SAE AS 5385D-2017 Cargo Restraint Straps - Design Criteria and Testing Methods.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 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 2017 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:/standards.sae.org/AS5385D AEROSPACE STANDARD AS5385 REV. D Issued 2000-09 Reaffirmed 2012-11 Revised 2017-05 Supe

5、rseding AS5385C Cargo Restraint Straps - Design Criteria and Testing Methods RATIONALE Revision D eliminates D5 and D6 end fittings, revises the flammability test burn rate consistent with FAA regulations amendment 111, and renumbers paragraphs per current requirements for SAE standards. TABLE OF CO

6、NTENTS 1. SCOPE 3 2. REFERENCES 4 2.1 Applicable Documents 4 2.1.1 SAE Publications . 4 2.1.2 NAS Publications . 4 2.1.3 ISO Publications 4 2.1.4 FAA Publications . 5 2.1.5 U.S. Federal Test Methods Standards 5 2.1.6 EASA Publications 5 2.2 Definitions 5 3. DESIGN CRITERIA . 8 3.1 Compatibility 8 3.

7、2 Ultimate Load 9 3.3 Elongation . 9 3.4 Flammability 9 3.5 Environmental Degradation . 10 3.6 Dimensions . 10 3.6.1 Length . 10 3.6.2 Width . 11 3.7 Tensioning Device . 11 3.8 End Fittings . 12 3.9 Webbing and Sewing 12 3.10 General 13 4. TESTING METHODS 13 5. QUALITY CONTROL 17 6. MARKINGS . 18 SA

8、E INTERNATIONAL AS5385D Page 2 of 21 7. OPTIONS 19 7.1 Types of Hardware (Tensioning Device and End Fittings) 19 7.2 Rated Ultimate Load, if Different from 22250 N (5000 lbf) 19 7.3 Length of the Fixed and Adjustable Webbing Lengths . 19 7.4 Color Scheme . 19 7.5 Definition of Expected Storage and S

9、ervice Life (Affects Environmental Degradation, Webbing Abrasion, Cyclic Load Test) . 19 7.6 Optional Tests . 19 7.7 Tension Force Indicator 20 8. OPERATING CONSIDERATIONS 20 9. NOTES 20 Figure 1 Examples of restraint strap equipment, including tensioning device C, end fitting D, and tension force i

10、ndicator E . 7 Figure 2 Two-piece restraint strap assembly 8 Figure 3 10 Figure 4 18 Figure 5 Typical marking labels . 19 Table 1 17 SAE INTERNATIONAL AS5385D Page 3 of 21 1. SCOPE 1.1 This SAE Aerospace Standard (AS) aims at identifying the design criteria and testing methods adequate to guarantee

11、the ultimate load and operational dependability of cargo restraint strap assemblies with a typical 22250 N (5000 lbf) rated ultimate tension load capability, as used by the airline industry in order to restrain cargo on board civil transport aircraft during flight: a. cargo loaded and tied down onto

12、 airworthiness certified air cargo pallets, themselves restrained into aircraft lower deck or main/upper deck cargo systems and meeting the requirements of NAS 3610 or AS36100, or b. non-unitized individual pieces of cargo, or pieces of, cargo placed onto an unrestrained (“floating”) pallet into eit

13、her lower deck or main deck containerized cargo compartments of an aircraft. 1.2 The same restraint strap assemblies can also be used in other applications such as: a. restraint of non-containerized (bulk loaded) baggage and cargo in aircraft compartments, b. to ensure cargo restraint inside an airw

14、orthiness certified air cargo container. NOTE 1: The ultimate loads allowable on the attachment points available in most aircraft bulk compartments and inside most air cargo containers are significantly lower than 22250 N (5000 lbf). This results in the restraint arrangements ultimate load capabilit

15、y being dictated by the weakest element, i.e., the attachment points; typical 22250 N (5000 lbf) ultimate load restraint straps will, therefore, be in excess of the allowable for such applications. 1.3 This Standard describes the design criteria for individual restraint strap assemblies, but does no

16、t intend specifying in any manner the way they are to be used aboard aircraft to ensure proper restraint throughout the certified flight envelope. Tie-down arrangements shall meet all the applicable requirements of the Airworthiness Authorities approved Weight and Balance Manual for the aircraft typ

17、e or sub-type concerned, particularly as regards, but not necessarily limited to, ultimate load factors to be taken into account to determine the number of straps to be used in each direction of restraint, maximum angles to be observed with the direction of restraint, minimum spacing of attachment p

