V-Speeds Reference for the Piper PA-44 Seminole

ISSUED: November 3, 2016 REVISED: October 1, 2018 ! SECTION 3 PA-44-180, SEMINOLE 3.1 GENERAL (continued) EMERGENCY PROCEDURES Crew Alerting System (CAS) Messages (continued) Warnings - Red Checklist Event CAS Message Page Cause* CAS Warnings with Text Messages Alternator Failure 3-28 L ALTR FAIL 3-29 R ALTR FAIL High Cylinder Head Temperature LENG CHT 3-23 Left and/or right alternator is turned ON and has failed as determined by voltage regulator Left and/or right engine CHT exceeds 500 °F RENG CHT Low Fuel Quantity L FUEL QTY 3-24 Left or right fuel quantity is less than 5 gals. R FUEL QTY CO Level High CO LVL HIGH 3-52 CO level greater than 200 parts | per million (PPM). Starter Engaged L START ENGD 3-49 R START ENGD Landing Gear Failure GEAR SYS 3-27 Landing Landing Gear CHECK GEAR 3-26 Position Unsafe High Heater Temperature HTR OVRHEAT 3-51 Underspeed Protection USP ACTIVE 3-43 The autopilot Underspeed Protection (USP) mode is Left or right engine starter is engaged for greater than 30 seconds gear system malfunction while on the ground Landing gear selector is not in the down position when aircraft is less than 400 ft AGL with MAP less than 14 in Hg (mutable aural) or flaps greater than first "notch” (non-mutable aural). Landing gear is selected UP while on the ground. Cabin heater has sensed an overheat condition and has shut down the heater actively preventing an under speed condition. *CAS Messages/Alerts may have small time delays to avoid nuisance alarms. ISSUED: November 3, 2016 REVISED: October 1, 2018 REPORT: VB-2636 3-3 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.1 GENERAL (continued) Crew Alerting System (CAS) Messages (continued) Warnings - Red (continued) Checklist Event CAS Message Page Cause* CAS Warnings with EIS Indications Propeller None .3-50 Overspeed Propeller speed is greater than 2720 RPM for more than 5 seconds. Oil Temperature None 3-23 Exceedance Oil Temperature greater than 245°F. Oil Pressure None 3-22 Exceedance Oil Pressure less than 25 PSI or greater than 115 PSI. Total Fuel Quantity None 3-24 Low Battery Voltage None NA Alternator None 3-28 Amperage Emergency Battery Voltage None 3-32 Landing Gear None 3-27 Failure Total fuel quantity less than 10 gals. Primary battery voltage less than: 24 V when RPM less than 1100 or 25 V when RPM greater than 1100 Or Primary battery voltage greater than 32 V. Left and/or right alternator amperage is greater than 65 AMPS. Emergency battery voltage is less than 20 V or greater than 32 V. Malfunction in any of the landing gear as indicated by a red circle on the landing gear display. *CAS Messages/Alerts may have small time delays to avoid nuisance alarms. REPORT: VB-2636 3-4 ISSUED: November 3, 2016 REVISED: December 15, 2017 SECTION 3 PA-44-180, SEMINOLE 3.1 GENERAL (continued) EMERGENCY PROCEDURES Crew Alerting System (CAS) Messages (continued) Cautions - Amber CAS Event CAS Message Checklist Page CAS Cautions with Text Messages CO Level High 3-52 CO LVL HIGH Cause* CO level greater than or equal to 50 but less than 200 parts per million (PPM). Left or right fuel quantity is less than 10 gals. Low Fuel Quantity L FUEL QTY 3-24 R FUEL QTY Landing Gear Failure GEAR SYS 3-27 Landing Landing Gear Position Unsafe CHECK GEAR 3-26 Hydraulic Pump HYDR PUMP ON 3-48 gear system malfunction while in flight Landing gear selector is not in the down position when aircraft is greater than 400 ft AGL with MAP less than 14 in Hg (mutable aural) or flaps greater than first "notch" (non-mutable aural) Hydraulic pump has been running for greater than 16 seconds Pitot Heat Fail PITOT HEAT FAIL 3-47 Pitot heat is selected ON and is inoperative Pitot Heat Off PITOT HEAT OFF 3-47 Pitot heat is selected OFF (double chime is suppressed) Oil Pressure Exceedance CAS Cautions with EIS Indications None 3-22 Total Fuel Quantity None 3-24 Low Emergency Battery Voltage None NA Oil pressure between 26 PSI and 55 PSI when propeller speed is greater than 1500 RPM or oil pressure between 96 and 115 PSI. Total fuel quantity is less than 20 gals. Emergency battery voltage is less than 23.3 V. ISSUED: November 3, 2016 REVISED: December 