Multifunction Display (MFD)

• MFD refers to Multifunction Display

Multifunction Display

• An MFD is a 6x8 inch active area color, NVG-compatible display
• The cockpit configuration for the MH-65E consists of a dual MFD configuration (inboard/outboard) for both the pilot and copilot
• It enables the aircrew to maintain a high state of situational awareness and integrated control of the aircraft while maintaining a heads-up posture
• The MFDs provide pilot interface and display control for flight/navigation symbology, tactical sensor video, and aircraft systems
• Aircraft systems include engine, fuel, and power train
• It also manages the engine indicator and crew alert system as well as communication preset lists
• The MFDs are numbered from left to right, 1 through 4

Operating Modes

Primary Flight Display

• The Primary Flight Display (PFD) includes several key indications
• These are attitude directional indication (ADI), airspeed indication, barometric altimeter (BARALT), instantaneous vertical speed indication (IVSI), radar altimeter (RADALT), and Triple Tach, etc
• Other components are the horizontal situation indication (HIS), traffic collision avoidance system (TCAS), and Torque Indication

Attitude Directional Indication

• An attitude directional indicator contains the aircraft reference indicator, pitch scale indicator, roll/sky pointer, and slip/skid indicator in the center of the display
• The aircraft reference indicator contains a white continuous welded wing with center bull's-eye
• It is centered when wings level and zero pitch, horizontally aligned, and located at the center of the attitude display providing a zero-pitch angle reference
• The pitch scale indicator displays major scale markings with numeric markings for every 10 degrees of pitch for the first 40 degrees in the positive direction and the first 20 degrees in the negative direction
• Minor markings present for every 5 degrees of pitch for the first 45 degrees in the positive direction and the first 25 degrees in the negative direction

Airspeed Indication

• The airspeed display is located on the left side, displaying indicated airspeed data from the Airspeed Unit (ASU)
• The data includes the airspeed tape and digital readout
• White minor markings are displayed for every 5 knots, and white major markings are shown alongside numerical labels for every 10 knots of airspeeds
• These labels show airspeeds of 20 knots and higher
• The current airspeed is displayed in knots in the Airspeed Window digital readout over the range of 20 to 500 knots
• Outside that range, the readout changes

Barometric Altimeter

• Altitude data is displayed inside the altitude window on the right side of the screen
• The altitude display comprises the altitude tape and the pilot adjustable barometric setting window
• The barometric corrected altitude data is provided via the altitude tape, which displays white tick marks accompanied by white digits every 100 feet
• The altitude window contains a digital readout of the barometric corrected altitude data in the center of the altitude tape
• The digital readout has large rolling white digits with increments of 20 feet on a black background
• The digital readout displays over the range of -1,500 to 55,000 feet
• Ouside this range a white dash mark is displayed instead
• The barometric setting window, located at the bottom of the altitude display, is the bottom right corner of the active DU screen
• The barometric setting range is from 22.00 to 32.00 inHg
• inHg signifies inches of mercury

Instantaneous Vertical Speed Indication

• IVSI helps pilots monitor an aircraft's altitude and rate of climb or descent in real time
• They are especially useful during dynamic flight maneuvers, such as rapid climbs or descents

Radar Altimeter

• The RADALT system consists of a receiver/transmitter, antenna system, and indicators in the PFD display on both sides of the cockpit
• The receiver/transmitter provides altitude and validity output to the MFDs, CDUs, and DCUs
• The radar altitude digital readout is color-coded in relation to the radar altitude low setting indicator
• For white, the current radar altitude value is more than 10 ft above the radar altitude low setting indicator
• For yellow, the current radar altitude value is less than 10 ft above the radar altitude low setting indicator
• For red, the readout is when the current radar altitude value is at or below the radar altitude low setting indicator

Triple Tach

• The NR (rotor speed) is indicated on each PFD triple tach display as the center tape
• It has a digital readout of NR at the top, and it is designed so that at normal operating limits each scale is adjusted to show one horizontal line for ease of monitoring
• A FADEC overspeed safety feature will shut down an engine at 429 RPM ±4 RPM N2/NR
• This also includes an added safety measure that will not allow the shutdown of the second engine if/when it subsequently reaches this limit

Horizontal Situation Indication

• Heading data is represented on the PFD by an HSI reference aircraft, a compass rose, and a lubber line digital readout with lubber line
• The heading display capability also includes a true heading reference indicator that is displayed when the magnetic/true setting is TRUE
• A reference heading indicator and reference heading/reference track digital readout, plus a full compass rose (360 degrees) and an arc (80 degrees) compass

