Reims Aviation Reims F 172 N Technical specifications
'
I
\...
1\
lHCR/\FT
FLIGHT M/\NUAL
REHvLS
/CESSN/\ F
172
N
Manufacturer
RE
I
MS
AVII\TION
Aerodrome
de
REHvfS
-PRUNAY
51100
REUv
fS
FRANCE
Ftench
Type
Certificate
No.
25
Serial
Number
:
Sections
: 2 - 3 - 5
Pages
2- 1 tltru i2- 7
3- 1 tlm1 3 - 8
5- 1 tlrru
S-3
ReQ;istration
Number
This
is
the
exact
translation
of
the
F
172
N
French
Flight
Manual
approved
by
DGAC
on
pctobe
r 27,
1976.
This
aircraft
must
be
operated
in
accordance
with
the
limite;
specified
in
this
Flight
Manual.
THIS DOCUMENT
MUST
BE
CARRIED
lN
THE
AIRCRAFT
/\T
/\LL
TIMES.
/\
lrcrafl
S
eda
1
No
.
lSlS
Qll
0-t
(
(
(
Flight
Manual
REIMS/CESSNA
F172N
Edition
1
....
August
1976
Revision
3 -
Sertember
1
~
TABLE
OF
CONTENTS
DGAC
Approved
Cover
P:tge
Table
of
Contents
List
of
Revised
Pages
SECTION
1 - GENERAL
Doc
wn
ents
A
V"a.
i
la
b1
e
Principal
Dimensions
Description
and
Characteristic
Dimensions
Instrument
Panel
Fuel
System
Electrical
System
Wing
Flap
System
Cabin
Heating
and
Ventilating
System
Parking
Bra.ke
System
Stall
Warning
Hom
SECTION
2 -
LIMITATIONS
Certificat
i
on
Basis
Indicated
Airspeed
Limitations
Approved
Maneuvers
0-1
0-2
al)d
0-3
U-4
:111d
0-5
1-1
1-2
1-3
thru
1
-5
1-6
::tnd
1-7
1-8
and
1-9
1
-1
0
thru
1-15
1-15
1-16
1-16
1-
16
2-1
2- 1
and
2-2
2-3
Engine
Operation
Limitations
<tnd
lnstnunent
Markings
2-3
;:wd
2-4
Placards
2-5
thru
2-7
SECTION
3 - ElvtERGENCY
PROCEDURES
Engine
Failure
Fires
Electrical
Power
Supply
System
Ma
lftmct
ions
Flight
In
Icing
Conditions
Inadvertent
Spin
Recovery
From
A
Spiral
Dive
Landing
Without
Pitch
Control
Forced
Landings
Ditching
3-1
and
3-2
3-2
t
hru
3
-4
3-4
3-4
~nd3-5
3-5
3-5
and
3-6
3- 6
3-6
and
3-7
3-7
and
3-8
Flight
Manual
REIMS/CESSNA
F172N
SECTION
4 -
NORMAL
PROCEDURES
Edition
1 -
August
197
6
Revision
4 -
May
1979
Loading
Graph
and
Center
of
Gravity
Moment
Envelope
4- 2
thru
4-6
Exterior
Inspection
Before
Flight
and
In-Flight
Checl<s
Operating
Details
Rough
Engine
Operation
or
Loss
of
Power
Specific
Operation
SECTION
5 -
PERFORMANCE
Notification
Demonstrated
Crosswind
Noise
Level
Airspeed
Correction
Table
Stall
Indicated
Airspeeds
Performance
and
Specifications
Tal
<
eoff
Distance
Maximum
Rate
of
Climb
Cruise
Performance
Range
and
Endurance
Profile
Landing
Distance
-
Jv
1a.x
im
urn
Glide
SECTION
6 -
APPENDIX
Servicing
Maintenance
Optional
Systems
0-3
4-7
thru
4-9
4-10
thru
4-
14
4-
15
thru
4-23
4-24
thru
4-
25
4 -25
thru
4 -27
5-1
5-1
5-1A
S-2
S-3
5-4
and
5-5
5-6
thru
5-8
.
5-9
and
5-10
5-12
and
5-13
5-
14
l h
ru
5-
17
5-18
5-19
6-0.
1
thru
6-0.
4
6-0.
5
thru
6-0.
7
6-1.
0 ·
and
on
l
Flight
Manual
.
REIMS/CESSNA
F172N
UST
OF
REVISED PAGES
Revisi0n
Revised
Pages
N
ature
of
Change
Edition
1 -
August
1976
Revision
4 -
Ma
y
1979
1
0-4
InsP.rt.ion
of
the
n o
atplan
e
optio
n.
