Tag Archives: ff0000

12 March 2009

Cougar Helicopters Inc. Sikorsky S-92A C-GZCH (Transport Canada)

Cougar Helicopters, Inc., Flight 91 (Cougar 91), a Sikorsky S-92A helicopter, departed St. John’s International Airport (CYYT), Newfoundland, enroute to the Hibernia oil platform (the largest offshore oil platform) located 315 kilometers (196 miles) to the southeast in the Jeanne d’Arc Basin of the Grand Banks. The helicopter departed at 9:17 a.m. and climbed to its enroute cruise altitude of 9,000 feet (2,743 meters), leveling off at 9:32 a.m.

The aircraft was under the command of Captain Matthew William Davis, with First Officer Timothy Ross Lanouette. There were sixteen passengers. All on board were wearing full immersion suits.

Captain Davis had 5,997 hours of flight experience accumulated over 20 years as a professional helicopter pilot. He held a Canadian Airline Transport Pilot License with a Rotorcraft rating and was type-rated in the S-92A. He had 1,067 hours in type.

First Officer Lanouette had flown a total of 2,854 hours during 23 years with the Canadian Forces, and the 11 months he had worked for Cougar Helicopters. He also held a Canadian Airline Transport License with Rotorcraft rating. He was type-rated in the S-92A, and had 97 hours in type.

The Hibernia oil drilling and production platform, located at N. 46° 45′ 1.57″, W. 48° 46′ 58.54″, in 80 meters (262 feet) depth of water.

At 9:45:05, the crew received a series of indications of falling oil pressure in the transmission (also referred to as the main gear box, or MGB). Within 1 second, the amber CAUTION light was replaced by a red WARNING light and and audible “GEARBOX PRESSURE. . . GEARBOX PRESSURE. . .” warning. Within the next 20 seconds, the transmission oil pressure dropped from the normal range of 45–70 pounds per square inch (310.3–482.6 kilopascals) to less than 5 p.s.i. (34.5 kPa) This constituted an in-flight emergency which required that the crew land or ditch the helicopter immediately.

For the helicopter crew, ditching at sea must always be considered a life-and-death situation. At the time of the emergency, the surface weather along the route of flight was estimated as wind from the south-southeast at 22 knots (11.3 meters per second) (Beaufort Scale 6) and waves of 2.5 meters (8.2 feet) with a period of 7 seconds (Sea State 5). The water temperature was 0 °C (32 °F.). There were significant questions as to the survival chances of those on board Cougar 91.

Bristow Helicopters’ AS 332L Super Puma G-TIGK afloat in Sea State 5 conditions in the North Sea. (Air Accidents Investigation Branch)

Instead of proceeding with ditching, though, at 9:45:27, Captain Davis called Gander Area Control Center and declared an emergency:

“Gander Center, Cougar 91, mayday. Sir, we have a main gearbox oil pressure problem, request immediate clearance back to takeoff.”

The request was approved by air traffic control and Cougar 91 turned back toward St. John’s, approximately 54 nautical miles (62 miles/100 kilometers) away. Captain Davis began a descent from 9,000 feet (2,743 meters) at 9:45:31. The helicopter’s turn toward St. John’s was completed at 9:45:47.

At 9:45:58, Captain Davis told First Officer Lanouette that he was initiating a descent to the water and had Lanouette begin the emergency procedures check list.

Cockpit of a Sikorsky S-92A during a night flight over Riyadh, Saudi Arabia. (Ahmed Hader via Wikipedia)

A few minutes later, Captain Davis called Gander ACC, “I’m going to the nearest terra firma I can get. Whatever I see first, if it’s Cape Spear or a parking lot. We’ve lost all gearbox pressure at this time.”

Finishing the emergency check list, First Officer Lanouette informed Captain Davis that they were in a LAND IMMEDIATELY condition. Davis replied that he was going to level off at 1,000 feet (305 meters). At 9:51:50 the pilot increased collective pitch to stop the descent. Engine torque increased and Cougar 91 leveled off at 800 feet (244 meters).

The flight crew suspected that the low oil pressure warnings were actually a sensor problem. Their previous training had suggested that any imminent problem with the transmission would be preceded by noises and vibrations, which they had not experienced. Also, because the oil temperature indication had not increased, they suspected that the transmission had not actually lost oil at all.

