S 23 Load distribution limits
a) The ranges of weight and c.g. within which the aeroplane is to be safely operated must be selected by the applicant.
b) The c.g. range must not be less than that which corresponds to the weight of each occupant, varying between a minimum of 55 kg for the pilot alone up to the maximum placarded weight with a pilot and passenger, together with a variation in fuel contents from zero to full fuel. The placarded maximum [occupant] weight must be not less than [86 kg] per person. (See AMC S 23 b).)
S 25 Weight limits
Maximum weight. The maximum weight must be established so that it is:
a) not more than:
1) the highest weight selected by the applicant;
2) the design maximum weight, which is the highest weight at which compliance with each applicable structural loading condition and each applicable flight requirement is shown.
b) not less than the weight which results from the empty weight of the aeroplane, plus a weight of occupant(s) of [86] kg for a single-seat aeroplane, or [172] kg for a two-seat aeroplane, plus the required minimum equipment, plus fuel [for at least 60 minutes flight at maximum continuous power.]
c) [not less than the weight which results with one (86 kg pilot) occupant, required minimum equipment and maximum fuel. (See AMC S 25 c).)]
S 561 General
a) The aeroplane, although it may be damaged in emergency landing conditions, must be designed as prescribed in this paragraph to protect each occupant under those conditions.
b) The structure must be designed to give each occupant every reasonable chance of escaping serious injury in a crash landing when proper use is made of belts and harnesses provided for in the design, in the following conditions:
1) Each occupant experiences, separately, ultimate inertia forces corresponding to the accelerations shown in the following:
c) Each aeroplane with a retractable landing gear must be designed to protect each occupant in a landing with wheel(s) retracted under the following conditions:
1) A downward ultimate inertia force corresponding to an acceleration of 3 g;
2) A coefficient of friction of 0.5 at the ground.
d) Except as provided in S 787, the supporting structure must be designed to restrain, under loads up to those specified in sub paragraph b) 1) of this paragraph, each item of mass that could injure an occupant if it came loose in a minor crash landing.
e) Where the failure of all or part of the engine mounting structure could result in an engine following a trajectory that could pass through any part of the normal crew accommodation or fuel tanks, the attachment structure must be designed to withstand an ultimate inertia force corresponding to an acceleration of 15 g in that direction.
S 786 Protection from injury
a) [Each seat and its supporting structure must be so designed that in the event of a collapse of any or all of the landing gear units the risk of serious injury to the occupant is minimised.] (See AMC S 786 a).)
b) Rigid structural members or rigidly mounted items of equipment, must be padded where necessary to protect the occupant(s) from injury during minor crash conditions.
[AMC S 786 a) (Interpretative Material)
The seat support structure should be designed, as far as is practicable, so as to prevent spinal or other serious injuries to the occupant in a minor crash landing in which the landing gear may have collapsed. It is recommended that rigid structural members are not located in a position likely to cause injury in such a crash landing and that energy absorbent materials should be used under the seat structure to reduce the impact loads being applied to the occupant’s spine.]
S 1519 Weight and c.g.
a) The maximum weight determined under S 25 a) must be established as an operating limitation.
b) The c.g. limitations determined under S 23 must be established as operating limitations.
c) The empty weight and the corresponding c.g. positions must be determined in accordance with S 29.
S 1557 Miscellaneous markings and placards
a) Baggage compartment. Each baggage compartment must have a placard stating
the loading limitations.
b) Fuel and oil filler openings. The following apply:
1) Fuel filler openings must be marked at or near the filler cover with the minimum
fuel grade and fuel/oil ratio.
2) Oil filler openings must be marked at or near the filler cover:
i) with the grade; and
ii) if the oil is detergent or non detergent.
c) Fuel tanks. The usable fuel capacity of each tank must be marked either at the selector or on the gauge (when provided) or on the tank if this is translucent and visible to the pilot in flight.
d) In-flight engine starting. A placard must be provided stating any limitations to be observed during in-flight engine starting.
e) Loading
1) The following data must be placarded in each aeroplane so as to be plainly visible to the pilot:
i) Empty weight [(actual);]
ii) Maximum weight;
iii) Maximum and minimum cockpit load;
iv) Cockpit load conditions for two-seater flown solo;
v) [Fuel load limitations for the range of allowable cockpit loads.]
2) [Removable ballast.] If removable ballast is used, the place for carrying ballast
must have a placard stating instructions for the proper placement and securing of the removable ballast under each loading condition for which removable ballast is necessary.
f) Aerobatic manoeuvres. A placard prohibiting aerobatic manoeuvres and intentional spinning must be plainly visible to the pilot.
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