[Federal Register Volume 70, Number 45 (Wednesday, March 9, 2005)]
[Rules and Regulations]
[Pages 11536-11539]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-4076]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-28-AD; Amendment 39-13994; AD 2005-05-06]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Models RB211 Trent 768-
60, Trent 772-60, and Trent 772B-60 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Rolls-Royce plc (RR) models RB211 Trent 768-60, Trent 772-60, 
and Trent 772-60 turbofan engines. That AD currently requires initial 
and repetitive surge margin testing of engines. This AD requires the 
same actions but at updated intervals. This AD also requires 
installation of updated software for the engine electronic controllers 
(EECs), and adds a terminating action for the surge margin testing 
requirement. This AD supersedure results from RR requiring EEC software 
to be revised, and extending the repetitive interval for surge margin 
testing for engines that have incorporated the software update for the 
EECs. This AD also results from RR introducing a stage 1 high pressure 
(HP) compressor casing and intermediate case outer location ring with 
wear-resistant coating, to reduce wear to prevent reduction in surge 
margin. We are issuing this AD to prevent a possible dual-engine in-
flight surge, which could result in dual engine power loss.

DATES: Effective March 24, 2005. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of March 24, 2005.
    We must receive any comments on this AD by May 9, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     By mail: Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 2003-NE-28-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
     By fax: (781) 238-7055.
     By e-mail: [email protected].
    You can get the service information referenced in this AD from 
Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011-44-
1332-242424; fax; 011-44-1332-245-418.
    You may examine the AD docket, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7175; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On July 24, 2003, the FAA issued AD 2003-15-
09, Amendment 39-13252 (68 FR 46444, August 6, 2003). That AD requires 
initial and repetitive surge margin testing of RR models RB211 Trent 
768-60, Trent 772-60, and Trent 772B-60 turbofan engines. That AD 
resulted from several reports of low power surges. That condition, if 
not corrected, could result in a possible dual-engine in-flight surge, 
which could result in loss of control of the airplane.

Actions Since AD 2003-15-09 Was Issued

    Since that AD was issued, the Civil Aviation Authority (CAA), which 
is the airworthiness authority for the United Kingdom (U.K.), recently 
notified us of related actions taken by the manufacturer to improve the 
engine surge margin. RR has extended the repetitive interval for surge 
margin testing for engines that have incorporated a certain software 
revision for the EECs. RR has also introduced a stage 1 HP compressor 
casing and intermediate case outer location ring with wear-resistant 
coating. This coating will prevent axial movement of components during 
operation, preventing wear resulting in increased rotor tip clearance 
and reduced surge margin. This AD requires initial and repetitive surge 
margin testing of engines. This AD also requires revised

[[Page 11537]]

software for the EEC to increase the in-flight N3 low idle schedule, 
and to maximize HP compressor surge margin. This AD also requires 
installing a stage 1 HP compressor casing and intermediate case outer 
location ring with wear-resistant coating. Incorporating these 
modifications is a terminating action to the repetitive surge margin 
testing. The actions specified in this AD are intended to prevent a 
possible dual-engine in-flight surge, which could result in dual engine 
power loss.

Relevant Service Information

    We have reviewed and approved the technical contents of RR Alert 
Service Bulletin (ASB) No. RB.211-71-AD509, Revision 3, dated October 
17, 2003, which describes procedures for initial and repetitive surge 
margin testing of engines. We have also reviewed and approved the 
technical contents of RR Service Bulletin (SB) No. RB.211-72-D574, 
Revision 1, dated January 12, 2004. That SB describes procedures for 
installing a stage 1 HP compressor casing and intermediate case outer 
location ring with wear-resistant coating. The CAA classified these 
service bulletins as mandatory and issued AD G-2004-010, dated April 8, 
2004, in order to ensure the airworthiness of these RR models RB211 
Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines in the 
U.K.

Differences Between This AD and the Service Information

    Although RR ASB No. RB.211-71-AD509, Revision 3, dated October 17, 
2003, allows surge margin testing of engines during revenue service, 
this AD only allows surge margin testing during dedicated maintenance 
checks.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the United Kingdom (U.K), and 
is type certificated for operation in the United States under Sec.  
21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. In keeping with this 
bilateral airworthiness agreement, the CAA has kept us informed of the 
situation described above. We have examined the findings of the CAA, 
reviewed all available information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.

FAA's Determination and Requirements of This AD

    Although no airplanes that are registered in the United States use 
these engines, the possibility exists that they could be used on 
airplanes that are registered in the United States in the future. The 
unsafe condition identified previously is likely to exist or develop on 
other RR models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 
turbofan engines of the same type design. We are issuing this AD to 
prevent a possible dual-engine in-flight surge, which could result in 
loss of control of the airplane. This AD requires initial and 
repetitive surge margin testing of engines, and incorporating revised 
software for the EECs. This AD also requires installing a stage 1 HP 
compressor casing and intermediate case outer location ring with wear-
resistant coating, to reduce wear to prevent reduction in surge margin. 
These installations are considered terminating action to the repetitive 
surge margin testing. You must use the service information described 
previously to perform the actions required by this AD.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for public comment before issuing this AD 
are unnecessary. Therefore, a situation exists that allows the 
immediate adoption of this regulation.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-28-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the rule 
that might suggest a need to modify it. If a person contacts us 
verbally, and that contact relates to a substantive part of this AD, we 
will summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend the AD 
in light of those comments.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national Government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2003-NE-28-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 11538]]

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-13252 68 FR 
46444, August 6, 2003, and by adding a new airworthiness directive, 
Amendment 39-13994, to read as follows:

2005-05-06 Rolls-Royce plc: Amendment 39-13994. Docket No. 2003-NE-
28-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
24, 2005.

