Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Model BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 Turbofan Engines, 55759-55761 [E9-25942]
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Federal Register / Vol. 74, No. 208 / Thursday, October 29, 2009 / Rules and Regulations
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.
DEPARTMENT OF TRANSPORTATION
Related Information
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG Model
BR700–715A1–30, BR700–715B1–30,
and BR700–715C1–30 Turbofan
Engines
(h) Refer to MCAI Transport Canada Civil
Aviation Airworthiness Directive CF–2008–
34, dated December 2, 2008; and Bombardier
Service Bulletin 670BA–49–012, Revision A,
dated August 28, 2008; for related
information.
Material Incorporated by Reference
(i) You must use Bombardier Service
Bulletin 670BA–49–012, Revision A, dated
August 28, 2008, to do the actions required
by this AD, unless the AD specifies
otherwise.
(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
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference 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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on October
19, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–25648 Filed 10–28–09; 8:45 am]
dcolon on DSK2BSOYB1PROD with RULES
BILLING CODE 4910–13–P
VerDate Nov<24>2008
14:45 Oct 28, 2009
Jkt 220001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0045; Directorate
Identifier 2007–NE–53–AD; Amendment 39–
16041; AD 2009–21–04]
RIN 2120–AA64
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Repair Scheme BRG3086 Issue 1 instructs
the repair of the High-Pressure (HP)
Compressor Front Drum Assembly Damping
Grooves. This repair has an impact on the life
of the HP Compressor Front Drum Assembly.
We are issuing this AD to prevent
failure of front HP compressor rotors,
which could result in an uncontained
engine failure and damage to the
airplane.
DATES: This AD becomes effective
December 3, 2009.
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:
Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
e-mail jason.yang@faa.gov; telephone
(781) 238–7747; fax (781) 238–7199.
Contact Rolls-Royce Deutschland Ltd
& Co KG, Eschenweg 11, Dahlewitz,
15827 Blankenfelde-Mahlow, Germany;
telephone 49 (0) 33–7086–1768; fax 49
(0) 33–7086–3356, or go to: https://
www.rolls-royce.com/deutschland/en/
default.htm, for a copy of the service
information referenced in this AD.
SUPPLEMENTARY INFORMATION:
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
55759
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 12, 2009 (74 FR
7004). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states that:
Repair Scheme BRG3086 Issue 1 instructs
the repair of the HP Compressor Front Drum
Assembly Damping Grooves. This repair has
an impact on the life of the HP Compressor
Front Drum Assembly. This emergency
airworthiness directive has been raised to
mandate certain specific CAUTION notes
related to specific subtasks of the BR715
Time Limits Manual (TLM) T–715–3BR
instructing a reduced life for certain Serial
Numbers (SN) of the HP Compressor Front
Drum Assemblies Part No. BRH20070 after
repair BRG3086 Issue 1 has been applied and
Part No. BRR21918 after repair BRG3086
Issue 1 has been applied. Results for each
individual repair case are listed in the latest
revision of Non-Modification Service
Bulletin SB–BR700–72–A900437.
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.
Since we issued the proposed AD, we
found it necessary to add a column to
Table 1 for affected HP compressor rotor
front disc assemblies operating under
the C1–30 derated design engine
mission.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
with the change described previously.
Differences Between This AD and the
MCAI or Service Information
We have found it necessary to differ
from the MCAI as follows:
• We don’t require operators to
amend the Time Limits Manual.
• We don’t allow the operators to
show compliance by using RRD ASB
SB–BR700–72–A900437, initial issue,
dated February 26, 2007. Some of the
affected parts are not included in the
initial issue of the ASB.
• We have incorporated in this AD,
the life reduction Table for the HPC
drum assemblies, by serial number (SN),
that are specified in RRD ASB SB–
BR700–72–A900437, Revision 2, dated
September 17, 2009.
• HPC drum assembly, P/N
BRH20070 is not affected by the AD;
since only certain HPC drums with P/
N BRR21918 were affected in
E:\FR\FM\29OCR1.SGM
29OCR1
55760
Federal Register / Vol. 74, No. 208 / Thursday, October 29, 2009 / Rules and Regulations
accordance with RRD ASB SB–BR700–
72–A900437, Revision 2, dated
September 17, 2009.
Costs of Compliance
Based on the service information, we
estimate that this AD will affect about
14 engines installed on airplanes of U.S.
registry. We also estimate that it will
take about 10 work-hours per engine to
comply with this AD. The average labor
rate is $80 per work-hour. Required
parts will cost about $100,000 per
engine. Based on these figures, we
estimate the cost of the AD on U.S.
operators to be $1,411,200.
