20200406003849A

Accident · Substantial damage

FAA accident report · Robinson Helicopter R44 II · Hillsboro, OR · April 6, 2020

Date
April 6, 2020 · 14:05 local
Place
Hillsboro, OR
Airport
Portland-Hillsboro
Phase of flight
Takeoff: Rotation
Operating rules
General operating rules (Part 91)
Damage
Substantial damage
Aircraft
N725GT
NTSB investigation
NTSBWPR20LA119
Reported as
Robinson Helicopter R44 II
Reported engine
Lycoming IO-540-AE1A5
People aboard
1
Fatal injuries
0
Other injuries
0
Pilot’s certificate
Airline transport
Pilot’s flight hours
11,000 total

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.

Upon departure from the ramp area, at approximately 30 ft AGL and at 30 KIAS, the pilot indicated they heard and felt a loud ?bang?, followed by a noticeable reduction in engine RPM. The pilot then observed the low rotor RPM horn and warning light, and entered into an autorotation. Upon landing on the taxiway, the aircraft received substantial damage to the tail section and landing gear.

Two witnesses on the ground observed the aircraft?s departure, each noting an audible ?pop? Followed by a partial reduction in engine RPM as the aircraft climbed to approximately 30 ft AGL. One witnesses on the ground observed the pilot shut down the engine post landing.

During the post-crash teardown, separation between the outer and inner layers of the engine air induction hose, Robinson part number A785-31, manufacturing batch code 3Q17, was observed. The air induction hose was sent to the NTSB lab for further testing and could not be determined as a causal factor the investigation.

As the FAA filed it

UPON DEPARTURE FROM THE RAMP AREA, AT APPROXIMATELY 30 FT AGL AND AT 30 KIAS, THE PILOT INDICATED THEY HEARD AND FELT A LOUD ?BANG?, FOLLOWED BY A NOTICEABLE REDUCTION IN ENGINE RPM. THE PILOT THEN OBSERVED THE LOW ROTOR RPM HORN AND WARNING LIGHT, AND ENTERED INTO AN AUTOROTATION. UPON LANDING ON THE TAXIWAY, THE AIRCRAFT RECEIVED SUBSTANTIAL DAMAGE TO THE TAIL SECTION AND LANDING GEAR.

TWO WITNESSES ON THE GROUND OBSERVED THE AIRCRAFT?S DEPARTURE, EACH NOTING AN AUDIBLE ?POP? FOLLOWED BY A PARTIAL REDUCTION IN ENGINE RPM AS THE AIRCRAFT CLIMBED TO APPROXIMATELY 30 FT AGL. ONE WITNESSES ON THE GROUND OBSERVED THE PILOT SHUT DOWN THE ENGINE POST LANDING.

DURING THE POST-CRASH TEARDOWN, SEPARATION BETWEEN THE OUTER AND INNER LAYERS OF THE ENGINE AIR INDUCTION HOSE, ROBINSON PART NUMBER A785-31, MANUFACTURING BATCH CODE 3Q17, WAS OBSERVED. THE AIR INDUCTION HOSE WAS SENT TO THE NTSB LAB FOR FURTHER TESTING AND COULD NOT BE DETERMINED AS A CAUSAL FACTOR THE INVESTIGATION.

NTSB investigation

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