INSTRUCTOR REVIEW GUIDE LESSON N4SYS-17_IGR 1.5 HOURS AVIONICS SYSTEMS REVIEW

Transcription

1 Lecture Discussion 1 INSTRUCTOR REVIEW GUIDE LESSON N4SYS-17_IGR 1.5 HOURS AVIONICS SYSTEMS REVIEW Class Preparation Instructional Aids Aircrew Operating Handbook Volume 2.1 Aircraft Systems for the C-146A Aircraft Aircrew Operating Handbook Volume 2.2 Aircraft Systems for the C-146A Aircraft Honeywell Primus 2000 Integrated Avionics System Manual MEL-Minimum Equipment List Rev. C CDL-Configuration Deviation List N4SYS-17_IGR Slide 1 Welcome This lesson provides a review of the C-146A Avionics Systems. Slide 2 Module Terminal Learning Objectives Instructor: During this review, we will discuss what you learned during your computer based training and identify any areas that you may need additional help with or any unanswered questions. Let the students read the Terminal Learning Objectives for this review. Advance to the next slide. Slide 3 Module 1 Terminal and Enabling Learning Objectives Instructor: Read the module TLO and ELOs and ask the students if they have any questions or concerns about any specific sections. Slide 4 Communication Systems Overview Instructor: Review the Communication (BUS) Systems Bus Systems

2 Lecture Discussion 2 Slide 5 VHF Communications Instructor: Select each button on screen to reveal each corresponding image. Description Components Integrated Communication Unit (ICU) Radio Management Unit (RMU) COM 1 HOT Button Slide 6 VHF Communication (Cont.) Operation Operation with Other Systems Integrated Tuning System Audio Integrating System Data Acquisition System Landing Gear Position and Warning Flight Management System (FMS) Slide 7 Check on Learning 1 The VHF communication system can be operated by what components? a. Radio Management Units (RMUs) b. Clearance Delivery Head (CDH) c. Flight Management System (FMS) d. all of the above (correct answer) e. none of the above Slide 8 HF Communication Instructor: Select blue boxes on the image. Description

3 Lecture Discussion 3 Components - Primus 2000 operations manual for RMU operation with HF Radio Operation with Other Systems VHF Communication Audio Integrating VHF Navigation Flight Management System (FMS) avionics Slide 9 Check on Learning 2 How many of the 280,000 discrete operating frequencies available through HF radio can be present in channels? a. 125 b. 115 c. 100 d. 99 (correct answer) Slide 10 Cottonmouth Friendly Forces Tracker (FFT) Instructor: Select the image for more information. Components Antenna Configuration Instructor: Select the caution button for more information. CAUTION: THE COTTONMOUTH MUST NEVER BE CONNECTED DIRECTLY TO AN ACTIVE GPS ANTENNA, OR TO A DISTRIBUTED GPS NETWORK. I-MODE TRANSMISSIONS FROM THE RADIO WILL DESTROY THE ACTIVE ELEMENTS IN THE ANTENNA AND OTHER EQUIPMENT POSSIBLY CONNECTED TO THE DISTRIBUTED FEED. Slide 11 Cottonmouth Friendly Forces Tracker (FFT) (Cont.) Instructor: Review the image on screen. Batteries and External Power Operation

4 Lecture Discussion 4 Instructor: Select the Note, Caution, and Warning buttons. Note: If zeroized, the unit will be inoperable unit it is returned to normal operation in depot mode. Caution: REMOVE BATTERIES BEFORE SHIPMENT OR INACTIVE STORAGE OF 30 DAYS OR MORE. Warning: LITHIUM BATTERIES CONTAIN HAZARDOUS AND REACTIVE MATERIALS. DISPOSE OF IAW ALL PROPER LOCAL, STATE, AND FEDERAL REGULATIONS. DO NOT DISPOSE OF IN UNCONTROLLED TRASH. IMPROPER HANDLING, REVERSE CURRENT OPERATION, OR HIGH ENVIRONMENTAL TEMPERATURE MAY RESULT IN INTERNALLY GENERATED HEAT, FIRE, EXPLOSION, OR THE RELEASE OF TOXIC MATERIALS AND GASES. Slide 12 Check on Learning 3 The Cottonmouth FFT must never be connected directly to an active GPS antenna, or to a distributed GPS network. a. True (correct answer) b. False Slide 13 Intercommunication System Description Operation Slide 14 Intercommunication System (Cont.) Instructor: Review the table on screen. Transmit/Receive Capabilities by Crew Position VHF1 VHF2 HF ARC- 231 PRC1 PRC2 NET1 NET2 NET3 Pilot ACP 1 X X X X X X R X Copilot ACP 2 X X X X X X R X Observer ACP5 X X X X X X X X Oper 1 Oper 2 R R R X X X X X ACP 4 Oper 3 ACP 3 R R R X X X X X Oper 4 R R R X X X X X

