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Comparative/similar specifications

UKUSAGermanyFranceEuropeRelated SpecificationsAlloyManufacturers SpecificationsCompany
BS S510W.-Nr. 1.1151MSRR 6057Rolls-Royce
BS S511MSRR 6058Rolls-Royce
BS S514/W.-Nr. 1.1169
BS S524/AMS 5689WL 1.4544/Z10CNT18-11EN 3488MSRR 6565Rolls-Royce
BS S527AMS 5512WL 1.4544/EN 3488MSRR 6523Rolls-Royce
BS S529AMS 5529WL 1.4564
BS S530MSRR 6579Rolls-Royce
BS S532MSRR 6628Rolls-Royce
BS S533
BS S538AMS 5719WL 1.4939Z12CNDV12MSRR 6504Rolls-Royce
MSRR 6514Rolls-Royce
WL 1.773415CDV6ASNA 3100Airbus
15CDV6ASNA 3102Airbus
CCT LA 071Turbomeca
AMS 5510WL 1.4544/Z6CNT1810EN 3488ASNA 3106Airbus
1.4541
AMS 5862W.-Nr. 1.454213-8 Mo
AMS 563915-5 PH
AMS 552517-4 PH
W.-Nr. 1.454117-7 PH
BS S528AMS 5528WL 1.4564EN 2540MIL-S-2504317-7 PH
AMS 5517W.-Nr. 1.4310MIL-S-5059301 1/2 H
AMS 5516301 1/4 H
AMS 5518W.-Nr. 1.4310MIL-S-5059301 FH
AMS 5513W.-Nr. 1.4301302
AMS 5604WL 1.4548304
AMS 5511W.-Nr. 1.4307304Airbus
Z6CNT18304LDMD 276-23Snecma
S515321
321CCT LA 081Turbomeca
S5261.4541347
BS S5344130
AMS 6345W.-Nr. 1.7216MIL-S-187294130 ann.
AMS 58644130 norm.
AMS 5519W.-Nr. 1.4310MIL-S-5059A286

Comparative/similar specifications

UKUSAGermanyFranceEuropeRelated SpecificationsAlloyManufacturers SpecificationsCompany
BS S510W.-Nr. 1.1151MSRR 6057Rolls-Royce
BS S511MSRR 6058Rolls-Royce
BS S514/W.-Nr. 1.1169
BS S524/AMS 5689WL 1.4544/Z10CNT18-11EN 3488MSRR 6565Rolls-Royce
BS S527AMS 5512WL 1.4544/EN 3488MSRR 6523Rolls-Royce
BS S529AMS 5529WL 1.4564
BS S530MSRR 6579Rolls-Royce
BS S532MSRR 6628Rolls-Royce
BS S533
BS S538AMS 5719WL 1.4939Z12CNDV12MSRR 6504Rolls-Royce
MSRR 6514Rolls-Royce
WL 1.773415CDV6ASNA 3100Airbus
15CDV6ASNA 3102Airbus
CCT LA 071Turbomeca
AMS 5510WL 1.4544/Z6CNT1810EN 3488ASNA 3106Airbus
1.4541
AMS 5862W.-Nr. 1.454213-8 Mo
AMS 563915-5 PH
AMS 552517-4 PH
W.-Nr. 1.454117-7 PH
BS S528AMS 5528WL 1.4564EN 2540MIL-S-2504317-7 PH
AMS 5517W.-Nr. 1.4310MIL-S-5059301 1/2 H
AMS 5516301 1/4 H
AMS 5518W.-Nr. 1.4310MIL-S-5059301 FH
AMS 5513W.-Nr. 1.4301302
AMS 5604WL 1.4548304
AMS 5511W.-Nr. 1.4307304Airbus
Z6CNT18304LDMD 276-23Snecma
S515321
321CCT LA 081Turbomeca
S5261.4541347
BS S5344130
AMS 6345W.-Nr. 1.7216MIL-S-187294130 ann.
AMS 58644130 norm.
AMS 5519W.-Nr. 1.4310MIL-S-5059A286

