Tag Archives: Aircraft Accident

28 November 1979, 00:49:50 GMT

Air New Zealand McDonnell Douglas DC-10-30 ZK-NZP at London Heathrow Airport, July 1977. (Eduard Marmet via Wikipedia)
Air New Zealand McDonnell Douglas DC-10-30 ZK-NZP at London Heathrow Airport, July 1977. (Eduard Marmet via Wikipedia)

28 November 1979: An Air New Zealand sightseeing flight to Antarctica, Flight TE 901, departed Auckland Airport (AKL) on the North Island of New Zealand, at 1917 GMT, 27 November (8:17 a.m., 28 November, local time). The flight was planned to proceed to the vicinity of McMurdo Station at the south end of Ross Island, off the continent of Antarctica, and then return to Christchurch International Airport (CHC) on New Zealand’s South Island. The duration of the flight was estimated to be 11 hours and would travel a total of 5,360 miles (8,626 kilometers), all during daylight hours.

Air New Zealand had previously flown thirteen Antarctic excursions. On this date, the airliner operated as Flight TE 901 was a five year old McDonnell Douglas DC-10-30, registration ZK-NZP. On board the airliner were a flight crew of five, cabin crew of fifteen and 237 passengers.

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Collins

The pilot in command (PIC) was Captain Thomas James Collins. Captain Collins held an airline transport pilot license with a DC-10 type rating. He had flown a total of 11,151 flight hours, of which 2,872 had been aboard DC-10s. Because of the flight’s planned duration, the crew included two more pilots, First Officer Gregory Mark Cassin and First Officer Graham Neville Lucas. There were also two flight engineers, Flight Engineer Gordon Barrett Brooks and Flight Engineer Nicholas John Maloney. All were very experienced pilots, type-rated in the DC-10. None, however, had previously flown the Antarctic route.

19 days before the flight, Captain Collins and First Officer Cassin had received an audio-visual briefing of the planned flight. They also flew the route in a cockpit simulator. The route of previous flights had taken the airliners from the Ross Sea into McMurdo Sound, well west of Ross Island and its 12,448 foot (3,794 meters) active volcano, Mount Erebus. At a pre-determined waypoint, the airliner turned left toward McMurdo Station. The airline’s minimum altitude through this area was 16,000 feet (4,877 meters) until south of McMurdo Station, and then only if certain weather conditions were present.

Air New Zealand flight planners had discovered that data which had been entered into the aircraft’s Area Inertial Navigation System (AINS) computer was incorrect. The coordinates of the for the destination waypoint were  actually 2˚10′ west of the intended destination waypoint. The intended route was to take TE 901 directly over Mount Erebus to the emergency whiteout landing area near Williams Field (ICAO: NZWD) about 10 miles (16 kilometers) from McMurdo Station on the Ross Ice Shelf. Because of the data error, however, all previous flights had approached from well west of Ross Island before turning toward McMurdo Station at West Dailey Island. The navigation data was corrected, but the flight crew had not been informed of the change or the reason for it.

DC-10 navigation console. (Unattributed)
DC-10 navigation console. (Unattributed)

The flight toward Antarctica proceeded normally. Exactly five hours after takeoff, Captain Collins began a descent from TE 901’s cruising altitude. At this point the airliner was approximately 140 miles (225 kilometers) north of McMurdo Station. First Officer Cassin advised air traffic control, Mac Center, of their descent. The controller acknowledged and gave the current weather at McMurdo as “. . . low overcast in the area at about 2,000 feet [607 meters] and . . . some snow but our visibility is still about 40 miles [64 kilometers]. . . .” In the cockpit, Captain Collins commented that the clouds were lower than previously reported, and that, it would be, “Very hard to tell the difference between the cloud and the ice.”

First Officer Cassin requested descent to 16,000 feet (4,877 meters) but Mac Center directed the flight to “descend and maintain Flight Level 180.” (18,000 feet/5,486 meters)

Over the next six minutes, TE 901 traveled 50 miles as it descended to FL 180. Radio transmissions during the let down were unclear, with Mac Center, Flight 901 and Ice Tower all trying to make contact. It is possible that the high terrain between the airliner and McMurdo Station was blocking the signals. The pilots discussed using other frequencies. Captain Collins and Flight Engineer Brooks discussed the airliner’s present weight and the minimum speed required, which was calculated to be 252 knots.

Satellite image of Ross Island. McMurdo Station is at the tip of the narrow peninsula in the lower left quadrant. (NASA)
Satellite image of Ross Island. McMurdo Station is at the tip of the narrow peninsula in the lower left quadrant. (NASA)
rossislandmap
Topographic map of Ross Island, Antarctica (1:250,000 scale) (USGS)

At 00:24:44, the DC-10’s Altitude Alert sounded, indicating that the airplane had reached the assigned altitude of Flight Level 180.

At 00:31:01, Captain Collins told the crew, “I’ll have to do an orbit here I think.” Seven seconds later, he said, “Well actually it’s clear out here if we get down. . .and—” Someone in the cockpit replied, “It’s not clear on the right hand side here.” First Officer Cassin said, “No.”

