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Figure 3. Power Transients
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Propeller Systems, Aircraft, Model Specification
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Figure 4. Design



img
MIL-P-26367A
3.4.11
Range and rates of pitch change. -
* 3.4.11.1 Flight and ground operation. - (Curves shall be supplied showing the range
of blade angle travel available, range at applicable step settings, range of pitch
change as a function of blade angle, rpm, and pressure or voltage, as applicable.)
3.4.12 Maximum diameter.- The maximum diameter of the propeller(s) shall not
inches.
feet
exceed
3.4.13 Position. -  The propeller is designed for a
(insert
tractor or pusher) installation.
The direction of propeller rotation, when viewed from the
3.4.14 Rotation. -
rear of the aircraft, shall be as follows:
Type of drive
Direction of rotation
Single
Dual
Front
Rear
(Insert direction of rotation right hand or left hand as applicable,  The front
propeller of a dual rotation assembly is the furthermost propeller from the engine or
gearbox.)
3.4.15 Number of blades. - The number of blades of the propeller shall be as
follows:
Configuration
No. of blades
Fixed blades
Removable blades
(In cases of dual rotation propellers, indicate dual.)
3.4.16  Design Aq. -
The estimated maximum design Aq versus speed curves, in-
cluding the determining information shall be as shown on figure
(The data and
curves shall be furnished in accordance with figure 4.)
The propeller blade activity factor shall be
3.4.17 Blade activity factor. -
AF (nondimensional).
The propeller polar moment of inertia shall
* 3.4.18 Polar moment of inertia. -
slug-ft2.
be
3.7 Drawing and diagrams. - The following (insert manufacturer's corporate
name) drawings and diagram form a part of this specification: (Designate applicable
drawings and diagrams, including a propeller intallation drawing, as specified in
MIL-P-26366.)
9

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