7-srm_compress.pdf

Srtuctural Repair Manual

1. 1
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
STRUCTURAL REPAIR MANUAL INTRODUCTION Manufacturers
publish
Structural

Repai
r
Manual (SR
M) to
provide data for
the
structural
maintenance of commercial

airpl
a
nes which have
sustai
ned structural damage.
The Manuals are approved by
the
Aircraft
Manufacturers
Aviation Authority, for exampl
e:
•
D
GCA Dir
ection Générale
De L’Aviation
Civile
(
F
rance)
•
F
AA :
F
ederal Aviati
on Admi
nistration( USA)
•
T
he St
ructural R
e
pair Manual
contai
ns
:
materi
al

ide
n
tific
a
tio
n
for struc
t
ure su
b
ject
to field repair, t
y
pical

repai
r
s general appli
c
abl
e
to
structu
r
al
co
mpo
n
ents of th
e

airpl
a
ne that are most likely to be damaged,
•
infor
mati
o
n

rel
a
tive
to mate
rial s
ubsti
tution, fas
t
ene
r

instal
lati
on,
•
a
irplane ali
gnment check procedure
•
and a brief descri
p
tion of pr
ocedures that must be
performed concurrently with st
ructural rep
a
ir
, su
ch as
protective treatment of repai
r
parts and seali
ng of integral

fuel ta
nks.
Where repairs are
not
included, it does not follow that the
structure concerned is not repa
irabl
e
. Either it
has
not
be
en
found practicabl
e to desi
g
n
a
typical repair, or service
experi
ence has not yet i
ndicated a requirement.
In some instances, an adequat
e
repair design will require
eval
u
a
tio
n
by the M
a
n
u
factu
r
er.
Consider the foll
owi
n
g w
h
en ty
pica
l rep
a
ir
s are not found:
•
A
ccomplish
a
repair in accordance with the general repair
practices and procedures provi
d
e
d

in ch
a
p
te
r 51 -
S
truc
tures

General -
o
f
the manual.
•
P
reparing
a specifi
c
repair design for the damage not
covere
d.
•
R
eplaci
ng of the damaged part.
As
service experi
ence indicates a requi
r
ement, the manual

will
be revised to include actual
, specific repairs to both
primary an
d secon
d
a
r
y structur
es. To ensure consi
s
tent
handling of these
re
visio
n
s, in
dex cate
g
o
ri
es h
a
ve
be
en

established for all
known
types of re
pa
irs, altho
u
g
h some

information which falls within
these categories
will not be
rel
eased until warranty
service experience.
It is indented that, in the ev
ent
of
a major damage, the
informati
on incl
uded in the ma
nual be suppl
e
mented
as
required by direct liaison
wit
h t
h
e r
e
pair
as
s
igned

Manufacturer Customer Support Representative.

2. 2
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
STRUCTURAL REPAIR MANUAL For orderi
ng
structural
repa
ir parts see Spare Parts
Identificati
o
n, located i
n

the 00-
Introduction Part.
The manual wi
ll serve as a
m
e
dium
t
h
r
o
ugh whic
h
t
h
e
airplane operators will be advi
sed
of actual repairs with
general
-
interest nature, desi
g
ne
d
by
the Manufacturer or by
the ai
rplane operator.
SERVICE BULL
E
TINS
Service bul
letins w
h
ich have
in
corporated are listed i
n
the
00 -
I
ntroduction secti
o
n.
Service
Bulleti
ns are recommen
dati
ons from Manufacturer,
which are not urgent
to
put into ac
tion.

3. 3
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
REVISI
ON SERVICE
LIST OF EFFECTIVE PA
GES
The
SRM
is
provided with a Li
st of Effec
t
ive Pages. All
pages are listed i
n
sequence
, together with
their latest
r
e
v
is
ion dat
e.
I
n
Air
bus
M
a
nuals
t
h
e lis
t
is
loc
a
t
e
d in
ev
er
y
AT
A Chapter. Boei
ng provi
d
es
it in the Manual
s
Intro
ducti
o
n
.
The List of Effective
P
a
ges
will be revised with each regular
revisi
on of the Manual.
REGULAR REVISION SERVICE Revision service to the manual

