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system is operative.
(5) Install the co-pilot's seat. Refer to Section 25-10.
AIRCRAFT
Auto Flight DA 40 Series
AMM
Page 210
20 Sep 2007 22-10-00 Doc # 6.02.01
Rev. 5
8. Remove/Install the Pitch Trim Servo Clutch
A. Remove the Pitch Trim Servo Clutch
Detail Steps/Work Items Key Items/References
CAUTION: DO NOT APPLY STRONG FORCES TO THE CARDAN SHAFT. THE UPPER
CARDAN JOINT CONNECTS TO A PART WHICH IS WEAK BY DESIGN TO GIVE
OCCUPANT PROTECTION IN AN EMERGENCY LANDING.
(1) Remove the pitch trim servo. Refer to Paragraph 7.
(2) Remove the screw which holds the cap to the
capstan.
(3) Remove the cap from the capstan.
(4) Release chain tension with chain adjuster. On the chain gear next to the servo.
(5) Remove the chain from the chain gear.
(6) Remove the 2 screws which attach the clutch and
the chain adjuster to the mounting plate.
Hold the clutch and the chain adjuster.
(7) Remove the clutch and the chain adjuster.
B. Install the Pitch Trim Servo Clutch
Detail Steps/Work Items Key Items/References
(1) Put the clutch and the chain adjuster in place on
the mounting plate.
(2) Install the 2 screws which attach the clutch and
the chain adjuster to the mounting plate.
(3) Install the chain to the chain gear.
(4) Put the cap in place on the capstan.
(5) Install the screw which holds the cap to the
capstan.
(6) Install the pitch trim servo. Refer to Paragraph 7.
AIRCRAFT
DA 40 Series
AMM
Auto Flight
Doc # 6.02.01
Rev. 5 22-10-00 Page 211
20 Sep 2007
9. Adjust the Bridle Cable Tension
A. Equipment
Item Quantity Part Number
Cable tension gauge. 1 Commercial.
B. Adjustment Procedure
Detail Steps/Work Items Key Items/References
(1) Loosen the bolts in the clamps which connect the
bridle cable to the push-rod.
Do not remove the bolts. Loosen just
enough so that the next step can be
done.
(2) Using a small plastic hammer, move the clamps
along the push-rod to adjust the bridle cable
tension.
Adjust tension to 89 ± 22 N (20 ± 5 lb).
Measure cable tension with cable
tension gauge.
(3) Tighten the bolts in the clamps which connect the
bridle cable to the push-rod.
AIRCRAFT
Auto Flight DA 40 Series
AMM
Page 212
20 Sep 2007 22-10-00 Doc # 6.02.01
Rev. 5
10. Adjust the Clutch Torques
A. Equipment
Item Quantity Part Number
% Goodrich Slip Clutch Test Stand. 1 Goodrich 20-9855-03
B. Adjustment Procedure
Detail Steps/Work Items Key Items/References
% (1) Remove the clutch from the airplane. Refer to Section 22-10 of the AMM.
(2) Install the clutch assembly on the slip clutch test
stand.
Refer to the equipment manufacturers'
documentation.
(3) Measure clockwise (CW) and counter-clockwise
(CCW) clutch torque, adjust if necessary.
Refer to the equipment manufacturers'
documentation.
The correct clutch torques are:
% Roll servo 2.03 ± 0.23 Nm
% (18 ± 2 in.lb)
% Pitch servo 3.39 ± 0.34 Nm
% (30 ± 3 in.lb)
Pitch trim servo 4.07 ± 0.45 Nm
(36 ± 4 in.lb)
(4) Remove the clutch assembly from the slip clutch
test stand.
% (5) Install the clutch to the airplane. Refer to Section 22-10 of the AMM.
AIRCRAFT
DA 40 Series
AMM
Auto Flight
Doc # 6.02.01
Rev. 5 22-10-00 Page 213
20 Sep 2007
11. Mechanical Check of the Autopilot System
Do this check at the intervals given in Section 05-10.
Detail Steps/Work Items Key Items/References
(1) Check bridle cable tension for the roll servo,
adjust if necessary.
Refer to this Section.
(2) Check bridle cable tension for the pitch servo,
adjust if necessary.
Refer to this Section.
(3) Check the clutch torque settings for the roll servo,
adjust if necessary.
Refer to this Section.
(4) Check the clutch torque settings for the pitch
servo, adjust if necessary.
Refer to this Section.
(5) Check the clutch torque settings for the pitch trim
servo, adjust if necessary.
Refer to this Section.
(6) Perform Pitot and static system leak tests. Refer to Section 34-10.
AIRCRAFT
Auto Flight DA 40 Series
AMM
Page 214
20 Sep 2007 22-10-00 Doc # 6.02.01
Rev. 5
Intentionally left blank
AIRCRAFT
DA 40 Series
AMM
Communications
Doc # 6.02.01
Rev. 5 23-TITLE Page 1
20 Sep 2007
CHAPTER 23
COMMUNICATIONS
AIRCRAFT
Communications DA 40 Series
AMM
Page 2
　
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