Piper aircraft corporation Cherokee pa-28-180 Technical specifications

--

----

-

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--

----

-

---··

--·-

-·

-- ···-

-·

·-··-·

·-

- ·- ·-

···-

···--·-···--··---·

··

-···

--·

-·

""

··--

··

·

--

--~-------.

Pl PER

·A

I RGH

~

Fi f J

~

P

f--rH=..

C KE:.:.:

~--------------

Ar-P::.:>OvLt;

REPORT

VB-163 ,

FA.GE

-----·--

DUPLICATE

AIRPLANE

FLIGHT

MANUAL

MODEL

PA

-28-180

SERIAL

NOS. 671 THRU

5600

FAA

IDENTIFICATION

NO.

------

SERIAL

NO.

28-5043

THIS

DOCUMENT

MUST

BE

KEPT

IN AIRPLANE

AT

ALL

TIMES.

FAA

APPROVED:

Original

signed

by

Walter

R.

Haldeman*

Walter

R.

Haldeman

'

Chief,

Engineering

&

Manufacturing

Branch

Southern

Region

~

-

-Atlanta,

Georgia

DATE:

August

3,

1962

FAA

APPROVED:

C..e.u.

~7--

Gene

Dearing

·

Aerospace

Engineer

.

For

Retype

Only.

DATE:

August

12, 1964

VH-CHJ

THIS AFM HAS BEEN EDITED TO INCLUDE CONVERTED UNITS OF

MEASUREMENT THAT ARE COMMONLY USED WITHIN AUSTRALIA,

ADDITIONAL OPERATIONAL LIMITATIONS THAT ARE FOUND IN THE

PIPER OWNER’S HANDBOOK (PIPER P/N: 753-765) AND ANY OTHER

DOCUMENTS THAT ARE APPLICABLE BY AIRCRAFT SERIAL

NUMBER, ISSUED BY PIPER AIRCRAFT OR RELEVANT AUTHORITY.

j

~

REP

A

~

"?

i:::

D

i

~-------

I

_J

I

1 C..H E

CKEG

!

l

-!

-AP_

P

_R-

0

\/

i':

C.

'

I

i

'

i

I

!

I

--------

I

REVISION

NO.

1

2

3

PAGE

1

2

P I P t R A :

D.C

p

A'

~

T

I I\ I

~

, I G0RP

Dr;• r l

O"t'E''T

f'

'''Trn

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1~

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r...

t L 1

...

1 , u n L . •

~

•

L..

.

....

u

...

d .,,

RE?ORT

VB

-163

DESCRIITION

Airplane

Flight

Manual

Model

PA-28-180

P /

\GE

_ __!!_

__

_

APPROVED

DATE

Dele

.

ted

Propeller

Pitch

Jnforma-

,II~·

W

a

t~

an

tion.

Added

Static

R.P.M.

~~P!~visor

f

Information

SO-EMD0-42

5/25/64

Placards

Section:

~

Added

Placard

No.

5

Supervis

or

7/

8/ 64

Added

to

Placard

No.

3:

