Airworthiness Directives; CFM International, S.A. CFM56-5B1/P; -5B2/P; -5B3/P; -5B3/P1; -5B4/P; -5B4/P1; -5B5/P; -5B6/P; -5B7/P; -5B8/P; and -5B9/P Turbofan Engines, 25597-25599 [E8-10050]
Download as PDF
Federal Register / Vol. 73, No. 89 / Wednesday, May 7, 2008 / Proposed Rules
(c) Statement of disagreement. (1) If
we deny your appeal regarding a request
for amendment, you may file a concise
statement of disagreement with the
denial. We will maintain your statement
with the record you sought to amend,
and any disclosure of the record will
include a copy of your statement of
disagreement.
(2) When practicable and appropriate,
we will provide a copy of the statement
of disagreement to any prior recipients
of the record.
Subpart C—Disclosure of Records
§ 261a.11
Restrictions on disclosure.
We will not disclose any record about
you contained in a system of records to
any person or agency without your prior
written consent unless the disclosure is
authorized by 5 U.S.C. 552a(b).
rwilkins on PROD1PC63 with PROPOSALS
§ 261a.12
Exempt Records.
(a) Information compiled for civil
action. This regulation does not permit
you to have access to any information
compiled in reasonable anticipation of a
civil action or proceeding.
(b) Law enforcement information.
Pursuant to 5 U.S.C. 552a(k)(2), we have
determined that it is necessary to
exempt the systems of records listed
below from the requirements of the
Privacy Act concerning access to
records, accountings of disclosures of
records, maintenance of only relevant
and necessary information in files, and
certain publication provisions,
respectively, 5 U.S.C. 552a(c)(3), (d),
(e)(1), (e)(4)(G), (H) and (I), and (f), and
§§ 261a.5, 261a.7, and 261a.8 of this
part. The exemption applies only to the
extent that a system of records contains
investigatory materials compiled for law
enforcement purposes.
(1) BGFRS-1 Recruiting and
Placement Records.
(2) BGFRS 2 Personnel Security
Systems.
(3) BGFRS 4 General Personnel
Records.
(4) BGFRS 5 EEO Discrimination
Complaint File.
(5) BGFRS 18 Consumer Complaint
Information.
(6) BGFRS 21 Supervisory
Enforcement Actions and Special
Examinations Tracking System.
(7) BGFRS 31 Protective
Information System.
(8) BGFRS 32 Visitor Registration
System.
(9) BGFRS 36 Federal Reserve
Application Name Check System.
(10) BGFRS/OIG 1 OIG
Investigative Records.
(c) Confidential references. Pursuant
to 5 U.S.C. 552a(k)(5), we have
VerDate Aug<31>2005
18:34 May 06, 2008
Jkt 214001
determined that it is necessary to
exempt the systems of records listed
below from the requirements of the
Privacy Act concerning access to
records, accountings of disclosures of
records, maintenance of only relevant
and necessary information in files, and
certain publication provisions,
respectively, 5 U.S.C. 552a(c)(3), (d),
(e)(1), (e)(4)(G), (H) and (I), and (f), and
§§ 261a.5, 261a.7, and 261a.8 of this
part. The exemption applies only to the
extent that a system of records contains
investigatory material compiled to
determine an individual’s suitability,
eligibility, and qualifications for Board
employment or access to classified
information, and the disclosure of such
material would reveal the identity of a
source who furnished information to the
Board under a promise of
confidentiality.
(1) BGFRS-1 Recruiting and
Placement Records.
(2) BGFRS-2 Personnel Security
Systems.
(3) BGFRS-4 General Personnel
Records.
(4) BGFRS-10 General Files on
Board Members.
(5) BGFRS-11 Official General
Files.
(6) BGFRS-13 Federal Reserve
System Bank Supervision Staff
Qualifications.
(7) BGFRS-14 General File on
Federal Reserve Bank and Branch
Directors.
(8) BGFRS-25 Multi-Rater
Feedback Records.
(9) BGFRS/OIG-1 OIG Investigative
Records.
(10) BGFRS/OIG-2 OIG Personnel
Records.
