Piper Aircraft Corporation PA-32R-301T, Saratoga SP Pilot Operating Handbook

PIPER AIRCRAFT CORPORATION

PA.32R.3OI,

SARATOGA

SP

SECTION I

GENERAL

1.T INTRODUCTION

SECTION

GENERAL

I

This

Pilot's Operating

an operating

as

furnished

supplied by

This handbook

competent applicable

guide

be a

used for

operational

Assurance that

guide

pilot

to the

the airplane

is not designed

flight instruction,

federal air

for

basic

regulations or advisory

flight

purposes

the airplane is

responsibility of the

the airplane

determining

remaining within

for

markings,

Although the

in-flight capabilities,

reference.

that

placards, and

arrangement

it should

pilot

The

should

with the limitations,

characteristics

The

provided

emergency

and

procedures,

information that

Section has been

reference to the

made by the

been

numbers, item numbers

of the airplane

handbook

has been

with a "finger-tip"

procedures have been

performance and other sections

may be

furnished

section.

deliberate

Handbook is designed

pilot.

for the

FAR/CAR.

by

manufacturer.

knowledge

instruction

owner.

the operating

this

It includes

or a training manual and

unless

pilot

The

is safe for flight.

limitations

handbook.

of this handbook

not be used solely as an occasional

study the entire

performance,

procedures

before flight.

divided into numbered

tab divider for

required in flight.

with a red tab divider

Provisions

omission

pages

and

for expansion of

noted as being intentionally

maximum

for

the material required

It also

as a substitute for

contains supplemental

adequate and

of current airworthiness

circulars.

It is not intended

should

kept in a current status.

in an airworthy condition

in command

The pilot

as outlined

handbook to familiarize

and

quick

placed

to

The

of certain

paragraph numbers, figure

is responsible

responsible

is also

by instrument

is intended to increase

operational

(arabic)

reference.

ahead

provide

"Emergency

to

sections

The limitations

of the normal

easier

Procedures"

present an

handbook have

the

left

utilization

to be

data

directives,

not be

is the

for

operating

himself

handling

each

access

instant

blank.

to

its

to

ISSUED:

NOVEMBER

8, 1979

REPORT:

VB'1080

l-l

SECTION

GENERAL

I

PIPER AIRCRAFT

PA-32R-301,

12'11'

CORPORATION

SARATOGA SP

5',6"

ll,r)Zl^

7'

178.3

30.0

tip)

pivot

(sq.

point

ft.)

(ft.)

to wing

Wing Area

Min. Turning Radius

(from

1"

o

36',2

REPORT: VB-r080

r-2

11"

7'

THREE VIEW

11',1"

27'4"

Figure

d

l-l

ISSUED:

{'

'u"

NOVEMBER

8,

1979

PIPER AIRCRAFT

PA-32R-301,

SARATOGA

I.3 ENGINE

2 BLADE PROPELLER

(a)

Number of Engines

(b)

Engine Manufacturer

(c)

Engine

Model Number

CORPORATION

SP

SECTION

GENERAL

Lycoming

ro-540-KlG5D

T

I

(d)

Rated Horsepower

(e)

Rated

(0

(g) (h)

(i)

0)

3 BLADE PROPELLER

(a) (b)

(c)

(d) (e)

(0

(g) (h)

(i) ü)

(inches)

Bore Stroke

Displacement Compression Ratio Engine

Number of Engines

Engine Engine Model

Rated Horsepower Rated

(inches)

Bore Stroke

Displacement Compression Engine

(rpm)

Speed

(inches)

(cubic

Type

Manufacturer

Number

(rpm)

Speed

(inches)

(cubic

Ratio

Type

inches)

Max.

Cont.

Power

294

2600

Six

Cylinder,

Horizontally Opposed,

ro-540-KlG5D

Six Cylinder,

Horizontally

Opposed,

T.O. Power-

Min. Limit

5

300

2700

5.t25

4.375

541.5

8.7: I

Direct Drive,

Air Cooled,

Injected

Fuel

Lycoming

300

2700

5.125

4.375

541.5

8.7:l

Direct

Drive,

Air Cooled,

Injected

Fuel

I

1.5. PROPELLER

2 BLADE

(a) (b)

ISSUED:

PROPELLER

Number of Propeller Manufacturer

NOVEMBER

Propellers

t, 1979

REPORT:

Hartzell

VB-10t0

1-3

SECTION I GENERAL

(c)

Blade

(d)

Number

(e)

Ilub-Modet--

(f)

Propeller Diameter

(l)

(2)

(g)

Propeller

BLADE

3

(a)

Number

(b)

Propeller

(c)

Blade Model

(d)

Number of Blades

(e)

Hub Model

(f)

Propeller

(l)

(2)

(g)

Propeller Type

r.7

FUEL

Model

of Bladqs

Minimum Maximum

Type

PROPELLER

of Propellers

Manufacturer

Diameter

Minimum Maximum

(inches)

PIPER

AIRCRAFT

PA-32R-30r,

HC-C2Y(K,R)-r(

Hydraulically

Hydraulically Actuated

CORPORATION

SARATOGA

F8475D-4

Constant

F7663R-O

HC-C3YR-r(

Constant Speed,

SP

)F

78.5

80

Speed,

Actuated

Hartzell

)F

76

78

2

I

3

AVGAS

(a) (b)

(c)

REPORT: VB-1080

ONLY

Fuel

Capacity

Usable

Fuel

(l)

(2)

Fuel

Grade, Aviation

Minimum

Alternate

t-4

(U.S.

Grade

Fuels

(total)

gal.)

gal.) (total)

100

Lycoming

ISSUED:

REVISED:

-

Green or I00LL - Blue

Aviation Grade

Refer

Service Instruction 1070.

to

latest

revision

NOVEMBER 8. 1979

17,

SEPTEMBER

1984

107

102

of

PIPER

PA.32R-301,

1.9 oIL

AIRCRAFT

CORPORATION

SARATOGA

SP

SECTION

GENERAL

I

(a)

(b)

(c)

I.T1

(a) (b)

(c)

(d)

I.I3

Refer to Figure 6-5

Load.

Capacity

Oil

Specification

oil

Viscosity

Oil

(l)

Above

(2)

30oF

(3)

0o to 70oF

(4)

Below

MAXIMUM WEIGHTS

Maximum Takeoff Maximum Maximum

Maximum

Compartments

STANDARD

(U.S. quarts)

per

Average

60oF

to 90oF

l0oF

Weight

Landing Weight Ramp Weight

Weights

AIRPI,ANE

in Baggage

for the Standard

Refer to

Lycoming Service

Ambient Temp. for Starting

Instruction

SINGLE

50

40

30 20

(lbs.)

FORWARD

100

WEIGHTS

Ernpty

Weight

latest

MULTI

zl0

and

issue of

1014.

50

40 or

40

or 20W-30

20W-30

3600 3600

361

AFT

100

the Useful

12

5

r.15 BAGGAGE SPACE

(a)

Compartment

(b) (c)

SPECIFIC

1.I7

(a) (b)

ISSUED: NOVEMBER

REVISED:

Width

Entry

Height

Entry

Wing Loading

Power

Loading

SEPTEMBER

Volume

(inches)

LOADING

(lbs. per

(cubic

(lbs. per

8, 1979

17'

1984

sq. ft.)

hp)

feet)

FORWARD

7.0

16.0

22.0

REPORT:

AFT

t7.3

48.0

26.0

20.2

t2.0

VB-10t0

1-5

PIPER

PA-32R-301,

2.1 GENERAL

AIRCRAFT

CORPORATION

SARATOGA SP

LIMITATIONS

SECTION 2

SECTION

LIMITATIONS

2

This

section

instrument

operation

of the airplane

Limitations

which require handbook

(Supplements).

2.3

AIRSPEED LIMITATIONS

provides

the

markings, color coding

and

associated

with

supplements can

SPEED

Never Exceed

ceed this speed in

Maximum

(VNd

except in smooth air and then only

Structural Cruising Speed

- Do

not exceed

Speed

any

(Vr.rr)

operation.

this speed

with caution.

Design

not make

ments above

Maneuvering Speed

or

full

abrupt control

speed.

this

At 3600 LBS. G.W.

At 2230 LBS. G.W.

"FAA Approved"

and basic

its

systems.

those

optional systems

- Do

not ex-

(Va

-

Do

)

move-

operating

placards

necessary

and

found in Section

be

KIAS KCAS

197

154 150

134

105

limitations,

for

equipment

9

189

t32

104

ISSUED:

NOVEMBER 8, 1979

REPORT:

VB-10t0

2-l

SECTION

2

LIMITATIONS

PIPER

CAUTION

AIRCRAFT

PA.32R.3OI,

CORPORATION

SARATOGA

SP

Maneuvering speed decreases

as the effects

pronounced. Linear interpolation

more

for

used

of aerodynamic

intermediate

Maneuvering speed should

while

SPEED

operating

in rough air.

Maximum Flaps Extended Speed Do not exceed this speed with

extended.

Maximum

Speed

when extending

Maximum Landing

Speed

when

Maximum Landing

Speed

with the landing

Landing Gear Extension

(Vlo)

-

not exceed this speed

Do

the landing

Gear

(Vr-o)

-

retracting

(V'u)

-

Do not

Do not exceed this

the

gear

exceed this

landing

Gear

extended.

the flaps

gear.

Retraction

gear.

Extended

at lighter

forces become

gross

not

(Vrs)

-

speed

weight

may

weights.

be exceeded

KIAS

n2 109

t32

il0 r09

t32 r30

be

KCAS

130

2.5 AIRSPEED INDICATOR

MARKING

(Never

Red Radial

Line

Exceed)

Yellow Arc

(Caution

Green

White

Arc

(Normal

(Flap

Range

-

Smooth Air Only)

Operating

Down)

REPORT: VB-1080

2-2

MARKINGS

Range)

ISSUED:

IAS

154 KTS to

KTS to

60

KTS

57

to

NOVEMBER

I97

KTS

I97 KTS

I54 KTS

I 12 KTS

1979

8,

PIPER I'A-32R-30I,

2.7

AIRCR

AI.-'t COR PORATION

SARATO(;A

POWUR PLANT

2 lll.ADE PROPEI-t-l:l(

(l)

Numbcr

(h)

Enginc Manufacturcr

(c)

Engine Model

of Engincs

SP

LIMITATIONS

No.

SECTION 2

LIMITATIONS

I

Lycoming

r0-540-K rc5D

(d)

Enginc

(l)

(2)

(3)

Operating

Maximum Horse Power

Maxinum Engine

(RPM)

Maximum Oil Temperature

[-imits

('F)

(e)

Oil Pressure

Minimum Maximum

(f)

Fuel Maximum

(g)

Fuel

(mininrum

(h)

Number

(i)

Propeller Manufacturer

Propeller Hub and Blade Model

0)

(k)

Propeller Diameter

Minimum

Maximum

(l)

Blade Angle Limits

l-ow High Pitch Stop

(red

Flow/

Pressure

(red

(AVGAS

grade)

of Propellers

Pitch Stop

line)

ONLY)

(inches)

Speed

Max.

Cont.

Power

294

2600

245

HC-C2Y(K,R)-r(

T.O.

5 Min. Limit

gal/hr;

35

100 or l00LL

Aviation

13.5o

Power-

300

2700

245

25 PSI

t00 PSt

14 PSI

Grade

Hartzell

)F/

F8475D-4

78.5

0.2"

t

34"

t

I

80

lo

lSSl-lED: REVISED:

NOvf,MBER 8. 1979

SEPTEMBER 17, 1984

REPORT:

VB-10t0

2-3

sEcTloN

2

LIMITATIONS

PIPER ATRCRAFT CORPORATION

PA.32R.3OI, SARATOGA

SP

3 BLADE

(a)

Number

(b)

Engine

(c)

Engine Model

(d)

Engine Operating

(l)

(2) (3)

(e)

Oil Pressure

PROPEL.LER

of Engines

Manufacturer

Maximum Horse Maximum Rotation

Maximum Oil

Minimum

Maximum

(0

Fuel Flow/ Pressure

Maximum

(g)

Fuel

Grade

(h)

Number of Propellers

(i)

Propeller Propeller Hub

0)

(k)

Propeller Diameter

Minimum Maximum

(l)

Blade

Low High

Manufacturer

Angle Limits

Pitch Stop

No.

Limits

Power

Temperature

(red

line)

(red

line)

(red

line)

(minimum grade)

and Blade

(inches)

Speed

Model

(RPM)

(o

F)

Lycoming

I0-540-KrG5D

gal/hr;

35

-

Green

100

l00LL

Aviation

HC-C3YR-l

F7663R-0

12.4" ! 0.2"

32.0o t

300

2700

245

25 PSI

100 PSI

14 PSI

or

-

Blue

Grade

Hartzell

(

)F/

76\

78

1.0"

I

REPORT:

2-4

VB-1080

ISSUED: NOVEMBER t,

REVISED: SEPTEMBER

1979

I, l9t6

PIPER

PA.32R.301,

AIRCRAFT

CORPORATION

SARATOGA SP

SECTION

LIMITATIONS

2

2.9 POWER

(a)

(b)

(c)

(d)

PLANT INSTRUMENT

Tachometer

(l)

2

Green

Yellow Arc

Red Line

(2)

3 Blade

Green Arc

Red Line

Temperature

Oil

Green Arc Red Line

Pressure

Oil

Green Arc

Yellow Yellow Arc (Start

Red Line Red Line

Fuel Flow/ Pressure

Green

Red Line

Propeller

Blade

Arc

Propeller

(Normal

(Maximum) 245"F

(Normal

(Caution

Arc

(Caution

Warm Up)

and

(Minimum) (Maximum) 100

(Normal

Arc

(Maximum)

2.IIWEIGHT LIMITS

MARKINGS

(Normal

(5

Minute

Operating Range) 500 to

Limit) 2600

2600 RPM 2700 RPM

to

(Maximum) 2700 RPM

(Normal

Operating Range) 500 to

(Maximum)

Operating Range)

Operating

Range)

Operating Range) 0

(ldle)

Range) 60

90 PSI to

gal/hr.

35

2700 RPM 2700

75o to

PSI to

25 PSI to

to 34.9

gal/hr.:

RPM

245oF

90 PSI

PSI

60

100 PSI

25 PSI

PSI

gal/hr.

14 PSI

(a)

Maximum Weight

(b)

Maximum

(c)

Maximum Baggage

ISSUED:

Ramp Weight

Refer

weight as

Section 5

to

limited by

NOVEMBER

(100

lbs.

NOTE

(Performance)

1979

t,

each compartment)

for maximum

performance.

LBS.

3600

LBS.

3615

2OO LBS.

REPORT: VB-1080

2-5

SECTION

2

LIMITATIONS

PIPER

AIRCRAFT

PA-32R-301,

CORPORATION

SARATOGA

SP

2.I3 CENTER OF GRAVITY

Weight

Pounds

3600 3200

2400

(and

less)

Straight line

The

datum

Forward

Inches Aft of

variation between

used

leading edge at

untapered and

is

It

the loaded. See

proper

MANEUVER LIMITS

2.I5

No

acrobatic

responsibility of the airplane

the

pilot

to insure that

Section

loading

maneuvers including

LIMITS

Limit

Datum

9t.4

83.5

78.0

NOTES

is

inches ahead

78.4

the

tapered

instructions.

section.

the

(Weight

6

points

of the

intersection

owner and

Balance) for

and

approved

is

airplane

spins

Rearward

Inches

given.

wing

the

of

properly

Aft of

95.0

Limit

Datum

I

2.I7 FLIGHT

(a) (b)

(c) (d)

LOAD FACTORS

Positive Load Factor Negative Load

Positive Load Negative Load Factor - Flaps

REPORT: VB'1080

2-6

(Maximum)

Factor

Factor - Flaps Down

(Maximum)

Down

ISSUED:

inverted maneuvers

(Maximum)

maneuvers

NOVEMBER

approved

No

inverted

approved

8'

3.8

2.0G

1979

G

PIPER AIRCRAFT PA-32R-30r, SARATOGA

CORPORATION

SP

SECTION

LIMITATIONS

2

2.I9 TYPES

The

accordance

(a)

(b)

(c)

(d) (e)

2.21 FUEL LIMITATIONS

(a)

(b)

(c)

2.23 NOISE

The corrected

propeller

installations.

No determination

Administration

acceptable

OF OPERATIONS

with

V.F.R.

is approved

FAR

9l

or

airplane

Day

Night V.F.R

I.F.R.

Day

I.F.R.

Night Non icing

Total Capacity

UnusableFuel..

unusable

The

gallons in

per

total

Usable The usable

each wing interconnected tanks).

Fuel . . ..

LEVEL

installations

that

or unacceptable

fuel for this airplane

each wing

side, each

in this airplane

fuel

(51 gallons

level of

noise

and 78.4 d

has

the noise

for the

following

operations

FAR 135.

has been determined

in

critical

having two interconnected

side

is the total

this

flight attitudes

has been determined

per

side, each

B(A)

is

77.6

for

aircraft

been made by

levels of this airplane are

for operation at,

into,

equipped

when

GAL.

U.S.

IO7

.....5U.S.G4L.

as

(2.5 gallons

tanks).

is the

I02 U.S. GAL.

gallons in

as

5l

having two

side

d B(A)

three

for two

bladed

propeller

the Federal Aviation

or should

or

out of,

4ny

airport.

in

2.5

be

The above

been verified

noise level Standards

is in compliance with all F.A.R. 36

model

type.

ISSUED:

statement

by and

test flights conducted

approved

- Aircraft Type

NOVEMBER

noise level stated

notwithstanding

by the Federal

the

Aviation Administration

in accordance with

and Airworthiness Certification.

noise standards

8'

1979

REPORT: VB-1080

above

F.A.R.36,

This aircraft

applicable

has

Noise

this

to

in

2-7

SECTION

2

LIMITATIONS

PIPER

AIRCRAFT CORPORATION

PA-32R-301, SARATOGA

SP

FLIGHT

2.25

AND

The following limitations

airplane

removed:

(a)

(b) (c) (d)

(e)

(0

WITH

CARGO

rear cabin

the

with

The airplane

cargo

and

door

is not approved.

Maximum

No smoking.

loose articles

All

Jumper's control Operation

static

surfaces.

REAR CABIN

DOOR

REMOVED

must

door

flown with the rear cabin

be

may

removed.

door

speed -

approved

147 KIAS

must be

must be kept free of

lines

VFR flight conditions

DOOR OR

be observed

rear

or

Flight

tied down and stowed.

REAR CABIN

in the operation

cabin door

the front door

with

door

pilot's

only.

and

or rear

controls

DOOR

of this

cargo door

cabin

removed

and

REPORT:

2-8

VB-I080

ISSUED: NOVEMBER

8, 1979

PIPEN

AIRCRAFT

CORPORATION

PA-32n-3{[, SARATOGA

PLACARDS

2.29

SP

SECTION

LIMTTATIONS

2

In full view

of

the

THIS AIRPLANE NORMAL CATEGORY

PLIANCE WITH

STATED

IN THE FORM

MARKINGS

MANEUVERS INCLUDING

THIS AIRCRAFT

DAY AND NIGHT

EQUIPPED

FAR

I35.

ln full vicw of thc

bc installed:

Fuel

on Proper Tank

Electric Fucl Pump On

Enginc Gages Chcckcd

Alternate Air

Scat Backs Erect

Closed

pilot:

MUST BE OPERATED

AIRPLANE

THE

OPERATING

AND MANUALS.

SPINS,

APPROVED

NON.ICINC FLIGHT

rN ACCORDANCE

pilot,

thc following

TAKEOFF

Mixture Set

Propeller Set Fastcn Belts/ Harness

LANDING CHECKLIST

CHECKLIST

FOR V.F.R.,

takeoff

AS

COM.

