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【范围】
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This document establishes techniques for validating that an Aircraft Station Interface (ASI) complies with the interface
requirements delineated in MIL-STD-1760C. For validation of aircraft designed to MIL-STD-1760A Notice 2 AS4764
Issued 1995-04 applies. For validation of aircraft designed to MIL-STD-1760B Notice 3 AS47641 Issued 1999-08 applies.
1.1 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-1760C. 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.
1.2 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 Ⅰinterface. Aircraft with Class Ⅱ
ASI’s will use the appropriate subset of these Class I methods.
1.3 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.
1.4 Limitations
The methods contained herein are based on MIL-STD-1760C. 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.
1.5 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. AGP: 115 V/200 V AC Power Interface
j. HVP: 270 V DC Power Interface
k. FOC: Fiber Optic Interface
I. INT: Initialization
m. CON: ASI Connector
n. UMB: Umbilical Cable
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 reserved for mission store interface (MSI) requirements. 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.
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