2
3
6-
1.
0 (Cont 1
d )
6-16.
1
thru
G-1G.3G
0-2
thru
0- 4
1- 11 1
-4,
1-6
1-7,
1- 10 tl
uu
1-16
2 -
1,
2-2
, 2- 6
3-1
thru
3-8
4-1
, 4- 6,
4-8
4- 10
thru
4-27
5-4
and
5-5
6-
2.1,
6-7.2
and6-7.3
0
-2
, 0- 4 a
nd
0
-5
1-6
thru
1-
8,
1-11
1- 13
thru
1- 16
2-1
and
2-2
2-4 thru 2-7
3-2
and
3-4
4-7
thru
4- 10
4-13
and
4-18
5-2
6-1.0
6-2.
1
and
6..:.2~
2
6-7
. 2
and
6
-7
.3
6-7.6
and
6- 7
.7
6-
17.1,6
-
18.1
and
6-18.
2
1978
Model
beginning
w
ith
Serial
Number
1
64
0.
1979
Model
beg
inning
with
Serial
Number
1750.
o'Lo'L
tt
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Revision
No
4
{
Flight
Manual
RE
I
MS/
CESSNA
f172
N
LIST
OF
REVISED PAGES
Na
ture
of
Revised
Pages
Change
0-3
, 0
-4
, 0-5
1980
Model
1-1
' 1-
9,
1-11
beginning
wi
th
1-14,
1- 16
Serial
Number
2-1,
2-4
thru
2-6
19
to.
3-4,
4-2
and
4-2/\
4-10
thm
4-13
4- 18,
4-
20
thru
4-27
5-
lA,
5-18
S-2
thru
S-
4
S-6
thru
5-8
5-14
thru
5-18
6-
0.6
6
-1.
0
(1/2
)a
n
d(2/2)
6-1.
1,
6-1.2
6-2.1,
6-
2.2
Edition
1 -
Augmt
1976
Revis
i
on
4 - rv
iay
1979
Approval
Date
Visa
A,'LA.o
.
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:11111
a I
REIMS/CESSN/\
f172N
SECTION.l
GENERAL
NOTIFICATION
Edit
i
C'll
I - I'd'g
II~~~
I
~
l/
(;
Revisi0n
1\ -l\\:1y l
<J7~J
This
manual
contains
the
instructions
for
use,
and
the
list
of
Servicing
and
periodic
inspections,
as
well
as
the
performance
data
of
the
Model
REIMS/C£SSNA
f172N.
DOCUMENTS
AVAILABLE
The
following
is a
check
list
of
the
dnt:<,
inform;<tio
tJ
and
liccllscs
th:1r
are
part
of
the
airc
raft
file
:111d
required
b)'
Regulations
. The>'
sltould
be
made
available
at
all
times
to
relevant
Authority.
(
1)
Airworthiness
C
ertific:tte.
(2)
Registration
Certificate.
(3)
Radio
Installation
License
(if
rad.io
installed)
.
(4)
Log
Books.
(5)
Flight
Manual.
(6)
Certificate
of
Noise
Level,
1-1
1-2
Flight
Manual
REIMS/CESSNA
F172N
Edition
1
-August
1976
f--
-
--
8,
22m
__
_
____!.
_______
--!
PRINCIPAL
DIMENSIONS
*
PIVOT
PO
I
NT
1---
-
----
--
--
10,
97 m
-
1,91
m
Figure
1-1
NOTES.
1
Wmo
uun t.Mown
wuh
tHobf.
ll
ohu
inlUlle-d
2 M1a1mvm
hetQht
&how" Wt1h
n,o~
9t
"
c:Stpre-u.ed,
111
tuf"\
and
no•
1tru1 orOOHiy
1nfllted
, and
flaUung
beacon •
nualled
.
*
PIVOT POINT
Flight
Manu:tl
REIMS
/CESSNA
f172N
Edition
1 -
/\\!~list
l97(i
DESCRIPTION
AND
CHARACTERlSTfC
DIMENSIONS
OVER-ALL
DIMENSIONS
Wing
Sp:lll
Maximum
Length
lvbximum
Height
WING
Airfoil
Type
Wing
Area
Dihedral
Angle
Angle
of
Incidence
1
AILERONS *
Area
Control
Travel,
WING
FLAPS
Method
of
Actuation
Area
Control
Travel
Wing
Ro
ot
Wing
Tip
Up
Down
HORJZONTAL STABILIZER
AND
ELEVATOR. *
Stabilizer
A
rea
Angle
of
Incidence
*
Cable
control
systems
10.
