Beechcraft Debonair 35-33 Pilot Operating Handbook

PILOT'S

OPERATING HANDBOOK

AND FAA

APPROVED

AIRPLANE

FLIGHT

MANUAL

for

the

CUeechcraft ®

Debonair 35-33

FAA

APPROVED

IN

NORMAL

AND

UTILITY CATEGORY

BASED

ON CAR 3. THIS DOCUMENT MUST BE CARRIED IN

THE AIRPLANE

AT

ALL

TIMES AND BE KEPT WITHIN REACH

OF THE PILOT DURING

ALL

FLIGHT OPERATIONS.

THIS HANDBOOK INCLUDES

THE MATERIAL REQUIRED

TO

BE

FURNISHED TO THE PILOT

BY

FAR PART 23.

"

)....,

~~o

Mfr's

Serial No. _ _

l---'

ll/'-__

v _ _

___

_

Registralion

No

.

~~4

A=

FAAApprovedby:

~

_,K._~

W. H. 'SCHUL

TZ

BEECH AIRCRAFT

CORPORATION

DOA

CE·2

THIS HANDBOOK SUPERSEDES

ALL

BEECH

PUBLISHED

OWNER'S MANUALS, FLIGHT MANUALS, AND CHECK LISTS
ISSUED FOR THIS AIRPLANE WITH

THE EXCEPTION OF FAA

APPAOVED AIRPLANE FLIGHT MANUAL SUPPLEMENTS.

P/N

33-590000-158

Reissued :

April,

1982

DEBONAIR

33

PILOT'S

OPERATING

HANDBOOK

and

FAA

APPROVED

AIRPLANE FLIGHT

MANUAL

LOG

OF

REVISIONS

ORIGINAL (A)

.....

..

....

..

. . . . . . .

......

..

JUNE

1977

REISSUE (B) . . . . . . . . . . . . . . . . . . . . . . . . . . . . APRIL

1982

PAGE

DESCRIPTION

OF

REVISION

T

itle

Page

Logo

Page

A

Page

a

thru

b

1-1 thru 1-20

2-1

th

ru 2-24

3-1

thru

3-10

4-1

thru

4-16

5-1

thru

5-32
6-1 thru 6-22
7-1

thru

7-30
8-1

thru

8-52
Section 9

See Log

of

Supplements

10-1

thru

10-67 March 1981

.

1

B

PageA

~

BEECHCRAFT

Debonair

33

INTRODUCTION

This Pilot's Operating Handbook

and

FAA

Approved

Air-

plane

Flight

Manual

is

in

the

format

and

contains

data

recommended

in

the

GAMA

(General

Aviation

Manu-

facturers

Association) Handbook

Specification

Number

1.

Use

of

this

specification by all

manufacturers

will

provide

the

pilot

the

same type data

in

the

same place

in

all of

the

handbooks.

In recent years, BEECHCRAFT handbooks contained most

of

the

data

now

provided,

however,

the

new

handbooks

contain

more detailed data

and

some

entirely

new

data.

For example,

attention

is called

to

Section X SAFETY IN-

FORMATION. BEECHCRAFT

feels

it

is

highly

important

to

have SAFETY INFORMATION in a condensed

form

in

the

hands

of

the

pilots. The SAFETY INFORMATION

should

be

read and studied. Periodic

review

will

serve as a

reminder

of

good

piloting

techniques

.

April

1982

a

PILOT'S OPERATING

HANDBOOK

and

FAA

APPROVED

AIRPLANE FLIGHT

MANUAL

TABLE OF

CONTENTS

SECTION 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . General

SECTION

II

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Limi

tations

SECTION

III

...

......

.......

... Emergency

Procedures

SECTION IV . . . . . . . . . . . . . • . . . . . . . .

Normal

Procedures

SECTION V

..........................

...

Performance

SECTION

VI

.......

Weight

and

Balance;Equipment List

SECTION VII . . . . . . . . . . . . . . . . . . . . Systems Description

SECTION VI

II

....

Hand

ling

, Servicing and

Maintenance

SECTION IX . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Supplemen

ts

SECTION

X . . . . . . . . . . . . . . . . . . . . . . . Safety I

nformation

b

April

1982

BEECHCRAFT

Debonair33

SUBJECT

SECTION

1

GENERAL

TABLE OF

CONTENTS

PAGE

lmportant

Notice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1-3

Use of

the

Handbook . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4

Revising

the

Handbook . . . . . . . . . . . . . . . . . . . . . . . . . .

1-

7

Supplements

Revision Record . . . . . . . . . . . . . . . . . . . . 1 -7

Vendor-lssued

STC

Supplements

. . . . . . . . . . . . . . . . . 1-8

Airplane

Three

View

. . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 -9

Ground

Turning

Clearance . . . . . . . . . . . . . . . . . . . . . . 1-10

Descriptive Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 -

11

Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11

Propeller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 -

11

Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 -11

Oil Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-

12
Weights

...............................

.

....

1-

12

Cabin

And

Entry

Dimensions

. . . . . . . . . . . . . . . . 1-

12

Baggage Space and Entry

Dimensions

. . . . . . . 1-

12

Specific Loadings „ „ „

..

„ „ „ „ „ „

..

„

„.

1-

12

General Airspeed

rerminology

and Symbols . . . . .

1-13

Meteoro

logical

Terminology

. . . . . . . . . . . . . . . . . . . . . 1-

15

Power

Terminology

„.

„„„

„

„„

„ „

„„.

„ „ .

1-16

Engine Controls and

tnstruments

. . . . . . . . . . . . . . . . 1

-16

Airplane

Performance and

Flight

Planning

Terminology

. . . . . . . . . . . . . . . . . . . . . . . . 1-17

Weight

and Balance Terminology . . . . . . . . . . . . . . . .

1-18

April

1982

1-1

BEECHCRAFT

Debonair33

Section 1

General

THANK

YQU

...

for

displaying confidence

in

us by

/'"""

sel

ecting

a BEECHCRAFT

airplane. Our

design

engineers

,

assemblers

and

inspectors have utilized

their

skills

and

years

of

experience

to

ensure

that

the

BEECHCRAFT

Debonair

meets

the

hi

gh

standards

of

quality

and

performance

for

which

BEECHCRAFT

airplanes

have

~

become

famous

throughout

the

world

.

IMPORTANT

NOTICE

This handbook

must

be read

carefully

by

the

owner

and

operator

in

order

to

become

familiar

with

the

operation

of

the

BEECHCRAFT Debonair. The handbook presents

suggestions

and

recommendations

to

help

obtain

safe and

maximum

performance

without

sacrificing

economy. The

BEECHCRAFT Debonair

must

be operated according to

the

Pilot's

Operati

ng

Handbook

and

FAA Approved

Airp

lane

Flight

Manual

, and,lor placards located

in

the

airplane .

As a further

rem ind er.

the

owner

and

operator

of

this

airplane

should

also be

familiar

with

the

Federal

Aviation

Regulations applicable to

the

operation

and

maintenance

of

the

airplane

and

FAR

Part

91

General Operating

and

Flight

Rules . Further,

the

airplane

must

be operated and

maintained

in

accordance

with

FAA

Airworthiness

Directives

which

may be issued

against it.

The

Federal

Aviation

Regulations place

the

responsibility

for

the

maintenance

of

this

airplane

on

the

owner

and

the

operator

who

must

ensure

that

all

maintenance

is

done

by

qualified

mechanics

in

conformity

with

all

airworthiness

requiremen

ts established

for

this

airplane

.

.

All

limits,

procedures, safety practices,

time

limits,

servicing, and

maintenance

requirements

contained

in

this

handbook

are

considered

mandatory

for

the

continued

airworthiness

of

this

airplane,

in a condition

equal to

that

of

its

original

manufacture.

April

1982

1-3

Sectionl
General

BEECHCRAFT

Debonair33

Authorized

BEECHCRAFT

Aero

or

Aviation

Centers

or

Internat

ional

Distributors

or Dealers can provide

!"\

recommended

modification,

service,

and

operating

procedures

issued by

both

FAA

and

Beech

Aircraft

Corporation,

which

are

designed

to

get

maximum

utility

and

safety

from

this

airplane.

USE

OF THE

HANDBOOK

The

Pilot's

Operating

Handbook

is

designed

so

that

nec-

essary

documents

may

be

maintained

for

the

safe

and

efficient

operation

of

the

BEECHCRAFT Debonair. The

handbook has

been

prepared

in

loose

leaf

form

for

ease in

maintenance

and in a

convenient

size

for

storage. The

handbook has been

arranged

with

quick

reference

tabs

im-

printed

with

the

title

of

each

section

and

contains

ten

basic

divisions:

Secti

on

1

General

Section 2

Li

mitations

Section 3 Emergency Procedures

Section 4

Normal

Procedures

Section 5

Performance

Section 6

Weight

and

Balance(Equipment

List

Section 7

Systems

Description

Section 8

Handling,

Servicing

and

Maintenance

Section 9

Supplements

Section

10

Safety

Information

1-4

April

1982

BEECHCRAFT

Debonair33

Section 1

General

NOTE

Except as noted, all airspeeds quoted in

this

handbook are

lndi

cated Airspeeds (IAS)

and

as-

sume zero

instrument

error.

In

an

effort

to

provide as

complete

covera ge

as

possible, applicable to

any

configuration

of

the

airplane, some

optional

equipment

has been

included

in

the

scope

of

the

handbook.

How-

ever,

due

to

the

variety

of

airplane

appoint

-

ments

and

arrangements

available,

optional

eq

uipmen

t described and depicted

herein

may

not

be designated as

such

in every case.

The

following

information

may

be provided

to

the holder

of

this

manual

auto matically:

1.

Original issues and revisions

of

Class

and

II

Service

lnstruct

ions.

2.

Origin

al issues and revis i

ons

of

FAA

Ap-

proved

Airplane

Flight

Manual

Supple-

ments

.

3. Reissues

and

Revisions

of

FAA

Ap-

proved

Airplane

Flight

Manuals, Flight

Handbooks,

Owner

's

Manuals,

Pilot's

Operating

Manuals

and

Pilot's Oper-

at

ing Handbooks.

Th

is

service is free and

wil

l be provided only

to

holders of this tiandbook

who

are listed on

the

F

AA Aircr

aft

Registration

Bran

ch List

or

the

BEECHCRAFT

International

Owners

Notifi -

cation

Service List,

and

then

only

if

you are

listed by airplane serial

number

for

the

model

April

1982

1-5

BEECHCRAFT
Debonair33

Section

1

General

REVISING

THE

HANDBOOK

lmmediately

following

the

title

page

is

the

"Log

of

Revisions" page(s). The

Log

of Revisions pages

are

used

for

maintaining a listing

of

all

effective pages in

the

hand-

book (except

the

SUPPLEMENTS section),

and

as a record

of

revisions to these pages. In

the

lower

right

corner

of

the

out

lined portion

of

the

Log of Revisions is a box containing

a capital letter

which

denotes

the

issue

or

reissue

of

the

handbook.

This

letter

may be suffixed by a

number

which

ind

icates

the

numerical

revision .

When

a revision

to

any

information

in

the

handbook is made, a

new

Log

of

Re-

visions

will

be issued.

All

Logs

of

Revisions

must

be re-

tained in

the

handbook

to

provide a

current

record

of

ma-

terial

status

until

a reissue is made.

WARNING

Wheri

this

handbook

is

used

for

airplane

operational purposes

it

is

the

pilot's

respon-

sibility

to

maintain

it

in

current

status.

AIRPLANE

FLIGHT

MANUAL

SUPPLEMENTS

REVISION

RECORD

Section IX

contains

the

FAA Approved

Airplane

Flight

Manual

Supplements headed by a Log

of

Supplements

page.

On

the

"Log"

page is a

listing

of

the

FAA Approved

Supplemental Equipment available

for

installat

ion

on

the

airplane.

When

new

suppl

ements

are rece ived

or

existing

Supplements

are

revised, a

new

"Log

" page

will

replace

the

previous one, since

it

contains a listing

of

all previous

approvals, plus

the

new

approval. The supplemental

material

will

be added

to

the

grouping

in accordance

with

the

descriptive listing.

April

1982

1-7

Section 1
General

BEECHCRAFT

Debonair33

NOTE

Upon

receipt

of a new

or revised s

upplemen

t,

compare

the

"Log"

page

ju~

received

with

the

existing

"Log"

page

in

the

manual.

Retain

the

"Log"

page

with

the

latest date

on

the

bottom

of

the

page

and

discard

the

other

log .

VENDOR-ISSUED

STC

SUPPLEMENTS

When

a

new

airplane

is

delivered

from

the

factory,

the

---....._

handbook delivered

with

it

contains

either

an STC

(Supplemental

Type

Certificate) Supplement

or

a Beech

Fl

ight

Manual

Supplement

for

ever

y i

nstalled

item

requiring a supplement. lf a new

handbook for

operation

of

the

airp

lane is

obtained

at a later

date, it

is the

responsi-

bility

of

the

owner/operator

to

ensure

that

all required STC

Supplements

(as

well

as

weight

and balance

and

other

pertinent

data) are

transferred

into

the

new

handbook.

1-8

April

1982

BEECHCRAFT
Debonair33

WING

AREA

177.6

sq.

ft.

THREE

VIEW

12'2:1"

Section

1

General

32'9.9"

------

----i

t-----

-----

25'6"

--

---

~

8

'3"

7.5"

min.

84"

DIAMETER

~

9'6.7"

April

1982

1-9

Section

1

General

BEECHCRAFT

Debonair33

GROUND

TURNING

CLEARANCE

A

A Radius for Wing Tip . . . . . . . . . . . . . . . . . .

26

ft. 4 in.

B Radius for Nose

Wheel . . . . . . . . . . . . . . .

12

ft. 2 in.

C Radius for

Inside Gear . . . . . . . . . . . . . . . . 5 ft. 1 in.

D Radius for

Outside Gear . . . . . . . . . . . . . .

14

ft. 8 in.

TURNING RADI! ARE CALCULATEO USING FULL STEER-

ING,

ONE BRAKE AND PARTIAL POWER.

1-10

April

1~82

,

BEECHCRAFT

Debonair

33

Section 1

General

DESCRIPTIVE

DATA

ENGINE

The

BEE

CHCRAFT Debonair

33

is

powered

by a

Continen-

tal 10-

470

-J

wet

sump,

fuel

injection

engine.

This

six-

cylinder

powerplant

is rated

at

225

hp

at

2600

rpm

for

take-off and

maximum

continuous

operation. The 10-

470-K

engine is eligible

for

installation

but

not

directly in-

terchangeable

with

the

10-470-J

engine.

PROPELLER

Hartzell

constant speed,

two

blade,

84

inch

diameter

pro -

peller using a Hartzell BHC-92ZF-1

Dl

hub

with

8447

blades.

~

FUEL

NOTE

Other

propellers

are

approved

but

not

installed

as

original

equipment. These are listed in

the

FAA Ai rcraft Specificat

ion

3A

15

or

approved

by

Supplemental Type Certificate.

Aviation

Gasoline

80/87

(red)

minimum

grade

or

alternate

grades lOOLL (blue)

or

100

(green). See

Engine

Manufacturer's

Bulletin

.

STANDARD SYSTEM

Total

Capacity . . . . • . . . . . . . . . . . . . . . . . . . . . . .

50

gal.

Total Usable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

44

gal.

,,,,,,,.--....

OPTIONAL SYSTEM

Total

Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . .

70

gal.

Total Usable

...

........

.......

.........

...

63

gal.

April

1982

1-11

Section 1
General

Oll

CAPACITY

The oil capacity is

10

quarts.

WEIGHTS

BEECHCRAFT

Debonair33

Maximum

Ramp

Weight ......

.

........

. . .

..

2910

lbs

Maximum

Take-

Off

Weight

. . . . . . . . . . . . . . . . .

2900

lbs

Maximum

Landing

Weight

.............

.

....

2900

lbs

Maximum

Zero Fuel

Weight

. . . . . .

No

Structural

Limit

Maximum

Weight

in

Baggage

Compartment

............

.

......

270

lbs

CABIN

AND

ENTRY

DIMENSIONS

L

engt

h . . . .... ......

. ....

....

.............

6

ft

11

in.

