MIL-STD-2088 Bomb Rack Unit Bru, Single Store, AircraftThis standard establishes the general guidelines and criteria for the design and development of a single store bomb rack unit BRU for carriage and release of airborne stores excluding air-to-air missiles from fixed wing and rotary wing aircraft using a single suspension point or suspension points spaced at 14 or 30 inches. This standard addresses detailed requirements for gravity non-ejected, pyrotechnic, hydraulic, and pneumatic powered BRUs. Mechanical aircraft armament interoperable interfaces are incorporated to enhance cross utilization and servicing capabilities between military aircraft and aircraft stores see 3.1 of all services of the Department of Defense DoD and North Atlantic Treaty Organization NATO nations.

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MIL-STD-2088B

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to occur until time has elapsed, with the electrical interrupt removed, to permit a BRU "Lock-Shut-Firing" if release energy is present.

5.1.6.3 Alternative interrupt removal. As an alternative, the release control circuit may be monitored for the presence of electrical energy to initiate the release of the BRU's stored energy. If insufficient electrical energy is present to cause the release of energy, then the electrical and mechanical interrupts may be removed simultaneously. To ensure the accuracy and integrity of the voltage monitoring system, it shall be verified against other electrical circuit energy levels that are independently verified.

5.1.6.4 Safety interlock ground operation. During ground loading and unloading

operations, the safety interlock mechanical interrupt shall be removed without the removal of the electrical interrupt. To ensure maximum protection with the mechanical interrupt removed while the electrical interrupt is in place, the electrical interrupt shall be prevented from being removed until the mechanical interrupt is replaced (SAFE position).

5.1.6.5 Safety interlock control. The safety interlock shall be designed for either manual or remote operation. Remote operation shall be controlled through the safety interlock drive mechanism using aircraft power and commands. The safety interlock mechanism shall be capable of being latched in the GROUND position for store loading or downloading operations. The safety interlock shall not be latched in the ARMED position and shall return to its SAFE position when power is removed from the drive mechanism (provided the store supports are in their latched positions). The safety interlock shall return to its SAFE position when the GROUND position latch is released, without the use of tools. The safety interlock design shall prevent it from being forced from its SAFE position by combinations of vibration and/or acceleration forces induced by the aircraft's mission profile. The safety interlock may be held in the ARMED position by the safety interlock drive mechanism, but shall not be independently latched in the ARMED position. The safety interlock shall be operable by one person locally without power or tools and shall be capable of operation within 10 seconds. Placing the safety interlock in the ARMED position shall not release the store support latches nor provide release initiation power. The design shall not require the use of manually inserted or removable parts to accomplish safety interlock operations. The complete safety interlock system shall be protected from inadvertent operation due to external physical contact. To the maximum extent possible, the safety interlock mechanical and electrical interrupts shall be positioned within the BRU to prevent inadvertent store release as a result of single component failures. There shall only be

one safety interlock mechanism for each BRU.

5.1.6.6 Safety interlock drive mechanism. The BRU shall have an in-flight operable drive mechanism for its safety interlock. This drive mechanism shall require the application of energy to force the safety interlock from its SAFE position to its ARMED position. When in its de- energized state, the drive mechanism shall not force the safety interlock from its SAFE position during any combination of vibration and/or acceleration forces induced by the aircraft's mission