Airworthiness Directives; General Electric Company (GE) CF34-1A, CF34-3A, and CF34-3B Series Turbofan Engines, 62481-62485 [E9-28236]
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Federal Register / Vol. 74, No. 228 / Monday, November 30, 2009 / Rules and Regulations
62481
Actions
Compliance
Procedures
(4) If the cracks identified in paragraph (f)(3) of
this AD meet or exceed the limits specified in
paragraph 3 of Cessna Citation Alert Service
Letter ASL525A–78–01, Revision 1, dated
October 27, 2009, replace the thrust attenuator paddle and attachment hardware, as applicable.
(i) If the conditions of paragraph 3.A.(1) of
Cessna Citation Alert Service Letter
ASL525A–78–01, Revision 1, dated October 27, 2009, are met, replace before further flight after the inspection required in
paragraph (f)(3) of this AD. After the replacement, continue with the repetitive inspections specified in paragraph (f)(1) of
this AD.
(ii) If the conditions of paragraph 3.A.(2) of
Cessna Citation Alert Service Letter
ASL525A–78–01, Revision 1, dated October 27, 2009, are met, replace within the
next 150 hours TIS after the inspection required in paragraph (f)(3) of this AD. After
the replacement, continue with the repetitive inspections specified in paragraph
(f)(1) of this AD.
Follow Cessna Citation Alert Service Letter
ASL525A–78–01, Revision 1, dated October 27, 2009.
Alternative Methods of Compliance
(AMOCs)
(g) 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. Send information to Attn: T.N.
Baktha, Aerospace Engineer, 1801 Airport
Road, Room 100, Wichita, Kansas 67209;
telephone: (316) 946–4155; fax: (316) 946–
4107. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
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Material Incorporated by Reference
(h) You must use Cessna Citation Alert
Service Letter ASL525A–78–01, Revision 1,
dated October 27, 2009, to do the actions
required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(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; Internet: https://www.cessna.com.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
(4) You may also review copies of the
service information incorporated by reference
for this AD 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: https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
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14:56 Nov 27, 2009
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Issued in Kansas City, Missouri, on
November 19, 2009.
Patrick R. Mullen,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–28234 Filed 11–27–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0328; Directorate
Identifier 2008–NE–44–AD; Amendment 39–
16103; AD 2009–24–11]
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.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for GE
CF34–1A, CF34–3A, and CF34–3B
series turbofan engines. This AD
requires removing from service certain
part number (P/N) and serial number
(SN) fan blades within compliance
times specified in this 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 results 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 SN fan blades
and aft actuator head hoses, which
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could result in an under-cowl fire and
subsequent damage to the airplane.
DATES: This AD becomes effective
January 4, 2010. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of January 4, 2010.
ADDRESSES: You can get the service
information identified in this AD from
General Electric Company, GE–
Aviation, Room 285, 1 Newmann Way,
Cincinnati, OH 45215, telephone (513)
552-–3272; fax (513) 552–3329; e-mail:
geae.aoc@ge.com. The Docket
Operations office is located at Docket
Management Facility, U.S. Department
of Transportation, 1200 New Jersey
Avenue, SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
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.
The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to GE CF34–1A, CF34–3A, and
CF34–3B series turbofan engines. We
published the proposed AD in the
Federal Register on April 8, 2009 (74 FR
15896). That action proposed to require
removing from service certain P/N and
SN fan blades within compliance times
specified in the proposed 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.
SUPPLEMENTARY INFORMATION:
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Federal Register / Vol. 74, No. 228 / Monday, November 30, 2009 / Rules and Regulations
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 provided in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Modify Wording in
Compliance Paragraphs (f)(2) Through
(f)(6)(ii)
One commenter requests that we
modify the wording in proposed AD
compliance paragraphs (f)(2) through
(f)(6)(ii), by adding words that the
actions required by GEAE SB CF34–AL
S/B 72–0250 apply only to those
engines that have not had the actions of
GEAE SB CF34–AL S/B 72–0245
performed. The commenter states that
GEAE SB CF34–AL S/B 72–0250 only
applies to fan blades with SNs listed in
GEAE SB CF34–AL S/B 72–0245.
