Piper WARRIOR III PA-28-161, Руководство по эксплуатации для пилотов

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4.25 CLIMB
The best rate of climb at gross weight will be obtained at 79 KIAS. The
best angle of climb may be obtained at 63 KIAS. At lighter than gross weight
these speeds are reduced somewhat. For climbing en route, a speed of 87
KIAS is recommended. This will produce better forward speed and in-
creased visibility over the nose during the climb.
When reaching the desired altitude, the electric fuel pump may be
turned off.
4.27 CRUISE
The cruising efficiency and speed is determined by many factors, including
power setting, altitude, temperature, loading and equipment installed in the
airplane.
The normal cruising power is 55% to 75% of the rated horsepower of the
engine. Airspeeds which may be obtained at various altitudes and power
settings can be determined from the performance graphs provided by Section
5.
Use of the mixture control in cruising flight significantly reduces fuel
consumption while reducing lead deposits when alternate fuels are used. The
mixture should be full rich when operating above 75% power, and leaned
during cruising operation when 75% power or less is being used.
To lean the mixture for best power cruise performance place the
mixture control full forward and set the throttle slightly below (approximately
35 RPM) the desired cruise power setting and lean the mixture to peak RPM.
Adjust the throttle, if necessary, for final RPM setting.
For Best Economy cruise, a simplified leaning procedure which
consistently allows accurate achievement of best engine efficiency has been
developed. Best Economy Cruise performance is obtained with the throttle
fully open. To obtain a desired cruise power setting, set the throttle and
mixture control full forward, taking care not to exceed the engine speed
limitation, then begin leaning the mixture. The RPM will increase slightly
but will then begin to decrease. Continue leaning until the desired cruise
engine RPM is reached. This will provide best fuel economy and maximum
miles per gallon for a given power setting. See following CAUTION when
using this procedure.
4.25 CLIMB
The best rate of climb at gross weight will be obtained at 79 KIAS. The
best angle of climb may be obtained at 63 KIAS. At lighter than gross weight
these speeds are reduced somewhat. For climbing en route, a speed of 87
KIAS is recommended. This will produce better forward speed and in-
creased visibility over the nose during the climb.
When reaching the desired altitude, the electric fuel pump may be
turned off.
4.27 CRUISE
The cruising efficiency and speed is determined by many factors, including
power setting, altitude, temperature, loading and equipment installed in the
airplane.
The normal cruising power is 55% to 75% of the rated horsepower of the
engine. Airspeeds which may be obtained at various altitudes and power
settings can be determined from the performance graphs provided by Section
5.
Use of the mixture control in cruising flight significantly reduces fuel
consumption while reducing lead deposits when alternate fuels are used. The
mixture should be full rich when operating above 75% power, and leaned
during cruising operation when 75% power or less is being used.
To lean the mixture for best power cruise performance place the
mixture control full forward and set the throttle slightly below (approximately
35 RPM) the desired cruise power setting and lean the mixture to peak RPM.
Adjust the throttle, if necessary, for final RPM setting.
For Best Economy cruise, a simplified leaning procedure which
consistently allows accurate achievement of best engine efficiency has been
developed. Best Economy Cruise performance is obtained with the throttle
fully open. To obtain a desired cruise power setting, set the throttle and
mixture control full forward, taking care not to exceed the engine speed
limitation, then begin leaning the mixture. The RPM will increase slightly
but will then begin to decrease. Continue leaning until the desired cruise
engine RPM is reached. This will provide best fuel economy and maximum
miles per gallon for a given power setting. See following CAUTION when
using this procedure.
PIPER AIRCRAFT CORPORATION SECTION 4
PA-28-161, WARRIOR III NORMAL PROCEDURES
PIPER AIRCRAFT CORPORATION SECTION 4
PA-28-161, WARRIOR III NORMAL PROCEDURES
ISSUED: JULY 1, 1994 REPORT: VB-1565
4-21
ISSUED: JULY 1, 1994 REPORT: VB-1565
4-21