Standards and specifications by country

SpecificationAlloyCompany
Europe
EN 3488Rolls-Royce
EN 3488Rolls-Royce
EN 3488Airbus
EN 254017-7 PH
France
Z10CNT18-11Rolls-Royce
Z12CNDV12Rolls-Royce
15CDV6Airbus
15CDV6Airbus
Z6CNT1810Airbus
Z6CNT18304LSnecma
25CD4SJethete M-152
Germany
W.-Nr. 1.1151Rolls-Royce
W.-Nr. 1.1169
WL 1.4544/Rolls-Royce
WL 1.4544/Rolls-Royce
WL 1.4564
WL 1.4939Rolls-Royce
WL 1.7734Airbus
WL 1.4544/Airbus
1.4541
W.-Nr. 1.454213-8 Mo
W.-Nr. 1.454117-7 PH
WL 1.456417-7 PH
W.-Nr. 1.4310301 1/2 H
W.-Nr. 1.4310301 FH
W.-Nr. 1.4301302
W.-Nr. 1.4307304Airbus
WL 1.4548304
1.4541347
W.-Nr. 1.72164130 ann.
W.-Nr. 1.4310A286
WL 1.7214Jethete M-152
UK
BS S510Rolls-Royce
BS S511Rolls-Royce
BS S514/
BS S524/Rolls-Royce
BS S527Rolls-Royce
BS S529
BS S530Rolls-Royce
BS S532Rolls-Royce
BS S533
BS S538Rolls-Royce
BS S52817-7 PH
S515321
S526347
BS S5344130
BS S535Jethete M-152
USA
AMS 5689Rolls-Royce
AMS 5512Rolls-Royce
AMS 5529
AMS 5719Rolls-Royce
AMS 5510Airbus
AMS 586213-8 Mo
AMS 563915-5 PH
AMS 552517-4 PH
AMS 552817-7 PH
AMS 5517301 1/2 H
AMS 5516301 1/4 H
AMS 5518301 FH
AMS 5513302
AMS 5511304Airbus
AMS 5604304
AMS 63454130 ann.
AMS 58644130 norm.
AMS 5519A286

Standards and specifications by country

SpecificationAlloyCompany
Europe
EN 3488Rolls-Royce
EN 3488Rolls-Royce
EN 3488Airbus
EN 254017-7 PH
France
Z10CNT18-11Rolls-Royce
Z12CNDV12Rolls-Royce
15CDV6Airbus
15CDV6Airbus
Z6CNT1810Airbus
Z6CNT18304LSnecma
25CD4SJethete M-152
Germany
W.-Nr. 1.1151Rolls-Royce
W.-Nr. 1.1169
WL 1.4544/Rolls-Royce
WL 1.4544/Rolls-Royce
WL 1.4564
WL 1.4939Rolls-Royce
WL 1.7734Airbus
WL 1.4544/Airbus
1.4541
W.-Nr. 1.454213-8 Mo
W.-Nr. 1.454117-7 PH
WL 1.456417-7 PH
W.-Nr. 1.4310301 1/2 H
W.-Nr. 1.4310301 FH
W.-Nr. 1.4301302
W.-Nr. 1.4307304Airbus
WL 1.4548304
1.4541347
W.-Nr. 1.72164130 ann.
W.-Nr. 1.4310A286
WL 1.7214Jethete M-152
UK
BS S510Rolls-Royce
BS S511Rolls-Royce
BS S514/
BS S524/Rolls-Royce
BS S527Rolls-Royce
BS S529
BS S530Rolls-Royce
BS S532Rolls-Royce
BS S533
BS S538Rolls-Royce
BS S52817-7 PH
S515321
S526347
BS S5344130
BS S535Jethete M-152
USA
AMS 5689Rolls-Royce
AMS 5512Rolls-Royce
AMS 5529
AMS 5719Rolls-Royce
AMS 5510Airbus
AMS 586213-8 Mo
AMS 563915-5 PH
AMS 552517-4 PH
AMS 552817-7 PH
AMS 5517301 1/2 H
AMS 5516301 1/4 H
AMS 5518301 FH
AMS 5513302
AMS 5511304Airbus
AMS 5604304
AMS 63454130 ann.
AMS 58644130 norm.
AMS 5519A286

Standards and specifications by company

SpecificationAlloyCountry
Airbus
ASNA 3100Germany
ASNA 3102France
ASNA 3106USA
304USA
Rolls-Royce
MSRR 6057UK
MSRR 6058UK
MSRR 6565UK
MSRR 6523UK
MSRR 6579UK
MSRR 6628UK
MSRR 6504UK
MSRR 6514UK
Snecma
DMD 276-23304LFrance
Turbomeca
CCT LA 071France
CCT LA 081321France

