Printed in Great BritainPrinted in Great BritainPrinted in Great BritainR Contents 1 Sep.15/14 R Contents 2 Sep.15/14 00-00 1/ Jun.15/08 2 00-01 1 Dec.15/13 00-01 2 Dec.15/13 00-01 3 Dec.15/13 00-01 4 Dec.15/13 00-01 5 Dec.15/13 00-01 6 Dec.15/13 00-01 7 Dec.15/13 00-01 8 Dec.15/13 00-01 9 Dec.15/13 00-01 10 Dec.15/13 00-01 11 Dec.15/13 00-01 12 Dec.15/13 00-01 13 Dec.15/13 00-01 14 Dec.15/13 00-01 15 Dec.15/13 00-01 16 Dec.15/13 00-01 17 Dec.15/13 00-01 18 Dec.15/13 00-01 19 Dec.15/13 00-01 20 Dec.15/13 00-01 21 Dec.15/13 00-01 22 Dec.15/13 00-01 23 Dec.15/13 00-01 24 Dec.15/13 00-01 25 Dec.15/13 00-01 26 Dec.15/13 00-01 27 Dec.15/13 00-01 28 Dec.15/13 00-01 29 Dec.15/13 00-01 30 Dec.15/13 00-01 31 Dec.15/13 00-01 32 Dec.15/13 00-02 1 Dec.15/12 00-02 2 Dec.15/12 00-02 3 Dec.15/12 00-02 4 Dec.15/12 00-02 5 Dec.15/12 00-02 6 Dec.15/12 00-02 7 Dec.15/12 00-02 8 Dec.15/12 00-02 9/ Dec.15/12 10 00-03 1/ Dec.15/12 2 00-04 1/ Jun.15/08 2 10-00 1/ Jun.15/08 2 R 10-01 1 Sep.15/14 R 10-01 2 Sep.15/14 R 10-01 3 Sep.15/14 R 10-01 4 Sep.15/14 R 10-01 5 Sep.15/14 R 10-01 6 Sep.15/14 R 10-01 7 Sep.15/14 R 10-01 8 Sep.15/14 R 10-01 9 Sep.15/14 R 10-01 10 Sep.15/14 R 10-01 11 Sep.15/14 R 10-01 12 Sep.15/14 R 10-01 13 Sep.15/14 R 10-01 14 Sep.15/14 R 10-01 15/ Sep.15/14 16 20-01 1 Jun.15/10 20-01 2 Jun.15/10 20-01 3/ Jun.15/10 4 --------------- END --------------- 3RR**Printed in Great Britain** CHAPTER 05
TIME LIMITS
LIST OF EFFECTIVE PAGES

CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 05 CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 05 CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 05

LIST OF EFFECTIVE PAGES-05 Page 1/2 Sep.15/14 C=CONFIG B=BREAKOUTGENERAL DATA 05-00-00 GENERAL DATA(General Data) 1

RECORDING AND CONTROL OF THE LIVES OF PARTS 05-00-01 RECORDING AND CONTROL OF THE LIVES OF

PARTS(Recording and Control of the Lives of Parts) 1

FLIGHT PROFILES AND OPERATIONAL MONITORING 05-00-02 FLIGHT PROFILES AND OPERATIONAL

MONITORING(Flight Profiles and Operational Monitoring - Group A Parts) 1

MAXIMUM APPROVED LIVES - RECOMMENDED GROUP B PARTS 05-00-03 MAXIMUM APPROVED LIVES(Maximum Approved

Lives - Recommended Group B Parts) 1

CALENDAR LIFE LIMIT 05-00-04 CALENDAR LIFE LIMIT(Calendar Life Limit) 1

05-10-00 TIME LIMITS(Flight Profiles and

Operational Monitoring - Group A Parts) 1

MAXIMUM APPROVED LIVES 05-10-01 MAXIMUM APPROVED LIVES(AIRWORTHINESS

LIMITATIONS - Maximum Approved Lives - Group A Parts and Mandatory Group B Parts) 1 3RR**Printed in Great Britain** CHAPTER 05 - TIME LIMITS
TABLE OF CONTENTS



# 05−CONTENTS Page 1 Sep.15/14 CHAPTER BREAKOUT SECTION CONFIG/ SUBJECT SUBJECT PAGE EFFECTIVITYMANDATORY INSPECTIONS 05-20-01 MANDATORY INSPECTIONS OF GROUP A

PARTS(AIRWORTHINESS LIMITATION - Mandatory Inspections of Group A Parts) 1 3RR**Printed in Great Britain**



# 05−CONTENTS Page 2 Dec.15/13 CHAPTER BREAKOUT SECTION CONFIG/ SUBJECT SUBJECT PAGE EFFECTIVITYGENERAL DATA

TASK 05-00-00-860-000 General Data 1. General Data A. This Manual contains Airworthiness Limitations and Non-Airworthiness Limitations Chapters. Airworthiness Limitations Chapters are approved by EASA under approval No. EASA.E.C.01618. Airworthiness Limitations are applied to the maximum approved lives of Group A parts, mandatory Group B parts and mandatory inspection of parts. Non-Airworthiness Limitations are applied to general data, recording and control of lives of parts, flight profiles and operational monitoring, recommended Group B parts lives and calendar life limits. Airworthiness Limitation Chapters are: Chapter 05-10-01 Maximum Approved Lives - Group A Parts and Mandatory Group B Parts Chapter 05-20-01 Mandatory Inspections of Group A Parts Non-Airworthiness Limitation Chapters are: Chapter 05-00-00 General Data Chapter 05-00-01 Recording and Control of the Lives of Parts Chapter 05-00-02 Flight Profiles and Operational Monitoring Chapter 05-00-03 Maximum Approved Lives - Recommended Group B Parts Chapter 05-00-04 Calendar Life Limitation 3RR**Printed in Great Britain**