Hei

ght

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 ft 2 in.

Width

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 ft 6 in.

Cabin Door .

..........

.

.... 37

in.

wide

by

36

in.

high

BAGGAGE SPACE

AND

ENTRY DIMENSIONS

Compartment

Volume

. . . . . . . . . . . . . . . . . . . . .

16

.5

cu

ft

Door

Width

(Minimum)

. . . . . . . . . . . . . . . . . . . . . .

18.5

in.

Door Height

(Minimum)

. . . . . . . . . . . . . . . . . . . . . .

22.5

in.

SPECIFIC LOADINGS (Maxi

mum

Take-Off

Weight)

Wing Loading . . . . . . . . . . . . . . . . . . . . . . . . . .

16

.3 lbs/sq

ft

Power

Loadi

ng

. . . . . . . . . . . . . . . . . . . . . . . . . . .

12.9

lbs;hp

1-12

April

1982

r""\

,..........._,

,,.--...._

~

./

BEECHCRAFT
Debonair33

Section 1

General

GENERAL

AIRSPEED

TERMINOLOGY

AND

SYMBOLS

CAS

Ca

librated Airspeed is

the

indicated

speed

of an

airplane, corrected

for

position

and

instrument

error. Calibrated airspeed is

equal

to

true

airspeed in standard

atmosphere

at

sea

level.

GS

Ground

Speed is

the

speed

of

an

airplane

relative to

the

ground

.

IAS lndicated Airspeed is

the

speed

of

an

airplane

as

shown

on

the

airspeed

indicator

when

corrected for

instrument

error

. IAS values

published

in

this

handbook assume zero

instrument

error.

KCAS Calibrated Airspeed expressed in "

knots"

.

KIAS

lndicated Airspeed expressed in "

knots

".

TAS

True Airspeed is

the

airspeed

of

an

airplane

relative

to

undisturbed

air

which

is

the

CAS

corrected for

altitude, temperature,

and

compressibility

.

VA

Maneuvering

Speed is

the

maximum

speed

at

which

application

of

full

available

aero-

dynamic control

will

not

overstress

the

airplane

.

VFE

Maximum

Flap Extended Speed is

the

highest

speed permissible

with

wing

flaps in a pre-

scribed extended posit i

on

.

April

1982

1-13

Section 1
General

BEECHCRAFT

Debonair33

VLE

Maximum

Landing Gear Extended Speed is

the

maximum

speed

at

which

an

airplane

can be safely

flown

with

the landing

gear

extended.

VLO

Maximum

Landing

Gear

Operating

Speed is

the

maximum

speed

at

which

the landing

gear

can

be

safely extended

or

retracted.

VNE Never Exceed

Speed is

the

speed

limit

that

may

not

be exceeded at

any

time.

VNO

Maximum

Structural

Cruising

Speed is

the

or Vc speed

that

should

not

be exceeded

except

in

smooth

air

and

then

only

with

caution.

Vs

Stalling

Speed

or

the

minimum

steady fli

ght

speed at

which

the

airplane

is

controllable.

Vso

Stalling

Speed or

the

minimum

steady

flight

speed at

which

the

airplane

is

controllable

in

the

landing

configuration.

Vx

Best

Angle-of-Climb

Speed is

the

airspeed

which

delivers

the

greatest

gain

of

altitude

in

the

shortest possible

horizontal

distance.

Vy

Best Rate-of-Climb Speed is the airspeed

which

delivers

the

greatest

ga in

in

altitude

in

the

shortest

possible

time.

1 -1 4 April 1

982

BEECHCRAFT

Section

1

Debonair33

General

r

METEOROLOGICAL

TERMINOLOGY

ISA

International

Standard

Atmosphere

in

which

( 1)

The

air

is a

dry

perfect

gas;

(2)

The

temperature

at sea level is

15°

Celsius

(59°

Fahrenheit);

(3)

The pressure

at

sea level is

29.92

in Hg.

(1013.2 mill

ibars);

(4)

The

temperature

gradient

from

sea

level

to

the

altitude

at

which

the

temperature

is

-56.5° C (-69.7°

F)

is -0.

00198°

C

(-0.003566°

F)

per foot and zero above

that

altitude.

OAT

Outside

Air

Temperature

is

the

free

air

static temperature, obtained

either

from inflight

temperature

indica -

tions adjusted

for

instrument

error and compressibi

lity

effects,

or

ground

meteorological sources.

lndicated

The

number

actually

read

from

an

~

Pressure

alti

meter

when

the

barometric

sub-

Altitude

scale has been set to

29.92

in

Hg.

(1013.2

millibars).

Pressure

Altitude

measured

from

standard

~

Altitude

sea-level pressure

(29.92

in. Hg) by

a pressure

or

barometric

altimeter.

lt is

the

indicated pressure

altitude

corrected

for

position

and

instrument

error. In

this

Handbook.

altimeter

instrument

errors are assumed to be

zero.

Position

errors

may

be

obtained

from

the

Altimeter

Correction Graph .

April

1982

•

1-15

Section 1
General

Station

Pressure

Wind

BEECHCRAFT

Debonair33

Actual

atmospheric

pressure

at

field

elevation.

The

wind

velocities recorded as

variables

on

the

charts

of

this

hand-

book

are

to be understood as

the

head -

wind

or

tailwind

components

of

the

reported

winds.

POWER

TERMINOLOGY

Take off and

Maximum
Co

nti

nuous

Cruise
Cl

imb

Highest

power

rating

not limited

by

time.

Power recommended

for

cruise climb.

ENGINE

CONTROLS

AND

INSTRUMENTS

Throttle

Control

Propeller
Control

1-

16

Used

to

control

power

by

intro-

ducing

fuel-air

mixture

into

the

intake passages

of

the

engine.

Settings

are

reflected by readings

on

the

manifold

pressure gage.

This control requests

the

propeller

governor

to

maintain

engine/

propeller rpm

at

a selected

value

by

controlling

propeller

blade

angle

.

April

1982

BEECHCRAFT

Debonair33

Mixture
Control

EGT
(Exhaust Gas
Temperature
lndicator)

Tachometer

Propeller
Governor

Section 1

General

This

control

is used to

set

fuel

pres-

sure (flow) in all

modes

of

operation

and

cuts

oft

fuel

completely

for

engine

shut

down.

This

indicator

is used to

identify

the

Jean

and

best

power

fuel

pressure

(flow)

for

various

power

settings.

lndicates

the

rpm

of

the

engine/

propeller.

Regulates

the

rpm

of

the

engine/

propeller by

increasing

or

decreasing

the

propeller

pitch

through a pitch

change

mechanism

in

the

propeller

hub.

/'\

AIRPLANE

PERFORMANCE

AND

FLIGHT

PLANNING

TERMINOLOGY

Climb
Gradient

Demonstrated
Crosswind
Velocity

April

1982

The

ratio

of

the

change

in

height

during a portion

of

a climb,

to

the

horizontal distance traversed

in

the

same

time

interval.

The

maximum

90°

crosswind

com-

ponent

for

which

adequate control of

the

airplane

during

take-off

and

land-

ing

was

actually

demonstrated

during

certification

tests.

1-

17

Section 1
General

MEA

Route

Segment

GPH

PPH

BEECHCRAFT

Debonair33

Minimum

enroute

IFR

altitude.

A part

of

a route. Each end

of

that

part is identified by: (1) a geograph­ical location;

or

(2) a

point

at

which

a

definite

radio

fix

can

be

established.

U.S.

Gallons

per

hour.

Pounds per

hour

.

WEIGHT

AND

BALANCE

TERMINOLOGY

Reference
Datum

Station

Arm

Moment

Airplane

Center of
Gravity

(C.G.)

1-18

An

imaginary

vertical

plane

from

which

all

horizontal

distances are

measured

for

balance purposes.

A

location

along

the

airplane

fuselage

usually

given in

terms

of

distance

from

the

reference

datum.

The horizontal distance

from

the

ref

-

erence

datum

to

the

center

of

gravity

(C.G.)

of

an

item.

The product of

the

weight

of

an

item

multiplied

by

its

arm.

(Moment

divided

by

a

constant

is used

to

simplify

bal-

ance calculations

by

reducing

the

number

of digits.)

The

point

at

which

an

airplane

would

balance if suspended.

lts

distance

from

the

reference

datum

is

found

by dividing

the

total

moment

by

the

total

weight

of

the

airplane.

April

1982

BEECHCRAFT

Section

1

Debonair

33

General

~

C.G.

Arm

The

arm

obtained by adding

the

air-

plane's

individual

moments

and

dividing

the

sum

by

the

total

weight.

C.G.

Limits

The

extreme

center

of

gra

vity

loca-

--....

tions

within

which

the

airplane

must

be operated

at

a given

weight.

Usable Fuel

Fuel available

for

flight

planning.

,...--.,.

Unusable

Fuel

remaining

after a runout

test

Fuel

has been completed in accordance

with

governmental

regulations.

Standard

Weight

of

a standard

airplane

Empty

including

unusable

fuel,

full

Weig

ht

operating

fluids

and

full

oil.

Basic Standard

empty

weight

plus

Empty optional

equipment.

Weight

Payload

Weight

of

occupants, cargo and

~

baggage.

Useful

Difference

between

take-off

weight,

Load

or

ramp

weight

if

applicable, and

basic

empty

weight.

_,........._

Maximum Maximum

weight

approved

for

ground

Ramp maneuvering. (lt

includes

weight

of

Weight

start, taxi, and

run-up

fuel).

,,,,...--...._

Maximum

Maximum

weight

approved

for

the

Take-

off

start of

the

take-off

run.

Weight

April

1982

1-19

Section 1

BEECHCRAFT

General

Debonair33

Maximum

Maximum

weight

approved

for

the

/"'\

Landing

landing

touchdown.

Weight

Zero Fuel

Weight

exclusive

of

usable fuel.

Weight

....--

Tare The

weight

of chocks, blocks, stands,

etc„

used on

the

scales

when

weighi

ng

an airplane.

..-....,

Leveling

Those

points

which

are used

during

the

Points

weighing

process to level

the

airplane.

Jack Points on

the

airplane

identified

by

the

Points

manufacturer

as suitable

for

supporting

the

airplane

for

weighing

or

other

purposes.

1-20

April

1982

BEECHCRAFT

Debonair33

SUBJECT

SECTION

II

LIMITATIONS

TABLE

OF

CONTENTS

PAGE

Airspeed

Limitations

. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2-3

Airspeed lndicator Markings . . . . . . . . . . . . . . . . . . . . .

2-4

Power Plant

Limitations

. . . . . . . . . . . . . . . . . . . . . . . . . 2-5

Engine

......................

.

.......

.

.......

2-5

Operating L

imitations

. . . . . . . . . . . . . . . . . . . . 2-5

Fuel Grades . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2-5

Oil Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5

Propeller Specifications . . . . . . . . . . . . . . . . . . . . . . . 2-6

Power Plant

Instrument

Markings . . . . . . . . . . . . . . . .

2-6

Miscella neous

Instrument

Markings . . . . . . . . . . . . . . 2-7

Weight Limi

ts

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8

Center

of

Gravity

Limits

. . . . . . . . . . . . . . . . . . . . . . . . .

2-8

Maneuver Limits

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2-8

Approved

Maneuvers

. . . . . . . . . . . . . . . . . . . . . . . . . . . .

2-9

Flight Load Factors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9

Minimum Flight

Crew

. . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9

Kinds of Operation

Limits

. . . . . . . . . . . . . . . . . . . . . . . . 2-9

Required E

quipment

for Various

Conditions

of

Flight „ „ „ „ „ „ . „

„.

„ „ „ „ 2-

10

Fuel

..........................................

. 2-

19

Seating

.......

.

.......

.

.........

.

........

.

....

. 2-

19

Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-

20

April

1982

2-1

BEECHCRAFT

Debonair33

Section

II

Limitations

The

following

limitations

must

be

observed

in

the

operation

of

this

airplane.

AIRSPEED LIMITATIONS

CAS

IAS

SPEED

KNOTS

MPH

KNOTS

MPH

REMARKS

Never Exceed 195 225 197 227 Do n

ot

exceed

VNE

this

speed in

any operation

Maximum

161

185 162 186 Do

not

exceed

Structural

th

is

speed

Cruising except

in

smooth

VNo or Vc

air

and

then

only

with

caution

Maneuvering

123 142 123 142

Do

not

make

full

VA

or

abrupt

control

movements above
this

speed

Maximum

104

120 107 123

Do

not

extend

Flap

flaps

or

operate

Extensi

on/

with

flaps ex-

Extended

tended above

VFE

this

speed

Maximum

122 140

122 140 Do

not

extend,

Landing Gear

retrac t

or

operate

Operating/

with

landing

gear

Extended

extended above

VLO

and

VLE

this

speed except

in

emergency

April

1982

2-3

N

~

*AIRSPEED

INDICATOR

MARKINGS

CAS

IAS

MARKING

KNOTS

MPH

KNOTS

MPH

White

Are

52-104

60-120

51-107

59-123

Green Are 62-161

71-185

60-162

69-186

Yellow Are

161-195

185

-225

162-197 186-227

Red

Line

195

225

197

~

*The Airspeed lndieator is marked in CAS values

==

....

CD

(X)

N

)

)

)

'

\ )

227

SIGNIFICANCE

Full Flap Operating Range
Normal Operating Range
Operate

with

eaution only in

sm

ooth air

Maximum

speed

for

ALL operations

)

)

\ )

c

(/)

3

CD

-·

~

...

-·

~-

g

0

:::J

III

IJJ

m

Cm

CD

(')

c::T

:z:

g

(')

Q)

::c

::;· J>

w .,,

w

-l

BEECHCRAFT

Debonair33

Section

II

Limitations

The

following

limitations

must

be observed in

the

operation of

this

airplane.

AIRSPEED LIMITATIONS

CAS

IAS

SPEED

KNOTS

MPH

KNOTS

MPH

REMARKS

Never Exceed 195 225 197 227 Do not exceed

VNE

this

speed in

any ope rat

ion

Maxi

mum

161 185 162 186 Do

not

exceed

Structural t

his

speed

Cruising

except

in

smooth

VNo or Vc

air and

then

only

wit

h caution

Maneuvering

123 142 123 142

Do n

ot

make

full

VA

or

abrupt con

tro

l
movements above
this

speed

Maximum

104

120 107 123

Do n

ot

extend

Flap

flaps

or

operate

Extensior\f

with flaps ex-

Extended

tended above

VFE

th

is speed

Maximum

122

140

122 1

40

Do not extend,

Landing Gear

retrac t

or

operate

Operati

ng/

with land ing

gear

Extended

ex

te

nded above

VLO

and

VLE

this speed except
in

emergency

April

1982

2-3

N

~

~

"'C

:::!.

.....

(D

00

N

*AIRSPEED INDICATOR

MARKINGS

CAS IAS

MARKING

KNOTS

MPH

KNOTS MPH

White

Are

52-104

60-120

51-107

59-123

Green Are 62-161

71-185

60-162

69-

186

Yellow Are

161-195

185-225 162-197

186-227

R

ed

Line

195

225

197

227

*The Airspeed lndieator is marked in CAS values

)

'

SIGNIFICANCE

Full Flap Operating Range
Normal

Operating Range

Operate

with

eaution

only

in

smooth

air

Maximum

speed

for

ALL

operations

)

)

)

c:

(/)

3

~

;::o·

~

III

-·

... 0

-·

~

0 -

~

-

Ul

CJ

m

Om

~

(")

r:r

:i:

g

(")

III

::0

~·

~

W"'TI

w

-1

/""'-

BEECHCRAFT

Debonair33

POWER

PLANT

LIMITATIONS

Section

II

Limitations

_../

ENGINE

Continental

10-470-J

or

10-470-K

fuel

injected

engine.

OPERATING LIMITATIONS

Engine Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2600

rpm

Cylinder Head Temperature . . . . . . . . . . . . .

460°F;238°C

Oil

Temperature

. . . . . . . . . . . . . . . . . . . . . . . .

225°F/107°C

Oil Pressure

Mi

nimum

Maximum

Fuel Pressure

30

psi

80

psi

Minimum

................................

1.5 psi

Maximum

...............................