·

~~~

·

"BAGGAGE,

MAX.

200

LBS.,

z¥csupervisor

8/5/64

SEE

WEIGHT

AND BALANCE

SO-EMD0-43

.

DATA

FOR

BAGGAGE LOADINGS

BETWEEN

150

LBS

. AND 200

LBS."

l 1

Added

Sensenich

M76EMMS

4 3

5 1

6 1

7 2

4

2

FAA

APPROVED

8/3/62

Item

5

add

ed

to

Pro

c

edures

Section.

Limitations

Section:

Revised

Oil

Temperature

and

Fuel

Pressure

Range

Limitation

Section:

Add

note

to

Engine

Limits

C.

G.

Range:

1975lbs.

85.9

In.

95.9

In.

1650

lbs

.

84.0

In.

95.9

In.

Was

18.50

lbs.

85.1

In.

95.9ln.

Added

Procedures

Section

And

Item

6

Added

Placard

No . 6

Supervisor,

SO-EMD0-43

10/20/64

/d_~l/5/66

/

l~~erv1sor,

SO-EMD0-43

.'J

~

•

Up~

5/20/66

~rvisor

SO-EMD0-43

l

PREPARED

CHECKED

APPROVED

Revision

No.

8

9

l()

..

1

2,3

5

6

1

2,3

4

3

1

2

FAA

APPROVED

8/3/62

PIPER AIRCRAFT

CORP

D[VHOPM[NT

CENHR,

HRO

BEACH,

FLA.

Airplane

Flight

Manual

Model

PA-28-180

RE

PORT VB-103

Description

Revised

Oil

Temperature,

Oil

Pressure

and

Fuel

Pressure

Limitations

Revised

Pla

cards

No . 3

and

No.

5

Added

Page

5

Procedures

Section

-

Added

Item

7

PAGE

III

Approved

Date

Added

Page

6 /

-/

[

/

~

,

I

7./l

'"

c_

;(

("~.

"Henry

C.

Falier

7/15/66

"

Supervisor

Limitations

Section

Add

"or

0-360-A4A

C.

G.

Range

-

Placard

·

No. 1

and

Placard

No.

3

revised

to

include

utility

category

operations.

SO-EMD0-43

Added

utility

category

max.

wt.

an

d

appro

v

ed

maneuvers

Procedures

Section

-

Added

to

Item

3

"For

Normal

Category

Operation·:

Added

Placard

No. 7.

Placards

Section

-

Added

utility

category

operation

to

Item

4.

Added

Utility

Category

Added

maximum

positive

irt

rtd

JJj

:

load

factor

for

Utility

4"

·

G-{}'aCf~l2

/6 1

66

Category.

Added

Baggage

pervtsor

Capacity

.

0-

EMD0-43

PIPER

AIRCRAfT

COIP

CHI:CI<EO

OEYELOPMUT

CEMTEI,

YUO

BUCN,

fll.

Airplane

Flight

Manual

Model

PA-28-180

-~

REPORT

VB-163

PAGE

IY

1

~--------L-----~~~~----~~==~~~

REVISION

NO.

11

12

13

14

15

16

17

PAGE.

3

2

3,

4

1

Title

1

FAA

APPROVED

8/3(62

DESCRIPTION

Placards

Section:

Revised

Placard

No. 1

to

read,

"In

Full

View

of

the

Pilot"

Revised

C. G.

Range

Revised

Placard

No. 4

and

No. 7

to

read:

"In

full

view

.of

the

pilot"

Added

Aircraft

Serial

Numbers

1571

and

1573

to

Engine

and

Propeller

Limitations

Added

Propeller

Designations

Allocated

Piper

Report

No. VB-163

to

thls

Manual.

Added

Applicable

Serial

Nos.

1

Thru

4377

Added

Supplement

No. 1

APPROVED

DATE

~f{:IL

5/12/67

SO-EMD0-43

i

;{~/~5/67

/

~

rVIsor

0-EMD0-43

//,~4/2/68

/@~rVISOr

SO--EM00-43

1

L_~6/3/68

/

'i!~rvisor

SO-EMD0-43

!J.~

6/24/68

Supervisor

SO-EMD0-43

_

JJ.m-:{~e_~

'

Herb· M.

To~n'iey

1

lltJ

'//,

~

FAA

OOA

SO-l

'(~

.AI

c

JJ.

yn. t