5 Lecture Discussion 5 ACP 6 Transmit/Receive Capabilities Malfunctions Stuck Key Stuck PTT Sub-AMU1 Malfunction Sub-AMU2 Malfunction Emergency Mode (Self-Initiated) Audio Intercom Net (INT NET) Audio System Errors on Load Shed Instructor: Select the Note Button Note: If the flight crew has to load-shed the Mission Bus, the BIT light will start blinking and they will see failures of ACP 3, 4, and 6. However, the BIT light will stop blinking after a short time and the remaining system (ACPs 1, 2, and 5) will still operate normally. Slide 15 Check on Learning 4 The first operator to begin transmitting over a particular transmitter or PA will have control priority until releasing the PPT, at which time another operator may begin transmission. a. True (correct answer) d. False Slide 16 Passenger Address (PA) and Call System Instructor: Review the image on screen. Description Components PA Amplifier

6 Lecture Discussion 6 Flight Deck Calls Panel Emg Call Cabin Call Gnd Call Cabin Headset Ground Crew Jacks Operation with Other Systems Slide 17 Turbine Section Operation Connect a personal electronic device (PED) to the AUD INPUT connector, press the PAX BRIEF switch (annunciator light on) to enable the input. Play back the prerecorded message, then press the PAX BRIEF switch again (annunciator light off) to disable the input. The PED can then be disconnected from the system. Instructor: Select each Note button on screen. Note: The PAX BRIEF input is not intended for any long term playback (more than approximately 15 minutes). The audio output stage of the Passenger Address amplifier is not designed to be utilized for long periods of time and will overheat. Note: When playing back the prerecorded message it may be necessary to set the output volume of the PED at or near maximum to overcome any noise gate internal to the Passenger Address system. If an audio equalizer is included in the PED player application (e.g. Windows Media Player) then it might be helpful to boost the equalizer bands in the frequency range between 250 and 4000 Hz approximately 3 to 6dB. Slide 18 Audio Integrating Description Components Operation Operation with Other Systems Slide 19 Cockpit Voice Recorder (CVR) Description

7 Lecture Discussion 7 Components Operation Operation with Other Systems Slide 20 Check on Learning 5 Which component records all cockpit conversations? a. FDR b. CVR (correct answer) c. ELT d. IRS Slide 21 Flight Data Recorder (FDR) Preflight Check of FDR Erasure of Data Slide 22 Integrated Automatic Tuning System Description Radio Management Unit (RMU) Operation By using the1/2 Key, the display from the opposite head can be duplicated on the first. Tuning can be accomplished and then control returned to the other side When the function legends are in Magenta, it means that cross controlling is being exercised This function does not affect the ATC window. In TCAS installations, moving the cursor to the ATC window and depressing the 1/2 key causes the opposite side transponder to become active The Amber indications show that that frequency was tuned by use of cross side tuning Slide 23 Integrated Automatic Tuning System (Cont.) Operation Navigation backup Mode

8 Lecture Discussion 8 The RMU can also be used to display engine information and CAS msg Operation with other Systems VHF COM Direct COM Tuning Slide 24 Clearance Delivery Control Display Head (CDH) Instructor: Select the image on screen. Operations Provides an alternate or emergency backup capability for tuning the remote #1 VHF Comm transceiver or #1 VHF Nav receiver in the event the RSB tuning is not available EMERG Mode locks out all other COM and NAV tuning sources for the #1 Nav. Is NOT related to MHz Used for Comm prior to engine start to reduce power draw Operation with other Systems Slide 25 Soft Smoke Barrier Two-Way Communications The ceiling jacks are tied together in parallel to the Observer s ACP. Communication with the flight deck is enabled according to the settings on the Observer s ACP. NOTE: It is impossible to accidently transmit over any aircraft radio from the smoke barrier ceiling jacks. Slide 26 Static Discharging The static discharging system is used to reduce radio frequency electromagnetic interference associated with the discharge of aircraft electrostatic charges accumulated during flight. Slide 27 RF Distribution RF Distribution Network Instructor: Select the Warning, Caution, and NOTE buttons. Warning: TRANSMISSION FROM THE ARC-231 AND PRC-117G RADIOS IS PROHIBITED DURING CRITICAL PHASES OF FLIGHT.

