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NOTE
The maximum landing mass given in Chapter 2 is the highest mass for landing conditions at the maximum descent velocity. This velocity was used in the strength calculations to determine the landing gear loads during a particularly hard landing.
Perform landing approach and landing according to Chapter 4A, but maintain an increased airspeed during landing approach.
Approach speed .......................... 71 KIAS (1150 kg, 2535 lb)
WARNING
Damage of the landing gear can result from a hard landing with a flight mass above the maximum landing mass.
Doc. No. 6.01.05-E Revision 1 03-Mar-2003 Page 4B - 19
CHAPTER 5
PERFORMANCE
Page
5.1 INTRODUCTION....................................... 5-2
5.2 USEOFTHEPERFORMANCETABLESANDDIAGRAMS...... 5-2
5.3 PERFORMANCETABLESANDDIAGRAMS ................. 5-3
5.3.1 AIRSPEED CALIBRATION .......................... 5-3
5.3.2 DIAGRAMFORSETTINGENGINEPERFORMANCE ..... 5-4
5.3.3 PRESSUREALTITUDE-DENSITYALTITUDE .......... 5-5
% 5.3.4 INTERNATIONALSTANDARDATMOSPHERE .......... 5-6
5.3.5 STALLINGSPEEDS ............................... 5-7
5.3.6 WINDCOMPONENTS ............................. 5-8
5.3.7 TAKE-OFFDISTANCE ............................. 5-9
5.3.8 CLIMB PERFORMANCE -TAKE-OFFCLIMB .......... 5-12
5.3.9 CLIMB PERFORMANCE -CRUISE CLIMB ............ 5-14
5.3.10 CRUISING(TRUE AIRSPEED TAS)................. 5-16
5.3.11 LANDINGDISTANCE -FLAPS LDG ................ 5-17
5.3.12 LANDINGDISTANCE -FLAPS UP.................. 5-21
5.3.13 GRADIENTOFCLIMBONGO-AROUND ............ 5-25
5.3.14 APPROVED NOISE DATA ........................ 5-25
%
Doc. No. 6.01.05-E Revision 3 26-May-2003 Page 5 - 1
5.1 INTRODUCTION
The performance tables and diagrams on the following pages are presented so that, on the one hand, you can see what performance you can expect from your airplane, while on the other they allowcomprehensive and sufficiently accurate flight planning. The values in the tables and the diagrams were obtained in the framework of the flight trials using an airplane and power-plant in good condition, and corrected to the conditions of the International Standard Atmosphere (ISA = 15 EC/59 °F and 1013.25 hPa/29.92 inHg at sea level).
The performance diagrams do not take into account variations in pilot experience or a poorly maintained airplane. The performances given can be attained if the procedures quoted in this manual are applied, and the airplane has been well maintained.
Where appropriate, any flight performance degradation resulting from the absence of wheel fairings is given as a percentage.
5.2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS
In order to illustrate the influence of a number of different variables, the performance data is reproduced in the form of tables or diagrams. These contain sufficiently detailed information so that conservative values can be selected and used for the determination of adequate performance data for the planned flight.
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