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|  MIL-L-23822C(AS)
The frequency bands and associated acceleration input levels
shall be as follows:
Nine (9) g's
a. 20 to 60 CpS
Three (3) g's
b. 60 to 500 CpS
One (1) g
c. 500 to 1200 Cps
In each axis and in each frequency band the test time shall be
divided equally between those resonances recorded in the test of
4.4.3.3.1 in that axis and frequency band. Where no resonances
were noted in that axis and frequency band, the frequency shall
be continuously varied over the band frequency for the duration of
the vibration in that axis. Frequency control shall be automatic
and may be either linear or logarithmic. At the conclusion of the
test, the components comprising one rocket engine shall be static
fired at the rated thrust for the duration shown in Table I. Re-
sults of the firing shall indicate compliance with the requirements
of 3.4.
Vibration endurance life test. Each component
4.4.3.3.3
comprising the second rocket engine subjected to the resonance
survey, 4.4.3.3.1, shall be subjected to the endurance life test.
The endurance life shall be established by repeating the vibration
tests of 4.4.3.3.2 (total time element of 9 hours) until damage
is visible or a total time of 45 hours is reached, whichever occurs
first. If the components (listed in 4.4.3.3) are undamaged at
the completion of the test, the second rocket engine comprised
of these components shall be static fired at the rated thrust in
compliance with Table I and the results recorded for comparison
with the requirements of 3.4. Should any of the components of
the rocket engine (listed in 4.4.3.3) show visible damage before
completion of 45 hours of test, details on the nature and time of
damage shall be recorded.
Acceptance criteria. Unless otherwise specified
4.4.4
in the contract or purchase order, preproduction evaluation sam-
ples shall be approved on the basis of compliance with this specifi-
cation and all applicable drawing and specification requirements.
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