Airworthiness Directives; General Electric Company CF34-10E2A1; CF34-10E5; CF34-10E5A1; CF34-10E6; CF34-10E6A1; CF34-10E7; and CF34-10E7-B Turbofan Engines, 52215-52217 [2011-21313]
Download as PDF
Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
(b) None.
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Effective Date
(a) This AD is effective September 26,
2011.
1. The authority citation for part 39
continues to read as follows:
■
Affected ADs
[Amended]
2011–18–01 General Electric Company:
Amendment 39–16783; Docket No.
FAA–2010–0998; Directorate Identifier
2010–NE–29–AD.
PART 39—AIRWORTHINESS
DIRECTIVES
52215
Applicability
(c) This AD applies to General Electric
Company (GE) CF6–45A, CF6–45A2, CF6–
50A, CF6–50C, CF6–50CA, CF6–50C1, CF6–
50C2, CF6–50C2B, CF6–50C2D, CF6–50E,
CF6–50E1, and CF6–50E2 series turbofan
engines, including engines marked on the
engine data plate as CF6–50C2–F and CF6–
50C2–R, with a low-pressure turbine (LPT)
rotor stage 3 disk that has a part number (P/
N) listed in Table 1 of this AD installed.
TABLE 1—LPT ROTOR STAGE 3 DISK P/NS
1473M90P01
1479M75P01
1479M75P05
1479M75P09
9061M23P06
9061M23P10
9061M23P16
1473M90P02
1479M75P02
1479M75P06
1479M75P11
9061M23P07
9061M23P12
9224M75P01
1473M90P03
1479M75P03
1479M75P07
1479M75P13
9061M23P08
9061M23P14
Unsafe Condition
(d) This AD results from seven reports of
uncontained failures of LPT rotor stage 3
disks and eight reports of cracked LPT rotor
stage 3 disks found during shop visit
inspections. We are issuing this AD to
prevent LPT rotor separation, which could
result in an uncontained engine failure and
damage to the airplane.
involving the separation of the turbine midframe forward flange from the compressor
rear frame aft flange, except that the
separation of these engine flanges solely for
the purposes of transportation without
subsequent engine maintenance does not
constitute an engine shop visit.
Compliance
(e) You are responsible for having the
actions required by this AD performed at
each shop visit after the effective date of this
AD, at which the LPT module assembly is
separated from the engine.
(j) 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.
Initial Inspection
(f) At the next shop visit after the effective
date of this AD, clean and fluorescentpenetrant inspect the LPT rotor stage 3 disk
forward spacer arm, including the use of a
wet-abrasive blast to eliminate residual or
background fluorescence before inspecting.
You can find guidance on cleaning the disk
and performing the FPI in the CF6–50 Engine
Manual, GEK 50481 72–57–02.
(k) For more information about this AD,
contact Tomasz Rakowski, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; phone: (781) 238–7735; fax: (781)
238–7199; e-mail: tomasz.rakowski@faa.gov.
mstockstill on DSK4VPTVN1PROD with RULES
Repetitive Inspection
(g) Thereafter, clean and inspect the LPT
rotor stage 3 disk forward spacer arm, as
specified in paragraph (f) of this AD, at each
engine shop visit that occurs after 1,000
cycles since the last FPI of the LPT rotor
stage 3 disk forward spacer arm.
(h) If a crack or a band of fluorescence is
present, remove the disk from service.
Alternative Methods of Compliance
Related Information
Material Incorporated by Reference
(l) None.
Issued in Burlington, Massachusetts on
August 15, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2011–21312 Filed 8–19–11; 8:45 am]
BILLING CODE 4910–13–P
Definitions
(i) For the purpose of this AD:
(1) The LPT module assembly is defined as
consisting of turbine mid-frame, LPT stage 1
nozzle, LPT stator cases and vanes, LPT
rotor, and turbine rear frame.
