Space product assurance - Material selection for controlling stress-corrosion cracking

This Standard covers the following processes of the general materials, mechanicals parts and processes (MMPP) flow of ECSS-Q-ST-70:
•   The selection of metal alloys for which preference is given to approved data sources (Table 5 1 to Table 5 3)
•   The criticality analysis to determine if a stress corrosion cracking (SCC) evaluation is necessary
This Standard sets forth the criteria to be used in the selection of materials for spacecraft and associated equipment and facilities so that failure resulting from stress-corrosion is prevented.
It is intended to provide general criteria to be used in stress-corrosion cracking control, which begins during design thanks to a methodological material selection.
This document does not intend to include all factors and criteria necessary for the total control of stress­corrosion cracking in all alloys.
The criteria established in this Standard are only applicable to designs for service involving exposure conditions similar to testing conditions
As regards weldments, this Standard is applicable to aluminium alloys, selected stainless steels in the 300 series and alloys listed in Table 5 1.
This Standard is not applicable to listed materials whose behaviour differs at elevated temperature and in specific chemical.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

Raumfahrtproduktsicherung - Kriterien für die Werkstoffwahl zur Vermeidung von Spannungsrisskorrosion

Assurance produit des projets spatiaux - Sélection des matériaux en vue d'éviter leur fissuration par corrosion sous contrainte

La présente norme couvre les processus suivants des flux généraux de matériaux, composants mécaniques et procédés (MMPP) de l'ECSS-Q-ST-70 :
 la sélection des alliages métalliques pour lesquels la préférence est donnée à des sources de données approuvées (Tableau 5-1 à Tableau 5-3) ;
 l'analyse de criticité permettant de déterminer si une évaluation de la fissuration par corrosion sous contrainte (SCC) est nécessaire.
La présente norme détaille les critères à utiliser pour sélectionner les matériaux destinés aux engins spatiaux et aux équipements et installations associés de sorte à éviter toute défaillance due à la corrosion sous contrainte.
Elle vise à fournir les critères généraux à utiliser pour contrôler la fissuration par corrosion sous contrainte, en commençant dès le stade de la conception grâce à une sélection méthodique des matériaux.
Le présent document n'a pas pour but de donner de façon exhaustive tous les facteurs et critères nécessaires pour éviter la fissuration par corrosion sous contrainte chez tous les alliages.
Les critères définis dans la présente norme ne s'appliquent qu'aux conceptions d’équipements destinés à fonctionner dans des conditions d’exposition similaires à celles des conditions d'essai.
En ce qui concerne les ensembles soudés, la présente norme s'applique aux alliages d’aluminium, aux aciers inoxydables choisis dans la série 300 et aux alliages répertoriés dans le Tableau 5-1.

Zagotavljanje varnih proizvodov v vesoljski tehniki - Merila za izbiro materialov za izogibanje stresnim korozijskim razpokam

Ta standard obravnava naslednje procese splošne sheme materialov, mehanskih delov in procesov (MMPP) iz standarda ECSS-Q-ST-70:  • izbiro kovinskih zlitin, kjer imajo prednost odobreni podatkovni viri (preglednica 5.1 do 5.3), • potrebna je analiza kritičnosti za ugotavljanje, ali je potrebna ocena stresnega korozijskega pokanja (SCC). Ta standard določa merila, ki se uporabljajo pri izbiri materialov za vesoljska plovila in povezano opremo ter obrate, da se preprečijo odpovedi zaradi stresne korozije.  Namenjen je zagotavljanju splošnih meril, ki se uporabljajo pri izogibanju stresnim korozijskim razpokam, ki se začne med projektiranjem po zaslugi metodološke izbire materialov.  Ta dokument ne namerava zajeti vseh dejavnikov in meril, potrebnih za popolno izogibanje stresnim korozijskim razpokam v vseh zlitinah.  Merila, določena v tem standardu, se uporabljajo samo za zasnove za uporabo, ki vključuje pogoje izpostavljenosti, podobne preskusnim pogojem. Kar zadeva zvare, se ta standard uporablja za aluminijeve zlitine, izbrana nerjavna jekla iz skupine 300 in zlitine, navedene v preglednici 5.1. Ta standard se ne uporablja za navedene materiale, katerih obnašanje se razlikuje pri povišani temperaturi in v posebni kemikaliji. Ta standard se lahko prilagodi posameznim lastnostim in omejitvam vesoljskega projekta v skladu s standardom ECSS-S-ST-00.

General Information

Status
Published
Public Enquiry End Date
27-Feb-2014
Publication Date
01-Dec-2014
Technical Committee
Current Stage
6060 - National Implementation/Publication (Adopted Project)
Start Date
06-Nov-2014
Due Date
11-Jan-2015
Completion Date
02-Dec-2014

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Standards Content (Sample)

SLOVENSKI STANDARD
SIST EN 16602-70-36:2015
01-januar-2015
1DGRPHãþD
SIST EN 14101:2004
Zagotavljanje varnih proizvodov v vesoljski tehniki - Merila za izbiro materialov za
izogibanje stresnim korozijskim razpokam
Space product assurance - Material selection for controlling stress-corrosion cracking
Raumfahrtproduktsicherung - Kriterien für die Werkstoffwahl zur Vermeidung von
Spannungsrisskorrosion
Assurance produit des projets spatiaux - Sélection des matériaux en vue d'éviter leur
fissuration par corrosion sous contrainte
Ta slovenski standard je istoveten z: EN 16602-70-36:2014
ICS:
49.025.01 Materiali za letalsko in Materials for aerospace
vesoljsko gradnjo na splošno construction in general
49.140 Vesoljski sistemi in operacije Space systems and
operations
77.060 Korozija kovin Corrosion of metals
SIST EN 16602-70-36:2015 en
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.

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SIST EN 16602-70-36:2015

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SIST EN 16602-70-36:2015


EUROPEAN STANDARD
EN 16602-70-36

NORME EUROPÉENNE

EUROPÄISCHE NORM
October 2014
ICS 49.025.01; 49.140 Supersedes EN 14101:2001
English version
Space product assurance - Material selection for controlling
stress-corrosion cracking
Assurance produit des projets spatiaux - Sélection des Raumfahrtproduktsicherung - Kriterien für die
matériaux en vue d'éviter leur fissuration par corrosion sous Werkstoffwahl zur Vermeidung von
contrainte Spannungsrisskorrosion
This European Standard was approved by CEN on 11 April 2014.