We do not agree. The proposed AD
stated in paragraph (f) that only fan
blade SNs listed in GEAE SB CF34–AL
S/B 72–0245 are affected. That
paragraph is now paragraph (h) in this
AD, as we recodified the AD paragraphs
to add clarification in response to
another comment we received. We did
not change the AD.
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Request for Eddy Current Inspection
(ECI) for Fan Blades That Have More
than 1,200 Cycles-In-Service (CIS)
Bombardier Flexjet and GE Aviation
request that we also include an ECI in
the AD for fan blades that have more
than 1,200 CIS on the effective date of
the AD.
We agree. We changed proposed AD
paragraph from ‘‘(g)(3) For fan blades,
P/N 6018T30P14, with more than 850
cycles-since-new (CSN), but fewer than
1,200 CSN on the effective date of this
AD, within 350 CIS after the effective
date of this AD, perform an initial ECI
of the fan blades for cracks’’ to ‘‘(k)(3)
For fan blades, P/N 6018T30P14, with
more than 850 CSN, perform an initial
ECI of the fan blades for cracks within
350 CIS after the effective date of this
AD’’ in this AD.
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14:56 Nov 27, 2009
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Under-Cowl Fire Determination of
Cause Not Consistent
GE Aviation states that, in the
Discussion section of the proposed AD,
the statement that it was not possible to
determine the cause of the under-cowl
fire was not consistent with the GE fire
investigation. GE stated that their fire
investigation concluded that the most
probable cause of the under-cowl fire
was the separation of the variable
geometry aft actuator head hose from
the fuel control.
We do not agree. The exact cause of
the fire could not be determined due to
the thermal damage. We did not change
the AD.
Clarification of Gearbox Separation
Statement
GE Aviation states that, in the
Discussion section of the proposed AD,
the statement that the gearbox separated
from the engine needs clarification. GE
Aviation states that the gearbox is
designed to uncouple from the engine
during high-load events such as a fan
blade out, and the gearbox is secured to
the engine by secondary restraint cables.
This uncoupling occurred on the lefthand mount, and should not have
contributed to the hose failure if the
hose was properly aligned.
We do not agree. The wording is
factually correct, and we did not state
that the separation caused the fire. We
did not change the AD.
Claim That the Fire Event Was a
Controlled Fire
GE Aviation claims that the event that
this AD results from was a ‘‘controlled
fire’’ as the fire had been put out and
did not create a hazard for the airplane.
We do not agree. The fire continued
to burn unabated until the unidentified
fuel source was exhausted. We did not
change the AD.
Recommendation To Include GE
Remote Diagnostics
GE Aviation and Mesaba Airlines
recommend that GE Remote Diagnostics
be included in proposed AD compliance
paragraph (f)(6) as an alternate method
of compliance (AMOC) for monitoring
blade health. GE Aviation also
recommends that we allow a recurrent
ECI at 600-cycle intervals for
consistency between the Regional Jet
and Business Jet operators. GE Aviation
states that the fan blade tang cracking
algorithms developed by GE have been
validated analytically, as well as in the
field, and contributed substantially to
finding three cracked blades during
2008.
We do not agree. We cannot include
the GE Remote Diagnostics program,
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because it is a program outside
regulatory control. Further, the program
cannot replace a visual inspection to
verify fan blade cracks. Finally, no GE
service bulletin requirement or FAA
requirement exists for ECI of the fan
blades operating in engines in the
Regional Jet operations. We did not
change the AD.
Request To Revise the Wording in
Proposed AD Compliance Paragraphs
(f) and (g)
GE Aviation requests that we revise
the wording in proposed AD
compliance paragraphs (f) and (g) to
clarify our instructions related to
operators who fly a Regional Jet with a
CF34–3A1 engine in a Business jet
application. The commenter states that
GEAE SB CF34–AL S/B 72–0245 and SB
CF34–AL S/B 72–0250 apply to a small
number of Business Jet operators with
the CF34–3A1 engine, who fly under the
Regional jet manual.
