adf-t-12c/d...fixed loop antenna adf-t-12c/d system components figure 1-1 b e n d i x a v i o n i c...
TRANSCRIPT
I n s t a l l a t i o n M a n u a l
A D F - T - 1 2 C / D A u t o m a t i c D i r e c t i o n F i n d e r S y s t e m
/
B e n d i A v i o n i c s D i v i s i o n
r
T A B L E O F C O N T E N T S
S E C T I O N I G E N E R A L I N F O R M A T I O N
Paragraph Page
1 - 1 . D e s c r i p t i o n 1 - 1
S E C T I O N I I I N S T A L L A T I O N
Preliminary Inspection System Configuration
Interconnect Cabling Unit Installation
Adjustment Preparation
Adjustment Procedure
Equipment Checkout
Preflight Check
Flight Check
Ins ta l la t ion o f CW Osc i l l a to r K i t Opt ion
2 - 1 . 2 - 1
2 - 2 . 2 - 1
2 - 3 . 2 - 1
2 - 4 . 2 - 1
2 - 6 . 2 - 6
2 - 7 . A .
2 - 7 . B .
2 - 1 0
2 - 1 0
2 - 8 . 2 - 1 1
S E C T I O N I I I D I A G R A M S
I l l u s t r a t i o n s 3 - 1
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 i/ ii
9
L I S T O F I L L U S T R A T I O N S
F i g u r e Page
ADF-T-12C/D System Components
Model 201C/D ADF Receiver, Outline Dimensions Model 201F ADF Receiver, Outline Dimensions Model 551A Servo Amplifier-Indicator, Outline Dimensions Model 551C Dual ADF Indicator, Outline Dimensions
Model 55IE Servo Amplifier-Indicator, Outline Dimensions Model 551RL Servo Amplifier-Indicator, Outline Dimensions Model 102A/B Audio Amplifier, Outline Dimensions Doubler Plate, Loop Mounting Installation Model 2321E Fixed Loop Antenna, Outline Dimensions Sense Whip Antenna 2V008
ADF-T-12C/D System Interconnect Diagram
1 - 1 . i v
2 - 1 . 2 - 2
2 - 2 . 2 - 3
2 - 3 . 2 - 7
2 - 4 . 2 - 8
2 - 5 . 2 - 8
3 - 1 . 3 - 1
3 - 2 . 3 - 2
3 - 3 . 3 - 3
3 - 4 . 3 - 4
3 - 5 . 3 - 5
3 - 6 . 3 - 6
3 - 7 . 3 - 7
3 - 8 . 3 - 8
3 - 9 . 3 - 9
3 - 1 0 . 3 - 1 0
3 - 1 1 . 3 - 1 1
3 - 1 2 . 3 - 1 3
3 - 1 3 . 3 - 1 5
3 - 1 4 . 3 - 1 6
L I S T O F T A B L E S
T a b l e Page
1 - 1 . Sys tem Components
S y s t e m S p e c i fi c a t i o n s
1 - 2
2 - 1 . Loop Stage Adjustment Procedure
Opera t iona l P rob lems and Poss ib le Causes 2 - 9
2 - 2 . 2 - 1 1
%
> ^ M O N 9TESTf;
/8;o ’.1' 2- 3- A- 200 I1400-^. ' 8 0 0
1 6 0 0Q . r
I
9m w m
M o d e l 2 0 I F A D F R e c e i v e r
M o d e l 2 0 1 D A D F R e c e i v e r
Model 551A/E Servo Ampl ifier - Ind icator
M o d e l 5 5 1 R L S e r v o A m p l i fi e r - I n d i c a t o r
M o d e l 5 5 1 C Dual-Synchro Indicator
M o d e l 2 3 2 1 E F ixed Loop An tenna
ADF-T-12C/D System Components F i g u r e 1 - 1
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1i v
S E C T I O N I G E N E R A L I N F O R M A T I O N
D E S C R I P T I O N1 - 1 .
The basic Automatic Direction Finding (ADF) system consists of an ADF receiver, afixed- loop antenna and aservo-amplifier bearing indicator. Table 1-1 describes the components and accessories used in various ADF-T-12C and ADF-T-12D system configurations. Figure 1-1 illustrates some of these components. The sole difference between an ADF-T-12C and an ADF-T-12D system is the digitally tuned 201F ADF receiver. Use of the 201F receiver classifies the system as an ADF-T-12D. All components (including the receiver) and acces¬ sories are system-interchangeable. Specifications for both systems are listed in table 1-2. Dimensions, weights and connector data are given on the outline drawings in Section III.
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 1 - 1
S E C T I O N I
G E N E R A L I N F O R M A T I O N
T A B L E 1 - 1 S Y S T E M C O M P O N E N T S
B E N D I X
T Y P E / PA R T N U M B E R
D E S C R I P T I O N R E M A R K S
2 0 1 C ADF Receiver with tuning meter. ( Ins ta l la t ion o f CW k i t 2V017-01 converts 201C to 201D). ADF Receiver with tuning meter and CW option,
ADF Receiver with digital tuning, out- of-lock monitor, and BFO (CW mode is standard). No tuning meter. S e r v o - A m p l i fi e r I n d i c a t o r
Basic ADF-T-12C receiver (no CW mode).
2 0 1 D O p t i o n a l A D F - T- 1 2 C r e c e i v e r .
2 0 1 F S t a n d a r d A D F r e c e i v e r i n A D F - T - 12D system.
5 5 l A S t a n d a r d r e s o l v e r - i n d i c a t o r - i n d i c a t e s A D F b e a r i n g r e l a t i v e to aircraft heading. O p t i o n a l r e s o l v e r - i n d i c a t o r . Similar to 551A but incorporating synchro-transmitter for dr iving a remote indicator (such as a551C). Optional indicator permitting dis¬ play of two bearing sources; re¬ quires one 551E for each pointer.
Opt ional ind icator which when man¬ ually matched to compass heading provides ADF compass bearing.
5 5 1 E S e r v o - A m p l i fi e r I n d i c a t o r
5 5 1 C Dual Pointer (independently driven) Synch ro I nd i ca to r
5 5 1 R L S e r v o - A m p l i fi e r I n d i c a t o r w i t h manually rotatable azimuth dial and blue-white lighting.
A C C E S S O R I E S
2 T 0 2 8 - 0 1 Universal Installation Kit containing bulk coax and necessary connectors. Installation Kit consisting of:
2 V 0 0 5 2 V 0 0 7
Two requ i red fo r dua l i ns ta l l a t i on .
2T006-( ) - M a i n c a b l e - S e n s e a n t e n n a l e a d - i n
c a b l e
2V008-02 -Sense antenna -long wire 4006310 - Loop cable
Sense Antenna -54-inch whip Sense Antenna -long wire BFO (CW) K i t
2 V 0 0 8 - 0 1
2 V 0 0 8 - 0 2 Included in most 2T006-( )kits. C o n v e r t s 2 0 1 C r e c e i v e r t o 2 0 1 D .2 V 0 1 7 - 0 1
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 11 - 2
S E C T I O N I G E N E R A L I N F O R M A T I O N
T A B L E 1 - 1
SYSTEM COMPONENTS (continued)
B E N D I X
T Y P E / PA R T N U M B E R
D E S C R I P T I O N R E M A R K S
1 0 2 A Audio Amplifier (14 Vdc) Required for loudspeaker opera¬ t i o n .
S a m e a s 1 0 2 A .1 0 2 B Audio Amplifier (28 Vdc) 8 - f o o t I n s t a l l a t i o n C a b l e f o r 1 0 2 A o r B .
Bracket for remotely mounting two 5 5 I E S e r v o - A m p l i fi e r I n d i c a t o r s .
2 V 0 1 4 - 0 1
6 2 C 0 3 5 - 0 1 Dual system use only.
T A B L E 1 - 2
S Y S T E M S P E C I F I C A T I O N S
D E S C R I P T I O N
C H A R A C T E R I S T I C ADF-T-12C (201C/D) ADF-T-12D (201F)
Frequency Range : B a n d 1 B a n d 2 B a n d 3
2 0 0 - 4 0 0 k H z 4 0 0 - 8 0 0 k H z 8 0 0 - 1 6 0 0 k H z
C h a n n e l S p a c i n g = 1 k H z
B a n d s w i t c h i n g & D i g i t a l T h u m b ¬ w h e e l s
R E C :
1 9 0 - 4 4 0 k H z 4 2 0 - 9 0 0 k H z 8 5 0 - 1 7 5 0 k H z
Tun ing Me thod B a n d s w i t c h i n g & C o n v e n t i o n a l Tun ing D ia l . REC: M C W a n d V o i c e
R e c e p t i o n
CW Recept ion
S a m e a s T - 1 2 C
Same as T-12C (CWC W : B F O :
mode) A D F :A D F : A u t o m a t i c D i r e c t i o n
F i n d e r - M C W , C W and Vo ice recep t ion
S a m e a s T - 1 2 C
S e n s i t i v i t y : A D F
(AM or CW signal) 90 pV/m input will produce ±3. 0bear ing to s igna l source with S+N/N ratio o f 6 d B .
