RR RB211 - 535E4 TLM: 05 - 00 - 01 - 800 - 000 Recording and Control of the

Lives of PartsRR RB211 - 535E4TLM 05 - 00 - 01 - 800 - 000RevDate: Jul 01/14 Recording and Control of the Lives of Parts Effectivity: 535/ALL RECORDING AND CONTROL OF THE LIVES OF PARTS Printed: Mar 31/15 THIS PAGE MUST NOT BE RETAINED FOR REFERENCE TASK 05 - 00 - 01 - 800 - 000 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 plc. Such information will assist in spares provisioning, warranty claims, repair planning and the establishment of an economical operation. The making by Rolls -Royce plc 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 plc. The appropriate warranty arrangements made between Rolls -Royce plc and the operator will govern the relationships 1between 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'. Group 'A' parts and their mandatory lives are listed in the Time Limits Manual, TASK 05 - 10 - 01 - 800 - 000. Group 'B' parts are listed in this TASK. 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 (C.A.A.) 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 plc 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 may prove to be less than that permitted by Rolls -Royce plc for airworthiness consideration; for example, corrosion or wear may result in rejection of the part at an earlier life than the quoted limitation. It should be noted that while limitations are established and issued by Rolls -Royce plc, responsibility for controlling the lives of Group 'A' parts in service rests with the 2operator.

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 of parts which are primarily affected by cyclic stresses. Variations in stage lengths, flight patterns and thrust reverser operations may be taken into consideration when establishing the lives. There may be certain parts which are influenced as much by the total hours they are in service as by the number of flight cycles they complete; these hours are defined as the difference in time between the aircraft leaving the ground and it touching down. In such cases, the lives are expressed in flight cycles and hours, whichever is completed first being the limiting factor. 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. CAUTION: FOR CALCULATIONS USED IN THE FOLLOWING TABLE THE WORD SHAFT REFERS TO THE L.P. COMPRESSOR ROTOR SHAFT AND THE I.P. AND L.P. TURBINE SHAFT ONLY.WITH THE EXCEPTION OF BLADES ALL OTHER COMPONENTS MUST BE CONSIDERED AS DISCS B. Pilot Training One `Flight Cycle` as normal for the training flight plus the following additions which must be made for each 3`touch and go`

or `overshoot`: (1) One fifth of a 'Flight Cycle' for a disc. (2) One fifth of a 'Flight Cycle' for each LP compressor (fan) blade and annulus fillers (3) One 'Flight Cycle' for a shaft. For example, one training flight that includes one 'overshoot' and four 'touch and go' is the equivalent of two 'Flight Cycles' for a disc and each LP compressor (fan) blade and annulus fillers and six 'Flight Cycles' for a shaft. NOTE: If the flight cycles are to be recorded as whole numbers, any final cyclic calculations must be rounded up to the nearest whole number for records. 5. Recording of Lives CAUTION: EMPHASISIS IS PLACED ON THE VITAL IMPORTANCE OF THE CONTROL OF GROUP A PARTS BY MAINTAINING DETAILED LIFE RECORDS . THESE RECORDS FORM THE ONLY IDENTIFICATION OF THE LIFE COMPLETED BY EACH PART THEREBY MAKING ANY MARKING OF THESE PARTS UNNECESSARY AND COULD COMPROMISE PART INTEGRITY The repair facility is required to make records and supply information as follows: A. Maintain an internal record system for each Group 'A' and B* parts, whether in service or held serviceable in stores 4pending 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 should 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 plc 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 to 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 should be included with the paperwork accompanying engines or modules when returned to the operator. The same information must be sent to Rolls -Royce plc. 6. Intermixing of Group 'A' Parts between Engine 5Marks

This Time Limits Manual (TLM) gives the approved lives for the RB211 - 535E4 engine type and the engine marks that follow: RB211 - 535E4 - 37 RB211 - 535E4 -B- 37 RB211 - 535E4 -C- 37 There are several Group 'A' part numbers that are applicable to more than one engine type or mark. It is not permitted to install a Group 'A' part that has operated in an engine type or mark not given in this TLM into one of these engine marks without the approval of Rolls -Royce plc. Refer to section 7. for intermixing of Group 'A' parts between engine marks covered by this manual. 7. Intermixing of Group 'A' and 'B' Parts between Engine Marks and/or Flight Profiles CAUTION: THIS PROCEDURE MUST NOT BE USED FOR PARTS THAT HAVE BEEN ARTIFICALLY AGED DURING A MID-LIFE REWORK, OR FOR THE CALCULATION OF REWORK THRESHOLDS. THIS INFORMATION MUST BE OBTAINED FROM ROLLS -ROYCE. A. Where the engine configuration allows, Group 'A' and Group 'B' parts may be moved between any combination of 535E4 - 37 Flight Profile 'A', 535E4 - 37 Flight Profile B, 535E4 -B- 37 and 535E4 -C- 37 operation. B. The published Declared Life of Group 'A' and Group 'B' parts may be different from one engine mark and/or flight profile to another. The Time Limits Manual 6contains four sets

