4130
4130
General
This chromium-molybdenum alloy is among the most widely used aircraft steels, valued for its excellent weldability, ease of fabrication, and moderate hardenability. In thinner sections, it responds well to heat treatment, achieving high strength levels. Even in its normalised condition, it offers sufficient strength for many engineering applications. For enhanced wear and abrasion resistance, the material can be nitrided.
Uses
DRILL RODS, DOWNHOLE TOOLS, WELLHEAD EQUIPMENT, PUMPS, VALVES, PRESSURE VESSELS, FLANGED PIPE FITTINGS, SELF-LOCKING NUTS, AIRCRAFT EXTERIOR COMPONENTS, STRUCTURAL PARTS, LANDING GEAR COMPONENTS, FASTENERS, SHAFTS.
Chemical Analysis
C
·
0.28-0.33
Mn
·
0.40-0.60
Mo
·
0.15-0.25
S
·
0.040 MAX
Si
·
0.15-0.35
Cr
·
0.90-1.10
Ni
·
0.25 MAX
P
·
0.035 MAX
| C | Mn | Mo | S | Si | Cr | Ni | P |
|---|---|---|---|---|---|---|---|
| 0.28-0.33 | 0.40-0.60 | 0.15-0.25 | 0.040 MAX | 0.15-0.35 | 0.90-1.10 | 0.25 MAX | 0.035 MAX |
Typical Mechanical Properties
TEN. STRENTH
655-896 MPa
0.2% PROOF STRESS
517-758 MPa
ELONG.
20%
HARDNESS
217-235 HB
| TEN. STRENTH | 0.2% PROOF STRESS | ELONG. | HARDNESS |
|---|---|---|---|
| 655-896 MPa | 517-758 MPa | 20% | 217-235 HB |