3 June 1973: While maneuvering at low altitude at the Paris Air Show, the first production Tupolev Tu-144S, CCCP-77102, Aeroflot’s new Mach 2+ supersonic airliner, broke apart in midair and crashed into a residential area. All six crew members and eight people on the ground died. Another 25 were injured.
The Tu-144 was built by Tupolev OKB at the Voronezh Aviation Plant (VASO), Pridacha Airport, Voronezh. It was a large delta-winged aircraft with a “droop” nose for improved low speed cockpit visibility and retractable canards mounted high on the fuselage behind the cockpit. It was flown by a crew of 3 and was designed to carry up to 140 passengers.
77106 is 65.50 meters (215 feet, 6.6 inches) long, with a wingspan of 28.00 meters (91 feet, 10.4 inches). The tip of the vertical fin was 11.45 meters (37 feet, 6.8 inches) high. The 144S has a total wing are of 503 square meters (5,414 square feet). Its empty weight is 91,800 kilograms (202,384 pounds) and the maximum takeoff weight is 195,000 kilograms (429,901 pounds). (A number of Tu-144S airliners had extended wing tips, increasing the span to 28.80 meters (94 feet, 5.9 inches) and the wing area to 507 square meters (5,457 square feet).
The Tu-144S was powered by four Kuznetsov NK-144A engines. The NK-144 is a two-spool axial-flow turbofan engine with afterburner. It uses a 2-stage fan section, 14 stage compressor section (11 high- and 3 low-pressure stages), and a 3-stage turbine (1 high- and 2 low-pressure stages). It is rated at 147.0 kilonewtons (33,047 pounds of thrust) for supersonic cruise, and 178.0 kilonewtons (40,016 pounds of thrust) with afterburner for takeoff. The NK-144A is 5.200 meters (17 feet, 0.7 inches) long, 1.500 meters (4 feet, 11.1 inches) in diameter and weighs 2,827 kilograms (6,233 pounds).
The 144S has a cruise speed of Mach 2.07 (2,200 kilometers per hour/1,367 miles per hour) with a maximum speed of Mach 2.35 (2,500 kilometers per hour/1,553 miles per hour). The service ceiling is approximately 20,000 meters (65,617 feet). Its practical range is 3,080 kilometers (1,914 miles).
In actual commercial service, the Tu-144 was extremely unreliable. It was withdrawn from service after a total of just 102 commercial flights, including 55 passenger flights.
The cause of the accident is not known, other than the obvious structural failure, but there is speculation that the Tu-144 was trying to avoid another airplane.
At 1:00 p.m., 17 March 1964, Joan Merriam Smith departed Oakland International Airport, on California’s San Francisco Bay, on what would be the first leg of an around-the world flight. Her first stop would be Tucson, Arizona, approximately 650 nautical miles (1,200 kilometers) to the east-southeast.
Mrs. Smith intended to follow the easterly route of Amelia Earhart, who had departed from Oakland on both of her attempts at the around-the-world flight. The first try, 17 March 1937, was a westerly route, with a first stop at Hawaii. The second try, 2 June 1937, was an eastbound route.
The two routes were planned to take advantage of seasonal weather patterns.
Mrs. Smith wanted to follow Earhart’s eastbound route, but by leaving in mid-March, she put herself at a disadvantage with respect to the weather she would encounter as she traveled around the Earth.
Unlike Earhart, who had two of the world’s foremost navigators in her flight crew, Mrs. Smith would fly alone, her only companion a small teddy bear. She would navigate by pilotage and ded reckoning, and by using radio aids such as non-directional beacons (NDBs) and VHF omnidirectional ranges (VORs).
Forecast adverse weather caused her to leave Tucson for her next stop, New Orleans, Louisiana, at 2:00 a.m., 18 March. Dodging the weather, she was forced to make an intermediate fuel stop at Lubbock, Texas. She finally arrived in New Orleans at 4:00 p.m. that afternoon. After another early morning start, she flew on to Miami, Florida, on 19 March.
