[Federal Register Volume 67, Number 59 (Wednesday, March 27, 2002)]
[Rules and Regulations]
[Pages 14630-14632]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-6912]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-05-AD; Amendment 39-12684; AD 2002-06-07]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6-80E1 
Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to General Electric Company (GE) CF6-80E1 series turbofan 
engines, installed on Airbus Industrie A330 series airplanes. This 
action requires initial and repetitive pressure testing of the 
directional pilot valve (DPV) assembly, with replacement of DPV 
assemblies that fail the pressure test, or, replacing the DPV assembly 
without performing pressure testing, with a serviceable DPV assembly, 
or, deactivating the fan reverser for no longer than 10 days until 
replacement of the DPV assembly is done. This amendment is prompted by 
a review of thrust reverser safety analyses following a report of 
inadvertent thrust reverser deployment on another make and model 
engine. The actions specified in this AD are intended to prevent 
inadvertent thrust reverser deployment, which, if it occurred in-
flight, could result in loss of control of the airplane.

DATES: Effective May 1, 2002. The incorporation by reference of certain 
publications listed in the rule is approved by the Director of the 
Federal Register as of May 1, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before May 28, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2002-NE-05-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: ``[email protected]''. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The service information referenced in this AD may be obtained from 
Middle River Aircraft Systems, Mail Point 46, 103 Chesapeake Park 
Plaza, Baltimore, MD, 21220-4295, attn: Warranty Support, telephone: 
(410) 682-0094, fax: (410) 682-0100. This information may be examined, 
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: Karen Curtis, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7192; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA received a report of inadvertent 
thrust reverser deployment on a Pratt & Whitney powered Airbus 
Industrie A300-600 series airplane. Following that event, the FAA 
reviewed thrust reverser safety analyses on other make and model 
engines, including GE CF6-80E1 series turbofan engines that are used on 
Airbus Industrie A330 series airplanes. A review of thrust reverser 
actuation system (TRAS) shop findings and component failure rate data, 
test data, and system safety analyses revealed that a hidden failure 
mode involving the directional pilot valve (DPV) assembly exists. The 
DPV assembly controls the direction of the operation of the center 
drive unit when the TRAS is activated. If high pressure downstream of 
the pressure regulating and shutoff valve (PRSOV) exists in combination 
with a leaking DPV assembly, an inadvertent deployment could occur. 
High pressure downstream of the PRSOV can be caused by auto-restow of 
the thrust reverser, PRSOV open failures, or significant PRSOV leakage. 
PRSOV open failures and significant PRSOV leakage are detected by the 
DPV assembly pressure switch. DPV assembly open failures and 
significant DPV assembly leakage are detected by the inability to stow 
the reverser. However, there exists a range of DPV assembly leakage 
rates from a closed DPV assembly which are not detectable during normal 
operation.

[[Page 14631]]

This undetectable failure mode of the DPV assembly, concurrent with 
high pressure downstream of the PRSOV, can result in an inadvertent 
thrust reverser deployment. This condition, if not corrected, could 
result in inadvertent thrust reverser deployment, which, if it occurred 
in-flight, could result in loss of control of the airplane.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of Middle 
River Aircraft Systems CF6-80E1 Alert Service Bulletin (ASB) No. 
78A5053, dated October 30, 2001, that describes procedures for thrust 
reverser inspections and checks, and DPV assembly replacement.

FAA's Determination of an Unsafe Condition and Required Actions

    Although none of these affected engine models are used on any 
airplanes that are registered in the United States, the possibility 
exists that the engine models could be used on airplanes that are 
registered in the United States in the future. Since an unsafe 
condition has been identified that is likely to exist or develop on 
other GE CF6-80E1 series turbofan engines of the same type design, 
installed on Airbus Industrie A330 series airplanes, this AD is being 
issued to prevent inadvertent thrust reverser deployment, which, if it 
occurred in-flight, could result in loss of control of the airplane. 
This AD requires:
     Initial and repetitive pressure testing of the DPV 
assembly, with replacement of DPV assemblies that fail the pressure 
test, or
     Replacing the DPV assembly without performing pressure 
testing, with a serviceable DPV assembly, or
     Deactivating the fan reverser for no longer than 10 days 
until replacement of the DPV assembly is done.
    The actions are required to be done in accordance with the service 
bulletin described previously.

