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Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 1 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
** ON A/C 051-100, 201-250, 351-400, 601-650
TASK 72-00-00-200-013-A
Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes
CAUTION: THE LIMITS WHICH FOLLOW ARE APPLICABLE ON A CONTINUE IN SERVICE BASIS ONLY.
EACH LIMIT IS BASED ON WHAT THE STRUCTURE OF THE BLADE MUST BE AND DOES
NOT INDICATE THAT THERE WILL NOT BE DETERIORATION OF THE ENGINE PERFORM-
ANCE, STABILITY, OPERATING LIMITS OR PART REPAIRABILITY.
FIN : 1000EM1 , 1000EM2
1. Reason for the Job
Refer to the MPD TASK: 724000-I1
BORESCOPE INSPECTION OF INSIDE OF COMBUSTION CHAMBER AND HP TURBINE STAGE 1 VANES
This task gives the procedure for the borescope inspection of the combustion chamber and the HPT first stage
vanes.
2 Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specific AR BORESCOPE - FLEXIBLE
No specific AR BORESCOPE - RIGHT ANGLE, FLEXSCOPE
No specific AR COVER - EYE
No specific AR WARNING NOTICE(S)
No specific Torque wrench: range to between 70 and 80 lbf.in
(0.79 and 0.90 m.daN)
B. Consumable Materials
REFERENCE DESIGNATION
(Material No. V02-141) corrosion resistant steel lockwire
(Material No. V10-094) anti-seize compound
(Material No. V10-129) anti-seize paste
C. Work Zones and Access Panels
ZONE/ACCESS ZONE DESCRIPTION
FOR 1000EM1 (ENGINE-1)
437AL, 438AR,
451AL, 452AR
FOR 1000EM2 (ENGINE-2)
447AL, 448AR,
461AL, 462AR
D. Expendable Parts
FIG.ITEM DESIGNATION IPC-CSN
1 gasket 72-42-10-81-010
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 2 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
E. Referenced Information
REFERENCE DESIGNATION
(Ref. 70-23-11-911-013-A). General Torque Tightening Techniques
(Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
(Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
(Ref. 72-00-00-200-014-A). Borescope Inspection of the Stage 1 High Pressure Turbine (HPT)
Blades and Duct Segments
(Ref. 74-21-41-000-010-A). Removal of the Igniter Plug
(Ref. 74-21-41-400-010-A). Installation of the Igniter Plug
(Ref. 78-30-00-040-012-A). Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for
Ground Maintenance
(Ref. 78-32-00-010-010-A). Opening of the Thrust Reverser Halves
(Ref. 78-32-00-410-010-A). Closing of the Thrust Reverser Halves
Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Left Side)
(PRE SBE 72-0221) SHEET 1
Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Right Side)
(PRE SBE 72-0221) SHEET 1
Borescope Inspection Ports for the First Stage Vanes and the Combustion Chamber Liner (PRE SBE 72-
0221) SHEET 1
Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (Left Side)
(POST SBE 72-0221) SHEET 1
Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (Right Side)
(POST SBE 72-0221) SHEET 1
Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (POST SBE
72-0221) SHEET 1
HPT 1st Stage Vane Area Names and Dimensional References
HPT 1ST Stage Vane Area Names and Dimensional References SHEET 1
HPT 1st Stage Vane Area Names and Dimensional References
HPT 1st Stage vane Area Names and Dimensional References
HPT 1st Stage Vane Area Names and Types of Damage
HPT 1st Stage Vane Area Names and Types of Damage
Combustion Chamber Area Names SHEET 1
Inner Combustion Chamber Liner Dimensions References SHEET 1
Outer Combustion Chamber Liner Segments Dimensions References SHEET 1
Combustion Chamber Liner Segments Borescope Inspection Guidelines SHEET 1
Borescope Ports (PRE SBE 72-0221) SHEET 1
Borescope Ports (POST SBE 72-0221) SHEET 1
Combustion Chamber Damage Form SHEET 1
Combustion Chamber Damage Form SHEET 1
Combustion Chamber Damage Form SHEET 1
Combustion Chamber Damage Form SHEET 1
Combustion Chamber Damage Form SHEET 1
Combustion Chamber Damage Form SHEET 1
Combustion Chamber Damage Form SHEET 1
Combustion Chamber Damage Form SHEET 1
Combustion Chamber Damage Form SHEET 1
Combustion Chamber Damage Form SHEET 1
Combustion Chamber Damage Form SHEET 1
Combustion Chamber Liner Segment Crack Limits SHEET 1
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 3 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
REFERENCE DESIGNATION
Combustion Chamber Liner Segment Burn Limits SHEET 1
Combustion Chamber Liner Segment Attachment Post Visibility SHEET 1
Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1
Combustion Chamber Bulkhead Segment Burn Hole SHEET 1
Combustion Chamber Bulkhead Segment Attachment Post Visibility SHEET 1
Combustion Chamber Bulkhead Deflector Cracks and Burnback SHEET 1
Bulkhead Deflector Burnback
Fuel Nozzle End Cap Inspection Areas SHEET 1
Fuel Nozzle End Cap Inspection Areas SHEET 1
Fuel Nozzle Types of Damage SHEET 1
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 4 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
11629B
B4
B3
B2
B1
A
A
N_MM_720000_6_XRM0_01_00
Figure 72(IAE)-00-00-991-16200-13-A / SHEET 1/1 - Borescope Ports for Inspection of the
Combustion Chamber Liners and the First Stage Vanes (Left Side) (PRE SBE 72-0221)
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 5 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
11630C
B5
IP1
IP2
A
A
N_MM_720000_6_XTM0_01_00
Figure 72(IAE)-00-00-991-16300-13-A / SHEET 1/1 - Borescope Ports for Inspection of the
Combustion Chamber Liners and the First Stage Vanes (Right Side) (PRE SBE 72-0221)
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 6 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
IP1
IP2
B4
B3
B2
B1
B5
TDC
COMBUSTION
CHAMBER PORTS
VIEV WHEN YOU LOOK
FROM THE REAR OF THE ENGINE
IGNITER
POINTS
11632D
N_MM_720000_6_XVM0_01_00
Figure 72(IAE)-00-00-991-16400-13-A / SHEET 1/1 - Borescope Inspection Ports
for the First Stage Vanes and the Combustion Chamber Liner (PRE SBE 72-0221)
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 7 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
B8617
B5
B4
B3
B2
B1
A
A
N_MM_720000_6_YBM0_01_00
Figure 72(IAE)-00-00-991-25700-13-A / SHEET 1/1 - Borescope Ports for Inspection of
the Combustion Chamber Liners and the Stage 1 Vanes (Left Side) (POST SBE 72-0221)
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 8 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
B6
IP1
IP2
B8618
A
A
N_MM_720000_6_YDM0_01_00
Figure 72(IAE)-00-00-991-25800-13-A / SHEET 1/1 - Borescope Ports for Inspection of the
Combustion Chamber Liners and the Stage 1 Vanes (Right Side) (POST SBE 72-0221)
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 9 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
IP1
IP2
B5
B4
B3
B1
B6
TDC
COMBUSTION
CHAMBER PORTS
VIEW WHEN YOU LOOK
FROM THE REAR OF THE ENGINE
IGNITER
PORTS
B8634
B2
N_MM_720000_6_YHM0_01_00
Figure 72(IAE)-00-00-991-25900-13-A / SHEET 1/1 - Borescope Ports for Inspection
of the Combustion Chamber Liners and the Stage 1 Vanes (POST SBE 72-0221)
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 10 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
AIR HOLES
AIRFOIL COOLING
LEADING EDGE
OUTER PLATFORM
(2,540 mm)
0.100 in.
INNER PLATFORM
TRAILING EDGE
TRAILING
EDGE SLOT
LEADING
EDGE
COOLING
AIR
HOLES
PLATFORM
(46,99 mm)
1.850 in.
0.150 in.
COOLING
AIR
HOLES
PLATFORM
1/4 CHORD
1/2 CHORD
3/4 CHORD
2.100 in.
(53,34 mm)
FULL CHORD 1.700 in.
(43,18 mm)
INNER PLATFORM
LEADING EDGE
PWZXX11640E
CONCAVE AIRFOIL VIEW
(3,81 mm)
N_MM_720000_6_XZM0_01_00
Figure 72(IAE)-00-00-991-16600-13-A / SHEET 1/2 - HPT
1st Stage Vane Area Names and Dimensional References
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 11 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
AXIAL
RADIAL
CONCAVE AIRFOIL VIEW
pwzxxb8894a
SBE 72-0340
INNER PLATFORM
LEADING EDGE
LEADING EDGE
PLATFORM COOLING
AIR HOLES
PLATFORM COOLING
AIR HOLES
OUTER PLATFORM
LEADING EDGE
TRAILING EDGE
INNER PLATFORM
TRAILING
EDGE
1/2 CHORD
1/4 CHORD
3/4 CHORD
AIRFOIL COOLING
AIR HOLES
0.100in.
(2.540mm)
2.100in.
(53.34mm)
FULL CHORD
0.200in.
(5.080mm)
1.700in.
(43.18mm)
N_MM_720000_6_XZM0_02_00
Figure 72(IAE)-00-00-991-16600-13-A / SHEET 2/2 - HPT
1st Stage Vane Area Names and Dimensional References
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 12 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
0.200in (5,08mm)
CONVEX AIRFOIL VIEW
TRAILING EDGE
TRAILING EDGE
OUTER PLATFORM
INNER PLATFORM
TRAILING EDGE
11641D
1.200in
(30,48mm)
AIR HOLES
AIRFOIL COOLING
LEADING EDGE
N_MM_720000_6_YAM0_01_00
Figure 72(IAE)-00-00-991-16700-13-A / SHEET 1/1 - HPT
1ST Stage Vane Area Names and Dimensional References
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 13 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
LEADING EDGE
OUTER PLATFORM
LEADING
EDGE
INNER PLATFORM
LEADING EDGE
JUNCTION OF
AIRFOIL TO PLATFORM
FILLET RADIUS AREA
AXIAL
RADIAL
CONCAVE AIRFOIL VIEW SEEN THROUGH THE BORESCOPE
11907D
TRAILING
EDGE
SLOT WIDTH
0.080 in
(2.03 mm)
N_MM_720000_6_YCM0_01_00
Figure 72(IAE)-00-00-991-16800-13-A / SHEET 1/2 - HPT
1st Stage Vane Area Names and Dimensional References
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 14 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
SBE 72-0340
AXIAL
RADIAL
B8902
CONCAVE AIRFOIL VIEW SEEN THROUGH THE BORESCOPE
LEADING EDGE
OUTER PLATFORM
LEADING EDGE
INNER PLATFORM
LEADING EDGE
TRAILING EDGE
JUNCTION OF AIRFOIL
TO PLATFORM FILLET
RADIUS AREA
0.080in.
(2.03mm)
SLOT WIDTH
N_MM_720000_6_YCM0_02_00
Figure 72(IAE)-00-00-991-16800-13-A / SHEET 2/2 - HPT
1st Stage Vane Area Names and Dimensional References
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 15 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
LEADING
EDGE
RADIAL
WITH MISSING METAL
LEADING EDGE
HOLE PATTERN AREA
BURN WITH
TRAILING
MISSING METAL
EDGE
INNER PLATFORM
LEADING EDGE
AXIAL
LEADING EDGE
OUTER PLATFORM
11908B
CONCAVE AIRFOIL VIEW AS SEEN THROUGH THE BORESCOPE
BURN HOLE
N_MM_720000_6_YEM0_01_00
Figure 72(IAE)-00-00-991-16900-13-A / SHEET 1/2 - HPT
1st Stage vane Area Names and Dimensional References
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 16 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
SBE 72-0340
AXIAL
RADIAL
B8903
CONCAVE AIRFOIL VIEW SEEN THROUGH THE BORESCOPE
LEADING EDGE
TRAILING EDGE
INNER PLATFORM
LEADING EDGE
MISSING
METAL
AXIAL CRACK
WITH BURN
OUTER PLATFORM
LEADING EDGE
AXIAL
CRACK
CONCAVE
SURFACE
AREA
N_MM_720000_6_YEM0_02_00
Figure 72(IAE)-00-00-991-16900-13-A / SHEET 2/2 - HPT
1st Stage vane Area Names and Dimensional References
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 17 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
CONCAVE SURFACE
AREA
LEADING
EDGE
LEADING EDGE
OUTER PLATFORM
AXIAL CRACK
TRAILING
EDGE
BURN WITH
MISSING
MATERIAL
TRAILING EDGE
INNER PLATFORM
MISSING
METAL
INNER PLATFORM
LEADING EDGE
AXIAL CRACK
WITH BURN
AXIAL
RADIAL
PWZXX11909C
CONCAVE AIRFOIL VIEW AS SEEN THROUGH THE BORESCOPE
N_MM_720000_6_YGM0_01_00
Figure 72(IAE)-00-00-991-17000-13-A / SHEET 1/3 -
HPT 1st Stage Vane Area Names and Types of Damage
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 18 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
TRAILING EDGE
BURNS
LEADING EDGE
BURNS
BAFFLE
TRAILING EDGE
EXPOSED
(ONE SIDE OF VANE ONLY)
BURN THROUGH
BURNING
BURN THROUGH
(MISSING MATERIAL)
LEADING
VANE
EDGE
EDGE
LEADING
BAFFLE
FIVE ROWS LEADING
EDGE COOLING HOLES
(ONE SIDE OF VANE ONLY)
BURN THROUGH
BURNING
LEADING EDGE BURNS
TRAILING EDGE BURNS
E2346
CONCAVE AIRFOIL VIEW SEEN THROUGH BORESCOPE
A
A B
B
N_MM_720000_6_YGM0_02_00
Figure 72(IAE)-00-00-991-17000-13-A / SHEET 2/3 -
HPT 1st Stage Vane Area Names and Types of Damage
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 19 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
SBE 72-0340
AXIAL
RADIAL
pwzxxb8894a
CONCAVE AIRFOIL VIEW SEEN THROUGH THE BORESCOPE
LEADING EDGE
HOLE PATTERN AREA
LEADING EDGE
OUTER PLATFORM
LEADING EDGE
BURN HOLE
WITH MISSING
METAL
INNER PLATFORM
LEADING EDGE
TRAILING EDGE
BURN WITH
MISSING METAL
INNER PLATFORM
TRAILING EDGE
BURN WITH
MISSING
METAL
N_MM_720000_6_YGM0_03_00
Figure 72(IAE)-00-00-991-17000-13-A / SHEET 3/3 -
HPT 1st Stage Vane Area Names and Types of Damage
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 20 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
PLATFORM
LEADING EDGE
OUTER PLATFORM
FILLET RADIUS CRACK
PLATFORM - TO - AIRFOIL
TRAILING
EDGE
CONNECTED
LOOP CRACK
LEADING
EDGE
PARALLEL
CRACK
INNER PLATFORM
LEADING EDGE
FILLET RADIUS
AIRFOIL
SECTION
A-A
11910B
CONCAVE AIRFOIL VIEW AS SEEN THROUGH THE BORESCOPE
A
A
N_MM_720000_6_YJM0_01_00
Figure 72(IAE)-00-00-991-17100-13-A / SHEET 1/3 -
HPT 1st Stage Vane Area Names and Types of Damage
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 21 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
SBE 72-0340 B8905
CONCAVE AIRFOIL VIEW SEEN THROUGH THE BORESCOPE
A-A
SECTION
AIRFOIL
PLATFORM
FILLET RADIUS
A
A
LEADING EDGE
TRAILING EDGE
OUTER PLATFORM
LEADING EDGE
CONNECTED
LOOP CRACK
INNER PLATFORM
LEADING EDGE
PARALLEL
CRACK
PLATFORM - TO AIRFOIL
FILLET RADIUS CRACK
N_MM_720000_6_YJM0_02_00
Figure 72(IAE)-00-00-991-17100-13-A / SHEET 2/3 -
HPT 1st Stage Vane Area Names and Types of Damage
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 22 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
SBE 72-0340
CONCAVE AIRFOIL VIEW SEEN THROUGH BORESCOPE
E2347
B
A LEADING EDGE
BURNS
TRAILING EDGE
BURNS
VANE
LEADING
EDGE
LEADING
EDGE
BAFFLE
BURNING
BURN THROUGH
(ONE SIDE OF VANE ONLY)
FIVE ROWS LEADING
EDGE COOLING HOLES
B
LEADING EDGE BURNS
BURN THROUGH
(ONE SIDE OF VANE ONLY)
BURNING
TRAILING EDGE
BAFFLE
EXPOSED
BURN
THROUGH
(MISSING
MATERIAL)
A
TRAILING EDGE BURNS
N_MM_720000_6_YJM0_03_00
Figure 72(IAE)-00-00-991-17100-13-A / SHEET 3/3 -
HPT 1st Stage Vane Area Names and Types of Damage
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 23 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
PWXXX19752C
ROW 1
ROW 2
ROW 3 ROW 4 ROW 5
ROW 5
ROW 4
ROW 3
ROW 2
ROW 1
COMBUSTION CHAMBER
OUTER LINER SEGMENT
OUTER LINER SHELL
COMBUSTION CHAMBER
INNER LINER SHELL
SEGMENT
INNER LINER
BULKHEAD
DEFLECTOR
FUEL NOZZLE
BULKHEAD
SEGMENT
BULKHEAD
BULKHEAD
SEGMENT
POST
ATTACHMENT
A
A
N_MM_720000_6_YLM0_01_00
Figure 72(IAE)-00-00-991-17200-13-A / SHEET 1/1 - Combustion Chamber Area Names
** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 24 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
pwzxx11901e
PWV
ROW 1
ROW 2
ROW 3
ROW 4
ROW 5
VIEW OF THE INNER COMBUSTION CHAMBER SEGMENTS
N_MM_720000_6_YNM0_01_01
Figure 72(IAE)-00-00-991-17300-13-A / SHEET 1/1 -
Inner Combustion Chamber Liner Dimensions References
** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 25 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
pwzxx11906e
PWV
VIEW OF THE OUTER COMBUSTION CHAMBER SEGMENTS
ROW 5
ROW 4
ROW 3
ROW 2
ROW 1
IGNITER HOLES
BULKHEAD DEFLECTOR
BULKHEAD SEGMENT
IGNITER SEGMENT
N_MM_720000_6_YPM0_01_01
Figure 72(IAE)-00-00-991-17400-13-A / SHEET 1/1 - Outer
Combustion Chamber Liner Segments Dimensions References
** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 26 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
CIRCUMFERENTIAL
EDGE
MISSING MATERIAL
CIRCUMFERENTIAL
LENGTH
AXIAL
LENGTH
TRAILING
EDGE
SEGMENT TRAILING EDGE BURNBACK
NOTE: SEGMENT DAMAGE ASPECT RATIO:
CIRCUMFERENTIAL
AXIAL
MORE THAN 2
CIRCUMFERENTIAL
EDGE
MISSING
MATERIAL
CIRCUMFERENTIAL
LENGTH AXIAL
LENGTH
TRAILING
EDGE
B8881
BURN HOLE INCREASE TO SEGMENT TRAILING EDGE
NOTE: SEGMENT DAMAGE ASPECT RATIO:
CIRCUMFERENTIAL
AXIAL
LESS THAN OR EQUAL TO 2
N_MM_720000_6_YAR0_01_00
Figure 72(IAE)-00-00-991-23100-13-A / SHEET 1/1 - Combustion
Chamber Liner Segments Borescope Inspection Guidelines
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 27 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
SECTION
(B1 THRU B5)
DETAIL AT 5 POSITIONS
BUSHING
IGNITOR
PLUG
COMBUSTION CHAMBER
OUTER LINER
SHELL
SECTION
(IP1 AND IP2 PORTS)
DETAILS AT 2 POSITIONS 11633C
OUTER LINER SEGMENT
COMBUSTION CHAMBER
1 GASKET
2 PLUG
B-B
A-A
N_MM_720000_6_XXM0_01_00
Figure 72(IAE)-00-00-991-16500-13-A / SHEET 1/1 - Borescope Ports (PRE SBE 72-0221)
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 28 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
B8625A
CAUTION: DO NOT MOVE
THE SPACERS
OR THE INSERT
INSERT
IGNITOR
PLUG
COMBUSTION CHAMBER
OUTER LINER
SHELL
SECTION
(IP1 AND IP2 PORTS)
DETAILS AT 2 POSITIONS
B-B
SPACER
(0 TO 2 AS NECESSARY)
SECTION
(B1 THRU B6)
DETAIL AT 6 POSITIONS
1 GASKET
2 PLUG
A-A
OUTER LINER SEGMENT
COMBUSTION CHAMBER
A A
A A
N_MM_720000_6_YMM0_01_00
Figure 72(IAE)-00-00-991-26100-13-A / SHEET 1/1 - Borescope Ports (POST SBE 72-0221)
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 29 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
7
FLOW
ROW 5
ROW 1
ROW 2
ROW 3
ROW 4
B5491
INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED
FUEL
NOZZLE
No.
