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 5985-00-074-4763
NSN 5998-00-517-9170
NSN 5996-00-017-8261
NSN 6110-01-383-4531
NSN 6145-01-622-9730
NSN 6620-01-346-9340
NSN 5950-01-174-7597
NSN 5965-01-435-6644
NSN 5920-01-605-0214
NSN 6105-01-197-9632
NSN 5998-01-435-7507
NSN 6130-00-246-6915