ELECTRICAL CONNECTIONS.... 14
POWER.....14 AVIONICS OUTPUTS.....14 SERIAL INTERFACE.....14 SPEAKER AND HEADPHONE OUTPUTS.....14 MICROPHONE INPUTS.....15 TRANSMIT KEY INPUT.....15 INTERCOM SELECTOR SWITCH....15 REMOTE FLIP/FLOP INPUT.....15
ANTENNA INSTALLATION AND CONNECTIONS... 15
COMM AND NAV ANTENNAS....15 USE OF SPLITTER AND COMBINER....16
EQUIPMENT INTERFACE..... 17 LIMITATIONS ON USING A COMPOSITE SIGNAL... 33 LIMITATIONS ON DISTANCE, SPEED, AND TIME INFORMATION.. 33 POST INSTALLATION CHECKOUT.... 33
MOUNTING / WIRING CHECK.....33
Apollo SL30 Installation Manual
SETUP AND CHECKOUT..... 33 FINAL SYSTEM CHECK..... 37
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS...40 SECTION 3 - SPECIFICATIONS...41 ELECTRICAL.....41 PHYSICAL.....41 ENVIRONMENTAL.....41 AVIONICS OUTPUTS....42 NAV RECEIVER PERFORMANCE....43
VOR...... 43 LOCALIZER..... 43 GLIDESLOPE..... 44 OBS RESOLVER..... 44 COMPOSITE OUTPUT.... 44
COMM RECEIVER PERFORMANCE....45 COMM TRANSMITTER PERFORMANCE...45 INTERCOM PERFORMANCE....46 CONTROL INPUTS....46 ANTENNA REQUIREMENTS....46
COMM ANTENNA...... 46 NAV ANTENNA..... 46
SERIAL INTERFACE....47 REAR CONNECTOR PINOUT....47 SECTION 4 - LIMITATIONS....49 INSTALLATION.....49 COMPUTATION RATES....49 OPERATIONAL....49 APPENDIX A - TROUBLESHOOTING....51 CONTACTING THE FACTORY FOR ASSISTANCE...52 APPENDIX B - PERIODIC MAINTENANCE..53 VOR CHECKS....53 EQUIPMENT CALIBRATION....53
REFERENCE OSCILLATOR (COMM ONLY).... 53
CLEANING THE FRONT PANEL....53 APPENDIX C - ENVIRONMENTAL QUALIFICATIONS...55 APPENDIX D - ACCESSORIES....57 FROM GARMIN AT, INC.....57 APPENDIX E - SERIAL INTERFACE SPECIFICATIONS..59 INPUT COMMANDS....59 OUTPUT MESSAGES....59 DATA FORMAT.....60 DEFAULT MESSAGE OUTPUT....60 MESSAGE FORMATS....60 ii Apollo SL30 Installation Manual
Table of Contents MESSAGE DEFINITIONS.... 61
INPUT MESSAGES......61 REMOTE VOR LIST.....62 REMOTE LOCALIZER LIST.....64 REQUEST DATA OUTPUT.....66 SET ACTIVE VOR/LOC FREQUENCY AND RECEIVER FUNCTION....67 SET STANDBY VOR/LOC FREQUENCY AND RECEIVER FUNCTION...67 SET STANDBY COMM FREQUENCY AND TRANSCEIVER FUNCTION...68 SET ACTIVE COMM FREQUENCY AND TRANSCEIVER FUNCTION...68 SET NAV AUDIO MODE....69 SET OMNI-BEARING SELECT (OBS) VALUE....69 DME SENSOR INPUT....70

COMM RADIO PERFORMANCE SPECIFICATIONS
Input voltage range 10 to 40 VDC Operating temperature range 20C to +55C Transmit power 8 watts (Carrier Power) Certified TSO C37d/JTSO 2C37e (Comm transmitting) Certified TSO C38d/JTSO 2C38e (Comm receiving) Certified TSO C128/JTSO 2C128 (stuck mic)

SYSTEM INTERFACES

NAVIGATION RECEIVER
The SL30 can be installed in several configurations based upon individual requirements. This includes with or without an external course deviation indicator. The CDI may be discrete, serial, or composite.

COMM TRANSCEIVER

For standalone installations, the Comm requires connections to: a standard Comm antenna a microphone (or microphones) a speaker or headphone power input These items may be installed dedicated to the SL30 Comm, or by connection to an audio panel. The system can be configured to mix the NAV audio with the Comm audio if no external audio panel is used.

