McDonnell Douglas DC-10 rollout at Long Beach, 23 July 1970. (Boeing)
23 July 1970: At Long Beach, California, the first McDonnell Douglas DC-10 airliner was rolled out. A DC-10-10, serial number 46500 with FAA registration N10DC, this aircraft was used for flight testing and Federal Aviation Administration certification. It made 989 test flights, accumulating 1,551 flight hours. It was put into commercial service with American Airlines 12 August 1972, re-registered as N101AA.
The DC-10 was a wide-body commercial airliner designed for medium to long range flights. It was flown by a crew of three and depending on the cabin arrangement, carried between 202 and 390 passengers. The DC-10-10 was 170 feet, 6 inches (51.968 meters) long with a wingspan of 155 feet, 4 inches (47.346 meters) and overall height of 58 feet, 1 inch (17.704 meters). The airliner had an empty weight of 240,171 pounds (108,940 kilograms) and maximum takeoff weight of 430,000 pounds (195,045 kilograms). It was powered by three General Electric CF6-6D turbofan engines, producing 40,000 pounds of thrust, each. These gave the DC-10 a maximum cruise speed of Mach 0.88 (610 miles per hour, 982 kilometers per hour). Its range is 3,800 miles (6,116 kilometers) and the service ceiling is 42,000 feet (12,802 meters).
In production from 1970 to 1988, a total of 386 DC-10s were built in passenger and freighter versions. 122 were the DC-10-10 variant. Another 60 KC-10A Extender air refueling tankers were built for the U.S. Air Force and 2 KDC-10 tankers for the Royal Netherlands Air Force.
The first McDonnell Douglas DC-10 was in service with American Airlines from 12 August 1972 to 15 November 1994 when it was withdrawn from service and placed in storage at Tulsa, Oklahoma. The 24-year-old airliner had accumulated 63,325 flight hours.
After three years in storage, the first DC-10 returned to service flying for Federal Express. In 1998 it was modernized as an MD-10 and re-registered again, this time as N530FE. It was finally retired from service and scrapped at Goodyear, Arizona in 2002.
Bell X-2 46-674 airdropped from Boeing EB-50D Superfortress 48-096 near Edwards Air Force Base, California. (U.S. Air Force)Brigadier General Frank Kendall Everest, United States Air Force
23 July 1956: Lieutenant Colonel Frank Kendall “Pete” Everest, United States Air Force, became “The Fastest Man Alive” when he flew the USAF/NACA/Bell X-2 rocket plane, serial number 46-674, to Mach 2.87 (1,957 miles per hour, 3,150 kilometers per hour) at 87,808 feet (26,764 meters). The X-2 was air-dropped from Boeing EB-50D Superfortress 48-096, near Edwards Air Force Base, California.
The X-2 was a joint project of the U.S. Air Force and NACA (the National Advisory Committee for Aeronautics, the predecessor of NASA). The rocketplane was designed and built by Bell Aircraft Corporation of Buffalo, New York, to explore supersonic flight at speeds beyond the capabilities of the earlier Bell X-1 and Douglas D-558-2 Skyrocket. In addition to the aerodynamic effects of speeds in the Mach 2.0–Mach 3.0 range, engineers knew that the high temperatures created by aerodynamic friction would be a problem, so the aircraft was built from Stainless Steel and K-Monel, a copper-nickel alloy.
The Bell Aircraft Corporation X-2 was 37 feet, 10 inches (11.532 meters) long with a wingspan of 32 feet, 3 inches (9.830 meters) and height of 11 feet, 10 inches (3.607 meters). Its empty weight was 12,375 pounds (5,613 kilograms) and loaded weight was 24,910 pounds (11,299 kilograms).
The X-2 was powered by a throttleable Curtiss-Wright XLR25-CW-1 rocket engine that produced 2,500–15,000 pounds of thrust (11.12–66.72 kilonewtons) burning alcohol and liquid oxygen. The engine used two rocket chambers and had pneumatic, electrical and mechanical controls. The smaller chamber could produce a maximum 5,000 pounds of thrust, and the larger, 10,000 pounds (22.24 and 44.48 likonewtons, respectively). Professor Robert H. Goddard, “The Father of Modern Rocketry,” authorized Curtiss-Wright to use his patents, and his rocketry team went to work for the Curtiss-Wright Rocket Department. Royalties for use of the patents were paid to the Guggenheim Foundation and Clark university. Professor Goddard died before he could also make the move
Rather than use its limited fuel capacity to take off and climb to altitude, the X-2 was dropped from a modified heavy bomber as had been the earlier rocketplanes. The launch altitude was 30,000 feet (9,144 meters). After the fuel was exhausted, the X-2 glided to a touchdown on Rogers Dry Lake at Edwards Air Force Base.
