27 January 1967: During a “plugs out” test of the Apollo 1 Command Module, two weeks ahead of the scheduled launch of the Apollo/Saturn 1B AS-204—the first manned Apollo Program space flight—a fire broke out in the pressurized pure oxygen environment of the capsule and rapidly involved the entire interior.
The pressure rapidly built to 29 pounds per square inch (200 kPa) and 17 seconds later, at 23:31:19.4 UTC, the capsule ruptured.
The three astronauts, Lieutenant Colonel Virgil I. Grissom, United States Air Force, Lieutenant Colonel Edward H. White II, United States Air Force, and Lieutenant Commander Roger B. Chaffee, United States Navy, were killed.
AD ASTRA PER ASPERA
NASA has a detailed summary of the accident and investigation at:
23 January 1971: NASA Astronaut Eugene Andrew (“Gene”) Cernan, backup commander for Apollo 14, was flying NASA 947, a 1967 Bell Model 47G-3B-1 helicopter, (N947NA, serial number 6665), on a proficiency flight. He intended to practice vertical approaches as a warmup for a lunar landing.
With full fuel tanks, NASA 947 was heavy. Cernan decided to burn off some fuel by flying along the Indian River before the vertical approaches:
“That gave me a reason to loaf around the sky for a while and invest the extra fuel in some fun flying.
“Small boats dotted the clear water below and bright islands mounded here and there on the river. Hardly a ripple disturbed the mirrorlike surface. After so many months of hard work and concentration, I couldn’t resist the temptation for a bit of mischief known among pilots as ‘flat-hatting.’ So I nosed over and swooped down from a couple of hundred feet to dance the chopper around island beaches and among the boaters, steadily getting closer to the surface. . .
“Without realizing the danger, I flew into a trap that was the plague of seaplane pilots. Without ripples, the water provided no depth perception and my eyes looked straight through the clear surface to the reflective river bottom. I had lost sight of the water. But I was in control, or at least I thought so. . . until the toe of my left skid dug into the Indian River.
“. . . I twisted the collective with my left hand and applied more power, pulling back on the controls, trying to get the machine to climb out of trouble. A plume of water erupted beneath the skid, then the canopy struck and a rushing tidal wave filled my vision as the helicopter lost any semblance of aerodynamic design. In a single flashing instant, it went from a speed of 100 knots to flat zero with a lurch as severe as any I had ever felt landing on an aircraft carrier or staging in a spacecraft. I crashed with a spectacular explosion.”
—The Last Man on the Moon, by Eugene Cernan and Don Davis, St. Martin’s Press, New York, 1999, at Page 258
The Bell 47 was torn apart by the impact. The cabin section, with Cernan still strapped inside, sank to the bottom of the river. As a Naval Aviator, he was trained in under water egress. He freed himself from the wreck and made his way to the surface. Gasoline from the ruptured fuel tanks was floating on the water and had caught fire. Cernan suffered some minor burns, but was otherwise unhurt. He was rescued by fishermen who were nearby.
The location of the crash was in the Indian River near Malabar, Florida.
An accident investigation board, led by Astronaut James A. Lovell, commander of Apollo 13, concluded that the accident was pilot error, in that Cernan had misjudged his altitude when flying over the water.
A week after the flight crew for Apollo 17 was announced, in a meeting with Dr. Robert R. (“Bob”) Bob Gilruth, Director of the Manned Spacecraft Center, and Christopher C. Kraft, Jr., Deputy Director of MSC and Director of Flight Operations, Colonel James Alton McDivitt, U.S. Air Force, NASA’s Manager of the Apollo Spacecraft Program (and who had commanded Gemini 4 and Apollo 9), insisted that Gene Cernan be grounded for poor judgement and not assigned as commander of Apollo 17.
Chris Kraft wrote:
“Why didn’t you ask me about this crew?” he [McDivitt] demanded. “Cernan’s not worthy of this assignment, he doesn’t deserve it, he’s not a very good pilot, he’s liable to screw everything up, and I don’t want him to fly.
I was shocked at how strongly Jim was reacting. “Why didn’t you ask me” he pleaded. “Why didn’t you ask me?” Then he shocked me further. “If you don’t get rid of him, I’ll quit.”
. . . I called McDivitt and told him that Cernan was staying. . .
“Thank you,” he said. “You’ll have my resignation shortly.”