will be issued periodically.
Each man
u
a
l takes a revisi
on
number and date
of issue on
the outsi
de label, to c
heck the
effectivity
o
f t
he
hole
Manual

by a document list. Pages w
h
ic
h are revi
sed wi
ll be so indicated on the
list
of
effective pages by an asterisk (*) and i
d
entified by
a
date.
A

revised page may be dated prior
to, or as same as, the date
of the revisi
on cycl
e.
On
each i
n
divi
dual page the revi
sed area is indicated by a
revisi
o
n
ba
r on th
e left mar
g
in.
TEMP
ORARY REVIS
I
ON SERVI
CE
Temporary revision service to
the manual will
be issued as
necessa
ry
to
al
ert th
e
customer
of confi
g
uration differences
and to provide
temporary
in
st
ructions prior to the next

sche
d
u
le
d
revisi
o
n
.
Temporary revision will
also
be
issued as a
result of a
customer request for
planned
in
corporation of a service
bul
leti
n.
Each temp
ora
r
y revisi
on wi
ll b
e

in
corporated into the manual
withi
n 90 days
from
date
of
issua
n
ce, except fro
m
those

t
e
m
p
orar
y r
e
visions,
issued
as a result of
pl
anned
incorporati
on of a service bull
eti
n
.
These service bulleti
n
temporary revisions will remain active
until the Manufacturer

has
been
advised by the customer
that incorporati
o
n of
the
service
bul
leti
n

into the airplane has
been completed. Eac
h
t
e
mpor
ar
y
r
e
vis
ion
will ap
ply
t
o
one
s
u
bjec
t
on
ly a
n
d
will be keyed within this manual
, so that the temporary
revision will be filed adjacent
to the affected
pages.
Temporary revisions will not be
revised if changes are
r
e
quir
ed t
o
an exis
t
ing
t
e
m
p
orary revisi
on, the
temp
ora
r
y
revision will be reissued.

4. 4
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
CHAPTERI
ZATION
In accordance w
ith the ATA Specificati
o
n No.
100,
the
m
a
t
e
r
ial pres
ent
e
d in t
h
is
m
anual is divi
ded i
n
to
seven
cha
p
ters.
CHAPTER NUMBERS •
C
hapt
er
51 St
r
u
c
t
ures -
G
eneral
•
C
hapter 52 Doors
•
C
hapt
er
53 F
u
s
e
lage
•
C
hapter 54 Nacel
les
I
Pylons
•
C
hapter 55 Stabilizers
•
C
hapter 56 Windows
•
C
hapter 57 Wings

5. 5
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
53
57
52
54
56
55

6. 6
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
SRM
-
CHAPTER 51
Chapt
e
r
51 deals
wit
h t
hos
e subjec
t
s
whic
h ar
e general in
nature to the enti
r
e structure of
the airpl
a
ne. It contai
ns the
following subjects: General Inform
ation:
•
M
ajor Assembly Breakdow
n
•
P
rincipal Dimensi
ons
•
S
tructure Classific
a
ti
on
•
A
bbreviati
ons
•
A
pproved methods for damage clean-up.
Aerod
y
namic S
m
oot
h
n
ess:
•
R
equirement
s and recom
m
endat
ions f
o
r
f
light
saf
e
t
y
and
economic reasons. Processes an
d Proced
ures:
•
G
eneral procedures such as protective treatment,
hardness testing
and f
ir
e
damage ev
aluat
ion.
Mate
rials
:
•
S
heet Metal
•
M
inimum Bend R
a
dii

•
E
xtrusions and Formed Secti
o
ns
•
N
on-metallic Materials
•
S
ubstitution D
a
ta
Fasteners:
•
F
astener Codes
•
I
nstallation and R
e
moval
•
S
ubstitution D
a
ta
•
T
orque Values
•
H
ole Sizes
•
E
dge Margins
•
C
ountersi
nking
•
C
old Working
•
S
trength Values
Support of Airplane for Repair
:
•
D
etails of supports and l
o
ads w
h
ich can be appli
e
d at
vari
ous poi
nts on structure.
Alignment or Sy
mme
try
Checks
:
•
M
eans of checki
ng for sign
ificant deformati
on of the
structure. Da
mage R
e
mov
a
l: C
o
mposite Repair Instructions
•
D
etailed repair instructions
for all composite fabric
c
o
m
p
onents
inc
lud
in
g we
t
lay
-
up r
e
pair
s
and hot
bonding
rep
a
ir
s to fiber
gl
ass, carb
o
n
fib
e
r, aram
id
e
f
iber as we
ll as
hybr
id fa
br
ic
comp
on
e
n
ts
an
d sa
ndw
ich co
mpo
n
ents.

