[Federal Register Volume 78, Number 55 (Thursday, March 21, 2013)]
[Proposed Rules]
[Pages 17300-17303]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-06498]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28059; Directorate Identifier 2007-NE-13-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede an existing airworthiness directive
(AD) for all Rolls-Royce plc (RR) RB211-Trent 553-61, 553A2-61, 556-61,
556A2-61, 556B-61, 556B2-61, 560-61, 560A2-61, 768-60, 772-60, 772B-60,
875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 turbofan
engines. The existing AD currently requires inspection of the
intermediate-pressure (IP) compressor rotor shaft rear balance land for
cracks. Since we issued that AD, a crack was detected in a Trent 500 IP
compressor rotor shaft rear balance land during a shop visit, and
further engineering evaluation done by RR concluded that the cracking
may also exist in Trent 900 engines. This proposed AD would require
inspections of the IP compressor rotor shaft as required by the
existing AD while adding on-wing inspections for the Trent 500 engines,
and on-wing and in-shop inspections for the Trent 900 engines. We are
proposing this AD to detect cracking on the IP compressor rotor shaft
rear balance land, which could lead to uncontained engine failure and
damage to the airplane.
DATES: We must receive comments on this proposed AD by May 20, 2013.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Rolls-Royce
plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ;
phone: 011 44 1332 242424; fax: 011 44 1332 245418; email: http://www.rolls-royce.com/contacts/civil_team.jsp. You may view this service
information at the FAA, Engine & Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For information on the availability of
this material at the FAA, call 781-238-7125.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Frederick Zink, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone: 781-238-7779;
fax: 781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
28059; Directorate Identifier 2007-NE-13-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy
[[Page 17301]]
aspects of this proposed AD. We will consider all comments received by
the closing date and may amend this proposed AD because of those
comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On May 15, 2012, we issued AD 2012-10-12, Amendment 39-17061 (77 FR
31176, May 25, 2012), for all RR RB211-Trent 553-61, 553A2-61, 556-61,
556A2-61, 556B-61, 556B2-61, 560-61, 560A2-61, 768-60, 772-60, 772B-60,
875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 turbofan
engines. That AD requires continuing initial inspections, adding
additional inspections, and a mandatory terminating action. That AD
resulted from reports of additional cracking on RB211-Trent 700 and
RB211-Trent 800 IP compressor rotor shafts. We issued that AD to detect
cracking on the IP compressor rotor shaft rear balance land, which
could lead to uncontained engine failure and damage to the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2012-10-12, Amendment 39-17061 (77 FR 31176, May
25, 2012), a crack in a Trent 500 IP compressor rotor shaft rear
balance land was detected during a shop visit. Further engineering
evaluation, done by RR, concluded that the cracking may also exist in
Trent 900 engines.
Relevant Service Information
We reviewed RR Non-Modification Alert Service Bulletin (NMASB) No.
RB.211-72-AH058, dated December 13, 2012, and RR NMASB No. RB.211-72-
AH059, dated December 11, 2012. NMASB No. RB.211-72-AH058 describes
procedures for inspection of RB211-Trent 553-61, 553A2-61, 556-61,
556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 engines. NMASB No.
RB.211-72-AH059 describes procedures for inspection of RB211-Trent 970-
84, 970B-84, 972-84, 972B-84, 977-84, 977B-84, and 980-84 engines.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would retain all the requirements of AD 2012-10-
12, Amendment 39-17061 (77 FR 31176, May 25, 2012). This proposed AD
would add requirements to perform on-wing inspections for the Trent 500
and on-wing and in-shop inspections for the Trent 900 engines.
Costs of Compliance
We estimate that this proposed AD would affect about 136 engines
installed on airplanes of U.S. registry. We also estimate that it would
take about 14 hours per engine to perform required inspections. The
average labor rate is $85 per hour. Replacement parts are estimated to
cost about $2,271 per engine. Based on these figures, we estimate the
cost of the proposed AD on U.S. operators to be $470,696.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
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),
(3) Will not affect intrastate aviation in Alaska, to the extent
that it justifies making a regulatory distinction, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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 airworthiness directive (AD)
2012-10-12, Amendment 39-17061 (77 FR 31176, May 25, 2012), and adding
the following new AD:
Rolls-Royce plc: Docket No. FAA-2007-28059; Directorate Identifier
2007-NE-13-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by May 20, 2013.
(b) Affected ADs
This AD supersedes AD 2012-10-12, Amendment 39-17061 (77 FR
31176, May 25, 2012).
(c) Applicability
This AD applies to Rolls-Royce plc (RR) RB211-Trent 553-61,
553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, 560A2-61,
768-60, 772-60, 772B-60, 875-17, 877-17, 884-17, 884B-17, 892-17,
892B-17, 895-17, 970-84, 970B-84, 972-84, 972B-84, 977-84, 977B-84,
and 980-84 turbofan engines.
