Airworthiness Directives; Rolls-Royce plc RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 Turbofan Engines

[Federal Register Volume 71, Number 21 (Wednesday, February 1, 2006)]
[Rules and Regulations]
[Pages 5162-5165]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-826]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23031; Directorate Identifier 2005-NE-41-AD; 
Amendment 39-14467; AD 2006-03-03]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 553-61, 
553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Rolls-Royce plc (RR) RB211 Trent 553-61, 553A2-61, 556-61, 
556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 turbofan engines. 
This AD requires initial and repetitive borescope inspections for 
missing HPT rear seal plate locking plugs and damaged locking plug 
retaining wires, and removal of the engine from service if necessary, 
based on inspection results. This AD results from two reports of 
missing HPT rear seal plate locking plugs, damage to the HPT disc, and 
damage to the remaining locking plug retaining wires. We are issuing 
this AD to prevent uncontained release of the HPT rear side plate and 
HPT disc, resulting in damage to the airplane.

DATES: Effective February 16, 2006. The Director of the Federal 
Register approved the incorporation by reference of certain 
publications listed in the regulations as of February 16, 2006.
    We must receive any comments on this AD by April 3, 2006.

ADDRESSES: Use one of the following addresses to comment on this AD:
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
    <bullet> Fax: (202) 493-2251.
    <bullet> Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Rolls-Royce plc, P.O. Box 31, Derby, DE248BJ; UK, 
telephone: 011-44-1332-242424; fax: 011-44-1332-249936, for the service 
information identified in this AD.

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

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is 
the

[[Page 5163]]

airworthiness authority for the United Kingdom (U.K.), notified us that 
an unsafe condition may exist on RR RB211 Trent 500 series turbofan 
engines that have not incorporated RR Service Bulletin (SB) No. RB.211-
72-E767. The CAA advises that during shop visit, some engines were 
noticed to be missing some of the HPT turbine rear seal plate locking 
plugs. This resulted in scoring of the HPT disc rear diaphragm and 
impact damage to the remaining locking plug retaining wires, and could 
have led to release of the HPT rear seal plate and reduced low-cycle-
fatigue life of the HPT disc.

Relevant Service Information

    We have reviewed and approved the technical contents of RR Alert SB 
No. RB.211-72-AE358, Revision 3, dated July 13, 2005, that describes 
procedures for borescope inspecting the HPT rear seal plate locking 
plugs and locking plug retaining wires. The CAA classified this as a 
mandatory SB and issued AD G-2005-0007 R1, dated July 11, 2005, in 
order to ensure the airworthiness of these RB211 Trent 500 series 
turbofan engines in the U.K.

Bilateral Airworthiness Agreement

    These RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 
556B2-61, 560-61, and 560A2-61 series turbofan engines are manufactured 
in the U.K. and are type certificated for operation in the United 
States under the provisions of section 21.29 of the Federal Aviation 
Regulations (14 CFR 21.29) and the applicable bilateral airworthiness 
agreement. Under this bilateral airworthiness agreement, the CAA kept 
the FAA informed of the situation described above. We have examined the 
findings of the CAA, reviewed all available information, and determined 
that AD action is necessary 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 the engines could be used on 
airplanes that are registered in the United States in the future. The 
unsafe condition described previously is likely to exist or develop on 
other RR RB211 Trent 500 series turbofan engines of the same type 
design. We are issuing this AD to prevent uncontained release of the 
HPT rear side plate and HPT disc, resulting in damage to the airplane. 
This AD requires initial and repetitive borescope inspections for 
missing HPT rear seal plate locking plugs and damaged locking plug 
retaining wires. This AD also requires removing engines from service 
based on the number of HPT locking plugs with acceptable locking plug 
retaining wires installed. 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. 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 send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2005-23031; 
Directorate Identifier 2005-NE-41-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of the DMS Web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78) or you may visit 
http://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located on the plaza level of the Department of 
Transportation Nassif Building at the street address stated in 
ADDRESSES. Comments will be available in the AD docket shortly after 
the DMS receives them.

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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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:

[[Page 5164]]

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 adding the following new airworthiness 
directive:

2006-03-03 Rolls-Royce plc: Amendment 39-14467. Docket No. FAA-2005-
23031; Directorate Identifier 2005-NE-41-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
16, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 553-61, 
553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 
turbofan engines that have not incorporated RR Service Bulletin (SB) 
No. RB.211-72-E767. These engines are installed on, but not limited 
to, Airbus A340-500 and -600 series airplanes.

