Cessna 172N 1979 Pilot Operating Handbook
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Cessna 172N 1979 Pilot Operating Handbook

Cessna 172N 1979 Pilot Operating Handbook

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  • Page 66 SEE PDF Pages 161-165 for performance information in reference to Penn-Yann / Lycoming O-360 180HP upgraded.
  • Page 161 N5089G 17273538...
  • Page 166 System 40/50 Autopilots Pilot’s Operating Handbook MODES L– –R...
  • Page 167 System 40/50 POH * Asterisk indicates pages changed, added, or deleted by List of Effective Pages revision. Retain this record in front of handbook. Upon receipt of a Record of Revisions revision, insert changes and complete table below. Edition Number Publication Date Insertion Date/Initials Edition...
  • Page 168 System 40/50 POH Page Intentionally Blank 2nd Ed: October 25, 2002...

  • Page 169: Table Of Contents

    System 40/50 POH Table of Contents Section Page Introduction......................1-3 Notice.......................1-3 Block Diagrams....................2-3 Theory of Operation...................3-3 System 40 Modes of Operation............3-3 System 50 Modes of Operation............3-6 Procedures......................4-3 System 40 Function Pre-Flight Procedures........4-3 System 40 In-Flight Procedures............4-4 VOR Tracking and VOR Approach............4-4 Localizer Approach................4-4 GPS Tracking and GPS Approach............4-4 Procedure Turn Localizer Approach and Tracking with Standard DG..4-5...
  • Page 170 System 40/50 POH Page Intentionally Blank 2nd Ed: October 25, 2002...

  • Page 171: Introduction

    SYSTEM 40/50 POH SECTION 1 INTRODUCTION 2nd Ed: October 25, 2002...
  • Page 172 SYSTEM 40/50 POH Page Intentionally Blank 2nd Ed: October 25, 2002...

  • Page 173: Notice

    SYSTEM 40/50 POH Introduction The primary purpose of the System 40/50 Pilot Operating Handbook (POH) is to provide pilots with step-by-step functional Preflight and In-Flight Operating Procedures for the installed system. Notice This manual may be used in conjunction with FAA approved autopilot Airplane Flight Manual Supplement (AFMS), Pilots Operating Handbook Supplement (POHS), or Supplemental Flight Manual (SFM).
  • Page 174 SYSTEM 40/50 POH Page Intentionally Blank 2nd Ed: October 25, 2002...
  • Page 175 System 40/50 POH SECTION 2 BLOCK DIAGRAM 2nd Ed: October 25, 2002...
  • Page 176 System 40/50 POH Page Intentionally Blank 2nd Ed: October 25, 2002...

  • Page 177: Block Diagrams

    System 40/50 POH Block Diagrams MOD ES L– –R A U TO P ILO T M A STE R SW ITC H TU R N C O OR D IN ATO R 2 M IN T U R N R O L L S E RV O C O O R D IN ATO R PUSH D IR E C TIO N A L G Y R O...
  • Page 178 System 40/50 POH Page Intentionally Blank 2nd Ed: October 25, 2002...
  • Page 179 System 40/50 POH AUTO PILO T M ASTER SW ITCH ABSOLUTE PRESSURE ROLL SE RVO TR ANSDUCER T U RN COO RD INAT O R 2 M IN TURN PITCH S ERV O COOR DINATO R PUSH VO R/LO C/G PS DIRECTIONAL GYRO (S HOW N FO R RE FER ENCE) (O PTIO NAL)
  • Page 180 System 40/50 POH Page Intentionally Blank 2nd Ed: October 25, 2002...

  • Page 181: Theory Of Operation

    SYSTEM 40/50 POH SECTION 3 THEORY OF OPERATION 2nd Ed: October 25, 2002...
  • Page 182 SYSTEM 40/50 POH Page Intentionally Blank 2nd Ed: October, 25 2002...