_,..y')ff

H.

M.

Toomey

FAAOOAS0-1

L/1nJ~p1

.

l

r----------..-----------------~-------·

·

-

REVISION

NO.

18

19

20

21

22

PAGE

Title

2

FAA

AFPROVED

3/3/62

, IPEI A

II

CIAf J C

II

P.

Airplane

Flight

Manual

IEYELIPIEIT

CEITEI,

YEll

IUCI,

FLA.

Model

PA-28-180

REPORT

VB-163

DESCRIPTION

Changed

applicable

Serial

Nos.

from

1

thru

4377

to

1

thru

5600.

Changed

applicable

Serial

Nos.

from

1

thru

5600

to

S

71

thru

56'00.

Added

Forward

Ir1termediate

and

Forward

Gross

Weight

Points

Deleted

Forward

Intermediate

and

Forward

Gross

Weight

Points

Changed

oil

pressure

gauge

markings

PACE

v

APPROVED

DATE

.

=t]

l\\-

IG-n11~

'M~Itq

H.

M.

Toomey

U I

FAA DOA

SO-l

-jj.

n~~~

·

1/2J/t1

H.

M.

Toomey

FAA OOA

SO-l

'

0).

h'

·I

cnn.tS-Il-9'2

ht

H.

M.

Toomey

(/

FAA

DOA

SO-l

J1j1...,_

C?~~

9/l'f/11.

/~.c~.._Stephe;

l" ·-·

FAA

DOA

SO-l

tJtSA

d

Gv~

7-2s-7s

.......

I ...,,.,.

1.

Limitations

Section

Engine

Limits

Fuel

ProJ)eller

Power

Instruments

FAA APPROVED

8-3-62

REVISED

7-25-75

PIPEI

AIICIAFT

CliP .

IEYUIPIEif

CflfEI,

tEll

IUCI,

FU.

REPORT VB-163

Airplane

Flight

Manual

Model

PA-28-180

Pill

1

of

6

Piper

Model

PA-28-180

.

Normal

and

Utility

Category

4. 4

Utility

Category

No

inverted

maneuvers

approved.

2400

lbs

-

Normal

Category;

150

lbs

-

Utility

Category.

200

lbs

The

datum

used

is

78. 4

inches

ahead

of

wing

leading

edge

at

the

intersection

of

the

straight

and

tapered

section.

1.

No

_

rmal

Category

Forward

Limit

Weight

(Pounds)

(In. Aft

of

Datum)

2400

2200

1975

1650

2.

Utility

Category

92. l

89~

2

85.9

84.0

Weight

Forward

Limit

(Pounds)

(In. Aft

of

Datum)

1950

85.8

1650

84.0

Rearward

Limit

(In. Aft

of

Datum)

94.5

95.9

Rearward

Limit

(In.

Aft

of

Datum)

86.5

Straight

line

variation

between

points

given.

NOTE:

It

is

the

responsibility

of

the

airplane

owner

and

the

pilot

to

insure

that

the

airplane

is

properly

loaded.

See

weight

and

section

for

proper

loading

instructions.

1.

Normal

Category

-All

acrobatic

maneuvers

including

spins

prohibited.

2.

Utility

Category

-

Approve~

maneuvers

for

Utility

Category

only.

Spins

(Flaps

Up)

••••••.•

Steep

Turns

•••••.••••••

Lazy

Eights

•••••••••••

Chandelles

.••••••••••••

Entry

Speed

Stall

129

mph

129

FAA

APPROVED

8/3/62

REVISED

9/14/70

Rev.

No.

21

KIAS

148 |

121 |

122 |

100 |

1088.6 KGs 844.5 KGs

90.7 KGs

KIAS

112

PIPER AIRCRAFT CORP.

CHI[CKI[O

OEYELOPMUT

CUHI,

VERO

BEACH,

FLA.

Airplane

Flight

Manual

Model

PA-28-180

REPORT

VB-163

PAGE

3

of

6

l

~------~--------------~~~==~

l

Placards

l.

In full

view

of

the

pilot:

"THIS

AIRPLANE MUST

BE

OPERATED

AS

A NORMAL OR

UTILITY

CATEGORY AIRPLANE

IN

COMPLIANCE WITH

THE

OPERATING

