Gulfstream Aerospace AA-58 TIGER 1977, AA-58 TIGER 1978, AA-58 TIGER 1979 Pilot Operating Handbook

'

PILOTS OPERATING HANDBOOK

~II

Gulfstrea1n

Aerospace

Model

AA-58

TIGER

1977I1978/

1979

THIS HANDBOOK INCLUDES THE

MATERIAL

REQUIRED

TO

BE

FUR·

NISHED TO THE

PILOT

BY

FAR PART 23.

REGISTRATION NO.

GULFSTREAM AEROSPACE CORPORATION

SAVANNAH, GEORGIA, U.S.A.

©

Issued:

September

30,

1976

Revision

4,

Revised

May

12,

1983

0

Copyrishl

1979

All

ri~J1h

rNntd.

induding

lht

rig.Ill to

rqm><lun~·

1hi~

puhlicalion

No parl

m~y

t>e

rtprn·

ducffi.

~lured

m ;iny

rc-lntnl

.\y.\ttm.

or

lnn\mllh'd

many

parlor

funn

or

hy

any

me-an~.

r~clronic

pholocopyin11-.

microfilm,

microfid1e, nu·chan1cal.

or

olhrrwL'il".

without

prior

wn41tn

[>t'ffiU\~Hln

of

C.ul(slrcam

Amcnr~11

GULFSTREAM AEROSPACE MODEL

AA-5B TIGER

LIST OF EFFECTIVE PAGES

Dates

of

issue for original

and

revised

pages

are:

Original.

...

O ... September

30,

1976

Revision

...

1.

..

December

15, 1977

Revision

... 2 ...

July

15,

1978

Revision

...

3 ... February 15, 1979

Revision

... 4 ...

May

12,

1983

THE TOTAL NUMBER OF PAGES

IN

THIS HANDBOOK

IS

176 CON-

SISTING

OF

THE FOLLOWING. THIS INCLUDES THE SUPPLEMENTS

PROVIDED IN SECTION

9 WHICH COVER OPTIONAL SYSTEMS

AVAILABLE

IN

THE AIRPLANE.

Page No.

*Revision

No.

Title A ............................. 4

B ............... .

..

4

.

..

4

i............

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

3

ii

thru iii .......................... O

iv.. . ................. .

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4

...

2

.0

....

0

1-1

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

1-2

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..

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1-5

thru 1-12

2-1

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

2-2

Blank

2-3

.....

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.. 2-5 2-6. 2-7.

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

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......

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......

2

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1

..

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2-9

thru

2-12

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

..

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thru

3-4

...

..

35

......

3-6

thru 3-10

..

3-11

..

3-12

..

3-13 ....... .

3-14 thru 3-17.

......... 2

...... 0

........ 2

..

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2

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0

Page No.

•Revision

No.

3-18. . .... 1

3-19 ...

0

3-20 Blank

........... 0

4-1

and 4-2....

..

.... 0

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

4-4............... . .... 2

4-5

thru

4-9..

..

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

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.................................. 0

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

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

,_

0

4-13

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

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thru 4-21.. ................. 0

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.................................... 0

4-26

Blank.... . .. 0

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..

... 0

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Blank.... . . 0

5-3

thru

5-14

................... _ O

5-15 thru

5-17

. 2

5-18.......... .

0

5-19 thru

5-21..

. .. 2

5-22 and

5-23..

. O

5-24

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

5-25....

..

0

5-26

......

··························- 1

·zero

in

this

column

indicates

an original page.

Revised: May

12,

1983

198]

Gulfs1reilm

Aprospacr

Corporation

A

LIST OF EFFECTIVE PAGES

Page

No.

"Revision

No.

5-27 and 5-28.....

..

0

6-1.. ................ 0

6-2

Blank ................ 0

6-3

thru 6-15.... . .......... O

6-16......................

..

..... 3

6-17 ...................................

0

6-18 ................................... 1

619

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

6-20

Blank

....................... 0

7-1

thru

7-4

....................... 0

~5...........

. ......... 1

7-6

thru 7-11.

..

...... 0

7-12.......... 2

7-13 .................................... 4

7-14 .................................. 2

7-15 ................... -

""'""

0

7-16

and 7-16a ................. 1

7-16b Blank......... 1

7-17

thru

7-24.............. 0

~1

..

--·······--·-·--·-

.0

8-2

Blank..................

...

0

8-3

thru 8-5................ . 3

8-6

thru 8-10............. .

...

0

8-11

......... ·-..................... - 2

8-12.. . ........................ 1

8-13 and 8-14 ....................

O

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

..

....

0

9-2

Blank........... . ....... 0

9-3......................

..

........ a

9-4

Blank..

..

..... 0

10-1

and

10-2

.................... 0

10-3

........................ , ........... 3

10-4

thru 10-14 ................ 0

10-15

........................ "

""

2

10-16 ................................ 0

GULFSTREAM AEROSPACE

MODEL

AA-5B TIGER

·zero

in

this

column

indicates

an

original

page

.

Revised: May

12,

1983

B

GULFSTREAM

AMERICAN

MODEL

AA~58

TIGER

WELCOME

ABOARD!

WELCOME

ABOARD

y r AA-58

Tiger

has

been

designed

and

constructe?

to

provide

'fOU

wi_th

a

re~~onsive

four-place

airplane

to

serve

your

needs

for

either pleasure

or

business

flying in

both

comfort

and

economy.

This handbook has been prepared

to

.help you obtain the

maxi~um

P

!easu_re

a_nd

utility

from

your

airplane.

Read

it

carefully,

review

it

frequently,

and

keep

it

w1tl1

you

in

the

airplane

at

all

times.

With proper operational techniques and good maintenance, your

G~lfstr;arn

I

American Tiger should serve you well.

Get

to

know

your

Gulfs~ream

mencan

Dealer.

He

is

equipped

to

provide

any

assistance

that

may

be

required.

Revised:

February

15,

1979

PERFORMANCE~

SPECIFICATIONS

GULFSTREAM

AMERICAN

MODEL

AA~5B

Tl

GER

PERFORMANCE-SPECIFICATIONS*

SPEED:

Maximum

at

Sea

Level

148

KNOTS

Cruise,

75%

Power

at

8500

Ft.

139

KNOTS

Cruise, 65% Power at 8500 Ft. 128

KNOTS

CRUISE:

Recommended

Lean

Mixture

with fuel

allowance

for

engine start,

taxi, takeoff,

climb

and

45

minutes

reserve

at

45%

power.

75% Power at

8500

Ft. . . Range. 554 NM

51

Gallons

Usable

Fuel

. Time . 4

HRS:

5

~.11/N

75% Power at 8500 Ft. . Range. . . 373

NM

37 Gallons Usable

Fuel

. Time . 3

HRS:

2

~.lllN

RATEOFCLIMBATSEALEVEL

.B50FPM

SEHVICE

CEILING

. . 13,800

FT

TAKEOFF

PERFORMANCE:

Ground

Roll

Total

Distance

Over

50-Ft

Obstacle

LANDING

PERFORMANCE:

Ground

Roll

Total

Distance

Over

50-Ft

Obstacle

STALL

SPEED (CASI:

Flaps

Up,

Power

Off

.

Flaps

Down,

Power

Off

MAXIMUM

WEIGHT

STANDARD

EMPTY

WEIGHT:

BAGGAGE

ALLOWANCE

(Normal Category)

WING

LOADING:

Pounds/Sq Ft

POWER

LOADING:

Pounds/HP

FUEL

CAPACITY:

Total

01 L CAPACITY

ENGINE:

Avco Lycoming

180 BHP at 2700

RPM

PROPELLER: Fixed, Diarneter

.865

FT

.

1550

FT

.410

FT

. 1120

FT

.

56

KNOTS

. 53

KNOTS

2400

LBS

139B

LBS

.120LBS

17.1

13.3

52.6GAL BOTS

.0360A4K

75

IN.

•Performance S[lecifications

are

based

upon

standard

atmosrhere,

zero

wind,

and

gross

weight

conditions.

Issued:

September

30,

1976

II

GULFSTREAM

AMERICAN

MODEL

AA5B

TIGER

TABLE

OF

CONTENTS

TABLE

OF

CONTENTS

GENERAL

LIMITATIONS EMERGENCY

PROCEDURES

NORMAL

PROCEDURES

PERFORMANCE

...

WEIGHT & BALANCE/

EQUIPMENT

LIST

AIRPLANE

& SYSTEMS DESCRIPTION

AIRPLANE

HANDLING,

SERVICE &

MAINTENANCE

SUPPLEMENTS

(Optional

Systcrns Description

& Operating Procedures)

SAFETY

INFORMATION

Issued:

September

30,

1976

SECTION

. 1 ,2

.3

. 4

.5

.6

. 7

. '

'8

g

10

iii

WARRANTY

GULFSTREAM

AMER

CAN

MODEL

AA-58

Tl

GER

GULFSTREAM

AMERICAN

CORPORATION

(herein

GULFSTREAM

At~ER

ICAN) warrants each new aircraft and part

thereof

manufactured by

it,

tog~ther

with

all

new

aircraft

equipnient

and

accessories

bearing

the

name

"G

JLF-

STREAM

AMERICAN,"

to

be free

from

defects in material and

workmanship

under

normal

use

and

service,

but

extends

no

warranty

o~

any

kind,

express~d

or

implled,

to

any items

not

manufactured

by

GULFSTREAM

AMERICAN,

or

not

so

bearin-g

its

name,

whether

incorporated

into

or

installed

in

the

aircraft,

except

that

the

workmanship involved

in

installing suct1 items

is

warranted to be

without

defect.

The

obligation

of

GULFSTREAM AMERICAN under this

warranty

is

limited

to

replacement

or

repair,

at

the

option

of GULFSTREAM AMERICAN,

of any such aircraft,

or

any

part

or accessory which shall within

six

(6)

months

(twelve (12)

months

on

1978

and subsequent models) of operation be

found

defective. Such aircraft, part

or

accessory

is

to be returned to a

GU

LFSTA ::AM

AMERICAN

DEALER

upon

which examination by GULFSTREAM AMERICAN,

shall disclose

to its reasonable satisfaction to

lwve

been thus defective. This war-

ranty shall

not

in

any way

apply

to

or

cover any products which are

in

GULF-

STREAM AMERICAN's

opinion

damaged

as

a result of being

in

any

manner

altered

or

repaired

outside

of

the

factory of GULFSTREAM AMERICAN or

that

shall have been subject to misuse or negligence.

