Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines, 9502-9504 [E8-3192]
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9502
Federal Register / Vol. 73, No. 35 / Thursday, February 21, 2008 / Proposed Rules
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Empresa Brasileira de Aeronautica S.A.
(EMBRAER): Docket No. FAA–2008–
0194; Directorate Identifier 2007–NM–
263–AD.
Comments Due Date
(a) We must receive comments by March
24, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Embraer Model
EMB–135BJ airplanes, certificated in any
category.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance according
to paragraph (g) of this AD. The request
should include a description of changes to
the required inspections that will ensure the
continued operational safety of the airplane.
Subject
(d) Air Transport Association (ATA) of
America Code 28: Fuel.
ebenthall on PRODPC61 with PROPOSALS
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Fuel system reassessment, performed
according to RBHA–E88/SFAR–88
(Regulamento Brasileiro de Homologacao
Aeronautica 88/Special Federal Aviation
Regulation No. 88), requires the inclusion of
new maintenance tasks in the Critical Design
Configuration Control Limitations (CDCCL)
and in the Fuel System Limitations (FSL),
necessary to preclude ignition sources in the
fuel system. * * *
The corrective action is revising the
Airworthiness Limitations Section (ALS) of
the Instructions for Continued Airworthiness
(ICA) to incorporate new limitations for fuel
tank systems.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) The term ‘‘MPG,’’ as used in this AD,
means the Embraer Legacy BJ Maintenance
Planning Guide (MPG) MPG–1483, Revision
5, dated March 22, 2007.
(2) Before December 16, 2008, revise the
ALS of the ICA to incorporate Section A2.5.2,
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14:38 Feb 20, 2008
Jkt 214001
Fuel System Limitation Items, of Appendix 2
of the MPG. For all tasks identified in Section
A2.5.2 of Appendix 2 of the MPG, the initial
compliance times start from the later of the
times specified in paragraphs (f)(2)(i) and
(f)(2)(ii) of this AD; and the repetitive
inspections must be accomplished thereafter
at the interval specified in Section A2.5.2 of
Appendix 2 of the MPG, except as provided
by paragraphs (f)(4) and (g) of this AD.
(i) The effective date of this AD.
(ii) The date of issuance of the original
Brazilian standard airworthiness certificate
or the date of issuance of the original
Brazilian export certificate of airworthiness.
(3) Before December 16, 2008, or within 90
days after the effective date of this AD,
whichever occurs first, revise the ALS of the
ICA to incorporate items 1, 2, and 3 of
Section A2.4, Critical Design Configuration
Control Limitation (CDCCL), of Appendix 2
of the MPG.
(4) After accomplishing the actions
specified in paragraphs (f)(2) and (f)(3) of this
AD, no alternative inspections, inspection
intervals, or CDCCLs may be used unless the
inspections, intervals, or CDCCLs are part of
a later revision of Appendix 2 of the MPG
that is approved by the Manager, ANM–116,
FAA, or ANAC (or its delegated agent); or
unless the inspections, intervals, or CDCCLs
are approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (g) of this
AD.
FAA AD Differences
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Sanjay Ralhan,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1405; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
Frm 00009
Fmt 4702
Related Information
(h) Refer to MCAI Brazilian Airworthiness
Directive 2007–08–01, effective September
27, 2007; and Sections A2.5.2, Fuel System
Limitation Items, and A2.4, Critical Design
Configuration Control Limitation (CDCCL), of
Appendix 2 of the MPG; for related
information.
Issued in Renton, Washington, on February
13, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–3191 Filed 2–20–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Note 2: This AD differs from the MCAI
and/or service information as follows: The
MCAI specifies a compliance date of ‘‘Before
December 31, 2008’’ for doing the ALI
revisions. We have already issued regulations
that require operators to revise their
maintenance/inspection programs to address
fuel tank safety issues. The compliance date
for these regulations is December 16, 2008.
