[Federal Register: August 8, 2005 (Volume 70, Number 151)]
[Proposed Rules]
[Page 45595-45598]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08au05-27]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22036; Directorate Identifier 2005-NM-009-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and B4 Series
Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes,
and Model C4-605R Variant F Airplanes (Collectively Called A300-600
Series Airplanes); and Model A310 Series Airplanes; Equipped With
General Electric CF6-80A3 or CF6-80C2 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 adopt a new airworthiness directive (AD)
for certain Airbus airplane models, as specified above. This proposed
AD would require installing electro-pneumatic locking bar devices (TRAS
lock systems) in the engine nacelles, installing a dedicated and
shielded electrical circuit that is segregated from the existing thrust
reverser control system, and performing related investigative/
corrective actions if necessary. This proposed AD is prompted by the
manufacturer's reassessment of the thrust reverser systems in the
Airbus airplane models specified above, which showed that the thrust
reverser could inadvertently deploy in flight under certain conditions.
We are proposing this AD to prevent inadvertent deployment of thrust
reversers in flight, which could result in reduced controllability of
the airplane.
DATES: We must receive comments on this proposed AD by September 7,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web Site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-Wide Rulemaking Web Site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
By Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-22036; the directorate identifier for this docket is
2005-NM-009-AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-22036;
Directorate Identifier 2005-NM-009-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.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. Using the search function of our
docket Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit http://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified us that an
unsafe condition may exist on certain Airbus Model A300 B2 and B4
series airplanes; Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model C4-605R Variant F airplanes (collectively called
A300-600 series airplanes); and Model A310 series airplanes; equipped
with General Electric CF6-80A3 or CF6-80C2 engines. The DGAC advises
that the manufacturer has reassessed the thrust reverser systems of
those airplanes and has determined that the thrust reverser could
inadvertently deploy in flight. The manufacturer has developed a new,
improved design of the thrust reversers, which provides an independent
system to prevent deployment of the thrust reversers in flight.
Inadvertent deployment of the thrust reversers in flight could result
in reduced controllability of the airplane.
Relevant Service Information
Airbus has issued the following service bulletins (SBs), which
describe procedures for installing electro-pneumatic locking bar
devices (TRAS lock system) and a dedicated and shielded electrical
circuit that is segregated from the existing thrust reverser control
system. The new electrical circuit commands the locking bar devices
(TRAS locks), which would be installed in the engine nacelles.
Implementation of the following SBs is intended to provide an
independent system to prevent inadvertent deployment of thrust
reversers during flight.
[[Page 45596]]
Airbus SB A310-78-2023, dated October 7, 2003 (for Model A310
series airplanes equipped with General Electric CF6-80C2 engines and
not equipped with Full Authority Digital Engine Control (FADEC)),
specifies previous or concurrent accomplishment of Airbus SB A310-78-
2022, and describes modifying/retrofitting the electrical harness
routine from each lock to the pylon interfaces of the engine/nacelle,
and the existing monitoring wire; and activating the electrical system
of the aircraft.
Airbus SB A310-78-2022, dated January 7, 2003 (for Airbus Model 310
series airplanes equipped with General Electric CF6-80C2 engines and
not equipped with FADEC), describes modifying/retrofitting a new
electrical circuit between the forward cargo compartment and the wing/
pylon interfaces, a new electrical circuit in the engine pylons, and a
new electrical circuit in the avionics compartment and the forward
cargo compartment; and connecting the new electrical circuit. The SB
indicates that Parts 1 and 2 of the SB can be accomplished
independently and in any sequence, but Part 3 must be accomplished
after the first two parts. Full function can be assured once Airbus SB
A310-78-2023 has been accomplished.
Airbus SB A310-78-2025, dated July 23, 2004 (for Model A310 series
airplanes equipped with General Electric CF6-80A3 engines), specifies
previous or concurrent accomplishment of Airbus SB A310-78-2024, and
references Goodrich Service Bulletin 71-065 as an additional source of
service information. (After the issuance of Airbus SB A310-78-2025,
dated July 23, 2004, the Goodrich Service Bulletin was reissued as Rohr
Service Bulletin CF6-80A3, dated April 28, 2005.) Airbus SB A310-78-
2025 also describes the following procedures:
Modifying/retrofitting the existing monitoring wire and
activating the electrical system of the aircraft.
Modifying/retrofitting the electrical harness routine from
each lock to the pylon interfaces of the engine/nacelle.
Installing the support bracket for the electrical harness
of the engine/nacelle.
Modifying the stowed position of the hold-open rod bracket
of the engine/nacelle.
Replacing the lower end actuator gearbox with a gearbox
that integrates the locking bar.
