SAE AS 5877A-2007 Detailed Specification for Aircraft Pressure Refueling Nozzle《航空器压力加注嘴用详细规范》.pdf

《SAE AS 5877A-2007 Detailed Specification for Aircraft Pressure Refueling Nozzle《航空器压力加注嘴用详细规范》.pdf》由会员分享，可在线阅读，更多相关《SAE AS 5877A-2007 Detailed Specification for Aircraft Pressure Refueling Nozzle《航空器压力加注嘴用详细规范》.pdf（26页珍藏版）》请在麦多课文档分享上搜索。

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 reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2007 SAE International All rights reserved. No part of this publication m

3、ay 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: 724-776-4970 (outside USA)

4、 Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org AS5877 REV. A AEROSPACE STANDARD Issued 2001-07 Revised 2007-06 Superseding AS5877 Detailed Specification for Aircraft Pressure Refueling Nozzle RATIONALE This revision adds two new pressure fueling nozzle classes, u

5、pdates exisiting pressure refueling nozzle class definitions, updates publication references, adds new pressure fueling nozzle classes to performance and test requirement paragraphs, and corrects typographical errors. 1. SCOPE This SAE Aerospace Standard (AS) prescribes requirements for the various

6、types of nozzles that are used for the refueling of aircraft fitted with pressure fuel servicing systems. It is to be used as a replacement for MIL-N-5877, MS29520 and for all commercial applications. 1.1 Classification The nozzles specified herein shall be classified in accordance with Table 1. Typ

7、e I nozzles are primarily used by the US military services; Type II nozzles are primarily used in commercial service. 1.2 Field of Application This specification is for all nozzles that are utilized either in commercial or military applications where the aircraft system utilizes pressure fuel-servic

8、ing systems. The nozzle shall be compatible with and mate with the international aircraft adapter fitting in accordance to ISO 45 Aircraft Pressure Refueling Connections. 1.3 Nozzle Configuration The nozzle shall conform to the design interface envelope of Figure 1 of this document. The inlet config

9、uration outside of the envelope is at the manufacturers option and may be designed to have an angled, straight or variable configuration to meet individual requirements. The envelope restrictions are mandatory to assure that aircraft fuel system manufacturers and nozzle manufacturers have a common i

10、nterface with which to work. This will assure compatibility between the available nozzles and the aircraft refueling system adapters. The nozzle may be configured to include various features and be available in various inlet configurations including, but not necessarily limited to those shown in Tab

11、le 2. 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 other publications shall be the issue in effect on the date of the purchase order. In the event of conflict

12、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 regulations unless a specific exemption has been obtained. Copyright SAE International Provided by IHS under license with SAENo

13、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AS5877 Revision A - 2 - TABLE 1 Type Class Description I D-1 Pressure refueling nozzle with a curved inlet with a 6-bolt flange and without a hose end control valve. Various accessories may be added to the basic noz

14、zle as noted herein. I D-1R Same as Type I, Class D-1 except a 45-psi or 55-psi hose end control valve is included as an accessory. I D-2 Same as Type I, Class D-1 except the inlet is straight. I D-2R Same as Type I, Class D-2 except a 45-psi or 55-psi hose end control valve is included as an access

15、ory. I D-3 Same as Type I, Class D-1 except a variable inlet configuration is used. The variable inlet configuration can assume either the D-1 or D-2 configuration without disassembly. I D-3R Same as Type I, Class D-3 except a 45-psi or 55-psi hose end control valve is included as an accessory. II U

16、nderwing nozzle designed primarily for commercial usage with a straight body and various inlet connections and without a hose end control valve. Various inlets and accessories may be included as noted herein. II R Same as Type II except a hose end control valve is included as an accessory. The custo

17、mer shall specify the pressure setting for the hose end control valve. III - Underwing nozzle designed primarily for commercial usage with a variable geometry body and various inlet connections, but without a hose end control valve. Various accessories may be included as noted herein. III R Same as

18、Type III except a hose end control valve is included as an accessory. The customer shall specify the pressure setting for the hose end control valve. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-S