Standards and specifications by company

SpecificationAlloyCountry
Airbus
ASNA 3100Germany
ASNA 3102France
ASNA 3106USA
304USA
Rolls-Royce
MSRR 6057UK
MSRR 6058UK
MSRR 6565UK
MSRR 6523UK
MSRR 6579UK
MSRR 6628UK
MSRR 6504UK
MSRR 6514UK
Snecma
DMD 276-23304LFrance
Turbomeca
CCT LA 071France
CCT LA 081321France
AMSSpecifications
2300Premium Aircraft-Quality Magnetic Particle Inspection Procedure
2301Aircraft Quality Magnetic Particle Inspection Procedure
2303Aircraft Quality Martensitic Corrosion-Resistant Steels, Magnetic Particle Inspection Procedure
5010C-1215
5022C-1117
5024C-1137
5062C-1018
5069C-1018
5510321, sheet
5517301 1/4 H, sheet
5518302 1/2 H, sheet
552817-7PH, sheet
5525A-286, sheet
5610416 Condition A
5612410 Condition A
5613410 Condition A
5616418 (Greek Ascology) Condition A
5617Custom 455 (12-9-2)
5618440C Vac. Melt (Except Phos Content)
5620420F Condition A
5621420 Condition A
5627430 Condition A
5628431 Condition A
5629PH 13-8 MO
5630440C Condition A
5631440A Condition A
5632440F Se (Type 2)
5637302 Condition B (High Tensile Strength)
5639304 Condition A
5640303
5641303 Selenium Condition A
564317-4 PH Condition A
564417-4 PH Condition A
5645321 Condition A
5646347 Condition A
5647304L Condition A
5648316L Condition A
5650309 Condition A
5651310 Condition A
5653316L Condition A
5656Nironic 40 (21-6-9)
565715-7
565915-5 PH Condition A
5726A-286 (Cap 210 ksi) cold reduced (chem only)
5731A-286 (1800 °F/ 982 °C Solution Heat Treated, 1 hour)
5732A-286 (1800 °F/ 982 °C Solution Heat Treated and Aged)
5734A-286 (1800 °F/ 982 °C Solution Heat Treated, 1 hour)
5735Superseded by AMS-5732
5736Superseded by AMS-5731
5737A-286 Solution Treated (1650 °F / 899 °C) and Aged
5738303F High Yield Strength
5743AM-355
5764Nitronic 50 (XM-19) (22-13-5)
5848Nitronic 60
5853A-286
6260E-9310
6265E-9310 Vacuum Melt
6267E-9310 Vacuum Melt
6294E-4620
6304E-17-22A
6322E-8740
6348E-4130
6349E-4140
6370E-4130
6382E-4140
6411E-4330 Modified (Vacuum Melt)
6414E-4340 Vacuum Melt
6415E-4340
6416300M (Obsolete - use AMS 6419)
6417E-4340 Modified (Vacuum Melt)
6418Hy-Tuf
6419300M Vacuum Melt
6427E-4330 Modified
6431D6AC Vacuum Melt
6440E-52100
6444E-52100 Vacuum Melt
6448E-6150
6470E-135 Modified (Nitriding)
6471E-135 Modified (Nitriding) Vacuum Melt
6472E-135 Modified (Nitriding Comp A)
6485H-11
6487H-11 (Vacuum Melt)
6488H-11 (Vacuum Melt)
6490M-50 (Tool Steel)
6515Maraging (Grade 300)
6526HP 9-4-30
7727Kovar
AMSSpecifications
2300Premium Aircraft-Quality Magnetic Particle Inspection Procedure
2301Aircraft Quality Magnetic Particle Inspection Procedure
2303Aircraft Quality Martensitic Corrosion-Resistant Steels, Magnetic Particle Inspection Procedure
5010C-1215
5022C-1117
5024C-1137
5062C-1018
5069C-1018
5510321, sheet
5517301 1/4 H, sheet
5518302 1/2 H, sheet
552817-7PH, sheet
5525A-286, sheet
5610416 Condition A
5612410 Condition A
5613410 Condition A
5616418 (Greek Ascology) Condition A
5617Custom 455 (12-9-2)
5618440C Vac. Melt (Except Phos Content)
5620420F Condition A
5621420 Condition A
5627430 Condition A
5628431 Condition A
5629PH 13-8 MO
5630440C Condition A
5631440A Condition A
5632440F Se (Type 2)
5637302 Condition B (High Tensile Strength)
5639304 Condition A
5640303
5641303 Selenium Condition A
564317-4 PH Condition A
564417-4 PH Condition A
5645321 Condition A
5646347 Condition A
5647304L Condition A
5648316L Condition A
5650309 Condition A
5651310 Condition A
5653316L Condition A
5656Nironic 40 (21-6-9)
565715-7
565915-5 PH Condition A
5726A-286 (Cap 210 ksi) cold reduced (chem only)
5731A-286 (1800 °F/ 982 °C Solution Heat Treated, 1 hour)
5732A-286 (1800 °F/ 982 °C Solution Heat Treated and Aged)