75 pV/m input will produce ±3.0° bear ing to s igna l source with S+N/N ratio o f 6 d B .
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 1 - 3
S E C T I O N I G E N E R A L I N F O R M A T I O N
T A B L E 1 - 2
SYSTEM SPECIFICATIONS (continued)
D E S C R I P T I O N
C H A R A C T E R I S T I C ADF-T-12C (201C/D) ADF-T-12D (201F)
R E C 10 juV input will produce 50 mW output in to 500-ohm re¬ sistive load with S+N/N ratio o f 6 d B .
4kHz at -6 dB points 12 kHz at -60 dB points
15 /iV input wil l produce 50 mW output in to 500-ohm re¬ s is t i ve load w i th S+N/N ra t io o f 6 d B .
4kHz maximum at -6 dB points 1 2 k H z m a x i m u m a t - 6 0 d B p o i n t s
S a m e a s T - 1 2 C
S e l e c t i v i t y (Bandwidth)
A D F I n d i c a t o r
Speed (Settling Time) Audio Output :
R E C
7 s e c o n d s m a x i m u m w i t h indicator 175° off bearing
S a m e a s T - 1 2 C70 ±5 mW at 8pV min. input at 2 0 0 k H z a n d V O L s e t f o r m a x . 3 . 5 W m a x i m u m 1 0 W m a x i m u m
W i t h i n 1 0 d B b e t w e e n 2 0 0 a n d 2 0 0 0 H z
±1/4 dB between 350 and 2 5 0 0 H z r e l a t i v e t o a 1 0 0 0 H z 1 - W a m p l i fi e r o u t p u t
500 ohms (Headset) 3ohms (Speaker)
±3° from 70 /iV/m to 0. 5V/m
1 0 2 A 1 0 2 B
AF Response
S a m e a s T - 1 2 C S a m e a s T - 1 2 C
S a m e a s T - 1 2 C
with 102A/B S a m e a s T - 1 2 C
Output Impedance with 102A/B
Bearing Accuracy O p e r a t i n g C u r r e n t R e q u i r e m e n t s - Single Systems:
R e c e i v e r 5 5 l A I n d i c a t o r 5 5 1 R L I n d i c a t o r 5 5 I E I n d i c a t o r
1 0 2 A A u d i o A m p l i fi e r 1 0 2 B A u d i o A m p l i fi e r 5 5 1 C I n d i c a t o r
L i g h t i n g : R e c e i v e r 5 5 1 R L I n d i c a t o r
S a m e a s T - 1 2 C
S a m e a s T - 1 2 C
S a m e a s T - 1 2 C
1 4 V d c 2 8 V d c 1 4 V d c 2 8 V d c
3 0 0 m A
4 5 0 m A 4 5 0 m A 4 5 0 m A 6 5 0 m A
2 0 0 m A
3 2 0 m A 3 2 0 m A 3 2 0 m A
S a m e a s T - 1 2 C S a m e a s T - 1 2 C S a m e a s T - 1 2 C S a m e a s T - 1 2 C S a m e a s T - 1 2 Cl A
2 6 V a c 4 0 0 H z
1 0 0 m A 1 2 0 m A
1 7 0 m A 6 0 m A
3 2 0 m A 1 6 0 m A S a m e a s T - 1 2 C
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 11 - 4
S E C T I O N I I I N S T A L L A T I O N
2 - 1 . P R E L I M I N A R Y I N S P E C T I O N
Perform apreliminary inspection and test of the ADF-T-12C/D system before installation a s f o l l o w s :
Unpack the equipment and check it against installation requirements for correct model and par t numbers o f a l l components .
Visually inspect for any damage that may have occurred during shipment. Shipping damage claims should be made to the transportation company.
Complete the Bendix Quality Report Form and return it to Bendix.
2 - 2 . S Y S T E M C O N F I G U R A T I O N
Figures 3-1 and 3-2 illustrate typical single and dual systems.
2 - 3 . I N T E R C O N N E C T C A B L I N G
Use only approved cables, furnished with the basic interconnect cabling kits, to meet i n s t a l l a t i o n r e q u i r e m e n t s f o r v a r i o u s a i r c r a f t .
2 - 4 . U N I T I N S T A L L A T I O N
These ins t ruc t i ons a re app l i cab le to bo th sys tems . F igu re 3 -14 shows the e lec t r i ca l i n te r¬ connection for the ADF-T-12C/D system. Any change in antenna moimting positions may require acabling reversal, as noted on figure 3-14.
2 - 4 . A . R E C E I V E R
The receiver is usually mounted in or underneath the aircraft instrument panel. When mounted in the instrument panel the receiver dust cover is secured to mounting brackets, or to mounting flanges in the panel cutout (figure 3-3). Outline dimensions for the rece ive rs a re shown in figures 3 -4 and 3 -5 . Ins ta l l a t i on p rocedure i s as fo l l ows :
(1) If a14-volt dc power source is used, disregard steps (2) and (3) and proceed to step (4).
(2) If a28-voIt dc power source is used, a28-volt lamp (type 313R, P/N 4003018-0502) must be substituted for the 14-volt lamp in the 201C/D (four lamps are required in the 201F).
S l ide cover back to expose lamp. Turn un i t over and remove sheet meta l screw t h a t s e c u r e s l a m p h o l d e r. E x c h a n g e l a m p s a n d r e a s s e m b l y. F o r 2 0 1 F r e c e i v e r, p roceed as fo l l ows :
Locate DSl through DS4 mounted in thumbwheel switches (Figure 2-1).
Remove yellow jumper between lug on common baseplate of DS1/DS2 and lug on common base plate of DS3/DS4. Discard.
(a)
(b)
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 2 - 1
S E C T I O N I I I N S T A L L A T I O N2-4. A. (2)
(c) Remove the white/black ground lead from existing 14 Vcommon ground bar and solder to the lug between DS3 and DS4.
Y E L L O W J U M P E R R E M O V E F O R 4 - 2 8 V+ S U P P L Y
S H I F T 6 N D T O H E R E F O R + 2 0 VDSI\\ DS2 DS3/DS4
7
S>J C® G R O U N D L E A D
k T O P
F R O N T P A N E L
Model 201F Lighting Schematic F i g u r e 2 - 1
Remove voltage-switch key retained by asheet-metal screw at the rear of the receiver. Position switch to "28" and replace voltage-switch key to lock switch in pos i t ion .
Fasten connector mounting bracket with attached interconnect cable assembly to rear of receiver dust cover with the three screws supplied.
Secure connector cover to rear of receiver dust cover with the four screws supplied.
Attach the receiver mounting brackets (not supplied) to each side of the dust cover with four 6-32 x3/8-inch machine screws and applicable washers and nuts. See figure 3-3.
Drill two holes on each side of instrument panel cutout. Holes must align with holes in customer-fabricated receiver moimting brackets. See figure 3-3.
Place receiver dust cover, with attached mounting brackets, behind panel cutout so that mounting holes in the bracket align with holes in the instrument panel.
Secure receiver dust cover to instrument panel with four 6-32 x3/8-inch screws and appl icable washers and nuts.
If necessary, secure the rear of the receiver dust cover with asuitable supporting bracket. Support bracket must be fabricated in the field to meet individual instal¬ l a t i o n r e q u i r e m e n t s .
(3)
(4)
(5)
(7)
(8)
(9)
(10)
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 2 1 - 1 3 7 12 - 2
S E C T I O N I I I N S T A L L A T I O N
2 - 4 . B . S E R V O a m p l i fi e r / i n d i c a t o r
Model 551A/C/E/RL indicators are designed for mounting behind the panel. Mounting- hole dimensions are included on the outline drawings in Section III,
Install the servo amplifier/indicators using the appropriate outline drawing as aguide. Carefully cut the dial opening in the panel and drill mounting holes. Allow at least three inches for cable connections and removal passage.
In dual installations, the two 551E indicators can be installed remotely using bracket P/N 62C035. Check cable lengths between both 551E, the two receivers, the 551C indicator and the 26-volt 400 Hz source. See figure 3-2.