Captain Collins had observed an opening in the clouds to the left of the airplane, and decided to descend further under visual conditions. He first began a descending 360˚ turn to the right, followed by  a descending 180˚to the left. This put the DC-10 on a course away from McMurdo Station at 10,000 feet (3,048 meters). Captain Collins and the two flight engineers discussed the desired airspeed. With the flight still continuing outbound, at 00:42:49, Collins said, “We’re VMC [Visual Meteorological Conditions] around this way so I’m going to do another turn in.” The flight’s expert commentator, Peter Mulgrew, had entered the flight deck. Captain Collins said, “Sorry haven’t got time to talk but—” Mulgrew replied, “Ah well you can’t talk if you can’t see anything.” However, Mulgrew remained in the cockpit.

At 00:45:00, First Officer Cassin called McMurdo Center and reported, “. . . we are now at six thousand descending to two thousand and we’re VMC.”

Mount Erebus, the world's southernmost active volcano, with a height of 2,448 foot (3,794 meters). (Tattered Passport)
The world’s most southern active volcano, Mount Erebus on Ross Island, Antarctica, has a height of 12,448 feet (3,794 meters). (Tattered Passport)

Passing through 3,000 feet (914 meters), Flight Engineer Brooks asked, “Where’s Erebus in relation to us at the moment?” Someone answered, “Left about twenty or twenty-five miles.” Someone else asked, “Left do you reckon?” A voice said, “Well I don’t know—I think.” An unknown voice said, “I’ve been looking for it.” Cassin replied, “Yep, yep.” Brooks then said, “I’m just thinking of any high ground in the area, that’s all.”

Mulgrew replied, “I think it’ll be left, yes.” The second flight engineer, Nick Maloney, then said, “Yes, I reckon about here.”  Mulgrew answered, “Yes—no, no, I don’t really know.” Then at 00:47:02, he said, “That’s the edge,” probably indicating that he could see the edge of the ice sheet ahead.

At 00:47:06, a crewmember announced, “Down to two thousand.” Both Collins and Cassin acknowledged this, “Yes.” — “Yes.” The crew then set the flight director to hold airspeed and altitude.

At 00:47:43, Captain Collins said, “We might have to pop down to fifteen hundred here I think.” Cassin replied, “Yes, OK. . . Probably see further in anyway. . . It’s not too bad. . . I see vert speed for fifteen hundred feet.”

Flight Engineer Maloney said, “—It’s not right.” An unknown voice then said, “Bit thick here eh Bert?” Maloney replied, “Yeah my. . . . oath. . . (pause) You’re really a long while on . . . instruments this time are you?” Mulgrew then said, “I reckon Bird’s through here and—Ross Island there.” Maloney answered, “Yes,” and Mulgrew continued, “Erebus should be there.” Captain Collins says, “Right.” For the next forty seconds the crew discussed radio and navigation frequencies.

At 00:49:08, Mulgrew said, “That looks like the edge of Ross Island there.” Cassin attempted to contact McMurdo Tower. At 00:49:24, Maloney said, “I don’t like this.”

At 00:49:30, Captain Collins said, “We’re twenty-six miles north we’ll have to climb out of this.” Someone answered, “OK.” Cassin told Collins, “It’s clear on the right and (well) ahead.” Collins asked, “Is it?” Mulgrew said, “Yes.” Cassin, said, “No negative.” Cassin said, “No high ground if you do a one eighty.”

At 00:49:44 the airliner’s Ground Proximity Warning System is heard: WHOOP WHOOP—PULL UP—WHOOP WHOOP

00:49:48 Flight Engineer Brooks reports, “Five hundred feet.”

PULL UP

Brooks: “Four hundred feet.”

WHOOP WHOOP—PULL UP—WHOOP WHOOP

Captain Collins calls, “Go round power please.”

WHOOP WHOOP—PULL

At 00:49:50 GMT, ZK-NZP struck gradually rising terrain at an elevation of 1,467 feet (447 meters) above Sea Level, while flying at 260 knots (299 miles per hour/482 kilometers per hour). The DC-10 was totally destroyed and all 257 persons on board were instantly killed by the impact. The site of the crash was on the north slope of Mount Erebus, approximately 31 miles (50 kilometers) north of McMurdo Station, at Latitude 77˚25’30” South, Longitude 167˚27’30″East.

The navigation computer showed teh position of Flight 901, farther south and slightly left of its actual track—closer to Mount Erebus.
The navigation computer showed the position of Flight 901 a few miles farther to the south and slightly left of its actual track—closer to Mount Erebus. (Transport Accident Investigation Commission)
This detailed graphic shows the flight path an descent of Flight 901 and correlates the FDR data to give an idea of where the airplane actually was and where the crew thought it was..
This detailed graphic shows the flight path and descent profile of Flight TE 901 and correlates CVR and FDR data to give an idea of where the airplane actually was and where the crew thought it was. (Transport Accident Investigation Commission)
Crash site of Air new Zealand Flight 910 on teh slopes of Mount Erebus, Antarctica. (Bereau d'Archives des Accidents d'Avions)
Looking west at the crash site of Air New Zealand Flight TE 910 at an elevation of 1,467 feet (447 meters) above Sea Level, on the north slope of Ross Island, Antarctica. Mount Erebus is at the upper left of the photograph. The terrain has a gradual upward slope of 13˚, and cross slope, right to left, of -5˚. The debris field is aligned on a heading of 190˚ True and is approximately 570 meters long. (Bureau d’Archives des Accidents d’Avions)

The intensive investigation of the accident showed that, based on the route briefing, the flight crew expected to be about 26 miles to the west. In fact, TE 901 had proceeded almost precisely along the planned track. Analysis of the navigation computer showed that its INS position was in error by just 3.1 nautical miles (3.6 miles/ 5.7 kilometers), well within its known tolerance. It was indicating almost the exact location of the flight, if anything, closer to Mount Erebus than it really was.

