[Federal Register Volume 76, Number 206 (Tuesday, October 25, 2011)]
[Rules and Regulations]
[Pages 65941-65944]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-27513]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0993; Directorate Identifier 2010-NE-08-AD;
Amendment 39-16849; AD 2011-22-07]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211-524 Series,
RB211-Trent 700 Series, and RB211-Trent 800 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) issued by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
Cracking has been found on the inner wall between intermediate
dilution chutes on a total of five front combustion liners of the
standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72-
D133. The lives of two of these liners were confirmed to be below
the currently valid borescope inspection interval. Ultimately, crack
propagation could result in hot gas breakout with potential of
downstream component distress and multiple turbine blade release
beyond containment capabilities of the engine casings. Thus,
cracking of this nature constitutes a potentially unsafe condition.
Since Rolls-Royce Service Bulletin No. 72-E902 introduces
further developments of Rolls-Royce RB211 Service Bulletin No. 72-
D133, engines incorporating Rolls-Royce RB211 Service Bulletin No.
72-E902 are also considered to be potentially affected and are
therefore included in the applicability of this AD.
We are issuing this AD to detect cracks in the front combustion liner,
which could result in hot section distress, multiple blade release, and
possible damage to the airplane.
DATES: This AD becomes effective November 29, 2011. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in this AD as of November 29, 2011.
ADDRESSES: The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: Alan Strom, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; phone: 781-238-7143; fax: 781-238-7199.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on October 5, 2010 (75
FR 61363). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states that:
Cracking has been found on the inner wall between intermediate
dilution chutes on a total of five front combustion liners of the
standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72-
D133. The lives of two of these liners were confirmed to be below
the currently valid borescope inspection interval. Ultimately, crack
propagation could result in hot gas breakout with potential of
downstream component distress and multiple turbine blade release
beyond containment capabilities of the engine casings. Thus,
cracking of this nature constitutes a potentially unsafe condition.
Since Rolls-Royce Service Bulletin No. 72-E902 introduces
further developments of Rolls-Royce RB211 Service Bulletin No. 72-
D133, engines incorporating Rolls-Royce RB211 Service Bulletin No.
72-E902 are also considered to be potentially affected and are
therefore included in the applicability of this AD.
This AD requires a change to the initial and repeat borescope
inspection intervals for the front combustion liner.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Request To Expand Address for Service Information
One commenter, Rolls-Royce plc (RR), asked us to consider changing
the information for getting the service information to ``For any
questions concerning the technical content of the requirements in this
AD (NPRM), please contact your designated Rolls-Royce representative
for a copy of the service information, please download the publication
from your Aeromanager account at http://www.aeromanager.com. If you do
not have a designated representative or an Aeromanager account, please
contact Corporate Communications at Rolls-Royce plc, PO Box 31, Derby,
DE24 8BJ, United Kingdom, phone: 011-44-1331-242424, fax: 011-44-1332-
249936, or e-mail: http://www.rolls-royce.com/contact/civil_team.jsp
identifying the correspondence as being related to Airworthiness
Directives.'' RR states that this should make sure that any questions
from operators of their engines and those from other parties are
directed to the area best equipped to answer.
We partially agree. We agree that operators and maintenance
providers need to get timely and accurate service information, and that
additional information is worth including. We changed paragraph (k) of
the AD to state ``* * * contact Corporate Communications at Rolls-Royce
plc PO Box 31, Derby, DE24 8BJ, United Kingdom, Phone: 011-44-1331-
242424, fax 011-44-1332-249936 or e-mail from http://www.rolls-royce.com/contact/civil_team.jsp identifying the correspondence as
being related to Airworthiness Directives.''
We do not agree that operators or maintenance providers should
contact RR for questions about this AD. We did not include that
information in the AD.
Requests To Change References to the Service Bulletin That Is
Incorporated by Reference
Two commenters, American Airlines (AA) and The Boeing Company
(Boeing), asked us to add ``or later
[[Page 65942]]
revision'' after ``Service Bulletin No. RB.211-72-AF458, Revision 2,
dated December 21, 2007.'' Boeing stated the latest revision of Service
Bulletin (SB) No. RB.211-72-AF458 is Revision 4. Boeing stated that
airlines have been inspecting their combustion liners to Revision 4 of
the SB and the compliance intervals specified in the NPRM are
consistent with RR SB RB.211-72-AF458, Revision 4 and EASA AD 2009-
0243R1. AA stated the borescope inspection is the same on later
revisions, so the life should be counted from the latest SB revision.