We agree. We changed the compliance
section in this AD by adding the
requested information and by
recodifying the paragraphs.
Request To Correct a Typographical
Error
GE Aviation requests that we correct
a service bulletin issue date in
paragraph (f), to be July 30, 2008.
We agree. We corrected the date in the
AD, which is now in paragraph (h).
Request To Remove Inspection of
Rubstrips at CSN
Mesaba Airlines requests that we
remove the requirements to inspect the
fan blade rub strips on fan blades with
more than 1,200 CSN, within 20 CIS of
the AD effective date, and on fan blades
with fewer than 1,200 CSN, by 1,220
CSN. The commenter requests that we
add a rub strip inspection every 75 CIS
or 100 hours-in-service, until the fan
blades are replaced. The commenter
states that it is difficult to know the CSN
on each fan blade.
We do not agree. To reduce the risk
of fan blade failure, the rub strips need
to be inspected as required in the AD.
We did not change the AD.
Include a Process for Determining Fan
Blade Cyclic Limits
Mesaba Airlines states that the FAA
should include a process for
determining cyclic limits if the fan
blades CIS were not established when
the fan blades were introduced into
service.
We do not agree. If operators do not
track fan blade time or CIS, they will
need to apply for an alternative method
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Federal Register / Vol. 74, No. 228 / Monday, November 30, 2009 / Rules and Regulations
of compliance (AMOC) to this AD. We
did not change the AD.
Request for Separate ADs
Mesaba Airlines requests that we
issue separate ADs for the Regional Jet
fleet and the Business Jet fleet. The
commenter feels the proposed AD is far
too complex.
We do not agree. The compliance
section in the proposed AD is
sufficiently direct. We did not change
the AD.
Request To Define Terms
Mesaba Airlines requests that we
define the terms ‘‘CSLI’’ and ‘‘HSLI’’ in
the proposed AD compliance section.
In response, we note that we already
did, and direct Mesaba Airlines to
paragraph (f)(6) in the proposed AD, and
in this AD, to compliance paragraph
(h)(6).
Request To Not Include Service Bulletin
Requirements
Mesaba Airlines requests that we not
include the requirements of paragraph
3.A.(2)(d) of GEAE SB CF34–AL S/B 72–
0250 in the AD.
We agree. We did not include those
requirements in the AD.
Conclusion
We have carefully reviewed the
available data, including the comments
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.
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Costs of Compliance
We estimate that this AD will affect
1,966 engines installed on airplanes of
U.S. registry. We estimate that the fan
blade inspection and replacement
requirement will affect 300 of these
engines, and the actuator head hose
inspection would affect 1,662 engines.
We also estimate that it will take 0.5
work-hour per engine to inspect the fan
blade abradable rub strip, 6 work-hours
per engine to visually inspect the fan
blades, 11 work-hours per engine to
perform an eddy current inspection of
the fan blades, and 0.25 work-hour per
engine to inspect the actuator head hose
fitting, and that the average labor rate is
$80 per work-hour. Required parts will
cost $51,106,600. Based on these
figures, we estimate the total cost of the
AD to U.S. operators to be $51,184,000.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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Jkt 220001
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
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
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 39.13
62483
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2009–24–11 General Electric Company:
Amendment 39–16103. Docket No.
FAA–2009–0328; Directorate Identifier
2008–NE–44–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective January 4, 2010.
Affected ADs
(b) None.
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 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 (SN)
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 with fan drive
shaft, P/N 6036T78P02, and airworthiness
limitation section life limit of 22,000 CSN;
and
(g) For CF34–3A1 engines with fan drive
shaft, P/N 6036T78P02, and airworthiness
limitation section life limit of 15,000 CSN
that are in compliance with GE Aircraft
Engines (GEAE) Service Bulletin (SB) 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
(h) For CF34–3B1 engines with fan blades,
P/Ns 6018T30P14 or 4923T56G08, that have
a fan blade SN listed in Appendix A of GEAE
SB 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 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
cycles-since-new (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
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Instructions of GEAE SB 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 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
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 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
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.
