Rockwell Commander 112 User manual

Rockwell
Commander
112/B/Tc/TCA
REVISION
1: 23
APRIL
1977
CHANGED:
7
JANUARY
1980
MANUFACTURERSSERIALNO.
________________________
_
REGISTRATION
NO.
________________________________
_
For coordination
with
sales
and service
information,
Serial No.
126
thru
499
are
referred
to
as
Model
112A.
At
the
time
of
issue
of
this Maintenance Manual, the contents were,
to
the
best
of
Rockwell International's knowledge, adaquate
to
maintain the
aircraft
in a continued
airworthy
condition.
'!'
Rockwell International
General
Aviation
Division
5001
North
Rockwell Avenue
Bethany, Oklahoma 73008 PIN M112001-2
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**
Includes Interim Change 4/1/86 and
Interim Change 2, 9/1/96

Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**




ROCKWELL
COMMANDER
112/B/TC/TCA
MAINTENANCE MANUAL
LIST
OF
EFFECTIVE
PAGES
LIST
OF
EFFECTIVE
PAGES
TOTAL
NUMBER OF PAGES IN THIS PUBLICATION IS 287 CONSiSTING OF THE FOLLOWING:
Page
Issue
*Title
....................
Change
4
*A
........................
Change
4
*B
........................
Change
4
i
thru
iii
................
Revision
1
iv
Blank
................
Revision
1
v
thru
vi
.................
Change
2
1-1
.....................
Revision
1
1-2
......................
Change
1
1-3
.....................
Revision
1
1-4
thru
1-5
..............
Change
3
1-
6
........
. . . . . . . . . . .
..
Revision
1
1-7
thru
1-8
..............
Change
1
2-1
thru
2-5
.............
Revision
1
2-6
......................
Change
3
2-7
.....................
Revision
1
2-8
......................
Change
3
2-9
thru
2-10
............
Revision
1
2-11
.....................
Change
3
2-12
....................
Revision
1
*2-13
.....................
Change
4
*2-14
................•.•..
Change
4
2-15
.....................
Change
1
2-16
....................
Revision
1
2-17
.....................
Change
1
2-18
.....................
Change
2
2-18A
...................
Change
2
2-18B
Blank
....
. . . . . . . .
..
Change
2
2-19
thru
2-20
............
Change
2
2-20A
...................
Change
2
2-
20B
Blank
..........
. .
..
Change
2
2-21
.....................
Change
2
2-22
thru
2-29
...........
Revision
1
2-30
thru
2-32
............
Change
3
3-1
......................
Change
2
3-2
.....................
Revision
1
3-3
thru
3-4
..............
Change
2
3-5
....................
Revision
1
3-6
thru
3-8
..............
Change
2
*3-9
.......................
Change
4
3-10
......................
Change
3
*3-11
...............••...••
Change
4
3-12
.....................•
Change
1
3-13
.............•.•..•..•
Change
2
*3-14
.............•...•...•
Change
4
4-1
......................
Change
2
4-2
thru
4-9
.............
Revision
1
4-10
thru
4-11
............
Change
1
4-12
....
. . . . . . . . . . . . . . .
..
Change
3
4-13
thru
4-16
...........
Revision
1
4-17
.....................
Change
1
Page
Issue
4-18
thru
4-24
........
Revision
1
4-25
.....................
Change
3
4-26
thru
4-28
...........
Revision
1
4-29
.....................
Change
3
4-30
thru
4-34
..
.
........
Change
2
5-1
......................
Change
2
5-2
thru
5-4
.............
Revision
1
5-5
thru
5-6
..............
Change
2
5-
6A
....................
Change
2
5-6B
Blank
..............
Change
2
*5-7
thru
5-8
•..............
Change
4
5-
9
..............•........
Change
3
5-10
thru
5-11
...........
Revision
1
5-12
Blank
..............
Revision
1
6-1
..
. . . . . . . . . . . . . . . . .
..
Revision
1
6-
2
thru
6-
5
..
. . . . . . . . . .
..
Change
2
6-
6
thru
6-
9
...............
Change
3
6-10
....................
Revision
1
6-11
......................
Change
3
6-12
thru
6-14
...........
Revision
1
6-15
thru
6-16
...
. . . . . . .
..
Change
2
6-17
thru
6-19
...........
Revision
1
6-20
. . . . . . . . . . . . . . . . . . .
..
Change
3
6-21
thru
6-26
...........
Revision
1
7-1
thru
7-3
.............
Revision
1
7-4
......................
Change
2
7-5
thru
7-7
.............
Revision
1
7-8
......................
Change
2
7-9
.....................
Revision
1
7-10
thru
7-11
............
Change
2
7-12
....................
Revision
1
7-13
.....................
Change
1
7-14
thru
7-20
...........
Revision
1
7-21
.....................
Change
1
7-22
.....................
Change
2
7-23
thru
7-27
...........
Revision
1
7-28
Blank
..............
Revision
1
8-1
......................
Change
1
8-2
thru
8-3
.............
Revision
1
8-
4
......
. . . . . . . . . . . . . .
..
Change
2
8-4A
....................
Change
2
8-4B
Blank
..............
Change
2
8-5
thru
8-8
.............
Revision
1
8-
9
..
. . . . . . . . . . . . . . . . . .
..
Change
1
8-10
.....................
Change
2
8-11
thru
8-12
............
Change
1
8-13
.....................
Change
3
8-14
.....................
Change
2
8-14A
...................
Change
1
8-14B
Blank
.............
Change
1
INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.
*The asterisk indicates pages changed,
added
or
deleted by
the
current
change.
Change
4 A
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

LIST
OF
EFFECTIVE
PAGES
MAINTENANCE
MANUAL
LIST
OF
EFFECTIVE
PAGES (CONTD)
Page
Issue
8-15
thru
8-20
...........
Revision
1
8-21
.....................
Change
3
8-22
Blank
..............
Revision
1
9-1
thru
9-4
.............
Revision
1
9-
5
.....................
Change
1
9-6
thru
9-8
.............
Revision
1
10-1
thru
10-6
...........
Revision
1
10-7
.....................
Change
2
10-8
Blank
..............
Revision
1
10-9
thru
10-62
.........
Revision
1
10-
63
....................
Change
1
10-64
..
,
.................
Change
2
10-
64A
..................
Change
2
10-
64B
Blank
.............
Change
2
10-
65
..
. . . . . . . . . . . . . . . .
..