Much controversy ensued over who was at fault for the position error. Regardless of whether the flight was on the intended track, or on the erroneous track 25 miles west, the crew was fully aware that they were well north of McMurdo Station. Air New Zealand had established a minimum safe altitude of 16,000 feet (4,877 meters) until the flight was south of McMurdo.

3.37     Probable cause: The probable cause of this accident was the decision of the captain to continue the flight at low level toward an area of poor surface and horizon definition when the crew was not certain of their position and the subsequent inability to detect the rising terrain which intercepted the aircraft’s flight path.

AIRCRAFT ACCIDENT REPORT No. 79-139, Transport Accident Investigation Commission (TAIC), New Zealand, Section 3.37 at Page 34.

ZK-NZP was a McDonnell Douglas DC-10-30, s/n 46910, built at the Douglas Aircraft Company’s Long Beach, California, plant during November 1974. It arrived in New Zealand 14 December 1974 for service with Air New Zealand Limited. The –30 was a long range variant of the DC-10 series. It is designed to be operated by a flight crew of three. It is 182 feet, 1 inch (55.499 meters) long with a wingspan of 165 feet, 5 inches (50.419 meters) and overall height of 58 feet, 1 inch (17.704 meters.) One of the original “wide body” jets, the cylindrical fuselage of the DC-10 has a diameter of 19 feet, 9 inches (6.020 meters).

The DC-10-30 was powered by three General Electric CF6-50C turbofan engines, rated at 51,000 pounds of thrust (226.86 kilonewtons) at Sea Level. The CF6-50 is a two-spool, high-bypass-ratio axial-flow turbofan engine. It has a single-stage fan section, with a 17-stage compressor (3 low- and 14 high-pressure stages, and a 6-stage turbine (2 high- and 4 low-pressure stages). The CF6-50C has a maximum diameter of 8 feet, 9.0 inches (2.667 meters), fan diameter of 7 feet, 2.4 inches (2.195 meters) and length of 15 feet, 8.0 inches (4.775 meters). It weighs 7,896 pounds (3,582 kilograms).

The DC-10-30 has an empty weight of 266,191 pounds (120,742 kilograms) and maximum takeoff weight of 572,000 pounds (259,455 kilograms). ZK-NZP, operating as Flight TE 901, had an “all-up weight” of 199,150 kilograms (439,051 pounds), and for the conditions of this flight, the MTOW was calculated to be 253,105 kilograms (558,001 pounds). It’s actual takeoff weight was 246,507 kilograms (543,455 pounds).

The typical cruise speed of the DC-10 is 0.82 Mach (556 miles per hour, or 895 kilometers per hour, at 30,000 feet/9,144 meters) and its service ceiling is 42,000 feet (12,802 meters). The DC-10-30 variant has a maximum range of 6,600 miles (10,622 kilometers).

At the time of the accident, ZK-NZP had flown 20,763 hours since new (TTSN).

The largest remaining fragment of McDonnell Douglas DC-10-30 ZK-NZP was this portion of the fuselage and wings.
The largest remaining fragment of McDonnell Douglas DC-10-30 ZK-NZP was this portion of the fuselage and wings. (AP Images)

© 2016, Bryan R. Swopes

24 November 1959

Trans World Airlines’ Lockheed L-1049H Super Constellation N102R at Frankfurt, Germany, 1959. (Erich Marek)

24 November 1959: At 5:35 a.m., Central Standard Time, Trans World Airlines Flight 595, a Lockheed L-1049H Super Constellation freighter, N102R, crashed into a residential area about ¼-mile (0.4 kilometer) to the southeast of Midway Airport (MDW), Chicago, Illinois.

“How disabled plane, whose pilot tried to return to airport, crashed into homes on southwest side in holocaust of destruction.” —Chicago Tribune, Vol. CXVIII, No. 282, Wednesday, 25 November 1959, Page 3, columns 5–8)
(L–R) Auge, Helwig, Watters.

N102R had departed Midway Airport at approximately 5:31 a.m., Central Standard Time (11:31 UTC), en route to Los Angeles, California. The flight crew were Captain Claude Wilbert Helwig, First Officer Delmas Earl Watters, and Flight Engineer Aerion Lyman Auge, Jr.

A weather observation made ten minutes before takeoff reported the sky partially obscured, scattered clouds at 600 feet (183 meters), measured 900 foot (274 meters) overcast; visibility 3 miles (4.8 kilometers), with light rain, fog and smoke. The wind was 10 knots (5.14 meters per second) temperature 39 °F. (3.8 °C.) and dew point 38 °F. (3.3 °C.).

1 minute, 20 seconds after takeoff, the flight crew reported to the control tower that that they had a fire warning for the airplane’s number 2 engine (inboard, left wing) and that they would return to the airport. The tower cleared Flight 595 to land on Runway 31L. [Today, this runway is 31C.] The controller asked if they wanted to use a localizer approach, and received the answer, “I think we’ll make it VFR, OK,” meaning that the crew intended to remain in visual conditions below the overcast.