At 9:55:15, power to the helicopter’s flight recorder was cut off, indicating that something had occurred. There is every indication of a tail rotor drive failure. The helicopter’s main rotor r.p.m. increased from 103% Nr to 107% Nr. Ten seconds later, 9:55:25, the helicopter yawed to the right. The pilots lowered the collective, and moved the cyclic left and added left anti-torque pedal. At 9:55:36, the first officer called Gander, saying that they were ditching. At 9:55:37, Cougar 91 rolled right and the rate of right yaw increased to nearly 4° per second. At 9:55:44, the yaw rate increased to 20° per second.

At 9:55:47, both engines were shut down.

Descending through 600 feet (183 meters), the helicopter’s airspeed was 90 knots (167 kilometers per hour). Rotor r.p.m. fluctuated between 105% and 95% as the pilots raised and lowered the collective. The S-92 appeared to be in a stable autorotation descending through 425 feet (130 meters) at 75 knots (139 kilometers per hour) with 98% Nr. It then rolled to the right, reaching a bank  angle of 57°. The main rotor accelerated back to 105%. Passing through 400 feet (122 meters) the collective was raised and the main rotor r.p.m. began to droop. The helicopter was traveling downwind at this time, with an estimated 32 knot (60 kilometers per hour) tailwind. The aircraft went through a series of extreme pitch, roll and yaw changes as the flight crew fought for control.

At 09:55:54, the crew began an autorotative flare at 220 feet (67 meters). The Sikorsky S-92A descended through 90 feet (27 meters) with a rate of descent of at least 2,300 feet per minute (11.7 meters per second), possibly much greater, and an airspeed of 66 knots (122 kilometers per hour). The main rotor was decelerating through 81% Nr. The helicopter was in a 16° nose-up attitude with a 9° left bank.

Cougar 91 hit the water at 9:56 a.m. The force of the impact was so great that the fuselage structure failed. The forward section, including the cockpit, broke off, as did the tail boom. The cabin section rolled over to the left and the aircraft sank immediately. The location was N. 47° 26′ 4.17″, W. 51° 56′ 42.53″.

A Cougar Helicopters, Inc. Sikorsky S-92, C-GSCH, configured for search-and-rescue operations. (Sikorsky, a Lockheed Martin Company)

Of the 18 persons on board Cougar 91, only one passenger—who had been seated on the right side of the passenger cabin, just forward of center, Seat 3D—survived. All others were found still strapped in their seats. They had received major lower limb fractures, spinal injuries, etc., and drowned. The survivor was rescued by Cougar Rescue 61, a company S-92A helicopter specially configured for search and rescue operations. He had been in the freezing water for approximately 1 hour, 20 minutes.

Wreckage of Cougar 91 was recovered from the sea floor at a depth of approximately 550 feet (168 meters) and returned to St. John’s for analysis.

Examination of the the helicopter’s rotor blades showed that the main rotor was turning slowly at impact, and that the tail rotor was not turning at all.

Recovered wreckage of Cougar Helicopters’ Sikorsky S-92A C-GZCH. (Transport Canada)

The investigation revealed that two of three studs attaching the transmission oil filter bowl to the transmission housing had fractured from over-stressed fatigue fractures. This allowed the transmission oil to rapidly drain. This had occurred previously with another Sikorsky S-92A, VH-LOH, which made and emergency landing in Western Australia, 2 July 2008. Sikorsky determined that the original titanium studs should be replaced with steel studs and made changes to the Aircraft Maintenance Manual procedures.

The bevel gears of the transmission’s tail rotor drive pinion were completely stripped away, as a result of frictional heating of the transmission operating without oil, and resulted in a complete loss of tail rotor drive.

During the investigation, it was determined that Cougar Helicopters had not properly followed the mandatory procedures required by the Aircraft Maintenance Manual, which were intended to discover damaged studs prior to failure.

The flight crew misunderstood the aircraft systems, which led them to misdiagnose the problem. A factor was their previous training regarding transmission noise and vibration.