A four-engine Boeing B-50A Superfortress bomber, serial number 46-011, was modified as the ”mothership.” A second Superfortress, B-50D-95-BO 48-096, was also modified to carry the X-2, and was redesignated EB-50D. During the flight test program, the X-2 reached a maximum speed of Mach 3.196 (2,094 miles per hour, 3,370 kilometers per hour) and a maximum altitude of 126,200 feet (38,466 meters).
Frank Kendall Everest was a fighter pilot and flight instructor during World War II. He flew combat missions in both the Mediterranean and China-Burma-India Theaters of Operation. In May 1945 he was shot down. Everest was captured by the Japanese, held as a prisoner and tortured until the end of the war. After the war, Everest flew as a test pilot at Wright-Patterson Air Force Base, Ohio, and then at Edwards Air Force Base. On 23 July 1956, he was The Fastest Man Alive. Pete Everest retired as a brigadier general in 1970, and died in 2004.
Lieutenant Colonel Frank Kendall Everest, U.S. Air Force, wearing a David Clark Co. T-1 capstan-type partial-pressure suit for protection at high altitude, with a Bell X-2 rocketplane at Edwards AFB, circa 1956. (U.S. Air Force)
Major John H. Glenn, Jr., U.S. Marine Corps, in the cockpit of his North American Aviation F-86F Sabre, “MiG Mad Marine,” just after his second kill, 19 July 1953.
23 July 1953: Major John H. Glenn, Jr., United States Marine Corps, shot down his third and final MiG-15 fighter during the Korean War.
Major Glenn had previously flown a Grumman F9F Panther with VMF-311, but was assigned to the U.S. Air Force 25th Fighter Interceptor Squadron, 51st Fighter Interceptor Group, at K13, Suwon, Korea.
Major John H. Glenn, Jr., United States Marine Corps, standing with his North American Aviation F-86-30-NA Sabre, 52-4584, “MiG Mad Marine,” at Suwon, Korea, July 1953. (John Glenn Archives, The Ohio State University)
While on temporary duty with the Air Force squadron, Glenn flew the North American Aviation F-86F Sabre air superiority fighter. He shot down all three MiG fighters with F-86F-30-NA serial number 52-4584. His previous victories were on 12 July and 19 July, 1953, also against MiG-15 fighters.
Major Glenn had painted the names of his wife and two children, “Lyn Annie Dave,” on the nose of his airplane, but after being heard complaining that there “weren’t enough MiGs,” he came out one morning to find MIG MAD MARINE painted on the Sabre’s side.
John Glenn’s fighter, North American Aviation F-86F-30-NA Sabre, serial number 52-4584, at K13, Suwon, Korea, 1953. (U.S. Air Force)
“Flight.” Chris Kraft as Flight Director during the Mercury Program. (NASA)
From NASA:
Christopher C. Kraft, Jr., who died July 22, 2019, created the concept of NASA’s Mission Control and developed its organization, operational procedures and culture, then made it a critical element of the success of the nation’s human spaceflight programs.
“America has truly lost a national treasure today with the passing of one of NASA’s earliest pioneers – flight director Chris Kraft,” NASA Administrator Jim Bridenstine said in a statement. “We send our deepest condolences to the Kraft family.
“Chris was one of the core team members that helped our nation put humans in space and on the Moon, and his legacy is immeasurable. Chris’ engineering talents were put to work for our nation at the National Advisory Committee for Aeronautics, before NASA even existed, but it was his legendary work to establish mission control as we know it for the earliest crewed space flights that perhaps most strongly advanced our journey of discovery. From that home base, America’s achievements in space were heard across the globe, and our astronauts in space were anchored to home even as they accomplished unprecedented feats.”