5734A-286 (1800 °F/ 982 °C Solution Heat Treated, 1 hour)
5735Superseded by AMS-5732
5736Superseded by AMS-5731
5737A-286 Solution Treated (1650 °F / 899 °C) and Aged
5738303F High Yield Strength
5743AM-355
5764Nitronic 50 (XM-19) (22-13-5)
5848Nitronic 60
5853A-286
6260E-9310
6265E-9310 Vacuum Melt
6267E-9310 Vacuum Melt
6294E-4620
6304E-17-22A
6322E-8740
6348E-4130
6349E-4140
6370E-4130
6382E-4140
6411E-4330 Modified (Vacuum Melt)
6414E-4340 Vacuum Melt
6415E-4340
6416300M (Obsolete - use AMS 6419)
6417E-4340 Modified (Vacuum Melt)
6418Hy-Tuf
6419300M Vacuum Melt
6427E-4330 Modified
6431D6AC Vacuum Melt
6440E-52100
6444E-52100 Vacuum Melt
6448E-6150
6470E-135 Modified (Nitriding)
6471E-135 Modified (Nitriding) Vacuum Melt
6472E-135 Modified (Nitriding Comp A)
6485H-11
6487H-11 (Vacuum Melt)
6488H-11 (Vacuum Melt)
6490M-50 (Tool Steel)
6515Maraging (Grade 300)
6526HP 9-4-30
7727Kovar
Specifications
Airesearch
EMS-537A416H.T. (125 KSI Min.)
EMS-626AE-4130 H.T. (125 KSI Min.)
EMS-630AC-1144 (Stressproof)
EMS-641E-4340 Vac. Melt (Ariz. & Tor.)
EMS-642H-11
EMS-648AC-12L14-Ledloy "A"
EMS-55443AM-355 (Ariz. Div.)
EMS-562809310N & TV.M.
EMS-56276E-4330 Mod V.M. (Ariz. Div.)
EMS-56277E-4340 Mod V.M. (Ariz. Div.)
EMS-96242E-4330 Mod V.M. (Tor. Div.)
EMS-96244E-4340 Mod V.M. (Tor. Div.) 
(Use AMS-6417)
Bell
BPS 299-947-032E-9310 V.M.
BPS 299-947-055E-4340 V.M.
Bendix
CE-0896E-4340 Mod V.M.
CE-0906E-4330 Mod V.M.
BEMS-25003D(LA. DIV.) 440 Vac. Melt
Boeing
BMS 7-26E4340 Mod Vac. Melt N & T "300M" Class 1
BMS 7-27E-4330 Mod N & T Hi Transverse
BMS 7-28E-4340 V.M. E-4340
BMS 7-122E-4330 Mod V.M.
BMS 7-182HP9-4-30 (Types 11)
BMS 7-18521-6-9
BMS 7-249E9130 V.M.
General Dynamics
FMS-013117-4 PH
FMS-1011D6-AC V.M.
FMS-1012E4330 Mod V.M.
General Electric
B50-A-436-CAlloy "X" Sheet
B50-A-714AS-1X-750 Sheet
B50-TF-14A718 Sheet
B50-TF-15-AS718 Sol Tr (1750°)
B50-TF-25Alloy "X" Sheet
B50-TF-59Unitemp * "188" Sheet
B50-T-12AA-286 Sheet
B50-T12CA-286 Sheet
B50-T-26-S7L-605
B50-T-69A718 Sol Tr (AMS-5662)
B50-T-83AAlloy "X" Sheet
B50-T-1181CA-286 Sheet
B50-YP-44B-1-Rev.5X-750
C50-TF-13718 Sol Tr/Cold Reduced
Grumman Aircraft
GM-1010E-4330 Mod V.M.
GM-1012E-4340 Mod V.M.
GM-1013E-D6AC V.M.
Hughes Aircraft
HMS-6-1404Type 2 Class 1 (V.M.) Maraging 300
HMS-6-1105PH 13-8 MO
HMS-6-11214340 TYPE
Kaynar
MS-103 E-17-22Ann
Lockheed
LC05-1190 (CA. Co)300M V.M. (4340 Mod V.M.)
LCM05-2190D6AC (V.M.)
STM05-500 (Georgia)D6AC (V.M.)
STM05-501 (Georgia)300M V.M.
(4340 Mod V.M.)
(Reference MILS-8844 CL3)
STM05-602 (Georgia)PH 13-8 MO
McDonnell Douglas
DMS-1555E-4340 V.M.
DMS-1565431 Stainless Steel
DMS-1612410 Stainless Steel (Superseded by AMS-5612)
DMS-1662H-11 High Temp Alloy
DMS-176417-4 PH (use AMS 5643)
DMS-1841Hy-Tuf (GRB) A.Q. Alloy
Hy-Tuf V.M. (GR A)
DMS-1875718 Sol TR 
(Superseded by AMS-5662)
DMS-1893Custom 455
DMS-1935300 M V.M. (4340 Mod)
DMS-2050304-L Cond A
DMS-2100PH 13-8 MO Stainless Steel
MMS-260 (St. Louis)H-11 V.M. High Temp Alloy
MMS-265 (St. Louis)303 Sel. Cond. B
MMS-2102 (St. Louis)HP-9-4-30
Rockwell
ABO 170-014 (Autonetics)4750
HBO 160-001 (L.A. Div.)H-11 High Temp Alloy
LBO-160-133 (L.A. Div.)17-4 PH
LBO-160-164 (L.A. div.)18-9-5 Maraging (300 Grade)
LBO-160-170 (L.A. Div.)4340 Hi T.V.
LBO-160-151 (L.A. Div.)440-C Vac. Melt (Superseded by RBO-160-064)
MBO-160-003 (Downey Div.)17-4PH
MBO-160-006 (Downey Div.)8-9-6 Maraging (300 Grade)
MBO-160-029 (Downey Div.)A-286 Age Hard V.M.
MBO-160-034 (Downey Div.)304-L Vac. Melt
MBO-160-036 (Downey Div.)15-5 PH
MBO-160-037 (Downey Div.)304-L Vac. Velt
MBO-170-041 (Downey Div.)718 Sol Tr 1875° - 1950° (AMS-5664)
MBO-170-075 (Downey Div.)718 Sol Tr 1900° (AMS-5662)