— Flight: My Life in Mission Control, by Christopher C. Kraft and James L. Schefter, Dutton, New York, 2001, Chapter 23, at Pages 346 and 347
Gene Cernan, along with Ronald E. Evans and Harrison H. Schmitt, lifted off from the Kennedy Space Center aboard Apollo 17, 7 December 1972. On 11 December, he and Schmitt landed at the Taurus-Littrow Valley at the southeastern edge of Mare Serenitatis.
On 14 December 1972, Eugene Andrew Cernan was the last human to stand on the surface of The Moon.
The Bell Model 47, designed by Arthur M. Young of the Bell Aircraft Corporation, Buffalo, New York, was the first helicopter to receive civil certification from the Civil Aviation Administration, predecessor of the Federal Aviation Administration. On 8 March 1946, the aircraft received C.A.A. Type Certificate H-1.
The Bell 47G was the first helicopter manufactured by the Bell Aircraft Corporation at the company’s new plant at Fort Worth, Texas. It was also produced under license by Agusta, Kawasaki and Westland.
The Bell Model 47G-3B-1 was issued Type Certificate 2H-3 on 25 January 1963. It is a 3-place, single-engine light helicopter, operated by a single pilot. The helicopter has dual flight controls and can be flown from either the left or right. The airframe is constructed of a welded tubular steel framework with a sheet metal cockpit. The landing gear consists of two lateral, horizontal tubular cross tubes, and two longitudinal “skids,” curved upward at the front. Ground handling wheels can be attached to the skids. The most distinctive feature of the Bell 47 is the large plexiglass “bubble” canopy. The main rotor flight controls use a system of bell cranks and push-pull tubes. The cyclic and collective are hydraulically boosted. The tail rotor is controlled by pedals and stainless steel cables.
With rotors turning, the Bell 47G-3B-1 has an overall length of 43 feet, 5.55 inches (13.247 meters). From the forward tip of the skids to the aft end of the tail rotor guard, the fuselage is 32 feet, 7.40 inches long (9.942 meters). The main rotor has a diameter of 37 feet, 0.50 inches (11.290 meters). The tail rotor diameter is 5 feet, 10.1 inches (1.781 meters). Height to top of main rotor mast is 9 feet, 3.7 inches (2.837 meters).
The Bell 47G-3B-1 has an empty weight of approximately 1,820 pounds (826 kilograms), depending on installed equipment. Its maximum gross weight is 2,950 pounds (1,338 kilograms).
The main rotor, in common to all American-designed helicopters, rotates counter-clockwise as seen from above. (The advancing blade is on the helicopter’s right.) The anti-torque (tail) rotor is mounted to the right side of an angled tail boom extension, in a tractor configuration, and rotates counter-clockwise as seen from the helicopter’s left. (The advancing blade is above the axis of rotation.)
The main rotor is a two-bladed, under-slung, semi-rigid assembly that would be a characteristic of helicopters built by Bell for decades. The main rotor system incorporates a stabilizer bar, positioned below and at right angles to the main rotor blades. Teardrop-shaped weights are placed at each end of the bar, on 100-inch (2.540 meters) centers. The outside diameter of the stabilizer bar is 8 feet, 6.8 inches (2.611 meters). The pilot’s inputs to the cyclic stick are damped through a series of mechanical linkages and hydraulic dampers before arriving at the pitch horns on the rotor hub. The result is smoother, more stable flight, especially while at a hover. The stabilizer bar action is commonly explained as being “gyroscopic,” but this is incorrect. (A similar system is used on the larger Bell 204/205/212 helicopters.)
The Bell 47G-3B-1 used tip-weighted high-inertia metal main rotor blades. The airfoil is symmetrical, using the NACA 0015 profile. The operating range of the main rotor is 322–370 r.p.m.
The 47G-3B-1 used an AVCO Lycoming TVO-435-B1A, -B1B, -D1A, or -D1B engine. The TVO-435 is an air-cooled, turbosupercharged 433.976-cubic-inch-displacement (7.112 liter) vertically-opposed, six-cylinder overhead-valve engine with a compression ratio of 7.30:1. It is equipped with a Garrett AiResearch T-1108 turbosupercharger, which provides a constant manifold pressure with decreasing pressure altitude. The engine idles at 1,500 r.p.m. Its normal operating range is 3,000 to 3,200 r.p.m. (3,100–3,200 r.p.m., above 10,000 feet, or 3,048 meters). The TVO-435-B1 has a maximum continuous power rating of 220 horsepower at 3,200 r.p.m., with a manifold pressure of 27.5 inches Hg (0.931 Bar); and a maximum 270 horsepower at 3,200 r.p.m. at 32.8 inches Hg (1.111 Bar) (-B1) or 32.0 inches (1.084 Bar) (-D1) at Sea Level, for takeoff (5-minute limit).