7. 7
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE

8. 8
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
CHAPTER 52-57 Chapt
e
r
s
52 t
h
ru 57 deal wit
h
majo
r
ai
rplane c
o
m
p
onent
s
.
T
he s
e
ct
ion number
s
are

assigned for specific componen
ts with the ma
jor groupi
ng.
Section N
u
mberi
ng Boeing Aircraft Chapter 53, Fuselage
Section
A
TA Reference
D
e
sig
n
atio
n
•
41 53-10-00
F
uselage
betw
een BSTA 178 and BST
A 360
•
43 53-30-00
F
uselage
betw
een BSTA 360 and BST
A 540
•
4
4
53-40-00 Fuselage
betw
een BSTA 540 and BST
A 727
•
46 53-60-00
Fuselage
betw
een BSTA 727 and BST
A 887
•
4
7
53-70-00
F
uselage betw
een BSTA 888 and BST
A 1016
•
48 53-80-00
Fuselage
betw
een BSTA 1016 and BSTA 1156

9. 9
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
SUBJECT NUMBERS ASSIGNM
E
NT
CHAPTERS 52 THRU 57 5X-XX -
-00 General -01 Ski
n
s and Plates
-02 Structure Complete -03 Stri
ngers and Skin Stiffeners
-04 Interc
o
s
tals
-05 Longerons -06 Formers -07 Frames -08 Bulkheads -09 R
ibs
-10 Spars -11 Intermediate, Auxiliary and Subspars -12 Keel Structure -13 Beams -14 Landing Gear Support Structure -15 D
o
or Surround Structure
-
16 Edge M
e
mber
s

-
17 thru 29 not used
-30 Auxili
ary
-31thru 49 not used -50 Floor Structure -52 Se
at Tracks
-53 C
a
rgo Compartment
Speci
a
l Structure
5X-XX -
-54 thru-69 not used -70 Fill
ets an
d Fairi
n
gs, Skins and Plating
-72 R
a
do
mes
a
n
d
Antenna Fairin
gs
-
73 thru 89 not used
-90 Attac
h
ment Fittin
g
s
-91 thru-99 not used

10. 10
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
PAGE BL
OCK AL
L
O
CATION
In Cha
p
te
r
s
52 thr
u
5
7
eac
h s
ubject represents a structural
element. All of the data concer
ni
ng that el
ement are covered
withi
n that sub
ject. To provi
d
e to
pic se
pa
rati
on p
a
ge bl
ocks
are used. •
IDENTI
FICATION:
Page 1to 99
•
AL
LOWABLE DAMA
G
E:
Page 101 to 199
•
REPAIRS:
Page 201 to 999
Chapt
e
r
51 has
no ident
if
y
ing page bloc
k
.

11. 11
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE

12. 12
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
DAMAGE CLASSI
F
I
CATION
The term “damage”
as used i
n
th
e Structural
Repair Manual
and other Manuals, is defined
as includi
ng any and every
type of p
e
r
m
an
e
n
t deform
a
tio
n
o
r
alter
a
tio
n
to any c
r
oss
-
sectio
n of a
structural comp
o
n
e
n
t.
Deformati
o
n or alterati
on to the
cross-secti
o
n
of a structura
l
comp
o
n
e
n
t results fro
m
ma
ny ca
uses w
h
ich can be general
ly
categ
o
r
ize
d into four mai
n
gr
o
u
p
s
:
•
Mechani
cal action
-
includes brinelling, buckling,
burnishi
ng, burring, chafing,
cracking, distorti
on (twisti
ng),
erosion, fretting, ga
lli
ng, gouging, indent
ation, misal
ignment,
nicki
ng, rub
b
in
g, scorin
g
, scr
atching, and
gener
a
l wear
.

