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LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D ENGINE – HPT ROT OR
ASSEMBL Y (72 - 52 -
00) –
IMPROVED HPT ROT OR ST AGE 1 BLADE BSI INTER V ALS FOR INDIA REGION
SERVICE
BULLETIN T able of contents
1.
REVISION
INFORMA TION .
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3 A.
Revision reason .
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3 B.
Revision history .
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SUMMAR Y .
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3 A.
Reason .
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3.
PLANNING
INFORMA TION .
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3 A.
Applicability .
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3 B.
Concurrent requirements .
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3 C.
Reason .
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3 D.
Description .
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4 E.
Compliance .
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4 F .
Approval .
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5 G.
Manpower .
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5 H.
W eight and balance .
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5 I.
Electrical load data .
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5 J.
Software accomplishment summary .
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5 K.
Referenced documentation .
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5 L.
Documentation af fected .
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5 M.
Industry support information .
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5 N.
Interchangeability .
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4.
MA TERIAL
INFORMA TION .
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5.
ACCOMPLISHMENT
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6 A.Engine Cooldown .
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6 B.Safety Precautions .
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6 C.Get Access .
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7 D.Deactivation of the Thrust Reverser System for Maintenance .
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7 E.HPT BSI .
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7 F .Return Aircraft to Service .
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6.
ADDITIONAL
INFORMA TION .
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18 A.
Additional information .
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18 LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D Page 1/ 18 Issue 003 - 00 - 2025 - 07 - 30 © CFM
PROPRIET AR Y
INFORMA TION:
Subject to the restrictions on the media.
LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D List of tables T able:
Reasons for update .
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2 T able:
Support equipment .
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6 T able 1:
CFM Contact Information .
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18 List of figures Figure 1:
Location of HPT Rotor Stage 1 Blades Assemblies .
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10 Figure 2:
Example V iews With a
4.0 mm Borescope .
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1 1 Figure 3:
Example V iews With a
6.0 mm Borescope .
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12 Figure 4:
HPT Rotor Stage 1 Blade Cracks Example (Uninstalled) .
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13 Figure 5:
HPT Rotor Stage 1 Blade Cracks Example (Installed) .
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14 Figure 6 (Sheet 1/2):
HPT Rotor Stage 1 Blade BSI Example V iews .
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15 Figure 6 (Sheet 2/2):
HPT Rotor Stage 1 Blade BSI Example V iews .
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16 Figure 7:
HPT BSI Guidelines for Engines Paired on Same Aircraft .
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17 CFM
PROPRIET AR Y
INFORMA TION The information contained in this document is CFM proprietary information and is disclosed in confidence.
It is the property of CFM and shall not be used, disclosed to others or reproduced without the express written consent of CFM, including, but without limitation, it is not to be used in the creation, manufacture, development, or derivation of any repairs, modifications, spare parts, design, or configuration changes or to obtain F AA or any other government or regulatory approval to do so.
If consent is given for reproduction in whole or in part, this notice and the notice set forth on each page of this document shall appear in any such reproduction in whole or in part.
The information contained in this document may also be controlled by U.S.
export control laws.
Unauthorized export or re - export is prohibited.
Reasons for update T able:
Reasons for update [TECHNICAL] T o update paragraph
3.,
PLANNING
INFORMA TION.
References No References Management information Manufacturer recommendation:
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Recommended T ask type:
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Inspection Original issue date:
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2022 - 09 - 27 LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D Page 2/ 18 Issue 003 - 00 - 2025 - 07 - 30 © CFM
PROPRIET AR Y
INFORMA TION:
Subject to the restrictions on the media.
LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D
1.
REVISION
INFORMA TION A.
Revision reason Issue Number Revision Reason 001 Baseline.
002 T o update paragraph
5.,
ACCOMPLISHMENT INSTRUCTIONS.
003 T o update paragraph
3.,
PLANNING
INFORMA TION.
B.
Revision history Issue Number Issue Date 001 2022 - 09 - 27 002 2025 - 04 - 16
2.
SUMMAR Y A.
