17 January 1966: A United States Air Force Boeing B-52G-115-BW Stratofortress, 58-0256, and its 7-man crew, along with a second B-52, were flying an Airborne Nuclear Alert patrol over the Mediterranean Sea. The bomber, call sign “Tea 16,” was armed with four Mark 28 nuclear bombs carried in its bomb bay.
At approximately 10:30 a.m., the two B-52s rendezvoused with two Boeing KC-135A-BN Stratotankers, based at Morón Air Base, Spain, for the second aerial refueling of the mission. The aircraft were at 31,000 feet (9,448 meters) off the southern coast of Spain.
Major Larry G. Messinger, a veteran of World War II, aboard as a relief pilot, was flying Tea 16 from the left seat. The aircraft commander, Captain Charles J. Wendorf, was in the right, co-pilot’s seat, while 1st Lieutenant Richard J. Rooney, the assigned co-pilot, rode in a jump seat behind them.
Major Messinger later said, “We came in behind the tanker, and we were a little bit fast, and we started to overrun him a little bit. . . .”
B-52G 58-0256 collided with the refueling boom of “Troubadour 14” (KC-135A 61-0273). The boom penetrated the bomber’s fuselage, broke structural members and the left wing broke off. The B-52 exploded. The fully-loaded tanker, on fire, went into a steep dive. At 1,600 feet (488 meters), it also exploded.
The four crewmen aboard the tanker were killed. Three of the seven men on the B-52 ejected, and the co-pilot, who was not in an ejection seat, literally fell out of the disintegrating bomber. The navigator’s parachute did not open and he was killed. Three others were unable to escape the doomed airplane and were also killed.
As the B-52 broke apart, the four nuclear bombs it carried in the bomb bay fell free. Three of them fell near the fishing village of Palomares. In two of these, the conventional explosives that “implode” the plutonium to start a chain reaction, detonated on impact, but a nuclear explosion did not occur. However, plutonium was scattered over the area. The third bomb was recovered intact, though it was slightly damaged. The retarding parachute of the fourth Mark 28 opened and it was carried offshore by the wind and fell into the Mediterranean Sea.
A massive recovery operation took place. The fourth bomb was recovered after five months. It had come to rest in an underwater canyon at a depth of 2,550 feet (777 meters).
558 acres (226 hectares) of land in and around Palomares was contaminated. The soil was removed and placed in steel barrels for transportation to the United States for burial at the Savannah River Plant, a nuclear reservation in South Carolina.
The Mark 28 was a two-stage radiation-implosion thermonuclear bomb which was designed by the Los Alamos National Laboratory and produced from January 1958 to May 1966. In 1968, it was redesignated B-28. More than 4,500 were manufactured in as many as 20 variants. Explosive yield varied between 70 kilotons and 1.45 megatons. The B-28-Y1 in the photograph above is a 1.1 megaton weapon. The bomb remained in service until 1991.
16 January 1942: Transcontinental and Western Air, Inc., Flight 3, was a transcontinental passenger flight enroute to Los Angeles, California from New York City.
The airplane was a Douglas DC-3-362, registered NC1946.
The pilot in command was Captain Wayne C. Williams, an 11-year employee of T&WA. He had 12,204 hours total flight time with more than 3,500 hours in DC-3s. He had flown 204 hours at night within the previous six months. The co-pilot was S. Morgan Gillette, who had been with T&WA for a little less that 1 year, 6 months. He had 1,330 hours of flight time with 650 in DC-3s.
After a refueling stop at Las Vegas Airport, the airliner departed at 7:07 p.m. Pacific Standard Time, on the final leg of the flight to the Lockheed Air Terminal at Burbank, California (officially, the Bob Hope Airport, but now known Hollywood Burbank Airport). It was dark, but the weather was clear. Because of wartime regulations, the lighted airway beacons on the route had been extinguished.
At 7:20 p.m., PST, Flight 3 crashed into a vertical cliff face on Potosi Mountain, an 8,517-foot (2,596 meters) mountain 32 miles (51.5 kilometers) southwest of Las Vegas, Nevada. The DC-3 was completely destroyed and all 22 persons aboard were killed, including actress Carole Lombard, Mrs. Clark Gable.
In planning the flight, the crew had made an error in the compass course for this leg of the flight. Their written flight plan, filed with the airline’s operations department, indicated a compass course of 218° which took them directly to the mountain.
Carole Lombard (née Jane Alice Peters) was one of the most successful motion picture actresses in Hollywood. She was born at Fort Wayne, Indiana, in 1908, and had her first motion picture role in 1921. At age 16, she was under contract to the Fox Film Corporation and as was customary, was given a more dramatic name. She was primarily a comedic actress though she also had several dramatic roles.
Lombard was nominated for an Academy Award for Best Actress in “My Man Godfrey” which starred William Powell, to whom she was married 1931–1933. In 1938, Lombard married actor Clark Gable.
