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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425,
427-428, 430-433, 435-450, 501-501, 503-504, 506-506, 508-508, 510-51
2, 517-525, 527-527, 529-529, 531-536, 540-550, 561-567, 571-571, 582600
TASK 72-00-00-200-025-A
Over-Serviceable-Limit Extensions
FIN: 1000EM1 1000EM2
WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE
ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGIN
E PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN
BURN YOU.
1.
Reason for the Job
This TASK is applicable to NON /P and NON /3 engines.
It can occur that specific defects do not agree with the "Maximum Serviceable Limit
s", and that the maintenance facilities, at a given location, are not sufficient to do th
e necessary corrective actions.
In these circumstances, limit extensions will permit to send the engine where correcti
on is possible, or to schedule the necessary maintenance in the extension period.
NOTE:
2.
The limit extensions are one-time extensions only. Applicable hardware acti
on is necessary at the completion of the extended serviceable period.
Job Set-up Information
A.
Work Zones and Access Panels
ZONE/ACCESS
400
B.
ZONE DESCRIPTION
POWER PLANT, NACELLES AND PYLONS
Referenced Information
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
REFERENCE
DESIGNATION
Ref. 72-21-00-210-009
-A
Inspection of Fan Rotor Blades Installed on the Fan
Disk
Ref. 72-23-00-000-008
-A
Removal of the Fan Outlet Guide Vane (OGV) Doub
lets
Ref. 72-23-00-210-003
-C
Detailed Inspection of Spinner, Engine Inlet, Fan Bl
ades, Fan Outlet and Abradable Material
Ref. 72-23-00-400-008
-A
Installation of the Fan Outlet Guide Vane (OGV) Do
ublets
Ref. 79-00-00-210-003
-A
Visual Inspection of the Oil System
Ref. Fig. Booster Rotor and Stator Damage Extended
Ref. Fig. Extended Vanes Damage Limits
Ref. Fig. Inspection/Check of the Fan Outlet Guide Vanes (OGV)
Ref. Fig. Outlet Guide Vane (OGV) Inner Platform for Missing Material
Ref. Fig. Measurements of Airfoil Indication on Low Pressure Turbine Blades
(all stages)
Ref. Fig. Outlet Guide Vane (OGV) Inner Platform for Cracks
Ref. Fig. Cracks and Missing Material in the Dome Area
3.
Job Set-up
SUBTASK 72-00-00-941-071-A
A.
Not applicable
4.
Procedure
Ref. Fig. Booster Rotor and Stator Damage Extended
Ref. Fig. Extended Vanes Damage Limits
Ref. Fig. Inspection/Check of the Fan Outlet Guide Vanes (OGV)
Ref. Fig. Outlet Guide Vane (OGV) Inner Platform for Missing Material
Ref. Fig. Measurements of Airfoil Indication on Low Pressure Turbine Blades (all stag
es)
SUBTASK 72-00-00-210-071-A
A.
Over-serviceable-limit Extensions
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
1.Fan and booster
A.Spinner front con
e
(1)Corrosion marks
(white mushroom p
attern) before part
removal.
A continu
ation in se
rvice of 1
00 cycles
maximum
is permitt
ed.
B.Spinner rear cone
(1)Oil wetting at in
ner of spinner cone
or fan disk or forwa
rd fan shaft.
50 cycles
(2)Seal ring tear: a
ny number if cumul
ated length is more
than 0.400 in. (10.
16 mm).
50 cycles
C.Fan blade
(1)Fully missing mo
lydag on inner face
s of the platforms
250 cycles
(2)Flaking of Cu.Ni.
In coating on blade
dovetail pressure fa
ces (contact areas),
up to 10% if the co
ating adherence is
correct in the adjac
ent areas and if the
re is no indication o
f wear on base mat
erial.
Do the ins
pection ag
ain of the
fan blade
before 12
00 cycles.
Repeat ex
tension is
permitted.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(3)Flaking of Cu.Ni.
In coating on blade
dovetail pressure fa
ces (contact areas),
more than 10% an
d less than 50% if t
he coating adheren
ce is correct in the
adjacent areas and
if there is no indicat
ion of wear on base
material.
400 cycle
s.
(4)Shingling at mid
span shrouds
Turn the s
hingled bl
ades to th
e 12 o'clo
ck positio
n and uns
hingle wit
h hand for
ce or by u
sing a pie
ce of woo
d. Examin
e blades f
or service
ability Re
f. AMM TA
SK 72-2100-210-0
09. Remo
ve and se
nd the shi
ngled blad
es to a sh
op for a di
mensional
inspection
and an Flu
orescent P
enetrant I
nspection
(FPI) in le
ss than 50
cycles.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(5)Nicks, dents, scr
atches and sheared
edges on midspan s
hroud surfaces up t
o 0.035 in. (0.89 m
m) deep if defects
are not in the mids
pan shroud to airfoi
l fillet radius.
50 cycles
(6)Missing or dama
ged hard coating on
midspan shroud pre
ssure faces more th
an 20% but less th
an 40% of coated a
rea.
50 cycles
D.Fan disk
(1)Wear greater th
an 50% of area on
disk dovetail pressu
re faces.
100 cycles
E.Booster rotor bla
de for:
(1)Piece missing: a
ny number in area
G, at Leading Edge
(LE) and Trailing Ed
ge (TE) tip corners,
0.800 in. (20.32 m
m) radial and 0.500
in. (12.70 mm) axi
al.
50 cycles
or 75 hou
rs
(whicheve
r comes fi
rst)
(2)Cracks and tears
in area G, 0.800 in.