GENERAL DATA 

# 05−00−00 EFFECTIVITY: TAY/ALL Page 1/2 Jun.15/08RECORDING AND CONTROL OF THE LIVES OF PARTS

TASK 05-00-01-800-801 Recording and Control of the Lives of Parts 1. Equipment and Material A. Standard equipment Vibro-engraving tool B. Consumable materials OMat 1/202 Chromating touch-up OMat 7/24 EEL resistant touch-up 2. General Adequate and accurate information about the lives and disposition of engine parts and their condition at repair is important to both the operator and Rolls-Royce. Such information will assist in spares provisioning, warranty claims, repair planning and the establishment of an economical operation. A recommendation by Rolls-Royce of the life of a part does not imply that a part will achieve this life and it does not constitute a warranty of the part by Rolls-Royce. The warranty arrangements made between Rolls-Royce and the operator will control the relationship between the parties. The type of record and the degree of control over the life varies according to the part. For these purposes parts are divided into three groups, A, B, and C. Mandatory lives for Group A parts and Group B parts are given in TASK 05-10-01-800-000.The remaining Group B parts which are not mandatory life limited but are given recommended lives are also listed in TASK 05-00-03-800-000.
NOTE : Tay Manuals use the classification of Group A, Group B and Group C parts. These parts can also be referred to as Critical, Sensitive and Unclassified parts. Group A parts = Critical parts. Group B parts = Sensitive parts. Group C parts = Unclassified parts. Identify if a Life Limited Part (LLP) was operated before in a different engine type or mark, LLP records must be checked if disposition, repairs or TVs are related to the specified engine type or mark. 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 1 Dec.15/13 R3. Group A Parts Group A parts comprise those major rotating parts of an engine the failure of which could, if uncontained, affect the airworthiness of the aircraft. They are the only parts of the engine for which an Airworthiness Authority certified life is required and notification of the lives must be made to each aircraft operator. These parts are thus subjected to strict life limitations which must not be exceeded in service. These limitations are made as a result of experience collected by Rolls-Royce through cyclic rig testing, development engine testing, metallurgical investigation and other techniques, including sampling of service run parts. The service life achieved on a part can prove to be less than that permitted by Rolls-Royce for airworthiness consideration. For example, corrosion or wear can result in rejection of the part at an earlier life than the quoted limitation. The operator must controll the lives of Group A parts in service. The lives of Group A parts are expressed in terms of Flight Cycles. This is the most direct and accurate way of controlling the service life or parts. The life is calculated from the rate of fatigue life usage per Datum Flight. Flight cycle and Datum Flight profile data are given in TASK 05-00-02-800-000. 4. Definition of a Flight Cycle A. Normal flying A normal take-off to landing according to the Datum Flight Profile for the engine type. B. Touch and go or overshoot R One full (1/1) of a flight cycle for each touch and go or overshoot recorded on the aircraft for the period during which the engine was installed needs to be added to the life of all group A parts. R R R C. Pilot Training One Flight Cycle for the initial take-off and final landing. One full (1/1) of a flight cycle for each touch and go or overshoot recorded on the aircraft for the period during which the engine was installed needs to be added to the life of all group A parts. R R R R For example, one training flight that includes one 'overshoot' and three 'touch and go's' is the equivalent of five R Flight Cycles for all group A parts. 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 2 Dec.15/13 R5. Recording of Lives
CAUTION : EMPHASIS IS PLACED ON THE VITAL IMPORTANCE OF MAINTAINING LIFE RECORDS ON ALL GROUP A PARTS. THESE RECORDS FORM THE ONLY IDENTIFICATION OF LIFE COMPLETED BY EACH PART. The repair facility is required to make records and supply information as follows: A. Keep an internal record for each Group A part, if in service or held serviceable in stores pending issue to a module. These records are vitally important to the life control of parts and must therefore be accurate and up to date. Record the part serial number and modification standard against the total life in terms of Flight Cycles and hours, expressed numerically (not in life code letters). To help locate parts quickly, the record system must index parts under description and modification standard and, separately, under engine type and serial numbers and/or module number. B. Record and tell the operator and Rolls-Royce the reasons for rejection of any part, and its total running time in Flight Cycles and hours. C. Calculate, from information received from the operator, the residual life of a part and decide if or not it can be refitted in an engine and/or module without becoming time expired in advance of the engine and/or module life requirements of the operator. D. Advise operators of the serial numbers and life completed in Flight Cycles and hours on those parts which have been fitted into engines and/or modules during shop visits. The advice must be included with the paperwork accompanying engines and/or modules during shop visits. The advice must be included with the paperwork accompanying engines or modules when returned to the operator. The same information must be sent to Rolls-Royce. 6. Special Requirements A. Reason for special requirements This manual contains four sets of declared cyclic lives applicable to the Group A Parts and the Mandatory Group B Parts. These are defined as Flight Plan A, Flight Plan B, Flight Plan C, and Flight Plan D Life Profile Operations. The Flight Profiles applicable to these Flight Plans are published in the Time Limits Manual, Chapter 05-00-02. Group A Parts can be transferred between profiles. To enable operators to continue with their Actual Profile Operation or to allow Group A Parts be transferred between flight plans, the following records must be maintained: (1) Installation history 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 3 Dec.15/13 R(2) Regular interval review of profiles. Refer to Engine Maintenance Manual, Chapter 70-01-10, Flight Profiles and Operational Monitoring. (3) Revised life limits. B. Recording installation history The life of each Group A Parts and Mandatory Group B Parts must be recorded, refer to paragraph 5. C. Regular interval review of profiles After an operator has been classified into an approved Life Profile Operation, it is the responsibility of the Operator, if required by his local Airworthiness Authority, to provide the preceding years flight profile data in order to continue operating within the specified Flight Plan. D. Revised life limits Any operator changing from one Life Profile Operation to another or vice versa must notify Rolls-Royce of this change. These revised lives limits must be recorded against the individual Group A Parts and the Mandatory Group B Parts. 7. Mandatory Group B Parts These are parts which test and service experience have shown require special attention in service in order to avoid failures which: Can be serious in terms of engine disruption but are classed as considerably less significant than the possible consequences of a Group A part failure, or Though not hazardous in their own right, can threaten the integrity of a Group A part. A. Any mandatory life limitations developed for such parts are given in TASK 05-10-01-800-000. These parts are also identified in paragraph 10, List of Group B Parts, with an asterisk. Routine scheduled inspection checks, where appropriate, will need to be included in the Aircraft Maintenance Schedule and supplemented by an advisory Notice to Operators (NTO). In some cases, these inspections will be instructed in a non-modification Service Bulletins. The remaining parts in this group are those whose failure can cause extensive secondary damage. 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 4 Dec.15/13 RIt is uneconomic to run these parts to lives at which high failure rates can occur. They are generally removed from service at the longest life consistent with an acceptable failure rate. It is important to maintain a number of these parts at lives ahead of the majority to give adequate warning of the life at which failure can be expected. This procedure will protect the operator from campaign situations. Main line bearings and turbine blades must be included in this system. Included in this group are parts of a high initial cost which will normally have an extended service life. The provisioning of such parts is based on a small protection stock. The size of which depends upon those long-life parts which can require replacement over a short-time, if life-limiting features become apparent. It is important to ensure that the lives of such parts are suitably spaced over the engines or modules in any operation to keep the size of the protection stock to a minimum and to avoid a sudden spares requirement. Suitable spacing is defined as a sufficient scatter between high-life and low-life parts and a sufficient number of high-life parts far enough ahead of the majority to provide adequate time to deal with any life limitation. Records of parts fitted to engines/modules at repair, together with current engine/module lives, can be combined to produce a distribution block graph as shown in Fig. 05-00-01-990-001. It is recommended that protection stocks cover the leading parts and the time between these and the majority will indicate the delivery requirement for each operator's future repairs. In many instances the scatter will occur naturally, due to engine/module growth, part-life repairs and rectification. Where this is not so, a life stagger is recommended to be introduced artificially, before large numbers of parts are refitted to complete high hours beyond current experience, by fitting new or low-life parts at repair to space out the life distribution pattern. Rolls-Royce will make available to all operators the current service experience on Group B parts, as a basis upon which life extensions, where appropriate, can be planned depending upon the individual operation. It is necessary to life mark or maintain life records of Group B parts, refer to paragraph 9. All Group B parts are listed in paragraph 10. 8. Group C Parts It is suggested that the parts in this group are life marked only to assist in warranty claims and spares provisioning. The only type of record desirable for this group is the life of the part when it is finally scrapped, which will guide spares provisioning. 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 5 Dec.15/13 R9. Life Markings of Group B and C Parts A. Life marking
NOTE : The control of Group A parts is maintained by records, therefore the marking of these parts is not necessary. Where a group B part has no serial number and no paperwork records, the part must be suitably life marked as detailed in B. This method is based on a minimum level of life marking in association with the life records of the related engine or module. Where engines are being maintained by modules it is necessary for each module to be individually identified and its life records maintained separately. It is only necessary to mark parts on two occasions: (1) when new or ex-pool parts are fitted, and (2) when parts removed from an engine or module enter a parts pool This practice will give the benefit of substantial economy in the marking space available on small parts such as blades. It will be necessary to identify those parts which are replaced during engine or module repair so that their running times can be calculated at the time of life marking. A suitable method is to mark the part with a symbol representing the date on which the part was fitted, indicating the month and year, using the number of the month and the last two digits of the year and interposing a hyphen, e.g. October 1988 would be indicated 10-88. At the time of life marking, the running time is calculated by reference to the engine or module log records. A part removed from a parts pool for fitting to an engine or module must have the date marked adjacent to the life marking. In a future life calculation the calculated life since fitting would be added to the life denoted by the life marking. On a part removed from an engine or module for transfer into a parts pool, the life is calculated from the log records, and the part life-marked using a code such as that detailed in sub-paragraph B. Any previously applied date mark must be deleted at the time of life marking. 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 6 Dec.15/13 RB. Life marking code Suitable life marking codes are shown in the tables below, using 25 letters. Table 1 gives a range of 0 to 2,500 hours, table 2 gives a range of 0 to 12,500 hours. If table 1 is used, a circle with the figure 5 in it is to be engraved on the parts before the first life marking letter. If table 2 is used, a circle with the figure 6 in it is to be engraved on the parts before the first life marking letter. Table 1 A=0-100 F=501-600 L=1001-1100 Q=1501-1600 V=2001-2100 B=101-200 G=601-700 M=1101-1200 R=1601-1700 W=2101-2200 C=201-300 H=701-800 N=1201-1300 S=1701-1800 X=2201-2300 D=301-400 J=801-900 O=1301-1400 T=1801-1900 Y=2301-2400 E=401-500 K=901-1000 P=1401-1500 U=1901-2000 Z=2401-2500