Ground track of TWA Flight 595, 24 November 1959. (Civil Aeronautics Board)

According to the accident investigation report,

      In the turn to final approach to runway 31 the aircraft banked in excess of 45 degrees during which it developed an excessive rate of sink. When the aircraft reached the tops of the trees its wings were nearly level and its nose was raised in a climbing attitude; however, the descent continued. The wing flaps were being retracted during the last 5 to 10 seconds of the final descent and were found to be symmetrically extended at 24 percent upon impact.

A controller saw the airplane crash into the residential area. The time was established by the time of the power failure caused when the Super Constellation hit the Commonwealth Edison Company power lines.

The three members of the flight crew and 11 people of the ground were killed. Another 11 people were injured.

Investigators found that the number 2 engine had been shut down and its propeller feathered, but there was no evidence of any inflight fire.

The investigative board found the the flight crew’s decision to remain below the clouds was reasonable under the circumstances.

     In anticipation of landing, a gear-down, flap-extended configuration was established on the downwind portion of the traffic pattern. The wing flaps were at least in the takeoff position of 60 percent and had been allowed, presumably to remain so extended since takeoff, because less than one minute had elapsed from the start of the takeoff roll until the fire warning, and at that time the captain planned to return to land. The track over the ground on the “downwind” curved toward the runway. When the aircraft was positioned to start the turn to final approach a sharp turn was needed to avoid overshooting the extended centerline of runway 31L.

     The Board believes the captain attempted such a turn, and in doing so combined a very steep bank with high gross weight ¹ and three-engine aircraft configuration in such a manner that the aircraft entered a regime of flight describable as being on the backside of the power curve. More power and altitude than was available to him was needed to safely recover the aircraft At some point in this turn the captain very probably decided to discontinue the landing approach and attempted to “go-around.” Hence, he called for gear up at or near this same point, but for an unexplained reason the wing flap controls were positioned for flap retraction.

The nose landing gear and left main gear assemblies were found to be in the up position but unlocked, and the right main gear was up and locked. The wing flaps were extended symmetrically at about 24 percent of their full travel. The flap control valve and follow-up mechanism were positioned to raise the flaps. The cockpit flap control lever was found to be about 1/8-inch (3.2 millimeters) aft of the full up position, with the lever bent over 80 degrees to the left. There was no indication that the lever had been forcibly moved fore or aft.

Wreckage of Lockheed L-1049H Super Constellation N102R in a hangar at Chicago Midway Airport 25 November 1959. (Civil Aeronautics Board)

The Civil Aeronautics Board determined that the Probable Cause of the accident was

     . . . the maneuvering of the aircraft in a manner that caused it to develop an excessive rate of sink in the turn to final approach.

Lockheed L-1049 Super Constellation three-view illustration with dimensions. (Lockheed Aircraft Corporation)

The L-1049 series was 18 feet, 4 inches (5.588 meters) longer than the preceding L-749 Constellation, with cylindrical “plugs” installed fore and aft of the wing. The L-1049H was the final commercial variant of the Super Constellation series. It could be converted from a passenger airliner to an air freighter configuration in a few hours. The L-1049 was 113 feet, 3.7 inches (34.536 meters) long, with a wingspan of 123 feet, 0 inches (37.490 meters), and overall height of 24 feet, 9.5 inches (7.557 meters). The fuselage had a maximum diameter of 11 feet, 7½ inches ( meters).

The total wing area was 1,650 square feet (153.3 square meters). The wings’ leading edges were swept aft 7° 28.7′, while the trailing edges swept forward 3° 13′. They had 7° 36.6′ dihedral.

Factory cutaway Wright Aeronautical Division 988TC18 turbocompound engine. (Aircraft Engine Historical Society)

N102R was powered by four air-cooled, direct-fuel-injected, 3,347.662 cubic-inch-displacement (54.858 liters) Wright Aeronautical Division 988TC18EA3 Duplex Cyclone turbocompound engines with a compression ratio of 6.70:1. The turbocompound engine used captured exhaust gases to drive three Power Recovery Turbines. These PRTs were coupled to the engine’s crankshaft. This system added approximately 450 horsepower to the engine’s total power output.

The 988RC18EA3 had Normal Power ratings of 2,860 horsepower at 2,650 r.p.m. at Sea Level; 2,920 horsepower at 2,650 r.p.m. at 4,800 feet (1,463 meters); 2,450 horsepower at 2,600 r.p.m. at 16,400 feet (4,999 meters). Its Maximum Power ratings were 3,400 horsepower at 2,900 r.p.m. to 4,000 feet (1,219 meters) for Take Off; and 2,600 horsepower at 2,600 r.p.m. at

The engines turned three-bladed Hamilton Standard propellers through a 0.4375:1 propeller gear reduction. The reduction gears were strengthened to support 4,000 horsepower. The Wright 988TC18EA3 was 7 feet, 5.53 inches (2.274 meters) long, 4 feet, 8.59 inches (1.473 meters) in diameter, and weighed 3,640 pounds, ± 1% (1,651 kilograms).15,200 feet (4,633 meters). 115/145-octane aviation gasoline was required.

The L-1049 had a maximum speed for normal operations (VNO) of 260 knots (299 miles per hour/482 kilometers per hour) and a maximum speed (VNE) of 293 knots (337 miles per hour/543 kilometers per hour) up to 11,000 feet (3,353 meters). VNO was reduced by 9 knots, and VNE reduced by 11 knots, for each 2,000 foot (610 meters) increase in altitude above 11,000 feet.

