Category Archives: Aviation

26 September 1949

XT-28 48-1471 landing at Edwards AFB 3 Feb 1950
The first of two North American Aviation  XT-28 prototypes, 48-1371, lands at Edwards Air Force Base 3 February 1950. (U.S. Air Force)

26 September 1949: At Vultee Field, a private industrial airport in Downey, California, North American Aviation test pilot Jean LeRoy (“Skip”) Ziegler ¹ took the first of two prototype military flight trainers, the XT-28 (NAA Model 159–2), U.S. Air Force serial number 49-1371, for its first flight. The 45-minute flight was two weeks ahead of schedule.

The Long Beach Press-Telegram reported:

New Training Plane Tested

     LOS ANGELES, Sept 27. (AP) The Air Force’s first postwar training plane—North American’s T-28—has tried her wings and found they work very well.

     The company announced that the twin cockpit craft—designed to train pilots for advanced high speed fighters and bombers—flew 45 minutes yesterday. Said test pilot Skip Ziegler, “It handles more like a fighter than a trainer.” He termed the flight, “completely satisfactory.”

     The T-28 has a ceiling of 29,800 feet and can move 288 miles an hour. The T-6, present Air Force trainer, ceilings at 22,000 and travels 205 m.p.h. top.

Long Beach Press Telegram, Vol. LXII, No. 240, Tuesday, 27 September 1949, Page A-5, Column 1

One of the two North American Aviation XSN2J-1 prototypes in flight of the Southern California shoreline, circa 1946. (North American Aviation, Inc./San Diego Air & Space Museum Archives, Catalog #: 00033269)

The XT-28 was developed from an earlier North American Aviation project for the United States Navy. In 1946, NAA proposed their Model 142, as a replacement for the World War II SNJ/T-6 Texan, a trainer which had also been built by North American, and used by  both the Navy and the U.S. Army Air Forces. The Navy designated the proposed airplane XSN2J-1. Two were built and assigned Bureau of Aeronautics serial numbers (“Bu. No.”) 121449 and 121450. 121449 was the first to fly, 15 February 1947.

The Navy tested both aircraft, but did not order them into production.

One of the two North American Aviation XSN2J-1 prototypes during testing at NATC Patuxent River, Maryland, October 1948. The prototype is armed with with five-inch air-to-surface rockets. (National Archives and Records Administration)

A year later, NAA made a similar proposal to the United States Air Force. The Air Force wanted a trainer to transition pilots into turbojet-powered aircraft. Similar to the XSN2J-1, the XBT-28 was changed to tricycle landing gear, a first for a miltiary trainer. The prototype’s two cockpits were laid out very similar to the new, swept-wing North American XP-86 Sabre. The Air Force ordered the airplane into production as the T-28A. The first T-28A arrived at Eglin Air Force Base, Florida, 15 June 1950, where it would tested for suitability as a flight trainer.

Prototype North American Aviation XBT-28. (T-28 Trojan Foundation)

The North American Aviation T-28 Trojan is an all-metal, two-place airplane with retractable tricycle landing gear. The dual cockpits are arranged in tandem. The T-28A was used by the United States Air Force as a primary training aircraft, while the more powerful T-28B and T-28C were employed by the U.S. Navy. The airplane was noted for its stability and handling qualities, its easy recovery from stalls and spins, and its excellent visibility.

Initially, the T-28 was built at North American Aviation’s Downey Division, in Downey, California, which at the time was primarily a farming community about 13 miles (21 kilometers) south of downtown Los Angeles, California. Production was shifted to North America’s Columbus Division in Columbus, Ohio.