Reason T o improve reliability of the high pressure turbine (HPT) module airfoils on LEAP - 1A engines operating in the India region and reduce significant events.
3.
PLANNING
INFORMA TION A.
Applicability This Service Bulletin is applicable to:
• Engine type:
LEAP - 1A
• Engine model(s):
LEAP - 1A23,LEAP - 1A24,LEAP - 1A24E1,LEAP - 1A26,LEAP - 1A26CJ,LEAP - 1A26E1,LEAP - 1A29,LEAP - 1A29CJ,LEAP - 1A30,LEAP - 1A32,LEAP - 1A33,LEAP - 1A33B2,LEAP - 1A35A This Service Bulletin is applicable to all LEAP - 1A engines.
Engine models are defined as follows:
Group 1:
LEAP - 1A29, LEAP - 1A29CJ, LEAP - 1A30, LEAP - 1A32, LEAP - 1A33, LEAP - 1A33B2, and LEAP - 1A35A.
Group 2:
LEAP - 1A23, LEAP - 1A24, LEAP - 1A24E1, LEAP - 1A26, LEAP - 1A26CJ, and LEAP - 1A26E1.
The HPT rotor stage 1 blades P/N 2747M92P01, P/N 2553M91G03, P/N 2553M91G05, P/N 2553M91G06, P/N 2553M91G07, and P/N 2553M91G08 are af fected by this Service Bulletin.
B.
Concurrent requirements None.
C.
Reason
(1) Objective:
T o improve reliability of the HPT module airfoils on LEAP - 1A engines operating in the India region and reduce significant events.
(2) Condition:
LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D Page 3/ 18 Issue 003 - 00 - 2025 - 07 - 30 © CFM
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INFORMA TION:
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LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D The LEAP - 1A engines operating in the India region have exhibited HPT module airfoil distress at earlier cycle times.
(3) Cause:
Operating environment can make the HPT module airfoils more susceptible to cracking in the field.
(4) Inspection:
Shortened borescope inspection (BSI) interval of the HPT rotor stage 1 blades to examine distress on the airfoils.
(5) Substantiation:
Substantiation is by fleet experience.
Recommended inspection of the engines is more frequent than that published in the Maintenance Planning Document (MPD) (1,600 cycles).
D.
Description This Service Bulletin introduces reduced, targeted BSI intervals of the HPT rotor stage 1 blades for LEAP - 1A engines operating in the India region.
The India region includes:
Bangladesh, Bhutan, India, Maldives, Nepal, and Sri Lanka.
E.
Compliance Category 2 CFM recommends for HPT rotor stage 1 blades that have accumulated over 1,100 departures in the India region to do the following:
• For Group 1 thrust ratings:
- For HPT rotor stage 1 blades with more than 2,400 flight cycles since new , do the initial inspection as specified in paragraph
5.E.
within 100 flight cycles.
- For all other HPT rotor stage 1 blades, do the initial inspection as specified in paragraph
5.E.
before the HPT rotor stage 1 blades accumulate 2,500 flight cycles since new .
- Repeat the inspection specified in paragraph
5.E.
at an interval that does not exceed 150 cycles.
• For Group 2 thrust ratings:
- For HPT rotor stage 1 blades with more than 5,000 flight cycles since new , do the initial inspection as specified in paragraph
5.E.
within 100 flight cycles.
- For all other HPT rotor stage 1 blades, do the initial inspection as specified in paragraph
5.E.
before the HPT rotor stage 1 blades accumulate 5,100 flight cycles since new .
- Repeat the inspection specified in paragraph
5.E.
at an interval that does not exceed 300 cycles.
NOTE:
If the HPT rotor stage 1 blade departures are unknown, then perform this Service Bulletin on engines that have accumulated over 1,100 departures in the India region.
NOTE:
If the engine rating changes between Group 1 and Group 2, then follow the instruction for Group 1 thrust rating.
NOTE:
Inspections completed ahead of Service Bulletin issuance will be credited, provided the inspection was performed in accordance with the instructions contained within this Service Bulletin.
