Safety Investigation Report 2018:1 Factual Information/1.6/1.6.8 Aircraft Systems/13
SAFETY INVESTIGATION REPORT MH370 (9M-MRO)
13) Engines
The aircraft is fitted with two engines (Model: RB211 TRENT 892B- 17) manufactured by Rolls-Royce. The RB211 TRENT 892B-17 engine is a high bypass turbofan (bypass ratio of 6.4:1 at a typical cruise thrust) axial flow, three-rotor with a single low pressure fan driven by a five-stage, low-pressure turbine.
The engine has an eight-stage intermediate pressure compressor driven by a single-stage turbine and a six-stage high pressure compressor driven by a single-stage turbine.
The engine take-off thrust is 92,800 lb and weighing approximately 15,700 lb (7,136 kg). The engines are certified in accordance with the US FAA Type Certificate E00050EN.
The FAA Type Certificate Data Sheet certifies that the engines meet the smoke and gaseous emission requirements of the US FAR 34. The engine is certified under FAR Part 36 Stage 3 Noise regulation.
The engine is fitted with a digital Electronic Engine Fuel Control System and it interfaces with many systems and components in the form of primary analogue or ARINC 629 buses.
The following analogue engine fuel and control system interfaces and correlates with the other systems for supply and feedback:
- Engine ignition - ignition unit power
- Engine air - actuator and valves
- Engine controls - resolver excitation and position
- Engine indicating - engine parameter data
- Engine exhaust - thrust reverser operations
- Engine oil - oil cooling and indications
- Engine starting - auto-start and manual start
- Electrical power - aircraft power from the Electrical Load Management System (ELMS)
The following ARINC 629 engine fuel and control system interfaces and correlates with other systems for supply, control and indication data:
- AIMS - indication, air data and flight management control
- Cockpit controls - switch position and indication
- Flap Slat Electronic Unit (FSEU) - Flap indication
- Proximity Switch Electronic Unit (PSEU) - Landing gear lever position
- Air Supply Cabin Pressure Controller (ASCPC) - Pneumatic system demand
The RB211 TRENT 892B-17 engine Electronic Engine Control (EEC) serves as the primary component of the engine fuel control system and uses data from the engine sensors and aircraft systems to control the engine operations. The EEC controls most of the engine components and receives feedback from them. These digital data go to the Engine Data Interface Unit (EDIU) and send the signal to the AIMS. The AIMS transmits and receives a large amount of data to and from the EEC. These include:
- Engine bleed status - EEC thrust limit calculations
- Air data - EEC thrust limit calculations
- Engine data – system requirements
- Autothrottle Engine Pressure Ratio (EPR) trim - thrust balancing
- Condition monitoring - performance tracking
- Maintenance data - trouble shooting
- Primary display system data - indication.