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 2012 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/AS686B AEROSPACE STANDARD AS686 REV. B Issued 1969-03 Revised 2001-10 Reaffirmed
5、2012-11 Superseding AS686A Piloted Ring Seal Tube Swivel Connection Assembly RATIONALE AS686B has been reaffirmed to comply with the SAE five-year review policy. FOREWORDChanges in this Revision are format/editorial only.1. SCOPE:This standard presents the designer with sufficient information to ful
6、ly define the configuration of the connection and to determine the limits of application for given conditions.1.1 Purpose:To provide design criteria and an index of parts and standards for piloted ring seal tube swivel connections.2. REFERENCES:ARP573AS130MS9378MS9083MS90843. DETAIL REQUIREMENTS:3.1
7、 The assembly diagram in Figure 1 shows the connection assembly with the alternative fastener selection.3.2 This aircraft engine connection is intended for use with fluids such as fuel, oil or air. The temperature range of this connection is dependent upon the material used for the ring seal and is
8、normally within the -65 F to +500 F range. The maximum operating pressure can vary from 800 psi to 3000 psi dependent upon the tube size and wall thickness, and the ring seal and fastener size.(This document supersedes and cancels ARP686, issued 3-15-66, and AS687A, issued 1-15-63.)SAE AS686B Page 2
9、 of 3 a. Use ARP573, “Silver and Copper Alloy Brazed Joints for Aircraft Power Plants,“ for the fabrication of the tube and sleeve assembly. Caution: Cadmium plated parts cannot be subjected to brazing cycle temperature.b. On thru-fastener design, use a connector with turned flange and slab head bol
10、ts, and provide adequate flange and shell wall thickness based on strength requirements using the standard collars and sleeve.c. Ring seals to be coated sparingly with petrolatum or the fluid used in the system and assembled in groove of sleeve. Rotation of sleeve recommended to assure proper positi
11、oning of ring seal.d. Tube may be straight or formed to desired bend radius per AS130, “Bending Radius, Tube.“FIGURE 13.3 Dimensions and recommended torque data applicable to the assembly shown in Figure 1 are given below in Table 1. The minimum tube swage length (A) is equal to the maximum length o
12、f mating hole in the sleeve. Tube swaged diameter should be in accordance with ARP573. The minimum straight tube length should be preferably in accordance with ARP573. This dimension may be reduced to a limit established by dimension “A“ where design permits.SAE AS686B Page 3 of 3 TABLE 1PREPARED UNDER THE JURISDICTION OFSAE COMMITTEE E-25, GENERAL STANDARDS FOR AEROSPACE PROPULSION SYSTEMS
