Below is an extract of the regulation regarding the building of an aircraft. If it is a new type in SA you will need to go through the pains.... Be careful of US designs (especially ultralights) as I believe the US do not require load testing or structural analysis for single seat ultralights (I stand to be corrected on this!) There are many fine designs that should cover the entire spectrum of flying microlights/sport planes. Zodiac CH601/701, Savannah, Sonex, Bushbaby, Raven etc.
I think if you have the welding done by an approved airframe manufacturer/welder you should be OK (Kitplanes for Africa charge R1500/day in the welding shop last time I checked)
Why re-invent the wheel? I reckon it would save you a lot of frustration if you build a type that already has all the below info in place. Having said that I recently talked to a guy building a Kitfox - CAA told him he had to submit an engineering design report as there were no Kitfoxes flying in South Africa
24.01.2.A.1 Engineering design analyses – Regulation 24.01.2(5)(a) refers
(1) The owner of an amateur-built aircraft shall ensure that proof of engineering design analysis for the aircraft or type of aircraft is available, validated and traceable.
(2) The engineering design analysis for an amateur-built aircraft shall include the following:
(a) the design criteria basis;
(b) a schedule of how compliance with the design criteria basis is proposed;
(c) a predicted performance analysis prior to commencing of proving flights;
d) an aerodynamic analysis appropriate to the type of aircraft, in accordance with the checklist attached as Annex C;
(e) a structural analysis appropriate to the type of aircraft; and
(f) an analysis of the power plant/s and propeller/s (if applicable) and of the systems appropriate to the type of aircraft.
24.01.2.A.2 Design criteria
In the design of an amateur-built aircraft, the following conditions must be met:
(a) The aircraft must be able to withstand the maximum loads to be expected in service without any permanent deformation or any deformation which may interfere with the safe operation of the aircraft. See section 24.01.2.A.7 “Static testsâ€Â.
(b) The aircraft structure must be designed to be able to withstand ultimate loads; that is the limit loads multiplied with a safety factor as specified in the relevant subgroup.
(c) The aircraft must not have any apparent unsatisfactory features of design and construction.
(d) (i) It is desirable, but not prescribed, that the constructor makes use of approved aircraft components, such as engines, propellers, wheels, instruments, avionics, electrical components and similar items. Structural components of other aircraft that are still airworthy may also be used.
(ii) Where items, including materials, not normally approved for aircraft construction are to be used, the constructor shall prove to the Commissioner or, if applicable, to the organisation approved for the purpose in terms of Part 149, as the case may be, that the item, items or materials have characteristics which make them suitable in all respects for the intended purpose and meet the design criteria referred to in TS 24.01.2.A.1(2)(a).
(iii) The items, referred to in sub-paragraph (ii), include engines and propellers, provided that no adverse characteristics of the engine, propeller, or engine-propeller combination are evident.
(e) The constructor remains fully responsible for the integrity of the aircraft. Any inspections made by an inspector, to determine that such aircraft has been built from acceptable materials and in accordance with normal aircraft construction procedures, are carried out on the basis of the information given by the constructor to the inspector, and by careful study of the relevant drawings.
(f) Where applicable, suitable means must be provided to minimize the possibility of carburetor icing.
(g) The complete power plant installation, including the propeller, as installed in the aircraft, must undergo a test sequence as determined in the design criteria referred to in TS 24.01.2.A.1(2)(a).
(h) Only fuel of a grade that will not cause destructive detonation and will minimize the possibility of vapour locks shall be used.
Note: Airworthiness standards that are acceptable to the Commissioner include –
(a) BCAR Section K ‘Light Aircraft
(b) FAR 23 ‘Light Aircraft
(c) JAR-VLA ‘Very Light Aircraft’
(d) AFNOR – The French ACPULS certification
(e) DHV – The German ‘Gute Siegel’ certification
(f) USHGA – The US Hang Gliding Association
(g) AHGF – The Australian Hang Gliding Federation
(h) SHV – The Swiss Hang Verein certification
(i) SAPA – The South African Parachute Association reserve parachute testing procedure
(j) DULV