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Air Conditioning Systems For Subsonic Airplanes
- Aerospace Standard
Published December 03, 2007 by SAE International in United States
This ARP discusses design philosophy, system and equipment requirements, and ambient conditions and design considerations for systems within the ATA 100 Specification, Chapter 21 (Reference 1). This chapter is principally concerned with passenger and crew environment and the air conditioning system that maintains this environment.
The airplane air conditioning system comprises that arrangement of equipment, controls and indicators that supply and distribute air to the occupied compartments for ventilation, pressurization, and temperature and moisture control. The principal features of the system are:
A supply of fresh air from at least two sources with independent control valves
A means for heating
A means for cooling (air or vapor cycle units and heat exchangers)
A means for removing excess moisture from the air supply
A ventilation subsystem
A temperature control subsystem
A pressure control subsystem
Other system components for treating cabin air such as filtration and humidification would be included, as would the ancillary functions of equipment cooling and cargo compartment conditioning.
The interface with the major associated system, the pneumatic system (Chapter 36 of ATA 100), is at the inlet of the air conditioning shutoff valves. This boundary definition aligns with that in the ATA 100 Specification.
|Aerospace Standard||Air Conditioning Systems for Subsonic Airplanes|
|Aerospace Standard||Emergency Evacuation Illumination|
Data Sets - Support Documents
No Datasets Available
AC-9 Aircraft Environmental Systems Committee
Furthers the advancement of technology related to the research, design, test and utilization of aircraft environmental and anti-icing/deicing systems. Develops and updates standards, recommended practices, and information reports contributing to the quality, economy, and safety of commercial and military aircraft.
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