MBO-170-076 (Downey Div.)718 Sol Tr 1875°m - 1950° (AMS-5664)
RBO-170-101 (Rocketdyne)718 Sol Tr 1875° - 1950° (AMS-5662)
RBO-170-153 (Rocketdyne)718 Sol Tr 1900° (AMS-5662)
STO-160LB0012 (Corporate)9-4-30 Vac. Melt
Standard Pressed Steel
SPS-M-118A-286 15% Cold Reduced
SPS-M-175Waspaloy Cold Reduced
SPS-M-250A-286 (Cap. 200KSI) Cold Reduced
SPS-M-275718 Sol Tr 1750° (AMS-5662)
SPS-M-646MP35N
Voi Shan
VS-286T-116A-286 (Cap. 220KSI) Cold Reduced
Specifications
Airesearch
EMS-537A416H.T. (125 KSI Min.)
EMS-626AE-4130 H.T. (125 KSI Min.)
EMS-630AC-1144 (Stressproof)
EMS-641E-4340 Vac. Melt (Ariz. & Tor.)
EMS-642H-11
EMS-648AC-12L14-Ledloy "A"
EMS-55443AM-355 (Ariz. Div.)
EMS-562809310N & TV.M.
EMS-56276E-4330 Mod V.M. (Ariz. Div.)
EMS-56277E-4340 Mod V.M. (Ariz. Div.)
EMS-96242E-4330 Mod V.M. (Tor. Div.)
EMS-96244E-4340 Mod V.M. (Tor. Div.) 
(Use AMS-6417)
Bell
BPS 299-947-032E-9310 V.M.
BPS 299-947-055E-4340 V.M.
Bendix
CE-0896E-4340 Mod V.M.
CE-0906E-4330 Mod V.M.
BEMS-25003D(LA. DIV.) 440 Vac. Melt
Boeing
BMS 7-26E4340 Mod Vac. Melt N & T "300M" Class 1
BMS 7-27E-4330 Mod N & T Hi Transverse
BMS 7-28E-4340 V.M. E-4340
BMS 7-122E-4330 Mod V.M.
BMS 7-182HP9-4-30 (Types 11)
BMS 7-18521-6-9
BMS 7-249E9130 V.M.
General Dynamics
FMS-013117-4 PH
FMS-1011D6-AC V.M.
FMS-1012E4330 Mod V.M.
General Electric
B50-A-436-CAlloy "X" Sheet
B50-A-714AS-1X-750 Sheet
B50-TF-14A718 Sheet
B50-TF-15-AS718 Sol Tr (1750°)
B50-TF-25Alloy "X" Sheet
B50-TF-59Unitemp * "188" Sheet
B50-T-12AA-286 Sheet
B50-T12CA-286 Sheet
B50-T-26-S7L-605
B50-T-69A718 Sol Tr (AMS-5662)
B50-T-83AAlloy "X" Sheet
B50-T-1181CA-286 Sheet
B50-YP-44B-1-Rev.5X-750
C50-TF-13718 Sol Tr/Cold Reduced
Grumman Aircraft
GM-1010E-4330 Mod V.M.
GM-1012E-4340 Mod V.M.
GM-1013E-D6AC V.M.
Hughes Aircraft
HMS-6-1404Type 2 Class 1 (V.M.) Maraging 300
HMS-6-1105PH 13-8 MO
HMS-6-11214340 TYPE
Kaynar
MS-103 E-17-22Ann
Lockheed
LC05-1190 (CA. Co)300M V.M. (4340 Mod V.M.)
LCM05-2190D6AC (V.M.)
STM05-500 (Georgia)D6AC (V.M.)
STM05-501 (Georgia)300M V.M.
(4340 Mod V.M.)
(Reference MILS-8844 CL3)
STM05-602 (Georgia)PH 13-8 MO
McDonnell Douglas
DMS-1555E-4340 V.M.
DMS-1565431 Stainless Steel
DMS-1612410 Stainless Steel (Superseded by AMS-5612)
DMS-1662H-11 High Temp Alloy
DMS-176417-4 PH (use AMS 5643)
DMS-1841Hy-Tuf (GRB) A.Q. Alloy
Hy-Tuf V.M. (GR A)
DMS-1875718 Sol TR 
(Superseded by AMS-5662)
DMS-1893Custom 455
DMS-1935300 M V.M. (4340 Mod)
DMS-2050304-L Cond A
DMS-2100PH 13-8 MO Stainless Steel
MMS-260 (St. Louis)H-11 V.M. High Temp Alloy
MMS-265 (St. Louis)303 Sel. Cond. B
MMS-2102 (St. Louis)HP-9-4-30
Rockwell
ABO 170-014 (Autonetics)4750
HBO 160-001 (L.A. Div.)H-11 High Temp Alloy
LBO-160-133 (L.A. Div.)17-4 PH
LBO-160-164 (L.A. div.)18-9-5 Maraging (300 Grade)
LBO-160-170 (L.A. Div.)4340 Hi T.V.
LBO-160-151 (L.A. Div.)440-C Vac. Melt (Superseded by RBO-160-064)
MBO-160-003 (Downey Div.)17-4PH
MBO-160-006 (Downey Div.)8-9-6 Maraging (300 Grade)
MBO-160-029 (Downey Div.)A-286 Age Hard V.M.
MBO-160-034 (Downey Div.)304-L Vac. Melt
MBO-160-036 (Downey Div.)15-5 PH
MBO-160-037 (Downey Div.)304-L Vac. Velt
MBO-170-041 (Downey Div.)718 Sol Tr 1875° - 1950° (AMS-5664)
MBO-170-075 (Downey Div.)718 Sol Tr 1900° (AMS-5662)
MBO-170-076 (Downey Div.)718 Sol Tr 1875°m - 1950° (AMS-5664)
RBO-170-101 (Rocketdyne)718 Sol Tr 1875° - 1950° (AMS-5662)
RBO-170-153 (Rocketdyne)718 Sol Tr 1900° (AMS-5662)
STO-160LB0012 (Corporate)9-4-30 Vac. Melt
Standard Pressed Steel
SPS-M-118A-286 15% Cold Reduced
SPS-M-175Waspaloy Cold Reduced
SPS-M-250A-286 (Cap. 200KSI) Cold Reduced
SPS-M-275718 Sol Tr 1750° (AMS-5662)
SPS-M-646MP35N
Voi Shan
VS-286T-116A-286 (Cap. 220KSI) Cold Reduced

