[Federal Register Volume 64, Number 103 (Friday, May 28, 1999)]
[Rules and Regulations]
[Pages 28905-28907]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-13484]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-19-AD; Amendment 39-11179; AD 99-11-08]
RIN 2120-AA64
Airworthiness Directives; General Electric Aircraft Engines CF34
Series Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to General Electric Aircraft Engines (GE) CF34 series
turbofan engines, that requires installation of a main fuel control
(MFC) that incorporates a flange vent groove and installation of an MFC
with improved overspeed protection. This amendment is prompted by
reports of rapid uncommanded engine acceleration events. The actions
specified by this AD are intended to prevent uncommanded engine
accelerations, which could result in an engine overspeed, uncontained
engine failure, and damage to the airplane.
DATES: Effective date: July 27, 1999. The incorporation by reference of
certain publications listed in the regulations is approved by the
Director of the Federal Register as of July 27, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from GEAE Technical Publications, Attention: N. Hanna MZ340M2,
1000 Western Avenue, Lynn, MA 01910; telephone (781) 594-2906, fax
(781) 594-0600. This information may be examined at the Federal
Aviation Administration (FAA), New England Region, Office of the
Regional Counsel, 12 New England Executive Park, Burlington, MA; or at
the Office of the Federal Register, 800 North Capitol Street, NW, suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Norman Brown, Controls Specialist,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7181, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to General Electric Aircraft Engines
(GE) CF34 series turbofan engines was published in the Federal Register
on September 18, 1998 (63 FR 49877). That action proposed to require,
within 800 hours time in service (TIS), or 120 days after the effective
date of this AD, whichever occurs first, installation of an MFC
incorporating a flange vent groove. In addition, the action proposed to
require installation of an MFC with improved overspeed protection: for
CF34-3A1 and -3B1 series engines, installed on Canadair Regional Jet
airplanes, within 4,000 hours TIS after the effective date of this AD,
or 24 months after the effective date of this AD, whichever occurs
first; and for CF34-1A, -3A, -3A1, -3A2, and -3B series engines,
installed on Canadair Challenger airplanes, at the next hot section
inspection, or within 60 months after the effective date of this AD,
whichever occurs first. The actions are required to be accomplished in
accordance with GE CF34 Alert Service Bulletin (ASB) No. A73-18,
Revision 1, dated September 24, 1997; CF34 ASB No. A73-32, Revision 2,
dated May 29, 1998; CF34 ASB No. A73-33, Revision 1, dated May 29,
1998; and CF34 ASB No. A73-19, Revision 1, dated February 20, 1998.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public.
Since the publication of the notice of proposed rule making (NPRM),
GE has issued Revision 2, dated May 29, 1998, to ASB A73-32 that added
effectivity information to the Planning Information section of ASB A73-
32. GE has also issued Revision 1, dated May 29, 1998 to ASB 73-33 that
added effectivity information to the Planning Information section of
ASB A73-33. The ASB revisions have not affected the technical or
economic content of this proposed AD. We have added the updated ASB
revisions to paragraphs (a), (b)(1), and (b)(2) of the compliance
section of this AD. GE has implemented the vent groove and improved
overspeed protection design changes in new MFC's. In addition, we have
made editorial changes to the compliance section of this AD to improve
readability and to remove ambiguity. We changed the requirement ``with
a flange vent groove reworked in accordance with'' in paragraph (a) to
``with a flange vent groove modified in accordance with.'' We made the
change so that you are not restricted to installing only reworked
MFC's, and to allow you to install a new MFC with the design
improvements. We added the base part number 6078T55 of the MFC to each
of the P0X numbers to remove any ambiguity over the MFC's that must be
replaced. We changed the requirement ``Install a reworked MFC with
improved overspeed protection'' in paragraph (b) to ``Install a
serviceable MFC with improved overspeed protection.'' We made the
change to allow you to install a new MFC that incorporates the improved
overspeed protection design change, and so you are not restricted to
installing only reworked MFC's. We added the word ``within'' to the
requirements of paragraphs (b)(1), (b)(2), and (b)(3) to allow you to
perform the actions before reaching the specified calendar times after
the effective date of the AD. We removed the new MFC P/N's from
paragraphs (b)(1), (b)(2), and (b)(3) and changed ``install MFC'' to
``install a serviceabl MFC.'' We removed the
P/N's so that you will not have to request an alternate method of
compliance in accordance with paragraph (d) of this AD if a new MFC P/N
is certificated for use on the applicable engines. We also added a new
paragraph (c) that defines a serviceable MFC.
