Quantcast Table 2-1. Operator's Controls. (cont) - TM-1-6625-735-140042

 

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Table 2-1. Operator's Controls. (cont) - TM-1-6625-735-140041
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TM-1-6625-735-14 Test Set Stabilization System P/N 70700-20650-050 Manual
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Table 2-1. Operator's Controls. (cont) - TM-1-6625-735-140043
TM 1-6625-735-14
Table 2-1.
Operator's Controls. (Cont)
CONTROL, INDICA-
TOR, TEST POINT, OR
CONNECTOR
FUNCTION
NO. 1 and NO. 2 AS SW
Go on to indicate simulated airspeed is less than 60 knots. When indicators are
,60 KNOTS Indicators
on, 15 vdc can be monitored at NO. 1 and NO. 2 AS SW test points. When
indicators are off, -15 vdc can be monitored at NO. 1 and NO. 2 AS SW test
points.
No. 1 and No. 2 INTLK
Go on when No. 1 and No. 2 stabilator amplifiers are electrically connected
28 and No. 1 and No. 2
and helicopter dc electrical power is applied to stabilator system. Power that
INTLK 28 OS Indicators
turns on No. 1 INTLK 28 indicator also turns on No. 2 INTLK OS indicator.
Power that turns on No. 2 INTLK 28 indicator also turns on No. 1 INTLK 28
OS indicator. When indicators are on, 28 vdc can be monitored at No. 1 and
No. 2 INTLK 28 vdc test points.
ENGAGE 1 Indicator
Goes on to indicate stabilator control/auto flight control panel SAS 1 switch is
engaged and stability augmentation system (SAS) amplifier is installed. Power
is supplied from helicopter dc electrical power system, through engaged posi-
tion of control panel SAS 1 switch, through SAS amplifier, and through test
set connector J3 to ENGAGE 1 indicator. Pressing test set LAMP TEST but-
ton also causes ENGAGE 1 indicator to go on.
ENGAGE 2 Indicator
Goes on to indicate stabilator control/auto flight control panel SAS 2 switch is
engaged. Power is supplied from helicopter dc electrical power system, through
engaged position of control panel SAS 2 switch, and through test set connector
J3 to ENGAGE 2 indicator. Pressing test set LAMP TEST button also causes
ENGAGE 2 indicator to go on.
AIRSPEED SWITCH
Provides capability for simulating and visual monitoring of airspeed logic com-
Simulator
mands. These commands are used for testing coordinated turn function of SAS
amplifier yaw channel.
,60 KNOTS Indicator
Goes on to indicate that simulated or monitored airspeed is less than 60 knots.
When mode selector control is placed to ,60 KNOTS, 15 vdc from test set
power supply controls circuitry in test set, allowing 28 vdc from test set 28
VDC SAS circuit breaker to turn on indicator. When mode selector control is
placed to ,60 KNOTS, 15 vdc is also supplied through test set connector J3
to SAS amplifier. When mode selector control is placed to NORM, No. 1 sta-
bilator amplifier airspeed switch logic is supplied through test set connector J3,
through NORM of mode selector switch, and back through connector J3 to
SAS amplifier. If No. 1 stabilator amplifier airspeed switch logic is +15 vdc,
,60 KNOTS indicator goes on. Pressing test set LAMP TEST button also
causes indicator to go on.
Mode Selector Control
NORM supplies No. 1 stabilator amplifier airspeed switch logic commands
through test set connector J3 to SAS amplifier. If logic command is 15 vdc
(,60 knots), circuitry in test set allows 28 vdc from test set 28 VDC SAS cir-
cuit breakers to turn on ,60 KNOTS indicator.,60 KNOTS supplies 15 vdc
from test set power supply through test set connector J3 to SAS amplifier. In
this position, 15 vdc also controls circuitry in test set allowing 28 vdc from
test set 28 VDC SAS circuit breaker to turn on ,60 KNOTS indicator. >60
KNOTS supplies -15 vdc from test set power supply through test set connec-
tor J3 to SAS amplifier.
2-25

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