Mass & Balance Exam 1

Mass and Balance Exam 1, 30 questions, 60 minutes

1.

The Disposable Load is the: (a) (b) (c) (d)

2.

A large passenger aircraft takes off but has to make an immediate landing following an engine failure. This may cause: (a) (b) (c) (d)

3.

the the the the

centre of pressure centre of gravity main undercarriage nose wheel

An aircraft is weighed before coming into service. Once operational items are added who is responsible for re-establishing the position of the centre of gravity and the Basic Empty Mass? (a) (b) (c) (d)

5.

a higher than normal threshold speed and undercarriage damage a lower than normal threshold speed and risk of stalling a higher than normal threshold speed but no risk of structural damage a lower than normal threshold speed and risk of undercarriage damage

An aircraft with nose and mainwheels is stationary on the ground. The total mass of the aircraft can be considered to be equal to a single pinpoint mass acting through the position of: (a) (b) (c) (d)

4.

mass of passengers and baggage, plus items of load including fuel and other consumable fluids. mass of crew and their baggage, plus removable units and other equipment the Dry Operating Mass less payload and fuel. mass of fuel and other consumable fluids.

the the the the

pilot operator aircraft manufacturer parts supplier

An aircraft has a mass of 12,499 lbs. The equivalent mass in kilograms is: (a) (b) (c) (d)

27,500 kg 5,700 kg 24,200 kg 5,900 kg

Bristol Groundschool

Mass & Balance Exam 1

6.

An aircraft fuel tank can hold a maximum volume equivalent to 2300kg of fuel at 0.80SG. The tank is loaded with fuel at 0.78SG, the volume of fuel that can be loaded l oaded is: (a) (b) (c) (d)

7.

litres litres litres litres

Given a floor load limit of 5000 N/m 2 what is the maximum mass permissable for a box with floor area 0.4m x 0.4m under 1G conditions? (a) (b) (c) (d)

8.

1840 2243 2359 2875

80 kg 81.6 kg 78.4 kg 800 kg

Refer to the data for the single engine piston/propeller aeroplane in Section II of the loading manual to answer this question. The aircraft datum for centre of gravity calculation is at the (a) (b) (c) (d)

9.

Which axis is the C of G normally referenced to? (a) (b) (c)

10.

mean aerodynamic chord leading edge mean aerodynamic chord trailing edge nose tail

longitudinal lateral vertical

Which of the following statements is correct? (i) (ii) (iii) (iv) (v) (vi)

(a) (b) (c) (d)

The Dry Operating Mass is the Zero Fuel Mass minus the Traffic Load The Dry Operating Mass is the Zero Fuel Mass plus the Variable Load The Zero Fuel Mass is the Dry Operating Mass minus the Traffic Load The Zero Fuel Mass is the Dry Operating Mass plus the Variable Load The Basic Empty Mass is the Zero Fuel Mass plus the Variable Load The Traffic Load is the Zero Fuel Mass minus the Dry Operating Mass (i) (ii) and (vi) (i) (iii) (iv) and (v) (ii) (v) and (vi) (i) and (vi)



11.

The most important factor governing C of G limits is (a) (b) (c) (d)

12.

An aircraft has a Mean Aerodynamic Chord (MAC) of 180cm and the centre of gravity once the aircraft is loaded is calculated to be at 25%MAC. In order to move the centre of gravity position to 40%MAC the load must be redistributed so that the position of the centre of gravity moves (a) (b) (c) (d)

13.

forward 15 cm aft 15 cm aft 27 cm forward 27 cm

An aircraft has a Dry Operating Mass of 37,400kg. The Performance Limited Take-Off Mass is 67,400kg and the Performance Limited Landing Mass 52,800kg. The Certificate of Airworthiness Maximum Structural Take-Off Mass is 66,000kg, the Maximum Structural Landing Mass is 54,000kg and the Maximum Zero Fuel Mass is 52,000kg. The fuel load before taxy is 16,000kg. Allowing 500kg for start, taxy and take-off and 12,400kg for trip fuel the maximum allowed traffic load is: (a) (b) (c) (d)

14.

keeping stall speeds low keeping landing speeds low minimising drag and increasing efficiency the limits of elevator and horizontal stabiliser deflection

12300 13500 14600 13100

kg kg kg kg

An aircraft has two baggage holds. The forward hold has a moment arm of 180” aft of the datum and the aft hold has a moment arm 460” aft of the datum. The aircraft mass when loaded is 22600 kg and the centre of gravity is at 375” aft of the datum. How much mass must be moved from the forward hold to the aft hold to move the centre of gravity position to 385” aft of the datum? (a) (b) (c) (d)

675 kg 723 kg 1010 kg 807 kg



15.

