SD3-60 AIRCRAFT MAINTENANCE MANUAL - DESCRIPTION & OPERATION (PRE-MOD A8062)

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1 SD3-60 AIRCRAFT MAINTENANCE MANUAL z AMM ADF SYSTEM - DESCRIPTION & OPERATION (PRE-MOD A8062) 1. Description The ADF system provides radio signal reception in the frequency range 190 KHz to KHz and is used in conjunction with: - the gyro compass system. Refer to , pb1. - the VOR/ILS/Marker beacon system. Refer to , pb1. to provide headings relative to the ADF station being received. An audio output is also provided for use by the audio system. Refer to , pb1. The system has a number of different, but related, modes of operation and includes a self-test facility. The basic aircraft has one ADF system, but a second is available as a special order only and is identical in operation to the basic system. A. Detail (1) Receiver. Collins type ADF-60A (Part number ). The unit, idented 1RD1, is located in the No.3 avionics bay. The received signal is used by the receiver to provide two outputs. One is the transmitter station bearing which is fed to both VOR/ILS/Marker beacon RMI's to provide relative bearings. The second is an audio output which is fed to the audio system for identification of the transmitter station. (2) Controller, Collins type CTL-60 (Part number ). Refer to Figure 1. The CTL-60 ADF controller comprises all the controls and indications necessary for the system management. These are as follows:- (a) Active and preselected frequency displays (b) Active/preselect switch (ACT/PRE) (c) Frequency select knobs (d) Function switch (OFF/ANT/ADF/TONE) (e) TUNE button (f) TEST button The controller, idented 'F', is mounted on panel 2P. Page 1 Jan 31/12

2 z SD3-60 AIRCRAFT MAINTENANCE MANUAL (3) Antenna, Collins type ANT-60A (Part number ). The antenna is an integrated loop and sense antenna mounted on the underside of the aircraft at Stn and is idented 1RD3. (4) No.2 ADF, if fitted. The units of the No.2 ADF system have been allocated the following locations and idents. (a) ADF-60A receiver; No.4 avionics bay, idented 2RD1. (b) CTL-60 controller; adjacent to No.1CTL-60 on panel 2P, idented 'Z'. (c) ANT-60A antenna; on underside of aircraft at Stn.210.2, idented 2RD3. 2. Operation The ADF system is provided with 28V D.C. operating power via C/B No.405 on distribution panel 5D (C/B No.435 on distribution panel 6D is allocated to the No.2 ADF system when fitted). The power is connected to the CTL-60 which in turn supplies the rest of the system. The controls and indications provided on the CTL-60 are operational as follows:- A. Active and preselected frequency displays. These provide indication of the frequency currently being used, the active frequency, and a second frequency which has been preselected and set into the controller ready for use. The top display is the active frequency and the bottom display is the preselected frequency. B. Active/preselect switch When set to ACT, the active frequency can be adjusted by the frequency select knobs, and when set to PRE, the preselected frequency can be adjusted by the frequency select knobs. C. Frequency select knobs Two concentric knobs are provided. The larger knob controls the two left hand digits and the smaller knob controls the three right hand digits. The two left hand digits cease changing at the frequency limits although the knob continues to turn. The three right hand digits have frequency roll over and also variable rate tuning, i.e. the faster the smaller knob is turned the more digits per click will be obtained as opposed to the one-digit-per-click rate. D. Function switch The function switch has four positions:- OFF, ANT, ADF and TONE. (1) In the OFF position the system is de-energised. Page 2

3 SD3-60 AIRCRAFT MAINTENANCE MANUAL z (2) In the ANT position the audio output is active, enabling identification of the station but no directional information is supplied and therefore the VOR/ILS/Marker beacon RMI pointers will remain parked. (3) In the ADF position both aduio and directional information are available. (4) In the TONE position both audio and directional information are available but in addition a 1KHz tone identifies keyed CW stations. E. TUNE button When the tune button is pressed it immediately transfers the active and preselected frequencies. The preselected frequency therefore becomes the active frequency and is displayed as the top display and vice versa. F. TEST button When the test button is pressed the system self test is initiated. G. Volume control (V) 3. Self Test This controls the audio volume. When the system self test in initiated by pressing the CTL-60 TEST button the VOR/ILS/Marker beacon RMI pointers will change 90 and a 1 KHz tone will be heard. (This assumes that the VOR/ILS/Marker beacon and audio systems are energised). Page 3 Jan 31/12

