### INTERTEC H OVERLOAD , INC . FA A Exhibi t Lis t FA

A 201 0 - 019 4



### n Descriptio n 1 Applicatio n fo rRepai rSta Cer t 2003091 8 - 4 p p 2 O p Spec

s - 2007051 4 - 7 p p 3 Typ e Cert Dat a Shee t No . A12E A - 5 7 p p 4 Publication s Revisio n Statu s - 3 p p 5 Main t record s - 2 6 p p 6 Lt rdt d 20080102 3 - R t o FA A apolog y - 1 p p 7 Applicatio n fo rRepai rSta Cer t 2007112 9 - 2 p p 

### 8 2150.3 A 9 215 3 B 1 0 

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f Transportatio n Applicstlo n fc r Reoaj rStatio n Certificat e and/o rRatin g , < 0 

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; 1 . Rspai rStatso n Name , Numbsr , Locatio n an d Addres s 2 . Reason s fo rSubmissio n a . Officia l Nam e er

f Statio n 

### INTERTEC H OVERLOA D INC . Numbe r b . locatso n wher e busines s conducte d 

### 736 6 Hayvenhurs t Avenu e VariNuys , CA9140 6 1 3 Origina l Applicatio n fo rCertificat e an d Ratin g [ j Chang e i n Ratin g O Chang e i n Locatio n o rHousin g an d FaciilSiss n Chang e i n Owisrshi p n Othe r^Spsafy ; c . Officia l Mailin g Addres s o f Repai rStatio n (Number , Street , City , Stat e & ZIP } 

### 735 8 Hayvenhurs t Avenu e Va n Nuys , CA 9140 6 i d . Doin g Busines s As : \ 3 - Rating s Apptte d for : 

### 0 Airfram e j n Clas s 1 5 D Clas s 2 • 1 D Clas s 3 I n C!ass 4 

### O Accessorie s ; D Clas s 1 \ C I Clas s 2 I n Clas s 3 

## Q Powsrpian t n Clas s 1 D Clas s 2 n Clas s 3 

## ^ LImltec i ^ AtrfrarPi e D Engin e n Propelle r i i Instrumen t 

## n Propelle r D Clas s 1 n Clas s 2 

# n Radi o D Clas s 1 

# D Clas s 2 Clas s 3 

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D Clas s 1 D Clas s 2 D Clas s 3 n Clas s <

« n Accessorie s I I Landin g Gea r n Float s 

### n Radi o Q Roto rBlade s

i~~ l Fabri c • Emergenc

y Equip . • Non-Dest . Tes t D Specialize d Service s (specify )

\ 4 . Lis t o f Maintenanc e Function s Corstracte d t o Outsid e Agencies : 

### \ Non-Destructiv e Testin g - X-Ra y 7 Ultra-sound , an d Edd y Curren t • Heat Treatin g an d CA D platin g \ Powe rPlan t - Heav

y Maintenanc e 

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13 . Applicant' s CerUficatio n 

## • 1 Nam e o f Owne r(Includ e name(s } o f individua l owner , al l partners , o rcorpotatior t nam e givin g stat e an d dat e o f Incotporstion ) 

### Dea n R . Camb e I ! hereb y certify that ! hav e bee n authorize d b y th e repai rstatio n identifie d i n Ite m 1 afcwv e t o mak e thi s applicatio n ; . an d tha t statement s an d attachment s heret o ar e tru e an d correc t t o th e bes t o f m y knowledge . \ / ^ jDst e 

### ! 9/18/200 3 Authorize d Signatur e ^

' ti^^i^'^'mtt ^ Printe d Nam e of Authorasd Signe r 

### Timoth y J . Kena n Titi a 

### Inspecto r ; Agenc y Displa y o f Estimate d Burdem^ri a FA A esfimate s that th e averag e burde n fo rthi s repor t for m i s 1 5 minute s pe rresponse . Yo u ma y submi t I an y comments regardin g th e accurac y o f ihi s burde n estimat e o ran y suggestion s fo rreducin g tfi e burde n t o th e Offsc e of Managemen t an d Budget . ~^o u ma y als o sen d comment

s t o th e Federa l Aviatio n Administration , Aircraf t Maintenanc

e Division , AFS-300 , 80 0 Indepopdenc a Avenue , SW , Washington , 20591 , Attention : 0M B numbe r2120-0010 , Nn m 8310- 3 (6-M ) Stipereesls s Previou s KSWo n NSN : 0052-00-686-100 2 N\ '



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## AIECRA? T LISTIN G

TYP E BOMBA.RDIE

RAEROSPACE CESSNA A..IRCRA1'

T CO . GULFSTREA

M AEROSPAC E RAYTHEO N AIRCRAF

T GENERA L DYNAMIC S LOCKHEED AIRCRAF

T CO . DASSAULT AVIATIO

N SABERLINE

R MAKE CHALLENGE

R60 0 / 60 1 SERIE S LEA RJET - 24/25/35/36/55/6 0 SERIE S CITATIO N MODE L 50 0 / 60 0 SERIE S GULFSTREA

M G- l 159 , G-1159A , G-I

V HAWKE R125 , 400 , 600,700 , 800 , 100 0 SERIE S BEECH.IE T - 400/400 A MITSUBISH

I - MU-30 0 DiamondW

I WESTWIN

D I & II (112 4 & 112

4 A) ASTR A 1125 , 112 5 S P & 112 5 SP X LOCKHEE

D JET STA

R FALCO N 10,20,50 , 90 0 SABERLINE

RN A 265-40/60/70/8 0

• ^ <t \:M

' Ha>\v;risii.;;s : Avcivj c - Vai l Nuvs , C A 'JM0 6 

## AIRCRA,FT - I:ISTIN €

TYP E BOMB.ARDIE

RAEROSPAC E V CESSN A AIRCRAF

T CO . GL^LFSTRFA

M AEROSPAC E ILWTIIEO N AIRCILAF

T ISREAL E AIRCRAF

T iNDUST . LOCKHEE

D AIRCRAF

T CO . DASSAUL

T AVIATIO

N 

# ^c r

-~.. . .\ , --• • 

### /

/ 

## "MAK E / 

## 'CHALLENGE R600/60 1 SERIE S * ^ LEA RJET - 24/25/35/36/55/6 0 SERIE S ^' - CITATIO N MODE

L 50 0 / 60 0 SERIE S GULFSTREA

M G- l 159 , G-1159A , G-I

V <^ - HAWKE R"125/5)^ , 40(5' . 600 , TpC

C 800 . 100

0 SERIE S -i-- ^ 0\r^^ . BEECHJET-400./400 A s^ ^ WESTWIND i & I

I (112 4 & 112 4 A ) •> - ASTR A ! 125,112 5 S P & 1125 SP X ^ ^ LOCKHEED JE

T STA Rc \^ " " '-

^ FALCON 10 . 20 . 50,90 0 iV y 1 . f



### \ 

# ^ A

### \ U.S . Departmen t o f Transportatio n Federa l Aviatio n Administratio n 

### Operation s Specification s

1 2 3 4 5 7 2 5 6 0 10 1 44 9 TABL E O F CONTENT S PAR T A - General

Issuanc e an dApplicabilit y Definition s an dAbbreviation s Rating s an dLimitation s Summar y o f Specia l Authorization s an dLimitation s Exemption s Designate dPerson s Electronic/Digital Recordkeepin g System , Electronic/Digital Signature , an dElectroni c Medi a Europea n Aviatio n Safet

y Authorit y Rating s fo

r Repai r Station s Locate dOutsid e th e Unite dState s Additional Fixe dLocation s Antidru g an dAlcoho l Misus e Preventio n Progra m H Q CONTRO L

DAT E 11/16/0 4 11/16/0 4 01/30/0 4 09/23/9 8 02/20/9 8 01/30/0 4 04/04/0 3 11/16/0 4 11/16/0 4 01/22/0 4 EFFECTIV E

DAT E 11/08/0 6 11/08/0 6 05/14/0 7 11/08/0 6 (No t used ) 11/08/0 6 03/23/0 4 (No t used ) (No t used ) 11/08/0 6 AMENDMEN T

NUMBE R 3 2 8 6 4 0



# I CERTIF Y THA T THI S I S A TRUEJCQP Y O F TH E ORIGINA L FAA VNYFSD (



# i ' , v

v. . \ \ Prin t Date : 05/14/200 7 Certificat e No. : IOQR689 X Intertec h Overload , Inc . •;| -



# ^ - 2U.S . Departmen t o f Transportatio n Federa l Aviatio n Administratio n 

### Operation s Specification s A003 . Rating s an dLimitation s H Q Control : H Q Revision : 01/30/0 4

010 Th e Certificat e Holde r

i s authorize dth e followin g Rating s and/o r Limitations : Clas s Rating s Non e Authorize

d

Limite dRating s Ratin g Airfram e Manufacture r

BOMBARDIER, INC . Mak e / Mode l CL-600-1A1 1 (CL-600 ) SERIES CL-600-2A1 2 (CL-601 ) SERIES

LEARJE T INC . 24/25/31/35/36/55/6 0

SERIES

CESSN A AIRCRAF

T CO . MODE

L 500 (CITATION

) SERIES MODE L 65 0 (CITATION

)

GULFSTREA

M AEROSPAC

E CORPORATIO

N G- l I59/G-1159A/G-I V Limitation s Accomplis h maintenance , inspections , repairs , modifications , dail

y servicing an dtroubleshootin

g in accordance wit

h the manufacturer' s maintenanc e / overhau l manuals , customer' s specification s and/o

r FA A approve ddata . Accomplis h maintenance , inspections , repairs , modifications , dail

y servicing an dtroubleshootin

g i n accordance wit

h th e manufacturer' s maintenanc e / overhau l manuals , customer' s specification s and/o

r FA A approve ddata . Accomplis h maintenance , inspections , repairs , modifications , dail

y servicing an dtroubleshootin

g in accordance wit

h th e manufacturer' s maintenanc e / overhau l manuals , customer' s specification s and/o

r FA A approve ddata . Accomplis h maintenance , inspections , repairs , modifications , dail

y servicing an dtroubleshootin

g i n accordance wit

h the ma&iufacturer's maintenance / overhau l manuals , customer' s specification s and/o

r FA A approve ddata . 

## -yV, . 

### ^^' ^ Prin t Date : 5/14/200 7 A003- I Intertec h Overload , Inc . Certificat e No. : IOQR689 X

### U.S . Departmen t o f Transportatio

n Federa l Aviatio n Administratio

n Operation s Specification s Limite dRating s Min g Manufacture r

RAYTHEO

N AIRCRAF

T CO . Make/Mode l BS/HS 12 5 SERIE S 400/600/70

0 BA e 12 5 SERIES 800/100

0 BEECHJET4Q0/400

A MU-300-1 0 (DIAMON

D II)

GULFSTREA

M AEROSPAC

E LP . 112

5 WESTWIN

D ASTR A ASTR A SP X

LOCKHEE

D MARTI N CORPORATIO

N LOCKHEE

D 1329-2 3 (JETSTAR

) SERIES

A VIONS MARCE

L FALCO

N 1 0 DASSAULT-BREGUE

T AVLVnON (AMD/BA

)

DASSAUL

T AVIATIO

N MYSTER

E FALCO N 2 0 / 5 0 / 90 0 

# ICERTIFYTHATTHISIS A TRUECQPY O F TH E ORIGINA L



# . ^>^H^ ^

' FA A VN Y FSD O Limitation s Accomplish maintenance , inspections , repairs , modifications , dail

y servicin g andtroublesliootin

g i n accordanc e wit

h th e manufacturer' s maintenanc

e / overhaul manuals , customer' s specification s and/o

r FA A approveddata . Accomplish maintenance , inspections , repairs , modifications , dail

y servicin g andtroubleshooting i

n ' accordanc e wit

h th e manufacturer' s maintenanc

e / overhaul manuals , customer' s specification s and/o

r FA A approve ddat a Accomplis h maintenance , inspections , repairs , modifications , dail

y servicin g an dtroubleshooting i

n accordanc e wit

h the manufacturer' s maintenanc

e / overhau l manuals , customer' s specification s and/o

r FA A approve ddata . Accomplish maintenance , inspections , repairs , modifications , dail

y servicin g an dtroubleshooting i

n accordanc e wit

h the manufacturer' s maintenanc

e / overhaul manuals , customer' s specification s and/o

r FA A approveddata . Accomplis h maintenance , mspections , repairs , modifications , dail

y servicin g andtroubleshooting i

n accordanc e wit

h the manufacturer' s maintenanc

e / overhaul manuals , customer' s specification s and/o

r FA A approveddata .

Prin t Date : 5/14/200 7 V . A003- 2 Intertec h Overload , Inc . Certificat e No. : IOQR689 X 

# 1 '' /U.S . Departmen t o f Transportatio n Federa l Aviatio n Administratio n 

### Operation s Specification s Limite dRating s Ratin g Manufacture r

SABRELINE

R CORPORATIO

N Make/Mode l

NA265-40/60/70/S O

EMBREA R EM

B 145/13 5 (LEGACY

) SERIE S

Powerplan t AVC O Lycomin g Model s AL

F 502 L an dAL F 502L- 2

Honeywel l Internationa

l Inc . Model s TF

E 73 1 (Series ) (AlliedSignal , Garrett

)

Genera l Electri c Aircraf

t Engine s (GE) ModelCF34-lA

Genera l Electri c Compan

y • Aircraf t Engine Grou

p Model s CJ610-4,CJ610-6 , CJ610-8,CJ610-8A,an d CF700-2D- 2 Limitation s Accomplis h maintenance , inspections , repairs , modifications , dail

y servicin g an dtroubleshootin

g i n accordanc e wit

h th e manufacturer' s maintenance / overhau l manuals , customer' s specification s and/o

r FA A approve ddata . Accomplis h maintenance , inspections , repairs , modifications , dail

y servicin g an dtroubleshootin

g i n accordanc e wit

h th e manufacturer' s maintenance / overhau l manuals , customer' s specification s and/o

r FA A approveddata . Perfor mmaintenance an

d inspection checks . Remova

l an d installation of

powerplan t component s externa

l t o th e powerplan t cor e i n accordance wit h manufacturers ' maintenanc e manual s and/o

r othe r FA A approve ddata . Perfor mmaintenance an

d inspection checks . Remova

l an d installation of

powerplan t components externa

l t o the powerplan t cor e i n accordance wit h manufacturers ' maintenanc e manual s and/o

r othe r FA A approve ddata . Perfor mmaintenance an

d inspection checks . Remova

l an d installation o f

powerplan t components externa

l t o the powerplan t cor e i n accordance wit h manufacturers ' maintenanc e manual s and/o

r othe r FA A approve ddata . Perfor mmaintenance an

d inspection checks . Remova

l an d installation o f

powerplan t components externa

l t o th e powerplan t cor e i n accordance wit h manufacturers ' maintenanc e manual s and/o

r othe r FA A approve ddata . . . ^



### W 

# X ^ Prin t Date : 5/14/200 7 A003- 3 Intertec h Overload , Inc . Certificat e No. : IOQR689 XU.S . Department o f Transportatio n Federa l Aviatio

n Administratio n Operation s Specification s Limite dRating s Ratin g Manufacture r Mak e / Mode l Limitation s Prat t & Whitne y Divisio n • Unite dTechnologie s Corporatio n Model s JT l 2A-6 , JT l 2A-6A , JT12A- 8

Prat t & Whitne y Canada , Inc . Model s JT l 5D , JT15D-1 , JT15D IA,m5D-lB , JT15D-4B , Tri5D-5A ,

Prat t & Whitne y Canad a Corp . Model s PW305A . PW305 B

Rolls-Royc e Deutschlan d Lt d& C o K G Model s Spe y 511-8 , Ta y 611- 8



# <e > (fiC C 

# ^ ° =:U J 

# h^u- J 

# ss^ »->- ' 

# to r 1-^ - DCUJA , UJ^NA ' O L C ^ Rolls-Royc e Corporatio n (Indiana ) Mode l A E 3007 A (Series )

Rolls-Royc e Limite d- Bristo l Engine s Divisio n Model s Vipe r M K 522 , Vipe r M K 601-2 2



### L£ - Perfor mmaintenanc e an d inspectio n checks . Removal an d installatio n o f

powerplan t component s extema l t o th e powerplan t

core in accordanc e wit h manufacturers ' maintenanc e manual s and/o r

othe r FA A approve ddata . Perfor mmaintenanc e an d inspectio n checks . Removal an d installatio n o f

powerplan t component s extema l t o th e powerplan t

cor e in accordanc e wit h manufacturers ' maintenanc e manual s and/o r

othe r FA A approve ddata . Perfor mmaintenanc e an d inspectio n checks . Removal an d installatio n o f

powerplan t component s extemal t o th e - powerplan t

cor e i n accordanc e wit h manu&cturers ' maintenanc e manual s and/o r

othe r FA A approve ddata . Perfon n maintenanc e an d inspectio n checks . Removal an d installatio n o f

powerplan t component s extema l t o th e powerplan t

cor e i n accordanc e wit h manufacturers ' maintenanc e manual s and/o r

other FA A approve ddata . Perfor mmaintenanc e an d inspectio n checks . Removal an d installatio n o f

powerplan t component s extema l t o th e powerplan t

cor e in accordanc e wit h manufacturers ' maintenanc e manual s and/o r

other FAA approve ddata . Perfor mmaintenanc e an d inspectio n checks . Removal an d installatio n o f

powerplan t component s extema l t o th e pov^eiplant

cor e i n accordanc e wit h manufacturers ' maintenanc e manual s and/o r

other FA A approve ddata . 

### «. . Prin t Date : 5/14/200 7 A003- 4 Intertec h Overload , Inc . Certificat e No. : IOQR689 X 

# sU.S . Departmen t o f Transportatio n Federa l Aviatio n Administratio n 

### Operation s Specification s Limite dRating s Ratin g Instrument s - Altimeter y an d Pitot/Stati c Systems Manufacture r

Al l Makes Mak e / Mode l Al l Model s

Instrument s (Installation ) Al l Make s Al l Model s

Accessorie s Honeywel l Internationa

l Inc . (Allie dSignal , Garrett

) AP

U Model s GTCP3 6 (Series )

Radio (Installation ) Al l Make s Al l Model s



# I CERTIF Y THA T THI S I S A TRU E COPYOFTH E ORIGINA L 

# FA A VN Y FSD O Limitation s Limite dt o the removal , replacement, installation , test , an dinspectio n o f altimeters , stati c systems , pito

t systems , automatic altitud

e reportin g syste mequipment, i

n accordance wit h Appendice s E an

dF of Title 1 4 Cod e Of Federa l Regulation s (14CFR).Part43 . Limite dt o th e removal , replacement , installation , an din aircraf t testing of certificate d variou s component

s an dthei r relatedsystems component

s (VG, DG , Attitud

e Indicator, HSI , ADI , RMI , Movin

g Map , Compas s Systems , an

dAttitud e Systems , Fligh

t Director, an

d Autopilot equipment/systems) . Perfor mmaintenance an

d inspection checks . Remova

l an d installation o

f powerplan t components externa

l t o the powerplan t cor e i n accordance wit h manufacturers ' maintenance manual s and/o

r othe r FA A approve ddata . Limite dt o the removal , replacement , installation , an dinaircrait testing of certificate d components o

f HF/VHF/UH

F Communication , Navigation , Thunderstor

mDetection , Weathe r Rader, Traffi

c Advisory , an dTAW S Systems . A

s wel l as tes t an dinspec t fo r compliance wit h Titl e 1 4 Cod

e of Federa l Regulation s Par

t 91 . 171 , an

d 91.207 . Limite dt o the removal , replacement , test

an dinspectio n o f transponders , (Mod

e S An d ATCRBS) , i

n accordance wit

h Appendice s E an

dF if titl e 1 4 Cod e of Federa l Regulations . (1 4 CFR ) Par t 43 . Limite dRating s - Specialize dService s Ratin g Specifieation s Non e Authorized . Limitation s

Prin t Date : 5/14/200 7 A003- 5 Intertec h Overload , Inc . Certificat e No. : IOQR689 X 

# r/ A 

# \ cU.S . Departmen t o f Transportatio n Federa l Aviatio n Administratio n 

### Operation s Specification s Al l wor k shal l b e accomplishe di n accordanc e wit h th e customer' s specification , manufacture' s maintenanc e /

overhau l manuals , and/o r FA A Approve dData . 1 . Issue db y th e Federa l Aviatio n Administration . 2 . Support

informatio n reference : 3 . Thes e Operation s Specification s ar e approve dby directio n o f th e Administrator . Dees , Jen y N Principa l Avionic s Inspecto r 4 . Dat e Approva l i s effective : 5/14/0 7 5 . I hereb y accep t

ajdj^ceiv e th e Operation s Specification s in thi s paragraph .

Agen t fo r Servic e [MBE , DEA N R WPO l Amendmen t

Number : 8

Date : 5/14/0 7



# I CERTIF Y THA T THI S fS A TRUE^Y^THE^ORfGINA L 

# ^AmF^O" ^

Prin t Date : 5/14/200 7 \ 

# ' K r A003- 6 Intertec h Overload , Inc . Certificat e No. : IOQR689 XDEPARTIVIEN T O F TRANSPORTATIO N FEDERA L AVIATIO N ADMINISTRATIO N A12E A Revision 3 5 Gulfstrea m G-l15 9 G-1159A G-1159 8 G-I V G V GV-S P GIV- X Apri l 15,201 0 TYP E CERTIFICAT E DAT A SHEE T NO . A12E A Thi s datastieet

whic h i s par

t of Typ e Certificate No . A12E A prescribe s condition s an dlimitation s unde r whic h the produc t

fo r whic h th e typ e certificate wa s issue dmeet s th e airworthines s requirement s o f th e Civi l Air

Regulation s an

dFedera l Aviatio n Regulations . Typ e Certificat

e Holder : Gulfstrea mAerospac e Corporatio n P.O . Box 220 6 Savannah , Georgi a31402-220 6 I . - Mode l G-1159 . Gulfstrea mI I (Transpor t Category) . Approve dOctobe r 19.1967 . Engine s Fuel 2 Roll s Royc e Spe y R B (163 ) 511- 8 (Typ e Certificat e E2EU ) America n Britis h Kerosen e

ASTM D 1655-7 8 Je t

A ASI A D 1655-7 8 Je t

A- 1 I.A.T.A . 1988 : Kerosen e typ e MIL-T-8313 3 Grad e JP- 8 D Eng . R.D . 245 3 Issu e 5 (2 ) D Eng . R.D . 249 4 Issu e 1 0 Canadia n CI S Frenc h Romania n

America n Britis h Canadia n CI S Frenc h Germa n CAN/CGC B 3.23-M8 6

T-1 , TS- I & R T (COS T 10227-86 ) T-7 , (GOS T 12308-66 ) AIR3405/ C (3754/7 3 CS-3) ) STA S 563 9 JP- 4 Wid e Cu t

Tvo e (Se e NOT E 5 ) ASTM D 1655-8 9 Je t

B MIL-T-5624 N Grad e JP- 4 I.A.T.A . 1987 : JP. 4 typ e D Eng . R.D . 245 4 Issu e 4 (2 ) D Eng . R.D . 248 6 Issu e 9 CAN/CGS B 3.2 2 M8 6 T- 2 (GOS T 10027-86 ) AI R3407/ B T L 9130-00 6 Issu e 6 Pag e No . Re v No . Pag e No . Rev . No . Pag e No . Rev . No . I

3 1 2 1 1 7 4 1 2 3 2 3 0 2 2 1 9 4 2 2 9 3 1 6 2 3 2 6 4 3 2 7 4 1 6 2 4 2 6 4 4 3 0 5 1 3 2 5 2 6 4 5 2 5 6 3 0 2 6 2 6 4 6 3 4 7 1 5 2 7 2 6 4 7 3 4 8 1 6 2 8 3 0 4 8 2 8 9 1 3 2 9 2 6 4 9 3 4 1 0 3 0 3 0 2 9 5 0 2 9 1 1 1 9 3 1 2 2 5 1 2 9 1 2 1 9 3 2 2 1 5 2 3 5 1 3 1 6 3 3 3 0 5 3 3 0 1 4 3 0 3 4 2 6 5 4 2 9 1 5 1 9 3 5 2 7 5 \ 30^ - 1 6 1 6 3 6 •2 6 5 6 3 5 1 7 1 6 3 7 3 0 5 7 3 3 1 8 3 0 3 8 2 8 1 9 3 0 3 9 2 9 2 0 2 9 4 0 2 8A12E A Pag e 2 ff' 

# 1 ^' Y

Fue l (con't ) America n Britis h Canadia n Frenc h Germa n JP- 5 Hig h Flash-Poin t Tvo e MIL-T-5624 N Grad e JP- 5 D Eng . R.D . 245 2 Issu e 2 (3 ) D Eng . R.D . 249 8 Issu e 7 3-GP-24M a AI R3404/ C T L 9130-00 7 Issu e 4

Oi l Fue l shal l confor mt o th e specificatio n a s liste do r t o subsequen t

revision s foun d i n th e lates t

approve dAirplan e Fligh t Manual . Castro l 3 C an d32 5 Aeroshel l Turb o Oi l 39 0 an d50 0 Esso/Exxo n 238 0 Mobi l Je t

Oi l 1 1 Chevro n Je t

Engin e Oi l 5 Calte x RP M Je t

Engin e Oi l 5 Texac o S.A.T.O . 773 0

Engin e Limit s NOTE : Mixin g o f oil s i s no t

recommende dfo r

APU , Oi l shal l confor mt o th e specificatio n a s liste do r t o subsequen t

revision s foun di n th e lates t approve dAirplan e Fligh t Manual . Stati c Thrus t

(std . dav ) S.L . Takeoff ( 5 min. ) 11,4001b . Maximu mcontinuou s 10,94 0 lb . Maximu mpermissibl e engin e roto r operatin g speeds : N l (lo w compressor ) (106.6% ) 8,95 0 n^ m N 2 (hig h compressor ) (100.1% ) 12,50 0 rp m Maximu mpermissibl e temperamres : Turbin e outle t

ga s (Trimme r

Resistors , Inc. ) Takeof f ( 5 min. ) Maximu mcontinuou s Momentar y maximu mdurin g start s an drelight s Maximu mwit h revers e thrus t (3 0 secon dlimit ) Maximu mover-temperatur e (2 0 secon dlimit ) 585° C 540° C 570° C 490° C 610° C Engine s wit h S.B . S p 77-4 3 (2 0 secon dlimit ) (12 0 secon dlimit ) Oi l inle t Oi l inle t (1 5 min . limit ) Fue l inle t temperatur e t o engin e hig h pressur e pum p Fue l inle t

temperatur e (1 5 min . limit ) Maximu mAi r

Blee dExtractio n (Percen t o f n o blee dmas s flow) Maximu mengin e hig h pressur e blee d Maximu mengin e lo w pressur e blee d 2.45 % 3.65 % 615° C

595° C 100° C 120° C 9a° C 110° C

Auxiliar y Powe r

Uni t (APU ) AirResearc h GTCP-36-6 : S/ N 1 thr u 24 8 an d77 5 Maximu mpermissibl e exhaus t ga s temperatur e ' 700° C Maximu mroto r

spee d- al l condition s 110 % AP U alternato r

loa dratin g 20Kv a AP U rate doutpu t

shaf t powe r 1 Oh p (wit h 5 0 lb . pe r

min . blee dai r

an dambien t temperat e o f

113°F ) ^Pag e 3 

# %S ± A12EA

AP U (con't ) AirResearc h GTCP-36-100G : S/ N 25 0 thr u 299 , excep t

25 2 Maximu mpermissibl e exhaus t

ga s temperature -

- U p t o 60 % rp mdurin g star

t 988° C 60 % -100 % durin g star

t 821C ° to 732° C (linea r decrease )

- Runnin g Maximu mroto r spee d- al l condition s AP U alternato r

loa dratin g (wit h 46. 6 lb . pe r

min . blee dair

and ambient temperature o f

103°F) 732° C 110 % 20Kv a 50h p Airspee dLimit s (CAS ) V ^m o Mm o = V a Vs h M,s b = Vf e Vlo Vi e V ^mc a Vl l (Maximumoperating ) Se alevel t o 24,10 0 ft. .85 ® 24,10 0 ft

an dabov e (Maneuvering ) (Spee dbrake ) Se aleve l to 28,10 0 ft . .85 ® 28,10 0 ft. an

dabov e (Flap s dovr

ato 39° ) (Flap s dow n to 20° ) (Flap s dow n t o 10° ) (Landin g gea

r operation ) (Landin g gea

r extended ) (Minimumcontro l air ) (Landin g light

operation ) 42 3 mp h 24 5 mp h 38 9 mp h 19 6 mp h 25 3 mp h 28 8 mp h 25 9 mp h 28 8 mp h 11 7 mp h 28 8 mp h 36 7 knot s

21 3 knot s 33 8 knot s 17 0 knot s 22 0 knot s 25 0 knot s 22 5 knot s 25 0 knot s 10 2 knot s 25 0 knot s Maximu mOperatin g Altitud e 43,00 0 fee t (airplane s modifie db y Aircraf t Servic e Chang e 29 9 ar

e approve dt o 45,00 0 feet. ) Maximu mWeigh t (lb. ) Aircraf

t S/ N 1 thr u 8 2 & 77 5 1 thr u 8 2 & 77 5 8 3 tlir u 10 0 1 thr u 10 0 & 77 5 10 1 thr u 21 6 1 thr u 21 6 an d77 5 21 7 thr u 299 , excep t 249 , 25 2 & 77 5 Wit h ASC * 10A&4 1 8 1



### - - 25 6 23 3 Max . Zer o

Fuel 38,00 0 39,00 0 39,00 0 42,00 0 42,00 0 42,00 0 42,00 0 Max . Ram

p 58,00 0 60,00 0 60,00 0 62,50 0 62,50 0 65,30 0 65,30 0 Max .

Take-Of f 57,50 0 59,50 0 59,50 0 62,00 0 62,00 0 64,80 0 64,80 0 Max .

Landin g 51,43 0 55,00 0 55,00 0 58,50 0 58,50 0 58,50 0 58,50 0 *Se e NOT E 6 Datum M.4.C . Fue l Capacit y Statio n 0 i s 4 5 inche s forwar do f th e ji g poin t

a t th e centerlin e o f

th e airplan e i

n th e nos e whee l well , 147,2 8 in . (L,E . o f

M.A.C . = Fuselag e Statio n 404.13 ) S/ N 1 thr u 8 2 & 775 : Gravit y o r Pressur e Fueling : Tota l 22,62 0 lb . Usabl e 22,50 0 lb , Ann * -1-433.0 S/ N 1 thr u 8 2 & 77 5 wit

h AS C 4 1 & AS C lOA , an dS/ N 8 3 thr u 216 : Gravit y o r Pressure Fueling : Tota l 23,40l ) lb . Usabl e 23,30 0 lb . Arm * 435. 9 Fue l weight s base dupo

n fue l densit y o f 6.7 5 lb . per

gal . See NOTE 1 fo

r syste mfiiel andunusabl e fuel .A12E A Pag e 4 

# is ^

Oi l Capacit y

Seria l No . Eligibl e *Am i base do n groundstati c attitud e (-1.5 ° FRL ) Engine Oi l 13. 7 lb./14. 6 U.S . pints-lef t engin e (An n = +564.0 ) 14. 6 lb./15. 6 U.S . pints-righ t engin e (Ar

m= +564.0 ) AP U Oi l 5. 1 lb./5. 4 U.S . pint s (Ar m= +620.0 ) Oi l weight s base dupo

n oi l densit

y o f 7. 5 lb . per

gal . See NOT E 1 fo r syste moil . Capacitie s shown ar

e fo r engin e oi l tankag e only . Tota l engin e oi l i s a

n additiona

l 1 4 lb . pe r

engine . S/ N 1 thr u 216 , includin g 775 ; & S/ N 21 7 thr u 29 9 wit h Aircraf t Servic e Chang e 233 , excep t S/ N 24 9 an d252 .

V , 

# APag e 5 

# r T A12E A oCfEFSTREA

M G- l 15 9 WEIGHT AN

D CENTE ROF GRAVITY ENVELOP

E AT GROUN

D STATI C ATTITUD E 

## GULFSTREA M AEROSPAC E 01 1 5 9 (INCLUDIN G TI P TAN KAIRPLANE ) WEIGH T AN D BALANC E DAT A

ALLOWABL E ZER O FUE L GROS S WEIGH T

C G ENVELOP E I F TH E ZFG W I S WITHI N TH E ENVELOPE , TH E FUELE D AIRCRAF T WIL L B E WITHI N FA A APPROVE D LIMIT S FO R AL L FUE L LOADINGS . 42,00 0 41,00 0 40,00 0 39,00 0 38,00 0 37,00 0 36,00 0 35,00 0 34,00 0 3 3 00 0 \ 

# N /

\ \ \ 

# c -

L > 1 ' 

### \ A — 

### \ j 

### i

- ^ \ 

# v P A \ \ ^ 

# k

' ; ^ 

## i i 1 \1 Ii 1 : 1 A 1 i 

# 1 1 \ 1 1

— 1

—"' i ._ _ :

\ 

# N

V ^ ^ > \ \

k \ :

3 0 3 2 3 4 3 6 3 8 4 0 4 2

CENTE RO F GRAVIT Y - % MA C

AIRPLAN E SEFJA L NO . 1 t THR U 8 2 AN D 77 5 1 THR U 8 2 AN D 77 5 8 3 THR U 10 0 1 THR U 10 0 AN D 77 5 10 0 AN D SU B EXCLUDIN G 77 5 10AAND4 1 IA12E A Pag e 6 

# ^fS ^ IL Mode l G-1159 . Gulfstrea mH-(Transoor t Category) . Increase dRang e Airplan e (Ti n Tanks) , Approve d Ma y 13.1977 . Engine s Fue l 2 Roll s Royc e Spey R B (163-25 ) 511- 8 (Typ e Certificat e E2EU ) America n Britis h Canadia n CI S French Romania n Kerosen e

ASTM D 1655-7 8 Je t

A ASTA D 1655-7 8 Jet

A- 1 I.A.T.A . 1988 : Kerosen e typ e MIL-T-8313 3 Grad

e JP- 8 D Eng . R.D . 245 3 Issu e 5 (2 ) DEng . R.D . 249 4 Issu e 1 0 CAN/CGC B 3.23-M8 6 T-1 , TS- 1 & RT(GOS T 10227-86 ) T-7 , (GOS T 12308-66 ) AI R3405/ C (3754/7 3 CS-3) ) STA S 563 9 JP- 4 Wid e Cu

t Typ e (Se e NOT

E 5 ) America n Britis h ASTM D 1655-8 9 Je t B MIL-T-5624 N Grade JP- 4 I.A.T.A . 1987 : JP, 4 typ e D Eng . R,D . 245 4 Issu e 4 (2 ) D Eng , R,D . 248 6 Issu e 9 Canadia n CI S French Germa n America n Britis h Canadia n French Germa n CAN/CGS B 3,2 2 M8 6

T- 2 (GOS T 10027-86 ) AIR3407/

B T L 9130-00 6 Issu e 6 JP- 5 High Flash-Point

Typ e MIL-T-5624N Grad

e JP- 5 D Eng . R.D . 245 2 Issu e 2 (3 ) D Eng . R.D . 249 8 Issu e 7 3-GP-24M a AI R3404/ C T L 9130-00 7 Issu e 4

Oi l Fue l shall confor

mto th e specification s a s liste dor to subsequent

revision s foun

di n th e lates t approve dAirplan e Flight

Manual . Castro l 3 C an d32 5 Aeroshell Turb o Oil 39 0 and50 0 Esso/Bxxon 238 0 Mobil Jet Oi l 1 1 Chevro n Jet

Engin e Oi

l 5 Caltex RP M Je t Engin e Oil 5 Texac o SAT O 773 0

Engine Limit s NOTE : Mixingo f oil s i s not

recommende dfo

r APU . Oil shall confor

mt o th e specification s a s liste dor to subsequent

revision s foun

di n th e lates t approve dAirplan e Flight

Manual . Stati c Thrus t

(std . day ) S.L . Takeof f ( 5 min. ) Maximu mcontinuou s 11,4001b . 10,9401b , Maximu mpermissibl e engin e roto r operatin g speeds : N l (lo w compressor) (106,6% ) 8,95 0 rp m N2 (high compressor ) (100.1% ) 12,500 rp mPag e 7 A12E A

Engin e Limit s (con't ) Maximu mpermissibl e temperatures : Turbin e outle t

ga s (Trimme r

Resistors , Inc. ) Takeof f ( 5 min. ) Maximu mcontinuou s Momentar y maximu mdurin g start s an drelight s Maximu mwit h revers e tlirus t (3 0 secon dlimit ) Maximu mover-temperatur e (2 0 secon dlimit ) Engine s wit h S.B . S p 77-4 3 (2 0 secon dlimit ) (12 0 secon dlimit ) 585° C 540° C 570° C 490° C 610° C 615° C 595° C Oi l inle t Oi l inle t (1 5 min . limit ) 100° C 120° C

Auxiliar y Powe r

Uni t (APU ) Fue l inle t temperatur e t o engin e hig h pressur e pum p Fue l inle t

temperatur e (1 5 min . limit ) Maximu mAi r

Blee dExtractio n (Percen t o f n o blee dmas s flow) Maximu mengin e hig h pressur e blee d Maximu mengin e lo w pressur e blee d AirResearc h GTCP-36-6 : S/N 1 thr u 24 8 an d77 5 Maximu mpermissibl e exhaus t ga s temperatur e Maximu mroto r

spee d- al l condition s AP U alternato r

loa dratin g AP U rate doutpu t

shaf t powe r (wit h 5 0 lb . pe r

min . blee dai r

an dambien t temperatur e o f

113°F ) 90° C 110° C

2.45 % 3.65 % 700° C 110 % 20Ky a lOh p

AirResearc h GTCP-36-100G : S/ N 25 0 thr u 299 , excep t

25 2 Maximu mpermissibl e exhaus t ga s temperatur e -

- U p t o 60 % rp mdurin g star t 988° C 60 % - 100 % durin g star t 82 1 ° C t o 732° C (linea r decrease )

Airspee dLimit s (CAS ) -Runnin g Maximu mroto r

spee d- al l condition s AP U alternato r

loa dratin g AP U rate doutpu t

shaf t powe r (wit h 46. 6 lb . pe r

min . blee dai r

an dambien t temperatur e o f

103°F ) 732° C 110 % 20Ky a 50h p

V *^m o Mni o = V a Vs h Ms h = Vf e Vl o Vl . Vmc a Vl l (Maximu moperating ) 34 5 mp h (30 0 knots ) a t

S.L . .8 5 @ 28,10 0 ft

an dabov e (Maneuvering ) (Spee dbrake ) Se aleve l t o 33,50 0 ft. .8 5 @ 33,50 0 ft. an dabov e (Flap s dow n t o 39° ) (Flap s dow n t o 20° ) (Flap s dow n t o 10° ) (Landin g gea r

operation ) (Landin g gea r

extended ) (Minimu mcontro l air ) (Landin g ligh t

operation ) t o 38 9 mp h (33 8 knots ) 18 4 mp h 34 5 mp h 19 6 mp h 25 3 mp h 28 8 mp h 25 9 mp h 28 8 mp h 11 7 mp h • 28 8 mp h a t

28,10 0 ft. 16 0 knot s 30 0 knot s 17 0 knot s 22 0 knot s 25 0 knot s 22 5 knot s 25 0 knot s 10 2 knot s 25 0 knot sA12E A 

### ' ^ ^ Maximu mOperatin g Altitude 43,00 0 fee t (airplane s modifiedby Aircraf t Servic e Chang e 29 9 ar

e approvedt

o 45,00 0 feet. ) Maximu mWeigh t (lb. )

Datu m M.A.C . Fue l Capacit y

Oi l Capacit y

Seria l No . Eligibl e Aircraf t S/ N 1 thr u 21 6 & 77 5 21 7 thr u 299 , excep t 24 9 & 25 2 Wit

h ASC * 20 0 

### " Max . Zer

o Fue l 42,00 0 42,00 0 Max . Ram

p 66,00 0 66,00 0 Max .

