15 August 1951

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William Barton Bridgeman (TIME Magazine)
William Barton Bridgeman (Boris Artzybasheff/TIME Magazine)

15 August 1951: Just 8 days after he set an unofficial world speed record of Mach 1.88 (1,245 miles per hour; 2,033.63 kilometers per hour), Douglas Aircraft Company test pilot William Barton (“Bill”) Bridgeman flew the rocket-powered United States Navy/National Advisory Committee on Aeronautics (NACA) Douglas D-558-II Skyrocket, Bu. No. 37974, to a world record altitude at Edwards Air Force Base in the high desert of Southern California.

The Skyrocket was airdropped at 34,000 feet (10,363 meters) from a highly-modified U.S. Navy P2B-1S Superfortress, Bu. No. 84029. The mother ship was a U.S. Air Force Boeing B-29-95-BW Superfortress, 45-21787, transferred to the Navy and flown by another Douglas test pilot, George R. Jansen.

Douglas D-558-II Skyrocket, Bu. No., 37974, NACA 144, is dropped from the Boeing P2B-1S Superfortress, Bu. No. 84029, NACA 137. (NASA)
Douglas D-558-II Skyrocket, Bu. No., 37974, NACA 144, is dropped from the Boeing P2B-1S Superfortress, Bu. No. 84029, NACA 137. (NASA)

The flight plan was for Bridgeman to fire the rocket engine and allow the Skyrocket to accelerate to 0.85 Mach while climbing. The Skyrocket was powered by a Reaction Motors LR8-RM-6 engine, which produced 6,000 pounds of thrust. As the rocketplane continued to accelerate to Mach 1.12, the test pilot was to pull up, increasing the angle of climb while holding an acceleration rate of 1.2 Gs. This would result in a constantly increasing angle of climb. When it reached 50°, Bridgeman was to maintain that, climbing and accelerating, until the rocket engine ran out of fuel.

Initially, the plan was to continue climbing after engine shutdown until the D-558-II was approaching stall at the highest altitude it could reach while on a ballistic trajectory. There were differing expert opinions as to how it would behave in the ever thinner atmosphere. On the morning of the flight, Douglas’ Chief Engineer, Ed Heinemann, ordered that Bridgeman push over immediately when the engine stopped.

Bill Bridgeman stuck to the engineers’ flight plan. As the Skyrocket accelerated through 63,000 feet (19,200 meters), it started to roll to the left. He countered with aileron input, but control was diminishing in the thin air. The next time it began there was no response to the ailerons. Bridgeman found that he had to lower the Skyrocket’s nose until it responded, then he was able to increase the pitch angle again. At 70,000 feet (21,336 meters), travelling Mach 1.4, he decided he had to decrease the pitch angle or lose control. Finally at 76,000 feet (23,165 meters), the engine stopped. Following Heinemann’s order, Bridgeman pushed the nose down and the D-558-II went over the top of its arc at just 0.5 G.

Bill Bridgeman. (Unattributed)
Bill Bridgeman. (Unattributed)

“In the arc she picks up a couple of thousand feet. The altimeter stops its steady reeling and swings sickly around 80,000 feet. The altitude is too extreme for the instrument to function.

“Eighty thousand feet. It is intensely bright outside; the contrast of the dark shadows in the cockpit is extreme and strange. It is so dark lower in the cockpit that I cannot read the instruments sunk low on the panel. The dials on top, in the light, are vividly apparent. There seems to be no reflection. It is all black or white, apparent or non-apparent. No half-tones. It is a pure, immaculate world here.

“She levels off silently. I roll right and there it is. Out of the tiny windows slits there is the earth, wiped clean of civilization, a vast relief map with papier-mâché mountains and mirrored lakes and seas. . . .

“It is as if I am the only living thing connected to this totally strange, uninhabited planet 15 miles below me. The plane that carries me and I are one and alone.”

—The Lonely Sky, William Bridgeman with Jacqueline Hazard, Castle and Company LTD, London, 1956, Chapter XXII at Page 268.

After the data was analyzed, it was determined that William Bridgeman and the Douglas Skyrocket had climbed to 79,494 feet (24,230 meters), higher than any man had gone before. This was the last flight that would be made with a Douglas test pilot. The rocketplane was turned over to NACA, which would assign it the number NACA 144.