(2) An engine shop visit is the induction
of an engine into the shop for maintenance
VerDate Mar<15>2010
18:50 Aug 19, 2011
Jkt 223001
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
1473M90P04
1479M75P04
1479M75P08
1479M75P14
9061M23P09
9061M23P15
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0187; Directorate
Identifier 2011–NE–07–AD; Amendment 39–
16784; AD 2011–18–02]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company CF34–10E2A1;
CF34–10E5; CF34–10E5A1; CF34–
10E6; CF34–10E6A1; CF34–10E7; and
CF34–10E7–B Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above with certain part
number (P/N) fan rotor spinners
installed. This AD requires removing
from service certain fan rotor blade
retainers, and removing from service the
fan rotor spinner support that was
installed with those fan rotor blade
retainers. This AD was prompted by a
fan rotor spinner support found cracked
at the attachment lugs. We are issuing
this AD to prevent high-cycle fatigue
cracking of the fan rotor spinner support
attachment lugs, leading to separation of
the fan rotor spinner assembly,
uncontained failure of the engine, and
damage to the airplane.
DATES: This AD is effective September
26, 2011.
SUMMARY:
E:\FR\FM\22AUR1.SGM
22AUR1
52216
Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations
For service information
identified in this AD, contact GE–
Aviation, M/D Rm. 285, One Neumann
Way, Cincinnati, OH 45215, phone:
513–552–3272; e-mail:
geae.aoc@ge.com. You may review
copies of the referenced service
information at the FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
ADDRESSES:
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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: John
Frost, Aerospace Engineer, Engine
Certification Office, FAA, 12 New
England Executive Park, Burlington, MA
01803; phone: 781–238–7756; fax: 781–
238–7199; e-mail: john.frost@faa.gov.
SUPPLEMENTARY INFORMATION:
mstockstill on DSK4VPTVN1PROD with RULES
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 published in the Federal
Register on May 11, 2011 (76 FR 27282).
Investigation of a General Electric
Company CF34–10E turbofan engine
experiencing high fan frame vibrations
led to removal of the fan rotor spinner.
Eight of the twelve attachment lugs on
the fan rotor spinner support were
found cracked. The cause of the
vibration was determined to be a nonsynchronous vibration induced by a
spinner redesign that removed an
interference between the fan blade
retainers and the spinner. That NPRM
proposed to require removing from
service certain fan rotor blade retainers,
and removing from service the fan rotor
spinner support that was installed with
those fan rotor blade retainers. We are
issuing this AD to prevent high-cycle
fatigue cracking of the fan rotor spinner
support attachment lugs, leading to
separation of the fan rotor spinner
assembly, uncontained failure of the
engine, and damage to the airplane.
VerDate Mar<15>2010
17:10 Aug 19, 2011
Jkt 223001
Comments
We gave the public the opportunity to
participate in developing this AD. We
received one comment which is
presented below.
Request for Compliance Clarification
One commenter, Regionla Compagnie
Aerienne Europeene, requests that we
clarify the AD as to what parts are
allowed to be reinstalled when affected
parts are removed for either scheduled
or unscheduled maintenance before the
AD compliance time is reached.
We do not agree. When the affected
parts are removed from the engine,
paragraphs (h) and (i) of this AD are
clear that those parts are not to be
reinstalled into the engine. Any FAAapproved part except those prohibited
by paragraphs (h) and (i), is eligible for
installation. We did not change the AD.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Costs of Compliance
We estimate that this AD will affect
164 engines installed on airplanes of
U.S. registry. We also estimate that it
will take about 2 work-hours per engine
to perform the actions required by this
AD, and that the average labor rate is
$85 per work-hour. If all removed parts
get replaced, required parts will cost
about $10,458 per engine. Based on
these figures, we estimate the total cost
of the AD to U.S. operators to be
$1,742,992.
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.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
Regulatory Findings
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 that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 (AD):
■
2011–18–02 General Electric Company:
Amendment 39–16784 ; Docket No.
FAA–2011–0187; Directorate Identifier
2011–NE–07–AD.
