Airworthiness Directives; Airbus 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 Airplanes; Equipped With General Electric CF6-80A3 or CF6-80C2 Engines, 12550-12555 [E7-4734]
Download as PDF
<![CDATA[
12550
Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations
discovery of propeller control cables with a
defective crimping. Two cable ends were
found uncrimped at the factory after an
engine run-up test, and one cable end was
also found uncrimped on the first 100-hour
time-in-service aircraft maintenance check. If
not corrected, an incorrect crimping of the
propeller control lever cable could generate
a decrease of the propeller revolutions per
minute which could result in loss of power.
Actions and Compliance
(e) Unless already done, within the next 50
hours time-in-service (TIS) after April 20,
2007 (the effective of this AD), inspect for the
batch number identification and replace
defective control cables as necessary in
accordance with the paragraph B. of the
‘‘ACCOMPLISHMENT INSTRUCTIONS’’ of
EADS SOCATA TBM Aircraft Mandatory
Alert Service Bulletin SB 70–123, dated
October 2004.
FAA AD Differences
Note: This AD differs from the MCAI, the
´ ´
French Direction generale de l’ aviation civile
(DGAC) AD No. F–2004–175, dated
November 10, 2004, as follows:
(1) The requirement of paragraph 3.1 of
DGAC AD No. F–2004–175, dated November
10, 2004, was based on the urgency in
November 2004. However, in 2007, this
action is not necessary.
(2) For the requirement of paragraph 3.2 of
DGAC AD No. F–2004–175, dated November
10, 2004, the FAA has determined the
seriousness of the condition does not warrant
a compliance time of 25 hours TIS; we
require instead a compliance time of 50
hours TIS.
sroberts on PROD1PC70 with RULES
Other FAA AD Provisions
(f) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Staff,
FAA, ATTN: Albert J. Mercado, Aerospace
Safety Engineer, FAA, Small Airplane
Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329–
4119; fax: (816) 329–4090, has the authority
to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Before using any approved AMOC on any
airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in
the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
VerDate Aug<31>2005
15:23 Mar 15, 2007
Jkt 211001
Related Information
´ ´
(g) Refer to Direction Generale de l’
Aviation Civile Airworthiness Directive No.
F–2004–175, dated November 10, 2004 (the
MCAI); and EADS SOCATA TBM Aircraft
Mandatory Alert Service Bulletin SB 70–123,
dated October 2004, for related information.
Material Incorporated by Reference
(h) You must use EADS SOCATA TBM
Aircraft Mandatory Alert Service Bulletin SB
70–123, dated October 2004, to do the actions
required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact EADS SOCATA, Direction
des Services, 65921 Tarbes Cedex 9, France;
telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5
62.41.76.54; or SOCATA AIRCRAFT, INC.,
North Perry Airport, 7501 Airport Road,
Pembroke Pines, Florida 33023; telephone:
(954) 893–1400; fax (954) 964–4141.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; or at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on March
9, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–4736 Filed 3–15–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22036; Directorate
Identifier 2005–NM–009–AD; Amendment
39–14994; AD 2007–06–13]
RIN 2120–AA64
Airworthiness Directives; Airbus 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 Airplanes; Equipped With
General Electric CF6–80A3 or CF6–
80C2 Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus airplane models, as specified
above. This AD requires installing
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
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 AD results from 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 issuing this
AD to prevent inadvertent deployment
of thrust reversers in flight, which could
result in reduced controllability of the
airplane.
DATES: This AD becomes effective April
20, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of April 20, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://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 street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to 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
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Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations
sroberts on PROD1PC70 with RULES
Electric (GE) CF6–80A3 or CF6–80C2
engines. That NPRM was published in
the Federal Register on August 8, 2005
(70 FR 45595). That NPRM proposed to
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.
Since the Issuance of the NPRM
We have received copies of the
following Airbus service bulletins:
• Airbus Service Bulletin A300–78–
6024, Revision 01, dated April 22, 2005.