We do not agree. On review of the SB, we determined that the
inspection requirements and limits called out in the SB are already in
the engine and aircraft maintenance manuals. We changed the AD to
remove the incorporation by reference of the SB.
One commenter, AA, asked us to revise paragraph (f) of the AD to
specifically call out which paragraphs of SB RB.211-72-AF458 are
incorporated by reference. AA stated the NPRM called out all of section
3 of the SB, which is too prescriptive given the nature of the
inspections.
We do not agree. On review of the SB, we found incorporation by
reference unnecessary. We changed the AD to remove the incorporation by
reference of the SB.
Request To Remove an Engine Model From the Applicability
One commenter, AA, asked us to remove the RR RB211-535 engine model
from the applicability of the proposed AD. AA stated they have recorded
no crack findings against the RB211-535 model.
We agree. The thermal, acoustical, and vibratory stress environment
of the RB211-535 combustion liner is different from that of the other
engines to which this AD applies. We removed the RB211-535E4-37, RB211-
535E4-B-37, RB211-535E4-C-37, and RB211-535E4-B-75 from the
Applicability paragraph (c) of this AD, and updated our cost estimate
to reflect the fewer affected engines.
Request To Change the Number of Cracking Events
One commenter, Boeing, asked us to change paragraph (d) of the
proposed AD to specify that six cracking events have been found instead
of five. Boeing states that changing paragraph (d) of the proposed AD
will more accurately reflect the need for the inspections.
We agree. Although an additional cracking event has occurred, the
AD was prompted by the investigation of five events. We changed
paragraph (d) of this AD to reflect six known cracking events.
Request To Add a Grace Period for Compliance
One commenter, Boeing asked us to change paragraphs (f)(1)(i) and
(f)(1)(iii) of the proposed AD to add ``within 15 cycles of the date of
issue of the AD'' before the word ``or.'' Boeing states that adding the
15 cycle grace period will give operators time to get back to base for
the inspection.
We partially agree. No additional grace period is required. This AD
does not require inspecting any engine earlier than 250 cycles after
the effective date of the AD. We clarified the wording of paragraph (f)
to make this clearer.
Statement of the Possibility of Cost and Operational Impact Increasing
One commenter, Federal Express, stated that cost and operational
impact could increase if certain RB211-535 models are added to the
applicability of the proposed AD. The commenter provided no reason for
its statement.
We agree. However, additional engine models are not being added,
and we are specifically excluding the RB211-535 engine in response to
another comment. We did not change the AD in response to this comment.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Costs of Compliance
Based on the service information, we estimate that this AD will
affect about 46 products of U.S. registry. We also estimate that it
will take about 1.5 work-hours per product to comply with this AD. The
average labor rate is $85 per work-hour. No parts are required so parts
will cost $0 per product. Based on these figures, we estimate the cost
of the AD on U.S. operators to be $5,865.
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 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 this AD:
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),
3. Will not affect intrastate aviation in Alaska, and
4. 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 regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (phone: (800) 647-5527) is provided in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
[[Page 65943]]
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]
2. The FAA amends Sec. 39.13 by adding the following new AD:
2011-22-07 Rolls-Royce: Amendment 39-16849. Docket No. FAA-2010-
0993; Directorate Identifier 2010-NE-08-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
29, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce (RR) turbofan engine models
RB211-524G2-T-19, RB211-524G3-T-19, RB211-524H2-T-19, RB211-524H-T-
36, RB211-Trent 768-60, RB211-Trent 772-60, RB211-Trent 772B-60,
RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-
Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17 and RB211-
Trent 895-17 that incorporate RR Service Bulletin (SB) RB.211-72-
D133 or RB.211-72-E902. These engines are installed on, but not
limited to, Airbus A330 series airplanes; Boeing 747-400 series, 767
series, and 777 series airplanes.
Reason
(d) This AD results from:
Cracking has been found on the inner wall between intermediate
dilution chutes on a total of five front combustion liners of the
standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72-
D133. The lives of two of these liners were confirmed to be below
the currently valid borescope inspection interval. Ultimately, crack
propagation could result in hot gas breakout with potential of
downstream component distress and multiple turbine blade release
beyond containment capabilities of the engine casings. Thus,
cracking of this nature constitutes a potentially unsafe condition.
Since Rolls-Royce Service Bulletin No. 72-E902 introduces
further developments of Rolls-Royce RB211 Service Bulletin No. 72-
D133, engines incorporating Rolls-Royce RB211 Service Bulletin No.
72-E902 are also considered to be potentially affected and are
therefore included in the applicability of this AD.
