13 January 2012: This McDonnell Douglas F-15E-47-MC Strike Eagle, 89-0487, became the first F-15 to have logged over 10,000 flight hours. Regularly assigned to Captain Justin Pavoni, Pilot, and Lieutenant Colonel David Moeller, Weapons System Officer and commander of the 335th Expeditionary Fighter Squadron, on the mission which achieved the milestone, 487 was flown by Captain Ryan Bodenheimer, pilot, and Captain Erin Short, WSO, the two youngest flyers in the squadron.
89-0487 was accepted by the Air Force on 13 November 1990. At the time of this event, 487 was considered to be the flag ship of the 335th Expeditionary Fighter Squadron. During a three month period at Bagram Air Base, this individual F-15E flew 1,200 hours and dropped 15% of all the bombs dropped by the squadron.
During Operation Desert Storm, Captains Tim Bennett and Dan Bakke, USAF, flying this F-15E, call sign “Packard 41,” used a GBU-10 Paveway II 2,000-pound laser-guided bomb to “shoot down” an Iraqi Mi-24 Hind attack helicopter. 487 is the only F-15E to have scored an air-to-air victory.
This airplane is still in service with the United States Air Force. It passed 12,000 flight hours on 16 August 2016. It has been deployed for combat operations 17 times.
The Strike Eagle was begun as a private venture by McDonnell Douglas. Designed to be operated by a pilot and a weapons system officer (WSO), the airplane can carry bombs, missiles and guns for a ground attack role, while maintaining its capability as an air superiority fighter. It’s airframe was a strengthened and its service life doubled to 16,000 flight hours. The Strike Eagle became an Air Force project in March 1981, and went into production as the F-15E. The first production model, 86-0183, made its first flight 11 December 1986.
The McDonnell Douglas F-15E Strike Eagle is a two-place twin-engine multi-role fighter. It is 63 feet, 9 inches (19.431 meters) long with a wingspan of 42 feet, 9¾ inches (13.049 meters) and height of 18 feet, 5½ inches (5.626 meters). It weighs 31,700 pounds (14,379 kilograms) empty and has a maximum takeoff weight of 81,000 pounds (36,741 kilograms). The F-15E is powered by two Pratt and Whitney F100-PW-229 turbofan engines which produce 17,800 pounds of thrust (79.178 kilonewtons) each, or 29,100 pounds (129.443 kilonewtons) with afterburner.
The Strike Eagle has a maximum speed of Mach 2.54 (1,676 miles per hour, (2,697 kilometers per hour) at 40,000 feet (12,192 meters) and is capable of sustained speed at Mach 2.3 (1,520 miles per hour, 2,446 kilometers per hour). Its service ceiling is 60,000 feet (18,288 meters). The fighter-bomber has a combat radius of 790 miles (1,271 kilometers) and a maximum ferry range of 2,765 miles (4,450 kilometers).
Though optimized as a fighter-bomber, the F-15E Strike Eagle retains an air-to-air combat capability. The F-15E is armed with one 20mm M61A1 Vulcan 6-barrel rotary cannon with 512 rounds of ammunition, and can carry four AIM-9M Sidewinder heat-seeking missiles and four AIM-7M Sparrow radar-guided missiles, or a combination of Sidewinders, Sparrows and AIM-120 AMRAAM long range missiles. It can carry a maximum load of 24,500 pounds (11,113 kilograms) of bombs and missiles for ground attack.
13 January 1982: At 3:59 p.m. Eastern Standard Time (20:59 UTC), Air Florida Flight 90, a Boeing 737-222, registration N62AF, s/n 19556, began its takeoff roll at Washington National Airport (DCA). The airliner, with a flight crew of two and three cabin attendants, carried 74 passengers en route Fort Lauderdale, Florida, with an intermediate stop at Tampa.
The departure was delayed 1 hour, 45 minutes when the airport closed due to a snowstorm. When the airport reopened, heavy snow was still falling.
Snow and ice had accumulated on the airliner’s wings and fuselage. The airplane had previously been de-iced but the flight crew elected not to repeat the procedure. Further, they did not activate the engine anti-ice system.