CEN and CENELEC members are bound to comply with the 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 Centre or to any CEN and CENELEC
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 and CENELEC member into its own language and notified to the CEN-CENELEC Management Centre
has the same status as the official versions.

CEN and CENELEC members are the national standards bodies and national electrotechnical committees 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, Netherlands, Norway, Poland, Portugal, Romania, Slovakia,
Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom.







CEN-CENELEC Management Centre:
Avenue Marnix 17, B-1000 Brussels
© 2014 CEN/CENELEC All rights of exploitation in any form and by any means reserved Ref. No. EN 16602-70-36:2014 E
worldwide for CEN national Members and for CENELEC
Members.

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SIST EN 16602-70-36:2015
EN 16602-70-36:2014 (E)
Table of contents
Foreword . 5
1 Scope . 6
2 Normative references . 7
3 Terms, definitions and abbreviated terms . 8
3.1 Terms from other standards . 8
3.2 Terms specific to the present standard . 8
3.3 Abbreviated terms. 8
4 Principles . 9
4.1 Stress corrosion . 9
4.2 Evaluation of metal alloys . 9
5 Requirements . 10
5.1 Stress corrosion cracking resistance evaluation of metal alloys . 10
5.1.1 Overview . 10
5.1.2 Requirements for case 1 . 10
5.1.3 Requirements for Case 2 . 11
5.2 Materials selection criteria . 11
5.2.1 General . 11
5.2.2 High SCC resistance alloys . 11
5.2.3 Moderate SCC resistance alloys . 12
5.2.4 Low SCC resistance alloys . 12
5.2.5 Unlisted materials . 13
5.3 Design and assembly . 13
5.4 Customer’s approval . 13
Annex A (normative) Request for SCC resistance evaluation - DRD . 23
A.1 DRD identification . 23
A.1.1 Requirement identification and source document . 23
A.1.2 Purpose and objective . 23
A.2 Expected response . 23
A.2.1 Scope and content . 23
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EN 16602-70-36:2014 (E)
A.2.2 Special remarks . 23
Annex B (normative) SCC resistance test specifications and procedures
(Work Proposal) - DRD . 24
B.1 DRD identification . 24
B.1.1 Requirement identification and source document . 24
B.1.2 Purpose and objective . 24
B.2 Expected response . 24
B.2.1 Scope and content . 24
B.2.2 Special remarks . 24
Annex C (normative) Stress-corrosion evaluation form (SCEF) - DRD . 25
C.1 DRD identification . 25
C.1.1 Requirement identification and source document . 25
C.1.2 Purpose and objective . 25
C.2 Expected response . 25
C.2.1 Scope and content . 25
C.2.2 Special remarks . 29
Annex D (informative) Grain orientation . 31
D.1 Introduction . 31
D.2 Anisotropy of grain orientation . 31
Annex E (informative) SCC resistance of alloys . 35
E.1 Stress corrosion susceptibility . 35
E.2 Metal alloys. 36
E.2.1 Aluminium . 36
E.2.2 Steel . 36
E.2.3 Nickel . 36
E.2.4 Copper . 36
Annex F (informative) Stress sources . 38
F.1 Introduction . 38
F.2 Stress sources . 38
Bibliography . 39

Figures
Figure C-1 : Example of a Stress-corrosion evaluation form . 29
Figure D-1 : Grain orientations in standard wrought forms . 32
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EN 16602-70-36:2014 (E)
Figure D-2 : Examples of tensile stresses in short transverse direction applied
during assembly . 33
Figure D-3 : Examples of tensile stresses in short transverse direction resulting
from assembly . 34
Figure E-1 : Typical residual stress distributions in 7075 Aluminium alloys . 37

Tables
Table 5-1: Alloys with high resistance to stress-corrosion cracking . 14
Table 5-2: Alloys with moderate resistance to stress-corrosion cracking . 18
Table 5-3: Alloys with low resistance to stress-corrosion cracking . 20
Table F-1 : Sources of stress. 38


4

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SIST EN 16602-70-36:2015
EN 16602-70-36:2014 (E)
Foreword
This document (EN 16602-70-36:2014) has been prepared by Technical
Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN.
This standard (EN 16602-70-36:2014) originates from ECSS-Q-ST-70-36C.
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 April 2015,
and conflicting national standards shall be withdrawn at the latest by April
2015.
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 patent rights.
This document supersedes EN 14101:2001.
This document has been prepared under a mandate given to CEN by the
European Commission and the European Free Trade Association.
This document has been developed to cover specifically space systems and has
therefore precedence over any EN covering the same scope but with a wider
domain of applicability (e.g. : aerospace).
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, Former 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.
5

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SIST EN 16602-70-36:2015
EN 16602-70-36:2014 (E)
1
Scope
This Standard covers the following processes of the general materials,
mechanicals parts and processes (MMPP) flow of ECSS-Q-ST-70:
• The selection of metal alloys for which preference is given to approved
data sources (Table 5-1 to Table 5-3)
• The criticality analysis to determine if a stress corrosion cracking (SCC)
evaluation is necessary
This Standard sets forth the criteria to be used in the selection of materials for
spacecraft and associated equipment and facilities so that failure resulting from
stress-corrosion is prevented.
It is intended to provide general criteria to be used in stress-corrosion cracking
control, which begins during design thanks to a methodological material
selection.
This document does not intend to include all factors and criteria necessary for
the total control of stress-corrosion cracking in all alloys.
The criteria established in this Standard are only applicable to designs for
service involving exposure conditions similar to testing conditions
As regards weldments, this Standard is applicable to aluminium alloys, selected
stainless steels in the 300 series and alloys listed in Table 5-1.
This Standard is not applicable to listed materials whose behaviour differs at
elevated temperature and in specific chemical.
This standard may be tailored for the specific characteristic and constrains of a
space project in conformance with ECSS-S-ST-00.
6

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EN 16602-70-36:2014 (E)
2
Normative references
The following normative documents contain provisions which, through
reference in this text, constitute provisions of this ECSS Standard. For dated
references, subsequent amendments to, or revision of any of these publications
do not apply, However, parties to agreements based on this ECSS Standard are
encouraged to investigate the possibility of applying the more recent editions of
the normative documents indicated below. For undated references, the latest
edition of the publication referred to applies.

