MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

CHAPTER

22
AUTO FLIGHT
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

CHAPTER 22 AUTO FLIGHT

LIST OF EFFECTIVE PAGES

CH-SE-SU C PAGE DATE CH-SE-SU C PAGE DATE

Title Page
List of Effective R 1～2 Nov 20/2015
Pages

Table of Contents 1 Nov 20/2013

2 Nov 20/2013
22-10-00 1 Feb 20/2013
2 Feb 20/2013
22-11-00 1 Feb 20/2013
2 Feb 20/2013
R 3 Nov 20/2015
R 4 Nov 20/2015
5 Feb 20/2013
6 Feb 20/2013
7 Feb 20/2013
R 8 Nov 20/2015
R 9 Nov 20/2015
R 10 Nov 20/2015
11 Feb 20/2013
12 Feb 20/2013

N= new
R= revised 22-LIST OF EFFECTIVE PAGES
D= deleted Page 1
Nov 20/2015
TP211A01-NAC
MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

THIS PAGE IS INTENTIONALLY LEFT BLANK

22-LIST OF EFFECTIVE PAGES

Page 2
Nov 20/2015
TP211A01-NAC
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

CHAPTER 22 AUTO FLIGHT

TABLE OF CONTENTS

SUBJECT CH-SE-SU PAGE EFF

AUTOPILOT 22-10-00
General 1 ALL
System description 1 ALL
Controls and indicators 1 ALL
AUTOPILOT AND SERVO 22-11-00
General 1 ALL
System description 1 ALL
System operation 4 ALL
Controls and indicators 7 ALL

22- TABLE OF CONTENTS

Page 1
Nov 20/2013
TP211A01-NAC
MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

THIS PAGE IS INTENTIONALLY LEFT BLANK

22- TABLE OF CONTENTS

Page 2
Nov 20/2013
TP211A01-NAC
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

AUTOPILOT

1. General

The autopilot system helps the pilot control the aircraft.

2. System description

A. Functions

The autopilot system is a full-digital dual-channel system providing the function of

automatic flight in three axes of pitch, roll and yaw and the function of pitch trim as well as
the function of fail safe protection.

B. Operation principle

Ref. Fig 001.

The autopilot interlinks with the AHS, ADS and electronic flight instruments by the data
bus.

AHS

Autopilot
Air data system

Electronic flight
instrument

Figure 1. Autopilot system - Schematic diagram

C. compose

The autopilot system includes 1 set of autopilots.

3. Controls and indicators

The autopilot is controlled by the Mode Select Panel and Autopilot Panel.
The operation conditions of the autopilot are displayed on the EADI of the electronic flight

EFF：ALL 22-10-00
Page 1
Feb 20/2013
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

instrument system.

EFF：ALL 22-10-00
Page 2
Feb 20/2013
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

AUTOPILOT AND SERVO

1. General

The autopilot system is a full-digital dual-channel system providing the function of automatic
flight in three axes of pitch, roll and yaw and the function of pitch trim as well as the function of
fail safe protection.

2. System description

A. Function

The autopilot and servo system has the following functions:

- Pitch control
- Roll control
- Yaw control
- Auto-TRIM
- Flight directing
- Attitude hold
- Automatic-disengagement
- Advisory for automatic-disengagement.

B. Operation principle

Ref. Fig 001.

The autopilot processes the commands from the aircraft sensor system (AHS, ADS, FMS)
and the left/right pilot or the output signals from the mode select panel. It does a full
automatic pilot function and flight direction function for the pilot. The autopilot system
obeys the rules of the Class I automatic approach.