9 Lecture Discussion 9 Caution: TRANSMISSION ON MISSION RADIOS CAN POTENTIALLY INTERFERE WITH NAVIGATION AIDS. NOTE: All of the RF equipment discussed in this section has operating specifications, such as power and frequency operating range. Despite these limitations, it is possible to operate a given configuration out of specification. Slide 28 RF Distribution Antenna Selection Switch Slide 29 Mission Radio Junction Box Instructor: Select blue box on image. Radio Rack uncovered Mission Radio Junction Box Slide 30 ARC-231 Radio Instructor: Select blue box on image. Overview Line-Of-Sight (LOS) voice and data communications Maritime Voice Have Quick (HQ) UHF Single Channel Ground and Airborne Radio System (SINCGARS) Satellite Communications (SATCOM) DAMA - Demand Assignment Multiple Access (DAMA) or Demand Assignment Single Access (DASA) digital voice and data communications Non-DAMA Digital voice and data communications. Beacon Transmission Slide 31 ARC-231 Radio (Cont.) Instructor: Select blue box on image. Description ARC-231 R/T ARC-231 Fill Panel

10 Lecture Discussion 10 Slide 32 ARC-231 Radio (Cont.) Instructor: Select blue box on image. ARC-231 Control Indicator Slide 33 PRC-117G Radio The PRC-117G Multiband Manpack Radio is a tactical transceiver designed for use by military/agency personnel requiring Type-1, National Security Agency (NSA) certified, secure voice and data communications. Features 99 programmable Presets 99 programmable waveform presets Built-in Test (BIT) Internal Ground-Based GPS Receiver VINSON, Advanced Narrowband Digital Voice Terminal (ANDVT), Advanced Encryption Standard (AES), FASCINATOR, and KG-84C embedded encryption modes for VHF-low through UHF bands BATON or MEDLEY encryption mode for ANW2 Automatic scan operation of both Cipher Text (CT) and Plain Text (PT) channels Support for remote Keypad Display Unit (KDU). Slide 34 PRC-117G Radio (Cont.) Instructor: Select each button on screen. Description PRC-117Gs (Radio Rack) PRC-117G Controls, Indicators, and Connectors. Slide 35 PRC-117G Radio (Cont.) Keyboard Display Units (KDU) Remote KDU

11 Lecture Discussion 11 Slide 36 Module 1 Summary Instructor: Read the module TLO and ELOs and ask the students if they have any questions or concerns before moving on. Slide 37 Module 2 Terminal/Enabling Learning Objectives Instructor: Read the module TLO and ELOs and ask the students if they have any questions or concerns about any specific sections. Slide 38 Electronic Systems Displays Electronic Systems Displays Slide 39 Electronic Systems Displays (Cont.) Flight Altitudes Airspeeds Vertical Speed Attitude Heading Course Orientation Flightpath Commands Weather and Mapping Presentations Aircraft System Indications Source Annunciations TCAS EGPWS Slide 40 Electronic Systems Displays (Cont.) Attitude Director Indicator (ADI) ADI Display and Annunciations Airspeed Display Altitude Display Vertical Speed Display

12 Lecture Discussion 12 Horizontal Situation Indicator (HIS) Full Compass Display Arc Display Slide 41 Electronic Systems Displays (Cont.) Instructor: Select each button on screen to display corresponding images. Typical PFD Presentations Takeoff Roll Mode Climb to Initial Altitude Enroute Cruise Setup for Approach Weather Display on PFD Slide 42 Electronic Systems Displays (Cont.) Comparison Monitoring Takeoff Mode Takeoff Roll Mode Climb to Initial Altitude Enroute Cruise Setup for Approach Weather Display on PFD Slide 43 Propeller System Overview (Cont.) Instructor: Review the table on screen. Comparison Monitoring Comparison Monitoring Parameter Annunciation Trip Point Attitude ATT Active only when either pitch or roll comparators show ±5 pitch or ±6 roll Heading HDG ±10 Altitude ALT ±200 ft

