P.O. Box 31, DERBY 

DE24 8BJ, UK 

Telephone: 44 (0) 1332 242424 

Fax: 44 (0) 1332 249936 m 

Rol Is-Royce 

TRANSMITTA 

The technical information contained in this document has been approved under the authority 

of - See Planning Information, Approval. 

Signed Date Jun. 29/11 

N. J. Wright 

RB211-524G/H-T SERIES PROPULSION SYSTEMS SERVICE BULLETIN 

ALERT 

This document transmits Revision 2 to Service Bulletin RB211-73-AGO54 

Document History 

Service Bulletin Revision Status 

Initial Issue Mar.l8/10 

Revision 1 Jun.27/11 

Bulletin Revision 2 

Remove 

All pages of the 

Service Bulletin 

Supplement Revision Status 

Incorporate 

Pages 1 to 9 of the 

Service Bulletin 

ALERT 

Reason for change 

To correct revision number 

of AEC Service Bulletin 

referenced in this 

Ro 1 1 s-Royce Se rvi ce 

Bulletin (RR RMR SB0161) 

Transmittal - Page 1 of 2 

CHECK THAT ALL PREVIOUS TRANSMllTALS HAVE BEEN INCORPORATED 

If any have not been received please advise Customer Data Services, Rolls-Royce plc, Derby, England 

O Rolls-Royce plc (date as above) Printed in Great Britain 
LIST OF EFFECTIVE PAGES

The effective pages to this Service Bulletin following incorporation of Revision

2 are as follows:

Page Revision Number Revision Date

Bulletin

R 1 2 Jun.29/11

R 2 2 Jun.29/11

R 3 2 Jun.29/11

R 4 2 Jun.29/11

R 5 2 Jun.29/11

R 6 2 Jun.29/11

R 7 2 Jun.29/11

R 8 2 Jun.29/11

R 9 2 Jun.29/11

Printed in Great Britain

RB.211−73−AG054

Transmittal - Page 2
1. Planning Information

A. Effectivity

(1) Boeing 747

RB211-524G2-19, 524G2-19/11, 524G2-19/15,524G2-T-19, 524G2-T-19/11,

524G2-T-19/15,524G3-19, 524G3-19/15,524G3-T-19, 524G3-T-19/15,524H2-19,

524H2-19/11, 524H2-19/15,524H2-T-19, 524H2-T-19/11, 524H2-T-19/15 Engines

prior to Serial No.13820.

(2) Boeing 767

RB211-524H-36, 524H-36/11, 524H-T-36, 524H-T-36/11 Engines prior to Serial

No.13820.

B. Concurrent Requirements

None

C. Reason

(1) Problem and Evidence

There is a requirement to introduce new Full Authority Fuel Controller

(FAFC) software with revised functionality including a new fan flutter

Keep Out Zone (KOZ).

In addition, an engineering review of the FAFC, based on in-service

experience, has identified a number of areas where improvements in

software may be made.

(2) Substantiation

The changes introduced by this Service Bulletin have been the subject of

satisfactory verification testing by the unit manufacturer at both a

software module level and a system level.

The software timing savings have been validated using regression testing

which concluded that there are no inadvertent functional changes affecting

the software. Successful validation testing, including unit rig testing on

the Rolls-Royce Systems Test Facility (STF), has taken place under both

normal operating conditions and known failure conditions.

FUEL AND CONTROL - FUEL CONTROLLER - INTRODUCTION OF A CONTROLLER WITH A REVISED

STANDARD OF SOFTWARE ISSUE 17 - MOD.73-AG054

Printed in Great Britain

RB.211−73−AG054

Page 1 of 9

Mar.18/10

R Jun.29/11
(3) Objective

Incorporation of this Service Bulletin is designed to upgrade the software

standard and maintain unit reliability.

(4) Effect of Bulletin on:

(a) Operation

Not affected

(b) Maintenance

Not affected

(c) Overhaul

Not affected

(d) Repair Schemes

Not affected

(e) Interchangeability

Not affected

D. Description

(1) This Service Bulletin covers the fitment to engines of an FAFC

incorporating Aero Engine Controls Service Bulletin FAFC2000-73-7725,

R dated Jun 22/10. Initial Issue

(2) The software changes introduced by this Service Bulletin are:

(a) Engine control behavior under conditions of dedicated generator drive

or bearing failure has been found to be unacceptable when the rate of

generator rundown is low or the resultant N3 signal is noisy.