Take-Oft " 65,50 0 65,50 0 Max .

Landing 58,500 58,500 *Se e NOT E 6 and"Seria

l No . Eligible. " Statio n 0 i s 4 5 inche s forwar do f the ji g point

a t th e centerlin e o f

the airplan e i

n the nos e whee l well . 147.2 8 in . (L.E . o f

M.A.C . = Fuselag e Statio n 404.13 ) Gravit y o r Pressure Fueling : Tota l 26,93 6 lb . Usabl e 26,80 0 lb . Ann * +445. 2 Fuel weight s base dupon fue l densit y of 6.7 5 lb . per

gal . Se e NOT E 1 fo

r systemfue

l an dunusabl e fuel . *Ar mbase don groun dstati c attitude (-1.5°FRL ) Engin e Oil AP U Oi l 13.71b./14. 6 U.S . pints-lef t engin e (Ar

m= +564.0 ) 14. 6 lb./15. 6 U.S . pints-right engin e (An n = +564.0 ) 5. 1 lb./5. 4 U.S . pint s (An n = +620.0 ) Oi l weight s base dupo n oi l densit y o f 7. 5 lb . pe r

gal . Se e NOT E 1 fo

r systemoil . Capacitie s show n ar

e fo r engin e oi l tankag e only . Tota l engin e oil i s a

n additiona

l 1 4 lb , pe r engine , S/ N 1 thr u 21 6 an d77 5 wit h Aircraf t Servic e Chang e 200 ; andS/ N 21 7 thr u 299 , excep t 24 9 an d252 .



### v. .Pag e 9 

### ^ A12E A GULFSTREA

M G- l 15 9 WEIGH T AN

D CENTE ROF GRAVITY ENVELOP

E AT GROUN

D STATI C ATTITUD E (WITH TIP TANKS ) 

## GULFSTREA M AEROSPAC E G1 1 5 9 (INCLUDIN G TI P TAN KAIRPLANE ) WEIGH T AN D BALANC E DAT A

ALLOWABL E ZER O FUE L GROS S WEIGH T

C G ENVELOP E I F TH E ZFG W I S WITHI N TH E ENVELOPE , TH E FUELE D AIRCRAF T WIL L B E WITHI N FA A APPROVE D LIMIT S FO R AL L FUE L LOADINGS . 42,00 0 41,00 0 40,00 0 39,00 0 38,00 0 — 37,00 0 36,00 0 35,00 0 34,00 0 33,00 0 

### —

—

—

— - •



### —

\ \ 1 1 

### '

i 

# s \ 

# 7

\

- " ••' " 1 1 

### \ C

n ...• • 

### \ \ \ \ * ^ \ J V 

# • ^ v 

# V \

• 

### \ \ ^ " " 1 ...j .

—- i . . 1 

# v i \ ' \ 

# k -

_N \ 

## V \ 

# A

- - t " • 1

1



### . ; . '

i 

### —

3 0 3 2 3 4 3 6 3 8 4 0 4 2

CENTE RO F GRAVIT Y - % MA C

AIRPLAN E SERIA L NO . 1 THR U 8 2 AN D 77 5 1 THR U B 2 AN D 77 5 8 3 THR U 10 0 1 THR U 10 0 AN D 77 5 10 0 AN D SU B EXCLUDIN G 77 5 WIT H AS C 10AAND4 1 8 1 O R 20 0 ENVELOP E A B B C CA12E A 

### Pag e 1 0 f V S" i III . - Mode l G-1159A . Gulfstream-l U (Transpor t Category) . Approve dSeptembe r 22.1980 . Th e G- l 159

A i s th e same a s th e G- l 15 9 excep t fo r the following differences : (a ) Wing : Spa

n i s increase d6 feet , chor

dincrease dforwar

dof origina l front beam , contou

r change dforwar

do f mid-chord , an

d5-foo t winglet s added . (b ) Fuselage : Additio n o f a2-foot sectio n af t o f main door , radom

e extende d an dcontou r modified , an

dnew curve dwindshiel dan dsuppor t structure . (c ) Maximu

mtakeof f weigh t increase dto 68,20 0 lb./69,70 0 lb . (d ) Variou s change s to autopilot , flight instruments , an

dengin e instruments . Engine s 2 Roll s Royc e Spe y R B (163-25 ) 511- 8 (Typ e Certificat e E2EU) Fue l America n Britis h Canadia n CI S French Romania n Kerosen e

ASTM D 1655-7 8 Je t

A ASTA D 1655-7 8 Je t

A- 1 I.A.T.A . 1988 : Kerosen e typ e MIL-T-8313 3 Grade JP- 8 D Eng . R.D . 245 3 Issu e 5 (2 ) DEng . R.D . 249 4 Issu e 1 0 CAN/CGC B 3.23-M8 6 T-1 , TS- 1 & R

T (GOS T 10227-86 ) T-7 , (GOS T 12308-66 ) AI R3405/ C (3754/7 3 CS-3) ) STA S 563 9 JP- 4 Wide Cut

Typ e (Se e NOT

E 5 ) America n Britis h ASTM D 1655-8 9 Je t B MIL-T-5624N Grad e JP- 4 I.A.T.A . 1987 : JP. 4 typ e D Eng . R.D . 245 4 Issu e 4 (2 ) D Eng . R.D . 248 6 Issu e 9 Canadia n CI S French Germa n America n Britis h Canadia n Frenc h Germa n CAN/CGS B 3.2 2 M8 6

T- 2 (GOS T 10027-86 ) AI R3407/ B T L 9130-00 6 Issu e 6 JP- 5 High Flash-Point

Typ e M1L-T-5624

N Grade JP- 5 D Eng . R.D . 245 2 Issu e 2 (3 ) D Eng . R.D . 249 8 Issu e 7 3-GP-24M a AI R3404/ C T L 9130-00 7 Issu e 4 Fuel shal l confor

mt o th e specification s a s liste dor to subsequen

t revision s foun

di n th e lates t approve dAirplan e Flight

Manual .

V .Pag e 1 1 

### ^'^^ ^ A12E A Oi l Castro l 3 C an d32 5 Aeroshel l Turb o Oi

l 39 0 and50 0 Esso/Exxo n 238 0 Mobi l Je t Oil I I Chevro n Jet

Engine Oil 5 Calte x RP M Je t Engin e Oi

l 5 Texac o SAT O 773 0

Engin e Limit s NOTE : Mixing o f oil s i s no t recommende dfo

r APU . Oil shal l confon

n to th e specification s a s liste do r to subsequent

revision s foun

di n th e lates t approve dAirplan e Flight

Manual . Stati c Thrus t

(std . day ) S.L . Takeof f ( 5 min. ) Maximumcontinuou s 11,4001b . 10,9401b . Maximu mpermissibl e engin e roto r operatin g speeds : N l (lo w compressor) (106.6% ) 8,95 0 rpm N 2 (high compressor

) (100.1% ) 12,50 0 rpm Maximu mpermissibl e temperatures : Turbin e outlet

ga s (Trimme

r Resistors , Inc. ) Takeof f ( 5 min. ) Maximumcontinuou s Momentar y maximu mdurin g start s andrelight s Maximu mwit

h revers e thrus t

(3 0 secon dlimit ) Maximumover-temperatur e (2 0 secon dlimit ) Engine s wit

h S.B . S p 77-4 3 (2 0 secon dlimit )

(12 0 secon dlimit ) 585° C 540° C 570° C 490° C 610° C 615° C 595° C

Auxiliar y Powe r Uni t (APU ) Oil inlet 100° C Oi l inlet (1 5 min . limit) 120° C Fuel inlet temperatur

e to engin e hig h pressur e pum p 90° C Fue l inle t temperatur

e (1 5 min . limit ) 110° C MaximumAir

Blee dExtractio n (Percent o f n o blee dmas s flow) Maximumengin e hig h pressure blee d2.45 % Maximu mengin e lo

w pressure blee d3.65 % AirResearc h GTCP-36-100 G Maximumpermissibl e exhaus t ga s temperature -

- Up to 60 % rp

mdurin g star

t 60%-100 % durin g star

t -Runnin g Maximu mrotor spee d- all condition s AP U alternato r

loa dratin g AP U rate doutput

shaf t powe r (wit h 46. 6 Ib.^e r

min . blee dair

andambien t temperature o f

103°F ) 988° C 82I°Cto732° C (linea r decrease ) 732° C 110 % 20Kv a 50h p

V, .A12E A Pag e 1 2 

# f^' ^ Airspee dLimit s (CAS )

Maximu mOperatin g Altitud e Maximu mWeigh t

(lb. ) M „

^s b M. K = "s b ^f e 'l o 'me g (Maximu moperating )

Se aleve l t o 28,00 0 ft. .8 5 @ 28,00 0 ft

an d abov e (Maneuvering ) (Spee dbrake ) Se aleve l t o 28,00 0 ft. .8 5 @ 28,00 0 ft. an d abov e (Flap s dow n t o 39° ) (Flap s dow n t o 20° ) (Flap s dow n t o 10° ) (Landin g gea r

operation ) (Landin g gea r

extended ) (Minimu mcontro l air ) (Minimu mcontro l ground ) 39 2 mp h 23 7 mp h 39 2 mp h 195 mp h 25 3 mp h 28 8 mp h 25 9 mp h 28 8 mp h 11 7 mp h 103 mp h 34 0 knot s

20 6 knot s 34 0 knot s 170 knot s 22 0 knot s 25 0 knot s 22 5 knot s 25 0 knot s 10 2 knot s 8 9 knot s 45,00 0 fee t

Datu m M.A.C . Fue l Capacit y Aircraf t S/ N 249 , 252 , 30 0 thr

u 426 , an d 87 5 249 , 252 , 30 0 thr

u 426 , an d 87 5 42 7 & Su

b Wit

h AS C *



### - - 7 0



### - - Max . Zer

o Fuel 42,00 0 44,00 0 44,00 0 Max . Ram

p 68,70 0 70,20 0 70,20 0 Max .

Take-Ofi ^ 68,20 0 69,70 0 69,70 0 Max .

Landin g 58,50 0 58,50 0 58,50 0 * Se e NOT E 6 .

Th e zer o datu mi s 2 1 inche s forwar do f th e ji g poin t

a t th e centerlin e o f

th e aiiplan e i n th e nos e whee l wel l o r 19 3 inche s forwar do f

Fuselag e Statio n 193B . 165. 4 in . (L.E . o f

M.A.C . = Fuselag e Statio n 387.8 ) S/ N 249 , 252 , 30 0 thr u 371 , an d 875 : Gravit y o r

Pressur e Fueling : Tota l 28,0141b . Usabl e 27,90 0 lb . Ann * 430. 4

Oi l Capacit y S/ N 37 2 an d subsequen t

an d S/ N 875 , 249 , 252 , an d 30 0 thr u 37 1 wit h AS C 30 : Gravit y o r

Pressur e Fueling : Tota l 28,44 4 lb .

_Usabl e 28,3001b .

Ann * +423. 3 Fue l weight s base dupo n fue l densit y o f 6.7 5 lb . pe r

gal . *Ar mbase do n groun dstati c attitud e (-1.5 ° FRL ) Engin e Oi l AP U Oi l 13. 7 lb./14. 6 U.S . pints-lef t engin e (Ar m= +564.0 ) 14. 6 lb./15. 6 U.S . pints-righ t engin e (Ar m= +564.0 ) 4.7 5 lb./5. 4 U.S . pint s (Ar m= +620.0 ) Oi l weight s base dupo n oi l densit y o f 7. 5 lb . pe r

gal . Se e NOT E 1 fo r

syste moil . Capacitie s show n ar e fo r engin e oi l tankag e only . Tota l engin e oi l i s a n additiona l 1 4 lb . pe r engine . Seria l No . Eligibl e S/ N 249 , 252 , 30 0 an d subsequent , includin g S/ N 875 .Pag e 1 3 (^ '



# \£ \ A12E A

GULFSTREA

M G- l 159A WEIGH T AN D CENTE ROF GRAVIT

Y ENVELOP

E A T GROUND STATI C ATTITUD E



# i i GULFSTREA M AEROSPAC E G1159 A WEIGH T AN D BALANC E DAT A ALLOWABL E ZER O FUE L GROS S WEIGH T

C G ENVELOP E I F TH E ZFG W I S WITHI N TH E ENVELOPE , TH E FUELE D AIRCRAF T WIL L B E WITHI N FA A APPROVE D LIMIT S FO R AL L FUE L LOADINGS . 35 h 4 4 000 i -' '

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## v. .A12E A Pag e 1 4 

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# r- h IV . Mode l G-1159B . Gulfstream-e--ir B (Transpor t Category) . Approve dSeptembe r 17.1981 . Th e G- l 159B i s the sam

e a s th e G- l 15 9 excep t

fo r the following differences : (a ) Wing : Spa

n i s increase d6 feet , chor

dincrease dforwar

do f origina l front beam , contou

r change dforwar

do f mid-chord , an

d5-foo t winglet s added . Fuselage : Addition o f

optional extende dmodifie dcontour radome . Maximu mtakeof f weight increase dto 68,20 0 lb./69,70 0 lb . Variou s change s t

o autopilot , fligh

t instruments , an

dfue l quantit y instruments . NOTE : Mode

l G-1159 , al

l seria l numbers , ar

e eligibl e fo

r identificatio n a s Mode

l G-1159 B whe

n modifiedi

n accordanc e wit

h GA C Aircraf

t Servic e Chang e (ASC ) 300 . (c ) (d ) Engine s Fue l 2 Roll s Royc e Spe y R B (163-25 ) 511- 8 (Typ e Certificat e E2EU ) America n Britis h Canadia n CI S Frenc h Romania n Kerosen e

ASTM D 1655-7 8 Je t

A ASTA D 1655-7 8 Je t

A- 1 I.A.T.A . 1988 : Kerosen e typ e MIL-T-8313 3 Grad e JP- 8 D Eng . R.D . 245 3 Issu e 5 (2 ) D Eng . R.D . 249 4 Issu e 1 0 3-GP-23-M8 6 T-1 , TS- 1 & R T (GOS T 10227-86 ) T- 7 (GOS T 12308-66 ) AI R3405/C (3754/7 3 (CS-3) ) STA S 563 9 America n Britis h JP- 4 Wide Cut Typ e (Se e NOT

E 5 ) ASTM D 1655-8 9 Je t

B MIL-T-5624N Grad e JP- 4 I.A.T.A . 198 7 JP. 4 typ e D Eng . R.D . 248 6 Issu e 9 D Eng . R.D . 245 4 Issu e 4 (2 ) Canadia n CI S Frenc h Germa n America n Britis h Canadia n Frenc h Germa n CAN/CGS B 3.2 2 M8 6 grade

T- 2 (GOS T 10027-86 ) AI R3407/ B T L 9130-00 6 Issu e 6 JP- 5 High Flash-Point

Typ e Mn.-T-5624 N Grad e JP- 5 D Eng . R.D . 245 2 Issu e 2 (3 ) D Eng . R.D . 249 8 Issu e 7 3-GP-24M a AI R3404/ C T L 9130-00 7 Issu e 4 Fue l shal l confor

mto the specification s a s liste do r to subsequen

t revision s foun

din th e lates t approve dAirplan e Fligh t

Manual . Oil Castro l 3 C an d32 5 Aeroshel l Turb o Oi

l 39 0 and50 0 Esso/Exxo n 238 0 Mobi l Jet Oi l II Chevro n Jet

Engine Oi

l 5 Calte x RP M Jet Engin e Oi l 5 NOTE : Mixin g o f

oil s i s no t recommende dfo

r APU . Oi l shal l confor

mt o the specification s a s liste do r to subsequen

t revision s foun

din th e lates t approve dAirplan e Fligh t

Manual .

v .Pag e 1 5 c\bi'' ^ A12E A Engin e Limit s Stati c Thrus t (std . day ) S.L . Takeof f ( 5 min. ) Maximu mcontinuou s 11,400 lb . 10,940 lb . Maximumpermissibl e engin e rotor operatin g speeds : N l (lo w compressor ) (106.6% ) 8,95 0 rp m N 2 Oiig h compressor ) (100,1% ) 12,500 rpm Maximu mpermissibl e temperatures : Turbin e outle t

ga s (Trimmer

Resistors , Inc ) Takeof f ( 5 min, ) 585° C Maximu mcontinuou s 540° C Momentar y maximu mdurin g start s an drelight s 570° C Maximu mwit

h revers e thrus t

(3 0 secondlimit ) 490° C Maximumover-temperature (2 0 secondlimit) 610° C Engine s wit

h S.B , S p 77-4 3 ( 20 secondlimit) 615° C

(12 0 secondlimit ) 595° C Oi l inle t 100° C Oil inle t (1 5 min , limit ) 120° C

Auxiliar y Powe r Uni t (APU) Fuel inle t temperatur e t o engin e high pressure pum p Fue l inle t temperamr e (1 5 min . limit) Maximu mAi r

Blee dExtractio n (Percen t o f n o blee dmas s flow) Maximu mengin e hig h pressure bleed Maximu mengin e lo w pressure blee d 90° C 110° C 2.45 % 3.65 % AirResearc h GTCP-36-100 G Maximumpermissibl e exhaus t ga s temperatur

e -

- U p t o 60 % rp mdurin g star

t 60 % - 100 % durin g star

t -Runnin g Maximu mroto r

spee d- al l condition s AP U alternato r

loadratin g AP U rate doutpu t

shaf t powe r (wit h 46. 6 lb . pe r

min . blee dai

r an dambien t temperatur e o f

103°F ) AiResearc h GTCP-36- 6 Maximu mpermissibl e exhaus t ga s temperatur

e Maximu mroto r

spee d- all condition s AP U Alternato r

loa dratin g AP U rate doutpu t

shaf t power (wit h 5 0 lb . pe r

min . blee dai

r an dambien t temperature o f

113°F ) 988° C 821°Cto732° C (linea r decrease ) 732° C 110 % 20Kv a 50h p

700° C 110 % 20Kv a lOh p

V .A12E A Pag e 1 6 

# ^= t Airspee dLimit s (CAS ) 'm o M „ ^'s b M , V , sb " f e "l o ^l e 'me g (Maximu moperating )

Se aleve l t o 28,00 0 ft, .8 5 ® 28,00 0 ft

an dabov e (Maneuvering ) (Spee dbrake ) Se aleve l t o 28,00 0 ft, ,8 5 @ 28,00 0 ft, an dabov e (Flap s dow n t o 39° ) (Flap s dow n t o 20° ) (Flap s dow n t o 10° ) (Landin g gea r

operation ) (Landin g gea r

extended ) (Minimu mcontro l air ) (Minimu mcontro l ground ) 39 2 mp h 23 7 mp h 39 2 mp h 19 5 mp h 25 3 mp h 28 8 mp h 25 9 mp h 28 8 mp h 11 5 mp h 10 3 mp h 34 0 knot s

20 6 knot s 34 0 knot s 17 0 knot s 22 0 knot s 25 0 knot s 22 5 knot s 25 0 knot s 10 0 knot s 8 9 knot s Maximu mOperatin g Altitud e Maximu mWeigh t

(lb, ) 45,00 0 fee t

Aircraf t Mod , No . 1 & Sub , 1 & Sub , Wit

h AS C * 27 5 Max , Zero

Fuel 42,00 0 44,00 0 Max , Ram

p 68,70 0 70,20 0 Max ,

Take-Of f 68,20 0 69,70 0 Max ,

Landin g 58,50 0 58,50 0 Datu m M.A.C . Fue l Capacit y

Oi l Capacit y

Seria l No . Eligibl e * Se e NOT E 6 . Statio n 0 i s 4 5 inche s forwar do f th e ji g poin t

a t th e centerlin e o f

th e airplan e i n th e nos e whee l well . 165.3 9 in . (L.E . o f

M.A.C . = Fuselag e Statio n 387.81 ) Modificatio n Nos . 1 thr u 8 Gravit y o r

Pressur e Fueling :

Modificatio n Nos . 9 an dSubsequent . Gravit y o r

Pressur e Fueling : Tota l Usabl e Arm * Tota l Usabl e Arm * 28,01 4 lb .

27,90 0 lb . +430. 4 28,44 4 lb . 28,30 0 lb . +423. 3 Fue l weight s base dupo n fue l densit y o f 6.7 5 lb . pe r

ga l *Ar mbase do n groun dstati c attitud e (-1.5 ° FRL ) Engin e Oi l AP U Oi l 13. 7 lb./14. 6 U.S . pints-lef t engin e (Am i = +564.0 ) 14. 6 lb./15. 6 U.S . pints-righ t engin e (Ar m= +564.0 ) 4.7 5 lb./5. 4 U.S . pint s (Ar m= +620.0 ) Oi l weight s base dupo n oi l densit y o f 7. 5 lb . pe r

gal . Se e NOT E 1 fo r

syste moil . Capacitie s show n ar e fo r engin e oi l tankag e only . Tota l engin e oi l i s a n additiona l 1 4 lb . pe r engine . G- l 159 ; S/

N 1 thr u 299 , includin g 775 , excludin g 24 9 & 252 , whe n modifie db y Aircraf t Servic e Chang e 300 .

V,.Pag e 1 7 

# - r A12E A

Q 

## GULFSTREA M AEROSPAC E G1 1 59 B WEIGH T AN D BALANC E DAT A ALLOWABL E ZER O FUE L GROS S WEIGH T

C G ENVELOP E I F TH E ZFG W I S WITHI N TH E ENVELOPE , TH E FUELE D AIRCRAF T WIL L B E WITHI N FAA APPROVE D LIMIT S FO R AL L FUE L LOADINGS . 44,00 0 43,00 0 42,00 0 41,00 0 40,00 0 39,00 0 38,00 0 37,00 0 36,00 0 35,00 0 

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3 4 3 6 3 8 4 0 4 2 4 4 4 6

CENTE RO F GRAVIT Y - % MA C 4 8

MODIFICATIO N NO . 1 AN D SUB S 1 AN D SUB SA12E A Pag e 1 8 /f\ h 7 ^ V . - Mode l G-I

V (Transpor t

Category) . Approve dApri l 22.198 7 Engine s Fue l

Oi l

Engin e Limit s 2 Roll s Royc e Ta y Mar k 611- 8 (FA

A Typ e Certificat

e No . E25NE) (LBA/EAS A Typ e Certificat e No . 6327 ) America n Britis h Canadia n Chines e CI S Frenc h America n Britis h Canadia n America n Britis h Canadia n Frenc h Kerosene

ASTM D 1655 , Jet

A ASTM D 1655 , Jet

A- 1 MIL-T-83133 , Grade JP 8 MIL-DTL-8313 3 De f Stan . 91-8 7 De f Stan . 91-9 1 CAN/CGSB-3.2 3 G B 6537-9 4 No . 3 GOS T 10227-86 , T-1 , TS- 1 & R T DCSE A 13 4 JP- 4 Wid e Cu t Typ e (Se e NOTE 5 ) ASTM D 1655 , Jet

B ASTMD661 5 Mn.-DTL-5624 , Grade JP 4 MIL-PRF-5624 Grade JP 4 DEF . STAN . 91-8 8 CAN/CGSB-3.2 2 JP- 5 High Flas h - Point

Typ e MIL-DTL-5624 , Grad e JP 5 MrL-PRF-562

4 Grade JP 5 De f Stan . 91-8 6 3-GP-3.2 4 DCSE A 14 4 Fue l shal l confor

mt o th e specificatio n a s liste do r to subsequen

t revision s foundi n th e lates t

approvedAirplane Flight

Manual . Th e followin g oil s ar

e approvedfo

r us e i n th e engin e andAPU : 3 Centistoke Aeroshel l Turb o Oi

l 39 0 Castro l 3 C Turbin e Oi

l Castro l 32 5 Engine Oi

l ESSO/Exxo n Turb o 238 9 5 Centistoke Esso/Exxo n Turb o Oi

l 238 0 Mobi l Je t Oil I I Mobi l Je t Oil 25 4 Castro l 500 0 Ga s Turbine Oi l Aeroshel l Turbin e Oi

l ATO 50 0 NOTE : Mixin g o f

oil s i s no t recommende dfo

r APU . NOTE : Mixin g of

oil s i s not recommende dbu t

brand s ma

y b e mixe di f operationall y essential . Oil s of the abov e brands , when reclaime dt o the approve dRolls-Royc e standar dfo r viscosit y andgrade , are approvedfo r use . Oi l shal l confor

mt o th e specificatio n a s liste do r

t o subsequent

revision s i

n the lates t approve dAirplane Fligh

t Manual . Stati c Thrus t

(std . day ) S.L . Rate dTakeof

f (Se e Not e 14 ) Rate dMaximumcontinuou s 13,85 0 lb . 12,4201b .Pag e 1 9 r Y ^ 

### ^ •• t A12E A Engin e Limit s (con't ) Maximumpermissibl e continuou s rotor operatin g speeds : N l (lo w compressor ) (95.5% ) 8,01 5 rp m N 2 (hig h compressor ) (97.5% ) 12,17 2 rp m Maximumpermissibl e temperature s (°C) : Turbin e ga s tem

p measure da

t nozzl e guid e vane s ahea

do f first low stag e pressur e turbine : Takeof f (Se e Note 14) Maximumcontinuou s Momentar y maximu mdurin g gioun dstart s Momentar y maximu mdurin g airstart s (rehghts ) Maximu mover-temperature (2 0 secon dlimit) Oil tem p (minimumfo

r starU'ng) Oil tem p (maximum ) Oil tem p (1 5 minute limit ) Fuel inle t tem p to engin e hig h pressure pum p Fuel inle t temperature (1 5 min . limit ) Maximu mPermissibl e Ai

r Blee dExtractio n 7t h Stag e HP C Blee d 12t h Stag e HP C Blee d(ma

x continuou s an

dbelow ) Fa n Blee d 800 ° 715 ° 700 ° 780 ° 820 ° -40 ° 105 ° 120 ° 90 ° 120 ° 7. 0 lb./se c 10.01b./se c 10. 5 lb./se c Auxiliar y Powe r Uni t (APU ) AirResearc h GTCP-36-100 G

Maximumpermissibl e exhaus t ga s temperatur

e - U p t o 60 % rp mdurin g star

t 988° C 60 % -100 % durin g star

t 82 1 ° C to 732° C (linea r decrease ) Runnin g 732° C Maximumroto r

spee d- al l condition s 110 % AP U alternato r

loa dratin g 30Kv a AP U rate doutpu t

shaf t powe r 50h p (wit h 46. 6 lb . pe r

min . blee dai

r an dambient tem p o f 103°F ) Honeywel l 36-150fG ) fS/

N 100 0 -153 5 b y AS C 465 ) Maximumpermissibl e exhaus t ga s temperature U p t o 50 % rp mdurin g star

t 1785° F 51 % - 87 % durin g star

t 1785° F to 1350° F (linea r decrease ) 87 % - 100 % durin g star

t 1350° F Runnin g 1230° F Maximumroto r

spee d- al l conditions : 110.70 % AP U alternato r

loa dratin g 30Kv a AP U rate doutpu t

shaf t powe r 47.3hp (wit h 66. 8 lb . pe r

min . blee dair ) Airspee dLimit s (CAS ) Vmo^^m o (Maximumoperating ) Se e Altitude/Mac h Fligh

t Operatin g Envelop e Vf e Vl o Vi e V, me g raca (Maneuvering ) (Flap s down to 39° ) (Flap s dow n to 20° ) (Flap s dow n t o 10° ) (Landin g gea

r operation ) (Landin g gea

r extended ) (Minimu mcontro l ground) (Minimumcontro l air

) 19 5 mp h

23 5 mp h (1 ) 19 6 mp h 20 6 mph (1 ) 25 3 mph' " 28 8 mp h 25 9 mph 28 8 mp h 12 8 mp h 12 0 mp h ^ V . 17 0 knot s 20 6 knot s (1 ) 17 0 knot s 18 0 knot s (1 ) 22 0 knot s 25 0 knot s 22 5 knot s 25 0 knot s 11 1 knot s 10 4 knot sA12E A Pag e 2 0 C ' 

# ^SfMaximu mOperatin g Altitud e Maximu mWeigh t (lb, ) (1 ) Aircraf t S/ N 100 0 thr u 1213wit

h n59SB41190 , S/

N 121 4 an

dsubsequent 45,00 0 fee t Aircraf t S/ N 1000 thr u 121 3 1000 thr u 121 3 wit

h AS C 6 1 1000 thr u 121 3 wit

h AS C 26 1 100 0 thn i 121 3 wit

h AS C 19 0 121 4 & Su

b 1500 & Sub s wit

h AS C 44 0 (G400 ) 1500 & Sub s wit

h AS C 43 6 (G300 ) Max . Zer o Fue l 46,50 0 49,00 0 49,00 0 49,00 0 49,00 0 49,00 0 49,00 0 Max . Ram

p 73,60 0 73,60 0 73,60 0 75,00 0 75,00 0 75,00 0 72,40 0 Max .

Take-Of f 73,20 0 73,20 0 73,20 0 74,60 0 74,60 0 74,60 0 72,00 0 Max .

Landin g 58,50 0 58,50 0 58.50 0 66,00 0 66,00 0 66,00 0 66,00 0 Datum M.A.C , Fue l Capacit y

Oi l Capacit y GIV/GIV(G400 ) Tota l 29,60 5 l

b Usabl e 29,50 0 lb . Arm * +430. 4 GIV(G300 ) 27,00 5 l b 26,90 0 l b +426. 5

Seria l No . Eligibl e For weigh t andbalanc e purposes , the zer o datumi s 1 5 inche s af t o f the ji g poin t a t th e centerlin e o f

th e airplan e i

n th e nos e whee l well or

20 6 inche s forwar

do f Fuselag e Statio n 206 . 166.2 2 in . (L.E . o f

M.A.C . = Fuselag e Statio n 387.7 ) Gravit y o r Pressur e Fueling : Fue l weight s base dupo

n fue l densit y o f 6.7 5 lb . per

gal . * Ar mbase don groundstati c altitud e (-1.5 ° FRL ) Tota l engin e oil capacit

y 14. 0 lb./14. 4 U.S . pint s (eac h engine ) Usabl e engin e oi l capacit

y 10. 1 Ib./lO. S U.S . pint s (each engine ) (Ar m= +582,00 ) Oil weight s base dupo

n oi l densit

y of 7. 5 lb . per

gal . Se e NOT E 1 fo r systemoil . Capacitie s show n ar

e fo r engin e oi l tankag e only . Tota l engin e oi l i s a

n additiona

l 16. 8 lb . pe

r engine . AP U oil 4.7 5 lb./5. 0 U.S . Pint s (Ar m= +620.0 ) S/ N 100 0 throug h 153 5 (1500-153 5 ar e G300/G400) . AIRSPEED LIMIT S (MAXIMU M OPERATING )Pag e 2 1 i - ^ 

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# Aircraf t Zer o Fue l Gros s Weigh t Envelop e

Fo rS N 1000-121 3 | Zer o Fue l 46.50 0 Maximu m Weigii t (lb s

Landin g 58,50 0 Ram p

73,60 0 Takeof

f 73,20 0 

## I f th e ZFG W i s withi n th e envelope , th e fuele d aircraf t wil l b e withi n FA A approve d limit s fo ral l fue l loadings . H I ~ A R 4 D 

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% MAC )

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# tA12E A Pag e 2 4 c \ 

# fS= } Aircraf t Zer o Fue l Gros s Weigh t Envelop e F a S N 1000-121 3 wit h AS C 6 1 Maximu m Weiqh t (lbs ) Zer o Fue l 49,00 0 Landin g

58,50 0 Ram p

73,60 0 Takeof

f 73,20 0 

## 5 0 4 9 4 8 4 7 4 6 § 4 5 o • Q 4 4

—H H 

## £ 4 3 N 

## 4 2 4 1 4 0 3 9 I f th e ZFG W

•



### / 

# Y

\ \ 

### / /

\ \ 

# V , ' i s withi n th e envelope , th e fuele d aircraf t wil l b e withi n FA A approve d limit s fo ral l fue l loadings .

, ^ ^ ^



## 3 6 3 7 3 8 3 9 4 0 4 1 4 2 4 3 4 4 4 5 Cente ro f Gravit y (

% MAC ) 4 6

v. .Pag e 25 C \\>



# k ^ \ A12E A 

# Aircraf t Zer o Fue l Gros s Weigh t Envelop e

Fo rS N 1000-121 3 wit h AS C 26 1 Maximu m Weiah t (lbs ) Zer o Fue l 49,00 0 Landin g

58,50 0 Ram p Takeof f 1 73,60 0 73,20 0 | 

## I f th e ZFG W i s withi n th e envelope , th e fuele d aircraf t wil l b e withi n FA A approve d limit s fo ral l fue l loadings .

3 5 3 6 3 7 3 8 3 9 4 0 4 1 4 2 ' 4 3 Cente ro f Gravit y (

% MAC ) 4 4 4 5 4 6A12E A Pag e 2 6 

### ^\^' ^



# Aircraf t Zer o Fue l Gros s Weigh t Envelop e

Fo rS N 121 4 an d Subs , ai d S N 1000-121 3 wit h ASC I 9 0 an d S N 150 0 ai d Subs , wit h AS C 44 0

Maximu m Weiqh t (lbs ) Zer o Fue l 49,00 0 Landin g

66,00 0 Ram p Takeof f 1 75,00 0 74,60 0 | 

## I f th e ZFG W i s withi n th e envelope , th e fuele d aircraf t wil l b e withi n FA A approve d limit s fo ral l fue l loadings . >JL » 

### 4 9 4 8 4 7 4 R 

### S^4 5 

### o o ^ 4 4 

# f 4 3 j u . N 4 2 4 1 4 0 3 9 3 8 3 7 - - 

# V

\ \ \ \ 

# V \ \ ' 

# s

• — . 

# X

> 

# \ l ^

""" ^ 

# X \ \ X



### ^ 

## 3 5 3 6 3 7 3 8 3 9 4 0 4 1 4 2 ;4 3 4 4 Cente ro f Gravit y (

% MAC ) 4 5 4 6

V, .Pag e 27 

# i V ^ A12E A 

# Aircraf t Zer o Fue l Gros s Weigh t Envelop e

Fo rS N 150 0 an d Subs , wit h AS C 43 6

Maximu m Weigh t (lbs ) Zer o Fue l 49,00 0 Landin g

66,00 0 Ram p

72,40 0 Takeof

f 1 72,00 0 1

5 0 4 9 4 8 4 7 4 6 - 4 5 o 

## ^ 4 4 § 4 3 O u . N 4 2 4 1 4 0 3 9 3 8 3 7 I f th e ZFG W i s withi n th e envelope , th e fuele d aircraft wil l b e withi n FA A approve d limit s fo ral l fue l loadings .