IN

LIMII'AI-IONS

OF PLACARDS,

NO ACROBATIC

APPROVED.

I.F.R.,

WHEN

W|TH FAR

and

Flaps Sct

Trim Tab Set

Controls Doors Latchcd

Air Conditioner

el OR

landing

checklists

Free

A

will

Off

Fuel on

Seat

Backs Erect

Fasten

Electric

Beltsi

The

landing

ISSUED:

Proper Tank

Harness

Fuel Pump

CONDITIONER OFF" item in the above takeoff

"AlR

checklists is

NOVEMBER

-

On

mandatory

t, 1979

Mixture

Propcller

for

air conditioned aircraft

-

Rich

-

Set

Cear Down

Flaps Set

(White

Arc)

Air Conditioner Off

only.

REPORT:

VB-1080

and

2'9

SECTION

LIMITATTONS

2

PIPER AIRCRAFT

PA-32R-301,

CORPORATION

SARATOGA

SP

On the instrument

On

the instrument

ln full view

FOR

REMOVED,

AND AIRPLANE

ln full view

Near emergency

panel

Ve

134

panel

DEMO X-WIND

pilot: (For

of

the

FLIGHT

PROCEDURES

FLIGHT

pilot:

of the

Vro

gcar

gear

(aircraft

lever

EMERGENCY

(aircraft

knob

in full view

KIAS at

(See

A.F.M.)

in full view

operations

WITH

SEE

THE

SECTIONS

MANUAL.

132

DN, I

Vre

t32

MAX

equipped

equipped with

pilot:

the

of

3600 LBS.

pilot:

of the

17

KTS

with the rear

THE DOOR

LIMITATIONS

OF

l0 UP

with lever

DOWN

THE

cable

door removed)

release):

releasc):

override

gear

selector

Near emergency

gear

On

Near

GEAR UP

DOWN

REPORT: VB-10t0

2-10

EMERGENCY

(aircraft

lever

OVERRIDE

TO

ENGAGE

LEVER

TO

I,EVER

latch

GEAR

UP, LATCH

RELEASE

-I.^ULL

(aircraft

OVERRIDE

switch:

GEAR

EXT

equipped

ENGAGED

OVERRIDE:

UP

& RELEASE

equipped

LATCH

IO

I

I32 KIAS MAX

ISSUED:

REVISED:

PULL

with

backup

DOWN

with

backup

KIAS MAX

NOVEMBER

DECEMBER

gear

extender):

t

t, 1979

10. t98lt

PIPER

PA-32R.30I, SARATOGA

AIRCRAFT

CORPORATION

SP

SECTION

LIMITATIONS

2

Adjacent

to upper door latch

ENGAGE

ln

full

view

of

WARNING TURN

LIGHTS WHEN IN CLOSE PROXIMITY

TO GROUn-D OR

THROUGH CLOUD,

full

ln

view of the

the air conditioner

WARNING

BE OFF

CLIMB PERFORMANCE.

On the

inside of the

MAXIMUM

MEn-T SECTION MANUAL.

(front

and rear doors):

LATCH BEFORE FLICHT

pilot:

the

OFF

DURINC

FOG

OR HAZE.

pilot,

in the

is installed:

__

AIR CONDITIONER MUST

TO INSURE NORMAL TAKEOFF

forward

BAGGAGE

LBS.

100

THE AIRPLANE

OF

of

area

baggage

THIS

SEE THE LIMITATIONS

conditioner controls

the air

compartment:

COMPART-

STROBE

FLIGHT'

when

FLIGHT

aft baggage

On

closeout

MAXIMUM BAGGAGE

MENT HAT SHELF.

On storm

ISSUED: NOVEMBER

REVISED:

window:

OCTOBER

IOO LBS.

DO

N.O HEAVY

NOT OPEN

8, 1979

1983

ll'

THIS

ABOVE

COMPART-

OBJECTS ON

I29 KIAS

REPORT: VB-I080

2-tt

SECTION 2

LIMITATIONS

PIPER

AIRCRAFT

PA.32R.3OI,

CORPORATION

SARATOGA

SP

On executive

writing table

CAUTlOlr.- THIS

STOWED

LANDIT-G.

On the

Adjacent to fuel tank filler caps

Adjacent

face

to

of the

fuel

DU RING TAKEOFF AND

tachometer

AFTER

REDUCE POWER TO

2600 RPM

FUEL

-

AVIATIOn-

filler

tank

caps

AVGAS

TABLE

(2

IOO OR IOOLL

(serial

blade

MIt'r".

5

GRADE

propeller

numbers

OIIILY

MUST

only)

32R-83 13010

BE

and up):

REPORT: 2-t2

VB-1080

ss

GRADE

IOOLL

GRADE

too

ISSUED:

REVISED:

NOVEMBER

OCTOBER

8, 1979

ll, 1983

PIPER

PA..]2R..]OI,

3.I

emergencies and

required operation of

of

AIRCRAF'T CORPORATION

SARATO(;A

GENERAL

recommended

The

(FAA

the airplane as determined

the

airplane are

SP

T]MERGEN('Y

SECTION 3

EMERGENCY PROCEDURES

procedures for

critical situations

regulations)

presented.

emergency

coping

provided

are

procedures

the operating and

by

various

with

this section.

by

those

and

SECTION

PROCEDURES

of

types

All of

necessary

features

design

3

the

for

Emergency

equipment which require

(Supplements).

The first

checklist which supplies an action

emphasis on the operation

The remainder

procedures

complete understanding

more

These

particular

procedures

portion

of the

containing additional

procedures

condition

described,

and common sense.

procedures given

should an emergency

Most basic

normal

here,

provide

procedures which

pilot

part

this information

a

review standard

proficient

in this section and

emergency

pilot

of

source of reference and

are

in them.

associated

handbook

this section consists

of

systems.

of

section is devoted

of

suggested as a

are

but

Pilots

arise.

training.

is not intended to replace such

not

should familiarize

procedures,

Although these

the same for

emergency

of

an

optional

provided in

abbreviated

with those

supplements are

sequence

for critical

to amplified

provide the

information

procedures.

the

course of action

not a substitute

are

prepared

be

such as a

review, and to

all aircraft.

procedures periodically

to

themselves

to take appropriate

power

emergencies

provide information

lt

situations

coping

for

for sound

landings,

off

are discussed

training,

is

suggested

systems and

Section

emergency

little

with

emergency

pilot

with a

the

with

judgment

the

with

action

are a

only

but

on

that the

to remain

9

to

ISSUED: REVISED:

NOVEMBER

SEPTEMBER

1979

8'

17' l9t4

REPORT:

vB'10E0

3-l

SECTION EMERGENCY

3

PIPER

PROCEDURES

.TIRCRAFT CORPORATION

PA.32R.]OI, SARATOGA SP

3.3 EMERGENCY

PROCEDURES

ENGINE FIRE DURING START

Starter

Mixture ..

Throttle Electric fuel

Fuel selector'.. .. .

Abandon if fire continues

ENGINE POWER

lf sufficient runway

straight ahead.

lf

area ahead

Gear selector switch

Emergency

backup

If sufficient

Maintain

Fuel selector

Electric

pump

LOSS DURING

remains for a normal

is rough, or

gear

lever

gear

extender). ..

altitude has been

safe airspeed

pump

fuel

if it is necessary

(aircraft

equipped with

.

gained

Mixture

Alternateair....

gear

Emergency

lf

power

is not regained,

lever.

proceed

CHECKLIST

TAKEOFF

landing, leave

to attempt

power

wit h

crank

. idle cut-off

gear

down

to clear obstructions:

in

. .. . . latched

ENGAGED

a restart:

OVERRIDE

switch

containing

..check

as

...

landing.

off

engine

and

position

to tank

check

RICH

. OPEN

required

open

OFF OFF

land

UP

fuel ON

REPORT:

3-2

VB-1080

ISSUED:

REVISED:

NOVEMBER

Sf,PTEMBER

1979

t,

I' l9tb

PIPER PA-32R.30I,

AIRCRAFT

CORPORATION

SARATOGA SP

EMERGENCY

SECTTON

PROCEDURES

3

ENGINE

Fuel selector....

Electric

POWER

pump

fuel

LOSS

Mixture

Alternate air ..

Engine

lf

tank containing

When

gauges .

fuel flow is indicated, check

no

power

Alternateair...

Electric fuel

'

fuel.

is restored:

pump

Mixture

power

lf

POWER OFF LANDTNG

On

lever in

KIAS to

is

not restored

aircraft equipped

OVERRIDE

prevent

Trim for 80 KIAS

Locate suitable Establish spiral

1000 ft, above

When field can easily be

field.

pattern.

field

prepare

with the backup

ENGAGED

landing

at downwind

IN FLIGHT

tank selector

for

gear

from

position

reached

extend full flaps for

position

power

off landing.

gear

extender,

position

inadvertently free

before

for normal

containing

check

. .

cause

of

to be

.. . adjust

emergency

lock

airspeed

falling.

landing

shortest

to tank

switch

fuel

oN

...

RICH

..

. OPEN

for indication

power loss

of

it is on a

sure

CLOSED

.... oFF

necessary

as

gear

to

drops

approach.

landing.

106

I

|

I

Touchdowns shoutd

flaps.

When

committed to

Landing Throttle

Fuel selector

Mixture

Flaps

gear

.

normally be made

landing:

selector .

.. ..

lgnition

Master

Seat

TSSUED: NOVEMBER

switch ..

belt and

harness

t, 1979

REVISED: SEPTEMBER

I' 1966

at lowest

possible

REPORT:

airspeed

......

. idle cut-off

with full

DOWN

oFF oFF

. set

OFF OFF

tight

VB-1080

3-3

SECTION

3

EMERGENCY

PIPER AIRCRAFT CORPORATION

PROCEDURES

PA.32R.3OI,

SARATOGA

SP

FIRE IN

Source of fire

Electrical Master switch

Vents Cabin heat.

Land as sooh as

Engine Fuel selector

Throttle

FLIGHT

fire

..

fire:

(smoke

.

practicable.

Mixture

Electric fuel Heater and defroster ..

Proceed with

LOSS

Land as soon as

landing.

LOSS OF

pump

power

OIL PRESSURE

OF

FUEL FLOW

off landing

possible

in

cabin)

and

procedure.

investigate cause. Prepare

,...

CLOSED

idle cut-off

check OFF

.....

power

for

check

oFF

off

:

pump

Electric Fuel

fuel

selector

ENGINE DRIVEN FUEL

Throttle

pump

Electric

Throttle

The

indicate a

REPORT:

3-4

fuel

lack of a

leak in

VB-10t0

lf normal

immediately pump should

fuel flow

engine

indication

the fuel

PUMP FAILURE

CAUTIONS

operation

re-established,

be turned

system

or

and fuel flow

OFF.

the

while

fuel exhaustion.

ISSUED;

containing

the electric

electric

fuel

NOVEMBER

check

reset

not

is

fuel

pump is on

on

usable

..

....

required

as

8'

.oN

tank

fuel

retard

oN

could

1979

PIPER

PA-32R-301,

AIRCRAFT CORPORATION

SARATOGA

SP

EMERGENCY

SECTION

PROCEDURES

3

HIGH OIL

Land landing.

TEMPERATURE

nearest airport

at

ELECTRICAL

annunciator

ALT

Ammeter

ammeter

If

...

shows

ALT switch

Reduce

ALT

If

electrical

circuit

switch

power not

breaker ..

ALT switch

If alternator

as

soon

power.

output cannot

practical.

FAILURES

light illuminated

zero

loads

.

restored

The

investigate

and

minimum

to

be

battery

restored,

the

is

problem.

the

reduce electrical

remaining

only

Prepare

. ....

loads

source

power off

for

to verify

check

inop.

check and

required

as

."

land as

and

of electrical

alt.

. OFF

reset

oN

OFF

ELECTRICAL

electrical

FOR OPERATION

Electrical

alternator

If

ALT

Land

Anticipate

ISSUED:

REVISED:

load)

AIRPLANES

load

loads are

switch

soon as

as

complete

NOVEMBER

MARCH

OVERLOAD

WITH

INTERLOCKED

...

not reduced

practical. Battery

electrical

1979

t,

19tl

20'

(alternator

the only

is

failure.

over 20

BAT AND

remaining

above

amps

ALT SWITCH

source

REPORT:

'

known

reduce

.

OFF

power

of

VB-1080

3-5

SECTION 3

EMERGENCY

PIPER

PROCEDURES

AIRCRAFT

PA-32R.30T, SARATOGA

CORPORATION

SP

AIRPLANES WITH SEPARATE

FOR

OPERATION

switch

ALT

switch

BAT

If alternator

soon as

as

load ..

Electrical

Land

alternator

If

loads are

Due to

frequency ON when required by an

loads are

reduced

practical

increased

noise, operation with ALT

and BAT switch

not

reduced

NOTE

system

OFF

electrical

BAT AND

voltage and radio

should be made only

system

ALT switch

switch . as

BAT

Land as

soon as

possible.

If the battery is

Anticipate complete electrical failure.

NOTE

depleted, the

landing

gear

be lowered using the emergency extension

procedure.

inoperative.

gear position

The

lights

ALT

SWITCH

reduce to minimum

switch

failure.

required

must

will be

ON

OFF

PROPELLER OVERSPEED

Throttle

pressure

Oil

control

Prop

Airspeed

Throttle

REPORT: VB-1080

3-6

.....

full DECREASE

then

control available

as required

below 2700

ISSUED:

REVISED: MARCH

NOVEMBER

retard

. . . check

rpm,

set if any

.... reduce

remain

to

rpm

1979

I,

19tl

20,

PIPER

AIRCRAF*T

SARATOGA

CORPORATION

SP

EMERGENCY

SECTION

PROCEDURES

3

EMERGENCY

Prior to

,

)M^t".

Circuit

Radio

Gear

emergency

swirctr..........

breakers................

lights

indicator bu1bs............

If landing

Airspeed......

backup

landing

with

elecfical

all

above

gear

Landing

Emergency

If

Emergency

If

the

LANDING

gear

does

selector

gear

lever

gear

extender)

gear

still

gear

lever

release)

lever

gear

knob

release).

cable

power has been

procedures.

extension

not check

(aircraft

does

(aircraft equipped

(aircraft

GEAR

not check

gear

The

EXTENSION

procedure:

locked:

and

down

equipped

with

and

down

EMERGENCY

airplane,

tailing

(under

lost, the

position indicator

..'....'...'...-.'.off

...OVERRIDEENGAGED (while

locked:

-.-..Hold

emergency

DOWN

gear is down

until

normal conditions

10

seconds

.PULL,

normal

10

seconds

landing

to

while

conditions

to

gear

must

will

lights

...............check

.'....."""check

(in

daytime)

..........check

..below

92

""""""""'DOWN

airPlane)

tailing

fish

goar lever

position, while

and

take

will

down

extended

be

illuminate.

not

and

airPlane

take

and

be down

fish tailing

be

ON

KIAS

in the

fish

locked approx. locked)

approx.

locked)

using

RECOYERY

SPIN

Rudder.........

Control

whee1...........

Throttle.......

Rudder.........

Control

ISSUED: NOVEMBER

REYISED: SEPTEMBER

wheel..........

8'

1979

18'

...."""""""nsutra1

1990

.'.........""""fu11opposite

direction

'full

neufializing

(when rotation

regain

required

level

.....""""'as

REPORT:

rotation

of

ailerons

smoothly

to

attitude

while

stops)

forward

.................id1e

flight

VB-1080

3'7

to

SECTION

3

EMERGENCY

DOOR

OPEN

If

airspeeds

botl

upper and

be

will

PROCEDURES

latches are

side

reduced

slightly.

PIPER

open,

AIRCRAFT CORPORATION

PA-32R.301, SARATOGA

slightly

the

door will

rail

open

SP

and

To close the door

Slow airplane to

vens

Cabin

window

Storm

Ifupper

If

latch is

latch is open

side

latches are open

both

in flight:

KIAS

92

open.............

'.......'.."......pu11

moving

...............c1ose

"""""'open

'........1atch

armrest

on

latch

latched

to

..latch

then

while

handle

position

side

toP

larch larch

REPORT: VB-1080

3-8

ISSUED:

REVISED:

NOVEMBER

MARCH

8,

20'

1979

1981

PIPER

AIRCRAFT

PA.32R.3OI,

CORPORATION

SARATOGA

SP

EMERGENCY

SECTION

PROCEDURES

3

AMPLIFIED EMERGENCY

3.5

The following

information

understanding

emergency situation.

an

ENGINE

3.7

Engine

attempt

fuel

to extinguish

back into the

lf a

control

attempt

the engine.

J

should

an

to idle cut-off,

If the engine

either case

ln

be extinguished

The

external

for thi

putpo-t. äf

of the recommended

FIRE DURING

fires

during

induction

present

fire is

to

fuel selector

the

draw

has started, continue

(above),

fire extinguishing

paragraphs

START

start are

the fire

fire

valve should

is

to

system.

before

open

by

the

the throttle and

into the engine.

back

if fire continues

the best available

method

PROCEDURES

presented

are

providing

usually the

try to start

be oFF and

the

of action

course

engine

has

operating to

more

is to be

result of

to

pilot

with

and

overpriming.

the engine

started,

the

crank

try

than

external

the mixture

used.

(GENERAL)

supply additional

the

This

pull

the

seconds,

at idle

complete

cause

The

mixture

fire

cut-off

ä more

probable

and draw

move

engine.

to

a few

means.

first

excess

is an

into

the

of

fire

if

3.9 ENGINE

proper

The

the circumstances

depend

on

If sufficient

landing

the

baci-up

ENGAGED

airspeed and

the

The

TSSUED:

gear

If the area ahead

gear

selector

gear

lf sufficient

älectric

fuel

alternate

NOVEMBER

POWER

action

runway remains

down

extender,

position.

altitude

switch the

pump

air should

LOSS DURING

to be taken

land straight

and

is

rough,

to the UP

switch

latch

has been

fuel selector to another

insure

to

REVISED: SEPTEMBER

if

of the

to complete

it is necessary

or if

the emergency

gained

that it is

be OPEN.

1979

t,

l,

l9t6

of

loss

particular

ahead.

position.

to attempt

ON

TAKEOFF

power

occurs

situation'

a normal

to clear

On aircraft

gear

lever

a

tank

that

and

takeoff

during

landing,

obstructions,

equipped

in the OVERRIDE

restart,

containing

mixture

the

leave

maintain

fuel.

is RICH.

REPORT:

will

the

move

the

with

safe

a

Check

VB'10t0

3'9

SECTION

3 PIPER

EMERGENCY

PROCEDURES

AIRCRAFT CORPORATION

PA.32R-30T,

SARATOGA

SP

aircraft

On

will extend

approximately 103

iJ ioughly halved. If the situation

in thc retractcd

OVERRIDE ENGAGED

If cngine failure was

regaincd after switching

may require up

power

If

(refer

to the emergency

ENGINE POWER

3.1T

Complete

power

and

occuis at

(refer

to

maintained.

