[Federal Register Volume 74, Number 32 (Thursday, February 19, 2009)]
[Rules and Regulations]
[Pages 7643-7645]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-3355]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0169; Directorate Identifier 2007-NE-45-AD;
Amendment 39-15819; AD 2009-04-13]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG,
BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) issued by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
The application of most recent 3D FEM modeling has resulted in
the need to reconsider the disc lives as currently shown in the Time
Limits Manual. The current Post Certification Life Statement for the
low pressure (LP) compressor (fan) disc assembly revises the
Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000
flight cycles for both the BR715 LP (fan) disc assembly Part No. (P/
N) BRH10048 and BR715 LP compressor (fan) disc assembly P/N
BRH19253, when installed in the BR700-715A1-30 engine model and
operated against the Hawaiian Flight Mission.
We are issuing this AD to prevent uncontained failure of the LP
compressor (fan) disc assembly and damage to the airplane.
DATES: This AD becomes effective March 26, 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:
[email protected]; telephone (781) 238-7747; 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 5, 2008 (73
FR 6638). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states that:
The application of most recent 3D FEM modeling has resulted in
the need to reconsider the disc lives as currently shown in the Time
Limits Manual. The current Post Certification Life Statement for the
low pressure (LP) compressor (fan) disc assembly revises the
Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000
flight cycles for both the BR715 LP (fan) disc assembly P/N BRH10048
and BR715 LP compressor (fan) disc assembly P/N BRH19253, when
installed in the BR700-715A1-30 engine model and operated against
the Hawaiian Flight Mission.
This AD requires, within 25 flight cycles after the effective date
of the AD:
Amending the Airworthiness Limitations Section (ALS) of
the Time Limits Manual SUBTASK 05-10-01-860-016, by revising the
``GIVEN LIFE A1-30 RATING (FLIGHT CYCLES)'' for both the LP compressor
(fan) disc assembly P/N BRH10048 and LP compressor (fan) disc assembly
P/N BRH19253 from 33,000 flight cycles to 25,000 flight cycles; and
Checking the lifing of both the LP compressor (fan) disc
assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N
BRH19253 if the relevant compressor (fan) disc assembly is currently
installed or was previously installed, in the BR700-715A1-30 engine
model and operated under the Hawaiian Flight Mission; and
Removing the relevant compressor (fan) disc assembly from
service before further flight, if the consumed life has exceeded the
maximum approved life specified in the ALS.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
[[Page 7644]]
Request To Change the AD Applicability
Rolls-Royce Deutschland requests that we change the AD
applicability from ``This AD applies to Rolls-Royce Deutschland Ltd &
Co KG (RRD), BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30
turbofan engines, with a low pressure (LP) compressor disc assembly,
part number (P/N) BRH10048 or P/N BRH19253, when installed in the
BR700-715A1-30 engine model and operated against the Hawaiian Flight
Mission'' to ``This AD applies to Rolls-Royce Deutschland Ltd & Co KG
(RRD), BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan
engines, with a low pressure (LP) compressor disc assembly, P/N
BRH10048 or P/N BRH19253''. The commenter states that due to fan module
mixing between engine models, the AD is applicable to all relevant fan
assemblies that have, are, could, or will operate against the Hawaiian
Flight Mission, when installed in the BR710-715A1-30 engine.
We agree, and changed the AD applicability.
Request To Combine the Compliance Requirements
Rolls-Royce Deutschland requests that the AD require the operators
check the lifing of the LP compressor disc assemblies, P/N BRH10048 and
P/N BRH19253, using the amended Time Limits Manual (TLM), whether
currently installed or previously installed in the BR700-715A1-30
engine, and operated under the Hawaiian Flight mission.
We partially agree. Operators are responsible for following the
applicable ALS of the TLM to ensure that all critical rotating parts
are replaced within the life limitations specified in the Manual.
However, for clarification purposes, we included this action in the AD.
Other AD Changes
We determined the AD must be complied with, within 25 flight cycles
after the effective date of the AD, instead of 100 flight cycles after
the effective date, as proposed, to expeditiously amend the ALS of the
TLM with life reduction of the relevant fan disk assembly.
We also require removing fan disk assemblies from service before
the next flight if their consumed life has exceeded the maximum
approved life as specified in the ALS of the TLM. All life limited part
must be removed from service before reaching its declared life in the
ALS.
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
We estimate that this AD will affect about 240 engines installed on
aircraft of U.S. registry. This LP compressor (fan) disc assembly
removal does not impose any additional labor costs if performed at the
time of scheduled engine overhaul. We also estimate that it will take
about one work-hour per engine to calculate and re-establish the
achieved cyclic life for an LP compressor (fan) disc assembly, and that
the average labor rate is $80 per work-hour. We estimate that the
prorate cost of the life reduction per engine will be $33,000. Total
cost of this AD is, therefore, $7,939,200.
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 http://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (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:
2009-04-13 Rolls-Royce Deutschland Ltd & Co KG (formerly BMW Rolls-
Royce GmbH, and BMW Rolls-Royce Aero Engines): Amendment 39-15819.
Docket No. FAA-2007-0169; Directorate Identifier 2007-NE-45-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
26, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG
(RRD), BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan
engines, with a low pressure (LP) compressor (fan) disc assembly,
part number (P/N) BRH10048 or P/N BRH19253. These engines are
installed on, but not limited to, McDonnell Douglas Corporation
model 717-200 airplanes.
[[Page 7645]]
Reason
(d) The mandatory continuous airworthiness information (MCAI)
states:
The application of most recent 3D FEM modeling has resulted in
the need to reconsider the disc lives as currently shown in the Time
Limits Manual. The current Post Certification Life Statement for the
low pressure (LP) compressor (fan) disc assembly revises the
Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000
flight cycles for both the BR715 LP (fan) disc assembly P/N BRH10048
and BR715 LP compressor (fan) disc assembly P/N BRH19253, when
installed in the BR700-715A1-30 engine model and operated against
the Hawaiian Flight Mission.
This condition, if not corrected, could result in uncontained
failure of the LP compressor (fan) disc assembly and damage to the
airplane.
Actions and Compliance
(e) Within 25 flight cycles after the effective date of this AD,
do the following actions, unless already done.
(1) Amend the Airworthiness Limitations Section (ALS) of the
Time Limits Manual SUBTASK 05-10-01-860-016, by revising the ``GIVEN
LIFE A1-30 RATING (FLIGHT CYCLES)'' for both the LP compressor (fan)
disc assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N
BRH19253 from 33,000 flight cycles to 25,000 flight cycles.
(2) Check the lifing of both the LP compressor (fan) disc
assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N
BRH19253 if the relevant compressor (fan) disc assembly is currently
installed or was previously installed, in the BR700-715A1-30 engine
model and operated under the Hawaiian Flight Mission.
(3) Remove the relevant compressor (fan) disc assembly from
service before further flight, if the consumed life has exceeded the
maximum approved life specified in the ALS.
Alternative Methods of Compliance (AMOC)
(f) 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 European Aviation Safety Agency AD 2007-0116-
E, dated May 4, 2007, for related 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: [email protected];
telephone (781) 238-7747; fax (781) 238-7199, for more information
about this AD.
Issued in Burlington, Massachusetts, on February 10, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E9-3355 Filed 2-18-09; 8:45 am]
BILLING CODE 4910-13-P