SYSTEM 55 AUTOPILOT
Contents
1. APR will be annunciated 53 The selected heading will now be flown until the autopilot computes that an on course turn must be made to minimize overshoot at the point of intercept At the time the on course turn begins the HDG mode will extinguish NOTE INTERCEPT ANGLES GREATER THAN 45 USUALLY RE SULT IN SOME COURSE OVERSHOOT DEPENDING ON THE DIS TANCE FROM THE STATION AND AIRCRAFT SPEED THERE FORE ANGLES GREATER THAN 45 ARE NOT RECOMMENDED 54 Back Course Straight In Approach Optional HSI Back Course 085 gt te x 1 a Tune navigation radio to LOC frequency b Set Course Pointer to published inbound front course heading c Press REV mode switch d Heading bug can be set to missed approach heading after course capture N l NOTE To establish a selected angle of intercept dual mode inter cept on the back course set the course pointer to the pub lished inbound front course 55 heading and the heading bug to the desired heading to es tablish the selected angle in tercept 310 Press the HDG and REV mode switches simultaneously Upon capture of the back course the autopilot automatically cancels HDG mode and tracks the final approach course Single Cue Flight Director Operation Optional wuy A remote Parallax Adjustment is provided to change the height of the horizontal display to compensate for different seat heights a2. SOFT If the heading bug is within 5 of center and needle deflection is less than 10 the computer will immediately establish this sensitivity level when NAV is selected The system includes a course deviation monitor If the aircraft strays off LOC centerline by 50 needle deflection the NAV annunciator flashes a warning It also flashes when the OBS NAV flag is displayed When that occurs the FAIL annunciation will illuminate PILOT SELECTABLE INTERCEPT ANGLE S The pilot may select an angle of intercept less than the standard 45 Simply place the heading bug on the D G on the desired heading to be used for the course intercept and push both HDG and NAV switches si multaneously HDG NAV and APR will be annunciated HDG NAV APR Es OW oe oe ee TEC 27 The selected heading will now be flown until the autopilot computes that an on course turn must be made to minimize overshoot at the point of intercept At the time the on course turn begins the HDG mode will extinguish and you must move the heading bug to match the localizer course This will allow the autopilot the full range of cross wind correction during NAV APR track mode NOTE INTERCEPT ANGLES GREATER THAN 45 USUALLY RE SULT IN SOME COURSE OVERSHOOT DEPENDING ON THE DIS TANCE FROM THE STATION AND AIRCRAFT SPEED THERE FORE ANGLES GREATER THAN 45 ARE NOT RECOMMENDED 28 Straight in Localizer Approach and Tracking with Standard D
3. b 1 a Tune navigation radio 3 a In 90 increments set 4 a Once established in NOTE to LOC frequency heading bug to inbound NAV mode set heading bug The pilot may elect to use b Set published inbound procedure turn heading to the published missed CWS for stabilizing the LOC course heading with b When established on approach heading If a aircraft for missed course pointer inbound procedure turn missed approach is approach and then press c Push REV mode switch heading press NAV mode declared at the middle HDG mode 2 a Set heading bug to switch marker disconnect the published outbound autopilot and stabilize the procedure turn heading aircraft for the missed b Press HDG mode switch approach before engaging HDG and VS modes 32 Localizer Intercept and Tracking Optional H S I With the appropriate localizer frequency selected set the course selector to the INBOUND localizer course and engage the NAV mode to track the localizer front course inbound or back course outbound When a localizer is channeled and NAV mode is selected the System 55 will automatically execute high sensitivity gain for the approach and automatically activate the APR mode NAV and APR will be annunci ated If the course needle is at full scale deviation the autopilot will establish a 45 intercept angle As the aircraft approaches the localizer course the autopilot senses the closure rate and gradually smoothly shallows the intercep
4. following of the desired command 57 For manually controlled flight by the flight director place the FD AP master switch in the FD position FD This disables the autopilot servos allowing the pilot to control the aircraft to the flight director commands OFF FD AP MASTER FD AP To engage the autopilot without interruption FD simply place the FD AP master switch in the FD AP position OFF FD AP MASTER NOTE A PITCH MODE ALT OR VS AND A ROLL MODE HDG NAV OR REV MUST BE ACTIVATED BEFORE THE STEERING COMMAND BARS WILL COME INTO VIEW 58 SYSTEM FAILURE AND CAUTION ANNUNCIATIONS The System 55 contains a number of automatic failure and caution annunications to advise the pilot of operational problems They are as follows ANNUNCIATION Flashing RDY for 5 seconds with audible tone Flashing RDY with Audible tone then Extinguished Flashing NAV REV or APR Flashing NAV REV or APR Steady FAIL Flashing VS Flashing GS CONDITION Indicates Autopilot disconnect All Annunciations except RDY are cleared Turn Coordinator Gyro Rotor Speed Low Autopilot dis connects and can not be re engaged Indicates off Navigation course by 50 needle deviation or more Indicates invalid Radio Navigational Signal Indicates excessive Vertical Speed Error over selected VS usually climb Indicates off glideslope centerline by 50 needle deviation or more 59 ACTION N A Chec
5. modify the present vertical speed using the VS knob The pilot may re enter the CWS mode at any time by simply depressing the CWS switch on the control wheel positioning the aircraft in the de sired roll and pitch attitude and releasing the CWS switch NOTE After initial autopilot engagement when the CWS switch is depressed the roll and pitch servos will be disengaged during the maneuvering phase An audible tone will be heard indicating servo disengagement HEADING MODE Heading HDG mode may be selected initially from CWS mode or RDY mode Set the heading bug on the DG or optional HSI to the desired heading and press the HDG switch The HDG annunciator will illumi nate New headings can be selected simply by repositioning the heading bug A reminder When operating in the HDG mode the system is not cou pled to any navigation aid It merely flies a specific heading It will be necessary to monitor navigation instruments for course deviation due to wind drift and to establish wind correction angles 11 NAV Intercept and Tracking with Standard DG To intercept and track a VOR RNAV Loran or GPS course tune the Navigation Radio receiver to the proper frequency and select the desired course Move the heading bug in the direction of desired travel to match the selected course Engage the NAV mode If the course needle is at full scale deviation the autopilot will establish a 45 intercept angle As the aircraft appro
