longitudinal instability, increase in takeoff distance,
Q1-23.
What substance is used to reduce friction,
increase in control forces, increase in stall speeds,
cool metallic parts, prevent wear, and protect
decrease in flight range, and a decrease in rate of climb.
against corrosion?
The requirements, procedures, and responsibilities for
Q1-24.
What are the four methods of applying
aircraft weight and balance control are defined in the
technical manual, USN Aircraft Weight and Balance
Q1-25.
What type of lubrication fittings rests level
Control, NAVAIR 01-1B-50. Additional requirements
with the surface and will not interfere with
and/or
procedural
instructions
for
specific
moving parts?
type/model/series aircraft weight and balance control
Q1-26.
Where would you find the prewash lubrica-
are specified in the aircraft's NATOPS manuals and the
tion chart for a particular aircraft?
technical manual, Weight and Balance Data, NAVAIR
Q1-27.
What document should you consult for spe-
01-1B-40. In case of conflicting requirements,
cial safety requirements and personal protec-
procedures, or instructions, OPNAVINST 4790.2 and
tive equipment prior to using any lubricant?
the NATOPS manual take precedence over NA
01-1B-50 and NA 01-1B-40. NA 01-1B-50 takes
WEIGHING AND BALANCING
precedence over the NA 01-1B-40, pending mandatory
AIRCRAFT
resolution of the conflict through the procedures
LEARNING OBJECTIVE: Identify the
described in the NA 01-1B-50.
various methods of weighing aircraft.
WEIGHT
Recognize the flight characteristics of the
improperly weighed or balanced aircraft.
One of the basic elements of aircraft design is
aircraft weight and balance. The estimated weight and
Flight characteristics of aircraft are directly
balance of an aircraft is used in determining such
dependent upon their weight and balance conditions.
design criteria as engine requirements, wing area,
An aircraft whose weight is greater than its allowable
landing gear requirements, and payload capacity. Any
maximum gross weight, or whose center of gravity (cg)
weight change, either in manufacturing, modification,
is located outside its prescribed cg limits, may
or maintenance, will have distinct effects on aircraft
experience one or more unsatisfactory flight
performance and/or payload capability. Figure 1-16
characteristics. Some of these conditions are
Figure 1-16.--Weight terminology.
1-21