C. Installation location
Installation locations of the autopilot system are shown in Table 001.

EFF：ALL 22-11-00
Page 1
Feb 20/2013
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

Figure001 Autopilot System - Schematic diagram

EFF：ALL 22-11-00
Page 2
Feb 20/2013
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

Table 001 Components of Autopilot system – Location

SN Description Installation location Zone /Access PNL

1 Left side of pilot glare

Mode select panel
shield

2 Right side of pilot glare

Mode select panel
shield

3 Autopilot panel Central console

4 Electronic equipment
FCC
rack

5 Rudder Servo FR 43 RH

6 Elevator servo FR 43 RH

7 Center Wing Rear Spar

Aileron Servo
LH

8 Trim servo LH of FR 45 thru FR46

D. Components

The autopilot system consists of the FCC, the mode select panel, the autopilot panel, the
flight control servo and the servo cable.

(1) Flight control computer

The flight control computer provides the calculations of flight direction and the
AP/yaw damper for the pilot and copilot to control the elevator, the aileron, the rudder
and the elevator trim tab. The digital amplifier with dual channels and two servos
provides a fail-safe protection for the attitude control of three-axes and elevator trim.
Two independent calculation channels ensure that the flight direction function of the
left pilot is isolated from the right pilot. Two different processors and the languages
are used in each channel so as to improve the different redundancy monitoring
technique.
(2) Mode select panel
The select buttons of the flight direction modes are installed on the mode select
panel. The compatibility for these modes are monitored by the flight control computer
and verified by the light for indication on the selected mode buttons.
(3) Autopilot panel
The autopilot panel includes:
- The autopilot engaged/disengaged bar
- The yaw damper engaged/disengaged bar
- Autopilot transfer and turbulence mode switch

EFF：ALL 22-11-00
Page 3
Nov 20/2015
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

- Pitch control wheel/ Steering knob

(4) Flight control servo
The servo and the servo support are used to put the main control surface and
elevator trim tab in position. The flight control servo is an accurate drive mechanism.
The servo has a DC motor, a velocity measuring motor, a gear chain and a meshing
clutch. The servo support has a super-control safety slip clutch and a drum wheel
(chain wheel), which connects the servo and the control surface.
The meshing clutch is powered by the AP panel and controlled through an engaged
bar. The velocity measuring motor is activated through the flight control computer.
The speed of servo with dual channels is fed back to the flight control computer for
monitoring so as to ensure the fail-safe protection function.
(5) Servo cable
The servo cable is used to connect the servo and control system, and transmit the
control action of the servo to the control surfaces.

3. System operation

A. Work pattern
(1) Mode select
(a) Push the mode buttons on the mode select panel, to make sure that each button
indicator light comes on and that the related information is displayed on the
EADI.
(b) When a mode is set, push the Go-Around button to set the Go-Around mode.
The mode set before is cancelled. The system will go into the Go-Around mode,
and “GA” (green) is displayed on the EADI.
(2) Lateral mode
(a) Push the HDG mode button on the MSP-85. The HDG indicator light comes on,
the HDG (green) is displayed on the EADI.
(b) Move the heading cursor of the EHSI to 30° left of lubber line and then to 30°
right. Then move it to the position below the lubber line. Make sure that the
EADI command bar moves along with the heading cursor. If the aircraft roll
attitude is horizontal, when the cursor is below lubber line, the command bar
must point ZERO.
(c) Move the heading cursor to right until the command bar correctly reaches the
maximum right turn command. Push the 1/2 BANK mode button on the MSP-85.
Make sure that the 1/2 BANK indicator light comes on, and the command bar
shows one decreased right deflection command quantity.
(d) Cancel all modes. Make sure that the command bar on EADI disappears and
the HDG and the1/2 BANK indicator lights go off.
(e) Disengage the DME. Tune the navigation receiver to the local VOR frequency.
Turn the course knob to make sure that the course pointer points to the radio
station and that deviation bar return to ZERO.