A Douglas D-558-II Skyrocket, Bu. No. 37974. glides back toward Rogers Dry Lake at Edwards Air force Base. A North American Aviation F-86E-1-NA Sabre, 50-606, flies chase. Major Charles E. "Chuck" Yeager frequently flew as a chase pilot for both Bill Bridgeman and Scott Crossfield. (NASA)
A Douglas D-558-II Skyrocket, Bu. No. 37974, glides back toward Rogers Dry Lake at Edwards Air Force Base. A North American Aviation F-86E-1-NA Sabre, 50-606, flies chase. Lieutenant Colonel Frank K. “Pete” Everest and Major Charles E. “Chuck” Yeager frequently flew as chase pilots for both Bill Bridgeman and Scott Crossfield. (NASA)

Bill Bridgeman had been a Naval Aviator during World War II, flying the Consolidated PBY Catalina and PB4Y (B-24) Liberator long range bombers with Bombing Squadron 109 (VB-109), “The Reluctant Raiders.” Bridgeman stayed in the Navy for two years after the war, then he flew for Trans-Pacific Air Lines in the Hawaiian Islands and Pacific Southwest Airlines in San Francisco, before joining Douglas Aircraft Co. as a production test pilot, testing new AD Skyraiders as they came off the assembly line at El Segundo, California. He soon was asked to take over test flying the D-558-2 Skyrocket test program at Muroc Air Force Base.

The D-558-II Skyrocket was Phase II of a planned three phase experimental flight program. It was designed to investigate flight in the transonic and supersonic range. It was 46 feet, 9 inches (14.249 meters) long with a 25 foot (7.62 meter) wing span. The wings were swept back to a 35° angle. The Skyrocket was powered by a Westinghouse J34-WE-40 11-stage axial-flow turbojet engine, producing 3,000 pounds of thrust, and a Reaction Motors LR8-RM-6 four-chamber rocket engine, which produced 6,000 pounds of thrust. The rocket engine burned alcohol and liquid oxygen.

There were three D-558-2 Skyrockets. Between 4 February 1948 and 28 August 1956, they made a total of 313 flights. Bill Bridgeman’s speed and altitude record-setting Skyrocket, Bu. No. 37974, NACA 144, is in the collection of the Smithsonian Institution National Air and Space Museum.

Douglas D-558-2 Skyrocket, Bu. No. 37974, NACA 144. (NASA)

© 2016, Bryan R. Swopes

15 August 1939

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Junkers Ju 87 B-1 Sturzkampfflugzeug (“Stuka”) photographed before World War II. Note the extended dive brake under the wing. (Unattributed)

15 August 1939: As Nazi Germany prepared for a war now just weeks away, the Luftwaffe gave a demonstration of its Junkers Ju 87 B-1 Stuka dive bombers for a group of generals at a test range near Neuhammer-am-Queis, Silesia:

. . . scores of generals were assembled at the training area at Neuhammer to watch a dive-bombing demonstration. Already, said Rudolf Braun, who took part with his unit (I St. G 3) there was a feeling of war in the air.

Hauptmann Rudolf Braun, Knight’s Cross of the Iron Cross

Normally the order of attack was the Kommandeur’s Stab Kette (Staff Flight) first, followed by Staffels 1, 2, and 3. For some unknown reason Staffel I, led by Oberleutnant Peltz, was this time ordered to attack last. It would save Rudolf Braun’s life.

The Met. reported cloud from 6,000 feet down to 2,500 with clear visibility below. At 6.00 a.m. Hauptmann Sigel led his Gruppe into attack at 12,000 feet. Half-rolling his Ju. 87 he plunged nearly vertically earthwards, with Oberleutnants Eppen and Mueller on each side.

On the ground below, the generals (including Wolfram von Richthofen, the Stuka’s chief) listened to the whining crescendo of the dive-bombers as they plummeted towards the ground. Horrified, they knew that nothing could avert disaster. The Met. report was wrong. Cloud base was at three hundred feet.

Hauptmann Sigel, yelling into his microphone, “Pull out!” managed to do so himself a few feet above the trees. But Eppen went in, Mueller went in, and both burst into flames. The nine Ju. 87s of Staffel 2 and two of Staffel 3 all went in.