Replacing the pneumatic tubing situated upstream from the
pressure regulated shut-off valve (PRSOV) with a new PRSOV having a
third line of defense (TLOD) tubing connector.
Modifying the hold-open rod bracket of the fan cowl.
Accomplishing the test job set-up, extended operational
test of the circuit breaker monitoring system, and the test for the
stow and deploy switches included in the thrust reverser functional and
indicating/warning sensors test.
Airbus Service Bulletin A310-78-2024, dated October 15, 2003 (for
Model A310 series airplanes equipped with CF6-80A3 engines), describes
procedures for the airplane and the engine/nacelle that include the
following:
Modifying the hold-open rod bracket of the fan cowl.
Installing the actuation system lock.
Modifying the wiring in a certain circuit breaker panel.
Airbus Service Bulletin A300-78-6024, dated October 7, 2003 (for
Model A300-600 series airplanes equipped with General Electric CF6-80C2
engines and equipped with FADEC), specifies previous or concurrent
accomplishment of Airbus SB A300-78-6021, Revision 1, dated October 7,
2003, and describes procedures for the following:
Installing an actuation system lock.
Modifying the wiring in a certain circuit breaker panel.
Accomplishing the test job set-up, extended operational
test of the circuit breaker monitoring system, and the test for the
stow and deploy switches included in the thrust reverser functional and
indicating/warning sensors test.
Airbus SB A300-78-6021, Revision 1, dated October 7, 2003 (for
Model A300-600 series airplanes equipped with General Electric CF6-80C2
engines and equipped with FADEC), describes procedures for the
following:
Part 1--Modifying/retrofitting a new electrical circuit
between the forward cargo compartment and the wing/pylon interfaces.
Part 2--Modifying/retrofitting a new electrical circuit in
the engine pylons.
Part 3--Modifying/retrofitting a new electrical circuit in
the avionics compartment; modifying/retrofitting a new electrical
circuit between the avionics compartment and the forward cargo
compartment; and modifying/retrofitting a new electrical circuit.
Airbus SB A300-78-6025, dated October 7, 2003 (for Model A300-600
series airplanes equipped with General Electric CF6-80C2 engines not
equipped with FADEC), specifies previous or concurrent accomplishment
of Airbus SB A300-78-6022, and describes procedures for the following:
Installing an actuation system lock.
Modifying the wiring in a certain circuit breaker panel.
Accomplishing the test job set-up, extended operational
test of the circuit breaker monitoring system, and the test for the
stow and deploy switches included in the thrust reverser functional and
indicating/warning sensors test.
Airbus SB A300-78-6022, Revision 1, dated January 7, 2003 (for
Model A300-600 airplanes equipped with General Electric CF6 80C2
engines and not equipped with FADEC), describes procedures for the
following:
Part 1--Modifying/retrofitting a new electrical circuit
between the forward cargo-compartment and the wing/pylon interfaces.
Part 2--Modifying/retrofitting a new electrical circuit in
the engine pylons.
Part 3--Modifying/retrofitting a new electrical circuit in
the avionics compartment; modifying/retrofitting a new electrical
circuit between the avionics compartment and the forward cargo
compartment; and modifying/retrofitting a new electrical circuit.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The DGAC mandated
the above service bulletins and issued French airworthiness directive
F-2004-165, dated October 13, 2004, to ensure the continued
airworthiness of these airplanes in France.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States. Therefore, we are proposing this AD,
which would require accomplishing the actions specified in the service
information described previously.
Costs of Compliance
This AD affects about 101 airplanes of U.S. registry. (The total
number of airplanes in the following table totals more than 101
airplanes because most of the airplanes would be required to accomplish
two of the specified service
[[Page 45597]]
bulletins.) The following table provides the estimated costs for U.S.
operators to comply with this proposed AD at an average labor rate per
hour of $65.
Estimated Costs for Modifications (Listed by Applicable Service Bulletin)
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Cost per Number of
Airbus service bulletin (SB) Work hours Parts airplane airplanes Cost per SB
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A300-78-6021, Revision 1....................... 257 $15,185 $31,890 36 $1,148,040
A300-78-6022, Revision 1....................... 289 18,198 36,983 34 1,257,422
A300-78-6024................................... 4 150 410 36 14,760
A300-78-6025................................... 4 150 410 34 13,940
A310-78-2024................................... 4 18,009 35,884 27 968,868
A310-78-2025................................... 4 150 410 31 12,710
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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
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.
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
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. 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 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
Accordingly, under the authority delegated to me by the
Administrator, the FAA 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 adding the following new
airworthiness directive (AD):
Airbus: Docket No. FAA-2005-22036; Directorate Identifier 2005-NM-
009-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by September 7, 2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to Airbus series airplanes,
certificated in any category, as identified in the service bulletins
listed in Table 1 of this AD.
