EQUIPMENT INSTALLATION MANUAL For the GDC ROLL STEERING CONVERTER P/N 0-000-XX-00( ) April, 0 DAC International 0 McNeil Drive Austin, TX Copyright 0, DAC International. All rights reserved. 0-0-0 Z.doc 0-0-0 Page of
RECORD OF REVISIONS REV DESCRIPTION DATE APPROVED IR INITIAL RELEASE E --0 LW A Correct P/N of mating connector E //0 LW B CHANGED BREAKER TO AMPS E-0 //0 LW C Reduced V and V install kits into one universal kit and added instructions for configuration. Added wiring //0 LW diagram for Bonanza A-. E0 D Omit approval pending E //0 LW E Add numerous wiring diagrams E 0//0 LW F Add additional wiring diagrams, correct table E /0/0 LW G Add lighting bus circuit diagram to all wiring diagrams. Omit jumper on drawings Fig. &. /0/0 CC Add note to installation section, page. E H Add Reference page for lighting connections and correct drawings. Add KLN- incompatibility stmt to Operation Overview and Appendix A. Correct pin references on ARINC HSI drawings. Remove Isolation Coupler from Fig. 0. Add 0 model & update all applicable sections and drawings. Add Isolation Coupler to Figure drawing. Add Follow-on Installation Data form and instructions. E 0//0 LW I Add FD and AP0 drawing. E Delete 0-00-0 kit information. Edit drawings to reflect 0 vs 0 differences //0 CC J K Correct typo on Figure ARINC HSI with Century IV drawing; Add Isolation Coupler requirement statement to OPTIONAL EQUIPMENT section; Add various drawings; minor changes on misc drawings; added Appendix D, Receiver interconnect to RS/ARINC ; Added STC Permission Stmt E //0 LW //0 LW L Added various drawings; Added gain jumper flag note to various King autopilot drawings; Corrected pin-out on various STEC drawings; Add note to Appendix C. Add Note: This A/P is not STC d on all relevant drwgs. Fig Add Note: Fig Remove AP-Offset line Add jumper b/t pin 0 & GainSel Add pin to J 00hz Rtn //0 LW 0-0-0 Z.doc 0-0-0 Page of
REV DESCRIPTION DATE APPROVED Fig Add lines b/t DG and Iso Coupler and pin info for D Exc Fig Change jumper for GainSel to dotted line and add flag note: If turn is sluggish, install this jumper. Fig 0 Add line between pin of AP Comp and pin of GDC Add KCP pins and dotted lines Fig Add Iso Coupler to prevent voltage spike to Roll Computer when setting breaker. Fig Add STEC 0 Pinout E M Added various drawings; Revised website link on pg ; Added KLN-A to Operation Note Appendix A Note as non-compatible with the GDC. /0/0 LW Fig - Revised wiring illustrations. Fig - Add kz flag note. Fig 0 - Remove Type Sel jumper & added jumper to Phase Sel. Fig - Add Type Sel jumper. Fig Add Phase Sel. N Added paragraph to PMA Section, pg. Removed Installation Manual from kit part list, pg. Added paragraph to Installation Section, pg. Added paragraph to Environmental Section, pg. Revised Figure, Pg, Relay Interconnect Diagram. Fig, Pg 0 - Add KC- computer for KFC00 autopilot & ground shield at pin & of GDC. Fig, Pg Removed jumper from pins &. Removed non-stc d drawings Added additional wiring diagrams (Fig,,,,,,,,,, & ). E 0/0/0 BH P Added ARC00 with IG-A / NSD-0 / NSD-000 0//0 BH drawing & Century 000 drawings. E R Added KAP0 with KIA drawing E0 /0/0 BH S Delete S-TEC 0//0/ (DC) with S-TEC 0. Revised S-TEC 0 (AC) with 0 HSI drawing to include S-TEC /0/ autopilots. Added STC Pending statement to ARC00/00, Century 000 and KAP 0 drawings. E T Corrected EXC pin reference on SN00 P on Figure drawing E0. U Revised Century II or III with D drawing to change pins D & E at CD (Pigtail) from C & F at CD (Fixed). Changed labels to DG Exc KHz from Roll Exc KHz. Reworded flag notes for clarity on all drawings. Added 0//0 BH //0 BH 0//0 BH 0-0-0 Z.doc 0-0-0 Page of
REV DESCRIPTION DATE APPROVED flag note to ground all shielded wiring on drawings in Fig -,,,, &. Added drawing for KCS System with KG-0A & SN0 / SN00. Removed ARC 00, ARC 00, Century 000 & KAP0 drawings. 00A software version not supported. E V Reworded Required Equipment header and first sentence on page 0. Reworded last sentence in Optional Equipment paragraph on page. Added ARC 00 (Fig -), ARC 00 (Fig ), Century 000 (Fig -) and KAP 0/0/0 BH 0 (fig -) drawings E W Edited jumper on drawing KING KAP 0 w/ KI-A at 0/0/ BH GDC pin to pin and flag notes relative to change. Inserted Century II/III with NSD-0A / NSD-000 to C- Radio Coupler drawing. Renumbered pages. Edited various drawing notes. E X Remove page ( GDC STC permission statement) 0// BH renumber pages E Y Add Collins AP-0 drawing E-0 0/0/ BH Z Update for 00C software E0-0 0// BH 0-0-0 Z.doc 0-0-0 Page of
Table of Contents RECORD OF REVISIONS... INTRODUCTION:... DESCRIPTION:... PART NUMBERS:... REGULATORY COMPLIANCE:... Software... PMA... Environmental... REQUIRED EQUIPMENT... 0 OPTIONAL EQUIPMENT... SPECIFICATIONS:... Physical:... Electrical:... Serial Data Input:... ARINC Input: (-0 Only)... Roll Sum Steering Output:... Reference Inputs:... AP Offset Input:... Annunciator Output:... Flag Input:... Certification:... Reliability:... OPERATION:... Overview... Analog Output... Reference Inputs (Excitation)... ARINC Input... Mode Annunciator Control... Super Flag Input... INSTALLATION... Material Not Supplied... Special Tools... Mounting Considerations... Wiring Considerations... Pre Modification Planning... Equipment Interfaces... Installation Summary... Steering Output Scale Factor Determination... 0 Configuration Pins... Gain Settings Using Ref input J-... Gain Settings Using Ref input J-... Phase Selection... Position/Rate Selection... Baud Rate Selection... Receiver Setup... REMOVAL AND REPLACEMENT... Removal, GDC... 0-0-0 Z.doc 0-0-0 Page of