Change
1
10-
66
..............
. . . .
..
Change
2
10-66A
..................
Change
2
10-66B
Blank
............
Change
2
10-67
thru
10-68
..........
Change
1
10-
68A
..................
Change
1
10-
68B
Blank
. . . . . . . . . . .
..
Change
1
10-69
thru
10-70
..........
Change
2
10-70A
..................
Change
3
10-70B
Blank
.............
Change
2
10-71
thru
10-72
.........
Revision
1
10-73
..
,
.................
Change
1
10-74
....................
Change
2
10-75
....................
Change
2
10-76
Blank
..............
Change
2
Change
1
........
September
2,
1977
Change
2
..........
March
24,
1978
Change
3
.............
April
16,
1979
Change
4
...........
January
7,
1980
INSERT
LATEST
CHANGED PAGES, DESTROY SUPERSEDED PAGES.
*The asterisk indicated pages changed,
added
or
deleted
by
the
current
change.
B
ROCKWELL
COMMANDER
112/B/TC/TCA
Change
4
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

ROCKWELL
COMMANDER
112/B/TC/TCA
MAINTENANCE
MANUAL
INTRODUCTION
INTRODUCTION
This
Rockwell
International,
General
Aviation
Division
Maintenance
Manual
has
been
prepared
by
the
Tech-
nical
Publications
Department.
It
contains
informa-
tion
on
all
aircraft
systems
and
operating
procedures
required
for
safe
and
effective
maintenance.
It
shall
not
be
used
as
a
substitute
for
sound
judgement.
APPLICABLE PUBLICATIONS
1.
2.
3.
4.
Pilots
Operating
Handbook
or
Flight
Manual
Pilots
Checklist.
Illustrated
Parts
Catalog.
Service
Releases.
HOW
TO
GET
COPIES
AUTOMATIC DISTRIBUTION
To
receive
future
changes
and
revisions
to
this
manual
or
to
any
other
publication
automatically,
an
aircraft
unit
must
be
established
on
the
automatic
distribution
list
maintained
by
the
Technical
Publications
Depart-
ment.
All
owners
of
new
and
used
aircraft
can
be
established
on
the
automatic
distribution
list
or
change
existing
publications
requirements
of
an
aircraft
unit
by
submitting
a
properly
executed
Technical
Manual
Owner
Address
Change
Card
Form
(AC
1661) found
in
the
front
of
all
Maintenance
Manuals
leaving
the
factory.
Other
publications
may
be
purchased
by
completing
Technical
Manual
Order
Form
(AC
1658
or
AC
1659). Additional
information
is
provided
in
Service
Information
No.
SI-IOI.
ADDITIONAL
COPIES
Additional
copies
of
this
manual
and
related
changes
may
be
procured
by
submitting
a
Technical
Manual
Order
Form
(AC
1658
or
AC 1659) found
in
the
back
of
all
Maintenance
Manuals
delivered
from
the
factory.
REQUESTING
MANUALS
CORRECTIONS/
CHANGES
Recommended
changes
or
corrections
to
this
manual
may
be
submitted
by anyone
using
the
manual.
Change/
correction
recommendations
shall
be
submitted
on
the
Publications
Change
Request
Form
(AC
1432)
foundin
the
back
of
all
manuals
delivered
from
the
factory.
All
recommended
changes
will
be
reviewed
by
Cus-
tomer
Service,
Engineering,
etc.,
before
incorpora-
tion
or
rejection.
Additional
forms
may
be
requested
from
Rockwell
International
-
General
Aviation
Division.
CHANGES
AND
REVISIONS
There
are
two
types
of
changes
and
one
type
of
revi-
sion
used
to
keep
this
manual
current.
The
material
compiled
in
these
changes
and
revisions
will
consist
of
information
necessary
to
maintain
the
present
equipment
or
new
equipment
added
to
the
airplane.
It
is
imperative
that
this
material
be
inserted
in
the
manual
at
the
time
it
is
received.
INTERIM
CHANGE
An
interim
change
will
be
distributed
anytime
it
is
necessary
to
forward
immediate
information
to
the
holders
of
maintenance
manuals.
The
interim
change
will
consist
of
colored
pages
which
are
inserted
in
the
appropriate
section
of
the
manual
until
formal
white
change
pages
are
issued.
This
interim
change
will
include
deletions
and/or
additions
of
material
pertinent
to
specific
paragraphs
or
illustrations
of
the
manual.
FORMAL CHANGE
A
formal
change
will
be
distributed
periodically,
to
holders
of
maintenance
manuals,
and
will,
in
most
instances,
supersede
previous
interim
changes.
These
changes
will
be
page
replacements
and
shall
be
inserted
in
the
manual
in
accordance
with
the
in-
structions
given
below:
1.
2.
Replace
the
obsolete
pages
in
the
manual
with
formal
change
pages
of
the
same
page
number.
Insert
pages,
with
page
numbers
followed
by
a
letter,
in
direct
sequence
with
the
same
common
numbered
page,
i.
e
.,
5-1,
5-1A,
5-2,
5-2A,
5-2B:
and
5-3.
REVISIONS
The
revision
is
distributed
when
over
sixty
percent
of
the
manual
has
been
changed
due
to
major
changes
to
equipment
and/or
accumulated
formal
changes
require
a
revision
to
the
manual.
A
revision
will
replace
every
existing
page
in
the
manual
and
should
be
inserted
in
the
manual
as
follow
s:
i
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

INTRODUCTION MAINTENANCE
MANUAL
ROCKWELL
COMMANDER
112/B/TC/TCA
1.
Remove and
dispose
of
all
pages
in
the
manual
except
the
tab
dividers
and
insert
the
new
pages
in
each
section.
IDENTIFICATION OF CHANGED MATERIAL
Changed
text
will
be
identified
by a
black
vertical
line
along
the
outside
margin
of
the
page,
opposite
revised
or
added
material.
Changed
illustrations
will
have
symbols
within
the
border
of the
illustration
to
indicate
minor
changes.
Major
changes
requiring
complete
redrawing
of
an
illustration
will
be
indicated
by a
black
vertical
line
along
the
outside
margin
of
the
page
opposite
the
illustration.
Revisions
of
text
and
illustrations
will
not
have
any
change
markings
as
they
are
treated
as
new
pages
in
a new
manual.