During the takeoff the engines were slow to accelerate and the airplane took much longer than normal to gain flight speed. Though it did become airborne, the 737 reached an altitude of just 352 feet (107 meters) when it stalled and struck the 14th Street Bridge, and then crashed into the Potomac River.
The airliner broke through the ice covering the river and sank. There were only five survivors.
In addition to those who died aboard the 737, four persons on the 14th Street Bridge were killed when the airliner struck their cars.
Many people who witnessed the crash tried to help the survivors by going in to the freezing water to reach them.
The U.S. Park Police responded with a 1979 Bell 206L-1 LongRanger II helicopter, Eagle 1, (N22PP, serial number 45287) flown by Officers Donald W. Usher and Melvin E. Windsor. The pilot, Don Usher, hovered low, sometimes with the skids of the helicopter in the water, while Gene Windsor tried to reach the survivors.
A passenger in the water, Arland D. Williams, Jr., twice caught lines that had been lowered from the helicopter, but in both cases, he passed them to others in the water:
“He was about 50 years old, one of half a dozen survivors clinging to twisted wreckage bobbing in the icy Potomac when the first helicopter arrived. To the copter’s two-man Park Police crew he seemed the most alert. Life vests were dropped, then a flotation ball. The man passed them to the others. On two occasions, the crew recalled last night, he handed away a lifeline from the hovering machine that could have dragged him to safety. The helicopter crew who rescued five people, the only persons who survived from the jetliner, lifted a woman to the riverbank, then dragged three more persons across the ice to safety. Then the lifeline saved a woman who was trying to swim away from the sinking wreckage and the helicopter pilot, Donald W. Usher, returned to the scene but the man was gone.”
— “A Hero – Passenger Aids Others, Then Dies.” The Washington Post, January 14, 1982.
“So the man in the water had his own natural powers. He could not make ice storms, or freeze the water until it froze the blood. But he could hand life over to a stranger, and that is a power of nature too. The man in the water pitted himself against an implacable, impersonal enemy; he fought it with charity; and he held it to a standoff. He was the best we can do.”
— Rosenblatt, R., “The Man in the Water,” Time Magazine, January 25, 1982
The National Transportation Safety Board determines that the probable cause of this accident was the flightcrew’s failure to use engine anti-ice during ground operation and takeoff, their decision to takeoff with snow/ice on the airfoil surfaces of the aircraft, and the captain’s failure to reject the takeoff during the early stage when his attention was called to anomalous engine instrument readings. Contributing to the accident were the prolonged ground delay between deicing and the receipt of ATC takeoff clearance during which the airplane was exposed to continual precipitation, the known inherent pitchup characteristics of the B-737 aircraft when the leading edge is contaminated with even small amounts of snow or ice, and the limited experience of the flightcrew in jet transport winter operations.
— NATIONAL TRANSPORTATION SAFETY BOARD AIRCRAFT ACCIDENT REPORT NTSB-AAR-82-8, 10 August 1982, Section 3.2 at Page 82
The National Transportation Safety Board also wrote, “The Safety Board commends the heroic actions of the helicopter pilot and crewman who participated in the rescue effort.”
The Boeing 737-200 series is a short-to-medium range narrow body twin-engine civil transport. It had a flight crew of two and could carry a maximum of 136 passengers.
The 737-200 is 100 feet, 2 inches (30.531 meters) long with a wingspan of 93 feet (28.346 meters) and overall height of 36 feet, 10 inches (11.227 meters). Its empty weight is 69,700 pounds (31,615 kilograms) and maximum takeoff weight is 115,500 pounds (52,390 kilograms).
The airliner is powered by two Pratt & Whitney JT8D-9A low-bypass axial-flow turbofan engines, each producing 14,500 pounds of thrust (64.499 kilonewtons) at Sea Level. JT8D-9A was a two-spool engine with a 2-stage fan section, 11-stage compressor (4 low- and 7 high-pressure stages), nine combustion chambers and a 4-stage turbine (1 high- and 3 low-pressure stages). The JT8D-9A was 42.5 inches (1.080 meters) in diameter, 123.5 inches (3.137 meters) long, and weighed 3,196 pounds (1,450 kilograms).
Maximum speed of the 737-200 is 0.82 Mach (544 miles per hour/780 kilometers per hour) and the service ceiling is 35,000 feet (10,700 meters).