(d) Unsafe Condition
This AD was prompted by detection of a crack in a Trent 500
intermediate-pressure (IP) compressor rotor shaft rear balance land
with follow-on RR engineering evaluation concluding that cracking
may also exist in Trent 900 engines. We are issuing this AD to
detect cracking on the IP compressor rotor shaft rear balance land,
which could lead to uncontained engine failure and damage to the
airplane.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 17302]]
(f) RB211-Trent 700 Series Engines--Rear Balance Land Inspections
(1) Within 625 cycles-in-service (CIS) after June 29, 2012, or
before the next flight after the effective date of this AD,
whichever occurs later, borescope inspect the IP compressor rotor
shaft rear balance land. Use RB211 Trent 700 Series Propulsion
System Non-Modification Alert Service Bulletin (NMASB) No. RB.211-
72-AG270, Revision 4, dated March 21, 2011, sections 3.A.(2)(a)
through 3.A.(2)(c) and 3.A.(3)(a) through 3.A.(3)(c) for in-shop
procedures, or 3.B.(2)(a) through 3.B.(2)(c) and 3.B.(4)(a) through
3.B.(4)(c) for on-wing procedures, to do the inspection.
(2) Thereafter, repeat the inspection within every 625 cycles-
since-last inspection (CSLI). You may count CSLI from the last
borescope inspection or the last eddy current inspection (ECI),
whichever occurred last.
(3) At each shop visit after the effective date of this AD,
perform an ECI and visually inspect the IP compressor rotor shaft
rear balance land, and visually inspect the balance weights. Use
RB211 Trent 700 and Trent 800 Series Propulsion Systems NMASB No.
RB.211-72-AG085, Revision 2, dated July 7, 2011, sections 3.A.
through 3.C., to do the inspections.
(g) RB211-Trent 800 Series Engines--Rear Balance Land Inspections
(1) Within 475 CIS after June 29, 2012, or before the next
flight after the effective date of this AD, whichever occurs later,
borescope inspect the IP compressor rotor shaft rear balance land.
Use RB211 Trent 800 Series Propulsion System NMASB No. RB.211-72-
AG264, Revision 5, dated March 21, 2011, sections 3.A.(2)(b) through
3.A.(2)(c) and 3.A.(3)(a) through 3.A.(3)(c) for in-shop procedures,
or 3.B.(2)(a) through 3.B.(2)(c) and 3.B.(4)(a) through 3.B.(4)(c)
for on-wing procedures, to do the inspection.
(2) Thereafter, repeat the inspection within every 475 CSLI. You
may count CSLI from the last borescope inspection or the last ECI,
whichever occurred last.
(3) At each shop visit, perform an ECI and visually inspect the
IP compressor rotor shaft rear balance land, and visually inspect
the balance weights. Use RB211 Trent 700 and Trent 800 Series
Propulsion Systems NMASB No. RB.211-72-AG085, Revision 2, dated July
7, 2011, sections 3.A. through 3.C., to do the inspections.
(h) RB211-Trent 500 Series Engines--Rear Balance Land Inspections
(1) Within 340 CIS after the effective date of this AD,
borescope inspect the IP compressor rotor shaft rear balance land.
Use RB211 Trent 500 Series Propulsion Systems NMASB No. RB.211-72-
AH058, dated December 13, 2012, sections 3.A.(2)(a) through
3.A.(2)(c), 3.A.(3)(a) through 3.A.(3)(d), and 3.A.(5)(a) through
3.A.(5)(c) for on-wing procedures, to do the inspection.
(2) Thereafter, repeat the inspection within every 340 CSLI. You
may count CSLI from the last borescope inspection or the last ECI,
whichever occurred last.
(3) At each shop visit, perform an ECI and visually inspect the
IP compressor rotor shaft rear balance land, and visually inspect
the balance weights. Use RB211 Trent 500 and Trent 900 Series
Propulsion Systems Non-Modification Service Bulletin (NMSB) No.
RB.211-72-G448, Revision 3, dated July 7, 2011, sections 3.D.(4)
through 3.D.(5), 3.D.(6)(f) through 3.D.(7)(w), 3.D.(8)(f) through
3.D.(8)(w), 3.D.(11), and 3.D.(12), to do the inspections.
(i) RB211-Trent 900 Series Engines--Rear Balance Land Inspections
(1) Within 280 flight cycles after the effective date of this
AD, borescope inspect the IP compressor rotor shaft rear balance
land. Use RB211 Trent 900 Series Propulsion Systems NMASB No.
RB.211-72-AH059, dated December 11, 2012, sections 3.A.(2)(a)
through 3.A.(2)(c), 3.A.(3)(a) through 3.A.(3)(d), and 3.A.(5)(a)
through 3.A.(5)(c), to do the inspection.
