Document ID: chunk:federal_register_of_legislation:F2025C00050:body:0:p322
Version: federal_register_of_legislation:F2025C00050
Segment Type: other
Provision Reference: 
Character Range: 1120986–1124604

given the following:
(a)           OAT and pressure height;
(b)           using cockpit temperature and an altimeter setting of 1013.2 hPa.
2.1.2              For subsection 2.1.1, the methods are the following:
(a)           density altitude charts;
(b)           manual computer;
(c)           flight manual charts;
(d)           mathematics.
2.2                    Take-off and landing
2.2.1              Use the flight manual to extract maximum structural take-off and landing weights mentioned in subsection 2.2.2 according to the requirements mentioned in subsection 2.2.3.
2.2.2              Given a typical flight scenario, for the items mentioned in subsection 2.2.3, use performance charts to extract the following:
(a)           maximum take-off weight;
(b)           maximum landing weight;
(c)           take-off distance required (TODR);
(d)           landing distance required (LDR);
(e)           climb weight limit;
(f)             take-off parameters – power, flap setting, take-off safety speed;
(g)           landing parameters – flap, threshold speed and state the conditions on which the parameters listed in (f) and (g) are based.
2.2.3              For subsection 2.2, the following requirements apply:
(a)           apply information extracted from ERSA;
(b)           determine TODA and LDA at a ground ALA;
(c)           apply the CASA regulatory requirements/orders as applicable to single-engine aeroplanes;
(d)           extract/derive entry parameters for take-off and landing charts viz:
(i)             temperature and pressure;
(ii)            take-off and landing weights;
(e)           extract structural weight limits from a flight manual.

3.                       Climb, cruise and descent performance
3.1.1              From typical charts or tables, determine the following data for climb, cruise and descent:
(a)           time, speed, distance, fuel flow/quantity;
(b)           appropriate engine settings;
(c)           rates of climb/descent;
(d)           the conditions under which an aeroplane will achieve maximum range and endurance.
3.1.2              Determine the following, using the fuel units of US gal, kg, litres:
(a)           best air and ground nm/unit of fuel;
(b)           least fuel/air or ground nm.

4.                       Weight and balance
4.1                    Weight calculations
4.1.1              Calculate the following:
(a)           mid-zone weight;
(b)           landing weight;
(c)           take-off weight at an intermediate landing point.
4.2                    Loading
4.2.1              Explain the following terms:
(a)           arm, moment, datum, station, index unit;
(b)           CG and CG limits;
(c)           mean aerodynamic chord (MAC);
(d)           empty weight, ZFW, ramp weight;
(e)           maximum take-off and maximum landing weights;
(f)             floor loading limits.
4.2.2              Demonstrate the ability to:
(a)           express CG as a % of MAC;
(b)           determine CG position relative to the datum;
(c)           determine movement of CG with changes in load distribution and mass.
4.2.3              Given appropriate data use a typical loading system or a load sheet to distribute load to maintain CG within limits throughout a flight. This objective requires the ability to perform 1 or more of the following tasks:
(a)           extract the following weight limits from a flight manual:
(i)             empty weight ZFW;
(ii)            maximum structural take-off and landing weight.
(b)           determine the following:
(i)             maximum payload;
(ii)            maximum load per