GULFSTREAM AMERICAN

makes no

warranty

whatsoever with respect to

engines, radios,

propellers, ignition appar<1tus, starting devices,

~enerators,

bat-

teries,

or

other

trade

accessories, inasmuch

as

such products are generally war-

ranted separately by their respective manufocturers .

"THESE

WARRANTY

PROVISIONS ARE EXPRESSLY IN LIEU OF

ALL

OTHER

WARRANTIES,

EXPRESSED,

STATUTORY

OR

IMPLIED

IN

FACT

OR

BY

LAW,

INCLUDING

ANY

IMPLIED

WARRANTY

OF

MERCHANT·

ABILITY

OR FITNESS FOR A

PARTICULAR

PURPOSE,

AND

OF

ANY

OTHER

OBLIGATION

OR

LIABILITY

ON

Ti!E

PART

OF

GULFSTREAM

AMERICAN,

EXPRESSED

OR

IMPLIED,

OF

A~Y

NATURE

WHATSOEVER

.

GULFSTREAM

AMERICAN

NEITHER

ASSUMES NOR

AUTHORIZES

ANY

OTHER

PERSON OR BUSINESS

ORGANIZATION

TO

ASSUME FOR

IT

ANY

OTHER

WARRANTY

OR

LIABILITY

IN

CONNECTION

WITH

THE

SALE,

USE

OR

OPERATION

OF ITS PRODUCTS."

IMMEDIATELY

ON

COMMENCING

FIRST

USE

OF

AN

AIRCRAFT, A WAR-

RANTY

VALIDATION

CARD

MUST

BE

FILLED

OUT

AND

MAILED

TO

THE

ATTENTION

OF THE CUSTOMER SERVICE

MANAGER,

COMMERCIAL

LIGHT

AIRCRAFT,

P.O.

BOX

2206,

SAVANNAH,

GEORGIA,

31402. NO

WARRANTY

CLAIMS

WILL

BE

HONORED

IF

THIS

CARD

IS

NOT ON

FILE

AT

THE

FACTORY.

iv

Revised: Feilnwry 15,

1979

GULFSTREAM AMERICAN MODEL

AA

58 TIGER

TABLE

OF CONTENTS

Three

View

..

Introduction

..

Descriptive Data

Engine . Propeller

Fuel

..

Oil

...

SECTION

1

GENERAL

Maximum

Certificated

Weights

Standard

Airplane

Weights

Cabin

and

Entry

Dimensions

Baggage

Space and Entry Dimensions

Specific Loadings . ,

..

Symbols, Abbreviations and Terminology

General Airspeed Terminology and Symbols Meteorological

Terminology

.......

.

Engine

Power

Terminology

. ,

....

, . . .

..

Airplane

Performance

anrl

Flight

Planning

Terminology

Weight and Balance

Terminology

....•..

Issued: September 30, 1976

SECTION 1

GENERAL

Page

. 1·2

. 1·3 . 1·3 . 1·3 . 1·3

.

1-4

. 1-4

. 1 8 . 1

·9

. 1·9

. 1·9 . 1·9

1·10

1-10

1.11 1-11

1-1

SECTION 1 GENERAL

9

....

NOTES:

1

1.

2.

Wheel base

length

5'

4•:

Minimum turning radius 19' 11·;

3.

Pivot

point -center

of

main

gear tire.

GULFSTREAM AMERICAN

MODEL AA·5B

TIGER

_J

figure

1-1.

Three

View

Revised: July 15,1978

1 2

GULFSTREAM AEROSPACE MODEL

AA58

TIGER

INTRODUCTION

SECTION

1

G'CNERAL

The ten

sections

of

this

handbook

contain

the

Information

needed

by

the

pilot

for

safe

and

efficient

operation

of

the

Gulfstream

Aerospace Model

AA·58 airplanes.

This

handbook

also

includes

the material

required

to

be

furnished

to the

pilol

by FAR, Part

23,

and

supplemen\al

data

covering

Gulfstream

Aerospace designed

optional

equipment installed in the airplane.

Section 1 provides basic data and

information

of

general Interest to

the

pilot,

to

assist

him in loading, sheltering, handling, and routine

prefllgr.t

check-

ing

of

the airplane.

Also

Included In

this

section

are

definitions

and explana-

tions

of

the

symbols,

abbreviations

and

termlnology

used

In

this

handbook.

DESCRIPTIVE DATA ENGINE

NOTE

Unless

otherwise

noted,

a!1

per-

formance and operational

data

in

this book are based on sea

level,

standard day, and airplane

gross

weight

conditions.

Number

of Engines:

Manufacturer:

Avco

Lycoming

Model

Number: 0-360-A4K

Type: Normally-aspirated, direct-drive, air-cooled, horizonta!!y-opposed,

carburetor

equipped, four-cylinder engine

with

360

cubic

inch

displacement.

Horsepower

Rating and

Engine

Speed:

180

HP at

2700

RPM

PROPELLER

Manufacturer:

McCauley

Model

Number: 1A170/FFA 7563, 1A 170/KFA 7563 or

1A

170EIKFA 7563 Diameter: 75 inches Type: Fixed

pitch

Revised: May

12,

1983

1·3

(0

1CJfl3

Gulfslwarn

Aerospace

Corpor;il1on

SECTION 1 GENERAL

GULFSTREAM

AME '11CAN

MODEL

AA·5B

TIGER

FUEL

CAUTION

UNDER

NO

CIRCUMSTANCES

SHOULD

FUEL

OF

A LOWER

OC.

TANE

RATING

THAN

THAT

SPECI·

FIED

BELOW,

OR

AUTOMOTIVE

FUEL

(REGARDLESS

OF

OCTANE)

BE

USED.

I Grade (and

color):

100

Minimum

Grade Aviation Fuel (green). 100

Low

Lead

Avia_tion

Fuel (.blue)

is

also approved. Refer

to

the latest revision

of

Lycoming

Service

Instruction

No. 1070

for

further

information

concerning fuels.

Capacity

is

at

an

ambient temperature

of

70°F (21°C):

OIL

Total: 52.6 U.S. gallons (43.8 Imperial gallons) (199.0 Liters) Each

Tank: 26.3

U.S.

gallons (21.9 Imperial gallons) (99.5 Liters)

Total Usable:

51

U.S.

gallons (42.5 lrnpcrial gallons) (193 Liters)

Grade (Specification).

Aviation Grade Straight

Mineral Oil

Ml

L-L-6082 (Figure 1-2) shall

be

used to

replenish oil supply during the first 25 hours

of

operation and at

the

first

25-hour

oil

change. Continue

to

use

this grade

of

oil for the first 50

hours

of

operation.

NOTE

The

airplane

is

de(ivered

from

the

.

factory

with

corrosion preventative air-

plane

engine oil. This oil should

be

Urained after the first 25 hours

of

en-

gine operation.

Ml L-L·22851

~Figure

1-2)

Ast1less

Dispersant Oil: This specification oil shall

be

used

after the

first

50 hours

of

engine operation.

1 4

Revised: July 15, 1978

GULFSTREAM

AMERICAN

MODEL

AA-58

TIGER

TRADE

NAME

MIL-G-21164

GREASE (Note

1)

Aeroshell Grease

17

Braycote

664

PED 3350

Grease

Royea

64

Grease

TG-4727

Grease

MIL-G-6711

GRAPHITE (Note 1)

Graphite Graphite

Graphite

SECTION 1

GENERAL

MANUFACTURER

Shell Oil Company

Bray

Oil

Company

Standard

Oil

Company

Royal

Lubricants

Company

Texaco

1nc.

Dixon

Company

Electrofilm

Company

Electro-Graph Company

MIL-H-5606

HYDRAULIC

FLUID

(Note 1)

3125

HVD

Oil

Humble

Oil

& Refining

Company

Brayco

Micronic

756C

Bray Oil

Company

PED-3337, -3335

Standard

Oil

Company

Royco

756A

& 8

Royal Lubricants

Company

XSL 7828

Shell

Oil

Company

YT-283

Union

Carbide

VV-P-236

PETROLATUM

(Note 1)

Braycote 236

Bray Oil

Company

Parma

70

Humble

Oil & Refining

Company

Royea

1 R

Royal Lubricants

Company

MIL-L-7870

OIL

(Note

1)

Brayco 363

Bray

Oil

Company

Cosmolube 263

E.

F.

Houghton Company

Enco Instrument

Oil

Humble

Oil

& Refining

Company

Low

Temperature Oi!

1692

Texaco

Inc.

Royco

363

Royal

Lubricants

Company

Figure 1-2

Lubricants

(Page 1

of

3)

Issued:

September

30,

1976

1 5

SECTION 1 GENERAL

TRADE

NAME

MIL-G-25760 GREASE (Note

1)

Aeroshell Grease

16

Braycote

6605

Royea

60R

Supermil ASU No. 06752

TG-4971 Grease

MIL-G-7711 GREASE

!Note

1)

Aeroshell No. 6

Regal

AFB 2

GULFSTREAM

AMERICAN

MODEL AA-58

TIGER

MANUFACTURER

Shell Oil

Company

Bray Oil

Company

Royal

Lubricants

Company

American

Oil

Company

Texaco

Inc.

Shell Oil

Company

Texaco

Inc.

MIL-L-6082

STRAIGHT

MINERAL

OIL

- ENGINE (Notes 1

and

2)

Aeroshell Oil

65

Shell Oil

Company

Aeroshell Oil

100

Shell Oil

Company

Chevron

Aviation

Oil

65

Chevron Oil

Company

Grade

1100

Chevron Oil

Company

Avrex

101/1065

Mobil Oil

Company

Avrex

101/1100

Mobil Oil

Company

Conoco

Aero

Oil

1065

Continental

Oil

Company

Conoco

Aero

Oil

1100

Continental

Oil

Company

Grade 1065

Champion

Oil & Refining

Company

Grade 1100

Champion

Oil & Refining

Company

MIL-L-22851 ASHLESS DISPERSANT

OIL

- ENGINE (Notes 1

and

2)

-

Aeroshell W120

Shell Oil

Conlpany

Aeroshell W80

Shell Oil

Company

Chevron

Aero

Oil

Grade

120

Standard

Oil

Company

RT-451

Mobil Oil

Company

RM-173E

Mobil

Oil

Company

Figure 1-2

Lubricants

(Page 2

of

3)

Issued:

September

30,

1976

GULFSTREAM

AMERICAN

MODEL AA-5B Tl

GER

TRADE NAME

SECTION 1

GENERAL

MANUFACTURER

MIL-L-22851 ASHLESS DISPERSANT

OIL

- ENGINE (Notes 1

and

2)

(Cont.)