17.5

psi

FUEL GRADES

Aviation

Gasoline

80/87

(red)

minimum

grade or a

ltern

ate

grades 1

OOLL

(blue)

or

100

(green). See Eng

ine

Manufacturer's

Bulletin.

Oll

SPEC

IFICATIONS

Ashless

dispersant oils

must

meet Teledyne Continental

Motors

Corporation Specification

MHS-248

. Refer

to

APPROVED ENGINE OILS in

the

Handling, Servicing, and

Maintenance

section

April

1982

2-5

Section

II

Limitations

PROPELLER SPECIFICATIONS

Hartzell

eonstant speed propeller
Hub: BHC-92ZF-101
Blades:

8447

BEECHCRAFT

Debonair33

Diameter:

Maximum

84

in.,

Minimum

82

in.

Piteh settings at

33

in. sta.:

Low

11°,

High

not.under

,,..-....,.

26°
Spinner: Hartzell

837-3

Governor: Hartzell hydraulie (

84-3) or

Woodward

hydraulie (210335)

NOTE

Other propellers

are

approved

but

not

installed

as original

equipment.

These

are

listed in

the

FAA

Airerah

Speeifieation

3A

15

or

approved

by

Supplemental Type Certifieate.

POWER

PLANT

INSTRUMENT

MARKINGS

Oll

TEMPERATURE

----

Caution (Yellow Radial) . . . . . . . . . . . . . .

100°F;38°C

/

Operating Range

(Green Are) . . . . . . . .

100°

to

225

°F;38°

to

107°C

Maximum

(Red Radial) . . . . . . . . . . . . . .

225

°F/

107°C

Oll

PRESSURE

Minimum

Pressure (Red Radial)

............

30

psi

Operating Range (Green Are)

.........

30

to

60

psi

Maximum

Pressure (Red Radial) .

...........

80

psi

TACHOMETER

2-6

Operating Range (Green Are)

...

2000

to

2600

rpm

Maximum

RPM (Red Radial) . . . . . . . . . . . .

2600

rpm

April

1982

-

BEECHCRAFT

Debonair33

FUEL PRESSURE

Section

II

Limitations

Minimum

(Red

Radial) . . . . . . . . . . . . . . . . . . . .

1.5

psi

Operating Range (Green Are)

......

. 4.25

to

17 psi

Maximum

(Red

Radial)

..............

...

..

17

.5 psi

CYLINDER HEAD TEMPERATURE

Operating Range

(Green Are) . . . . . . . .

200°

to

460

°F/93°

to

238°C

Maximum

Temperature

(Red

Radial) . . . . . . . . . . . . . . . . . . . . . . .

460

°F;238 °C

MANIFOLD PRESSURE

Operating Range

(Green Are) . . . . . . . . . . . . . . . . . . .

15

to

29.6

in. Hg

Maximum

(Red

Radial)

................

29.6

in. Hg

MISCELLANEOUS

INSTRUMENT

MARKINGS

INSTRUMENT VACUUM
With

Autopilot

Minimum

(Red Radial)

...

....

..

.......

3.

75

in. Ag

Operating Range (Green Are) . . 3.

75

to 4.

25

in. Hg

Maximum

(Red Radial) . . . . . . . . . . . . . . . . . 4.6 in. Hg

r'

,,..-....,_

Without

Autopilot

Minimum

(Red Radial)

..

....

..

.....

....

4.4

in. Hg

Operating Range (Green Are)

..

...

4.8

to 5.2 in. Hg

Maximum

(Red

Radial)

....

.............

5.5 in. Hg

FUEL QUANTITY

Yellow

Band (44-gallon system)

E

to

1;2

full

April

1982

2-7

Sect

ion II

Limitations

WEIGHT

LIMITS

BEECHCRAFT

De

bonair33

Max

imum

Ramp

Weight

....................

2910

lbs

Max

imum

Take

-off

and Landing

Weight ... .

......

....

.........

29

00 lbs

Zero Fuel Wei

ght

. . ...........

No

Structural Limit

ation

Ma

ximum Baggage Compartment

Load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

270

lbs

CENTER

OF

GRAVITY

LIMITS

(Gear

Down)

Fo

rward: 78

.0 inches a

ft

of

datum

to

2550

lbs

with

s

traight

line variation to 82.1 inches

at

2900

lbs.

Aft:

86

.7 inches aft of

datum

to

2525

lbswith

straight

line

variat ion to

85.7

inches at

2900

lbs.

REFERENCE

DATUM

Datum is

83

.1

inch

es

forw

ard

of

cent

er

line

through

forw

ard jack p

oints

.

MAC

leadi ng edge is 66. 7 inches

aft

of

datum

.

MAC

leng

th

is 65.3 inche

s.

MANEUVER

LIMITS

This is a

utility

category

airp

lane. Spins are prohibited . No

acrobatic maneuvers are approved except those

listed

bel

ow

.

Maximu

m slip duration:

2-8

30

seconds

for

airplanes

wit

h baffl ed

main

fuel

cells

in

both wings .

20

seconds

for airplanes w i

th

unbaffled

main

fue

l cells

in either

wing

.

April

1982

BEECHCRAFT

Debonair33

Section

II

Limitations

APPROVED

MANEUVERS

(2900

POUNDS)

MANEUVER

ENTRY

SPEED

(CAS)

Chandelle . . . . . . . . . . . . . . . . . . . . . .

123

kts,1142

mph

Steep

Turn

. . . . . . . . . . . . . . . . . . . . .

123

kts,1142

mph

Lazy Eight . . . . . . . . . . . . . . . . . . . . . .

123 kts,1

142

mph

Stall (Except

Whip)

.........

Use

slow

deceleration

Minimum

tue/

for

above

maneuvers -10

gallons

each

main

tank.

Spins

are

prohibited.

FLIGHT

LOAD

FACTORS

(2900

POUNDS)

Positive

Maneuvering

Load Factors

Flaps

Up

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.

4G

Flaps

Down

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.0G

MINIMUM

FLIGHT

CREW

One

(1) Pilot

KINDS

OF

OPERATION

LIMITS

1. VFR day

and

night

2.

IFR

day

and night

April

1982

2-9

Section

II

Limitations

BEECHCRAFT

Debonair33

REQUIRED

EQUIPMENT

FOR

VARIOUS

CONDITIONS

OF

FLIGHT

Part

91

of

the

Federal

Aviation

Regulations specifies

the

minimum

numbers

and types

of

airplane i

nstruments

and

equipment

which

must

be

installed

and operable

for

various

kinds of

flight

conditions. Th is

includes

VFR

day,

V

FR

night,

IFR

day, and

IFR

night

.

Regulations also

require

that

all

airplanes

be

certificated

by

the

manufacturer

for

operations

under

various

flight

conditions.

At

certification,

all

required

equipment

must

be

in operating

condition

and

should be

maintained

to assure

continued

airworthiness. lf

deviations

from

the

installed

equipment

were

not

permitted, or

if

the

operating

rules

did

not

provide

for

various

flight

conditions, the

airplane

could

not

be

flown

unless all equ

ipment was

operable .

With

appropriate

lim

itation

s,

the

operation

of

every system

or

component

installed

in

the

airplane is

not

necessary,

when

the

rema

ining

operative

instruments

and

equipment

provide

for

cont

inued

safe operation. Operation in

accordance

with lim

itations

es

tablished

to

maintain

airworthines

s,

can

perm

it

continued

or

uninterrupted

operati

on

of

the

air

plane

tem

porarily

.

For

the

sake

of

brevity, the

Required

Equipment

Listing

does

not

include

obviously required

items

such as

wings

,

rudders

, flaps, engine,

landing

gear, etc. Also

the list does

not include

items

which

do

not

affect

the

airworthiness

of

the

airplane such as

entertainment

systems, passenger

convenience

items

, etc. However,

it

is

important

to

note

that

ALL

ITEMS WHICH ARE RELA TED TO THE AIR-

WORTHINESS OF

THE AIRPLANE

AND

NOT INCLUDED

ON

THE LIST ARE AUTOMATICALLY REOUIRED TO

BE

OPERATIVE.

2-

10

April

1982

BEECHCRAFT
Debonair33

Section II

Limitations

To

enable

the

pilot

to

rap i

dly

deter

mine

the

FAA

equipment

requ

irem

ents

necessary

for

a fli

ght into

specific

conditions, the

following

equipment

requirements

and

exceptions are presented.

lt is

the

final responsibility

of

the

pilot

to

determine

whether

the

lack of, or inoperative

status

of

a piece

of

equipment

on

his

airplane,

will limit

the

conditions

under

which

he

may

opera

te

the

airplane

.

WARNING

FLIGHT

IN

ICING CONDITIONS IS PRO-

HIBITED.

LE

GEND

Numbers

refer

to quantit

ies required to be operative

for

a

specified

condition.

(-) lndicates

that

the

item

may

be inoperative

for

the

~

specified

condition.

(*) Refer

to

the

REMARKS AND/OR EXCEPTIONS

column

fo r

explicit

information

or

refe rence .

April

1982

2-11

N

'

...

N

~

'tl

...

...

<D

to

N

SYSTEM

anq/or

COMPONENT

GENERAL

Overwater

flight

ATA

100

CHAPTER

23

COMMUNICATIONS

VHF

communications

syste m

ATA

100

CHAPTER

24

ELECTRICAL

POWER

Battery
DC

generator

)

)

)

VFR

Day

VFR

Night

/FR

Day

/FR

Night

Remarks

andlor

Exceptions

*

*

* *

-*

Per FAR

91

* * *

*

-*Per

FAR

91

1 1 1 1
1 1 1 1

)

)

)

c~

~.

!l

....

-·

I»

0

~.

:J

0

:J

(II

!lJ

m

Om

(1)

(')

tT

::I:

g

(')

I»

::c

:;·

~

w..,,

w

.....

)>

'O

::::!.

....

t.D

(X)

N

N

.

....

w

)

)

ATA

100

CHAPTER

25

EQUIPMENT

AND

FURNISHING

Seat belts
Shoulder

harness

Emergency

locato r

trans

-

mitter

ATA

100

CHAPTER

26

FIRE PROTECTION

Portable

fire

extingui

sher

ATA

100

CHAPTER

27

FLIGHT

CONTROLS

Elevator

trim

tab indicator

~~~

~~~~~~~~~~~~~~~~~~~~

~~~~~~~~~~~~

~~~~~~~~~

)

1 1 1 1
* * *

*

1 1 1 1

*

* *

*

1 1 1 1

) )

- Per Person

or

Per

FAR

91

-

*Pilot

and copil

ot

if

installed

- Per FAR

91

-

*Optiona

l

-

\ )

c

CJ

~

m

CT

m

0

(")

; J:

::;·

(")

w

::D

w

)>

!:':

"T1

~

3 C/)

;::+'

~

I»

...

...

-·

-·

0

0 :J

:J

-

(1)

-

':->

...

.i:.

)>

"C

::!.

...

Ul

Q)

"'

SYSTEM

and/or

COMPONENT

Flap

position

indication lights

Stall

warning

ATA

100

CHAPTER

28

FUEL

EQUIPMENT

Auxi

lia ry

fuel

pum

p

Engine driven fuel

pump

Fu

el

quantity

indicator

Fuel press

ure

indicator

)

)

)

VFR

Day

VFR

Night

/FR

Day

/FR

Night

Remarks

andl or

Exceptions

2 2 2

2 -

1 1 1

1

1 1

1

1

1 1

1

1

2 2

2

2

-

1

1

1 1

)

)

)

c:

C/)

3

CD

:;·

~

III - ·

„ 0

-·

::::s

0 -

::::s

-

In

IJJ

m

Cm

CD

(')

lj

~

g

(')

III

:Jl

:;· )>

w

..,,

w

-1

)>

"O

::!.

.....

c.o

00

1\)

':"

....

Cl

)

l )

ATA

100

CHAPTER

30

ICE

AND

RAIN

PROTECTION

Pitot heater

ATA

100

CHAPTER

32

LANDI

NG

GEAR

La

nding

gear

motor

Landi ng gear positi

on

ind

ication

lights

L

and

ing gear

aural

w

arni

ng

horn

)

*

1

2

1

*

1 1

1

1 1

2

2

2

1

1

1

)

) ( )

-*Optional

-

0

CD

<Dm
er

m

0 (")

;

::z::

=-·

(")

w

:u

w

)>

r-

'Tl

-1

~r

(J)

-·

<D

;~

:::i„

o·

g

:J

III=

~

....

~

)>

"O

~

....

w

CO

N

SYSTEM

and/or

COMPONENT

ATA

100

CHAPTER

33

LIGHTS

Cockpit and in

strument

li

ghts

.

Landing light
Rotati ng beacon
Position

light

ATA

100

CHAPTER

34
NAVIGATION
INSTRUMENTS

Altime

ter

Airspeed indicator

)

) )

VFR

Day

VFR

Night

/

FR

Day

/

FR

Night

Remarks

and I or

Exceptions

- *

-

*

-*Lights

must

be operative.

-

*

-

*

-*Per FAR

91

-

1

-

1

-

3

-

3

1

1

1 1

1 1

1 1

) )'

)

c:

C/)

3

<D

;:::;.·

g_

~

0

-·

J

0 -

J -

Cll

Cl

o

rn

CD

(')

CT

:::C

g

(')

Q)

::II

::;·

)>

w 'Tl

w

-l

)>

"C

~.

...

tD

CO

N

':"

...

....i

)

)

Ver

tical speed

Magnetic

compass

Attitude

indicator

Turn

and slip indicator
Directional gyro
Clock

Transponder

Navigation equ

ipment

.

ATA

100

CHAPTER

35

OXYGEN

Oxygen system

ATA

100

CHAPTER

37

VACUUM

Vacuum system fo r

instrument

air

Vacuum gage

)

*

1

-

-

-

-

*

-

*

-

-

*

*

1 1

-

1

-

1

-

1

- 1

*

*

* -

* *

- 1

- 1

*

1

1
1
1
1
*

*

*

1

1

)

-*Optiona l

-*

Per

FAR

91

-*Per FAR 9 1

-*Per FAR

91

)

0

IXl

CD

m

CT

m

0

C')

;

:::c

:;· C')

w

:1J

w

)>

"T1

....

§'

(/)

-·

CD

„ 0

s.

~.

-·

0

0

::l

::l

-

III

-

r:->

~

00

):>

'tl

:::!

.

~

<D

00

"'

SYSTEM

andjor

COMPONENT

ATA

100

CHAPTER

77

ENGINE

INDICATING

INSTRUMENTS

Engi ne

tachometer

indicator

Manifold

pressure indicator

ATA

100

CHAPTER

79

ENGINE

Oll

INSTRUMENTS

Oil pressure ind

icator

Oil

temperature

indicator

)

)

)

VFR

Day

VFR

Night

/FR

Day

/FR

Night

Remarks

and/or

Exceptions

1 1 1 1

1 1

1 1

1 1 1 1
1 1 1 1

)

)

)

c:

t/)

3

CD

;:+'

~

II)-·

...

0

ö'

:::1

iil

al

m

Cm

CD

(')

c:r

J:

g

(')

II)

:::0

::;·

):>

w

'T1

w

-1

BEECHCRAFT

Debona

ir33

FUEL

STANDARD SYSTEM

Section

II

Limitations

Total Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . .

50

gal.

Total Usable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

44

gal.

OPTIONAL SYSTEM

Total

Capacity

.........

............

.......

70 gal.

Total Usable

.

......

.

......

.

.............

..

63

gal.

FUEL

MANAGEMENT

Take-off

on

left

main

tank.

Use

auxiliary

fuel

in

level

flight

only

and

do

not

use

for

take

oft

or landing. Use

at

least

10

gallons

from

left

main

tank

before use of

auxiliary

fuel.

When

operati

ng

fue

l selector, feel for

detent

position.

Do not

take

oft

when

Fuel

Quant

ity

Gages indicate in

Yellow

Band or

with

less

than

13

gallons

in each

main

tank.

Maximum

slip

duration

:

30

seconds for

airplanes

with

baffled

main

fuel

cells

in

both

wings.

20

seconds for airplanes

with

unbaffled

main

fuel

cells

in

either

wing.

SEATING

All

occupied seats

must

be in

the

upright

position

for

take

-

off and

landing.

