1.1. AIRPLANE GENERAL CHARACTERISTICS

Transcription

1 AIRPLANE CHARACTERISTICS 1.1. AIRPLANE CHARACTERISTICS ENGINES a. Number of Engines 2 b. Engine Manufacturer Pratt & Whitney Canada c. Engine Model Number PT6A-66 d. Rated Horsepower 850 e. Propeller Speed(rpm) Takeoff and climb Cruise /2000 f. Engine Type Free Turbine, Reverse Flow, 2-Shaft Compressor stages and type 4 axial stages 1 centrifugal stage Turbine stages and type 1 stage compressor 2 stages power Combustion chamber type annular PROPELLERS a. Number of Propellers 2 b. Propeller Manufacturer Hartzell c. Blade Models Left (CW Rotating, inner tip down) HE 8218 Right (CCW Rotating, inner tip down) LE 8218 d. Number of Blades 5 e. Hub Models Left (CW Rotating) HC-E5N-3 or HC-E5N-3A Right (CCW Rotating) HC-E5N-3L or HC-E5N-3AL f. Propeller Diameter 85 in. (2.16 m.) g. Propeller Type Hydraulically Operated, Single Acting, Constant Speed, Full Feathering, Reversible Page 1.1-1

2 PILOT S OPERATING HANDBOOK A RPLANE CHARACTERISTICS FUEL a. Total Capacity U.S. Gal. (1597 LTS) b. Usable Fuel U.S. Gal. (1583 LTS) c. Fuel Specification Refer to latest revision of Pratt & Whitney Service Bulletin No (including Jet A, Jet A-1, Jet B, JP4 and JP8) Aviation Gasoline is not permitted d. Approved Additives Anti Ice Additive per latest revision of Pratt & Whitney Service Bulletin No (including Phillips PFA 55 MB, MIL-I-27686D and MIL-I-27686E) OIL a. Total Oil Capacity (each engine) 3.35 U.S. Gal. (12.7 LTS) b. Usable Oil Quantity (each engine) 1.25 U.S. Gal. (4.7 LTS) c. Oil Specification Only MOBIL JET OIL II, AEROSHELL TURBINE OIL 500, CASTROL 5000 and EXXON TURBO OIL 2380 engine oils have been tested and are approved for use on the P.180 airplane within the recommendations of the latest revision of P&WC Engine Service Bulletin No The other oils listed in the above P&WC Engine Service Bulletin are not approved for use on the P.180 airplane. Page 1.1-2

3 AIRPLANE CHARACTERISTICS MAXIMUM WEIGHTS a. Maximum Ramp Weight 11,600 LBS (5262 kg) b. Maximum Takeoff Weight 11,550 LBS (5239 kg) c. Maximum Landing Weight 10,945 LBS (4965 kg) d. Maximum Zero Fuel Weight 9800 LBS (4445 kg) e. Maximum Weight in Baggage Compartment 350 LBS (159 kg) This is the maximum weight of baggage allowed in a fully available baggage compartment. The installation of some optional equipments may require a partial utilization of the baggage compartment with a corresponding reduction of the above maximum weight allowed for baggage loading AIRPLANE WEIGHTS a. Typical Equipped Empty Weight 7,500 LBS (3266 kg) b. Maximum Useful Load (standard airplane including ramp fuel) 4,230 LBS (1919 kg) Refer to the Weight and Balance Manual for Empty Weight value and Useful Load value to be used for C.G. calculations of the airplane specified. Page 1.1-3

4 PILOT S OPERATING HANDBOOK A RPLANE CHARACTERISTICS CABIN & ENTRY DIMENSIONS a. Cabin Length FT (6.00 m.) b. Cabin Width 6.07 FT (1.85 m.) c. Cabin Height 5.74 FT (1.75 m.) d. Cabin Door Width 2.00 FT (0.61 m.) e. Cabin Door Height 4.43 FT (1.35 m.) BAGGAGE SPACE & ENTRY DIMENSIONS a. Compartment Volume cu.ft. (1.25 cu.m.) This is the volume of baggage allowed in a fully available baggage compartment. The installation of some optional equipments may require a partial utilization of the baggage compartment with a corresponding reduction of the volume available for baggage stowing. b. Compartment Length 5.57 ft. (1.70 m.) c. Baggage Compartment Door Width 2.30 ft. (0.70 m.) d. Baggage Compartment Door Height 1.97 ft. (0.60 m.) SPECIFIC LOADINGS a. Wing Loading lbs. per sq. ft kg. per sq.m. b. Power Loading 6.79 lbs. per hp 3.08 kg. per hp Page 1.1-4

5 AIRPLANE CHARACTERISTICS MAXIMUM WEIGHTS a. Maximum Ramp Weight 12,150 LBS (5511 kg) b. Maximum Takeoff Weight 12,100 LBS (5489 kg) c. Maximum Landing Weight 11,500 LBS (5216 kg) d. Maximum Zero Fuel Weight 9800 LBS (4445 kg) e. Maximum Weight in Baggage Compartment 350 LBS (159 kg) This is the maximum weight of baggage allowed in a fully available baggage compartment. The installation of some optional equipments may require a partial utilization of the baggage compartment with a corresponding reduction of the above maximum weight allowed for baggage loading AIRPLANE WEIGHTS a. Typical Equipped Empty Weight 7,500 LBS (3266 kg) b. Maximum Useful Load (standard airplane including ramp fuel) 4,230 LBS (1919 kg) Refer to the Weight and Balance Manual for Empty Weight value and Useful Load value to be used for C.G. calculations of the airplane specified. Page Mod (Suppl. 15)

6 PILOT S OPERATING HANDBOOK A RPLANE CHARACTERISTICS CABIN & ENTRY DIMENSIONS a. Cabin Length FT (6.00 m.) b. Cabin Width 6.07 FT (1.85 m.) c. Cabin Height 5.74 FT (1.75 m.) d. Cabin Door Width 2.00 FT (0.61 m.) e. Cabin Door Height 4.43 FT (1.35 m.) BAGGAGE SPACE & ENTRY DIMENSIONS a. Compartment Volume cu.ft. (1.25 cu.m.) This is the volume of baggage allowed in a fully available baggage compartment. The installation of some optional equipments may require a partial utilization of the baggage compartment with a corresponding reduction of the volume available for baggage stowing. b. Compartment Length 5.57 ft. (1.70 m.) c. Baggage Compartment Door Width 2.30 ft. (0.70 m.) d. Baggage Compartment Door Height 1.97 ft. (0.60 m.) SPECIFIC LOADINGS a. Wing Loading lbs. per sq. ft kg. per sq.m. b. Power Loading 6.79 lbs. per hp 3.08 kg. per hp Page 1.1-4

7 LIST OF ACRONYMS AND ABBREVIATIONS 1.2. LIST OF ACRONYMS AND ABBREVIATIONS ACAS ADC ADF ADS AFD AGL AHC AHRS AIS AOA AP ATC ATT BAT BRG CAUT C/B CCP CDU COM, COMM CPAS CPCS CWTS DBU DCP DCU DG DH DME ECS Airborne Collision Avoidance System Air Data Computer Automatic Direction Finder Air Data System Adaptive Flight Display Above Ground Level Attitude Heading Computer Attitude Heading Reference System Audio Integrating System Angle of Attack Autopilot Air Traffic Control Attitude Battery Bearing Caution Circuit Breaker Cursor Control Panel Control Display Unit Communications Collins Portable Access System Cabin Pressure Control System Control Wheel Trim Swtches Database Unit Display Control Panel Data Concentration Unit Directional Gyro Decision Height Distance Measuring Equipment Environmental Control System Page 1.2-1

8 PILOT S OPERATING HANDBOOK LIST OF ACRONYMS AND ABBREVIATIONS ECU EDC EFIS EIS ELT EMER, EMG EPB EPU FD FDU FGC FGP FGS FLT FMC FMS FWLF FWRF GA GCS GPS HDG H MIC HSI IAPS ID ILS INB IOC ISI LOC External Compensation Unit Engine Data Concentrator Electronic Flight Instrument System Engine Indicating System Emergency Locator Transmitter Emergency Emergency Power Bus Emergency Power Unit Flight Director Flux Detector Unit Flight Guidance Computer Flight Guidance Panel Flight Guidance System Flight Flight Management Computer Flight Management System Forward Wing Left Flap Forward Wing Right Flap Go Around Ground Clutter Suppression Global Positioning System Heading Hand Microphone Horizontal Sistuation Indicator Integrated Avionics Processor System Identifier Instrument Landing System Inboard Input/Output Concentrator Integrated Standby Instrument Localizer Page 1.2-2

9 LIST OF ACRONYMS AND ABBREVIATIONS LSC LWD MFD MKR MSW MWIF MWOF NAV OUTB PCD PFD RTU RWD SAT SSEC STBY SYS TAS TAT TAWS TCAS TDR VHF VOR WOW WRN XPNDR YD Low Speed Cue Left Wing Down Multifunction Display Marker Beacon Control Wheel Master Switch Main Wing Inboard Flap Main Wing Outboard Flap Navigation Outboard Personal Computer Data Primary Flight Display Radio Tuning Unit Right Wing Down Static Air Temperature Static Source Error Correction Standby System True Air Speed Total Air Temperature Terrain Awareness and Warning System Traffic Alert and Collision Avoidance System Transponder Very High Frequency VHF Omnidirectional Radio Range Weight on Wheels Warning Transponder Yaw Damper Page 1.2-3