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Page Title:
Noise-Level Measurements (Turbo-Shaft) |
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| MIL-D-23222A(AS)
(Cont)
3.10.5.3
(b) 60 percent to 100 percent intermediate power.
(C) Idle to 100 percent intermediate power.
(2) Turbo-shaft Engines
(a)
RPM for power approach to intermediate power.
(b)
RPM for power approach to maximum power.
(C)
Idle to 100 percent intermediate power.
(d)
Idle to maximum power.
(e)
Normal rated to intermediate power.
(f)
Intermediate to maximum power.
(g)
Minimum power to maximum power.
(h)
Minimum booster engine power to maximum
booster engine power.
On multi-engine helicopters, required for two engines on one side
only. This test shall be performed by starting with slow acceleration
and deceleration rates then increasing to an intermediate rate and
finally increasing to a snap rate (idle to Intermediate throttle advance-
ment time second). Snap rate need not be perfomed with the manual
control in (d), (e), (f), and (h). Data shall be recorded at one
fourth second intervals. A minimum of 10 data points; (or sufficient
data to show control system transients) shall be reported for each
acceleration and deceleration.
3.l0.5.4
NOISE LEVEL MEASUREMENTS (TURBO-SHAFT). - With
all engines operating at intermediate ratings noise
level measurements shall be taken on the ground on one side of the
helicopter only, at 30 intervals on 25 foot and 5O foot radii, on
lines originating at the aft-most portion of tail pipe(s). Instru-
mentation action shall be reported in the Instrumentation Report
Item (1) of 3.2.
ENGINE CHARACTERISTICS AT VARYING POWER LEVER
3.10.6
SETTINGS
3.10.6.1
ALTITUDE IDLE SCHEDULE AT LOW AIRSPEEDS. - A low
speed descent from service ceiling to 2000 feet
pressure altitude with power lever in idle position (flight idle for
turbo-shaft engines) shall be performed.
3.10.7
ALTITUDE POWER CONTROL PERFORMANCE
69
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