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Printed in Great Britain
Printed in Great Britain
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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

05

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(Flight Profiles and

Operational Monitoring - Group A Parts) 1

MAXIMUM APPROVED LIVES - RECOMMENDED GROUP B

PARTS 05-00-03

MAXIMUM APPROVED LIVES(Maximum Approved

Lives - Recommended Group B Parts) 1

CALENDAR LIFE LIMIT 05-00-04

CALENDAR LIFE LIMIT(Calendar Life Limit) 1

05-10-00

TIME LIMITS(Flight Profiles and

Operational Monitoring - Group A Parts) 1

MAXIMUM APPROVED LIVES 05-10-01

MAXIMUM APPROVED LIVES(AIRWORTHINESS

LIMITATIONS - Maximum Approved Lives -

Group A Parts and Mandatory Group B

Parts) 1

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CHAPTER 05 - TIME LIMITS

TABLE OF CONTENTS

05−CONTENTS

Page 1

Sep.15/14

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

Dec.15/13

CHAPTER BREAKOUT

SECTION CONFIG/

SUBJECT SUBJECT PAGE EFFECTIVITY
GENERAL DATA

TASK 05-00-00-860-000 General Data

1. General Data

A. This Manual contains Airworthiness Limitations and Non-Airworthiness

Limitations Chapters.

Airworthiness Limitations Chapters are approved by EASA under approval No.

EASA.E.C.01618.

Airworthiness Limitations are applied to the maximum approved lives of

Group A parts, mandatory Group B parts and mandatory inspection of parts.

Non-Airworthiness Limitations are applied to general data, recording and

control of lives of parts, flight profiles and operational monitoring,

recommended Group B parts lives and calendar life limits.

Airworthiness Limitation Chapters are:

Chapter 05-10-01 Maximum Approved Lives - Group A Parts and Mandatory

Group B Parts

Chapter 05-20-01 Mandatory Inspections of Group A Parts

Non-Airworthiness Limitation Chapters are:

Chapter 05-00-00 General Data

Chapter 05-00-01 Recording and Control of the Lives of Parts

Chapter 05-00-02 Flight Profiles and Operational Monitoring

Chapter 05-00-03 Maximum Approved Lives - Recommended Group B Parts

Chapter 05-00-04 Calendar Life Limitation

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GENERAL DATA

EFFECTIVITY: TAY/ALL 05−00−00

Page 1/2

Jun.15/08
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 EEL resistant touch-up

2. General

Adequate and accurate information about the lives and disposition of engine

parts and their condition at repair is important to both the operator and

Rolls-Royce.

Such information will assist in spares provisioning, warranty claims, repair

planning and the establishment of an economical operation.

A recommendation by Rolls-Royce of the life of a part does not imply that a

part will achieve this life and it does not constitute a warranty of the part

by Rolls-Royce. The warranty arrangements made between Rolls-Royce and the

operator will control the relationship between the parties.

The type of record and the degree of control over the life varies according to

the part. For these purposes parts are divided into three groups, A, B, and C.

Mandatory lives for Group A parts and Group B parts are given in TASK

05-10-01-800-000.The remaining Group B parts which are not mandatory life

limited but are given recommended lives are also listed in TASK

05-00-03-800-000.

NOTE: Tay Manuals use the classification of Group A, Group B and Group C

parts. These parts can also be referred to as Critical, Sensitive and

Unclassified parts.

Group A parts = Critical parts.

Group B parts = Sensitive parts.

Group C parts = Unclassified parts.

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

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

TVs are related to the specified engine type or mark.

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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 thus subjected to strict life limitations

which must not be exceeded in service.

These limitations are made as a result of experience collected by Rolls-Royce

through cyclic rig testing, development engine testing, metallurgical

investigation and other techniques, including sampling of service run parts.

The service life achieved on a part can prove to be less than that permitted

by Rolls-Royce for airworthiness consideration. For example, corrosion or wear

can result in rejection of the part at an earlier life than the quoted

limitation.

The operator must controll the lives of Group A parts in service.

The lives of Group A parts are expressed in terms of Flight Cycles. This is

the most direct and accurate way of controlling the service life or parts. The

life is calculated from the rate of fatigue life usage per Datum Flight.

Flight cycle and Datum Flight profile data are given in TASK 05-00-02-800-000.

4. Definition of a Flight Cycle

A. Normal flying

A normal take-off to landing according to the Datum Flight Profile for the

engine type.

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

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.

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5. Recording of Lives

CAUTION: EMPHASIS IS PLACED ON THE VITAL IMPORTANCE OF MAINTAINING LIFE RECORDS

ON ALL GROUP A PARTS. THESE RECORDS FORM THE ONLY IDENTIFICATION OF

LIFE COMPLETED BY EACH PART.

The repair facility is required to make records and supply information as

follows:

A. Keep an internal record for each Group A part, if in service or held

serviceable in stores pending issue to a module.

These records are vitally important to the life control of parts and must

therefore be accurate and up to date.

Record the part serial number and modification standard against the total

life in terms of Flight Cycles and hours, expressed numerically (not in

life code letters).

To help locate parts quickly, the record system must index parts under

description and modification standard and, separately, under engine type

and serial numbers and/or module number.

B. Record and tell the operator and Rolls-Royce the reasons for rejection of

any part, and its total running time in Flight Cycles and hours.

C. Calculate, from information received from the operator, the residual life

of a part and decide if or not it can be refitted in an engine and/or

module without becoming time expired in advance of the engine and/or module

life requirements of the operator.

D. Advise operators of the serial numbers and life completed in Flight Cycles

and hours on those parts which have been fitted into engines and/or modules

during shop visits. The advice must be included with the paperwork

accompanying engines and/or modules during shop visits. The advice must be

included with the paperwork accompanying engines or modules when returned

to the operator. The same information must be sent to Rolls-Royce.

6. Special Requirements

A. Reason for special requirements

This manual contains four sets of declared cyclic lives applicable to the

Group A Parts and the Mandatory Group B Parts. These are defined as Flight

Plan A, Flight Plan B, Flight Plan C, and Flight Plan D Life Profile

Operations. The Flight Profiles applicable to these Flight Plans are

published in the Time Limits Manual, Chapter 05-00-02. Group A Parts can be

transferred between profiles. To enable operators to continue with their

Actual Profile Operation or to allow Group A Parts be transferred between

flight plans, the following records must be maintained:

(1) Installation history

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(2) Regular interval review of profiles. Refer to Engine Maintenance

Manual, Chapter 70-01-10, Flight Profiles and Operational Monitoring.

(3) Revised life limits.

B. Recording installation history

The life of each Group A Parts and Mandatory Group B Parts must be

recorded, refer to paragraph 5.

C. Regular interval review of profiles

After an operator has been classified into an approved Life Profile

Operation, it is the responsibility of the Operator, if required by his

local Airworthiness Authority, to provide the preceding years flight

profile data in order to continue operating within the specified Flight

Plan.

D. Revised life limits

Any operator changing from one Life Profile Operation to another or vice

versa must notify Rolls-Royce of this change.

These revised lives limits must be recorded against the individual Group A

Parts and the Mandatory Group B Parts.

7. Mandatory Group B Parts

These are parts which test and service experience have shown require special

attention in service in order to avoid failures which:

Can be serious in terms of engine disruption but are classed as considerably

less significant than the possible consequences of a Group A part failure,

or

Though not hazardous in their own right, can threaten the integrity of a

Group A part.

