[Federal Register: October 25, 2007 (Volume 72, Number 206)]
[Proposed Rules]
[Page 60604-60606]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25oc07-27]
[[Page 60604]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0053; Directorate Identifier 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 (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for General Electric Company (GE) CF6-50, -80A1/A3, and
-80C2A series turbofan engines, installed on Airbus A300 and A310
series airplanes. That AD currently requires initial and repetitive
inspections and checks of the thrust reverser actuation systems. This
proposed AD would require revised inspection thresholds and intervals,
and would require the same actions and additional inspections of the
thrust reverser actuation system locking features. This proposed AD
results from refined safety analyses performed on the thrust reverser
systems by GE and Airbus. We are proposing this AD to prevent
inadvertent in-flight thrust reverser deployment, which can result in
loss of control of the airplane.
DATES: We must receive any comments on this proposed AD by December 24,
2007.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
Federal eRulemaking Portal: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility: U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Contact Middle River Aircraft Systems, Mail Point 46, 103
Chesapeake Park Plaza, Baltimore, MD, 21220, attn: Warranty Support,
telephone: (410) 682-0094, fax: (410) 682-0100 for the service
information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
Robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0053;
Directorate Identifier 98-ANE-54-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov
, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this proposed AD.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov
; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
Discussion
The FAA proposes to amend 14 CFR part 39 by superseding AD 99-18-
20, Amendment 39-11286 (64 FR 48286, September 3, 1999). That AD
requires initial and repetitive inspections and checks of the thrust
reverser actuation systems, and allows extended repetitive inspection
intervals if an optional double p-seal configuration is installed. That
AD was the result of a report of a higher than anticipated center drive
unit cone brake failure rate, which reduces the overall thrust reverser
system protection against inadvertent deployment. That condition, if
not corrected, could result in inadvertent in-flight thrust reverser
deployment, which can result in loss of control of the airplane.
Actions Since AD 99-18-20 Was Issued
Since AD 99-18-20 was issued, refined safety analyses performed on
the thrust reverser systems installed on GE CF6-50, -80A1/A3, and -
80C2A series turbofan engines were completed by GE and Airbus.
Relevant Service Information
We have reviewed and approved the technical contents of Middle
River Aircraft Systems (MRAS) Alert Service Bulletin (ASB) No. CF6-50
S/B 78A3001, Revision 4, dated August 30, 2007, ASB No. CF6-80A1/A3 S/B
78A1002, Revision 5, dated July 19, 2007, and ASB No. CF6-80C2A1/A2/A3/
A5/A8/A5F S/B 78A1015, Revision 7, dated August 30, 2007. These ASBs
describe procedures for performing initial and repetitive thrust
reverser system inspections and checks.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. For that reason, we are proposing this AD,
which would require revised inspection thresholds and intervals, and
would require inspections of the thrust reverser actuation system
locking features. The proposed AD would require that you do these
actions using the relevant service information described previously.
Costs of Compliance
We estimate that this proposed AD would affect 206 engines
installed on airplanes of U.S. registry. We also estimate that it would
take about one work-hour per engine to perform the proposed additional
inspection, and that the average labor rate is $80 per work-hour. Based
on these figures, we estimate the total additional cost of the proposed
AD for one inspection of the U.S. fleet, to be $28,000.
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
[[Page 60605]]
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.
Docket Number Change
We are transferring the docket for this proposed AD to the Federal
Docket Management System (FDMS) as part of our on-going docket
management consolidation efforts. The new Docket No. is FAA-2007-0053.
The old Docket No. became the Directorate Identifier, which is 98-ANE-
54-AD.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the proposed AD:
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. Would 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 regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 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. The FAA amends Sec. 39.13 by removing Amendment 39-11286 (64 FR
48286, September 3, 1999) and by adding a new airworthiness directive
to read as follows:
General Electric Company: Docket No. FAA-2007-0053; Directorate
Identifier 98-ANE-54-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by December 24,
2007.
Affected ADs
(b) This AD supersedes AD 99-18-20, Amendment 39-11286.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-50, -
80A1/A3, and -80C2A series turbofan engines. These engines are
installed on Airbus A300 and A310 series airplanes.