A detailed story of Joan Merriam Smith’s flight is told in Fate on a Folded Wing, written by Tiffany Ann Brown.¹ Her route followed Earhart’s eastward across the United States; south over the Caribbean Sea to South America; then across the South Atlantic Ocean; Africa, Asia, and finally, to the Pacific Ocean, where Mrs. Smith’s route diverged from Earhart’s.
Smith’s itinerary: Across the United States from Oakland, California, to Tucson, Arizona; Lubbock, Texas; New Orleans, Louisiana; Miami, Florida. Then over the Caribbean Sea to San Juan, Paramaribo, Natal; east across the South Atlantic to Dakar, Gao, Fort-Lamy, Al-Fashir, Khartoum, Aden. From Africa, Smith headed into South Asia: Karachi, Calcutta, Akyab, Rangoon; and then Southeast Asia: Bangkok, Singapore, Jakarta, Surabaya, Kupang; Darwin, Northern Territory, Australia; and Lae, New Guinea. From here, Smith deviated from Earhart’s route across the Pacific Ocean by flying to Guam instead of Howland Island; then Wake Island; Midway Island; Honolulu, Hawaii; and, finally Oakland.
Mrs. Smith’s flight was troubled by adverse weather, leaking fuel tanks, out-of-calibration radio equipment, a recalcitrant autopilot, problems with the hydraulic and electrical systems, and a heater that would not work. And weather. . .
She arrived back at Oakland International at 9:12 a.m., on 12 May 1964, having flown approximately 27,750 miles (44,659 kilometers). The total duration of her journey was 55 days, 20 hours, 12 minutes. She had flown 35 legs on 23 days. Mrs. Smith wrote that the circumnavigation had taken a total of 170 flight hours, with 47 hours on instruments and 26 hours of night time.
Joan Merriam Smith is credited with having made the first solo circumnavigation of the Earth by the Equatorial route, and the longest solo flight.
The airplane flown by Joan Merriam Smith was a Piper PA-23-160 Apache E, serial number 23-1196, U.S. registration N3251P, which she had named City of Long Beach. The red and white airplane was manufactured by the Piper Aircraft Corporation at Lock Haven, Pennsylvania, in 1958. It had been purchased by the State of Illinois Department of Aeronautics to use checking state-owned aeronautical facilities. When the the state acquired a faster aircraft, the Apache was sold in November 1963. The Federal Aviation Administration issued a registration certificate to Mrs. Smith on 30 December 1963.
The Piper PA-23-160 Apache E was a 4-place, twin-engine, light airplane with retractable tricycle landing gear. It was 27 feet, 2 inches (8.280 meters) long with a wingspan of 37 feet, 0 inches (11.278 meters) and overall height of 10 feet, 1 inch (3.073 meters). The airplane had an empty weight of 2,230 pounds (1,011.5 kilograms) and maximum gross weight of 3,800 pounds (1,723.7 kilograms).
The Apache E was powered by two air-cooled, normally-aspirated, 319.749-cubic-inch-displacement (5.240 liter) Lycoming O-320-B horizontally-opposed 4-cylinder overhead valve (OHV) engines with a compression ratio of 8.5:1. The O-320-B is a direct-drive, right-hand tractor engine, rated at 160 horsepower at 2,700 r.p.m. The O-320-B is 2 feet, 5.56 inches (0.751 meters) long, 2 feet, 8.24 inches (0.819 meters) wide and 1 foot, 10.99 inches (0.584 meters) high. It weighs 278 pounds (126.1 kilograms). The engines turned two-bladed Hartzell constant-speed propellers.
N3251P’s engines were modified with Rajay Co., Inc., Turbo 200 turbochargers.
The PA-23-160 had a cruise speed of 150 knots (173 miles per hour/278 kilometers per hour) and maximum speed was 159 knots (183 miles per hour/295 kilometers per hour). The service ceiling was 17,000 feet (5,182 meters).
During a flight from Las Vegas, Nevada, to Long Beach, 9 January 1965, the cabin heater in the nose of the Apache caught fire. With the cabin filled with smoke and gasoline fumes, and unable to reach any airport, Mrs. Smith crash-landed the airplane in rocky terrain in the Ord Mountains, southeast of Barstow in the high desert of southern California. After it has slid to a stop, N3251P continued to burn and was largely destroyed. Mrs. Smith and her passenger, Willam Harry Eytchison, were slightly injured.