SERIAL INTERFACE

DME Distance Measure Equipment SL/GX GPS products MX Multi-Function Display

REGULATORY COMPLIANCE

The Apollo SL30 is designed and tested to meet the following TSOs/JTSOs: FAA TSO-C37d/JTSO 2C37e for Comm transmit FAA TSO-C38d/JTSO 2C38e for Comm receive FAA TSO-C128/JTSO 2C128 for unintentional transmission (stuck mic) FAA TSO-C34e/JTSO C34e for ILS Glideslope receive FAA TSO-C36e/JTSO C36e for ILS Localizer receive FAA TSO-C40c/JTSO 2C40c for VOR receive FAA TSO-C66c/JTSO 2C66b for DME display The Apollo SL30 complies with the FCC requirements specified in: CFR 47, Part 87, Aviation Services, Subpart D, Technical Requirements The Apollo SL30 complies with the FCC requirements specified in: CFR 47, Part 15, Radio Frequency Devices, Subpart B, Unintentional Radiators The Apollo SL30 software is designed and tested to RTCA/DO-178B, level C and ED-12B, level C. Note: Unauthorized changes or modifications to the SL30 may void the compliance to required regulatory agencies and authorization for continued equipment usage.

UNPACKING THE EQUIPMENT

Carefully unpack the equipment. Visually inspect the package contents for any evidence of shipping damage. Retain all shipping containers and packaging material in case reshipment is necessary.

PACKAGE CONTENTS

As shipped from the Garmin AT factory, the Apollo SL30 package includes most items necessary for installation other than supplies normally available at the installation shop, such as wire and cable ties, and required input and output equipment. The standard items included in the package are listed in Table 1. Table 1 - Package Contents
Part # 430-6040-3xx Install kits 162-1575 162-1577 162-1008 202-0001 204-0037 204-2100 221-0400 224-0404 245-0027 310-5181-xx or 310-5197-xx 310-5192-xx 998-0048 Manual kits 560-0403-xx 560-0404-xx 561-0262-xx Accessories 115-0007 S712-0007-012 Description SL30 NAV/COMM Part number: 424-2006-300 15-pin d-sub connector shell 37-pin d-sub connector shell Right angle coax plug Cable tie Edge grommet Shoulder bushing 4-40 x 1/4 SS pan head Phillips machine screw with lock washer 4-40 x 1/4 SS flat head Phillips machine screw Crimp contact for d-sub, 20 to 24 awg wire Mounting frame NOTE: Only 310-5197-xx is qualified for helicopter use. Connector mounting plate 3/32 hex driver Part number: 564-0064-300 SL30 Users Manual SL30 Installation Manual SL30 Quick Reference Guide NAV signal splitter/combiner Internal 3 amp slow blow fuse Qty 2 6" 1 -4xx 1 Optional Optional

INSTALLATION CONSIDERATIONS

MOUNTING CONSIDERATIONS

The SL30 is designed to mount in the avionics stack in the aircraft instrument panel within easy view and reach of the pilot. The standard package includes a mounting frame for ease of mounting, connections, and service of the unit. Allow an additional one-inch clearance to the rear of the mounting frame for connectors and cables. For typical installations, the SL30 does not require external cooling. When mounting the unit, leave a clearance of 1/8 to 1/4 inch between avionics to allow for air circulation.
MINIMUM SYSTEM CONFIGURATION
VFR Installation VFR installation need only include an SL30 with power, audio, and antenna connections. Without an external CDI, no glideslope information is obtainable. However, the unit will maintain full VOR and Localizer functionality including an internal CDI display. IFR VOR/LOC Installation IFR installation requires: SL30 External CDI/HSI indicator that meets the following criteria: 1. The course deviation indicator shall have an input impedance of 1 k ohm 10% and a deflection sensitivity of 150 mV 10% for full scale deflection. 2. The valid flag shall have an input impedance of 1 k ohms 10%.
Installation 3. The valid flag sensitivity shall be 125 mV 10% for the flag to leave the stop and 260 mV 10% maximum for flag to be fully concealed. 4. The To/From flag shall have an input impedance of 200 ohms 10% and a sensitivity of 40 mV 15% at 25oC with flag fully in view. 5. The OBS resolver should be compatible with a standard 6-wire OBS interface: H.Reference output high C.Reference output low D.S1 COS input high E.S3 COS input low F.S4 SIN input high G.S2 SIN input low Any electrical zero crossing will work because the SL30 will calibrate out any errors. Glideslope Installation Glideslope installation requires: SL30 External non-numeric glideslope indicator that meets the following criteria: 1. The glideslope deviation shall have an input impedance of 1 k ohm 10% with a deflection sensitivity of 150 mV 10% for full scale deflection. 2. The glideslope valid flag shall have an input impedance of 1 k ohm 10%. 3. The glideslope valid flag sensitivity shall be 125 mV 10% for the flag to leave the stop, and 260 mV 10% maximum for flag to be fully concealed. Helicopter Requirements The SL30 is qualified for helicopter installation with certain mount tube and SL configurations (see Section 4 Limitations).

