Avionics Manual for Piper PA-44 Seminole

through the propeller shaft to maintain constant RPM settings. The governor controls engine speed by varying the pitch of the propeller to match load torque. to engine torque in response to changing flight conditions. Each propeller is controlled by the propeller control levers located in the center of the power control quadrant. Feathering a propeller is accomplished by moving the control fully aft through the low RPM detent into the FEATHER position. Unfeathering is accomplished by moving the propeller control forward. This releases oil accumulated under pressure and moves the propeller out of the FEATHER position. ISSUED: November 3, 2016 REVISED: October 1, 2018 REPORT: VB-2636 7-3 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.5 ENGINES AND PROPELLERS (continued) Unfeathering Accumulators Unfeathering accumulators store engine oil under pressure from the governors, which is released back to the governors for propeller unfeathering when the propeller control lever is moved out of the feathered position. A feathering lock, operated by centrifugal force, prevents feathering during engine shutdown by making it impossible to feather any time the engine speed falls below 950 RPM. For this reason, when feathering a propeller in flight, the pilot must move the propeller control into the FEATHER position before the engine speed drops below 950 RPM. 7.7 ENGINE CONTROLS Engine controls consist of a throttle, a propeller control and a mixture control lever for each engine. These controls are located on the control quadrant on the lower center of the instrument panel where they are accessible to both the pilot and the copilot (Figure 7-1). The controls utilize teflon-lined control cables to reduce friction and binding. The throttle levers are used to adjust the engine manifold pressure. A gear up warning system, triggered by low manifold pressure, is intended to alert the pilot of an impending gear up landing. Whenever manifold pressure drops below 14 in Hg with the landing gear not down and locked, a CHECK GEAR CAS message is activated along with a continuous CHECK GEAR aural alert. If the airplane is higher than approximately 400 feet AGL, the CAS CAUTION is triggered. Below 400 feet AGL, the CAS WARNING is triggered. Since this low manifold condition might be experienced during normal descent, the CHECK GEAR aural alert may be muted by pressing the appropriate acknowledge softkey on the PFD. Once muted, the aural alert is silenced, but the associated CHECK GEAR CAS text message will remain present until manifold pressure is increased, or the gear is deployed. All throttle operations should be made with a smooth, not too rapid movement to prevent unnecessary engine wear or damage to the engines. REPORT: VB-2636 ISSUED: November 3, 2016 7-4 PA-44-180, SEMINOLE 7.7 ENGINE CONTROLS (continued) THROTTLES CONTROL QUADRANT Figure 7-1 SECTION 7 DESCR/OPERATION PROPELLERS MIXTURES FRICTION ADJUSTMENT LEVER (Right side of Quadrant) ALTERNATE AIR The propeller control levers are used to adjust the propeller speed from high RPM (low pitch) to feather (high pitch). The mixture control levers are used to adjust the air to fuel ratio. An engine is shut down by the placing of the mixture control lever in the full lean (cut-off) position. The friction adjustment lever on the right side of the control quadrant may be adjusted to increase or decrease the friction holding the throttle, propeller, and mixture controls, or to lock the controls in a selected position. ISSUED: November 3, 2016 REVISED: December 15, 2017 REPORT: VB-2636 7-5 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.7 ENGINE CONTROLS (continued) The alternate air controls are located on the control quadrant just below the engine control levers. When an alternate air lever is in the up, or CLOSE, position the engine is operating on filtered air; when the lever is in the down, or OPEN, position the engine is operating on unfiltered, heated air. The cowl flap control levers (Figure 7-3), located below the control quadrant, are used to regulate cooling air for the engines. The levers have three positions: full open, full closed, and intermediate. A lock incorporated in each control lever, locks the cowl flap in the selected position. To operate the cowl flaps, depress the lock and move the lever toward the desired setting. Release the lock after initial movement and continue movement of the lever. The control will stop and lock into place at the next setting. The lock must be depressed for each selection of a new cowl flap setting. REPORT: VB-2636 7-6 PULL-CLOSE COWL L R FLAP PUSH-OPEN COWL FLAP CONTROLS Figure 7-3 ISSUED: November 3, 2016 REVISED: December 15, 2017 PA-44-180, SEMINOLE SECTION 7 DESCR/OPERATION 7.9 GARMIN G1000 AVIONICS SYSTEM NOTE Refer to the latest appropriate revision and -XX part number of the Garmin G1000 Pilot's Guide for the Piper PA-44 Seminole, (Garmin P/N 190-02198-00) for complete descriptions of the G1000 integrated avionics system and operating procedures. The Garmin G1000 Integrated Avionics System consists of a Primary Flight Display (PFD), a Multi-Function Display (MFD), an Audio Panel, an Attitude and Heading Reference System (AHRS), an Air Data Computer (ADC), and the sensors and computers to process flight and engine information for display to the pilot. The system contains