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5.3.13 GRADIENT OF CLIMB ON GO-AROUND
The DA 40 D reaches a constant gradient of climb of 4.86 % (conforming to an angle of 2.8°) in the following condition:
-Mass............................... max. flight mass (1150 kg, 2535 lb)
-Power lever ......................... MAX
-Flaps .............................. LDG
% -Airspeed............................ 70 KIAS -ISA, MSL
5.3.14 APPROVED NOISE DATA
With exhaust pipe:
ICAO Annex 16 Chapter X .................. 78.7 dB(A)
JAR-36 Subpart C ........................ 78.7 dB(A)
With muffler:
ICAO Annex 16 Chapter X .................. 69.5 dB(A)
JAR-36 Subpart C ........................ 69.5 dB(A)
%
Doc. No. 6.01.05-E Revision 3 26-May-2003 Page 5 - 25
CHAPTER 6
MASS AND BALANCE / EQUIPMENT LIST
Page
6.1 INTRODUCTION....................................... 6-2
6.2 DATUM PLANE........................................ 6-3
6.3 MASS AND BALANCE REPORT .......................... 6-3
6.4 FLIGHT MASS AND CENTER OF GRAVITY ................. 6-5
6.4.1 MOMENT ARMS .................................. 6-7
6.4.2 LOADING DIAGRAM .............................. 6-8
6.4.3 CALCULATION OF LOADING CONDITION ............. 6-9
% 6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE ......... 6-11
% 6.4.5 PERMISSIBLE MOMENT RANGE ................... 6-13
% 6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY .......... 6-15
%
Doc. No. 6.01.05-E Revision 2 30-Apr-2003 Page 6 - 1
6.1 INTRODUCTION
In order to achieve the performance and flight characteristics described in this Airplane Flight Manual and for safe flight operation, the airplane must be operated within the permissible mass and balance envelope.
The pilot is responsible for adhering to the permissible values for loading and center of gravity (CG). In this, he should note the movement of the CG due to fuel consumption. The permissible CG range during flight is given in Chapter 2.
The procedure for determining the flight mass CG position is described in this Chapter. Over and above this there is a comprehensive list of the equipment approved for this airplane (Equipment List), as also a list of that equipment installed when the airplane was weighed (Equipment Inventory).
Before the airplane is delivered the empty mass and the corresponding CG position are determined, and entered in Section 6.3 MASS AND BALANCE REPORT.
NOTE
Following equipment changes the new empty mass and the corresponding CG position must be determined by calculation or by weighing.
Following repairs or repainting the new empty mass and the corresponding CG position must be determined by weighing.
Empty mass, empty mass CG position, and the empty mass moment must be certified in the Mass and Balance Report by an authorized person.
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