1、 ASD-STAN STANDARD NORME ASD-STAN ASD-STAN NORM ASD-STAN prEN 4832 Edition P1 2017-01 PUBLISHED BY THE AEROSPACE AND DEFENCE INDUSTRIES ASSOCIATION OF EUROPE - STANDARDIZATION Rue Montoyer 10 - 1000 Brussels - Tel. + 32 2 775 8126 - Fax. + 32 2 775 8131 - www.asd-stan.org ICS: Descriptors: ENGLISH V
2、ERSION Aerospace series Adaptor, Pipe coupling 24 Cone up to 35 000 kPa (5 080 psi) Ring-locked fitting and Ring-locked fitting-reducer Inch Series Technical specification Luft- und Raumfahrt Adapter Rohrverschraubung 24 Konus bis 35 000 kPa (5 080 psi) Anschlussverschraubung mit Sicherungsring und
3、Reduzierer Inch-Reihe Technische Lieferbedingung Srie arospatiale Adapteur Systme de raccordement interface conique 24 jusqu 35 000 kPa (5 080 psi) Raccords implanter avec bague de scurite (normal et de reduction) - Srie inch Spcification technique This “Aerospace Series” Prestandard has been drawn
4、up under the responsibility of ASD-STAN (The AeroSpace and Defence Industries Association of Europe - Standardization). It is published for the needs of the European Aerospace Industry. It has been technically approved by the experts of the concerned Domain following member comments. Subsequent to t
5、he publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examination and review by users and formal agreement of ASD-STAN, the ASD-STAN prEN will be su
6、bmitted as a draft European Standard (prEN) to CEN (European Committee for Standardization) for formal vote and transformation to full European Standard (EN). The CEN national members have then to implement the EN at national level by giving the EN the status of a national standard and by withdrawin
7、g any national standards conflicting with the EN. ASD-STAN Technical Committee approves that: “This document is published by ASD-STAN for the needs of the European Aerospace Industry. The use of this standard is entirely voluntary and its applicability and suitability for any particular use, includi
8、ng any patent infringement arising therefrom, is the sole responsibility of the user.” ASD-STAN reviews each standard and technical report at least every five years at which time it may be revised, reaffirmed, stabilized or cancelled. ASD-STAN invites you to send your written comments or any suggest
9、ions that may arise. All rights reserved. No parts of this 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 prior written permission of ASD-STAN. Order details: E-mail: sales
10、asd-stan.org Web address: http:/www.asd-stan.org/ Edition approved for publication 1stJanuary 2017 Comments should be sent within six months after the date of publication to ASD-STAN Mechanical domain Copyright 2017 ASD-STAN prEN 4832:2017 (E) 2 Contents Page Foreword 4 Introduction 4 1 Scope . 5 2
11、Normative references . 5 3 Technical Requirements 7 3.1 System Description 7 3.1.1 Hydraulic pressures 7 3.1.2 Environmental conditions 7 3.1.3 Hydraulic architecture . 8 3.1.4 Hydraulic fluid . 8 3.1.5 Reliability 8 3.1.6 Maintainability 8 3.1.7 Particular conditions 9 3.2 Design and construction 9
12、 3.2.1 Materials and surfaces protection . 9 3.2.2 Threads . 10 3.2.3 Installation and lubrication. 10 3.2.4 Marking . 12 4 Performances 12 4.1 Proof pressure 12 4.2 Pneumatic pressure tightness 12 4.3 Hydraulic impulse resistance . 12 4.4 Minimum hydrostatic capability (burst test resistance) 13 4.