Affected ADs

    (b) This AD supersedes AD 2003-15-09, Amendment 39-13252.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) models RB211 Trent 
768-60, Trent 772-60, and Trent 772B-60 turbofan engines. These 
engines are installed on, but not limited to, Airbus 330 series 
airplanes.

Unsafe Condition

    (d) This AD results from RR requiring engine electronic 
controller (EEC) software to be revised, and extending the 
repetitive interval for surge margin testing for engines that have 
incorporated the software revision for the EECs. This AD also 
results from RR introducing a stage 1 high pressure (HP) compressor 
casing and intermediate case outer location ring with wear-resistant 
coating, to reduce wear to prevent reduction in surge margin. We are 
issuing this AD to prevent a possible dual-engine in-flight surge, 
which could result in dual engine power loss.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

No Revenue Service Surge Margin Testing Allowed

    (f) Although RR Alert Service Bulletin (ASB) No. RB.211-71-
AD509, Revision 3, dated October 17, 2003, allows surge margin 
testing of engines during revenue service, this AD only allows surge 
margin testing during dedicated maintenance checks.

Initial Surge Margin Testing

    (g) Perform initial surge margin testing using paragraph 3 and 
Method A(1) of the Accomplishment Instructions of RR ASB No. RB.211-
71-AD509, Revision 3, dated October 17, 2003, as follows:
    (1) Before further flight, for engines that have accumulated 
more than 2,000 cycles-since-new (CSN) on the effective date of this 
AD; and for engines that have accumulated more than 1,000 cycles-
since-overhaul (CSO) of the HP compressor casings and blades.
    (2) Before accumulating 2,000 CSN for engines that have not had 
an overhaul of the HP compressor casing and blades.
    (3) Before accumulating 1,000 CSO for engines that have had an 
overhaul of the HP compressor casings and blades.

EEC Software Update

    (h) Within 6 months from the effective date of this AD, install 
an EEC that features revised software to increase the in-flight N3 
low idle schedule. Information on the revised software standard that 
features the increase in the in-flight N3 low idle schedule can be 
found in RR SB No. RB.211-73-AE224.

Repetitive Surge Margin Testing

    (i) For engines that do not have a revised EEC installed, as 
specified in paragraph (h) of this AD, perform repetitive surge 
margin testing at intervals not to exceed 130 cycles-since-last 
surge margin test. Use paragraph 3 and Method A(1) of the 
Accomplishment Instructions of RR ASB No. RB.211-71-AD509, Revision 
3, dated October 17, 2003, for testing.
    (j) For engines that do have a revised EEC installed, as 
specified in paragraph (h) of this AD, perform repetitive surge 
margin testing at intervals not to exceed 160 cycles-since-last 
surge margin test. Use paragraph 3 and Method A(1) of the 
Accomplishment Instructions of RR ASB No. RB.211-71-AD509, Revision 
3, dated October 17, 2003, for testing.

Terminating Action

    (k) Within 4,500 cycles-in-service after the effective date of 
this AD, install a stage 1 HP compressor casing and intermediate 
case outer location ring with wear-resistant coating. Use paragraph 
3.A. of the Accomplishment Instructions of RR Service Bulletin No. 
RB.211-72-D574, Revision 1, dated January 12, 2004, to do this. 
Performing these actions is considered terminating action for the 
repetitive surge margin testing required by this AD.

Alternative Methods of Compliance

    (l) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (m) You must use the Rolls-Royce plc service information 
specified in Table 1 of this AD to perform the testing and 
modifications required by this AD. The Director of the Federal 
Register approved the incorporation by reference of the documents 
listed in Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 
1 CFR part 51. You can get a copy from Rolls-Royce plc, PO Box 31, 
Derby, England, DE248BJ; telephone: 011-44-1332-242424; fax; 011-44-
1332-245-418. You may review copies at the FAA, New England Region, 
Office of the Regional Counsel, Attention: Rules Docket No. 2003-NE-
28-AD, 12 New England Executive Park, Burlington, MA; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
    Table 1 follows:

                                      Table 1.--Incorporation by Reference
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          Service bulletin No.                       Page                Revision                Date
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RB.211-71-AD509.........................  All.......................               3  October 17, 2003.
Total Pages: 6..........................
RB.211-72-D574..........................  All.......................               1  January 12, 2004.
Total Pages: 12.........................
Supplement to RB.211-72-D574............  All.......................               1  January 12, 2004.
Total Pages: 2..........................
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[[Page 11539]]

Related Information

    (n) CAA airworthiness directive G-2004-010, dated April 8, 2004, 
also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on February 25, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 05-4076 Filed 3-8-05; 8:45 am]
BILLING CODE 4910-13-P