Table 2 A=0-500 F=2501-3000 L=5001-5500 Q=7501-8000 V=10001-10500 B=501-1000 G=3001-3500 M=5501-6000 R=8001-8500 W=10501-11000 C=1001-1500 H=3501-4000 N=6001-6500 S=8501-9000 X=11001-11500 D=1501-2000 J=4001-4500 O=6501-7000 T=9001-9500 Y=11501-12000 E=2001-2500 K=4501-5000 P=7001-7500 U=9501-10000 Z=12001-12500 When the life exceeds the range covered by the table, use the letter Z with other letters to denote the life marking required. Example 1, life marking using table 1: (1) Part removed from engine at 742 hours for entry into pool: Part marked 5 (in a circle) H (2) Part fitted to second engine: Part date marked (3) Part removed for entry into pool at engine running time of 1,370 hours since date marking: Date mark deleted and letter O added; life marking will then read 5 (in a circle) HO (4) Part fitted to third engine: Part date marked 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 7 Dec.15/13 R(5) Part removed for entry into pool at engine running time of 2,700 hours since date marking: Date mark deleted and letters ZB added: life marking will then read 5 (in a circle) HOZB C. Method of marking
CAUTION : METAL STAMPS OR ELECTRO-ETCHING MUST NOT BE USED TO LIFE MARK ANY PART. D. To avoid the setting up of stress concentrations, the code must be applied using vibro-engraving tool. Where magnesium cases are engraved, the immediate area will require reprotection using 10 percent solution of OMat 1/202 Chromating touch up, followed by an application of OMat 7/24 EEL resistant touch-up clear varnish. Refer to OP TASK 70-00-00-300-304. E. Position of marking The code letters must be marked adjacent to the part number in such a manner that they will not be mistaken for a part of a serial or other number. On parts where surface areas for marking are relatively small (as in blades and vanes), alternative positions for life marking are given in para.F. F. Alternative marking instructions (1) Compressor and turbine blades and vanes Typical examples of rotor blades and stator vanes and the areas in which life markings are to be applied are illustrated in Fig.05-00-01-990-002 , Fig.05-00-01-990-003 , Fig.05-00-01-990-004 , Fig.05-00-01-990-005 , Fig.05-00-01-990-006 , Fig.05-00-01-990-007 , Fig.05-00-01-990-008 , Fig.05-00-01-990-009 , Fig.05-00-01-990-010 , Fig.05-00-01-990-011 and Fig.05-00-01-990-012 . If the marked vane in an assembly, is replaced by a new vane, or one of comparable life to the original, the replacement vane must be marked with the life coding appropriate to the original vanes in the group. Proximity of the markings to certain areas is subject to limitation. The prohibited areas and limits of proximity are specifically defined for blades and vanes in Fig.05-00-01-990-002 to Fig.05-00-01-990-012. 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 8 Dec.15/13 R10.List of Group B Parts ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY LP Compressor Rotating Fairing LP compressor rotating fairing (72-30-10,01-060) 1 LP compressor nose cone assembly (72-30-10,01-010) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY LP Compressor Blades LP compressor blade * (72-31-12,02-010) 22 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY LP Compressor Case and Vanes LP compressor case (72-32-20,01-250) 1 LP outlet guide vane assembly (72-32-30,01-360) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Splitter Fairing Splitter fairing assembly (72-33-10,01-005) 1 IP inlet guide vane assembly (72-33-10,01-110) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY IP Compressor Stator Vanes - Stages 1 and 2 Stage 1 vane (72-33-22,02-010) 72 Stage 1 vane (72-33-22,02-030) 12 Stage 1 vane (72-33-22,02-050) 4 Stage 1 vane (72-33-22,02-070) 4 Stage 2 vane (72-33-22,02-130) 80 Stage 2 vane (72-33-22,02-150) 16 Stage 2 vane (72-33-22,02-170) 4 Stage 2 vane (72-33-22,02-190) 4 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY IP Compressor Rotor Stage 1 IP compressor stage 1 blade (72-33-31,01-005) 63 IP compressor spacer, stages 1 to 2 (72-33-31,01-070) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY IP Compressor Rotor Stage 2 IP compressor stage 2 blade (72-33-32,02-005) 72 IP compressor spacer, stages 2 to 3 (72-33-32,02-065) 1 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 9 Dec.15/13 RATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY IP Compressor Rotor Stage 3 IP Compressor Stage 3 blade (72-33-33,03-005) 99 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY LP /IP compressor Shaft and Fittings Inner race - Rear roller bearing

- LP/IP compressor drive shaft (72-33-40,04-140) 1 Gearwheel - Driving - LS gearbox drive (72-33-40,04-160) 1 Inner race - Front roller bearing - LP/IP compressor drive shaft (72-33-40,04-200) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY IP Compressor Outlet Guide Vanes IP compressor outlet guide vane multiple assembly (72-35-10,01-660) 11 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Intermediate Compressor Case Intermediate compressor case (72-35-21,01-350) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HPC IGVs HP compressor variable inlet guide vanes (72-35-24,04-025) 53

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Internal Gearbox Rear bearing support housing (72-35-42,01-320) 1 Rear bearing assembly LP compressor shaft (72-35-42,01-340) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Front bearing support housing (72-35-43,01-524) 1 Front bearing assembly - LP compressor

shaft (Mk.650-15 only) (72-35-43,01-750) 1 Front bearing assembly - LP compressor

shaft (Mks.610-8,611-8 and 620-15 only) (72-35-43,01-550) 1 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 10 Dec.15/13 RATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Spur gear assembly-driven - LS gearbox drive (72-35-44,02-020) 1 Gearshaft - driving - LS gearbox drive (72-35-44,02-150) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Gearshaft - driven - LS gearbox drive (72-35-45,02-260) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Bevel gear - driving - HS gearbox (72-35-46,03-006) 1 Retainer - bearing - driving bevel gear (72-35-46,03-015) 1 Roller - bearing - driving bevel gear (72-35-46,03-017) 30 Race outer - bearing - driving bevel gear (72-35-46,03-019) 1 Thrust bearing - driving bevel gear (72-35-46,03-035) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Gearshaft - bevel - driven - HS gearbox drive (72-35-47,03-140) 1 Retainer - bearing - driven bevel gearshaft (72-35-47,03-145) 1 Roller - bearing - driven bevel gearshaft (72-35-47,03-150) 12 Race - bearing - driven bevel gearshaft (72-35-47,03-155) 1 Thrust bearing - driven bevel gearshaft (72-35-47,03-165) 1 Housing - roller bearing and driven

bevel gearshaft (72-35-47,03-280) 1 Roller - bearing - driven bevel gearshaft (72-35-47,03-285) 12

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Bearing assembly - HP compressor rotor (72-35-48,04-040) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Compressor Case Assembly HP compressor vanes 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 11 Dec.15/13 RStage 1 vane (72-37-12,02-100) 2 Stage 1 vane (72-37-12,02-145) 2 Stage 2 vane (72-37-12,02-220) 2 Stage 2 vane (72-37-12,02-285) 2 Stage 3 vane (72-37-12,02-340) 2 Stage 3 vane (72-37-12,02-400) 2 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Compressor Case Assembly HP compressor vanes Stage 4 vane (72-37-13,02-500) 116 Stage 4 vane (72-37-13,02-502) 116 Stage 4 vane (72-37-13,02-504) 116 Stage 4 split line vane (72-37-12,02-510) 2 Stage 4, 3-span vanes (72-37-13,02-520) 2 Stage 5 vane (72-37-13,03-050) 122 Stage 5 vane (72-37-13,03-052) 122 Stage 5 vane (72-37-13,03-054) 2 Stage 5 split line vane (72-37-13,03-056) 2 Stage 5, 2-span vanes (72-37-13,03-060) 2 Stage 6 vane (72-37-13,03-100) 120 Stage 6 vane (72-37-13,03-102) 120 Stage 6 vane (72-37-13,03-104) 120 Stage 6 split line vane (72-37-13,03-106) 2 Stage 6, 2-span vanes (72-37-13,03-110) 2 Stage 7 vane (72-37-13,03-125) 108 Stage 7 vane (72-37-13,03-127) 108 Stage 7 vane (72-37-13,03-129) 108 Stage 7 vane (72-37-13,03-131) 2 Stage 7 vane (72-37-13,03-133) 2 Stage 8 vane (72-37-13,03-187) 100 Stage 8 vane (72-37-13,03-189) 100 Stage 8 vane (72-37-13,03-191) 2 Stage 8, 2-span vanes (72-37-13,03-193) 2 Stage 9 vane (72-37-13,03-240) 102 Stage 9 vane (72-37-13,03-242) 102 Stage 9 vane (72-37-13,03-244) 102 Stage 9 vane (72-37-13,03-246) 2 Stage 9, 2-span vanes (72-37-13,03-248) 2 Stage 10 vane (72-37-13,03-300) 106 Stage 10 vane (72-37-13,03-302) 106 Stage 10 vane (72-37-13,03-304) 106 Stage 10 split line vane (72-37-13,03-306) 2 Stage 10, 2-span vanes (72-37-13,03-308) 2 Stage 11 vane (72-37-13,03-370) 120 Stage 11 vane (72-37-13,03-372) 120 Stage 11 vane (72-37-13,03-374) 120 Stage 11 split line vane (72-37-13,03-376) 2 Stage 11, 2-span vanes (72-37-13,03-378) 2 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 12 Dec.15/13 RATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP compressor Case Assembly HP compressor vanes HP compressor case, 7th stage air offtake duct assembly (72-37-14,04-055) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Compressor Air Guide Tube, Drive

Shaft and Fittings Thrust bearing assembly - LP rotor (72-37-32,02-090) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Compressor Rotor Stages 1 to 3 HP compressor stage 1 blade assembly (72-37-33,03-205) 47 Shaft - HP compressor - front (72-37-33,03-237) 1 HP compressor stage 2 blade (72-37-33,03-260) 73 HP compressor spacer, stages 1 to 2 (72-37-33,03-282) 1 HP compressor stage 3 blade (72-37-33,03-305) 89 HP compressor spacer, stage 2 to 3 (72-37-33,03-327) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Compressor Stages 4 to 7 HP compressor stage 4 blade (72-37-34,04-355) 101 HP compressor spacer, stages 3 to 4 (72-37-34,04-372) 1 HP compressor stage 5 blade (72-37-34,04-390) 107 HP compressor spacer, stages 4 to 5 (72-37-34,04-395) 1 HP compressor stage 6 blade (72-37-34,04-415) 103 HP compressor spacer, stages 5 to 6 (72-37-34,04-420) 1 HP compressor stage 7 blade (72-37-34,04-440) 101 HP compressor spacer, stages 6 to 7 (72-37-34,04-445) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Compressor Rotor Stages 8 to 11 HP compressor stage 8 blade (72-37-35,05-465) 88 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 13 Dec.15/13 RHP compressor spacer, stages 7 to 8 (72-37-35,05-470) 1 HP compressor stage 9 blade (72-37-35,05-490) 89 HP compressor spacer, stage 8 to 9 (72-37-35,05-495) 1 HP compressor stage 10 blade (72-37-35,05-515) 87 HP compressor spacer, stages 9 to 10 (72-37-35,05-520) 1 HP compressor stage 11 blade (72-37-35,05-540) 88 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Compressor Stage 12 Adapter ring (72-37-36,06-150) 1 HP compressor stage 12 blade (72-37-36,06-170) 89 Seal - air - outer (72-37-36,06-190) 1 Seal - air - inner (72-37-36,06-270) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Compressor OGVs 5-span OGVs (72-37-41,01-110) 3 6-span OGVs (72-37-41,01-130) 12 HP Thrust Bearing Housing Assembly Thrust bearing assembly - HP rotor (72-37-41,01-195) 1 HP rotor thrust bearing housing assembly (72-37-41,01-225) 1 HP rotor thrust bearing housing assembly (72-37-41,01-235) 1