•
C
hemic
a
l or electro-chemical re
a
c
tion
-
inc
ludes

corrosi
on, pinholes, pi
tting, and scali
n
g.
•
T
hermal action
or cy
cli
n
g
-
includ
e
s b
r
ittle
ness, b
u
ckl
ing,
burni
ng, heating,
and pickup.
•
I
n
h
erent metallurgical characteristics
-
inclu
d
e
s col
d

shut, cre
e
p
(plastic fl
o
w
), fatig
ue (cyclic stre
ssing
), incl
usio
n,
and porosity. Damage cl
assified under the l
a
st
two categories
, in all areas,
is consi
d
ered as being non re
pai
r
able, and the structural
component must be replaced.
Dam
a
g
e
cl
assifie
d
u
n
der the first two cate
go
ries i
n
certain
specifi
e
d areas of the airpl
a
ne
structure, is consi
d
ere
d
as
bei
ng repai
r
able.
Investigatio
n of Damage
In order that the necessary
repa
ir
p
r
o
c
ed
ur
es c
an be
determi
ned, the type and extent of damage must be
pr
oper
ly
a
n
d t
h
or
oughly
inv
e
s
t
iga
t
e
d
.

In order to determi
ne the da
m
a
ge
categ
o
ry, the sus
p
ected
or affected are
a
m
u
st be p
r
e
p
ared by removing any foreign
matter de
p
o
sits from the co
mp
o
n
ent su
rface
,
cutting o
u
t
any broken, bent, heated, burn
t or otherwise obvi
ously
damaged areas of the component, and removing l
o
ose
rivets where apparent. •
I
n additi
on to the damaged or
affected area itself, any
adjacent attachment points
and! or connec
ti
ons, thr
o
u
g
h
which abnormal loads may have
been transmitt
ed, must be
fully investigated. •
I
f misalig
nme
n
t or twistin
g
of the a
ir
p
la
n
e
structur
e i
s

suspected, ali
g
nment and! or l
e
veli
ng checks must be
c
a
r
r
ied ou
t
.

13. 13
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
DAMAGE CATEGORIES After cleani
ng and invest
igating the damaged and
surrounding area, th
e damage must be cl
assified i
n
to one
of the fol
lo
win
g thr
ee categ
o
r
ies, also taki
n
g
into acc
o
u
n
t
the locati
on of the damage.
REPAIRABLE DAMAGE The damage must be classifi
ed either as “All
owabl
e

Damage”
o
r
as
dam
age which requires
a repair
.

Allow
a
ble Da
mage
Allow
abl
e damage is defined as
damage which is slight or
of little significance, and is
un
lik
el
y to be of s
u
fficie
n
t
sever
ity to pro
p
a
g
a
te furth
e
r d
a
m
a
g
e
in th
e i
mme
di
ate
vicinity. Note:
Allow
a
ble does not me
an that repair is
u
n
n
ecessary
.
F
o
r example, scratches and
b
u
rring are inclu
d
e
d
in
th
is categor
y
,
an
d

it is necessary
to
remove rou
g
h
and
sharp
edges and smooth out the damage. In add
i
tio
n
,
an
y damage to surface coatings
and
/
or pro
t
ective treatment must be
repaired using an approved procedure dealt w
i
th u
n
d
er SRM chapter 51.
Non-allow
a
ble Dama
ge
Damage
w
h
ich exceeds the “A
llowable Damage”
limits
must be repai
red by cutting
out the damaged area of a
structural component and inserti
ng or attaching a
rei
n
forcing piece. Th
e
s
e spec
ific rep
a
ir
s ar
e to be fo
un
d
in
each chapter of the SRM. NON REPAIRABLE DAMAGE Non repai
rabl
e damage is defi
ne
d as d
a
m
a
ge to str
u
ctura
l
components which cannot
be repaired and where
replacement of the compl
e
te
co
mpo
n
ent is
reco
mme
n
d
e
d

as a repair is not pr
acti
cal or economical.