EFF：ALL 22-11-00
Page 4
Nov 20/2015
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

(f) Select the HDG mode on the MSP-85. Then the HDG indicator light comes on
and the HDG (green) is displayed on the EADI. Make sure that the EHSI course
pointer and the deviation bar points to the VOR direction.
(g) Monitor the location of the EHSI course pointer. Set the DG (directional gyro) of
the AHS switch panel in the DG mode. Turn the compass dial to “R” and “L” with
the deflection switch on the AHS switch panel. Do this, until the EHSI course
pointer points at 20° on the right side of the heading line. Adjust the EHSI
heading bug to a location below the heading line.
(h) Adjust the course pointer of the EHSI to the right side for 20° again (the course
pointer points to 40° right of the lubber line). Select the NAV mode on the
MSP-85. Make sure that the EADI command bar points ZERO. The deviation
bar of the EHSI moves towards the left side to the maximum range. The HDG
light of the MSP-85 goes off, the NAV light of the MSP-85 comes on. The HDG
(green) and the VOR1 (white) are displayed on the EADI at the same time.
(i) The course knob of EHSI slowly turns counterclockwise until the deviation bar
returns to the center. The HDG (green) and the VOR1 or the VOR2 (white)
disappear and that the VOR1 or the VOR2 is displayed on the EADI when the
deviation bar is between the two points and the center.
(j) Adjust the EHSI course pointer to move the EHSI deviation bar to the center.
Turn the compass dial to move the course pointer below the lubber line. When
the aircraft roll attitude is horizontal, the command bar slowly moves to
horizontal.
(k) Engage the DME. Turn the course pointer to 360°. When the DME is less than 2
mile, the EADI command bar moves a little or stays static.
(l) Select the HDG and the ALT modes on the MSP-85. The HDG and the ALT
indicator lights on MSP-85 come on. The HDG (green) and the ALT (green) are
displayed on the EADI. Set the heading cursor and the course pointer below of
the lubber line. Tune the VIR receiver to the frequency of the local instrument
landing system. Disengage the radio altimeter.
(m) Select the APPR mode on the MSP-85. Make sure that the APPR indicator light
comes on, the HDG (green), the ALT (green) and the LOC1 (white) are displayed
on the EADI.
(n) Operate the test switch of the VIR receiver to connect and disconnect until the
LOC (green) is captured. The LOC1 (white) disappears, and the LOC1 (green)
and the GS (white) are displayed on the EADI at this time. The GS (white)
disappears and the GS (green) is displayed on the EADI after the GS is captured
and the command bar points at the direction of the GS capture.
(o) Engage radio altimeter. The command bar is ZERO in pitch.
(p) Push the GA button. Make sure to cancel the aircraft command mode. The
related information displayed on the MSP-85 and the EFIS disappear. The
lateral GA (green) and the longitudinal GA (green) are displayed on the EADI
and the command bar indicate nose up and wing level-off.
(q) Push the SYNC button. Make sure that the Longitudinal GA (green) disappears,
the command bar points to ZERO in pitch.
(r) Check of Long Range Navigation (LRN)

EFF：ALL 22-11-00
Page 5
Feb 20/2013
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

