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Rolls-Royce Deutschland Ltd & Co KG ROLLS Eschenweg 11, Dahlewitz 15827 Blankenfelde-Mahlow D Germany Tel: +49 33-7086-4040 ROYCE E-mail: rrd.service.bulletins@rolls-royce.com
PUBLICATIONTRANSMITTAL The technical content of this document is approved under the authority of the DOA ref. EASA.21J.065.
Date Aug. 2/22 Printed in Great Britain TAY SERIES PROPULSION SYSTEM SERVICE BULLETIN ALERT Export Control Rating: This technical information/software is not controlled under the German export control regulations.
This document transmits the Initial Issue of Non-Modification Service Bulletin TAY-72-A1797.
Non-Modification Service Bulletin Initial Issue Remove Incorporate Reason for change Pages 1 to 19 of the Initial Issue.
Non-Modification Service Bulletin.
ALERT TAY-72-A1797 Transmittal - Page 1 of 1
RETAIN THIS LETTER OF TRANSMITTAL - CHECK THAT ALL PREVIOUS TRANSMITTALS HAVE BEEN INCORPORATED If any have not been received please advise the Publication Services Department at the following address:
Rolls-Royce plc, PO Box 31, Derby DE24 8BJ, England or e-mail: airlines.publication.services@rolls-royce.com © Rolls-Royce Deutschland Ltd & Co KG (date as above) Printed in Great Britain.
No text on this page: it may be a figure. Open the PDF to see it.
1. Planning Information A. Effectivity
(1) Fokker 70.
All Tay 620-15/20 Engines.
Modules M04100AA, M04101AA, M04102AA and M04103AA (Combustion and HP Turbine Module).
(2) Fokker 100.
(a) All Tay 620-15 Engines.
Modules M04100AA, M04101AA, M04102AA and M04103AA (Combustion and HP Turbine Module).
(b) All Tay 650-15 and Tay 650-15/10 Engines.
Modules M04300AA and M04301AA (Combustion and HP Turbine Module).
B. Concurrent Requirements None.
C. Reason Cracking of the High Pressure (HP) turbine stage 2 intermediate air seal bolts (72-41-21, 01-862), P/N AS26710 in service has been reported that could lead to a failure of these bolts in this location and subsequent secondary damage to surrounding critical parts (HP turbine stage 1 and stage 2 rotor discs).
ENGINE - HIGH PRESSURE (HP) TURBINE ROTOR DISCS AND BLADES STAGE 1 AND STAGE 2 - BORESCOPE INSPECTION OF THE CAVITY SURROUNDING THE HP TURBINE STAGE 2 INTERMEDIATE
AIR SEAL - NON-MODIFICATION SERVICE BULLETIN Printed in Great Britain TAY−72−A1797 Page 1 of 19 Aug. 2/22 Aug. 2/22 Initial Issue
D. Description SAFETY INTENT: For Tay 620-15 and Tay 620-15/20 Engines:
The safety intent of this Non-Modification Service Bulletin is to instruct a visual borescope inspection of the HP turbine stage 2 rotor disc front side for possible damage.
Failed HP turbine stage 2 intermediate air seal bolts (72-41-21, 01-862), P/N AS26710 can cause damage on the front side of the HP turbine stage 2 rotor disc.
For Tay 650-15 and Tay 650-15/10 Engines:
The safety intent of this Non-Modification Service Bulletin is to instruct a visual borescope inspection of the HP turbine stage 1 rotor disc rear side for possible damage.
Failed HP turbine stage 2 intermediate air seal bolts (72-41-21, 01-862), P/N AS26710 can cause damage on the rear side of the HP turbine stage 1 rotor disc.
For Tay 620-15 and Tay 620-15/20 Engines:
This Non-Modification Service Bulletin instructs a visual borescope inspection of the HP turbine stage 2 on the front side of the HP turbine stage 2 rotor disc. The intent is to identify if cracked bolts (72-41-21, 01-862), P/N AS26710 from the HP turbine stage 2 intermediate air seal assembly are directly visible or if indications of secondary damage can be found on the HP turbine stage 2 rotor disc front side.
