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Standard

THE ADVANCED ENVIRONMENTAL CONTROL SYSTEM (AECS) COMPUTER PROGRAM FOR STEADY STATE ANALYSIS AND PRELIMINARY SYSTEM SIZING
1986-10-01
HISTORICAL
AIR1706A
Many different computer programs have been developed to determine performance capabilities of aircraft environmental control systems, and to calculate size and weight tradeoffs during preliminary design. Many of these computer programs are limited in scope to a particular arrangement of components for a specific application. General techniques, providing flexibility to handle varied types of ECS configurations and different requirements (i.e., during conceptual or preliminary design, development, testing, production, and operation) are designated "company proprietary" and are not available for industry-wide use. This document describes capabilities, limitations, and potentials of a particular computer program which provides a general ECS analysis capability, and is available for use in industry. This program, names AECS1, was developed under the sponsorship of the U.S. Air Force Flight Dynamics Laboratory (References 1 and 2).
Standard

The Advanced Environmental Control System (AECS) Computer Program for Steady State Analysis and Preliminary System Sizing
2003-10-31
HISTORICAL
AIR1706B
Many different computer programs have been developed to determine performance capabilities of aircraft environmental control systems, and to calculate size and weight tradeoffs during preliminary design. Many of these computer programs are limited in scope to a particular arrangement of components for a specific application. General techniques, providing flexibility to handle varied types of ECS configurations and different requirements (i.e., during conceptual or preliminary design, development, testing, production, and operation) are designated “company proprietary” and are not available for industry-wide use. This document describes capabilities, limitations, and potentials of a particular computer program which provides a general ECS analysis capability, and is available for use in industry. This program, names AECS1, was developed under the sponsorship of the U.S. Air Force Flight Dynamics Laboratory (References 1 and 2).
Standard

GUIDE FOR PREPARING AN ECS COMPUTER PROGRAM USER'S MANUAL
1980-06-01
HISTORICAL
ARP1623
These recommendations apply to the user's manual for any computer program pertaining to aircraft ECS. This includes computer programs for: a Cabin air conditioning and pressurization performance. b Avionics equipment cooling system performance. c Engine bleed air system performance. d Compartment and equipment thermal analysis. e Environmental protection system performance. These recommendations apply to user's manuals for generalized computer programs as well as those for a specific component or system.
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
1956-03-15
HISTORICAL
ARP89B
This recommended practice covers automatic cabin temperature control systems of the following types for pressurized and unpressurized cabins: Type I - Proportioning. Type II - On-Off, or Cycling. Type III - Floating, including modifications thereof.
Standard

TEMPERATURE CONTROL EQUIPMENT, AUTOMATIC, AIRCRAFT COMPARTMENT
1992-03-01
HISTORICAL
ARP89C
The recommendations of this ARP are primarily intended to be applicable to temperature control of compartments, occupied or unoccupied, of civil aircraft whose prime function is the transporting of passengers or cargo. The recommendations will apply, however, to a much broader category of civil and military aircraft where automatic temperature control systems are applicable.
Standard

Aircraft Compartment Automatic Temperature Control Systems
2018-08-23
CURRENT
ARP89D
The recommendations of this SAE Aerospace Recommended Practice (ARP) for aircraft compartment automatic temperature control systems are primarily intended to be applicable to occupied or unoccupied compartments of civil and military aircraft.
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 SYSTEMS LIFE CYCLE COST
1985-10-01
HISTORICAL
AIR1812
This report contains background information on life cycle cost elements and key ECS cost factors. Elements of life cycle costs are defined from initial design phases through operational use. Information on how ECS designs affect overall aircraft cost and information on primary factors affecting ECS costs are discussed. Key steps or efforts for comparing ECS designs on the basis of LCC are outlined. Brief descriptions of two computer programs for estimating LCC of total aircraft programs and their use to estimate ECS LCC, are included.
Standard

Environmental Control Systems Life Cycle Cost
2017-02-07
CURRENT
AIR1812B
This report contains background information on life cycle cost elements and key ECS cost factors. Elements of life cycle costs are defined from initial design phases through operational use. Information on how ECS designs affect overall aircraft cost and information on primary factors affecting ECS costs are discussed. Key steps or efforts for comparing ECS designs on the basis of LCC are outlined. Brief descriptions of two computer programs for estimating LCC of total aircraft programs and their use to estimate ECS LCC, are included.
Standard

Engineering Analysis System (EASY) Computer Program for Dynamic Analysis of Aircraft ECS
2003-10-31
HISTORICAL
AIR1823A
The Engineering Analysis SYstem (EASY) computer program is summarized in this report. It provides techniques for analysis of steady-state and dynamic (transient) environmental control system (ECS) performance, control system stability, and for synthesis of optimal ECS. General uses of a transient analysis computer program for ECS design and development, and general features of EASY relative to these uses, are presented. This report summarizes the nine analysis options of EASY, EASY program organization for analyzing ECS, data input to the program and resulting data output, and a discussion of EASY limitations. Appendices provide general definitions for dynamic analysis, and samples of input and output for EASY.
Standard

ENVIRONMENTAL CONTROL SYSTEM TRANSIENT ANALYSIS COMPUTER PROGRAM (EASY)
2011-08-10
HISTORICAL
AIR1823
The Environmental Control Analysis SYstem (EASY) computer program is summarized in this report. Development of this computer program initially was sponsored by the U.S. Air Force Flight Dynamics Laboratory. (See References 1, 2, 3, and 4.) It provides techniques for determination of steady state and dynamic (transient) ECS performance, and of control system stability; and for synthesis of optimal ECS control systems. The program is available from the U.S. Air Force, or as a proprietary commercial version. General uses of a transient analysis computer program for ECS design and development, and general features of EASY relative to these uses, are presented. This report summarizes the nine analysis options of EASY, EASY program organization for analyzing ECS, data input to the program and resulting data output, and a discussion of EASY limitations. Appendices provide general definitions for dynamic analysis, and samples of input and output for EASY.
Standard

The Control of Excess Humidity in Avionics Cooling
2020-05-12
CURRENT
ARP987B
This Aerospace Recommended Practice (ARP) outlines the causes and impacts of moisture and/or condensation in avionics equipment and provides recommendations for corrective and preventative action.
Standard

AIRCRAFT CABIN PRESSURIZATION CONTROL CRITERIA
1993-06-01
HISTORICAL
ARP1270
These recommendations cover the basic criteria for the design of aircraft cabin pressurization control systems as follows: (1) To ensure aircraft safety. (2) Physiology and limits which govern maximum permissible pressure time relations as related to aircraft passenger comfort. (3) General pressurization control system performance requirements designed to satisfy (2). (4) Technical considerations relevant to satisfying (3).
Standard

Aircraft Cabin Pressurization Control Criteria
2006-06-28
HISTORICAL
ARP1270A
These recommendations cover the basic criteria for the design of aircraft cabin pressurization control systems as follows: (1) To ensure aircraft safety. (2) Physiology and limits which govern maximum permissible pressure time relations as related to aircraft passenger comfort. (3) General pressurization control system performance requirements designed to satisfy (2). (4) Technical considerations relevant to satisfying (3).
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