EN reference Reference in text Title
EN 16601-00-01 ECSS-S-ST-00-01 ECSS system - Glossary of terms
EN 16602-70 ECSS-Q-ST-70 Space product assurance - Materials, mechanical parts
and processes.
EN 16602-70-37 ECSS-Q-ST-70-37 Space product assurance - Determination of the
susceptibility of metals to stress-corrosion cracking.
NASA-MSFC-SPEC Design criteria for controlling stress-corrosion
522B (July 1987) cracking

7

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SIST EN 16602-70-36:2015
EN 16602-70-36:2014 (E)
3
Terms, definitions and abbreviated terms
3.1 Terms from other standards
For the purpose of this Standard, the terms and definitions from ECSS-ST-00-01
and ECSS-Q-ST-70 apply.
3.2 Terms specific to the present standard
3.2.1 stress-corrosion
combined action of sustained tensile stress and corrosion that can lead to the
premature failure of materials
3.3 Abbreviated terms
For the purpose of this Standard, the abbreviated terms from ECSS-S-ST-00-01
and the following apply:

Abbreviation Meaning
stress-corrosion cracking
SCC
stress-corrosion evaluation form
SCEF

8

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EN 16602-70-36:2014 (E)
4
Principles
4.1 Stress corrosion
Certain materials are more susceptible to stress corrosion cracking (SCC) than
others. If a susceptible material is placed in service in a corrosive environment
under tension of sufficient magnitude, and the duration of service is sufficient
to permit the initiation and growth of cracks, failure occurs at a stress lower
than that which the material is normally be expected to withstand. The
corrosive environment need not be severe in terms of general corrosive attack.
NOTE Service failures due to stress-corrosion are
frequently encountered in cases where the
surfaces of the failed parts are not visibly
corroded in a general sense.
Moreover, stresses are additive and threshold stresses for susceptibility are
often low. There have been a number of stress-corrosion failures for which
design stresses were intermittent and of short duration, and only of minor
significance in contributing to failure. Stress-corrosion cracking in those cases
occurred because of a combination of residual and assembly stresses not
anticipated in design.
4.2 Evaluation of metal alloys
Resistance to stress- corrosion cracking of metal alloys depends mainly on
factors:
• Grain orientation (see Annex D)
• Susceptibility to SCC (see Annex E)
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SIST EN 16602-70-36:2015
EN 16602-70-36:2014 (E)
5
Requirements
5.1 Stress corrosion cracking resistance evaluation of
metal alloys
5.1.1 Overview
Clause 5.1.2 lists the requirements applicable for applications involving and
identified as case 1:
• unlisted materials (i.e. materials not listed in tables 1, 2 or 3), or
• combinations of materials and environments outside the scope of this
Standard
Clause 5.1.3 lists the requirements applicable for application involving listed
materials with
• moderate SCC resistance,
• low SCC resistance, or
• moderate or low SCC resistance and coated or plated with materials with
a high SCC resistance.
and identified as case 2.
NOTE The classes for high, moderated and low
resistance to SCC are defined in ECSS-Q-ST-70-37.
5.1.2 Requirements for case 1
a. A request for evaluation shall be established in conformance with the
DRD in Annex A.
b. As a reply to the customer request for SCC evaluation, the supplier shall
provide a work proposal (including test specifications and procedures) in
conformance with the DRD in Annex B.
NOTE An example of approved test specifications and
procedures is ECSS-Q-ST-70-37.
c. The supplier shall perform a detailed evaluation of susceptibility
according to test specifications and procedures approved by the customer
10

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SIST EN 16602-70-36:2015
EN 16602-70-36:2014 (E)
NOTE This is often the case for many applications
involving unfamiliar materials, or unusual
combinations of materials and environments.
d. The results of stress corrosion cracking resistance evaluation shall be
reported in conformance with DRD in Annex A of ECSS-Q-ST-70-37.
e. The SCC test report shall be submitted for customer’s approval before the
material under evaluation is used or incorporated in a design.
5.1.3 Requirements for Case 2
a. The supplier shall provide the SCEF in conformance with the DRD in
Annex C.
5.2 Materials selection criteria
5.2.1 General
a. The supplier shall use in preference high SCC resistance alloys listed in
Table 5-1.
NOTE Selecting an alloy from this table avoid the need
to perform a stress corrosion evaluation
5.2.2 High SCC resistance alloys
5.2.2.1 Surface treated materials
a. Alloys which are surface treated shall be evaluated according to 5.1.3a.
NOTE 1 For example:
• Metals having been treated with surface
treatments such as nitriding and
carburising.
• A low-strength plain carbon steel,
carburised on the surface to a hardness
corresponding to a tensile strength above 1
370 MPa (200 ksi).
NOTE 2 Surface treatment such as nitriding and
carburising can make a stress-corrosion
evaluation necessary for a material not
normally considered susceptible.
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5.2.3 Moderate SCC resistance alloys
5.2.3.1 Coated and plated materials
a. Alloys with moderate SCC resistance and coated or plated with materials
with a high SCC resistance shall be evaluated according to 5.1.3a.
NOTE 1 For example: Even though 2024-T6 aluminium
is anodised, this material has moderate
resistance to stress corrosion.
NOTE 2 All electroplated, anodised and chemical-
conversion coatings on otherwise acceptable
materials are excluded from the requirements
of this specification
5.2.3.2 Thin materials (alloy or temper of metal)
a. Sheet material less than 6,5 mm (0,250 inch) thick of the aluminium alloys
listed in Table 5-2 do not require a SCEF according to Annex C.
b. Alloys used for electrical wiring, thermocouple wires, magnet windings
and similar non-structural electrical applications do not require a SCEF
according to Annex C.
5.2.3.3 Others
a. Alloys and tempers listed in Table 5-2 shall only be considered for use
when a suitable alloy cannot be found in Table 5-1.
b. Materials listed in Table 5-2 shall not be used for applications involving
high installation stress.
NOTE Examples of application involving high stress
are springs or fasteners
5.2.4 Low SCC resistance alloys
a. Alloys and tempers listed in Table 5-3 shall only be considered for use in
applications where the probability of stress-corrosion is remote.
5.2.4.2 Coated and plated materials
a. Alloys with low SCC resistance and coated or plated with materials with
a high SCC resistance shall be evaluated according to 5.1.3a.
NOTE 1 For example: Even 440C stainless steel is
chrome plated, this material has low resistance
to stress corrosion.
NOTE 2 All electroplated, anodised and chemical-
conversion coatings on otherwise acceptable
materials are excluded from the requirements
of this specification
12