Metallurgy and specifications

Steel is defined as a material with a mass content of iron larger than the content of any other chemical element, and with a carbon content of usually less than two percent.

Different grades of steel are achieved by adding other alloying elements, such as manganese, nickel, chrome, titanium and molybdenum to the basic mix. By adding these alloys in varying quantities different grades of steel can be achieved that fulfil different needs. Also, most steel alloys can, after manufacture, be heat treated to various conditions to fulfil different applications.

Steel can be categorised into three basic groups:

  • Non-alloyed steel
  • Alloy steel
  • Stainless steel

Non-alloyed steel – The basic steel with no significant amounts of alloy deliberately added.

Alloy steel – The basic steel with some alloying elements added. The most important alloying elements include Aluminum (AI), Boron (B), Cobalt (Co), Chromium (Cr), Copper (Cu), Manganese (Mn), Molybdenum (Mo), Niobium (Nb), Nickel (Ni), Phosphorus (P), Lead (Pb), Sulphur (S), Silicon (Si), Titanium (Ti), Vanadium (V), Tungsten (W).

Stainless steel – Stainless steels contain a mass fraction of at least 10.5 % chromium and a maximum of 1.2 % carbon. Other important alloying elements include Ni, Mo, Cu and many others, depending on the desired properties and application. Usually steels that do not form rust in the natural environment are named stainless steels. The most important group within the stainless steels are the austenitic stainless steels, which contain a minimum of 18 % chromium and 8 % nickel. Austenitic stainless steels are not magnetisable. Due to the austenitic structure they show a good ductility, and at low temperatures are very cold formable and show good weldability.

Effect of alloying elements in steel

The properties of steel can be widely influenced by alloying elements and heat treatment conditions. The most important element besides iron is carbon. The carbon is essential in steels which are to be hardened by quenching and tempering. The hardness of steel, as with all steel groups, is directly related to the amount of carbon alloyed.

Some alloying elements are of importance for the production of steel during melting, especially aluminum and silicon.

Aluminum is besides silicon, the most important deoxidising agent. In deoxidised steel the aluminum content is typically around 0.01 % Al. In nitriding steel, with typical contents of 0.8 to 1.2 % Al, aluminum increases the hardness of the hard-surface layer and its wear resistance.

Fine grained structural steel contains up to 0.015 % Al to induce the fine grained structure which increase the strength and ductility character of the steel.

Heat and scale resistant steels contain typically about 1.0 to 1.7 % Al to create a firmly adhering oxide layer on the surface.

In high-temperature steels low amounts of aluminum increase the high-temperature strength.

Chromium increases the ability to harden heat-treatable steels, and raises the tensile strength whilst the ductility is only slightly lowered. Used in heat-treatable steels up to 3.5 %, Cr increases the effective hardening depth where large diameters or thicknesses are heat treated. Decarburisation of high pressure hydrogenation steel is minimised by alloying up to 12 % Cr.

In stainless steels, chromium is the most important alloying element. Above 12 % Cr steel forms a chromium oxide layer on its surface that gives stainless steels its unique resistance against atmospheric corrosion; depending on the individual grade, up to 30 % Cr is alloyed. Heat and scale resistant steels contain up to 30 % Cr to create a chromium oxide layer on the steel surface that protects the steel from further scaling.

Cobalt is used as an alloying element for high-alloyed steels. Maraging steels contain up to 12 % Co. Tool steels, especially high speed steels, contain up to 10 % Co in order to achieve high hardness in elevated temperature applications.

