Republic Aircraft Twin Bee Flight Manual
Transcript of Republic Aircraft Twin Bee Flight Manual
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8/11/2019 Republic Aircraft Twin Bee Flight Manual
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Page
I
UNITED
CONSULTANTS'
ORP.
Nonvood,,
Mass.
ThLs
docunent
roust
be
kcpt
ln
airptane
at
all
tines'
F.A.t.
APproved
Date-..--
Model
UC-I(J
place)
normal
cate8ory
o .
F.A.A.
Ident i f icat ion
Serial
No
r..SiIE .grs'
the following
limitations
alrplanel
:
nust
be
observed
in
he operation
of
thie
-gEC&S,r
1[wo Lycoming
Moclel
Io-350-BlD
engines
Eneine linltsr For all operations-2?O0 R'P'S' ' 180 HP
Arej.,
1OO
Mininurn
octane
aviation
gasoline'
Prooellersr
llwo
}lartzell
Morlel
}iC-C2YK-2RB'
G;fTlilifs)ins,
with
?666L-z
brades.
Pitch
constant
sPeed
full
feath
setf,ing
at
30
inch
statio
],ow
l4
deg.,
Feather-79'3
deg'
Diarneterr
?2
inches
to
74
inches'
Avoid
continuous
operation
between
2o00 and
2250
R'P'M'
power
gj]-Eeruexelglet
green trrc(nonoal
operation)
50
deg'
to
JtrEII9EE4EJI20 ateg. C3 Yellow Arc (caution) 20 deg. to 50 deg' cl
Red
Line
(Max)
120
deg'
C'
Oll- Pressurer
Green
Arc
(norual
operating)
50
to
90
psi
I
YeIIow
Arc
(caution)
z5 to
5o
psi
an't
90
to
100
psil
Red
line
(min)
25
psit Red
tine
(rnax)
I00
pei'
F u e l P r e s s u r e l G r e e n A r c ( n o r r n a l o p e r a t i n g ) 0 t o } l p s i
Red
Line
(uax)
ff
Psi.
Irelgpelelt
Green
Arc
(nornal
operating)
60o to
2000
RP
and
2250
to
2700 RPMI
Real
Arct(avoid
contlnuous
operation)
20o0
to
2250
RPM
Red
Liner
(max)
2700
RPM.
I
Green
Arc
(Norrnal
oPeratlng
c ,
range)
90
deg. to
Red line(max,
260
260
deg.
deg.
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Table
of
finitC.
(contd)
Page
2
Airspeed
lfunits
and
narklngs
t
" "rliuilieq
-elrEpegl
ntH:"H":if,
v',.)
Maneuvering
sPeed
(vn)
l{ax
Struc
tural
Cnrlslng
speed
(Vrro)
Max
Flaps extended
sPeed
-
(vr")
'Max
oear
Extended
sPeed
(vr")
Single
Engfne
l4in.control
speed
(Vr")
Slngle
Engine
Sest rate
of
clirob
speed
Caution
range
Normal
operating
range
Flaps Ex&nded
Range
r56lrPir
(red
l ine)
131
MPt{
r32
MPlt
IO5
MPH
100
r[PH
58
MPH
(Red
Radial l ine)
79
lPH
(Blue
railial
line
L32
to r55
MPli
(YeIIow
arc)
52
to
L32
wrr
(
green
arc)
49 to I05
MPlt
(white
arc
)
NoterDlar reuver lng invo lv ingapproachtosta l l ingangleor fu l lappl ica-
t l o n o f e l e v a t o r , r u d d e r , o r a i l e r o n s , s h o u l d b e c o n f i n e d t o s p e e d s
below'naneuverS.ng. Peed.
Flleht
load
factorst
Max
Positive
Max.
Negatlve
Dlaxisun--yeiehJr 380O
lbs.
-C-G:--Eg1ggL
See diagran
on
page
3
for
C'G' range
with
Bear
retraction
monent
is
+2900
ln'-lbs'
1 . 80 " 9 "
No inverted
DaneuverB
approved.
gear
extended
97.5
inches
ftrd.
of
wing
L.E.
is
the
responsibility
of the
airplane
owner
a
ensure
that
the
airplane
Ls'
properly
loaded.
Datun
is
Noter
Lt
pilot
to
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h1z
.5
E-
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l,tnitations
BfaserEn
(
conttl
)
Page
4
a)
On
cover
assenbly,
Just
aft
of
controls
for
main
fle1
shut-off
valves'
in
fuII
view
of
pilott
nust
be
ted
as
a nomal
cate
trDo
no t
144
Kf
CAS Flaps uP.'
tMa.rteuve
s
at
Max.
Grose
weight-114
Kt
cas."
airolane
in
conpliance
wlth
the
operating
lirnitations-
stated
in
the
Form of
placarde,
narklngs
and
nanuals"'
tic
Maneuvere(
nc l
"Max.