(d) Criminal law enforcement
information. Pursuant to 5 saU.S.C.
552a(j)(2), we have determined that the
OIG Investigative Records (BGFRS/OIG–
1) are exempt from the Privacy Act,
except the provisions regarding
disclosure, the requirement to keep an
accounting, certain publication
requirements, certain requirements
regarding the proper maintenance of
systems of records, and the criminal
penalties for violation of the Privacy
Act, respectively, 5 U.S.C. 552a(b),
(c)(1), and (2), (e)(4)(A) through (F),
(e)(6), (e)(7), (e)(9), (e)(10), (e)(11) and
(i).
By order of the Board of Governors of the
Federal Reserve System, April 30, 2008.
Jennifer J. Johnson,
Secretary of the Board.
[FR Doc. E8–9927 Filed 5–6–08; 8:45 am]
BILLING CODE 6210–01–P
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25597
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0174; Directorate
Identifier 2008–NE–03–AD]
RIN 2120–AA64
Airworthiness Directives; CFM
International, S.A. CFM56–5B1/P; –5B2/
P; –5B3/P; –5B3/P1; –5B4/P; –5B4/P1;
–5B5/P; –5B6/P; –5B7/P; –5B8/P; and
–5B9/P Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
CFM International, S.A. CFM56–5B1/P;
–5B2/P; –5B3/P; –5B3/P1; –5B4/P;
–5B4/P1; –5B5/P; –5B6/P; –5B7/P;
–5B8/P; and –5B9/P turbofan engines.
This proposed AD would require initial
and repetitive eddy current inspections
(ECIs) of certain part number (P/N) lowpressure (LP) turbine rear frames. This
proposed AD results from a refined
lifing analysis by the engine
manufacturer that shows the need to
identify initial and repetitive inspection
thresholds for inspecting certain LP
turbine rear frames. We are proposing
this AD to detect low-cycle-fatigue
cracks in the LP turbine rear frame,
which could result in engine separation
from the airplane, possibly leading to
loss of control of the airplane.
DATES: We must receive any comments
on this proposed AD by July 7, 2008.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• 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.
You can get the service information
identified in this proposed AD from
CFM International, Technical
Publications Department, 1 Neumann
Way, Cincinnati, OH 45215; telephone
(513) 552–2800; fax (513) 552–2816.
FOR FURTHER INFORMATION CONTACT:
Stephen Sheely, Aerospace Engineer,
E:\FR\FM\07MYP1.SGM
07MYP1
25598
Federal Register / Vol. 73, No. 89 / Wednesday, May 7, 2008 / Proposed Rules
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail:
stephen.k.sheely@faa.gov; telephone
(781) 238–7750; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2008–0174; Directorate Identifier 2008–
NE–03–AD’’ in the subject line of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of 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 with FAA
personnel concerning this proposed AD.
Using the search function of the Web
site, anyone can find and read the
comments in any of our dockets,
including, if provided, the name of the
individual who sent the comment (or
signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78).
rwilkins on PROD1PC63 with PROPOSALS
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.
Discussion
CFM International, S.A. performed a
refined lifing analysis that shows the
need to identify initial and repetitive
inspection thresholds for inspecting LP
turbine rear frames, P/Ns 338–171–703–
0; 338–171–704–0; 338–171–705–0; and
338–171–706–0. These parts are
installed in CFM56–5B1/P; –5B2/P;
VerDate Aug<31>2005
18:18 May 06, 2008
Jkt 214001
–5B3/P; –5B3/P1; –5B4/P; –5B4/P1;
–5B5/P; –5B6/P; –5B7/P; –5B8/P; and
–5B9/P turbofan engines. This proposed
AD would require initial and repetitive
ECIs of these LP turbine rear frames.
This condition, if not corrected, could
result in low-cycle-fatigue cracks in the
LP turbine rear frame, engine separation
from the airplane, possibly leading to
loss of control of the airplane.