A. Any mandatory life limitations developed for such parts are given in TASK

05-10-01-800-000. These parts are also identified in paragraph 10, List of

Group B Parts, with an asterisk. Routine scheduled inspection checks, where

appropriate, will need to be included in the Aircraft Maintenance Schedule

and supplemented by an advisory Notice to Operators (NTO). In some cases,

these inspections will be instructed in a non-modification Service

Bulletins.

The remaining parts in this group are those whose failure can cause

extensive secondary damage.

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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 which depends upon those long-life

parts which can require replacement over a short-time, if life-limiting

features become apparent. It is important to ensure that the lives of such

parts are suitably spaced over the engines or modules in any operation to

keep the size of the protection stock to a minimum and to avoid a sudden

spares requirement.

Suitable spacing is defined as a sufficient scatter between high-life and

low-life parts and a sufficient number of high-life parts far enough ahead

of the majority to provide adequate time to deal with any life limitation.

Records of parts fitted to engines/modules at repair, together with current

engine/module lives, can be combined to produce a distribution block graph

as shown in Fig. 05-00-01-990-001.

It is recommended that protection stocks cover the leading parts and the

time between these and the majority will indicate the delivery requirement

for each operator's future repairs. In many instances the scatter will

occur naturally, due to engine/module growth, part-life repairs and

rectification. Where this is not so, a life stagger is recommended to be

introduced artificially, before large numbers of parts are refitted to

complete high hours beyond current experience, by fitting new or low-life

parts at repair to space out the life distribution pattern.

Rolls-Royce will make available to all operators the current service

experience on Group B parts, as a basis upon which life extensions, where

appropriate, can be planned depending upon the individual operation.

It is necessary to life mark or maintain life records of Group B parts,

refer to paragraph 9. All Group B parts are listed in paragraph 10.

8. Group C Parts

It is suggested that the parts in this group are life marked only to assist in

warranty claims and spares provisioning.

The only type of record desirable for this group is the life of the part when

it is finally scrapped, which will guide spares provisioning.

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RECORDING AND CONTROL OF THE LIVES OF PARTS

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9. Life Markings of Group B and C Parts

A. Life marking

NOTE: The control of Group A parts is maintained by records, therefore the

marking of these parts is not necessary.

Where a group B part has no serial number and no paperwork records, the

part must be suitably life marked as detailed in B.

This method is based on a minimum level of life marking in association with

the life records of the related engine or module.

Where engines are being maintained by modules it is necessary for each

module to be individually identified and its life records maintained

separately.

It is only necessary to mark parts on two occasions:

(1) when new or ex-pool parts are fitted, and

(2) when parts removed from an engine or module enter a parts pool

This practice will give the benefit of substantial economy in the

marking space available on small parts such as blades. It will be

necessary to identify those parts which are replaced during engine or

module repair so that their running times can be calculated at the time

of life marking.

A suitable method is to mark the part with a symbol representing the

date on which the part was fitted, indicating the month and year, using

the number of the month and the last two digits of the year and

interposing a hyphen, e.g. October 1988 would be indicated 10-88.

At the time of life marking, the running time is calculated by

reference to the engine or module log records.

A part removed from a parts pool for fitting to an engine or module

must have the date marked adjacent to the life marking. In a future

life calculation the calculated life since fitting would be added to

the life denoted by the life marking.

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

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

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

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

marking.

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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 before the first life marking letter. If

table 2 is used, a circle with the figure 6 in it is to be engraved on the

parts before the first life marking letter.

Table 1

A=0-100 F=501-600 L=1001-1100 Q=1501-1600 V=2001-2100

B=101-200 G=601-700 M=1101-1200 R=1601-1700 W=2101-2200

C=201-300 H=701-800 N=1201-1300 S=1701-1800 X=2201-2300

D=301-400 J=801-900 O=1301-1400 T=1801-1900 Y=2301-2400

E=401-500 K=901-1000 P=1401-1500 U=1901-2000 Z=2401-2500

Table 2

A=0-500 F=2501-3000 L=5001-5500 Q=7501-8000 V=10001-10500

B=501-1000 G=3001-3500 M=5501-6000 R=8001-8500 W=10501-11000

C=1001-1500 H=3501-4000 N=6001-6500 S=8501-9000 X=11001-11500

D=1501-2000 J=4001-4500 O=6501-7000 T=9001-9500 Y=11501-12000

E=2001-2500 K=4501-5000 P=7001-7500 U=9501-10000 Z=12001-12500

When the life exceeds the range covered by the table, use the letter Z with

other letters to denote the life marking required.

Example 1, life marking using table 1:

(1) Part removed from engine at 742 hours for entry into pool:

Part marked 5 (in a circle) H

(2) Part fitted to second engine:

Part date marked

(3) Part removed for entry into pool at engine running time of 1,370 hours

since date marking:

Date mark deleted and letter O added; life marking will then read 5

(in a circle) HO

(4) Part fitted to third engine:

Part date marked

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(5) Part removed for entry into pool at engine running time of 2,700 hours

since date marking:

Date mark deleted and letters ZB added: life marking will then read 5

(in a circle) HOZB

C. Method of marking

CAUTION: METAL STAMPS OR ELECTRO-ETCHING MUST NOT BE USED TO LIFE MARK ANY

PART.

D. To avoid the setting up of stress concentrations, the code must be applied

using vibro-engraving tool.

Where magnesium cases are engraved, the immediate area will require

reprotection using 10 percent solution of OMat 1/202 Chromating touch up,

followed by an application of OMat 7/24 EEL resistant touch-up clear

varnish. Refer to OP TASK 70-00-00-300-304.

E. Position of marking

The code letters must be marked adjacent to the part number in such a

manner that they will not be mistaken for a part of a serial or other

number.

On parts where surface areas for marking are relatively small (as in blades

and vanes), alternative positions for life marking are given in para.F.

F. Alternative marking instructions

(1) Compressor and turbine blades and vanes

Typical examples of rotor blades and stator vanes and the areas in

which life markings are to be applied are illustrated in

Fig.05-00-01-990-002 , Fig.05-00-01-990-003 , Fig.05-00-01-990-004 ,

Fig.05-00-01-990-005 , Fig.05-00-01-990-006 , Fig.05-00-01-990-007 ,

Fig.05-00-01-990-008 , Fig.05-00-01-990-009 , Fig.05-00-01-990-010 ,

Fig.05-00-01-990-011 and Fig.05-00-01-990-012 .

If the marked vane in an assembly, is replaced by a new vane, or one of

comparable life to the original, the replacement vane must be marked

with the life coding appropriate to the original vanes in the group.

Proximity of the markings to certain areas is subject to limitation.

The prohibited areas and limits of proximity are specifically defined

for blades and vanes in Fig.05-00-01-990-002 to Fig.05-00-01-990-012.

