AIRCRAFT REVISION REVISION

CUSTOMIZATION DOCTYPES TITLE

TYPES DATE NUMBER
A318 A319 01-Nov- 72-56-00-210-002-A - Inspection/Check of
LAO AMM 30
A321 A320 2023 the Turbine Frame Assembly
TAIL NUMBER - MSN - FSN: RDPL-34188 - 04596 - 001
Print date: 2024-02-19 13:16:07
sonnyraymundo@laoairlines.com

** ON A/C FSN ALL

TASK 72-56-00-210-002-A
Inspection/Check of the Turbine Frame Assembly
FIN: 1000EM1 1000EM2
1. Reason for the Job
Self explanatory

2. Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

QT
REFERENCE DESIGNATION
Y
No specific AR ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE
No specific AR WARNING NOTICE(S)

B. Work Zones and Access Panels

ZONE/ACCESS ZONE DESCRIPTION

210 CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD
400 POWER PLANT, NACELLES AND PYLONS
FOR 1000EM1(ENGINE-1)
437AL, 438AR, 451AL, 452
AR
FOR 1000EM2(ENGINE-2)
447AL, 448AR, 461AL, 462
AR

C. Referenced Information
 REFERENCE DESIGNATION
Ref. 71-13-00-010-040-B Opening of the Fan Cowl Doors
Ref. 71-13-00-410-040-B Closing of the Fan Cowl Doors
Ref. 72-00-00-200-025-A Over-Serviceable-Limit Extensions
Ref. 72-00-00-200-025-A0 Over-Serviceable-Limit Extensions
1
Ref. 72-56-00-000-001-A Removal of the Flame Arrestor and Flange Assembly
Ref. 72-56-00-300-003-A Replacement of Defective Studs
Ref. 72-56-00-300-006-A Replacement of the Oil Supply Tube Assembly
Ref. 72-56-00-400-001-A Installation of the Flame Arrestor and Flange Assembly
Ref. 78-11-11-000-041-A Removal of the Core Nozzle Assembly
Ref. 78-11-11-400-041-A Installation of the Core Nozzle Assembly
Ref. 78-11-12-000-041-A Removal of the Centerbody
Ref. 78-11-12-400-041-A Installation of the Centerbody
Ref. 78-30-00-081-041-B Make the Thrust Reverser Serviceable after Maintenance
Ref. 78-30-00-481-041-B Make the Thrust Reverser Unserviceable for Maintenance
Ref. 78-36-00-010-040-B Opening of the Thrust Reverser Doors
Ref. 78-36-00-410-040-B Closing of the Thrust Reverser Doors
Ref. Fig. Turbine Frame Struts
Ref. Fig. Turbine Frame Section
Ref. Fig. No. 5 Bearing Support

3. Job Set-up

SUBTASK 72-56-00-860-054-A
A. Aircraft Maintenance Configuration
(1) Make sure that the core nozzle is removed Ref. AMM TASK 78-11-11-000-041.
(2) Make sure that the centerbody is removed Ref. AMM TASK 78-11-12-000-041.

SUBTASK 72-56-00-941-051-A
B. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:

(a) Put a WARNING NOTICE(S) in position to tell persons not to start the engi
ne.
(2) Make sure that the engine shutdown occurred five minutes or more before you do
this procedure.
(3) On the overhead maintenance panel 50VU:

(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutt
on switch is off.

(b) Put a WARNING NOTICE(S) in position to tell persons not to energize the F
ADEC 1(2).

SUBTASK 72-56-00-010-053-A
C. Get Access
(1) Open the fan cowl doors Ref. AMM TASK 71-13-00-010-040:
 (2) FOR 1000EM1 (ENGINE-1)
437AL, 438AR
(3) FOR 1000EM2 (ENGINE-2)
447AL, 448AR
(4) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position.

SUBTASK 72-56-00-040-051-A
D. Make the thrust reverser unserviceable Ref. AMM TASK 78-30-00-481-041.