WARNINGS, CAUTIONS,
AND
NOTES
The
following
definitions
apply
to "WARNINGS",
"CAUTIONS", and "NOTES" found throughout
the
manual.
ii
I
WARNING
I
An
operating
procedure,
practice,
or
condition,
etc.,
which
may
result
in
injury
or
death,
if
not
carefully
observed
or
followed.
An
operating
procedure,
practice,
or
condition,
etc.,
which
may
result
in
damage
to
equipment,
if
not
carefully
observed
or
followed.
NOTI
An
operating
procedure,
practice,
or
condition,
etc.,
which
is
essential
to
emphasize.
WORDING
The
concept
of
word
usage
and
intended
meaning
which
has
been
used
in
preparing
this
manual
is
as
follows:
"Shall"
has
been
used
only when
application
of
a
pro-
cedure
is
mandatory.
"Should"
has
been
used
only when
application
of a
procedure
is
recommended.
"May"
and
"need
not"
have
been
used
only when
appli-
cation
of
a
procedure
is
optional.
'Will"
has
been
used
only
to
indicate
futurity,
never
to
indicate
any
degree
of
requirement
for
application
of a
procedure.
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

ROCKWELL
COMMANDER
112/B/TC/TCA
MAINTENANCE
MANUAL
TABLE
OF
CONTENTS
TABLE
OF
CONTENTS
SECTION PAGE
GENERAL
INFORMATION
................
1-1
II
GROUND
HANDLING,
SERVICING,
INSPECTION,
AIRFRAME
MAINTENANCE,
LUBRICATION
AND
STORAGE.
. . . . . . . . . . . . . . . .
..
2-1
III
HYDRAULICS. . . . . . . . . . . . . . . . . . . . . .
..
3-1
IV
POWER
PLANT
AND
PROPELLER
..........
4-1
V
FUEL
SYSTEM
.......................
5-1
VI
LANDING
GEAR,
WHEELS
AND
BRAKES. . . .
..
6-1
VII
FLIGHT
CONTROLS
...................
7-1
VIII
INSTRUMENTS.......................
8-1
IX
HEATING
AND
VENTILATION
....
· ·
....
· .
..
9-1
X
ELECTRICAL
SYSTEM
..................
10-1
iii/iv
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

ROCKWELL
COMMANDER
112/B/TC/TCA
MAINTENANCE MANUAL
LIST
OF
ILL
USTRATIONS
Figure
1-
1
1- 2
2- 1
2- 2
2- 3
2- 4
2- 5
2- 6
2- 7
2-
8
2-
9
2-10
2-11
2-12
2-13
2-14
2-15
2-16
3-
1
3-
2
3-
3
3-
4
3-
5
3-
6
3-
7
3-
8
4-
1
4- 2
4- 3
4- 4
4-
5
4-
6
4-
7
4-
8
4-
9
4-10
4-11
4-12
4-13
I
:=i~
4-16
5-
1
5- 2
5-
3
5-
4
5- 5
5- 6
5-
7
5-
8
Change
2
LIST
OF
ILLUSTRATIONS
Title
Page
General
Dimensions
•.•.•...•.•••.•
1-
2
Station
Diagram
.•.••.••.•.•.••.••
1-
4
Internal
Control
Lock.
. • • . . • . . • • .
..
2-
2
Mooring
.........•...............•
2-
3
Jacking
.........................•
2-
4
Servicing
Chart
........••.....•.••
2-
7
Hydraulic
Power
Pack
.••....•.....
2-
8
Induction
Air
Filter
.•••...•••...•.
2-
9
Fuel
Tank
Capacity
.........•...••
2-10
Inspection
Intervals
Chart.
• • • • • •
••
2-12
Windows
and
Windshield
Installation
2-17
Cabin
Door
•...............•
• .
••
2-18
Baggage
Door
.......•...•••..••.
2-20
Wing
Installation
.......•...•••••.
2-22
Empennage
Installation
.•..•••••••
2-24
Inspection
Plates
and
Access
Covers
2-25
Lubrication
Chart
•.......•.•••••
2-26
Torque
Values
• . . . . . . • . . . . . • • •
•.
2-32
Hydraulic
Equipment
Locator
•...•.
3-
2
Hydraulic
System
Schematic
-
Gear
Retracted
••••..••.....•...
3-
3
Hydraulic
System
Pressure
Settings
Landing
Gear
Actuating
Cylinders
.•
Hydraulic
Power
Pack
......••••.
Hydraulic
Gear
Lines
.•.•••••••.
Hydraulic
System
Check
...•.•••••
Trouble
Shooting
Hydraulic
System
.
3-
6
3-
7
3-10
3-11
3-12
3-13
Engine
Assembly
•.......•....•..•.
4-
2
Magneto
-
Cam
End
View
.••....•.•
4-
4
Ignition
Wiring.
• . . . . . . • . . . . . . • . .
.•
4-
6
Induction
Air
System
•.............
4-
7
Fuel
Injection
System
......•......•
4-
9
Carburetor
.................•....
4-10
Exhaust
Stack
•.•..•..•............
4-14
Engine
Baffle
Assembly
•....••••.•.
4-15
Engine
Control
Quadrant
••••••..•••
4-17
Engine
Mount
•....•.••..•.•.••..•.
4-20
Engine
Cowling
...•.....•.........
4-22
Detail
Engine
Specifications
.•......
4-25
Propeller
••.......•.........•..•.
4-28
Propeller
Pitch
Settings
...........
4-30
Checking
Blade
Angle
.............
4-30
Trouble
Shooting
Engine
and
Propeller
.....................
4-
31
Fuel
System
......................
5-
2
Transmitter
Installation
. . • •• • .
•.
5-
4
Fuel
Calibration
Table
....••••••.
5-
6
Transmitter
Float
Arm
Adjustment.
5-
7
Fuel
Gascolator
............•••••
5-
8
Finger
Inlet
Screen
.......•.•••••
5-
9
Fuel
Selector
. . . . . . • . . . . . • . . • •
••
5-
9
Trouble
Shooting
Fuel
System
••••.
5-10
Figure
6- 1
6-
2
6- 3
6- 4
6-
5
6-
6
6- 7
6- 8
6- 9
6-10
6-11
6-12
7- 1
7- 2
7- 3
7- 4
7- 5
7-
6
7- 7
7- 8
7- 9
7-10
7-12
7-11
7-13
7-14
7-15
7-16
8-
1
8- 2
8-
3
8- 4
8-
5
8-
6
9-
1
9-
2
9-
3
10-1
10-2
10-
3
10-4
10-
5
10-
6
10-7
10-8
thru
10-27
Title
Main
Landing
Gear
•...............
