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|  MIL-L-23822C(AS)
Static exposure. The rocket engine shall operate
3.5.1
after static exposure at a temperature of +140 F 3 F when
supplied with propellants at a temperature of +140 F 3 F, and after
static exposure at a temperature of -65 F 3 F when supplied
with propellants at a temperature of -65 F 3 F. The rocket
engine shall meet the performance requirements of 3.4 after being
subjected to the static exposure test of 4.4.3.1.
The rocket engine shall meet
Temperature cycling.
3.5.2
the requirements of 3.4 after being subjected to the temperature
cycling test of 4.4.3.2.
Vibration.
3.5.3
Vibration endurance. The rocket engine shall meet
3.5.3.1
the requirements of 3.4 after being tested for a minimum of nine
hours as specified in 4.4.3.3.2.
The rocket engine
Vibration endurance life test.
3. 5.3.2
shall be tested as specified in 4.4.3.3.3.
The probability of successful operation
Reliability.
3.6
of the rocket engine shall be not less than O.975 at the 80 per cent
confidence level.
Safety. The Liquid Propellant Rocket Engine LR64
3.7
shall meet the minimum safety requirements of WS-4613.
Cleanliness. All components and assemblies of the
3.8
rocket engine shall be free from burrs, sharp edges, scratches,
chips, grease, oil and other foreign material which could result
in malfunction of the rocket engine or components, or which could
be a safety hazard in handling.
Workmanship. The rocket engine, including all parts
3.9
and assemblies, shall be constructed and finished in a manner to
assure compliance with all requirements of this specification. Part
icular attention shall be paid to marking of parts and assemblies,
to plating, machine screw assemblage, welding and brazing where
applicable. The standards of workmanship exhibited in any approved
preproduction sample, subject to any qualification stated in the
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