LIST OF EFFECTIVE PAGES

The effective pages to this Service Bulletin are as follows:

Page Revision Number Revision Date

Bulletin

1 Sep.3/10

2 Sep.3/10

3 Sep.3/10

4 Sep.3/10

5 Sep.3/10

6 Sep.3/10

7 Sep.3/10

8 Sep.3/10

9 Sep.3/10

10 Sep.3/10

Appendix 1

1 Sep.3/10

Printed in Great Britain

RB.211−71−AG416

Transmittal - Page 2
1. Planning Information

A. Effectivity

Airbus A330

RB211 TRENT 768-60, TRENT 768-60/15, TRENT 768-60/16, TRENT 768-60/17

Propulsion Systems.

RB211 TRENT 772-60, TRENT 772-60/15, TRENT 772-60/16, TRENT 772-60/17

Propulsion Systems.

RB211 TRENT 772B-60, TRENT 772B-60/15, TRENT 772B-60/16, TRENT 772B-60/17

Propulsion Systems.

RB211 TRENT 772C-60, TRENT 772C-60/15, TRENT 772C-60/16 Propulsion Systems.

B. Reason

A number of Trent 700 air intake cowl, primary assembly structures (refer to

Bombardier Aerospace-Shorts NMSB RB211-71-015, Figure 2), were found with

cracks in the forward bulkhead web, web stiffeners, boundary angles and to a

lesser extent on the Thermal Anti Ice (TAI) spray ring during shop visit.

Analysis of the effects of cracking on these structures identified a need to

inspect the primary assembly and to rectify the damage found.

This Non-Modification Service Bulletin (NMSB) instructs an inspection of the

forward bulkhead assembly, the TAI spray ring and its associated attachment

links. The intent of this inspection is to identify and rectify damage.

Operators are also requested to provide details of the findings to aid problem

understanding. These findings will also help define the most effective way of

managing the issue in-service.

Permitted damage limits are provided to help operators with managing their

fleet (refer to Fig.1 and Table 1). If any component is found to have damage

more than these limits, it must be repaired before the air intake is returned

to service.

C. Description

This NMSB instructs a borescope inspection of the forward bulkhead, TAI spray

ring assembly and attachment brackets.

Advise Bombardier Aerospace-Shorts and your local Rolls-Royce Field Service

Office (FSO) of NMSB accomplishment and inspection results in accordance with

Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015. Refer to Appendix 1.

POWERPLANT - AIR INTAKE COWL - INSPECTION OF THE FORWARD BULKHEAD, THERMAL ANTI ICE

(TAI) SPRAY RING ASSEMBLY AND ATTACHMENT BRACKETS (BOMBARDIER AEROSPACE-SHORTS

NON-MODIFICATION SERVICE BULLETIN RB211-NAC-71-015) NON-MODIFICATION SERVICE BULLETIN

- NON - MOD.71-AG416

Printed in Great Britain

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Page 1 of 10

Sep. 3/10

Sep. 3/10
D. Compliance

ALERT

This NMSB is anticipated to be the subject of an EASA Airworthiness Directive.

Rolls-Royce recommends that the procedures contained within Bombardier

Aerospace-Shorts NMSB RB211-71-015 and 3. Accomplishment Instructions are done

at the following opportunities given the age of the air intakes since new or

life since replacement of the air intake primary assembly.

NOTE: A flow chart is provided (refer to Fig.1) to assist with the planning of

the various inspection procedures.

NOTE: When the complete component life history is available, inspect the air

intake cowl in accordance with Compliance (1.D.).

NOTE: When the history of an air intake is partial or unknown, prior to

inspection of the air intake cowl in accordance with Compliance (1.D.),

apply one of the following methods to estimate the accumulated life of

the air intake cowl:

(1) If it can be proven that an air intake cowl has been in continued

use with one particular operator from its entry into service until

the date the NMSB is accomplished the aircraft life from that

operators fleet leader must be adopted.

(2) If it cannot be proven that the air intake cowl has been in

continued use with a particular operator from entry into service

until the date the NMSB is accomplished, the Yearly Fleet Leader

method is to be applied. Refer to Accomplishment Instructions

(3.C.).

NOTE: It is imperative that operators continue to maintain an accurate record

of the air intake cowl lives to avoid the need to repeat the Yearly

Fleet Leader life calculations in the future.

(1) For air intakes with a life less than 5000 cycles since new accomplish the

initial inspection of the primary assembly in accordance with step

D.(1)(a) or step D.(1)(b), whichever is greater.

(a) When the air intake cowl has accumulated 5000 cycles since new

(b) Within 24 months from the issue of this NMSB

(2) For air intakes with a life greater than 5000 cycles since new accomplish

the initial inspection of the primary assembly within 24 months from issue

of this NMSB.

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Sep. 3/10
(3) If it can be shown that the previous repair of the air intake introduced a

new complete primary assembly (including TAI spray ring and installation),

then the initial inspection can be delayed and performed after 5000 cycles

of service has accumulated since the repair was accomplished.

(4) If no damage is found after the initial inspection, do repeat inspections

of the air intake primary assembly as follows:

(a) TAI spray ring and attachment links every 2500 cycles.