Main
Landing
G;~ar
Strut
Assembly
..
Nose
Landing
Gear
.•...•........•.
Nose
Landing
Gear
Strut
Assembly
..
Emergency
Extension
Valve
Control.
Nose
Gear
Shimmy
Dampener
.....
.
Nose
Wheel
Steering
System
......
.
Wheel
and
Tire
Assemblies
•.......
Tire
and
Strut
Inflation
Pressures
..
.
Brake
Cylinder
Assemblies
........
.
Brake
Assembly
.................
.
Trouble
Shootin!~
The
Landing
Gear
System
.......................
.
Control
Column
Aileron
Controls
................
.
Aileron
Control
Chain
Location
....
.
Flap
Controls
Installation
.........
.
Wing
Flap
Warning
Switch
.........
.
Rudder
Pedal
Installation
.........
.
Rudder
Controll:,
.................
.
Elevator
Controls
................
.
Elevator
T
rim
Controls
...........
.
Elevator
Trim
\Vheel
.............
.
Aileron-Rudder
Interconnect
Rig¢.ng
Control
Travel
Gage
Locations
.....
.
Control
Surface
Travel
and
Cable
Tensions
.....................
.
Control
Surface
BalanCing
........
.
Cable
Tensions
Temperature
Conversion
Chart
.............
.
Trouble
Shootin:s
Flight
Control
System
......................
.
Instrument
PanEl
................
.
Pitot-Static
System
•...............
Pitot-Static
Test
Bulb
.............
.
Vacuum
System
Installation
.......
.
Instrument
Markings
•.............
Trouble
Shooting
Instruments
and
Vacuum
System
...............
.
Heating
and
DeL:-osting
System
Page
6-
4
6-
6
6- 8
6-10
6-12
6-13
6-14
6-18
6-20
6-21
6-23
6-25
7-
2
7-
5
7- 8
7-
9
7-10
7-12
7-14
7-15
7-16
7-18
7-21
7-19
7-22
7-23
7-23
7-24
8-
2
8-
4
8-
5
8-
6
8-10
8-15
Installation
.........•..........
9- 2
Valve
Assembly
................
9-
4
Cabin
Ventilation
System
Installation
9-
6
Battery
Charge
Rates
.............
10-
2
Hydrometer
Readings
.............
10-
2
Battery
•.........................
10-
2
Alternator
........................
10-
3
Electrical
Load
Chart
.............
10-
5
Bulb
Replaceme:lt
Guide
...........
10-
5
Circuit
Breakers
.................
10-
6
See
Wiring
Diag:::-ams
Index,
Part
I
..•
10-
9
v
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

LIST
OF
ILLUSTRATIONS
MAINTENANCE
MANUAL
LIST
OF
ILLUSTRATIONS
(CONTO)
Title
Page
10-28
Connector
and
T-Strip
Locator.
.
..
10-32
10-29
thru
10-38
See
Wiring
Diagrams
Index,
Part
II
10-33
10-39
Connector
and
T-Strip
Locator.
.
..
10-46
10-40
thru
10-49
See
Wiring
Diagrams
Index,Part
III
10-47
10-50
thru
10-57
See
Wiring
Diagrams
Index,
Part
IV
10-61
vi
ROCKWELL
COMMANDER
112/B/TC/TCA
Change
2
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

ROCKWELL
COMMANDER
112/B/TC/TCA
MAINTENANCE MANUAL SECTION I
GENERAL
lNFORMATION
SECTION I
GENERAL INFORMATION
T
ABLE
OF
CONTENTS
GENERAL DESCRIPTION
.................••
PRINCIPAL DIMENSIONS
•..•....•.........•
General
.•.••..•...•....••.....•••••.•.•
Wing
••..•..............................
Horizontal
Stabilizer
and
Elevators
•.•.•••
Vertical
Stabilizer
and Rudder
..••.•...•.•
Fuselage
•..•......•...........•.••....•
Areas
•....•••..••..••..•.•.•..•...••••
FUSELAGE AND
WING
ST
AT
IONS
•.•.....•.•
AIRCRAFT STRUCTURES
••.•...••.•
,
•.•...•
Fuselage
•••••••.••••••.••..•...•.•.••••
GENERAL DESCRIPTION
Page
1-1
1-1
1-1
1-3
1
..
3
1-3
1
..
3
1-3
1-3
1-3
1-3
These
aircraft
are
low-wing,
single-engine
aircraft
designed
for
business
and
pleasure.
The
Models
112/B
are
powered
by a
Lycoming
IO-360-C1D6,
200-
horsepower
engine while
the
Models
112TC/TCA
are
powered
by
a Lycoming
T0-360-C1A6D,
21D-horse-
powered
engine.
These
aircraft
use
a
Hartzell
2-
blade,
constant-speed
propeller.
Structural
integrity,
flight
safety,
and
minimum
maintenance
requirements
are
assured
by
the
construction
and
design
of
the
ma-
jor
airframe
components.
The
wing
design
and
its
position
in
relation
to
the
fuselage
provides
the
best
capability
and
aircraft
controllability
desired
for
optimum
performance.
The
design
concept
of
the
aircraft
embodies
maximum
safety,
minimum
main-
tenance
requirements
and
ease
of
accomplishing
nec-
essary
maintenance
and
servicing.
Access
covers,
doors,
and
quick opening engine cowling
provide
easy
access
to
aircraft
and
engine
systems
components.
The
retractable
tricycle
landing
gear
is
operated
hy-
draulically
during
normal
operation.
Passenger
and
pilot
comfort
are
assured
by
the
design of
the
seating
and
interiors,
which
are
completely
insulated
and
up-
holstered
for
noise
abatement,
warmth
and
appearance.
The
cabin
will
seat
up
to
three
passenger
s
in
addition
Wing
...................................
.
Empennage
••....••.•.•.•..............•
AIRCRAFT SYSTEMS
•.••......••.....•....
Hydraulic
System
•.•..•••......•..••....
Power
Plant
•.•.•.••••.•.••..•..•....•.•
Fuel
System
.•.....•...........•.•......•
Landing
Gear,
Wheels, and
Brakes
•.....•
Flight
Controls
••.......................
Instruments
•...•••.•.•........•....••..
Heating and Ventilation
.•.•...........••.
Electrical
System
•.•.....••.......•.....