RM-180E

Mobil

Oil Company

TX-6309

Texaco

Inc.

Premium

AD

120

Texaco

Inc.

Premium

AD

80

Texaco

Inc.

Oil E-120

Exxon

Company

Oil A-100

Exxon

Cornpany

Oil E-80

Exxon

Company

Note 1:

The

vendor

rroducts listed

in

this

chart

have been

selected

as

representative

of

the

specificntion

under

which they

appear.

Other

equivalent

rroducts

conforming

to

the same specification

may

be used.

Note

2: Oils

conforming

to

the

latest revision

of

Lycoming Service

Instruction

No.

1014

may

be

used.

Figure

1·2 Lubricants (Page 3 of 3)

Issued:

September

30, 1976

1-

7

SECTION 1 GENERAL

•Recommended

Viscosity;

Average

Ambient

Air

Temperature

Above 6(l"F (16"C)

30'F

(-1"C)

to

90'F

(32°CJ

O'F

(-18"C)

to

70'F (21"C)

Below

1

O'F

(-1

:?°C)

Mineral Grade

SAE 50 SAE

40

SAE

30

SAE

20

GULFSTREAM

AMERICAN

I

MODEL AA-5B

Tl

GER

Ashless

Dispersant

SAE

40

or

SAE

50

SAE

40

SAE

40 or

SAE

30

SAE

30

*Refer

to

latest

revision

of

Lycoming Service

Instruction

No.

1014

for

further

information.

Oil

Capacity

Sump:

8 U.S.

Quarts

(6.66

Imperial

Quarts)

(7.57

Liters)

Minimum

Safe

Quantity

in

Sump:

2 U.S.

Quarts

(1.67 Imperial

Quarts)

I 1.B9

liters)

It

is

recommended

that

lubricating oil

be

changed

at

least every

50

hours

of

engine

operation.

MAXIMUM

CERTIFICATED

WEIGHTS

Takeoff:

Landing:

Normal

Category:

Utility

Category:

2400

pounds

2050

pounds

CAUTION

THE REAR SEATS

SHALL

NOT

BE

OCCUPIED

DURING

FLIGHT

IN

UTILITY

CATEGORY OPERATIONS.

Normal

ca"tegory:

Utility

Category:

2400

pounds

2050

pounds

Weiylit

in

Baggage

Compartment,

Normal

Category:

120

pounds

maximum

allowable

if

e.g.

is

within

Center

of

Gravity Envelope (Figure 6·5).

Refer

to

Section

6 for cargo

!oading

instructions.

Weight in Baggage

Compartment,

Utility

Category:

IN

THIS

CATEGORY

THE

BAGGAGE COMPARTMENT AND REAR SEATS

SHALL

NOT

BE

OCCUPIED.

Issued:

September

30,

1976

1-8

GULFSTREAM

AMERICAN

MODEL

AA-SB

TIGER

STANDARD

AIRPLANE

WEIGHTS

NOTE

Actual weights for each

airpl<:ine

wil!

vary, accordi11a

to

installed erpiipmcnt.

Refer

to weight and b<llance data

supplied

with

the

particular

airplnne

for

specific

<lata

for

that

airplane.

Standard

Empty

Weight: 1398 lbs.

Maximum Useful Load: Normal Catefjory: 1002

Utility

C<1te~1ory:

652

CABIN

AND

ENTRY

DIMENSIONS

SECTION 1

GENEnAL

Detailed

dirnensions

of

the

cabin

interior

and

canopy

opening

are

rrovirled

in

Section 6.

BAGGAGE

SPACE

AND

ENTRY

DIMENSIONS

B<iggage

area

and

access

dimensions

are

provided

in

Section

6.

SPECIFIC

LOADINGS

Wing

Loading:

Power Looding:

17

.1

pounds

per

square

foot

13.3 pounds per B.H.P.

SYMBOLS,

ABBREVIATIONS

AND

TERMINOLOGY

GENERAL

AIRSPEED

TERMINOLOGY

AND

SYMBOLS

KCAS

Kll\S

KTl\S

Knots

Calibre1ted Airspeed

is

indicated

airspeed

corrected

for

rosition

and

i11strurnent

error

and

expressed in

~nots.

Knots

calibrated

airspeed

is

equal

to

KTAS

in

standard

atmosphere

;:it

sea level.

Knots

Indicated

Airspeed

is

tile speed sfiown on

the

outer

sc;ile

of

the

oirspecd

indicator

<1nd

expressed

in

knots.

Knots

True Airspeed

is

the

<rirspced expressed

in

knots

relotive

to

undisturlird

;:iir

which

is

KCAS

corrected

for altitudP. anrl

temperature.

!ssur.d: Septcrnlir.r 30, 1976

1 g

SECTION 1

GENERAL

Vy

GULFSTREAM

AMERICAN

MODEL

AA-58

Tl

GER

Maneuvering Speed

is

the

maximum

speed

at

which

application

of

full available

control

will

not

overstress

the

airplane.

Maximum Flap Extended Speed

is

the

highest speed permissible

at

which wing flaps can be

extended.

Maximum

Structural

Cruising

Speed

is

the

speed

that

should

not

be

exceeded

except

in

smooth

air,

then

only with

caution.

Never Exceed Speed

is

the

speed limit

that

may

not

be

exceeded at

any

time.

Stalling Speed (Clean)

·is

the

minimum

steady flight

speed

at

which

the

airplane

is

controllable.

Stalling Speed (Landing)

is

the

minimum

steady flight

speed

at

which

the

airplane

is

controllable

in

the

landing configuration.

Best

Angle·of-Climb Speed

is

the

speed which results

in

the

greatest gain

of

altitude

in

a given horizontal distance.

Best

Rate-of·Climb Speed

is

the

speed which results

in

the

greatest gain

in

altitude

in

a given time.

METEOROLOGICAL

TERMINOLOGY

OAT

Standard Temperature

Pressure Altitude

Outside

Air

Temperature

is

the

free air

static

temperature. It

is

expressed

in

either

degrees Celsius (Centigrade)

or

degrees

Fahrenheit,

Standard

Temperature

is

15°C (59"F)

at

sea level pressure

altitude

and

decreases

by

2°C

(4°F) for each 1000

feet

of

altitLtde.

Pressure

Altitude

is

the

altitude

read

from

an altimeter

when

the

barometric

subscale has been set

to

29.92 inches

of

mercury

(1013

mb).

ENGINE

POWER

TERMINOLOGY

BHP

RPM

1-10

Brake Horsepower

is

the

power

developed by

the

engine.

Revolutions Per Minute

is

engine speed (number of revolutions

engine turns per minute).

Issued: September 30,

1976

GULFSTREAM

AMERICAN

MODEL

Ak5B

TIGER

SECTION 1

GENERAL

AIRPLANE

PERFORMANCE

AND

FLIGHT

PLANNING

TERMINOLOGY

Demonstrated Crosswind Velocity

Usable

Fuel

Unusable Fuel

GPH

g

Demonstrated

Crosswind Velocity

is

the velocity of

the

crosswind

component

for

which

adequat11

control

of

the

airplane

during

takeoff

and

landing

was

actually

demonstrated

during

certification

tests.

Usable

Fuel

is

the

fuel available

for

flight.

Unusable

Fuel

is

the

quantity

of

fuel

that

cannot

be

used

in

flight.

Gallons

Per

Hour

is

the

amount

of

fuel (in

gallons)

consumed

per

hour.

g

is a unit

of

acceleration

equivalent

to

that

produced

by

the

force

of

gravity.

WEIGHT

AND

BALANCE

TERMINOLOGY

Reference

Datum

Station

Arm

Moment

Center

of

Gravity

(e.g.)

e.g.

Arm

Reference

Datum

is

an

imaginary

vertical

plane

from

which

a!I

horizontal

distances

are

measured

for

ba!ance

purposes.

Station

is a location

along

the

airrlane

longitudina I axis

given in

terms

of

the

distance

from

the

reference

datum.

Arm

is

the

horizontal

distance

from

the

reference

datum

to

the

center

of

gravity

(e.g.)

of

an

item.

Moment

is

the

product

of

the

weight

of

an

item

multiplied

by

its

arm. ! Moment

divided

by

the

constant

1000

is

used in

this

Handbook

to

simplify

balance

calculations

by

reducing

the

number

of

digits.)

Center

of

Gravity

is

the

point

at

which

an

airplane

would

ba!·

a

nee

if

suspended.

I ts

distance

from

the

reference

datum

is

found

by

dividing

the

total

moment

by

the

total

weight

of

the

<Jirplane. Center

of

Gravity

Arm

is

the

arm

obtained

by

adding

the

airplane's

individual

moment

and

dividing

the

sum

by

the

total

weight.

Issued:

September

30,

1976

1

11

SECTION 1 GENERAL

e.g.

limits

Standard Empty

Weight

Basic

Empty

Weight

Useful

Load

Gross

Weight

Maximum Takeoff Weight

Maxiinum Landing

Weight

Tare

GULFSTREAM

AMERICAN

MODEL

AA

58 Tl GER

~enter

~f

~ravi~

Limits

are

the

extreme

center

of

gravity

loca·

t1o~s

wuhm

which

the

airplane

can

be

operated

at a given

weight.

~tand~rd

Empty

Weight

is

the

weight

of a standard

airp:.ane,

mctud1ng

unusable

fuel,

full

operating

fluids

and

full

engine

oil.

Basic

Empty

Weight

is

the

standard

empty

weight

plus

the

weight

of

optional

equipment.

Useful

load

is

the

difference

between

maximum

gross

weight

and

the

basic

empty

weight.

Gross

Weight

Is

the

maximum

weight

to

which

the

airplane

is

certificated.