of Declared Cyclic lives applicable to Group 'A' (Chapter 05 - 10 - 01) and Group 'B' (Chapter 05 - 10 - 02) parts: (1) 535E4 - 37 datum life (Flight Profile A) (2) 535E4 - 37 reduced life (Flight Profile B) (3) 535E4 -B- 37 datum life (4) 535E4 -C- 37 datum life C. The flight profiles applicable to 535E4 - 37 Flight Profiles A and B, the 535E4 -B- 37 and the 535E4 -C- 37 are published in the Aircraft Maintenance Manual, Chapter 70 - 01 - 10. D. After a component is moved between engine marks and/or flight profiles, the Declared Life relating to the new Engine Mark and/or flight profile must be used. Refer to Group 'A' parts (Chapter 05 - 10 - 01) and Group 'B' parts (Chapter 05 - 10 - 02). E. The calculations necessary to move Group 'A' and Group 'B' parts between Engine Marks and/or flight profiles are given below. (1) The following steps and Figure 05 - 00 - 01 - 990 - 014 - 001 must be completed to calculate the equivalent cycles since new (CSN) in the new Engine Mark and/or flight profile. Figure 05 - 00 - 01 - 990 - 014 - 002 details worked examples. (a) The fraction of life used must be calculated for each of the ratings and/or flight profiles in 7which the component has been

operated. Do this by dividing the cycles flown, by the declared life for each rating and/or flight profile. Refer to Group 'A' parts (Chapter 05 - 10 - 01) or Group 'B' parts (Chapter 05 - 10 - 02). (b) The total fraction of life used must now be calculated. Do this by summing up all of the fractions of the life calculated in 6.E. (1).(a) above. The answer must be less than 1.0. (c) The equivalent CSN must now be calculated. Do this by multiplying the total fraction of life used, as calculated in 6.E.(1).(b) above, by the components Declared Life in the Engine Mark and/or flight profile the component will be operated in. Refer to Group 'A' parts (Chapter 05 - 10 - 01) or Group 'B' parts (Chapter 05 - 10 - 02). NOTE: Record the equivalent CSN as an integer, calculated to the next highest whole number, against the component. (d) If required, the cycles remaining to the Declared Life may be calculated by subtracting the answer in 6.E.(1).(c) above from components Declared Life in the Engine Mark and/or flight component will be operated in. Refer to Group 'A' parts (Chapter 05 - 10 - 01) or Group 'B' parts (Chapter 05 - 10 - 02). 88. Operation to 535E4 - 37 Flight Profile 'A'

NOTE: The default Flight Profile for 535E4 - 37 operation is Flight Profile 'B'. NOTE: The requirements for classification into Flight Profile 'A' are given in the Aircraft Maintenance Manual, Chapter 70 - 01 - 10. Additional information is given below. A. Annual Review of profiles (1) After an operator has been approved to operate to Flight Profile 'A' by their local Airworthiness Authority, it is the operators responsibility, if required by his local Airworthiness Authority, to provide them with subsequent years flight profile data in order to continue operating to Flight Profile 'A'. B. Revised Component Life (1) Any operator changing from Flight Profile 'A' to Flight Profile 'B' or vice versa must notify their local Airworthiness Authority of this change and apply the calculations detailed in section 6 to calculate the equivalent component cycles since new. NOTE: The equivalent cycles since new must be recorded against each individual Group 'A' and Group 'B' Part.

99. Reliability Sensitive Parts

A. Reliability Sensitive parts are those that are not critical but must have a high level of serviceable operation to give satisfactory reliability. Operators are recommended to maintain a record of all Reliability Sensitive parts lives. Reliability Sensitive parts are sub divided into three categories. (1) Group B Group B parts are Reliability Sensitive parts, which have a recommended life. All group B parts have a serial number. It is considered necessary to life mark or maintain life records of Group 'B' parts, refer to paragraph 11. All Group 'B' parts are listed in paragraph 12. (2) Reliability Sensitive Monitored These are Reliability Sensitive parts that are given a serial number. (3) Reliability Sensitive Traceable These Reliabilty Sensitive parts do not usually have a serial number, but it is acceptable to add a serial number or life mark to the part. B. 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.