Use the data for the single engine piston/propeller aircraft in Section II of the loading manual to answer this question. Complete the manifest below using the following information and determine the centre of gravity positions for take-off and landing. Front seat occupants Third & fourth seat pax Baggage zone B Baggage zone C Fuel loading at start Trip fuel take-off to touchdown

ITEM

MASS

380 lb 170 lb 60 lb 120 lb 50 USG 40 USG

ARM (IN)

MOMENT X 100

1. BASIC EMPTY CONDITION

2415

1876.46

2. FRONT SEAT OCCUPANTS

380

79

300.20

3. THIRD & FOURTH SEAT PAX

170

117

198.90

4. BAGGAGE ZONE “A”

nil

108

nil

5. FIFTH & SIXTH SEAT PAX

nil

152

nil

6. BAGGAGE ZONE “B”

60

150

90.00

7. BAGGAGE ZONE “C”

120

180

216.00

SUB-TOTAL = ZERO FUEL MASS 8. FUEL LOADING

300

225.00

SUB-TOTAL = RAMP MASS 9. SUBTRACT FUEL FOR START, TAXI & RUN UP. (SEE NOTE)

SUB-TOTAL = TAKE OFF MASS 10. TRIP FUEL

SUB-TOTAL = LANDING MASS



Which positions in the chart below correctly indicate the position of the aircraft centre of gravity and mass for take-off and landing respectively?

2 8 0 0

2 9 0 0

3 0 0 0

7 . 7 8

3 2 0 0

3 1 0 0

3800 3700

2 7 0 0

3650

A

C

B

2 6 0 0

3600

3500

2 5 0 0 3400

2 4 0 0

3300

2 3 0 0

0 0 1/ T N E M O M

3200

D

2 2 0 0

F

E

S D N U O P

3100 3000

2 1 0 0

2900

2 0 0 0 2800

1 9 0 0

-

T H GI E W

2700

1 8 0 0

2600

1 7 0 0

2500

1 6 0 0

2400 2300

1 5 0 0 2200

70

72

74

76

78

80

82

84

86

88

90

2100

CENTRE OF GRAVITY - INCHES AFT OF DATUM

(a) (b) (c) (d)

16.

A and D A and E B and E C and F

The fleet mass is (a) (b) (c) (d)

the average Dry Operating Mass of a fleet of aeroplanes obtained by weighing all the aircraft the average Dry Operating Mass of a fleet of aeroplanes obtained by weighing some of the aircraft the average Dry Operating Mass of a fleet of aeroplanes which varies by no more than 0.5% of the Dry Operating Mass the average Dry Operating Mass of a fleet of aeroplanes as stated by the manufacturer



17.

An aircraft not included in a fleet mass system must be weighed (i) (ii) (iii) (iv)

(v)

(a) (b) (c) (d) 18.

cannot move laterally. will not move if passengers move. will not move if correct fuel management is observed. will move within certain limits as fuel is burnt off providing correct fuel management is observed.

The weighing of an aircraft is the responsibility of the: (a) (b) (c) (d)

20.

(i) and (ii) (ii) (iv) and (v) (i) (iii) (iv) and (v) (ii) and (iv)

The centre of gravity position: (a) (b) (c) (d)

19.

when transferred from one JAA operator to another every 4 years every nine years when there is reason to suspect that modifications have been carried out and the effect on mass and balance has not been accounted for when the cumulative effects cause the centre of gravity position to deviate more than 0.5%MAC from the mean

licensing authority. operator. manufacturer. Captain.

An aircraft has a Ramp Mass of 286,000kg and a centre of gravity position 980” aft of the datum, the Maximum Taxy Mass is 323,000kg. As much freight as possible is to be added to the rear hold which has a moment of 1078” without moving the centre of gravity beyond the aft limt of 982” or exceeding the Maximum Taxy Mass. The greatest amount of freight that can be loaded is: (a) (b) (c) (d)

6420 6210 5320 5950

kg kg kg kg



21.