4 z SD3-60 AIRCRAFT MAINTENANCE MANUAL ADF System Figure 1 Page 4

5 SD3-60 AIRCRAFT MAINTENANCE MANUAL z AMM ADF SYSTEM - MAINTENANCE PRACTICES (PRE-MOD A8062) 1. Adjustment/Test A. Bench tests The ADF system should be tested in accordance with the procedure in the relevant Manufacturers Manual. B. Pre-installation tests Check that the units are free from signs of mechanical damage, corrosion or other defects. C. Post-installation tests (1) Hangar functioning (a) Refer to , pb301. Provide electrical power. (b) Select ACT and ANT on CTL-60 and set in the frequency of any strong ADF station which can be received in the hangar. NOTE: In the event of non-reception, take the aircraft outside the hangar. (c) Check for satisfactory audio reception in all phones and speakers. Adjust volume controls as necessary. NOTE: Audio panel volume controls are inactive for ADF. (d) Select PRE on CTL-60 and set in the frequency of a second strong ADF station. (e) Monentarily press the TUNE button on the CTL-60 and check that the frequencies are interchanged and that the second station is now being received. (f) Check that a tone is heard when the function switch is set to TONE. (g) On CTL-60 set the function switch to ADF. (h) Set the VOR/ILS/Marker beacon RMI pointer switches to ADF and check that the pointers move to a stable position. (i) Press and hold the CTL-60 TEST button and check that the VOR/ILS/Marker beacon RMI pointers move approximately 90 and that a tone is heard. (j) Release the TEST button and check that the pointers return to original position ± 2 at a rate exceeding 20 per second. Page 201

6 z SD3-60 AIRCRAFT MAINTENANCE MANUAL (k) (l) Check that the bearing is in the correct sense and that the uncoded needle point is less than ± 2. Select ACT on the CLT-60 and set in an unused frequency and check that the VOR/ ILS/Marker beacon RMI pointers park at the 3-o'clock position. (2) Compass base functioning. NOTE: 1. These tests are to be carried out on an approved compass/adf base using radio stations approved for calibration purpose covering the centre and extremes of the frequency band if possible. 2. Tests are to be carried out only in the period of time between 2 hours after sunrise and 2 hours before sunset. 3. Atmospheric conditions must be free from static. 4. Results must be kept with the inspection records for each individual aircraft. (a) At the start of each loop swing have the aircraft nose pointed towards the ADF station being used. (b) Loop swings must be effected with readings taken every 45. The aircraft gyro compass should be used as the heading reference with the error information on the deviation card taken into account. NOTE: Any ADF bearings which fall outside limits should initiate, in the first instance, a heading check against a datum compass. (3) Adjustments are required if the following accuracies are not achieved: Relative bearing Accuracy 0 and 180 ±4 330 to 0308 and ±5 150 to 210 Elsewhere ±6 (4) To adjust the ADF-60A receiver refer to the relevant section in the Collins ADF-60A Maintenance Manual. Page 202

SD3-60 AIRCRAFT MAINTENANCE MANUAL - DESCRIPTION & OPERATION (PRE-MOD A8062) (1) Transceiver, Collins type DME40, (Part No.

SD3-60 AIRCRAFT MAINTENANCE MANUAL - DESCRIPTION & OPERATION (PRE-MOD A8062) (1) Transceiver, Collins type DME40, (Part No. AMM 53.0.0.0DME SYSTEM - DESCRIPTION & OPERATION (PRE-MOD A8062) 1. Description A. General Two identical D.M.E. systems are installed, one for each pilot. Frequency selection is made via each respective