For Tay 650-15 and Tay 650-15/10 Engines:
This Non-Modification Service Bulletin instructs a visual borescope inspection of the HP turbine stage 1 blade retaining and locking plates on the rear side of the HP turbine stage 1 rotor disc. The intent is to identify if cracked bolts (72-41-21, 01-862), P/N AS26710 from the HP turbine stage 2 intermediate air seal assembly are directly visible or if indications of secondary damage can be found on the HP turbine stage 1 blade retaining and locking plates.
Printed in Great Britain TAY−72−A1797 Page 2 of 19 Aug. 2/22 Aug. 2/22 Initial Issue
E. Compliance ALERT For engines when installed or have been installed on an aircraft operated under an Operator Certificate issued by the Islamic Republic of Iran:
- This Non-Modification Service Bulletin must be accomplished on engines within 50 flight cycles or within 2 months after receipt of this Non-Modification Service Bulletin, whichever occurs first.
- This Non-Modification Service Bulletin must be accomplished again at intervals of not more than 500 flight cycles or within 12 month after the previous accomplishment, whichever occurs first.
For all other engines:
- This Non-Modification Service Bulletin must be accomplished on engines which, at the date of issue of this Non-Modification Service Bulletin, have turbine stage 2 intermediate air seal bolts (72-41-21, 01-862), P/N AS26710 installed that have accumulated more than 10000 flight cycles, within 1000 flight cycles or within 12 months after receipt of this Non-Modification Service Bulletin, whichever occurs first.
NOTE: If the age of the turbine stage 2 intermediate air seal bolts (72-41-21, 01-862), P/N AS26710 is unknown it has to be assumed that they have been installed since initial engine build.
- This Non-Modification Service Bulletin must be accomplished on engines which, at the date of issue of this Non-Modification Service Bulletin, have turbine stage 2 intermediate air seal bolts (72-41-21, 01-862), P/N AS26710 installed that have accumulated less than 10000 flight cycles, before the turbine stage 2 intermediate air seal bolts (72-41-21, 01-862), P/N AS26710 have accumulated 10000 flight cycles or within 1000 flight cycles after receipt of this Non-Modification Service Bulletin, whichever occurs later.
NOTE: If the age of the turbine stage 2 intermediate air seal bolts (72-41-21, 01-862), P/N AS26710 is unknown it has to be assumed that they have been installed since initial engine build.
- This Non-Modification Service Bulletin must be accomplished again at intervals of not more than 2000 flight cycles or within 24 month after the previous accomplishment, whichever occurs first.
F. Approval The technical content of this document is approved under the authority of the DOA ref. EASA.21J.065.
Printed in Great Britain TAY−72−A1797 Page 3 of 19 Aug. 2/22 Aug. 2/22 Initial Issue
G. Manpower
(1) In Service 3 hours.
(2) At Overhaul Not applicable.
H. Material Price and Availability Not applicable.
I. Tooling Price and Availability New tools are not required.
J. Industry Support Information The incorporation of this Non-Modification Service Bulletin is not free of charge.
NOTE: For further information contact your Rolls-Royce Customer Service Representative.
K. Weight and Balance
(1) Weight Change None.
(2) Moment Arm No effect.
(3) Datum ES2540 (PPS100).
L. Electrical Load Data The aircraft electrical load is not affected by this Non-Modification Service Bulletin.
M. Software Accomplishment Summary Not applicable.
Printed in Great Britain TAY−72−A1797 Page 4 of 19 Aug. 2/22 Aug. 2/22 Initial Issue
N. References For Tay 620-15 and Tay 620-15/20 Engines:
(1) Aircraft Maintenance Manual, Chapter 71-00-00.
For Tay 650-15 and Tay 650-15/10 Engines:
(1) Aircraft Maintenance Manual, Chapter 71-00-00.
O. Other Publications Affected None.
P. Interchangeability of Parts Not affected.
Printed in Great Britain TAY−72−A1797 Page 5 of 19 Aug. 2/22 Aug. 2/22 Initial Issue
2. Material Information A. Parts to be Replaced None.
B. Expendable Parts Refer to the related Manual tasks given in the Accomplishment Instruction of this Non-Modification Service Bulletin.
