31A Instrument Systems

 

TTP	B1-L3	ATA31A
Beech 90 Series	B2-L3	Instrument Systems

ELECTRONIC FLIGHT INSTRUMENT SYSTEM 

        Central Display Systems The EFIS consists of three color adaptive flight displays  (AFDs),  two  PFDs  and  one  MFD. The PFDs are AFD-3010s and the MFD is an AFD-3010E. The EFIS has two display control panels (DCPs). The integrated flight information system (IFIS) functions of the EFIS are provided by the file server unit (FSU) and a cursor control panel (CCP).

         The PFD replaces a conventional attitude director indicator (ASI), HSI, altitude indicator (ALI), airspeed indicator (ASI), and vertical speed indicator (VSI). The No. 1 PFD shows the attitude, navigation/compass,  flight control,  primary  air data (that consists of altitude, airspeed, and vertical speed), and TCAS advisory functions for the pilot. The No. 1 PFD receives data bus inputs from both input/output concentrators, (IOCs), both attitude heading systems (AHSs), and both air data systems (ADSs). The No. 1 PFD provides a data bus output to the integrated avionics pro- cessor system (IAPS). The No. 2 PFD operates the same as the No. 1 PFD.

The MFD shows the engine indicating displays, navigation/compass, weather  radar, flight management features such as map/summary checklist, and diagnostic. The MFD also provides a reversion backup for the No. 1 PFD. The MFD receives the same data bus inputs as the No. 1 PFD. The MFD receives a data bus from the MDC. The No. 1 MFD provides a data bus output to the IAPS. The MFD has a discrete connection to the CCP and an ethernet capability to interface with the FSU for IFIS services.

The No. 1 DCP provides the display control inputs for the No. 1 PFD and MFD. The pilot uses the No. 1 DCP to select barometric pressure correction, V-speed reference setting, navigation source selection, bearing source selection, weather radar control, and display range selection. The No. 2 DCP operates the same as the No. 1 DCP. The CCP gives the pilot functional control of the IFIS screens on the No. 1 MFD.

Control of engine data, weather radar operation, navigation sources, bearing pointers, speed references, and altitude references is via the DCP along with the flight display LSKs. When a DCP menu button is pushed, the PFD shows the appropriate menu. While the menu is in view, the PFD LSKs are active. Two DCPs are installed, one for the pilot- side system and one for the copilot-side system. The following are the controls on the DCP:

•  BARO—The   barometric   (BARO)   knob is used to control the barometric pressure setting and to cancel the flight level 180 (FL180) alert. 

 

• REFS—The references (REFS) button selects and remove the REFS menu on the PFD. Two REFS menu pages are available. The REFS 1/2 menu shows Vspeed reference values on the left side of the display and RA MIN, BARO MIN, and Vref settings on the right side of the display. Each of these value settings can be changed by the pilot and selected for display via the REFS menu. The REFS 2/2 page shows units of measurement, METRIC ALT (Altitude) ON/OFF, FL (Flight Level) alert ON/OFF, and FLT Dir (Flight Director) style on the left side.

 

•  MENU SET—The menu set (MENU SET) knob moves the cyan selection box between different controls/menus on the PFD. The LSK on the PFD can also be used to position the cyan selection box.

 

• NAV/BRG—The         navigation/bearing (NAV/BRG)  button  selects  and  removes the  NAV SOURCE and BRG SOURCE menus on the PFD.

 

•  GCS—The   ground   clutter   suppression (GCS) button selects and removes the weather radar GCS feature. The GCS feature automatically times out after 30 seconds.

 

•  TILT—The TILT knob (outer knob) controls the weather radar antenna tilt angle. Electronic stops limit the selected tilt angle.

•  RANGE—The RANGE knob (inner knob) controls the range for navigation and hazard avoidance maps on the PFD and MFD. The display ranges are: 10, 25, 100, 200 and 300 NM.

•  ENGINE—The  ENGINE  button  selects the engine data to be displayed.

The FSU contains the software to operate the IFIS and manage data loading for the other aircraft systems as required. The IFIS obtains weather and other timely data through the optional XM weather receiver or the optional CMU and VHF3.

