[Federal Register: April 5, 2005 (Volume 70, Number 64)]
[Rules and Regulations]
[Page 17199-17201]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05ap05-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2004-NE-06-AD; Amendment 39-14033; AD 2005-07-09]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF34-8E Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for General Electric Company (GE) CF34-8E series turbofan engines
with certain serial number (SN) master variable geometry (VG) actuators
installed. That AD currently requires initial and repetitive reviews of
the airplane computer systems for master VG actuator fault messages.
That AD also requires replacement of actuators reported faulty by the
Full Authority Digital Engine Control (FADEC). This AD requires the
same reviews. This AD also prohibits installation of affected master VG
actuators onto any CF34-8E series turbofan engine after the effective
date of the AD. This AD results from the need to add to the list of
affected parts, master VG actuators made by a parts manufacturing
approval (PMA) holder. We are issuing this AD to prevent dual-channel
electrical signal faults in the master VG actuator which will cause an
uncommanded reduction of thrust to idle with a subsequent loss of the
ability to advance thrust above idle, and will result in a multiengine
loss of thrust if dual-channel faults occur on more than one engine
simultaneously.
DATES: Effective April 20, 2005. The Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulations as of April 20, 2005.
We must receive any comments on this AD by June 6, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2004-NE-06-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information referenced in this AD from
General Electric Company via Lockheed Martin Technology Services, 10525
Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672-
8400, fax (513) 672-8422.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA. You may examine the service information, at the FAA,
New England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Robert Grant, Aerospace Engineer,
Aircraft Certification Office, FAA, Engine and Propeller Directorate,
12 New England Executive Park, Burlington, MA; telephone (781) 238-
7757; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: On February 13, 2004, the FAA issued AD
2004-04-04, Amendment 39-13485 (69 FR 8098, February 23, 2004). That AD
requires initial and repetitive reviews of the airplane computer
systems for master VG actuator fault messages of certain SN master VG
actuators. That AD also requires replacement of actuators reported
faulty by the FADEC. The background for that AD is as follows:
In September of 2002, GE, the manufacturer of CF34-8E series
turbofan engines, replaced its supplier
[[Page 17200]]
of dual-channel linear variable differential transformers (LVDTs),
installed on the master VG actuator, part number 4120T02P02. Since that
changing of suppliers, four master VG actuators, installed on CF34-8E
engines, with LVDTs produced by the new supplier have been reported
with single-channel electrical signal faults. The CF34-8E engines use
the same part number VG master actuator as the CF34-8C series engines,
which have experienced 54 LVDT faults in service, to date. One of these
master VG actuators also experienced a failure of the second LVDT
channel, seventeen days after the first single-channel fault report,
resulting in the FADEC commanding the engine power to idle. The
manufacturer's investigation revealed LVDT coil wire deformation and
breakage, caused by thermal expansion of potting material. That
condition, if not corrected, could result in dual channel electrical
signal faults in the master VG actuator, which will cause an
uncommanded reduction of thrust to idle with a subsequent loss of the
ability to advance thrust above idle, and result in multiengine loss of
thrust if dual-channel faults occur on more than one engine
simultaneously, and possible loss of the airplane.
Actions Since AD 2004-04-04 Was Issued
Since AD 2004-04-04 was issued, we learned that PMA holder, Arkwin
Industries, Inc., has master VG actuators in service with affected
LVDTs installed. The same unsafe condition described previously for
master VG actuators, SN APM238AE, and SNs APM242AE and up, is likely to
exist or develop on these PMA master VG actuators. The PMA actuators
are identified by P/N 1211508-002, SN 238AE, and SNs 241AE and up.
These actuators also have GE P/N 4120T02P02 marked on them.
Relevant Service Information
We have reviewed and approved the technical contents of GE Alert
Service Bulletin (ASB) No. CF34-8E-AL S/B 75-A0001, Revision 3, dated
February 14, 2005, that describes procedures for initial and repetitive
reviews of the airplane computer systems for fault messages, and
replacement of actuators reported faulty by the FADEC.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other CF34-8E series turbofan engines of the same type
design. We are issuing this AD to prevent dual-channel electrical
signal faults in the master VG actuator, which will cause an
uncommanded reduction of thrust to idle with a subsequent loss of the
ability to advance thrust above idle, and will result in a multiengine
loss of thrust if dual-channel faults occur on more than one engine
simultaneously.
This AD prohibits installation of any master VG actuator specified
in this AD, onto any CF34-8E series turbofan engine after the effective
date of the AD. This AD also requires an initial review within 10 days
after the effective date of the AD, of the airplane computer systems
for fault messages, and replacement of actuators reported faulty by the
FADEC. Actuator hardware troubleshooting may be required to identify
faulty actuators. Also, this AD requires the same repetitive reviews,
at intervals not to exceed 10 days. Replacement of actuators reported
faulty by the FADEC is required either before further flight or within
10 days of the first fault occurrence, based on requirements defined in
the service information described previously, for the actual fault
reported. 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 submit any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2004-NE-06-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the rule
that might suggest a need to modify it. If a person contacts us
verbally, and that contact relates to a substantive part of this AD, we
will summarize the contact and place the summary in the docket. We will
consider all comments received by the closing date and may amend the AD
in light of those comments.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
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 the regulation:
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 by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2004-NE-06-AD'' in your request.