Page
1-6
1-6
1-6
1-6
1-6
1-7
1-7
1-7
1-7
1-7
1-8
to
the
pilot.
Entrance
doors
located
on both
sides
of
the
fuselage
provide
access
to
the
cabin
area.
A
baggage
compartment,
which
contains
22 cubic
feet
of
storage
space,
is
located
aft
of
the
rear
seats
and
is
accessible
through
a
door
on
the
left
side
of
the
fuselage,
or
from
the
rear
seats.
PRINCIPAL
DIMENSIONS
GENERAL
Wing Span
Model 112 •. •. •. . . . . .
393.00
inches
(32 '
-9
")
Model
112B/TC/TCA
••
427.20
inches
(35
'-7.20")
Overall
Length
300.50
inches
(25 '
.0.50")
Height
to
Top of
Vert.
Stab 101. 00
inches
(8
'-5.00")
Main
Gear
Tread
Model 112
....•.•..•
128.44
inches
(10'
-8.
44
It)
Mode1112B/TC/TCA
131. 40
inches
(10'
-11.. 40")
Main
Gear
to
Nose
Gear
Model 112
•...•••.•..
82.97
inches
(6
'-10.97")
Mode1112B/TC/TCA..
82.50
inches
(6
'_10. 50
ft
)
Gross
Weight
Model 112
(thru
SiN
125)
••.•.••.••
2550
lbs.
1-1
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

SECTION I
GENERAL
INFORMATION MAINTENANCE MANUAL
1----------
25' -
O.
50"---------,1
*
32'
- 9
ft
**
35'
-
7.20"
* 112 *
10'
-
8.44"
**
112B/TC/TCA
**
10'
-
11.40"
Figure
1-1.
General
Dimensions
1-2
-1
8'r
ROCKWELL
COMMANDER
112/B/TC
/TCA
X161A7
Change
1
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

ROCKWELL
COMMANDER
112/B/TC/TCA
MAINTENANCE MANUAL SECTION I
GENERAL
INFORMATION
Model
112 (126
and
subs)
•.•.••••••
26501bs.
Model
112B
.•..••••••.•••..••.•••
2800
lbs.
Model
112TC
••••..•.•.•••...••..•
2850
Ibs.
Model
112TCA • • . • . • . • . . . • . • . • • • • 2950
Ibs.
C.
G.
Limit,
Gross
Wt. FWD
(Normal
Category)
Model
112
(thru
SiN
125)
••.•....
15.
fifo
MAC
Model
112 (126
and
subs)
•...••••
18.8%
MAC
Model
112B
•...•....•..•..•••••
24.58% MAC
Model
112TC
....•••..........••
24.84%
MAC
Model
112TCA
•.......•.•...•••
26.68% MAC
c.G.
Limit,
Gross
Wt.
AFT
(Normal
Category)
Model
112
.....................
31.
5fifo
MAC
Model
112/B/TC/TCA
.••••••••••
31.77% MAC
WING
Airfoil
Section
(Chordwise).
NACA 632415
Modified
Root
Chord
•.•........•.•.•.•..••...•...
70.30
Tip
Chord
Model
112 •. . . . •. . . . . •. . . . . . •• . • •
35.15
in.
Models
112B/TC/TCA
•..•••••.•.••
32.
10
in.
Mean
Aerodynamic
Chord
Model
112 • . . •• . . . • . . . • . • •. • • . • . • 55.
05
in.
Model
112/B/TC/TCA
• • . • . • . • . • . •
59.84
in.
Angle
of
Incidence,
tip
..•••••••••••••••..•.
00
Dihedral
(at
main
spar)
•. . . • . •. . •. •• • . •. . . • • 70
Aspect
Ratio
Model
112 . . . . • . . . . . • • • • • . • • • • • • • . . .
.•
7.20
Models
112B/TC/TCA
.................
7.85
HORIZONTAL
STABILIZER
AND
ELEVATORS
Span
....................
161.
50
in.
(13
'_5.
50
If)
Airfoil
Section
•..•••...•
NACA
66-010
Modified
Root
Chord
..•..•••••••.•••••
• • . • •
••
47.
46
in.
Tip
Chord
••.•.•.•••••.••••.••••••.•
18.
36
in.
Mean
Aerodynamic
Chord
••••••••.•••
35.00
in.
Angle
of
Incidence
.•......••....••..••....
_20
Dihedral
•...•...
• • . . • . • • • • • • • . • • . . . . . . . • 00
Aspect
Ratio
.•.....••••.•••••..••.•...••
5. 38
Taper
Ratio
.•
. . . • • • • . . . . • . . • • . . • • • . . • . .
O.
39
VERTICAL
STABILIZER
AND
RUDDER
Airfoil
Section
...•..••••••..•...
NACA
66-012
Root
Chord
Model
112 • . . . . . . • • • • • • • • • • • • • • •
71.20
in.
Model
112B/TC/TCA
•.•••••••.•••
80.70
in.
Mean
Aerodynamic
Chord
Model 112 • . . . . . • • • . • • • • • . • . • . • •
50.90
in.
Model
112B/TC/TCA
••••••••••.••
56.81
in.
FUSELAGE
Cabin
Interior
-
Height
•.•.•..••..•..••
49.00
in.
-Width
•.•.•••.•.•.•..•
47. 00
in.
-
Length.
. . . • •. •. . . . . .
..
75.00
in.
-
Volume
....••.........
*99
cu.
ft.
*Rudder
pedal
to
back
of 2nd
seat.
Baggage
Compartment
Interior
-
-
Volume
••...•.•......•
22
cu.
ft.
2001bs.
-CapaCity
.•....••...••.•
AREAS
Wing
Model112
•...•..•..•....•.•..
Models
112B/TC/TCA
(incl
glove)
Aileron
••.........••....••......•
Flaps
•.....•....•.......•.•.....
Horizontal
Stabilizer
(incl
elev.
)
•...
Elevators
(incl
tabs)
•••.•...•.....
Vertical
Stabilizer
(incl
rudder)
Model
112
•...•.•••••••••.....
Models
112B/TC/TCA
•.••....••
Rudder
Model
112
•...•.•••.•.•.•.•...
Models
112B/TC/TCA
•...•...••
152.00
sq.
ft.
163.81
sq.
ft.
11. 00
sq.
ft.
18.00
sq.
ft.
33.64
sq.
ft.
18. 00
sq.
ft.
17.
00
sq.
ft.
22.36
sq.
ft.
5.00
sq.
ft.
