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Figure 4-4. Diagnostic Flow Chart for ADS Leak Test.
Up
TM-9-1270-219-13-P Fire and Flight Air Data Subsystem Helicopter Armament: XM 143 PN 03-004-02 Manual
Next
Figure 4-5. Pneumatic Circuit for AADS Pitot Leak Test.
TM 9-1270-219-13&P
the
stopwatch
when
the
indication
falls
b. E q u i p m e n t
Setting-Up
to 250 knots.
Verify the performance of the tester, pitot
(1)
After 60 seconds the indication shall not
in
accordance
with
TO
(6)
static systems
be lower than 220 knots.
33D-2-6-9-11.
Open the vent valve on the capacity tank
A p p l y power to the helicopter in accordance
(7)
(2)
to release the pressure.
with
TM
55-1520-236-23
or
TM
55-1520-
2 3 9 - 2 3 and switch on the power supplies to
e. AADS
Static
Leak
Test.
the Air Data Subsystem.
R e m o v e the AADS cover.
C h a n g e the pneumatic circuit to that shown
(1)
(3)
NOTE
(2)
Close the static vent valve on the tester
a n d adjust the baro-set to make the altimeter
A l I t h r e a d e d test connections are to be
read zero feet.
sealed by using 1 to 2 turns of teflon
plumbers tape.
(3)
C l o s e the vent valve on the tank. Close the
shut-off valve on the tank. Reduce the static
Helicopter Plumbing Check.
c.
pressure at the tester to 3200 feet.
(1) Check that all connections are tight.
(4)
Open the shut-off valve on the tank. Observe
the altimeter on the tester. Start the stop
(2) Check that there are no visible signs of
w a t c h when the indication falls to 3000 feet.
damage to the plumbing.
After 60 seconds the indication shall not
(5)
d. AADS Pitot Leak Test.
be lower than 500 feet.
Open the tank vent valve to release the
(6)
pressure.
Disconnect the pneumatic circuit and remove
(7)
Do not exceed the pressures stated or
the AADS adapter.
permanent
damage
may
result
to
the
AADS
seals
or
the
EPU
pressure
transducers.
f. E P U a n d P l u m b i n g P i t o t L e a k T e s t .
Remove the AADS from the helicopter as
(1)
Connect the pneumatic circuit as shown in
(1)
specified in paragraph 4-3.
Fix the adapter to the AADS pitot head.
(2)
Close the pitot vent valve on the tester.
(2)
Close the vent valve on the capacity tank.
(3)
Connect
the
pneumatic
circuit
shown
in
Raise the pitot pressure at the tester to
175 knots
the
airspeed
and
observe
indicator.
Close the vent and shut-off valves on the
(4)
capacity tank. Close the vent valve on the
tester. Open the pressure source valve on
(3)
O v e r a period of 120 seconds, the indication
the
tester
and
raise
the
pitot
pressure
at
shall not fall below 168 knots.
the tester to 255 knots.
Open the tank vent valve to release the
Open
the
tank
shut-off
valve
and
observe
(5)
(4)
pressure.
the
airspeed
indicator
on
the
tester.
Start
4-10

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