Relevant Service Information
We have reviewed and approved the
technical contents of CFM International,
S.A. Service Bulletin No. CFM56–5B S/
B 72–0620, Revision 1, dated December
20, 2007, that describes procedures for
performing ECIs of the LP turbine rear
frame.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
type design. We are proposing this AD,
which would require initial and
repetitive ECIs of the affected P/N LP
turbine rear frames.
Costs of Compliance
We estimate that this proposed AD
would affect 426 CFM56–5B series
turbofan engines installed on airplanes
of U.S. registry. We estimate that it
would take about 3 work-hours to
perform an eddy current inspection of
an LP turbine rear frame. The average
labor rate is $80 per work-hour. A
replacement LP turbine rear frame costs
about $102,240. If all 426 LP turbine
rear frames needed replacement, we
estimate the total cost of the proposed
AD to U.S. operators to be $43,656,480.
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
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Frm 00005
Fmt 4702
Sfmt 4702
products identified in this rulemaking
action.
Regulatory Findings
We have 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 that the proposed 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. Would 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. You may get a copy
of this summary at the address listed
under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
CFM International, S.A.: Docket No. FAA–
2008–0174; Directorate Identifier 2008–
NE–03–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by July 7,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to CFM International,
S.A. CFM56–5B1/P; –5B2/P; –5B3/P; –5B3/
P1; –5B4/P; –5B4/P1; –5B5/P; –5B6/P; –5B7/
P; –5B8/P; and –5B9/P turbofan engines with
E:\FR\FM\07MYP1.SGM
07MYP1
Federal Register / Vol. 73, No. 89 / Wednesday, May 7, 2008 / Proposed Rules
low-pressure (LP) turbine rear frames, part
numbers 338–171–703–0; 338–171–704–0;
338–171–705–0; and 338–171–706–0,
installed. These engines are installed on, but
not limited to, Airbus A318, A319, A320, and
A321 series airplanes.
Unsafe Condition
(d) This AD results from a refined lifing
analysis by the engine manufacturer that
shows the need to identify initial and
repetitive inspection thresholds for
inspecting certain LP turbine rear frames. We
are issuing this AD to detect low-cyclefatigue cracks in the LP turbine rear frame,
which could result in engine separation from
the airplane, possibly leading to loss of
control of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
Initial Inspection
(f) Perform an initial eddy current
inspection (ECI) of the LP turbine rear frame
using paragraphs 3.A. through 3.A.(7)(d) of
the Accomplishment Instructions of CFM
International, S.A. Service Bulletin (SB) No.
CFM56–5B S/B 72–0620, Revision 1, dated
December 20, 2007, at the following
compliance times:
(1) For commercial engine applications,
within 25,000 cycles-since-new (CSN) on the
LP turbine rear frame.
(2) For corporate engine applications,
within 19,000 CSN on the LP turbine rear
frame.
(3) For engines with unknown LP turbine
rear frame CSN, within 300 cycles from the
effective date of this AD.
Repetitive Inspections
(g) Perform repetitive ECIs of the LP
turbine rear frame using paragraphs 3.A.
through 3.A.(7)(d) of the Accomplishment
Instructions of CFM International, S.A. SB
No. CFM56–5B S/B 72–0620, Revision 1,
dated December 20, 2007. Use the inspection
intervals in paragraph 3.A.(8) of the
Accomplishment Instructions of CFM
International, S.A. SB No. CFM56–5B S/B
72–0620, Revision 1, dated December 20,
2007.
rwilkins on PROD1PC63 with PROPOSALS
LP Turbine Rear Frame Removal Criteria
(h) Remove LP turbine rear frames from
service that have a single crack length of 2.56
inches (65 mm) or longer, or multiple cracks
with accumulated crack length of 2.56 inches
(65 mm) or longer.
Alternative Methods of Compliance
(i) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(j) European Aviation Safety Agency AD
2007–0221, dated August 13, 2007, also
addresses the subject of this AD.
(k) Contact Stephen Sheely, Aerospace
Engineer, Engine Certification Office, FAA,
VerDate Aug<31>2005
18:18 May 06, 2008
Jkt 214001
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: stephen.k.sheely@faa.gov;
telephone (781) 238–7750; fax (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
April 29, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–10050 Filed 5–6–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0520; Directorate
Identifier 2008–NM–018–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 777–200 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Boeing Model 777–200 series airplanes.