ATA FIG/ITEM QTY PER ENGINE Diffuser Case Diffuser case assembly (72-37-42,02-100) 1 Primary air scoop (72-37-42,02-300) 10 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Outer Combustion Case Assembly Outer combustion case assembly (72-40-30,01-100) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Combustion Liner and Discharge Nozzle

Assembly Combustion liner (72-41-11,01-020) 5 Combustion liner (72-41-11,01-160) 3 Combustion liner (72-41-11,01-295) 1 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 14 Dec.15/13 RCombustion liner (72-41-11,01-440) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Turbine NGVs Stage 1 NGV (72-41-21,01-060) 24 Stage 1 NGV (610-8,611-8 and 620-15 only) (72-41-21,01-062) 24 Stage 1 NGV (610-8,611-8 and 620-15 only) (72-41-21,01-064) 24 Stage 1 introscope NGV (650-15 only) (72-41-21,01-130) 1 Stage 2 NGV (650-15 only) (72-41-21,01-750) 26 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Turbine Bearing Support Assembly Bearing support assembly - HP turbine (72-41-22,02-185) 1 Stop ring - flexible bearing support (72-41-22,02-345) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Turbine Bearing Housing Assembly Roller bearing assembly - HP turbine (72-41-23,03-650) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Turbine Shaft Bearing sleeve - HP turbine shaft (72-41-31,01-045) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Turbine Rotor Stage 1 HP turbine stage 1 blade (72-41-32,02-040) 88 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY HP Turbine Rotor Stage 2 HP turbine stage 2 blade (72-41-33,03-290) 126 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY LP Nozzle Case and Vanes LP turbine front nozzle case (72-52-10,01-030) 1 LP turbine rear nozzle case (72-52-10,01-180) 1 Stage 1 NGV assembly (72-52-10,01-350) 8 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 15 Dec.15/13 RStage 1 NGV assembly (72-52-10,01-352) 1 Stage 1 NGV assembly (72-52-10,01-354) 9

Stage 2 NGV assembly (72-52-10,01-700) 31 Stage 3 NGV assembly (72-52-10,01-820) 1 Stage 3 NGV assembly (72-52-10,01-850) 30 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY LP Turbine Rotor Stage 1 LP turbine stage 1 blade (72-52-22,02-450) 84 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY LP Turbine Rotor Stage 2 LP turbine stage 2 blade (72-52-23,03-500) 80 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY LP Turbine Rotor Stage 3 Raceway - inner - LP turbine bearing (72-52-24,04-470) 1 LP turbine stage 3 blade (72-52-24,04-500) 76 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY LP Turbine Bearing - Support and Fairings Bearing support assembly - LP turbine (72-52-31,01-040) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY LP Turbine Bearing Support Case LP turbine case (72-52-32,02-050) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Rear Engine Mount Link - rear engine mount (72-52-40,08-020) 1 Link - rear engine mount (72-52-40,08-030) 1 Pin - rear engine mount (72-52-40,08-050) 2 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Exhaust Mixer Cone, fairing - assembly of - LP turbine

bearing support mixer (72-53-10,01-316) 1 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 16 Dec.15/13 RATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Shaft, gear driven - breather rotor (72-61-12,04-065) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Gear, spur-driving breather shaft (72-61-14,06-010) 1 Gear, spur-driving starter drive (72-61-14,06-090) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Shaft, gear-hydraulic pump drive (72-61-15,07-020) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Shaft, gear-hydraulic pump drive

(Mks.620-15 and 650-15 only) (72-61-16,08-140) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Gearshaft - idler - starter drive (72-61-18,10-040) 1 Race, roller, bearing - front (72-61-18,10-045) 1 Gear, spur-driving hydraulic pump drive (72-61-18,10-070) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Roller bearing assembly - AC generator

shaft (Mks.610-8 and 611-8 only) (72-61-19,11-660) 1 Shaft, driven bevel gear (72-61-19,11-050) 1 Gear, bevel - gearbox drive (72-61-19,11-055) 1 Gear, spur-driving idler stator drive (72-61-19,11-060) 1

Gear, spur-driving idler backing pump (72-61-19,11-090) 1 Bearing, assembly, ball thrust - driven

bevel shaft (72-61-19,11-210) 1 Shaft IDG drive 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 17 Dec.15/13 R(Mks.620-15 and 650-15 only) (72-61-19,11-340) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox

Gear spur - driven, backing pump drive (72-61-22,13-050) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Shaft - idler, oil pump drive (72-61-22,14-050) 1 Gear spur - Idler, fuel pump drive (72-61-22,14-055) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Gearshaft - driven - oil pump drive (72-61-23,15-040) 1 Roller race - front - oil pump drive (72-61-23,15-060) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Gearshaft - fuel pump drive (72-61-24,16-050) 1 Gear, spur - driving - fuel control unit (72-61-24,16-055) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Gearshaft, driven - tachometer drive (72-61-25,17-010) 1 Thrust bearing - tachometer gearshaft drive (72-61-25,17-015) 2

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Shaft - driven - FCU and RPM

indicator drive (72-61-26,18-060) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Shaft, driving wheelcase gears (72-61-27,19-010) 1 Gear, bevel driving wheelcase gears (72-61-27,19-015) 1 Thrust bearing - driving bevel gear (72-61-27,19-160) 1 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 18 Dec.15/13 RBearing housing - driving bevel gear (72-61-27,19-180) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY High Speed Gearbox Roller bearing - generator drive

(Mks.610-8 and 611-8 only) (72-61-28,20-260) 1 Shaftgear, spur - driving VSCF

generator drive (Mks.610-8 and 611-8 only) (72-61-28,20-295) 1 Gearshaft, spur, drive-VSCF

generator (Mks.610-8 and 611-8 only) (72-61-28,20-635) 1 Gearshaft, spur, idler - VSCF

generator (Mks.610-8 and 611-8 only) (72-61-28,20-640) 1 Race, outer roller - VSCF

generator driven gearshaft (Mks.610-8 and 611-8 only) (72-61-28,20-600) 1 Race, outer roller - VSCF

generator idler shaftgear (Mks.610-8 and 611-8 only) (72-61-28,20-670) 1 Retainer, roller assembly - VSCF

generator (Mks.610-8 and 611-8 only) (72-61-28,20-630) 1 Retainer, roller assembly - VSCF

generator (Mks.610-8 and 611-8 only) (72-61-28,20-650) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Low speed (L.S.) gearbox Gearwheel, bevel - driving LS gearbox (72-61-02,02-070) 1 Gearwheel, bevel - driving LS gearbox (72-61-02,02-070) 1 Gearwheel, bevel - driven LS gearbox (72-61-02,02-255) 1 Gearwheel, bevel - driven LS gearbox (72-61-02,02-315) 1

ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY By-Pass Ducts Front by-pass duct assembly (72-71-01,01-100) 1 Access panel assembly (72-71-01,01-198) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY By-Pass Ducts 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 19 Dec.15/13 RIntermediate by-pass duct assembly (72-71-02,02-240) 1 Access panel assembly (72-71-02,02-330) 3 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY By-Pass Ducts Rear by-pass duct assembly (72-71-03,03-250) 1 ATA FIG/ITEM QTY PER ENGINE PART DESCRIPTION C-S-S,FIG-ITEM QTY Fuel Spray Nozzles Nozzle assembly (73-11-06,01-005) 9 Nozzle assembly (Mk.650-15 only) (73-11-06,01-120) 1 Nozzle assembly (73-11-06,01-205) 1 Nut, spanner - nozzle retaining assembly (Mks.610-8, 611-8 and 620-15 only) (73-11-06,01-230) 1 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 20 Dec.15/13 RBlock graph for stagger programme Fig.05-00-01-990-001 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 21 Dec.15/13 RLife marking - LP compressor outlet guide vane Fig.05-00-01-990-002 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 22 Dec.15/13 RLife marking - IP compressor IGV Fig.05-00-01-990-003 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 23 Dec.15/13 RLife marking - IP compressor vane Fig.05-00-01-990-004 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 24 Dec.15/13 RLife marking - IP compressor rotor blade Fig.05-00-01-990-005 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 25 Dec.15/13 RLife marking - IP compressor outlet guide vanes Fig.05-00-01-990-006 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 26 Dec.15/13 RLife marking - HPC IGV Fig.05-00-01-990-007 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 27 Dec.15/13 RLife marking - HP compressor rotor blades Fig.05-00-01-990-008 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 28 Dec.15/13 RLife marking - HP compressor vanes Fig.05-00-01-990-009 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 29 Dec.15/13 RLife marking - HP turbine nozzle vanes Fig.05-00-01-990-010 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 30 Dec.15/13 RLife marking - Turbine rotor blade Fig.05-00-01-990-011 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 31 Dec.15/13 RLife marking - LP turbine nozzle vanes Fig.05-00-01-990-012 3RR**Printed in Great Britain**

