Thursday, August 03, 2017

Loss of Engine Power (Total): Lancair IV-P, N420M; fatal accident occurred August 03, 2017 near McClellan Airfield (KMCC), Sacramento County, California

Dr. Marshall Michaelian


The National Transportation Safety Board traveled to the scene of this accident.

Additional Participating Entity:
Federal Aviation Administration / Flight Standards District Office; Sacramento, California

Aviation Accident Factual Report - National Transportation Safety Board: https://app.ntsb.gov/pdf

Investigation Docket - National Transportation Safety Board: https://dms.ntsb.gov/pubdms

http://registry.faa.gov/N420M

Location: Rio Linda, CA
Accident Number: WPR17FA179
Date & Time: 08/03/2017, 1503 PDT
Registration: N420M
Aircraft: Michaelian Lancair IV-TP
Aircraft Damage: Substantial
Defining Event: Loss of engine power (total)
Injuries: 1 Fatal
Flight Conducted Under: Part 91: General Aviation - Personal 

On August 3, 2017, at 1503 Pacific daylight time, an experimental, amateur-built Lancair IV-TP, N420M, was substantially damaged when it was involved in an accident near Rio Linda, California. The commercial pilot was fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.

An onboard GPS and avionics unit captured data from the accident flight; the airplane departed Auburn Municipal Airport (AUN), Auburn, California, about 1455. The pilot established the airplane on a heading of about 195° toward the destination of San Carlos, California and began to climb. The pilot contacted air traffic control and requested visual flight rules flight following to the destination, and when the controller advised the pilot that the airplane had been identified on radar, the pilot did not respond. The controller then saw the airplane turn and descend toward McClellan Airfield (MCC), Sacramento, California; no further communications were received from the accident pilot. (See Figure 1).

Figure 1: Flight Track Showing Diversion

Data showed that, at 1459:17, the fuel pressure began to rise from about 40 pounds per square inch (psi) to 43 psi. A few seconds later, after reaching 6,492 ft mean sea level (msl), the airplane pitched down and banked to the left, reaching 25° nose down and 36° left wing down. At 1459:24, torque and N1 (gas generator speed) were at 64% and 95%, respectively, and 15 seconds later, began to decrease consistent with the engine producing idle power. During that time, the oil pressure dropped from about 31 to 15 psi and fuel flow was reduced from 46 to 16 gallons per hour; the interstage turbine temperature decreased from 1,118°F to 786°F.

At 1459:53, the oil pressure increased to 28 psi and the voltage began to slowly decrease from 28 volts, consistent with the generator turning off and the airplane being powered by the standby alternator. The N1 stabilized about 65%, and the engine torque dropped to about 8%. At 1501:41, N1 began to decrease again and reached 0 about 15 seconds later, with a simultaneous decrease in oil pressure and ITT. At 1502:00, the aircraft banked about 40° to the left, aligning with runway 16 at MCC.

During the last 38 seconds of the flight, the airplane lost about 425 ft of altitude while slowing from 125 knots (kts) to 89 kts. During this time, the engine torque and N1 were 0, while the propeller rpm consistently slowed from 1,746 to 948. The next data point, 1 second later, depicted the airspeed as 0, and several parameters showed discontinuities consistent with impact.

Witnesses saw the airplane flying south along 28th Street toward MCC at low altitude. The airplane then made a sharp turn to the right and disappeared into the trees.

After the accident, the pilot's family listened to the radio transmissions for the final portion of the flight and they stated that they heard the pilot make three radio transmissions, the second of which was not discernable aside from the airplane's registration number. The third transmission was (presumably) the pilot acknowledging a controller's directions to squawk a discrete code by pressing the microphone; the pilot did not report an emergency or convey that he was in distress. 

Pilot Information

Certificate: Commercial
Age: 71, Male
Airplane Rating(s): Multi-engine Land; Single-engine Land
Seat Occupied: Left
Other Aircraft Rating(s): None
Restraint Used:
Instrument Rating(s): Airplane
Second Pilot Present: No
Instructor Rating(s): None
Toxicology Performed: Yes
Medical Certification: Class 3 With Waivers/Limitations
Last FAA Medical Exam: 10/01/2014
Occupational Pilot: No
Last Flight Review or Equivalent: 02/01/2016
Flight Time:  (Estimated) 7300 hours (Total, all aircraft) 

The pilot's personal flight records were not recovered. On his last application for a medical certificate, the pilot reported 7,000 total hours of flight experience. 

