2206

Question 1

is one of the many factors to have a safe and efficient flight.

Answer 1

Proper weight and balance control

Question 2

Proper weight and balance control is one of the many factors to have a

Answer 2

safe and efficient flight.

Question 3

The three equally important elements are

Answer 3

-weighing of the aircraft
-maintaining the weight and balance records
-proper loading of the aircraft

Question 4

If one of element is________, it defeats the whole purpose of the system.

Answer 4

inaccurate

Question 5

Final loading calculations are meaningless if either the aircraft has been

Answer 5

improperly weighed or the records contain an error.

Question 6

EFFECTS OF IMPROPER LOADING

Answer 6

decreases the efficiency and performance of an aircraft
failure to complete the flight or failure to start the flight.
abnormal stresses placed upon the structure, changed flying characteristics

Question 7

decreases the efficiency and performance of an aircraft:

Answer 7

• altitude
  - maneuverability
  - rate of climb
  - speed

Question 8

Aircraft can perform safely and achieve their designed efficiency only when they

Answer 8

are operated and maintained in the way their designers intended.

Question 9

The responsibility for proper weight and balance control begins with the ________ and __________ and extends to the _______ who maintain the aircraft and the ________ who operate them.

Answer 9

engineers, designers, technicians, pilots

Question 10

are engineered utilizing state of-the-art technology and materials to achieve maximum reliability and performance for the intended category.

Answer 10

Modern Aircraft

Question 11

(EWCG)

Answer 11

empty weight center of gravity

Question 12

The designers carefully determine the ideal center of gravity (CG) and calculate the ___________ from this specific location.

Answer 12

maximum allowable deviation

Question 13

The FAA-certificated ___________ or ______ who maintains the aircraft keeps the weight and balance records current, recording any changes that have been made because of repairs or alterations.

Answer 13

mechanic or repairman

Question 14

has the responsibility prior to every flight to know the maximum allowable weight of the aircraft and its CG limits.

Answer 14

pilot in command (PIC)

Question 15

reduces the efficiency of an aircraft and the available safety margin if an emergency condition should arise.

Answer 15

Excessive weight

Question 16

When an aircraft is designed, it is made as light as the required structural strength allows, and the wings or rotors are

Answer 16

designed to support the maximum allowable weight.

Question 17

The weight of an aircraft is increased, the wings or rotors must produce additional lift and the structure must support not only the additional __________but also the ________ imposed by flight maneuvers.

Answer 17

static loads, dynamic loads

Question 18

the wings of a 3,000-pound airplane must support 3,000 pounds in level flight, but when the airplane is turned smoothly and sharply using a bank angle of 60°, the dynamic load requires the wings to support twice this or

Answer 18

6,000 pounds.

Question 19

normal =
utility =
acrobatic =

Answer 19

3.8 times its weight
4.4 times its weight
6.0 times its weight

Question 20

high density altitude =

Answer 20

a condition where the air is less dense

Question 21

When operating from a high-density altitude airport, the____________ and _____________ must be consulted

Answer 21

Pilot’s Operating
Handbook (POH) or Airplane Flight Manual (AFM)

Question 22

If maximum range is required =
If maximum load is required =

Answer 22

reduce occupants or baggage
reduced (fuel) range

Question 23

OVERLOADING PROBLEMS

Answer 23

higher takeoff speed, which results in a longer takeoff run
* Both the rate and angle of climb are reduced.
* The service ceiling is lowered.
* The cruising speed is reduced.
* The cruising range is shortened.
* Maneuverability is decreased.
longer landing roll is required because the landing speed is higher
* Excessive loads are imposed on the structure, especially the landing gear

Question 24

Maximum operational weight may also be limited by the

Answer 24

departure or arrival airport’s runway length.

Question 25

Proper load distribution is also important, ______________________________within limits specified in the POH or AFM.

Answer 25

weight must be distributed to keep the CG

Question 26

If CG is too far forward, a heavy passenger or baggage should be

Answer 26

moved to the rear.

Question 27

If the CG is too far aft,

Answer 27

shifted forward.

Question 28

Fuel load should be

Answer 28

balanced laterally.

Question 29

Far more critical than for an airplane.

Answer 29

WEIGHT AND BALANCE OF A HELICOPTER

Question 30

These seating limitations are noted by a , usually on the instrument panel, and they should be strictly followed.

Answer 30

placard

Question 31

are the major sources of weight changes.

Answer 31

Repairs and alterations

Question 32

It is sometimes possible to install a ________ in order for the aircraft to operate again within the normal CG range.

Answer 32

fixed ballast

Question 33

refers to the location of the CG of an aircraft.

Answer 33

Balance control

Question 34

Its the primary importance to aircraft stability, which is a _______

Answer 34

factor in flight safety.

Question 35

This is balanced by a variable nose-up force, which is produced by a ___________________ on the horizontal tail surfaces that varies directly with the airspeed.

Answer 35

downward aerodynamic force

Question 36

If a rising air current should cause the nose to pitch up, the airplane slows and the ________ on the____________The weight concentrated at the ______________ If the nose should drop in flight, the___________ and the increased downward tail load brings the nose back up ______.