EQUIPMENT MOUNTING

Once the cable assemblies have been made, attach the 15- and 37-pin d-sub and coaxial cable connectors to the rear connector mounting plate and the mounting frame as illustrated in Figure 4 and Figure 5. Route the wiring bundle as appropriate. The rear connector plate should be attached to the mounting frame before installing the frame in the instrument panel. The rear connector plate can be used to tie down the cable assemblies. Use the supplied edge guard to protect the cable from sharp edges. Connect the shield grounds directly to the connector mounting plate. Once the cable assemblies are complete and the connectors are attached to the mounting frame, install the mounting frame assembly in the instrument panel as illustrated in Figure 2. Be sure to use low-profile head screws in the side of the mounting frame so the unit will slide in and out freely. Attach the front of the mounting frame to the instrument panel. Use support brackets to attach the rear of the frame to the aircraft.

MOUNTING TUBE INSTALLATION
Care must be taken when installing the mounting tube to ensure you can properly insert and secure the unit. There must be a minimum vertical spacing of 0.040 inches between units to prevent interference with the cam locking mechanisms. Mounting tubes with clearance
Installation dimples help maintain the proper clearance. The mounting tube must be installed with the clearance dimples pointing up. The mounting tube should be flush to the instrument panel and allow sufficient clearance for the back of the bezel of the unit to mount flush to the mounting tube. Sufficient clearance must exist in the instrument panel opening to allow ease of insertion and removal of the unit. If the back of the unit bezel does not mount flush to the mounting tube, the connector may not engage fully.
Figure 2 - Full Stack Mounting Tube Spacing Secure the mounting tube to the instrument panel structure. Mounting screw heads must not protrude into the mounting tube. Be sure to use the appropriate screws so the unit will slide in and out freely. The screws attaching the mounting tube to the instrument panel structure must not interfere with the insertion of the unit. Failure to prevent interference will result in damage to the unit or prevent its insertion. Take care that the mounting tube is not distorted when it is attached to the instrument panel and structural supports. Shims may be necessary to properly install the mounting tube. If the mounting tube is distorted out of square, the unit may either bind when being inserted or the cam lock may not engage.

UNIT INSERTION

Position the cam lock as shown below. The front lobe of the cam should be vertical. The cam lock mechanism should be fully unscrewed (turned counter-clockwise). Slide the unit into the frame. Turn (clockwise) and carefully hand-tighten (4 in-lb max.) the cam lock mechanism using only the 3/32" hex driver provided in the installation package. Using a larger tool than the one provided makes it easy to exceed the allowable torque on the cam lock resulting in damage to the unit. The unit will be pulled into the frame securing the unit and the connectors when fully engaged. Do NOT overtighten. The back of the bezel must be flush to the mounting tube. If the cam lock is hard to turn or the unit does not seat fully, the unit is probably binding and the mounting tube should be checked.
Figure 3 - Cam Lock Positioning

UNIT REMOVAL

To remove the unit from the mounting frame, turn the screw counter-clockwise with the hex driver to unscrew the cam lock mechanism. The unit will begin to pull away from the mounting tube. Turn the screw until slight resistance is felt and then pull the unit from the frame. Do not exert excessive turning force at the end of the cam lock travel or the unit may be damaged. With the cam lock fully disengaged, pull the unit straight out holding onto the sides of the bezel. It is not recommended that you pull the unit out by the rotary knobs. No special extraction tools are required, if the mounting tube is properly installed.

Microphone input connections should be made using a twisted pair shielded cable. Attach the signal ground to the mic ground pin on the rear connector and connect the shield to the rear connector plate.

TRANSMIT KEY INPUT

The TxKey input on the rear connector must be pulled low to ground to enable the transmitter. This input should be connected to a microphone or yoke mounted momentary push button switch.

INTERCOM SELECTOR SWITCH

The SL30 includes a voice activated intercom function that can be enabled by an external control switch. This is an optional connection. When making connection for the intercom selection, connect the intercom selection input to a remote mounted normally open switch (an alternate action switch can be used). Connect the other terminal of the switch to ground. The intercom function is enabled when the input is pulled low to ground.