To provide for coordinated implementation
of these regulations and this AD, we are
using this same compliance date in this AD.
We also included a compliance time of
‘‘within 90 days after the effective date of this
AD’’ in paragraph (f)(3) of this AD, rather
than ‘‘within 180 days after the effective date
of this AD,’’ as specified by the MCAI. We
have coordinated these compliance times
with ANAC.
PO 00000
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Sfmt 4702
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0078; Directorate
Identifier 2007–NE–40–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc RB211 Series Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated 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:
High pressure (HP) turbine discs recently
inspected in accordance with the Engine
Manual have exhibited cracks in the disc rim.
The discs have failed to meet the inspection
acceptance criteria and have been returned to
Rolls-Royce for engineering investigation.
This investigation has concluded that the
cracks have resulted from scores within the
cooling air holes in the disc rim that could
have been introduced during new part
E:\FR\FM\21FEP1.SGM
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Federal Register / Vol. 73, No. 35 / Thursday, February 21, 2008 / Proposed Rules
manufacture or during overhaul of the disc.
The engineering investigation has concluded
that if this cracking was undetected then it
could result in uncontained disc failure and
a potential unsafe condition for the aircraft.
We are proposing this AD to prevent
uncontained disc failure, possibly
resulting in damage to the airplane.
DATES: We must receive comments on
this proposed AD by March 24, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: Docket Management Facility:
U.S. Department of Transportation, 1200
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
ebenthall on PRODPC61 with PROPOSALS
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is the
same as the Mail address provided in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Ian
Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
e-mail: ian.dargin@faa.gov; telephone
(781) 238–7178, fax (781) 238–7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2007–0078; Directorate Identifier 2007–
NE–40–AD’’ in the subject line of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
VerDate Aug<31>2005
14:38 Feb 20, 2008
Jkt 214001
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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD 2006–0180,
dated June 26, 2006, for RB211–524
series engines, AD 2006–0181, dated
June 26, 2006, for RB211–22B engines,
and AD 2006–0182, dated June 28, 2006,
for RB211–535 series engines, to correct
the same unsafe condition for the
specified products. The EASA ADs
state:
HPT discs recently inspected in
accordance with the Engine Manual have
exhibited cracks in the disc rim. The discs
have failed to meet the inspection acceptance
criteria and have been returned to RollsRoyce for engineering investigation. This
investigation has concluded that the cracks
have resulted from scores within the cooling
air holes in the disc rim that could have been
introduced during new part manufacture or
during overhaul of the disc. The engineering
investigation has concluded that if this
cracking was undetected then it could result
in uncontained disc failure and a potential
unsafe condition for the aircraft.
You may obtain further information by
examining the MCAI ADs in the AD
docket.
Relevant Service Information
Rolls-Royce plc has issued Alert
Service Bulletin No. RB.211–72–AE969,
dated May 9, 2006. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI ADs.
FAA’s Determination and Requirements
of This Proposed AD
These products have been approved
by the United Kingdom (UK), and are
approved for operation in the United
States. Pursuant to our bilateral
agreement with the UK, they have
notified us of the unsafe condition
described in the MCAI ADs, and service
information referenced above. We are
proposing this AD because we evaluated
all pertinent information and
determined an unsafe condition exists
and is likely to exist or develop on other
products of the same type design. This
proposed AD would require initial and
repetitive eddy current inspections of
HP turbine discs.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 506 products of U.S.
registry. We also estimate that it would
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
9503
take about 4 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $80 per work-hour. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$161,920.
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 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 this 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); 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 regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
E:\FR\FM\21FEP1.SGM
21FEP1
9504
Federal Register / Vol. 73, No. 35 / Thursday, February 21, 2008 / Proposed Rules
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Rolls-Royce plc: Docket No. FAA–2007–
0078; Directorate Identifier 2007–NE–
40–AD.