(20.32 mm) from ti
p: any number, les
s than 0.800 in. (2
0.32 mm) radial an
d less than 0.492 i
n. (12.50 mm) axia
l.
50 cycles
or 75 hou
rs
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(3)Wear or local dis
tortion of TE and LE
tips if less than 15
blades, 0.984 in. (2
4.99 mm) radial an
d 0.590 in. (14.99
mm) axial.
100 cycles
or 150 ho
urs
(whicheve
r comes fi
rst)
(4)Nicks, dents, scr
atches for area E: a
ny number, less tha
n 0.059 in. (1.50 m
m) in diameter, pro
trusion acceptable,
not thru.
50 cycles
or 75 hou
rs
(whicheve
r comes fi
rst)
(5)Nicks, dents, scr
atches for airfoil ou
t of area E, not LE
and TE: any numbe
r, less than 0.236 i
n. (5.99 mm) in dia
meter, protrusion a
cceptable.
50 cycles
or 75 hou
rs
(whicheve
r comes fi
rst)
(6)Nicks, dents, scr
atches out of area
E on LE and TE: ma
ximum axial length
less than 0.059 in.
(1.50 mm).
50 cycles
or 75 hou
rs
(whicheve
r comes fi
rst)
(7)Distorted LE and
TE, out of area E:
maximum circumfe
rence equals 0.275
in. (6.98 mm) radia
l length equals 0.70
8 in. (17.98 mm).
50 cycles
or 75 hou
rs
(whicheve
r comes fi
rst)
F.Booster vanes (st
age 1 only) for:
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(1)Piece missing:
Maximum 20 blade
s more than 0.256 i
n. (6.50 mm) axial,
0.728 in. (18.49 m
m) radial, no cracks
starting from dama
ge area allowed in
areas A and B.
50 cycles
or 75 hou
rs
(whicheve
r comes fi
rst)
(2)Cracks and tears
in area C, any num
ber, more than 0.2
56 in. (6.50 mm) r
adial and 0.078 in.
(1.98 mm) axial. In
areas A and B, any
number more than
0.128 in. (3.25 m
m) radial and 0.039
in. (0.99 mm) axia
l.
10 cycles
or 15 hou
rs
(whicheve
r comes fi
rst)
(3)Distortion of TE
and LE: any numbe
r, if the length L is
not more than 1.00
0 in. (25.40 mm) a
nd the maximum di
mension X along th
e chord width is not
more than 0.482 i
n. (12.24 mm).
50 cycles
or 75 hou
rs
(whicheve
r comes fi
rst)
(4)Nicks, dents, scr
atches for areas A
and B: any numbe
r, less than 0.157 i
n. (3.99 mm) in dia
meter, protrusion p
ermitted.
10 cycles
or 15 hou
rs
(whicheve
r comes fi
rst)
(5)Nicks, dents, scr
atches for area C: a
ny number, less tha
n 0.295 in. (7.49 m
m) in diameter, pro
trusion permitted.
50 cycles
or 75 hou
rs
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(6)Nicks, dents, scr
atches LE and TE m
aximum axial lengt
h less than 0.118 i
n. (3.00 mm) in dia
meter.
20 cycles
or 30 hou
rs
(whicheve
r comes fi
rst)
(7)Cracked inner sh
roud: maximum of
four cracks extendi
ng from the LE to t
he TE of the inner s
hroud (passing thro
ugh a recess) are p
ermitted if there is
a minimum separati
on of three non-cra
cked vane recesses
between two cracke
d recesses.
3000 hour
s or "C" c
heck
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
A sound check (see
note below) done o
n the vanes at, and
adjacent to the crac
ked inner shroud ar
ea, must demonstr
ate no difference in
tonality.
MAX. EX
TENSION
This exten
sion may
be used a
gain indefi
nitely in in
tervals of
3000 hour
s as long
as there is
no further
deteriorati
on of thes
e conditio
ns.
NOTE:
S
o
u
n
d
to
n
al
it
y
c
h
e
c
k
re
c
o
m
m
e
n
d
at
io
n.
A
s
o
u
n
d
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
to
n
al
it
y
c
h
e
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b
ra
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bl
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m
at
er
ia
li
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si
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e
th
e
in
n
er
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
s
h
ro
u
d
is
st
ill
in
c
o
nt
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ct
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it
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c
yl
in
d
ri
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
c
al
to
ol
m
a
d
e
of
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el
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it
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y
0.
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(
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7
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).
(F
or
e
x
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
a
m
pl
e,
a
ra
tc
h
et
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o
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
o
d
d
o
n
ot
p
er
m
it
th
e
d
et
e
ct
io
n
of
si
g
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a
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
e
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
k.
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© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
fo
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https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
e
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
st
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https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
o
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st
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https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
e
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th
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https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
th
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ot
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er
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© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(8)Vane LE and TE
Nicks, dents a
nd scratches
on LE and TE i
n areas B and
C with a maxi
mum axial len
gth less than
0.117 in. (2.9
7 mm).
10 cycles
or 50 hou
rs
(whicheve
r comes fi
rst)
-
2 cycles o
r 10 hours
(whicheve
r comes fi
rst)
Nicks, dents a
nd scratches
on LE and TE i
n area A with
a maximum a
xial length of
0.117 in. (2.9
7 mm).
2.Fan frame
A.Fan frame
(1)Cracks, any num
ber if maximum len
gth of 0.160 in. (4.
06 mm) and minim
um separation of 1.
000 in. (25.40 m
m).
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(2)Nicks and dents:
any number
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
B.Fan inlet case
(1)Cracks: any nu
mber, if maximum l
ength of 0.160 in.
(4.06 mm) and min
imum separation of
1.000 in. (25.40 m
m).