This proposed AD would require
repetitive inspections for any wrinkle in
certain external skin panels, and for
cracking at the fuselage bulkhead shear
tie end fastener locations at certain
stations of section 48 of the fuselage;
and doing related investigative and
corrective actions if necessary. This
proposed AD results from a report of
cracks found in the external skin on the
left and right sides of the Section 48
panel of the fuselage on two airplanes
with skin wrinkles found at two of the
external crack locations. We are
proposing this AD to detect and correct
wrinkles and cracks in certain external
skin panels of Section 48, which could
join together and result in reduced
structural integrity of support structure
for the vertical and horizontal stabilizers
and inability of the airplane to sustain
limit loads.
DATES: We must receive comments on
this proposed AD by June 23, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
PO 00000
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Fmt 4702
Sfmt 4702
25599
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility 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 Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Duong Tran, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6452; fax (425) 917–6590.
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–2008–0520; Directorate Identifier
2008–NM–018–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 because of 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
We have received a report of cracks
found in the external skin on the left
and right sides of the section 48 panel
of the fuselage on two airplanes. There
were ten external skin cracks on one
airplane with 22,732 total flight hours
and 20,286 total flight cycles; the cracks
were 0.20 to 0.50 inch in length at
E:\FR\FM\07MYP1.SGM
07MYP1
Agencies
[Federal Register Volume 73, Number 89 (Wednesday, May 7, 2008)]
[Proposed Rules]
[Pages 25597-25599]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-10050]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0174; Directorate Identifier 2008-NE-03-AD]
RIN 2120-AA64
Airworthiness Directives; CFM International, S.A. CFM56-5B1/P; -
5B2/P; -5B3/P; -5B3/P1; -5B4/P; -5B4/P1; -5B5/P; -5B6/P; -5B7/P; -5B8/
P; and -5B9/P Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for CFM International, S.A. CFM56-5B1/P; -5B2/P; -5B3/P; -5B3/P1; -5B4/
P; -5B4/P1; -5B5/P; -5B6/P; -5B7/P; -5B8/P; and -5B9/P turbofan
engines. This proposed AD would require initial and repetitive eddy
current inspections (ECIs) of certain part number (P/N) low-pressure
(LP) turbine rear frames. This proposed AD results from a refined
lifing analysis by the engine manufacturer that shows the need to
identify initial and repetitive inspection thresholds for inspecting
certain LP turbine rear frames. We are proposing this AD to detect low-
cycle-fatigue cracks in the LP turbine rear frame, which could result
in engine separation from the airplane, possibly leading to loss of
control of the airplane.
DATES: We must receive any comments on this proposed AD by July 7,
2008.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
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.
You can get the service information identified in this proposed AD
from CFM International, Technical Publications Department, 1 Neumann
Way, Cincinnati, OH 45215; telephone (513) 552-2800; fax (513) 552-
2816.
FOR FURTHER INFORMATION CONTACT: Stephen Sheely, Aerospace Engineer,
[[Page 25598]]
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
stephen.k.sheely@faa.gov; telephone (781) 238-7750; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2008-0174; Directorate
Identifier 2008-NE-03-AD'' in the subject line of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of the proposed AD. We will consider
all comments received by the closing date and may amend the proposed AD
in light of 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
with FAA personnel concerning this proposed AD. Using the search
function of the Web site, anyone can find and read the comments in any
of our dockets, including, if provided, the name of the individual who
sent the comment (or signed the comment on behalf of an association,
business, labor union, etc.). You may review the DOT's complete Privacy
Act Statement in the Federal Register published on April 11, 2000 (65
FR 19477-78).
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.
Discussion
CFM International, S.A. performed a refined lifing analysis that
shows the need to identify initial and repetitive inspection thresholds
for inspecting LP turbine rear frames, P/Ns 338-171-703-0; 338-171-704-
0; 338-171-705-0; and 338-171-706-0. These parts are installed in
CFM56-5B1/P; -5B2/P; -5B3/P; -5B3/P1; -5B4/P; -5B4/P1; -5B5/P; -5B6/P;
-5B7/P; -5B8/P; and -5B9/P turbofan engines. This proposed AD would
require initial and repetitive ECIs of these LP turbine rear frames.
