Appendix C Basic Landing Conditions
ED Decision 2003/18/RM
|
Condition |
Tail wheel type |
Nose wheel type |
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|
Level landing |
Tail-down landing |
Level landing with inclined reactions |
Level landing with nose wheel just clear of ground |
Tail-down landing |
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|
Reference section |
CS-VLA 479 (a)(1) |
CS-VLA 481 (a)(1) |
CS-VLA 479 (a)(2)(ii) |
CS-VLA 479 (a)(2)(ii) |
CS -VLA 481 (a)(2) and (b) |
|
|
Vertical component at c.g |
nW |
nW |
nW |
nW |
nW |
|
|
Fore and aft component at c.g. |
KnW |
0 |
KnW |
KnW |
0 |
|
|
Lateral component in either direction at c.g |
0 |
0 |
0 |
0 |
0 |
|
|
Shock absorber extension (hydraulic shock absorber) |
Note (2) |
Note (2) |
Note (2) |
Note (2) |
Note (2) |
|
|
Shock absorber deflection (rubber or spring shock absorber) |
100 % |
100% |
100% |
100% |
100% |
|
|
Tyre deflection |
Static |
Static |
Static |
Static |
Static |
|
|
Main wheel loads (both wheels) |
Vr |
(n-L)W |
(n-L)Wb/d |
(n-L)Wa’/d’ |
(N-LW |
(n-L)W |
|
Dr |
KnW |
0 |
KnWa’/d’ |
KnW |
0 |
|
|
Tail (nose) wheel loads |
Vf |
0 |
(n-L)Wa/d |
(n-L)Wb’/d’ |
0 |
0 |
|
Df |
0 |
0 |
KnWb’/d’ |
0 |
0 |
|
|
Notes |
(1), (3), and (4) |
(4) |
(1) |
(1), (3), and (4) |
(3) and (4) |
|
NOTES:
(1) K may be determined as follows: K = 0.25 for W = 1361 kg or less; K = 0.33 for W = 2722 kg or greater, with linear variation of K between these weights.
(2) For the purpose of design, the maximum load factor is assumed to occur throughout the shock absorber stroke from 25% deflection to 100% deflection unless otherwise shown and the load factor must be used with whatever shock absorber extension is most critical for each element of the landing gear.
(3) Unbalanced moments must be balanced by a rational conservation method.
(4) L is defied in CS-VLA 725(e).
(5) n is the limit inertia load factor, at the c.g. of the aeroplane, selected under CS-VLA 473(d),(f), and (g).
