[Federal Register Volume 75, Number 5 (Friday, January 8, 2010)]
[Rules and Regulations]
[Pages 1017-1020]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-31274]
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Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
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Federal Register / Vol. 75, No. 5 / Friday, January 8, 2010 / Rules
and Regulations
[[Page 1017]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0328; Directorate Identifier 2008-NE-44-AD;
Amendment 39-16161; AD 2010-01-04]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF34-1A,
CF34-3A, and CF34-3B Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for GE CF34-1A, CF34-3A, and CF34-3B series turbofan engines. That
AD currently requires removing from service certain part number (P/N)
and serial number (S/N) fan blades within compliance times specified in
the AD, inspecting the fan blade abradable rub strip on certain engines
for wear, inspecting the fan blades on certain engines for cracks,
inspecting the aft actuator head hose fitting for correct position,
and, if necessary, repositioning the hose fitting. This ad supersedure
requires the same actions but corrects the effectivity for certain fan
blades requiring corrective actions and changes the effective date of
the current AD. This AD supersedure results from the FAA discovering
that the existing AD has an incorrect effectivity for certain fan
blades requiring corrective actions, and from a report of an under-cowl
fire and a failed fan blade. We are issuing this AD to prevent failure
of certain P/N and S/N fan blades and aft actuator head hoses, which
could result in an under-cowl fire and subsequent damage to the
airplane.
DATES: This AD becomes effective January 25, 2010. The Director of the
Federal Register previously approved the incorporation by reference of
certain publications listed in the regulations as of January 4, 2010.
We must receive any comments on this AD by March 9, 2010.
ADDRESSES: Use one of the following addresses to comment on this AD.
Federal eRulemaking Portal: Go to http://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.
Contact General Electric Company, GE-Aviation, Room 285, 1 Neumann
Way, Cincinnati, OH 45215, telephone (513) 552-3272; fax (513) 552-
3329; e-mail: [email protected] for the service information identified in
this AD.
FOR FURTHER INFORMATION CONTACT: John Frost, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; telephone (781) 238-7756; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA amends 14 CFR part 39 by superseding
AD 2009-24-11, Amendment 39-16103 (74 FR 62481, November 30, 2009).
That AD requires removing from service certain P/N and S/N fan blades
within compliance times specified in the AD, inspecting the fan blade
abradable rub strip on certain engines for wear, inspecting the fan
blades on certain engines for cracks, inspecting the aft actuator head
hose fitting for correct position, and, if necessary, repositioning the
hose fitting. That AD was the result of a report of an under-cowl fire
and a failed fan blade. That condition, if not corrected, could result
in an under-cowl fire and subsequent damage to the airplane.
Actions Since AD 2009-24-11 Was Issued
Since AD 2009-24-11 was issued, we discovered that when we
recodified the compliance section as part of our response to a comment
received on the proposed AD, we inadvertently left out of the AD
certain fan blade effectivity information from paragraphs (f) and (g)
and (j). Paragraphs (f) and (g) are missing information on fan blades,
P/Ns 6018T30P14 or 4923T56G08, that have any fan blade S/Ns listed in
Appendix A of General Electric Aircraft Engines (GEAE) Service Bulletin
(SB) No. CF34-AL S/B 72-0245, Revision 01, dated July 30, 2008. Also,
paragraph (j) is missing information on fan blades, P/N 6018T30P14 or
P/N 4923T56G08, that have any fan blade S/Ns listed in Appendix A of
GEAE SB No. CF34-BJ S/B 72-0229, Revision 01, dated July 30, 2008. This
AD supersedure adds the missing information to the compliance section
and changes the effective date of the original AD to the same effective
date as this AD, to prevent possible grounding of airplanes.
Relevant Service Information
We have reviewed and approved the technical contents of the
following GE Aircraft Engines SBs:
CF34-AL S/B 73-0046, Revision 02, dated August 27, 2008,
and CF34-BJ S/B 73-0062, Revision 02, dated August 27, 2008, that
provide instructions for inspecting the orientation of the aft actuator
hose assembly and the main fuel control.
CF34-AL S/B 72-0245, Revision 01, dated July 3, 2008,
CF34-BJ S/B 72-0229, Revision 01, dated July 30, 2008, and CF34-BJ S/B
72-0230, Revision 01, dated July 30, 2008, that provide instructions
for replacing certain existing blades, P/Ns 6018T30P14 and 4923T56G08,
that have a S/N listed in Appendix A of those SBs.