The maximum operating altitude for the L-1049 was 25,000 feet (7,620 meters). Its maximum range was 4,140 miles (6,663 kilometers).

N102R had a manufacture date of 6 June 1957. When it went through a scheduled overhaul 8 March 1959, it had accumulated 3,432:08 hours of flight time.

Claude Wilbert Helwig was born 9 July 1919 in San Francisco, California. He was the son of Henry Wilbert Helwig, a truck driver, and Mina Helwig Borchard. He attended Balboa High School in San Francisco, graduating in 1937.

Helwig enlisted in the United States Army Air Forces 12 March 1941. He had brown hair, gray eyes, a light complexion, was 5 feet, 8 inches (178 centimeters) tall and weighed 133 pounds (60 kilograms). Helwig was honorably discharged 9 March 1943 and was commissioned as a second lieutenant, Air Corps, Army of the United States (AUS), 10 March 1943. he was assigned to in the 14th Troop Carrier Squadron, 61st Troop Carrier Group.

Lieutenant Helwig married Miss Josephine Crull at Crow Creek Township, North Carolina, 20 May 1943. The ceremony was performed by J.W. Johnson, Justice of the Peace.

Following World War II, Helwig remained in the U.S. Air Force Reserve, serving with the rank of captain. He was discharged 1 April 1953. Captain Helwig had been awarded the Air Medal with 13 oak leaf clusters (14 awards). Captain Helwig’s remains were interred at Glen Oaks Memorial Park, Chico, California.

Delmas Earl Watters was born at Estill Springs, Tennessee, 30 November 1922. He was the son of Earl Watters, a locomotive fireman,  and Annabelle Smith Watters.

He attended Tennessee Technological University, Cookeville, Tennessee.

Watters enlisted as an aviation cadet in the United States Navy, 9 December 1942, at Atlanta, Georgia. He entered pre-flight school at Athens, Georgia, 1 May 1942, then underwent flight training at Corpus Christi, Texas. His enlistment was terminated to accept a commission as an ensign, United States Navy Reserve, 26 December 1944.

Ensign Watters married Miss Theda Jeanne McMillan in King County, Washington, 30 December 1945. The ceremony was performed by J. Robert Walter of the Central Presbyterian Church, Seattle, Washington. They later divorced.

Ensign Watters was promoted to the rank of lieutenant (junior grade), 1 January 1947.

Watters later transferred to the United States Air Force with the rank of first lieutenant. During the Korean War, he was awarded the Distinguished Flying Cross with one oak leaf cluster (two awards).

Watters married Miss Jean Ruth Cleere at the Chapel of Roses, Pasadena, California, California, 30 December 1951. They would have one son.

First Officer Watters’ remains were interred at the Mountain View Cemetery and Mausoleum, Altadena, California.

Aerion Lyman Auge, jr., was born 8 June 1924 in Jefferson, Kentucky. He was the son of Aerian Lyman Auge, an electrician, and Isabelle Veronica Jahn Auge.

Auge served in the United States Navy during World War II.

Auge married Yvonne Easton in Pierce County, Washington, 19 April 1946. They would have three daughters. Flight Engineer Auge’s remains were interred at the Inglewood Park Cemetery, Inglewood, California.

Thanks to TDiA reader George Firis for suggesting this subject. Mr. Firis’s aunt lived in an apartment building that was destroyed.

¹ The computed allowable gross takeoff weight for this flight was 127,400 pounds (57,788 kilograms). At departure, the aircraft weighed 126,606 pounds (57,428 kilograms). The allowable landing weight was 115,000 pounds (52,163 kilograms).

© 2024, Bryan R. Swopes

22 November 1944

Consolidated PB4Y-2 Privateer. (U.S. Navy)
Consolidated Vultee PB4Y-2 Privateer. (U.S. Navy)

22 November 1944: At Lindbergh Field, San Diego, California, a brand new Consolidated Vultee PB4Y-2 Privateer, Bu. No. 59554, took off on its first test flight. A company crew of six men were aboard.

Shortly after takeoff at 12:20 p.m., the left outboard wing of the airplane separated. The airplane immediately went out of control and crashed near a residential area in Loma Portal, a short distance west of the airfield. The wing panel struck the roof of a house at 3121 Kingsley Street. All six crew members were killed. The house was occupied but there were no persons injured inside.

The wreck of Consolidated PB4Y-2 Privateer, Bu. No. 59554, burns on a hillside west of Lindbergh Field, 22 November 1944. (U.S. Navy)
The wreck of Consolidated Vultee PB4Y-2 Privateer Bu. No. 59554 burns on a hillside west of Lindbergh Field, 22 November 1944. (U.S. Navy via EAA Warbirds of America)

Members of the bomber’s flight crew included Marvin Rea Weller, Robert Vencil Skala, Clifford Polson Bengston, and Rans Raymond Estis.

The left outer wing panel of PB4Y-2 Bu. No. 59554 struck the roof of the residence at 3121 Kingsley Street, Loma Portal, San Diego. It came to rest in the front yard. (U.S. Navy)
The left outer wing panel of PB4Y-2 Bu. No. 59554 struck the roof of the residence at 3121 Kingsley Street, Loma Portal, San Diego. It came to rest in the front yard. (U.S. Navy via EAA Warbirds of America)

The wing section was recovered and the cause of the separation was quickly discovered. 98 of the 102 bolts which secured it to the inner wing section had never been installed. Two workers who were responsible for installing these missing bolts, and two inspectors who had signed off the work as having been properly completed, were fired.

