Manual - Bay Area Aero Club
Contents
1. 1 8 AP Display Lamps Illuminated at Power Up System Twenty 2 4 AP Display All Lamps Extinguished System Twenty 2 4 AP Display RDY for Operation eene 2 5 AP Display Turn Coordinator Failure System Twenty 2 5 AP Display Low Voltage Flag System Twenty sess 2 6 AP Display Lamps Illuminated at Power Up System Thirty 2 8 AP Display TRIM UP Lamp Extinguished System Thirty 2 8 AP Display ALT Lamp Only Illuminated System Thirty 2 9 AP Display All Lamps Extinguished System 2 9 AP Display RDY for Operation System 2 10 AP Display Turn Coordinator Failure System Thirty 2 10 AP Display Low Voltage Flag System 2 11 ALT HOLD ON OFF Switch Display Lamps Illuminated at Power Up System Thirty ALT 2 14 ALT HOLD ON OFF Switch Display UP Lamp Extinguished System Thirty ALT 2 14 ALT HOLD ON OFF Switch Display DN Lamp Extinguished System Thirty ALT 2 15 ALT HOLD ON OFF Switch Display ALT ON Lamp Extinguished System Thirty ALT 2 15 AP Display ST Mode Engaged System Twenty 121121111111 22. Fig 2 11 AP Display Turn Coordinator Failure System Thirty 2 10 3rd Ed Feb 15 07 5 INFO ES cH OR Ma gt up o Lo H TURN COORDINATOR 2 MIN Fig 2 12 AP Display Low Voltage Flag System Thirty 3rd Ed Feb 15 07 2 11 5 Page Intentionally Blank 2 12 3rd Ed Feb 15 07 5 2 1 3 System ALT Perform the actions shown in Table 2 3 For each action verify the corresponding response where applicable Table 2 3 Power Up Test System Thirty ALT ACTION RESPONSE 1 Set Yaw Damper Master Switch to OFF position if installed 2 Set Battery Master Switch to ON position 3 Set Avionics Master Switch to ON position 4 Set ALT HOLD Master Switch to ALT ON UP and DN lamps ON position illuminate on ALT HOLD ON OFF Switch display as shown in Fig 2 13 UP lamp extinguishes after 2 seconds as shown in Fig 2 14 DN lamp extinguishes after 7 seconds as shown in Fig 2 15 ALT ON lamp extinguishes after 10 seconds as shown in Fig 2 16 3rd Ed Feb 15 07 2 13 5 Fig 2 13 ALT HOLD ON OFF Switch Display ALT UP and DN Lamps Illuminated at Power Up System Thirty ALT Fig 2 14 ALT HOLD ON OFF Switch Display UP Lamp Extinguished System Thirty ALT 2 14 3rd Ed Feb 15 07 5 Fig 2 15 ALT HOLD ON OFF Switch Display DN Lamp Extinguished System Thirty ALT Fig 2 16 ALT H
3. continued from page 2 20 ACTION RESPONSE 28 Disconnect autopilot by any one of the following means a Press optional AP DISC Switch typically located on Control Wheel b Press Hold optional MODE SEL Switch typically located on Control Wheel for 3 seconds c Press Hold PUSH MODE Switch located on bezel for 3 seconds RDY lamp flashes and audible alert sounds a periodic tone while all other lamps are extinguished After 5 seconds RDY lamp stops flashing but remains illuminated and audible alert is squelched 29 Move A C Control Wheel left and right Note If a Yaw Damper is installed proceed to step 39 30 Actuate A C Rudder Pedals alternately in succession to sense their freedom of movement about yaw axis A C Control Wheels increased freedom of movement indicates that Roll Servo is disengaged then proceed to step 30 Otherwise 31 Set Yaw Damper Master Switch to ON position 32 Turn Yaw Trim Knob until A C Rudder Pedals stop 33 Attempt actuation of A C Rudder Pedals alternately in succession 2 22 A C Rudder Pedals reduced freedom of movement indicates that Yaw Servo is engaged Yaw Servo can be overridden If not set Yaw Damper Master Switch to OFF position and do not use 3rd Ed Feb 15 07 5 Table 2 4 Pre Flight Test System Twenty continued from page 2 22 ACTION RESPONSE 34 Turn Yaw Trim Knob fully COW Left A C Rudde
4. 34 3rd Ed Feb 15 07 2 2 3 System ALT 5 Prior to takeoff and with engine running perform the actions shown Table 2 6 For each action verify the corresponding response where applicable Table 2 6 Pre Flight Test System Thirty ALT continued on page 2 37 ACTION RESPONSE 1 Move A C Control Wheel forward and aft to sense its freedom of movement about pitch axis 2 Engage altitude hold mode 3 Attempt movement of A C Control Wheel forward and aft ALT ON lamp is illuminated on ALT HOLD ON OFF Switch display as shown in Fig 2 28 Control Wheels reduced freedom of movement indicates that Pitch Servo is engaged Pitch Servo can be overridden If not disconnect autopilot and do not use 4 Move A C Control Wheel as far forward as possible After 3 seconds UP lamp becomes illuminated on ALT HOLD ON OFF Switch display as shown in Fig 2 29 and audible alert sounds a steady tone After 7 seconds UP lamp flashes and audible alert becomes periodic 5 Move A C Control Wheel aft until UP lamp is extinguished Audible alert is squelched 6 Move A C Control Wheel as far aft as possible 3rd Ed Feb 15 07 After 3 seconds DN lamp becomes illuminated on ALT HOLD ON OFF Switch display as shown in Fig 2 30 and audible alert sounds a steady tone After 7 seconds DN lamp flashes and audible alert becomes periodic 2 35 5 Fi
5. DSNG SWITCH MODE SELECT SWITCH OPTIONAL Fig 1 2 System Thirty Block Diagram 1 6 3rd Ed Feb 15 07 5 MASTER ALTHOLD gt SWITCH ALT ENGIDSNG SWITCH OPTIONAL ALT HOLD ON OFF SWITCH ALT ENGIDSNG ALTITUDE PITCH COMPUTER PITCH SERVO TRANSDUCER Fig 1 3 System Thirty ALT Block Diagram 3rd Ed Feb 15 07 1 7 5 YAW YAW DAMPER MASTER YAW DAMPER YAW SERVO SWITCH OPTIONAL OPTIONAL Fig 1 4 Yaw Damper Block Diagram 1 8 3rd Ed Feb 15 07 5 SECTION 2 PRE FLIGHT PROCEDURES 3rd Ed Feb 15 07 2 1 5 Page Intentionally Blank 2 2 3rd Ed Feb 15 07 5 2 1 Power Up Test 2 1 1 System Twenty Perform the actions shown in Table 2 1 For each action verify the corresponding response where applicable Table 2 1 Power Up Test System Twenty ACTION RESPONSE 1 Set Yaw Damper Master Switch to OFF position if installed 2 Set Battery Master Switch to ON position 3 Set Avionics Master Switch to ON position 4 Set Autopilot Master Switch to ON RDY ST HD LO TRK and HI TRK position lamps illuminate on AP display as shown in Fig 2 1 for 7 seconds and then extinguish as shown in Fig 2 2 RDY lamp alone re illuminates on AP display within 3 minutes as shown in Fig 2 3 Note 1 Notes 1 Should a Turn Coordinator failure be detected the RDY lamp on the AP display wil
