Take Flight G-BSCY PA-28-151 1981 Owner's manual

Pilot’s Operating Handbook
G-BSCY
Take
A V I A T I O N . c o m

Disclaimer
Take
A V I A T I O N . c o m
This pdf scan of the Pilots Operating
Handbook (POH) is for information,
and to aid flight planning only.
It should not replace reference to the
original documents, due to possible
updates since publication.
These are available for inspection at
Take Flight Aviation Limited on
request.

A0
AIRCRAFT
MODIFICATIONS
INC.
F.A.A.
APPROVED
AIRPLANE
SUPPLEMENTAL
FLIGHT
MANUAL
For
PIPER
CHEROKEE
MODEL
PA-28-151
With
LYCOMING0-320-D2A,
-D2B,
-D2C,
or
-D3G
PENGINE
INSTALLED
REGISTRATION
NUMBER
G3
fSS
C
Y
SEIA
NUMER761
So0
This
Supplemental
Flight
Manual
is
F.A.A.
approved
material
and
must
be
in
the
airplane
for
all
operations
when
Lycoming
0-320-D2A,
0-320-D2B,
0-320-D2C
or
0-320-D3G
engine
is
installed
in
accordance
with
STC
SA2969SW.
The
information contained
herein
supplements
or
supersedes
the
information
in
the
form
of
placards,
markings,
and
approved4tnanual
material.
For
limitations,
procedures
and
performance
information
not
contained
in
this
Supplemental
Flight
Manual
consult
the
basic
airplane
placards,
markings
and
approved
manual
material.
F.A.A.
AP
R
#4VED~f~
on
P.
Watson,
Chief,
Engineering
&
Manufacturing
Branch
FEDERAL
AVIATION
ADMINISTRATION
Southwest
Region
Fort
Worth,
Texas
76101
DATE:
October
21,
1981
S.T.C.
No.
SA2969SW
Page
1
of
2
pages
Waco-Madison
Cooper
Airport
*
P.O.
Box
5219
* Waco,
Texas
76708
* 817-752-8381

AIRCRAFT
MODIFICATIONS
INC.
PIPER
CHEROKEE MODEL PA-28-151
SUPPLEMENTAL
FLIGHT
MANUAL
I. GENERAL
1.
ENGINE:
Lycoming
0-320-D2A
or
Lycoming 0-320-D2B
or
/-"
Lycoming
0-320-D2C
or
Lycoming O-320-D3G
2.
PROPELLER:
Sensenich
74DM6-0-60
or
Sensenich
74DM6-0-58
II.
LIMITATIONS
1.
ENGINE
LIMITS:
Maximum
Continuous:
150
H.P.
- 2650
RPM
Takeoff
(Five
(5)
Minutes)
160 H.P. - 2700 RPM
2.
PROPELLE
LIMITS:
Static
RPM
at
maximum
throttle
setting:
Not
over
2450,
Not
under
2350
Diameter:
Maximum
= 74
inches
Minimum
=
72 inches
I' 3.
ENGINE
INSTRUMENT
TACHOMETER:
(0
MARKINGS:
Green Arc
2200
-
2650
RPM
Yellow
Arc
2650
- 2700'RPM
Red
Radial
- 2700
RPM
III.
PROCEDURES
No
Change
IV.
PERFORMANCE
The
performance
of
this
airplane
equipped
with
a
Lycoming
0-320-D2A,
0-320-D2B,
0-320-D2C,
or
0-320-D3G
engine
is
equal
to
or
better
than
the
original
F.A.A.
approved
performance.
F.A.A.
APPROVED
S.T.C.
No.
SA2969SW
DATE:
10/21/81
Page
2
of
2
pages
Waco-Madison
Cooper
Airport
- P.O.
Box
5219
* Waco,
Texas
76708
*
817-752-8381

P IPER
A
IR
AFI
C P
REPORT
vB-575
P_I
MODEL
PA-28-151
OEYIOPLII
UNI1T,
VERO
H[ACH,
RtA.
____________
AGE TITLE
A
P P
ROV
E D AEROPLANE FLIGtT
MA
NUA
L
FOR
TItE
P
I
P
ER MODEL
PA-28-151
tO-
Iff$D
PREPARED
IN
ACCORDANCE
WITH
BRITISH
CIVIL
AIRWORTHINESS
REQUIRENENYS
SERIAL
NUMBER:
28-7415001
TO
28-7615999
BY:
SheehanBY*
CHECKED
BY:
.
(__
R.
K.
Kirby
APPROVED
BY
:
>Lt-
-'
"
John
Fmat
rict:
Manager,
Flight
Test
IS
ST
DATE"::
/
/ 0
,:,.. l'n
U
"
"/ -"
I
"~i
,,L[
P
AA
l.'f.\
/
1,,:
...
7 , l ; : . . .. . . .. . .. . ... .... . .

