Airworthiness Directives; General Electric Company (GE) CF34-10E Series Turbofan Engines, 32775-32776 [07-2843]
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Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25896; Directorate
Identifier 2006–NE–33–AD; Amendment 39–
15093; AD 2007–12–15]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF34–10E
Series Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is superseding an
existing airworthiness directive (AD) for
GE CF34–10E series turbofan engines.
That AD currently requires removing
the fuel inlet strainer from main fuel
pump (MFP) part number (P/N)
2043M12P03, installing a certain
replacement flange as an interim repair,
remarking the MFP to P/N 2043M12P04,
and performing initial and repetitive
visual inspections of the main fuel filter.
This AD requires removing MFPs, P/Ns
2043M12P03, 2043M12P04, 837600–3,
and 837600–4, from service and
installing an improved MFP with a
different P/N. This AD results from GE
determining that the cause of MFP fuel
strainer failure is a design problem with
the strainer. We are issuing this AD to
prevent engine in-flight shutdown due
to MFP malfunctions.
DATES: This AD becomes effective July
19, 2007.
ADDRESSES: You can get the service
information identified in this AD from
General Electric Company via Lockheed
Martin Technology Services, 10525
Chester Road, Suite C, Cincinnati, Ohio
45215, telephone (513) 672–8400, fax
(513) 672–8422.
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room W12–140 on the ground floor of
the West Building, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Kenneth Steeves, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone: (781) 238–7765, fax:
(781) 238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 by
superseding AD 2006–20–06,
Amendment 39–14775 (71 FR 57403,
September 29, 2006), with a proposed
AD. The proposed AD applies to GE
CF34–10E2A1, –10E5, –10E5A1, –10E6,
pwalker on PROD1PC71 with RULES
SUMMARY:
VerDate Aug<31>2005
17:11 Jun 13, 2007
Jkt 211001
–10E6A1, and –10E7 turbofan engines,
with MFP P/Ns 2043M12P03, P/N
2043M12P04, 837600–3, and 837600–4,
installed. We published the proposed
AD in the Federal Register on
September 29, 2006 (71 FR 57403). That
action proposed to require removing
MFPs, P/N 2043M12P03, 2043M12P04,
83600–3, and 83600–4 from service and
installing an improved MFP, not later
than July 31, 2007.
Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
(800) 647–5227) is located on the plaza
level of the Department of
Transportation Nassif Building at the
street address stated in ADDRESSES.
Comments will be available in the AD
docket shortly after the DMS receives
them.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Address the Use of Parts Manufacturer
Approval (PMA) Parts
One commenter, Mr. Jack Buster of
the Modification and Repair Parts
Association (MARPA), states that the
PMA part may often share the identical
design data with the original part while
carrying a completely different part
number; therefore, it is possible the AD
will not address certain defective PMA
parts installed on the aircraft, allowing
the unsafe condition to continue.
The same commenter also states that
it is possible that a ‘‘new and improved’’
PMA version of the defective original
part may already exist in the
marketplace. Therefore, specifying one
approved part in preference to a
different, but also approved part, will
impart a commercial advantage to one
manufacturer over the other.
We agree. We changed the final rule
to add the PMA P/Ns 837600–3 and
837600–4 to the Applicability and
replacement requirements of the final
rule.
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
32775
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect
50 CF34–10E series turbofan engines
installed on airplanes of U.S. registry.
We also estimate that it will take about
3 work-hours per engine to perform the
required actions, and that the average
labor rate is $80 per work-hour.
Required parts will cost about $4,226
per engine to upgrade the MFP to a
different P/N to make it serviceable.
Based on these figures, we estimate the
total upgrade cost of this AD to U.S.
operators to be $223,300.
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 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); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
E:\FR\FM\14JNR1.SGM
14JNR1
32776
Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
this summary at the address listed
under ADDRESSES.
P/N 2043M12P03, 2043M12P04, 837600–3 or
837600–4.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
Recommended Actions
(h) We recommend that operators avoid
performing the actions in this AD on both
engines installed on the same airplane at the
same time, if at all possible.
Adoption of the Amendment
Alternative Methods of Compliance
(i) The Manager, Engine Certification
Office, FAA, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14775 (71 FR
57403, September 29, 2006) and by
adding a new airworthiness directive,
Amendment 39–15093, to read as
follows:
I
2007–12–15 General Electric Company:
Amendment 39–15093. Docket No.
FAA–2005–25896; Directorate Identifier
2006–NE–33–AD.
