MIL-DTL-82945B (OS)
4.3.3 Propellant aging. Three blocks of cured propellant from each batch of rocket motor propellant and
three blocks from each batch of catapult propellant used in the first article sample shall be submitted to
the Indian Head Division, Naval Surface Warfare Center, Indian Head, MD 20640-5000, Attn: Code E28,
for aging testing. High-temperature aging shall be conducted for 84 days with an atmosphere of 22
percent relative humidity and at 165 ± 5F. At zero time and at the end of the 28-, 56-, and 84-day aging,
physical properties shall conform to MIL-DTL-32124, Type V (rocket motor propellant) and MIL-DTL-
32124, Type VI (catapult propellant). The rate for stress/strain determination shall be 2.0 inches/minute.
The sample shall be cast into rectangular cardboard containers approximately 1.5 inches high by 8 inches
wide by 11 inches long. All samples submitted shall be bare propellant, individually wrapped in
moistureproof packaging and properly identified as to propellant lot and batch number. Failure of the
propellant to meet the requirements of the applicable specification shall be cause for rejection of the
propellant batch.
4.3.4 Propellant morphology. Two rocket motor grain assemblies and two catapult grain assemblies
from each batch of propellant used in the first article sample shall be submitted for morphological
examination of the propellant. All samples shall be individually wrapped in moistureproof packaging and
properly identified as to propellant lot, batch number, and grain serial number. These tests shall be used
as baseline information.
4.4 Quality conformance inspection. Quality conformance inspection shall consist of the examinations
and tests of 4.4.4 through 4.4.6, conducted on samples selected as specified in 4.4.2. The contractor is
responsible for assuring that all rocket catapults offered for acceptance meet all requirements of the
applicable drawings and specifications. Items of inspection shall be serialized and inspection data
traceable to a specific serial number.
4.4.1 Test reports. When specified in the contract or order (see 6.2), the contractor shall furnish test
reports to the procuring activity. Test reports shall include the following information as described in
4.4.1.1 through 4.4.1.7:
a.
Propellant description (see 3.2.2)
b.
Static firing performance test results (see 4.4.5.1)
c.
Summary sheet
d.
Ammunition data cards
e.
Propellant/assembly production records
f.
Certification of age of explosive components and propellant (see 3.3)
g.
Metal parts manufacturing records
4.4.1.1 Propellant description. The following propellant information shall be submitted with each
production lot. The materials and components of each propellant batch shall list the manufacturer, lot
number, and date of manufacture. The burning rates for the rocket motor propellant at 1000, 2000, 3000,
and 4000 psi performed at -65°F and 165°F for each pressure (three samples at each temperature and
pressure per batch) shall be included. The burning rates for the catapult propellant at 500, 1000, 1500, and
2000 psi performed at 77°F for each pressure (three samples at each temperature and pressure per batch)
shall be included. In addition, include the results of tensile strength and elongation tests at -65°F, 77°F,
and 165°F with a pull rate of 2 inches/minute (five samples at each temperature per batch), heat of
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