14. 14
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE

15. 15
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE

16. 16
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
TY
PES
O
F
S
T
RUCTURAL DAMAGE
In order to facilitate the classi
fication of different repair
procedures, the vari
ous types
of
da
m
age are gr
ouped as
follows: Ma
rk
•
A
mark is to be underst
ood as a damage area of any
size where an accumul
a
tion of
scratches, nicks, chips,
burrs or gouges etc.
is present i
n
such a w
a
y that the
damage must be treated as an ar
ea and not as a series of
indiv
idual sc
r
a
t
c
hes
,
gouges
et
c
.

Scratch •
A
scratch is a line of dama
ge of any depth and length in
the materi
al and results in a
c
r
os
s-
s
e
c
t
ional ar
e
a
change.

It is usually caused by contact with a object. Gouge

•
A
gouge i
s
a damage area of any size w
h
ic
h results i
n
a
cross—section
a
l a
r
e
a
cha
n
g
e
. It is usua
lly caused by
contact with a relativel
y
shar
p object which produces a
conti
n
uous, sharp or smooth
channel-like groove in the
mate
ria
l.
Crack •
A
crack is a partial fracture or complete break i
n
the
mate
ria
l with the most sign
ifica
n
t cross-secti
o
n
a
l a
r
e
a

c
h
ange.

Dent •
A
dent is normally a dama
ge area w
h
ich is depressed
with respect to its normal
contour. There is no cross
s
e
c
t
ional area c
hange in t
he m
a
t
e
r
ial;
ar
ea
boundar
ies

are smooth.
Distorsion •
A
ny twisting, bendi
n
g or pe
rm
an
en
t
s
t
r
a
in
which r
e
sult
s

in misali
gnment or
ch
an
ge of sh
ap
e. May b
e
cause
d
b
y

imp
a
ct fro
m
a for
e
ig
n
ob
ject, but usua
lly r
e
s
u
lts from
vibration or moveme
nt of ad
jace
n
t
attache
d
comp
o
n
e
n
ts.
This group incl
udes bendi
n
g, buckling, deformation,
imbal
ance, misal
ignment,
pinchi
ng, and twisti
ng.

17. 17
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
REPAIRS I
deally
,
r
epair
s
ar
e des
igned t
o
m
eet
s
t
at
ic
and f
a
t
igue
stren
g
th re
qui
re
me
nts
for the
service life of the airplane.
Practical s
o
luti
o
n
s to rep
a
ir
pr
ob
le
ms so
meti
mes r
e
q
u
ir
e a
repair which will not ne
cessarily be permanent.
These are: Time Limited Repair •
M
ust be repl
aced after a specifi
ed time with a permanent
rep
a
ir
.
Interim R
e
pair
•
M
ust be inspected at specifie
d i
n
tervals and repl
aced if
there is deteri
oration.
Chapter 52 -
57 of the SRM cover typical repairs for
general use and sp
eci
f
ic repairs for know
n problems
which are generally applicabl
e to all operators. The
m
a
nual does
not
inc
lude s
p
ecific repai
r
s where a
prev
e
n
tive mod
ificati
o
n
is pr
ovi
d
ed in a servi
c
e bull
etin.
Repairs in the manual ar
e authority approved.

18. 18
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
STRUCTURE CLASS
I
FICATION
A schemati
c
breakdow
n of the
aircraft structure showing the
r
e
lat
ions
h
ip bet
ween pr
im
ar
y

and secondary
structure and
‘Princi
p
al Structural El
ements’
(
P
SE).
A List of PSE’s
is given i
n
the chapter w
here applicabl
e
.
The structure of the ai
rcraft is
classified either as pri
m
ary or
seco
nd
ary. Primary structur
e is that structure whlich
contri
butes significantl
y
to
carryi
n
g flight, ground and
pressurizati
on l
o
ads.
Secon
d
a
ry structure is that stru
cture w
h
ich carri
es only air or
iner
t
ia I
oads
generat
ed on or
within t
h
e s
e
condar
y
s
t
r
u
c
t
ur
e.

Within the primary structure
there are el
ements that are
desi
g
nated PSE; PSE’s
a
re those
elements that contri
bute
signiflcantly
t
o carrying fligh
t, ground and pressurizati
on
Ioads, and whose i
n
te
grity is essenti
a
l i
n
maintai
n
ing the
overal
l structural i
n
t
egrity of the airpl
a
ne.
NOTE: Where tw
o items that are PSE
are connected together and
the conconnecti
ng
item is re
movabl
e then the connecti
ng
item is also to be consi
dered as PSE.
PSE parts are i
d
entifi
ed i
n
Chapter 51 -
S
tructure
Classific
a
ti
on.