Effective Date
(a) This AD is effective September 26,
2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric
Company (GE) CF34–10E2A1; CF34–10E5;
CF34–10E5A1; CF34–10E6; CF34–10E6A1;
CF34–10E7; and CF34–10E7–B turbofan
engines, with a fan rotor spinner part number
(P/N) 2050M34G03; 2050M34G04;
2050M34G05; 2050M34G06; 2437M60G01; or
2437M60G02, installed.
Unsafe Condition
(d) This AD was prompted by a fan rotor
spinner support found cracked at the
E:\FR\FM\22AUR1.SGM
22AUR1
Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations
attachment lugs. We are issuing this AD to
prevent high-cycle fatigue cracking of the fan
rotor spinner support attachment lugs,
leading to separation of the fan rotor spinner
assembly, uncontained failure of the engine,
and damage to the airplane.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
52217
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
Compliance
(e) Comply with this AD within 1,800
hours-in-service after the effective date of
this AD, unless already done.
[Docket No. FAA–2011–0385; Directorate
Identifier 2010–NM–256–AD; Amendment
39–16780; AD 2011–17–16]
RIN 2120–AA64
Discussion
Airworthiness Directives; Airbus Model
A330–200, A330–300, A340–300, A340–
500, and A340–600 Series Airplanes
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 April 26, 2011 (76 FR
23218). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
Removal of Fan Rotor Blade Retainers
(f) Remove from service the 24 fan rotor
blade retainers, P/N 2050M56P02.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
Removal of Fan Rotor Spinner Support
(g) Remove from service the fan rotor
spinner support that operated with the fan
rotor blade retainers removed in paragraph (f)
of this AD.
Installation Prohibition
(h) After the effective date of this AD, do
not install any fan rotor blade retainer, P/N
2050M56P02, into any engine. Do not
attempt to repair, make serviceable, or reinstall, this part.
(i) After the effective date of this AD, do
not install any fan rotor spinner support
removed in paragraph (g) of this AD, into any
engine. Do not attempt to repair, make
serviceable, or re-install, this part.
Alternative Methods of Compliance
(AMOCs)
(j) 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.
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:
SUMMARY:
During a Back-up Control Module (BCM)
retrofit campaign * * *, some BCMs have
been found with loose gyrometer screws.
* * * When the aeroplane is in control
back up configuration (considered to be an
extremely remote case), an oscillation of the
BCM output order may cause degradation of
the BCM piloting laws, potentially leading to
erratic motion of the rudder and possible
subsequent impact on the Dutch Roll, which
constitutes an unsafe condition.
*
(k) For more information about this AD,
contact John Frost, Aerospace Engineer,
Engine Certification Office, FAA, 12 New
England Executive Park, Burlington, MA
01803; phone: 781–238–7756; fax: 781–238–
7199; e-mail: john.frost@faa.gov.
(l) Refer to GE Service Bulletin No. CF34–
10E S/B 72–0186, for related information.
Contact GE–Aviation, M/D Rm. 285, One
Neumann Way, Cincinnati, OH 45215,
phone: 513–552–3272; e-mail:
geae.aoc@ge.com, for a copy of this service
information. You may review copies of the
referenced service information at the FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
mstockstill on DSK4VPTVN1PROD with RULES
Related Information
* * * [S]everal Pedal Feel Trim Units
(PFTU) have been found with loose or broken
screws during the accomplishment of
maintenance tasks on A330 fitted with
electrical rudder and A340–600. The loose or
failed screws could lead to the loss of the
coupling between the Rotary Variable
Differential Transducer (RVDT) shaft and the
PFTU shaft, and consequently to a potential
rudder runaway when the BCM is activated.
Issued in Burlington, Massachusetts, on
August 15, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2011–21313 Filed 8–19–11; 8:45 am]
BILLING CODE 4910–13–P
VerDate Mar<15>2010
17:10 Aug 19, 2011
Jkt 223001
*
*
*
*
*
*
*
*
*
The unsafe condition is loss of control
of the airplane. We are issuing this AD
to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective
September 26, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 26, 2011.
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.
