23-10-00
AMM

6. Remove/Install the NAV (VOR/LOC/GS) Antenna
The NAV (VOR/LOC/GS) antenna is integral to the horizontal stabilizer. Refer to Diamond for data on the NAV antenna.
7. Remove/Install the NAV Antenna Coupler
A. Remove the NAV Antenna Coupler
Detail Steps/Work Items  Key Items/References 
(1)  Remove the instrument panel cover.  Refer to Section 25-10. 
(2)  Dis-connect the connectors from the unit. 
(3)  Remove the screws which attach the unit to the bracket on the instrument panel floor. 
(4)  Remove the unit from the airplane. 

B. Install the NAV Antenna Coupler
Detail Steps/Work Items  Key Items/References 
(1)  Put the unit in place on the bracket on the instrument panel floor. 
(2)  Install the screws which attach the unit to the bracket. 
(3)  Connect the connectors at the unit. 
(4)  Install the instrument panel cover.  Refer to Section 25-10. 

Page 210 Doc # 6.02.01 09 Jan 2003 Rev. 4
23-10-00
Communications
AMM

8. NAV/COM Test
If possible, do an operational flight check after the radio has been replaced. Alternatively use a % NAV/COM test set to make sure that the system operates correctly. Refer to the manufacturer's Installation Manual for performance specifications.
Detail Steps/Work Items  Key Items/References 
(1)  Do a test of each control function.  Refer to Section 23-10 and Section 34-52. 
(2)  At a sufficient altitude, contact a ground station at least 50 NM away and another close by.  If possible, select stations with frequencies at both the high and low end of the NAV/COM band. 
(3)  Test the VOR system at 4000 ft. Select a VOR frequency within a 40 NM range. Listen to the station identifier. Test the operation of the tone identifier filter. Fly inbound and outbound on a selected VOR radial. Look for the correct LEFT/RIGHT and TO/FROM indications. Monitor the VOR accuracy. 
(4)  Do a test of the DME remote channeling.  If installed. 
(5)  Do a test of localizer (LOC) and glideslope (GS) operation and accuracy on a suitable runway. 
(6)  If necessary, adjust the viewing contrast of the LCD display.  Through the access hole in the front panel. 

Doc # 6.02.01 Page 211
Rev. 4 09 Jan 2003

23-10-00
AMM

Intentionally left blank
23-10-00
Communications
AMM

Section 23-50
Audio Integrating

1. General
The audio system in the DA 40 has the following components: ) Audio panel. One of the following audio panels can be installed in the DA 40: ) PM 1000 II voice-activated (VOX) intercom, see Figure 1. ) Bendix/King KMA 28 audio amplifier with voice-activated (VOX) intercom, see Figure 2. This unit also includes a marker beacon receiver. %) Garmin GMA 340 audio amplifier with voice activated (VOX) intercom, see Figure 3. This unit % also includes a marker beacon receiver. ) Sockets for 4 head-sets on the rear face of the center console. ) Press-to-transmit (PTT) switches in the handles of both control sticks. ) Cockpit speaker in the roof of the cockpit. %) Socket for hand-held microphone on the bottom left side, or bottom center of the instrument panel.
The voice-activated intercom gives full hands-free intercom when head-sets are used.
Doc # 6.02.01 Page 1
Rev. 4 09 Jan 2003

23-50-00
AMM

Figure 1: PM 1000 II Intercom
23-50-00
Communications
AMM

2. Description
A. PM 1000 II Intercom
Figure 1 shows the PM 1000 II Intercom. It is mounted above the NAV/COM 1 set in the avionics % rack in the instrument panel, see Chapter 31.
The PM 1000 II is a four channel VOX intercom with individual amplifiers for each outlet. The head-set jack-plugs connect to the PM 1000 II. When the unit is set to OFF (or when the power fails), an internal relay connects the pilots head set to the airplane radio. This gives fail-safe operation. A 2-color LED in the control panel shows green when the power is on and red during radio transmissions. The LED functions as stuck mic indicator.
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：鉆石40飛機維護手冊 DA 40 SERIES AMM 2(34)