This recommended practice establishes a test procedure for determining the propensity of aircraft turbine engine cleaning and maintenance materials for causing stress-corrosion cracking of titanium alloy parts. The evaluation is conducted on representative titanium alloys by determining the effect of contact with cleaning and maintenance materials on tendency of pre-stressed titanium alloys to crack when subsequently heated to elevated temperatures. Test conditions are based upon manufacturer's maximum recommended operating solution concentration. Chemical solutions and compounds used for pre-inspection cleaning or for preservation of titanium alloy aircraft turbine engine parts shall be subject to qualification requirements of this test practice. The test does not give consideration to cleaning or corrosion-preventive properties of the compounds.
SAE ARP1795A-1984 history
1990SAE ARP1795A-1990 Stress Corrosion of Titanium Alloys, Effect of Cleaning Agents on Aircraft Engine Materials