Currently, the control laws will respond to a sub-idle N3 signal by

increasing fuel flow in a valid attempt to maintain the required idle

speed.

An N3 signal rate check is introduced to assist in the accommodation

of dedicated generator failures. In addition, the N3 idle control

schedule is revised to prevent a failing N3 signal resulting in a

significant increase in fuel scheduling.

Printed in Great Britain

RB.211−73−AG054

Page 2

Mar.18/10

R Jun.29/11
(b) To avoid the possibility of encountering on-wing fan flutter whilst on

the ground when the FAFC is in primary Engine Pressure Ratio (EPR) or

alternate N1 mode of control, the commanded EPR or N1 must be

restricted from stabilising in the fan flutter KOZ, defined by upper

and lower limits.

An automatic KOZ is introduced to prevent steady state operation in

the fan flutter region. When enabled the KOZ prevents the EPR or N1 of

the engine stabilising within the fan flutter region.

(c) A recent event on an RB211 524G/H powered aircraft indicates that

deteriorated engines, running with a high N1 at an EPR, could be

thrust limited during climb with no indication other than a

discrepancy on the pilots EPR gauge. During the event the discrepancy

was reported as 0.02 EPR between two engines. Investigation confirmed

that the limitation was caused by the N1 back-up control loop in the

FAFC.

The N1 back-up control loop exists to limit engine thrust should an

EPR measurement error exist that causes a large difference between EPR

command and measured EPR, resulting in the steady state control law

increasing fuel. The back-up loop is set to limit N1 to the N1

reversionary command plus fixed offset.

An offset is introduced to the N1 reversionary command that is a

function of altitude. The setting of the offset ensures that low

altitude flight regimes are unaffected and that increased margin to

the back-up limitation is available to prevent EPR shortfall events at

higher altitudes.

(d) There has been one occurrence of an in-flight shut-down caused by an

indicated high oil temperature (TOIL), due to a failure of the lane A

oil temperature bulb. The oil temperature indication logic is designed

to manage temperature bulb problems by recognising a discrepancy (the

two lanes are more than 15 deg C apart) and choosing the signal

closest to 100 deg C. The problem is attributed to an intermittent

bulb fault, resulting in the logic incorrectly selecting the faulty

signal.

A TOIL rate check is introduced which is used in conjunction with the

TOIL validation logic to ensure intermittent signals are detected and

correctly accommodated.

Printed in Great Britain

RB.211−73−AG054

Page 3

Mar.18/10

R Jun.29/11
(e) During in-service operation, operators have suffered delays due to

failed attempts at engine starting on extreme cold days (-27 deg C or

below). Data from the events has shown that engines were operating at

idle on the absolute minimum idle speed setting, 55 percent N3. The

engine autostart abort occurred just as the affected engines were

beginning to stabilise at idle, with the instantaneous speed at abort

being just below 55 percent N3. The autostart hang/stall detection

function is active up to 55 percent N3. Therefore, an engine about to

stabilise at an idle speed close to 55 percent N3 can be

misinterpreted as being about to stall and an autostart abort may

occur.

The upper limit for hang/stall detection is revised to ensure it is

always at least 3 percent lower than the idle schedule in order to

remove the possibility of operators experiencing an incorrect

hang/stall when starting in extremely cold temperatures.

(f) An engineering review of the software has shown that a single cycle

High Pressure Shut Off Valve (HPSOV) microswitch transition from OPEN

to CLOSED can cause incorrect fuel scheduling and cause the engine to

hang.

The revised software incorporates a fault integrator when the FAFC

detects that the HPSOV microswitch has changed from one switch state

to the other. When this transition occurs the fault integrator counts

for four software cycles to confirm that the transition has genuinely

occurred. This confirmation prevents the incorrect fuel scheduling.

(g) A review of service operation has shown that the subject engines with

autostart functionality enabled may suffer a large number of autostart

related maintenance messages set, indicating failure to meet fuel-on

conditions, particularly when no cross-bleed is available. The

maintenance message is set if fuel-on conditions are not met within 65

seconds.

The software is revised to increase the timer to 120 seconds. This

increase allows the engine more time to satisfy the fuel-on

conditions.

Printed in Great Britain

RB.211−73−AG054

Page 4

Mar.18/10

R Jun.29/11
(h) T20 measurement faults at engine start may cause nuisance P30 pipe

leak messages, as the P30 model is a function of T20. Failure of the

T20 signal, low but in range, will cause the P30 model to increase in

value. If it increases by 40 percent then this will trip the P30 pipe

leak logic. This results in the setting of maintenance message 7x808

ENG PNEUMATIC LINE FAIL and a DO NOT DISPATCH status message being

set.