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
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://
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.
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:
■
2009–21–04 Rolls-Royce Deutschland Ltd &
Co KG (formerly BMW Rolls-Royce
GmbH and BMW Rolls-Royce Aero
Engines): Amendment 39–16041. Docket
No. FAA–2009–0045; Directorate
Identifier 2007–NE–53–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective December 3, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce
Deutschland Ltd & Co KG model BR700–
715A1–30, BR700–715B1–30, and BR700–
715C1–30 turbofan engines. These engines
are installed on, but not limited to,
McDonnell Douglas 717–200 airplanes.
Reason
(d) Repair Scheme BRG3086 Issue 1
instructs the repair of the High-Pressure (HP)
Compressor Front Drum Assembly Damping
Grooves. This repair has an impact on the life
of the HP Compressor Front Drum Assembly.
We are issuing this AD to prevent failure
of front HP compressor rotors, which could
result in an uncontained engine failure and
damage to the airplane.
Adoption of the Amendment
Actions and Compliance
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(e) Remove the following HP Compressor
drum assemblies from operation before
reaching the life limit specified in Table 1 of
this AD.
■
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
PART 39—AIRWORTHINESS
DIRECTIVES
TABLE 1—FLIGHT CYCLE LIFE BY PART NUMBER, SERIAL NUMBER, AND MISSION FOR AFFECTED HP COMPRESSOR
ROTOR FRONT DISC ASSEMBLIES
Serial
No.
dcolon on DSK2BSOYB1PROD with RULES
Disc assembly part No.
BRR21918
BRR21918
BRR21918
BRR21918
BRR21918
BRR21918
BRR21918
BRR21918
BRR21918
BRR21918
BRR21918
BRR21918
BRR21918
BRR21918
............................................................
............................................................
............................................................
............................................................
............................................................
............................................................
............................................................
............................................................
............................................................
............................................................
............................................................
............................................................
............................................................
............................................................
VerDate Nov<24>2008
14:45 Oct 28, 2009
Jkt 220001
PO 00000
A1–30
design
1,107
1,120
1,122
1,144
1,154
1,163
1,166
1,194
1,217
1,232
1,255
1,259
1,271
1,292
Frm 00014
Fmt 4700
B1–30 and
C1–30
designs
A1–30
Hawaiian
6,600
6,800
7,000
7,300
6,800
6,800
6,500
6,900
7,000
7,200
7,300
7,500
7,300
7,300
4,500
4,700
4,900
5,000
4,700
4,700
4,500
4,800
4,900
5,000
5,100
5,200
5,100
5,100
Sfmt 4700
E:\FR\FM\29OCR1.SGM
4,500
4,700
4,900
5,000
4,700
4,700
4,500
4,800
4,900
5,000
5,100
5,200
5,100
5,100
29OCR1
C1–30
Tropical
and derated
tropical
3,800
4,000
4,100
4,200
4,000
4,000
3,800
4,000
4,100
4,200
4,300
4,400
4,300
4,300
C1–30
Derated
design
6,600
6,800
7,000
7,300
6,800
6,800
6,500
6,900
7,000
7,200
7,300
7,500
7,300
7,300
Federal Register / Vol. 74, No. 208 / Thursday, October 29, 2009 / Rules and Regulations
Other FAA AD Provisions
(f) Alternative Methods of Compliance
(AMOCs): The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(g) Refer to MCAI Emergency
Airworthiness Directive 2007–0050–E, dated
February 26, 2007, and Rolls-Royce
Deutschland Ltd & Co KG Alert Service
Bulletin SB–BR700–72–A900437, Revision 2,
dated September 17, 2009, for related
information. Contact Rolls-Royce
Deutschland Ltd & Co KG, Eschenweg 11,
Dahlewitz, 15827 Blankenfelde-Mahlow,
Germany; telephone 49 (0) 33–7086–1768;
fax 49 (0) 33–7086–3356, or go to: https://
www.rolls-royce.com/deutschland/en/
default.htm, for a copy of this service
information.
(h) Contact Jason Yang, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail jason.yang@faa.gov; telephone
(781) 238–7747; fax (781) 238–7199, for more
information about this AD.
Issued in Burlington, Massachusetts, on
October 1, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E9–25942 Filed 10–28–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
of the nipple, caused by the socket locking
balls. During tear down investigations of selfsealing coupling P/N 9304000–305 (Socket
Assembly), internal socket wear has been
observed. Wear that exceeds the allowable
limits could lead to reduced oil flow, and
further wear could contribute to separation of
the Self-Seal Coupling, making the engine
inoperable and subsequent shut down. As
secondary damage, the generator may fail,
releasing oil into the nacelle and increasing
the possibility of fire.