Comments Due Date
(a) We must receive comments by March
24, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR)
models RB211–535E4 series, RB211–535E4–
B series, RB211–535E4–C series, RB211–
535C series, RB211–524 series, and RB211–
22B series turbofan engines. These engines
are installed on, but not limited to, Boeing
747, 757, and 767, Lockheed L–1011, and
Tupulev Tu204 airplanes.
Reason
(d) European Aviation Safety Agency AD
2006–0180, dated June 26, 2006, AD 2006–
0181, dated June 26, 2006, and AD 2006–
0182, dated June 28, 2006, state:
High pressure (HP) turbine discs recently
inspected in accordance with the Engine
Manual have exhibited cracks in the disc rim.
The discs have failed to meet the inspection
acceptance criteria and have been returned to
Rolls-Royce for engineering investigation.
This investigation has concluded that the
cracks have resulted from scores within the
cooling air holes in the disc rim that could
have been introduced during new part
manufacture or during overhaul of the disc.
The engineering investigation has concluded
that if this cracking was undetected then it
could result in uncontained disc failure and
a potential unsafe condition for the aircraft.
We are issuing this AD to prevent
uncontained disc failure, possibly resulting
in damage to the airplane.
ebenthall on PRODPC61 with PROPOSALS
Actions and Compliance
(e) Unless already done, perform an initial
eddy current inspection (ECI) of the HP
turbine disc air cooling holes. Information on
ECI of HP turbine disc cooling holes can be
found in RR Engine Overhaul Process
Manual No. TSD594–J, Overhaul Process 223,
dated May 1, 2001.
Initial Inspection for RB211–22B Series
Turbofan Engines
(f) For RB211–22B series turbofan engines:
(1) If an installed HP turbine disc has more
than 9,500 cycles-since-new (CSN) on the
effective date of this AD, then ECI the HP
turbine disc by whichever is the soonest of
the following conditions:
VerDate Aug<31>2005
14:38 Feb 20, 2008
Jkt 214001
(i) Within 500 cycles from the effective
date of this AD; or
(ii) At the next shop visit where the HP
turbine rotor is removed from the combustor
outer casing.
(2) If an installed HP turbine disc has 9,500
or fewer CSN on the effective date of this AD,
then ECI the HP turbine disc by whichever
is the soonest of the following conditions:
(i) Before reaching 10,000 CSN; or
(ii) At the next shop visit where the HP
turbine rotor is removed from the combustor
outer casing and the HP turbine disc has
more than 2,750 CSN.
(3) For HP turbine rotors at shop visit and
already removed from the combustor outer
casing on the effective date of this AD, ECI
the HP turbine disc before reinstalling the HP
turbine rotor in the combustor outer casing.
Initial Inspection of RB211–524 Series
Turbofan Engines
(g) For RB211–524 series turbofan engines,
ECI the HP turbine disc at the soonest of the
following after the effective date of the AD:
(1) At the next shop visit where the HP
turbine blades are removed from the HP
turbine disc and when the HP turbine disc
has more than 2,750 CSN.
(2) For HP turbine rotors at shop visit and
the HP turbine blades are removed from the
HP turbine disc and the HP turbine disc life
is more than 2,750 CSN, ECI the turbine disc
before reinstalling the HP turbine blades.
Initial Inspection of RB211–535C, –535E4,
–535E4–B, and –535E4–C Series Turbofan
Engines
(h) For RB211–535C, –535E4, –535E4–B,
and –535E4–C series turbofan engines:
(1) If an installed HP turbine disc has
17,500 or fewer CSN on the effective date of
this AD, then ECI the HP turbine disc by
whichever is the soonest of the following
conditions:
(i) Before reaching 18,000 CSN; or
(ii) At the next shop visit where the HP
turbine rotor is removed from the combustor
outer casing, and the HP turbine disc has
5,000 or more CSN.