This photograph of 59544's outer left wing shows the position of the 98 missing attachment bolts. (U.S. Navy)
This photograph of 59544’s outer left wing shows the position of the 98 missing attachment bolts. (U.S. Navy via EAA Warbirds of America)

The Consolidated Vultee PB4Y-2 Privateer was a long range heavy bomber produced for the United States Navy during World War II for patrol, anti-shipping/anti-submarine and bombing missions against Japanese installations on the remote islands of the vast Pacific Ocean area. The Privateer was developed from the Consolidated B-24 Liberator (which was designated PB4Y-1 in U.S. Navy service).

The PB4Y-2 was normally operated by a combat crew of 11–13 men. It was 74 feet, 7 inches (22.733 meters) long with a wingspan of 110 feet (33.528 meters) and overall height of 30 feet, 1½ inches (9.182 meters). The bomber had an empty weight of 39,400 pounds (17,872 kilograms) and its maximum takeoff weight was 64,000 pounds (29,030 kilograms).

A Consolidated Vultee PB4Y-2 Privateer in flight. The aft dorsal turret is aiming directly at the camera. (United States Navy)
Consolidated Vultee PB4Y-2 Privateer, Bu. No. 59602, in flight. The aft dorsal turret is aiming directly at the camera. (United States Navy)

The PB4Y-2 was powered by four 1,829.39-cubic-inch-displacement (29.978 liter) air-cooled, supercharged Pratt & Whitney R-1830-94 two-row 14-cylinder radial engines. The turbosuperchargers installed on B-24s were deleted, as high altitude operation was not required by the Navy. The R-1830-94 had a Normal Power rating of 1,100 horsepower at 2,600 r.p.m. to 7,500 feet (2,286 meters), and 1,000 horsepower at 2,600 r.p.m., at 14,700 feet (4,481 meters). The Military Power rating was 1,350 horsepower at 2,800 r.p.m. to 2,000 feet (610 meters), and 1,100 r.p.m. at 2,800 r.p.m. to 13,750 feet (4,191 meters). The engines drove three-bladed Hamilton Standard propellers through a 16:9 gear reduction. The R-1830-94 was 4 feet, 0.40 inches (1.229 meters) in diameter, 4 feet, 11.63 inches (1.515 meters) long and weighed 1,573 pounds (714 kilograms).

A Consolidated Vultee PB4Y-2 Privateer in flight, circa 1945. (U.S. Navy)
Consolidated Vultee PB4Y-2 Privateer, Bu. No. 59602, in flight, circa 1944. (U.S. Navy)

The PB4Y-2 Privateer had a cruise speed of 158 miles per hour (254 kilometers per hour) and a maximum speed of 249 miles per hour (401 kilometers per hour) at 12,000 feet (3,658 meters). Its service ceiling was 18,300 feet (5,579 meters) and maximum range of 2,900 miles (4,667 kilometers).

Defensive armament for the Privateer consisted of twelve .50-caliber Browning M2 machine guns mounted in six powered turrets. The maximum bomb load was 8,000 pounds (3,629 kilograms).

This aerial photograph of Lindbergh Field, San Diego, California, shows the location of the PB4Y-2 crash site, and nearby, the position where the outer wing panel was found. (U.S. Navy)
This aerial photograph of Lindbergh Field, San Diego, California, shows the location of the PB4Y-2 crash site, and nearby, the position where the outer wing panel was found. (U.S. Navy via EAA Warbirds of America)

The most distinctive visual difference between the B-24/PB4Y-1 Liberator and the PB4Y-2 Privateer is the substitution of a single tall vertical fin for the two outboard oval-shaped fins and rudders of the earlier design. Those two fins blocked the view of gunners as they scanned the skies and oceans. Testing by Ford, the major producer of B-24 Liberators, found that a single large vertical fin also provided better stability. A second identifying characteristic of the Privateer are the gun turrets. A large, spherical, Engineering and Research Corporation (ERCO) ball turret was installed in place of the B-24’s Emerson turret at the nose. Two Martin turrets were placed on top of the fuselage rather than one on the B-24. Two teardrop-shaped ERCO power turrets replaced the open waist gun positions of the Liberator and because they could converge directly under the bomber, eliminated the need for a belly-mounted ball turret.

Consolidated-Vultee PB4Y-2 privateer. (U.S. Navy)

739 PB4Y-2 Privateers were accepted by the U.S. Navy in 1944–1945. Bu. No. 59544 was deleted from the production contract and payment for that airplane was deducted from the total paid to Consolidated Vultee. The Privateers remained in service with the U.S. Navy until 1954 and with the United States Coast Guard until 1958. Two remain airworthy today, Bu. No. 66300, at the Yanks Air Museum, Chino, California, and Bu. No. 66302, at Goss Hawk Unlimited, Inc., Casa Grande, Arizona. Another six are on display.

Consolidated PB4Y-2 Privateer Bu. No. 66302 at Casa Grande, Arizona. (Goss Hawk Unlimited, Inc.)

The pilot of the Privateer was Marvin Rea Weller. Weller had a ruddy complexion, brown hair and eyes, was 5 feet, 10 inches (1.78 meters) tall, and weighed 143 pounds (65 kilograms). He was born at Augusta, Virginia, 8 August 1919, the fourth of five children of Walton Tobias Weller, a farmer, and Mayna Rea.