The internal lighting connection for the 551RL is brought out on J1 pin 4. Mating con¬ nector P3 pin 4should be connected to the aircraft dimmer circuit on the flight instru¬ ment lighting bus. The indicator is factory wired for 14 Vdc operation. To convert the lighting to 28 Vdc, remove jumpers W1 and W2 and install jumper W3. These items are physically located on TB7 which is the rearmost terminal strip on the bottom side of the indicator (figure 2-2).
D S l I
m m m « T B 7 O
G N DD C i n p u t f r o m c o n n e c t o r J l - 4
Model 551RL Lighting Schematic F i g u r e 2 - 2
A U D I O A M P L I F I E R2 - 4 . C .
The optional audio (speaker) amplifier is designed to be mounted in any convenient loca¬ tion in the aircraft, such as behind the instrument panel, on ashelf where agood elect¬ rical ground can be made through the chassis or pin 5of Jl. Figure 3-1 illustrates the unit connected in the system. Installation procedures for the audio amplifier are as f o l l o w s :
(1) Check receiver to audio-amplifier cable distance.
Drill three holes in the selected mounting surface to the dimensions illustrated in figure 3-10 and partially insert three screws.
(2)
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 2 - 3
S E C T I O N I I I N S T A L L A T I O N2 - 4 . C .
(3) Mount the audio amplifier by inserting the screw heads through the mounting holes in the flanges.
Position the unit so that the screw heads slip in the notches of the mounting holes.
Tighten screws securely.
Wire audio-amplifier cable to receiver connector (Jl) and connect Amphenol plug to amplifier (see figures 3-1 and 3-14). Avoid routing output cable close to input c a b l e o r o t h e r a u d i o c a b l e s .
Mount and connect speaker to shielded lead.
(4)
(5)
(6)
(7)
2 - 5 . A N T E N N A I N S T A L L A T I O N
Accurate azimuth and over-the-station performance of the ADF-T-12C/D system requires the loop antenna be moimted exactly on the fore-and-aft center line of the aircraft.
S E N S E A N T E N N A2 - 5 . A .
(1) Determine whether the sense antenna is to be top or bottom mounted. Refer to the system interconnect diagram for correct antenna coimector wiring for bottom mount.
- C A U T I O N -
Do not mount either of the sense antennas near other trans¬ mitting/receiving antennas.
(2) When the 54-inch whip is employed as asense antenna (figure 3-13) it must be located at least 3feet from the propeller and mounted in aplace having sufficient structural strength to prevent tearing if the antenna should vibrate violently.
(3) When the longwire type sense antenna is used, the length should be 8to 12 feet. One end is supported by the feed-thru insulator and the other with an insulated strain relief anchored to top rudder structure.
Sense antenna and lead-in capacitance must be within the limits of 125 ±25 pF. Low-capacitance coaxial line should be used to minimize capacitive effects and provide proper signal ratios to the receiver.
2 - 5 . B . L O O P A N T E N N A
(1) Determine whether the loop antenna wUl be top or bottom mounted. Refer to the system interconnect diagram for correct antenna connector wiring for top mount.
(2) Select the approximate mounting location on the fore-and-aft centerline of the air¬ c r a f t .
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 12 - 4
S E C T I O N I I
I N S T A L L A T I O N 2-5. B. (2)
- N O T E -
Quadrantal error compensation must be done by trial and error before the exact mounting location can be determined. Aircraft must be well clear of any metal hangars, electric or telephone wires, buried cables, etc. that could cause bearing errors.
Temporarily tape the loop to the outside of the aircraft. Loop must be upside down for connector clearance and the aircraft positioned to anormal flight attitude. Make loop cable entrance into the aircraft without drilling any holes in the aircraft skin (via window, door, or removable inspection cover). Ensure adequate loop cable length for the selected location.
(3)
- N O T E -
Bearing indications on the servo amplifier/indicator will be reversed with the loop mounted upside down. Compute bearing differences accordingly.
(4) Use aground compass rose if available. If not, the aircraft directional gyro or compass must be used to determine aircraft rotation angles. If the compass must be used, compass error should be checked prior to proceeding.
(5) Select aradio station of known position, at least 20-miles distance and free from static and fading. Tune the receiver to the station. (See paragraph 2. 7. B. (1) remark on 201F tuning.)
(6) Rotate the aircraft so that the nose is pointing directly at the transmitting station. The servo amplifier/indicator must now read zero.
(7) Set the directional gyro to zero degrees (or note the compass heading) and in agree¬ ment with the servo amplifier/indicator.
(8) Rotate the aircraft counterclockwise around the compass rose in 15-degree incre¬ ments. Compare the directional gyro or corrected compass heading with the servo amplifier/indicator readings at each increment. Chart the results. The difference between the two readings is the quadrantal error. Maximum errors will be at the 45-, 135-, 225-, and 315-degree points.
Repeat steps (2) through (8) until aloop position along the aircraft centerline is found where the 6-degree loop compensation reduces the quadrantal error to a minimum. Secure loop in this location and lightly pencil mark the outline of the loop antenna on the surface of the aircraft .
(9)
(10) Remove the loop from the aircraft and locate the doubler plate over the center of t h e o u t l i n e .
- C A U T I O N -
Loop should be positioned so that holes are drilled only through the skin of the aircraft. Do not drill through frame stations or s t r i n g e r s .
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 2 - 5
S E C T I O N I I I N S T A L L A T I O N2-5. B. (10)
Mark and drill the five mounting holes in the aircraft skin.
Route loop cable through the interior of the aircraft, securing as necessary to prevent chafing on structure and/or interference with control cables. Avoid locating the cable closely parallel to noisy conductors such as inverter, alternator or other high current level conductors.
Place doubler plate in position inside the aircraft so that the mounting nuts on doubler plate align with fixed loop mounting screws. Apply Minnesota Mining and Manufacturing ECO-801 Type-A sealer between doubler plate and aircraft skin. See figure 3-11.
Secure cable connector and doubler plate to aircraft skin with two 6-32 placed in mounting holes from outside of aircraft.
Insert loop cable connector through doubler plate and aircraft skin from inside the aircraft. Apply ECO-801 Type-A sealer between doubler plate and cable connector.
- C A U T I O N -
If the loop to be installed is supplied with acompressible gasket ring, insert this between the loop connector and doubler plate.
Place loop in position so that loop and loop cable connectors mate. Apply ECO-801 Type-A sealer between loop gasket and aircraft skin.
Secure loop to aircraft skin with two 8-32 binding-head screws placed from outside aircraft to match with the elastic stop nuts on doubler plate. Loop gasket must be compressed to approximately l/32-inch at loop centerline.
S E N S E A N D L O O P A N T E N N A T U N I N G
(11)
(12)
(14)
(15)
(16)
2 - 6 .
2 - 6 . A . A D J U S T M E N T P R E PA R AT I O N
After the ADF-T-12C/D system is installed, the sense antenna and loop antenna tuning should be adjusted for optimum performance. These adjustments are located under the RE shield cover of the 201( )receiver chassis. Accessibility requires the use of lap- adapter cable, Bendtx part number 2V011-01. Early versions of this cable should be modified to include aDPDT toggle switch (P/N 2088618-0003) in the lead from pin 1 (sense antenna input to the receiver) and the lead from pin 16 (ADF servo signal output) at the receiver end of the cable, figure 2-3. This switch should be mounted on the bracket holding the connector plug to the receiver connector. Switch wiring should be short and as direct as practicable.
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 12 - 6
S E C T I O N I I I N S T A L L A T I O N2 - 6 . A .
TO SENSE ANTENNAa
T o R C V R J ] - l
r l 2 0 p F T U N E S E N S E
A m V
T U N E L O O P
T O I N D I C A T O Ra
T o R C V R J l - 1 6
L a p - a d a p t e r C a b l e M o d i fi c a t i o n S c h e m a t i c F i g u r e 2 - 3
2 - 6 . B . A D J U S T M E N T P R O C E D U R E S
(1) Remove receiver chassis from dust cover and connect lap-adapter cable between r e c e i v e r c o n n e c t o r J 1 a n d r e c e i v e r d u s t c o v e r c o n n e c t o r P I .
(2) Set the receiver function switch to REC, the bandswitch to the 190-440 kHz position, and the lap-adapter toggle switch to the Tune Sense position.
(3) Tune up to astat ion at , or as c lose as possib le to, 440 kHz for the ADF-T-12C (399 kHz for the 201F receiver).
(4) Using suitable tool, adjust trimmer C22 for maximum tuning indicator deflection. See figure 2-4. In the 201F receiver, capacitor C22 may be adjusted by connecting adc voltmeter set to +10 Vdc maximum between TP2 (+) and chassis ground. TP2 is connected to the col lector of t ransis tor Q9 in the lower- le f t rear sect ion of the 2 0 1 ( ) r e c e i v e r s .
