National Transportation Safety Board
Aviation Accident Final Report




Carson City, NV

Accident Number:


Date & Time:

03/01/2017, 1250 PST





Aircraft Damage:


Defining Event:

Fuel related


1 Serious

Flight Conducted Under:

Part 91: General Aviation - Personal



The airline transport pilot was conducting the airplane's first flight after about 1 1/2 years of inactivity and the completion of an annual inspection. A witness reported that the airplane took off normally, but the retractable landing gear remained extended. As the airplane neared the end of the runway, about 300 ft above ground level, the engine sounded as though it "decreased to idle." The airplane entered a right, 180o turn and descended rapidly before impacting the ground.

During a postaccident test run, the engine operated normally at both idle and full power settings and during abrupt changes between idle and full power. However, it operated inconsistently at 2,100 rpm for about 30 seconds before stabilizing at that power setting. During this time, the fuel pump pressure fluctuated. Following the test run, the fuel manifold valve was disassembled, revealing rust on the screen, lower housing, and plunger, consistent with exposure to water. The diaphragm was removed and a small amount of fuel was found on the "dry" side of the valve; the vent extending from this section was examined and clear of debris. Examination of the airframe and engine maintenance logs revealed that the airplane flew a total of 73 hours and underwent 3 annual inspections in the previous 8 years. It is likely that water accumulated in the fuel system sometime during the airplane's prolonged periods of disuse, resulting in corrosion of the fuel manifold valve's internal components. Because the corrosion was internal, it would not have been detected without disassembly of the fuel manifold, which is not part of the annual inspection procedure. It is likely that this corrosion caused the manifold valve plunger to temporarily stick, which restricted fuel flow to the engine and resulted in the anomalous operation during the postaccident test run as well as the loss of power on the accident flight. Following the loss of engine power, the pilot initiated a turn back to the runway, during which the airplane exceeded its critical angle of attack and experienced an aerodynamic stall.


Probable Cause and Findings

The National Transportation Safety Board determines the probable cause(s) of this accident to be:

A total loss of engine power due to internal corrosion of the fuel manifold valve. Also causal was the pilot's decision to return to the runway following the loss of engine power shortly after takeoff, and his exceedance of the airplane's critical angle of attack during the turn, which resulted in an aerodynamic stall.




Fuel distribution - Fatigue/wear/corrosion (Cause)

Fuel distribution - Malfunction (Cause)

Personnel issues

Aircraft control - Pilot (Cause)

Factual Information


On March 1, 2017, about 1250 Pacific standard time, a Bellanca 17-30A, N39894, experienced a loss of engine power shortly after takeoff from the Carson Airport (CXP), Carson City, Nevada. The pilot, sole occupant, was seriously injured, and the airplane sustained substantial damage to both wings. The airplane was registered to and operated by the pilot as a 14 Code of Federal Regulations Part 91 personal flight. Visual meteorological conditions prevailed at the time of the accident no flight plan was filed for the local flight.

At the time of this report, the pilot was unable to provide a statement or complete the NTSB Pilot/Operator Aircraft Accident/Incident Report Form 6120.1.

A witness reported that he observed the airplane takeoff normally, with the exception that the landing gear remained in the down position. At the end of the runway, when the airplane was no higher than 300 feet, it sounded as if the engine decreased to idle. The airplane made a right 180o turn and descended rapidly before impacting the ground.

Postaccident examination of the airframe revealed continuous control continuity throughout the airframe. In addition, control continuity was established from the cabin to the throttle, mixture, and propeller controls. The fuel lines were intact from the engine to the firewall, and from the wing tanks to the fuselage; the remaining lines were inaccessible due to airframe damage. Air was blown from the engine driven fuel pump inlet line aft through the fuel selector and air/fuel exited the left wing fuel tank outlet line. With no obvious anomalies with the airframe or engine, the engine was shipped to Continental Motors to be run in a test cell.

The engine was installed into a test cell. It started normally and ran for a while at 1,200 RPM with no anomalies noted. The power was increased to 2,100 rpm and the engine operated inconsistently; the fuel pump pressure was fluctuating, and after about 30 seconds the engine stabilized. After stabilization, a magneto check was completed and no abnormalities were noted. The engine power was increased to 2,400 RPM momentarily before full power was applied; the engine continued to operate normally. The engine power was abruptly changed between idle and full power several times with no anomalies noted. Unable to recreate the inconsistent running engine, it was shut down normally and removed from the test cell.