At the time of the accident, N3251P had just under 3,000 hours total time on the airframe (TTAF), and less than 400 hours on new engines (TSN).
Joan Ann Merriam was born 3 August 1936 at Oceanside, Long Island, New York, U.S.A. She was the daughter of Arthur Ray Merriam, Jr., a railroad office stenographer, and Ann Marie Lofgren Merriam. The family relocated to Wayne, Michigan, where Joan attended Jefferson Junior High School and Wayne High School.
Joan’s father died at the age of 43, New Year’s Day, 1952. She and her mother then moved to Miami, Florida. Flying from Detroit to Miami aboard a Lockheed Constellation, Joan was allowed to visit the flight deck and speak to the crew.
The airline flight sparked an interest in aviation. She began taking lessons at the age of 15. Joan learned to fly at the Embry-Riddle Aeronautical Institute, then located at at Tamiami Airport. She first soloed an airplane at the age of 16 years. On 7 November 1953, shortly after her 17th birthday, she was issued private pilot certificate. Special permission was obtained from the FAA for her to take the written exams for commercial pilot before she turned 18.
Joan graduated from Miami Senior High School in 1954.
Mrs. Merriam gave Joan a Cessna 140, a single-engine light airplane, making her one of the youngest people in the United States to own an airplane. Joan said that her mother was “the bravest passenger,” as she practiced all of the maneuvers required for a commercial pilot’s license. By the time she was 18, she earned a commercial pilot certificate with an instrument rating, and a flight instructor certificate. She began instructing at Tamiami. She flew charters from Florida to Texas, living in that state before moving to Panama City, Florida. On her twenty-third birthday, the earliest that she was eligible, Miss Merriam was issued an airline transport pilot certificate (ATP) by the FAA. She had flown nearly 5,000 hours.
Miss Merriam would later own a Piper Cub modified for aerobatics, a second Cessna 140, and a Cessna 172.
In the fall of 1955, Miss Merriam married Harold MacDonald, a student in aeronautical engineering. She worked as a flight instructor for Avex, Inc., at Tamiami Airport. Mr. and Mrs. MacDonald soon divorced.
In 1960, Miss Merriam was living in Panama City, Florida, where she was employed as a pilot for West Florida Natural Gas Company, one of very few women who flew as corporate pilots at the time. (Contemporary newspapers reported that she was “one of three women corporation pilots in the country.”) Reflecting the sexist attitudes of the time, news features often described her as a “blue-eyed platinum blonde,” and made mention of “her personal aerodynamic attributes.” In an interview, Miss Merriam said that a major reason preventing more women from executive flying were, “executive’s wives, and executive’s secretaries.”
She had met Lieutenant (j.g.) Marvin G. (“Jack”) Smith, Jr., U.S. Navy, in 1958. Lieutenant Smith was executive officer of USS Vital (MSO-474), an Agile-class minesweeper homeported at Panama City. She moved to San Leandro, California, and worked as a contract instrument flight instructor at Oakland International Airport for the Sixth United States Army, which was then based at the Presidio of San Francisco.
Miss Merriam and Lieutenant Smith were married at Monterey, California, 23 September 1960. The couple later moved to Long Beach, where Lieutenant Commander Smith’s next ship, USS Endurance (AM-435), was homeported.
In February 1965, Joan Merriam Smith was flying for Rajay Industries out of Long Beach, California. (Rajay was a turbocharger manufacturer which had supplied the turbos for Mrs. Smith’s Apache.) She had been conducting functional and reliability tests on a modified Cessna 182C Skylane, N8784T. The airplane was owned by the V. E. Kuster Co., of Long Beach, a supplier of oil field equipment.
The flight test plan for 17 February 1965 called for the Cessna to be flown at altitudes between 5,000 and 23,000 feet (1,524–7,010 meters). Mrs. Smith was flying. Also on board was her biographer, Beatrice Ann (“Trixie”) Schubert.
