Piper PA-23 Aztec Pilot's Operating Handbook

Single Engine Service Ceiling (ft) .Single Engine Absolute Ceiling (ft) Landing Roll (Flaps down) (Max effort) (ft) Landing Distance Over 50-ft Barrier (Flaps down) (ft) ALTITUDE CRUISING SPEEDS (MPH) Normally Aspirated Turbo Charged 820 820 1250 1-2220 80 (69.5). .70 (61) .76 (66). .1250 72220 80 (69.5) 70 (61) 76 (66) 1490 1530 120 (102) 107 (93) 240 115 (100) 102 (88.5) 97 (84.5).. 97 (84.5) 265 104 (90) -:95 (82.5) 21,100 over 30,000 19,800 over 30,000 5000 .15,300 6400 18,700 850 850 1620. .1620 Normally Aspirated Man. Engine Altitude Speed Range Fuel Press. Speed J เ No Reserve Con. (in Hg) (rpm) (feet) (mph) (knots) (miles) (gph) Normal Intermediate Economy Long Range 2222 26 2400 4,000 210 (183) 830 34.0 24 2400 6,000 208 (181) 1080 27.0 24 2200 6,400 204 (177) 1110 25.0 20 2200 10,200 195 (170) 1210 21.0 GENERAL SPECIFICATIONS REVISED: January 25, 1974 PAGE 1 : AZTEC "E" ALTITUDE CRUISING SPEEDS (MPH) (cont) Turbo Charged TIO-540-CIA Man. Engine Altitude Speed Range Fuel Press. Speed No Reserve Con. (in Hg) (rpm) (feet) (mph) (knots) (miles) (gph) ' Turbo 34.0 2400 22,000 245 (213) 1050 .32.6 Intermediate ..30.0 2400 24,000 233 (203) -1-125 29.0 Economy 26.0 2400 24,000 .218 - (190) 1175 .26.0 Long Range 24.0 2200 24,000 196 (170) 1310 21.0 WEIGHTS Gross Weight (lbs) Maximum Landing Weight (lbs) Zero Fuel Gross Weight (lbs) Empty Weight (Standard, lbs) USEFUL LOAD (Standard, lbs) POWER PLANT Engine (Lycoming) Rated Horsepower Rated Speed (rpm) Bore (inches) Stroke (inches) Displacement (cu. in.) Compression Ratio Dry Weight (lbs) · FUEL AND OIL Fuel Capacity (U.S. gal) Usable Fuel Ser. nos. 27-4426, 274574 thru 27-7405476 Ser. nos. 27-7554001 and up Fuel Aviation Grade (min óctane) Oil Capacity (qts) each Engine PAGE 2 Normally Turbo Aspirated Charged 5200. 5200 *4940 4940 } 4400 4500 ☐ -3042 3229 2158 1971 IO-540-C4B5 TIO-540-ĊIA 250 250 2575* 2575 5.125 5.125 4.375 4.375 541'.5 541.5 8.5:1 7.2:1 402 490 144 144 140 140 137 137 91/96 100/130 12 12 GENERAL SPECIFICATIONS REVISED: October 1, 1974 - BAGGAGE Maximum Baggage (lbs) Forward Compartment Maximum Baggage (lbs) Rear Compartment With oxygen installed Baggage Space (cu ft) Forward Compartment Baggage Space (cu ft) Rear Compartment Baggage Door Size (in) Forward Compartment Baggage Door Size (in) Rear Compartment DIMENSIONS Wing Span (ft) Wing Area (sq ft) Length (ft) • Height (ft) Wing Loading (lbs per sq ft) Power Loading (lbs per hp) Propeller Diameter (maximum, in) AZTEC "E" Normally Turbo Aspirated Charged 150 150 150 150 105 105 21.3 21.3 25.4 25.4 19.5 x 30.5 19.5 x 30.5 30 x 31 30 x 31 37.2 207.6 31' 2.625" 10.3 25.05 10.4 77 37.2 207.6 31' 2.625" 10.3 25.05 10.4 77 LANDING GEAR Wheel Base (ft) 7.5 7.5 Wheel Tread 11.3 11.3 Tire Pressure Nose 27 27* Main 46 46 1 Tire Size Nose (four ply rating)* Main (eight ply rating) 600 x 6 700 x 6 600 x 6 700 x 6 "On turbocharged Aztec "E" only with serial no. 27-4781 and subsequent, nose tire is 6.00 x 6, six ply rating and should be inflated to 32 psi. GENERAL SPECIFICATIONS ISSUED: September 1, 1970 REVISED: December 10, 1971 PAGE 3 ¦ + | AZTEC "E" PAGE 4 12' 6.00" 37' 1.750" H-114.00" -7' 2.562" 6' 8.500" 3' 10.610" HORIZONTAL REF LINE- ☐ STATIC GROUND LINE 7' 6.00" 31' 2.625" 5' 7.00" 9' 8.750" REF. 5° DIHEDRAL 10' 3.875" GENERAL SPECIFICATIONS ISSUED: September 1, 1970 ¨REVISED: June 28, 1971 ] DESCRIPTION AIRPLANE AND SYSTEMS Engine and Accessories (Normally Aspirated) Engine and Accessories (Turbocharged) Fuel Injection Fuselage and Wing Structure Landing Gear Hydraulic System Control System and Surfaces Fuel System Electrical System Instrument Panel Heating and Ventilating System Finish Baggage Compartments Seats Cabin Features Radio Equipment 1 3 3 4 6 7 10 11 12 12 12 12 13 _ AZTEC "E" DESCRIPTION AIRPLANE AND SYSTEMS ENGINE AND ACCESSORIES (Normally Aspirated) The Lycoming IO-540-C4B5 engines in the Aztec are rated at 250 HP at 2575 RPM. These engines have a compression ratio