5.75
sq.
ft.
FUSELAGE
AND
WING
STATIONS
The
station
diagram
shown
in
Figure
1-
2
provide
s a
convenient
method
for
identifying
and
locating
refer-
ence
points
on
major
components
of
the
fuselage
and
wings.
These
reference
points
are
numbered
in
inches.
The
fuselage
stations
are
numbered
from
zero
to
298.50
inches
aft
of
zero.
Rib
stations
of
the
wing
and
horizontal
stabilizer
are
measured
from
the
centerline
of
the
fuselage
outboard,
along
the
surface
leading
edge.
The
top
of
the
vertical
stabilizer
rep-
resents
the
highest
reference
plane
which
is
101.00
inches
above
ground
level.
References
to
fuselage
and
wing
stations
numbers
and
Z
lines
are
used
as
a
means
of
pin-
pointing
the
location
of
structural
and
system
component
installations.
AIRCRAFT
STRUCTURES
FUSELAGE
The
fuselage
consists
of
the
nose
section,
center
section
and
aft
section.
The
nose
section
extending
from
fuselage
station
22.00
to
62.50
houses
the
power
plant
and
retractable
nose
landing
gear.
Nose
landing
gear
doors,
which
open
and
close
as
the
gear
is
ex-
tended
or
retracted,
form
an
aerodynamically
smooth
nose
section
during
flight.
The
nose
section
is
joined
to
the
center
fuselage
section
at
fuselage
station
62.50,
which
is
also
the
location
of
the
engine
firewall.
The
center
fuselage,
which
contains
the
main
cabin
area
and
baggage
compartment,
extends
from
fuselage
sta-
tion
62.50
to
178.00
where
it
is
joined
to
the
aft
fuse-
lage
section.
This
section,
which
houses
the
seats
for
pilot
and
three
passengers,
has
two
doors
that
afford
easy
access
to
the
aircraft
from
either
side.
The
pilots
area
is
equipped
with
a
wide-vision
wind-
shield
and
large
door
windows
to
assure
maximum
1-3
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

~
I
iI:o-
n
::r
§
~
Co:)
."
CI
c
...
•
-
I
~
'"
-
a
::::!".
0
:::I
e
Q'
CI
...
a
a
v;
:r
CD
CD
....
2.
~
~
~
~
~
~
~
~
~
CJ:)
co
(7.)
iI:o-
~
0
co
(7.)
iI:o-
N
?'
~
!C
!""'"
~
?'
::J
~
?'
;0
.....
o 0 N
iI:o-
c:J1
~
c:J1
C;.:)
Co:)
c:J1
o 0 0 0 0 0 0 0 0 0
. ,
roaJ-----
4.80
-38.70
47.16
\\1
I
58.95
70.50
I I
275.122 286.08
LEFT
HORIZONTAL
STABILIZER
N
0 275.12 298.50
I
--
Z 120.50
Z 82.75 Z 83.80
Z 63.41
Z 28.58 I
I~
J.
\---
~
o 22.00 27.50 62.50 85.00 123.00 168.32 178.00 205.00 230.50 263.00
§
~
t-rJ
t'"
~
~
N
2
0m
~tzjtzj
ozn
tzj'"
~~~
...::Jt"'-
(3
Z
~
!:
Z
-t
m
Z
,.
Z
n
m
~
,.
Z
C
,.
r-
~
~8~
txla:
~~
'4ztzj
n~t'"
>~t'"
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

ROCKWELL
COMMANDER
112/B/TC/TCA
MODELS
112B/TC/TCA
'1;)
d--
26.50
47.30
65.30
82.50
101.10
119.50
142.40
165.20
189.00
198.00
215.20
r:-
(C
Lt'.)
M
.....
CI':I
M
u-)
r:-
cO
N M
'<:t'
Lt'.)
MAINTENANCE MANUAL
~
PI;l
N
~
...:l
~
<
~
til
...:l
-<
~
0
N
-
~
::z::
~
~
~
...:l
0
Lt'.)
0
r:-
0
Lt'.)
N
.....
~
t-
N
0
LI.":)
0
N
.....
o
o
0 0
r:-«>
.
N
C'?
CI':I
«>
N
LI.":)
r:-
.
N
00
N
Figure 1-2. Station Diagram (Sheet 2 of 2)
Change
3
SECTION I
GENERAL
INFORMATION
.....
~
M
(C
N
o
o
\----M
(C
N
o
Lt'.)
'l---+----+-I
\----
0
M
N
o
o
1---+-----+--;----
~
N
o
o
«>
k----'-,...----+--\---
r:-
.....
o
o
--M
N
.....
o
o
Lt'.)
«>
o
LI.":)
r:-
\---r-..::,.--.'--+---
N
o
I~!::=::=r--/---
0
00
0
oo
0
";'cO
0
(CLI.":)
Lt'.)
N N N
N
N
--/---0
00
Lt'.)
cO
N
N
XU
23
1-5
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

SECTION I
GENERAL
INFORMATION MAINTENANCE MANUAL ROCKWELL
COMMANDER
112/B/TC/TCA
pilot
visibility
during flight.
The
aft fuselage
section,
extending
from
fuselage
station
178.00
to 263.00,
is
permanently
secured
to the
center
fuselage
section
and
provides
structural
attachment
points
for
the
em-
pennage flight
surfaces
and
controls.
This
section
houses
the
battery,
hydraulic
power
pack
unit and
various
control
surface
cables.
The
entire
fuselage
is
designed to
assure
a
strong
safety
margin
for
all
flight conditions and to
provide
attaching
structures
for
the wing and empennage.
Sturdy
aluminum
floor-
ing supported by longitudinal
beams
and bulkheads
extends
from
the
firewall
aft
through
the
baggage
com-
partment.
The
center
wing
structure
is
attached
to
the fuselage so
that
part
of
the wing
torque
is
absorbed
by the fuselage
structure.
WING
Each
wing
is
of
an
all-metal
stressed-skin
construc-
tion
incorporating
spars,
formed
ribs
and
an
integral
fuel
tank
contained
in
a
three-
rib
section,
forward
of
the
main
spar.
The
main
spar
of
each
wing
is
joined
at
the
center
of the
fuselage
with
spar
cap
splices.
The
wing
is
installed
in
the
lower
center
fuselage
section
and
secured
to the fuselage
loadbearing
frames
and fittings by
bolts
and
nuts
at
stations
85.00,
123,00
and
forward
of
station
148.00.