97
m
With
OptiC'n::tl
Strobe
Light~
8.
22m
2.
68
Ill
With
Fla~hin~
Beacou
::m<..l
Nose
Strut
Depre
sse
cl
NACA2412
(1\lodi!ic<.l)
16.16m2
+ 1°
37'
(<tt
25%
chord)
+ 0°4
7'
-
2°50
'
1.
66
m2
;wo
+ lo
15° + 1°
Electric
/
C?..
ble
1.
97
m2
+
oo
00
to
40° -
zo
t-3
Flight
Manua
1
REIMS
/CESSNA
F172N
Elevd.tor
Area
Control
Travel,
Up
Down
ELEVATOR
TRlM
TAB
Control
Travel,
Up
Down
VERTl
CAL
FIN
AND
RUDDER
-)t
Fin
Area
Rudder
Area
Control
Travel
,
Left
(parallel
to
a / c
Right
longitudinal
axis)
lANDING
GE.t\R
Type
Shod<
Absor
b
er
}
Nose
Gear
Main
Gear
Tread
Nose
Wheel
Tire
and
Pressure 5.
00
X 5
Main
Wheel
Tire
and
Pressure 6,
00
X 6
Nose
Gear
Shock
S
trut
Pressure
·'.1-
Cable
control
systems
1-4
Edition
1 -
August
19
76
R
evision
2 - J
une
197'7
1. 35
m2
(incl
u
ding
tab
)
.J...
10
280 I
-
oo
+
10
23°
-
oo
28°
+
10
-
oo
130 +
10
-
oo
1.
26
m2
0.
69m2
16° + 1°
1G0 + 1°
Fixe~
Tric
y
cle
Air
-
Oil
Tub
ul
ar
Spring
2.
55
m
2.
14
bars
31 psi
2.
00
bars
29
psi
3.
10
bars
45
psi
Flight
Manu:tl
REIMS/CESSNA
F172N
Edition
1 -
1\ugust
1976
POWER PLANT
Engine
Fuel
Lycoming
0-320-HZAD
160
BHP
(119
kW)
100
LL
Grade
1\
viation
Fuel
(Blue
Color)
NOTE
100
(Formerly
100/
13
0)
1\v
iation
Grade
Fuel
(Green)
with
maximum
lead
content
of
4.
6
cc
per
gallon
is
also
approved
for
use
(Refer
to
Avco
Lycoming
Se
rv -
ice
Bulletin
W
1070F).
Oil
:
Recommended
Viscosity
For
Temperature
Range
:
MIL
-
L-6082
Aviation
Grade
Straight
Mineral
Oil
:
SAE
SO
above
16°C
SAE
40
between
-
1°
C
and
32°C
SAE
30
between
-
l8°C
and
21
°C
SAE
20
below
-
12°C,
MIL- L-
228S1
Ashless
Dispersant
Oil
:
SAE
40
or SAE
SO
above
16°C
SAE
40
between-
1
°C
and
32°C
SAE
30
or
SAE 40
between-
18°C
and
21°C
SAE
30
below
-
12°C
Carburetor
Heater
PROPELLER
Type
Number
of
Blades
Manually
Operated
!'vic
Cauley
1
C160
/
DTM7557
2.
Diameter,
Maximum
:
1.
91
m
Minimum
:
1.
88
m
Type
:
Fixed
pitch.
CABIN
Seating
Doors
Baggage
compartment
4
(plus
optional
child
seat)
2
i-5
flight
M:tntt:1l
REIMS/
CESSN.A f
172
N
INSTRUMENT
PANEL
Figure
1- 2
(Sheet
1
of
2)
l -6
Edit
i
on
1 -
.Augnst
1976
Revision
3 -
September
1978
.....
I
N
-{
/1
N
0
......
N
1.
Ammeter
2.
Suction
Gage
3.
Oil
Temperature,
Oil
Pressure,
and
Fuel
Qu
antity
Indicators
4.
Clock
5.
Tachometer
6.
Flight
I
nstrument
Group
7.
Airplane
Registration
Number
8.
Secondary
Altimeter
9.
Encoding
Altimeter
1 0.
ADF
Bearing
In
di c
ator
1 1,
Course
Deviation
Indicators
1 2.
Transponder
1
3.
Magnetic
Com
p
ass
1 4.
Marker
Beacon
Indicator
Lights
an
d
Switches
1
5.
Audio
Control
Panel
1
6.
Autopilot
Control
Unit
1 7.
Radios
1
8.
Ecouom
y
Mixture
Indicator
1
9.
Additional
Instrument
Space
2 0.
ADF
Radio
2 1.