Aircraft and Owner/Operator Information

Aircraft Make: Michaelian
Registration: N420M
Model/Series: Lancair IV-TP
Aircraft Category: Airplane
Year of Manufacture: 2004
Amateur Built: Yes
Airworthiness Certificate: Experimental
Serial Number: LIV 071
Landing Gear Type: Retractable - Tricycle
Seats: 4
Date/Type of Last Inspection: 08/04/2016, Condition
Certified Max Gross Wt.:
Time Since Last Inspection: 61 Hours
Engines: 1 Turbo Prop
Airframe Total Time: 934.7 Hours at time of accident
Engine Manufacturer: Diemech Turbines
ELT: Installed
Engine Model/Series: M601D
Registered Owner: Pilot Proficiency Inc.
Rated Power: 750 hp
Operator: On file
Operating Certificate(s) Held: None

The Lancair IV-TP was an experimental, amateur-built airplane constructed mainly of composite materials The pilot purchased the kit directly from Lancair International Inc., in November 1995. The airplane received a special airworthiness certificate in the experimental category in September 2004. The logbook entry on August 4, 2016, stated that "a list of discrepancies and unairworthy items" were provided to the airplane's owner. This list, and the mechanic who performed the inspection, could not be located after the accident. The pilot recorded that he replaced the starter/generator in July 2016 at a total time of 868.0 hours.

Engine and Propeller

The Diemech M601D engine is a two-spool engine comprising a gas generator that drives a power turbine, which drives a reduction gearbox. The gas generator compressor consists of two axial flow stages and one centrifugal stage. Inlet air enters the compressor section radially just forward of the accessory section and travels forward through the compressor. The exiting compressor air enters an annular combustor to mix with fuel for the combustion process. The gas generator turbine nozzles then direct the expanded flowpath gases to the gas generator turbine, which directs the exiting gases to the power turbine for the final power extraction before exiting the engine forward of the compressor inlet.

The power turbine drives the propeller system by means of the reduction gearbox. The accessory gearbox, which is located on the aft end of the engine drives all engine accessories by a direct shaft coming from the compressor spool. Typical engine accessories are the main fuel pump, fuel control unit, starter/generator, hydraulic pump, and the propeller governor, which is driven by the reduction gearbox located at the front of the engine.

The oil system is a circulatory pressure system with an integral oil tank incorporated into the accessory gearbox. This system provides lubrication for all areas of the engine and oil pressure for the torque meter and propeller pitch control.

The powerplant was controlled by three sets of levers. The power lever controlled the power output of the engine and the propeller blade angles in Beta and reverse. The propeller lever controlled the propeller speed via the primary propeller governor and emergency propeller feathering. The condition lever actuated the fuel shutoff valve and, if an emergency circuit was on, controlled engine power.

The propeller was equipped with an overspeed governor on the cylinder front face, which featured an internal spring-loaded weighted valve. Centrifugal forces of the propeller rpm act on the weighted valve, and once the spring pressure is overcome, the valve opens, allowing oil from the low pitch area in the hub to the drain until the rpm decreases to correspond with speed setting.

The airplane was not equipped with an emergency electric propeller feather pump; thus, emergency feathering could be activated by moving the propeller lever onto the feather stop. However, this required the gas generator portion of the engine to still be operating, since the gas generator drove the main oil pump and provided oil pressure to the propeller for pitch control and emergency feathering. However, when an engine loses power for any reason, the gas generator section quickly stops rotating and there is no engine oil pressure available to feather the propeller. With no engine power to turn the propeller, it will quickly stop rotating, making the counterweights and aerodynamic pressure on the rotating blades the only driving force available to feather the propeller. Unless the pilot immediately moves the propeller conditioning lever into the feather stop when the engine loses power, the propeller will effectively be locked at the blade pitch that was selected at the time of the engine failure.

Fuel System

The airplane was last fueled on July 29. According to the refueling technician, the pilot requested that the airplane be refueled to capacity, and the records indicated he purchased 103 gallons of Jet A. The technician recalled filling both of the wing tanks; he noted that the pilot rarely filled the belly tank. Onboard data indicated that the right and left fuel tanks each contained about 20 gallons of fuel before the flight, but the total amount of fuel onboard was unknown.

The fuel system comprised two 56-gallon wing tanks and a 36-gallon belly tank; all tanks fed into a 24-gallon header tank. From the header tank via an electric boost pump, the fuel passed through a filter and continued by the fuel pressure sensor and then the fuel flow sensor to the fuel control unit (FCU). The fuel pressure and flow rate displayed on the instrument panel were based on what the pressure header tank supplied to the FCU. The header tank was equipped with a vent line.