\ 

### \ \ ^ 

# V \ \ 1 

### — 

# \ l X

. \ >



### *'** ^ \ \ \

...... ^



## 3 5 3 6 3 7 3 8 3 9 4 0 4 1 4 2 ' 4 3 4 4 4 5 4 6 Cente ro f Gravit y (

% MAC ) \; .AI2E A Pag e 2 8 

# 4 n

VI . - Model G

V (Transpor t

Catc-gorv) . Approve dApri l 11.199 7 Th e Gulfstrea

mG V i s th e sam

e a s tli e Gulfstrea

mG-I V except fo r th e followin g differences : • approximately 15 % increas e i n maximumtakeof

f an dlandin g weight s • maximu moperatin g altitud e increas e fro m45,00 0 ft

t o 51,00 0 f t • engine chang e fro

mRoll s Royc e Ta

y t o Roll s Royc e Deutschlan dBR700-710A1-1 0 (increase dtlims t an dhighe r bypas s ratio ) • addition of

Ful l Authorit y Digita l Engin e Control s (FADEC ) • win g spa n increase dfrom74. 6 ft

to 93, 5 ft • addition s t

o th e fuselag e o f

a5 foot sectio n forwar

do f th e main entr

y door , anda2 foo

t sectio n af t o f th e win g •approximatel y 30 % increas e i n horizonta l tai l are a • addition o f

composit e material flight

contro l siuface s an

dthrus t reverser s Engine s 2 BM W - Roll s Royc e Deutschlan dBR700-710A1-1 0 (FA A Typ e Certificat

e No , E00057EN ) (EAS A Typ e Certificat e No . E.018 ) Fue l America n

Britis h Canadia n Chines e CI S Frenc h America n Britis h Canadia n CI S America n Britis h Canadia n Frenc h Kerosen e

AST M D 1655-92 , Jet

A ASTM D 1655-92 , Jet

A- 1 MrL-DTL-83133 , Grad e JP- 8 GST U 320.00149943,007-9 7 GST U 320,00149943.011-9 9 De f Stan,91-8 7 De f Stan , 91-9 1 CAN/CGSB-3,2 3 G B 6537-9 4 No , 3 GOS T 10227-86 , T - 1 , TS- 1 & R T DCSE A 134/ A JP- 4 Wid e Cut

Typ e (Se e NOTE 5 ) ASTMD661 5 MIL-DTL-5624 (JP

4 Grade ) De f Stan,91-8 8 CAN/CGSB-3,22-200 1 GOS T 10277-8 6 JP- 5 High Flash-Point

Tvo e MIL-DTL-5624 JP 5 Grad e De f Stan , 91-8 6 3-GP-3,24 DCSE A 144/ A Fue l shall confor

mto th e specificatio n a s liste dor to subsequent

revision s foun di n th e lates t

approve dAirplan e Fligh

t Manua l (AFM) , See AF M fo r information o

n hig h flash poin t

fuels . Oi l Th e following oil s ar e approve dfo

r us e i n th e engin e an

dAPU : 3 Centistok

e Typ e Oils : 5 Centistok

e Typ e Oils : Aeroshel l Turbin e Oi l 39 0 Aeroshel l Turbin e Oi l 50 0 Cas&o l Aero 500 0 Exxo n Turb o Oil 238 0 Mobil Jet Oi l I I Mobil Je t Oi l 25 4 NOTE : Mixin g o f

oil s i s no t recommende dfo

r APU . NOTE : Mixing o f

oil s i s not recommende dbut

brand s ma

y b e mixe dif operationall y essential . Oil s o f the abov e brands , when reclaime dt o the approve dstandar

dfo r viscosit y andgrade , ar

e approve dfo

r use . Oil shall confor

mt o th e specificatio n a s liste do r to subsequent

revision s i

n the lates t approve dAirplan e Fligh

t Manual . ^Pag e 2 9 f 

# l^i . A12E A Engin e Limit s Stati c Thrus t (std . day ) S.L . Takeof f ( 5 min. ) Maximu mcontinuou s 14,75 0 lb . 14,45 0 lb . Maximu mpermissibl e engin e rotor operatin g speeds : N l (lo w pressur e compressor) MaximumTakeof

f (se e Not e 14 ) (101.1% ) Maximu mContinuou s (101.0% ) Maximu mOverspee d(2 0 seconds ) (101.5% ) Revers e Thrus t

(3 0 seconds ) ( 70% ) N 2 (hig h pressur e compressor) Maximu mTakeof

f (se e Not e 14) ( 99.6% ) Maximu mContinuou s (98.9% ) Maximu mOverspee d(2 0 seconds ) ( 99.8% ) 100%N 1 equal s 7,43 1 rp

m 100 % N 2 equal s 15,89 8 rp m

Powe r Rang e Idle t o 1.0 6 EP R 1.0 6 t o 1. 3 EP R Above 1. 3 EP

R Au^ciliar y Powe r Uni t (APU) 7,51 3 rpm 7,50 5 rp m 7,54 2 rp m 5,20 1 rpm 15,83 4 rp m 15,72 3 rpm 15,86 6 rp m Maximu mpermissibl e temperature s (°C) : Turbin e ga s temperature measure da t nozzl e guid e vane s ahea

dof first lo w stag e pressur e turbine ; Takeof f (se e Not e 14

) 900 ° Maximu mcontinuou s 860 ° Maximu mprio r

to star t 150 ° Maximu movertemperature (2 0 second s limit ) 905 ° Momentar y maximumdurin g groun dstart s 700 ° Momentar y maximu mdurin g infligh

t restart s 850 ° Oil tem p (minimu mbefor

e acceleratin g fo

r T/O ) +20 ° Oil tem p (minimu mfo

r starting ) -30 ° Oi l tem p (maximum ) 160 ° Fue l inle t temperature t o low pressure pum p a t S.L . 54 ° Fuel outle t

temperature fromengin e hig h pressur e pump (unresbicte dmaximum) 158 ° Fue l outle t

temperature (1 5 min . limit ) 165 ° Fue l inle t temperature (minimum) -40 ° Blee dExtractio n EP R= P50/P2 : Tli e amount s o f blee dextractio n fromstage s 5 an d8 , respectively , are relate dt o th e core enb y mas s flow, W26 . Th e amount o f fa n blee dextractio n i s relate dt o th e fa

n entr y mas s flow, W l A . Norma l Flo w (% ) Stag e 5 

### **** * 4. 4 4. 3 Stage s

7. 8 4. 2 

### **** * Fa

n 

### **** * 0. 2 0. 4 MaximumFlo w (% )

Stag e 5 3. 0 8. 3 8. 5 Stag e 8

12. 1 7. 9 

### **** * Fa

n 0. 6 1. 6 1. 8 Allie dSignal - Mode

l RE22 0 {GV } Rate dOutpu t

Shaf t Powe r 62 hp (continuous ) 7 0 hp ( 5 minutes ) 10 1 h p ( 5 seconds ) Maximu mGenerato r

Output Shaf t Spee d12,000 rp m Maximu mExhaus t

Ga s Tem p (EGT ) a t Rate dOutpu t

124 1 ° F (T

j = 14 0 °F ) Maximu mAllowabl e Roto r Spee d^ 48,32 0 rp m(T2 < 11 5 °F) Maximu mAllowabl e EG

T * Starting : 1922 ° F (105 0 °C )

[fo r T j < -2 0 ° F (-2 9 °C) , P

2 > 6.7 5 psia ] Operating : 135 0 ° F (73 2 °C ) [fo r T2=140 ° F (6 0 °C) ]A12E A Pag e 3 0 

# 's > Airspee dLimit s (CAS )

Maximu mOperatin g Altitude Vmo^m o (Maximumoperating ) Va Vf e Vlo Vi e V, meg (mph) Se e AF M fo r Altitude/Mac h Flight

Operatin g Envelop e (Maneuvering ) (Flap s dow n to 39° ) (Flap s dow n to 39 ° wit

h ASC19 A or 73 A incorporated ) (Flap s dow n to 20° ) (Landin g gea

r operation ) (Landin g gea

r extended ) (Minimu mcontro l ground ) (Minimumcontro l air ) (KCAS ) 23 7 mp h 190 mp h 19 6 mp h 25 3 mp h 25 9 mp h 28 8 mp h 11 8 mp h 12 9 mp h 20 6 knot s

16 5 knot s 170 knot s 22 0 knot s 22 5 knot s 25 0 knot s 10 3 knot s 11 2 knot s 51,00 0 fee t Maximu mWeigh t (lb. ) Aircraf t S/ N 50 1 & Sub s Max . Zer o

Fue l 54,50 0 Max . Ram

p 90,90 0 Max .

Take-Of f 90,50 0 Max .

Landin g 75,30 0 Datu m M.A.C . Fue l Capacit y Fo r weigh t andbalanc e purposes , th e zero datu mi s 4 5 inche s forwar

do f th e ji g point a t th e centerlin e o f

th e airplan e in th e nos e wheel well . 171.1 9 in . (L.E . of

M.A.C . = Fuselag e Statio n 524.74 ) Gravit y o r Pressur e Fueling :

Tota l Usabl e Arm * S/

N 50 1 thr a54 8 Without AS C 5 0 41,5061b . 41,0261b . +558. 0 S/ N 54 9 an dsubs , and50 1 thr u 54 8 wit h AS C 5 0 41,4891b . 41,3001b . + 558. 5

Oil Capacit

y

Seria l No . Eligibl e C . G . Envelop e Fue l weight s base dupo

n fue l densit y o f 6.7 5 lb . pe

r gal . * Ar mbase don groun dstati c attitud e (-1.5 ° FRL) 16. 9 lb./1 8 U.S . pint s 22. 0 lb./24. 4 U.S . pint s Tota l engin e oi l capacit

y (eac h engine) : Lucas-Wester

n Gearbo x AP T Gearbo x (Art n = +785.00 ) Oil weight s base dupo

n oi l densit

y o f 7. 5 lb . pe r gal . Se e NOTE 1 fo

r systemoil . Capacitie s shown ar

e fo r engin e oi l tankag e only . Tota l engin e oi l i s a

n additional 9. 5 lb . pe r

engine . AP U oil 9.00 lb./9. 6 U.S . Pint s (Ar m= +782.5 ) S/ N 50 1 throug h 693 , plu s 69 9 (s/ n 66 6 change dto 699) . Se e Figur e 1- 3 fo r G V Zero Fuel Gros s Weigh

t vs . Cente r of Gravit y (S/ N 50 1 throug h 56 9 withou t AS C 73/73A ) ; Se e Figure 1-3

A fo r G V Zero Fue l Gros s Weigh

t vs . Cente r o f Gravit y (S/ N 57 0 andsubs , andS/

N 50 1 throug h 56 9 wit

h AS C 73/73A )Pag e 3 1 

# ii l A12E A 

### Figur e 1-3 : Zer o Fue l Gros s Weigh t Cente ro f Gravit y Envelop e

(Fo rAirplane s Withou t AS C 73/73A ) 5 6 5 5 5 4 5 3 5 2 

### -

- . 5 1 

### o o o § 5 0 

# I > 4 9 

# 1 ^ ^ O 

## •3 4 7 4 6 4 5 4 4 4 3 4 2 (

1 

### 31 — 

# 4 J 

# r

i



### ' \

1 

# V [i j f i

[5 1 

# N

— 

# N

— 1 — 

# s . X

\ ^

" ^ < PtNo . 1

2 3 4 5 6 7 

# N

^ C G

35.5 0 34.5 0 34.5 0 34.8 0 37.3 0 43.0 0 43.0 0 

# V >

^ @

7 Weigh t

4570 0 4825 0 5400 0 5450 0 5450 0 5085 0 4435 0

i 

### 3 3 3 4 3 5 3 6 3 7 3 8 3 9 4 0 4 1 4 2 4 3 4 4 4 5 4 6 C G ( % 

### MAC )A12E A Pag e 3 2 

# "j S

o o o 

### 5 6 5 5 5 4 5 3 5 2 5 1 § . 5 0 0 ) 

### 4 9 

### B O 

### I 4 8 u . 

### « 4 7 4 6 4 5 4 4 4 3 4 2 

### Figur e 1-3A : Zer o Fue l Gros s Weigh t Cente ro f Gravit y Envelop e (Fo rAirplane s Wit h AS C 73/73A )

r r~ i 

# 3 ]

2 4 

# f

\ \ 1

— 1 — 

# V [1 j r"~ i 

# B

\

. ^

— 1 — 

### \ > .

— 1 — , 

### \

""^ ^ w PtNo . 1

2 3 4 5 6 7 

# N

^ C G

35.5 0 34.5 0 34.5 0 34.8 0 37.3 0 45.0 0 45.0 0 

# X ^

^

— 1 

# N

..• ^

— 1 — Weigh t

4570 0 4825 0 5400 0 5450 0 5450 0 4960 0 4400 0



# V 

# X

1 6 |

-7 |



### 3 3 3 4 3 5 3 6 3 7 3 8 3 9 4 0 4 1 4 2 4 3 4 4 4 5 4 6 C G ( % 

### MAC ) \, .Pag e 3 3 

### ^ A12E A VI I - Mode l GV-S P (Transpor t Category) . Approve dAugus t 14 . 200 3 Th e Gulfstrea

mGV-S P i s th e sam

e a s the Gulfstrea

mG V excep t fo r the followin g differences : • A Honeywel l Advance dFlight Deck Displa y Suite t o improv e flight

cre w situationa

l awarenes s an

doperationa

l capabilifies , • Airframe aerodynami c improvements , engin e improvements , andoperationa l change s fo

r increase dperformance , rang e an deconomics , • Cabi n mai n entr

y door relocate dforwar

dandsevent

h cabi n windo w pai r

added . • Cabi n improvement s fo r increase dbaggag e space , extemal visibilit y andcomfort . • Mino r

syste mchange s fo

r reliabilit y an dspac e utilization . NOTE : Ther e are tw o variant s o f th e GV-S P (Se e Not

e 8) : (1 ) Th e G550 , whic h i s identica l to tlt e GV-SP , an

d(2 ) th e G500 , whic h ha s areduce dfue

l capacity . Engine s 2 BM W - Roll s Royc e Deutschlan dBR700-710C4-1 1 (FAA Typ e Certificate No . E00057EN ) (EAS A Typ e Certificat e No . E.018 ) Fuel Kerosen e America n

Britis h Canadia n Chines e CI S Frenc h America n British , Canadia n CI S America n Britis h Canadia n French ASTM D 1655-92 , Je t A ASTM D 1655-92 , Je t

A- 1 MIL-DTL-83133 , Grad e JP- 8 GSTU 320.00149943.007-9 7 (RT Type ) GST U 320.00149943.011-9 9 (TS- 1 Type ) DEF . STAN . 91-8 7 DEF . STAN . 91-91 ) CAN/CGSB-3.2 3 G B 6537-9 4 No . 3 GOS T 10227-86 , TS- 1 &R T DCSE A 134/ A JP- 4 Wid e Cut

Typ e (Se e NOTE 5 ) ASTMD661 5 MIL-DTL-5624 (JP

4 Grade ) De f Stan . 91-8 8 CAN/CGSB-3.22-200 1 GOS T 10277-8 6 (Grad e T-2 ) JP- 5 Hig h Flash-Point

Typ e MnL-DTL-562

4 (JP 5 Grade ) De f Stan . 91-8 8 3-GP- 3 DCSE A 144/ A Fuel shal l confor

mto th e specificatio n a s liste dor to subsequent

revision s foun din th e lates t

approve dAirplan e Flight

Manua l (AFM) . Oil . See AF M fo r informatio n on hig h flash poin t fuels . Th e followin g oil s ar

e approve dfo

r us e i n th e engin e an dAPU : 5 Centistoke Typ e Oils : Aeroshel l Turbin e Oil 50 0 Aeroshel l Turbin e Oil 56 0 B P Turb o Oil 219 7 Castro l Aero 500 0 Exxo n Turb o Oi

l 219 7 Exxo n Turb o Oil ^38 0 Mobil Je t Oil II ' Mobi l Je t Oi l 25 4 Mobi l Je t Oi l 29 1 TurboNycoi l 60 0 Royc o 50 0 Royc o 56 0 ^A12E A 

### Pag e 3 4 ^J h T " Oi l (con't )

Engin e Limit s '

— -NOTE : Mixingo f

oil s i s not recommende dfo

r APU . NOTE : Mixing of

oil s i s not recommende dbu t

brand s ma

y b e mixe di f operationall y essential . Oil s o f th e abov e brands , whe

n reclaimedt

o th e approve dstandar

dfo r viscosit y an dgrade , are approve dfo

r use . Oi l shall confom

i t o th e specificatio n a s liste do r to subsequen

t revision s i

n th e lates t approvedAirplane Flight

Manual . Stati c Thrus t

(std . day ) S.L . Takeof f ( 5 minutes ) Maximumcontinuou s Maximumpermissibl e engin e roto r operating ! N l (lo w pressure compressor ) Maximu mTakeof f (se e Note 14) Maximu mContinuou s Maximu mOverspeed(2 0 seconds ) Revers e Thrus t

(3 0 seconds ) N 2 (hig h pressur

e compressor) Maximu mTakeof f (se e Not e 14 ) Maximu mContinuou s Maximu mOverspeed(2 0 seconds ) 100%N 1 equal s 7,43 1 rp

m 100 % N2 equal s 15,89 8 rpm 15,3851b . 14,45 0 lb . peeds : (101.1% ) (101.0% ) (101.5% ) ( 70% ) ( 99.6% ) (98.9% ) ( 99.8% ) 7,51 3 rp m 7,50 5 rp m 7,54 2 rp m 5,20 1 rpm 15,83 4 rpm 15,72 3 rp m 15,86 6 rpm Maximumpermissibl e temperature s (°C) : Turbin e ga s temperatur

e measure da

t nozzl e guid e vane s ahea

dof first lo w stag e pressure turbine : Takeof f (se e Not e 14 ) 900 ° Maximu mcontinuou s 860 ° Maximumprio r

t o star t 150° Maximumovertemperatur

e (2 0 second s limit ) 905 ° Momentar y maximu mdurin g groun dstart s 700 ° Momentar y maximu mdurin g infligh

t restart s 850 ° Oil tem p (minimu mbefor e acceleratin g fo

r T/O ) +20 ° Oil tem p (minimu mfo r starting ) -30 ° Oil tem p (maximum

) 160 ° Fuel inlet temperatur

e t o low pressur e pum

p a t S.L . 54 ° Fue l outle t temperatur

e fromengin e hig h pressure pum

p (unrestricte dmaximum ) 158 ° Fue l outle t temperature , H

P pum p maximu m(1 5 min . limit) 165 ° Fuel inlet temperatur

e (minimum) -40 ° Blee dExtractio n EP R= P50/P2 : The amount s o f blee dextractio n fromstage s 5 an d8 , respectively , are relate dto th e cor

e entr y mas s flow, W26 . Th e amoun t o f fa n bleedextractio n i s relate dto th e fa

n enfr y mas s flow, WIA . Powe r Rang e Idl e t o 1.0 6 EP R 1.0 6 t o 1. 3 EP

R Abov e 1. 3 EP

R Auxiliar y Powe r Uni t (APU ) Norma l Flo w (% ) Stag e 5 

### **** * 4. 3 4. 2 Stag e 8

7. 7 4. 1 

### **** * Fa

n 

### **** * 0. 2 0. 4 Maximu mFlow (% ) Stag e 5 3. 0 8. 2 8. 3 Stag e 8

12. 0 7. 8 

### **** * Fa

n 0. 6 1. 6 1. 8 Allie dSigna

l - Mode l RE22 0 {GV } Rate dOutput

Shaf t Powe r 6 2 hp (continuous ) 7 0 hp ( 5 minutes ) 10 1 h p ( 5 seconds )

### Pag

e 3 5 (X^' T 

# ¥ 2 A12E A AP U (con't )

Airspee dLimit s (CAS )

Maximu mOperatin g Altitud e Maximu mWeigh t (lb. ) Maximu mGenerator

Outpu t Shaf t Spee d12,000 rp m Maximu mExhaus t

Ga s Tem p (EGT ) a t Rate dOutpu t

124 1 ° F (T

j = 14 0 °F) Maximu mAllowabl e Roto r

Spee d48,32 0 rpm(T2 < 115°F ) Maximu mAllowabl e EGT Starting : 192 2 ° F (1050-°C ) [fo r T , < -2 0 ° F (-2 9 °C) , P

j > 6.7 5 psia ] Operating : 135 0 ° F (73 2 °C ) [forT2=140°F(60°C) ] Vmo^m o (Maximumoperaring )

" a Vf e V, ''l o 1e 'me g (mph ) Se e AF M fo r Altitude/Mac h Flight

Operatin g Envelop e (Maneuvering ) (Flap s dow n t o 39° ) (Flap s dow n t o 20° ) (Flap s dow n t o 10° ) (Landin g gea

r operation ) (Landin g gea

r extended ) (Minimumcontro l ground ) (Minimumcontro l air) (KCAS ) 23 7 mp h 19 6 mp h 25 3 mp h 28 8 mp h 25 9 mp h 28 8 mp h 123 mp h 12 9 mp h 20 6 knot s

17 0 knot s 22 0 knot s 25 0 knot s 22 5 knot s 25 0 knot s 10 7 knot s 11 2 knot s 51,00 0 fee t Aircraf t S/ N 500 1 & Sub s (als o G550 ) 500 1 & Sub s wit

h ASC10(G500 ) Max . Zer o Fue l 54,50 0 54,50 0 Max . Ram

p 91,40 0 85,50 0 Max .

Take-Of f 91,00 0 85,10 0 Max .

Landin g 75,30 0 75,30 0

Datum M.A.C . Fue l Capacit y

Oi l Capacit

y

Seria l No . Eligibl e C . G . Envelop e For weigh t andbalanc e purposes , th e zer o datumi s 4 5 inche s forwar do f th e ji g poin

t a t th e centerlin e of

th e airplan e in th e nos e whee l well . 171.1 9 in . (L.E . of

M.A.C . = Fuselag e Statio n 524.74 ) Gravit y or Pressur e Fueling : Tota l Usabl e Arm * GV-S P (G550 )

41,4891b . 41,3001b . + 558. 5 GV-S P (G500 ) 35,38 9 lb . 35,20 0 lb . + 551. 9 Fue l weight s base dupo n fiiel densit y o f 6.7 5 lb . pe r

gal . *Ar mbase do n groun dstati c attitud e (-1.5 ° FRL ) 25. 7 lb./27. 4 U.S . pint s 10. 4 lb./ l 1.0 U.S . pint s Tota l engin e oi l capacit

y (eac h engine) : Hispano-Suiz aGearbo x Usabl e Oi l (Ar m= +785.00 ) Oil weight s base dupon oi l densit y o f 7, 5 lb . pe r gal . Se e NOT E 1 fo r syste moil . Capacitie s show n ar

e fo r engin e oi l tankag e only . Tota l engin e oi l i s a

n additiona

l 9, 5 lb , pe

r engine . AP U oi l 9.00 lb./9. 6 U.S . Pint s (An n = +782.5 ) S/ N 500 1 an

dsubsequent . Se e figure o n next

pag e fo r GV-S P Zero Fue

l Gros s Weigh'^vs , Cente

r o f Gravit y (S/ N 500 1 andsubsequem) .A12E A 

### Pag e 3 6 ^j-i> T 

# f

GV-S P Zer o Fue l Gros s Weigh t Cente ro f Gravit y Envelop e

(Fo rS/N 500 1 an d Subsequent ) 5 6 5 5 5 4 5 3 52 § 5 1 o 

# rs o

. c 

### 'a > 5 4 9 ( 0 (A O 

### §4 8 0 ) 3 11 . 

### § 4 7 N 

### 4 6 4 5 44 4 3 4 2 

# r

— 1 — ,- i 

### 3 I

2 - 4 / "

1 

### \

— 1 — 

### \ 

# [ 1 

# v ^

! • 1 

### b

" ^ 

# S 

# N

1 , 

# V >

1 

# N

-** ^

— 1 — 

### V 

### RNo . 

### 1

2 3 4 5 6 7 \

^

1 

### C G

35.5 0 34.5 0 34.5 0 34.8 0 37.3 0 45.0 0 45.0 0 

### \ X 

# N

— \ — 

### Weigh t

4570 0 4825 0 5400 0 5450 0 5450 0 4960 0 4400 0 

# V \

1 

# H

(7 -

— i — 

### 333 4 3 5 3 6 3 7 38394 0 41424344454 6 CG(%MAC )Pag e 3 7 

# 6i5" f A12E A VII I - Mode l GIV- X (Transpor t Category) . Approve dAugus t 12 , 200 4 Th e Gulfstrea

mGIV- X i s th e same a s th e Gulfstrea mGIV excep t

fo r th e followin g differences : • A Honeywel l advance dflight dec k displa y suit e (commo n wit

h th e GV-SP ) t

o improv e flight

crew situational awarenes s an

doperationa

l capabilitie s Airfram e nos e commo n wit

h the GV-S P Airfram e aerodynami c improvement s an dengin e improvement s fo r increase drang e an

dpayload Cabi n mai n entr

y door relocate daf

t an dfuselag e 1 2 inc h extensio n incorporate d Ta y 61 1 engin e replace dwit

h derivativ e Ta

y 611-8C . Adde dengin e FADEC Redesigne dthrus t

reverser , nacell e andpylo n Syste mimprovement s Electrical powe

r generatio n (commo n wit

h GV-SP ) Dua l digita l cabi n temperatur

e contro l an

dpressurizatio n (commo n wit h GV-SP ) Nos e landin g gea

r (commo n wit

h GV-SP ) Replace dAP

U wit h Honeywell 36-15 0 AP

U Redesigne dflap/stab actuatio n syste mwit h digital contro l Redesigne dmai n landin g gea r wheel s andbrake s Adde dflight

contro l systemhard-over

protectio n syste m NOTE : Ther

e are tw o variant s of

th e GIV- X (se e Not e 8) : (1 ) Th e G450 , whic h i s identica l t o th e GIV-X , and(2 ) th e G350 , which ha s areduce dfiiel capacity . Engine s 2 Roll s Royc e Ta y Mar k 611-8 C (FA

A Typ e Certificat

e No . E25NE ) (EASA/LB A Typ e Certificat e No . 6327 ) Fue l America n Britis h Canadia n Chines e CI S French Kerosen e

ASTM D 1655 , Je

t A ASTM D 1655 , Je

t A- 1 MIL-T-83133 , Grade JP8 * MIL-DTL-83133 , Grade JP 8 DE F STA N 91-8 7 DE F STA N 91-9 1 CAN/CGSB-3.2 3 GB 6537-9 4 No . 3 GOS T 10227-86 , T-1 , TS- 1 & R T DCSE A 13 4 JP- 4 Wid e Cut

Typ e (Se e NOT

E 5 ) America n ASTM D 1655 , Jet B ASTMD661 5 MIL-PFR-5624 , Grad e JP4 * MIL-DTL-562 4 Grad e JP4 Britis h Canadia n America n Britis h Canadia n Frenc h DE

F STA N 91-8 6 CAN/CGSB-3.2 2 JP- 5 Hig h Flas h - Poin

t Typ e MIL-DTL-5624 , Grade JP 5 MIL-PRF-562 4 Grade JP 5 DEF.STAN.91-8 8 CA N 3-GP-3.2 4 • DCSE A 14 4 Fue l shal l confor

mto th e specificatio n a s liste dor to subsequent

revision s foun di n th e lates t

approve dAirplan e Fligh

t Manual . *Wit h fue l syste micin g inhibito r

(FSII) . Maximu

mconcentratio n 0.15 % b y volume . DER D 245 1 Issu e 2 and3 MIL-I-27686E . o r an y exac t equivalent V, .A12E A Oi l Pag e 3 8 

# f . n " Th e followin g oil s ar

e approve dfo

r us e in th e engin e an

dAPU : 3 Centistoke (Typ e I ) Aeroshel l Turb o Oi

l 39 0 Casfro l 32 5 Engin e Oil ESSO/Exxo n Turb o 238 9

Engin e Limits 5 Centistoke (Typ e II ) Esso/Exxo n Turb o Oi

l 238 0 Mobi l Je t Oil I I Mobil Jet Oi l 25 4 Castro l Aero 500 0 Aeroshel l Turbin e Oi

l 50 0 Royc o Turbin e Oi

l 50 0 NOTE : Mixin g o f

oil s i s no t recommende dfo

r APU . NOTE : Mixin g of

oil s i s no t recommende dbu t

brand s ma

y b e mixedi f operationall y essential . Oil s o f the abov e brands , when reclaime dt o th e approve dRolls-Royc e standar dfo r viscosit y an dgrade , are approvedfo

r use . Oil shall confor

mt o the specificatio n a s liste do r t o subsequent

revision s i

n the lates t approve dAirplane Fligh

t Manual . Stati c Thrus t

(std . day ) S.L . Rate dTakeof

f (Se e Not e 14 ) Rate dMaximu

mcontinuou s 13,8501b . 12,4201b . Maximumpermissibl e continuou s roto r operatin g speeds : N l (lo w compressor) (95.5% ) 8,01 5 rp m N 2 (high compressor) (97.5% ) 12,17 2 rp m Maximumpermissibl e temperature s (°C) : Turbin e ga s tem

p measureda

t nozzl e guid e vane s ahea

do f first low stag e pressur e turbine : Takeof f (Se e Not e 14 ) Maximu mcontinuou s Momentar y maximu mdurin g groundstart s Momentar y maximu mdurin g airstart s (relights ) Maxiinu mover-temperatur e (2 0 secon dlimit ) Oi l tem p (minimu mfo r starting ) Oi l tem p (maximum) Oi l tem p (1 5 minut

e limit) Fue l inlet tem p t o engin e high pressure pum p Fuel inle t temperatur

e (1 5 min . limit) MaximumPermissibl e Air Blee dExtractio n 7t h Stag e HP C Bleed 12t h Stag e HPC Bleed(ma

x continuou s an dbelow ) HP C BleedTota

l (ma x continuou s andbelow ) Fa n Blee d 800 ° 715 ° 700 ° 780 ° 820 ° -40 ° 105 ° 120 ° 95 ° 130 ° 7. 0 lb./se c 6. 9 lb./se c 10.01b./se c 10. 5 lb./se c Auxiliar y Powe r Uni t (APU ) Honeywel l 36-15 0

Maximumpermissibl e exhaus t ga s temperature - U p t o 60 % rp

mdurin g star

t . 985° C 60%-100 % durin g star

t ' 985°Cto757° C (linea r decrease ) Runnin g 757° C Maximu mrotor spee d- al l condition s 107 % AP U altemato r

loa dratin g 40Ky a AP U rate doutpu t

shaf t powe r « 6 1 h p (wit h 62. 4 lb . per

min . blee dai

r an dambient

tem p o f 103°F)^ -

### Pag

e 3 9 A . S 1 A12E A Airspee dLimit s (CAS )

Maximu mOperatin g Altitud e MaximumWeight

(lb. ) Vjjjg/Mffi Q (Maximumoperating ) Se e AF M fo r Altitude/Mac h Flight

Operatin g Envelop e V j (Maneuvering ) Vf g (Flap s dow n t o 39° ) (Flap s dow n to 20° ) (Flap s dow n to 10° ) (Landin g gea

r operation ) (Landin g gea

r extended ) (Minimu mcontro l ground ) (Minimu mconfrol air , takeoff ) (Minimu mcontro l air , landing ) V , ^l o l e V Vmcg mc a Vmcl 23 5 mph 19 6 mp h 25 3 mp h 28 8 mph 25 9 mph 28 8 mp h 12 5 mp h 12 2 mp h 11 4 mph 20 6 knot s

17 0 knot s 22 0 knot s 25 0 knot s 22 5 knot s 25 0 knot s 10 9 knot s 10 6 knot s 9 9 knot s 45,00 0 fee

t Aircraf t S/ N 400 1 andsub s 400 1 andsub s wit

h AS C 00 4 (G350 ) 400 1 andsub s wit

h AS C 01 6 (G45 0 only ) Max . Zero Fuel 49,00 0 49,00 0 49,00 0 Max . Ram

p 74,30 0 71,30 0 75,00 0 Max .

Take-Of f 73,90 0 70,90 0 74,60 0 Max .

Landin g 66,00 0 66,00 0 66,00 0

Datum M.A.C . Fue l Capacit y Fo r weigh t andbalanc e purposes , th e zero datumi s 2 7 inche s af t o f th e ji g poin

t a t th e centerlin e o f

th e airplan e i

n the nos e wheel well o r

20 6 inche s forwar

do f Fuselag e Statio n 206 . 166.2 2 in . (L.E . of

M.A.C . = Fuselag e Statio n 387.7 ) Gravit y o r Pressure Fueling : Tota l Usabl e Arm * GIV- X (G450 )

29,60 5 l b 29,50 0 lb . +430. 4

Oi l Capacit y

Seria l No . Eligibl e C G Envelop e Fuel weight s base dupo n fue l densit y o f 6.7 5 lb . pe

r gal . *Ar mbase do n groun dstati c attitud e (-1.5 ° FRL ) Tota l engin e oi l tan

k capacit y 13. 5 lb./14. 4 U.S . pint s (eac h engine ) Usabl e engin e oi l tan

k capacit y 10. 1 lb./10. 8 U.S . pint s (eac h engine ) (Ar m= +582.00 ) Oil weight s base dupo n oi l densit y o f 7. 5 lb . pe r gal . Capacitie s show n abov e ar e fo r engin e oil tankag e only . Tota l engin e oi l i s 2 7 lb/28. 8 US pint s pe r engin e Se e NOT E 1 fo

r syste moil . Usabl e APU oi l 5. 7 lb./6. 0 U.S . Pint s (Ar m= +620.0 ) S/ N 400 1 andsubsequent . Se e figur e on next pag e fo r the GlV- X Zer

o Fue l Gros s Weigh t

vs . Cente r o f Gravit y envelop e (S/

N 400 1 andsubsequent) .A12E A Pag e 4 0



### GIV- X Zer o Fue l Gros s Weigh t Cente ro f Gravit y Envelop e

(Fo rS/ N 400 1 an d Subsequent )Pag e 4 1 

### ^\-.~ \ A12E A Dat aPertinent

t o Al l Model s Excep t

a s Indicate d Levelin g Mean s Minimu mCrew Maximu mPassenger s Baggag e o r

Carg o Limitation s Longitudinal : Lug s a t right nos e wel l door

longero n ST

A 61. 5 & 72. 5 Lateral : Lug s on rea

r fac e o f bulkheadST

A 44. 5 i n nos e wheel well . 2 (Pilo t an dCo-Pilot ) 1 9 - hmite db y emergenc y exi t requirement s Cabi n Floo r Aircraf t S/ N 1 thr u 29 9 and31 6 andsubsequent , includin g 775 , excep t 24 9 & 252 : Main cabi n floor

fuselag e statio n 19 3 t o 321.5 . Dea dweigh t carg o loadin g maximu

m unifor mloa dove r entir e widt h o f floor shal l b e 4 9 lb . per

square foot . Maximu

m unifor mloa dwit h a20-inc h clea

r aisl e dow n th e middl e shal l b e 9 8 lb . pe r square ft. Maximumdeadweight , carg o loa do n on e isolate dsquare foot , a t leas t 3 0 inche s from another load , shall b e 26 0 lb. , excep t in th e middl e aisl e wher e i t shal l b e 184 lb . Aircraf t S/ N 249 . 252 , 30 0 thr

u 315 : Main cabi n floor

fuselag e statio n 19 3 t o 213 . Dea dweight carg o loadin g maximu

m unifor mloa dove r entir e widt h o f floor shall b e 2 0 lb . pe

r square foot . Maximum unifor mloa dwit h a20-inc h clea

r aisl e dow mth e middl e shal l b e 4 0 lb . pe r square foot . Maximumdea

dweight , carg o loa

don on e isolate dsquare , a t leas t 3 0 inche s fro

m another load , shal l b e 26 0 lb. , excep t i n th e middl e aisl e where i t shal l b e 18

4 lb . Mai n cabi n floor

fuselag e statio n 21 3 t o 321.5 . Dea dweigh t carg o loadin g maximu

m unifor mloa dove r entir e widt h o f floor shal l b e 4 9 lb . per

square foot . Maximu

m unifor mloadwit

h a20-inc h clea

r aisl e dow n th e middl e shal l b e 9 8 lb . pe r square foot . Maximu

mdea dweight , carg o loa

do n on e isolate dsquare foot , a t leas t 3 0 inche s fro manothe r load , shall b e 26 0 lb. , excep t in th e middl e aisl e wher

e i t shall b e 18

4 lb . All Aircraft . S/

N 1 an dsubsequent : Main cabi n floor

fuselag e statio n 321. 5 to 498 . Dea dweight carg o loadin g maximu

m unifor mloadin g shal l b e 10

0 lb . per square fcxjt

. Main cabi n floor

fuselag e statio n 49 8 to 539.75 . Maximumunifor mloadin g shal l b e 6 5 lb . pe

r squar e foot . MaximumBaggag e (al l model s excludin g GV . GV-SP) : Compartment

af t o f fuselag e statio n 539.7 5 t o bulkheado r pressure dome . Capacit y - 2,00 0 lb . les s an

y weight adde di n equipment

ba y Maximumfloor

loadin g - 6 5 Ib./sq . ft. CG . - ST A 56 5 fo r 200 0 lb . I f

furthe r aft , correspondin g reductio n i n capacit y required . Main cabi n floor

loadin g limitations . G

V S/ N 50 1 andsubsequent : Main cabi n floor

fuselag e statio n 22 9 t o 426 : Dea dweight carg o loadin g maximu

m Unifor mloa dove r entir e widt h o f floor shal l b e 4 9 Ib/ft^ . Maximumunifom i loa dwit h a 2 0 inc h clea

r aisl e down the middl e shal l b e 9 8 lb/ft" . Maximu mdea dweight carg o loa d o n on e isolate dsquar

e foot , a t leas t 3 0 inche s fro

manother load , shal l b e 20 0 lb. , excep t in th e middl e aisl e wher

e i t shal l b e 18 7 lb . Main cabi n floor

fuselag e statio n 42 6 t o 632 : Dea dweight carg o loadin g maximu

m unifor mloadin g shall b e 10

0 Ib/ft^ . Main cabi n floor

fuselag e statio n 63 2 t o 684 : Ma x unifor mloadin g shal l b e 6 5 Ib/ft^ . MaximumBaggage . G

