Eagle ICA-D212-725, Инструкция по эксплуатации

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ICA-D212-725 (76)
Page 19 of 21
CHAPTER 76 – ENGINE CONTROLS (76-00-00)
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COPYRIGHT

2007 BY DART AEROSPACE LTD.
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THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED OR COMMUNICATED TO ANY
OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
Revision:
0
Date: 07.05.31
76.3.2.1.3 Remove four screws with four
shims securing solenoid (19) to bracket
assembly (21).
76.3.2.2 Installation – Flight Idle
Solenoid
76.3.2.2.1
Position solenoid (19, Figure 76-
3) on bracket assembly (21) and, using
previously removed shims, secure with four
screws.
76.3.2.2.2 Check
that plunger of solenoid
is centered through bushing (22). If necessary,
adjust thickness of shims to align plunger
through bushing.
76.3.2.2.3
Position solenoid with base (20)
on fuselage structure and secure in place with
four bolts and four washers. Position solenoid to
its lowest position so that cam will not contact
solenoid at any position. (Final adjustment will
be accomplished during rigging.)
76.3.2.2.4 Connect cable assembly
terminals to terminals of solenoid.
76.3.2.2.5
Position cam (24) on bellcrank
(23) and secure with two bolts and two serrated
washers. Make final adjustment of cam during
rigging (Refer to paragraph 76.3.2.3.)
76.3.2.3 Rigging – Flight Idle Solenoid
76.3.2.3.1
Rotate twist grip control on
collective lever until the power shaft stop arm
(39, Figure 76-3) is aligned with the 38 degree
mark on the engine fuel control.
76.3.2.3.2 Check
that plunger of solenoid
(19 operates freely through bracket bushing
(22). If necessary, adjust shims between
solenoid and bracket to obtain plunger
alignment.
76.3.2.3.3
Position solenoid (19) with
bracket (21) on serrated base (20) to obtain a
0.040 (1.016 mm) ± 0.010 inch (0.254 mm)
clearance between tip of plunger and projected
surface of cam (24). Secure in place with four
bolts and four washers.
76.3.2.3.4
Projected surface of arm should
be just aft of center line of the solenoid plunger.
Adjust cam (21) on bellcrank (23) if necessary,
but clearance must still be maintained.
76.3.2.3.5
Check operation of flight idle
stop in ground run. If necessary, readjust to
obtain 71% ± 1% RPM, indicated on GAS
PRODUCER TACHOMETER (N1). Check
release by actuating solenoid using push button
switch pilot’s collective stick.
76.3.3 UpTrim for the T5317 Engine
76.3.3.1
Accomplish a maximum power
(torquemeter pressure) check. (Refer to FMS-
D212-725-1).
76.3.3.2
If the check is satisfactory,
uptrim is not required. If the installed engine
does not satisfactorily meet the maximum power
check, insure that the engine compressor is
clean and perform adjustment/test checks of the
variable inlet guide vane and bleed band
systems per Honeywell Maintenance Manual
T5313B and T5317 series. If these checks are
satisfactory, limited uptrim of the checks engine
is now allowed using the following procedure.
NOTE
Large changes in available torque
may signal more severe engine,
airframe, or instrument problems
which should not be treated as
normal deterioration requiring uptrim.
76.3.3.2.1 Fuel
Control Adjustment.
WARNING
ADJUSTMENTS TO THE FUEL
CONTROL MAY AFFECT
SAFETY OF FLIGHT. ONLY
DESIGNATED AND QUALIFIED