1、_ ARP5918AEROSPACERECOMMENDEDPRACTICEIssued 2006-07 Standard Test Criteria for Aircraft Refuelers RATIONALEThe purpose of this SAE Aerospace Recommended Practice is to establish the minimum recommended test stand setup and to establish the minimum inspection, testing, operation, and performance crit
2、eria and procedures to evaluate aircraft refuelers for fueling and/or defueling aircraft. 1. SCOPE This SAE Aerospace Recommended Practice (ARP) establishes the minimum recommended Test Stand Setup and Procedures for inspecting and testing Aircraft Refuelers. The inspection and test procedure shall
3、be used to evaluate the operation and performance of an Aircraft Refueler to assure that it meets the minimum refueling performance criteria and is fit for aircraft fueling and/or defueling operations. These procedures shall be used to test new Aircraft Refuelers and may be used to perform routine t
4、ests to confirm that the Aircraft Refuelers comply with the minimum performance criteria as specified herein. This document covers all types of Aircraft Refuelers, stationary (e.g., cabinet type units) or mobile (e.g., hydrant service vehicles, tankers, etc). NOTE: Aircraft refueling vehicle design
5、and operating requirements are provided in separate SAE ARP Documents. NOTE: This document does NOT address Aircraft Refuelers with operating pressure above 150 psi although many of the paragraphs can be used as a guideline. 2. APPLICABLE DOCUMENTS The following publications form a part of this docu
6、ment 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 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 d
7、ocument takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 2.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) o
8、r 724-776-4970 (outside USA), www.sae.org. ARP1247 General Requirements for Aerospace Ground Support Equipment, Motorized and Non-motorized AIR1375 General Requirements for Aerospace Special Purpose Airline Ground Support Equipment AIR4783 Glossary of Terms - Aircraft Refueling AIR4929 Aircraft Refu
9、eling Pressure Surge Creation and Limitation Reaffirmed 2011-11SAE 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 pa
10、rticular use, including any patent infringement arising therefrom, 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 2
11、011 SAE International All rights reserved. No part of this publication 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: T
12、el: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-4970 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.orgSAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/ARP5918SAE ARP5918 - 2
13、 -ARP4974 Design And Operation of Aircraft Refueling Hydrant Servicers ARP5818 Design And Operation of Aircraft Refueling Tanker Vehicles AS5877 Detailed Specification for Aircraft Pressure Refueling Nozzle SAE Handbook 2.2 API/EI Publications Available from American Petroleum Institute, 1220 L Stre
14、et, NW, Washington, DC 20005-4070, Tel: 202-682-8000, http:/api-ec.api.org. API/EI Bulletin 1529 API/EI Standard for Aviation Fueling Hose API/EI Bulletin 1542 Identification Markings for Dedicated Aviation Fuel Manufacturing and Distribution Facilities, Airport Storage and Mobile Fuelling Equipment
15、 API/EI Bulletin 1581 Specifications and Qualifications Procedures for Aviation Jet Fuel Filter/Separators API/EI Bulletin 1582 Similarity for API/EI 1581 Aviation Jet Fuel Filter/Separators API/EI Bulletin 1583 Specifications and Qualifications Procedures for Aviation Jet Fuel Filter Monitors With
16、Absorbent Type Elements API/EI Bulletin 1584 API/EI Standard for Four-Inch Hydrant System Components and Arrangements 2.3 ASME Publications Available from American Society of Mechanical Engineers, 22 Law Drive, P.O. Box 2900, Fairfield, NJ 07007-2900, Tel: 973-882-1170, www.asme.org. ASME B31.3 Proc
17、ess Piping 2.4 ASTM Publications Available from ASTM International, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959, Tel: 610-832-9585, www.astm.org.ASTM D 910 Standard Specification for Aviation Gasolines ASTM D 1655 Standard Specification for Aviation Turbine Fuels ASTM D 6615 Standard Spe
18、cification for Jet B Wide-Cut Aviation Turbine Fuels 2.5 ATA Publications Available from Air Transport Association of America, Inc., 1301 Pennsylvania Avenue, NW, Suite 1100, Washington, DC 20004-1707, Tel: 202-626-4000, www.airlines.org. ATA Specification 103 Standards for Jet Fuel Quality Control
19、at Airports SAE ARP5918 - 3 -2.6 Joint Inspection Group Publications To be supplied with Purchase Specifications if compliance with this Publication is required. JIG 9 Guidelines for Aviation Fuel Quality and Operating Procedures for Joint into Plane Fueling Services 2.7 NFPA Publications Available
