Bell Cranks - Page 51 of 59

1465 part numbers
145C3172-1 NSN 1680-01-514-0342
74A425115-1004 (inavy) Bell Crank NSN 1680-01-514-3423 Cross Reference: 74A425115-1002
  • fighter aircraft-first (f18 e/f) end application
  • agav criticality code justification
74A425115-1003 NSN 1680-01-514-3424 Cross Reference: 74A425115-1001
  • fighter aircraft-first ( f18 e/f ) end application
17P8D8214-503 Fan Duct Inner Blocker Door Link Assy NSN 1680-01-514-7794
  • c-17a aircraft end application
  • consists of 1 link and 3 bushing sleeves special features
  • titanium material
5128T43G01 Aircraft (inavy) Bell Crank NSN 1680-01-514-8386
  • ge f414-400 engine end application
  • agav criticality code justification
2-41352-7 NSN 1680-01-515-6979
  • f5 aircraft end application
6-73192-41 NSN 1680-01-516-2153
  • f-5 aircraft end application
  • 10.000 inches 1st end center to center distance between fulcrum and arm end hole/slot/ball
  • aluminum alloy material
5HR40442-135 NSN 1680-01-516-3689
65-13742-6 NSN 1680-01-516-4574
  • boeing 707 end application
75A613782-2011 Drive Rudder Bell Crank NSN 1680-01-516-5154
  • harrier 11 aircraft end application
75A610001-2007 Aileron Arm-idler NSN 1680-01-516-7433
  • dimensions: 1.000 in. x 2.060 in. x 3.450 in. special features
  • aluminum material
  • anodize surface treatment
75A610001-2005 Aileron Arm-idler NSN 1680-01-516-7434
  • dimensions: 1.000 in. x 2.060 in. x 3.560 in. special features
  • aluminum material
  • anodize surface treatment
75A610001-2008 Aileron Arm-idler NSN 1680-01-516-7441
  • dimensions: 1.000 in. x 3.180 in. x 3.200 in. special features
  • aluminum material
  • anodize surface treatment
17P2C7866-2 Stabilizer Strut Drive-overtravel Mechanism Crank Assy NSN 1680-01-517-9236
  • c-17a end application
  • titanium material
17P2C7866-1 Stabilizer Strut Drive-overtravel Mechanism Crank Assy NSN 1680-01-518-0008
  • c-17a acft end application
  • titanium material
5HF71044-103 Rh Bell Crank NSN 1680-01-519-0613
  • f/a-22 raptor end application
  • c/o 1ea bell crank assembly, p/n 5hl88410-106 special features
17P2C1370-507 Rigid Connecting Link NSN 1680-01-519-3034
  • 0.790 inches bore diameter
  • between 2.270 inches and 2.280 inches bore length
  • c-17a acft end application
  • bearing and lubrication fitting accommodation features provided
  • plain fulcrum bore shape
17P2C1370-508 Rigid Conncting Link NSN 1680-01-519-3857
  • 0.790 inches bore diameter
  • between 2.270 inches and 2.280 inches bore length
  • c-17a acft end application
  • bearing and lubrication fitting accommodation features provided
  • plain fulcrum bore shape
66-13952-1 NSN 1680-01-519-5320
901-031-643-109 Air (inavy)bell Crank Assy NSN 1680-01-520-8071
  • mv-22 tilt rotor aircraft end application
  • agav criticality code justification
3F13490026D (inavy) Throttle Arm Assembly NSN 1680-01-520-9489
  • control assembly end application
  • agav criticality code justification
3F13490027D (inavy) Throttle Arm Assembly NSN 1680-01-520-9490
  • control assembly end application
  • agav criticality code justification
354011-5 NSN 1680-01-521-0689
  • between 0.770 inches and 0.820 inches bore length
  • plain fulcrum bore shape
  • 2.250 inches 2nd end center to center distance between fulcrum and arm end hole/slot/ball
  • iron cast material
  • tongue end, vertical holes other arm style designator
354011-7 NSN 1680-01-521-0692
  • between 0.770 inches and 0.820 inches bore length
  • plain fulcrum bore shape
  • 2.250 inches 2nd end center to center distance between fulcrum and arm end hole/slot/ball
  • iron cast material
  • tongue end, vertical holes other arm style designator
354011-6 NSN 1680-01-521-0693
  • between 0.770 inches and 0.820 inches bore length
  • plain fulcrum bore shape
  • 2.250 inches 2nd end center to center distance between fulcrum and arm end hole/slot/ball
  • iron cast material
  • tongue end, vertical holes other arm style designator