Smith was flying across the San Gabriel Mountains, which divide southern California’s coastal plain from the high desert. The highest peak in the range, Mount San Antonio, which was not far east of her course, rises to 10,046 feet (3,062 meters).
Witnesses said that the airplane had been flying normally, estimated at between 1,000 and 2,000 feet (305–610 meters) above the mountainous terrain, when the right wing folded back along the fuselage. The airplane, with the engine revving, went into a dive and crashed into the north slope of Blue Ridge, a few miles west of Wrightwood, California, 10–12 seconds later. There was an explosion and fire.
Joan Merriam Smith and Trixie Ann Schubert were killed.
Investigators found that both wings had failed outboard of the struts. The outer wing panels, both ailerons and the left elevator were located approximately 1½ miles (2½ kilometers) from the point of impact. Examination showed that the aircraft had suffered severe loads. “There was no evidence of fatigue or failure of the aircraft before the inflight structural failure.”
The Civil Aeronautics Board reported the Probable Cause: “The pilot entered an area of light to moderate turbulence at high speed, during which aerodynamic forces exceeding the structural strength of the aircraft caused in-flight structural failure.” According to the CAB, the Cessna 182 had an airspeed in excess of 190 miles per hour (306 kilometers per hour) when it entered the area of turbulence.
Her remains were interred at Forest Lawn Memorial Park, Cypress, California.
For her accomplishment, Joan Merriam Smith was posthumously awarded the Harmon Aviatrix Trophy for 1965. At a ceremony held in the Indian Treaty Room of the Executive Office Building, 15 December 1965, the trophy was presented to her husband, Lieutenant Commander Marvin G. Smith, Jr., by Vice President Hubert Humphrey.
Mrs. Smith had intended to attempt an altitude record with the turbocharged Skylane. On 20 July 1965, her husband, Marvin G. Smith, set the record at 10,689.6 meters (35,070.9 feet), flying a Cessna 210A Centurion with an IO-470 engine.²
TDiA would like to thank Ms. Tiffany Ann Brown for suggesting this subject, and for her invaluable contribution.
¹ Fate on a Folded Wing: The True Story of Pioneering Solo Pilot Joan Merriam Smith, by Tiffany Ann Brown. Lucky Bat Books, 2019.
² FAI Record File Number 9977 (Class C, Sub-Class C1c: powered airplanes, takeoff weight 1000 to 1750 kg).
18 March 1939: At 12:57 p.m., Pacific Standard Time (19:47 G.M.T.), the Boeing Model S-307 Stratoliner, NX19901, took off from Boeing Field, Seattle, Washington, on Test Flight No. 19. Julius Augustus Barr was the pilot in command.
The S-307, Boeing serial number 1994, was a prototype four-engine, pressurized commercial airliner. It had first flown on 31 December 1938, with Boeing’s Chief of Flight Test, Edmund Turney (“Eddie”) Allen, as first pilot (the Pilot in Command), and Julius Barr as his copilot. Allen had flown the first eighteen flights. “The performance of aircraft NX 19901 on flights prior to Test Flight No. 19 had either met or exceeded the manufacturer’s estimates.”
Julius Barr was employed by Boeing as a test pilot, 16 November 1938. Following Flight Test No. 15, Allen approved Barr to act as first pilot on the Model 307. He first served as the pilot in command of NX19901 on 21 January 1939. This was a taxi test, with the Stratoliner never leaving the ground. Barr first flew the airplane nearly two months later, 16 March 1939, with copilot Earl Alvin Ferguson. Barr made two more flights on 17 March. Harlan Hull, Chief Pilot of Transcontinental and Western Air, Inc., flew as copilot.
At takeoff on 18 March 1939, Barr had only 2 hours, 6 minutes as pilot in command of the Boeing 307; and 17 hours, 55 minutes as second in command. He had flown as an observer aboard NX19901 for 1 hour, 52 minutes.