Flight
Hour
Recorder
2 2 .
Map
Compartrne:J.t
2 3!_C_
abin
Heat
and
Air
Control
Knob
s
24.
Cigar
Ughter
25.
Wing
Flaps
Switch
and
Position
Indicator
26.
Mixture
Contro
l
Knob
2
7.
Throttle
(With
Friction
Lock)
28
.
Static
Pressure
Alternate
Source
V
alve
29.
Instrument
and
Radio
Dial
Light
Dimming
Rheostat
30,
Microphone
31.
Air
Conditioning
Controls
3
2.
Fuel
Selector
Valve
Handle
3
3.
Rudder
Trim
Control
Le
v
er
34.
Elevator
Trim
Control
Wheel
35.
Carburetor
Heat
Control
Knob
36.
Ele
c
trical
Switches
37.
Circuit
Breakers
38.
Parking
Brake
Handle
39.
Avionics
Power
Switch
'40.
Low-Voltage
Warning
Light
41.
Ignition
Switch
42.
Auxiliary
Mike
Jacl<
43.
Master
Switch
44
.
Phone
Jack
·
~5
.
Pdmer
>
Flight
Manual
Ed
i
tion
1 -
August
1976
Revision
3 -
Septemb
er
1978
REIMS/CESSNA
F
172
N
FUfL
QUAN
T
IT
Y
TR
ANSM
ITTER (
FILL ER
CAP
COND
ITION:
SYSTEM SHOWN
WITH
fUEL SELECTOR VALV E
IN
BOTH
POSI
TlpN
.
•
TO
ENGI
NE
·
C O DE
FUEL SUPPL
'(
VENT
MECHANICAL
LI
N
KAG
E
E
LEC
TR
IC
AL
CONNECTIO
N
FUEL
SYSTEM
fUH
OUANTI r y INDICATORS
II
]
DRAIN
VALVE
FUEL
QUAN
TI
TY
lkAN
SMITTE R
SElECTOR
VALVE
ORAIN PLUG
FUEl
Sl
f-lAINE
R FUEL
STRAINER
DRA
IN
CONTROL
TO
ENSURE
MAXIMUM
FUEL
C.~<PAC
I
TY
WHEN REFUE
li
NG
AND
k
\I
NII.OZE
CROSS·FEE
OI
NG
WH(
N
PA
R
((
0 ON A SL
OP
I
NCi
SUIIFACE PL
ACE
THE FUEL
S
EL
EC
lCl
R\/A
l
V~
lr.
f
iTHtR
lH
T OR
IUGo
iT "OSITION.
-
-0
THIIOTTL
E
CONTROL
--
--
CAriBURET
Dil
-
'----r-r-----l
-
-.....
0
--
TO
EN
G
INE
...
M
IX
T
URE
CON
TR
OL
Fi
gu
re
1-
3'
1-8
Flight
Manual
REIMS/CESSNA
F172N
Edition
1 -
August
t97G
Revision
4 -
May
1979
FUEL
SYSTEM
Fuel
is
supplied
to
tlH!
engine
frum
two
taJJ.l:s,
one
in
eacll
wing.
From
these
tanl<s,
fuel
flows
by
gravity
to
a
four-position
selector
v~lve
labeled
"RIGHT",
"BOTII",
"LEFT"
and
"OFF"
and
through
a
fuel
strainer
to
the
carburetor
.
For
additional
information
on
LubrlcatioiJ
and
Servicing,
refer
to
the
maintenance
guide
of
this
aircraft.
FUEL
QUANTITY
DATA
USABLE FUEL
TANKS
ALL
FLIGHT
UNUSABLE
FUEL
CONDITIONS
TWO
STANDARD
WING
-
81.
S
litres
152
litres
11
litres
21.5
US
Gal.
40
US
Gal.
3
US
Gal
,
each
OPTIONAL
.
TWO
LONG
RANGE
WING
102
litres
189
litres
15
litres
27
US
Gal.
50
US
Gal.
4 US
Gal.
Figure
1-4
N 0 T E
Fuel
quantity
i..nd
icators
cannot
be
relied
upon
for
accurate
readings
during
skids
1
slips,
or
unusual
attitudes.
FUEL
TANK
SUMP
QUICK-DRJ\IN
VALVES
TOTAL
FUEL
VOLUl\1E
163
lil:res
43
US
Gal.
204
liti-es
54
US
Gal.
Each
fuel
tank
sump
is
equipped
with
a
fuel
quicl
<
-cirain
valve
which
extentls
through
the
lower
surface
of
the
Witlg
just
outboard
of
the
cabin
door.