REMOTE FLIP/FLOP INPUT

The SL30 includes a remote flip/flop input. This is an optional input that can be connected to a remote mounted (such as on the yoke) momentary push button switch which pulls the input low to ground. The remote flip/flop input will only toggle the Comm frequencies when Comm frequencies are displayed and will only toggle NAV frequencies when NAV frequencies are displayed.
ANTENNA INSTALLATION AND CONNECTIONS

COMM AND NAV ANTENNAS

The SL30 requires a standard 50 vertically polarized Comm antenna and a horizontally polarized NAV/VOR/Localizer/Glideslope antenna. Follow the antenna manufacturers installation instructions for mounting the antennas. The Comm antenna should be a standard Comm antenna that operates on Comm frequencies between 118.00 and 137.000 MHz. The NAV antenna should be a VOR/Localizer/Glideslope NAV antenna that receives VOR frequencies between 108 and 117.95 MHz, and localizer frequencies between 108 and 112 MHz and glideslope information between 328.6 and 335.4 MHz. The NAV and Comm antennas should also be mounted as far apart as practical from the ELT antenna, preferably one on top and the other on the bottom of the aircraft fuselage. Some ELTs have exhibited re-radiation problems generating harmonics that may interfere with GPS signals. This can happen when the Comm (SL40 or any other Comm) is transmitting on certain frequencies such as 121.15 or 121.175 MHz, which may cause the ELT output circuit to oscillate from the signal coming in on the ELT antenna coax. The antenna coax cable should be made of RG-142B or a comparable quality 50 coax. Assembly instructions for the rear coax connector are included in Figure 6.

Figure 18 - SL30 NAV to Sandel Discrete Connections

GSI Up GSI Down

NAV 29
NAV ILS Enrgze 10 Composite

Composite 19 Gnd 37

1. Use shieled cable for resolver signals. 2. Connect cable shields to the mounting frame: pigtails < 1.25 inches. 3. Connect shields chassis ground at both ends of each shielded cable. 4. Refer to Limitations on Using a Composite Signal paragraph in this chapter. 5. Not all indicator connections are shown, only those interfacing to the SL30. Consult the appropriate installation manuals for complete wiring instructions.
Figure 19 - SL30 NAV to Sandel SN3308 Converter Connections
Sperry Unisys/Honeywell Lamp Voltage From Dimmer Circuit

Sperry RD 550A P1 P2 C D

Sperry RD 650 P1 P6 +Up +Down
GSI Up GSI Down +GS Flag -GS Flag GS Superflag
Glideslope +Flag Glideslope -Flag
Glideslope Superflag Glideslope Superflag Lo

CDI Right CDI Left

+ Right + Left

NAV Superflag

NAV Superflag NAV Superflag Lo

OBS A/H OBS C

OBS D (COS Hi) OBS E (COS Lo)

Rslvr{F} Rslvr{G}

OBS F (SIN Lo) OBS G (SIN Lo)
Figure 20 - SL30 to Sperry RD 550A and RD650 Wiring
Collins Rockwell Lamp Voltage From Dimmer Circuit

Collins 331A-6P P34

Collins 331A-9G P1 P6
Collins PN-101 P1 r q +Up +Down
Figure 21 - SL30 to Collins 331A-6P, 331A-9G, and PN-101 Wiring

Century Flight Systems

Lamp Voltage From Dimmer Circuit

Century NSD 360A CD 28

Century NSD 1000 CD 28 Glideslope +Up Glideslope +Down
Glideslope Flag + Glideslope Flag -

Right Dev + Left Dev +

From + To +
OBS Rotor H OBS Rotor C OBS Stator D OBS Stator E OBS Stator F OBS Stator G
Figure 22 - SL30 to Century NSD 360A and NSD 1000 Wiring
LIMITATIONS ON USING A COMPOSITE SIGNAL
If an external converter is driven from the composite output in conjunction with a full function CDI/HSI with resolver, the indicator head type, when selected from the Setup Mode during the post installation checkout, should be RESOLVER. In this installation, the composite output will be disabled whenever the VOR monitor mode is active or back course localizer mode is enabled. This will cause the external converter to flag. If the CONVERTER option is selected from the Setup Mode as the indicator head type, neither of these two options is available to the pilot and the composite output should always be valid. The CONVERTER setup option should be used if an external converter is the only indicator interfaced to the SL30.
LIMITATIONS ON DISTANCE, SPEED, AND TIME INFORMATION
When Nav tuning is provided to the Apollo GX, the GX will output Distance, Speed, and Time (DST) information on the MapCom output. It is the installers responsibility to ensure that this information is displayed in an acceptable fashion. For instance, in an installation where two Apollo SL30s are integrated in the system, it is not appropriate to display DST information on the SL30 that is not providing the tuning information. Apollo SL30 SW version 1.2, or later, provides the means for disabling the display of DST information.