There were ten persons on board the Stratoliner for Test Flight No. 19. In addition to Julius Barr as P.I.C., the designated copilot was Earl Ferguson. There were two alternate copilots, Harlan Hull and Benjamin J. Pearson, an assistant sales manager for Boeing. Ralph LaVenture Cram was first aerodynamcist, assisted by John Kylstra. William C. Doyle served as oscillograph operator, and Harry T. West, Jr., was the engineering officer. These were all Boeing employees. Pieter Guillonard, technical director of Koninklijke Luchtvaart Maatschappij N.V. (KLM Royal Dutch Airlines), acted as recorder and photographer, while Albert Gillis von Baumhauer, an engineer with the Luchtvaartdienst (the Dutch Aviation Authority), acted as an assistant aerodynamicist.
Specialized test equipment had been installed at the copilot’s position. For this reason, Von Baumhauer, rather than the designated copilot, Ferguson, was in the copilot’s seat during this test flight. (Von Baumgartner held a Dutch private pilot certificate, issued 28 November 1931. Since that time, he had flown only 116 hours, and had no experience flying multi-engine aircraft. He was not qualified to act as copilot.)
Guillonard and Von Baumhauer had recommended a series of tests to be conducted on Test Flight No. 19, including observing the airplane’s behavior following an engine cut on takeoff with no rudder input; a series of side slips and stall tests. Von Baumhauer had emphasized “complete stalls” rather than initiating recovery when stall was detected.
After takeoff, NX19901 climbed to 10,000 feet (3,048 meters) and at 140 miles per hour (225 kilometers per hour) a series of static longitudinal stability tests were performed. According to the test flight plan, side slips were to be investigated next.
At 1:12 P.M. (PST) a radio message was transmitted from NX 19901 to the Boeing Aircraft Company radio station located at Seattle, Washington, which message gave the position of the aircraft as being between Tacoma Washington and Mount Rainier at an altitude of 11,000 feet. Some two or three minutes later, while flying at a comparatively slow rate of speed in the vicinity of Alder, Washington, the aircraft stalled and began to spin in a nose down attitude. After completing two or three turns in the spin, during which power was applied, it recovered from the spin and began to dive. The aircraft partially recovered from the dive at an altitude of approximately 3,000 feet above sea level, during which recovery it began to disintegrate. Outboard sections of the left and right wings failed upward and broke entirely loose from the aircraft. Major portions of the vertical fin and portions of the rudder were carried away by wing wreckage. The outboard section of the left elevator separated from the stabilizer and both fell to the ground detached. The right horizontal tail surface, being held on by the fairing long the top surface and also by the elevator trim tab cables, remained with the fuselage. The No. 1 engine nacelle also broke loose from the aircraft and fell to the ground separately. The main body of the aircraft settled vertically and struck the ground in an almost level attitude both longitudinally and laterally at a point approximately 1,200 feet above sea level. Watches and clocks aboard the aircraft, which were broken by the force of the impact, indicated the time of the accident at approximately 1:17 p.m. (PST).
—AIR SAFETY BOARD REPORT, at Pages 34–35.
All ten persons aboard were killed in the crash. The Stratoliner was destroyed. Because of the water ballast in the main fuel tanks, there was no post crash fire.
During the crash investigation it was found that two B-17s had previously been spun. The first,
. . . while flying with a gross load of about 42,000 pounds at an altitude of 14,000 feet, went into an inadvertent spin and made two complete turns before recovery was effected. During the pull-out from the ensuing dive, permanent distortion occurred in the structure of both wings, necessitating the installation of new wings on the aircraft.
In the second of these experiences, a similar ship was intentionally permitted to enter a spin following a complete stall. The controls were immediately reversed and the aircraft responded promptly, enabling the pilot to effect recovery after three-fourths of a turn in—
Evidence indicated that power was used in recovery from the spin in the case of NX 19901. It should be noted that in the two instances above described recovery from spin in similar aircraft was accomplished without the employment of power. In one of these cases, permanent distortion occurred in both wings.
—AIR SAFETY BOARD REPORT, at Pages 48 and 49.
Structural failure of the wings and horizontal tail surfaces due to the imposition of loads thereon in excess of those for which they were designed, the failure occurring in an abrupt pull-out from a dive following recovery from an inadvertent spin.