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10.List of Group B Parts

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

LP Compressor Rotating Fairing

LP compressor rotating fairing (72-30-10,01-060) 1

LP compressor nose cone assembly (72-30-10,01-010) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

LP Compressor Blades

LP compressor blade * (72-31-12,02-010) 22

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

LP Compressor Case and Vanes

LP compressor case (72-32-20,01-250) 1

LP outlet guide vane assembly (72-32-30,01-360) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Splitter Fairing

Splitter fairing assembly (72-33-10,01-005) 1

IP inlet guide vane assembly (72-33-10,01-110) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

IP Compressor Stator Vanes -

Stages 1 and 2

Stage 1 vane (72-33-22,02-010) 72

Stage 1 vane (72-33-22,02-030) 12

Stage 1 vane (72-33-22,02-050) 4

Stage 1 vane (72-33-22,02-070) 4

Stage 2 vane (72-33-22,02-130) 80

Stage 2 vane (72-33-22,02-150) 16

Stage 2 vane (72-33-22,02-170) 4

Stage 2 vane (72-33-22,02-190) 4

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

IP Compressor Rotor Stage 1

IP compressor stage 1 blade (72-33-31,01-005) 63

IP compressor spacer, stages 1

to 2

(72-33-31,01-070) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

IP Compressor Rotor Stage 2

IP compressor stage 2 blade (72-33-32,02-005) 72

IP compressor spacer, stages 2

to 3

(72-33-32,02-065) 1

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ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

IP Compressor Rotor Stage 3

IP Compressor Stage 3 blade (72-33-33,03-005) 99

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

LP /IP compressor Shaft and

Fittings

Inner race - Rear roller bearing

-

LP/IP compressor drive shaft (72-33-40,04-140) 1

Gearwheel - Driving - LS gearbox

drive

(72-33-40,04-160) 1

Inner race - Front roller

bearing -

LP/IP compressor drive shaft (72-33-40,04-200) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

IP Compressor Outlet Guide Vanes

IP compressor outlet guide vane

multiple assembly (72-35-10,01-660) 11

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Intermediate Compressor Case

Intermediate compressor case (72-35-21,01-350) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HPC IGVs

HP compressor variable inlet

guide vanes

(72-35-24,04-025) 53

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Internal Gearbox

Rear bearing support housing (72-35-42,01-320) 1

Rear bearing assembly LP

compressor shaft

(72-35-42,01-340) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Front bearing support housing (72-35-43,01-524) 1

Front bearing assembly - LP

compressor

shaft (Mk.650-15 only) (72-35-43,01-750) 1

Front bearing assembly - LP

compressor

shaft (Mks.610-8,611-8 and

620-15 only)

(72-35-43,01-550) 1

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ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Spur gear assembly-driven - LS

gearbox drive

(72-35-44,02-020) 1

Gearshaft - driving - LS gearbox

drive

(72-35-44,02-150) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Gearshaft - driven - LS gearbox

drive

(72-35-45,02-260) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Bevel gear - driving - HS

gearbox

(72-35-46,03-006) 1

Retainer - bearing - driving

bevel gear

(72-35-46,03-015) 1

Roller - bearing - driving bevel

gear

(72-35-46,03-017) 30

Race outer - bearing - driving

bevel gear

(72-35-46,03-019) 1

Thrust bearing - driving bevel

gear

(72-35-46,03-035) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Gearshaft - bevel - driven - HS

gearbox drive (72-35-47,03-140) 1

Retainer - bearing - driven

bevel gearshaft

(72-35-47,03-145) 1

Roller - bearing - driven bevel

gearshaft

(72-35-47,03-150) 12

Race - bearing - driven bevel

gearshaft

(72-35-47,03-155) 1

Thrust bearing - driven bevel

gearshaft

(72-35-47,03-165) 1

Housing - roller bearing and

driven

bevel gearshaft (72-35-47,03-280) 1

Roller - bearing - driven bevel

gearshaft

(72-35-47,03-285) 12

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Bearing assembly - HP compressor

rotor

(72-35-48,04-040) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Compressor Case Assembly

HP compressor vanes

3RR

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RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 11

R Dec.15/13
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

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Compressor Case Assembly

HP compressor vanes

Stage 4 vane (72-37-13,02-500) 116

Stage 4 vane (72-37-13,02-502) 116

Stage 4 vane (72-37-13,02-504) 116

Stage 4 split line vane (72-37-12,02-510) 2

Stage 4, 3-span vanes (72-37-13,02-520) 2

Stage 5 vane (72-37-13,03-050) 122

Stage 5 vane (72-37-13,03-052) 122

Stage 5 vane (72-37-13,03-054) 2

Stage 5 split line vane (72-37-13,03-056) 2

Stage 5, 2-span vanes (72-37-13,03-060) 2

Stage 6 vane (72-37-13,03-100) 120

Stage 6 vane (72-37-13,03-102) 120

Stage 6 vane (72-37-13,03-104) 120

Stage 6 split line vane (72-37-13,03-106) 2

Stage 6, 2-span vanes (72-37-13,03-110) 2

Stage 7 vane (72-37-13,03-125) 108

Stage 7 vane (72-37-13,03-127) 108

Stage 7 vane (72-37-13,03-129) 108

Stage 7 vane (72-37-13,03-131) 2

Stage 7 vane (72-37-13,03-133) 2

Stage 8 vane (72-37-13,03-187) 100

Stage 8 vane (72-37-13,03-189) 100

Stage 8 vane (72-37-13,03-191) 2

Stage 8, 2-span vanes (72-37-13,03-193) 2

Stage 9 vane (72-37-13,03-240) 102

Stage 9 vane (72-37-13,03-242) 102

Stage 9 vane (72-37-13,03-244) 102

Stage 9 vane (72-37-13,03-246) 2

Stage 9, 2-span vanes (72-37-13,03-248) 2

Stage 10 vane (72-37-13,03-300) 106

Stage 10 vane (72-37-13,03-302) 106

Stage 10 vane (72-37-13,03-304) 106

Stage 10 split line vane (72-37-13,03-306) 2

Stage 10, 2-span vanes (72-37-13,03-308) 2

Stage 11 vane (72-37-13,03-370) 120

Stage 11 vane (72-37-13,03-372) 120

Stage 11 vane (72-37-13,03-374) 120

Stage 11 split line vane (72-37-13,03-376) 2

Stage 11, 2-span vanes (72-37-13,03-378) 2

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 12

R Dec.15/13
ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP compressor Case Assembly

HP compressor vanes

HP compressor case, 7th stage

air

offtake duct assembly (72-37-14,04-055) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Compressor Air Guide Tube,

Drive

Shaft and Fittings

Thrust bearing assembly - LP

rotor

(72-37-32,02-090) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Compressor Rotor Stages 1 to

3

HP compressor stage 1 blade

assembly

(72-37-33,03-205) 47

Shaft - HP compressor - front (72-37-33,03-237) 1

HP compressor stage 2 blade (72-37-33,03-260) 73

HP compressor spacer, stages 1

to 2

(72-37-33,03-282) 1

HP compressor stage 3 blade (72-37-33,03-305) 89

HP compressor spacer, stage 2 to

3

(72-37-33,03-327) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Compressor Stages 4 to 7

HP compressor stage 4 blade (72-37-34,04-355) 101

HP compressor spacer, stages 3

to 4

(72-37-34,04-372) 1

HP compressor stage 5 blade (72-37-34,04-390) 107

HP compressor spacer, stages 4

to 5

(72-37-34,04-395) 1

HP compressor stage 6 blade (72-37-34,04-415) 103

HP compressor spacer, stages 5

to 6

(72-37-34,04-420) 1

HP compressor stage 7 blade (72-37-34,04-440) 101

HP compressor spacer, stages 6

to 7

(72-37-34,04-445) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Compressor Rotor Stages 8 to

11

HP compressor stage 8 blade (72-37-35,05-465) 88

3RR

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RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 13

R Dec.15/13
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

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Compressor Stage 12

Adapter ring (72-37-36,06-150) 1

HP compressor stage 12 blade (72-37-36,06-170) 89

Seal - air - outer (72-37-36,06-190) 1

Seal - air - inner (72-37-36,06-270) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Compressor OGVs

