1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there
2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2016 SAE International All rights reserved. No part of this p
3、ublication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-497
4、0 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/ARP217D AEROSPACE RECOMMENDED PRACTICE ARP217 REV. D Issued 1951-03 Revised 1999-
5、03Reaffirmed 2016-10 Superseding ARP217C Testing of Airplane Installed Environmental Control Systems (ECS) RATIONALE ARP217D has been reaffirmed to comply with the SAE five-year review policy. 1. SCOPE:This document deals with ground and flight test of airplane installed Environmental Control System
6、s (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 nois
7、e, 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.1.1 Purpose:This document defines recommended tests and test procedures for airplane
8、 installed ECS. The purpose of these tests is to:a. verify system pressure integrity (leakage),b. verify integration and compatibility of ECS with other airplane systems, andc. determine overall system performance in conditions representative of those which may be encountered during operations.SAE I
9、NTERNATIONAL ARP217D Page 2 of 30 FIGURE 1 - Environmental Control SystemsSAE INTERNATIONAL ARP217D Page 3 of 30 1.2 Field of Application:These tests (and procedures) may be used for commercial and military airplane certification (test of first article) or for production airplane (to ensure built as
10、 design) tests. The selection of the appropriate test conditions, instrumentation, and test procedures depends on a large number of variables (airplane configuration, system concept, hardware, integration with other on-board systems, certification or production airplane, etc.). Thus, these are addre
11、ssed in general terms. This document is intended to serve as a guide in the planning and conduct of tests. The specification or contractual or regulatory (Federal Aviation Regulations (FAR), Joint Airworthiness Regulations (JAR) requirements should be considered. The test plan and procedure should b
12、e coordinated with the appropriate agency.Test data may be used to show compliance with the applicable airplane specification, contractual, or regulatory requirements and to verify analytical simulation models. If the former is intended, it is extremely important to obtain prior approval of the test
13、 plan and procedure from the appropriate agency. 2. REFERENCES:2.1 Applicable Documents:The following publications form a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. The applicable issue of other publications shall be the issue in effect on
14、 the date of the purchase order. In the event of conflict between the text of this document and references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and laws unless a specific exemption has been obtained.2.1.1 SAE Publicat
15、ions: Available from SAE, 400 Commonwealth Drive, Warrendale, PA 15096-001.ARP1307 Measurement of Exterior Noise Produced by Airplane Auxiliary Power Units and Associated Equipment during Ground OperationsARP1323 Type Measurement of Airplane Interior Sound Pressure Levels in CruiseAIR806 Air Conditi
16、oning Design Information for Cargo and High Density Passenger Transport PlanesAIR1266 Fault Isolation in Environmental Control Systems of Commercial TransportsAIR1706 The Advanced Environmental Control Systems (AECS) Computer Program for Steady State Analysis and Preliminary System sizingAIR1823 Tra
17、nsient ECS Computer ProgramAIR1826 Airplane Environmental Systems Acoustical Design ConsiderationsARP85 Air Conditioning Equipment, General requirements for Subsonic AirplanesARP89 Temperature Control Equipment, Automatic Airplane CompartmentARP292 Air Conditioning, Helicopter, General requirements
18、forARP699 High Temperature Pneumatic Duct Systems for AirplaneSAE INTERNATIONAL ARP217D Page 4 of 30 2.1.1 (Continued):ARP731 General Requirements for Application of Vapor Cycle Refrigeration Systems for AirplaneARP1270 Airplane Pressurization Control CriteriaARP1796 Engine Bleed Air Systems for Air
19、planeARP4073 Air Cycle Air Conditioning Systems for Military Air Vehicles2.2 Other Applicable References:AFGS 87145 General Design Specification Environmental Control, AirborneMIL-D-8708 Demonstration Requirements for AirplanesMIL-E-18927 Environmental Control Systems, Airplane, General Requirements
