. The excellent low noise and emission characteristics of the BR710 ensure access to all local airports around the globe. The BR710 is the cleanest and quietest engine in its class, with margin to spare it has capability to meet future, tougher rules. The BR710 is the first member of the successful BR700 family with more than 3,600 BR700 engines in service with customers worldwide.
By the end of 2016 the BR710 had accumulated about 9.9m Engine Flying Hours since EIS with about 3,000 engines in service. CorporateCare is a total risk transfer program that increases asset value and liquidity. For a fixed hourly cost CorporateCare covers all Engine parts and labour when the time comes for the engine to be sent to an authorised Rolls-Royce overhaul facility. It covers all parts and labour for mandatory and recommended service bulletins, as well as unscheduled shop visit costs.
This comprehensive coverage permits accurate budgeting based on each aircraft’s forecast utilisation. The Rolls-Royce global network of repair and overhaul operations ensures convenient access to the required facilities. Quality is assured as only authorised Rolls-Royce facilities are used for CorporateCare. CorporateCare covers.
Rolls Royce 250 Maintenance Manual C20
G e n e r a l Engine description includes a discussion of each major component and each major system of the en- gine. Numerical values in this manual are given in terms standard to existing practices in the United States. 2018 dodge big horn 4x4 service manual.
Rolls Royce 250 C30p
NOTE: The M250- -C20R/1 se ries engine s contain eith er a large compr essor scr oll or a reduced scroll. A M250- -C20R/1 engine assembly contain ing a large compres sor scroll (single port customer bleed) is identified as P/N 23034148.
A M250- -C20R/1 engine assembly containing a reduced scroll (dual port cust omer bleed) is identifi ed as P/N 230382 00. For illustra tion purpos es, the reduce d scroll engine configur ation P/N 23038200 will be referred to as M250-C20R/1(RS) throughout this manual. NOTE: The M250- -C20R/2 Ser ies engine (P/N 2303 5212) has a Sundstr and/Pe sco, Argot ech/TR W or CECO fuel pump assembly. A M250- -C20R/2 engine assembly (P/N 23053265) has a CECO suction fuel pump. For identification purposes, the M250- -C20R/2 engine with a CECO fuel pump will be identified as M250-C20R/2(SP) throughout this manual.
NOTE: The M250- -C20R engine (P/ N23033 373) is the same as the M250- -C20R/1 (RS) exce pt that the C20R gearbox has a kidney pad housing, impending by-pass oil filter indicator, and the ignitio n exciter is airfra me mounted. A M250- -C20R engine assembly with a rear mount, two 6 cubic inch accum ulator s and a double check valv e is identifie d as P/N 2305959 7. For identification purposes, this second M250-C20R engine assembly will be identified as M250-C20R(ST).
NOTE: This manual addresses M250- -C20R, M250- -C20R/1, M250- -C20R/2 and M250- -C20R/4 en- gines. For additional information concerning M250- -C20R series engine designations or air- frame applications, refer to M250-C20R CSL 4002. Components The major engine components are a compressor, combustion section, turbine, and power and acces- sory gearbo x. Compressor The compressor assembly consists of a compressor front support assembly, compressor rotor assembly, compr essor case assembly, and compressor diffuser assembly. Air enters the engine throug h the compre ssor inlet and is compressed by four axial compresso r stages and one centri f- ugal stage. The compres sed air is dischar ged through the scroll type dif fuser into two ducts which convey the air to the combus tion section.
Co mb us ti on Se ct ion The combustio n section consists of the outer combustion case and the combus tion liner. A spark igniter and a fuel nozzl e are mounted in the aft end of the outer combus tion case. Air enters the single comb ustion liner at the aft end, through holes in the liner dome and skin. The air is mixed with fuel spraye d from the fuel nozzle and combustion takes place. Combu stion gases move for- ward out of the combustion liner to the first-stage gas producer turbine nozzle. T ur bi ne The turbine consists of a gas producer turbine support, a power turbine support, a turbine and exhaus t collector support, a gas producer turbi ne rotor and a power turbine rotor. The turbine is mount ed be tween the combusti on section and the power and accessor y gearbox.
Rolls Royce 250 C30
The two-stage gas producer turbine drives the compressor and accessory gear train. The two- -stage pow- er turbine furni shes the output power of the engine. The expanded gas dischar ges in an upward direction through the twin ducts of the turbine and exhaust collector support.