PIPER
AIRCRAFT
CORP
REPORT
VB-575
SAMODEL PA-28-151
§EYE.IPUENT
CENTER,
YER0
BEACH,
RtA.
_____
°'his
is
th This
is tho Flighi
Manual which
forms
partoliho
3-. U CSL
r7'I
-0 a 2
C
nific
te
o
Conifc
ca
Airwo
hinss
for
aircaf
.............
..
'........
.... /
SECTION
I.
GENERAL
A.
Registration Particulars
i.
Airplane
designation:
PIPER Model
PA-28l151
2. Registration
Marks:
&
C3
GY
3.
Constructor's
Serial
Number:
.'g-76 506.
4.
Designed
and
Constructed
by:
Piper
Aircraft
Corporation
Vero
Beach,
Florida,
U.S.A.
32960
5.
F.A.A.
Certificate
of
Airworthiness
for
Export:
Number:
Date
of
Issue:
6.
Model
PA-28-151
British
Flight
Manual,
Piper
Aircraft
Corporation
Report
VB-575,
Approved
by
the
Secretary,
CiVil
Aviation Authority
on:
7.
This
airplane
shall
be
operated
in
accordance
with
the
limitations
in
Section
II
and any
additional limitations
in
the
Supplements
contained
in
Section
VI.

PIPER AIRCRAFT CORP. REPORT VB-575
X"
BEY[OP
IRT
CENTER,
YERO
BEACH,
FLA.
MODEL
PA-28-151
FAtE
2
SECTION
1.
GENERAL
(continued)
B.
Table
of
Contents
PAGE
SECTION
I.
GENERAL
A.
Registration
particulars
...........................................
I
B.
Table
of
Contents
..................................................
2
C.
Amendment
System...................................................6
D.
General
Arrangement
Drawing
.......................................
9
E.
Determination
of
Temperature
in
Relation
to
i.S.A
...............
10
F.
Definitions
.................
...................................
SECTION
II. LIMITATIONS
A.
Maximum
Weight
Limitations
.......................................
14
B.
Baggage
Loading
...................................................
14
C..
Fuel
System
....................................................
D.
Centre
of
Gravity
........................
E.
Power
Plant
Limitations
...........
..............................
.1
F.
Airspeed
Limitations
...........................
.........
......
G.
Miscellaneous
Limitations........................................ 21
SECTION
111.
EMERGENCY
PROCEDURES
A.
Introduction
.................................................
2"
B.
Engine
Fire
During
Start
.........................................
28
C.
Engine Power Loss
During
Take-off
................................
28
D.
Engine
Power
Loss
In
Flight
...
.................................
30
E.
Power-off
Landing
......
.
.......................................
.31
F. F
ire
.........
..................................................
3Z

I
PIPER
AIRCRAFT
CORP.
REPORT
VB-575
Eo
"YELEOP
UIT
CE
R,
YEIRO
BEACH,
R
A.
MODEL
rA-28-151
F AtE
3
SECTION
.GENERAL
(continued)
PAGE
G.
Lo
S
of
Oil
Pressure
............................................
It.
Loss
of
Fuel
Pressure
............................................
34
1.
High Oil
Temperature
...................................
........
35
J. Alternator
Failure
.............................................
35
K.
Engine
Roughness
................................................
36
..... .. ... 37
~~L,
Spins
.. ............
M.
Open
Door
............
....
...................................
37
SECTION
IV.
NORMAL
PROCEDURES
•A.
Preflight
.........................
..............................
39
B.
Walk-around
Inspection
..........................
..............
39
C.
Before
Starting
Engine
..........
.............................
42
D. Starting.Engine
When
Cold
......................................
E Starting
Engine
When
Hot
..................................
43
F.
Starting
Engine
When
Flooded
................................
..... 44
a.
General
Information
for
Starting
Engine
.....................
44
H.
Taxi
............... ........................................
45
I.
Before
Takeoff.
.................................................
45
j.
Normal
Take-off
(Flaps
up).......................................
K.
Crosswind Component...............................................
48
L..
Takeoff
Climb..................................................
48
M.
Normal
Climb
....................................................
.. 48
N.
Normal
Cruise...................................................48
0.
Approach
and
Lndin
...........................................
49
p
Post
Landing
.......................................................
51

