MIL-T-18607(Aer)
3.8.1.2 Bonding. -Electrical bonding shall be in accordance with MIL-B-5087
with special allowance made for flexibility in the bonds to provide for thermal
expansion.
3.8.2 Voltage. -The equipment shall be designed to operate from the primary
electrical power system of the aircraft.
3.8.3 Power. - Electrical power consumption of any single heating unit l .Xier
continuous operation shall not exceed 100 watts.
3.9 Reports and Engineering data.
3.9.1 Anti-icing system data. - The airplane manufacturer shall submit to the
procuring acitiviy for approval a report on the design of the system showing a
complete schematic drawing of the proposed system and complete data on heat require-
ments and heat available and weight. These data shall be sufficiently detailed to
permit evaluation of the accuracy of the methods used and shall contain complete sample
calculations for at least one condition. The report shall also contain a word
description of system operation. Submission and approval of this report is a
prerequisite for any other approvals on the system or equipment.
3.9.2 System test report. - Prior to conducting ground or flight tests of
the system, the contractor shall submit a test program for approval by the procuring
activity.
3.9.3 Evaluation and extrapolation. - At the completion of the flight testing
of the system, a complete report on the testing shall be submitted. This report shall
include an evaluation and extrapolation of the data to design icing conditions. Final
approval of the anti-icing system is contingent on satisfactory submission on this
data.
3.10 Workmanship. -The anti-icing system, including all parts and acces-
sories, shall be fabricated and finished in a thoroughly workmanlike manner.
Particular attention shall be given to freedom from defects, accuracy of dimensions,
and marking of parts and assemblies.
4.
QUALITY ASSURANCE PROVISIONS
4.1 Preproduction tests:
4.1.1 A representative item of each item of equipment used in the system
shall be tested to indicate suitability of the design for the use intended. These
tests shall be in accordance with the manufacturer-approved equipment s-pacifications
and shall include life and performance tests, plus the applicable environmental tests
in accordance with Specification MIL-E-5272A.
4.2 Prototype tests:
4.2.1 The ground and flight tests specified below shall be conducted on an
airplane to demonstrate compliance of the anti-icing equipment with the requirements
of this specification. Wherever possible, it is desirable to conduct these tests on
ground mock-ups, if his facilities permit, to preclude damage to the airplane in case
of system malfunction and to ensure early detection of deficiencies. Details of
testing shall be in accordance with the manufacturer-approved testing specification
and shall include the tests listed in 4.2.2 and 4.2.3.
4.2.2 Ground test. - Ground tests shall be conducted to demonstrate control
system operation, temperature indication system operation, operation of overheat
warning or control, general security and safety Of the system for flight testing,
distribution of available airflow, and freedom from overheating and detrimental effects
of differential expansion.
4.2.3 Flight tests .-Flight tests shall be conducted to demonstrate control
system operation, temperature indication operation, operation of overheat warning or
control, freedom from overheating and detrimental effects of differential expansion.
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