6. eene 2 25 Pre Flight Test System Thirty ALT esee 2 35 3rd Ed Feb 15 07 5 SECTION 1 OVERVIEW 3rd Ed Feb 15 07 1 1 5 Page Intentionally Blank 1 2 3rd Ed Feb 15 07 5 1 1 Document Organization Section 1 Overview Section 2 Pre Flight Procedures Section 3 In Flight Procedures Section 4 Operating Parameters Section 5 Glossary 1 2 Purpose This Pilot s Operating Handbook POH provides Pre Flight and In Flight operating procedures for the S TEC System Twenty Thirty Thirty ALT Autopilot AP Note This POH must be carried in the aircraft and made available to the pilot at all times It can only be used in conjunction with the Federal Aviation Administration FAA approved Aircraft Flight Manual AFM or Aircraft Flight Manual Supplement AFMS Refer to the applicable AFM or AFMS for aircraft specific information such as unique ground tests limitations and emergency procedures Note The System Twenty Thirty Thirty ALT autopilot is a tool provided to aircraft owners that serves to assist them with cockpit workload management The ability of the autopilot to provide optimum assistance and performance is directly proportional to the pilot s knowledge of its operating procedures Therefore it is highly recommended that the pilot develop a thorough understanding of the autopilot its modes and operating procedures in Visual Meteorological Conditions VMC prior t
7. lamp will extinguish and the audible alert will be squelched 3 1 6 2 System Thirty ALT If the altitude hold mode is engaged then the autopilot will provide a prompt whenever it is Hele tang to manually trim the aircraft about the pitch axis using the Elevator Trim Wheel Should the pitch servo loading exceed a preset threshold for a period of three seconds either the UP lamp or DN lamp will become illuminated as a RO to trim the aircraft in the indicated direction This is shown in Fig 3 8 In addition an audible alert will sound a steady tone If no action is taken after four more seconds then the lamp will flash and the audible alert will become periodic Once the aircraft has been sufficiently trimmed such that the pitch servo loading is below the preset threshold the lamp will extinguish and the audible alert will be squelched 3 8 3rd Ed Feb 15 07 5 TURN COORDINATOR 2 MIN 5 INFO ME Rma UP _ TURN COORDINATOR 2 MIN b TRIM DN Required Fig 3 7 AP Display Manual Trim Prompts System Thirty 3rd Ed Feb 15 07 3 9 5 a TRIM UP Required b TRIM DN Required Fig 3 8 ALT HOLD ON OFF Switch Display Manual Trim Prompts System Thirty ALT 3 10 3rd Ed Feb 15 07 5 3 2 Approach Procedures 3 2 1 Straight In LOC Approach 3 2 1 1 Heading System DG Select the LOC frequency on the Navigation Receiver Set the Heading Bug to the FRONT INBOUND LOC heading
8. lamps illuminate on AP display as shown in Fig 2 6 TRIM UP lamp extinguishes after 2 seconds as shown in Fig 2 7 RDY ST HD LO TRK HI TRK and TRIM DN lamps extinguish after 7 seconds as shown in Fig 2 8 ALT lamp extinguishes after 10 seconds as shown in Fig 2 9 RDY lamp alone re illuminates on AP display within 3 minutes as shown in Fig 2 10 Note 1 Notes 1 Should a Turn Coordinator failure be detected the RDY lamp on the AP display will not re illuminate as shown in Fig 2 11 and the autopilot will not operate 2 Should T amp B A be 30 below its rated value the Low Voltage Flag will be in view on the AP display as shown in Fig 2 12 3rd Ed Feb 15 07 2 7 5 A P SAY TURN COORDINATOR 2 MIN Fig 2 6 AP Display RDY ALT ST HD LO TRK HI TRK TRIM UP TRIM DN Lamps Illuminated at Power Up System Thirty INFO eon RMA L 4 LO HI ct TURN COORDINATOR 2 MIN Fig 2 7 AP Display TRIM UP Lamp Extinguished System Thirty 2 8 3rd Ed Feb 15 07 5 TURN COORDINATOR 2 MIN Fig 2 8 AP Display ALT Lamp Only Illuminated System Thirty TURN COORDINATOR 2 MIN Fig 2 9 AP Display All Lamps Extinguished System Thirty 3rd Ed Feb 15 07 2 9 5 5 INFOR 40 Ma e 17 TURN COORDINATOR 2 MIN Fig 2 10 AP Display RDY for Operation System Thirty TURN COORDINATOR 2 MIN
9. the point at which it is time to turn the aircraft again At that point turn the Heading Bug in two successive 90 increments to establish the aircraft on the FRONT INBOUND PROCEDURE TURN heading At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT INBOUND VOR course Engage the high track mode The autopilot will track the FRONT INBOUND VOR course A summary pictorial of this procedure is shown in Fig 3 16 3rd Ed Feb 15 07 3 19 5 255 3 20 CX 130 N N M aN RAM A Select VOR frequency Set OBS to FRONT INBOUND VOR course Set Heading Bug to FRONT OUTBOUND VOR heading Engage heading mode Turn Heading Bug to establish aircraft on FRONT OUTBOUND VOR course Set Heading Bug to FRONT OUTBOUND PROCEDURE TURN heading Turn Heading Bug in two successive 90 increments to establish aircraft on FRONT INBOUND PROCEDURE TURN heading Turn Heading Bug to establish aircraft on FRONT INBOUND VOR course Engage high track mode Track FRONT INBOUND VOR course At middle marker if missed approach is declared disconnect autopilot Stabilize aircraft Set Heading Bug to missed approach heading Engage heading mode Fig 3 15 VOR Approach with Procedure Turn DG 3rd Ed Feb 15 07 25 gt 5 7 CX gt N 4 N x x 0 x Select VOR frequency Set Cours
10. 14 LOC Approach with Procedure Turn HSI 3rd Ed Feb 15 07 5 3 2 4 VOR Approach with Procedure Turn 3 2 4 1 Heading System DG Select the VOR frequency on the Navigation Receiver Set the OBS to the FRONT INBOUND VOR course Set the Heading Bug to the FRONT OUTBOUND VOR heading and then engage the heading mode At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT OUTBOUND VOR course At the appropriate point thereafter set the Heading Bug to the FRONT OUTBOUND PROCEDURE TURN heading Hold this heading until the point at which it is time to turn the aircraft again At that point turn the Heading Bug in two successive 90 increments to establish the aircraft on the FRONT INBOUND PROCEDURE TURN heading At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT INBOUND VOR course Engage the high track mode The autopilot will track the FRONT INBOUND VOR course A summary pictorial of this procedure is shown in Fig 3 15 3 2 4 2 Heading System HSI Select the VOR frequency on the Navigation Receiver Set the Course Pointer to the FRONT INBOUND VOR course Set the Heading Bug to the FRONT OUTBOUND VOR heading and then engage the heading mode At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT OUTBOUND VOR course At the appropriate point thereafter set the Heading Bug to the FRONT OUTBOUND PROCEDURE TURN heading Hold this heading until