Table 1.--Applicability
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General
Series airplane Electric Airbus service bulletin Date
engine model
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A300 B2 and B4; A300 B4-600, B4-600R, CF6-80C2 A300-78-6024.............. October 7, 2003.
and F4-600R, C4-605R Variant F
airplanes (collectively called A300-600
series airplanes).
A300 B2 and B4; A300 B4-600, B4-600R, CF6-80C2 A300-78-6021, Revision 1.. October 7, 2003.
and F4-600R, C4-605R Variant F
airplanes (collectively called A300-
600).
A300 B2 and B4; A300 B4-600, B4-600R, CF6-80C2 A300-78-6025.............. October 7, 2003.
and F4-600R, C4-605R Variant F
airplanes (collectively called A300-
600).
A300 B2 and B4; A300 B4-600, B4-600R, CF6-80C2 A300-78-6022, Revision 1. January 7, 2003.
and F4-600R, C4-605R Variant F
airplanes (collectively called A300-
600).
A310.................................... CF6-80C2 A310-78-2023.............. October 7, 2003.
A310.................................... CF6-80C2 A310-78-2022.............. January 7, 2003.
A310.................................... CF6-80A3 A310-78-2025.............. July 23, 2004.
[[Page 45598]]
A310.................................... CF6-80A3 A310-78-2024.............. October 15, 2003.
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Unsafe Condition
(d) This AD was prompted by the manufacturer's reassessment of
the thrust reverser systems in the Airbus airplane models specified
in Table 1 of this AD, which showed that the thrust reverser could
deploy in flight under certain conditions. We are issuing this AD to
prevent inadvertent deployment of thrust reversers in flight, which
could result in reduced controllability 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.
Installing TRAS Locks System and Accomplishing Modifications
(f) For airplanes identified in the service bulletins specified
in Table 2 of this AD: Within 36 months after the effective date of
this AD, install the electro-pneumatic locking bar devices (TRAS
Lock Systems) in the thrust reverser system of the nacelles, in
accordance with the Accomplishment Instructions of the applicable
service bulletin.
Table 2.--Installing TRAS Lock Systems
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General
Series airplane Electric Airbus service bulletin Date
engine model
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A300 B2 and B4; A300 B4-600, B4-600R, CF6-80C2 A300-78-6024.............. October 7, 2003.
and F4-600R, C4-605R Variant F
airplanes (collectively called A300-600
series airplanes).
A300 B2 and B4; A300 B4-600, B4-600R, CF6-80C2 A300-78-6025.............. October 7, 2003.
and F4-600R, C4-605R Variant F
airplanes (collectively called A300-
600).
A310.................................... CF6-80C2 A310-78-2023.............. October 7, 2003.
A310.................................... CF6-80A3 A310-78-2025.............. July 23, 2004.
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Note 1: Airbus SB A310-78-2025, dated July 23, 2004, references
draft Goodrich Service Bulletin 71-065 as an additional source of
service information. After the issuance of Airbus A310-78-2025, the
Goodrich SB was reissued as Rohr Service Bulletin CF6-80A3, dated
April 28, 2005.
(g) For airplanes identified in the service bulletins specified
in Table 3 of this AD: Prior to or concurrent with the
accomplishment of the applicable service bulletin specified in
paragraph (f) of this AD, accomplish all the modifications and
actions related to an independent third line of defense on the
thrust reversers, in accordance with the Accomplishment Instructions
of the applicable service bulletin specified in Table 3 of this AD.
Table 3.--Prior or Concurrent Accomplishment
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General
Series airplane Electric Airbus service bulletin Date
engine model
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A300 B2 and B4; A300 B4-600, B4-600R, CF6-80C2 A300-78-6021, Revision 1.. October 7, 2003.
and F4-600R, C4-605R Variant F
airplanes (collectively called A300-
600).
A300 B2 and B4; A300 B4-600, B4-600R, CF6-80C2 A300-78-6022, Revision 1.. January 7, 2003.
and F4-600R, C4-605R Variant F
airplanes (collectively called A300-
600).
A310.................................... CF6-80C2 A310-78-2022.............. January 7, 2003.
A310.................................... CF6-80A3 A310-78-2024.............. October 15, 2003.
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Alternative Methods of Compliance (AMOCs)
(h) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
Related Information
(i) French airworthiness directive F-2004-165, dated October 13,
2004, also addresses the subject of this AD.
Issued in Renton, Washington, on August 2, 2005.
Kevin Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-15594 Filed 8-5-05; 8:45 am]
BILLING CODE 4910-13-P