SUBTASK 72-56-00-010-054-A
E. Open the thrust reverser doors Ref. AMM TASK 78-36-00-010-040:
(1) FOR 1000EM1 (ENGINE-1)
451AL, 452AR
(2) FOR 1000EM2 (ENGINE-2)
461AL, 462AR

4. Procedure
Ref. Fig. Turbine Frame Struts
Ref. Fig. Turbine Frame Section
Ref. Fig. No. 5 Bearing Support
SUBTASK 72-56-00-210-051-A
A. Visual inspection of the Turbine Frame Assembly:

MAXIMUM SERVICEABLE
INSPECT/CHECK REMARKS
LIMITS
1.Forward and aft outer fla
nges for:
- Cracks connecting b Not serviceable
olt holes
- Cracks extending fro One crack, 0.20 in. (5.1 m
m bolt holes to outer m) max. per hole with a mi
edge of flange nimum 5-hole separation b
etween cracks
- Cracks extending fro Five cracks, 0.20 in. (5.1 m
m bolt holes toward m) max. per flange with a
casing skin minimum 10-hole separatio
n between cracks. Axial cra
cks only
- Cracks in other area Five cracks per flange, 0.20
s of flange in. (5.1 mm) long with a mi
nimum 5 in. (127 mm) sep
aration between any other
cracks
- Nicks, scores and scr Five per flange, 1 in. (25.4
atches mm) long, 0.01 in. (0.25 m
m) deep, after removal of h
igh metal with a minimum
1 in. (25.4 mm) separation
2.Engine mounting lug are
as, airframe attach points
only for:
- Cracks out of bolt ho Not serviceable
les
- Cracks in welds or in Not serviceable
other areas of engin
e mounting lug area

- Nicks, scores and scr Any number, 1 in. (25.4 m

atches m) long, 0.02 in. (0.5 mm)
deep after removal of high
metal with a minimum 1 in.
(25.4 mm) separation
3.All other areas of outer c
asing skin for:
- Cracks Not serviceable
- Nicks, scores and scr Any number, 1 in. (25.4mm
atches ) long, 0.03 in. (0.76 mm)
deep after removal of high
metal and 1 in. (25.4 mm)
minimum apart
4.Oil supply and scavenge
tubes for:
- Cracks Not serviceable Replace the oil supply tube R
ef. AMM TASK 72-56-00-300-
006.
- Nicks, scratches Any number, 0.01 in. (0.25 Replace the oil supply tube R
mm) deep after removal of ef. AMM TASK 72-56-00-300-
high metal 006.
- Dents Two per tube, smooth cont Replace the oil supply tube R
our, 0.05 in. (1.27 mm) de ef. AMM TASK 72-56-00-300-
ep 006.
- Oil marks Any amount
5.Struts for:
- Cracks Not serviceable
- Nicks, scores and scr Any number, any length, 0.
atches 02 in. (0.51 mm) deep afte
r removal of high metal
- Dents Any number, smooth conto
ur, 0.02 in. (0.51 mm) dee
p
- Broken stud or dama Three (3) maximum: Replace the stud Ref. AMM T
ged threads - If not adjacent to eac ASK 72-56-00-300-003 withi
h other: 500 hours/5 n 500 hours/500 cycles.
00 cycles
- If two (2) non-service
able studs are adjace
nt, but the third one i
s separated from the
m by two (2) servicea
ble studs: 500 hours/
500 cycles
6.No. 7 and No. 10 struts
(oil supply and scavenge t
ubes) bulkheads for:
- Cracks in the bulkhe Two cracks, any length on
 ad wall each bulkhead
- Cracks from the bulk Not serviceable
head, extending in t
he outer hub skin
7.Sump flooding boss area
for:
- Cracks in the hub Two cracks, no longer than
1 in. (25.4 mm) and 1 in. (
25.4 mm) apart, minimum
Flame arrestor for:
- Cracks in all areas in Any number
cluding the retaining
metal strip
- Missing retaining stri Serviceable, if one strip re
ps mains
- Honeycomb grid plu Any area up to 50 percent
g for clogging of clogging
- Honeycomb missing Not serviceable Replace the flame arrestor wi
thin the next 10 cycles Ref. A
MM TASK 72-56-00-000-001
Ref. AMM TASK 72-56-00-40
0-001.
8.Thermal insulation blank Not serviceable Install a new blanket. See ov
ets erserviceable limit extension
- Missing or protuding Ref. AMM TASK 72-00-00-20
blanket in the flowpa 0-025.
th
9.Guide bushing for the oil
supply tube for:
- Worn area No more than 0.06 in. (1.5
2 mm)
- Flush with the LPT b Not serviceable 600 cycles or 750 hours max
ore . serviceable extension is allo
wed with less than 0.06 in. (
1.52 mm). 25 cycles or 50 h
ours max. serviceable extens
ion is allowed with more than
0.06 in. (1.52 mm).
10.The drain nipple for:
- Cracks on the weld b Not serviceable
ead
- Deterioration of thre Less than a quarter of thre
ads ads after removal of burrs
- Circular scratches, ar Any number 0.005 in. (0,1
eas X and Z 3 mm) deep after removal
of high metal
- Circular scratches, ar Any amount, that cannot b
ea Y e felt with a 0.040 in. (1,0
mm) scriber
- Axial scratches, area Any number 0.03 in. (0,8
 s X and Z mm) deep after removal of
high metal

