Piper Aircraft Corporation Seneca II PA-34-200T Owner's manual
FAA
APPROVED IN N
ORMAL
CATEGORY BASED
ON
FAR
23
AND
FAA
PART
21
. SUBPART J.
THIS
HANDBOOK
INCLUDES
THE
MATERIAL
REQUIRED
TO
BE FUR
NI
SHED TO
THE
Pl LOT
BY
FAR
23
AND
FAR
PART
21
. SUBPART J AND CONSTIT
UTE
S
THE
APPROVED
Al
RP
LANE
FUG
HT
MANUAL
ANO
MUST
BE
CARRIED
IN
THE
AIRPLANE
AT
ALL
TIME
S.
Al
RPLANE SER
IA
L NQ
__
J_
1±
_-
_7
_B
_7_
0_0_
6_
6
__
_
PILOT'S
OPERATING
HANDBOOK
1999
Kg.
SENECA
II
PA-34
-
200T
REPORT. VB-
1140
FAAAPPROVEDBY
:
LJJ
~
WARD EVANS
D.O.A. NO. S0-1
PIPER AJRCRAFT CORPORATI
ON
VERO BEACH,
FLORIDA
AIRPLANE
REGI
STRATION
NO. 9 H
-RE
B ¥ DATE0
0F
APPROVAL: SEP
TEMB
ER
12
. i
980
E
XTREME
CARE
M U
ST
BE
EXERCISED
TO
Llt\TIT 1
HE
US[
OF
THIS
HAi\DBOOK
ro
APPLICABLE Al
RCRA
F
T_
1 HIS HAt
DHOOK
I!::>
\ALI
D
FOR
LSE
\\'ITH
THE
AIRPLA
-E
IDENTIFIED
0 '
THE
F
>\CE
OF
THE
TITLE
PA.GE_ ll
BSEQUENT
RE\'
I
10\l
.-SL'
PPLIED
Br
PIPER
AIRCRAFT
CORPORATION
Ml
l
ST
BE
PROPERLY
11\SERTED
REPORT:
VB-1140
Published
by
PUBUCATIO}\S
DEPARTMEJ\'T
Piper Aircraft Corporati
on
j,
,u
e
d:
S~pt
e
m
bt'r
I~
-
I
l)
~
(l
APPLICABILITY
Application
of
this
handbook
is limited
to
the
Piper
PA-34-200T model
airplane
having a gross weight
of 4407
pounds
(1999 Kg.)
and
with serial
numbers
34-7770001
and
up_
This
handbo
ok
cannot
be
used
for
operational
purposes
unless kept in a
current
status
.
REVISIONS
The
information
compiled in
the
Pilot's
Operating
Handbook
will be.
kept
current
by
revisions
distributed
to
the
ailplane owners.
Revision material will
consist
of
information
necessary
to
update
the
text
of
the
present
handbook
and
/o
r
to
add
information
to cover added airplane
equi
pment.
I.
Revisi
ons
Revisions will
be
distributed whenever necessary as
complete
page replacements
or
additions and shall
be
inserted
into
the
handbook
in
accordance with
the
instructions
given below:
l.
Revision pages will replace only pages
with
the
same page
number.
2.
Insert
all additional pages
in
proper
numerical
order
within each section.
3. Page
numbers
followed
by
a small
letter
shall
be
inserted
in
direct sequence
with
the same
common
numbered
page.
IL
I
dentifi
cation
of
Revised Material
Revised
text
and illustrations shall
be
indicated
by
a black vertical linealong the outside margin
of
the
page,
opposite
re
vised,
added
or
deleted
material. A line along the outside margin
of
the
page
opposite
the
page
number
will indicate
that
an
entire page was
added.
Black lines will indicate only
current
revisions
with
changes
and
additions
to
or
de
l
etions
of
existing
text
and
illustrations. Changes
in
capitalization, spelling,
punctuation
or
the physical location
of
material
on
a page
will
not
be
i
dentified
by
symbols.
ORIGINAL PAGES ISSUED
The
original pages issued
for
this
handbook
prior
to
revision are given below:
T~tle.
ii
through'·
J-1
thr
ough 1-14.
~-
I
rhrough 2-10.
3-1
through J-17.
4-
1
through4-26
.
