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|  MIL-L-23822C(AS)
4.4.3.2 (Cont'd)
At the conclusion of each temperature cycling series, the rocket
engine and the propellants shall be stabliz ed at the final cycle
temperature and shall then be static fired. The results of the
firing shall indicate compliance with the requirements of 3.4.
4.4.3.3
Vibration. Vibration tests shall be performed
on the following components of two rocket engines. The pro-
pulsion unit, the multi-purpose nitrogen valve, the oxidizer valve
and shear fitting, the fuel valve and shear fitting, and the two
nitrogen check valves shall each be attached to its respective
rigid fixture capable of transmitting the vibration conditions spec-
ified herein. Attachment of each component listed above to its
respective fixture shall be made through the service mounting
which represents dynamically the most adverse service mounting
possible. The amplitude of applied vibration shall be monitored
on each test fixture near the component's mounting points.
Resonance survey. A resonance survey shall
4.4.3.3.1
be conducted on each component (listed in 4.4.3.3) of two rocket
engines. Vibratory accelerations not greater than 3 g's shall
be applied successively along each of the axes noted below:
a. Parallel with the longitudinal axis of the unit
b. Along an axis perpendicular to the longi-
tudinal axis
c. Along an axis perpendicular to both (a) and (b)
Each component (listed in 4.4.3.3) shall be vibrated throughout
the frequency range of 20 cps through 1200 cps by slowly vary-
ing the frequency over a one-hour period. If required by avail-
able test equipment, the tests may be conducted in stages. All
resonant frequencies shall be recorded for use in 4. 4.3.3.2
and 4.4.3.3.3.
Vibration endurance. Following the resonance
4.4.3.3.2
survey, 4.4.3.3.1, each component of one rocket engine (listed
in 4.4.3.3) shall be vibrated for a total of three hours in each
of the frequency bands noted below. This three hour period shall
be divided equally between the three axes noted in 4.4.3.3.1.
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