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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

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LIST OF EFFECTIVE PAGES-05

Page 1/2

Sep.15/14

C=CONFIG B=BREAKOUT
GENERAL 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

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CHAPTER 05 - TIME LIMITS

TABLE OF CONTENTS

05−CONTENTS

Page 1

Dec.15/13

CHAPTER BREAKOUT

SECTION CONFIG/

SUBJECT SUBJECT PAGE EFFECTIVITY
MANDATORY INSPECTIONS 05-20-01

MANDATORY INSPECTIONS OF GROUP A

PARTS(AIRWORTHINESS LIMITATION -

Mandatory Inspections of Group A Parts) 1

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05−CONTENTS

Page 2

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CHAPTER BREAKOUT

SECTION CONFIG/

SUBJECT SUBJECT PAGE EFFECTIVITY
RECORDING 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.

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Identify if a Life Limited Part (LLP) was operated before in a different

engine type or mark, LLP records must be checked if disposition, repairs or

TVs are related to the specified engine type or mark.

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.

R B. Touch and go or overshoot

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

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For example, one training flight that includes one 'overshoot' and three

R Flight Cycles for all group A 'touch and go's' is the equivalent of five

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

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B. 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.

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It 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.

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On a part removed from an engine or module for transfer into a parts

pool, the life is calculated from the log records, and the part

life-marked using a code such as that detailed in sub-paragraph B. Any

previously applied date mark must be deleted at the time of life

marking.

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

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(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.

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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 (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

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PART 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

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PART 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

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PART 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

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PART 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

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Page 12

R Dec.15/13
PART 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

5RR

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RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 13

R Dec.15/13
PART 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

5RR

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EFFECTIVITY: TAY/ALL 05−00−01

Page 14

R Dec.15/13
PART 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

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RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 15

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PART 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

5RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

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Page 16

R Dec.15/13
PART 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

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Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

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Page 17

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PART 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

5RR

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RECORDING AND CONTROL OF THE LIVES OF PARTS

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Page 18

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PART 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

5RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 19

R Dec.15/13
Block graph for stagger programme

Fig. 05-00-01-990-001 (Fig. 1)

5RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 20

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Life marking - LP compressor outlet guide vane

Fig. 05-00-01-990-002 (Fig. 2)

5RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

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Page 21

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Life marking - IP compressor inlet guide vane

Fig. 05-00-01-990-003 (Fig. 3)

5RR

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RECORDING AND CONTROL OF THE LIVES OF PARTS

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Page 22

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Life marking - IP compressor vane

Fig. 05-00-01-990-004 (Fig. 4)

5RR

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RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 23

R Dec.15/13
Life marking - IP compressor rotor blade

Fig. 05-00-01-990-005 (Fig. 5)

5RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 24

R Dec.15/13
Life marking - IP compressor outlet guide vanes

Fig. 05-00-01-990-006 (Fig. 6)

5RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 25

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Life marking - HP compressor inlet guide vane

Fig. 05-00-01-990-007 (Fig. 7)

5RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 26

R Dec.15/13
Life marking - HP compressor rotor blades

Fig. 05-00-01-990-008 (Fig. 8)

5RR

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RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 27

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Life marking - HP compressor vanes

Fig. 05-00-01-990-009 (Fig. 9)

5RR

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RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 28

R Dec.15/13
Life marking - HP turbine nozzle vanes

Fig. 05-00-01-990-010 (Fig. 10)

5RR

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RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 29

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Life marking - Turbine rotor blade

Fig. 05-00-01-990-011 (Fig. 11)

5RR

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RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 30

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Life marking - LP turbine nozzle vanes

Fig. 05-00-01-990-012 (Fig. 12)

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RECORDING AND CONTROL OF THE LIVES OF PARTS

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Page 31/32

R Dec.15/13
TASK 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.

5RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING - GROUP A PARTS

EFFECTIVITY: TAY/ALL 05−00−02

Page 1

Mar.23/07
Datum flight profile - H.P. speed (N2)

Fig. 05-00-02-990-003 (Fig. 1)

5RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING - GROUP A PARTS

EFFECTIVITY: TAY/ALL 05−00−02

Page 2

Mar.23/07
Datum flight profile - L.P. speed (N1)

Fig. 05-00-02-990-004 (Fig. 2)

5RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING - GROUP A PARTS

EFFECTIVITY: TAY/ALL 05−00−02

Page 3/4

Mar.23/07
MAXIMUM 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.

5RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−00−03

Page 1/2

Jun.15/08
CALENDAR 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.

5RR

Printed in Great Britain

CALENDAR LIFE LIMIT

EFFECTIVITY: TAY/ALL 05−00−04

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. 1 198 
MAXIMUM 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.

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B. This section details the maximum approved lives on Group A and Mandatory

Group B parts which must not be exceeded in service.

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MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 1

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CAUTION: 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.

R CAUTION: 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.

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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.

R CAUTION: 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

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5RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 2

R Sep.15/14
R CAUTION: 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.

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R CAUTION: 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.

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R Donor application is the TAY engine mark in which a Group A part or NOTE:

Group B part was operated before a change.

R

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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

5RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 3

R Sep.15/14
APPROVED 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

5RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 4

R Sep.15/14
APPROVED 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

5RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 5

R Sep.15/14
APPROVED 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

5RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 6

R Sep.15/14
APPROVED 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

5RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 7

R Sep.15/14
SUBTASK 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

5RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 8

R Sep.15/14
MANDATORY 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)

5RR

Printed in Great Britain

MANDATORY INSPECTIONS OF GROUP A PARTS

EFFECTIVITY: TAY/ALL 05−20−01

Page 1

R Jun.15/10
IP 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)

R HP Compressor Rear Drive Shaft (72-37-31,01-010), 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)

R , EM TASK 72-52-21-200-003 LP Turbine Shaft (72-52-21,01-485)

(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)

5RR

Printed in Great Britain

MANDATORY INSPECTIONS OF GROUP A PARTS

EFFECTIVITY: TAY/ALL 05−20−01

Page 2

R Jun.15/10
LP Turbine Stage 3 Rotor Disc (72-52-24,04-400), EM TASK 72-52-24-200-000

(INSPECTION/CHECK-00, PB801)

5RR

Printed in Great Britain

MANDATORY INSPECTIONS OF GROUP A PARTS

EFFECTIVITY: TAY/ALL 05−20−01

Page 3/4

R Jun.15/10
All enquires regarding this manual 

should be addressed to:- 

TECHNICAL PUBLICATIONS DEPARTMENT 

ROLLS-ROYCE plc 

DERBY 

P0:BOX 31 : DERBY : ENGLAND DE24 8BJ