CF34-AL S/B 72-0250, Revision 01, dated November 26, 2008,
and CF34-BJ S/B 72-0231, Revision 02, dated November 26, 2008, that
provide instructions for inspecting the fan case abradable rub strip
and fan blade tangs.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other GE CF34-1A, CF34-3A, and CF34-3B series turbofan
engines of the same type design. We are issuing this AD supersedure to
prevent failure of certain P/N and S/N fan blades and aft actuator head
hoses, which could result in an under-cowl fire and subsequent damage
to the airplane. This AD
[[Page 1018]]
requires removing from service certain P/N and S/N fan blades within
compliance times specified in the AD, inspecting the fan blade
abradable rub strip on certain engines for wear, inspecting the fan
blades on certain engines for cracks, inspecting the aft actuator head
hose fitting for correct position, and, if necessary, repositioning the
hose fitting. You must use the service information described previously
to perform the actions required by this AD.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2008-0328; Directorate
Identifier 2008-NE-44-AD'' in the subject line of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of the rule that might suggest a need
to modify it.
We will post all comments we receive, without change, to http://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 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 http://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 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.
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 the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. 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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Under the authority delegated to me by the Administrator, the Federal
Aviation Administration amends part 39 of the Federal Aviation
Regulations (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 39-16103 (74 FR
62481, November 30, 2009), and by adding a new airworthiness directive,
Amendment 39-16161, to read as follows:
2010-01-04 General Electric Company: Amendment 39-16161. Docket No.
FAA-2008-0328; Directorate Identifier 2008-NE-44-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
25, 2010.
Affected ADs
(b) This AD supersedes AD 2009-24-11, Amendment 39-16103.
Applicability
(c) This AD applies to General Electric Company (GE) CF34-1A,
CF34-3A, CF34-3A1, CF34-3A2, CF34-3B, and CF34-3B1 turbofan engines.
These engines are installed on, but not limited to, Bombardier
Canadair Models CL-600-2A12, CL-600-2B16, and CL-600-2B19 airplanes.
Unsafe Condition
(d) This AD results from the FAA discovering that the existing
AD has an incorrect effectivity for certain fan blades requiring
corrective actions, and from a report of an under-cowl fire and a
failed fan blade. We are issuing this AD to prevent failure of
certain part number (P/N) and serial number (S/N) fan blades and aft
actuator head hoses, which could result in an under-cowl fire and
subsequent damage to 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.
CF34-3A1 and CF34-3B1 Engines
(f) For CF34-3A1 engines that meet all of the following
criteria, perform the actions specified in paragraph (i) of this AD:
(1) Fan drive shaft, P/N 6036T78P02, installed; and
(2) Airworthiness limitation section fan drive shaft life limit
of 22,000 cycles-since-new (CSN); and
(3) Installed fan blades, P/Ns 6018T30P14 or 4923T56G08, that
have any fan blade S/Ns listed in Appendix A of General Electric
Aircraft Engines (GEAE) SB No. CF34-AL S/B 72-0245, Revision 01,
dated July 30, 2008.
(g) For CF34-3A1 engines that meet all of the following
criteria, perform the actions specified in paragraph (i) of this AD:
[[Page 1019]]
(1) Fan drive shaft, P/N 6036T78P02, installed; and
(2) Airworthiness limitation section fan drive shaft life limit
of 15,000 CSN; and
(3) In compliance with GEAE SB No. CF34-AL S/B 72-0147, dated
May 21, 2003, Revision 01, dated October 17, 2003, Revision 02,
dated August 5, 2004, or Revision 3, dated August 28, 2003; and
(4) Installed fan blades, P/Ns 6018T30P14 or 4923T56G08, that
have any fan blade S/Ns listed in Appendix A of GEAE SB No. CF34-AL
S/B 72-0245, Revision 01, dated July 30, 2008.
(h) For CF34-3B1 engines that meet all of the following
criteria, perform the actions specified in paragraph (i) of this AD:
(1) Installed fan blades, P/Ns 6018T30P14 or 4923T56G08; and
(2) With any fan blade S/Ns listed in Appendix A of GEAE SB No.
CF34-AL S/B 72-0245, Revision 01, dated July 30, 2008.