Replacement, GDC... Removal, Mode Annunciator... Replacement, Mode Annunciator... EQUIPMENT CHECKOUT... Ground Functional Test... Flight Functional Test... CONTINUED AIRWORTHINESS:... INSTRUCTIONS TO COMPLETE FOLLOW-ON INSTALLATION DATA FORM:... FOLLOW-ON INSTALLATION DATA FORM... CONNECTOR PIN OUT: (0-000-0)... 0 OUTLINE DRAWINGS... GDC Outline... Switch / Annunciator Outline... Isolation Coupler Outline... SLIDE LATCH ASSEMBLY... APPENDIX A RS AVIATION FORMAT... APPENDIX B ARINC INPUT... Label - Bank Angle Command... APPENDIX C RECEIVER INTERCONNECT... Figure RS Interconnect Diagram... Figure ARINC Interconnect Diagram... APPENDIX D - OPTIONAL LIGHTING CONTROLS... Figure Day / Night Switch Interconnect Diagram... Figure Relay Interconnect Diagram... APPENDIX E - TYPICAL INTERCONNECT... 0 Figure - TYPICAL INTERCONNECT... Figure - ARC 00A with G0A... Figure - ARC 00A (DC) with NSD-0... Figure - ARC 00/S0A with PN 0... Figure - ARC 00B/CA-0A/FD (0VAC) with G0A... Figure - ARC 00B/CA-0A/FD (0VAC) with G0A... Figure - ARC 00B/CA-0A/FD (DC) with NSD-0... Figure - ARC 00B/CA-0A/FD with IG-A / NSD-0 / NSD-000... Figure - CENTURY 000 with D... Figure 0 - CENTURY 000 with FDV... 0 Figure - CENTURY 000 with IG-A / NSD-0 / NSD-000... Figure - CENTURY 000 with KI-A... Figure - CENTURY II or III with D to C/M/P Radio Coupler... Figure - CENTURY II / III with 000C DG / D to C / D Console / Amp... Figure - CENTURY II / III with ARINC HSI to C / D Console/Amp... Figure - CENTURY II / III with IN-A HSI to C / D CONSOLE/AMP... Figure - CENTURY II / III with NSD-0A / NSD-000 to C- Radio Coupler... Figure - CENTURY II / III with NSD-0A / NSD-000 to C / D CONSOLE/AMP... Figure - CENTURY III with SN0 / SN00 to C- Radio Coupler... Figure 0 - CENTURY IV with ARINC HSI... 0 Figure - CENTURY IV with IG-A / NSD-0 / NSD-000... Figure - COLLINS AP0 with A-R... Figure - COLLINS AP0 with FDC/V... Figure - KING KAP 0 with 000C- DG... 0-0-0 Z.doc 0-0-0 Page of
Figure - KING KAP 0 with KI-A... Figure - KING KCS SYSTEM with KI- / A and KA- / KA-... Figure - KING KCS SYSTEM with KG-0A & SN0 / SN00 HSI... Figure - KING KFC 0 with EFIS 0... Figure - KING KFC 0 with KI-A... Figure 0 - KING KFC 0 with SN0 / SN00 & KG-0A... 0 Figure - KING KFC 00 / 00 Series with KI-A... Figure - KING KFC 00 with KA- & KPI-0A... Figure - KING KFC 00 with KI- HSI... Figure - KING KFC 00 / 00 Series with KPI-... Figure - KING KFC 00 Series with SN0 / SN00 & KG-0A... Figure - KING KFC 00 Series with SN0 / SN00 without DG... Figure - KING KFC with EFIS 0... Figure - S-TEC 0//0/ (DC) with NSD-0A / NSD-000... Figure - S-TEC 0//X/0/ (AC) with 0 HSI... Figure 0 - S-TEC 0//0 with KI-A... 0 Figure - S-TEC 0//0/ with ARINC HSI... Figure - S-TEC 0/0/ (AC) with U-00- DG... Figure - S-TEC 0/0/ (AC) with D DG... Figure - S-TEC (DC) with DDG... Figure - S-TEC / (AC) with HSI... Figure - S-TEC 0 with G0A HSI... 0-0-0 Z.doc 0-0-0 Page of
INTRODUCTION: This Installation Manual contains installation data, specifications and Instructions for Continued Airworthiness for the DAC International Model GDC Roll Steering Converter, Part Number 0-000-XX-00( ). Check the DAC International website www.dacint.com/gdc regularly for updates to this manual or for additional information. DESCRIPTION: The GDC Roll Steering Converter with software version 00A is designed to receive RS or RS serial data from a Navigation System to produce both an analog Roll Sum Steering (RSS) signal and ARINC labels bank angle command and ground speed. The GDC Roll Steering Converter with software version 00B (or later) is designed to receive RS or RS serial data or ARINC Label from a Navigation System to produce an analog Roll Sum Steering (RSS) signal. The GDC output signal connects to the heading error input of the aircraft s existing autopilot. The GDC mimics the heading error signal of the aircraft s installed HSI or DG. The GDC does not reduce or otherwise alter any existing safety features of the autopilot, such as bank limiting, rate limiting and protection from a hard over. The GDC provides lateral (roll) data only (no pitch data is supplied by the GDC). The pilot simply selects between heading mode and mode using the supplied switch / annunciator. In heading mode, the autopilot operates as always, tracking the heading bug of the HSI or DG. In mode, the GDC RSS signal drives the autopilot s heading channel. The GDC calculates the correct course intercept angle from the data supplied by the, smoothly guiding the aircraft onto the course. The GDC then holds the aircraft on the selected course. If the is programmed with Flight Plan data, the GDC will calculate the new intercept angle at each waypoint change, intercepting and holding the new course without pilot intervention. The GDC is designed to operate with both rate based and position based autopilots. ERROR ANNUN / SW ERROR ROLL STEERING HSI / CDI AUTOPILOT SERIAL / FLAG ARINC IN (-0 Only) GDC RSC 0-0-0 Z.doc 0-0-0 Page of
PART NUMBERS: The GDC Data Converter is available under the following part number: 0-000-0 GDC Roll Steering Converter, with RS and ARINC Auto-Baud Detect Input (Recommended for all new installations) Software part number, where ( ) contains the number zero for initial release, or any letter, A Z to denote a minor change. The following GDC version is no longer available and no longer supported. 0-000-0-00A GDC Roll Steering Converter, with RS Input and ARINC Low Speed Output REGULATORY COMPLIANCE: Software The Model GDC software was developed in accordance with RTCA/DO-B to criticality level C. PMA This manual contains FAA Approved installation instructions for installation of the DAC International model GDC unit under the GDC AML STC for use in those Part Class I, II, and III aircraft (as defined in AC.0-C) listed on the GDC AML. Installation of the GDC into US-registered CFR Part Class I, II or III aircraft not included in the AML, Part Class IV aircraft, any part,, or aircraft, or non-u.s. registered aircraft requires separate airworthiness approval. Environmental The Model GDC meets the DO-0D environmental categories listed later in this manual. The performance and environmental limitations under which the GDC was granted PMA are described in this manual. It is the responsibility of the facility installing this article whether on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the equipment limitations. The article may be installed only if performed under CFR Part or the applicable airworthiness requirements. 0-0-0 Z.doc 0-0-0 Page of
REQUIRED EQUIPMENT Each Roll Steering System requires the following items: Part Number Description Qty 0-000-0 GDC Roll Steering Converter, RS & ARINC Auto- Baud Detect Input 0-00-0 Connector Kit, GDC Data Converter 0-0-0 Annunciator Kit, GDC Data Converter V/V NOTE: The Annunciator / Switch, P00, comes pre-configured for V operation. For V operation, see the section titled INSTALLATION - Wiring Considerations. Complete installation kits are available under kit part numbers 0-00-0 and 0-0-0. Individual pieces are available under the part numbers shown. Contact DAC International sales to place orders. Part Number Description Qty 0-00-0 Connector Kit, GDC Data Converter M0/-F Connector, Receptacle, pin D-Sub M0/- Socket, Crimp Style, female P0 Slide Latch Kit, shell size P00 Backshell, -Pin D-Sub 0-0-0 Annunciator Kit, GDC Data Converter P00 Mode Annunciator / Switch with V lamps P00 Lamp, V 0-0-0 Z.doc 0-0-0 Page 0 of
