Airworthiness Directives; General Electric Company (GE) CF6-80C2B Series Turbofan Engines, 70382-70384 [2011-29228]
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70382
Federal Register / Vol. 76, No. 219 / Monday, November 14, 2011 / Proposed Rules
inch. The requirements of this AD take
precedence over the actions required in the
service information.
(1) The fuel return line assembly (Cessna
P/N 0500118–49) and the steering tube
assembly (Cessna P/N MC0543022–2C); and
(2) The fuel return line assembly (Cessna
P/N 0500118–49) and the airplane structure.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Wichita Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(k) Related Information
(1) For more information about this AD,
Trenton Shepherd, Aerospace Engineer,
Wichita ACO, FAA, 1801 Airport Road,
Room 100, Wichita, Kansas 67209; phone:
(316) 946–4143; fax: (316) 946–4107; email:
trent.shepherd@faa.gov.
(2) For service information identified in
this AD, contact Cessna Aircraft Company,
Product Support, P.O. Box 7706, Wichita, KS
67277; telephone: (316) 517–6000; fax: (316)
517–8500; email:
Customercare@cessna.textron.com; Internet:
https://www.cessna.com. You may review
copies of the referenced service information
at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of this
material at the FAA, call (816) 329–4148.
Issued in Kansas City, Missouri, on
November 7, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2011–29315 Filed 11–10–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25738; Directorate
Identifier 2006–NE–27–AD]
jlentini on DSK4TPTVN1PROD with PROPOSALS
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF6–80C2B
Series Turbofan Engines
VerDate Mar<15>2010
16:39 Nov 10, 2011
Jkt 226001
2006–NE–27–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.
Examining the AD Docket
Actions Since Existing AD Was Issued
Since we issued AD 2007–12–07 (72
FR 31174, June 6, 2007), we received
two reports of ice crystal condition
flameouts on engines equipped with
ECU software version 8.2.Q1. Prompted
by these reports, GE developed ECU
software version 8.2.R with improved
inclement weather capability, and
enhanced fuel metering valve (FMV)
fault handling logic to reduce the risk of
engine IFSD caused by intermittent
FMV feedback signals.
Subsequently, we received reports of
eight engine IFSD events and four
engine flameout ground events. These
events were caused by ignition system
induced noise creating dual-channel
faults in the CPU. The event engines
were operating with 8.2.Q1 and 8.2.R
versions of ECU software and equipped
with the new generation of front panel
assembly (FPA) and pressure subsystem
(PSS) circuit boards. Prompted by these
reports, GE developed an ECU hardware
fix to eliminate the potential for dualchannel CPU faults due to ignition
system-induced noise. This proposed
AD supersedure removes the affected
ECUs from the fleet. These ECUs, if not
corrected, could result in flameout or
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
(phone: (800) 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION 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; email: tomasz.rakowski@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to all GE CF6–80C2B series
turbofan engines. The existing AD
currently requires installing software
version 8.2.Q1 to the engine electronic
control unit (ECU), which increases the
engine’s margin to flameout. Since we
issued that AD, we have received
reports of additional engine events. This
proposed AD would require the removal
of the affected ECUs from service. We
are proposing this AD to prevent engine
flameout or un-commanded engine inflight shutdown (IFSD) of one or more
engines, leading to an emergency or
forced landing of the airplane.
DATES: We must receive comments on
this proposed AD by January 13, 2012.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, 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.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
SUMMARY:
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–2006–25738; Directorate Identifier
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
Discussion
On May 30, 2007, we issued AD
2007–12–07, Amendment 39–15085 (72
FR 31174, June 6, 2007), for all GE CF6–
80C2B series turbofan engines. That AD
requires installing software version
8.2.Q1 to the ECU, which increases the
engine’s margin to flameout. That AD
was prompted by multiple reports of
flameout events during flight on engines
with an ECU software version preceding
version 8.2.Q1, including reports of
events where all engines simultaneously
experienced a flameout. Investigation
showed that exposure to ice crystals
during flight was associated with these
flameout events. That AD action was
intended to minimize the potential of an
engine flameout event caused by ice
accretion and shedding during flight.