PIPER
AIRCRAFT
CORP.
REPORT
VB-575
*MODEL PA-28-151
11EL~OPUEIRT
BEIER,.
VERO
BEACH,
FLA.
"n---0
PACE
4 ,
SECTION
I.
GENERAL (continued)
PAGE
Q.
Engine
Shut-down ...................................
,
.............
51
R.
Rough
Air
Flight
............
..................................
51
SECT
ION
V.
PERFORMANCE
A. General
.............
...........................
............ .52
B.
Maximum
Take-off
and
LAnding Weight
for
Altitude
and
Temperature
.......
................................
58
C.
Take-off
Procedures
and
Speeds ...................................
60
D.
Take-off
Field Lengths
.
........................................
61
E.
Net
Take-off
Flight
Path
...........................................
67
F.
En
Route
Performance
...............................................
70
G.
Landing
Procedures
and
Speeds .....................................
73
H.
Landing
Field
Lengths
...
.....................
...................
74
I.
Net
Glide
Range
..
..............................................
77
SECTION
VI.
SUPPLEMENTS
Explanation
of
the
Supplemen System
................................
79
Record
of
Supplements
.......
....
...................................
80

PIPER
AIRCRAFT
CORP.
REPORT VB-575
. DEYEtPUEPI
CEUTE!,
YEl
BEACH,
FIA.
MODET.
PA-28-151
SECTION
I-
GENERAL
(
continued
PAGE
LIST
OF
ILLUSTRATIONS
Figure
1.
General
Arrangement Drawing
................................
9
Figure
2.
Determination
of
Temperature
in
relation
to
I.S.A
........
Lo
Figure
3.
Centre
of
Gravity
Envelope
.
..............................
16
Figure
4.
Conversion
of
Wind
Velocities
............
...............
53
Figure
5.
Pitot Head
Location
...........................
;
......... 54
Figure 6. Position
Error Correction to
Obtain E.A.S. (MP) ........
55
Figure
7.
Position
Error Correction
to
Obtain
E.A.S.
(Knots)
...... 56
Figure
8.
Maximum
Take-off
and
Landing
Weight
for
Altitude
and
Temperature
.
................................
59
Figure
9.
Take-off Run Required
....................................
63
Figure
10.
Take-off
Distance
Required
................................
66
Figure
II°:
Net
Take-off
Flight
Path
...........
.....................
69
"
Figure
12.
En
Route
Perfor'mance
Ceiling.
and
Cross
Rate
of
Climb
....
.72
Figure
13.
Landing
Distance R~quired
.......
..........................
76
Figure
14.
Net.
Glide
Range ............................................
78

PIPER
AIRCRAFT
CORP575
EYELOPMET
CENTER,
VEtO
PEACH,
f
LA.
PtE
6
SECTION I.
GENERAL,
(continued)
C.
Amendment
System
I I
The
current
amendment
state
of
this
manual
is
noted
on
the
amendment
record
sheet
(Page
7).
Amendmentsto
the
text
are
indicated
by
a
vertical
line
in
the
tiargin
together
with
the.
revision
number.
The
revision
number
and
the
revision
date
are
given
in
the
margin
of
the
revised
page.
This
revision
number
supersedes
the
original
issue and all
previous
revisions
and
contains
the
latest
approved
information
pertinent
to
the
airplahe.
Amendments
to
supplements
published by
another
ogani-
zation
other
than
Piper.
Aircraft Corporation,
and
included
in
this
manual
without
the
consent
of
Piper
Aircraft
Cor-
poration,
are
the
responsibility
of
that
organization.
These
amendments
will
not
necessarily
be
reflected
on
-
the
amendment record
sheet
of
Page
80
of
Section VI.
-A
record
of
approved
supplements
and
their
embodiment
into
the
manual
is
provided
for
on
Page 80
of
Section
VI.

------ [
PER
AIRCRAFT
G REPORTVB-575
-1
E
M,
MODEL
PA-228-151
UNIED
STATES
F.A.A.
'N
AMENDmENT
RECORD
SHEET
REVISION
DATE
OF
REVISED
APPROVAL
PAGES
NO.
REVISION.
BY
DATE
(CAA)
REVISION
TITLE
AFFECTED
DAY
110.
YR.
DAY
140
YR
125
3
74
R.F.
Deleted
Reference
to
22
& 23
Aerobatic
Manoeuvres
cQaalified
Battery
Capacity
36
/
5
4
Deleted
Propeller
Check
45
Changed
Example
&
Climb
70
Q
Speed
at
Light
Weight
CAJ
.O
*1
A:Redrawn 72
"
'
-
-
........
.....
..
...
........
...................
.
......
a 5 '
2
L5
10
74
R.K. Deleted
Reference
to
Aero-
7
[
7/
batic
Manoeuvres
20
Specified
Battery
Capacity
36
1A
.A
fl-
AFPROV
1)D
Corrected
T.O.
Distance
63,
66
Charts
61, 64
3 1 8
75
L.11;
Add
new
wing-flops
extended
19, 20,
21,
speed
and
serial
number
26,
49
-
T
I
P
-
,-75
effectivity.
'A
-'A
'-0
-I
AP"
" '
4
1 M5
6 p
Revised
Applicability
up
tc
Title
& 7
Serial
No.
28-7615999
..
j/ ti
I I

