MIL-PRF-8565/7A (AS)
REQUIREMENTS:
1. Part or identifying number. The part or identifying number (PIN) of the battery covered by
this specification sheet shall be D8565/7-2. The D8565/7-2 battery supersedes the D8565/7-1
battery.
2. Dimensions and weight. The dimensions of the battery shall be as shown on figure 1 contained
in the specification sheet. The weight of the battery shall be not greater than 29.0 kilograms
(see 3.8.3 and 4.5.3). In addition, the weight of any production battery shall vary by not greater
than ± 0.6 kg from the average weight of the three approved qualification sample batteries but
may not exceed the 29.0-kilogram limit.
3. Capacity. The rated capacity of the battery shall be not less than 24 ampere-hours (Ah).
See 3.8.6 as modified herein.
4. Battery mounting. The battery's side mounting brackets shall be used to support the battery as
shown on figure 3 of the general specification. If vibration isolators are used, sufficient clearance
between the battery and any structure shall be provided to ensure that the battery will not strike
the structure under any swaying motion.
5. Service life. The battery's service life (useful life) in aircraft shall be not less than 3 years. The
battery shall require no scheduled maintenance during the 3 years (see 3.8.9, 4.5.10, and 6.11.7).
6. Qualification inspection and conformance inspection. Table I lists the required inspections.
7. MIL-PRF-8565 variance. The battery shall comply with MIL-PRF-8565 except as follows.
7.1 Change "18.0 volts" to "20.0 volts" in the following paragraphs:
4.5.6 Electrical test preparation, first sentence.
4.5.7 Capacity discharge, second sentence.
4.5.11 Capacity discharge at 49°C (120°F), third sentence.
4.5.17 Temperature rise and float test, step e, second sentence.
4.5.23 Physical integrity at high temperature test, steps b and k.
TABLE III Capacity performance requirements, requirements (1), (2), and (3).
7.2 Modify the following paragraphs:
3.5.5 Receptacles. Insert the following after the first sentence: "Each battery shall include
the following receptacle(s) as its electrical interface to the aircraft. The J1 receptacle (main
receptacle) shall be MS3509, style 1 (pink). It shall contain the battery's positive and negative
electrical power connections and shall be mounted as shown on figure 1 of the specification sheet.
The J2 receptacle (auxiliary receptacle) is required only when heaters are incorporated into the
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