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EN 16602-70-36:2014 (E)
5.2.5 Unlisted materials
a. The stress-corrosion resistance of alloys and weldments not listed in this
document shall be ascertained:
1. by means of tests conducted in an environment representative of
the proposed application, or
2. by means of direct comparison with similar alloys and weldments
for which susceptibility is known to be low.
5.3 Design and assembly
a. The directional variation of the alloy shall be considered in the design of
the manufactured product.
NOTE 1 The directional variation can be appreciable
with respect to SCC.
NOTE 2 This is necessary for the evaluation of the
susceptibility to stress corrosion cracking.
b. The supplier shall include both the residual stress distribution and the
grain orientation in designing a part to be machined from wrought
aluminium.
c. During design and assembly, the supplier shall avoid tension which is
applied in transverse directions.
NOTE For example: Figure D-2 and Figure D-3 in
Annex D illustrate undesirable situations.
d. The supplier shall ensure that stress corrosion threshold stresses are not
exceeded by the combination of the following sources of stresses:
1. residual and assembly stress;
2. stresses resulting from operational, transportation and storage
loads;
3. assembly stresses result from improper tolerances during fit-up,
overtorquing, press fits, high-interference fasteners and welding;
NOTE See for examples Figure D-2 and Figure D-3.
4. residual stresses as a result of machining, forming and
heat-treating operations.
5.4 Customer’s approval
a. The customer shall approve the SCEF before any of the following alloy,
temper or weldment can be used or incorporated in a design:
1. coated, plated or surface-treated alloys, and weldments listed in
Table 5-1;
2. any alloys, tempers and weldments listed in Table 5-2;
3. any alloys, tempers and weldments listed in Table 5-3;
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4. any alloys, tempers and weldments not listed in this Standard.
NOTE In special cases where specific data are already
available on a material under environmental
conditions representative of anticipated
exposure, a stress-corrosion evaluation form for
use of this material within prescribed limits can
be submitted for approval.
Table 5-1: Alloys with high resistance to stress-corrosion cracking
(a) Steel Condition
Carbon steel (1000 series) Below 1 225 MPa (180 ksi) UTS
1
Low alloy steel (4130, 4340, etc.) Below 1 225 MPa (180 ksi) UTS
(E) D6AC, H-11 Below 1 450 MPa (210 ksi) UTS
Music wire (ASTM 228) Cold drawn
HY-80 steel Quenched and tempered
HY-130 steel Quenched and tempered
HY-140 steel Quenched and tempered
1095 spring steel Quenched and tempered
2
300 series stainless steel (unsensitized) All
400 series Ferritec stainless steel (404, 430, 431, 444, etc.) All
21-6-9 stainless steel All
Carpenter 20 Cb stainless steel All
Carpenter 20 Cb-3 stainless steel All
A286 stainless steel All
4
AM350 stainless steel SCT 1000 and above
AM355 stainless steel SCT 1000 and above
5
Almar 362 stainless steel H1000 and above
Custom 450 stainless steel H1000 and above
Custom 455 stainless steel H1000 and above
15-5 PH stainless steel H1000 and above
6,7
PH 14-8 Mo stainless steel CH900 and SRH950 and above
PH 15-7 Mo stainless steel CH900
17-7 PH stainless steel CH900
3
Nitronic 33 All
(E) Maraging steel MARVAL X12 All
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EN 16602-70-36:2014 (E)
1. A small number of laboratory failures of specimens cut from plate more than 2 inches thick have been
observed at 75 % yield, even within this ultimate strength range. The use of thick plate should therefore
be avoided in a corrosive environment when sustained tensile stress in the short transverse direction is
expected.
2. Including weldments of 304L, 316L, 321 and 347.
3. Including weldments.
4. SCT 1000 = sub-zero cooling and tempering at 538 °C (1 000 °F).
5. H1000 hardened above 538 °C (1 000°F).
6. CH900 cold worked and aged at 480 °C (900 °F).
7. SRH950 = solution treated and tempered at 510 °C (950 °F).
(E) ESA classification not in NASA MSFC-SPEC-522A.

Table 5-1: Alloys with high resistance to stress-corrosion cracking (cont.)
(b) Nickel Alloy Condition
Hastelloy C All
Hastelloy X All
Incoloy 800 All
Incoloy 901 All
Incoloy 903 All
3
Inconel 600 Annealed
Inconel 625 Annealed
3
Inconel 718 All
Inconel X-750 All
Monel K-500 All
Ni-Span-C 902 All
René 41 All
Unitemp 212 All
Waspaloy All
3. Including weldments

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Table 5-1: Alloys with high resistance to stress-corrosion cracking (cont.)
(c) Aluminium alloys:
1,2
Wrought Cast
3
Alloy Condition Alloy Condition
1000 series All 355.0, C355.0 T6
2011 T8 356.0, A356.0 All
2024, rod bar T8 357.0 All
2219 T6, T8 B358.0 (Tens-50) All
(E) 2419 T8 359.0 All
(E) 2618 T6, T8 380.0, A380.0 As cast
5
3000 series All 514.0 (214) As cast
4,5 5
5000 series All 518.0 (218) As cast
5
6000 series All 535.0 (Almag 35) As cast
6
(E) 7020 T6 A712.0, C712.0 As cast
7049 T73
7149 T73
7050 T73
7075 T73
7475 T73
1. Mechanical stress relieved (TX5X or TX5XX) where possible.
2. Including weldments of the weldable alloys.
3. The former designation is shown in parenthesis when significantly different.
4. High magnesium content alloys 5456, 5083 and 5086 should be used only in controlled
tempers (H111, H112, H116, H117, H323, H343) for resistance to stress-corrosion
cracking and exfoliation.
5. Alloys with magnesium content greater than 3,0 % are not recommended for
high-temperature application, 66 °C (150 °F) and above.
6. Excluding weldments.
(E) ESA classification - not in NASA MSFC-SPEC-522A.