North American Aviation T-28A Trojan internal arrangement. (U.S. Air Force)

The XT-28 and production T-28As were 32.0 feet (9.754) long with a wingspan of 40.6 feet (12.375 meters), and overall height of 12.7 feet (3.871 meters). The wing had an angle of incidence of 2° with 3° of negative twist, and 8° dihedral. The total wing area was 268.0 square feet (24.9 square meters). The vertical fin was offset 1° to the left of the airplane’s centerline. The prototype and early production T-28As had an empty weight of had an empty weight of 6,909 pounds (2,998 kilograms). This was increased in later aircraft to 7,282 pounds (3,303 kilograms). The Maximum Takeoff Weight (MTOW) was 7,751 pounds (3,516 kilograms).² The two prototypes had a belly-mounted speed brake. All T-28As had provisions for this installation.

North American Aviation XT-28 three-view illustration with dimensions. (U.S. Air Force)

The XT-28 and production T-28A were powered by an air-cooled, supercharged, 1,301.868 cubic inch (21.334 liter) Wright Aeronautical Division Cyclone 7 R-1300-1 (853C7BA1) 7-cylinder radial engine with a compression ratio of 6.2:1. This engine required 91/98 octane aviation gasoline. It was rated at 700 horsepower at 2,400 r.p.m., and 800 horsepower at 2,600. r.p.m. for takeoff. The engine also produced some jet thrust from its exhaust system. The engine thrust line was angled downward 5° from fuselage reference line. The R-1300-1 drove a two blade, 10 foot, 0 inch (3.048 meters) diameter Aeroproducts hydraulic variable pitch propeller through 0.5625:1 gear reduction. The engine was 4 feet, 1.12 inches (1.248 meters) long, 4 feet, 2.45 inches (1.281 meters) in diameter, and weighed 1,065 pounds, (483 kilograms).

The XT-28 had a maximum fuel capacity of 125 gallons (473 liters), carried in two wing tanks. Two additional tanks were added to later production T-28As, increasing the capacity to 177 gallons (670 liters).

The T-28A had a cruise speed of 165 knots (190 miles per hour/306 kilometers per hour, and maximum speed of 247 knots (284 miles per hour/457 kilometers per hour) at 5,800 feet (1,768 meters). VNE varied from 190 knots (219 miles per hour/352 kilometers per hour) at 25,000 feet (7,620 meters) with external load, to 340 knots (391 miles per hour/630 kilometers per hour) at Sea Level, clean. The airplane’s best power off glide speed was 105 knots (120 miles per hour/194 kilometers per hour).

The T-28A could climb at a maximum rate of 1,870 feet per minute (9.5 meters per second). Its service ceiling was 24,000 feet (7,315 meters). The maximum range was 720 nautical miles (829 statute miles/1333 kilometers) in early production models, or 880 nautical miles (1,013 statute miles/1,630 kilometers) in aircraft with increased fuel capacity.

For training purposes, the T-28A could be armed with one detachable gun pod under each wing. Each pod contained a .50-caliber AN-M3 Browning Aircraft Machine Gun. These had a rate of fire of approximately 1,100 rounds per minute. Each gun was supplied with 100 rounds of ammunition. The trainer could also be equipped with a removable bomb rack for a 100-pound (45 kilogram) bomb. Three 2.25 inch (5.7 centimeters) Sub-Caliber Aerial Rocket (SCAR)—Rocket, 2.25-Inch Practice—rockets could be carried on pylons mounted to hardpoints under each wing.

The first production North American T-28A Trojan, 49-1494 (North American serial number 159-1), at the National Museum of the United States Air Force. Delivered to Wright-Patterson AFB, this aircraft was used as a static test airframe. (U.S. Air Force 050322-F-1234P-020)

A total of 1,948 T-28s were built from 1950 to 1957. 1,194 of these were T-28As. The Air Force retired its T-28As by 1959. Many USAF T-28As were pulled from storage at Davis-Monthan Air Force Base, Tucson, Arizona, and were converted to the T-28D configuration for combat operations during the Vietnam War. Others were converted to the AT-28D attack variant, which included an ejection seat.