5-1
through
.5->J
.
h-1
th
r
ou
gh
6-M.
7
-1
through --42. 8
-1
through
~
-l
fl.
9-1through9-64
.
IU
-1 through
10-2
REPORT:
VB-'140
iii
PILOT'S OPERATING HANDBOOK LOG
OF
REVISIONS
Current Revisions to the PA-34-200T Seneca II Pilot's
Operat
ing
Handbook
,
REPORT
: VB-1140 issued
September
12.
1980
.
Revision Revised
FAA
Approval
Number
and Pages Description
of
Revision Signature and
Code Date
'
4-i~
llev
-:
<;
.-:;,\
I.Jw
Ao
~'1
+-tv
Ol
I
~
\Joe..
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-11
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ll.;
0 -r 1A.. ·l,
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1:
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I
I
I
!
:1
I
~EPORT:
VB-114i>
SECTION
1
SECTION
2
SECTION 3
SECTION
4
SECTION
5
SECTION 6
SECTION
7
SECTION
8
SECTtON
9
SECTION
10
TA'BLE OF CONTENTS
GENERAL
LIMITATIONS
EMERGENCY PROCEDURES
NORMAL
PROCEDURES
PERFORMANCE
WEIGHT
AND
BALANCE
DESCRIPT.
ION
AND
OPE.RATION
OF
THE
AIRPLANE AND ITS
SYSTEMS
AIRPLANE
HANDLING
, SERVI
CING
AND
MAINTENANCE
SUPPLEMENTS
SAFETY
TIPS
REPORT:
VB·ll40
"
Paragraph
No.
TABLE
OF
CONTENTS
S.ECTIO~
I
GENERAL
Page
No.
I. I intr
oduction...
.
..
. .
......
......
. . .
.....
. .
....
.
..............
.
....
......
..
.
..
. . .
J-1
1.3 Engines
...
.......
.
...
. .
....
......
..
.......
....
.....
. .
.....
........
.
............
1-3
I 5 Prope
ll
er
s . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3
1.
7
Fuel
...............•
.
..
..
....
.
.. ..
...
. .
....
...
.
....
.
..
..
....................
...
1
-4
I.9
Qj
l . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . •. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4
I.
II
Maximum
\Ve
ights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4
1.
13
Ba
gg
age
Space.
.
......
. .
....
......
....
. .
...
.......
.....
..
...
...........
.
..
.
..
.
..
1-5
I
15
Specific Loadings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-5
1.
17
Symbo
ls.
Abbreviation
s
and
Terminolo
gy
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
-7
I.
19
Conversion
Factors.
.
......
. . . .
......
. .
..
.
..
...........
. .
........
.
..
......
...
.
....
1-1
[
REPORT:
VB-1140
l-i
PIPER
AIRCRAFI
CORPORATION
PA-3+200T,
SENECA
II
1.3 ENGINES
(a)
Number
of
Engines
(b)
Engine
Manufacturer
(c) Engine
Mo
de
l •
lu
mber
(1)
Left
(2)
Right
(d)
Rated
Borsepower
(1) Sea level
(2)
12,
000
ft.
(e)
Rated
Speed
(rpm)
(0
Bore
..(-in
ches)
(g)
Stroke
(in
che
s)
(h)
Displacement
(cu
b
ic
inches)
(i)
Compressi
on
Ratio
(j)
Engine
Type
1. S
PROPELLERS
(a)
Number
of
Propellers
(b) Propeller
Manufacturer
Hartzell
(
l)
Pr
opelleT
Hub
and
Blade Models
.
a.
Left
Right
b. Left
Right
When propeller deici
ng
boots
are installed:
c. Le
ft
Right
d.
Left
Right
(2)
Number
of
Bl
ades
McCaul
ey
(l)
Propeller
Hub
and Blade Models
a.
Left
b.
