Hello. Sign In
Standards Store


Revision B, July 1, 2015

Complete Document

(R) Engine Bleed Air Systems for Aircraft

View Abstract
Product Details
Document History

Detail Summary

Active, Most Current

Price (USD)
Single User
In Stock
Add to Cart

People Also Bought These:

SAE AS9101
ASTM A480/A480M
ASTM A240/A240M

Product Details:

  • Revision: Revision B, July 1, 2015
  • Published Date: July 2015
  • Status: Active, Most Current
  • Document Language: English
  • Published By: SAE International (SAE)
  • Page Count: 23
  • ANSI Approved: No
  • DoD Adopted: No

Description / Abstract:

This SAE Aerospace Recommended Practice (ARP) discusses design philosophy, system and equipment requirements, installation environment and design considerations for military and commercial aircraft systems within the Air Transport Association (ATA) ATA 100 specification, Chapter 36, Pneumatic. This ATA system/chapter covers equipment used to deliver compressed air from a power source to connecting points for other systems such as air conditioning, pressurization, ice protection, cross-engine starting, air turbine motors, air driven hydraulic pumps, on board oxygen generating systems (OBOGS), on board inert gas generating systems (OBIGGS), and other pneumatic demands.

The engine bleed air system includes components for preconditioning the compressed air (temperature, pressure or flow regulation), ducting to distribute high or low pressure air to the using systems, and sensors/instruments to indicate temperature and pressure levels within the system.

The engine bleed air system may interface with the following Air Transport Association (ATA) 100 systems:

Chapter 21 - Air Conditioning

Chapter 29 - Hydraulic Power

Chapter 30 - Ice and Rain Protection

Chapter 34 - Navigation (Indication Systems/Probe Aspiration)

Chapter 36 - Pneumatics

Chapter 38 - Water/Waste

Chapter 49 - Airborne Auxiliary Power

Chapter 73 - Engine Fuel & Control

Chapter 75 - Engine Air

Chapter 78 - Engine Exhaust

Chapter 80 - Engine Starting

The interface with these systems/chapters is at the inlet of the shutoff/control valve of each associated system. This boundary definition aligns with that in the ATA 100 specification.

This document also applies to military aircraft. The system functions and interface with other systems are basically the same as commercial aircraft systems. However, military engine bleed air systems often interface with additional systems such as anti-G suit, gun gas purge, and canopy seal.

The primary emphasis of this document is on systems which use the aircraft engine as the source of the pneumatic supply. Alternate supply systems are discussed in Section 7. 


The purpose of this document is to provide guidelines and recommended practices for analysis, design, and installation of aircraft engine bleed air systems.
AIA/NAS Aerospace Standards