(i) Do the following for the engines meeting the criteria in
paragraph (f), (g), or (h) of this AD, as applicable:
(1) Remove listed fan blades from service within 4,000 cycles-
in-service (CIS) after the effective date of this AD or by December
31, 2010, whichever occurs first.
Initial Visual Inspection of the Fan Blade Abradable Rub Strip for Wear
(2) For fan blades with 1,200 or more CSN on the effective date
of this AD, perform an initial visual inspection of the fan blade
abradable rub strip for wear within 20 CIS after the effective date
of this AD. Use paragraphs 3.A.(1) through 3.A.(2) of the
Accomplishment Instructions of GEAE SB No. CF34-AL S/B 72-0250,
Revision 01, dated November 26, 2008, to perform the inspection.
(3) For fan blades with fewer than 1,200 CSN on the effective
date of this AD, perform an initial visual inspection of the fan
blade abradable rub strip for wear within 1,220 CSN. Use paragraphs
3.A.(1) through 3.A.(2) of the Accomplishment Instructions of GEAE
SB No. CF34-AL S/B 72-0250, Revision 01, dated November 26, 2008, to
perform the inspection.
(4) If you find a continuous 360 degree rub indication, before
further flight, visually inspect the fan blades using paragraphs
3.A.(2)(a) through 3.A.(2)(b) of the Accomplishment Instructions of
GEAE SB No. CF34-AL S/B 72-0250, Revision 01, dated November 26,
2008.
(5) If you find a crack in the retaining pin holes of the fan
blade, remove the blade from service.
Repetitive Visual Inspection of the Fan Blade Abradable Rub Strip for
Wear
(6) Within 75 cycles-since-last inspection (CSLI) or 100 hours-
since-last-inspection (HSLI), whichever occurs later, perform a
visual inspection of the fan blade abradable rub strip for wear. Use
paragraphs 3.A.(1) through 3.A.(2) of the Accomplishment
Instructions of GEAE SB No. CF34-AL S/B 72-0250, Revision 01, dated
November 26, 2008, to perform the inspection.
(i) If you find a continuous 360 degree rub indication, before
further flight, visually inspect the fan blades using paragraphs
3.A.(2)(a) through 3.A.(2)(b) of the Accomplishment Instructions of
GEAE SB No. CF34-AL S/B 72-0250, Revision 01, dated November 26,
2008.
(ii) If you find a crack in the retaining pin holes of the fan
blade, remove the blade from service.
Inspection of the Aft Actuator Head Hose Fitting on CF34-3A1 and CF34-
3B1 Engines
(7) Within 750 hours time-in-service (TIS) after the effective
date of this AD, visually inspect and, if necessary, reposition the
aft actuator head hose fitting. Use paragraph 3.A of the
Accomplishment Instructions of GEAE SB No. CF34-AL S/B 73-0046,
Revision 02, dated August 27, 2008, to perform the inspection.
CF34-1A, CF34-3A, CF34-3A2, CF34-3B, and CF34-3A1 Engines
(j) For CF34-3A1 engines that meet all of the following
criteria, perform the actions specified in paragraph (l) of this AD:
(1) Fan drive shaft, P/N 6036T78P02, installed; and
(2) Airworthiness limitation section fan drive shaft life limit
of 15,000 CSN that are not in compliance with GEAE SB No. CF34-AL S/
B 72-0147, dated May 21, 2003, Revision 01, dated October 17, 2003,
Revision 02, dated August 5, 2004, or Revision 03, dated August 28,
2003; and
(3) With fan blades, P/Ns 6018T30P14 or 4923T56G08, that have
any fan blade S/Ns listed in Appendix A of GEAE SB No. CF34-BJ S/B
72-0229, Revision 01, dated July 30, 2008.
(k) For CF34-1A, CF34-3A, CF34-3A2, and CF34-3B engines that
meet all of the following criteria, perform the actions specified in
paragraph (l) of this AD:
(1) Installed fan blades, P/N 6018T30P14 or P/N 4923T56G08; and
(2) Installed fan blade S/Ns listed in Appendix A of GEAE SB No.
CF34-BJ S/B 72-0229, Revision 01, dated July 30, 2008:
(l) Do the following for the engines meeting the criteria in
paragraph (j) or (k) of this AD as applicable:
(1) Remove listed fan blades, P/N 6018T30P14, from service
within 2,400 CSN.