19、AE AS5877 Revision A - 3 - FIGURE 1 - ENVELOPE REQUIREMENTS3. Certain provisions (dimensions required for connection with the adapter and envelope dimensions) of this specification are the subject of international standardization agreements ASIC AIR STD 25/4, NATO STANAG 3105, and ISO 45. When a rev

20、ision of AS5877 is proposed which shall affect or violate the international agreements concerned, appropriate reconciliation action through international standardization channels shall be taken. 4. Nozzle poppet face shall be located at 0.475 to 0.506 inches above the Adapter Locking Lug Reference P

21、lane (adapter is located in an underwing position with the lugs on the surface away from the aircraft wing). Nozzle poppet travel shall be 1.375 min to 1.436 max inches. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without li

22、cense from IHS-,-,-Feature Size/Type Description Inlet Thread 2, 2-1/2 55-psig for US Navy, US Marine Corps and US Air Force. 3.3.11 Maintenance Wherever possible, industry standard seals (packings or O-rings) shall be utilized provided they meet the requirements of this specification. The overhaul

23、of the nozzle shall be possible by maintenance personnel with a minimum of training, tools and equipment normally available commercially. 3.3.12 Protective Devices A protective bumper of a fuel resistant material shall be provided around the outlet major diameter to protect the aircraft structure an

24、d the nozzle from accidental impact damage during use and operation. Optional self-sacrificing (of non-foreign object damage FOD design), brackets, pads or rings may be provided to protect certain critical parts of the nozzle from damage caused by dragging. 3.3.13 Dust Cap A non-metallic cap shall b

25、e provided to prevent dust and other foreign debris from entering the outlet portion of the nozzle during handling and storage. When the nozzle is connected to a receiving adapter, the dust cap shall hang free so that it shall not interfere with the refueling operation. The use of springs for cap re

26、tention is not allowed. The material of the cap shall be resistant to exposure to ultra-violet, aviation fuels and the combination of high humidity and temperature. 3.3.14 Lubrication The nozzle shall operate without the use of lubricants. 3.3.15 Fuel Compatibility The nozzle shall not malfunction w

27、hen used with fuels conforming to MIL-DTL-5624, MIL-DTL-83133, MOD DEF STAN 91-91 (DERD 2494), ASTM D 1655, ASTM D 6227, ASTM D 6615, and ASTM D 910. 3.3.16 O-rings, Packings and Seals O-rings or packings and associated seals shall be suitable for use in hydrocarbon fuels and meet the test requireme

28、nts of this specification. Special shaped seals shall be kept to a minimum. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AS5877 Revision A - 9 - 3.3.17 Pressures 3.3.17.1 System Operating Pres

29、sure The nozzle shall be designed to refuel aircraft at a maximum operating pressure of 60-psi (413.7-kPa) with a surge pressure of up to 300-psi (2068.5-kPa). 3.3.17.2 Pressure Loss The corrected gauge pressure loss across the nozzle and the mating adapter shown in Figure 4 shall be kept to a minim

30、um. The use of the adapter in Figure 4 provides a standard of comparison for all manufacturers. Other pressure loss data using other mating adapters may also be useful to the customer. 3.3.17.2.1 Military Type I, Class D-1, D-2 or D-3 Nozzles The pressure loss across the nozzle/adapter combination s

31、hall not exceed 15-psid at a flow rate of 600 gpm. 3.3.17.2.2 Military Type I, Class D-1R, D-2R or D-3R Nozzles The pressure loss across the nozzle/hose end control valve/adapter shall not exceed 35-psid at a flow rate of 600 gpm. The hose end control valve shall be in a full (blocked) open position

32、 for this requirement. 3.3.17.2.3 Commercial Nozzles, All Types Due to the many commercial configurations possible no specific design parameter will be offered in this document for those nozzle configurations. Manufacturers shall determine and report the pressure loss for the various combinations of

33、 equipment offered. 3.3.17.3 Pressure Limitation (Class D-1R, D-2R, D-3R 4-60-psig - 2 cc/min; During actuation - 0-60-psig - 2 cc/min per actuation. (4) Test fluid shall be 2,2,4-Trimethylepentane and Toluene mixed 70-30% by volume. (5) Test fluid to be 2,2,4-Trimethylepentane. SAE AS5877 Revision