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
SUPPLEMENTARY INFORMATION:
During a Back-up Control Module (BCM)
retrofit campaign in accordance with
[European Aviation Safety Agency] (EASA)
AD 2006–0313 requirements, some BCMs
have been found with loose gyrometer
screws.
The gyrometer is installed on the DELRIN
plate by internal screws and the DELRIN
plate is installed on BCM casing by external
screws.
Investigations done by the BCM
manufacturer SAGEM have shown that the
root cause of these events is a lack of design
robustness of the BCM[.] When the aeroplane
is in control back up configuration
(considered to be an extremely remote case),
an oscillation of the BCM output order may
cause degradation of the BCM piloting laws,
potentially leading to erratic motion of the
rudder and possible subsequent impact on
the Dutch Roll, which constitutes an unsafe
condition.
EASA AD 2008–0131 was issued to
prohibit aeroplane dispatch with FCPC3
[flight control primary computer] inoperative
(from GO IF to NO GO) as an interim
solution, limited to A330 and A340–300
fitted with electrical rudder.
After EASA AD 2008–0131 issuance,
several Pedal Feel Trim Units (PFTU) have
been found with loose or broken screws
during the accomplishment of maintenance
tasks on A330 fitted with electrical rudder
and A340–600. The loose or failed screws
could lead to the loss of the coupling
between the Rotary Variable Differential
Transducer (RVDT) shaft and the PFTU shaft,
and consequently to a potential rudder
runaway when the BCM is activated.
EASA AD 2009–0153 retained the
requirements of EASA AD 2008–0131 and
extended the applicability to A340–500/600
aeroplanes.
This [EASA] AD, which supersedes EASA
AD 2009–0153 retaining its requirements,
requires the installation of:
—a new BCM on A330 and A340–200/–300
series aeroplanes fitted with electrical
rudder, and
—an improved PFTU on A330 and A340–
200/–300 series aeroplanes fitted with an
electrical rudder and A340–500/&600
series aeroplanes,
E:\FR\FM\22AUR1.SGM
22AUR1
Agencies
[Federal Register Volume 76, Number 162 (Monday, August 22, 2011)]
[Rules and Regulations]
[Pages 52215-52217]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-21313]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0187; Directorate Identifier 2011-NE-07-AD;
Amendment 39-16784; AD 2011-18-02]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF34-10E2A1;
CF34-10E5; CF34-10E5A1; CF34-10E6; CF34-10E6A1; CF34-10E7; and CF34-
10E7-B 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 with certain part number (P/N) fan rotor spinners
installed. This AD requires removing from service certain fan rotor
blade retainers, and removing from service the fan rotor spinner
support that was installed with those fan rotor blade retainers. This
AD was prompted by a fan rotor spinner support found cracked at the
attachment lugs. We are issuing this AD to prevent high-cycle fatigue
cracking of the fan rotor spinner support attachment lugs, leading to
separation of the fan rotor spinner assembly, uncontained failure of
the engine, and damage to the airplane.
DATES: This AD is effective September 26, 2011.
[[Page 52216]]
ADDRESSES: For service information identified in this AD, contact GE-
Aviation, M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, phone:
513-552-3272; e-mail: geae.aoc@ge.com. You may review copies of the
referenced service information at the FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA. For
information on the availability of this material at the FAA, call 781-
238-7125.
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 AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: John Frost, Aerospace Engineer, Engine
Certification Office, FAA, 12 New England Executive Park, Burlington,
MA 01803; phone: 781-238-7756; fax: 781-238-7199; e-mail:
john.frost@faa.gov.
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 published in the Federal Register on May 11, 2011 (76 FR
27282). Investigation of a General Electric Company CF34-10E turbofan
engine experiencing high fan frame vibrations led to removal of the fan
rotor spinner. Eight of the twelve attachment lugs on the fan rotor
spinner support were found cracked. The cause of the vibration was
determined to be a non-synchronous vibration induced by a spinner
redesign that removed an interference between the fan blade retainers
and the spinner. That NPRM proposed to require removing from service
certain fan rotor blade retainers, and removing from service the fan
rotor spinner support that was installed with those fan rotor blade
retainers. We are issuing this AD to prevent high-cycle fatigue
cracking of the fan rotor spinner support attachment lugs, leading to
separation of the fan rotor spinner assembly, uncontained failure of
the engine, and damage to the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. We received one comment which is presented below.