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 32 Dec.15/13 RFLIGHT PROFILES AND OPERATIONAL MONITORING - GROUP A PARTS

TASK 05-00-02-800-000 Flight Profiles and Operational Monitoring - Group A Parts 1. Datum Flight Profiles Four sets of datum flight profiles are used to establish the declared cyclic life of the Group A parts as defined in the Time Limits Manual, Chapter 05-10-01. These datum flight profiles are defined as flight plan A to flight plan D profile operation and published in figures attached. For plan A datum flight profile, refer to Fig.05-00-02-990-009 and Fig.05-00-02-990-010. For plan B datum flight profile, refer to Fig.05-00-02-990-011 and Fig.05-00-02-990-012. For plan C datum flight profile, refer to Fig.05-00-02-990-013 and Fig.05-00-02-990-014. For plan D datum flight profile, refer to Fig.05-00-02-990-015 and Fig.05-00-02-990-016.
NOTE : Information on collection and monitoring of the flight profiles is given in Chapter 70-01-10 of the Engine R Maintenance Manual. 3RR**Printed in Great Britain**

FLIGHT PROFILES AND OPERATIONAL MONITORING 

# 05−00−02 EFFECTIVITY: TAY/ALL Page 1 Dec.15/12 RPlan A Flight Profile - HP Speed (N2) Fig.05-00-02-990-009 3RR**Printed in Great Britain**

FLIGHT PROFILES AND OPERATIONAL MONITORING 

# 05−00−02 EFFECTIVITY: TAY/ALL Page 2 Dec.15/12 RPlan A Flight Profile - LP Speed (N1) Fig.05-00-02-990-010 3RR**Printed in Great Britain**

FLIGHT PROFILES AND OPERATIONAL MONITORING 

# 05−00−02 EFFECTIVITY: TAY/ALL Page 3 Dec.15/12 RPlan B Flight Profile - HP Speed (N2) Fig.05-00-02-990-011 3RR**Printed in Great Britain**

FLIGHT PROFILES AND OPERATIONAL MONITORING 

# 05−00−02 EFFECTIVITY: TAY/ALL Page 4 Dec.15/12 RPlan B Flight Profile - LP Speed (N1) Fig.05-00-02-990-012 3RR**Printed in Great Britain**

FLIGHT PROFILES AND OPERATIONAL MONITORING 

# 05−00−02 EFFECTIVITY: TAY/ALL Page 5 Dec.15/12 RPlan C Flight Profile - HP Speed (N2) Fig.05-00-02-990-013 3RR**Printed in Great Britain**

FLIGHT PROFILES AND OPERATIONAL MONITORING 

# 05−00−02 EFFECTIVITY: TAY/ALL Page 6 Dec.15/12 RPlan C Flight Profile - LP Speed (N1) Fig.05-00-02-990-014 3RR**Printed in Great Britain**

FLIGHT PROFILES AND OPERATIONAL MONITORING 

# 05−00−02 EFFECTIVITY: TAY/ALL Page 7 Dec.15/12 RPlan D Flight Profile - HP Speed (N2) Fig.05-00-02-990-015 3RR**Printed in Great Britain**

FLIGHT PROFILES AND OPERATIONAL MONITORING 

# 05−00−02 EFFECTIVITY: TAY/ALL Page 8 Dec.15/12 RPlan D Flight Profile - LP Speed (N1) Fig.05-00-02-990-016 3RR**Printed in Great Britain**

FLIGHT PROFILES AND OPERATIONAL MONITORING 

# 05−00−02 EFFECTIVITY: TAY/ALL Page 9/10 Dec.15/12 RMAXIMUM APPROVED LIVES - RECOMMENDED GROUP B PARTS

TASK 05-00-03-800-000 Maximum Approved Lives - Recommended Group B Parts 1. Recommended Group B Parts Lives
PART DESCRIPTION PART NO. RECOMMENDED LIFE (FLIGHT CYCLE)

Pre SB 72-1320 JR34082, JR28894A 15,000 (NMSB 72-1353) LP nozzle guide vane, stage 2 (72-52-10,01-700) SB 72-1320 JR34355, JR34393A 23,000* (NMSB 72-1353) JR34496A LP nozzle guide vane, stage 2 (72-52-10,01-700) * This life limit is subject to a satisfactory borescope inspection at 20,000 flight cycles and at 22,000 flight cycles, R as stated in Non-Modification Bulletin SB 72-1353. 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−00−03 EFFECTIVITY: TAY/ALL Page 1/2 Dec.15/12 RCALENDAR LIFE LIMIT

TASK 05-00-04-800-000 Calendar Life Limit A. The calendar life of an engine operated in non-airline operation is stated in Non-Modification Service Bulletin SB 70-1050. 3RR**Printed in Great Britain**

CALENDAR LIFE LIMIT 

# 05−00−04 EFFECTIVITY: TAY/ALL Page 1/2 Jun.15/08TIME LIMITS

TASK 05-10-00-200-000 Flight Profiles and Operational Monitoring - Group A Parts

1. The content of this TASK is transfered to TASK 05-00-02-800-000 (FLIGHT PROFILES AND OPERATIONAL MONITORING, PB1) R R 3RR**Printed in Great Britain**

TIME LIMITS 

# 05−10−00 EFFECTIVITY: TAY/ALL Page 1/2 Jun.15/08 RMAXIMUM APPROVED LIVES - GROUP A PARTS AND MANDATORY GROUP B PARTS

TASK 05-10-01-800-000 AIRWORTHINESS LIMITATIONS - Maximum Approved Lives - Group A Parts and Mandatory Group B Parts