The TVO-435 is 34.73 Inches (0.882 meters) high, 33.58 inches (0.878 meters) wide and 24.13 inches (0.613 meters) deep, and weighs 464.00 pounds (178.26 kilograms) to 481.00 pounds (182.89 kilograms), depending of the specific engine variant.
Engine torque is sent through a centrifugal clutch to a gear-reduction transmission, which drives the main rotor through a two-stage planetary gear system. The transmission also drives the tail rotor drive shaft, and through a vee-belt/pulley system, a large fan on the forward face of the engine to provide cooling air.
The Bell 47G-3B1 has a maximum cruise speed of 80 miles per hour (129 kilometers per hour) from 1,000 to 4,500 feet (305–1,372 meters). This decreases to 70 miles per hour up to 10,000 feet (3,048 meters), and 50–60 miles per hour (80–97 kilometers per hour) up to 15,000 feet (4,572 meters). The helicopter’s maximum speed (VNE) is 105 miles per hour (169 kilometers per hour) from Sea Level to 4,500 feet (1,372 meters). Above that altitude, VNE is reduced 7 miles per hour (11.3 kilometers per hour) for every 1,000 foot (305 meters) increase in altitude. Above 15,000 feet, the VNE continues to decrease at 5 miles per hour (8 kilometers per hour) per 1,000 feet (305 meters).
The Bell 47G-3B-1 demonstrated the ability to over in ground effect (HIGE) at a gross weight of 2,850 pounds (1,293 kilograms) at the summit of Pike’s Peak, 14,115 feet (4,302 meters), in the Rocky Mountains of Colorado. The Density Altitude was approximately 15,000 feet (4,572 meters). At the same gross weight, it hovered out of ground effect (HOGE) at 9,000 feet (2,743 meters), Density Altitude. The helicopter has a maximum altitude limitation of 20,000 feet (6,096 meters).
Fuel is carried in two gravity-feed tanks, mounted above and on each side of the engine. The total fuel capacity is 61.6 gallons (233.2 liters), however, usable fuel is 57 gallons (216 liters). The helicopter has a maximum range of 273 miles (441 kilometers).
In production from 1946 until 1974, more than 7,000 Model 47 helicopters were built, worldwide. Production of the Model 47G-3B-1 began in March 1962 and a total of 337 of were built. The initial sales price was $46,950 (equivalent to $346,740 in 2018 dollars). NASA bought two -G-3B-1s in 1967. Another 415 were built for military customers, designated TH-13T.
In 2010, the type certificates for all Bell 47 models were transferred to Scott’s Helicopter Service, Le Sueur, Minnesota, which continues to manufacture parts and complete helicopters.
22 January 1968: At 22:48:00.86 UTC (5:48:08 a.m., Eastern Standard Time) a Saturn IB rocket lifted off from Launch Complex 37B at the Cape Kennedy Air Force Station, Cape Kennedy, Florida, carrying LM-1, an unmanned Apollo Program lunar lander, into a low-Earth orbit.
AS-204 reached Mach 1 at T + 0:59.8, passing 24,574 feet (7,490.16 meters). First stage separation occurred at T + 02:23.6, at an altitude of 194,228 feet (59,201 meters), with the vehicle accelerating through 7,563 feet per second (2,305 meters per second).
The AS-204 S-IVB engine cut off occurred at T + 09:53 at 536,166 feet (163,423 meters) with the vehicle travelling 25,659 feet per second (7,820 meters per second). Orbital insertion occurred at T + 00:10:03 at an altitude of 88 nautical miles (163 kilometers) with a velocity of 25,684 feet per second (7,828 meters per second). The orbit was elliptical with an apogee of 120 nautical miles (222 kilometers) and perigee of 88 nautical miles (163 kilometers). The orbital period was 88.39 minutes.