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(2)Nicks and scratc
hes: any number
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(3)Crater in abrada
ble liner (length<5x
width) and damage
other than crack ru
b and circumferenti
al defect: if the da
mage is within the
maximum servicea
ble limit Ref. AMM
TASK 72-23-00-21
0-003, but the fan
case parent metal i
s exposed and is co
nfirmed via visual i
nspection to be und
amaged.
50 cycles
or 125 ho
urs
(whicheve
r comes fi
rst)
(4)Grooves in abra
dable liner (oriente
d within 0 degree t
o 80 degree from e
ngine axis and leng
th>5x width: if the
damage is within th
e MAX serviceable li
mit Ref. AMM TASK
72-23-00-210-003,
but the fan case pa
rent metal is expos
ed and is confirmed
via visual inspectio
n to be undamage
d.
50 cycles
or 125 ho
urs
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
(5)Circumferential
defect in abradable
liner (360 degree o
r oriented within 80
degree to 90 degre
e from engine axi
s): for one or a cu
mulated defect less
than 2.000 in. (50.
80 mm) if the fan c
ase parent metal re
mains not damaged
under visual inspect
ion.
MAX. EX
TENSION
50 cycles
or 125 ho
urs
(whicheve
r comes fi
rst)
C.Outlet Guide Van
es (OGV) for:
Ref. Fig. Inspectio
n/Check of the Fan
Outlet Guide Vanes
(OGV)
(1)Broken vane: no
t serviceable, the b
roken vane has to b
e removed prior to
next flight.
10-cycles
extension
if the brok
en vane is
removed.
A complet
e set insp
ection is r
equired w
hen a new
doublet is
installed.
Replace th
e vane do
ublet Ref.
AMM TAS
K 72-23-0
0-000-00
8 and Ref.
AMM TAS
K 72-23-0
0-400-00
8.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
(2)Missing vane: on
e doublet missing
MAX. EX
TENSION
10-cycles
extension.
A complet
e set insp
ection is r
equired w
hen a new
doublet is
installed.
Replace th
e vane do
ublet Ref.
AMM TAS
K 72-23-0
0-000-00
8 and Ref.
AMM TAS
K 72-23-0
0-400-00
8.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
(3)Transversal crac
ks on inner platfor
m: not more than 3
0 transversal crack
s per platform for t
he whole set:
With no more
than 15 trans
versal cracks i
ncluded 5 ope
ned transvers
al cracks maxi
mum on area
E.
With no more
than 15 trans
versal cracks i
ncluded 5 ope
ned transvers
al cracks maxi
mum on area
I.
And with no
more than 15
transversal cr
acks included
5 opened tran
sversal cracks
maximum on
area M.
Do not change the
place of the cracke
d OGV on the engin
e for view of transv
ersal cracks and op
ened transversal cr
acks.
Ref. Fig. Outlet Gui
de Vane (OGV) Inn
er Platform for Crac
ks
MAX. EX
TENSION
750-cycle
s extensio
n renewab
le after in
spection.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(4)Cracks on outer
platform: from or al
ong the airfoil are d
efined in:
Ref. Fig. Inspectio
n/Check of the Fan
Outlet Guide Vanes
(OGV)
50-cycles
extension
(5)Metal LE missin
g: up to 0.780 in.
(19.81 mm) in heig
ht and 0.390 in. (9.
91 mm).
100-cycle
s extensio
n
(6)Nicks and/or de
nts, on LE (metallic
LE), if damage bet
ween 0.120 in. (3.0
5 mm) and 0.190 i
n. (4.83 mm) deep.
A maximu
m service
extension
of 100 cyc
les.
(7)Erosion of comp
osite material, any
amount
50 cycles
or 125 ho
urs
(whicheve
r comes fi
rst)
(8)Missing material
on only one side of
the inner platform f
or extrados or front
edge, see Sheet 1 o
f.
Ref. Fig. Outlet Gui
de Vane (OGV) Inn
er Platform for Miss
ing Material
Less than 0.160 in.
2 (103.23 mm2) on
two platforms maxi
mum.
Do not change the
place of OGV with
missing material on
the engine.
No missing OGV all
owed on the set.
10-cycles
extension
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
(9)Missing material
on only one side of
the inner platform f
or intrados or aft e
dge, see Sheet 1 o
f.
Ref. Fig. Outlet Gui
de Vane (OGV) Inn
er Platform for Miss
ing Material
For five platforms
maximum and no
missing OGV allowe
d on the set.
Do not change the
place of OGV with
missing material on
the engine.
MAX. EX
TENSION
See Sheet
2 of for ex
tension cri
teria.
Ref. Fig.
Outlet Gui
de Vane
(OGV) Inn
er Platfor
m for Cra
cks
D.OGV inner shrou
d
(1)Cracks, cut or to
rn seal at mating wi
th OGV: any amoun
t
25 cycles
or 50 hou
rs
(whicheve
r comes fi
rst)
E.Fan duct panels
(1)One fan duct pa
nel missing is permi
tted, if you make s
ure that the Variabl
e Bleed Valve (VB
V) area is free of u
nwanted object bef
ore the first aircraft
release of the day.
10 cycles
(2)Missing louvers
on panel
50 cycles
with 3 mis
sing louve
rs maxim
um.
F.Splitter fairing
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(1)Cracks: any amo
unt
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
G.Mid acoustical pa
nels
(1)Disbonded damp
er more than 20%
of the total surface.
20 cycles
3.Compressor rotor
A.Compressor rotor
blades
NOTE:
The depth
of a defect
such as a n
ick is meas
ured along
the axis of
the damag
e unless ot
herwise no
ted.
