GROUND SCHOOL
AUTOPILOT
VC-99 B
OBJETIVO

IDENTIFICAR O FUNCIONAMENTO DO
“AUTOPILOT” DA AERONAVE VC-99 .
SCREENPLAY
1. TERMS DEFINITIONS
2. CONCEPT AND PURPOSE
3. COMPONENTS
4. FLIGHT DIRECTOR MODES
5. AUTOPILOT DISENGAGEMENT
6. CONTROLS AND INDICATORS
7. MESSAGES
8. LIMITATIONS
TERMS DEFINITIONS
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AIR DATA COMPUTER (ADC);
RADIO ALTIMETER SYSTEM (RA);
STALL PROTECTION SYSTEM (SPS);
ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS);
ELETRONIC FLIGHT INSTRUMENT SYSTEM (EFIS);
HORIZONTAL STABILIZER CONTROL UNIT (HSCU);
AURAL WARNING UNIT (AWU);
RADIO MANAGEMENT SYSTEM (RMS);
FLAP ELETRONIC CONTROL UNIT (FECU);
FLIGHT MANAGEMENT SYSTEM (FMS);
FLIGHT GUIDANCE SYSTEM (FGS);
FLIGHT DIRECTOR (FD);
AUTOPILOT (AP).
SCREENPLAY
1. TERMS DEFINITIONS
2. CONCEPT AND PURPOSE
3. COMPONENTS
4. FLIGHT DIRECTOR MODES
5. AUTOPILOT DISENGAGEMENT
6. CONTROLS AND INDICATORS
7. MESSAGES
8. LIMITATIONS
CONCEPT AND PURPOSE
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PRIMUS 1000 Automatic Flight Control System
(AFCS) is a fully integrated, fail passive three-axis
flight control system which incorporates lateral and
vertical guidance, yaw damper and automatic pitch
trim functions.

The AUTOPILOT provides yaw estabilization and
folllows pitch and roll attitude commands from
FLIGHT DIRECTOR.
SCREENPLAY
1. TERMS DEFINITIONS
2. CONCEPT AND PURPOSE
3. COMPONENTS
4. FLIGHT DIRECTOR MODES
5. AUTOPILOT DISENGAGEMENT
6. CONTROLS AND INDICATORS
7. MESSAGES
8. LIMITATIONS
CONCEPT AND PURPOSE