OPTIONAL EQUIPMENT Certain installations require the use of an Isolation Coupler assembly. Isolation Coupler is used to transformer isolate the GDC reference input (excitation) and/or analog (heading error signal) output for installations where these signals are not referenced to airframe ground. Refer to the applicable installation drawings later in this manual for usage. This assembly is sold separately and requires a separate installation kit. Part Number Description 0-0-0 Isolation Coupler 0-00-0 Installation Kit, Isolation Coupler Complete installation kits are available separately under kit part number 0-00-0. Individual pieces are available under the part numbers shown. Contact DAC International sales to place orders. Part Number Description Qty 0-00-0 Installation Kit, Isolation Coupler M0/-F Connector, Receptacle, pin D-Sub M0/- Socket, Crimp Style, female P00 Slide Latch Kit P00 Backshell, -Pin D-Sub 0-0-0 Z.doc 0-0-0 Page of
SPECIFICATIONS: Physical: The GDC attaches to the airframe via four mounting holes. See the paragraph titled GDC Outline Drawing for further details. RSC LRU Height.... Width.... (Includes mounting flange) Depth.... Weight... 0. lb. The Isolation Coupler (optional) attaches to the airframe via four mounting holes. See the paragraph titled Isolation Coupler Outline Drawing for further details. Height.... in Width.... in (Includes mounting flange) Depth.... in Weight... 0. lb. Annunciator Height... 0. Width... 0. (Includes mounting flange) Depth.... Weight... 0.0 lb. Electrical: Input Voltage... / VDC (0Vdc Vdc operational) Input Current... 0. Amp maximum at VDC Annunciator lamp current... 0.0 Amp at VDC, 0.0 Amp at VDC Serial Data Input: Format... RS or RS serial data in RNAV 0, RNAV, King 0 or King format from a navigation system Baud Rate... Selectable (00, 00) ARINC Input: (-0 Only) Labels... Bank Angle Command, Label Baud Rate... Auto-Baud Detect 0-0-0 Z.doc 0-0-0 Page of
Roll Sum Steering Output: Description... Analog bank angle command with program pin selectable scale factors to match most autopilot input levels. Program pin selection for position based or rate based output. Program pin selectable phasing. Load... K Reference Inputs: General Description... AC or DC excitation used to excite the heading bug on the HSI or DG. The GDC uses the reference input to produce a steering signal with correct phase and amplitude characteristics. Two reference inputs are provided. Use only one, depending on the autopilot type. The unused input will be a no-connect. See typical interconnect diagrams later in this manual. AP Ref... Reference voltage input for use with gain settings found in Table. Maximum Input Level... volts peak (0Vrms) Load:... 0K AP Ref... Reference voltage input for use with gain settings found in Table. Maximum Input Level... volts peak (0.Vrms) Load:... 0K 0-0-0 Z.doc 0-0-0 Page of
AP Offset Input: Autopilot Offset... For autopilots that use a signal common that is not airframe ground. Many use Vdc (relative to airframe) as the heading bug signal common. In these cases, connect the autopilot signal common to the GDC offset input pin, P-. Maximum Input Level... volts peak (Vrms) Load:... 0K Annunciator Output: Coupled... Normally Open relay contacts configured as a SPST switch intended to control an external mode annunciator. The GDC closes the contacts when the steering output is valid. It cycles the contacts between open and closed at a Hz rate if steering data is invalid. Closed contacts connect pins P- and P-. Max current:... 0mA Flag Input: Description... Valid input to the GDC at J-, supplied from a receiver Super Flag output ( or V). Voltage:... Greater than V is valid, less than V is invalid. Load... 00K ohms Certification: PMA DO-B... Level C DO-0D... D/BADSXXXXXXABBBAVB/AE/XXX Reliability: MTBF... Greater than 0,000 hours. 0-0-0 Z.doc 0-0-0 Page of
OPERATION: Overview The GDC Roll Steering Converter receives ARINC, Label Bank Angle Command (BNR) (-0 model only), RS or RS serial data in RNAV 0, RNAV, King 0 or King format from a navigation system. It extracts Cross Track, Ground Speed and Track Angle Error information from the data stream to compute an appropriate bank angle command to return the aircraft to the Desired Track computed by the navigation system. NOTE: The Bendix/King KLN-B and KLN- Receivers are not compatible with the GDC Roll Steering Converter. See Appendix A, SIL GDC-0. Analog Output The GDC produces an analog Roll Sum Steering (RSS) signal that drives the heading channel of the autopilot. Phasing and amplitude of the RSS signal is based on the reference input supplied to the GDC from the autopilot and the gain and phase settings established by the program pins (refer to Tables, and ). The GDC will accept either an AC or a DC reference input as well as reference inputs that contain an offset from airframe ground. The internal circuitry implements a multiplying Digital-to-Analog converter that uses the external reference input to produce the desired signal output amplitude and phase relative to the reference input. Certain installations (Century II and III, for example) will not accept a heading error signal referenced to ground, so require the Isolation Coupler in order to transformer isolate the GDC output signal. Reference Inputs (Excitation) The GDC contains two reference inputs to accommodate the wide range of reference voltages available. Input Ref will accommodate excitation voltages up to a maximum input of volts peak (0Vrms). Input Ref will accommodate excitation voltages up to a maximum of volts peak (Vdc or 0.Vrms). The determination of which reference to use will depend on the gain needed to match the autopilot scale factor as well as the maximum expected reference voltage. Certain installations (Century II and III, for example) produce a reference voltage that is floating relative to airframe ground. These installations require the Isolation Coupler in order to transformer isolate the GDC reference input signal. ARINC Input The GDC, (-0 model with software 00B or later) receives an ARINC digital input containing label. Label (Octal) Description Bank Angle Command (BNR) Mode Annunciator Control The GDC contains a Normally Open relay contact configured as a SPST switch to control the external mode annunciator. This annunciator is further controlled by external switching and is active when the pilot selects mode in place of heading mode with the external switch. Refer to the typical interconnect diagram 0-0-0 Z.doc 0-0-0 Page of
