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2.4
ESTABLISH THE LOCATION FOR THE AOA PROBE
The AOA probe is mounted on the wing with the following limitations:
The AOA probe is mounted a minimum of 24 in. outboard of the propeller arc.
The AOA probe is a mounted a minimum of 12 in. inboard of the wing tip.
The AOA probe is a mounted at least 6 in. outboard of any struts or landing gear.
The AOA probe is a mounted between 10% to 90% of the Mean Aerodynamic Cord (MAC).
The AOA probe must not be mounted on a wing that contains a remote compass system if heated
probe is to be installed for the AOA probe.
Due to the number of aircraft, wing designs, inspection locations, braces, struts and so on, the object of
the best location is "clean air flow / undisturbed air" at the location of the AOA probe for all angles,
slips or attitudes, would not affect the measurement of air present at the AOA probe.
Listed below are three different scenarios, find and complete the one that pertains to your installation and
use the following formulas when calculating the additional load and drag:
(AOA Probe + Hardware Weight) X (Aircraft "G" Limit) X 1.5 (Safety Margin) = Additional Load
Examples:
.6lbs
X
6.6
X
(Drag Coefficient) X (Frontal Area of the AOA Probe) X V
.000327
X
.064
IF a non-structural inspection panel is available, determine that the existing structure will support the
additional load and drag of the AOA probe and mounting hardware. Please refer to AC43.13-2B Chapter
1 & Chapter 3 for guidance. This is the preferred method of installing the AOA probe and in most cases
will require no additional support structure. However, if you have a very fast and/or a thin skinned aircraft
the addition of supporting structure may be required. Please refer to AC43-13-1B Chapter 4, AC43.13-2B
Chapter 1 & Chapter 3 for guidance.
IF no inspection panel is available to support the AOA probe, an inspection hole along with a doubler
and/or supporting structure may be installed in the wings skin. Please refer to AC43.13-1B Chapter 4,
AC43.13-2B Chapter 1 & Chapter 3 for guidance.
P/N D201305000058
Rev 1 Jul 2013
Figure 2-1: AOA Probe in Wing
1.5
= 5.94lbs.
X
200²
=
.83712
KLR 10 Installation Manual
²
= Drag in LBS at V
NE
NE
Planning
Page 2-3
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