Answer 36

downward force, tail decreases, CG pulls the nose back down. , airspeed increases, level flight

Question 37

As long as the CG is maintained within the allowable limits for its weight, the airplane has

Answer 37

adequate longitudinal stability and control.

Question 38

If the CG is too far aft, it is too near the center of lift; the airplane is

Answer 38

unstable and difficult to recover from a stall.

Question 39

If the unstable airplane should enter a spin, the spin could become flat making recovery

Answer 39

difficult or impossible.

Question 40

If the CG is too far forward, the downward tail load needs to be________ to maintain level flight.

Answer 40

increased

Question 41

This increased tail load has the same effect as carrying additional weight; the aircraft must fly at a ___________and drag increases.

Answer 41

higher angle of attack

Question 42

A more serious problem caused by the CG being too far forward is

Answer 42

the lack of sufficient elevator authority.

Question 43

At low takeoff speeds, the elevator might not produce enough nose-up force to rotate; on landing there may ____________ elevator force to flare the airplane.

Answer 43

not be enough

Question 44

For each item of weight added to the left of the center line of the aircraft (also known as __________), there is generally an equal weight at a corresponding location on the right.

Answer 44

buttock line zero or BL-0

Question 45

The__________ can be upset by _________________. The position of the lateral CG is not normally computed for an airplane, but the pilot must be aware of the adverse effects that result from a laterally unbalanced condition.

Answer 45

lateral balance, uneven fuel loading or burn off.

Question 46

This is corrected by using the __________ until enough fuel has been used from the tank on the heavy side to balance the airplane.

Answer 46

aileron trim tab

Question 47

are more critical due to fuel imbalance because as the fuel is used from the outboard tanks,

Answer 47

Swept-wing airplanes

Question 48

The WSC

Answer 48

WEIGHT-SHIFT CONTROL

Question 49

The WSC aircraft has a relatively set platform wing without a tail. The pilot achieves control by ____________

Answer 49

shifting weight.

Question 50

The weight of the airframe and its payload is attached to the wing at a single point in a ____________

Answer 50

pendulous arrangement.

Question 51

The flight controls primarily

Answer 51

affect the pitch-and-roll axes.

Question 52

Pilot should consult the POH or_________________ for maximum takeoff weight and minimum and maximum seat weight limits prior to each flight.

Answer 52

Aircraft Operating Instructions (AOI)

Question 53

is also a pendulum-style aircraft. Its airframe CG is fixed at the pendulum attach point. It is more limited in controllability than the WSC aircraft because it lacks an aerodynamic pitch control.

Answer 53

The powered parachute

Question 54

Pitch (and lift) control is primarily a function of the.

Answer 54

power control

Question 55

is primarily a function of the power control.

Answer 55

Pitch (and lift) control

Question 56

The________ is controlled by the pilot only in the vertical dimension; this is in contrast to all other aircraft. He or she achieves this control through the use of lift and weight. Wind provides all other movement.

Answer 56

balloon

Question 57

Documentation containing the pertinent specifications for aircraft certificated under the CARs.

Answer 57

Aircraft specifications

Question 58

(GAMA) The horizontal distance from the reference datum to the CG of an item. The algebraic sign is plus (+) if measured aft of the datum or to the right side of the center line when considering a lateral calculation. The algebraic sign is minus (–) if measured forward of the datum or the left side of the center line when considering a lateral calculation.

Answer 58

Arm

Question 59

A weight installed or carried in an aircraft to move the center of gravity to a location within its allowable limits.

Answer 59

Ballast

Question 60

. The empty weight of the aircraft plus the weight of the required crew, their baggage, and other standard items, such as meals and potable water.

Answer 60

Basic Operating Weight BOW

Question 61

(GAMA) The point at which an airplane would balance if suspended. Its distance from the reference datum is determined by dividing the total moment by the total weight of the airplane. It is the mass center of the aircraft, or the theoretical point at which the entire weight of the aircraft is assumed to be concentrated. It may be expressed in percent of MAC (mean aerodynamic cord) or in inches from the reference datum.

Answer 61

Center of Gravity (CG)

Question 62

The weight of the airframe, engines, all permanently installed equipment, and unusable fuel. Depending upon the part of the federal regulations under which the aircraft was certificated, either the undrainable oil or full reservoir of oil is included.

Answer 62

Empty Weight

Question 63

A list of items approved by the FAA for installation in a particular aircraft. The list includes the name, part number, weight, and arm of the component. Installation or removal of an item in the equipment list is considered to be a minor alteration.

Answer 63

Equipment list

Question 64

. An average weight accepted by the FAA for aircraft of identical make and model that have the same equipment installed. When a fleet weight control program is in effect, the fleet weight of the aircraft can be used rather than requiring every individual aircraft to be weighed.

Answer 64

Fleet weight

Question 65

. The point about which a lever balances.

Answer 65

fulcrum

Question 66

The takeoff weight of an aircraft minus the fuel burned and/or dumped en route

Answer 66

Landing Weight

Question 67

A force that causes or tends to cause an object to rotate. It is indicated by the product of the weight of an item multiplied by its arm.

Answer 67

Moment