ED Decision 2003/18/RM
Acceptable values of limit average manoeuvring control-surface loadings may be obtained from figure B1 of this Appendix in accordance with the following:
(a) For horizontal tail surfaces -
(1) With
the conditions in CS-VLA 423(a)(i),
obtain 
as a function of W/S and surface deflection,
using -
(i) Curve C of figure B1 for a deflection of 10 o or less;
(ii) Curve B of figure B1 for a deflection of 20 o;
(iii) Curve A for a deflection of 30 o or more;
(iv) Interpolation for all other deflections; and
(v) The distribution of figure B7; and
(2) With
the conditions in CS-VLA 423(a)(2),
obtain from curve B of figure B1
using the distribution of figure B7.
(b) For vertical tail surfaces -
(1) With
the conditions in CS-VLA 441(a)(1),
obtain as a function of W/S and surface deflection
using the same requirements as used in sub-paragraphs
(a) (1)(i) to (a)(1)(v) of this paragraph;
(2) With
the conditions in CS-VLA 441(a)(2),
obtain from Curve C, using the distribution of
figure B6; and
(3) With
the conditions in CS-VLA 441(a)(3),
obtain from Curve A, using the distribution of
figure B8.
(c) For ailerons, obtain w from Curve B, acting in both the up and down directions, using the distribution of figure B9.
FIGURE B1 – LIMIT AVERAGE MANOEUVRING CONTROL SURFACE LOADING.
FIGURE B2 – MANOEUVRING TAIL LOAD INCREMENT (UP OR DOWN)
As an alternative to Figure B2, the following may be used:
where:
k is the radius of gyration of the aircraft in pitch
lt is the distance between the aeroplane centre of gravity and the centre of the lift of the horizontal tail
V is the aircraft speed in m/s.
FIGURE B3 UP AND DOWN GUST LOADING ON HORIZONTALTAIL SURFACE.
FIGURE B4 RESERVED.
FIGURE B5 - GUST LOADING ON VERTICAL TAL SURFACE.
FIGURE B6 -TAIL SURFACE LOAD DISTRIBUTION.
NOTES:
(a) In balancing conditions in CS-VLA 421, P = 40% of net balancing load (flaps retracted); and P = 0 (flaps deflected).
(b) In the condition in CS-VLA 441(a)(2), P = 20% of net tail load.
(c) The load on the fixed surface must be -
(1) 140% of the net balancing load for the flaps retracted case of note (a);
(2) 100% of the net balancing load for the flaps deflected case of note (a); and
(3) 120% of the net balancing load for the case in note (b).
FIGURE B7 TAIL SURFACE LOAD DISTRIBUTION.
FIGURE B8 TAIL SURFACE LOAD DISTRIBUTION.
FIGURE B9 AILERON LOAD DISTRIBUTION.