1010. 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. 11. 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 and could compromise integrity. Where a Group 'B' part is not identified by serial number which may be used in monitoring its life or paperwork records are not kept, then the part should be life marked using a suitable method as detailed. 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 11substantial

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 should 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 should be deleted at the time of life marking. B. Life marking code 12A suitable life marking code table is shown

below, utilising 25 letters covering 0 to 2,500 hours. To distinguish the code from that in use on engines of a different life range, the figure 5 (encircled) is to be engraved on the parts prior to the first life marking letter. 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 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 of life marking: - (1) Part removed from engine at 742 hours for entry into pool: Part marked 5(encircled)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(encircled)HO 13(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(encircled)HOZB CAUTION: METAL STAMPS OR ELECTRO-ETCHING MUST NOT BE USED TO LIFE MARK ANY PART. C. Method of marking To avoid the setting up of stress concentrations, the code must be applied using vibro-engraving tool. Where magnesium components are engraved, the immediate area will require reprotection. For chromated areas refer to TASK 70 - 00 - 00 - 300 - 304 (T.S.D.594 - J, O.P.304). For resistant localised protection, apply OMat 766 two pack epoxy primer and catalyst. D. Position of marking The code letters should, 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. Parts on which the life mark is to be positioned other than adjacent to the part number are specified in para.E. E. Special marking instructions (1) Compressor and turbine blades and vanes Typical examples of rotor blades and 14stator 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 - 001, Fig.05 - 00 - 01 - 990 - 005 - 002, Fig.05 - 00 - 01 - 990 - 005 - 003, Fig.05 - 00 - 01 - 990 - 005 - 004, Fig.05 - 00 - 01 - 990 - 005 - 005, Fig.05 - 00 - 01 - 990 - 006 - 001, Fig.05 - 00 - 01 - 990 - 006 - 002, Fig.05 - 00 - 01 - 990 - 006 - 003, Fig.05 - 00 - 01 - 990 - 007 - 001, Fig.05 - 00 - 01 - 990 - 007 - 002, Fig.05 - 00 - 01 - 990 - 007 - 003, Fig.05 - 00 - 01 - 990 - 007 - 004, Fig.05 - 00 - 01 - 990 - 007 - 005, Fig.05 - 00 - 01 - 990 - 007 - 006, Fig.05 - 00 - 01 - 990 - 007 - 007, Fig.05 - 00 - 01 - 990 - 008 - 001, Fig.05 - 00 - 01 - 990 - 008 - 002, Fig.05 - 00 - 01 - 990 - 009 - 001, Fig.05 - 00 - 01 - 990 - 009 - 002, Fig.05 - 00 - 01 - 990 - 009 - 003, Fig.05 - 00 - 01 - 990 - 010, Fig.05 - 00 - 01 - 990 - 011 - 001, Fig.05 - 00 - 01 - 990 - 011 - 002, Fig.05 - 00 - 01 - 990 - 012 - 001, Fig.05 - 00 - 01 - 990 - 012 - 002, Fig.05 - 00 - 01 - 990 - 012 - 003, Fig.05 - 00 - 01 - 990 - 013 - 001, Fig.05 - 00 - 01 - 990 - 013 - 002, Fig.05 - 00 - 01 - 990 - 013 - 003, Fig.05 - 00 - 01 - 990 - 013 - 004, Fig.05 - 00 - 01 - 990 - 013 - 005, Fig.05 - 00 - 01 - 990 - 013 - 006, Fig.05 - 00 - 01 - 990 - 013 - 007, Fig.05 - 00 - 01 - 990 - 013 - 008 and Fig.05 - 00 - 01 - 990 - 013 - 009. Additional component markings for build, strip and/or repair traceability purposes may also be applied in the areas depicted in the afore mentioned Figures. If the marked vane in an assembly,is replaced by a new vane, or one of comparable life to the original, the 15replacement vane should 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 - 013 - 009. Every effort should be made to keep all component markings within the permitted marking area. However, it is recognised that due to space limitations on some Rotor Blades and Stator/Nozzle Guide Vanes, it is not always possible to satisfy these requirements. In such cases, component markings extending beyond permitted marking areas may be up to, but not over, a corner, edge or radius. This exception does NOT apply to Turbine Blades. In all other aspects, component markings must comply with the requirements of the relevant marking specifications. 12. List of Group 'B' Parts Engine Front Mount A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE L.H. and R.H. inner support link pin 71 - 21 - 01 01 - 090 162