The 737-200 first flew 8 August 1967. 1,095 –200s were built. The last one in service with an American airline, Aloha Airlines, was retired 21 March 2008.
The Bell Helicopter Company Model 206L-1 LongRanger II is a 7-place light helicopter developed from the earlier 5-place Model 206B JetRanger series. It is designed to be flown by a single pilot in the right front seat, and is certified for Visual Flight Rules.
The 206L-1 is 42 feet, 8 inches (13.005 meters) long, overall, and 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 37 feet (11.278 meters) and turns counter-clockwise (seen from above) at 395 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 11° negative twist. The blade tips are swept.
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 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 LongRanger II is powered by an Allison 250-C28B turboshaft engine. This engine produces 500 shaft horsepower but is de-rated to the limit of the main transmission, 435 horsepower at 104% N1 (52,980 r.pm.). The 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 angled 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. Vertical fins are attached to the outboard ends of the horizontal stabilizers and above the tailboom centerline. The fins are slightly offset to the left and counteract the helicopter’s Dutch roll tendency.
The helicopter has an empty weight of approximately 2,160 pounds (979 kilograms), depending on installed equipment, and the maximum gross weight is 4,050 pounds (1,836 kilograms).
The LongRanger II 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 Model 206L LongRanger first flew in 1974 and the 206L-1 LongRanger II variant entered production in 1978. It was replaced several years later by the 206L-3. The LongRanger remains in production as the Model 206L-4.
Bell 206L-1 LongRanger II serial number 45287 was issued an Airworthiness Certificate 17 August 1979. N22PP was transferred to the Department of the Interior, Northwest Region, at Boise, Idaho, in April 1998 and re-registered N613. At Mesa Verde National Park, Colorado, 30 October 2000, N613 was substantially damaged when its tail rotor blades failed due to improper manufacturing techniques. (NTSB Report DEN01LA012) The helicopter was repaired and returned to service. Its engine had been upgraded to an Allison 250-C30P. The helicopter’s FAA registration was cancelled 10 October 2014.
Restored to its original colors in 2016, Eagle One was placed on display at the National Law Enforcement Museum in Washington, D.C.
13 January 1949: William P. Odom set a Fédération Aéronautique Internationale (FAI) World Record for Distance in a Straight Line when he flew a Beechcraft Model 35 Bonanza, N80040, named Waikiki Beech, from Honolulu, Oahu, Territory of Hawaii, to Oakland, California, an official distance of 3,873.48 kilometers (2,406.87 miles).¹
The Chicago Daily Tribune reported the event:
Odom Flight from Hawaii Sets Light Plane Record
Hops Pacific to Oakland in 22 Hours
Oakland, Cal., Jan. 13 (Special)—Flyer Bill Odom set a new light plane record today in a flight across the Pacific from Hawaii, but dwindling gasoline supplies forced him to cut short his eastward flight and he landed here at 6:38 p.m. (8:38 Chicago time).
Odom, who had planned to continue on to Teterboro, N.J., 5,285 miles from his starting place in Hawaii had been in the air 22 hours and six minutes. He left Honolulu at 6:32 p.m. Wednesday (10:32 p.m. Wednesday Chicago time).
The flight over the Pacific, more than 2,300 miles, broke the light plane record of 2,061 miles set by two Russian flyers, A. Goussarov and V. Glebov Sept. 23, 1937, from Moscow to Krasnoyarsk. The record is recognized by the International Aeronautical federation for light planes, first category, 397–549 cubic inches engine displacement.
Uses Most of Fuel
Odom was two hours behind schedule and had only about 80 out of his 260 gallons of gasoline when he passed over the Golden Gate at 4:27 p.m. (6:27 p.m. Chicago time.) Head winds had taken a heavy toll of his gasoline load.
He radioed that he intended to add as much mileage as possible to his record before landing. He kept on, reaching Reno, Nev. where ice on his wings and a snowstorm on the airport forced him to turn back.
He then headed for Sacramento airport but no civil aeronautics administration officials were there and he landed at Oakland. There, the plane and its instruments were sealed.
“Boy, am I tired,” Odom said.