If altitude

fuel

and the

the cause of

selector

turn the electric

and

alternate air

position

equipped with

automatically

KIAS.

position

to ten seconds.

is

regained,

not

power

engine

restored

will be

a low altitude,

paragraph

the

3.13).

permits,

to OPEN.

power

to be

when

The

by

position.

caused

tanks until

fuel

proceed

checklist

LOSS

loss is

shortly after

first step

the

An airspeed

switch

pump

fuel

If no

loss.

it is on a

sure

glide

latching

the fuel

Check

the backup

engine

distancewith

dictates,

the emergency

fuel exhaustion,

by

the empty

with

paragraph

and

FLIGHT

IN

usually caused

fuel

is

to

selector

Move the

ON.

the

fuel flow is

tank containing

gear

extender,

power

the

the landing

Power Off

3.

flow is

prepare

of

for an

at least

to

mixture

gauges

engine

indicated,

fails at

landing

gear

power

lines are

fuel

Landing

l3).

fuel

by

restored,

emergency

92 KIAS

another

for an

fuel.

the landing

speeds below

gear

extended

retained

can be

gear

flow

tank containing

controlto

check

in the

lever

not be

will

filled.

procedure

interruption

power loss

If

landing

should

RICH

indication

the tank

Sear

,

This

be

of

REPORT:

3r0

VFlOto

ISSUED:

REVISED:

NOVEMBER

SEPTEMBER

1979

8'

I, 1986

PIPER AIRC

PA-32R-301,

RAF'T

SARATOGA

C ORPORATION

SP

SECTION

EMERGENCY PROCEDURES

3

When

position,

necessary.

)

landing.

BOTH. Move

This may restore

there is

fuel

may restore

normal.

restored

may require

(refer

3.13

OVERRIDE

prevent

with the backup

KIAS, Air

restore

airports

have

power

turn

preceding

If

the

If

time

partial

a

could take

power.

If

engine

after switching

power

If

to the emergency checklist and

POWER

If loss

is restored move the alternate air to the CLOSED

OFF the electric

permits,

the

throttle

power

fuel

some time

failure was caused by

up to ten

is

not regained,

OFF

power

of

ENGAGED

landing

gear

Cond. off) and

power

are not effective, and

in

immediate vicinity; it may be

the

sufficient altitude.

windmilling and the

will navel approximately

If

another

If

wind condition.

intentions.

pump

fuel

steps do

turn the

system

power

If

seconds.

not restore

ignition

mixture

and

problem

if

the

restriction.

to be used up, and allowing the engine

loss is due

fuel

until the empty fuel lines are

tanks

proceed

and adjust the

power, prepare

switch

is

to

fuel

to

control

levers

rich

too

Try

other

water, fuel flow indications

exhaustion,

with the Power

paragraph

3.13).

LANDING

occurs

at altitude,

position

before airspeed drops

from inadvertently

extender, trim the aircraft

for

look

At

propeller

possible,

pilot

gliding

best

control

1.5 miles for

notify

the

passenger

or

lock

free

falling on aircraft

a suitable field.

if

permits,

time

possible

angle, with no wind, with the

in full DECREASE rpm,

each thousand

FAA

is

by

aboard,

radio

mixture

for an emergency

L then to

R

then

to different

mixture

lean a

or too

fuel tanks. Water

power

Landing

Off

emergency

gear

to 106

best

gliding

for

If measures taken to

your

check

to land at one

feet

altitude

of

your

of

let him help.

difficulty

control

back to

settings.

or

in

the

to windmill

will be

not

will

filled. This

procedure

lever in

KIAS to

equipped

(80

angle

charts

you

if

engine

aircraft

the

in

a

and

as

if

be

for

no

When

field. Try to

this make

extend

widening

ISSUED:

normal

a

full flaps for the shortest

REVISED:

you

have located

1000 feet

be at

landing

your pattern,

using

NOVEMBER E,

SEPTEMBER

a suitable

approach. When the

field,

establish a spiral

above the field

landing. Excess

flaps

or slipping,

1979

1, 1986

pattern

downwind

at the

field

a combination of these.

or

easily be

can

altitude

may

REPORT: VB-1080

around

position,

reached,

lost

be

3-11

to

by

SECTION

3

EMERGENCY

Whether

If

factors.

bring

,*lä

better

to

wheels-up

I

lwill

lconditions,

t

g"r

the

plane

the

o, other

protect

be äxcessively

landing

airplanes

On

ran

free

will takä

landing

op

OVERRIDE

prevent

landing

the

Touchdown

PROCEDURES

to attempt

a

field chosen

stop,

to a

large obstacles

occupants

the

or

sofi

normally

will

equipped

at airspeed-s

approximately

is desiä,

ENGAGED

gear

from

normally

should

PIPER

landing is obviously

the

short,

below

it will

with

gear

should

in ttre

aircraft.

the

of

or

be safer

with the

approximately

necessary

be

smootl

field,

when

backup

10 seconds

position before

inadvertently

made at

be

AIRCRAT-T

PA-32R.301.

gear

up

down.

be

gear

the

however,

If,

landing

do

and

gear

to

airspeed

the

free

the

down

or

firm,

and

If there

in

the

water

in

less damage

extender,

KIAS

103

down

to be

latch the

dlops

falling'

possible

lowest

C ORPORATION

SARATOGA

many

depends

and

down

field

and,

ovenide

on

long enough

stumps

are

position

is suspected

depth,

of any

airplane'

the

to

landing

ttre

normal

under

locked.

and

lever

KIAS

106

to

airspeed.

in the

SP

to

or

will

a

gear

If a

to

(a)

Down

Gear

When

landing

and

oFF

master

the harness

normally

If the

retracted.

Landing

committed

gear

DoWN,

move the

and

(if

instailed)

made at

master

to

close

mixn[e

ignition

should

lowestpossible

the

swirch

gear

a

throttle,

the

idle

to

switches

be

NOTE

is OFF,

emergency

down

nrrn

oFF.

After

The seat

cut-off.

tightened.

airspeed'

gear

the

landing'

selector

fuel

the

flap

final

belts

Touchdown

be

cannot

setting,

and

should

select

valve

nrn

shoulder

be

to

REPORT:

3-12

VB-1080

ISSUED:

REVISED:

NOVEMBER

SEPTEMBER

8,

18'

1979

1990

PIPER

PA.32R.3{II,

AIRCRAFT

CORPORATION

SARATOGA

SP

EMERGENCY

SECTION

PROCEDURES

3

(b)

Gear

the emercencv sear

;;;;;;;ä";t.";;;l;;In

bclow

,"tr"toi

hn"i

r""t

io".frOo"n

airspeed.

FTRE

3.I5

The

tt

cabin.

iirt*.lnt

to bc

action

Check

an

lf

sfrouiO

l;;ff

bc

bnF.

Up Landing

aircraft

On

103

When

nutnc

nup

b.l6

IN FLIGHT

prcsence

essential

is

readings,

taken

thc

for

clcctrical

turncd

Ä

KIAS.

committed

to

ietting,

slbuldei

and

should

firc

of

thaiitt.

"huru.t.,

differs

source

firc

.

Off

runding

equipped

levär

to

and

OFF

it.

turn

hurn.rt

Ue

is noted

rour".

of

somewhat

the

of

is indicated

cebinvents

ffri

shor,ld

be

the

with

OVERRIDE

the

in

inadue't"ntlv

landing'

move-rhe

.otter

(if

normutiy

through

lire

of the

smoke,

each

in

first'

fire

(smoke

should

as

madc

backup

close

mixturc

and

insülled)

made

smoke'

by

oi

case'

in

soon

,qear

öNGAGED

extendins

throttle

the

to

ignition

should

the

at

smell

promptly.identilied

indications

other

cabin),

the

opcncd

be

possible'

as

extender'

at

turn

'

cut-off'

idle

switches

be

lowest

and

master

the

and

latch

position

airspeeds

fuel

the

After

The

oFF'

tightened'

possible

in

heat

through

sincc

switch

heat

cabin

the

I

lfanenginefireisprcsent,switchthefuelselectortooFFandclosethe

cut-off.

idle

throttlc.

oFF.

communication

permits,

The'mixture

landing

a

cases,

ln all

The

extremely

gencral

äetermining

emergcncy'

ISSUED:

REVISED:

NOVf,MBER

DECEMBER

sirould

trri-[."rc,

not

is

should

possibility

be at

requircd

be

t.Äot..

pilot

änd

factor

1979

t'

l0'

and

select

made

of

l9t6

NOTE

an

defroster

master

immediately'

cngine

Thc

judgment

for

Turn

should

switch

fire

procedurc

should

action

in

the

oFF.

flight

given

be

such

elcctric

oFF.

be

lf

is

-is

the

an

REPORT:

fuel

lf

the

VB'10t0

pump

radio

terrain

3-r3

SECTION

3

PIPER

EMERGENCY PROCEDUNES

AIRCRAFT

PA.32R-30I,

CORPORATION

SARATOGA

SP

LOSS OF

3.I7

of oil

Loss

pressure usually

oil

landing should

a

systlm,

cause

may

airport

gaüge malfunciion, the

such

settings

and

prevent

and

A complete loss of

the result ofa faulty

be

and be

time as a

unnecessarily,

Depending

airportiandin[

piessureioss,

of äctual

smoke, are

3.I9

fuel

flow

on a

oil

apparent,

lf cngine

LOSS

The most

tank

occurs,

stoppage

OF

probable

selcöted

turn ON

tank containing

PRESSURE

OIL

pressure

indicates

engine

prepared

dead stick

the circumstances,

on

power isstill available,

while

FUEL

failure

or

the electric

may

damage.

pressure

oil

for a

engine

landing

as this

such

an airport

and

occurs,

FLOW

cause

usable

either

be

a malfunction

made as

be

indication

gauge. ln

forced

of

either

landing.lf

may stop

can be

hasten complete

may

suddcn

as

proceed

loss of

thc engine

pümp

fuel

fuel.

partial

is not close.

or

complete'

in

the

possible

as

soon

may

procced toward

case,

the

suddenly.

accomplished.

it may

bc advisablc

particularly if othcr

increases

with Power

fuel flow

is either

driven

check

and

;

pressure

oil

signify

problcm

Maintain

Dont

power

temperatures,

in

Off

fucl depletion

pump.

fucl

that

partial

A

investigate

to

cxhaustion

oil

the nearest

is not-a

altitude

change

loss.

to make

indications

Landing.

lf

fuel

the

of

loss

regulating

the

or

pressure

until

power

an off

oil

or

in thÖ

fuel

of

loss

selector

is

,,

loss of

lf

electric

fuel

After fuel

flow

lf fuel

nearest

suitable

REPORT:

3r4

pressure is due

fuel

pump will

flow and

drop,

to

starts

airport

normat

lf

immcdiately

pump should

indication

how

syst€m,

VB-10t0

supply

power

are

turn

*oon as

"i

engine

re-established,

be turned

could

or fuel

exhaustion.

faiture

to

sufficient

regained,

the electric

possible

CAUTION

operation

indicate

of the engine

flow.

fuel

turn the

fuel

have

and

fucl flow

and

clcctric

the

The lack

off.

lcak in thc

a

ISSUED:

driven

electric

pump

oN

the cause

is

of fuel

NOVEMBER

fuel

fuelpump

and

invcstigated'

not

fuel

pump the

oFF.

at

land

t'

the

1979

PIPER

AIRCRAFT

PA-32R-30I,

CORPORATION

SARATOGA

SP

EMERGENCY

SECTION

PROCEDURES

3

BNGI\TE

3.2I

an e

If

turn ON

should

of

cause

L;ICH

3.23

A.

levet,

oil

defective

airport

A steady,

nearest pressure

DRIVEN

ngine driven

:hJelectric

made at

be

the failure

the

If normal

immediately

pump

how

system,

TEMPERATURE

OIL

abnormally

an obstruötion

gauge,

and

or

have the

rapid

gauge

and

for an

airpäit

FUEL

pump failure

fuel

pump.

fuel

nearest

investigated.

engine

re-established,

should

be

indication

fuel

or

temperature

oil

high

the

in

causes.

other

investigated.

cause

oil temperature

in

rise

mechanic

let a

accompanying

PUMP

throttle

The

appropriate

CAUTION

operation

indicate

as

Land

investigate

loss

off'

turned

:ould

exhaustion.

oil c<.,oler,

FAILURE

indicated,

is

should

airport

fuel

and

the

lack

The

leak

a

indication

damaged

as

soon

is a sign

the

pressure.

of

retard

be

then

flow

of a

in the

may be

improper

or

of

as

is not

fuel fuel fuel

trouble.

as soon

electric

practical at

problem'

the throttle

reset. A possible

caused

landing

and the

a

by

baffle.:"Is,

an appropriate

at

Land

Watch

the oil

and

low

a

the

ELECTRICAL

3.25

Loss of

ammeter.

and

is zero

the landing

as

The

can

electrical

failure

alternator

plished by

troubl.

ihe and up)

TSSUED:

this

REVISED:

FAILURES

alternator

not

light.

be

executing

merely

lf

assutned.

no

Before

load

circuit

moving

breakers

is to

step

the

caused

was

procedure

NOVEMBER

MARCH

output

fhe

tow by

increase

should

for a

attempt

switch

ALT

a

by should

8'

19t1

20'

is detected

following

actuating

in the

reduced

be

popped

reset

to

to oFF

momentary

return

1979

through

procedure,

electrically

an

ammeter

the

the ammeter

reading

much

as

circuit.

overvoltage

one second

for

overvoltage

reading

zero

insure that

powered

is noted,

possible. Check

as

relay. This

condition

a normal reading.

to

the

dev-ice,

and then to

(16.5

REPORT:

on the

reading

such

alternator

the

is

accom-

oN. If

volts

VB-1080

3-15

SECTION

3

EMERGENCY

ammett r continues

the

If

not remain

and

battery.

3.26

electrical

reset, tur

as soon

land

ELECTRICAL

load)

PIPER

PROCEDURES

indicate

.

off

as p'actical.

OVERLOAD

to

the ALT

All

switch,

electrical

(alternator over 20 amps

AIRCRAFT CORPORATION

PA-32R-3OI'

output,

"0"

maintain

load is being

SARATOGA

if

or

the

minimum

alternator will

electrical load

supplied

above

SP

the

by

known

abnormatly

If

known

above

battery,

low

a

battery,

a low

minutes.

5

ALT

off

switch

turning

and the

remaining

failure.

airplanes

For

BAT switch

continue

and

ON

decrease

within

practical.

high alternator

electrical

battery

a

indication

the

overload

the

lf

non-essential

operation,

switch

oFF and

source

All

of electrical

with

and the ammeter

OFF

to monitor

minutes,

5

electrical

Due

noise,

the BAT

when

llthc

lowered using the

be

procedure.

inoperative.

output

operating

for the

load

other

or

fault

should

begin

condition

equipment.

the electrical

when

land as soon

power. Also

separate

loads are

BAT

the ammeter.

the BAT

turn

being supplied

NOTE

higher voltage

to

operation with

switch OFF

required by

an electrical

NOTE

battcr'-\ rs dcplcti:tl.

gear position

The

is observed

conditons)

abnormal

persists attempt to

For

as

electrical

to decrease

airplanes with

load cannot

practical.

The

anticipate

ALT switch

and

should

decrease' Turn

If the alternator

switch OFF

the alternator.

by

radio frequency

and

the ALT

should

switch ON

be made

failure.

t.rll(llnr

tlli

cmcl'gency cxtcttsiort

S..r,

lights

(more

it

may

load.

towatd

normal

reducethe

interlocked

be reduced

battery

complete

operations,

the

output

land

and

only

.,.,,

be

will

20 amps

than

caused

be

cause is

If the

within

load by

is tlie only

electrical

turn

B,AT switch

does

as soon

by

BAT

turn

the

not

as

REPORT:

3-16

VB-1080

ISSUED:

REVISED:

NOVEMBER

MARCH

1979

8,

20, 1981

PIPER AIRC RAT"T

PA-32R-301,

PROPELLER

3.27 Propeller

governor

full low

If

pressure.

oil

rpm

and then set if

throttle

SARATOGA

low

or

pitch.

propeller

The

used to

overspeed is caused by a

oil

overspeed should occur,

propeller

maintain 2700 RPM.

C ORPORATION

SP

OVERSPEED

pressure

which allows the

control should

any conEol

is

available. Airspeed should be

SECTION

EMERGENCY PROCEDURES

malfunction in

propeller

retard

the throttle and

moved to

be

blades to rotate to

full DECREASE

the

reduced

propeller

check the

3

and

3.29 EMERGENCY

Prior

that the master swirch is

it

is daytime,

indicators for faulty

proceeding

to

the

Refer

emergency extension

I

If

to below 92

the

raining

landing

KIAS. Move

LANDING

with an emergency

ON and that the circuit

radio lights

bulbs.

to

purposes.

gear

should be turned

Par. 4.39 for

not

does

the landing

On aircraft equipped with the

gear

lever in

If

tle

OVERRIDE ENGAGED

the

landing

gear

still

does

a. On airplanes equipped with the

emergency fish

tailing the airplane.

gear

lever in

b. On airplanes equipped with the cable

extend knob

Under normal conditions,

require

approximately

fish

while

eittrer of the above

10

seconds for

GEAR

EXTENSION

gear

extension,

breakers

off. Check

NOTE

differences

procedure

check down and

gear

backup

not check down and locked:

gear

EIvIERGENCY DOWN

the

performed

is

locked, reduce the airspeed

selector

extender,

position

lever release,

to the

place

fishtail the airplane.

and

position

release, PULL the emergency

ailing the airplane.

procedures,

the

gear

to extend

and

check

not

have

the

when

for

DOWN

the emergency

position

as

appropriaüe,

lock

down.

to insure

opened.

landing

position.

hold

and

If

gear

the

while

will

If all electrical

using the above

illuminate.

)

ISSUED:

REVISED:

NOVEMBER

power

has

been

procedures.

8,

The

1979

SEIrIEMBER IE, t990

lost,

gear position

the

landing

gear

must be extended

indicator

REPORT:

lights will

VB-1080

not

3-17

SECTION 3 EMERGENCY PROCEDURES

PIPER AIRCRAF"X C ORPORATION

PA-32R.301,

SARATOGA

SP

3.31 SPIN

Intentional

RECOVERY

spins

inadvertently entered,

direction of

the ailerons.

rudder

the

regain

3.33 OPEN

The cabin door

rotation.

Move

and

level flight attitude.

a

DOOR

Move

the

ease back on

is double

throttle to

flight at both the top and

latch,

upper

This

open.

door will

made with the door open.

If

bottr upper and

and airspeed will be

To close the door

vents

and open

latch is

latched

latch.

not fully engage

or

will usually

not affect

the storm

pull

open,

position.

happen

normal flight characteristics,

side

reduced slightly.

in flight, slow the

on the

If both

prohibited

are

in this airplane.

immediately apply

IDLE.

remote.

the side

If

the

while

wheel

When

wheel

However, should

latch, the door

or soon

airplane

top

moving the

close

the conftol

the control

latched, so the chances

side are

at takeoff

larches are open,

window.

armrest

latches are open,

rudder opposite

full

forward while

full

rotation

the

required

as

its springing

of

afterward.

normal

and

the door

latch is open,

will trail

KIAS,

to 92

the side

If

stops,

you

qpring

may

partially

A

landing can

slightly

close

latch il.

handle to the

latch

latch then

a spin

to the

neunalizing

neumlize

to smoothly

open

forget the

partia[y

open

open'

the cabin

If the side

the top

is

in

be

3.35

ENGINE

ROUGHNESS

Engine roughness

induction filter icing,

First adjust the

rough if

the

mixture

Move the alternate

pump.

fuel

Switch

problem.

the

Check

are abnormal

REPORT: VB-1080

3-18

the

engine

the

proceed

may be caused

ignition

or

mixture

is too

selector

for maximum

rich

to OPEN and

air

to another

gauges

accordingly.

problems.

lean.

or too

tank to see

for abnormal

REVISED: SEPTEMBER

by dirt

in the

smoothness.

then turn

readings.