13 Lecture Discussion 13 Indicated Airspeed IAS ±20 kt Localizer Deviation LOC 1/2 dot Glideslope Deviation GS 2/3 dot Radar Altitude RA 10 + (average RAD ALT)/8 Azimuth Deviation AZ 1/2 dot Glidepath Deviation GP 2/3 dot Fault Warning Computer FWC FWC1 and FWC2 miscompare with an associated amber or cyan message Engine ENG Engine data miscompare between EICAS display and what is sensed by the DAU Slide 44 Electronic Systems Displays (Cont.) Instructor: Select each button on screen to display corresponding images. Failure Indications for IRS, MADC, Heading and Course Select, and Flight Director Failure Indications for Radar Altitude, Vertical and Course Deviation, and Distance Excessive Attitude Declutter Bank greater than ± 65 Pitch greater than 30 up Pitch greater than 20 down Slide 45 Electronic Systems Displays (Cont.) Instructor: Select each button on screen. PFD Test PFD Test Pattern 1 PFD Test Pattern 2 Slide 46 Check on Learning 6 The PFDs are part of the EFIS displays. a. True (correct answer) b. False

14 Lecture Discussion 14 Slide 47 Check on Learning 7 What information is not shown on the PFD? a. Airspeed b. Altitude c. Electronic System (correct answer) d. Fuel System (correct answer) Slide 48 Check on Learning 8 Engine exceedance is shown on the PFD. a. True b. False (correct answer) Slide 49 Electronic Systems Displays (Cont.) Multifunction Display (MFD) Slide 50 Electronic Systems Displays (Cont.) Multifunction Display (MFD) Slide 51 Electronic Systems Displays (Cont.) Instructor: Select each blue button for more information. MAIN ½ Menu MAIN ½ Menu DISPLAY Menu Radar Menus RADAR Menu (PRIMUS 660) RADAR SUB (PRIMUS 660) MFD SYSTEM Menus

15 Lecture Discussion 15 SYSTEM Menus SYSTEM 1/3 Menu Page SYSTEM 2/3 Menu Page SYSTEM 3/3 Menu Page FUEL SET Menu FMS Menu FMS Menu CURSOR Menu MFD FORMAT Slide 52 Electronic Systems Displays (Cont.) Instructor: Select each blue button for more information. MAIN 2/2 Menu MAIN 2/2 Menu (MFD) 2 TEST Test Menu Engine Exceedance Display Engine Exceedance Display AND Illustration TREND EXCEED Slide 53 Electronic Systems Displays (Cont.) Instructor: Review the image on screen. Slide 54 Aircraft Systems Displays Instructor: Select each blue button for more information. MFD Navigation Format MFD Arc Mode MFD Arc Mode Failure Warning Displays

16 Lecture Discussion 16 MFD Plan Mode MFD Plan Mode Failure and Warning Displays MFD Compass Rose Mode MFD Compass Rose Failure and Warning Displays Slide 55 Aircraft Systems Displays (Cont.) Instructor: Select each button on screen. FLIGHT CONTROL (Flight Control System) Flight Control System Page Flight Control Caution and Status Messages HYDR Hydraulic System Page Hydraulic Caution and Status Messages ENGINE (Engine System) FUEL (Fuel Supply) Slide 56 Aircraft Systems Displays (Cont.) Instructor: Select each button on screen. ELECTR (DC/AC Power Supply) ECS (Environmental Control System) ICE PROTECT (Ice Protection System) APU (Auxiliary Power Unit) CPCS/OXY (Cabin Pressurization and Control/Oxygen System DOORS (Doors) SYS MAINT (System Maintenance Information) SENSOR DATA Slide 57 Display System Reversionary Modes Reversionary Control Panel

17 Lecture Discussion 17 Slide 58 Display Failure Reversionary Modes Instructor: Review the Table on screen. Display System Reversionary Modes Signal Generator (SG) 1 and 2 failures Display Controller Failures Display System Reversionary Modes Function Source of Control, Default, Inop, or Last Value (Note 1) Onside Display Controller (DC) Failed Both Display Controllers (DC) Failed Bearing sources, circle ( O ) Default VOR 1 Default VOR 1 Bearing sources, diamond Default VOR 2 Default VOR 2 Primary navigation source Default Onside VOR/LOC Default Onside VOR/LOC Primary navigation source Default Off Default Off Selected heading Cross-side DC Default Invalid Heading SYNC button Default Off Default Off DC selected course Cross-side DC Default Invalid Course direct-to button Default Off Default Off Selected altitude Cross-side DC Default Invalid Selected airspeed Cross-side DC Default Invalid Selected ADC Cross-side DC Default Onside ADC Selected sensor Cross-side DC Default Onside AHRS [Block 20EA] IRS PFD HSI mode Default Arc without WX Default Arc without WX DH/MDA select Default DH Default DH DH set Default Invalid Default Invalid Barometric set format Default Inches Default Inches Bezel button selections Cross-side DC Last Selections (Notes 2 and 3) Bezel knob selections Cross-side DC Last Selection Slide 59 Standby Navigation Display Instructor: Review bullet points on screen regarding RMU Standby Navigation Display. RMU Heading Arc Display RMU Standby Navigation Display Slide 60 Standby Navigation Display Failure Indications Standby Navigation Failure