11. 15 Turn Yaw Trim Knob fully CW 3rd Ed Feb 15 07 Right A C Rudder moves forward Pedal slowly 2 37 5 Table 2 5 Pre Flight Test System ALT continued from page 2 37 RESPONSE 16 Turn Yaw Trim Knob CCW until A C Rudder Pedals stop 17 Set Yaw Damper Master Switch to OFF position 18 Actuate A C Rudder Pedals A C Rudder Pedals increased alternately in succession freedom of movement indicates that Yaw Servo is disengaged 19 Trim A C for takeoff 2 38 3rd Ed Feb 15 07 5 SECTION 3 IN FLIGHT PROCEDURES 3rd Ed Feb 15 07 3 1 5 Page Intentionally Blank 3 2 3rd Ed Feb 15 07 5 3 1 Normal Operating Procedures 3 1 1 Stabilizer ST Mode System Twenty Thirty Set the L R Turn Knob under its index and then engage the stabilizer mode The ST lamp alone will be illuminated as shown in Fig 3 1 to acknowledge that this mode is engaged The autopilot will hold the aircraft at wings level Turning the L R Turn Knob to the left or right of its index will cause the aircraft to turn either left or right respectively The L R Turn Knob is active only when the stabilizer mode is engaged TURN COORDINATOR 2 MIN Fig 3 1 AP Display ST Mode Engaged 3rd Ed Feb 15 07 3 3 5 3 1 2 Heading HD Mode System Twenty Thirty Set the Heading Bug to the desired heading on the compass c
12. 19 AP Display HD Mode Engaged System 2 19 AP Display LO TRK Mode Engaged System Twenty 2 21 Ed Feb 15 07 2 20 2 21 2 22 2 23 2 24 2 25 2 26 2 27 2 28 2 29 2 30 3 6 3 7 3 8 3 9 AP Display HI TRK Mode Engaged System Twenty 2 21 Display ST Mode Engaged System 2 27 AP Display HD Mode Engaged System 2 27 AP Display LO Mode Engaged System 2 29 AP Display LO Mode Engaged System Thirty 2 29 AP Display HI TRK and ALT HOLD Modes Engaged System Thirty 2 31 AP Display HI TRK and ALT HOLD ModeS Engaged TRIM UP Required System Thirty 2 32 AP Display HI TRK and ALT HOLD ModeS Engaged TRIM DN Required System Thirty 2 32 ALT HOLD ON OFF Switch Display ALT HOLD Mode Engaged System Thirty ALT 2 36 ALT HOLD ON OFF Switch Display ALT HOLD Mode Engaged TRIM UP Required System Thirty ALT 2 36 ALT HOLD ON OFF Switch Display ALT HOLD Mode Engaged TRIM DN Required System Thirty ALT 2 36 AP Display ST Mode 3 3 AP Display HD Mode Engaged eee 3 4 AP Display LO TRK Mode Engaged siisii 3 5 AP Displ
13. Ed Feb 15 07 2 19 5 Table 2 4 Pre Flight Test System Twenty continued from page 2 18 ACTION RESPONSE 18 Turn Course Pointer right until A C Control Wheel turns to the left CDI needle deflection is 2 dots left of center 19 Turn Course Pointer left until CDI A C Control Wheel stops needle is centered Note Proceed to step 28 20 Turn OBS until CDI needle is centered 21 Engage low track mode LO TRK lamp alone is illuminated on AP display as shown in Fig 2 19 22 Engage high track mode HI TRK lamp alone is illuminated on AP display as shown in Fig 2 20 23 Turn OBS until CDI needle A C Control Wheel turns to the right deflection is 2 dots right of center 24 Turn OBS until CDI needle A C Control Wheel turns to the left deflection is 2 dots left of center 25 Turn OBS until CDI needle is A C Control Wheel stops centered Note Proceed to step 28 26 Engage low track mode LO TRK lamp alone is illuminated on AP display as shown in Fig 2 19 27 Engage high track mode HI TRK lamp alone is illuminated on AP display as shown in Fig 2 20 2 20 3rd Ed Feb 15 07 5 TURN COORDINATOR 2 MIN Fig 2 19 AP Display LO TRK Mode Engaged System Twenty TURN COORDINATOR 2 MIN Fig 2 20 AP Display HI TRK Mode Engaged System Twenty 3rd Ed Feb 15 07 2 21 5 Table 2 4 Pre Flight Test System Twenty
14. Heading System 3 11 3 2 3 LOC Approach with Procedure 3 16 3 2 3 1 Heading System 3 16 3 2 3 2 Heading System 3 16 3 2 4 VOR Approach with Procedure 3 19 3 2 4 1 Heading System 3 19 3 2 4 2 Heading System 3 19 3rd Ed Feb 15 07 3 3 Yaw Damper Operation essent 3 22 duos AUTO ttti ie Rr 3 22 952 ON MOUO er ER D ek 3 22 333 Yaw Damper Trim rr ent etr rt 3 22 3 4 Autopilot DISCONMCCEH eie teen 3 23 3 4 1 System Twenty 3 23 34 2 System Thirty ALT ee e 3 23 4 Operating Parameters yan apeti pap dan panda pop onn 4 1 RONAXIS EMS iret 4 3 42 AI ooo come tiir teta hte rr a 4 3 5 5 1 3rd Ed Feb 15 07 5 Fig 1 1 1 2 1 3 1 4 List of Figures Pg System Twenty Block Diagram seen 1 5 System Thirty Block 1 6 System Thirty ALT Block 1 7 Yaw Damper Block
15. ND VOR heading Engage heading mode Turn Heading Bug to establish aircraft on FRONT INBOUND VOR course Engage high track mode Track FRONT INBOUND VOR course At middle marker if missed approach is declared disconnect autopilot Stabilize aircraft Set Heading Bug to missed approach heading Engage heading mode Fig 3 11 Straight In VOR Approach DG 3rd Ed Feb 15 07 Select VOR frequency Set Course Pointer to FRONT INBOUND VOR course Set Heading Bug to FRONT INBOUND VOR heading Engage heading mode Turn Heading Bug to establish aircraft on FRONT INBOUND VOR course Engage high track mode Track FRONT INBOUND VOR course At middle marker if missed approach is declared disconnect autopilot Stabilize aircraft Set Heading Bug to missed approach heading Engage heading mode Fig 3 12 Straight In VOR Approach HSI 3rd Ed Feb 15 07 3 15 5 3 2 3 LOC Approach with Procedure Turn 3 2 3 1 Heading System DG Select the LOC frequency on the Navigation Receiver Set the Heading Bug to the FRONT OUTBOUND LOC heading and then engage the heading mode At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT OUTBOUND LOC course At the appropriate point thereafter set the Heading Bug to the FRONT OUTBOUND PROCEDURE TURN heading Hold this heading until the point at which it is time to turn the aircraft again At that point turn t