Unsafe Condition

    (d) This AD results from two reports of missing HPT rear seal 
plate locking plugs, damage to the HPT disc, and damage to the 
remaining locking plug retaining wires. We are issuing this AD to 
prevent uncontained release of the HPT rear side plate and HPT disc, 
resulting in damage to the airplane.

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.

Initial Borescope Inspection

    (f) Borescope-inspect for missing HPT rear seal plate locking 
plugs and damaged locking plug retaining wires, between 500 and 
1,000 cycles-since-new (CSN) or cycles-since-overhaul where the 
locking plug wires were replaced, or within 50 cycles after the 
effective date of this AD, whichever occurs later.
    (g) Use paragraphs 3.B.(1)(a) through 3.B.(1)(k)(xi) of the 
Accomplishment Instructions of RR Alert Service Bulletin No. RB.211-
72-AE358, Revision 3, dated July 13, 2005, to do the inspection.

Repetitive Borescope Inspections

    (h) Using the criteria and intervals in the following Table 1, 
repeat the borescope inspection and remove engines from service to 
inspect the HPT disc.

                    Table 1.--Engine Removal Criteria
------------------------------------------------------------------------
  If the number of HPT locking
  plugs with acceptable locking     Then repeat the    Remove the engine
 plug retaining wires installed,       borescope        from service to
 determined in paragraph (f) of   inspection within:   inspect HPT disc:
           this AD is:
------------------------------------------------------------------------
(1) Zero or one.................  Not applicable....  Before further
                                                       flight.
(2) Two.........................  Not applicable....  Within 15 CSLI.
(3) Three or four...............  100 cycles-since-   Before
                                   last-inspection     accumulating
                                   (CSLI) intervals.   1,100 cycles-
                                                       since-loss of
                                                       locking plug(s)
                                                       or 1,100 CSN, or
                                                       1,100 cycles-
                                                       since-last
                                                       acceptable
                                                       inspection,
                                                       whichever occurs
                                                       later.
(4) Five........................  1,000 CSLI          Not applicable.
                                   intervals.
------------------------------------------------------------------------

    (i) Use paragraphs 3.B.(1)(a) through 3.B.(1)(k)(xi) of the 
Accomplishment Instructions of RR Alert Service Bulletin No. RB.211-
72-AE358, Revision 3, dated July 13, 2005, to do the inspection.
    (j) For Table 1, item (3), if possible, determine when the loss 
of locking plug(s) occurred by reviewing the engine vibration 
history. If it is not possible to determine the point of locking 
plug release, use 1,100 CSN, or 1,100 cycles-since-last acceptable 
inspection, whichever occurs later.

Alternative Methods of Compliance

    (k) 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.

Related Information

    (l) United Kingdom Civil Aviation Authority airworthiness 
directive G-2005-0007 R1, dated July 11, 2005, also addresses the 
subject of this AD.

Material Incorporated by Reference

    (m) You must use the Rolls-Royce plc Alert Service Bulletin and 
Appendices listed in Table 2 of this AD to perform the inspections 
required by this AD. The Director of the Federal Register approved 
the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Rolls-
Royce plc, P.O. Box 31, Derby, DE248BJ; UK, telephone: 011-44-1332-
242424; fax: 011-44-1332-249936, for a copy of this service 
information. You may review copies at the Docket Management 
Facility; U.S. Department of Transportation, 400 Seventh Street, 
SW., Nassif Building, Room PL-401, Washington, DC 20590-0001, on the 
Internet at http://dms.dot.gov; 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/cfr/ibr-locations.html.

                                      Table 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
        Alert Service Bulletin No.                   Page              Revision                Date
----------------------------------------------------------------------------------------------------------------
RB.211-72-AE358..........................  ALL.....................            3  July 13, 2005.
  Total Pages: 16
Appendix 1 to ASB No. RB.211-72-AE358....  ALL.....................            3  July 13, 2005.
  Total Pages: 2
Appendix 2 to ASB No. RB.211-72-AE358....  ALL.....................            3  July 13, 2005.
  Total Pages: 2
----------------------------------------------------------------------------------------------------------------



[[Page 5165]]

    Issued in Burlington, Massachusetts, on January 24, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 06-826 Filed 1-31-06; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T03:48:55.569043+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

172d1c28d385975e52995887e4f65bed7d192ebffa3d1d313b06ebfebe79a865

Text SHA-256

bfafac28ef3a8724854ac267f97e354242542ec82da083dc412a82b4b47eb342