NTSB Identification: LAX94FA323
HISTORY OF FLIGHT
On August 13, 1994, at 1331 Pacific daylight time, a civilian Lockheed C-130A, N135FF, operating as Tanker 82, impacted mountainous terrain near Pearblossom, California. The airplane was destroyed and the crew of three were fatally injured. The flight originated from Hemet-Ryan Airport (HMT), Hemet, California, at 1310. Visual meteorological conditions prevailed at the time of the accident, and a company flight plan was filed for the operation. The airplane was owned by Aero Firefighting Service Company, Inc., and operated by the U.S. Forest Service as a public use aircraft.
According to U.S. Forest Service personnel, the airplane was responding to a fire near the Tehachapi Mountains at the request of the California Department of Forestry. The crew was receiving flight following from High Desert TRACON (Joshua Approach Control) and the airplane's encoding altimeter was indicating 7,800 feet msl. A review of air traffic control communication tapes revealed two unidentified transmissions; one of an unintelligible squeal, followed by a brief expletive at 1331.
According to some witnesses, the airplane had been in level flight when a fireball and/or explosion occurred in the vicinity of the left-wing, inboard engine, followed by separation of the left wing. Other witnesses observed the right engine "blow," followed by a second explosion; and the airplane turned to the right. Witnesses further noted that the airplane "rolled," "rotated clockwise," "arc[ed] down to the right," and "barrel rolled" after the fire/explosion.
Witnesses also stated that the ground impact of the main wing and fuselage resulted in an additional fireball and explosion, and one witness stated that the smoke from the ground fire rose vertically in an undisturbed column.
The pilot, copilot, and flight engineer were rated in the airplane. A review of the pilot/operator accident report prepared by the operator revealed that the crew had current flight experience in the accident airplane. According to FAA inspectors, at the time of the accident, the flight was being operated in accordance with applicable regulations.
The airplane was delivered to the U.S. Air Force in December 1957. In April 1959, it was modified to become a C-130A-II, to perform an electronic reconnaissance mission. In September 1964, it was de-modified and reconfigured to a "near standard C-130A" and transferred to the Air National Guard. In August 1986, the airplane was transferred to Davis-Monthan Air Force Base for storage. In June 1988, it was removed from storage. In June 1990, modification as a restricted category firefighting aircraft was approved per FAA Form 337. A Restricted Category Special Airworthiness Certificate, which authorized aerial dispensing of fire retardant, was issued in May 1990.
A review of maintenance records revealed that on April 22, 1994, the airplane was returned to service after a progressive inspection cycle. The inspection program was an FAA approved and authorized aircraft inspection program (AAIP). The airplane completed an eddy current inspection in April 1991. All parts tested met the inspection standard. Investigators estimated that at the time of the accident, the airplane was within weight and balance limitations and had sufficient fuel to complete the planned flight.
On July 17, 1994, (the most recent record available) the operator completed a Day Off Inspection (seven-day check.) The records of subsequent checks were onboard the airplane and were destroyed.
According to recorded information from the Bureau of Land Management's Automatic Lightning Detection System (ALDS), there was lightning activity in the area of the accident site at the time of the crash. Witnesses, both on the ground and in the air near the accident site, reported that the airplane was clear of clouds and that there was no visible electrical activity at the time of the accident.
AIDS TO NAVIGATION
The impact site was located along an imaginary line connecting Hemet-Ryan Airport and Tehachapi, California. At 1330, the pilot reported to Joshua Approach Control that he intended to "go straight for the next 42 miles."
According to U.S. Forest Service officials, dispatch information included magnetic direction to the fire and distance from the departure airport, along with the latitude and longitude of the fire's location. The operator reported that the crew was familiar with the area and that the airplane was equipped with a global positioning system (GPS).
After takeoff, the crew initiated two-way radio contact with Ontario Approach Control. The crew responded to radio calls without delay or difficulty until 1330 (about 1.5 minutes before the accident.) All communications were routine with no indication of any in-flight problems.
WRECKAGE AND IMPACT INFORMATION
The wreckage was located in the San Gabriel Mountains, on the north face of Pleasant View Ridge, near Pechner Canyon, about the 6,500-foot level. The airplane's right wing was separated from the main wreckage.
A total of six center wing pieces, five pieces of the upper wing surface and one piece of stringer, were found approximately 1,000 feet in advance of the separated main wing. Numerous pieces of 1-inch-thick, yellow styrofoam, a green interior wing panel, and a torn portion of a fuel cell liner were also found in the same general area. None of the debris had been involved in the resulting ground fire. The styrofoam material was reported to have been located beneath the auxiliary fuel cell. Portions of the styrofoam exhibited evidence of surface charring. Light sooting of the wing pieces was consistent with normal service.