S
for
ar
tion and
extension
8?
KT
CAS.,
s
control
Kf
cAs."
tDenonstrated Crosswind velocity
I7 KT"
o f
)
Insid
e
rudder
aerodYnaraic
balance
l-ower
ribr
,rTranEfer
Aux.
Fuel- to
rnain
tank
in
l.gvel
fU;ghl
onIV
"
nAux.
ta.nk
nust
be
filLed
for
water
talce-off
and
landin
t into
known
Ic
,
conditions
blted.
"
b)
"Rvd.
baggege
conpartrnenfpon
top
of uain
fuel
tank
fille
neck
coverr
,r'Ma:r
Baggage
caPac ity
200
1b6,.
"
c)
Aft
baggage
cornpartment,
on
vertical
upholstered
panel
at
aft
end
of
conPartnent
r
"Max.
Baggage
cap4gity-199-fbs."
d )
Adjacent
to
fuel
f i l ler
caPst
Tank
Capacityr
8
on6,
Ioo,/130
nin.
grade
"Aux.
tank
capacityr
15
gallons
loo,/130
nin'
grade
"'
e)
on sill
of
each
main
cabin
doorr
down
e(s)
when
door(s)
for
entrance
- ^ *
* ^ a a r r ^
i
f
s
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Er'*.glgeC
pase
5
FueI
Svstenr
Auxiliary
Fuel
Svstenr
l r a n s f e r a u x i t i a r y f u e l t o n a i n t a n k i n l e v e ] . f l i g h t o n ] . y
when
rnain
tank
ig
between
J/4
and
L/8
fulI.
Putr
etectric
tranefer
slvitch
in the
'enpty"
position
to
trangfer fue; fron aux. tahtr to mai'n
tank,
(red
indicator
light
near
switch
will
cone on.
)
Flow
froD
aux'
tank
to
main
tank
is
bY
gravitY.
Aux.
tarlc
is
nornally
filled
whtle
al rplane
ie
on the
grou
(cap.
16
u.S.
gallons).
However, aux'
tank
can
be
fil led
while
in
flight by
transfering
fuel fron
the
nain
tank
by
use
of
the electric
transfer
punp.
to
transfer
fuel
fron
rnaln tank
to
aux.
tank
Fut
electrlc
t r ans f e r sw i t ch in t he 'F u1 l ' pos i t l on ( re t l l n i I i ca t o r J . i gh t
near
swltch
will
corneon)
'
Holdl
fuel
quantlty
selector
e$itch
in.the
"AUll'"
position
to
determine
quantlty
of
fuel
in
the
aux. tan*"'
The additlonal
heat
arormd
the
engine
fuel
punp and linesr
as a result of prolongetl growrd idIe, can result in fuel
vapors
which
will
affect
idle
operatlon,
particularly
on
hot
days.
l{hen
engine
RPMstarts
to
drop below
noI:nal
ictle
RPM,
turn
electric
auxiliary
punps
"0N"
Pronellers
t
FuIl-
trhottlg
on
operative
engine
to
naintain
altitude
an{.a5.rspeeQ.
l{aintaln
at
least
?9
IPH
CAS'
the
best
elngLe engine rate of clinb speed (btue radial line on
airspeed
indicator).
Inoperative
engine
procedure
is
as
followsl
a)
Close
thrott le
U)
Pull
prop control
back,
past
stop,
to
"Feather"posit io
e)
Miiiure
control
rr1df6
Cut-offr '.
d)
Ignit ion
switch
"0ff".
e)
Electrlc
auxiliary
punp
'offl
.
.f)
Main
fuel
valve
"off"
on
inoperative
engine
side'
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Procedures
[contd)
Page
5
Stall
Speedt
(cal ibrated
airspeed)
(power
off)
Unfeatherine
Procedure
t
a)
turn nain
fuel valvenon".
b) Advance
propeller
control
to
low
BPM
position(approx-
inately halfruay
between
eaeh end
of
nor"nal
travel).
c) Start engine. following the nonlal starting procedure
d)
Allow
engine
to
idle
at
loo to 1J0o
RPMuntil
oil
*
slip
**Accel.
at
lroderate
i"ate
into
a ro11-
of f .
Less than I0O
ft.
alt is
Lo6t
fron
point of uncroL-
lable cond. to point where
Level
flight
is regained.
tenperature
begirpe
to rise.
e)
Re-eynchronl.ze
engineg.
Performance
r
Flisht
CharacteriEtics
Cridtcal
Engine
Inoperative
(left)
(FulI
Power
on operatlve engine).