—AIR SAFETY BOARD REPORT, at Page 56
The Boeing Model 307 was operated by a crew of five and could carry up to 33 passengers. It was the first pressurized airliner and, because of its complexity, it was also the first airplane to include a flight engineer as a crew member. It could maintain a cabin pressure equivalent to 12,000 feet (3,650 meters) to a pressure altitude of 19,000 feet (5,791 meters).
The Model 307 used the wings, tail surfaces, engines and landing gear of the production B-17B Flying Fortress heavy bomber. The vertical fin and rudder were of the same design as the B-17B’s, though somewhat larger. The fuselage was circular in cross section to allow for pressurization. It was 74 feet, 4 inches (22.657 meters) long with a wingspan of 107 feet, 3 inches (32.690 meters) and overall height of 20 feet, 9½ inches (6.337 meters). The wings had 4½° dihedral and 3½° angle of incidence. The empty weight was 29,900 pounds (13,562.4 kilograms) and loaded weight was 45,000 pounds (20,411.7 kilograms).
The airliner was powered by four air-cooled, geared and supercharged, 1,823.129-cubic-inch-displacement (29.875 liter) Wright Cyclone 9 GR-1820-G102 9-cylinder radial engines with a compression ratio of 6.7:1, rated at 900 horsepower at 2,200 r.p.m., and 1,100 horsepower at 2,200 r.p.m. for takeoff. These drove three-bladed Hamilton-Standard Hydromatic propellers through a 0.6875:1 gear reduction in order to match the engine’s effective power range with the propellers. The GR-1820-G102 was 4 feet, 0.12 inches (1.222 meters) long, 4 feet, 7.10 inches (1.400 meters) in diameter, and weighed 1,275 pounds (578 kilograms).
The maximum speed of the Model 307 was 241 miles per hour (388 kilometers per hour) at 6,000 feet (1,828.8 meters). Cruise speed was 215 miles per hour (346 kilometers per hour) at 10,000 feet (3,048 meters). The service ceiling was 23,300 feet (7,101.8 meters).
Julius Augustus Barr was born at Normal, Illinois, 6 December 1905. He was the son of Oren Augustus Barr, a teacher and school superintendent, and Margaret M. Wallace Barr. He grew up in Pittsburg, Kansas. He attended the Kansas State Teachers College at Pittsburg in 1925. He was a member of the Alpha Gamma Tau (ΑΓΤ) fraternity, of which he was the treasurer.
Barr enlisted in the Air Corps, United States Army, and was trained as a pilot at Brooks and Kelly Fields, San Antonio, Texas.
On 1 July 1928, Julius Barr married Miss Effie Hortense Roberson at Pittsburg, Kansas. They would have two children, Jo Anne Barr, and Gene Edward Barr.
In 1930, Barr and his family lived in Cheyenne, Wyoming. He flew as an air mail pilot, and was employed by Boeing Air Transport.
During the mid 1930s, the Barr family traveled to China, where he acted as manager of the airport at Hankow, and conducted flight training. He then flew as the personal pilot of Zhang Xueliang (also known as Chang Hseuh-Liang), (“The Young Marshal”). Zhang and another of other communist generals arrested Chiang Kai-Shek in the Xi’an Incident, December 1936. Chiang was released after two weeks, and Zhang placed under house arrest for the remainder of his life. (The others were executed.) Julius Barr then served as the personal pilot for Soong Mei-ling (“Madame Chiang”), and helped General Chang with the air defense of Shanghai during the Second Sino-Japanese War.
Barr and his family departed Hong Kong aboard S.S. Empress of Russia, which arrived at Victoria, British Columbia, Canada, 14 November 1938. He then went to work as a test pilot for Boeing two days later.
Julius Barr had flown a total of approximately 5,000 hours. Of these, 2,030 hours were in single-engine airplanes, 2,240 hours in twin-engine, and 765 hours in 3 engine.
Julius Augustus Barr was buried at the Mount Olive Cemetery, Pittsburg, Kansas.
