[Federal Register Volume 69, Number 1 (Friday, January 2, 2004)]
[Rules and Regulations]
[Pages 2-4]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-31665]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-58-AD; Amendment 39-13402; AD 2003-26-05]
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 adopting a new 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. This AD 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. This AD also requires replacement of actuators reported 
faulty by the Full Authority Digital Engine Control (FADEC). This AD 
results from nine reports of master VG actuator electrical signal 
faults, one report of which was a dual-channel fault, resulting in the 
FADEC commanding the engine power to idle. We are issuing this AD to 
prevent VG master actuator dual-channel electrical signal faults:
    [sbull] Which will cause an uncommanded reduction of thrust to idle 
with a subsequent loss of the ability to advance thrust above idle; and
    [sbull] Could result in a multi-engine loss of thrust if dual-
channel faults occur on more than one engine simultaneously.

DATES: This AD becomes effective January 20, 2004. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of January 20, 2004.
    We must receive any comments on this AD by March 2, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
    [sbull] By mail: The 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.
    [sbull] By fax: (781) 238-7055.

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    [sbull] 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. You may examine the service 
information, by appointment, 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.

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: In September of 2002, GE, the manufacturer 
of CF34-8C1 series and CF34-8C5 series turbofan engines replaced its 
supplier of dual-channel linear variable differential transformers 
(LVDTs), installed on the master VG actuator, P/N 4120T02P02. Since 
that changing of suppliers, nine master VG actuators with LVDTs 
produced by the new supplier have been reported with single-channel 
electrical signal faults sent to the MDC and to the FADEC. 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 on-going investigation has revealed LVDT coil wire 
deformation and breakage, caused by thermal expansion of potting 
material. The affected master VG actuators are identified by SNs 
APM238AE, and SNs APM242AE and up. A dual channel LVDT failure that 
occurs at a certain phase of flight will result in a single engine loss 
of thrust control. VG master actuators with dual channel LVDT failures 
that occur simultaneously on multiple engines will cause a multi-engine 
loss of thrust control.

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 1, dated 
November 7, 2003, that describes procedures for initial and repetitive 
reviews of the airplane MDC for master VG actuator fault messages, and 
if the MDC is inoperative, reviews of the EICAS 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 CF34-8C1 series and CF34-8C5 series turbofan engines 
of the same type design. We are issuing this AD to prevent VG master 
actuator dual-channel electrical signal faults:
    [sbull] Which will cause an uncommanded reduction of thrust to idle 
with a subsequent loss of the ability to advance thrust above idle; and
    [sbull] Could result in a multi-engine 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 master VG actuator 
fault messages, and if the MDC is inoperative, a review of the EICAS 
for fault messages, and replacement of actuators reported faulty by the 
FADEC. This AD also requires 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. 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.

Changes to 14 CFR Part 39--Effect on the AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47998, July 22, 2002), which governs our AD system. This regulation now 
includes material that relates to special flight permits, alternative 
methods of compliance, and altered products. This material previously 
was included in each individual AD. Since this material is included in 
14 CFR part 39, we will not include it in future AD actions.

Interim Action

    These actions are interim actions and we may take further 
rulemaking actions in the future.

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. 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.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications with you. You can get more information about plain 
language at http://www.faa.gov/language and http://www.plainlanguage.gov.

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.

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;

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    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 adding the following new airworthiness 
directive:

2003-26-05 General Electric Company: Amendment 39-13402. Docket No. 
2003-NE-58-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
20, 2004.

Affected ADs

    (b) None.

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, part number 4120T02P02, serial number (SN) 
APM238AE, and SNs APM242AE and up, installed. 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 nine reports of master VG actuator 
electrical signal faults, one report of which was a dual-channel 
fault, resulting in the Full Authority Digital Engine Control 
(FADEC) commanding the engine power to idle. We are issuing this AD 
to prevent VG master actuator dual-channel electrical signal faults:
    (1) Which will cause an uncommanded reduction of thrust to idle 
with a subsequent loss of the ability to advance thrust above idle; 
and
    (2) Could result in a multi-engine 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.

Initial Review

    (f) 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 
1, dated November 7, 2003.

Repetitive Review

    (g) 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 1, dated November 7, 2003.

Alternative Methods of Compliance

    (h) 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

    (i) 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 fault 1 messages at the same 
time, whether intermittent or continuous, the MDC must be reviewed 
for master VG actuator faults before further flight. If actuator 
faults are still present for both engines, then at least one master 
VG actuator must be replaced before further flight.
    (2) If a master VG actuator switches channels, the actuator must 
be replaced before further flight.

Material Incorporated by Reference

    (j) You must use GE Alert Service Bulletin No. CF34-8C-AL S/B 
75-A0007, Revision 1, dated November 7, 2003, to perform the reviews 
and actuator dispositions required by this AD. The Director of the 
Federal Register approved the incorporation by reference of this 
service bulletin in accordance with 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 Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

Related Information

    (k) None.

    Issued in Burlington, Massachusetts, on December 17, 2003.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-31665 Filed 12-31-03; 8:45 am]
BILLING CODE 4910-13-P