SAE ARP 6385-2017 Aircraft Fuel Pump Mechanical and Electrical Safety Design.pdf
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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 ther
2、efrom, 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 2017 SAE International All rights reserved. No part of this
3、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: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-49
4、70 (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:/standards.sae.org/ARP6385 AEROSPACE RECOMMENDED PRACTICE ARP6385 Issued 2017-10 Aircraft Fuel Pump Mechanical an
5、d Electrical Safety Design RATIONALE This document is a continuation of the safety information presented in ARP594, which covered the thermal aspects of fuel pump safety design. Other failure modes in FAA AC 25.981-1C fall under the umbrellas of mechanical and electrical design. This new document wi
6、ll address these key elements and when used in combination with ARP594 and ARP5794, will represent a basis for the proper pump design and testing, and support certification of an airframe fuel pump installation. 1. SCOPE The requirements presented in this document address the key considerations for
7、mechanical and electrical safety in aircraft fuel pump design. Document sections focus on understanding safety relative to an electrically motor driven fuel pump assembly acting as an ignition source for explosive fuel vapors within the airplane tank. 1.1 Purpose This Aerospace Recommended Practice
8、(ARP) provides fuel booster pump design considerations commensurate with industry requirements for prevention of ignition of explosive fuel vapors and the confinement of spark-initiated explosions by means of mechanical and electrical design features. Guidelines are presented for proper design of fu
9、el pumps and systems to meet the intent of 14CFR 25.901(c), Amendment 25-40 or later, and 14CFR 25.981, Amendment 25-102 or later and FAA AC 25.981-1C for in-tank ignition sources and the general safety requirements of MIL-STD-882. In addition, recommendations are presented for proper assembly, test
10、ing, and repair/overhaul to verify safe fuel pump design that prevents mechanical and electrical arcs and sparks. 2. 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
11、other publications shall be the issue negotiated between Seller and Buyer. 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, supercedes applicable laws and regulations unless a specif
12、ic 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) or +1 724-776-4970 (outside USA), www.sae.org. ARP594 Fuel Pump Thermal Safety Design ARP4761 Guidelines and Methods for
13、 Conducting the Safety Assessment Process on Civil Airborne Systems and Equipment SAE INTERNATIONAL ARP6385 Page 2 of 12 ARP5794 Centrifugal Aircraft Fuel Pump Requirements, Design and Testing, Aerospace Standard ARP8615 General Specification For Fuel System Components 2.2 Military Publications Copi
14、es of these documents are available online at http:/quicksearch.dla.mil. MIL-STD-810 Environmental Engineering Considerations and Laboratory Tests MIL-STD-882 System Safety 2.3 Other Federal Aviation Administration Advisory Circular Fuel Tank Ignition Source Prevention Guidelines, Document Number AC
15、 25.981-1C. Title 14, Code of Federal Regulations Aeronautics and Space, Paragraph 25.981, Fuel Tank Ignition Prevention RTCA DO160, Environmental Conditions and Test Procedures for Airborne Equipment ASTM E659 Standard Test Method for Autoignition Temperature of Chemicals 3. RELATED REQUIREMENTS FR
16、OM 14CFR 25.981, FAA AC 25.981-1C, AND MIL-STD-882 3.1 Introduction For commercial fuel pumps, the governing regulations for fuel tank safety are provided in 14CFR 25.981 Amendment 125. Detailed guidance to demonstrate compliance for fuel tank ignition prevention is provided in FAA AC 25.981-1C. The
17、re are four primary phenomena that can result in ignition of fuel vapors within an airplane fuel tank. These categories are as follows: Electrical Arcs and Sparks Filament Heating Friction Sparks Hot Surface Ignition or Auto-ignition For military applications, safety guidance is provided by MIL-STD-
18、882, which does not delineate failure categories but focuses on the System Safety Process of identifying, assessing, documenting, and reducing safety risks. The risks are categorized by severity and probability and ranked in a Risk Assessment Matrix. The focus is on risk reduction through design imp
19、rovements, warning devices, signage, procedures, training, and personal protective equipment. In addition to the criteria set forth in MIL-STD-882, the design guidelines presented in FAA AC 25.981-1C should be considered for military products to provide the safest product. 3.2 Definitions ARC FAULT
20、CIRCUIT BREAKER: A device that provides circuit breaker protection by detecting electrical arcing faults and interrupts electrical power to the circuit. AUTO-IGNITION TEMPERATURE: The minimum temperature at which an optimized flammable vapor and air mixture will spontaneously ignite when heated to a
21、 uniform temperature in a normal atmosphere without an external source of ignition. Refer to ASTM E659 for information on standard autoignition test procedures. SAE INTERNATIONAL ARP6385 Page 3 of 12 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS: A type of Airworthiness limitations that define t
22、hose features of the design that must be maintained to ensure that ignition sources will not develop within the fuel tank. These parameters must be verified prior to initial installation in the aircraft and also during maintenance and overhaul as determined by the Component Maintenance Manual. (Othe
23、r types of fuel tank system Airworthiness limitations may include mandatory replacement times, inspection intervals, and related inspection procedures.) ELECTRICAL ARCS: Electrical arcs occur between electrodes which are in contact with each other and carry excessive current which results in melting
24、 at the contact points. This may result in electric arc plasma and/or ejection of molten or burning material. The term thermal sparks is used interchangeably with electrical arcs. ELECTRICAL SPARKS: A spark that is initiated by a potential difference which causes an electrical breakdown of a dielect
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