5 March 1966: British Overseas Airways Corporation Speedbird 911, an around-the-world flight, departed Tokyo-Haneda Airport (HND) at 1:58 p.m., enroute Hong Kong-Kai Tak (HKG), with 113 passengers and 11 crew members. The airliner was a Boeing 707-436 Intercontinental, serial number 17706, with British registration G-APFE. It was nearly six years old, having been delivered 29 April 1960, and had 19,523 hours on the airframe.
Shortly before takeoff, the flight crew requested a change from an IFR flight plan to VFR, with a course that would take the airliner near Mount Fuji. The 707 climbed to an altitude of 16,000 feet (4,875 meters) as it approached the mountain from the southwest. The weather was very clear. A weather station on Fuji recorded wind speeds of 60–70 knots (111–130 kilometers per hour).
Flying upwind toward Fuji at 320–370 knots (592–685 kilometers per hour), Speedbird 911 encountered severe Clear Air Turbulence that resulted in a catastrophic structural failure of the airframe. The vertical fin attachment failed and as it fell away, struck the left horizontal stabilizer, breaking it off. Next, the ventral fin and all four engine pylons failed due to extreme side loads. The 707 went in to a flat spin, trailing fuel vapor from ruptured tanks. The entire tail section broke away, the right wing failed, and the nose section came off.
The 707 left a debris field that was 10 miles (16 kilometers) long. Speedbird 911 crashed in a forest on the lower flanks of Mount Fuji at about the 3,500 foot (1,066 meter) level. The forward section crashed about 1,000 feet (300 meters) away from the main wreckage. All 124 persons aboard were killed.
Probable Cause(s) The probable cause of the accident is that the aircraft suddenly encountered abnormally severe turbulence over Gotemba City which imposed a gust load considerably in excess of the design limit.
—ICAO Circular 82–AN/69 at Page 49
The accident was photographed by the Japanese Self Defense Forces from the East Fuji Maneuver Area, located in the foothills of the volcano. A passenger aboard Speedbird 911 had been filming with an 8 mm movie camera. The camera and film were recovered from the wreckage and the film was developed as part of the investigation. The film showed that the aircraft had experienced severe turbulence immediately before the accident. (Investigators estimated the peak acceleration at 7.5 g.)
A U.S. Navy Douglas A-4 Skyhawk was sent to look for the accident site. When the fighter approached Mount Fuji, it also encountered severe turbulence, to the point that the pilot feared the small fighter would break up in flight. After returning to base, the A-4 was grounded for inspection. Its accelerometer indicated that it had experienced acceleration forces ranging from +9 Gs to -4 Gs.
G-APFE was a Boeing 707-436 Intercontinental, built in 1960 for British Overseas Airways. At the time of the accident, it had made 6,744 flights and accumulated a total of 19,523:33 hours (TTAF).
The -436 was a stretched version of the original 707-120, but with Rolls-Royce Conway 508 bypass turbojet engines (now called turbofans) in place of the standard Pratt & Whitney JT3C-6 turbojet engines. 15 ordered by British Overseas Airways Corporation in 1956.
The fuselage and wings of the Intercontinental were lengthened, allowing an increased load and greater fuel capacity. It could carry 189 passengers and had a range 1,600 miles further than the -120. Transoceanic flights without an intermediate fuel stop were possible.
Initially, British aviation authorities refused to certify the -436 because of low-speed handling concerns. Boeing increased the height of the vertical fin 40 inches and added a ventral fin. These modifications became standard on all future 707s and were retro-fitted to those already manufactured.
The Boeing 707-420 series airliners were 152 feet, 11 inches (46.609 meters) long, with a wingspan of 142 feet, 5 inches (43.409 meters) and overall height 42 feet, 2 inches (12.852 meters) at its operating empty weight. The leading edges of the wings and tail surfaces are swept 35°. The fuselage has a maximum diameter of 12 feet, 8.0 inches (3.759 meters). The 707 International has a typical empty weight of 142,600 pounds (64,682 kilograms), and a maximum takeoff weight (MTOW) of 312,000 pounds (141,700 kilograms). The usable fuel capacity is 23,820 gallons (90,169 liters).
