Gallup, NM, USA
N573B
Piper PA-31P
While maneuvering during a precautionary landing with the right engine shutdown, the airplane entered a Vmc roll and an uncontrolled descent, and impacted wires, trees, and terrain. According to air traffic control communications, while en route the pilot experienced a rough running right engine and performed a precautionary shutdown of the engine. The pilot elected to divert to an airport and received vectors from air traffic control for a visual approach. Witnesses who were located at the airport reported the airplane was on a normal downwind for the runway. When the airplane reached the approach end of the runway, the pilot turned to the right which was away from the airport. A witness who was monitoring the UNICOM frequency informed the pilot he was turning away from the airport and the pilot responded, "Busy." The airplane continued the right turn subsequently entered a Vmc roll and a rapid descent toward the terrain. The airplane wreckage was located on hilly, rocky terrain approximately 3 miles south of the airport. The airplane was fragmented and destroyed during the impact sequence and post-impact fire. Examination of the airframe and propellers revealed no anomalies that would have precluded normal operations. Examination of the left engine revealed the forward gearbox was destroyed and mechanical continuity of the rotating components and internal mechanisms was established. Examination of the right engine revealed the forward gearbox was destroyed and mechanical continuity of the rotating components and internal mechanisms was established. The reason for the reported rough running engine was not determined. The lifters installed in both engines during the overhauls were not approved lifters for the accident engines.
HISTORY OF FLIGHT On December 29, 2004, at 1018 mountain standard time, a Piper PA-31P (Navajo) twin-engine airplane, N573B, was destroyed when it impacted transmission lines, trees and terrain following a loss of control while maneuvering near Gallup, New Mexico. The commercial pilot, who was the sole occupant, sustained fatal injuries. The airplane was registered to and operated by the pilot. Visual meteorological conditions prevailed, and an instrument flight rules (IFR) flight plan was filed for the Title 14 Code of Federal Regulations Part 91 personal flight. The flight departed Glendale Airport, Glendale, Arizona, at 0917, and was destined for Newton, Kansas. According to the Glendale Federal Aviation Administration (FAA) control tower, the pilot received an IFR clearance to Newton, Kansas, at 0850. At 0915:16, prior to takeoff, the pilot stated, "...I got an engine that is running pretty hot, I'm gonna pull off here." At 0915:29, the pilot informed the controller he was going to taxi the airplane to the ramp to troubleshoot the problem. At 0915:52, the pilot stated, "I'm gonna make a quick phone call and I'll let you know what I want to do." At 0916:28, the pilot stated, "...once you get a little air movement past it looks like it's gonna be okay, I just do not want to hold too long. At 0917:16, the local controller cleared the pilot for takeoff. According to the Albuquerque Air Route Traffic Control Center (ARTCC), the pilot reported he was on frequency, at 0928. At 1002:48, the pilot stated, "...I think I'm gonna do a precautionary shutdown of the right engine [I'd] like vectors to the [uh next] landing strip..." At 1703, the controller stated, "...understand [you're] shuttin down the uh right engine." The pilot confirmed the right engine shutdown, and requested vectors to the nearest airport. The controller informed the pilot of two landing locations, GUP and Black Rock Airport, near Zuni, New Mexico, which were approximately the same distance. The pilot chose GUP due to weather considerations. At 1007:38, the controller asked, "The heading is uh, I'm showin zero four zero at fifty two miles, able to make that?" The pilot acknowledged, "no problem..." At 1013:34, the controller asked the pilot if emergency equipment was needed at GUP, and the pilot stated, "negative." At 1016:10, the controller informed the pilot the winds at GUP were at 170 degrees at 16 knots. At 1017, the pilot was cleared for the visual approach to GUP and shortly thereafter, the pilot was cleared to the GUP UNICOM frequency. No further communications were recorded between the pilot and the ARTCC controller. Witnesses, who were located at the Gallup Municipal Airport, reported that Albuquerque ARTCC notified Gallup Flying Service, a local fixed based operator, that a Piper Navajo (PA-31P) was inbound with the right engine shut down due to a "rough running, shaking" engine. Shortly thereafter, the witnesses observed the airplane on a "normal downwind for runway 24." One witness communicated with the pilot on the UNICOM frequency, and the pilot indicated "he had things in control." When the airplane was near the approach end of runway 24, the witness observed the airplane turn right and heading away from the airport. The witness then contacted the pilot on the UNICOM frequency and informed him he was turning away from the airport. The pilot responded, "Busy." The witnesses observed the airplane continue the right turn, stall, and enter a rapid descent toward the terrain. One witness stated the airplane "went into a VMC roll to the right...the VMC roll developed fully into a vertical dive and remained so until the airplane impacted the ground." The witness who was monitoring the UNICOM frequency lost sight of the airplane behind a ridge line and then saw smoke. A witness who lived near the accident site reported he heard something above his house and observed an airplane coming towards him. He heard engines "going on and off again." The airplane was flying straight, then turned sideways and went down. The witness could not tell if either engine was operating. According to the pilot's friends and relatives, the accident flight engine shutdown was the third or fourth engine shutdown the pilot performed since he