13、5 Flexure resistance . 13 4.6 Reuse capability . 14 4.7 Tensile load capability 14 4.8 Thermal shock 15 4.9 Over tightening 15 4.10 Electrical conductivity . 16 4.11 Salt spray 16 4.12 Vibration . 17 4.12.1 General 17 4.12.2 Normal flight conditions . 17 4.12.3 Fan blade off event (FBO) . 19 4.12.4
14、Wind millingsustained engine imbalance 19 4.13 Fire test . 19 4.14 System pressure test 19 4.15 Stress corrosion . 20 5 Quality Assurance . 20 5.1 Responsibility for inspection 20 5.2 Classification of inspections 20 5.3 Qualification inspection 20 5.3.1 General 20 5.3.2 Product qualification . 20 5
15、.4 Quality conformance inspection 20 5.4.1 Non-destructive tests . 20 5.4.2 Acceptable quality level 20 5.4.3 Destructive tests 21 prEN 4832:2017 (E) 3 5.4.4 Inspection . 21 5.4.5 Rejection and retest 21 5.5 Quality conformance inspection procedures 22 5.5.1 Examination of product . 22 5.5.2 Materia
16、l certification . 22 5.5.3 Rolled threads 22 5.5.4 Fluid passages . 22 5.5.5 Sampling instructions 22 5.5.6 Periodic inspections . 22 5.6 Test conditions . 22 5.6.1 Test fluids . 22 5.6.2 Specimen preparation . 22 5.6.3 Lubricants 22 5.6.4 Qualification test procedures . 22 5.6.5 Sampling instructio
17、ns 22 6 Preparation for delivery . 24 6.1 Cleaning. 24 6.2 Packaging . 24 6.3 Marking . 24 6.4 Intermediate container . 24 6.5 Shipping container 24 6.6 Inspection . 24 Bibliography . 25 prEN 4832:2017 (E) 4 Foreword This standard was reviewed by the Domain Technical Coordinator of ASD-STANs Mechani
18、cal Domain. After inquiries and votes carried out in accordance with the rules of ASD-STAN defined in ASD-STANs General Process Manual, this standard has received approval for Publication. Introduction This standard is co-owned standard and a functional equivalent of AS5000. There should be no techn
19、ical objection to use AS5000 as replacement of EN 4832 parts. Further revisions to this standard shall be coordinated with the SAE committee. European Standards use the International System of units (SI); however, large segments of the aerospace industry make use of other measurement systems as a ma
20、tter of common working practice. All dimensions and units used in this Standard are given in SI units, with other units also indicated for the convenience of the user. The decimal sign used in European Standards is the comma (“,”); however, the comma is not used in common working practice with non-S
21、I dimensions. Therefore, in common with many other aerospace standards, the decimal point (“.”) is used in this Standard when providing dimensions in inch-pound units. NOTE The use of non-SI units and the decimal point in this Standard does not constitute general acceptance of measurement systems ot
22、her than SI within European Standards. prEN 4832:2017 (E) 5 1 Scope This specification establishes the requirements for Ring locked fitting assemblies according to EN 4833 and EN 4836, for use in aircraft systems at nominal operating pressure of 35 000 kPa (5 080 psi) maximum and temperature range o
23、f -54 C to +135 C (-65 F to +275 F). 2 Normative 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 ref
24、erenced document (including any amendments) applies. EN 2424, Aerospace series Marking of aerospace products EN 3311, Aerospace series Titanium alloy TI-P64001 (Ti-6Al-4V) Annealed Bar for machining D 110 mm EN 3314, Aerospace series Titanium alloy TI-P64001, solution treated and aged; bar for machi
25、ning D = 75 mm EN 4833, Aerospace series Pipe coupling 24Cone up to 35000kPa (5080psi) Ring-locked fitting Flared End Inch Series with Extra Fine Thread Pitch1)EN 4834, Aerospace series Adaptor, Pipe coupling 24Cone up to 35 000 kPa (5 080 psi) Port for Ring locked fitting Inch Series Geometric conf