BORESCOPE INSPECTION REPORTING FORM
AIRLINE DATE
ENGINE NUMBER HOURS CYCLES
OBL ROW
IGNITER SEGMENT
8
FUEL
NOZZLE
No.
N_MM_720000_6_YGN0_01_00
Figure 72(IAE)-00-00-991-21700-13-A / SHEET 1/1 - Combustion Chamber Damage Form
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 30 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
FLOW
ROW 5
ROW 1
ROW 2
ROW 3
ROW 4
B5492
FUEL
NOZZLE
No.
INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED
FUEL
NOZZLE
No.
FUEL
NOZZLE
No.
BORESCOPE INSPECTION REPORTING FORM
AIRLINE DATE
ENGINE NUMBER HOURS CYCLES
OBL ROW
FUEL
NOZZLE
No.
N_MM_720000_6_YHN0_01_00
Figure 72(IAE)-00-00-991-21800-13-A / SHEET 1/1 - Combustion Chamber Damage Form
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 31 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
BORESCOPE INSPECTION REPORTING FORM
AIRLINE
ENGINE NUMBER HOURS
DATE
CYCLES
OBL ROW
SEGMENT NUMBER
INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED
FLOW
B5493
1
IGNITER SEGMENT
4
N_MM_720000_6_YJN0_01_00
Figure 72(IAE)-00-00-991-21900-13-A / SHEET 1/1 - Combustion Chamber Damage Form
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 32 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
BORESCOPE INSPECTION REPORTING FORM
AIRLINE
ENGINE NUMBER HOURS
DATE
CYCLES
OBL ROW
SEGMENT NUMBER
INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED
FLOW
B5494
2
N_MM_720000_6_YKN0_01_00
Figure 72(IAE)-00-00-991-22000-13-A / SHEET 1/1 - Combustion Chamber Damage Form
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 33 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
BORESCOPE INSPECTION REPORTING FORM
AIRLINE
ENGINE NUMBER HOURS
DATE
CYCLES
OBL ROW
SEGMENT NUMBER
INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED
FLOW
B5495
3
N_MM_720000_6_YLN0_01_00
Figure 72(IAE)-00-00-991-22100-13-A / SHEET 1/1 - Combustion Chamber Damage Form
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 34 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
BORESCOPE INSPECTION REPORTING FORM
AIRLINE
ENGINE NUMBER HOURS
DATE
CYCLES
OBL ROW
SEGMENT NUMBER
INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED
FLOW
B5496
4
N_MM_720000_6_YMN0_01_00
Figure 72(IAE)-00-00-991-22200-13-A / SHEET 1/1 - Combustion Chamber Damage Form
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 35 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
FLOW
ROW 5
ROW 1
ROW 2
ROW 3
ROW 4
B5497
FUEL
NOZZLE
No.
INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED
FUEL
NOZZLE
No.
FUEL
NOZZLE
No.
BORESCOPE INSPECTION REPORTING FORM
AIRLINE DATE
ENGINE NUMBER HOURS CYCLES
IBL ROW
FUEL
NOZZLE
No.
N_MM_720000_6_YNN0_01_00
Figure 72(IAE)-00-00-991-22300-13-A / SHEET 1/1 - Combustion Chamber Damage Form
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 36 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
BORESCOPE INSPECTION REPORTING FORM
AIRLINE
ENGINE NUMBER HOURS
DATE
CYCLES
IBL ROW
SEGMENT NUMBER
INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED
FLOW
B5498
2
N_MM_720000_6_YPN0_01_00
Figure 72(IAE)-00-00-991-22400-13-A / SHEET 1/1 - Combustion Chamber Damage Form
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 37 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
BORESCOPE INSPECTION REPORTING FORM
AIRLINE
ENGINE NUMBER HOURS
DATE
CYCLES
IBL ROW SEGMENT NUMBER
INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED
FLOW
B5499
3
N_MM_720000_6_YQN0_01_00
Figure 72(IAE)-00-00-991-22500-13-A / SHEET 1/1 - Combustion Chamber Damage Form
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 38 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
BORESCOPE INSPECTION REPORTING FORM
AIRLINE
ENGINE NUMBER HOURS
DATE
CYCLES
IBL ROW SEGMENT NUMBER
INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED
FLOW
B8502
4
N_MM_720000_6_YRN0_01_00
Figure 72(IAE)-00-00-991-22600-13-A / SHEET 1/1 - Combustion Chamber Damage Form
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 39 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
BORESCOPE INSPECTION REPORTING FORM
AIRLINE
ENGINE NUMBER HOURS
DATE
CYCLES
OBL ROW
IBL ROW
SEGMENT NUMBER
SEGMENT NUMBER
INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED
FLOW
B8503
N_MM_720000_6_YSN0_01_00
Figure 72(IAE)-00-00-991-22700-13-A / SHEET 1/1 - Combustion Chamber Damage Form
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 40 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
(CAN NOT BE SEEN)
IGNITER RAIL
EDGE
CIRCUMFERENTIAL
0.750in
(19,050mm)
(REFERENCE)
EDGE
BURNBACK
IGNITER RAIL
BURNBACK MISSING
MATERIAL
EDGE
BURNBACK
MISSING
MATERIAL
EDGE
TRAILING
SEGMENT EDGE BURNBACK - OBL NO.1 IGNITER SEGMENT
(CAN NOT BE SEEN)
IGNITER RAIL
CUTAWAY VIEW
ATTACHMENT POST,
(TYPICAL)
A A
45°
45°
IGNITER RAIL BURNBACK AND IGNITER HOLE EDGE BURNS LIMITED
A
TO AREAS AS GIVEN IN INSPECTION LIMITS
PWZXXB8886A
EDGE
CIRCUMFERENTIAL
EDGE
BURNBACK
MISSING
MATERIAL
MISSING
MATERIAL
EDGE
TRAILING
SEGMENT EDGE BURNBACK - OBL NO.1 THAT IS NOT AN IGNITER SEGMENT
N_MM_720000_6_YDR0_01_00
Figure 72(IAE)-00-00-991-23300-13-A / SHEET 1/1 - Combustion Chamber Liner Segment Crack Limits
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 41 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
CIRCUMFERENTIAL
EDGE
MISSING
MATERIAL EDGE
BURNBACK
MISSING
MATERIAL
EDGE
BURNBACK
MISSING
MATERIAL
TRAILING
EDGE
SEGMENT EDGE BURNBACK THAT HAVE OR DO NOT HAVE
COMBUSTION
HOLE RIM
(EXAMPLE)
COMBUSTION HOLE
RIM BURNBACK
CIRCUMFERENTIAL
EDGE
MISSING
MATERIAL
BURN HOLE
LONGEST DIMENSION
TRAILING
EDGE
MISSING
MATERIAL
BURNS THAT LOOK
LIKE THEY COULD
CAUSE MATERIAL
TO BREAK OFF
B8887
SEGMENT BURN HOLE - OBL AND IBL SEGMENTS THAT HAVE OR
DO NOT HAVE COMBUSTION HOLES
COMBUSTION HOLES, OBL NO. 2 THROUGH OBL NO. 5 AND IBL NO. 1 THROUGH IBL NO. 5
N_MM_720000_6_YER0_01_00
Figure 72(IAE)-00-00-991-23400-13-A / SHEET 1/1 - Combustion Chamber Liner Segment Burn Limits
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 42 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
pwzxxe9341
PWV
ATTACHMENT POST
CUTAWAY VIEW
(TYPICAL)
MISSING COATING
LEADING EDGE
DIA 4.826 mm
(0.19 in)
POST VISIBLE < 50% POST VISIBLE > 50%
A
A
N_MM_720000_6_XBP0_01_00
Figure 72(IAE)-00-00-991-53700-13-A / SHEET 1/1 -
Combustion Chamber Liner Segment Attachment Post Visibility
** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 43 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
BULKHEAD SEGMENT
INSPECTION AREAS
BULKHEAD SEGMENT CRACKS
CRACK
SEPARATION
PWZXXB8882A
BULKHEAD DEFLECTOR
SLOT LENGTH
0.300 in (7,620 mm)
(REFERENCE)
BULKHEAD
CRACK
CRACKS WHICH LOOK LIKE
THEY WILL GO THROUGH
EACH OTHER AND CAUSE
MATERIAL TO BREAK OFF
BULKHEAD
DEFLECTOR
BULKHEAD
SEGMENT
0.600 in
(15,240 mm)
(REFERENCE)
(12,065 mm)
(REFERENCE)
0.475 in
BULKHEAD DEFLECTOR
AIRHOLE CIRCLE
1.375 in
(34,925 mm)
(REFERENCE)
N_MM_720000_6_YCN0_01_00
Figure 72(IAE)-00-00-991-21000-13-A / SHEET 1/
1 - Liner (Bulkhead) Segment Inspection Areas and Cracks
** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 44 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
BURN HOLE
LONGEST DIMENSION
(MISSING MATERIAL)
BULKHEAD SEGMENT BURN HOLE
B8883
N_MM_720000_6_YCR0_01_00
Figure 72(IAE)-00-00-991-23200-13-A / SHEET 1/1 - Combustion Chamber Bulkhead Segment Burn Hole
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 45 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
pwzxxe9342a
PW
V
PANEL BURN BACK
POST VISIBLE < 50%
BULKHEAD SHELL
POST VISIBLE > 75%
> 50% EXPOSURE OF THIS
STUD IS NOT ALLOWED
SHELL BURNING/CRACKING
AT ATTACHMENT POST HOLE
NOT ALLOWED
N_MM_720000_6_XBQ0_01_01
Figure 72(IAE)-00-00-991-53800-13-A / SHEET 1/1 - Combustion
Chamber Bulkhead Segment Attachment Post Visibility
** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 46 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
BULKHEAD DEFLECTOR CRACKS
CRACKS WHICH LOOK LIKE
THEY WILL GO THROUGH
EACH OTHER AND CAUSE
MATERIAL TO BREAK OFF DEFLECTOR
CRACK
CIRCUMFERENTIAL
CRACK
DEFLECTOR EDGE
BURNBACK
MISSING
MATERIAL
MISSING MATERIAL
BULKHEAD DEFLECTOR BURNBACK
pwzxxb8884e
N_MM_720000_6_YBR0_01_00
Figure 72(IAE)-00-00-991-23000-13-A / SHEET 1/1 -
Combustion Chamber Bulkhead Deflector Cracks and Burnback
** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 47 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
DISTANCE FROM COMBUSTION
AIR HOLE TO EDGE OF BURN BACK.
MISSING MATERIAL
COMBUSTION AIR HOLE
DIAMETER IS 0.076in.
(1.93mm)
(REFERENCE)
"V" NOTCH BURNING
BULKHEAD DEFLECTOR BURNBACK
MISSING MATERIAL
COMBUSTION AIR HOLE
DIAMETER IS 0.076in.
(1.93mm)
(REFERENCE)
BULKHEAD DEFLECTOR BURNBACK
pwzxxe7554
N_MM_720000_6_XAA0_01_00
Figure 72(IAE)-00-00-991-19900-13-A / SHEET 1/2 - Bulkhead Deflector Burnback
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 48 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
INCREASED LIMITS AS DESCRIBED IN STEP (C), AT
INSPECTION OF 250 HOURS DO NOT APPLY AT THESE
FOUR LOCATIONS. INCREASED LIMITS APPLY AT ANY OF
THE OTHER 16 LOCATIONS IF THE MINIMUM SEPARATION
REQUIREMENTS ARE MET.
SCHEMATIC REAR VIEW
IGNITER LOCATIONS
pwzxxe2485a
DEFLECTORS WITH BURNS THAT ARE LESS THAN
0.130in. (3.302mm) FROM THE COMBUSTION
AIR HOLES MUST BE SEPARATED BY A MINIMUM
OF THREE DEFLECTORS WITH BURNS THAT ARE
MORE THAN 0.130in. (0.320mm) FROM THE
COMBUSTION AIR HOLES.
N_MM_720000_6_XAA0_02_00
Figure 72(IAE)-00-00-991-19900-13-A / SHEET 2/2 - Bulkhead Deflector Burnback
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 49 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
0.400 in.
(10,16mm)
REFERENCE
NO DAMAGE IS
PERMITTED
END CAP
CLEARANCE
HEATSHIELD
PWYXX19842A
NO DAMAGE
IS PERMITTED
A
N_MM_720000_6_XZN0_01_00
Figure 72(IAE)-00-00-991-20800-13-A / SHEET 1/1 - Fuel Nozzle End Cap Inspection Areas
** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 50 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
9
RADIAL CRACKS CIRCUMFERENTIAL CRACKS
END CAP HEAT SHIELD SECTIONS
THAT ARE BROKEN AWAY
19843A
A A
A
N_MM_720000_6_YAN0_01_00
Figure 72(IAE)-00-00-991-20900-13-A / SHEET 1/1 - Fuel Nozzle End Cap Inspection Areas
** ON A/C 051-100, 201-250, 351-400, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 51 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
PWZXX19756C
(FUEL NOZZLE)
0.020in
(0,51mm)
WIDTH
(REFERENCE)
CRACK
C
C
BURN-BACK
QUADRANT
0.180in (4,57mm)
SLOT
SECTION
C-C
FUEL NOZZLE
0.020in (0,51mm)
(REFERENCE)
COMBUSTION CHAMBER
(WHEN YOU LOOK FORWARD AT THE
12 O'CLOCK POSITION)
BORESCOPE VIEW
B
END CAP
HEATSHIELD
END CAP
HEATSHIELD
FUEL NOZZLE
END CAP
HEATSHIELD
CLEARANCE
GAP
B
N_MM_720000_6_YRM0_01_00
Figure 72(IAE)-00-00-991-29800-13-A / SHEET 1/1 - Fuel Nozzle Types of Damage
** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 52 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
3. Job Set-up
Subtask 72-00-00-941-078-A
A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes 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) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
Subtask 72-00-00-010-112-A
B. Open the fan cowls (Ref. AMM TASK 71-13-00-010-010) :
(1) FOR 1000EM1 (ENGINE-1)
437AL, 438AR
(2) FOR 1000EM2 (ENGINE-2)
447AL, 448AR
Subtask 72-00-00-040-066-A
C. Deactivate the Thrust Reverser
WARNING: THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) MUST BE DEACTIV-
ATED BEFORE WORKING ON OR AROUND THE THRUST REVERSER. FAILURE TO
DEACTIVATE THE HCU CAN RESULT IN INADVERTENT THRUST REVERSER OPERA-
TION AND INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT.
