Boeing 767 assumed temperature reduced thrust,

 

ASSUMED TEMPERATURE REDUCED THRUST 

Regulations permit the use of up 25% takeoff thrust reduction for operation with assumed temperature reduced thrust. Use of reduced thrust is not allowed on runways contaminated with water, ice, slush or snow. Use of assumed temperature reduced thrust is not recommended if potential windshear conditions exist. 






Enter the minimum assumed temperature table with airport pressure altitude and read minimum assumed temperature. If assumed temperature is below this valve, use the takeoff %N1 table to set takeoff thrust. To find assumed temperature reduced thrust, obtain the assumed temperature %N1 by entering the assumed temperature limit %N1 table with actual airport temperature and assumed temperature if operating with packs off apply the bleed adjustment shown in %N1 adjustments for engine bleeds table. Apply the altitude adjustment shown in the %N1 altitude  adjustment table. Check the resulting value by entering the minimum assumed temperature limit %N1 table with actual airport temperature and pressure altitude. Use the greater of assumed temperature limit %N1 or minimum %N1 as the assumed temperature reduced thrust %N1 determine takeoff speeds using the actual takeoff weight and assumed temperature. 


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MAX CLIMB %N1 
This table shows Max climb %N1 for a 250/290/.78 climb speed schedule. Normal engine bleed for packs on and anti-ice off. Enter table with airport pressure altitude and TAT and read %N1. %N1 adjustments are shown for packs off and anti-ice operation. 








GO-AROUND %N1
To find Max GO-AROUND %N1 based on normal engine bleed for packs on, enter the GO-AROUND %N1 table with airport pressure altitude and reported OAT or TAT read %N1. %N1 adjustments are shown for packs off and anti-ice operation. 







FLIGHT WITH UNRELIABLE AIRSPEED/TUBULENT AIR PENETRATION 
Pitch attitude and average %N1 information is provided for use in all phases of flight in the event of unreliable airspeed/mach indications resulting from blocking or freezing of the pitot system. Loss of Radome or turbulent air may also cause unreliable airspeed mach indications. The cruise table in this section may also be used for turbulent air penetration. Pitch attitude is shown in bold type for emphasis since altitude and/or vertical speed indications may also be unreliable. 






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