- Axial scratches, area Not serviceable

Y
- Nicks in area Z Any number 0.03 in. (0,8
mm) deep after removal of
high metal
- Nicks in areas X and Not serviceable
Y
11.The flange assembly fo
r:
- Cracks at hole locati Any amount of cracks if no A maximum service extensio
ons on the intermedi missing material (not inclu n of 10 cycles or 25 hours is
ate flange ding stop drill), and no crac permitted for crack with miss
ks between bolt holes, are ing material or cracks betwee
permitted n two bolt holes.
- Dent Any amount if the ratio of t
he depth of the dent over t
he minimal length of the de
nt is 10% or less
- Missing or broken int Two bolts: A maximum service extensio
ermediate flange bol - Two missing bolts or n of 25 cycles or 60 hours is
ts - Two broken bolts or permitted.
- One missing bolt and If the service extension limit
one broken bolt is expired, replace missing or
broken bolts Ref. AMM TASK
72-56-00-400-001.
If more than two bolts, there
is no service extension availa
ble.
12.The No. 5 bearing supp
ort for:
- Cracks in area U Serviceable
13.The oil inlet cover for:
- Rub marks from the All quantities are permitted All quantities are permitted if
seal teeth if the average is 0.010 in. ( the average is 0.010 in. (0.2
0.25 mm) in depth over th 5 mm) in depth over the full
e full circumference circumference.

5. Close-up

SUBTASK 72-56-00-410-053-A
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the centerbody Ref. AMM TASK 78-11-12-400-041.
(3) Install the core nozzle Ref. AMM TASK 78-11-11-400-041.
(4) Close the thrust reverser doors Ref. AMM TASK 78-36-00-410-040:

(a) FOR 1000EM1 (ENGINE-1)

451AL, 452AR

(b) FOR 1000EM2 (ENGINE-2)

 461AL, 462AR

SUBTASK 72-56-00-440-051-A
B. Make the thrust reverser serviceable Ref. AMM TASK 78-30-00-081-041.

