MIL-T-18607(Aer)
Flight conditions shall include at least the following:
(1) Normal Takeoff and climb to operating altitude
(2) Normal descent and landing
(3) Level flight at speed for maximum endurance,
maximum speed, and an intermediate speed approxi-
mately halfway between these speeds at 5,000,
12,000 and 20,000 feet altitudes
4.2.3.1 Instrumentation shall be Installed to determine the quantity and
temperature of air from each heat source and the temperature and quantity of airflow
in all main distribution ducts. least 3 wing stations on one side of the airplane
and 2 stations on one horizontal and one vertical tail surface shall be instrumented
to provide a chordwise profile of exterior and inner skin temperatures as well as
temperature drop and airflow through the double skin passages. Sufficient structural
temperatures shall be measured to ensure that structural overheating does not occur.
Shielded thermocouples shall be used for measuring air temperatures in locations
where there is a substantial difference between air temperature and the surrounding
metal. If there are discontinuities in the heated areas, sufficient temperature
measurements shall be made to determine the effect of the heat flow from the heated to
the unheated area.
4.3 Individual tests.
4.3.1 Each anti-icing "system installation shall be inspected and tested to
determine that the air distribution and system leakage is within allowable limits as
specified in the design analysis. In addition each installation shall be inspected to
meet the requirements of paragraph 3.10.
PREPARATION FOR DELIVERY
5.
(Not applicable.)
6.
NOTES
6.1 Intended use. - The equipment outlined in this specification is intended
for use in naval aircraft for preventing the formation of ice on the wing and
empennage surfaces during flight, and for removing frost from these surfaces prior to
take-off.
6.2 Windshield anti-icing.-The provision of windshield anti-icing, a
necessary item on any airplane equipped for operation in icing conditions, is not
covered in this specification, but will be included in the detail specification of the
airplane. If practical, windsheild anti-icing may be an integral part of surface
anti-icing as herein specified.
6.3 Cabin heating. - Cabin heating is covered in Specification MIL-H-18609(Aer)
and as in the case with windshield anti-icing, may be an integral part of the surface
anti-icing system as herein specified.
6.4 Publication. - NACA technical note No. 1472, "The Calculation of the heat
required for Thermal Anti-ice Prevention in Specified Icing Conditions" should be
studied thoroughly by the designer of the equipment herein specified.
PATENT NOTICE. - When Government drawings, specifications or
other data are used for any purpose other than in connection
with a definitely related Government procurement operation, the
United States Government thereby incurs no responsibility nor
-
any obligation whatsoever; and the fact that the Government
.
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