later in this manual. If GDC output data is valid, the relay contacts are closed, allowing the mode annunciator to illuminate. If the data is invalid, the GDC will cause the mode annunciator to blink at a Hz rate and command the steering output to zero degrees of bank (wings level). The mode annunciator blinks if either the super flag input is invalid or the serial data from the is missing or not the correct format (see Appendix A). Super Flag Input The GDC reads the Super Flag ( or Vdc) from the receiver. If the flag is greater than Vdc, the flag shall be considered valid, if less than Vdc, the flag shall be considered as invalid. If the Super Flag indicates invalid, the GDC shall produce a steering signal of zero degrees, blink the annunciator relay and invalidate the ARINC label, bank command data, and label, ground speed data. 0-0-0 Z.doc 0-0-0 Page of
INSTALLATION This Installation Manual is FAA Approved and contains detailed installation instructions for installing the GDC into specific aircraft as listed in the AML-STC. There are required FARs that must be complied with and followed to insure an airworthy installation. The Pre Modification Planning section will guide you through these requirements. This section provides details for the installation of the GDC Roll Steering Converter, including configuration, wiring, mounting and checkout procedures. Follow the procedures and recommendations found in this section to assure a successful installation. Read this entire section before beginning the installation. Prior to installation, determine the required scale factor and phasing for use with the aircraft s autopilot. Consider the location of the mode selector / annunciator switch; it should be installed within the pilot s primary field of view and easily accessible by the pilot. Complete an electrical load analysis in accordance with AC.-B, Chapter prior to starting the aircraft modification to insure the aircraft has sufficient load capability. Complete an aircraft weight and balance prior to aircraft modification to insure the aircraft has sufficient weight and CG margin. Material Not Supplied The following items are required for the installation but not supplied: Wire: MIL-W-/ or equivalent Shielded Wire: MIL-C-00 or equivalent Mounting screws: MS0 -, each Circuit Breaker: Klixon -- or equivalent Tie straps or lacing cord Ring terminals (for grounding) Splices Special Tools Use the following crimp tool to ensure reliable crimp contact connections to connector J and Annunciator. Crimp tool M0/-0 Positioner M0/-0 (J crimp contacts) 0-0-0 Z.doc 0-0-0 Page of
Mounting Considerations The GDC Roll Steering Converter can mount in the avionics bay, shelf or other suitable structure. It can be mounted in any orientation. The optional Isolation Coupler can mount in the avionics bay, shelf or other suitable structure. It can be mounted in any orientation. Attach the GDC and Isolation Coupler to suitable structure using the following hardware. Screw, - X / Flat Washer, # Lock Washer, # Nut, - MS0- AN0-L MS- MS- AN or MS self-locking nut plates may be used in place of the nut and lock washer specified above. Mount the / mode annunciator / switch as near as practical to the autopilot mode controller. If there is insufficient space there, mount the mode annunciator within the pilot s primary field of view, near the HSI or CDI. Wiring Considerations Wiring should be done in accordance with AC.-B, Chapter. Refer to the typical interconnect diagram later in this manual for specifics. Use to AWG wire for all connections. Fabricate wiring harness; refer to the interconnect diagrams and pin description. Test all the wiring for continuity and for shorts. Insure aircraft power is on the correct pins of J; refer to Table. Install slide latch assembly onto J using instructions found later in this manual. The mode annunciator/switch, P00, comes pre-configured for V operation. For V operation, perform the following steps:. Pull firmly on the edges of the lens to disengage the lamp assembly from the body. The lamp assembly will hinge out and away from the body.. Remove and discard the four existing lamps, and replace with the four V lamps, P00, contained in the kit.. Push the lens firmly back into the body. 0-0-0 Z.doc 0-0-0 Page of
Pre Modification Planning Annunciator/Switch The / annunciator switch should be located near the HSI/ DG or alternately, near the existing autopilot mode annunciators. Power Requirements A suitable location will need to be determined for the RSS circuit breaker. It is recommended that power to the GDC be supplied from the same source and the autopilot, typically the avionics buss. Equipment Interfaces The GDC provides steering command through the Datum of the autopilot based on input. The must be capable of providing either ARINC label or RS data in Aviation Format described in section appendix A and appendix B-ARINC input of the manual. Autopilot The GDC is compatible with the autopilot models listed in the Limitations Section of the GDC STC. During installation, the GDC in configured to emulate the Heading Datum output of the existing HSI or DG. Refer to the wiring diagrams in Section appendix E of this manual. No modifications to the autopilot wiring are necessary. The GDC will use the same Heading Datum reference feeding the HSI or DG. As part of this modification, the HSI or DG Heading Datum error signal is rewired through the supplied / annunciator switch, enabling either the current Heading Datum error signal of the GDC steering signal to feed the autopilot heading datum input Installation Summary Mechanical Summary Panel layout is evaluated for the best placement of the / annunciator. Based on an evaluation of the DO-0 limitations found in this manual, a suitable location is found for the GDC computer. Weight and balance is performed. Electrical Summary Electrical Load Analysis is performed. A dedicated circuit breaker in location is determined. Power and ground lines are installed. An applicable wiring diagram is selected from those available in this manual. Reference and heading datum interconnects are installed per the selected diagram. Ground Checkout Summary Wiring is verified. Basic operation is verified with the ground test. Functional Flight Test Summary Autopilot Datum performance is evaluated. GDC RSS performance is evaluated. 0-0-0 Z.doc 0-0-0 Page of
