Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 Turbofan Engines, 18220-18222 [E8-6866]
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<![CDATA[
18220
Proposed Rules
Federal Register
Vol. 73, No. 65
Thursday, April 3, 2008
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.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0224; Directorate
Identifier 2007–NE–44–AD]
RIN 2120–AA64
Examining the AD Docket
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG (RRD)
BR700–715A1–30, BR700–715B1–30,
and BR700–715C1–30 Turbofan
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
provided by the aviation authority of
Germany to identify and correct an
unsafe condition on an aviation
product. The MCAI states the following:
mstockstill on PROD1PC66 with PROPOSALS
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.
VerDate Aug<31>2005
16:52 Apr 02, 2008
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
ADDRESSES:
Jkt 214001
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is the
same as the Mail address provided in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
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 https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
PO 00000
Frm 00001
Fmt 4702
Sfmt 4702
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
E:\FR\FM\03APP1.SGM
03APP1
18221
Federal Register / Vol. 73, No. 65 / Thursday, April 3, 2008 / Proposed Rules
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.
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.
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:
§ 39.13
[Amended]
2. The FAA amends § 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.
A1–30
Design
BRH20130 ........................................................................
BRH20131 ........................................................................
B1–30
Design
15971
15971
C1–30
Design
13324
13324
A1–30
Hawaiian
10500
10500
C1–30
Tropical
17647
17647
3794
3794
C1–30
derated
Tropical
7941
7941
HIGH PRESSURE (HP) TURBINE STAGE 2 ROTOR DISC
mstockstill on PROD1PC66 with PROPOSALS
Mandatory decreased maximum approved life
Engine thrust rating
Engine flight mission
Part No.
A1–30
Design
BRH19423 ........................................................................
BRH19427 ........................................................................
VerDate Aug<31>2005
16:52 Apr 02, 2008
Jkt 214001
PO 00000
Frm 00002
21165
21165
Fmt 4702
B1–30
Design
C1–30
Design
17800
17800
Sfmt 4702
13372
13372
E:\FR\FM\03APP1.SGM
A1–30
Hawaiian
1165
21165
03APP1
C1–30
Tropical
10893
10893
C1–30
derated
Tropical
13461
13461
18222
Federal Register / Vol. 73, No. 65 / Thursday, April 3, 2008 / Proposed Rules
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
and AIM, Federal Aviation
Administration, 800 Independence
Avenue, SW., Washington, DC 20591;
telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
History
On March 12, 2008, an NPRM was
published in the Federal Register for
Airspace Docket No. 08–AAL–6, FAA
Docket No. FAA–2008–0111 (73 FR
13159), revoking Area Navigation Jet
Routes J–889R and J–996R in Alaska.
Subsequent to publication, it was found
that the FAA docket number was
incorrect; the correct number is FAA–
2008–0180. In addition, the reference to
one Area Navigation Jet Route was
incorrectly stated in the title of the
NPRM. The correct Jet Route should
have stated J–888R, instead of J–889R.
This action corrects those errors.
Correction to Final Rule
Accordingly, pursuant to the
authority delegated to me, the FAA
docket number and the title of the
NPRM as published in the Federal
Register on March 12, 2008 (73 FR
13159), Airspace Docket No. 08–AAL–6,
FAA Docket No. FAA–2008–0111, and
incorporated by reference in 14 CFR
71.1, is corrected as follows:
DEPARTMENT OF TRANSPORTATION
§ 71.1
Federal Aviation Administration
On page 13159, correct the FAA
docket number and the title to read as
follows:
*
*
*
*
*
14 CFR Part 71
[Docket FAA No. FAA–2008–0180; Airspace
Docket No. 08–AAL–6]
*
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM); correction.
AGENCY:
This action corrects a notice
of proposed rulemaking (NPRM)
published in the Federal Register March
12, 2008 (73 FR 13159), Airspace Docket
No. 08–AAL–6, FAA Docket No. FAA–
2008–0111. In that rule, the FAA docket
number is incorrect. The correct FAA
docket number should state FAA–2008–
0180, instead of FAA–2008–0111. In
addition, a typographical error to one Jet
Route was made in the title. The title of
the NPRM should reference Jet Route J–
888R, instead of J–889R. This action
corrects those errors.
