Republic Aircraft Twin Bee Flight Manual

8/11/2019 Republic Aircraft Twin Bee Flight Manual

1/20


2/20

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.


3/20

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


4/20

h1z

.5

E-


5/20

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


6/20

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'


7/20

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


15/20

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


16/20

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


17/20

EhocLSlru

(contd)

Page

J-6

Instructions

are

given for

both

ptesaure readings

and

neasurements.

Before

atterapting

to

tal


18/20

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.


19/20

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.


20/20

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)

Republic Aircraft Twin Bee Flight Manual

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Transcript of Republic Aircraft Twin Bee Flight Manual