dual GPS WAAS receivers, dual VOR/ILS receivers, dual VHF communications transceivers, a transponder, and an integrated crew alerting system (CAS) to alert the pilot of advisory, caution and warning messages. The G1000 system also provides System Message Advisories, which | alert the pilot to abnormalities associated with the G1000 system. The G1000 system also has a terrain proximity system, Traffic Information Service (TIS) and FliteCharts. Optional avioncs equipment include ADF, DME, Class B TAWS, Traffic Advisory System (TAS), Surface Watch, Jeppesen ChartView, Synthetic Vision, AOPA Facilities Directory, Flight Stream 510 WiFi and Bluetooth® connectivity, and the Garmin Datalink (GDL) for XM weather and music. Primary Flight Display The Primary Flight Display (PFD) displays airspeed, attitude, altitude, and heading information in a traditional format. Slip information is shown as a trapezoid under the bank pointer. One width of the trapezoid is equal to one ball width slip. Rate of turn information is shown on the scale above the rotating compass card; a standard rate turn is accomplished when the turn rate trend vector stops at the second tick mark (standard rate tick mark). OAT information is presented in the lower left corner of the PFD. The measured value of OAT is adjusted for probe recovery factor and ram air effects to indicate static air temperature. ISSUED: November 3, 2016 REVISED: October 1, 2018 REPORT: VB-2636 7-7 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.9 GARMIN G1000 AVIONICS SYSTEM (continued) Primary Flight Display (continued) The primary function of the PFDs is to provide attitude and heading data from the Attitude and Heading Reference System, air data from the Air Data Computer, and navigation and alerting information. Synthetic Vision and Pathways may be utilized to increase situational awareness. The following controls are available on the PFD (clockwise from top right): Communications frequency volume and squelch knob • • • • Communications frequency transfer button Communications frequency set knobs Altimeter (BARO) setting knob (large knob) ⚫ Course knob (small knob) • Map range knob and cursor control • FMS control buttons and knob • Flight planning buttons ⚫ PFD softkey buttons • Altitude reference set knob • Heading bug control • Navigation frequency set knobs • Navigation frequency transfer button • Navigation frequency volume and Identifier knob The primary function of the VHF Communication portion of the G1000 is to enable external radio communication. The primary function of the VOR/ILS Receiver portion of the equipment is to receive VOR, Localizer, and Glide Slope signals. The primary function of the GPS portion of the system is to acquire signals from the GPS and WAAS satellites and process this information in real-time to obtain the user's position, velocity, and time. This GPS WAAS is certified under TSO C146a and therefore is qualified as a primary navigation system. The PFD also displays autopilot status and mode annunciation, at the top, center of the display. REPORT: VB-2636 ISSUED: November 3, 2016 7-8 PA-44-180, SEMINOLE SECTION 7 DESCR/OPERATION Primary Flight Display (continued) Attitude and Heading Reference System (AHRS) The AHRS uses rate sensors, air data, GPS data and magnetic variation to calculate pitch, roll, heading and sideslip. The AHRS incorporates internal monitors to continually validate the information it sends to the flight displays. If a failure is detected, a red X will be displayed in place of the incorrect information. If the pilot suspects the validity of an indication that has not been invalidated by the internal monitors, he should cross check related indications on the PFD and the standby instrument to verify the suspect information. If the entire AHRS unit fails, a red X will be displayed over the attitude and heading indicators. The AHRS may be re-set in-flight and will align while the airplane is in motion. Alignment will occur quicker if the wings are kept level during the alignment process. Note that if the AHRS fails, the course pointer on the HSI will point straight up. The CDI will still function properly and course may still be set using the digital window. Air Data Computer (ADC) The ADC provides airspeed, altitude, vertical speed, and air temperature to the display system, the traffic systems and the flight management system. The ADC incorporates internal monitors to continually validate the information it sends to the flight displays. If a failure is detected, a red X will be displayed in place of the incorrect information. If the pilot suspects the validity of an indication that has not been invalidated by the internal monitors, he should cross check related indications on the PFD and the standby instrument to verify the suspect information. If the entire ADC unit fails, a red X will be displayed over altitude and airspeed indicators, and a yellow X will be displayed over the vertical speed indicator. ISSUED: November 3, 2016 REPORT: VB-2636 REVISED: December 15, 2017 7-9 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE Primary Flight Display (continued) Crew Alerting System (CAS) Messages The Crew Alerting System (CAS) consists of Master Warning and Master Caution indicators operating in conjunction with CAS messages and aural alerts. The Master Warning and Caution indicators are located on