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DA 40 Series
Detail Steps/Work Items Key Items/References
(13) Do an inspection of the flap controls which you have connected or adjusted. S If necessary for your airworthiness authority, do a second inspection of the controls.
(14) Do a test for correct operation and range of movement of the aileron system. If necessary, adjust the aileron system. Refer to Section 27-10.
(15) Do an inspection of the aileron controls which you have connected or adjusted. S If necessary for your airworthiness authority, do a second inspection of the controls.
(16) Do a functional check of these lights: S Navigation lights. S Strobe lights (ACL's). S Taxi light. S Landing light. Refer to Section 33-40. Left wing only. Left wing only.
(17) Do a functional check of the Pitot heating system. Left wing only. Refer to Section 34-10.
(18) Do a Pitot and static system leak test. Left wing only. Refer to Section 34-10.
(19) Refuel the airplane to the unusable fuel level. Refer to Section 12-10.
(20) Do a fuel quantity indication calibration check. Lycoming version only. Refer to Section 28-40.
(21) Install these items after access: S The left/right pilots’ seats. S Main landing gear access panel. S Center section rear access panel. S Inboard fuel tank access panel. As necessary. Refer to Section 25-10.
(22) Do an air test. Refer to the DA 40 Airplane Flight Manual.
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3. Remove/Install the A or B-Bolts
A. Remove the A or B-Bolts
Detail Steps/Work Items Key Items/References
(1) Remove the wing Refer to Paragraph 2.
(2) Remove the A or B bolt: S Hold the flats on the flange of the bolt with a wrench. S Remove the self-locking nut from the A or B-bolt. S Remove the A or B-bolt. Refer to Figure 4. Access for the A-bolt through the hole in the front root rib. Access for the B-bolt through the access panel in the bottom shell.
Front Root Rib
Access Hole
Bonded Bush A-Bolt
Rear Root Rib
Bonded Bush
Access B-Bolt Panel
RIGHT SHOWN LEFT OPPOSITE
Figure 4: A and B-Bolt Installation
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B. Install the A or B-Bolts
DA 40 Series
Detail Steps/Work Items Key Items/References
(1) Examine the A or B-bolt. Look specially for: S Corrosion. S Scratches on the bearing surfaces. S Deformation. S Damage to the threads. No corrosion permitted. Maximum depth 0.1 mm (0.004 in). No deformation permitted. No damage permitted.
(2) Examine the A or B-bolt bush. Look specially for: S Looseness between the A or B-bolt bush and the root rib. S Damage to the root rib where the bush attaches. S Damage to the bush.
(3) Install the A or B-bolt: S Install the bolt in the bush. S Hold the flats on the flange of the bolt with a wrench. S Install the washer and self-locking nut. Refer to Figure 4. Access for the A-bolt through the hole in the front root rib. Access for the B-bolt through the access panel in the bottom shell. Torque: 32 Nm (23.6 ft.lb).
(4) Install the wing. Refer to Paragraph 2.
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LEFT SHOWN RIGHT OPPOSITE
Figure 5: Control Surface Hinge Bracket Installation
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4. Remove/Install Control Surface Hinge Brackets 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：钻石40飞机维护手册 DA 40 SERIES AMM 4(69)