Revision 01 describes essentially the
same procedures specified in the
original issue of the service bulletin,
dated October 7, 2003 (referenced in the
NPRM as one appropriate source of
service information). Revision 01 also
adds technical notes referring to certain
Middle River Aircraft Systems (MRAS)
proprietary data 491B1200200,
491B1200201, 491B1200202, and
491B1200203, Revision B, dated
September 9, 2003, which provide
instructions to install the electropneumatic locking bar devices in the
nacelles on GE Model CF6–80C2
engines with a full authority digital
engine control (FADEC) thrust reverser
system, as additional sources of service
information.
• Airbus Service Bulletin A300–78–
6025, Revision 01, dated April 22, 2005.
Revision 01 describes essentially the
same procedures specified in the
original issue of the service bulletin,
dated October 7, 2003 (referenced in the
NPRM as one appropriate source of
service information). Revision 01 also
adds technical notes referring to certain
MRAS proprietary data 491B1200202
and 491B1200203, both Revision B, both
dated September 9, 2003, as additional
sources of service information. The
proprietary data provide instructions to
install the electro-pneumatic locking bar
devices in the nacelles on GE Model
CF6–80C2 engines with a power
management control (PMC) thrust
reverser system.
• Airbus Service Bulletin A310–78–
2023, Revision 01; and Airbus Service
Bulletin A310–78–2025, Revision 01;
both dated April 22, 2005. These service
bulletins were issued to advise
operators of the issuance of technical
notes referenced in MRAS proprietary
data 603A1000, 603A1001, 603A2000,
603A2001, and 603A2100. The
proprietary data provides instructions to
install the electro-pneumatic locking bar
devices, as additional sources of service
information. (Airbus Service Bulletin
VerDate Aug<31>2005
15:23 Mar 15, 2007
Jkt 211001
A310–78–2023, dated October 7, 2003;
and Airbus Service Bulletin A310–78–
2025, dated July 23, 2004; were
referenced as appropriate sources of
service information in the NPRM.)
• Airbus Service Bulletin A310–78–
2022, Revision 02, including
Appendices 01 and 02, dated July 18,
2006. (The original version of this
service bulletin, dated January 7, 2003,
was referenced as an appropriate source
of service information in the NPRM.)
Revision 02 updates certain figures
referenced in the original version of the
service bulletin.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Withdraw the NPRM
One commenter, American Airlines,
states that it appears inconsistent to
invest a significant amount of money for
additional protection by installing
electro-pneumatic locking bar devices
(TRAS lock system). The commenter
points out that the FAA has previously
extended the inspection interval of
current mandated inspections in
another existing AD that also addresses
inadvertent thrust reverser deployment.
We infer that American Airlines is
questioning the cost benefit of the
additional protection that the AD
provides, and would like us to
withdraw the NPRM. We acknowledge
that, although we have extended the
inspection intervals due to positive
results of past inspections, the
possibility still exists that a directional
pilot valve (DPV) leak may occur. This
type of leak is a hidden failure that
cannot be detected at the system level,
and could result in inadvertent thrust
reverser deployment. We have
determined that installation of electropneumatic locking bar devices will
ensure an adequate measure of
protection for the system. No change is
necessary to the AD in this regard.
Requests To Revise the Applicability
Two commenters, Tradewinds
Airlines and GE Transportation, request
that the applicability stated in the
NPRM be revised by removing Airbus
Model A300 B2 and B4 series airplanes.
One commenter points out that those
models are not specified in the French
airworthiness directive, and that there
are no service bulletins specified in the
NPRM that are applicable to those
models.
We agree with the commenters. We
acknowledge that the Model A300 B2
and B4 series airplanes are not equipped
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
12551
with the affected engines and were
inadvertently included in the NPRM.
The applicability of this AD is revised
to remove those airplane models.
