ID: 3658
Customer: Oleg Ostapenko E-mail: ostapenko2002@yahoo.com
Customer: Oleg Ostapenko E-mail: ostapenko2002@yahoo.com
CH AP T ER 2 : CENT R E O F G R AV IT Y CALCU LAT IO
R e p r e s e n t a t i v e P P L - t y p e q u e s t i o n s t o t e s t k n o w l e d g e o f Ma s s a n d Ba l a n c e .
1.An aircraft weighing 2 000 lb with a total C of G moment of 169 400 lb-ins uplifts 440 lb of fuel. If the effective arm of the fuel is 88.5 inches aft of the datum, what will be the aircraft’s new mass and C of G moment?
a. |
1 560 lb |
208 |
340 lb-ins. |
b. |
2 440 lb |
169 |
488.5 lb-ins. |
c. |
1 560 lb |
169 |
488.5 lb-ins. |
d. |
2 440 lb |
208 |
340 lb-ins. |
2. |
Your aircraft has: |
|
|
|
A Take-off Mass |
= |
2 353 lbs |
|
A calculated C of G for departure |
= |
89.75 inches aft of the |
|
|
|
datum |
|
An estimated fuel burn |
= |
200 lb with a C of G |
|
|
|
85.00 inches aft of datum. |
The position of the C of G on landing will be?
a.90.19 inches aft of the datum
b.82.52 inches aft of the datum
c.105.98 inches aft of the datum
d.96.97 inches aft of the datum
3.Your aircraft has an oil reservoir, with a capacity of 3 Imperial gallons, which is positioned 20 inches aft of the datum. Given that the oil weighs 9.1 lb/gal, the reservoir will possess a moment of:
a.60 lb-ins
b.27.3 lb-ins
c.182 lb-ins
d.546 lb-ins
4.The Maximum Take off Mass of an aircraft may be limited by:
a.structural design load limits and or runway length, altitude and temperature
b.the authorised performance category of the aircraft, i.e. utility / normal / aerobatic
c.the airworthiness condition of the aircraft
d.all of the above
5.At what mass and C of G position would it be safe to operate the aircraft represented by the attached Mass vs C of G Envelope? See Graph 1, Page 311.
a. |
2 250 lb |
86.00 inches aft of the datum |
b. |
2 000 lb |
84.00 inches aft of the datum |
c. |
1 900 lb |
82.00 inches aft of the datum |
d. |
2 300 lb |
86.00 inches aft of the datum |