15, 2017 REPORT: VB-2636 3-5 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.1 GENERAL (continued) Crew Alerting System (CAS) Messages (continued) Advisories -- White CAS Event CAS Message Checklist Page Cause* CAS Advisory with Text Message Emergency Power In Use 3-31 EMERG BATT ON Emergency battery is in use Fuel Imbalance FUEL IMBAL NA Left and right fuel quantities differ by greater than 10 gals. PFD Fan Failure PFD FAN FAIL 3-47 The PFD cooling fan has failed MFD Fan Failure MFD FAN FAIL 3-47 The MFD cooling fan has failed Avionics Fan Failure AV FAN FAIL 3-47 The avionics cooling fan has failed Terminology Many emergencies require some urgency in landing the aircraft. The degree of urgency varies with the emergency; therefore the terms “land as soon as possible" and "land as soon as practical" are employed. These terms are defined as follows: - Land as soon as possible A landing should be accomplished at the nearest suitable airfield considering the severity of the emergency, weather conditions, field facilities, and ambient lighting. Land as soon as practical - Emergency conditions are less urgent, and although the mission is to be terminated, the emergency is such that an immediate landing at the nearest suitable airfield may not be necessary. REPORT: VB-2636 3-6 ISSUED: November 3, 2016 REVISED: December 15, 2017 PA-44-180, SEMINOLE SECTION 3 EMERGENCY PROCEDURES 3.3 AIRSPEEDS FOR SAFE OPERATIONS One engine inoperative air minimum control One engine inoperative best rate of climb....... One engine inoperative best angle of climb. Maneuvering (3800 lb) Never exceed .56 KIAS .88 KIAS .82 KIAS 135 KIAS (115 KIAS @ 2870 LB) .202 KIAS 3.5 EMERGENCY PROCEDURES CHECKLIST 3.5a Engine Inoperative Procedures An inoperative engine can be identified by various means, including the fact that directional control is maintained by applying rudder pressure toward the operative engine (DEAD FOOT INDICATES DEAD ENGINE). Additionally, engine indications such as EGT and oil pressure may help in identifying an inoperative engine. After identification, verify complete power loss on that engine by retarding its throttle and noting the absence of engine or aircraft response. Engine Securing Procedure (Feathering Procedure) THROTTLE PROPELLER MIXTURE.. COWL FLAP MAG LEFT/RIGHT Switches .. FUEL PUMP Switch ALTR Switch ..... FUEL selector Electrical load .CLOSE FEATHER (950 RPM Min.) CUT-OFF …………….. CLOSE .OFF .OFF .OFF ..OFF REDUCE | ISSUED: November 3, 2016 REVISED: December 15, 2017 REPORT: VB-2636 3-7 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5a Engine Inoperative Procedures (continued) The engine securing procedure should always be accomplished in a sequential order on the inoperative engine. Move the throttle of the inoperative engine towards IDLE. If no changes are noted, the correct identification of the inoperative engine is confirmed. Move the propeller control to FEATHER (fully aft) before the propeller speed drops below 950 RPM, otherwise the propeller will not feather. One engine inoperative performance will decrease significantly if the propeller of the inoperative engine is not feathered. Engine Failure During Takeoff (Speed Below 75 KIAS or Gear Down) THROTTLES Brakes (or land and brake)..... IMMEDIATELY CLOSE ….AS REQUIRED …………..MAINTAIN Directional Control If insufficient runway remains for a complete stop: Brakes...... MIXTURES .APPLY MAXIMUM BRAKING CUT-OFF FUEL Selectors. ..OFF MAG LEFT/RIGHT Switches ........... .OFF BATT MASTR Switch. ...OFF Directional Control....... MAINTAIN and AVOID OBSTACLES If engine failure occurs during the takeoff roll, the takeoff MUST be aborted. If failure occurs after liftoff but before 75 KIAS is achieved or before the landing gear is retracted, the takeoff should also be aborted. REPORT: VB-2636 3-8 ISSUED: November 3, 2016 REVISED: December 15, 2017 PA-44-180, SEMINOLE SECTION 3 EMERGENCY PROCEDURES 3.5a Engine Inoperative Procedures (continued) Engine Failure During Takeoff (Speed Above 75 KIAS) If sufficient runway remains for a complete stop: GEAR ........ Land..... Directional Control THROTTLES. VERIFY DOWN STRAIGHT AHEAD || MAINTAIN CLOSE Brakes AS REQUIRED If GEAR is in transit or UP and the decision is made to continue: WARNING In many combinations of aircraft weight, configuration, ambient conditions and speed, negative climb performance may result. Refer to Climb Performance chart- One Engine Operating - Gear Up, Figure 5-21. MIXTURES PROPELLERS THROTTLES. FLAPS FULL RICH FULL INCREASE FULL OPEN .FULL UP VERIFY UP . IDENTIFY and VERIFY GEAR..... Inoperative Engine THROTTLE (Inop. Engine)….. PROPELLER (Inop. Engine) MIXTURE (Inop. Engine). Establish Bank.... Climb Speed Rudder Trim CLOSE FEATHER CUT-OFF .2° to 3° INTO OPERATING ENGINE .88 KIAS ...TOWARD OPERATING ENGINE TO APPROXIMATELY 1/2 TRAPEZOID ON THE SLIP INDICATOR COWL FLAP (Operating Engine). COWL FLAP (Inop. Engine).... MAG LEFT/RIGHT Switches (Inop. Engine)...... FUEL PUMP (Inop. Engine) ALTR Switch (Inop. Engine)... FUEL Selector (Inop. Engine). ..AS REQUIRED . CLOSE .OFF .OFF .OFF ...OFF Land as soon as practical. ISSUED: November 3, 2016 REPORT: VB-2636 REVISED: December 15, 2017 3-9 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5a Engine Inoperative Procedures (continued) If engine failure occurs after liftoff with the gear still down and 75 KIAS has been attained, the best course of action will depend on the runway remaining and aircraft configuration. Also the pilot's decision must be based on a personal judgement, taking into consideration such factors as obstacles, the type of terrain beyond the runway, altitude and temperature, weight and loading, weather, airplane condition, and the pilot's own proficiency and capability. Attempt to maintain the one engine inoperative best rate of climb speed (VYSE: 88 KIAS). Do not allow airspeed to decrease below the air minimum control speed (VMCA: 56 KIAS). An inoperative engine can be identified by various means, including the fact that directional control is maintained by applying rudder pressure toward the operating engine (DEAD FOOT INDICATES DEAD ENGINE). Additionally, engine indications such as EGT and oil pressure may help in identifying an inoperative engine. After identification, verify complete power loss on that engine by retarding its throttle and noting the absence of engine or aircraft response. Once the aircraft is trimmed and the inoperative engine is secured, close the cowl flap of the operating engine as much as possible without exceeding engine temperature limits. Land as soon as practical at the nearest suitable airport. REPORT: VB-2636 3-10 ISSUED: November 3, 2016 REVISED: December 15, 2017 PA-44-180, SEMINOLE SECTION 3 EMERGENCY PROCEDURES 3.5a Engine Inoperative Procedures (continued) Engine Failure During Climb Airspeed....... Directional Control MIXTURE.... PROPELLERS ...... THROTTLES Inoperative Engine.... .MAINTAIN MAINTAIN 88 KIAS FULL RICH FULL INCREASE FULL OPEN THROTTLE (Inop. Engine)…………………... PROPELLER (Inop. Engine) MIXTURE (Inop. Engine). Establish Bank. Climb Speed..... Rudder Trim. IDENTIFY and VERIFY CLOSE FEATHER CUT-OFF .2° to 3° INTO OPERATING ENGINE .88 KIAS .TOWARD OPERATING ENGINE TO APPROXIMATELY 1/2 TRAPEZOID ON THE SLIP INDICATOR COWL FLAP (Operating Engine)..... AS REQUIRED COWL FLAP (Inop. Engine) ..... FUEL PUMP (Inop. Engine) CLOSE MAG LEFT/RIGHT Switches (Inop. Engine) ..... .OFF .OFF ALTR Switch (Inop. Engine).. OFF .OFF FUEL Selector (Inop. Engine). Land as soon as practical. An inoperative engine can be identified by various means, including the fact that directional control is maintained by applying rudder pressure toward the operating engine (DEAD FOOT INDICATES DEAD ENGINE). Additionally, engine indications such as EGT and oil pressure may help in identifying an inoperative engine. After identification, verify complete power loss on that engine by retarding its throttle and noting the absence of engine or aircraft response. After the faulty engine has been identified and power loss has been verified, complete the Engine Securing Procedure. Continue a straight ahead climb until sufficient altitude (minimum of 1000 feet above ground elevation) is reached to execute the normal One Engine Inoperative Landing procedure at the nearest suitable airport. ISSUED: November 3, 2016 REVISED: December 15, 2017 REPORT: VB-2636 3-11