SuperStress
Aerospace
- May 5, 2003
- 94
Hi folks; I haven't been around for a while... life just gets too busy.
Wil - this might be one for you.
The folks I represent are in the process of procuring a major piece of replacement structure for an aging airframe. The supplier wants to "butt drive" solid rivets (D-rivets) in the primary structure. By "butt drive", they mean to drive the rivets with the gun on the tail instead of the manufactured head. (This is NOT referring to the wonderful "NACA" rivet installations where the tails were bucked into machined countersinks...)
All of the process specs and test data support only "standard" installation, and don't specifically address this method. The OEM used the standard method during original manufacture.
The customer's position is that without test data showing equivalent hole fill and durability (as verified by testing), and without a process specification that specifically controls the proposed process, complete with Quality Assurance inspection and acceptance criteria, deviating from the tried-and-true method of rivet installation should not be allowed.
However, the customer is getting significant push-back from the supplier, a well-respected aerospace manufacturer.
Is anyone aware of any resources (old NACA data, or other public-domain resources) that might address this installation and it's interchangeability with standard installations?
If my question isn't clear, let me know...
SuperStress
Wil - this might be one for you.
The folks I represent are in the process of procuring a major piece of replacement structure for an aging airframe. The supplier wants to "butt drive" solid rivets (D-rivets) in the primary structure. By "butt drive", they mean to drive the rivets with the gun on the tail instead of the manufactured head. (This is NOT referring to the wonderful "NACA" rivet installations where the tails were bucked into machined countersinks...)
All of the process specs and test data support only "standard" installation, and don't specifically address this method. The OEM used the standard method during original manufacture.
The customer's position is that without test data showing equivalent hole fill and durability (as verified by testing), and without a process specification that specifically controls the proposed process, complete with Quality Assurance inspection and acceptance criteria, deviating from the tried-and-true method of rivet installation should not be allowed.
However, the customer is getting significant push-back from the supplier, a well-respected aerospace manufacturer.
Is anyone aware of any resources (old NACA data, or other public-domain resources) that might address this installation and it's interchangeability with standard installations?
If my question isn't clear, let me know...
SuperStress