A
sampler
cup
stored
in
the
aircraft
is
used
to
examine
the
fuel
for
the
presence
of
water
and
seuiment,
A
"STRAINER
DR./\IN KNOB
11
is
located
inside
the
engine
nose
cap
access
door
and
is
connected
to
the
strainer
quicl<-draiu
valve.
After
the
!mob
has
been
released,
make
sure
that
strainer
drain
is
cl
o
sed.
1- 9
Flight
Manual
REIMS/CESSNA F172N
Edition
1 -
August
197
6
Revision
2 -
June
1977
ELECTRICP
..
L
SYSTEM
Electrical
energy
is
supplied
by
a
28-volt
1
direct-current
system
powered
by
an
engine
-
driven,
50-amp
alternator
and
a
24
-
volt,
14-amp
hour
battery
located
on
the
left
side
of
the
firewall.
Power
is
supplied
to
most
general
electrical
and
all
avionics
circuits
through
the
primary
bus
bar
and
tbe
avionics
bus
bar,
which
are
interconnected
by
an
avionics
power
switch.
The
primary
bus
is
on
anytime
the
master
switch
is
turned
on,
and
is
not
affected
by
starter
or
external
power
usage.
Both
bus
bars
are
on
anytime
the
master
and
avionics
power
switches
are
turned
on.
CAUTION
Prior
to
turning
the
master
switch
on
or
off
,
starting
the
engine
or
applying
an
external
power
source,
the
avionics
power
switch,
labeled
"AVIONICS
POWER",
should
be
turned
off
to
prevent
any
hannful
transient
voltage
from
damaging
the
avionics
equipment
.
MASTER
SWITCH
.
The
master
switch
is a
split-rocker
type
switch
labeled
11
MASTER",
and
is
11
0N
11
in
the
up
position
and
11
0FF
11
in
the
down
position.
The
right
half
of
tbe
switch,
labeled
''BAT",
controls
all
electrical
power
to
the
airplane.
The
left
half,
labeled
"AL
T",
controls
the
alternator.
Normally,
both
sides
of
the
master
switch
should
be
used
simultaneously
,
however,
the
"BAT"
side
of
the
switch
could
be
turned
11
0N
11
separately
to
check
equipment
while
on
the
ground.
1
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M;tnu:1l
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August
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172
N
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1979
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1-tl
Flight
Manual
REIMS/CESSNA
F172N
Edition
1 -
August
1976
Rev
is
ion
2 -
June
1977
To
check
or
use
avionics
equipment
or
radios
while
on
the
ground,
the
avionics
power
switch
must
also
be
turned
on.
The
11
AL
T"
side
of
the
switch,
when
placed
in
the
11
0FF
11
position
,
removes
the
alternator
from
the
electrical
system
.
With
this
switch
in
the
11
0FF
11
position,
the
entire
electrical
load
is
placed
on
the
battery.
Continued
operation
with
the
alternator
switch
in
the
11
0FF
11
position
will
reduce
ba
tt
ery
power
low
enough
to
open
the
battery
contactor,
remove
power
from
the
alternator
field,
and
prevent
alternator
restart
.
AVIONICS POWER
SWITCH
El
ectrical
power
from
the
airplane
primary
bus
to
the
avionics
bus
is
controlled
by
a
toggle
-
type
circuit
breaker-switch
labeled
11
A
VlONlCS
POWER''
.
T11e
switch
is
located
on
the
left
side
of
the
switch
and
control
panel
and
is
11
0N
11
in
the
up
position
and
11
0Ff
11
in
the
down
position.
With
the
switch
in
the
"0Ff
11
position,
no
electrical
power
will
be
applied
to
the
avionics
equipment,
regardless
of
the
position
of
the
master
switch
or
the
individual
equipment
switches.
The
avionics
power
switch
also
functions
as
a
circuit
breaker.
If
an
electrical
malfunction
should
occur
and
cause
the
circuit
breaker
to
open,
elec
-
trical
power
to
the
avionics
equipment
will
be
interrupted
and
the
switch
toggle
will
automatically
move
to
the
"OFF"
position
.
If
this
occurs,
allow
the
circuit
breaker
approximately
two
minutes
to
cool
before
pl
acing
the
toggle
in
the
11
0N
11
position
again.
If
the
circuit
breaker
opens
again,
do
not
reset
it.
The
avionics
power
switch
should
be
placed
in
the
11
0FF
11
position
prior
to
turning
the
master
switch
on
or
off,
start
-
ing
the
engine,
or
applying
an
external
power
source,
and
may
be
utilized
in
place
of
the
individua
l
avionics
equipment
switches
.
l-12
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