V S/ N 50 1 andsubsequent : Compartment

af t o f fuselag e statio n 684.0 0 t o pressure bulkhead : Capacit y - 250 0 lb . les s an

y weight adde din equipment

ba y Maximumfloor

loadin g - 6 5 Ib/ft

^ Approve dsmok

e detectio n syste mrequired .A12E A Pag e 4 2 n b' ^ Main cabin floor

loadin g limitations . GV-S P S/ N 500 1 andsubsequent : Main cabin floor

fuselag e statio n 20 5 t

o 426 : Dea

dweight carg o loadin g maximu

m unifor mloa dove r entir e widt h o f floor shall b e 4 9 lb/ft" . Maximu munifor mloa dwit h a 2 0 inc h clea

r aisl e down th e middl e shall b e 9 8 lb/ft" . Maximumdea dweigh t carg o loa d on on e isolate dsquar

e foot , a t leas t 3 0 inche s fromanother

load , shal l b e 200 lb. , except i n th e middl e aisl e where i t shall b e 187 lb . Main cabi n floor fiiselage statio n 42 6 t o 632 : Dea

dweight carg o loadin g maximu

m unifor mloadin g shall b e 10

0 Ib/ft ^ Main cabi n floor

fiiselage statio n 63 2 to 684 : Maximumunifor mloadin g shall b e 65 Ib/ft ^ Maximumbaggage . GV-S P S/ N 500 1 an dsubsequent : Compartment

af t o f fuselag e statio n 684.0 0 t

o pressure bulkhead : Capacit y - 250 0 lb. , les s any weigh t adde di n equipment

ba y Maximumfloor

loadin g - 6 5 Ib/ft

^ Approve dsmok

e detectio n systemrequired . Mai n cabi n floor

loadin g limitations . GIV- X S/ N 400 1 an dsubsequent : Main cabi n floor

forwar do f th e overwin g pressure floor (Fuselag e statio n 14

5 to 321.5) : Dea dweight carg o loadin g maximu

munifor mloa dover entire widt

h o f floor i s 4 9 pound s pe r

squar e foot . Maximu

munifor mloa dwit h a20-inc h clea

r aisl e dow n th e middl e i s 9 3 pound s pe

r square foot . Maximu

mdea dweight loa don on e isolate dsquar e foot , a t leas t 3 0 inche s fromanothe

r load , i s 26 0 pound s excep t i n th e center

aisl e wher

e i t i s 184 pounds . Overwin g pressure floor (Fuselag e statio n 321. 5 to 498) : Deadweigh t carg o maximumunifor

mloadin g i s 10

0 pound s pe

r square foot . Mai

n cabin floor sfructur e af t o f th e overwin g pressur

e floor (Fuselag e statio n 49 8 t o 539.75) : Dea d weigh t carg o maximumuiufor

mloadin g i s 6 5 pound s pe r square foot . Maximumbaggage . GIV- X S/ N 400 1 an dsubsequent : Compartment

af t o f fuselag e statio n 539.7 5 t o 59 6 (fla t pressur e bulkliead) . Capacit y - 2,00 0 lb . les s an

y weigh t addedi n equipment

ba y Maximumfloor

loadin g - 6 5 Ib./sq . ft. CG . - ST A 56 5 fo r 200 0 lb . If

furthe r aft, correspondin g reductio n in capacit y required . Othe r Operatin g Limitation s Th e aircraf t mus t b e operate din accordanc e wit h th e lates t

FA A approve drevisio n t

o the Airplan e Flight

Manual . Th e Model GV-S P Airplan e Fligh t Manua l i s GAC-AC-G550-OPS-0001 . Th e Model GV-S P (G550 ) Airplan e Fligh t Manua l i s GAC-AC-G550-OPS-000I . Th e Mode l GV-S P (G500 ) Airplane Fligh t Manua l i s GAC-AC-G500-OPS-0001 . Th e Mode l GIV- X Airplan e Fligh t Manua l i s GAC-AC-G450-OPS-0001 . Th e Mode l GFV-

X (G450 ) Airplane Fligh

t Manua l i s GAC-AC-G450-OPS-0001 . Th e Mode l GIV- X (G350 ) Airplan e Fligh t Manua l i s GAC-AC-G350-OPS-0001 .Pag e 4 3 

# < r A12E A

Contro l Surfac e Movement s Model s G- l 159 . G- l 159 A an dG- l 159B Elevator s Elevator trimta b Rudde r Rudde r trim Aileron s Ailero n frim Flap s Speedbrakes : U p 24 ° (+1/2°,-1/2° ) U p 10°(+l°,-r ) Righ t 22 ° t o 22.5 ° Righ t 7.5°(+l°,-l° ) U p 10°(+1°,-1° ) U p 15 ° (+4° , -4° ) Airplane s wit

h fou r pane l spee dbrake s Airplane s wit

h si x Groundspoiler (all spoilers ) Right 43 ° (+3° , -3° ) pane l spee dbrake s Right 26 ° (+2° , -2° ) U p 55 ° (+3° , -3° ) Down Down Lef t Lef t Dow n Down Down Lef t Lef t 13°(+0°,-l° ) 20°(+l°,-l° ) 22 ° t o 22.5 ° 7.5°(+l°,-l° ) 10°(+r,-l° ) 15 ° (+4°,-4° ) 39 ° (+0° , - 1 1/2° ) 43 ° (+3° , -3° ) 26 ° (+2° , -2° ) Horizonta l stabilizer

trave l rang e - Leadin g edg e down : G-1159 ; S/

N 1 th m100 , includin g 775 , without AS C No . 81 : G- l 159 ; S/

N 1 thr u 10 0 wit h AS C No . 81 , an

dS/ N 10 1 thr u 29 9 G- l 159A ; S/

N 30 0 andsubsequent , includin g S/ N 24 9 and252 : G-1159B : Mode l G-IV : Elevator s Elevato r tri mta b Rudde r Rudde r frim Aileron s Ailero n trim Flap s Spee dbrake s Groundspoiler (all spoilers ) U p U p Righ t Righ t Up U p Righ t Up 24 ° (+1/2°,-1/2° ) 8°(+l°,-1° ) 22 ° to 22.5 ° 7.5°(+l°,-1° ) 10°(+1°,-1° ) 15 ° (+4°,-4° ) 26 ° (+2° , -2° ) 55 ° (+4° , -3° ) Down

Dow n Lef t Lef t Dow n Down Down Lef t (0 ° t o -4.5° ) (0 ° t o -5° ) (-l°to-6° ) (-l°to-6° ) 13°(+0°,-r ) 22°(+l°,-1° ) 22 ° t o 22.5 ° 7.5°(+l°,-l° ) 10°(+1°,-1° ) 15 ° (+4° , -4° ) 39°(+0°,- 1 1/2° ) 26 ° ( + 2° , -2° ) Horizonta l stabilizer

trave l rang e - Leadin g edg e down : -1 ° (+1/4° , -1/4° ) to-4.6 ° (+1/4°,-1/4° ) Model s G V andGV-SP : Elevator s Elevato r trimta b Rudde r Rudde r trim U

p U p Right Righ t 24 ° (+1/2°,-1/2° ) 8°(+l°,-1° ) 22 ° to 25 ° 7.5°(+l°,-l° ) Dow n

Down Lef t Lef t 13°(+0°,-1° ) 22°(+r,-1° ) 22 ° t o 25 ° 7.5°(+r,-1° ) Note : Rudder

tri mma y b e offse t (+3° , -3° ) maximuma s require dfo r directional tri mwit h th e cockpi t

tri mkno b an

drudde r pedal s re-reference dt o zero . Se e PC S Riggin g Procedure s Repor t GV-MS-51 . Aileron s Up ir(+l°,-2° ) Down 11°(+1°,-2° ) Ailero n trimUp ] 5 ° (-^4°,-4° ) Dow n 15 ° (+4°,-4° ) Flap s Dovr a39 ° (+1°,-!° ) Spee dbrake s (Right

& Left ) 4 Outb' dPanel s (Flight

Spoilers ) U p 30 ° (+2° , -8° ) 2 Inb' dPanel s (Groun dSpoilers ) ' Up 30 ° (+2° , -5° ) Groun dspoiler s (all ) Up 55 ° (+4 ' Horizonta l stabilizer fravel rang e - Leadin g Edg e Travel : Norma l Operatio n -1.5 ° (+1/4° , -1/4° ) t o -4.6 ° (+1/4° , Emerg . Stab . Mode -1.25 ° (+1/4° , -1/4° ) to'-4.6 ° (+1/4 ° 

### v. . -5° )

1/4° ) -1/4° )A12E A Pag e 4 4 

# f^-Y Mode l GIV-X : Elevator s U p Elevator tri mta b U

p Rudde r Righ

t Rudde r tri mRigh

t Aileron s U p Ailero n tri mU

p Flap s Speedbrake s (Righ

t & Left ) 4 Outb' dPanel s (Flight

Sp ) 2 Inb' dPanel s (Groun dSp ) Groun dspoiler s (all ) 24 ° (+1/2° , • 8°(+r,- 1 22 ° t o 25.0 ° 1/2° ) 

### ' ) 7.5 ' 10 ° 15 ° '(+1 ' (+1 ° (+4 ° ,-1° ) -1° ) -4° ) Down

Dow n Lef t Lef t Dow n Dow m Down 

### i3°(+o°,-r ) 22°(+l°,-1° ) 22 ° t o 25.0 ° 7.5°(+l°,-1° ) 10 ° (+r,-r ) 15 ° (+4°,-4° ) 39°(+0°,- 1 1/2° ) U p 26 ° (+2 ° -5° ) U p 26 ° (+2 ° -2° ) U p 55 ° (+4° , -3° )

' (+1/4° , -1/4° ) Horizonta l stabilizer fravel rang e - Leadin g edg e down : to-4.6 ° (+1/4°,-1/4° ) Certificatio n Basi s Model G- l 159 ; S/ N 1 thr u 299 . an d775 : CA R4 b date dDecembe

r 31 , 1953 , includin g Amendment s 4b- l thr u 4b-14 , Specia

l Regulation s SR422 B an

dSR450A , an

dSpecia l Condition s in Attachmen t A o f FA A letter t o Grumma

n dated Septembe r 27 , 1965 , plu s FA

R25.132 5 (effectiv e Februar y 1 , 1965) ; 25.17 5 (effectiv e Mar . 1 , 1965 ) i n lie u o f 4b . 155(b) , an

dexemption : No . 695A , CA R4b.437 , "Fuel Jettisonin g System, " FA RPar t 3 6 par . 36.1(c)(2 ) fo

r airplan e S/

N 1 thr u 165 an d77 5 approve dfo

r a62,00 0 lb . takeofl ' weight an dFA RPar t 3 6 Appendi x C fo

r airplan e S/

N 16 6 thr u 29 9 excep t

249 , 252 , an

d775 . Typ e Certificat

e A12E A issue dOctober

19 , 1967 . Dat

e o f applicatio n fo

r Typ e Certificat

e wa s Jun e 24 , 1964 . Complianc e wit

h the following optiona

l requirement s ha s bee

n established : Datacoverin g ditchin g requirement s o f 4b.361 , includin g 4b.362(d ) and4b.742(e ) (but excludin g 4b.64 5 an d4b.636 ) ar

e approved . Whe

n th e operatin g rule s requir e emergenc y ditchin g equipment complianc e wit

h 4b.64 5 an

d4b.64 6 mus t

b e demonstrated . Gulfstrea mRepor t 1159 - GER- 7 entitle d"Outfitting Requirement s fo r FA A Certificatio n fo

r Ditching " provide s a

n acceptabl e mean s fo

r showin g complianc e wit

h 4b.64 5 an

d4b.646 . Airplan e Flight

Manua l Revisio n 1 3 must

b e incorporated . Equivalent

Safet y Findings : (1 ) CA R4b.l6 0 an

dFA R25.201 , Stall Demonstratio n (2 ) CA R4b.362(b)(4 ) andFA

R25.807(a)(4 ) Emergenc y Exit s Model G-1159A ; S/

N 249 . 252.30 0 an dsubsequent : Par t 2 5 o f th e FA Reft'ectiv e Febraar

y 1 , 1965 , andAmendment s 25- 2 throug h 25-8 , 25-10 , 25-12 , 25-1 6 throug h 25-22 , 25-24 , 25-26 , 25-27 , 25-2 9 through 25-34 , 25-37 , 25-4 0 (a s applicabl e t o a ne w AP U installation) ; FA

R25.130 9 o f

Amendmen

t 25-4 1 an dFA R25.132 9 of

Par t 2 5 dated Februar y 1 , 196 5 (a s applie dt o ane w autopilo t installation) ; FA

R25.99 4 (crashworthines s fue l systemcomponents) ; an

dFA R25.58 1 (lightain g protection ) o f Amendmen

t 25-23;Specia

l FA R2 7 throug h Amendmen

t 2 (fiie l ventin g emission) ; FA

R3 6 through Amendmen

t 8 (nois e , requirements) .

Th e specia

l condition s containe di n th e FAA' s letter t o Grumma

n date dSeptembe

r 27 , 1965 , applicabl e t

o th e Gulfstrea

mModel G- l 15 9 airplane , ar e als o applicabl e to th e Gulfstrea mMode l G- l 159 A airplane , excep t

tha t referenc e t o "4b.450 " in th e "Coolin g Systems " specia l condition s i s replace dby "FA

R25.104 3 containe di n Par t 2 5 o f th e FA Reffectiv e Februar

y 1 , 1965. " I

n addition , specia

l condition s pertainin g to dynami c gus t load s containe di

n th e enclosure to FA

A AEA-21 2 lette

r date dJuly 22,1980 . Complianc e wit

h th e following Optiona

l Requirement s ha s bee n established : Datacoverin g ditchin g requirement s o f 25.801 , includin g 25.807(d ) an d25.1585(a) (bu

t excludin g 25.1411 ) ar

e approved . Whe

n th e operatin g rule s requir e emergenc y ditchin g equipment , complianc e wit

h 25.141 1 and25.141 5 mus t b e demonstrated . Gulfsfrea mRepor t 1159-GER- 7 entitle d"Outfittin g Requirement s fo r FA A Certificatio n fo

r Ditching " provide s a

n acceptabl e mean s fo r showin g complianc e wit

h 25.141 1 an

d25.1415 . \ .Pag e 4 5 

# ^ T A12E A Equivalen t Safet y Findings : (1 ) CA R4b.l6 0 andFA

R25.201 , Stall Demonstratio n (2 ) CA R4b.362(b)(4 ) andFA

R25.807(a)(4 ) Emergenc y Exit s (3 ) FA R25.773(b ) (2) , Direc t

Visio n Windo w Mode l G- l 159B ; S/

N 1 throug h 299 . includin g 775 : Fuselage , Empennage , Autopilo t andNoise : Ca r 4b , date dDecember

31 , 1953 , includin g Amendment s 4b- l thr u 4b-14 , Specia

l Regulatio n SR450A , an

dSpecia l Condition s in Attachment A o f FA A lette r to Grumma

n date dSeptembe

r 27 , 1965 , plu s FA

R25.132 5 (effectiv e Febniar y 1,1965) ; FA

R25.17 5 (effectiv e March I , 1965 ) in lie u o f CA R4b . 155(b) ; FA

R36.7(d)(3)(ii) ; CA

R4b.450 , Coolin g Systems . Wing Assembly , Landin g Gear , Fuselag e an dEmpennag e Modifications : FA R25 , effectiv e Februar

y 1,1965 , Amendment s 25- 2 thr u 25-8 , 25-10 , 25-12 , 25-1 6 thr u 25-22 , 25-24 , 25-26 , excep t FA R25.1203(b)(3) , 25-27 , 25-2 9 thr a25-31 , 25-34 , 25-37 , 25-4 0 (a s applicabl e to anew AP U installation) ; FA

R25.130 9 o f Amendmen

t 25-4 1 andFA

R25.132 9 o f

FA R2 5 date dFebruar

y 1 , 1965 ; FA

R25.99 4 (Crashworthines s Fuel SystemComponents) ; andFA R25.58 1 (Lightnin g Protection ) o f

Amendment

25-23 ; Specia

l Federa l Aviatio n Regulatio n 27 through Amendmen

t 2 (Fue l Ventin g Emissions) . Th e specia

l condition s containe din th e FAA' s letter to Grumma

n date d Septembe r 27 , 1965 , applicabl e to Gulfstrea mModel G-115 9 airplane , ar e als o applicabl e to th e Gulfsfrea

mModel G- l 159 B airplane . I n addition , the specia

l conditio n pertainin g t o dynami c gus t loads , containe din th e enclosure to FA A letter AEA-212 , date dJul y 22 , 1980 , i s applicabl e to th e Mode l G- l 159 B airplane . Complianc e wit

h th e followin g Optiona

l Requirement s ha s bee n established : Data coverin g ditchin g requirement s o f 4b,361 , includin g 4b,362(d ) and4b,742(e ) (bu t excludin g 4b,64 5 and4b.646 ) are approved . Whe n operatin g rule s requir

e emergenc y ditchin g equipment , complianc e wit h 4b,64 5 and4b,64 6 mus t

b e demonstrated . Gulfstrea mRepor t 1159-GER- 7 entitle d"Outfittin g Requirement s fo r FA A Certificatio n fo r Ditching " provide s a

n acceptabl e mean s fo

r showin g complianc e wit

h 4b,64 5 an

d4b.646 . Equivalen t Safet y Findings : (1 ) CA R4b.l6 0 an dFA

R25.201 , Stall Demonsfration (2 ) CA R4b,362(b)(4 ) an

dFA R25,807(a)(4 ) Emergenc y Exit s Model s G-1159 . G1159A . an dG-1159B : FA R25,771 , Amendment

4 . A lockabl e door

i s no t require dbetwee n th e pilo t andpassenge

r compartments . Mode l G-fV ; S/ N 100 0 andsubsequent : FA RPar t 25 , effectiv e Februar

y 1 , 1965 , includin g Amendment s 25- 1 through 25-56 , excep t fo r th e followin g section s whic h ar e limite dto showin g complianc e wit h th e amendment s indicated : Sectio n 25.10 9 25.57 1 25.67 1 25.807(c)(2 ) 25.81 3 Amendment FA R25 , date dFebruar

y 1 , 196 5 25-2 2 (a s applie s t

o fuselag e andempennage ) FA R25 , date dFebruar

y 1 , 196 5 25-1 5 FA R25 , date dFebruar

y 1 , 196 5 FA R36 , includin g Amendment s 36- 1 throug h 36-12 . SFA R27 , includin g Amendment s 27- 1 throug h 27-5 . Complianc e wit

h th e followin g Optiona

l Ditchin g Requirement s ha s been established : Dat acoverin g ditchin g requirement s o f 25.801 , includin g 25.563 , 25.%)7(d) an d 25.1585(a ) (bu t

excludin g 25.1411 ) ar

e approved . When th e operatin g rule sA12E A Pag e 4 6 

# 1 s > requir e emergenc y ditchin g equipment , complianc e wit h 25.141 1 and25.141 5 mus t b e demonstrated . Gulfstrea mRepor t 1159-GER- 7 entitle d"Outfittin g Requirement s fo

r FA A Certificatio n fo

r Ditching " provide s a

n acceptabl e mean s fo r showin g complianc e wit

h 25.141 1 an d25.1415 . Equivalent

Safet y Findings : (1 ) FA R25.201 , Stal l Demonsfration (2 ) FA R25.729(e)(2) , Landin g Gea r Warnin g Hor

n (3 ) FA R25.773(b)(2) , Direc t

Visio n Windo w (4 ) FA R25.807(a)(4) , effectiv e Februar y 1 , 1965 , Ova

l Emergenc y exi t

Window s wit

h Horizonta l Majo r Axi s (5 ) FA R25.811(d ) and25.812(b) , Emergenc y Exi t Marker , Locator , an

dBulkhead/Divider

Sign s Model GV : S/

N 50 1 an dsubsequent : FA RPar t 25 , effectiv e Februar

y 1,1965 , includin g Amendment s 25- 1 throug h 25-81 , excep t fo r th e followin g section s whic h ar e limite dto showin g complianc e wit h the amendment s indicated : Sectio n 25.10 9 25.807(c)(2 ) 25.81 3 Amendmen t FA R25 , date dFebruar

y 1 , 196 5 25-1 5 FA R25 , date dFebruar

y 1 , 1965 FA R34 , includin g Amendment s 34-1 . FA R36 , includin g Amendment s 36- 1 throug h 36-2 0 Shoulder harnes s on al

l seat s wil l b e i

n lie u o f demonsfratedcomplianc e t o th e tes t requirement s o f

FA R25.562(c)(5 ) an

d(c)(6 ) per

Amendmen

t 25-64 . Complianc e wit

h th e requirement s o f

FA R25.78 5 i

n referenc e to FA

R25.56 2 (c)(5 ) an

d(c)(6 ) nee dnot

b e demonstrate ddu e to thi s concession . Note : Th e certificatio n basi s o f th e G V regardin g 25.56 2 wa s establishe dbase don FA A understandin g tha

t thi s model will no t

operate i n part

12 1 service . Therefore , installatio n o f shoulder hamesse s i

n lieu o f demonstrate dcomplianc e to 25.562(c)(5 ) an d(c)(6 ) applie s onl y to aircraf

t no t engage di n par t 12 1 passenger

carryin g service . I f

th e aircraf

t i s operate din par

t 121 , fiill complianc e to th e requirement s o f 25.56 2 (includin g paragraph s (c)(5 ) an

d(c)(6) ) an

d25.78 5 mus t

b e shown . Complianc e wit

h th e Optiona

l Ditchin g Requirement s ha s bee n establishe da s follows : Dat a coverin g th e ditchin g requirement s o f FAR25;801 , includin g 25.563 , 25.807(e) , and25.1585(a) , bu t excludin g 25.1411 , ar

e approved . When th e operatin g rule s require emergenc y ditchin g equipment , complianc e wit h 25.141 1 an

d25.141 5 mus t

b e demonstrated . Gulfstrea mRepor t 1159 - GER-7 , entitle d"Outfittin g Requirement s fo r FA A Certificatio n fo

r Ditching " provide s a

n acceptabl e mean s fo

r showin g complianc e wit

h 25.141 1 and25.1415 . Specia l Conditions : HIR F (Hig h hitensit

y Radiate dFields ) No . 25-NM-105 , effectiv e September 28 , 1995 . Hig h Altitud e Operation s No . 25-ANM-108 , effectiv e Novembe r 16 , 1995 . NOTE : Th e hig h altitud e specia l conditio n include s pressurizatio n syste mrequirements , a s wel l a s damag e toleranc e requirement s o n th e pressure vessel . Therefore , an y change s t

o th e pressurizatio n syste mor

modification s o r

repair s t o th e pressure vessel mus t

b e approve di

n accordanc e wit

h th e requirement s define din th e specia l condition . Th e damag e toleranc e requirement s i n the specia

l conditio n ar

e specifie di

n term s o f cabi n altitud e tim e history , whic h i s afunction o f th e cabi n lea

k rate . Th e specifie dcabi n altitud e time histor

y requirement

ca n b e me t wit h apressur

e vesse l openin g o f

7. 2 square inche s effectiv e are a(whic h consider s th e appropriate discharg e coefficient assumin g a

n emergenc y descent) . Th e determinatio n o f a n equivalent

crac k lengt h wil l depen dupo n th e particula r locatio n o f

th e crack , th e pressure vesse l configiiratio n in tha t locatiog , th e directio n o f

th e crack , etc . Th e approva

l o f modification s and/or

repair s mus t

tak ^ int o account th e requirement s o f

th e specia

l conditio n andho w the

y apply t o th e p^ticula r

locatio n an

dPag e 4 9 

# 4< i A12E A

* Thes e system s hav e no change s fro mthe basi c GI

V model ; therefore tli e paragraph s remai n a t the origina

l GIV certificatio n basi s an dth e late r amendment

wa s no t adopted . Amendmen

t 25- 0 i s th e original publishe dversio n o f Par t 25 , Februai y 1 , 1965 . * * Unmodifie dstructure remain s in complianc e wit h th e earlie r

amendment

listed . Ne

w o r modifie dstructur e i s i n complianc e wit h th e late r amendment

leve l listed . Par t 34 , Amendmen

t 34- 3 Par t 36 , Amendmen

t 36-2 4 Shoulde r harnes s on all seat s wil l b e in lieu of demonstrate dcomplianc e t o th e tes t requirement s o f §25.562(c)(5 ) an

d(c)(6 ) pe r

Amendment

25-64 . Complianc e t o th e tes t requirement s o f

§25.78 5 i n referenc e t

o §25.562(c)(5 ) an d(c)(6 ) nee dno t b e demonstrate ddu e t o thi s concession . Thes e provision s ar

e acceptabl e fo

r singl e or multipl e occupan

t seatin g system s whic h ar

e forward , aft, or side facing . Note : Th e certificatio n basi s o f th e GFV- X regardin g 25.56 2 wa s establishe dbasedon FA A understandin g tha

t thi s mode l will no t operate i n par

t 12 1 service . Therefore , installatio n o f

shoulder hamesse s i

n lie u o f demonsfrate dcomplianc e t o 25.562(c)(5 ) an

d (c)(6 ) applie s onl y to aircraf t no t engage din part

12 1 passenge r

carryin g service . I

f the aircraf t i s operate di n par

t 121 , ful l complianc e t o th e requirement s o f 25.56 2 (includin g paragraph s (c)(5 ) an

d(c)(6) ) an

d25.78 5 mus t

b e shown . Complianc e wit

h th e Optiona

l Ditchin g Requirement s ha s bee n establishe da s follows : Dat a coverin g th

e ditchin g requirement s o f 1 4 CF RPar t 25.801 , includin g 25.563 , 25.807 an d 25.1585(a) , bu t

excludin g 25.1411 , ar

e approved . When th e operatin g rule s requir e emergenc y ditchin g equipment , complianc e wit h Part s 25.141 1 an

d25.141 5 mus t

b e demonstrated . Gulfsfrea mRepor t no . 1159-GER-7 , entitle d"Outfittin g Requirement s fo r FA A Certificatio n fo

r Ditching" , provide s a

n acceptabl e mean s fo

r showin g complianc e wit

h Part s 25.141 1 an

d25.1415 . FA R25.813(e ) a

t Amendment

25-4 6 i s not

include di n th e certificatio n basis . Specia l Conditions : No . 25-262-SC , HIR

F (Hig h Intensit

y Radiate dFields) . No . 25-180-SC , Enhance dVisio n System(EVS) . No . 25-258-S C Interactio n o f System s an

dStructure . Exemptions : No . 814 2 [FA

R25.901(c)] , Uncontrolle dHigh Thrus t Failure Condition . NOTE : Th e FA

A ha s conclude dtha

t the occurrenc e of

an y unconfrollabl e hig h thrus t failur e condition , or

an y o f th e associate dcausa

l failure s liste din Sectio n 05-50-0 0 o f tli e applicabl e airplan e Maintenanc e Manua l "ma y endange r th e saf e operatio n o f

a n airplane " an

dhenc e ar e reportabl e unde

r FA R121.703 , 125.409 , an

d135.415 . Equivalen t Safet y Findings : (1 ) FA R25.807 , Elliptical Overwin g Emergenc y Exit s wit h aHorizontal Majo

r Axis , TA D ELO S Mem o No . AT5080AT-T-A- 2 (2 ) FA R25.811(d ) and25.812(b) , Emergenc y Exit Marker , Locator , an dBulkhea dDivide r Signs , TA D ELO S Memo . No . AT5177AT-T-C- 1 (3 ) FA R25.841(b)(6) , Cabi n Pressurizatio n - Hig h Altitud e Takeof

f andLandin g Field Elevations , TA

D ELO S Memo No . AT5177AT-T-S-2 9 (4 ) FA R25.85 3 and25.869 , Flammabilit y Substantiatio n fo

r Electrical Equipment , TA D ELO S Mem o No . AT5177AT-T-A- 9 (5 ) FA R25.933 , Flight

Critica l Thrus t Reverser , TA

D ELO S Mem o No . AT5080AT-T-P- 1 Productio n Basi s Model s G- l 159 . G- l 159A . G- l 159B , G-IV . GV-S P andGIV-X : Productio n Certificate No . 23 , issue dJun e 11 , 1968 ; Production Certificate No . 507 , issue dJuly 17 , 1968 ; Productio n Certificate No . 7S0 , issue dSeptembe r 1,1978 ; reissue dSeptember 22 , 1980 ; Novembe r 19 , 1982 ; Augus t

31 , 1987 ; Jun e 11,1997 , an dAugus t 14 , 2003 , andNovembe

r 16 , 2004 , excep t

Model 1159B . See NOT E 7 an dNOTE 8 . '^ ^A12E A Pag e 5 0 ^ i •^• * Equipment The%asic require dequipment a s prescribe di

n the applicabl e airworthines s regulation s (se e Certificatio n Basis ) mus t b e installe di

n th e aircraf

t fo r certification . Approve dequipment i s show n in Grumma

n G- l 15 9 Typ e Design Equipmen t List , 1159-GER-l , o

r Gulfstrea m11 1 G- l 159

A Typ e Desig n Equipmen t List , 1159A-GER-37 , lates t FA A approve drevision . Fo

r th e Model s G-IV , GV , GV S P an dGIV-X , se e th e Illustrate dPart s Catalo g (IPC ) fo r a n approve dequipmen

t listing . I n addition , th e followin g item s o f equipment

ar e required : (a) Whe n a n airplan e i s outfitte dto carr y passengers , a

n FA A approvedpassenger

oxygen systemmus t

b e installed . (b ) FA A Approve dAirplan e Flight Manual . NOTE Weigh t an dBalanc e (a ) Curren

t weigh t an dbalanc e report , includin g lis t o f equipment

include din certificate dempt y weight , an dloadin g instruction s when necessary , mus t b e provide dfo

r eac h airplan e a

t the tim e o f origina l certification . Tli e weight

an dbalanc e repor

t shal l includ e a s par

t o f th e empt y weight , syste mfuel , tota l oi l an dhydrauli c fluid. (b ) Syste mfuel : Th e weight

o f all fiie l require dto fill all line s andtank s u p to zero/readabl e fue

l poin t o n the fue l gage s i n th e mos t critica l flight attitude . 1 . G- l 15 9 airplane s (CA R4b.416) : (i ) S/ N 1 throug h 29 9 without

ti p tanks : Unusabl e fue

l - 12 0 lb . tota l Fue l line s - 4 4 lb . total Systemfue

l - 16 4 lb . Tota l (ii ) S/ N 1 throug h 29 9 havin g tip tank s installe d(AS C 200) : Unusable - 1361b . total Fue l line s - 5 0 lb . tota

l Syste mfue l - 18 6 lb . Tota

l 2 . G- l 159

A andG- l 159 B airplane s (FA R25.959) : (i ) Al l seria l numbers : Unusabl e fuel * - 11 4 lb . tota l Fue l line s - 4 4 lb . tota

l Syste mfuel-1581b . tota

l * Include s 2 6 lb . undrainable . 3 . G-I V airplane s (FA

R25.959) : (i ) Al l seria l numbers : Unusabl e fuel * - 10

5 lb . tota l Fue l line s - 4 5 lb . total Syste mfuel - 1501b . tota

l * Include s 1 3 lb . undrainabl e 4 . G V airplane s (FA

R25.959) : (i ) S/ N 5t) I through 54 9 without AS C 50 : Unusabl e fuel * - 48 0 lb . Fue l line s - 3 0 lb . Syste mfuel-51 0 lb . (ii ) S/ N 55 0 & subs , andS/

N 50 1 through 54 9 wit

h AS C 50 : Unusabl e fuel * - 1891b . Fue l line s - 3 0 lb . Syste mfuel-21 9 lb . •Include s 3 2 lb . undrainabl e 5 . GV-S P airplane s (FA

R25.959) : (i ) S/ N 500 1 an

dsubsequent Unusabl e fuel*-18 9 lb . Fue l line s - 3 0 lb . Syste mfuel-21 9 lb . •Include s 3 2 lb . undrainabl e 6 . GFV- X airplane s (FAR25.959 ) (i ) S/ N 400 1 andsubsequent Unusabl e fuel * - 1051b . Fue l line s - 4 5 lb . Systemfuel - 1501b . *Include s 1 3 lb . undrainabl e ^ _ (c ) Syste moil : Th e weight

o f oi l remainin g i

n th e engin e line s andtank s afte r ^tractin g th e oi lPag e 4 7 

# A ^ 

# •

T A12E A configuratio n bein g modifie do r required . Th e resultin g inspectio n progra mmus t als o consider other applicabl e structural criteria . Exemptions : 25.571(e)(1 ) Birdimpac t Spee d Equivalent

Safet y Findings : (1 ) FA R25.103 , Stal l Speed s define dby Vsl g i n lieu o f Vmi n (2 ) FA R25.341 , JA

RDiscrete Tune dGus t

i n lieu o f Stati c Gus t (3 ) FA R25.807(a)(4) , effectiv e Februar y 1 , 1965 , Ova

l Emergenc y Window s wit h Horizonta l Majo r Axi s (4 ) FA R25.811(d ) and25.812(b) , Emergenc y Exi t Marker , Locator , an

dBulkhead/Divider

Sign s (5 ) FA R25.933 , Preventio n o f

Inadvertent

Infligh t Thrus t Reverser Deploymen

t Model GV-SP : S/

N 500 1 andsubsequent FA RPar t 25 , effectiv e Februar

y 1 , 1965 , includin g Amendment s 25- 1 through 25-98 , wit h th e following exceptions :

• Shoulde

r hamesse s on all seat s wil l b e provide din lieu o f demonstrate dcomplianc e t o th e tes t requirement s o f

FA R25.562(c)(5 ) and(c)(6 ) o f Amendmen

t 25-64 . (Itomplianc e wit

h th e requirement s o f

FAR25.78 5 i n referenc e t o FA R25.562(c)(5 ) an d(c)(6 ) ar e no t demonstrate ddu e to thi s concession . Note : Th e certificatio n basi s o f th e GV-S P regardin g 25.56 2 wa s establishe dbase don FA A understandin g tha

t thi s model wil l no t

operate i n part

12 1 service . Therefore , installatio n o f

shoulder harnesse s i

n lieu o f demonstrate dcomplianc e to 25.562(c)(5 ) and (c)(6 ) applie s onl y t o aircraf t no t engage din part

12 1 passenger

carryin g service . I f

th e aircraf t i s operate di

n par t 121 , fiill complianc e to th e requirement s o f 25.56 2 (includin g paragraph s (c)(5 ) an d(c)(6) ) and25.78 5 mus t b e shown .