16

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SIST EN 16602-70-36:2015
EN 16602-70-36:2014 (E)
Table 5-1: Alloys with high resistance to stress-corrosion cracking (cont.)
(d) Copper Alloy
1 2
CDA no. Condition (% cold rolled)
110 37
3,4
170 AT, HT

3,4
172 AT, HT
194 37
195 90
230 40
422 37
443 10
510 37
521 37
619 40 (9 % B phase)
619 40 (95 % B phase)
688 40
706 50
725 50, annealed
280, 524, 606, 632, 655, 704, 710 0
715, (E) 917, (E) 937 0
1. Copper Development Association alloy number.
2. Maximum per cent cold rolled for which stress-corrosion-cracking data are available.
3. AT - annealed and precipitation hardened.
4. HT - work hardened and precipitation hardened.
(E) ESA classification not in NASA MSFC-SPEC-522A.

17

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SIST EN 16602-70-36:2015
EN 16602-70-36:2014 (E)
Table 5-1: Alloys with high resistance to stress-corrosion cracking (cont.)
(e) Miscellaneous Alloy (wrought) Condition
Beryllium, S-200C Annealed
HS 25 (L605) All
HS 188 All
MP35N All
Titanium, 3Al-2.5V All
Titanium, 6AI-4V All
Titanium, 13V-11Cr-3AI All
(E) Titanium OMI 685, IMI 829 All
Magnesium, M1A All
...

SLOVENSKI STANDARD
kSIST FprEN 16602-70-36:2014
01-februar-2014
Zagotavljanje varnih proizvodov v vesoljski tehniki - Merila za izbiranje materialov
za izogibanje stresnim korozijskim razpokam
Space product assurance - Material selection for controlling stress-corrosion cracking
Raumfahrtproduktsicherung - Kriterien für die Werkstoffwahl zur Vermeidung von
Spannungsrisskorrosion
Assurance produit des projets spatiaux - Sélection des matériaux en vue d'éviter leur
fissuration par corrosion sous contrainte
Ta slovenski standard je istoveten z: FprEN 16602-70-36
ICS:
49.025.01 Materiali za letalsko in Materials for aerospace
vesoljsko gradnjo na splošno construction in general
49.140 Vesoljski sistemi in operacije Space systems and
operations
77.060 Korozija kovin Corrosion of metals
kSIST FprEN 16602-70-36:2014 en
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.

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kSIST FprEN 16602-70-36:2014

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kSIST FprEN 16602-70-36:2014


EUROPEAN STANDARD
FINAL DRAFT
FprEN 16602-70-36
NORME EUROPÉENNE

EUROPÄISCHE NORM

October 2013
ICS 49.025.01; 49.140 Will supersede EN 14101:2001
English version
Space product assurance - Material selection for controlling
stress-corrosion cracking
Assurance produit des projets spatiaux - Sélection des Raumfahrtproduktsicherung - Kriterien für die
matériaux en vue d'éviter leur fissuration par corrosion sous Werkstoffwahl zur Vermeidung von
contrainte Spannungsrisskorrosion
This draft European Standard is submitted to CEN members for unique acceptance procedure. It has been drawn up by the Technical
Committee CEN/CLC/TC 5.

If this draft becomes a European Standard, CEN and CENELEC members are bound to comply with the CEN/CENELEC Internal
Regulations which stipulate the conditions for giving this European Standard the status of a national standard without any alteration.

This draft European Standard was established by CEN and CENELEC in three official versions (English, French, German). A version in any
other language made by translation under the responsibility of a CEN and CENELEC member into its own language and notified to the
CEN-CENELEC Management Centre has the same status as the official versions.

CEN and CENELEC members are the national standards bodies and national electrotechnical committees 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, Netherlands, Norway, Poland, Portugal, Romania, Slovakia,
Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom.

Recipients of this draft are invited to submit, with their comments, notification of any relevant patent rights of which they are aware and to
provide supporting documentation.

Warning : This document is not a European Standard. It is distributed for review and comments. It is subject to change without notice and
shall not be referred to as a European Standard.



CEN-CENELEC Management Centre:
Avenue Marnix 17, B-1000 Brussels
© 2013 CEN/CENELEC All rights of exploitation in any form and by any means reserved Ref. No. FprEN 16602-70-36:2013 E
worldwide for CEN national Members and for CENELEC
Members.

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kSIST FprEN 16602-70-36:2014
FprEN 16602-70-36:2013 (E)
Table of contents
Foreword . 5
1 Scope . 6
2 Normative references . 7
3 Terms, definitions and abbreviated terms . 8
3.1 Terms from other standards . 8
3.2 Terms specific to the present standard . 8
3.3 Abbreviated terms. 8
4 Principles . 9
4.1 Stress corrosion . 9
4.2 Evaluation of metal alloys . 9
5 Requirements . 10
5.1 Stress corrosion cracking resistance evaluation of metal alloys . 10
5.1.1 Overview . 10
5.1.2 Requirements for case 1 . 10
5.1.3 Requirements for Case 2 . 11
5.2 Materials selection criteria . 11
5.2.1 General . 11
5.2.2 High SCC resistance alloys . 11
5.2.3 Moderate SCC resistance alloys . 12
5.2.4 Low SCC resistance alloys . 12
5.2.5 Unlisted materials . 13
5.3 Design and assembly . 13
5.4 Customer’s approval . 13
Annex A (normative) Request for SCC resistance evaluation - DRD . 23
A.1 DRD identification . 23
A.1.1 Requirement identification and source document . 23
A.1.2 Purpose and objective . 23
A.2 Expected response . 23
A.2.1 Scope and content . 23
2