16. OLD ON OFF Switch Display ALT ON Lamp Extinguished System Thirty ALT 3rd Ed Feb 15 07 2 15 5 Page Intentionally Blank 2 16 3rd Ed Feb 15 07 2 2 Pre Flight Test 2 2 1 System Twenty 5 Prior to takeoff and with engine running perform the actions shown in Table 2 4 For each action verify the corresponding response where applicable Table 2 4 Pre Flight Test System Twenty continued on page 2 18 ACTION RESPONSE 1 Move A C Control Wheel left and right to sense its freedom movement about roll axis 2 Set L R Turn Knob located on bezel under its index 3 Engage stabilizer mode ST lamp alone is illuminated on AP display as shown in Fig 2 17 4 Attempt movement of A C Control Wheel left and right A C Control Wheels reduced freedom of movement indicates that Roll Servo is engaged Roll Servo can be overridden If not disconnect autopilot and do not use 5 Turn L R Turn Knob to the left side of its index A C Control Wheel turns to the left 6 Turn L R Turn Knob to the right side of its index A C Control Wheel turns to the right 7 Set L R Tum Knob under its index A C Control Wheel stops Note If A C is equipped with a heading system HSI or DG then proceed to step 8 If A C is not equipped with a heading system then proceed to step 13 only if a VOR frequency can be selected Otherwise proceed to step 26 3rd Ed F
17. S TEC Pilot s Operating Handbook Twenty Thirty Thirty Alt Y COBHAM 5 Asterisk indicates pages changed added or deleted by current revision List of Effective Pages iei Retain this record in front of handbook Upon receipt of a Record of Revisions revision insert changes and complete table below Revision Number Revision Date Feb 01 00 Jun 24 02 Feb 15 07 3rd Ed Feb 15 07 i 5 Page Intentionally Blank ii 3rd Ed Feb 15 07 5 Table of Contents Sec Pg 1 M Qa 1 1 BDocumentOrganizatiori oorr rte nte re P een 1 3 1 2 AS uet o Debet tiii tes 1 3 1 3 ee 1 3 1 4 Modes Of Operalion rientro mtr 1 4 1 4 1 RollAxiS GOMWO k w koi ket ai yo tre toe e rette eb tne 1 4 1 4 2 Pitch Axis CONTON sisane gaiari 1 4 1 5 kote bio Rn ence ee 1 4 2 Pre Flight Procedures iri treten perdes 2 1 24 Power p Tesla an ai PAG ander 2 3 2 1 1 SYSI MIWENN TEE 2 3 2 42 System IMIM 2 7 2 1 3 System Thilty ALT 2 13 2 2 a a 2 17 2 2 1 System Twenty essere eisiaa 2 17 2 2 2 System cac i Ce 2 25 2283 System Thilty AL
18. and audible alert sounds a steady tone After 7 seconds TRIM DN lamp flashes and audible alert becomes periodic 34 Move A C Control Wheel forward until TRIM DN lamp is extinguished 2 30 Audible alert is squelched 3rd Ed Feb 15 07 5 Wo INF vi CHIN CZA UP LO Hi 7 ST HD TRK TURN COORDINATOR 2 MIN Fig 2 25 AP Display HI TRK and ALT HOLD Modes Engaged System Thirty 3rd Ed Feb 15 07 2 31 5 cn INFOR T 4 le HI 42 z LO TURN COORDINATOR 2 MIN Fig 2 26 AP Display HI TRK and ALT HOLD Modes Engaged TRIM UP Required System Thirty Aey INFO W cn RM gt UP o 6 LO HI TURN COORDINATOR 2 MIN Fig 2 27 AP Display HI TRK and ALT HOLD Modes Engaged TRIM DN Required System Thirty 2 32 3rd Ed Feb 15 07 5 Table 2 5 Pre Flight Test System Thirty continued from page 2 30 ACTION RESPONSE 35 Disconnect autopilot by any of the following means a Press optional AP DISC Switch typically located on Control Wheel b Press Hold optional MODE SEL Switch typically located on Control Wheel for 3 seconds c Press Hold PUSH MODE Switch located on bezel for 3 seconds 36 Move A C Control Wheel left and right RDY lamp flashes and audible alert sounds a periodic tone while all other lamps are extinguished After 5 seconds RDY lamp stops flashing but remains illuminated and a
19. and then engage the heading mode At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT INBOUND LOC course Engage the high track mode The autopilot will track the FRONT INBOUND LOC course A summary pictorial of this procedure is shown in Fig 3 9 3 2 1 2 Heading System HSI Select the LOC frequency on the Navigation Receiver For reference only set the Course Pointer to the FRONT INBOUND LOC course Set the Heading Bug to the FRONT INBOUND LOC heading and then engage the heading mode At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT INBOUND LOC course Engage the high track mode The autopilot will track the FRONT INBOUND LOC course A summary pictorial of this procedure is shown in Fig 3 10 3 2 2 Straight In VOR Approach 3 2 2 1 Heading System DG Select the VOR frequency on the Navigation Receiver Set the OBS to the FRONT INBOUND VOR course Set the Heading Bug to the FRONT INBOUND VOR heading and then engage the heading mode At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT INBOUND VOR course Engage the high track mode The autopilot will track the FRONT INBOUND VOR course summary pictorial of this procedure is shown in Fig 3 11 3 2 2 2 Heading System HSI Select the VOR frequency on the Navigation Receiver Set the Course Pointer to the FRONT INBOUND VOR course Set the Heading Bug to the FRONT INBOUND VOR heading an
20. ard HSI or DG and then engage the heading mode The HD lamp alone will be illuminated as shown in Fig 3 2 to acknowledge that this mode is engaged The autopilot will turn the aircraft onto the selected heading and hold it A new heading can be subsequently selected by setting the Heading Bug to it TURN COORDINATOR 2 MIN Fig 3 2 AP Display HD Mode Engaged 3 4 3rd Ed Feb 15 07 5 3 1 3 Low Track LO Mode System Twenty Thirty Select the VOR frequency on the Navigation Receiver Maneuver the aircraft to within 1 CDI needle width and 10 heading of the selected course Engage the low track mode The LO TRK lamp alone will be illuminated as shown in Fig 3 3 to acknowledge that this mode is engaged The autopilot will track the selected course with minimum authority thereby ignoring short term CDI needle deflections excursions to inhibit aircraft scalloping during VOR station passage TURN COORDINATOR 2 MIN Fig 3 3 AP Display LO TRK Mode Engaged 3rd Ed Feb 15 07 3 5 5 3 1 4 High Track Mode System Twenty Thirty 3 1 4 1 LOC Course Tracking Select the LOC frequency on the Navigation Receiver Maneuver the aircraft to within 1 CDI needle width and 10 heading of the selected course Engage the high track mode The HI TRK lamp alone will be illuminated as shown in Fig 3 4 to acknowledge that this mode is engaged The autopilot will track the selected course wi