April

1982

2-19

Section

II

Limitations

PLACARDS

On Fuel Selector Panel:

BEECHCRAFT

Debonair33

ILh

ao

NOT

TAKE

OFF

IF

FUEL

QUANTITY

GAGES

~

'V

INDICATE

IN

YELLOW

BAND

OR

WITH

LESS

-$-

L

THAN

13

GALLONS

IN

EACH

MAIN

TANK

_J

Standard

44 Gallon

(Usab/e)

System

:

2-

20

OFFÜ

(USE

10

GAL

FIRST)

LH

TANKO

22

GAL

L

0

OFF

O

RH

T

ANK

22

GAL

_J

April

1982

BEECHCRAFT

Debonair33

Section

II

Limitations

Optional

63

Gallon (Usable)

Fuel

System

:

1

OFFÜ

(USE

10

GAL

FIRST)

LH

TANKO

22

GAL

O

RH

TANK

22

GAL

L

0

(AUX

TANK)

20

GAL

(USE

SECOND)

.-

LEVEL

FLIGHT

ONLY

_J

Above

Emergency

Landing

Gear

Extension

Handle:

EMERGENCY

LANDING

GEAR

INSTRUCTIONS

TO

EXTEND

ENGAGE

HANDLE

IN

REAR

OF

FRONT

SEAT

AND

TURN

COUNTERCLOCKWISE

AS

FAR

AS

POSSIBLE

(50

TURNS)

Above

Landing

Gear

Mechanical

Position

lndicator

When

Winter

Baff/es

Are

lnstalled:

NOTICE

REMOVE WINTER

BAFFLES

WHEN

OAT

EXCEEDS

70°

F

L _J

April

1982

2-21

l

Section

II

Umitations

BEECHCRAFT

Debonair33

PLACARDS

(Cont'd)

On

Right

Hand

Subpanel:

/ '

( \

( + l

\ I

' /

FIRE

DOOR

PULL

TO

CLOSE

On

Inner

Side

Of

Baggage

Compartment

Door:

BAGGAGECOMPARTMENT

-$-

LOAD

IN

ACCORDANC

E

WITH

AIRPLANE

FLIGHT

MANUAL

-$-

MAXIMUM

ST

RUCTURAL

CAPACITY -270

POUNDS

On

Storm

Window:

CAUTION

00

NOT

OPEN

ABOVE

145

MPH

(126

KNOTS)

~

L

_J

2-22

April

1982

BEECHCRAFT

Debonair33

Section

II

Limitations

In Full View of

Pilot (CA

SJ:

j

UTILITY

CATEGORY

AIRPLANE

l

L

OPERATE

IN

Acc"oRDANCE

W

ITH FAA

APPROVED

AIRPLANE

FLIGHT

MANUAL

INTENTIONAL

SPINS

PROHIBITED

NO

ACROBATIC

MANEUVERS

APPROVED

EXCEPT

THOSE

LISTED

IN

THE

AIRPLANE

FLIGHT

MANUAL

_J

AUX

FUEL

PUMP

OPERATION

TAKE-OFF

AND

LAND

WITH

AUX FUEL

PUMP

OFF

EXCEPT

IN

CASE

OF

LOSS

OF

FUEL

PRESSURE

AIRSPEED

LIMITAT

IO N

MAXIMUM

SPEED

WITH LANDING GEAR

EXTENDEO

INORMA

LI

140 MPH

MAXIMUM "DESIGN MANEUVERING

SPEED

142

MPH

L

_J

Above

Inside Door Handle:

CAUTION

AFTER
DOOR

CLOSING

ROTA

TE

HANDLE

TO

FULL

L LOCKED POSITION

_J

April

1982

2-23

Section

II

Limitations

PLACARDS

(Cont'd)

In Ful/ View

of T

he

Pilot:

BEECHCRAFT

Debonair33

(Unless baffled

mai

n fuel cel/s are insta

lled

in

both

wi

ngs).

ITuRNING

TYPE

TAKEOFFS,

ANOI

TAKEOFF IMMEDIATEL Y

FOLLOWING

FAST

TAXI

TURN PROHIBITED.

AVOID

PROLONGED

SLIPS

(20

SECONDS OR

~

1

MORE) WITH

FUEL

TANKS

LESS

THAN

HALF

FULL.

_j

2-24

April

1982

BEECHCRAFT

Debonai

r33

SECTION

III

EMERGENCY

PROCEDURES

TABLE OF

CONTENTS

SUBJECT

PAGE

Emergency Airspeeds . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3-3

Engine Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3-4

During

Take-O

ff

Ground

Roll . . . . . . . . . . . . . . . . . 3-4

After

Liftoff

and

in

Flight . . . . . . . . . . . . . . . . . . . . .

3-4

Engine Disc

rep

ency

Checks . . . . . . . . . . . . . . . . . .

3-5

Rough

Ru

nning

En

gine

. . . . . . . . . . . . . . . . . . .

3-5

Loss of En

gine

Power

. . . . . . . . . . . . . . . . . . . .

3-5

Airstart

Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3-5

Engine Fire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3-6

In

FI

ight

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6

On

The

Ground

. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3-6

Maximum Glide

Configuration

. . . . . . . . . . . . . . . . . . .

3-6

Em

ergency Descent

. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3-

7

Landing Emergencies

......

..

....................

3-

7

Landi ng W

ith

out

Power

. . . . . . . . . . . . . . . . . . . . . .

3-

7

Landing Gear Retracted W

ith

Power

. . . . . . . . . .

3-

7

Systems

Emergen

cies . . . . . . . . . . . . . . . . . . . . . . . . . . .

3-8

Propeller Overspeed . . . . . . . . . . . . . . . . . . . . . . . . .

3-8

Generator-Out

Procedu

re

. . . . . . . . . . . . . . . . . . . .

3-8

Landing Gear

Manual Exte

nsion

. . . . . . . . . . . . . . 3-8

Landing Gear Retrac

tion

After

Practice

Manual Extension

. . . . . . . . . . . . . . . . .

3-9

Un

latched

Door

in

Flight

. . . . . . . . . . . . . . . . . . . .

3-10

Spins ....

.....................

.

................

3-10

Emerg e

ncy

Speed Reduction . . . . . . . . . . . . . . . . . . . .

3-10

April

1982

3-1

BEECHCRAFT
Debonair33

Section III

Emergency Procedures

All

airspeeds quoted

in

this section are indicat

ed

airspeeds

(!AS).

EMERGENCY

AIRSPEEDS

Emergency Descent . . . . . . . . . . . . . . . .

122

kts/140

mph

Glide . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

105

kt's

/121

mph

Em

ergency Landing

Approach

.......

.

..

80

kts/92

mph

CAUTION

The approach airspeed is

hig

her

than

normal

to

assure

the

availability

of

control

during

flare

without

power.

The

following

information

is presented to enable

the pilo

t

to form,

in

advance, a

definite

plan

of

act i

on

for

coping

with the

most

probable

emergency

situations

which

could

occur in the operation

of

the

airplane.

Where

practicable,

the

emergencies

requiring

immedia

te

corrective

action

are

treated in check

l

ist

form

for

easy reference and

familiari-

zation. Other situations,

in which

more

time

is

usually

per -

mitted

to

decide

on

and execute a

plan

of action, are

discussed at some lengt h.

April

1982

3-3

Section

III

Emergency Procedures

ENGINE

FAILURE

DURING

TAKE-OFF GROUND ROLL

1.

Throttle

- CLOSED

2. Braking -

MAXIMUM

3. Fuel Selector Valve -

OFF

BEECHCRAFT

Debonair33

4. Battery and Generator

Switches -OFF

AFTER LIFTOFF

AND

IN

FLIGHT

Landing

straight

ahead

is

usual/y

advisable.

lf

sufficient

a/titude is avai/ab/e

for

maneuvering,

accomplish

the

fol/owing:

1. Fuel Selector Valve - SELECT OTHER

MAIN

TANK

(Check to feel detent)

2.

Auxiliary

Fuel Pump - ON

3.

Mixture

- FULL RICH,

then

LEAN as required

4. Magnetos - CHECK

LEFT

and RIGHT,

then

BOTH

NOTE

The rnost probable cause

of

engine fai

lure

would

be loss

of

fuel

flow

or

improper

functioning

of

the

ignition system.

lf

No

Restart

1.

Select most favorable landing site.

2.

See EMERGENCY LANDING procedure.

~

3.

The use of landing gear is dependent

on

the

terrain

where

landing rnust be made.

3-4

April

1982

'""""

BEECHCRAFT

Debonair33

ENGINE DISCREPANCY CHECKS

Section

III

Emergency

Procedures

__.,

CONDITION: ROUGH RUNNING ENG/NE

1.

Mixture

- FULL

RICH,

then LEAN

as

required

2.

lgnition

Switch

- CHECK

LEFT

and RIGHT,

then

BOTH

CONDITION· LOSS

OF

ENG/NE POWER

1. Fuel Pressure Gage -

CHECK

lf

fuel

pressure is

abnormally

/ow:

a.

Mixture

- FULL

RICH

b.

Auxiliary

Fuel Pump -

ON

(Lean

as

required)

c.

Auxiliary Fuel Pump - OFF

if

performance does not

improve in a

few

moments.

2.

Fuel

Quantity

lndicator - CHECK for fuel supply

in

tar'<

being used.

lf

tank

being

used

is empty:

Fuel Tank Selector Valve - SELECT ANOTHER

MAIN

FUEL

TANK (feel

for

detent)

AIR

START

PROCEDURE

a.

Fuel Selector Valve - SELECT

MAIN

TANK MORE

NEARLY FULL (check to feel detent)

b.

Throttle -

RET

ARD

c.

Mixture

- FULL

RICH

d.

Auxiliary

Fuel Pump - ON

until

power

is regained,

then

OFF.

(Leave

on

if

engine driven

fuel

pump is

inoperative.)

e.

Throttle - ADVANCE to desired

power

f.

Mixture

- LEAN

as

required

April

1982

3-5

Section III

Emergency Procedures

ENGINE

FIRE

IN FLIGHT

BEECHCRAFT

Debonair33

The

FIRE

DOOR control on the outboard side

of

the

right

lower

subpanel is used

to

close

oft

all heating system

outlets

so that smoke and

fumes

will

not

enter

the

cabin. In

....-_.

the event of engine fire,

shut

down

the engine as

follows

and make a landing:

1. Fire Door Control - PULL TO CLOSE

2. Mi

xture

- IDLE CUT-OFF

3. Fuel Selector Valve -

OFF

4.

Battery

and Generator Switc

hes - OFF (Extending

the

landing gear can be accomplished

manually

if

desired.)

5. Do not attempt

to

restart engine.

ON

THE GROUND

1.

Mixture

- IDLE CUT-OFF

2. Fuel

Selector Valve - OFF

3.

Battery, Generator and

lgnit

ion

Switches

- OFF

4. Extinguish

with

Fire Extinguisher.

MAXIMUM

GLIDE

CONFIGURATION

1. Landing Gear - UP

2. Flaps -

UP

3. Propeller - PULL for

LOW

RPM

4. Airspeed -

105

kts/121

mph

Glide distance is approximately 1 .7 nautical

miles

(2

statute miles) per

1000

feet of altitude above

the

terrain

.

3-6

April

1982

~

BEECHCRAFT
Debonair

33

EMERGENCY

DESCENT

Section

III

Emergency

Procedures

_.,,

1. Power - IDLE

2. Propeller - HI RPM

3. Landing Gear - DOWN

4. Airspeed - ESTABLISH

122

kts/140

mph

LANDING

EMERGENCIES

LANDING WITHOUT POWER

The approach speed is

higher

than

normal

to

assure the

availability of control

during

flare

without

power. When

as-

sured of reaching the

landing site selected, and

on

final

approach:

1.

Airspeed -

80

kts;92

mph

2.

Fuel Selector Valve - OFF

3.

Mixture

- IDLE CUT-OFF

4. Flaps -

AS

REQUIRED

5. Landing Gear - DOWN

OR

UP, DEPENDING

ON

TERRAIN

6.

Battery and Generator

Switches

- OFF

r----..

LANDING GEAR RETRACTED - WITH POWER

lt

possible, choose

firm

sod

or

foamed r

unway.

Make

a

normal approach, using flaps as necessary.

When

you

are

sure

of

making the selected landing spot:

1.

Throttle - CLOSED

2.

Mixture

- IDLE CUT-OFF

3.

Battery and Generator Switches - OFF

4. Fuel Selector Valve - OFF

,....--...._

5.

Keep

wings

level

during

touchdown.

6.

Get clear

of

the airplane as soon as possible

after

it

stops.

April

1982

3-7

Section

III

Emergency

Procedures

SYSTEMS

EMERGENCIES

PROPELLER OVERSPEED

1. Throttle -

RET

ARD TO

RED

UNE

2. Airspeed - REDUCE

3.

Oil

Pressure - CHECK

WARNING

BEECHCRAFT

Debonair33

lf loss of oil pressure

was

the cause

of

over-

speed,

the

engine

will

seize

after

a short period

of operation.

4. Land

- SELECT NEAREST SUITABLE SITE

and

follow

LANDING EMERGENCIES procedure.

GENERATOR

OUT PROCEDURE

A

failure

of

the

generator

will

place the

entire

electrical

operation

of

the

aircraft

on

the

battery.

Generator

failure

may be indicated by

the

ammeter.

When a generator

failure

occurs

in

flight

, all non-essential electrical load

,,....-..,.

should be discontinued

to

conserve

the

battery life. - '-

LANDING

GEAR

MANUAL

EXTENSION

Manual

extension of

the

landing gear can be facilitated

by

first reducing airspeed. Then proceed as follows:

1. LOG GEAR Circuit Breaker - OFF (PULL OUT)

2. Landing Gear

Switch

Handle - DOWN position

,,...-.....

3.

Handcrank Handle Cover (at rear

of

front

seats) -

REMOVE

3-8

April

1982

BEECHCRAFT
Debonair33

Section

III

Emergency

Procedures

4. Handcrank - ENGAGE and TURN COUNTERCLOCK-

,..-.... WISE AS

FAR AS POSSIBLE (approximately

50

turns)

CAUT/ON

The

manual

extension system is designed

to

lower

the

landing gear only.

DO

NOT

ATIEMPT

TO RETRACT THE GEAR MANUALLY.

5.

lf

electrical system is operative, check landing

gear

position lights and

warning

horn

(check LDG GEAR

INDICATOR and LDG GEAR WARNING

circuit

breakers

engag

ed)

.

6. Check mechanical landing gear indicator -

DOWN

7.

Handcrank - DISENGAGE.

Always

keep

it

stowed

when

not

in

use

.

WARNING

Do

not operate

the

landing gear electrically

with

the

handcrank engaged, as damage

to

the

mechanism could occur.

After

emergency

landing gear extension, do

not

move

any

landing gear controls

or

reset any

switches

or

circuit breakers

until

airplane

is

on

jacks as

failure

may

have been in

the

gear

up

circuit

and gear

might

retract

on

the

ground.

LAN

DING GEAR RETRACTION AFTER PRACTICE

MANUAL

r"°'\

EXTENSION

After

practice

manual

extension

of

the

landing gear,

the

gear may be retracted electrically, as follows:

1.

Handcrank - CHECK, STOWED

2. Landing Gear

Motor

Circuit

Breaker - IN

3. Landing Gear - RETRACT

April

1982

3-9

Section III

Emergency Procedures

UNLATCHED DOOR IN FLIGHT

BEECHCRAFT

Debonair33

lf

the

cabin door is

not

locked it may come

un

latched

in

flight.

This may

occur

during

or

just

after

take-off. The

door

wi

ll

trail

in a position

approximately 3

inches

open,

but

the

flight

characteristics of

the

airplane

will

not

be affected,

except

that

rate of

climb

will

be reduced. Return

to

the

field

.---

in a normal

manner

. lf practicable,

during

the

landing

flare

-out

have a passenger hold

the

door

to

prevent

it

from

swinging

open.

SPINS

Spins

are

prohibited. lf a

spin

is

entered inadvertently

:

lmmediately

move

the

control

column

full

forward

and

simultaneously

apply

full

rudder opposite

to

the

direction

of

the

spin;

continue

to hold

this

control

position

until

rotation stops

and

then

neutralize

all

controls

and execute

a

smooth

pull

ou t.

