MS21250 bolt torque values
MS21250 bolt torque values
(OP)
I have a combination of the following bolt & nut (also some washers):
Bolt MS21250-05016
Nut H55LH4367-054
I have no direction in the SRM regarding the torque. While I have requested confirmation from the aircraft manufacturer, in the mean time I am trying to chase down something that can be of help.
Does anyone have a suggestion?
TIA
Phil
Bolt MS21250-05016
Nut H55LH4367-054
I have no direction in the SRM regarding the torque. While I have requested confirmation from the aircraft manufacturer, in the mean time I am trying to chase down something that can be of help.
Does anyone have a suggestion?
TIA
Phil





RE: MS21250 bolt torque values
http://doc
This is 180ksi rated bolt series for up to 450F degrees. For every bolt size you can find the ultimate tensile strength (force to brake) of the bolt in the last column of the table. I assume your bolt is 5/16" and for that size the minimum tensile strength is 11100 lbf.
You will need to calculate the bolt tightning torque such that the induced force in the bolt will be less than the break load of 11100 lbf with the desired factor of safety.
RE: MS21250 bolt torque values
RE: MS21250 bolt torque values
BTW if there are any c130 folks out there, this relates to the Main Landing Gear Beam to Drag Angle connection (STA577, RBL61.625, WL255 {approx}).
Phil
RE: MS21250 bolt torque values
Phil
RE: MS21250 bolt torque values
http://doc
RE: MS21250 bolt torque values
http://gltrs.grc.nasa.gov/reports/1990/RP-1228.pdf
RE: MS21250 bolt torque values
Chapter 6 states that the standard torque table should be used as a guide in tightening nuts, studs, bolts and screws whenever specific torque values are not called out in the maintenance manual.
A 5/16 - 24, 160+KSI using any nut except shear type = 140-203 inch pounds.
RE: MS21250 bolt torque values
RE: MS21250 bolt torque values
Why wouldn't the standard torque tables/formulas be used in a situation where the torque is not called-out in the MM/SRM?
If he is working on a C-130 (and assume this is a military aircraft) then their T.O.'s will list the 1-1A-8 - Aircraft Structural Hardware, as applicable to this airframe.
There is a section in this TO that describes how to calculate torque if it is not given by the manufacturer.
AOG waiting for the aircraft manufacturer to give torque for standard hardware?
RE: MS21250 bolt torque values
We have resolved this particular issue but getting a copy of TO 1-1A-8 would be nice... :)
Phil
RE: MS21250 bolt torque values
Too many times people post here, then drop without finishing the thread.
RE: MS21250 bolt torque values
RE: MS21250 bolt torque values
RE: MS21250 bolt torque values
"Torque value", huh? On a very critical application at that, eh?
It saddens me that highly-educated people continue to put their faith into something which clearly has dubious or limited, at best, relationship to bolt load.
There are so many variables which affect how much of the input torque actually results in bolt tension, yet many of us choose to remain oblivious to this reality. No wonder cranes collapse, reactors leak, wheels fly off of trucks, and airplanes fall out of the sky! C'mon, we all know that "Torque" is not and CANNOT be an indication of how "tight" a bolt is!
Tightening a bolt by applying "torque" (with a calibrated torque wrench even!) and then walking away, exepecting all to be fine, is almost negligent. Since "torque" has such an unknown relationship to a bolt's load, one must always take the next obvious step: measurement and verification. The easiest way of doing this is by measuring the stretch of the loaded fastener.
Ciao,
HevïGuy
www.heviitech.com