LIMITATIONS

STATED

IN

THE

FORM

OF

PLACARDS, MARKINGS

AND MANUALS.

ALL

MARKINGS AND PLACARDS

ON

THIS AIRPLANE APPLY

TO

ITS OPERATION

AS

A

UTILITY

CATEGORY AIRPLANE. FOR

NORMAL AND

UTILITY

CATEGORY OPERATIONS,

REFER

TO

11-IE AIRPLANE

FLIGHT

MANUAL.

FOR SPIN

RECOVERY,

USE

FULL

RUDDER AGAINST SPIN:

FOL-

LOWED IMMEDIATELY

BY

FORWARD

WHEEL.

NO

ACROBATIC MANEUVERS (INCLUDING SPINS) ARE APPROVED

FOR NORMAL CATEGORY

OPERATIONS."

2.

Adjacent

to

upper

door

latch:

3.

"ENGAGE

LATCH BEFORE

FLIGHT."

On

the

inside·of

the

baggage

compartment

door:

"MAXIMUM BAGGAGE 125

LBS."

(S/N

671

to

1760A)

(MAXIMUM BAGGAGE MAY

BE

INCREASED TO 200 LBS.

IN

ACCORD

ANCE WITH PIPER

SERVICE

SPARES

LEITER

NO. 242)

UTILITY

CATEGORY OPERATION -

NO

BAGGAGE OR

AFT

PASSEN-

GERS ALLOWED. NORMAL CATEGORY OPERATION -

SEE

AIR-

PLANE

FLIGHT

MANUAL WEIGHT AND BALANCE SECTION

I:"OR

BAGGAGE AND

AFT

PASSENGER LIMITATIONS.

4. In

full

view

of

the

pilot:

"ROUGH AIR OR MANEUVERING

SPEED

129 MPH. "

•iUTILITY CATEGORY OPERATION -

NO

AFT

PASSENGERS

ALLOWED."

5. On

the

instrument

panel

in

full

view

of

the

pilot

when

the

oil

cooler

·

winterization

kit

is

installed:

"OIL

COOLER

WINTERIZATION

PLATE

TO

BE

REMOVED WHEN

AMBIENT

TEMPERATURE

EXCEEDS

50°

F."

6.

On

the

instrument

panel

in

full

view

of

the

pilot

when

the

autoflite

is

installed:

"FOR

HEADING CHANGES: PRESS DISENGAGE SWITCH

ON

CONTROL

WHEEL.

CHANGE HEADING,

RELEASE

DISENGAGE

SWITCH.

FAA APPROVED

8/3/62

...

REVISED

4/2/68

Rev.

No. 13

PIPER

AIRCRAfT

CORP

CHIECKEO

DEVELOPMENT

CENTER,

YERO

BEACH,

fLA.

REPORT

VB-163

Airplane

Flight

Manual

Model

PA-28-180

PAGE

4

of

6

Placards

(Cont'd)

7.

In

full

view

of

the

pilot:

"UTILITY

category

operation.

The

following

information

is

noteworthy:

•

a.

The

stall

characteristics

of

the

PA-28-180

are

normal

with

the

nose

pitching

down

moderately

following

the

stall,

occasionally

with

a

moderate

roll

which

can

be

corrected

by

normal

use

of

ailerons

and

rudder

against

the

roll.

b.

Prolonged

use

of

full

rudder

during

stall

practice

may

result

in

a

rapid

roll

followed

by

a

spin

and

should

be

avoided.

Recovery

from

an

incipie_nt

spin

may

be

effected

in

less

than

o~e

additional

turn

by

use

of

opposite

rudder

followed

by

full

forward

control

wheel.

c.

In

the

event

that

a

fully

developed

spin

is

inadvertently

experienced,

recovery

is

best

made

by

using

full

opposite

rudder

followed

by

full

forward

wheel

and

full

opposite

aileron.

The

control

positions

agains

the

spin

should

be

maintained

during

the

entire

recovery,

which

may

require

several

turns

and

a

substantial

loss

of

altitude

if

the

airplane

is

loaded

heavily

with

a

rearward

center

of