21. ay HI TRK Mode 3 6 AP Display ST and ALT HOLD Modes Engaged System Thirty 3 7 ALT HOLD ON OFF Switch Display ALT HOLD Mode Engaged System Thirty ALT 3 8 AP Display Manual Trim Prompts System 3 9 AP Display Manual Trim Prompts System Thirty ALT 3 10 Straight In LOC Approach 3 12 Straight In LOC Approach US eese 3 13 Straight In VOR Approach DG ener 3 14 Straight In VOR Approach HS isisisi nnn 3 15 LOC Approach with Procedure Turn 3 17 3rd Ed Feb 15 07 vii 5 3 14 3 15 3 16 3 17 3 18 viii LOC Approach with Procedure Turn 3 18 VOR Approach with Procedure Turn 3 20 VOR Approach with Procedure Turn 3 21 Yaw Damper Master 3 22 Yaw Damper Trim 2 erint teneas 3 22 List of Tables Pg Power Up Test System 2 3 Power Up Test System 2 7 Power Up Test System Thirty 2 13 Pre Flight Test System Twenty esee 2 17 Pre Flight Test System Thirty
22. d then engage the heading mode At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT INBOUND VOR course Engage the high track mode The autopilot will track the FRONT INBOUND VOR course A summary pictorial of this procedure is shown in Fig 3 12 3rd Ed Feb 15 07 3 11 4 265 gt 3 12 Select LOC frequency Set Heading Bug to FRONT INBOUND LOC heading Engage heading mode Turn Heading Bug to establish aircraft on FRONT INBOUND LOC course Engage high track mode Track FRONT INBOUND LOC course At middle marker if missed approach is declared disconnect autopilot Stabilize aircraft Set Heading Bug to missed approach heading Engage heading mode Fig 3 9 Straight In LOC Approach DG 3rd Ed Feb 15 07 Select LOC frequency Set Course Pointer to FRONT INBOUND LOC course reference only Set Heading Bug to FRONT INBOUND LOC heading Engage heading mode Turn Heading Bug to establish aircraft on FRONT INBOUND LOC course Engage high track mode Track FRONT INBOUND LOC course At middle marker if missed approach is declared disconnect autopilot Stabilize aircraft Set Heading Bug to missed approach heading Engage heading mode Fig 3 10 Straight In LOC Approach HSI 3rd Ed Feb 15 07 3 13 4 265 gt 3 14 Select VOR frequency Set OBS to FRONT INBOUND VOR course Set Heading Bug to FRONT INBOU
23. e Pointer to FRONT INBOUND VOR course Set Heading Bug to FRONT OUTBOUND VOR heading Engage heading mode Turn Heading Bug to establish aircraft on FRONT OUTBOUND VOR course Set Heading Bug to FRONT OUTBOUND PROCEDURE TURN heading Turn Heading Bug in two successive 90 increments to establish aircraft on FRONT INBOUND PROCEDURE TURN heading Turn Heading Bug to establish aircraft on FRONT INBOUND VOR course Engage high track mode Track FRONT INBOUND VOR course At middle marker if missed approach is declared disconnect autopilot Stabilize aircraft Set Heading Bug to missed approach heading Engage heading mode Fig 3 16 VOR Approach with Procedure Turn HSI 3rd Ed Feb 15 07 3 21 5 3 3 Yaw Damper Operation The optional Yaw Damper serves to dampen excessive adverse yaw It operates in either the AUTO mode or ON mode depending upon the position of the Yaw Damper Master Switch shown in Fig 3 17 AUTO gt ON Fig 3 17 Yaw Damper Master Switch The Yaw Trim Knob shown in Fig 3 18 is used to center the slip skid ball when the yaw servo is engaged Fig 3 18 Yaw Trim Knob 3 3 1 AUTO Mode With the Yaw Damper Master Switch in the AUTO position the yaw servo will become automatically engaged whenever a roll mode ST HD LO TRK HI TRK is engaged 3 3 2 ON Mode With the Yaw Damper Master Switch in the ON position the yaw servo will be en
24. eb 15 07 2 17 5 Table 2 4 Pre Flight Test System Twenty continued from page 2 17 ACTION RESPONSE 8 Set Heading Bug under Lubber Line 9 Engage heading mode HD lamp alone is illuminated on AP display as shown in Fig 2 18 10 Turn Heading Bug to the left side of Lubber Line A C Control Wheel turns to the left 11 Turn Heading Bug to the right side of Lubber Line A C Control Wheel turns to the right 12 Set Heading Bug under Lubber Line A C Control Wheel stops Note If it is not possible to select a local VOR frequency on Navigation Receiver then proceed to step 26 Otherwise proceed to step 13 13 Select local VOR frequency on Navigation Receiver Note Proceed to either step 14 HSI or step 20 DG 14 Turn Course Pointer until CDI needle is centered 15 Engage low track mode LO TRK lamp alone is illuminated on AP display as shown in Fig 2 19 16 Engage high track mode HI TRK lamp alone is illuminated on AP display as shown in Fig 2 20 17 Turn Course Pointer left until CDI needle deflection is 2 dots right of center 2 18 A C Control Wheel turns to the right 3rd Ed Feb 15 07 5 TURN COORDINATOR 2 MIN Fig 2 17 AP Display ST Mode Engaged System Twenty cH INFOR gl e M r TURN COORDINATOR 2 Fig 2 18 AP Display HD Mode Engaged System Twenty 3rd
25. ed after a roll mode ST HD LO TRK HI TRK has been engaged 3rd Ed Feb 15 07 4 3 5 Page Intentionally Blank 4 4 3rd Ed Feb 15 07 5 SECTION 5 GLOSSARY 3rd Ed Feb 15 07 5 1 5 Page Intentionally Blank 5 2 3rd Ed Feb 15 07 Term ALT AP CDI CW CCW DG DISC DN DSNG ENG FAA GPS HD HI TRK HSI IFR LO TRK LOG MAP OBS PN POH RDY ST UP VMC VOR 3rd Ed Feb 15 07 5 Meaning Aircraft Altitude Autopilot Course Deviation Indication Clockwise Counter Clockwise Directional Gyro Disconnect Down Disengage Engage Federal Aviation Administration Feet Global Positioning System Heading High Track Horizontal Situation Indicator Instrument Flight Rules Low Track Localizer Missed Approach Point Omnibearing Selector Part Number Pilot s Operating Handbook Ready Stabilizer Visual Meteorological Conditions Very High Frequency Omnidirectional Radio Range 5 Page Intentionally Blank 5 4 3rd Ed Feb 15 07 S TEC Information contained in this document is subject to change without notice 2007 S TEC All rights reserved Printed in the United States of America S TEC and the S TEC logo are registered trademarks of S TEC Notice Contact S TEC Customer Support at 800 872 7832 fora Return Material Authorization RMA number prior to the return of any component for any reason One 5 Way Municipal A
