TCH.1C-27J-2-29JG
Safety Conditions:
Be aware of information contained in SAFETY
PROCEDURE - FUNCTIONAL TEST (refer to para
)
before performing functional test.
PROCEDURE:
2-33.1 This test is to be performed after the replacement
of the Hydraulic Fluid Quantity Indicator.
A.Throughout the window check on the reservoir No.
1 (No. 2) visual fluid level quantity indicatorthat the
hydraulic fluid quantity is about 12.5 litres.
B.Connect the external electrical power supply 115 V
ac (six pin plug) to the aircraft and switch-on.
C.Power on the aircraft as follows:
-On the Electrical Power Generation System
Control Panel (202VE) set the battery switch to
ON;
-On the Electrical Power Generation System
Control Panel (202VE) check that the light
AVAIL(on the pushbutton AC EXT) illuminates;
-On the Electrical Power Generation System
Control Panel (202VE), press the pushbutton
ACEXT and check that the light ON illuminates.
D.Ensure that the circuit breaker HYDRAULICS IND
QTY (33DE), located on Overhead Circuit
Breakers Panel (271VE) in position B 5, is closed.
E.Check that the quantity indicator pointer SYS 1
(SYS 2) in the Hydraulic Fluid Quantity
Indicator,located on the main instrument panel (RH
side) indicates about Full.
F.Power off the aircraft (battery switch to OFF) and
depress the AC EXT pushbutton.
G.Switch-off the external power supply and
disconnect the six pin plug from the aircraft.
29-30-20
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