Kraft — whose full name was Christopher Columbus Kraft — joined the NASA Space Task Group in November 1958 as NASA’s first flight director, with responsibilities that immersed him in mission procedures and challenging operational issues. He personally invented the mission planning and control processes required for crewed space missions, in areas as diverse as go/no-go decisions, space-to-ground communications, space tracking, real-time problem solving and crew recovery.
During the Apollo program, Kraft became the Director of Flight Operations at MSC, responsible for overall human spaceflight mission planning, training and execution. His leadership in this critical area continued through the Apollo 12 mission in 1969, at which time he became deputy director of the Center. He served as the center director from January 1972 until his retirement in August 1982, playing a vital role in the success of the final Apollo missions, the Skylab crewed space station, the Apollo-Soyuz Test Project and the first flights of the space shuttle.
Kraft was born Feb. 28, 1924 in Phoebus, Virginia, now a part of Hampton, Va. There he attended high school and developed strong interests in non-aeronautical topics such as baseball, and drum and bugle corps. Unlike many of his aerospace peers later in his career, he wasn’t interested in airplanes. After high school, he wanted to attend college, but didn’t know where or what he should study. He chose Virginia Polytechnic Institute (VPI, now Virginia Tech) and enrolled in mechanical engineering in 1941. He credits his experiences in the military Corps of Cadets at the institute for the foundation of his leadership training that would later characterize his personality in his NASA career.
By 1942, the VPI campus was being depleted of students because of the war effort, and Kraft patriotically decided to join the Navy as an aviation cadet. Unfortunately, his right hand had been severely burned when he was three years old, and he was declared unfit for military service. Ironically, his old hand injuries did not hamper his athletic prowess — he played catcher on the VPI baseball team. A professor in the engineering department was an enthusiastic airplane devotee and passed his interest on to young Kraft. An elective course in basic aerodynamics inspired him to major in aeronautical engineering. In 1944, he graduated with one of the first degrees in that field awarded by the Institute.
Kraft was familiar with the work of the federal National Advisory Commitee on Aeronautics — NASA’s predecessor agency — at Langley, which was located only about 7 miles from his home. However, he felt that Langley was too close to home, and accepted a job offer from Chance Vought in Connecticut — with a back-up offer from the NACA also in hand. After experiencing first-day bureaucratic frustration at Vought, he opted to accept his back-up offer. So, in January 1945, he returned to Virginia to join the staff of the Langley Memorial Aeronautical Laboratory. Kraft was assigned to the Flight Research Division under the leadership of Robert Gilruth and Hewitt Phillips, men he held in awe. He contributed to many critical programs that had been conceived by Gilruth, including evaluations of the flying qualities of aircraft, and free-fall model tests to measure transonic and supersonic aerodynamics. He served as project engineer on flying-qualities investigations of the P-51H, an advanced version of the famous Mustang. He also conducted analytical work on gust alleviation, and directed a pioneering study of potentially dangerous wake turbulence caused by trailing vortices.
With the advent of the jet age of the 1950s, he was assigned as project engineer on flight tests of the Navy’s high-priority Vought F8U Crusader, which was exhibiting numerous birthing problems in its earliest versions. The problems uncovered by Langley flight tests included unacceptable g-force control behavior during maneuvers, which was determined to result from unintentional pivoting of the unique movable wing used by the configuration. Working with Langley test pilot Jack Reeder, Kraft identified the structural source of the problem, and took on the unpleasant job of telling the Navy that its new first-line aircraft was potentially dangerous. His warnings were heeded by Navy management, resulting in grounding of the F8U fleet, much to the chagrin of many operators of the new aircraft. He then encountered one of the most contentious members of the Navy’s Bureau of Aeronautics, who questioned the Langley results and doubted the conclusions drawn by the NACA. That Marine Major was named John Glenn. Following a detailed examination of the Langley study results with Kraft and Reeder, and interviews with Navy pilots who flew the aircraft, Glenn was convinced and became a believer. The F8U was subsequently redesigned, as recommended by Kraft and his associates at Langley, and served the nation as an outstanding fighter during the Vietnam War.