Ailerons

should

be

neutral

and

throttle

in

idle posit

ion

at all

times

during

recovery.

EMERGENCY

SPEED

REDUCTION

In

an

emergency,

the

landing gear

may

be used

to

create

additional drag.

Should

disorientation

occur

under

in-

strument

conditions,

the

lowering

of

the

land

ing

gear

will

reduce

the

tendency

for

excessive speed

build-up.

This

procedure

would

also be appropriate

for a non-instrument

rated

pilot

who

unavoidably

encounters

instru

ment

condi-

tions

or

in

other emergencies such as severe

turbulence.

Should

the

landing gear be used at speeds

higher

than the

max

imum

extension speed, a special

inspection

of

the

gear

doors

in

accordance

with

shop

manual

procedures is re-

quired,

with

repair as necessary.

3-10

April

1982

BEECHCRAFT

Debonair33

SECTION

IV

NORMAL

PROCEDURES

TABLE OF

CONTENTS

SUBJECT

PAGE

Speeds for Safe Operati

on

. . . . . . . . . . . . . . . . . . . . . . . 4-3

' Preflight lnspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4

-4

B

efore

Starting

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-7

Starti ng . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4- 7

After

Starting

and Taxi . . . . . . . . . . . . . . . . . . . . . . . . . .

4-9

Before Take-Off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4-9

T

ake-Off

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-11

Cl

imb

..........................

.

.........

.

...

. . 4-11

Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-11

Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 1

Before Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-

12

Balked Landing

........

. .

.....

. . .

..............

4-12

After

Landing

......

.............

. . .

..........

..

4-12

Shutdown

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4-13

Environmental Systems . . . . . . . . . . . . . . . . . . . . . . . . .

4-13

Cold

Weather Operation

. . . . . . . . . . . . . . . . . . . . . . . .

4-13

lcing Conditions

....

.........

. . . . . . .... .

........

4-

15

Engine Break-in Inform a

tion

. . .

.........

........

4-15

April

1982

4-1

BEECHCRAFT

Debonair33

Section IV

Normal Procedures

All

airspeeds

quoted

in this section are indicated airspeeds

(/AS)

AIRSPEEDS

FOR SAFE

OPERATION

Take -off

Lift-oft

..............................

67

kts/77 mph

50

Ft.

..............................

73 kts;84

mph

Maximum

Climb

Best Rate (Vy) . . . . . . . . . . . . . . . . . . . . .

90

kts/ 1

04

mph

Best Angle

(V

xl

.....................

71

kts/

82

mph

Cruise

Climb

..................

.

....

113 kts

/130

mph

Maximum

Turbulent

Air

Penetration . . . . . . . . . . . . . . . . . . . . . . .

123

kts/

142

mph

Balked Landing Climb

.................

70

kts/

81

mph

Landing Approach

.....................

70

kts;81 mph

Maximum

Demonstrated

Crosswind

...........................

17

kts/

20

mph

April

1982

4-3

Section

IV

Normal

Procedures

PREFLIGHT

INSPECTION

Emergency Locator

Transmitter -ARMED

Location may vary

with

individual airplanes

1.

CABIN:
a. Parking Brake - SET
b.

Control Lock - REMOVE

c.

All

Switches

- OFF

2.

RIGHT FUSELAGE:

BEECHCRAFT

Debonair33

a.

Baggage Compartment Door - SECURE

b.

Static Pressure

Button

- UNOBSTRUCTED

4-4

April

1982

BEECHCRAFT

Debonair33

SectionlV

Normal

Procedures

3.

EMPENNAGE:

a.

Control Surfaces -

CHECK

...___/

b.

Tie Down - REMOVE

c. Position Light -

CHECK

4.

LEFT

FUSELAGE:
a. Static Pressure Button - UNOBSTRUCTED
b.

All

Antennas - CHECK

5.

LEFT

WING TRAILING

EDGE:

a. Flap -

CHECK

b. Aileron -

CHECK

c.

Wing Tip -

CHECK

d.

Position Light - CHECK

6.

LEFT

WING LEADING EDGE:

a.

Stall Warning -

CHECK

b.

Pitot Tube -

CHECK,

(Remove Cover)

c.

Fuel Tank(s) -

CHECK

OUANTITY; Filler Cap(s) -

SECURE.

d. Cabin

Air

lntake - CHECK

e.

Tie Down and Chocks - REMOVE

7.

LEFT

LANDING GEAR:

a.

Wheel Weil Door, Tire and

Strut -CHECK

b.

Fuel

Vent

- CHECK

,

..-r--

c.

Fuel Sump(s) - DRAIN

d. Fuel Selector Valve Sump and Auxiliary Fuel Cell

lnterconnect Line -

DRAIN; Cover -

SECURE

April

1982

4-5

Section

IV

Normal

Procedures

8.

NOSE SECTION:

BEECHCRAFT

Debonair33

a.

Engine Oil - CHECK (See Servicing, Section 8) Cap

~

and Dipstick - SECURE /

b.

Left Cowl - SECURE
c. Propeller - CHECK, General Condition, Nicks, etc.
d.

Landing Light - CHECK
e.

Wheel Weil Doors, Tire and

Strut

- CHECK

~

f. lnduction

Air

lntake - CLEAR

g.

Engine -

CH

ECK GENERAL CONDITION
h. Right Cowl - SECURE
i. Chocks - REMOVE

9. RIGHT LANDING GEAR:
a.

Fuel

Vent

- CHECK

b.

Fuel Sump{s) - DRAIN

c.

Wheel

Weil Door, Tire and

Strut

- CHECK

10

. RIGHT WING LEADING EDGE:

a. Tie

Down

and Chocks - REMOVE

b. Fuel Tank(s) - CHECK OUANTITY; Filler Cap(s) -

SECURE

~

11

. RIGHT WING TRAILING EDGE:

a.

Po

sitio

n Light - CHECK

b.

Wing

Tip - CHECK

c.

Aileron

- CHECK

d. Flap - CHECK

CAUTION

NEVER

TAXI

IF

ANY STRUT IS FLAT.

4-6

April

1982

,-..

BEECHCRAFT

Debonair33

BEFORE

STARTING

Section

IV

Normal

Procedures

_./

1. Seats - POSITION

AND

LOCK;

Seat

Backs - UPRIGHT

2.

Seat

Belts

- FASTEN

3.

Parking Brake - SET

4.

All

Avionics

- OFF

~

5.

Circuit

Breakers - IN

6. Land

ing

Gear Handle -

DOWN

7. Flaps - UP

8. L

ight

Switches -As

Required

9.

Fuel Selector Valve - CHECK OPERATION;

S!=LECT

~

LEFT

MAIN

TANK.

10.

Battery

and

Generator

Switches

- ON (

lt

externa l

power

is used,

turn

Generator

Switch

- OFF. See

Sections 7 and 8)

11. Fuel

Quantity

lndicators

- CHECK QUANTITY

WARNING

Do

not

take

oft

if

gages

indicate

in

yellow

arc

or

with

less

than

13

gallons

in

each main tank.

STARTING

CAUTION

Vern

ier-type

engine

controls

should

not

be

rotated

clockwise

after

being advanced

to

the

full

forward

position.

1.

Mixture

- FULL AICH

2. Propeller - HIGH RPM

3.

Throttle -Approximately

1;2

inch

open

April

1982

4-7

SectionlV
Normal Procedures

NOTE

BEECHCRAFT

Debonair33

lf

the

engine is hot,

and

the

ambient

tempera-

ture

is

90°F

or

above, place mi

xture

control

in

IDLE CUT-OFF,

switch

auxiliary

fuel

pump

to

ON

for

30

to

60

seconds.

then

OFF. Return

mixture

control

to

FULL RICH.

4.

lgnition

Switch

- BOTH

5.

Auxiliary

Fuel Pump - ON (

until

fuel

pressu re stabilizes

then

OFF

).

6.

Starter

Button

- Press

until

engine

starts.

CAUT/ON

Do

not

engage Starter

for

more

than

30

seconds

in

any

4-minute

period.

7.

In

the

Event

of

Overprime

Condition:

a.

Mixture

- IDLE CUT-OFF

b.

Throttle

- OPEN

c.

Starter

Button

- PRESS

d.

As

engine

starts

reduce

throttle

to

IDLE

and

advance

mixture

to

FULL RICH

NOTE

During

hot

starts. if

there

is

an

indication of

vapor

in

the

fuel

system

(fluctuating

fuel

pressure

),

switch

the

auxiliary

fuel

pump

to

ON

to

purge

the

system. Then

turn

it

OFF.

8.

Throttle -1000

to

1200

rpm .

9.

Oil Pressure - CHECK

-

10. External Po

wer

(if used) - DISCONNECT.

Generator

~

Switch

- ON

11.

All

Engine lndicators - CHECK

4-8

April

1982

BEECHCRAFT

Debonair33

Section

IV

Normal

Procedures

CAUTION

The

ammeter

indication

should

be less

than

.25 charge at

1000

to

1200

rpm

within two

minutes,

with

no

additional electrical equip-

ment

on.

lf

not, this

indicates a

malfunction

in

the

electrical system

and

the

airplane

should

be

shut

down

.

AFTER

STARTING,

AND

TAXI

1. Brakes - RELEASE

AND

CHECK

2.

Avionics

Equipment

- ON,

AS

REQUIRED

3.

Lights -AS

REQUIRED

CAUTJON

Do

not

operate

engine

above

1200

RPM

until

oil

temperature

reaches

75°F

(24 °C).

/'

BEFORE

TAKEOFF

1. Parking Brake - SET

2.

Seat Belts and

Shoulder

Harnesses - CHECK

NOTE

All

reclining

seats

must

be in

the

upright

posi-

tion durin

g takeoff.

3.

Avionics

- CHECK

4. Engine

Instruments

- CHECK

5.

Flight

Instruments

- CHECK

AND

SET

April

1982

4-9

Sect

ionlV

Normal Procedures

BE

ECHCRAF

T

Debonai

r33

6.

Ammeter

- CHECK -

for

stabilized

indication

betwe

en 0

and .25

charge

at

1000

to

1200

rpm. Ammeter

sho

uld

show

some

decrease

from

the

initial

indication

.

7.

Auxiliary

Fuel Pump - CHECK OFF

8.

Throttle -1900

RPM

9.

Propeller

- EXERCISE

to

obtain

300

to

400

rpm

drop

;

return

to

high

rpm

10. Magnetos

- CHECK

at

1700

rpm

(variance

between

i

ndividua

l magnetos should n

ot

exceed

50

rpm,

maxi-

mum drop n

ot

to exceed 150 rpm.)

11. Tr

im - S

ET

a.

Aileron

- NEUT

RAL

(if

ins

talled )

b.

El

evator - 0° (3°

nose

up

if

only front

sea

ts

are

occup

ied)

12. Fl

aps - Check

operation, then UP

13.

Doo r

and

Windows

- SECURE

14.

Controls

- CHECK PROPER DIRECTION AND FREE-

DOM

OF

MOVEMENT

15. Mixture

- FULL RICH (or

as

required

by

field elevatio

n)

16. Brakes

- RELEASED

17.

Instrume

nts - CHECK

(M

ake

final

check

of

manifo

ld

pre

ssure,

fuel

pressure

, a

nd rpm

at

the

start

of

the

take-

off

run.

)

4-10

April

1982

BEECHCRAFT

Debonair33

TAKE-OFF

SectionlV

Normal

Procedures

Take-

Off

Power . . . . . . . . . . . . . . Full Throttle,

2600

rpm

1. Power - SET TAKE-OFF POWER

(Mixture

- SET as

required by

field elevation)

2.

Brakes - RELEASE THEN ACCELERATE to recom -

mended speeds

3.

Landing Gear - RETRACT

(when

positive rate of

climb

is

established and

insufficient

runway

remains

for

landing)

4.

Airspeed - ESTABLISH DESIRED CLIMB SPEED

(when

clear

of

obstacles)

CLIMB

Maximum

Continuous

......

..

. Full

throttle,

2600

rpm

Cruise Climb . . . . .

25

in. Hg (or

full

throttle)

2500

rpm

1. Engine Temperatures - MONITOR

2.

Power - SET

AS

DESIRED.

3.

Mixture

- SET FUEL PRESSURE

~

CRUISE

See Cruise Charts in PERFORMANCE Section.

1. Power - SET

,,.-....,

2.

Mixture

- SET FUEL PRESSURE

DESCENT

1.

Altimeter

- SET

~

2.

Power -

AS

REQUIRED (avoid prolonged idle settings

and

low

cylinder head tempera-...ires)

3.

Mixture

- ENRICH

AS

REQUIRED

April

1982

4 -

11

SectionlV
Normal

Procedures

BEFORE

LANDING

1.

Seat Belts - SECURE

NOTE

BEECHCRAFT

Debonair33

All recli ni

ng

seats rnust

be

in

the

upright

posi-

ti

on

during

landing.

2. Fuel Selector Valve - SELECT

MAIN

TANK

MORE

NEARLY FULL

3.

Mixture

- FULL RICH (or as required by field elevation)

~

4. Landing Gear - DOWN and CHECK. (Observe
rnaxirnurn

extension

speed)

5.

Landing Light -

AS

REQUIRED

6.

Flaps - DOWN (Observe rnaxirnurn

extension

speed)

7.

Airspeed - ESTABLISH LANDING APPROACH SPEED.

8.

Propeller - HIGH RPM

BALKED

LANDING

1. Power - FULL THROTILE,

2600

RPM

2. Airspeed -

70

kts/81 rnph

until

clear

of

obstacles, then

trirn

to

normal clirnb speed

3. Landing Gear -

UP

4. Flaps - UP

AFTER

LANDING

1. Landing Light -

AS

REQUIRED

2. Flaps -

UP

3. Trirn Tab - SET TO

0°

4-12

April

1982

BEECHCRAFT
Debonair33

SectionlV

Normal

Procedures

SHUTDOWN

1.

Brakes - SET

2. Electrical

and

Radio

Equipment

- OFF

3.

Throttle

- CLOSE

4.

Mixture

- IDLE CUT-OFF

5. lgnition

Switch

- OFF,

after

engine

stops

6.

Battery

and

Generator

Switches

- OFF

7. Control Lock - INSTALL,

if

conditions

warrant.

8. lnstall

wheel

chocks and release brakes

if

the

airplane

is

to be left

unattended

.

ENVIRONMENTAL

SYSTEMS

HEATING

AND

VENTILATION

Refer

to

the

SYSTEMS DESCRIPTION Section

for

op-

eration

of

heati ng and

ventilation

controls.

COLD

WEATHER

OPERATION

PREFLIGHT INSPECTION

All

accumulations of ice,

snow

and

frost

must

be

removed

from

the

wings

, tail,

control

surfaces and hinges,

pro-

peller,

windshield, fuel

cell

filler

caps, crankcase vents.

and

fuel

vents. lf

such

accumulations

are

not

removed

completely,

the

airplane shall

not

be

flown

. The deposits

will

not

blow

off

in

flight. While

an adverse

weight

factor

is

clearly

involved

in

the

case of heavy deposits,

it

is less

obvious

that

even slight

accumulations

will

disturb

or

com-

pletely destroy

the

designed aerodynamic properties

of

the

airfoils.

The normal

preflight

procedures

should

then

be

com-

pleted,

with

particular

attention

given

to

check

of

flight

controls for

complete

freedom

of

movement.

April

1982

4-13

Section

IV

Normal

Procedures

ENGINE

BEECHCRAFT

Debonair33

Use engine oil

in

accordance

with

Consumable

Materials

in

the

HANDLING, SERVICING

AND

MAINTENANCE Sec-

tion .

Always

pull

the

propeller

through

by hand, opposite

the

direction

of

rotation, several

times

to clear

the

engine

and

"limber

up"

the

cold, heavy

oil

before using

the

starter.

This

will

also !essen

the

load

on

the

battery

if

ex-

ternal

power

is

not

used.

Under

very cold conditions,

it

may

be necessary

to

preheat

the

engine prior to a start.