Gear
and
flaps
upr
52
MPH
Gear
and
llaos
down
(fuol
f laps,-
30
deg.) 49 rFH
c
h t
E '
r ) d
> G
o o
o o
. G t
a)
6 :
t { O o P . P O
o r p i n d ( 0
- t t b o
o t {
C P P C
A d o o o . r l
o
f t
d
q t P
o hl'
.+,
(d
l ' {
k
t r
5
-{
blt
o s
d d {t
t c .P
o
o
o
o
d . . l c r A h t ' b l ) d
- l
l . {
d o
ctl
15
Cr{ P{ C
Fl
Pr
Zl h
ct
o
(d '.1
..1
(d
Etr E
Fl Ul F{
.i
d
rl
( 5 I + | E P ' r - r
r{l
Fll
-l
At a\
+
rn
\O
d A
a
ul
A @
d A
F l d
q-r
r.{
l q {
a r l
t r o
..t
C
Fl
--t
Fl
{.}
k E
, h
u t 5
O'
,P
l r a ,
A l l
E
B
o
u,
d
F{
q{
I
c)
tr
Fl
tr
.P
o
Ir
o
d
J
(H
I
o,
c
r{
o
h
a
ul
o
o
k
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Vac
uulr
Sys;ten
Page 14
tn
\o
t\
F{
N
(n
-t
t{
>r
r t O
u)
A A
d c l t {
c u l o
6 P* l q r l
.P
O
:r-{
o d + {
o + t
t r o k
, {
t d
a u t
o o
E - l
>
I l
5 d
F.l
rl
g >
d l
t r
> o
E q {
t
5 0 . 4
t + {
o
O
O F I O T r r
d o . c h
> 0 4 o c t
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Lanllins
Qear
(contd)
page
15
cylinder
pernitting
a
"break"
in
the
linkage.
fhe tail
wheel is
rotated to the
up
and
down
position
and
the
gain gear
is retracted
an
extended .
A control is
provided
in
the
cockpit
to
engage
or
disengage
a
tail
wheel
lock thus
pernitting
the
tail
wheel
to
be
locked
in
the
center posit ion or to be .unlocked in order to swivel. The control is
Iocated above the hull
deck
Just
aft of
the h3rdraulic
power
'pack.
the
nain
wheels
are
610O x
6 and
tiree are
7r0O
x
6.
The tai l
.qltree1
s a
10" srnooth
contour
type.
The
naln
gear
dl6c
type brakes
are
actuated
by toe
pedals
on
the
pi).ot's
rudder
pedals.
llydraullc
brake
cylinders
located
in
front of
the
rudder
pedals
are
readily
accessible
in
the
cockpit: for servi:cing.
A
brake
fluid
reservoir
which
is
attached
to
the
brake
cylinders
wlth
flexible llneb providee a reserve of fluld for the
braJce systen.
A
parking
valve is
lnstalled
in each
of the
linee
between the
naster
brake
cylinder
and the
wheel. The
positions of
these
parking
valves
are
controlled
by
a single
parking control
locatec
Just
below the ins
ment
pahel
at the
extrene
left
side.
Sesj.;llcl
Sjfesr
Inflate
main
wheel
tires
to
JB
psi
and inflate
the tail
wheel t ire
to
4J
Psi.
Efqlesr The bralre systen ls filled with MIL-0-J6o6 (petroleurn
base.).
hydraulic
brake
fluid.
.Po
not
use
vegetablc
base
Urake
fluids
when refllling
the
systen.
If
it
is necessary
to bleed
the
brake
system
to
get
air
out of
the
lines, fluid
should
be
addett
under
pressure
at
the bleeder attach
ment
on the
bralce unit.
No
ad
ustnent
of
brake
clearances
is necessary
on the
Twin Bee
brakes.
If
after
extended
service,
braking
action
requires too
uruch
movenent of the toe pedals, new brake llnings can easily be installed
by renoving
the
four
bolts
which attach
the
bralce
units,
then replacin
the
brake
linings.
Shsr, -gtEult
llhe followlng
service instrpctions
when followed will
result in
a'rapld
and
proper
servicing of
your shoek absorber.
All referenced
used
in thls
outline
pertaLn to the
illustration
belowt
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EhocLSlru
(contd)
Page
J-6
Instructions
are
given for
both
ptesaure readings
and
neasurements.
Before
atterapting
to
tal
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Elegtrical
Svstern
Page
U
Thc
Twin
Bee ie
equipped
with
a l2-volt
electrical
systen
and the
power supply
conBists
of one
J4
a,np-hr.
battery
and tYto
35-at0p
genera
torsone
on
each
engine
(wo
50-anp
generatDrc
can be
supplieil
as
optlonal
equlpment).
The electrical systen schenatic dlagran is shown on page 18.
The
two
35
arnp
generator installation
is the
baslc
-1
systen'
and
the
two
5o-anp
generator
installation ls the
-J
system.
above
the
aft
baggage
compartroent,
and
is accessible
from
the outside
by removing
an
access
cover
dLrectly abovethe
battery.