18、oints, etc. 1.4 When restraint strap assemblies are attached to the edge rails of a certified air cargo pallet meeting the requirements of NAS 3610 or AS36100, operating instructions should duly take into account the restraint net attachment point locations on the pallet edge rail and other requirem

19、ents defined by the appropriate NAS 3610 or AS36100 configuration drawing(s). 1.5 The use of reliable and guaranteed restraint strap assemblies does not alone ensure flight safety: it also requires straps to be used and tie-down to be performed in accordance with operating instructions established b

20、y the aircraft manufacturer, by competent, suitably trained, personnel. 1.6 Subject to proper operating instructions as per 1.3 and 1.4 being defined and complied with, using unit restraint strap assemblies manufactured to an adequate design and a tested ultimate load capability is nevertheless deem

21、ed necessary in order to ensure flight safety. General utilization guidelines and calculation methods adequate to guarantee the effectiveness and ultimate load strength of tie-down/lashing arrangements performed to restrain cargo on board civil transport aircraft may be found in ARP5595 (or ISO 1604

22、9-2 equivalent). SAE INTERNATIONAL AS5385D Page 4 of 21 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 ef

23、fect 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 document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 2.1

24、.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. AIR1490 Environmental Degradation of Textiles ARP5595 Cargo Restraint Straps - Utilization Guidelines AS11

25、30 Air and Air/Surface (Platform) Cargo Pallets AS1491 Interline Air Cargo Pallets AS33601 Track and Stud Fitting for Cargo Transport Aircraft, Standard Dimensions for AS36100 Air Cargo Unit Load Devices - Performance Requirements and Test Parameters 2.1.2 NAS Publications Available from Aerospace I

26、ndustries Association, 1000 Wilson Boulevard, Suite 1700, Arlington, VA 22209-3928, Tel: 703-358-1000, www.aia-aerospace.org. NAS 3610 Rev 10 Minimum Airworthiness Requirements and Test Conditions for Certified Air Cargo Unit Load Devices 2.1.3 ISO Publications Available at http:/webstore.ansi.org/

27、or International Standard Organization (ISO), website www.iso.org, or any of the national standards institutes worldwide, members of ISO. ISO 2076 Textiles - Man-made fibres - Generic names ISO 7166 Aircraft - Rail and stud configuration for passenger equipment and cargo restraint (updated AS33601 t

28、rack and stud, see above) ISO 9788 Air cargo - Double stud tie-down fittings Design and testing requirements ISO 16049-1 Air cargo equipment - Restraint straps - Part 1: Design criteria and test requirements ISO 16049-2 Air cargo equipment - Restraint straps - Part 2: Utilization guidelines and lash

29、ing calculations SAE INTERNATIONAL AS5385D Page 5 of 21 2.1.4 FAA Publications Available from Federal Aviation Administration, 800 Independence Avenue, SW, Washington, DC 20591, Tel: 866-835-5322, www.faa.gov. Federal Aviation Regulations Title 14 Code of Federal Regulations (14 CFR) Part 25, Airwor

30、thiness Standards: transport category airplanes Technical Standard Order TSO-C172 Cargo Restraint Strap Assemblies 2.1.5 U.S. Federal Test Methods Standards Available at http:/quicksearch.dla.mil/. U.S. Federal Test Method Standards No. 191A, Method 4108, Strength and elongation, breaking; textile w

31、ebbing, tape and braided items U.S. Federal Test Method Standards No. 191A, Method 5309-1, Abrasion resistance of textile webbing 2.1.6 EASA Publications Available from European Aviation Safety Agency, Postfach 10 12 53, D-50452 Cologne, Germany, Tel: +49-221-8999-000, www.easa.eu.int. European Avia

32、tion Safety Agency CS-25 (EASA CS), Certification Specification for Large Aeroplanes European Technical Standard Order ETSO-C172 Cargo Restraint Strap Assemblies 2.2 Definitions For the purpose of this Standard, the following definitions apply: 2.2.1 RESTRAINT STRAP ASSEMBLY Elementary tie-down unit

33、 consisting of flat woven textile webbing, (one fixed length end and one adjustable end), one tensioning device and two end fittings, used for restraint of cargo on board civil transport aircraft. 2.2.2 TIE-DOWN Fact of restraining cargo movements in relation to an aircrafts structure, throughout th

34、e range of relative accelerations resulting from the allowable flight envelope, by means of an appropriate use of a number of elementary tie-down devices against each direction of restraint. 2.2.3 FLAT WOVEN TEXTILE WEBBING Conventional or shuttleless woven narrow fabric made of textile fibers, gene