ISSUED:

injector

The engine

ON the

contamination

if fuel

gauge readings

If

any

NOVEMBER

nozzles,

will run

electric

8,

18,

fuel

is

1979

1990

PIPER PA.32R.301,

"BOTH.'

,

)

magneto at available

discretion.

AIRCRAFT

The

roughness

If

CORPORAIION

SARATOGA

magneto switch

If

operation

reduced

airpoft.

powef

persists,

SP

be

should

then

is satisfactory

RICH

full

with

prepare for a

EMERGENCY

to'f-"

moved

magneto'

either

on

mixture

precautionary

PROCEDI.JRES

"R,"

then

landing

a

to

landing

SECTION

back

then

proceed on

the

at

pilot's

at

3

to

that

first

ISSUED: SEPTEMBER

18,

1990

REPORT:

VB-1080

3-19

PIPER

AIRCRAFT

PA-32R-30I,

CORPORATION

SARATOGA

SP

NORMAL

SECTION

PROCEDURES

4

GENERAL

4.T

section

This

normal

procedurös

üy

operations

and those

the operating

Normal

equipment

(Supplements).

review

aircraft.

all

this

airplane.

supplies

operation

which how

in-flighi

should

which

procedures

These

to supply

and

Pilots

first

un

u.iion

in order

section

The

of

remainder

The

provide

perform them.

to

reference

used

be

SECTION

NORMAL

describes

for the

n"".traiy

design

and

the

airplane.

PROCEDURES

recommended

operation

for

features

procedures associated

require

ihould

portion of

sequence

the sYstems.

detailed

for this

handbook

are

inforniation

familiarize

become

to

this

section

the

of

information

This

the

to

due

PurPose.

provided

on

proficient

section

consists

for normal

is devoted

portion of the

lengthy

4

procedures

the

of

All

of the

airplane

the

of

those

with

supplements

present a

to

procedures

themselves

in the normal

of a short

operations

to amplified

eXplanations

and

section

explanation.

r.equired

airplane

optional

provided

are

source

which

the

with

is not

The

the

for

(FAA

presented'

are

of

not the

are

procedures

operations

check

fgrm

emphasis

little

normal

procedures

of the

intended

short

conduct

regulations)

determined

as

systems

in Section

reference

same

given in

list

procedures

for use

checklist

form

of

and

for

of the

which

on the

and

an

as

9

4.3

,

i

of tne

under

ISSUED:

REVISED:

AIRSPEEDS

following

The

ai.plane.

standard

Tf,ese

conditions

NOVEMBER

SEPTEMBER

FOR SAFE OPERATIONS

are

airspeeds

figures

8'

are those

are

at sea

1979

17'

which

for standard

level.

19E4

airplanes

significant

flown

REPORT:

operation

the

to

gross weight

at

VB-1080

4-l

SECTION

NORMAL

4

PROCEDURES

PIPER AIRCRAFT CORPORATION

PA-32R-301,

SARATOGA SP

Performance for

depending airplane and equipment,

(a)

(b)

(c) (d) (e)

(0

upon

Best

Rate of

gear gear

Best

Angle of

gear gear

Turbulent Air Maximum Flap Landing Maximum Demonstrated

a specific airplane may vary from

the equipment installed,

Climb Speed

down, flaps up .....

up, flaps up

Climb Speed down, up, flaps up

Operating Speed

Final Approach

the condition

atmospheric conditions

flaps up

(See

Speed.

(Full

Speed

Crosswind Velocity

published

of the engine,

and

piloting

technique.

... 80

.. .9I

.

.76

.

..80

Subsection 2.3) . 134

. . . I 12 KIAS

Flaps)

... . 79 KIAS

.. .. 17

figures

KIAS KIAS

KIAS KIAS KIAS

KTS

REPORT:

4-2

VB-I080

ISSUED:

NOVEMBER

8, 1979

PIPER

PA-32R-301,

AIRCRAFT

CORPORATION

SARATOGA

SP

:"'t

NORMAL

SECTION

PROCEDURES

4

....f...

*

NORMAI,

4.5

PREFLIGHT

COCKPIT

Control

Parking

Allswitches...'

Avionics

Mixture

Master Fuel Annunciator Flaps.

Master Primary

Trim

wheel

brake

switch

gauges

switch

flight

.

WALK.AROUND

PROCEDURES

CHECK

..

.

Panel

controls.

. .

*

+

Figure

CHECKLIST

t

4-l

't...

*

ä

.)..""""""

+

. release

. .

.

...

.f

t

restraints

set

.

..

. OFF

OFF

.

.....idlecut-off

. check

.

proper oPeration

ProPer

oN

"

'..

quantitY

....check

oFF

....

oPeratron

neutral

ISSUED: REVISED:

NOVEMBER

SEPTEMBER

8'

1979

17'

19t4

REPORT:

VB-1080

4-3

SECTION

NORMAL

4

PROCEDURES

PIPER

AIRCRAFT

PA-32R.301,

CORPORATION

SARATOGA

SP

systems

static

and

Pitot

Windows Required

Tow

Baggage

RIGHT

bar

PaPers

and

door..

WING

baggage'

Surfacecondition....

Flap

Aileron Wing

tank

Fuel

tank

Fuel

tank

Fuel

quanttty

Fuel

down

Tie

tip

and

vent.

sumps

and

hinges

lights.

.

'.

gauge

chock

..

hinges

and

Maingearstrut.....,

..

Tire

block

Brake

air

Fresh

NOSE

General

Cowling Windshield Propeller

SECTION

Air inlets

Chock

gear strut

Nose

wheel

Nose

Engine

..

oil .

Dipstick

filler

Oil

strainer

Fuel

Baggage

Landing

inlet

condition

and

baffle

cap.

door..

light.

and

.

sPinner'

.

tire

'

seals

.

drain

.

disc

check

..

ProPerlY

. close

ice,

of

.

'

and

'....dratn

clean

check

board

on

- secure

secure

and

snow

frost,

'check

"

check

'

check

.

'

suPPlY

check

- secure

'

check

ProPer

'check

"

remove

.

proper

' '

(4.5

t .5

cap

clear

for

fuel

in')

' '

. .

stow

.....

..

clear

'

'.

.

..

visuallY

.. drain

sediment

water,

..

',

inflation

'..check

.

....

'.check

clear

'

check

.

secure

clean

'

check

.

clear

'

. removg

,

..

.

proper

t.25

'

quantitY

'

and

in')

check

seated secure

under

secure

inflation

.

(3'25

......check

....check

..

ProPerlY

...

container

place

.

. . .

.

close

.....check

REPORT:

4-4

VB-1080

ISSUED:

REVISED:

NOVEMBER

SEPTEMBER

8,

l7'

1979

1984

PIPER

PA-32R-30r,

AIRCRAFT CORPORATION

SARATOGA

LEFT WING

Surface condition

air inlet

Fresh

chock

Tie down

Main

Tire

Brake Fuel Fuel

Fuel Fuel

Pitot/static

Wing tip and

Aileron

Flap

and

gear

strut

..

and

block

quantity

tank

tank vent.

sump.

tank

head ..

hinges

and

hinges

and

gauge

lights

EMPENNAGE

SECTION

SP

. .

NORMAL

PROCEDURES

of

clear

ice, frost, snow

...' clear

4

.. remove

proper

. .

.

disc

water,

: : : ::T:l:

: : :

inflation

visually

drain

sediment

:::::

. . .

(4.5

check

- secure

check

and

ProPer

: i:'::;::i

.....'check

....

in.)

.5

t

. check

check

. . check

supply

cap

. clear

for

fuel

'.check

Antennas General

Baggage

condition

Tail lights

Elevator Rudder

Tie down

MISCELLANEOUS

Fuel strainer

Masterswitch..'.

switch

heat

Pitot Interior Exterior

Fuel

)

Pitot

Stall

ISSUED:

REVISED:

lighting

strainer

.

warning

NOVEMBER

.

. .

..

switches

drain'....

. . ..

horn

8, 1979

SEPTEMBER

17,

1984

....drain

:::::::1::l'sll

i":

.. ON

. ..

.....ONandcheck

visuallYcheck

.....

contents

dispose

and

REPORT:

.. ...check

.....check

....check

.. remove

and

'.

and

container

of

valve

-

- warm

check

. .

VB-1080

check

oN

check

secure

check

4'5

SECTION

NORMAL

4

PROCEDURES

PIPER

AIRCRAFT CORPOhATION

PA-32R-301,

SARATOGA

SP

switch . ..

heat

switch

and harness

belts

STARTING

brake

switches

. ...

.

lighting

All

Pitot

Master

Passengers

doors

All

Seat

BEFORE

Parking

Propeller......

selector

Fuel

Radios

STARTING

Throttle

. .

ENGINE

Masterswitch..,.

pump

Electric

Mixture

Starter. Mixture Throttle

Oil

fuel

pressure

.

..

ENGINE

WHT]N COLD

..... oFF

....

. close and secure

fasten

check

full INCREASE

. . desired

adjust

/

inertia

..

I12" open

board

reel

set

rpm

tank

OFF

adjust

check

STARTING

Throttle

Master Electric fuel

ENGINE

switch

pump

Mixture

Starter.

Mixture

Throttle

Oilpressure.....

REPORT: VB-I080

4-6

WHEN HOT

. idle

.....engage

.,

ISSUED: NOVEMBER

REVISED: SEPTEMBER

I12" open

.. oN

ON

cut-off

..advance

adjust

....check

1979

8'

1984

17,

PIPER

PA-32R-301,

AIRCRAFT

CORPORATION

SARATOGA

SP

NORMAL

SECTION

PROCEDURES

4

STARTING

Throttle

ENGINE

Masterswitch...

Electric

Mixture Starter.

Mixture

Throttle

Oil

STARTING

Master switch

All

Terminals

External

Proceed

Throttle External

Master

Oil

WARM.UP

Throttle

fuel

PumP

Pressure....'

WITH

power

with

power

switch

.,

.

equiPment

normal

electrical

pressure

WHEN

EXTERNAL

Plug...

start

Plug...

. .

FLOODED

POWER

SOURCE

,. .

disconnect

,. .

insert

...

Iowest

- check

ON

1000

full

open

oN

....

... oFF

idle cut-off

....engage

...advance

retard

....

..check

...

OFF

. . OFF

.'...connect

fuselage

in

possible

from

ro

RPM

fuselage

ammeter

.....check

RPM

1200

TAXIING

Chocks

area

Taxi

Parking

Throttle

Prop

Brakes.

Steering

ISSUED:

brake

.

. .

REVISED:

..

'.

NOVEMBER

SEPTEMBER

8'

1979

17'

1984

.....

. .apply

.....check

REPORT:

removed

.

release

.

slowlY

high

VB-1080

clear

RPM

4-7

SECTION

NORMAL

4

PROCEDURES

PIPER

AIRCRAFT CORPORATION

PA-32R-301,

SARATOGA

SP

GROUND

I Parking

Propeller.

Throttle

Magnetos

Vacuum

temperature

Oil

pressure...

Oil

CHECK

brake

Air conditioner

Annunciator

Propeller.

panel

Alternateair....

pump

Electric Fuel

Throttle

BEFORE TAKEOFF

Master switch

Flight

fuel

flow

instruments.

Fuelselector.....

pump

Electric Engine

fuel

gauges

Alternateair.....

backs

Seat

Mixture ...

Prop ..

Belts/ harness

Empty seats

Flaps.

Trim tab

Controls Doors

Air

conditioner

Parking

.

brake . .

.

. ...

.

max.

- max.

.. . .4.8" to 5.2"

: : : : : : : : : : : : : : : :

.....

full

INCREASE

. 2000

175

50

RPM

...

drop

diff.

......check

. .....check

press-to-test

. .. . exercise

- then

full INCREASE

......check

......

......check

..... retard

.. oN

. check

proper

.

.. oN

. check

... CLOSED

. erect

yl:ii:*mt

snugly

fastened

.... set

latched

. .

.... oFF

release

. . .

set

Hg.

oFF

tank

set

. set

free

REPORT:

4-8

VB-l080

ISSUED: NOVEMBER

REVISED:

SEPTEMBER

8, 1979

17, 1984

PIPER AIRCRAFT

CORPORATION

PA.32R.$I, SARATOGA SP

TAKEOFF

NORMAL

SECTION

PROCEDURES

4

Flaps

.

Ttrim

.

Accelerate to

74

Control wheel ..

..

OR

.

to

wheel

SOFT

58

SHORT

Flaps

Trim Throttle ..

Accelerate

Control

After breaking

weight.

(OVERRIDE

Gear

equipped

Accelerate

Flaps

with backup

to

.

climb

CLIMB

rate

angle

route

(3600

up)

(3600

up)

fuel

(3600

pump

Best rate

(flaps

Best

(flaps

Best angle

(flaps

Best

(flaps En Electric

to

KIAS,

80

FIELD,

to

KIAS depending

66

ground,

accelerate

ENCAGED on

speed

(gear

lb)

(gear

lb)

(gear

lb)

(gear

lb)

depending

OBSTACLE

gear

extender). ..

down)

up)

down)

up)

to 6l

aircraft

on aircraft

CLEARANCE

.....

on aircraft

to 7l KIAS

.....retracted

slightly

weight

back

to

power

full

back

to climb

climb

rotate

slightly

weight.

....

.

rotate

depending

....r€tractslowly

OFF

aft of

pressure

of

aft

brake

pressure

on aircraft

. . .80

.. .9I

. . .76

. ..80

r05 KIAS

.. .

at a safe

neutral

attitude

. .25"

neutral

prior

release

attitude

UP

KIAS

altitude

to

ISSUED:

REVISED:

NOVEMBER t,

SEPTEMBER

1979

I, 19861

REPORT:

VB-10E0

4-9

SECTION

NORMAL

CRUISING

Reference,

power

Normal

Power

Mixture

APPROACH

Fuel

Seat

Belts/harness Electric

Mixture

Propeller.

Gear Flaps.

4

PROCEDURES

performance

max

fuel

table.

Power

PumP

setting

selector

backs

.

AND

...

..

Airconditioner......

charts,

LANDING

..

'

. ..

PIPER

Avco

AIRCRAFT

PA.32R.3OI,

l'ycoming

CORPORATION

SARATOGA

Operator's

. set

. .

,

. down

Pcr

-

.

fasten

132

. set

Manual

.....75V0

Power

...

proper

. erect

/

..

. ..

..

KIAS

white

-

...

SP

and

table

adjust

tank

adjust

oN

set

. set

max.

arc

oFF

NORMAL

Flaps.

...

Trim

Throttle

sHoRT

rtaps...

I

Trim

Throttle

...

GO.AROUND

Propeller.

Throttle

Control

Airspeed

Gear......

Flaps.

Trim

REPORT: 4-t0

TECHNIQUE

. .

FTELD

wheel

.

..

.

..

.

.....

VB-I0t0

TECHNIQUE

..

ISSUED:

REVISED:

as

. .95

as

.......400

..79

as

INCREASE

full

.. .

FORWARD

full

...

back

...

rotate

to

Pressure

climb

....80

retract

as requircd

'.

NOVEMBER

SEPTEMBER

required

KIAS

required

KIAS

required

attitudc'

KIAS

".UP

sl<lwlY

1979

8,

t9t4

17,

to

PIPER PA-32R-30r,

STOPPING ENGINE

Flaps

Electric fuel

Air conditioner ..

Radios Propeller.

AIRCRAFT

SARATOGA

pump

.

electrical

and

Throttle . . . Mixture ...

Magnetos

Master switch . .

PARKING

Parking

Control

Flaps.

Wheel

Tie downs

brake ...

.. .

wheel

chocks....

CORPORATION

SP

equiPment

SECTION

NORMAL PROCEDURES

..

retract

. .

..... oFF

OFF

... oFF

full INCREASE

. . full aft

. .. . idle cut-off

OFF OFF

set

....

full

in

secure

,

belts

uP

place

secured with

.

.....

4

ISSUED:

NOVEMBER

8'

1979

REPORT:

VB-1080

4-rt

PIPER

AIRCRAFT

PA-32R.30I,

CORPORATION

SARATOGA

SP

NORMAL

SECTION

PROCEDURES

4

PREFLIGHT

4.7

Theairplaneshouldbegivenathoroughpreflightand.walk-around

preflight

;;t;;,

The

*,,'pututi6n

check.

;;.f"r.;G. ;;iir,;;J";y

takeoff.

CHECK

should

of weight

A weather

factors

other

i-nclude

and

Uiieting

relatlng

check

a

C.G.limits,

to

be

a safe

should

the

of

takeoff

obtained

should

flight

the

be

operational

intended

checked

flight

before

airplane's

distanceand-in-flight

for

CAUTION

flap

The

boardins

the

in

support

position

the

ÜP

weight

airplane'

posiiion

on

should

The

before

steP'

the

noted

be

must

flaps

they will

be

lock

before placed

and

COCKPIT

control

seat belts

Insure

mixture

quantity

switch.

to

trim

has

required

the

all

that

should

gauges

and

Check

neutral.

accumulated

papers are

Upon

wheeländ

entering

the

set

cockpit,

the

parking

release

biake.

lnugn.toswitchu'eor.p.rurnoFFallavionicsequipment.(tosavepower

The

units).

the

on

master

that

to

for

wear

switch,

annunciator

the

OFF

Turn

operation

remove

cleanliness

any

fhe

check

panel illuminates

master

the

set

and

moisture

and

that

fuel

the

unip."u.rrt

ift"

ON

check

"p.iä,i"".

p;;p;,

i;,

drains

*fuä"*r

securing

electrical

in

be

for adequate

check

primary

the

Open

in the

the

the-pitot

on-board'

the

for

flight

and the

supply,

controls

and

check

Properly

switches

idle cut-off.

flaps

lines.

Turn

proper

static

stowandsecurethetowbarandbaggage.Closeandsecurethebaggagedoor'

I I

the

Begin

WING

the

wing

walk-around

surface

RIGHT

tnatlträ

oif,"..*trunäous

fuel

the

gauge.

interference.

Check

irt"

op"rutional

unJ

condition.

good

Open

indiÄior

ouantitv

indicator

l1,u,';;c;ii;.r.

il;i;ff;itguug..

of obstructions.

ISSUED:

REVISED:

NOVEMBER

SEPTEMBER

at

control

and

substances.

the

and

cap

inboard

Eaäh

assist

to

quantity

Räplace

E,

trailing

the

Check

Static

tip and

wing

visually

pilot

the

should

securely.

äap

1979

1984

17'

surfaces

the

wicks

check^the

tänk

in

Tugh

of the

edge

are clear

aileron

flap,

ihould

for damage'

lights

fuel

furnished

is

determining

the

The fuel

wing

right

ice,

of

hinges

and

firmly

be

supply'

with

fuel

indication

vent

tank

REPORT:

checking

by

frost,

for damage

attached

Check

external

an

quantities

was

that

should

or

snow

and

the fuel

fuel

of less

the

on

clear

be

VB-1080

4-13

in

SECTION

NORMAL

4

PROCEDURES

PIPER

AIRCRAFT

PA-32R-301,

CORPORATION

SARATOGA

SP

Place a container under

quick

through

tank, and

be drained

the

making

insure that all water

daily

Remove the tie down and

drain located

sure that enough

and sediment

prior

to the

When draining

be taken

before starting

to insure

Next, complete a check

proper inflation; there should

load. Check

normal

a visual check of

static

Check

that

the brake block and

the fresh air

the tire for cuts, wear, and

NOSE SECTION

general

Check

leakage and necessary. nicks, cracks,

The

the

The

landing

that the cowling

propeller

or other defects.

light should be

condition

and

quick

the

the lower

at

has been drained to verify the

fuel

first flight

drain. Drain the fuel

inboard rear corner of each

is removed. The fuel system should

and

each refueling.

after

CAUTION

any amount of

fuel,

care

should

that no fire hazard exists

engine.

chock

landing

of the

4.5

be

inlet is clear of foreign matter

of the

is

secure.

spinner should be checked for

The

air

clean and

geat.