  • Page 183: System 40 Modes Of Operation

    SYSTEM 40/50 POH 3.0 Theory of Operation 3.1 System 40 Modes of Operation MODES NOTE: The Aircraft (AC) instrument light rheostat controls the annunciator and indicator brightness. The System 40 provides the aircraft with Roll Axis control only. The Turn Coordinator contains the Rate Gyro, Autopilot pick-off, Rate Gyro RPM detector, and an instrument power monitor that will flag if low system voltage occurs.
  • Page 184 SYSTEM 40/50 POH MODES 10. ON/OFF Mode Switch engages the roll system in the Stabilizer (STB) Mode. This allows use of the Turn Knob to command up to a standard rate turn. (90%). MODES 11. Navigation Mode Switch (NAV) will engage the VOR/GPS/LORAN Tracking Mode.
  • Page 185 SYSTEM 40/50 POH MODES 12. Approach Mode Switch (APR) engages the VOR/GPS/LORAN or Localizer Tracking Mode. This provides a higher level of system gain for more active tracking of VOR, GPS or Localizer front course signals. MODES 13. Reverse Approach Mode Switch (REV) will engage the Reverse Tracking Mode for use when tracking a localizer back course.

  • Page 186: System 50 Modes Of Operation

    SYSTEM 40/50 POH 14. HDG/STB Turn Knob/Switch allows left or right proportional turn commands to the roll servo in the STB Mode only. It activates the turn command for roll axis maneuvers up to 90% of standard turn rate. MODES 15.
  • Page 187 SYSTEM 40/50 POH The System 50 incorporates an accelerometer and absolute pressure transducer as pitch sensors. When the Altitude Hold Mode is engaged, an elevator trim sensor in the pitch servo will detect the elevator trim condition. Green Ready Light (RDY) illuminates when autopilot is ready for engagement.
  • Page 188 SYSTEM 40/50 POH Page Intentionally Blank 2nd Ed: October, 25 2002...

  • Page 189: Procedures

    System 40/50 POH SECTION 4 PROCEDURES 2nd Ed: October 25, 2002...
  • Page 190 System 40/50 POH Page Intentionally Blank 2nd Ed: October 25, 2002...

  • Page 191: System 40 Function Pre-Flight Procedures

    System 40/50 POH Procedures System 40 Functional Pre-Flight Procedures NOTE: There must be adequate aircraft DC voltage (14 or 28VDC) to perform these checks. Low voltage may adversely effect the Functional Pre-flight Procedures. 1. Position the Avionics Master Switch ON, then position the A/P Master Switch to ON.

  • Page 192: System 40 In-Flight Procedures

    System 40/50 POH 4.2 System 40 In-Flight Procedures 1. A/P Master Switch ON; RDY light illuminates. 2. Trim aircraft to desired flight conditions. Maintain yaw trim during all autopilot operations. 3. Center Turn Knob, press and release ON/OFF Switch. 4. Set Turn Knob to level or turning flight, as desired. 5.
  • Page 193 System 40/50 POH 310 ° ° ° ° 310 ° ° ° ° 130 ° ° ° ° 085 ° ° ° ° 265 ° ° ° ° 1. A. Tune navigation to LOC frequency. Verify signal. B. Select HDG Mode, position the aircraft on OUTBOUND LOC HDG. C.

  • Page 194: Straight-In Localizer Approach And Tracking With Standard Dg

    System 40/50 POH 4.7 Straight In Localizer Approach and Tracking with Standard DG 265 ° ° ° ° 085 ° ° ° ° 130 ° ° ° ° 1. A. Tune navigation radio to Localizer frequency. Verify signal. B. Select the HDG Mode and position aircraft on the published LOC INBOUND heading course.

  • Page 195: Procedure Turn Localizer Approach And Tracking, Optional Hsi

    System 40/50 POH 4.8 Procedure Turn Localizer Approach and Tracking, Optional HSI 310 ° ° ° ° 130 ° ° ° ° 310 ° ° ° ° 265 ° ° ° ° 085 ° ° ° ° 1. A. Tune navigation radio to LOC frequency. B.

  • Page 196: Back Course Straight-In Approach, Optional Hsi

    System 40/50 POH 4.9 Back Course Straight-In Approach, Optional HSI Back Course 265° ° ° ° 085° ° ° ° 310 ° ° ° ° Use the Reverse Mode to track the front course OUTBOUND or the back course INBOUND to the airport. Set the HSI Course Pointer to the front course INBOUND heading.

