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 

1
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'. 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 

2
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 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 

4
 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 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 

5
Marks

 

 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 

6
contains 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 

7
 which 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).

8
 

 8. 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.

9
 9. 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.

 

10
 10. 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 

11
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 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

12
 

 A 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 

14
stator vanes and 

 the areas in which life markings are to 

be applied are 

 illustrated in Fig.05-00-01-990-002, 

 Fig.05-00-01-990-003, Fig.05-00-01-990-

004, 

 Fig.05-00-01-990-005-001, 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 

15
 replacement 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

16
 2

 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

17
 Centre 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 *

18
 22

 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

19
 72-32-31

 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

20
 72-32-41

 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

21
 02-330

 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

22
 Stage 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

23
 72-32-42

 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

24
 38

 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

25
 PART 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

26
 L.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

27
 locating 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

28
 L.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

29
 Combustion 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

30
 Stage 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

31
 Rear 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

32
 72-41-42

 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

33
 12

 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

34
 Stage 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

35
 I.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

36
 L.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

37
 L.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

 

38
 Block 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 

39
stages 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 ] 

40
 Permitted 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 ] 

42
 Permitted 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 

43
 vanes

 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