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GENERAL EQUIPMENT INC.
8770 Sunset Drive #191 ● Miami FL 33173 · USA
Tel: +1 305 468 4650
+33 6 68 96 24 99
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Fax: +1 360 937 2965
+33 8 21 46 30
77 |
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GENERAL EQUIPMENT INC.
8770 Sunset Drive #191 ● Miami FL 33173 · USA
Tel: +1 305 468 4650
+33 6 68 96 24 99
·
Fax: +1 360 937 2965
+33 8 21 46 30
77 |
M28
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TYPE: |
Aircraft |
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DESCRIPTION: |
M28 Skytruck |
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PRICE: |
Upon Request |
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PACKING: |
Ex-Work |
M28 SKYTRUCK
The M28 SKYTRUCK is a multi-purpose airplane, STOL class commuter category, adapted for operation from short, unpaved runways, at high-elevation airfields. It is powered by two Pratt & Whitney Canada PT6A-65B turboprop engines, combined with 5-blade synchrophased, automatic-feathering, fully reversible Hartzell HC-B5MP-3D propellers
The equipment installed in the airplane provides for VFR and IFR day and night operation in all – weather condition except for severe icing. Short – duration flight in light to moderate unknown icing conditions is permissible
The M28 SKYTRUCK airplane holds:
· Type Certificate No. A.058 issued by EASA. for conformity with the requirements of FAR Part 23, Amendment 1 through 42, 23.1309 Amendment 49, 23.203, 23.205, 23.207 and 23.1545 Amendment 50, Part 34 Subpart B, and Part 36 Appendix G.
· Type Certificate No. A56CE issued by USA Department of Transportation FAA in accordance with 14 Code of Federal Regulation part 21 § 21.29 for conformity with FAR Part 23, Amendment 1 through 42, Part 34 Subpart B, and Part 36 Appendix G.
Depending on the equipment installed, the airplane can be operated in the following mission versions:
passenger transport (19 seats or 18 seats plus toilet),
cargo transport (2300 kg payload),
Paradrop (17 seats),
Mix version,
The airplane flight and radio/navigation equipment provides for VFR and IFR flying capability, day and night, and brief entry into icing conditions.
In the cargo transport version, the airplane is suited for carriage of cargo boxes, loose or, when liquid, in special container inside the fuselage or in barrels.
The airplane fuselage is a semi-monocoque all-metal structure. The fuselage forward section contains a cockpit and entry door, center section houses a passenger/cargo cabin, while the aft section features a cargo (paradrop) door, electrical/air-conditioning equipment compartments, pressure (central) refuelling door, and hydraulic system ground service systems.
Rear cargo (paradrop) door and side door in a forward section of the fuselage provide for passengers boarding and cargo loading.
The floor and seat beam structure allows for installation of a range of conversion equipment configurations: fixed-type passenger seats, paradrop deployment systems, restraint systems for loose cargo.
The cabin provides for installation of:
19 passenger seats, of which 6 are single, 6 are double and one or single benches or toilet compartment (option),
Benches (8 seats),
The fuselage has got steps to enable climbing up the wing, three (3) emergency exits and, as standard, attach joints for installation of the following:
- loose cargo restraint systems;
The seat guideways in the fuselage longerons and the floor (2) ensure quick replacement of the equipment and conversion of the airplane configuration.
Cargo loading is facilitated by application of a hoist and a system of rails for cargo transportation inside the fuselage. The hoist is fitted with scales to facilitate location of cargo items of various weight.
The aft cargo/passenger door provides for installation of two leaves hydraulically openable inside the fuselage on ground and in flight.
Two emergency exits are provided in the cabin’s rear, each fitted with emergency lighting installed above, and powered from an independent emergency power supply source. The window on the cockpit starboard functions as one of the emergency exits.
On the left side of the cabin there are three (3) and on the right side there are four (4) double windows each fitted with a roller sunshade. Two bubble windows so called blisters mounted in the place of normal windows, ensure outside observation.
The cockpit windows are provided with shutters and a sunscreen for protection against excessive cockpit heating caused by prolonged parking. On each side of the cockpit there is an additional small hinged window openable inside.
All passenger seats are positioned at guideways providing for quick installation/removal owing to their attachment by means of quick-disconnect camlocks. The seats are provided with head-rests and folding tables, as well as arm-rests.
The wing of semi-monocoque, two-spar, all-metal split structure consists of the centerwing and two outboard wings. The space between spars is used for integral fuel tanks.
The wing is fitted with slats, ailerons, flaps, flaperons and spoilers. All fuel tanks inside the wings are provided with sockets for installation of fuel gauge senders.
Cantilever, all-metal, semi-monocoque construction, with twin vertical fins
and rudders, a horizontal stabilizer and split elevator. Both rudders and
elevator halves incorporate trim tabs.
Tricycle, non-retractable type with a nose wheel steerable for taxi and takeoff. Main wheels are provided with hydraulic brake fitted with anti-skid (ABS) system.
The flight control system of cable/pushrod type ensures control for the rudders and elevator, ailerons, flaps, spoilers and trim tabs from both pilots’ workstations.
Elevator, rudder-, and aileron trim tabs are electrically controlled, with the elevator trim tab provided with an auxiliary mechanical control system. Wing flaps and spoilers are hydraulically operated.
The
hydraulic system is used to operate nose wheel steering, wing flap extension
and retraction, spoiler deployment, main wheel braking and cargo door
opening.
The system is powered from two engine-driven pumps. The emergency hydraulic power source is a hydro-accumulator, which ensures operation of wing flaps, spoilers, wheel braking, cargo door opening and parking brake application.
Variable-output hydraulic pumps are supplied with working fluid from a tank pressurized by propeller slipstream air.
The airplane is powered by two PT6A-65B turboprop engines, driving all-metal, five-blade constant-speed propellers with thrust reverse and feathering capability.
Ø Max. Takeoff Power 1100 SHP constant up to + 50.5oC (123oF)
Ø Max. Continuous Power 1100 SHP constant up to + 45.5oC (114oF)
Ø Max. Cruise Power 1000 SHP constant up to +42.5oC (108oF) & up to 1600 m altitude, ISA conditions
Ø Max. Cruise Power (Climb),
extraordinary circumstances 1000 SHP constant up to 3,900 altitude (12,800 ft) ISA conditions
Ø Five-blade,
all-metal Hartzell
HC-B5MP-3 propeller, diameter 2.82 m
Capability for manual propeller feathering from any power and RPM setting, automatic electronic feathering system active at speeds exceeding 91% Ng, light annunciation of automatic feathering system READY.
Propeller minimum blade angle annunciation through control lever position. Mechanical lock (stop) for reverse setting, light and aural (horn) warning for in-flight thrust reverse lock removal. Light annunciation of maximum torque (43.3 psi) warning (picked up at propeller shaft).
Propeller electrical anti-ice system is a part of airplane standard equipment.
Oil system is an integral part of each engine. The airframe portion of the system consists of two oil coolers fitted with thermostats and power supply systems for the automatic prop feathering pressure and propeller shaft maximum torque warning.
Main fuel tanks, together with two electric fuel feed pumps and fuel gauge senders are located in the outboard wings each. Auxiliary fuel tanks are those located in outboard wing tips and in centerwing.
The fuel tanks have the following capacities:
- Main tanks in outboard wings - 1320 l. (348 US gal.)
- Auxiliary tanks in centerwing: - 580 l. (153 US gal.)
- Auxiliary tanks in outboard wings - 378 l. (100 US gal.)
Total capacity of the fuel system amounts to 2278 liters (600 US gal.; 1765 kg).
The main tanks in outboard wings and auxiliary fuel tanks in centerwing can be replenished either through fillers or pressure-filled.
Auxiliary fuel tanks in outboard wings can be replenished through fuel fillers or by means of the electric fuel pumps in the main tanks, whose primary function is to pump fuel into main tanks during their refuelling.
Filler inlet diameter: 60 mm (2.36 inches).
Double protection system is provided for tanks against overfilling when pressure refuelling, with a provision for manual control of tank filling.
System provides for cross feeding (each engine can be feed from each main tank).
The fire protection system for each engine consists of an automatic fire detection unit built up of nine (9) sensors located inside the engine nacelle, and of a combined visual (light)/aural (horn) annunciation in the cockpit. Each nacelle is equipped with a halone-type fire extinguisher, manually activated in two stages. Both fire extinguishers can be applied for fighting fire inside one of the engine nacelles. Each fire extinguisher is fitted with a pressure gauge and a thermal-type safety provision.
Each engine nacelle features fireproof steel fire walls for fire containment.
The airplane is equipped with an electrical icing protection system for propeller bledes, cockpit windshields and pressure probes (pitot tubes), and with a heat-type system using engine exhaust gases for anti-icing protection of the engine air intakes. Engine air inlet ducts are further protected by installation of inertial separators.
Icing warning is provided from an annunciator light in the cockpit and a visual icing indicator externally mounted on the fuselage.
The heating system uses engine bleed air, and is provided with both automatic and manual selection/control of the cabin air temperature. Warm air is distributed through floor-level outlets in cabin and cockpit, and additionally through two air outlets directed onto cockpit side windows. Passenger cabin ventilation system is supplied with cold air from airscoops on the engine nacelles. Cool air is distributed through overhead ducts to individual airblow ports provided for each passenger seat and installed in the cabin ceiling sections.
Cockpit is ventilated with air scooped from two intakes on both sides of the fuselage nose, and ducted to floor-installed outlets. The cockpit is also equipped with two ventilation fans.
The electrical-powered air conditioner unit, with provision for either starter-generator or ground power supply, ensures cockpit and cabin air temperature reduction (even with engines OFF) of 10 to 12oC for ambient temperatures ranging from 30 to 40oC.
The air conditioner unit of 20,000 BTU capacity uses HFC-13A refrigerant as working fluid.
Air is scooped from the cabin rear by
ventilation fans, cooled down in the two heat-exchanger (evaporator) units,
and then ducted through ventilation channels to the individual airblow ports
installed at each passenger seat and in the cockpit.
The basic source of electrical power are two starter-generators of 28V D.C. and 12 kW power output each (operating in the generator mode), supplying power in parallel to a single bus, from which all electric loads are powered and the batteries charged. The emergency power supply source are two Nickel-Cadmium batteries of 26Ah capacity each, which can be also used for engine starting.
In addition, the electric power system includes two voltage regulator and generator protection units, and a ground power connection.
The secondary electric power supply sources are two transistor converters of 200/115V, 400Hz output and 1500 VA capacity each, supplying power to the cockpit windshield icing protection systems, two 250 VA converters, and a transformer unit to ensure power supply of 115V AC, 36V AC, 26V AC voltage (avionics, hydraulic system pressure gauging system).
The power output of a single generator is sufficient to cover electric power requirement from all loads installed onboard the airplane.
During normal operation, all electric power sources (batteries and generators) operate in parallel and supply power to a single bus.
With both generators failed, the batteries energize the emergency power supply bus, which supplies power to the primary electrical loads, systems affecting flight safety and flight/navigation instruments.
A standard ground power unit (GPU) connection has been installed in the forward fuselage section to ensure external power supply for ground maintenance and air-conditioner operation with engines OFF.
The cockpit and instrument panel lighting has been effected by a combination of internal instrument illumination and spot lights with light intensity regulation capability. General cabin illumination is provided from deflectable ceiling panels, while the cockpit light comes from a ceiling-installed lamp.
A lamp provided in the aft fuselage illuminates the cargo compartment and stairs or ramp.
External lighting includes position and anti-collision lights. Landing and taxi lights are installed in the fuselage forward section.
Flight instruments are supplied with total and static pressure from Pitot tubes (PWD-5 probes) installed on both fuselage sides. The Pitot tube on the port side supplies total pressure data to the flight/navigation instruments at the pilot-in-command station, while that on the starboard to the corresponding instruments at the co-pilot station. Static pressure data for the flight/navigation instruments are provided from static pressure receivers installed inside the fuselage.
The connected chambers of the static pressure receivers of both Pitot tubes constitute a stand-by static pressure source, with the RH (starboard) Pitot tube functioning as a stand-by source of total pressure information.
When the „STATIC” valve on the LH vertical control panel is switched from the „PRIMARY” to „STAND-BY” position, the flight/navigation instruments at the pilot-in-command station receive static pressure data from the stand-by source.
The flight instruments are switched over to stand-by source data supply by means of static and total pressure valve levers.
The starboard Pitot tube supplies also the airspeed information to the flight data recorder.
Pitot heads are fitted with an electric anti-icing system.
The set of instruments arranged on the cockpit panels provides for IFR/VFR (instrument and visual) flying capability, day and night.
The center forward cockpit features a classic-style, T-configuration instrument panel.
The LH and RH instrument panels, located directly in front of each pilot’s station, incorporate flight and navigation instruments. The center panel features navigation and communication unit clusters, including a weather radar and a GPS receiver, as well as all engine operation monitoring instruments and fuel gauge indicators.
The anti-glare screen mounted over the instrument panel incorporates a built-in center control panel including automatic pilot controls and annunciator lights of the primary failure-, fire-, and limit torque exceedance warning system.
The center support of the instrument panel is provided by the center control panel unit featuring engine control levers, and trim tab/flap position indicators. The upper (overhead) control panel contains an array of annunciator lamps, combined with verbal warning, and sets of switches for engine starting, fuel system control, and master switches for power supply and avionics.
The LH side control panels contain controls for cockpit and instruments lighting, flight data recorder, entry door operation and hydraulic system monitoring, pressure setting and flight/navigation instruments power supply switches.
The RH side control panels include circuit breakers for primary and emergency electric power supply, air-conditioning and anti-ice system ON/OFF switches, etc.
All controls and test system elements have been designed in compliance with FAR 23, while ensuring minimum pilot workload.
Radio/navigation equipment provides radio communication and working out of the radio/navigation data.
Standard equipment of the airplane consists
of three systems:
Ø VHF communication system,
Ø Active response system,
Ø Navigation system:
ü VOR/LOC/GS/MKR,
ü ADF,
ü Gyro compass.
Communications
The VHF system operates based on two KTR 908 (COMM1,COMM2) radios. Internal communication and radio beacon signals monitoring are effected by means of two KMA24H-70 audio selectors. The airplane is fitted with an emergency locator transmitters (ELT) EBC 502 operating at three rescue frequencies 121.5, 243 MHz.
Active Response
The system operates based on the MST 67A transponder (mod A, C and Mod S TCAS Compatibile), operating in conjunction with a digital air data computer, in communication with ground air traffic control. Besides the code, the system automatically transmits airplane altitude information.
Navigation
VOR/LOC/GS/MKR system based on two KNR 634A (NAV1, NAV2) navigation receivers providing for standard VOR navigation.
The system output is displayed on the EFIS 50 Electronic Horizontal Situation Indicator (EHSI) (LH & RH instrument panels). The navigation data developed by the system are supplied to the automatic pilot. The KNR 634A navigation system is provided with a localizer (LOC), glide slope (GS) and marker receivers.
The data displayed on the EFIS 50 Electronic Horizontal Situation Indicator include:
- magnetic course of a typical compass card (course marker),
- airplane heading (radial),
- lateral deviation from the course (cross-track angle),
- radio beacon or waypoint TO/FROM indications,
- radiocompass (ADF) indications,
- glide slope; and
- marker information
The LCR 92S12 laser platform provides magnetic course information signal, which is displayed on both EFS 50 Electronic Horizontal Situation Indicators (LH & RH instrument panels). The platform features a magnetic correction switch-off provision, which can be used when magnetic course correlation function is disengaged, and navigation is continued based on the gyroscopic course. The laser platform also supplies roll and pitch data for both EFS 50 Electronic Attitude Director Indicators (EADI) (LH & RH instrument panels).
The reserve 520 10B Artificial Horizon is installed on central instrumental panel.
For regions of poor VOR-station coverage, the airplane will feature a KDF 806 radio-compasses (ADF1) whose input is displayed on both EFS 50 Electronic Horizontal Situation Indicators (LH & RH instrument panels).
Additionally the airplane in standard configuration featuring following systems:
- Navigation System (NAV3), operating based on the KLN 900 GPS receiver. Navigation data from the KLN 900 can be supplied to the autopilot. The KLN 900 GPS features a vertical navigation function to provide for a GPS landing approach capability. This is an extra instrument landing approach system in addition to the standard ILS existing on the plane. Navigation data, including a flight plan, generated by the GPS receiver, can be displayed on the Electronic Horizontal Situation Indicators (LH & RH instrument panels) at all times, as pilot-selected from the EFIS control panel,
- Second laser platform LCR 92S12 constitute another, independent source of magnetic course information as well as of pitch and roll data. The information is displayed on EFIS indicators, with the course information source selected from HDG1, HDG2 switch,
- DME KDM 706A (Distance Measuring Equipment) tuned from two navigation data sources (VOR1, VOR2), providing for angular/distance navigation. The DME output is displayed on EFIS indicators,
- KRA 405B Radio-Altimeter provides for a very precise altitude measurement up to 2500 feet. The radio-altimeter indications are displayed on the Electronic Horizontal Situation Indicators on the LH and RH instrument panels. The pilot can select to have the reading displayed on both EFS 50 EHSI’s.
- Second KDF 806 Radiocompass (ADF2) facilitates navigation at landing approach when the airdrome is not equipped with the ILS. The ADF indications are displayed on both Electronic Horizontal Situation Indicators (EFIS) (LH & RH instrument panels), with the information source pilot-selected between ADF1 or ADF2 from the EFIS control panel.
- KHF 1050 long-range communications HF Radio.
Airplane optional radio/navigation equipment:
- RDR 2000 Weather Radar to depict weather situation within the radius of up to 240 miles in both horizontal and vertical section. Weather conditions can be displayed on both EHSI’s (LH & RH instrument panels).
- EGPWS Mk. VI System,
- TCAS CAS 67 System,
- KFC 325 Autopilot. The KFC325 Automatic Flight Director is a three-axes integrated system, which combines, in a single computer, autopilot functions with pre-determined functions of a Flight Director system (installed only on version MPA).
The KCP 220 computer from the autopilot package works out all input signals for the Flight Director commands and autopilot decisions (roll, pitch, trim), and provides for continuous monitoring of the information. The autopilot co-operates with the Electronic Horizontal Situation Indicator EHSI and EADI Electronic Artificial Horizon (EFS 50) installed on the LH instrument panel. The flight director information can be switched over for display on the EADI indicator on the RH instrument panel. Navigation input for the autopilot is supplied from the KNR 634A primary navigation system (NAV1) or from secondary navigation system (NAV2) or from the KLN 900 GPS receiver, depending on which navigation system has been selected by the pilot. The autopilot executive elements are the pitch-, roll-, yaw- and elevator trim tab servos. The KDC 222 air data computer provides airspeed, altitude, vertical and lateral acceleration information. The system ensures electrical control for the elevator trim tab, along with the automatic trim system. The arrangement also features a manual elevator trim tab control capability with the autopilot OFF (disengaged) or if a failure exists in the automatic control system. In the case of autopilot failure, the autopilot is disengaged from a control wheel-installed AP DISCONNECT switch.
With the autopilot not installed, the elevator trim tab is electrically controlled by means of the autopilot–package component servo, as well as manually, by means of a knob installed on the cockpit ceiling.
The SAS warning system provides for:
- annunciation of status information (green lamps)
- warning information (yellow lamps)
- failure/emergency warning (red lamps)
The latter indicator light, i.e. red lamps, give warning of:
- exhaust gas temperature limit exceedance
- limit torque exceedance
- minimum oil pressure
- engine fire
and furthermore, they provide warning of:
- stalling speed approach (light and aural warning)
- maximum operating speed (aural warning).
The function of the installed optionally Solid State Flight Data Recorder (SSFDR) is to record the following information:
ANALOG PARAMETERS ONE-TIME SIGNALS
1. Duty parameters: 1. Autopilot ON
(a/c, No., Time, Data) 2. Icing
2. Time. 3. Airframe Pneumatic De-Ice System ON
3. Date (if installed optional equipment)
4. Vertical Acceleration 4. Autofeathering Armed, LH
5. Horizontal Acceleration 5. Autofeathering Armed, RH
6. Elevator Position 6. Manual Prop Feathering, LH
7. Elevator Trim Tab Position 7. Manual Prop Feathering, RH
8. Rudder Position 8. Fire in Engine, LH
9. Flap Position 9. Fire in Engine, RH
10. Aileron Position 10. Low Fuel (Reserve)
11. Indicated Airspeed 11. Spoiler Deployment
12. Pressure Altitude 12. External Radio Communications
13. Propeller Speed, LH Operating
14. Propeller Speed, RH 13. Generator OFF, LH
15. Engine Compressor Turbine Speed, LH 14. Generator OFF, RH
16. Engine Compressor Turbine Speed, RH 15. Minimum Oil Pressure, LH
17. Engine Torque, LH 16. Minimum Oil Pressure, RH
18. Engine Torque, RH 17. Limit Exhaust Gas Temperature, LH
19. Pitch Attitude 18. Limit Exhaust Gas Temperature, RH
20. Roll Attitude 19. Max. Prop. Shaft Torque, LH
21. Magnetic Course 20. Max. Prop. Shaft Torque, RH
22. Geometrical Attitude 21. Thrust-Reverse Lock Removed, LH
23. Emergency Power Supply Bus Voltage 28V DC 22. Thrust Reverse Lock Removed, RH
24. Emergency Power Supply Bus Voltage 115V AC 23. Prop Heating OFF, LH
25. Emergency Power Supply Bus Voltage 36V AC 24. Prop Heating OFF, RH
25. Slat Deployment, LH
26. Slat Deployment, RH
Empty Weight, Min Standard Equipment Configuration 4090 ± 10 kg (8950±22 lbs)
Maximum Takeoff Weight 7500 kg (16534 lbs)
Maximum Landing Weight 7500 kg (16534 lbs)
Maximum Weight, Zero Fuel 6900 kg (14550 lbs)
Maximum Useful Load 3090 kg (6803 lbs)
Maximum
Payload
2300 kg (5070 lbs)
- up to 2000 kg (4409 lbs) inside passenger/cargo cabin
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up to 300 kg (662 lbs) inside underfuselage
pod (if instaled)
Minimum Weight for Flight 4700 kg (10420 lbs)
Maximum Fuel Weight/Volume in Wing Tanks 1766 kg/2280 l./600 US Gal.
Maximum Fuel Weight/Volume in Auxiliary Fuselage Tank 1620 kg/2090 l./550 US Gal.
Maximum Fuel Weight/Volume in Airplane 3286 kg/4240 l./1100 US Gal.
Airplane Center-of-Gravity Limits 22¸33% MAC
4.482÷4.710 m RCS
(Reference Coordinate System)
Max. Operating Speed, VMO 355 km/h (192 KTS)
Maneuvering Speed, VA 244 km/h (132 KTS)
Min. Control Speed, Critical Engine Failure,VMC 153 km/h ( 82 KTS)
Safety Speed for Takeoff 170 km/h ( 91 KTS)
Minimum Airspeed 170÷180 km/h (92÷97 KTS)
Stall Speed, Takeoff Configuration 123 km/h (66 KTS)
Rate-of-Climb 12 m/s (2 160 ft/min)
Takeoff Run 255 m (835 ft)
Takeoff Distance (to 35 ft.) 325 m (1 065 ft)
Landing Roll 235 m (770 ft)
Landing Distance (from 50 ft.) 560 m (1 836 ft)
Maximum Range (Fuel in Wing Tanks)
at 3000 m (10000 ft) altitude, 45 min.
Navigational Fuel Reserve 1450 km (785 NM) at 3000 m altitude,
18 passengers, 45 min. Navigational Fuel Reserve
1200 km (650 NM)
at cruise altitude of 6000 m
(~20000 ft)
with 45 min.
Navigational Fuel
Reserve
1800 km (975 NM)
Limit Operating Load Factors
- Cruise Configuration (+3.0) / (-1)
- Landing Configuration (+2) / (0)
Max. Operating Altitude 3000¸4000 m (9 842¸13 123 ft)
Max. Altitude with Oxygen Supply 7 600 (25 000 ft)
Service Ceiling, One Engine Inoperative 3 750 m (12 136 ft)
Operating Ambient Temperature Range - 50oC to +50oC
Min. Runway Capacity 5.5 kG/cm2 (78 psi)
Approved Kinds of Operations IFR, night and day
- Wing Span 22.06 m (72.4 ft)
- Length, Overall 13.10 m (43 ft)
- Height (Empty) 4.90 m (16 ft)
- Horizontal Stabilizer Span 5.14 m (16.8 ft)
- Prop Blade Ground Clearance 0.81 m (2.6 ft)
- Lift Surface Loading 188.7 kG/m2 (2 683 psi)
Landing Gear
-
Wheel
Track
3.4 m (11 ft)
- Wheel
Base
4.35 m (14.3 ft)
- Tyre Size:
- Main Wheel 720x310 mm (28.3 x 12.4 in)
- Nose Wheel 561x169 mm (22.1 x 6.65 in)
Cabin
- Length 5.26 m (17.2 ft)
- Width 1.74 m (5.7 ft)
- Height 1.72 m (5.7 ft)
- Volume 13.5 m3 (474.7 cu.ft)
Forward (Side) Door
- Width 0.59 m (2 ft)
- Height 1.20 m (3.9 ft)
Cargo Door, Leaves Hydraulically-Opened Into Fuselage Interior
- Width 1.20 ¸ 0.9 m (4 ÷ 3 ft)
- Length .60 m (8.5 ft)
Emergency Exits
- Width 0.62 m (2 ft)
Height 0.93 m (3 ft)
AVIONICS:
Two (2) KNR 634A NAV/MKR Receivers # 1, # 2
One (1) KLN 900 GPS Receiver
One (1) KDM 706A DME
One (1) KRA 405B Radar Altimeter
One (1) KHF 1050 HF Transceiver
One (1) RDR2000 Weather Radar with KMD 540MFD
One (1) KFC 325 3-axis Autopilot (1 set) - option
Two (2) AHRS LCR92S12 Platforms #1, #2 (1 set)
One (1) KAD 481 Air Data Computer (1 set)
Two (2) KMA 24H-70 Audio/Marker Panels (2 set)
Two (2) H10-40 Headsets
Two (2) KTR 908 (2) VHF Radio # 1, # 2
Two Frequency ELT EBC 502
One (1) MST76A Mode A, C, S, TCAS compatible Transponder
Two (2) KDF 806 (2) ADF # 1, #2
EGPWS Mk.VI - option
TCAS CAS 67 - option
SSFDR Flight Data Recorder
Cockpit Voice Recorder FA2100
ENGINE INSTRUMENTS:
L.H. & R.H. Engine Inter-Turbine Temperature (ITT) Indicators
L.H. & R.H. Engine Oil Pressure and Temperature Indicators
L.H. & R.H. Engine RPM (Ng) Indicators, Turbine
L.H. & R.H. Propeller RPM (Np) Indicators
L.H. & R.H. Engine Torque (TQ) Indicators
L.H. & R.H. Engine Fuel Flow Indicators
Fuel Quantity Indicator w/Total Fuel Indication
Fuel Pressure Indicator (L.H./R.H. Engine Switch)
Inlet Air Temperature Indicator (L.H./R.H. Engine Switch)
FLIGHT INSTRUMENTS:
EFS 50 Electronic Flight Indicators (EHSI and EADI); Dual (Pilot and Copilot)
Two (2) Barometric Altimeters
Two (2) Airspeed Indicators
Two (2) Turn and Bank Indicators
Two (2) Vertical Speed Indicators
Two (2) Hour Clocks
Magnetic Compass
Artificial Horizon, Standby
OAT Indicator
FLIGHT CONTROLS:
Flaperons, Elevator and Rudder Cable/Pushrod Type Control Line
Flight Controls, Dual (Pilot in Command and
Copilot)
Control Wheel
Pedals
Toe Brakes
Power Plant, Quadrant Type Controls
L.H. & R.H. Engine Fuel Condition
L.H. & R.H. Engine Power and Reverse
L.H. & R.H. Propeller Speed and Feather
Double-Slotted Wing Flaps, Hydraulically Actuated
Spoilers Hydraulically Actuated (with Automatic One Engine Failure Retraction)
Automatic Slats Retraction and Lower System with Stall Warning System
Trim System Aileron, Elevator (Dual Mechanical & Electrical) and Rudder
Main Gear Brakes, Hydraulic (with Brakes Lock)
Nose Gear Steering, Hydraulic
ELELECTRICAL POWER:
Two (2) 28V D.C. Starter/Generators (12kW Power Output Each)
Two (2) Generator Control Units
Two (2) Nickel-Cadmium Batteries (26Ah Capacity Each) with Protection Units
Two (2) 115V A.C. Converters
115/36V A.C. Transformer
Ground Power Unit (GPU) Connection
Ammeter
Voltmeter
1st and 2nd Battery Max Temperature Warning Systems
EXTERIOR LIGHTS:
Two (2) Landing and Taxi Lights (Fuselage Nose Installed)
Navigation Lights Red, Green and White (Wing Tips and Tail Installed)
Anti-Collision Lights, Strobe (Fins Installed)
INTERIOR LIGHTS:
Cockpit Ceiling Lights
Instrumental and Control Panel Lights
Cabin Ceiling Lights
Rear Ceiling Lights
Annunciator Signs
POWER PLANT:
Two PRATT&WHITNEY CANADA PT6A-65B Turboprop Engines; 1100 SHP; 6000 hr. TBO;
L.H. & R.H. Engine Max. ITT Warning Systems
L.H. & R.H. Engine Ignition System (Dual Ignitors)
L.H. & R.H. Engine Oil Pumps
L.H. & R.H. Engine Oil Coolers
L.H. & R.H. Engine Min. Oil Pressure and Chips in Oil Warning Systems
L.H. & R.H. Engine Oil Filters
L.H. & R.H. Engine Wash Rings (integral)
L.H. & R.H. Engine Vibration Isolation
L.H. & R.H. Engine Nacelles with Easily Openable Bottom and Side Covers
Fire Detection System
L.H. & R.H. Engine Fire Fighting System (Two Reservoirs)
L.H. & R.H. Engine Intake Inertial Separator
Two (2) HARTZELL HC-B5MP-3D Propellers; 5-Blade; All-Metal; Constant Speed; Full Feathering; Reversible; 3000 hr. TBO;
L.H. & R.H. Propeller Govemors
L.H. & R.H. Overspeed Govemors
L.H. & R.H. Propeller Automatic Feathering System (Engine Failure)
L.H. & R.H. Propeller Ready for Feathering and Max. TQ Warning Systems
Two (2) Propeller Spinners
Synchrophaser
FUEL SYSTEM:
Integral Fuel Tanks of 2250 l. (595 US Gallons) of Usable Fuel
L.H. & R.H. Engine (Main Tanks) Fuel Pumps (4)
L.H. & R.H. Engine Shutdown Valves
L.H. & R.H. Engine Fuel Filters (Fine Strainers)
Drain Valves
L.H. & R.H Auxiliary-Tank Jet-Stream Pumps (6)
L.H. & R.H Auxiliary-Tank Jet-Stream Pump Valves
Cross-Feed Line with Cross-Feed Valve
L.H. & R.H. Engine Fuel Contamination and Low Fuel Pressure Warning System
Low Fuel Warning System (Annunciator)
Pressure Fuelling System Shut-off Valve
HYDRAULIC POWER:
Two (2) Engine-Driven Hydraulic Pumps
Hydro-Accumulator
Hydraulic Tank (Pressurized by Ram Air)
Hydraulic Fluid Filters
Drain Valve
Ground Suction Valve
Ground Pressure Valve
Braking Pressure Gauge (L.H. & R.H. Brakes)
Hydro-Accumulator Pressure Gauge
L.H. & R.H. Hydraulic Circuit Low Pressure and Max Temperature Warning Systems
EXTERIOR:
Anti-Errosion Protection
Landing Gear, Nose (Tubeless, Low Pressure Tire)
Landing Gear, Main (Tubeless Low Pressure Tire)
Anti-Skid System
Anti-Icing System
Propellers (Electric)
Windshields (Electric)
Engine Inlets (Exhaust-Heated)
Pitot Probes (Electric)
Ice Detector
Pitot System, Dual with Pressure Source Switch
Main Door, Inward Opening, Hydraulically Actuated Two Cowers (with Lock)
Crew Door (with Lock)
Two Jettisonable Emergency Exits (with Independent Lighting)
Double Windows with Sun Shades (7)
Two (2) Bubble Windows
Retractable Steps (for Wing Climb)
Three Jack Points (Fuselage)
Tie-Down Provision
Customer-Selected External Painting Scheme
INTERIOR:
Instrument Panels
Seats (Pilot & Copilot)
Seat Belts (Pilot & Copilot) with Shoulder Restrain System (Inertia Reel of Two Shoulder Straps)
Rigid Upholstery Panels (Painted)
Cockpit Barrier
Rear Cabin Barrier
Operational Equipment Installation Points
Luggage Rack
Toilet (for 18 sets version only)
Benches
Crew Oxygen System (Two Bottles)
First-Aid Kit
Flight Engineer Headset Plug-In Socket
Additional Headset Plug-In Socket
Two (2) Fire Extinguishers (Cockpit and Cabin)
Stairs
Axe
Basic Tool Set
Tow Bar
Wheel Chocks
Support Jack
Ladder
Set of Locks
Set of Plugs and Covers
Documentation (AFM, MM etc.)
ENVIRONMENTAL:
Soundproofing
Heating System Cabin (Bleed Air Type)
Ventilation System Cockpit
Ram Air (Fuselage Nose Intakes)
Ventilation Fans (Two Instrumental Panel Mounted)
Ventilation System Cabin (Ram Air)
Air-conditioning
OPERATIONAL EQUIPMENT:
Passenger transport version:
Fixed Passenger Seats w/Seat Belts:
6 twins seats
7 single seats (for 19 passenger version only)
6 single seats (for 18 passenger version only)
Lavatory Compartment (for 18 seats version only)
Rear Partition between 19 and 20 frame
Luggage rack
Cargo transport version
cargo Hoist
restraint systems
roller floor
Paratrooper System
paratroop gate
annunciation/Control/Warning Harnesses and Attach Fittings,
Ambulance/medevac version
6 stretchers
Materials mentioned in the airplane documentation can be substituted by others, provided that they meet the requirements of the pertinent National Standards (PN) and/or they are approved material equivalents determined in the document entitled: “Polish Equivalents for the US-Made Materials in M20 Airplane”, Ref. File No. LTO-33/E/122/94, in accordance with the design/engineering change introduction regulations, and upon approval of civil airworthiness authority.
The airplane is operated “ON CONDITION”.
The airplane Maintenance Manual defines the criteria applicable to technical condition evaluation for equipment and accessory units.
In addition, there are certain service life limitations for airframe assys due to material fatigue considerations.
The airplane equipment is operated “ON CONDITION”, further to provisions of the M28 airplane Maintenance Manual.
The airplane engines and engine accessories are operated “ON CONDITION”, further to the recommendations of the PT6A-65B Engine Maintenance Manual.
The initial service life limits for the airframe and landing gear will be extended through bulletin issuance.
The airframe major assys and equipment units of time-limited service life are, as follows:
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Airframe: ¨ Initial service life 8 000 flying hours
PT6A-65B Engine: ¨ Engine TBO 6 000 flying hours
HC-B5MP-3D/M10876ANSK Propeller: ¨ TBO 3 000 hrs of engine operation or 60 months
Main & Nose Gear Wheel: ¨ Service life 6 000 takeoff/landings
Brake Assy: ¨ Service life 6 000 takeoff/landings
Main Gear & Nose Gear: ¨ Service life 6 000 takeoff/landings
Equipment (service life limits): ¨ 210944 Overspeed Governor 4 500 hrs of engine operation ¨ 23080-054 Generator-Starter 1 000 flying hrs ¨ ECN75B Fuel Pump 1 000 flying hrs ¨ ET-01-P Electromechanism 2 000 flying hrs ¨ UT-6D Electromechanism 2 000 flying hrs ¨ EPK-2T-60T Electromechanism 5 000 flying hrs .. 1394T100-3Z Turn Indicator 2 000 flying hrs
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Specification and photos are not contractual and are subject to verification upon inspection
NB: Aircraft offered for sale subject to contract, prior sale, withdrawal from the market and information regarding any aircraft or helicopter and provided verbally or in written documentation and/or contained within this e.mail or associated paper-work should be taken as a guide only in determining the suitability, including that aircraft or helicopters specification and/or performance. We highly recommend that any buyer or lessee perform their own inspections and due diligence to verify any and all technical, performance and specification information contained therein including OEM claims.
PLEASE NOTE: AIRCRAFT SPECIFICATIONS SUBJECT TO VERIFICATION UPON INSPECTION. WE DO NOT ACCEPT ANY LIABILITY FOR AIRCRAFT DEFECTS, HISTORY OR TECHNICAL RECORD ERRORS. IT IS THE BUYERS RESPONSIBILITY TO INDEPENDENTLY VERIFY THE AIRCRAFT AND COMPONENT HISTORY.
TAKE NOTICE!
PLEASE BE ADVISED THAT INFORMATION INCLUDED IS CONFIDENTIAL IN NATURE AND IS BASED ON PRE-EXISTING BUSINESS RELATIONSHIP WITH THE LEGAL OWNER OF PROPERTY DESCRIBED HEREIN (IF APPLICABLE). AS SUCH, UPON RECEIPT OF SAID INFORMATION THE RECEIVER AKNOWLEDGES THAT ANY UNAUTHORIZED CONTACT WITH SAID LEGAL SELLER WILL BE CHARACTERIZED AS A BREACH OF CONFIDENTIALITY AND SAID AGREEMENT MAY BE ENFORCED UNDER EXISTING LAW OR IN EQUITY.
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