(1) Deactivate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-040-012) .
Subtask 72-00-00-010-110-A
D. Open the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010) :
(1) FOR 1000EM1 (ENGINE-1)
451AL, 452AR
(2) FOR 1000EM2 (ENGINE-2)
461AL, 462AR
4. Procedure
Subtask 72-00-00-290-059-A
CAUTION: THE ENGINE IS HOT IMMEDIATELY AFTER SHUTDOWN AND CAN CAUSE BURNS AND
DAMAGE TO THE BORESCOPE EQUIPMENT. WAIT 2-3 HOURS AFTER SHUTDOWN BE-
FORE YOU DO A BORESCOPE INSPECTION.
A. General
PRE SBE 72-0221
(1) There are five borescope ports and two ignitor ports to give access to the combustion chamber and
the HPT stage 1 vanes.
(Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage
Vanes (Left Side) (PRE SBE 72-0221) SHEET 1)
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 53 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
(Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage
Vanes (Right Side) (PRE SBE 72-0221) SHEET 1)
(Ref. Fig. Borescope Inspection Ports for the First Stage Vanes and the Combustion Chamber Liner
(PRE SBE 72-0221) SHEET 1)
POST SBE 72-0221
(2) There are six borescope ports and two igniter ports give access to the combustion chamber and the
HPT stage 1 vanes.
(Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes
(Left Side) (POST SBE 72-0221) SHEET 1)
(Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes
(Right Side) (POST SBE 72-0221) SHEET 1)
(Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes
(POST SBE 72-0221) SHEET 1)
END OF SBE 72-0221
(3) The names of different parts and dimensional references of the combustion chamber and the HPT 1st
stage vanes are shown.
(Ref. Fig. HPT 1st Stage Vane Area Names and Dimensional References)
(Ref. Fig. HPT 1ST Stage Vane Area Names and Dimensional References SHEET 1)
(Ref. Fig. HPT 1st Stage Vane Area Names and Dimensional References)
(Ref. Fig. HPT 1st Stage vane Area Names and Dimensional References)
(Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage)
(Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage)
(Ref. Fig. Combustion Chamber Area Names SHEET 1)
(Ref. Fig. Inner Combustion Chamber Liner Dimensions References SHEET 1)
(Ref. Fig. Outer Combustion Chamber Liner Segments Dimensions References SHEET 1)
Use these names when identifying borescope inspection limits.
(4) Use these terms when you identify a combustion chamber condition seen during borescope
inspection:
(a) BURN: A local area of burner liner segment, bulkhead segment, or deflector surface that
has changed colour, has a rough surface texture or shows thinner material because of high
temperatures. Burns can be located all around but more are found downstream of combustion
holes in the burner liner segments.
(b) BURN HOLE: A local burn area that has continued through the base material and does not
extend to the leading or trailing edge of the segment.
(Ref. Fig. Combustion Chamber Liner Segments Borescope Inspection Guidelines SHEET 1)
(c) EDGE BURNBACK: Full thickness liner segment burns that start at an edge, occur more at the
segment trailing edge location but have also occurred at the leading edge. Burnback is segment
material that is missing. Complete edge burnback is when segment material is missing from the
trailing edge to the leading edge.
(Ref. Fig. Combustion Chamber Liner Segments Borescope Inspection Guidelines SHEET 1)
(d) RADIAL BURNBACK: Full thickness burning on deflector edge continuing radially inward toward
fuel nozzle.
(5) General inspection guidelines:
(a) Give the results of decreased time inspections to your IAE representative.
(b) If a piece of combustion chamber materials breaks off between inspection times, a borescope
inspection of the high pressure turbine is necessary. If the high pressure turbine is not damaged
after the material breaks off you can continue the combustion chamber borescope inspections at
the times given by other limits.
(c) All spalled ceramic coating on the combuster segments, the bulkhead segments or the bulkhead
deflectors is acceptable without a decreased borescope inspection time.
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 54 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
(d) Bulkhead and liner segments: Any coating loss on the bulkhead/liner segment due to cracks is
not considered material liberation or break off. Material liberation or break off is defined as the
coating loss along with the bulkhead/liner segment parent material missing.
(6) Use these terms when you identify an HPT 1st stage vane condition seen during borescope
inspection:
(a) BURNS: A local area of 1st stage vane surface that has changed colour, has a rough surface
texture or shows thinner material because of high temperature. Burns can be located all around.
(b) BURN THROUGH: A local burn area that has continued through the airfoil surface. Cracks that
have burned to more than 0.050 in. (1.27 mm) separation are also burn through.
(c) TRAILING EDGE BURNS: Burns or burn through that start at the airfoil trailing edge and
continue forward to the airfoil leading edge.
(d) LIFT UP: An area where the surface on one side of a crack is higher than the surface on the
other side of the crack.
(e) COATING DAMAGE: Chips, spalling, flakes, blisters, peeling or oxidation that is confined to the
coating.
(f) CONNECTED LOOP CRACK: A crack or a group of cracks that show an isolated area of vane
metal.
(g) LEADING EDGE: The area from the first row of cooling holes on the concave side of the vane to
the first row of cooling holes on the convex side of the vane.
(7) General inspection guidelines:
(a) Give the results of decreased time inspections to your IAE representative.
(b) All ceramic coating damage is acceptable without a decreased borescope inspection time.
Extended operation with a large quantity of ceramic coating not there can possibly cause the
vane to be out of limits and cannot be repaired at overhaul.
Subtask 72-00-00-010-093-A
B. Get Access to the Combustion Chamber and the HPT 1st Stage Vanes
PRE SBE 72-0221
(1) Get access to the combustion chamber and the HPT 1st stage vanes through the B1 to B5 and IP1
and IP2 ports as follows:
(a) For the B1 to B5 ports, remove the 5 plugs and gaskets at the locations shown.
(Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage
Vanes (Left Side) (PRE SBE 72-0221) SHEET 1)
(Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage
Vanes (Right Side) (PRE SBE 72-0221) SHEET 1)
(Ref. Fig. Borescope Ports (PRE SBE 72-0221) SHEET 1)
(b) For the IP1 and IP2 ports, remove the igniter plugs (Ref. AMM TASK 74-21-41-000-010) .
(Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage
Vanes (Right Side) (PRE SBE 72-0221) SHEET 1)
(Ref. Fig. Borescope Ports (PRE SBE 72-0221) SHEET 1)
NOTE: Do not remove the igniter insert. (Ref. Fig. Borescope Ports (PRE SBE 72-
0221) SHEET 1)
POST SBE 72-0221
(2) Get access to the combustion chamber and the HPT 1st stage vanes through the B1 to B6 and IP1
and IP2 ports as follows:
(a) For the B1 to B6 ports, remove the 6 plugs and gaskets at the locations shown.
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 55 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
(Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1
Vanes (Left Side) (POST SBE 72-0221) SHEET 1)
(Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1
Vanes (Right Side) (POST SBE 72-0221) SHEET 1)
(Ref. Fig. Borescope Ports (POST SBE 72-0221) SHEET 1)
(b) For the IP1 and IP2 ports, remove the igniter plugs (Ref. AMM TASK 74-21-41-000-010) .
(Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1
Vanes (Right Side) (POST SBE 72-0221) SHEET 1)
(Ref. Fig. Borescope Ports (POST SBE 72-0221) SHEET 1)
NOTE: Do not remove the igniter insert. (Ref. Fig. Borescope Ports (POST SBE 72-
0221) SHEET 1)
END OF SBE 72-0221
Subtask 72-00-00-290-060-A
C. Examine the combustion chamber, fuel injectors and the first stage vanes for damage
CAUTION: THE LIMITS WHICH FOLLOW ARE APPLICABLE ON A CONTINUE IN SERVICE BASIS
ONLY. EACH LIMIT IS BASED ON WHAT THE STRUCTURE OF THE BLADE MUST BE
AND DOES NOT INDICATE THAT THERE WILL NOT BE DETERIORATION OF THE EN-
GINE PERFORMANCE, STABILITY, OPERATING LIMITS OR PART REPAIRABILITY.
(1) Put the BORESCOPE - RIGHT ANGLE, FLEXSCOPE or BORESCOPE - FLEXIBLE in to the ports
and examine the combustion chamber, fuel injectors and the first stage vanes for damage.
(Ref. Fig. Borescope Ports (PRE SBE 72-0221) SHEET 1)
NOTE: An COVER - EYE is recommended on the eye that is not used, to decrease eye tension.
(2) If damage seen is not listed, contact your IAE representative.
Subtask 72-00-00-220-101-A
D. Convex and Concave Surface Cracks/Burns
(Ref. Fig. HPT 1st Stage Vane Area Names and Dimensional References)
(Ref. Fig. HPT 1st Stage vane Area Names and Dimensional References)
(Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage)
Pre SBE 72-0340
SBE 72-0340
NOTE: All cracks or sections of cracks burned to a width of more than 0.050 in. (1.27 mm) are burn holes.
Use the applicable burn limits.
NOTE: If a convex or a concave burn extends to the leading edge, you must use leading edge criteria.
(1) Accept with an inspection each 600 hours if:
(a) There is more than one axial crack 3/4 chord length or longer. Axial and radial cracks can go
through each other.
(b) There are many radial cracks that are more than 1.500 in. (38.1 mm) in length. Axial cracks can
go through radial cracks.
(c) There is a burn that has caused a burn through that is between 0.050 in. (1.27 mm) and 0.100 in.
(2.54 mm) at its shortest dimension.
(2) Accept with an inspection each 300 hours if:
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 56 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
(a) There is a burn that has caused a burn through that is between 0.100 in. (2.54 mm) and 0.30 in.
(7.62 mm) at its shortest dimension.
(3) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There is axial or radial crack lift up of more than 0.050 in. (1.27 mm).
(b) There are connected loop cracks that show a piece of vane metal that is calculated to be more
than 0.500 in. (12.7 mm) in length.
(c) There is a crack that is three-quarters of a chord length long or longer that also goes in to a
leading edge or a convex surface burn through.
(d) There is a burn that has caused a burn through that is more than 0.300 in. (7.62 mm) at its
shortest dimension.
Subtask 72-00-00-220-064-A
E. Leading Edge Cracks and Leading Edge Burns
(Ref. Fig. HPT 1st Stage vane Area Names and Dimensional References)
Pre SBE 72-0340
SBE 72-0340
NOTE: There is no limit to the number of leading edge tight cracks permitted without decreased inspection
times.
(1) Accept with an inspection each 600 hours if:
(a) There are leading edge cracks and burns that have caused base vane material burn through
within the leading edge cooling holes and it measures less than 0.85 in. (21.59 mm) in length
radially.
(2) Accept with an inspection each 300 hours if:
(a) There is leading edge base vane material burn through that extends less than 0.20 in. (5.08 mm)
beyond the first row of leading edge cooling air holes and it measures less than 0.65 in. (16.51
mm) axially and 0.85 in. (21.59 mm) radially.
(3) Accept with an inspection each 75 hours if:
(a) There is leading edge base vane material burn through that extends less than 0.25 in. (6.35 mm)
beyond the first row of leading edge cooling holes and it measures less than 0.65 in. (16.51 mm)
axially and 0.85 in. (21.59 mm) radially.
(4) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There is leading edge base vane material burn through that extends more than 0.25 in. (6.35
mm) beyond the leading edge cooling air holes.
(b) There is leading edge base vane material burn through of more than 0.85 in. (21.59 mm) radially.
(c) There is leading edge base vane material burn through of more than 0.65 in. (16.51 mm) axially.
(d) There is axial trailing edge base vane material burn through and/or a crack that measures more
than three quarters of the cord length.
(e) There is axial leading edge base vane material burn through plus a crack that measures three
quarters of the cord length.
(f) There is baffle burn-through.
(g) There is baffle cracking.
Subtask 72-00-00-220-065-A
F. Trailing Edge Burns
(Ref. Fig. HPT 1st Stage vane Area Names and Dimensional References)
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 57 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
(Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage)
Pre SBE 72-0340
SBE 72-0340
(1) Accept with an inspection each 600 hours if:
(a) There is a burn through that goes between one quarter and one half of the chord length from the
trailing edge and is more than 0.500 in. (12.7 mm) in width at the trailing edge.
NOTE: 0.500 in. (12.7 mm) is equal to five trailing edge cooling air slots.
(2) Accept with an inspection each 300 hours if:
(a) There is a burn through that goes between one half and three quarters of the chord length from
the trailing edge and is more than 0.500 in. (12.7 mm) in width at the trailing edge.
NOTE: 0.500 in. (12.7 mm) is equal to five trailing edge cooling air slots.
(3) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There is a burn through that goes more than three quarters of the chord length from the trailing
edge and is more than 0.500 in. (12.7 mm) in width at the trailing edge.
NOTE: 0.500 in. (12.7 mm) is equal to five trailing edge cooling air slots.
(b) There is a trailing edge burn through inboard of the first two trailing edge cooling slots.
Subtask 72-00-00-220-066-A
G. Cracks on the Inner and Outer Platforms
(Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage)
Pre SBE 72-0340
SBE 72-0340
(1) Accept with an inspection each 600 hours if:
(a) There is a crack that is more than 0.500 in. (12.7 mm) in length.
(2) Accept with an inspection each 300 hours if:
(a) There is a crack that is more than 1.000 in. (25.4 mm) in length.
(3) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There is a crack that is parallel to the airfoil fillet radius, that goes around the airfoil leading edge
and that is more than 1.500 in. (38.1mm) in length.
Subtask 72-00-00-220-067-A
H. Cracks on the Inner and Outer Platform Airfoil Fillet Radius
(Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage)
Pre SBE 72-0340
SBE 72-0340
(1) Accept with an inspection each 600 hours if:
(a) There is a fillet crack that is more than 1.000 in. (25.4 mm) in length and that goes from the fillet
on to the airfoil.
(2) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There is a crack that is more than 1.000 in. (25.4 mm) in length and a part of the length is eroded
to a width of more than 0.030 in. (0.76 mm).
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 58 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
(b) There is a crack in the fillet radius that is more than 1.500 in. (38.1 mm) in length and that goes
around the airfoil leading edge.
Subtask 72-00-00-220-138-A
J. Burns on the Inner and Outer Platforms
(Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage)
Pre SBE 72-0340
SBE 72-0340
(1) Accept with an inspection each 600 hours if:
(a) There are burns that go from the edge of the platform to the platform airfoil fillet.
(2) Accept with an inspection each 300 hours if:
(a) There are burns that have caused a burn through that is less than 0.250 in. (6.35 mm) in length.
(3) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There are burns that have caused a burn through that is more than 0.250 in. (6.35 mm) in length.
Subtask 72-00-00-220-068-A
K. Make a record of the damage that you find when you do a borescope inspection of the combustion
chamber
(1) Use the Combustion Chamber Damage Forms to record the damage.
(Ref. Fig. Combustion Chamber Damage Form SHEET 1)
(Ref. Fig. Combustion Chamber Damage Form SHEET 1)
(Ref. Fig. Combustion Chamber Damage Form SHEET 1)
(Ref. Fig. Combustion Chamber Damage Form SHEET 1)
(Ref. Fig. Combustion Chamber Damage Form SHEET 1)
(Ref. Fig. Combustion Chamber Damage Form SHEET 1)
(Ref. Fig. Combustion Chamber Damage Form SHEET 1)
(Ref. Fig. Combustion Chamber Damage Form SHEET 1)
(Ref. Fig. Combustion Chamber Damage Form SHEET 1)
(Ref. Fig. Combustion Chamber Damage Form SHEET 1)
(Ref. Fig. Combustion Chamber Damage Form SHEET 1)
Subtask 72-00-00-220-069-A
L. Burner liner segment cracks
(1) Accept inner and outer burner liner segments that have combustion holes without a decreased
borescope inspection time if:
(a) There are two cracks completely through a segment in the axial direction and each crack goes
through combustion holes that are separated by a combustion hole without a crack.
(b) There are two cracks completely through a segment in the axial direction and one of the cracks
goes through a combustion hole and the other crack is separated by a combustion hole and is
not less than 0.700 in. (17.8 mm) from a circumferential edge.