1 Select NAV mode on the MSP-85. Select LRN1 for the main course
navigation source. The LRN1 (white) is displayed on the EADI.
2 Engage the flight management system to make sure that it stays in the
STATIC TEST state. Make sure that the LRN1 (green) is displayed on the
EADI. Engage the autopilot. Push the "ROLL 20 DEG R →” key on the
UNS display. Make sure that the EADI command bar turns right. Make sure
that the control wheel turns right until it stops. Push the "ROLL 20 DEG L
→” key on the UNS display. Make sure that the EADI command bar turns
left. Make sure that the control wheel turns left until it stops.
(3) Vertical mode
CAUTION: MAKE SURE THAT THE ALTITUDE PRE-SELECTOR DOES NOT
SELECT THE ALTITUDE OF THE AIRCRAFT OTHERWISE THE
VERTICAL MODE SELECTION WILL BE INHIBITED.
(a) Connect the air data tester to the air data system. Set 200 Kn on the ASI and a
climb rate of +2000 ft/min on the TVI (VSI, if there is a rate-of-climb meter) with
the air data tester.
(b) Engage the autopilot. Do not select each lateral mode and the vertical mode.
The VS mode must be automatically selected. The vertical speed reference on
the EADI must agree with the vertical speed indication (if there is a rate-of-climb
meter installed, the vertical speed cursor on the VSI must conform to the vertical
speed indication). The EADI command bar points ZERO pitch command.
(c) Use the tester to simulate the state of the stop climb. Select the SPEED mode
on the MSP-85. Make sure that the SPEED indicator light comes on, the ASI
airspeed cursor agrees with the pointer.
(d) Select the ALT mode on the MSP-85. The SPEED indicator light on the MSP-85
goes off (it indicates that this mode is cancelled), and the ALT indicator light
comes on. ALT (green) is displayed on the EADI. The EADI command bar points
to the zero pitch command.
(e) Turn the BARO knob on the ALT-85A altimeter indicator to change the altimeter
display to appreciably higher or lower than pre-selected altitude. The command
bar slowly pitches down if the altitude indication is appreciably higher than
pre-selected altitude, and that pitches up if the altitude indication is lightly lower
than pre-selected altitude. Set the BARO knob to 1013 mbar (29.92 inHg).
(f) Set the altitude to 5000 ft ± 100 ft. Select the CLIMB mode on the MSP-85. The
CLIMB indicator light on the MSP-85 comes on and the CLM 140 is displayed on
the EADI. Push the PERFORM SELECT button to make the CLM150H is
displayed on the EADI. The ASI airspeed cursor changes from 140 kn to 150 kn.
(g) Change the airspeed with the air data tester to change the ASI indication to
appreciably higher or lower than the value pointed by the airspeed cursor. If the
airspeed is appreciably higher than the value pointed by the airspeed cursor, the
command bar pitches up. If the air speed is appreciably lower than the value
pointed by the airspeed cursor, the command bar stops at the aircraft symbol
(airspeed 150 kn).
(h) Push the PERFORM SELECT button for the second time. The CLM140 is
displayed on the EADI. The airspeed cursor changes from 150 kn to 140 kn.
(i) Set SPEED button on the MSP-85. The SPEED indicator light on the MSP-85

EFF：ALL 22-11-00
Page 6
Feb 20/2013
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

comes on. The IAS (green) is displayed on the EADI.

(j) Set DESCEND button on the MSP-85. The DESCEND indicator light on the
MSP-85 comes on. The DES1000 is displayed on the EADI. (If there is a
rate-of-climb meter installed, the vertical speed cursor of the VSI points at 1000
ft/min.)

B. Power Supply

The power supply of the autopilot system is shown in Table 002.

Table 002. Power supply summary

Equipment Designation Bus/C/B PNL Row/Column

Autopilot L MSP/R MSP DC 28 V/ LH（RH）DC C/B PNL

APP A/APP B

FCC A/FCC B

Servo AP TRIM DC 28 V/ LH（RH）DC C/B PNL

AP CONT

4. Controls and indicators

A. Control unit

(1) The autopilot panel

The autopilot panel (APP-85) includes these controls (Ref. Fig. 002)
(a) ENGAGED Bars
Move the AP and YD engaged bars with protective side plates to ENGAGE, to
engage the autopilot and the yaw damper. The AP can be engaged just when
the yaw damper is engaged because the AP and the yaw damper are
interconnected. When the autopilot or the yaw damper is powered, the FCC
starts the prestarting routine test procedure. If the first test procedure is not
completed The system will not engage, i.e. the AP and YD engaged bars will
return to the DISENGAGED positions automatically. The engagement message
for the AP is displayed on the EADI in green. The disengagement warning is
shown on the integrated warning light box, as follows:
- L AP OFF, R AP OFF in red color,
- L YD OFF and R YD OFF in yellow color.
When engaged for the first time (without flight direction mode select), the
autopilot has two basic operation modes: roll holding and vertical speed holding.