6. of 90 rather than the full 180 When the outbound leg is completed again rotate the HDG bug in the direction of the turn in 90 increments to re establish the inbound course and press the NAV switch twice when localizer needle deflection is near 50 of full scale If on this inbound leg you wish to rearm the glideslope press the NAV switch only once 39 Procedure Turn for Glideslope Approach 1 a Tune navigation radio to ILS frequency b Follow the procedure s for LOC Approach Intercept and Tracking in this manual 2 a If a procedure turn is required enter the procedure turn above the published alti tude b Upon entering the inbound procedure turn sequence press the VS mode switch c Rotate the VS SELECTOR knob to establish the desired rate of descent to reach approach altitude at completion of the procedure turn d Upon reaching approach altitude press the ALT mode switch e When the NAV mode switch is pressed and if the aircraft is below the glide slope the APR and GS annunciations will illuminate along with the ALT annunciation f Upon capture of the glide slope the ALT annunciation will extinguish See text ref Glideslope Operation 3 a If a circling or straight in approach to the ILS course is established descend to approach altitude well in ad vance of reaching the outer marker 40 glideslope prior to reaching the outer marker follow the procedure
7. primary purpose of the System 55 Pilot Information Manual PIM is to provide potential S TEC Autopilot buyers with step by step Functional Preflight and In Flight Operating procedures for the system NOTE This manual is for information only Not approved for cockpit use AIP HDG NAV w APR REV TRIMS ALT GS VS H VS X100 SYSTEM 55 SCHEMATIC Directional Turn HSI Flight Director VOR LOC Gyro Optional Coordinator Optional Optional Flight Guldance Programmer Computer 3 Annunciator Alt VS Preselect A Optional Optional ri i 5 Trim Servo Pressure Optional Transducer Acronyms Used in This Manual ALT AFMS A P CB CDI CWS DG FAA GPS HD Hg HSI HI TRK IFR IFP IMC LOC LORAN LO TRK NAV OBS PIM PSI RDY SFM ST TSO VFR VMC VOR Altitude Airplane Flight Manual Supplement Auto Pilot Circuit Breaker Course Deviation Indicator Control Wheel Steering Directional Gyro Federal Aviation Administration Global Positioning System Heading Mercury Horizontal Situation Indicator High Gain Tracking Instrument Flight Rules In Flight Procedures Instrument Meteorological Conditions Localizer Long Range Navigation Low Gain Tracking Navigation Omnibearing Selector Pilot Information Manual Pounds Per Square Inch Ready Supplemental Flight Manual Stabilizer Technical Standard Order Visual Flight Rules Visual Meteorologica
8. remote annunciator is installed NAV APR CAP and SOFT will be annunciated 18 VERTICAL SPEED VS In order to engage vertical speed the autopilot roll axis must be engaged Selecting CWS mode or any roll mode will satisfy this requirement In CWS mode the pilot may select the desired vertical speed in 100 ft in crements by rotating the VS knob clockwise or counter clockwise With any roll mode engaged the pilot may select the VS mode by press ing the VS mode select switch The autopilot will synchronize with the aircraft s vertical speed at the time the mode is selected and the corre sponding vertical speed will be indicated in the Programmer Computer display Vertical speed may now be modified in 100 ft increments by ro tating the VS knob clockwise or counter clockwise The positive symbol annunciation indicates a climb vertical speed se lection Clockwise rotation of the VS knob increases the rate of climb and counter clockwise rotation decreases the rate of climb to 0 The negative symbol annunciation indicates a descent vertical speed selec tion Counter clockwise rotation of the VS knob increases the rate of descent and clockwise rotation decreases the rate of descent to 0 Maxi mum selectable VS limits are 1600 FPM NOTE IF THE VS MODE ANNUNCIATOR FLASHES WHILE IN THE VS MODE THIS IS AN INDICATION OF EXCESSIVE ERROR BETWEEN ACTUAL VERTICAL SPEED COMPARED TO SE LECTED VERTICAL SPEED USUALLY I
9. resulting To ensure that no hidden failures have occurred conduct a trim preflight check prior to every flight 22 Procedure Turn Localizer Approach Standard D G Select the appropriate localizer frequency Set the heading bug to the OUTBOUND localizer course and engage the REV mode to track the lo calizer front course outbound or back course inbound When a localizer is channeled and REV mode is selected the System 55 will automatically execute high sensitivity gain for the approach and REV and APR will be annunciated If the course needle is at full scale deviation the autopilot will establish a 45 intercept angle As the aircraft approaches the localizer course the autopilot senses the closure rate and gradually smoothly shallows the intercept angle The point at which this turn begins is variable depend ing on the aircraft position and closure rate to the course However the turn will always begin between 100 full scale needle deflection and 20 of full scale During the intercept sequence the system operates in maximum gain and sensitivity to needle position and motion 90 of standard rate turn When the localizer course is intercepted and the needle is centered indi cating course capture initiation of the tracking gain program is automatic If the aircraft is equipped with the optional annunciator the REV APR and CAP modes will be annunciated 23 The high sensitivity level is mainta
10. will capture and track back course outbound z 51 2 a Set heading bug to pub lished outbound procedure turn heading b Press HDG mode switch C 310 x 3 a In 90 increments set heading bug to inbound pro cedure turn heading b Press REV mode switch Autopilot will intercept cap ture and track back course inbound to the airport Localizer Back Course Intercept and Tracking Optional H S I With the appropriate localizer frequency selected set the course selector to the INBOUND Localizer FRONT Course and engage the REV mode to track the localizer back course inbound or front course outbound When a localizer is channeled and REV mode is selected the System 55 will automatically execute high sensitivity gain for the approach and automatically activate the APR mode REV and APR will be annunci ated If the course needle is at full scale deviation the autopilot will establish a 45 intercept angle As the aircraft approaches the localizer course the autopilot senses the closure rate and gradually smoothly shallows the intercept angle The point at which this turn begins is variable depend ing on the aircraft position and closure rate to the course However the turn will always begin between 100 full scale needle deflection and 20 of full scale During the intercept sequence the system operates in maximum gain and sensitivity to needle position and motion 90 of standard rate turn
11. 130 NOTE The pilot may elect to use CWS for stabilizing the aircraft for missed approach and then press HDG mode Glideslope Intercept and Tracking To arm the automatic glideslope capture function the following condi tions must be met a NAV receiver must be tuned to the appropriate fre quency b glideslope signal must be valid no flag c autopilot must be in NAV APR ALT modes d aircraft must be 60 or more below the GS centerline during the approach to the intercept point and within 50 needle deviation of the localizer centerline at the point of intercept usu ally the outer marker Glideslope arming will occur when the above conditions have existed for 10 seconds Illumination of the GS annunciator will occur indicating arming has been accomplished The ALT annunciator remains on 37 Glideslope capture is indicated by extinguishing of the ALT annunciation NOTE IF VECTORED TO INTERCEPT THE LOCALIZER TOO CLOSE TO THE GLIDESLOPE INTERCEPT POINT RESULTING IN LESS THAN 60 GS NEEDLE DEVIATION WHEN ON COURSE THE SYSTEM WILL NOT AUTOMATICALLY ARM THE GLIDE SLOPE MANUAL ARMING MUST THEN BE FOLLOWED Manual Arm Automatic Capture If approach vectoring locates the aircraft above or too near the glideslope centerline at the intercept point usually the outer marker it becomes nec essary to execute manual arming of the glideslope This is done by a pressing the ALT switch once if operating in the a