Right
SECTION l
GENERAL
')
Continental
TSI0-360E
or
TSI0-360EB
LTSI0-360E
or
LTSIG-
360EB
200
215
2575
4.438
3.875
360
7.5: I
Six Cylinder, Direct Drive,
Horizontally Opposed, Air Cooled
BHC-C2YF-2CKF
/FC8459-8R
BHC-C2YF-2CLKF/FJC8459-8R
BHC-C2YF-2CKUF/FC8459-8R
BHC-C2YF-2CLKUF{FJC8459-8R
BHC-C2YF-2CKF/FC8459B-
8R
BHC-C2YF-2CLKF/FJC8459B-8R
BHC-C2YF-2CK
UF
/FC8459B-8R
B_HC-C2YF-2CLKUF
/F
JC8459B-8R
2
3AF34C502
/80HA-4
3AF34C503
/LSOHA-4
When
propeller
deicing
boots
are
jnstal
led :
Same
as above. 3
(2)
Number
of
Blades
(c)
Propeller
Diameter
(1)
M
aximum
(2)
Minimum
(d)
Propeller
Type
ISSUED:
SEPTEMBER
12,
1980
76
75
Constant
Speed, Hydraulically
Actuated,
Full
Feathering
REPORT:
VB-1140
1-3
SECTION 1
GENERAL
1.7
FUEL
(a)
Fuel
Capacity
(U.S. gal)
(total)
(I)
Without
op
ti
onal
tanks
(2) With
optional
tanks
(b)
Usable
Fuel
(U.
S.
gal)
(total)
(I} WithoLt optional
tanks
(2) With
o~tional
tanks
(C)
Fuel
(II
Minim Jm Grade
(2) Altcrn.=1e Fuelf,
1.9 OIL
(a) Oil
Ca
pa
cit~
(U.S. quarts) (p
er
engine)
(b)
Oil Specific<:
tion
(c) Oil Viscosit:
per
Average Ambiem
Temp
.
{l)
Below40°F
(2)
Above
~0°
F
PIPER
AIRCRAFT
CORPORATION
PA-34-200T. SENECA
II
98
128
93
123
JOO
Green
or
IOOLL
Blue
Av1allon
Grade
Refer
to
latest revision
of
Continental
Service Bulletin
"Fuel
and Oil Grades"
8
Refer
to
latest issue
of
Continental
Service Bulletin
"Fuel
and Oil Grades"
A\'iation Grade
1065
1100
S.A.E
.N
o.
30
50
When o
pe
raung
temperatures
overlap
indicated
nnges,
use the lighter grade
of
oil. Multi-viscosity
oils m
ee
ting
Teledyne
Continental
Motors·
Specifkation
MHS-24A are
approved.
1.11 MAXIMUM WEIGHTS
(a)
Maximum
Takeoff
Weight (lbs)/
(Kg
.)
(b)
Maximum
Landing
Weight (lbs)/(Kg.)
(c)
Maximum
Zero
Fuel
Weight
(lbs)/
(Kg.)
-
Standard
(d) Maxirnum
V.
eights in Baggage
Compartments
(lbs)I (Kg.)
REPORT:
VB-1140
14
FORWARD
1
00
/45
4407/1999
4342
/
1970
4000
/
1814
AFT
100
/45
rs
'llED:
SEPTEMBER
12. 1980
SECTION l
GENERAL
n n
k-13
_·6
.....
1-
··
--,........,,,
PIPER
AIRCRAFr
CORPORATION
PA-34-200T, SENECA II
Wing Area (sq. f
t.
) '208.7
Min.
Turning
Radius
(ft
.) 33.2
(from
pivot
point
to
wingtip)
n
~
I
i------------38
'
lG
.
81"----
--
-
---
--1
---
12'
5.-4
"
------i
~EPORT:
VB-1140
.-2
-......,,~
6
'
4 "
DIAMETER
======~~~~8
::!E~~~~~~===~~:::==J1'.::
0
fmHt0m
"-4r/
..
L-
rr
.
er--1
---------28
'
7.47"---
---
---t
.._.--11'
U"--
STATIC
GROUND
LIME
THREE VIEW
Figure l · I
-1
,.
)"
"
ISSUED:
SEPTEMBER
12, 1980
PIPER
AIRCRAFT
CORPORATION
PA-34-200T, SENECA
11
l
.l
INTRODUCTION
SECTION 1
GENERAL
SECTION
l
GENERAL
This
Pilot's
Operating
Handbook
is
designed
for
maximum
utilization as an
operating
guide
for
the
pilot
It
includes
the
material
required
to
be furnished
to
the
pilot
by
FAR
23
and
FAR
Part
21
Subpan
J.