26、iguration1)EN 4836, Aerospace series Pipe coupling 24Cone up to 35000kPa (5080psi) Ring-locked fitting Reducer Flared End Inch Series with Extra Fine Thread Pitch1) EN 6102, Aerospace series Fluid, Hydraulic, Phosphate ester-base, fire resistant Technical specification1)ISO 2685, Aircraft Environmen
27、tal test procedure for airborne equipment Resistance to fire in designated fire zones ISO 2859 (all parts), Sampling procedures and tables for inspection by attributes ISO 3161, Aerospace UNJ threads General requirements and limit dimensions ISO 4287, Geometrical Product Specification (GPS) Surface
28、texture: Profile method Terms, definitions and surface texture parameters ISO 6772, Aerospace Fluid systems Impulse testing of hydraulic hose, tubing and fitting assemblies ISO 6773, Aerospace Fluid systems Thermal shock testing of piping and fittings ISO 7137:1995, Aircraft Environmental conditions
29、 and test procedures for airborne equipment ISO 7257, Aircraft Hydraulic tubing joints and fittings Rotary flexure test ISO 10583:1993, Aerospace fluid systems test methods for tube/fitting assemblies ISO 11218:1993, Aerospace Cleanliness classification for hydraulic fluids 1)Published as ASD-STAN P
30、restandard at the date of publication of this standard (www.asd-stan.org). prEN 4832:2017 (E) 6 AMS 2486, Conversion coating of titanium alloys fluoride-phosphate type2)AMS 2488, Anodic treatment of titanium and titanium alloys2)AMS 2700, Passivation of corrosion resistant steels2) AMS 5643, Steel b
31、ars, forgings, tubing and rings, corrosion resistant 16.5 Cr, 4.0 Ni, 4.0 Cu2)AMS 5659, Steel, Corrosion Resistant, Bars, Wire, Forgings, Rings, and Extrusions 15Cr 4.5Ni 0.30Cb (Nb) 3.5Cu, Consumable Remelted, Precipitation Hardenable2)AMS 5731, Steel bars, forgings, tubing and rings, corrosion and
32、 heat resistant 15Cr-25.5Ni-1.2Mo-2.1Ti-0.006B-0.30V solution heat treated2)AMS 5732, Steel bars, wire, forgings, tubing and rings, corrosion and heat resistant 15Cr-25.5Ni-1.2Mo-2.1Ti-0.006B-0.30V consumable electrode melted, 1800F (982C), solution and precipitation heat treated2)AMS 5734, Steel ba
33、rs, forgings and tubing, corrosion and heat resistant 15Cr-25.5Ni-1.2Mo-2.1Ti-0.006B-0.30V consumable electrode melted, 1650F (900C), solution and heat treated2)AMS 5737, Steel, corrosion and heat resistant, bars, wire, forgings, and tubing, and rings 15Cr-25.5Ni-1.2Mo-2.1Ti-0.006B-0.30V Consumable
34、electrode melted, 1650F (899C), solution and precipitation heat treated2)AMS 5743, Steel corrosion and heat resistant, bars, and forging2)AMS-QQ-A-225/9, Aluminium alloy bar, rod, wire and special shapes, rolled, drawn or cold finished, 70752)AS 5620, Titanium Hydraulic Tubing , Ti-3Al-2.5V Cold Wor
35、ked and stress Relieved, Up to 35000kPa (5080psi), Requirements for Qualification, Testing and Control2) 2)Published by: SAE International (www.sae.org). prEN 4832:2017 (E) 7 3 Technical Requirements 3.1 System Description 3.1.1 Hydraulic pressures 3.1.1.1 High pressure lines Nominal pressure: 35 00
36、0 kPa (5 080 psi) Maximum pressure: 42 000 kPa (6 091 psi) relief valve setting Intermediate pressure: 450 kPa (65 psi) hydraulic reservoir pressure Minimum pressure: atmospheric pressure depressurised system 3.1.1.2 Low pressure lines Minimum pressure: atmospheric pressure depressurised system Nomi
37、nal pressure: 6 900 kPa (1 000 psi) up to dash 24 3.1.1.3 Suction Lines Nominal pressure: 1 520 kPa (220 psi) Minimum pressure: 21 kPa absolute (3 psi) pump suction lines 3.1.2 Environmental conditions 3.1.2.1 Hydraulic pressures: Proof pressure: 2 x nominal pressure3)Burst pressure: 4 x nominal pre