gravity.

4.

Except

as

noted

above,

all

operating

procedures

for

this

airplane

are

normal.

FAA

APPROVED

8/3/62

·

REVISED

4/2/68

Rev.

No. 13

KIAS

112

l

PRE,.AI'ti[O

CHI[CKEO

Procedures

Section

(Cont'd

.)

FAA APPROVED

8/3/62

PIPER

AIRCRAfT

CORP

Airplane

Flight

Manual

Model

PA

28-180

OfVHOPIEU

CUHR,

YERO

BEACH,

fU.

5.

REPORT

VB-163

PAGE

5

of

6

(Electric

Pitch

Trim

Installation

Only)

The

following

emergency

information

applies

in

case

of

electric

pitch

trim

malfunction:

a.

In

case

of

malfunction,

disengage

electric

pitch

trim

by

pulling

out

circuit

breaker

on

instrument

panel.

b.

In

emergency,

electric

pitch

trim

may

be

overpowered

usin~

manual

pitch

trim

.

c.

In

cruise

configuration,

malfunction

results

in

10°

pitch

change

and

30

Ft.

altitude

variation.

6 .

(Autoflite

Installation

Only)

The

following

emergency

information

applies

in

case

of

autoflite

malfunction:

a.

In

case

of

malfunction

PRESS

disconnect

switch

on

pilot's

control

wheel.

b;

Rocker

switch

on

instrument

panel

-

ORF

.

c . Unit

may

be

overpowered

manually

.

d.

In

cruise

configuration

malfunction,

3

seconds

delay

results

in

60°

bank,

and

100

Ft.

altitude

loss.

e.

In

approach

configuration

malfunction,

1

second

delay

results

in

10°

bank

and

0

Ft

.

aititude

loss

.

7.

(AutoControl

III

Installation

Only)

I .

Limitations:

Pilot

off

during

take

off imd

landing

.

II.

Procedures:

a.

Normal

Operation

Refers

to

Manufacturer's

Operation

Manual.

b.

Emergency

1.

In

case

of

malfunction,

disengage

manual

controls.

2 . In

emergency,

pilot

may

be

overpowered

manually.

_

3.

In

cruise

configuration

malfunction,

3

second:;

delay

results

in

60°

bank

and

100

Ft.

altitude

loss

.

REVISED

7/15/66

Rev.

No . 8

4.

In

approach

configuration

malfunction,

1

second

delay

results

in

10°

bank

and

0

Ft.

altitude

loss.

l

~,

PREPAI't£0

PIPER AIRCRAFT CORP.

Airplane

Flight

Manual

Model

PA

-28-180

CHECKED

API"I'tOVEO

3.

Performance

Section

FAA

APPROVED

8/3/62

DEYHOPMUT

CENTER,

YERO

BEACH,

fLA.

REPORT VB-163 PAGE 6

of

6

The

following

performance

figures

were

obtained

during

FAA

Type

tests

and

may

be

realized

under

conditions

indicated

with

the

airplane

and

engine

in

good

condition

and

with

average

piloting

technique.

All

performance

is

given

for

2400

potmds.

Loss

of

altitude

during

stalls

varied

from

125

to 200

feet,

depending

on

configuration

and

power.

Stalling

speeds,

in

mph,

power

off,

versus

angle

of

bank

(Calibrated

Airspeed):

Angle

of

bank

Flaps

Up

Flaps

Down

0

67

57

20

69 40

76

50

83 60

94

REVISED

7/15/66

Rev.

No.

8

·----------------~---------------------------------r------------

--

--~

Airpbne

