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Table 2-1. Operator's Controls
Up
TM-11-6625-2843-14 Test Set Synchro TTU-23/E Manual
Next
Operating Procedures for Differential Test
TM 11-6625-2843-14
POWER-INPUT connector J202.
a n d (6) below, and if it is a dual unit, omit (3) and (4)
( 4 ) With aircraft power available, set POWER 1 7
below.
switch to ON. Check to see that POWER 16 indicator
(3) Connect autosyn test cable J (QB84930-1)
lights.
from the indicator under test to test adapter cable G
( 5 ) Check for 26 volts ac 10 percent across 26V
(QB86030-1).
b i n d i n g posts 18 and 19.
(4) Connect power source cable F (QB86032-1),
f r o m the disconnected aircraft cable to adapter cable B
(6) Check for 10.8 volts ac 10 percent across
1 0 . 8 V binding posts 19 and 20.
(QB86031-1), and connect the adapter cable to
POWER-INPUT connector J202.
b. Calibration Procedure.
(5)
Connect
dual
indicator
test
cable
K
( 1 ) Perform initial test procedure (a above).
(QB86029-1) from the indicator under test to test
(2) Rotate AMPLIFIER
GAIN
8
control
fully
adapter cable G (QB86030-1).
clockwise.
(6) Connect power source cable E (QB86031-1)
( 3 ) Set TEST SEL 2 switch to SERVO, and allow
f r o m the disconnected aircraft cable to adapter cable B
the test set a l-minute warmup interval.
(QB86031-1), and connect the adapter cable to
NOTE
POWER-INPUT  connector  J202.
The signal input to the servoamplifier is
(7) With aircraft power available, set POWER 17
taken from the center tap of AMPLIFIER
switch to ON. Check to see that POWER 16 indicator
GAIN 8 control. The source for this voltage
lights. Allow the test set a l-minute warmup interval.
m a y be measured across VTVM binding posts
( 8 ) Check for 26 volts ac 10 percent across 26V
2 1 and 22,
b i n d i n g posts 18 an 19.
(4)  Rotate  transmitter  B201  to  the  angles
(9) Check for 10.8 volts ac 10 percent across
specified by the calibration book for the unit under
1 0 . 8 V binding posts 19 and 20.
test.
b. Electrical Zero Check.
(5) Check to see that the unit under test tracks
( 1 ) Perform initial test procedure (a a b o v e ) .
transmitter B201 is within acceptable tolerances.
( 2 ) Set TEST SEL 2 switch to SYN IND.
c. Low-Inertia Motor Test
( 3 ) Set SYN IND 4 switch to E-Z.
( 1 ) Perform calibration procedure (b a b o v e ) .
( 4 ) The indicator assumes its electrical zero posi-
(2) Set TEST SEL 2 switch to MOTOR.
tion. Check this position against the calibration value
( 3 ) Set MOTOR VOLTS 7 switch to VAR 0
for the unit under test.
(4) Adjust MOTOR VOLTS VAR 6 control for
c. C a l i b r a t i o n P r o c e d u r e .
rated voltage of motor under test as measured at
( 1 ) Perform electrical zero check (b a b o v e ) .
VTVM binding posts 21 and 22.
( 2 ) Set SYN IND 4 switch to CAL.
( 5 ) Set MOTOR VOLTS 7 switch S201 to FXD .
(3)  Rotate  transmitter  B201  to  the  angles
(6) Slowly advance MOTOR VOLTS 5 control
specified by the calibration book for the unit under
until the pointer of the indicator under test begins to
test.
rotate.
(4) Check to see that the unit under test tracks
(7) Check to see that the fixed-phase voltage
transmitter B201 is within acceptable tolerances.
measured at binding posts 21 and 22 is within the
(5) Turn POWER 17 switch to off.
t o l e r a n c e s specified for the motor.
( 6 ) Disconnect all test cables.
(8) Set MOTOR VOLTS 7 switch to VAR and
(7) Reconnect the aircraft cable to the indicator
adjust MOTOR VOLTS FXD 5 control to the level ob-
under
test.
t a i n e d in (7) above.
2-8.  Operating
Procedures
for
Servoed
In-
( 9 ) Advance MOTOR VOLTS VAR 6 control un-
dicator  Test
t i l the indicator under test begins to rotate.
O p e r a t i n g procedures for servoed indicator test include
(10) Monitor the variable-phase starting voltage
a n initial test, a calibration procedure, and a low-iner-
a c r o s s VTVM binding posts 21 and 22.
tia motor test.
(11) Turn POWER 17 switch to off.
a. Initial Test.
( 1 2 ) Disconnect all test cables.
( 1 ) Disconnect the aircraft cable to the servoed in-
(13) Reconnect the aircraft cable to the indicator
dicator under test.
under test.
(2) Connect servoed indicator test cable H
Operating
Procedures
for
Transmitter
(QB84967-1) from the indicator under test to test
Test
adapter cable G (QB86030-1).
(3) Connect power source cable C (QB86033-1)
a  Disconnect
the
aircraft
cable
to
transmitter
f r o m the disconnected aircraft cable to adapter cable B
under test.
b. C o n n e c t a u t o s y n t e s t c a b l e J ( Q B 8 4 9 9 8 - 1 ) f r o m
(QB86063-1), and connect the adapter cable to

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