Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines, 56457-56460 [E8-22521]
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Federal Register / Vol. 73, No. 189 / Monday, September 29, 2008 / Rules and Regulations
this AD requires that you repair the crack
before further flight.
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, Transport Airplane
Directorate, 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: Tom Rodriguez,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1137; 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.
(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 FAAapproved 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.
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2007–0263, dated October 3, 2007,
and the service information specified in
Table 2 of this AD, for related information.
TABLE 2—SERVICE INFORMATION
Service Bulletin
Revision
ATR Service Bulletin ATR42–32–0092 ..................................................................................................
ATR Technical Instruction ATR42, ATR42–07–01 .................................................................................
Messier-Dowty Service Bulletin 631–32–194 .........................................................................................
Messier-Dowty Special Inspection Service Bulletin 631–32–191 ..........................................................
Original ..................
Original ..................
Original ..................
2 .............................
Material Incorporated by Reference
(i) You must use the service information
specified in Table 3 of this AD to do the
Date
June 25, 2007.
February 5, 2007.
June 6, 2007.
August 30, 2007.
actions required by this AD, unless the AD
specifies otherwise.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE
Service Bulletin
Revision
ATR Service Bulletin ATR42–32–0092 ..................................................................................................
Messier-Dowty Service Bulletin 631–32–194 .........................................................................................
Messier-Dowty Special Inspection Service Bulletin 631–32–191 ..........................................................
Original ..................
Original ..................
2 .............................
Messier-Dowty Special Inspection Service
Bulletin 631–32–191, Revision 2, dated
Date
June 25, 2007.
June 6, 2007.
August 30, 2007.
August 30, 2007, contains the following
effective pages:
Revision level
shown on page
Date shown on page
1, 3, 8 ....................................................................................................................................................
2, 6, 7, 9, 10 ..........................................................................................................................................
4, 5 ........................................................................................................................................................
jlentini on PROD1PC65 with RULES
Page No.
2 .............................
1 .............................
Original ..................
August 30, 2007.
February 26, 2007.
December 13, 2006.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact ATR, 316 Route de Bayonne,
31060 Toulouse, Cedex 03, France.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington; 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on August
12, 2008.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–19365 Filed 9–26–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0078; Directorate
Identifier 2007–NE–40–AD; Amendment 39–
15683; AD 2008–20–04]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc RB211 Series Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
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16:29 Sep 26, 2008
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Federal Register / Vol. 73, No. 189 / Monday, September 29, 2008 / Rules and Regulations
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:
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.
DATES: This AD becomes effective
November 3, 2008.
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: 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:
Discussion
jlentini on PROD1PC65 with RULES
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 February 21, 2008 (73 FR
9502). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states that:
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.
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16:29 Sep 26, 2008
Jkt 214001
Comments
One commenter, Federal Express,
recommends that we give previous
credit for eddy current inspections
(ECIs) previously performed on RB211–
535 HP turbine discs per AD 2006–17–
12 and Rolls-Royce plc (RR) Alert
Service Bulletin (ASB) No. RB.211–72–
AE651, dated November 22, 2004. The
commenter states that the same ECI of
the HP turbine discs is referenced in
that AD, as in the proposed AD.
We agree. Initial inspections done
before the effective date of this AD on
RB211–535 HP turbine discs per RR
ASB No. RB.211–72–AE651, dated
November 22, 2004, and done on
RB211–22B HP turbine discs per RR
ASB RB.211–72–AE717, dated January
21, 2005, and done on RB211–524 HP
discs per RR ASB RB.211–72–AE718,
dated January 24, 2006, comply with the
initial inspection requirements specified
in this AD. We added this information
to the previous credit paragraph of the
AD.
Request To Exclude HP Turbine Discs
From the AD
One commenter, Boeing, requests that
we exclude RB211–524 HP turbine discs
that have incorporated RR Service
Bulletin (SB) No. RB.211–72–C109 or
RR SB No. RB.211–72–C762 from the
AD. The commenter states that these
SBs introduced new HP turbine rotors
with reduced stress levels and those
rotors are not affected by this AD.
We agree. We changed the
applicability to exclude RB211–524 HP
turbine discs that incorporate these SBs.
Request To Remove the Revision Date
Boeing also requests that we update or
remove the reference to the revision
date of RR Repair Document TSD–594–
J Overhaul Process 223, from the AD.