The flight crew had significant trouble controlling the helicopter following the tail rotor failure. Shutting down the engines prior to lowering the collective resulted in a significant loss of rotor r.p.m. As the aircraft pitched, rolled and yawed, they were unable to turn the helicopter into the wind. They began their autorotative flare at too high an altitude with too low airspeed, which resulted in a nearly vertical impact. Because of the very low main rotor r.p.m., the impact forces were high enough to destroy the helicopter.

Sikorsky S-92. (Sikorsky, a Lockheed Martin Company)

Cougar 91 was a Sikorsky S-92A, registered C-GZCH (c/n 92-0048). The company had named the helicopter The Jeanne d’Arc Breeze. It had been completed by Sikorsky in 2006 at the Coatesville, Pennsylvania, plant, and was initially registered in the United States as N71143. The helicopter had accumulated a total of 2,194.3 flight hours (TTAF) since new, and 1,773 cycles.

The Sikorsky S-92A is a twin-engine, medium lift transport helicopter with a single main rotor and tail rotor. The tricycle landing gear is retractable. The S-92 is a development of the Sikorsky S-70 Blackhawk military utility helicopter. It is operated by a flight crew of two, and can carry nineteen passengers.

The helicopter has an overall length of 68 feet, 6 inches (20.879 meters) with rotors turning. The fuselage is 56 feet, 2 inches (17.120 meters) long, and has a maximum width across the sponsons of 12 feet, 9 inches (3.886 meters). The overall height is 17 feet, 11 inches (5.461 meters). The S-92A has an empty weight of 15,575 pounds (7,065 kilograms) and Maximum Takeoff Weight (MTOW) of 26,500 pounds (12,020 kilograms).

Sikorsky S-92 three-way illustration with dimensions (Sikorsky, a Lockheed Martin Company)

The S-92A has a four-bladed, fully-articulated main rotor with a diameter of 56 feet, 4 inches (17.170 meters). The main rotor turns counter-clockwise, as seen from above. (The advancing blade is on the helicopter’s right side.) The blade tips are swept aft 30° and have 20° anhedral. The four-bladed tail rotor has a diameter of 11 feet, 0 inches (3.353 meters) and is mounted on the right side of the tail rotor pylon in tractor configuration. It is canted 30° to the left, allowing it to generate left as well as anti-torque thrust. The tail rotor turns clockwise as seen from the helicopter’s left. (The advancing blade is below the axis of rotation.)

Power is supplied by two General Electric CT7-8A turboshaft engines rated at 2,740 shaft horsepower, each. This is a single-spool, front-drive, free-turbine engine with a 5-stage axial-flow, 1-stage centrifugal-flow compressor section, and a 2-stage gas generator turbine and 2-stage free power turbine. The engine is equipped with a Full-Authority Digital Engine Control (FADEC) system. The CT7-8A is 4 feet, 0.8 inches (1.240 meters) long, 2 feet, 2.0 inches (0.660 meters) wide and 2 feet, 1.0 inches (0.635 meters) high. It weighs 542.0 pounds (245.8 kilograms).

The CT7-8A has a Maximum Continuous Power rating of 1,523 shaft horsepower at 44,660 r.p.m., Ng (22,200 r.p.m., Np). The Takeoff Power rating is 1,879 shaft horsepower for Take-off (5-minute limit). For emergency situations, the engine can produce 2,043 shaft horsepower at 46,340 r.p.m., Ng, for 30 seconds (One Engine Inoperative, or OEI).

The Sikorsky S-92A has a maximum continuous cruise speed of 151 knots (280 kilometers per hour). Its maximum speed, VNE, is 165 knots (306 kilometers per hour). The service ceiling is 15,000 feet (4,572 meters). It can hover in ground effect (HIGE) at 9,200 feet (2,804 meters), and out of ground effect (HOGE) at 6,700 feet (2,042 meters). With one engine inoperative, the helicopter’s service ceiling is 5,500 feet (1,676 meters). The maximum range, with 30-minute fuel reserve, is 480 nautical miles (889 kilometers).

Sikorsky S-92. (Sikorsky, a Lockheed Martin Company)

The S-92A is certified for Category A operations, meaning that, if one engine fails during takeoff, it can either return to the takeoff point or continue to fly away on the remaining engine.