Traffic Collision Avoidance System

• TCAS monitors the airspace around the aircraft advising the aircrew of nearby transponder equipped (Modes A, C, and S) aircraft that may pose a collision threat
• TCAS operates without support from ATC ground stations
• The system displays traffic alerts/advisories on the MFD TCAS display using color-coded symbols and text
• It provides aural alerts to assist the crew in avoiding midair collisions
• Tracking is performed by repetitious TCAS interrogations in Mode C format
• When interrogated, transponders reply after a fixed delay
• Measurement of time between interrogation transmissions and reply

Torque Indication

• Torque data is represented on the PFD by a scaled analog tape (total torque) and Engine No. 1 and No. 2 digital readout
• Additionally, limit lines are provided for maximum continuous power, maximum takeoff power, and 4-second maximum transient power operating limits
• In the AEO Condition, the torque display analog tapes are color-coded based on the current torque value as related to the operational limit lines for dual-engine operation. The portion of the tape below the max continuous power limit line, e.g. yellow solid line at 88% total torque)is green. the portion of the tape above the max continuous power limit line but below the max takeoff limit line is yellow. the portion above the max takoff limit line, e.g. red solid line at 100% is red
• One Engine Inoperative Mode (OEI) is defined as an engine being operated at less than 40% N1

One Engine Inoperative Mode

• During single-engine operations, degraded engine operations, or a major FADEC failure, the FADEC can adjust the N1 limits to permit one of three modes
• The three modes are OEI CT or Continuous OEI with standard day available torque, 66.3%
• OEI LO or 2-minute OEI, standard day available torque 75.5%
• OEI HI or 30-second OEI, standard day available torque, 77.7%.

Navigation Page

• Pressing the key R8 on the FP SUM page will access the FP SUM - FPLN FUEL & POWER MGMT page The FP SUM - FPLN FUEL & POWER MGMT page shows an overview for fuel and power requirements
• It gives assigned FPPs and values needed to complete the FPLN

Flight Plan Fuel Summary Page

• This page displays the FPP number/LEG, FPP ID/IDENT, aircraft weight by the end of the leg/GW, plus predicted fuel used for the active leg of the active fly plan
• The fuel estimation is based on the predicted fuel from the present position to the end of the active leg
• It also gives remaining fuel at the end of a given leg/RMNG, the amount of fuel required at the end of a leg to completion/BNGO, and maximum torque available/RQD

Flight Plan Summary Page

• To access the FL SUM page, press the FP SUMM Key on the top row of the MFD
• The page provides the capability to plan and execute an active flight plan and alternate plans
• Real-time navigation and sensor inputs perform the functions of the active flight plan

FPP Display

• The MFD Flight Plan Summary creates active flight plan FPPs that are displayed on the Navigation page as follows:
• A Cyan color represents past FPPs
• Magenta represents current and future FPPs -Yellow represents a Computer Error or variables that were not possible given the current information

Map Orientation

• The limitations of the MFD Flight Plan Display Page:
• The Flight Plan display uses a variety of points and variables which include legs, search and rescue points, direction, heading
• There a several different map overlays that can be selected such as wind data, range rings, or FD overlays.

MFD Overlays Menu

• The various MFD menus allow the pilot to modify symbology, waypoint altitudes, map overlay details such as terrain awareness, or control display features

Video Page

• The Video Page uses a variety of different input types that the pilot can select. These inputs can be from EOIR, Auxillary camera, Hoist Camera, and Heads-up Camera

Communications Page

• The MFD Communications Page provides a list of all the available Communication (CM), and High Frequency
• Selecting the tune key will tune the A/C radio to the highlighted preset
• The CHNL(channel) keys move the highlighted green indicator up and down depending on what preset is needed

Status Page

• The MFD Status Page provides an indication of the status of LRUs and indicates the conditions
• Green means the LRU is fully functional, amber means the LRU is degraded, red means the LRU failed, and white means the status is unknown
• Pressing the STAT key will reset all of the LRU status words

ADC Navigation Source

• ADC1 are in the primary source for a copilot display. ADC2 is the primary source for a pilot's display. The ADCs are generally the source for airspeed and altitude data as well as the backup source for vertical speed. The ADCs are located in the AV Rack and measure the temperature by using 2 sensors on the aircraft nsoe.

EICAS

• The Engine Indication and Crew Alerting System is the page which can be used to provide engine and mechanical information to the flight crew. Some of the provided information includes the hydraulic data, the fuel and electrical power data, etc. The EICAS mode will manage the aricraft status and exceedance management
• The Engine and Gearbox data is represented by analog tapes and digital readouts.
• The parameters can be indicated in green, yellow, and red If below a yellow line, the tape is yellow; if normal it is green; and if above a yellow line then it is red

Hydraulic Indications

• Hydraulic pressure is indicated on the Hydraulics page, showing both primary and secondary pressure with highest and lowest pressures
• Color coding shows the current health of the hydraulic system