(b) Inner and outer boundary angles and bulkhead every 5000 cycles.

(5) If damage is found repeat inspections in accordance with the limits and

intervals provided in Fig.1 and Table 1.

(6) If multiple engines on a given aircraft are found to have broken TAI spray

ring attachment links, depair engines as instructed in Fig.1.

Depair - replace one air intake cowl with a serviceable unit to reduce the

risk of having two air intake cowls with broken TAI spray ring attachment

links (more than permitted limit) on one aircraft.

E. Approval

The technical content of this Non-Modification Service Bulletin was approved

under the authority of Design Organisation Approval EASA.21J.031 on Aug.26/10.

F. Manpower

Refer to Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015.

G. Material Price and Availability

Refer to Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015.

H. Tooling Price and Availability

Refer to Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015.

I. References

(1) Engine Manual, 71-61-00, Removal and Installation.

(2) Airbus A330 Aircraft Maintenance Manual, 71-61-41, Maintenance Practices

(3) Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015

(4) Airbus aircraft Service Bulletin A330-71-3025

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Sep. 3/10
2. Material Information

Refer to Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015.

Printed in Great Britain

RB.211−71−AG416

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Sep. 3/10

Sep. 3/10
3. Accomplishment Instructions

A. The procedure contained in Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015,

3.Accomplishment Instructions has been developed to allow inspection to be

completed with the air intake cowl installed on-wing. It is permitted for the

inspection to be accomplished with the air intake cowl removed.

CAUTION: IN ORDER TO REDUCE THE POTENTIAL FOR MULTIPLE-ENGINE IN-FLIGHT SHUTDOWN,

POWER LOSS OR OTHER ANOMALY DUE TO MAINTENANCE ERROR, ROLLS-ROYCE

RECOMMENDS THAT OPERATORS AVOID PERFORMING MAINTENANCE ON MULTIPLE

ENGINES INSTALLED ON THE SAME AIRCRAFT AT THE SAME TIME. IF IT IS NOT

POSSIBLE TO AVOID MAINTENANCE ON MORE THAN ONE ENGINE AT THE SAME TIME,

ROLLS-ROYCE RECOMMENDS THAT ADDITIONAL CONTROLS ARE APPLIED IN ORDER TO

MAKE SURE THAT MAINTENANCE TASKS HAVE BEEN COMPLETED AS DEFINED.

MAINTENANCE GUIDELINES SHOULD BE REVISED, WHERE POSSIBLE, TO PROMOTE

THIS RECOMMENDATION.

(1) If necessary remove air intake cowl in accordance with current overhaul or

maintenance procedures (Engine Manual, 71-61-00, Removal and Installation

or Aircraft Maintenance Manual, 71-61-41, Maintenance Practices).

(2) Inspect the air intake cowl in accordance with Bombardier Aerospace

-Shorts NMSB RB211-NAC-71-015 and 3.Accomplishment Instructions.

(3) If applicable, fit the air intake cowl, or a replacement, to the engine in

accordance with current overhaul or maintenance procedures (Engine Manual,

71-61-00, Removal and Installation or Aircraft Maintenance Manual,

71-61-41, Maintenance Practices).

B. Permitted damage limits and repeat inspection intervals

Outer Boundary Angle (OBA) Forward Bulkhead

Length of Crack(s)

Found millimeters

(inches) - Largest

Crack on Unit

Repeat Inspection

Interval

(Cycles)

Step (1)

Length of Crack(s)

Found millimeters

(inches) - Largest

Crack on Unit

Repeat Inspection

Interval

(Cycles)

Step (1)

None 5000 None 5000

25,4 (1.00) 5000 25,4 (1.00) 3225

50,8 (2.00) 5000 50,8 (2.00) 2825

76,2 (3.00) 5000 76,2 (3.00) 2425

101,6 (4.00) 5000 101,6 (4.00) 2025

127,0 (5.00) 4600 127,0 (5.00) 1600

152,4 (6.00) 4125 152,4 (6.00) 1200

177,8 (7.00) 3650 177,8 (7.00) 800

203,2 (8.00) 3200 203,2 (8.00) 400

228,6 (9.00) 2750 228,6 (9.00) Reject

See Step (3)

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Sep. 3/10

Sep. 3/10
Outer Boundary Angle (OBA) Forward Bulkhead

Length of Crack(s)

Found millimeters

(inches) - Largest

Crack on Unit

Repeat Inspection

Interval

(Cycles)

Step (1)

Length of Crack(s)

Found millimeters

(inches) - Largest

Crack on Unit

Repeat Inspection

Interval

(Cycles)

Step (1)

254,0 (10.00) 2300

279,4 (11.00) 1825

304,8 (12.00) 1375

330,2 (13.00) 900

355,6 (14.00) 450

381,0 (15.00) Reject

See Step (2)

Table 1

(1) Get the Repeat inspection interval from the longest crack found on a unit.

There is no limit to the number of cracks but there must be a minimum

distance between the cracks (centre to centre) of 3 times the length of

the longest crack. Reject units found to have cracking more than this

limit.

