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Standard

The Control of Excess Humidity in Avionics Cooling
2003-10-31
HISTORICAL
ARP987A
The purpose of this document is threefold: (1) to review the problem of moisture in avionics equipment, (2) to outline methods for correcting conditions of excess moisture in existing avionics installations, and (3) to recommend design practices for new avionics cooling system installations which will minimize the adverse effects of moisture.
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

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

Testing of Airplane Installed Environmental Control Systems (ECS)
2021-12-27
CURRENT
ARP217D
This document deals with ground and flight test of airplane installed Environmental Control Systems (ECS), Figure 1. The ECS provide an environment, controlled within specified operational limits of comfort and safety, for humans, animals, and equipment. These limits include the following: pressure, temperature, humidity, ventilation air velocity, ventilation rate, wall temperature, audible noise, vibration, and environment composition (ozone, contaminants, etc.). The ECS are composed of equipment, controls, and indicators that supply, distribute, recycle and exhaust air to maintain the desired environment.
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

TESTING OF PROTOTYPE AIRPLANE AIR CONDITIONING SYSTEMS
1951-03-15
HISTORICAL
ARP217
These recommendations are written to cover the testing of air conditioning equipment as installed in the prototype aircraft for the purpose of: A Demonstrating safety of the installation. B Demonstrating performance of the installation. a Aircraft ducting and distribution system. b Component parts (i.e., vendors equipment) C Obtaining data for future design.
Standard

TESTING OF COMMERCIAL AIRPLANE ENVIRONMENTAL CONTROL SYSTEMS
1997-10-01
HISTORICAL
ARP217C
These recommendations are written to cover the testing of environmental control equipment, functioning as a complete and installed system in civil aircraft for the purpose of: a Demonstrating the safety of the installation and equipment. b Demonstrating proper functioning of the installation and equipment. c Demonstrating performance of the installation and equipment. d Obtaining data for future design and to aid in the analysis of in-service performance of the system and equipment.
Standard

TESTING OF COMMERCIAL AIRPLANE ENVIRONMENTAL CONTROL SYSTEMS
1973-10-15
HISTORICAL
ARP217B
These recommendations are written to cover the testing of environmental control equipment, functioning as a complete and installed system in civil aircraft for the purpose of: a Demonstrating the safety of the installation and equipment. b Demonstrating proper functioning of the installation and equipment. c Demonstrating performance of the installation and equipment. d Obtaining data for future design and to aid in the analysis of in-service performance of the system and equipment.
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

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

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

Spacecraft Equipment Environmental Control
2006-03-24
HISTORICAL
AIR1168/13
This part of the manual presents methods for arriving at a solution to the problem of spacecraft inflight equipment environmental control. The temperature aspect of this problem may be defined as the maintenance of a proper balance and integration of the following thermal loads: equipment-generated, personnel-generated, and transmission through external boundary. Achievement of such a thermal energy balance involves the investigation of three specific areas: 1 Establishment of design requirements. 2 Evaluation of properties of materials. 3 Development of analytical approach. The solution to the problem of vehicle and/or equipment pressurization, which is the second half of major environmental control functions, is also treated in this section. Pressurization in this case may be defined as the task associated with the storage and control of a pressurizing fluid, leakage control, and repressurization.
Standard

Spacecraft Equipment Environmental Control
2011-07-25
CURRENT
AIR1168/13A
This part of the manual presents methods for arriving at a solution to the problem of spacecraft inflight equipment environmental control. The temperature aspect of this problem may be defined as the maintenance of a proper balance and integration of the following thermal loads: equipment-generated, personnel-generated, and transmission through external boundary. Achievement of such a thermal energy balance involves the investigation of three specific areas: 1 Establishment of design requirements. 2 Evaluation of properties of materials. 3 Development of analytical approach. The solution to the problem of vehicle and/or equipment pressurization, which is the second half of major environmental control functions, is also treated in this section. Pressurization in this case may be defined as the task associated with the storage and control of a pressurizing fluid, leakage control, and repressurization.
Standard

OZONE PROBLEMS IN HIGH ALTITUDE AIRCRAFT
1996-07-01
HISTORICAL
AIR910A
The purpose of this report is to provide information on ozone and its control in high altitude aircraft environmental systems. Sources of this information are listed in the selected bibliography appearing at the end of this report, to which references are made throughout.
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