(iii) For HP turbine rotors at shop visit on
the effective date of this AD that are removed
from the combustor outer casing, and that
have HP turbine discs with 5,000 or more
CSN, ECI the HP turbine disc before
reinstalling the HP turbine rotor in the
combustor outer casing.
(2) If an installed HP turbine disc has more
than 17,500 CSN on the effective date of this
AD, then ECI the HP turbine disc by
whichever is the soonest of the following
conditions:
(i) Within 500 cycles from the effective
date of this AD; or
(ii) At the next shop visit where the HP
turbine rotor is removed from the combustor
outer casing.
(iii) For HP turbine rotors at shop visit on
the effective date of this AD that are removed
from the combustor outer casing, ECI the HP
turbine disc before reinstalling the HP
turbine rotor in the combustor outer casing.
HP Turbine Disc Permanent Etching
(i) On successful completion of the initial
inspection only, permanently etch NMSB 72–
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
AE969 onto the HP turbine disc, adjacent to
the part number.
Repetitive ECI Inspections
(j) Thereafter, perform repetitive ECIs at
every shop visit where the HP turbine blades
are removed from the HP turbine disc.
Information on ECI of HP turbine disc air
cooling holes can be found in RR Engine
Overhaul Process Manual No. TSD594–J,
Overhaul Process 223, dated May 1, 2001.
(k) 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.
Previous Credit
(l) Initial inspections done before the
effective date of this AD on HP turbine discs
with a disc life above the minimum threshold
(5,000 CSN for the RB211–535 engines and
2,750 CSN for both the RB211–524 and the
RB211–22B engines) at the time of
inspection, per paragraph 1.C.(2) of RR Alert
Service Bulletin No. RB.211–72–AE969,
comply with the initial inspection
requirements specified in this AD.
Related Information
(m) Refer to EASA AD 2006–0180, dated
June 26, 2006, AD 2006–0181, dated June 26,
2006, and AD 2006–0182, dated June 28,
2006, for related information.
(n) Contact Ian Dargin, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: ian.dargin@faa.gov; telephone
781 238–7178; fax 781 238–7199, for more
information about this AD.
Issued in Burlington, Massachusetts, on
February 13, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–3192 Filed 2–20–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2007–0022; Airspace
Docket 07–AEA–07]
Proposed Amendment of Class E
Airspace; Waynesburg, PA
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking.
AGENCY:
SUMMARY: This action proposes to
amend the Class E airspace area at
Waynesburg, PA, to accommodate a new
Standard Instrument Approach
Procedure (SIAP) that has been
developed for Green County Airport. As
a result, controlled airspace extending
upward from 700 feet Above Ground
E:\FR\FM\21FEP1.SGM
21FEP1
]]>Agencies
[Federal Register Volume 73, Number 35 (Thursday, February 21, 2008)]
[Proposed Rules]
[Pages 9502-9504]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-3192]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0078; Directorate Identifier 2007-NE-40-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated 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:
High pressure (HP) turbine discs recently inspected in
accordance with the Engine Manual have exhibited cracks in the disc
rim. The discs have failed to meet the inspection acceptance
criteria and have been returned to Rolls-Royce for engineering
investigation. This investigation has concluded that the cracks have
resulted from scores within the cooling air holes in the disc rim
that could have been introduced during new part
[[Page 9503]]
manufacture or during overhaul of the disc. The engineering
investigation has concluded that if this cracking was undetected
then it could result in uncontained disc failure and a potential
unsafe condition for the aircraft.
We are proposing this AD to prevent uncontained disc failure, possibly
resulting in damage to the airplane.
DATES: We must receive comments on this proposed AD by March 24, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility: U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
ian.dargin@faa.gov; telephone (781) 238-7178, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2007-0078; Directorate
Identifier 2007-NE-40-AD'' in the subject line of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this proposed AD. We will consider
all comments received by the closing date and may amend this proposed
AD based on those comments.
