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|  MIL-W-81752A(AS)
3.9.2 - Interchangeability -
Items which require frequent
replacement such as transparent panels shall be designed to have
interchangeable fit and attach hole patterns in accordance with MIL-I-
8500 to permit replacement with minimum danger or damage during
Removal and re-installation shall be
installation of the new part.
possible without affecting the entire system.
3.3.9 - Handling - Windshield systems shall be designed to prevent
damage due to the strains imposed during ground handling, maintenance,
Areas which are convenient for seating and
removal, and servicing.
stepping by maintenance personnel shall be designed to withstand such
loads.
3.9.4 - Warpage - Parts, which are subject to warpage or
distortion when not installed, shall be suitably protected and shall
be placarded to forbid nesting, if applicable.
3.9.5 - Seals - Provisions shall be made to protect weather seals
and cockpit pressurization system seals from damage as a result of
normal maintenance activities and from normal entrance and egress by
Designs of seals shall provide for simple replacement.
the crew.
3.9.6 - Replacement - The design Mean Time To Remove And Replace
(MTTRAR) at the organizational level, shall be furnished as part of
the design approval report.
The minimum MTTRAR shall be as specified
by the procuring activity.
3.10 Reliabilty - Reliability shall be a basic consideration in
A reliability
the design of all components used in the system.
program shall be established in accordance with MIL-STD-785. The
design threshold reliability expressed quantitatively in MTBF shall be
furnished as part of the design approval report. The minimum MTBF
required shall be as specified in the contract (See 6.2.1).
3.11 - Design data - Prior to installation of a windshield
assembly or system on an aircraft, the contractor shall prepare a
report on the design of the system.
3.12 - Test plan - A report covering the proposed laboratory and
flight tests required to prove the system design, shall be prepared
prior to conducting of the final laboratory or flight test required to
prove the system performance.
4. - QUALITY ASSURANCE PROVISIONS
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