When equipment is added or removed from a transport aircraft the equipment position is often described in terms of its body station. In this context a body station is: (a) (b) (c) (d)

22.

The Take-Off Mass of an aircraft is 3620 kg, the Landing Mass is 3280 kg and the Basic Empty Mass is 1875 kg. The fuel load on take-off is 380 kg and the traffic load is 1150 kg. The Dry Operating Mass is: (a) (b) (c) (d)

23.

3025 1660 2130 2090

kg kg kg kg

Maximum Taxi Mass: (a) (b) (c)

(d)

24.

a distance from the balance arm datum expressed in inches or centimetres a position defined by a longitudinal reference system originating at the design stage the distance from the nose of the aircraft in inches or centimetres the distance from the leading edge of the front spar

is the same as the Maximum Take Off Mass. depends on the oleo pressures and extensions. provides for a reserve of fuel to enable the aircraft to start, taxi into position ready for take-off and take-off and be at it's Maximum Structural Take-Off Mass at the commencement of the take-off run. is governed by the airport authorities according to ambient temperature in order to protect the tarmac from the load on the wheels.

Use the data for the medium range twin jet in Section IV of of the loading manual to answer this question. Refer to figure 4.3 on page 21. The specimen aircraft has a Take-Off Mass of 60,000kg. After take-off the flaps are retracted from 15º to 0º. The centre of gravity moves (a) (b) (c) (d)

0.23 inches forward 0.23 inches aft 14 inches forward 5.2 inches forward



25.

26.

Which of the following statements are true for an overloaded aircraft? (i) (ii) (iii) (iv) (v) (vi) (vii) (viii) (ix)

take-off distance required is increased climb gradient is increased because the aircraft is slower rate of climb is decreased take-off safety speeds are increased range is increased endurance is decreased engine-out performance is decreased VMCA is increased landing distance is decreased

(a) (b) (c) (d)

(i) (iii) (iv) (v) (vi) (vii) (viii) (ix) (i) (iii) (iv) (vi) (vii) (iii) (iv) (vi) (vii) (viii) (i) (ii) (iii) (iv) (vi) (vii)

Refer to table 4.2 in the loading manual to answer this question. The distance of body station 500E from the datum is (a) (b) (c) (d)

27.

500 348 110 458

inches inches inches inches

Given the following information: Basic Empty Mass Dry Operating Mass Zero Fuel Mass Traffic load Fuel

30,400 kg 32,500 kg 40,800 kg 8,300 kg 12,200 kg

The All Up Mass is: (a) (b) (c) (d) 28.

50,900 53,000 44,700 61,300

kg kg kg kg

Use the data for SEP1 in Section II of the loading manual to answer this question. The Basic Empty Mass of this aircraft is: (a) (b) (c) (d)

2415 3650 2543 2602

lb lb lb lb



29.

The aircraft shown below has two body gear bogies, two wing mounted bogies and a nose gear.

The mass recorded on the bogies and their moment arms in a routine weighing is as follows: Nose gear Left main gear Left body gear Right body gear Right main gear

22,000 kg 37,600 kg 32,400 kg 32,500 kg 37,700 kg

305” aft 1245” aft 1378” aft 1378” aft 1245” aft

The centre of gravity position is: (a) (b) (c) (d)

30.

1098” aft 1171” aft 1278” aft 952” aft

Which of the following statements is true? (a) (b) (c) (d)

The Regulated Take-Off Mass is the same as the structural TOM The Regulated Take-Off Mass is the higher of the structural and performance limited Take-Off Masses The Regulated Take-Off Mass is the lower of the structural and performance limited Take-Off Masses The Regulated Take-Off Mass is the performance limited TakeOff Mass



Intentionally Blank



Mass & Balance Exam 1, 30 Questions, 60 Minutes

A

B

C

D

A

1

16

2

17

3

18

4

19

5

20

6

21

7

22

8

23

9

24

10

25

11

26

12

27

13

28

14

29

15

30

B

C

D

Name:……………………………………….



1

a

11

d

21

b

2

a

12

c

22

d

3

b

13

a

23

c

4

b

14

d

24

a

5

b

15

c

25

b

6

d

16

b

26

d

7

b

17

b

27

b

8

c

18

d

28

a

9

a

19

b

29

b

10

d

20

d

30

c



Mass & Balance Exam 1

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