North American Aviation test pilot Robert A. (“Bob”) Hoover, with a U.S. Navy T-28B Trojan, circa 1953. (National Museum of Naval Aviation)

XT-28 48-1371 was sent to “The Boneyard” at Davis-Monthan Air Force Base near Tucson, Arizona, 23 January 1961, and to reclamation, 18 June 1965. In 1974, it was observed, disassembled, at the Hamilton Aviation Company yard in Tucson. (Hamilton produced modified T-28s: the military T-28R-1, and the civilian T-28R-2 Nomair.)

¹ For biographical information about Skip Ziegler, please see “This Day in Aviation” for 12 Nay 1953 at: https://www.thisdayinaviation.com/12-may-1953/

© 2025, Bryan R. Swopes

26 September 1927

Flight Lieutenant Sidney N. Webster, RAF, leads the Schneider Trophy Race with his Supermarine S.5 N220. (Unattributed)
Flight Lieutenant Sidney N. Webster, RAF, leads the Schneider Trophy Race with the blue and silver Supermarine S.5 racer, N220. (Unattributed)
Flight Lieutenant Sidney Norman Webster, Royal Air Force.
Flying Officer Sidney Norman Webster, Royal Air Force, circa 1919. (Unattributed)

26 September 1927: Flight Lieutenant Sidney Norman Webster, A.F.C., of the Royal Air Force High-Speed Flight, won the 1927 Schneider Trophy Race, flying a Supermarine S.5 float plane, number N220.

The course consisted of seven laps of a 50-kilometer course at Venice, Italy. Webster completed the race in 46 minutes, 20.3 seconds, averaging 281.656 miles per hour (453.281 kilometers per hour). He established a new Fédération Aéronautique Internationale (FAI) World Record for Speed Over 100 Kilometers.¹

Webster’s teammate, Flight Lieutenant Oswald Worsley, flying S.5 N219, placed second with a time of 47:46.7 and average speed of 272.91 miles per hour (439.21 kilometers per hour).

With its engine running, this Supermarine S.5 shows off its very clean lines.

The Supermarine S.5 was designed by Reginald Mitchell, who would later design the famous Supermarine Spitfire fighter. N220 was a single-place, single-engine, low-wing monoplane equipped with pontoons for landing and taking off on water. The airplane was of all metal construction, primarily duralumin (a hardened alloy of aluminum and copper). The airplane used surface radiators in the skin of the wings for engine cooling.

The S.5 had a length of 24 feet, 3½ inches (7.404 meters), wingspan of 26 feet, 9 inches (8.153 meters) and height of 11 feet, 1 inch (3.378 meters). The S.5’s empty weight was 2,680 pounds (1,216 kilograms) and gross weight was 3,242 pounds (1,471 kiograms).

Supermarine S.5 N220 at Venice, Italy, September 1927. (FlightGlobal)
Supermarine S.5 N220 at Venice, Italy, September 1927. (FlightGlobal)

Webster’s Supermarine S.5 was powered by a water-cooled, naturally-aspirated 1,461.135-cubic-inch-displacement (23.943 liter) D. Napier and Son, Ltd., Lion Mk.VIIB, serial number 63106, a double-overhead camshaft (DOHC) twelve-cylinder engine with three banks of four cylinders. This was called a “Triple-Four,” “W-12,” or “broad arrow” configuration. The Napier Lion had an included angle of 60° between each cylinder bank.

D. Napier and Son, Ltd., Lion VII “broad arrow” 12-cylinder aircraft engine.

The Mk.VIIB had four valves per cylinder and a compression ratio of 10:1. It produced 875 horsepower at 3,300 r.p.m. The Lion VIIB drove a two-bladed fixed-pitch propeller through a gear reduction unit with a ratio of 0.765:1. (Worsley’s Supermarine S.5, N219, was equipped with a 900 horsepower direct-drive Mk.VIIA.) The engine used a mixture of 75% gasoline, 25% benzol, and 0.22% “T.E.L. dope” (tetraethyl lead) additive. The Napier Lion Mk.VII was 5 feet, 6¼ inches (1.683 meters) long, 3 feet, 2½ inches (0.978 meters) wide and 2 feet, 10½ inches (0.876 meters) high. The geared Mk.VIIB was heavier than the direct drive Mk.VIIA, and weighed 920 pounds (417 kilograms).

