[Federal Register: April 3, 2008 (Volume 73, Number 65)]
[Proposed Rules]
[Page 18220-18222]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03ap08-20]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 18220]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0224; Directorate Identifier 2007-NE-44-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG
(RRD) BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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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) provided by the aviation
authority of Germany to identify and correct an unsafe condition on an
aviation product. The MCAI states the following:
It is necessary to change the limits of the High Pressure (HP)
Turbine Stage 1 and Stage 2 Rotor Discs. The maximum approved life
of these discs is decreased for all flight missions.
This Emergency Airworthiness Directive (EAD) has been raised to
instruct mandatory decreased maximum approved lives in the BR715
Time Limits Manual (TLM) T-715-3BR for the HP Turbine Stage 1 Rotor
Disc for both Part No. BRH20130 and Part No. BRH20131 and of the
High Pressure (HP) Turbine Stage 2 Rotor Disc for both Part No.
BRH19423 and Part No. BRH19427 for all flight missions. The life
limits are decreased by the same proportion for all flight missions,
thus back to birth pro-rata calculations due to the life limit
changes are not necessary.
We are proposing this AD to prevent rotating parts that may have
exceeded their low-cycle fatigue life limits from failing, which could
result in uncontained engine failure and subsequent damage to the
airplane.
DATES: We must receive comments on this proposed AD by May 5, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://
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 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 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: 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.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0224;
Directorate Identifier 2007-NE-44-AD'' at the beginning 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 http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Emergency Airworthiness Directive (EAD) 2007-0152-E, dated June 1,
2007, to correct an unsafe condition for the specified products. The
EASA EAD states:
It is necessary to change the limits of the High Pressure (HP)
Turbine Stage 1 and Stage 2 Rotor Discs. The maximum approved life
of these discs is decreased for all flight missions.
This Emergency Airworthiness Directive (EAD) has been raised to
instruct mandatory decreased maximum approved lives in the BR715
Time Limits Manual (TLM) T-715-3BR for the HP Turbine Stage 1 Rotor
Disc for both Part No. BRH20130 and Part No. BRH20131 and of the
High Pressure (HP) Turbine Stage 2 Rotor Disc for both Part No.
BRH19423 and Part No. BRH19427 for all flight missions. The life
limits are decreased by the same proportion for all flight missions,
thus back to birth pro-rata calculations due to the life limit
changes are not necessary.
You may obtain further information by examining the EASA EAD in the AD
docket.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of
Germany, and is approved for operation in the United States. Pursuant
to our bilateral agreement with Germany, they have notified us of the
unsafe condition described in the EASA EAD and service information
referenced above. We are proposing this AD because we evaluated all
information provided by EASA and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design. This proposed AD would require reducing the published life
limits of HP Turbine Stage 1 Discs, P/Ns BRH20130 and BRH20131, and HP
Turbine Stage 2 Discs, P/Ns BRH19423 and BRH19427.
Costs of Compliance
We estimate that this proposed AD would affect 260 engines
installed on airplanes of U.S. registry. We also estimate that it would
take about 1 work-hour per engine to perform the proposed actions and
that the average labor rate is $80 per work-hour. Based
[[Page 18221]]
on these figures, we estimate the total cost of the proposed AD to U.S.
operators to be $20,800. Our cost estimate is exclusive of possible
warranty coverage.
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, 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 AD:
Rolls-Royce Deutschland Ltd & Co KG: Docket No. FAA-2008-0224;
Directorate Identifier 2007-NE-44-AD.
Comments Due Date
(a) We must receive comments by May 5, 2008.
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.
These engines are installed on, but not limited to, McDonnell
Douglas Model 717-200 airplanes.
Reason
(d) It is necessary to change the limits of the High Pressure
(HP) Turbine Stage 1 and Stage 2 Rotor Discs. The maximum approved
life of these discs is decreased for all flight missions.
This Emergency Airworthiness Directive (EAD) has been raised to
instruct mandatory decreased maximum approved lives in the BR715
Time Limits Manual (TLM) T-715-3BR for the HP Turbine Stage 1 Rotor
Disc for both Part No. BRH20130 and Part No. BRH20131 and of the
High Pressure (HP) Turbine Stage 2 Rotor Disc for both Part No.
BRH19423 and Part No. BRH19427 for all flight missions. The life
limits are decreased by the same proportion for all flight missions,
thus back to birth pro-rata calculations due to the life limit
changes are not necessary.
We are issuing this AD to prevent rotating parts that may have
exceeded their low-cycle fatigue life limits from failing, which
could result in uncontained engine failure and subsequent damage to
the airplane.
Actions and Compliance
(e) No later than 30 days after the effective date of this AD
the following mandatory actions need to be completed for each
individual BR700-715 HP Turbine Stage 1 Rotor Disc for both Part No.
BRH20130 and Part No. BRH20131 and High Pressure (HP) Turbine Stage
2 Rotor Disc for both Part No. BRH19423 and Part No. BRH19427
installed in a BR700-715A1-30, B1-30 or C1-30 engine:
(1) Identify the mandatory decreased maximum approved life for
the HP Turbine Stage 1 and Stage 2 Rotor Discs listed in the tables
below:
High Pressure (HP) Turbine Stage 1 Rotor Disc
----------------------------------------------------------------------------------------------------------------
Mandatory decreased maximum approved life
-----------------------------------------------------------------------------
Engine thrust rating Engine flight mission
Part No. -----------------------------------------------------------------------------
C1-30
A1-30 B1-30 C1-30 A1-30 C1-30 derated
Design Design Design Hawaiian Tropical Tropical
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BRH20130.......................... 15971 13324 10500 17647 3794 7941
BRH20131.......................... 15971 13324 10500 17647 3794 7941
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High Pressure (HP) Turbine Stage 2 Rotor Disc
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Mandatory decreased maximum approved life
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Engine thrust rating Engine flight mission
Part No. -----------------------------------------------------------------------------
C1-30
A1-30 B1-30 C1-30 A1-30 C1-30 derated
Design Design Design Hawaiian Tropical Tropical
----------------------------------------------------------------------------------------------------------------
BRH19423.......................... 21165 17800 13372 1165 10893 13461
BRH19427.......................... 21165 17800 13372 21165 10893 13461
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[[Page 18222]]
Note: Approved lives in the table are in flight cycles
(2) Record the mandatory maximum approved life in the applicable
lifing documentation. It is mandatory to use the values given in the
two tables in step (e)(1) of this AD.
Alternative Methods of Compliance (AMOCs)
(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 EASA Emergency Airworthiness Directive 2007-0152-E,
dated June 1, 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: jason.yang@faa.gov;
telephone (781) 238-7747; fax (781) 238-7199, for more information
about this AD.
Issued in Burlington, Massachusetts, on March 19, 2008.
Ann C. Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-6866 Filed 4-2-08; 8:45 am]
BILLING CODE 4910-13-P