Waspaloy® Round Bar - AMS 5708
Waspaloy® round bar – AMS 5708 (Type 2 capable of AMS 5709) is a precipitation‑hardening, nickel‑based superalloy containing chromium and cobalt that is engineered for high‑strength, high‑temperature aerospace applications. It is most commonly used in aircraft fasteners and structural hardware where exceptional mechanical strength is required at temperatures up to 1,500°F (816°C), along with oxidation resistance in environments reaching 1,750°F (954°C). Waspaloy® 5708 is produced using multiple‑melt practices, typically involving vacuum induction melting (VIM) followed by either vacuum arc remelting (VAR) or electroslag remelting (ESR), resulting in a highly refined microstructure and consistent performance for critical aerospace components.
- Inventory & Specs
- Chemical Composition
- Physical Properties
- Mechanical Properties
- Datasheet
- Additional Info
- FAQs
Inventory Size Ranges for Waspaloy® 5708
| Type | Thickness | AMS Standards | UNS | Get a Quote |
|---|---|---|---|---|
| Bar | 0.236" - 1.010" | AMS 5708 Type 2, AMS 5709 (Capable of) | UNS NO7002 | Get a Quote |
Characteristics of Waspaloy® 5708
Waspaloy® 5708 offers an exceptional combination of high tensile strength, fatigue resistance, and thermal stability, particularly in fastener and hardware applications exposed to elevated temperatures. The alloy maintains reliable mechanical properties under sustained heat and stress, making it well suited for load‑bearing aerospace components. Its nickel‑based chemistry, enhanced with chromium and cobalt, provides strong oxidation resistance and environmental stability at temperatures significantly higher than conventional alloy steels. The refined microstructure achieved through multiple‑melt processing contributes to consistent quality, improved cleanliness, and dependable performance in demanding service conditions where safety and reliability are critical.
Working with Waspaloy® 5708
Waspaloy® 5708 is a high‑strength superalloy that requires specialized processing and machining practices due to its toughness and tendency to work‑harden. Machining typically demands rigid setups, sharp tooling, controlled feeds, and reduced cutting speeds compared to lower‑strength alloys. Forming operations are generally performed under carefully controlled conditions, as the alloy’s strength limits cold workability. Heat treatment plays a critical role in achieving the required mechanical properties, with strength developed through solution heat treatment followed by aging. The multiple‑melt production routes used for Waspaloy® 5708 help improve consistency and processability, but experience with nickel‑based superalloys is essential to successfully manufacture high‑performance fasteners and aerospace hardware.
Other industry standards we comply with:
- PWA LCS
- GE Aircraft Engine (GT193)
- GE Aviation S-SPEC-35 AeDMS S-400
- RR SABRe Edition 2
- Fairchild MS305
- DFARS Compliant
- EN 2.4654
Common Trade Names
- Waspaloy®
Industry Applications for Waspaloy® 5708
- Aerospace Fasteners
- Jet Engine Components
- Missile Components
Chemical Composition
| Element | Min | Max | |
|---|---|---|---|
| C | Carbon | 0.02 | 0.10 |
| Mn | Manganese | - | 0.10 |
| Si | Silicon | - | 0.15 |
| P | Phosphorus | - | 0.015 |
| S | Sulfur | - | 0.015 |
| Cr | Chromium | 18.00 | 21.00 |
| Co | Cobalt | 12.00 | 15.00 |
| Mo | Molybdenum | 3.50 | 5.00 |
| Ti | Titanium | 2.75 | 3.25 |
| Al | Aluminum | 1.20 | 1.60 |
Physical Properties
| Property | Value |
|---|---|
| Density | 0.296 lb/in3 (8.19 g/cm3) |
| Melting Range | 2,425 to 2,565 ºF (1,329 to 1,407 ºC) |
Mechanical Properties
| Property | Value |
|---|---|
| Hardness | BHN 302 max / Rockwell C 34-44 |
Datasheet
Additional Info
A Brief History of Waspaloy® 5708
Waspaloy® 5708 is a precipitation‑hardening, nickel‑based superalloy developed to support the increasing performance demands of modern aerospace fastening and high‑temperature structural applications. As jet engine and airframe designs advanced, engineers required materials capable of delivering very high tensile strength at elevated temperatures while maintaining oxidation resistance and long‑term reliability. Waspaloy® emerged as a solution to these challenges, offering a refined balance of strength, thermal stability, and environmental resistance in demanding aerospace service conditions.