Since his retirement from NASA, Kraft has consulted for numerous companies including IBM and Rockwell International, served as a Director-at-Large of the Houston Chamber of Commerce, and as a member of the Board of Visitors at Virginia Tech. In 2001, he published an autobiography entitled “Flight: My Life in Mission Control.” His book is a detailed discussion of his life through the end of the Apollo program, and was a New York Times bestseller.
He has received numerous awards and honors for his work. These include the NASA Outstanding Leadership Medal; four NASA Distinguished Service Medals; the Distinguished Alumnus Citation from Virginia Tech, in 1965; the Distinguished Citizen Award, given by the City of Hampton, Virginia, in 1966; the John J. Montgomery Award, in 1963; the Goddard Memorial Trophy, awarded by the National Space Club, in 1979; and the John F. Kennedy Astronautics Award for 1996. In 1999, he was presented the Rotary National Award for Space Achievement for which he was cited as “A driving force in the U.S. human space-flight program from its beginnings to the Space Shuttle era, a man whose accomplishments have become legendary.”
In 2006, NASA honored Christopher C. Kraft, Jr., for his key involvement in America’s space programs with the Ambassador of Exploration Award, given to astronauts and other key individuals who participated in the Mercury, Gemini, and Apollo space programs, for realizing America’s vision of space exploration from 1961 to 1972.
On April 4, 2011, NASA named its Building 30 Mission Control Center at the Johnson Space Center in his honor, in recognition of his service to the nation and its space programs. The Christopher C. Kraft, Jr., Mission Control Center has now operated for 50 years in support of space missions. At the naming ceremony, Flight Director Glynn Lunney commented “The Control Center today…is a reflection of Chris Kraft.”
Chris Kraft married his high school sweetheart, Betty Anne Turnbull, in 1950. They have a son and a daughter, Gordon and Kristi-Anne.
Last Updated: July 23, 2019
Editor: Brian Dunbar
TDiA recommends: FLIGHT: My Life in Mission Control, by Christopher C. Kraft and James L. Schefter, Dutton, New York, 2001.
Dick Smith’s Bell 206B-3 JetRanger III, VH-DIK, at Ball’s Pyramid, the world’s tallest sea stack, 12 miles southeast of Lord Howe Island in the South Pacific Ocean. (Dick Smith Collection)
22 July 1983: Richard Harold (“Dick”) Smith landed his Bell JetRanger III helicopter, VH-DIK, at the Bell Helicopter Hurst Heliport (0TE2), in Hurst, Texas, United States of America. He had completed the first solo around-the-world flight by helicopter.
Dick Smith, with his wife, “Pip,” being interviewed at Hurst, Texas. His Bell 206B-3 JetRanger III, VH-DIK, is in the background. (Bell Helicopter TEXTRON)
352 days earlier, 5 August 1982, Dick Smith had departed from Hurst on an eastbound circumnavigation. He had purchased the helicopter specifically to make this flight, and named it Australian Explorer. The aircraft, as standard production Bell Model 206B-3, serial number 3653, had been built at the Bell Helicopter TEXTRON plant in Hurst. It was registered VH-DIK by the Australia Department of Aviation, 2 June 1982.
The JetRanger was equipped with a Collins LRN 70 VLF/Omega navigation system, and a Collins autopilot. A larger fuel tank was installed.
Smith’s journey was made in three major segments:
Leg 1: Hurst, Texas, U.S.A., to London, England, from 5 August to 19 August 1982
Leg 2: London, England, to Sydney, New South Wales, Australia, 13 September to 3 October 1982
Leg 3: Sydney, N.S.W., Australia, to Hurst, TX, U.S.A., 25 May to 22 July 1983
The total distance flown was reported in FLIGHT as 32,258 miles (51,914 kilometers). The total flight time was over 260 hours.
Smith’s circumnavigation had also included the first solo flight by helicopter across the Atlantic Ocean. During the journey, he set five separate Fédération Aéronautique Internationale (FAI) world records for Speed Over a Recognized Course. ¹
Dick Smith’s Bell Model 206B JetRanger III, VH-DIK (c/n 3653), Australian Explorer. (Museum of Applied Arts & Sciences)
The Bell JetRanger is a 5-place, single-engine light civil helicopter developed from Bell Helicopter’s unsuccessful OH-4 entrant for the U.S. Army’s Light Observation Helicopter (LOH, or “loach”) contract. It is flown by a single pilot in the right front seat. Dual flight controls can be installed for a second pilot. The helicopter was certified for VFR flight, but could be modified for instrument flight.
