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Note: Do inspection items 3 through 10 while the rudder, the fairing for the horizontal stabilizer, and the horizontal tail tips are removed. 
3.  Remove the horizontal stabilizer. Refer to Section 55-10. 
4.  Inspect the inner skin of the horizontal stabilizer through all access holes with mirror and flashlight. Check for damage, cracks, and delamination. Refer to Section 55-10. 
5.  Inspect the interior structure of the horizontal stabilizer through all access holes with mirror and flashlight. Check for damage, cracks, delamination and disbonding from the horizontal tail skin. Look specially at these components: S Front spar. S Rear spar. S Trailing edge web. S All interior ribs & stiffeners. S Structure next to holes for mounting brackets. Refer to Section 55-10. 
6.  Inspect the inner skin of the vertical stabilizer through all access holes with mirror and flashlight. Check for damage, cracks, and delamination. Refer to Section 53-10. 
7.  Inspect the interior structure of the vertical stabilizer through all access holes with mirror and flashlight. Check for damage, cracks, delamination and disbonding from the horizontal tail skin. Look specially at these components: S Front web. S Rear web. S Lower rib (front & rear). S Structure next to holes for horizontal tail mounting brackets. Refer to Section 53-10. 
8.  Inspect the inner skin of the rear fuselage through all access holes with mirror and flashlight. Check for damage, cracks, delamination and disbonding from the sandwich foam. Refer to Section 53-10. 

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Inspection Items  Initials 
9.  Inspect the interior structure of rear fuselage through all access holes with mirror and flashlight. Check for damage, cracks, delamination and disbonding from the fuselage skin. Look specially at these components: S Ring frames 1, 2, and 3. Refer to Section 53-10. 
10.  Install the horizontal tail. Refer to Section 55-10. 
11.  Do a coin-tap test for delamination of the fuselage shell. 
12.  Do a coin-tap dest for delamination of the center section top and bottom shells. 
13.  Complete the Findings Report (2 pages). Record the following: S Defects found during the 2000 Hour Structural Check. S Structural defects found during the associated 1000 hour inspection. S All structural defects that were detected and repaired since new or since the last 2000 Hour Structural Check. 
14.  Send a copy of the completed Findings Report (2 pages) to the manufacturer, i.e., Diamond Aircraft Industries GmbH Office of Airworthiness N.A. Otto-Str. 5 A-2700 Wiener Neustadt Austria by mail, fax (+43-2622-26780) or e-mail (airworthiness@diamond-air.at). Note: The manufacturer will use the completed Findings Reports for the continous improvement of the checklist for the 2000 Hour Structural Check. 

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FINDINGS REPORT DA 40 AT 2000 HOURS STRUCTURAL CHECK 
Registration :  __________________  Date : _______________ 
Airplane S/N  : _________________  Airplane Operating Hours : _______________ 
Maintenance Organization:  AMM Rev. used for check : _______________ 
　
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