35、rally with multiple plies, and the prime function of which is load bearing. A characteristic of webbing is its narrow fabric selvedge. 2.2.4 TENSIONING DEVICE Mechanical device inducing a tensile force in the load restraint assembly (e.g., ratchets, winches, overcenter buckles). See examples in Figu

36、re 1, C1, C2, and C6. 2.2.5 TENSION RETAINING DEVICE Metallic part connecting the webbing by clamping action and retaining the force induced in the tensioning device by hand (e.g., cambuckles, sliding bar buckles). SAE INTERNATIONAL AS5385D Page 6 of 21 2.2.6 END FITTING Metallic device connecting t

37、he webbing or the tensioning device to the attachment point on the aircraft structure, the pallet edge rail or the load (see examples in Figure 1, D1 to D4). NOTE 2: The end fittings most commonly used on air cargo restraint straps include: a. retainer equipped flat hook (see example in Figure 1, D1

38、), b. air cargo tie-down double stud (male) fitting that conforms to either ISO 9788, for restraint of 22250 N (5000 lbf) ultimate load, or AS33601, for lower ultimate loads, connected directly (sewn to the webbing, see example in Figure 1, D3) or by an intermediate ring, or c. piece of aircraft res

39、traint (female) rail conforming to AS33601. 2.2.7 TENSION FORCE INDICATOR A device (see 7.7) that indicates the tensile force applied to the restraint strap assembly by means of the tensioning device and the movement of the load acting on the load restraint device. 2.2.8 LENGTH OF RESTRAINT STRAP AS

40、SEMBLY 2.2.8.1 Length (IGF) Length of a fixed end, measured from the force bearing point of the end fitting to the outer turning radius of the connection of the webbing to the tensioning device (see Figure 2). 2.2.8.2 Length (IGL) Length of an adjustable end, measured from the free end of the webbin

41、g with the minimum possible length engaged into the closed tensioning device to the force bearing point of the end fitting (see Figure 2). 2.2.8.3 Total Length (I) (IGF) + (IGL) + length of the tensioning device. 2.2.9 BREAKING FORCE (BF) The maximum force that the restraint strap assembly withstand

42、s when tested in a complete form, i.e., with tensioning device and end fittings. 2.2.10 HAND FORCE (HF) Force applied to the handle of the tensioning device, which creates the tensile force in the restraint strap assembly. 2.2.11 LIMIT LOAD (LL) The maximum load to be expected in service. Refer to 1

43、4 CFR/EASA CS 25.301 (a). It is two-thirds of the ultimate load (see hereafter); i.e., 14827 N (3333 lbf) for a typical rated ultimate load of 22250 N (5000 Ibf). SAE INTERNATIONAL AS5385D Page 7 of 21 A restraint strap assembly (complete) A1, A2 space for marking (label) B webbing C tensioning devi

44、ces C1 ratchet tensioner C2 ratchet tensioner with tensino force indicator (see also E) C3 sliding bar buckle C4, C5 overcenter buckles C6 lashing winch D end fittings D1 snap hook, flat, swivel or twisted, with retainer D2 flat hook, with retainer D3 double stud tie-down fitting (directly sewn onto

45、 webbing) D4 triangle, designed to engage with an anchorage E tension force indicator (see also C2) F tension retaining device (cambuckle, sliding bar buckle) Figure 1 - Examples of restraint strap equipment, including tensioning device C, end fitting D, and tension force indicator E SAE INTERNATION

46、AL AS5385D Page 8 of 21 Figure 2 - Two-piece restraint strap assembly 2.2.12 ULTIMATE LOAD (UL) The limit load multiplied by a safety factor of 1.5; refer to 14 CFR/EASA CS 25.303. The restraint strap assemblys rated ultimate load shall be guaranteed not to exceed the measured breaking force (BF). I

47、t shall be used for computation of cargo tie-down arrangements, based on the ultimate load factors defined in the Airworthiness Authorities approved Weight and Balance Manual, in each direction of restraint, throughout the certified flight envelope of the aircraft type. 2.2.13 RESIDUAL TENSION The t

48、ension force which can be measured in the webbing of a strap assembly attached between two fixed points, after its length was adjusted and its tension device was operated and latched with the reference hand force (HF), prior to application of any external load. 2.2.14 COMPETENT PERSON Designated per

49、son, suitably trained, qualified by knowledge and practical experience, and with the necessary instructions to enable the required tests and examinations to be carried out. 2.2.15 TRACEABILITY CODE Series of letters and/or numbers marked on a component or an assembly which enables its manufacturing and in service history to be retraced, including webbing production batch identification. 2.2.16 BATCH (Production Batch) Pe