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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 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 with fan drive
shaft, P/N 6036T78P02, and airworthiness
limitation section life limit of 15,000 CSN,
that are not in compliance with GEAE SB
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
(k) For CF34–1A, CF34–3A, CF34–3A2,
and CF34–3B engines with fan blades, P/N
6018T30P14 or P/N 4923T56G08, that have a
fan blade SN listed in Appendix A of GEAE
SB 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 fan blades, P/N 6018T30P14,
from service within 2,400 CSN.
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(2) Remove 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
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 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
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 a fan blade
SN listed in Appendix A of GEAE SB 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 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
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:
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
(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 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
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 CF34–BJ S/B 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 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 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 life limit
of 15,000 CSN; and
(ii) Is listed in Appendix A of GEAE SB
CF34–BJ S/B 72–0229, Revision 01, dated
July 30, 2008; or
(iii) Is listed in Appendix A of GEAE SB
CF34–BJ S/B 72–0230, Revision 01, dated
July 30, 2008.
E:\FR\FM\30NOR1.SGM
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62485
Federal Register / Vol. 74, No. 228 / Monday, November 30, 2009 / Rules and Regulations
(2) Do not install any fan blade into any
CF34–3A1 engine with fan drive shaft, P/N
6036T78P02, with an airworthiness
limitation section 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 life limit
of 22,000 CSN and,
(ii) Is listed in Appendix A of GEAE SB
CF34–AL S/B 72–0245, Revision 01, dated
July 3, 2008.
Alternative Methods of Compliance
Executive Park, Burlington, MA 01803; email: john.frost@faa.gov; telephone (781)
238–7756; fax (781) 238–7199, for more
information about this AD.
(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.
Material Incorporated by Reference
Related Information
(p) Contact John Frost, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
(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
CF34–AL S/B 73–0046 Total Pages: 8 ..............................................................................
CF34–BJ S/B 73–0062 Total Pages: 8 ..............................................................................
CF34–BJ S/B 72–0229 Total Pages: 158 ..........................................................................
CF34–BJ S/B 72–0230 Total Pages: 153 ..........................................................................
CF34–BJ S/B 72–0231 Total Pages: 8 ..............................................................................
CF34–AL S/B 72–0245 Total Pages: 153 ..........................................................................
CF34–AL S/B 72–0250 Total Pages: 9 ..............................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact General Electric Company,
GE-Aviation, Room 285, 1 Newmann 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
November 18, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E9–28236 Filed 11–27–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
WReier-Aviles on DSKGBLS3C1PROD with RULES
[Docket No. FAA–2009–0886 Directorate
Identifier 2009–CE–045–AD; Amendment
39–16109; AD 2009–24–15]
RIN 2120–AA64
Airworthiness Directives; SOCATA
Model TBM 700 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
VerDate Nov<24>2008
14:56 Nov 27, 2009
Jkt 220001
All
All
All
All
All
All
All
Revision
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.................
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.................
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.................
.................
Date
02
02
01
01
02
01
01
August 27, 2008.
August 27, 2008.
July 30, 2008.
July 30, 2008.
November 26, 2008.
July 03, 2008.
November 26, 2008.
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 aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on September 28, 2009 (74 FR
49345). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
It was noticed on assembly line an
elongation of bolts connecting power leads
on R700 and R701 shunts. An incorrect
tightening torque value is likely to be the
cause of the elongation.
This condition, if left uncorrected could
lead to heating, electrical arcing or smokes
and could result in an in-flight loss of
electrical power.
It was noticed on assembly line an
elongation of bolts connecting power leads
on R700 and R701 shunts. An incorrect
tightening torque value is likely to be the
cause of the elongation.