(2) Accept inner and outer burner liner segments that do not have combustion holes without a decreased
borescope inspection time if:
(a) There is one crack completely through axially that is more than 0.700 in. (17.8 mm) from a
circumferential edge.
(3) Accept inner and outer burner liner segments that have combustion holes with an inspection each
600 hours if:
(a) There are two or more cracks downstream of a combustion hole, one of the cracks goes from the
combustion hole to the trailing edge and no other crack goes more than half the distance to the
same combustion hole or trailing edge.
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 59 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
(4) Accept inner and outer burner liner segments that do not have combustion holes with an inspection
each 600 hours if:
(a) There are two or more axial cracks, one crack is completely through the segment and is more
than 0.700 in. (17.8 mm) from a circumferential edge. No other crack is more than half the axial
length of the segment or nearer than 0.700 in. (17.8 mm) to a circumferential edge.
(5) Accept inner and outer burner liner segments that have combustion holes with an inspection each
300 hours if:
NOTE: You must also do a borescope inspection of the stage 1 HPT blades (Ref. AMM TASK 72-
00-00-200-014) each 300 hours if the liner segments are on a 300-hour repeat borescope in-
spection for segment cracking.
(a) There are 2, 3 or 4 cracks completely through axially, and each crack goes through a combustion
hole and at least two cracks go through adjacent combustion holes.
(b) There are two or more cracks downstream of a combustion hole, one crack goes from a
combustion hole to the trailing edge and no other crack goes more than two thirds of the distance
to the same combustion hole or trailing edge
(c) There are cracks that can cause a piece of segment material up to 0.250 in.2 (161.29 mm.2) in
area to break off.
NOTE: Material break off is defined as the coating loss along with the liner segment parent ma-
terial missing.
(6) Accept inner and outer burner liner segments that do not have combustion holes with an inspection
each 300 hours if:
NOTE: You must also do a borescope inspection of the stage 1 HPT blades (Ref. AMM TASK 72-
00-00-200-014) each 300 hours if the liner segments are on a 300-hour repeat borescope in-
spection for segment cracking.
(a) There are two or more axial cracks, one crack is completely through the segment and is more
than 0.700 in. (17.8 mm) from a circumferential edge. No other crack is more than two thirds the
axial length of the segment or nearer than 0.700 in. (17.78 mm) to a circumferential edge.
(b) There are cracks that can cause a piece of segment material up to 0.250 in.2 (161.29 mm.2) in
area to break off.
NOTE: Material break off is defined as the coating loss along with the liner segment parent ma-
terial missing.
(7) All segments, remove the engine in less than 30 cycles and tell your IAE representative if:
(a) There are cracks that can cause a piece of segment material more than 0.250 in.2 (161.29
mm.2) in area to break off.
NOTE: Material break off is defined as the coating loss along with the liner segment parent ma-
terial missing.
Subtask 72-00-00-220-070-A
M. Segment Edge Burnback
(1) Accept segments without a decreased borescope inspection if:
(a) There is edge burnback of less than 0.70 in. (17.78 mm) and the following conditions are met:
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 60 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
1 There is no liner shell damage (burn-through or cracks).
2 There is damage to the rails around the igniter holes on the row 1 igniter segment less than
135 degrees.
3 You must not be able to see an attachment post.
(2) Accept segments with an inspection each 600 hours if:
(a) The edge burnback is between 0.70 in. (17.78 mm) and 0.90 in. (22.86 mm) and the following
conditions are met:
1 There is no liner shell damage (burn-through or cracks).
2 There is damage to the rails around the igniter holes on the row 1 igniter segment less than
135 degrees.
3 You must not be able to see an attachment post.
(3) Accept segments with an inspection each 300 hours if:
(a) The edge burnback is more than 0.90 in. (22.86 mm) and the following conditions are met:
1 Liner shell damage (burn-through or cracks) must not have an area of more than 0.50 in.2
(322.58 mm2).
2 There is damage to the rails around the igniter holes on the row 1 igniter segment less than
135 degrees.
3 One attachment post is visible up to 50 percent in one or more liner segments.
NOTE: A maximum of three liner shell damage locations for each burner assembly is al-
lowed.
(4) If the edge burnback is more than 1 in. (25.40 mm), you must also do a borescope inspection of the
stage 1 HPT blades each 300 hours.
(5) All segments,
(Ref. Fig. Combustion Chamber Liner Segment Crack Limits SHEET 1)
remove the engine in less than 30 cycles and tell your IAE representative if:
(a) There is complete edge burnback on one segment and another area of edge burnback more than
1 in. (25.40 mm) on the same segment.
(b) There are two or more segments with complete edge burnback. Refer to
for burnback inspection limits which need engine removal in less than 30 cycles.
(c) There is damage to the rails around the igniter holes on the row 1 igniter segment more than 135
degrees.
(Ref. Fig. Combustion Chamber Liner Segment Crack Limits SHEET 1)
(d) There is edge burnback that shows an attachment post more than 50 percent or an attachment
post is missing.
(e) There is liner shell damage (burn-through or cracks) that is more than 0.500 in.2 (322.58 mm2)
in area or there are more than three locations of liner shell damage less than 0.500 in.2 (322.58
mm2) in all the burner assembly.
Subtask 72-00-00-220-071-A
N. Surface Burns and Burn-Through Holes in Liner Segments
(1) Accept segments (with or without combustion holes)
(Ref. Fig. Combustion Chamber Liner Segment Burn Limits SHEET 1)
without a decreased borescope inspection time if:
(a) As much as all the surface is burned.
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 61 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
(b) There are segment burn-through holes that are less than 0.35 in. (8.89 mm) in length and the
following conditions are met:
1 There must be no liner shell damage (burns, burn-through, cracks).
2 There is damage to the rails around the igniter holes on the row 1 igniter segment less than
135 degrees.
3 You must not be able to see an attachment post.
(2) Accept segments (with or without combustion holes)
(Ref. Fig. Combustion Chamber Liner Segment Burn Limits SHEET 1)
with an inspection each 600 hours if:
(a) There is a segment burn-through hole that is between 0.35 in. (8.89 mm) and 0.65 in. (16.51 mm)
in length and the following conditions are met:
1 There must be no liner shell damage (burns, burn-through, cracks).
2 There is damage to the rails around the igniter holes on the row 1 igniter segment less than
135 degrees.
3 You must not be able to see an attachment post.
(3) Accept segments (with or without combustion holes)
(Ref. Fig. Combustion Chamber Liner Segment Burn Limits SHEET 1)
(Ref. Fig. Combustion Chamber Liner Segment Attachment Post Visibility SHEET 1)
with an inspection each 300 hours if:
(a) There is a segment burn-through hole that is between 0.65 in. (16.51 mm) and 1 in. (25.40 mm)
in length and the following conditions are met:
1 Liner shell damage (burns, burn-through, cracks) must not have an area of more than 0.50
in.2 (322.58 mm2).
2 Liner shell damage (burns, burn-through, cracks) must not occur in more than three
locations.
3 There is damage to the rails around the igniter holes on the row 1 igniter segment less than
135 degrees.
4 One attachment post is visible up to 50 percent in one or more liner segments.
(b) There are segment burns or cracks that can cause a piece of segment material more than 0.50
in. (12.70 mm) in length to break off.
(4) Segments (with or without combustion holes),
(Ref. Fig. Combustion Chamber Liner Segment Crack Limits SHEET 1)
(Ref. Fig. Combustion Chamber Liner Segment Attachment Post Visibility SHEET 1)
remove the engine in less than 30 cycles and tell your IAE representative if:
(a) There is a segment burn-through hole that is more than 1 in. (25.40 mm) in length.
(b) There is damage to the rails around the igniter holes on the row 1 igniter segment more than 135
degrees.
(c) One attachment post is visible more than 50 percent in one or more liner segments.
(d) More than one attachment post is visible on one or more liner segment.
(e) There is liner shell damage (burns, burn-through, cracks) that is more than 0.500 in.2 (322.58
mm2) in area or occurs in more than three locations that are less than 0.500 in.2 (322.58 mm2)
in area.
Subtask 72-00-00-220-074-A
P. Bulkhead Segment Cracks
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 62 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
(1) Accept all bulkhead segments without a reduced inspection if:
(Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1)
(a) There is no more than one crack on any side of a bulkhead segment. There is no limit to the
length of the crack.
(b) There are two or more cracks on the same side of a bulkhead segment, less than 0.375 in. (9.52
mm).
(2) Accept all bulkhead segments with a 600-hour repeat borescope inspection if:
(Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1)
(a) There are two or more cracks more than 0.375 in. (9.52 mm) on the same side of any bulkhead
segment.
(3) Accept all bulkhead segments with a 300-hour repeat borescope inspection if:
(Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1)
NOTE: You must also do a borescope inspection of the stage 1 HPT blades (Ref. AMM TASK 72-00-
00-200-014) each 300 hours if the combustor is on a 300-hour repeat borescope inspection
for bulkhead segment cracking.
(a) There are cracks that may liberate a piece of material equal to or less than 0.25 in.2 (161.29
mm2).
NOTE: Material liberation is defined as the coating loss along with the segment parent material
missing.
(b) There are two or more cracks on the same side of any bulkhead segment. At least one crack
extends from the edge of the bulkhead segment under the fuel nozzle guide or to the inner rim
of the bulkhead segment, and another is at least 0.375 in. (9.52 mm). These cracks must be
separated by less than 0.50 in. (12.70 mm).
(4) Remove the engine in less than 30 cycles if:
(Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1)
(a) There are cracks that may liberate a piece of material more than 0.25 in.2 (161.29 mm2).
NOTE: Material liberation is defined as the coating loss along with the segment parent material
missing.
(b) There are two or more cracks on the same side of any bulkhead segment. At least one crack
extends from the edge of the bulkhead segment under the fuel nozzle guide or to the inner rim
of the bulkhead segment, and another is at least 0.375 in. (9.52 mm). These cracks must be
separated by more than 0.50 in. (12.70 mm).
Subtask 72-00-00-220-075-A
Q. Bulkhead Segment Burns and burn-through holes
(1) Accept all bulkhead segments
(Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1)
(Ref. Fig. Combustion Chamber Bulkhead Segment Burn Hole SHEET 1)
without a decreased borescope inspection time if:
(a) As much as all the surface is burned.
(b) There is one bulkhead segment burn-through hole less than 2 in. (50.80 mm) in length and the
following conditions are met:
1 There must be no damage to the bulkhead liner below.
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 63 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
2 A bulkhead segment attachment post must not be visible.
(c) There are multiple bulkhead segment burn-through holes less than 1 in. (25.40 mm) in length and
the following conditions are met:
1 There must be no damage to the bulkhead liner below.
2 A bulkhead segment attachment post must not be visible.
(2) Accept all bulkhead segments
(Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1)
(Ref. Fig. Combustion Chamber Bulkhead Segment Burn Hole SHEET 1)
with an inspection each 600 hours if:
(a) There is one bulkhead segment burn-through hole more than 2 in. (50.80 mm) but less than 3 in.
(76.20 mm) in length and the following conditions are met:
1 There must be no damage to the bulkhead liner below.
2 A bulkhead segment attachment post must not be visible.
(b) There are multiple bulkhead segment burn-through holes more than 1 in. (25.40 mm) but less
than 1.50 in. (38.10 mm) in length and the following conditions are met:
1 There must be no damage to the bulkhead liner below.
2 A bulkhead segment attachment post must not be visible.
(3) Accept all bulkhead segments with an inspection each 300 hours if:
(Ref. Fig. Combustion Chamber Bulkhead Segment Attachment Post Visibility SHEET 1)
(a) One attachment post is visible up to 50 percent in one or more bulkhead segments.
(4) All bulkhead segments, remove the engine in less than 30 cycles and tell your IAE representative if:
(Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1)
(Ref. Fig. Combustion Chamber Bulkhead Segment Burn Hole SHEET 1)
(Ref. Fig. Combustion Chamber Bulkhead Segment Attachment Post Visibility SHEET 1)
(a) There is one bulkhead segment burn-through hole that is more than 3 in. (76.20 mm) in length.
(b) There are multiple bulkhead segment burn-through holes that are more than 1.50 in. (38.10 mm)
in length.
(c) There is a bulkhead liner burn-through hole that is more than 0.50 in.2 (322.58 mm2) in area.
(d) One attachment post is visible more than 50 percent in one or more bulkhead segments.
(e) More than one attachment post is visible on one or more bulkhead segment.
Subtask 72-00-00-220-076-A
R. Bulkhead Deflector Cracks
(1) Accept all bulkhead deflectors
(Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1)
(Ref. Fig. Combustion Chamber Bulkhead Deflector Cracks and Burnback SHEET 1)
without a decreased borescope inspection time if:
(a) There are cracks that are not circumferential.
(b) There are circumferential cracks that can cause material less than 0.500in. (12.7 mm) in length to
break off.
(2) All bulkhead deflectors,
(Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1)
(Ref. Fig. Combustion Chamber Bulkhead Deflector Cracks and Burnback SHEET 1)
remove the engine in less than 30 cycles and tell your IAE representative if:
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 64 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
(a) There is a circumferential crack than can cause material more than 0.500 in. (12.7 mm) in length
to break off.
Subtask 72-00-00-220-139-A
S. Bulkhead Deflector Burns
(Ref. Fig. Combustion Chamber Bulkhead Deflector Cracks and Burnback SHEET 1)
(Ref. Fig. Bulkhead Deflector Burnback)
(1) Accept all bulkhead deflectors without a decreased borescope time if:
(a) There are surface burns or base material burns that are less than the full deflector thickness
or there are full material thickness burns that are less than 0.280 in. (7.112 mm) from the
combustion air holes.
(2) Accept all bulkhead deflectors with an inspection each 1000 hours if:
(a) There are full material thickness burns between 0.230 in. (5.842 mm) and 0.280 in. (7.112 mm)
from the combustion air holes.
(3) Accept all bulkhead deflectors with an inspection each 500 hours if:
(a) There are full material thickness burns between 0.180 in. (4.572 mm) and 0.230 in. (5.842 mm)
from the combustion air holes.
(4) Accept all bulkhead deflectors with an inspection each 250 hours if:
(a) There are full material thickness burns between 0.130 in. (3.30 mm) and 0.180 in. (4.572 mm)
from the combustion air holes.
(b) There is localized burning in a "V" notch pattern with the point of the "V" directed toward and on a
radial line with the combustion air holes on the deflector radially inward to 0.080 in. (2.032 mm) of
the combustion air holes.
(c) There are full material thickness burns that are less than 0.130 in. (3.30 mm) from the
combustion air holes, but do not go into the combustion air holes. This burning can extend for
a maximum of 180 degrees around the circumference of the deflector. This is acceptable for
a maximum of four locations around the circumference of the combustor. Deflectors with this
condition must be separated by a minimum of three deflectors with full material thickness burns
that are more than 0.130 in. (3.30 mm) from the combustion air holes. It is not acceptable at the
igniter location or the locations adjacent to the igniters.
(5) All bulkhead deflectors, remove the engine in less than 30 cycles and tell your IAE representative if:
(a) There are burns that are more than the limits given above.
Subtask 72-00-00-220-106-A
T. End Cap Heatshield Damage on the Fuel Nozzles
(Ref. Fig. Fuel Nozzle End Cap Inspection Areas SHEET 1)
(Ref. Fig. Fuel Nozzle End Cap Inspection Areas SHEET 1)
(Ref. Fig. Fuel Nozzle Types of Damage SHEET 1)
(1) Accept the fuel nozzle if:
(a) The clearance between the end cap and the nozzle is fully closed.
(b) There is no limit to the number of radial and circumferential cracks in the end cap heatshield.
(c) Some or all of the end cap segments are broken away.
(2) Replace the fuel nozzle if:
(a) There are cracks, distortion, erosion or other damage on the areas adjacent to the end cap
heatshield.
5. Close-up
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 65 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Subtask 72-00-00-410-090-A
A. Close the Borescope Inspection Ports
PRE SBE 72-0221
(1) Close the borescope inspection ports, after the borescope inspection is completed, as follows:
(Ref. Fig. Borescope Ports (PRE SBE 72-0221) SHEET 1)
(a) For the B1 thru B5 ports:
1 Lubricate the plug (2) threads using anti-seize paste (Material No. V10-129) or anti-seize
compound (Material No. V10-094). Wipe off excess paste.
NOTE: It is permissible to correct minor thread damage to a threaded hole with a 0.5625-
18UNJF-3B die.
2 Install the plugs and the IPC -CSN (72-42-10-81-010) gasket (1).
3 TORQUE the plugs to between 70 and 80 lbf.in (0.79 and 0.90 m.daN)
(Ref. AMM TASK 70-23-11-911-013) .
4 Safety the plugs with corrosion resistant steel lockwire (Material No. V02-141).
(b) For the IP1 and IP2 ports:
1 Install the igniter plugs (Ref. AMM TASK 74-21-41-400-010) .
POST SBE 72-0221
(2) Close the borescope inspection ports, after the borescope inspection is completed, as follows:
(Ref. Fig. Borescope Ports (POST SBE 72-0221) SHEET 1)
(a) For the B1 thru B6 ports:
1 Lubricate the plug (2) threads using anti-seize paste (Material No. V10-129) or anti-seize
compound (Material No. V10-094). Wipe off excess paste.