(5) Set the function switch to ADF and align the loop stage in accordance with table 2-1. Use stations as close to the ends of the bands as possible. See figures 2-4 and 2-5.
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 2 - 7
S E C T I O N I I I N S T A L L A T I O N
R F S H I E L D
o o o o o o
C 2 2
/
R e c e i v e r, R F S h i e l d , B o t t o m V i e w F i g u r e 2 - 4
\ © o o o © G O G © O O O
(201C/D) ( 2 0 I F )
8 5 0 8 0 0
( 2 0 I C / D ) ( 2 0 I F )
4 2 0 4 0 0
( 2 0 I C / D ) ( 2 0 I F )
1 9 0 2 0 0
R F S H I E L D
Receiver, RF Shield, Top View F i g u r e 2 - 5
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 12 - 8
S E C T I O N I I
I N S T A L L A T I O N
T A B L E 2 - 1 L O O P S T A G E A D J U S T M E N T P R O C E D U R E
A D F - T - 1 2 C A D F - T - 1 2 D
B A N D S W I T C H
P O S I T I O N
R C V R . T U N I N G
F R E Q . k H z
B A N D S W I T C H
P O S I T I O N
R C V R . T U N I N G
F R E Q . k H z S T E P
N O . I N S T R U C T I O N S
1 9 0 - 4 4 0 k H z1 2 0 0 k H z 2 0 0 - 4 0 0 k H z 2 0 0 k H z With lap-adapter s w i t c h s e t t o T u n e
Sense pos i t ion a l low needle to point to s t a t i o n .
P r e s s T E S T s w i t c h
to d r i ve po in te r o f f approximately 90° and se t l ap -adap te r sw i t ch to Tune Loop pos i t ion.
A d j u s t L I f o r m a x i ¬ m u m i n d i c a t i o n o n
tuning meter (dc volt¬ m e t e r f o r 2 0 1 F r e ¬
c e i v e r ) .
Repea t i n s t r uc t i ons i n s tep 1except ad jus t C3.
R e p e a t s t e p s 1 a n d 2 u n t i l re tun ing g ives no inc rease o f m e t e r d e fl e c t i o n .
Repea t i ns t ruc t i ons i n s tep 1excep t ad jus t L2 .
Repea t i ns t ruc t i ons i n s tep 1except ad jus t C4.
R e p e a t s t e p s 4 a n d 5 u n t i l re tun ing g ives no inc rease o f m e t e r d e fl e c t i o n .
Repea t i n s t r uc t i ons i n s tep 1except ad jus t L3 .
Repea t i n s t r uc t i ons i n step 1except ad just C6.
R e p e a t s t e p s 7 a n d 8 u n t i l re tun ing g ives no increase o f m e t e r d e fl e c t i o n .
a .
b .
c .
2 S a m e 4 0 0 k H z S a m e 4 0 0 k H z
3 S a m e S a m e
4 4 2 0 - 9 0 0 k H z 4 5 0 k H z 4 0 0 - 8 0 0 k H z 4 0 0 k H z
4 2 0 - 9 0 0 k H z5 9 0 0 k H z S a m e 8 0 0 k H z
6 4 2 0 - 9 0 0 k H z S a m e
7 8 5 0 - 1 7 0 0 k H z 9 0 0 k H z 8 0 0 - 1 6 0 0 k H z 8 0 0 k H z
8 5 0 - 1 7 0 0 k H z8 1 7 0 0 k H z S a m e 1 6 0 0 k H z
8 5 0 - 1 7 0 0 k H z9 S a m e
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 2 - 9
S E C T I O N n I N S T A L L A T I O N
2 - 7 . E Q U I P M E N T C H E C K O U T
Before take-off, determine if the ADF-T-12C/D system is operating properly.
2 - 7 . A . P R E F L I G H T C H E C K
s Tune in stations evenly spaced on each band of the receiver. In the ADF-T-12C maximum tuning-meter deflection should be obtained at peak signal.
(1)
Adjust volume control to desired listening level.(2)
(3) With the function switch in the CW or BFO position, tune in one station in each band until aclear 1000-Hz signal is heard.
(4) Position aircraft on aknown true heading.
(5) S e t r e c e i v e r s w i t c h t o A D F a n d t u n e i n s t a t i o n .
Compare bearing on servo amplifier/indicator with true bearing. Bearings must agree within ±3 degrees with little or no "himting" observed on indicator.
Press TEST bu t ton on f ron t pane l o f rece ive r and observe ind ica to r po in te r. Ind i¬ cator pointer will rotate away from indicated bearing while TEST button is pressed.
(6)
(7)
Release TEST button, and observe indicator pointer. Indicator pointer should return to the ind icated bear ing.
(8)
For ADF-T-12D, se lec t aband o ther than tha t con ta in ing the s ta t ion d ia led in . The out-of-lock MON lamp should light.
(9)
Return the bandswitch to the correct band. The out-of-lock MON lamp should go out.
When the optional NORMAL/EMERGENCY switch is installed (figure 3-14), repeat the preflight check with the switch set to EMERGENCY; then return the switch to t h e N O R M A L p o s i t i o n .
(10)
(11)
\
If adual system is installed, turn one receiver OFF, check the other as described, then repeat fo r the second rece iver.
(12)
Rotate the azimuth knob to ensure full rotation of azimuth card (551RL only).(13)
Turn instrument lighting control ON. Ensure indicator lamps are operating.(14)
2 - 7 . B F L I G H T C H E C K
A i rborne tes t shou ld emp loy the fo l low ing fl igh t tes t p rocedure :
(1) Using the REC mode, select astation of average power from adistance of about 50 miles. Using tuning meter in the 201C/D, adjust receiver frequency until maximum signal s t rength is obta ined. When tuning 201F i t wi l l be apparent that audio f requency
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 12 - 1 0
S E C T I O N I I I N S T A L L A T I O N2-7. B. (1)
response, as well as audio level, will increase slightly when tuned 1or 2kHz (de¬ pending on signal strength) on either side of the desired station. The correct tuning for optimum performance will be the exact station frequency and not the point of loudest audio. This is true of any ADF receiver but will be noticed more readily in the 201F receiver because of the precise tuning.
(2) F ly toward the s ta t ion .
(3) S e t t h e f u n c t i o n s w i t c h t o A D F.
Note the bearing on the servo amplifier/indicator. Unless the station is weak, there should be no prolonged hunting by the indicator pointer.
Make a360-degree standard rate turn and observe the servo amplifier/indicator. The indicator pointer should track the turn without "losing" the station.
(4)
(5)
(6) Select arange station to check the over-the-station performance of the system.
Set the receiver to ADF and home-in on the range station.
Maintain asteady heading and observe the indicator pointer as the aircraft approaches and passes over the station. The pointer should oscillate slightly and as the cone of silence is passed, should abruptly swing to areading of 180 degrees from the original bea r i ng i nd i ca t i on .
(7)
(8)
(9) Maintain heading until the station is passed. If pointer reversal is unsatisfactory, the information in table 2-2 may help in determining the trouble.
2 - 8 . INSTALLATION OF CW OSCILLATOR KIT OPTION (Part Number 2V017-01)
Refer to ADF-T-12B/C Maintenance Manual, LB. 2012A, for complete instructions.
T A B L E 2 - 2 O P E R A T I O N A L P R O B L E M S A N D P O S S I B L E C A U S E S
I N D I C A T I O N P O S S I B L E C A U S E
Reversa l before enter ing cone o f s i lence.
Reversa l a f te r reach ing cone o f s i lence.
E x t e n d e d a r e a o f c o n f u s i o n . E x c e s s i v e p o i n t e r o s c i l l a t i o n .
E x c e s s i v e q u a d r a n t a l e r r o r.
S e n s e a n t e n n a e l e m e n t t o o f a r a f t .
S e n s e a n t e n n a e l e m e n t t o o f a r f o r w a r d .
Sense antenna too long or too short.
L o o p i n c o r r e c t l y l o c a t e d o r p o s s i b l e a r e s u l t of change in aircraft configuration.