The proposed AD references the
revision date of May 1, 2001, but the
document is now up to the revision date
of March 15, 2004.
We agree. We removed the date
reference from the AD.
Etching Requirement Eliminated
We eliminated the requirement to
permanent etch ‘‘NMSB 72–AE969’’
onto the HP turbine disc from the AD,
as it is not necessary.
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
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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
506 products of U.S. registry. We also
estimate that it will take about 4 workhours per product to comply with the
basic requirements of this proposed AD.
The average labor rate is $80 per workhour. Based on these figures, we
estimate the cost of the 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 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); 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 AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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Federal Register / Vol. 73, No. 189 / Monday, September 29, 2008 / Rules and Regulations
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 (telephone
(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, Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 AD:
■
2008–20–04 Rolls-Royce plc: Amendment
39–15683. Docket No. FAA–2007–0078;
Directorate Identifier 2007–NE–40–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective November 3, 2008.
jlentini on PROD1PC65 with RULES
Affected ADs
(b) None.
(c) This AD applies to Rolls-Royce plc (RR)
models RB211–535E4 series, RB211–535E4–
B series, RB211–535E4–C series, RB211–
535C series, and RB211–22B series turbofan
engines. This AD also applies to RB211–524
series turbofan engines except for engines
with high pressure (HP) turbine discs
incorporating RR Service Bulletin (SB) No.
RB.211–72–C109 or RR SB No. RB.211–72–
C762. These engines are installed on, but not
limited to, Boeing 747, 757, and 767,
Lockheed L–1011, and Tupolev 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:
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 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
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16:29 Sep 26, 2008
Jkt 214001
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.
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
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56459
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.
Repetitive ECI Inspections
(i) 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.
(j) 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
(k) 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.
(l) Initial inspections done before the
effective date of this AD using the following
RR Alert Service Bulletins, comply with the
initial inspection requirements specified in
this AD:
(1) RB211–535 HP turbine discs per RR
ASB No. RB.211–72–AE651, dated November
22, 2004.
(2) RB211–22B HP turbine discs per RR
ASB RB.211–72–AE717, dated January 21,
2005.
(3) RB211–524 HP discs per RR ASB
RB.211–72–AE718, dated January 24, 2006.
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 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, for more
information about this AD.
Material Incorporated by Reference
(o) None.
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Federal Register / Vol. 73, No. 189 / Monday, September 29, 2008 / Rules and Regulations
Issued in Burlington, Massachusetts, on
September 19, 2008.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E8–22521 Filed 9–26–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0676; Directorate
Identifier 2007–NM–280–AD; Amendment
39–15676; AD 2008–19–09]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.28 Mark 0070 and 0100
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This 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:
jlentini on PROD1PC65 with RULES
Service experience has shown that heavy
MLG (main landing gear) shimmy vibration
can occur due to faulty/empty dampers or
due to excessive free play in the T/L (torque
link) apex joint. In several cases this shimmy
vibration resulted in a MLG main fitting
failure * * * finally resulting in a collapse
of the MLG causing extensive damage to the
wingtip, aileron and flaps. * * *
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
November 3, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 3, 2008.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
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16:29 Sep 26, 2008
Jkt 214001
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1137; fax (425) 227–1149.
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 July 2, 2008 (73 FR 37898).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
Service experience has shown that heavy
MLG (main landing gear) shimmy vibration
can occur due to faulty/empty dampers or
due to excessive free play in the T/L (torque
link) apex joint. In several cases this shimmy
vibration resulted in a MLG main fitting
failure. In those cases where only the upper
torque link attachment lug failed the damage
to the aircraft was limited. In all other cases
the MLG main fitting cracked, finally
resulting in a collapse of the MLG causing
extensive damage to the wingtip, aileron and
flaps. To prevent the collapse of the MLG,
Messier-Dowty has designed an upper torque
link fuse pin with a static strength lower than
the demonstrated strength of the MLG main
fitting. In case of a heavy shimmy vibration
the upper torque link fuse pin will fail before
the main fitting. Therefore the installation of
an upper torque link fuse pin will protect the
LH and RH (left- and right-hand) MLG main
fitting against extreme shimmy loads and
thus against a MLG main fitting failure and
a MLG collapse. Since an unsafe condition
has been identified that may exist or develop
on aircraft of the same type design this
Airworthiness Directive requires the
modification of the MLG by replacing the
upper torque link pin with a new fuse pin.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
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provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
about 2 products of U.S. registry. We
also estimate that it will take about 15
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Required parts will cost about $0 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of this AD
to the U.S. operators to be $2,400, or
$1,200 per product.
