[Federal Register Volume 70, Number 61 (Thursday, March 31, 2005)]
[Rules and Regulations]
[Pages 16401-16403]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-6247]



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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.

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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: [email protected].
    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.

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    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

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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]
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