Installation Control Test In the Setup Mode, turn the large knob to reach the CONTROL TEST page. This function tests the operation of the front panel controls on the SL30. 1. Press each button. The function name for each control will appear on the display after the button is pressed. 2. Turn the small knob. The numeric values on the right side of the display will change. Display Test In the Setup Mode, turn the large knob to reach the PRESS SEL TO TEST DISPLAY page. 1. Press SEL. 2. A series of display tests will be performed to test each LED. Observe the display for any missing LEDs. 3. When the test is completed, the display will return to normal mode. Flags Test The Flags test in Setup Mode sends an active signal for each selected flag so you can test the interface to the connected devices directly from the front panel while you are on the ground. The Flag tests include LOC (Localizer), BC (Back Course), FR (From), TO (TO), NAV (NAV), and GS (Glideslope). When a selection is in large text, an active signal is sent from the SL30. 1. In the Setup Mode, turn the large knob to the FLAGS TEST page. 2. Press SEL. The Localizer (LOC) selection will flash. 3. Turn the small knob to change the selection to large text. Check the attached indicator for the appropriate flag. Turn the small knob one click in either direction to change the selection back to small text. 4. Turn the large knob to the next flag type and turn the small knob to change it to large text. You can only select FR or TO as active, not both at the same time. 5. Ensure the flags are reset to all small text when you are finished testing. CDI Test This function tests for CDI function and allows for calibration between the SL30 and the attached CDI. 1. In the Setup Mode, turn the large knob to reach the CDI TEST page. 2. Press SEL to activate selection. The value will flash. 3. Rotate the small knob to change the value. The values "0-6" may be used to center the CDI needle. 4. Turn the small knob left or right to center the needle. 5. Press ENT when the needle is centered. 6. Turning the small knob left or right past a value of "6" will test the deflection of the CDI needle. GSI Test This function tests for GSI function and allows for calibration between the SL30 and the attached GSI. 1. In the Setup Mode, turn the large knob to reach the GSI TEST page. 2. Press SEL to activate selection. The value will flash. Apollo SL30 Installation Manual 35

FINAL SYSTEM CHECK

The SL30 functions should be complete at this time. The final check includes verifying VOR and ILS operation. Start with the unit turned on and operating in the normal mode. Refer to the users manual for operating instructions. RS-232 Serial Interface Checks The interfaces to other equipment, such as the GX series GPS, should be checked as follows: 1. Operate the SL30 and GX unit in normal mode. 2. Press the Direct To button on the GPS unit and select an airport. Press ENT. 3. Operate the SL30 in Comm mode. Press SEL. Apollo SL30 Installation Manual 37
Installation 4. Verify that the remote frequencies of the airport selected via the GPS unit are displayed on the SL30. The interface to a DST data source (such as an Apollo GX or DB30) should be checked as follows: 1. Operate the SL30 in NAV mode and ensure the DME is operating with a valid signal. 2. Press the SEL button to bring up the NAV frequency recall lists. 3. Turn the large knob one click to the left (counterclockwise) to show the DST display prompt. If you do not see the Show DST Display, either the feature is disabled, or you are not receiving the data through the serial port. 4. Press ENT to replace the current NAV display with DST data. Verify that DST data is passed to the SL30. To check the serial data output connections, verify the data from the SL30 can be displayed on the other units, such as the MX series multi-function display or the Apollo GX Nav Frequency display. For serial interface checks to a serial CDI consult the CDI installation checkout procedures. Comm Flight Test Check A flight test is recommended as a final installation verification. The performance may be verified by contacting a ground station at a range of at least 50nm while maintaining an appropriate altitude and over all normal flight attitudes. Performance should be checked using low, high, and mid band frequencies. Check the VOR 1. Tune a local VOR station within 50 miles. 2. Verify the audio ident/voice quality. 3. Verify the Morse code decoder IDs the station (95% probability). 4. Fly to and from the station. 5. Verify NAV flag, TO/FR flag, and CDI are operational. 6. Record accuracy in System Log (see manual). Check the ILS 1. Tune an ILS at the local airport. 2. Verify the audio ident/voice quality. 3. Verify the Morse code decoder IDs the station (95% probability). 4. Fly the approach. 5. Verify NAV flag, GS flag, and CDI and GSI are operational. 6. Verify BC annunciator.

CONTROL INPUTS

Transmit key..Input pulled low to ground to enable the transmitter Intercom select..Input pulled low to ground to enable the intercom function Flip/Flop..Remote Comm flip/flop input, connect to a momentary button to ground for remote flip/flop operation.

ANTENNA REQUIREMENTS

COMM ANTENNA
The Apollo SL30 requires a VHF Comm antenna meeting the following specifications: Standard 50 vertically polarized antenna with a VSWR < 2.5:1.