NOTE: On APP-85 Autopilot Panel, L and R are respectively represents

EFF：ALL 22-11-00
Page 7
Feb 20/2013
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

controlling the steering direction to the left and right, DN and UP

represents controlling the pitch-up and pitch-down direction,
ENGAGED represents the engaged position for AP and YD,
DISENGAGED represents the disengaged position for AP and YD.

Figure 002 Autopilot panel – Controls and indicators

1. Turbulence Indication Light; 2. Autopilot Transfer Indication Light; 3. Autopilot
transfer switch; 4. AP engaged bar; 5. YD engaged bar; 6. Turbulence mode switch;
7. Pitch control wheel; 8. Steering knob.
(b) AP XFR (Autopilot transfer) switch
The AP XFR switch is used to select the FCC channel. Push the AP XFR switch
to move the autopilot to the right pilot system, this will occur:
- Indication light of the AP XFR button switch is illuminated;
- An arrow “→”is displayed on the EADI.
Push the AP XFR button switch again, this will occur:
- The autopilot will go back to the left pilot system
- The arrow “←” is displayed on the EADI.
When AP system control returns to the left pilot system, the AP XFR indication
light is off.
(c) TURB (Turbulence) Switch
When the aircraft is within turbulence, press the TURB button to achieve AP
system milder control and increase the passenger comfortableness. When
selecting TURB mode, the indication light in the button switch is illuminated;
press again to turn off the TURB mode, and the indication light in the button
switch is off. When selecting the approach mode (APPR), the linkage restrains
the use of TURB mode.

EFF：ALL 22-11-00
Page 8
Nov 20/2015
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

(d) Pitch Control Wheel

The pitch control wheel is used to provide vertical reference commands such as
IAS (indicated airspeed) and VS (vertical speed). These values can be changed
into new values through operating the pitch control wheel and observing the
displayed values on EFIS and the above indicated reference values (on the side
which is decided by the AP XFR switch). When the operation is completed, a
spring makes the control wheel return to the neutral position. When the system
is operating in the modes of climbing, descending, altitude holding or altitude
tracking, it will return to the basic vertical speed mode once the operation of the
pitch control wheel is completed. The pitch control wheel is inoperative when the
glide slope (GS) is captured or the AP is disengaged.
(e) Steering knob
The steering knob provides the function of performing all lateral commands
except the approach (APPR) capturing or Localizer (LOC) capturing. Turn the
knob from the centre stop point to the left or right, the system will send a roll rate
command which is proportional to the displacement. The output command of
the steering knob is a speed signal. A spring will make the knob return to the
centre stop point when the deflection is completed. After operating with the
steering knob, the system mode is rolling hold and it maintains the roll angle
given by the steering knob. When the roll angle is less than 5°, the system mode
is heading hold and it holds the heading of the aircraft the moment holding mode
is started in use. The roll angle limit is 32°, and the steering knob has no use
when AP is cut off.
(2) Mode select panel
The mode select panel is used to select the flight directing mode. The mode button
adopts a push-engage/push-disengage logic. Push the mode button to select the
mode, and cancel the incompatible operation modes at the same time. If the
selected mode requirements can be fulfilled within the system, then the indication
light in the mode button is illuminated. (Ref. Fig. 003):

Indication light

Figure 003 Mode select panel

NOTE: The PERFORM SELECT button is not used as the mode button but used
together with the CLIMB mode.
The mode button is interconnected, so only the compatible modes can be used
together at the same time. If lateral modes are not selected, the system operates in

