1、BSI Standards PublicationBS EN 4697:2016Aerospace series Generaland installation requirementsfor passenger seat fittingsBS EN 4697:2016 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of EN 4697:2016. Itsupersedes BS EN 4697:2012 which is withdrawn.The UK participatio
2、n in its preparation was entrusted to TechnicalCommittee ACE/12, Aerospace fasteners and fastening systems.A list of organizations represented on this committee can beobtained on request to its secretary.This publication does not purport to include all the necessaryprovisions of a contract. Users ar
3、e responsible for its correctapplication. The British Standards Institution 2016. Published by BSI StandardsLimited 2016ISBN 978 0 580 90787 6ICS 49.095Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was published under the authority of theStanda
4、rds Policy and Strategy Committee on 30 April 2016.Amendments issued since publicationDate Text affectedBS EN 4697:2016EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 4697 April 2016 ICS 49.095 Supersedes EN 4697:2012English Version Aerospace series - General and installation requirements for p
5、assenger seat fittings Srie arospatiale - Exigences gnrales et dinstallation pour sige passager Luft- und Raumfahrt - Allgemeine und Einbau Anforderungen an die Sitzanbindung von Passagiersitzen This European Standard was approved by CEN on 27 September 2015. CEN members are bound to comply with the
6、 CEN/CENELEC Internal Regulations which stipulate the conditions for giving this European Standard the status of a national standard without any alteration. Up-to-date lists and bibliographical references concerning such national standards may be obtained on application to the CEN-CENELEC Management
7、 Centre or to any CEN member. This European Standard exists in three official versions (English, French, German). A version in any other language made by translation under the responsibility of a CEN member into its own language and notified to the CEN-CENELEC Management Centre has the same status a
8、s the official versions. CEN members are the national standards bodies of Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Ne
9、therlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey andUnited Kingdom. EUROPEAN COMMITTEE FOR STANDARDIZATION COMIT EUROPEN DE NORMALISATION EUROPISCHES KOMITEE FR NORMUNG CEN-CENELEC Management Centre: Avenue Marnix 17, B-1000 Brussels 2016 CEN All r
10、ights of exploitation in any form and by any means reserved worldwide for CEN national Members. Ref. No. EN 4697:2016 EBS EN 4697:2016EN 4697:2016 (E) 2 Contents Page European foreword . 3 1 Scope 4 2 Normative references 4 3 Abbreviations . 5 4 Requirements . 5 4.1 General 5 4.2 Interface . 8 4.3 I
11、nstallation Requirements 11 4.4 Performance and Safety . 13 4.5 Stress requirements 14 4.5.1 Static requirements . 14 4.5.2 Dynamic requirements (rear fitting only) 16 4.6 Environmental requirements 21 4.7 Additional requirements . 21 5 Qualification . 21 Annex A (informative) Standard evolution for
12、m 22 BS EN 4697:2016EN 4697:2016 (E) 3 European foreword This document (EN 4697:2016) has been prepared by the Aerospace and Defence Industries Association of Europe - Standardization (ASD-STAN). After enquiries and votes carried out in accordance with the rules of this Association, this Standard ha
13、s received the approval of the National Associations and the Official Services of the member countries of ASD, prior to its presentation to CEN. This European Standard shall be given the status of a national standard, either by publication of an identical text or by endorsement, at the latest by Oct
14、ober 2016, and conflicting national standards shall be withdrawn at the latest by October 2016. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. CEN and/or CENELEC shall not be held responsible for identifying any or all such paten
15、t rights. This document supersedes EN 4697:2012. According to the CEN-CENELEC Internal Regulations, the national standards organizations of the following countries are bound to implement this European Standard: Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, F
16、ormer Yugoslav Republic of Macedonia, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom. BS EN 4697:2016EN 4697:2016 (E) 4 1 Sc
17、ope This European Standard specifies the installation and removal requirements and the space envelopes for passenger seat fittings on aircraft. The purpose is to reduce the installation time and the tooling required for seat installation by standardizing the seat attachment fasteners (fittings). 2 N
18、ormative references The following documents, in whole or in part, are normatively referenced in this document and are indispensable for its application. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendmen
19、ts) applies. EN 9100, Quality Management Systems Requirements for Aviation, Space and Defence Organizations EN 9133, Aerospace series Quality management systems Qualification procedure for aerospace standard parts AMS 1424J, Deicing/Anti-Icing Fluid, Aircraft1)AMS 1428F, Fluid, Aircraft De-icing/Ant
20、i-Icing, Non-Newtonian, (Pseudoplastic)1) AMS 1550B, Cleaner, Water Base, Aircraft Interior Hard Surface Materials1)AMS 1630C, Cleaner, Carpet Shampoo Type1)AMS 1631C, Cleaner, Carpet Water Extraction Type1)AS8049B, Performance Standard for Seats in Civil Rotorcraft, Transport Aircraft and General A
21、viation Aircraft1)CS-25 Amendment 5, 5thSeptember 2008, Certification Specification for Large Aeroplanes2)FAR 25 Amendment 127, 28thOctober 2008, Airworthiness Standards: Transportation Category Airplanes3)RTCA DO-160F ,6thDecember 2007, Environmental Conditions and Test Procedures for Airborne Equi
22、pment4)1) Published by: SAE National (US) Society of Automotive Engineers (http:/www.sae.org/). 2) Published by: European Aviation Safety Agency (EASA), Postfach 101253, D-50452 Koeln, Germany. 3) Published by: FAA National (US) Federal Aviation Administration (http:/www.faa.gov/). 4) Published by:
23、Radio Technical Commission for Aeronautics (RTCA), 1828 L Street, NW, Suite 805 Washington, DC 20036, USA. BS EN 4697:2016EN 4697:2016 (E) 5 3 Abbreviations For the purposes of this standard, the following abbreviations apply. A/C Aircraft. Acc. According. Fwd Forward. SLD Shear Locking Device. 4 Re
24、quirements 4.1 General The fitting design shall fit within the given space envelope, according to Figure 1 and Figure 6. Key 1 Monument 2 Fitting body 3 Carpet 4 Floor panel 5 Seat rail 6 Raceway Figure 1 Fitting environment 1 All fittings attached to seat legs shall be pre-set to the correct seat t
25、rack dimensions with fine adjustment of the fitting during installation not being necessary. Minimum front to rear fitting distance shall be 482,6 mm (19”) between the extreme studs of each fitting. Figure 2 Aircraft Coordinate System BS EN 4697:2016EN 4697:2016 (E) 6 The front attachment fasteners
26、shall cover the tolerances in X-direction (see Figure 2) that might occur due to installation tolerances (of the seat leg and of the A/C structure). The fitting weight shall be according to Table 1. Table 1 Fitting classes Fitting class Fitting Weight g A Rear triple stud fitting 150 B 250 C Rear qu
27、adruple stud fitting 200 D 290 E Forward single stud fitting 50 F 90 Maintenance or repair work on the seat track shall be taken into account during fitting design. Details see Figure 3. Dimensions in millimetres Figure 3a Seat track top view Figure 3b Seat track 3 D view Continued BS EN 4697:2016EN
28、 4697:2016 (E) 7 Figure 3c Damage repair cross section 1 Figure 3d Damage repair cross section 2 Figure 3e Damage repair top view Key 1 If the amount of material removed on one side of a seat track exceeds 0,3 mm (0,012 inch) maximum in depth, it is necessary to remove the same amount from the other
29、 side, so that a level surface is achieved 2 Minimum remaining thickness after rework 3 Maximum rework depth as reference to nominal thickness Figure 3 Seat track allowable damage limits and repair solutions The fitting design shall show no evidence of any movement/rattling of the fitting-track comb
30、ination. A continuous load path shall be ensured at all times. A shear-locking device should only be incorporated in the rear fitting. Fitting design and performance shall be validated incorporating the fitting-seat combination. BS EN 4697:2016EN 4697:2016 (E) 8 4.2 Interface The fitting shall be co
31、mpatible with the standard seat track concept, see Figure 4 and Figure 5 including the tolerances of the installed seat tracks see Figure 6 and Figure 7. Dimension A Tolerance of 0,1 mm (0,004 inch) on 1 pitch Tolerance of 0,5 mm (0,020 inch) on 100 pitches Figure 4 Seat rail top view Detailed seat
32、rail dimensions, see Table 2. Figure 5 Seat rail cross section BS EN 4697:2016EN 4697:2016 (E) 9 Table 2 Seat rail dimensions Dimensions in millimetres (in inches) A B C D E H R1 R2 R3 min. max. min. max. min. max. min. max. min. max. min. max. min. max. min. max. min. max. 25,3 25,5 19,7 20,0 10,7
33、11,0 20,5 21,0 7,8 8,0 2,3 2,7 13,75 14,25 0 1,0 0,8 1,8 Full 1,0040,9960,7870,7760,4330,4210,8270,8070,3150,3070,1060,0910,03900,0710,031Full NOTE 1 Diameter B and slot centerline D shall be coincident with slot centerline C to within 0,13 mm (0,005 inch). NOTE 2 All faces shall be within 0,5 of th
34、e specified position relative to the upper surface of the rail. Figure 6 Location tolerances of separate tracks BS EN 4697:2016EN 4697:2016 (E) 10 Key 1 Seat track on section 1 2 Junction seat rail 3 Centerline of A1 A2 4 Seat track on section 2 A1 Last hole of seat track section 1 A2 Last hole of s