20、from the National Fire Protection Agency, 1 Batterymarch Park, Quincy, MA 02169-7471, Tel: 617-770-3000, www.nfpa.org.NFPA 10 Standard for Portable Fire Extinguishers NFPA 385 Tank Vehicles for Flammable and Combustible Liquids NFPA 407 Standards for Aircraft Fuel Servicing 2.8 United States - Code
21、of Federal Regulations (CFR) Available from the United States Government Printing Office, 732 North Capitol Street, NW, Washington, DC 20401, Tel: 202-512-0000.Transportation (DOT) 49 CFR 178, 180, 393, 571 2.9 Local Requirements Available from the local State, Municipality, Governmental Unit, Local
22、 Agency, or Airport Owner or Operators office as required by the Vehicle Purchase Specifications. 3. DEFINITIONS Definitions for terms or phrases as used in this document are defined in AIR4783, ARP4974, and ARP5818. Other terms or phrases as used in this document shall be defined as follows. ACCURA
23、CY OF A COMPONENT OR SYSTEM: The component or system operate and perform to a level of accuracy as referenced or stated herein. AIRCRAFT REFUELER OEM: The original equipment manufacturer of the aircraft refueler. BACK PRESSURE: The pressure gauge reading measured directly downstream of the listed co
24、mponent. BACK-PRESSURE CONTROL VALVE: The valve on the test stand that is adjusted to produce a pressure reading in the test stand manifold. CAB-CHASSIS OEM: The original equipment manufacturer of the cab-chassis. PRIMARY PCS: Primary Pressure Control System, the first pressure control system that c
25、ontrols the aircraft refueling pressure. The PCS may also control flow. All measurements shall be measured directly downstream of the refueling nozzle(s). PROPER OPERATION: Refers to a component or system as listed and means that the component or system performs in a satisfactory manner as indicated
26、 by the manufacturer of component or system. This statement shall also mean that the component, a system, or any integral parts of a system are not damaged, are in good operating condition as required by the component manufacturers recommended inspection requirements, and that there are no indicatio
27、ns showing that any of its parts are faulty. SAE ARP5918 - 4 -SECONDARY PCS: Secondary Pressure Control System, the second pressure control system that controls the aircraft refueling pressure directly downstream of the refueling nozzle(s). The PCS may also control flow. SURGE TEST CONTROL VALVE: Th
28、e valve on the test stand that is automatically operated to close within a designated timeframe, from full-open to full-closed, to stop fuel flow into the test stand manifold. VEHICLE OEM: The original equipment manufacturer of the vehicle and identified as the final-stage vehicle manufacturer.VEHIC
29、LE PURCHASE SPECIFICATIONS: The vehicle specifications as stipulated by the purchaser outlining the minimum equipment, capabilities, and operating requirements. 4. TEST FACILITY DESIGN CRITERIA 4.1 General Requirements The test facility shall be equipped with all necessary test equipment and instrum
30、entation to test aircraft refueling vehicles by simulating aircraft refueling operations and provide a pass or fail result for each particular test. All tests shall be performed to the criteria as described within this document to indicate compliance with this standard. This document provides the mi
31、nimum test requirements for an aircraft refueling vehicle to document that at the time of testing, the vehicle performs satisfactory for all aircraft refueling operations. The test facility and its equipment shall be designed to continuously operate without undue stresses or abnormal wear on any com
32、ponents or structures. The test facility shall be designed so that the principles of engineering and ergonomics are designed into the test procedure and functional controls of the test equipment and instrumentation. All test facilities shall meet all federal, state, local, statutory requirements app
33、licable at the installed location. 4.2 Materials of Construction All materials in contact with the fuel and not specified elsewhere in this document shall be corrosion resistant and shall not be adversely affected by or affect the fuel. Except for pumps which may be unlined steel, all metallic compo
34、nents and piping shall be of aluminum, stainless steel, or internally lined carbon steel, as required by local code. All material in contact with the fuel shall also be free of cadmium, lead, or zinc. Brass components shall be minimized but accepted in hose couplings and sump drain valves. Copper co