Remote reversion switches allow the pilot or copilot  to  select  normal  or  cross-side  AHS source input and ADC source input. The PILOT DISPLAY reversion switch engages the PFD compressed display on the pilot PFD or the MFD.

 An impending stall speed (ISS) low speed cue (LSC) marker for indicated airspeed shows on the airspeed tape when airborne. The LSC is advisory in nature and is not a substitute for a stall warning system. The ISS LSC marker is constantly positioned from the bottom of the airspeed tape to the current ISS LSC value. The marker becomes emphasized and the airspeed digital readout turns red when the airspeed gets significantly below the ISS LSC value. The ISS LSC value for the King Air C90GTi is based on the following flap positions:

•  Flaps up ISS LSC..........................88 KIAS

•  Flaps approach ISS LSC...............83 KIAS

•  Flaps down ISS LSC.....................78 KIAS

The electronic flight instrument system (EFIS) consists of three adaptive flight display (AFD) panels, two cursor control panel (CCP) units, one multifunction keyboard panel (MKP) unit, and four single knob panel (SKP) units. The EFIS is controlled by a combination of a touchscreen interface and dedicated hard keys. Some functions of the system may be performed by using the keys, buttons on the touchscreens, or with a combination of both methods.

ADAPTIVE FLIGHT DISPLAY (AFD)

The AFD is an integrated “smart” display unit used for primary flight display (PFD) and multi- function display (MFD). Three AFD panels are installed across the cockpit. Each AFD is a touch screen allowing interactive control of display functions. Each AFD may be referred to as a Display Unit (DU), and numbered DU1 (left PFD), DU2 (center MFD) and DU3 (right PFD). In addition to the normal display functions, the AFD is a multiprocessor computing platform capable of hosting other functional software. Each AFD has five core processors operating independently; each processor utilizes shared memory for moving data between the processing zones, allowing each processor to have control over its own operations.

 All displays have a wide viewing angle and high contrast  such  that  they  are  clearly  interpreted when viewed from either pilot position. The PFDs provide the display of primary attitude, heading, altitude, airspeed, navigation, flight guidance, and pilot selectable formats. The MFD provides display of engine indication, crew alerting messages, and pilot selectable formats. Pilot selectable formats include maps, charts, weather, navigation data, maintenance information, and checklist.

All displays have a wide viewing angle and high contrast such that they are clearly interpreted when viewed from either pilot position. The PFDs provide the display of primary attitude, heading, altitude, airspeed, navigation, flight guidance, and pilot selectable formats. The MFD provides dis- play of engine indication, crew alerting messages, and pilot selectable formats. Pilot selectable for- mats include maps, charts, weather, navigation data, maintenance information, and checklist.

 

The applications hosted by the PFD include the following:

•  Attitude direction indicator (ADI)

•  Horizontal situation indicator (HSI)

•  Crew alerting system (CAS)

 

•  ECDU  for  Datalink  and  controller  pilot data link communications (CPDLC)

•  Electronic checklists (ECL)

•  Engine indication system (EIS)

 

•  Flight management system (FMS) (includ- ing LPV)

•  Integrated flight information system (IFIS)

•  Radio tuning system (RTS)

•  Synoptic (SYN)

•  Synthetic vision system (SVS)

•  Topographical maps

•  TAWS

The applications hosted by the MFD include the following:

•  Application license manager (ALM)

 

•  Attitude direction indicator (ADI) & hori- zontal situation indicator (HSI)

•  Crew alerting system (CAS)

•  Electronic checklists (ECL)

 

•  Engine indication system (EIS) and synoptic (SYN)

•  Integrated flight information system (IFIS)

•  Onboard maintenance system (OMS)

•  Radio tuning system (RTS)

•  Topographical maps (TOPO)

FLIGHT DISPLAY SYSTEM APPLICATION (FDSA-6500)

 

The  flight display  system  is  comprised  of  the flight display system application (FDSA) functional  software hosted on processor 1 of each AFD. The outboard displays are called primary flight displays (PFD). The center display is called a multifunction display (MFD).

 The display window manager (DWM) software coordinates the display of different formats on the AFD screen. These format configurations are selected based on pilot selection and availability of applications. In the event of a failure, DWM will automatically execute a display reversion algorithm to maintain a safe flight deck for the pilots. The  inboard  and  outboard  displays  can also be reconfigured manually by the pilots using switches located on the flight deck.