(1)Stages 1-4 radia
l cracks within 0.30
0 in. (7.62 mm) of
the LE and TE more
than 0.250 in. (6.3
5 mm) but less tha
n 0.400 in. (10.16
mm) in length.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(2)Stages 1-4 chor
d-wise cracks more
than 0.200 in. (5.0
8 mm) but less tha
n 0.300 in. (7.62 m
m) in length.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(3)Stages 1-4 nick
s, missing material
and erosion on the
LE and TE found in
Dim. B more than
0.040 in. (1.02 m
m) but less than 0.
080 in. (2.03 mm) i
n depth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(4)Stages 1-4 dent
s on the LE and TE
found in Dim. B mo
re than 0.040 in.
(1.02 mm) but less
than 0.080 in. (2.0
3 mm) in depth, an
d less than 0.060 i
n. (1.52 mm) defle
ction from the origi
nal contour.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(5)Stages 1 nicks,
dents and tears on
the LE and TE in Di
m. A more than 0.2
50 in. (6.35 mm) b
ut less than 0.300 i
n. (7.62 mm) in de
pth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(6)Stages 1-4 missi
ng material and ero
sion at the LE and T
E tip corners more t
han 0.300 in. (7.62
mm) but less than
0.400 in. (10.16 m
m) in depth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(7)Stage 2, more t
han four blades mis
sing material and e
rosion at the LE an
d TE tip corners mo
re than 0.300 in.
(7.62 mm) but less
than 0.400 in. (10.
16 mm) in depth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(8)Stage 3, more t
han five blades mis
sing material and e
rosion at the LE an
d TE tip corners mo
re than 0.300 in.
(7.62 mm) but less
than 0.400 in. (10.
16 mm) in depth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(9)Stage 4, more t
han six blades miss
ing material and er
osion at the LE and
TE tip corners more
than 0.300 in. (7.6
2 mm) but less tha
n 0.400 in. (10.16
mm) in depth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(10)Stages 1-4 nick
s, dents and missin
g material on the L
E and TE of the low
er 25% of the airfoi
l (but not the root r
adius) more than 0.
300 in. (7.62 mm)
but less than 0.080
in. (2.03 mm) in de
pth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(11)Wear and scrat
ches of the TE platf
orm of stage 2 and
stage 3 of more tha
n 0.030 in. (0.76 m
m) but less than 0.
080 in. (2.03 mm) i
n depth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(12)Stages 2-3 TE r
oot radius nicks, de
nts and scratches
more than 0.030 i
n. (0.76 mm) but le
ss than 0.080 in.
(2.03 mm) in dept
h.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(13)Stages 5-9 radi
al cracks that are n
ot more than 0.200
in. (5.08 mm) from
the LE or TE and m
ore than 0.150 in.
(3.81 mm) but less
than 0.200 in. (5.0
8 mm) in length.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(14)Stages 5-9 cho
rd-wise cracks that
are not more than
0.200 in. (5.08 m
m) from the tip and
are more than 0.15
0 in. (3.81 mm) bu
t less than 0.200 i
n. (5.08 mm) in len
gth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(15)Stages 5-9 nick
s, tears, missing m
aterial and erosion
on the LE and TE fo
und in Dim. B that
are more than 0.04
0 in. (1.02 mm) bu
t less than 0.080 i
n. (2.03 mm) in de
pth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(16)Stages 5-9 den
ts on the LE and TE
found in Dim. B tha
t are more than 0.0
40 in. (1.02 mm) b
ut less than 0.080 i
n. (2.03 mm) in de
pth and less than
0.060 in. (1.52 m
m) deflection from
the original contou
r.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(17)Stages 5-9 nick
s, dents and tears o
n the LE and TE fou
nd in Dim. A that ar
e more than 0.150 i
n. (3.81 mm) but t
han less 0.200 in.
(5.08 mm) in dept
h.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(18)Stages 5-9 mis
sing material and e
rosion at the LE an
d TE tip corners if t
he damage is more
than 0.200 in. (5.0
8 mm) but less tha
n 0.300 in. (7.62 m
m) in depth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(19)Stages 5-9 curl
on the end of the ai
rfoil when the blade
chord is more than
50% but less than
75% of the chord
maximum radial len
gth, 0.300 in. (7.62
mm), when it does
not engage the stat
ionary parts during
operation.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(20)Stages 5-9 nick
s, dents and missin
g material edges fo
und in the lower 2
5% of the airfoil (b
ut not the root radi
us) more than 0.03
0 in. (0.76 mm) bu
t less than 0.080 i
n. (2.03 mm) in de
pth.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(21)Two blade lock
s in the same stage
with any number of
cracks if no blade lo
cks are loose on th
at stage.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
(22)One loose blad
e lock in a stage if t
he other blade lock
on the same stage i
s not loose or crack
ed.
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
4.Compressor front
stator
A.Casing cracks: 0.
170 in. (4.32 mm)
maximum length in
skin
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
B.Casing nicks, pit
s, scores or scratch
es, any amount, an
y depth
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
C.Broken actuation
ring connector, one
side only, if connect
or is replaced
5 cycles
D.Vane actuation ri
ng cracks, distortio
n, bends, twists or
distress, provided ri
ng has not separate
d
5 cycles
E.Loose vane asse
mblies with metal-t
o-metal contact on
up to 50% of vanes
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
5.Combustion case
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
A.Forward and aft fl
ange radial cracks i
nward from bolt hol
es
10 cycles
B.Midflange radial c
racks
10 cycles
C.Maximum of ten
broken midflange b
olts with no more t
han four broken bol
ts in any group of 2
0
25 cycles
D.High Pressure Tu
rbine (HPT) shroud
cooling and Compre
ssor Discharge Pres
sure (CDP) pad cra
cks: more than 0.0
60 in. (1.52 mm) fr
om bolt holes
10 cycles
6.Combustion cham
ber
A.Dome assembly
(1)Radial crack in s
pectacle plate
25 hours
Any number up to
2.500 in. (63.50 m
m) in length and no
t connected to each
other.