26. eft until CDI needle deflection is 2 dots right of center 2 26 A C Control Wheel turns to the right 3rd Ed Feb 15 07 5 TURN COORDINATOR 2 MIN Fig 2 21 AP Display ST Mode Engaged System Thirty TURN COORDINATOR 2 MIN Fig 2 22 AP Display HD Mode Engaged System Thirty 3rd Ed Feb 15 07 2 27 5 Table 2 5 Pre Flight Test System Thirty continued from page 2 26 ACTION RESPONSE 18 Course Pointer right until CDI needle deflection is 2 dots left of center A C Control Wheel turns to the left 19 Turn Course Pointer left until CDI needle is centered A C Control Wheel stops Note Proceed to step 28 20 Turn OBS until CDI needle is centered 21 Engage low track mode LO TRK lamp alone is illuminated on AP display as shown in Fig 2 23 22 Engage high track mode 23 Turn OBS until CDI needle deflection is 2 dots right of center HI TRK lamp alone is illuminated on AP display as shown in Fig 2 24 A C Control Wheel turns to the right 24 OBS until CDI needle deflection is 2 dots left of center A C Control Wheel turns to the left 25 Turn OBS until CDI needle is centered A C Control Wheel stops Note Proceed to step 28 26 Engage low track mode LO TRK lamp alone is illuminated on AP display as shown in Fig 2 23 27 Engage high track mode HI TRK lamp alone is illuminated
27. g 2 28 ALT HOLD ON OFF Switch Display ALT HOLD Mode Engaged System Thirty ALT Fig 2 29 ALT HOLD ON OFF Switch Display ALT HOLD Mode Engaged TRIM UP Required System Thirty ALT Fig 2 30 ALT HOLD ON OFF Switch Display ALT HOLD Mode Engaged TRIM DN Required System Thirty ALT 2 36 3rd Ed Feb 15 07 5 Table 2 6 Pre Flight Test System ALT continued from page 2 35 ACTION RESPONSE 7 Move A C Control Wheel forward until DN lamp is extinguished Audible alert is squelched 8 Disengage altitude hold mode ALT ON lamp is extinguished on ALT HOLD ON OFF Switch display 9 Move A C Control Wheel forward and aft A C Contro Wheels increased freedom of movement indicates that Pitch Servo is disengaged Note If a Yaw Damper is installed then proceed to step 10 Otherwise proceed to step 19 10 Actuate A C Rudder Pedals alternately in succession to sense their freedom of movement about yaw axis 11 Set Yaw Damper Master Switch to ON position 12 Turn Yaw Trim Knob until A C Rudder Pedals stop 13 Attempt actuation of A C Rudder Pedals alternately in succession 14 Turn Yaw Trim Knob fully CCW A C Rudder Pedals reduced freedom of movement indicates that Yaw Servo is engaged Yaw Servo can be overridden If not set Yaw Damper Master Switch to OFF position and do not use Left A C Rudder Pedal slowly moves forward
28. gaged at all times entirely independent of autopilot operation 3 3 3 Yaw Damper Trim With the yaw servo engaged rotate the Yaw Trim Knob to center the slip skid ball 3 22 3rd Ed Feb 15 07 5 3 4 Autopilot Disconnect 3 4 1 System Twenty Thirty The autopilot can be disconnected by any of the following means 1 Press optional AP DISC Switch typically located on Control Wheel 2 Press Hold optional MODE SEL Switch typically located on Control Wheel for 3 seconds 3 Press Hold PUSH MODE Switch located on bezel for 3 seconds 4 Set Autopilot Master Switch to OFF position 5 Pull Autopilot Circuit Breaker 3 4 2 System Thirty ALT The autopilot can be disconnected by any of the following means 1 Press optional ALT ENG DSNG Switch typically located on Control Wheel 2 Press ALT HOLD ON OFF Switch located on instrument panel 3 Set ALT HOLD Master Switch to OFF position 4 Pull ALT HOLD Circuit Breaker 3rd Ed Feb 15 07 3 23 5 Page Intentionally Blank 3 24 3rd Ed Feb 15 07 5 SECTION 4 OPERATING PARAMETERS 3rd Ed Feb 15 07 4 1 5 Page Intentionally Blank 4 2 3rd Ed Feb 15 07 5 4 1 Roll Axis Limits Turn Rate Piston A C 90 Standard Rate Turn Turboprop A C 75 Standard Rate Turn 4 2 Pitch Axis Limits Altitude 32 000 FT Vertical Force Due to Acceleration 0 60 g Modes For the System Thirty the pitch mode ALT HOLD can only be engag
29. ged The autopilot will hold the aircraft at its current captured absolute pressure altitude ES cH ORM r UP LO HI TURN COORDINATOR 2 MIN Fig 3 5 AP Display ST and ALT HOLD Modes Engaged System Thirty 3rd Ed Feb 15 07 3 7 5 3 1 5 2 System Thirty ALT Maneuver the aircraft to the desired altitude Engage the altitude hold mode The ALT ON lamp will be illuminated as shown in Fig 3 6 to acknowledge that this mode is engaged The autopilot will hold the aircraft at its current captured absolute pressure altitude Fig 3 6 ALT HOLD ON OFF Switch Display ALT HOLD Mode Engaged System Thirty ALT 3 1 6 Manual Elevator Trim Prompts System Thirty Thirty ALT 3 1 6 1 System Thirty If the altitude hold mode is engaged then the autopilot will provide a prompt whenever it is Hele tsa to manually trim the aircraft about the pitch axis using the Elevator Trim Wheel Should the pitch servo loading exceed a preset threshold for a period of three seconds either the TRIM UP lamp or TRIM DN lamp will become illuminated as a prompt to trim the aircraft in the indicated direction This is shown in Fig 3 7 In addition an audible alert will sound a steady tone If no action is taken after four more seconds then the lamp will flash and the audible alert will become periodic Once the aircraft has been sufficiently trimmed such that the pitch servo loading is below the preset threshold the
30. he Heading Bug in two successive 90 increments to establish the aircraft on the FRONT INBOUND PROCEDURE TURN heading At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT INBOUND LOC course Engage the high track mode The autopilot will track the FRONT INBOUND LOC course A summary pictorial of this procedure is shown in Fig 3 13 3 2 3 2 Heading System HSI Select the LOC frequency on the Navigation Receiver For reference only set the Course Pointer to the FRONT INBOUND LOC course Set the Heading Bug to the FRONT OUTBOUND LOC heading and then engage the heading mode At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT OUTBOUND LOC course At the appropriate point thereafter set the Heading Bug to the FRONT OUTBOUND PROCEDURE TURN heading Hold this heading until the point at which it is time to turn the aircraft again At that point turn the Heading Bug in two successive 90 increments to establish the aircraft on the FRONT INBOUND PROCEDURE TURN heading At the appropriate point turn the Heading Bug to establish the aircraft on the FRONT INBOUND LOC course Engage the high track mode The autopilot will track the FRONT INBOUND LOC course A summary pictorial of this procedure is shown in Fig 3 14 3 16 3rd Ed Feb 15 07 265 5 0 085 gt x Select LOC frequency Set Heading Bug to FRONT OUTBOUND LOC heading E
31. irport Mineral Wells TX 76067 9236 Tel 800 872 7832 Fax 940 325 3904 www s tec com www cobham com 5 PN 8777