NOTE: It is permissible to correct minor thread damage to a threaded hole with a 0.5625-
18UNJF-3B die.
2 Install the plugs and the IPC -CSN (72-42-10-81-010) gasket (1).
3 TORQUE the plugs to between 70 and 80 lbf.in (0.79 and 0.90 m.daN)
(Ref. AMM TASK 70-23-11-911-013) .
4 Safety the plugs with corrosion resistant steel lockwire (Material No. V02-141).
(b) For the IP1 and IP2 ports:
1 Install the igniter plugs (Ref. AMM TASK 74-21-41-400-010) .
END OF SBE 72-0221
Subtask 72-00-00-410-094-A
B. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser halves (Ref. AMM TASK 78-32-00-410-010) :
(a) FOR 1000EM1 (ENGINE-1)
451AL, 452AR
(b) FOR 1000EM2 (ENGINE-2)
461AL, 462AR
Subtask 72-00-00-410-132-A
Customer : F2I
Type : A318/A319/A320/A321
Rev. Date : May 01, 2018
Manual : AMM
Selected applicability : 358-358
72-00-00-200-013-A - Borescope Inspection of inside
of Combustion Chamber and HP turbine stage 1 Vanes
Print Date: August 09, 2018 Page 66 of 66
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
C. Close Access
(1) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010) :
(a) FOR 1000EM1 (ENGINE-1)
437AL, 438AR
(b) FOR 1000EM2 (ENGINE-2)
447AL, 448AR
(2) Remove the warning notice(s).
End of document

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Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes.pdf

  • 1. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 1 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. ** ON A/C 051-100, 201-250, 351-400, 601-650 TASK 72-00-00-200-013-A Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes CAUTION: THE LIMITS WHICH FOLLOW ARE APPLICABLE ON A CONTINUE IN SERVICE BASIS ONLY. EACH LIMIT IS BASED ON WHAT THE STRUCTURE OF THE BLADE MUST BE AND DOES NOT INDICATE THAT THERE WILL NOT BE DETERIORATION OF THE ENGINE PERFORM- ANCE, STABILITY, OPERATING LIMITS OR PART REPAIRABILITY. FIN : 1000EM1 , 1000EM2 1. Reason for the Job Refer to the MPD TASK: 724000-I1 BORESCOPE INSPECTION OF INSIDE OF COMBUSTION CHAMBER AND HP TURBINE STAGE 1 VANES This task gives the procedure for the borescope inspection of the combustion chamber and the HPT first stage vanes. 2 Job Set-up Information A. Fixtures, Tools, Test and Support Equipment REFERENCE QTY DESIGNATION No specific AR BORESCOPE - FLEXIBLE No specific AR BORESCOPE - RIGHT ANGLE, FLEXSCOPE No specific AR COVER - EYE No specific AR WARNING NOTICE(S) No specific Torque wrench: range to between 70 and 80 lbf.in (0.79 and 0.90 m.daN) B. Consumable Materials REFERENCE DESIGNATION (Material No. V02-141) corrosion resistant steel lockwire (Material No. V10-094) anti-seize compound (Material No. V10-129) anti-seize paste C. Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION FOR 1000EM1 (ENGINE-1) 437AL, 438AR, 451AL, 452AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR, 461AL, 462AR D. Expendable Parts FIG.ITEM DESIGNATION IPC-CSN 1 gasket 72-42-10-81-010
  • 2. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 2 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. E. Referenced Information REFERENCE DESIGNATION (Ref. 70-23-11-911-013-A). General Torque Tightening Techniques (Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR) (Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR) (Ref. 72-00-00-200-014-A). Borescope Inspection of the Stage 1 High Pressure Turbine (HPT) Blades and Duct Segments (Ref. 74-21-41-000-010-A). Removal of the Igniter Plug (Ref. 74-21-41-400-010-A). Installation of the Igniter Plug (Ref. 78-30-00-040-012-A). Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance (Ref. 78-32-00-010-010-A). Opening of the Thrust Reverser Halves (Ref. 78-32-00-410-010-A). Closing of the Thrust Reverser Halves Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Left Side) (PRE SBE 72-0221) SHEET 1 Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Right Side) (PRE SBE 72-0221) SHEET 1 Borescope Inspection Ports for the First Stage Vanes and the Combustion Chamber Liner (PRE SBE 72- 0221) SHEET 1 Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (Left Side) (POST SBE 72-0221) SHEET 1 Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (Right Side) (POST SBE 72-0221) SHEET 1 Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (POST SBE 72-0221) SHEET 1 HPT 1st Stage Vane Area Names and Dimensional References HPT 1ST Stage Vane Area Names and Dimensional References SHEET 1 HPT 1st Stage Vane Area Names and Dimensional References HPT 1st Stage vane Area Names and Dimensional References HPT 1st Stage Vane Area Names and Types of Damage HPT 1st Stage Vane Area Names and Types of Damage Combustion Chamber Area Names SHEET 1 Inner Combustion Chamber Liner Dimensions References SHEET 1 Outer Combustion Chamber Liner Segments Dimensions References SHEET 1 Combustion Chamber Liner Segments Borescope Inspection Guidelines SHEET 1 Borescope Ports (PRE SBE 72-0221) SHEET 1 Borescope Ports (POST SBE 72-0221) SHEET 1 Combustion Chamber Damage Form SHEET 1 Combustion Chamber Damage Form SHEET 1 Combustion Chamber Damage Form SHEET 1 Combustion Chamber Damage Form SHEET 1 Combustion Chamber Damage Form SHEET 1 Combustion Chamber Damage Form SHEET 1 Combustion Chamber Damage Form SHEET 1 Combustion Chamber Damage Form SHEET 1 Combustion Chamber Damage Form SHEET 1 Combustion Chamber Damage Form SHEET 1 Combustion Chamber Damage Form SHEET 1 Combustion Chamber Liner Segment Crack Limits SHEET 1
  • 3. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 3 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. REFERENCE DESIGNATION Combustion Chamber Liner Segment Burn Limits SHEET 1 Combustion Chamber Liner Segment Attachment Post Visibility SHEET 1 Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1 Combustion Chamber Bulkhead Segment Burn Hole SHEET 1 Combustion Chamber Bulkhead Segment Attachment Post Visibility SHEET 1 Combustion Chamber Bulkhead Deflector Cracks and Burnback SHEET 1 Bulkhead Deflector Burnback Fuel Nozzle End Cap Inspection Areas SHEET 1 Fuel Nozzle End Cap Inspection Areas SHEET 1 Fuel Nozzle Types of Damage SHEET 1
  • 4. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 4 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 11629B B4 B3 B2 B1 A A N_MM_720000_6_XRM0_01_00 Figure 72(IAE)-00-00-991-16200-13-A / SHEET 1/1 - Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Left Side) (PRE SBE 72-0221) ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 5. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 5 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 11630C B5 IP1 IP2 A A N_MM_720000_6_XTM0_01_00 Figure 72(IAE)-00-00-991-16300-13-A / SHEET 1/1 - Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Right Side) (PRE SBE 72-0221) ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 6. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 6 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. IP1 IP2 B4 B3 B2 B1 B5 TDC COMBUSTION CHAMBER PORTS VIEV WHEN YOU LOOK FROM THE REAR OF THE ENGINE IGNITER POINTS 11632D N_MM_720000_6_XVM0_01_00 Figure 72(IAE)-00-00-991-16400-13-A / SHEET 1/1 - Borescope Inspection Ports for the First Stage Vanes and the Combustion Chamber Liner (PRE SBE 72-0221) ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 7. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 7 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. B8617 B5 B4 B3 B2 B1 A A N_MM_720000_6_YBM0_01_00 Figure 72(IAE)-00-00-991-25700-13-A / SHEET 1/1 - Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (Left Side) (POST SBE 72-0221) ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 8. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 8 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. B6 IP1 IP2 B8618 A A N_MM_720000_6_YDM0_01_00 Figure 72(IAE)-00-00-991-25800-13-A / SHEET 1/1 - Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (Right Side) (POST SBE 72-0221) ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 9. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 9 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. IP1 IP2 B5 B4 B3 B1 B6 TDC COMBUSTION CHAMBER PORTS VIEW WHEN YOU LOOK FROM THE REAR OF THE ENGINE IGNITER PORTS B8634 B2 N_MM_720000_6_YHM0_01_00 Figure 72(IAE)-00-00-991-25900-13-A / SHEET 1/1 - Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (POST SBE 72-0221) ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 10. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 10 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. AIR HOLES AIRFOIL COOLING LEADING EDGE OUTER PLATFORM (2,540 mm) 0.100 in. INNER PLATFORM TRAILING EDGE TRAILING EDGE SLOT LEADING EDGE COOLING AIR HOLES PLATFORM (46,99 mm) 1.850 in. 0.150 in. COOLING AIR HOLES PLATFORM 1/4 CHORD 1/2 CHORD 3/4 CHORD 2.100 in. (53,34 mm) FULL CHORD 1.700 in. (43,18 mm) INNER PLATFORM LEADING EDGE PWZXX11640E CONCAVE AIRFOIL VIEW (3,81 mm) N_MM_720000_6_XZM0_01_00 Figure 72(IAE)-00-00-991-16600-13-A / SHEET 1/2 - HPT 1st Stage Vane Area Names and Dimensional References ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 11. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 11 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. AXIAL RADIAL CONCAVE AIRFOIL VIEW pwzxxb8894a SBE 72-0340 INNER PLATFORM LEADING EDGE LEADING EDGE PLATFORM COOLING AIR HOLES PLATFORM COOLING AIR HOLES OUTER PLATFORM LEADING EDGE TRAILING EDGE INNER PLATFORM TRAILING EDGE 1/2 CHORD 1/4 CHORD 3/4 CHORD AIRFOIL COOLING AIR HOLES 0.100in. (2.540mm) 2.100in. (53.34mm) FULL CHORD 0.200in. (5.080mm) 1.700in. (43.18mm) N_MM_720000_6_XZM0_02_00 Figure 72(IAE)-00-00-991-16600-13-A / SHEET 2/2 - HPT 1st Stage Vane Area Names and Dimensional References ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 12. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 12 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 0.200in (5,08mm) CONVEX AIRFOIL VIEW TRAILING EDGE TRAILING EDGE OUTER PLATFORM INNER PLATFORM TRAILING EDGE 11641D 1.200in (30,48mm) AIR HOLES AIRFOIL COOLING LEADING EDGE N_MM_720000_6_YAM0_01_00 Figure 72(IAE)-00-00-991-16700-13-A / SHEET 1/1 - HPT 1ST Stage Vane Area Names and Dimensional References ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 13. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 13 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. LEADING EDGE OUTER PLATFORM LEADING EDGE INNER PLATFORM LEADING EDGE JUNCTION OF AIRFOIL TO PLATFORM FILLET RADIUS AREA AXIAL RADIAL CONCAVE AIRFOIL VIEW SEEN THROUGH THE BORESCOPE 11907D TRAILING EDGE SLOT WIDTH 0.080 in (2.03 mm) N_MM_720000_6_YCM0_01_00 Figure 72(IAE)-00-00-991-16800-13-A / SHEET 1/2 - HPT 1st Stage Vane Area Names and Dimensional References ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 14. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 14 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. SBE 72-0340 AXIAL RADIAL B8902 CONCAVE AIRFOIL VIEW SEEN THROUGH THE BORESCOPE LEADING EDGE OUTER PLATFORM LEADING EDGE INNER PLATFORM LEADING EDGE TRAILING EDGE JUNCTION OF AIRFOIL TO PLATFORM FILLET RADIUS AREA 0.080in. (2.03mm) SLOT WIDTH N_MM_720000_6_YCM0_02_00 Figure 72(IAE)-00-00-991-16800-13-A / SHEET 2/2 - HPT 1st Stage Vane Area Names and Dimensional References ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 15. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 15 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. LEADING EDGE RADIAL WITH MISSING METAL LEADING EDGE HOLE PATTERN AREA BURN WITH TRAILING MISSING METAL EDGE INNER PLATFORM LEADING EDGE AXIAL LEADING EDGE OUTER PLATFORM 11908B CONCAVE AIRFOIL VIEW AS SEEN THROUGH THE BORESCOPE BURN HOLE N_MM_720000_6_YEM0_01_00 Figure 72(IAE)-00-00-991-16900-13-A / SHEET 1/2 - HPT 1st Stage vane Area Names and Dimensional References ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 16. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 16 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. SBE 72-0340 AXIAL RADIAL B8903 CONCAVE AIRFOIL VIEW SEEN THROUGH THE BORESCOPE LEADING EDGE TRAILING EDGE INNER PLATFORM LEADING EDGE MISSING METAL AXIAL CRACK WITH BURN OUTER PLATFORM LEADING EDGE AXIAL CRACK CONCAVE SURFACE AREA N_MM_720000_6_YEM0_02_00 Figure 72(IAE)-00-00-991-16900-13-A / SHEET 2/2 - HPT 1st Stage vane Area Names and Dimensional References ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 17. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 17 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. CONCAVE SURFACE AREA LEADING EDGE LEADING EDGE OUTER PLATFORM AXIAL CRACK TRAILING EDGE BURN WITH MISSING MATERIAL TRAILING EDGE INNER PLATFORM MISSING METAL INNER PLATFORM LEADING EDGE AXIAL CRACK WITH BURN AXIAL RADIAL PWZXX11909C CONCAVE AIRFOIL VIEW AS SEEN THROUGH THE BORESCOPE N_MM_720000_6_YGM0_01_00 Figure 72(IAE)-00-00-991-17000-13-A / SHEET 1/3 - HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 18. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 18 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. TRAILING EDGE BURNS LEADING EDGE BURNS BAFFLE TRAILING EDGE EXPOSED (ONE SIDE OF VANE ONLY) BURN THROUGH BURNING BURN THROUGH (MISSING MATERIAL) LEADING VANE EDGE EDGE LEADING BAFFLE FIVE ROWS LEADING EDGE COOLING HOLES (ONE SIDE OF VANE ONLY) BURN THROUGH BURNING LEADING EDGE BURNS TRAILING EDGE BURNS E2346 CONCAVE AIRFOIL VIEW SEEN THROUGH BORESCOPE A A B B N_MM_720000_6_YGM0_02_00 Figure 72(IAE)-00-00-991-17000-13-A / SHEET 2/3 - HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 19. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 19 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. SBE 72-0340 AXIAL RADIAL pwzxxb8894a CONCAVE AIRFOIL VIEW SEEN THROUGH THE BORESCOPE LEADING EDGE HOLE PATTERN AREA LEADING EDGE OUTER PLATFORM LEADING EDGE BURN HOLE WITH MISSING METAL INNER PLATFORM LEADING EDGE TRAILING EDGE BURN WITH MISSING METAL INNER PLATFORM TRAILING EDGE BURN WITH MISSING METAL N_MM_720000_6_YGM0_03_00 Figure 72(IAE)-00-00-991-17000-13-A / SHEET 3/3 - HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 20. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 20 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PLATFORM LEADING EDGE OUTER PLATFORM FILLET RADIUS CRACK PLATFORM - TO - AIRFOIL TRAILING EDGE CONNECTED LOOP CRACK LEADING EDGE PARALLEL CRACK INNER PLATFORM LEADING EDGE FILLET RADIUS AIRFOIL SECTION A-A 11910B CONCAVE AIRFOIL VIEW AS SEEN THROUGH THE BORESCOPE A A N_MM_720000_6_YJM0_01_00 Figure 72(IAE)-00-00-991-17100-13-A / SHEET 1/3 - HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 21. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 21 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. SBE 72-0340 B8905 CONCAVE AIRFOIL VIEW SEEN THROUGH THE BORESCOPE A-A SECTION AIRFOIL PLATFORM FILLET RADIUS A A LEADING EDGE TRAILING EDGE OUTER PLATFORM LEADING EDGE CONNECTED LOOP CRACK INNER PLATFORM LEADING EDGE PARALLEL CRACK PLATFORM - TO AIRFOIL FILLET RADIUS CRACK N_MM_720000_6_YJM0_02_00 Figure 72(IAE)-00-00-991-17100-13-A / SHEET 2/3 - HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 22. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 22 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. SBE 72-0340 CONCAVE AIRFOIL VIEW SEEN THROUGH BORESCOPE E2347 B A LEADING EDGE BURNS TRAILING EDGE BURNS VANE LEADING EDGE LEADING EDGE BAFFLE BURNING BURN THROUGH (ONE SIDE OF VANE ONLY) FIVE ROWS LEADING EDGE COOLING HOLES B LEADING EDGE BURNS BURN THROUGH (ONE SIDE OF VANE ONLY) BURNING TRAILING EDGE BAFFLE EXPOSED BURN THROUGH (MISSING MATERIAL) A TRAILING EDGE BURNS N_MM_720000_6_YJM0_03_00 Figure 72(IAE)-00-00-991-17100-13-A / SHEET 3/3 - HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 23. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 23 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PWXXX19752C ROW 1 ROW 2 ROW 3 ROW 4 ROW 5 ROW 5 ROW 4 ROW 3 ROW 2 ROW 1 COMBUSTION CHAMBER OUTER LINER SEGMENT OUTER LINER SHELL COMBUSTION CHAMBER INNER LINER SHELL SEGMENT INNER LINER BULKHEAD DEFLECTOR FUEL NOZZLE BULKHEAD SEGMENT BULKHEAD BULKHEAD SEGMENT POST ATTACHMENT A A N_MM_720000_6_YLM0_01_00 Figure 72(IAE)-00-00-991-17200-13-A / SHEET 1/1 - Combustion Chamber Area Names ** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
  • 24. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 24 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. pwzxx11901e PWV ROW 1 ROW 2 ROW 3 ROW 4 ROW 5 VIEW OF THE INNER COMBUSTION CHAMBER SEGMENTS N_MM_720000_6_YNM0_01_01 Figure 72(IAE)-00-00-991-17300-13-A / SHEET 1/1 - Inner Combustion Chamber Liner Dimensions References ** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
  • 25. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 25 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. pwzxx11906e PWV VIEW OF THE OUTER COMBUSTION CHAMBER SEGMENTS ROW 5 ROW 4 ROW 3 ROW 2 ROW 1 IGNITER HOLES BULKHEAD DEFLECTOR BULKHEAD SEGMENT IGNITER SEGMENT N_MM_720000_6_YPM0_01_01 Figure 72(IAE)-00-00-991-17400-13-A / SHEET 1/1 - Outer Combustion Chamber Liner Segments Dimensions References ** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
