Fastener Installation And Removal - Cessna 510 Mustang Structural Repair Manual

1. Tools and Materials
NAME
Isopropyl Alcohol
Color Chemical Film
Treatment
Adhesive
Adhesive
Methyl n-Propyl Ketone
2. Solid Shank Rivets
A. General.
(1) The solid shank rivets, in general, used on this airplane are made from 2117 aluminum alloy. In some locations, rivets
made from 5056 aluminum alloy, titanium, or monel are used.
(2) Rivets made from 5056 and 2117 aluminum alloy can be stored and used at room temperature.
B. Installation.
(1) Solid rivets can be installed by the use of a rivet gun and bucking bar or a suitable squeeze riveting tool. Rivet guns
and bucking bars must be large enough to drive the rivets quickly. A driving duration of three to four seconds is the
optimum, while seven seconds must be the maximum. Bucking bars must be very smooth when driving aluminum
alloy rivets. Refer to Hole Size and Edge Distance in this chapter for hole sizes.
(2) Table 1, Table 2 and Table 3 show the grip ranges, shank projection before driving, and the driven head sizes for
solid shank rivets used in nonfluid tight applications.
(3) Cracked Driven Heads.
(a) Cracks in driven heads are undesirable and must be kept to a minimum.
(b) Cracks on the sides of driven heads which run at a 45-degree angle to the flat surface of the head are caused by
upsetting the rivet material beyond the limit of its ductility. Diagonal cracks must be evaluated as follows:
1 Hairline or superficial cracks are allowable in all cases, regardless of their numbers. Intersecting superficial
cracks are also acceptable.
2 Rivets with diagonal cracks which do not intersect are acceptable. The maximum number must be three.
3 Rivets with severe cracks are not acceptable and must be replaced.
(c) There are two types of vertical cracks: one caused by a lap in rivet wire, and the other caused by over heat-
treating the rivets. It is very important to distinguish between these two types.
1 Cracks due to lap in rivet wire are rare. The surface exposed by the cracks will be smooth and dull in
appearance and will be only a few thousandths of an inch deep (0.005 to 0.015 inch (0.13 to 0.38 mm)).
These cracks are permitted.
2 When cracks from overheating appear, they are usually found in a large percentage of the rivets being
driven. This cracking is due to excessive temperatures being reached during the heat-treatment of the rivet.
Copyright © Textron Aviation Inc.
Retain printed data for historical reference only. For future maintenance, use only current data.

FASTENER INSTALLATION AND REMOVAL

NUMBER MANUFACTURER
TT-I-735 Commercially Available
Alodine 1000 Henkel Surface Technologies
32100 Stephenson Highway
Madison Heights, MI 48071
Pliogrip 7779 Ashland Chemical Company - Foundry
Urethane Products Division
3M DP820 Minnesota Mining and Manufacturing
Company
Adhesive Coatings and Sealers Division -
3M
3M Center
St. Paul, Minnesota 55144
Eastman Chemical Company
Kingsport, TN 37662
FOR TRAINING PURPOSES ONLY
ISSUE 02 , JAN 2018
Model 510 Structural Repair Manual (Rev 2)
51-40-03-0 (Rev 1)
USE
Cleaning Solvent
Protective treatment of
aluminum.
Installation of Click Bond
adhesive nutplates
Installation of Click Bond
adhesive nutplates
To remove unwanted adhesive
during adhesive nutplate
installation
Print Date: Wed Mar 21 05:10:19 CDT 2018
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