NOTE: The following setup procedures are for diagnosing interfacing problems. Steering Output Scale Factor Determination The GDC is designed to mimic the heading error signal produced by the existing HSI or DG, so it can operate with the wide variety of autopilots in current use. These various autopilots employ a wide range of reference voltages and scale factors to interface with the array of HSI and DG control heads. Reference voltage, or excitation, is the autopilot signal used to excite the Heading Select bug in the HSI or CDI. As used in this manual, scale factor refers to the autopilot s response to the heading error input signal, expressed in volts per degree of bank. Examples are 00mv/deg and 0mv/deg. Examples of excitation voltage are Vac and Vdc. The GDC first computes the bank angle using data from the. It then uses the reference voltage along with the scale factor setting (gain setting) to produce a signal that feeds into the autopilot s heading error input to produce the desired bank angle. The GDC has ten (0) choices for scale factor, selected with a combination of program pins ( each) and reference inputs ( each). Tables and describe the program pin combinations for the various scale factors. To determine the appropriate setting for a given autopilot, first determine the autopilot excitation amplitude in volts (AC or DC). Next, determine the autopilot scale factor from the autopilot maintenance data. The scale factor needs to be expressed as volts/degree of bank. Divide the scale factor by the excitation (scale factor / excitation voltage). Then look in Tables and for the nearest Scaling value to the one just computed. If the gain is set too high, the commanded course intercept will be overly aggressive. For 0-degree course changes, too much gain will often cause the aircraft to turn inside the new course then S-turn back to capture the track. If the gain is set too low, the commanded course intercept will be sluggish. For a 0-degree course change, too little gain will often cause the aircraft to overshoot the desired course then S-turn back to capture the track. Some autopilots limit the maximum bank angle to less than the 0 degrees, degrees for example. In these cases, the aircraft will exhibit the symptoms of too little gain because the aircraft cannot turn sharp enough to capture the track without overshooting. Examine the attitude indicator during a 0-degree course change to verify that the aircraft banks to 0 degrees, or in the case of rate based autopilots, to a standard rate turn. 0-0-0 Z.doc 0-0-0 Page 0 of
Configuration Pins The GDC produces one of five () different RSS output levels for each reference input. This scaling selection is accomplished with program pins J-0, J- (-0 model only) and J-. Tables and define the scale factors available for each of the reference inputs, Ref and Ref. Gain Settings Using Ref input J- (Excitation: Maximum input of volts peak, (0 Vrms) Scaling J-0 J- () J- 0.00 Open Ground Open () 0.0 Open Open Open 0.00 Open Open Ground 0.00 Ground Open Open 0.00 Ground Open Ground () Applicable to software -00B or later. Table RSS Output Scaling Selection for Ref input Gain Settings Using Ref input J- (Excitation: Maximum input of volts peak, ( Vdc or 0. Vrms) Scaling J-0 J- () J- 0.0 Open Ground Open () 0.0 Open Open Open 0.00 Open Open Ground 0.0 Ground Open Open 0.00 Ground Open Ground () Applicable to software -00B or later. Table RSS Output Scaling Selection for Ref input 0-0-0 Z.doc 0-0-0 Page of
Phase Selection The GDC will accommodate steering signals that are in phase with the reference or out of phase with the reference. For DC heading error signals, in-phase means a positive error signal produces a right turn, a negative error signal produces a left turn. Determine the correct phasing from the autopilot maintenance data then wire P- accordingly. If the phasing is incorrectly wired, the autopilot will turn the opposite direction when coupled to the GDC Roll Steering Converter. Position/Rate Selection Phase P- IN Phase with Reference Open OUT of Phase with Reference Ground Table Phase Selection The GDC is designed to operate with both position based and rate based autopilots. Configuration is set by program pin P-. Scaling J- Position Based Open Rate Based Ground Table Position / Rate Selection Position based autopilots require attitude information from the attitude indicator or vertical gyro. Rate based autopilots require turn rate information from the turn coordinator rate gyro. Determine the autopilot type, if it is rate based then connect J- to program pin common, J-. 0-0-0 Z.doc 0-0-0 Page of
Baud Rate Selection Table removed in revision U. The GDC Roll Steering Converter, P/N 0-000-0, with software -00B or later, will accept two () baud rates for data configured using program pin P-. Baud Rate P- 00 Open 00 Ground Table Serial Baud Rate Selection Note: Use Program Pin Common, J-, as ground for all program pin connections. Receiver Setup Refer to the manufacturer's instructions for the interfaced to the GDC RSC. Configure the to output the RS Aviation Format data described in Appendix A. 0-0-0 Z.doc 0-0-0 Page of
