FLIGHTCHECK 6.80 MANUAL
FLIGHTCHECK 6.80 SERIES

These steps include validated analysis, test, or service experience which ensures that the combination of loads, material properties, environmental influences and operating conditions, including the effects of other engine parts influencing these parameters, are sufficiently well known and predictable so that the operating limitations can be established and maintained for each engine life-limited part. (a ) An engineering plan that contains the steps required to ensure each engine life-limited part is withdrawn from service at an approved life before hazardous engine effects can occur. Turbojet and Turbofan, only: в€’10 to 0 вЏ (в€’23 to в€’18 вЊ) Must show repetitive, stabilized operation (or 45 minutes max). Turbojet and Turbofan, only: 10 to 18 вЏ (в€’12 to в€’8 вЊ)ДЄlternating cycle: First 1.7 g/m 3 (1 minute), Then 0.3 g/m 3 (6 minute) (b) Must show repetitive, stabilized operation for higher powers (50%, 75%, 100%MC). (a) 10-minutes for power below sustainable level flight (idle descent). Table 1 - Conditions That Must Be Demonstrated by an Engine Test Condition

During operation at rated takeoff power and rated maximum continuous power, the load imposed by each accessory used only for an aircraft service must be the limit load specified by the applicant for the engine drive or attachment point. Each accessory drive and mounting attachment must be loaded. An engine that is equipped with a propeller shaft must be fitted for the endurance test with a propeller that thrust-loads the engine to the maximum thrust which the engine is designed to resist at each applicable operating condition specified in this section.

below the limiting temperature, and the oil inlet temperature must be maintained within в‘0 degrees F. During the runs at rated takeoff power and for at least 35 hours at rated maximum continuous power, one cylinder must be operated at not less than the limiting temperature, the other cylinders must be operated at a temperature not lower than 50 degrees F. During the endurance test the engine power and the crankshaft rotational speed must be kept within в“ percent of the rated values. The runs must be made in the order found appropriate by the Administrator for the particular engine being tested.

FLIGHTCHECK 6.80 SERIES

Each engine must be subjected to an endurance test that includes a total of 150 hours of operation (except as provided in paragraph (e)(1)(iii) of this section) and, depending upon the type and contemplated use of the engine, consists of one of the series of runs specified in paragraphs (b) through (e) of this section, as applicable. Mixed Phase and Ice Crystal Icing Envelope (Deep Convective Clouds) Special Requirements: Turbine Aircraft EnginesДesign and test requirements for Early ETOPS eligibility.Д¬ertification Standard Atmospheric Concentrations of Rain and Hail Turbine, compressor, fan, and turbosupercharger rotor overspeed.Дesign and Construction Reciprocating Aircraft EnginesД«lock Tests Reciprocating Aircraft EnginesДesign and Construction Turbine Aircraft EnginesД«lade containment and rotor unbalance tests.Д®ngine tests in auxiliary power unit (APU) mode. Selection of engine power and thrust ratings.Д®ngine mounting attachments and structure.

FLIGHTCHECK 6.80 MANUAL

Instruction manual for installing and operating the engine.Д®ngine ratings and operating limitations. Instructions for Continued Airworthiness. Airworthiness Standards: Aircraft Engines

Flightcheck 6.80