Embraer EMB145, Operation Manual

Page: 1982 / 2662

AIRPLANE
OPERATIONS
MANUAL
LANDING GEAR AND
BRAKES
REVISION 40
2-12-15
Page
1
Code
01
A
O
M-145/1
114
NOSE WHEEL STEERING SYSTEM
The nose wheel steering system is electronically controlled and
hydraulically operated. It is powered by the hydraulic system 1. The
Electronic Control Module is energized when the landing gear is down
and locked, with the airplane on ground. In this condition, steering can
be controlled by either the pedals or the steering handle. In either
case, the commanded displacement is measured by a potentiometer
box, which transmits the signal to the Electronic Control Module. The
Electronic Control Module signals the hydraulic manifold to pressurize
the steering actuator in the commanded direction. For monitoring
purpose, a feedback potentiometer in the nose landing gear leg
transmits nose wheel displacement information to the Electronic
Control Module.
Maximum nose wheel displacement values due to actuation of the
steering handle and pedals are presented in the table below in degrees:
CERTIFICATION APPLICABILITY
PEDALS
ONLY
STEERING
HANDLE
ONLY
HANDLE
AND
PEDALS
CTA/JAA All Airplanes 5

71

76

Pre-Mod. SB 145-32-
0002
5

50

55

FAA
Post-Mod. SB 145-32-0002
or S/N 145.029 and on
5

71

76

NOTE: Steering handle actuation with nose wheels beyond their
operational limits may cause damage to the nose wheel
steering system.
Check if the nose wheel position indication mark is within the
nose wheel position indication scale limits.
A position sensor set to 7

disengages the system if the nose wheel is
rotated above this limit by using the rudder pedals. To reengage the
system, resume command through the handle.