MIL-I-18259(Aer)
letters 1/2 inch high, and include the following information, as applicable:
FILL WITH:
(Name and Specification number of fluid or fluids)
WHEN CHANGING FLUIDS DRAIN AND FLUSH WITH
CAPACITY
TO
PSIG
PRESSURE WITH
(Additional filling instructions or data considered necessary)
3.4 Pressure Relief Valves and Safety Discs. - The design of the system shall include
pressure relief valves or other safety features as required to prevent overpressurizing or
excess pressure due to thermal expansion.
3.5 Drain.- Systems utilized for dual purposes shall provide a means for draining and
flushing the system at the lowest point.
3.6 Threaded-Fittings.- AN and MS straight threaded fittings only shall be used and
shall be assembled and connnected in accordance with Drawings AND10049, AND10056, and AND10064.
3.7 Supports.- All tubing shall be rigidly supported. Tube supports shall be such as to
prevent injury to the tubing. The maximum spacing between supports shall not exceed 24 inches,
except that where tubes support fittings the spacings shall be suitably reduced.
3.8 Spray Tube.- The spray tube shall be designed to provide adequate anti-icing, de-
greasing and washing with minimum greasing
3.9 Controls. - Controls shall be conveniently located with respect to operating
personnel
3.9.1 Control Markings.- Controls shall be marked to indicate their function, and
normal, minimum and maximum fluid flow where applicable
3.10 Gauge.- A suitable gauge shall be provided for indicating the amount of fluid in
tanks exceeding one gallon capacity. The gauge shall be so located in the aircraft as to be
plainly visible to operating personnel during flight.
3.11 Loss of Fluid.- The system shall be such that there will be no loss of fluid during
flight maneuvers of the aircraft.
3.12 De-Greasing.- De-greasing systems are required on reciprocating engine aircraft to
remove oil film from windows.
4. QUALITY ASSURANCE PROVISIONS
4.1 Classification of Tests.-
4.1.l Preproduction Tests.- The first of any new model of equipment and the first of any
installation in a new model aircraft shall be subjected to all the tests of this specification.
4.1.2 Inspection Tests.- Inspection tests are conducts on each installation. Inspec-
tion tests shall consist of Examination of System, Proof Pressure, and Ground test.
4.2 Examination of System. - Each system and component thereof not covered by detail
specifications, shall be carefully examined to determine conformance with all installation
requiremezts not covered by tests.
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