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and UV damage.
- Inspect the skin for delamination.
- Inspect for damage to the core or
disbond between the skin and the core.
- Inspect the ribs for bonding with the
skins.
x
25. Remove the flap push-rods and examine
them for damage. Look especially for rub
marks and excessive wear. The maximum
wear permitted is 0.127 mm (0.005 in).
Measure the amount of wear as follows:
- Take a measurement of the push-rod
diameter at the edge of the paint
- Take a measurement of the push-rod
diameter at the middle of the wear mark
- Compare the two measurements. If the
maximum wear permitted is exceeded,
replace the push-rod.
Install the pushrods.
x x
26. Remove and replace the flap hinge
hardware.
x
27. Examine the flap hinges and control horn.
Check the laminate around the hinges and
the control horn fasteners for cracks or
delamination.
Look especially for too much play.
Play allowed:
− Axial: ± 1.00 mm (± 0.04 in)
− Radial: ± 0.25 mm (± 0.01 in).
x x x x
28. Install the flaps back on the wings.
(Refer to Chapter 57-50).
x
Time Limits and
Maintenance Checks
DA20-C1 AMM
Page 36
30 Apr 2009 05-20-00 Doc # DA201-C1
Rev. 15
Interval (Flight Hours)
Inspection Items 50 100 200 1000 6000 Initials.
29. Remove the flap and aileron bellcrank
access panels in the wing (Refer to Chapter
52-40).
- Examine the aileron and flap control
system. Look especially for correct
attachment and lock devices
(Refer to Chapter 27-10 and 27-50).
- Install the access panels.
x x x x
30. Examine the pitot head. Look especially for
correct attachment.
x x x x
31. Examine the vent and drain holes in the
wings, fuselage and control surfaces.
Make sure that they are clear.
x x x x
32. Do a test for axial play in the B-bolts.
(Refer to Chapter 57-10).
x x x x
33. Do a visual inspection and a tap test of the
spar bridge.
- Examine the condition of the laminates
and the bond to the fuselage.
Look especially around:
- The LH and RH A-bolt bushing.
- The B-bolt bushing.
- The MLG brackets.
- The LH and RH top aft outer corners
(behind the back-rest).
Do a visual inspection of the inside spar
bridge.
(Refer to Chapter 51-00, Pg. 5, Item 6.A.)
x x
34. Do a visual inspection and a tap test.
Check for delamination of fuselage skin
outboard of the seat fastener through the
side of spar bridge.
x
DA20-C1 AMM
Time Limits and
Maintenance Checks
Doc # DA201-C1
Rev. 14 05-20-00 Page 37
30 Oct 2008
Interval (Flight Hours)
Inspection Items 50 100 200 1000 6000 Initials.
35. Remove the aileron push-rods and examine
them for damage. Look especially for rub
marks and excessive wear. The maximum
wear permitted is 0.254 mm (0.010 in).
Measure the amount of wear as follows:
- Take a measurement of the push-rod
diameter at the edge of the paint
- Take a measurement of the push-rod
diameter at the middle of the wear mark
- Compare the two measurements. If the
maximum wear permitted is exceeded,
replace the push-rod.
Install the aileron push-rods.
(Refer to Chapter 27-10).
x x
36. Visually examine the main pin bushing in the
spar stump.
Replace the main pin bushing if it is
damaged.
x
37. Visually examine the main pin bushing in the
spar bridge.
Replace the main pin bushing if it is
damaged.
x
38. Install the wings.
(Refer to Chapter 57-10).
x x
Time Limits and
Maintenance Checks
DA20-C1 AMM
Page 38
30 Oct 2008 05-20-00 Doc # DA201-C1
Rev. 14
H. General
All items performed, the findings, as well as their correction must be recorded in accordance with
an approved procedures manual. Contact Diamond Aircraft if damages are determined which
cannot be repaired in accordance with an approved procedures manual.
Interval (Flight Hours)
Inspection Items 50 100 200 1000 6000 Initials.
1. Examine the pitot-static system. Look
especially for leaks.
− Do a low-range static leak test
(Refer to Chapter 34-10).
− Do a pitot test
(Refer to Chapter 34-10).
− Make sure the pitot-static system is
clean.
x x
2. Perform a functional check of the pitot static
heat system (if installed).
Inspection Interval;
1000 hrs. or 12 months, whichever
comes first.
Refer to chapter 34-10
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