[Federal Register Volume 67, Number 100 (Thursday, May 23, 2002)]
[Rules and Regulations]
[Pages 36090-36092]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-12631]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-04-AD; Amendment 39-12754; AD 2002-10-08]
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 thrust reverser inspections and 
checks, and allows extended threshold and repetitive inspection 
intervals for certain inspections if an optional double p-seal 
configuration is installed. This amendment is prompted by reports of 
service-induced hardware deterioration that reduces the overall thrust 
reverser system protection against inadvertent deployment, which can 
result in loss of control of the airplane. The actions specified in 
this AD are intended to prevent inadvertent in-flight thrust reverser 
deployment, which can result in loss of control of the airplane.

DATES: Effective June 27, 2002. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of June 27, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before July 22, 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-04-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8:00 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 Office Park; telephone (781) 238-7192; fax (781) 
238-7199.

SUPPLEMENTARY INFORMATION: The FAA has determined that thrust reverser 
inspections and checks are necessary as precautionary actions, to 
provide an acceptable level of safety for GE CF6-80E1 series turbofan 
engines. This determination has been made after reviewing thrust 
reverser safety analyses following a report of inadvertent thrust 
reverser deployment on another make and model engine. This amendment is 
prompted by the following reports:
    -The translating cowl inner bondment (bulb) seal can become 
deformed during use in service, resulting in cuts, tears, nicks, holes, 
and missing sections that compromise aerodynamic stow retention.
    -The forward (Dagmar) fairing and the aft frame assembly 
can become damaged during use in service, compromising stow retention.
    -The center drive unit (CDU) cone brake holding torque can 
become less than the minimum acceptable value to the extent that the 
CDU cone brake becomes inoperative.
    -The thrust reverser electromechanical brake holding torque 
can become less than the minimum acceptable value to the extent that 
the thrust reverser actuation system (TRAS) lock becomes inoperative. 
This holding torque of less than the minimum acceptable value can also 
be caused by damage to a flexible shaft assembly.
    These conditions, if not corrected, could result in inadvertent in-
flight thrust reverser deployment, which can 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 alert service bulletin (ASB) No. CF6-80E1 SB 
78A5043, Revision 1, dated January 22, 2002 that describes procedures 
for initial and repetitive thrust reverser inspections and checks.

FAA's Determination of an Unsafe Condition and Required Actions

    Although this affected engine model is not used on any airplanes 
that are registered in the United States, the possibility exists this 
engine model could be used on airplanes that are registered in the 
United States in the future. This AD is being issued to prevent 
inadvertent in-flight thrust reverser deployment, which can result in 
loss of control of the airplane. This AD requires initial and 
repetitive thrust reverser inspections and checks, and allows extended 
threshold and repetitive inspection intervals for certain inspections 
if an optional double p-seal configuration is installed. The actions 
are required to be done in accordance with the service bulletin 
described previously.

[[Page 36091]]

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-04-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.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
by contacting 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.


 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-10-08  General Electric Company: Amendment 39-12754. Docket No. 
2000-NE-04-AD.

Applicability

    This airworthiness directive (AD) is applicable to General 
Electric Company (GE) CF6-80E1 series turbofan engines. These 
engines are installed on, but not limited to, 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 in-flight thrust reverser deployment, 
which can result in loss of control of the airplane, do the 
following:

Engines That Do Not Have Improved Double P-Seal Configuration

    (a) For engines that do not have the improved double P-seal 
configuration introduced by Middle River Aircraft Systems (MRAS) 
service bulletin (SB) 78-5037, original issue or Revision 1, inspect 
and check each fan thrust reverser half in accordance with 2.B., 
2.C., and 2.D. of the Accomplishment Instructions of MRAS alert 
service bulletin (ASB) No. 78A5043, Revision 1, dated January 22, 
2002, as follows:
    (1) Perform initial inspections and checks before exceeding 
7,000 flight hours time-since-new (TSN) or 1,000 flight hours time-
in-service (TIS), whichever occurs later, after the effective date 
of this AD.
    (2) Thereafter, perform inspections and checks at intervals not 
to exceed 7,000 flight hours TIS since last inspection or check.

Engines That Do Have Improved Double P-Seal Configuration

    (b) For engines that do have the improved double P-seal 
configuration introduced by MRAS SB 78-5037, original issue or 
Revision 1, inspect and check each fan thrust reverser half in 
accordance with 2.B. and 2.C. of the Accomplishment Instructions of 
MRAS ASB No. 78A5043, Revision 1, dated January 22, 2002, as 
follows:
    (1) Perform initial inspections and checks before exceeding 
25,000 flight hours TSN or 1,000 flight hours TIS, whichever occurs 
later, after the effective date of this AD.
    (2) Thereafter, perform inspections and checks at intervals not 
to exceed 25,000 flight hours TIS since last inspection or check.
    (c) Also for engines that do have the improved double P-seal 
configuration introduced by MRAS SB 78-5037, original issue or 
Revision 1, check each fan thrust reverser half in accordance with 
2D. of the Accomplishment Instructions of MRAS ASB No. 78A5043, 
Revision 1, dated January 22, 2002, as follows:
    (1) Perform initial check before exceeding 7,000 flight hours 
TSN or 1,000 flight hours TIS, whichever occurs later, after the 
effective date of this AD.
    (2) Thereafter, perform checks at intervals not to exceed 7,000 
flight hours TIS since last check.

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 airworthiness directive, 
if any, may be obtained from the ECO.


[[Page 36092]]



Special Flight Permits

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

Documents That Have Been Incorporated By Reference

    (f) The inspections and checks must be done in accordance with 
Middle River Aircraft Systems Alert Service Bulletin No. CF6-80E1 SB 
78A5043, Revision 1, dated January 22, 2002. 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 Capitol 
Street, NW, suite 700, Washington, DC.

Effective Date

    (g) This amendment becomes effective on June 27, 2002.

    Issued in Burlington, Massachusetts, on May 9, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-12631 Filed 5-22-02; 8:45 am]
BILLING CODE 4910-13-U