[Federal Register Volume 64, Number 35 (Tuesday, February 23, 1999)]
[Proposed Rules]
[Pages 8762-8763]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-4367]
[[Page 8762]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-54-AD]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF6-50, -80A1/
A3, and -80C2A Series Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to General Electric Company (GE) CF6-
50, -80A1/A3, and -80C2A series turbofan engines installed on Airbus
A300 and A310 series aircraft. This proposal would require initial and
repetitive thrust reverser inspections and checks, and allow extended
repetitive inspection intervals if an optional double p-seal
configuration is installed. This proposal is prompted by the report of
a higher than anticipated center drive unit (CDU) cone brake failure
rate which reduces the overall thrust reverser system protection
against inadvertent deployment. The actions specified by the proposed
AD are intended to prevent inadvertent inflight thrust reverser
deployment, which can result in loss of control of the aircraft.
DATES: Comments must be received by March 25, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 98-ANE-54-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``9-ad-
[email protected]''. Comments sent via the Internet must contain the
docket number in the subject line. Comments may be inspected at this
location between 8:00 a.m. and 4:30 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Middle River Aircraft Systems, Mail Point 446, 103
Chesapeake Park Plaza, Baltimore, MD, 21220-4295, attn: Warranty
Support, telephone: (410) 682-0098, fax: (410) 682-0100. This
information may be examined at the FAA, New England Region, Office of
the Regional Counsel, 12 New England Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT: William S. Ricci, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7742, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 98-ANE-54-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, New England Region, Office of the Regional Counsel,
Attention: Rules Docket No. 98-ANE-54-AD, 12 New England Executive
Park, Burlington, MA 01803-5299.
Discussion
This proposed airworthiness directive (AD) is prompted by the
report of a higher than anticipated center drive unit (CDU) cone brake
failure rate that reduces the overall thrust reverser system protection
against inadvertent deployment. The Federal Aviation Administration
(FAA) has determined that thrust reverser inspections and checks are
necessary for all General Electric Company (GE) CF6 series turbofan
engine installations on Airbus aircraft. This condition, if not
corrected, could result in inadvertent inflight thrust reverser
deployment, which can result in loss of control of the aircraft.
The FAA has reviewed and approved the technical contents of Middle
River Aircraft Systems CF6-50 Service Bulletin (SB) No. 78-3001,
Revision 2, dated December 18, 1997, CF6-80A1/A3 SB No. 78-1002,
Revision 3, dated January 21, 1999, and CF6-80C2 Alert Service Bulletin
(ASB) No. 78A1015, Revision 5, dated January 21, 1999, that describe
procedures for thrust reverser inspections and checks.
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require initial and repetitive thrust reverser
inspections and checks, and allows extended repetitive inspection
intervals if an optional double p-seal configuration is installed. This
AD would require these actions to be accomplished in accordance with
the service documents described previously. There are approximately 849
engines of the affected design in the worldwide fleet. The FAA
estimates that 193 engines installed on aircraft of U.S. registry would
be affected by this proposed AD, that it would take approximately 5
work hours per engine to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Based on these figures, the
total cost impact of the proposed AD on U.S. operators is estimated to
be $57,900.
The regulations proposed herein would not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
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) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the
[[Page 8763]]
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
General Electric Company: Docket No. 98-ANE-54-AD.
Applicability: General Electric Company (GE) CF6-50, -80A1/A3,
and -80C2A series turbofan engines, installed on Airbus A300 and
A310 series aircraft.
Note 1: This airworthiness directive (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 (b) 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: Required as indicated, unless accomplished
previously.
To prevent inadvertent inflight thrust reverser deployment,
which can result in loss of control of the aircraft, accomplish the
following:
(a) Perform initial and repetitive thrust reverser inspections
and checks as follows:
(1) For GE CF6-50 series engines, perform inspections and checks
in accordance with paragraph 2., Accomplishment Instructions, of
Middle River Aircraft Systems CF6-50 SB No. 78-3001, Revision 2,
dated December 18, 1997, as follows:
(i) Perform the initial inspections and checks within 1,500
hours time in service (TIS) after the effective date of this AD.
(ii) Thereafter, perform inspections and checks at intervals not
to exceed 6,000 hours TIS since last check.
(2) For CF6-80A1/A3 series engines, perform inspections and
checks in accordance with paragraph 2., Accomplishment Instructions,
of Middle River Aircraft Systems CF6-80A1/A3 SB No. 78-1002,
Revision 3, dated January 21, 1999, as follows:
(i) Perform the initial inspections and checks within 1,500
hours TIS after the effective date of this AD.
(ii) Thereafter, perform inspections and checks at intervals not
to exceed 7,000 hours TIS since last check.
(3) For CF6-80C2 series engines, perform inspections and checks
in accordance with paragraph 2., Accomplishment Instructions, of
Middle River Aircraft Systems CF6-80C2 Alert Service Bulletin (ASB)
No. 78A1015, Revision 5, dated January 21, 1999, as follows:
(i) Perform the initial inspections and checks within 600 hours
TIS after the effective date of this AD.
(ii) Thereafter, perform repetitive inspections and checks as
follows:
(A) For engines with a double p-seal configuration, having
translating cowl part numbers 491B1613000-109 or D52B1000-9, perform
repetitive inspections and checks at intervals not to exceed 7,000
hours TIS since last inspection.
(B) For all other engines, perform repetitive inspections and
checks at intervals not to exceed 600 hours TIS since last
inspection.
(4) Perform corrective actions or deactivate the fan reverser in
accordance with paragraph 2., Accomplishment Instructions, of the
applicable SB or ASB prior to further flight.
(b) 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.
Operators shall submit their request through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Engine Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(c) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the aircraft to a location where
the requirements of this AD can be accomplished.
Issued in Burlington, Massachusetts, on February 16, 1999.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 99-4367 Filed 2-22-99; 8:45 am]
BILLING CODE 4910-13-U