# Accident 20000605005509A: Hughes 269C1, Brentwood, CA, June 5, 2000

- Type: FAA accident report (Accident/Incident Data System), as reported
- Date: June 5, 2000, 16:00 local time
- Place: Brentwood, CA
- Damage: Substantial damage
- Phase of flight: Practice Training Manuevers
- Operating rules: General operating rules (Part 91)
- Location: 37.9356° N, 121.7190° W: Placed by OpenAirDocs: center of Brentwood, CA, within about 6 miles (OpenAirDocs)
- Nearby events: https://openairdocs.org/map.md?lat=37.9356&lon=-121.7190&mi=10
- Aircraft: N2029H, a cancelled registration (https://openairdocs.org/deregistered/N2029H-2013-10-25) (OpenAirDocs)
- Registry model: Schweizer 269C-1 (registry code 8059504, https://openairdocs.org/model/schweizer-269c-1) (OpenAirDocs)
- Registry engine: Lycoming HO-360 series (registry code 41513, https://openairdocs.org/engine/lycoming-ho-360-series) (OpenAirDocs)
- Reported make and model: HUGHES 269C1
- Reported engine: LYC HO360C1A
- People aboard: 1
- Fatal injuries: 0
- Pilot certificates: Student
- Pilot flight hours: 87 total, 60 in the last 90 days
- NTSB investigation: [NTSB LAX00LA216](https://openairdocs.org/ntsb/LAX00LA216) (OpenAirDocs)
- FAA source: FAA Aviation Safety Information Portal (https://asip.faa.gov/)
- Page: https://openairdocs.org/incident/20000605005509A

## Narrative

As the FAA filed it, in capitals; the FAA replaces private details with ^PRIVACY DATA OMITTED^.

(-23) NO NARRATIVE (.4) THE SOLO STUDENT PILOT WAS PRACTICING QUICK STOP MANEUVERS. HE REPORTED THAT, DURING ONE MANEUVER, THE HELICOPTER WAS NEARLY STOPPED IN A HIGH HOVER AT 30 FEET AGL, AND HE WAS DESCENDING TO LOW HOVER WHEN THE HELICOPTER STARTED VIBRATING AND YAWED TO THE LEFT. THE CONTROLS BECAME INEFFECTIVE AND THE HELICOPTER STARTED SPINNING AROUND UNTIL IT IMPACTED THE GROUND AND THEN ROLLED ON ITS SIDE. WHEN EXAMINED AFTER THE ACCIDENT, THE MAIN ROTOR BLADES EXHIBITED MODEST LEADING EDGE DAMAGE, MODEST CHORDWISE STRIATIONS, AND APPROXIMATELY 20 DEGREES OF UNIFORM ROOT-TO-TIP UPWARD BENDING DEFORMATION. ONE TAIL ROTOR BLADE WAS UNDAMAGED AND THE OTHER WAS BENT ABOUT 10 DEGREES TIP-INBOARD AT THE MIDSPAN. THE ENGINE WAS STARTED AND RAN SMOOTHLY. NO PREACCIDENT MECHANICAL ANOMALIES WERE NOTED. THE NATIONAL TRANSPORTATION SAFETY BOARD DETERMINES THE PROBABLE CAUSE(S) OF THIS ACCIDENT AS FOLLOWS. THE STUDENT'S IMPROPER EXECUTION OF A QUICK-STOP MANEUVER IN THAT HE MISJUDGED HIS ALTITUDE AND FAILED TO TERMINATE AT A STATIONARY HOVER PRIOR TO DESCENDING TO A LOW HOVER. THIS RESULTED IN AN EXCESSIVE ENGINE POWER REQUIREMENT                                                         AND THE STUDENT IMPROPERLY COORDINATED THE USE OF THE COLLECTIVE AND ANTI-TORQUE CONTROLS.

## The NTSB's investigation of this event (1)

From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model.

- [NTSB LAX00LA216](https://openairdocs.org/ntsb/LAX00LA216), Jun 5, 2000: Schweizer 269C-1 (N2029H), Brentwood, CA, substantial damage. Probable cause: The student's improper execution of a quick-stop maneuver in that he misjudged his altitude and failed to terminate at a stationary hover prior to descending to a low hover. This resulted in an…

From the FAA Accident/Incident Data System. Reports are matched to registry aircraft by N-number and event date, checked against the reported make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. For accidents, the NTSB's own investigation is the fuller record.

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