Microlighters

What is the definition of an LSA aircraft or does it get registered as one ?
Does all Cheetha’s and Bushbaby’s fall this category ?

From willem (at RAASA) on Avcom a summary of local LSA

Here are the specifications for an aircraft to be qaulified as an LSA:

Max take off mass: 600 kg for land plane
Maximum Stall Speed at Gross Landing Configuration: 45kts
Maximum speed, level flight max cont power: 150 kts
Max no seats (incl Pilot): 2
Single engine (non turbine or jet): yes
Unpressurised: yes
Prop: Fixed or VP or CS in flight adjustable
Undercarriage: Fixed tricycle or tail wheel or retract

There is currently no provision for a aerobatic rating on a NPL.
We will however look at incorporating this into Part 62 in the future.

So I rekon they all fit other than the new Safari which has 700kg MAUW. I think the key is the 450kg mark. If under 450KG then Microlight (3axis), else LSA.

Hi there, the Safari will be available soon as both LSA and PPL

Is the Cheetha then a CCM as it Max take off mass is less than 600 kg ?

If the Cheetah had a MTOW of 450kg then it is a CCM

the 600KG is the upper limit not the target, in other words, if the plane has a MTOW between 450 and 600 it is still an LSA

If I am not mistaken, an aircraft weighing less than 450kg will also be LSA, if the empty weight, or stall speed do not fit in the 'microlight' definition.

For an aircraft to be a microlight, it must fit all of the microlight rules - and the same for LSA - it must meet all of the requirements. It is entirely possible to have an aircraft with a MAUW of 350kg that is PPL only...

Stil don't understand when it is a CCM and when LSA

t-bird wrote:Stil don't understand when it is a CCM and when LSA

Hi,

Both are 3-axis planes, it is a CCM if the MAUW is 450kg or below, if MAUW is between 450 and 600kg's it is LSA. But as Justin pointed out, it is not just the weight, if the stall speed is above 45k, top speed above 150k, more than one engine, more than 2 seats or jet/turbo prop it becomes a PPL and above only plane even if the weight is within the limits.

Fly safe,
Rudi

t-bird wrote:Stil don't understand when it is a CCM and when LSA

In reality most modern fixed wing "microlight" aircraft fall into the LSA category, especially if they are powered by 4-stroke engines. There are legacy models such as the old Skyfoxes and Basics, the Challengers that are very light and as such fall into the previous fixed wing microlight (now called conventional controlled microlight) category. There is also a lower weight limit of 260Kg empty, without fuel, but with water and oil if neccessary. If your aircraft is a fixed wing and is heavier than this then you fall into the LSA category. ( I think they calculated this back from 450kg - 2X90kg adults plus 10kg fuel, but this was the maximum empty weight they allowed me when I was building my Bushbaby to include it in the CCM category). Mine is slightly above that

Can somebody please enlighten me about the above LSA requirements.

The stall speed is very loosely mentioned in most builder plans or kits!

From reading various articles I am still confused about this for the LSA criteria...

Above post states stall speed at gross landing configuration = less than 45 knots.

my question is:

Does this mean V so = 45 knots and less (with full landing flaps extended)????

OR

Does this mean V s = 45 knots and less (with flaps full retracted - clean wing)????

Landing Config would normally include flaps extended.

Light Sport Aeroplanes
24.01.2.O.1 Design Standards

Non-type certified light sport aeroplanes shall meet the design criteria of either amateur-built aircraft or production built aircraft.

24.01.2.O.2 Classification parameters

(1) For and aeroplane to be classified as a light sport aeroplane, the following parameters need to be met:
(a.) Maximum take-off mass of: i. 600 kilograms for land planes

ii. 650 kilograms for amphibian and sea planes

(b.) Maximum stall speed or minimum steady flight speed at maximum take-off mass of 45 Knots (no flaps – Vs1) at standard atmospheric conditions at sea level at most critical C of G.

(c.) Maximum air speed in level flight with maximum continuous power (Vh) of not more than 140 Knots CAS under standard atmospheric conditions at sea level

(d.) Two place maximum

(e.) Single reciprocating (non-turbine or jet)

(f.) Unpressurised cabin

(g.) A Fixed, VP or CS in flight adjustable propeller

(h.) Fixed tricycle, tail wheel or retractable undercarriage

(2) For the purpose of establishing conformity with sub-paragraph (1), the following payloads are to be included:

(a.) 84 kg per seat,
(b.) Oil and other liquids in the engine as required for flight,
(c.) The lesser of fuel load or 60 kg
(d.) Luggage mass as allowed by the manufacturer,
(e.) safety rescue system if one is fitted,

(i.) all standard and additional equipment and systems as fitted

(3) The wing loads of a light sport aeroplane shall subscribe to the following formula:

MTOW/(span)2 ≥ 3