  • 26. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 26 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. CIRCUMFERENTIAL EDGE MISSING MATERIAL CIRCUMFERENTIAL LENGTH AXIAL LENGTH TRAILING EDGE SEGMENT TRAILING EDGE BURNBACK NOTE: SEGMENT DAMAGE ASPECT RATIO: CIRCUMFERENTIAL AXIAL MORE THAN 2 CIRCUMFERENTIAL EDGE MISSING MATERIAL CIRCUMFERENTIAL LENGTH AXIAL LENGTH TRAILING EDGE B8881 BURN HOLE INCREASE TO SEGMENT TRAILING EDGE NOTE: SEGMENT DAMAGE ASPECT RATIO: CIRCUMFERENTIAL AXIAL LESS THAN OR EQUAL TO 2 N_MM_720000_6_YAR0_01_00 Figure 72(IAE)-00-00-991-23100-13-A / SHEET 1/1 - Combustion Chamber Liner Segments Borescope Inspection Guidelines ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 27. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 27 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. SECTION (B1 THRU B5) DETAIL AT 5 POSITIONS BUSHING IGNITOR PLUG COMBUSTION CHAMBER OUTER LINER SHELL SECTION (IP1 AND IP2 PORTS) DETAILS AT 2 POSITIONS 11633C OUTER LINER SEGMENT COMBUSTION CHAMBER 1 GASKET 2 PLUG B-B A-A N_MM_720000_6_XXM0_01_00 Figure 72(IAE)-00-00-991-16500-13-A / SHEET 1/1 - Borescope Ports (PRE SBE 72-0221) ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 28. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 28 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. B8625A CAUTION: DO NOT MOVE THE SPACERS OR THE INSERT INSERT IGNITOR PLUG COMBUSTION CHAMBER OUTER LINER SHELL SECTION (IP1 AND IP2 PORTS) DETAILS AT 2 POSITIONS B-B SPACER (0 TO 2 AS NECESSARY) SECTION (B1 THRU B6) DETAIL AT 6 POSITIONS 1 GASKET 2 PLUG A-A OUTER LINER SEGMENT COMBUSTION CHAMBER A A A A N_MM_720000_6_YMM0_01_00 Figure 72(IAE)-00-00-991-26100-13-A / SHEET 1/1 - Borescope Ports (POST SBE 72-0221) ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 29. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 29 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 7 FLOW ROW 5 ROW 1 ROW 2 ROW 3 ROW 4 B5491 INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED FUEL NOZZLE No. BORESCOPE INSPECTION REPORTING FORM AIRLINE DATE ENGINE NUMBER HOURS CYCLES OBL ROW IGNITER SEGMENT 8 FUEL NOZZLE No. N_MM_720000_6_YGN0_01_00 Figure 72(IAE)-00-00-991-21700-13-A / SHEET 1/1 - Combustion Chamber Damage Form ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 30. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 30 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. FLOW ROW 5 ROW 1 ROW 2 ROW 3 ROW 4 B5492 FUEL NOZZLE No. INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED FUEL NOZZLE No. FUEL NOZZLE No. BORESCOPE INSPECTION REPORTING FORM AIRLINE DATE ENGINE NUMBER HOURS CYCLES OBL ROW FUEL NOZZLE No. N_MM_720000_6_YHN0_01_00 Figure 72(IAE)-00-00-991-21800-13-A / SHEET 1/1 - Combustion Chamber Damage Form ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 31. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 31 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. BORESCOPE INSPECTION REPORTING FORM AIRLINE ENGINE NUMBER HOURS DATE CYCLES OBL ROW SEGMENT NUMBER INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED FLOW B5493 1 IGNITER SEGMENT 4 N_MM_720000_6_YJN0_01_00 Figure 72(IAE)-00-00-991-21900-13-A / SHEET 1/1 - Combustion Chamber Damage Form ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 32. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 32 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. BORESCOPE INSPECTION REPORTING FORM AIRLINE ENGINE NUMBER HOURS DATE CYCLES OBL ROW SEGMENT NUMBER INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED FLOW B5494 2 N_MM_720000_6_YKN0_01_00 Figure 72(IAE)-00-00-991-22000-13-A / SHEET 1/1 - Combustion Chamber Damage Form ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 33. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 33 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. BORESCOPE INSPECTION REPORTING FORM AIRLINE ENGINE NUMBER HOURS DATE CYCLES OBL ROW SEGMENT NUMBER INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED FLOW B5495 3 N_MM_720000_6_YLN0_01_00 Figure 72(IAE)-00-00-991-22100-13-A / SHEET 1/1 - Combustion Chamber Damage Form ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 34. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 34 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. BORESCOPE INSPECTION REPORTING FORM AIRLINE ENGINE NUMBER HOURS DATE CYCLES OBL ROW SEGMENT NUMBER INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED FLOW B5496 4 N_MM_720000_6_YMN0_01_00 Figure 72(IAE)-00-00-991-22200-13-A / SHEET 1/1 - Combustion Chamber Damage Form ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 35. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 35 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. FLOW ROW 5 ROW 1 ROW 2 ROW 3 ROW 4 B5497 FUEL NOZZLE No. INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED FUEL NOZZLE No. FUEL NOZZLE No. BORESCOPE INSPECTION REPORTING FORM AIRLINE DATE ENGINE NUMBER HOURS CYCLES IBL ROW FUEL NOZZLE No. N_MM_720000_6_YNN0_01_00 Figure 72(IAE)-00-00-991-22300-13-A / SHEET 1/1 - Combustion Chamber Damage Form ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 36. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 36 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. BORESCOPE INSPECTION REPORTING FORM AIRLINE ENGINE NUMBER HOURS DATE CYCLES IBL ROW SEGMENT NUMBER INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED FLOW B5498 2 N_MM_720000_6_YPN0_01_00 Figure 72(IAE)-00-00-991-22400-13-A / SHEET 1/1 - Combustion Chamber Damage Form ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 37. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 37 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. BORESCOPE INSPECTION REPORTING FORM AIRLINE ENGINE NUMBER HOURS DATE CYCLES IBL ROW SEGMENT NUMBER INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED FLOW B5499 3 N_MM_720000_6_YQN0_01_00 Figure 72(IAE)-00-00-991-22500-13-A / SHEET 1/1 - Combustion Chamber Damage Form ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 38. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 38 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. BORESCOPE INSPECTION REPORTING FORM AIRLINE ENGINE NUMBER HOURS DATE CYCLES IBL ROW SEGMENT NUMBER INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED FLOW B8502 4 N_MM_720000_6_YRN0_01_00 Figure 72(IAE)-00-00-991-22600-13-A / SHEET 1/1 - Combustion Chamber Damage Form ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 39. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 39 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. BORESCOPE INSPECTION REPORTING FORM AIRLINE ENGINE NUMBER HOURS DATE CYCLES OBL ROW IBL ROW SEGMENT NUMBER SEGMENT NUMBER INCLUDE DIMENSIONS WHERE POSSIBLE FOR ALL DAMAGE REPORTED FLOW B8503 N_MM_720000_6_YSN0_01_00 Figure 72(IAE)-00-00-991-22700-13-A / SHEET 1/1 - Combustion Chamber Damage Form ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 40. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 40 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (CAN NOT BE SEEN) IGNITER RAIL EDGE CIRCUMFERENTIAL 0.750in (19,050mm) (REFERENCE) EDGE BURNBACK IGNITER RAIL BURNBACK MISSING MATERIAL EDGE BURNBACK MISSING MATERIAL EDGE TRAILING SEGMENT EDGE BURNBACK - OBL NO.1 IGNITER SEGMENT (CAN NOT BE SEEN) IGNITER RAIL CUTAWAY VIEW ATTACHMENT POST, (TYPICAL) A A 45° 45° IGNITER RAIL BURNBACK AND IGNITER HOLE EDGE BURNS LIMITED A TO AREAS AS GIVEN IN INSPECTION LIMITS PWZXXB8886A EDGE CIRCUMFERENTIAL EDGE BURNBACK MISSING MATERIAL MISSING MATERIAL EDGE TRAILING SEGMENT EDGE BURNBACK - OBL NO.1 THAT IS NOT AN IGNITER SEGMENT N_MM_720000_6_YDR0_01_00 Figure 72(IAE)-00-00-991-23300-13-A / SHEET 1/1 - Combustion Chamber Liner Segment Crack Limits ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 41. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 41 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. CIRCUMFERENTIAL EDGE MISSING MATERIAL EDGE BURNBACK MISSING MATERIAL EDGE BURNBACK MISSING MATERIAL TRAILING EDGE SEGMENT EDGE BURNBACK THAT HAVE OR DO NOT HAVE COMBUSTION HOLE RIM (EXAMPLE) COMBUSTION HOLE RIM BURNBACK CIRCUMFERENTIAL EDGE MISSING MATERIAL BURN HOLE LONGEST DIMENSION TRAILING EDGE MISSING MATERIAL BURNS THAT LOOK LIKE THEY COULD CAUSE MATERIAL TO BREAK OFF B8887 SEGMENT BURN HOLE - OBL AND IBL SEGMENTS THAT HAVE OR DO NOT HAVE COMBUSTION HOLES COMBUSTION HOLES, OBL NO. 2 THROUGH OBL NO. 5 AND IBL NO. 1 THROUGH IBL NO. 5 N_MM_720000_6_YER0_01_00 Figure 72(IAE)-00-00-991-23400-13-A / SHEET 1/1 - Combustion Chamber Liner Segment Burn Limits ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 42. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 42 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. pwzxxe9341 PWV ATTACHMENT POST CUTAWAY VIEW (TYPICAL) MISSING COATING LEADING EDGE DIA 4.826 mm (0.19 in) POST VISIBLE < 50% POST VISIBLE > 50% A A N_MM_720000_6_XBP0_01_00 Figure 72(IAE)-00-00-991-53700-13-A / SHEET 1/1 - Combustion Chamber Liner Segment Attachment Post Visibility ** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
  • 43. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 43 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. BULKHEAD SEGMENT INSPECTION AREAS BULKHEAD SEGMENT CRACKS CRACK SEPARATION PWZXXB8882A BULKHEAD DEFLECTOR SLOT LENGTH 0.300 in (7,620 mm) (REFERENCE) BULKHEAD CRACK CRACKS WHICH LOOK LIKE THEY WILL GO THROUGH EACH OTHER AND CAUSE MATERIAL TO BREAK OFF BULKHEAD DEFLECTOR BULKHEAD SEGMENT 0.600 in (15,240 mm) (REFERENCE) (12,065 mm) (REFERENCE) 0.475 in BULKHEAD DEFLECTOR AIRHOLE CIRCLE 1.375 in (34,925 mm) (REFERENCE) N_MM_720000_6_YCN0_01_00 Figure 72(IAE)-00-00-991-21000-13-A / SHEET 1/ 1 - Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
  • 44. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 44 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. BURN HOLE LONGEST DIMENSION (MISSING MATERIAL) BULKHEAD SEGMENT BURN HOLE B8883 N_MM_720000_6_YCR0_01_00 Figure 72(IAE)-00-00-991-23200-13-A / SHEET 1/1 - Combustion Chamber Bulkhead Segment Burn Hole ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 45. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 45 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. pwzxxe9342a PW V PANEL BURN BACK POST VISIBLE < 50% BULKHEAD SHELL POST VISIBLE > 75% > 50% EXPOSURE OF THIS STUD IS NOT ALLOWED SHELL BURNING/CRACKING AT ATTACHMENT POST HOLE NOT ALLOWED N_MM_720000_6_XBQ0_01_01 Figure 72(IAE)-00-00-991-53800-13-A / SHEET 1/1 - Combustion Chamber Bulkhead Segment Attachment Post Visibility ** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
  • 46. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 46 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. BULKHEAD DEFLECTOR CRACKS CRACKS WHICH LOOK LIKE THEY WILL GO THROUGH EACH OTHER AND CAUSE MATERIAL TO BREAK OFF DEFLECTOR CRACK CIRCUMFERENTIAL CRACK DEFLECTOR EDGE BURNBACK MISSING MATERIAL MISSING MATERIAL BULKHEAD DEFLECTOR BURNBACK pwzxxb8884e N_MM_720000_6_YBR0_01_00 Figure 72(IAE)-00-00-991-23000-13-A / SHEET 1/1 - Combustion Chamber Bulkhead Deflector Cracks and Burnback ** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
  • 47. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 47 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. DISTANCE FROM COMBUSTION AIR HOLE TO EDGE OF BURN BACK. MISSING MATERIAL COMBUSTION AIR HOLE DIAMETER IS 0.076in. (1.93mm) (REFERENCE) "V" NOTCH BURNING BULKHEAD DEFLECTOR BURNBACK MISSING MATERIAL COMBUSTION AIR HOLE DIAMETER IS 0.076in. (1.93mm) (REFERENCE) BULKHEAD DEFLECTOR BURNBACK pwzxxe7554 N_MM_720000_6_XAA0_01_00 Figure 72(IAE)-00-00-991-19900-13-A / SHEET 1/2 - Bulkhead Deflector Burnback ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 48. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 48 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. INCREASED LIMITS AS DESCRIBED IN STEP (C), AT INSPECTION OF 250 HOURS DO NOT APPLY AT THESE FOUR LOCATIONS. INCREASED LIMITS APPLY AT ANY OF THE OTHER 16 LOCATIONS IF THE MINIMUM SEPARATION REQUIREMENTS ARE MET. SCHEMATIC REAR VIEW IGNITER LOCATIONS pwzxxe2485a DEFLECTORS WITH BURNS THAT ARE LESS THAN 0.130in. (3.302mm) FROM THE COMBUSTION AIR HOLES MUST BE SEPARATED BY A MINIMUM OF THREE DEFLECTORS WITH BURNS THAT ARE MORE THAN 0.130in. (0.320mm) FROM THE COMBUSTION AIR HOLES. N_MM_720000_6_XAA0_02_00 Figure 72(IAE)-00-00-991-19900-13-A / SHEET 2/2 - Bulkhead Deflector Burnback ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 49. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 49 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 0.400 in. (10,16mm) REFERENCE NO DAMAGE IS PERMITTED END CAP CLEARANCE HEATSHIELD PWYXX19842A NO DAMAGE IS PERMITTED A N_MM_720000_6_XZN0_01_00 Figure 72(IAE)-00-00-991-20800-13-A / SHEET 1/1 - Fuel Nozzle End Cap Inspection Areas ** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
  • 50. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 50 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 9 RADIAL CRACKS CIRCUMFERENTIAL CRACKS END CAP HEAT SHIELD SECTIONS THAT ARE BROKEN AWAY 19843A A A A N_MM_720000_6_YAN0_01_00 Figure 72(IAE)-00-00-991-20900-13-A / SHEET 1/1 - Fuel Nozzle End Cap Inspection Areas ** ON A/C 051-100, 201-250, 351-400, 601-650
  • 51. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 51 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PWZXX19756C (FUEL NOZZLE) 0.020in (0,51mm) WIDTH (REFERENCE) CRACK C C BURN-BACK QUADRANT 0.180in (4,57mm) SLOT SECTION C-C FUEL NOZZLE 0.020in (0,51mm) (REFERENCE) COMBUSTION CHAMBER (WHEN YOU LOOK FORWARD AT THE 12 O'CLOCK POSITION) BORESCOPE VIEW B END CAP HEATSHIELD END CAP HEATSHIELD FUEL NOZZLE END CAP HEATSHIELD CLEARANCE GAP B N_MM_720000_6_YRM0_01_00 Figure 72(IAE)-00-00-991-29800-13-A / SHEET 1/1 - Fuel Nozzle Types of Damage ** ON A/C 051-102, 104-110, 151-250, 351-400, 451-550, 601-650
  • 52. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 52 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 3. Job Set-up Subtask 72-00-00-941-078-A A. Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes 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) pushbutton switch is off. (b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2). Subtask 72-00-00-010-112-A B. Open the fan cowls (Ref. AMM TASK 71-13-00-010-010) : (1) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (2) FOR 1000EM2 (ENGINE-2) 447AL, 448AR Subtask 72-00-00-040-066-A C. Deactivate the Thrust Reverser WARNING: THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) MUST BE DEACTIV- ATED BEFORE WORKING ON OR AROUND THE THRUST REVERSER. FAILURE TO DEACTIVATE THE HCU CAN RESULT IN INADVERTENT THRUST REVERSER OPERA- TION AND INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT. (1) Deactivate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-040-012) . Subtask 72-00-00-010-110-A D. Open the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010) : (1) FOR 1000EM1 (ENGINE-1) 451AL, 452AR (2) FOR 1000EM2 (ENGINE-2) 461AL, 462AR 4. Procedure Subtask 72-00-00-290-059-A CAUTION: THE ENGINE IS HOT IMMEDIATELY AFTER SHUTDOWN AND CAN CAUSE BURNS AND DAMAGE TO THE BORESCOPE EQUIPMENT. WAIT 2-3 HOURS AFTER SHUTDOWN BE- FORE YOU DO A BORESCOPE INSPECTION. A. General PRE SBE 72-0221 (1) There are five borescope ports and two ignitor ports to give access to the combustion chamber and the HPT stage 1 vanes. (Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Left Side) (PRE SBE 72-0221) SHEET 1)
  • 53. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 53 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Right Side) (PRE SBE 72-0221) SHEET 1) (Ref. Fig. Borescope Inspection Ports for the First Stage Vanes and the Combustion Chamber Liner (PRE SBE 72-0221) SHEET 1) POST SBE 72-0221 (2) There are six borescope ports and two igniter ports give access to the combustion chamber and the HPT stage 1 vanes. (Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (Left Side) (POST SBE 72-0221) SHEET 1) (Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (Right Side) (POST SBE 72-0221) SHEET 1) (Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (POST SBE 72-0221) SHEET 1) END OF SBE 72-0221 (3) The names of different parts and dimensional references of the combustion chamber and the HPT 1st stage vanes are shown. (Ref. Fig. HPT 1st Stage Vane Area Names and Dimensional References) (Ref. Fig. HPT 1ST Stage Vane Area Names and Dimensional References SHEET 1) (Ref. Fig. HPT 1st Stage Vane Area Names and Dimensional References) (Ref. Fig. HPT 1st Stage vane Area Names and Dimensional References) (Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage) (Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage) (Ref. Fig. Combustion Chamber Area Names SHEET 1) (Ref. Fig. Inner Combustion Chamber Liner Dimensions References SHEET 1) (Ref. Fig. Outer Combustion Chamber Liner Segments Dimensions References SHEET 1) Use these names when identifying borescope inspection limits. (4) Use these terms when you identify a combustion chamber condition seen during borescope inspection: (a) BURN: A local area of burner liner segment, bulkhead segment, or deflector surface that has changed colour, has a rough surface texture or shows thinner material because of high temperatures. Burns can be located all around but more are found downstream of combustion holes in the burner liner segments. (b) BURN HOLE: A local burn area that has continued through the base material and does not extend to the leading or trailing edge of the segment. (Ref. Fig. Combustion Chamber Liner Segments Borescope Inspection Guidelines SHEET 1) (c) EDGE BURNBACK: Full thickness liner segment burns that start at an edge, occur more at the segment trailing edge location but have also occurred at the leading edge. Burnback is segment material that is missing. Complete edge burnback is when segment material is missing from the trailing edge to the leading edge. (Ref. Fig. Combustion Chamber Liner Segments Borescope Inspection Guidelines SHEET 1) (d) RADIAL BURNBACK: Full thickness burning on deflector edge continuing radially inward toward fuel nozzle. (5) General inspection guidelines: (a) Give the results of decreased time inspections to your IAE representative. (b) If a piece of combustion chamber materials breaks off between inspection times, a borescope inspection of the high pressure turbine is necessary. If the high pressure turbine is not damaged after the material breaks off you can continue the combustion chamber borescope inspections at the times given by other limits. (c) All spalled ceramic coating on the combuster segments, the bulkhead segments or the bulkhead deflectors is acceptable without a decreased borescope inspection time.