During normal operation, the FAFC logic should be using the aircraft

T20 value. When there is no agreement between the engine and aircraft

values, the logic will select an engine value. In this situation, if

the engine values disagree by more than 5K, then the lowest in-range

value will be selected.

The software is revised so that P30 pipe logic disables when engine

T20 is selected (indicating that there is no agreement between

aircraft and engine T20) AND the engine T20 values disagree by more

than 15K. Analysis has shown that a 15K error will not cause the P30

pipe leak check to fail and hence errors less than this are

acceptable.

(i) The opportunity is taken to introduce timing savings in order to make

the software more efficient and allow additional code to be

implemented.

(3) Existing units may be reworked in accordance with the vendor service

bulletin.

(4) Units incorporating this Service Bulletin will be identified by a new type

number (see 2D).

(5) The Boeing 747 Airplane Flight Manual (AFM) will require revision to

disallow the use of take-off EPR at or below the upper fan flutter KOZ.

The Boeing 767 AFM will not be revised at present. Take-off EPR in the fan

flutter KOZ is not possible on the Boeing 767 because no aircraft are

currently configured with fixed derate capability.

E. Compliance

ALERT

This Service Bulletin must be accomplished on all engines by 31st December

2014.

F. Approval

The technical content of Service Bulletin 73-AG054 was approved by a

representative of the European Aviation Safety Agency (EASA) on Mar.10/10, EASA

certificate No.10029185.

Printed in Great Britain

RB.211−73−AG054

Page 5

Mar.18/10

R Jun.29/11
This Service Bulletin has been reviewed by the Federal Aviation Authority (FAA)

and the repairs and modifications herein comply with the applicable Federal

Aviation Regulations (FAR(s)) and are FAA approved.

This Service Bulletin has been approved by the Boeing Commercial Airplane

Company.

G. Manpower

R Refer to Aero Engine Controls Service Bulletin FAFC2000-73-7725, Initial Issue

dated Jun 22/10.

H. Material Price and Availability

R Refer to Aero Engine Controls Service Bulletin FAFC2000-73-7725, Initial Issue

dated Jun 22/10.

I. Tooling Price and Availability

R Refer to Aero Engine Controls Service Bulletin FAFC2000-73-7725, Initial Issue

dated Jun 22/10.

J. Weight and Balance

(1) Weight Change

None

(2) Moment Arm

No effect

(3) Datum

Power Plant Station (PPS) 100

K. References

(1) Refer to Aero Engine Controls Service Bulletin FAFC2000-73-7725, Initial

Issue

R

R dated Jun 22/10.

(2) This Service Bulletin is subsequent to the following Rolls-Royce RB211

Service Bulletin:

73-D435

Fuel and control - Fuel controller - Introduction of a controller with

revised standard of software (TRW Lucas SB FAFC2000-73-7543).

(3) Engine Manual, 72-00-34, Removal and Installation

Printed in Great Britain

RB.211−73−AG054

Page 6

Mar.18/10

R Jun.29/11
(4) Aircraft Maintenance Manual, Removal/Installation

L. Other Publications Affected

For effect on Illustrated Parts Catalogue (IPC) refer to 2. Material

Information.

M. Interchangeability of Parts

Not affected

Printed in Great Britain

RB.211−73−AG054

Page 7

Mar.18/10

R Jun.29/11
2. Material Information

A. The kit required consists of the following parts:

None

B. Parts to be reworked:

None

C. New production parts:

The following parts will be made available as future spares:

None.

D. Vendor units affected:

The following unit type number changes have been allocated to identify units

embodying the features of this Service Bulletin:

All Engines

73-21-09

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

01350 FAFC2000

-11BK5

1 .Control, fuel (VU4287) - FAFC2000

-11BJ5

(1)

01350 FAFC2000

-12BK6

1 .Control, fuel (VU4287) - FAFC2000

-12BJ6

(1)

E. Instruction disposition codes:

(1) Old and new parts are freely and fully interchangeable.

Printed in Great Britain

RB.211−73−AG054

Page 8

Mar.18/10

R Jun.29/11
3. Accomplishment Instructions

A. The revised Full Authority Fuel Controller (FAFC) software introduced by this

Service Bulletin is interchangeable with the existing. Remove existing and

install new in accordance with current overhaul or maintenance procedures

(Engine Manual, 72-00-34, Removal and Installation or Aircraft Maintenance

Manual, 73-21-13, Removal/Installation).

