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Carbon dioxide Fuels and Energy Sources Materials AC-9 Aircraft Environmental Systems Committee

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Standard

Spacecraft Life Support Systems
2011-06-20
HISTORICAL
AIR1168/14
A life support system (LSS) is usually defined as a system that provides elements necessary for maintaining human life and health in the state required for performing a prescribed mission. The LSS, depending upon specific design requirements, will provide pressure, temperature, and composition of local atmosphere, food, and water. It may or may not collect, dispose, or reprocess wastes such as carbon dioxide, water vapor, urine, and feces. It can be seen from the preceding definition that LSS requirements may differ widely, depending on the mission specified, such as operation in Earth orbit or lunar mission. In all cases the time of operation is an important design factor. An LSS is sometimes briefly defined as a system providing atmospheric control and water, waste, and thermal management.
Standard

Aircraft Electrical Heating Systems
2011-10-17
CURRENT
AIR860B
It is intended that the scope of this information report be limited to electrical heating of passenger, crew, and cargo compartments only. No attempt has been made to develop the complete electrical circuitry associated with the electrical heating components; however, the electrical circuitry required for heating component operation, safety, and monitoring will be included as available. Specific design information is given for various modern aircraft utilizing electrical heating. Each aircraft discussed will be identified by alphabetical letter designation and included in the appropriate appendix.
Standard

Aircraft Electrical Heating Systems
2006-03-24
HISTORICAL
AIR860A
It is intended that the scope of this information report be limited to electrical heating of passenger, crew, and cargo compartments only. No attempt has been made to develop the complete electrical circuitry associated with the electrical heating components; however, the electrical circuitry required for heating component operation, safety, and monitoring will be included as available. Specific design information is given for various modern aircraft utilizing electrical heating. Each aircraft discussed will be identified by alphabetical letter designation and included in the appropriate appendix.
Standard

AIRCRAFT ELECTRICAL HEATING SYSTEMS
1992-03-01
HISTORICAL
AIR860
It is intended that the scope of this information report be limited to electrical heating of passenger, crew, and cargo compartments only.
Standard

TEMPERATURE CONTROL EQUIPMENT, AUTOMATIC AIRPLANE CABIN
1943-01-01
HISTORICAL
ARP89
These specifications are written to cover automatic temperature controls under three classifications, namely: A AUTOMATIC TEMPERATURE CONTROLS - GENERAL - Dealing with features applicable to all types and uses. B AUTOMATIC TEMPERATURE CONTROLS - MILITARY AND COMMERCIAL - Covering features applicable to military aircraft and commercial aircraft. C DESIRABLE DESIGN FEATURES - General information for use of those concerned in meeting the requirements contained herein.
Standard

GUIDE FOR QUALIFICATION TESTING OF AIRCRAFT AIR VALVES
1982-10-01
HISTORICAL
ARP986A
This document defines tests to be performed on electrically, pneumatically, and mechanically actuated (regulating, modulating, and shutoff) air valves. The valves may be further defined as those which function in response to externally applied forces or in response to variations in upstream and/or downstream duct air conditions to maintain a calibrated duct air condition (i.e., air flow, air pressure, air temperature, air pressure ratio, etc.). The requirements of this document should govern for all qualification tests unless different requirements are established by the detail specifications.
Standard

GUIDE FOR QUALIFICATION TESTING OF AIRCRAFT AIR VALVES
1968-11-01
HISTORICAL
ARP986
This document defines the tests to be performed on electrically, pneumatically, and mechanically actuated (regulating, modulating, and shutoff) air valves. The valves may be further defined as those which function in response to externally applied forces or in response to variations in upstream and/or downstream duct air conditions to maintain a calibrated duct air condition (i. e., air flow, air pressure, air temperature, air pressure ratio, etc. ). The requirements of this document should govern for all qualification tests unless different requirements are established by the detail specifications.
Standard

Air Cycle Air Conditioning Systems for Air Vehicles
2019-08-20
CURRENT
AS4073B
This SAE Aerospace Standard (AS) defines the requirements for air cycle air conditioning systems used on military air vehicles for cooling, heating, ventilation, and moisture and contamination control. General recommendations for an air conditioning system, which may include an air cycle system as a cooling source, are included in MIL-E-18927E and JSSG-2009. Air cycle air conditioning systems include those components which condition high temperature and high pressure air for delivery to occupied and equipment compartments and to electrical and electronic equipment. This document is applicable to open and closed loop air cycle systems. Definitions are contained in Section 5 of this document.
Standard

Air Cycle Air Conditioning Systems for Military Air Vehicles
2000-03-01
HISTORICAL
AS4073
This SAE Aerospace Standard (AS) defines the requirements for air cycle air conditioning systems used on military air vehicles for cooling, heating, ventilation, and moisture and contamination control. General recommendations for an air conditioning system, which may include an air cycle system as a cooling source, are included in MIL-E-18927E (AS) and MIL-E-87145 (USAF). Air cycle air conditioning systems include those components which condition high temperature and high pressure air for delivery to occupied and equipment compartments and to electrical and electronic equipment. This document is applicable to open and closed loop air cycle systems. Definitions are contained in Section 5 of this document.
Standard

Aircraft Humidification
2015-11-09
HISTORICAL
AIR1609A
This SAE Aerospace Information Report (AIR) covers the design parameters for various methods of humidification applicable to aircraft, the physiological aspects of low humidities, the possible benefits of controlling cabin humidity, the penalties associated with humidification, and the problems which must be solved for practical aircraft humidification systems. The design information is applicable to commercial and military aircraft. The physiological aspects cover all aircraft environmental control applications.
Standard

Aircraft Humidification
2021-01-14
CURRENT
AIR1609B
This SAE Aerospace Information Report (AIR) covers the design parameters for various methods of humidification applicable to aircraft, the physiological aspects of low humidities, the possible benefits of controlling cabin humidity, the penalties associated with humidification, and the problems which must be solved for practical aircraft humidification systems. The design information is applicable to commercial and military aircraft. The physiological aspects cover all aircraft environmental control applications.
Standard

Environmental Control for Civil Supersonic Transport
2011-08-10
CURRENT
AIR746C
This document supplements ARP85, to extend its use in the design of ECS for supersonic transports. The ECS provides an environment controlled within specified operational limits of comfort and safety, for humans, animals, and equipment. These limits include pressure, temperature, humidity, conditioned air velocity, ventilation rate, thermal radiation, wall temperature, audible noise, vibration, and composition (ozone, contaminants, etc.) of the environment. The ECS is comprised of equipment, controls, and indicators that supply and distribute conditioned air to the occupied compartments. This system is defined within the ATA 100 specification, Chapter 21. It interfaces with the pneumatic system (Chapter 36 of ATA 100), at the inlet of the air conditioning system shutoff valves.
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