L.H. and R.H. outer support link pin 71 - 21 - 01 01 - 100 2 L.H. and R.H. support link 71 - 21 - 01 01 - 130 2 Centre thrust link pin, front 71 - 21 - 01 01 - 280 1 Centre thrust link pin, rear 71 - 21 - 01 01 - 285 1 Outer support assembly 71 - 21 - 01 01 - 400 1 Centre support link -spherical bearing housing 71 - 21 - 01 01 - 500 1 Bush, sleeve housing, centre thrust link 71 - 21 - 01 01 - 538 * 1 Engine Rear Mount A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE L.H. and R.H. link 71 - 21 - 02 01 - 112 2 Link pin 71 - 21 - 02 01 - 121 4 17Centre link

71 - 21 - 02 01 - 200 1 Link pin 71 - 21 - 02 01 - 211 2 Support bracket 71 - 21 - 02 01 - 600 1 L.P. Compressor (Fan) Module Installation A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Fan retention shaft assembly 72 - 00 - 31 01 - 384 1 H.S. External Gearbox A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Module 72 - 00 - 61 01 - 002 1 L.P. Compressor Blades and Dampers A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE LP Compressor fan blade 72 - 31 - 11 01 - 280 * 22 Fan blade annulus filler assembly 72 - 31 - 11 01 - 350 * 1822

L.P. Compressor Disc, Thrust Ring and Seals A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Nose cone support ring assembly 72 - 31 - 12 01 - 152 1 L.P. Compressor Rotor Shaft A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Inner bearing race 72 - 31 -20 01 - 200 1 I.P. Compressor Front Bearing Support A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Housing assy 72 - 32 - 11 01 - 140 1 L.P. compressor front roller bearing 72 - 32 - 11 03 - 420 1 I.P. compressor front roller bearing 72 - 32 - 11 03 - 920 1 I.P. Compressor Shafts A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Rear curvic ring, I.P. compressor 1972 - 32 - 31

01 - 060 1 Front stub shaft 72 - 32 - 31 01 - 070 1 I.P. Compressor Blades A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Stage 1 blade 72 - 32 - 32 01 - 130 50 Stage 2 blade 72 - 32 - 32 01 - 150 57 Stage 3 blade 72 - 32 - 32 01 - 170 48 Stage 4 blade 72 - 32 - 32 01 - 190 53 Stage 5 blade 72 - 32 - 32 01 - 231 49 Stage 6 blade 72 - 32 - 32 01 - 251 46 I.P. Compressor Case A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Stage 1 rotor case 2072 - 32 - 41

01 - 020 1 Stage 2 to 6 case 72 - 32 - 41 01 - 050 1 I.P. Compressor Stator Vanes A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Stage 1 vane 72 - 32 - 42 02 - 040 50 Stage 1 vane 72 - 32 - 42 02 - 080 8 Stage 1 vane 72 - 32 - 42 02 - 120 2 Stage 1 vane 72 - 32 - 42 02 - 136 38 Stage 1 vane 72 - 32 - 42 02 - 137 38 Stage 1 vane 72 - 32 - 42 02 - 160 2 Stage 2 vane 72 - 32 - 42 02 - 290 58 Stage 2 vane 72 - 32 - 42 2102 - 330

8 Stage 2 vane 72 - 32 - 42 02 - 370 2 Stage 2 vane 72 - 32 - 42 02 - 386 38 Stage 2 vane 72 - 32 - 42 02 - 387 38 Stage 2 vane 72 - 32 - 42 02 - 410 2 Stage 2 vane 72 - 32 - 42 02 - 450 1 Stage 2 vane 72 - 32 - 42 02 - 490 1 Stage 3 vane 72 - 32 - 42 03 - 040 52 Stage 3 vane 72 - 32 - 42 03 - 080 8 Stage 3 vane 72 - 32 - 42 03 - 136 38 Stage 3 vane 72 - 32 - 42 03 - 137 38 22Stage 3 vane