(2)Circumferential
crack in spectacle p
late
25 hours
Any number up to
3.600 in. (91.44 m
m) in length separa
ted by 4.800 in. (1
21.92 mm).
(3)Connected crack
s in spectacle plate
25 hours
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
Not more than one
radial crack 2.500 i
n. (63.50 mm) long
with one circumfere
ntial crack 3.600 in.
(91.44 mm) long, s
eparated by 4.800 i
n. (121.92 mm).
(4)Missing material
from spectacle plat
e
25 hours
The damage is mor
e than the given li
mits.
(5)Radial crack in d
eflector or sleeve
25 cycles
Any number up to
0.600 in. (15.24 m
m) in length.
(6)Circumferential
cracks in deflector
or sleeve
25 cycles
Any number up to
0.900 in. (22.86 m
m) in length.
(7)Connected crack
s in deflector or sle
eve
25 cycles
Connection of any r
adial and circumfer
ential cracks within
limits of (5) and (6)
above. Limit is exce
eded when third cra
ck connects.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(8)Up to 25 dome c
ooling holes total in
any deflector are e
xposed.
More than 25 expos
ed dome cooling ho
les total in any defl
ector.
100 cycles
(a)Up to 25 dome c
ooling holes total in
any deflector are e
xposed.
Do BSI aft
er each 7
50 cycles.
(b)More than 25 ex
posed dome cooling
holes total in any d
eflector.
Refer to sheets 2 a
nd 3 of the figure: .
Ref. Fig. Cracks an
d Missing Material i
n the Dome Area
25 cycles
continue-i
n-service l
imit
(9)Missing material
from extensions on
sleeve
Any amount up to
0.240 in. (6.10 m
m) maximum dept
h.
50 cycles
(10)Burn through h
oles
25 cycles
3 per dome 1.200 i
n. (30.48 mm) x 1.
200 in. (30.48 mm)
maximum.
(11)Cracks and mis
sing material from t
he secondary swirl
nozzle venturi
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(a)Up to 10 second
ary swirl nozzle ven
turis with total miss
ing material at each
venturi more than
0.100 IN. (2.54 M
M) but not more th
an 0.300 IN. (7.62
MM) in width.
Do BSI aft
er each 7
50 cycles.
(b)Any number of s
econdary swirl nozz
le venturis with tot
al missing material
more than 0.300 I
N. (7.62 MM) in wid
th or more than 10
secondary swirl noz
zle venturis with tot
al missing material
at each venturi mor
e than 0.100 IN.
(2.54 MM) in width.
Refer to the sheets
2 and 3 of the figur
e: .
Ref. Fig. Cracks an
d Missing Material i
n the Dome Area
25 cycles
continue-i
n-service l
imit
B.Inner and outer li
ners
(1)Outer liner axial
cracks
100 cycles
Up to five cracks ac
ross more than one
panel, and a crack
can go across up to
five panels in seque
nce.
(2)Outer liner axial
cracks from outer si
de borescope (for a
ll CFM56-5B engine
s other than CFM56
-5B DAC engines)
25 cycles
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
Up to 5 cracks acro
ss more than one p
anel, and a crack c
an go across up to f
ive panels. At least
one of the cooling ri
bs (3, 4, 5, or 6) do
es not have cracks
that extend throug
h to the outer side.
Rib 1 is not cracked
through.
(3)Outer liner axial
cracks from outer si
de borescope (for C
FM56-5B DAC engi
nes):
25 cycles
(a) The crack does
not connect to a cir
cumferential crack.
(b) The crack goes
across cooling rib
3.
(4)Inner liner axial
cracks
100 cycles
Up to five cracks ac
ross more than one
panel, and a crack
can go across up to
four panels in sequ
ence.
(5)Circumferential
cracks
25 cycles
Any number up to t
hree dilution lands i
n length separated
by three non-crack
ed dilution lands.
(6)Connected crack
s (for all CFM56-5B
engines other than
CFM56-5B DAC eng
ines)
100 cycles
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
Connection of any a
xial and circumfere
ntial cracks up to m
aximum limits of pa
ragraphs (1), (2),
(3), and (4).
(7)Connected crack
s (for CFM56-5B DA
C engines):
25 cycles
(a) The connected c
racks are not more
than the individual
axial and circumfer
ential crack limits a
bove.
(b) A second axial c
rack, connected to t
he pair of connecte
d cracks, is not lon
ger than one panel
in length.
(8)Burn through or
missing material
100 cycles
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
There are not more
than eight areas th
at are not more tha
n two times the dia
meter of a dilution
hole. There are not
more than two area
s that are not more
than three times th
e diameter of a dilu
tion hole. There are
not more than one
area that is not mo
re than four times t
he size of a dilution
hole. There are not
more than three ar
eas in adjacent pan
els that are aligned
axially if they have
a separation of a m
inimum of three dil
ution lands that are
not damaged.
(9)Missing overhan
gs
25 cycles
Per liner: 17 areas
each twice the size
of a dilution hole, p
roviding maximum
axial alignment of d
istress is three adja
cent panels.
(10)Distortion
25 cycles
Any amount within
0.700 in. (17.78 m
m) of original conto
ur.