REMOVAL AND REPLACEMENT Removal, GDC. Open the circuit breaker powering the GDC.. Remove the connector by disengaging the slide latch then pulling the connector free.. Remove four () screws securing the unit to the airframe. Replacement, GDC. Open the circuit breaker powering the GDC.. Attach the unit to the airframe with four () screws.. Seat the connector then engage the slide latch to secure.. Close circuit breaker.. Perform ground functional test found under Equipment Checkout in this manual. Removal, Mode Annunciator. Open the circuit breaker powering the GDC.. Pull firmly on the edges of the lens to disengage the lamp assembly from the body. The lamp assembly will hinge out and away from the body.. Release the two () pawls by unscrewing the flat-head screws located inside the body.. Unplug the lamp module from the sleeve. Replacement, Mode Annunciator. Open the circuit breaker powering the GDC.. Plug the lamp module into the sleeve.. Secure by engaging the two () pawls to the sleeve.. Plug the lamp module into the body - it will snap into place.. Close the circuit breaker.. Perform ground functional test found under Equipment Checkout in this manual. 0-0-0 Z.doc 0-0-0 Page of
EQUIPMENT CHECKOUT The GDC provides conversion of RS serial data or ARINC digital data (0-000-0 with software 00B or later) from a receiver into a steering signal connected to the autopilot heading channel through switching controlled by the / mode selector switch. There are no other operator controls associated with the GDC unit. The receiver and the Autopilot must both be operational in order to perform this functional checkout. Ground Functional Test. Insure that all control surfaces are clear and that the control wheel is centered in roll.. Apply power to the Receiver and Autopilot.. Set the / Mode selector to.. On the HSI, center the heading bug.. Engage the autopilot in Heading Mode.. Operate the heading bug; observe that the control wheel turns left and right in response to the heading bug operation.. Center the control wheel using the heading bug.. Create and activate a flight plan in the unit according to existing maintenance and / or flight manual instructions.. Place the / Mode selector in the position. With RS interface, observe illuminates and is not blinking. With ARINC interface, Label may not validate with less than 0 knots ground speed. If receiver has test page mode, set receiver to test page to test for steady indication. Refer to applicable receiver documentation for state of Label valids. If receiver does not provide valid ground speed for testing then it will be necessary to taxi aircraft in excess of 0 knots ground speed or fly to test for valid. 0. Remove power from the receiver.. Observe that the mode annunciator begins to blink within seconds.. Verify that the control wheel centers once the mode annunciator blinks.. Disengage the autopilot.. Ground test complete. Secure aircraft power. Flight Functional Test. Set the / Mode selector to.. On the HSI, center the heading bug.. Engage the autopilot in Heading Mode.. Operate the heading bug; observe that the control wheel turns left and right in response to the heading bug operation.. Center the heading bug. 0-0-0 Z.doc 0-0-0 Page of
. Create and activate a flight plan in the unit according to existing maintenance and / or flight manual instructions. Manually fly the aircraft until the cross track error is between and miles.. Place the / Mode selector in the position. Observe that illuminates and is not blinking.. Observe that the aircraft turns to intercept the course selected in Step. Note: The GDC limits the intercept angle to º maximum. (Intercept angle = difference between Desired Track and Track.). Observe that the aircraft captures the course without overshoot or undershoot. 0. Operate the heading bug; observe that the heading bug has no effect.. Select on the / Mode selector.. Observe that the aircraft follows the heading bug.. Flight test complete. 0-0-0 Z.doc 0-0-0 Page of
CONTINUED AIRWORTHINESS: This section provides data intended to assist the installer with establishing Instructions for Continued Airworthiness as required by FARs.,.,. and.. INSTRUCTIONS TO COMPLETE FOLLOW-ON INSTALLATION DATA FORM: For follow-on installations, complete the data sheet found on the following page. Also include a wiring diagram specific to the installation. On the data sheet, complete the aircraft make and model, registration number and serial number sections. Then describe the location of the GDC converter in sufficient detail, using station location numbers or other common reference points. For example, GDC located under the instrument panel, right outboard side. Use of sketches is recommended. Likewise, describe the location of the annunciator / switch. Describe or sketch the wire bundle routing. Produce a wiring diagram specific to the aircraft installation. Use of wiring diagrams extracted from the installation manual, 0-0-0, or sketches are also acceptable. Also a copy can be obtained from the ICA. Include a copy of the Instructions for Continued Airworthiness (ICA) (0-0-0) along with the data sheet and wiring diagram with the aircraft records. A copy of the Instructions for Continued Airworthiness (0-0-0) may be obtained from the DAC International web site at http://www.dacint.com/products or by contacting DAC International at -00--. 0-0-0 Z.doc 0-0-0 Page of
FOLLOW-ON INSTALLATION DATA FORM AIRCRAFT MAKE AND MODEL: AIRCRAFT TAIL NUMBER: AIRCRAFT SERIAL NUMBER: LOCATION DESCRIPTION of GDC ROLL STEERING CONVERTER: LOCATION DESCRIPTION of MODE/ANNUNCIATOR switch: WIRE ROUTING: 0-0-0 Z.doc 0-0-0 Page of
The GDC meets the environmental test categories detailed below in accordance with RTCA/DO-0D, Environmental Conditions and Test Procedures for Airborne Equipment. NOMENCLATURE: Model GDC Roll Steering Converter PART NO: 0-000-XX-XXXX MANUFACTURER: DAC International ADDRESS: 0 McNeil Drive, Austin, TX Section Category Remarks.0 Temperature and Altitude D 0,000 Ft Temperature controlled.0 Temperature Variation B Partially controlled temperature.0 Humidity A Standard Humidity.0 Operational Shock and Crash Safety D Fixed wing.0 Vibration S Curves L, M and C. Fixed Wing Turbojet, Turbofan, Turboprop and reciprocating Instrument Panel or Fuselage.0 Explosion Proofness X Not Tested 0.0 Waterproofness X Not Tested.0 Fluids Susceptibility X Not Tested.0 Sand and Dust X Not Tested.0 Fungus Resistance X Not Tested.0 Salt Spray X Not Tested.0 Magnetic Effect A 0. meter to.0 meter.0 Power Input B Alternator / Rectifiers.0 Voltage Spike B volts.0 AF Conducted Susceptibility Power B Inputs.0 Induced Signal Susceptibility A 0.0 Radio Frequency Susceptibility (Radiated and Conducted) V 0 volts/meter.0 Emission of Radio Frequency Energy B.0 Lightning Induced Transient Susceptibility AE.0 Lightning Direct Effects X Not Tested.0 Icing X Not Tested.0 ESD X Not Tested Alternator / Rectifiers 0-0-0 Z.doc 0-0-0 Page of
