Bell Cranks - Page 40 of 59

1465 part numbers
128L10033-5 NSN 1680-01-309-1453
  • fulcrum bore features provided
128L10033-6 NSN 1680-01-309-1454 Cross Reference: 128L10033-2
  • fulcrum bore features provided
7-311660006-23 NSN 1680-01-315-1728 Cross Reference: 7-311660006-21
  • ah-64a helicopters end application
123CSM11861-505 NSN 1680-01-315-5689
  • aircraft model e-2c end application
  • agav criticality code justification
16T7309-805 NSN 1680-01-318-7700
  • f-16c/d end application
  • aluminum alloy material
123AMM42114-3 NSN 1680-01-321-3345
  • c-2 aircraft end application
  • aluminum alloy material
107C2608-6 NSN 1680-01-342-4309
  • aircraft model h-46 end application
  • aluminum alloy material
DAA3122A101-004 NSN 1680-01-353-2275 Cross Reference: DAA3122A101-002
  • pacer special end application
17P6W8209-2 (rh) No 1 Spoiler Actuator Support Crank Assy NSN 1680-01-355-2945
  • c-17 acft end application
17P6W8223-2 Rh No. 4 Support Spoiler Actuator Crank Assy NSN 1680-01-355-4777
  • c-17a acft end application
  • c/o 1ea crank, 4ea fittings, 10ea bushings special features
17P6W8209-1 NSN 1680-01-356-3486
  • c-17 aircraft end application
  • crank assembly, spoiler actuator sprt, no. 1 (lh) supplementary features
17P6W8219-501 Lh No. 3 Support Spoiler Actuator Crank Assy NSN 1680-01-357-4534 Cross Reference: 17P6W8219-1
  • c-17a acft end application
  • c/o 1ea crank, 4ea fittings, 12ea bushings special features
DAA3122A378-007 NSN 1680-01-365-6068
  • 3.003 inches bore length
  • pacer special end application
  • 4.000 inches 2nd end center to center distance between fulcrum and arm end hole/slot/ball
  • 0.62475 inches 1st end end hole/ball diameter
  • raised face pivot hole, clevis both ends style designator
DAA3255A112-032 NSN 1680-01-366-3129
  • b-2 aircraft end application
DAA3255A123-011 NSN 1680-01-366-6765
  • pacer special end application
  • 3.410 inches 1st end center to center distance between fulcrum and arm end hole/slot/ball
  • 0.6250 inches 2nd end end hole/ball diameter
  • main landing gear, emergency uplock release fsc application data
DAA3255D222-001 NSN 1680-01-366-7305
  • b-2 aircraft end application
  • steel material
DAA3255A123-012 NSN 1680-01-367-0240
  • pacer special end application
  • 3.410 inches 1st end center to center distance between fulcrum and arm end hole/slot/ball
  • 0.6250 inches 2nd end end hole/ball diameter
  • main landing gear, emergency uplock release fsc application data
DAB3122A014-005 NSN 1680-01-367-4231
  • pacer special end application
  • bell crank assembly eaid locking system is special features
  • aluminum alloy material
17P2N3026-502 NSN 1680-01-368-1541 Cross Reference: 17P2N3026-2
  • c-17 aircraft end application
  • aluminum alloy material
DAB3122A014-009 NSN 1680-01-368-6682
  • pacer special end application
  • 2.250 inches 1st end center to center distance between fulcrum and arm end hole/slot/ball
  • bell crank assembly eaid locking system is special features
  • aluminum alloy material
DAA3255A112-035 NSN 1680-01-369-1574
  • b-2 aircraft end application
DAA3255A112-036 NSN 1680-01-369-5348
  • pacer special end application
L6314038-011 NSN 1680-01-369-7018
  • b-1b bomber airplane end application
  • used in drove-chute door system special features
L6317137-003 NSN 1680-01-369-8590
  • between 0.248 inches and 0.252 inches bore length
  • b-1b aircraft end application
  • 1.500 inches 1st end center to center distance between fulcrum and arm end hole/slot/ball
  • 0.250 inches 2nd end end hole/ball diameter
  • steel material
17P2A3147-501 NSN 1680-01-370-1566 Cross Reference: 17P2A3147-1
  • 0.080 inches counterbore depth
  • 0.750 inches bore diameter
  • 10.890 inches bore length
  • c-17a aircraft end application
  • titanium material