purchased the airplane in August 2004. PERSONNEL INFORMATION The pilot held a commercial pilot certificate, issued on April 22, 1989, with single-engine land, multi-engine land, and instrument airplane ratings. The pilot was issued a second-class medical certificate on September 14, 2004, with a limitation for corrective lenses. According to the pilot's personal logbook, as of the last entry dated December 23, 2004, the pilot had accumulated 935 total flight hours, 849 hours as pilot-in-command, and 470 hours in multi-engine airplanes. The pilot had logged 45 hours in the accident airplane. In the preceding 90 days, the pilot had logged 27 total flight hours, of which 10 hours were in the accident airplane, and in the preceding 30 days, he logged 10 total flight hours, of which 4 hours were in the accident airplane. On June 9, 2004, the pilot completed an instrument proficiency check, pilot proficiency award program (WINGS Phase II), and a high altitude airplane endorsement at Flight Safety International, Lakeland, Florida. On July 7-16, 2004, the pilot completed 16 hours of instruction in a Piper Navajo simulator at Flight Safety International. AIRCRAFT INFORMATION The accident airplane, N573B, a Piper PA-31P, serial number 31P-7530008, was manufactured by Piper Aircraft Corporation in 1975. The Piper PA-31P is a pressurized twin-engine, low wing, all metal airplane of semimonocoque design. The airplane was powered by two six-cylinder, air cooled, geared propeller reduction, horizontally opposed, turbocharged, fuel injected, internal combustion engines. The airplane was issued a FAA Standard Airworthiness Certificate on December 23, 1974, and was certificated for normal category operations. The airplane was registered to the pilot on August 28, 2004. A review of the airplane's maintenance records revealed the airframe underwent a recent annual inspection on July 30, 2004, at a total airframe time of 6,773.1 hours, and a Hobbs meter time of 1,270.7 hours. On December 23, 2004, at an hour meter time of 1,319.7, the airframe's air conditioning system was serviced, and an emergency locator transmitter (ELT) check was performed. The left engine, a Lycoming TIGO-541-E1A (serial number RL-753-62) engine rated at 425 horsepower, underwent a major overhaul and was installed on the airframe on May 3, 2004, at a total time of 2,182 hours, and a Hobbs meter time of 1,198.6 hours. The engine's most recent 100-hour inspection was completed on July 30, 2004, at a total time of 2,256 hours and 74.1 hours since major overhaul. A mechanic and friend of the pilot reported that during a flight on December 13, 2004, the pilot experienced a violent vibration with the left engine while on final approach to the Glendale Airport. At the time of the event, the left engine had accumulated approximately 120 hours since major overhaul. Examination of the engine revealed the number 4 cylinder exhaust valve cap and keeper were broken, and the exhaust valve was loose. According to the maintenance logbook entry dated December 18, 2004, the mechanic "removed the #4 cylinder assembly on the #1 engine due to lifter failure." Per instructions from the facility that completed the engine overhaul, the mechanic installed a serviceable cylinder assembly and installed new lifters (12) on all six cylinders. The mechanic and pilot test ran the engine and no anomalies were noted. The left propeller was a three-bladed Hartzell HC-C3YN-2LUF (hub serial number DG663B) single acting, hydraulically operated constant speed model with feathering capability. The propeller was overhauled and installed on the airplane on August 4, 2003. On December 28, 2004, the propeller hub was replaced during compliance with Hartzell Service Bulletin HC-SB-61-271. The right engine, a Lycoming TIGO-541-E1A (serial number L-275-62) engine rated at 425 horsepower, underwent a major overhaul and was installed on the airframe on February 4, 2004, at an unknown total time, and a Hobbs meter time of 1,179.4 hours. The engine's most recent 100-hour inspection was completed on July 30, 2004, at 91.3 hours since major overhaul. According to the right engine maintenance records, on August 6, 2004, the propeller governor was replaced with an overhauled unit. The engine was "ground run and flight checked" with no anomalies. According to the pilot's personal logbook, on August 7, 2004, the pilot noted in the logbook remarks, "lost [right] turbo and cabin pressure at 15,000 feet, return for repair." On August 12, 2004, at 114.9 hours since major overhaul, the differential pressure controller and waste gate were removed and replaced, and a new exhaust gas temperature probe and new exhaust gaskets were installed. The engine operational and leak checks were "satisfactory." No subsequent maintenance entries were noted in the right engine logbook. The right propeller was a three-bladed Hartzell HC-C3YN-2LUF (hub serial number DG242) single acting, hydraulically operated constant speed model with feathering capability. The propeller was overhauled and installed on the airplane on August 11, 2003. METEOROLOGICAL INFORMATION At 0953, the routine aviation weather report (METAR) for GUP, located approximately 3 miles north of the accident site, was the wind from 170 degrees at 16 knots, gusting to 22 knots, 10 statute miles visibility, sky broken at 6,000, 7,500 and 9,000 feet, temperature 10 degrees Celsius, dew point 4 degrees Celsius, and altimeter 29.96 inches. The witnesses reported visual flight rules (VFR) conditions at the airport at the time of the accident. WRECKAGE AND IMPACT INFORMATION The National Transportation Safety Board's on-scene investigation began on December 30, 2004, at 0800. The accident site was located in hilly and rocky terrain approximately 3 miles south-southeast of GUP. Examination of the accident site revealed the airplane impacted the terrain on a measured magnetic heading of approximately 300 degrees at an elevation of approximately 6,500 feet msl. The Global Positioning System (GPS) coordinates recorded