The fuel components were removed from the engine. The fuel manifold valve was disassembled and rust indicative of corrosion was present on the screen and lower housing of the unit. The plunger was removed and it also exhibited rust. The diaphragm was removed and a small amount of fuel was found on the "dry" side of the valve; the vent extending from this section was examined and clear of debris.

The most recent entries from the airplane's airframe and engine maintenance logbooks were three annual inspections that occurred over a span of about 8 years. The tach time difference between these inspections was a total of 73 hours, for an average of 9 hours a year. The wife of the pilot reported that they purchased the airplane in 2002, and it has been parked in a hangar for a majority of their ownership. About 1.5 years leading up to the accident, the airplane had been undergoing an annual inspection and new paint, which was completed on February 24, 2017. When the maintenance was completed, the pilot ran the airplane's engine on the ground for about 45 minutes with no anomalies noted; the accident flight was the first flight post maintenance.

According to a Continental Motors representative the fuel manifold valve is generally not disassembled by a mechanic in the field, and there are rarely issues with this engine component. If fuel issues are suspected, the troubleshooting section of the Continental Motors Standard Practices Manual (M-0) directs the mechanic to an isolated fix. If the problem is isolated to the fuel manifold, it is to be removed and either sent to an appropriate overhaul facility, or replaced by a new or rebuild from Continental Motors.



History of Flight

Initial climb

Fuel related (Defining event)

Loss of engine power (total)

Off-field or emergency landing


Aerodynamic stall/spin

Collision with terr/obj (non-CFIT)



Pilot Information


Airline Transport; Flight Engineer


61, Male

Airplane Rating(s):

Multi-engine Land; Multi-engine Sea; Single-engine Land; Single-engine Sea

Seat Occupied:


Other Aircraft Rating(s):


Restraint Used:


Instrument Rating(s):


Second Pilot Present:


Instructor Rating(s):


Toxicology Performed:


Medical Certification:

Class 1 Without Waivers/Limitations

Last FAA Medical Exam:


Occupational Pilot:


Last Flight Review or Equivalent:


Flight Time:

22000 hours (Total, all aircraft)



Aircraft and Owner/Operator Information

Aircraft Make:






Aircraft Category:


Year of Manufacture:


Amateur Built:


Airworthiness Certificate:


Serial Number:


Landing Gear Type:




Date/Type of Last Inspection:

02/24/2017, Annual

Certified Max Gross Wt.:


Time Since Last Inspection:

1 Hours


1 Reciprocating

Airframe Total Time:

3394 Hours as of last inspection

Engine Manufacturer:



Not installed

Engine Model/Series:


Registered Owner:

On file

Rated Power:

285 hp


On file

Operating Certificate(s) Held:



Meteorological Information and Flight Plan

Conditions at Accident Site:

Visual Conditions

Condition of Light:


Observation Facility, Elevation:

CXP, 4705 ft msl

Distance from Accident Site:

0 Nautical Miles

Observation Time:

1255 PST

Direction from Accident Site:


Lowest Cloud Condition:



10 Miles

Lowest Ceiling:


Visibility (RVR):


Wind Speed/Gusts:

4 knots /

Turbulence Type Forecast/Actual:

/ None

Wind Direction:


Turbulence Severity Forecast/Actual:

/ N/A

Altimeter Setting:

30.41 inches Hg

Temperature/Dew Point:

7°C / -9°C

Precipitation and Obscuration:

No Obscuration; No Precipitation

Departure Point:

Carson City, NV (CXP)

Type of Flight Plan Filed:



Carson City, NV (CXP)

Type of Clearance:


Departure Time:

1250 PST

Type of Airspace:



Airport Information


Carson Airport (CXP)

Runway Surface Type:


Airport Elevation:

4705 ft

Runway Surface Condition:


Runway Used:


IFR Approach:


Runway Length/Width:

6100 ft / 75 ft

VFR Approach/Landing:

Forced Landing


Wreckage and Impact Information

Crew Injuries:

1 Serious

Aircraft Damage:


Passenger Injuries:


Aircraft Fire:


Ground Injuries:


Aircraft Explosion:


Total Injuries:

1 Serious

Latitude, Longitude:

39.192222, -119.732778 (est)



Administrative Information

Investigator In Charge (IIC):

Samantha A Link

Report Date:


Additional Participating Persons:

Aaron Southerland; Federal Aviation Administration; Reno, NV

Kurt Gibson; Continental Motors; Mobile, AL

Publish Date:



The NTSB did not travel to the scene of this accident.

Investigation Docket: