INTRODUCTION

According to the requirement of CCAR-25 and FAR-25,XI'AN AIRCRAFT COMPANY has designed and developed a short-medium range aircraft MA60(Modem Ark 60)that is a twin turbo-prop multi-role aircraft with a commuter services as its primary roles. It has a maximum take-off weight of 21,800kg and a seating capacity of up to 60 passengers in the high density version. With a pressurized cabin, the aircraft possesses the level of comfort comparable to trunk aircraft. The aircraft is well-suited to fulfil a variety of other roles such as executive transport, light package carrier, remote sensing and aerial research services, coast guard, border patrol, air ambulance and other community services, etc.

MA60 is a state-of-art design that can be a cost-effective solution in a wide variety of roles.

The aircraft has the following features:  

* A1lweather,day/night night capability 
* Pressurized cabin
* Operability from semi-prepared runways
* Two-man operation flight deck 
* Operability from high altitude airfields on hot days with little or no compromise on take-off weight
* Cabin comfort level matching with that of trunk aircraft 
 
POWER PLANT

MA60 is powered by two Pratt and Whitney Canada PW-127J engines driving two 247F-33.962m diameter 4 bladed propellers supplied by Hamilton Standard, USA. The engines are mounted on wings. The power plant has the following features:

* Light weight
* Three axles free turbine engine
* EEC control system supplies accurate control and monitoring
* β control system
* Low fuel consumption, 30% lower than normal technology engine
* Max. Take-of power of 2,750SHP
* Power from free turbine is transmitted to the propeller through a reduction gear box.
* propellers are constant speed, variable pitch (feathering to reverse)and auto synchronized One turbo generator GTCP36-150,made by Honeywell, USA, as APU
* Air conditioning on the ground to improve the cabin environment
* Ground electric power supply and starting engines

FUEL SYSTEM

* Two integral wing fuel tanks (two groups)and two bladder-type tanks with usable capacity of 5,200 liters. Single point pressure refueling offered
* Gravity reading is available
* Normal fuel supply by injection pumps
* Electrical pumps supply the fuel under the emergency condition
* Fuel can also be supplied by gravity now
* Electrically operated cross-feed valve ensures supply of fuel to a single engine from both tanks or to both engines from single tank
* Capacitance gauging show contents of each wing tank and total contents
* Rate of fuel indicator for each engine

PERFORMANCE

* Balanced take-off field length (MTOW) Sea level，ISA: 1,300m H=1,219m,ISA+10℃: 1,600m
* Landing field length required (MLW) Dry runway，at destination Sea level，ISA: 1,400m
* Single-engine net ceiling (95%MTOW) ISA:3,200m
* Maximum operational cruise altitude: 7,620m
* Max cruising speed (TAS) 96%MTOW,ISA H=5486 450km/h STAGE PERFORMANCE ISA，still air，Cruise altitude 6,096m,IFR reserves
 
STRUCTURES

Structure designed for 30,000FH,25000 take-off/landings,or 25 calendar years servicing life.

RELIABILITY

Achieving a high degree of reliability has been one of the major goals in the design and this has resulted in selecting systems, sub-systems and other equipment which are well proven, certificated and have established a good track record of reliability. For example, the PW-127family of engines has estab1ished over the years a reputation for extremely reliable engines. The integrated digital avionics system has inherently a high level of reliability (MTBF is 8,000-12,000 flight hours)with practically no maintenance-intensive component which might wear out or break down. Redundancy has been built into all critical areas so that the overall system reliability is high.

MAINTAINABILITY and AVAILABILITY

Attention has been given right from the beginning for easy maintenance and thus to increase aircraft dispatch rate.

Equipment needing inspection/maintenance have been provided with the easy access, the PW-127 engine is of modular construction and thus easy to maintain. Furthermore, the cowling is designed in such a way that the front and rear ends are large and panels to have full access to servicing points on engine and aircraft accessories. The avionics equipment, hydraulic system and the air conditioning system bays, all have large doors for easy assess.