Maximun1

Takeoff

Weight

is

the

maximum

weight

approvec

for

the

start

of

the

takeoff

run.

Maxi

mu~

landing

Weight

is

the

maximum

weight

approved

for

the

landing

touchdown.

Ta~e

~s

the

w_eight

of

chocks,

blocks,

stands,

etc.,

used

when

~e1gh1ng

an

airplane,

and

ls

included

in

the

scale readings.

Tare

I~

deductec~

from

the

scale

reading

to

obtain

the

actual

(net)

airplane

weight.

Issued;

September

30,

1976

GULFSTREAM AMERICAN MODEL

Ak53

TIGER

TABLE OF CONTENTS

SECTION

2

LIMITATIONS

SECTION 2

LIMITATIONS

Page

Introduction

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

2-3

Airspeed Limitations

.........•...........................

,

......

2-4

Airspeed Indicator Markings

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

,

..... ~ .......

2-4

Power

Plant Limitations

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

2-5

Power Plant Instrument Markings

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

2-5

Weight Limits

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

2-6

Center

of

Gravity Limits

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

2-6

Maneuver Limits

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

,

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

2-7

Flight Load Factor Limits

...................••.............•.....

2-8

Fuel Limitations

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

,

.......... , .... , ..... , ......

2-8

Placards

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

2-9

Issued: September 30, 1976

2-1

/12·2 blank)

GULFSTREAM

AMERICAN

MODEL

AA·5B

TIGER

INTRODUCTION

SECTION 2

LIMITATIONS

This

section

presents

the

operating

limitations,

instrument

marki'1gs,

and

basic

placarding

necessary

for

the

safe

operation

of

the

airplane, its

ergine,

standard

systems

and

standard

equipment.

Where

the

significance

of

an

orerating

limita-

tion,

marking

or

placard

is

not

obvious,

an

explanation

is

presented.

Limitations

associated

with

Gulfstream

American

designed

optional

equipment

are

contained

I

in Section 9.

The

Gulfstream

American

Model

AA-58

is

certificated

'under

FAA

Type

Certi-

I

ficate No. A 16EA.

The

airplane

is

equipped

for

day

VFR

(with

standard

equipment)

and

may

be

equipped

for

night

VFR

and/or

IFR

operations.

FAR

Part

91

establishes

the

minimum

required

instrurnents

and

equipment

for

these

operations_

The

reference

to

types

of

flight

operations

on

the

operating

lin1itations

placarrl

reflects

equip-

inent

installed

at

the

time

the

Airvvorthiness

Certificate

was

issued.

THIS

AIRPLANE

IS

NOT

APPROVED

FOR

FLIGHT

IN ICING

CONDITIONS.

Revised:

February

15,

1979

23

SECTION 2

LIMITATIONS

GULFSTREAM

AMERICAN

MODEL

AA5B

TIGER

AIRSPEED

LIMITATIONS

Airspeed

limitations

and

their

operational

significance

are

shown

in

Figure

2-1.

KCAS

KIAS

SPEED (MPH

(MPH

REMARKS

CASI

IASI

VNE

Never

Exceed

Sreed

174 172

Do

not

exceed

this

speed

(2001 (1981

in

any

operation.

VNO

Maximum

Structural

Cruising

143 142

Do

not

exceed

this

speed

Speed

(1651 (1641

except

1n

smooth

air,

and

then

only

with

caution.

VA

Maneuvering

Sreed

113

112

Do

not

make

full

or

abrupt

(1301

1129)

control

movements

above

this

speed.

VFE

M<iximum

Flap

Extender!

Speed

104 103

Do

not

exceed

this

speed

I 120)

I

119)

with

flilps

extended.

Maximwn

Canopy

Open Speed

113

112

Do

not

exceed

tt1is speed

(130)

(129)

jwith

canopy

open.

Figure

2-1.

Airspeed

Limitations

AIRSPEED

INDICATOR

MARKINGS

Airspeed

indicator

markings

and

tt1eir

color

code

significance

are

shown

in

Figure

2·2.

KCAS

MARKING

(MPH CASI

SIGNIFICANCE

VALUE

OR RANGE

Wl1ite

Arc

53.104

Flap

Operating

Range.

Lower

limit

is

maximum

weigt1t

161·

120)

Vs

0

in

landing

configuration.

Upper

limit

is

maximum

speed

perrnissible

with

flaps

extendeci.

Grt:en

Arc

56-143

Normal

Operating

Ranqe.

Lower

limit

is

maximum

wei~Jhl

(65·

1651

Vs

with

flaps

retrac!ed.

Upper

limit

is

maximum

struc·

turnl

cruising

speed.

Yellow

Arc

143 174

Operations

must

be

conducted

with

caut'1on

and

only

'n

I 165·200)

smoo1~1

air.

Red

Linc

174

Maxirnurn

speed

for

any

operations.

(2001

Figure

2-2.

Airspeed

l~dicator

Markin~

24

lssu~d:

St~pternber

30,

1976

GULFSTREAM AEROSPACE MODEL

AA-58 TIGER

POWER PLANT LIMITATIONS

SECTION

2

LIMITATIONS

Engine

Manufacturer:

Avco Lycoming Engine Model 0-360-A4K

Engine

Operating

Limits

for Takeoff and

Continuous

Operations·

Maximum

Power:

180

BHP

Maximum

Engine Speed: 2700

RPM

Maximum

Oil Temperature: 245°F (118°C)

Oil Pressure

Minimum

(idling):

25

PSI

Maximum:

100

PSI

Normal

Range:

60

to

90

PS!

Fuel Pressure.

Minimum:

0.5

PSI,

Maximum: 8 PSI

Propeller

Manufacturer:

McCau1ey

Propeller

Model Number: 1A1701FFA 7563, 1A170/KFA 7563 or 1A 170E/KFA

7563

Propeller Diameter,

Maximum:

75

inches.

Propeller

Operating

Limits:

.

Avoid

continuous

opcrntion

between

1850

and

2250

nPM

while

descend·

ing.

POWER PLANT INSTRUMENT MARKINGS Power plant

instrument

markings and their color code significance

are

shown

in Figure 2-3.

RED LINE GREEN ARC

YELLOW

ARC

INSTRUMENT

MINIMUM NORMAL

CAUTION

LIMIT OPERATING

RANGE

Tachometer -

2200-

2700

RPM

1850-

2250

RPM

Oil Temperature

-

100°F-245°F

-

{J8°C-

t 18°C)

-

Fuel Pressure 0.5

PSI

0.5-8

PS!

-

Oil Pressure

25

PSI•

60-90

PSI

-

'Idling

..

Start

and

warm

up

Figure

2-3.

Power Plant

Instrument

Markings

Revised: May 12, 1983

(C,\

1983

Gull:,1ream

Aerospace

Corporalion

RED

LINE

MAXIMUM

LIMIT

2700

RPM

245°F {118°C)

B

PSI

~

00

PSI

..

SECTION 2

LIMITATIONS

WEIGHT

LIMITS

NORMAL

CATEGORY

Maximum

Takeoff

Weight: 2400 lbs.

Maximum

Landing Weight: 2400 lbs.

GULFSTREAM

AEROSPACE

MODEL

AA-58

TIGER

Weight in Baggage

Compartment,

Normal

Category:

120

pounds

maximum

c.llow-

able

if

C.G.

is

within

center

of

gravity

envelope

(Figure

6-5). Refer

to

Section

6

for

cargo

loading

instructions.

UTILITY

CATEGORY

Maximum

Takeoff

Weight: 2050 lbs.

Maximum

Landing Weight:

2050

lbs.

Maximum

Weight in Baggage

Compartment:

In

the

Utility

Category,

the

baggage

compartment

and

rear

seat

must

not

be

occupied.

CENTER OF

GRAVITY

LIMITS

NORMAL

CATEGORY

Center

of

Gravity

Range:

Forward:

81.0 inches

aft

of

datum

at

1920 lbs.

or

less,

with a straight

line

variation

to

89.0

inches

aft

of

datum

at

2400

lbs.

Aft:

92.5 inches

aft

of

reference

datum

at

all

weights

up

to

2400 lbs.

Reference

Datum:

50.0

is

inches.

It

is

located

at

the

front

face

of

lower

portion

of firewall.

UTILITY

CATEGORY

Center of Gravity

Rarige:

Forward:

81.0 inches ah

of

datum

at 1920 lbs.

or

less,

with

a straight line

variation

to

83.17 inches aft

of

datum

at

2050 lbs.

Ah:

85.32 inches

ah

reference

of

datum

at

all

weights

up

to

2050 lbs.

Reference

Datu1n:

is

50.0

inches. It

is

located

at

the

front

face

of

lower

ponion

of

firewall.

26

Issued:

September

30,

1976

GULFSTREAM

AMERICAN

MODEL

AA5B

TIGER

MANEUVER

LIMITS

NORMAL

CATEGORY

SECTION 2

LIMITATIONS

This

airplane

is

certificated

in

both

the

normal

and

utility

category.

The

normal

CATEGORY

This airplane

is

not

designed for aerobatic flight. However,

in

the acquisition

of

I

various certificates such

as

commercial pilot,

instrument

pilot

and

flight

instructor,

certain

maneuvers

are

required

by

the

FAA.

All

of

these

maneuvers,

except

spins,

are

permitted

in

this

airplane

when

011erated in

the

Utility

Category.

Maximum

Design

Weight

Design

Maneuvering

Speed

. 2050 lbs.

. 113

KCAS

1130

MPH)

In

the

Utility

Category,

the

baggage

compartment

and

rear

seat

must

not

be

occupied.

No

aerobatic

maneuvers

are

approved

except

those

listed

below:

Maneuver

Chandelles

Lazy

Eights

Steep

Turns

Stalls

(Except

Whip

Stalls)

Spins

Prohibited

Recommended

Entry

Speed*

.

113

KCAS 1130 MPH)

.

113

KCAS (130 MPH)

.

113

KCAS 1130 MPH)

Slow

Deceleration

..

Abrupt

use

of

the

controls

is

prohibited

above

113 KCAS {130 MPH}.

Revised:

July

15,1978

2 7

SECTION 2 LIMITATIONS

GULFSTREAM

AMER 1

CAN

MODEL AA-56

TIGER

The

important

thiny

to

remember

in flight

maneuvers

is

that

the

airplane

is

dean

in

aerodynamic

design

and

will

build

up

speed

quickly

with

the

nose

down.