EFF：ALL 22-11-00
Page 9
Nov 20/2015
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

roll holding mode; if vertical modes are no selected, the system operates in pitch
holding or vertical speed holding modes.
(a) HDG mode
Select the HDG mode. The command bar on the EADI is displayed and directs
the aircraft to the heading indicated by heading cursor. Control and limit the AP
command of roll to 27° and the maximum limitation of the roll speed to 4°/s.
(b) 1/2 BANK mode
The half bank mode reduces the roll order limitation to 12.5°, which can be used
for all roll modes except approach mode (APPR) capture or any LOC capture
modes.
(c) NAV mode
Push the navigation (NAV) mode button to select the navigation mode. The
system operates in the navigation mode selected and displayed by EFIS. The
AP always flies in the current (main) course shown on EFIS. Press the NAV
button and the navigation mode is in preparation. When the navigation data
source is valid and meets the capture conditions, the navigation mode will be
captured. Before capture, the navigation system is in the auxiliary mode of the
heading select, and the system operates according to the heading displayed on
the EHSI. The system flies according to the digital optimization control law and
provides the omni-bearing self adaptive capture (including true airspeed
compensation at capture point). It sends flight commands after capturing to
keep on the navigation course.
(d) Approach Mode (APPR)
PUSH the approach (APPR) mode button to select the approach mode, which is
similar to the navigation mode. When the data of the instrument landing system
is selected and displayed by EFIS, the system prepares to glide slope (GS) after
heading captured. When glide slope is captured, the vertical mode will be
canceled. The system sends the glide slope command and hold in the glide
slope course. The radio altitude messages are used to decide the control law
increment of LOC and GS. When VOR approach mode and back course mode
are used, the GS is suppressed. When the system operates in the back course
mode, the control law of back course is used to hold the system in the back LOC
course.
(e) ALT mode
Turn the ALT tuning knob on the course heading select panel, if the AP is
engaged or only the lateral mode is valid during the flight directing status, the
system will prepare altitude pre-select mode automatically with the exception of
glide slope capture. When the flight path goes through the set altitude, the ALT
will be captured. The capture point is the function of the altitude rate and the
altitude deviation (relative to the pre-selected altitude). When ALT is captured,
the previous selected vertical mode is canceled, and sends the flight command
of tracking the selected altitude to the aircraft.
During the capture (not tracking) of the pre-selected altitude, any change of the
pre-selected value will cause the system to operate in basic vertical speed
holding mode and make preparation for another altitude pre-select. During the
tracking (the system operates in the altitude holding mode) of altitude pre-select,

EFF：ALL 22-11-00
Page 10
Nov 20/2015
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

for another altitude pre-select.

(f) CLIMB mode
Push the CLIMB button to select the climb mode. The system will provide the
calculation command to fly and keep the IAS profile specifically set and
pre-programmed for the aircraft type. Two speed profiles (L-low speed. H-high
speed) can be selected through the PERFORM SELET button. The IAS
reference is displayed on EADI and the IAS reference cursor on EADI will
change along with the IAS command (the cruise IAS value determined by L/H).
The minimum vertical speed is designed as a rating value 2.55 m/s (500 ft/min)
to make sure that the flight altitude will not decrease In climb mode.
(g) DESCEND mode
The DESCEND mode is used to transfer smoothly from the initially selected
vertical mode to the pre-programmed vertical descending. When the mode is
selected, the system will give a smooth pitch change command. The vertical
descending speed for this command is pre-programmed. Always use the pitch
control wheel to change the descending speed.
(h) SPEED mode
Use the SPEED mode button to select the speed hold mode. When the mode is
selected, the system will keep the IAS (indication airspeed). The IAS reference
value is displayed on EADI and can be revised through the pitch control wheel
on the AP panel or the setting knob of the airspeed indication cursor on ASI.
(i) PERFORM SELECT button
This button is not a mode button. It can do these functions:
CLIMB mode: Select the climb profiles of low and the high speed.
NOTE: All buttons except the performance button on the mode select panel are
push-engage /push-disengage buttons.

B. Indicators

The flight mode is displayed on EADI. The display position of operation status and the
display content refer to Figure 004.

EFF：ALL 22-11-00
Page 11
Feb 20/2013
 MA60 AIRCRAFT MAINTENANCE MANUAL (PART I SDS)

Figure 004 Autopilot data on the EADI

EFF：ALL 22-11-00
Page 12
Feb 20/2013