72 - 32 - 42 03 - 120 2 Stage 3 vane 72 - 32 - 42 03 - 160 2 Stage 4 vane 72 - 32 - 42 03 - 290 63 Stage 4 vane 72 - 32 - 42 03 - 320 8 Stage 4 vane 72 - 32 - 42 03 - 360 2 Stage 4 vane 72 - 32 - 42 03 - 375 38 Stage 4 vane 72 - 32 - 42 03 - 376 38 Stage 4 vane 72 - 32 - 42 03 - 400 2 Stage 4 vane 72 - 32 - 42 03 - 475 1 Stage 5 vane 72 - 32 - 42 04 - 060 66 Stage 5 vane 2372 - 32 - 42

04 - 082 8 Stage 5 vane 72 - 32 - 42 04 - 088 2 Stage 5 vane 72 - 32 - 42 04 - 100 2 Stage 5 vane 72 - 32 - 42 04 - 125 38 Stage 5 vane 72 - 32 - 42 04 - 130 38 Outlet guide vane 72 - 32 - 42 04 - 350 78 Outlet guide vane 72 - 32 - 42 04 - 368 8 Outlet guide vane 72 - 32 - 42 04 - 374 2 Outlet guide vane 72 - 32 - 42 04 - 418 2 Outlet guide vane 72 - 32 - 42 04 - 420 38 Outlet guide vane 72 - 32 - 42 04 - 425 2438

Outlet guide vane 72 - 32 - 42 04 - 460 1 Outlet guide vane 72 - 32 - 42 04 - 465 1 I.P. Compressor Inner Shrouds A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Stage 1 shroud 72 - 32 - 42 02 - 575 1 Stage 2 shroud 72 - 32 - 42 02 - 620 1 Stage 3 shroud 72 - 32 - 42 03 - 575 1 Stage 4 shroud 72 - 32 - 42 03 - 620 1 Stage 5 shroud 72 - 32 - 42 04 - 020 1 Outlet guide vane shroud 72 - 32 - 42 04 - 540 1 Compressor Intermediate Case Module A.T.A.FIG/ITEMQTY PER 25PART DESCRIPTIONCHAPTERNUMBERENGINE

I.P. Compressor location bearing conical support assembly 72 - 33 - 00 01 - 020 1 Compressor Intermediate Case A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE H.P. location bearing support cone assembly 72 - 33 - 10 04 - 200 1 Intermediate Case 72 - 33 - 10 04 - 500 1 I.P. Location Bearing A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Internal gearbox annular panel assembly 72 - 33 -21 01 - 171 1 I.P. compressor location bearing assembly 72 - 33 -21 01 - 300 1 I.P. compressor to turbine rigid shaft coupling 72 - 33 -21 01 - 415 1 I.P. shaft coupling locking sleeve 72 - 33 -21 01 - 385 1 26L.P. Location Bearing

A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE L.P. compressor location ball bearing assy 72 - 33 -22 01 - 095 1 Internal Gearbox, Driving Gearshaft Assembly A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Bevel driving shaft 100T 72 - 33 - 31 01 - 050 1 H.P. location ball bearing assembly 72 - 33 - 31 01 - 130 1 Driving shaft assy 72 - 33 - 31 01 - 270 1 Internal Gearbox, Driven Gearshaft Assembly A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Bevel driven shaft 39T 72 - 33 - 32 01 - 670 1 L.P. Compressor (Fan) Case Support Structure (Not A-Frame) A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Thrust Reverser duct assembly -flanged 27locating ring

72 - 34 - 11 02 - 020 1 L.P. compressor rear case diaphragm assembly 72 - 34 - 11 02 - 300 1 L.P. Compressor (Fan) Case Support Structure (AFrame) A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE L.H. L.P. compressor case support assembly 72 - 34 - 13 01 - 085 1 R.H. L.P. compressor case support assembly 72 - 34 - 13 01 - 185 1 L.P. Compressor (Fan) Case A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Front case assembly 72 - 34 - 14 01 - 300 1 L.P. compressor outlet guide vane and rear case assembly 72 - 34 - 15 03 - 499 1 L.P. Compressor Intake Rotating Fairing A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE 28L.P. compressor balanced spinner assembly

72 - 35 - 01 01 - 085 1 Nose cone fairing assembly 72 - 35 - 01 01 - 220 1 Combustion Outer Case A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Combustion outer case assembly 72 - 41 - 11 01 - 350 1 H.P. compressor support cone 72 - 41 - 11 01 - 675 1 Combustion Inner Front and Inner Rear Cases A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Combustion inner rear case assembly 72 - 41 - 12 01 - 050 1 Combustion inner front case assembly 72 - 41 - 12 03 - 500 1 Combustion Liners A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Combustion rear inner liner 72 - 41 - 13 01 - 650 1 29Combustion rear outer liner