This condition, if left uncorrected could
lead to heating, electrical arcing or smokes
and could result in an in-flight loss of
electrical power.
For the reason described above, this
Airworthiness Directive (AD) mandates the
replacement of the power lead bolts on R700
and R701 shunts.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
January 4, 2010.
On January 4, 2010, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Albert Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4119; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
Comment Issue: Costs of Compliance
´
Ms. Catherine Herau, SOCATA, states
the cost of the required parts (4 bolts) is
$10, not $50. Consequently, the cost of
the proposed AD on U.S. operators is
$2,350 or $50 per product.
We agree with the commenter, and we
are changing the costs of compliance in
the final rule AD action to reflect the
more accurate estimated costs.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
E:\FR\FM\30NOR1.SGM
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]]>Agencies
[Federal Register Volume 74, Number 228 (Monday, November 30, 2009)]
[Rules and Regulations]
[Pages 62481-62485]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-28236]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0328; Directorate Identifier 2008-NE-44-AD;
Amendment 39-16103; AD 2009-24-11]
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.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE
CF34-1A, CF34-3A, and CF34-3B series turbofan engines. This AD requires
removing from service certain part number (P/N) and serial number (SN)
fan blades within compliance times specified in this 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 results 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 SN 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 4, 2010. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of January 4, 2010.
ADDRESSES: You can get the service information identified in this AD
from General Electric Company, GE-Aviation, Room 285, 1 Newmann Way,
Cincinnati, OH 45215, telephone (513) 552--3272; fax (513) 552-3329; e-
mail: geae.aoc@ge.com. The Docket Operations office is located at
Docket Management Facility, U.S. Department of Transportation, 1200 New
Jersey Avenue, SE., West Building Ground Floor, Room W12-140,
Washington, DC 20590-0001.
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 proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to GE CF34-1A, CF34-3A, and
CF34-3B series turbofan engines. We published the proposed AD in the
Federal Register on April 8, 2009 (74 FR 15896). That action proposed
to require removing from service certain P/N and SN fan blades within
compliance times specified in the proposed 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.
[[Page 62482]]
Examining the AD Docket
You may examine the AD docket on the Internet at https://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 provided in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Modify Wording in Compliance Paragraphs (f)(2) Through
(f)(6)(ii)
One commenter requests that we modify the wording in proposed AD
compliance paragraphs (f)(2) through (f)(6)(ii), by adding words that
the actions required by GEAE SB CF34-AL S/B 72-0250 apply only to those
engines that have not had the actions of GEAE SB CF34-AL S/B 72-0245
performed. The commenter states that GEAE SB CF34-AL S/B 72-0250 only
applies to fan blades with SNs listed in GEAE SB CF34-AL S/B 72-0245.
We do not agree. The proposed AD stated in paragraph (f) that only
fan blade SNs listed in GEAE SB CF34-AL S/B 72-0245 are affected. That
paragraph is now paragraph (h) in this AD, as we recodified the AD
paragraphs to add clarification in response to another comment we
received. We did not change the AD.
Request for Eddy Current Inspection (ECI) for Fan Blades That Have More
than 1,200 Cycles-In-Service (CIS)
Bombardier Flexjet and GE Aviation request that we also include an
ECI in the AD for fan blades that have more than 1,200 CIS on the
effective date of the AD.
We agree. We changed proposed AD paragraph from ``(g)(3) For fan
blades, P/N 6018T30P14, with more than 850 cycles-since-new (CSN), but
fewer than 1,200 CSN on the effective date of this AD, within 350 CIS
after the effective date of this AD, perform an initial ECI of the fan
blades for cracks'' to ``(k)(3) For fan blades, P/N 6018T30P14, with
more than 850 CSN, perform an initial ECI of the fan blades for cracks
within 350 CIS after the effective date of this AD'' in this AD.