E:\FR\FM\14NOP1.SGM
14NOP1
Federal Register / Vol. 76, No. 219 / Monday, November 14, 2011 / Proposed Rules
un-commanded IFSD of one or more
engines, leading to an emergency or
forced landing of the airplane.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require the
removal from service of certain affected
ECU part numbers (P/Ns) with software
version 8.2.Q1 and prior, which are
susceptible to engine flameouts due to
inclement weather, and those with the
new generation FPA/PSS circuit boards,
which are susceptible to IFSD. The
proposed compliance times for removal
are based on the ECU’s degree of
susceptibility to engine flameout or
IFSD. This proposed AD would also
prevent airplanes from having more
than one ECU with P/N 2121M37P02,
2121M38P02, or 2121M41P02, installed.
Costs of Compliance
We estimate that this proposed AD
would affect 697 GE CF6–80C2B series
turbofan engines installed on airplanes
of U.S. registry. We also estimate that it
would take about 4 work-hours per
engine to perform a removal and
replacement of the ECU, and that the
average labor rate is $85 per work-hour.
A replacement ECU costs about $4,600.
Based on these figures, we estimate the
total cost of the AD to U.S. operators to
be $3,443,180.
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 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),
(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.
70383
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2007–12–07, Amendment 39–15085 (72
FR 31174, June 6, 2007), and adding the
following new AD:
General Electric Company: Docket No. FAA–
2006–25738; Directorate Identifier 2006–
NE–27–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by January 13, 2012.
(b) Affected ADs
This AD supersedes AD 2007–12–07,
Amendment 39–15085 (72 FR 31174, June 6,
2007).
(c) Applicability
This AD applies to General Electric
Company (GE) CF6–80C2B1F, CF6–
80C2B1F1, CF6–80C2B1F2, CF6–80C2B2F,
CF6–80C2B3F, CF6–80C2B4F, CF6–
80C2B5F, CF6–80C2B6F, CF6–80C2B6FA,
CF6–80C2B7F, and CF6–80C2B8F turbofan
engines, including engines marked on the
engine data plate as CF6–80C2B7F1.
(d) Unsafe Condition
This AD results from:
(1) Two reports of engine flameout events
during flight in inclement weather
conditions; and
(2) Eight reports of engine in-flight
shutdown (IFSD) events caused by dualchannel central processing unit (CPU) faults
in the electronic control unit (ECU); and
(3) Four reports of engine flameout ground
events.
(e) We are issuing this AD to prevent
engine flameout or un-commanded engine
IFSD of one or more engines, leading to an
emergency or forced landing of the airplane.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
(f) Compliance
PART 39—AIRWORTHINESS
DIRECTIVES
(1) Remove from service ECUs with part
numbers (P/Ns) listed in Table 1 of this AD,
within 6 months or 450 engine flight cycles
after the effective date of this AD, whichever
occurs first.
1. The authority citation for part 39
continues to read as follows:
Comply with this AD within the
compliance times specified unless already
done.
(g) ECU Removal
jlentini on DSK4TPTVN1PROD with PROPOSALS
TABLE 1—AFFECTED ECU P/NS
1471M63P01
1471M63P06
1471M63P11
1471M63P16
1471M63P25
1471M63P30
1471M63P35
1519M89P04
1519M89P09
1519M89P16
1519M89P21
1519M89P26
VerDate Mar<15>2010
16:39 Nov 10, 2011
1471M63P02
1471M63P07
1471M63P12
1471M63P17
1471M63P26
1471M63P31
1471M63P36
1519M89P05
1519M89P10
1519M89P17
1519M89P22
1820M33P01
Jkt 226001
PO 00000
1471M63P03
1471M63P08
1471M63P13
1471M63P18
1471M63P27
1471M63P32
1519M89P01
1519M89P06
1519M89P13
1519M89P18
1519M89P23
1820M33P02
Frm 00019
Fmt 4702
Sfmt 4702
1471M63P04
1471M63P09
1471M63P14
1471M63P23
1471M63P28
1471M63P33
1519M89P02
1519M89P07
1519M89P14
1519M89P19
1519M89P24
1820M33P03
E:\FR\FM\14NOP1.SGM
14NOP1
1471M63P05
1471M63P10
1471M63P15
1471M63P24
1471M63P29
1471M63P34
1519M89P03
1519M89P08
1519M89P15
1519M89P20
1519M89P25
1820M33P04
70384
Federal Register / Vol. 76, No. 219 / Monday, November 14, 2011 / Proposed Rules
TABLE 1—AFFECTED ECU P/NS—Continued
1820M33P05
1820M33P06
1820M33P07
1820M33P08
months or 4,500 engine flight cycles after the
effective date of this AD, whichever occurs
first.
engine flight cycles after the effective date of
this AD, whichever occurs first.