The airplane was equipped with a VR Avionics Fuel System Management (FSM), which was designed to automatically select the fuel tank with the lowest quantity as the feeder tank. In an effort to equalize the fuel level, the tank would be switched to the lowest when an imbalance of 3 gallons was reached. The system additionally monitored the fuel pumps and fuel pressure, providing the pilot with an annunciation if the levels were low. 

Meteorological Information and Flight Plan

Conditions at Accident Site: Visual Conditions
Condition of Light: Day
Observation Facility, Elevation: KMCC, 77 ft msl
Distance from Accident Site: 2 Nautical Miles
Observation Time: 2155 UTC
Direction from Accident Site: 178°
Lowest Cloud Condition: Clear
Visibility:   10 Miles
Lowest Ceiling: None
Visibility (RVR):
Wind Speed/Gusts: 6 knots /
Turbulence Type Forecast/Actual:
Wind Direction: 240°
Turbulence Severity Forecast/Actual:
Altimeter Setting: 29.87 inches Hg
Temperature/Dew Point: 37°C / 7°C
Precipitation and Obscuration: No Obscuration; No Precipitation
Departure Point: AUBURN, CA (AUN)
Type of Flight Plan Filed: VFR
Destination: SAN CARLOS, CA (SQL)
Type of Clearance: VFR Flight Following
Departure Time: 1454 PDT
Type of Airspace:

Airport Information

Airport: MC CLELLAN AIRFIELD (MCC)
Runway Surface Type: Concrete
Airport Elevation: 76 ft
Runway Surface Condition: Dry
Runway Used: 16
IFR Approach: None
Runway Length/Width: 10599 ft / 150 ft
VFR Approach/Landing:  Forced Landing; Straight-in

Wreckage and Impact Information

Crew Injuries: 1 Fatal
Aircraft Damage: Substantial
Passenger Injuries: N/A
Aircraft Fire: None
Ground Injuries: N/A
Aircraft Explosion: None
Total Injuries: 1 Fatal
Latitude, Longitude: 38.703889, -121.401667 

The accident site was in the back yard of a residence located at the corner of two streets. Powerlines were located 190 ft north of the wreckage with two support structures (wood poles) on both sides of the street about 73 ft apart. A powerline about 190 ft from the main wreckage exhibited several bends in the center area consistent with airplane impact. (See Figure 2)

Figure 2: Accident Site

The airplane came to rest upright on level terrain oriented on an approximate 100° magnetic heading. The main wreckage, which comprised a majority of the airframe and engine, was located about 1.3 nautical miles (nm) from the approach end of runway 16 at MCC.

The airframe remained relatively intact and the cockpit sustained minor crush damage. The throttle was between the mid- and full-throttle positions; the propeller lever was at feather and the condition lever was mid-range. The throttle quadrant retention clip was displaced and the throttle lever was slightly bent. It could not be determined if the clip displacement was the result of cockpit deformation at impact.

The generator switch was selected to "on," and the generator circuit breaker was out. The air conditioner switch was "on."

Fuel System

According to the recorded airplane data, the fuel pressure remained relatively stable through the flight. After the accident, the left and right fuel pumps were selected to "auto" and the center pump was selected to "off." During post-accident examination, the fuel line was detached from the FCU and the system was activated. Upon activation of the boost pump, about 20 gallons of fluid was pumped from the header tank at a flow rate of about 70 gph, consistent with normal operation.

An external examination revealed that the FCU had sustained impact damage, and whether there was air in the system could not be determined. Functional testing of the FCU and hydromechanical system revealed no anomalies that would have prevented normal operation. The mechanical fuel pump was removed and disassembled, revealing that its shaft was intact. There was no evidence of excessive wear or pre-impact damage that would have prevented normal operation.

Engine Examination

The engine was removed and placed in a test cell for operational testing. The engine started normally. The propeller was cycled twice from fine to feather pitch to purge the propeller piston cavity of air. After an initial idle period, the engine power was increased to 85% N1. Acceleration and deceleration behavior were acceptable, with no indications of hesitation, stall, or flameout.

The examination revealed no evidence of pre-impact mechanical malfunction or failure that would have precluded normal operation.

Propeller Examination

The propeller was generally intact and clean. The spinner was not present. When one blade was rotated around its span axis, all other blades rotated in unison, consistent with internal mechanical integrity. There was no evidence of positive blade twisting along the span axis, which is normally observed when the propeller is being driven with engine power at impact. The leading edges of all the blades, although abraded from normal use, displayed no evidence of soft or hard body impact damage. A geometric analysis of shear damage to the bearing ring concluded that the blades were at the minimum flight angle (low pitch stop) of about 18° to 20°, or fine pitch. The emergency condition of the blades during an engine problem should be feather, or 90°; the dual-acting propeller was not equipped with an internal feathering spring.