5-span OGVs (72-37-41,01-110) 3

6-span OGVs (72-37-41,01-130) 12

HP Thrust Bearing Housing

Assembly

Thrust bearing assembly - HP

rotor

(72-37-41,01-195) 1

HP rotor thrust bearing housing

assembly

(72-37-41,01-225) 1

HP rotor thrust bearing housing

assembly

(72-37-41,01-235) 1

ATA FIG/ITEM QTY PER ENGINE

Diffuser Case

Diffuser case assembly (72-37-42,02-100) 1

Primary air scoop (72-37-42,02-300) 10

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Outer Combustion Case Assembly

Outer combustion case assembly (72-40-30,01-100) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Combustion Liner and Discharge

Nozzle

Assembly

Combustion liner (72-41-11,01-020) 5

Combustion liner (72-41-11,01-160) 3

Combustion liner (72-41-11,01-295) 1

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 14

R Dec.15/13
Combustion liner (72-41-11,01-440) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Turbine NGVs

Stage 1 NGV (72-41-21,01-060) 24

Stage 1 NGV (610-8,611-8 and

620-15 only)

(72-41-21,01-062) 24

Stage 1 NGV (610-8,611-8 and

620-15 only)

(72-41-21,01-064) 24

Stage 1 introscope NGV (650-15

only)

(72-41-21,01-130) 1

Stage 2 NGV (650-15 only) (72-41-21,01-750) 26

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Turbine Bearing Support

Assembly

Bearing support assembly - HP

turbine

(72-41-22,02-185) 1

Stop ring - flexible bearing

support

(72-41-22,02-345) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Turbine Bearing Housing

Assembly

Roller bearing assembly - HP

turbine

(72-41-23,03-650) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Turbine Shaft

Bearing sleeve - HP turbine

shaft

(72-41-31,01-045) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Turbine Rotor Stage 1

HP turbine stage 1 blade (72-41-32,02-040) 88

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

HP Turbine Rotor Stage 2

HP turbine stage 2 blade (72-41-33,03-290) 126

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

LP Nozzle Case and Vanes

LP turbine front nozzle case (72-52-10,01-030) 1

LP turbine rear nozzle case (72-52-10,01-180) 1

Stage 1 NGV assembly (72-52-10,01-350) 8

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 15

R Dec.15/13
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

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

LP Turbine Rotor Stage 1

LP turbine stage 1 blade (72-52-22,02-450) 84

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

LP Turbine Rotor Stage 2

LP turbine stage 2 blade (72-52-23,03-500) 80

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

LP Turbine Rotor Stage 3

Raceway - inner - LP turbine

bearing

(72-52-24,04-470) 1

LP turbine stage 3 blade (72-52-24,04-500) 76

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

LP Turbine Bearing - Support and

Fairings

Bearing support assembly - LP

turbine

(72-52-31,01-040) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

LP Turbine Bearing Support Case

LP turbine case (72-52-32,02-050) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Rear Engine Mount

Link - rear engine mount (72-52-40,08-020) 1

Link - rear engine mount (72-52-40,08-030) 1

Pin - rear engine mount (72-52-40,08-050) 2

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Exhaust Mixer

Cone, fairing - assembly of - LP

turbine

bearing support mixer (72-53-10,01-316) 1

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 16

R Dec.15/13
ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Shaft, gear driven - breather

rotor

(72-61-12,04-065) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Gear, spur-driving breather

shaft

(72-61-14,06-010) 1

Gear, spur-driving starter drive (72-61-14,06-090) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Shaft, gear-hydraulic pump drive (72-61-15,07-020) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Shaft, gear-hydraulic pump drive

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

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Gearshaft - idler - starter

drive

(72-61-18,10-040) 1

Race, roller, bearing - front (72-61-18,10-045) 1

Gear, spur-driving hydraulic

pump drive

(72-61-18,10-070) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Roller bearing assembly - AC

generator

shaft (Mks.610-8 and 611-8

only)

(72-61-19,11-660) 1

Shaft, driven bevel gear (72-61-19,11-050) 1

Gear, bevel - gearbox drive (72-61-19,11-055) 1

Gear, spur-driving idler stator

drive

(72-61-19,11-060) 1

Gear, spur-driving idler backing

pump

(72-61-19,11-090) 1

Bearing, assembly, ball thrust -

driven

bevel shaft (72-61-19,11-210) 1

Shaft IDG drive

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 17

R Dec.15/13
(Mks.620-15 and 650-15 only) (72-61-19,11-340) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Gear spur - driven, backing

pump drive

(72-61-22,13-050) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Shaft - idler, oil pump drive (72-61-22,14-050) 1

Gear spur - Idler, fuel pump

drive

(72-61-22,14-055) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Gearshaft - driven - oil pump

drive

(72-61-23,15-040) 1

Roller race - front - oil pump

drive

(72-61-23,15-060) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Gearshaft - fuel pump drive (72-61-24,16-050) 1

Gear, spur - driving - fuel

control unit

(72-61-24,16-055) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Gearshaft, driven - tachometer

drive

(72-61-25,17-010) 1

Thrust bearing - tachometer

gearshaft drive

(72-61-25,17-015) 2

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Shaft - driven - FCU and RPM

indicator drive (72-61-26,18-060) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Shaft, driving wheelcase gears (72-61-27,19-010) 1

Gear, bevel driving wheelcase

gears

(72-61-27,19-015) 1

Thrust bearing - driving bevel

gear

(72-61-27,19-160) 1

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 18

R Dec.15/13
Bearing housing - driving bevel

gear

(72-61-27,19-180) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

High Speed Gearbox

Roller bearing - generator drive

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

Shaftgear, spur - driving VSCF

generator drive (Mks.610-8 and

611-8 only)

(72-61-28,20-295) 1

Gearshaft, spur, drive-VSCF

generator (Mks.610-8 and 611-8

only)

(72-61-28,20-635) 1

Gearshaft, spur, idler - VSCF

generator (Mks.610-8 and 611-8

only)

(72-61-28,20-640) 1

Race, outer roller - VSCF

generator driven gearshaft

(Mks.610-8 and 611-8 only) (72-61-28,20-600) 1

Race, outer roller - VSCF

generator idler shaftgear

(Mks.610-8 and 611-8 only) (72-61-28,20-670) 1

Retainer, roller assembly - VSCF

generator (Mks.610-8 and 611-8

only)

(72-61-28,20-630) 1

Retainer, roller assembly - VSCF

generator (Mks.610-8 and 611-8

only)

(72-61-28,20-650) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Low speed (L.S.) gearbox

Gearwheel, bevel - driving LS

gearbox

(72-61-02,02-070) 1

Gearwheel, bevel - driving LS

gearbox

(72-61-02,02-070) 1

Gearwheel, bevel - driven LS

gearbox

(72-61-02,02-255) 1

Gearwheel, bevel - driven LS

gearbox

(72-61-02,02-315) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

By-Pass Ducts

Front by-pass duct assembly (72-71-01,01-100) 1

Access panel assembly (72-71-01,01-198) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

By-Pass Ducts

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 19

R Dec.15/13
Intermediate by-pass duct

assembly

(72-71-02,02-240) 1

Access panel assembly (72-71-02,02-330) 3

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

By-Pass Ducts

Rear by-pass duct assembly (72-71-03,03-250) 1

ATA FIG/ITEM QTY PER ENGINE

PART DESCRIPTION C-S-S,FIG-ITEM QTY

Fuel Spray Nozzles

Nozzle assembly (73-11-06,01-005) 9

Nozzle assembly (Mk.650-15 only) (73-11-06,01-120) 1

Nozzle assembly (73-11-06,01-205) 1

Nut, spanner - nozzle retaining

assembly

(Mks.610-8, 611-8 and 620-15

only)