PIPER
AIRCRAFT
CORP.
REPORTVB-575
MODEL PA-28-151
c,.,l
DEYELO
ENT
CETE,
VE1O
BEACH,
FA.
PACE
8
C.A.A. AMENDMENT RECORD SHEET
REVISION DATE OF
REVISED APPROVAL
PAGES
NO.
REVISION
BY
DATE (CAA)
REVISION
TITLE
AFFECTED.
AY
MO.
JYR.
DAY
MO.
YR.
~/

I________
R
IER
A
IR
C
RAFTI
CO0R
P
REPORT
VB-575
,EYELOPUEIT
CERTER,
VERO
BEACH,
FLA.
SECTION
I.
GENERAL,
(continued)
D.
General Arrangement
Drawing
(not
to
scale)
vp
FIGURE
1.
5' 3"
_J:P3
9.6"
''-
rM"
GIOVID
0

MODEL
PA-28-
151
PAGE
IC0
,*7-
-....
iso'
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J
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I.
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~~~ ~ ~ I M-"
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... J-TUR :1

PIPER
AIRCRAFT
CO
RP
REPORTVB-575
E
[LtOPtE
T
CE
lER,
VERO
BEACH,
FLA.
SECTION
I.
GENERAL,
(continued)
F. Definitions
1.
AIR
TEAPERATURE
The temperature
of
the
free
air
near
to,
but
not
In-
fluenced
by
the
aeroplane.
This
temperature
may be
a
reported, forecast
or,
when
permitted
by
the
Air
Navigation
Regulations,
a
declared
temperature
derived
in
accordance
with
an
approved system,
2.
ALTITUDE
The altitude
shown
on
the
charts
is
pressure
altitude
which
is
the
expression
of
atmospheric
pressure
in
terms
of
altitude
above
mean
sea
level
according
to
the
inter-relation
of
these
factors
in
the
International
Standard
Atmosphere
(I.S.A.).
This
May
be
obtained
by
setting
the
sub-scale
of an
accurate
pressure
type
altimeter
at 1,013
millibars
(29.92
inches
or
760
millimeters
of
mercury).
3.
I.S.A.
International Standard
Atmosphere.
See
Page
10
for
temperature
variation
versus altitude.
4.
GRADIENT
OF
CLIIB
The
tangent
of
the
angle
of
climb
expressed
as
a
percen-
tage
i.e.,
change
in
height
x
100
horizontal distance
traveled

PIPER
AIRCRAFT
CO
RP.
REPORT
VB-575
EJ,,,E A
MODEL PA-28-151
SECTION
1.
GENERAL,
(continued)
5.
GROSS
PERFORUANCE
The
average
performance
which
a
fleet
of
aeroplanes
can
be
expected
to
achieve
or
exceed
if
satisfactorily
main-
tained
and
flown
in
accordance
with
the
associated tech-
niques
described
in
the
manual.
6.
NET PERFORMANCE
The
gross
performance modified
in
the
manner
prescribed
in
the
relevant
requirement
to
make
appropriate
allowance
for
those
variations
from
the
Gross
Performance
which
are
not
dealt
with
in
Operational
Regulations.
7. HARD
RUNWAY
A
surface
such
as
concrete
or tarmac.
8. HEIGHT
The
lowest
distance between
the
lowest
part
of
the
aero-
plane
and
the'relevant
datum.
9.
WEIGHT
The total
weight
of
the
aeroplane,
including
fuel,
oil,
equipment,
crew
and
payload.
10.
A.S.I.R.
The
uncorrected
Air
Speed
Indicator Reading.

