Printed in Great BritainContents 1 Dec.15/13 Contents 2 Dec.15/13 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 32 00-02 1 Mar.23/07 00-02 2 Mar.23/07 00-02 3/ Mar.23/07 4 00-03 1/ Jun.15/08 2 00-04 1/ Jun.15/08 2 10-00 1/ May 1/98 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 20-01 1 Jun.15/10 20-01 2 Jun.15/10 20-01 3/ Jun.15/10 4 --------------- END --------------- 5RRPrinted 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

- GROUP A PARTS(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(Time limits) 1

MAXIMUM APPROVED LIVES - GROUP A PARTS AND MANDATORY GROUP B PARTS 05-10-01 MAXIMUM APPROVED LIVES(AIRWORTHINESS

LIMITATIONS - Maximum Approved Lives - Group A Parts and Mandatory Group B Parts) 1 5RRPrinted in Great Britain CHAPTER 05 - TIME LIMITS
TABLE OF CONTENTS



# 05−CONTENTS Page 1 Dec.15/13 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 5RRPrinted in Great Britain



# 05−CONTENTS Page 2 Dec.15/13 CHAPTER BREAKOUT SECTION CONFIG/ SUBJECT SUBJECT PAGE EFFECTIVITYRECORDING 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 E.E.L. 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. The making by Rolls-Royce of a recommendation of the life of a part does not imply that any particular part will achieve this life and it does not constitute a warranty of the part by Rolls-Royce. The appropriate warranty arrangements made between Rolls-Royce and the operator will govern 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 (05-10-01, MAXIMUM APPROVED LIVES, Page Block 1). The remaining Group B parts which are not mandatory life limited but are given recommended lives are also listed in TASK 05-10-01-800-000 (05-10-01, MAXIMUM APPROVED LIVES, Page Block 1) .
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. 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 1 Dec.15/13 RIdentify 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. 3. 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 therefore subjected to strict life limitations which must not be exceeded in service. These limitations are established from experience accumulated 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. It must be noted that while limitations are established and issued by Rolls-Royce, responsibility for controlling the lives of Group A parts in service rests with the operator. 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 Chapter 70-01-10 of the Maintenance Manuals. 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, See Chapter 70-01-10 of the Maintenance Manual. 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 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 2 Dec.15/13 RFor 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. 5. Recording of Lives
CAUTION : EMPHASIS IS PLACED ON THE VITAL IMPORTANCE OF MAINTAINING DETAILED 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. Maintain an internal record system for each Group A part, whether 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. Part serial number and modification standard must be recorded against the total life in terms of Flight Cycles and hours, both expressed numerically and not in life code letters. In the interest of rapid location of particular parts this 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 make known to 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 whether 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 or modules when returned to the operator. The same information must be sent to Rolls-Royce. 6. Mandatory Group B Parts Included in this group are parts which test and service experience have shown require special attention in service in order to avoid failures which: A. 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 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 3 Dec.15/13 RB. Though not hazardous in their own right, can threaten the integrity of a Group A part. Any mandatory life limitations developed for such parts are given in TASK 05-10-01-800-000 (05-10-01, MAXIMUM APPROVED LIVES, Page Block 1) . These parts are also identified in paragraph 9, 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 selected cases, such inspections will be instructed by means of non-modification Service Bulletins. The remaining parts in this group are those whose failure can cause extensive secondary damage. It 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 the stock depends upon those long-life parts which can require replacement over a short-time, must life-limiting features become apparent. The lives of such parts must be 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 (Fig. 1). 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. The scatter can 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. 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 4 Dec.15/13 RIt is considered necessary to life mark or maintain life records of Group B parts, refer to paragraph 8. All Group B parts are listed in paragraph 9. 7. 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. 8. 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. 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 5 Dec.15/13 ROn 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. B. 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 prior to 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 prior to 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, the letter Z is to be used in conjunction 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 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 6 Dec.15/13 R(4) Part fitted to third engine: Part date marked (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 per cent solution of OMat 1/202 Chromating touch up, followed by an application of OMat 7/24 E.E.L. resistant touch-up clear varnish. Refer to TASK 70-00-00-300-304 (TSD 594-J, OP 304). E. Position of marking The code letters must,whenever possible, 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.E. 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. 2), Fig. 05-00-01-990-003 (Fig. 3), Fig. 05-00-01-990-004 (Fig. 4), Fig. 05-00-01-990-005 (Fig. 5), Fig. 05-00-01-990-006 (Fig. 6), Fig. 05-00-01-990-007 (Fig. 7), Fig. 05-00-01-990-008 (Fig. 8), Fig. 05-00-01-990-009 (Fig. 9), Fig. 05-00-01-990-010 (Fig. 10), Fig. 05-00-01-990-011 (Fig. 11) and Fig. 05-00-01-990-012 (Fig. 12). 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. 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 7 Dec.15/13 RProximity 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 (Fig. 2) to Fig. 05-00-01-990-012 (Fig. 12). 9. List of Group B Parts