72 - 41 - 13 02 - 100 1 Combustion front inner liner 72 - 41 - 13 02 - 250 1 H.P. Nozzle Guide Vanes and Fittings A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Nozzle guide vane assembly 72 - 41 - 14 01 - 106 17 Intrascope nozzle guide vane 72 - 41 - 14 01 - 300 1 H.P. Compressor Blades A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Stage 1 blade 72 - 41 - 32 01 - 105 57 Stage 2 blade 72 - 41 - 32 01 - 150 82 Stage 3 blade 72 - 41 - 32 01 - 220 94 Stage 4 blade 72 - 41 - 32 01 - 320 97 30Stage 5 blade

72 - 41 - 32 01 - 340 76 Stage 6 blade 72 - 41 - 32 01 - 350 74 H.P. Compressor Cases A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Stage 1 outer case 72 - 41 - 41 01 - 070 1 Stage 2 outer case 72 - 41 - 41 01 - 450 1 Front locating cone assembly 72 - 41 - 41 01 - 550 1 Stage 3 outer case 72 - 41 - 41 02 - 450 1 Centre locating cone assembly 72 - 41 - 41 03 - 145 1 Stage 4 outer case 72 - 41 - 41 03 - 450 1 Stage 5 outer case 72 - 41 - 41 04 - 450 1 31Rear locating cone assembly

72 - 41 - 41 04 - 540 1 Stage 6 outer case 72 - 41 - 41 05 - 450 1 H.P. Compressor Stator Vanes A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Stage 1 inner stop vane 72 - 41 - 42 01 - 180 4 Stage 1, 2 span outer stop vane 72 - 41 - 42 01 - 200 4 Stage 1 inner and outer stop vane 72 - 41 - 42 01 - 240 4 Stage 1 vane 72 - 41 - 42 01 - 300 1 Stage 1 vane 72 - 41 - 42 01 - 360 24 Stage 1 undersize vane 72 - 41 - 42 01 - 362 24 Stage 1 inner shroud ring 72 - 41 - 42 01 - 380 4 Stage 2 inner stop vane 3272 - 41 - 42

02 - 180 4 Stage 2 inner and outer stop vane 72 - 41 - 42 02 - 240 4 Stage 2 vane 72 - 41 - 42 02 - 320 90 Stage 2 vane 72 - 41 - 42 02 - 360 24 Stage 2 undersize vane 72 - 41 - 42 02 - 362 24 Stage 2 shroud ring, small 72 - 41 - 42 02 - 380 2 Stage 2 shroud ring, large 72 - 41 - 42 02 - 404 2 Stage 3, 6 span vane 72 - 41 - 42 03 - 100 4 Stage 3, 5 span outer stop vane 72 - 41 - 42 03 - 125 4 Stage 3 inner and outer stop vane 72 - 41 - 42 03 - 150 4 Stage 3, 5 span vane 72 - 41 - 42 03 - 310 3312

Stage 3 shroud ring 72 - 41 - 42 03 - 380 4 Stage 4, 5 span outer stop vane 72 - 41 - 42 04 - 055 12 Stage 4, 5 span inner and outer stop vane 72 - 41 - 42 04 - 070 4 Stage 4, 6 span, outer stop vane 72 - 41 - 42 04 - 125 4 Stage 4, 6 span inner and outer stop vane 72 - 41 - 42 04 - 150 4 Stage 4 shroud ring 72 - 41 - 42 04 - 380 4 Stage 5, 5 span outer stop vane 72 - 41 - 42 05 - 180 1 Stage 5, 4 span outer stop vane 72 - 41 - 42 05 - 200 14 Stage 5, 4 span inner and outer stop vane 72 - 41 - 42 05 - 240 16 Stage 5, 5 span vane 72 - 41 - 42 05 - 280 1 34Stage 5 shroud ring

72 - 41 - 42 05 - 380 1 H.P. Turbine Disc A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Inner bearing race 72 - 41 - 51 01 - 400 1 H.P. Turbine Blades A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Rotor blade 72 - 41 - 52 01 - 140 102 I.P. Turbine Case A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE H.P. and I.P. bearings support outer case 72 - 51 -21 02 - 065 1 H.P. turbine roller bearing 72 - 51 -21 02 - 180 1 H.P. and I.P. turbine bearings support 72 - 51 -21 02 - 200 1 I.P. turbine roller bearing 72 - 51 -21 02 - 530 1 35I.P. and L.P.1 Nozzle Guide Vanes