 The PFD software provides the functionality that is traditionally known as the PFD on a half- page window. This is divided into two components: the ADI and the HSI. The ADI features include airspeed, attitude, altitude, vertical speed, flight control annunciations, flight director, lateral and vertical deviation, marker beacon, radio altitude, ground speed, true airspeed, and navigation per- formance functionality. The HSI features include compass, heading, course, elapsed time, navigation, and bearing information functionality.

The FDSA software is controlled using touch- screen control, or using the CCP, SKP, and MKP in conjunction with on screen menus and multi- function window (MFW) touchscreen buttons.

 The PFD has touchscreen hotspots that allow direct touch control of the most commonly used PFD functions. Five large hotspots are presently defined. The hotspot areas are highlighted when the display is touched in an open area  of the sky/ground background. The visual cue persists for approximately one second after the touch is released. Touching the HSI area toggles the HSI between an HSI or MAP format. Touching the navigation source readout allows selection of the available navigation sources. Touching the over- lay readout allows selection of map overlays such as traffic, weather, and lightning. Touching the bearing pointer readout allows the user to select the navigation source to be shown on the bearing pointers.

 The engine indication system (EIS) software provides full-time display of critical engine data, non-critical  engine  data,  and  non-engine  data. The displayed data consists of Torq, ITT, Prop, N1, Fuel Flow, Oil Press, and Oil Temp.

 The Nav Master software keeps track of the pilot selectable  layers  of map information,  provides the necessary selection menus for map overlays, controls the navigation display formats, and controls navigation source selection. The Nav Master provides selection and control of the PFD Task Menus, and provides range control.

 The built-in-test  equipment (BITE)/maintenance software provides the power- up and runtime diagnostic functionality for the AFD. This software will monitor and report through the adaptive flight display runtime (AFDR) health monitor function any detected hardware or software faults.

 

 MULTIFUNCTION KEYBOARD PANEL (MKP)

 

The MKP is used by the flight crew to enter alphanumeric data into the FMS or other on-screen entry fields. In addition, the MKP provides several quick access keys (QAKs) to enable quick MFD window control. Other functions include a dedicated pan / range control for map and charts, as well as FMS action keys (Cancel, Message, Execute). Hard keys are also provided for CAS expand/ collapse control and numeric radio tuning.

CURSOR CONTROL PANEL (CCP)

 

The CCP is used by the flight crew to allocate a cursor to a display, move the cursor under tabbing or free-floating control, and select / operate on-screen controls. The CCP is designed to work with the AFD tabbed-cursor user interface.

 

The CCP provides the following front-panel functions:

 

•  Cursor selection on the on-side or center display by the “PFD” and “MFD” buttons

•  Tab Cursor movement (forward / backwards) by rotation of the large outer “TAB” knob

 

•  Character-by-Character or numeric data entry by rotation of the large inner “DATA” knob

 

• Display item selection or activation by pressing the large inner “DATA” knob

•  Display  of  an  on-screen  menu  by  the“MENU” button

 

•  Closing on-screen menus, dialog boxes, or edits by the “ESC” button

 

•  Display radio tuning (megahertz) by rota- tion of the small outer “TUNE” knob

 

•  Display radio tuning (kilohertz) by rotation of the small inner “TUNE” knob

 

•  Radio tuning swap function by pressing the small inner “TUNE” knob

 

•  Display of traffic on the on-side display by the “TFC” button

 

•  Smooth cursor movement (all angle, force sensitive) by lateral translation of the large knob assembly

 

 SINGLE KNOB PANEL (SKP)

 

The SKP is a single knob with a push select switch used as a BARO SET control and as a radar TILT control.

When used as a BARO SET control, the SKP pro- vides the following functions:

 

•  Manual barometric setting by rotation of the knob (when aircraft is in manual baro mode)

 

•  Preset barometric setting by rotation of the knob (when aircraft is in STD baro mode)

•  Toggle   between   manual   and   standard (STD) baro mode by pressing the knob

 

When used as a radar TILT control, the SKP pro- vides the following functions:

•  Toggle between manual and auto tilt operation

•  Adjustment of manual radar tilt up or down

 

 

REVERSION SWITCH PANEL FUNCTIONAL DESCRIPTION

 

The aircraft  reversion switch  panel provides the following functions. Note that since the RSP is certified as part of the aircraft, not all functions may be included, or others may be added at OEM option.