(2) Thereafter, repeat the inspection within every 280 CSLI. You
may count from the last borescope inspection or the last ECI,
whichever occurred last.
(3) At each shop visit after the effective date of this AD,
perform an ECI and visually inspect the IP compressor rotor shaft
rear balance land, and visually inspect the balance weights. Use
RB211 Trent 500 and Trent 900 Series Propulsion Systems NMSB No.
RB.211-72-G448, Revision 3, dated July 7, 2011, sections 3.D.(4)
through 3.D.(5), 3.D.(6)(f) through 3.D.(7)(w), 3.D.(8)(f) through
3.D.(8)(w), 3.D.(11), and 3.D.(12), to do the inspection.
(j) Mandatory Termination Action for RB211-Trent 700 and RB211-Trent
800 Engines
(1) For RB211-Trent 700 engines. At the next shop visit in which
any level of inspection or strip is scheduled to be carried out on
the IP compressor, remove the existing IP compressor balance
weights.
(2) For RB211-Trent 800 engines. At the next shop visit in which
any level of inspection or strip is scheduled to be carried out on
the IP compressor, remove the existing IP compressor balance
weights.
(3) Once you have removed the balance weights, do not re-install
them on any IP compressor shaft rear balance land.
(k) Credit for Previous Actions
(1) For RB211-Trent 700 series engines:
(i) If you borescope inspected your RB211-Trent 700 series
engine using RB211 Trent 700 Series Propulsion System NMASB No.
RB.211-72-AG270, Revision 1, dated December 14, 2009, or Revision 2,
dated December 21, 2010, or Revision 3, dated February 25, 2011,
before the effective date of this AD, you have satisfied the
requirements of paragraph (f)(1) of this AD.
(ii) If you performed the ECI and visual inspection of your
RB211-Trent 700 series engines using RB211 Trent 700 and Trent 800
Series Propulsion Systems NMASB No. RB.211-72-AG085, Revision 1,
dated September 27, 2010, before the effective date of this AD, you
have satisfied the ECI and visual inspections required by paragraph
(f)(3) of this AD.
(2) For RB211-Trent 800 series engines:
(i) If you borescope inspected your RB211-Trent 800 series
engine using RB211 Trent 800 Series Propulsion System NMASB No.
RB.211-72-AG264, Revision 3, dated December 21, 2010, or Revision 4,
dated February 25, 2011, before the effective date of this AD, you
have satisfied the requirements of paragraph (g)(1) of this AD.
(ii) If you performed the ECI and in-shop visual inspection of
your RB211-Trent 800 series engines using RB211 Trent 700 and Trent
800 Series Propulsion Systems NMASB No. RB.211-72-AG085, Revision 1,
dated September 27, 2010, before the effective date of this AD, you
have satisfied the ECI and visual inspections required by paragraph
(g)(3) of this AD.
(3) For RB211-Trent 500 and 900 series engines:
(i) If you performed the ECI of your RB211-Trent 500 series
engines using RB211 Trent 500, 700 and 800 Series Propulsion Systems
NMASB No. RB.211-72-AF260, Revision 4, dated July 28, 2009, and
RB211 Trent 500 and Trent 900 Series Propulsion Systems NMSB No.
RB.211-72-G448, Revision 2, dated December 23, 2010 before the
effective date of this AD, you have satisfied the ECIs required by
paragraph (h)(3) of this AD.
(ii) If you performed the in-shop visual inspection of your
RB211-Trent 500 series engines using RB211 Trent 500 and Trent 900
Series Propulsion Systems NMSB No. RB.211-72-G448, Revision 2, dated
December 23, 2010, before the effective date of this AD, you have
satisfied the in-shop visual inspections required by paragraph
(h)(3) of this AD.
(l) Definitions
For the purpose of this AD, a shop visit is defined as
introduction of an engine into a shop and disassembly sufficient to
expose the IP compressor module rear face.
(m) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures in 14 CFR 39.19 to make your
request.
(n) Related Information
(1) For more information about this AD, contact Frederick Zink,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803; phone: 781-238-7779; fax: 781-238-7199; email:
[email protected].
(2) European Aviation Safety Agency AD 2013-0002, dated January
4, 2013 also pertains to the subject of this AD.
(3) For service information identified in this AD, contact
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby,
England, DE248BJ; phone: 011-44-1332-242424; fax: 011-44-1332-
245418; Internet: http://www.rolls-royce.com/contact/civil_team.jsp.
(4) You may view the referenced service information at the FAA,
Engine & Propeller Directorate, 12 New England Executive Park,
Burlington, MA 01803. For information on the availability of this
material at the FAA, call 781-238-7125.
[[Page 17303]]
Issued in Burlington, Massachusetts, on March 13, 2013.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2013-06498 Filed 3-20-13; 8:45 am]
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