You may obtain further information by
examining the MCAI in the AD docket.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
December 3, 2009.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 3, 2009.
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:
Shahram Daneshmandi, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue,
SW., Renton, Washington 98057–3356;
telephone (425) 227–1112; fax (425)
227–1149.
SUPPLEMENTARY INFORMATION:
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Discussion
14 CFR Part 39
[Docket No. FAA–2009–0654; Directorate
Identifier 2008–NM–083–AD; Amendment
39–16058 AD 2009–22–07]
RIN 2120–AA64
Airworthiness Directives; Saab AB,
Saab Aerosystems Model SAAB 2000
Airplanes
dcolon on DSK2BSOYB1PROD with RULES
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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:
There have been reported incidents of
brinelling to the self-sealing coupling Part
Number (P/N) 9304000–303 (Nipple
Assembly). The wear is visible in the groove
VerDate Nov<24>2008
14:45 Oct 28, 2009
Jkt 220001
55761
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 21, 2009 (74 FR 35828).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
There have been reported incidents of
brinelling to the self-sealing coupling Part
Number (P/N) 9304000–303 (Nipple
Assembly). The wear is visible in the groove
of the nipple, caused by the socket locking
balls. During tear down investigations of selfsealing coupling P/N 9304000–305 (Socket
Assembly), internal socket wear has been
observed. Wear that exceeds the allowable
limits could lead to reduced oil flow, and
further wear could contribute to separation of
the Self-Seal Coupling, making the engine
inoperable and subsequent shut down. As
secondary damage, the generator may fail,
releasing oil into the nacelle and increasing
the possibility of fire.
For the reason described above, this
Airworthiness Directive (AD) requires the
inspection of the affected nipple- and socket
assemblies and, if wear is found outside the
specified limits, replacement of worn parts.
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
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
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
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 6
products of U.S. registry. We also
estimate that it will take about 1 workhour per product to comply with the
basic requirements of this AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $480, or $80 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
E:\FR\FM\29OCR1.SGM
29OCR1
]]>Agencies
[Federal Register Volume 74, Number 208 (Thursday, October 29, 2009)]
[Rules and Regulations]
[Pages 55759-55761]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-25942]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0045; Directorate Identifier 2007-NE-53-AD;
Amendment 39-16041; AD 2009-21-04]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG
Model BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) issued by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
Repair Scheme BRG3086 Issue 1 instructs the repair of the High-
Pressure (HP) Compressor Front Drum Assembly Damping Grooves. This
repair has an impact on the life of the HP Compressor Front Drum
Assembly.
We are issuing this AD to prevent failure of front HP compressor
rotors, which could result in an uncontained engine failure and damage
to the airplane.
DATES: This AD becomes effective December 3, 2009.
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: Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail
jason.yang@faa.gov; telephone (781) 238-7747; fax (781) 238-7199.
Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11,
Dahlewitz, 15827 Blankenfelde-Mahlow, Germany; telephone 49 (0) 33-
7086-1768; fax 49 (0) 33-7086-3356, or go to: https://www.rolls-royce.com/deutschland/en/default.htm, for a copy of the service
information referenced in this AD.
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 12, 2009
(74 FR 7004). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states that:
Repair Scheme BRG3086 Issue 1 instructs the repair of the HP
Compressor Front Drum Assembly Damping Grooves. This repair has an
impact on the life of the HP Compressor Front Drum Assembly. This
emergency airworthiness directive has been raised to mandate certain
specific CAUTION notes related to specific subtasks of the BR715
Time Limits Manual (TLM) T-715-3BR instructing a reduced life for
certain Serial Numbers (SN) of the HP Compressor Front Drum
Assemblies Part No. BRH20070 after repair BRG3086 Issue 1 has been
applied and Part No. BRR21918 after repair BRG3086 Issue 1 has been
applied. Results for each individual repair case are listed in the
latest revision of Non-Modification Service Bulletin SB-BR700-72-
A900437.
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.
Since we issued the proposed AD, we found it necessary to add a
column to Table 1 for affected HP compressor rotor front disc
assemblies operating under the C1-30 derated design engine mission.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD with the change described
previously.
Differences Between This AD and the MCAI or Service Information
We have found it necessary to differ from the MCAI as follows:
We don't require operators to amend the Time Limits
Manual.
We don't allow the operators to show compliance by using
RRD ASB SB-BR700-72-A900437, initial issue, dated February 26, 2007.