 

• Display reversion control and power-off (forces manual display reversion) – one per display.

 

•  Air Data Reversion – one per side. Selects between on-side and cross side air data.

 

• AHS Reversion – one per side. Selects between on-side and cross side attitude data.

 

•  Touchscreen disable – one per display, dis- ables touchscreen for cleaning or due to malfunction.

 

•  CCP/Touch  Display  Control  Inhibit  or Touch PFD due to malfunction or for cleaning.

 

•  Directional Gyro Normal / DG switches – one per AHRS. Switches heading from a slaved to free (DG) mode.

 

•  Slew +/- switches – one per AHS. Allows adjustment of heading when in DG mode.

•  Emergency Tuning – one per aircraft. Tunes

COM1 to 121.5 MHz.

    •  Pilot Static Air Source Alternate

The engine indication crew alerting system (EICAS) window is a dedicated display that shows an integration of engine instruments, temperature information and the Crew Alerting System (CAS) messages. The EICAS display is divided into four areas, separated by thin gray lines. The displays are as follows:

•  Torque

•  Interstage Turbine Temperature (ITT)

•  Propeller RPM

•  Prop syncrophaser display

•  N1

•  Fuel Flow

•  Oil Pressure

•  Oil Temperature

 

• Air Temperature: Static Air Temperature (SAT), International Standard Atmosphere (ISA) deviation, Ram Air Temperature (RAT).

 

•  Crew Alerting System messages: Warnings (red), Cautions (amber), Advisories (cyan), and Status (white).

The engine parameters displayed are color coded to correspond to their respective ranges and limits. While the parameters are in the normal range the indications will display in green. When reaching, or exceeding, the parameter limits the display will change to amber or red depending on the nature of the exceedance.

The CAS messages are shown in order of priority. Warnings at the top of the list followed by Cautions, Advisories, and Status messages. New messages are highlighted in inverse video.

The CAS quick access key located on the Multifunction Keyboard Panel (MKP) is used to expand the Crew Alerting System (CAS) list into the Multifunction Window (MFW). Subsequent push will contract the CAS list. Upon the failure of an outer PFD, display reversion occurs and the data shows on the MFD and the non-failed PFD.

The  crew  alerting  system  (CAS)  provides  the crew with plain text messages for WARNING (red),  CAUTION  (amber), ADVISORY  (cyan) and STATUS (white) alerts. Two red MASTER WARNING flashers located in the glareshield (one in front of the pilot and one in front of the copilot) are a part of the system, as are two amber MASTER CAUTION flashers (located just inboard of the MASTER WARNING flashers). CAS messages are tested by pressing the placarded, ANNUN - PRESS TO TEST button, located on the overhead light panel.

 

WARNING CAS messages (red) will cause both MASTER WARNING flashers to illuminate and a Warning Aural Tone (triple chime) to sound. When a WARNING message illuminates, it will flash until the MASTER WARNING is reset by pushing the MASTER WARNING flasher switch. If the  condition which caused the WARNING message to illuminate is corrected prior to reset- ting the MASTER WARNING, the CAS message and MASTER WARNING will extinguish. WARNING messages on the PFD (TCAS/TAWS) have assigned voice aural alerts which will not be preceded by a Warning Aural or MASTER WARNING flasher.

 

CAUTION  CAS  messages  (amber)  will  cause both MASTER CAUTION flashers to illuminate and a Caution Aural Tone (single chime) to sound. When a CAUTION message illuminates, it will flash until the MASTER CAUTION is reset by pushing the MASTER CAUTION flasher switch. If the condition which caused the CAUTION message to illuminate is corrected prior to resetting the MASTER CAUTION, the CAS message and MASTER CAUTION will extinguish.

 

Aural alerts (voices and tones) are prioritized by importance. If a lower priority WARNING or CAUTION message is active without being reset, and a higher priority WARNING message becomes active, the audio system will complete the lower priority aural message and then play the higher priority one. If two or more messages are active at the same time, and a higher priority aural alert is playing, pressing the MASTER WARNING/MASTER

CAUTION flasher switch will acknowledge all of the appropriate CAS messages.