DEPARTMENT OF TRANSPORTATION
Affected ADs
(b) This AD supersedes AD 2006–20–06,
Amendment 39–14755.
Federal Aviation Administration
Applicability
(c) This AD applies to General Electric
Company (GE) CF34–10E2A1, –10E5,
–10E5A1, –10E6, –10E6A1, and –10E7
turbofan engines, with main fuel pump
(MFP) part number (P/N) 2043M12P03, P/N
2043M12P04, P/N 837600–3, and P/N
837600–4 installed. These engines are
installed on, but not limited to, Embraer ERJ
190–100–STD, ERJ 190–100–LR, and ERJ
190–100–IGW airplanes.
Unsafe Condition
(d) This AD results from GE determining
that the cause of MFP fuel strainer failure is
a design problem with the strainer. We are
issuing this AD to prevent engine in-flight
shutdown due to MFP malfunctions.
pwalker on PROD1PC71 with RULES
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.
Definition
(g) For the purpose of this AD, a
serviceable MFP is one that does not have
VerDate Aug<31>2005
17:11 Jun 13, 2007
Jkt 211001
Issued in Burlington, Massachusetts, on
June 1, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 07–2843 Filed 6–13–07; 8:45 am]
BILLING CODE 4910–13–P
Effective Date
(a) This airworthiness directive (AD)
becomes effective July 19, 2007.
MFP Removal and Installation
(f) Not later than July 31, 2007, remove
MFPs, P/Ns 2043M12P03, 2043M12P04,
837600–3, and 837600–4 from service and
install a serviceable MFP.
Related Information
(j) GE Service Bulletin No. CF34–10E S/B
73–0013, dated December 15, 2006, pertains
to the subject of this AD.
(k) Contact Kenneth Steeves, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone (781) 238–7765, fax (781)
238–7199, for more information about this
AD.
14 CFR Part 39
[Docket No. FAA–2007–27849; Directorate
Identifier 2006–NM–249–AD; Amendment
39–15094; AD 2007–12–16]
RIN 2120–AA64
Airworthiness Directives; Dassault
Model Falcon 2000EX and Falcon
900EX Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an airworthiness authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as some stringer
reinforcements (F900DX) and some
rivets (F900DX/F2000EX) missing from
the skin panels on each side of the
fuselage between frames 9 and 10 on
certain Falcon 900DX and Falcon
2000EX EASy aircraft; this situation
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
affects the structural integrity of the
fuselage. We are issuing this AD to
require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective July
19, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 19, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1137;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
allow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This AD references the MCAI and
related service information that we
considered in forming the engineering
basis to correct the unsafe condition.
The AD contains text copied from the
MCAI and for this reason might not
follow our plain language principles.
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 12, 2007 (72 FR
18415). That NPRM proposed to require
inspecting skin panels on each side of
the fuselage between frames 9 and 10,
including holes and structure, where
missing rivets are found, adding missing
rivets and stringer caps, as applicable,
and contacting the manufacturer if the
holes are out-of-round beyond tolerance,
or if cracks are found, as applicable. The
MCAI states that following the
incorporation of a design change to the
Karman fairing, it has been determined
that some stringer reinforcements
E:\FR\FM\14JNR1.SGM
14JNR1
Agencies
[Federal Register Volume 72, Number 114 (Thursday, June 14, 2007)]
[Rules and Regulations]
[Pages 32775-32776]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 07-2843]
[[Page 32775]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25896; Directorate Identifier 2006-NE-33-AD;
Amendment 39-15093; AD 2007-12-15]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF34-10E
Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for GE CF34-10E series turbofan engines. That AD currently
requires removing the fuel inlet strainer from main fuel pump (MFP)
part number (P/N) 2043M12P03, installing a certain replacement flange
as an interim repair, remarking the MFP to P/N 2043M12P04, and
performing initial and repetitive visual inspections of the main fuel
filter. This AD requires removing MFPs, P/Ns 2043M12P03, 2043M12P04,
837600-3, and 837600-4, from service and installing an improved MFP
with a different P/N. This AD results from GE determining that the
cause of MFP fuel strainer failure is a design problem with the
strainer. We are issuing this AD to prevent engine in-flight shutdown
due to MFP malfunctions.
DATES: This AD becomes effective July 19, 2007.
ADDRESSES: You can get the service information identified in this AD
from General Electric Company via Lockheed Martin Technology Services,
10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513)
672-8400, fax (513) 672-8422.