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE LP Compressor Blades LP compressor blade * 72-31-12 02-010 22

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Splitter Fairing Splitter fairing assembly 72-33-10 01-005 1 IP inlet guide vane assembly 72-33-10 01-110 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE IP Compressor Rotor Stage 1 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 8 Dec.15/13 RPART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE IP compressor stage 1 blade 72-33-31 01-005 63 IP compressor spacer, stages 1 to 2 72-33-31 01-070 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE IP Compressor Rotor Stage 3 IP Compressor Stage 3 blade 72-33-33 03-005 99

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE IP Compressor Outlet Guide Vanes IP compressor outlet guide vane

multiple assembly 72-35-10 01-660 11

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Intermediate Compressor Case Intermediate compressor case 72-35-21 01-350 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE HP Compressor Inlet Guide Vanes HP compressor variable inlet guide vanes 72-35-24 04-025 53

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Internal Gearbox 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 9 Dec.15/13 RPART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Rear bearing support housing 72-35-42 01-320 1 Rear bearing assembly LP compressor shaft 72-52-42 01-340 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Spur gear assembly-driven - LS gearbox drive 72-35-44 02-020 1 Gearshaft - driving - LS gearbox drive 72-35-44 02-150 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Gearshaft - driven - LS gearbox drive 72-35-45 02-260 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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 03-265 1 Retainer - bearing - driven bevel gearshaft 72-35-47 03-280 1 Roller - bearing - driven bevel gearshaft 72-35-47 03-285 12 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 10 Dec.15/13 RPART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Bearing assembly - HP compressor rotor 72-35-48 04-040 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE HP Compressor Case Assembly HP compressor vanes Stage 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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 72-37-13 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 03-054 122 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 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 11 Dec.15/13 RPART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE HP compressor Case Assembly HP compressor vanes HP compressor case, 7th stage air

offtake duct assembly 72-37-14 04-055 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE HP Compressor Air Guide Tube, Drive

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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 12 Dec.15/13 RPART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE HP Compressor Rotor Stages 8 to 11 HP compressor stage 8 blade 72-37-35 05-465 88 HP 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Diffuser Case Diffuser case assembly 72-37-42 02-100 1 Primary air scoop 72-37-42 02-300 10

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Outer Combustion Case Assembly Outer combustion case assembly 72-40-30 01-100 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Combustion Liner and Discharge Nozzle

Assembly 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 13 Dec.15/13 RPART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Combustion liner 72-41-11 01-020 5 Combustion liner 72-41-11 01-160 3 Combustion liner 72-41-11 01-295 1 Combustion liner 72-41-11 01-440 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE HP Turbine Bearing Housing Assembly Roller bearing assembly - HP turbine 72-41-23 03-650 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE HP Turbine Shaft Bearing sleeve - HP turbine shaft 72-41-31 01-045 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE HP Turbine Rotor Stage 1 HP turbine stage 1 blade 72-41-32 02-040 88

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE HP Turbine Rotor Stage 2 HP turbine stage 2 blade 72-41-33 03-290 126 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 14 Dec.15/13 RPART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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 Stage 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE LP Turbine Rotor Stage 1 LP turbine stage 1 blade 72-52-22 02-450 84

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE LP Turbine Rotor Stage 2 LP turbine stage 2 blade 72-52-23 03-500 80

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE LP Turbine Bearing - Support and Fairings Bearing support assembly - LP turbine 72-52-31 01-040 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE LP Turbine Bearing Support Case LP turbine case 72-52-32 02-050 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 15 Dec.15/13 RPART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Exhaust Mixer Cone, fairing - assembly of - LP turbine

bearing support mixer 72-53-10 01-316 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE High Speed Gearbox Shaft, gear driven - breather rotor 72-61-12 04-065 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE High Speed Gearbox Shaft, gear-hydraulic pump drive 72-61-15 07-020 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE High Speed Gearbox Shaft, gear-hydraulic pump drive