Weller graduated from Mt. Sidney High School in Fort Defiance, Virginia, and then attended the Augusta Military Academy, 1937–38.

Marvin Weller was taught to fly by H. P. Grim, Jr., at Staunton Airport, a small airfield five miles northeast of Staunton, Virginia, in 1937. He was then employed as an assistant instructor and flew for a locally-based airline. Later, Weller worked as a flight instructor at Georgia Aero Tech in Augusta, and the Ryan School of Aeronautics at San Diego, California. Both schools provided basic and primary flight instruction for the U.S. Army Air Corps.

Weller married Miss Audrey Lorraine Brubeck of Staunton, 27 April 1941, at Fort Defiance, Virginia. They lived in San Diego.

Marvin Weller had been employed as a test pilot and aircraft commander by Consolidated-Vultee for two-and-a-half years at the time of his death.

The funeral of Marvin Rea Weller was presided by Rev. J.M. McBryde, who married Mr. and Mrs. Weller three years earlier. His remains were interred at the Thornrose Cemetery, Staunton, Virginia.

© 2022, Bryan R. Swopes

22 November 1933

Kalinen K-7
К-7 на аэродроме (“K-7 at the airport”), right front quarter view. (Уголок неба)

22 November 1933:

The K-7 Disaster

     On Wednesday, November 22, the Russian aircraft K-7, claimed to be the largest landplane in the world, crashed near Kharkhoff, 420 miles south-west of Moscow. Fourteen lives were lost. It is reported that M.K.A. Kalinin, the designer and director of the Kharkhoff aeroplane works, and Snegeriff, one of the best-known pilots in Russia, are among the dead. It seems that sabotage is suspected by the authorities, for the O.G.P.U. (Soviet secret police) is represented on the commission of experts investigating the disaster. Twenty trial flights had been successfully made before the crash.
 

     The design and construction of the K-7 took five years. She had a span of 208 ft., weighed about 20 tons and accommodated 120 passengers. She was considered a big stride forward in the approach to the “all-wing” aircraft, and most of the accommodation and equipment was in the wing. A few days before the accident the existence of the K-7 was revealed to the general public by “Pravda.” It was declared that the aircraft represented a “victory of the utmost political importance,” as she was constructed entirely of Soviet steel from the mills at Duiepropetrovsk. Hitherto Russia had [imported] materials for her aircraft.

—The Aircraft Engineer, Supplement to FLIGHT, 30 November 1933, at Page 1201.

The K-7 was designed by Konstantin Alekseevich Kalinin and built over a two-year period at the Kharkov State Aircraft Manufacturing Company factory at Kharkov, Ukraine. It was intended as either a heavy bomber in military service or as a civil transport. The K-7 was the largest airplane built up to that time.

К-7 в полете (“K-7 flight”) (Уголок неба)
К-7 в полете (“K-7 flight”) (Уголок неба)
Константин Алексеевич Калинин

The K-7 was an effort to perfect a “wing only” aircraft. The tail surfaces were supported by tail booms. It was operated by a crew of 11 and could carry up to 120 passengers in compartments inside the wings. The K-7 was 28.00 meters (91 feet, 10.4 inches) long with a wingspan of 53.00 meters (173 feet, 10.6 inches). The extremely large wing had an area of 254.00 meters².

As originally built the airplane was powered by six 2,896.1-cubic-inch-displacement (47.459 liter) liquid-cooled, supercharged, Mikulin AM-34 single overhead cam (SOHC) 60° V-12 engines mounted in nacelles on the leading edge of the wing. The engines were rated at 750 horsepower, each, and drove two-bladed propellers. When it was determined that power was insufficient, a seventh and then an eighth engine were added to the trailing edge in pusher configuration.

The K-7 had an empty weight of 21,000 kilograms and maximum weight of 40,000 kilograms. It’s cruise speed was 204 kilometers per hour (127 miles per hour) and the maximum speed was 234 kilometers per hour (145 miles per hour). The service ceiling was 5,500 meters (18,045 feet) and the range was 1,000 kilometers (621 miles).

In military configuration, the K-7 would be armed with 20 mm cannon and 7.62 mm machineguns. A bomb load of up to 16,000 kilograms (35,274 pounds) would be carried.

Cамолет К-7

The Kalinin K-7 made only 7 test flights before it crashed. 15 of the 20 persons aboard were killed. Kalinin was not among the dead, as had been report by Flight in the article above. One of the two tail booms failed. Some suggested that sabotage was involved. A government commission determined that the structure of the tailbooms was sufficiently strong, but that oscillations induced by aerodynamic flutter led to the failure.

During World War I, Konstantin Kalinin was awarded the Order of Sv.Stanislav. He had been given the Order of the Red Banner of Labor in 1935. However, during the Stalin purges, on 23 October 1938, he was executed as an enemy of the state.

Kalinen K-7
К-7 на аэродроме (“K-7 at the airport”), left front quarter view with engines running. (Уголок неба)

© 2018, Bryan R. Swopes

20 November 1940

North American Aviation's NA-73X fighter prototype, engine idling, with Vance Breese in the cockpit at Mines Field, Los Angeles, 26 October 1941. (North American Aviation Inc.)
North American Aviation’s NA-73X fighter prototype, engine idling, with Vance Breese in the cockpit at Mines Field, Los Angeles, 26 October 1940. (North American Aviation Inc.)