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kSIST FprEN 16602-70-36:2014
FprEN 16602-70-36:2013 (E)
A.2.2 Special remarks . 23
Annex B (normative) SCC resistance test specifications and procedures
(Work Proposal) - DRD . 24
B.1 DRD identification . 24
B.1.1 Requirement identification and source document . 24
B.1.2 Purpose and objective . 24
B.2 Expected response . 24
B.2.1 Scope and content . 24
B.2.2 Special remarks . 24
Annex C (normative) Stress-corrosion evaluation form (SCEF) - DRD . 25
C.1 DRD identification . 25
C.1.1 Requirement identification and source document . 25
C.1.2 Purpose and objective . 25
C.2 Expected response . 25
C.2.1 Scope and content . 25
C.2.2 Special remarks . 29
Annex D (informative) Grain orientation . 31
D.1 Introduction . 31
D.2 Anisotropy of grain orientation . 31
Annex E (informative) SCC resistance of alloys . 35
E.1 Stress corrosion susceptibility . 35
E.2 Metal alloys. 36
E.2.1 Aluminium . 36
E.2.2 Steel . 36
E.2.3 Nickel . 36
E.2.4 Copper . 36
Annex F (informative) Stress sources . 38
F.1 Introduction . 38
F.2 Stress sources . 38
Bibliography . 39

Figures
Figure C-1 : Example of a Stress-corrosion evaluation form . 29
Figure D-1 : Grain orientations in standard wrought forms . 32
Figure D-2 : Examples of tensile stresses in short transverse direction applied during
assembly . 33
3

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kSIST FprEN 16602-70-36:2014
FprEN 16602-70-36:2013 (E)
Figure D-3 : Examples of tensile stresses in short transverse direction resulting from
assembly . 34
Figure E-1 : Typical residual stress distributions in 7075 Aluminium alloys . 37

Tables
Table 5-1: Alloys with high resistance to stress-corrosion cracking . 14
Table 5-2: Alloys with moderate resistance to stress-corrosion cracking . 18
Table 5-3: Alloys with low resistance to stress-corrosion cracking . 20
Table F-1 : Sources of stress. 38


4

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kSIST FprEN 16602-70-36:2014
FprEN 16602-70-36:2013 (E)
Foreword
This document (FprEN 16602-70-36:2013) has been prepared by Technical
Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN
(Germany).
This document (FprEN 16602-70-36:2013) originates from ECSS-Q-ST-70-36C.
This document is currently submitted to the Unique Acceptance Procedure.
This document will supersede EN 14101:2001.
This document has been developed to cover specifically space systems and will
the-refore have precedence over any EN covering the same scope but with a
wider do-main of applicability (e.g. : aerospace).
5

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kSIST FprEN 16602-70-36:2014
FprEN 16602-70-36:2013 (E)
1
Scope
This Standard covers the following processes of the general materials,
mechanicals parts and processes (MMPP) flow of ECSS-Q-ST-70:
• The selection of metal alloys for which preference is given to approved
data sources (Table 5-1 to Table 5-3)
• The criticality analysis to determine if a stress corrosion cracking (SCC)
evaluation is necessary
This Standard sets forth the criteria to be used in the selection of materials for
spacecraft and associated equipment and facilities so that failure resulting from
stress-corrosion is prevented.
It is intended to provide general criteria to be used in stress-corrosion cracking
control, which begins during design thanks to a methodological material
selection.
This document does not intend to include all factors and criteria necessary for
the total control of stress-corrosion cracking in all alloys.
The criteria established in this Standard are only applicable to designs for
service involving exposure conditions similar to testing conditions
As regards weldments, this Standard is applicable to aluminium alloys, selected
stainless steels in the 300 series and alloys listed in Table 5-1.
This Standard is not applicable to listed materials whose behaviour differs at
elevated temperature and in specific chemical.
This standard may be tailored for the specific characteristic and constrains of a
space project in conformance with ECSS-S-ST-00.
6

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FprEN 16602-70-36:2013 (E)
2
Normative references
The following normative documents contain provisions which, through
reference in this text, constitute provisions of this ECSS Standard. For dated
references, subsequent amendments to, or revision of any of these publications
do not apply, However, parties to agreements based on this ECSS Standard are
encouraged to investigate the possibility of applying the more recent editions of
the normative documents indicated below. For undated references, the latest
edition of the publication referred to applies.

EN reference Reference in text Title
EN 16601-00-01 ECSS-S-ST-00-01 ECSS system - Glossary of terms
EN 16602-70 ECSS-Q-ST-70 Space product assurance - Materials, mechanical parts
and processes.
EN 16602-70-37 ECSS-Q-ST-70-37 Space product assurance - Determination of the
susceptibility of metals to stress-corrosion cracking.
NASA-MSFC-SPEC Design criteria for controlling stress-corrosion
522B (July 1987) cracking

7

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kSIST FprEN 16602-70-36:2014
FprEN 16602-70-36:2013 (E)
3
Terms, definitions and abbreviated terms
3.1 Terms from other standards
For the purpose of this Standard, the terms and definitions from ECSS-ST-00-01
and ECSS-Q-ST-70 apply.
3.2 Terms specific to the present standard
3.2.1 stress-corrosion
combined action of sustained tensile stress and corrosion that can lead to the
premature failure of materials
3.3 Abbreviated terms
For the purpose of this Standard, the abbreviated terms from ECSS-S-ST-00-01
and the following apply:

Abbreviation Meaning
stress-corrosion cracking
SCC
stress-corrosion evaluation form
SCEF

8

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kSIST FprEN 16602-70-36:2014
FprEN 16602-70-36:2013 (E)
4
Principles
4.1 Stress corrosion
Certain materials are more susceptible to stress corrosion cracking (SCC) than
others. If a susceptible material is placed in service in a corrosive environment
under tension of sufficient magnitude, and the duration of service is sufficient
to permit the initiation and growth of cracks, failure occurs at a stress lower
than that which the material is normally be expected to withstand. The
corrosive environment need not be severe in terms of general corrosive attack.
NOTE Service failures due to stress-corrosion are
frequently encountered in cases where the
surfaces of the failed parts are not visibly
corroded in a general sense.
Moreover, stresses are additive and threshold stresses for susceptibility are
often low. There have been a number of stress-corrosion failures for which
design stresses were intermittent and of short duration, and only of minor
significance in contributing to failure. Stress-corrosion cracking in those cases
occurred because of a combination of residual and assembly stresses not
anticipated in design.
4.2 Evaluation of metal alloys
Resistance to stress- corrosion cracking of metal alloys depends mainly on
factors:
• Grain orientation (see Annex D)
• Susceptibility to SCC (see Annex E)
9