Some of the affected parts are not included in the initial issue of the
ASB.
We have incorporated in this AD, the life reduction Table
for the HPC drum assemblies, by serial number (SN), that are specified
in RRD ASB SB-BR700-72-A900437, Revision 2, dated September 17, 2009.
HPC drum assembly, P/N BRH20070 is not affected by the AD;
since only certain HPC drums with P/N BRR21918 were affected in
[[Page 55760]]
accordance with RRD ASB SB-BR700-72-A900437, Revision 2, dated
September 17, 2009.
Costs of Compliance
Based on the service information, we estimate that this AD will
affect about 14 engines installed on airplanes of U.S. registry. We
also estimate that it will take about 10 work-hours per engine to
comply with this AD. The average labor rate is $80 per work-hour.
Required parts will cost about $100,000 per engine. Based on these
figures, we estimate the cost of the AD on U.S. operators to be
$1,411,200.
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://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:
2009-21-04 Rolls-Royce Deutschland Ltd & Co KG (formerly BMW Rolls-
Royce GmbH and BMW Rolls-Royce Aero Engines): Amendment 39-16041.
Docket No. FAA-2009-0045; Directorate Identifier 2007-NE-53-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
3, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG model
BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines.
These engines are installed on, but not limited to, McDonnell
Douglas 717-200 airplanes.
Reason
(d) Repair Scheme BRG3086 Issue 1 instructs the repair of the
High-Pressure (HP) Compressor Front Drum Assembly Damping Grooves.
This repair has an impact on the life of the HP Compressor Front
Drum Assembly.
We are issuing this AD to prevent failure of front HP compressor
rotors, which could result in an uncontained engine failure and
damage to the airplane.
Actions and Compliance
(e) Remove the following HP Compressor drum assemblies from
operation before reaching the life limit specified in Table 1 of
this AD.
Table 1--Flight Cycle Life by Part Number, Serial Number, and Mission for Affected HP Compressor Rotor Front
Disc Assemblies
----------------------------------------------------------------------------------------------------------------
C1-30
A1-30 B1-30 and A1-30 Tropical and C1-30
Disc assembly part No. Serial No. design C1-30 Hawaiian derated Derated
designs tropical design
----------------------------------------------------------------------------------------------------------------
BRR21918.................... 1,107 6,600 4,500 4,500 3,800 6,600
BRR21918.................... 1,120 6,800 4,700 4,700 4,000 6,800
BRR21918.................... 1,122 7,000 4,900 4,900 4,100 7,000
BRR21918.................... 1,144 7,300 5,000 5,000 4,200 7,300
BRR21918.................... 1,154 6,800 4,700 4,700 4,000 6,800
BRR21918.................... 1,163 6,800 4,700 4,700 4,000 6,800
BRR21918.................... 1,166 6,500 4,500 4,500 3,800 6,500
BRR21918.................... 1,194 6,900 4,800 4,800 4,000 6,900
BRR21918.................... 1,217 7,000 4,900 4,900 4,100 7,000
BRR21918.................... 1,232 7,200 5,000 5,000 4,200 7,200
BRR21918.................... 1,255 7,300 5,100 5,100 4,300 7,300
BRR21918.................... 1,259 7,500 5,200 5,200 4,400 7,500
BRR21918.................... 1,271 7,300 5,100 5,100 4,300 7,300
BRR21918.................... 1,292 7,300 5,100 5,100 4,300 7,300
----------------------------------------------------------------------------------------------------------------
[[Page 55761]]
Other FAA AD Provisions
(f) Alternative Methods of Compliance (AMOCs): The Manager,
Engine Certification Office, FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures found in 14 CFR
39.19.
Related Information
(g) Refer to MCAI Emergency Airworthiness Directive 2007-0050-E,
dated February 26, 2007, and Rolls-Royce Deutschland Ltd & Co KG
Alert Service Bulletin SB-BR700-72-A900437, Revision 2, dated
September 17, 2009, for related information. Contact Rolls-Royce
Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827
Blankenfelde-Mahlow, Germany; telephone 49 (0) 33-7086-1768; fax 49
(0) 33-7086-3356, or go to: https://www.rolls-royce.com/deutschland/en/default.htm, for a copy of this service information.
(h) Contact Jason Yang, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail jason.yang@faa.gov;
telephone (781) 238-7747; fax (781) 238-7199, for more information
about this AD.
Issued in Burlington, Massachusetts, on October 1, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E9-25942 Filed 10-28-09; 8:45 am]
BILLING CODE 4910-13-P
