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MIL-A-62463B(AT)
4.6.6 Breakout pressure. To determine conformance to 3.4.1.6:
a. For type I actuator only:
1. Plug port 3.
2. Apply 3200 200 psi (22,064 1,380 kPa) to port 11 and hold this pressure.
b. Slowly apply pressure to the appropriate port (2 or 17) and increase pressure until wing
shaft rotation occurs and continues. Perform this operation with wing shaft in the full
CW position, the full CCW position and in both directions from mid-travel. Record the
pressure required to initiate rotation in each case.
4.6.7 Vane seal and piston ring leakage. To determine conformance to items 1 and 2 of tables I
and III:
4.6.7.1 Vane seal leakage.
a. For type I actuator:
1. Plug port 3.
2. Apply 3200 200 (22,064 1,380 kPa) to port 11 and hold this pressure.
b. Alternately apply pressure to ports 2 and 17 for type I actuator, or to ports 2 and 7 for
type II actuator, and cycle shaft 15 times in each direction of rotation. Apply
3200 200 psi (22,064 1,380 kPa) for 5 seconds at each end of cycle (at full rotation).
c. Apply 3200 200 psi (22,064 1,380 kPa) to the ports specified in table VII, with the
shaft secured at the positions listed in table VII. In each case, hold 3200 200
(22,064 1,380 kPa) and measure leakage form the ports specified below (see 4.3.2).
1. Type I actuator vane seal leakage from port 2 or 17, whichever is not used to apply
pressure.
2. Type II actuator vane seal leakage from port 2 or 7, whichever is not used to apply
pressure.
4.6.7.2 Piston ring leakage.
a. For type I only:
1. Plug port 3.
2. Apply 3200 200 psi (22,064 1,380 kPa) to port 11 and hold this pressure.
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