Check

inches of strut exposure under a

r.5

proper

disc.

nose

section;

Check the

inlets

should be clear ofobstructions.

intact.

look for oil

windshield

gear

the

inflation.

tanks

proper

fuel

for

strut

Make

fluid

or

and clean if

detrimental

Remove the chock and

there

should be

Check the seals. Check

seated and that the oil

under

the

Close and secure

LEFT

WING

The

substances.

REPORT:

4-14

3.25

tire for cuts, wear,

the oil level;

fuel strainer valve

wing surface should be clear

Check that

VB-1080

gear

check the

inches of strut

t.25

and

make sure that the dipstick has been

filler cap

the nose baggage door.

has

located under the fuselage.

the fresh air

nose

exposure under

proper

inflation.

properly

been

of ice, frost, snow,

inlet is

clear

strut

secured. Place

ISSUED:

REVISED: SEPTEMBER

proper

for

normal static load.

a

the

Check

other extraneous

or

foreign matter

of

inflation;

engine baflle

properly

container

a

NOVEMBER I, 1979

17, 1984

and

PIPER AIRCRAFT PA-32R-30I,

SARATOGA

CORPORATION

SP

SECTION 4

NORMAL PROCEDURES

remove

should be

the

4.5

chock.

Check

inches of strut exposure

t.5

the main

gear strut for

under a

proper inflation:

normal static load.

the tire and the brake block and disc.

Open the fuel cap and visually

should securely.

the indication that was on the

match

(See

RIGHT

WING

check the fuel

fuel

for further fuel system

supply. The

quantity gauge.

description.)

tank vent should be clear of obstructions. Place a container

drain. Drain enough fuel to verify the

sediment has

and

Remove tie

underside

of

obstructions.

and

flap.

hinges for

been removed.

down and

remove the cover

the wing. Make sure the

Check the

wing tip and

damage

and operational

static wicks are firmly altached and in

proper

fueland

f

rom the

holes are open

lights for

good

condition.

to insure

pitot/static

damage.

Check

interference. Check

EMPENNAGE

Check

surfaces of the empennage interference. the baggage

clean and

are

from all hinges down,

the condition of any

Fairings

to be sure it is stowed

intact.

interference

push

artd

remove the tie down rope.

and

The elevator and

of any type. Check

rods

antennas

should be examined

access covers should

properly,

rudder should

the condition of the tabs

are sound and operational.

located

Check that

on the

for

damage

be attached

the

be

operational

If the tail

there

Check

quantity

The fuel

quick

the

on the

clear of

aileron.

that

cap

the

Replace

under

that all water

head

and

the

fuselage. All

and operational

properly. lights on the

and

Check

tail

and free

insure that

has been tied

MISCEI-LANEOUS

cockpit

the

Enter

located

lever center

draining

while

insure

is drained,

it will

a tank

from

seconds

few

for water

tank

on a

on

seat. The fuel selector should be

the strainer:

the fuel in

that

as well as the fuel in the fuel strainer. When

take approximately six

to the

longer. After draining the fuel

sediment at the

and

position.

and drain the

the right-hand side of

the

fuel

strainer. If the fuel tanks

ISSUED: NOVEMBER REVISED:

SEPTEMBER

fuel strainer by

the cabin, below the

positioned

"OFF," "LEFT"

lines between each tank outlet

seconds

to drain

in the following

*RIGHT."

and

fuel in

all the

are less than

strainer, check

drain under

the aircraft with

8, 1979

17, 1984

pressing

forward

This

and thefuel

the fuel

tanks are

one of

full.

for

the

REPORT:

down

sequence

is done

the

it

will

leakage

fuel

VB-1080

on the

edge of

to

strainer

full,

lines

take

and

selector

4-15

a

SECTION

NORMAL

4

PROCEDURES

PIPER

AIRCRAFT

PA.32R.301,

CORPORATION

SARATOGA

SP

the

Turn

turning

turn

perform a

äf

detector

detector.

for and'ttre door

overhead

seats should

and shoulder

"ON"

.bN"

walk-around

contents

the

0o

with

slightly

Check

all

When

proper cloiing

overhead

should

latch

master switch

necessary

the

pitot heat

the

container

in the

check

flaps

Reset the

up.

heated

the

should

Care

check

performed.

of the

öperation

maximum

elements.

passengers

latching

and

latch

gently

be

button

fastened.

snugly

be

harnesses.

"ON"

switch

check

the

pitot

be

The unit

should

to

on board,

are

button

pulled

turned

and

switches.

and

exterior

the

on

placed under

warning

stall

to

flaps

head

CAUTION

taken

heated

becomes

limited

be

avoid

procedures.

turned

shut,

to the

passengers should

All

begin

the

After

the exterior

lights and

horn

25o ot

proper heating'

for

when

pitot head

very

to

damaging

pilot

the

The

the

to

door

the

"LOCK"

interior

the

lights are

checking

light switches.

examine

the fuel

40"

an

three

should

"LOCK"

handle

position. Seat

strainer drain.

by moving

check

and

operational

being

is

hot' Ground

minutes

heating

the

check

rear door should

position'

firmly

fasten their

and.dispose

inboard

the

cabin

the

latched

belts

lights by

checked,

be closed,

The front

and

on

seat

interior

the outboard

Next,

lift lift

doors

the

empty

belts

If the

type)

s-eät

bility

flaps,

restraint

If

the

installed,

feature

REPORT: VB-1080

4-16

fixed

installed,

is

Uett

to

trim,

inertia

should

shoulder

and

all

etc.,

the

for

pull

a

NOTE

it must

adjusted

controls,

while

occuPant'

type

reel

test

be

Performed'

harness

to allow

including

of

(non-inertia

connected

be

proper accessi-

fuel selector,

maintaining

shoulder

locking

its

adequate

harness

restraint

ISSUED: NOVEMBER

REVISED:

reel

the

to

is

AUGUST

8, 1979

1981

28,

PIPER AIRCRAFT

PA-32R-301, SARATOGA SP

CORPORATION

NORMAL

SECTION 4

PROCEDURES

4.9 BEFORE

Before

lever moved to the full then be

in

are

and

STARTING ENGINE

starting the

engine,

INCREASE

moved to the desired

the radios are

4.I1 STARTING ENGINE

(a)

Starting Engine

Open the throttle

master switch and the

When Cold

to full RICH for approximately

primed.

Move the mixture

.

rotating

by

release the magneto

RICII

and move

If

the engine

the starter and

(b)

Starting Engine

magneto switch

the

reprime.

When

the brakes

rpm

tank. Check

OFF.

lever approximately

control

fuel

to idle cut-off and engage

electric

switch, advance

the throttl€

does not

to the desired setting.

fire

within

Hot

should be

position.

make sure

to

set

The fuel selector

all

the propeller

and

the circuit

ll2inch. Turn ON the

pump.

Move the mixture control

4 seconds.

clockwise.

the mixture control

five to ten seconds, disengage

The

When

engine

engine fires,

the

should

breakers

is now

the starter

to full

master switch lever to idle switch clockwise. advance

(c)

Starting

switch and turn OFF control magneto

magneto switch, advance the mixture and

ISSUED:

REVISED:

Open the throttle

and

cut-off

When the

the

mixture

Engine When Flooded

The

throttle lever should

lever

to

idle

switch clockwise.

NOVEMBER

t,

SEPTEMBER

approximately

the electric

and engage

move the throttle to the desired

and

the electric

cut-off

1979

17, 1984

ll2 inch. Turn ON

pump.

fuel

Move

rotating the

by

pump.

the

starter

retard the

the mixture

Move the

by rotating

release

throttle.

REPORT:

fuel

the starter

engine fires, release the magneto

be full OPEN. Turn ON the

and engage

When the engine fires,

the

control

magneto

switch,

setting.

master

mixture

the the

VB-10t0

4-17

SECTION

NORMAL

4

PROCEDURES

PIPER

AIRCRAFT

PA-32R-30I,

CORPORATION

SARATOGA

SP

(d)

Starting

An optional

allows

without

Turn the

OFF. POSITIVE BLACK

jumper

rn

*t

normal

the

After

possible

cable

alternator

ATTEMPT

ALTERNATOR

Engine

operator

the

having

Connect

to

master

the

(+)

lead'to

into

cable

plug is inserted,

ttr"

starting

engine

the

RPM,

aircraft.

the

from

ammeter

FLIGHT

For all

jurnper

normal

cables,

bFF, but

parallel by

in

This

will

not

give

increase

External

With

feature

to use

gain access

switch

RED

terminal

NEGATIVE

the

socket

the

technique.

has

reduce

tö

for an

OUTPUT.

the

possible

is

it

turning

longer

the

Power

the

called

external

an

the airplane's

to

and

OFF

of the

Iead

external

an

of

(,

located

electrical

the

started,

sparking,

the

Turn

indication

THERE

IF

NOTE

operations

master

to use

master

the

cranking

amPerage.

Sources

Piper

battery

turn all

PEP

terminal.

on

system

reduce

and

IS

switch

NO

master

using

switch

the ship's

switch

capabilities,

External

to

crank

battery'

electrical

jumper

kit

l2-volt

the

battery

Insert the

fuselage.

oN.

is

power to

disconnect

ON

output'

of

INDICATION

PEP

the

should

be

battery

ON.

but

Power

the

equipment

cable

and

plug of

Note

Proceed

the

check

and

DO

(PEP)

engine

the

to

the the

that

with

.lowest

jumper

the

NOT

OF

REPORT:

4-18

Care

battery

supply

battery.

mastei

starter

the

external

VB-1080

should

has

can

This

switch

engaged.

is

battery

ship's

power suPPlY.

be

been

reduced

be

CAUTION

exercised

depleted,

be

can

ON

If cranking

is at a

because

external

the

level

to the

tested by

momentarily

speed

higher

level

ISSUED:

REVISED:

if

ship's

the

power

ship's

of the

turning

the the

while

increases,

the

than

NOVEMBER

DECEMBER

8,

18,

1979

1981

PIPER

PA-32R-301,

AIRCRAFT

CORPORATION

SARATOGA

SP

SECTION

NORMAL PROCEDURES

4

when the engine

pressure is

ihe trouble.

pressure

bperating

not inäicated

In cold

indicati6n.

Handbook,

Starter manufacturers

seconds

thirty

cranking

with

periods

4.13 WARM.UP

the engine

warm

low

'I'akeoff

engine

ground

damage

4.I5

instructed

Ascertain and

up

RPM,

Do

ai

is warm.

not

containing

to the

TAXIING

Before

and

that

areas

taxi

this

may

operate

ProPeller

attempting

approved

thä

are

is firing

within

weather

engine

If the

Engine

recommend

minute

two

a

shorten

will

at

practice may

as soon

made

be

engine

the

stones,

loose

blades.

taxi

to

by

chocks

clear.

häve

Release

evenly,

thirty

take

it will

has

Troubles

rest

life

the

1000 to

result

as

high

at

gravel or any

the

qualified

a

been

the

advance

seconds,

few

a

failed-to

and

that

between

the

of

RPM.

1200

in fouled

ground check

the

when

RPM

airplane,

person

removed

parking

throttle

the stop

seconds

start,

to

the engine

longer

to

refer

Their Remedies'

cranking

periods be limited

cranking

starter'

prolonged

Avoid

plugs'

spark

is completed

runningup

loose material

ground

and

brake'

persomel should

authorized

propeller back

that

get

lf oil

an oil

800 RPM.

and determine

to

the Lycoming

periods. Longer

idling at

and the

the

over

cause

owner.

blast

or taxiing

that may

by

to

be

Power

forward

and

propeller iurns to

objects.

ascertain

Observe

If

Avoid

not

Do

sround äurnug"

containing

to

ISSUED:

REVISED:

apply

l;w

in

wing

and

ProPeller

be applied

the

clearances

the

loose

should

set

possible,

holes

operate

the

AUGUST

SEPTEMBER

bräkes

to determine

pitch, high

effectiveness

when

station

an

ruts when

engine

stones,

blades'

1981

28'

17' 1984

slowly

RPM

of

taxiing

observer

taxiing

high

at

gravel

start the

to

their

setting.

steering'

the

near buildings

outside

over

when

RPM

or any

roll.

taxi

effectiveness.

taxiing,

While

or other

the airplane'

uneven

ground'

runningup

loose material

REPORT:

Taxi a

Taxi

make

taxiing

or

that

feet

few

the

with

slight

stationary

over

cause

may

VB-1080

4-1ta

PIPER AIRCRAI.-T

CORPORATION

PA-32R.30I, SARATOGA

SP

NORMAL

SECTION

PROCEDURES

4

4.17 GROUND CHECK

Set the

with the

exceed I

parking

propeller

75

RPM and

sct at

50 RPM. Operation

vacuum

the

Check

Thc magnetos

brake.

high

the difference

on one

gauge: the indicator

ar 2000 RPM.

the annunciator

Check

check the air conditioner

'l'he

propeller control should

check for takeoff.

forward

proper

To obtain

on the instrument

RPM during this

from high

cycled

warm engine oil

that

operation

check.

to low RPM at

l'he electric fuel

during warm-up

Prior to

of

takeoff, the electric

power

during

temperature and

the

engine

to make sure

takeoff,

oil

is being

and

maximum

ln cold

has circulated.

pump

should

pressure.

run for

Drop

RPM.

betw€en

magneto

pane I lights

the

and

rpm,

panel.

should

with

alternate

moved

be

placed

then

push

the

not allow a drop

Do

weather,

three times before

least

turned OFF briefly

should

pump

be

that the

should be

engine-driven

the engine-driven

The temperature

the first

time of

should be

ofl'on

the nragnetos

should read

checked at 2000

either magneto should

should not

not

exceed

l0

4.8" Hg. to

press-to-test

the

air.

through its complete

in full

pedestal-mounted

INCREASE rpm for

of more than 5ü)

propeller

the

control

takeoff to make sure

pump

turtred ON again

pump

may

the

day.

be

low for

RPM

exceed

seconds.

5.2"

button.

control

Also

range

fully

should be

after starting

is operating.

prevent

to

fail. Check

time if

some

:,

not

Hg.

to

or

loss

oil

ISSIIED: REVlSt r.r:

NOVEMBER

E,

SEPTEMBER 17,

l9El

1984

REPORT:

vB-10t0

4-19

SECTION

NORMAL

4

PROCBDURES

PIPER

AIRCRAFT

PA-32R-301, SARATOGA

CORPORATION

SP

{.T9 BEFORE

All aspccts

exccuting

Aftcr takeoff,

I

selector switch is

lgcar

airspccd

not

at which the system no

rctract.

TAKEOFF

of each

thc takcoff

procedure.

on aircraft

placed

For obstacle clcarance

altitudc airports, the landing discrction by

latching thc emergency

placing

thc

gear

lf dcsircd, thc oVERRIDE

latchcd

sclcctor switch is

to rctract the

runway.

soon as sufficicnt airspeed

gcar

systcm to normal operation.For

extend and retract the

instrument

installcd.

not

'

If thc airplane

rccommcnded

Aftcr all

proccdurc

bcforc

If

thc

pancl,

must bc

takeoff, aird

placed

in thc UP

gcar

prematurely,

ovcrridc lock

gear

just

as he

is to

be

that all

aspccts

passcngers

of

performed.

particular

takeoff should be

equipped

in the

longer commands

with the backup

gear

up

on takeoff and

gear

can be retracted

gear

selector switch

lever in the OVERRIDE

ENCAGED

gear

the

position.

or the aircraft

is used for takeoff,

and terrain

with the

if the back-up

would

opcrated

wcar

takcoff are considercd,

the

thän retract as

will

Care

clearance

normal operation,

gear

selector

with the

parachutes.

considered

gear

position

in the UP

gcar

for

aftcr

before downr,

takeoffs

lift-offat

position

ENGAGED

position

can be

should always

settle

could

it should

are obtained,

switch

gear

extender

rear cabin door

a

prior

thc

if

gear

extender,

reaching the

from high

pilot's

the

and

position.

selccted

soon as

be disengaged

the

prctakeoff

the

be taken

onto

back

to return

pilot

located

systcmwere

removed,

should

on

check

to

the

will

then

and

gear

not

the

as

the

it

is

Turn ON

insfiumcnts as propcr

gaugcs.

(fullcst).

tank

Thc alternate air

All scat backs

tApproximatcly

ft. with a straight

RBPORT:

tb20

VFlOtO

th€

mastcr

requircd. Check

switch and

Turn ON

should

should be

KIAS

8l

line

ercct.

sea level

at

variation

check and

the fuel selector

the elcctric

be in

betwecn'

fucl

the CLOSED

to approximately

ISSUED:

REVISED:

set

to make

pump

and

position.

100

NOVEMBER

SEPTEMBER

of thc

all

sure it

check

KIAS

llight

is on the

enginc

the

10'000

at

t,

l, t9t6

1979

PIPER

AIRCRAFT

CORPOR

PA-32R-30I, SARATOGA

SP

ATION

NORMAL

SECTION

PROCEDI.JRES

4

'f

hc nrixture and

shoulder harness should be

.and

cmpty

)he

movemcnt and

and thc

conditioner

seats.

Exercise

parking

and

must be

type)

seat

propeller

the flaps and

set

response.

brake

OFF to insure

lf the

fixed shoulder

is

installed,

belt and adjusted

bility to all controls,

flaps, trim,

restraint for the occupant.

lf the inertia reel type shoulder harness

installed.

feature should tre

4.2I TAKEOFF

NORMAL T'ECHNIQUE

a

control

fastened.

levers should be set, and the

Fastcn

trim tab. lnsure

All doors should

relcased. On

NOTE

be

air

nornral takeoff

harness

(non-inertia

it must be connected to the

to allow

including luel

while maintaining

etc.,

pull

(See

of its locking

test

performed.

Charl, Section 5)

seat

the seat bclts snugly

proper

prrlperly

secured and latched

flight

around

control

conditioncd models, the

performance.

reel

proper

accessi-

selector,

adequate

is

restraint

belts

air

When

the available

obstacle The flaps

clearance is no factor, the

should

aft of neutral.

q()ntr<ll

to 74

wheel to lift off, thcn control

climb speed. Retract

thc runway

NOVEMBER

SEPTI.IMBER

abcelerate the

the desired

Ianding on

)

lSStlED:

RIIVISED:

runway length is well

be set in the retracted

Align the

to 80

airplane

KIAS

is

no longer

dependingon

t, 1979

17,

l9t4

in

cxcess of that rcquired and

normal takeoff

position

and

with lhc runway,

weight. Apply

pitch

attitude as

the landing

possible.

gcar

technique may be used.

pitch

the

when

trim set slightly

l'ull

apply

back

requircd to attain

a straight-ahead

REPORT:

power,

and

pressureto

VB-10t0

4-21

SECTION 4

NORMAL

PROCEDURES

PIPER

AIRCRAFT CORPORATION

PA-32R-30r,

SARATOGA

SP

MAXIMUM PERFORMANCE

Chart, Section

Align the airplane with the runway,

slightly aft of neutral, and advance

brakes

weight, and apply back

accelerate

When clear

and allow the

SHORT

For

pitch

trim set

the brakes, and

Release

depending

bräaking

gear

select

rate-of-climb

angle-of-climb Slowly

retract the flaps

5)

airplane

pressure

to

74 KIAS, depending

67 to

of obstacles, increase

FIELD TECHNIQUE

short or soft field

slightly aft of

advance

the brakes,

on weight,

ground,

accelerate

UP*. Continue

speed, 9l

speed, 80

takeoff,

neutral, Align

the throttle

allow

and apply

to

to climb

KIAS,

while

to

accelerate

to rotate for lift off.