The JetRanger is 38 feet, 9.5 inches (11.824 meters) long, overall. On standard skid landing gear the overall height is 9 feet, 4 inches (2.845 meters). The Bell 206A has an empty weight of approximately 1,700 pounds (771 kilograms), depending on installed equipment. The maximum gross weight is 3,200 pounds (1,451.5 kilograms). With an external load suspended from the cargo hook, the maximum gross weight is increased to 3,350 pounds (1,519.5 kilograms).
Three view drawing of the Bell Model 206A/B JetRanger with dimensions. (Bell Helicopter TEXTRON)
The two-bladed main rotor is semi-rigid and under-slung, a common feature of Bell’s main rotor design. It has a diameter of 33 feet, 4.0 inches (10.160 meters) and turns counter-clockwise (seen from above) at 394 r.p.m. (100% NR). (The advancing blade is on the helicopter’s right side.) The rotor blade has a chord of 1 foot, 1.0 inches (0.330 meter) and 10° negative twist. The airfoil is symmetrical. The cyclic and collective pitch controls are hydraulically-boosted.
The two-bladed tail rotor assembly is also semi-rigid and is positioned on the left side of the tail boom in a pusher configuration. It turns at 2,550 r.p.m., clockwise, as seen from the helicopter’s left. (The advancing blade is below the axis of rotation.) The tail rotor diameter is 5 feet, 6.0 inches (1.676 meters).
The turboshaft engine is mounted above the roof of the fuselage, to the rear of the main transmission. Output shafts lead forward to the transmission and aft to the tail rotor 90° gear box. The transmission and rotor mast are mounted tilting slightly forward and to the left. This assists in the helicopter’s lift off to a hover, helps to offset its translating tendency, and keeps the passenger cabin in a near-level attitude during cruise flight.
A vertical fin is attached at the aft end of the tail boom. The fin is offset 4° to the right to unload the tail rotor in cruise flight. Fixed horizontal stabilizers with an inverted asymmetric airfoil are attached to the tail boom. In cruise flight, these provide a downward force that keeps the passenger cabin in a near-level attitude.
The 206A was powered by an Allison 250-C18 turboshaft engine (T63-A-700) which produced a maximum of 317 shaft horsepower at 104% N1, 53,164 r.pm. The improved Model 206B JetRanger and 206B-2 JetRanger II used a 370 horsepower 250–C20 engine, and the Model 206B-3 JetRanger III had 250-C20B, -C20J or -C20R engines installed, rated at 420 shaft horsepower at 105% N1, (53,519 r.p.m.). Many 206As were upgraded to 206Bs and they are sometimes referred to as a “206A/B.” The Allison 250-C20B has a 7-stage compressor section with 6-stage axial-flow stages, and 1 centrifugal-flow stage. The 4-stage axial-flow turbine has a 2-stage gas producer (N1) and 2-stage power turbine (N2). These were very light weight engines, ranging from just 141 to 173 pounds (64.0 to 78.5 kilograms).
The helicopter’s main transmission is limited to a maximum input of 317 shaft horsepower (100% Torque, 5-minute limit). The engine’s accessory gear unit reduces the output shaft speed to 6,016 r.p.m. N2, which is further reduced by the transmission’s planetary gears, and the tail rotor 90° gear box.
The JetRanger has a maximum speed, VNE, of 150 miles per hour (241 kilometers per hour) up to 3,000 feet (914 meters). Its best rate of climb, VY, is at 60 miles per hour (97 kilometers per hour) and best speed in autorotation (minimum rate of descent and maximum distance) is at 80 miles per hour (129 kilometers per hour), resulting in a glide ratio of about 4:1. The service ceiling is 13,500 feet (4,145 meters) with the helicopter’s gross weight above 3,000 pounds (1,361 kilograms), and 20,000 feet (6,096 meters) when below 3,000 pounds. The helicopter has a maximum range of 430 miles (692 kilometers).
Richard Harold (“Dick”) Smith, AO, 1999. (Rob Tuckwell/National Portrait Gallery 2012.216)
¹ FAI Record File Numbers 2286, 2287, 2288, 10033 and 10272