Propeller Governor

An external visual examination revealed that the propeller governor was undamaged. Oil was seen exiting the mounting flange passages. The accident airplane was not equipped with an emergency electric propeller feathering pump. According to Lancair, there was no requirement or installation guidance for such a system.

The airplane was equipped with a VR Avionics Turbine Starter Limiting/Monitoring System (TSLM). It was designed to act as a start sequence controller, an engine protection limiter, and an engine monitor/recorder. Data from the unit indicated that the pilot did not attempt to restart the engine during the flight. 

Medical And Pathological Information

The County of Sacramento Coroner, Sacramento, California, completed an autopsy on the pilot. The cause of the pilot's death was listed as blunt force injuries. Atherosclerotic disease was reported as a finding, with up to 70% and 60% stenosis in the left anterior descending branch and right coronary arteries, respectively. An area of fibrosis, confirmed by microscopic exam, was also reported, consistent with a remote myocardial infarction. No other significant natural disease was identified. These findings placed the pilot at some increased risk for a sudden cardiac event, including a heart attack or arrhythmia. First responders reported that the pilot stopped breathing shortly after being extricated from the wreckage.

Toxicology testing performed at the FAA's Forensic Sciences Laboratory was negative for carbon monoxide and ethanol. The results were positive for Atorvastatin and Pioglitazone.






















































NTSB Identification: WPR17FA179
14 CFR Part 91: General Aviation
Accident occurred Thursday, August 03, 2017 in Rio Linda, CA
Aircraft: Michaelian Lancair IV-TP, registration: N420M
Injuries: 1 Fatal.

This is preliminary information, subject to change, and may contain errors. Any errors in this report will be corrected when the final report has been completed. NTSB investigators either traveled in support of this investigation or conducted a significant amount of investigative work without any travel, and used data obtained from various sources to prepare this aircraft accident report.

On August 03, 2017, at 1503 Pacific daylight time, a single-engine experimental Michaelian Lancair IV-TP, N420M, impacted a residential area in Rio Linda, California following a loss of engine power while on approach to Mc Clellan Airfield, Sacramento, California. The commercial pilot, the sole occupant, was fatally injured; the airplane was substantially damaged. The airplane was registered to Pilot Proficiency Inc., and operated by the pilot under the provisions of 14 Code of Federal Regulations Part 91. The personal flight departed from Auburn Municipal Airport, Auburn, California at 1455 with a planned destination of San Carlos Airport, San Carlos, California. Visual meteorological conditions prevailed and a flight plan had not been filed; the pilot was receiving flight following advisories.

Located in the wreckage was a Garmin GPSMAP 396, battery-powered portable GPS receiver. The unit stores date, route-of-flight, and flight-time information; all recorded data is stored in non-volatile memory.

Recorded data plots were recovered for the time frame that matched the anticipated flight track of the airplane departing from Auburn. The track indicated that the airplane departed from runway 25 about 1455. After becoming airborne, the airplane climbed and headed toward San Carlos on a heading of about 220 degrees. At 1459:28, with the airplane about 6,800 ft msl, the airplane began a gradual descent and shifted to a 240-degree heading. The airplane continued in the direction while cruising between about 215-200 kts until 1502:02 when the airplane made a left turn to adjoin the final approach leg to runway 16 at Mc Clellan Airfield.

The last six hits of the flight track occurred over 35 seconds from 1502:06 to 1502:41. During that time the speed increased from 130 kts to 91 kts and the altitude decreased about 510 ft. The last recorded point placed the airplane approximately 790 feet north-northeast of the accident site at 155 feet msl.

Numerous witnesses observed the airplane flying south along 28th street toward Mc Clellan Airfield at a low altitude. The airplane suddenly made a sharp turn to the right and disappeared into the trees.

The accident site was in a backyard of a residence located on the corner of U street (east-west oriented) and 28th street (north-south oriented). Powerlines were located 190 ft north of the wreckage with two support structures (wood poles) on both sides of 28th street (south side of U street), at a distance of 75 ft apart. The lines had been separated from the west structure attach fittings (35-ft high) but remained attached to the east structure (about 50 ft high). The upper powerline had several bends in the center area consistent with the airplane having made contact with the wire.



RIO LINDA (CBS13) — The wreckage of Thursday’s deadly small plane crash was removed from the backyard of a Rio Linda home on Friday.

The pilot killed in that crash is being remembered for his giving-spirit and passion for flying.

Dr. Marshall Michaelian died when his plane crash-landed in a backyard a mile from the McClellan Air Field Thursday.

Crews hoisted the wreckage from the small plane—backwards from its final crash landing spot in a backyard.