(See

the airplane

back

6l

if no obstacle

if obstacle

climbing

WITH

the throttle

FLAPS

set the brakes,

to

to 68

to 63

on weight,

Chart,

the airplane

speed

Section

power.

the climb

flaps should be

to full

to accelerate

pressure to rotate

KIAS depending

to 7l

while accelerating

present,

is

clearance

out.

RETRACTED

the

adjust

power. Release

full

KIAS, depending

breaking

After

retract

and

that desired'

to

5)

lowered

with the

to 58

to the

to

or

is

the

to 25o

runway,

to 66

lift off.

for

weight,

on

flaps up

the flaps

consideration.

a

pitch

ground,

gear*.

and

up best

(See

trim

the

on

the

set

KIAS

After

and

best

rlf

desired,

on

oVERRIDE

the

takeoff,

placed

g.ur pr.tnutrtöly,

överrlde

sufficient

operation.

REPORT: +22

and

in the

lock

terrain

VB-r080

up

aircraft

equipped

ENGAGED

gear

position. In this

ot

is used

clearance

then

will

the aircraft

for takeoff,

the

with

backup

position can be selected

retract

case care

coutd settle

it should

is obtained,

as soon as

to

the

should be

back

be disengaged

the

return

ISSUED:

REVISED:

gear

extender'

latched

and

gear

selector

to retract

not

taken

the runway'

onto

as

gear

system

to normal

NOVEMBER

SEPTEMBER

before

switch

If the

soon

1979

E'

I,

l9E6

the

is

the

as

PIPER AIRCRAFT

CORPORATION

PA.32R.3{II, SARATOGA

CLIMB

4.23

SP

NORMAL

SECTION

PROCEDURES

4

The

best rate

best angle of climb these speeds

KIAS is

increased

Upon

are

recommended. This

visibility

reaching

On aircraft

extender, during climbs at best angle

speed

speed above approximately 5000

of climb at

may be obtained

reduced somewhat+.

over

a safe altitude,

at

gross

will

the nose during

equipped with

any altitude and best rate

altitude, it may be necessary to OVERRIDE

landing

during

increased

4.25 CRUISING

\

The cruising speed

setting, altitude, temperature, loading

airplane.

The

normal maximum cruising

the engine. When selecting

pressure

Lycoming Operator's Manual", should

for

continuous operation,

the

reduced

ENGAGED to

gear

from extending automatically

climb. This altitude

climb

power

airspeed.

is

determined by many factors,

cruising RPM

weight

KIAS. At

at 80

For climbing

produce

the climb.

e lectric fuel

the

NOTE

and

and equipment

power

as specified

be

obtained at 9l

will be

lighter than

en

better

pump

the

backup

of climb

feet density

prevent

decreases with

increases with

is75%oof

below 2300,

observed.

the

by the appropriate

KIAS.

gross

route,

forward

may

gear

select

the

spged

a

speed and

be turned

including

installed

horsepower

rated

limiting manifold

The

weight

of 105

off.

power

in the

of

"Avco-

To obtain the desired

according to the

Use of the mixture control in cruising flight

significantly,

during cruising ope ration when75/epower

exists

"RICH"

)

rTo

"

handbook, all

followed.

to

as

position

obtain the

power

especialty at

the amount of

for

performance

parameters

power,

setting table in this

higher

altitudes. The mixture

power

being used, the

operations

all

presented

listed

ISSUED: NOVEMBER t, 1979

REVISED:

SEPTEMBER

I, l9t6

set

the manifold

manual.

or less is being

under

5000

in the

on the

performance

pressure

reduces

mixture

feet.

Performance

fuel

should

used.

should

REPORT:

and

consumption

be

If any

in

be

Section

charts

must

VFlOtO

RPM

leaned

doubt

full

the

of this

+23

be

sEcTloN

NORMAL

a

PROCEDURES

PIPER

A IRCRAFT

PA-32R.30I,

CORPORATION

SARATO(;A

SP

lean

To

enginc

fhc

until

reachcä

hccn

conlrol

imooftr.

consumcd.

raf.r,

indicates

(ECT)

itir

towards

The

indicates

bcst

airplane

the

lf

gauge,

piJceOure.

Following

pilot

The

to öonditions

alert

expcctd,

powcr

systems

tti

cleaning.

event

geardown

the

äf

reductlon

ptace

During

fucl

Thcre

flight.

serängs-

are Jpe rating.

"ctu"tly

are

of'a hydraulic

position.

g"at

i"tractcd

in ainpeed

flight bctween

the mixture,disengage

becomes

in the leaner

the

flow metcrwillgivea

fuel

low side

besr

power.

mor.

a

refer lo

leral-off

should

thc

rough.

instrumcnt

of

economy

is equipped

uc'cui"te

the

for

monilor

which

alternate

account

kctp

to detärmine

lf the

consumed.

beirig

no mechanical

system

tru.

Th.

airspeed

und

remote

airfields

indicating

cylinders.

powcr sctting.

the

foi

with

means

"Avco-l-ycoming

cruise.

weather

lcad

might

control

air

of

how the

flow

fuel

uplocks

malfunction.

airspecd

for any

should

.ang.

or

lock and

thc

cnrich

Then

panel until

pull thc mixtrrrc

lhe

that

thc

engine

closcapprqximationof

as sh0wn

percent of

that

the optional

leaning

of

airplane

the

conditions

icing. lf

to

power

exhausl

is ävailable

Operator's

should

while

induclion

in the ON

used

time and

indication

fuel non.le

a

with

givcn

flight

fuel

fuel flow

may

landinSgear

the

in

landing

the

geardown

powe

r

made

be

water.

over

and

is considerably

sctting.

when

conttrtl

pushing thc

by

thc

the

the.p.ilot.

to

limit

becomcs

fucl

fuel

high

rature

lcan ntixturc

mixturc

operation

on

while

gas tempe

Manual"'

trimmed'

be

syslcm

should

icing

flyingand

postion'

in conncclion

quantity

fuel

higher

rcquire

clogged

be

gcar will

isapproximatelyT50l

and

system.

I'rce-fall

Allowa

planning

nces

extcnded

for thc

has

being

flow

side

For

bc

is

with

Saugc

than

ln the

to the

orderto

ln

should

fuel

Always

switching

before

preclud€

Lb"for should

in use. Thc

tank

malfunction

of fwl slarvation

should be suspecled.

REPORT:

tb24

keep

used ahcrnately

be

remember

tanks.

making

a

he

clcctric

of the

Vll0t0

changid

engine

should

rhe airplane

that lhe

should

and

se lection.

hasty

anolher

to

fucl

drivrjn

occur

which

at

lateral

in best

each tank

l'rom

lcft

bc

and

pump is

the

fucl

on

to

tank

timc

fucl

clcctric

punrp should

l'trcl

ar any

timc

duringcruise

trim

h.ur

one

at

pump should

period

short

for a

provide conlinuity

is e xhatrstcd

ftrel

bcfore

hc normally

immc'diate

during

selcctor

ISSIIED:

OI:I; so

11'apparcnl.

flight.

should

NOVEMBER

REVISED:

flight.

inlervals.

bc turncd

thcrcafter'

ol llow,

I'ront

that

cxhattslion

l'uct

immcdiatcly

bc

JULY

19, 1982

lf

t'

the

oN

-l

thc

lhc

any

signs

1979

o

PIPER AIRCRAFT CORPORATION

PA-32R-301,

positioned position.

4.27 APPROACH

SARATOGA SP

to

fullest tank

the

AND

and the

LANDING

electric

NORMAL

pump

fuel

SECTION

PROCEDURES

switched to the ON

4

Accomplish

Depending

appropriate:

are

NORMAL

When available

flown

approach

down

normal

be

maintain

approach tünway

wind

at the

landing furnished.

should

and

minimum

distances

the

If

fixed shoulder

the

is installed,

type)

seat belt

to all

bility

flaps, trim,

restraint

If the inertia

installed,

feature should

field

on

TECHNIQUE

runway

and landing

final approach

the

the desired

landing

and

be varied

aircraft

loading.

possible safe speed

with

Landing

and adjusted

Check

controls,

etc., while

the occupant.

for

reel type

pull

a

test of

be

length and

(No

Performance

length

technique

approach

and the

according

generally

It is

this technique

early in the

List

NOTE

harness

it must

to allow

(non-inertia

be connected

proper

including

maintaining adequate

shoulder

its locking

performed.

factors the

other

Chart

is in excess

be utilized.

may

at 95 KIAS with

course

The amount

angle.

of the

speed

landing surface, conditions

to the

good practice

consistent with

vary,

will

landing approach

reel

to the

accessi-

fuel

selector,

harness

is

restraint

following

Furnished)

of required

The aircraft

of flap used

procedures

runway length,

should

power

required

during

aircraft at contact with

contact the

to

existing

performance charts are

conditions.

ground

a

to

the

of

As

not

ISSUED:

REVISED:

NOVEMBER

AUGUST

2t,

8'

1979

19tl

REPORT:

VB-10t0

4-2s

SECTION

NORMAL

4

PROCEDURES

PIPER

AIRCRAFT CORPORATION

PA-32R-301,

SARATOGA SP

SHORT

Section

When

FTELD

5)

available runway

LANDING

Ianding is of major concern,

employed. with full

as early

contact the

flaps and apply consistent with

The aircraft should be

gear

flaps,

possible.

as

ground

and

down

Reduce

close to stall speed. After

full aft travel on the control wheel and maximum

existing conditions.

idle

the speed slightly during landing flareout

4.29 GO.AROUND

initiate a

To

should

throttle

climb speed

when

best angle

of

trim

be

set

while

positive

a

of climb speed

climb speed

as required.

4.3I STOPPING

go-around from a landing

INCREASE

to full

pitch

the

of 80 KIAS.

climb

(9

I KIAS)

attitude

Retract

is

established.

(80

KIAS) for obstacle clearance or to the

if obstdcles

ENGINE

APPROACH

length

is minimal

POWER

obstacle clearance to

or

this approach/landing

The

final

glide

ground

approach at 79

path

should be stabilized

contact,

flown on the

power.

approach, the

and the throttle should be advanced to full

is increased to obtain

the landing

gear

and slowly retract the flaps

(See

OFF

technique may be

retract the

braking

prop

the balked

Allow the airplane to accelerate to the

best

are not a factor. Reset

longitudinal

the

Chart,

KIAS

and

control

landing

rate

radio and electrical

Prior to shutdown,

OFF.

pilot's

At the

pump

turned OFF.

The

all

discretion,

must be

flaps

the flap step

should be

The air conditioner

lock

position,

pulling

and

INCREASE control should be left full aft

magneto and master switches

cautioned

should

the

and

mixture

the

to

avoid

REPORT: VB-1080

4-26

equipment

the

flaps

NOTE

placed

should

in

the UP

be raised

to support weight.

accordingly.

be turned OFF, the

engine stopped by

control back to idle

engine

must

vibration

be turned

OFF.

ISSUED:

REVISED: SEPTEMBER

should be

and the

position

Passengers

for

propeller

disengaging the

cut-off.

turned

electric fuel

in the full

set

mixture

The

throttle

while stopping. Then the

NOVEMBER 8, 1979

17,

1984

PIPER

PA-32R-301,

433

ground

and

be secured

snug.

retracted.

AIRCRAFT

PARKING

parking

the

Set

with

secured behind the

by looping

The flaps are

CORPORATION

SARATOGA SP

lf necessary,

brake.

the

of the nose

aid

the safety

rear

locked

seats.

when

wheel

The

belt

in the

the airplane

tow

aileron

through

UP

NORMAL

should

provided

bar

and stabilator

the control wheel

position

and

SECTION

PROCEDURES

be moved on

with each

airplane

controls should

pulling

and

should be left

'

the

it

Tie

tail skid.

steering

downs

can

The rudde

and normally

435 STALLS

stall characteristics

The

approaching

bäiween

gentle pitching may

The

With rhe

be as

can

During

masteÄwitch

the

lift detector

reset to 0o

actuated.

stall is

five and

gross

flaps up

great

ten knots

weight

rhis

as

The stall

master

preflight, the stall

on, setting

to determine

the inboard

and

be secured

held

r is

does

indicated

precede the

also

statling

speed

4fi)

feet,

warning

switch

if the

rings

to

position

in

not have

the

of

a stall

by

stall

above

with

speed

is increased

dcpending

NOTE

system

OFF.

warning

flaps to

the

horn

lift detector

provided under each

by its connections

be secured.

to

Saratoga

speed.

stall.

power

3

on

is inoperative

system should

25o or40o

is actuated.

SP

are

warning

horn which

Mild airframe

and full

off

K'IS. Lossofaltitude

configuration

with

be

raising the

and

The flaps

to

raised

determine

wing and

nose wheel

to the

conventional'

is activated

buffeting

is 5?

flaps

duringstalls

power'

and

the

turning

checked

by

outboard

should

if the

then

horn

to the

An

and

KIAS.

be

is

TURBULENT

4.3?

ln keeping

,"comm.nded

reduced

airspeed

cauied by

occur as a räsutt

ISSUED:

REVISED:

be

gusts and

NOVEMBER

SEPTEMBER

AIR OPERATION

good operating

with

turbulent air

when

that

to maneuvering

ro allow

the turbulence

of

t, 1979

for

l7'

speed to

inadvertent

ofdistractions

or

l9t4

practice

used

is encountered

reduce

speed

caused

in all

expected,

or

struclural

the

build-ups,

the

by

REPORT:

aircraft,

which

conditions.

VB-rü0

it

the

loads

may

1-27

is

sEcrloN

NORMAL

4

PROCEDURES

4.39 LANDING GEAR

PIPER

AIRCRAFT

PA.32R.3OI,

CORPORATION

SARATOGA

SP

Some aircraft

(backup gear

power

conditions*,

This system

when the

override

ai rspeed

this system

ENGAGED

emergency release

lever.For

with the

The

landing

the

simultaneouily

pressure is approxiÄately

lielector

lbact<up

back-üp-gear selectoi power.

also operate and

gear

the override,

normal

gear

if the

ld

pilot should

The red

switch'is gear

*I*it"tt

The red

gear

the

are equipped

extender)

will also

which

even

prevent

- power values to hold

or

position without

pull

lever,

pull lgver up

operation,

gear

become

warning

flight-whin

not in

this warning

in the

is

not

warning

switch

selector

back-up

gear position

gear

in

extender

gear

iimultaneouily

selector

switch

with

extends

though

the

retraction

are

the emergency

maintaining

lever

the

pilot should

the

located

extender

familiar

indicators

the instrument

on

light

the throttle

l4 inches

th-e DOWN

DOWN

light

on the

is

has

on

in the UP

system

an airspeed

landing

the

pilot

below

full

may

the

of

up and

not

landing

predeter

a

gear

manua

to disengage

extend

instrument

the

on

system

and

position. On

will

lowered

the instrument

ground when

were not

function

the

with

warning

panel

reduced

is

mercury.or

of

aircraft

also occur

landing

the

position and

position.

power sensing

-

gear

under

selected

have

gear

bY

mined

inthe OVERRIDE

r

leve

pressure

I

the latch

push

latch,

the

retract

nd

a

panel,

lled

insta

and

lights.

the

and

where

to

below,.

equipped

during

the

panel and

the

flight

gear and

throttle

master

system

low airspeed

gear down

normal

minimum.

means

on

down.

release

then

the

just

as

significance

operate

horn

manifold

the

and.the

with

when

the

is not

horn

the

is ON

switch

-

To

th€

To

gear

he

of

gear

the the

gear

full

will

green

three

The

associated

each

Radio

obtain

flying.

radio lights

*Approximately

REPORT:

VB-10t0

4-2t

on

lights

gear ii locked

lights'

dimmer

gelr lights

aircraft

When

lights'dimmer

automaticallY

will

at

KIAS

103

instrument

the

extended

in the

WARNING

switch

intensity

full

is operated

switch

altitude,

any

panel

position.

must

during

at

is turned

dim.

power off

ISSUED:

REVISED:

off

gear

to

and

individually

.operate

be

daytime

night

on,

NOVEMBER

SEPTEMBER

as

1979

8'

l' 19t6

PIPER

AIRCRAFT

PA-32R-3{ll,

on aircraft

oFF

EXT.

whenever position.

the imergency

CORPORATION

SARATOGA

equipped

SP

with

rigni iirmediately

geai

the backup

below

lever

the

is

SECTION

NORMAL PROCEDURES

yellow

gear

extender

gear

the OVERRIDE

in

the

setec19ly!1c-\{tl-!fl

4

4uTol

ENGAGED

the

when

performed procedure

;;;;;&;".

gear

selector

gr..n.

ir"

Emergency

traini-ng

for

in order

aircraft

On

must

On aircraft

iVp.-l-ÄNpING

ptior

iutteO breaker

gear

system

WEIGHT

4.41

It

airplane

while

For

to

be

must

operation.

responsibility

is the

remainiwithin

in flight.

wcight

pürporet, the

to

friveirt

equipped

teftln

be

which

GEAR

executing

t"s"t ait.t

BALANCE

AND

balance

and

Landing

ttre

iüe UP

do

PUMP

emergency

the

complelion

of

allowable

the

data,

Gear

following

hydraulic

thc bäckup

with

position

NÖT

circuit

owner

the

refer

Extension

pump

until

the

have

breaker

extension

of the

and

weight

to section

Procedure

changes

from

gear

all

backup

installed

is

procedure'.The

procedure

pilot

to

center

vs.

(weight

6

(Par.

3.29)

made

be

must

activatingduring

extender

position

gear

the

indicators

extcnder

must

and

landing

circuit

and

normal

that

envelope

Balancc).

to allow

determine

gravity

of

to the

the

pull

a

be

the

is

ISSUED:

REVISED:

AUGUST

2t, l9tl

SEPTEMBER I, l9t6

REPORT:

YFlOtO

+29

PIPER

AIRCRAFT

PA-32R-30r,

CORPORATION

SARATOGA

SP

SECTION

PERFORMANCE

5

GENERAL

5.T

All of the

information

Performance

equipment

(Supplements).

INTRODUCTION

5.3

The

measured

analytically

and

temperature,

The

for varying

aircraft.

procedures in a

stated

Effects of conditions

pilot,

the

landing

required

applicable

which

performance information

Flight

etc.

performance

degrees

This

such

performance, or

performance.

procedures, and

PERFORMANCE

(

regulations)

FAA

Saratoga

the

to

information

require

Test Data corrected

expanded

performance,

handbook

-

PERFORMANCE

for

are

charts

proficiency

pilot

of

holvever,

properly

not considered

effect of

as the

the

Endurance

inflight

can

fuel

flow

SECTION

associated

5

and complementary

provided in this

SP is

those optional

with

supplements

AND FLIGHT

presented in this section

I.C.A.O. standard

to

the various

unfactored

maintained

or

soft

effect

grossly

be

param€ters of weight,

and do not

mechanical deterioration

or

can be duplicated

airplane.

on the charts must be

grass

runway

of winds

aloft on cruise

affected by

quantity checks are

performance

section.

systems

provided

is

in Section

PLANNING

is based

day conditions

make any allowance

following

by

evaluated

surface on

takeoff and

improper

recommended.

altitude,

and

leaning

and

on

the

of

the

range

9

by

REMEMBER!

The information

outlines

chart

ISSUED:

a detailed

includes

NOVEMBER

REVISED:

get

To

provided by

plan

flight

its

own

example

Performance

extrapolation

should

charts

purposes.