All 707-series aircraft are powered by four jet engines installed in nacelles below and forward of the wings on pylons. The -420 Internationals were powered by Rolls-Royce Conway Mk. 508 engines. The Rolls-Royce Conway (R.Co.12) is a two-spool, axial-flow, low-bypass turbofan engine. The engine has a 7-stage low- and 9-stage high-pressure compressor section, 12 interconnected combustion liners, with a single-stage high- and 2-stage low-pressure turbine. The Mk. 508 has a Maximum Continuous Power rating of 14,625 pounds of thrust (65.055 Kilonewtons), and 17,500 pounds of thrust (77.844 Kilonewtons) at 9,990 r.p.m., for Takeoff. The engine is 3 feet, 6.0 inches (1.067 meters) in diameter, 11 feet, 4.0 inches (3.454 meters) long, and weighs 4,542 pounds (2,060 kilograms).
The -420 series had a maximum cruise speed of 593 miles per hour 954 kilometers per hour) at 30,000 feet (9,144 meters)—0.87 Mach; and economical cruise speed of 550 miles per hour (885 kilometers per hour) at 35,000 feet (10668 meters).
Boeing built 1,010 Model 707 airplanes between 1957 and 1979. Of these, 37 were the 707-420 Intercontinental variant.
24 January 1963: A Boeing B-52C-40-BO Stratofortress, 53-0406, call sign “Frosh 10,” of the 99th Bombardment Wing, Heavy, was conducting a low-altitude training flight using terrain-following radar. Eight crewmen were aboard. Flying at or below 500 feet (152 meters) above ground level (AGL) and at 280 knots (322 miles per hour, 519 kilometers per hour) the bomber encountered wind gusts of up to 40 knots (21 meters per second).
As the turbulence became severe, the aircraft commander, Lieutenant Colonel Dante E. Bulli, began a climb to avoid it. At approximately 2:52 p.m., EST, however, the vertical fin attachment failed and the B-52 began rolling to the right and pitching down. Colonel Bulli, unable to control the airplane, ordered the crew to abandon the bomber.
B-52C 53-0406 crashed into the west side of Elephant Mountain, a 3,774 foot (1,150 meters) forest-covered mountain, 6 miles (10 kilometers) from Greenville, Maine. Only three men, Colonel Bulli, co-pilot Major Robert J. Morrison and navigator Captain Gerald J. Adler, were able to get out of the B-52, but Major Morrison died when he hit a tree. Lieutenant Colonel Joe R. Simpson, Jr., Major William W. Gabriel, Major Robert J. Hill, Jr., Captain Herbert L. Hansen, Captain Charles G. Leuchter and Technical Sergeant Michael F. O’Keefe were also killed.
Large sections of Frosh 10 are still on Elephant Mountain. The crash site is a popular hiking destination.
The Boeing B-52 Stratofortress had been designed as a very high altitude penetration bomber, but changes in Soviet defensive systems led to a change to very low altitude flight as a means of evading radar. This was subjecting the airframes to unexpected stresses. Several crashes resulted from structural failures during turbulence.
Less than one year later, Boeing was conducting flight tests of the B-52 in turbulence, using a highly-instrumented B-52H. That airplane also lost its vertical fin when it encountered severe turbulence in Colorado. The Boeing test pilots aboard were able to save the bomber and landed it six hours later.
Dante E. Bulli was born at Cherry, Illinois, 17 July 1922, the second child of Italian immigrants Giovanni Bulli, a salesman, and Anna Gareto Bulli. He attended Hall High School before working on the aircraft assembly lines of the Lockheed Aircraft Company in California.
Bulli enlisted as an aviation cadet in the U.S. Army Air Corps in 1942. He was commissioned as a second lieutenant, Army of the United States, 5 December 1943, and promoted to first lieutenant, 5 December 1946.
In 1947 Lieutenant Bulli married Miss Evelyn Lewis, also from Cherry, Illinois.
“Dan” Bulli was a combat veteran of World War II, the Korean War and the Vietnam War. He flew B-24 Liberators, the B-29 Superfortress and B-52 Stratofortress. He retired from the Air Force in 1974.
Colonel Dante E. Bulli died at Omaha, Nebraska, 30 December 2016, at the age of 94 years.