• Th e requirement s o f

FA R25.57 1 a

t Amd t 25-9 8 are limite dt

o the fuselag e andfuselag e change s only . Th e remainder o f th e aircraf

t sfructur e i s certifie dto th e requirement s o f 25.57 1 a t Amd t 25-81 . FA RPar t 34 , includin g Amendment s 34- 1 throug h 34-3 . FA RPar t 36 , includin g Amendment s 36- 1 throug h 36-22 , Complianc e wit

h th e Optiona

l Ditchin g Requirement s ha s bee n establishe da s follows : Dat a coverin g th e ditchin g requirement s o f FA R25,801 , includin g 25,563 , 25,807(e) , an d25.1585(a) , bu t excludin g 25.1411 , are approved . Whe n th e operatin g rule s require emergenc y ditchin g equipment , complianc e wit h 25.141 1 an

d25.141 5 mus t

b e demonstrated . Gulfsfrea mRepor t 1159-GBR-7 , entifled"Outfittin g Requirement s fo r FA A Certificatio n fo

r Ditching " provide s a n acceptabl e mean s fo

r showin g complianc e wit

h 25.141 1 an

d25,1415 . Specia l Conditions : No . 25-180-SC , Enhance dVisio n Systems . No . 25-262-SC , HIR

F (Hig h Intensit

y Radiate dFields) . Exemptions : No . 794 6 [FA

R25.813(e)] , Mid-Cabi n Door s Between Passenger Compartments . No . 8004 , 814 2 [FA

R25,90 1 (c)] , Uncontrollabl e High Thrus t Failure Conditions . NOTE : Th e FA

A ha s conclude dtha

t th e occurrenc e of

any uncontrollabl e hig h thrus t failur e condition , or

an y o f th e associate dcausa

l failure s liste din Sectio n 05-50-0 0 of the applicabl e airplan e Maintenanc e Manua l "ma y endange r th e saf e operatio n o f

a n airplane " an

dhenc e ar e reportabl e under

FA R121.703 , 125.40 9 an

d135.415 . Equivalent

Safet y Findings : ; (1 ) FA R25.807(g)(2) , Gulfstrea

mOverwin g Emergenc y Exi t Windows , TA

D ELO S Mem

o No . AT5177AT-T-A- 2 A crewmembe

r traine din evacuatio n i s a

n additiona

l require dcrewmembe

r on all flights o f

1 0 to 1 9 passengers . Th e require dpilo t an dco-pilo t caimo t serv e thi s function . Th e additiona l crewmembe

r mus t b e traine din th e optimummetho dfo r evacuating\hroug h th e Gulfsfrea m elliptica l exit s an din procedure s fo

r directin g passenger

flow to {veven

t someon e wh o doe s no t fit throug h a n elliptical exi t

fromblockin g i t

s o tha t other s canno t

us e it . Eac h operato rA12E A Pag e 4 8 

# i ' s^ f

(2 ) (3 ) (4 ) •mus t establis h an

dmaintain atrainin g progra mfo r thi s additiona

l crewmembe

r (t o include a

n initia l andrecurrent

curriculum) i

n accordanc e wit

h Gulfstrea

mDocumen

t G500-OMS-1 , Revisio n 1 (fo

r G50 0 operations ) or

G550-OMS-1 , Revisio n 1 (fo r G55 0 operations) , an

d mus t keep arecor

dof tha t trainin g availabl e fo

r inspectio n by the FAA . A pre-flight

briefin g o

n the configuratio n specifi c egres s procedure s an dexit s o f the airplan e mus t b e provide dto all passenger s befor e each flight. Thi s briefin g mus t include adetaile d explanatio n o f

the optimu

mmetho dfo

r evacuatin g tlirough th e overwin g Gulfstrea melliptica

l exits , whic h i s dependant

upo n th e interio r

configuratio n inboar

do f the exit . FA R25.811(d ) an

d25.812(b) , Emergenc y Exit Marker , Locator

an dBulkhead/Divide

r Signs , TA D ELO S Mem

o No . AT5177AT-T-C- 1 FA R25.841(b)(6) , Cabin Pressurizatio n - High Altitud e Takeof f an dLanding Operations , TA D ELO S Mem

o No . AT5177AT-T-S-2 9 FA R25.853 , 25.869 , Flammabilit y Substantiatio n o f

Electroni c Equipment , TA D ELO S Mem o No . AT5177AT-T-A- 9 Mode l GIV-X : S/

N 400 1 andsubsequen

t 1 4 CF RPar t 25 , effectiv e Februar

y 1 , 1965 , includin g Amendment s 25- 1 through 25-10 1 wit h the exception s liste dbelow : Sectio n 25.21(e ) 25.30 5 25.32 1 25.33 3 25.335(b ) 25.34 1 25.34 3 25.36 5 25.37 3 25.39 1 25.42 7 25.44 5 25.45 9 25.49 1 25.56 1 25.57 1 25.67 1 25.677(c ) 25.69 3 25.69 5 25.80 7 Titl e

Proo f o f compliance . Strengt h an ddeformation . Fligh t load s - General . Fligh t maneuverin g envelope . Design airspeed s (spee dmargin) . Gus t an dturbulenc e loads . Design fue l an doi l loads . Pressurize dcompartment

loads . Speedcontro l devices . Confro l surfac e load s - General . Unsymmetrica

l loads . Auxiliar y aerodynami c surfaces . Specia l devices . Takeof f ru n Emergenc y landin g condition s Damag e toleranc e an

dfatigu e evaluatio n o f

structure . Contro l systems-General . Trimsystem s Joint s Power-boos t

an dpower operate dcontro l syste m Emergency exit s 25.807(c)(2),(d)(4 ) Emergency exit s 25.813(a),(b),(c),(d),( 0 Emergenc y exi t acces s 25.84 1 25.85 7 25.85 8 25.96 3 25.97 3 25.101 3 25.144 7 25.151 7 25.155 7 Pressurize dcabin s Amendmen t 25- 7 25-54 , 25-86* * 25-23 , 25-86* * 25-0 , 25-86* * 25-2 3 25-0 , 25-86* * 25-18,25-86* * 25-54 , 25-87* * 25-0 , 25-86* * 25-0 , 25-86* * 25-0 , 25-86* * 25-0 , 25-86* * 25-0 * 25-0,25-91* * 25-23 , 25-64 (seats) , 25-9 1 (ne w sfructure)* * 25-5 4 (win g an

dempennage ) 25-9 6 (fuselag e changes)* * 25-, 0 25- 0 25-0 * 25- 0 25-55 * 25-15 * 25-46 * 25-38 , 25-87* * Carg o compartmen

t classificatio n 25-32 * Carg o or baggag e compartinen t smok e or fire detectio n systems . Fue l Tank s Fuel tan k filler connectio n Oi l tank s Equipmen t standard s fo

r oxyge n dispensin g unit s Rough air speed , VR

A Miscellaneou s marking s an d pound s 25-54 * 25-40 * 25-40 * 25-36 * 25-41,25-87* *

I 25-8 6 (ne w paragraph-NA) * 25-38 *Pag e 5 1 

# \^ r A12E A i n th e tank s which i s abov e the "zer o gage " levels . (d ) Th e abov e "unusable " fue l i s tha t amoun t o f fue l i n th e tanks , includin g tan

k trappe dfue

l a s define di n CA R4b.41 6 or

FA R25.959 , which i s unavailabl e to th e engine s under critica l flight conditions . Th e usabl e fue l capacit y i s given unde

r sectio n entitle d"Fuel Capacity " fo r each airplan e model . Th e "unusable " fue l i s include di

n th e syste mfue

l a s indicate di

n (a ) abov e an dnee dno t

b e accounte dfo

r separately . Se e FA

A approve dAirplan e Flight Manua l fo r infonnatio n concemin g th e following : (1 ) Maximumfue

l unbalanc e betwee n lef

t an dright tank s fo r take-of f andin-flight

operations . (2 ) Recommende dairplan e groun dattitud e to obtai n equa l fue l quantitie s durin g servicing . (3 ) Fue l additives . NOT E 2 . Placards :

NOT E 3 . Th e require dplacard s fo r Model s G-1159 , G-1159A , an dG-1159 B ar

e liste di n th e appropriate Airplan e Flight Manual . The require dplacard s fo r Model s G-IV , GV , GV-S P andGFV- X are liste din Chapte

r 1 1 o f th e appropriat e Airplan e Maintenanc e Manual . Retiremen t

Times :

NOT E 4 .

NOT E 5 . Th e retirement time s o f fatigu e critica

l lif e limite dcomponent s ar

e liste din Sectio n IV , Chapte r 5 o f th e appropriate Gulfsfrea

mAerospac e Model G- l 15 9 (Gil) , G- l 159 A (GUI) , G- l 159 B (GIIB) , o r G-IV . Retirement

time s fo r th e GV , GV-S P an

dGFV- X ar e liste di n Sectio n 05-10-0 0 o f

th e applicabl e Airplan e Maintenanc e Manual . Th e retirement times o f thes e lif e limite dcomponent s canno t b e altere dwithout

FA A Engineerin g approval . Fo r airplane s havin g tim e (landings ) in mor e tha n on e configuration , contac t Gulfsfrea mAerospac e Engineerin g fo

r remainin g lif

e limitations . Us e o f CAS C Regulators : I n th e even t

th e CAS C 14 6 regulator s are used , th e aircraf t i s limite dto 18,000 ft. altitude , unles s Gulfsfrea mAmerica

n G- l 15 9 Aircraf

t Servic e Chang e 1 7 or

Drawin g No . 1159RDF163 D i s incorporated . Whe

n tli e CAS C 174 fue

l flow regulato r

i s installed . Aircraf

t Servic e Chang e 5 2 mus t als o b e incorporated . Us e o f JP ^ Fuel :

NOT E 6 . Th e us e o f

JP- 4 fue l (wid e cut ) a s agree dto b y th e operator , Rolls-Royce , andth e appropriate airworthines s authorit

y ma y resul t in areductio n o f

H P fue l pum p life . Aircraf t Servic e Clhanges : Th e followin g are th e mos t significant

Aircraf t Servic e Change s (ASC's ) fo r th e respectiv e model aircraft , dealin g primaril y wit

h change s t o weight

andfue l capabilities . Thi s i s no t

th e complete lis t

o f ASC' s fo r an y o f thes e models . Model G- l 15 9 (Gil) : Aircraf t Servic e Chang e (ASC ) lOA , "Wing-Fuel Balanc e Line s - Modificatio n of " Applicabl e to S/

N 1 throug h 8 2 andS/

N 775 . Aircraf t Servic e Chang e (ASC ) 41 , "Increase dGros s Weigh t Win g Modifications. " Applicabl e to S/

N 1 throug h 8 2 an

dS/ N 775 . Aircraf t Servic e Chang e (ASC ) 81 , "62,50 0 PoundIncrease dGros s Weight Modification. " Applicabl e t o S/

N 1 throug h 10

0 an dS/ N 775 . Aircraf t Servic e Chang e (ASC ) 175 , "Exhaus t (AT A No . 78 ) Nois e Abatement Progra mThrus t Reverser Installation. " Applicabl e to S/

N 1 throug h 165 an

dS/ N 775 . Aircraf t Servic e Chang e (ASC ) 200 , "Fuel Tip Tank s - Installatio n Of " V, .A12E A 

### Pag e 52 ^ / t i -f ~ 

# P Applicabfrt o S/

N 1 throug h 21 6 an

dS/ N 775 . Aircraf t Servic e Chang e (ASC ) 226 , "Dra g Brac e Penetratio n Prevention. " Applicabl e t o S/

N I throug h 20 8 an

dS/ N 775 . Aircraf t Servic e Chang e (ASC ) 233 , "Installatio n o f Tip Cap. " Applicabl e t o S/

N 1 throug h 21 6 an

dS/ N 77 5 wit h AS C 20 0 andS/

N 21 7 an dsubs , except

S/ N 775 . Aircraf t Servic e Chang e (ASC ) 256 , "hicrease dGros s Weigh t (65,30 0 lb . withou t

Ti p Tanks). " Applicabl e to S/

N 1 an dsubsequent . Aircraf t Servic e Chang e (ASC ) 299 , "45,00 0 Foo t Operatin g Altitude. " Applicabl e to S/

N 1 andsubsequent . Mode l G- l 159 A (GUI) : Aircraf t Servic e Chang e (ASC ) 30 , "Increase dFue l Capacit y to 28 , 30 0 lb. , G- l 159A: " Applicabl e to all S/

N 249 , 252 , 30 0 throug h 371 , an d875 . Aircraf t Servic e Chang e (ASC ) 70 , "Increase dGros s Weights , G- l 159A. " Applicabl e t o S/

N 249 , 252 , 30 0 through 426 , an d875 . Mode l G- l 159BfGUB) : Aircraf t Servic e Chang e (ASC ) 252 , "Increase dFue l Capacit y t o 28,30 0 lb. , G- l 159B. " Applicabl e to all G- l 159 B S/N . Aircraf t Servic e Chang e (ASC ) 275 , "Increase dGros s Weights , G- l 159B. " Applicabl e to all G- l 159B S/N . Mode l OrV : Aircraf t Servic e Chang e (ASC ) 61 , "49,00 0 lb . Zero Fue l Gros s Weight

fricrease (wifl

i Speed Reshiction) , G-FV. " Applicabl e t o S/

N 100 0 throug h 1213 . Aircraf t Servic e Chang e (ASC ) 190 , "Increase dRamp , Landin g andZer o Fue l Gros s Weight , G-FV. " Applicabl e t o S/

N 100 0 throug h 1213 . Aircraf t Servic e Chang e (ASC ) 261 , "49,00 0 lb . Zer o Fue l Gros s Weight

Increase , G-IV. " Applicabl e t o S/

N 100 0 throug h 1213 . Aircraf t Servic e Chang e (ASC ) 436 , "G30 0 Modification " wil l designat e thos e aircraf t a s Mode l G-I V (G300) . Thos e aircraf

t shal l b e operate dimde

r Airplane Fligh

t Manua l GAC-AC-G300-OPS-0001 . Applicabl e t o S/

N 150 0 an

dsubsequent . Aircraf t Servic e Chang e (ASC ) 440 , "G400 Modification " wil l designate thos e aircraf t a s Mode l G-I V (G400) . Thos e aircraf

t shal l b e operate dunde

r Airplane Fligh

t Manua l GAC-AC-G400-OPS-0001 . Applicabl e to S/

N 150 0 an dsubsequent . Aircraf t Servic e Chang e (ASC ) 46 5 "Auxiliar y Powe r Unit (APU ) 36-150(G ) Installation. " Applicabl e to S/

N 100 0 t o S/

N 1535 . Mode l GV : Aircraf t Servic e Chang e (ASC ) 50 , "Af t Fue l Pickups-Location , GV . Applicabl e to S/

N 50 1 throug h 548 . Aircraf t Servic e Chang e (ASC ) 73A , "Honeywell Enhancement-Winter Certification , (include s 5602 1 lAC , 45 % CG Expansion , an dRevise dStal l Barrie r Activatio n Schedule) , GV" . Applicabl e t o S/

N 50 1 throug h 569 .Pag e 5 

# lii ' , r A12E A

NOTE 7 . Model GV-SP :

Aircraf t Servic e Chang e (ASC ) 10 , "G50 0 Modification " wil l designat e thos e aircraf

t a s Mode l GV-S P (G500) . Thos e aircraf

t shal l b e operate dunde

r Airplan e Fight

Manua l GAC-AC-G500-OPS-0001 . Applicabl e to S/

N 500 1 an

dsubsequent . Aircraf t Servic e Chang e (ASC ) 11 , "G55 0 Modification " wil l designate tiiose aircraf t a s Mode l GV-S P (G550) . Thos e aircraf

t shall b e operate dunde

r Airplan e Fight

Manua l GAC-AC-G550-OPS-0001 . Applicabl e to S/

N 500 1 an

dsubsequent . Aircraf t Servic e Chang e (ASC ) 035A , "Europea n Aviatio n Safet

y Agency (EASA)/Join t

Aviatio n Authoritie s (JAA ) Certificatio n Basi c Requirements " convert s aircraf t t o th e configuratio n require dby th e EAS A Typ e Certificate fo

r th e GV-S P (No . EASA.IM.A.070) . Dat asupportin g AS C 035 A ar e FA A approve dfo

r GV-S P aircraf

t unde r Gulfstrea mconfro l specifically bein g prepare dfo r an dprio r t o expor t t o a n EAS A member

country , o r

t o acountr

y tha t require s th e EAS A Typ e Desig n configm-ation . Followin g transfe r t o th e foreig n registry , if

the aircraf

t i s returne dto U.S . regisfratio n anda n applicatio n fo

r Standar d Airworthines s i s submitted , then thi s AS C mus t b e remove dandth e aircraf t returne dt o it s U.S . Typ e Desig n configuration . Aircraf

t fittedwit h AS C 03 5 A shal l b e operate dunde r th e lates t approve dversio n o f

Airplane Fight Manual , GAC-AC-G500-OPS-000 1 (fo r aircraf t wit h AS C 10 ) or GAC-AC-G550-OPS-000 1 (fo r aircraf t vnt h AS C 11) , plu s Airplan e Flight Manua l Supplement

No . G550-2008-0 2 (applicabl e t o bot h th e G50 0 an dG55 0 variants) . Applicabl e to S/

N 500 1 andsubsequent . Model GIV-X : Aircraf t Servic e Chang e (ASC ) 002A , "Europea n Aviatio n Safet

y Agenc y (EASA)/Join t

Aviatio n Authoritie s (JAA ) Certificatio n Basi c Requirements " convert s aircraf t t o th e configuratio n require db y th e EAS A Typ e Certificate fo

r th e GIV- X (No . EASA.IM.A.070) . Dat asupportin g AS C 002 A are FA A approve dfo

r GIV- X aircraf

t unde r Gulfstrea mconfro l specifically bein g prepare dfo r an dprio r to expor t to a n EAS A membe

r country , o r

t o acounh y tha

t require s th e EAS A Typ e Desig n configuration . Followin g transfer t o th e foreig n registry , i f

th e aircraf

t i s returne dt o U.S . regisfratio n anda n applicatio n fo

r Standar d Airworthines s i s submitted , then thi s AS C mus t b e remove dandth e aircraf t returne dt

o it s U,S . Typ e Desig n configuration . Aircraf t fittedwit h AS C 002

A shal l b e operate dunder

th e lates t approvedversio n o f

Airplan e Fight

Manua l GAC-AC-G350-OPS-000 1 (fo r aircraf t witi i AS C 004 ) or

GAC-AC-G450-OPS-000 1 (for aircraf t wit h AS C 005) , plu s Airplan e Flight

Manua l Supplement

No . G450-2008-0 1 (applicabl e t o boti i th e G35 0 an dG45 0 variants) . Applicabl e t o S/

N 400 1 an

dsubsequent . Aircraf t Servic e Chang e (ASC ) 004 , "G35 0 Modification " wil l designate thos e aircraf t a s Mode l GIV- X (G350) . Thos e aircraf

t shal l b e operate dunder

Airplan e Figh

t Manua l GAC-AC-G350-OPS-0001 . Applicabl e t o S/

N 400 T andsubsequent . Aircraf t Servic e Chang e (ASC ) 005 , "G45 0 Modification " wil l designate thos e aircraf t a s Mode l GIV- X (G450) . Thos e aircraf

t shal l b e operate dunder

Airplan e Fight

Manua l GAC-AC-G450-OPS-0001 . Applicabl e t o S/

N 400 1 andsubsequent . Aircraf t Servic e Chang e (ASC ) 016 , "G45 0 MaximumTakeof f Gros s Weight

Increase. " Applicabl e t o S/

N 400 1 andsubsequent . Productio n Basis : Airplane s produce da

t Bethpage . New York : (a ) Mode l G- l 15 9 (G-II) : Typ e Certificate A12E A (issue dOctobe

r 19 , 1967) , S/

N 1 tiuough 7 , 9 , 11 , 12 , 13 , 15 , 16 , 17,18 , and22 . Productio n Certificate No . 2 3 (issue dJun e 11 , 1968) , S/ N 23 , 25,26 , 28 , 30 , 34 , 35 , 37 , an d40 . ^ Aunlane s produce da

t Savannah . Georgia : (a ) Model G- l 15 9 (G-II) : Typ e Certificate A12E A (issue dOctobe

r 19 , 1967) , S/N^8,10 , 14 , 19 , 20 , an d21 . Productio n Certificat

e No . 50 7 (issue dJul y 18 , 1968) , and7S 0 (issue dSepteniber 1,197 8 an

dreissue d November

19 , 1982) ; S/

N 24 , 27 , 29 , 31 , 32 , 33 , 36 , 38 , 39,4 1 throug h 25 6 (exiOjidin g 24 9 and252 ) an

d775 .A12E A Pag e 5 4 ' j ^1~ ~

(b ) Model G-rr59 A (G-lII) : Productio n Certificat e No . 7S O (issue dSeptembe r 1 , 197 8 an

dreissue d September

22 , 1980) ; S/

N 249 , 252 , 300 throug h 495 , an d875 . (c ) Model G- l 159B (G-IIB) , none . ModifiedMode l G- l 15 9 airplane . (d ) Model G-I

V (G-IV) : Productio n Certificat e No . 7S 0 (issue dSeptembe r 1 , 197 8 an

dreissue dAugus t

31 , 1987) , S/ N 100 0 andsubsequent . (e ) Mode l G

V (GV) : Productio n Certificat e No . 7S O (issue dSeptember 1 , 197 8 an

dreissue dJun e 11 , 1997) , S/ N 50 1 an dsubsequent . ( 0 Mode l GV-S P (GV-SP) : Productio n Certificate No . 7S O (issue dSeptembe r 1 , 197 8 an

dreissue d Augus t 14 , 2003) , S/

N 500 1 an

dsubsequent . (g ) Mode l GFV-

X (GIV-X) : Productio n Certificat e No . 7S 0 (issue dSeptember 1 , 197 8 an

dreissue d November

16 , 2004) , S/

N 400 1 an

dsubsequent . NOT E 8 . Alternate Aircraf t Identifications : Th e followin g provide s approve daltemate aircraf t identificatio n informatio n assumin g incorporatio n o f the associate d(listed ) ASC : Model G-IV , seria

l numbe r 150 0 & Subs , ar

e eligibl e fo

r identificatio n a s Model G-I V (G300 ) whe

n modifie din accordanc e vvit h GA C Aircraf

t Servic e (Thang

e (ASC ) 436 . Model G-rV , seria

l numbe r 150 0 & Subs , ar

e eligibl e fo

r identificatio n a s Model G-f V (G400 ) whe

n modifie di n accordanc e wit h GA C Aircraf

t Servic e Chang e (ASC ) 440 . Model GV-SP , seria

l numbe r 500 1 an dsubsequent

are eligibl e fo

r identificatio n a s Mode

l GV-S P (G550 ) whe n modifie din accordanc e wit h GA C Aircraf t Sei-vice Chang e (ASC ) 11 . Model GV-SP , seria

l numbe r 500 1 an dsubsequent

ar e eligibl e fo

r identificatio n a s Model GV-S P (G500 ) when modifie di

n accordanc e wit

h GAC Aircraf

t Servic e Chang e (ASC ) 10 . Mode l GIV-X , seria

l numbe r 400 1 an dsubsequent

are eligibl e fo

r identificatio n a s Model GIV- X (G450 ) whe n modifie din accordanc e wit h GAC Aircraf

t Servic e Chang e (ASC ) 005 . Model GIV-X , seria

l numbe r 400 1 an dsubsequent

ar e eligibl e fo

r identificatio n a s Mode

l GIV- X (G350 ) when modifie di

n accordanc e wit

h GA C Aircraf t Servic e Chang e (ASC ) 004 . NOT E 9 . Cockpi t

Fiel do f View : Th e cockpi t

front windshiel ddimension s fo

r th e Model s G- l 159 , G- l 159A , G- l 159B , G-IV , G-V , GV-SP , an

dGFV- X airplane s ar

e critica l fo r forwar dfieldo f vie w certificatio n requirements ; therefore , n o equipment

shoul db e installe do n to p of th e glar e shiel dwithou t

prio r coordinatio n wit

h a n FA A Aircraf t Certificatio n Office . NOT E 10 . Model G- l 159A . S/ N 249 . 31 3 and330 : Th e equipment

liste di n Gulfsfrea

mAmerica

n Repor t No . 1159A-GER-78 , "Roya l Danis h Air Forc e Gulfsfrea

mII I Lo g Boo k Entry, " date dApri l 8,1982 , mus t b e FA A approved , removed , o r rendere dinoperativ e prio r

to issuanc e o f

astandar dairworthines s certificate o n Model G- l 159A , S/N249 , 313 , and330 . NOT E 11 . System s Modifications :

Th e G-IV , GV , GV-S P an

dGIV- X model s incorporat e integrate davionic s system s using software-base d lin e replaceabl e unit s (LRU's ) which shar e adigita l signa l transmissio n bus . Th e avionic s configuratio n o f th e G-IV , GV , GV-S P an

dGIV- X a s delivere dfro

mproduction , i s critica

l to th e proper

operatio n o f

th e cockpi t instrumentatio n system . Modificatio n to tiie LR U softwar e supplie dwit

h th e G-IV , GV , GV-S P o r GIV-X , replacemen t

o f a n LR U wit h adifferen

t LRU , additio n o f

ne w LRU , or

alteratio n o f

a n LR U interfac e coul d adversel y affect

th e airworthines s o f

the certifie dproduct . Accordingly , n o chafe s to th e integrate dPag e 5 5 

# 4 

# S

T A12E A avionic s syste mshoul db e mad e without coordinatio n wit

h th e Aircraf

t Certificatio n Offic e havin g jurisdictio n ove

r the modifier . NOTE 12 . Cockpit Modifications : An y modificatio n or

change s i n cockpi t configuratio n whic h ma

y affect aircre w workload , cockpi t nois e level o r

day/night lightin g mus t

b e evaluate db y a

n FA A Aircraf t Certificatio n Flight

Tes t Pilo t o r Flight Standard s Operatio n Inspector . NOTE 13 . Delete d(Januar y 13,1997 ) NOTE 14 . Us e o f Takeof f Tlirust : Fo r Model s G-FV, GV , GV-S P andGIV-X , us e of takeof f thrus t fo r more tha n five (5 ) minute s [not

t o exceed te n (10 ) minutes ] i s approve dfo r us e only i n th e event

of a n inoperativ e engin e du e to shutdow n o r failure . NOT E 15 . Information to Modifiers :

Information to modifier s o n limitation s whic h impac t origina l certificatio n requirement s o f th e Gulfstrea

m G V ar e containe di

n Gulfsfrea

mRepor t GV-GER-1242 , Gulfsfrea

mV Interio r

Certificatio n Requirement s Document . Informatio n to modifier s on limitation s whic h impac t origina l certificatio n requirement s o f the Gulfsfrea mGV-S P ar

e containe din Gulfsfrea

mRepor t GVSP-GER-6044 , Gulfstrea mGV-S P Interio r Certificatio n Requirement s Document . Informatio n to modifier s on limitation s whic h impac t origina l certificatio n requirement s o f th e Gulfsfrea

mGFV- X ar e containe din Gulfsfrea

mRepor t GIVX-GER-1619 , GIV- X Interio r

Certificatio n Requirement s Document . NOTE 16 . G-Il Agin g Aircraf t Progra m A s par t o f th e G-II Agin g Aircraf

t Program , a

n Airworthines s Limitation s Sectio n (ALS ) i s bein g addedt o th e current

G-II Maintenanc e Manual . I n addition , aSupplementa

l Structural Inspectio n Documen t (SSID ) i s bein g develope di n order

t o provid e the correspondin g inspectio n procedure s andmethods . Th e AL S an d SSID ar e bein g develope dt o FA

R25.57 1 a

t Amendmen

t 25-54 , base do n th e damag e toleranc e requirement s of AC91-56A . Throug h th e damag e toleranc e requirements , th e AL S an dSSI D wil l remov e certai n lif e limitation s o n previou s saf e lif e certifie dcomponents . Wit h th e incorporatio n o f

th e AL S an

dSSID , th e G-I

I airfram e Extende dServic e Goa

l (ESG ) wil l b e 40,00 0 flight hour s an d36,00 0 flights. NOTE 17 . GI

V Airworthines s Limitations : As par t o f th e MSG 3 Program , a

n Airworthines s Limitation s Sectio n (ALS ) ha s bee n adde dto th e GI V Maintenanc e Manua

l fo r aircraf t seria l numbe r 1400 an dsubsequent , andfo

r all othe r GI V aircraf t havin g incorporate dAS C 416 . Thi s AL S ha s been develope dto FA R25.57 1 a

t Amendment

25-54 , basedo

n the damag e toleranc e requirement s o f AC91-56A . I t

i s cbrifrolledb y th e FA

A an dcan notTD

B change db y th e aircraf t operator . Through th e damag e toleranc e requirements , th e AL S remove s certai n lif e limitation s o n previou s saf

e lif e certifie dcomponents . NOTE 18 . Delete d(Augus t 14,2003 ) NOTE 19 . RVSM :

Pe r th e approve dTyp e Design , GV-S P S/ N 500 1 andsubsequent

(i.e. , G55 0 andG50 0 model aircraft ) ar e considere dt o b e complian t wit h th e Reduce dVertica

l Separatio n Minim a(RVSM ) technical requirement s containe di n FA

A Document

91-RVSM ; however , operationa l approva l t o fly i n RVS M airspac e mus t stil l b e grante db y th e cognizant

Flight Standard s organization . Pe r the approve dTyp e Design , GIV- X S/ N 400 1 an

dsubsequent

(i.e. , G45 0 an dG35 0 mode l aircraft ) ar e considere dt o b e complian t wit h th e Reduce dVertica

l Separatio n Minim a(RVSM ) technica l requirement s containe din FA

A Document

91-RVSM ; however , operationa l approva l to fly in RVS M airspac e mus t stil l b e grante db y th e cognizant

Flight Standard s organization . NOTE 20 . Cockpit Vide o EHsplay :A12E A Pag e 5 6 i f ^ ^ Th e avionic s STChttectur

e o f th e GV-S P an dGIV- X model s include s acapabilit y to displa

y multiple , assorte d vide o input s o

n th e cockpit

displa y unit s positione ddirectl y i n front o f th e pilots . Becaus e thes e display s affec t cre w workload , change s t o th e approve dvide o inpu t source s (includin g the additio n o f ne w vide o source s o r capabilities ) will require aspecifi c FA A approval , includin g specifi c acknowledgement an d concurrenc e fro

ma n FA A Aircraf t Certificatio n Office . NOT E 21 . Directio n Indicator Requirements : Gulfstrea mModel s G-IV , GV , GV-SP , an dGIV- X mee

t 1 4 CF Rpar t 25.1303(a)(3 ) requirement s fo r a directio n indicato r

(non-stabilize dmagneti c compass ) b y installatio n o f

Standb y Digita

l Readin g Magneti c Indictor System s throug h th e followin g means : G-I V Standb y Digital an dBearin g Distanc e Indicator (DBDI ) syste mdrive n b y flux valv e G V Standb y Radi o Magneti c Indicato r (RMI ) systemdriven b y flux valv e GV-SP/GIV- X Integrate dStandb y Insfrumen t System(ISIS ) an

dElecfroni c Bearin g Distanc e Indicator (EBDl ) syste mdrive n b y magnetomete r NOT E 22 . Forwar

dObserver' s Sea

t (Jum p Seat ) Th e Forwar

dObserver' s Sea

t (Jum p Seat ) i s approve dfo

r taxi , takeoff

, an dlandin g on th e GV , GV-SP , an d GIV- X model s a s par

t o f Typ e Design . Th e Forwar dObserver' s Sea

t (Jum p Seat) i s approve dfo

r taxi , takeoff , andlandin g on th e Gil , GIU , andGI V if verifiedb y th e installin g ST C or

other FA A approve ddata . I n flight us e o f the jump sea

t in any Gulfsfrea

mmode l als o require s tha

t relate darticles , specifically a n FA A approve dshoulder

harnes s an dOxyge n system , are installed . I n addition , G n S/

N Ithroug h 20 8 an

dS/ N 77 5 require AS C 22 6 b e installe dfo r jum p sea t approval . NOT E 23 . AP

U Limitation s For GIV- X serie s (G450/G350 ) airplan e seria l number s 4147,4151 , an

dS/ N 415 3 through 4171 , the Gulfsfrea mAirplan e Flight

Manua l Supplement s note dbelo w must b e attache dt

o th e G45 0 AF

M date d1 2 Augus t 2004 , o r the G35 0 AF

M date d2 8 Octobe

r 2004 : S/ N AFMS # S/ N AFMS # 414 7 G450-2009-04-414 7 416 2 G450-2009-04-416 2 4 5 1 G450-2009-04-415 1 416 3 G450-2009-04-416 3 4:5 3 G450-2009-0 2 o r

G450-2009-04-415 3 416 4 G450-2009-04-416 4 4 5 4 G450-2009-0 2 o r

G450-2009-04-415 4 416 5 G450-2009-04-416 5 4 5 5 G450-2009-0 2 o r

G450-2009-04-415 5 416 6 0450-2009-04^16 6 4 5 6 G450-2009-0 2 or

G450-2009-04-415 6 416 7 G450-2009-04-416 7 4 : 5 7 G450-2009-0 2 or

G450-2009-04-415 7 416 8 G450-2009-04-416 8 4 5 8 G450-2009-04-415 8 416 9 G450-2009-04-416 9 4 5 9 G450-2009-04-415 9 417 0 0450-2009-04^17 0 4 6 0 G450-2009-0 2 o r

G450-2009-04-416 0 417 1 G450-2009-04-417 1 4l6 1 G450-2009-04-416 1 For GV-S P serie s (G550/G500 ) airplan e seria l number s 5205 , 5218 , S/

N 522 0 dwoug

h 5224 , an dS/ N 522 6 throug h 5249 , th e Gulfsfrea mAirplan e Flight

Manua l Supplement s note dbeld w mus t b e attache dto th e G55 0 AF M date d1 4 Augus t

2003 , o r th e G50 0 AF

M date d0 5 Decembe

r 2003 :Pag e 5 7 

## ^ t A12E A S/ N 520 5 521 8 522 0 522 1 522 2 522 3 522 4 522 6 522 7 522 8 522 9 523 0 523 1 523 2 523 3 523 4 AFMS # G550-2009-0 2 o r

G550-2009-05-520 5 •G550-2009-05-521 8 G550-2009-0 2 o r

G550-2009-05-522 0 G550-2009-0 2 orG550-2009-05-522 1 G550-2009-0 2 o r

G550-2009-05-522 2 G550-2009-0 2 o r

G550-2009-05-522 3 G550-2009-05-522 4 G550-2009-0 2 o r

G550-2009-05-522 6 G550-2009-0 2 o r

G550-2009-05-522 7 G550-2009-0 2 o r

G550-2009-05-522 8 G550-2009-0 2 o r

G550-2009-05-522 9 G550-2009-0 2 o r

G550-2009-05-523 0 G550-2009-05-523 1 G550-2009-05-523 2 G550-2009-05-523 3 G550-2009-05-523 4 S/ N 523 5 523 6 523 7 523 8 523 9 524 0 524 1 524 2 524 3 524 4 524 5 524 6 524 7 524 8 524 9 AJFMS # G550-2009-05-523 5 G550-2009-05-523 6 G550-2009-05-523 7 G550-2009-05-523 8 G550-2009-05-523 9 G550-2009-05-524 0 G550-2009-05-524 1 G550-2009-05-524 2 G550-2009-05-524 3 G550-2009-05-524 4 G550-2009-05-524 5 G550-2009-05-524 6 G550-2009-05-524 7 G550-2009-05-524 8 G550-2009-05-524 9



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## http://ww\v.gulfstream.com/product_support/technical_pubs/pubs/revs.lit m 3/2/201 1 

# c - H

## Gulfstrea m GI S - Publication s Revisio n Statu s OJ/27/ n

ASC/ACB/C B Inde x Computerize d Maintenanc e Progra m CD-RO M (CUSP

) 

### Rev . 7 7 3 1 Decembe r201 1 2 7 Januar y 201 1 Corrosio n Preventio n & Contro l Manua l Rev . 2 Cruis e Manua l Rev . 6 3 0 Septembe r200 B 2 4 Octobe r2005 5 Marc h 198 7 Crals e Manua l (Ti p Tank ) Rev . 2 2 5 Apri l 199 4 Deicing/Anti-lcin g Flui d Applicatio n Guid e Rev . 1 Fligh t Manua l Rev . 3 9 Groun d Handlin g i Servicin g Handboo k 

### Rev . 1 1 3 0 M y 200 7 1 4 Jul y 201 0 2 8 Octobe r201 0 2 8 Ma y 201 0 7 Jul y 201 0 GHS H Quic k

Refsronc e Card s Rev . 1 0 2 8 May 201 0 7 Jul y 201 0 Illustrate d Part s Catalog " *NOrB : Wit h Rev . 44 , th e Gtl/lI B Manual s hav e bee n combined . Rev . 5 8 Illustrate d Part s Catalo g (Ti p Tan k Supplement ) Basi c 3 1 Decembe r201 0 2 7 Januar y 201 1 1 5 Marc h 198 1 Maintenanc e DV

O Library Maintenanc e Manua l Rev . 7 7 Maintenance/Operational/Placardin g Rev . 9 a Maste rMinimu m Equipmen t Us t Rev . 9 a 

### 2010-0 2 2 7 Januar y 201 1 3 1 Decembe r201 0 2 7 Januar y 201 1 3 0 Decembe r200 9 1 8 Januar y 201 0 3 0 Decembe r200 9 1 8 Januar y 201 0 Maste rMinimu m Equipmen t Us t - Par t 9 1 Rev . 9 a 3 0 Decembe r200 9 1 8 Januar y 201 0 Nois e Informatio n Manua l Rev . 1 1 1 Jun e 201 0 Structura l Repai rManua l Rev . 1 0 3 1 Decembe r201 0 2 7 Januar y 201 1 Technician s Pocke t Guid e Rev . 9 Wirin g Diagra m Manua l Aircraf t Effe^tivU y 1-100 , Includin g 77 5 Aircraf t Effectivit y lOI-lSB , Excludin g 24 9 & 25 2 Rev . 3 9 Rev . 3 3 2 8 Ma y 201 0 7 Jul y 201 0 3 1 Decembe r201 0 3 1 Decembe r201 0 2 7 Januar y 201 1 2 7 Januar

y 201 1



## \ 6 

# 6- H

### Gulfstrea m GII B - Publicatiot^ s Revisio n Statu s 1/27/1 1

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Referenc e Card s RB</ . 1 0 2 8 Ma y 201 0 7 Jul y 201 0 2 8 Ma y 201 0 7 Jul y 201 0 Illustrate d Part s Catalog * "NOTE : Wit h Rev . 44 , th e GWII B Manual s hav e bee n combined . Rev . 5 8 3 1 Decembe r201 0 2 7 Januar y 201 0 Maintenanc e DV D Librar y 2010-0 2 2 7 Januar y 201 0 Maintenanc e Manua l Rev . 4 3 3 1 Decembe r201 0 2 7 Januar y 201 0 Maintenance/Operationat/Placardin g Rev . 9 a 3 0 Decembe r200 3 1 8 Januar y 201 0 Maste rMinimu m Equipmen t Us t Rev . 9 a Maste rMinimu m Equipmen t Us t ~ Par t 9 1 Rev . 9 a 3 0 Decembe r200 9 1 8 Januar y 201 0 3 0 Decembe r200 9 1 8 Januar y 201 0 Nois e Informatio n Manua l Rev , 1 1 1 Jun e 201 0 Structura l Repai rManua l Rev . 1 0 3 1 Decembe r201 0 2 7 Januar y 201 0 Techniaan s Pocke t Guid e Rev^ Q Wirin g Diagra m Manua l Aircraf t EffectMt y 1-100 , Includin g 77 5 Aircraf t Effectivit y 101-258 , Excludin g 24 9 & 25 2 Rev . 3 9 Rev . 3 3 28Mey-2(}iQ - 7July201 Q 3 1 Decembe r201 0 3 1 Decembe r201 0 2 7 Januar y 201 1

2 7 Januar y 201 1



# V

# K ^ C~ 1

### iJiiiiii i C 3 "VES^LOwOk O 770 1 WootJIe y Ave . Va n Nuys , CA . 9140 6 818.904.195 5 Phon e 818.904.198 8 Fa x Repai rStatio n No . I0QR689 X MAKE/MODE L GULFSTREA

M 1159 B REG . No . N477G G SERIA L No .

