Mooney M20V Acclaim Ultra, Руководство по эксплуатации для пилотов

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MOONEY
M20V ACCLAIM ULTRA
SECTION VI
WEIGHT AND BALANCE
6 - 3
AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE - 03-16-2017
INTRODUCTION
This section describes the procedure for calculating loaded aircraft weight and moment for vari-
ous flight operations. In addition, procedures are provided for calculating the empty weight and
moment of the aircraft when the removal or addition of equipment results in changes to the
empty weight and center of gravity. A comprehensive list of all Mooney equipment available for
this airplane is included in this section. Only those items checked (X) were installed at Mooney
and are included in the empty weight- and- balance data.
The aircraft owner and/or pilot, has the responsibility of properly loading the aircraft for safe
flight. Data presented in this section will enable you to carry out this responsibility and insure that
your airplane is loaded to operate within the prescribed weight and center- of- gravity limitations.
At the time of delivery, Mooney International Corporation provides the empty weight and center
of gravity data for the computation of individual loadings. (The empty weight and C.G. (gear
extended) as delivered from the factory is tabulated on page 6- 6 when this manual is supplied
with the aircraft from the factory.)
FAA regulations also require that any change in the original equipment affecting the empty-
weight and center of gravity be recorded in the Aircraft Log Book. A convenient form for maintain-
ing a permanent record of all such changes is provided on page 6- 6. This form, if properly main-
tained, will enable you to determine the current weight- and- balance status of the airplane for
load scheduling. The weight- and- balance data entered as your aircraft left the factory, plus the
record you maintain on page 6- 6, is all of the data needed to compute loading schedules.
The maximum certificated gross weight for the CMI powered M20V is 3368 lbs (1528 Kg) for
Takeoff and 3200 pounds (1452 Kgs) for Landing. Maximum useful load is determined by sub-
tracting the corrected aircraft empty weight from its maximum gross weight. The aircraft must be
operated strictly within the limits of the Center- of- Gravity Moment Envelope shown on page
6- 10.