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This SAE Aerospace Standard (AS) provides standard methods for testing main engine and auxiliary power unit installations to demonstrate fireproofness or fire resistance. This document details the instrumentation required and the procedures to be followed to determine the calibration parameters of the flame to be used during the fire test.

Powerplant and propulsion system components are required to carry a satisfactory level of fire resistance. The fire resistance requirements are defined in various FAA publications. This document provides typical pass/fail criteria for powerplant and propulsion system components that are certified by fire tests.

This SAE Aerospace Standard (AS) provides standard methods for testing main engine and auxiliary power unit installations to demonstrate fireproofness or fire resistance. The standard addresses: • test equipment, instrumentation, and calibration; • test boundary conditions and test setup; • test pass/fail criteria

The SAE A-22 committee is developping a SAE standards or recommended practices to address the FAA Tasking Request to develop industry standards to update AC20-135 change 1, Powerplant Installation and Propulsion System Component Fire Protection Test Methods, Standards and Criteria. The new proposed standards will be used to demonstrate compliance with powerplant fire protection requirements. The purpose of the AS6826/1 sheet is to define the scope and the standard flame definition of the standard

This document lists the minimum set of boundary conditions, for both on-ground and in-flight operational states, that must be considered when defining the test setup and test procedures for a fire test when the testing is to be conducted in accordance with FAA AC 20-135, and provides a methodology for determining the values associated with those boundary conditions.

The aviation industry created this information report to provide a means for evaluation of fire test anomalies such as post-test burning and back-side burning during fire tests of powerplant components and nacelles.

An SAE ARP is proposed to help applicants comply with 14 CFR 23.903(b)(1) and section 25.903(d)(1) and equivalent requirements from other regulatory authorities.

This ARP will describe practices that may help a part 23, 25, 27, or 29 aircraft applicant to comply with 14 CFR xx.861/865 or equivalent foreign regulations.

Provide basis for conducting Fire Protection and Flammability Testing with ability to support the maximum flight and landing load expected during a recognize a fire condition.

This document defines a consistent industry approach on engine and and auxillary power unit (APU) wiring to meet aircraft EWIS fire and flammability requirements. EWIS regulations apply to many different aircraft types that have propulsion systems certified to FAA 14 CFR part 33 & EASA CS-E. This document will compare these aircraft regulations and then reference the current 14 CFR part 33 requirements for propulsion systems to demonstrate how they can be leveraged to show compliance to EWIS requirements for all aircraft types. APUs are certified to the aircraft level requirements and are included in this document to clarify the type of data suggested to meet the Part/CS-25 EWIS requirement and/or associated normal aircraft regulations.