Immediate Adoption of This AD

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for prior public comment are unnecessary. 
Therefore, a situation exists that allows the immediate adoption of 
this regulation.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NE-05-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it would 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, 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:

2002-06-07  General Electric Company: Amendment 39-12684. Docket No. 
2002-NE-05-AD.

Applicability

    This airworthiness directive (AD) is applicable to General 
Electric Company (GE) CF6-80E1 series turbofan engines that are 
installed on Airbus Industrie A330 series airplanes.

    Note 1: This 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

    Compliance with this AD is required as indicated, unless already 
done.
    To prevent inadvertent thrust reverser deployment, which, if it 
occurred in-flight, could result in loss of control of the airplane, 
do the following:
    (a) Perform one of the following, in accordance with paragraphs 
2.B. and 2.C. of the Accomplishment Instructions of Middle River 
Aircraft Systems Alert Service Bulletin (ASB) No. 78A5053, dated 
October 30, 2001, before exceeding 7,000 flight hours time-since-new 
(TSN) or 1,000 flight hours time-in-service (TIS) after the 
effective date of this AD:
    (1) Perform a directional pilot valve (DPV) assembly pressure 
check for leakage, and, if necessary, do one of the following:

[[Page 14632]]

    (i) Replace the DPV assembly with a serviceable assembly, and 
then perform a system test of the thrust reverser, or
    (ii) Deactivate the thrust reverser. However, the DPV assembly 
must be replaced with a serviceable assembly, and a system test of 
the thrust reverser performed within 10 days after deactivation.
    (2) Replace the DPV assembly with a serviceable assembly, and 
then perform a system test of the thrust reverser.
    (b) Thereafter, at intervals not to exceed 7,000 flight hours 
TIS since the last check or replacement of the DPV assembly, perform 
one of the following, in accordance with paragraphs 2.B and 2.C. of 
the Accomplishment Instructions of Middle River Aircraft Systems ASB 
No. 78A5053, dated October 30, 2001:
    (1) Perform a DPV assembly pressure check for leakage, and, if 
necessary, either:
    (i) Replace the DPV assembly with a serviceable assembly and 
then perform a system test of the thrust reverser, or
    (ii) Deactivate the thrust reverser. However, the DPV assembly 
must be replaced with a serviceable assembly, and a system test of 
the thrust reverser performed within 10 days after deactivation.
    (2) Replace the DPV assembly with a serviceable assembly and 
then perform a system test of the thrust reverser.

Definition of Serviceable DPV Assembly

    (c) For the purpose of this AD, a serviceable DPV assembly is an 
assembly that has either accumulated zero TSN, or has accumulated 
zero TIS after having passed the tests in the Middle River Aircraft 
Systems Component Maintenance Manual GEK 85007 (78-31-51), 
Directional Pilot Solenoid Valve, Page Block 101, Testing and 
Troubleshooting, or has been successfully leak checked in accordance 
with paragraph 2.B. of the Accomplishment Instructions of Middle 
River Aircraft Systems ASB No. 78A5053, dated October 30, 2001.

Alternative Methods of Compliance

    (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 (ECO). 
Operators must submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the ECO.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
Secs. 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 done.

Incorporation by Reference

    (f) The actions required by this AD must be done in accordance 
with Middle River Aircraft Systems CF6-80E1 Alert Service Bulletin 
(ASB) No. 78A5053, dated October 30, 2001.
    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 Middle River Aircraft Systems, 
Mail Point 46, 103 Chesapeake Park Plaza, Baltimore, MD, 21220-4295, 
attn: Warranty Support, telephone: (410) 682-0094, fax: (410) 682-
0100. Copies may be inspected, 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 Capital Street, NW., suite 700, Washington, DC.

Effective Date

    (g) This amendment becomes effective on May 1, 2002.

    Issued in Burlington, Massachusetts, on March 14, 2002.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-6912 Filed 3-26-02; 8:45 am]
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