Carole Lombard had been on a War Bonds tour and was returning home to Hollywood. She was seated in an aisle seat in the third row, next to a U.S. Army private. Her mother, Elizabeth Peters, was seated directly across the aisle.
NC1946 was a DC-3-362, c/n 3295, built in February 1941 for Transcontinental and Western Air by the Douglas Aircraft Company at Santa Monica, California. It was an all-metal, twin-engine civil transport with retractable landing gear. The airplane was operated by a pilot and co-pilot and could carry up to 21 passengers.
The DC-3-362 was 64 feet, 5 inches (19.634 meters) long with a wingspan of 95 feet (28.956 meters). It was 16 feet, 11 inches (5.156 meters) high. The airplane weighed approximately 18,000 pounds (8,165 kilograms) empty and had a gross weight of 25,200 pounds (11,431 kilograms).
NC1946 was powered by two air-cooled, supercharged 1,823.129-cubic-inch-displacement (29.875 liter) Wright Aeronautical Division Cyclone 9 GR-1820G202A nine-cylinder radial engines with compression ratio of 6.7:1. These engines had a Normal Power rating of 1,100 horsepower at 2,400 r.p.m., and 1,200 horsepower at 2,500 r.p.m. for Takeoff, burning 91/96 octane aviation gasoline. They drove three-bladed, constant-speed, full-feathering Hamilton Standard Hydromatic propellers through a 0.5625:1 gear reduction. The GR-1820G202A was 4 feet, 2.04 inches (1.271 meters) long, 4 feet, 7.10 inches (1.400 meters) in diameter, and weighed 1,310 pounds (594 kilograms).
The DC-3 had a cruise speed of 150 miles per hour (241 kilometers per hour) and maximum speed of 237 miles per hour (381 kilometers per hour) at 8,500 feet (2,591 meters). The airplane had a service ceiling 24,000 feet (7,315 meters), and its range was 1,025 miles (1,650 kilometers).
The Douglas DC-3 was in production for 11 years with 10,655 civil and C-47 military airplanes built, and another 5,000 license-built copies. Over 400 are still in commercial service.
15 January 2009: At 3:25 p.m., Eastern Standard Time, U.S. Airways Flight 1549 departed from Runway 4 at LaGuardia International Airport (LGA) enroute to Seattle-Tacoma International Airport (SEA) with a stop at Charlotte, North Carolina (CLT). On board were 150 passengers and 5 crewmembers. The pilot-in-command was Captain Chesley Burnett Sullenberger III, and the co-pilot was First Officer Jeffrey B. Skiles.
Flight 1549 (radio call sign, “Cactus Fifteen-Forty-Nine”) was an Airbus Industrie A320-214, with registration N106US.
Captain Sullenberger was a 1973 graduate of the United States Air Force Academy and had served as a pilot in McDonnell F-4 Phantom IIs until 1980, when he left the Air Force and began a career as an airline pilot. To date, “Sully” had flown 19,663 total hours with 4,765 hours in the Airbus A320.
First Officer Skiles was also a highly experienced pilot with 15,643 total hours, but this was his very first flight aboard the A320 after completing the airline’s pilot transition course.
First Officer Skiles was the pilot flying on the first leg of the flight. The airliner was climbing and gaining airspeed, when at 3:27:11, it collided with a large flock of Canada Geese at an altitude of 2,818 feet (859 meters), approximately 4.5 miles (7.2 kilometers) from the runway. Birds were ingested in both engines which immediately lost thrust. Captain Sullenberger took over the controls while Skiles began the engine restart procedure.
A portion of the Cockpit Voice Recorder transcript follows:
15:27:07 Sullenberger: After takeoff checklist complete.
15:27:10.4 Sullenberger: Birds.
15:27:11 Skiles: Whoa.
15:27:11:4 (Sound of thump/thud(s), followed by shuddering sound.)
15:27:12 Skiles: Oh (expletive deleted).
15:27:13 Sullenberger: Oh yeah. (Sound similar to decrease in engine noise/frequency begins.)
15:27:14 Skiles: Uh oh.
15:27:15 Sullenberger: We got one rol — both of ’em rolling back.
15:27:18 (Rumbling sound begins and continues until approximately 15:28:08.)
15:27:18.5 Sullenberger: Ignition, start.
15:27:32.9 Sullenberger: MAYDAY MAYDAY MAYDAY. Uh this is uh Cactus Fifteen-Thirty-Nine [sic] hit birds, we’ve lost thrust (in/on) both engines we’re turning back towards LaGuardia.
15:27:42 LaGuardia Departure Control: OK uh, you need to return to LaGuardia? Turn left heading of uh Two Two Zero.
15:27:43 (sound similar to electrical noise from engine igniters begins.)