Since EASA issued its AD, another cracking event has occurred,
bringing to six the total of crack events of which we are aware. We
are issuing this AD to detect cracks in the front combustion liner,
which could result in hot section distress, multiple blade release,
and possible damage to the airplane.
Actions and Compliance
(e) Unless already done, do the following actions.
Initial Inspection
(f) Perform a borescope inspection of the front combustion liner
inner wall, before accumulating the cyclic limits specified in
paragraphs (f)(2) and (f)(3) of this AD.
(1) If you incorporated paragraph 3.A.(2)(a) of RR Alert Service
Bulletin (ASB) RB.211-72-AF458, Revision 4, dated March 9, 2009, or
ASB RB.211-72-AF458, Revision 5, dated April 20, 2011, you have
satisfied the requirements of paragraph (f) of this AD.
(2) If the engine has a combustion liner installed with:
(i) A LIFE on the effective date of this AD, that is equal to or
greater than the initial inspection threshold specified in column
(b) of Table 1 of this AD or a LIFE on the effective date of this
AD, that is not known, within 250 cycles after the effective date of
this AD, perform a borescope inspection as specified in paragraph
(f) of this AD.
(ii) A LIFE on the effective date of this AD, that is less than
the initial inspection threshold specified in column (b) of Table 1
of this AD, perform the borescope inspection before the LIFE exceeds
the limit specified in column (c) of Table 1 of this AD.
Repeat Inspection
(3) Thereafter, repeat the borescope inspection specified in
paragraph (f) of this AD at intervals not to exceed the cycles
specified in column (d) of Table 1 of this AD.
Table 1--Initial Inspection Thresholds and Limits
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Column (a) Column (b) Column (c) Column (d)
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Initial inspection
Initial limit if LIFE is less Repeat inspection
Engine model inspectionthreshold than the initial interval
inspection threshold
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(i) RB211-524G2-T-19, 524G3-T-19 and 1,150 cycles.............. 1,400 cycles.......... 1,400 cycles.
524H2-T-19.
(ii) RB211-524H-T-36................ 550 cycles................ 800 cycles............ 800 cycles.
(iii) RB211-Trent 768-60, 772-60 and 1,250 cycles.............. 1,500 cycles.......... 1,500 cycles.
772B-60.
(iv) RB211-Trent 892-17, RB211-Trent 750 cycles................ 1,000 cycles.......... 1,000 cycles.
884-17, RB211-Trent 884B-17, RB211-
Trent 877-17, RB211-Trent 875-17,
RB211-Trent 892B-17 and RB211-Trent
895-17 engines.
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Definitions
(g) This AD defines LIFE as the lowest of:
(1) The number of cycles-since-new of the combustion liner, or
(2) The number of cycles-in-service (CIS) since replacement of
the inner wall, or
(3) The number of CIS since the inner wall of the combustion
liner was last borescope-inspected, or inspected by performing
paragraph 3.A.(2)(a) of RR ASB RB.211-72-AF458, Revision 4, dated
March 9, 2009 or ASB RB.211-72-AF458, Revision 5, dated April 20,
2011.
FAA AD Differences
(h) This AD differs from the Mandatory Continuing Airworthiness
Information (MCAI) in that the MCAI AD applies to the RB211-Trent
772C-60 engine, which is not type certificated in the United States.
The MCAI also allows use of later revisions of the SBs. This AD does
not.
Other FAA AD Provisions
(i) Alternative Methods of Compliance (AMOCs): The Manager,
Engine Certification Office, FAA, has the authority to approve AMOCs
for this AD if requested using the procedures found in 14 CFR 39.19.
Related Information
(j) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2009-0243R2, Corrected, dated February 22, 2011, for
related information.
(k) Rolls-Royce ASB RB.211-72-AF458, Revision 4, dated March 9,
2009, or ASB RB.211-72-AF458, Revision 5, dated April 20, 2011,
provide information on how to do the actions required by this AD.
For service information identified in this AD, contact Corporate
Communications at Rolls-Royce plc, PO Box 31, Derby, DE24 8BJ,
United Kingdom, phone: 011-44-1331-242424, fax: 011-44-1332-249936,
or e-mail: http://www.rolls-royce.com/contact/civil_team.jsp
identifying the correspondence as related to airworthiness
directives.
(l) Contact Alan Strom, Aerospace Engineer, Engine Certification
Office, FAA, Engine & Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail: [email protected];
phone: 781-238-7143; fax: 781-238-7199, for more information about
this AD.
Material Incorporated by Reference
(m) None.
[[Page 65944]]
Issued in Burlington, Massachusetts, on October 18, 2011.
Peter A. White,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2011-27513 Filed 10-24-11; 8:45 am]
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