(3) Remove from service ECUs with P/Ns
listed in Table 2 of this AD, within 60
(2) Remove from service ECUs with P/N
2121M37P01, 2121M37P02, 2121M38P01,
2121M38P02, 2121M41P01 and
2121M41P02, within 14 months or 1,050
1820M33P09
TABLE 2—AFFECTED ECU P/NS
1471M63P37
1519M89P27
1820M33P10
2121M25P01
2121M29P02
1471M63P38
1519M89P28
1820M33P11
2121M25P02
2121M37P03
1471M63P39
1519M89P29
1820M33P12
2121M26P01
2121M38P03
1471M63P40
1519M89P30
1820M33P13
2121M26P02
2121M41P03
(h) Installation Prohibition
(1) After the effective date of this AD, do
not install any ECU P/N listed in Table 1 of
this AD onto any airplane.
(2) After the effective date of this AD, do
not operate any airplane with more than one
ECU, P/N 2121M37P02, 2121M38P02, or
2121M41P02, installed.
(i) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs for this AD. Use
the procedures in 14 CFR 39.19 to make your
request.
across the Black River at Mile 1.0 near
La Crosse, Wisconsin. Drawspan is
currently operated by an onsite bridge
tender, opening on signal following twohour notification. The proposed change
is for drawspan operation by remote
operator, opening immediately upon
demand.
Comments and related material
must reach the Coast Guard on or before
January 13, 2012. A public meeting will
be held on November 29, 2011.
ADDRESSES: You may submit comments
identified by docket number USCG–
2011–0937 using any one of the
following methods:
(1) Federal eRulemaking Portal:
https://www.regulations.gov.
(2) Fax: (202) 493–2251.
(3) 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.
(4) Hand delivery: Same as mail
address above, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The telephone number
is (202) 366–9329. Comments can also
be delivered in person at the public
meeting on November 29, 2011, 6 p.m.
at the Black River Beach Neighborhood
Center, 1433 Rose Street, La Crosse, WI
54603.
To avoid duplication, please use only
one of these four methods. See the
‘‘Public Participation and Request for
Comments’’ portion of the
SUPPLEMENTARY INFORMATION section
below for instructions on submitting
comments.
(j) Related Information
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; email: tomasz.rakowski@faa.gov.
Issued in Burlington, Massachusetts, on
November 3, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2011–29228 Filed 11–10–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
33 CFR Part 117
[Docket No. USCG–2011–0937]
jlentini on DSK4TPTVN1PROD with PROPOSALS
RIN 1625–AA09
Drawbridge Operation Regulation;
Black River, La Crosse, WI
Coast Guard, DHS.
ACTION: Notice of proposed rulemaking
and public meeting.
AGENCY:
The Coast Guard proposes a
change to drawbridge operations for the
Canadian Pacific Railroad Drawbridge
SUMMARY:
VerDate Mar<15>2010
16:39 Nov 10, 2011
Jkt 226001
DATES:
If
you have questions on this proposed
rule, call or email Mr. Eric Washburn,
Bridge Administrator, Western Rivers,
(314) 269–2378, email
Eric.Washburn@uscg.mil. If you have
questions on viewing or submitting
FOR FURTHER INFORMATION CONTACT:
PO 00000
Frm 00020
Fmt 4702
Sfmt 4702
1471M63P42
1519M89P32
1820M33P15
2121M29P01
material to the docket, call Renee V.
Wright, Program Manager, Docket
Operations, telephone (202) 366–9826.
SUPPLEMENTARY INFORMATION:
Public Participation and Request for
Comments
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.
Submitting Comments
If you submit a comment, please
include the docket number for this
rulemaking (USCG–2011–0937),
indicate the specific section of this
document to which each comment
applies, and provide a reason for each
suggestion or recommendation. You
may submit your comments and
material online (https://
www.regulations.gov), or by fax, mail or
hand delivery, but please use only one
of these means. If you submit a
comment online via https://
www.regulations.gov, it will be
considered received by the Coast Guard
when you successfully transmit the
comment. If you fax, hand deliver, or
mail your comment, it will be
considered as having been received by
the Coast Guard when it is received at
the Docket Management Facility. We
recommend that you include your name
and a mailing address, an email address,
or a phone number in the body of your
document so that we can contact you if
we have questions regarding your
submission.