34、A - 22 - TABLE 6 - FUEL RESISTANCE AND LOW TEMPERATURE TEST SCHEDULE Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AS5877 Revision A - 23 - 4.6.10.2 Open The test in 4.6.10.1 with the unit open

35、 and connected to the test adapter. The test pressure shall be 300-psig (2068.5-kPa). 4.6.11 Burst Pressure 4.6.11.1 Closed The unit shall be closed for this test. 240-psig (1655-kPa) pressure shall be applied to the inlet for at least 1 min. On Class D-1R, D-2R, D-3R and R nozzles, the regulator sh

36、all be blocked in the open position during this test. The inlet pressure shall be reduced to 60-psig (413.7-kPa) for 1 min. There shall be no visual evidence of structural rupture to any part of the nozzle. External leakage through normal sealing joints shall be permissible as long as the leakage qu

37、its once the pressure has been reduced to 60-psig. 4.6.11.2 Open The unit shall be attached to a test adapter and the nozzle in the open position. The test in 4.6.11.1 shall be repeated with a pressure of 450-psig (3103-kPa). 4.6.12 Drop Test The nozzle, attached to a 12-ft (3.66-m) length of 2-1/2-

38、in hose, shall be dropped at least 10 times from a height of 6 ft (1.83-m) onto a concrete floor. The hose shall be full of test fluid and pressurized to 15-psig (103.4-kPa). Drops shall be configured to impact at least four times upon the carrying handles (two on each), three times at 90 to the car

39、rying handles and three times on the operating lever or in the area in which the operating lever is located should the operating lever be protected by other structure. On the nozzle utilizing a wheel-type carrying handle, the drop testing can be conducted at random locations around the nozzle. The u

40、pstream portion of the hose shall lie at floor level during the test. Following this test the nozzle shall be subjected to the functional test of 4.6.2.1 and the leakage test in accordance with 4.6.4.2 (positive pressures only). There shall be no evidence of damage to the nozzle that would affect th

41、e performance of the unit. If the carrying handles are bent following the test to a level sufficient enough to prevent operation, they shall be bent back to a position that allows operation. Out right breakage of the handles shall be a cause for failure. The drop test above shall be repeated a total

42、 of four more times (40 drops). It is permissible to replace the carrying handles and operating lever a maximum of one time during this repeated test. It shall be so noted in the test report. 4.6.13 Electrical Conductivity With the nozzle attached to the test adapter, resistance reading shall be mad

43、e between the nozzle inlet and the adapter-mounting flange. Resistance shall not exceed 10 . 4.6.14 Disassembly and Inspection The nozzle shall be disassembled in accordance with the maintenance manual for inspection of all parts. All anomalies shall be reported and discussed in the text of the repo

44、rt. There shall be no evidence of wear, other defects or indication of imminent failure of any part that would cause the nozzle to fail to function within the specified limits. There shall be no evidence of loose fragments that could enter the aircraft fuel system. 4.6.15 Strainer Strength The strai

45、ner shall be blocked in a suitable fashion to prevent flow through it. It shall be subjected to a differential pressure of 35-psi in the fueling direction without damage. Increase the differential pressure to determine the point at which damage occurs. The results of both tests shall be reported. An

46、 optional test to determine the maximum defueling flow capability of the strainer may be of value to some nozzle users. Addition of such test data in the test report may be of value to and required by these users. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo rep

47、roduction or networking permitted without license from IHS-,-,-SAE AS5877 Revision A - 24 - 4.6.16 Worn Adapter Test A test adapter bayonet flange shall be machined to make the lugs and slots in accordance with the dimensions outlined in ARP5298. The tests specified in 4.6.2.1 and 4.6.4.1 at pressur

48、es of 5 and 120 psig (34.5 and 827.4-kPa) shall be conducted. The test unit shall be attached to the worn adapter and opened. The nozzle shall be checked to determine if it can be removed from the adapter in the open position by slowly rotating it in a counter-clockwise direction. The nozzle shall be positively locked in the “connected” position. 4.7 Approval The manufacturer shall use ingredients, manufacturing procedures and methods of inspection on production nozzles, which are the same as those used on the qualification samples. If it is necessary to make