  • Page 197: Back Course Procedure With Optional Hsi

    System 40/50 POH 4.10 Back Course Procedure Turn with Optional HSI 265 ° ° ° ° Back Course 085 ° ° ° ° 310 ° ° ° ° 130 ° ° ° ° Use the Reverse Mode to track the front course OUTBOUND or the back course INBOUND to the airport.

  • Page 198: System 50 Functional Pre-Flight Procedures

    System 40/50 POH 4.11 System 50 Functional Pre-Flight Procedures NOTE: Refer to the System 40 Pre-Flight Procedures for Roll Command checks. NOTE: During the functional checks, the system requires adequate DC voltage of 14 or 28 VDC minimum, as appropriate. NOTE: The System 50 uses a vertical acceleration accelerometer to detect short-term AC motions, which, with the altitude...
  • Page 199 System 40/50 POH 3. Engage STB Mode, move control wheel to the neutral position using the Left/Right Control knob. NOTE: The A/P can be engaged and disengaged repeatedly without repeating the test sequence, unless electrical power is interrupted. If a power interruption occurs, accomplish the test again to get a RDY indication.

  • Page 200: System 50 In-Flight Procedures

    System 40/50 POH 4.12 System 50 In-Flight Procedures CAUTION Conduct the required Pre-flight test, if necessary, in flight. However, the pitch servo will engage and disengage as part of the Self-Test. Therefore do not attempt flight maneuvers during the power-up test. CAUTION If the pilot fails to trim the aircraft, the UP or DN Trim Light will annunciate and after 4 seconds the trim light will flash.

  • Page 201: Emergency Procedures

    System 40/50 POH 4.13 Emergency Procedures This information is supplemental to and does not supercede or amend the information provided in the AFMS, POHS, SFM, for specific aircraft and autopilot installation manuals. NOTE: If the aircraft does not have a copy of the required AFMS, POHS, or SFMs' please contact customer service and S-TEC will provide a copy at no cost.
  • Page 202 System 40/50 POH Page Intentionally Blank 4-14 2nd Ed: October 25, 2002...
  • Page 203 System 40/50 POH SECTION 5 APPENDICES 2nd Ed: October 25, 2002...
  • Page 204 System 40/50 POH Page Intentionally Blank 2nd Ed: October 25, 2002...

  • Page 205: Appendix A: Specifications

    System 40/50 POH Appendix A: Specifications System Requirements Programmer/Computer Power required 14/28 Vdc Weight 2.2 lbs. (40), 2.8 lbs. (50) Dimensions 3.28 x 3.28 x 7.4 in. Directional Gyro (optional) Power required Vacuum or pressure, 4.5-5.2 Hg Minimal air flow 2.2 CFM Air filtration 3 Micron, 95%...
  • Page 206 System 40/50 POH System Current Requirements Average Operating Current System @14 Vdc @28 Vdc 1.0 Amps 0.5 Amps 2.0 Amps 1.0 Amps Max Current System @14 Vdc @28 Vdc 3.0 Amps 2.0 Amps 5.0 Amps 3.0 Amps 2nd Ed: October 25, 2002...

  • Page 207: Glossary

    SYSTEM 40/50 POH SECTION 6 GLOSSARY 2nd Ed: October 25, 2002...
  • Page 208 SYSTEM 40/50 POH Page Intentionally Blank 2nd Ed: October 25, 2002...
  • Page 209 SYSTEM 40/50 POH GLOSSARY Term Meaning Aircraft Altitude AFMS Airplane Flight Manual Supplement Auto Pilot Circuit Breaker Course Deviation Indicator Directional Gyro Federal Aviation Administration Global Positioning System Heading Mercury Horizontal Situation Indicator Instrument Flight Rules In Flight Procedures Instrument Meteorological Conditions Localizer LORAN Long Range Navigation...
  • Page 210 SYSTEM 40/50 POH Page Intentionally Blank 2nd Ed: October 25, 2002...
  • Page 211 S-TEC Corporation A Meggitt Aerospace Systems Company One S-TEC Way · Municipal Airport Mineral Wells, Texas 76067-9236 USA Telephone: 940/325-9406; FAX: 940/325-3904 1-800-USA-STEC www.s-tec.com Information in this document is subject to change without notice. ©2002 S-TEC Corporation. All rights reserved. Printed in the United States of America. S-TEC and the S-TEC logo are registered trademarks of S-TEC Corporation.

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