 

ADVISORY  CAS  messages  are  cyan  and  do not trigger MASTER CAUTION or MASTER WARNING lights.

 

STATUS CAS messages are white and do not trigger MASTER CAUTION or MASTER WARNING lights.

 

The red MASTER WARNING and amber MASTER CAUTION flashers feature both a “bright” and a “dim” mode of illumination intensity. The “dim” mode will be selected automatically whenever all of the following conditions are met: a generator is on the line; the OVERHEAD FLOOD LIGHTS are OFF; the PILOT INSTR PNL lights are ON; and the ambient light level in the cockpit (as sensed by a photoelectric cell located in the overhead light control panel) is below a preset value. Unless all of these conditions are met, the “bright” mode will be selected automatically.

 

The CAS messages in the crew alerting and warning system should be tested before every flight, and anytime the integrity of a CAS message is in question. Depressing the ANNUN - PRESS TO TEST button, located on the overhead panel, illuminates all the CAS messages, MASTER WARNING flashers, and MASTER CAUTION flashers. Any lamp that fails to illuminate when tested should be replaced.

The CAS messages are shown in order of priority. Warnings at the top of the list followed by cautions, advisories, and status messages.

The Cursor Control Panel is used by the flight crew to allocate a cursor to a display, move the cursor under tabbing or free-floating control, and select / operate on-screen controls.

WINDOW MANAGEMENT

WINDOW SIZES

The window sizes are referred to as full, half, and quarter size. MFWs do not match up exactly with the full display, half of the display, or quarter of the display space. Other aspects of the display, such as the EICAS format and the touchscreen tool bar also take up display space and prevent, for example, a half size MFW from occupying exactly half of the display space. The window size indicates  the physical dimensions of the window and therefore the corresponding display space that a window receives. Window size is managed to maintain consistency with the window format displayed within the window. Not all window formats are available for all window sizes. Full window size formats will occupy the entire area of a display allocated for the MFWs. Half window size formats will occupy the left or right half of a displays area allocated for the MFWs and quarter window size formats will occupy a corner quarter of a displays area allocated for the MFWs.

 

PFD SIZE

 

If either PFD1 or PFD2 fails, the MFD will automatically switch to a reverted PFD format. Similarly, if the MFD fails, PFD1 and PFD2 will automatically switch to a reverted PFD format. The reverted PFD format contains a full display height by half window width PFD layout. If the EICAS format on the center display is invalid, the outboard displays will automatically switch to a reverted PFD format to display the EICAS format.

ADI SIZE

 

The ADI is composed of static symbols and dynamic symbols. ADI consists of: Sky/Ground, Horizon Line, Aircraft Symbol, Attitude in Alignment Annunciation, Pitch (Tape and Pitch Target Markers), Roll (Pointer and Scale), Half Bank, Slip/Skid, Miscompare Flags and Fail Flags. The attitude indication is displayed as part of the PFD. The vertical height of the ADI is fixed, and does not expand to keep the flight path vector (FPV)conformal longer when the FPV is displayed far below the aircraft center.

 MFW SIZE 

 Selection of the MFW sizes are provided via the Format Selection Dialog Box.

EICAS FORMAT

 

The EICAS format is displayed as one of the following formats:

•  Primary EICAS format

•  Expanded EICAS format

 

When all displays are available, the EICAS format will be displayed on the left outboard side of MFD. If the MFD fails then both PFD1 and PFD2 goes into a reverted mode in which the EICAS window is displayed in the middle of the PFDs. If the center FDSA is not receiving valid A661 from the local EICAS and is not receiving valid A661 from either outboard AFDs EICAS, then the outboard AFDs will display the EICAS format.

 

The expanded CAS format consists of the primary EICAS format with a CAS expansion panel pop-out window. The CAS expansion panel popout extends out of the primary EICAS format towards the MFW format when the expanded EICAS format is displayed. The CAS expansion panel pop-out is overlayed on top of the associated MFW format.

PTP  Beech 90 Series	B1	LOC	FOT	SGH	R/I	MEL	TS
	B2	LOC	FOT	SGH	R/I	MEL	TS