 |
|||
|
|
|||
| ||||||||||
|
|  MIL-H-8891A
Set ground test reservoir pressurizing valve to
psi
Set ground test stand relief valve to
psi
Set ground test stand output to
gpm
Set ground test stand pressure compensator to
psi
--
Use hydraulic fluid conforming to MIL-H-8446
Ground test stand output filter shall be microns absolute
(Any other precautions or information considered necessary.)
NOTE :
The contractor shall fill in the above values.
CAUTION NOTE:
The vehicle manufacturer shall provide a caution note
stipulating the maximum safe flow for landing-gear
retraction checks during the time the aircraft is on
jacks.
Removal of entrapped air - Suitable means, such as
3.5.5
bleeder valves, shall be provided for removal of entrapped air. Disconnec-
tion of lines or loosening of tubing nuts does not constitute "suitable
means". Equipment and system configuration shall, insofar as practicable,
be designed to automatically scavenge free air to a reservoir or other col-
lection points where operation will not be affected and where release can
be conveniently accomplished (see 3.10.4).
3.5.5.1
System air tolerance - The system shall be designed
and configured such that the presence of entrapped air that is not removed
or scavenged per paragraph 3.5.5 shall not cause sustained loss of system
pressure or degradation of system performance during all conditions of in-
tended vehicle operation.
3.5.6
System pressure indication - Pressure-indicating equip-
ment acceptable to the procuring activity shall be provided to indicate the
system pressure in hydraulic systems or subsystems. On engine-driven multi-
pump systems, pressure-indicating equipment shall be provided for each pump
to enable the flight crew to check for proper operation of each pump with
shutdown of any engine. The pressure indicators shall be so located as to
be readily visible by the flight crew.
3.5.6.1
System low-pressure warning light - In addition, but `
not as a substitute for the requirement of 3.5.8, a suitable warning light
shall be installed in the cockpit in a conspicuous location to warn the
pilot of low hydraulic system pressure. The light shall be actuated by a
pressure switch in the system. For Navy vehicles, there shall be a separate
warning light for each hydraulic system. The warning light, or lights, shall
not be actuated by any combination of flight-control operations under normal
operations. A momentary flicker of the warning light during ground checkout
only is permissible, provided such condition is adequately described in the
appropriate vehicle operation and maintenance manuals and provided such con-
dition does not occur during flight unless a system malfunction exists.
3.5.6.2
Maintenance check gages and indicators - Pressure gages/
indicators that require a preflight, postflight, or daily check shall not
require workstands or platforms in order to read the gages or indicators.
|
|
Privacy Statement - Press Release - Copyright Information. - Contact Us |
Click
here for thousands of PDF manuals