RPPIPER
AIRCRAFT
CORP
VB-575
c~a
ETE1DPEB1
RTU
?E
eEAR,
IA.
MODEL PA-28-151
ODEVELOPMENT
CETER,
Y[R0
DFAC_,
RLA.
I uf~rAti[
133
SECTION
I.
GENERAL,
(continued)
IL.
I.A.S.
The
Indicated Air
Speed,
which is
the
A.SI.R.
corrected
for
instrument
error
only.
12.
E.A.S.
The.Equivalent
Air
Speed, which
is
I.A.S.
correjted
for
position
and
compressibility
errors.
13.
T.A.S.
The
True
Air
Speed
of the
aeroplance relative
to
the
undisturbed
air,
which
is
the
E.A.S.
corrected
for
altitude
and
temperature.
14.
TAKE-OFF
SAFETY
SPEED
The
minimum
speed
at
which,
following sudden
and.
complete
failure
of the
engine
in
the
take-off
configuration,
adequate
control
exists
to
establish
a
glide
di
a
safe
margin
above
the
stall.
15.
MANOEUVRING
SPEED
The
maximum
speed
for full
application
of
primary
flight
controls.
16.
V___O
The
Normal
Operating
Limit
Speed
which
is the
maximum
cruising
speed.

AA[IfCO
.
RL'LOWIVB-575
FACE
__
_
SECTION
II.
LIMITAT
IONS
TIE
AEROPLANE
MUST
BE
OPERATED
SO
TMAT
TiIl
LIMITATIt)NS
ANI1
INSTRUCTIONS
IN
TIlIS
SECTION
ARE OBSERVED.
A.
The
following
weights
given
are
maximum
liitaotious.
1.
The
eximum
Take-off
Weight
is
2325
potinds.
2.
The
Maximum
Landing
Weight
is
2325
pounds.
3.
The
11aximum
Weight
for
the
manoeuvres
listed
on
l'ag 27
is
1950
pounds..
4.
The
aeroplane
is
not
structurally
limited
by
a
zero
Id I
weight
limit.
B.
Baggage
LoadiI&
*
The
maximum
baggage
capacity
is
200
pounds.
For
acrohat
In
operation,
baggage
and
aft
passengers
are
not
allowed.
C.
Fuel
System
I.
There
are
no
fuel
loading
limitationS.
However,
it is
recommended
that
the,
fuel
load
be
symmetrical
to
provide
better'rol-.
control.
2.
The
word
."gallob"
as
used
throughout
this
report
,.ans
U.S.
gal.lon
unless
otherwise
stated.
3.
The
unusable
fuel
in
this
aircraft
has
been
determined
as
1.0
gallon
in
each
wing
in
critical
flight
attitudes.
(1.0
gallon
is
the
total
per
side).
Items
marked
*
must
either
be
placarded
or
the
applicable
i&-
strument
colour
marked.
0
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iA-Th-
Il
SECTION
11.
LIIATIONS
(continued)
4.
The
usable fuel
in
this
aircraft
has
becl,
deltc-.lil.d
is
48.0
gallons
in
critical
flight
attitllde'.
(481.0
gallons
it
the
total
per
aeroplane).
5;
The
fuel
selector
may
be
ie
either
"Right'':ilt'
o'r
"Left
Tank"
position
for
any
flight.
coiiif.igiirat
ioit.
Use
fullest
tank
for
take-off
.and t;i]
inni
6.
The
electric
fuel
pump
should
be.''ON"
for
tak(a-
iI
landing
and
when
the
engine
driven
pump
iS
i li'otNI[
Ivy.
It is
a
good
procedure
to
use
the
e[ectric
u
I
It pnilp
when
switching
tanks.
D.
Centre-of
Gravity
I
The
aircraft
loading
is
to
be
listri
tl ed
so
Ilioo uit!"
centre
of
gravity
ties
between
the
lh.
lts
of'
83.0
i
aft
of
the
datum
at
1950
pounds,
87.0
iinches
AF.
ot.
tlic
datum
a.t
2325
pounds
bnd
an
oft
1iisi1
of
93.0
fm-lt-s.
.
aft
of
the
datum
at
2325
pounds
and
below.
The
c'.
1 .. limitations
have a straight
line variation betwecn
[ie
* points
given.
2.
The
load
is
to
be
distributed
so
that
the
centre-of-jgravity
for
th
nanoeuvres.
listed
on
Pg.
22
ties
between
t.i{
limit
l;
of
83.0
inches
aft
of
tile
datum
at
1950
pounds
knd,
an
a
•
limit
of
86.5
inches
aft
of. the
d;nlnu,
at
1950
pounds
.n?
below.
r
3.
'The
datum
is
78.4
inches,
ahead
of
tiwr
wing
leidin);
ri
,edg
at
tile
inboard
inlcrsection
of
lite
siVl
igiht
aie,1
Iapr.,I
sect.011