12. DISEN GAGES THE AUTOPILOT THERE WILL BE A RESIDUAL OUT OF TRIM FORCE AT THE CONTROL WHEEL BE ALERT FOR THIS CONDITION IF THE AUTOPILOT IS DISENGAGED WHILE TRIM IS ANNUNCIATED 20 OPTIONAL AUTOTRIM If the autopilot is equipped with optional autotrim the aircraft elevator trim will be maintained automatically when the trim master switch is on and a pitch mode is activated When the elevator trim is in motion TRIM and the sia up or Y dn symbol will annunciate indicating trim in motion and direction of travel Should the trim continue to run in excess of 7 seconds these annuncia tions will flash If the trim master switch is OFF or a failure has occurred in the autotrim the system will automatically revert to Pitch Trim Indicator mode of op eration NOTE USING THE TRIM SWITCH ON THE CONTROL WHEEL WHILE THE PITCH AXIS OF THE AUTOPILOT IS EN GAGED WILL DISCONNECT THE AUTOPILOT 21 The autotrim option also provides the pilot with Manual Electric Trim when the autopilot is disengaged or if only a roll axis mode has been en gaged To use manual electric trim simply push the trim toggle switch located on the aircraft s control wheel in the desired direction of trim FOR WARD for nose down or AFT for nose up TRIM will be annunciated and will flash while the trim is in motion The S TEC trim system is designed to accept any type of single failure mechanical or electrical without uncontrolled operation
13. G Na A 085 gt 2 265 ee z 4 N 1 a Tune navigation radio to localizer frequency b Set HDG bug to published inbound course c Press NAV mode switch Autopilot will intercept capture and track the localizer course 2 If a missed approach is declared at the middle marker a Disconnect the autopilot and stabilize the aircraft for the missed approach b Set the HDG bug to the published missed approach heading 29 l c Press the HDG mode switch d Press the VS mode switch if desired X 130 NOTE The pilot may elect to use CWS for stabilizing the aircraft for missed approach and then press HDG mode Procedure Turn Localizer Approach Optional H S I Select the appropriate localizer frequency Set the course selector to the INBOUND localizer course and engage the REV mode to track the local izer front course outbound or back course inbound When a localizer is channeled and REV mode is selected the System 55 will automatically execute high sensitivity gain for the approach and REV and APR will be annunciated If the course needle is at full scale deviation the autopilot will establish a 45 intercept angle As the aircraft approaches the localizer course the autopilot senses the closure rate and gradually smoothly shallows the intercept angle The point at which this turn begins is variable depend ing on the aircraft posit
14. LES GREATER THAN 45 ARE NOT RECOMMENDED 47 Back Course Straight In Approach Standard DG 265 KX Back Course 4 N 1 a Tune navigation radio to LOC frequency b Set heading bug to inbound final approach heading 085 gt N l N 310 c Press REV mode switch Autopilot will intercept and track the back course to the airport 48 Procedure Turn Localizer Back Course Approach Optional H S I Select the appropriate localizer frequency Set the course selector to the INBOUND Localizer FRONT Course and engage the NAV mode to track the localizer back course outbound or front course inbound When a localizer is channeled and NAV mode is selected the System 55 will automatically execute high sensitivity gain for the approach and NAV and APR will be annunciated If the course needle is at full scale deviation the autopilot will establish a 45 intercept angle As the aircraft approaches the localizer course the autopilot senses the closure rate and gradually smoothly shallows the intercept angle The point at which this turn begins is variable depending on the aircraft position and closure rate to the course However the turn will always begin between 100 full scale needle deflection and 20 of full scale During the intercept sequence the system operates in maximum gain and sensitivity to needle position and motion 90 of standard rate turn When the localizer course is i
15. N A CLIMB AND THE PI LOT SHOULD ADJUST AIRCRAFT POWER OR REDUCE THE VER TICAL SPEED COMMAND AS APPROPRIATE 19 ALTITUDE ALT The altitude hold mode ALT may be engaged with any roll mode CWS mode or VS mode engaged by pressing the ALT mode switch The air craft will maintain the pressure altitude present at the time of ALT mode selection Altitude Correction for en route barometric pressure changes may be made while in ALT mode by rotation of the VS knob Each Click will change the altitude by 10 ft The maximum altitude correction is 200 ft Corrections in excess of 200 ft will require selecting the VS mode and climbing or descending to the new altitude and re engaging ALT mode Pitch Trim Indicator Without automatic trim or when trim is turned off a sensor in the System 55 autopilot pitch servo detects out of trim elevator loads When such forces exceed a preset level and time delay TRIM will annunciate on the Flight Guidance Programmer Computer with either the si up or W dn symbol annunciated to indicate the direction elevator trim is required In addition effective with unit serial number 321 and on an audible warning tone will sound for 5 seconds NOTE This is the same audible beeping tone emitted when the autopilot is disconnected but at a slower rate The annunciation will be steady for about 5 seconds then flash until proper trim conditions have been met NOTE IF TRIM IS ANNUNCIATED AND THE PILOT
16. N position and ob serve that all segments of the Programmer Computer display and optional Annunicator if installed illuminate for 5 seconds during the test TEC Satisfactory completion is indicated by only RDY remaining on at the conclusion of the 5 second test S TEC Should a fault be detected the FAIL annunciation will remain on at the conclusion of the test and the autopilot can not be engaged If the the autopilot detects the Turn Coordinator rotor speed as low or not turning the display will remain blank and the autopilot can not be en gaged If this condition occurs you should consult your dealer before other use of the autopilot is attempted AIP F Ay S TEC Preflight Test Without Optional Autotrim Center the control wheel Press and release the Control Wheel Steering CWS switch CWS and VS should annunciate Move the aircraft control wheel in both the roll and pitch axes to overpower the autopilot servos Control motions should be smooth without looseness or free play Press the control wheel Disconnect switch RDY will flash then annunciate steady An audible tone should be heard indicating the autopilot disconnect Move the aircraft controls to ensure freedom and confirm the autopilot has disconnected If optional autotrim is not installed this concludes the preflight test Preflight Test With Optional Autotrim With the aircraft controls centered grasp the control wheel and press and
