20000120008039A

Accident · Substantial damage

FAA accident report · Bell UH-1H · Ft Meyers, FL · January 20, 2000

Date
January 20, 2000 · 13:30 local
Place
Ft Meyers, FL
Phase of flight
Autorot Descent (Rotorcraft)
Operating rules
General operating rules (Part 91)
Damage
Substantial damage
Aircraft
N853M
NTSB investigation
NTSBMIA00TA070
Reported as
Bell UH1H
Reported engine
Lycoming T53L13B
Fatal injuries
0
Pilot’s flight hours
20,840 total3,400 in this make and model60 in the last 90 days

From the FAA’s Accident/Incident Data System (AIDS), through its Aviation Safety Information Portal, as reported. The NTSB investigates accidents separately, and its record of an accident is the fuller one. The aircraft is matched to the registry 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.

What happened

The FAA’s narrative, in sentence case. The FAA writes it in capitals and removes private details.

(-23) An inspection of the wreck concluded that the engine had failed. The engine has been sent back to the manufacturer for analysis. Honeywell rep. Dave looper coordinated the shipping and inspection. (.4)according to the pilot, he was about 30 minutes into the post inspection maintenance flight at about 350 to 400 feet AGL, when he heard a loud 'bang' and engine RPM decayed to zero. His choice of autorotation site required use of main rotor RPM to clear trees and he landed hard and rolled over. The T-53-L-13B engine underwent factory disassembly examination, with FAA oversight. Material analysis determined that portions of the 2nd stage gp turbine disc had fractured and separated due to peak strain low cycle fatigue, resulting in structural and imbalance damage and engine failure. No material, lubrication, or fuel control defects were identified that would have contributed to the disc separation.

As the FAA filed it

(-23) AN INSPECTION OF THE WRECK CONCLUDED THAT THE ENGINE HAD FAILED. THE ENGINE HAS BEEN SENT BACK TO THE MANUFACTURER FOR ANALYSIS. HONEYWELL REP. DAVE LOOPER COORDINATED THE SHIPPING AND INSPECTION. (.4)ACCORDING TO THE PILOT, HE WAS ABOUT 30 MINUTES INTO THE POST INSPECTION MAINTENANCE FLIGHT AT ABOUT 350 TO 400 FEET AGL, WHEN HE HEARD A LOUD 'BANG' AND ENGINE RPM DECAYED TO ZERO. HIS CHOICE OF AUTOROTATION SITE REQUIRED USE OF MAIN ROTOR RPM TO CLEAR TREES AND HE LANDED HARD AND ROLLED OVER. THE T-53-L-13B ENGINE UNDERWENT FACTORY DISASSEMBLY EXAMINATION, WITH FAA OVERSIGHT. MATERIAL ANALYSIS DETERMINED THAT PORTIONS OF THE 2ND STAGE GP TURBINE DISC HAD FRACTURED AND SEPARATED DUE TO PEAK STRAIN LOW CYCLE FATIGUE, RESULTING IN STRUCTURAL AND IMBALANCE DAMAGE AND ENGINE FAILURE. NO MATERIAL, LUBRICATION, OR FUEL CONTROL DEFECTS WERE IDENTIFIED THAT WOULD HAVE CONTRIBUTED TO THE DISC SEPARATION.

NTSB investigation

The NTSB’s investigation of this event, with its probable cause and findings. Matched to this report by N-number and date.