of 8.5:1 and use 91/96 minimum octane aviation fuel. Both engines on the Aztec are equipped with a geared starter, alternator, vacuum pump, fuel injector, two magnetos, shielded ignition system, diaphragm fuel pump, propeller governor and an oil thermostat. The left engine is equipped with a hydraulic pump. Engine mounts are of steel tubing construction and incorporate vibration absorbing Lord mounts. Engine cowls are cantilever structures, attached at the firewall. Side panels are quickly removable by means of quick release fasteners. The nose section is split for quick removal. The exhaust system is a crossover type with exhaust gases directed outboard at the bottom of the nacelles in the area of the cowl flaps. The cowl flaps, located on the bottom of the engine nacelles provide additional cooling for ground operation or high temperature conditions. They are manually operated by push-pull controls located in the cabin, on the fuel control panel located between the front seats. An efficient aluminum oil cooler is mounted on a rear baffle of each engine. Engine oil drainage is accomplished with quick oil drain valves located on the inboard rear corner of the engine crankcases. The “Compact" propellers on the Aztec are Hartzell constant speed, full-feathering units which represent new concepts in basic design. They combine low weight with simplicity in design and are controlled entirely by use of the propeller control levers located in the center of the control quadrant. Feathering of the propellers is accomplished by moving the controls fully aft through the low RPM detent into the feathering position. Feathering takes approximately three to ten seconds. A propeller is unfeathered by moving the prop control ahead and engaging the starter. Loss of engine oil pressure will also result in propeller feathering. ENGINE AND ACCESSORIES (Turbocharged) The Lycoming TIO-540-C1A- engines in the Turbo-Aztec are rated at 250 HP at 2575 RPM. These engines have a compression ratio of 7.2:1 and use 100/130 minimum octane aviation fuel. The special Inconel exhaust valves and high temperature high altitude shielded ignition harness allow continued operation at high manifold pressure without decreasing overhaul time or engine life. Internal piston cooling is accomplished by injecting oil into the piston interior. - Each of the engines on the Aztec is equipped with TEO 659 turbochargers. The turbocharger is designed to increase the power output and efficiency of the engine by supplying compressed air to the engine intake manifold. This allows the engines to operate at peak power at a much higher altitude than normally aspirated engines. The power to drive the turbocharger is extracted from energy in the exhaust gas. The exhaust gases are ducted through the turbine and then directed overboard at the bottom of the nacelles in the area of the cowl flaps. The cowl flaps, located on the bottom of the engine nacelles, provide cooling for ground operation or high temperature at low airspeed-high power conditions. They are manually operated by push-pull controls located in the cabin on the fuel control panel between the front seats. For multi-engine operation maximum cowl flap position is half open. Single engine operation requires fully open flap on operative engine. AIRPLANE AND SYSTEMS ISSUED: September 1, 1970 PAGE 1 ] PAGE 2 Turbo System Schematic ISSUED: September 1, 1970 AIRPLANE AND SYSTEMS _ _ EXHAUST MANIFOLD 10 ПАНКСАН FUEL THROTTLE 011 RETURN KNJICTON -INLET MANIFOLD PRESSURE NOZZLE VINT PUSE PUMP VENT LINE. ་ DENSITY CONTROLLER, TO CRANKCASS OVERBOARD DRAIN TURBO-BYPASS DOOR FILTERED AIR TURBOCHARGER ALTERNATE AIR BOUNCE (UNITED AR EXHAUST GAS AIR INTAKE & COMPRESSOR DISCHARGE PRESSURE INLET MANIFOLD PRESSURE OIL OUTLET AT EXHAUST BYPASS VALVE ASSEMBLY ENGINE OIL PRESSURE INLET FILTER. AIR INLET PUJARINTIAL PRESSURE CONTROL COMPRESSOR DISCHAROL AIR DECA PRISSUR TEMPERATURE OVERBOARD -DRAIN AZTEC "E" EXHAUST BYPASS VALVE ASSEMBLY. EXHAUST GAS DISCHARGE !