(73-11-06,01-230) 1

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 20

R Dec.15/13
Block graph for stagger programme

Fig.05-00-01-990-001

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 21

R Dec.15/13
Life marking - LP compressor outlet guide vane

Fig.05-00-01-990-002

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 22

R Dec.15/13
Life marking - IP compressor IGV

Fig.05-00-01-990-003

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 23

R Dec.15/13
Life marking - IP compressor vane

Fig.05-00-01-990-004

3RR

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 rotor blade

Fig.05-00-01-990-005

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 25

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

Fig.05-00-01-990-006

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 26

R Dec.15/13
Life marking - HPC IGV

Fig.05-00-01-990-007

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 27

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

Fig.05-00-01-990-008

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 28

R Dec.15/13
Life marking - HP compressor vanes

Fig.05-00-01-990-009

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 29

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

Fig.05-00-01-990-010

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 30

R Dec.15/13
Life marking - Turbine rotor blade

Fig.05-00-01-990-011

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 31

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

Fig.05-00-01-990-012

3RR

Printed in Great Britain

RECORDING AND CONTROL OF THE LIVES OF PARTS

EFFECTIVITY: TAY/ALL 05−00−01

Page 32

R Dec.15/13
FLIGHT PROFILES AND OPERATIONAL MONITORING - GROUP A PARTS

TASK 05-00-02-800-000 Flight Profiles and Operational

Monitoring - Group A Parts

1. Datum Flight Profiles

Four sets of datum flight profiles are used to establish the declared cyclic

life of the Group A parts as defined in the Time Limits Manual, Chapter

05-10-01.

These datum flight profiles are defined as flight plan A to flight plan D

profile operation and published in figures attached.

For plan A datum flight profile, refer to Fig.05-00-02-990-009 and

Fig.05-00-02-990-010.

For plan B datum flight profile, refer to Fig.05-00-02-990-011 and

Fig.05-00-02-990-012.

For plan C datum flight profile, refer to Fig.05-00-02-990-013 and

Fig.05-00-02-990-014.

For plan D datum flight profile, refer to Fig.05-00-02-990-015 and

Fig.05-00-02-990-016.

NOTE: Information on collection and monitoring of the flight profiles is

R Maintenance Manual. given in Chapter 70-01-10 of the Engine

3RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING

EFFECTIVITY: TAY/ALL 05−00−02

Page 1

R Dec.15/12
Plan A Flight Profile - HP Speed (N2)

Fig.05-00-02-990-009

3RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING

EFFECTIVITY: TAY/ALL 05−00−02

Page 2

R Dec.15/12
Plan A Flight Profile - LP Speed (N1)

Fig.05-00-02-990-010

3RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING

EFFECTIVITY: TAY/ALL 05−00−02

Page 3

R Dec.15/12
Plan B Flight Profile - HP Speed (N2)

Fig.05-00-02-990-011

3RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING

EFFECTIVITY: TAY/ALL 05−00−02

Page 4

R Dec.15/12
Plan B Flight Profile - LP Speed (N1)

Fig.05-00-02-990-012

3RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING

EFFECTIVITY: TAY/ALL 05−00−02

Page 5

R Dec.15/12
Plan C Flight Profile - HP Speed (N2)

Fig.05-00-02-990-013

3RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING

EFFECTIVITY: TAY/ALL 05−00−02

Page 6

R Dec.15/12
Plan C Flight Profile - LP Speed (N1)

Fig.05-00-02-990-014

3RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING

EFFECTIVITY: TAY/ALL 05−00−02

Page 7

R Dec.15/12
Plan D Flight Profile - HP Speed (N2)

Fig.05-00-02-990-015

3RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING

EFFECTIVITY: TAY/ALL 05−00−02

Page 8

R Dec.15/12
Plan D Flight Profile - LP Speed (N1)

Fig.05-00-02-990-016

3RR

Printed in Great Britain

FLIGHT PROFILES AND OPERATIONAL MONITORING

EFFECTIVITY: TAY/ALL 05−00−02

Page 9/10

R Dec.15/12
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)

Pre SB 72-1320 JR34082, JR28894A 15,000

(NMSB 72-1353)

LP nozzle guide vane, stage 2

(72-52-10,01-700)

SB 72-1320 JR34355, JR34393A 23,000*

(NMSB 72-1353) JR34496A

LP nozzle guide vane, stage 2

(72-52-10,01-700)

* This life limit is subject to a satisfactory borescope inspection at

R as stated in 20,000 flight cycles and at 22,000 flight cycles,

Non-Modification Bulletin SB 72-1353.

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−00−03

Page 1/2

R Dec.15/12
CALENDAR LIFE LIMIT

TASK 05-00-04-800-000 Calendar Life Limit

A. The calendar life of an engine operated in non-airline operation is stated

in Non-Modification Service Bulletin SB 70-1050.

3RR

Printed in Great Britain

CALENDAR LIFE LIMIT

EFFECTIVITY: TAY/ALL 05−00−04

Page 1/2

Jun.15/08
TIME LIMITS

TASK 05-10-00-200-000 Flight Profiles and Operational

Monitoring - Group A Parts

1. The content of this TASK is transfered to TASK 05-00-02-800-000 (FLIGHT

PROFILES AND OPERATIONAL MONITORING, PB1)

R

R

3RR

Printed in Great Britain

TIME LIMITS

EFFECTIVITY: TAY/ALL 05−10−00

Page 1/2

R Jun.15/08
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 05-10-01-860-036

1. General Data

A. EASA TASK approval date Mar.11/2014. Approved by EASA under Approval-No.

10048464.

R

R

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

Group B parts which must not be exceeded in service.

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 1

R Sep.15/14
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.

R

R

R

R

R

R

R

R

R

R

R

R

CAUTION: SEVERAL OF THE GROUP A PARTS ARE COMMON TO THE TAY AND OTHER ENGINE

TYPES. THE CHANGE OF GROUP A PARTS BETWEEN THE TAY AND OTHER ENGINE

TYPES IS NOT PERMITTED. IT IS THE OPERATORS RESPONSIBILITY TO MAKE

SURE THAT A GROUP A PART REMOVED FROM ONE ENGINE TYPE IS NOT

RE-FITTED TO ANOTHER ENGINE TYPE.

CAUTION: IT IS PERMISSIBLE TO INTERCHANGE A GROUP A OR GROUP B PART BETWEEN

THE SAME MARK OF TAY ENGINE OPERATING IN AIRLINE AND NON-AIRLINE

OPERATION. NON-AIRLINE OPERATED ENGINES HAVE A CALENDAR LIFE LIMIT.

WHEN TRANSFERRING THE APPLICABLE PART FROM NON-AIRLINE TO AIRLINE

OPERATION, INSPECTION IN ACCORDANCE WITH THE ENGINE MANUAL MUST BE

CARRIED OUT. GROUP A PARTS THAT HAVE BEEN DISASSEMBLED TO PIECE-PART

LEVEL MUST BE MANDATORY INSPECTED IN ACCORDANCE WITH CHAPTER

05-20-01 OF THIS MANUAL.