Unsafe Condition
(d) This AD results from refined safety analyses performed on
the thrust reverser systems by GE and Airbus. We are issuing this AD
to prevent inadvertent in-flight thrust reverser deployment, which
can result in loss of control of the airplane.
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 Inspection for CF6-50 Series Turbofan Engines
(f) For CF6-50 series turbofan engines, perform initial thrust
reverser inspections using Section 2, Accomplishment Instructions,
of Middle River Aircraft Systems (MRAS) Alert Service Bulletin (ASB)
No. CF6-50 S/B 78A-3001, Revision 4, dated August 30, 2007, as
follows:
(1) On Airbus A300 series airplanes with a Three Light Reverser
Indication Circuit configuration, and without thrust reverser
actuation system (TRAS) locks installed, perform the initial
inspections and checks within 1,500 hours time-in-service (TIS)
after the effective date of this AD.
(2) On Airbus A300 series airplanes with a Three Light Reverser
Indication Circuit configuration, and with TRAS locks installed,
perform the initial inspections and checks within 7,000 hours TIS
after the effective date of this AD.
(3) On Airbus A300 series airplanes with a Two Light Reverser
Indication Circuit configuration, and without TRAS locks installed,
perform the initial inspections and checks within 1,500 hours TIS
after the effective date of this AD.
(4) On Airbus A300 series airplanes with a Two Light Reverser
Indication Circuit configuration, and with TRAS locks installed,
perform the initial inspections and checks within 7,000 hours TIS
after the effective date of this AD.
Repetitive Inspections for CF6-50 Series Turbofan Engines
(g) For CF6-50 series turbofan engines, perform repetitive
thrust reverser inspections using Section 2, Accomplishment
Instructions, of MRAS ASB No. CF6-50 S/B 78A-3001, Revision 4, dated
August 30, 2007, as follows:
(1) On Airbus A300 series airplanes with a Three Light Reverser
Indication Circuit configuration, and without TRAS locks installed,
perform repetitive inspections and checks at the following:
(i) Within every 2,500 hours time-since-last-inspection (TSLI),
perform paragraph 2.D., Translating Cowl Air Seal, Dagmar Fairing
and Aft Frame Inspection; and paragraph 2.I., Fan Reverser
Operational Check.
(ii) Within every 6,000 hours TSLI, perform paragraph 2.C.,
Pneumatic Drive Motor (PDM) Disc Brake Holding Torque Check;
paragraph 2.E., Feedback Rod to Yoke Alignment Check and Inspection
of Feedback Yoke and Feedback Rod; paragraph 2.F., Translating Cowl
Auto Re-Stow Function Check; and paragraph 2.I., Fan Reverser
Operational Check.
(2) Within every 7,000 hours TSLI on Airbus A300 series
airplanes with a Three Light Reverser Indication Circuit
configuration, and with TRAS locks installed, perform repetitive
inspections and checks.
(3) On Airbus A300 series airplanes with a Two Light Reverser
Indication Circuit configuration, and without TRAS locks installed,
perform repetitive inspections and checks at the following:
(i) Within every 2,500 hours TSLI, perform paragraph 2.D.,
Translating Cowl Air Seal, Dagmar Fairing and Aft Frame Inspection;
and paragraph 2.I., Fan Reverser Operational Check.
(ii) Within every 6,000 hours TSLI, perform paragraph 2.C.,
Pneumatic Drive Motor (PDM) Disc Brake Holding Torque Check;
paragraph 2.E., Feedback Rod to Yoke Alignment Check and Inspection
of Feedback Yoke and Feedback Rod; paragraph 2.G., Translating Cowl
Auto Re-Stow Function Check; paragraph 2.H., Over Pressure Shutoff
Valve (OPSOV) Indication Check; and paragraph 2.I., Fan Reverser
Operational Check.
(4) On Airbus A300 series airplanes with a Two Light Reverser
Indication Circuit configuration, and with TRAS locks installed,
perform repetitive inspections and checks within every 7,000 hours
TSLI.
Initial and Repetitive Inspections for CF6-80A1/A3 Series Turbofan
Engines
(h) For CF6-80A1/A3 series turbofan engines installed on Airbus
A310-200 airplanes, perform initial and repetitive thrust reverser
inspections using Section 2, Accomplishment Instructions, of MRAS
ASB No. CF6-80A1/A3 S/B 78A-1002, Revision 5, dated July 19, 2007,
at the following:
(1) For initial inspection, within 1,500 hours TIS after the
effective date of this AD.