C.Combustor inner
cowl bolts
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(1)Missing bolt: ma
ximum of three bolt
s are missing with f
our bolts intact bet
ween two missing b
olts. All other bolts
are tight with tack
welds intact.
50 cycles
for next c
heck, the
n repeat B
SI every 4
00 cycles.
(2)Bolt tack weld cr
acked but bolt is no
t loose: if a maxim
um of five tack wel
ds are cracked, no
more than two cons
ecutive, with four t
ack welds intact bet
ween two cracked t
ack welds.
25 cycles
for first ch
eck, 50 cy
cles for se
cond chec
k, repeat
BSI every
100 cycle
s.
(3)Bolt tack weld is
cracked and bolt is
loose: if one or mor
e bolts are loose.
5 cycles
7.Fuel Nozzles
A.Fuel nozzles with
dislodged wear slee
ves or wear sleeves
with 4 interrupted
weld designs
5 cycles
8.HPT nozzle
A.LE missing materi
al, from cracking or
burn-through, up to
0.500 in. (12.70 m
m) X 0.500 in. (12.
70 mm) per vane.
Maximum of 4 vane
s per 90 degree arc
25 cycles
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
B.Concave surfaces
of airfoil missing m
aterial, from cracki
ng or burn-through,
up to 0.750 in. (19.
05 mm) diameter p
er vane
25 cycles
C.Convex side missi
ng panel
25 cycles
provided
HPT blade
s are withi
n limits.
D.Inner and outer p
latforms missing m
aterial, from cracki
ng or burn-through,
up to 0.500 in. (12.
70 mm) diameter p
er segment
25 cycles
E.TE missing materi
al up to 0.750 in.
(19.05 mm) in axial
direction
25 cycles
F.Baffle missing ma
terial, any amount
10 cycles
9.HPT rotor blade
A.TE cracks in area
A less than 0.200 i
n. (5.08 mm) long
10 cycles
B.TE cracks and co
nvex airfoil cracks
within 0.500 in. (1
2.70 mm) of TE (te
n blades maximu
m ) in area B less t
han 0.300 in. (7.62
mm) long
25 cycles
C.Radial tip cracks l
ess than 0.350 in.
(8.89 mm) long
10 cycles
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
D.LE cracks in area
A less than 0.100 i
n. (2.54 mm) long
10 cycles
E.Axial nose or gill
hole cracks in area
B less than 0.050 i
n. (1.27 mm) long
10 cycles
F.Radial nose or gill
hole cracks in area
B less than 0.060 i
n. (1.52 mm) long
10 cycles
G.Radial nose or gil
l hole cracks in are
a C less than 0.030
in. (0.76 mm) long
10 cycles
H.Through wall hole
in area A and area
B
(1)Any number of b
lades if cavity 2 is n
ot exposed on all bl
ades.
25 cycles
J.Through wall hole
in area C less than
0.300 in. (7.62 m
m) in diameter.
50 cycles
10.HPT shroud and
stage 1 Low Pressu
re Turbine (LPT) no
zzle
A.HPT shrouds
(1)Circumferential
cracks that are not
connected and are
more than 1 in. (2
5.40 mm) long.
25 cycles
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(2)Circumferential
cracks more than
0.25 in. (6.35 mm)
long or closer than
0.25 in. (6.35 mm)
from the shroud ed
ge that connect to
axial cracks, unless
the connected crac
ks are within the li
mit for missing mat
erial, then missing
material limit can b
e used.
25 cycles
(3)Burn-through of
shroud rub land on
all HPT shrouds in o
r less than 0.001 i
n.2 (0.645 mm2) <
Area < 0.005 in.2
(3.226 mm2) is per
mitted if the shroud
does not drop into t
he flowpath.
75 cycles
NOTE:
This C-I-S l
imit is for a
reduced int
erval, repe
at inspectio
n.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
(4)Burn-through of
shroud rub land on
all HPT shrouds in o
r less than 0.005 i
n.2 (3.226 mm2) <
Area < 0.015 in.2
(9.677 mm2) is per
mitted if the shroud
does not drop into t
he flowpath.
NOTE:
MAX. EX
TENSION
25 cycles
This C-I-S l
imit is for a
reduced int
erval, repe
at inspectio
n.
(5)Burn-through of
shroud rub land on
all HPT shrouds wh
en Area > 0.015 in.
2 (9.677 mm2) is p
ermitted if the shro
ud does not drop in
to the flowpath.
25 cycles
(6)Material loss on
split-line forward co
rners more than 0.
250 in. (6.35 mm) i
n axial direction an
d 0.080 in. (2.03 m
m) in circumferenti
al direction is permi
tted, if there is no o
ther burn-through
on the shroud.
400 cycles
NOTE:
This C-I-S l
imit is for a
reduced int
erval, repe
at inspectio
n.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
(7)Material loss on
split-line on areas d
ifferent than forwar
d and aft corners is
permitted if area
(A) is above 0.013 i
n.2 (8.387 mm2) O
R distance from ori
ginal contour in circ
umferential directio
n (d) is above 0.08
0 in. (2.03 mm), if
there is no other bu
rn-through on the s
hroud.
NOTE:
400 cycles
This C-I-S l
imit is for a
reduced int
erval, repe
at inspectio
n.
(8)Material loss on
split-line on areas d
ifferent than forwar
d and aft corners is
permitted if area
(A) is above 0.013 i
n.2 (8.387 mm2) A
ND distance from o
riginal contour in ci
rcumferential direct
ion (d) is above 0.0
80 in. (2.03 mm), if
no other burn-throu
gh on the shroud.