Since

proper

speed

control

is

essential

for

execution

of

any

maneuver,

care

should

always

be

exercised

to

avoid

excessive

speed

and

its

resultant

heavy

airframe

loads. In

the

execution

of

all

maneuvers,

avoid

abrupt

use

of

controls.

As

noted,

SPINS

:4-RE

PROHIBITED.

In

case

of

an

inadvertent

spin,

recovery

is

effect~

by

reduc1n~

thrott!e

to

idle,

neutralizing

the

aileron,

applying

full

rudder

o~pos1te

to

the

.sp1~

rotation,

and

applying

full

down

elevator

simultaneously

with.

rudder

application.

The

controls

should

be

applied

briskly

and

held

until

rotation

stops.

As

the

rotation

stops,

neutralize

the

anti-spin

rudder,

then

apply

smooth elevator

back

pressure

to

bring

the

nose

up

to

the

level

flight.

FLIGHT

LOAD

FACTOR

LIMITS

NORMAL

CATEGORY

Flight

Load

Factors

(Gross

Weight

- 2400 lbs.)

Flaps Up

..

Flaps

Down

UTILITY

CATEGORY

Flight

Load

Factors

(Gross

Weight

- 2050 lbs.)

Flaps Up

..

Flaps

Down

FUEL

LIMITATIONS

+3.Bg,

-1.52g

.....

+3.5g

+4.4g,

-1.

76g

.....

+3.5g

2 Tanks: 26.3 U.S. gallons

each.

121.9 Imperial gallons) (99.5 Liters)

Total

Fuel: 52.6 U.S. gallons 143.8 Imperial gallons) (199.1 Liters)

28

Us.able

Fuel

(all

flight

conditions):

51

U.S.

gallons

(42.5 Imperial galiions)

(193 Liters)

Issued:

September

30,

1976

GULFSTREAM AMERICAN

MODEL

AA

5B

TIGER

PLACARDS

SECTION

2

LIMITATIONS

The

following

information

is

displayed in the

form

of

composite or individual

placards:

( 1) In

full

view

of

the

pilot;

THIS

AIRPLANE

Ml'ST

BE

OPERATED

AS A NORMAL

OR

UTILITY

CATEGORY

AIRPLANE

IN

COMPLIANCE

WITH

THE

OPERATING

LIMITATIONS

STATED

IN

THE

FORM

OF

PLACARDS,

MARKINGS

AND

MANUALS.

NORMAL

CATEGORY-

MAXIMUM

DESIGN

WEIGHT ------ - ----

---

- -

__

2400

LBS

DESIGN

MANEUVERING

SPEED

VA-

- -

----

- - ---l

13

KNOTS

CAS

FLIGHT

LOAD

FACTORS:

FLAPS

UP

_____

+l.6,-1.52

F"LAPS

DOWN_

- - _ --____

+J.5

NO

ACROBATIC

MANEUVERS,

INCLUDING

SPINS,

APPROVED,

UTILITY

CATEGORY-

MAXIMUM

DESIGN

WEIGHT

- - - - - - - - -

----

- - - -

_2oso

LBS

DESIGN

MANEUVERING

SPEED

VA

___

_ --____

ClJ

KNOTS

CAS

FLIGHT

LOAD

FACTORS,

FLAPS

UP

______

+4.4,

-1.76

FLAPS

OOWN

- -

_________

+3.5

REAR

SEAT

MUST

NOT

0E

OCCUPIED

ACROBATIC

MANEUVERING

LIMITED

TO

THE

FOLLOWING1

MANEUVER

ENTRY

SPEED.CAS

CHANDfLLES

_______

-----

--------

____

ti3

KNOfS

LAZY

EIGHTS-----

- -

___

---

- -

------___

l13KNOTS

STEEP

TURNS

___ ----__

------

- -

______

113

KNOTS

STALLS

(EXCEPT

WHIP

STALLS)

_______

,.SLOW

DECELERATION

SPINS

PROHIBITED

MAXIMUM

ALTITUDE

LOSS

IN

STALL

___

- - _

____

350

FEE

DEMONSTRATED

CROSSWIND

VELOCITY

__ -_______

16

KNOr

THIS

AIRPLANE

NOT

APPROVED

FOR

FLIGHT

IN

ICING

CONDITIONS.

THIS

AIRPLANE

IS

CERTIFIED

FOR

THE

FOLLOW!l'<G

OPERATIONS1

IFR

VFR

DAY

N!GHT

WHEN

PROPERLY

EQUIPPED

PER

FAR

91

REFER

TO

WEIGHT

ANO

BALANCE

DATA

FOR

LOADING

INSTRUC-

TlONS.

READ

FUEL

GAGES

IN

LEVEL

FLIGHT

ONLY.

FOR

NORMAL

OPERATION -MAINTAIN

FUEL

0ALANCE',

5603007-96

AA-Sf

(2) On

control

gust lock:

CONTROL LOCK

REMOVE BEFORE

STARTING

ENGINE

Revised:

December

15,

1977

I

SECTION 2

LIMITATIONS

(3)

On

fuel

selector

valve:

LEFT FUEL

25.5

U.S.

GAL.

0

RIGHT FUEL

25.5

U.S.

GAL

Q

FUEL SELECTOR

(4) Left side

of

instrument

panel:

(5)

Aft

of

fuel

tank

caps:

I

FUEL

MIN

100/130

OCT.

26.3

U.S.

GAL

TOTAL

CAP.

19.0

U.S.

GAL

TO

TAB

GULFSTREAM AMERICAN

MODEL AA-5B

TIGER

(6)

On

instrument

panel

(if

strobe

lights are

installed):

~RNQFF

STROBE IN CLOUD.

FOG

~-Hi',ZE

TAXI WITH STROBE

OFF

-----

-·------~--···

-·

-~--

Revised: December

15,

197

7

GULFSTREAM AMERICAN MODEL AA·5B TIGER

(7)

On

instrument

panel:

[

/\UT

ION F LASHINc;

BEA

co-~

IN

CLOUDS

MAY

CAUSE

VISUAL

DISORIENTATION

-

----

- ---

---------·---·-

---

(8)

Adjacent

to

canopy

latch:

(9) In baggage

compartment:

120

POUNDS

MAXIMUM

BAGGAGE

FOR

/\DDITIONAI_

LOADING

INSTnUCTIONS

SEE

WE!Gf!T

ANO

BALANCE DATA

NO

HEAVY

0!3JfCTS

ON

HAT

SHELF

Under

rear

seat

liase:

NO

STEP

BFFORF

FLIGHT

SEAT flACK MUST

flE

TURNED

f10WN

TO

COVER

THIS AREA

(10) Inside canopy

tail,

Ir.It side:

On

rear

seat

base:

SECTION 2

Lll\f

ITATIDNS

NO

PASSENGERS

340

POUNDS

MAXIMUM

CARGO

DISTRIBUTE

EVENLY

FOR

ADDITIONAL LOAOING

INSTRUCTIONS

SEE

WEIGHT

ANO

BALANCE

DATA

ANO

PILOTS

QPEAAllNG

HANDBOOK

111

KNOTS

MAX

WITH

CANOf'Y

OP[N

TO

HCRE

- .

..

. .

·----·:]

[ t

NO

rllrJllT

WITH

CANOPY

OPEN

Rf

YONO

THIS

POIN_T

{11)

l11terior

of

1:;i11opy

adjacent

to

lock.

-

PU'.;H

TO

UNLOCK

Revised: DP.CP.mlier

15,

1977

2

11

I

SECTION 2 LIMITATIONS

(12) On wing

outer

ribs

(1f

strobe lights

are

1nstallcdl:

WARNING

-HIGH--

VOLTAGE

WAIT

ti

MINUTES

AFTER

SHUTTING

OFF

BEFORE

STARTING

ANY

WORK

ON

THIS

UNIT

-CAUTION-

rH1s

UNIT

PULARI

l y

SENSITIVE

WHITE

OR

RED

l

~AD

POSITIVE

BLACK

LEAD

AND

OR

CASE

NEGATIVE

(13)

Adjacent

to

auxiliary

power plug

(if

installed):

CAUTION-

12

VOLT

DC

ONLY.MASTEH

SW

MUST

BE

OFF

{14)

On

instrument

panel:

AVOID

CONTINUOlJ~

Of'EHAl

ION

l:IETWEEN

18;,0

&

2250

HPM

WHll

(

Ut:SCCNUING

{ 15) On

bau~Jage

door.

TO

OPEN

DOOR FROM INSIDC,

SLIDE

HANDLE

fORWARD•

( J 6)

On

glove

liux

door:

TIRE

1-'RESSURf

NOSE 25 L8S MAIN

35

LBS

2

12

GULFSTREAM

AMERICAN

MODEL

Ak5B

TIGER

Revised:

December

15,

1977

GULFSTREAM

AMERICAN

MODEL

Ak5B

TIGER

SECTION 3

EMERGENCY

PROCEDURES

SECTION 3

EMERGENCY

PROCEDURES

TABLE

OF

CONTENTS

Page

Introduction

........

. . .

..

. . . . . . . .

.. ..

. . .

..

. . . .

.....

33

Airspeeds

For

Safe

OpenHions

(IAS)

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

.........

3.3

OPERATIONAL

CHECKLISTS

Engine Failures . .

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

3-3

Engine Failure During Takeoff Run

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

3-3

Engine

Failure Immediately

After

Takeoff

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

3-3

Engine

Failure

During

Flight

. ,

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

3-4

Forced Landings. . . . .

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

3-4

Emergency Landing

Without

Engine Power

............ , ...........

3-4

Precautionary

Landing

With Engine

Power

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

,

........

3-4

Ditching

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

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

3-5

Fires . . . . . . . . . . . . . . . . . . . . .

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

,

...........

3-5

During

Start

On

Ground

. . . . .

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

3-5

Engine Fire

In

Flight

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

...

3-6

Electrical Fire

In

Flight . . . .

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

3-6

Cabin Fire . . . . . . . . . . 3·6

Wing Fire

.........

.

Icing

......

.

Inadvertent

Icing

Encounter

........

.