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 2 -11 /12
S E C T I O N I I I D I A G R A M S
S E N S E A N T E N N A R E C E P TA C L E
M O D E L Z 3 2 I E F I X E D L O O P A N T E N N A
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M O D E L 2 0 1 ( ) AOF RECEIVER
R E F E R T O M T E R C O N N C C T I N G
C M A G f M M
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M O D E L I 0 2 A / B A U D I O A M P L I F I E R
( O P T I O N A L ) M O D E L 5 5 1 0
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ADF-T-12( )System Insta l lat ion Pictor ia l Diagram F i g u r e 3 - 1
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 3 7 1 3 - 1
t
S E C T I O N I I I D I A G R A M S
S E N S E A N T E N N A SENSE ANTENNA # 1
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D U A L I N D I C A T O R
A D F R C V R
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S E E J S E E I N T E R C O N N E C T > D I A G R A M
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M A I N C A B L E
L O O P C A B L E L O O P C A B L E
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D U A L B R A C K E T 6 2 C 0 3 5
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I N D I C AT O R S (REMOTE OR PANEL MID)
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L O O P # 1 232 IE
L O O P # 2
Typical Dual ADF-T-12( ) Insta l la t ion F i g u r e 3 - 2
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 13 - 2
S E C T I O N I I I D I A G R A M S
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B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 3 - 3
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B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 3 - 7
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Sense UTiip Antenna 2V008 F i g u r e 3 - 1 3
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 3 - 1 5
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T A B L E O F C O N T E N T S
S E C T I O N I G E N E R A L I N F O R M A T I O N
Paragraph Page
1 - 1 . D e s c r i p t i o n 1 - 1
S E C T I O N I I I N S T A L L A T I O N
Preliminary Inspection System Configuration
Interconnect Cabling Unit Installation
Adjustment Preparation
Adjustment Procedure
Equipment Checkout
Preflight Check
Flight Check
Ins ta l la t ion o f CW Osc i l l a to r K i t Opt ion
2 - 1 . 2 - 1
2 - 2 . 2 - 1
2 - 3 . 2 - 1
2 - 4 . 2 - 1
2 - 6 . 2 - 6
2 - 7 . A .
2 - 7 . B .
2 - 1 0
2 - 1 0
2 - 8 . 2 - 1 1
S E C T I O N I I I D I A G R A M S
I l l u s t r a t i o n s 3 - 1
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 i/ ii
9
L I S T O F I L L U S T R A T I O N S
F i g u r e Page
ADF-T-12C/D System Components
Model 201C/D ADF Receiver, Outline Dimensions Model 201F ADF Receiver, Outline Dimensions Model 551A Servo Amplifier-Indicator, Outline Dimensions Model 551C Dual ADF Indicator, Outline Dimensions
Model 55IE Servo Amplifier-Indicator, Outline Dimensions Model 551RL Servo Amplifier-Indicator, Outline Dimensions Model 102A/B Audio Amplifier, Outline Dimensions Doubler Plate, Loop Mounting Installation Model 2321E Fixed Loop Antenna, Outline Dimensions Sense Whip Antenna 2V008
ADF-T-12C/D System Interconnect Diagram
1 - 1 . i v
2 - 1 . 2 - 2
2 - 2 . 2 - 3
2 - 3 . 2 - 7
2 - 4 . 2 - 8
2 - 5 . 2 - 8
3 - 1 . 3 - 1
3 - 2 . 3 - 2
3 - 3 . 3 - 3
3 - 4 . 3 - 4
3 - 5 . 3 - 5
3 - 6 . 3 - 6
3 - 7 . 3 - 7
3 - 8 . 3 - 8
3 - 9 . 3 - 9
3 - 1 0 . 3 - 1 0
3 - 1 1 . 3 - 1 1
3 - 1 2 . 3 - 1 3
3 - 1 3 . 3 - 1 5
3 - 1 4 . 3 - 1 6
L I S T O F T A B L E S
T a b l e Page
1 - 1 . Sys tem Components
S y s t e m S p e c i fi c a t i o n s
1 - 2
2 - 1 . Loop Stage Adjustment Procedure
Opera t iona l P rob lems and Poss ib le Causes 2 - 9
2 - 2 . 2 - 1 1
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M o d e l 2 0 I F A D F R e c e i v e r
M o d e l 2 0 1 D A D F R e c e i v e r
Model 551A/E Servo Ampl ifier - Ind icator
M o d e l 5 5 1 R L S e r v o A m p l i fi e r - I n d i c a t o r
M o d e l 5 5 1 C Dual-Synchro Indicator
M o d e l 2 3 2 1 E F ixed Loop An tenna
ADF-T-12C/D System Components F i g u r e 1 - 1
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1i v
S E C T I O N I G E N E R A L I N F O R M A T I O N
D E S C R I P T I O N1 - 1 .
The basic Automatic Direction Finding (ADF) system consists of an ADF receiver, afixed- loop antenna and aservo-amplifier bearing indicator. Table 1-1 describes the components and accessories used in various ADF-T-12C and ADF-T-12D system configurations. Figure 1-1 illustrates some of these components. The sole difference between an ADF-T-12C and an ADF-T-12D system is the digitally tuned 201F ADF receiver. Use of the 201F receiver classifies the system as an ADF-T-12D. All components (including the receiver) and acces¬ sories are system-interchangeable. Specifications for both systems are listed in table 1-2. Dimensions, weights and connector data are given on the outline drawings in Section III.
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 1 - 1
S E C T I O N I
G E N E R A L I N F O R M A T I O N
T A B L E 1 - 1 S Y S T E M C O M P O N E N T S
B E N D I X
T Y P E / PA R T N U M B E R
D E S C R I P T I O N R E M A R K S
2 0 1 C ADF Receiver with tuning meter. ( Ins ta l la t ion o f CW k i t 2V017-01 converts 201C to 201D). ADF Receiver with tuning meter and CW option,
ADF Receiver with digital tuning, out- of-lock monitor, and BFO (CW mode is standard). No tuning meter. S e r v o - A m p l i fi e r I n d i c a t o r
Basic ADF-T-12C receiver (no CW mode).
2 0 1 D O p t i o n a l A D F - T- 1 2 C r e c e i v e r .
2 0 1 F S t a n d a r d A D F r e c e i v e r i n A D F - T - 12D system.
5 5 l A S t a n d a r d r e s o l v e r - i n d i c a t o r - i n d i c a t e s A D F b e a r i n g r e l a t i v e to aircraft heading. O p t i o n a l r e s o l v e r - i n d i c a t o r . Similar to 551A but incorporating synchro-transmitter for dr iving a remote indicator (such as a551C). Optional indicator permitting dis¬ play of two bearing sources; re¬ quires one 551E for each pointer.
Opt ional ind icator which when man¬ ually matched to compass heading provides ADF compass bearing.
5 5 1 E S e r v o - A m p l i fi e r I n d i c a t o r
5 5 1 C Dual Pointer (independently driven) Synch ro I nd i ca to r
5 5 1 R L S e r v o - A m p l i fi e r I n d i c a t o r w i t h manually rotatable azimuth dial and blue-white lighting.
A C C E S S O R I E S
2 T 0 2 8 - 0 1 Universal Installation Kit containing bulk coax and necessary connectors. Installation Kit consisting of:
2 V 0 0 5 2 V 0 0 7
Two requ i red fo r dua l i ns ta l l a t i on .
2T006-( ) - M a i n c a b l e - S e n s e a n t e n n a l e a d - i n
c a b l e
2V008-02 -Sense antenna -long wire 4006310 - Loop cable
Sense Antenna -54-inch whip Sense Antenna -long wire BFO (CW) K i t
2 V 0 0 8 - 0 1
2 V 0 0 8 - 0 2 Included in most 2T006-( )kits. C o n v e r t s 2 0 1 C r e c e i v e r t o 2 0 1 D .2 V 0 1 7 - 0 1
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 11 - 2
S E C T I O N I G E N E R A L I N F O R M A T I O N
T A B L E 1 - 1
SYSTEM COMPONENTS (continued)
B E N D I X
T Y P E / PA R T N U M B E R
D E S C R I P T I O N R E M A R K S
1 0 2 A Audio Amplifier (14 Vdc) Required for loudspeaker opera¬ t i o n .
S a m e a s 1 0 2 A .1 0 2 B Audio Amplifier (28 Vdc) 8 - f o o t I n s t a l l a t i o n C a b l e f o r 1 0 2 A o r B .
Bracket for remotely mounting two 5 5 I E S e r v o - A m p l i fi e r I n d i c a t o r s .
2 V 0 1 4 - 0 1
6 2 C 0 3 5 - 0 1 Dual system use only.
