MIL-V-62475 Vehicle, Fire Support Team, M981 FistvThis specification covers a full-tracked, land combat, fire support team vehicle, with a high degree of tactical maneuverability.

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MIL-V-62475(AT)

ITEM

TABLE I. Dismounted operable FISTV components.

1. AN/TVQ-2, G/VLLD

(including items for ground operation)

2. AN/TAS-4B, Closed cycle cooler night sight

(including collimator and battery case)

3. AN/PSG-2A or AN/PSG-5 DMD (including cables and battery)

4. AN/GRC-160, Radio

(including antenna battery)

5. AN/GRA-39, Radio set control group (remote)

3.4.4 Transportability. The FISTV vehicle shall be capable of being transported in the existing C-130 aircraft in accordance with Drawing 12306657. In this air transport configuration, the vehicle shall not exceed a vertical height of 103.5 inches (in)

[2628 millimeters (mm)] when the chassis deck is not higher than 73 in (1854 mm) (see 4.6.3.4).

3.4.5 Welding repairs. Welding repairs of any type or class shall be made only when, and to the extent, specifically authorized by the applicable drawings, specifications or welding procedures which have been approved by the procuring activity. Welding of aluminum alloys shall be in accordance with MIL-W-8604. Welding of steel shall be in accordance with

MIL-W-8611 (see 4.6.3.5).

3.5 Performance. A complete FISTV vehicle, loaded to approximately 26 900 lbs

(12 200 kg) shall perform as specified herein with the targeting head in the stowed position unless otherwise noted. The FISTV, serviced and equipped for prevailing climatic conditions, shall operate as specified with or without special equipment. Performance as specified herein, shall be demonstrated on smooth, level, hard-surfaced roads free of loose material. A section of the road shall have an artificial bump as shown in figure 1 and it shall be traversed at least once every five miles [8 kilometers (km)] (see 4.6.4).

3.5.1 FISTV system.

3.5.1.1 Reliability. The FISTV vehicle system shall have a minimum acceptable value mission reliability of 0.8 when operated in accordance with the composite mission profile (see 3.5.3). This value is based on the GFE reliability as shown in table II (see 4.6.4.1).