Landing

With a Flat Main Tire

..

Landing With a

Flat

Nosewheel Tire

..........

.

Electrical

Power

Supply

System

Malfunctions

Ammeter

Shows

Discharge . .

......

.

:ssued: September 30, 1976

.

3-7

. . 3 7

.

..

3-7

. . 3·8

..

......

3-8

..

3-8

.......

38

3 1

SECTION

3

GULFSTREAM

AMERICAN

MODELAA5B

TIGER

EMERGENCY

PROCEDURES

TABLE

OF

CONTENTS

(Continued)

Page

AMPLIFIED

PROCEDURES

Engine Failures

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

3-9

Forced

Landings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

...

3-10

Ground

Fires

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

3-10

In-Flight Engine Fires

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

3-11

In-Flight Electrical Fires

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

,

........

3-11

Emergency

Operation

in

Clouds

...... , ...............

,

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

3-12

Vacuum

System

Failure

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

3·

12

Executing

a 1

BD°

Turn

in

Clouds

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

,

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

3-12

Emergency

Descent

Through

Clouds

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

3-13

Recovery

From a Spiral

Dive

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

3-13

Flight In Icing

Conditions

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

3-14

Static

Source

Blocked

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

3-15

Spins

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

3-16

Rough

Engine

Operation

Or

Loss

Of

Power

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

3-16

Carburetor

Icing..................................

.

....

3-16

Spark

Plug

Fouling

. . . . . .

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

3-16

Magneto

Malfunction

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

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

3-17

Low Oil

Pressure/Engine

Overheat

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

3-17

Electrical

Power

Supply

System

Malfunctions

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

,

........

3-17

Overvoltage

Protection

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

,

......

3-18

Insufficient

Output

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

3-18

Brake

Failure

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

3-18

Windshield

Obscuration

...... , ......................

,

........ , ..

3-19

3-2

Issued: September 30,

1976

GULFSTREAM

AMERICAN

MODEL

AA~5B

TIGER

INTRODUCTION

SECTION 3

EMERGENCY PROCEDURES

This

section

provides

the

pilot

with

checklists

and

amplified

procedures

that

enable

him

to

cope

with

emergencies

that

may

be

encountered

in

operating

the

airplane. If

proper

preflight

inspections,

operating

procedures,

and

maintenance

practices

are

used,

emergencies

rlue

to

airplane

or

engine

malfunction

should

be

rare. Likewise,

careful

flight

planning

and

good

pilot

judgement

can

minimize

enroute

weather

emergencies.

However,

should

any

er;nergency

develop,

the

guidelines

in

this

section

should

be

considered

and

applied

as

necessary

to

correct

the

problen1.

AIRSPEEDS FOR SAFE

OPERATIONS

(IAS)

Engine Foi!ure

After

Takeoff

....... , .....

, . ,

... , ..

65 Kl AS (75 MPH)

Maneuvering

Speed

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

,,

.....

, .112

KIAS

(129

MPH)

Maximum

Glide

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

72

KIAS

183

MPH)

Precautionary

Landing With Engine Power

..........

, .65

KIAS

(75

MPH)

Landing

Without

Engine Power

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

65

KIAS

(75

MPH)

OPERATIONAL

CHECKLISTS

ENGINE

FAILURES

Engine Failure During Takeoff Run

Ill

Throttle -IDLE.

12)

Brakes - APPLY.

13)

Mixture -IDLE

CUT~OFF.

(4)

Ignition

Switch - OFF.

151

Master - OFF.

Engine Failure Immediately After Takeoff

11)

Aicspeed - 65

to

75 KIAS

175

to

86 MPH)

121

Mixture -IDLE

CUT~OFF.

{3) Fuel Selector Valve - OFF.

(4)

Ignition

Switch - OFF.

(5) Master Switch - OFF.

Issued: September 30, 1976

SECTION 3

GULFSTREAM

AME

RICAN

MODEL

AA·SB

TIGER

EMERGENCY

PROCEDURES

Engine Failure During Flight

Ill

Arr>peed - 72

KIAS

183

MPH).

(2)

Carburetor Heat - ON.

13)

Fuel Selector Valve

-SWITCH

TANKS.

141

Mixture

- RICH.

(5) Master Switch -

ON

(6)

Auxiliary Fuel Pump -

ON

(7)

Throttle

- OPEN

1/4

inch

(8)

Ignition Switch -

BOTH

191

Primer - IN and LOCKED.

(10) Starter - PRESS

if

propeller

is

stopped.

NOTE

Gliding distance

is

approximately 1.7

nautical miles {2 statute miles) for each

1000 feet of altitude above terrain.

FORCED

LANDINGS

Emergency

landing

Without Engine Power

Ill

Airspeed - 72

KIAS

183

MPH)

(2) Radio - TRANSMIT MAYDAY on 121.5 MHz giving location and

intentions.

131

Mixture -ID

LE

CUTOFF.

(4) Fuel Selector Valve - OFF.

(5) Ignition Switch - OFF

(6) Wing Flaps - AS REOUI RED. (7) Master

Switch -

OFF.

(8) Canopy -

UNLATCH

PRIOR TO TOUCHDOWN

19)

Touchdown -

SLIGHTLY

NOSE

HIGH.

(10)

Brakes-

AS

REQUIRED

Precautionary

landing

With Engine Power

3-4

Ill

Air>peed - 65

KIAS

175

MPH)

(2) Radio - Advise

ATC

of intentions.

131

Wing

Flaps-

AS

REQUIRED

(4) Select Fields - FLY OVER, noting terrain and obstructions,

then

re-

tract flaps upon reactiing a safe altitude and airspeed.

(5)

Radio and Electrical Switches - OFF

(6)

Wing

Flaµs --·ON

{on

final

approach).

Issued: September

30,

1976

GULFSTREAM

AMERICAN

MODEL

AA-58

TIGER

SECTION

3

EMERGENCY

PROCEDURES

17)

Aicspeed - 65

KIAS

175

MPH)

(8) Master

Switch -OFF.

191

Canopy -

UNLATCH

PRIOR TO

TOUCHDOWN.

110)

Touchdown -SLIGHTLY

NOSE

HIGH.

(11)

Ignition

Switch

- OFF

(12) Brakes - AS

REQUIRED.

Ditching

111

Radio -

TRANSMIT

MAYDAY

ON 121.5 MHz, giving

location

and I

intentions

(lf

electrical power

is

available).

121

Heavy Objects - SECURE

131

Flaps -

ON

(4) Approach - High Winds, Heavy

Seas --INTO

THE WIND.

Light Winds, Heavy Swells -

PARALLEL

TO

SWELLS.

151

Power -

ESTABLISH

350

FT/MIN

DESCENT

at

65 KIA.S

175

MPH)

161

Canopy -

FULLY

OPEN

171

Touchdown

- NOSE

HIGH

ATTITUDE

AT

MINIMUM

DESCENT

RATE

AND

AIRSPEED

(8)

Face

- CUSHION at

touchdown

with

folded coat or

seat

cushion

(9) Airplane -

EVACUATE

through canopy

I 10) Life Vests and Raft -

INF

LATE

FIRES

During

Start

On

Ground

(

1)

Cranking -

CONTINUE

to

get a start which wou!d suck

the

flames and

accumulated

fuel

through

the

carburetor

and

into

the

engine.

If

engine starts:

(2) Power - 1800

RPM

for a few minutes.

(3) Engine -

SHUTDOWN and inspect

for

damage.

a.

Fuel Selector - OFF

b. Master

Switch -OFF.

c.

Ignition Switch - OFF.

!f

engine fails

to

start:

(4)

Evacuate passengers.

(5)

Engine -

SECURE.

a.

Mixture - IDLE

CUTOFF.

Revised:

July

15, 1978

3.5

SECTION

3

GULFSTREAM

AMERICAN

MODEL

AA-58

Tl

GER

EMERGENCY

PROCEDURES

b.

Master

Switch

- 0

FF.

c. Ignition

Switch -OFF.

d. Fuel

Selector

Valve -

OFF.

(6) Fire -

EXTINGUISH

using fire

extinguisher,

seat

cushion,

wool

blanket,

or

dirt.

Engine Fire in Flight

(1)

Mixture -IDLE

CUTOFF

(2) Fuel

Selector

Valve -

OFF

131

Master Switch -

OFF

(4)

Cabin

Heat

and

Air -OFF

(5) Airspeed -

115

KIAS

1132 MPH)

If

fire

is

not

extinguished, increase

glide

speed

to

attempt

to

blow

the

tire

out.

(6)

Forced

Landing -EXECUTE

{as

described

in Landing

Without

Engine

Power).

Electrical

Fire

in

Flight

If fire

is

in

engine

compartment:

(1) Master

Switch-

OFF.

121

Venrs/Cabin

Air/Heat -OFF/CLOSED

(3)

Land

airplane

as

soon

as possible

If

fire

is

in

cockpit:

( 1)

Master

Switch -OFF

(2) All

Other

Switches

(except

ignition

switch) -OFF

(3)

Vents/Cabin

Air/Heat -CLOSED

(4) Fire Extinguisher -

ACTIVATE

(if

available!

If

fire

appears

to

be

out

and

electrical

power

is

necessary

to

continue

flight:

(

5)

Master

Switch

- ON

(6)

Circuit

Breakers - CHECK

for

faulty

circuit,

do

not

reset.

(7)

Radio/Electrical

Switches

- ON

one

at

a

time,

with

delay

after

each

until

short

circuit

is

located.

(8)

Vents/Cabin

Air/Heat

- OPEN

when

fire

is

out.

Cabin Fire

(1) Master

Switch -OFF

(2)

Vents/Cabin

Air/Heat

- CLOSED

3-0

Issued:

September

30,

1976

GULFSTREAM AMERICAN MODEL AA·5B TIGER

SECTION

3

EMERGENCY PROCEDURES

{3)

Fire Extinguisher - ACTIVATE

(if

available)

WARNING

AFTER

DISCHARGING

AN EXTINGUISHER WITHIN A CLOSED CABIN, VENT!

LATE THE CABIN.

(4) Land

the

airplane

as

soon as possible

to

inspect for damage.

Wing

Fire

ICING

(1)

Navigation Light Switch - OFF

(2) Pitot

Heat

Switch

(if

installed) - OFF

(3) Land

as

soon

as

possible.

