Effectivity: 912 Series
Edition 1 / Rev. 0
d04053
page 35
May 01/2007
BRP-Rotax
INSTALLATION MANUAL
09185
09184
attachment point
L1 R1 L2 R2 L3 R3 L4 R4
max. allowable forces (limit load) in (N)
in x, y and z axis
5000 1900
max. allowable bending moment (limit
load) in (Nm) in x, y and z axis
77 39
attachment point
L5 R5 L6 R6
max. allowable forces
(limit load) in (N)
in x axis
5 000
in y axis 2 000
in z axis 3 000
max. allowable bending
moment (limit load) in (Nm)
in x, y and z axis
100
▲ WARNING: Tighten all engine suspension screws as specified by the
aircraft manufacturer.
10.2) Permissible fitting positions
See Fig. 9/10/11.
To simplify the matter, reference is made only to the 4 engine attachment points
R1, L1, R2 and L2.
◆ NOTE: All dimensions to point of reference (P) and the system of
coordinates remain unchanged.
The following details of engine position are with reference to aircraft on
ground, ready for take off.
- engine suitable for propeller in tractor or pusher arrangement,
- propeller shaft above cylinders. See Fig. 2.
▲ WARNING: For upside down installation of the engine, the lubrication
system, fuel system and the cooling system are unsuitable!
Longitudinal axis:
- The centre of the attachment points L1 and L2 must be on axis x2 parallel
to the x axis.
Allowable pitch deviation of parallelism of axes:
max. 6° counter-clockwise, on ground
max. 10° counter-clockwise, in operation
max. 30° clockwise (see Fig. 9)
▲ WARNING: On installations with fuel tank located above carburetor level
combined with badly closing carb float valve, fuel could pass
into cylinders at more than 6° decline of propeller shaft axis
after longer periods of downtime. See FAR, § 33.17.
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