the lower right softkey of the PFD. CAS messages appear on the lower right side of the PFD during normal and reversionary mode operations. They are categorized as warning, caution or advisory and are prioritized in the following order: Warning (Red) Messages - appear at the top of the message stack Caution (Amber) Messages - appear in the middle of the stack Advisory (White) Messages appear at the bottom of the stack Warning (Red) Messages - Warning conditions are conveyed via a flashing (red) Master Warning indicator, a repeating triple chime and either a flashing (inversely red on white) CAS message or a flashing EIS gage indication. Warnings may be acknowledged by pressing the lower right softkey on the PFD. When acknowledged, the Master Warning indicator will extinguish, and the aural chime will silence. If applicable, the CAS message will stop flashing and will revert to normal (red on black) text. Warning CAS messages persist until the initiating condition is removed. A Warning is triggered whenever a gage on the Engine Indication System (EIS) exceeds a red line. In this event, the Master Warning indicator and triple chime are triggered (and acknowledged) normally, but without an accompanying Warning CAS message. Instead, the appropriate EIS gage will flash until the exceedance is removed. REPORT: VB-2636 7-10 ISSUED: November 3, 2016 REVISED: October 1, 2018 PA-44-180, SEMINOLE Primary Flight Display (continued) SECTION 7 DESCR/OPERATION Crew Alerting System (CAS) Messages (continued) Caution (Amber) Messages Caution conditions are conveyed via a flashing (amber) Master Caution indicator, a non-repeating double chime and either an inverse (black on amber) CAS message or a flashing EIS gage indication. Cautions may be acknowledged by pressing the lower right softkey on the PFD. When acknowledged, the Master Caution indicator will extinguish, and if applicable, the CAS message will will revert to normal (amber on black) text. Caution text messages persist until the initiating condition is removed. A Caution is triggered whenever a gage on the Engine Indication System (EIS) enters the yellow range. In this event, the Master Caution indicator and double chime are triggered (and acknowledged) normally, but without an accompanying Caution CAS message. Instead, the appropriate EIS gage will flash until the exceedance is removed. Advisory (White) Messages Advisory messages are conveyed via a non-repeating single chime and a (white on black) text message. Advisory CAS messages do not require acknowledgment and will persist until the initiating condition is removed. System Annunciations System Annunciations do not trigger Warning or Caution indications and do not require pilot action to acknowledge. These annunciations are typically divided into two categories: • Hardware or functional failures, indicated graphically with text or yellow "X" over the failed display. Optional systems alerts such as those generated by terrain awareness or traffic avoidance systems. These annunciations and alerts are indicated in accordance with their system descriptions. ISSUED: November 3, 2016 REPORT: VB-2636 REVISED: October 1, 2018 7-11 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE Primary Flight Display (continued) Aural Alerts The G1000 system generates the following aural alerts: Master Warning - Repeating triple chime. • Master Caution - Non-repeating double chime. • • • Advisory - Non-repeating single chime. Autopilot disconnect and preflight test complete (warble tone). ⚫ TAWS, Terrain, and Obstacle cautions/warnings and various voice alerts. • Traffic System various voice alerts. • Airspeed greater than VNE - "Airspeed...Airspeed" voice alert. • Low airspeed - Airspeed voice alert of an impending underspeed condition (if equipped with optional Underspeed Protection). Stall Warning - "Stall...Stall" voice alert. • • • “Five-hundred" voice alert - when aircraft descends within 500 feet above the terrain or runway threshold. - "Minimums..Minimums" voice alert when the aircraft reaches MDA/DH if set by the pilot. ⚫ "SurfaceWatch" voice alerts (if Surface Watch installed). ⚫ "Timer Expired" voice alert when countdown timer reaches zero. • "Vertical Track” voice alert when aircraft is one minute from VNAV Top of Descent. ⚫ "CHECK GEAR" voice alert - In flight when the manifold pressure is 14 inches of mercury or below and the landing gear selector is not in the DOWN position. ⚫ “CHECK GEAR" voice alert - In flight when the flaps are extended more than 10° and the landing gear selector is not in the DOWN position. • • • “CHECK GEAR" voice alert - On the ground when the landing gear selector is in the UP position. "Engaging Autopilot" voice alert when autopilot automatically engages in LVL mode. (if equipped with optional Electronic Stability and Protection) REPORT: VB-2636 7-12 ISSUED: November 3, 2016 REVISED: October 1, 2018 PA-44-180, SEMINOLE SECTION 7 DESCR/OPERATION Primary Flight Display (continued) System Message Advisories The G1000 system generates several System Message Advisories. These [ messages are annunciated by flashing the PFD lower right softkey label, and are accessed/hidden by depressing that softkey. For a complete list of these messages, see the Garmin G1000 Cockpit Reference Guide. THIS SPACE INTENTIONALLY LEFT BLANK ISSUED: November 3, 2016 REVISED: October 1, 2018 REPORT: VB-2636 7-13