CONNECTOR PIN OUT: (0-000-0) Table removed in revision U. The GDC Roll Steering Converter, P/N 0-000-0, with software -00B or later, contains a single -pin male connector, J, per MIL-C-0. The mating connector, P, is described previously under the section Equipment Supplied. Pin Signal Function A+ Vdc Primary Power Serial Out RS Output Serial In RS Input Reserved (VPP) AP-OUT Autopilot Output AP-REF Autopilot Reference, 0.Vac max () RX-A ARINC Receive A RX-B ARINC Receive B BAUDSEL Serial Baud Rate Select 0 GAINSEL Autopilot Gain Select Prog Pin Common Program Pin Common Lamp A Mode Annun Relay Armature Phase Select Phase select program pin Power Common Vdc Return AP-COM Autopilot Common (ground) Serial Common RS Common Reserved (/PGM Enable) AP-REF Autopilot Reference, 0Vac max () AP-OFFSET Autopilot Offset Input (A/P Common) +Vdc max 0 Shield ARINC Shield Common GAINSEL Autopilot Gain Select () GAINSEL0 Autopilot Gain Select 0 TYPESEL0 Rate Based Select Lamp B Mode Annun Relay N.O. Contact Super Flag In / Vdc valid flag from Table J Pin Description NOTES: Do not use pins labeled Reserved. These are for factory test and In-Circuit-Programming () Connect only one reference. Refer to Reference Inputs section. () Does not apply to software versions prior to 00B. 0-0-0 Z.doc 0-0-0 Page 0 of
OUTLINE DRAWINGS GDC Outline Note: Dimensions are in inches. 0-0-0 Z.doc 0-0-0 Page of
Switch / Annunciator Outline 0 PIN OUT (REAR VIEW) PANEL CUTOUT Outline for part number P00 Note: Dimensions are in inches. 0-0-0 Z.doc 0-0-0 Page of
Isolation Coupler Outline 0-0-0 Z.doc 0-0-0 Page of
SLIDE LATCH ASSEMBLY Assemble the slide latch mechanism, part number P0 or P00, onto the mating connector as pictured using the hardware supplied with the slide latch. NUT LOCK WASHER FLAT WASHER CONNECTOR SLIDE LATCH SCREW 0-0-0 Z.doc 0-0-0 Page of
APPENDIX A RS AVIATION FORMAT The GDC accepts data in the RS Aviation Format produced by most panel mount receivers. Various manufacturers refer to this data as RNAV, KING or MAPCOM. The following table contains the minimum data set required by the GDC. The GDC is designed to disregard additional data records transmitted from the. NOTE: The Bendix/King KLN-A and KLN- Receiver update rate of track is too slow to maintain aircraft on course. If connected to a KLN-A or KLN-, expect a -degree track angle error left and right of course over a minute period. Receivers that supply the following minimum data set and any of the previously mentioned baud rates should be compatible with the GDC. Insure the GDC is configured for the correct baud rate (refer to "Serial Baud Rate Selection" located earlier in this manual). Aviation Data Format Description <STX> ASCII Start of Transmission character other data C<cr> track; in degrees magnetic (ex: º) D<cr> ground speed; in knots (ex: kt) GR000<cr> crosstrack; L (left) or R (right) in hundredths of nautical miles (ex: Right 0.nm) I<cr> desired track; in tenths of degrees (ex:.º) other data <ETX> ASCII End of Transmission character. Each data field ends in a <cr> or <cr> <lf>. <cr> - ASCII carriage return character (0D hex). <lf> - ASCII line feed character (0A hex) 0-0-0 Z.doc 0-0-0 Page of
The GDC Roll Steering Converter, P/N 0-000-0, with software -00B or later, will accept 00 or 00 baud. Software 00B (or later) accepts the following data in RS Aviation Format. Receivers that supply the following minimum data set (excluding Horizontal Command Signal) and any of the previously mentioned baud rates should be compatible with the GDC. Ensure the GDC is configured for the correct baud rate (refer to "Serial Baud Rate Selection" located earlier in this manual). Aviation Data Format Description <STX> ASCII Start of Transmission character other data C<cr> track; in degrees magnetic (ex: º) D<cr> ground speed; in knots (ex: kt) GR000<cr> crosstrack; L (left) or R (right) in hundredths of nautical miles (ex: Right 0.nm) I<cr> desired track; in tenths of degrees (ex:.º) hr0<cr> Horizontal Command Signal; L (left) or R (right) in tenths of degrees (ex: Right.0 degrees) other data <ETX> ASCII End of Transmission character. Each data field ends in a <cr> or <cr> <lf>. <cr> - ASCII carriage return character (0D hex). <lf> - ASCII line feed character (0A hex) 0-0-0 Z.doc 0-0-0 Page of
APPENDIX B ARINC INPUT The GDC Roll Steering Converter, P/N 0-000-0, with software 00B (or later) accepts input of ARINC Label Bank Angle Command in the following format: Label - Bank Angle Command Label shall be formatted as follows: 0 0 0 0 0 0 0 0 0 0 P SSM S Roll Angle (two s compliment if negative) PAD SDI Label P = odd parity SSM = sign status matrix 00 = fail/warning = normal S = sign bit, 0=positive roll angle SDI = source/destination identifier (always zero) Data Range: ±0 Resolution: 0.0 0 0 0-0-0 Z.doc 0-0-0 Page of
APPENDIX C RECEIVER INTERCONNECT Connect the GDC to a single source only. The following diagrams are the recommended interconnections for each source. Refer to Figure for RS interconnect. Refer to Figure for ARINC interconnect. NOTE: For Procedure Turns and Holding Patterns capabilities provided by some Receivers interface to the ARINC output of the receiver shown in Figure. RECEIVER GDC RS OUT RS COM SUPER FLAG Serial In Serial Com Super Flag Figure RS Interconnect Diagram RECEIVER GDC TX-A RX-A TX-B RX-B /V BUS SHIELD 0 SHIELD Super Flag Figure ARINC Interconnect Diagram 0-0-0 Z.doc 0-0-0 Page of
APPENDIX D - OPTIONAL LIGHTING CONTROLS LIGHTING BUS A+ A+ SWITCH/ANN P00 Figure Day / Night Switch Interconnect Diagram RELAY M0/-0P SWITCH/ANN P00 +V AVIONICS PWR DIMMER N00 Figure Relay Interconnect Diagram 0-0-0 Z.doc 0-0-0 Page of
APPENDIX E - TYPICAL INTERCONNECT All wiring, wire gauge and wire type shall be according to the INSTALLATION section of this manual. Mounting shall use the hardware called out in this manual or AN / MS equivalent fasteners. NOTE: THESE S ARE FOR REFERENCE ONLY. For configurations not illustrated by drawing refer to the Installation section earlier in this manual for configuration, wiring, mounting and checkout procedures. Many autopilot units provide both an AC and a DC excitation signal. Verify the HSI or DG is connected to the autopilot signal and reference as shown in that diagram. Refer to the HSI or DG manufacturer s data and the autopilot manufacturer s data for additional information. Visit our website: www.dacint.com/gdc for additional information. 0-0-0 Z.doc 0-0-0 Page 0 of