Particular

attention

should

be

given to the

oil cooler, engine sump and propeller

hub

to

ensure proper preheat. A

start

with

congealed oil

in

the

system may produce

an

indication

of

normal

pressure

im-

mediately

after

the

start,

but

then

the

oil pressure may

de-

crease

when

residual

oil

in

the

engine

is

pumped

back

with

the

congealed oil in

the

sump.

lf

an

engine

heater

capable

of

heating

both

the

engine

sump

and cooler is

not

available,

the

oil should be drained

while

the

engine

is

hot

and stored

in a warm

area

until

the

next

flight.

lf

there

is

no

oil pressure

within

the

first

30

seconds

of

running, or

if oil pressure drops

after a few

minutes

of

ground operation,

shut

do

wn

and check

for

broken

oil

lines, oil cooler leaks

or

the

possibility

of

congealed oil.

NOTE

lt

is advisable to use external

power

for

start-

ing

in

cold

weather.

During

warm-up,

monitor

engine

temperatures

closely,

since it

is

quite

possible to exceed the

cylinder

head

temperature

limit

in

trying

to

bring

up

the

oil

temperature.

Exercise

the

propeller several

times

to

remove cold oil

from

~

the

pitch

change mechanism. The propeller

should

also be

cycled occasionally in

flight.

4-14

April

1982

BEECHCRAFT

Debonair33

Section

IV

Normal

Procedures

During

letdown

and landing,

give

Special

attention

to

en-

gine

temperatures,

since

the

engine

w ill have a

tendency

toward

overcooling.

ICING

CONDITIONS

Flight

in

lcing

Conditions ls Prohibited.

ENGINE

BREAK-IN

INFORMATION

See Section 7, Systems

April

1982

4-

15

BEECHCRAFT

Debonair33

SECTION

V

PERFORMANCE

TABLE

OF

CONTENTS

SUBJECT

lntroduction

to Performance and

PAGE

Flight Planning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-3

Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5-3

Comments Pert i

nent

to

the Use

of

Performance Graphs . . . . . . . . . . . . . . . . . . . . . . . . . .

5-9

Airspeed Calibration - Normal System . . . . . . . . . . . 5

-10

Altimeter

Correction - Normal System . . . . . . . . . . . 5-

11

Fahrenheit

to

Celsius Temp

erature

Conversion . . .

5-12

I

SA

Conversion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5-13

Stall Speeds - Power ldle . . . . . . . . . . . . . . . . . . . . . . .

5-14

Wi

nd

Compone n

ts

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5-15

Take-Off Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5-16

/"

Climb .

........

.....

........

.....

....

...

......

. .

5-

17

Time, Fuel and Distance to Climb . . . . . . . . . . . . . . . 5-

18

Cruise Power

Settings

75

% MCP (Or Full Throttle) . . . . . . . . . . . . . . . . .

5-19

65

% MCP (Or Full Throttle) . . . . . . . . . . . . . . . . .

5-20

55% MCP (Or Full Throttle) „ „ „ „ „ „ „ „ . 5-

21

45% MCP (Or Full Throttle) .

..........

.

.....

5-22

Cruise Speeds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-

23

Manifold Pressure vs RPM . . . . . . . . . . . . . . . . . . . . . .

5-24

Fuel F

low

vs

Brake Horsepower . . . . . . . . . . . . . . . . . 5-

25

Fuel Flow vs Fuel Pressure . . . . . . . . . . . . . . . . . . . . . 5-

26

Range Profile -

63

Gallons . . . . . . . . . . . . . . . . . . . . . .

5-27

Range Profi

le -44

Gallons . . . . . . . . . . . . . . . . . . . . . .

5-28

April

1982

5-1

SectionV

Performance

BEECHCRAFT

Debonair33

TABLE

OF

CONTENTS

(Continued)

SUBJECT

PAGE

Endurance Profile -

63

Gallons . . . . . . . . . . . . . . . . .

5-29

Endurance Profile -

44

Gallons . . . . . . . . . . . . . . . . .

5-30

Landing Distance .

.......

.

......................

5-31

,.......,_

5-2

April

1982

BEECHCRAFT

Debonair33

SectionV

Performance

INTRODUCT

ION

TO

PERFORMANCE

AND

FLIGHT

PLANNING

The graphs and tables

in

this

section

present

performance

i

nformation

for fl i

ght

planning

at

various

parameters

of

weight,

power,

altitude

and

temperature.

Examples

have

been presented

on

all

performance

graphs. In addition,

the

calculations

for

flight

time, block speed and fuel

required

for a proposed

flight

are

detailed

below. All

examples and

calculations

utilize

the

follow

ing conditions:

CONDITIONS

At

Denver:

Outside

Air

Temperat

ure

. . . . . . . . . . . . .

15

°C (59°F)

Field Elevation . . . . . . . . . . . . . . . . . . . . . . . . . .

5330

ft

Altimeter

Setting

. . . .

........

. . . . .

...

29.60

in. Hg

Wind

........................

. . . „

270°

at

10

kts

Runway

26L

length ...

........

..

........

10,010

ft

Route

of

Trip

*DEN-VS 1

-AMA

For VFR Cruise at

11

,500

feet

ROUTE

MAGNETIC

DIST

SEGMENT

COURSE

NM

DEN-COS 161°

55

COS-PUB

153°

40

PUB

-TBE

13~

0

74

TBE-DHT

132°

87

DHT-

AMA

125°

65

WIND

OAT

11500

11500

FEET FEET

DIR/KTS

oc

010/30

-5

010/30

-5

100;20

0

200;20

9

200;20

10

*REFERENCE: Enroute

Low

Altitude

Chart

L-6

April

1982

ALT

SETTING

IN.HG

29.60

29.60

29.56

29.56

29.56

5-3

SectionV
Performance

At

Amar

illo:

BEECHCRAFT

Debonair33

Outside

Air

Temperature . . . . . . . . . . . . .

25°C

(77°F)

Field Elevation . . . . . . . . . . . . . . . . . . . . . . . . . .

3605

ft

Al

timeter

Setting

......

.

.........

....

29.56

in. Hg

Wi

nd

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 80°

at

1 0 kts

Runway

21

Length . . . . . . . . . . . . . . . . . . . . .

13500

ft

To

determine

pressure

altitude

at

origin

and

destination

airports, add

100

feet

to

field

elevation

for

each

.1

in. Hg

below

29. 92, and subtract

100

feet

from

field

elevation

for

each .1 in.

Hg

above 29.92.

Pressure

Al

titude

at DE

N:

29.92 -29.60

= .

32 in.

Hg

The pressure altitude at DEN is

320

feet

above

the

field

elevation.

5330 + 320 = 5650

ft

Pressure

Altitude

at

AMA:

29.92 -29.56 = .36

in. Hg

The pressure

altitude

at

AMA

is

360

feet

above

the

field elevation.

5-4

3605 + 360 = 3965

ft

NOTE

For

flight

planning,

the

difference

between

cruise

altitude

and cruise pressure

altitude

has

been ignored.

April

1982

BEECHCRAFT

Debonair33

SectionV

Performance

Calculations

for

flight

time,

block speed and

fuel

requirement

:

Cruise

Climb

:

Enter the graph for TIME,

FUELAND

DISTANCE TO CLIMB

at 1 5°C

to

5650

ft

and

to

2900

lbs. Enter

at -5°C

to

11 ,500

ft

and to

2900

lbs. Read:

Time

to

Climb =

(22

- 9) =

13

min

Fuel Used

to Climb

= (6.2 - 2.5) = 3.7 gal

Distan

ce Traveled = (45 - 18) =

27

NM

The c

ruise pow

er setting is assumed to be

at

2450

rpm.

Since

cruise

at

11,500

feet requires

full

throttle, the

manifold

pr e

ssure

and

fuel

flow

should

be read

from either

the cruise

power

setting table

for

75

percent

or

65

per

-

cent

maxi

mum

continuous

power.

The

temperatures

for cruise are presented

for

a standard

day

(ISA);

20°C

(36°F) above a standard day

(ISA+ 20°

C);

and

20°C

(36°F)

below

a standard day (ISA -

20°C).

These

should

be used for

flight planning.

The IOAT values

are

true

temperature

values

which

have been adjusted

for the

compressibility effects. IOAT

should

be used for

setting

cruise

power

while

enroute

.

,---.......

Enter the graph

for

ISA

conversion at

11

,500

feet

and

the

temperature

for

the

route

segment

:

DEN

-PUB OAT

-5

°C

ISA

Condition

ISA+

3° C

~

PUB-TBE OAT

0°C

=

ISA Condition =

ISA+

8° C

TBE-DHT OAT

= 9°C

ISA

Condition

=

ISA+

17

°C

~

DHT-AMA

OAT

10°C

ISA Condition

ISA+

18

°C

April

1982

5-5

SectionV
Performance

BEECHCRAFT

Debonair33

Enter

the

cru ise

power

settings table

for 75%

maximum

co

ntinu

ous

power

(or

full

throttle)

at

10,000

ft,

12,000

ft,

ISA

and

ISA + 20°C.

TEMPERATURE

ISA

ISA+

20°c

FUEL FUEL

ALTI-

MAN

. FLOW

MAN

.

FLOW

TUDE

PRESS . PSI/

TAS

PRESS.

PSI/

TAS

FEET IN.

HG

GPH

KNOTS

IN.

HG

GP

H KNOTS

1

0000

20

.1 6.1/12.0

156

20

.1

5.6/11.2

155

12000

18

.6

5.5/11

.1

154

18

.6

5.

1/10.5

152

lnt

erpolate

for

11,

500

feet

and

the

temp

erature

for

the

appropriate

route

segment

. Results

of

the

interpolations

are:

5-6

MAN.

FUEL

ROUTE

PRESS . FLOW

TAS

SEGMENT

IN.

HG

PSl/GPH

KNOTS

DEN-PUB

18

.9

5.6/11 .2

154

PUB-TBE

18

.9 5.5/ 11.1

154

TBE-DHT

18.9

5.3

/ 10.8

153

DHT

-AMA

18

.9 5.3/10.7

153

NOTE

The above are exact values

for

the

assumed

condit

ions.

April

1982

BEECHCRAFT

Debonair

33

SectionV

Performance

Time and fuel used

were

calculated as

follows:

Time

= Distance

Ground

Speed

Fuel Used

=(Time)

(Fuel Flow)

Results

are

:

EST

GROUND

ROUTE

DISTANCE

SPEED

SEGMENT

NM

KNOTS

DEN-COS

*

28

183

COS-PUB

40

180

PUB-TBE

74

139

TBE-DHT 87 141

DHT-

AMA

65

143

FUEL

TIME

AT

USED

CRUISE

FOR

ALTITUDE

CRUISE

HRS: MIN

GAL

0:09 1.7
0:

13

2.4

0:

32

5.9
0:37 6.7
0:

27

4.8

*Distance required to

climb

has been subtracted

from

segment distance.

TIME

- FUEL -

DISTANCE

TIME

FUEL

DISTANCE

ITEM HRS:

MINS

GAL

NM

Start

, Runup,

Ta

xi and Take-

off

acceleration

0:

00

1.7 0

Climb

0:

13

3.7

27

Cruise 1:

58

21.5

294

Total

2:

11

26

.9 321

April

1982

5-7

SectionV
Performance

To

tal Flight Time: 2 hours,

11

minutes

BEECHCRAFT

Debonair33

Block Speed: 321

NM

+ 2 hours,

11

minutes = 146

knots

Reserve

Fuel (45

minutes

at

45%

maximum

continuous

power)

Enter

the

cruise

power

Settings

table

for

45%

MCP (or

full throttle). The fuel

flow

for

45%

MCP

is

8.3

gallons

per

hour

.

Reserve

fuel =

(45

min)

(8.3 GPH) =

6.2

gallons

Total Fuel = 26.9 + 6.2 = 33.1 gallons

The estimated landing weight is

determ

ined by

subtracting

the

fuel

required for

the

trip

from

the

ramp

weight

:

Assumed

ramp

weight = 2910

lbs

Estimated

fuel

from

DEN to

AMA = (26

.9 gal) (6 lbsjgal)

=1611bs

Estimated landing

weight = 2910

- 161 =

2749

lbs

~

Examples have been provided

on

the

performance

graphs.

The above cond

iti

ons have been used

throughout.

Rate of

climb

was

determined

for

the

initial

cruise

altitude

conditions.

5-8

April

1982

--

BEECHCRAFT

Debonair

33

SectionV

Performance

COMMENTS

PERTINENT

TO

THE

USE

OF

PERFORMANCE

GRAPHS

1.

The example,

in

addition

to

presenting

an

answer

for

a

particular

set

of

conditions,

also

presents

the

order

in

which

the

graphs should

normally

be used, i.e.,

if

the

first

item in

the

example is OAT.

then

enter

the

graph

at

the

known

OAT.

2. The reference

lines

indicate

where

to

begin

following

guide

lines. Always

project

to

the

reference

line

first.

then

follow

the

guide

lines

to

the

next

known

item

.

3.

lndicated airspeeds (IAS)

were

obtained

by using

the

AIRSPEED CALIBRATION

NORMAL

SYSTEM Graph.

4. The associated

conditions

define

the

specific

conditions

from

which

performance

parameters

have

been determined. They

are

not

intended

to

be used as

instructions

,

however

,

performance

values de-

termined

from

charts

can only be achieved

if

specified

conditions

exist.

5.

The

full

amount

of

usable

fuel

is available

for

all

~

approved

flight

conditions

.

April

1982

5-9

Cf

.....

0

230

200

220

100

210

190

200

1

70

if

190

~

180

s 170

~

~

1

60

~

1

60

!!!

~

1

40

„

5 1

30

120

3

110

I!?

~

1

60

~

150

w

~

140

~

1

30

~

120

„

5

11

0

~100

1

00

90

90

80

l>

90

70

„

~

70

60

.....

CO

CO

N

)

AIRSPEED

CALIBRATION -NORMAL

SYSTEi\11

EXAMf>LE

~

INDICATED A IRSPEEO

ASSUMES

ZERO INSTRUMENT EA

ROR

~

90

KNOTS

l104

MPH)

FLAPS DOWN

FLAPS

UP

:

:

60

70

eo

90

100 110 120 1

30

140

150 160 170

1 190

200

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1

70

80

90 100110120130140

150 160

170 1801

90

200

210220230

IAS • INDICATEO

AIRSPEED.....,

MPH

)

)

230
220

210

200

if

190

~

190

~

'70

~

l2

160

~

160

~

140

„

5

130
1

20

3

110
1

00

90
80

70

190

180

170

!!?

~

160

1 160

0

~

140

l2

~

130-

0

~

120

~110

' 100

3

90

eo

70
60

CAS

88

KNOTS

(101 MPH

I

FLAPS DOWN

60

M

90 ~ 1001W120130140

IAS

• INOICATEO AIRSPEED

......

KNOTS

~

,-----,--1 1

--

1 „

--

1 ,- 1

10

eo

oo

100

110

t20130140

iso

160

IAS

• INDICATEO AIASPEEO

rv

MPH

) )

)

"'tl

cn

m m

:::i.

n

0 - ·

... 0

3

:::1

QI

<

:::1

n
m

aJ

m

Om

m

C1

C"

::i::

0

C1

;

:J:J

::;

· l>

~~

)>

"O

2:

....

CO

00

...,

'!'

....

....

)

)

)

)

)

)

ALTIMETER

CORRECTION

-

NORMAL

SYSTEM

NOTE.

IND

ICATEO AIRSPEEO ANO I

NDI

CATED ALTITUDE A SSUM E

--

ZE

RO INST

AUMENT

ERROR

üI

30

0

liii"

~~

20

"<:

10

z"

o ~

65 °

~~

-10

8~

C::o:

·20·

~~

::;u

-30·

~~

-40

::>

!!!

-

50·

FLAPS

UP

50

60

10

so

90

100

1io

120

1:io

14<>

150

160

170 1

80

190

200

IAS -

INDICfEO

AIRSPEED ~ KNOTS

1 '

1'1•1'1'1'I'11 1'1'

1'I'I'1' 1'

1 '

1•1

60

70

80

90

100

110 120

130

140 150

160

170

180

190

200 210 220 230

IAS -INDICATEO AIRSPEED ~ MPH

-

80

EX

AMPL

E

IAS

F

LAPS

IN

OICATEO

PRESSUAE

ALTITUO

E

A

LTIM

ETER CORRECTlON

AC

TUA

L PRESSURE A L TITUOE

FLAPS DOWN

112 KNOTS

UP

5

000 FEET

10

FEET

- 5

000

10

:.