NAV ANTENNA

The Apollo SL30 requires a VHF NAV antenna meeting the following specifications: Standard 50 horizontally polarized antenna with a VSWR < 3:1 Capable of receiving VOR/LOC/GS (Recommend Comant Industries P/N CI 157P) 108.00 117.95 MHz (VOR/LOC) 328.60 335.4 MHz (GS) Note: Multiple NAV antennas may be used with an RF signal splitter/combiner, part number 115-0007, at the radio. Refer to page 16.
RS-232.. Defined in Appendix E - Serial Interface Specifications

REAR CONNECTOR PINOUT

The SL30 includes two rear panel connectors, a 15-pin for the Comm interface connections and a 37-pin for the rear panel connections. The pinout for the connectors is listed in the following tables. Table 2 - Comm Interface Connector Pinout Pin #
I I O I -O I I I I O I O O I

Connection

Power + Reserved Reserved TxKey NC Speaker Mic ground Mic 1 Power ground Reserved Reserved Intercom select Audio ground Headphone Mic 2

Function

Main DC power input Do not connect Do not connect Transmit enable key, pulled low to transmit Do not connect Speaker terminal output Microphone input ground connection Microphone input #1 Main power ground input Do not connect Do not connect Intercom function select, pulled low to turn on the intercom function Speaker and headphone ground connection Headphone terminal output Microphone input #2

Viewed from rear of unit

Table 3 - Rear Panel Connector Pinout Pin #
I I O I O I I I O O O O O O O O --O O O O O O O I O O O O O O O O -O O
Power + Power ground Serial ground RxD1 TxD1 Test Input OBS_D {S1} Flip/Flop GSI superflag Nav + valid + FROM + TO CDI + Right CDI + Left Back course OBS_F {S4} Reserved Reserved Composite Output Audio ground Reserved Reserved NAV Audio Output OBS_H {R HI} OBS_C {R LO} OBS_E {S3} Nav superflag GSI + valid NAV - valid GSI + Up GSI + Down GSI - Valid ILS energize OBS_G {S2} Reserved Power control Ground (comp)
Main DC power input Main power ground input RS-232 signal ground RS-232 channel 1 serial data input RS-232 channel 1 serial data output Reserved for manufacturers test Resolver input pin from Channel D (COS) Remote NAV/Comm frequency flip/flop input GSI high level valid flag output Nav low level valid flag output + From flag output + To flag output CDI + Right output CDI + Left output Active low output when reverse sensing is engaged Resolver input pin from Channel F (SIN) Do not connect Do not connect VOR/LOC composite signal Audio signal ground pin Do not connect Do not connect Low level audio output Resolver output pin to channel H Resolver return signals C Resolver return signals E Nav high level superflag output GSI low level valid flag output Signal ground for NAV valid flag GSI +Up output GSI +Down output Signal ground for GS valid flag Active low output when a localizer frequency is tuned Resolver return signals G Do not connect Power control output sinks up to 50 mA when unit is on VOR/LOC composite ground return

Environmental Qualification Form Manufacturer: Garmin AT, Inc. 2345 Turner Road SE Salem, Oregon 97302 DO-106C Description of Conducted Tests Section
4.0 4.5.4 4.6.3 5.0 6.8.0 9.0 10.0 11.0 12.0 13.0 14.0 15.0 16.0 17.0 18.0 19.21 22.0 23.0 24.0 Equipment tested to Category C1 No cooling required Equipment tested to 35,000 feet Equipment tested to Category C, 2C/min Equipment tested to Category A, standard humidity environment Equipment tested for both operational and crash safety shocks. (Equipment operated normally after the crash safety shocks.) Equipment tested without shock mounts to Categories B, M, and N (tested to Robust Helicopter Vibration per DO-160D) Equipment identified as Category X, no test required Equipment identified as Category X, no test required Equipment identified as Category X, no test required Equipment identified as Category X, no test required Equipment identified as Category X, no test required Equipment identified as Category X, no test required Equipment is Class Z Equipment tested to Categories A & B Equipment tested to Category A Equipment tested to Categories A & B Equipment tested to Category Z Equipment tested to Category V for conducted, Category U for radiated Equipment tested to Category Z Equipment tested to Categories A3 and B2 Equipment identified as Category X, no test required Equipment identified as Category X, no test required
Environmental Qualifications The Apollo SL30 Nav module has been tested to the following environmental categories per procedures defined in RTCA/DO-160D. Environmental Qualification Form SL30 NAV portion Manufacturer: 430-6040-3XX Garmin AT, Inc. TSO-C34e, TSO-C36e, TSO-C40c, & 2345 Turner Road SE TSO-C66c Salem, Oregon 97302 DO-160D Description of Conducted Tests Section
4.0 Equipment tested to Category B1 with Operating temp: -20C to +55C Short time hi temp: to +70C Ground survival temp: -55C to +85C No cooling required Equipment tested to 25,000 feet Equipment tested to Category C, 2C/min Equipment tested to Category A, standard humidity environment Equipment tested for both operational and crash safety shocks to Category B. (Equipment operated normally after the crash safety shocks.) Standard vibration category S (curves M and B) Robust Helicopter Vibration Category U (curves F and F1) Equipment identified as Category X, no test required Equipment identified as Category X, no test required Equipment identified as Category X, no test required Equipment identified as Category X, no test required Equipment identified as Category X, no test required Equipment identified as Category X, no test required Equipment is Class Z, <0.3 meters Equipment tested to Categories A & B Equipment tested to Category A Equipment tested to Categories A & B Equipment tested to Category Z Equipment tested to Category V Equipment tested to Category M Equipment tested to Categories A3 and B2 Equipment identified as Category X, no test required Equipment identified as Category X, no test required Equipment tested to Category A