E,

SEPTEMBER

performance, follow the chart

chart

how

(Flight

5.5

charts

it is used.

paragraph

using

to show

performance

WARNING

information

beyond

not be

1979

17,

the limits shown

used for flight

1984

derived

Planning

in this section.

by

the

on

planning

REPORT:

procedures.

Example)

Each

VB-1080

5-1

PIPER AIRCRAFT CORPORATION

PA-32R-301,

SARATOGA

SP

SECTION

PERFORMANCE

5

FLIGHT

5.5

For

installed

(a)

PLANNING EXAMPLE

purposes

on the airplane.

this example

of

Aircraft Loading

The first step

weight and

Section

by

The

factory

airplane have

the aircraft should be

C.G.

Make

ll)

determine

position.

After

center

(Weight

6

empty

basic

has been

been made

logbook and

made to

location of the

use of

and the

C.G.

total weight

the

proper

the

following weights flight

planning

example.

is assumed

it

planning

in

gravity

of

Balance) of this

and

weight

entered

in

affecting weight and

Weight and

determine

airplane.

Weight and

Range

utilization

have been determined

flight

the

by utilizing

for

the airplane

Figure 6-5. If any alterations

Balance Record

the current

Balance Loading

Weight

and

the airplane and

of

of the

2

that a

is to calculate

the

blade

information

handbook.

as

balance,

empty

basic

graph

(Figure

the center

licensed

Form

information

for consideration

propeller is

the airplane

provided

at to

reference

(Figure

weight

(Figure

6-15)

gravity

of

provided

in the

the the

to

6-7)

and

6-

to

the

The landing weight

fuel to be used

the

(l)

Basic Empty

(l)

Occupants

(3)

Baggage

(6

Fuel

lb/gal.

Takeoff Landing

(a)(5)

minus

(3480

lbs. minus

balance calculations

and

within

the approved

ISSUED:

(4) (5) (6)

The takeoff weight

weight

position

NOVEMBER

REVISED: SEPTEMBER

cannot

been established

has

Weight

(6

x 170

and Cargo

x 50)

Weight

(gXl),

180 lbs.)

is below

8' 1979

17, 1984

be determined

lbs.)

the maximum

have

limits.

until the

to

[refer

of 3600

determined

REPORT:

item

weight of

(g)

(l)].

2100

1020 lbs.

60

300

3480

3300

lbs.

and

the

VB-10t0

lbs.

lbs. lbs. lbs.

lbs.

the

C.G'

5'3

SECTION 5

PERFORMANCE

(b)

Takeoff

and Landing

PIPER

AIRCRAFT

PA-32R-301,

CORPORATION

SARATOGA

SP

After

determining

and landing

must

the aircraft

considered.

be

loading,

All of the existing conditions at the

airport

the flight.

the appropriate Takeoff Performance

graph

length of runway necessary

distance.

manner using the existing conditions

and, when established, the landing

listed below. The takeoff

flight

must

Apply the

(Figures

be

acquired,

departure airport conditions

5-7,

5-9,

evaluated and maintained

l,

5-13, 5-15 and 5-17) to

5-l

for the takeoff

The landing

The conditions and calculations

have fallen well below the

(1)

Pressure Altitud.e

(2)

Temperature

(3)

Wind Component

(4)

Runway Length Available

(5)

Runway Required

distance calculations

weight.

and landing distances

available runway lengths.

all aspects of the takeoff

departure and destination

throughout

and takeoff weight

and Takeoff

performed

are

at

the destination

for

the ex4mple flight

Ground Roll

determine the

and/or the

in

required for

barrier

the same

airport

Departure Destination

Airport Airport

1200 ft.

l60c

IO KTS

Headwind

3000

1700 ft.*

ft.

400 ft.

24C

5

4600 ft.

1490 ft.**

to

are

the

KTS

*reference

**reference

Figure 5-15 Figure

REPORT: VB-r080

5-4

5-45

ISSUED:

NOVEMBER 8,

REVISED: SEPTEMBER

1979

17, 1984

PIPER

AIRCRAFT

CORPORATION

PÄ.32R.30I, SARATOGA SP

SECTION 5

PERFORMANCE

NOTE

The remainder

in this flight

condition.

considered by cruise and

(c)

Climb

The next step

necessary climb

The desired cruise

outside air

considered

Distance, and

distance

temperature conditions

subtract

departure

The remaining

components

pressure altitude and

field

The following values

instructions

(l)

(2)

(3)

(4)

(5)

of the

plan

example

The

effect of

pilot

the

descent

segment components.

temperature

in

determining

Time to

and time

values

performance.

in

flight

the

pressure

Climb

for the

have been

values are

cruise

at the departure

the values obtained

conditions

for the climb

in

Cruise Cruise

Time to (8

min.

Distance

nautical 2

nautical

Fuel to Climb minus .5

from those

values

the flight

Pressure

OAT

Climb

minus

to

Climb

miles minus

miles)

gal.)

segment of the flight

temperature.

planning

Altitude

1.5 min.)

(3.5 gal

performance

charts used

assume a no

wind

winds aloft must be

when

plan

altitude

computing

example is to determine

climb,

corresponding

and

the first variables to be

the climb components

(Figure

graph

pressure

established, apply the existing

field to

from

for the

altitude and outside

graph (Figure

graph

the

cruise

are the true fuel, distance and

were determined

example.

(l

1.5

from the

After the fuel,

5-25).

for the field of

pressure

plan

altitude.

corrected

from the

6000

6.5 min.*

9.5 nautical miles*

cruise

Fuel,

Now,

time

above

60c

gal.*

3

the

air

for

ft.

*reference

ISSUED:

Figure

NOVEMBER

5-25

8' 1979

REVISED: SEPTEMBER

17,

1984

REPORT:

VB-1080

5-5

SECTION

5

PERFORMANCE

(d)

Descent

The

descent data

provide

distance.

the descent

PIPER

be

will

distance

AIRCRAFT CORPORATION

PA-32R-301, SARATOGA

prior

determined

for establishing

to the cruise data to

the total cruise

SP

Utilizing

the

basic

figures

temperature at

adjustment

temperature conditions

find the

the cruise

fuel, distance

must be adjusted

values,

fuel,

distance

4l). Now, subtract the

from fuel, distance

descent segment

(e)

Cruise

subtract the

descend appropriate

Setting

The

selected

airspeed from

values obtained

the

and time

The values obtained

(l)

Time

(12

min. minus

(2)

Distance to

(28

nautical miles

2

nautical

(3)

Fuel

to

(3

gal.

Using the

previously calculated distance

to establish

Avco Lycoming

(Figure5-27)

Table

established

cruise

pressure

and

the destination

use the

at

and

values obtained

from

values needed

by

example are shown below.

of the

Descend

to

I min.) I

Descend

miles)

Descend

gal.)

0.5

minus

total distance

the total

pressure

power

the Speed

altitude

should

Power

altitude and OAT, determine

time for

descent

for the field

(Figure

pressure

541).

altitude

These

airport. To find the necessary

existing

the destination airport as variables

time values

pressure

from the

altitude and

(Figure

graph

from the field conditions

the

proper

minus

conditions to find the true

cruise

for the flight

utilization of the

26

nautical miles*

plan.

graphs

for the

I

2.5

min*

to be traveled during the flight,

cruise

Operator's

selecting the cruise

when

and

now be utilized to

graph

distance.

temperature

(Figure

to climb

Manual

and distance

Refer

to the

and the

power

values and the

determine the

5-31).

Power

setting.

and

to

5-

gal.*

to

true

setting Operator's

*reference

REPORT:

5-6

Calculate

the cruise

from the information

Manual.

Figure

VB-1080

541

consumption for

fuel

provided

ISSUED: NOVEMBER

REVISED: SEPTEMBER

by the Avco

the cruise

Lycoming

power

8,

l?,

1979 1984

PIPER AIRCRAFT CORPORATION

PA-32R-301,

cruise speed and

fuel

SARATOGA

The

cruise

consumption

SP

is found

time

the cruise

by

the

fuel

cruise

PERFORMANCE

dividing the

by

is found by multiplying

time.

cruise distance

SECTION

by

the cruise

5

the

(f)

The

cruise

the flight

planning

(l)

Total Distance

(2)

Cruise

(e)(l)

(dX2),

miles minus miles minus

miles)

(3)

Cruise

(4)

Cruise

(5)

Cruise

Consumption

(6)

Cruise (e)(2) (256

divided

(7)

Cruise (e)(5)

(13.8

by

Flight

Total

The total

time to descend

the

taken from

values

be converted

must

calculations

example

Distance

(c)(4)

minus

(291.5

nautical

9.5 26 nautical

Power Speed

Fuel

Time

divided

nautical

multiplied

GPH multiplied

1.77 hrs.)

Time

flight time

by

miles

144.5 KTS)

by

Fuel

and

the climb

hours before

to

established

follows:

as

are

minus

nautical

(e)(4),

(e)(6),

by

is determined

the cruise

and descent

adding them

for the cruise

291.5 nautical

nautical

256

65%o

144.5 KTS

1.77 hrs.

-/

by adding

time, Remember!

graphs

the time to

in minutes

are

to the cruise

segment

miles

J

miles

(economy)

TAS*

13.8 GPH

(l

46 min.)

gar.

24.5

climb,

The

time

and

time'

of

hr.

examPle:

*reference

ISSUED:

REVISED:

The following

(l)

Total Flight

(cX3) plus

(.1I

hrs.

(6.5

min.

46 min.)

5-31

Figure

NOVEMBER

SEPTEMBER

flight time

Time

(dXl) plus

plus

.18 hrs.

plus

I

8' 1979

17,

1984

I

min.

r

is required

(eX6),

plus

1.77 hrs.)

plus I

hr.

the flight

for

REPORT:

planning

2.06

2 hrs. 3.5

VB-1080

hrs.

min.

5'7

SECTION

5

PERFORMANCE

(g)

Total Fuel Required

PIPER

AIRCRAFT CORPORATION

PA-32R-301, SARATOGA

SP

Determine the total

fuel to

the

gallons) the total

descend

is determined,

fuel weight

The total

shown

below.

(l)

Total Fuel

(c)(5) (3.0 (30.0

gal. plus 2.5

fuel required

the cruise

and

multiply

for the flight.

used

fuel calculations

Required

(dX3) plus

plus

gal. plus

gal.

multiplied

by 6

by adding

I'uel.

this value by

the fuel to climb,

When the

galto

6lbl

for the example flight

(eX7),

gal.)

24.5

lb/gal.) 180.0

total

determine

plan

fuel

30.0

(in

are

gal, lbs.

REPORT:

5-8

VB-1080

ISSUED:

REVISED:

NOVEMBER

SEPTEMBER

8,

17,

1979 1984

5-12

REPORT:

SECTION

PERFORMANCE

VB'1080

AIRSPEED

SYSTEM

Figure

5-3

ISSUED:

CALIBRATION

NOVEMBER

t'

1979

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CORPORATION

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30"

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1

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Wing flaps: Angle Stsll

STALL

40'

of bank: 20"

speed:

59

10

SPEED VERUS

NOVEMBER

KIAS

20

ANGLE

OF BANK

Figure

t, 1979

DEGREES

-

ANGLE

5-5

OF BANK

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79

78 77

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PA. 1

MAL PROCEDURE

TAKEOFF

ASSOCTATED

PAVED,

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CONDTTTONS:

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DRY RUNWAY

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Takeoff distance (3-Blade);

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weight:

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speed: 74

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OUTSIDE AIR TEMPERATURE

RPM AND

27OO

0 10 20

PA-32R-301

_

FLAPS

ASSOCIATEO

FULLTHROTTLE BEFORE BRAKE RELEASE

PAVE LEVEL DFY RUNWAY

30 40

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CONDITIONS:

3600 3400 3200 3000

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2600

3600 3400 3200 3000 2800 2600

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GROUND

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PERFORMANCE

NOVEMBER

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FLAPS

8,

1979

25'

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PA.32R-301,

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27, 1979

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as

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LES AND TERFAIN PERMIT.

as

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pressure

Outside air temp:

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z

o

lrJ

z

r-

E!

F'

F

-o

\o

{

\a

sä

IJO r-

:g

o

F'

7

F

H

ta,

o

11

ö

F

PA-32R-301

GEAR

RATE

2600

OF CLIMB

TED GEAR UP, MIXTURE

91 K|AS

RPM FULLTHROTTLE

2-BLADE PROP

UP

CONDITIONS

FLAPS UP

AS

NOTED

z

ttt

,rt

0a

L)

(x)

"

BICH

LEANED

OF PEAK

TO

äF

?>

u l.l

Itl

FOR NORMAL OPERATIOiIS

wlTH 2-BLADE PROP

RP'{ TO 2600 AS SOON

REDUCE

AS

OBSTACLES

PERMlT.

Climb

I

i.)

t

IE

I

Ct

o\

e

F

E

-40

3

-30

OUTSIDE

-20

-10 0

AIR

10 20 30

TEMPERATURE

_

OC

40

o

RATE

500

OF CLIMB

1()0() 1600

_

FT.,/ MIN.

Outsids Gross Rato of climb:

IIISTALLED

TERFAIN

AI{D

pressure

altitude:

air temp.:

weight: 3480

6OO

+6"C

lbs.

fpm

6000 ft.

(260()

RPMI

Ft

fF

(,

iJH

ür>

3>

"ü

I-;

;ö

!E

n3

:t

FI

F

E

Ov)

t-H

'E

z2

El

l!,

H

o

z

rrr

REPORT: VB-l080

5-22

(3

BLADE PROPELLER

Figure

5-23

ISSUED:

-

NO TrME

NOVEMBER

LIMIT)

GEAR UP

RATE

OF CLIMB

(2

BLADE

PROPELLER

.

5 MIN

G

E

(Y)

I

ul

o

ut

F

tr

o

lrr

=

N

I

N

o5o

o

G

ul

tr

3

x

ot

tt

-

&

G

U

I

ÄoE

A

=z

o

a

I

o.

o

lt

s

ltA.D

aa

I

=E

2-

I

u

A

@

=

J

c

D

o

A

o

.:

FJ

F

SECTION

PERFORMANCE

5

N

00

I

F

o

PIPER AIRCRAFT

PA-32R-301, SARATOGA

E

ö

oPoo

s

oO(,cc

g gf;

o o 5$

E

EE

@

3 .: E.E

5 e ijä

I

FüD

öa

t:

:.

-@-a

EF

(oN

*s'.eE

il:G

.o-

I

CORPORATION

I'

1979

LIMIT)

o

tt

o

ah

F

o

f

=

uJ

F

E

ul

E

ut

c

o

tt

o

UJ

E

F

o

f

I

o

ul

F

.E

E

=

J

olto

=

E

I

SP

ISSUED: NOVEMBER 8, 1979

FUEL, TIME AND DISTANCE TO CLIMB

Figure

5-25

PIPER AIRCRAFT

PA-32R-301,

oo

ctJ

te

o

(Y)

I

7=

Hf

XE

ilx

F<

s=

Jt,

o

o.

<o"

I

r

o-'

tr

u.l

o

ot

ah

.o

o

ro

oo

Eo

eZ

Z-

ü2

F

E,

UJ

3

oÄoto

SARATOGA SP

CORPORATION

jj

o

E

oo(J(JFoq

.&$33Eüe

.:.:ir,:o!

ttooicy

ooäAE6F

sssE:ä!

AO= o !=

*EiEn=E

rro.:-!6

5 ci# 9-lo

äöoooEri

't

Fuäsr*,*

gi.:1,,1,!,1',

.

; E6-

REPORT: VB-10t0

s-23

iu.|

z

-:

ti

CG

)

J

f

88

EE

F@

NN

u.l

lt

R9

f

r

J

u

J

t-

o

EIF

o

PERFORMANCE

SECTION

5

'A)

a

6a 1t

(,trI

rtl u

-.2

ö<

Fl

o?

=E!

'.\t

F-

"s=

ui

tJ€ (,re

LYCOMING

Std.

Temp.

Alt.

oc

Press

Alt.

Feet

It

l5

SL

7E

{

!.a

ua

rr

CDH

.i. z

\a

H

EE

F

FI

r000 2000 3000

4000 5000 6000

7000

8000 9000

10,000

r

1,000

12,000

13,000 14,000 15,000

Fl

maintain

I

To

from standard

standard.

constant

altitude

t3

lt

9

7

5 3

I

-l

-3

-5

-1

-9

I

-l

-13

-t5

power, correct manifold

temperature.

MODEL IO-540-K,

HP

165

Agp11.

RPM &

2100 2200 2300

22.5

22.3

22.1

2t.9

21.7

21.5

21.3

2t.0

20.8

20.6

20.4

20.2

20.0

5570 Rated

-

fuel I1.9

MAN. PRESS,

21.8

21.6

21.4

21.2

21.0

20.8

20.6

20.4

20.2

20.0

19.8

19.6

t9.4

19.2

manifold

Add

21.2

21.0

20.'l

20.5

20.3

20.1

19.8

19.6

19.4

19.2

19.0

18.7

t 8.5

18.3

18.0

pressure

gal/hr.

2400

20.7

20.5

20.2

20.0

19.8

19.6

r9"3

r9. I

18.9

18.6

18.4

t8.2

18.0

17.7

t7.3

16.9

approximately

pressure

-L, -M

195 HP

Aptryl_!3.|

RPM

SERIES,300 Hp ENGINE

Rated

-.65V0

MAN.-PRESS.

&

I 3.8

gal/!t.

2100 2200 2300 2400

25.6

25.3

25.t

24.8

24.6

24.3

24.0

23.7

24.7

24.4

24.2

23.9

23.'7 22.8

23.5

23.2 22.3

22.9 22.0

22.5 21.8

0.16"

23.5

23.3

23.O

22.5

2t.5

21.2

Hg

23.2

22.9

22.7

7t<

22.2

22.0

21.7

2t.5

21.2

21.0

20.7

20.4

for each

23.8

for air temperature above

22!_HP

-Approx.

RPM & MAN.

75%L\&!

-

fuel

16.0_ga_l

PRESS.

2200 2300 2400

27.6

27.3

27.t

26.8

26.5

5oC

standard; subtract for

26.6

26.3

26.1

25.8

25.6

25.3

25.0

variation

in induction

trr

25.8

25.5

25.2

24.9

24.6

24.4

24.t

23.8

air temperature

temperature below

(jE hJ-

,:.

A-

a>

>i

Äo

>f;

At^

F1

oU)

<':

>=

z\)

6Z

Fur

>

=

z

ISSUED:

REVISED:

NOVEMBER

SEPTEMBER

MAXIMUM

8, 1979

17, 1984

SPEED

Figure 5-29

.

PERFORMANCE

o-

tr

f

o<J

I

rt3ö

ir$

(Y)

8=8

oi>

zio

6ilü

E5E

o-

(,):lE

UJ

J.

PA-32R.301,

PIPER

IIJ

E

o

lJ.

E

..

I

9

E

J

C)

AIRCRAFT CORPORATION

N

(Y)

I

oJo

(,)ro

?gg

t

u.l

(,

F

o

SARATOGA

-o.9

U

öooG

E(J(JF

cJJ5

.9

o

o=o

äd9

6,=ü

ooo

or

e o-:

.E öI

g

o.:(o

*N

+

O(J

Oo

o(o

@+

o:!

i

SP

REPORT:

VB-r0t0

5-27

PERFORMANCE

SECTION

o

o:z

o

'o

-.n

F

)

F

ut

o.

uJ

o

+

Oo

tl

RH

o{

FG

oE

9E

ouJ

$o

85

o

rf

N

o

str

^(,

uJ

F

f

tr

DI

o

l!ulo.