1t
aJso
contains
supplemental
data
supplied
by
the
airplane
manufacturer.
This
handbook
is
not
designed as a
subsiitute
for adequa1e and
competent
flight
instruction
,
knowledge
of
current
airworthiness directives, applicable federal
air
regulations
or
advisocy circulars.
It
is
not
intended
co
be
a
guide
for
basic flight
instruction
or
a training
manual
and
should
not
be
used
for
operational
purposes
unless
ke
pt
in
a cu.rr
ent
status.
As.surance
that
the
airplane is
in
an
airworthy
condition is the responsibility
of
the
owner
.
The
pilot
in
command
is responsible
for
determining
that
the
airplane is safe
for
flight.
The
pilot
is also responsible
for
remaining 1Nithin
the
operating limitations as
outlined
by
instrument
markings, placards, and
this
handbook.
Although
the
arrangement
of
this
handbook
is
inte
nded
to
increase
its
in-flight capabilities,
it
should
not
be
used solely
as
an
occasional
operating reference.
The
pilot
should
study
the
entire
handbook
to
familiarize himself
with
the
limitations,
performance,
procedures
and
operational handling characteristics
of
the airplane before flight.
The
han
dbook
has
been
divided
into
numbered (arabic) sections each provided
with
a "finger-tip'"
tab
divider
for
quick
reference.
The
limitations
and
emergency
procedures have been placed
ahead
of
the
normal procedures,
performance
and
other
sections
to
provide easier access
to
infonnation
that
may
be
required
in
flight.
The
"Emergency
Procedures" Section has been furnished
with
a red tab divider
to
present
an
instant
reference
to
the
section. Provisions for expansion
of
the
handbook
have been made
by
the deliberate omission of certain
paragraph
numbers.
figure numbers, item numbers and pages
noted
as
being
intentionally
left
blank.
lSS
U
ED
: SEPTEl\"IBER 12, 1980 REPORT: VB-1140
1-1
SECTION 1
GENERAL
EPORT
: VB-1140
6
PIPER
AIRCRAFT
CORPORATION
PA-3+200T, SENECA II
THlS
PAGE
lNTENTIONALLY
LEFT
BLANK
JSSUED:
SEPTEMBER
12. 1980
PIPER
AIRCRAFT
CORPORATION
PA-34-200T.
SENECA
ti
1.13
BAGGAGE
SPACE
(a)
Compartment
Volume
(cubic feet)
(b)
Entry
Width
(inches)
(c)
Entry
Height
(inches~
I.IS
SPECIFIC
LOADINGS
(a) Wing
Loading
Obs
per
sq
ft)
(b)
Power
Loading
(lbs
per
hp)
( I) Sea level
(2) 12,000
ft.
ISSUED:
SEPTEMBER
12
. 1980
FORWARD
15.3
24
21
SECTION I
GENERAL
AFT
17
.3
21.1
I l.0
10.2
REPORT: VB-1140
1-5
SECTION 1
GENERAL
Vy
(bl
Mete
o
rolo
gi
cal
Terminology
ISA
OAT
Indic
ated
Pressure
Al
titude
Pressure
Altitude
Statio
n
Pressure
Wind
(c 1
Power
Terminology
Takeoff
Powe
r
Maximum
Con
t
inuou
s
Power
.
EPORT:
VB-l140
·8
PIPE
R
AIRCRAFT
CORPORATION
PA-34-
200T,
S
ENECA
II
Stalling
Speed
or
the mm1mum
steady
fligh1
speed
at
whkh
th~
airplane
is
con
tro!lable.
St
aUing
Speed
or
rhe
mrnirnum
steady
flight
speed
a.t
which
the
airplane
is
controllable
in
the
landing
configu
r
ation.
Inte
nt
ional
One
Engine In
operative
Speed
is a
minimum
speed
selected
by
the
manufacturer
for
intentionally
rendering
one
engine
inoperative
in
flight.
Best
Angle-
of-Climb
Speed
1s
the
airspee
d
which
delivers
th~
greatest
gain
of
altitude
in the
shortest
possible
ho
rizontal
distance.