SUBTASK 05-10-01-860-036 1. General Data A. EASA TASK approval date Mar.11/2014. Approved by EASA under Approval-No. 10048464. R R B. This section details the maximum approved lives on Group A and Mandatory Group B parts which must not be exceeded in service. 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 1 Sep.15/14 RCAUTION : THE FOLLOWING AIRWORTHINESS LIMITATIONS HAVE BEEN SUBSTANTIATED BASED ON ENGINEERING ANALYSIS THAT ASSUMES THIS PRODUCT WILL BE OPERATED AND MAINTAINED USING THE PROCEDURES AND INSPECTIONS PROVIDED IN THE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS SUPPLIED WITH THIS PRODUCT BY THE TYPE CERTIFICATE HOLDER, OR ITS LICENSEES. FOR ENGINE CRITICAL PARTS AND PARTS THAT INFLUENCE ENGINE CRITICAL PARTS, ANY REPAIR, MODIFICATION OR MAINTENANCE PROCEDURES NOT APPROVED BY THE TYPE CERTIFICATE HOLDER, OR ITS LICENSEES, OR ANY SUBSTITUTION OF SUCH PARTS NOT SUPPLIED BY THE TYPE CERTIFICATE HOLDER, OR ITS LICENSEES, CAN MATERIALLY AFFECT THESE LIMITS.
CAUTION : IT IS POSSIBLE TO REACH THE MAXIMUM APPROVED LIFE OF A PART IN AN ENGINE/MODULE BETWEEN REWORKS OR BEFORE SOME OTHER REASON REQUIRES REMOVAL OF AN ENGINE/MODULE. IT IS THE OPERATORS RESPONSIBILITY TO MAKE SURE THAT THESE APPROVED PART LIVES ARE NOT EXCEEDED.
CAUTION : THE FAN DISC AND THE FAN BLADES ARE COMMON TO DIFFERENT MARKS OF TAY ENGINE. DEPENDING ON THE SERVICE BULLETIN STANDARD, THE CHANGE OF FAN DISCS AND/OR BLADES BETWEEN DIFFERENT MARKS OF TAY IS PERMITTED. HOWEVER, THE REMAINING SERVICE LIFE OF A FAN DISC OR BLADE WILL BE THE LIFE RELATED TO THE LOWEST DECLARED DISC LIFE OR RECOMMENDED BLADE LIFE ON EITHER ENGINE MARK. IT IS THE OPERATORS RESPONSIBILITY TO MAKE SURE THAT THE LIFE REMAINING, AS RECORDED IN THE ENGINE LOG BOOK, IS THAT RELATED WITH THE LOWEST LIFE DECLARED FOR EITHER ENGINE MARK.
CAUTION : R SEVERAL OF THE GROUP A PARTS AND GROUP B PARTS ARE COMMON TO DIFFERENT MARKS OF THE TAY ENGINE. THE CHANGE OF A GROUP A PART OR GROUP B PART BETWEEN THE 620-15, 650-15 AND 651-54 MARKS OF THE TAY IS PERMISSIBLE. HOWEVER, THE REMAINING SERVICE LIFE OF THAT PART WILL BE THE LIFE RELATED WITH THE LOWEST DECLARED OR RECOMMENDED LIFE OF THAT PART ON EITHER ENGINE MARK. IT IS THE REPAIR FACILITY / OPERATORS RESPONSIBILITY TO MAKE SURE THAT THE LIFE REMAINING, AS RECORDED IN THE ENGINE LOG BOOK, IS THAT RELATED WITH THE LOWEST LIFE DECLARED OR RECOMMENDED FOR EITHER ENGINE MARK. IT IS NOT PERMISSIBLE TO CHANGE A GROUP A PART OR GROUP B PART FROM THE 611-8 OR 611-8C MARKS TO THE 620-15, 650-15 OR 651-54 MARKS OF THE TAY AND VICE VERSA. R R R R R R R R R R R R
CAUTION : SEVERAL OF THE GROUP A PARTS ARE COMMON TO THE TAY AND OTHER ENGINE TYPES. THE CHANGE OF GROUP A PARTS BETWEEN THE TAY AND OTHER ENGINE TYPES IS NOT PERMITTED. IT IS THE OPERATORS RESPONSIBILITY TO MAKE SURE THAT A GROUP A PART REMOVED FROM ONE ENGINE TYPE IS NOT RE-FITTED TO ANOTHER ENGINE TYPE.
CAUTION : IT IS PERMISSIBLE TO INTERCHANGE A GROUP A OR GROUP B PART BETWEEN THE SAME MARK OF TAY ENGINE OPERATING IN AIRLINE AND NON-AIRLINE OPERATION. NON-AIRLINE OPERATED ENGINES HAVE A CALENDAR LIFE LIMIT. WHEN TRANSFERRING THE APPLICABLE PART FROM NON-AIRLINE TO AIRLINE OPERATION, INSPECTION IN ACCORDANCE WITH THE ENGINE MANUAL MUST BE CARRIED OUT. GROUP A PARTS THAT HAVE BEEN DISASSEMBLED TO PIECE-PART LEVEL MUST BE MANDATORY INSPECTED IN ACCORDANCE WITH CHAPTER 05-20-01 OF THIS MANUAL. 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 2 Sep.15/14 RCAUTION : IT IS PERMISSIBLE TO INTERCHANGE A MODULE OR ENGINE FROM AIRLINE TO NON-AIRLINE OPERATION. NON-AIRLINE OPERATED ENGINES HAVE A CALENDAR LIFE LIMIT. WHEN TRANSFERRING THE APPLICABLE MODULE OR ENGINE FROM AIRLINE TO NON-AIRLINE OPERATION, COGNISANCE MUST BE TAKEN OF THE CALENDAR LIFE DATUM OF THE GROUP A PARTS. AT THE TIME OF TRANSFER THE GROUP A PARTS ARE IMMEDIATELY SUBJECT TO THE NON-AIRLINE CALENDAR LIFE LIMITATION. THE CALENDAR LIFE CAN BE RESET TO ZERO ONLY BY PIECE-PART INSPECTION OF ALL THE GROUP A PARTS.
CAUTION : R WHERE A GROUP A PART OR GROUP B PART IS CHANGED BETWEEN ENGINE MARKS, THE LOWEST DECLARED OR RECOMMENDED LIFE OF THE PART AS RECORDED IN THE ENGINE LOG BOOK AT CHANGE IS NEVER TO BE EXCEEDED. R R
CAUTION : R WHERE A GROUP A PART OR GROUP B PART IS CHANGED BETWEEN ENGINE MARKS, THE REMAINING LIFE IN THE CURRENT APPLICATION NEEDS TO BE UPDATED IN CASE OF LATER CHANGES TO THE DECLARED OR RECOMMENDED LIFE IN THE PARTS DONOR APPLICATION HISTORY. ROLLS-ROYCE WILL INFORM OPERATORS ABOUT SUCH CHANGES TO THE LIFE DECLARATION BY UPDATE OF THE TLM, SUPPORTED BY A NON-MODIFICATION SERVICE BULLETIN ADDRESSING ALL POTENTIALLY AFFECTED PRODUCTS. R R R R R R R
NOTE : R Donor application is the TAY engine mark in which a Group A part or Group B part was operated before a change. R R C. The lives are expressed in terms of flight cycles based on a datum flight profile, refer to TASK 05-00-02-800-000 (FLIGHT PROFILES AND OPERATIONAL MONITORING, PB1). The definition of a flight cycle and the method of recording and controlling the lives of parts is described in TASK 05-00-01-800-801 (RECORDING AND CONTROL OF THE LIVES OF PARTS, PB1). D. Part Numbers In some cases, for compatibility with the engine log book, the critical group A component part number and assembly part number are listed. E. Pro rata calculation of Group A Parts and Group B Parts interchanged between engines with different Flight Profiles. Four flight profiles are applicable to the Tay 650-15 engine. Plan A, plan B, plan C and plan D. (1) The following conditions exist where the flight plan or cyclic life limit can change and which will require a calculation of the residual life of Group A and Group B parts: (a) An Operator changes flight plans, e.g. from flight plan B to flight plan A. (b) An engine is transferred from one Operator to another Operator with a different flight plan, e.g. from flight plan D to flight plan B. 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 3 Sep.15/14 R(c) A Group A part or mandatory Group B part is transferred between two engines with different flight profiles. (2) In the event of any of the three conditions above, a pro rata calculation is carried out to establish the residual life of the applicable part(s). The formula is as follows: (Number of cycles accumulated in old plan, divided by cyclic life limit in old plan) multiplied by cyclic life limit in new plan. This equals the new achieved cyclic life of the part. The new achieved cycles are subtracted from the new plan cycles limit to give the residual life of the part.
NOTE : If more than two Operators are involved, the individual ratios of each Operator are added together and then multiplied by the new cyclic life limit (refer to example 3 below).
NOTE : Flight cycles are recorded in complete numbers. If the pro rata figure is calculated into decimals, the highest complete figure is to be recorded (e.g. 3723.7 is rounded to 3724).
NOTE : The examples used are based upon the cyclic life limits contained in Transmittal Letter 9 of the Time Limits Manual. These limits can be changed in a future issue. Example 1. An Operator has achieved 3400 Cycles Since New (CSN) in flight plan B. The operator has now been confirmed in flight plan A. Using the LP compressor rotor disc as an example: 3400 (achieved cycles in plan B) divided by 21000 (plan B life limit) = 0.1619 0.1619 multiplied by 23000 (plan A limit) = 3724 (3723.7), therefore the new achieved cyclic life is 3724 flight cycles. The residual life of the part in flight plan A is 23000 - 3724 = 19276 flight cycles.

Example 2. An engine has achieved 7600 CSN in service with a flight plan A Operator. The engine is now being transferred to a flight plan D Operator. Using the LP compressor rotor disc as an example: 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 4 Sep.15/14 R7600 (achieved cycles in plan A) divided by 23000 (plan A life limit) = 0.33043 0.33043 multiplied by 20000 (plan D limit) = 6609 (6608.6), therefore the new achieved cyclic life is 6609 flight cycles. The residual life of the part in flight plan D is 20000 - 6609 = 13391 flight cycles.

Example 3 (Multiple Operators). An engine has achieved 6700 CSN in service with a flight plan A Operator. The engine was then transferred to a plan B Operator who accumulated a further 2300 cycles. The engine is now being transferred to a flight plan C Operator. Using the LP compressor rotor disc as an example: 6700 (achieved cycles in plan A) divided by 23000 (plan A life limit) = 0.29130 2300 (achieved cycles in plan B) divided by 21000 (plan B life limit) = 0.10952 Add these two figures together (0.29130 + 0.10952) = 0.40082 0.40082 multiplied by 20000 (plan C limit) = 8017 (8016.4), therefore the new achieved cyclic life is 8017 flight cycles. The residual life of the part in flight plan C is 20000 - 8017 = 11983 flight cycles. F. Combination of pro-rata calculation and consideration of lowest declared life at engine mark changes R R Example 1 R History (sequential) R R Consumed cycles R Approved life Tay 650-15 Plan A R 2300 23000 R Tay 650-15 Plan C R 5000 20000 R Pro-Rata Tay 650-15 Plan D R 5000 18700 R Pro-Rata Tay 620-15 Plan A R 2000 22000 R Adopts an Approved Life R Tay 620-15 Plan B R 1500 20000 R Cannot pro-rata due to adopted life R R Calculation of life for new application: R Change between Tay 650-15 missions by sequential pro-rata: R 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 5 Sep.15/14 RConsumed cycles = R 2300/23000 X 20000 = R 2000 Remaining life = R 20000-2000 = R 18000 R Tay 650 A to C Consumed cycles at change = R R 2000+5000 = R 7000 Consumed cycles = R 7000/20000 X 18700 = R 6545 Remaining life = R 18700-6545 = R 12155 R Tay 650 C to D Change between engine marks Tay 650-15 plan D to Tay 620-15 plan A R Consumed cycles at change = R R 6545+5000 = R 11545 Lower Approved Life = R 18700 R Adopted Approved Life of 650 Plan D R R Remaining life = R 18700-11545 = R 7155 Tay 650 D to Tay 620 A R Change between missions Tay 620-15 plan A to Tay 620-15 Plan B R Consumed cycles at change = R 11545+2000 = R 13545 Approved life of new mission is greater than adopted Approved Life R Lower Approved Life = R 18700 R Adopted Approved Life of 650 Plan D R R Remaining life = R 18700-13545 = R 5155 Tay 620 A to Tay 620 B R FINAL consumed cycles = R 13545+1500 = R 15045 R FINAL remaining life = R 18700-15045 = R 3655 Example 2 R History (sequential) R R Consumed cycles R Approved life Tay 620-15 Plan A R 2000 22000 R Tay 620-15 Plan B R 1500 20000 R Pro-Rata Tay 650-15 Plan A R 2300 23000 R Adopts an Approved Life R Tay 650-15 Plan D R 5000 18700 R Can pro-rata due to lower Approved Life R R Tay 650-15 Plan A R 2300 23000 R Can pro-rata, but limited to adopted life R R Calculation of life for new application: R Change between Tay 620-15 missions by pro-rata: R 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 6 Sep.15/14 RConsumed cycles = R 2000/22000 X 20000 = R 1819 Remaining life = R 20000-1819 = R 18181 Tay 620 A to B Change between engine marks Tay 620-15 Plan B to Tay 650-15 Plan A R Consumed cycles at change = R R 1819+1500 = R 3319 Lower Approved Life = R 20000 R Adopted Approved Life of 620 Plan B R R Remaining life = R 20000-3319 = R 16681 R Tay 620 B to Tay 650 A R Change between missions Tay 650-15 Plan A to Tay 650-15 Plan D R Consumed cycles at change = R 3319+2300 = R 5619 Approved Life of new mission is smaller than adopted Approved Life R Consumed cycles = R 5619/20000 X 18700 = R 5254 Remaining life = R 18700-5254 = R 13446 R Tay 650 A to D Changes between missions Tay 650-15 Plan D to Tay 650-15 Plan A R Consumed cycles at change = R 5254+5000 = R 10254 Approved Life of new mission is equal to adopted Approved Life: R Lower consumed cycles = R 10254/18700 X 20000