He covered more than 2,500 miles from Honolulu to Reno, but as he did not land at Reno the record will remain about 2,300 miles, the distance from Honolulu to Oakland.
Odom had bucked headwinds since he switched his single engined Beechcraft’s course south to fly over San Francisco instead of Seattle. He said he changed his course by mistake this morning. Somehow, he said, he lost his PBY escort from Honolulu and veered to the right.
He first had hunted out and ridden winds that took him northeast toward Seattle, but 1,800 miles out of Hawaii he hit a high pressure area that gave him for a time, tailwinds that enabled him to conserve gasoline.
Late Model Plane
Odom’s plane is a post-war model with a V-type tail, a tricycle landing gear that tucks up into the wings, a tiny little 185 horsepower, six cylinder unsupercharged engine. Its total weight with fuel, pilot, emergency gear, radio, and full equipment at take-off was only 3,750 pounds. It is an all-metal, low-wing monoplane which in its standard form can carry four passengers including pilot.
For his flight Odom had extra radio and a 100 gallon fuel tank installed in the cabin. Each wing tip also has a specially made fuel tank carrying 60 gallons, making 120 gallons total in those two containers. The normal tankage for the Bonanza is 40 gallons.
Odom holds the around the world flight record of 73 hours, 5 minutes and 11 seconds, set Aug. 11, 1947, from Chicago to Chicago in a converted A-20 bomber.
N80040 was the fourth prototype Beechcraft Model 35 Bonanza. (The first two were static test articles.)
The Beechcraft Model 35 Bonanza is a single-engine, four-place all-metal light civil airplane with retractable landing gear. The Bonanza has the distinctive V-tail with a 30° dihedral which combined the functions of a conventional vertical fin and rudder, and horizontal tail plane and elevators.
The Model 35 was 25 feet, 2 inches (7.671 meters) long with a wingspan of 32 feet, 10 inches (10.008 meters) and height of 6 feet, 6½ inches (1.994 meters). It had an empty weight of 1,458 pounds (661 kilograms) and gross weight of 2,550 pounds (1,157 kilograms.)
NX80040, s/n 4, and the following production models were powered by an air-cooled, 471.24-cubic-inch-displacement (7.72 liter) Continental Motors, Inc., E185 horizontally-opposed 6-cylinder engine. This engine was rated at 165 horsepower at 2,050 r.p.m. (NX80150, s/n 3, had been equipped with a 125-horsepower Lycoming O-290-A.) The Bonanza had a two-bladed electrically-controlled variable pitch R-100 propeller with a diameter of 7 feet, 4 inches (2.235 meters) made of laminated wood.
The “V-tail Bonanza” had a maximum speed of 184 miles per hour (296 kilometers per hour) at Sea Level, and a cruise speed of 175 miles per hour ( 282 kilometers per hour)at 10,000 feet (3,048 meters). Its service ceiling was 18,000 feet (5,486 meters). With full fuel, 40 gallons (151.4 liters), the airplane had a range of 750 miles (1,207 kilometers).
The Beechcraft 35 was in production from 1947 to 1982. More than 17,000 Model 35s and the similar Model 36 were built.
William Paul Odom was born at Raymore, Missouri, 21 October 1919. He was the first of three children of Dennis Paul Odom, a farmer, and Ethel E. Powers Odom.
Odom, then working as an airport radio operator, married Miss Dorothy Mae Wroe at Brentwood, Pennsylvania, 3 December 1939.
During World Ward II, from 1944 to 1945, Odom flew for the Chinese National Aviation Corporation (CNAC), flying “The Hump,” the air route over the Himalayas from India to China.
Bill Odom had flown a Douglas A-26 Invader named Reynolds Bombshell around the world in 3 days, 6 hours, 55 minutes, 56 seconds, 12–16 April 1947. He made a second around the world flight, 7–11 August 1947, again flying the A-26. The duration of this second trip was 3 days, 1 hour, 5 minutes, 11 seconds. Neither flight was recognized as a record by the FAI.
In April 1948, Odom flew a former U.S. Navy Consolidated RY-1, Bu. No. 67798 ² for the Reynolds Boston Museum China Expedition. The expedition ended abruptly and Odom flew the airplane out of China to Japan without authorization from either nation. He and the airplane’s owner, Milton Reynolds, were taken into custody and the airplane impounded.