The Supermarine S.5 had a maximum speed of 319.57 miles per hour (514.3 kilometers per hour).

“Webbie” Webster had been awarded the Air Force Cross on 2 January 1922. He received a second award, signified by a “bar” added the the ribbon of his medal, 11 October 1927:

Air Ministry.

11th October, 1927.

     The KING has been graciously pleased to approve the award of a Bar to the Air Force Cross held by Flight Lieutenant Sidney Norman Webster, A.F.C., in recognition of his achievement winning the recent “Schneider Cup” Air Race.

Flight Lieutenant Sidney N. Webster, RAF, stands with his winning Supermarine S.5, N220, at the Woolston factory. Designer Reginald Mitchel is in the front row at center.
Flight Lieutenant Sidney N. Webster, RAF, stands with his winning Supermarine S.5, N220, at the Woolston factory. Designer Reginald Mitchell is in the front row at center.

In January 1946, Air Commodore Webster was appointed Commander of the Most Excellent Order of the British Empire. He was promoted to Air Vice Marshal in 1949 and retired from the Royal Air Force 12 August 1950.

Air Vice Marshal Sidney Norman Webster, C.B.E., A.F.C. and Bar, Royal Air Force, died 5 April 1984 at the age of 83 years.

Schneider trophy at the Science Museum, London. (Wikipedia)
Coupe d’Aviation Maritime Jacques Schneider (the Schneider Cup) at the Science Museum, London. (Wikipedia)

¹ FAI Record File Number 11070

© 2018, Bryan R. Swopes

26 September 1911

Lieutenant Thomas Dewitt Milling at the controls of a Wright Model B, 1911. (Library of Congress)
Lieutenant Thomas DeWitt Milling at the controls of a Wright Model B, 1911. (Library of Congress)

At  the Aero Club of America Meet on 26 September 1911, at the Nassau Boulevard Aerodrome on Long Island, New York, Lieutenant Thomas DeWitt Milling set a world endurance record of 1 hour, 54 minutes, 42.6 seconds with two passengers, for which he was awarded the Rodman Wanamaker Endurance Trophy.

Burgess-Wright biplane taking off at the Harvard-Boston Aero Meet, August-September 1911. (Anthony Philpott/Wright State University Libraries, Special Collections and Archives, Item Identifier Number ms338_02_02)

The Daily Local News reported:

     Lieut. Milling was the hero of the day when he alighted with his Burgess Wright biplane and passengers, Paul Revere and William Ecke, both of Company L, Twenty-ninth Infantry. The three men had been in the air 1 hour 54 minutes 4 2 seconds, which beats by 16 minutes 2 seconds the world’s duration record with two passengers established by M. Mamet at Rheims, France.

     George W. Beatty was the only other aviator who started in the weight carrying duration contest. His crank case broke after he had been in the air 29 minutes an 18 seconds and he had to descend.

ARMY OFFICER GETS $1,000 PRIZE

     The weight of the two privates with Lieut. Milling was 252½ pounds. They circled around the pylons in a high wind between 4 and 6 p.m. Lieut. Milling won the $1,000 prize and the applause of 8,200 spectators. The army aviator won the tri-State aeroplane race and $7,500 several week sago in Boston. It was only two months ago that he learned to fly an aeroplane.

Daily Local News, West Chester, Pennsylvania, Vol. XXXIX, No, 267, Wednesday, 27 September 1911, Page 1, Column 1

A Burgess-Wright biplane flying at the Harvard-Boston Aero Meet, August 26–September 4, 1911. (Anthony Philpott/Wright State University Libraries, Special Collections and Archives, Item Identifier Number ms338_08_07)

The trophy is on display at the National Museum of the United States Air Force.

