INTRODUCTION TO AIRCRAFT STRUCTURAL REPAIR TECHNIQUES & SUBSTANTIATION
Target audience is A&P mechanics and young engineers. This blog is a tease but currently free because my original Boeing textbook “Liaison Engineering Discussion Series” is being rewritten. Formatting has been lost during cut and paste.
(CAUTION: The following is not approved data consult the SRM or contact a DER)
“Typical Repairs for Aircraft Structures
This section describes typical repairs of the major structural parts of an airplane. When repairing a damaged component or part, consult the applicable section of the manufacturer’s SRM for the aircraft. Normally, a similar repair is illustrated, and the types of material, rivets, and rivet spacing and the methods and procedures to be used are listed. Any additional knowledge needed to make a repair is also detailed. If the necessary information is not found in the SRM, attempt to find a similar repair or assembly installed by the manufacturer of the aircraft.
Corrugated Skin Repair
Some of the flight controls of smaller general aviation aircraft have beads in their skin panels. The beads give some stiffness to the thin skin panels. The beads for the repair patch can be formed with a rotary former or press brake.
Replacement of a Panel
Damage to metal aircraft skin that exceeds repairable limits requires replacement of the entire panel.
A panel must also be replaced when there are too many previous repairs in a given section or area. (or contact a DER)
In aircraft construction, a panel is any single sheet of metal covering. A panel section is the part of a panel between adjacent stringers and bulk heads. Where a section of skin is damaged to such an extent that it is impossible to install a standard skin repair, a special type of repair is necessary.
The particular type of repair required depends on whether the damage is repairable outside the member, inside the member, or to the edges of the panel.
Outside the Member
For damage that, after being trimmed, has 81⁄2 rivet diameters or more of material, extend the patch to include
the manufacturer’s row of rivets and add an extra row inside the members.
Inside the Member
For damage that, after being trimmed, has less than 81⁄2 manufacturer’s rivet diameters of material inside the
members, use a patch that extends over the members and an extra row of rivets along the outside of the members.
Edges of the Panel
For damage that extends to the edge of a panel, use only one row of rivets along the panel edge, unless the
manufacturer used more than one row. The repair procedure for the other edges of the damage follows the previously explained methods.”
We will review this repair in detail as time goes by
Feedback and questions encouraged. Comment here, email us at firstname.lastname@example.org, or visit our website at http://www.Callahan.aero or our Facebook page, “Callahan Aircraft Services, LLC“
James W. Callahan, FAA DER
540 N College St.
AUburn, AL 36830
Not responsible for anything below this line