Inadvertent

Icing

Encounter

(1)

Pitot

Heat

Switch -ON

(if

installed)

(2)

Carburetor Heat -

ON

as

required

NOTE

Continuous

engine

operation

with

car-

buretor

heat on

is

not

recommended

due

to

the

decrease

in

engine efficien-

cy.

If

severe icing

conditions

require

extended

use

of

carburetOr

heat

the

engine

mixture

should

be

leaned during

use

of

carburetor

heat.

(3)

Cabin

Heat - ON

(4) Defrosters - OPEN

(5)

Engine - Increase

RPM,

(do

not

exceed red

line)

and periodically

change

RPM

to

minimize ice

buildup

on

propelle1 blades.

(6)

Turn

back

or

change

altitude

to

obtain

outside

air

conditions

that

are

less likely

to

cause icing.

(7)

If icing

continues

p!an a

landing

at

the

nearest

airport.

Under

extremely

rapid icing

conditions

select a

suitable

ernergency landing

s;te.

Issued:

September

30,

1976

SECTION 3

GULFSTREAM

AMERICAN

MODEL AA·5B

TIGER

EMERGENCY PROCEDURES

WARNING

WITH AN

ICE

ACCUMULATION

ON

OR

NEAR

THE

WING

LEADING

EDGES

A HIGHER STALLING

SPEED

MAY

BE

EXPECTED. PLAN

ALL

MANEUVERS ACCORDINGLY.

(Bl

Airspeed - If possible increase airspeed

and

fly

at a higher

than

normal

cruise

speed

until a landing

is

begun.

(9)

Approach

for

landing

at a higher

airspeed·

than

normal

depending

on

amount

of

ice

accumulation.

(10) Flaps -

UP

(Do

not

attempt

to

extend

flaps for landing)

(11)

Land

in a slightly

nose

high

attitude.

LANDING

WITH A

FLAT

MAIN

TIRE

( 1)

Wing

Flaps -AS

DESI

RED

(2) Elevator Control -

NOSE

HIGH

(3) Aileron Control - BANK TOWARD GOOD

Tl

RE.

(4)

Touchdown

- GOOD

TIRE

FIRST,

hold

airplane

off

flat tire as

long

as

possible.

LANDING

WITH A

FLAT

NOSEWHEEL TIRE

(1)

Wing

Flaps -AS

DESIRED

(2) Elevator Control -

NOSE

HIGH

(3)

Touchdown

- hold

nose

gear

off

runway

as long as possible.

(4) Brakes - Use

brakes

cautiously.

Allow

airplane

to

roll to a

stop

if

possible.

ELECTRICAL

POWER

SUPPLY SYSTEM MALFUNCTIONS

Ammeter

Shows

Discharge

38

( 1)

Alternator

Circuit

Breaker

- Check

NOTE

If

circuit

breaker

trips,

wait

15

seconds

before

resetting

it.

Issued:

September

30,

1976

GULFSTREAM

AMERICAN

MOOEL

AA~5B

TIGER

(2) Field

Circuit

Breaker - Check

SECTION 3

EMERGENCY PROCEDURES

(3)

If

Field

Circuit

Breaker

is

tripped,

land

as

soon

as

practical.

(4) If

Field

Circuit

Breaker

is

not

tripped,

and

ammeter

continues

to

show

discharge,

set

alternator

side

of

master

switch

to

OFF

ard

land

as

soon

as practical.

AMPLIFIED

PROCEDURES

ENGINE

FAILURES

If

the engine fails during the takeoff run,

prior

to

liftoff,

the airpilane should

be

stopped

as

soon

as possible. In cases

of

partial failure (resulting in loss

of

power)

the

pilot

may

have

the

option

of

continuing

the

takeoff

or

aborting

it.

Obviously

this

is a decision

that

must

be

made

by

the

pilot

in light

of

existi:ng

conditions,

however,

an

aborted

takeoff

{if

possible)

in

most

cases

is

the

safest

approach.

This

checklist

provides

items

that

may

assist

the

pilot

in

increasin~

the

safety

of

the

airplane

during

such

situations.

If

the

engine

fails

(either

completely

or

partially)

it

is

essential

that

the

nose

of

the

airplane

be

lowered

promptly

so

that

a safe airspeed can be

maintained.

At

low

altitudes,

in

most

cases,

the

aiq1!ane

should

be

flown

straight

ahead

for a

landing,

with

only

small

directional

changes

to

avoid

obstructions

or

people

on

the

ground.

Seldom

are

there

either

the

altitude

or

airspeed

available

for

a 180"

gliding

turn

back

to

the

runway.

These

checklists

are based

upon

the

assumption

that

the

pilot

will have

adequate

time

to

secure

the

fuel

and

ignition

systems

prior

to

touchdown,

however,

the

pilot

must

keep

in

mind

that

his

primary

duty

is

control

of

the

airplane.

If

the

engine

fails in flight

(complete

loss

of

power)

the

best glide

speed,

as shown

in

Figure

3-1

should

be

established

as

quickly

as possible. Once

the

proper

gliding

speed

has

been

established

and

a glide

toward a suitable

landing

site

entered,

an

effort

should

be

made

to

determine

the

cause

of

the

engine fai! ure.

If

there

is

sufficient

time

an engine

restart

should

be

attempted

per

the

check[ist.

Either

lack

of

time

for a

restart

or

failure

of

the

engine

to

start

will

necessitate

a forced

landing.

Obviously a thorough

knowledge

of

the

airplane

and

the

appropriate

checklists

may

give

the

pilot

that

slight margin

of

time

necessary

to

make

a restart

rather

than a forced

!anding.

Issued:

September

30,

1976

39

SECTION 3

EMERGENCY PROCEDURES

MAXIMUM

GLIDF

GULFSTREAM

AMERICAN

MODEL AA-58

TIGER

SPEED

J2

KNOfS

!83 MPHI !AS

PROPELLER

WINOMILUNG

FLAPS

UP

ZERO WINO

OL..~~~-'--'-~~---'--~-'-~~'-~-'-~~~~

NAUT. MILES 0

STAT. MILES 0

FORCED

LANDINGS

10

GROUND

DIST

ANGE

Figure

3.1

Maximum

Glide

16

10

20

lJ

If

the

engine

cannot

be

restarted

and a forced

landing

is

imminent,

select

a

suitable

landing

zone

and

prepare

for a landing

as

discussed in

the

EMERGENCY

LANDING

WITHOUT

ENGINE

POWER

checklist.

If

engine

power

is

available

and

a landing

is

to

be

attempted

at

an area

other

than

an

airport,

the

landing area

should

be

obseived

from

a safe

but

!ow

altitude.

Inspect

the

terrain

for

obstructions

and

surface

conditions

prior

to

attempting

a

landing.

Perform

the

landing

as discussed in

the

PRECAUTIONARY

LANDING

WITH

ENGINE

POWER

checklist.

1f

ditching

is

to

be

atte~pted

heavy

objects

in

the

baggage area

should

be

secured.

Folded

coats

or

cushions

should

be available for

occupants

to

use for face

protec-

tion

at

touchdown.

If

there

i5

5ufficienl

ti111e,

transmit

a Mayday message

on

121.5

MHz giving

location

and

intentions.

Perform

the

ditching

as

discussed in

the

DITCHING

checklist.

GROUND

FIRES

Ground

fires

may

be

caused

by

over-priming

the

engine,

therefore,

proper

pro-

cedures

will help

prevent

fires

when

starting

the

engine.

Issued:

September

30,

1976

3

10

SECTION:

GULFSTREAM

AMERICAN

MOOELAA5BTIGER

EMERGENCY

PROCEDURE~

Should a ground

fire occur, the

following

procedures

are

suggested:

(

1)

Keep the engine running

to

ingest the flames into

carbur~tor.

Increase

engine

RPM

to

1800 RPM.

(2) Dispatch ground personnel

for

fire

equipment.

(3)

When

assistance

arrives,

turn

fue!

selector

valve

OFF.

Let

engine

stop

due

to

fuel starvation. Set Master

Switch

and lqnition Sv,ritch

to

OFF.

(4)

If

no

assistance

is

available

or

the fire

is

beyond

control,

turn

the fuel

selector

OFF,

mixture

OFF,

Mastet Switch OFF,

lgnitior"I

Switch OFF.

ABANDON

AIRCRAFT.

IN·FLIGHT

ENGINE

FIRES

In-flight

engine fires in today's modern

aircraft

are extremely rare.

It

should be

noted

that

the

presence

of

smoke

does

not

always

mean

that a flaming

fire exists.

For

example,

it

may

be

engine

oil

on

the

exhaust

system. If, in

the

pilot's

judgement,

an

engine

fire exists,

the

following

procedures

are

suggested:

111

Mixture -

IDLE

CUTOFF

(2)

Fuel

Selector

Valve -

OFF

(3) Master

Switch -OFF

(4)

Cabin

Heat

and

Air -OFF

(5)

Establish a maximum

safe

rate

of

descent.

Increasing

speed

may

blow

the

fire

out.

(6)

Slide

slip

maneuvers

may

be

used,

as

necessary,

to

direct

flames

away

from

cabin

area.

(7)

Select a suitable

field

for a forced

landing.

IBI

Notify

ATC

if possible.

(9)

Complete

the

forced

!anding. Do

not

attempt

to

restart

the

engine.

IN-FLIGHT

ELECTRICAL

FIRES

Indication

of

in·flight

electrical fires

may

be

wisps

of

smoke

or

the

smell

of

hot

or

burning

insulation.

Should

an

electrical

fire

develop,

the

fol(owing

procedures

are

suggested:

If

fire

is

in

engine

compartment:

(1) Master

Switch -OFF.

121

Vent/Cabin Air/Heat - OFF/CLOSED

(3)

Land

airplane

as

soon

as

possible

Revised:

July

15, 1978

3·

11

SECTION 3

GULFSTREAM

AMERICAN

MODEL

AA·5B

TIGER

EMERGENCY PROCEDURES

If

fire

is

in

cockpit:

(1) Master Switch - OFF

(2) All

Other

Switches

(except

ignition

switch) -OFF

(3) Vents/Cabin

Air/Heat

- CLOSED

(4) Fire Extinguisher -

ACTIVATE

(if

available)

If

fire

appears

to

be

out

and

electrical

power

is

necessary

to

continue

flight:

{!J)

Master

Switch

- ON

(6)

Circuit

Breakers -CHECK

for

faulty

circuit,

do

not

reset.