The Rodman Wanamaker Endurance Trophy on display in the Early Years Gallery of the National Museum of the United States Air Force. (U.S. Air Force)
The Rodman Wanamaker Endurance Trophy on display in the Early Years Gallery of the National Museum of the United States Air Force. (U.S. Air Force)

© 2024, Bryan R. Swopes

25 September 1978, 16:02:07 UTC

PSA Flight 182, on fire after mid-air collision, 25 September 1978. (Hans Wendt, County of San Diego)

25 September 1978: At 09:02:07 a.m., local time, the worst aircraft accident in California history occurred when a Boeing 727-214 airliner, civil registration N533PS, operated by Pacific Southwest Airlines (PSA) as Flight 182, crashed at the intersection of Dwight Street and Nile Street in the North Park neighborhood of San Diego, 4,830 meters (3.00 miles) northwest of Lindbergh Field (SAN), today known as San Diego International Airport.

Flight 182 was a regularly scheduled commercial airline flight from Sacramento, California to San Diego, with a stopover at Los Angeles. Captain James E. McFeron, a 17-year veteran of PSA, was in command. First Officer Robert E. Fox was the pilot flying the 727 on this leg. The Flight Engineer (also called the Second Officer) was Martin J. Wahne. Also in the cockpit, occupying the two “jump seats” were two off-duty PSA captains. Four flight attendants were on duty in the passenger cabin along with 126 passengers, which included 30 PSA employees.

In clear weather and early morning sunlight, the airliner was on an visual approach to Lindbergh. The 727 passed over the Mission Bay VORTAC (MZB), a navigation aid 3.4 miles (5.5 kilometers) northwest of the airport, and turned left to a heading of 090° to intercept the downwind leg of the approach.

Detail of current aeronautical chart of airspace around San Diego International Airport (Lindbergh Field.)
Detail of current aeronautical chart of airspace around San Diego International Airport (Lindbergh Field), center near bottom of image. Montgomery field is at the upper right.

Ahead of the 727, a single-engine light airplane, a Cessna 172, N7711G, with an instructor and student aboard, had made two practice ILS approaches to Runway 9 at Lindbergh and departed to the northwest, returning to its base at Montgomery Field (MYF), 6.4 miles (10.3 kilometers) north-northeast of SAN.

Approach Control called, Cessna 7711G, radar contact, maintain VFR at or below 3500 [1,067 meters], fly heading 070, vector (for) final approach course.” The pilot of the Cessna, David T. Boswell, acknowledged the east-north-easterly heading and the altitude restriction. About 15 seconds later, at 08:59:39, the controller informed the 727, “Additional traffic’s twelve o’clock, three miles, just north of the field, northeastbound, a Cessna One Seventy-Two climbing VFR out of one thousand four hundred.” [427 meters] At 08:59:50, First Officer Fox reported, Okay, we’ve got that other twelve.”

Radar tracks show that N7711G initially maintained the assigned heading but after about one minute, turned 20° right to 090°, the same heading as that of Flight 182.

At 09:00:23, Approach Control acknowledged Flight 182: “Okay, sir, maintain visual separation, contact Lindbergh Tower 133.3. Have a nice day, now!”

Flight 182 switched radio frequencies and Captain McFeron checked in with the tower: “Lindbergh, PSA 182. Downwind.” The Tower Controller responded, “PSA 182, Lindbergh Tower, traffic 12 o’clock, one mile, a Cessna.”

In the cockpit there was confusion about the reported conflicting traffic ahead. Captain McFeron asked, “Is that the one we’re looking at?” Flight Engineer Wahne replied, “Yeah—but I don’t see him now.” McFeron called the Tower, “Okay, we had it there a minute ago.” The Controller replied, “One Eighty-Two, roger.” The Captain continued, “I think he’s passed off to our right.”

Inside the cockpit, McFeron said, “He was right over there a minute ago.” Wahne agreed, “Yeah.”