Copper is used in carbon steels to increase resistance to atmospheric corrosion. In some high alloyed austenitic stainless steel grades copper is added to increase the creep resistance or the corrosion resistance.

Manganese is widely used for deoxidation and is therefore present in small quantities in nearly all steels. The introduction of manganese to an alloy is frequently an economic solution for increasing strength or improving the hardenability of steels. The maximum content can be up to 14 % in abrasion resistant austenitic manganese steels.

Molybdenum. Up to 2 % of Molybdenum is used as an alloying element in various grades of steels. In low alloyed steels it increases the ability to harden the steel and prohibits the temper brittleness of chromium and manganese alloyed heat treatable steels. In tool steels its ability to induce carbides is used to increase abrasion resistance and tempering resistance.

When added to stainless steel, molybdenum increases the resistance to corrosion, especially against pitting corrosion.

Nickel is used as an alloying element for various steel grades and applications.

With up to 2.2 % in case hardening steels and heat treatable steels, it increases ductility by inducing a fine grain structure, and allows full-diameter quenching and tempering.

The ductility at low temperatures of low and high alloyed steels is improved by alloying up to about 10 % Ni.

Austenitic stainless steels contain a minimum of 18 % chromium and 8 % nickel.

Silicon is a powerful deoxidiser and has additionally provides the following advantages

Spring steels use typically 0.6 to 1.8 % Si to increase yield and tensile strength and the limit of proportionality. Heat and scale resistant steels contain up to 4.5 % Si to help the formation of a protective layer. Transformer steels with up to 4.3 % Si have high electrical resistance and low hysteresis loss.

Sulphur is - similar to phosphorus - regarded as an undesirable element - except for special applications - that forms impurities in steel, and decreases ductility in different ways.

Increased sulphur contents of about 0.15 - 0.3 % S can however be used to improve cutting properties of steel (free cutting steel).

Titanium is used in fine-grain steels to create the fine-grain structure by precipitation of titanium carbides at high temperatures. This increases ductitlity, strength and weldability.

In stainless steels it is used to improve the resistance against intercrystalline corrosion by forming titanium carbides and thus preventing precipitation of chromium carbides.

Tungsten is alloyed up to about 8 % in various tool steels to improve hardness and wear resistance at normal and elevated temperatures.

Vanadium can be alloyed below 0.1 % to fine-grain steels with a similar effect to titanium, and is also alloyed in contents up to 4 % to tools steels to improve hardness and wear resistance.

How to calculate the weight

The weight is easily calculated. Simply multiply the appropriate alloy density by the thickness, width, and length of the required part (see worked example below).

Metricdensity (g/cm³)x Tx Wx L= weight
Example7.80 g/cm³x 6mmx 2mx 1m= 93.60 kg
Imperialdensity (lbs/in³)x Tx Wx L= weight
Example0.285 lbs/in³x 4inx 48inx 144in= 7879.68 lbs

For imperial weight calculations certain measurements (fractions) need to be converted to decimal inches. For an accurate calculation it is also important to allow for the rolling tolerance which affects the thickness and the cutting tolerances which affect the width and length. These vary from thickness to thickness – please contact us for details.

Density of steel

The acknowledged density of mild steel is 7.80 g/cm3 (0.285 lbs/in3). Depending on the alloy elements added to manufactured specifications this can vary between 7.75 and 8.05 g/cm3 (0.280 and 0.291 lbs/in3).