B. For rework of the existing FAFC, refer to Aero Engine Controls Service Bulletin

R dated Jun 22/10. FAFC2000-73-7725, Initial Issue

C. A record of accomplishment is required.

Printed in Great Britain

RB.211−73−AG054

Page 9

Mar.18/10

R Jun.29/11
AERO ENGINE CONTROLS

SHAFTMOOR LANE

HALL GREEN

BIRMINGHAM B28 8SW

ENGLAND

TELEPHONE: 44 121 707 7111

FAX: 44 121 707 8826

TRANSMITTAL

FAFC2000-73-7725 Page 1 of 2

Jun 22/10

©2010 Rolls-Royce Goodrich Engine Control Systems Limited

301430

FULL AUTHORITY FUEL CONTROL TYPE: FAFC2000

ATA REF 73-21-09

THIS PAGE TRANSMITS THE INITIAL ISSUE OF SERVICE BULLETIN FAFC2000-73-7725

Please note the Company name has changed from Goodrich Engine Control Systems to

Aero Engine Controls.

Reason for issue

This service bulletin (modification) introduces the approved main processor software (known as 

issue 17).

Action

Keep this SB with the Component Maintenance Manual. Put in this SB Transmittal page and the SB 

pages 1 thru 8 dated Jun 22/10.

APPROVED FOR AERO ENGINE CONTROLS

SERVICE BULLETIN TRANSMITTAL

Signed: Date: 22nd June 2010
Aero Engine Controls

TRANSMITTAL

FAFC2000-73-7725 Page 2 of 2

Jun 22/10

©2010 Rolls-Royce Goodrich Engine Control Systems Limited

BLANK PAGE
FAFC2000-73-7725

Page 1 of 8

Jun 22/10

©2010 Rolls-Royce Goodrich Engine Control Systems Limited

Aero Engine Controls

SERVICE BULLETIN

ENGINE FUEL AND CONTROL - CONTROL -

FULL AUTHORITY FUEL CONTROL TYPE FAFC2000

INTRODUCTION OF APPROVED MAIN PROCESSOR SOFTWARE ISSUE 17

1. Planning Information

A. Effectivity

Full Authority Fuel Control (FAFC), Types: 

FAFC2000-11-BJ-5, FAFC2000-12-BJ-6.

NOTE: This Service Bulletin can also be applicable to FAFC types with previous issues 

of approved main processor software.

B. Concurrent Requirements

None

C. Reason

(1) Problem

It is necessary to make changes that will improve the current version of control 

software in the Full Authority Fuel Control (FAFC).

(2) Substantiation

The changes introduced by this Service Bulletin (modification) have had satisfactory 

verification and validation tests.

(3) Objective

Incorporation of this Service Bulletin (Modification) will improve the current software 

standard and maintain the FAFC reliability.

D. Description

This Service Bulletin introduces new approved ’Flight Release’ main processor software 

into the FAFC. The new software (Issue 17) has changes which makes necessary 

functional enhancements, corrections and various improvements to the current FAFC 

software. The new software identity is:

Main processor (Lanes A and B):

Remote processor (Lanes A and B):

EEPROM data file:

FAF1MU50B.GRP

FAFCRU27A.GRP (Current)

FAFEEP90A.DAT
FAFC2000-73-7725

Page 2 of 8

Jun 22/10

©2010 Rolls-Royce Goodrich Engine Control Systems Limited

Aero Engine Controls

SERVICE BULLETIN

The main processor software is stored in the D07 and D08 Computer assemblies. When 

the accomplishment instructions (para. 3.) have been done the FAFC type number 

changes as follows:

E. Compliance

Do this Service Bulletin (modification) to in-service and repair FAFC units as agreed with 

Rolls-Royce plc.

F. Approval

The technical content of this Service Bulletin has been approved as part of Rolls-Royce 

Service Bulletin 73-AG054.

G. Manpower

At workshop visit:

Program and recertify the FAFC only - 10 hours.

H. Weight and Balance

No Change.

I. References

FAFC2000 Component Maintenance Manual (CMM) (73-21-09).

DCU 1026 Production Acceptance Test Rig (ET 597109) Ground Equipment Manual 

(GEM).

Rolls-Royce RB211 Service Bulletin 73-AG054.

J. Other Publications Affected

FAFC2000 Component Maintenance Manual (CMM) (73-21-09) Testing and 

Troubleshooting and the Illustrated Parts List Sections.