Another commenter, Airbus, requests
that the associated modification
numbers for the corresponding service
bulletins be added to the applicability of
the NPRM. Airbus suggests that adding
the associated modification numbers
will make it easier for operators to
comply with the AD and will help
operators to avoid having to request
alternative methods of compliance.
We partially agree with the
commenter’s request in this case. The
applicability of French airworthiness
directive F–2004–165 excludes
airplanes on which Airbus Service
Bulletins A310–78–2024; A310–78–
2025; A310–78–2022; A310–78–2023,
A300–78–6022, Revision 1; A300–78–
6025; A300–78–6021 original issue or
Revision 01; and A300–78–6024; have
been accomplished in-service, as well as
certain modifications accomplished
during production. We agree that
revising the applicability of the final
rule is necessary to exclude airplanes on
which certain modifications have been
accomplished during production.
However, as is our standard practice, we
have not excluded those airplanes that
have accomplished certain
modifications in service in the
applicability of this final rule. Rather,
this final rule includes requirements to
accomplish the actions specified in the
service bulletins that clearly identify the
airplanes that the service bulletins
affect. The requirements of the specified
service bulletins will ensure that the
actions required by this final rule are
accomplished on all affected airplanes.
Operators must continue to operate the
airplane in the configuration required
by this final rule unless an alternative
method of compliance is approved. We
have, however, added a new Note 1 and
Table 2 to this final rule that provide a
list of corresponding modifications with
the applicable service bulletins for ease
of reference for the operators. We have
re-identified subsequent notes and
tables accordingly.
Requests To Revise the ‘‘Costs of
Compliance’’ Section
Several commenters, including theAir
Transport Association (ATA), on behalf
of one of its members, American
Airlines, and FedEx and GE
Transportation, request that the
estimated costs of complying with the
NPRM be revised to add additional
work hours. American Airlines states
that the NPRM would require
concurrent accomplishment of four
service bulletins that are not specified
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Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations
in the NPRM. American Airlines
estimates it will take 600 work hours
and $283,042 for parts per each of its
airplanes, rather than the costs
estimated in the applicable service
bulletins in the NPRM for various
airplane models. FedEx explains that
the cost estimates in the NPRM are not
realistic because additional
modification requirements are necessary
that are described in MRAS and
Goodrich/Rohr technical documents.
One commenter, GE Transportation,
also points out that certain cost
information is available in certain
service information that is not referred
to in the NPRM.
We acknowledge that certain
estimated costs were not included in the
NPRM. We have obtained the additional
service information from MRAS, but it
does not contain estimated cost
information. We also have requested
further information from one of the
commenters, GE Transportation, which
has provided some new cost
information figures to us. We have
revised the estimated costs of the AD by
including the estimated costs of
accomplishing the MRAS service
bulletins. We have coordinated those
estimated costs with Airbus.
Request To Clarify ‘‘Relevant Service
Information’’ Section
GE Transportation suggests certain
revised wording regarding the work
tasks described in the service bulletins
specified in the ‘‘Relevant Service
Information’’ section of the NPRM.
We consider that the descriptions of
the work tasks in the NPRM adequately
describe those tasks. Since that section
of the preamble in the NPRM does not
reappear in the final rule, no change to
the AD is necessary.
Request To Consider the Possibility of
No Deployment
American Airlines requests that we
consider the possibility that an increase
in risk of no deployment on landing
may occur with the modification
installed. American Airlines states that
the modification could affect reliable
operations in those airports restricted by
short runway lengths when employing
the Minimum Equipment List
provisions.
We acknowledge the commenter’s
concern. In its reassessment of thrust
reverser reliability, the manufacturer
considered the possibility of thrust
reverser non-deployment on landing
with the third line of defense (TLOD)
system installed. The reassessment
showed that the thrust reverser without
the TLOD could inadvertently deploy in
flight under certain conditions, which
could lead to decreased aircraft
controllability. We have determined that
the basic two-line-of-defense
architecture does not adequately
address the system’s vulnerability to
damage and long-term maintainability.