4990

FEE

T

50

60

70

80

90

100

110

120

130

140

IAS

- INOICATEO

AIASPEED

rv

K

NOTS

T

'1

' 1 ' 1 ' 1 ' 1 ' 1 ' 1 1 I

1 1 1

I

60

70

80

90

100 110

120 1

30140

150 1

60

IAS - !NOICATED AIRSPEED

rv

MPH

0

IJJ

CD

m

er

m

0

(')

il

::c

::;·

(')

w

l:J

w

)>

.,,

-4

-:

:::i.

tn

0

CD

...

(')

3

=·

I»

0

:J :J

g <

Section

V

Performance

BEECHCRAFT

Debonair33

1 e

~

~I

:zi

,

0 2 0 2 2 0 0 0

..t)

'"

(")

n - 1

"'!

7 1 1 1

:J S

33H

!l30

5-12

A

pril

19

82

,,.-...,

BEECHCRAFT

Debonair33

w

""

~

:c

~

z

...

!

0

....

""

"'

;(

a::

c

w

:'.!

>

~

z

0

0

~

>

u

c

<

2

~

"'

c(

w

""

;;:

"'

w

""

...

§

,,;

"'

April

1982

SectionV

Performance

u

j-;-+-1,,

"""'

-r+

-+

~

ol

UJ

a::

·

".:.-!"'--

-+-

-.,...;<:-~

.Y..-i-'

,o.+'f-r+

0

~

.133~

-

30n.Ll.L

111

31lnSS3ijd

<!

a::

UJ

+-

..1'1'1+++

0

0..

I~

,_

0

5-

13

'!1

....

.i:a

~

'tJ

::!.

....

<D

CX>

N

STALL

SPEEDS -POWER

IDLE

"!Qlli_

1

TH[

MAXIM

UM

ALTITUOE LOSS

EXPER

IENCEO

WHILE

CO

NOUCTIN(i

STALLS

IN

ACCOROA

NCE

WITH CAM

3 120 WAS 200 rT

2

ANORMAL

STALL

RECOVERY

TECHNIOUE

MAY

BE

USED

2800 2600

2400

2200

WE

IGHT ~POU

NDS

)

\.

)

)

2000

0 10

20

30

40

50

60

ANGLE

OF

BANK~DEGREES

)

S:tia1~fE

FLAPS

ANGLE OF BANK

STALL SPEED

90

100

BO

90

V>

....

I

0

„

z

::;

70

l

80

~

0

w

w

w

w

„

„

"'

"'

70

::l

60

::l

;!

;!

"'

"'

60

50

1

50

40

)

2600

LBS

UP

30

"

62

KNOTS

7 1 MPH

)

"O

Cfl

CD CD

:::i.

~

0

-·

... 0

3

:s

III<

:s

0

CD

o:J

o~

CD

(')

CT

:I:

g

(')

III

lJ

=-·~

w

"Tl

w

-1

~

/".

BEECHCRAFT
Debonair

33

SectionV

Performance

WIND

COMPONENTS

Demonstrated

Crosswind

Component

is

17

kts

EXAMPLE:
WINOSPEED

ANGLE BETWEEN WIND OIRECTION ANO

FLIGHT

PATH

HEADWIND COMPONENT

CROSSWIND COMPONENT

F

LIGHT

PATH

V>

....

20

0

z

:.l

....

z

w

10

z

0

Q.

:::;;

0

u

0

z

~

0

0

..:

w

X

.10

0

April

1982

10

20

CROSSWINO COMPONENTS

30

KNOTS

20

KTS

500

13 KTS

15 KTS

5-

15

(J1

.

.....

Ol

l>

"C

~

.....

Cl)

(X)

N

TAKE-OFF

DISTANCE

ASSOCIATED CONOITJONS

EXAMPLE

OAT

POWER

MIX

TURE

FLAPS
LA NDI

NG

GEAR

J5,J.3.KC14

FULL

THROnLE

2600

RPM

LEAN

TO

APPAOPAIATE

FUEL PAESSURE

UP

AETAACT A

FTE

R POSITI VE

CU

MB ESTAB

USHED

~'<

~

10'<

"'

p..\.~\~\)

ISA

sv~'<

~~'<s

lt

IH

WEIGHT 1 TAK

E O

FF

SPEED

LIFT-OFF 1 50

FT

POUNDS KNOTS

MPH

KNOTS M

PH

2900

67

77

73 84

2800

66

76

72 83

600

63 73 69 79

1

~ 4

00

1

60

1 69 1 66 1

76

1

2200

58

67

64

74

w

z

_,

w

(.)

1

a:

PRESSURE

ALTITUDE

TAKE OFF W EIGHT
HEAO WIND

COMP

GROUND ROLL
TOTAL DISTA

NCE

OVER

A

!:10

FT

OBST A

CLE

TAKE OFF SPEED AT

UFT OFF

50

FT

'

~

~

..

•

~d:P,

~

S'-

-40

.30 -20

-10 0 10

20

30

40

50

28

00

2800 2400

2200

OUTSI

DE

AIR

TEMPERATURE

"'°C

•

WEIGHT

,...., POUN

DS

1 1 1 1 1 1 1 1 1 1

,--i-

1-11-.--1

-40 -

20

0

20

40

60

so

1

00 120

OUTSIDE A IR

TEMPEAATUA

E,.....°F

)

)

)

)

15 C

159

Fi

5650

FT

2900

LBS

9 5 KNOTS

1900

fEET

-""

1

67 KN

OTS

(77

MPH)

">

~

-:!!/

73 KNOTS (8d

MPHI

#«.&°

A.~

.,_

"(q

~

~

9""q;f

0

w ~ w

;;f.!:>

V'.

A.'<J

z

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ffi

~

ffi

s f?

tt;

tli

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a:

a:

0 10

20

30 0

50

WI

ND CO

MPONENT

OBSTACLE HEIGHT

rv

KN

OTS

rv

FEET

8000

5000

4000

ffi

i

3000

~

~

2000

1

000

0

)

)

'V

"'

CD

CD

:i.

!l

0

-·

....

0

3

::::1

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g

al

m

Cm

CD

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CT

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III

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l>

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w -1

""'!

)>

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:!.

......

c.D

Cl)

N

C11

'

......

-.J

)

)

ASSOCIATED CONOITIONS

POWER FULL THR

OTI

LE

AT

2600

RPM

)

)

CLIMB

EXAMP

LE

OAT

}

MIXTU

RE

LEAN TO APPRO

PRJ

ATE

FUEL PRESSURE

CUMB

SPEED

90

KNOTS (ALL WEIGHTS)

PRESSUAE ALTITUDE

WEIGH

T

FLAPS UP
L.A

NDtNG GEAR UP

z

~

1

"'

"

~

0

s

1

04

MPH

400

300

200

1

00

I

Llllldl

l l

i.llll

lllllllli

i! lllcil

llli

1

II

II

'"

"'

'fli

. 1 1 1 1 1 1 1 1 1

-70

-60 .50

-40 -30

-20 -10

0 10

20

30

4{)

50

O

UTSIDE

AtR TEM

PEAATUAE"'

0

c

1

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1

-80 -60

-40

·20

0

20

40

60

80

100 120

OUTSI

DE

AIR TEMPEAATURE

"'

0

f

IIJ

T

2800

3S,

33KC

16

RA

TE OF-CUMB

CUMB G

RADIENT

CUMB SPEED

13

00

1200

\\

00

1

000

z

900

~

800

2

"'

700

"

:J

~

6

00

0

llimmm

1

s

1500

4

00

3

00

200

100

~

o

2600 2400

2200

WEIGH

T

rv

PO

UNDS

13
12

11

10
9

B

7
6
5

5° C 123°

F)

11500FT

2878 L8S

4

70

FT,MIN

43

%

)

90 KNOTS

(104

MPHI

...

1

ffi

0

~

"

"'

" a

0

IJJ

CD

m

a-

m

0 (")

;

::z::

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(")

w l:J

w

)>

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CD

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.

Q)

0

:::1 :::1

g <

01

'

-'

CO

)>

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::!.

-'

c.o

CO

1\)

ASSOCIATED

CO

NDITIONS T

IME

, FUEL

AND

DIS

TANCE

TO

CLIMB

EXAMPLE

POWER

FUEL OENSI

TV

MIXTU

R[

)

2&

IN

t l

(i

OR

fULL T

HROTILE

2600 RPM

GO

ll!GAL

CU

MB

SPEED 113 KNOTS

130 MPH

OAT

AT TAKE-O FF

OAT AT CRUI

SE

AIRPORT PRESSU

RE

ALT!TUDE

CRUISE PRESSURE A LTITUOE

IN

ITI

AL

CUMB

WEIGHT

Lf

l\N

10

Af>

PROPRIAT

E

FUEL

PRESSUAE

,._,

-

i<ifmi

,\

·

:;:rn~.·

,'dm

-50

-40 ·

30

-20 -10

10

20

30

40

50

60

OUTSID E AIR TEMPERATUREf'v° C

1 1

. ., 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1

~ ~ ~

o w m w

oo 100

1w

1m

OUTSIDE A

IR

TEMPERATUAE

"'o

F

)

)

T

IME

T0

CLIMB (22-91

FUE:l TO C

UMB (6.2-2.5)

DISTANCE

TO

CLI

MB (45-18)

,;

·

~

.;,~~

q,~

'

,

~:

-

w

;

-i

~

21

0Q.

10

20

30

40

TIM

E TO C

LIM

ßrvM

INUT

ES

f t

1 ' l 1 1

'l

'l'T 1 T

'l

r

l"'-

1'1

0 1 2 3 4 5 6 7 B 9 10

FU

EL TO

CUMB"'GALLO

NS

t . t

f T ) r·

r-T1--

·1

1 1 1 1 1 1

111

0

10

20

30

40

50

60

70

80

OISTANCE

TO CLIMB"'NAUTICA

L MILES

)

2900

)

1s0c (59°

F)

-5

°C (23°

FJ

5650 FT

11

soo

n

2900

LBS

13

MIN

3.7

GAL

27

NM

)

.,,

CJ)

ai ai

:::i.

0

0 :!'.

... 0

3

:l

~

<

0

ai

liJ

m

Om

ai

()

C" :J:
0

()

~

lJ

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l>

~~

l>

"C

::!.

_.

(!)

00

N

01

'

_.

(!)

'

)

) )

'_

)

CRUISE

POWER SETTINGS

75%

MAX

IMUM

CONTINUOUS

POWER

IOR

FULL THROTTLE)

@

AVERAGE

CRU

ISE

WEIGHT • 2700

LBS

.

ISA

-36°F

(-20°C)

STANDARD

DAY

llSAI

PRESS

ENGINE

MAN.

FUE

L

ENGINE

MAN.

FUEL

ALT. OAT

SPEED

PRESS

FL

OW

T

AS

OAT

SPEED

PRE

SS FLOW

T

AS

OAT

OF j

oC

.

PS

I IG PHIKTSI

MPH

oFloc

PSI IGPH

KTSIMPH

oF

/oc

FEET

RPM

IN

HG

RPM

IN

HG

SL

211 - 3

2450

23.4 7.3 113.411461 168 631

17

2450

24

.0 7

.3 113.4

149

2000

201 - 7

2450

22.9

7.3 113.41

148

NOTES

1.

F

ULL

THRO

TTLE

MANIFOLD PRESSURE SETTINGS

ARE

APPROXIMATE.

2.

SHADED

AREA

REPRESENTS

OPERATION WITH

FULL

THROTTLE.

)

()

I

SA

+36°F

l+20°cJ

ENGINE

MAN. FUEL

SPEED PRESS

FLOW 1 TAS

RPM I N

HG

-~-

cm

CD

m

CT

m

0

(")

;

:J:

::;·

(")

CtJ

:IJ

CtJ

l>

"TI

~

~

~

Cl>

0

CD

...

(")

3

:::!'.

Q) 0

~

~

~

<

'f

N

0

)>

'C

::!.

_.

(.0

(X)

N

CRUISE

POWER SETTINGS

65%

MAXIMUM

CONTIN

UOUS POWEn (OR

FULL THl10TTLE)

@

AVERAGE CRUI

SE

WEIGHT

• 2700 LBS.

I

SA -36°F (-2

0°c1

STANC:rARD

OAY (ISA

) I

SA

+36°F.. (+20°CJ

PRESSI IE

NGIN

EI

MAN

. I

FUEL

A<Cf.

OAT

SPEED PRESS

FLOW

TAS

ENGI

NEIMAN. I

FUEL

OAT

1 SPEED PRESS

FLOW

ENGI

NEIMAN

. I

FUEL

TAS

- 1

OAT

1 SPEED PRESS

FLOW

FEET

1 ° F j

0

c 1 'RPM

!IN

HG

°F 1°c

1 RPM

iiN

HG 1 PSI

IGPHIKTSIMPH

1°Fi0c 1 RPM

SL

26

- 3

2li50• 21

.2

5.8

11.5 1

37

158

62

17

2450

21.7 6.8 11.5 140

162

98

37

2450

2000

19 - 1 2450 20.7

5.8

11.5

140 161

55 13 24

50

21.3

6.8

11

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165

91

33

2450

4

000

12

11 2450

20.3

5.8

11.5 14 2 164

48

9

2450

208

5.8 1

1.5

145

167

84

29 2450

6000

5

15

2450 19 .8

5.8

11.5

145

167 41

5

2450

20.4 6.8

11

.5

148

170 77 25

2450

8000

- 2

19

2450

19.4 5.8 11.5

147 170

34

1

2450 19.9 6.8 11.5

151

174 70 2 1 2

450

• 1

10

000

- 9

23

2450 18.9 5.8 11.5 150 173

27

- 3 2450

19.5 6.8

11.5

153 177

@'.•

'

17

245()

12000

- 16

27

2450 18.5

5.8

11

.5 153

176

2()

;~

7

W

24!1!!

18.6 M

11

.1

164

'

'1itij·

116

,3

2450

!

f4000

-23

- 31

24$0 ...

·~

xr&

'

.

5.J

10

.9

151 174

13

-f1

'.

%i45o

17

.3

s.o

10

.3

150

l,73

49

9 2450

lßOOO

-30

-

35

2450

16.0

4.9

10.1

148

170

(1

..;.

j!j

24$0

160

46

9.6 141;

.16$

41

6

246()

NOTES:

1.

FULL

THROTTLE

MANIFOLIJ

PRESSURE SETTINGS

ARE

APPROXIMATE

.

2. SHAOEO

AREA

REPRESENTS

OPERATION

WITH

FULL THROTTLE

)

)

)

)

)

TAS

1

65

168
171

174

)

"tl

ff)

CD CD

::i.

~

0

-·

„ 0

3

:s

C»

<

:s

0

CD

IJJ

m

Cm

CD

(')

er

:I:

g

(')

C»

:JJ

::;·

)>

w .,,

w

-4

J>

"O

==

...

CD

CO

N

Cf

N

...

)

PRESS

ALT

.

O

AT

FEET

OF

oc

SL

26

--4

20uu 19

7

4ono

p - 11

1>000

5 - 15

9nnn

- 2 -19

10000 -10

- 23

L7U00

- 17 - 27

14000

24

31

NOTES

:

)

)

CRUISE

POWER SETTINGS

55%

MAXIMUM

CONTINUOUS

POWER (OR FULL THRO

TTL

E>

@AV

ERAGE

CRUISE WEIGHT =

2700

LBS.

ISA

-36"F

(-20°c1

STANDARD

DAY (ISA>

ISA

+36°F

(+20°c>

ENG

INE

MAN.

FUEL

ENGINE

MAN.

FUEL

ENGINE

MAN.

