ASN Wikibase Occurrence # 214817
This information is added by users of ASN. Neither ASN nor the Flight Safety Foundation are responsible for the completeness or correctness of this information.
If you feel this information is incomplete or incorrect, you can submit corrected information.
| Date: | Monday 27 August 2018 |
| Time: | 10:36 |
| Type: |  Stoddard-Hamilton Glasair Super II RG |
| Owner/operator: | Private |
| Registration: | N8162H |
| MSN: | 2224 |
| Year of manufacture: | 1995 |
| Total airframe hrs: | 2020 hours |
| Engine model: | Superior Air Parts IO-361-J1HD2 |
| Fatalities: | Fatalities: 0 / Occupants: 1 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | North of Yuma International Airport (KNYL), Yuma, AZ -
 United States of America
|
| Phase: | Landing |
| Nature: | Private |
| Departure airport: | San Diego, CA (MYF) |
| Marana, AZ (AVQ) | |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
The private pilot reported that, about 35 minutes into the personal cross-country flight, the experimental, amateur-built airplane's alternator field toggle switch/circuit breaker tripped. He reset the switch, and all systems appeared normal. About 5 minutes later, the switch tripped again, and the pilot cycled the switch. About 2 minutes later, the pilot noticed that the engine manifold pressure was dropping, along with the airplane’s airspeed, consistent with a partial loss of engine power. The engine then experienced a total loss of power when he was maneuvering for an emergency landing to a nearby airport. The airplane subsequently landed short of the runway and sustained substantial damage to the aft fuselage.
The engine had been installed about 91 flight hours and 5 months before the accident flight, and a condition inspection was completed the same month of installation. Maintenance records indicated that during the period between the engine installation and the accident, maintenance was limited to routine oil changes, magneto timing adjustments, the replacement of exhaust gas temperature and cylinder head temperature probes, and the installation of a replacement alternator.
Postaccident examination of the engine revealed that the throttle linkage had detached from the throttle arm of the fuel injection servo. The rod end bearing for the linkage and the throttle arm were intact and undamaged, but the connecting bolt and its associated washers, castellated nut, and cotter pin were missing. The butterfly valve within the throttle body was in the closed position, and the throttle lever in the cabin was in the full forward (open) position. It is likely that the bolt securing the linkage had not been sufficiently tightened and secured with a cotter pin during the installation and that the error was not detected during the subsequent condition inspection.
The investigation determined that the electrical system malfunction was unrelated to the loss of engine power.
Probable Cause: A total loss of engine power as a result of the detachment of the throttle linkage from the throttle arm of the fuel injector servo due to an insufficiently tightened and secured bolt and the subsequent inadequate maintenance inspection.
Accident investigation:
 |
|
Sources:
NTSB
https://flightaware.com/live/flight/N8162H
FAA register: https://registry.faa.gov/aircraftinquiry/NNum_Results.aspx?NNumbertxt=8162H%20
Location
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 29-Aug-2018 17:35 | Geno | Added |
| 27-Nov-2019 07:16 | ASN Update Bot | Updated [Time, Operator, Nature, Departure airport, Destination airport, Source, Damage, Narrative, Accident report, ] |
Corrections or additions? ... Edit this accident description
The Aviation Safety Network is an exclusive service provided by:
Quick Links:
| ASN Home | Send Correction / Feedback |
| FSF Home | Disclaimer | Copyright |
| Contact Us | Privacy Policy |
| Press / Media |
CONNECT WITH US:
©2024 Flight Safety Foundation