15:28:02 Skiles: Airspeed optimum relight. Three hundred knots. We don’t have that.
15:28:03 Flight Warning Computer: Sound of single chime.
15:28:05 Sullenberger: We don’t.
15:28:05 LGA Departure Control: Cactus Fifteen-Twenty-Nine [sic], if we can get it for you do you want to try to land Runway One Three?
15:28:05 Skiles: If three nineteen. . .
15:28:10.6 Sullenberger: We’re unable. We may end up in the Hudson.
15:29:28 Sullenberger: We’re gonna be in the Hudson.
15:29:33 LGA Departure Control: I’m sorry say again Cactus?
15:29:53 LGA Departure Control: Cactus Fifteen-Forty-Nine radar contact is lost you also got Newark Airport off your two o’clock in about seven miles.
15:30:24 Ground Proximity Warning System: TERRAIN TERRAIN. PULL UP. PULL UP. (“Pull Up” repeats until the end of the recording.)
15:30:38 Sullenberger: We’re gonna brace.
Though air traffic controllers had made runways available at the three closest airports for an emergency landing, Flight 1549 had lost too much airspeed and altitude to reach any of them. Despite the best efforts of Captain Sullenberger and First Officer Skiles to restart the two damaged engines, there was no alternative but to ditch the airliner into the Hudson River.
The A320 hit the water in a slight nose-up attitude at approximately 130 knots (150 miles per hour, 241 kilometers per hour). The airliner quickly slowed then began drifting with the tide. The force of the impact had twisted the airframe and the cargo doors’ seals began to leak. N106US began to settle into the water.
Cabin attendants opened the doors and activated the emergency slides, which acted as flotation rafts. Passengers quickly evacuated the airliner and many of them stood on the wings to stay out of the frigid water.
Before he left his airplane, Captain Sullenberger twice went through the cabin to make sure than no one was left aboard. He was the last person to leave Flight 1549.
Rescue efforts were immediately under way. Everyone on board was saved, and there were just five serious injuries sustained during the emergency.
This accident is known as “The Miracle on the Hudson” and the crew of U.S. Airways Flight 1549 are regarded as national heroes.
This was the most successful ditching on an airliner since Pan American World Airways Flight 6, a Boeing 377 Stratocruiser named Sovereign of the Skies, went down in the Pacific Ocean, 15 October 1956.
U.S. Airways Flight 1549 was flown with an Airbus Industrie A320-214, s/n 1024, registration N106US. It was built at Aéroport de Toulouse – Blagnac, France in 1999. At the time of the accident, N106US had 25,241.08 total flight hours on the airframe in 16,299 cycles.
The A320-200 series is a medium-range, narrow body twin engine airliner, introduced during the mid-1980s. It uses “fly-by-wire” systems and was the first airliner with “side stick controllers.” The airliner is flown by a pilot and co-pilot.
The A320-214 is 37.57 meters (123 feet, 3 inches) long with a wingspan of 34.10 meters (111 feet, 11 inches) and overall height of 11.76 meters (38 feet, 7 inches). Average empty weight of the airplane is 42,600 kilograms (93,917 pounds) and the maximum takeoff weight (MTOW) is 78 tonnes (171,961 pounds).
N106US was powered by two CFM International CFM56-5B4/P high bypass turbofans engines, producing up to 120.102 kilonewtons (27,000 pounds of thrust) each. It is a two-spool axial flow engine with a single-stage fan, 13 stage (4 low- and 9 high-pressure stages) compressor section and 4-stage (1 high- and 3 low-pressure stages) turbine section. The engine is 72.0 inches (1.829 meters) in diameter, 102.4 inches (2.601 meters) long and weighs 5,250 pounds (2,381 kilograms)
The A320-200 series has a cruising speed of 0.78 Mach (828 kilometers per hour, 515 miles per hour) at 11,000 meters (36,090 feet) and a maximum speed of 0.82 Mach (871 kilometers per hour, 541 miles per hour) at the same altitude. The airliner’s service ceiling is 12,000 meters (39,370 feet) and the maximum range, fully loaded, is 6,100 kilometers (3,790 miles).
The Airbus A320 is still in production with more that 3,400 airplanes delivered, and another 2,900 on order.
N106US is displayed at the Carolinas Aviation Museum, Charlotte, North Carolina, in the condition that it was in when removed from the Hudson River.
Captain Chesley Burnett Sullenberger III retired from U.S. Airways 10 March 2010. First Officer Jeffrey B. Skiles remained with the airline, although he took an extended leave of absence.
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 enroute 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 deicing 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, there 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 was 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 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 394 r.p.m. (100% NR). (The advancing blade is on the helicopter’s right side.) The rotor blade has a chord of 1 foot, 1.0 inches (0.330 meter) and 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 435 horsepower, the limit of the main transmission. 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 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.
13 January 1942: “. . .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. . . .” — Wikipedia