Rudolf Braun and his comrades of Staffel I had heard Sigel’s warning and remained circling above the cloud layer through which columns of black smoke were now rising from the wreckage of thirteen dive bombers. I St. G 3 lost twenty-six young aircrew that day.

— Duel of Eagles, Group Captain Peter Wooldridge Townsend, C.V.O., D.S.O., D.F.C. and Bar, Royal Air Force. Castle Books, Edison, New Jersey, 2003, Chapter 14 at Pages 171–172.

Two Junkers Ju 87 Stuka dive bombers.

The Junkers Flugzeug-und-Motorenwerke AG Ju 87 B-1 Sturzkampfflugzeug (“diving combat aircraft”) was a two-place, single-engine, low-wing monoplane with fixed landing gear, designed as a dive bomber. The airplane, commonly known as the “Stuka,” has a blocky, unstreamlined appearance. Its most identifiable feature is its sharply-tapered, inverted “gull wing.” ¹

The Ju 87 made its first flight 17 September 1935. Among the tests pilots who flew it during pre-production testing were Hanna Reitsch and aeronautical engineer Gräfin Melitta Schenk von Stauffenberg.

The Stuka was used in the murderous attack on Wieluń, Poland, 1 September 1939, just 18 days after the accident at Neuhammer-am-Queis. This was the very first combat action of World War II. In just over one hour, 75% of the town was destroyed and more than 1,200 people were killed. The death rate was twice that of the infamous attack on the Spanish town of Guernica by the Nazi Condor Legion during the Spanish Civil War.

The Ju 87 B-1 was the first variant to be produced in large numbers and was in service at the beginning of World War II. The airplane is 11.000 meters (36.089 feet) long with a wingspan of 13.800 meters (45.276 feet) and height of 3.770 meters (12.369 feet). The total wing area is 31.9 square meters (343.4 square feet). The B-1 variant had an empty weight of 2,745 kilograms (6,052 pounds), and gross weight of 4,235 kilograms (9,337 pounds).

Two-view illustration of the Junkers Ju 87 B-1, with dimensions in millimeters. (Junkers Ju 87 B-1 Betriebsanleitung, at Page 0 05)

The Ju 87 B-1 was powered by a liquid-cooled, supercharged 34.989 liter (2,135.190 cubic-inch-displacement) Junkers Jumo 211 A inverted 60° V-12 engine. The 211 A had direct fuel-injected and the cylinder heads were machined for four spark plugs per cylinder. The compression ratio was 6.57:1, requiring 88-octane gasoline. It was rated at a maximum 900 Pferdestärke at 2,200 r.p.m. at 5,500 meters (18,045 feet). The engine turned a three-blade Junkers-Verstelluftschraube propeller with a diameter of 3.4 meters (11.2 feet) through a 1.55:1 gear reduction. The Jumo 211 A weighed 660 kilograms (1,455 pounds).

The Stuka B-1 had a maximum dive speed of 600 kilometers per hour (373 miles per hour). The Ju 87 B-1 had a service ceiling of 8,000 meters (26,247 feet), and range of 550 kilometers (342 miles).

The B-1 was armed with two fixed 7.92 mm Rheinmetall-Borsig MG17 machine guns with 1,000 rounds of ammunition per gun, and one MG 15 machine gun on a flexible mount with 900 rounds of ammunition. It could carry a single 500 kilogram (1,102 pound) bomb under the fuselage.

Junkers Ju 87 V-4 prototype, D-UBIP, WNr 4924, circa 1936.

An interesting feature the the Stuka was its automatic pull-out system. Once the bomb had been dropped, the airplane automatically began a 5–6 g recovery. This could save the airplane if the pilot became target-fixated, or blacked out.

The Ju 87 was equipped with a Zeiss gyro-stabilized bomb sight. According to an article in Air Force Times, the Stuka was a very accurate dive bomber. “. . . even the worst drops typically landed within 100 feet [30.5 meters] of the target. Good hits were either on target or no more than 15 feet [4.6 meters]off-center.”