20、 forMIL-T-18606 Test Procedures for Airplane Environmental SystemsSTANAG 2895 Extreme Climate Conditions and Derived Conditions for Use in DefiningDesign/Test Criteria for NATO Forces2.3 Acronyms:ACM Air Cycle MachineAFB Air Force BaseAPU Auxiliary Power UnitARP Aerospace Recommended PracticeATA Air
21、 Transport AssociationBITE Built-In-Test EquipmentCFR Code of Federal RegulationsDER Designated Engineering RepresentativesDMIR Designated Manufacturing Inspection RepresentativesECS Environmental Control SystemsEGT Exhaust Gas TemperatureEICAS Engine Indicating and Crew Alerting SystemEPR Engine Pr
22、essure RatioFAA Federal Aviation AdministrationFAR Federal Aviation RegulationJAA Joint Aviation AuthoritiesJAR Joint Airworthiness RegulationOBOGS On-Board Oxygen Generating SystemOBIGGS On-Board Inert Gas Generating SystemPRSOV Pressure Regulating and Shut Off ValveTAI Thermal Anti-IceSAE INTERNAT
23、IONAL ARP217D Page 5 of 30 3. ENVIRONMENTAL CONTROL SYSTEMS:The ECS typically consists of the following two major systems.3.1 Pneumatic System (ATA 36):The pneumatic system delivers compressed air from the source(s) to on-board services such as, the air-conditioning system packs; engine inlets, ram
24、air inlets and flight surfaces anti-icing or de-icing systems; drives for thrust reverser, flaps, hydraulic pumps, and engine start motor; pressurization of hydraulic fluid reservoir, fuel tanks, and potable water; rain removal and anti-icing of transparencies; etc. In military airplane, the system
25、may also service the following systems.a. On-Board Oxygen Generating System (OBOGS) which extracts oxygen from the air for crew and passengers use;b. On-Board Inert Gas Generating System (OBIGGS) which extracts nitrogen from the air for fuel tank inerting;c. Canopy seals;d. Anti-G system that utiliz
26、es the pressure and flow of air to pressurize the anti-g suit. The suit on pressurization restricts the flow of blood to the lower extremities thus providing protection (loss of consciousness) against gravitational (Gz) forces.e. Radar pressurization system.There are no restrictions on the use of pn
27、eumatic power for operating other systems. The above list identifies systems commonly serviced by the pneumatic system.The typical air-sources of the pneumatic system are the propulsive engines, on-board compressors, on-board Auxiliary Power Unit (APU), and external ground air supply (ground air car
28、t or terminal built-in-compressed air supply system). The system receives compressed air from the above sources, controls its routing, and delivers it to the using systems. Cross-bleed and isolation valves are included in the distribution manifold to maintain essential functions in the event of supp
29、ly or using system failure. Check that pressure regulating and shut off valves are incorporated to ensure delivery of air within pressure limits to the using systems. Heat exchangers, temperature controllers and over-temperature shut-off features are added to control and/or limit supply air temperat
30、ure. To ensure proper operation, monitoring of performance, and to facilitate trouble-shooting and maintenance, sensors and controllers are added as required. A typical pneumatic system is described in 4.4.SAE INTERNATIONAL ARP217D Page 6 of 30 3.2 Air Conditioning System (ATA 21):The air conditioni
31、ng system consists of the following significant subsystems.a. The cabin (passenger and flight crew compartments) conditioning system controls and conditions cabin air supply (fresh and recirculated). It consists of the air conditioning pack(s) including heat sink(s), the cabin-air recirculation syst
32、em components, and the air distribution and exhaust ducting. It interfaces with the pneumatic system at the flow control valve of the pack. Cabin temperature controllers and cabin temperature sensors are part of this system. A cabin-air humidification system may form a part of the cabin conditioning
33、 system. This system increases the relative humidity of selected compartments, such as flight deck, crew rest and passenger.b. The cabin pressure control system controls air flow overboard to maintain cabin altitude and altitude rates of change within designed limits. It consists of the pressure con
34、troller, selector, and valve(s) to control overboard discharge of cabin air to limit maximum and minimum cabin pressures. Safety valves (positive and negative pressure) are included to safeguard structure during failure or abnormal conditions.c. The equipment cooling system provides cooling air for