18 Lecture Discussion 18 Slide 61 Check on Learning 9 On the Standby Navigation Display, upon failure of the DME distance, NAV, or ADF frequency, digital bearing data is replaced with. a. white b (correct answer) c. X d. X Slide 62 EICAS MAIN Menu Selections Instructor: Select each blue button for more information. REF Data T/O Menu Automatic Engine Torque Computation CLIMB CRUISE LANDG SINGLE ENGINE COPY Menu COPY Sub-Menu Go-Around Vspeed Display REF DATA Set Parameters OFF and Removed. VREF and Current Flap Setting Displayed on PFD. Torque Bug Moves to Landing Value. EICAS Menu Returns to REF DATA. Slide 63 Check on Learning 10

19 Lecture Discussion 19 Pushing the REF DATA key on the MFD MAIN menu allows entry of target speeds, flap settings and engine torque parameters for various flight phases. a. True (correct answer) b. False Slide 64 Crew Alerting System Engine Instrument Display Format Slide 65 Primary Engine Display Engine Instrument Display Format Engine Miscompare Annunciations Torque (TQ) Display Propeller Speed (NP) Display Interstage Turbine Temperature (ITT) Ignition (IGN) Annunciation High Pressure Turbine (NH) Display Low Pressure Turbine (NL) Underspeed/Overspeed Annunciation Oil Temperature (OIL TEMP) Display Oil Pressure (OIL PRESS) Display Fuel Flow Display (FF LBS/HR digital readout) Fuel Quantity Display (FQ LBS digital readout) Primary Engine Display Failure Indications Slide 66 Check on Learning 11 What symbol and message are used to indicate DAU channel miscompare on the Primary Engine Display? A)? and Engine B)? and Engine

20 Lecture Discussion 20 C)? and MISCMP - ENGINE (correct answer) D)? and MISCMP - ENGINE Slide 67 Cabin Control Display Cabin Information Display Slide 68 Independent Instruments Instructor: Select each button on screen. Chronometer Inclinometers Slide 69 Module 2 Summary Instructor: Read the module TLO and ELOs and ask the students if they have any questions or concerns. Slide 70 Module 3 Terminal/Enabling Learning Objectives Instructor: Read the module TLO and ELOs and ask the students if they have any questions or concerns about any specific sections. Slide 71 Automatic Flight Control (Autoflight) Overview Autopilot (AP) Yaw Damper (YD) Flight Director (FD) Auto-Trim Integrated Avionics Computer #1 (IAC 1) Two independent Micro Air Data Computers (MADCs) Inertial Reference System (IRS) Flight Management System (FMS) Data Acquisition Units (DAUs) Slide 72 Automatic Flight Control (Autoflight) Overview (Cont.) Instructor: Asks students if there are questions regarding the AFCS Schematic. AFCS Schematic

21 Lecture Discussion 21 Slide 73 Automatic Flight Control (Autoflight) Overview (Cont.) The AP engages in the pitch range +/- 50 and in the roll range +/- 75. The AP control limits for roll are +/-35, except in approach mode. When in approach mode, the roll limits are reduced linearly from +/-25 above 200 ft radio altitude, to +/-5 at zero ft radio altitude. The AP pitch control limits are +/-20. In the approach mode, the nose-down pitch limit (-20 ) is programmed linearly to -6 during the transition from 150 ft radio altitude to 15 ft radio altitude. Instructor: Select the Warning button for more information. WARNING: ENGAGEMENT OF THE AP IS PROHIBITED DURING T/O AND GO- AROUND MODES. Slide 74 Flight Guidance Computer (FGC) Instructor: Use the scroll bars to review the FGC Data Inputs. FGC Data Inputs Slide 75 Autopilot (AP) Disconnect Button Control Wheel, AP Disconnect Button Touch Control Steering (TCS) Slide 76 Go-Around (GA) Switches Instructor: Select the Warning button for more information. GA Switches Autotrim WARNING: IF MANUAL TRIM IS ACTIVATED WHEN THE AP IS ACTIVE, THEN THE AP AUTOMATICALLY DISENGAGES. Slide 77 FD/AP Display Control Panels (DCPs) Instructor: Select the buttons on screen for more information. Value DH MDA DH/MDA Ranges Range 0 to 2,500 ft 0 to 16,000 ft