After careful review of the available data, including the changes
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (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
[[Page 28906]]
impact, positive or negative, on a substantial number of small entities
under the criteria of the Regulatory Flexibility Act. A final
evaluation has been prepared for this action and it is contained in the
Rules Docket. A copy of it may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to 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
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
99-11-08 General Electric Aircraft Engines: Amendment 39-11179.
Docket 98-ANE-19-AD.
Applicability: General Electric Aircraft Engines (GE) CF34-1A,
CF34-3A, -3A1, -3A2, and CF34-3B and -3B1 series turbofan engines,
installed on but not limited to Bombardier, Inc. Canadair airplane
models CL-600-2A12, -2B16, and -2B19.
Note 1: This airworthiness directive (AD) applies to each engine
identified in the preceding applicability provision, regardless of
whether it has been modified, altered, or repaired in the area
subject to the requirements of this AD. For engines that have been
modified, altered, or repaired so that the performance of the
requirements of this AD is affected, the owner/operator must request
approval for an alternative method of compliance in accordance with
paragraph (d) of this AD. The request should include an assessment
of the effect of the modification, alteration, or repair on the
unsafe condition addressed by this AD; and, if the unsafe condition
has not been eliminated, the request should include specific
proposed actions to address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent uncommanded engine accelerations, which could result
in an engine overspeed, uncontained engine failure, and damage to
the airplane, accomplish the following:
(a) For all CF34-3A1 -3B, and -3B1 engines, with main fuel
control (MFC) part numbers (P/N's) 6078T55P02, 6078T55P03,
6078T55P04, 6078T55P05, 6078T55P06, 6078T55P07, 6078T55P08,
6078T55P09, or 6078T55P10 installed, within 800 hours time in
service (TIS), or 120 days after the effective date of this AD,
whichever occurs first, install an MFC with a flange vent groove
modified in accordance with the Accomplishment Instructions of GE
CF34 Alert Service Bulletin (ASB) No. A73-18, Revision 1, dated
September 24, 1997, or CF34 ASB No. A73-32, Revision 1, dated
September 24, 1997, or Revision 2, dated May 29, 1998, as
applicable.
(b) Install a serviceable MFC with improved overspeed protection
as follows:
(1) For all CF34-1A, -3A, and -3A2 series engines, install a
serviceable MFC at the next hot section inspection, or within 60
months after the effective date of this AD, whichever occurs first,
in accordance with step 2A through step 2G of the Accomplishment
Instructions of CF34 ASB No. A73-33, dated November 21, 1997, or
Revision 1, dated May 29, 1998.
(2) For CF34-3A1, and -3B series engines installed on Canadair
aircraft models CL601 or CL604 (Challenger airplanes), install a
serviceable MFC at the next hot section inspection, or within 60
months after the effective date of this AD, whichever occurs first,
in accordance with step 2A through step 2G of the Accomplishment
Instructions of CF34 ASB No. A73-33, dated November 21, 1997, or
Revision 1, dated May 29, 1998.
(3) For CF34-3A1 and -3B1 series engines installed on Canadair
aircraft model CL601RJ (Regional Jet airplanes), install a
serviceable MFC within 4,000 hours TIS after the effective date of
this AD, or within 24 months after the effective date of this AD,
whichever occurs first, in accordance with step 2A through step 2G
of the Accomplishment Instructions of CF34 ASB No. A73-19, Revision
1, dated February 20, 1998.
(c) For the purposes of this AD, a serviceable MFC is defined as
a new MFC that incorporates the improved overspeed protection
modifications, or an MFC that has been reworked to provide the
improved overspeed protection as provided by the applicable GE ASB.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Engine Certification Office.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Engine Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(e) Special flight permits may be issued in accordance with
Sec. Sec. 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(f) The MFC replacement must be done in accordance with the
following General Electric Aircraft Engines alert service bulletins:
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Document No. Pages Revision Date
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A73-18......................... All.................... 1..................... September 24, 1997.
A73-19......................... All.................... 1..................... February 20, 1998.
A73-32......................... All.................... 1..................... September 24, 1997.
A73-32......................... All.................... 2..................... May 29, 1998.
A73-33......................... All.................... Original.............. November 21, 1997.
A73-33......................... All.................... 1..................... May 29, 1998.
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[[Page 28907]]
This incorporation by reference was approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from GEAE Technical Publications,
Attention: N. Hanna MZ340M2, 1000 Western Avenue, Lynn, MA 01910;
telephone (781) 594-2906, fax (781) 594-0600. Copies may be
inspected at the FAA, New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA; or at the
Office of the Federal Register, 800 North Capitol Street, NW, suite
700, Washington, DC.
(g) This amendment becomes effective on July 27, 1999.
Issued in Burlington, Massachusetts, on May 17, 1999.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 99-13484 Filed 5-27-99; 8:45 am]
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