20 November 1940: North American Aviation’s Chief Test Pilot, Paul Baird Balfour, made his first flight in the NA-73X, NX19998, prototype for a Royal Air Force fighter, the Mustang Mk.I.

Vance Breese was the free-lance test pilot who made the first seven flights in the new airplane. Breese claimed to have made a bet with North American executives that Balfour would crash the prototype on his first flight.

Paul B. Balfour (1908–1951). This is Balfour’s NAA employee file card. (North American Aviation Inc.)

This flight was scheduled to be a high speed test. Edgar Schmued, the designer, offered to show Balfour around the airplane. “Before this flight, I asked Balfour to get into the airplane and go through the routine of a takeoff and flight. He responded that one airplane is like another and he would not need the routine checkout.”

The ground crew started the NA-73X’s 1,150 horsepower Allison V-1710-39 liquid-cooled V-12 engine at 5:40 a.m. and let it warm up to normal operating temperature. When it was restarted just prior to Paul Balfour’s flight, “it was a little hard to start,” according to Olaf Anderson, the airplane’s mechanic.

The prototype Mustang, NA-73X, lies upside down in a plowed field, 20 November 1941. (North American Aviation Inc.)
The prototype Mustang, NA-73X, lies upside down in a plowed field, 20 November 1940. (North American Aviation Inc.)

Balfour took off from Mines Field at about 7:10 a.m. After about twelve minutes of flight, the Allison stopped running. Balfour was too far from Mines Field to make it back to the runway. He landed in a plowed field west of Lincoln Boulevard. When the tires hit the soft surface, the prototype flipped over. Balfour was not hurt and was able to crawl out of the upside-down wreck.

The Civil Aeronautics Board report described the damage as “engine housing broken, both wingtips damaged, tail surfaces damaged, top of fuselage damaged, and other miscellaneous damage.” The NA-73X had accumulated just 3 hours, 20 minutes of flight.

Vance Breese won his bet.

Paul Balfour was not injured in the crash landing, but the NA-73X prototype was significantly damaged. (North American Aviation Inc.)
Paul Balfour was not injured in the crash landing, but the NA-73X prototype was significantly damaged. (North American Aviation Inc.)

According to the C.A.B. investigation, the engine had stopped due to fuel starvation when Balfour neglected to select another tank.

The prototype was taken back to the factory and rebuilt. It would become the famous Mustang, one of the most significant aircraft of World War II.

Damage to the wingtips, tail surfaces, fuselage. (North American Aviation Inc.)
Damage to the wingtips, tail surfaces, fuselage. (North American Aviation Inc.)

Robert C. Chilton was hired as the new Chief Test Pilot. He would continue testing the Mustang developments throughout the war. Chilton made his first flight in NA-73X on 3 April 1941.

The Mustang prototype was hoisted out of the plowed field and taken back to the factory where it was rebuilt. (North American Aviation Inc.)
The Mustang prototype was hoisted out of the plowed field and taken back to the factory where it was rebuilt. (North American Aviation Inc.)

Paul Balfour continued to work for North American Aviation, testing the NA-40 and NA-40B prototypes and the B-25 Mitchell medium bomber. He later served in the United States Air Force.

Paul Baird Balfour was born 5 July 1908 in Washington State. He was the son of Fred Patrick Balfour and Edna May Baird Balfour. Balfour attended two years of college.

Paul Balfour entered the U.S. Army Air Corps (prior to 1930). He was stationed at Rockwell Field, San Diego, California.

Balfour married Martha Lillette Cushman of Coronado, California, at Yuma, Arizona, 6 June 1930.

Balfour began working as a test pilot for North American Aviation, Inc., 1 March 1936.

On 2 July 1938, he married Lois Tresa Watchman at Kingman, Arizona. They would have two children.

Paul B. Balfour, center, with a North American Aviation B-25 Mitchell medium bomber. (Photograph courtesy of Neil Corbett, Test and Research Pilots, Flight Test Engineers)
Paul B. Balfour, center, with a North American Aviation B-25 Mitchell medium bomber. (Photograph courtesy of Neil Corbett, Test and Research Pilots, Flight Test Engineers)

On 9 November 1951, Major Paul B. Balfour, U.S. Air Force, attached to the 1002nd Inspector General Group at Norton Air Force Base, California, was flying a North American VB-25J, 44-30955, a transport conversion of a B-25J-30-NC Mitchell medium bomber.

Shortly after takeoff, at about 10:00 a.m., the airplane developed engine trouble. Unable to return to Norton, Balfour attempted a belly landing at a small private airfield. Witness saw that the airplane’s left engine was idling, and its propeller was feathered. As he approached, the airplane was blocked by a windbreak of eucalyptus trees bordering U.S. Route 66. Balfour banked away from the trees but the B-25 crashed in an orange grove along Bloomington Avenue in Rialto, approximately 7 miles (11 kilometers) west of Norton.

Balfour, still buckled in his seat, was thrown clear of the burning wreck and landed in the street. One man on board was killed and two others seriously injured. Balfour died in a hospital three hours later. He was 41 years old. Major Balfour was buried at the Inglewood Park Cemetery, Inglewood, California.

Burning wing of North American VB-25J 44-30955, near Rialto, California, 9 November 1951.
Burning wing of North American VB-25J 44-30955, near Rialto, California, 9 November 1951.

© 2016, Bryan R. Swopes