[Federal Register: March 31, 2005 (Volume 70, Number 61)]
[Rules and Regulations]
[Page 16401-16403]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr31mr05-5]
[[Page 16401]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-58-AD; Amendment 39-14030; AD 2005-07-06]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF34-8C1
Series and CF34-8C5 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for General Electric Company (GE) CF34-8C1 series and CF34-8C5
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 Maintenance Data
Computer (MDC) for master VG actuator fault messages, and if the MDC is
inoperative, reviews of the Engine Indication and Crew Alerting System
(EICAS) for fault messages. That AD also requires replacing actuators
reported faulty by the Full Authority Digital Engine Control (FADEC).
This ad requires those same actions, and expands the applicability to
additional actuators by part number (P/N) and SN. This AD also
prohibits installation of affected master VG actuators onto any CF34-
8C1 and CF34-8C5 engine after the effective date of this AD. This AD
results from the need to add to the list of affected parts, master VG
actuators made by parts manufacturer approval (PMA). 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.
DATES: Effective April 15, 2005. The Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulations as of April 15, 2005.
We must receive any comments on this AD by May 31, 2005.
ADDRESSES: Use one of the following addresses to comment on this AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2003-NE-58-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, by appointment, 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 December 17, 2003, the FAA issued AD
2003-26-05, Amendment 39-13402 (69 FR 2, January 2, 2004). That AD
requires initial and repetitive reviews of the airplane Maintenance
Data Computer (MDC) for fault messages for the master VG actuator, and
if the MDC is inoperative, reviews of the Engine Indication and Crew
Alerting System (EICAS) for fault messages. That AD also requires
replacing actuators reported faulty by the Full Authority Digital
Engine Control (FADEC). That AD resulted from reports of nine master VG
actuators with linear variable differential transformers (LVDTs) with
single-channel electrical signal faults sent to the MDC and to the
FADEC. One of those master VG actuators also experienced a failure of
the second LVDT channel 17 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 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.
Actions Since We Issued AD 2003-26-05
Since we issued AD 2003-26-05, we have become aware of a PMA
holder, Arkwin Industries, Inc., that has master VG actuators in
service with the same 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 additional PMA
master VG actuators. We also received an additional 45 reports of
single-channel electrical signal faults. The PMA P/N and SNs of the
additional master VG actuators are P/Ns 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. CF34-8C-AL S/B 75-A0007, Revision 3, dated
February 14, 2005, that describes procedures for:
Initial and repetitive reviews of the airplane MDC for
fault messages from the master VG actuator,
Reviews of the EICAS for fault messages if the MDC is
inoperative, and
Replacing 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 CF34-8C1 series and CF34-8C5 series turbofan engines
of the same type design. 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.
This AD requires:
An initial review within 10 days after the effective date
of the AD, of the airplane MDC for fault messages for the master VG
actuator, and if the MDC is inoperative, a review of the EICAS for
fault messages, and replacement of actuators reported faulty by the
FADEC.
The same reviews, repetitively, at intervals not to exceed
10 days, and replacement of actuators reported faulty by the FADEC
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.
After the effective date of this AD, do not install any
master VG actuator that has a part number and serial number listed in
this AD onto any engine.
[[Page 16402]]
You must use the service information described previously to
perform the actions required by this AD.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-58-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. 2003-NE-58-AD'' in your request.
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 39-13402, 69 FR 2,
January 2, 2004, and by adding a new airworthiness directive, Amendment
39-14030, to read as follows:
2005-07-06 General Electric Company: Amendment 39-14030. Docket No.
2003-NE-58-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
15, 2005.
Affected ADs
(b) This AD supersedes AD 2003-26-05, Amendment 39-13402.
Applicability
(c) This AD applies to General Electric Company (GE) CF34-8C1
series and CF34-8C5 series turbofan engines, with master variable
geometry (VG) actuators, GE part number 4120T02P02, serial number
(SN) APM238AE, and SNs APM242AE and up; and Arkwin Industries, Inc.
Parts Manufacturer Approval (PMA) part number 1211508-002, SN 238AE
and SNs 242AE and up installed. The Arkwin PMA parts are also marked
with PN 4120T02P02. These engines are installed on, but not limited
to, Bombardier Inc. Model CL-600-2C10 (CRJ-700 & -701) and CL-600-
2D24 (CRJ-900) airplanes.
Unsafe Condition
(d) This AD results from the need to add to the list of affected
parts, master VG actuators made by parts PMA. 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 any
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 Maintenance Data Computer (MDC) fault history,
and if the MDC is inoperative, review the Engine Indication and Crew
Alerting System (EICAS) 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
Alert Service Bulletin (ASB) No. CF34-8C-AL S/B 75-A0007, Revision
3, dated February 14, 2005.
Repetitive Review
(h) At intervals not to exceed 10 days, repetitively review the
MDC fault history, and if the MDC is inoperative, review the EICAS
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-
8C-AL S/B 75-A0007, Revision 3, dated February 14, 2005.
Optional Terminating Action
(i) Replacing an affected master VG Actuator with a master VG
actuator not specified in this AD is terminating action for
[[Page 16403]]
the repetitive inspections requirement specified in paragraph (h) of
this AD for that actuator.
Credit for Actions Previously Completed
(j) Inspections completed before the effective date of this AD
using GE ASB No. CF34-8C-AL S/B 75-A0007, Revision 1 dated November
7, 2003; or Revision 2 dated December 16, 2004; or Revision 3 dated
February 14, 2005; are acceptable for compliance with the
corresponding inspection in this AD.
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, we impose the following conditions and
limitations on the issuance and use of Special Flight Permits for
this AD:
(1) If both engines report FADEC fault 1 messages at the same
time, whether intermittent or continuous, review the MDC for master
VG actuator faults before further flight. If actuator faults are
still present for both engines, then replace at least one master VG
actuator before further flight.
(2) If a master VG actuator switches channels, replace the
actuator before further flight.
Material Incorporated by Reference
(m) You must use GE Alert Service Bulletin No. CF34-8C-AL S/B
75-A0007, Revision 3, dated February 14, 2005, to perform the
reviews and actuator dispositions required by this AD. The Director
of the Federal Register approved the incorporation by reference of
GE Alert Service Bulletin No. CF34-8C-AL S/B 75-A0007, Revision 3,
dated February 14, 2005, under 5 U.S.C. 552(a) and 1 CFR part 51.
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 Federal Aviation Administration (FAA), New England
Region, Office of the Regional Counsel, 12 New England Executive
Park, Burlington, MA 01803-5299; 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 23, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-6247 Filed 3-30-05; 8:45 am]
BILLING CODE 4910-13-P