The
battery
relay
swltch
is
located
at
the
fonvatd
end
of
the battery
Just
above
the
wing rear-
apar
cross-tie memberand ie
accessl.ble
.through the
opening provided for the battery.
,
Circuit breakers
are
provLded
for
protection
of the
indlvidual
circuits
and
are
located
on an aft sloping
panel
above the
hu1l
tieek
floor
Just
forward
of
the raain fuel shut-off valve'
controls and hydrau
power
pack.
'
The
paralleling relay
and
voltage regulatora are
located on a
horizontal-
shelf
Just
aft
of the instruroent
panel.
Each
engine
is
equippett
with a 12
volt
geared
starter.
Th:
starter
soLenoid
operated switches are located in the area of the
battery
Just
above
the
wing rear
spar
cross-tie nenber.
They
are
accessible
through
the
opening
provided for the battery.
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Insoect ion
Page
1P
Pre-LLigL r
The following
safety
procedure
instructions
nust becone an inte-
gral
part of
the
aircraft owner's
operational
routine
and./or
preflight
tnspec ti
on.
Before
each
flight, visually
inspect
the
airplane,
and/ot
deter-
nine that t
1.The
tires
are
satisfactorily
inflated
and
not
excessively worn
2.The Landing
gear
shock struts
are
properly
inflated
and have
the
proper
extension.
J.The
propel lers
are free
of detr inental
nlcks.
4.Bhe
engine
cowling
and
inspection opening
coyers
are
securer
5.There
Ls
no
external
damage
or
operational
ihterference
to
con
trol surfaces,
wings,
hul1,
cabin
or
f loate.
6.There is no corosion of structure r particularly if airplane is
operating
in salt
water.
?.Phe
hull
is
drained of water,
and that
the
hulI
drain
plugs
are
properly
instal led.
8.The surface
control
locks,
i f
used,
are
renoved.
p.The
fuel
tanks
are ful1 or are at a
.safe
level of
proper
fuel.
l0.fhe
fuel
tank filler caps
are
tieht.
1l . | lhe
fuel
system vents
are open.
12.Ihe nain and aux. tank sumps are free of water by draining onc
a
day.
IJ.The
fuel f i l ter, located on- wing
root r ib, is free
of
water
and sedinent
by
draining
once a
week.
14.There are no obvious fuel dr oil
leaks.
15.The engine oi l is
at
,proper
level.
15.The
brakes are
working properly.
17.The windshield
is
clean and free of
defects.
l8.There Ls no snow or ice on the
wings or control
surfaces.
'19.411 required papers are in order and in the airplane.
20.The
weather
is satisfactory for the type of flylng
you
expect
t o d o
.
Z1. l lhe raaio equi iment is
in
order.
22.Upon
entering
the
airplane, ascertain that
all surface
controls
are
free
and operate normalIy, that the landing
gear
and other
controls
are in
proper
posit ions,
that
al l engine controls
operate
properly,
that
bow
door is
locked
and the
main
eabin
doors are
locked and the
safety latch
engaged.
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I nsoect ion
(contd)
Page
2o
Noter
I f
the
main
cabin
doors are
locked'
at
upper
center of
instrument
panel
,
are
unlocked
the red
l ight '
adjacent
onr
the
green
1ight, l -ocated
wil l be
on.
I f
the
doors
to
the
anber
1ight,
wi l l
b
It
is the
piLots
responsibil i ty
to load the
airplane within the
approved
C.G. l imits
Approved
the
Figure
on
Airplane
Loadlng Index"
A
typical
loadtng
is
I
tem
Pilot
& co-pi lot
2 nassengers
@
'
s t i .
95 .0
baggage
@
Sta. LI8.0
anchor
&
line
Fire ext inguisher
Fuel-main
tanx(3/4
fu1l)
Enpty
weight
S
otals
weight and
C.G. Limits
(lnches
aft
daturn)
are
$iven
in
page
2L.
weight and
C.G.
is
controlled by
uslng
the
"Airplane
tables
on
pageE
22
& 23.'
given
below r
Weight
Index
340
2I
340
3i
r40
t7
I
0 . 3
?
o , 5
349
40
25L2
ir5
3796
'
t+2?.8(428)
From
the figure
on
Page
6r
f rd. limit
index=
423
(tandplane)
I
.,
,'
=
44I
(
seaplane
)
aft
linit
index
=454
(
landplane
&
seaplane)
The above
calculated
index
of
428 is
within
linits
for operation as a
landplane
.
For water
operat ion
lncrease
index
t44r-428)=
13 units.
Transfer fuel
from main
tank to
aux.
tank.
with aux.
tank
empty,
and
filllng
aux.
tank
to
3/l+
nark
on
gauge
wiLl
increase
Index
1l
units
(see
page
23)