2. Material Information

A. Material - Price and Availability

The cost of the parts and manpower to accomplish this Service Bulletin will be charged to 

the operator.

B. Tooling - Price and Availability

If applicable a supplement to this service bulletin will be issued later.

FAFC2000-11-BJ-5

FAFC2000-12-BJ-6

Becomes

Becomes

FAFC2000-11BK5

FAFC2000-12BK6
FAFC2000-73-7725

Page 3 of 8

Jun 22/10

©2010 Rolls-Royce Goodrich Engine Control Systems Limited

Aero Engine Controls

SERVICE BULLETIN

C. Material Necessary for Each FAFC

The consumable items necessary to do the accomplishment instructions are given in the 

related CMM. Some of the items necessary can be supplied in a kit as follows (the 

equivalent alternatives can be used for the items shown): 

NOTE: To get the software kit necessary to do the accomplishment instructions for this 

Service Bulletin send a Purchase Order to one of the addresses that follow (or 

use one of the E-mail addresses that follow):

AMERICAS

Spares Service Desk

Customer Services America

4115 Corporate Center Drive

Monroe

North Carolina

28110-1313

USA

Telephone: +1 704-282-2545

Fax: +1 704-238-8533

E-mail: cs.spares@goodrich.com

Part Number Qty/

FAFC Description InstructionNote No.

86611121 Software Modification Kit

You only need to order one kit but you must give the 

quantity of FAFC to be changed.

The software modification kit includes:

FAFC2000-73-7725 Copy of this service bulletin

86611108 CD-ROM (new Control and Test files) 1

86620040 1 Unit label (-11BK5) 2

86620040 1 Unit label (-12BK6) 2

77765463 4 D07/D08 assembly label 2

77769766 16 IC adhesive cover 2

Instruction Notes

1 Copy the CD-ROM files onto the DCU 1026 Production Acceptance Test Rig (ET 

597109). The CD will automatically copy the files to their correct directories. 

Make a folder icon for the new type number and rename shortcut icons for the new 

test files. Reboot the computer.

2 Discard and attach new item
FAFC2000-73-7725

Page 4 of 8

Jun 22/10

©2010 Rolls-Royce Goodrich Engine Control Systems Limited

Aero Engine Controls

SERVICE BULLETIN

EUROPE, MIDDLE EAST, and AFRICA

Spares Service Desk

Customer Services Europe, Middle East and Africa

Stratford Road

Solihull

B90 4LA

UK

Telephone: +44 (0)121 451 5851

Fax: +44 (0) 121 451 5949

E-mail: cs.europe@Goodrich.com

ASIA/PACIFIC

Spares Service Desk

Customer Services Asia Pacific

Customer Services

Goodrich Control Systems Pte. Ltd.

39 Changi North Crescent

Singapore 499642

Telephone: +65 6543 7233

Fax: +65 6542 7236

E-mail: ap.spares@Goodrich.com

D. Changed Parts

The parts that can be changed and their new part numbers after the change are as 

follows:

Instruction Note(s):

1. Do the change and identify the part with the new part number.

3. Accomplishment Instructions

The accomplishment instructions must be done by an authorised Maintenance, Repair and 

Overhaul Facility. To put the new software into the FAFC do the tests and procedures that 

follow. Refer to the CMM, Testing and Troubleshooting section unless other sections in the 

CMM are given.

New Part

Number

Qty/

FAFC Description Old Part 

Number

Instruction

Note No.

86634895 2 D07 Control Computer Assembly 

(Pre SB 7256)

86628598 1

86634894 2 D07 Control Computer Assembly 

(Post SB 7256)

86628597 1

86634897 2 D08 S/M Computer Assembly

(Pre SB 7257)

86628600 1

86634896 2 D08 S/M Computer Assembly

(Post SB 7257)

86628599 1
FAFC2000-73-7725

Page 5 of 8

Jun 22/10

©2010 Rolls-Royce Goodrich Engine Control Systems Limited

Aero Engine Controls

SERVICE BULLETIN

A. Pre-Programming Procedure

(1) Do the Prepare for the Test Procedure.

(2) Do the Fault Code Store Extract and Translate procedures.

(3) Remove the two D07 and the two D08 computer assemblies from the FAFC (refer to 

the CMM, Disassembly section).

(4) Do the D07/D08 Preparation procedure and the Program Erasure procedure to the 

two D07 and the two D08 computer assemblies (refer to the CMM, Testing and 

Troubleshooting section).

