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[Federal Register Volume 75, Number 5 (Friday, January 8, 2010)]
[Rules and Regulations]
[Pages 1017-1020]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-31274]

========================================================================
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. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
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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.

-----------------------------------------------------------------------

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: geae.aoc@ge.com 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: 
john.frost@faa.gov; 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: john.frost@faa.gov; 
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: geae.aoc@ge.com.
    (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
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