In the same article, the legendary Royal Navy test pilot, Captain Eric Melrose Brown, C.B.E., D.S.C., A.F.C., K.C.V.S.A., Ph.D., Hon. F.R.Ae.S., R.N., is quoted:

“A dive angle of 90 degrees is a pretty palpitating experience, for it always feels as if the aircraft is over the vertical and is bunting, and all this while terra firma is rushing closer with apparent suicidal rapidity. In fact I have rarely seen a specialist dive bomber put over 70 degrees in a dive, but the Ju 87 was a genuine 90-degree screamer. . . the Ju 87 felt right standing on its nose, and the acceleration to 335 mph [539 km/h] was reached in about 4,500 feet [1,372 meters], speed thereafter creeping up to the absolute permitted limit of 375 mph [604 km/h], so that the feeling of being on a runaway roller coaster experienced with most dive bombers was missing. I must confess that I had a more enjoyable hour’s dive-bombing practice than I had ever experienced with any other aircraft of this specialist type. Somehow the Ju 87D did not appear to find its natural element until it was diving steeply. Obviously the fixed undercarriage and large-span dive brakes of the Junkers were a highly effective drag combination.”

Only two Stukas still exist, one, a Ju 87 G-2, at the RAF Museum at Hendon, and the other, a Ju 87 R-2, is at the Museum of Science and Industry, Chicago, Illinois.

¹ TDiA has not found any source that provides the details of the Ju 87’s most characteristic feature: the angles of anhedral and dihedral of its wings. TDiA estimates that the wings’ inner section has -12° anhedral, while the outer wing panels have approximately 8° dihedral.

© 2018, Bryan R. Swopes

15 August 1935

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Will Rogers and Wiley Post with the Lockheed Model 9E Orion hybrid at Renton, Washington. The pontoons have just been installed on the airplane in place of its fixed landing gear. (Unattributed)
Will Rogers and Wiley Post with the Lockheed Model 9E Orion hybrid at Renton, Washington. The pontoons have just been installed on the airplane in place of its fixed landing gear. (Seattle Post Intelligencer Collection/Museum of History & Industry)

15 August 1935: Two of the most famous men of their time, Wiley Hardeman Post and William Penn Adair (“Will”) Rogers, were killed in an airplane crash near Point Barrow, Alaska.

Post, a pioneering aviator who had twice flown around the world—once, solo—and helped develop the pressure suit for high altitude flight, was exploring a possible air mail route from the United States to Russia. His friend, world famous humorist Will Rogers, was along for the trip.

Transcontinental and Western Airlines' Lockheed Model 9E special, NC12283. This airplane would be modified by Pacific Airmotive, Burbank, California, for Wiley Hardeman post. (Ed Coates Collection)
Transcontinental & Western Air Incorporated’s Lockheed Model 9E Special, NC12283. This airplane would be modified by Pacific Airmotive, Burbank, California, for Wiley Hardeman Post. (Ed Coates Collection)

Post’s airplane was a hybrid, built from the fuselage of a former Transcontinental & Western Air, Inc., Lockheed Model 9E Orion Special, NC12283, combined with a wing from a Lockheed Model 7 Explorer. T&WA operated the Orion for two years before selling it to Charles Babb, Glendale, California. Babb installed the salvaged wing from a modified Lockheed Model 7 Explorer, Blue Flash, NR101W, which had crashed in Panama in 1930.

The Orion’s standard 450 horsepower Pratt & Whitney Wasp SC1 engine was replaced with an air-cooled, supercharged, 1,343.8-cubic-inch-displacement (22.021 liter) Pratt & Whitney Wasp S3H1 nine-cylinder radial engine (serial number 5778), rated at 550 horsepower at 2,200 r.p.m. to 5,000 feet (1,524 meters), and 600 horsepower at 2,250 r.p.m. for takeoff. A three-bladed Hamilton Standard variable-pitch propeller was used. Both the SC1 and S3H1 were direct drive engines. The S3H1 was 3 feet, 7.01 inches (1.093 meters) long and 4 feet, 3.60 inches (1.311 meters) in diameter. It weighed 865 pounds (392 kilograms).

Post also wanted to replace the retractable landing gear with pontoons for water landings.

Lockheed engineers were of the opinion that the hybrid aircraft and the other modifications which were requested by Post were dangerous and refused to do the work. Pacific Airmotive, also located in Burbank, California, however, agreed to modify the airplane. Several names were used to describe the hybrid airplane, such as “Lockheed Aurora,” as well as others perhaps less polite. It was given the restricted registration NR12283.

NR12283 was 27 feet, 6 inches (8.382 meters) long with a wingspan of 48 feet, 6 inches (14.783 meters). The wing area was 313 square feet (29.079 square meters).