Impact B This recommendation is to address a condition that may result in an Increased Rate of In - Flight Shutdowns (IFSD), T ake - Of f Aborts (T OA), Air T urn Backs (A TB) or Diversions (DIV).
LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D Page 4/ 18 Issue 003 - 00 - 2025 - 07 - 30 © CFM
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LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D NOTE:
This Service Bulletin can be done on wing.
NOTE:
The Service Bulletin recommended targeted HPT rotor stage 1 blades inspections are in addition to the regularly scheduled MPD tasks.
This Service Bulletin is of fered to improve the reliability or performance of your CFM product, or to help prevent the occurrence of the event or condition described in this Service Bulletin.
If the operator elects not to participate in the bulletin, that decision will be taken into consideration by CFM in evaluating future product performance issues that may arise in the operator ’ s fleet.
F .
Approval The technical content of this Service Bulletin is approved by the F AA and under the Authority of DOA No.
EASA.21J.086.
G.
Manpower After you get access to the engine, you will need approximately 4 man - hours to do the inspection portion of this Service Bulletin.
H.
W eight and balance W eight and balance are not changed.
I.
Electrical load data Not Applicable.
J.
Software accomplishment summary Not Applicable.
K.
Referenced documentation Airbus A318/A319/A320/A321 Aircraft Maintenance Manual (AMM) L.
Documentation affected None.
M.
Industry support information None.
N.
Interchangeability Not Applicable.
4.
MA TERIAL
INFORMA TION List of material sets Not Applicable.
LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D Page 5/ 18 Issue 003 - 00 - 2025 - 07 - 30 © CFM
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LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D List of support equipment Support equipment Name T ool Number Reference (Qty) MFR Unit $ Price (Pkg Qty) L/T Standard T ools AR TICULA TING
BORESCOPE (4 mm or 6 mm diameter) - Not Applicable
(1) - - ( -) - NOTE:
Replenishment Lead T ime (L/T) in days.
NOTE:
Prices are provided for planning purposes and are subject to change.
List of supplies Not Applicable.
List of spares Not Applicable.
List of removed spares Not Applicable.
5.
ACCOMPLISHMENT
INSTRUCTIONS A.
Engine Cooldown W ARNING:
BE
CAREFUL WHEN YOU DO WORK ON THE ENGINE P AR TS AFTER THE ENGINE SHUTDOWN.
USE
APPLICABLE
THERMAL GLOVES.
THE ENGINE P AR TS CAN ST A Y HOT FOR ONE HOUR AFTER
SHUTDOWN AND CAN BURN YOU.
W ARNING:
REFER T O THE
PRODUCT LABEL AND THE MANUF ACTURER’S (MA
TERIAL) SAFETY DA T A SHEET (SDS) FOR
INSTRUCTIONS ON THE
HAZARDS, ST ORAGE, SAFE
HANDLING AND PROPER USE OF THIS
PRODUCT .
(1) If a faster cooldown is necessary , do a dry motoring for more than five minutes as soon as possible when the aircraft is grounded.
Refer to the Airbus A318/A319/A320/A321 AMM, 71 - 00 - 00,
ADJUSTMENT/TEST , T ASK 71 - 00 - 00 - 700 - 805 - A.
NOTE:
The dry motoring will help to cool down the engine.
B.
Safety Precautions
(1) On the center pedestal, on the ENG panel 1 15VU, do as follows:
(a) Make sure that the
ENG/MODE selector switch is in the NORM position.
(b) Make sure that the
ENG/MASTER 1(2) control switch was in the OFF position for a minimum of five minutes before you do this procedure.
(c) Put W ARNING
NOTICE(S) in position to tell persons not to operate in the locations that follow:
ENG/MODE selector switch.
ENG/MASTER 1(2) control switch.
LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D Page 6/ 18 Issue 003 - 00 - 2025 - 07 - 30 © CFM
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LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D
(2) On the ENG section of maintenance panel 50VU, do as follows:
(a) Make sure that the ON legend of the F ADEC GND PWR/1(2) push - button switch is of
f.