  • 54. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 54 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (d) Bulkhead and liner segments: Any coating loss on the bulkhead/liner segment due to cracks is not considered material liberation or break off. Material liberation or break off is defined as the coating loss along with the bulkhead/liner segment parent material missing. (6) Use these terms when you identify an HPT 1st stage vane condition seen during borescope inspection: (a) BURNS: A local area of 1st stage vane surface that has changed colour, has a rough surface texture or shows thinner material because of high temperature. Burns can be located all around. (b) BURN THROUGH: A local burn area that has continued through the airfoil surface. Cracks that have burned to more than 0.050 in. (1.27 mm) separation are also burn through. (c) TRAILING EDGE BURNS: Burns or burn through that start at the airfoil trailing edge and continue forward to the airfoil leading edge. (d) LIFT UP: An area where the surface on one side of a crack is higher than the surface on the other side of the crack. (e) COATING DAMAGE: Chips, spalling, flakes, blisters, peeling or oxidation that is confined to the coating. (f) CONNECTED LOOP CRACK: A crack or a group of cracks that show an isolated area of vane metal. (g) LEADING EDGE: The area from the first row of cooling holes on the concave side of the vane to the first row of cooling holes on the convex side of the vane. (7) General inspection guidelines: (a) Give the results of decreased time inspections to your IAE representative. (b) All ceramic coating damage is acceptable without a decreased borescope inspection time. Extended operation with a large quantity of ceramic coating not there can possibly cause the vane to be out of limits and cannot be repaired at overhaul. Subtask 72-00-00-010-093-A B. Get Access to the Combustion Chamber and the HPT 1st Stage Vanes PRE SBE 72-0221 (1) Get access to the combustion chamber and the HPT 1st stage vanes through the B1 to B5 and IP1 and IP2 ports as follows: (a) For the B1 to B5 ports, remove the 5 plugs and gaskets at the locations shown. (Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Left Side) (PRE SBE 72-0221) SHEET 1) (Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Right Side) (PRE SBE 72-0221) SHEET 1) (Ref. Fig. Borescope Ports (PRE SBE 72-0221) SHEET 1) (b) For the IP1 and IP2 ports, remove the igniter plugs (Ref. AMM TASK 74-21-41-000-010) . (Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Right Side) (PRE SBE 72-0221) SHEET 1) (Ref. Fig. Borescope Ports (PRE SBE 72-0221) SHEET 1) NOTE: Do not remove the igniter insert. (Ref. Fig. Borescope Ports (PRE SBE 72- 0221) SHEET 1) POST SBE 72-0221 (2) Get access to the combustion chamber and the HPT 1st stage vanes through the B1 to B6 and IP1 and IP2 ports as follows: (a) For the B1 to B6 ports, remove the 6 plugs and gaskets at the locations shown.
  • 55. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 55 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (Left Side) (POST SBE 72-0221) SHEET 1) (Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (Right Side) (POST SBE 72-0221) SHEET 1) (Ref. Fig. Borescope Ports (POST SBE 72-0221) SHEET 1) (b) For the IP1 and IP2 ports, remove the igniter plugs (Ref. AMM TASK 74-21-41-000-010) . (Ref. Fig. Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 Vanes (Right Side) (POST SBE 72-0221) SHEET 1) (Ref. Fig. Borescope Ports (POST SBE 72-0221) SHEET 1) NOTE: Do not remove the igniter insert. (Ref. Fig. Borescope Ports (POST SBE 72- 0221) SHEET 1) END OF SBE 72-0221 Subtask 72-00-00-290-060-A C. Examine the combustion chamber, fuel injectors and the first stage vanes for damage CAUTION: THE LIMITS WHICH FOLLOW ARE APPLICABLE ON A CONTINUE IN SERVICE BASIS ONLY. EACH LIMIT IS BASED ON WHAT THE STRUCTURE OF THE BLADE MUST BE AND DOES NOT INDICATE THAT THERE WILL NOT BE DETERIORATION OF THE EN- GINE PERFORMANCE, STABILITY, OPERATING LIMITS OR PART REPAIRABILITY. (1) Put the BORESCOPE - RIGHT ANGLE, FLEXSCOPE or BORESCOPE - FLEXIBLE in to the ports and examine the combustion chamber, fuel injectors and the first stage vanes for damage. (Ref. Fig. Borescope Ports (PRE SBE 72-0221) SHEET 1) NOTE: An COVER - EYE is recommended on the eye that is not used, to decrease eye tension. (2) If damage seen is not listed, contact your IAE representative. Subtask 72-00-00-220-101-A D. Convex and Concave Surface Cracks/Burns (Ref. Fig. HPT 1st Stage Vane Area Names and Dimensional References) (Ref. Fig. HPT 1st Stage vane Area Names and Dimensional References) (Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage) Pre SBE 72-0340 SBE 72-0340 NOTE: All cracks or sections of cracks burned to a width of more than 0.050 in. (1.27 mm) are burn holes. Use the applicable burn limits. NOTE: If a convex or a concave burn extends to the leading edge, you must use leading edge criteria. (1) Accept with an inspection each 600 hours if: (a) There is more than one axial crack 3/4 chord length or longer. Axial and radial cracks can go through each other. (b) There are many radial cracks that are more than 1.500 in. (38.1 mm) in length. Axial cracks can go through radial cracks. (c) There is a burn that has caused a burn through that is between 0.050 in. (1.27 mm) and 0.100 in. (2.54 mm) at its shortest dimension. (2) Accept with an inspection each 300 hours if:
  • 56. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 56 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (a) There is a burn that has caused a burn through that is between 0.100 in. (2.54 mm) and 0.30 in. (7.62 mm) at its shortest dimension. (3) Remove the engine in less than 10 cycles and tell your IAE representative if: (a) There is axial or radial crack lift up of more than 0.050 in. (1.27 mm). (b) There are connected loop cracks that show a piece of vane metal that is calculated to be more than 0.500 in. (12.7 mm) in length. (c) There is a crack that is three-quarters of a chord length long or longer that also goes in to a leading edge or a convex surface burn through. (d) There is a burn that has caused a burn through that is more than 0.300 in. (7.62 mm) at its shortest dimension. Subtask 72-00-00-220-064-A E. Leading Edge Cracks and Leading Edge Burns (Ref. Fig. HPT 1st Stage vane Area Names and Dimensional References) Pre SBE 72-0340 SBE 72-0340 NOTE: There is no limit to the number of leading edge tight cracks permitted without decreased inspection times. (1) Accept with an inspection each 600 hours if: (a) There are leading edge cracks and burns that have caused base vane material burn through within the leading edge cooling holes and it measures less than 0.85 in. (21.59 mm) in length radially. (2) Accept with an inspection each 300 hours if: (a) There is leading edge base vane material burn through that extends less than 0.20 in. (5.08 mm) beyond the first row of leading edge cooling air holes and it measures less than 0.65 in. (16.51 mm) axially and 0.85 in. (21.59 mm) radially. (3) Accept with an inspection each 75 hours if: (a) There is leading edge base vane material burn through that extends less than 0.25 in. (6.35 mm) beyond the first row of leading edge cooling holes and it measures less than 0.65 in. (16.51 mm) axially and 0.85 in. (21.59 mm) radially. (4) Remove the engine in less than 10 cycles and tell your IAE representative if: (a) There is leading edge base vane material burn through that extends more than 0.25 in. (6.35 mm) beyond the leading edge cooling air holes. (b) There is leading edge base vane material burn through of more than 0.85 in. (21.59 mm) radially. (c) There is leading edge base vane material burn through of more than 0.65 in. (16.51 mm) axially. (d) There is axial trailing edge base vane material burn through and/or a crack that measures more than three quarters of the cord length. (e) There is axial leading edge base vane material burn through plus a crack that measures three quarters of the cord length. (f) There is baffle burn-through. (g) There is baffle cracking. Subtask 72-00-00-220-065-A F. Trailing Edge Burns (Ref. Fig. HPT 1st Stage vane Area Names and Dimensional References)
  • 57. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 57 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage) Pre SBE 72-0340 SBE 72-0340 (1) Accept with an inspection each 600 hours if: (a) There is a burn through that goes between one quarter and one half of the chord length from the trailing edge and is more than 0.500 in. (12.7 mm) in width at the trailing edge. NOTE: 0.500 in. (12.7 mm) is equal to five trailing edge cooling air slots. (2) Accept with an inspection each 300 hours if: (a) There is a burn through that goes between one half and three quarters of the chord length from the trailing edge and is more than 0.500 in. (12.7 mm) in width at the trailing edge. NOTE: 0.500 in. (12.7 mm) is equal to five trailing edge cooling air slots. (3) Remove the engine in less than 10 cycles and tell your IAE representative if: (a) There is a burn through that goes more than three quarters of the chord length from the trailing edge and is more than 0.500 in. (12.7 mm) in width at the trailing edge. NOTE: 0.500 in. (12.7 mm) is equal to five trailing edge cooling air slots. (b) There is a trailing edge burn through inboard of the first two trailing edge cooling slots. Subtask 72-00-00-220-066-A G. Cracks on the Inner and Outer Platforms (Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage) Pre SBE 72-0340 SBE 72-0340 (1) Accept with an inspection each 600 hours if: (a) There is a crack that is more than 0.500 in. (12.7 mm) in length. (2) Accept with an inspection each 300 hours if: (a) There is a crack that is more than 1.000 in. (25.4 mm) in length. (3) Remove the engine in less than 10 cycles and tell your IAE representative if: (a) There is a crack that is parallel to the airfoil fillet radius, that goes around the airfoil leading edge and that is more than 1.500 in. (38.1mm) in length. Subtask 72-00-00-220-067-A H. Cracks on the Inner and Outer Platform Airfoil Fillet Radius (Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage) Pre SBE 72-0340 SBE 72-0340 (1) Accept with an inspection each 600 hours if: (a) There is a fillet crack that is more than 1.000 in. (25.4 mm) in length and that goes from the fillet on to the airfoil. (2) Remove the engine in less than 10 cycles and tell your IAE representative if: (a) There is a crack that is more than 1.000 in. (25.4 mm) in length and a part of the length is eroded to a width of more than 0.030 in. (0.76 mm).
  • 58. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 58 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (b) There is a crack in the fillet radius that is more than 1.500 in. (38.1 mm) in length and that goes around the airfoil leading edge. Subtask 72-00-00-220-138-A J. Burns on the Inner and Outer Platforms (Ref. Fig. HPT 1st Stage Vane Area Names and Types of Damage) Pre SBE 72-0340 SBE 72-0340 (1) Accept with an inspection each 600 hours if: (a) There are burns that go from the edge of the platform to the platform airfoil fillet. (2) Accept with an inspection each 300 hours if: (a) There are burns that have caused a burn through that is less than 0.250 in. (6.35 mm) in length. (3) Remove the engine in less than 10 cycles and tell your IAE representative if: (a) There are burns that have caused a burn through that is more than 0.250 in. (6.35 mm) in length. Subtask 72-00-00-220-068-A K. Make a record of the damage that you find when you do a borescope inspection of the combustion chamber (1) Use the Combustion Chamber Damage Forms to record the damage. (Ref. Fig. Combustion Chamber Damage Form SHEET 1) (Ref. Fig. Combustion Chamber Damage Form SHEET 1) (Ref. Fig. Combustion Chamber Damage Form SHEET 1) (Ref. Fig. Combustion Chamber Damage Form SHEET 1) (Ref. Fig. Combustion Chamber Damage Form SHEET 1) (Ref. Fig. Combustion Chamber Damage Form SHEET 1) (Ref. Fig. Combustion Chamber Damage Form SHEET 1) (Ref. Fig. Combustion Chamber Damage Form SHEET 1) (Ref. Fig. Combustion Chamber Damage Form SHEET 1) (Ref. Fig. Combustion Chamber Damage Form SHEET 1) (Ref. Fig. Combustion Chamber Damage Form SHEET 1) Subtask 72-00-00-220-069-A L. Burner liner segment cracks (1) Accept inner and outer burner liner segments that have combustion holes without a decreased borescope inspection time if: (a) There are two cracks completely through a segment in the axial direction and each crack goes through combustion holes that are separated by a combustion hole without a crack. (b) There are two cracks completely through a segment in the axial direction and one of the cracks goes through a combustion hole and the other crack is separated by a combustion hole and is not less than 0.700 in. (17.8 mm) from a circumferential edge. (2) Accept inner and outer burner liner segments that do not have combustion holes without a decreased borescope inspection time if: (a) There is one crack completely through axially that is more than 0.700 in. (17.8 mm) from a circumferential edge. (3) Accept inner and outer burner liner segments that have combustion holes with an inspection each 600 hours if: (a) There are two or more cracks downstream of a combustion hole, one of the cracks goes from the combustion hole to the trailing edge and no other crack goes more than half the distance to the same combustion hole or trailing edge.
