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 5999-00-369-7664
NSN 5990-01-216-0148
NSN 5996-01-351-6485
NSN 6110-01-421-2714
NSN 5960-01-328-8248
NSN 5925-00-561-9648
NSN 5920-00-973-8366
NSN 6130-01-158-6139
NSN 6220-01-461-2499
NSN 5965-01-144-9699
NSN 6645-01-240-4640
NSN 5950-00-500-2709