= R R 10967 Remaining life = R 20000-10967 = R 9033 Tay 650 A to D FINAL consumed cycles = R 10967+2300 = R 13267 R FINAL remaining life = R 20000-13267 = R 6733 Example 3 R History (sequential) R R Consumed cycles R Approved life Tay 651-54 R 2000 20000 R Tay 650-15 Plan B R 4000 21000 R Adopts an Approved Life R Tay 650-15 Plan A R 2300 23000 R Cannot pro-rata due to adopted life R R Tay 650-15 Plan D R 5000 18700 R Can pro-rata due to lower Approved Life R R Tay 650-15 Plan B R 3000 21000 R Can pro-rata, but limited to adopted life R R Calculation of life for new application: R 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 7 Sep.15/14 RChange between engine marks Tay 651-54 to Tay 650-15 Plan B R Consumed cycles at change = R R 2000 = R 2000 Lower Approved Life = R 20000 R Adopted Approved Life of Tay 651 R R Remaining life = R 20000-2000 = R 18000 R Tay 651 to Tay 650 B R Change between missions Tay 650-15 Plan B to Tay 650-15 Plan A R Consumed cycles at change = R 2000+4000 = R 6000 Approved life of new mission is greater than adopted Approved Life R Lower Approved Life = R 20000 R Adopted Approved Life of Tay 651 R R Remaining life = R 20000-6000 = R 14000 R Tay 620 B to Tay 650 A R Change between missions Tay 650-15 Plan A to Tay 650-15 Plan D R Consumed cycles at change = R 6000+2300 = R 8300 Approved Life of new mission is smaller than adopted Approved Life R Consumed cycles = R 8300/20000 X 18700 = R 7761 Remaining life = R 18700-7761 = R 10939 R Tay 650 A to Tay 650 D R Change between missions Tay 650-15 Plan D to Tay 650-15 Plan B R Consumed cycles at change = R 7761+5000 = R 12761 Approved Life of new mission is greater than adopted Approved Life and current application has lower Approved Life than the adopted Approved Life: R R Consumed cycles = R 12761/18700 X 20000 = R 13649 Remaining life = R 20000-13649 = R 6351 Tay 650 D to B R FINAL consumed cycles = R 13649+3000 = R 16649 FINAL remaining life = R 20000-16649= R 3351 G. All group A part lives listed are non-finite, unless otherwise indicated. 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 8 Sep.15/14 RSUBTASK 05-10-01-870-001 2. Group A Parts Lives Part Description Part No. Plan A (Flight Cycles Plan B (Flight Cycles Plan C (Flight Cycles Plan D (Flight Cycles Pre SB 72-1356 LP compressor rotor dics assembly (72-31-11,01-100) JR31198A (JR31199@) 23,000 21,000 20,000 18,700

SB 72-1356 LP compressor rotor dics assembly (72-31-11,01-100) JR34563A (JR34305@) 23,000 21,000 20,000 18,700

IP compressor rotor dics stage 1 (72-33-31,01-025) JR28921 23,000 21,000 20,000 20,000

IP compressor rotor dics stage 2 (72-33-32,02-025) JR28922 23,000 21,000 20,000 20,000

IP compressor rotor dics stage 3 (72-33-33,03-025) JR29568 23,000 21,000 20,000 20,000

Pre SB 72-1416 LP/IP compressor drive shaft (72-33-40,04-100) JR32465 23,000 21,000 20,000 20,000

SB 72-1416 LP/IP compressor drive shaft (72-33-40,04-100) JR35036 23,000 21,000 20,000 20,000

Pre SB 72-1416 HP compressor rotor rear drive shaft (72-37-31,01-010) JR32289 (part of assembly JR32288A) 22,000 20,000 20,000 20,000

SB 72-1416 HP compressor rotor rear drive shaft (72-37-31,01-010) JR35029 (part of assembly JR35028A) 22,000 20,000 20,000 20,000 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 9 Sep.15/14 RSB 72-1458 Part 1 HP compressor rotor rear drive shaft (72-37-31,01-010) JR35208 (part of assembly JR35207A) 22,000 20,000 20,000 20,000

SB 72-1458 Part 2 HP compressor rotor rear drive shaft (72-37-31,01-010) JR32289 (part of assembly JR35204A) 22,000 20,000 20,000 20,000

SB 72-1458 Part 3 HP compressor rotor rear drive shaft (72-37-31,01-010) JR35029 (part of assembly JR35205A) 22,000 20,000 20,000 20,000

SB 72-1665 HP compressor rotor rear drive shaft (72-37-31,01-010) JR57392 (part of assembly JR57309) 22,000 20,000 20,000 20,000

Pre SB 72-1416 LP compressor rotor rear drive shaft (72-37-32,02-085) JR32466 23,000 21,000 20,000 20,000

SB 72-1416 LP compressor rotor rear drive shaft (72-37-32,02-085) JR35037 23,000 21,000 20,000 20,000

HP compressor rotor disc stage 1 (72-37-33,03-165) JR18049 22,000*** 20,000*** 20,000*** 20,000***

*** The life limit of some of these critical parts have been reduced. For details see SB 72-A1740. HP compressor rotor disc stage 2 (72-37-33,03-250) JR18742 22,000 20,000 20,000 20,000

HP compressor rotor disc stage 3 (72-37-33,03-295) JR18743 22,000*** 20,000*** 20,000*** 20,000***

*** The life limit of some of these critical parts have been reduced. For details see SB 72-A1740. HP compressor rotor disc stage 4 (72-37-34,04-340) JR18744 22,000 20,000 20,000 20,000 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 10 Sep.15/14 RHP compressor rotor disc stage 5 (72-37-34,04-385) JR18746 22,000 20,000 20,000 20,000

HP compressor rotor disc stage 6 (72-37-34,04-410) JR18748 22,000*** 20,000*** 20,000*** 20,000***

*** The life limit of some of these critical parts have been reduced. For details see SB 72-A1740. HP compressor rotor disc stage 7 (72-37-34,04-435) JR17365 22,000*** 20,000*** 20,000*** 20,000***

*** The life limit of some of these critical parts have been reduced. For details see SB 72-A1740. HP compressor rotor disc stage 8 (72-37-35,05-460) JR17367 22,000 20,000 20,000 20,000

HP compressor rotor disc stage 9 (72-37-35,05-485) JR17369 22,000 20,000 20,000 20,000

HP compressor rotor disc stage 10 (72-37-35,05-510) JR18526 22,000 20,000 20,000 20,000

HP compressor rotor disc stage 11 (72-37-35,05-535) JR17373 22,000 20,000 20,000 20,000

Pre SB 72-1121 HP compressor rotor disc, stage 10/11 spacer (72-37-35,05-545) JR32209 22,000 20,000 20,000 20,000

SB 72-1121 HP compressor rotor disc, stage 10/11 spacer (72-37-35,05-545) JR32298 22,000 20,000 20,000 20,000

HP compressor rotor disc, stage 12 (72-37-36,06-160) JR31928 (part of assembly JR31927A) 22,000*** 20,000*** 20,000*** 20,000***

*** The life limit of some of these critical parts have been reduced. For details see SB 72-A1740. 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 11 Sep.15/14 RHP compressor rotor disc, stage 11/12 spacer (72-37-36,06-180) JR32213 22,000 20,000 20,000 20,000

Pre SB 72-1327 HP turbine shaft (72-41-31,01-027) JR32287 (part of sub assembly JR32286A and assembly JR32285A) 23,000 21,000 21,000 20,000

SB 72-1327 Part 1 HP turbine shaft (72-41-31,01-027) JR34539 (part of sub assembly JR34537A and assembly JR34554A) 23,000 21,000 21,000 20,000

SB 72-1327 Part 2 HP turbine shaft (72-41-31,01-027) JR34538 (part of sub assembly JR34536A and assembly JR34555A) 23,000 21,000 21,000 20,000

SB 72-1327 Part 3 HP turbine shaft (72-41-31,01-027) JR34538 (part of sub assembly JR32286A and assembly JR34579A) 23,000 21,000 21,000 20,000

SB 72-1327 Part 5 HP turbine shaft (72-41-31,01-027) JR32287 (part of sub assembly JR32286A and assembly JR34791A) 23,000 21,000 21,000 20,000