@

.tt

F

o

z

F

5

REPORT: VB-l080

s-28

Figure

5-31

REVISED:

ISSUED:

NOVEMBER

OCTOBER

ll, 1983

8, 1979

SPEED

.

CRUISE

POWER

N

o-

T

t4

(,

F

u

f

E

o

2

ää

OU

tz

gt

I

t

=E

;ä

rP

9o

iu

z

oo

o

EGÄ

4l

3t

E!

i

Es

q

F

o

z

t

*i

F

E

'5

tt

4'

gxxx

oFoo

c

<o60

.9

(J

o

o-

F

I

oaooo

.!2

p

{)

=

o

o)

:

äe

ro

(o

o3o

o

tc

t

8s

o)

G

]FFF

o

.:

tt

of

lceq

o

+

6d

E

ro

F

k=

9rrr

.GAAÄ

900s

o

OF

urX

o

(oö!,fg

+

SECTION 5

PERFORMANCE

Eä

ts<

ot{

*.u

ö5

I'a

..L

o

o.

u.l

;se

v

Hä;

Äoz

-20

F

(9

ur

s8a

ooo

FOO

oö

o

(o

o

PIPBR

AIRCRAFT

PA-32R-30I,

CORPORATION

SARATOGA

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5

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G

ur

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I

Gulo.

I

o

+

o

o'

N

o

u.l

o

ur

uJ

o

E

F

f

tr

o.

uJ

v

o

I

o

n

o

att

F

z

SP

?r0

(,

(t

,l

Fl

E{

-13

RANGE

=

I

a

-9

-5

PA.

_

ASSOCIATED

RANGE

DESCENT DISTANCE, GEAR

FLAPS UP, MIXTURE

PEAK EGT. 102 GAL. USABLE.FUEL,

3600 LBS. GROSS

2R-

CRUISE

CONDITIONS:

INCLUDES CLIMB

LEANED TO

WT., NO W|ND

1

POWER

AND

UP,

lal

FO Ei

;z

't

z

.)

ut

rsA

ja

Ua F-

':z

a>

r6

t) l!i

t!E

AJ-

-oo

\O \O

*{

(,

z

'11r

G'ö

oc

=F

"a

t;

=

2,

\o

o

ut

-1

G,

f F

E

ut

o-

3

u,

= o

E

7

o

z

F

ttt

15

1. ADD I N.M.

DEGREE CENTIGRADE

STANDARD

2. SUBTRACT

EACH

Cruise Cruise outside air temp.: Power: 65%

Range with reserve: 92O N.M.

1 x

Range no

1

x

RANGE FOR EACH

TEMPERATURE.

1.5 N.M. RANGE

DEGREE

FUEL FLOW

POWER

15.O GPH

75%

13.8

65%

1I,9

s5%

e:

pressure

(6-3)

923

=

reserve: 1013 N.M.

(6-3)

1016 N.M.

=

FOR

CENTIGR

GPH GPH

altitude: 6000

+

N.M

6oC

Irl

rü>

rF

b.J

-

C,DQ

>Y

F2

>:

+

(INCLUDES

BANGE - NAUTICAL

DISTANCE

TO

MILES

CLIMB

AND OESCENDI

>=

aY/

4z

RBPORT:

5-32

VB-I080

Figure 5-39

REVISED:

ISSUED:

NOVEMBBR

OCTOBER

o

if

o

N

ooo

o

lJ

-

ENDURANCE

3onrllv

tunsstud

ooo

o

+

ooo

N

SBCTION 5

o.

IJJ

o

z

E

o

UJ

f

z

2

O*y_tr

F;fid

!lGo.uJ

6J

n3E3

L<.

stsd

ou.rJo

B" t!

<

F'

x

=

o

@

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o

=

o

ed

o

t

(,

ai

.o

J

f

o

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F

=

o

ah

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o

oulo

(Ü)

I

3co

s8<s

ooo

I

xz

oo

EQ

t3

qqol

r4d

000

.a

EEE

E

0

UJ

E

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x

(JO-UrU

LöCC

Äoz

ise

-20

I

q

üögg

f 5E!

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o(,

H=3

g3

--

-.

U

6

@äF

j

^sC

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P €E

;ß

ts

ss

@D

QO

'c

@-

öf-

@

P nP

ö nr

E is

; üH

ö

F

o

(ü)

E

PERFORMANCE

fL

.6

PIPBR

AIRCRAFT

PA.32R-30I,

CORPORATION

SARATOGA SP

ll, 1983

8, 1979

o

@

t

5E

o

lll

l

z

@

UJ

o

z

I

F

o

o!cl

o

ISSUED:

NOVEMBER

FUEL, TIME, AND

Hffi

PA-32R.30I, SARATOGA

F

0

oul

ürG

E

F

u6

oi

I

-e

00

z

ä8

C'

L

lrJ

EP

t

F

g;

UJ

o

z

o

(rl

o

-

o

N

o

z

lu

E

t-

j

ul

ll-

3

!r

9rr

üE

?F

I

t

6

A

J

lr

Ä'

5

E

ül

o

PIPER

AIRCRAFT

t, 1979

REPORT: VB-10E0

5-33

Figure

DISTANCE TO

5-41

DESCEND

l:

ilillI

1111

I

ü

Q r-r

Hb

_Ea

{e

!:

da

e5

E.!

oo

:o

it

6.1

o

.E

oo

8

d

B

E;

6

ö

@

ot

o

t-

e

':

!

ö

o

Jaa

-: ci

ett

il

d

!

a

6

9n

il

Eo

!t

N

+

i;

.g

E

t

z

@

({

'-

r

3

h

.=e

to

a

E

Ftt

3o

o

8

at

oö

cll

o

ao

aso

s

$r

?

s

E(v)

o

öo

;

r

2

uJ

Iilt

tl

ti

3

+llEil

läl

lXt

11

lF

ld

o

2

u,

ul

L

J

f

I

ft

t

o

a

U

u

)

ul

IA

CORPORATION

SP

PERFORMANCE

ü

(J

SECTION

5

5-34

REPORT:

sEcTtoN

PERFORMANCE

VB-10E0

GLIDE RANGE

Figure 543

REVISED:

ISSUED: NOVEMBER

DECEMBER

l0'

I'

t979

l9t6

-:

JO

og

(,

F

o!

Eo

ulB

(9P

zä

Ulz

.A

5

o.

5

tr,

tr

\

PIPER AIRCRAFT

PA-32R-301,

CORPORATION

SARATOGA

u

a

o

0

o

6

o

rt

ul

o

_o

F

f

o

E

l!

G

i

o

N

o

t!

c

F

f

.r

ul

o.

I

o

r!

c,

2

G

<(

ut

o

J

I

(J

F

-

aa

ul

4

E

J

SP

tr6

ute

"ä

a

v)

FI

.;

o

EI

z

r-

EE

Irl

F

-€

\o

-t

\o

v

E

:t

F

ts

Eg

I

ä?

-Hg

fit> L

Ezl

.ü gi;

?t!'

üxrn

>H X> vtz

(t)

v

F

z

Fg

tt

F

ö

F

Example:

U

Destination Destination O.A.T.:

4

Landing

Wind:

FI

trj

Landing

F

STANDARD

WING FLAPS

PAVED LEVEL DRY RUNWAY

FULL STALL

pressure 400

(headwindl

-40

24"C

1490 ft.

OUTSIDE

-'to

AIR

weight 33OO lbs.; approach speed 78 KIAS

knots

5

CONDITIONS

40" POWER

TOUCHDOWN

o 10 20 30

TEMPERATURE

PA-32R-301

RMANCE

WHEELS

OFF

EXTEN

40

"C

-

3600

3400 3200

WEIGHT

AND BRAKESTIR

3000 2800 2600

_

POUNDS

WIND COMPONENTS

2000

I AOO

1 600

1400

200

_

KTS.

rd :E

(,

lll

IJH

&>

a*

'A)

4,

=>

>,j

('l

:

F L

I

>f;

t

ao

U

rcF

G

E

to

F

r o

lo

E

ul

o

ul

o

z

F

I

o I

o

=

z

J

Irt

Qa

;ä

rtl >Fi

to

äz

trj

H

z

Ur

REPORT: VB-1080

s-36

LANDING

GROUND ROLL.

TIRES

@

?3

F

;

Eä:

o-

"3#

I

T Hää

OD

-l F-o

N

G

O.

EHä

E

ä*I

SECTION

PERFORMANCE

(Y)

F

o

I

o

z

l

e

3E=

tr

<

öd:

J

eä=

Z.6E

oiz

E=

Y

ul

o

5

Figure

AND

5-47

ISSUED:

BRAKES

NOVEMBER 8,

1979

STANDARD

U

@

a

E

x

WHEELS,

o

q)

3l;

J

G

-iI o

c

.;E:

6

c

E

9o

L

-_

o

I

o

c

g!

'o

o

ci€e

E5

ä u1

o

Fo ö

o

kB!

..o

x

@

o

q_o

lll

o

g)

'a

(Jlj9

9a

Il

öoooo

rO@tlN

Soooo

-

SCNVIS|O

110U

ONnOU9

t)NtoNv]

Nac

o<

o=

o.

uJ

F

o

F

uJ

u.l

f

tt

o9

o"

o

I

o

@

o

YU

öB

o(9

o

oI

ol

EÄ

öo

F9

ooo

N

o

at,

o

6

o

b

o

F

v

o

UJ

z

o

o-

E

o

a

o

z

=

F

2

I

PIPER

AIRCRAFT

PA-32R-301,

CORPORATION

SARATOGA

SP

o a

c

ItJ

I

z

o

t5

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E!

FI

_6

\o

\t

\a

ttl

Fd

F

ts

I

(r€ {€

"ä

.F

EA

trj

>*

:*

UO

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i3

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öo=

'o

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22

HF

rz

--

oz

ro

Fg

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,i,

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q:

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>i Äö

>f;

At^

Ovt

,ü

>a

Fd

I>-

zQ

6Z

Fi

lal

>

H

z

Fl

ur

PA-32R-301

z

2

GROUP

_

3

o

tat

F

((

Example:

Destination Destination O.A.7.: 24"C Landing

Wind: 5

Landing distance:146O

prssure

weight: 33OO lbs

(headwind)

knots

-30

OUTSIDE

-2() -10 0 10

PTIONAL

ASSOCIATED

FLAPS 40"

wlNO

altitude:

LEVEL DRY

PAVED.

FULL STALL TOUCHOOWN

4OO ft.

AIR TEMPERATURE

LANDING

1 INSTALLED

NO.

CONDITIONS:

POWER OFF,

RUNWAY

LANDING GEAR

20

LANDING

"C

-

PERFORMANCE

GEAR

HEAVY

SEE EOUIPMENT

3600

3400 3200

WEIGHT

3000

_

POUNDS

2800 2600

DUTY

LI

WIND COMPONENT

15

2000

1 aoo

600

400

200

1 000

_

F

r

E

u

E

to

t

r o

rn

E

ul

o

ur

o

z

F

at,

ö

o

z

ä

z

KTS

I

J

REPORT:

5-38

SECTION 5

PERFORMANCE

LANDING

VB-l080

ISSUED: NOVEMBER

HEAVY

GROUND

DUTY

ROLL

GROUP

Figure 5-51

-

OPTIONAL

NO. I

INSTALLED

LANDING GEAR

8'

1979

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AIRCRAFT

PA-32R.30I,

CORPORATION

SARATOGA

SP

PIPER

AIRCRAFT

PA.32R-30I,

CORPORATION

SARATOGA

SP

WEIGHT AND

SECTION

BALANCE

6

6.I GENERAL

to

order

In

A.ri!n.O

gruulty Ättftougft

the maiimum

baggage.

ift"itfi.

takeoff.

airplane

it,.

C.G.

takeoff

pr.,nutur.ty

ituUifity

;;J

of

into

(C.G.) position

the airplane

with

airplane

Misloading

will

tr.uui.r

too

is

or

wiit

recovery

;pi"

approved

of

fai

landing.

Center

the

achieve

airplane,

the

number

the

is loaded

carries

take

nät

airplane

gravity

forward

tikeoff

on

reduced.

Ue

limit.

WEIGHT

performance and

the

must

it

within

flexibiliiy

offers

adult

of

flexibility

within

consequences

climb

off,

is loaded,

is a determining

in any

c.G.

If the

tend

or

This

becomes

more

SECTION

AND

flown with

be

approved

the

passengers,

comes

responsibility.

loading

the

or cruise

the

airplane,

too

is

pitch up

to

leaä

can

difficult

6

BALANCE

flying characteristics

the

operating

loading,

of

it cannot

full fuel

envelope

aircraft.

any

t-or

as a

well

as

performance

climb

less

in ilight

factor

be difficult

may

it

far aft,

the

duri'g

inadvertent

to

center

the

as

and

weight

tanks

The

before

properly

range

be.

and

pilot

An

(envelope)'

must

he

ove.rloaded

loaded

it

characteristics'

to

airplane

climb.

stalls

of

may

Longitudinal

and

gravity

are

which

center

with

flown

maximum

ensure

makes

one.

have.

will

If the

rotate

spins,

even

moves

of

a

for

aft

Aproperlyloadedairplane,however'.willperformasintended'Before

airptane

the

i..utio"

*.tgftt

;;ühi

poriri"n

änd

is computed

of

and

for

then

ISSUED:

REVISED:

licensed,

is

aiiplane

the

locaiion,

c.G.

loa.ded

the

determining

NOVEMBER

OCTOBER

is weighed,

it

(basic

empty

plus the

tt.

airplane by

whether

1979

8'

1983

ll'

optional

pitot can

computing

they

a basic

1nd

weight

equipment)'

derermine

within

are

consists

the total

the approved

empty

the standard

of

Using

the

weight

REPORT:

weight

the.basic

weight

and

envelope.

C.G.

and

empty

c.G.

and

moment

VB-l080

6-l

SECTION

WEIGHT

6

AND BALANCE

PIPER

AIRCRAFT CORPORATION

PA-32R-301,

SARATOGA SP

The basic

and Balance Data Form (Figure

equipment

responsible

and C.G.

Weight and Balance Record. The owner

A weight and balance calculation fuel or calculations

baggage

The

production

load. Note that the useful

passengers.

C.G.

AIRPLANE

6.3

At

airplane with the

is

data

supplied

empty weight and C.G.

(Figure

6-7). The

position

following pages

and

current values

is

added or any modification

for

the work

can be boarded

prior

to adding

is

to write these

and

required

so

fuel to insure against improper loading.

are

in

computing basic

load includes

Following this is the method

WEIGHING

the time of

basic

licensing. Piper Aircraft

PROCEDURE

empty weight and center of

by Figure 6-5.

and the Weight

6-5)

should

to compute a new

is necessary

to keep within allowable

as

forms used in weighing an airplane

empty weight,

location

are

recorded

always be used.

work is

in the Aircraft Log

should

for computing takeoff weight and

usable

make

in

determining

C.G.

fuel, baggage, cargo and

Corporation

gravity

in

and Balance

Whenever

done. the mechanic

empty

basic

Book

sure that

limits.

position, and

provides

location. This

The removal or addition of equipment or airplane modifications can

the basic

affect

weighing gravity

procedure

location:

empty weight and center of

to determine this basic empty weight and center of

gravity.

following is a

The

the Weight

Record

new

weight

the

and

it is

done.

how much

Check

useful

each

rn

(a)

(

REPORT:

6-2

Preparation

l) Be

certain that

are installed in the

(2)

Remove excessive dirt, rags

and tools

(3)

Defuel

airplane. Then open all

fuel is drained.

undrainable

unusable fuel

VB-1080

all items checked in the airplane equipment list

proper

location

grease,

from the airplane before

Operate

engine

fuel is used and engine stops.

(5

gallons

total, 2.5

in

the airplane.

moisture, foreign items

weighing.

luel

drains until

remaining

all

on each tank until all

Then add the

gallons

each wing).

such as

ISSUED: NOVEMBER 8, 1979

REVISED:

JULY

19, 1982

PIPER

AIRCRAFT

PA.32R.3OI,

CORPORATION

SARATOGA SP

CAUTION

WEIGHT

SECTION 6

AND BALANCE

Whenever the fuel system

and fuel is replenished

engine for

the

1000 RPM on each tank

the

with oil to full capacity

pilot

position.

control surfaces

proper

(4)

(5)

(6)

exists in

Fill

Place forward

all

in the

closed.

Weigh the

minimum of three minutes at

a

fuel supply

and copilot seats in fourth

Put

location

airplane

in scale readings due to wind.

(b)

Leveling

(l)

With

airplane

fully extended

(2)

Level airplane

to center bubble

(c)

Weighing - Airplane Basic Empty

on scales,

position.

(refer

on level.

is completely

it

will be

necessary

to insure

lines.

in

flaps

in the neutral position.

inside a closed

the fully retracted

and all entrance and baggage doors

block main

to Figure

6-3) deflating nose

Weight

drained

to run

that no air

(4th)

Tow bar should be

building to

gear

oleo

notch, aft of

position

prevent

pistons

wheel

and

errors

in the

tire,

ISSUED:

(

l) With the

airplane

shown on each scale.

reading.

NOVEMBER 8, 1979

level

and brakes released, record the

Deduct the tare, if

REPORT:

any,

weight

from each

VB-l0E0

6-3

SECTION

6

WEIGHT AND

Position

Scale

and

Symbol

BALANCE

PIPER AIRCRAFT

PA-32R-301,

Scale

Reading

Tare

CORPORATION

SARATOGA

Net

Weight

SP

Nose Wheel

Right

Main

Wheel

Left Main

Basic Empty Weight,

as Weighed

(d)

Wheel

Basic Empty Weight

(l)

The following

it

when

C,C. Arm

78.4

is

(N)

(R)

(L)

(r)

WEIGHING FORM

Figure

Center

geometry

level. Refer

c.G

6-l

of Gravity

applies to the

Leveling

to

Level Points

(Fuselage

Left

paragraph

Side)

PA-32R-301 airplane

(b).

6.3

r!

o

A

=

B

=

REPORT:

6-4

N

14.?

109.7

VB-I080

R+L

B

LEVELING DIAGRAM

Figure 6-3

Wing Leading

The

the

intersection

tapered

ISSUED:

Edge

is

datum

78.4

inches

wing leading edge at the

of the untapered and

section.

NOVEMBER 8, 1979

ahead of

PIPER

PA.32R.3OI,

AIRCRAFT

CORPORATION

SARATOGA

SP

WEIGHT

AND

SECTION 6

BALANCE

(2)

The basic empty

including optional equipment,

can be determined

C.C. Arm

=

N

Where:

6.5 WEIGHT

The Basic Empty

listed in Figure 6-5 are

figures apply number shown.

The basic

entered in the

been

provided

a

complete

permanently installed equipment moment

AND BALANCE

Weight,

only to the specific

present

to

empty

weight

Weight and Balance

the current

history

must be

entered in the

Center of Gravity

for the airplane as licensed at the

of the

status of the airplane basic

previous modifications. Any change to

of

weight center ol

following formula:

by the

+

(R

(A)

L)

(B)

gravity (as

full oil and

inches

weighed

unusable fuel)

1=}tri+ft+l_

DATA AND

airplane serial number and registration

airplane,

or modification

Weight and Balance Record.

as

Record

RECORD

Location

and

factory. 1-hese

licensed at the

(Figure

6-7). This lorm empty

affects weight

which

Uselul Load

factory, has

weight

is

and

the

or

ISSUED: REVISED:

NOVEMBER

OCTOBER

8, 1979

11, 1983

REPORT:

VB-1080

6-5

Piper Aircraft Corporation PA-32R-301T, Saratoga SP Pilot Operating Handbook

Specifications and Main Features

Frequently Asked Questions

User Manual