TCH.1C-27J-2-29JG
2-7.2
BLEEDING NO. 1 SYSTEM (refer to figure
(Cont'd)
3.Supply the circuit from the test stand, then operate the
following controls several times in order to bleed No. 1
system: flaps (normal circuit), spoilers, elevators and
rudder.
NOTE
Perform step 4 and step 6 only in case of
bleeding due to a complete system
replenishment or the Reservoir installation.
4.Bleed the aircraft reservoir pressurization pipe by
slacking the pipe fitting (9) from union (10) of the
reservoir No. 1 system.
5.The system is bled when the hydraulic fluid, visible
through the test stand transparent pipe, is free of air
bubbles.
6.Retighten the pipe fitting (9) at the union (10) after
bleeding.
7.Stop the hydraulic test stand (AGE NO. 00262) and
annul the pressure.
2-7.3
BLEEDING NO. 2 SYSTEM (refer to figure
)
1.Set up the hydraulic test stand (AGE NO. 00262) as
follows: flow 8 gpm (30 l/min), pressure 1422 psi (98.9
kg/cm²), operating with stand reservoir depressurized
(aircraft reservoir empty) and return pressure 17 psi
(1.20 kg/cm²).
2.Connect delivery and return hoses of the hydraulic
test stand to respective No. 2 system test ports of
ground service panel by removing caps (4 and 5) of
the delivery hoses (7) and return hoses (6).
(Cont'd)
29-10-00
2-47