A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE I.P. turbine nozzle vane assembly 72 - 51 -22 01 - 370 35 I.P. turbine intrascope nozzle guide vane 72 - 51 -22 01 - 460 1 I.P. Turbine Blades A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Rotor blade 72 - 51 - 32 01 - 140 112 Inner bearing race 72 - 51 - 33 01 - 450 1 L.P. Turbine Case A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE L.P.2 and L.P.3 nozzle vanes outer case assembly 72 - 51 - 51 01 - 060 1 L.P. Turbine Rotor Disc A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE 36L.P.1 turbine disc inner seal

72 - 51 - 61 01 - 279 1 L.P.2 to L.P.3 turbine disc spacer ring 72 - 51 - 61 01 - 400 1 L.P. turbine bearing inner race 72 - 51 - 61 01 - 550 1 L.P. Turbine Rotor Blades A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Stage 1 blade 72 - 51 - 62 01 - 055 78 Stage 2 blade 72 - 51 - 62 01 - 090 64 Stage 3 blade 72 - 51 - 62 01 - 140 64 L.P. Turbine Bearing and Support -Exhaust Case A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Exhaust case assembly 72 - 51 - 71 02 - 350 1 L.P. Turbine Bearing and Support -Hub and Fairing A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE 37L.P. turbine roller bearing

72 - 51 - 72 03 - 200 1 L.P. turbine bearing support assembly 72 - 51 - 72 03 - 300 1 High Speed Gearbox Oil Pumps, Pressure and Scavenge A.T.A.FIG/ITEMQTY PER PART DESCRIPTIONCHAPTERNUMBERENGINE Oil pump assembly 72 - 61 - 30 01 - 100 1 Spray nozzle assembly 73 - 11 - 05 01 - 056 14 P4 air, spray nozzle assembly 73 - 11 - 05 01 - 120 2 Igniter, spray nozzle assembly 73 - 11 - 05 01 - 200 2 13. Group C Parts Turbine tip seal segments L.P. turbine nozzle guide vanes Exhaust cone Gas generator fairings

38Block graph for stagger programme

Fig.05 - 00 - 01 - 990 - 001 [ Not selected for printing ] Front bearing housing and I.G.V. assembly life marking Fig.05 - 00 - 01 - 990 - 002 [ Not selected for printing ] Permitted areas for component marking on LP Compressor blades Fig.05 - 00 - 01 - 990 - 003 [ Not selected for printing ] Permitted areas for component marking on LP compressor outlet guide vanes assembly Fig.05 - 00 - 01 - 990 - 004 [ Not selected for printing ] Permitted areas for component marking on IP compressor stage 1 rotor blades Fig.05 - 00 - 01 - 990 - 005 - 001 [ Not selected for printing ] Permitted areas for component marking on IP compressor stages 2 thru 6 rotor blades Fig.05 - 00 - 01 - 990 - 005 - 002 [ Not selected for printing ] Permitted areas for component marking on HP compressor stages 1 thru 3 rotor blades Fig.05 - 00 - 01 - 990 - 005 - 003 [ Not selected for printing ] Permitted areas for component marking on HP compressor 39stages 4 thru 6

rotor blades Fig.05 - 00 - 01 - 990 - 005 - 004 [ Not selected for printing ] Permitted areas for component marking on HP compressor rotor blades (all stages) Fig.05 - 00 - 01 - 990 - 005 - 005 [ Not selected for printing ] Permitted areas for component marking on IP compressor stages 1, 2, 4 and 5 stator vanes Fig.05 - 00 - 01 - 990 - 006 - 001 [ Not selected for printing ] Permitted areas for component marking on IP compressor stage 3 stator vanes Fig.05 - 00 - 01 - 990 - 006 - 002 [ Not selected for printing ] Permitted areas for component marking on IP compressor OGV's Fig.05 - 00 - 01 - 990 - 006 - 003 [ Not selected for printing ] Permitted areas for component marking on HP compressor stage 1 stator vanes Fig.05 - 00 - 01 - 990 - 007 - 001 [ Not selected for printing ] Permitted areas for component marking on HP compressor stage 1 stator vanes Fig.05 - 00 - 01 - 990 - 007 - 002 [ Not selected for printing ] 40Permitted areas for component marking on HP compressor

