Artificial and natural icing flight tests were conducted on the UH-60A Black Hawk helicopter to verify the existence of a light icing envelope. Testing consisted of 9.0 productive flight hours in the icing environment. The aircraft handling qualities and vibration levels were acceptable throughout the limited artificial and natural icing conditions tested. The UH-60A demonstrated safe operation in light icing conditions up to and including 0.3 gm/m3 LWC without operating the blade deice system. However, the potential for aircraft damage exists in icing conditions greater than 0.3 gm/m3. Three deficiencies were identified including aircraft damage from rotor system ice sheds, improper droop stop positions during shutdown, and failure of the blade deice electrical protection system to protect the blades against a heater element short circuit.
UH-60A Light Icing Envelope Evaluation with the Blade Deicing Kit Installed But Inoperative
1982
59 pages
Report
Keine Angabe
Englisch
Aircraft , Ice formation , Rotor blades(Rotary Wings) , Flight testing , Flight envelope , Environments , Vibration , Aerodynamic characteristics , Damage assessment , Helicopter rotors , Deicing systems , Ice prevention , Helicopters , UH-60A aircraft , Black hawk helicopters , Rotor systems ice sheds , Icing envelopes , Artificial icing , Natural icing , Handling qualities , flying qualities , Droop stop positions
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