35、eat track section 2 Figure 7 Track splice tolerance in x The fitting shall be compatible with the currently marketed seat concepts. Therefore several clevis positions of the fitting should be available. The rear fitting shall have dimensions according to Figure 8 and Figure 9 and a compact design wi
36、thout any sharp edges or corners. The front fitting shall have dimensions according to Figure 10 and a compact design without any sharp edges or corners. Dimensions in millimetres Key 1 Shear pin 2 Stud 3 Fitting body Figure 8 Design example rear fitting bottom side BS EN 4697:2016EN 4697:2016 (E) 1
37、1 Dimensions in millimetres Key 1 Bolt 2 Fitting body 3 Floor panel 4 Carpet 5 Seat rail 6 Reference only, 35 to 45 is the best angle for the load introduction Figure 9 Dimensions 2 rear fitting side view It shall be possible to route seat-to-seat cables by/alongside/near the fitting, which in turn
38、shall not damage or squeeze the cables when the seats are shifted inside the rail. Therefore the width shall not exceed max. 25,4 mm (max. 1 inch), according to Figure 8 and Figure 10. Particular attention shall be paid to galvanic corrosion between seat tracks and fitting materials. The seat track
39、fitting material shall be corrosion resistant, considering not only the potential action of water/humidity, but also fluids and materials present in the normal seat environment, as well as passenger activity. 4.3 Installation Requirements The fitting shall be quickly lockable by one person without t
40、he need for any tools. A single tool Allen Key 3/16, or 5/16 shall be used for unlocking of the attachments fasteners. The maximum force for the locking operation shall not exceed (5 1) daN, respecting ergonomic aspects. The (pure) seat installation time, comprising two (2) Fwd and two (2) aft fitti
41、ngs, shall not exceed one (1) minute. The last seat row may have a longer installation time due to restricted accessibility of a monument installation (e.g. Doghouses, partitions, etc.). The SLD shall not include parts that have to be disassembled or removed from the device for seat position shiftin
42、g, removal and installation. The locking motions of the fitting shall not damage the seat track, floor panels or any other component and their surfaces. A clear and reliable visible indication for the SLD in locked position shall be incorporated in order to guarantee correct installation and engagem
43、ent of the fitting. BS EN 4697:2016EN 4697:2016 (E) 12 The SLD engagement/disengagement to the track shall be directly visible to personnel (e.g. quality inspector) standing in the longitudinal passenger aisle. Unhindered access to the attachment fitting shall be considered, e.g. without the need to
44、 disassemble any parts of the seat or any adjacent components as stowages, doghouses, etc. The shifting of seats (movement of the seat in x-direction) fwd and aft shall be possible without having to remove them from the seat rail. The fitting design shall prevent jamming in the seat rail, neither du
45、ring changing the seat position nor during seat installation/removal. The fitting design shall allow seat reconfiguration within five (5) min (e.g. unlock, shift, re-lock of a seat group). For unfastening operations of the fitting the environment shall be considered (e.g. floor panels, carpet, racew
46、ays, monuments), as per Figure 10. Dimensions in millimetres Key 1 Stud 2 Front seat leg 3 Shear pins 4 Rear seat leg 5 Fitting 6 Seat to seat cables 7 Seat track 8 Clearance fitting monument no tool access feasible 9 Monument Figure 10 Fitting Environment 2 BS EN 4697:2016EN 4697:2016 (E) 13 4.4 Pe
47、rformance and Safety In order to avoid unfastening by unauthorized persons, unlocking shall only be possible by use of a tool, see 4.3. SLD Locking function/ device shall not require the use of safety wire. The front and rear fitting shall be protected against abuse loading from passenger feet and l
48、uggage. The fitting design shall avoid passenger injuries. The SLD shall be designed for positive engagement in the seat track. This positive engagement can be gravity, spring loading or self-locking under forward or downward inertia load factors or a combination of these. The SLD shall lock itself
49、in the engaged position by an approved means to sustain flight, landing, abuse and ground test loads. Three (3) life cycle/performance tests shall be performed according to the following procedure: a) Operation of the locking device: The design shall consider a minimum use of 1 000 cycles operating of the locking device. 1) Fit into the seat track. 2) Lock. 3) Unlock. 4) Lift out of the seat rail. Pass/Fail criteria: Rattling. Friction. Play. Forc