(2) Remove listed fan blades, P/N 4923T56G08, from service
within 1,200 CIS since the bushing repair of the fan blade hole.
Initial Eddy Current Inspection of the Fan Blades
(3) For fan blades, P/N 6018T30P14, with more than 850 CSN,
perform an initial eddy current inspection (ECI) of the fan blades
for cracks within 350 CIS after the effective date of this AD. Use
paragraphs 3.A. or 3.B. of the Accomplishment Instructions of GEAE
SB No. CF34-BJ S/B 72-0229, Revision 01, dated July 30, 2008, to
perform the inspection.
(4) For fan blades, P/N 6018T30P14, with 850 or fewer CSN on the
effective date of this AD, perform an initial ECI of the fan blades
for cracks within 1,200 CSN. Use paragraphs 3.A. or 3.B. of the
Accomplishment Instructions of GEAE SB No. CF34-BJ S/B 72-0229,
Revision 01, dated July 30, 2008, to perform the inspection.
(5) If you find a crack in the retaining pin holes of the fan
blade, remove the blade from service.
Repetitive ECI of the Fan Blades
(6) For fan blades, P/N 6018T30P14, within 600 CSLI, perform an
ECI of the fan blades for cracks. Use paragraphs 3.A. or 3.B. of the
Accomplishment Instructions of GEAE SB No. CF34-BJ S/B 72-0229,
Revision 01, dated July 30, 2008, to perform the inspection.
(7) If you find a crack in the retaining pin holes of the fan
blade, remove the blade from service.
Initial Visual Inspection of the Fan Blade Abradable Rub Strip for Wear
(8) For engines with fan blades, P/N 6018T30P14, installed that
have any fan blade S/Ns listed in Appendix A of GEAE SB No. CF34-BJ
S/B 72-0229, Revision 01, dated July 30, 2008, with 1,200 or more
CSN on the effective date of this AD, and that haven't had an ECI of
the fan blades for cracks, do the following:
(i) Perform an initial inspection of the fan blade abradable rub
strip for wear within 20 CIS after the effective date of this AD.
Use paragraph 3.A.(1) of the Accomplishment Instructions of GEAE SB
No. CF34-BJ S/B 72-0231, Revision 02, dated November 26, 2008, to
perform the inspection.
(ii) If you find a continuous 360 degree rub indication, before
further flight, perform a visual inspection of the fan blades for
cracks. Use paragraphs 3.A(2)(a) or 3.A(2)(b) of the Accomplishment
Instructions of GEAE SB No. CF34-BJ S/B 72-0231, Revision 02, dated
November 26, 2008, to perform the inspection.
(iii) If you find a crack in the retaining pin holes of the fan
blade, remove the blade from service.
Repetitive Inspection of the Fan Blade Abradable Rub Strip for Wear
(9) For engines with fan blades, P/N 6018T30P14, installed, if
you have performed an ECI of the fan blade, you don't need to
inspect the fan blade abradable rub strip for wear.
(10) For engines with fan blades, P/N 6018T30P14, installed,
within 75 CSLI or 100 HSLI, whichever occurs later, do the
following:
(i) Perform a visual inspection of the fan blade abradable rub
strip for wear. Use paragraph 3.A.(1) of the Accomplishment
Instructions of GEAE SB No. CF34-BJ S/B 72-0231, Revision 02, dated
November 26, 2008, to perform the inspection.
(ii) If you find a continuous 360 degree rub indication, before
further flight, visually inspect the fan blades using paragraphs
3.A.(2)(a) through 3.A.(2)(b) of the Accomplishment Instructions of
GEAE SB No. CF34-BJ S/B 72-0231, Revision 02, dated November 26,
2008.
(iii) If you find a crack in the retaining pin holes of the fan
blade, remove the blade from service.
Inspection of the Aft Actuator Head Hose Fitting on CF34-3A1 and CF34-
3B Engines
(11) For CF34-3A1 engines, within 300 hours TIS after the
effective date of this AD, visually inspect and, if necessary,
reposition the aft actuator head hose fitting. Use paragraph 3.A of
the Accomplishment Instructions of GEAE SB No. CF34-BJ S/B
[[Page 1020]]
73-0062, Revision 02, dated August 27, 2008, to perform the
inspection.