19. 19
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE

20. 20
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
PROCEDURE F
O
R MANUAL USAGE
The followi
ng procedure is recomm
ended for the effici
ent use
of the Structural R
e
pai
r Manual:
1.
Check for allow
a
ble damage.
2.
From the Table of C
onten
ts of the m
a
n
u
a
l find th
e
cha
p
ter to whic
h the
damaged part bel
ongs.
3.
Turn to the Table of C
onten
ts of the selected chapter,
find subject number of Allow
abl
e Damage.
4.
Dam
a
g
e
Cl
assificati
o
n
-
G
ene
ral, to determi
n
e
if the
damage is all
o
wabl
e.
5.
lde
n
tify
the dam
a
g
e
d
p
a
rt.
6.
lf it is found t
hat the damage exceeds
the al
lowable, the
part must be identifi
ed in
order to determi
ne the
applicable re
p
a
ir fi
gu
re
.
7.
From the Tabl
e of C
o
ntents
of that chapter, find subject
num
b
e
r of i
d
e
n
tificati
o
n
figu
re, th
at incl
ud
es the
damaged par
t
.
8.
Find the item number of
the damaged pa
rt from th
e
ide
n
tific
a
tio
n
figu
re.
9.
Check mo
d
ificatio
n
sta
t
us of the damaged part.
10.
Turn to tab
u
lati
o
n
she
e
t of
the i
d
entificatio
n figure. Find
the applicable repai
r fi
gure number.
11.
Apply repai
r
figure to actual damage.
12.
Turn to the rep
a
ir
fig
u
r
e
mentioned abov
e, read notes
and instructions carefully
, and perform the repair
accor
d
ing to the fi
gur
e
.
13.
Use the Table of Contents
, att
h
e beginni
ng of each
cha
p
ter, as
a nu
mer
ic
a
l
14.
lndex
t
o locate a specific subject withi
n a specific
section of a chapter.
15.
Rea
d
a
ll th
e tex
t
material, su
p
p
o
r
ting fig
u
r
e
s
and
references withi
n a
specific subject.
16.
Cha
p
te
r 5
1
lists the se
ctions a
n
d subsectio
n
s
general
ly appl
icabl
e
(excep
t whe
n
limite
d
) to
the
entire airpl
a
ne.
17.
Cha
p
te
rs 5
2
,53, 54, 5
5
, 56, a
n
d 57 list suc
h
sections
and subjects which are app
lic
abl
e resp
ectiv
e
ly
to
those speci
f
ic chapters only.
18.
The use of the ta
ble of conte
n
ts to loc
a
te sp
ecific
rep
a
ir
s, suppl
e
ments the information g
ive
n a
bove.
19.
Within every chapter ,except 56, any subject which contains the word “repair”,
lists ea
ch re
pa
ir fi
gur
e
number and title which is ap
plicable to the specific
sub
ject.
20.
Look for all
the Cross -
R
eferences to the
Mai
n
tenance Manual, Proc
ess Specificati
o
ns and
Standard Practi
ce Ma
nu
als.

21. 21
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE
TY
PICAL
AIRPLANE
E
F
F
E
CT
I
V
I
T
Y AL
L
O
CATION LI
ST

The
I
ist
g
ives
Infor
m
ation
a
b
out:
•
T
he
c
u
r
r
ent
o
perat
o
r
•
M
odel
Senes,
•
B
lock
Number,
•
L
ine
N
umber
(Cum
li
ne),
•
O
mni
N
umber,
•
R
egistry
Number
•
M
anufacturer
S
enal
Number
(MFG)
T
h
e
I
is
t
s
ar
e pubuis
hed
in alphabet
ic
a
l
o
rder,
I
o
c
a
t
e
d
in t
h
e
Intro
ducti
o
n
pa
rt
ofth
e
S
RM.

22. 22
Linhas aéreas Inteligentes
BOEING-SRM COMPOSITE