C. Instructions/Disposition Code:
None.
Printed in Great Britain TAY−72−A1797 Page 6 of 19 Aug. 2/22 Aug. 2/22 Initial Issue
3. Accomplishment Instructions A. General NOTE: When the words "refer to" are used in the Accomplishment Instruction and there are other acceptable methods, techniques and practices (including tools, equipment and test equipment) those acceptable methods, techniques and practices (including tools, equipment and test equipment) can be used to complete the work, however Rolls-Royce Deutschland always recommends to use the procedures referred to in the Accomplishment Instruction. When the words "in accordance with" are used in the Accomplishment Instruction, the methods, techniques and practices (including tools, equipment and test equipment) in the specified document must be used.
NOTE: In order to reduce the potential for multiple-engine in-flight shutdown, power loss, or other anomaly due to maintenance error, Rolls-Royce Deutschland recommends that Operators avoid performing maintenance on multiple engines installed on the same aircraft at the same time. If it is not possible to avoid maintenance on more than one engine of an aircraft at the same time Rolls-Royce Deutschland recommends that additional controls are applied in order to ensure that maintenance tasks have been completed as defined.
NOTE: In order to avoid damage to the borescope equipment it is necessary that the engine has cooled down for at least two hours after shutdown.
WARNING: YOU MUST BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE IS STOPPED. THE ENGINE PARTS CAN STAY HOT FOR ALMOST ONE HOUR.
WARNING: DO NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN CAUSE AN INJURY. IF YOU GET AN INJURY, PUT IT IN COLD WATER FOR TEN MINUTES AND GET MEDICAL AID.
(1) Obey all the WARNINGS and CAUTIONS in the procedures that are referred to.
(2) Consumable Materials
(a) Refer to the related Manual tasks given in this instruction.
Printed in Great Britain TAY−72−A1797 Page 7 of 19 Aug. 2/22 Aug. 2/22 Initial Issue
(3) Tools and Equipment
(a) Refer to the table that follows:
REFERENCE DESIGNATION No Specific Flexible video-borescope with a 3,9 to 4,0 mm (0.15 to 0.16 in.) diameter, a minimum length of 2,0 meters (6.56 ft.).
Side view tip adaptor Depth of Field (DOF): 5,8 to 200,0 mm (0.23 to 7.87 in.)
(or 5,8 to infinity (0.23 in. to infinity)) Resolution 440000 pixel (768 x 576) [predecessor generation @ 290000].
(b) For further tools and equipment refer also to the related Manual tasks given in this instruction.
B. Remove the blanking plug of the borescope access port for the High Pressure (HP) turbine stage 2 blade examination that is installed on the rear bottom side of the core engine (Refer to the Aircraft Maintenance Manual, Chapter 71-00-00, TASK 71-00-00-200-816).
C. Install the tools to turn the HP turbine rotor (Refer to the Aircraft Maintenance Manual, Chapter 71-00-00, TASK 71-00-00-200-816).
D. Examine the cavity surrounding the HP turbine stage 2 intermediate air seal
(1) For Tay 620-15 and Tay 620-15/20 Engines:
Examine the HP turbine stage 2 on the front side of the HP turbine stage 2 rotor disc in accordance with the following steps D.(1)(a) to D.(1)(g) (Refer to Figure 1) NOTE: The borescope inspection of the HP turbine stage 2 on the front side of the HP turbine stage 2 rotor disc is necessary at four positions. The access for the borescope inspection of the HP turbine stage 2 on the front side of the HP turbine stage 2 rotor disc is from the rear through the HP turbine stage 2 blades. The identification of the four different borescope inspection positions is ensured by turning the HP turbine rotor and counting the HP turbine stage 2 blades at the same time. The HP turbine stage 2 contains in total 126 blades. The HP turbine stage 2 blades are illustrated on Figure 1, detail D.