15 5 TIM E

12393. 5 CYCL E

725 5 DAT E JAN.06,«©(» r COMPUE D WIT H TH E FOLLOWIN G CMP : 1 . 21151 6 - Coolin g Turbin e Uni t Oi l Leve l Check . 2 . 21153 5 - Wate r

Separato r

Ba g - Service /

Disas.'icmbly /

Clean / Replace . 3 . 212510-Emergenc y Pressurizatio n Valve-Operationa l Test . 4 . 23207 8 - Cockpi t

Voic e Recorder

UL B Switc h Cleaning . 5 . 23210 3 - Cockpi t

Voic e Rc-corde

r UL B - Functiona l Test . 6 . 23210 6 - CV RUnde r Wate r Locato r Beaco n Switc h Clean (DKI20) . 7 . 23456 5 - Wick , Chec k I /il l Horizonta l SlabUizer Stati c {Cilin

j 8 . 234570-Wick , Chec k Righ t Horizonta l Stabilize r

Stati c (OIIB ) 9 . 23458 0 - Wick , Chec k Vertical s Stabilize r

Stati c (GIIB) . 10 . 24002 5 - Maste r

Warnin g /

Auxiliary Maste r

Warnin g Powe r

C U Light Complet e Check . 11 . 24501 0 - Lef

t D C Generato r

Brus h - Inspection . 12 . 24501 5 - Righ t

D C Generato r

Brus h - Inspection . 13 . 25753 0 - Lavatory Companmen l (Above Floor ) - Inspection . 14 . 99740 7 - AD74-8-9R 2 MO D Lavatories . 15 . 26175 8 - Portabl e Halo n Fir e Extinguishe r

(Af t Lavatory ) - Inspection . 16 . 26176 0 - Foitabl e Halo n Fire Extinguishe r ^Cockpi t No . 1 } - Inspection . ^ 17 . 270145-^Tak e Of

f AlarmSyste mOperationa l Tes t " '^. i 18 . 999005-•AD90-2- 5 T/ O Alar m0/Tes t ' 19 . 270626.-Righ t

Win g na p Travelin g Nut-Lnbiicatio a- . - .- - 20 . 270621'-'lef

t Win g Ha p Travelin g Nut-Lubrication . J~"' - - • 21 . 270629-TStal l Barrie r Actuator-Lubrication.-r ^ "^"I . I 22 . 270635-^Confro l Surface/Hing e Joint s Lube . " ^ '' - 2.3 . 270730^SpoilerLoa dRelie f Bunge e (Left)-KblMicadon . "!'"' ' ' ^ 24 . 270731-JSpoilerlxa dRelie f Bunge e (Right)-Lrfsricaiion . • 25 . 27073 5 - Ailero n Loa dRelie f Bunge e (Left ) - Lubrication . 26 . 27073 6 - Ailero n Loa dRelie f Bunge e (Right ) - Labiication . 27 . 27102 5 - Elevato r

Loa dRelie f

Bunge e - Lubtfcaiion . 28 . 30101 6 - Windshiel dWipe r Moto r OscUlatin g Shaf

t (Left ) - Service . 29 . 301017-.Windshiel dWipe r Moto r OscUlatin g Shaf

t (Right)-Service . 30 . 32061 0 - Mai n Landin g Gear (Left ) - LubricaUo a 31 . 32062 0 - Mai n Landin g Gea r Right ) - Lubrication . 32 . 32063 0 - Nos e Gear - Lubrication . 3.3 . 51502 0 - 2 4 Mont

h Honeycom

b - Inspectio n /

Bon dTest . 34 . 521530 - Entranc e Doo r Inflaubl e Sea l - Remova l / Installation . P/

N o n 159SCB420-15. 35 . 522510-Mai n Entranc e Door-Operationa l Test . 36 . 52252 0 - Entranc e Doo r Inflatabl e Seal Syste m- Operationa l Tes L 37 . 52254 5 - Entranc e IXior Inspection . 38 . 52255 5 - Entranc e Doo r Hing e Pin s Inspectio a 39 . 53151 0 - Inspec t

Torsio n Box . 40 . 53153 5 - Inspec t

Shea r Clip s Af t Fuselage . 41 . 53350 0 - Inspec t

Uniiance . Comp . Behin dPanel . 42 . 53351 0 - Inspec t

Fuilranc e Com

p (AB V FLR) . 43 . 53401 0 - Inspec t

Entrance . Com

p (BLW FLR) . 44 . 53601 0 -Baggag e Companmen l Abov e Hoo r - Inspection . 45 . ^3701 0 -Tai l Coinpannven t Ahiw e Hoor - Inspection . 46 . 80I5.V)-Engin e .Starter-Oi l Leve l Chec k (Engin e Pos . 2 ) MAINTENANC E RELEAS E Th e aiicrali . airlranie. aia-raf t engine , applianc e identifie dafx)ve wa s repairedan dinspectedi n accordanc e with Manufacturer' s maiiiienanc c manua

l an dcurren t

niainteiiaiic e rule s o f

th e I'cdera l Aviatio n Regulatio n an di s approve dlo r retur n t o senic e wit

h respec t ill th e wor

k perliirnwd . Pcnineii l detail s o f wor k porliirme darc o n til e a

t thi s Repai r

Statio n unde r

wor k orde r No . 2278 . 

# 0(JM U SK;NI:I) _ .Sve dLM-Hasa

n l-'o r Intertec h Overload . Inc . V . 

# C - S

# ICERTIFYTHATTHISIS A TRUEMPXO F TH E ORIGINAL FA A VN Y FSD O 

# -t-A

^ p

### INTE^^TEC H 770 1 Wooc ' Ave . Va n Nuys , C A40 6 818.904.19b o Phon e 818.904.198 8 Fa x Repai r Statio n No . I0QR689 X 

### Make / Mode l GULFSTREAM II B REG. # N477G G Seria l

15 5 TIM E

12404. 7 CYCL E

725 9 

### Dat e

JAN.19 , 200 7 COMPUE D niT H TH E FOLLOWIN G CMP(s) : 1 . 27063 0 Rudde r

Torqu e Tub e Bearin g - Lubrication . 2 . 27132 1 Rudde r

Bunge e - Lubrication . 3 . 28061 0 Fue l Pum

p Aut o Chang e Operationa l Test . 4 . 30102 0 Win g Anti-ic e (Left ) - Operationa l Test . 5 . 30102 5 Win g Anti-ic e (Right ) - Operationa l Test . 6 . 7610l5Engin e Control s - Operationa l Tes t (Engin e Positio n I) . 7 . 76201 5 Engin e Control s - Operationa l Tes t (Erigin e Positio n 2) . 8 . 34805 1 UDAT E NDB 2 NAV DATA BANK . 9 . 34403 8 Ver y High Frequenc y Omn i Rang e (VORr-Instrumen t Flight Rules(IF R)Chec k

(FA R91.171). . COMPLIE D mT H TH E FOLLOmN G MAINTENANCE : 10 . 32683 5 Mai n Whee l an dTir e (Lef t Inboar dNo.2 ) - Remova l / Installation . P/

N 5004899-5 , S/

N MAY85-I398 , TIR E P/ N 348F83-2 . S/

N OF F 12831294 . S/

N o n 62I2I2I0 . Se e Avial l Whee l an dBrak e Service s FA A For m8130-3 . 11 . 71302 5 Lef

t Engin e Lowe

r Cow l Removal/Installation , P/ N II59P20328-1 , S/

N ofr310 , S/

N o n 266 5 (LOA N ER) . Se e Aeroshea r

Aviatio n Services . Inc . FA A For m8130-3 . • • ; 12 . 714.'!25Right.EngineLowerCow l Removal/Installation , P/ N 1159P20328-1 , S/

N off3IJ,S/Non46l(LO.\NER) . Se e ^ Aeroshea r

Aviatip n Services . Inc , FA A For m813(>- 3 i i ~ I V ~ j 1.;.= : - MAINTENANC E RELEAS E ' l^^i^- . : l~ i Th e aircraft . airfTanie,'aircraf t engine , applianc e identifie dabov e wa s repaire dan dinspecte di n accordanc e with Manufacturer' s f- ' ' maintenanc e maniul , curren t maintenanc e rule s o f

theTediera l Aviatio n Regulatio n an di s improve dfo r retur n t o servic e with 1 respec t t o th e wor k

peribnhed . Pertinen t

detail s o f wor k perl^rmi dar e o n file a t

thi s Repai r

StationjAtfe r

wor k orde r No . 2280 . _^ .r ~ . rt ~ • ^ • SIGNE D 

# 3^ g Rodne y Bryan t

fo r Intertec h Overloa dInc .



### \S I

# ICERTIFYTHATTHISIS A TRUE^^ ^

O F THEjpmGINA L FA A VN Y FSD O

^ 

### %\Q

### INTE;:^TEC: H 7701 WOOD,. , Ave . Va n Nuys , C A 40 6 

### 818.904.195 5 Phon e 818.904.198 8 Fa x Repai rStatio n No . I0QR689 X 

# v

Make/Mode l GULFSTREA

M II B 

### REG. #

N477G G 

### Seria l

15 5 

### TIM E

12437. 5 

### CYCL

E 727 5 

### Dat e

JUL Y 14 , 200 7 WOR K ORDE R243 4 COMPLIE D WIT H TH E FOLLOWING : I . INSTALLE D A KG S 6 0 HERT Z POWE R C0NVERTF: R IA W THF . KO S FRIiQUENC Y CONVERTE R INSTALLATIO N O N Gi l AIRCRAF T MANUA L (NO . AAS-R7 I REVISIO N 7/6/07 . AN D ALS O IN.S'fALLE D TH E 6 0 HERTZ CONVERTE R IA W IF R WIR E DRAWIN G NO . 41551-001 . OPERATIONA L CHEC KSATISFACTORY . WEIGH T AN D BALANC E AN D EQUIPMEN T LLS T WER E AMMENDE D AN D MAD E PAR T O F TH E AIRCRAFT' S PERMANEN T RECORD S P/N O F CONVERTE R HSI2fl . 2 . INSTALLE D A NE W VORTE X GENERATO R IA W G2 B M M 57-00-OO.P/ N O N I S 11.S9W20n2-I3 . MAINTENANC E RELEAS E Th e aircraft , airframe , aircraf t engine , appliance identifie d abov e wa s repaire d an d inspecte d I n accordanc e wit h Manufacturer' s maintenanc

e manual , curren t maintenance rule s o f th e Federa l Aviatio n Regulatio n an d i s approve d fo rretur n t o service wit h respec t t o th e wor k

perfomicd . Pertinen t detail s o f wor k performe d ar

e o n file a

t thi s Repai rStatio n underwor k orde rNo . 243 4 SIGNE D •jgS::::^^^^-' - " Rodne y Bryant , fo rIntertec h Overloa d Inc .



### - ^ 

# 3 

# V

# ICERTIFYTHATTHISIS A TRU^O^YiJF^TH E ORIGINA L FA A VN Y FSD O

i i



### v. . 

# I.V '

### riiiiiiii i 770 1 Woodle y Ave , Va n Nuys , CA . 9140 6 818.904.195 5 Phon e 818.904.198 8 Fa x Repai rStatio n No . WOR KORDERS : 2314.234.' ! & 236 5 MAKE/MODE L GULFSTREA M 1159 B REG . No . N477G G 1

SERIA L No , 15 5 TIM E

12437. 5 CYCL E

727 5 DAT E

JUL Y 15 , 200 7 WOR K ORDERS : 2314.234 5 & 236 5 COMPLIE D WIT H TH E FOLLOWIN G CM P CODES : 1 . C/ W CM P 34101 3 - PILO T PITO T LEA KCHECK . 2 . C/ W CM P 34101 7 - CO-PILO T PITO T LEA KCHECK . 3 . C/ W CM P 21201 5 - CABI N PRESSUR E CONTROLLE R (MANUA L MODE ) OPS . TEST . <t . C/ W CM P 216027 - PRESSURIZATIO N SAFTE Y VALV E INSPECTIO N & FUNCTIONA L TEST . 5 . C/ W CMP21764 6 -BATTER Y FA N CIRCULATO R OPS . TEST . 6 CA V CM P 24102

3 - P I LO T INERTI A REE L OP S TEST . 7 . C/ W CM P 25401 0 - FIRS T AI D KI T INSPECTION-INSTALLE D NE W FIRS T AI D KI T P/i N 70002-00 . 8 . C/ W CM P 38011 1 - POTABL E H2 0 SYSTE M - FLUS H AN D SANITIZE . 9 . C/ W CM P 26101 5 - FIR E T HANDL E OP S CHECK . 10 . C/WCMP26I025-R1GHTENGINEFIREEXT . SYS . FUNCTIONA L TEST . 11 . C/ W CM P 26I5I 0 - LEF T ENGIN E FIR E ST L WEIGH T CHECK . 12 . C/WCMP26I5I5-RIGHTENG1NEFIREBTLWEIGHTCHECK . 13 . C/ W CM P 26175 8 - INSPECTIO N O F AF T LAV . HALO N FIR E EXTINGUISHER . M . C/ W CM P 261760-INSPECTIO N O F COCKPIT S I HALO N FIR E EXTINGUISHER . 15 . C/ W CM P 27010

5 - FLT . CONT . MANUA L SO V OPS . TEST . 16 . C/ W CM P 270150 - GROUN D SPOILE R OPS TES T ( 6 PANEL ) GIIB . 17 . C/WCMP270310-RUDDERCONT . SYS . OPSTEST(SP-50 ) 18 . C/ W CM P 2706l>-LUB E LEFTI/ B FLA P ACT . BUSHING . .- - ' 19 . CAVCMP2706I9-LUBELEFTO/ B FLA P ACT . BUSHING . 20 . C/ W CM P 270622-LUB E RIGH T I/B FLA P ACT . BUSHING . 21 . C/ W CM P 271022-ELEV . ACTUATO R DAMPE R SHAF T INSPECTION . 22 . C/ W CM P 272018-.AILERO N ACT . DAMPE R SHAF T (LEFT ) INSPECTION . - • r 23 . C/ W CM P 27201 9 -;AILERO N AC T DAMPE R SHAF T (RIGHT ) INSPECTION . 7 .. . 24 . C/ W CM P 27401 1 -JNPSEC T LEF T O/ B FLA P ACT . YOKE.. - • -• - 25 . C/ W CM P 274012-.INSPEC T LEF T I/ B FLA P ACT . YOKE . • 26 . C/ W CM P 274311-INSPEC T RIGH T O/ B FLA P ACT . YOKE . 27 . C/ W CM P 27431 2 - INSPEC T RIGH T I/ B FLP A ACT . YOKE . 28 . C/WCMP2805I5-APUFUELWINGS.O.V-FUNCT1ONALTES T 29 . c m CM P 32102 6 - CORROSIO N PREVENTIO N NL G AXL E ASSY . .30 ; C/ W CM P 32391 8 - REMOVAL/INSTALLATIO N O F LEF T SID E BRAC E ACTUATOR . .11 . C/ W CM P 32401'2 - INSPECTIO N LEF T MAI N GEA R STRIKE R ARM . .-(2 . C/ W CM P .325025-INSPECTIO N RIGH T MAI N GEA RSTRIKE RARM . 33 . C/ W CM P 33021 0 - EMERGENC Y EXI T LIGH T OP S TES T .1 4 C/ W CMP.33I5I0 - REPLAC E EMERGENC Y EXI T LIGH T BATTERY . P/ N OF F MNI300 , P/

N O N D2013 . .3 5 CAVCMP34l5l7-ATTrrUDEIND . # 1 BATTER Y OP S TEST-PS835 . 36 . CA V CM P .34706

7 - EMERGENC Y ATTITUD E GYR O POWE R SUPPL Y REMOVAL/

INSTALLATION . 37 . C/ W CM P .34403

8 - VO R SYSTE M CHEC K(FA R 91.171 ) J8 . C/ W CM P 38010 1 - FRES H WATE R SYSTE M FILTE R ELEMEN T REPLACEMENT . P/ N ALI10-G . 39 . C/ W CM P 491005 - AP U ENCLOSUR E INSPECTIO N (36-6) . 40 . C/ W CM P 491510-AP U OI L CHANGF7FILTE R CHECK . 41 . C/ W CM P 49I5I2-LUB E AP U ALTERNATO R SPLIN E (.36-6) . 42 . C/ W CM P 522525-TAI L DOO R WARNIN G OP S TEST . 43 . C/ W CM P 523010 - LUB E ENTRANC E DOOR . 44 . C/WCMP53I010-NOS E RADOM E INTERIO R INSP . 45 . C/ W CM P 53102 0 - INSPECTIO N O F FUSELAG E EXTERIOR . 46 . C/ W CM P 531540 - INSPECTIO N O F TAILCON E INTERIOR . 47 . C/ W CM P 53352 0 - INSPECTIO N O F COMPARTMEN T ENTRANC E (SHELF) . 48 . C W CM P 53451 0 - INSPECTIO N O F CABI N COMPARTMEN T (ABOV E FLOOR) . 49 . C/ W CM P 5.39020-INSPECTIO N O F RIGH T ML G INSTALLATION . 50 . C/ W CM P 54iq20-INSPECTIO N O F LEF T PYLO N INTERIOR . ? 51 . C/ W CM P 551025 - INSPECTIO N O F RUDDE R EXTERNAL . -J 53 . C/ W CM P 551026-RUDDE R BALLAS T WEIGH T INSPECTIO N (LEADONLY) . 53 . C/ W CM P 575002-RIGH T WINGLE T ATTACHMEN T HARDWAR E INSPECTION . 54 . C/ W CM P 575003 - LEF T WINGLE T ATTACHMEN T HARDWAR E INSPECTION . 55 . C/ W CM P 71102 0 - POWERPLAN T INTERNA L INSPECTION - NO . I ENGINE . 56 . C W CM P 711520-roWERPLAN T INTERNA L INSPECTION-NO . 2 ENGINE . 57 . C/ W CM P 78201 7 - LUB E LEF T THRUS T REVERSE R AF T PIVOT . (ASC384) . 58 . C/ W CM P 78.101 7 - LUB E RIGH T THRU.ST REVERSE R AF T PIVO T (ASC.1S4) . 59 . CA V CM P 261527-WEIGHTCHEC KO F COCKPI T PORTABL E FIR E EXT . (NO . I ) 60 . C/WCMP2hl5.15-WEIGH T CHEC KO F ENTRANC E PORTABL E FIR E EXT . 61 . C/ W CM P 261537 - WEIGHTCHEC KO F LAV . PORTABL E FIR E EX T 62 . C/ W CM P 5.3801 0 - INSPECTIO N O F NOS E WHEE L WEL L AN D GEAR . 63 . C/ W CM P 5.1851 0 MI. O WHEE L WEL L COMPARTMEN T INPSECTION . 64 . CA V CM P 53901 0 - INSPl-CTIO N O F LEF T ML G INSTALLATION . 65 . C/ W CM P 54152 0 - RIGH T PYLO N INTERIO R INSPECTION . 66 . C' W CM P 71.101 1 - I.KI T ENGIN E NOS E COW L INSPECTIO N 67 . C.WCMP7I45I I - RIUI H ENGIN E NOS E COW L INSPECTIO N \ f. 8 C.A V CM P 491010-,M'UGrCP.16- 6 OP S TEST . 6 9 C W CMP4940.1 0 . AI' U OTCI'.16- 6 EG T TIIERMO.STAT Rr:MOVAI..INSTALl.ATION . 70 C W CMI " 49251 0 - AP U GTCP,16- 6 REMOVAL/INSTAl,l. A tlO N 7 1 C W CM P 92536 0 INSPECTIO N O F BAGGAGi ; DOO R CRAC K5-9 9 NEX T DI E 'S ' 12487. 5 IIRS . COMPLIK D nilI I rut : IVU.OniSOM.USTF.S.ISCE : 7 ^ RI:M0VH D AN D Rfil'I.ACE D AP U OTCP36- 6 EGT 1 1 IliRMOSTA T IV. \ OF F 107996-4- 1 S/

N 511 : P/ N O. N I29S5.52-I- 1 S/N 1101 . 73 . C W CM P 35161 0 - IIVDROSTATI C TE.S T O F NO. I (1 2 DOirii; . D.VT E O F ll \ DRO : W W 22"" , 2007 . 

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4 S/ N OFF . P/N ' O N 900-700-03.^-03 4 .S/ N O N F20fl26l . D.O..V

L NOVE.MBER1998 . 79 . C/ W CM P CODE S 34651 0 AND 34651 5 - REMOVE D AN D RE-INSTALLE D REPAIRE D PILOT S AND CO-PILOT S AIRSPEE D INDICATORS . SE E GLOBA L TEC H FORM(S ) 8I30-3.NO . S86I 3 * .S8614 . 80 . C/W CM P CODE S .347020 AN D .34702 5 - REMOVE D AN D REPLACE D PILOT S AN D CO-PILOT S COURS E INDICATOR S AFTE RREPAI R SE E GLOBA L TEC M FA A FOR.V I 8130- 3 (2) . SI . C/W CM P COD E 77452 5 - REMOVE D LEFT ENGIN E TACHOMETERINDICATO RAN D REPLACE D IT WITH A REPAIRE D UNIT . P/ N OFFH90I-245S/NOFF346D , P/ N O N H901-24.SS/

N O N 2S1E . 82 . C/ W CM P 73752 5 - REMOVE D RIGH T ENGIN E FUE L FLO W INDICATO RAN D REPLACE D IT WIT H A FUNCTIONALL Y TESTE D UNIT . P/ N OF F H930- 6 S/

N OF F I03C , P/

N O N H930- 7 S/

N O N I iSB . 83 . C/W CM P .14701 0 - REMOVE D NO . I FLIGH T DIRECTO RINDICATO RAN D SEN T OU T FORREPAI RAN D REINSTALLED.OP S CHEC K GOOD . P/

N 792-6357-00 7 S/

N 40.SI . 84 . C/ W CM P 22201 0 - REMOVE D AUTOPILO T CONTROLLE RAN D REPLACE D IT WIT H A REPAIRE D UNIT . OP S CHEC K GOO . P/

N OF F 2.^86689-90 3 S/

N OF F 09771837 , P/

N O N 22.^86689-90 3 S/

N O N O.'i80762 . 85 . C/ W CM P 22101 5 - REMOVE D ROL L AXI S COMPUTE RAND REPLACE D I T WIT H A REPAIRE D UNI T P/ N OF F 4049729-90 1 S/

N OF F 1091121 , PN/O N 4049728-90 1 S/ N O N 035I62I . 86 . REPLACE D RIGH T WIN G ROO T LIGH T BULB . OP S CHECKE D GOOD . P/ N 4559 . 87 . C/ W CM P 33203 5 - L/

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N 1IS9W20I24-42 . 92 . REPLACE D LEF T I/ B FLA P SEAL . P/

N 1159W20224-42 . 93 . CA V CM P COD E 7I302 S - REMOVA L AN D INSTALLATIO N O F L/ H LOWE RCOW L AFTE RREPAIR : P/ N OF F I l.';9P20328- l S/ N OF F 266.S(LOANER) , P/

N O N I I.S9P20328- 1 S/

N O N 310 . SE E AEROSHEA RFAA FORiV I 8130-3 . 94 . C/W CM P COD E 71452 5 - REMOVA L AN D INSTALLATIO N O F R/ H LOWE RCOW L AFTE RREPAIR : P/ N OF F I I.S9P20329- I S/ N OF F 46l(LOANER) , P/

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N OF F 8.SIA K

S/ N OF F 2.^603 . P/

N O N 851A K

S/ N O N 1S7037 . SE E FA A FOR M 8130-3 . 96 . CA V CM P 34201 5 - CO-PILO T PITO T HEA D REMOVA L & INSTALLATION , P/ N OF F «5IA K

S/ N OF F 2.S602 , P/

N O N 8.S1A

K S/ N O N 217370 . SE E FA A FOR M 8130- 3 -r".. - --r"-.- . ---.. _ 97 . C/ W CM P 24763 5 - BATTERY FAILURE MONITO R/AMPLIFIER . P/ N OF F II59AV213I2- 3 S/ N OF F 313C , P/

N O N 1 l.'i9AV2I312- 3 S/ N O N I83C . SE E FA A FOR M 8(30-3 . ' • ' • " ' . 98 . REMOVED^UDI O CONTRO L CENTE R# 1 AN D R^pLXCE D I T WIT H A REPAIRE D UNIT:. ^ OF F 522-3763-00 2 S/ N OF F 4983 , PI H O N 522-37634)0 2 S/

N O M 633 . ; ; 99 . REMOVE D AUDI O CONTRO L CENTE R# 2 AN D REPLACE D IT WIT H A REPAIRE D UNIT : P/ N OF F 522-3763-00 2 S/ N OF F 4982 , P/

N O N 522-3763-00 2 Sfl

N O N 1943 . 100 . REMOVE D KLN-90 0 AND SEN T FO RREPAI ROP S CHEC K GOOD . P/

N O66-O4034-OIO

I S/ N 1780 . MAINTENANC E RELEAS E Tli e aircraft , airframe , aircraf t engine , applianc e identifie dabov e wa s repaire dan dInspecte di

n accordanc e with Manufacturer' s maintenanc e manua l an dcurren t maintenanc e rule s o f

th e Federal Aviatio n Regulatio n an di s approve dfor return t o servic e wit

h respec t t o th e wor

k performed . Pertinen t

detail s o f

wor k performe dare o

n file a t tlii s Repai r

Statio n unde r

wor k orde r NO's . 2314 , 234 5 & 2365 . .. - SIGNE D RoSneySryant , Fonntertec h Overload , Inc .



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AUG . 23 , 200 7 HOR KORDE R 2.111 5 COMPLIE D WIT H TH E FOLLOWIN G M.MNTEN.4NCE : 1 . C/ W CM P 36201 0 - REMOVE D A DEFECTIV E LEI' f II P VALV E AN D REPLACE D I T Will i A TESTE D H P PRESSUR E VALVE . RE l ERENC E FA A FOR M 8130- 3 UNDE R Wi.'R KORDE R AR00I02OI . IAW G 2 M M ClIAP T 36-OI-OO.C/

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N OFF : H93»- 6 P/

N ON : II9J00- 7 S/N OFF : 115 B S/N ON : 101 . 5 . COMPLIE D WIT H CM P 34501 5 BRI l E TUB E INDICATO R CONSOL E - REMOVA L / INSTALLATION . REMOVE D Lf)ANE R RADA R INDICATO R AN D INSTALLE D OVERHAULE D RADA R INDICATOR , REFERENC E DUNCA N AVIAHO N CRS # JOVRI94 F FA A l-OR M 8130- 3 UNDE R WOR KORDE R V2WS A DATE D 7-21-2007 . P/ N 0KI70N : 006-3086-3 0 S/ N OFFrX346 4 S/N O.N : 3327 . f ^ * " -r^ T -^-T , .MAINTENANC E RELEAS E —i ; .-.41 w aircraft , airrrame , aircraft engine , appliance i<lentifie d abov e wa s tepaire d an d inspecte d i n accordanc e wit h Manufacturer' s '^"maintenanc e manual , curren t maintenanc e rule s o f th e Federa l .\viutiotfRegulatior , an d i s approve d fo rretUFrTtb servic e wit h 5 . respec t l o th e wor k

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t thi s Repai rStitio n under-wor k orde rNo . 250 5 SIONE D \:i\~} ' Rodne y Bryaii L fo rIntertec h Overloa d Inc .

# ICERTIFYTHATTHISIS A TRU E COaY45 F TH E ORIGINA L FA A VN Y FSD O

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## OVE;RI_O.A. D 770 1 Woo d " \ve . Va n Nuys , CA . .40 6 818.904.195c ) Phon e 818.904.198 8 Fa x Repai rStatio n No . I0QR689 X 

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AUGUS T 27 , 200 7 WOR KORDE R 246 4 COMPLIE D WIT H TH E FOUOWIW G MAINTENANCE : 1 . SERVICE D OXYGE N SYSTEM . 2 . SERVICE D EMERGENC Y GEA R BOTTL E WIT H NITROGEN . 3 . SERVICE D POTABLE WATERSYSTEM . 4 . INSTALLE D A CIRCUI T BREAKERFO RTH E 6 0 HERTZ FREQUENC Y CONVERTE RPERIF RDRAWING * 41551-001 . 5 . REMOVE D RIGH T ENGIN E H P RP M INDICATO RAND SEN T OU T FO RREPAIR , REINSTALLE D REPAIRE D H P RPM INDICATOR . REFERENC E GLOBA L TEC H INSTRUMENT S INC . CRS #G3OR20 8 FAA FORM 8130- 3 UNDE RWORK

ORDER5888 4 DATED 8-2-2007 . P/ N OFF/O N 11901-244 S/ N OFF/O N 2.52E . 6 . 7 . UPDATE D NA V DAT A BASE . NEX T UPDAT E DU E SEPTEMBE R27TM , 2007 .

MAINTENANC E RELEAS E Th e aircraft , airframe , aircraf t engine , applianc e identifie dabov e wa s repaire dan dinspecte di n accordanc e wit h Manufacturer' s maintenanc e manual , cunen t maintenanc e rule s o f

th e Federal Aviatio n Regulatio n an di s approve dfitir return t o servic e with respec t t o th e wor

k perfoimed . Pertinen t

detail s o f wor k performe dar e o

n fil e a t thi s Repai r

Statio n unda^^ % orde r No , 246 4

• :»-" * .4. " * "• * Rodne y Bt^ant . forIntertec h Overloa d Inc .



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### iJiiiii'ii 770 1 Wood I 'e . Van Nuys , CA . 9140 S 818.904.195i , , ..on e 81 8 90 ^ 193 8 Fax Repai rStatio n No . 10QR689X

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15 5 TIM E

12452. 1 CYCL E 729 4 Dat e

SEP T 25 , 200 7 WOR K ORDE R2.12

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M FILT|; REI.EMlrN T R|:M0VAL/1NS I AI.I.ATION . 3 . C/ W CMP3S011 1 - POIABI. E WATERSY.STE M FLUSH . 4 . C/ W CM P - NO, l I:M1:RGENC V ATTITUD E INDICATO RH A TTI RY OI' S TE,ST , 5 . C/ W CMP.33151 0 - EMERGENC Y EXI T LIG l I T BATTER Y REPLACEMENT . 6 . C/ W CMP26n6 0 - PORfABL E HALO N FIRI - EXTINGUISHE RINSPECTION ( CCX^KPIf ) 7 . C/W CM P 26175 8 - PORTABL E HALO N FIRE EXTINGUIS I lE R(AI T LAVATORY ) INSPECTION , 8 . C/ W CM P 2.';202 0 LIF E VEST S - INSPI:CTIO N RECERTIl-CA J ION , 9 . C/ W CM P 32301 0 - NOS E GEARWHEEL AN D TIR E (LETT ) REMOVAI7IN,SI"AI.LATION , I'/ N WHEE L ,'\SS V OFF/O N 9.5433* 7 S-T

M OF F NO\80-767 5 S/O N OCT8I-833 . P/ N TIR E O I F/O N 217K22- I ST X OF F .5342030 6 S/

N O N 30-580676 . REFERENC E AER O 'NVHEEI , A N BR.VK

E FA A FOR M 813C-3 . UNDE RW/ O 3366 5 D,\ l E D 8/6/03 . 10 . C/ W CM P COD E 98454 0 C B 45 4 - INSPECTIO N O F RUDDE RSTO P BOL T S . 11 . CM P COD E 98452 0 - C/ W C B 45 2 - REPLACEMEN T O F AILERON/ELEVATO RLOA D RELIEF BUNO t E S 12 . CM P COD E 25203 1 - NO. I LIF E VES T REMOVAL/INSTALL , INSPECTION NF.XT DUE 9/12/09 . 13 . CM P COD E 25203 2 -NO. 2 LIFE VES T REMOVAL/INSTALL , INSPECTIO N NEX T DU E 4/18/2017 . 14 . CM P COD E 25203 3 - N0. 3 LIF E VES T REMOVAL/INSTAL L INSPECTIO N NEX T DU E 4/18/2017 . 15 . CM P COD E 252034-N0. 4 LIF E VES T REMOVAL/INSTALL . INSPECTIO N NEX T DU E 4/18/2017 . 16 . CM P COD E 25203 5 - N0. 5 LIF E VES T REMOVAL/INSTALL , INSPECTIO N NEX T DU E 3/07/2010 . 17 . CM P CODE ; 252036 - N0. 6 LIF E VES T REMOVAL/INSTALL . INSPECTIO N NE.X T DU E 3/07/2010 . I g . CM P COD E 252037J:;;NO. 7 LIF E VFIS T REMOVAL/INSTALL , INSPECTIO N NEX T DU E 3/07/2010 .



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# y ^ fc19 . CMPC i L>2038-NO.8Lll"EVE,S l , ..AIOVAI./1NSTAL1. . I' \ .flO N NEX T DU E 3/07/2 C 20 . CM P COD E 252039 - N0. 9 LIF E VES T REMOVAL/INSTALL , INSPECTIO N NEX T Dli E 3/07/2010 . 21 . CM P COD E 252040-NO . 1 0 LIF E VES T REMOVAL/INSTALL . INSPECTIO N NEX T DU E 4/lg,'2017 . 22 . CM P COD E 2.^204 1 - NO. I I LIF E VES T REM0VA171NSTAI.1, , INSPECTIO N NEX T OL E 3/07/2010 , 23 . CM P COD E 252042 - N0.I 2 LllT- l VES T REMOVAI./lNSTAl.L . INSPECTIO N NEX T D ( ! E 9/12/2009 . 24 . CM P C0DI- ; 2.1204 3 - NO.1 3 LIF E VES

T REMOVAL/INSTAL L INSPECTIO N NE X f DUl - 4/18/2017 . 25 . CM P CODi;25204 4 - Nf).l 4 LIF E Vi:. S 1 REMOVAL/INSTAL L INSPECTIO N NEX T Dl'i ; 3/07/2010 . 26 . CM P COD E 25205 7 - PILOTS LIF E Vi:S T REMOVAL/INSTALL . IN.S1'ECTK) N NEX T DU E 4/IS/20I7 . 27 . CM P COD E 252058-CO-PILOT S LIF E VES T REMOVAL'INSTALL , INSPECTIO N NEX T DU E 4/18/201 7 28 . C/ W CM P 24031 0 - D C DISTRBUTIO N SYSTEM OPER.ATIONAI . CHECK . 29 . C/ W CM P 247590 - A C DI.STRIBUTIO N OPERATIONA L CHECK . 30 . C/ W CMP270610-RUDDERPEDALCONTROLS-LUBRICATIO N 31 . C/ W CM P 31151 5 - TON E GENERATO R SPEAKE R REMOVAL/INSTALLATION . P/ N OE F .5.57-4-000 , P/N O N 105145 , S A OF F 265 , S/N O N N/A . 32 . C/ W CM P 77301 5 - R/ H ENGIN E TGT'INDICATO R REMOVAL/INSTALLATION . REMOVE D AN D REPLACE D FO R TROUBLESIKXJTIN G PURPOSES . OP S CHEC KGOOD . 33 . C/ W CMP34403 8 - VOI^IF R CHEC KPE R FA R 91.171 . C:OMPLIE D WIT H TH E FOLLOWIN G MAINTENANCE : 1 . REMOVE D PYLO N BAGGAG E LIGH T BUL B AN D INSTALLE D NE W LIGH T BUL B IA W CHAPTE R 3 3 O F TH E -^GlIBMM . P/NCE307 . .tr . .t^. . ' t r. • . .•:* - • .-i i - • - •.:i i - - } - 2 . - REMOVE D AN D REPLACE D UPPE R TAI L NAVIGATIO N LIGF . T BUL B IA W CHAPTE R 3 3 O F TH E GII B MM . P/ N ^6i a ^ t = i '•^^- ' • ^~^ ' ' • 3 . -^REMOVE D AN D REPLACE D ICELIGH T BUL B WIT H NE W LIGHT'-BUL B IA W CHAPTE R 3 3 O F THEXiU B MM . P/NA7079B-24 . " « t; ^ -U , 4 . INSTALLE D NE W 0 2 BLOWOU T DIS C AN D SNA P RIN G IA W TH E GII B MM , CIlAPTE R 35 . P/ N P28070 - DISK . MSI6625I062-SNA P RING . ' • - : • " 5 . REMOVE D FLOORBOARDS . CLEANE D AN D REMOVE D CORROSIO N O N FLOORBOARD S AN D STRUCTUR E PE R SR M 51-13-20 , REPLACE D ON E FLOORBOAR D AN D TW O NUTPLATES , FLOORBOAR D P/ N II59BH2I006 - 3 . REINS'VALLE D FLOORBOARDS . REFERENC E AEROSHEA R WOR KORDE R C07-I057 2 DATE D 9/18/200 7 IA W TH E DRAWIN G NUMBE R I I59BH40022REV.E . - REMOVE D SPLI T WATE R DRAI N LINE , CLEANE D U P ElMTIiAPPPE D WATE R AN D SURROUNDIN G AREA , REMOVE D CORROSIO N PE R SR M 51-13-20 , PROTECTE D ARE A WIT H AV30 . INSTALLE D NE W WATE R DRAI N LINE . P/ N I24001-8CR04SO . OP S CHEC KGOOD . REMOVE D CONTACTO R I N AP U JUNCTIO N BO X AN D IN.STAI.LE D NE W CONTACIOR , CONTACTO R OPS CHECKE D GOOD , IA W TH E GII B MM . CHAPTE R 24-01-00 . P/ N OFF/O N DII-25B. V .S/ N OF F C-8I92 9 S/ N O N CP 8813.5 . REMOVE D DIMMIM G RHEOSTA T FO R TH E RADA R ALTIMETE R AN D INSTALLE D A NE W RHEOSTA T P/N KV6N A VSI)50I.A . IA W TH E GII B WDM . CHAPTE R 24 , MAINTENAN<: E REI.E.AS E T h e aircmn . airframe , aircraft engine , applianc e identifie d abov

e wa s repaire d an d inspccle d i n ac.;ordanc e wit h Manufacturer' s mainlenane e manual , curren t maintenanc e rule s o f th e Fedeni l Aviatio n Regulatio n an d i s approve d fu rretur n t o servic e wit h respec t t o th e wor k

performed . Pertinen t detail s o f wor k perfomie d ar

c o n file a

t thi s Repni rSlatici i unde rwor k jtrder-No.-252 4 siGNED';7^:<rrr^ - —

- Rodne y Hrjant , To

rIntertec h Oierloa d Inc .