Lindbergh Tower authorized Flight 182 to land, “PSA 182—cleared to land,” and McFeron acknowledged with, “PSA 182’s cleared to land.” He then asked the Flight Engineer, “Are we clear of that Cessna?” Wahne said, “Supposed to be!” McFeron responded, “I guess.” In the cockpit’s jump seat, one of the two off-duty captains said, “I hope!”

At 09:01:21, Captain McFeron stated, “Oh, yeah, before we turned downwind, I saw him about one o’clock, probably behind us now.”

First Officer Fox called for the wing flaps to be lowered and then at 09:01:31 he asked for the landing gear to be lowered. At 09:01:38, Fox said, There’s one underneath [pause] I was looking at that inbound there.” Flight 182 was now descending through 2,600 feet (793 meters).

At 09:01:47, the Flight 182’s Cockpit Voice Recorder picked up the sound of the collision.

The Boeing 727 struck the Cessna 172 from above and behind, with the impact occurring on the forward underside of the 727’s right wing, approximately 12.5 feet (3.8 meters) outboard of the wing root. The airliner was heavily damaged and on fire, having lost both the number 5 and 6 leading edge flaps. The number 3 leading edge slat and number 4 inboard leading edge flap were damaged. Chordwise damage penetrated to the forward wing spar. The airplane’s System A hydraulic lines and pressurized fuel lines were routed along the wing’s leading edge, in front of the forward wing spar. The NTSB estimated that only partial hydraulic pressure would have been available. With the flight controls damaged, Flight 182 rolled and turned to the right. On a heading of approximately 200°, it crashed into residential neighborhood in a 300 mile per hour (483 kilometers per hour), 50° dive.

According to seismographs at the Museum of Natural History, San Diego, the impact occurred at 09:02:07 a.m., Pacific Daylight Savings Time (16:02:07 UTC).

The Cessna 172 was also heavily damaged and on fire. The largest piece of the Cessna impacted six blocks away from the scene of the 727 crash, near 32nd Street and Park Avenue.

PSA Flight 182, a Boeing 727-214, registration N533PS, shortly before impact, 0902 a.m., 25 September 1978.
PSA Flight 182, a Boeing 727-214, registration N533PS, shortly before impact, 0902 a.m., 25 September 1978. (Hans Wendt, County of San Diego)

All 135 persons aboard the 727, both persons on the Cessna, and seven persons on the ground were killed. Another nine persons on the ground were injured. Twenty-two homes in a four-block area were destroyed or damaged.

The last words of the flight deck personnel recorded by the Cockpit Voice Recorder were that of an unidentified voice saying, “Ma, I love you.”

Scene of the crash of Flight 182, 25 September 1978. (San Diego Union-Tribune)
Scene of the crash of Flight 182, 25 September 1978. (San Diego Union-Tribune)

The Pilot in Command of Flight 182, Captain James E. McFeron, had been employed by Pacific Southwest Airlines since 1961. He held an Airline Transport Pilot Certificate and was type-rated in both the Lockheed L-188 Electra and the Boeing 727. He had a total of 14,382 flight hours, with 10,482 hours in the Boeing 727.

First Officer Robert E. Fox, Jr., also held an ATP certificate. Of his 10,049 flight hours, 5,800 were in the 727. He had been with PSA for 9 years.

Flight Engineer Martin J. Wahne had worked for PSA for 11 years. He had 10,800 hours, with 6,587 hours in the Boeing 727.

The Pilot in Command of the Cessna was Gunnery Sergeant David Lee Boswell, U.S. Marine Corps, who was stationed at Camp Pendleton, north of San Diego. Gunnery Sergeant Boswell held Commercial Pilot and Flight Instructor certificates, with Airplane—Single– and Multi–Engine Land ratings. He was receiving instrument flight instruction to apply for an Instrument Rating. Boswell had 407 total flight hours, and had flown 61 hours in the previous 90 days.

The Instructor Pilot on board the Cessna was Martin B. Kazy, Jr., an employee of the aircraft owner, Gibbs Flight Center at Montgomery Field. He held Commercial Pilot and Flight Instructor certificates, with Airplane Single– and Multi–Engine Land, and Instrument–Airplane ratings. He had a total of 5,137 flight hours. Kazy had flown 347 hours in the previous 90 days.

