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(18)  Adjust the E/W potentiometer on the slaving control unit to zero the external digital millivolt meter.  Use a non-magnetic blade screwdriver. (0 volts DC ± 50 millivolts). 
(19)  Set the slaving control to SLAVE. 
(20)  Align the airplane on each of the cardinal headings in turn.  The error between the compass card on the HSI and the external reference compass must be less than ±2o. 
(21)  Set all airplane electrical systems to OFF. 
(22)  Remove the digital millivolt meter. 
(23)  Install the slaving control unit in the instrument panel: S Push the slaving control unit into position in the panel. S Install 2 attaching screws. 

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Section 34-30
Landing and Taxiing Aids

1. General
This Section tells you about the landing and taxiing aids that can be installed in the DA 40.
Refer to the equipment manufacturers' manuals for more data about other options of landing and taxiing aids.
2. Description
The DA 40 can have the following landing and taxiing aids:
) A localizer system which is part of the VOR/LOC/GS system. Refer to Section 34-52 for more data about the VOR/LOC/GS system.
) A glideslope system which is part of the VOR/LOC/GS system. Refer to Section 34-52 for more data about the VOR/LOC/GS system.
) A marker beacon receiver which is part of the audio integrating system. Refer to Section 23-50 for more data about the marker beacon receiver functions of the audio integrating system.
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% % % % %  1. General  Section 34-40 Independent Position Determining 
% %  This Section tells you about the independent position determining systems that can be installed in the DA 40. Refer to these Sections for data about the systems: 
%  Section 34-42  Strike Finder System 
%  Section 34-45  Stormscope System 

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% 
%  Section 34-42 
%  Strike Finder System 
% 
%  1. General 

% This Section tells you about the strike finder system that can be installed in the DA 40. Refer to the % manufacturer′s manual for more data about the equipment. Refer to Chapter 92 for the wiring % diagrams.
% The strike finder system consists of the following items:
%) Strike finder display.
%) Strike finder sensor.
% 2. Description and Operation
% The strike finder detects and analyzes the electrical activity emanating from thunderstorms within a % 200 nautical mile (nm) radius of the airplane.
% The Insight strike finder SF 2000 consists of a display and a sensor. The display employs a digital % signal processor which, among other components, processes and displays the signal detected by the % sensor.
% A. Strike Finder Display
% Figure 1 shows the Insight strike finder display. It is located on the left side of the avionics rack in % the instrument panel, see Chapter 31.
% The avionics bus supplies power to the strike finder display. The ALT/BAT switch and the AVIONIC % MASTER switch must be set to ON to supply power through the STRIKE circuit breaker to the % strike finder display. Refer to Chapter 92 for the wiring diagrams.
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%  Figure 1: Insight Strike Finder, SF 2000 
% 
%  The strike finder display has these controls and displays: 
%  ) 30-degree Azimuth Marker - helps to identify the location of thunderstorms relative to the 
　
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