SUBTASK 72-56-00-410-054-A
C. Close Access
(1) Close the fan cowl doors Ref. AMM TASK 71-13-00-410-040:
(2) FOR 1000EM1 (ENGINE-1)
437AL, 438AR
(3) FOR 1000EM2 (ENGINE-2)
447AL, 448AR
(4) Remove the access platform(s).
(5) Remove the WARNING NOTICE(S).
 A

CLEVIS
MOUNT

A CLEVIS
MOUNT

FERRULE
FERRULE 16 1

15 2

14 3

13 4

INNER
HUB 12 5

11 6

OUTER
HUB 10 7

9 8
H

F
OIL SUPPLY H SCAVENGE
S-M56-MM-04229-01

TUBE TUBE
DRAIN
NIPPLE

04 PRE-SB 72-176
ENGINE AFT
CLEVIS MOUNTS
N_MM_725600_6_RAA0_01_01

Figure 72-56-00-991-30500-06-A (SHEET 1/6) - Turbine Frame Struts

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 A

CLEVIS
MOUNT

A CLEVIS
MOUNT
D

FERRULE
FERRULE 16 1

15 2

14 3

13 4

INNER
HUB 12 5

OUTER 11 6
HUB

10 7
E
9 8
H

G
OIL SUPPLY H SCAVENGE
S-M56-MM-04230-01

TUBE DRAIN TUBE

NIPPLE

02 POST-SB 72-176
ENGINE AFT
CLEVIS MOUNTS
N_MM_725600_6_RAA0_02_01

Figure 72-56-00-991-30500-06-A (SHEET 2/6) - Turbine Frame Struts

** ON A/C FSN ALL
 C

ENGINE MOUNTS

OUTER CASE

STRUT

STUD
S-M56-MM-04231-01

N_MM_725600_6_RAA0_03_01

Figure 72-56-00-991-30500-06-A (SHEET 3/6) - Turbine Frame Struts

** ON A/C FSN ALL
 D

ENGINE MOUNTS

OUTER CASE

STRUT

STUD

E
STRUT

51 mm
(2.008 in)

51 mm
S-M56-MM-04232-01

(2.008 in)
AREA TO BE
INSPECTED

N_MM_725600_6_RAA0_04_01

Figure 72-56-00-991-30500-06-A (SHEET 4/6) - Turbine Frame Struts

** ON A/C FSN ALL
 F

OUTER HUB SKIN

STRUT

BULKHEAD

LPT FRAME
GUIDE
BUSHING

OIL SUPPLY
TUBE

OUTER HUB SKIN

STRUT

BULKHEAD
LPT FRAME
GUIDE
BUSHING

OIL SUPPLY
S-M56-MM-04235-01

TUBE

N_MM_725600_6_RAA0_05_01

Figure 72-56-00-991-30500-06-A (SHEET 5/6) - Turbine Frame Struts

** ON A/C FSN ALL
 SECTION
H-H

NIPPLE

B
WELD SPOT

DETAIL B
TANGENT AREA X
POINT AREA Y
AREA Z

0.03 (0.8)
1/3
2/3
S-M56-MM-04970-01

N_MM_725600_6_RAA0_06_00

Figure 72-56-00-991-30500-06-A (SHEET 6/6) - Turbine Frame Struts

** ON A/C FSN ALL
 SECTION
A-A
OUTER
CASING

TANGENTIAL
SYMETRICAL
SECTION
A STRUT

A
EXHAUST PLUG
ATTACHMENT
STUD

INTERMEDIATE
FLANGE
BOLT

FLANGE
ASSEMBLY

FLAME
ARRESTOR

OIL SUPPLY
TUBE
(FROM STRUT No.10
AT 7:00 O'CLOCK)
OIL SCAVENGE
TUBE
(TO STRUT No. 7)

OVER BOARD SEAL

DRAIN TUBE
(AT 6:00 O'CLOCK)
S-M56-MM-04300-01

STRUT No.7
(AT 5:00 O'CLOCK)

N_MM_725600_6_UBM0_01_00

Figure 72-56-00-991-33500-06-A (SHEET 1) - Turbine Frame Section

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 SECTION
A-A

CRACKS IN
AREA U

A
A
CRACKS IN
AREA U

A
S-M56-MM-05320-01

N_MM_725600_6_UCM0_01_00

Figure 72-56-00-991-33600-06-A (SHEET 1) - No. 5 Bearing Support

** ON A/C FSN ALL
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.