17. RIM UNTIL THE FAULT IS COR RECTED S TEC SYSTEM 55 NORMAL OPERATING PROCEDURES In order to activate any mode the autopilot master switch must be in the ON position and the RDY annunciator must be illuminated CONTROL WHEEL STEERING CWS Your new System 55 has a very desirable mode of operation Control Wheel Steering CWS This feature is the quickest way to engage both the Roll and Pitch Axes of the System and synchronize the autopilot with the present aircraft attitude AIP vs amp m CAPR JR REY J Act JC vs J TEC Depress and hold the Control Wheel Steering switch located on the air craft s control wheel The CWS and VS modes will annunciate and RDY will extinguish Position the aircraft in the desired roll and pitch attitude Note Aircraft vertical speed x 100 will be displayed in the Program mer Computer Annunciator window directly above the VS selector knob Example 6 equals 600 FPM rate of climb Allow the aircraft to stabilize in the desired attitude for 2 to 3 seconds release the Control Wheel Steering switch and the autopilot roll and pitch servos will engage synchronized with the Aircraft s turn rate and vertical speed 10 NOTE IF THE AIRCRAFT ROLL ANGLE IS GREATER THAN A STANDARD RATE TURN WHEN THE CWS SWITCH IS RELEASED THE BANK ANGLE WILL BE REDUCED TO PRODUCE 90 OF A STANDARD RATE TURN AS A MAXIMUM From the CWS mode the pilot may select other modes such as HDG NAV ALT or may
18. SYSTEM 55 AUTOPILOT Pilot s Information Manual 3 HDG NAV APR REV CAP VS ALT GS FD CWS SOFT SEL FAIL DSBL TRIM RDY HDG NAV APR REV TRIMS ALT GS vs 4 TEC THIS MANUAL IS FOR INFORMATION ONLY NOT APPROVED FOR COCKPIT USE Table of Contents General Introduction System Schematic List of Acronyms Modes of Operation Preflight Procedures A B Autopilot Optional Autotrim Normal Operating Procedures A B G z POVOZA Control Wheel Steering Heading Mode NAV Intercept Tracking Standard DG Selectable Intercept Angle s NAV Intercept Tracking Optional HSI Selectable Intercept Angle s Approach APR Mode Switch Vertical Speed VS Altitude Mode ALT Pitch Trim Indicator Autotrim Optional Procedure Turn Localizer Approach Std DG Localizer Intercept Tracking Standard DG Procedure Turn Localizer Approach Optional HSI Localizer Intercept Tracking Optional HSI Glideslope Intercept Tracking Procedure Turn Back Course Approach Std DG Localizer Back Course Intercept Track Std DG Procedure Turn Back Course Approach Opt HSI Localizer Back Course Intercept Track Opt HSI Flight Director Operation Optional System Failure and Caution Annunciations Autopilot Disconnect System Specifications 10 11 12 14 28 47 15 16 36 54 17 19 20 20 21 23 26 31 38 43 46 50 53 57 60 61 62 34 Introduction The
19. When the localizer course is intercepted and the needle is centered indi cating course capture initiation of the tracking gain program is automatic If the aircraft is equipped with the optional annunciator the REV APR and CAP modes will be annunciated 52 The high sensitivity level is maintained for about 15 seconds while wind correction angle is established Turn rate maximum is then reduced to 45 standard rate The optional remote annunciator will indicate REV APR CAP and SOFT If the course selector is within 5 of center and needle deflection is less than 10 the computer will immediately establish this sensitivity level when NAV is selected Since the heading bug is not used for the final approach segment the pilot may elect to move the heading bug to the published missed approach heading for reference and use in the heading mode should a missed ap proach be necessary The system includes a course deviation monitor If the aircraft strays off LOC centerline by 50 needle deflection the NAV annunciator flashes a warning It also flashes when the H S I NAV flag is displayed When that occurs the FAIL annunciation will illuminate PILOT SELECTABLE INTERCEPT ANGLE S The pilot may select an angle of intercept less than the standard 45 Simply place the heading bug on the desired heading to be used for the course intercept and push both HDG and REV switches simultaneously HDG REV and
20. aches the selected course the autopilot senses the closure rate and gradually smoothly shallows the intercept angle The point at which this turn begins is variable depending on the aircraft position and closure rate to the course However the turn will always begin between 100 full scale needle deflection and 20 of full scale During the intercept sequence the system operates in maximum gain and sensitivity to needle position and motion 90 of standard rate turn When the selected course is intercepted and the needle is centered indi cating course capture initiation of the tracking gain program is automatic If the aircraft is equipped with the optional Annunciator the NAV and CAP modes will be annunciated 12 The high sensitivity level is maintained for about 15 seconds while wind correction angle is established Turn rate maximum is then reduced to 45 standard rate The optional remote Annunciator will indicate NAV CAP and SOFT Approximately 60 seconds later the turn rate maximum is reduced to 15 of standard rate and the lowest level of sensitivity is achieved At this point the optional remote Annunicator will indicate NAV and SOFT The CAP annunciation will extinguish If the Heading bug is within 5 of center and needle deflection is less than 10 the computer will immediately establish this lowest sensitivity level when NAV is selected This condition provides low a
21. blished Turn rate maximum is then reduced to 45 of standard rate The optional remote annunciator will indicate REV APR CAP and SOFT If the heading bug is within 5 of center and needle deflection is less than 10 the computer will immediately establish this sensitivity level when NAV is selected The system includes a course deviation monitor If the aircraft strays off LOC centerline by 50 needle deflection the NAV annunciator flashes a warning It also flashes when the OBS NAV flag is displayed When that occurs the FAIL annunciation will illuminate PILOT SELECTABLE INTERCEPT ANGLE S The pilot may select an angle of intercept less than the standard 45 Simply place the heading bug on the D G on the desired heading to be used for the course intercept and push both HDG and REV switches si multaneously HDG REV and APR will be annunciated 46 The selected heading will now be flown until the autopilot computes that an on course turn must be made to minimize overshoot at the point of in tercept At the time the on course turn begins the HDG mode will extin guish and the heading bug must be moved to match the localizer back course inbound This will allow the autopilot the full range of cross wind correction during NAV APR track mode NOTE INTERCEPT ANGLES GREATER THAN 45 USUALLY RE SULT IN SOME COURSE OVERSHOOT DEPENDING ON THE DIS TANCE FROM THE STATION AND AIRCRAFT SPEED THERE FORE ANG