(7)

Radio/Electrical

Switches

- ON

one

at a time,

with

delay

after

each

until

short

circuit

is

located.

(8)

Vents/Cabin

Air/Heat -OPEN

when

fire is

out.

EMERGENCY

OPERATION

IN

CLOUDS

Vacuum

System

Failure

A

vacuum

system

failure

may

disable

the

directional

and

attitude

indicators,

thus

forcing

the

pilot

to

rely

on

the

turn

coordinator

or

turn

and

bank

indicator

if

he

inadvertently

flies

into

clouds.

The

following

procedures

assume

that

only

the

electrically"powered

turn

coordinator

or

turn

and

bank

indicator

is

operative,

and

the

pilot

is

not

instrument

rated.

Executing a 180"

Turn

in

Clouds

Upon

inadvertently

entering

the

clouds,

an

immediate

plan

should

be

made

to

turn

back

as follows:

3·

12

( 1)

Note

the

time

of

the

minute

hand

and

observe

the

position

of

the

sweep

second

hand

on

the

clock.

Note

compass

heading.

{2) When

the

sweep

second

hand

indicates

the

nearest

half-minute, initiat.e

a

standard

rate

left

turn,

holding

the

turn

coordinator

symbolic

airplane

wing

opposite

the

lower

left

index

mark

for

60

seconds.

Then roll

back

to

level

flight

by

leveling

the

miniature

airplane.

(3)

Check

accuracy

of

the

turn

by

observing

the

compass

heading

which

:;houlU

Le

reciprocal

of

the

original

heading.

(4) If

necessary,

adjust

heading

primarily

with

skidding

motions

rather

than

rolling

motions

so

that

the

compass

will

read

more

accurately.

(5)

Maintain

altitude

and

airspeed

by

cautious

application

of

elevator

con-

trol.

Avoid

overcontrolling

by

using a

very

small

pitch

control

changes.

Issued: September 30, 1976

GULFSTREAM

AMERICAN

MODEL

AA~5B

TIGER

SECTION

3

EMERGENCY PROCEDURES

Emergency

Descent

Through

Clouds

If

VFR

flight

conditions

cannot

be

re-established by performing a

180°

turn,

a

descent

through

the

cloud

deck

to VFR

conditions

may be

appropriate.

If

possible,

obtnin

radio clearance for an

emergency

descent

through

clouds.

To

guard

against a spiral dive,

choose

an easterly

or

Westerly heading

to

minimize

compass

card

swings

due

to

changing

bank

angles.

In

addition,

use a

minimum

control

wheel

movement

and steer a

straight

course

with

rudder

control

by

monitoring

the

turn

coordinator.

Occasionally

check

the

compass

heading

and

make

minor

corrections

to

hold an

approximate

course. Before

descent

into

the

I

clouds,

set

ur

a stabilized let-down

condition

as follows:

(

1)

Apply

full

carburetor

heat.

(2)

Reduce

power

to

set up a

500

to

600

ft./min.

rate of

descent.

(3)

Adjust

the

elevator

trim

control

wheel for a stabilized

descent

at

75

KIAS

186

MPH).

(4) Use

minimum

control

wheel

motion

and avoid

abrupt

movement.

(5)

Monitor

turn

coordinator

and

make

corrections

by

rudder

alone.

(6)

Check

trend

of

compass

card

movement

and make

cautious

corrections

with

rudder

to

stop

turn.

(7)

Upon

breaking

out

of

clouds,

resume

normal

cruising flight.

·Recovery Fro1n

a Spiral Dive

If a spiral

is

encountered,

proceed

as follows:

(1) Close throttle.

(2)

Stop

the

turn

by using

coordinated

aileron and rudder

control

to

align

the

symbolic

airplane

in

the

turn

coordinator

with

the

horizon

reference line.

(3)

Cautiously

apply

elevator

back

pressure

to

slowly reduce

the

indicated

airsreed

to

75 KIAS (86 MPH).

(4)

Adjust

the

elevator

trim

control

to

maintain a 75

KIAS (86 MPH) glide.

(5) Use

minimum

control

wheel

movement,

using

rudder

control

to

hold

a

straight

heading.

(6)

Apply

carburetor

heat.

(7) Clear engine occasionally,

but

avoid using enough power

to

disturb

the

trimmed

glide.

(BJ

Upon

breaking

out

of

clouds, resume normal cruising flight.

Revised: July 15,1978

3-13

SECTION 3

GULFSTREAM

AMERICAN

MODEL AA·5B

TIGER

EMERGENCY PROCEDURES

FLIGHT

IN

ICING

CONDITIONS

Carburetor

~ce

~ay

be

encountered

at

any time. Normally,

the

first indicatio;i

of

carburetor

ice

Jn

the

AA-58

is

a slight

drop

in

engine RPM which

be

. d b

1·

. '

may

accompan1e Y s 1ght engine roughness. If

carburetor

icing

is

suspected,

the

following

procedures

are suggested:

( 1)

Appl~

full

~arburetor

heat. Engine

roughness

may

then

occur

due

to

an

over-nch

mixture

or

water

from

the

melting

ice.

NOTE

Continuous

engine

operation

with

carburetor

heat

on

is

not

recommended

du~

~o

the

resultant

decrease

in

engine

etf1c1ency. If severe icing

conditions

re-

quire

extended

use

of

carburetor

heat

the

engine

mixture

should

be

leaned

during

use

of

carburetor

heat.

Flying

i~

k~o.wn

icing

conditions

is

prohibited

by FAA regulations. However,

should

wmg

1c1ng

occur

the

following

procedures

are suggested:

3-14

( 1)

Turn

pltot

heat

ON

(2)

Turn

cabin

heat

ON.

(3)

Open

windshield

defroster

vent.

(4)

If

IFR

o~

~nder

control

of

an

in-flight

ground

facility,

notify

them

of

the

cond.1t1on

and

request

assistance. A

change

of

altitude,

if

possible,

o~

reversin~

cou.rs:

to

fly

out

of

the icing

conditions

may be desirable.

(5)

Pilot

technique

1s

important

in this

situation:

A. Increase

and

decrease

engine

RPM

(do

not

exceed

red line)

to

keep

propeller

clear

of

ice.

B.

Increase ai.rspeed if possible. This

technique

reduces angle of at-

tack

exposing

less

surface

area for ice

accumulation.

C.

Do.

not

exte~d

flaps. A clean

configuration

will

expose

less

surface

_to

ice

a~d

will

prevent

a change in air flow over

the

tail surfaces.

(6)

Monitor

engine

RPM

for

any

indication

of

carburetor

ice.

(Refer

to

Carburetor

Ice Procedures.)

(7) Plan a landing

at

the

first suitable

airport.

The

following procedures are

suggested:

A.

~f

the

wi~?s~~eld

ls

obstructed,

the

canopy

may be opened

to

Improve v1s1b1hty. A forward slip may be helpful.

Issued:

September

30, 1976

GULFSTREAM

AMERICAN

MODEL

AA

58

TIGEn

SECTION

3

EMERGENCY

PR

OCEOURES

B.

Rernernber

that

ice

accumulntion

increases wing

loading,

decreases

performance,

decreases

range

and

INCREASES

STA

LL

SPEEDS.

When

landing,

plan a slightly

higher

than

normal

air

speed

during

landing

approach.

Guard

against increased stall

speed

created

by

the

above

mentioned

conditions.

Touch

down

in a slightly

nose

high

attitude.

REMEMBER:

Intentional

flying in icing conditions !S PROH!

SITED!

STATIC

SOURCE

BLOCKED

If

erroneous

readings

are

suspected

on

the

instruments

associated

with

the

pitot·static

system

{airspeed

indicator,

altimeter

and

vertical

speed

indicator)

pitot

heat

should

be

applied

(for

erroneous

airspeed

indications)

in

case

the

problem is due

to

ice

or

water

accumulation

in

the

pitot

head.

Fa~lure

of

pitot

heat

to

correct

the

problem

may

indicate

blockage

of

the

static

sources.

Obviously

in a

situation

such

as this, a

landing

should

be

planned

at

the

nearest

suitable

airport.

If

it

is

necessary

to

continue

the

flight,

and

particularly

if

the

flight

is

in

marginal

conditions, a static

source

must

be

supplied

to

the

airspeed

indicator

and

altimeter.

If

an

alternate

air

source

is

installed

on

your

airplane, a static

air

source

can

be

applied

to

these

instruments

by

pulling

out

the

ALT,STATlC

AIR valve

located

on

the

left

side

of

the

instrurnent

panel.

NOTE

Close

the

canopy

when

using

alternate

static

air

source.

At

airspeeds

above

87

KIAS 1100 MPH)

subtract

6 KIAS

17

MPH)

from

indicated

airspeed

and

80

feet

from

indicated

altitude.

If

your

airplane

is

not

equipped

with

an

alternate

static

air

source, a static

source

can

be

supplied

to

the

airspeed

indicator

and

altimeter

by

breaking

the

glass

on

the

face

of

the

vertical

speed

indicator.

If

this

is

done

remember

the

following:

( 1)

The

vertical

speed

indicator

will

be

inoperative.

(2)

Some

error

may

be

expected

in

airspeed

and

altitude

indications.

At

a;rspeeds

above

87 KIAS 1100 MPH)

subtract

6 KIAS

(7

MPH)

from

indicated

airspeed

and

80

feet

from

indicated

altitude.

(3)

The

canopy

must

be

kept

closed,

since

opening

it

could

introduce

large

errors

in

airspeed

and

altitude

indications.

Issued:

September

30,

1976

3-15

SECTION

3

GULFSTREAM

AMER!

CAN

MODEL

AA-58

Tl

GER

EMERGENCY

PROCEDURES

SPINS

-;~e

A:-58

is1nNoTt

certificated

for

spins,

in

either

the

Normal

or

Utility

Gulfstream Aerospace AA-58 TIGER 1977, AA-58 TIGER 1978, AA-58 TIGER 1979 Pilot Operating Handbook

Specifications and Main Features

Frequently Asked Questions

User Manual