REMOTE LOCALIZER LIST

The following two commands work together in allowing remotely connected devices to provide a list of localizer frequencies associated with an airport to the SL30. The remote device should first send the Remote Localizer List Header command (message identifier 22), followed by a sequence of Remote Localizer Input commands (message identifier 23). The SL30 maintains a single remote localizer list, so each new list received will replace any previous list. Subsequent receptions of localizer lists for the same airport are ignored. There may be up to twenty entries in the remote Localizer list. Any entries past twenty will be ignored. Remote Localizer List Header This input command marks the beginning of a Localizer list sent by a remote device. It specifies the five character airport identifier associated with the localizer frequencies in the list. Message format: 64 Apollo SL30 Installation Manual
Serial Interface Specifications V. Message Class. This is a VHF NAV message. 22.. Message Identifier. aaaa. Airport identifier. Note that if the airport identifier is less than four characters, then the trailing characters will be filled with spaces. Airport Identifiers are restricted to using ASCII characters 0-9 and A-Z. Example message: $PMRRV22SLE<Sp><chksum><CR><LF> Indicates the start of a remote localizer list associated with the airport SLE. Remote Localizer Input This input is used to input Localizer frequency data used for the remote recall function. The data consists of three characters to identify the runway associated with the localizer, followed by two characters defining the frequency. Message format: V. Message Class. This is a VHF NAV message. 23.. Message Identifier. iiii. Station or Runway identifier. This field will provide an identifier for the localizer which can be either the actual station identifier or a string indicating the runway associated with the localizer. The station identifier can be up to four characters long. A runway identifier will typically be two numbers that indicate the runway direction followed by the character R, C, or L to differentiate between parallel runways (right, center, and left). Note that if either type of identifier is less then four characters, then the trailing characters will be filled in with spaces. Identifiers are restricted to using ASCII characters 0-9 and A-Z. mk. Frequency: m = MHz, where m = MHz frequency 30h, with the desired frequency ranging from 108 to 111 MHz, or 3Ch to 3Fh; k = (desired kHz offset / 25 kHz) + 30h, where the desired frequency ranges from 000 to 950 kHz, or the even numbers from 30h to 56h. Note that the field will be checked to ensure that it is in range and a valid localizer frequency. Frequencies used for VORs, which can also be found in the range of 108.10 to 111.95 MHz, will not be accepted in this message type. Example message: $PMRRV2331<Sp><Sp>><<chksm><CR><LF> Identifier is 31 , indicating a runway, and the localizer frequency is 110.300 MHz.

SET NAV AUDIO MODE

This message is used to change the current NAV audio mode. There are three possible settings for this mode. The first is OFF, which suppresses all of the NAV audio. The second is IDENT, which will suppress the voice portion of the NAV audio signal and emphasize the Morse Code station identifier. The third choice is VOICE, which will emphasize voice signal and suppress the Morse Code station identifier. Message format: V. Message class. This is a VHF NAV message. 31.. Message identifier. a. NAV audio mode. 0 = OFF, I = IDENT, V = VOICE Example message: $PMRRV31I<chksm><CR><LF> Set the current NAV Audio mode to IDENT.
SET OMNI-BEARING SELECT (OBS) VALUE
This message is used to set the OBS value used by the SL30 as the selected radial for computing the course deviation from a VOR. This message will have no effect unless the SL30 is configured to use the internal OBS source, or a serial OBS source. Message format: Apollo SL30 Installation Manual 69
Serial Interface Specifications V..Message class. This is a VHF NAV message. 34.Message identifier. vvv..OBS Value in degrees, ranging from 000 to 359. Example message: $PMRRV34310<chksm><CR><LF> Set the OBS value to 310 degrees.