22. cted course is intercepted and the needle is centered indicating course capture initiation of the tracking gain program is automatic 15 If the aircraft is equipped with the optional annunciator the NAV and CAP modes will be annunciated The high sensitivity level is maintained for about 15 seconds while wind correction angle is established Turn rate maximum is then reduced to 45 standard rate The optional remote annunciator will indicate NAV CAP and SOFT Approximately 60 seconds later the turn rate maximum is reduced to 15 standard rate and the lowest level of sensitivity is achieved At this point the optional remote annunciator will indicate NAV and SOFT The CAP annunciation will extinguish If the course selector is within 5 of center and needle deflection is less than 10 the computer will immediately establish this lowest sensitivity level when NAV is selected This condition provides low activity levels during station passage when VOR signals are erratic In other words it ignores short term needle ex cursion The system includes a course deviation monitor If the aircraft strays off course or LOC centerline by 50 needle deflection the NAV annunciator flashes a warning It flashes at station passage because of short term needle excursion and because NAV signal is inadequate It also flashes when the H S I NAV flag is displayed When that occurs the FAIL an nunciatio
23. ctivity levels during station passage when VOR signals are erratic In other words it ignores short term needle ex cursion The system includes a course deviation monitor If the aircraft strays off course or LOC centerline by 50 needle deflection the NAV annunciator flashes a warning It flashes at station passage because of short term needle excursion and because the NAV signal is inadequate It also flashes when the OBS NAV flag is displayed When that occurs the FAIL annunciation will illuminate When operating in the NAV SOFT mode and needle deflection of 50 or more is experienced for 1 5 minutes the gain program will switch to NAV CAP SOFT increasing sensitivity and authority to re establish the aircraft on course 13 When a course change of 10 or more is required at an en route VOR se lect the new course and reset the NAV mode to reinstate the capture se quence Set the DG heading bug to the new course PILOT SELECTABLE INTERCEPT ANGLE S The pilot may select an angle of intercept less than the standard 45 Simply place the heading bug on the D G to the desired heading to be used for the course intercept and push both HDG and NAV switches si multaneously Both HDG and NAV will be annunciated The selected heading will now be flown until the autopilot computes that an on course turn must be made to minimize overshoot at the point of intercept At the time the on course turn begins the HDG mode will extin
24. eading bug to the INBOUND localizer course and engage the NAV mode to track the localizer front course inbound or back course outbound When a localizer is channeled and NAV mode is selected the System 55 will automatically execute high sensitivity gain for the approach and automatically activate the APR mode NAV and APR will be annunci ated If the course needle is at full scale deviation the autopilot will establish a 45 intercept angle As the aircraft approaches the localizer course the autopilot senses the closure rate and gradually smoothly shallows the intercept angle The point at which this turn begins is variable depend ing on the aircraft position and closure rate to the course However the turn will always begin between 100 full scale needle deflection and 20 of full scale During the intercept sequence the system operates in maximum gain and sensitivity to needle position and motion 90 of standard rate turn When the localizer course is intercepted and the needle is centered indi cating course capture initiation of the tracking gain program is automatic If the aircraft is equipped with the optional annunciator the NAV APR and CAP modes will be annunciated 26 The high sensitivity level is maintained for about 15 seconds while wind correction angle is established Turn rate maximum is then reduced to 45 standard rate The optional remote annunciator will indicate NAV APR CAP and
25. guish and you must move the heading bug to match the selected radio course This will allow the autopilot the full range of cross wind correction during NAV track mode 14 NOTE INTERCEPT ANGLES GREATER THAN 45 USUALLY RE SULT IN SOME COURSE OVERSHOOT DEPENDING ON THE DIS TANCE FROM THE STATION AND AIRCRAFT SPEED THERE FORE ANGLES GREATER THAN 45 ARE NOT RECOMMENDED NAV INTERCEPT AND TRACK OPTIONAL H S L If your aircraft is equipped with an optional Horizontal Situation Indica tor your S TEC autopilot will receive both left right deviation and course information when the course selector is set to the desired course With an H S I the heading bug is not used during tracking To intercept and track a VOR RNAV LORAN or GPS Course select the desired course with the H S I Course Selector and engage the NAV mode If the course needle is at full scale deviation the autopilot will establish a 45 intercept angle As the aircraft approaches the selected course the autopilot senses the closure rate and gradually smoothly shallows the intercept angle The point at which this turn begins is variable depend ing on the aircraft position and closure rate to the course However the turn will always begin between 100 full scale needle deflection and 20 of full scale During the intercept sequence the system operates in maximum gain and sensitivity to needle position and motion 90 of standard rate When the sele
26. ined for about 15 seconds while wind correction angle is established Turn rate maximum is then reduced to 45 standard rate The optional remote annunciator will indicate REV APR CAP and SOFT If the heading bug is within 5 of center and needle deflection is less than 10 the computer will immediately establish this sensitivity level when REV is selected Set the heading bug to the outbound procedure turn heading and select heading mode At the appropriate time in 90 increments set the head ing bug to the inbound procedure turn heading Once established on the inbound procedure turn heading follow the localizer intercept and track ing procedures for standard D G 24 Procedure Turn Localizer Approach and Tracking with Standard D G N 4 N l 310 265 gt z 1 a Tune navigation radio to LOC frequency b Set heading bug to pub lished outbound LOC heading c Push REV mode switch 2 a Set heading bug to outbound procedure turn heading b Press HDG mode switch 25 oy 4 1 N 3 a In 90 increments set heading bug to inbound procedure turn heading DQ 085 gt 4 a Set heading bug to in bound LOC heading b Press NAV mode switch Autopilot will intercept and capture localizer course and track inbound to the airport Localizer Intercept and Tracking Standard D G With the appropriate localizer frequency selected set the h