The Lunar Module separated from the S-IVB stage at T + 00:53:55.24. It was the allowed to cold-soak for about 3 hours. At T + 03:59.46, the LM’s descent engine was fired but aborted by the guidance computer after 4.0 seconds. A little over 3 hours later, at T + 06:10:42, the descent engine was fired a second time, and burned until T + 06:13:14.7.
The ascent engine fired at 06:12:14.7 while the descent and ascent stages were still joined. The engine burned 60.0 seconds. It was fired a second time at T + 07:44:13.
With the tests completed, the orbits of the separated LM stages were allowed to decay. LM-1 quickly re-entered Earth’s atmosphere and was destroyed.
The purpose of the Apollo 5 mission was to test the Grumman-built Lunar Module in actual spaceflight conditions. Engines for both the descent and ascent stages had to be started in space, and be capable of restarts. Although the mission had some difficulties as a result of programming errors, it was successful and a second test flight with LM-2 determined to be unnecessary and was cancelled.
SA-204 ¹ had originally been the scheduled launch vehicle for the Apollo 1 manned orbital flight.
When a fire in the command module killed astronauts Virgil I. (“Gus”) Grissom, Edward H. White and Roger B. Chaffee, 27 January 1967, the rocket was undamaged. It was moved from Launch Complex 39 and reassembled at LC 37B for use as the launch vehicle for Apollo 5.
The Saturn IB was a two-stage, liquid-fueled, heavy launch vehicle. It consisted of a S-IB first stage and S-IVB second stage. The total height of AS-204 was 181 feet, 0.355 inches (55.17782 meters). The Saturn IB rocket stood 141 feet, 8.644 inches (43.19636 meters), without payload. It had a maximum diameter of 22.8 feet (6.949 meters), and the span across the first stage guide fins was 40.7 feet (12.405 meters). Its empty weight was 159,000 pounds (72,122 kilograms) and at liftoff, it weighed 1,296,000 pounds (587,856 kilograms). It was capable of launching a 46,000 pound (20,865 kilogram) payload to Earth orbit.
The S-IB first stage was built by the Chrysler Corporation Space Division at the Michoud Assembly Facility near New Orleans, Louisiana. The first stage was 80 feet, 4.089 inches (24.4878606 meters) long, with a maximum diameter of 21 feet, 8.0 inches (6.604 meters) (21 feet, 5.0 inches across the Redstone tanks). The stage was powered by eight Rocketdyne H-1 engines, burning RP-1 and liquid oxygen. Eight Redstone rocket fuel tanks, with four containing the RP-1 fuel, and four filled with liquid oxygen, surrounded a Jupiter rocket fuel tank containing liquid oxygen. Total thrust of the S-IB stage was 1,666,460 pounds (7,417.783 kilonewtons) and it carried sufficient propellant for a maximum 4 minutes, 22.57 seconds of burn. The first stage of AS-204 was S-IB-4.
The McDonnell Douglas Astronautics Company S-IVB stage was built at Huntington Beach, California. The stage was 61 feet, 4.555 inches (18.708497 meters) long, with a maximum diameter of 21 feet, 8.0 inches (6.604 meters). It was powered by a single Rocketdyne J-2 engine, fueled by liquid hydrogen and liquid oxygen. The J-2 produced 229,714 pounds of thrust (1,021.819 kilonewtons), at high thrust, and 198,047 pounds (880.957 kilonewtons) at low thrust). The second stage carried enough fuel for 7 minutes, 49.50 seconds burn at high thrust.
The Lunar Module was a two-stage vehicle designed to transport two astronauts from Lunar Orbit to the surface of the Moon, provide shelter and a base of operations while on the Moon, and then return the astronauts to lunar orbit, rendezvousing with the Apollo Command and Service Module. It was designed and built by the Grumman Aerospace Corporation at Bethpage, Long Island, New York.
The Descent Stage incorporated extendable landing gear, a hypergolic-fueled rocket engine to brake from orbital speed, establish a landing trajectory, and then decelerate for landing. The TRW Space Technology Laboratories Lunar Module Descent Engine (LMDE) produced a maximum of 10,500 pounds of thrust (46.706 kilonewtons), and could be throttled from 10–100% thrust. The stage also carried support equipment, oxygen, water, etc., needed by the astronauts, and equipment for use during surface activities.
To return to Lunar Orbit, the Descent Stage was left behind, and the Bell Aerosystems Lunar Module Ascent Engine (LMAE) was fired. This engine also used hypergolic fuel and produced 3,500 pounds of thrust (15.569 kilonewtons).