35、the electrical or electronic equipment. In military airplane the system may also have liquid coolant loops for cooling high density avionics or dielectric coolant.d. The galley and lavatory ventilation systems provide for removal of odors.e. Defog system prevents fog formation on transparent surface
36、s; this provides improved visibility.f. Large transports may have a cargo compartment conditioning (or heating) system for the carriage of animals and perishable cargo.g. On long range airplanes, special areas may be reserved for crew rest and they may have air conditioning systems that can be indep
37、endently controlled.h. Emergency ventilation (ram-air) system for cabin conditioning in the event of loss of all in-flow or for smoke evacuation.i. Heating provisions for areas such as galleys, doors, etc., that tend to get cold during flight.j. In military airplane air conditioning system may inclu
38、de special filters (or equipment) to protect the occupants from nuclear biological and chemical agents.SAE INTERNATIONAL ARP217D Page 7 of 30 3.3 Applicable Regulations and Requirements:The regulations and requirements applicable to ECS depend on the airplane category.3.3.1 Civil Airplane: In the Un
39、ited States, the Federal Aviation Administration (FAA) of the Department of Transportation has jurisdiction to certify civil aircraft as safe. Other nations have similar agencies. Twenty-nine Authorities in Europe have formed Joint Aviation Authorities (JAA). JAA has developed Joint Aviation Require
40、ments (JARs) in the field of design and manufacture, operations and maintenance of aircraft and in the field of personnel licensing. It ensures uniform implementation of JARs so that certificates, approvals, licenses, etc., granted by one of its full members can be accepted by the others. Its goal i
41、s to promote European Safety System world-wide.Code of Federal Regulations (CFR), Title 14 Parts 23 and 25 contain FAA transport category airplane airworthiness standards. Part 23 deals with normal, utility, acrobatic and commuter category airplanes, and Part 25 deals with transport category airplan
42、es. JAR-25 contains JAA airworthiness standards for large turbine airplanes and JAR-23 contains JAA airworthiness standards for normal, aerobatics, utility and commuter categories. This ARP deals primarily with Part 25 airplanes. However, the tests and procedures presented herein, with modifications
43、 due to differences in regulations, may be used for Part 23 airplanes. The FAR Part 25 and JAR Part 25 regulations relevant to ECS, for transport category airplanes, are as follows:FAR or JAR Section25.831 Ventilation25.832 Cabin Ozone Concentration25.833 Heating Systems25.841 Pressurized Cabins25.8
44、43 Tests for Pressurized Cabins25.857 Cargo Compartment Classification25.1301 Function and Installation25.1309 Equipment, Systems, and Installations25.1322 Warning, Caution, and Advisory lights25.1438 Pressurization 5 psig 1 psig (31 kPa 7 kPa gage). Flow required to maintain the duct system at the
45、selected pressure is determined and compared to the estimated leakage at the test pressure. The estimate should include the internal leakage of the control valves exhausting out of the duct system. If leakage is greater than the estimate, the leakage source is determined (feeling for air movement, l
46、istening for noise, observing for soap solution bubbles, etc.) and corrected. The duct system is inspected for deflections under pressure loading to assure clearances around system components are as designed.On satisfactory completion of the low pressure test and inspection, the system is progressiv
47、ely pressurized to higher pressures, and flow required to maintain the system at constant pressure determined. Extreme caution should be exercised in the conduct of the test as failure of system components can cause equipment damage and personnel injury.4.4.1.2 Integration and Compatibility: The pur
48、pose of this test is to ensure that the system has been integrated properly and that it works in harmony with the other on-board systems. Refer to Figure 2. The pneumatic system consists of APU bleed-air supply, engine bleed-air supply and ground air supply. To verify the APU supply system, start an
49、d operate the APU per its operating procedures. Open the APU valve. Observe the manifold gage pressure (flight deck or installed instrumentation). Open and close the isolation valve and the pack valve(s) to confirm compatibility between the APU and the user systems, i.e., there are no undesirable overshoots in the APU Exhaust Gas Temperature (EGT), distribution manifold pressure oscillations are damped, and that there is no adverse