Therefore, the modification is necessary
to prevent the identified unsafe
condition. In addition, we have not seen
an increase in occurrences of thrust
reverser nondeployments on landing for
aircraft that have a TLOD or other thrust
reverser third lock-type system
installed. No change to the AD is
necessary regarding this issue.
Request To Use Latest Service Bulletin
Revisions
Several commenters, including the
ATA, on behalf of one of its members,
American Airlines, and FedEx, note that
new revisions of certain service
bulletins have been issued since the
issuance of the NPRM. The commenters
are requesting that we mandate the new
revisions, which contain test procedures
that will take less time for the operators
to accomplish.
We agree with the commenters. We
have received certain newer revisions of
the service bulletins (described
previously) from the manufacturer and
have specified those revisions in Table
3 of the AD. Additionally, we received
new revisions of the service bulletins
specified in Table 2 of the AD from the
manufacturer. We have revised Table 2
of the AD accordingly.
Explanation of Change to Applicability
We have revised the applicability of
the AD to identify model designations
as published in the most recent type
certificate data sheet for the affected
models.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither significantly
increase the economic burden on any
operator nor increase the scope of the
AD.
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 are required to accomplish
two of the specified service bulletins.)
The following table provides the
estimated costs for U.S. operators to
comply with this AD at an average labor
rate per hour of $80.
ESTIMATED COSTS FOR MODIFICATIONS (LISTED BY APPLICABLE SERVICE BULLETIN)
Work
hours
Airbus service bulletins (SB)
sroberts on PROD1PC70 with RULES
A300–78–6021,
A300–78–6024,
A300–78–6022,
A300–78–6025,
A310–78–2024,
A310–78–2025,
Revision
Revision
Revision
Revision
Revision
Revision
02
01
02
01
01
01
...............................................................................
...............................................................................
...............................................................................
...............................................................................
...............................................................................
...............................................................................
None of the airplanes required to
accomplish the following service
bulletins are currently on the U.S.
Register. The airplanes affected by the
following service bulletins are currently
VerDate Aug<31>2005
15:23 Mar 15, 2007
Jkt 211001
257
206
289
206
262
206
$19,652
223,649
19,220
223,649
19,119
194,487
operated by non-U.S. operators under
foreign registry; therefore, they are not
directly affected by this AD action.
However, we consider it necessary to
include these airplanes to ensure that
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Fmt 4700
Sfmt 4700
Cost per
airplane
Parts
$40,212
240,129
42,340
240,129
40,079
210,967
Number of
airplanes
36
36
34
34
31
31
Cost per SB
$1,447,632
8,644,644
1,439,560
8,164,386
1,242,449
6,539,977
the unsafe condition is addressed if any
affected airplane is imported and placed
on the U.S. Register in the future. The
estimated costs apply to any affected
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Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations
airplane should it be imported and
placed on the U.S. Register in the future.
ESTIMATED COSTS FOR MODIFICATIONS FOR CERTAIN OTHER AIRPLANES
Work
hours
Airbus service bulletin (SB)
A310–78–2022 .........................................................................................................................................................
A310–78–2023 .........................................................................................................................................................
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 AD will
not have federalism implications under
Executive Order 13132. This AD will
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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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 AD and placed it in the AD docket.
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, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
275
206
Parts
Cost per
airplane
19,652
$223,649
41,652
$240,129
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2007–06–13 Airbus: Amendment 39–14994.
Docket No. FAA–2005–22036; Directorate
Identifier 2005–NM–009–AD.
Effective Date
(a) This AD becomes effective April
20, 2007.
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; except for
those airplanes on which the following
applicable modifications have been
incorporated in production: Airbus
Modification 12348, 12349, 12350,
12514, and 12511.
TABLE 1.—APPLICABILITY
General Electric engine model
Airbus service bulletin and
revision
A300 B4–605R and F4–605R airplanes .................................
A300 B4–605R and F4–605R airplanes .................................
A300 B4–601, B4–603, B4–605R, and C4–605R Variant F
airplanes.