Flight

Manual

I

CMICGa

PIPER AIRCRAFT CORP.

D£HLOP!HMT

CUHI,

HU

lEACH,

FLA.

REPORT

VB-261

AIRPLANE

FLIGHT

MANUAL

SUPPLEMENT

NO. 2

CENTER

OF

GRAVITY RANGE

FOR

MODEL

PA-28-180

Supolement

I

Model

PA-28-180

PUE

l

THIS AIRPLANE

FLIGHT

MANUAL

SUPPLEMENT

IS APPLICABLE TO

AIRCRAFT

WITH

SERIAL

NUMBERS 28-671 TO

28-3072,

I0)CLUSIVE,

WHEN PIPER PART NO.

65280-00

TUBE-LANDING GEAR

STRUT

PISTON

IS

INSTALLED.

SERIAL

NUMBERS

28-3073

TO

28-5859

MAY USE THIS

SUPPLEMENT

WITH

NO

ADDITIONAL MODIFICATION

TO

THE

AIRCRAFT.

THIS DOCUMENT

0.-fUST

BE

ATTACHED

TO

THE

AIRPLANE

FLIGHT

!'viANUAL

M

.J

..

/}

(

"--1

FAA APPROVED:

,;{.:.k(..u._.y;.,

C:

~~

Cf.

C.

Stephen,

FAA

C{JA

SO-l

Piper

Aircraft

Corporation

DATE:

September

14, 1970

----~------~---------

,

• -·--

lPU:.>AJIID PI PER AIRCRAFT C0RP.

Airplane

Fli

gnt

Manual

i

Suppleme

nt

I

CHICKIO

OEHlOPiHXT

CUTER,

nan

SUCH,

FLA.

~Iodel

PA-2

8

-1

80 I

MPltOVSI)

PU£

REPORT

V13-261

i i

t_IPER

MODEL

PA-28

-180

~~zg:!c~~~~~~~~

I

. I

REVISION

I?

AGE APPROVED

DATE

NO. I

I

-;

I

.

I

-

...

..

FAA

APPROVED

9/14/70

L_

___;____

___

.J

..

CMIC!Ue

PIPER AIRCRAFT CORP.

DEYHOPIHU

CUHI,

YEU

IEACR,

FlA.

REPORT

VB-161

I

Airplane

Flight

~'lanual

Supplement

:\1ode1

PA-28-180

PACE

l

of

2

PIPER

MODEL

PA-28-1

80

NORMAL

~'\'D

UTILITY

Category

Weight

(Pounds)

2400

2200

2150

1650

Forward

Limit

(In. Aft

of

Datum)

91.0

87.8

87.0

84.0

2.

Utility

Category

Weight

(Pounds)

1950

1650

"No

Change"

"No

Change"

Forward

Limit

(In. Aft of

Datum)

85.8

"-

"

84.0

Rearward

Limit

(In. Aft

of

Datum)

94.5

95.9

Rearward

Limit

(In. Aft of

Datum)

86.5

,.

I>Ul'AilCD

FAAA

roved9/14/70

PIPER

O£HlOPM£U

AIRCRAFT

CUTEI,

YEU

REPORT

VB-261

C0RP.

IUCH,

FlA.

C.

G.

RANGE

AND

WEIGHT

INCHES

AFT

OF

DATU:t\,1

Airplane

Flight

:..1anual

Supplement

tv1odel

PA.,.28-l80

PUE

2

or

2

PUP.AaiD

PIPER

AIRCRAFT

C0RP. !Weight

and

Balance

Data

CHICKID

DEVELOPMENT

CfNTEI,

YERO

BEACH,

FLA.

Model .

PA-28-180

AI'PitOVID REPORT VB-165

PUE

l

Section

1

·WEIGHT AND BALANCE DATA

..

MODEL PA-28-180 CHEROKEE

..

Airplane

Serial

Number

28·-

..

Registration

Number

Date

~

·,

AIRPLANE EMPTY WEIGHT

I C. G.

Arm

I

Weight

X

(Inches

Aft=

Moment

Item

{lbs)

of

Datum)

(In-lbs)

Actual

Standard

Empty

Weight *

Computed

Optional

Equipment

Unusable

Fuel

· (3

Pints)

_

2.2

103.0

227

Licensed

Empty

Weight

=

Total

of

Above

Items

•

Standard

Empty

Weight

includes

paint,

hydraulic

fluid

and

undrainable

engine

oil

•

AIRPLANE

USEFUL

LOAD ..

(Gross

Weight)

-

(Licensed

Empty

Weight)

=

Useful

Load

.

Normal

Category:

(2400

ibs)

-(

lbs)

=

lbs.

Utility

Category:

(1950

lbs)

-(

lbs)

= ·

lbs.

THIS LICENSED EMPTY WEIGHT, C.

G.

AND

USEFUL

LOAD