35、mponents will be minimized but accepted in drain lines that render the product as waste fuel. Non-metallic materials shall not affect or be adversely affected by the fuel under any operating conditions specified for any equipment handling the product. 4.3 Refueling System Test Stand Design Requireme
36、nts The test stand shall be designed with the minimum components and instrumentation as shown in the attached drawing in Appendix A. The components shall have the following minimum requirements to perform a complete test of an aircraft refueling vehicle: 4.3.1 Fuel Hydrant Discharge System The fuel
37、hydrant discharge system shall have a piping system with the outlet terminating with a hydrant valve. The fuel hydrant discharge system shall have the following minimum requirements: 4.3.1.1 Comply with ASME B31.3 and NFPA 407 requirements. 4.3.1.2 Pumping system capable of continuously pumping the
38、product at the stable steady Discharge Pressure listed below. The test piping shall be equipped with a pressure control system that maintains a stable fuel pressure within 2 psig within any period of time during the complete test. The system shall also be capable of continuously pumping at the desig
39、nated pressure, the minimum flow rate listed below. The Discharge System shall be set to operate as follows: SAE ARP5918 - 5 - Discharge Pressure: 150 psig or the highest steady pressure that is achieved at any hydrant on the airport hydrant system where the vehicle is used (Measured by the hydrant
40、fuel pressure gauge) Discharge Flow: Flow rate that is 20% higher than the flow rating of the Aircraft Refueler (as designated by the Aircraft Refueler OEM) 4.3.1.3 Except for airport installations, Filter-Separator and/or filter-monitor vessel(s) that filters all fuel before dispensing it through t
41、he hydrant valve. 4.3.1.4 Hydrant valve that meets all API/EI 1584 requirements, unless a different hydrant valve is used on the airport hydrant system where the vehicle is used. The hydrant valve shall have the same components, operation, and performance as the hydrant valves used on the airport hy
42、drant system where the vehicle is used. 4.3.1.5 Hydrant fuel pressure gauge that measures the fuel pressure directly upstream of the hydrant valve. The gauge shall be a digital gauge with a pressure transducer. The gauge shall be calibrated and have a range of 0 to 200 psig and a minimum accuracy of
43、 2% of full scale. The gauge shall also have test ports to calibrate and test its accuracy. 4.3.1.6 Fuel flow meter that measures all fuel dispensed through the test stand. The meter shall be capable of being calibrated to +/-0.1% and 0.05% repeatability and be rated for the operating pressure and f
44、low required for the test vehicle. The meter shall be used as a reference only and not used as a master meter for calibrations. 4.3.1.7 Fuel temperature gauge that measures the fuel temperature directly upstream of the hydrant valve. The gauge shall be a digital gauge and shall have test ports to ca
45、librate and test its accuracy. 4.3.2 Fuel Receiving System The test stand shall be equipped with a fuel receiving system that returns fuel to a test product tank and does not develop more than 5 psig back pressure measured directly downstream of the underwing nozzle connections. A dedicated test pro
46、duct tank is preferred. The fuel receiving system shall have the following minimum requirements: 4.3.2.1 Ground Fueling System Test The ground fueling test system shall be used to test the Aircraft Refuelers ground fueling connections. The ground fueling test system shall consist of two 2-1/2 inch u
47、nderwing nozzle adapters connected to a manifold piping assembly that is symmetrically connected into a tee that connects to a single pipeline that recirculates fuel back to the product tank. The adapters shall be installed so that they are in a horizontal position and at a height of 30 inches 10 in
48、ches above the ground.4.3.2.2 Elevated Fueling System Test The elevated fueling test system shall be used to test the Aircraft Refuelers elevated fueling connections (e.g., connections located on an elevating platform). The elevated fueling system shall consist of two 2-1/2 inch underwing nozzle ada
49、pters connected to a manifold piping assembly that is symmetrically connected into a tee that connects to a single pipeline that recirculates fuel back to the product tank. The adapters shall be installed so that they are overhead in a vertical position and at a height of 192 inches 1 inch, measured from the ground to the bottom of the nozzle adapter. NOTE: The test stand may be equipped with either the ground fueling system te