Request for Compliance Clarification
One commenter, Regionla Compagnie Aerienne Europeene, requests that
we clarify the AD as to what parts are allowed to be reinstalled when
affected parts are removed for either scheduled or unscheduled
maintenance before the AD compliance time is reached.
We do not agree. When the affected parts are removed from the
engine, paragraphs (h) and (i) of this AD are clear that those parts
are not to be reinstalled into the engine. Any FAA-approved part except
those prohibited by paragraphs (h) and (i), is eligible for
installation. We did not change the AD.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting the
AD as proposed.
Costs of Compliance
We estimate that this AD will affect 164 engines installed on
airplanes of U.S. registry. We also estimate that it will take about 2
work-hours per engine to perform the actions required by this AD, and
that the average labor rate is $85 per work-hour. If all removed parts
get replaced, required parts will cost about $10,458 per engine. Based
on these figures, we estimate the total cost of the AD to U.S.
operators to be $1,742,992.
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
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 that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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 airworthiness
directive (AD):
2011-18-02 General Electric Company: Amendment 39-16784 ; Docket No.
FAA-2011-0187; Directorate Identifier 2011-NE-07-AD.
Effective Date
(a) This AD is effective September 26, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company (GE) CF34-
10E2A1; CF34-10E5; CF34-10E5A1; CF34-10E6; CF34-10E6A1; CF34-10E7;
and CF34-10E7-B turbofan engines, with a fan rotor spinner part
number (P/N) 2050M34G03; 2050M34G04; 2050M34G05; 2050M34G06;
2437M60G01; or 2437M60G02, installed.
Unsafe Condition
(d) This AD was prompted by a fan rotor spinner support found
cracked at the
[[Page 52217]]
attachment lugs. We are issuing this AD to prevent high-cycle
fatigue cracking of the fan rotor spinner support attachment lugs,
leading to separation of the fan rotor spinner assembly, uncontained
failure of the engine, and damage to the airplane.
Compliance
(e) Comply with this AD within 1,800 hours-in-service after the
effective date of this AD, unless already done.
Removal of Fan Rotor Blade Retainers
(f) Remove from service the 24 fan rotor blade retainers, P/N
2050M56P02.
Removal of Fan Rotor Spinner Support
(g) Remove from service the fan rotor spinner support that
operated with the fan rotor blade retainers removed in paragraph (f)
of this AD.
Installation Prohibition
(h) After the effective date of this AD, do not install any fan
rotor blade retainer, P/N 2050M56P02, into any engine. Do not
attempt to repair, make serviceable, or re-install, this part.
(i) After the effective date of this AD, do not install any fan
rotor spinner support removed in paragraph (g) of this AD, into any
engine. Do not attempt to repair, make serviceable, or re-install,
this part.
Alternative Methods of Compliance (AMOCs)
(j) 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
(k) For more information about this AD, contact John Frost,
Aerospace Engineer, Engine Certification Office, FAA, 12 New England
Executive Park, Burlington, MA 01803; phone: 781-238-7756; fax: 781-
238-7199; e-mail: john.frost@faa.gov.
(l) Refer to GE Service Bulletin No. CF34-10E S/B 72-0186, for
related information. Contact GE-Aviation, M/D Rm. 285, One Neumann
Way, Cincinnati, OH 45215, phone: 513-552-3272; e-mail:
geae.aoc@ge.com, for a copy of this service information. You may
review copies of the referenced service information at the FAA,
Engine & Propeller Directorate, 12 New England Executive Park,
Burlington, MA. For information on the availability of this material
at the FAA, call 781-238-7125.
Issued in Burlington, Massachusetts, on August 15, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2011-21313 Filed 8-19-11; 8:45 am]
BILLING CODE 4910-13-P