32. l not re illuminate as shown in Fig 2 4 and the autopilot will not operate 2 Should T amp B A be 30 below its rated value the Low Voltage Flag will be in view on the AP display as shown in Fig 2 5 3rd Ed Feb 15 07 2 3 5 TURN COORDINATOR 2 MIN Fig 2 1 AP Display RDY ST HD LO TRK HI TRK Lamps Illuminated at Power Up System Twenty TURN COORDINATOR 2 MIN Fig 2 2 AP Display All Lamps Extinguished System Twenty 2 4 3rd Ed Feb 15 07 5 ala yy TURN COORDINATOR 2 MIN Fig 2 3 AP Display RDY for Operation System Twenty 5 INF Ven 5 ORM UP 4 HI W ST HD TURN COORDINATOR 2 MIN Fig 2 4 AP Display Turn Coordinator Failure System Twenty 3rd Ed Feb 15 07 2 5 5 INFO ve H ORM gt UP UP Lo HI WR TRIM TURN COORDINATOR 2 MIN Fig 2 5 AP Display Low Voltage Flag System Twenty 2 6 3rd Ed Feb 15 07 5 2 1 2 System Perform the actions shown in Table 2 2 For each action verify the corresponding response where applicable Table 2 2 Power Up Test System Thirty ACTION 1 Set Yaw Damper Master Switch to OFF position if installed 2 Set Battery Master Switch to ON position 3 Set Avionics Master Switch to ON position 4 Set Autopilot Master Switch to ON RDY ALT ST HD LO TRK HI TRK position TRIM UP and TRIM DN
33. ngage heading mode Turn Heading Bug to establish aircraft on FRONT OUTBOUND LOC course Set Heading Bug to FRONT OUTBOUND PROCEDURE TURN heading Turn Heading Bug in two successive 90 increments to establish aircraft on FRONT INBOUND PROCEDURE TURN heading Turn Heading Bug to establish aircraft on FRONT INBOUND LOC course Engage high track mode Track FRONT INBOUND LOC course At middle marker if missed approach is declared disconnect autopilot Stabilize aircraft Set Heading Bug to missed approach heading Engage heading mode Fig 3 13 LOC Approach with Procedure Turn DG 3rd Ed Feb 15 07 3 17 5 25 gt 3 18 CY E 130 N NS 1 SIN A N x Select LOC frequency Set Course Pointer to FRONT INBOUND LOC course reference only Set Heading Bug to FRONT OUTBOUND LOC heading Engage heading mode Turn Heading Bug to establish aircraft on FRONT OUTBOUND LOC course Set Heading Bug to FRONT OUTBOUND PROCEDURE TURN heading Turn Heading Bug in two successive 90 increments to establish aircraft on FRONT INBOUND PROCEDURE TURN heading Turn Heading Bug to establish aircraft on FRONT INBOUND LOC course Engage high track mode Track FRONT INBOUND LOC course At middle marker if missed approach is declared disconnect autopilot Stabilize aircraft Set Heading Bug to missed approach heading Engage heading mode Fig 3
34. o using it under Instrument Flight Rules IFR 1 3 General Control Theory The System Twenty Thirty Thirty ALT is a rate based autopilot When in control of the roll axis the autopilot senses turn rate along with the non rate quantities of heading error and course deviation indication When in control of the pitch axis the autopilot senses acceleration along with the non rate quantity of altitude These sensed data provide feedback to the autopilot which processes them in order to control the aircraft through the use of mechanisms coupled to the control system The roll servo is typically coupled to the ailerons and the pitch servo is coupled to the elevator The System Twenty controls only the roll axis The System Thirty controls both the roll axis and pitch axis Activation of roll axis control must always precede activation of pitch axis control The System Thirty ALT controls only the pitch axis 3rd Ed Feb 15 07 1 8 5 optional Yaw Damper senses excessive adverse yaw about the yaw axis and responds by driving the yaw servo in the proper direction to provide damping The yaw servo is coupled to the rudder 1 4 Modes of Operation 1 4 1 Roll Axis Control Each press release of the optional MODE SEL Switch typically located on the Control Wheel or PUSH MODE Switch located on the bezel successively engages the roll modes below Stabilizer ST Mode Used to Hold Wings Level Heading HD Mode Used to Tu
35. on AP display as shown in Fig 2 24 2 28 3rd Ed Feb 15 07 5 2 gl cH INFOR iy gt 7 UP e LO HI TURN COORDINATOR 2 MIN Fig 2 23 AP Display LO TRK Mode Engaged System Thirty INF ve Rma UP o LO ST HD TURN COORDINATOR 2 MIN Fig 2 24 AP Display HI TRK Mode Engaged System Thirty 3rd Ed Feb 15 07 2 29 5 Table 2 5 Pre Flight Test System Thirty continued from page 2 28 ACTION RESPONSE 28 Move A C Control Wheel forward and aft to sense its freedom of movement about pitch axis 29 Engage altitude hold mode ALT lamp is iluminated AP display as shown in Fig 2 25 30 Attempt movement of AC Control Wheel forward and aft A C Control Wheels reduced freedom of movement indicates that Pitch Servo is engaged Pitch Servo can be overridden If not disconnect autopilot and do not use 31 Move A C Control Wheel as far forward as possible After 3 seconds TRIM UP lamp becomes illuminated on AP display as shown in Fig 2 26 and audible alert sounds a steady tone After 7 seconds TRIM UP lamp flashes and audible alert becomes periodic 32 Move A C Control Wheel aft until TRIM UP lamp is extinguished Audible alert is squelched 33 Move A C Control Wheel as far aft as possible After 3 seconds TRIM DN lamp becomes illuminated on AP display as shown in Fig 2 27
36. r Pedal slowly moves forward 35 Turn Yaw Trim Knob fully CW Right A C Rudder Pedal slowly moves forward 36 Turn Yaw Trim Knob CCW until A C Rudder Pedals stop 37 Set Yaw Damper Master Switch to OFF position 38 Actuate A C Rudder Pedals A C Rudder Pedals increased alternately in succession freedom of movement indicates that Yaw Servo is disengaged 39 Trim A C fortakeoff 3rd Ed Feb 15 07 2 23 5 Page Intentionally Blank 2 24 3rd Ed Feb 15 07 2 2 2 System 5 Prior to takeoff and with engine running perform the actions shown in Table 2 5 For each action verify the corresponding response where applicable Table 2 5 Pre Flight Test System Thirty continued on page 2 26 ACTION RESPONSE 1 Move A C Control Wheel left right to sense its freedom of movement about roll axis 2 Set L R Turn Knob located on bezel under its index 3 Engage stabilizer mode ST lamp alone is illuminated on AP display as shown in Fig 2 21 4 Attempt movement of A C Control Wheel left and right Control Wheels reduced freedom of movement indicates that Roll Servo is engaged Roll Servo can be overridden If not disconnect autopilot and do not use 5 Turn L R Turn Knob to the left side of its index A C Control Wheel turns to the left 6 Turn L R Turn Knob to the right side of i