T A B L E 1 - 2
S Y S T E M S P E C I F I C A T I O N S
D E S C R I P T I O N
C H A R A C T E R I S T I C ADF-T-12C (201C/D) ADF-T-12D (201F)
Frequency Range : B a n d 1 B a n d 2 B a n d 3
2 0 0 - 4 0 0 k H z 4 0 0 - 8 0 0 k H z 8 0 0 - 1 6 0 0 k H z
C h a n n e l S p a c i n g = 1 k H z
B a n d s w i t c h i n g & D i g i t a l T h u m b ¬ w h e e l s
R E C :
1 9 0 - 4 4 0 k H z 4 2 0 - 9 0 0 k H z 8 5 0 - 1 7 5 0 k H z
Tun ing Me thod B a n d s w i t c h i n g & C o n v e n t i o n a l Tun ing D ia l . REC: M C W a n d V o i c e
R e c e p t i o n
CW Recept ion
S a m e a s T - 1 2 C
Same as T-12C (CWC W : B F O :
mode) A D F :A D F : A u t o m a t i c D i r e c t i o n
F i n d e r - M C W , C W and Vo ice recep t ion
S a m e a s T - 1 2 C
S e n s i t i v i t y : A D F
(AM or CW signal) 90 pV/m input will produce ±3. 0bear ing to s igna l source with S+N/N ratio o f 6 d B .
75 pV/m input will produce ±3.0° bear ing to s igna l source with S+N/N ratio o f 6 d B .
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 1 - 3
S E C T I O N I G E N E R A L I N F O R M A T I O N
T A B L E 1 - 2
SYSTEM SPECIFICATIONS (continued)
D E S C R I P T I O N
C H A R A C T E R I S T I C ADF-T-12C (201C/D) ADF-T-12D (201F)
R E C 10 juV input will produce 50 mW output in to 500-ohm re¬ sistive load with S+N/N ratio o f 6 d B .
4kHz at -6 dB points 12 kHz at -60 dB points
15 /iV input wil l produce 50 mW output in to 500-ohm re¬ s is t i ve load w i th S+N/N ra t io o f 6 d B .
4kHz maximum at -6 dB points 1 2 k H z m a x i m u m a t - 6 0 d B p o i n t s
S a m e a s T - 1 2 C
S e l e c t i v i t y (Bandwidth)
A D F I n d i c a t o r
Speed (Settling Time) Audio Output :
R E C
7 s e c o n d s m a x i m u m w i t h indicator 175° off bearing
S a m e a s T - 1 2 C70 ±5 mW at 8pV min. input at 2 0 0 k H z a n d V O L s e t f o r m a x . 3 . 5 W m a x i m u m 1 0 W m a x i m u m
W i t h i n 1 0 d B b e t w e e n 2 0 0 a n d 2 0 0 0 H z
±1/4 dB between 350 and 2 5 0 0 H z r e l a t i v e t o a 1 0 0 0 H z 1 - W a m p l i fi e r o u t p u t
500 ohms (Headset) 3ohms (Speaker)
±3° from 70 /iV/m to 0. 5V/m
1 0 2 A 1 0 2 B
AF Response
S a m e a s T - 1 2 C S a m e a s T - 1 2 C
S a m e a s T - 1 2 C
with 102A/B S a m e a s T - 1 2 C
Output Impedance with 102A/B
Bearing Accuracy O p e r a t i n g C u r r e n t R e q u i r e m e n t s - Single Systems:
R e c e i v e r 5 5 l A I n d i c a t o r 5 5 1 R L I n d i c a t o r 5 5 I E I n d i c a t o r
1 0 2 A A u d i o A m p l i fi e r 1 0 2 B A u d i o A m p l i fi e r 5 5 1 C I n d i c a t o r
L i g h t i n g : R e c e i v e r 5 5 1 R L I n d i c a t o r
S a m e a s T - 1 2 C
S a m e a s T - 1 2 C
S a m e a s T - 1 2 C
1 4 V d c 2 8 V d c 1 4 V d c 2 8 V d c
3 0 0 m A
4 5 0 m A 4 5 0 m A 4 5 0 m A 6 5 0 m A
2 0 0 m A
3 2 0 m A 3 2 0 m A 3 2 0 m A
S a m e a s T - 1 2 C S a m e a s T - 1 2 C S a m e a s T - 1 2 C S a m e a s T - 1 2 C S a m e a s T - 1 2 Cl A
2 6 V a c 4 0 0 H z
1 0 0 m A 1 2 0 m A
1 7 0 m A 6 0 m A
3 2 0 m A 1 6 0 m A S a m e a s T - 1 2 C
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 11 - 4
S E C T I O N I I I N S T A L L A T I O N
2 - 1 . P R E L I M I N A R Y I N S P E C T I O N
Perform apreliminary inspection and test of the ADF-T-12C/D system before installation a s f o l l o w s :
Unpack the equipment and check it against installation requirements for correct model and par t numbers o f a l l components .
Visually inspect for any damage that may have occurred during shipment. Shipping damage claims should be made to the transportation company.
Complete the Bendix Quality Report Form and return it to Bendix.
2 - 2 . S Y S T E M C O N F I G U R A T I O N
Figures 3-1 and 3-2 illustrate typical single and dual systems.
2 - 3 . I N T E R C O N N E C T C A B L I N G
Use only approved cables, furnished with the basic interconnect cabling kits, to meet i n s t a l l a t i o n r e q u i r e m e n t s f o r v a r i o u s a i r c r a f t .
2 - 4 . U N I T I N S T A L L A T I O N
These ins t ruc t i ons a re app l i cab le to bo th sys tems . F igu re 3 -14 shows the e lec t r i ca l i n te r¬ connection for the ADF-T-12C/D system. Any change in antenna moimting positions may require acabling reversal, as noted on figure 3-14.
2 - 4 . A . R E C E I V E R
The receiver is usually mounted in or underneath the aircraft instrument panel. When mounted in the instrument panel the receiver dust cover is secured to mounting brackets, or to mounting flanges in the panel cutout (figure 3-3). Outline dimensions for the rece ive rs a re shown in figures 3 -4 and 3 -5 . Ins ta l l a t i on p rocedure i s as fo l l ows :
(1) If a14-volt dc power source is used, disregard steps (2) and (3) and proceed to step (4).
(2) If a28-voIt dc power source is used, a28-volt lamp (type 313R, P/N 4003018-0502) must be substituted for the 14-volt lamp in the 201C/D (four lamps are required in the 201F).
S l ide cover back to expose lamp. Turn un i t over and remove sheet meta l screw t h a t s e c u r e s l a m p h o l d e r. E x c h a n g e l a m p s a n d r e a s s e m b l y. F o r 2 0 1 F r e c e i v e r, p roceed as fo l l ows :
Locate DSl through DS4 mounted in thumbwheel switches (Figure 2-1).
Remove yellow jumper between lug on common baseplate of DS1/DS2 and lug on common base plate of DS3/DS4. Discard.
(a)
(b)
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 2 - 1
S E C T I O N I I I N S T A L L A T I O N2-4. A. (2)
(c) Remove the white/black ground lead from existing 14 Vcommon ground bar and solder to the lug between DS3 and DS4.
Y E L L O W J U M P E R R E M O V E F O R 4 - 2 8 V+ S U P P L Y
S H I F T 6 N D T O H E R E F O R + 2 0 VDSI\\ DS2 DS3/DS4
7
S>J C® G R O U N D L E A D
k T O P
F R O N T P A N E L
Model 201F Lighting Schematic F i g u r e 2 - 1
Remove voltage-switch key retained by asheet-metal screw at the rear of the receiver. Position switch to "28" and replace voltage-switch key to lock switch in pos i t ion .
Fasten connector mounting bracket with attached interconnect cable assembly to rear of receiver dust cover with the three screws supplied.
Secure connector cover to rear of receiver dust cover with the four screws supplied.
Attach the receiver mounting brackets (not supplied) to each side of the dust cover with four 6-32 x3/8-inch machine screws and applicable washers and nuts. See figure 3-3.
Drill two holes on each side of instrument panel cutout. Holes must align with holes in customer-fabricated receiver moimting brackets. See figure 3-3.
Place receiver dust cover, with attached mounting brackets, behind panel cutout so that mounting holes in the bracket align with holes in the instrument panel.
Secure receiver dust cover to instrument panel with four 6-32 x3/8-inch screws and appl icable washers and nuts.
If necessary, secure the rear of the receiver dust cover with asuitable supporting bracket. Support bracket must be fabricated in the field to meet individual instal¬ l a t i o n r e q u i r e m e n t s .
(3)
(4)
(5)
(7)
(8)
(9)
(10)
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 2 1 - 1 3 7 12 - 2
S E C T I O N I I I N S T A L L A T I O N
2 - 4 . B . S E R V O a m p l i fi e r / i n d i c a t o r
Model 551A/C/E/RL indicators are designed for mounting behind the panel. Mounting- hole dimensions are included on the outline drawings in Section III,
Install the servo amplifier/indicators using the appropriate outline drawing as aguide. Carefully cut the dial opening in the panel and drill mounting holes. Allow at least three inches for cable connections and removal passage.