at the site were latitude North 35 degrees 28.498 minutes and longitude West 108 degrees 44.883 minutes. The right wing impacted transmission wires prior to impacting a tree and the terrain. A portion of the leading edge, which included the stall vane, was located between the transmission utility pole and the tree with the wire imbedded in the leading edge structure. The initial ground scar was located approximately 5 feet forward of the tree impact area. Fragmented windshield wipers were located in the tree debris and initial ground scar. Within the initial ground scar were fragmented engine gear box structure, gear box gears, and fragmented portions of navigational antennas. Airplane debris fanned outward from the initial ground scar to the main wreckage. The debris field contained the left wing aileron, left wing flap, right wing structure, left and right propeller assemblies, left and right engine cowlings, fragmented engine gearbox structure, engine accessories, broken sections of the windshield. The main wreckage, which consisted of the fuselage, the left wing, the left engine, and a portion of the right wing, came to rest inverted approximately 500 feet from the initial ground scar. The main wreckage was destroyed by a post-impact fire. The right engine separated from the right wing and came to rest approximately 100 feet from the main wreckage, approximately 600 feet from the initial ground scar. The left wing structure remained attached to the fuselage; however, the flight control surfaces were separated. The engine nacelle was fragmented and the left engine remained partially attached via control cables and wires. The left main landing gear was found extended, locked and attached to the left wing structure. The left wing fuel tanks were compromised and destroyed. The fuel pump and fuel filter were destroyed by fire. The fuel selector and firewall shutoff valves were destroyed by fire and their positions prior to impact were not determined. The flap jackscrew displayed no threads which was consistent with a retracted position. The aileron bell crank and two cables were secure. The control cable was continuous to the cockpit area and the cable end was broomstrawed and displayed thermal damage. The balance cable was continuous to the turnbuckle area where the cable was separated and displayed thermal damage. A majority of the right wing structure remained attached to the fuselage. The engine nacelle was fragmented and the right engine was separated. The right main landing gear was found extended and displayed thermal damage. The right wing fuel tanks were destroyed. The fuel pump and fuel filter were destroyed by fire. The fuel selector and firewall shutoff valves were destroyed by fire and their positions prior to impact were not determined. The flap control surface was partially separated and the flap jackscrew displayed no threads which was consistent with a retracted position. The aileron was separated and located beneath the forward fuselage. The aileron bellcrank was in position and both control cables were secure. The aileron control cable was intact to the cockpit area where it was still attached to a portion of the control wheel chain. The balance cable was intact to the center turnbuckle area. The aileron trim drum inner shaft displayed three threads forward extension consistent with a neutral position. The empennage was found inverted and partially attached to the fuselage. The vertical stabilizer, rudder, both horizontal stabilizers, and elevators displayed fire damage. The rudder and elevator control surfaces remained attached to their respective attach points. The rudder and elevator cables remained attached to the control surfaces. The cables were intact to the cockpit area; however, the cables were cut by rescue personnel during extrication. The rudder trim drum inner shaft displayed four threads forward extension consistent with a 3 - 5 degrees tab right position. The elevator trim drum inner shaft displayed a forward extension of approximately 0.65 inches consistent with a neutral elevator position. The cabin and cockpit were destroyed by fire. The cockpit engine control positions were not determined. The flight and engine instruments were destroyed. The fuel control panel was destroyed by fire and control positions were not determined. Rescue personnel reported the pilot seat and shoulder restraints were secure. The nose landing gear was broken and displayed thermal damage. The nose gear hydraulic actuator was extended consistent with the nose landing gear in an extended position. The left engine remained partial attached to the airframe and came to rest inverted. The engine accessories were separated and located in the debris field. The forward gear box was destroyed and the components were scattered throughout the debris field. The engine was partially damage by fire, and no evidence of catastrophic mechanical malfunction was noted. The fuel servo was located near the engine was damaged by fire. The turbocharger compressor and impeller displayed rotational scoring signatures. No evidence of foreign object debris (FOD) was noted in the turbocharger turbine or compressor assemblies. The three-bladed left propeller was separated from the engine and located in the debris field. One of the blades was separated near the propeller hub and was not located. Two blades remained attached to the propeller hub and displayed leading edge gouges, chord wise scratches across the cambered surface, and S-bending on the trailing edges. The propeller governor was separated from the mounting structure and was not located. The right engine was separated from the airframe, and no evidence of catastrophic mechanical malfunction was noted. The engine accessories were separated and located in the debris f
the pilot's failure to maintain minimum controllable airspeed which resulted in the loss of control, and impact with wires, a tree and terrain.
Source: NTSB Aviation Accident Database
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