DME SENSOR INPUT

This message is used to input the range, ground speed, and ETA decoded from an external DME sensor. Message format: V..Message class. This is a VHF NAV message. 41.Message identifier. rrrr.Range from DME station in 1/10th of a nautical mile units. The first two digits are the 10s and 1s place of the range, and the last digit is the 1/10ths place. This field may range in value from 0.0 NM (0000) to 999.9 NM (9999). If the distance from the DME station is greater than 999.9NM, the value should be encoded as ----. sss.Ground speed with respect to DME station in knots. This field may range in value from 0 knots (000) to 999 knots (999). If the ground speed with respect to the DME station is greater than 999 knots, the value should be encoded as ---. hmm..Time to station in hours and minutes. This field may range in value from 0 hours and 0 minutes (000) to 9 hours and 59 minutes (959). If the time to the station is greater than 9 hours and 59 minutes, the value should be encoded as ---. Example message: $PMRRV410983055147<chksm><CR><LF> Range from DME station is 98.3 NM, ground speed with respect to station is 55 knots, and the estimated time to the station is 1 hour and 47 minutes.

RESET STATUS

This message is sent to indicate to the host that the SL30 is running and ready to accept data on the serial port. It will be sent once upon startup and when requested by the host. Message format: V..Message class. This is a VHF NAV message. 20.Message identifier.
Serial Interface Specifications Example message: $PMRRV20<chksm><CR><LF> SL30 is running and ready to accept serial input.

Received an unknown message.

NAV RECEIVER STATUS

This message is used to output the current status of the NAV receiver. It will be output upon request or whenever the status changes. Message format: V..Message class. This is a VHF NAV message. 28.Message identifier. mk.Active NAV frequency: m = MHz, where m + 30h = desired MHz frequency in the range of 108 to 117 MHz. k = desired frequency in kHz, where k = (desired frequency / 25 kHz) + 30h, with desired frequency in range of 000 to 975 kHz in 50 kHz steps. mk.Standby NAV frequency: m = MHz, where m + 30h = desired MHz frequency in the range of 108 to 117 MHz. k = desired frequency in kHz, where k = (desired frequency / 25 kHz) + 30h, with desired frequency in range of 000 to 975 kHz in 50 kHz steps. s..Status: N = Normal mode, M = Monitor mode Example message: $PMRRV28E4?PM<chksm><CR><LF> Active NAV frequency is 117.100 MHz, Standby NAV frequency is 111.800 MHz, receiver is in monitor mode.

NAV AUDIO MODE

This message is used to output the current NAV audio mode. There are three possible settings for this mode. The first is OFF, which suppresses all of the NAV audio. The second is IDENT, which will suppress the voice portion of the NAV audio signal and emphasize the Morse Code station identifier. The third choice is VOICE, which will emphasize voice signal and suppress the Morse Code station identifier. Message format: V..Message class. This is a VHF NAV message. 29.Message identifier. a..NAV audio mode. 0 = OFF, I = IDENT, V = VOICE Example message: $PMRRV29I<chksm><CR><LF> The current NAV Audio mode is IDENT.
NAV MICROCONTROLLER SOFTWARE VERSION
This message is used to output the version string for the NAV microcontroller software. Message format: V. Message class. This is a VHF NAV message. 30.. Message identifier. vvvv.. Software version in ASCII e. Engineering version flag: R = Released version. E = Engineering version. Example message: $PMRRV300103E<chksm><CR><LF> NAV Microcontroller software is version 1.03. It is an engineering version.

NAV DSP SOFTWARE VERSION

This message is used to output the version string for the NAV DSP software. Message format: V. Message class. This is a VHF NAV message. 31.. Message identifier. vvvv.. Software version in ASCII e. Engineering version flag: R = Released version. E = Engineering version. Example message: $PMRRV310101R<chksm><CR><LF> NAV DSP software is version 1.01. It is a released version.

ADC DATA OUTPUT

This message outputs the current value of one of the ADC (Analog to Digital Converter) channels read by the NAV Microcontroller. This message is only available in normal mode. Message format: V. Message class. This is a VHF NAV message. 32.. Message identifier. c. ADC channel: 0 to = Input voltage level, in units of 125 mV. 1 = 3.3V reference, in units of 15 mV, value ranges from 0 to 255. 2 = 5V reference, in units of 25 mV, value ranges from 0 to 255. Apollo SL30 Installation Manual 75