[[Page 17201]]
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 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 39-13485 (69 FR
8098, February 23, 2004), and by adding a new airworthiness directive,
Amendment 39-14033, to read as follows:
2005-07-09 General Electric Company: Amendment 39-14033. Docket No.
2004-NE-06-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
20, 2005.
Affected ADs
(b) This AD supersedes AD 2004-04-04, Amendment 39-13485.
Applicability
(c) This AD applies to General Electric Company (GE) CF34-8E
series turbofan engines with the master variable geometry (VG)
actuators, GE part number (P/N) 4120T02P02, serial number (SN)
APM238AE, and SNs APM242AE and up; and Arkwin Industries, Inc. Parts
Manufacturer Approval (PMA) P/N 1211508-002, SN 238AE, and SNs 242AE
and up installed. The Arkwin PMA parts are also marked with P/N
4120T02P02. These engines are installed on, but not limited to,
Embraer 170 series airplanes.
Unsafe Condition
(d) This AD results from the need to add to the list of affected
parts, master VG actuators made by PMA holder, Arkwin Industries,
Inc. We are issuing this AD to prevent dual-channel electrical
signal faults in the VG master actuator, which will cause an
uncommanded reduction of thrust to idle with a subsequent loss of
the ability to advance thrust above idle, and which will result in a
multiengine loss of thrust if dual-channel faults occur on more than
one engine simultaneously.
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.
(f) After the effective date of this AD, do not install master
VG actuators specified in this AD onto any engine.
Initial Review
(g) Within 10 days after the effective date of this AD,
initially review the airplane computer systems for fault messages,
and replace actuators with faults reported by the full-authority
digital electronic control (FADEC). Follow the review and
replacement requirements of paragraph 3 of the Accomplishment
Instructions of GE Alert Service Bulletin (ASB) No. CF34-8E-AL S/B
75-A0001, Revision 3, dated February 14, 2005. The specific review
instructions depend on the version of FADEC software installed at
the time of the review, as detailed in the ASB.
Repetitive Review
(h) At intervals not to exceed 10 days, repetitively review the
computer systems for fault messages, and replace actuators with
faults reported by the FADEC. Follow the review and replacement
requirements of paragraph 3 of the Accomplishment Instructions of GE
ASB No. CF34-8E-AL S/B 75-A0001, Revision 3, dated February 14,
2005. The specific review instructions depend on the version of
FADEC software installed at the time of the review, as detailed in
the ASB.
Optional Terminating Action
(i) As an optional terminating action to the repetitive reviews
specified in this AD, replace the master VG actuator with a master
VG actuator not specified in this AD.
Previous Credit
(j) Previous credit is allowed for reviews and replacements of
master VG actuators performed before the effective date of this AD,
using paragraph 3 of GE ASB No. CF34-8E-AL S/B 75-A0001 Revision 1,
dated February 10, 2004, or Revision 2, dated December 15, 2004, or
Revision 3, dated February 14, 2005.
Alternative Methods of Compliance
(k) 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.
Special Flight Permits
(l) Under 39.23, the FAA imposes the following conditions and
limitations on the issuance and use of Special Flight Permits for
this AD:
(1) If both engines report FADEC status messages, with dispatch
classification the same as an actuator LVDT fault, at the same time,
whether intermittent or continuous, at least one engine must be
cleared of faults before further flight, even if none of the faults
are VG actuator-related.
(2) If both engines report FADEC status messages with dispatch
classification the same as an actuator LVDT fault, at the same time,
whether intermittent or continuous, the airplane computer systems
must be reviewed for master VG actuator faults before further
flight. If actuator faults are present for both engines, then at
least one master VG actuator must be replaced before further flight.
(3) If intermittent status messages are posted for both engines,
with the same dispatch classification as LVDT faults, and the cause
cannot be found, one of the actuators must be replaced before
further flight.
(4) If a master VG actuator with a single channel fault switches
channels, the actuator must be replaced before further flight.
Material Incorporated by Reference
(m) You must use GE Alert Service Bulletin No. CF34-8E-AL S/B
75-A0001, Revision 3, dated February 14, 2005, to perform the
reviews and actuator dispositions required by this AD. You can get a
copy from General Electric Company via Lockheed Martin Technology
Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215,
telephone (513) 672-8400, fax (513) 672-8422. You may review copies
at the FAA, New England Region, Office of the Regional Counsel, 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/code_of_federal_regulations/ibr_locations.html
.
Related Information
(n) None.
Issued in Burlington, Massachusetts, on March 25, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 05-6343 Filed 4-4-05; 8:45 am]
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