Under-Cowl Fire Determination of Cause Not Consistent
GE Aviation states that, in the Discussion section of the proposed
AD, the statement that it was not possible to determine the cause of
the under-cowl fire was not consistent with the GE fire investigation.
GE stated that their fire investigation concluded that the most
probable cause of the under-cowl fire was the separation of the
variable geometry aft actuator head hose from the fuel control.
We do not agree. The exact cause of the fire could not be
determined due to the thermal damage. We did not change the AD.
Clarification of Gearbox Separation Statement
GE Aviation states that, in the Discussion section of the proposed
AD, the statement that the gearbox separated from the engine needs
clarification. GE Aviation states that the gearbox is designed to
uncouple from the engine during high-load events such as a fan blade
out, and the gearbox is secured to the engine by secondary restraint
cables. This uncoupling occurred on the left-hand mount, and should not
have contributed to the hose failure if the hose was properly aligned.
We do not agree. The wording is factually correct, and we did not
state that the separation caused the fire. We did not change the AD.
Claim That the Fire Event Was a Controlled Fire
GE Aviation claims that the event that this AD results from was a
``controlled fire'' as the fire had been put out and did not create a
hazard for the airplane.
We do not agree. The fire continued to burn unabated until the
unidentified fuel source was exhausted. We did not change the AD.
Recommendation To Include GE Remote Diagnostics
GE Aviation and Mesaba Airlines recommend that GE Remote
Diagnostics be included in proposed AD compliance paragraph (f)(6) as
an alternate method of compliance (AMOC) for monitoring blade health.
GE Aviation also recommends that we allow a recurrent ECI at 600-cycle
intervals for consistency between the Regional Jet and Business Jet
operators. GE Aviation states that the fan blade tang cracking
algorithms developed by GE have been validated analytically, as well as
in the field, and contributed substantially to finding three cracked
blades during 2008.
We do not agree. We cannot include the GE Remote Diagnostics
program, because it is a program outside regulatory control. Further,
the program cannot replace a visual inspection to verify fan blade
cracks. Finally, no GE service bulletin requirement or FAA requirement
exists for ECI of the fan blades operating in engines in the Regional
Jet operations. We did not change the AD.
Request To Revise the Wording in Proposed AD Compliance Paragraphs (f)
and (g)
GE Aviation requests that we revise the wording in proposed AD
compliance paragraphs (f) and (g) to clarify our instructions related
to operators who fly a Regional Jet with a CF34-3A1 engine in a
Business jet application. The commenter states that GEAE SB CF34-AL S/B
72-0245 and SB CF34-AL S/B 72-0250 apply to a small number of Business
Jet operators with the CF34-3A1 engine, who fly under the Regional jet
manual.
We agree. We changed the compliance section in this AD by adding
the requested information and by recodifying the paragraphs.
Request To Correct a Typographical Error
GE Aviation requests that we correct a service bulletin issue date
in paragraph (f), to be July 30, 2008.
We agree. We corrected the date in the AD, which is now in
paragraph (h).
Request To Remove Inspection of Rubstrips at CSN
Mesaba Airlines requests that we remove the requirements to inspect
the fan blade rub strips on fan blades with more than 1,200 CSN, within
20 CIS of the AD effective date, and on fan blades with fewer than
1,200 CSN, by 1,220 CSN. The commenter requests that we add a rub strip
inspection every 75 CIS or 100 hours-in-service, until the fan blades
are replaced. The commenter states that it is difficult to know the CSN
on each fan blade.
We do not agree. To reduce the risk of fan blade failure, the rub
strips need to be inspected as required in the AD. We did not change
the AD.
Include a Process for Determining Fan Blade Cyclic Limits
Mesaba Airlines states that the FAA should include a process for
determining cyclic limits if the fan blades CIS were not established
when the fan blades were introduced into service.
We do not agree. If operators do not track fan blade time or CIS,
they will need to apply for an alternative method
[[Page 62483]]
of compliance (AMOC) to this AD. We did not change the AD.