To submit your comment online, go to
https://www.regulations.gov, click on the
‘‘submit a comment’’ box, which will
then become highlighted in blue. In the
‘‘Document Type’’ drop down menu
select ‘‘Proposed Rules’’ and insert
E:\FR\FM\14NOP1.SGM
14NOP1
]]>Agencies
[Federal Register Volume 76, Number 219 (Monday, November 14, 2011)]
[Proposed Rules]
[Pages 70382-70384]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-29228]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25738; Directorate Identifier 2006-NE-27-AD]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-80C2B
Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to all GE CF6-80C2B series turbofan engines. The
existing AD currently requires installing software version 8.2.Q1 to
the engine electronic control unit (ECU), which increases the engine's
margin to flameout. Since we issued that AD, we have received reports
of additional engine events. This proposed AD would require the removal
of the affected ECUs from service. We are proposing this AD to prevent
engine flameout or un-commanded engine in-flight shutdown (IFSD) of one
or more engines, leading to an emergency or forced landing of the
airplane.
DATES: We must receive comments on this proposed AD by January 13,
2012.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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 (phone: (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION 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; email: tomasz.rakowski@faa.gov.
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-2006-
25738; Directorate Identifier 2006-NE-27-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
On May 30, 2007, we issued AD 2007-12-07, Amendment 39-15085 (72 FR
31174, June 6, 2007), for all GE CF6-80C2B series turbofan engines.
That AD requires installing software version 8.2.Q1 to the ECU, which
increases the engine's margin to flameout. That AD was prompted by
multiple reports of flameout events during flight on engines with an
ECU software version preceding version 8.2.Q1, including reports of
events where all engines simultaneously experienced a flameout.
Investigation showed that exposure to ice crystals during flight was
associated with these flameout events. That AD action was intended to
minimize the potential of an engine flameout event caused by ice
accretion and shedding during flight.
Actions Since Existing AD Was Issued
Since we issued AD 2007-12-07 (72 FR 31174, June 6, 2007), we
received two reports of ice crystal condition flameouts on engines
equipped with ECU software version 8.2.Q1. Prompted by these reports,
GE developed ECU software version 8.2.R with improved inclement weather
capability, and enhanced fuel metering valve (FMV) fault handling logic
to reduce the risk of engine IFSD caused by intermittent FMV feedback
signals.
Subsequently, we received reports of eight engine IFSD events and
four engine flameout ground events. These events were caused by
ignition system induced noise creating dual-channel faults in the CPU.
The event engines were operating with 8.2.Q1 and 8.2.R versions of ECU
software and equipped with the new generation of front panel assembly
(FPA) and pressure subsystem (PSS) circuit boards. Prompted by these
reports, GE developed an ECU hardware fix to eliminate the potential
for dual-channel CPU faults due to ignition system-induced noise. This
proposed AD supersedure removes the affected ECUs from the fleet. These
ECUs, if not corrected, could result in flameout or
[[Page 70383]]
un-commanded IFSD of one or more engines, leading to an emergency or
forced landing of the airplane.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require the removal from service of certain
affected ECU part numbers (P/Ns) with software version 8.2.Q1 and
prior, which are susceptible to engine flameouts due to inclement
weather, and those with the new generation FPA/PSS circuit boards,
which are susceptible to IFSD. The proposed compliance times for
removal are based on the ECU's degree of susceptibility to engine
flameout or IFSD. This proposed AD would also prevent airplanes from
having more than one ECU with P/N 2121M37P02, 2121M38P02, or
2121M41P02, installed.
Costs of Compliance
We estimate that this proposed AD would affect 697 GE CF6-80C2B
series turbofan engines installed on airplanes of U.S. registry. We
also estimate that it would take about 4 work-hours per engine to
perform a removal and replacement of the ECU, and that the average
labor rate is $85 per work-hour. A replacement ECU costs about $4,600.
Based on these figures, we estimate the total cost of the AD to U.S.
operators to be $3,443,180.
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
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),
(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.
