Aircraft Sheet Metal Patch Repair Procedure

Principal requirements in repair of structures inspection of the damage and accurate estimate of the type of repair required important steps in repairing structural damage.

Aircraft sheet metal patch repair procedure.

Basic principles of sheet metal repair. The primary objective of aircraft repair is to restore damaged parts to their original condition. If the rivet is too long the formed head will be too large or the rivet may bend or. Supported metal skin support the sheet metal on the inside with a bucking bar.

Aircraft sheet metal work prem mahendranathan structural repair. It is not contrary to manufacturer s data. Sheet metal fabrication is considered a blend of art and science requiring finesse to achieve desirable results. Basic airframe repair subcourse number al0992 edition a us army aviation logistics school fort eustis virginia 23604 5439 4 credit hours edition date.

In spect rivet joints adjacent to damaged structure for partial failure by removing one or more. Removal of rivet heads with a cold chisel and hammer is not recommended because skin damage and distorted rivet holes will probably result. Place a splice where the member is. Stop drill the crack ends with a no.

The doubler should be of a. The user has determined that it is appropriate to the product being repaired. The proper length of rivet is an important part of the repair. Minimum rivet diameter is equal to the thickness of the thickest sheet to be riveted.

Maintain the original strength. Attach the doubler to the part with clamps and drill holes. When repair of a damaged part is possible first study the part carefully to fully understand its purpose or function. September 1994 subcourse overview this subcourse is designed to provide you with a general familiarization of the airframe of today s aircraft and repair procedures.

Sometimes the experience to achieve the desirable results can be costly. The art of sheet metal repair. The patch plate should have a cross sectional area equal to or greater than that of the original damage. Control parts wing covering or similar parts of the aircraft.

The diameter will depend on the number of rows of rivets you re planning on installing. The repair data may also be used as approved data and the ac chapter page and paragraph listed in block 8 of faa form 337 when. It is directly applicable to the repair being made. Cut out a circular patch from a sheet of aluminum that is the same thickness and the original aircraft skin.

Maintain the original strength. Fabricate a doubler of the same material but one size thicker than the part being repaired.