Sheet - Metric
Sheet - Imperial
Plate - Metric
Plate - Imperial
Thickness
mm
Size 
m
Weight
kg/sheet
Thickness
in
Size 
ft
Weight
lbs/sheet
Thickness
mm
Size 
m
Weight
kg/plate
Thickness
in
Size 
ft
Weight
lbs/plate
3002 x 14.71210 x 314.76.352 x 199.71/410 x 3306.7
3762 x 15.91410 x 317.210.002 x 1157.0
4002 x 16.31610 x 319.612.702 x 1199.41/210 x 3613.4
4572 x 17.21810 x 322.115.002 x 1235.5
5002 x 17.92010 x 324.53/410 x 3920.2
5592 x 18.82210 x 327.020.002 x 1314.0
6002 x 19.42410 x 329.425.402 x 1398.8110 x 31226.9
7102 x 111.12810 x 334.430.002 x 1471.0
8002 x 112.63210 x 339.31 1/410 x 31533.6
9142 x 114.33610 x 344.238.102 x 1598.21 1/210 x 31840.3
1.0002 x 115.74010 x 349.140.002 x 1628.0
1.2002 x 118.84710 x 357.750.002 x 1785.0
1.2202 x 119.24810 x 358.950.802 x 1797.6210 x 32453.8
1.2702 x 119.95010 x 361.360.002 x 1942.0
1.4202 x 122.35610 x 368.763.502 x 1997.02 1/210 x 33067.2
1.6002 x 125.16310 x 377.32 3/410 x 33373.9
1.7802 x 128.07010 x 385.970.002 x 11099.0
2.0002 x 131.47810 x 395.776.202 x 11196.3310 x 33680.6
2.0302 x 131.98010 x 398.280.002 x 11256.0
2.2862 x 135.99010 x 3110.490.002 x 11413.0
2.5002 x 139.310010 x 3120.2100.002 x 11570.0
2.5402 x 139.99810 x 3120.2101.602 x 11595.1410 x 34907.5
2.6402 x 141.410410 x 3122.7110.002 x 11727.0
3.0002 x 147.111810 x 3144.8120.002 x 11884.0
3.2502 x 151.012810 x 3157.0127.002 x 11993.9510 x 36134.4
4.0002 x 162.815710 x 3192.6130.002 x 12041.0
4.0602 x 163.716010 x 3196.35 1/210 x 36747.8
4.4602 x 170.017610 x 3215.9140.002 x 12198.0
4.7602 x 174.718710 x 3229.4150.002 x 12355.0
5.0002 x 178.519710 x 3241.7152.402 x 12392.7610 x 37361.3
6.0002 x 194.223610 x 3289.5
Sheet - Metric
Sheet - Imperial
Plate - Metric
Plate - Imperial
Thickness
mm
Size 
m
Weight
kg/sheet
Thickness
in
Size 
ft
Weight
lbs/sheet
Thickness
mm
Size 
m
Weight
kg/plate
Thickness
in
Size 
ft
Weight
lbs/plate
3002 x 14.71210 x 314.76.352 x 199.71/410 x 3306.7
3762 x 15.91410 x 317.210.002 x 1157.0
4002 x 16.31610 x 319.612.702 x 1199.41/210 x 3613.4
4572 x 17.21810 x 322.115.002 x 1235.5
5002 x 17.92010 x 324.53/410 x 3920.2
5592 x 18.82210 x 327.020.002 x 1314.0
6002 x 19.42410 x 329.425.402 x 1398.8110 x 31226.9
7102 x 111.12810 x 334.430.002 x 1471.0
8002 x 112.63210 x 339.31 1/410 x 31533.6
9142 x 114.33610 x 344.238.102 x 1598.21 1/210 x 31840.3
1.0002 x 115.74010 x 349.140.002 x 1628.0
1.2002 x 118.84710 x 357.750.002 x 1785.0
1.2202 x 119.24810 x 358.950.802 x 1797.6210 x 32453.8
1.2702 x 119.95010 x 361.360.002 x 1942.0
1.4202 x 122.35610 x 368.763.502 x 1997.02 1/210 x 33067.2
1.6002 x 125.16310 x 377.32 3/410 x 33373.9
1.7802 x 128.07010 x 385.970.002 x 11099.0
2.0002 x 131.47810 x 395.776.202 x 11196.3310 x 33680.6
2.0302 x 131.98010 x 398.280.002 x 11256.0
2.2862 x 135.99010 x 3110.490.002 x 11413.0
2.5002 x 139.310010 x 3120.2100.002 x 11570.0
2.5402 x 139.99810 x 3120.2101.602 x 11595.1410 x 34907.5
2.6402 x 141.410410 x 3122.7110.002 x 11727.0
3.0002 x 147.111810 x 3144.8120.002 x 11884.0
3.2502 x 151.012810 x 3157.0127.002 x 11993.9510 x 36134.4
4.0002 x 162.815710 x 3192.6130.002 x 12041.0
4.0602 x 163.716010 x 3196.35 1/210 x 36747.8
4.4602 x 170.017610 x 3215.9140.002 x 12198.0
4.7602 x 174.718710 x 3229.4150.002 x 12355.0
5.0002 x 178.519710 x 3241.7152.402 x 12392.7610 x 37361.3
6.0002 x 194.223610 x 3289.5

Density based on 7.80 g/cm3
(0.285 lbs/in3)

How to calculate the weight

The weight of bars is just as easily calculated. Simply multiply the appropriate alloy density (see chart below) by π, the squared radius (equals half the diameter) and length of the required part (see worked example below).

Metricdensity (g/cm³)x πx Lx (0.5 x d)²= weight
Example7.80 g/cm³x πx 2.5mx (0.5 x 0.4m)²= 2450.45 kg
Imperialdensity (lbs/in³)x πx Lx (0.5 x d)²= weight
Example0.285 lbs/in³x πx 144inx (0.5 x 15in)²= 7252.38lbs

How to calculate the weight

The weight of tubes is just as easily calculated. Simply multiply the appropriate alloy density (see chart below) by π, the length of the required part, and the variable q. q is herein defined as outer diameter of the tube, multiplied by the thickness and minus the squared thickness (see worked example below).

Metricdensity (g/cm³)x πx Lx q (= d x t - t²)= weight
Example7.80 g/cm³x πx 2.5mx (0.4m x 3mm - (3mm)²)= 72.96 kg
Imperialdensity (lbs/in³)x πx Lx q (= d x t - t²)= weight
Example0.285 lbs/in³x πx 144inx (15in x 0.2in - (0.2in)²)= 381.64lbs
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