Pacific Southwest Airlines' Boeing 727-214, N533PS, photographed at San Francisco International Airport, September 1975. (Edge to Edge Photography)
Pacific Southwest Airlines’ Boeing 727-214, N533PS, photographed at San Francisco International Airport, September 1974. (Edge to Edge Photography)

The aircraft operated as PSA Flight 182 was a Boeing 727–214, serial number 19688, which made its first flight 4 June 1968. At the time of the accident, the total time on the airframe (TTAF) was 24,088.3 hours. It had made 36,557 takeoffs and landings.

The Boeing 727–200 series was a stretched version of the original –100 model. It was designed to be operated by a flight crew of three, and could carry up to 189 passengers. The –200 was 153 feet, 2 inches (46.685 meters) long with a wingspan of 108 feet, 0 inches (32.918 meters) and overall height of 34 feet, 0 inches (10.363 meters). The empty weight was 98,400 pounds (44,633 kilograms) and maximum takeoff weight (MTOW) was 184,800 pounds (83,642 kilograms). The airliner was powered by three Pratt & Whitney JT8D-9 low-bypass axial-flow turbofan engines, rated at 14,500 pounds of thrust at Sea Level for takeoff (5-minute limit), and 12,600 pounds of thrust, maximum continuous power. This gave the 727–200 a maximum cruise speed of 0.9 Mach (610 miles per hour, or 982 kilometers per hour, at 30,000 feet/9,144 meters). Its service ceiling was 42,000 feet (12,802 meters), and the maximum range was 1,956 miles (3,148 kilometers).

1,832 727s were built by Boeing between 1963 and 1984. 1,245 of these were 727-200s.

This 1976 Cessna 172M is similar in appearance to Gibbs Flight Center's N7711G. (Skytamer)
This 1976 Cessna 172M is similar in appearance to Gibbs Flight Center’s N7711G. (Skytamer)

Cessna 172 N7711G was a 1975 Cessna 172M, serial number 17265788. It had 2,993 total flight hours on the airframe (TTAF). It was a single-engine, four-place light airplane with a high wing and fixed tricycle landing gear. 711G was painted white with “mustard” yellow trim. The 172M is 26 feet, 11 inches (8.201 meters) long with a wingspan of 36 feet, 0 inch (10.973 meters) and height of 8 feet, 9½ inches (2.680 meters). The empty weight is 1,350 pounds (612 kilograms) and gross weight is 2,300 pounds (1,043 kilograms). It is powered by an air-cooled, normally-aspirated 319.749-cubic-inch-displacement (5.240 liter) Lycoming O-320-E2D horizontally-opposed 4-cylinder direct-drive engine rated at 150 horsepower at 2,700 r.p.m. The engine drives a two-bladed McCauley fixed-pitch propeller with a diameter of 6 feet, 3 inches (1.905 meters). The engine installed on N7711G engine had 3,086 total hours since new (TSN) and 879 hours since overhaul (TSO). The 172M has a cruise speed of 138 miles per hour (222 kilometers per hour) at 8,000 feet (2,438 meters), and a maximum speed of 142 miles per hour (229 kilometers per hour) at Sea Level. The airplane’s service ceiling is 13,100 feet (3,993 meters) and its maximum range is 875 miles (1,408 kilometers).

More than 43,000 Cessna 172s have been built, more than any other airplane type.