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 2

R Sep.15/14
CAUTION: IT IS PERMISSIBLE TO INTERCHANGE A MODULE OR ENGINE FROM AIRLINE TO

NON-AIRLINE OPERATION. NON-AIRLINE OPERATED ENGINES HAVE A CALENDAR

LIFE LIMIT. WHEN TRANSFERRING THE APPLICABLE MODULE OR ENGINE FROM

AIRLINE TO NON-AIRLINE OPERATION, COGNISANCE MUST BE TAKEN OF THE

CALENDAR LIFE DATUM OF THE GROUP A PARTS. AT THE TIME OF TRANSFER

THE GROUP A PARTS ARE IMMEDIATELY SUBJECT TO THE NON-AIRLINE

CALENDAR LIFE LIMITATION. THE CALENDAR LIFE CAN BE RESET TO ZERO

ONLY BY PIECE-PART INSPECTION OF ALL THE GROUP A PARTS.

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

R

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.

R

R

R

R

R

R

R

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

R

C. The lives are expressed in terms of flight cycles based on a datum flight

profile, refer to TASK 05-00-02-800-000 (FLIGHT PROFILES AND OPERATIONAL

MONITORING, PB1). The definition of a flight cycle and the method of

recording and controlling the lives of parts is described in TASK

05-00-01-800-801 (RECORDING AND CONTROL OF THE LIVES OF PARTS, PB1).

D. Part Numbers

In some cases, for compatibility with the engine log book, the critical

group A component part number and assembly part number are listed.

E. Pro rata calculation of Group A Parts and Group B Parts interchanged

between engines with different Flight Profiles.

Four flight profiles are applicable to the Tay 650-15 engine. Plan A, plan

B, plan C and plan D.

(1) The following conditions exist where the flight plan or cyclic life

limit can change and which will require a calculation of the residual

life of Group A and Group B parts:

(a) An Operator changes flight plans, e.g. from flight plan B to flight

plan A.

(b) An engine is transferred from one Operator to another Operator with

a different flight plan, e.g. from flight plan D to flight plan B.

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 3

R Sep.15/14
(c) A Group A part or mandatory Group B part is transferred between two

engines with different flight profiles.

(2) In the event of any of the three conditions above, a pro rata

calculation is carried out to establish the residual life of the

applicable part(s).

The formula is as follows:

(Number of cycles accumulated in old plan, divided by cyclic life limit

in old plan) multiplied by cyclic life limit in new plan.

This equals the new achieved cyclic life of the part. The new achieved

cycles are subtracted from the new plan cycles limit to give the

residual life of the part.

NOTE: If more than two Operators are involved, the individual ratios

of each Operator are added together and then multiplied by the

new cyclic life limit (refer to example 3 below).

NOTE: Flight cycles are recorded in complete numbers. If the pro rata

figure is calculated into decimals, the highest complete figure

is to be recorded (e.g. 3723.7 is rounded to 3724).

NOTE: The examples used are based upon the cyclic life limits

contained in Transmittal Letter 9 of the Time Limits Manual.

These limits can be changed in a future issue.

Example 1.

An Operator has achieved 3400 Cycles Since New (CSN) in flight plan

B. The operator has now been confirmed in flight plan A. Using the LP

compressor rotor disc as an example:

3400 (achieved cycles in plan B) divided by 21000 (plan B life limit)

= 0.1619

0.1619 multiplied by 23000 (plan A limit) = 3724 (3723.7), therefore

the new achieved cyclic life is 3724 flight cycles.

The residual life of the part in flight plan A is 23000 - 3724 =

19276 flight cycles.

Example 2.

An engine has achieved 7600 CSN in service with a flight plan A

Operator. The engine is now being transferred to a flight plan D

Operator. Using the LP compressor rotor disc as an example:

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 4

R Sep.15/14
7600 (achieved cycles in plan A) divided by 23000 (plan A life limit)

= 0.33043

0.33043 multiplied by 20000 (plan D limit) = 6609 (6608.6), therefore

the new achieved cyclic life is 6609 flight cycles.

The residual life of the part in flight plan D is 20000 - 6609 =

13391 flight cycles.

Example 3 (Multiple Operators).

An engine has achieved 6700 CSN in service with a flight plan A

Operator. The engine was then transferred to a plan B Operator who

accumulated a further 2300 cycles. The engine is now being

transferred to a flight plan C Operator. Using the LP compressor

rotor disc as an example:

6700 (achieved cycles in plan A) divided by 23000 (plan A life limit)

= 0.29130

2300 (achieved cycles in plan B) divided by 21000 (plan B life limit)

= 0.10952

Add these two figures together (0.29130 + 0.10952) = 0.40082

0.40082 multiplied by 20000 (plan C limit) = 8017 (8016.4), therefore

the new achieved cyclic life is 8017 flight cycles.

The residual life of the part in flight plan C is 20000 - 8017 =

11983 flight cycles.

F. Combination of pro-rata calculation and consideration of lowest declared

life at engine mark changes

R

R

R Example 1

History

(sequential)

R

R

R Approved life Consumed cycles

R 2300 23000 R Tay 650-15 Plan A

R 5000 20000 R Tay 650-15 Plan C Pro-Rata

R 5000 18700 R Tay 650-15 Plan D Pro-Rata

R 2000 22000 R Tay 620-15 Plan A Adopts an Approved

R Life

R 1500 20000 R Tay 620-15 Plan B Cannot pro-rata

due to adopted

life

R

R

R Calculation of life for new application:

R Change between Tay 650-15 missions by sequential pro-rata:

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 5

R Sep.15/14
R 2300/23000 X 20000 = R 2000 Consumed cycles =

R 20000-2000 = R 18000 R Remaining life = Tay 650 A to C

Consumed cycles at

change =

R

R

R 7000 2000+5000 =

R 7000/20000 X 18700 = R 6545 Consumed cycles =

R 18700-6545 = R 12155 R Remaining life = Tay 650 C to D

R Change between engine marks Tay 650-15 plan D to Tay 620-15 plan A

Consumed cycles at

change =

R

R

R 11545 6545+5000 =

R 18700 R Lower Approved Life = Adopted

Approved Life

of 650 Plan D

R

R

R 18700-11545 = R 7155 Remaining life = Tay 650 D to

R Tay 620 A

R Change between missions Tay 620-15 plan A to Tay 620-15 Plan B

R 11545+2000 = R Consumed cycles at change = 13545

R Approved life of new mission is greater than adopted Approved Life

R 18700 R Lower Approved Life = Adopted

Approved Life

of 650 Plan D

R

R

R 18700-13545 = R 5155 Remaining life = Tay 620 A to

R Tay 620 B

R 13545+1500 = R 15045 R FINAL consumed cycles =

R 18700-15045 = R 3655 FINAL remaining life =

R Example 2

History

(sequential)

R

R

R Approved life Consumed cycles

R 2000 22000 R Tay 620-15 Plan A

R 1500 20000 R Tay 620-15 Plan B Pro-Rata

R 2300 23000 R Tay 650-15 Plan A Adopts an Approved

R Life

R 5000 18700 R Tay 650-15 Plan D Can pro-rata due

to lower Approved

Life

R

R

R 2300 23000 R Tay 650-15 Plan A Can pro-rata, but

limited to adopted

life

R

R

R Calculation of life for new application:

R Change between Tay 620-15 missions by pro-rata:

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 6

R Sep.15/14
R 2000/22000 X 20000 = R Consumed cycles = 1819

R 20000-1819 = R Remaining life = 18181 Tay 620 A to B

R Change between engine marks Tay 620-15 Plan B to Tay 650-15 Plan A

Consumed cycles at

change =

R

R

R 3319 1819+1500 =

R 20000 R Lower Approved Life = Adopted

Approved Life

of 620 Plan B

R

R

R 20000-3319 = R 16681 R Remaining life = Tay 620 B to

R Tay 650 A

R Change between missions Tay 650-15 Plan A to Tay 650-15 Plan D

R 3319+2300 = R Consumed cycles at change = 5619

R Approved Life of new mission is smaller than adopted Approved Life

R 5619/20000 X 18700 = R 5254 Consumed cycles =

R 18700-5254 = R 13446 R Remaining life = Tay 650 A to D

R Changes between missions Tay 650-15 Plan D to Tay 650-15 Plan A

R 5254+5000 = R Consumed cycles at change = 10254

R Approved Life of new mission is equal to adopted Approved Life:

R 10254/18700 X 20000 Lower consumed cycles =

=

R

R

10967

R 20000-10967 = R 9033 Remaining life = Tay 650 A to D

R 10967+2300 = R 13267 R FINAL consumed cycles =

R 20000-13267 = R 6733 FINAL remaining life =

R Example 3

History

(sequential)

R

R

R Approved life Consumed cycles

R 2000 20000 R Tay 651-54

R 4000 21000 R Tay 650-15 Plan B Adopts an Approved

R Life

R 2300 23000 R Tay 650-15 Plan A Cannot pro-rata

due to adopted

life

R

R

R 5000 18700 R Tay 650-15 Plan D Can pro-rata due

to lower Approved

Life

R

R

R 3000 21000 R Tay 650-15 Plan B Can pro-rata, but

limited to adopted

life

R

R

R Calculation of life for new application:

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 7

R Sep.15/14
R Change between engine marks Tay 651-54 to Tay 650-15 Plan B

Consumed cycles at

change =

R

R

R 2000 2000 =

R 20000 R Lower Approved Life = Adopted

Approved Life

of Tay 651

R

R

R 20000-2000 = R 18000 R Remaining life = Tay 651 to Tay

R 650 B

R Change between missions Tay 650-15 Plan B to Tay 650-15 Plan A

R 2000+4000 = R Consumed cycles at change = 6000

R Approved life of new mission is greater than adopted Approved Life

R 20000 R Lower Approved Life = Adopted

Approved Life

of Tay 651

R

R

R 20000-6000 = R 14000 R Remaining life = Tay 620 B to

R Tay 650 A

R Change between missions Tay 650-15 Plan A to Tay 650-15 Plan D

R 6000+2300 = R Consumed cycles at change = 8300

R Approved Life of new mission is smaller than adopted Approved Life

R 8300/20000 X 18700 = R 7761 Consumed cycles =

R 18700-7761 = R 10939 R Remaining life = Tay 650 A to

R Tay 650 D

R Change between missions Tay 650-15 Plan D to Tay 650-15 Plan B

R 7761+5000 = R Consumed cycles at change = 12761

Approved Life of new mission is greater than adopted Approved Life and

current application has lower Approved Life than the adopted Approved Life:

R

R

R 12761/18700 X 20000 = R Consumed cycles = 13649

R 20000-13649 = R Remaining life = 6351 Tay 650 D to

R B

R 13649+3000 = R FINAL consumed cycles = 16649

R 20000-16649= R FINAL remaining life = 3351

G. All group A part lives listed are non-finite, unless otherwise indicated.

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 8

R Sep.15/14
SUBTASK 05-10-01-870-001

2. Group A Parts Lives

Part Description Part No. Plan A

(Flight

Cycles

Plan B

(Flight

Cycles

Plan C

(Flight

Cycles

Plan D

(Flight

Cycles

Pre SB 72-1356

LP compressor rotor

dics assembly

(72-31-11,01-100)

JR31198A

(JR31199@)

23,000 21,000 20,000 18,700

SB 72-1356

LP compressor rotor

dics assembly

(72-31-11,01-100)

JR34563A

(JR34305@)

23,000 21,000 20,000 18,700

IP compressor rotor

dics stage 1

(72-33-31,01-025)

JR28921 23,000 21,000 20,000 20,000

IP compressor rotor

dics stage 2

(72-33-32,02-025)

JR28922 23,000 21,000 20,000 20,000

IP compressor rotor

dics stage 3

(72-33-33,03-025)

JR29568 23,000 21,000 20,000 20,000

Pre SB 72-1416

LP/IP compressor drive

shaft

(72-33-40,04-100)

JR32465 23,000 21,000 20,000 20,000

SB 72-1416

LP/IP compressor drive

shaft

(72-33-40,04-100)

JR35036 23,000 21,000 20,000 20,000

Pre SB 72-1416

HP compressor rotor

rear drive shaft

(72-37-31,01-010)

JR32289

(part of

assembly

JR32288A)

22,000 20,000 20,000 20,000

SB 72-1416

HP compressor rotor

rear drive shaft

(72-37-31,01-010)

JR35029

(part of

assembly

JR35028A)

22,000 20,000 20,000 20,000

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 9

R Sep.15/14
SB 72-1458 Part 1

HP compressor rotor

rear drive shaft

(72-37-31,01-010)

JR35208

(part of

assembly

JR35207A)

22,000 20,000 20,000 20,000

SB 72-1458 Part 2

HP compressor rotor

rear drive shaft

(72-37-31,01-010)

JR32289

(part of

assembly

JR35204A)

22,000 20,000 20,000 20,000

SB 72-1458 Part 3

HP compressor rotor

rear drive shaft

(72-37-31,01-010)

JR35029

(part of

assembly

JR35205A)

22,000 20,000 20,000 20,000

SB 72-1665

HP compressor rotor

rear drive shaft

(72-37-31,01-010)

JR57392

(part of

assembly

JR57309)

22,000 20,000 20,000 20,000

Pre SB 72-1416

LP compressor rotor

rear drive shaft

(72-37-32,02-085)

JR32466 23,000 21,000 20,000 20,000

SB 72-1416

LP compressor rotor

rear drive shaft

(72-37-32,02-085)

JR35037 23,000 21,000 20,000 20,000

HP compressor rotor

disc stage 1

(72-37-33,03-165)

JR18049 22,000*** 20,000*** 20,000*** 20,000***

*** The life limit of some of these critical parts have been reduced. For

details see SB 72-A1740.

HP compressor rotor

disc stage 2

(72-37-33,03-250)

JR18742 22,000 20,000 20,000 20,000

HP compressor rotor

disc stage 3

(72-37-33,03-295)

JR18743 22,000*** 20,000*** 20,000*** 20,000***

*** The life limit of some of these critical parts have been reduced. For

details see SB 72-A1740.

HP compressor rotor

disc stage 4

(72-37-34,04-340)

JR18744 22,000 20,000 20,000 20,000

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Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 10

R Sep.15/14
HP compressor rotor

disc stage 5

(72-37-34,04-385)

JR18746 22,000 20,000 20,000 20,000

HP compressor rotor

disc stage 6

(72-37-34,04-410)

JR18748 22,000*** 20,000*** 20,000*** 20,000***

*** The life limit of some of these critical parts have been reduced. For

details see SB 72-A1740.

HP compressor rotor

disc stage 7

(72-37-34,04-435)

JR17365 22,000*** 20,000*** 20,000*** 20,000***

*** The life limit of some of these critical parts have been reduced. For

details see SB 72-A1740.