DATES: Effective Date: 0901 UTC, April
3, 2008.
FOR FURTHER INFORMATION CONTACT: Ken
McElroy, Airspace and Rules Group,
Office of System Operations Airspace
mstockstill on PROD1PC66 with PROPOSALS
VerDate Aug<31>2005
16:52 Apr 02, 2008
Jkt 214001
Docket No. FAA–2008–0180
Proposed Revocation of Area Navigation Jet
Routes J–888R and J–996R; Alaska
Proposed Revocation of Area
Navigation Jet Routes J–888R and
J–996R; Alaska
SUMMARY:
[Amended]
*
*
*
*
Issued in Washington, DC, on March 27,
2008.
Stephen L. Rohring,
Acting Manager, Airspace and Rules Group.
[FR Doc. E8–6935 Filed 4–2–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
the navigable waters of San Diego Bay,
CA in support of the Red Bull Air Race.
The safety zone would be necessary to
provide for the safety of the crew,
spectators, participants in the event,
participating vessels and other vessels
and users of the waterway. Persons and
vessels would be prohibited from
entering into, transiting through, or
anchoring within this safety zone unless
authorized by the Captain of the Port or
his designated representative.
DATES: Comments and related material
must reach the Coast Guard on or before
April 11, 2008.
ADDRESSES: You may submit comments
identified by Coast Guard docket
number USCG–2008–0162 to the Docket
Management Facility at the U.S.
Department of Transportation. To avoid
duplication, please use only one of the
following methods:
(1) Online: https://
www.regulations.gov.
(2) Mail: Docket Management Facility
(M–30), U.S. Department of
Transportation, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590–
0001.
(3) Hand delivery: Room W12–140 on
the Ground Floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The telephone
number is 202–366–9329.
(4) Fax: 202–493–2251.
FOR FURTHER INFORMATION CONTACT: If
you have questions on this proposed
rule, call Petty Officer Adam Proctor,
Waterways Management Division, U.S.
Coast Guard Sector San Diego, CA, at
telephone (619) 278–7277. If you have
questions on viewing or submitting
material to the docket, call Renee V.
Wright, Program Manager, Docket
Operations, telephone 202–366–9826.
SUPPLEMENTARY INFORMATION:
Public Participation and Request for
Comments
AGENCY:
We encourage you to participate in
this rulemaking by submitting
comments and related materials. All
comments received will be posted,
without change, to https://
www.regulations.gov and will include
any personal information you have
provided. We have an agreement with
the Department of Transportation (DOT)
to use the Docket Management Facility.
Please see DOT’s ‘‘Privacy Act’’
paragraph below.
ACTION:
Submitting Comments
Coast Guard
33 CFR Part 165
[Docket No. USCG–2008–0162]
RIN 1625–AA00
Safety Zone; Red Bull Air Race; San
Diego Bay, San Diego, CA
Coast Guard, DHS.
Notice of proposed rulemaking.
SUMMARY: The Coast Guard proposes
establishing a temporary safety zone on
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
If you submit a comment, please
include the docket number for this
E:\FR\FM\03APP1.SGM
03APP1
]]>Agencies
[Federal Register Volume 73, Number 65 (Thursday, April 3, 2008)]
[Proposed Rules]
[Pages 18220-18222]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-6866]
========================================================================
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.
========================================================================
Federal Register / Vol. 73, No. 65 / Thursday, April 3, 2008 /
Proposed Rules
[[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).
-----------------------------------------------------------------------
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 https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor,
Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: 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 https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued 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
----------------------------------------------------------------------------------------------------------------
BRH20130.......................... 15971 13324 10500 17647 3794 7941
BRH20131.......................... 15971 13324 10500 17647 3794 7941
----------------------------------------------------------------------------------------------------------------
High Pressure (HP) Turbine Stage 2 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
----------------------------------------------------------------------------------------------------------------
BRH19423.......................... 21165 17800 13372 1165 10893 13461
BRH19427.......................... 21165 17800 13372 21165 10893 13461
----------------------------------------------------------------------------------------------------------------
[[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