© 2016, Bryan R. Swopes

25 September 1960

Commander John F. Davis, United States Navy, with a McDonnell F4H-1 Phantom II. Note the F6F-5K drone “kill” mark under the windshield. (U.S. Navy)
Commander John F. Davis, United States Navy, with a McDonnell F4H-1 Phantom II. Note the F6F-5K drone “kill” mark under the windshield. (U.S. Navy)

25 September 1960: At Edwards Air Force Base, California, Commander John Franklin (“Jeff”) Davis, United States Navy, flew a McDonnell F4H-1 Phantom II to a Fédération Aéronautique Internationale (FAI) World Record for Speed Over a Closed Circuit of 100 Kilometers Without Payload, averaging 2,237.37 kilometers per hour (1390.24 miles per hour).¹ Commander Davis flew the 62-mile circular course at an altitude of 45,000 feet (13,716 meters).

Diagram of the 100-kilometer closed circuit. (McDonnell)
Diagram of the 100-kilometer closed circuit. (McDonnell Aircraft Corporation)

“On 25 September 1960 Davis flew the shorter, 100-kilometer course at 1,390.24 miles per hour, roughly Mach 2.2. He went around the course in a continuous circle, at 70° of bank and three g’s. The heavy bank put the honeycomb structure of the right stabilator directly in the engine exhaust the entire way around, but it held on. These two flights demonstrated the brute strength of the airframe and the sophistication of the F4H navigation system around the curves.”

Engineering the F-4 Phantom II: parts into systems, by Glenn E. Bugos, Naval Institute Press, Annapolis, Maryland, 1996, Chapter 5 at Page 104.

For this flight, Commander Davis was awarded the Distinguished Flying Cross by Secretary of the Navy William Birrell Franke, 4 October 1960.

McDonnell F4H-1 Phantom II, Bu. No. 145311. This probably the Phantom flown by Jeff Davis for the 100-kilometer record. (U.S. Navy)
McDonnell F4H-1F Phantom II, Bu. No. 145311 (after 1962, redesignated as F-4A-2-MC). This is probably the Phantom flown by Jeff Davis for the 100-kilometer record. This airplane was damaged when the nose gear collapsed during an emergency landing at MCAS Cherry Point, 9 April 1964. (U.S. Navy)

John Franklin Davis was born at Chicago, Illinois, 4May 1921. He was the son of John E. Davis and Bernice B. McNair Davis.

On 11 July 1940, John Franklin Davis was admitted to the United States Naval Academy, Annapolis, Maryland, as a Midshipman. He graduated and was commissioned an Ensign, United States Navy, 9 June 1943. Ensign Davis served aboard the battleship USS New York (BB-34). He was promoted to Lieutenant (junior grade), 1 September 1944. He was promoted to Lieutenant, 1 April 1946.

Also in 1946, Lieutenant Davis qualified as a Naval Aviator. He was assigned as a pilot VF-74 aboard USS Midway (CVB-41). During the early 1950s, Lieutenant Davis served as operations officer for VF-191 aboard USS Oriskany (CVA-34). The squadron was equipped with the swept-wing Grumman F9F-6 Cougar. He then commanded VF-191, flying the Chance Vought F8U Crusader. Commander Davis was then assigned to the Bureau of Weapons as project officer for the McDonnell F4H Phantom II.

Following that assignment, Commander Davis was selected as executive officer of the Midway-class aircraft carrier, USS Coral Sea (CVA-43).

Captain John Franklin Davis, United States Navy.

United States Navy aircraft carriers are traditionally commanded by Naval Aviators, but they usually are required to have experience commanding a “deep-draft” ship. Early in his career, Captain Davis had served aboard the 27,000-ton USS New York. He was given command of the Haskell-class attack transport USS Talladega (APA-208) from 10 April 1965 through 1966. From 30 September 1968 to 15 November 1969, Captain Davis commanded the supercarrier USS Kitty Hawk (CV-63) during combat operations in Southeast Asia.

USS Kitty Hawk (CVA-63) (U.S. Navy)

Captain Davis was married to the former Miss Bonnie Adair of Bay St. Louis, Mississippi. They had six children.

Captain John Franklin Davis, United States Navy (Retired), died at Marrero, Louisiana, 16 May 1993. His ashes were spread at sea from his last command, USS Kitty Hawk.

¹ FAI Record File Number 8898

© 2017, Bryan R. Swopes