The Automatic Flight Control System (AFCS)
consists of dual IC-600's, autopilot servos, a Flight
Guidance Controller (GC-550), a pitch and turn
controller (PC-400) and a display controller (DC550).
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The Automatic Flight Control System interfaces with
the following systems: IRS, AHRS, RMS, ADC, RA,
SPS, EGPWS/ GPWS, EFIS, HSCU, AWU, FECU
and FMS.
AUTOPILOT SCHEMATIC
COMPONENTS
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IC-600 COMPUTER;
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FLIGHT GUIDANCE CONTROLLER (GC-550);
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PITCH AND TURN CONTROLLER (PC-400);
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DISPLAY CONTROLLER PANEL (DC-550).
FLIGHT GUIDANCE CONTROLLER
PITCH AND TURN CONTROLLER
DISPLAYS CONTROL PANEL
SCREENPLAY
1. TERMS DEFINITIONS
2. CONCEPT AND PURPOSE
3. COMPONENTS
4. FLIGHT DIRECTOR MODES
5. AUTOPILOT DISENGAGEMENT
6. CONTROLS AND INDICATORS
7. MESSAGES
8. LIMITATIONS
FLIGHT DIRECTOR MODES
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LATERAL MODES
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VERTICAL MODES
FLIGHT GUIDANCE CONTROLLER
LATERAL
VERTICA
L
PFD INDICATORS ( LATERAL  VERTICAL )
FLIGHT DIRECTOR MODES
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LATERAL MODES
- HEADING HOLD MODE
* Roll Hold Submode
* Turn Knob Submode
* Wings Level Submode
- HEADING SELECT MODE (HDG)
* Low Bank Mode
- VOR NAV MODE (VOR)
- VOR APPROACH MODE (VAPP)
- LOCALIZER MODES (LOC/BC)
- LNAV MODE
FLIGHT DIRECTOR MODES
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VERTICAL MODES
- PITCH HOLD MODE (não tem vert acoplado)
- ALTITUDE HOLD MODE (ALT) (niv instantâneo)
- ALTITUDE PRESELECT MODE (ASEL) (pré-seleção)
- FLIGHT LEVEL CHANGE MODE (FLC)
- SPEED HOLD MODE (SPD)
- VERTICAL SPEED HOLD MODE (VS)
- GLIDE SLOPE MODE (GS)
- GO AROUND MODE
* Takeoff Submode
* Speed Target Submode
- WINDSHEAR ESCAPE GUIDANCE MODE
SCREENPLAY
1. TERMS DEFINITIONS
2. CONCEPT AND PURPOSE
3. COMPONENTS
4. FLIGHT DIRECTOR MODES
5. AUTOPILOT DISENGAGEMENT
6. CONTROLS AND INDICATORS
7. MESSAGES
8. LIMITATIONS
AUTOPILOT DISENGAGEMENT
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Autopilot Engage/Disengage button
Quick Disconnect button
Voice Message “AUTOPILOT”
* Above 2500 ft RA (valid RA signal) – self canceled.
* Below 2500 ft RA (valid RA signal) – pressing
Autopilot Quick Disconnect Button twice.
* Invalid RA signal – pressing Autopilot Quick
Disconnect Button twice.
SCREENPLAY
1. TERMS DEFINITIONS
2. CONCEPT AND PURPOSE
3. COMPONENTS
4. FLIGHT DIRECTOR MODES
5. AUTOPILOT DISENGAGEMENT
6. CONTROLS AND INDICATORS
7. MESSAGES
8. LIMITATIONS
CONTROL WHEEL
THRUST LEVERS
PFD INDICATORS (V-BAR FORMAT)
PFD INDICATORS (CROSS-BAR FORMAT)
PFD INIDICATORS (CROSS-BAR FORMAT)
ROLL MISTRIM ANNUNCIATION
SCREENPLAY
1. TERMS DENIFINITIONS
2. CONCEPT AND PURPOSE
3. COMPONENTS
4. FLIGHT DIRECTOR MODES
5. AUTOPILOT DISENGAGEMENT
6. CONTROLS AND INDICATORS
7. MESSAGES
8. LIMITATIONS
MESSAGES
TYPE
MESSAGE
MEANING
WARNING
AUTOPILOT FAIL
Autopilot has failed and has
been automatically disengaged.
AUTO TRIM FAIL
Automatic pitch trim has failed.
AP ELEV MISTRIM
A pitch mistrim condition exists.
AP AIL MISTRIM
CAUTION
A roll mistrim condition exists.
LATERAL MODE OFF
Inadvertent loss of the Lateral
Flight Mode.
VERTICAL MODE OFF
Inadvertent loss of the Vertical
Flight Mode.
YAW DAMPER FAIL
Yaw Damper has failed and has
been automatically disengaged.
SCREENPLAY
1. TERMS DEFINITIONS
2. CONCEPT AND PURPOSE
3. COMPONENTS
4. FLIGHT DIRECTOR MODES
5. AUTOPILOT DISENGAGEMENT
6. CONTROLS AND INDICATORS
7. MESSAGES
8. LIMITATIONS
LIMITATIONS
For airplanes Pre-Mod. SB 145-31-0016,the Autopilot below 1500 ft AGL is only permited when
coupled to the captain’s Flight Director.
Minimum Altitude During ILS Approach
200 ft
Minimum Engagement Height
500 ft
Minimum use Height
160 ft
Malfunction altitude loss :
Cruise
80 ft
Maneuver
40 ft
ILS Approach
15 ft
 Descent below Minimum Decision Altitude on a non precision approach with autopilot engaged is
prohibited.
 Single engine go around with autopilot engaged is prohibited.
 Approach mode selection during localizer capture is allowed only when airplane is inbound.
 Go-around in basic mode ( roll and pitch) is allowed only with wings level.
NOTE: Coupled go-around height loss may be 75 ft.
SCREENPLAY
1. TERMS DEFINITIONS
2. CONCEPT AND PURPOSE
3. COMPONENTS
4. FLIGHT DIRECTOR MODES
5. AUTOPILOT DISENGAGEMENT
6. CONTROLS AND INDICATORS
7. MESSAGES
8. LIMITATIONS
OBJETIVO

IDENTIFICAR O FUNCIONAMENTO DO
“AUTOPILOT” DA AERONAVE VC-99.
“ POTÊNCIA NÃO É NADA
SEM CONTROLE”
GOODYEAR
Conduzindo os que
conduzem a Nação!

(Foreign Venture Capital Investors) (Amendment)