Printed in Great Britain TAY−72−A1797 Page 8 of 19 Aug. 2/22 Aug. 2/22 Initial Issue
CAUTION: MAKE SURE THAT NO OTHER PERSON TURNS THE HP TURBINE ROTOR DURING THE INSPECTION OF THE HP TURBINE STAGE 2 ROTOR DISC FRONT SIDE. THIS WILL HELP TO PREVENT DAMAGE TO THE ENGINE OR EQUIPMENT.
(a) Insert a 3,9 to 4,0 (0.15 to 0.16 in.) diameter flexible video-borescope through the borescope access port for the HP turbine stage 2 blade examination.
(b) Move the tip adapter of the flexible video-borescope in between two HP turbine stage 2 blades until you reach the HP turbine stage 2 Nozzle Guide Vanes (NGV) Trailing/Edge (T/E).
(c) Move the tip adapter of the flexible video-borescope to the gap between the HP turbine stage 2 blade inner front platform and the HP turbine stage 2 NGV inner rear platform.
(d) Put the tip adapter of the flexible video-borescope in a position so that you can examine the HP turbine stage 2 rotor disc front side through the gap between the HP turbine stage 2 blade inner front platform and the HP turbine stage 2 NGV inner rear platform [1] Examine the HP turbine stage 2 rotor disc front side for indications of damage [a] If you find no indications of damage, continue with step D.(1)(d)[2].
[b] If you find indications of damage, reject the engine NOTE: Rolls-Royce Deutschland, Service Engineering can be contacted if you are not sure about the indications of damage.
Contact details are:
Operational Service Desk (OSD)
- phone: +49 33-7086-3500.
- E-mail: DWOSD@rolls-royce.com.
1) Continue with step step D.(1)(f)
a) Replace the engine and send the removed engine to an approved TAY overhaul facility for detailed inspection and required corrective actions.
Printed in Great Britain TAY−72−A1797 Page 9 of 19 Aug. 2/22 Aug. 2/22 Initial Issue
[2] Remove the flexible video-borescope from the HP turbine rotor [a] Make sure that the flexible video-borescope is not in contact with the HP turbine rotor and you can turn the HP turbine rotor.
[b] Put the tip adapter of the flexible video-borescope in a position so that you can see the HP turbine stage 2 blades T/E.
CAUTION: MAKE SURE THAT THE FLEXIBLE VIDEO-BORESCOPE IS NOT IN
CONTACT WITH THE HP TURBINE ROTOR WHEN YOU TURN THE HP TURBINE ROTOR. IF YOU DO NOT OBEY THIS INSTRUCTION DAMAGE TO THE ENGINE OR EQUIPMENT CAN OCCUR.
[3] Turn the HP turbine rotor to the next borescope inspection position. At the same time use the flexible video-borescope to count the next 32 HP turbine stage 2 blades (Refer to the Aircraft Maintenance Manual, Chapter 71-00-00, TASK 71-00-00-200-816).
(e) Do the steps D.(1)(b) to D.(1)(d)[3] again for the three borescope inspection positions that remain.
(f) Remove the flexible video-borescope equipment from the engine.
(g) Record the result of the borescope inspection on the front side of the HP turbine stage 2 rotor disc in the Accomplishment Form on page 19 of this Non-Modification Service Bulletin. Continue with step E.
(2) For Tay 650-15 and Tay 650-15/10 Engines:
Examine the HP turbine stage 1 blade retaining and locking plates on the rear side of the HP turbine stage 1 rotor disc for damage in accordance with the following steps D.(2)(a) to D.(2)(g) (Refer to Figure 1) NOTE: The borescope inspection of the HP turbine stage 1 blade retaining and locking pates is necessary at four positions. The access for the borescope inspection of the HP turbine stage 1 blade retaining and locking plates is from the rear through the HP turbine stage 2 blades. The identification of the four different borescope inspection positions is ensured by turning the HP turbine rotor and counting the HP turbine stage 2 blades at the same time. The HP turbine stage 2 contains in total 126 blades. The HP turbine stage 2 blades are illustrated on Figure 1, detail D.
Printed in Great Britain TAY−72−A1797 Page 10 of 19 Aug. 2/22 Aug. 2/22 Initial Issue