Bes
t
Rate
-
of
-
Climb
Speed
is
the
airspeed
which
delivers
the
greatest
gain in alt
irude
in
the
shortest
possible
time
.
internat
i
onal
Standard
Atmosp
here
in whid1:
The
air is a
dry
pe
r
fect
gas;
The
temperature
at
sea
level is
15°
Celsius
(59°
Fahrenheit)
;
The
pressure
at
5ea
level
is
29.92
mches
hg.
(lOJ3
mb);
The
tempe
r
atur
e
gradiem
from
sea leveJ
lo
the
altitude
ac
which
che
temperatur
e i
-56
.
5°
C
(-69.7°F)
is
-0.00198"C
(-
0.003566°
F)
per
foot
and
z
ero
above
chat
altitude
.
Outside
Air
Temperature
is
the
free
air
static
temperarurc,
obtained
either
from
mtlighl
t
empera
t
ure
indicauons
or
ground
meteoro
logical
sources.
adjusted
for
instrument
e
rror
and
compressibility
effects
.
The
number
actuaUy
read
from
an
allimeter
when
the
barometric
subscale
has
been
set
to
29.
92
inches
of
mercury
(I
013
millibars).
Altitude
measured
from
standa
rd
sea
-level
pressure
t2Q.92
in.
Hg)
by a
pressure
or
barometric
altimeter.
It
is
Ihe
indicated
pressu
re
al
r
irud~
corrected
for
position
and
instrument
error. 1n
this
handbook,
altimeter
instrument
errors
are
assumed
to
be
zero
.
Actual
atmospheric
pressure
at
field
elevation
.
The
wind
velocities
recorded
as variables
on
lhe
charts
of
this
handbook
are
to
be
unders
t
ood
as
the
headwind
or
lailwmd
components
of
the
reported
wind
s.
Maximum
power
permiss
i
ble
for
takeoff.
Maximum
powe
r
permissible
continuously
during
flight.
J
SSl
l
EO:
SEPTEMBER
12, 1980
PI
P
ER
AIRCRAFT
C
ORPOR
ATION
PA-34-2
00
T,
SENE
CA
D
SECTION
J
GENERAL
1.17 SYMB
OLS
. ABBRE
VIATI
O
NS
AND TERMINOLOGY
The
followmg
defmitions
are
of
symbols.
abbreviations and terminology used
throughout
1..he
handbook
and
those which
may
be
of
added
operational
significance
to
th
e
pilot
(a'
General Airspeed
Tenninology
and
Symbols
CAS
KCAS
GS
IAS
K.IAS
M
TAS
ISSUED:
SE
P
TEM
BER
12,
1980
Calibraced Auspeed means
th
e
indicated
speed
of
an aircraft.
corrected
for
position
and
instrument
error. Cali
brated
airspeed
is
equal
m
true
.airspeed in
standard
at
mosphere
at
sea level.
Calibrated Airspeed expressed in
''Knots."
Ground
Speed is
the
speed
of
an airplane relative
to
the ground.
Indicated
Airspeed is
the
speed
of
an aircraft as
shown
on
the
airspeed mclicat
or
when
corrected
for
instrument
error.
IAS values
published in t
hi
s
lrnndbook
assume
zero
instrument
error
.
Indicated
Airspeed expressed in ''
Knots
.''
Mach
Number
is
the
r
atio
of
true
airspeed
co
the
speed
of
sound.
True
Airspeed is
the
airspeed
of
an airplane relative to undisturbed
air which is the CAS
corrected
for al
ti
tude,
temperature
and
compressibility.
Maneuvering Speed is
Lhe
maximum
speed
at
wh.ich application
of
full available
aerodynamic
control
will
not
overstress the airplane.
Maximum
Flap
Extended
Speed is
the
highest
speed
permissible
wi
th
wing flaps in a prescribed
extended
position.
Maximum Landing
Gear
Extended
Speed is the
maximum
speed
at
which an aircraft can
be
safely flown
with
the landing
gear
extended
.
Maximum
Landing
Gear
Operating
Speed
is t
he
maximum
speed
at
which
the
landing gear can be safely
extended
or
retracted
.
Air
minimum
control
speed
1s
the
minimum
llight
speed
at
which
the airplane is
controllable
wit11
a bank
of
not
more
than
5 degrees
when
one
engine
suddenly
becomes
inoperative and
the
remaining
engine is
operating
at
takeoff
power
.