(Mks.620-15 and 650-15 only) 72-61-16 08-140 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 16 Dec.15/13 RPART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE bevel shaft 72-61-19 11-210 1 Shaft IDG drive

(Mks.620-15 and 650-15 only) 72-61-19 11-340 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE High Speed Gearbox

Gear spur - driven, backing pump drive 72-61-21 13-050 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE High Speed Gearbox Shaft - driven - FCU and RPM

indicator drive 72-61-26 18-060 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE High Speed Gearbox 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 17 Dec.15/13 RPART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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 Bearing housing - driving bevel gear 72-61-27 19-180 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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 20-300 1 Gearshaft, spur driven - 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE Low speed (LS) gearbox Gearwheel, bevel - driving LS gearbox 72-62-02 02-070 1 Gearwheel, bevel - driving LS gearbox 72-62-02 02-070 1 Gearwheel, bevel - driven LS gearbox 72-62-02 02-255 1 Gearwheel, bevel - driven LS gearbox 72-62-02 02-315 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE By-Pass Ducts Front by-pass duct assembly 72-71-01 01-100 1 Access panel assembly 72-71-01 01-198 4 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 18 Dec.15/13 RPART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE By-Pass Ducts Intermediate by-pass duct assembly 72-71-02 02-240 1 Access panel assembly 72-71-02 02-330 3

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE By-Pass Ducts Rear by-pass duct assembly 72-71-03 03-250 1

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE 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

PART DESCRIPTION ATA CHAPTER FIG/ITEM NUMBER QTY PER ENGINE LP fuel system pressure relief valve* 73-21-12 01-900 1 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 19 Dec.15/13 RBlock graph for stagger programme Fig. 05-00-01-990-001 (Fig. 1) 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 20 Dec.15/13 RLife marking - LP compressor outlet guide vane Fig. 05-00-01-990-002 (Fig. 2) 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 21 Dec.15/13 RLife marking - IP compressor inlet guide vane Fig. 05-00-01-990-003 (Fig. 3) 5RRPrinted 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 vane Fig. 05-00-01-990-004 (Fig. 4) 5RRPrinted 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 rotor blade Fig. 05-00-01-990-005 (Fig. 5) 5RRPrinted 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 outlet guide vanes Fig. 05-00-01-990-006 (Fig. 6) 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 25 Dec.15/13 RLife marking - HP compressor inlet guide vane Fig. 05-00-01-990-007 (Fig. 7) 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 26 Dec.15/13 RLife marking - HP compressor rotor blades Fig. 05-00-01-990-008 (Fig. 8) 5RRPrinted 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 vanes Fig. 05-00-01-990-009 (Fig. 9) 5RRPrinted 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 turbine nozzle vanes Fig. 05-00-01-990-010 (Fig. 10) 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 29 Dec.15/13 RLife marking - Turbine rotor blade Fig. 05-00-01-990-011 (Fig. 11) 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 30 Dec.15/13 RLife marking - LP turbine nozzle vanes Fig. 05-00-01-990-012 (Fig. 12) 5RRPrinted in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS 

# 05−00−01 EFFECTIVITY: TAY/ALL Page 31/32 Dec.15/13 RTASK 05-00-02-800-802 Flight Profiles and Operational Monitoring - Group A Parts 1. Datum Flight Profiles One set of datum flight profile is used to establish the declared cyclic life of the group A parts as defined in the Time Limits Manual, Chapter 05-10-01. For the datum flight profile, refer to Fig. 05-00-02-990-003 (Fig. 1) and Fig. 05-00-02-990-004 (Fig. 2).
NOTE : Information on collection and monitoring of the flight profiles is given in Chapter 70-01-10 of the Engine Maintenance Manual. 5RRPrinted in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING - GROUP A PARTS 

# 05

−00

−02 EFFECTIVITY: TAY/ALL Page 1 Mar.23/07Datum flight profile - H.P. speed (N2) Fig. 05-00-02-990-003 (Fig. 1) 5RRPrinted in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING - GROUP A PARTS 

# 05

−00

−02 EFFECTIVITY: TAY/ALL Page 2 Mar.23/07Datum flight profile - L.P. speed (N1) Fig. 05-00-02-990-004 (Fig. 2) 5RRPrinted in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING - GROUP A PARTS 

# 05

−00

−02 EFFECTIVITY: TAY/ALL Page 3/4 Mar.23/07MAXIMUM 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, UNLESS OTHERWISE STATED)

