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gives a typical curing process.
Detail Steps/Work Items Key Items/References
(1) Maintain the temperature of the repair at 20 to
25 °C (68 to 77 °F) for at least 24 hours to precure
the repair.
If you do not have an oven or a
warming room you can make a
temporary enclosure around the repair
to trap the heat from a flame proof air
heater.
CAUTION: DO NOT ALLOW A TOO HIGH TEMPERATURE DURING THE CURE.
A TOO HIGH TEMPERATURE CAN DAMAGE THE COMPOSITE
STRUCTURE.
(2) After 24 hours raise the temperature of the repair
to at least 65 °C (149 °F) for a minimum of 6
hours to complete the first stage of the post-cure.
Monitor the temperature every 15
minutes for the first hour and then
hourly.
(3) After a minimum of 6 hours raise the temperature
of the repair to at least 80 °C (176 °F). Maintain
this temperature for a minimum of 14 hours to
complete the final post-cure.
The final stage post-cure time can be
divided into sections but you must make
sure that the repair has a minimum total
of 14 hours at post-cure temperature.
AIRCRAFT
Standard Practices and
Structures
DA 40 Series
AMM
Page 208
20 Sep 2007 51-20-00 Doc # 6.02.01
Rev. 5
Zone 1
Zone 1a
Zone 2
Zone 3
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Figure 1: Paint Color Scheme
AIRCRAFT
DA 40 Series
AMM
Standard Practices and
Structures
Doc # 6.02.01
Rev. 5 51-20-00 Page 209
20 Sep 2007
8. Exterior Paint Finish
A. Paint Color Scheme
CAUTION: YOU MUST PAINT THE AIRPLANE TO THE PAINT COLOR SCHEME. IF
YOU DO NOT PAINT THE AIRPLANE TO THE PAINT COLOR SCHEME,
YOU MAY CAUSE DAMAGE TO THE AIRPLANE STRUCTURE.
Since full strength of the fiber composite structure has only been shown up to a temperature of
% 54 EC (129 EF), the outer surface of the airplane must be painted white in accordance with
% Chapter 04 of this manual.
Exceptions are registration markings and warning marks, which are subject to the following
restrictions (refer to Figure 1):
% ) Zone 1 No registration markings or warning markings may be applied here, except for the
% placards in accordance with Section 11-20.
% ) Zone 1a This zone has the same restrictions as Zone 1, except that registration marks may be
% applied here which comply with the restrictions of Zone 2.
% ) Zone 2 Registration markings and warning markings may be applied here. They may be any
% shape and color, provided that the average absorption coefficient of each area measuring
% 200 mm by 200 mm (8" by 8") does not exceed 0.5. Examples which meet this criterion
% are:
% • Registration markings and warning markings of any shape, provided that colors with a
% solar absorptivity not exceeding 0.5 (e.g. light yellow or light green) are used.
% • Registration markings and warning markings of any color, provided that no area
% measuring 200 mm by 200 mm (8" by 8") is covered by more than 50%. One
% consequence is that the width of decoration stripes must not exceed 100 mm (4").
% ) Zone 3 Registration markings and warning markings of any shape and color may be applied here
% without restrictions.
AIRCRAFT
Standard Practices and
Structures
DA 40 Series
AMM
Page 210
20 Sep 2007 51-20-00 Doc # 6.02.01
Rev. 5
Figure 2: Scarfing the Paint Coat
AIRCRAFT
DA 40 Series
AMM
Standard Practices and
Structures
Doc # 6.02.01
Rev. 5 51-20-00 Page 211
20 Sep 2007
B. Painting a Large Repair Area
Refer to Figure 2. This procedure must be followed when the diameter of the area which must be
painted is larger than 200 mm (8 inches).
Detail Steps/Work Items Key Items/References
(1) Carefully scarf the edges of the existing paint
finish.
Do not sand through the existing antistatic
filler.
Minimum scarf length: 25 mm (1 inch).
To ensure that the anti-static filler of the
existing paint is electrically connected
to the anti-static filler of the new paint.
WARNING: DO NOT GET ACETONE, FILLER, OR PAINT ON YOUR SKIN.
ACETONE, FILLER, AND PAINT CAN CAUSE SKIN DISEASE.
WARNING: DO NOT BREATHE ACETONE, FILLER, OR PAINT FUMES.
ACETONE, FILLER, AND PAINT FUMES CAN CAUSE DISEASE.
CAUTION: THERE MUST BE NO GREASE OR DUST ON THE REPAIR AREA.
　
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