27. ion and closure rate to the course However the turn will always begin between 100 full scale needle deflection and 20 of full scale During the intercept sequence the system operates in maximum gain and sensitivity to needle position and motion 90 of standard rate turn When the localizer course is intercepted and the needle is centered indi cating course capture initiation of the tracking gain program is automatic If the aircraft is equipped with the optional annunciator the REV APR and CAP modes will be annunciated 30 The high sensitivity level is maintained for about 15 seconds while wind correction angle is established Turn rate maximum is then reduced to 45 standard rate The optional remote annunciator will indicate REV APR CAP and SOFT If the course selector is within 5 of center and needle deflection is less than 10 the computer will immediately establish this sensitivity level when REV is selected Set the heading bug to the outbound procedure turn heading and select heading mode At the appropriate time in 90 increments set the head ing bug to the inbound procedure turn heading Once established on the inbound procedure turn heading follow the localizer intercept and track ing procedures for optional H S I 21 Procedure Turn Localizer Approach and Tracking Optional HSI CX N ase lt B E eee 0 DQ A K 4 4 N Zzy N 1
28. k Power to Turn Coordinator Conduct other system checks as necessary Use HDG mode until Problem is identified Cross check raw NAV data compass hdg radio operation Check NAV Radio for proper reception Use HDG mode until problem is corrected Reduce VS Command and or adjust power as appropriate Check attitude and power Add or reduce power as appropriate Flashing GS Indicates invalid Disconnect autopilot steady FAIL glideslope radio and initiate go navigation signal around or missed approach as appropriate Inform ATC Flashing GS Indicates Manual Re enable by pushing Plus ALT Glideslope disable NAV mode switch NOTE IF ANY OF THE ABOVE FAILURE ANNUNCIATIONS OCCUR AT LOW ALTITUDE OR DURING AN ACTUAL INSTRUMENT APPROACH DISENGAGE THE AUTOPILOT EXECUTE A GO AROUND OR MISSED APPROACH AS APPROPRIATE INFORM ATC OF THE PROBLEM DO NOT ATTEMPT TO TROUBLESHOOT OR OTHERWISE IDENTIFY THE NATURE OF THE FAILURE UNTIL A SAFE ALTITUDE AND MANEUVERING AREA ARE REACHED OR SAFE LANDING IS EXECUTED Autopilot Disconnect The autopilot can be disconnected by any of the following actions A Turn the Autopilot Master switch OFF B Press the Autopilot Disconnect Trim Interrupt switch on the aircraft s control wheel C Pull the aircraft s AUTOPILOT Circuit Breaker D If the aircraft is equipped with optional automatic trim and the pitch axis of the autopilot is engaged depress the Trim switch on the aircraft c
29. l Conditions Very High Frequency Omnidirectional Radio Range SYSTEM 55 MODES OF OPERATION The System 55 Flight Guidance Programmer Computer serves the function of converting pilot commands to logic signals for the roll and pitch computer functions As the pilot enters the desired mode by press ing the appropriate mode selector switch the computer acknowledges the mode causing the appropriate annunciator to illuminate The Roll Computer receives signal inputs from the Directional Gyro or optional H S I VOR LOC RNAV Loran or GPS Deviation Indicators and the Turn Coordinator It computes roll servo commands for stabili zation turns radio intercepts and tracking The pitch computer receives signal inputs from the altitude pressure Transducer Accelerometer Glideslope Deviation Indicator and Vertical Speed Modifier Control or optional Altitude Selector Alerter or Alti tude Vertical Speed Selector It computes pitch servo commands for ver tical speed altitude hold and glide slope intercept and tracking Sensing for trim annunciation or optional automatic elevator trim is provided by the pitch servo Drive for the optional elevator trim servo is provided by the pitch computer SYSTEM 55 PREFLIGHT PROCEDURE The System 55 incorporates a SELF TEST which must pass before the autopilot can be engaged To perform the test aircraft D C electrical power must be on and supplied to the autopilot Place the AUTOPILOT MASTER switch to the O
30. ltitude hold mode and b pressing the ALT switch twice if operating in the VS mode Once capture is achieved the GS annunciation will illuminate and the ALT annunciation will extinguish The system includes a Glideslope deviation monitor If the aircraft strays off glideslope center line by 50 needle deflection the GS annunciator flashes a warning It also flashes when the GS flag is displayed When that occurs the FAIL annunciation will illuminate 38 NOTE IF IT BECOMES NECESSARY TO ESTABLISH A HOLDING PATTERN AT THE OUTER MARKER AUTOMATIC GLIDESLOPE ARMING CAN BE DISABLED BY PRESSING THE NAV SWITCH A SECOND TIME WHILE IN THE NAV APR MODE THE GS AN NUNCIATOR WILL FLASH AND ALT WILL BE ANNUNCIATED IF EQUIPPED WITH THE OPTIONAL REMOTE ANNUNCIATOR THE GS ANNUNCIATOR WILL FLASH AND THE ALT AND DSBL AN NUNCIATORS WILL ILLUMINATE TO INDICATE THAT THE GS MODE IS DISABLED TO RE ESTABLISH GS ARMING PRESS THE NAV MODE SWITCH AGAIN THE DSBL CONDITION ANNUN CIATOR WILL EXTINGUISH THE GS ANNUNCIATOR WILL CEASE TO FLASH AND BE STEADY REARMING WILL OCCUR WHEN ALL OTHER REQUIRED CONDITIONS STATED HAVE BEEN MET To fly the holding pattern if inbound to the outer marker press the NAV switch twice to disable the glideslope arming When the outer marker or holding fix is reached press the HDG switch and rotate the heading bug in the direction of the turn It is best to select the reciprocal course in in crements
31. n will illuminate 16 When operating in the NAV SOFT mode and needle deflection of 50 or more is experienced for 1 5 minutes the gain program will switch to NAV CAP SOFT increasing sensitivity and authority to re establish the aircraft on course When a course change of 10 or more is required at an en route VOR se lect the new course and reset the NAV mode to reinstate the capture se quence PILOT SELECTABLE INTERCEPT ANGLE S The pilot may select an angle of intercept less than the standard 45 Simply place the heading bug on the H S I on the desired heading to be used for the course intercept and push both HDG and NAV switches si multaneously Both HDG and NAV will be annunciated The selected heading will now be flown until the autopilot computes that an on course turn must be made to minimize overshoot at the point of intercept At the time the on course turn begins the HDG mode will extinguish 17 NOTE INTERCEPT ANGLES GREATER THAN 45 USUALLY RE SULT IN SOME COURSE OVERSHOOT DEPENDING ON THE DIS TANCE FROM THE STATION AND AIRCRAFT SPEED THERE FORE ANGLES GREATER THAN 45 ARE NOT RECOMMENDED APPROACH APR MODE SWITCH The APR mode provides increased sensitivity for VOR LORAN GPS or AREA NAV approaches The pilot may also select this mode if increased sensitivity is desired for en route NAV tracking NAV and APR will be annunciated on the Programmer Computer If the optional