On 8 March 1949, Odom made another FAI World Record flight with Waikiki Beech, from Honolulu to Teterboro, New Jersey, 7,977.92 kilometers (4,957.25 miles).³
With these records and record attempts, Bill Odom persuaded Jackie Cochran to buy a radically-modified P-51C Mustang named Beguine (NX4845N) for him to fly at the 1949 National Air Races at Cleveland Municipal Airport, Ohio.
Though he had never flown in a pylon race, Odom had qualified the P-51 Beguine for the 105 mile Sohio Trophy Race, held 3 September 1949. He won that race, averaging 388.393 miles per hour (625.058 kilometers per hour. He had also entered the Thompson Trophy Race, qualifying with a speed of 405.565 miles per hour (652.694 kilometers per hour.)
The Thompson Trophy Race was held on 5 September. On the second lap, Odom’s P-51 went out of control and crashed into a house near the airport. Bill Odom, along with a woman and child on the ground, were killed.
William Paul Odom’s remains were buried at the Friendship Cemetery, Columbus, Mississippi.
¹ FAI Record File Number 14512
² The airplane was originally ordered as a C-87A-CF Liberator Express transport for the U.S. Army Air Forces, serial number 43-30570, but was one of three which were transferred to the U.S. Navy.
#0000ff;">“. . .The first ejection seats were developed independently during World War II by Heinkel and SAAB. Early models were powered by compressed air and the first aircraft to be fitted with such a system was the Heinkel He 280 prototype jet-engined fighter in 1940. One of the He 280 test pilots, Helmut Schenk, became the first person to escape from a stricken aircraft with an ejection seat on 13 January 1942 after his control surfaces iced up and became inoperable. The fighter, being used in tests of the Argus As 014 impulse jets for Fieseler Fi 103 missile development, had its usual HeS 8A turbojets removed, and was towed aloft from Rechlin, Germany by a pair of Bf 110C tugs in a heavy snow-shower. At 7,875 feet (2,400 m), Schenk found he had no control, jettisoned his towline, and ejected. . . .”
13 January 1908: Henry Farman flew a circular one kilometer course at Issy-les-Moulineaux, France, in 1 minute, 28 seconds to win the Grand Prix de l’aviation, a prize of 50,000 francs, which had been offered by Henri Deutsch de la Meurthe in 1904.
Henri Deutsch de le Muerthe (1846–1919) was a wealthy French businessman with a strong interest in aviation. He was one of the founders of the Aéro-Club de France. Along with Ernest Archdeacon, he sponsored a series of prizes to promote advances in flight.
The biplane was built by brothers Charles and Gabriel Voisin, and was very similar to the Voisin-Delagrange I which they had built several months earlier. Henry Farman had requested some slight modifications. He first flew the airplane 30 September 1907.
Farman had previously won the Coupe d’Aviation Ernest Archdeacon (Ernest Archdeacon Cup) when he flew his Henri Farman nº 1 a distance of approximately 771 meters (2,530 feet) in 52 seconds, 26 October 1907.
The Henri Farman nº 1 (also known as the Voisin-Farman I) was a single-place, single-engine, two-bay biplane with the elevator forward and a “box kite” tail. It was 10.500 meters (34 feet 5.4 inches) long, with a wingspan of 10.000 meters (32 feet, 9.7 inches). The chord of each wing was 2.000 meters (6 feet, 6.7 inches), and vertical gap between the upper and lower wings was 1.500 meters (4 feet, 11.0 inches). There was no sweep or dihedral.
The complete airplane weighed 530 kilograms (1,169 pounds).
The airplane was powered by a steam-cooled, direct-injected, 487.14 cubic-inch-displacement (7.983 liter) Société Antoinette 8V 90° V-8 direct-drive engine ,designed by Léon Levavasseur. It produced 38 horsepower at 1,050 r.p.m. The engine turned a two-bladed pusher propeller, which had a diameter of 2.30 meters (7 feet, 6.6 inches). The engine was 1.120 meters (3 feet, 8 inches) long, 0.630 meters (2 feet, 1 inch) wide and (0.540 meters (1 foot, 9 inches) high. It weighed 95 kilograms (209 pounds).