B. Programming Procedure

(1) Do one of the two Programming procedures that follow:

(a) ROM 3000 Prommer

1 Do the Programming Procedure to install the new software into the D07 & 

D08 assemblies (refer to the CMM, Testing and Troubleshooting section).

NOTE: In the NOTE in step 3. E. 3. of the Programming Procedure the first 

pair of checksums must be 29E5 and the second pair 5C16.

(b) Lloyds ONBP 100 Board Programmer

NOTE: This is the preferred method of programming the software.

1 Make sure that the necessary software files are loaded in the Lloyds 

ONBP 100 Board Programmer.

2 Make sure the adaptor applicable to the D07 (adaptor AD017) or D08 

(adaptor AD018) card is installed to the Lloyds ONBP 100 Board 

Programmer.

3 Energise the Lloyds ONBP 100 Board Programmer and the PC.

4 When the PC has booted up select ONBP100 from the desktop.

5 The PC will prompt you for a password.

WRITE operator

The VDU will show the version of the Programmer Firmware.

NOTE: If you do not see the correct version of Programmer Firmware 

change it by use of the Lloyds Research Programmer Help File.

6 When the device table has loaded the VDU will show ’Programmer 

Connected’.

NOTE: If you do not see the message ’Programmer Connected’ you can get 

communication errors.
FAFC2000-73-7725

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Jun 22/10

©2010 Rolls-Royce Goodrich Engine Control Systems Limited

Aero Engine Controls

SERVICE BULLETIN

7 Select File.

8 Select Open Job and select the necessary Job File (refer to Checksum 

Table below).

9 Select Open.

10 Select Load Job, followed by Run Job.

11 When the files are downloaded to the programmer, select OK.

12 Make sure that the File Checksums are correct (refer to the Checksum 

Table below).

13 Select Load Job, Choose Device.

14 Select the device 27C256 Intel.

15 Select OK.

16 Before you install the card in the programmer do a check of the card 

connector and the adaptor connector. Make sure the pins are correct and 

not damaged.

17 Install the card in the programmer adaptor. Use the top plate to secure the 

card.

18 Select Program, Program.

19 When Programming is complete the applicable Board Checksum will be 

shown (refer to the Checksum Table below).

20 Select OK.

21 Use the hinged plate to remove the card from the programmer adaptor.

22 Do again paras (16) thru (21) for the next card of the same type, when 

both cards of the same type have been programmed, do para (23)

23 Do again paras (1) thru (22) for next card type to be programmed, when 

the two D07 cards and the two D08 cards are programmed do para (24).

Board Job File File Name File 

Checksum

Board 

Checksum

D07 D07_FMU150B.LRJ FRU150B.ABS

FRU150B.AB1

68C3

5D28

00EF85FB

D08 D08_FMU150B.LRJ FRU150B.ABS

FRU150B.AB1

68C3

5D28

00EF85FB
FAFC2000-73-7725

Page 7 of 8

Jun 22/10

©2010 Rolls-Royce Goodrich Engine Control Systems Limited

Aero Engine Controls

SERVICE BULLETIN

C. Post Programming Procedure

(1) Do the Assembly Completion Procedure (refer to the CMM, Testing and 

Troubleshooting) to the two D07 and the two D08 assemblies.

(2) Install the two D07 and the two D08 assemblies into the FAFC (refer to the CMM, 

Assembly).

(3) Do the Install New Trim Files in the D08 procedure (refer to the CMM, Testing and 

Troubleshooting). Use the software files that follow:

(4) Do the Standard Serviceability Test Schedule procedure (refer to the CMM, Testing 

and Troubleshooting). Use the changed software files that follow:

(5) Attach a new Unit Label marked with the new unit type number (i.e. FAFC2000-

11BK5 or FAFC2000-12BK6, new main processor software file (50B), existing 

remote processor software file (27A) and the EEPROM data file (90A).

Main Symbol Table: FMU150B

EEPROM Trim: UPD90A

Trim File Verification: VER90A.

Main Symbol Table: FMU150B

Lane A and B Main Software: FAF1MU50B

Y59F1 Automatic Test Program: Y59F139B

Y59F2 Automatic Test Program: Y59F232B

Y59F3 Automatic Test Program: Y59F335B
FAFC2000-73-7725

Page 8 of 8

Jun 22/10

©2010 Rolls-Royce Goodrich Engine Control Systems Limited

Aero Engine Controls

SERVICE BULLETIN

BLANK PAGE