SB 72-1416 HP turbine shaft (72-41-31,01-027) JR35035 (part of sub assembly JR35034A and assembly JR35033A) 23,000 21,000 21,000 20,000 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 12 Sep.15/14 RSB 72-1665 HP turbine shaft (72-41-31,01-027) JR57400 (part of sub assembly JR57401 and assembly JR57310) 23,000 21,000 21,000 20,000

Pre SB 72-1241 HP turbine rotor disc, stage 1 (72-41-32,02-010) JR32013 23,000 20,000 14,700 11,000

SB 72-1241 HP turbine rotor disc, stage 1 (72-41-32,02-010) JR33838 23,000 21,000 18,000 14,250

Pre SB 72-1241 HP turbine rotor disc, stage 2 (72-41-33,03-250) JR32014A (JR31660@) 23,000 21,000 20,000 20,000

SB 72-1241 HP turbine rotor disc, stage 2 (72-41-33,03-250) JR33839A (JR33840@) 23,000 21,000 20,000 20,000

HP turbine rotor disc, stage 2 sleeve (72-41-33,03-261) JR32553 23,000 21,000 20,000 20,000

HP turbine rotor disc, stage 2 sleeve (72-41-33,03-261) NPG2269 23,000 21,000 20,000 20,000

Pre SB 72-1416 LP turbine shaft (72-52-21,01-485) JR32471 (part of assembly JR32470A) 23,000 21,000 20,000 20,000

SB 72-1416 LP turbine shaft (72-52-21,01-485) JR35039 (part of assembly JR35038A) 23,000 21,000 20,000 20,000

LP turbine rotor disc assembly stage 1 (72-52-22,02-400) JR32318A (NPG2388@) 23,000 21,000 18,000 14,250 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 13 Sep.15/14 RSB 72-1755 LP turbine rotor disc assembly stage 1 (72-52-22,02-400) JR57972 (NPH8110@) 23,000 21,000 18,000 14,250

LP turbine rotor disc assembly stage 2 (72-52-23,03-440) JR32319 ** 23,000 21,000 21,000 20,000

SB 72-1755 LP turbine rotor disc assembly stage 2 (72-52-23,02-440) JR57973 23,000 21,000 21,000 20,000

LP turbine rotor disc assembly stage 3 (72-52-24,04-400) JR32320A (NPG2390@) ** 23,000 21,000 21,000 20,000

SB 72-1755 LP turbine rotor disc assembly stage 3 (72-52-24,04-400) JR57974 (NPH8113@) 23,000 21,000 21,000 20,000

* DENOTES FINITE LIFE
** GROUP A LIVES SHOWN FOR THESE PARTS ARE SUBJECT TO SAMPLING REQUIREMENTS DEFINED IN NON-MODIFICATION SERVICE BULLETIN TAY 72-1557
@ INCLUDED FOR COMPATIBILITY WITH ENGINE LOG BOOK

SUBTASK 05-10-01-870-002 3. Mandatory Group B Parts Lives

PART DESCRIPTION PART NO. PLAN A (FLIGHT CYCLES) PLAN B, C, D (FLIGHT CYCLES)

LP compressor rotor blade (72-31-12,02-010) JR31912 14,200 14,200 SB 72-1105, Pre SB 72-1436 LP compressor rotor blade (72-31-12,02-010) JR31911 22,000 20,000 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 14 Sep.15/14 RPART DESCRIPTION PART NO. PLAN A (FLIGHT CYCLES) PLAN B, C, D (FLIGHT CYCLES) SB 72-1436 Part 1 LP compressor rotor blade (72-31-12,02-010) JR35120 22,000 20,000

SB 72-1436 Part 2 LP compressor rotor blade (72-31-12,02-010) JR35121 22,000 20,000

SB 72-1222 LP compressor rotor blade (72-31-12,02-014) JR33865 22,000 20,000

SB 72-1222 LP compressor rotor blade (72-31-12,02-016) JR33866 22,000 20,000

* DENOTES FINITE LIFE 3RR**Printed in Great Britain**

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 15/16 Sep.15/14 RMANDATORY INSPECTIONS OF GROUP A PARTS

TASK 05-20-01-800-000 AIRWORTHINESS LIMITATION - Mandatory Inspections of Group A Parts 1. General A. Task revision date Jun.15/2008. Approved by EASA under Approval No. EASA.E.C.01618. B. A full inspection of Group A Parts is recommended by Rolls-Royce Deutschland when the component has been completely disassembled to piece-part level in accordance with the appropiate disassembly procedures contained in the Engine Manual. C. Inspections referred to as 'Focus inspect' in the relevant Engine Manual inspection task are mandatory inspections for the components listed below, in Section 2, when the following conditions are satisfied: (1) When the component has been completely disassembled to piece-part level in accordance with the appropriate disassembly procedure contained in the Engine Manual. and The part has accumulated in excess of 100 flight cycles in service since the last piece-part inspection.

or (2) The component removal was for damage or a cause directly related to its removal.

or (3) Where serviceable used components, for which the inspection history is not fully known, are being returned to service. 2. Mandatory Inspections for Individual Group A Parts LP Compressor Rotor Disc (72-31-11,01-100), EM TASK 72-31-11-200-000 (INSPECTION/CHECK-00, PB801) IP Compressor Rotor-Stage 1 Disc (72-33-31,01-025), EM TASK 72-33-31-200-000 (INSPECTION/CHECK-00, PB801) IP Compressor Rotor-Stage 2 Disc (72-33-32,02-025), EM TASK 72-33-32-200-000 (INSPECTION/CHECK-00, PB801) 3RR**Printed in Great Britain**

MANDATORY INSPECTIONS OF GROUP A PARTS 

# 05−20−01 EFFECTIVITY: TAY/ALL Page 1 Jun.15/10 RIP Compressor Rotor-Stage 3 Disc (72-33-33,03-025), EM TASK 72-33-33-200-000 (INSPECTION/CHECK-00, PB801) LP and IP Compressor Drive Shaft (72-33-40,04-100), EM TASK 72-33-40-200-000 (INSPECTION/CHECK-00, PB801) HP Compressor Rear Drive Shaft (72-37-31,01-010), R EM TASK 72-37-31-200-000 (INSPECTION/CHECK-00, PB801) LP Compressor Rotor Drive Shaft (72-37-32,02-085), EM TASK 72-37-32-200-002 (INSPECTION/CHECK-02, PB801) HP Compressor Stage 1 Rotor Disc (72-37-33,03-165), EM TASK 72-37-33-200-001 (INSPECTION/CHECK-01, PB801) HP Compressor Stages 2 and 3 Rotor Discs (72-37-33,03-250) and (72-37-33,03-295), EM TASK 72-37-33-200-002 (INSPECTION/CHECK-02, PB801) HP Compressor Stages 4, 5, 6 and 7 Rotor Discs (72-37-34,04-340), (72-37-34,04-385), (72-37-34,04-410) and (72-37-34,04-435), EM TASK 72-37-34-200-000 (INSPECTION/CHECK-00, PB801) HP Compressor Stages 8, 9, 10 and 11 Rotor Discs (72-37-35,05-460), (72-37-35,05-485), (72-37-35,05-510) and (72-37-35,05-535), EM TASK 72-37-35-200-000 (INSPECTION/CHECK-00, PB801) HP Compressor Stage 10 to 11 Rotor Disc Spacer (72-37-35,05-545), EM TASK 72-37-35-200-001 (INSPECTION/CHECK-01, PB801) HP Compressor Stage 12 Rotor Disc (72-37-36,06-160), EM TASK 72-37-36-200-001 (INSPECTION/CHECK-01, PB801) HP Compressor Stage 11 to 12 Rotor Disc Spacer (72-37-36,06-180), EM TASK 72-37-36-200-003 (INSPECTION/CHECK-03, PB801) HP Turbine Shaft (72-41-31,01-025), EM TASK 72-41-31-200-000 (INSPECTION/CHECK-00, PB801) HP Turbine Stage 1 Rotor Disc (72-41-32,02-010), EM TASK 72-41-32-200-000 (INSPECTION/CHECK-00, PB801) HP Turbine Stage 2 Rotor Disc (72-41-33,03-250), EM TASK 72-41-33-200-000 (INSPECTION/CHECK-00, PB801) LP Turbine Shaft (72-52-21,01-485) R , EM TASK 72-52-21-200-003 (INSPECTION/CHECK-03, PB801) LP Turbine Stage 1 Rotor Disc (72-52-22,02-425), EM TASK 72-52-22-200-000 (INSPECTION/CHECK-00, PB801) LP Turbine Stage 2 Rotor Disc (72-52-23,03-440), EM TASK 72-52-23-200-000 (INSPECTION/CHECK-00, PB801) 3RR**Printed in Great Britain**

MANDATORY INSPECTIONS OF GROUP A PARTS 

# 05−20−01 EFFECTIVITY: TAY/ALL Page 2 Jun.15/10 RLP Turbine Stage 3 Rotor Disc (72-52-24,04-405), EM TASK 72-52-24-200-000 (INSPECTION/CHECK-00, PB801) 3RR**Printed in Great Britain**

MANDATORY INSPECTIONS OF GROUP A PARTS 

# 05−20−01 EFFECTIVITY: TAY/ALL Page 3/4 Jun.15/10 R

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