38、ssure3)Air ambient temperature (outside engine and nacelle area) Normal operating conditions: -40 C to +94 C (-40 F to +201 F) Extreme operating conditions: -54 C to +135 C (-65 F to +275 F) Storage conditions: -54 C to +85 C (-65 F to +185 F) Survival conditions: -60 C to +135 C (-76 F to +275 F) A
39、ir ambient temperature in engine and nacelle area Normal operating conditions: -40 C to +170 C (-40 F to +338 F) Extreme operating conditions: -54 C to +200 C (-65 F to +392 F) Storage conditions: -54 C to +85 C (-65 F to +185 F) Survival conditions: -60 C to +200 C (-76 F to +392 F) 3)Nominal press
40、ure according to 3.1.1.1 High pressure lines. prEN 4832:2017 (E) 8 Hydraulic fluid temperature (outside engine and nacelle area) Normal operating conditions: -40 C to +110 C (-40 F to +230 F) Extreme operating conditions: -54 C to +135 C (-65 F to +275 F) Storage conditions: -54 C to +85 C (-65 F to
41、 +185 F) Survival conditions: -60 C to +135 C (-76 F to +275 F) Hydraulic fluid temperature in engine and nacelle area Normal operating conditions: -40 C to +120 C (-40 F to +248 F) Extreme operating conditions: -54 C to +135 C (-65 F to +275 F) Storage conditions: -54 C to +85 C (-65 F to +185 F) S
42、urvival conditions: -60 C to +150 C (-76 F to +300 F) 3.1.3 Hydraulic architecture See table 1. Table 1 size code of lines High pressure lines 04 06 08 10 12 16 20 Low pressure lines 04 06 08 10 12 16 20 24 Suction lines 08 10 12 16 20 24 32 3.1.4 Hydraulic fluid Type IV or V fire resistant phosphat
43、es ester based fluid in accordance with EN 6102. 3.1.5 Reliability Plug-in unions shall be designed for the aircraft life duration: 140 000 flight hours / 19 000 flight cycles / 25 years, whichever comes first. 3.1.6 Maintainability During the aircraft life, the plug-in unions will not need any main
44、tenance and shall stay without leakage or seepage. The use of “locked” plug-in unions shall be considered in order to: Eliminate the risk of adapter rotation in the port at tubing connection/disconnection (overtightening or loosing) in order to prevent the risk of a port damage or hydraulic leakage;
45、 Enable tubing connection/disconnection with one hand and one tool. prEN 4832:2017 (E) 9 3.1.7 Particular conditions Plug-in unions shall be: electrically conductive; designed to prevent jamming risk; corrosion resistant; galvanic corrosion resistant; designed with parts which cannot be lost during
46、installation and maintenance phases; fire resistant (5 min) or fire proof (15 min), if required; UV resistant. 3.2 Design and construction 3.2.1 Materials and surfaces protection Fittings shall be fabricated of materials listed in table 2 and in compliance with requirements in this specification or
47、as specified on the applicable part standard drawings. Table 2 Plug-in union materials Plug-in union Titanium alloy Ti6Al-4V according to EN 3311 and EN 3314aSteel 17 4 PH according to AMS 5643 Steel 15 5 PH according to AMS 5659 or AMS 5743 Steel A 286 according to AMS 5731 or AMS 5732 or AMS 5734
48、or AMS 5737 Aluminium alloy 7075T73 per AMS-QQ-A-225/9 only for large sizes from 24 to 32 aStandards are equivalent toAMS 4928 or AMS 4965 or AMS 4967.Titanium alloys shall be favoured for weight saving. Magnesium and magnesium alloy shall not be used. All mating surfaces during assembly shall be de
49、fined in order to reduce the friction coefficient as low as possible and not higher than 0,06. The plug-in unions shall be designed to mate with fittings made out of any material specified in table 3. The surfaces of plug-in union parts shall be protected in order to avoid the risk of corrosion, stress corrosion cracks, embrittlement, jamming or galvanic c