ARE

FOR

THE

AIRPLANE

AS

DELIVERED

FROM

THE

FACTORY.

REFER

TO

FORM

FAA-337

WHEN

ALTERA-

TIONS HAVE BEEN MADE. .

••

' -

.

PUPAall>

PIPER

AIRCRAFT

C0RP.

Weight

and

Balance

Data

CHIC

lUI>

DEVELOPMENT

CUTER,

YERO

BEACH,

FLA.

Model

PA-28-180

APP'AOYID

REPORT

VB-165

PACE

2

Section

1

e.G.

RANGE AND WEIGIIT INSTRUCTIONS

1.

Add

the

weight

of

all

item£

to

be

loaded

to

the

licensed

empty

weight.

2.

Use

the

loading

graph

to

determine

the

moment

of

all

items

to

be

carried

in

the

airplane.

3.

Add

the

moment

of

all

items

to

be

loaded

to

the

licensed

empty

weight

moment.

4.

Divide

the

total

moment

by

the

total

weight

to

determine

the

C. G.

location.

5.

By

using

the

figures

of

Item

1

and

Item

4,

locate

a

point

on

the

C. G.

range

and

weight

graph.

If

the

point

falls

within

the

C.

G.

envelope,

the

loading

meets

.

the

weight

and

balance

requirements.

SAMPLE LOADING PROBLEM .

(Normal

Categorl:)

Weight

Arm

Aft

Datum

Moment

{lbs)

(Inches)

(In-

Lbs)

Licensed

Empty

Weight

Oil

(8

quarts)

15

32.5

488

.

Pilot

and

Front

Passenger

340

85.5

29070

Passengers,

Aft*

(Rear

Seat)

340

ll8.1

40154

Fuel

(50

Gal.

Maximum)

95.0

Baggage *

142.8

Total

Loaded

Airplane

The

center

of

gravity

(C.

G.)

of

this

sample

loading

problem

is

at

inches

aft

of

the

·

datum

line.

Locate

this

point

( ) on

the

C. G.

range

and

weight

graph.

Since

this

point

falls

within

the

weight

-C. G.

envelope,

this

loading

meets

the

weight

and

balance

require-

ments.

IT

IS

THE

RESPONSIDILITY

OF

THE

PILOT AND

AIRCRAFT

OWNER

TO

INSURE

THAT

THE

AIRPLANE

IS

LOADED PROPERLY. .

*

Utility

Category

Operation

-No

baggage

or

aft

passengers

allowed.

PRE

FARED

CHECKED

APPROVED

5

10

,'

PIPER

AIRCRAFT

CORP

DEVELOPMENT

Cf~TER,

VERO

BEACH,

_

FLA.

.

.r

REPORT

VB-165

LOADING GRAPH

15

20 25

30

35

40

MOMENT/1000 (POUND INCHES)

45

Weight

& Balance

Data

Model

PA

28-180

PAGE 3 ·

Section

1

50

PREPARED

CHECKED

APPROVED

~

z

:::>

0

2400

2200

2000

p., 1800

z

-

~

g

; 1600

1400

1200 .

'•

PIPER AIRCRAFT

CORP

Weight &

Balance

Data

Model

PA

28-180

t:

tt!

:tt=t;:ttU

J-±

···

+-+-

. '

DEVELOPMENT

CENTER,

YERO

BEACH,

fLA.

REPORT VB-165

PAGE

4

Section

1

C.

G.

RANGE AND WEIGHT

·

-i

+

··

-+

-i

-f-

· -,

~

_;_

r::fJ+

-- -

3$+.-

H-4

--l+

-1-1

, •1 ·

t-

--

-1;-r·

-t+H-t-t-

:

:f

}-f-l, -+

-+

--l+

H

-

~

-

t-

-

H-t

.!

+-7

+ -

+

~

-r-

-±l

--

!+

'+-+-t

--

~i:

-

t-

.

·t-:;

-+

++•.--

-j-

l

-

w-~

++-

-.

.,

=~

-

~

.

i !

:.

~

. ..

~

·

!

--l--+-l-1

I ' ' I • ; . I I ' -

tt

t-

P'J.;

-

f-;

-H- ··-

J±±tr-

.

....

+

f=j::1q

::;:

t

t=;::t

:::j:::j::

1=t1

-:-.t-J-

=J_

·

:t+-+:;

.t

t::

;

H

,

i=J~.