Access
plates
located
at
various
points on the
lower
skin
of the wing provide
access
for
inspection and
repair
of the fuel
system
and
the flight
control
cabling.
Landing
gear
fitting/retraction
mechanisms
are
in-
stalled
in the
basic
wing
structures
to provide
attach-
ment points
for
the
main
landing
gear.
An
opening
in
the inboard leading edge of
each
wing
serves
as
a
ram
air
intake
for
the
cabin
ventilation
system..
An
electrically
operated
wing flap
is
installed
between
the fuselage and
aileron
on
each
wing.
The
flaps
are
attached to
the
aft
wing
spar
by hinge assembliesQ
Extension
and
retraction
of the wing
flaps
is
controlled
by an
electrically
controlled
jackscrew
and
torque
tube
arrangement.
Metal
ailerons,
extending
outboard
from
the
flaps
to wing
station
189000,
are
attached
to
the
aft wing
spar
by hinge
assemblies.
EMPENNAGE
The empennage
consists
of the
vertical
and
horizontal
stabilizers.
The
vertical
fin
assembly
is
made of two
separate
components;
an
upper
assembly
which
is
mated
at
the
horizontal
stabilizer,
and a
lower
stub
assembly
which
is
integral
with the
aft
tailcone
struc-
ture.
A
rudder
control
surface
is
attached
to the
ver-
tical
stabilizer
at
two hinge points. A
fiberglas
rudder
cap
contains
provisions
for
mounting
various
electronic
antennas and the
anti-collision
beacon.
The
horizontal
stabilizer,
consisting
of a fixed and
movable
elevator
surface,
is
attached
to the
lower
vertical
stabilizer
stub
assembly.
The
horizontal
and
vertical
stabilizers
both
utilize
stressed
and
beaded skin
construction
to provide maximum
strength
with minimum
structural
components. The
horizontal
surface
is
of
single
unit
constructions
with a fixed
for-
ward
surface
and a hinged
elevator
control
surface.
1-6
The
elevator
provides
mounting
attachment
for
a
fiberglass
tip-fairing
at
each
outboard
end
for
stream-
lined
appearance.
The
aft
tailcone
assembly
is
also
capped by a
fiberglass
stinger
containing
mounts
for
a
tail
navigation
light
and
lens
assembly,
and
tail
tie-
down
ring
mounted
in
the
vertical
fin
portion
of
the
cap_ The
rudder
and
elevators
are
controlled
by a
cable
and
pulley
system
attached
to
the
control
sur-
face
bellcrank
or
horn.
Controllable
trim
tabs
are
installed
on the
elevators.
A
ram
air
intake,
reces-
sed
into the
center
of
the
vertical
stabilizer,
pro-
vides
maximum
cool
air
for
in-flight
cabin
ventilation.
AIRCRAFT
SYSTEMS
HYDRAULIC SYSTEM
The
landing
gear
system
extension and
retraction
actuators
are
operated
by the
aircraft
hydraulic
sys-
tem.
Hydraulic fluid
under
pressure
is
supplied to
the
system
by an
electric
hydraulic
power
pack
unit
installed
in
the
left
forward
area
of the
aft
section_
A landing
gear
selector
switch,
mounted on
the
instrument
panel,
controls
the
direction
of fluid
flow
from
the
pump to
permit
gear
retraction
or
extension.
An
emergency
extension
system
is
provided
to
operate
the landing
gear
in
the event the
hydraulic
system
malfunctions.
The
gear
will
drop
by
gravity
assisted
by down
springs.
Other
hydraulic
components
use
hydrauliC fluid but
are
not function-
ally
associated
with
the
primary
hydraulic
system.
These
are
the
master
brake
cylinders,
nose
shimmy
dampener,
nose
and
main
gear
struts
and wheel
brakes.
All of
these
components have
self
contained
reservoirs
and
are
not dependent upon the
main
sys-
tem.
POWER
PLANT
MODELS
112/B.
A
direct-drive
200-horsepower
Lyc-
oming IO-360-C1D6 engine
is
used
to
power
the
air-
craft.
The
engine
is
a
four-cylinder
horizontally-
opposed
air
cooled engine which
employs
a wet
sump
oil
system
and
is
equipped with fuel
injection.
Engine
shock
mounts,
which dampen engine
and
propeller
vibration,
support
the engine
on
the
welded
tubular
engine mount bolted to the
airframe
firewall.
On
Model
112,
the engine
is
equipped with a
Hartzell
HC-E2YR-1BF/F7666A
all
metal
constant
speed
pro-
peller.
The
Model 112B
aircraft
is
equipped with a
Hartzell
HC-E2YR-1BF
/F8467-7R
propeller.
The
engine cowling
consists
of two
fiberglass
segments
that
are
easily
removed
for
quick
access
to
all
parts
of
the
engine.
The
lower
segment
is
attached
to
the
forward
fuselage
with machine
screws
and
is
removed
only when
removing
the
engine
or
performing
mainte-
nance on
the
lower
portion
of
the
engine.
The
upper
segment
containing
the
oil
access
door
is
held
in
place
to
the
lower
segment
by four Camioc
latches
and
two
studs.
Adjustable cowl
flaps,
located
in
the
lower
segment
of
the
engine cowl,
control
cylinder
head
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**

ROCKWELL
COMMANDER
112/B/TC/TCA
MAINTENANCE MANUAL SECTION I
GENERAL
INFORMATION
temperature
during
flight.
All
engine
accessories
except
the
alternator
are
attached
to
mounting
pads
on
the
engine.
MODELS
112TC/TCA.
A
direct-drive
210-horsepower
Lycoming
TO-3GO-C1A6D engine
is
used
to .power
the
aircraft.
The
engine
is
a
four-cylinder
horizontally-
opposed
air
cooled
turbocharged
engine which
employs
a
wet
sump
oil
system.
Engine shock
mounts,
which
dampen engine
and
propeller
vibration,
support
the
engine on
the
welded
tubular
engine mount
bolted
to
the
airframe
firewall.
The
engine
is
equipped with
a
Hartzell
HC-E2YR-1BF
/F8467-7R
all
metal
con-
stant
speed
propeller.
The
engine cowling
consists
of two
fiberglass
segments
that
are
easily
removed
for
quick
access
to
all
parts
of
the
engine.