HP compressor rotor

disc stage 8

(72-37-35,05-460)

JR17367 22,000 20,000 20,000 20,000

HP compressor rotor

disc stage 9

(72-37-35,05-485)

JR17369 22,000 20,000 20,000 20,000

HP compressor rotor

disc stage 10

(72-37-35,05-510)

JR18526 22,000 20,000 20,000 20,000

HP compressor rotor

disc stage 11

(72-37-35,05-535)

JR17373 22,000 20,000 20,000 20,000

Pre SB 72-1121

HP compressor rotor

disc, stage 10/11

spacer

(72-37-35,05-545)

JR32209 22,000 20,000 20,000 20,000

SB 72-1121

HP compressor rotor

disc, stage 10/11

spacer

(72-37-35,05-545)

JR32298 22,000 20,000 20,000 20,000

HP compressor rotor

disc, stage 12

(72-37-36,06-160)

JR31928

(part of

assembly

JR31927A)

22,000*** 20,000*** 20,000*** 20,000***

*** The life limit of some of these critical parts have been reduced. For

details see SB 72-A1740.

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 11

R Sep.15/14
HP compressor rotor

disc, stage 11/12

spacer

(72-37-36,06-180)

JR32213 22,000 20,000 20,000 20,000

Pre SB 72-1327

HP turbine shaft

(72-41-31,01-027)

JR32287

(part of sub

assembly

JR32286A and

assembly

JR32285A)

23,000 21,000 21,000 20,000

SB 72-1327 Part 1

HP turbine shaft

(72-41-31,01-027)

JR34539

(part of sub

assembly

JR34537A and

assembly

JR34554A)

23,000 21,000 21,000 20,000

SB 72-1327 Part 2

HP turbine shaft

(72-41-31,01-027)

JR34538

(part of sub

assembly

JR34536A and

assembly

JR34555A)

23,000 21,000 21,000 20,000

SB 72-1327 Part 3

HP turbine shaft

(72-41-31,01-027)

JR34538

(part of sub

assembly

JR32286A and

assembly

JR34579A)

23,000 21,000 21,000 20,000

SB 72-1327 Part 5

HP turbine shaft

(72-41-31,01-027)

JR32287

(part of sub

assembly

JR32286A and

assembly

JR34791A)

23,000 21,000 21,000 20,000

SB 72-1416

HP turbine shaft

(72-41-31,01-027)

JR35035

(part of sub

assembly

JR35034A and

assembly

JR35033A)

23,000 21,000 21,000 20,000

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 12

R Sep.15/14
SB 72-1665

HP turbine shaft

(72-41-31,01-027)

JR57400

(part of sub

assembly

JR57401 and

assembly

JR57310)

23,000 21,000 21,000 20,000

Pre SB 72-1241

HP turbine rotor disc,

stage 1

(72-41-32,02-010)

JR32013 23,000 20,000 14,700 11,000

SB 72-1241

HP turbine rotor disc,

stage 1

(72-41-32,02-010)

JR33838 23,000 21,000 18,000 14,250

Pre SB 72-1241

HP turbine rotor disc,

stage 2

(72-41-33,03-250)

JR32014A

(JR31660@)

23,000 21,000 20,000 20,000

SB 72-1241

HP turbine rotor disc,

stage 2

(72-41-33,03-250)

JR33839A

(JR33840@)

23,000 21,000 20,000 20,000

HP turbine rotor disc,

stage 2 sleeve

(72-41-33,03-261)

JR32553 23,000 21,000 20,000 20,000

HP turbine rotor disc,

stage 2 sleeve

(72-41-33,03-261)

NPG2269 23,000 21,000 20,000 20,000

Pre SB 72-1416

LP turbine shaft

(72-52-21,01-485)

JR32471

(part of

assembly

JR32470A)

23,000 21,000 20,000 20,000

SB 72-1416

LP turbine shaft

(72-52-21,01-485)

JR35039

(part of

assembly

JR35038A)

23,000 21,000 20,000 20,000

LP turbine rotor disc

assembly stage 1

(72-52-22,02-400)

JR32318A

(NPG2388@)

23,000 21,000 18,000 14,250

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 13

R Sep.15/14
SB 72-1755

LP turbine rotor disc

assembly stage 1

(72-52-22,02-400)

JR57972

(NPH8110@)

23,000 21,000 18,000 14,250

LP turbine rotor disc

assembly stage 2

(72-52-23,03-440)

JR32319

**

23,000 21,000 21,000 20,000

SB 72-1755

LP turbine rotor disc

assembly stage 2

(72-52-23,02-440)

JR57973 23,000 21,000 21,000 20,000

LP turbine rotor disc

assembly stage 3

(72-52-24,04-400)

JR32320A

(NPG2390@)

**

23,000 21,000 21,000 20,000

SB 72-1755

LP turbine rotor disc

assembly stage 3

(72-52-24,04-400)

JR57974

(NPH8113@)

23,000 21,000 21,000 20,000

* DENOTES FINITE LIFE

** GROUP A LIVES SHOWN FOR THESE PARTS ARE SUBJECT TO SAMPLING

REQUIREMENTS DEFINED IN NON-MODIFICATION SERVICE BULLETIN TAY 72-1557

@ INCLUDED FOR COMPATIBILITY WITH ENGINE LOG BOOK

SUBTASK 05-10-01-870-002

3. Mandatory Group B Parts Lives

PART DESCRIPTION PART NO.

PLAN A

(FLIGHT CYCLES)

PLAN B, C, D

(FLIGHT CYCLES)

LP compressor rotor

blade

(72-31-12,02-010) JR31912 14,200 14,200

SB 72-1105, Pre SB

72-1436

LP compressor rotor

blade

(72-31-12,02-010)

JR31911 22,000 20,000

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 14

R Sep.15/14
PART DESCRIPTION PART NO.

PLAN A

(FLIGHT CYCLES)

PLAN B, C, D

(FLIGHT CYCLES)

SB 72-1436 Part 1

LP compressor rotor

blade

(72-31-12,02-010)

JR35120 22,000 20,000

SB 72-1436 Part 2

LP compressor rotor

blade

(72-31-12,02-010)

JR35121 22,000 20,000

SB 72-1222

LP compressor rotor

blade

(72-31-12,02-014)

JR33865 22,000 20,000

SB 72-1222

LP compressor rotor

blade

(72-31-12,02-016)

JR33866 22,000 20,000

* DENOTES FINITE LIFE

3RR

Printed in Great Britain

MAXIMUM APPROVED LIVES

EFFECTIVITY: TAY/ALL 05−10−01

Page 15/16

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)

3RR

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 (72-52-22,02-425), EM TASK 72-52-22-200-000

(INSPECTION/CHECK-00, PB801)

LP Turbine Stage 2 Rotor Disc (72-52-23,03-440), EM TASK 72-52-23-200-000

(INSPECTION/CHECK-00, PB801)

3RR

Printed in Great Britain

MANDATORY INSPECTIONS OF GROUP A PARTS

EFFECTIVITY: TAY/ALL 05−20−01

Page 2

R Jun.15/10
LP Turbine Stage 3 Rotor Disc (72-52-24,04-405), EM TASK 72-52-24-200-000

(INSPECTION/CHECK-00, PB801)

3RR

Printed in Great Britain

MANDATORY INSPECTIONS OF GROUP A PARTS

EFFECTIVITY: TAY/ALL 05−20−01

Page 3/4

R Jun.15/10
ROLLS 

ROYCE @l 

All enquires regarding this manual 

should be addressed to:- 

TECHNICAL PUBLICATIONS DEPARTMENT 

ROLLS-ROYCE plc 

DERBY 

PO BOX 31 : DERBY : ENGLAND DE24 8BJ