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 removing airworthiness directive
(AD) 2007-12-07, Amendment 39-15085 (72 FR 31174, June 6, 2007), and
adding the following new AD:
General Electric Company: Docket No. FAA-2006-25738; Directorate
Identifier 2006-NE-27-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by January 13,
2012.
(b) Affected ADs
This AD supersedes AD 2007-12-07, Amendment 39-15085 (72 FR
31174, June 6, 2007).
(c) Applicability
This AD applies to General Electric Company (GE) CF6-80C2B1F,
CF6-80C2B1F1, CF6-80C2B1F2, CF6-80C2B2F, CF6-80C2B3F, CF6-80C2B4F,
CF6-80C2B5F, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, and CF6-80C2B8F
turbofan engines, including engines marked on the engine data plate
as CF6-80C2B7F1.
(d) Unsafe Condition
This AD results from:
(1) Two reports of engine flameout events during flight in
inclement weather conditions; and
(2) Eight reports of engine in-flight shutdown (IFSD) events
caused by dual-channel central processing unit (CPU) faults in the
electronic control unit (ECU); and
(3) Four reports of engine flameout ground events.
(e) We are issuing this AD to prevent engine flameout or un-
commanded engine IFSD of one or more engines, leading to an
emergency or forced landing of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified unless
already done.
(g) ECU Removal
(1) Remove from service ECUs with part numbers (P/Ns) listed in
Table 1 of this AD, within 6 months or 450 engine flight cycles
after the effective date of this AD, whichever occurs first.
Table 1--Affected ECU P/Ns
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
1471M63P01 1471M63P02 1471M63P03 1471M63P04 1471M63P05
1471M63P06 1471M63P07 1471M63P08 1471M63P09 1471M63P10
1471M63P11 1471M63P12 1471M63P13 1471M63P14 1471M63P15
1471M63P16 1471M63P17 1471M63P18 1471M63P23 1471M63P24
1471M63P25 1471M63P26 1471M63P27 1471M63P28 1471M63P29
1471M63P30 1471M63P31 1471M63P32 1471M63P33 1471M63P34
1471M63P35 1471M63P36 1519M89P01 1519M89P02 1519M89P03
1519M89P04 1519M89P05 1519M89P06 1519M89P07 1519M89P08
1519M89P09 1519M89P10 1519M89P13 1519M89P14 1519M89P15
1519M89P16 1519M89P17 1519M89P18 1519M89P19 1519M89P20
1519M89P21 1519M89P22 1519M89P23 1519M89P24 1519M89P25
1519M89P26 1820M33P01 1820M33P02 1820M33P03 1820M33P04
[[Page 70384]]
1820M33P05 1820M33P06 1820M33P07 1820M33P08 1820M33P09
----------------------------------------------------------------------------------------------------------------
(2) Remove from service ECUs with P/N 2121M37P01, 2121M37P02,
2121M38P01, 2121M38P02, 2121M41P01 and 2121M41P02, within 14 months
or 1,050 engine flight cycles after the effective date of this AD,
whichever occurs first.
(3) Remove from service ECUs with P/Ns listed in Table 2 of this
AD, within 60 months or 4,500 engine flight cycles after the
effective date of this AD, whichever occurs first.
Table 2--Affected ECU P/Ns
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
1471M63P37 1471M63P38 1471M63P39 1471M63P40 1471M63P42
1519M89P27 1519M89P28 1519M89P29 1519M89P30 1519M89P32
1820M33P10 1820M33P11 1820M33P12 1820M33P13 1820M33P15
2121M25P01 2121M25P02 2121M26P01 2121M26P02 2121M29P01
2121M29P02 2121M37P03 2121M38P03 2121M41P03 ....................
----------------------------------------------------------------------------------------------------------------
(h) Installation Prohibition
(1) After the effective date of this AD, do not install any ECU
P/N listed in Table 1 of this AD onto any airplane.
(2) After the effective date of this AD, do not operate any
airplane with more than one ECU, P/N 2121M37P02, 2121M38P02, or
2121M41P02, installed.
(i) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures in 14 CFR 39.19 to make your
request.
(j) Related Information
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; email:
tomasz.rakowski@faa.gov.
Issued in Burlington, Massachusetts, on November 3, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2011-29228 Filed 11-10-11; 8:45 am]
BILLING CODE 4910-13-P