stage 2 stator vanes Fig.05 - 00 - 01 - 990 - 007 - 003 [ Not selected for printing ] Permitted areas for component marking on HP compressor stage 3 stator vanes Fig.05 - 00 - 01 - 990 - 007 - 004 [ Not selected for printing ] Permitted areas for component marking on HP compressor stage 4 stator vanes Fig.05 - 00 - 01 - 990 - 007 - 005 [ Not selected for printing ] Permitted areas for component marking on HP compressor stage 5 stator vanes Fig.05 - 00 - 01 - 990 - 007 - 006 [ Not selected for printing ] Permitted areas for component marking on HP compressor stage 5 stator vanes Fig.05 - 00 - 01 - 990 - 007 - 007 [ Not selected for printing ] Permitted areas for component marking on HP turbine rotor blades Fig.05 - 00 - 01 - 990 - 008 - 001 [ Not selected for printing ] Permitted areas for component marking on HP turbine rotor blades Fig.05 - 00 - 01 - 990 - 008 - 002 41[ Not selected for printing ]

Permitted areas for component marking on HP turbine nozzle guide vanes Fig.05 - 00 - 01 - 990 - 009 - 001 [ Not selected for printing ] Permitted areas for component marking on HP turbine nozzle guide vanes Fig.05 - 00 - 01 - 990 - 009 - 002 [ Not selected for printing ] Permitted areas for component marking on HP turbine nozzle guide vanes Fig.05 - 00 - 01 - 990 - 009 - 003 [ Not selected for printing ] Permitted areas for component marking on IP turbine rotor blades Fig.05 - 00 - 01 - 990 - 010 [ Not selected for printing ] Permitted areas for component marking on IP turbine nozzle guide vanes Fig.05 - 00 - 01 - 990 - 011 - 001 [ Not selected for printing ] Permitted areas for component marking on IP turbine nozzle guide vanes Fig.05 - 00 - 01 - 990 - 011 - 002 [ Not selected for printing ] Permitted areas for component marking on LP turbine stages 1 thru 3 rotor blades Fig.05 - 00 - 01 - 990 - 012 - 001 [ Not selected for printing ] 42Permitted areas for component marking on LP turbine stages

1 thru 3 rotor blades Fig.05 - 00 - 01 - 990 - 012 - 002 [ Not selected for printing ] Permitted areas for component marking on LP turbine stage 1 thru 3 rotor blades Fig.05 - 00 - 01 - 990 - 012 - 003 [ Not selected for printing ] Permitted areas for component marking on LP turbine stage 1 nozzle guide vanes Fig.05 - 00 - 01 - 990 - 013 - 001 [ Not selected for printing ] Permitted areas for component marking on LP turbine stage 1 nozzle guide vanes Fig.05 - 00 - 01 - 990 - 013 - 002 [ Not selected for printing ] Permitted areas for component marking on LP turbine stage 1 nozzle guide vanes Fig.05 - 00 - 01 - 990 - 013 - 003 [ Not selected for printing ] Permitted areas for component marking on LP turbine stage 2 nozzle guide vanes Fig.05 - 00 - 01 - 990 - 013 - 004 [ Not selected for printing ] Permitted areas for component marking on LP turbine stage 2 nozzle guide 43vanes

Fig.05 - 00 - 01 - 990 - 013 - 005 [ Not selected for printing ] Permitted areas for component marking on LP turbine stage 2 nozzle guide vanes Fig.05 - 00 - 01 - 990 - 013 - 006 [ Not selected for printing ] Permitted areas for component marking on LP turbine stage 3 nozzle guide vanes Fig.05 - 00 - 01 - 990 - 013 - 007 [ Not selected for printing ] Permitted areas for component marking on LP turbine stage 3 nozzle guide vanes Fig.05 - 00 - 01 - 990 - 013 - 008 [ Not selected for printing ] Permitted areas for component marking on LP turbine stage 3 nozzle guide vanes Fig.05 - 00 - 01 - 990 - 013 - 009 [ Not selected for printing ] Calculations to move group 'A' and group 'B' parts between engine marks and/or flight profiles Fig.05 - 00 - 01 - 990 - 014 - 001 [ Not selected for printing ] Calculations to move group 'A' and group 'B' parts between engine marks and/or flight profiles Fig.05 - 00 - 01 - 990 - 014 - 002 [ Not selected for printing ] 44