32. nd manuver If a missed approach is declared the autopilot can be re engaged after a stabilized climb has been established NOTE The pilot may elect to use CWS while maneuvering the aircraft for the missed approach Procedure Turn Back Course Localizer Approach Standard D G Select the appropriate localizer frequency Set the heading bug to the Front course INBOUND localizer heading and engage the NAV mode to track the localizer back course outbound When a localizer is channeled and NAV mode is selected the System 55 will automatically execute high sensitivity gain for the approach and NAV and APR will be annunciated If the course needle is at full scale deviation the autopilot will establish a 45 intercept angle As the aircraft approaches the localizer course the autopilot senses the closure rate and gradually smoothly shallows the intercept angle The point at which this turn begins is variable depend ing on the aircraft position and closure rate to the course However the turn will always begin between 100 full scale needle deflection and 20 of full scale During the intercept sequence the system operates in maximum gain and sensitivity to needle position and motion 90 of standard rate turn When the localizer course is intercepted and the needle is centered indi cating course capture initiation of the tracking gain program is automatic If the aircraft is equipped with the optional annunciator
33. nd a remote switch allows flight director operation when the autopilot is not in use This system which integrates both the roll axis and pitch axis offers synchronized display of the flight profile It is automatically activated when the autopilot is engaged A Flight Director provides a visual indication of how accurately the pilot or autopilot is tracking the commands of the active mode of operation Activation is indicated by the FD annunciator on the remote an nunciator 56 For proper flight technique the sys tem presentation requires the pilot to roll and pitch the aircraft toward the steering command bars until the delta shaped reference is tucked into the steering command bars indicat ing that commands have been satis fied For example if the display is up and left the pilot would be re quired to establish a left turn pitch up attitude As bank angle and vertical speed ap proach the required amounts bank angle and pitch up attitude are shal lowed When the delta reference and the steering bars are matched the commands have been met Thereaf ter it is necessary to maneuver the aircraft to keep the display elements matched in order to accurately fly the programmed modes Accurate flight director operation requires alertness by the pilot and monitoring of the movement of the display Keeping it matched is quite simple However control inputs must be timely for accurate flight director
34. ntercepted and the needle is centered indi cating course capture initiation of the tracking gain program is automatic If the aircraft is equipped with the optional annunciator the NAV APR and CAP modes will be annunciated 49 The high sensitivity level is maintained for about 15 seconds while wind correction angle is established Turn rate maximum is then reduced to 45 standard rate The optional remote annunciator will indicate NAV APR CAP and SOFT If the course selector is within 5 of center and needle deflection is less than 10 the computer will immediately establish this sensitivity level when REV is selected Set the heading bug to the outbound procedure turn heading and select heading mode At the appropriate time in 90 increments set the head ing bug to the inbound procedure turn heading Once established on the inbound procedure turn heading follow the localizer back course intercept and tracking procedures for optional H S I 50 Back Course Procedure Turn with Optional HSI lt 265 Back Course 085 gt REvVerse mode is used to track the front course outbound or the back course inbound to the airport The HSI Course Pointer MUST be set to the front course inbound heading 1 a Tune the navigation re ceiver to LOC frequency b Set course pointer to pub lished inbound LOC front course heading c Press NAV mode switch Autopilot
35. o flashes when the H S I NAV flag is displayed When that occurs the FAIL annunciation will illuminate 34 Pilot Selectable Intercept Angles The pilot may select an angle of intercept less than the standard 45 Simply place the heading bug on the desired heading to be used for the course intercept and push both HDG and NAV switches simultaneously HDG NAV and APR will be annunciated HDG NAV APR es OW oe oe oe TEC The selected heading will now be flown until the autopilot computes that an on course turn must be made to minimize overshoot at the point of intercept At the time the on course turn begins the HDG mode will extinguish NOTE INTERCEPT ANGLES GREATER THAN 45 USUALLY RE SULT IN SOME COURSE OVERSHOOT DEPENDING ON THE DIS TANCE FROM THE STATION AND AIRCRAFT SPEED THERE FORE ANGLES GREATER THAN 45 ARE NOT RECOMMENDED 35 Straight in Localizer Approach and Tracking Optional HSI Na A 2 265 ee mS z z z 4 N 1 a Tune navigation radio to LOC frequency b Set course pointer to published inbound LOC course heading c Press NAV mode switch 2 a Once NAV mode is established heading bug can be set to published missed approach heading l 36 b At the middle marker if a missed approach is declared disconnect the autopilot and stabilize the aircraft for the missed approach before engaging HDG and VS modes 085 gt
36. ocalizer Back Course Intercept and Tracking Standard D G With the appropriate localizer frequency selected set the heading bug to the INBOUND Back Course localizer heading and engage the REV mode to track the localizer back course inbound or front course outbound When a localizer is channeled and REV mode is selected the System 55 will automatically execute high sensitivity gain for the approach and automatically activate the APR mode REV and APR will be annunci ated If the course needle is at full scale deviation the autopilot will establish a 45 intercept angle As the aircraft approaches the localizer course the autopilot senses the closure rate and gradually smoothly shallows the intercept angle The point at which this turn begins is variable depend ing on the aircraft position and closure rate to the course However the turn will always begin between 100 full scale needle deflection and 20 of full scale During the intercept sequence the system operates in maximum gain and sensitivity to needle position and motion 90 of standard rate turn When the localizer course is intercepted and the needle is centered indi cating course capture initiation of the tracking gain program is automatic If the aircraft is equipped with the optional annunciator the REV APR and CAP modes will be annunciated 45 The high sensitivity level is maintained for about 15 seconds while wind correction angle is esta
37. ontrol wheel 60 SYSTEM 55 SPECIFICATIONS Programmer Computer Power required Weight Dimensions TSO Autopilot TSO Flight Director 14 28 VDC 3 0 Ibs 6 25 X 1 50 X 10 60 in FAA C9c FAA C52a Note Unit will operate with either 14 or 28 VDC input however internal circuit board assemblies must be set up for a specific voltage Turn Coordinator Power required Flag voltage detector operating limits Flag RPM detector operating limits Current requirements Weight Dimensions Directional Gyro Power required Minimum air flow Air filtration Autopilot pickoff Weight Dimensions Internal lights Roll Servo Power required Current requirements Weight Dimensions 14 28 VDC 9 0 VDC approx Nominal RPM less 20 0 3 Amp 1 8 lbs 3 28 X 3 28 X 5 62 in Vacuum or pressure 4 5 to 5 2 in Hg 2 2 CFM 3 micron 95 AC linear transformer 5 KHz 8 VAC pp supplied by Autopilot 3 4 Ibs 3 38 X 3 38 X 8 35 in 14 28 VDC 14 28 VDC Included in System current requirements 2 9 Ibs 3 75 X 3 75 X 7 25 in cont 61 Specifications cont Pitch Servo Trim Sensor Power required 14 28 VDC Current requirements Included in System current requirements Weight 2 9 Ibs Dimensions 3 75 X 3 75 X 7 25 in Altitude Pressure Transducer Power required 10 VDC supplied by Programmer Computer Pressure range 0 15 PSI absolute Overpressure 150 of ope