(2) For repetitive inspections, within every 7,000 hours TSLI.
Initial Inspection for CF6-80C2A Series Turbofan Engines
(i) For CF6-80C2A series turbofan engines, perform initial
thrust reverser inspections using Section 2, Accomplishment
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Instructions, of MRAS ASB No. CF6-80C2A1/A2/A3/A5/A8/A5F S/B
78A1015, Revision 7, dated August 30, 2007, at the following:
(1) On Airbus A300 and A310 series airplanes with left-hand and
right-hand reverser halves that do not have the double/backup P-seal
introduced by MRAS SB No. CF6-80C2 S/B 78A1005, and that do not have
locking actuator assemblies (LAAs) installed, within 600 hours TIS
after the effective date of this AD.
(2) On Airbus A300 and A310 series airplanes with left-hand and
right-hand reverser halves that have the double/backup P-seal
introduced by MRAS SB No. CF6-80C2 S/B 78A1005, or that have LAAs
installed, within 7,000 hours TIS after the effective date of this
AD.
Directional Pilot Valve (DPV) Pressure Switch Check on Airbus Airplanes
With CF6-80C2A5F Engines Is Not Applicable
(3) The DPV pressure switch check per paragraph 2.F. is not
applicable to Airbus airplanes with CF6-80C2A5F left-hand and right-
hand fan reverser halves (model ES-CF6-5), because this check is
performed through the full authority digital electronic control
fault detection system.
Repetitive Inspections for CF6-80C2A Series Turbofan Engines
(j) For CF6-80C2A series turbofan engines, perform repetitive
thrust reverser inspections using Section 2, Accomplishment
Instructions, of MRAS ASB No. CF6-80C2A1/A2/A3/A5/A8/A5F S/B
78A1015, Revision 7, dated August 30, 2007, at the following:
(1) On Airbus A300 and A310 series airplanes with left-hand and
right-hand reverser halves that do not have the double/backup P-
seal, introduced by MRAS SB No. CF6-80C2 S/B 78A1005, and that do
not have LAAs installed, within every 600 hours TSLI.
(2) On Airbus A300 and A310 series airplanes with left-hand and
right-hand reverser halves that have the double/backup P-seal,
introduced by MRAS SB No. CF6-80C2 S/B 78A1015, or that have LAAs
installed, within every 7,000 hours TSLI.
Engines That Fail an Inspection or Check
(k) On engines that fail an inspection or check required by this
AD, perform corrective actions or deactivate the fan reverser per
Section 2, Accomplishment Instructions, of the applicable MRAS ASB,
before further flight.
Previous Credit
(l) Initial and repetitive inspections and checks of the thrust
reverser actuation systems done before the effective date of this AD
that use the following ASBs, comply with the requirements specified
in this AD:
(1) MRAS ASB No. CF6-50 S/B 78A-3001, Revision 2, dated December
18, 1997; and MRAS ASB No. CF6-50 S/B 78A-3001, Revision 3, dated
May 3, 2006.
(2) MRAS ASB No. CF6-80A1/A3 S/B 78A-1002, Revision 3, dated
January 21, 1999; and MRAS ASB No. CF6-80A1/A3 S/B 78A-1002,
Revision 4, dated May 3, 2006.
(3) MRAS ASB No. CF6-80C2 S/B 78A1015, Revision 5, dated January
21, 1999; and MRAS ASB No. CF6-80C2A1/A2/A3/A5/A8/A5F S/B 78A1015,
Revision 6, dated May 3, 2006.
Alternative Methods of Compliance
(m) The Manager, Engine Certification Office, FAA, has the
authority to approve alternative methods of compliance for this AD
if requested using the procedures found in 14 CFR 39.19.
Related Information
(n) France AD 1999-422- IMP(B), dated October 20, 1999, also
addresses the subject of this AD.
(o) Contact Robert Green, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
Robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199,
for more information about this AD.
Issued in Burlington, Massachusetts, on October 18, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E7-21000 Filed 10-24-07; 8:45 am]
BILLING CODE 4910-13-P