The airplane’s tail battered, its wings sawed off, its propellers bent

The FAA reports the plane was bound for San Carlos from Auburn when investigators believe the pilot attempted an emergency landing at McClellan Airfield.

Air traffic recordings describe the initial crash aftermath.

“We got a downed aircraft out here.”

“Can you let us know if you can see anything? They’re a mile out from the runway right on the approach in.”

The pilot, oral surgeon Marshall Michaelian is shown in photos on his dental practice website with his Lancair plane that he was flying when he crashed.

Michaelian was a volunteer for “Angel Flight” and had flown 28 missions, flying children with burn scars and hearing impairments to special needs camps in his plane.

“It’s sad, it’s very sad,” Auburn pilot Kenton Kiaser said.

Kiaser had recently befriended Michaelian.

He says Michaelian’s Lancair, a high-performance plane, was the envy of the airport.

“He had quite a bit of experience with the hours he had, and he had built the airplane that he was flying,” Kiaser said.

NTSB crews removed the plane from the crash site and will deconstruct it at a wreckage warehouse.

“I’ll do a teardown examination, where I’ll thoroughly look at the engine,” NTSB investigator Zoe Keliher said.

An NTSB preliminary investigation report is expected to be released next week. A full crash report will take a year.







The National Transportation Safety Board says Marshall Michaelian was flying from Auburn Municipal Airport with a destination of San Carlos south of San Francisco.

Witnesses told the Sacramento Sheriffs Department they saw his single-engine plane hit a power pole and trees before crashing into the yard of a home at the corner of 28th and U Streets in Rio Linda. Michaelian was pronounced dead at the scene.

The  Sacramento County Coroner has not released a cause of death.

Michaelian was flying a Lancair IV P. Lancair sells planes in kits to be assembled by people at their homes.

According to the National Transportation Safety Board, 28 Lancair planes have crashed since 1989, 11 of the crashes resulted in a fatality.

Six of the 28 crashes involved an IV P model.

The NTSB says failure to maintain sufficient speed was the cause of half of the IV P crashes.

The Federal Aviation Administration requires home-built aircraft be certified and pass annual airworthiness inspections.

The Federal Aviation Administration says a homebuilt aircraft must first receive an airworthiness certificate which can be obtained after 40 hours of flight time that prove it is "controllable."

Even with a certificate, pilots may not fly over populated areas unless they are in the process of landing at or taking off from airports.

Homebuilt aircraft must undergo the same annual or 100 flight-hour, whichever comes first, inspections as aircraft with standard airworthiness certificates.

FAA and NTSB inspectors are reviewing the crash.


http://www.capradio.org

The pilot of a small home-built airplane died when when the aircraft crashed into the yard of a Rio Linda home Thursday afternoon.

Sgt. Tony Turnbull, Sacramento County sheriff’s spokesman, said deputies responded to a report of a plane crash about 3 p.m. on property at 28th and U streets.

The pilot, the only person on board, was unresponsive. Sacramento Metropolitan Fire Department personnel provided medical aid, but the man was pronounced dead at the scene.

Turnbull said the plane did not damage any structures and no one else was injured.

The plane was a single-engine, home-built Lancair IV-P, according to Ian Gregor, a spokesman for the Federal Aviation Administration.

Tunbull said no information was available on where the flight originated or where the plane was headed. Witnesses reported that the plane was southbound at a low altitude, and it clipped power lines and trees as it came down on the property, he said.

The name of the pilot has not been released.

An investigation will be conducted by the FAA and the National Transportation Safety Board.

Turnbull said 28th Street is closed between Elverta Road and Elkhorn Boulevard, and U Street is closed between 26th and 30th streets.


RIO LINDA, Calif. (KCRA) — A pilot died Thursday afternoon after his small plane crashed into a Sacramento County neighborhood, the Sacramento County Sheriff's Department said.

The pilot was the only person on board the plane at the time.

The plane crashed into the backyard of a Rio Linda home near 28th and U streets, the Sacramento Metro Fire Department said. The scene is just north of McClellan Airfield.

The FAA said the plane -- a single-engine, home-built Lancair IV-P aircraft -- crashed for unknown reasons.

The incident will be investigated by the FAA and the NTSB.

A small power outage was reported in the area due to the plane crash. Aerial video from LiveCopter 3 shows downed power lines and trees at the crash scene.

2 comments:

  1. I knew Dr. Michaelian. I used to teach on his AST-300 quite a bit. He was a very good man! This is very, very sad news!

    ReplyDelete
  2. I am always saddened by any aviation death, general or otherwise, my prayers are with your family sir.

    ReplyDelete