# ICERTIFYTHATTHISIS A TRU E Ci>PyX) F TH E ORIGINA L FA A VN Y FSD O 

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## lNTE.?5lTE<r H 0\^E?:il_OA. D 770 1 Woodle y Van Nuys , CA . 9140 6 818.904,1955 1 . ? 818.904.198 8 Fa x Repai rStatio n No . 10QRS89 X

Make/Mode l GULFSTREA

M II B REG. #

N477G G Seria l

15 5 TIM E

12482. 1 CYCL E 730 7 Dat e

OC T 25 , 200 7 WOR K ORDE R255 2 COMPUE D IHn i Till : FOI.I.(nHS(iM.UNTENASCE : I r.-W rX'Pi+10.18-VOR/IF K CHEC K lA W FA R0 1 17 1 2 . C W CM P :.'!2IV. O . KI T SERVICE/FUNCTIONA L f Hr;C K IA W FAR9 1 20 7 BATTER Y EXPIRr S OC T 20O X I . fV W C M P 2617.i!| l - I'ORTABLF . HALO N FIRC EXTINGUISHE R(AF T LAV ) INPSPECTIO N 4 C W (M P 2617.5 0 - TORTADI.E HALO N FIRE E,\TINGi;iSHE R((OfKP I D INSPECTIO N

. < C/ W CM P j;i2I O - LI-.F

T ANTISKI D VALV E FILTE RINSPECTIO N 6 C/WCMP32i:i5-RlGHTANTISKIDVALV E FILTE RINSPECTIO N 7 . CA

V CM P 26183 0 -e\GINfc/AP U FIR E BOTTL E (APU , SERVIC E LIFE ) CARTRIDG E REPLACEMENT . t . C W CM P 3.^101 0 - 0 1 SYSTE M (PILOT ) OPERATIONA L TES T 9 . C/ W CM P .15101 5 - 0 2 SYSTE M (COPILOT ) OPERATIONA L TEST . 10 . C W CM P .163UI

2 - APU/E.iCTERNA

L AI RCHEC K

VALV E - OPERATIONA L TEST . II . C/ W CM P MSOSl-UPDAT E OF NDB 2 NA V DAT A BAN K 12 . C/WCMP32I8IS - BR-'KEdtlGHD-BLEEDINGPROCEDURES . 13 . C/WCMP32I3I 5 • ANTISKI D CONTRO L SYSTE M FIWCTIONA L TEST . M . C/Vi ' CM P 32 1 i m- WHEE L BRAKI S - FtWCTlONA L TEST . 1.1 . C/ W CM P .12181 0 -DRAK E (LEFT ) BLEEDIN G PROCEDURrS . 16 . C/ W CM P 27S8 1 .

< - ANGL

E O F ATTAC K

TRANSDUCE R(N O 2 ) REMOVAL/INSTALLATION . P/ N OFF/O N SLZi)t>9 2 SiT * OF F LHI173 B S/

N O N LH1325C . 17: ' fERVICEDHYDRAULICSYSTEM S IA W TFI E on e MM . CHAPTE RII-OWIO . ^ " ; '~ ' l > {•/W'CMP2705l6-ANGLEOrATTACKSYSTE6PSTEST . * " *• " W. " _tV W CM P 30irr, 0 - PROB E HEA T (ANGL E O F ATTACK)-OP S TEST . 20."'.~r/ W CM P 23152 5 • .Nl) . VT-I F TRANSCEIVER'--REM0VAL/INSTALLATI0N . P/ N OF F 622-IJ34r00 2 ST

U OF F 'M 6 P/ N O N 622-1879-00 1 S/

N O N 20279 . 2U—X/WCMP.141010-PPITOTSTATICSYSTEMLEAKCHECK . Z IL- _ 12 . E0V;>RRFLlGimNSPnt-nO N IA W TH E OllDSERlAl.NUMBE R15 5 AIRPLAN E FLIGH T MANUAL . ; ; , - * " • » • -.*

—- • ^»

_. . ,.*

_- > ; MA1NT£NA.MC E RELKAS E Th e liiciaft , liiframu . aircfal l vnylre , ipplitnc e identifitfi l abov e wa s repnirc danil inspeLte di n icuonlars e \%it h Manufacturer' s mainten^ ^ manual , curren t maintenanc e . rulti s ofth e Federa l A--ii(in n Regulatio n an di s appiDve dfor let.in i lu scrv'c u wilt : respec t t o th e wjrt ; perromied . Pertinen t detait s o f

wo t k ^rhyme dar e o n fil e a t

thi s Rxrpa i .Station unde r

wrir k orde i No . 255 2 SIONE E Rodne y Bryant , for

Intertec h Overloa dInc .



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## INTEP^TEC H CDvEP5LOAi 3 770 1 Woodle y •^• . Va n Nuys , CA , 9140 6 818,904,195 5 l e 818.904.198 3 Fa x Repai r Statio n No . 10QR689 X

Make / Mode l GULFSTREA

M II B REG. #

N477G G Seria l

15 5 TIM E

12502. 0 CYCLE

731 1 Dat e

NOV . 15 , 200 7 WOR K ORDE R259 7 COMPLIE D WIT H TH E FOLLOWIN G CMP : 1 . C/ W CMP35153 0 REPLACE D OXYGEN FILLE RVALV E WITH NE W VALVE . N O FURTHE RDEFECT S NOTED . P/ N O F VALV E MS22035-1 . COMPLIE D WIT H TH E FOLLOmN G MAINTENANCE : 2 . SERVICE D LEF T HAN D ENGIN E OI L IA W TH E GII B MM . CHAPTE R12-01-06 . 3 . SERVICE D RIGHT HAN D ENGINE OI L IAW TH E GII B MM , CHAPTE R12-01-06 . 4 . SERVICE D AP U OI L IA W TH E GII B MM , CHAPTE R12-01-06 . 5 . C/ W PREFLIGH T INSPECTIO N IA W TH E GII B SERIA L NUMBE R15 5 AIRPLAN E FLIGH T MANUA L MAINTENANC E RELEAS E Th e aircraf

t airframe , aircraf

t engine , applianc e identifie dabov e wa s repaire dan dinspectedi n accordanc e with Manufacturer' s maintenanc e manual , curren t maintenanc e rule s o f

th e Federal Aviatio n Regulatio n an di s approve dfoilFetu mt o servic e wit h

. respect t o th e wor

k performed . Pertinen t

detail s o f wor k performe dar e o n fil e a t

thi s Repai r

Statio n underwof e orde r No . 259 7 • ^ -. - ? V SIGNEE _^ _ * ' * " Shan e Hunt , foiTnfcrtech Uverlbi dInc .



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## INTERTEC H

Ox/'E^^I-OU& O 770 1 Woodle ^ \ Va n Nuys . CA . 9140 6 818.904.1955 . .n e 818.904.198 8 Fa x Repai rStatio n No . I0QR689 X

Make / Mode l GULFSTREA

M II B REG. #

N477G G Seria l

15 5 TIM E

12525. 5 CYCL E 731 9 Dat e

N0V.30 , 200 7 WOR K ORDE R262 8 COMPUE D WIT H TH E FOLLOWIN G CMP : I . C/W CM P 34805 1 - PERFORME D SATISFACTOR Y FM S NA V DAT A UPDAT E IA W UNIVERSA L UNS- I TEC H MANUAL . EXPIRE S I2J^0/07 . C/W CM P 32200 5 - LANDIN G GEA RHANDLE REMOVAL/INSTALLATION . P/ N OF F A486- 5 P/

N O N A486-1I , S/

N OF F 13 , S/

N O N 46 . REFERENC E EATO N AEROSPAC E FA A FOR M 8130- 3 UNDE RW/ O 2006940 , DATE D 3/20/06 . C/ W CM P 56152 0 SID E WINDO W PANE L (LEFT ) REMOVAL/INSTALLATION . REFERENC E GULFSTREA M FAA FOR M 8130- 3 UNDE RW/ O AOO l I03S60I , DATE D 9/10/01 . P/ N OFF/O N 159B10002-S115 , S/ N OF F 6H-5-3-105 , S/

N O N 010.58H2028 . C/ W CM P 30101 0 - WINDSHIEL D HEATIN G SYSTE M OP S TEST . C/W CM P 32030 6 - LANDIN G GEA RCYCLIN G OP S TEST . CA V CM P 320310 - NORMA L LANDIN G GEA RFUNCTIONA L TEST . C/ W CM P 290 1 lO-flYDRAULI C SYSTEM RESERVOIR . —

* - i - •- • i - C/W CM P 32131 5 - ANTISKI D CONTRO L SYSTE M FUNCTIONA L TEST . C/ W CM P 326830-MAI N GEA RWHEE L AN D TIRE'(LEF T O/ B NO.I ) REMOVAL/INSTALL . REFERNC E AER O WHEE L AND BRAK E FA A FORM 8130- 3 UNDER-W/ O 44898 , DATE D 11/30/07 . JiVHEE L ASSEMBL Y - P/ N OFF/O N 1159SCL20»3 , S/ N OFF/O N FEB83-741/AUG83-920 . TIR E - P/ N OFF/O N 348r83- 2 S/ N OF F 6024128 9 S/NON7I0H16L*-* - -.r^^ - -,r*--=^ -

» f i 10 . C/W CM P 32071 0 MAI N LANDIN G GEA RWHEE L BEARING S INSP/PACK . ' " 11 . CA V CMP326814rWHEE L BRAKE ASSY . INSPECTION . 12 . CA V CM P 326816-BRAK E PISTO N CLEARANC E CHECK . 13 . C/ W CM P 32684 0 - MAI N GEA RWHEE L AN D TIR E (RIGH T I/ B N0.3 ) REMOVAL/INSTALL.REFERNC E AER O WHEE L AND BRAK E FA A FOR M 8130- 3 UNDE RW/ O 44897 . DATE D 11/30/07 . WHEE L ASSEMBL Y - P/ N OFF/O N 1159SCL2IU-33 , S/ N OFF/O N MAR82-44 L TIR E - P/ N OFF/O N 348F83- 2 S/ N OF F 6018167 9 SI S O N 70970177 . 

## 1

v. .

# ICERTIFYTHATTHISIS A TRU E C^ Y O F THEORIGINA L FA A VN Y FSD O14 . C/ W CM P 32072 5 MAI N LANDIN G GEA RWHEE L BEARING S INSP/PACK . 15 . C/ W CM P 32732 4 - WHEEL BRAK E ASSY . INSPECTION . 16 . C/ W CM P 327336 - BRAK

E PISTONCLEARANC E CHECK . 17 . CA V CM P 32684 5 - MAIN GEA RWHEEL AN D TIR E (RIGH T O/ B N0.4)REM0VAL'INSTALL.REFERNC E AER O WHEE L AN D BRAK

E FAA FOR

M 8130- 3 UNDE RW/

O 44896 , DATE D 11/30/07 . WHEE L ASSEMBL Y - P/ \ OFF/O N 1I59SCL203-3I , S/ N OFF/O N NOV79-I5E . TIR E - P/.N OFF/O N 348F83- 2 S/ N OF F 60181687 , S/

N ON 71211163 . 18 . C/ W CM P 32072 0 - MAI N LANDIN G GEA RWHEE L BEARING S INSP/PACK . 19 . C/ W CM P 32731 4 - WHEEL BRAK E ASSY . INSPECTION . 20 . CA V CM P 327316 - BRAK

E PISTO N CLEARANC E CHEC K 21 . CA V CM P 32130 5 - WHEE L BRAKE S FUNCTIONA L TEST . 22 . CA V CM P 23251 0 - AUDI O AMPLIFIER - REMOVAL/INSTALLATION . REFERENCE AIR S FA A FOR M 8130- 3 UNDE RW/

O 14513 . DATE D 1/28/1999 . P/ N OFF/O N 522-3763-00 2 S/ N OF F 1943 , S/

N O N 1936 . 23 . CA V CM P 32182 5 - CHEC K WHEEL BRAK E WEAR . COMPLIE D WIT H TH E FOLLOWIN G MAINTENANCE : I . FABRICATE D AIRCRAF T DATA PLAT E USIN G 0.03 2 30 1 .2 5 HAR D STAINLES S STEE L SHEE T META L AN D ATTACHE D USIN G CR3213-4- 3 RIVET S ( 4 EACH) . AL L WORK WA S DON E IA

W FA R45.1 3 AN D GULFSTREA M AEROSPAC E ENGINEERIN G DRAWIN G II59SB40042 . \L4INTENANC E RELEAS E Th e aircraft , airfiame , aircraf t engine , applianc e identifie dabov e wa s repaire dan dinspecte di n accordanc e with Manufacturer' s maintenanc e manual ^ curren t maintenanc e rule s o f

th e Federa l Aviatio n Regulatio n an di s approve dfo r return t o servic e with' ' - , respec t t o th e work

performed . Pertinen t

detail s o f work perfoime dar e o n file a t

thi s Repai r

Statio n unde r

wor k orde r No . 262 8 * ' \£'~'' ~ f^i- i SIGNED^ A^r:^^^^^^ ^ ^• : "I. . —j ; Shan e Hunt , fo r Intertec h Overloa dInc.'- ,



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# ICERTIFYTHATTHISIS A TRU E CO^ y O F TH E ORIGINA L FA A VN Y FSD O

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# I ertec h Overload , I

77D 1 Woodle y Avenu e » va n Nuys . C A 9140 6 » phon e B1B.904 . 195 5 » fa x 818.904.198 8 Maintenanc e • Avionic s • Managemen t • Part s Sale s • Aircraf t Sale s • 24/ 7 Emergenc y Suppor t



## Januar y 23,200 8 Mr . Arvie McOumi s Principa l Maintenanc e Inspecto

r - Airworthines s Federa l Aviatio n Administratio n Va n Nuy s FSD6 . 

## 1650ijSiLerman,)jV:ay, Suit

e 33 0 Va n Nuys , C A 9140 6 Dea r fiispector McGiimis : I a mwriting t o yo u regardin g th e overloo k tha t occurre dwit

h respec t t o th e absenc e o

f ou r ratin g to perfor

m maintenanc e o

n .al l G-1159 B Aircraf

t Hii s wa s simply a

n overloo k o n ou r behalf an dwe apologiz e fo

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t thi s ha s cause

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t entrie s hav e bee n correctedby replacin g th e Repai r Station numbe

r

. wit h the appropnigit

e Certificat

e Numbe r o f th e individual wh o signedtiie maintenanc e release . Al l amende d entrie s wer e reviewe dby Intertech Overloa dan dVa n Nuy s FSDO . To ensur e tha t thi s never happen s agai

n prio r t o an y wor k bein g performe

db y Intertec h Overloa

dpersonnel I will personall

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Operation s Specification s an dverif y tha t we ar e properly rate dt

o perfor mth e requiredmaintenance .

Shan e Hun t Qualit y Manager . FA A C.R. S Noi IOQR689 X 

# RECEIVE D

. 

# JA N 2 3 i m v. . 

# VA N NUY S FSD O_ _]1 . . _l f additiona l spac e i s require d fo ran y item , attacf . cnalstieel s o f pape r Sr ^ -srvDM B Ap3rove»e¥eg-001 0 

# Q U.S . Departmen t o f Transportatio n Federa l Aviatio n Administratio n 

### Applicatio n fo rj^jo y 2 9 200 ? Repai rStatio n Ceitificat e and/o rRatin g M M f iv n rr . 

# VA N N U rtr r 

# «ee 1 . Repai rStatio n Name , Number , Locatio n an d Addres s a . Officia l Nam e o

f Statio n 

### INTERTEC H OVERLOA D INC . Numbe r 

### IOQR689 X b . Locatio n wher

e busines s conducte d 

### 770 1 WOODLE Y AVENU E VA N NUYS , C

A 9140 6 _ L 2 . Reason s fo rSubmissio n

c . Officia l Mailin g Addres s of Repai rStatio n (Number , Street , City , State & ZIP ) 

### 770 1 WOODLE Y AVENU E VA N NUYS , C

A 9140 6 d . Doin g Business As : 

### FA A CERTIFIE D REPAI R STATIO N I 1 Original/Applicatio n fo rCJertificat e an d Ratin g r~ l Chang e i n Ratin g r~ l Chang e i n Locatio n o rHousin g an d Facilitie s n Chang e i n Ownershi p S Othe r(Specify

) 

### AD D LEA R 4 0 SERIE S T O RATIN G AD D LEA R 45 SERIE S T O RATIN G AD D GULF . 1159 B T

O RATIN G 3 . Rating s Applie d fo r 

### [ D Airfram e D Clas s 1 n Clas s 2 • Clas s 3 n Clas s 4 

### | G Accessorie s n Clas s 1 Q Clas s 2 n Clas s 3 

### • Powerpian t n Clas s 1 n Clas s 2 Q Class 3 

### n Propelle r D Class 1 n Clas s 2 

# n Radi o D Clas s 1 n Clas s 2 O Class 3 

### • Instrumen t

n Clas s 1 D aass 2 O Clas s 3 D Clas s 4 

### I Limite d [ ^ Airiram e n Engin e n l^ropelle r D Instrumen t f l Accessorie s

n Landin g Gea r n Float s 

### n Radi o O Roto rBlade s



### D Fabri c r~ l Emeigenc

y Equip . [ J Non-Des t Tes t Q Specialize d Servk:e s (spec^ ;

14 . Lis t o f Maintenanc e Function s Contracte d t o Outsid e Agencies :

S . Applicant' s Certificatio n Nam e o f Owne r(Indud a mmefs ) o f indiwdua l owner , al l partners , w corporatio n nam e p/Wn g sfaf e an d dat e c f irxxtrporatian ) 

### DEA N R . CAMB E INTERTEC H OVERLOA D INC . CALIFORNI A 01/14/200 4 I hereby certif

y tha t I hav

e bee n authorize d b

y th e repai rstatio n identifie d i n Ite m 1 abovf e to mak e thi s applicatio n an d tha t statements an d attachment s heret o ar e tru e an d corve d t o th e best o f m y knowledge . Dat e 

### 11/27/200 7 Authorize d Signaturd L \^ . Printe d Nam e o f Authorize d Signe r 

### EANR . CAMB E "ntle 

### CE O Agenq ^ Display o f ^fimate d Burden : TTi e FA A estimates tha

t th e averag e burde n fo r(hi s repot t fbmf i i s 1 5 minutes pei^sponse . Yo u ma y submi t an y comment

s regardin g th e accurac

y o f thi s burde n estimat

e o ran y suggestion s forreducin g th e bunJe n to th e OfRc

e o f Managemen

t an d Budget Yo u ma y als o sen d comment

s to th e Federa l Aviatio n Administration , Aircraf t Maintenanc

e Division , AFS-300.80 0 Independenc e Avenue . SW , Washington , D C 20591 . Attention ; 0M B numbe r2120-0010 . 

# y

F A A For m 8310- 3 (8-95) supersede s Previou s Editio n NSN : 0052-00-686-100 2 

### \ 

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### Fo rFA A Us e Onl y Recor d o f Actio n Repai rStatio n Inspectio n Fo rFA A Us e Onl y 6 . Remark s (Identif y b y ite m number . Includ e deficiencie s found , rating s denied. )



# ICERTIFYTHATTHISIS A TRU E COPY : 

# O F TH E ORIGINA L FA A VN Y FSDO

7 . Finding s - Recommendation s 8 . Dat e o f Inspectio n I I A Statio n wa s foun d t o compl y wit h requirement s o f FA R 145 . I I B . Statio n wa s foun d t o compl y wit h requirement s o f FA R 14 5 excep t fo rdeficiencie s liste d I n Ite m 6 . \ I C . Recommen d certificat e wit h ratin g applie d fo ro n applicatio n b e issued . L i D - Recommen d Certificat e wit h ratin g applie d fo ro n applteatlo n (EXCEP T ttiose liste d i n ite m 6 ) b e Issued . 9 . Offic e

— SlgnaturB(s ) o f lnspector(s )

- —- Printe d Name(s ) o f lnspector(s ) 

# 1 

# 1 10 . Supervisin g o rAssigne d Inspecto r| 

### ACnO M TAKE N 

## iC H APPROVE D a s show n o n certilicat e issue d o n dat e show a |f~ ] DISAPPROVE D I CERTIFICAT E ISSUE D I Numbe r Inspector' s Signatur e

Dat e Inspector' s Printe d Nam e Trtl e F A A For m 8310- 3 (S-aS ) supersede s Previou s Editio n MSN : 0052-00-686-100 2 

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### 2150.3 A Appendi x 4

APPENDI X 4 ENPORCEWEN T SANCTIO

NGUIDANC E TABL E IbfTROPUCTION : Thi s ^^pendi x provide s guidanc e t o assur e greate r nationa l consistenc yi n enforcing th e Federa l Aviatio n Regulations . Sinc e th e Sanctio n Guidanc e Tabl e i s onl yintende d t o provid e genera l guidanc e fo r th e exercis e o f the agency' s prosecutoria l discretion , i t i s sufficientl ybroa d an d flexibl e t o permi t ful l consideratio n o f al l mitigating an d aggravating factors . EMPHASI S APPROAC H T O ENFORCEMENT ; A n increas e i n instance s o f nonconplianc e wit h a particula r regulation , a s wel l a s othe r circumstances , mayrequir e analysi s o f th e sufficiencj. ' o f sanction s previousl yinpose d fo r violation s o f tha t regulation . Fo r example , th e numbe r o f TC Aviolation s o r violation s involving flyin

g unde r th e influenc e o f alcoho l o r drug s ma yincrease , an d giv e ris e t o a concomitan t increas e i n th e numbe r o f accident s o r incidents . Analysi s o f sanction s an d othe r informatica i availabl e t o FA Aregardin

g suc h violation s ma yresul t i n a n agenc ydeterminatio n tha t th e curren t sanctio n polic yha s no t provide d a n effectiv e deterrent . Unde r thes e circumstances , safet yi n ai r commerc e an d ai r transportatio n an d th e publi c interes t ma y requir e a chang e i n sanctio n polic yan d a n increas e i n th e severit yo f sanctictt s in orde r t o pronot e vigilanc e an d dete r suc h violations . Notificatics i t o fiel d an d regiona l personne l o f enforcemen t activities/area s requiring a n emi^asi s approac h wil l b e accomplishe d throug h th e issuanc e o f (jompliance/Qiforcemen t Bulletins . (Orde r 2150.3A , paragraph ' 106) . GENERAL GUIDELINES ; Th e Sanctio n Guidanc e Tabl e i s intende d t o b e used onl y a s interna l guidanc e i n selecting an appropriat e sanction . It s purpos e i s t o assist , no t replace , the exercis e o f prosecutoria l judgment . Determination s a s t o whethe r certificat e actio n o r civi l penalt yactio n i s appropriat e shoul d b e mad e i n accordanc e wit h paragraph 20 6 o f th e Conqplianc e an d Enforcanen t Program , FA

AOrde r 2150.3A . Th e Tabl e represent s th e norma l rang e o f sanctio n fo r a singl e violatio n o f a particula r regulation . Allege d violation s wil l fal l withi n th e norma l rang e onl ywhe n th e violato r ha s n o prio r violation s an d th e actua l o r potentia l dange r involve d i s no t greate r tha n th e maximu m degre e o f dange r necessaril yinheren t i n an ysuc h violation . Sanction s abov e o r belo w th e norma l rang e ma yb e sough t base d o n othe r ccmsiderations , suc h a s factor s o f aggravatio n o r mitigatio n o r i f necessaryt o furthe r th e Administrator' s policy . P L 100-223 , effectiv e Decembe r 30 , 1987 , increase d tJi e maximu

mcivi l penalt y fo r violation s canmitte d b yai r carrier s fro

m$1,00 0 t o $10,00 0 pe r violaticxi . Th e increase d civi l penalt ymaximu mwil l serv e a s a n effectiv e deterren t an

d wil l decreas e th e likelihoo d tha t lo w number s o f violatiai s ma y b e acceptabl e t o a n qperato r a s a "cos t o f doin g business. " Experienc e ha s demonstrate d tha t multipl e violation s o f a singl e regulatio n ofte n resul t i n a sufficientl ydeterren t civi l penalty , eve n unde r th e $1,00 0 iriaximum . Althoug h th e ne w civi l penalt ymaximu mwil l ordinaril yresul t i n a large r civi l penalt y than wa s sough t unde r th e ol d maximum , th e computatio n o f penalt yfo r multipl e violation s shoul d no t b e don e simpl yb ymultiplyin g th e rang e of . sancticxi fo r a singl e violatio n o f a particula r regulatio n b yth e numbe r of

n flights . Rather , judgmen t shoul d b e exercise d in-determining th e seriouJhes s o f th e Pag e 1

### 2150.3 A

Appendi x 4 ~ " " violation s an

d applyin g a sanctio n tha t wil l serv e t o dete r futur e violaticxi s byth e violato r o r other s similarl ysituated ; i.e. , th e totalit yo f the circumstance s surroundin g th e cas e shoul d b e ccwisidered , includin g pas t violations . Wit h respec t t o certificat e actions , multipl e violation s (i.e. , multipl e violation s o f a singl e regulation , a singl e violatio n o f multipl e regulations , o r multipl e violation s o f multipl e regulations ) ma yresul t i n a sanctio n greate r than th e su mo f sanctio n range s fo r th e particula r violation s cited . Wher e a certificat e actio n fo r multipl e violation s doe s no t involve qualificaticMis , bu t rathe r i s solel ydisciplinaryo r punitive , a suspensio n fo r a fixed perio d o f day s shoul d b e irnpose d t o preven t o r dete r th e violato r and othe r person s similarl ysituate d fro mcanmittin g simila r violation s i n th e future . Wheneve r multipl e violation s demcHistrat e a lac k o f qualification s o r reaso n t o believ e tha t th e certificat e holde r ma ylac k qualifications , a remedia l sanctio n suc h a s revocatio n o r suspensio n pendin g demonstratica i o f qualification s i s appropriate . I n selectin g a n afpropriat e sanctio n outsid e th e norma l range , variou s aggravatin g an

d mitigatin g factor s an d circumstance s shoul d b e considered . Thes e includ e th e factor s liste d i n FA AOrde r 1000.9 D and FA AOrde r 2150.3 . Wit h respec t t o individuals , th e followin g shoul d als o b e considered . 1 . Significanc e i n degre e o f hazard t o th e safet yo f othe r aircraft , person s o r propert yi n th e aircraf t o r o n th e ground , create d b yth e allege d violation ; 2 . Natur e o f th e violatio n - inadverten t o r deliberate ; 3 . Pas t violatio n histor y(sinc e pas t complianc e shoul d b e th e norm , thi s facto r i s considere d onl yt o asses s th e nee d fo r a greate r tha n norma l sancticxi) ; 4 . Allege d violator' s leve l o f experience ; 5 . Attitud e o f allege d violator ; 6 . Natur e o f activit yinvolve d - private , publi c o r conmercial ; 7 . Abilit yo f allege d violato r t o absor b th e sanction ; an d 8 . Demonstrate d lac k o f qualificaticMis . 

## NOTE ; Wheneve

r apropose dsanctio n i s outsid e th e norma l rkng e o f penaltie s indicate di n thi s Table , i t shoul db e coordinate dwit h AGC-20 0 (Attn ; AQC-260 ) prio r t o th e issuanc e o f

t± e initia l enforcemen t actio n document . The EIRfil e shoul dccxitai n anotatio n o f th e basi s fo r

suc h departure .

V, .

### 2150.3 A Appendi x 4 Th e Sanctio n Guidance'^Tabl e describe s civi l penaltie s a s minimum , moderat e o r maximu mfo r a singl e violatio n o f a particula r regulation . Thes e term s ar e define d a s follows : (1 ) Violation s Canmitte d b yAi r Carrier s (CM

I o r afte r 12/31/87) . Ma x imu m$7,500-$10,00 0 Moderat e $4,000-$7,49 9 Minimu m$l,000-$3,99 9 (2 ) Violation s Committe d ByAirpor t Operators .

Ma x imu m$900-$l,00 0 Moderat e $750-$89 9 Minimu mi500-$74 9 (3 ) Violation s Ccxrenitte d ByAi r Carrie r Personnel . Maximu m$750-$l,00 0 Moderat e $550-$749 ' Minimu m$500-$54 9 (4 ) Violation s Committe d B yPar t 12 5 Operators .

Maximu m$750-$l,00 0 Moderat e $550-$74 9 Minimu m$400-$54 9 (5 ) Violation s Committe d ByPar t 12 5 Personnel .

Maximu m$750-$l,00 0 Moderat e $550-$74 9 Minimu m$500-$54 9 (6 ) Violation s Committe d B yGenera l Aviatio n Owners , Operators , Mechanics , Agencies , and Ncxi-Certificate d Persons . Maximu m$750-$l,00 0 Moderat e $550-$74 9 Minimu m$500-$54 9 (7 ) Violation s o f Sectio n 901(d ) o f th e FAAct , Conimitte d byPersca-i s Intending t o Boar d a Flight , Ar e Subjec t t o a Maximu mCivi l Penalt yo f $10,000 . (8 ) Violation s Committe d B yRepai r Station s an d Othe r Institutions .

Maximu m$750-$l,00 0 Moderat e $550-$74 9 Minimu m$400-$54 9 \ , Pag e 3

### 2150.3 A Appendi x 4

0 . Denia l o f Authorize d Ehtr yt o Fligh t Deck . P . Fligh t and Dut yTim e Limit:ations > Q . OperaticH i Withou t Require d Certificat e o r Rating . 1 . Medica l certificate . 2 . Lac k o f typ e rating . 3 . Misse d proficienc ycheck . 4 . Lac k o f curren t experience . 5 . Failur e t o hav e curren t certificat e i n possession . SANCTIO NPE R VIOLATION 3 0 t o 6 0 da ysus . 1 5 t o 9 0 da ysus .

1 5 t o 6 0 da ysus . 18 0 da ysus . t o rev . 3 0 t o 9 0 da ysus . 3 0 t o 9 0 da ysus . Mod . c.p . t o 1 da ysus .

R . Operatio n wit h Known Physica l Disability . III . Individual s an d Genera l Aviaticg i - (Xmers , Pilots ; Repai r Stations , Maintenanc e Personnel . A . Owner s an

d Operator s Othe r Tha n Require d Crewmembers . 1.Failur e t o compl ywit h airworthines s directives . 2 . Failur e t o performo r imprope r performanc e o f maintenance , including require d maintenance . 3 . Failur e t o mak e prope r entrie s i n aircraf t logs . 4 . Operaticx i o f aircraf t beyond annual , 100-hou r o r progressiv e inspection . Rev .

Mod . t o max . c.p . Mod . t o max . c.p .

Min . t o mod . c.p . Min . t o mod . c.p .

Pag e 1 1

### 2150.3 A

Appendi x 4

5 . Operatio n o f unairworth y aircraft . 6 . FalsificaticH i o f an yrecord . B . Repai r Stations . 1 , Failur e t o provid e adequatel y fo r prope r servicing , maintenanc e repairs , an

d inspection . 2 . Failur e t o provid e adequat e perscxine l wh o ca n perform , supervis e an

d inspec t work fo r whic h th e st:atic « i s rated . SANCTIC NPE R VIOLATIO N Mod , t o max . c.p . Rev . Mod . t o max . c.p .

Max . c.p . t o 7 day sus . an d thereafte r unti l adequat e personne l ar e provided . 3 . Failur e t o hav e enoug h qualifie d personne l t o kee p u p witJ i th e volum e o f work . 4 . Failur e t o maintai n record s o f supervisoryan

d inspectio n personnel . 5 . Failur e t o maintai n performanc e record s and reports . 6 . Failur e t o insur e correc t calibratio n o f eil l inspectio n an d tes t equlpnen t i s accon5>lishe

d a t prescribe d intervals . 7 . Failur e t o se t fort h adequat e descriptio n o f wor k performed . d.Failur e o f mechani c t o mak e lo g entries , record s o r reports . 9 . Failur e t o sig n o r ooinplet e maintenanc e release . 10 . Inspecticx i o f wor k performe d an d approva l fo r retur n t o servic e b yoUie r Uian a qualifie d Inspector . Max . c.p . t o 7 da ysus . an d thereafte r unti l certificat e holde r ha s enoug h qualifie d personnel . Mod . t o max . c.p . Mod . t o max . c.p . Min . t o max , c.p . Min , t o mod . c.p . Mod . t o max . c.p . Min . t o mod . c.p . Max . c.p . t o 3 0 da ysus .

Pag e 1 2 ,

### 2150.3 A Appendi x 4 SANCTIO NPE R VIOLATIO N 11 . Failur e t o hav e a n adequat e inspectio n syste mtha t produce s satisfactoryqualit ycontrol . 12 . Maintainin g o r altering a n articl e fo r whic h i t i s rated , withou t using require d technica l data , equijwen t o r facilities . 13 . Failur e t o perfor mo r properl y perfor mmaintenance , repairs , alterations , an d require d inspections . 14 . Maintainin g o r altering a n airframe , powerplant , propeller , instrument , radi o o r accessoryfo r whic h i t i s no t rated . 15 . Failur e t o repor t defect s o r unairworth

yccMiditions t o FA

Ai n a timel ymanner . 16 . Failur e t o satisf yhousin g an d facilit yrequirements . 17 . Chang e o f locatic»i , housin g o r facilitie s withou t advanc e writte n approval . 18 . Gyratin g a s a certificate d repai r statica l withou t a repai r statio n certificate . 19 . Failur e t o permi t FA At o inspect . C . Genera l Aviatio n Maintenanc e Personnel . 1 . Failur e t o revis e aircraf t dat a afte r majo r repair s o r alterations . Mod . c.p . t o 3 0 da ysus . an d thereafte r unit l a n adequat e inspectio n syste mi s attained . Max . c.p . t o 3 0 da ysus .

Mod . c.p . t o 3 0 da ysus .

Max . c.p . t o rev . Mod . t o max . c.p . Mod . C.p . t o sus . unti l housin g an d facilit y requireraent: s ar e satisfied . Mod . c.p . t o sus . unti l approva l i s given . Max . c.p .

Max . c.p . t o sus . unti l FA Ai s permitte d tx

> inspect . 3 0 t o 6 0 da ysus .

Pag e 1 3

### < 

## U.S . DEPARTIVIEN T O F TRANSPORTATIO N FEDERA L AVIATIO N ADMINISTRATIO N

Nationa l Polic

y SUBJ : FAA Complianc e an d Enforcemen t Progra m 

# ORDE R 2150.3 B Effective Date : 10/01/0 7 Thi s orde r

contain s policies , procedures , an d guideline s fo r th e Federa

l Aviatio n Administration' s complianc e an d enforcement program . The orde r

als o articulate s th e FAA' s philosoph y for usin g variou s remedies , includin g education , correctiv e action , informa l action , remedia l training , administrativ e action , an d legal enforcement action , t o addres s noncomplianc e wit h statutor y an d regulatory requirement s enforce dby th e FAA . I t provide s fo

r th e publi c awritte n statemen t o f th e Administrator' s polic y guidanc e for imposin g sanction s for

violation s o f

suc h requirements . Th e orde r i s use dat

al l level s b y agenc y persorme l wh o are engage di n th e investigation , reporting , an dprocessin g o f

enforcemen t

actions . I t

applie s t o al l office s wit

h regulator

y responsibilities . Thi s revisio n ofth e orde r

comprehensivel y update s policies , procedures , guidance , an d assignment s o f responsibility . I t

reorganize s th e order

i n amanne r

mor e usefiil fo r

agenc y personne l an d i s availabl e electronicall y t o agenc y personne l an d th e public . Th e revisio n amend s agenc y sanctio n guidanc e t o confon n t o statutory change s resultin g fi-omVisio n lOOCentur y o f Aviatio n Reauthorizatio n Ac t an d incorporate s guidanc e int o th e agency' s complianc e an d enforcement programorde r

o n policie s and , v

. program s tha t

hav e develope dsinc e th e las t comprehensiv e orde r

revisio n i n 1988;-Thos e fiiclude * policie s relatin g t o th e FAA' s exercis e o f it s authorit y t o administrativel y asses s civi l penaltie s an d guidanc e o n th e agency' s voluntary safet y programs . A workgrou p o f

agenc y personne l fromth e fieldan d headquarter s wit h extensiv e experienc e i n statutor y an d regulatory enforcement reviewe dth e agency' s policie s an d program s i n thi s are at o produc e thi s comprehensiv e revisio n ofth e agenc y orde r o n it s complianc e an denforcemen t program . 