NOTE:
MAX. EX
TENSION
200 cycles
This C-I-S l
imit is for a
reduced int
erval, repe
at inspectio
n.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
(9)Material loss on
split-line on areas d
ifferent than forwar
d and aft corners is
permitted if area
(A) is above 0.013 i
n.2 (8.387 mm2) A
ND distance from o
riginal contour in ci
rcumferential direct
ion (d) is above 0.0
80 in. (2.03 mm) A
ND when other bur
n-through with the
area over 0.001 in.
2 (0.645 mm2) is o
n the shroud.
MAX. EX
TENSION
25 cycles
B.Stage 1 LPT nozzl
e
(1)Cracks in all are
as up to 1.400 in.
(35.56 mm) long pr
ovided not more th
an two adjacent airf
oils per segment.
10 cycles
(2)One crack permi
tted on each airfoil,
from LE to TE, if th
ere is no missing m
aterial.
100 cycles
(3)Burns, erosion, c
orrosion and melte
d metal up to 1.000
in.2 (645.16 mm2)
per airfoil and no cr
acks extending fro
m distressed area if
there is no missing
material.
5 cycles
(4)Cracks in outer
and inner platforms
up to 1.000 in. (25.
40 mm).
100 cycles
11.LPT Rotor
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
A.LPT blades (all st
ages) for:
Measurement
s of airfoil indi
cation on LPT
blades (all sta
ges).
(1)Blade pretwist
-
Stage 1: pret
wist gaps suc
h that adjace
nt interlocks d
o not touch. P
ermitted if the
faces of the in
terlocks are n
ot worn.
-
Stages 2-4 ga
ps such that a
djacent interl
ocks do not c
ontact each ot
her.
(2)0.080 in. (2.03
mm) maximum defl
ection over a length
ten times longer m
aximum, only for st
age 1 LPT blades di
storted LEs, due to
overtemperature.
5 cycles
15 cycles
(3)Stages 1, 2, 3 bl
ades
-
Area E:
Any amount o
f impact dama
ge/rubbing pr
ovided there i
s no missing
material or cr
acks.
5 cycles o
r 10 hours
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
-
Other areas:
Any amount o
f impact dama
ge such as be
nding, nicks a
nd/or dents is
allowed provi
ded there is n
o missing mat
erial or cracks
exceeding 5
0% of chord
width.
MAX. EX
TENSION
5 cycles o
r 10 hours
(whicheve
r comes fi
rst)
(4)Stage 4 blades
-
Any amount o
f tip shroud in
terlock wear a
llowed.
25 cycles
or 50 hou
rs
(whicheve
r comes fi
rst)
-
Blades tip shr
oud protrusio
n not to excee
d 0.040 in.
(1.02 mm).
10 cycles
or 25 hou
rs
(whicheve
r comes fi
rst)
-
Area E:
Any amount of imp
act damage such as
nicks and/or dents i
s allowed provided
there is no missing
material or cracks.
-
5 cycles o
r 10 hours
(whicheve
r comes fi
rst)
Other areas:
Any amount of imp
act damage. One c
omplete airfoil and
any number of tip s
hrouds with associa
ted airfoil tips may
be missing provide
d engine vibration i
s not excessive.
5 cycles o
r 10 hours
(whicheve
r comes fi
rst)
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
-
Blade tip shro
uds shingled
or unlatched
provided rotor
turns freely a
nd engine vibr
ation is not ex
cessive.
MAX. EX
TENSION
5 cycles o
r 10 hours
in shingle
d conditio
n.
(whicheve
r comes fi
rst)
B.Nozzle segments
2 to 4
(1)Three cracks ma
ximum for each noz
zle segment if crack
s are more than 0.5
00 in. (12.70 mm)
(1/3 of the chord wi
dth) and less than
1.000 in. (25.40 m
m) (2/3 of the chor
d width) if the adja
cent nozzle segmen
ts have no more th
an two cracks more
than 0.500 in. (12.
70 mm) (1/3 of the
chord width) and le
ss than 1.000 in. (2
5.40 mm) (2/3 of t
he chord width).
200 cycles
(2)One crack maxi
mum for each nozzl
e segment that is
more than 1.000 i
n. (25.40 mm) (2/3
of the chord width)
including open airfo
il.
200 cycles
(3)One full chord cr
ack on two airfoils f
or each segment if
the adjacent nozzle
segments have no
more than one airfo
il with a full chord c
rack.
25 cycles
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(4)Nicks, dents, tea
rs, missing pieces u
p to 2.000 in.2 (12
90.32 mm2) on no
nadjacent vanes pr
ovided there are no
cracks extending fr
om distressed area
s.
10 cycles
(5)Burned areas wit
h missing material
or melted.
25 cycles
C.Stage 4 shroud a
bradable material
(1)Worn, jagged or
crushed sealing sur
face exceeding 5
0% of the honeyco
mb height provided
sectors of the shrou
d abradable materi
al are not missing.
10 cycles
12.LPT Casing
A.Forward and aft fl
anges
(1)One crack conne
cting two bolt holes
without penetrating
pressure vessel out
er skin
10 cycles
(2)One crack into s
kin 0.400 in. (10.1
6 mm) long maxim
um
10 cycles
B.External surface
of the casing
(1)One crack 0.400
in. (10.16 mm) lon
g maximum
10 cycles
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
C.Cooling air tube a
nd manifold assem
blies
MAX. EX
TENSION
10 cycles
(1)One separated ci
rcumferential tube
(2)3.000 in. (76.20
mm) cumulative co
oling air manifold cr
ack
(3)One separated c
ooling air tube supp
ort
D.Thread ports and
bosses
(1)One crack, 0.50
0 in. (12.70 mm) m
aximum providing t
here is no leakage.