The
lower
segment
is
attached
to
the
forward
fuselage
with
screws
and
is
removed
only when
removing
the
engine
or
performing
maintenance
on
the
lower
por-
tion of
the
engine. The
upper
segment
containing
the
oil
check
door
is
held
in
place
to
the
lower
segment
by
four
Camloc
latches
and
two
studs.
Adjustable
cowl
flaps,
located
in
the
lower
segment
of
the
engine
cowl,
control
cylinder
head
temperature
during
flight.
All
engine
accessories
except
the
alternator
are
at-
tached
to
mounting
pads
on
the
engine.
FUEL
SYSTEM
Fuel
is
stored
in
the
integral
forward
wing
structure
•
of
each
wing (wet wing fuel tanks)
outboard
of wing
station
82.50
and
extending
to
wing
station
142.40.
The
Model 112
(Serial
numbers
thru
125)
has
a fuel
system
capacity
of
32
U.
S.
gallons
per
tank,
usable.
The
Model 112 (Serial
numbers
126
thru
155)
has
a
fuel
system
capacity
of 34
U.
S.
gallons
per
tank,
usable.
The
Models 112
(Serial
numbers
156
thru
499), 112B, 112TC
and
112TCA
has
a fuel
system
capacity
of 24 U •
S.
gallons
per
tank,
usable
with
standard
tanks
installed,
and
34
U.
S.
gallons
per
tank
usable
with optional
tanks
installed.
The
fuel
tanks
are
serviced
through
filler
ports
located
on
top
of
both
wings.
Fuel
is
supplied
from
the
tanks
through
the
fuel
selector
valve to
the
fuel
gascolator.
From
the
gascolator,
fuel
travels
through
the
electrically
operated
auxiliary
fuel pump to
the
engine-driven
fuel
pump.
The
auxiliary
fuel pump
is
used
for
engine
starting
and
also
provides
fuel
pressure
to
the
engine
in
the
event of
an
engine-driven
fuel pump
failure.
LANDING
GEAR, WHEELS,
AND
BRAKES
The
retractable
tricycle
landing
gear
is
operated
hy-
draulically.
Should a
failure
occur
in
the
hydraulic
system
an
emergency
system
is
provided
for
emer-
gency
extension
of
the
gear.
The
gear
is
held
in
the
up pOSition by
hydraulic
pressure
lock
and will
free-
fall to the down and
locked
poSition
if
normal
hydraulic
system
pressure
is
lost.
Emergency
extension
of the
main
gear
is
accomplished
by
placing
the
emergency
gear
extension
knob
in
the
DOWN
position
to
release
hydraulic
fluid
trapped
in
the
uplock
portion
of
actu-
ators.
This
bypasses
hydraulic
fluid
directly
to
the
Change 1
hydraulic
power
pack
reservoir
allowing the
gear
to
drop
by
gravity,
assisted
by down
springs.
Mechani-
cally
actuated
landing
gear
doors
enclose
the
main
gear
struts
within
the
Wing.
The
nose landing
gear,
which
retracts
into a wheel
well
under
the
engine
is
enclosed
by
mechanically
operated
wheel
well
doors
when
the
gear
is
retracted.
The
nose
and
main
land-
ing
gear
wheels
are
machined
castings,
consisting
of
two wheel
halves.
The
wheel
halves
are
not
inter-
changeable;
but
the
complete
wheel
assemblies
are
interchangeable
according
to wheel
size.
Disc
type
hydraulic
brakes,
attached
to the
main
landing
gear,
are
individually
controlled
by applying
toe
pressure
to
the
rudder
pedals
at
either
pilot
position.
A
park-
ing
brake,
which
operates
from
the
master
brake
cyl-
inder,
is
engaged by applying
toe
pressure
on
the
rudder
pedals
and
pulling out
the
PARK BRAKE
con-
trol
knob.
The
nose
wheel
steering
system
is
tied
to
the
rudder
trim
system
and
operated
by
depressing
the
rudder
pedals.
Initial
depression
of
the
pedal
starts
the
nose
wheel
turning
toward
the
desired
di-
rection,
while
further
pedal
pressure
results
in
a
combination of
nose
wheel
steering
and
main
wheel
braking
to
turn
the
aircraft.
FLIGHT CONTROLS
The
aircraft
is
equipped with a dual flight
control
sys-
tem,
which
utilizes
control
columns,
control
wheels,
and
rudder
pedals
to
operate
the
primary
flight
control
suIiaces.
Trim
tabs,
located
on the
elevators
are
controlled
by
rotating
the
trim
tab
control
wheel,
lo-
cated
in
the
center
console.
A fixed
position
ground
adjustable
trim
tab,
is
installed
on
the
trailing
edge of
the
left
aileron.
The
wing
flaps
are
operated
electric-
ally
and
controlled
by a
switch
on
the
lower
right
side
of
the
instrument
panel.
An
internal
control
lock,
which may
be
installed
in
the
control
column,
secures
the
ailerons
and
elevators
in
the
neutral
position
when
the
aircraft
is
parked.
INSTRUMENTS
All
instruments
except
magnetic
compass
and
outside
air
temperature
gage
are
installed
in
the
main
instru-
ment
panel
and
sub-panel
areas,
and
are
grouped
ac-
cording
to function and
ease
of
surveillance.
All
pri-
mary
flight and
gyro
instruments
are
installed
in
the
left
side
of
the
main
instrument
panel.
Manifold
pres-
sure
and
tachometer
gauges
are
mounted
in
the
lower
center
area
of
the
main
panel
and
the
remaining
engine
instruments
are
grouped
horizontally
ac
ross
the
left
instrument
Sub-panel. Lighting
for
the
instruments
is
furnished
by a combination of
post
lights
and flood
lights.
Optional navigation and
communications
equip-
ment
is
located
in
the
center
and
right
side
of
the
main
instrument
panel.
HEATING
AND
VENTILATION
The
forced
air
heating
and
ventilation
system
provides
heat
and ventilation to
the
cabin
area.
Heat
is
obtained
1-7
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**
This manual suits for next models
3
Table of contents
Popular Aircraft manuals by other brands

FlySynthesis
FlySynthesis STORCH CL Maintenance manual

AUTO GYRO
AUTO GYRO MTOsport Flight and operation manual

Grumman American
Grumman American GA-7 COUGAR Maintenance manual

Piper Aircraft Corporation
Piper Aircraft Corporation Cherokee PA-28-140 Operation Procedure

Badfish
Badfish MONARCH user manual

Dream-Flight
Dream-Flight alula TREK Flight and Assembly Manual