Pre SB 72-1320 (NMSB 72-1353) LP nozzle guide vane, stage 2 (72-52-10,01-700) JR34082 JR28894A 15,000

SB 72-1320 (NMSB 72-1353) LP nozzle guide vane, stage 2 (72-52-10,01-700) JR34355 JR34393A JR34496A 23,000*

* This life limit is subject to a satisfactory borescope inspection at 20,000 flight cycles and 22,000 flight cycles as stated in Non-Modification Service Bulletin 72-1353. 5RRPrinted in Great Britain

MAXIMUM APPROVED LIVES 

# 05−00−03 EFFECTIVITY: TAY/ALL Page 1/2 Jun.15/08CALENDAR LIFE LIMIT

TASK 05-00-04-800-000 Calendar Life Limit 1. 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. B. Low Use in Airline Type Operation: New, overhauled or refurbished engines with an annual use of less than 1500 flight hours have a 12 year calendar life limit. This starts from when the engines are assembled. To let them be released for 12 more years, or to complete the approved overhaul life, the engines must be reworked. The rework will be done as given in the airline ́s engine management programme (EMP) or as recommended by Rolls-Royce. At a maximum of 24 years, or when the approved overhaul life is completed, the engines and accessories will be fully overhauled. 5RRPrinted in Great Britain

CALENDAR LIFE LIMIT 

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

### PROPULSION 

### SYSTEM TIME LIMITS MANUAL



### TIME LIMITS

TASK 

### 05-10-00-200-000 Time limits

, C



# - m W 

### .- l. The information contained within this TASK is not now reauired and has been 

### h

L 

### removed. m 0 

## 6



# 0

EFFECTIVITY: TAYIALL TIME LIMITS 

# 05-1 

# 0-00 Page 112 May. 

### 1198MAXIMUM 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 05-10-01-860-037 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. 5RRPrinted 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 : 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 5RRPrinted in Great Britain

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 2 Sep.15/14 RCAUTION : 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
CAUTION : R WHERE A GROUP A PART OR GROUP B PART HAS BEEN RECEIVED FROM DONOR APPLICATION IN TAY 650-15 OR TAY 620-15, REFER TO THE TASK 05-10-01-800-000, SECTION 1. OF THE DONOR APPLICATION FOR RULES AND EXAMPLES ON CALCULATION OF CONSUMED PART LIFE AT CHANGE. IF INFORMATION FROM THE DONOR APPLICATIONS MANUAL IS NOT AVAILABLE, CONTACT ROLLS-ROYCE. 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. Unless otherwise stated, the lives are expressed in terms of flight cycles based on a datum flight profile, refer to TASK 05-00-02-800-802 (FLIGHT PROFILES AND OPERATIONAL MONITORING - GROUP A PARTS). 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). 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. All Group A part lives listed are non-finite, unless otherwise indicated.

SUBTASK 05-10-01-870-001 2. Group A Parts Lives
APPROVED LIFE PART IDENT PART NO. (FLIGHT CYCLES, UNLESS OTHERWISE STATED)

Pre SB 72-1356 LP compressor rotor disc assembly (72-31-11,01-100) JR31198A (JR31199@) 20,000

SB 72-1356 LP compressor rotor disc assembly (72-31-11,01-100) JR34563A 20,000 5RRPrinted in Great Britain

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 3 Sep.15/14 RAPPROVED LIFE PART IDENT PART NO. (FLIGHT CYCLES, UNLESS OTHERWISE STATED)
IP compressor rotor disc, stage 1 (72-33-31,01-025) JR28921 20,000
IP compressor rotor disc, stage 2 (72-33-32,02-025) JR28922 20,000
IP compressor rotor disc, stage 3 (72-33-33,03-025) JR29568 20,000

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

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

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

SB 72-1416 HP compressor rotor rear drive shaft (72-37-31,01-010) JR35029 (part of assembly JR35028A) 20,000

SB 72-1458 Part 1 HP compressor rotor rear drive shaft (72-37-31,01-010) JR35208 (part of assembly JR35207A) 20,000

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

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

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

Pre SB 72-1416 LP compressor rotor drive shaft (72-37-32,02-085) JR32466 20,000 5RRPrinted in Great Britain

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 4 Sep.15/14 RAPPROVED LIFE PART IDENT PART NO. (FLIGHT CYCLES, UNLESS OTHERWISE STATED)