# / £ Robert A , Sturg i Actin g Adm i

Distribution : A-W-1;A- W (AT/PS/SM)-2;A- W (PP/AM/SF/ GCIFS/rAA'S)-3;A-XY

Z ( A T/AF/CS>2;Z- X (AS/AM/GC/FS)-3 ; A- Y (AM/ARlGC)-3,-A- Z (AM/AN/GC)-3;A-FAC/FACIFCS-0 ; A- F AF/F A T/FIA-OC

L TD);2FS-32 5 ;Initiate dBy : AGC-30 0

> 

# V 

# 6 - ^

## 10/01/0 7 2150.3 B Chapte r7 . Sanctio n Guidanc e Policie s 

## 1 . Purpose . Thi s chapte r provide s th e FAA' s policie s fo r determining a

n appropriat

e sanctio n onc e FA A enfoicemen

t personne l decid

e tha t lega l enforcemen

t actio n i s appropriate . Thi s chapter contain s the genera

l polic y th e FA

A intend s t

o appl y i n selecting th e type s o f

sanctions , range s o f sanction s within thos e types , andspecifi c sanction amount s t o impos e i n lega l enforcemen

t action s fo r typica l violation s ofth e FAA' s statut e an dregulations . Thi s guidanc e cover s th e parameter s bot h fo r selecting sanction s andfo

r modiiyin g sanction s during th e informa l procedures . Th

e guidanc e i n thi s chapte

r i s applie di n adjudication s unde r 4 9 U.S.C . § § 44106,44709,44710 , 44726,44924,46111,46301 , an d70115 . Hazardou s material s sanctio n guidanc e an dpolicie s are addressedi

n Appendix C . 2 . Genera l Guidelines . a . CertiJGcat

e Suspensio n Actio n an dCivi l Penalty Action : Sanction s fo r Punitiv e an d Deterren t Purposes . (1 ) General . I f

acertificat

e holde r improperl y exercise s th e privilege s of acertificate , a natura l consequenc e o f

tha t ac t i s t o los e the privilege s fo

r aperio do f

time commensurat

e wit h th e -violation . Balance dagains t thi s principle , however , th e FA A consider s th e advers e impac t tha t acertificat

e suspensio n coul dhav e o

n th e public . Thus , th e agenc y generally suspend s th e certificate s o f

individua l certificat e holder s fo

r violations . However , th e FA A usually take s civi l penalt y action agains t

air carrier s andairport s becaus e such action s do no t disrupt service , whic h ma y adversel y affec t th e public . Nevertheless , whe n th e FA A determine s tha

t safet y consideration s warran

t it , th e agenc y will suspendth e certificat e o f an y typ e o f certificat e holder . In n o cas e will th e FA

A tak e civi l penalt

y actio n alone when remedia l lega l actio n i s necessar

y or appropriate . (2 ) Us e o f bot h ptmitiv e certificat

e actio n an

dci^vi l penalt y actio n fo r th e sam e violations . Th

e FA A generall y doe s no t

tak e civil penalt

y actio n an dpunitiv e certificat e actio n (tha t is , certificat

e suspensio n fo

r afixed perio do f

time ) agains t

acertificat

e holde r fo r th e sam e conduct . I f

imusua l circumstance s warran

t deviatio n firomthi s practice , lega l counsel consul

t wit h th e Assistan

t Chie f Counsel fo

r Enforcemen

t (AGC-300 ) befor

e initiatin g th e actions . (3 ) Chang e in typ e o f

propose dsanction . Th

e initia l enforcemen

t actio n reflects th e agency' s bes t

assessmen

t ofth e appropriat

e sanctio n fo

r th e violation s alleged . Afte r initiatin g th e action , lega

l counsel ordinaril y doe s no t chang e th e typ e o f

sanctio n unles s additiona

l fact s o r circumstance s are presente dt o th e FAA tha t warran t achange . I f

th e actio n wa s coordinated imde r chapte r 6 , paragraph 3 , wit

h AGC-30 0 befor

e initiation , then lega

l counsel coordinate s an

y chang e i n th e typ e o f

sanctio n wit

h AGC-30 0 befor

e making th e change . b . Lega l Sanction s fo r

Remedia l Purposes . (1 ) Indefinit

e certificat e suspensio n pending complianc e o r demonstratio n o f qualification . Suspension actio n i s appropriat e wher e ther e i s aneedtemporarily t

o 7- 1

## 10/01/0 7 2150.3 B

suspen dth e privilege s ofth e certificat e o r ratin g pendin g demonstratio n o f qualificatio n o r complianc e with statutor

y oTregulator y requirements . FAA generall y use s remedia l suspensio n whe n an individua l doe s no t voluntaril y surrende r

hi s o r he r certificat e pendin g reexamination . Se e chapte r

5 . (2 ) Certificate revocatio n - general . Th e FAA revoke s acertificat e whe n acertificat e holde r lack s th e qualification s t o hol dth e certificate . Th e certificat e holder' s continue dexercis e ofth e privilege s ofth e certificat e i n suc h circumstance s woul db e contrar y t o safety i n ai r commerc e or

ai r transportatio n an dth e publi c interest . Revocatio n i s appropriat e wheneve r a certificat e holder' s conduc t demonstrate s alac k

ofth e technica l proficiency o r alac k ofth e degre e o f care , judgment , o r

responsibility , require dofth e holde r o f suc h acertificate . Order s o f revocatio n ar

e issue do n an emergenc y basi s whe n th e certificat e holde r lack s qualificatio n an di s reasonabl y abl e a s apractica l matte r t o exercis e th e privilege s ofth e certificate . Lega l counse l doe s no t alleg e alac k

o f qualification s t o avoi ddismissa l o f charge s imde r

4 9 C.F.R . § 821.33 , th e NTSB' s stal e complain t rule . (3 ) Certificate revocatio n - individuals . Th e FA A generall y revoke s an individual' s certificat e o r

ratin g wheneve r

h e o r sh e demonstrate s alac k

o f willingnes s o r

abilit y t o compl y consistentl y with statutor

y o r regulator y requirements . A lac k o f willingnes s o r

abilit y t o compl y ma y b e demonstrate db y suc h thing s a s repeate do r deliberat e violation s o r

b y violation s tha t involv e grossl y careles s o r reckles s conduct . Eve n asingl e violatio n ma y b e sufficien t t o warran t aconclusio n an individua l lacks qualifications . Th e FA A ordinaril y revoke s al l certificate s o f a perso n wh o commit s aviolatio n involvin g intentiona l falsification . (4 ) Certificate revocatio n - entities . Revocatio n i s normall y appropriat e whe n a certificate-holdin g entity deliberatel y o r flagrantly violate s th e statut e o r regulation s o r

falsifie s records . Revocatio n als o i s generall y appropriat e whe n th e certificat e holde r ha s committe dth e sam e o r similar violation s i n th e recen t

pas t demonstratin g alac k

o f qualification , o r

whe n th e certificat e holde r

n o longe r has , an ddoe s no t

obtai n i n areasonabl e time , th e persoime l o r equipmen t

t o conduc t

it s operatio n i n ful l complianc e with statutory an dregulator y requirements . (5 ) Mandatory certificat e revocation . Unde r 4 9 U.S.C . § 44710 , th e FA A i s require dt o revok e th e certificate s o f

an y airma n wh o ha s bee n con-^^cte do f violatin g certai n federa l o r stat e statute s relatin g t o acontrolle dsubstanc e whe n a n airplan e wa s use di n th e commissio n ofth e offens e an dth e airman serve da s a n airman , o r was aboardth e aircraft , i n connectio n wit h commissio n ofth e offens e o r th e facilitatio n ofth e commissio n ofth e offense . Eve n whe n ther e ha s bee n n o conviction , revocatio n i s require dwhe n an airma n ha s knowingl y carrie dout a n activit y pimishabl e unde r thes e crimina l statutes . Th e Administrato r ma y waiv e th e revocatio n i f ala w enforcemen t

office r request s th e waive r

an dth e Administrato r

decide s th e waive r

vn W facilitat e la w enforcemen t purposes . Se e 4 9 U.S.C . § 44710(f) . Unde r 4 9 U.S.C . § 44106 , th e FA A als o mus t

revok e th e registratio n certificat e o f an y airplan e use di n th e commissio n o f suc h a n offens e whe n th e us e wa s permitte db y th e owne r ofth e aircraf

t with knowledg e tha t

i t woul d b e use dfo r

suc h purpose . Unde r

4 9 U.S.C . § 44726 , th e FA A mus t revok e th e certificate s o f an y certificat e holde r

o r a n individua l wh o ha s acontrollin g o r ownershi p interes t

i n th e holde r

wh o was convicte do f

aviolatio n o f

federa l la w relatin g t o th e installation , production , repair , o r sal e o f acounterfei t

or fraudulently-represente daviatio n part o r materia l o r

knoviing|y , an dwit h th e v.. 7- 2

## 10/01/0 7 2150.3 B

inten t t o defraud , carrie dout

o r facilitateda

n activit y punishabl e unde

r suc h alaw . Th e Administrato

r ma y waiv e tha

t sanctio n t o facilitat e la w enforcemen

t purpose s or

amend , rather tha n revoke , acertificat

e unde r certain circumstances . See 4 9 U.S.C . § § 44726(f ) an d(g) . (6 } Mandator

y certificat e action fo r securit y concerns . Unde

r 4 9 U.S.C . § 46111 , th e Administrator

i s require dt o issu e a

n orde r amending , modifying , suspending , o r revokin g any FAA-issuedcertificat

e i f th e Administrator

i s notifie dby th e Unde

r Secretar y o f Borde r an d Transportatio n Securit

y (BTS ) ofth e Departmen

t o f Homelan dSecurit

y (DHS ) tha

t th e certificat e holde r poses , or i s suspecte do

f posing , aris k

o f air pirac y o r terroris mo

r athrea t t o airlin e o r passenge r safety . Unde

r 4 9 U.S.C . § 44924 , th e Administrator i s required , a t

th e reques t ofth e Unde

r Secretar y o f BTS , t o suspen do r revok e foreign repai

r station certificate s i n connectio n wit

h securit y audits . 3 . Applicabilit

y an dExclusions . The sanctio n guidanc e tabl e (table ) i

n Appendix B provide s type s o f sanction s an dgenera

l range s o f sanctio n amoimts fo

r violation s of

4 9 U.S.C . subtitl e VI I and1 4 C.F.R . part s 1-19

9 an d4 9 U.S.C . subtitle IX , chapter 70 1 and1 4 C.F.R . chapte

r III . Onc e th e agency ha s determine dtha t lega l enforcemen

t actio n i s warrante dfo

r aviolation , FAA enforcemen

t personne l us e th e tabl e an

dparagrap h 4 o f thi s chapter , a s wel

l a s an y other sanctio n guidanc e i n thi s order , t o determin e aproposedsanction . Th e matter s describe di n chapte r 7 , subparagraph s 3a.-d , are som e type s o f agenc y actio n tha

t fal l outsid e th e scop e o f paragraph 3 an

dthe table . a . Decision s t o Tak e Administrativ e Actio n (Warnin g Notice s o r Letter s o f Correction) . A

n administrativ e actio n doe s no t constitut e either aforma l adjudication ofth e inciden t o r afinding of'violation . Fo

r tha t reason , FA

A investigativ e persorme

l d o no t propos e a sanctio n using th e table . b . Th e FAA' s Exercis e o

f Prosecutoria l Discretion . Th e decisio n whethe r t o prosecute a particula r cas e i s base do n arevie w ofth e evidence andrelevant polic y an dlitigatio n considerations . The agenc y exercise s broa ddiscretio n in bot

h th e initia

l decision t o brin g alega

l enforcemen

t action , an di n an

y later determination t o compromis e o r setti e acas e base do n variou s considerations . Th e FAA' s discretio n in thes e area s i s absolut e an dpresumedt o b e immune fidmreview . Heckle r v. Cheney , 47 0 U.S . 821 , 83 1 (1985) . c . Hazardou s Material s Violations . Action s involvin g violation s ofth e federa l ha2ardou s material s transportatio n law , 4 9 U.S.C . chapte r 51 , or th e Department

o f Transportation' s Ha2ardou s Material s Regulations , 4 9 C.F.R . part s 10 6 throug h 185 . Enforcemen t sanctio n guidanc e fo

r thes e violation s i s foun

din Appendi

x C . d . Violation s b y Member s ofth e U.S . Arme dForces . Th e FA A i s requiredt o forwar

d report s of thes e violation s to th e Secretar y ofth e departmen

t concerne dunde

r 4 9 U.S.C . § 4610 1 (b) , wheneve

r th e violator

i s acting i n th e performanc e o f

officia l duties . Th

e FAA , however , take s remedia

l actio n i n additio n to referrin

g arepor t whe n th e violator , whethe

r or no t

V,. 

## 7- 3

## 10/01/0 7 2150.3 B

actin g i n th e performanc e o f official militar y duties , hold s a n FA A certificate , an dth e violator' s qualification s ar e a

t issue . Th e FA A ma y tak e punitiv e actio n agains t

amembe r

ofth e U.S . Arme dForce s fo

r aviolatio n conimitte dwhe n th e membe r i s no t performin g officia

l duties . 4 . Mitigatin g o r

Aggravatin g Factor s an dElements . Th e factor s i n chapte r 7 , subparagraph s 4.a . throug h m . hav e bee n develope dove r year s o f polic y makin g an dcas e adjudication . The y hav e prove n useful an dappropriat e fo r determinin g th e seriousnes s o f aviolatio n an dfor selectin g an appropriat e sanction . Element s fo r evaluatin g an dweighin g eac h facto r ar e als o described . Thes e factor s andelement s provid e aframewor k for determinin g sanction s fo r violation s specificall y liste di n th e tabl e a s wel l a s thos e no t specificall y listed . Al l th e factor s an delements , however , ma y not appl y t o eac h violation . Onl y thos e factor s an delement s tha t ar e relevan t

t o aviolatio n are considere di n determinin g asanctio n fo r th e violation . Thi s lis t

o f factor s an delement s i s no t intende dt o b e exhaustive ; othe r factor s ma

y b e relevan t

a s well . a . Natur e ofth e Violation . Thre e element s defin e th e natur e o f aviolation : first, whethe r th e violatio n was operationa l o r non-operational ; second , whethe r th e violatio n involve dcareles s o r reckles s conduct ; an dthird , whethe r th e violatio n involve dan y specia l aggravatin g o r mitigatin g factors . (1 ) Individuals . When an individua l wh o hold s acertificat e improperl y exercise s th e privilege s o f

tha t certificate , th e natura l consequenc e o f tha t ac t shoul db e los s o f

privilege s fo r

a perio do f tim e commensurat e with th e violation . Th e FAA , therefore , primaril y use s certificat e action s t o enforc e operationa l regulation s agains t individual s wh o hol dcertificates . Th e potentia l advers e impac t

tha t certificat e actio n ma

y hav e o n a n individual' s livelihoo ddoe s no t alte r thi s principle . Non-operationa l violation s may warran t adifferen t

typ e o f sanction . (2 ) Entities . Th e FAA ordinaril y take s civi l penalty actio n agains t acertificate-holdin g entit y (fo r example , a n ai r

carrier ) whe n i t

determine s ther e woul db e asubstantia l advers e impac t o n th e publi c interes t

fi:omdisrupte dservic e b y tha t certificat e holde r

an dth e impac t

i s not outweighe db y safety considerations . Eve n whe n asubstantia l advers e impac t woul doccur , whe n ther e i s anee dt o preven t continuin g violation s or

othe r egregiou s conduc t

b y an y certificat e holder , whe n an y certificat e holde r lack s qualification , o r

ther e i s areasonabl e basi s t o questio n th e qualification s o f an y certificat e holder , tiie FA A takes remedia l action , for example , revocatio n o r

indefinit e suspension , a s necessary . (3 ) Careles s o r

reckles s conduct . Violation s that involv e careles s o r

reckles s conduc t

i n violatio n o f

1 4 C.F.R . § 91.1 3 may warran t mor e sever e sanctions . Carelessnes s connotes conduc t tha t fall s belo w th e standar do f car e o r prudenc e expecte do f

areasonabl e person , o r holde r ofth e relevan t

certificate , actin g tmde r

th e sam e o r

simila r circumstances . Recklessnes s connote s conduc t

tha t demonstrate s agross , o r

eve n callou s o r

flagrant, disregar dfo r

safety . Aircraf t operation s tha t

d o no t othenvis e resul t

i n aviolatio n o f

aspecifi c regulatio n shoul db e evaluate di n ligh t

o f thes e standard s t o determin e whethe r the y constitut e careles s o r reckles s operation s i n violatio n o f 1 4 C.F.R . §91.13 . Whe n aperso n operate s a n aircraf t i n violatio n o f

a specifi c regulatio n othe r

tha n 1 4 C.F.R . §91.13 , however , tha t violatio n constitute s acareles s o r reckles s operatio n i n an do f itsel f I n thes e cases , th e misconduc t ma y als o resul t

i n aviolatio n o f 1 4 C.F.R . § 91.1 3 i f

i t actuall y o r

potentiall y endanger s th e live s o r propert y qfo'thers . 7- 4

## 10/01/0 7 2150.3 8

Whe n calculatin g th e amoun t o f sanctio n base do n thi s factor , adistinctio n generall y i s draw n betwee n instance s where-1 4 C.F.R . § 91.1 3 i s a n independen t

violatio n an dthos e wher e i t i s residua l to anothe r

violation . Whe n a1 4 C.F.R . § 91.1 3 violatio n i s residua l only , ahighe r sanctio n generall y i s no t

warrante dunles s th e conduc t i s als o reckless . b . Whethe r

th e Violatio n was Inadverten t an dNo t Deliberate . I f

aviolatio n i s deliberat e o r

no t inadvertent , asanctio n at th e uppe r

en dofth e rang e o r

exceedin g th e rang e fo r tha t typ e o f violatio n generall y i s appropriate . A deliberat e violatio n generall y warrant s a sanctio n that

i s mor e sever e tha n on e tha t i s jus t no t inadvertent . (1 ) No t deliberate . Thi s elemen t mean s alac k

ofth e degre e o f

deliberatio n foun din intentiona l misconduct . Deliberat e o r intentiona l misconduc t

i s a n aggravatin g circiunstanc e an d include s deliberat e conduc t that lead s t o aviolatio n a s wel l a s circumstance s indicatin g inten t t o commi t aviolation . (2 ) Inadvertence . A n ac t i s inadverten t

whe n i t i s th e resul t

o f bot h inattentio n an dlac k o f purposefu l choice . Fo r

example , a n inadverten t

ac t occur s whe n apilo t

flies a t a n incorrec t altitud e becaus e h e o r

sh e misrea dth e aircraft' s instruments ; however , i t i s no t a n inadverten t

ac t whe n apilo t

flie s a t a n incorrec t

altitud e a s aresul t

o f choosin g no t

t o consul t

th e aircraft' s instrument s o r

choosin g no t

t o us e othe r

availabl e mean s t o verif

y altitude . Th e tes t

t o b e applie d i s whethe r

th e conduct , no t

th e factual o r

lega l consequences , i s inadverten t an dunintended . Ferguso n v . Nationa l Transportatio n Safety Board . 67 8 F.2 d821 , 828-82 9 (9ti i Or . 1982) . c . Certificat e Holder' s Leve l o f Experience . (1 ) Leve l o f

experienc e refer s primaril y t o th e typ e o f certificat e an drating s hel d(fo r example , student , private , commercial, airlin e transpor t pilot , o r certifie dflight

instructor) , an d th e numbe r

o f hour s flown, b y th e certificat e holder . Certificat e holder s wit h greate r level s o f experienc e ma y b e hel dt o ahighe r standard . Thus , fo r

example , commercia l pilot s ma y b e hel d t o ahighe r

standar dtha n privat e pilot s an dairlin e tiansport pilot s ma y b e hel dt o a n eve n highe r standar dtha n commercia l pilots . (2 ) I n determinin g an appropriat e sanction , th e FA A may conside r th e exten t

t o whic h th e certificat e holder' s actio n deviate dfi-omth e degre e o f car e an ddiligenc e normall y expecte d o f aperso n -wit

h th e certificat e holder' s leve l o f experience . A significan t de-viatio n fi-omth e degre e o f car e an ddiligenc e expecte dofth e holde r o f tha t certificat e ma y warran t

amor e aggravate dsanction . d . Attitud e o f

th e Violator . (1 ) A goo dcomplianc e attitud e i s th e nor man ddoe s no t warran t areductio n i n sanction . A prio r violatio n histor y ma y sugges t tha t aperso n ha s apoo r

complianc e disposition , whic h i s an aggravatin g factor . Furthermore , aperso n wh o commit s a n ac t o r omissio n contrar y t o statutor y o r

regulator y requirement s afte r receivin g notic e throug h aprio r administrativ e actio n o r coimselin g tha t

suc h conduc t

i s i n violatio n o f

thos e requirement s migh t wel l b e regarde da s havin g apoo r

complianc e disposition . I n evaluatin g complianc e disposition,^th e FA A doe s no t V , . 

## 7- 5

## 10/01/0 7 2150.3 8

vie w a n allege dviolato r

a s havin g apoo r

attitud e becaus e th e allege dviolato r fail s t o respon dto alette r o f investigation , cheese s t

o b e represente db y counsel , o r contest s th e violation . (2 ) I n assessin g th e attitud e o f a n allege dviolator , th e FAA ma y conside r th e declaratio n o f a n emergenc y t o ai r

traffi c control . Whe n an emergenc y i s genuin e an dnot ofth e person' s ow n making , th e emergenc y i s exculpator y unde r 1 4 C.F.R . § 91.3(b) . However , thi s situatio n i s distinc t fiomth e situatio n where adeclaratio n o f emergenc y i s no t

exculpatory bu t

i s afacto r

tha t migh t b e appropriat e t o conside r i n determinin g sanction . I n emergenc y situations , th e FA A view s declarin g an emergenc y t o ai r traffi c contro l a s asig n o f goo djudgmen t

an daconstructiv e attitude . Whe n a n emergenc y i s o f aperson' s ow n making , that person' s declaratio n o f

an emergenc y ma y b e considere dmitigatin g i n determirun g th e sanctio n t o b e impose dfo r an y violation s committed , i n muc h th e same wa y i t i s considere dmitigatin g i f aperso n voluntaril y report s aviolation . e . Degre e o f

Hazard . (1 ) Th e degre e o f

hazar dmay b e increase da s aresul t ofth e interpla y ofth e operationa l environmen t

(fo r example , weathe r

conditions , congeste dvs . sparsel y populate dareas ) an dth e natur e o f th e threa t t o safety (t o th e lif

e o r propert y o f

another , includin g thos e in th e aircraf t beiri g operated , t o othe r

aircraft , o r

t o persons o r

propert y o n th e surface ) tha t th e misconduc t presents . TTi

e safet y threa t i s base do n th e reasonabl y foreseeabl e consequence s ofth e misconduct . Fo r

example , operatin g 50 0 fee t belo w th e minimu maltitud e pose s agreate r hazar d tha n operatin g 10 0 fee t

below . Similarly , i f

a n aircraf t operato r fail s t o compl y -wit

h an airworthines s directiv e b y operatin g 1 0 hour s pas t arequire dinspection , th e degre e o f hazar di s probabl y no t

a s grea t a s whe n th e aircraf

t i s operate d10 0 hour s beyon dth e required . An di t i s no t mitigatin g whe n aviolatio n doe s not resul t i n actua l harm ; tha

t i s simpl y fortuitous . (2 ) Th e sanctio n range s reflec t th e degre e o f

dange r normall y inheren t

i n a n averag e violatio n o f

aregulation , withou t

aggravatin g circumstances . A s discusse di n chapte r 7 , subparagrap h 5.b. , a n increas e i n th e degre e o f hazar dma y formth e basi s for exceedin g th e sanctio n ranges . Fo r

example , th e rang e fo

r a n unauthorize dlo w flight doe s no t assum e extrem e departure s fi-omrequire daltitudes , fo r example , flying an airplan e ove r acrowde dassembl y o f person s a t

5 0 fee t f . Actio n Take n b y Employe r o r Othe r Authority . Thi s facto r

ordinaril y involve s th e followin g elements : whethe r th e allege dviolator' s employe r ha s take n disciplinar y actio n an d whethe r crimina l prosecutio n i s involved . (1 ) Employmen t

discipline . Where th e violatio n woul dnormall y cal l for acertai n typ e o f enforcemen t

action , th e FAA take s tha t actio n regardles s o f

an y actio n take n b y th e violator' s employer . Generally , th e FA A doe s no t credi t a n employer' s disciplinary actio n towar daperio d o f suspensio n th e FA A impose s agains t th e violator' s certificat e becaus e o f the . differen t purpose s o f

government-ordered , a s contiaste dwit h employer-ordered , actions ! (2 ) Crimina l prosecution. Whe n arisin g ou t ofth e sam e conduct , local , state , o r federal prosecutio n doe s not

preclud e th e FA A fro mtakin g appropriat e remedial enforcemen t action ; no r 7- 6

## 10/01/0 7 2150.3 8

doe s i t preclud e th e FA A fro mtakin g appropriat e punitiv e enforcemen t action . Fo r

case s wher e federal , state , o r

local authoritie s prosecut e criminally , th e FA A generall y doe s tak e remedial enforcemen t

actio n i f that i s warrante ddespit e th e crimina l prosecution . However , th e FAA doe s no t generall y tak e punitiv e legal enforcemen t actio n for

th e sam e conduct , unles s it believe s th e crimina l sanction s are no t sufficien t t o provid e a

n adequat e deterren t

fo r futur e violation s b y th e violato r an dother s similarl y situated , o r whe n th e FA A want s t o establis h aviolatio n history record . I f

th e FA A decide s t o procee dwit h apunitiv e civi l enforcemen t actio n i n additio n t o th e crimina l prosecution , i t

generall y consider s th e crimina l penalties incurre di n thos e proceeding s i n determinin g th e appropriat e amoun t o f sanctio n t o b e sough t

i n th e FAA' s punitiv e enforcemen t

action . g . Us e o f

aCertificate . Thi s facto r relate s t o th e natur e o r

kin do f activity o r

operatio n involve da t

th e tim e th e violatio n wa s committed. Whethe r th e certificat e holde r

wa s engage di n student , private , commercial , o r airlin e activity bear s o n th e severit y ofth e sanction . Ai r carrier s ar e hel dt o th e highes t

standar do f

care . Likewise , persoime l engage di n ai r transportatio n ar e hel dt o th e highes t

safet y standard . h . Violatio n History . (1 ) A violation-fi-e e histor y i s th e expecte dnorm , no t th e exceptio n and , therefore , i s no t amitigatin g factor . Sanctio n range s i n th e tabl e generall y represen t th e norma l rang e o f

sanctio n fo r asingle , first-time, inadverten t violation . Give n th e expecte dnorm , aprio r violatio n recor d ca n b e evidenc e o f

apoo r complianc e dispositio n o r o f apatter n o f

disregar dfor

th e FAA' s regulations , whic h ar e aggravatin g factors . A s aresult , aviolatio n histor y ca n justif y imposin g a sanctio n at

th e highe r

en dofth e norma l rang e o r asanctio n beyon dth e norma l range . I t migh t als o justif y revocatio n rathe r

tha n suspensio n i f

th e patter n o f

violatio n reflect s alac k

o f qualification . I n addition , a-violatio n histor y migh t justif y acertificat e suspensio n i f previousl y issue dcivi l penaltie s hav e not produce dth e desire ddeterren t effect . I n decidin g whethe r a violatio n histor y justifie s aggravatin g th e sanctio n o r changin g th e usua l typ e o f sanction , th e FA A consider s th e lengt

h o f time tha t ha s elapse dbetwee n violations , whethe r th e violation s involve dth e sam e o r

simila r regulations , an dwhethe r th e violation s ar e factuall y similar . (2 ) Th e followin g action s constitut e violatio n histor y whe n the y involv e regulatory violation s an dbecom e final: order s o f amendment , modification , suspension , o r revocatio n o f

an FA A certificate ; order s assessin g aci-vi l penalty ; finding s o f

violatio n containe di n aconsen t order , orde r

o f complianc e o r

denial ; an dfinding s o f

violatio n mad e b y afedera l court . In addition , apart y may agre e a s par t o f asettlemen t

tha t th e FA A ma y conside r

allege dviolation s a s findings of-vaolatio n fo r futur e sanctio n determinations . i . Decisiona l Law . Decision s ofth e FA A decisioimiake r represen t

th e FA A Admiiustrator' s positio n o n issue s arisin g i n civi l penalty assessmen t actions , includin g issue s regardin g sanctions . Th e polic y i n thi s orde r als o represent s th e Administrator' s positio n o n sanction s i n lega l enforcemen t actions . T o th e exten t

that thi s documen t

conflict s wit

h FAA decisioimiake r

decision s publishe dbefor e thi s document' s issuance , th e sanctio n guidanc e polic y i n thi s orde r

supersede s thos e decisions . However , FAA decisiormiake r decision s publishe dafte r V . 

## 7- 7

## 10/01/0 7 2150.3 8

th e issuanc e o f

thi s document

that conflic t with th e polic y i

n thi s orde r

supersed e thi s document an dar e controlling . * — j . Abilit y t o Absor b Sanction . Sanction s shoul db e deterrent . Whil e punitiv e sanction s shoul dno t

b e undul y harsh , the y shoul db e substantia l enoug h t o preven t violator s fromprofitin g fromthei r

violations , tha t

is , th e sanctio n shoul db e hig h enoug h t o remov e an y profi t incentiv e for violations . Penaltie s shoul dneve r b e permitte dt o b e acos t o f doin g business . Ai r

carriers , i n particular , ar e require db y la w t o have'th e financia l wherewitha l t o operat e accordin g t o establishe dsafety standards . Whil e th e FA A doe s no t allo w financial circumstance s t o excus e an y violation , i t

doe s consider

acarrier' s siz e an dfinancial strengt h i n choosin g th e appropriat e sanctio n amount . Th e differenc e i n th e penaltie s fixedi n th e la w for larg e an dsmal l busines s concern s recognize s thi s fact . A civi l penalt y tha t ma y b e amer e cos t

o f doin g busines s t o a majo r ai r carrie r migh t compe l asmal l ai r

carrie r t o g o ou t o f business . Therefore , th e FAA use s ai r carrie r siz e a s on e mean s o f

ensurin g arelativel y equivalen t deterren t effec t o n eac h ai r carrie r tha t violate s th e sam e FA A regulation . Th e resultin g classificatio n o f ai r carrier s b y siz e an drange s o f

ci'vi l penaltie s are se t

fort h i n par t on e ofth e table . Fo r

al l entitie s an dindividuals , th e FA A consider s ability t o pa y acivi l penalt y an dth e effec t acivi l penalt y wil l hav e o n a person' s abilit y t o continu e i n busines s t o th e exten t i t know s suc h infonnation . k . Consistenc y o f

Sanction . On e ofth e agency' s goal s i s t o achiev e relativ e consistenc y i n imposin g simila r

sanction s for

similar violations . Th e FA A pursue s thi s objectiv e t o assur e fairnes s an ds o th e sanction' s impac t ha s an equivalen t

degre e o f deterren t o r disciplinary valu e t o other s similarl y situated . Thi s goa l ma y no t alway s b e achieved , however , becaus e ofth e inherenti y subjectiv e natur e ofth e exercis e o f judgmen t i n settin g sanctions . 1 . Whethe r

th e Violatio n wa s Reporte dVoluntarily . (1 ) Th e FA A ha s program s tha t allo w person s t o report

voluntaril y apparen t

violation s an dreceiv e lesse r

enforcemen t

actio n pro-vide dcertai n criteri aar e met . Thes e program s includ e th e aviatio n safety reportin g program , th e voluntar y disclosur e reportin g program , an dth e aviatio n safet y actio n program . Beside s thes e programs , th e FAA ma y gran t specia l enforcemen t consideratio n unde r

certai n circumstance s t o aperso n who , inciden t t o hi s o r he r repor t o f another' s violations , voltmtaril y disclose s hi s o r he r ow n participatio n i n th e sam e o r relate d violations . Thi s specia l enforcement consideratio n ma y rang e frommitigatin g th e sanctio n t o determinin g tha t

n o enforcemen t

actio n i s required . (2 ) J f aperso n i s not

covere dunde r

on e o f thes e program s bu t

nonetheles s voltmtaril y report s a n apparen t

violatio n t o th e FA A befor e th e FA A discover s it , take s immediat e actio n t o correc t th e noncompliance , an dwork s wit h th e FA A o n step s to preclud e recmrenc e ofth e apparen t violation , th e FA A ma

y conside r

suc h action s i n mitigatin g th e sanctio n fo r th e violation . m . Correctiv e Action . Th e FA A consider s correctiv e actio n amitigatin g facto r i n determinin g sanctio n pro-videdth e correctiv e actio n exceed s th e minimu mregulator y o r statutory requirements . Th e amoun t o f credi t give n i n settin g asanctio n depend s o n th e exten t an dtiming ofth e correctiv e action , that is , ho w extensiv e was th e correctiv e actio n an dho w c}uickl y wa s i t taken . Implementin g ne w procedure s that ar e abov e thos e require dunde r th e FAA' s regulation s 7- 8

## 10/01/0 7 2150.3 8 Minimu m$100-$29 9 (2 ) VIOLATION COMMITTE D B Y PART 129 OPERATO R Maximu m$18,750-$25,00 0 Moderat e $10,000- $ 18,74 9 Minimu m$2,000-$9,99 9 (3 ) VIOLATIO N COMMITTE D B Y PAR

T 12 5 OPERATOR . Larg e Busines s Concern : Maximu m$16,250-$25,00 0 Moderat e $8,750-516,24 9 Minimum$l,850-$8,74 9 Smal l Busines s Concer

n (fo r violation s covere dimder

4 9 U.S.C . § 46301(a)(5)(A)) : Maximum$8,250-Sn,00 0 Moderate $3,850-58,24 9 Minimu m$935-$3,84 9 Smal l Busines s Concer

n (fo r violation s covere dimder

4 9 U.S.C . § 46301(a)(1)(A ) o r (B ) bu t no t under 4 9 U.S.C . § 46301(a)(5)(A)) : Maximum$750- $ 1,10

0 Moderate $450-$74 9 Minimu m$25 0 $44 9 (4 ) VIOLATION COMMITTE D B Y AIRAGENC Y (INCLUDING REPAI RSTATION) . Larg e Busines s Concern : Maximu m$I6,250-$25,00 0 Moderat e $8,750- $ 16,24 9 Mfnimu m$l,850-$8,74 9 Small Busines s Concer

n (for violation s covere dunde

r 4 9 U.S.C . § 46301(a)(5)(A)) : Maximu m$7,150- $ 11,00

0 Moderat e $3,850-$7,14 9 Minimu m$935-$3,84 9 \ .

B- 5

## 10/01/0 7 2150.3 8

Fig . B-2-e . Othe r

provision s applicabl e t o individua l | Civi l Penalt y certificat e holder s cont . • Certificat e Actio n (b ) Lac k o f typ e ratin g 180-da y Suspensio n t o Revocatio n (c ) Misse dproficienc y chec k o r lin e chec k 30 - t o 90-day Suspensio n (d ) Lac k o f curren t experienc e 30 - t o 90-da y Suspensio n (e ) Failur e t o hav e curren t airman o r

medical certificat e i n possessio n Minimu mt o Moderat e (f ) Lac k o f initia l o r recurren t trainin g 30-t o 90-da y Suspensio n (g ) Operatio n wit h know n disqualifyin g disability Revocatio n (i ) Operatin g withou t

vali dmedica l certificat e whe n no t medicall y qualifie do r

applicatio n fo r

medical certificat e deferre d Revocatio n Fig . B-2-f

. Othe r Ai r Carrie r Personne l Civi l Penalt y Certificat e Actio n (1 ) Failur e t o kee p manua l curren t Minimu m 30-t o 90-day Suspensio n 3 . INDIVIDUAL S AN D GENERA L AVIATIO N - OWNERS . PILOTS . REPAI RSTATIONS . PILO T SCHOOLS . MAINTENANC E PERSONNEL . Fig . B-3-a . Owner s an dOperator s Othe r Tha n Require d( Civi l Penalt y Crewmember s Certificat e Actio n (1 ) Failur e t o compl y -wit h airworthines s directiv e Moderat e t o Maximu m (2 ) Failur e t o performo r improper performanc e o f maintenance , includin g require dmaintenanc e Moderat e t o Maximm n (3 ) Failur e t o mak e prope r entr y i n aircraf

t lo g Minimu mt o Moderat e (4 ) Operatio n o f

aircraf t beyon dannual , 100-hour , o r progressiv e inspectio n Minimu mt o Moderat e (5 ) Operatio n o f

unairworth y aircraf

t Moderat e t o Maximu m (6 ) Intentionall y fals e o r fi-audulent

entry , reproduction , o r alteratio n i n an y recor do r report Maximu m Revocatio n Fig . B-3-b . Repai r

Station s Civi l Penalt y Certificat e Actio n (1 ) Failur e t o provid e require dfacilitie s fo r prope r servicing , maintenance , repair , o r

inspectio n Moderat e t o Maximu m Indefinit e Suspensio n unti l complianc e t o Revocatio n



## 8-2 0

## 10/01/0 7 2150.3 8

Fig . B-3-b . Repai r

Station s cont . Civil Penalt y Certificate J Action (2 ) Failur e to provide qualifie

dpersonne l wh o ca n perfonn , supervise , an dinspec t

wor k fo r whic h th e statio n i s rate d Maximu m Indefinit e Suspension unti l complianc e t o 

## Revocation (3 ) Failur e t o maintain recor

do f supervisor y o r inspectio n personnel Moderat e t o Maximu

m (4 ) Failur e t o maintaJ

Q recor d Moderat e t o Maximu

m (5 ) Failur e t o ensur e tha t correct calibration of

al l inspectio n an dtes t equipmen t i s accomplishe

dat prescribedinterval s Minimu mto Maximu

m (6 ) Failur e t o adequately describ e wor k performed Minimu mt o Moderat

e (7 ) Failure o f

mechani c to mak

e lo g entry , record , o r

repor t (8 ) Failur e t o sig n or

complet e maintenanc e releas e Moderat e t o Maximu

m Minimu mt o Moderate (9 ) Inspectio n o f

wor k performed , o

r approva l for retur n to service , b y other tha n aqualifie

dinspecto r Maximu m U

p t o 30-da y Suspensio n (10 ) Failure t o hav e a

n adequat e inspection syste

mtha t produce s satisfactor

y qualit y contro l Moderat e t o Maximu

m (11 ) Maintainin g o r

alterin g a n articl e fo r whic h i t i s rated , withou t usin g require dtechnica

l data , equipmen

t o r facilitie s U p t o 30-da y Suspensio n Maximu m U

p t o 3 0-da y Suspensio n (12 ) Failur

e t o perfonn or

properl y perfon n maintenance , repair , alteration , o r

require dinspectio

n fo r a n ai r carrie r o r commercia

l operato r Moderat e t o Maximu

m U

p to 30-da y Suspensio n (13 ) Maintainin g or

alterin g a n airfi-ame, powerplant , propeller , instrument , radio , o r accessor y fo r which th e repai r statio n i s not

rate d Maximu m Suspensio n o r Revocation (14 ) Failure t o repor

t defec t o r unairworth

y conditio n to FAA in atimel y manne

r Moderat e t o Maximu

m (15 ) Failure t o satis ^ housin g an dfacilit y requiremen

t (16 ) Chang e o f

location , housing o r

facilitie s without

written approva l Moderat e Moderat e (17 ) Operatin g a s acertificatedrepai r station without

arepai r statio n certificat

e Maximu m (18 ) Failure to permi t

FA A t o inspect Maximu m Indefinit e Suspensio n unti l Complianc e (19 ) Failiuie t o perfor

minspection properly on part 125 aircraf t Moderat e (20 ) Failure t o compl

y wit h SFA R3 6 - Secon

doffens e Maximu

m (21 ) Failure t o maintain an dcarr y out BTS-requiredsecurit

y measure s unde r

4 9 U.S.C . § 44924(c)(1 ) Mandator y Suspensio n pending BT S finding o f complianc e ^ . 

## 8-2 1