Aluminum alloy, ams 4141; 11.422 in. Min 11.447 in. Max lg, 9.655 in. Min 9.675 in. Max w, 0.271 in. Min 0.278 in. Max diameter of 10 holes, 0.338 in. Min 0.345 in. Max diameter of 2 holes
A component of a vane assembly, compressor, aircraft gas turbine engine. It is designed to receive air from the preceding compressor blades and deliver it to the succeeding row of compressor blades, diffuser, or combustion area at correct pressure, velocity and direction.
Classification: Parts of gas turbine aircraft engines, other than for use in civil aircraft
NSN 5935-00-419-9472
NSN 5935-00-273-3861
NSN 6135-00-168-3876
NSN 5960-01-495-0859
NSN 5965-00-925-1725
NSN 6610-00-270-6649
NSN 7035-00-088-7355
NSN 6240-01-418-1917
NSN 2925-00-449-1604
NSN 5996-00-697-9684
NSN 6240-01-451-1409
NSN 5935-01-349-7725