22 Lecture Discussion 22 DH/MDA Preset Values (PUSH PRE Button) Value DH DH (CAT II) MDA Range 200 ft 100 ft 1,500 ft Avionics - Display Control Panel (DCP) Pilot DCP Copilot Course and Heading Select Airspeed and Altitude Select DH/MDA Set DH/MDA Set Knob Slide 78 FD/AP Display Control Panels (DCPs) Barometric Pressure Set Altimeter BARO Set Knob (IN/hPa) PFD Format FMT (PFD Format) Button Bearing Pointer Select BRG (Bearing Pointer) Buttons Navigation Source Select V/L, MLS, FMS (Navigation Source Select) Buttons O VOR1 (power-on default) ADF1 FMS OFF repeat O And Buttons VOR1 (power-on default) ADF1 FMS OFF repeat Slide 79 Guidance Control Panel (GCP) Mode Select Buttons HDG (Heading Select) NAV (Navigation)

23 Lecture Discussion 23 APP (Approach) BC (Back Course) BANK STBY (Standby) FLCH (Flight Level Change) VS (Vertical Speed) ALT (Altitude) VNAV (Vertical Navigation) Nose Up/Nose DN (Pitch Wheel) AP (Autopilot) Pushbutton YD (Yaw Damper) Pushbutton CPL (Couple) AP/FD Annunciations on PFD PFD with Green AP Engaged and Mode Annunciations Slide 80 Guidance Control Panel (GCP) Mode Select Buttons (Cont.) Autopilot Engage Autopilot Disengage Flight Guidance System Caution/Advisory Messages Flight Guidance System Power-Up Test FD Command Cues Modes of Operation Heading Hold Mode Roll Hold Mode Heading Select Mode VOR (NAV) Mode VOR (NAV) Arm Mode

24 Lecture Discussion 24 VOR Approach (VOR APP) Mode FMS-LNAV Localizer (NAV) Mode NAV Intercept NAV Tracking Back Course Mode Slide 81 Automatic Flight Control (Autoflight) Instrument Landing System (ILS) Approach Mode Dual Approach Track Mode ILS Approach Localizer Intercept Preview Mode and Transition Pitch Hold Mode With AP Engaged With AP Not Engaged Vertical Speed (VS) Hold Mode Flight Level Change (FLCH) Mode Altitude Preselect (ASEL) Mode Altitude Hold Mode Vertical Navigation (VNAV) Mode Vertical Flight Level Change (VFLCH) Vertical Altitude Select (VASL) Vertical Altitude Hold (VALT) Vertical Path (VPTH) Mode Go-Around (GA) Mode Slide 82 Indicating AFC-Related messages that can display in the CAS field of the EICAS display.

25 Lecture Discussion 25 Slide 83 Check on Learning 12 Which component supplies environmental data (altitude and speed) to the AFCS? a. MADC (correct answer) b. AHRS c. IRS d. FMS Slide 84 Check on Learning 13 If a Touch Control Steering (TCS) button is pressed and held, the elevator and aileron servo clutches disengage, allowing the pilot to manually fly the aircraft and establish a new reference pitch attitude. a. True (correct answer) b. False Slide 85 Check on Learning 14 Which AFCS component cancels all FD modes and disengages the autopilot and yaw damper? a. GCP STBY mode select button b. AP disconnect buttons c. TCS buttons d. GA switches (correct answer) Slide 86 Check on Learning 15 If the autopilot is engaged, no lateral FD mode is selected, and the bank angle is less than 6 degrees, the autopilot will roll the aircraft to a wings level attitude.

26 Lecture Discussion 26 a. True (correct answer) b. False Slide 87 Module 3 Summary Instructor: Read the module TLO and ELOs and ask the students if they have any questions or concerns about any specific sections. Slide 88 Lesson Conclusion This lesson reviewed the C-146A Avionics Systems.