Request for Separate ADs
Mesaba Airlines requests that we issue separate ADs for the
Regional Jet fleet and the Business Jet fleet. The commenter feels the
proposed AD is far too complex.
We do not agree. The compliance section in the proposed AD is
sufficiently direct. We did not change the AD.
Request To Define Terms
Mesaba Airlines requests that we define the terms ``CSLI'' and
``HSLI'' in the proposed AD compliance section.
In response, we note that we already did, and direct Mesaba
Airlines to paragraph (f)(6) in the proposed AD, and in this AD, to
compliance paragraph (h)(6).
Request To Not Include Service Bulletin Requirements
Mesaba Airlines requests that we not include the requirements of
paragraph 3.A.(2)(d) of GEAE SB CF34-AL S/B 72-0250 in the AD.
We agree. We did not include those requirements in the AD.
Conclusion
We have carefully reviewed the available data, including the
comments 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 1,966 engines installed on
airplanes of U.S. registry. We estimate that the fan blade inspection
and replacement requirement will affect 300 of these engines, and the
actuator head hose inspection would affect 1,662 engines. We also
estimate that it will take 0.5 work-hour per engine to inspect the fan
blade abradable rub strip, 6 work-hours per engine to visually inspect
the fan blades, 11 work-hours per engine to perform an eddy current
inspection of the fan blades, and 0.25 work-hour per engine to inspect
the actuator head hose fitting, and that the average labor rate is $80
per work-hour. Required parts will cost $51,106,600. Based on these
figures, we estimate the total cost of the AD to U.S. operators to be
$51,184,000.
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 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
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 adding the following new airworthiness
directive:
2009-24-11 General Electric Company: Amendment 39-16103. Docket No.
FAA-2009-0328; Directorate Identifier 2008-NE-44-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
4, 2010.
Affected ADs
(b) None.
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 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 (SN) 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 with fan drive shaft, P/N 6036T78P02,
and airworthiness limitation section life limit of 22,000 CSN; and
(g) For CF34-3A1 engines with fan drive shaft, P/N 6036T78P02,
and airworthiness limitation section life limit of 15,000 CSN that
are in compliance with GE Aircraft Engines (GEAE) Service Bulletin
(SB) 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
(h) For CF34-3B1 engines with fan blades, P/Ns 6018T30P14 or
4923T56G08, that have a fan blade SN listed in Appendix A of GEAE SB
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 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 cycles-since-new (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
[[Page 62484]]
Instructions of GEAE SB 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 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 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 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 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 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 with fan drive shaft, P/N 6036T78P02,
and airworthiness limitation section life limit of 15,000 CSN, that
are not in compliance with GEAE SB 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
(k) For CF34-1A, CF34-3A, CF34-3A2, and CF34-3B engines with fan
blades, P/N 6018T30P14 or P/N 4923T56G08, that have a fan blade SN
listed in Appendix A of GEAE SB 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 fan blades, P/N 6018T30P14, from service within 2,400
CSN.
(2) Remove 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 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 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 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 a fan blade SN listed in Appendix A of GEAE SB 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
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 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 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 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 CF34-BJ S/B 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 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 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 life limit of
15,000 CSN; and
(ii) Is listed in Appendix A of GEAE SB CF34-BJ S/B 72-0229,
Revision 01, dated July 30, 2008; or
(iii) Is listed in Appendix A of GEAE SB CF34-BJ S/B 72-0230,
Revision 01, dated July 30, 2008.
[[Page 62485]]
(2) Do not install any fan blade into any CF34-3A1 engine with
fan drive shaft, P/N 6036T78P02, with an airworthiness limitation
section 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 life limit
of 22,000 CSN and,
(ii) Is listed in Appendix A of GEAE SB 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 03, 2008.
CF34-AL S/B 72-0250 Total Pages: 9.. All..................... 01 November 26, 2008.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
General Electric Company, GE-Aviation, Room 285, 1 Newmann 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on November 18, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E9-28236 Filed 11-27-09; 8:45 am]
BILLING CODE 4910-13-P