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;
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]]>Agencies
[Federal Register Volume 73, Number 189 (Monday, September 29, 2008)]
[Rules and Regulations]
[Pages 56457-56460]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-22521]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0078; Directorate Identifier 2007-NE-40-AD;
Amendment 39-15683; AD 2008-20-04]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
[[Page 56458]]
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:
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.
DATES: This AD becomes effective November 3, 2008.
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: 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:
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 February 21, 2008
(73 FR 9502). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states that:
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.
Comments
One commenter, Federal Express, recommends that we give previous
credit for eddy current inspections (ECIs) previously performed on
RB211-535 HP turbine discs per AD 2006-17-12 and Rolls-Royce plc (RR)
Alert Service Bulletin (ASB) No. RB.211-72-AE651, dated November 22,
2004. The commenter states that the same ECI of the HP turbine discs is
referenced in that AD, as in the proposed AD.
We agree. Initial inspections done before the effective date of
this AD on RB211-535 HP turbine discs per RR ASB No. RB.211-72-AE651,
dated November 22, 2004, and done on RB211-22B HP turbine discs per RR
ASB RB.211-72-AE717, dated January 21, 2005, and done on RB211-524 HP
discs per RR ASB RB.211-72-AE718, dated January 24, 2006, comply with
the initial inspection requirements specified in this AD. We added this
information to the previous credit paragraph of the AD.
Request To Exclude HP Turbine Discs From the AD
One commenter, Boeing, requests that we exclude RB211-524 HP
turbine discs that have incorporated RR Service Bulletin (SB) No.
RB.211-72-C109 or RR SB No. RB.211-72-C762 from the AD. The commenter
states that these SBs introduced new HP turbine rotors with reduced
stress levels and those rotors are not affected by this AD.
We agree. We changed the applicability to exclude RB211-524 HP
turbine discs that incorporate these SBs.
Request To Remove the Revision Date
Boeing also requests that we update or remove the reference to the
revision date of RR Repair Document TSD-594-J Overhaul Process 223,
from the AD. The proposed AD references the revision date of May 1,
2001, but the document is now up to the revision date of March 15,
2004.
We agree. We removed the date reference from the AD.
Etching Requirement Eliminated
We eliminated the requirement to permanent etch ``NMSB 72-AE969''
onto the HP turbine disc from the AD, as it is not necessary.
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 506 products of U.S. registry. We also estimate that it
will 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 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 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); 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 AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
[[Page 56459]]
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 (telephone (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, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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 adding the following new AD:
2008-20-04 Rolls-Royce plc: Amendment 39-15683. Docket No. FAA-2007-
0078; Directorate Identifier 2007-NE-40-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
3, 2008.
Affected ADs
(b) None.
(c) This AD applies to Rolls-Royce plc (RR) models RB211-535E4
series, RB211-535E4-B series, RB211-535E4-C series, RB211-535C
series, and RB211-22B series turbofan engines. This AD also applies
to RB211-524 series turbofan engines except for engines with high
pressure (HP) turbine discs incorporating RR Service Bulletin (SB)
No. RB.211-72-C109 or RR SB No. RB.211-72-C762. These engines are
installed on, but not limited to, Boeing 747, 757, and 767, Lockheed
L-1011, and Tupolev 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:
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.
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.
Repetitive ECI Inspections
(i) 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.
(j) 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
(k) 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.
(l) Initial inspections done before the effective date of this
AD using the following RR Alert Service Bulletins, comply with the
initial inspection requirements specified in this AD:
(1) RB211-535 HP turbine discs per RR ASB No. RB.211-72-AE651,
dated November 22, 2004.
(2) RB211-22B HP turbine discs per RR ASB RB.211-72-AE717, dated
January 21, 2005.
(3) RB211-524 HP discs per RR ASB RB.211-72-AE718, dated January
24, 2006.
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 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, for more information
about this AD.
Material Incorporated by Reference
(o) None.
[[Page 56460]]
Issued in Burlington, Massachusetts, on September 19, 2008.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E8-22521 Filed 9-26-08; 8:45 am]
BILLING CODE 4910-13-P