In dual installations, the two 551E indicators can be installed remotely using bracket P/N 62C035. Check cable lengths between both 551E, the two receivers, the 551C indicator and the 26-volt 400 Hz source. See figure 3-2.
The internal lighting connection for the 551RL is brought out on J1 pin 4. Mating con¬ nector P3 pin 4should be connected to the aircraft dimmer circuit on the flight instru¬ ment lighting bus. The indicator is factory wired for 14 Vdc operation. To convert the lighting to 28 Vdc, remove jumpers W1 and W2 and install jumper W3. These items are physically located on TB7 which is the rearmost terminal strip on the bottom side of the indicator (figure 2-2).
D S l I
m m m « T B 7 O
G N DD C i n p u t f r o m c o n n e c t o r J l - 4
Model 551RL Lighting Schematic F i g u r e 2 - 2
A U D I O A M P L I F I E R2 - 4 . C .
The optional audio (speaker) amplifier is designed to be mounted in any convenient loca¬ tion in the aircraft, such as behind the instrument panel, on ashelf where agood elect¬ rical ground can be made through the chassis or pin 5of Jl. Figure 3-1 illustrates the unit connected in the system. Installation procedures for the audio amplifier are as f o l l o w s :
(1) Check receiver to audio-amplifier cable distance.
Drill three holes in the selected mounting surface to the dimensions illustrated in figure 3-10 and partially insert three screws.
(2)
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 2 - 3
S E C T I O N I I I N S T A L L A T I O N2 - 4 . C .
(3) Mount the audio amplifier by inserting the screw heads through the mounting holes in the flanges.
Position the unit so that the screw heads slip in the notches of the mounting holes.
Tighten screws securely.
Wire audio-amplifier cable to receiver connector (Jl) and connect Amphenol plug to amplifier (see figures 3-1 and 3-14). Avoid routing output cable close to input c a b l e o r o t h e r a u d i o c a b l e s .
Mount and connect speaker to shielded lead.
(4)
(5)
(6)
(7)
2 - 5 . A N T E N N A I N S T A L L A T I O N
Accurate azimuth and over-the-station performance of the ADF-T-12C/D system requires the loop antenna be moimted exactly on the fore-and-aft center line of the aircraft.
S E N S E A N T E N N A2 - 5 . A .
(1) Determine whether the sense antenna is to be top or bottom mounted. Refer to the system interconnect diagram for correct antenna coimector wiring for bottom mount.
- C A U T I O N -
Do not mount either of the sense antennas near other trans¬ mitting/receiving antennas.
(2) When the 54-inch whip is employed as asense antenna (figure 3-13) it must be located at least 3feet from the propeller and mounted in aplace having sufficient structural strength to prevent tearing if the antenna should vibrate violently.
(3) When the longwire type sense antenna is used, the length should be 8to 12 feet. One end is supported by the feed-thru insulator and the other with an insulated strain relief anchored to top rudder structure.
Sense antenna and lead-in capacitance must be within the limits of 125 ±25 pF. Low-capacitance coaxial line should be used to minimize capacitive effects and provide proper signal ratios to the receiver.
2 - 5 . B . L O O P A N T E N N A
(1) Determine whether the loop antenna wUl be top or bottom mounted. Refer to the system interconnect diagram for correct antenna connector wiring for top mount.
(2) Select the approximate mounting location on the fore-and-aft centerline of the air¬ c r a f t .
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 12 - 4
S E C T I O N I I
I N S T A L L A T I O N 2-5. B. (2)
- N O T E -
Quadrantal error compensation must be done by trial and error before the exact mounting location can be determined. Aircraft must be well clear of any metal hangars, electric or telephone wires, buried cables, etc. that could cause bearing errors.
Temporarily tape the loop to the outside of the aircraft. Loop must be upside down for connector clearance and the aircraft positioned to anormal flight attitude. Make loop cable entrance into the aircraft without drilling any holes in the aircraft skin (via window, door, or removable inspection cover). Ensure adequate loop cable length for the selected location.
(3)
- N O T E -
Bearing indications on the servo amplifier/indicator will be reversed with the loop mounted upside down. Compute bearing differences accordingly.
(4) Use aground compass rose if available. If not, the aircraft directional gyro or compass must be used to determine aircraft rotation angles. If the compass must be used, compass error should be checked prior to proceeding.
(5) Select aradio station of known position, at least 20-miles distance and free from static and fading. Tune the receiver to the station. (See paragraph 2. 7. B. (1) remark on 201F tuning.)
(6) Rotate the aircraft so that the nose is pointing directly at the transmitting station. The servo amplifier/indicator must now read zero.
(7) Set the directional gyro to zero degrees (or note the compass heading) and in agree¬ ment with the servo amplifier/indicator.
(8) Rotate the aircraft counterclockwise around the compass rose in 15-degree incre¬ ments. Compare the directional gyro or corrected compass heading with the servo amplifier/indicator readings at each increment. Chart the results. The difference between the two readings is the quadrantal error. Maximum errors will be at the 45-, 135-, 225-, and 315-degree points.
Repeat steps (2) through (8) until aloop position along the aircraft centerline is found where the 6-degree loop compensation reduces the quadrantal error to a minimum. Secure loop in this location and lightly pencil mark the outline of the loop antenna on the surface of the aircraft .
(9)
(10) Remove the loop from the aircraft and locate the doubler plate over the center of t h e o u t l i n e .
- C A U T I O N -
Loop should be positioned so that holes are drilled only through the skin of the aircraft. Do not drill through frame stations or s t r i n g e r s .
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 2 - 5
S E C T I O N I I I N S T A L L A T I O N2-5. B. (10)
Mark and drill the five mounting holes in the aircraft skin.
Route loop cable through the interior of the aircraft, securing as necessary to prevent chafing on structure and/or interference with control cables. Avoid locating the cable closely parallel to noisy conductors such as inverter, alternator or other high current level conductors.
Place doubler plate in position inside the aircraft so that the mounting nuts on doubler plate align with fixed loop mounting screws. Apply Minnesota Mining and Manufacturing ECO-801 Type-A sealer between doubler plate and aircraft skin. See figure 3-11.
Secure cable connector and doubler plate to aircraft skin with two 6-32 placed in mounting holes from outside of aircraft.
Insert loop cable connector through doubler plate and aircraft skin from inside the aircraft. Apply ECO-801 Type-A sealer between doubler plate and cable connector.
- C A U T I O N -
If the loop to be installed is supplied with acompressible gasket ring, insert this between the loop connector and doubler plate.
Place loop in position so that loop and loop cable connectors mate. Apply ECO-801 Type-A sealer between loop gasket and aircraft skin.
Secure loop to aircraft skin with two 8-32 binding-head screws placed from outside aircraft to match with the elastic stop nuts on doubler plate. Loop gasket must be compressed to approximately l/32-inch at loop centerline.
S E N S E A N D L O O P A N T E N N A T U N I N G
(11)
(12)
(14)
(15)
(16)
2 - 6 .
2 - 6 . A . A D J U S T M E N T P R E PA R AT I O N
After the ADF-T-12C/D system is installed, the sense antenna and loop antenna tuning should be adjusted for optimum performance. These adjustments are located under the RE shield cover of the 201( )receiver chassis. Accessibility requires the use of lap- adapter cable, Bendtx part number 2V011-01. Early versions of this cable should be modified to include aDPDT toggle switch (P/N 2088618-0003) in the lead from pin 1 (sense antenna input to the receiver) and the lead from pin 16 (ADF servo signal output) at the receiver end of the cable, figure 2-3. This switch should be mounted on the bracket holding the connector plug to the receiver connector. Switch wiring should be short and as direct as practicable.
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 12 - 6
S E C T I O N I I I N S T A L L A T I O N2 - 6 . A .
TO SENSE ANTENNAa
T o R C V R J ] - l
r l 2 0 p F T U N E S E N S E
A m V
T U N E L O O P
T O I N D I C A T O Ra
T o R C V R J l - 1 6
L a p - a d a p t e r C a b l e M o d i fi c a t i o n S c h e m a t i c F i g u r e 2 - 3
2 - 6 . B . A D J U S T M E N T P R O C E D U R E S
(1) Remove receiver chassis from dust cover and connect lap-adapter cable between r e c e i v e r c o n n e c t o r J 1 a n d r e c e i v e r d u s t c o v e r c o n n e c t o r P I .
(2) Set the receiver function switch to REC, the bandswitch to the 190-440 kHz position, and the lap-adapter toggle switch to the Tune Sense position.