We will post all comments we receive, without change, to https://
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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
2006-0180, dated June 26, 2006, for RB211-524 series engines, AD 2006-
0181, dated June 26, 2006, for RB211-22B engines, and AD 2006-0182,
dated June 28, 2006, for RB211-535 series engines, to correct the same
unsafe condition for the specified products. The EASA ADs state:
HPT discs recently inspected in accordance with the Engine
Manual have exhibited cracks in the disc rim. The discs have failed
to meet the inspection acceptance criteria and have been returned to
Rolls-Royce for engineering investigation. This investigation has
concluded that the cracks have resulted from scores within the
cooling air holes in the disc rim that could have been introduced
during new part manufacture or during overhaul of the disc. The
engineering investigation has concluded that if this cracking was
undetected then it could result in uncontained disc failure and a
potential unsafe condition for the aircraft.
You may obtain further information by examining the MCAI ADs in the AD
docket.
Relevant Service Information
Rolls-Royce plc has issued Alert Service Bulletin No. RB.211-72-
AE969, dated May 9, 2006. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI ADs.
FAA's Determination and Requirements of This Proposed AD
These products have been approved by the United Kingdom (UK), and
are approved for operation in the United States. Pursuant to our
bilateral agreement with the UK, they have notified us of the unsafe
condition described in the MCAI ADs, and service information referenced
above. We are proposing this AD because we evaluated all pertinent
information and determined an unsafe condition exists and is likely to
exist or develop on other products of the same type design. This
proposed AD would require initial and repetitive eddy current
inspections of HP turbine discs.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 506 products of U.S. registry. We also estimate that
it would take about 4 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $161,920.
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 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 this 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); 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 regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator,
[[Page 9504]]
the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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
airworthiness directive (AD):
Rolls-Royce plc: Docket No. FAA-2007-0078; Directorate Identifier
2007-NE-40-AD.
Comments Due Date
(a) We must receive comments by March 24, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) models RB211-535E4
series, RB211-535E4-B series, RB211-535E4-C series, RB211-535C
series, RB211-524 series, and RB211-22B series turbofan engines.
These engines are installed on, but not limited to, Boeing 747, 757,
and 767, Lockheed L-1011, and Tupulev Tu204 airplanes.
Reason
(d) European Aviation Safety Agency AD 2006-0180, dated June 26,
2006, AD 2006-0181, dated June 26, 2006, and AD 2006-0182, dated
June 28, 2006, state:
High pressure (HP) turbine discs recently inspected in
accordance with the Engine Manual have exhibited cracks in the disc
rim. The discs have failed to meet the inspection acceptance
criteria and have been returned to Rolls-Royce for engineering
investigation. This investigation has concluded that the cracks have
resulted from scores within the cooling air holes in the disc rim
that could have been introduced during new part manufacture or
during overhaul of the disc. The engineering investigation has
concluded that if this cracking was undetected then it could result
in uncontained disc failure and a potential unsafe condition for the
aircraft.
We are issuing this AD to prevent uncontained disc failure, possibly
resulting in damage to the airplane.
Actions and Compliance
(e) Unless already done, perform an initial eddy current
inspection (ECI) of the HP turbine disc air cooling holes.
Information on ECI of HP turbine disc cooling holes can be found in
RR Engine Overhaul Process Manual No. TSD594-J, Overhaul Process
223, dated May 1, 2001.
Initial Inspection for RB211-22B Series Turbofan Engines
(f) For RB211-22B series turbofan engines:
(1) If an installed HP turbine disc has more than 9,500 cycles-
since-new (CSN) on the effective date of this AD, then ECI the HP
turbine disc by whichever is the soonest of the following
conditions:
(i) Within 500 cycles from the effective date of this AD; or
(ii) At the next shop visit where the HP turbine rotor is
removed from the combustor outer casing.
