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large enough to insert a jigsaw.
(3) Cut out window all around 20mm (3/4 in) from
inner edge of fuselage bonding flange.
(4) Separate the remaining acrylic from fuselage
using a sharp blade or chisel and remove it.
Do not damage surrounding composite
structure.
(5) Carefully grind or sand away any remaining
adhesive from the bonding flange on the
fuselage.
Use extreme care not to damage the
surrounding composite or the bonding
flange.
CAUTION: KEEP BONDING SURFACES CLEAN FROM OIL, DIRT, AND
OTHER CONTAMINANTS.
WEAR GLOVES, RESPIRATOR, AND EYE PROTECTION WHEN
HANDLING RESIN, CLEANER, AND ADHESIVE.
(6) Vacuum the frame and surrounding areas to
remove any dust and debris.
(7) Glue small rubber shims using Loctite 495
around the circumference of the flange to bring
the glass flush to the fuselage skin.
There are approximately 16 shims used
on the right hand window and 19 shims
used on the left hand window.
(8) Pre-fit the acrylic window to the fuselage to
ensure that it is correctly trimmed. There
should be 3 mm (+/- 1 mm) gap between the
edge of the glass and the edge of the recessed
frame.
See Fig. 1
(9) Centre the window vertically and horizontally to
get even gaps all around.
DA20-C1 AMM
Windows
Doc # DA 201-C1
Rev. 15 56-11-00 Page 3
30 Apr 2009
Figure 1. Acceptable Fuselage and Glass Window Gap
Detail Steps/Work Items Key Items
(10) Put match marks on the window and fuselage
at the front, rear, top and bottom to allow
alignment during bonding.
(11) Remove all dust and debris from the bonding
surfaces.
(12) Clean the bonding surfaces of the fuselage
and window with cleaner Prekleeno 900 using
two paper towels, one wet, and one dry.
Always move in one direction around the
perimeter of the bonding area. Turn the cloth
several times to avoid the transfer of dirt.
Use the wipe on wet/wipe off dry
method.
(13) Allow 20-30 minutes minimum for the cleaned
areas to dry.
Allow longer dry times in cooler and/or
humid conditions.
(14) Inspect for proper cleaning.
(15) Apply adhesive Methacrylate MA925 to the
fuselage bonding flange. Apply one
continuous bead.
Make sure the bead cover most of the
bonding flange.
(16) Install the window on the fuselage immediately. Pot lifetime for adhesive Methacrylate
MA925 is 10 minutes.
(17) Move the window to align the marks and to
make the contour of the acrylic match that of
the fuselage as closely as possible.
Avoid excess local pressure as this can
lead to a wavy surface.
(18) Inspect for voids and for proper bond line.
(19) Remove excess adhesive from gap between
edge of acrylic and fuselage on the outside
and at edge of bonding flange on the inside.
(20) Apply enough flash tape to the exterior to
provide an even and constant pressure.
Windows
DA20-C1 AMM
Page 4
30 Apr 2009 56-11-00 Doc # DA 201-C1
Rev. 15
Detail Steps/Work Items Key Items
(21) Allow adhesive to cure for a minimum of 12
hours.
(22) Inspect the window for any unbonded and/or
voided areas or waviness.
(23) Remove internal masking tape and external
flashing tape.
(24) Using fresh low residue masking or flash tape,
mask off window edges and fuselage edges
around gap.
(25) Fill gap between window and fuselage with
black paintable exterior acrylic caulk (PF224,
black sealant)
Remove the excess black sealant with
plastic scraper or spatula.
(26) Allow the caulk to cure overnight.
(27) Remove masking or flash tape.
(28) Mask off fuselage and window in preparation
for paint application. Paint to original line on
fuselage and extend paint line to cover frame
line on window. See Figure 2.
Figure 2. Paint Dimension on Glass Window
DA20-C1 AMM
Wings
Doc # DA201-C1
Rev. 0 57-TITLE Page 1
19 Dec 1997
CHAPTER 57
WINGS
Wings
DA20-C1 AMM
Page 2
19 Dec 1997 57-TITLE Doc # DA201-C1
Rev. 0
Intentionally left blank
DA20-C1 AMM
Wings
Doc # DA201-C1
Rev. 0 57-CONTENTS Page 1
19 Dec 1997
TABLE OF CONTENTS
CHAPTER 57-00 WINGS - GENERAL .....................................................................................................1
1. General .............................................................................................................................1
CHAPTER 57-10 WING STRUCTURE.....................................................................................................1
　
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