Crush on the separated right wing components indicated a near-level attitude at impact. The identification was made by serial numbered components recorded as being located on the right side of the airplane. Examination of the debris revealed an outline of a burned and melted main wing structure, extending from the right wing tip to a section inboard of the No. 3 engine nacelle. The ground fire melted or consumed all fracture surfaces on the inboard portion.
A teardown inspection of the No. 3 and 4 engines revealed no evidence of rotational scoring. Although the supporting structure was fractured or consumed by fire, the engines retained their relative positions on the right wing. The persistent odor of ammonia was detected in and about the No. 3 engine.
Both the No. 3 and 4 propellers and hubs were found separated from their engines. The No. 3 propeller was found at -10 degrees (full reverse) while the No. 4 propeller was found at 67 degrees, and its dome stop ring was found to be almost in the feather position. There was no bending, twisting, or leading edge damage on any blade from either the No. 3 or No. 4 hubs. Two blades from the No. 3 hub had been consumed by fire up to the blade root.
The main fuselage and remaining left wing impacted rising terrain. The impact resulted in major structural collapse and disintegration, and a fire.
The cockpit area was identified, but efforts to access the interior portion were unsuccessful. Attempts at an aerial recovery of the cockpit were also unsuccessful and resulted in disintegration of the structure.
The No. 1 and 2 engines were recovered, and both exhibited evidence of rotational scoring. Both engines were displaced from their position relative to the left wing. Crush of the engine cases indicated a near 90-degree terrain impact angle on both engines.
The No. 1 and 2 propellers and hubs were separated from the engines. None of the No. 1 or 2 propeller components were recovered.
MEDICAL AND PATHOLOGICAL INFORMATION
There was no autopsy or toxicological examination of any of the crewmembers.
The wreckage was released to a representative of the U.S. Forest Service on October 17, 1995.
On November 16-17, 2003, subsequent to two other fire tanker accidents, the wreckage was re-examined at the accident site. Sections of the center and right wings were removed, and transported to the Safety Board Materials Laboratory for further examination.
According to the Laboratory's factual report, three underside sections of the center and right wings, extending between center wing section (CWS) 180R to CWS 220R (just outboard the "rainbow fitting"), were received. Chordwise, the sections included material from stringers 14 through 20. Much of the material was blackened, and displayed extensive heat damage.
A visual examination of the fracture surfaces revealed that most had features consistent with overstress separation. However, on one center wing section, at CWS 186R, two fracture regions displayed thumbnail patterns, indicative of fatigue, and crack arrest marks that extended from the thumbnail regions. Both fatigue regions propagated at an approximately 15-degree angle to the chord.
The first fatigue region was found in lower wing skin, on a flat, 90-degree plane relative to the skin surface, and extended from a rivet hole between stringer 14 and 15, aft for about 0.6 inch, before transitioning to overstress. The region had been covered by a 9.6-inch-wide doubler that extended from the forward edge of stringer 14 to the aft edge of stringer 15.
The fatigue region forward of the rivet hole was not available for examination. The regions aft of the fatigue region, up to stringer 20, displayed features consistent with overstress. The rivet hole from which the fatigue region initiated appeared to have been created when the doubler was attached to the wing structure. Similar rivet holes were not found between other stringers.
Scanning electron microscope examination of the fatigue region revealed thumbnail-shaped arrest marks, with half-moon-shaped regions in between. The fine features on the fracture face were obliterated by fire and environmental damage.
Energy dispersive spectroscopy revealed that the area adjacent to the fatigue region had a composition consistent with 7075 aluminum with the addition of calcium.
Skin thickness in the fatigue region was 0.092 inch, and thickness of the doubler was approximately 0.063 inch.
The second fatigue region was found on a 45-degree slant plane in the doubler, adjacent to the skin panel fatigue region. The region was 0.8 inch in length, and displayed beach marks consistent with fatigue propagation aft, similar to the other fatigue region.
The fracture surface aft of the fatigue region exhibited features consistent with overstress. The fracture surface forward of the fatigue region (a region approximately 0.95 inch in length) was found on a flat, 90-degree plane relative to the surface of the doubler; however, the fracture features were obliterated.
According to Lockheed Study LG81ER0148, the forward underside region of the center wing, at CWS 185.5, was known to be susceptible to fatigue. However, the location was slightly aft of the area examined. In addition, the study cited that the critical size for a crack growing in the wing skin alone was 1.72 inches, while the critical size for a crack growing in the wing skin and stringer together was 0.86 inch.