(2) If an installed HP turbine disc has 9,500 or fewer CSN on
the effective date of this AD, then ECI the HP turbine disc by
whichever is the soonest of the following conditions:
(i) Before reaching 10,000 CSN; or
(ii) At the next shop visit where the HP turbine rotor is
removed from the combustor outer casing and the HP turbine disc has
more than 2,750 CSN.
(3) For HP turbine rotors at shop visit and already removed from
the combustor outer casing on the effective date of this AD, ECI the
HP turbine disc before reinstalling the HP turbine rotor in the
combustor outer casing.
Initial Inspection of RB211-524 Series Turbofan Engines
(g) For RB211-524 series turbofan engines, ECI the HP turbine
disc at the soonest of the following after the effective date of the
AD:
(1) At the next shop visit where the HP turbine blades are
removed from the HP turbine disc and when the HP turbine disc has
more than 2,750 CSN.
(2) For HP turbine rotors at shop visit and the HP turbine
blades are removed from the HP turbine disc and the HP turbine disc
life is more than 2,750 CSN, ECI the turbine disc before
reinstalling the HP turbine blades.
Initial Inspection of RB211-535C, -535E4, -535E4-B, and -535E4-C Series
Turbofan Engines
(h) For RB211-535C, -535E4, -535E4-B, and -535E4-C series
turbofan engines:
(1) If an installed HP turbine disc has 17,500 or fewer CSN on
the effective date of this AD, then ECI the HP turbine disc by
whichever is the soonest of the following conditions:
(i) Before reaching 18,000 CSN; or
(ii) At the next shop visit where the HP turbine rotor is
removed from the combustor outer casing, and the HP turbine disc has
5,000 or more CSN.
(iii) For HP turbine rotors at shop visit on the effective date
of this AD that are removed from the combustor outer casing, and
that have HP turbine discs with 5,000 or more CSN, ECI the HP
turbine disc before reinstalling the HP turbine rotor in the
combustor outer casing.
(2) If an installed HP turbine disc has more than 17,500 CSN on
the effective date of this AD, then ECI the HP turbine disc by
whichever is the soonest of the following conditions:
(i) Within 500 cycles from the effective date of this AD; or
(ii) At the next shop visit where the HP turbine rotor is
removed from the combustor outer casing.
(iii) For HP turbine rotors at shop visit on the effective date
of this AD that are removed from the combustor outer casing, ECI the
HP turbine disc before reinstalling the HP turbine rotor in the
combustor outer casing.
HP Turbine Disc Permanent Etching
(i) On successful completion of the initial inspection only,
permanently etch NMSB 72-AE969 onto the HP turbine disc, adjacent to
the part number.
Repetitive ECI Inspections
(j) Thereafter, perform repetitive ECIs at every shop visit
where the HP turbine blades are removed from the HP turbine disc.
Information on ECI of HP turbine disc air cooling holes can be found
in RR Engine Overhaul Process Manual No. TSD594-J, Overhaul Process
223, dated May 1, 2001.
(k) 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.
Previous Credit
(l) Initial inspections done before the effective date of this
AD on HP turbine discs with a disc life above the minimum threshold
(5,000 CSN for the RB211-535 engines and 2,750 CSN for both the
RB211-524 and the RB211-22B engines) at the time of inspection, per
paragraph 1.C.(2) of RR Alert Service Bulletin No. RB.211-72-AE969,
comply with the initial inspection requirements specified in this
AD.
Related Information
(m) Refer to EASA AD 2006-0180, dated June 26, 2006, AD 2006-
0181, dated June 26, 2006, and AD 2006-0182, dated June 28, 2006,
for related information.
(n) Contact Ian Dargin, Aerospace Engineer, Engine Certification
Office, FAA, Engine & Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail: ian.dargin@faa.gov;
telephone 781 238-7178; fax 781 238-7199, for more information about
this AD.
Issued in Burlington, Massachusetts, on February 13, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-3192 Filed 2-20-08; 8:45 am]
BILLING CODE 4910-13-P