10 cycles
13.Turbine frame
A.Forward and aft fl
anges
10 cycles
(1)One circumferen
tial crack connectin
g two bolt holes
(2)One crack into s
kin 0.500 in. (12.7
0 mm) maximum
B.Engine mounting
lug areas airframe
attach points only
10 cycles
(1)One crack out of
one mount lug bolt
hole 0.250 in. (6.35
mm) maximum
(2)Skin crack 0.250
in. (6.35 mm) maxi
mum
C.Threaded parts a
nd bosses
10 cycles
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
(1)One crack, 0.50
0 in. (12.70 mm) lo
ng providing there i
s no fluid or air leak
age
D.Stud on the aft fa
ce of the inner hub
(1)Missing/broken/l
oose stud(s):
-
One or two st
uds
-
Three studs
500 hours
or 500 cyc
les
(whicheve
r comes fi
rst)
*If not adjacent to
each other
500 hours
or 500 cyc
les
(whicheve
r comes fi
rst)
*If two non-service
able studs are adja
cent, but the third
one is separated fro
m them by two ser
viceable studs
500 hours
or 500 cyc
les
(whicheve
r comes fi
rst)
*If not
Replace st
uds
-
Four studs or
more
Replace st
uds
E.Thermal insulatio
n blankets
100 cycles
(1)Missing or protr
uding blankets
F.Other areas
10 cycles
(1)One crack 0.250
in. (6.35 mm) maxi
mum
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
CONDITION
MAX. EX
TENSION
14.Accessory gearb
ox
A.Two opposite key
lock studs missing,
provided there is n
o leakage at flange
3 cycles o
r 30 hours
(whicheve
r comes fi
rst)
B.Oil leakage from
AGB/Starter carbon
seal Ref. AMM TAS
K 79-00-00-210-00
3.
10 cycles
provided s
eal drain li
ne is disco
nnected a
nd drain c
avity is ca
pped.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-30800-06-A (SHEET 1) - Booster Rotor and Stator Damage Extended
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-30900-06-A (SHEET 1/2) - Extended Vanes Damage Limits
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-30900-06-A (SHEET 2/2) - Extended Vanes Damage Limits
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
LTM - A318 / A319 / A320 / A321 - AMM - 01-Feb-2023 - 72-00-00-200-025-A - ... Page 62 of 71
CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-32100-06-A (SHEET 1/3) - Inspection/Check of the Fan Outlet Guide
Vanes (OGV)
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
LTM - A318 / A319 / A320 / A321 - AMM - 01-Feb-2023 - 72-00-00-200-025-A - ... Page 63 of 71
CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-32100-06-A (SHEET 2/3) - Inspection/Check of the Fan Outlet Guide
Vanes (OGV)
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
LTM - A318 / A319 / A320 / A321 - AMM - 01-Feb-2023 - 72-00-00-200-025-A - ... Page 64 of 71
CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-32100-06-A (SHEET 3/3) - Inspection/Check of the Fan Outlet Guide
Vanes (OGV)
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
LTM - A318 / A319 / A320 / A321 - AMM - 01-Feb-2023 - 72-00-00-200-025-A - ... Page 65 of 71
CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-58600-06-A (SHEET 1/2) - Outlet Guide Vane (OGV) Inner Platform
for Missing Material
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
LTM - A318 / A319 / A320 / A321 - AMM - 01-Feb-2023 - 72-00-00-200-025-A - ... Page 66 of 71
CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-58600-06-A (SHEET 2/2) - Outlet Guide Vane (OGV) Inner Platform
for Missing Material
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
LTM - A318 / A319 / A320 / A321 - AMM - 01-Feb-2023 - 72-00-00-200-025-A - ... Page 67 of 71
CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-58700-06-A (SHEET 1) - Measurements of Airfoil Indication on Low
Pressure Turbine Blades (all stages)
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
LTM - A318 / A319 / A320 / A321 - AMM - 01-Feb-2023 - 72-00-00-200-025-A - ... Page 68 of 71
CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-58500-06-A (SHEET 1) - Outlet Guide Vane (OGV) Inner Platform for
Cracks
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
LTM - A318 / A319 / A320 / A321 - AMM - 01-Feb-2023 - 72-00-00-200-025-A - ... Page 69 of 71
CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-32700-06-A (SHEET 1/3) - Cracks and Missing Material in the Dome
Area
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
LTM - A318 / A319 / A320 / A321 - AMM - 01-Feb-2023 - 72-00-00-200-025-A - ... Page 70 of 71
CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-32700-06-A (SHEET 2/3) - Cracks and Missing Material in the Dome
Area
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023
LTM - A318 / A319 / A320 / A321 - AMM - 01-Feb-2023 - 72-00-00-200-025-A - ... Page 71 of 71
CUSTOMIZATION
LTM
AIRCRAFT
REVISION
DOCTYPES
TYPES
DATE
A318 A319 A321
AMM
01-Feb-2023
A320
REVISION
NUMBER
TITLE
36
72-00-00-200-025-A - OverServiceable-Limit Extensions
TAIL NUMBER - MSN - FSN:
Print date: 2023-05-02 09:32:12
Figure 72-00-00-991-32700-06-A (SHEET 3/3) - Cracks and Missing Material in the Dome
Area
** ON A/C FSN 154-200, 246-300, 351-352, 356-356, 358-372, 378-425, 427-428, 430-433,
435-450, 501-501, 503-504, 506-506, 508-508, 510-512, 517-525, 527-527, 529-529, 531536, 540-550, 561-567, 571-571, 582-600
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
https://w3.airbus.com/1T40/document/595967_SGML_C/toc?itemId=595967_SGML... 02/05/2023