  • 59. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 59 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (4) Accept inner and outer burner liner segments that do not have combustion holes with an inspection each 600 hours if: (a) There are two or more axial cracks, one crack is completely through the segment and is more than 0.700 in. (17.8 mm) from a circumferential edge. No other crack is more than half the axial length of the segment or nearer than 0.700 in. (17.8 mm) to a circumferential edge. (5) Accept inner and outer burner liner segments that have combustion holes with an inspection each 300 hours if: NOTE: You must also do a borescope inspection of the stage 1 HPT blades (Ref. AMM TASK 72- 00-00-200-014) each 300 hours if the liner segments are on a 300-hour repeat borescope in- spection for segment cracking. (a) There are 2, 3 or 4 cracks completely through axially, and each crack goes through a combustion hole and at least two cracks go through adjacent combustion holes. (b) There are two or more cracks downstream of a combustion hole, one crack goes from a combustion hole to the trailing edge and no other crack goes more than two thirds of the distance to the same combustion hole or trailing edge (c) There are cracks that can cause a piece of segment material up to 0.250 in.2 (161.29 mm.2) in area to break off. NOTE: Material break off is defined as the coating loss along with the liner segment parent ma- terial missing. (6) Accept inner and outer burner liner segments that do not have combustion holes with an inspection each 300 hours if: NOTE: You must also do a borescope inspection of the stage 1 HPT blades (Ref. AMM TASK 72- 00-00-200-014) each 300 hours if the liner segments are on a 300-hour repeat borescope in- spection for segment cracking. (a) There are two or more axial cracks, one crack is completely through the segment and is more than 0.700 in. (17.8 mm) from a circumferential edge. No other crack is more than two thirds the axial length of the segment or nearer than 0.700 in. (17.78 mm) to a circumferential edge. (b) There are cracks that can cause a piece of segment material up to 0.250 in.2 (161.29 mm.2) in area to break off. NOTE: Material break off is defined as the coating loss along with the liner segment parent ma- terial missing. (7) All segments, remove the engine in less than 30 cycles and tell your IAE representative if: (a) There are cracks that can cause a piece of segment material more than 0.250 in.2 (161.29 mm.2) in area to break off. NOTE: Material break off is defined as the coating loss along with the liner segment parent ma- terial missing. Subtask 72-00-00-220-070-A M. Segment Edge Burnback (1) Accept segments without a decreased borescope inspection if: (a) There is edge burnback of less than 0.70 in. (17.78 mm) and the following conditions are met:
  • 60. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 60 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 1 There is no liner shell damage (burn-through or cracks). 2 There is damage to the rails around the igniter holes on the row 1 igniter segment less than 135 degrees. 3 You must not be able to see an attachment post. (2) Accept segments with an inspection each 600 hours if: (a) The edge burnback is between 0.70 in. (17.78 mm) and 0.90 in. (22.86 mm) and the following conditions are met: 1 There is no liner shell damage (burn-through or cracks). 2 There is damage to the rails around the igniter holes on the row 1 igniter segment less than 135 degrees. 3 You must not be able to see an attachment post. (3) Accept segments with an inspection each 300 hours if: (a) The edge burnback is more than 0.90 in. (22.86 mm) and the following conditions are met: 1 Liner shell damage (burn-through or cracks) must not have an area of more than 0.50 in.2 (322.58 mm2). 2 There is damage to the rails around the igniter holes on the row 1 igniter segment less than 135 degrees. 3 One attachment post is visible up to 50 percent in one or more liner segments. NOTE: A maximum of three liner shell damage locations for each burner assembly is al- lowed. (4) If the edge burnback is more than 1 in. (25.40 mm), you must also do a borescope inspection of the stage 1 HPT blades each 300 hours. (5) All segments, (Ref. Fig. Combustion Chamber Liner Segment Crack Limits SHEET 1) remove the engine in less than 30 cycles and tell your IAE representative if: (a) There is complete edge burnback on one segment and another area of edge burnback more than 1 in. (25.40 mm) on the same segment. (b) There are two or more segments with complete edge burnback. Refer to for burnback inspection limits which need engine removal in less than 30 cycles. (c) There is damage to the rails around the igniter holes on the row 1 igniter segment more than 135 degrees. (Ref. Fig. Combustion Chamber Liner Segment Crack Limits SHEET 1) (d) There is edge burnback that shows an attachment post more than 50 percent or an attachment post is missing. (e) There is liner shell damage (burn-through or cracks) that is more than 0.500 in.2 (322.58 mm2) in area or there are more than three locations of liner shell damage less than 0.500 in.2 (322.58 mm2) in all the burner assembly. Subtask 72-00-00-220-071-A N. Surface Burns and Burn-Through Holes in Liner Segments (1) Accept segments (with or without combustion holes) (Ref. Fig. Combustion Chamber Liner Segment Burn Limits SHEET 1) without a decreased borescope inspection time if: (a) As much as all the surface is burned.
  • 61. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 61 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (b) There are segment burn-through holes that are less than 0.35 in. (8.89 mm) in length and the following conditions are met: 1 There must be no liner shell damage (burns, burn-through, cracks). 2 There is damage to the rails around the igniter holes on the row 1 igniter segment less than 135 degrees. 3 You must not be able to see an attachment post. (2) Accept segments (with or without combustion holes) (Ref. Fig. Combustion Chamber Liner Segment Burn Limits SHEET 1) with an inspection each 600 hours if: (a) There is a segment burn-through hole that is between 0.35 in. (8.89 mm) and 0.65 in. (16.51 mm) in length and the following conditions are met: 1 There must be no liner shell damage (burns, burn-through, cracks). 2 There is damage to the rails around the igniter holes on the row 1 igniter segment less than 135 degrees. 3 You must not be able to see an attachment post. (3) Accept segments (with or without combustion holes) (Ref. Fig. Combustion Chamber Liner Segment Burn Limits SHEET 1) (Ref. Fig. Combustion Chamber Liner Segment Attachment Post Visibility SHEET 1) with an inspection each 300 hours if: (a) There is a segment burn-through hole that is between 0.65 in. (16.51 mm) and 1 in. (25.40 mm) in length and the following conditions are met: 1 Liner shell damage (burns, burn-through, cracks) must not have an area of more than 0.50 in.2 (322.58 mm2). 2 Liner shell damage (burns, burn-through, cracks) must not occur in more than three locations. 3 There is damage to the rails around the igniter holes on the row 1 igniter segment less than 135 degrees. 4 One attachment post is visible up to 50 percent in one or more liner segments. (b) There are segment burns or cracks that can cause a piece of segment material more than 0.50 in. (12.70 mm) in length to break off. (4) Segments (with or without combustion holes), (Ref. Fig. Combustion Chamber Liner Segment Crack Limits SHEET 1) (Ref. Fig. Combustion Chamber Liner Segment Attachment Post Visibility SHEET 1) remove the engine in less than 30 cycles and tell your IAE representative if: (a) There is a segment burn-through hole that is more than 1 in. (25.40 mm) in length. (b) There is damage to the rails around the igniter holes on the row 1 igniter segment more than 135 degrees. (c) One attachment post is visible more than 50 percent in one or more liner segments. (d) More than one attachment post is visible on one or more liner segment. (e) There is liner shell damage (burns, burn-through, cracks) that is more than 0.500 in.2 (322.58 mm2) in area or occurs in more than three locations that are less than 0.500 in.2 (322.58 mm2) in area. Subtask 72-00-00-220-074-A P. Bulkhead Segment Cracks
  • 62. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 62 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (1) Accept all bulkhead segments without a reduced inspection if: (Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1) (a) There is no more than one crack on any side of a bulkhead segment. There is no limit to the length of the crack. (b) There are two or more cracks on the same side of a bulkhead segment, less than 0.375 in. (9.52 mm). (2) Accept all bulkhead segments with a 600-hour repeat borescope inspection if: (Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1) (a) There are two or more cracks more than 0.375 in. (9.52 mm) on the same side of any bulkhead segment. (3) Accept all bulkhead segments with a 300-hour repeat borescope inspection if: (Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1) NOTE: You must also do a borescope inspection of the stage 1 HPT blades (Ref. AMM TASK 72-00- 00-200-014) each 300 hours if the combustor is on a 300-hour repeat borescope inspection for bulkhead segment cracking. (a) There are cracks that may liberate a piece of material equal to or less than 0.25 in.2 (161.29 mm2). NOTE: Material liberation is defined as the coating loss along with the segment parent material missing. (b) There are two or more cracks on the same side of any bulkhead segment. At least one crack extends from the edge of the bulkhead segment under the fuel nozzle guide or to the inner rim of the bulkhead segment, and another is at least 0.375 in. (9.52 mm). These cracks must be separated by less than 0.50 in. (12.70 mm). (4) Remove the engine in less than 30 cycles if: (Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1) (a) There are cracks that may liberate a piece of material more than 0.25 in.2 (161.29 mm2). NOTE: Material liberation is defined as the coating loss along with the segment parent material missing. (b) There are two or more cracks on the same side of any bulkhead segment. At least one crack extends from the edge of the bulkhead segment under the fuel nozzle guide or to the inner rim of the bulkhead segment, and another is at least 0.375 in. (9.52 mm). These cracks must be separated by more than 0.50 in. (12.70 mm). Subtask 72-00-00-220-075-A Q. Bulkhead Segment Burns and burn-through holes (1) Accept all bulkhead segments (Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1) (Ref. Fig. Combustion Chamber Bulkhead Segment Burn Hole SHEET 1) without a decreased borescope inspection time if: (a) As much as all the surface is burned. (b) There is one bulkhead segment burn-through hole less than 2 in. (50.80 mm) in length and the following conditions are met: 1 There must be no damage to the bulkhead liner below.
  • 63. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 63 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 2 A bulkhead segment attachment post must not be visible. (c) There are multiple bulkhead segment burn-through holes less than 1 in. (25.40 mm) in length and the following conditions are met: 1 There must be no damage to the bulkhead liner below. 2 A bulkhead segment attachment post must not be visible. (2) Accept all bulkhead segments (Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1) (Ref. Fig. Combustion Chamber Bulkhead Segment Burn Hole SHEET 1) with an inspection each 600 hours if: (a) There is one bulkhead segment burn-through hole more than 2 in. (50.80 mm) but less than 3 in. (76.20 mm) in length and the following conditions are met: 1 There must be no damage to the bulkhead liner below. 2 A bulkhead segment attachment post must not be visible. (b) There are multiple bulkhead segment burn-through holes more than 1 in. (25.40 mm) but less than 1.50 in. (38.10 mm) in length and the following conditions are met: 1 There must be no damage to the bulkhead liner below. 2 A bulkhead segment attachment post must not be visible. (3) Accept all bulkhead segments with an inspection each 300 hours if: (Ref. Fig. Combustion Chamber Bulkhead Segment Attachment Post Visibility SHEET 1) (a) One attachment post is visible up to 50 percent in one or more bulkhead segments. (4) All bulkhead segments, remove the engine in less than 30 cycles and tell your IAE representative if: (Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1) (Ref. Fig. Combustion Chamber Bulkhead Segment Burn Hole SHEET 1) (Ref. Fig. Combustion Chamber Bulkhead Segment Attachment Post Visibility SHEET 1) (a) There is one bulkhead segment burn-through hole that is more than 3 in. (76.20 mm) in length. (b) There are multiple bulkhead segment burn-through holes that are more than 1.50 in. (38.10 mm) in length. (c) There is a bulkhead liner burn-through hole that is more than 0.50 in.2 (322.58 mm2) in area. (d) One attachment post is visible more than 50 percent in one or more bulkhead segments. (e) More than one attachment post is visible on one or more bulkhead segment. Subtask 72-00-00-220-076-A R. Bulkhead Deflector Cracks (1) Accept all bulkhead deflectors (Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1) (Ref. Fig. Combustion Chamber Bulkhead Deflector Cracks and Burnback SHEET 1) without a decreased borescope inspection time if: (a) There are cracks that are not circumferential. (b) There are circumferential cracks that can cause material less than 0.500in. (12.7 mm) in length to break off. (2) All bulkhead deflectors, (Ref. Fig. Liner (Bulkhead) Segment Inspection Areas and Cracks SHEET 1) (Ref. Fig. Combustion Chamber Bulkhead Deflector Cracks and Burnback SHEET 1) remove the engine in less than 30 cycles and tell your IAE representative if:
  • 64. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 64 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (a) There is a circumferential crack than can cause material more than 0.500 in. (12.7 mm) in length to break off. Subtask 72-00-00-220-139-A S. Bulkhead Deflector Burns (Ref. Fig. Combustion Chamber Bulkhead Deflector Cracks and Burnback SHEET 1) (Ref. Fig. Bulkhead Deflector Burnback) (1) Accept all bulkhead deflectors without a decreased borescope time if: (a) There are surface burns or base material burns that are less than the full deflector thickness or there are full material thickness burns that are less than 0.280 in. (7.112 mm) from the combustion air holes. (2) Accept all bulkhead deflectors with an inspection each 1000 hours if: (a) There are full material thickness burns between 0.230 in. (5.842 mm) and 0.280 in. (7.112 mm) from the combustion air holes. (3) Accept all bulkhead deflectors with an inspection each 500 hours if: (a) There are full material thickness burns between 0.180 in. (4.572 mm) and 0.230 in. (5.842 mm) from the combustion air holes. (4) Accept all bulkhead deflectors with an inspection each 250 hours if: (a) There are full material thickness burns between 0.130 in. (3.30 mm) and 0.180 in. (4.572 mm) from the combustion air holes. (b) There is localized burning in a "V" notch pattern with the point of the "V" directed toward and on a radial line with the combustion air holes on the deflector radially inward to 0.080 in. (2.032 mm) of the combustion air holes. (c) There are full material thickness burns that are less than 0.130 in. (3.30 mm) from the combustion air holes, but do not go into the combustion air holes. This burning can extend for a maximum of 180 degrees around the circumference of the deflector. This is acceptable for a maximum of four locations around the circumference of the combustor. Deflectors with this condition must be separated by a minimum of three deflectors with full material thickness burns that are more than 0.130 in. (3.30 mm) from the combustion air holes. It is not acceptable at the igniter location or the locations adjacent to the igniters. (5) All bulkhead deflectors, remove the engine in less than 30 cycles and tell your IAE representative if: (a) There are burns that are more than the limits given above. Subtask 72-00-00-220-106-A T. End Cap Heatshield Damage on the Fuel Nozzles (Ref. Fig. Fuel Nozzle End Cap Inspection Areas SHEET 1) (Ref. Fig. Fuel Nozzle End Cap Inspection Areas SHEET 1) (Ref. Fig. Fuel Nozzle Types of Damage SHEET 1) (1) Accept the fuel nozzle if: (a) The clearance between the end cap and the nozzle is fully closed. (b) There is no limit to the number of radial and circumferential cracks in the end cap heatshield. (c) Some or all of the end cap segments are broken away. (2) Replace the fuel nozzle if: (a) There are cracks, distortion, erosion or other damage on the areas adjacent to the end cap heatshield. 5. Close-up
  • 65. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 65 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. Subtask 72-00-00-410-090-A A. Close the Borescope Inspection Ports PRE SBE 72-0221 (1) Close the borescope inspection ports, after the borescope inspection is completed, as follows: (Ref. Fig. Borescope Ports (PRE SBE 72-0221) SHEET 1) (a) For the B1 thru B5 ports: 1 Lubricate the plug (2) threads using anti-seize paste (Material No. V10-129) or anti-seize compound (Material No. V10-094). Wipe off excess paste. NOTE: It is permissible to correct minor thread damage to a threaded hole with a 0.5625- 18UNJF-3B die. 2 Install the plugs and the IPC -CSN (72-42-10-81-010) gasket (1). 3 TORQUE the plugs to between 70 and 80 lbf.in (0.79 and 0.90 m.daN) (Ref. AMM TASK 70-23-11-911-013) . 4 Safety the plugs with corrosion resistant steel lockwire (Material No. V02-141). (b) For the IP1 and IP2 ports: 1 Install the igniter plugs (Ref. AMM TASK 74-21-41-400-010) . POST SBE 72-0221 (2) Close the borescope inspection ports, after the borescope inspection is completed, as follows: (Ref. Fig. Borescope Ports (POST SBE 72-0221) SHEET 1) (a) For the B1 thru B6 ports: 1 Lubricate the plug (2) threads using anti-seize paste (Material No. V10-129) or anti-seize compound (Material No. V10-094). Wipe off excess paste. NOTE: It is permissible to correct minor thread damage to a threaded hole with a 0.5625- 18UNJF-3B die. 2 Install the plugs and the IPC -CSN (72-42-10-81-010) gasket (1). 3 TORQUE the plugs to between 70 and 80 lbf.in (0.79 and 0.90 m.daN) (Ref. AMM TASK 70-23-11-911-013) . 4 Safety the plugs with corrosion resistant steel lockwire (Material No. V02-141). (b) For the IP1 and IP2 ports: 1 Install the igniter plugs (Ref. AMM TASK 74-21-41-400-010) . END OF SBE 72-0221 Subtask 72-00-00-410-094-A B. Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the thrust reverser halves (Ref. AMM TASK 78-32-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 451AL, 452AR (b) FOR 1000EM2 (ENGINE-2) 461AL, 462AR Subtask 72-00-00-410-132-A
  • 66. Customer : F2I Type : A318/A319/A320/A321 Rev. Date : May 01, 2018 Manual : AMM Selected applicability : 358-358 72-00-00-200-013-A - Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes Print Date: August 09, 2018 Page 66 of 66 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. C. Close Access (1) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (2) Remove the warning notice(s). End of document