¹ The Apollo Program Saturn rockets were designated as both AS-xxx and SA-xxx. The AS-xxx designation was applied to the complete vehicle, or “full stack,” while the SA-xxx designation applied to only the multi-stage rocket assembly.
20 January 1930: Colonel Edwin E. Aldrin, Jr., Sc.D., United States Air Force (Retired), was born at Glen Ridge, New Jersey, the second child of Edwin Eugene Aldrin, Aviation Director of Standard Oil Company of New Jersey, and Marion Gaddys Moon Aldrin.
The family resided in Montclair, New Jersey. “Buzz” Aldrin attended Montclair High School, and participated in football and track and field (pole vault). He graduated in 1947.
After high school, Aldrin turned down a full scholarship to attend the Massachusetts Institute of Technology (M.I.T.) and instead entered the United States Military Academy at West Point, New York. During his Plebe Year (freshman), Cadet Aldrin placed first in academics and physical education. He was a member of the French Club and the track and swim teams. In his third year he was a cadet corporal, and was designated as “distinguished.” He served as a cadet lieutenant during his final year.
Aldrin graduated from West Point on 5 June 1951 with a Bachelor of Science Degree in Mechanical Engineering (B.S.M.E.). He was ranked third in his class. A notation in the class yearbook states,
“As is evidenced by his fine record at the Academy, Buzz should make a capable, dependable and efficient officer in the U.S. Air Force.”
—The Howitzer 1951, at Page 98
Aldrin accepted a commission as a second lieutenant in the United States Air Force, with his date of rank retroactive to 1 June 1951. Second Lieutenant Aldrin was assigned to basic flight training at Bartow Air Force Base, Florida. Advanced training took place at Bryan Air Force Base, Texas. He trained as a fighter pilot and transitioned to the North American Aviation F-86 Sabre at Nellis Air Force Base, near Las Vegas, Nevada.
Lieutenant Aldrin flew the North American Aviation F-86E Sabre with the 16th Fighter Interceptor Squadron, 51st Fighter Interceptor Wing, located at Suwon Air Base (K-13), Korea. On 14 May 1953 he shot down an enemy Mikoyan-Gurevich MiG 15 fighter, for which he was awarded the Distinguished Flying Cross.¹ Three weeks later, 7 June, he shot down a second MiG 15.
Buzz Aldrin flew 66 combat missions during the Korean War. After returning to the United States, he served as a flight instructor at Bryan AFB, Texas, and then a gunnery instructor at Nellis AFB, Nevada.
1st Lieutenant Edwin E. Aldrin, Jr., married Miss Joan Ann Archer at the Episcopal Church in Ho-ho-kus, New Jersey, 29 December 1954. They would have three children.
Lieutenant Aldrin’s next assignment was to the three-month Squadron Officer School at Maxwell Air Force Base, Montgomery, Alabama. Aldrin then served as an aide to Brigadier General Don Zabriskie Zimmerman, the Dean of Faculty at the newly-established United States Air Force Academy, which was then located at Lowry Air Force Base, Denver, Colorado.
In 1955, Captain Aldrin was assigned to the 22nd Fighter Day Squadron, 36th Fighter Day Wing, at Bitberg Air Base, Germany, flying the North American Aviation F-100 Super Sabre. The squadron trained at Wheelus Air Base in North Africa.
In 1959 Captain Aldrin returned to the United States to enter a masters degree program in aeronautics at the Massachusetts Institute of Technology, Cambridge, Massachusetts. Aldrin and his wife were both very seriously ill at this time, and he was a patient in a military hospital for the first six months. With nothing to do but study, Aldrin finished first among the other Air Force officers in the program.
Aldrin remained at M.I.T. to earn a Doctorate in Science in Astronautics (Sc.D.) by devising orbital navigation techniques. His thesis on Manned Orbital Rendezvous, earned Buzz another nickname: “Dr. Rendezvous.”
In October 1963, Major Aldrin was selected as an astronaut for the Gemini Program. He was one of 14 members of NASA Astronaut Group 3, which was announced 18 October 1963. He flew with James A. Lovell, Jr., aboard Gemini XII, 11–15 November 1966. They made 59 orbits of the Earth in 3 days, 22 hours, 34 minutes, 31 seconds. Aldrin performed the first successful “space walk.” He was outside the spacecraft for three “EVAs,” of 2 hours, 29 minutes; 2 hours, 6 minutes; and 55 minutes. A rendezvous and docking with an Agena target vehicle was also successful.