Wiley Post’s red Lockheed Orion/Explorer hybrid, NR12283, at Renton, Washington.

Post had the pontoons installed at Renton, Washington. The floats that he had ordered did not arrive on time so he installed a larger set intended for another aircraft.

NR12283, Wiley Post's hybrid Lockheed Orion/Explorer float plane, at Fairbanks, Alaska. (PBS)
NR12283, Wiley Post’s red hybrid Lockheed Orion/Explorer float plane, at Fairbanks, Alaska. (PBS)

After several days of flying from Seattle and through Alaska, Post and Rogers were nearing Point Barrow on the northern coast of the continent. They encountered dense fog and landed on Walakpa Bay, about 13 miles (21 kilometers) southwest of the village of Barrow.

“August 15, 1935 2:00 p.m. — Harding Lake, Alaska. Wiley Post and Will Rogers taxi for take-off. Last photo before their 6:30 p.m. crash near Barrow. Patton Collection #13 ” (Harding Lake Association)

After talking with a local resident, Clair Okpheah, they taxied back on the lagoon and took off to the north. Post banked to the right, but at about 50 feet (15 meters) the engine stopped. NR12283 pitched down, rolled to the right, and then its right wing struck the mud. The right wing and pontoon were torn off and the airplane crashed upside down. Post and Rogers died.

Clair Okpheah ran to Barrow for help. When a rescue party arrived 16 hours after the crash, the men recovered the bodies of Post and Rogers. It was noted that Wiley Post’s wristwatch had stopped at 8:18 p.m.

Wiley Post's hybrid airplane, NR12283, after the crash, 15 August 1935. (UPI)
The wreckage of Wiley Post’s Lockheed Model 9E Orion hybrid airplane, NR12283, after the crash at Walakpa Lagoon, Alaska, 15 August 1935. (UPI)

© 2018, Bryan R. Swopes

14 August 1979

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Red Baron, an Unlimited Class RB51 Mustang. (Octane 130)
Red Baron, an Unlimited Class RB51. (Octane 130)

14 August 1979: Air racer Steve Hinton set a new Fédération Aéronautique Internationale (FAI) speed record for piston engine, propeller-driven airplanes when he flew his highly-modified North American Aviation P-51 Mustang, Red Baron, to an average 803.138 kilometers per hour (499.047 miles per hour) over a 3 kilometer course at Tonapah, Nevada.¹

Unlimited Class North American Aviation P-51 Mustang, Red Baron.
Unlimited Class North American Aviation P-51 Mustang, Red Baron. (Jon R. Wallace)
Steve Hinton

Steve Hinton’s Mustang was a Dallas, Texas-built North American Aviation P-51D-25-NT, serial number 44-84961. His company, Fighter Rebuilders, modified the airplane for racing. The most noticeable change is the substitution of the standard Packard V-1650-7 Merlin V-12 engine and its four-bladed propeller with a larger, more powerful, 2,239.33-cubic-inch-displacement (36.695 liter) liquid-cooled, supercharged Rolls-Royce Griffon 57 single overhead cam (SOHC) 60° V-12 engine and dual, three-bladed, counter-rotating propellers from an Avro Shackleton bomber. A revised engine cowling gave Red Baron an appearance similar to the Allison-powered XP-51.

Red Baron crashed 16 September 1979 when an oil pump failure caused the propeller blades to move to flat pitch, dramatically increasing aerodynamic drag. Hinton suffered serious injuries but survived.

¹ FAI Record File Number 8438

© 2019, Bryan R. Swopes

14 August 1968

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Sikorsky S-61L N300Y, Los Angeles Airways, at Disneyland Heliport, Anaheim, California. (Robert Boser)
Sikorsky S-61L N300Y, Los Angeles Airways, at Disneyland Heliport, Anaheim, California. (Robert Boser)

14 August 1968: At 10:28:15 a.m., Pacific Daylight Time, Los Angeles Airways Flight 417, a Sikorsky S-61L helicopter, departed Los Angeles International Airport (LAX) on a regularly-scheduled passenger flight to Disneyland, Anaheim, California. On board were a crew of three and eighteen passengers. The aircraft commander, Captain Kenneth L. Waggoner, held an Airline Transport Pilot certificate and was type-rated in the Sikorsky S-55, S-58 and S-61L. He had a total of 5,877:23 flight hours, with 4,300:27 hours in the S-61L. Co-pilot F. Charles Fracker, Jr. had 1,661:18 flight hours, of which 634:18 were in the S-61L. Flight Attendant James A. Black had been employed with LAA for nearly ten years.

