The HH-53C follow-on tests were conducted to identify the effects of salt water ingestion in regard to engine deterioration, to identify system deficiencies, and the effects of high altitude operation particularly as it affects the auxiliary power plant (APP). The more important findings were as follows: (1) salt water exposure can cause significant engine power deterioration; therefore, engine air particle separators should be used for protection; (2) the second stage hydraulic system can overheat with ambient temperature conditions as low as 50 degrees F; (3) the APP operation was adequate for high altitude conditions; (4) downwind hover caused ingestion of exhaust gases into the oil coolers resulting in oil overtemperature; (5) the aircraft brakes were inadequate at high altitude, high gross weight combinations which required running landings and takeoffs. (Author)
Category II Systems Follow-On Tests fo the HH-53C Helicopter
1972
29 pages
Report
No indication
English
Optimal Category-A Helicopter Takeoff from a Runway
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