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AIRCRAFT
Standard Practices and
Structures
DA 40 Series
AMM
Page 6
20 Sep 2007 51-30-00 Doc # 6.02.01
Rev. 5
I. Fire Retardant Paint
(1) Courtaulds
Fire retardant paint : Courtaulds Aerospace N 56582/T508 (white)
Finishing varnish : Courtaulds Aerospace 4232-0303
Hardener : Courtaulds Aerospace N 39/1327 (4:1)
Supplier : PRO-DeSoto Deutschland GmbH
Aerospace Coatings
Lauenburger Landstr. 11
D-21039 Börnsen, Germany
Phone : +49-40-742193-10
Fax : +49-40-742139-69
(2) Hensel
Fire retardant paint : Hensotherm 2 KS (white)
Coating paint : Hensotop 84 f
Supplier : Rudolf Hensel GmbH
Lack- und Farbenfabrik
Süderstraße 235
D-20537 Hamburg, Germany
Phone :+49-40-214093
Fax :+49-40-214783
J. Acrylic Glass Cement
Acrylic glass cement : Polymerization cement Acrifix 92
Manufacturer : Röhm, Darmstadt, Germany
Supplier : Röhm Austria GmbH (see above)
AIRCRAFT
DA 40 Series
AMM
Standard Practices and
Structures
Doc # 6.02.01
Rev. 5 51-40-00 Page 1
20 Sep 2007
Section 51-40
Fasteners
1. General
This Section tells you about the fasteners used to attach panels and cowlings.
2. Description
The DA 40 has 2 main types of fastener. It has quick release cam-lock fasteners for panels which you
remove often, for example, engine cowlings, and screws for all the other access panels.
Figure 1 shows the quick-release cam-lock fastener. The fastener has 3 parts, a receptacle with a cam
track, a grommet and a stud. Rivets attach the receptacle to the airplane structure. A spring ring
attaches the stud assembly to the access panel and a compression spring holds the stud in the stud
assembly.
The T shaped end of the stud locates in a slot in the receptacle. When you turn the stud clockwise
through 90° it engages the cam track in the receptacle and pulls the access panel into position. When
the stud is turned fully 90° clockwise the T shaped end of the stud engages a small detent in the cam
track. The compression spring in the stud assembly holds the stud in position in the detent.
There are different length studs. Short studs for thin panels and longer studs for thicker panels. Not
all airplanes have the same length studs in the same position. This is because composite components
can vary in thickness.
If you replace a fastener, make sure that the new fastener has the correct length stud.
AIRCRAFT
Standard Practices and
Structures
DA 40 Series
AMM
Page 2
20 Sep 2007 51-40-00 Doc # 6.02.01
Rev. 5
Receptacle
Rivet
Spring Ring
Airplane Structure
Access Panel
Grommet
Stud
Figure 1: Quick Release Fastener
AIRCRAFT
DA 40 Series
AMM
Standard Practices and
Structures
Doc # 6.02.01
Rev. 1 51-40-00 Page 201
20 Sep 2007
Maintenance Practices
1. General
This Section tells you how to replace a quick release fastener stud in an access panel.
2. Replace a Quick Release Fastener Stud
A. Equipment
Item Quantity Part Number
Stud Pliers. 1 Camloc 4 P 3
B. Procedure
Detail Steps/Work Items Key Items/References
(1) Remove the damaged stud assembly:
S Turn the stud 90° counter-clockwise to
release it from the receptacle.
S Place the U jaw of the camloc pliers under
the rim of the stud assembly.
S Compress the stud assembly and remove it
from the grommet.
If fitted.
Refer to Figure 1.
Turn the stud assembly approximately
30° off axis.
(2) Install the new stud assembly:
S Select the correct length stud assembly.
S Put the stud assembly into the U jaw of the
camloc pliers.
S Compress the stud assembly with the camloc
pliers and install into the grommet.
S Engage the stud in the receptacle and turn
90° clockwise to lock the stud.
Turn the stud assembly approximately
30° off axis.
AIRCRAFT
Standard Practices and
Structures
DA 40 Series
AMM
Page 202
20 Sep 2007 51-40-00 Doc # 6.02.01
Rev. 5
Intentionally left blank
AIRCRAFT
DA 40 Series
AMM
Standard Practices and
Structures
Doc # 6.02.01
Rev. 5 51-60-00 Page 1
20 Sep 2007
Section 51-60
Control Surface Balancing
1. General
This Section tells you how to weigh and measure the residual moment of the control surfaces.
% WARNING: YOU MUST WEIGH AND BALANCE A CONTROL SURFACE AFTER ANY WORK
WHICH COULD AFFECT ITS WEIGHT OR ITS BALANCE. OUT OF BALANCE
CONTROL SURFACES CAN FLUTTER AND CAUSE STRUCTURAL FAILURE.
　
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