(12) For CF34-3B engines, within 400 hours TIS after the
effective date of this AD, visually inspect and, if necessary,
reposition the aft actuator head hose fitting. Use paragraph 3.A of
the Accomplishment Instructions of GEAE SB No. CF34-BJ S/B 73-0062,
Revision 02, dated August 27, 2008, to perform the inspection.
Credit for Previous Actions
(m) Inspections previously performed using the following GEAE
SBs meet the requirements specified in the indicated paragraphs:
(1) CF34-AL S/B 72-0250, dated August 15, 2008, meet the
requirements specified in paragraphs (i)(2) through (i)(4) of this
AD.
(2) CF34-AL S/B 73-0046, Revision 01, dated July 1, 2008, or
earlier issue, meet the requirements specified in paragraph (i)(7)
of this AD.
(3) CF34-BJ S/B 72-0229, dated April 10, 2008, meet the
requirements specified in paragraphs (l)(3) and (l)(4) of this AD.
(4) CF34-BJ S/B 72-0231, Revision 01, dated October 1, 2008, or
earlier issue, meet the requirements specified in paragraphs
(l)(10)(i) and (l)(10)(ii) of this AD.
(5) CF34-BJ S/B 73-0062, Revision 01, dated July 1, 2008, or
earlier issue, meet the requirements specified in paragraphs (l)(11)
and (l)(12) of this AD.
Installation Prohibitions
(n) After the effective date of this AD:
(1) Do not install any fan blade into any CF34-3A1 engine with
fan drive shaft, P/N 6036T78P02, with an airworthiness limitation
section fan drive shaft life limit of 22,000 CSN if that fan blade:
(i) Was installed in a CF34-3A1 engine with fan drive shaft, P/N
6036T78P02, with an airworthiness limitation section fan drive shaft
life limit of 15,000 CSN; and
(ii) Is listed in Appendix A of GEAE SB No. CF34-BJ S/B 72-0229,
Revision 01, dated July 30, 2008; or
(iii) Is listed in Appendix A of GEAE SB No. CF34-BJ S/B 72-
0230, Revision 01, dated July 30, 2008.
(2) Do not install any fan blade into any CF34-3A1 engine with
fan drive shaft, P/N 6036T78P02, with an airworthiness limitation
section fan drive shaft life limit of 15,000 CSN if that fan blade:
(i) Was installed in any CF34-3A1 engine with fan drive shaft,
P/N 6036T78P02, with an airworthiness limitation section fan drive
shaft life limit of 22,000 CSN; and
(ii) Is listed in Appendix A of GEAE SB No. CF34-AL S/B 72-0245,
Revision 01, dated July 3, 2008.
Alternative Methods of Compliance
(o) 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
(p) Contact John Frost, Aerospace Engineer, Engine Certification
Office, FAA, Engine & Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail: [email protected];
telephone (781) 238-7756; fax (781) 238-7199, for more information
about this AD.
Material Incorporated by Reference
(q) You must use the GE Aircraft Engines service information
specified in the following Table 1 to do the actions required by
this AD.
Table 1--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
CF34-AL S/B 73-0046..................
Total Pages: 8 All..................... 02 August 27, 2008.
CF34-BJ S/B 73-0062..................
Total Pages: 8 All..................... 02 August 27, 2008.
CF34-BJ S/B 72-0229..................
Total Pages: 158 All..................... 01 July 30, 2008.
CF34-BJ S/B 72-0230..................
Total Pages: 153 All..................... 01 July 30, 2008.
CF34-BJ S/B 72-0231..................
Total Pages: 8 All..................... 02 November 26, 2008.
CF34-AL S/B 72-0245..................
Total Pages: 153 All..................... 01 July 3, 2008.
CF34-AL S/B 72-0250..................
Total Pages: 9 All..................... 01 November 26, 2008.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register previously approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51, as of January 4, 2010.
(2) For service information identified in this AD, contact
General Electric Company, GE-Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215, telephone (513) 552-3272; fax (513) 552-3329;
e-mail: [email protected].
(3) You may review copies at the FAA, New England Region, 12 New
England Executive Park, Burlington, MA; or at the National Archives
and Records Administration (NARA). For information on the
availability of this material at NARA, call (202) 741-6030, or go
to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on December 29, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E9-31274 Filed 1-7-10; 8:45 am]
BILLING CODE 4910-13-P