aircraft rotated and all components appeared to be present on the aircraft. No smoke or flame was visible. At approximately 500 feet above the water the rotation stopped and the nose dropped to a 30 to 70° nose down angle and both engines could be heard increasing in power. Before the recovery could be completed the acft struck the ocean. The pilot, sole on board, was killed.

Executive Air

As the aircraft was taxiing for takeoff, witnesses noted the left rear baggage door was unlocked and hanging down. A warning was relayed to the pilot via the tower, but by then the aircraft was airborne and the pilot had reported a control problem. During lift-off, the aircraft pitched up sharply and entered an immediate right bank of about 45°. As the gear retracted, the bank angle decreased to about 20°. The aircraft was reported to yaw slightly from side to side and circle to the right while climbing to about 1,000 feet. A witness (in radio contact) asked the pilot about the problem; the pilot replied the controls (ctls) were locked to one side. On advice of others, the pilot tried to control the aircraft with engine power adjustments, but the aircraft lost altitude to about 200 feet agl. Subsequently, while maneuvering, it struck a tree, then hit a utility pole and crashed. During impact the lower fuselage, which housed the flight control linkages, was badly damaged. No preimpact mechanical problem was verified concerning the flight controls, autopilot or trim. A pilot, who had previously flown the aircraft with the baggage door open, said he experienced no adverse control problems. The pilot, sole on board, was killed.

Private Australian

The pilot was conducting a freight charter flight, and witness evidence confirmed that on DEPARTURE he was occupying the left-hand seat. The pilot was accompanied by a friend who was also a commercial pilot, but not endorsed on this type of aircraft. Approximately 18 minutes prior to the estimated time of arrival at the destination, the pilot reported leaving the cruising altitude of 6500 feet on descent. Several minutes after the descent report had been made, a witness about 50 kilometres from the destination reported seeing the aircraft pull-up into a very steep climb from an extremely low height with its wings level, and then become inverted. It then entered what was described by the witness as a spin or spiral dive, before impacting the ground in a near vertical descent. The pilot was found in the right-hand seat, and the passenger had been thrown clear of the wreckage. It was established that neither seat belt had been fastened at the time of the impact. Although it could not be determined which pilot was flying the aircraft at the time of the pull-up, medical evidence suggested that the pilot occupying the right-hand seat position was handling the controls at the time of ground impact. The weather at the time of the accident was fine and clear, with 10-15 knot winds.

Air Continental

The pilot departed Louisville, KY reportedly with a known oil leak in the right engine and was on the second leg of an on-demand air taxi cargo flight. About 14 minutes after entering Mansfield approach control airspace, the pilot requested and received an altitude change from 5,000 to 3,000 ft because he 'was picking up a lot of ice.' After entering Cleveland approach airspace he reported the right engine had failed and requested to return to Mansfield. The pilot was informed of Mansfield weather. He then indicated he wanted to try Cleveland, then reported he could not maintain altitude and wanted to go to Mansfield. The pilot was receiving vectors from Mansfield for an ASR approach to runway 23 and at about 1 1/2 miles from the threshold the pilot reported he was lowering the landing gear. The aircraft then disappeared from the radar scope. Investigation revealed improper weld repairs to the right engine case and separation of the number six cylinder from the case due to fatigue cracking in the through bolts and studs.