Never Exceed
Speed
or
Mach
Number
1s
the
speed
limit t
hat
may
nor
be
ex
c
eeded
at
any time.
Maximum
Stru
c
tural
Cruising Speed is
th
e speed
that
shou
ld
not
be
exL
·eeded
except
in
smooth
.air
and
then
only
with
caution
.
REPORT:
VB
·l140
1-7
SECTlO 1
GENERAL
Center
of
Gniviry
(C.G.)
C.G.
Ann
CG
Limits
Usable
Fuel
Unusab
le
Fuel
Standard
Empty
Weight
Basic
Empty
Weight
Payload
Useful
Load
Maximum
Ramp
Weighc
Max.unum
Takeoff
Weight
Maximum
Landing
Weight
Maximum Zero Fuel
Weight
REPORT: V
B-
JJ40
l-10
PIPER
AIRCRAFT
CORPORATION
PA-34-200T.
SENECA
Il
The
point
at
which
an
airplane
would
balance
1f
suspended.
I
rs
distance from
the
reference
datum is
found
by
dividing the
total
moment
by
the rot
al
weight
of
the
airplane
The
arm
obtained
by
adding
rhe
auplane's
individual
moments
and
dividing
rhe
sum
by
the
total
weight.
The
extreme
center
of
gravity locacjon wnhin which the airplane
must
be
operated
al
a given weighc.
Fuel
available
for
flight
planning.
Fuel
remaining
after
a
runout
test
has
been
completed
m
accordance
with
governmental
regulations
.
Weight
of
a
standard
airplane
including
unusable
fuel. full
operating
fluids and
full
oil.
Standard
empty
weight
plus
optional
equipment.
Weighr
of
occupan
ts. ca
rgo
and
baggage.
Difference bet
ween
takeoff
weighL
or
ramp
weight
if
applicable
and basic
empty
weight
.
Maximum weight
approved
for
ground
maneuver
.
tll
mcludes
weight
of
start,
taxi
and
run
up fuel.)
Maximum weight
approved
for
rhe
start
of
the
takeoff
run
.
Maxi
mum
weight
approved
for
the
landing
t
ouchdown.
~aximum
weight exclusive
of
usable fuel.
ISSl
l
ED:
SEPTEMBER
11, 1980
PIPER AIRCRAFT CORPORATION
PA-
34
-200T. SENECA
ll
Maximum
Climb
Power
Maximum
Cruise P
ower
(
d)
Engine I
nstru
me
nts
EG
T Gauge
Maximum
power
pe
rm
issible
during
climb
.
Maximum
power
permiss
ib
le during cnuse.
Exhaust Gas
Temperanire
Gauge
SECTIO~
I
GENERAL
(e)
Airplane
Performan
ce
and
Fli
ght
Plannjng
Terminolog
y
Climb
Gradient
Demonstrated
Crosswind
Velocity
{DE
MO
. X-
WIND)
Accelerate-Stop Di
stance
\1EA
Route
S
egment
The
dem
o
nstrated
ratio
of
the
change in
height
dun
ng
a
po
r
tion
of
a climb.
to
th
e
horizontal
distance traversed in the same time
interval.
The
demonstrated
crosswind
velocity is the
velocity
of
the
c
ro
sswind c
omponent
for which
adequate
control
of
the
airplane
during
takeo
ff
and
land
in
g was
act
ual
ly
demonstrated
during
certification
tests.
Th
e distance required
to
accelerate
an
airplane to a specified"speed
and,
assuming failure
of
an
engine
at
the
instant
chat speed is
attained. to bring
th
e airplane
to
a st
op
.
Minimum
en
route
IFR
altit
ude.
A
part
of
a route. Ea
ch
end
01
that
part
LS
identified
by
(
l)
a
geographical
location
;
or
(2) a
point
at
wh.ich a
definite
radio fix
can
be established.
(fl
Weight and Balance Terminology
Refe
rence
Damm
St:ltion
Arm
Mom1:nt
ISS'
UED:
SEPTEl\'1BER
12,
1980
An
imaginary vertical
plane
from
which
all
horizontal
distances
axe
measured
for
balance
purposes.