Gemini XII was the final manned flight of the Gemini Program. Buzz Aldrin moved on to the Apollo Program.
Along with Neil Alden Armstrong, Buzz Aldrin landed on the Moon, 20 July 1969.
Aldrin resigned from NASA in July 1971. Returning to operational service with the Air Force, Colonel Aldrin was assigned as Commandant of the U.S. Air Force Test Pilot School at Edwards Air Force Base, California. He retired in March 1972.
In Return To Earth, (Random House, Inc., New York, 1973) Buzz Aldrin wrote about the depression he suffered: After you’ve been to the Moon, what else is there?
Aldrin has been married three times. He and his first wife, Joan, divorced in December 1974. He married Mrs. Beverly I. Handelsman Van Zile, 19 December 1975. They divorced 10 April 1978. On Valentine’s Day, 14 February 1988, Aldrin married his third wife, Mrs. Lois Driggs Cannon. They divorced 28 December 2012.
Buzz Aldrin has written several books and he continues to advocate manned space exploration.
HAPPY 89th BIRTHDAY, Colonel Aldrin!
¹ Soviet records indicate that a MiG 15 of 913 IAP (Istrebitel’nyy Aviatsionnyy Polk, Fighter Aviation Regiment), 32nd IAD (Istrebitel’naya Aviatsionnyy Diveeziya, Fighter Aviation Division), based at Antung Air Base, China, was shot down by an F-86 on 13 May 1953. The pilot, Senior Lieutenant Hristoforov, ejected safely. There were three MiG 15 losses that occurred on 14 May 1953. Two MiGs of 224 IAP collided and both pilots, Senior Lieutenant Odintsov and Lieutenant Evgeny Stroliikov, ejected. Odintsov was seriously hurt. A third MiG 15 crash landed at Myagoy Air Base. Its pilot, Senior Lieutenant Vladimir Sedashev, 518 IAP, was killed.
John L. “Jack” Swigert, Jr., was born at Denver, Colorado, 30 August 1931, the first of three children of John Leonard Swigert, a physician, and Virginia Seep Swigert. Interested in aviation from an early age, he was a licensed Private Pilot at age 16. He graduated from Denver’s East High School in 1949.
Jack Swigert attended the University of Colorado in Boulder, Colorado. He was a member of the Air Force Reserve Officers Training Corps (AFROTC), played on the varsity football team, and was a member of the C Club. He graduated in 1953 with a Bachelor’s Degree in Mechanical Engineering. Following his graduation, Swigert was commissioned as a second lieutenant, United States Air Force Reserve.
Lieutenant Swigert flew fighters from bases in Japan and Korea, then after completing his active duty requirement, 2 October 1956, he transferred to the Air National Guard. He served with the Massachusetts ANG and Connecticut ANG.
Swigert earned a Master of Science degree in Aerospace Engineering from Rensselaer Polytechnic Institute, Troy, New York, in 1965, as well as a Master of Business Administration degree from the University of Hartford at Hartford, Connecticut.
While flying with the Air Guard, Swigert also worked for North American Aviation, Inc., as an engineering test pilot, and then for Pratt & Whitney.
He became one of 19 men selected as crewmembers of NASA’s Apollo Program 1965. He requested an assignment as pilot of the Apollo Command and Service Module.
Swigert was a member of the support team for the Apollo 7 mission, and was then selected for the Command Module Pilot for the Apollo 13 backup crew, along with John Watts Young and Charles M. Duke, Jr. When the primary crew CMP, Ken Mattingly, was thought to have been exposed to measles, he was withdrawn from Apollo 13 and Jack Swigert took his place.
Apollo 13 was planned as the third lunar landing mission. The circumstances of its flight are well known. When disaster struck, all three astronauts performed an amazing feat as they had to improvise their safe return to Earth.
Swigert left NASA in 1977 and entered politics. He was elected to the U.S. House of Representatives in 1982, representing the the 6th District of Colorado.
On the night of 27 December 1982, before he could be sworn into office, John Leonard Swigert, Jr., aerospace engineer, fighter pilot, test pilot, astronaut and congressman, died from complications of cancer.