This document establishes techniques for validating that an Aircraft Station Interface (ASI) complies with the interface requirements delineated in MIL-STD-1760B Notice 3. For validation of aircraft designed to MIL-STD-1760A Notice 2 AS4764 Issued 1995-04 applies.

Purpose:

The purpose of this document is to provide methods for validating that an aircraft's store electrical interface complies with the aircraft station interface (ASI) requirements of MIL-STD-1760 Notice 3. This document provides a modular, independent set of methods for each of the requirements in MIL-STD-1760 that applies to aircraft requirements. The methods herein apply to the auxiliary (AUX) interface as well as the primary interface of MIL-STD-1760.

Application:

The methods herein apply to initial validation of an aircraft design to the requirements of MIL-STD-1760 and are expected to be conducted as part of aircraft design validation (as opposed to qualification test, quality conformance test, flight line test, etc.). The methods contained in this document are sufficient to cover the Class I interface. Aircraft with Class II ASIs will use the appropriate subset of these Class I methods.

Tailoring:

The methods contained herein are general methods for conducting ASI validation and, as such, do not provide detailed procedures for these methods. It is intended that detailed procedures for validation of a specific ASI will be covered by tailored test plans and procedures prepared specifically for that aircraft. These tailored test procedures would, for example, address those peculiar commands required to step through sufficient operations and states to demonstrate compliance with the particular aircraft/store electrical interconnection system (AEIS) requirement under test.

Limitations:

The methods contained herein are based on MIL-STD-1760B through Notice 3. A future revision of this document will address MIL-STD-1760C test techniques. In addition, this document addresses testing compliance of an aircraft to MIL-STD-1760 based on the assumption that all tests are conducted at the aircraft's ASI connector and measurements of performance occur only at this ASI.

Identification System:

The test methods contained in this document are designated by an alphanumeric identification scheme. Each method is identified by a three alphabetical character combination followed by a three-digit number. The meaning of the first three individual letters is:

a. HBW: High Bandwidth Interface

b. MUX: Digital Multiplex Data Interface

c. LBW: Low Bandwidth Interface

d. REL: Release Consent Interface

e. INL: Interlock Interface

f. ADR: Address Interface

g. GND: Structure Ground

h. DCP: 28 V DC Power Interface

i. ACP: 115 V/200 V AC Power Interface

j. HVP: 270 V DC Power Interface

k. FOC: Fiber Optic Interface

l. INT: Initialization

m. CON: ASI Connector

n. COM: Communication Rules

o. MSG: Messages on the Digital Multiplex Data Interface

The three numbers following the letter code is a sequentially assigned number such that numbers 101 through 199 are for ASI requirements and 201 through 299 are for mission store interface (MSI) validation methods. When applicable, the letter following this three-digit number is the test method revision letter. For example, HBW101 represents the original version of the first test requirement (TR) for the ASI HBW interface while HBW101A represents the first revision of that requirement.