A300 B4–601, B4–603, B4–605R, and C4–605R Variant F
airplanes.
A310 airplanes .........................................................................
A310 airplanes .........................................................................
A310 airplanes .........................................................................
A310 airplanes .........................................................................
sroberts on PROD1PC70 with RULES
Airplane models
CF6–80C2 ..............................
CF6–80C2 ..............................
CF6–80C2 ..............................
A300–78–6024, Revision 01
A300–78–6021, Revision 02
A300–78–6025, Revision 01
April 22, 2005.
June 8, 2005.
April 22, 2005.
CF6–80C2 ..............................
A300–78–6022, Revision 02
June 8, 2005.
CF6–80C2
CF6–80C2
CF6–80A3
CF6–80A3
A310–78–2023,
A310–78–2022,
A310–78–2024,
A310–78–2025,
April 22, 2005.
July 18, 2006.
June 13, 2005.
April 22, 2005.
Note 1: We have provided a list of
corresponding modifications with the
applicable Airbus service bulletins in Table
2 of this AD for ease of reference for the
operators.
TABLE 2.—CORRESPONDING
MODIFICATIONS
Airbus service bulletin
A310–78–2022 and
A300–78–6022.
VerDate Aug<31>2005
15:23 Mar 15, 2007
Jkt 211001
..............................
..............................
..............................
..............................
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Fmt 4700
Modifications
12348, 12350, 12351,
and 12514.
Sfmt 4700
Revision
Revision
Revision
Revision
01
02
01
01
Date
TABLE 2.—CORRESPONDING
MODIFICATIONS—Continued
Airbus service bulletin
A310–78–2023 and
A300–78–6025.
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TABLE 2.—CORRESPONDING
MODIFICATIONS—Continued
Airbus service bulletin
Modifications
A310–78–2024 ..........
A310–78–2025 ..........
A300–78–6021 ..........
12552 and 12553.
12564.
12348, 12349, 12350,
and 12514.
12511.
A300–78–6024 ..........
Unsafe Condition
(d) This AD results from 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 Lock Systems and
Accomplishing Modifications
(f) For airplanes identified in the
service bulletins specified in Table 3 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 3.—INSTALLING TRAS LOCK SYSTEMS
Airplane models
General electric engine model
Airbus service bulletin and
revision
A300 B4–605R and F4–605R airplanes .................................
A300 B4–601, B4–603, B4–605R, and C4–605R Variant F
airplanes.
A310 airplanes .........................................................................
A310 airplanes .........................................................................
CF6–80C2 ..............................
CF6–80C2 ..............................
A300–78–6024, Revision 01
A300–78–6025, Revision 01
April 22, 2005.
April 22, 2005.
CF6–80C2 ..............................
CF6–80A3 ..............................
A310–78–2023, Revision 01
A310–78–2025, Revision 01
April 22, 2005.
April 22, 2005.
Note 2: Airbus Service Bulletin A310–78–
2025, Revision 01, dated April 22, 2005,
references draft Goodrich Service Bulletin
71–065 as an additional source of service
information. After the issuance of Airbus
Service Bulletin A310–78–2025, the
Goodrich service bulletin was reissued as
Rohr Service Bulletin CF6–80A3–NAC–71–
065, dated April 28, 2005.
(g) For airplanes identified in the
service bulletins specified in Table 4 of
this AD: Prior to or concurrent with the
accomplishment of the applicable
service bulletin specified in paragraph
Date
(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 4 of this AD.
TABLE 4.—PRIOR OR CONCURRENT ACCOMPLISHMENT
Airplane models
Airplanes equipped with General Electric engine model
Airbus service bulletin and
revision
A300 B4–605R and F4–605R airplanes .................................
CF6–80C2 (with full authority
digital engine control
(FADEC)).
CF6–80C2 (without FADEC)
A300–78–6021, Revision 02,
including Appendices 01
and 02.