GDC Roll Steering Converter GDC J A A+ POWER COMMON V OR VDC BUS SEE TABLES & SEE TABLES AND -0 ONLY ARINC RX-A ARINC RX-B COMMON 0 ARINC TX-A ARINC TX-B SHIELD SEE TABLE SEE TABLE REF - USE FOR EXCITATION VOLTAGES GREATER THAN VOLTS PEAK SEE TABLES AND INTERFACE SELECT RS or ARINC ONLY RS RX IN SERIAL COMMON SUPER FLAG IN ARINC TX-A <=RS RS TX OUT SHIELD SUPER FLAG OUT REF - USE FOR EXCITATION VOLTAGES LESS THAN VOLTS PEAK SEE TABLES AND FOR USE WITH AUTOPILOTS THAT USE A SIGNAL REFERENCE THAT IS A VOLTAGE ABOVE AIRFRAME COMMON, TYPICALLY VDC ISOLATION COUPLER IS USED TO TRANSFORMER ISOLATE THE GDC REFERENCE AND / OR OUTPUT FOR INSTALLATIONS WHERE THESE SIGNALS ARE NOT REFERENCED TO AIRFRAME GROUND. -0 ONLY ARINC TX-B COMMON 0 IATOR P00 (V OR V) PROGRAM PINS LAMP B LAMP A BAUD SELECT 0 BAUD SELECT GAIN SELECT 0 GAIN SELECT 0 INTERFACE GAIN SELECT -0 ONLY TYPE SELECT PHASE SELECT -0 ONLY Select RS or ARINC 0 LIGHTING VOLTAGE ERROR FROM HSI / CDI : : : : ISOLATION COUPLER 0-0-0 0 PROGRAM PIN COMMON AUTOPILOT RSS OUTPUT ERROR IN RSS COMMON GROUND AUTOPILOT INTERFACE REF EXCITATION REF EXCITATION AP OFFSET SIGNAL REFERENCE EXCITATION ( Vpk to Vpk) EXCITATION (LESS THAN Vpk) Figure - TYPICAL INTERCONNECT 0-0-0 Z.doc 0-0-0 Page of
GDC Roll Steering Converter G0A J P00 RSS CONVERTER ISOLATION COUPLER GDC 0-0-0 ARC-00A CA-A (0-xxx) AC HEADING DATUM J EXC D 0. VAC Pk-Pk 00HZ EXC B 00HZ RTN (A/C GRND) E SIG COM 0 AC IN SIGNAL A AP-OUT AP-COM ISOLATION COUPLER 0-0-0 AP-REF LAMP A LAMP B PROG PIN COMMON 0 GAINSEL TYPE SELECT 0 LIGHTING BUS GAINSEL0 PHASE SELECT AP-OFFSET BAUDSEL TYPE SELECT RSC P00 A -- OR VDC 0 0 SERIAL IN SERIAL COMMON SUPER FLAG IN RX-A RX-B SHIELD FOR INPUT SEE APPENDIX C - RECEIVER INTERCONNECT ARINC INPUT AVAILABLE ON PINS & ON PN 0-000-0 WITH SOFTWARE -00B OR LATER ARINC OUTPUT AVAILABLE ON PINS & ON PN0-000-0 WITH SOFTWARE -00A ENSURE ROLL CENTERING KNOB IS CENTERED CONNECT PARALLEL TO EXISTING WIRING DASHED LINES REPRESENT EXISTING WIRING GROUND BOTH ENDS OF ALL SHIELDING IF AIRCRAFT TURNS AWAY FROM TRACK LINE, REMOVE PHASE JUMPER AND RETEST Figure - ARC 00A with G0A 0-0-0 Z.doc 0-0-0 Page of
GDC Roll Steering Converter NSD-0A NSD-000 IG- A/C P00 RSS CONVERTER GDC ARC-00A CA-A DC HEADING DATUM J/P EXC EXC 0 +0VDC REG -0VDC REG 0 0 DC IN SIGNAL AP-OUT AP-COM BAUDSEL P00 LIGHTING BUS 0 AP-REF LAMP A LAMP B PROG PIN COMMON TYPE SELECT AP-OFFSET GAINSEL GAINSEL0 0 GAINSEL PHASE SELECT RSC A -- OR VDC 0 SERIAL IN SERIAL COMMON SUPER FLAG IN RX-A RX-B SHIELD FOR INPUT SEE APPENDIX C - RECEIVER INTERCONNECT ARINC INPUT AVAILABLE ON PINS & ON PN 0-000-0 WITH SOFTWARE -00B OR LATER ARINC OUTPUT AVAILABLE ON PINS & ON PN 0-000-0 WITH SOFTWARE -00A ENSURE ROLL CENTERING KNOB IS CENTERED CONNECT PARALLEL TO EXISTING WIRING DASHED LINES REPRESENT EXISTING WIRING Figure - ARC 00A (DC) with NSD-0 0-0-0 Z.doc 0-0-0 Page of
GDC Roll Steering Converter COLLINS PN 0 SWITCH / ANNUN P00 RSS CONVERTER GDC ISOLATION COUPLER 0-0-0 J/P ARC 00 S0A J/P AC REF HI H- D E 0 VAC 00HZ AC REF LO C- E F 0 VAC 00 HZ RETURN ERR HI X- A C COM ERR LO Y- B 0 AP Out Ref Lamp A 0 E HEADING ERROR ISOLATION COUPLER 0-0-0 Lamp B AP Com LIGHTING BUS SWITCH / ANNUN P00 Prog Com Gain Sel 0 Phase Sel RSC OR VDC A -- 0 Serial In 0 FOR INPUT SEE APPENDIX C - RECEIVER INTERCONNECT Serial Com ARINC INPUT AVAILABLE ON PINS & ON PN 0-000-0 WITH SOFTWARE -00B OR LATER Super Flag ARINC OUTPUT AVAILABLE ON PINS & ON PN 0-000-0 WITH SOFTWARE -00A RX-A CONNECT PARALLEL TO EXISTING WIRING RX-B DASHED LINES REPRESENT EXISTING WIRING 0 SHIELD GROUND BOTH ENDS OF ALL SHIELDING IF AIRCRAFT TURNS AWAY FROM TRACK LINE, REMOVE PHASE JUMPER AND RETEST Figure - ARC 00/S0A with PN 0 0-0-0 Z.doc 0-0-0 Page of
GDC Roll Steering Converter G0A P00 RSS CONVERTER GDC ARC-00A CA-0A 0VAC HEADING DATUM P EXC D E 0VAC 00HZ EXC SIGNAL B A 0 F K 00HZ RTN AC IN P00 AP-OUT AP-COM AP-REF LAMP A LAMP B 0 0 PROG PIN COMMON GAINSEL GAINSEL GAINSEL0 LIGHTING BUS PHASE SELECT AP-OFFSET BAUDSEL TYPE SELECT RSC A -- OR VDC SERIAL IN FOR INPUT SEE APPENDIX C - RECEIVER INTERCONNECT SERIAL COMMON ARINC INPUT AVAILABLE ON PINS & ON PN 0-000-0 WITH SOFTWARE -00B OR LATER SUPER FLAG IN RX-A RX-B ARINC OUTPUT AVAILABLE ON PINS & ON PN0-000-0 WITH SOFTWARE -00A ENSURE ROLL CENTERING KNOB IS CENTERED 0 SHIELD DASHED LINES BETWEEN HSI AND AUTOPILOT REPRESENT EXISTING WIRING - DO NOT REMOVE Figure - ARC 00A/CA-0A/FD (0VAC) with G0A 0-0-0 Z.doc 0-0-0 Page of
GDC Roll Steering Converter G0A P00 RSS CONVERTER GDC SPERRY/ARC-00B CA-0A/FD 0VAC HEADING DATUM J/P J/P EXC D 0VAC 00HZ EXC B 00HZ RTN 0 0 AC IN SIGNAL A AP-OUT AP-COM CHASSIS GND P00 LIGHTING BUS LAMP B PROG PIN COMMON 0 GAINSEL GAINSEL AP-REF LAMP A GAINSEL0 PHASE SELECT 0 AP-OFFSET BAUDSEL TYPE SELECT RSC A -- OR VDC SERIAL IN SERIAL COMMON SUPER FLAG IN RX-A RX-B 0 SHIELD FOR INPUT SEE APPENDIX C - RECEIVER INTERCONNECT ARINC INPUT AVAILABLE ON PINS & ON PN 0-000-0 WITH SOFTWARE -00B OR LATER ARINC OUTPUT AVAILABLE ON PINS & ON PN0-000-0 WITH SOFTWARE -00A ENSURE ROLL CENTERING KNOB IS CENTERED CONNECT PARALLEL TO EXISTING WIRING DASHED LINES REPRESENT EXISTING WIRING IF AIRCRAFT TURNS AWAY FROM TRACK LINE, REMOVE PHASE JUMPER AND RETEST Figure - ARC 00B/CA-0A/FD (0VAC) with G0A 0-0-0 Z.doc 0-0-0 Page of
GDC Roll Steering Converter NSD-0A NSD-000 IG- A/C P00 RSS CONVERTER GDC SPERRY/ARC-00B CA-0A/FD DC HEADING DATUM J/P EXC EXC 0 0-0VDC REG +0VDC REG 0 DC IN SIGNAL AP-OUT AP-COM SIGNAL GND CHASSIS GND P00 AP-REF LIGHTING BUS LAMP A LAMP B PROG PIN COMMON 0 GAINSEL GAINSEL0 GAINSEL TYPE SELECT AP-OFFSET 0 BAUDSEL PHASE SELECT RSC A -- OR VDC SERIAL IN SERIAL COMMON SUPER FLAG IN RX-A RX-B 0 SHIELD FOR INPUT SEE APPENDIX C - RECEIVER INTERCONNECT ARINC INPUT AVAILABLE ON PINS & ON PN 0-000-0 WITH SOFTWARE -00B OR LATER ARINC OUTPUT AVAILABLE ON PINS & ON PN 0-000-0 WITH SOFTWARE -00A ENSURE ROLL CENTERING KNOB IS CENTERED CONNECT PARALLEL TO EXISTING WIRING DASHED LINES REPRESENT EXISTING WIRING Figure - ARC 00B/CA-0A/FD (DC) with NSD-0 0-0-0 Z.doc 0-0-0 Page of