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5
Requirements
5.1 Stress corrosion cracking resistance evaluation of
metal alloys
5.1.1 Overview
Clause 5.1.2 lists the requirements applicable for applications involving and
identified as case 1:
• unlisted materials (i.e. materials not listed in tables 1, 2 or 3), or
• combinations of materials and environments outside the scope of this
Standard
Clause 5.1.3 lists the requirements applicable for application involving listed
materials with
• moderate SCC resistance,
• low SCC resistance, or
• moderate or low SCC resistance and coated or plated with materials with
a high SCC resistance.
and identified as case 2.
NOTE The classes for high, moderated and low
resistance to SCC are defined in ECSS-Q-ST-70-37.
5.1.2 Requirements for case 1
a. A request for evaluation shall be established in conformance with the
DRD in Annex A.
b. As a reply to the customer request for SCC evaluation, the supplier shall
provide a work proposal (including test specifications and procedures) in
conformance with the DRD in Annex B.
NOTE An example of approved test specifications and
procedures is ECSS-Q-ST-70-37.
c. The supplier shall perform a detailed evaluation of susceptibility
according to test specifications and procedures approved by the customer
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NOTE This is often the case for many applications
involving unfamiliar materials, or unusual
combinations of materials and environments.
d. The results of stress corrosion cracking resistance evaluation shall be
reported in conformance with DRD in Annex A of ECSS-Q-ST-70-37.
e. The SCC test report shall be submitted for customer’s approval before the
material under evaluation is used or incorporated in a design.
5.1.3 Requirements for Case 2
a. The supplier shall provide the SCEF in conformance with the DRD in
Annex C.
5.2 Materials selection criteria
5.2.1 General
a. The supplier shall use in preference high SCC resistance alloys listed in
Table 5-1.
NOTE Selecting an alloy from this table avoid the need
to perform a stress corrosion evaluation
5.2.2 High SCC resistance alloys
5.2.2.1 Surface treated materials
a. Alloys which are surface treated shall be evaluated according to 5.1.3a.
NOTE 1 For example:
• Metals having been treated with surface
treatments such as nitriding and
carburising.
• A low-strength plain carbon steel,
carburised on the surface to a hardness
corresponding to a tensile strength above 1
370 MPa (200 ksi).
NOTE 2 Surface treatment such as nitriding and
carburising can make a stress-corrosion
evaluation necessary for a material not
normally considered susceptible.
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5.2.3 Moderate SCC resistance alloys
5.2.3.1 Coated and plated materials
a. Alloys with moderate SCC resistance and coated or plated with materials
with a high SCC resistance shall be evaluated according to 5.1.3a.
NOTE 1 For example: Even though 2024-T6 aluminium
is anodised, this material has moderate
resistance to stress corrosion.
NOTE 2 All electroplated, anodised and chemical-
conversion coatings on otherwise acceptable
materials are excluded from the requirements
of this specification
5.2.3.2 Thin materials (alloy or temper of metal)
a. Sheet material less than 6,5 mm (0,250 inch) thick of the aluminium alloys
listed in Table 5-2 do not require a SCEF according to Annex C.
b. Alloys used for electrical wiring, thermocouple wires, magnet windings
and similar non-structural electrical applications do not require a SCEF
according to Annex C.
5.2.3.3 Others
a. Alloys and tempers listed in Table 5-2 shall only be considered for use
when a suitable alloy cannot be found in Table 5-1.
b. Materials listed in Table 5-2 shall not be used for applications involving
high installation stress.
NOTE Examples of application involving high stress
are springs or fasteners
5.2.4 Low SCC resistance alloys
a. Alloys and tempers listed in Table 5-3 shall only be considered for use in
applications where the probability of stress-corrosion is remote.
5.2.4.2 Coated and plated materials
a. Alloys with low SCC resistance and coated or plated with materials with
a high SCC resistance shall be evaluated according to 5.1.3a.
NOTE 1 For example: Even 440C stainless steel is
chrome plated, this material has low resistance
to stress corrosion.
NOTE 2 All electroplated, anodised and chemical-
conversion coatings on otherwise acceptable
materials are excluded from the requirements
of this specification
12

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kSIST FprEN 16602-70-36:2014
FprEN 16602-70-36:2013 (E)
5.2.5 Unlisted materials
a. The stress-corrosion resistance of alloys and weldments not listed in this
document shall be ascertained:
1. by means of tests conducted in an environment representative of
the proposed application, or
2. by means of direct comparison with similar alloys and weldments
for which susceptibility is known to be low.
5.3 Design and assembly
a. The directional variation of the alloy shall be considered in the design of
the manufactured product.
NOTE 1 The directional variation can be appreciable
with respect to SCC.
NOTE 2 This is necessary for the evaluation of the
susceptibility to stress corrosion cracking.
b. The supplier shall include both the residual stress distribution and the
grain orientation in designing a part to be machined from wrought
aluminium.
c. During design and assembly, the supplier shall avoid tension which is
applied in transverse directions.
NOTE For example: Figure D-2 and Figure D-3 in
Annex D illustrate undesirable situations.
d. The supplier shall ensure that stress corrosion threshold stresses are not
exceeded by the combination of the following sources of stresses:
1. residual and assembly stress;
2. stresses resulting from operational, transportation and storage
loads;
3. assembly stresses result from improper tolerances during fit-up,
overtorquing, press fits, high-interference fasteners and welding;
NOTE See for examples Figure D-2 and Figure D-3.
4. residual stresses as a result of machining, forming and
heat-treating operations.
5.4 Customer’s approval
a. The customer shall approve the SCEF before any of the following alloy,
temper or weldment can be used or incorporated in a design:
1. coated, plated or surface-treated alloys, and weldments listed in
Table 5-1;
2. any alloys, tempers and weldments listed in Table 5-2;
3. any alloys, tempers and weldments listed in Table 5-3;
13