=+

;

·

j:

·

'

:t~

.

i.

tj

t=

·

ttl

:::j:

.

::

.t.

f-

•

~

7

~

,

;;tl

:tJ::i

-+

-H+~

++-,

...,.+r+-+

,

+-

.t--

.

_H

-i

j : : I I : ; I I ' ' I ' . I

-t-

' ' . '

. I I .

I ' ' ' •

1-+-~

-H-

+-H-+++++++

,

•

~

l . ' '

_u_

! !

! i

' I

84

I

-+.

f I

+d

-i

H-+-b

' ' v

'

t-+

-: I

I '

'.

'

I 1 ; : ...-· ; ;

1 I I ' ' ' '

f i

86

88

'I

: I

I ' 90

..L..Ll-

] '

! '

'

+-

t+

-.!....\-

+ -t

~

!-+

-

' ' .

92

INCHES

AFT

OF

DATUM

~S/N

671 }'HRU

S/N

58591 INCLUSIVE)

+

,.

' '

~

-

H-

• !

' I

-~

-

H--t-

-

!-+

' '

94

96

PUPAIIID

.

CHICDD

APPROYID

.

..

PIPER

AIRCRAFT

C0RP.

DEYHOPMENT

UNTEI,

YERO

BEACH,

FLA.

REPORT

VB-165

WEIGHT AND BALANCE DATA

WEIGHING

PR

OCEDUR E

Weight

and

Balance

Data

Model

PA-28-180

PACE

5

Sectj

on

1

At

the

time

of

delivery,

Piper

Aircraft

Corporation

provides

each

airplane;!

with

the

licer.sed

empty

weight

and

center

of

gravity

location.

This

data

is

on

Page 1,

Section

1

of

this

Flight

~anual.

·

The

removal

or

addition

of

an

excessive

amount

of

equipment

or

excessive

airplane

modifi-

cations

can

affect

the

licensed

empty

weight

and

empty

weight

center

of

gravity.

The

follow-

ing

is

a

weighing

procedure

to

c!etermine

this

licensed

empty

weight

and

center

of

gravity

location:

1.

· PREPARATION

a.

Be

certain

that

all

items

checked

in

the

aiq~lane

equipment

list

are

installed

in

the

proper

location

in

the

airplane.

b.

Remove

excessive

dirt,

grease,

moisture,

foreign

items

such

as

rags

and

tools

from

the

airplane

before

weighing.

c.

Defuel

airplane.

Then

open

all

fuel

drains

until

all

remaining

fuel

is

drained.

Operate

engine

on

each

tank

until

all

undrainable

fuel

is

used

and

engine

stops.

)

. d.

Drain

all

·

oil

from

the

engine,

by

means

of

the

oil

drain,

with

the

airplane

in

ground

attitude.

This

will

leave

the

undrainable

oil

still

in

the

system.

Engine

oil

temperature

should

be

in

the

normal

operating

range

before

draining.

e.

Place

pilot

and

co-pilot

seats

In

fourth

(4th)

notch,

aft

of

for-Ward

position.

Put

flaps

in

the

fulfy

retracted

position

and

all

control

surfaces

in

the

neutral

posi-

tion.

Tow

bar

should

be

in

the

proper

location

and

all

entrance

and

baggage

doors

closed.

·

f.

Weigh

the

airplane

inside

a

closed

building

to

prevent

errors

in

scale

readings

due

to

wind

..

2.

LEVELING

a.

With

airplane

on

scales,

bl'ock

main

gear

oleo

pistons

in

the

fully

extended

position.

b.

Level

airplane

(see

diagram)

by

deflating

nose

wheel

tire,

to

center

bubble

on

level.

Piper Aircraft Corporation Cherokee PA-28-180 Technical specifications

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