(3) Tune up to astat ion at , or as c lose as possib le to, 440 kHz for the ADF-T-12C (399 kHz for the 201F receiver).
(4) Using suitable tool, adjust trimmer C22 for maximum tuning indicator deflection. See figure 2-4. In the 201F receiver, capacitor C22 may be adjusted by connecting adc voltmeter set to +10 Vdc maximum between TP2 (+) and chassis ground. TP2 is connected to the col lector of t ransis tor Q9 in the lower- le f t rear sect ion of the 2 0 1 ( ) r e c e i v e r s .
(5) Set the function switch to ADF and align the loop stage in accordance with table 2-1. Use stations as close to the ends of the bands as possible. See figures 2-4 and 2-5.
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 2 - 7
S E C T I O N I I I N S T A L L A T I O N
R F S H I E L D
o o o o o o
C 2 2
/
R e c e i v e r, R F S h i e l d , B o t t o m V i e w F i g u r e 2 - 4
\ © o o o © G O G © O O O
(201C/D) ( 2 0 I F )
8 5 0 8 0 0
( 2 0 I C / D ) ( 2 0 I F )
4 2 0 4 0 0
( 2 0 I C / D ) ( 2 0 I F )
1 9 0 2 0 0
R F S H I E L D
Receiver, RF Shield, Top View F i g u r e 2 - 5
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 12 - 8
S E C T I O N I I
I N S T A L L A T I O N
T A B L E 2 - 1 L O O P S T A G E A D J U S T M E N T P R O C E D U R E
A D F - T - 1 2 C A D F - T - 1 2 D
B A N D S W I T C H
P O S I T I O N
R C V R . T U N I N G
F R E Q . k H z
B A N D S W I T C H
P O S I T I O N
R C V R . T U N I N G
F R E Q . k H z S T E P
N O . I N S T R U C T I O N S
1 9 0 - 4 4 0 k H z1 2 0 0 k H z 2 0 0 - 4 0 0 k H z 2 0 0 k H z With lap-adapter s w i t c h s e t t o T u n e
Sense pos i t ion a l low needle to point to s t a t i o n .
P r e s s T E S T s w i t c h
to d r i ve po in te r o f f approximately 90° and se t l ap -adap te r sw i t ch to Tune Loop pos i t ion.
A d j u s t L I f o r m a x i ¬ m u m i n d i c a t i o n o n
tuning meter (dc volt¬ m e t e r f o r 2 0 1 F r e ¬
c e i v e r ) .
Repea t i n s t r uc t i ons i n s tep 1except ad jus t C3.
R e p e a t s t e p s 1 a n d 2 u n t i l re tun ing g ives no inc rease o f m e t e r d e fl e c t i o n .
Repea t i ns t ruc t i ons i n s tep 1excep t ad jus t L2 .
Repea t i ns t ruc t i ons i n s tep 1except ad jus t C4.
R e p e a t s t e p s 4 a n d 5 u n t i l re tun ing g ives no inc rease o f m e t e r d e fl e c t i o n .
Repea t i n s t r uc t i ons i n s tep 1except ad jus t L3 .
Repea t i n s t r uc t i ons i n step 1except ad just C6.
R e p e a t s t e p s 7 a n d 8 u n t i l re tun ing g ives no increase o f m e t e r d e fl e c t i o n .
a .
b .
c .
2 S a m e 4 0 0 k H z S a m e 4 0 0 k H z
3 S a m e S a m e
4 4 2 0 - 9 0 0 k H z 4 5 0 k H z 4 0 0 - 8 0 0 k H z 4 0 0 k H z
4 2 0 - 9 0 0 k H z5 9 0 0 k H z S a m e 8 0 0 k H z
6 4 2 0 - 9 0 0 k H z S a m e
7 8 5 0 - 1 7 0 0 k H z 9 0 0 k H z 8 0 0 - 1 6 0 0 k H z 8 0 0 k H z
8 5 0 - 1 7 0 0 k H z8 1 7 0 0 k H z S a m e 1 6 0 0 k H z
8 5 0 - 1 7 0 0 k H z9 S a m e
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 1 2 - 9
S E C T I O N n I N S T A L L A T I O N
2 - 7 . E Q U I P M E N T C H E C K O U T
Before take-off, determine if the ADF-T-12C/D system is operating properly.
2 - 7 . A . P R E F L I G H T C H E C K
s Tune in stations evenly spaced on each band of the receiver. In the ADF-T-12C maximum tuning-meter deflection should be obtained at peak signal.
(1)
Adjust volume control to desired listening level.(2)
(3) With the function switch in the CW or BFO position, tune in one station in each band until aclear 1000-Hz signal is heard.
(4) Position aircraft on aknown true heading.
(5) S e t r e c e i v e r s w i t c h t o A D F a n d t u n e i n s t a t i o n .
Compare bearing on servo amplifier/indicator with true bearing. Bearings must agree within ±3 degrees with little or no "himting" observed on indicator.
Press TEST bu t ton on f ron t pane l o f rece ive r and observe ind ica to r po in te r. Ind i¬ cator pointer will rotate away from indicated bearing while TEST button is pressed.
(6)
(7)
Release TEST button, and observe indicator pointer. Indicator pointer should return to the ind icated bear ing.
(8)
For ADF-T-12D, se lec t aband o ther than tha t con ta in ing the s ta t ion d ia led in . The out-of-lock MON lamp should light.
(9)
Return the bandswitch to the correct band. The out-of-lock MON lamp should go out.
When the optional NORMAL/EMERGENCY switch is installed (figure 3-14), repeat the preflight check with the switch set to EMERGENCY; then return the switch to t h e N O R M A L p o s i t i o n .
(10)
(11)
\
If adual system is installed, turn one receiver OFF, check the other as described, then repeat fo r the second rece iver.
(12)
Rotate the azimuth knob to ensure full rotation of azimuth card (551RL only).(13)
Turn instrument lighting control ON. Ensure indicator lamps are operating.(14)
2 - 7 . B F L I G H T C H E C K
A i rborne tes t shou ld emp loy the fo l low ing fl igh t tes t p rocedure :
(1) Using the REC mode, select astation of average power from adistance of about 50 miles. Using tuning meter in the 201C/D, adjust receiver frequency until maximum signal s t rength is obta ined. When tuning 201F i t wi l l be apparent that audio f requency
B e n d i x A v i o n i c s D i v i s i o n I . B . 2 0 1 2 - 1 3 7 12 - 1 0
S E C T I O N I I I N S T A L L A T I O N2-7. B. (1)
response, as well as audio level, will increase slightly when tuned 1or 2kHz (de¬ pending on signal strength) on either side of the desired station. The correct tuning for optimum performance will be the exact station frequency and not the point of loudest audio. This is true of any ADF receiver but will be noticed more readily in the 201F receiver because of the precise tuning.
(2) F ly toward the s ta t ion .
(3) S e t t h e f u n c t i o n s w i t c h t o A D F.
Note the bearing on the servo amplifier/indicator. Unless the station is weak, there should be no prolonged hunting by the indicator pointer.
Make a360-degree standard rate turn and observe the servo amplifier/indicator. The indicator pointer should track the turn without "losing" the station.
(4)
(5)
(6) Select arange station to check the over-the-station performance of the system.
Set the receiver to ADF and home-in on the range station.
Maintain asteady heading and observe the indicator pointer as the aircraft approaches and passes over the station. The pointer should oscillate slightly and as the cone of silence is passed, should abruptly swing to areading of 180 degrees from the original bea r i ng i nd i ca t i on .
(7)
(8)
(9) Maintain heading until the station is passed. If pointer reversal is unsatisfactory, the information in table 2-2 may help in determining the trouble.
2 - 8 . INSTALLATION OF CW OSCILLATOR KIT OPTION (Part Number 2V017-01)
Refer to ADF-T-12B/C Maintenance Manual, LB. 2012A, for complete instructions.
T A B L E 2 - 2 O P E R A T I O N A L P R O B L E M S A N D P O S S I B L E C A U S E S
I N D I C A T I O N P O S S I B L E C A U S E
Reversa l before enter ing cone o f s i lence.
Reversa l a f te r reach ing cone o f s i lence.
E x t e n d e d a r e a o f c o n f u s i o n . E x c e s s i v e p o i n t e r o s c i l l a t i o n .
E x c e s s i v e q u a d r a n t a l e r r o r.
S e n s e a n t e n n a e l e m e n t t o o f a r a f t .
S e n s e a n t e n n a e l e m e n t t o o f a r f o r w a r d .
Sense antenna too long or too short.
L o o p i n c o r r e c t l y l o c a t e d o r p o s s i b l e a r e s u l t of change in aircraft configuration.
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