Unlike solid‑solution alloys, Waspaloy® 5708 was engineered to achieve its performance through controlled heat treatment and precipitation strengthening, making it especially suitable for critical fasteners and hardware exposed to sustained heat and mechanical stress.
How Waspaloy® 5708 Was Developed
Waspaloy® 5708 was developed by alloy designers seeking to optimize high‑temperature strength and fatigue performance for aerospace components operating at temperatures up to 1,500°F (816°C). By combining a nickel‑based matrix with strategic additions of chromium and cobalt, metallurgists enhanced oxidation resistance, phase stability, and strength retention at elevated temperatures. The alloy’s strength is further increased through a precise precipitation‑hardening heat treatment process.
To meet strict aerospace quality requirements, Waspaloy® 5708 is produced using multiple‑melt practices, most commonly vacuum induction melting (VIM) followed by either vacuum arc remelting (VAR) or electroslag remelting (ESR). These processes significantly reduce impurities and improve microstructural uniformity, resulting in dependable performance for safety‑critical applications.
Early Applications of Waspaloy® 5708
As aerospace systems evolved to operate under higher loads and temperatures, Waspaloy® 5708 quickly gained acceptance for aircraft fasteners and high‑strength hardware where conventional steels and lower‑strength alloys could not meet performance requirements. Its ability to maintain strength and resist oxidation in hot engine and airframe zones made it well suited for bolting, fastening, and structural components subjected to both mechanical stress and elevated thermal exposure.
Early adoption focused on applications where weight reduction, reliability, and long service life were paramount, and where failure was not an option. Waspaloy® 5708 helped enable higher operating temperatures and improved overall system efficiency in advanced aerospace designs.
How Waspaloy® 5708 Is Used Today
Today, Waspaloy® 5708 remains a trusted material for aerospace fasteners and structural components requiring high strength at elevated temperatures and oxidation resistance up to approximately 1,750°F (954°C). It is commonly specified for critical hardware used in aircraft engines, exhaust systems, and high‑temperature airframe areas where performance margins are tight and material consistency is essential.
The alloy’s compatibility with AMS 5708 requirements, and in Type 2 conditions capable of AMS 5709, ensures repeatable performance and compliance with stringent aerospace standards. Its proven processing history and availability make it a preferred choice for fastener manufacturers and aerospace OEMs supporting both legacy platforms and next‑generation aircraft.
Your Trusted Supplier for Waspaloy® 5708
United Performance Metals is a global specialty metals solutions provider offering Waspaloy® 5708 round bar to support high‑performance aerospace applications. With deep expertise in nickel‑based superalloys and stringent aerospace quality requirements, UPM delivers materials produced through advanced multiple‑melt processes and supplied with full certification and traceability.
Backed by value‑added processing services and technical support, United Performance Metals helps customers meet demanding performance, quality, and delivery requirements for critical aerospace fastener and hardware programs.
Contact our team today to learn how Waspaloy® 5708 can support your next high‑temperature, high‑strength application.
Product FAQs
Waspaloy® 5708 is primarily used for aircraft fasteners and high‑strength aerospace hardware that must maintain mechanical integrity at elevated temperatures. It is particularly well suited for bolting and fastening applications where high tensile strength up to approximately 1,500°F (816°C) and oxidation resistance up to 1,750°F (954°C) are required.