(b) Put W ARNING
NOTICE(S) in position to tell persons not to energize the F ADEC 1(2).
C.
Get Access
(1) Open the fan cowl doors.
Refer to the Airbus A318/A319/A320/A321 AMM, 71 - 13 - 00,
MAINTENANCE
PRACTICES, T ASK 71 - 13 - 00 - 010 - 803 - A, and do as follows:
(a) For 4020KM1 (POWER PLANT -
DEMOUNT ABLE, ENGINE
1) 437AL, 438AR.
(b) For 4020KM2 (POWER PLANT -
DEMOUNT ABLE, ENGINE
2) 447AL, 448AR.
D.
Deactivation of the Thrust Reverser System for Maintenance W ARNING:
YOU MUST
DEACTIV A TE THE THRUST
REVERSER BEFORE YOU DO WORK ON OR AROUND IT .
IF YOU DO NOT , THE THRUST
REVERSER CAN OPERA TE
ACCIDENT ALL Y AND CAUSE AN INJUR Y AND/OR DAMAGE.
(1) Do the deactivation of the thrust reverser system for ground maintenance.
Refer to the Airbus A318/A319/A320/A321 AMM, 78 - 30 - 00,
DEACTIV A
TION/REACTIV A TION, T ASK 78 - 30 - 00 - 040 - 809 - A.
(2) Open the thrust reverser cowl doors.
Refer to the Airbus A318/A319/A320/A321 AMM, 78 - 36 - 00, MAIN-
TENANCE
PRACTICES, T ASK 78 - 36 - 00 - 010 - 806 - A, and do as follows:
(a) For 4020KM1 (POWER PLANT -
DEMOUNT ABLE, ENGINE
1) 451AL, 452AR.
(b) For 4020KM2 (POWER PLANT -
DEMOUNT ABLE, ENGINE
2) 461AL, 462AR.
E.
HPT BSI
(1) Do the BSI of the HPT rotor stage 1 blades (1, Figure 1 ) (SIN:
159A0).
Use Option A or Option B specified in steps
5.E.(1)(a) and
5.E.(1)(b), and do as follows:
(a) Option A.
Do the BSI with a
4.0 mm borescope.
For this BSI it is recommended to:
• Use approximately a
4.0 mm diameter articulating borescope.
• Use a 0 degree (forward looking) objective tip.
• Access the HPT rotor stage 1 blades (1, Figure 1 ) (SIN:
159A0) through the applicable BSI port.
Refer to the Airbus A318/A319/A320/A321 AMM, 72 - 52 - 00,
INSPECTION/CHECK, T ASK 72 - 52 - 00 - 290 - 803 - A, paragraphs
4.A.
through
4.D.
Refer to the Airbus A318/A319/A320/A321 AMM, 72 - 52 - 00,
INSPECTION/CHECK, T ASK 72 - 52 - 00 - 290 - 803 - A, paragraphs
4.A.
through
4.D.
• Insert the
4.0 mm borescope and look in the aft direction.
Refer to step
5.E.(1)(a)1.
• T urn the HPT rotor assembly (SIN:
15000) into position for each of the 60 HPT rotor stage 1 blades
(1) (SIN:
159A0).
Refer to step
5.E.(1)(a)2.
• Stop and do an inspection of the full blade span of the aft concave surface.
Refer to step
5.E.(1)(a)3.
1 It is not recommended to advance the
4.0 mm borescope circumferentially between the leading edge of the HPT rotor stage 1 blade
(1) (SIN:
159A0) and the trailing edge of the HPT stator stage 1 nozzle (SIN:
172A0).
If the
4.0 mm borescope is directed circumferentially between these components, be careful to not get the
4.0 mm borescope caught in the platform clearance between the HPT rotor stage 1 blade
(1) (SIN:
159A0) and the HPT stator stage 1 nozzle (SIN:
172A0).
LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D Page 7/ 18 Issue 003 - 00 - 2025 - 07 - 30 © CFM
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INFORMA TION:
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LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D 2 T urn the HPT rotor assembly (SIN:
15000) via the accessory gearbox (AGB) manual drive pad.