(2) Crack in OBA:

(a) Between 381,0 mm and 558.8 mm (15.00 in. and 22.00 in.) long, remove

the intake cowl before 100 flight cycles.

(b) Greater than 558,8 mm (22.00 in.) long, remove intake cowl before next

flight.

(3) Crack in forward bulkhead:

(a) Between 228,6 mm and 330,2 mm (9.00 in. and 13.00 in. ) long, remove

intake cowl before 100 flight cycles.

(b) Greater than 330,2 mm (13.00 in.) long, remove intake cowl before next

flight.

C. Trent 700 air intake cowl - life calculation - Yearly Fleet Leader method

(1) When the complete component life history is available, inspect the air

intake cowl in accordance with Compliance (1.D.).

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(2) To estimate the accumulated life of the air intake cowl when the history

is partial or unknown, apply the following methodology.

NOTE: This methodology is based on the Yearly Fleet Leader and allows the

calculation of conservative values to cover periods during which

the accumulation of flight cycles is unknown. It can be applied to

calculate the life from new or to cover only certain periods of the

component history.

(a) For periods where no history is available the Yearly Fleet Leader

accumulated flight cycles for the Airbus A330 (Trent 700 engine)

aircraft must be considered. The actual fleet leader lives from 1995

to 2009 have been provided in Table 2.

(b) Yearly fleet leader lives from Jan.01/10 onwards can be obtained from

Airbus.

(c) Calculations must include the accumulated Airbus A330 (Trent 700

engine) aircraft flight cycles from the date of the air intake cowls

initial entry into service until the date when this NMSB is

accomplished.

(d) If an operator does not have a record of the entry into service date

of the air intake cowl (it is not included on the air intake cowl

plate or aircraft log book) operators must contact Bombardier

Aerospace-Shorts to get the date of manufacture for each serialised

unit.

(e) If the initial entry into service date cannot be established then the

conservative start date of Apr.01/95 must be used.

(f) Each year of service must be divided into twelve equal periods (one

per month), except for the year 1995, which must be divided into nine

equal periods.

(g) The start date and end date of each period during which the history of

life accumulation is unknown must be rounded up to consider complete

months only.

(3) Calculation example

An operator needs to calculate the life of an air intake cowl from

Apr.17/02 (air intake cowl first flight). The operator wants to know the

parts life on Nov.30/09.

For periods where no history is available the Yearly Fleet Leader

accumulated Flight Cycles (FC) must be considered Refer to Table 2.

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(4) The calculation parameters are:

(a) Date of first flight - Apr.17/02.

Actual, recorded , life accumulated between Apr.17/02 to Jun.16/03 =

+723FC

No history is available for the following period Jun.16/03 to

Dec.11/06.

Actual, recorded, life accumulated between Dec.11/06 to Nov.30/09 =

+2100FC

(5) Calculation of life history

(a) Actual, recorded, life accumulated between Apr.17/02 to Jun.16/03 =

+723 FC

(b) Conservative life (calculated using Yearly Fleet Leader data) for the

period from Jun.16/03 to Dec.11/06:

To cover period from Jun.16/03 to Dec.31/03: +7x(1404/12)= +819 FC

To cover year 2004 = +1557 FC

To cover year 2005 = +1558 FC

To cover year 2006 = +1655 FC

Total = +5589 FC

NOTE: This period of conservative life is rounded up to complete

months.

Actual, recorded, life accumulated between Dec.11/06 and Nov.30/09 =

+2100 FC

Total Life = +723 FC + 5589 FC + 2100 FC = 8412 FC

As a result on Nov.30/09, the subject component has a life of 8412 FC.

NOTE: This calculation will remain valid as long as the operator

maintains traceability for this component until the end of the

parts life. If the operator loses an additional part of the

component history, a new calculation will need to be performed

with updated parameters.

It is imperative that the operators continue to maintain an

accurate record of the air intake cowl lives to avoid the need

to repeat the Yearly Fleet Leader calculations in the future.

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Page 8

Sep. 3/10

Sep. 3/10
Year Yearly Fleet

Leader Life

(FC)

1994 333

1995 938

1996 1178

1997 1270

1998 1327

1999 1269

2000 1415

2001 1413

2002 1465

2003 1404

2004 1557

2005 1558

2006 1665

2007 1733

2008 1619

2009 1674

Trent 700 A330 Yearly Fleet Leader

Lives 1995 to 2009

Table 2

D. Accomplishment of this NMSB should be recorded in the engine logbook or in

accordance with the local SB tracking system procedures.

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Sep. 3/10
Inspection Process Flow Chart

Fig.1

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Sep. 3/10
Non-Modification Service Bulletin 71-AG416

1. Record accomplishment of this Non-Modification Service Bulletin in accordance

with local Service Bulletin tracking system procedures.

2. Advise Bombardier Aerospace-Shorts and your local Rolls-Royce FSO of NMSB

accomplishment and inspection results regardless of findings. Refer to

Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015.

APPENDIX 1

Printed in Great Britain

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Appendix 1 - Page 1 of 1

Sep. 3/10

Sep. 3/10