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DA 40 Series

Detail Steps/Work Items  Key Items/References 
(10)  Do a test transmission on COM 2 from the pilot station.  Make sure that: S The PTT button gives proper transmission on COM 2. S The COM 2 receiver can be heard. S The volume and squelch can be adjusted. 
(11)  Do a test transmission on COM 2 from the co-pilot station.  Make sure that: S The PTT button gives proper transmission on COM 2. S The COM 2 receiver can be heard. S The volume and squelch can be adjusted. 
(12)  Push the COM 1/2 button.  Make sure that: S The pilot can communicate on COM 1. S The co-pilot can communicate on COM 2. 
(13)  Select each receiver in turn using the selector buttons.  Make sure that: S The LED in the button comes on to show that it is in use. S Audio from each selected equipment connects to the head-sets. 
(14)  Push the SPKR button.  Make sure that: S The selected audio sources can be heard in the cabin speaker. 
(15)  Push the SENS button.  Make sure that: S The marker beacon intensity LED changes from HI to LO and from LO to HI. 
(16)  Rotate the left small knob fully counterclockwise. 
(17)  Do a test transmission on COM 1 from the pilot station. 

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Detail Steps/Work Items  Key Items/References 
(18)  Set the AVIONIC MASTER switch to OFF. 
(19)  Set the ALT/BAT switch (Lycoming version) or ELECTRIC MASTER key switch (TAE version) to OFF. 
(20)  Disconnect the head-sets from the head-set sockets. 

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Section 23-60
Static Discharging

1. General
The static discharging system has two main parts, the electrical bonding system and the surface static discharging system. Refer to Section 51-80 for the electrical bonding system. Section 51-80 also describes the resistance measurements for the static discharge wicks.
The build-up of static electricity can affect the quality of radio communications on all COM and NAV equipment. It can also affect the quality of all NAV indications.
2. Description and Operation
The static discharging system removes the electro-static charge which collects on the airplane surfaces. The composite structure of the DA 40 does not let electricity flow through it. The airplane surfaces are covered with a special conductive filler through which the electricity flows to the static discharge wick.
Location and quantity of the static discharge wicks are given in the following table.
Location  Quantity 
LH wing tip, trailing edge  2 
RH wing tip, trailing edge  2 
LH horizontal tail tip, trailing edge  1 
RH horizontal tail tip, trailing edge  1 
Rudder, trailing edge, bottom  1 

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CHAPTER 24
ELECTRICAL POWER

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Electrical Power
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TABLE OF CONTENTS
CHAPTER 24
ELECTRICAL POWER

Section 24-00 % Electrical Power - Lycoming Engine
1.
General ..............................................1

2.
Component Identification .................................5

3.
Component Location ....................................5
　
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