You may examine the AD docket on the Internet at https://dms.dot.gov
or in Room W12-140 on the ground floor of the West Building, 1200 New
Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Kenneth Steeves, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; telephone: (781) 238-
7765, fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by
superseding AD 2006-20-06, Amendment 39-14775 (71 FR 57403, September
29, 2006), with a proposed AD. The proposed AD applies to GE CF34-
10E2A1, -10E5, -10E5A1, -10E6, -10E6A1, and -10E7 turbofan engines,
with MFP P/Ns 2043M12P03, P/N 2043M12P04, 837600-3, and 837600-4,
installed. We published the proposed AD in the Federal Register on
September 29, 2006 (71 FR 57403). That action proposed to require
removing MFPs, P/N 2043M12P03, 2043M12P04, 83600-3, and 83600-4 from
service and installing an improved MFP, not later than July 31, 2007.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The Docket Office (telephone (800) 647-5227) is
located on the plaza level of the Department of Transportation Nassif
Building at the street address stated in ADDRESSES. Comments will be
available in the AD docket shortly after the DMS receives them.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Address the Use of Parts Manufacturer Approval (PMA) Parts
One commenter, Mr. Jack Buster of the Modification and Repair Parts
Association (MARPA), states that the PMA part may often share the
identical design data with the original part while carrying a
completely different part number; therefore, it is possible the AD will
not address certain defective PMA parts installed on the aircraft,
allowing the unsafe condition to continue.
The same commenter also states that it is possible that a ``new and
improved'' PMA version of the defective original part may already exist
in the marketplace. Therefore, specifying one approved part in
preference to a different, but also approved part, will impart a
commercial advantage to one manufacturer over the other.
We agree. We changed the final rule to add the PMA P/Ns 837600-3
and 837600-4 to the Applicability and replacement requirements of the
final rule.
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 50 CF34-10E series turbofan
engines installed on airplanes of U.S. registry. We also estimate that
it will take about 3 work-hours per engine to perform the required
actions, and that the average labor rate is $80 per work-hour. Required
parts will cost about $4,226 per engine to upgrade the MFP to a
different P/N to make it serviceable. Based on these figures, we
estimate the total upgrade cost of this AD to U.S. operators to be
$223,300.
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 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); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of
[[Page 32776]]
this summary at the address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration 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 removing Amendment 39-14775 (71 FR
57403, September 29, 2006) and by adding a new airworthiness directive,
Amendment 39-15093, to read as follows:
2007-12-15 General Electric Company: Amendment 39-15093. Docket No.
FAA-2005-25896; Directorate Identifier 2006-NE-33-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 19,
2007.
Affected ADs
(b) This AD supersedes AD 2006-20-06, Amendment 39-14755.
Applicability
(c) This AD applies to General Electric Company (GE) CF34-
10E2A1, -10E5, -10E5A1, -10E6, -10E6A1, and -10E7 turbofan engines,
with main fuel pump (MFP) part number (P/N) 2043M12P03, P/N
2043M12P04, P/N 837600-3, and P/N 837600-4 installed. These engines
are installed on, but not limited to, Embraer ERJ 190-100-STD, ERJ
190-100-LR, and ERJ 190-100-IGW airplanes.
Unsafe Condition
(d) This AD results from GE determining that the cause of MFP
fuel strainer failure is a design problem with the strainer. We are
issuing this AD to prevent engine in-flight shutdown due to MFP
malfunctions.
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.
MFP Removal and Installation
(f) Not later than July 31, 2007, remove MFPs, P/Ns 2043M12P03,
2043M12P04, 837600-3, and 837600-4 from service and install a
serviceable MFP.
Definition
(g) For the purpose of this AD, a serviceable MFP is one that
does not have P/N 2043M12P03, 2043M12P04, 837600-3 or 837600-4.
Recommended Actions
(h) We recommend that operators avoid performing the actions in
this AD on both engines installed on the same airplane at the same
time, if at all possible.
Alternative Methods of Compliance
(i) The Manager, Engine Certification Office, FAA, 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) GE Service Bulletin No. CF34-10E S/B 73-0013, dated December
15, 2006, pertains to the subject of this AD.
(k) Contact Kenneth Steeves, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; telephone (781) 238-
7765, fax (781) 238-7199, for more information about this AD.
Issued in Burlington, Massachusetts, on June 1, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 07-2843 Filed 6-13-07; 8:45 am]
BILLING CODE 4910-13-P