38. outlined in the text on Manual Arming of the Glideslope b Upon reaching approach altitude press the ALT mode switch c Upon capture of LOC course NAV APR ALT and GS will illuminate if all conditions for glideslope operation are met see text ref Glideslope Operation This signifies automatic arming of the Glideslope function d Upon Glideslope capture the ALT annunciation will extinguish signifying GS capture NOTE If the final approach flown locates the aircraft above the Glideslope Intercept and Track Flying the Glideslope When making an ILS ap proach be sure to follow the published procedure for the approach you have been cleared to make See text for Localizer Intercept and Tracking Approach the glideslope intercept point with the aircraft stabilized in the altitude hold ALT mode If the aircraft requires approach flaps lower the flaps to the proper position refer to FAA AFM supplement for flap use limitations At glideslope intercept lower the landing gear if applicable and adjust power for the desired descent speed and published rate of descent For best tracking results 41 make power adjustments in small smooth increments to maintain the desired rate of descent and airspeed At the missed approach point or decision height or the autopilot s minimum operating altitude whichever is higher disengage the auto pilot to execute a manual landing or a go arou
39. rating maximum Weight 0 2 Ibs System Current Requirements Approximate 14 VDC 28 VDC Average operating current 1 0 Amp 0 5 Amp Maximum current 5 0 Amp 3 0 Amp Options Remote Annunciator Power required 0 2 Amp max Weight 0 75 Ibs Dimensions 1 60 X 3 42 X 3 80 in Flight Director Steering Horizon Requires installation of Remote Annunciator Power required Vacuum or pressure 4 5 to 5 2 in Hg Weight 3 0 Ibs Dimensions 3 50 X 3 50 X 6 92 in Internal lights 14 28 VDC cont 62 Specifications cont Automatic Elevator Trim Power required 14 28 VDC Current requirements Included in System current requirements Weight Included in System weight Dimensions internal Programmer Computer Trim Servo Power required 14 28 VDC Current requirements 0 5 Amp avg 2 0 Amp max Weight 2 9 Ibs Dimensions 3 75 X 3 75 X 7 25 in Other available options not covered in this Handbook ST 119 Altitude Vertical Speed Preselector ST 180 Slaved Horizontal Situation Indicator System ST 360 Altitude Selector Alerter Yaw Damper approved for many single and twin engined aircraft 63 S TEC Corporation One S TEC Way Municipal Airport Mineral Wells Texas 76067 9236 U S A Telephone 940 325 9406 FAX 940 325 3904 1 800 USA STEC s tec com The information in this publication is subject to change without notice P N 8779 03 99 Printed in U S A 64
40. release the Control Wheel Steering CWS switch CWS and VS should annunciate Push forward on the control wheel After about 3 seconds trim should run nose up Pull control wheel aft After about 3 seconds trim should move nose down Move the aircraft control wheel in both the roll and pitch axes to overpower the autopilot servos Control motions should be smooth without looseness or free play Move Manual Trim Switch up and down The autopilot should disengage RDY will flash then annunciate steady Trim should operate in the commanded direction The Trim Switch will disengage the autopilot only when a pitch mode is engaged Re engage CWS mode and press the Trim Interrupt AP Disconnect switch The autopilot should disengage RDY will flash then annunciate steady An audible tone should be heard indicating the autopilot disconnect Retrim aircraft for takeoff and check controls for freedom of movement Be sure the autopilot and trim are disengaged NOTE IF EITHER THE MANUAL ELECTRIC TRIM OR AUTOTRIM FAILS ANY PORTION OF THE PREFLIGHT TEST TURN THE TRIM MASTER SWITCH OFF DO NOT USE THE ELECTRIC TRIM UNTIL THE FAULT IS CORRECTED WITH TRIM MASTER SWITCH OFF THE AUTOPILOT TRIM INDI CATORS AND AUDIO WARNING ARE ACTIVATED IF THE ELECTRIC TRIM FAILS OR HAS AN IN FLIGHT POWER FAILURE THE SYSTEM AUTOMATICALLY REVERTS TO OUT OF TRIM ANNUNCIATION AND AUDIO WARNING SHOULD THIS OCCUR TURN THE TRIM MASTER SWITCH OFF AND REVERT TO MANUAL T
41. t angle The point at which this turn begins is variable depend ing on the aircraft position and closure rate to the course However the turn will always begin between 100 full scale needle deflection and 20 of full scale During the intercept sequence the system operates in maximum gain and sensitivity to needle position and motion 90 of standard rate turn When the localizer course is intercepted and the needle is centered indi cating course capture initiation of the tracking gain program is automatic If the aircraft is equipped with the optional annunciator the NAV APR and CAP modes will be annunciated 33 The high sensitivity level is maintained for about 15 seconds while wind correction angle is established Turn rate maximum is then reduced to 45 standard rate The optional remote annunciator will indicate NAV APR CAP and SOFT If the course selector is within 5 of center and needle deflection is less than 10 the computer will immediately establish this sensitivity level when NAV is selected Since the heading bug is not used for the final approach segment the pilot may elect to move the heading bug to the published missed approach heading for reference and use in the heading mode should a missed ap proach be necessary The system includes a course deviation monitor If the aircraft strays off LOC centerline by 50 needle deflection the NAV annunciator flashes a warning It als
42. the NAV APR and CAP modes will be annunciated 42 The high sensitivity level is maintained for about 15 seconds while wind correction angle is established Turn rate maximum is then reduced to 45 standard rate The optional remote annunciator will indicate NAV APR CAP and SOFT If the heading bug is within 5 of center and needle deflection is less than 10 the System 55 computer will immediately establish this sensitivity level when NAV is selected Set the heading bug to the outbound procedure turn heading and select heading mode At the appropriate time in 90 increments set the head ing bug to the inbound procedure turn heading Once established on the inbound procedure turn heading follow the localizer back course intercept and tracking procedures for standard D G 43 Back Course Procedure Turn Standard DG Back Course lt 265 gt 085 gt z 2 a Set heading bug to out bound procedure turn heading b Press HDG mode switch 1 a Tune navigation receiver to LOC frequency b Set heading bug to pub lished inbound front course heading c Press NAV mode switch 310 O 130 As 4 a Set heading bug to pub lished final approach course heading b Press REV mode switch Autopilot will complete in tercept capture and tracking of localizer back course 3 a In 90 increments set heading bug to inbound pro cedure turn heading L
Download Pdf Manuals
Related Search