FUE

L

SPEED PRESS FLOW

TA

S

OAT

SPEED PRESS FLOW

TAS

OAT

SPEED PR

ESS

FLOW

TAS

RPM

IN

HG

PSI GPH

KTS

MPH

oF

oc

RPM

IN

HG

PSI

GPH

KTS

MPH

oF

oc

RPM IN HG

PSI

GPH

KTS

IMPH

2300

20.2

4. 7 9.8

128

147

62

17

2300

20.7

4.7 9.8 131

150

98

37

2300

2 1,1 4.7

9.8 133 1

53

2300

19.7 4. 7

9.8 130

150

55

13

2300

20.3 4.7 9.8 133 153

9 1 33

2300 20.7

4.7

9.8

135

156

2300

19.2

4.7 9.8

132 152

48

9

2300

19.8 4.7

9.8

135

155 84 29

2300

20.2

4.7

9.8 138

158

2300

18

.7

4

-,

9.8 1

35

155 41 5

2300 19.3

4.7

9.8 137

158

77 25

2300 19.8 4. 7

9.8

140 161

2300

1

8.2

4.7

9.8

137 157

34

1

2300

18.8 4.7 9.8

140

161

70

21

23

00

19.3 4.7 9.R

14?

11>4

2300

17

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139

160

27

- 3

2300

18.3 4.7

9.8

14

2

163

63

17

2300

18.8

4

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9.8

144

166

2300

17.3 4

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9.8

141

163

20-

17

.9

4.7 9.8 144 166 ....

13

23()1) 11.•

""

„

.• , ...

187

2300

16.8 4

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9.8 143

165

-

-·~

1:1....,.

-·-111111

~

.~"u~

-t3.iit~j..,

~!J2

"-~~"

~

~~-',:

~~

•u,~

- V

·~<:::

~

»

-"-•

II

~

.&r

,\"l'

•i<

:

i<!!°t',

„.

1.

FULL

THROTTLE

MANIFOLD

PRESSURE

SETTINGS

ARE

APPROXIMATE

.

2.

SHADED

AREA

REPRESENTS O

PERATION

WITH

FULL THROTTLE

.

c

CJJ

CD

m

o-

m

0 (")

;

:J:

:::;·

(")

w l:I

w

J>

'l1

CD

~

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(/)

0

CD

... 0

3

=::!'.

C»

0

:J :J

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<

C1I

'

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)>

"C

::!.

...

U)

00

"'

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.1

PRESS

ALT.

OAT

FEET

oF

oc

SL

25

4

2000

18

- 8

4

000

11

- 12

600

0 4 - 16

8000

- 3 - 20

10

000

~10

- 23

12000 >-17 - 27

14

000 >-24 31

i

11111W

·=·

~2

NO

TES•

•

CRUISE POWER SETTINGS

45% MAXIMUM CONTINUOUS

POWER

(CR

FULL

THROTTLE

)

@I

AVERAG

E CRUISE

WEIGHT • 27

00 LBS.

ISA -

36°F 1-20

° c1

STANDARD DAY (ISA)

ENG

INE MAN.

FUEL

ENGINE

MAN.

FUEL

SPEED PRESS

FLOW

TAS

OAT

SPEED PRE

SS

FLOW

TAS

OAT

RPM

IN

HG PSI GPH

KTS

MPH

OF

oc

RPM

IN

HG

PSI

GP~

KTS Ml'H

Of

OC

.

21

00

20

.0

4.0

8.3

116

134 6 1 16 2100

20.

4 4.0 8.3 119

136 9 7

36

21

00

19.5

4.0 B.3

118

1

36

54 12 2 100 19.9 4.0

8.3 120

139

90

32

2100 19.1 4.0 8.3 1

20

138

47

9

2100 1

9.5

4.0

8 3

122

141

83

29

21

00 18.6

4.0 8.3 122 140 40

5 21

00

19.1 4.0 8.3 124

142

76 25

2

100

18.2

4.0

8.3

123 142 33 1 2100 18.7

4.0 8.3 125 144

69

21

2 100 17.7 4.0 8.3

125 144

26 - 3 2 1

00

18.2

4 .0 8.3 127 146

62

17

2 1

00

17.3

4

.0

8.3

126 146

19

- 7

2100

k<L7;,

~

~

4.0

8.

3 128 148

55 13

21

00

16.8

4.0

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i!l

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'

12

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1cio

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3.9 8.2 128

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9

ttoo

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2:100

,,,tl

3.8

7.

ll

1111

~)7

3$

3

1. FU

LL

THR

OTTLE MANIF

OLD PRESSURE SETTING

S A RE APPRO

XIMATE

.

2. S

HAO

ED AREA

REPRESEN

TS OPERAT

ION WI

TH FULL THROTTLE.

)

)

)

I

SA

+36°

F 1

+20°c1

ENGINE

MAN .

FU

CL

SPEED PRE SS F

LOW

RPM

IN

HG PSI GPH

2

100

20

9 4.0 8 .3

2100

20

.5 4.0

83

2100

2

00

4.0

8.3

21

00 19.5 4.0

8.3

21

00

19.1

4.0

8.3

2 1

00

18

.6

4.0

8.3

2 1

00

18.2

4.0

8 3

.2Hl0.

17~

3.8

7.9

2100 16.0

3.6

7.5

)

TAS

KT!

MPH

1

21

139

122

14

1

124 1

43
126 145
127 1

46
128 1

48

129 149

i2

1

t"!

l

0

)

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t/)

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g

0

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er

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BEECHCRAFT

Debonair

33

ASSOCIAT

ED

CONOITIO NS

CRUISE

SPEEDS

SectionV

Performance

AVERAGE CAUISE

WEIGHT

2700

LBS

EXAMPLE

~EALTITUDE

POWER

SETIING

l1

500FT

TEMPERATURE STANDARD

OAY

(ISAI

FULL

THROTILE

]450

RPM

rnue

AIRSPEED

154

KNOTS

16

000

15000

1

400

0

13000

12000

11000

~

UJ

UJ

10000

u..

2

UJ

9000

Cl

:;)

~

5

8000

<(

UJ

7000

a:

:;)

Cf)
Cf)

6000

UJ

a:

a._

5000

4000

3000

Q

Q

ii:'

ii:'

(J

(J

<

<

(J

(J

<

~

*

<;'?

<;'?

<;'?

.,,

.,,

Jg

~

~

~

i

i

i

f

a:

a:

a: a:

g

g

:X :X

-

"'

~

~

"'

"'

"'

2000

1000

Q.

Q.

1-

w

l::

l::

1-

·

"'

Q)

w

Q)

Q)

Q)

w

"'

Q)

"'

Q)

;.

~

~i

!! "

0

2

....

.

,.

SL

1 1 1

110

120

130 140

150

160

TAUE AIRSPEED

rv

KNOTS

April

19

82

5-23

UI

1

1\)

'"

l>

'tl

3.:

...

CD
CIO

1\)

(!)

:i:

z

?

w

a:

::>

V)

fil

a:

„

9

Ir

z

"

:;

)

25

24

23

22

21

20

19

18

1700

18

00

)

MANIFOLD

PRESSURE

vs

RPM

NOTRECOMMENDED-FOR

CRUISE

SEITING

1900

2000

2100

2200

2300

24

00

25

00

ENGJ

NE SPEED

,...,APM

)

)

EXAMPLE

EN

GINE

SPEED

2450

RPM

MAN!FOLD PAESSURE 18.9 IN

HG

WITHIN AECOMM ENDED

LIM

ITS

2600

)

)

'tl

Cf)

CD

CD

:::i.~

0

-·

... 0

3

::i

III<

::i

(')

CD

CD

m

Om

CD

(")

CT

::C

0 (")

~

::u

::;·

l>

w .,,

w

.....

_.

.,..--.....,

~

~

a:

BEECHCRAFT

Debonair33

SectionV

Performance

FUEL

FLOW

vs

BRAKE

HORSEPOWER

EXAMP

LE

<D

BRAK

E HORSEPOWER

14

6.3

CONOITION

(65% MC

P)

L

EVEL FLI

GHT

CRUISE LEAN

FUEL F

LOW

11.4 GAlJHA

12>

FUEL

FLOW

11

.0

GAlfti

A

CONDITION

LEVEL FLIGHT
CRUISE LE

AN

BRAKE HORSEP

OWER

„,

22

21

20

19

18

75

%

17

TAKE-O

FF

16

AND

CLI

MB

'§-

65%

<(

15

<.:J

2

;!

14

i

13

-'

w

~

12

11

10

55

%

CR

UISE

45%

80

90

100 110

120 130

140

150 160

170

180

190

200 210

220 230 240 250

BRAKE H

OASEPOW

ER

April

1982

5-

25

Section V

Performance

BEECHCRAFT

g;

1

w

<:

"'

w

"'

~

u:

::>

...

5 -

=

·-::;::

~

FUEL FLOW

vs

FUEL

PRESSURE

EXAMPLE

DebonairJJ

,.----.....

.....,...,

-

-

I+

.....

..,.

.....;

„

~

FUfl

FLOW

....,

......

......;_

~

-'-"

=

'

~

-.:.

~I

10 6

G

A~HR

~

.....

15-

--

t:l:

14

13

r-

12

II

IQ

c

8

Cl

....

,.._

....

r-

-.....

=-

....

~'

-

-

EE!e:t:

:t:

,,_

"'--'

._

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f--

.....

...;

......

-

-

...;.;

........

'""

-'

-.;

"""'-'

::;::

~

"-

"-

-'

-.;

'""

'-'

--i..;._

'"""'

......

-

-

-

......

-·

.....

~

-

,.,_

tt

....

....,

..,...

1:

-

-"

,....;.

.......

...

-

-=

--.;;

......

'-"

....

„

-~

-

,.,_

-

-4

3

._;_

1

5

5-

26

-

-.

+<

...........

-;-

7

8

t:t

1

10

FUEL fLOW""GAUiR

II

12

41-4

i....."

„

~·

13

'

'""

14

15

16

17

18

April

l

19

20

1982

III

:::

~

y-...._

l>

'tl

:::!.

....

(.0
()1)

N

U'I

'

N

-.J

)

)

)

)

RANGE

PROFILE -

63

GALLONS

STANDARD

OAY

llSAl

ASSOCIATED CONDITIONS

WEIGHT

2910

LBS

BEFORE

ENGINE

START

~

FUEL AVIATION GASOLINE

F

UEL

DENSITY

6 0 LBS GAL

INITIAL

FUE

L LOAOING

63

U.S GAL (

378

LBS)

20000

....

w

~

15000

?

w

RANGE

INCLUDES START, TAXI, ANO

CUMB

WITH

45 MINUT

ES RES

ERVE

FUEL

AT 45, MCP

.

,'))

)

)

EXAMPLE

PRESSURE ALTITUOE 11500

rT

POWER SETTING FULL THROTTLE

2450

RPM

RANGE 715 NM

0

:::;)

t::

~

1

0000

-

1<\'-~

CRUISE

TRUE

°'-Y.,

~0

AIRSPEED

rv

KNOTS

~~~

<(

w

a::

~P.

~~!::1™:

15

1

140

125

:::;)

Ul
Ul

5000

w

a:

0..

-

\:l

"

<:!

SL~

550

600 650

700

750

800

850

900 950

RANGE

rv

NAUTICAL MILES

(ZERO

WIND)

om

CD

m

c:r

m

0

C')

;

J:

::;· C')

w

lJ

w

)>

„

CD

~

~ C/)

0

CD

...

0

3

~.

111

0

:::J

:::J

g <

(11

""

00

l>

"O

::!.

....

<D

00

"'

RANGE

PROFILE -

44

GALLONS

ASSOCIATED CO NDITIONS

WEIGHT 2910 LBS

BEFORE

ENGINE

START

FUEL AVIATION GASOLINE

FUEL

OENSlfV 6 0

LBS~AL

INITIAL

run

LOAOING

44

u s

GAl.

(26

4 LBSI

)

20000

tü

~

15000

<

w

0

=>

....

5

10000

<!

U.J

a:

=>

cn
cn

w

lt

5000

SL

)

300

350

)

STANDARD

OAY

llSAI

~

RANG(

INCLUDES START. TAXI

ANO

CLIMB

WITH

45

MINUTE$

RESERVE FUEL

AT 45"Jii

MCP

IU

·

~~

0 Q.

a: a:

:r 0

.... 0

_,"'

_,"'

~

500

CRUISE TRUE
AIR

SPEED"'

KNOTS

tl

550

600

RANGErvNAUTICAL

MILES (ZERO WIND)

)

EXAM

PLE

PRESSURE

ALTI

TUOE

POWER

SEmNG

RANGf

650

)

-~

!;l

fl

ö

700

ll

SOOFT

FULL T

HROnLE

24

50

RPM

452 NM

)

-o

rn

III III

:::i.

~

0

-·

... 0

3

::1

g:

<

n

III

m

m

Om

III

(')

er

J:

0

(')

;

:JJ

:;·

l>

w.,,

w

-t

)>

'O

::::!.

...

to

CO

N

U1

.

N

to

)

)

)

)

ENDURANCE

PROFILE -

63

GALLONS

ASSOCIATEO CONOITIONS

WE

IGHT

2910

LBS

BEFOAE

ENGINE START

FUE

L

AV1AT

l0 N GASOLINE

FUEL DENSITY

6 0 LBS'GAL

INITIAL FUEL LOAOING 63 U.S GAL (378 LBSI

20000

t;:;

-

STANDARD

OAY

(ISA)

NOTE

ENDURANCE INCLUDES START. TAXI. ANO

CLIMB

WlTH

45

MINUTES RESERVE FUEL AT

45~

MCP

~

~'?~

::tti:t(.~

'),,,,~

,1:9

'),

~

~v"-.

~

~v"-

~o..'A-1

...

~

)

)

EXAMPLE

PRESSURE AL TITUDE

11

500

FT

POWER

sen1NG

FULL

THROTILE

2450

RPM

ENDURAN

CE

4 7 HOURS

(4

HOURS

42

MINUTE$)

~

15000

?

w

0

::i

1-

o~'?~~

"

J.

~O

,_D<„m

0""

0

'-0'-"'

-

~

154

" >r,44

·

,s„"

'<

CRUISE

TRUE

5 1

0000

<(

w

a:

::i

(/)

(/)

w

a:

0..

50

00

SL

-

-

-

-

-

3

.5

...,_y.'?'-

(!)

!i

~0':'.I

-;

;l!t 1

58

151

140

s

0..

(/)

'b

u·

0..

\f,

~

155

~

145

(.)

135

tr

i

~

l~

~

~

~

"'

149 140

\P

H131

1

1

1

4.

0 4.5

5.0

5.5

6.0

E

NDURANCE ~ HOURS

128

AI

RS

PE ED"-'

125

3-

~~

i

""'"119

1

6.5

7.0

KNOTS

7.5

,J

:

)!!

l;l

i

~

8.0

c

lll

II>

m

cr

m

0 (")

;

::c

::;·

(")

c.>

::0

c.>

)>

"tJ

II>

.,,

-1

:::i.

rn

0

II>

... 0

3 :?.

III 0

~ ~

g <

'f

w

0

)>

"O

:::!.

_.

tO
00

N

ENDURANCE

PROFILE •

44

GALLONS

ASSOCIATEO CONOITIQNS.

STANOARO

OAY

!ISAI

WEIGHT

2910

LOS

ß(fQAE

ENGINE STAAT

FUEL

AVIATIQN GASOLINE

NOTE

FUEL

OENSITV

6 0 LBS

GAL

INITI

AL f UH

LOAOING 44

US

GAL

(;>611

LUSI

EN5iJRANCE

INC

LUOES

S 1 AIH TAXI AND CLIMB

WITH

45

MIN

UTES R($[ nvr 1

Vll

AT 450..

MCP

)

9

u.

2

w

0

E

~

<(

w

a:

::>

"'

"'

w

a:
a.

20000

15000

.

5000

-

SL

.

1

2.0

)

d

117

1

1

2.5 3

.0

3.5

4.0 4.5

5.0

ENDURAN

CE"'

HO URS

)

)

5.5

~

PRESSURE ALTITUOE

11500

fl

POWER SETIING

FULL

TH!l01

lll

2450

RPM

ENOURAN

CE

3 02 HO

URS

1

pi

l;l

"'

'l

~

6.0

)

(3 HOUAS 1

MINUrt)

1.

"2

C/)

~

ä.

... 0

3

:s

~

<

g

°'

m

Cm

CD

(")

C"

::c

g

(")

m

:J:J

::;·

)>

w

"Tl

w

-i