Pilot's Operating Handbook for the Piper PA-34 Seneca II

oils meeting Teledyne Continental Motors' Specification MHS-24A are approved. 1.11 MAXIMUM WEIGHTS (a) Maximum Takeoff Weight (lbs) 4570 (b) Maximum Landing Weight (lbs) 4342 (c) Maximum Zero Fuel Weight (lbs) - Standard 4000 (d) Maximum Weights in Baggage Compartments (lbs) FORWARD AFT 100 100 1.13 STANDARD AIRPLANE WEIGHTS* (a) Standard Empty Weight (lbs): Weight of a standard airplane including unusable fuel, full operating fluids and full oil. (b) Maximum Useful Load (lbs): The difference between the Maximum Takeoff Weight and the Standard Empty Weight. (All weight in excess of 4000 lbs must consist of fuel) 2823 1747 *These values are approximate and vary from one aircraft to another. Refer to Figure 6-5 for the Standard Empty Weight value and the Useful Load value to be used for C.G. calculations for the aircraft specified. REPORT: VB-850 1-4 ISSUED: AUGUST 23, 1976 REVISED: JULY 25, 1980 PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II 1.15 BAGGAGE SPACE (a) Compartment Volume (cubic feet) (b) Entry Width (inches) (c) Entry Height (inches). 1.17 SPECIFIC LOADINGS (a) Wing Loading (lbs per sq ft) (b) Power Loading (lbs per hp) (1) Sea level (2) 12,000 ft. SECTION 1 GENERAL FORWARD 15.3 AFT 17.3 24 21 22 11.4 10.6 ISSUED: AUGUST 30, 1978 REPORT: VB-850 1-4a SECTION 1 GENERAL PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II REPORT: VB-850 1-4b THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: AUGUST 30, 1978 PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II SECTION 1 GENERAL 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols, abbreviations and terminology used throughout the handbook and those which may be of added operational significance to the pilot. (a) General Airspeed Terminology and Symbols CAS KCAS GS IAS KIAS M TAS VA VFE VLE VLO VMC VNE/MNE VNO Calibrated Airspeed means the indicated speed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. Calibrated Airspeed expressed in "Knots." Ground Speed is the speed of an airplane relative to the ground. Indicated Airspeed is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error. IAS values published in this handbook assume zero instrument error. Indicated Airspeed expressed in “Knots.” Mach Number is the ratio of true airspeed to the speed of sound. True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperature and compressibility. Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane. Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. Maximum Landing Gear Extended Speed is the highest speed at which an aircraft can be safely flown with the landing gear extended. Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended or retracted. Air minimum control speed is the minimum flight speed at which the airplane is controllable with a bank of not more than 5 degrees when one engine suddenly becomes inoperative and the remaining engine is operating at takeoff power. Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution. ISSUED: AUGUST 23, 1976 REPORT: VB-850 1-5 | SECTION 1 GENERAL PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II Vs VSO VSSE VX VY (b) Meteorological Terminology ISA OAT Indicated Pressure Altitude Pressure Altitude Station Pressure Wind Stalling Speed or the minimum steady flight speed at which the airplane is controllable. Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration. Intentional One Engine Inoperative Speed is a minimum speed selected by the manufacturer for intentionally rendering one engine inoperative in flight. Best Angle-of-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance. Best Rate-of-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time. International Standard Atmosphere in which: The air is a dry perfect gas; The temperature at sea level is 15° Celsius (59° Fahrenheit): The pressure at sea level is 29.92 inches hg. (1013 mb): The temperature gradient from sea level to the altitude at which the temperature is -56.5° C (-69.7°F) is -0.00198°C (-0.003566°F) per foot and zero above that altitude. Outside Air Temperature is the free air static temperature. obtained either from inflight temperature indications or ground meteorological sources, adjusted for instrument error and compressibility effects. The number actually read from an altimeter when the barometric subscale has been set to 29.92 inches of mercury (1013 millibars). Altitude measured from standard sea-level pressure (29.92 in. Hg) by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. In this handbook, altimeter instrument errors are assumed to be zero. Actual atmospheric pressure at field elevation. The wind velocities recorded as variables on the charts of this handbook are to be understood as the headwind or tailwind components of the reported winds. (c) Power Terminology Takeoff Power Maximum Continuous Power REPORT: VB-850 1-6 Maximum power permissible for takeoff. Maximum power permissible continuously during flight. ISSUED: AUGUST 23, 1976 REVISED: AUGUST 30, 1978 PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II Maximum Climb Power Maximum power permissible during climb. Maximum Cruise Power Maximum power permissible during cruise. (d) Engine Instruments EGT Gauge Exhaust Gas Temperature Gauge SECTION 1 GENERAL (e) Airplane Performance and Flight Planning Terminology Climb Gradient The demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval. Demonstrated Crosswind The demonstrated crosswind velocity is the velocity of the Velocity (DEMO. X-WIND) crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. Accelerate-Stop Distance MEA Route Segment The distance required to accelerate an airplane to a specified speed and, assuming failure of an engine at the instant that speed is attained, to bring the airplane to a stop. Minimum en route IFR altitude. A part of a route. Each end of that part is identified by: (1) a geographical location; or (2) a point at which a definite radio fix can be established. (f) Weight and Balance Terminology Reference Datum Station Arm Moment An imaginary vertical plane from which all horizontal distances are measured for balance purposes. A location along the airplane fuselage usually given in terms of distance from the reference datum. The horizontal distance from the reference datum to the center of gravity (C.G.) of an item. The product of the weight of an item multiplied by its arm. (Moment divided by a constant is used to simplify balance calculations by reducing the number of digits.) ISSUED: AUGUST 23, 1976 REVISED: JULY 9, 1979 REPORT: VB-850 1-7 SECTION 1 GENERAL PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II Center of Gravity (C.G.) C.G. Arm C.G. Limits Usable Fuel Unusable Fuel Standard Empty Weight Basic Empty Weight Payload Useful Load Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Maximum Zero Fuel Weight The point at which an airplane would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. The arm obtained by adding the airplane's individual moments and dividing the sum by the total weight. The extreme center of gravity locations within which the airplane must be operated at a given weight. Fuel available for flight planning. Fuel remaining after a runout test has been completed in accordance with governmental regulations. Weight of a standard airplane including unusable fuel, full operating fluids and full oil. Standard empty weight plus optional equipment. Weight of occupants, cargo and baggage. Difference between takeoff weight, or ramp weight if applicable, and basic empty weight. Maximum weight approved for ground maneuver. (It includes weight of start, taxi and run up fuel.) Maximum weight approved for the start of the takeoff run. Maximum weight approved for the landing touchdown. Maximum weight exclusive of usable fuel. REPORT: VB-850 1-8 ISSUED: AUGUST 23, 1976 PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II SECTION 1 GENERAL THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: AUGUST 23, 1976 REPORT: VB-850 1-9