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kSIST FprEN 16602-70-36:2014
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4. any alloys, tempers and weldments not listed in this Standard.
NOTE In special cases where specific data are already
available on a material under environmental
conditions representative of anticipated
exposure, a stress-corrosion evaluation form for
use of this material within prescribed limits can
be submitted for approval.
Table 5-1: Alloys with high resistance to stress-corrosion cracking
(a) Steel Condition
Carbon steel (1000 series) Below 1 225 MPa (180 ksi) UTS
1
Low alloy steel (4130, 4340, etc.) Below 1 225 MPa (180 ksi) UTS
(E) D6AC, H-11 Below 1 450 MPa (210 ksi) UTS
Music wire (ASTM 228) Cold drawn
HY-80 steel Quenched and tempered
HY-130 steel Quenched and tempered
HY-140 steel Quenched and tempered
1095 spring steel Quenched and tempered
2
300 series stainless steel (unsensitized) All
400 series Ferritec stainless steel (404, 430, 431, 444, etc.) All
21-6-9 stainless steel All
Carpenter 20 Cb stainless steel All
Carpenter 20 Cb-3 stainless steel All
A286 stainless steel All
4
AM350 stainless steel SCT 1000 and above
AM355 stainless steel SCT 1000 and above
5
Almar 362 stainless steel H1000 and above
Custom 450 stainless steel H1000 and above
Custom 455 stainless steel H1000 and above
15-5 PH stainless steel H1000 and above
6,7
PH 14-8 Mo stainless steel CH900 and SRH950 and above
PH 15-7 Mo stainless steel CH900
17-7 PH stainless steel CH900
3
Nitronic 33 All
(E) Maraging steel MARVAL X12 All
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1. A small number of laboratory failures of specimens cut from plate more than 2 inches thick have been
observed at 75 % yield, even within this ultimate strength range. The use of thick plate should therefore
be avoided in a corrosive environment when sustained tensile stress in the short transverse direction is
expected.
2. Including weldments of 304L, 316L, 321 and 347.
3. Including weldments.
4. SCT 1000 = sub-zero cooling and tempering at 538 °C (1 000 °F).
5. H1000 hardened above 538 °C (1 000°F).
6. CH900 cold worked and aged at 480 °C (900 °F).
7. SRH950 = solution treated and tempered at 510 °C (950 °F).
(E) ESA classification not in NASA MSFC-SPEC-522A.

Table 5-1: Alloys with high resistance to stress-corrosion cracking (cont.)
(b) Nickel Alloy Condition
Hastelloy C All
Hastelloy X All
Incoloy 800 All
Incoloy 901 All
Incoloy 903 All
3
Inconel 600 Annealed
Inconel 625 Annealed
3
Inconel 718 All
Inconel X-750 All
Monel K-500 All
Ni-Span-C 902 All
René 41 All
Unitemp 212 All
Waspaloy All
3. Including weldments

15

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Table 5-1: Alloys with high resistance to stress-corrosion cracking (cont.)
(c) Aluminium alloys:
1,2
Wrought Cast
3
Alloy Condition Alloy Condition
1000 series All 355.0, C355.0 T6
2011 T8 356.0, A356.0 All
2024, rod bar T8 357.0 All
2219 T6, T8 B358.0 (Tens-50) All
(E) 2419 T8 359.0 All
(E) 2618 T6, T8 380.0, A380.0 As cast
5
3000 series All 514.0 (214) As cast
4,5 5
5000 series All 518.0 (218) As cast
5
6000 series All 535.0 (Almag 35) As cast
6
(E) 7020 T6 A712.0, C712.0 As cast
7049 T73
7149 T73
7050 T73
7075 T73
7475 T73
1. Mechanical stress relieved (TX5X or TX5XX) where possible.
2. Including weldments of the weldable alloys.
3. The former designation is shown in parenthesis when significantly different.
4. High magnesium content alloys 5456, 5083 and 5086 should be used only in controlled
tempers (H111, H112, H116, H117, H323, H343) for resistance to stress-corrosion
cracking and exfoliation.
5. Alloys with magnesium content greater than 3,0 % are not recommended for
high-temperature application, 66 °C (150 °F) and above.
6. Excluding weldments.
(E) ESA classification - not in NASA MSFC-SPEC-522A.

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Table 5-1: Alloys with high resistance to stress-corrosion cracking (cont.)
(d) Copper Alloy
1 2
CDA no. Condition (% cold rolled)
110 37
3,4
170 AT, HT

3,4
172 AT, HT
194 37
195 90
230 40
422 37
443 10
510 37
521 37
619 40 (9 % B phase)
619 40 (95 % B phase)
688 40
706 50
725 50, annealed
280, 524, 606, 632, 655, 704, 710 0
715, (E) 917, (E) 937 0
1. Copper Development Association alloy number.
2. Maximum per cent cold rolled for which stress-corrosion-cracking data are available.
3. AT - annealed and precipitation hardened.
4. HT - work hardened and precipitation hardened.
(E) ESA classification not in NASA MSFC-SPEC-522A.

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Table 5-1: Alloys with high resistance to stress-corrosion cracking (cont.)
(e) Miscellaneous Alloy (wrought) Condition
Beryllium, S-200C Annealed
HS 25 (L605) All
HS 188 All
MP35N All
Titanium, 3Al-2.5V All
Titanium, 6AI-4V All
Titanium, 13V-11Cr-3AI All
(E) Titanium OMI 685, IMI 829 All
Magnesium, M1A All
Magnesium, LA141 Stabilised
Magnesium, LAZ933 All
(E) Cast alloy Magnesium ELEKTRON 21 T6
(E) ESA classification not in NASA MSFC-SPEC-522A.

Table 5-2: Alloys with moderate resistance to stress-corrosion cracking
(a) Steel Alloy Condition
Carbon steel (1000 series) 1 225 to 1 370 MPa
Low-alloy steel (4130, 4340, etc.) 1 225 to 1 370 MPa
Nitronic 32 All
Nitronic 60 All
403, 410, 416, 431 stainless steel (see footnote 1)
PH 13-8 Mo stainless stee
...

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