A
location
along the airplane fusela
ge
usually given in
tenns
of
distance
from
the
reference
datum
.
The
ho
ri
zon
tal distance from the reference
datum
to
the
cen
t
er
of
gravity
(C.G
.)
of
an
it
em
.
The
product
of
the weight
of
an
item multiplied
by
its arm.
(Mom~n
t
divjded by a cot1stant
is.
used
to
simplify
balanc~
i:
alcu!Jtion
s by
reducing
t
he
number
of
digits.)
REPORT:
VB-1140
l-9
PIPER
AIRCRAFT
CORPORATION
PA-34-200T. SENECA
ll
l.19
CONVERSION FACTI>RS
~ULTIPLY
BY
acres
0.4047
43560
0.0015625
atmospheres
(atm)
76
29.92
1.0133
L033
14.70
2116
bars
(bar)
0.98692
14.503768
British
Thennal
Unit
0.2519958
(BTU)
centimete
rs
(cm)
0.3937
0.032808
centimeters
of
0.01316
mercury
at
O"C
0.3937
(cm Hg)
0.1934
27.85
135.95
centimeters
per
0.032808
second
(cm
/sec.) 1.9685
O.QTJ37
cubic
centimeters
0.03381
(cm
1)
0.06102
3.531 x
10·
5
0.001
2.642 x ]
0-4
cubic feet
(cu.ft.)
28317
0.028317
1728
0.037037
7.481
28.32
cubic
feet
per
minute
0.472
(cu.
ft./min.)
0.028317
ISSUED:
SEPTEMBER
12,
J98(1
TO
OBTAIN
ha
sq.
ft.
sq. mi.
cm
Hg
in.Hg
bar
kg/cm
2
Jb./sq.
in.
Ib./sq.
ft.
atm.
lb./sq. in.
kg-cal
in.
ft.
atm
in
..
Hg
lb./sq. in.
lb./sq
. ft.
kg/m
2
ft./
sec.
ft
./min.
mph
n.
oz.
cu. in.
cu.
ft.
I
U.
S.
gal
cm
3
mJ
cu.
in.
cu.
yd.
U.S. gal.
l
I/sec.
m3 /min.
MULTIPLY
cubic
in,ches (cu.
in
.)
cubic
meters
(m
3)
cubic
meters
per
minute
(m
3 (
min.)
cubic
yards (cu.
yd.)
degrees {arc)
degrees
per
second
(deg./sec.)
drams, fluid
(dr.
0.)
drams,
avdp.
(dr.
aydp.)
feet
(fl)
feet
per
minute
(ft/min.)
BY
16.39
1.639 x 10 ·S
5.787 x
IO_.
0.554 l
0.
01639
4.329
x
10
3
0.01732
61024
1.308
35.3147
264.2
35.3147
27
0.7646
202
0.01745
0.01745
0
.1
25
0.0625
30.48
0.3048
12
0.33333
0.0606061
1.894
x
10
·"
J.645 x I04
0.01136
0.01829
0.508
0.00508
SECTION 1
GENERAL
TO
OBTAIN
cm
1
mJ
cu.
ft.
n.
oz.
I
U.S
. gal.
U.S.
qt.
cu. in.
cu.
yd
.
cu.
ft.
U.S. gal.
cu.
ft./
min
.
cu. ft.
m3
U.S. gal.
radians
radians/sec.
fl.
oz.
oz. avdp.
cm
m
in.
yd.
rod
m1.
NM
mph
km
/
hr.
cm/sec.
m/sec.
REPORT: VB-1140
l·
ll
SECTION 1
GENERAL
EPORT:
VB-1140
1l
PIPER
AIRCRAFT
CORPORATION
PA
-
34
-
200T,
SENECA
ll
ISSl.JE
D:
SEPTEMBER
12, J980
PIPER
AIRCRAFT
CORPORATION
PA-34-
200T,
SENECA
Il
JSSUED:
SEPTEMBER
12,
198Q
SECTION I
GENERAL
REPORT:
VB-1140
1-13
SECTION I
GENERAL
lEPORT:
VB-1140
~
14
PIPER
AIRCRAFT
CORPORATION
PA-34-200T, SENECA
ll
lSSl
lEO: SEPTE:\>IBER 12, 1980
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