SAE ARP1796B
Current
The latest, up-to-date edition.
Engine Bleed Air Systems for Aircraft
Hardcopy , PDF
English
12-05-2020
Important note : Users cannot be edited or removed once added to your Multi user PDF.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.
| DocumentType |
Standard
|
| Pages |
23
|
| PublisherName |
SAE International
|
| Status |
Current
|
| Supersedes |
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
.
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