Depending on installed equipment, the S-92A can make an emergency ditching in up to Sea State 5 or 6. (Sea State 5, is defined as “rough” with wave heights from 2.5–4.0 meters, Sea State 6 is 4–6 meters, and “very rough”.)

More than 300 Sikorsky S-92s have been built in both civil and military variants since 1998. It remains in production, and has been selected as the next U.S. presidential helicopter, currently designated as VH-92A.

Sikorsky VH-92A

© 2019 Bryan R. Swopes

15 January 2009: “The Miracle on the Hudson”

U.S. Airways’ Airbus Industrie A320-214 N106US. (Bureau of Aviation Accidents Archives)

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 Chesley B. Sullnberger
Captain Chesley B. Sullenberger, U.S. Airways

Captain Sullenberger was a 1973 graduate of the United States Air Force Academy and had served as a pilot in McDonnell Douglas F-4 Phantom IIs until 1980, when he left the Air Force and began a career as an airline pilot with Pacific Southwest Airlines (PSA). 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 Jeffrey B. Skiles
First Officer Jeffrey B. Skiles, U.S. Airways

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.

Canada geese (Branta candensis maxima) in flight.
Canada geese (Branta canadensis maxima) in flight.

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.

Break Transcript

The cockpit of a U.S. Airways Airbus A320-214, N108UW, the same type airliner as the flown by Sullenberger and Skiles. Photograph © Quinn Savit. Used with permission.
The cockpit of a U.S. Airways Airbus A320-214, N108UW, the same type airliner flown by Sullenberger and Skiles. (Photograph © Quinn Savit. Used with permission.)

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.

15:29:55 Ground Proximity Warning System: PULL UP. PULL UP. PULL UP. PULL UP. PULL UP. PULL UP.

15:30:01 Skiles: Got flaps out.

15:30:03 Skiles: Two hundred fifty feet in the air.

15:30:04 Ground Proximity Warning System: TOO LOW. TERRAIN.

15:30:06 Ground Proximity Warning System: TOO LOW. GEAR.

15:30:06 Skiles: Hundred and seventy knots.

15:30:09 Skiles: Got no power on either one? Try the other one.

15:30:09 Radio from another flight: Two One Zero uh Forty-Seven-Eighteen. I think he said he’s going in the Hudson.

15:30:15 Ground Proximity Warning System: CAUTION TERRAIN.

15:30:16 Skiles: Hundred and fifty knots.

15:30:17 Skiles: Got flaps two, you want more?

15:30:19 Sullenberger: No let’s stay at two.

15:30:21 Sullenberger: Got any ideas?

15:30:22 LGA Departure Control: Cactus Fifteen-Twenty-Nine [sic] if you can uh. . . you got uh Runway uh Two Nine available at Newark it’ll be two o’clock and seven miles.

15:30:23 Ground Proximity Warning System: CAUTION TERRAIN.

15:30:23 Skiles: Actually not.

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.

End Transcript

Flight track of U.S. Airways Flight 1549. (National Transportation Safety Board)

Though air traffic controllers had made runways available at the three closest airports for an emergency landing, Flight 1549 did not have enough 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 door 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.

U.S. Airways Flight 1549 afloat in the Hudson River on the afternoon of 15 January 2009.
U.S. Airways Flight 1549 afloat in the Hudson River on the afternoon of 15 January 2009.

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 Airbus A320 N106US floating on the Hudson River, 15 January 2009. (Steven Day/AP/NBC News)

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).

Rescue operation of Cactus 1549, 15 January 2009. (Wikipedia)

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 series is still in production. As of 31 December 2018, 8,605 A320s had been built.

N106US remains in the condition that it was in when removed from the Hudson River. It i stored outside at the departure end of Runway 36C, Charlotte Douglas International Airport (CLT), Charlotte, North Carolina.

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.

U.S. Airways' Airbus A320-214 N106US on display at the Carolinas Aviation Museum, Charlotte, North Carolina. (RadioFan)
U.S. Airways’ Airbus A320-214 N106US was previously on display at the Carolinas Aviation Museum, Charlotte, North Carolina. The museum is not presently in operation and N106US is stored outside. (RadioFan)

© 2019, Bryan R. Swopes