37. rn onto a Selected Heading and Hold it Low Track LO TRK Mode Used to Track a VOR Course High Track HI TRK Mode Used to Track a LOC Course Note A heading system HSI or DG is optional If the aircraft is equipped with a heading system then the heading mode can be engaged Otherwise the heading mode cannot be engaged i e it will be skipped over 1 4 2 Pitch Axis Control Each press of the ALT ENG DSNG Switch typically located on the Control Wheel optional for System Thirty ALT only or ALT HOLD ON OFF Switch located on the instrument panel System Thirty ALT only successively engages and disengages the single pitch mode below Altitude Hold ALT HOLD Mode Used to Hold Altitude 1 5 Block Diagrams The System Twenty Block Diagram is shown in Fig 1 1 The System Thirty Block Diagram is shown in Fig 1 2 The System Thirty ALT Block Diagram is shown in Fig 1 3 The Yaw Damper Block Diagram is shown in Fig 1 4 1 4 3rd Ed Feb 15 07 5 TURN COORDINATOR ROLL COMPUTER BATTERY MASTER SWITCH AUTOPILOT MASTER SWITCH ROLL SERVO DISCONNECT SWITCH OPTIONAL MODE SELECT SWITCH OPTIONAL HSI Fig 1 1 System Twenty Block Diagram 3rd Ed Feb 15 07 1 5 5 TURN COORDINATOR ROLL COMPUTER PITCH BATTERY T COMPUTER SWITCH AUTOPILOT Te MASTER SWITCH ALTITUDE TRANSDUCER ROLL SERVO DISCONNECT SWITCH OPTIONAL ALT ENG
38. th maximum authority 3 1 4 2 GPS Course Tracking Program a predefined course into the GPS Navigation Receiver comprised of course segments connected by waypoints Maneuver the aircraft to within 1 CDI needle width and 10 heading of each successive course segment Engage the high track mode The HI TRK lamp alone will be illuminated as shown in Fig 3 4 to acknowledge that this mode is engaged The autopilot will track the selected course segment with maximum authority 3 1 4 3 VOR Course Tracking Select the VOR frequency on the Navigation Receiver Maneuver the aircraft to within 1 CDI needle width and 10 heading of the selected course Engage the high track mode The HI TRK lamp alone will be illuminated as shown in Fig 3 4 to acknowledge that this mode is engaged The autopilot will track the selected course with maximum authority As a result however the aircraft may exhibit scalloping during VOR station passage cH INFO 99 ORM 2 UP Le WIC TURN COORDINATOR 2 MIN Fig 3 4 AP Display HI TRK Mode Engaged 3 6 3rd Ed Feb 15 07 5 3 1 5 Altitude Hold ALT HOLD Mode System Thirty Thirty ALT 3 1 5 1 System Thirty The altitude hold mode can only be engaged if a roll mode ST HD LO TRK HI TRK is already engaged Maneuver the aircraft to the desired altitude Engage the altitude hold mode The ALT lamp will be illuminated as shown in Fig 3 5 to acknowledge that this mode is enga
39. ts index A C Control Wheel turns to the right 7 Set L R Turn Knob under its index A C Control Wheel stops Note If A C is equipped with a heading system HSI or DG then proceed to step 8 If A C is not equipped with a heading system then proceed to step 13 only if a VOR frequency can be selected Otherwise proceed to step 26 3rd Ed Feb 15 07 2 25 5 Table 2 5 Pre Flight Test System Thirty continued from page 2 25 ACTION 8 Set Heading Bug under Lubber Line 9 Engage heading mode HD lamp alone is illuminated on AP display as shown in Fig 2 22 10 Turn Heading Bug to the left side of Lubber Line A C Control Wheel turns to the left 11 Turn Heading Bug to the right side of Lubber Line A C Control Wheel turns to the right 12 Set Heading Bug under Lubber Line A C Control Wheel stops Note If it is not possible to select a local VOR frequency on Navigation Receiver then proceed to step 26 Otherwise proceed to step 13 13 Select local VOR frequency on Navigation Receiver Note Proceed to either step 14 HSI or step 20 DG 14 Turn Course Pointer until CDI needle is centered 15 Engage low track mode LO TRK lamp alone is illuminated on AP display as shown in Fig 2 23 16 Engage high track mode HI TRK lamp alone is illuminated on AP display as shown in Fig 2 24 17 Turn Course Pointer l
40. udible alert is squelched A C Contro Wheels increased freedom of movement indicates that Roll Servo is disengaged 37 Move A C Control Wheel forward and aft Note If a Yaw Damper is installed proceed to step 47 38 Actuate A C Rudder Pedals alternately in succession to sense their freedom of movement about yaw axis Control Wheels increased freedom of movement indicates that Pitch Servo is disengaged then proceed to step 38 Otherwise 39 Set Yaw Damper Master Switch to ON position 40 Turn Yaw Trim Knob until A C Rudder Pedals stop 3rd Ed Feb 15 07 2 33 5 Table 2 5 Pre Flight Test System Thirty continued from page 2 33 RESPONSE 41 Attempt actuation of A C Rudder A C Rudder Pedals reduced freedom Pedals alternately in succession of movement indicates that Yaw Servo is engaged Yaw Servo can be overridden If not set Yaw Damper Master Switch to OFF position and do not use 42 Turn Yaw Trim Knob fully CCW Left A C Rudder Pedal slowly moves forward 43 Turn Yaw Trim Knob fully CW Right A C Rudder Pedal slowly moves forward 44 Turn Yaw Trim Knob CCW until A C Rudder Pedals stop 45 Set Yaw Damper Master Switch to OFF position 46 Actuate A C Rudder Pedals A C Rudder Pedals increased alternately in succession freedom of movement indicates that Yaw Servo is disengaged 47 Trim A C for takeoff 2
41. zaawan ian AAA 2 35 3 In Elighiti Procedures dines hee 3 1 3 1 Normal Operating 3 3 3 1 1 Stabilizer ST Mode System Twenty Thirty 3 3 3 1 2 Heading HD Mode System Twenty Thirty 3 4 3 1 3 Low Track LO TRK Mode System Twenty Thirty 3 5 3rd Ed Feb 15 07 iii 5 3 2 3 1 4 High Track HI TRK Mode System Twenty Thirty 3 6 3 1 4 1 LOC Course 3 6 3 1 4 2 GPS Course 3 6 3 1 4 3 VOR Course 3 6 3 1 5 Altitude Hold ALT HOLD Mode System Thirty Thirty ALT 3 7 31 51 Systemi Thiltyc it tbe iss 3 7 3 1 5 2 System Thirty 3 8 3 1 6 Manual Elevator Trim Prompts System Thirty Thirty ALT 3 8 3 1 6 1 System Thirty ecciesie entere 3 8 3 1 6 2 System Thirty ALT esses 3 8 Approach Procedures eene 3 11 3 2 1 Straight In LOC Approach eee 3 11 3 2 1 1 Heading System 3 11 3 2 1 2 Heading System 3 11 3 2 2 Straight In VOR 2 3 11 3 2 2 1 Heading System 3 11 3 2 2 2
Download Pdf Manuals
Related Search