At approximately 10:35 a.m., while flying at an estimated altitude of 1,200–1,500 feet (370–460 meters) above the ground, one of the helicopter’s five main rotor blades separated from the aircraft which immediately went out of control, started to break up, and crashed in a recreational park in Compton. All twenty-one persons on board, including the 13-year-old grandson of the airlines’ founder and CEO, were killed.

The Sikorsky S-61 was registered N300Y.  It had been the prototype S-61L, serial number 61031. Los Angeles Airways was the first civil operator of the S-61, purchasing them at a cost of $650,000 each. As of the morning of 14 August 1968, 61031 had accumulated a total of 11,863.64 hours flight time on the airframe (TTAF). It flew an estimated 3.17 hours on the morning of the accident.

Los Angeles Airways’ Sikorsky S-61L N300Y. Los Angeles City Hall is at the bottom of the image, just left of center. (AirHistory.net)

The Sikorsky S-61L was a civil variant of the United States Navy HSS-2 Sea King, and was the first helicopter specifically built for airline use. The prototype, N300Y, first flew 2 November 1961. It is a large twin-engine helicopter with a single main rotor/tail rotor configuration. Although HSS-2 fuselage is designed to allow landing on water, the S-61L is not amphibious, having standard fixed landing gear rather than the sponsons of the HSS-2 (and civil S-61N). The S-61L fuselage is 4 feet, 2 inches (1.270 meters) longer than that of the HSS-2. The S-61L is 72 feet, 7 inches (22.123 meters) long and 16 feet, 10 inches (5.131 meters) high, with rotors turning.

The main rotor has five blades and a diameter of 62 feet (18.898 meters). Each blade has a chord of 1 foot, 6.25 inches (0.464 meters). The tail rotor also has five blades and a diameter of 10 feet, 4 inches (3.149 meters). They each have a chord of 7–11/32 inches (0.187 meters). At 100% r.p.m., the main rotor turns 203 r.p.m. and the tail rotor, 1,244 r.p.m. The main rotor turns counter-clockwise, as seen from above. (The advancing blade is on the helicopter’s right side.) The tail rotor turns clockwise, as seen from the left side. (The advancing blade is below.)

The S-61L was powered by two General Electric CT58-140-1 turboshaft engines, each of which was rated for 1,400 shaft horsepower for takeoff and maximum power of 1,500 shaft horsepower for 2½ minutes. The main transmission was rated for 2,300 horsepower, maximum.

The S-61 has a cruise speed of  166 miles per hour (267 kilometers per hour).  The service ceiling is 12,500 feet (3,810 meters). 61031 had a maximum takeoff weight (MTOW) of 19,000 pounds (8,618.3 kilograms).

Between 1958 and 1980, Sikorsky built 794 S-61 series helicopters. 13 were S-61Ls.

Crash scene of Los Angeles Airways’ Sikorsky S-61L N300Y. (Benjamin John Olender/Los Angeles Times, Vol. LXXXVII,Thursday, 15 August 1968, Page 3, Columns 1–4)

The National Transportation Safety Board investigation found that most of the helicopter was contained with a small area of Leuders Park. One main rotor blade, however, was located approximately 0.25 miles (0.40 kilometers) west of the main wreckage. This blade is referred to as the “yellow” blade. (The main rotor blades marked with colored paint for simplicity, red, black, white, yellow, and blue.) Analysis found that this blade’s spindle, where it attached to the main rotor hub assembly, had failed due to a fatigue fracture. It was believed that the fracture began in an area of substandard hardness which was present in the original ingot from which the part was forged, and that inadequate shot-peening of the part during the overhaul process further weakened the spindle.

Diagram of fractured main rotor spindle. (NTSB)
Diagram of fractured main rotor spindle. (NTSB)

Los Angeles Airways had experienced a similar accident only three months earlier which had resulted in the deaths of all 23 persons on board. (Flight 841, 22 May 1968). L.A. Airways never recovered from these accidents and ceased all operations by 1971.

© 2016, Bryan R. Swopes