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

HP compressor rotor disc, stage 1 (72-37-33,03-165) JR18049 18,800
HP compressor rotor disc, stage 2 (72-37-33,03-250) JR18742 20,000
HP compressor rotor disc, stage 3 (72-37-33,03-295) JR18743 18,100
HP compressor rotor disc, stage 4 (72-37-34,04-340) JR18744 20,000
HP compressor rotor disc, stage 5 (72-37-34,04-385) JR18746 20,000
HP compressor rotor disc, stage 6 (72-37-34,04-410) JR18748 19,300
HP compressor rotor disc, stage 7 (72-37-34,04-435) JR17365 17,300
HP compressor rotor disc, stage 8 (72-37-35,05-460) JR17367 20,000
HP compressor rotor disc, stage 9 (72-37-35,05-485) JR17369 20,000
HP compressor rotor disc, stage 10 (72-37-35,05-510) JR18526 20,000
HP compressor rotor disc, stage 11 (72-37-35,05-535) JR17373 20,000

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

SB 72-1121 HP compressor rotor disc, stage 10/11 spacer (72-37-35,05-545) JR32298 20,000 5RRPrinted in Great Britain

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 5 Sep.15/14 RAPPROVED LIFE PART IDENT PART NO. (FLIGHT CYCLES, UNLESS OTHERWISE STATED)

HP compressor rotor disc, stage 12 (72-37-36,06-100) JR31928 (part of assembly JR31927A) 18,900

HP compressor rotor disc, stage 11/12 spacer (72-37-36,06-180) JR32213 20,000

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

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

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

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

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

SB 72-1416 HP turbine shaft (72-41-31,01-027) JR35035 (part of sub assembly JR35034A and assembly JR35033A) 20,000

SB 72-1665 HP turbine shaft (72-41-31,01-027) JR57400 (part of sub assembly JR57401 and assembly JR57310) 20,000 5RRPrinted in Great Britain

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 6 Sep.15/14 RAPPROVED LIFE PART IDENT PART NO. (FLIGHT CYCLES, UNLESS OTHERWISE STATED)

Pre SB 72-1241 HP turbine rotor disc, stage 1 (72-41-32,02-010) JR32013 12,600

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

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

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

HP turbine rotor disc, stage 2 sleeve (72-41-33,03-261) JR32553 (NPG2269) 20,000 20,000 Pre SB 72-1416 LP turbine shaft (72-52-21,01-485) JR32471 (part of assembly JR32470A) 20,000

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

LP turbine rotor disc assembly, stage 1 (72-52-22,02-400) JR32318A (NPG2388@) 20,000
LP turbine rotor disc, stage 2 (72-52-23,03-440) JR32319 ** 20,000
LP turbine rotor disc assembly, stage 3 (72-52-24,04-400) JR32320A ** (NPG2390@) 20,000

* DENOTES FINITE LIFE
** GROUP A LIVES SHOWN FOR THESE PARTS ARE SUBJECT TO SAMPLING REQUIREMENTS DEFINED IN NON-MODIFICATION SERVICE BULLETIN SB 72-1557
@ INCLUDED FOR COMPATIBILITY WITH ENGINE LOG BOOK 5RRPrinted in Great Britain

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 7 Sep.15/14 RSUBTASK 05-10-01-870-002
CAUTION : THE MANDATORY LIVES GIVEN ARE CALCULATED WITH A RESTRICTION OF FOUR RE-APPLICATIONS OF DRY FILM LUBRICANT TO THE BLADE DOVETAIL ROOT. DO NOT EXCEED THIS LIMIT. 3. Mandatory Group B Parts Lives
APPROVED LIFE PART IDENT PART NO. (FLIGHT CYCLES, UNLESS OTHERWISE STATED) LP compressor rotor blade (72-31-12,02-010) JR31912 14,200
SB 72-1105, Pre SB 72-1436 LP compressor rotor blade (72-31-12,02-010) JR31911 20,000

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

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

LP fuel system pressure relief valve (73-21-12,01-900) 70201-3 10,000 HOURS 5RRPrinted in Great Britain

MAXIMUM APPROVED LIVES 

# 05−10−01 EFFECTIVITY: TAY/ALL Page 8 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) 5RRPrinted 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 (72-52-22,02-400), 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) 5RRPrinted 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 (72-52-24,04-400), EM TASK 72-52-24-200-000 (INSPECTION/CHECK-00, PB801) 5RRPrinted 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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