It is recommended to turn in the opposite direction of normal rotation to avoid a pinched or a bound
4.0 mm borescope.
3 Move the
4.0 mm borescope between the HPT rotor stage 1 blades
(1) (SIN:
159A0) to get the perpendicular views of the concave surface aft zone.
Scan
4.0 mm borescope to view each HPT rotor stage 1 blade
(1) (SIN:
159A0) from the top - span (tip), to the mid - span, and lower - span (platform).
Refer to Figure 2 .
(b) Option B.
Alternative procedure.
Do the BSI with a
6.0 mm borescope.
For this BSI it is recommended to:
• Use approximately a
6.0 mm diameter articulating borescope.
• Use a 90 degrees (side looking) objective tip.
• Access the HPT rotor stage 1 blades (1, Figure 1 ) (SIN:
159A0) through the applicable BSI port.
Refer to the Airbus A318/A319/A320/A321 AMM, 72 - 52 - 00,
INSPECTION/CHECK, T ASK 72 - 52 - 00 - 290 - 803 - A, paragraphs
4.A.
through
4.D.
• Insert the
6.0 mm borescope and look in the aft direction.
• T urn the HPT rotor assembly (SIN:
15000) into position for each of the 60 HPT rotor stage 1 blades
(1) (SIN:
159A0).
Refer to step
5.E.(1)(b)1.
• Stop and do an inspection of the full blade span of the aft concave surface.
Refer to step
5.E.(1)(b)2.
1 T urn the HPT rotor assembly (SIN:
15000) via the AGB manual drive pad.
It is recommended to turn in the opposite direction of normal rotation to avoid a pinched or a bound
6.0 mm borescope.
2 Move the
6.0 mm borescope forward of the HPT rotor stage 1 blade
(1) (SIN:
159A0) looking aft to get the three views of the concave surface aft zone.
V iew each HPT rotor stage 1 blade
(1) (SIN:
159A0) at the top - span (tip), the mid - span, and the lower - span (platform).
Refer to Figure 3 .
It can be beneficial to turn the HPT rotor assembly (SIN:
15000) two to three times to get the top, mid, and lower views.
(c) Do a BSI of the HPT rotor stage 1 blades (1, Figure 1 ) (SIN:
159A0), use the technique specified in paragraph
5.E.(1)(a) or
5.E.(1)(b).
Refer to the Airbus A318/A319/A320/A321 AMM, 72 - 52 - 00,
INSPEC-
TION/CHECK, T ASK 72 - 52 - 00 - 290 - 803 - A, paragraph
4.E.(4) and do as follows:
1 Pay close attention to the HPT rotor stage 1 blade (1, Figure 1 ) (SIN:
159A0) concave airfoil, radially along cooling hole row 12 for any cracking.
Refer to Figure 4 and Figure 5 .
(d) Record and save the BSI videos and still images.
Refer to Figure 6 for example views of the HPT rotor stage 1 blade
(1) (SIN:
159A0).
(e) Obey the serviceability criteria specified in the Airbus A318/A319/A320/A321 AMM, 72 - 52 - 00,
INSPEC-
TION/CHECK, T ASK 72 - 52 - 00 - 290 - 803 - A, paragraph
4.E.(4) and do as follows:
1 Report any HPT rotor stage 1 blade unserviceable findings to your local CFM international field service representative.
Refer to Paragraph 6, Additional Information for CFM contact information.
(f) If the BSI shows an HPT rotor stage 1 blade condition that needs removal or re - inspection within 50 cycles as specified in the Airbus A318/A319/A320/A321 AMM, refer to Figure 7 for instructions for sister engine inspections and engine removals as necessary , and do as follows:
NOTE:
The second engine on the same aircraft is referred to as the "sister" engine in this Service Bulletin.
LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D Page 8/ 18 Issue 003 - 00 - 2025 - 07 - 30 © CFM
PROPRIET AR Y
INFORMA TION:
Subject to the restrictions on the media.
LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D 1 If one engine shows HPT rotor stage 1 blade conditions that would need removal or re - inspection within 50 cycles as specified in the Airbus A318/A319/A320/A321 AMM inspections referenced above in paragraph
5.E.(1)(c), the operator must do the HPT stage 1 blade
(1) (SIN:
159A0) inspection of the sister engine in accordance with this Service Bulletin, no later than 5 cycles after the first engine serial number (ESN) inspection, unless the sister engine was inspected as recommended by this Service Bulletin within the past 50 cycles for Group 1 or within the past 100 cycles for Group 2 engines.
2 If the sister engine has HPT rotor stage 1 blade conditions that would need removal or re - inspection within 50 cycles as specified in the Airbus A318/A319/A320/A321 AMM inspections referenced above in paragraph
5.E.(1)(c), remove one engine before the next flight.
F .
Return Aircraft to Service
(1) Close - up as follows:
(a) Make sure that the work area is clean and clear of tools and other items.
(b) Close the thrust reverser cowl doors.
Refer to the Airbus A318/A319/A320/A321 AMM, 78 - 36 - 00, MAIN-
TENANCE
PRACTICES, T ASK 78 - 36 - 00 - 410 - 806 - A, and do as follows:
1 For 4020KM1 (POWER PLANT -
DEMOUNT ABLE, ENGINE
1) 451AL, 452AR.
2 For 4020KM2 (POWER PLANT -
DEMOUNT ABLE, ENGINE
2) 461AL, 462AR.
3 Do the reactivation of the thrust reverser system after nacelle maintenance.
Refer to the Airbus A318/A319/A320/A321 AMM, 78 - 30 - 00,
DEACTIV A
TION/REACTIV A TION, T ASK 78 - 30 - 00 - 440 - 809 - A.
(c) Close access as follows:
1 Close the fan cowl doors.
Refer to the Airbus A318/A319/A320/A321 AMM, 71 - 13 - 00,
CLOSING OF THE F AN COWL DOORS, T ASK 71 - 13 - 00 - 410 - 803 - A, and do as follows:
a For 4020KM1 (POWER PLANT -
DEMOUNT ABLE, ENGINE
1) 437AL, 438AR.
b For 4020KM2 (POWER PLANT -
DEMOUNT ABLE, ENGINE
2) 447AL, 448AR.
2 Remove the W ARNING NOTICE(S).
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INFORMA TION:
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LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D 1 LEGEND:
1. HPT ROTOR STAGE 1 BLADE (QTY-60) (SIN: 159A0)
CDN ASSEMBLY (SIN: 00107) HPT STAGE 1
NOZZLE ASSEMBLY (SIN: 17200)
HPT ROTOR
ASSEMBLY (SIN: 15000) ICN-LEAP-1A-72000485-B-07482-00001-A-001-01 Location of HPT Rotor Stage 1 Blades Assemblies Figure 1 LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D Page 10/ 18 Issue 003 - 00 - 2025 - 07 - 30 © CFM
PROPRIET AR Y
INFORMA TION:
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LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D
HPT ROTOR STAGE 1 BLADE (QTY-60) (SIN: 159A0)
UPPER-SPAN MID-SPAN
LOWER-SPAN UPPER MID LOWER ICN-LEAP-1A-72000485-B-07482-00002-A-001-01 Example V iews W ith a
4.0 mm Borescope Figure 2 LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D Page 1 1/ 18 Issue 003 - 00 - 2025 - 07 - 30 © CFM
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INFORMA TION:
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LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D
HPT ROTOR STAGE 1 BLADE (QTY-60) (SIN: 159A0)
UPPER-SPAN MID-SPAN
LOWER-SPAN UPPER MID LOWER ICN-LEAP-1A-72000485-B-07482-00003-A-001-01 Example V iews W ith a
6.0 mm Borescope Figure 3 LEAP - 1A - 72 - 00 - 0485 - 01A - 930A - D Page 12/ 18 Issue 003 - 00 - 2025 - 07 - 30 © CFM
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INFORMA TION:
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