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Alloy MP35N® (AMS 5844/AMS 5845/ NACE MR0175)


Technical Data Sheet

Chemical Composition Limits
Weight % Ni Co Cr Mo Ti Fe Si Mn P B S C
MP35N® 33-37 Bal 19-21 9-10.5 1 max 1 max 0.15 max 0.15 max 0.015 max 0.010 max 0.010 max 0.03 max
MP35N® is a registered trademark of SPS Technologies Inc.

MP35N® is a multi-phase alloy containing Nickel, Cobalt, Chromium and Molybdenum with a unique range of properties - ultra high strength, toughness, biocompatibility and corrosion resistance. It is produced by vacuum induction melting and vacuum arc re-melting (VIM-VAR) and is then strengthened by work hardening and aging, giving hardnesses of up to 55-60 Rockwell C and strength levels as high as 260-300KSI.

Due, to this unique combination of properties, MP35N® has many applications in such industries as oil and gas, aerospace and medical. MP35N can be effectively used at cryogenic temperatures without embrittlement and maintain its properties at temperatures up to 600°F, and is also suitable for medical implants and orthodontic/prosthetic devices.

MP35N® is able to resist corrosion to most mineral acid, hydrogen sulfide and seawater environments whilst exhibiting excellent resistance to stress corrosion cracking and hydrogen embrittlement, even at high strength levels. NACE MR0175 allows a hardness of up to 51 HRC for material that has been work strengthened and aged by one of the processes listed in the table below.

Aircraft Materials supplies MP35N® in round bar certified to either AMS 5844 (0.270" - 1.520" diameter) or NACE MR0175 (0.5" - 2.5" diameter), as well as sheet, strip and plate products suitable for medical applications.

Typical Mechanical Properties

Material Condtion Ultimate Tensile Strength ksi 0.2 % Yield Strength ksi Elongation % Reduction of Area % Hardness HRC
MP35N ®
AMS 5844
Solution Heat Treated and Work Strengthened 255 225 12 50 45
MP35N®
AMS 5845
Solution Heat Treated and Work Strengthened and Aged 260 230 8 35 38 min

AMS 5844 is Solution Treated and Cold Worked. The AMS specification only requires that the hardness shall not be lower than 38 HRC or equivalent. However other typical mechanical properties of AMS 5844 are detailed above.

Material Condtion Tensile Strength ksi Yield Strength ksi Elongation % Reduction of Area % Hardness HRC
MP35N®
NACE MR0175
Age @ 1300°F/ 4 hrs 220 210 10 40 51 max
MP35N®
NACE MR0175
Age @ 1350°F / 4hrs 210 200 10 40 51 max
MP35N®
NACE MR0175
Age @ 1425°F / 6hrs 190 180 10 40 51 max
MP35N® Properties as per NACE MR0175 - Cold Drawn - Reduced Strength (min properties, round bar under 2" dia)

Availability
Alloy MP35N® is available in Round Bar, Tube, Wire, Sheet and Plate. For all stock availability contact Sales.

Specifications
UNS R30035

AMS 5758 - MP35N® VIM-VAR Bar
Solution heat treated @1900-1925°F for 4 to 8 hours

AMS 5844 - MP35N® VIM-VAR Bar
Solution heat treated @1900-1925°F for 4 to 8 hours and Work Strengthened

AMS 5845 - MP35N® VIM-VAR Bar
Solution heat treated @ 1900-1925°F for 4 to 8 hours, Work Strengthened & Aged @ 1000-1200°F for 4 hours

NACE MR0175
ASTM F-562 - Surgical Implant Applications
BS 7252-6 Surgical Implant Applications
ISO 5832-6 Surgical Implant Applications

MP35N® is a registered trademark of Standard Pressed Steel (SPS) Technologies Inc.

Services
At Aircraft Materials all stock items can be shipped out within 24 hours, usually within the same day. Even cutting orders for bar or sheet can be processed and dispatched the same day, and for time-critical situations such as AOGs, we have a dedicated AOG service desk ready to help (aog@aircraftmaterials.com).

Thanks to our global logistics network we can source from anywhere in the world in just a few days. We use a range of transport partners to enable us to ship overnight within the U.K. and Europe and provide fast shipping solutions to the rest of the world. If your requirement is urgent we can offer a priority shipping service, but also if time is not so critical we can offer more cost-effective options to ensure you get the best value for money. To find out more about our services click here.

Disclaimer
Every effort is made to ensure that technical specifications are accurate. However, technical specifications included herein should be used as a guideline only. All specifications are subject to change without notice.

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