This condition, if not corrected, could result in low-cycle-fatigue
cracks in the LP turbine rear frame, engine separation from the
airplane, possibly leading to loss of control of the airplane.
Relevant Service Information
We have reviewed and approved the technical contents of CFM
International, S.A. Service Bulletin No. CFM56-5B S/B 72-0620, Revision
1, dated December 20, 2007, that describes procedures for performing
ECIs of the LP turbine rear frame.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would require
initial and repetitive ECIs of the affected P/N LP turbine rear frames.
Costs of Compliance
We estimate that this proposed AD would affect 426 CFM56-5B series
turbofan engines installed on airplanes of U.S. registry. We estimate
that it would take about 3 work-hours to perform an eddy current
inspection of an LP turbine rear frame. The average labor rate is $80
per work-hour. A replacement LP turbine rear frame costs about
$102,240. If all 426 LP turbine rear frames needed replacement, we
estimate the total cost of the proposed AD to U.S. operators to be
$43,656,480.
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 have 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 that the proposed 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. Would 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. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration 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
airworthiness directive:
CFM International, S.A.: Docket No. FAA-2008-0174; Directorate
Identifier 2008-NE-03-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by July 7,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to CFM International, S.A. CFM56-5B1/P; -
5B2/P; -5B3/P; -5B3/P1; -5B4/P; -5B4/P1; -5B5/P; -5B6/P; -5B7/P; -
5B8/P; and -5B9/P turbofan engines with
[[Page 25599]]
low-pressure (LP) turbine rear frames, part numbers 338-171-703-0;
338-171-704-0; 338-171-705-0; and 338-171-706-0, installed. These
engines are installed on, but not limited to, Airbus A318, A319,
A320, and A321 series airplanes.
Unsafe Condition
(d) This AD results from a refined lifing analysis by the engine
manufacturer that shows the need to identify initial and repetitive
inspection thresholds for inspecting certain LP turbine rear frames.
We are issuing this AD to detect low-cycle-fatigue cracks in the LP
turbine rear frame, which could result in engine separation from the
airplane, possibly leading to loss of control of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Initial Inspection
(f) Perform an initial eddy current inspection (ECI) of the LP
turbine rear frame using paragraphs 3.A. through 3.A.(7)(d) of the
Accomplishment Instructions of CFM International, S.A. Service
Bulletin (SB) No. CFM56-5B S/B 72-0620, Revision 1, dated December
20, 2007, at the following compliance times:
(1) For commercial engine applications, within 25,000 cycles-
since-new (CSN) on the LP turbine rear frame.
(2) For corporate engine applications, within 19,000 CSN on the
LP turbine rear frame.
(3) For engines with unknown LP turbine rear frame CSN, within
300 cycles from the effective date of this AD.
Repetitive Inspections
(g) Perform repetitive ECIs of the LP turbine rear frame using
paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment
Instructions of CFM International, S.A. SB No. CFM56-5B S/B 72-0620,
Revision 1, dated December 20, 2007. Use the inspection intervals in
paragraph 3.A.(8) of the Accomplishment Instructions of CFM
International, S.A. SB No. CFM56-5B S/B 72-0620, Revision 1, dated
December 20, 2007.
LP Turbine Rear Frame Removal Criteria
(h) Remove LP turbine rear frames from service that have a
single crack length of 2.56 inches (65 mm) or longer, or multiple
cracks with accumulated crack length of 2.56 inches (65 mm) or
longer.
Alternative Methods of Compliance
(i) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(j) European Aviation Safety Agency AD 2007-0221, dated August
13, 2007, also addresses the subject of this AD.
(k) Contact Stephen Sheely, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
stephen.k.sheely@faa.gov; telephone (781) 238-7750; fax (781) 238-
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on April 29, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-10050 Filed 5-6-08; 8:45 am]
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