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| MIL-T-18232B(AS)
3.10.6.2.3
AIR INTAKES (PULSE JETS, RAMJETS, AND AIR AUGMENTED ROCKETS).
The permissible variation in total pressure at the diffuser
outlet shall not be greater than that established by the engine manufacturer and
approved by NAVAIR,
3.10.6.3
DUST PROTECTION SYSTEM RECIPROCATING, JET, TURPOPROP, AND
TURBOSHAFT ENGINES). - When required by the detail specifi-
cation, an air filter shall be provided.
3.10.7
EXHAUST SYSTEM
3.10.7.1
DESCRIPTION. - Exhaust system includes all pipes, stacks,
manifolds, and collectors together with flanges, and necessary
supports and attachments therefor used in carrying off exhaust gas. Exhaust
system joints5 connections, and necessary supports shall allow for thermal
expansion without damage to the engine or exhaust system. Suitable clearance
shall be provided between the exhaust system and nonstructural parts. Due con-
sideration shall be given to thermal effects on the adjacent structure
3.10.7.2
EXHAUST SYSTEMS (RECIPROCATING ENGINES). - The open end of
any exhaust pipe shall have suitable clearance in every
direction from flammable parts, and the exhaust gases shall not directly impinge
on any structural member.
3.10.7.3
PROPULSION OR ROCKET EXHAUST SYSTEMS (OTHER THAN RECIPROCATING).
The exhaust pipe nozzle shall be so located that the portion
of the jet within 15 included angle shall not impinge upon any part of the
target. If this is impracticable, protection as necessary shall be provided for
the target. The exhaust system outlet areas shall conform to the value upon which
the engine performance guarantees are based as specified in the applicable engine
specification. In the event that an area or a range of areas (variable tailcone)
differing from the above is employed, approval shall be obtained from NAVAIR.
3.10.8
COOLING SYSTEM
DESCRIPTION. - The cooling system shall be as required by
3.10.8.1
the detail specification.
3.10.8.2
COOLING SYSTEMS (RECIPROCATING ENGINES). - The cooling system
shall meet the temperature requirements of Specification
MIL-C-8678. Means shall be provided. to conduct or deflect the heat from exhaust
stacks or collectors away from the engine and accessory compartment.
3.10.8.3
COOLING SYSTEMS (TURBO ENGINES). - Cooling for engine com-
ponents shell be provided in accordance with the requirements
of Specification MIL-C-8678.
LUBRICATING SYSTEM
3.10.9
33
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