A300–78–6022, Revision 02,
including Appendices 01
and 02.
A310–78–2022 Revision 02,
including Appendices 01
and 02.
A310–78–2024 Revision 01,
including Appendices 01
and 02.
A300 B4–601, B4–603, B4–605R, and C4–605R Variant F
airplanes.
A310 airplanes .........................................................................
CF6–80C2 (without FADEC)
A310 airplanes .........................................................................
CF6–80A3 ..............................
Actions Accomplished According to
Previous Issues of Service Bulletins
(h) Actions accomplished in
accordance with the following service
Date
June 8, 2005.
June 8, 2005.
June 18, 2006.
June 13, 2005.
bulletins are acceptable for compliance
with the requirements of this AD, as
applicable, if done before the effective
date of this AD:
TABLE 5.—SERVICE BULLETINS ACCOMPLISHED PREVIOUSLY
sroberts on PROD1PC70 with RULES
Airbus service bulletin
A300–78–6021
A300–78–6021
A300–78–6022
A300–78–6024
A300–78–6025
A310–78–2022
A310–78–2022
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April 8, 2003.
October 7, 2003.
January 7, 2003.
October 7, 2003.
October 7, 2003.
January 7, 2003.
June 8, 2005.
Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations
12555
TABLE 5.—SERVICE BULLETINS ACCOMPLISHED PREVIOUSLY—Continued
Airbus service bulletin
Revision level
Date
A310–78–2023 ........................................................................
A310–78–2024 ........................................................................
A310–78–2025 ........................................................................
Original ...................................................................................
Original ...................................................................................
Original ...................................................................................
October 7, 2003.
October 15, 2003.
July 23, 2004.
Alternative Methods of Compliance
(AMOCs)
(i)(1) 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.
(2) Before using any AMOC approved
in accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies,
notify the appropriate principal
inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(j) French airworthiness directive F–
2004–165, dated October 13, 2004, also
addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use the applicable
Airbus service bulletins specified in
Table 6 of this AD to perform the
actions that are required by this AD,
unless the AD specifies otherwise. The
Director of the Federal Register
approved the incorporation by reference
of these documents in accordance with
5 U.S.C. 552(a) and 1 CFR part 51.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for a copy of this service information.
You may review copies at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington;
or at the National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
TABLE 6.—MATERIAL INCORPORATED BY REFERENCE
Airbus service bulletin
Revision level
A300–78–6021, including Appendices 01 and 02 ..................
A300–78–6022, including Appendices 01 and 02 ..................
A300–78–6024 ........................................................................
A300–78–6025 ........................................................................
A310–78–2022, including Appendices 01 and 02 ..................
A310–78–2023 ........................................................................
A310–78–2024, including Appendices 01 and 02 ..................
A310–78–2025 ........................................................................
Issued in Renton, Washington, on March 5,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–4734 Filed 3–15–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26324; Directorate
Identifier 2006–NM–214–AD; Amendment
39–14993; AD 2007–06–12]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
sroberts on PROD1PC70 with RULES
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Airbus Model
A330–300 airplanes. That AD currently
requires reinforcement of the structure
VerDate Aug<31>2005
15:23 Mar 15, 2007
Jkt 211001
02
02
01
01
02
01
01
01
............................................................................................
............................................................................................
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............................................................................................
............................................................................................
............................................................................................
of the center fuselage by installing
external stiffeners (butt straps) at frame
(FR) 53.3 on the fuselage skin between
left-hand (LH) and right-hand (RH)
stringer (STR) 13, and related
investigative and corrective actions.
This new AD requires additional
reinforcement of the structure of the
center fuselage by installing external
stiffeners (butt straps) at frame FR53.3
on the fuselage skin between LH and RH
STR13, and related investigative and
other specified actions. This AD also
adds airplanes to the applicability. This
AD results from cracking found at the
circumferential joint of FR53.3. We are
issuing this AD to prevent fatigue
cracking of the fuselage, which could
result in reduced structural integrity of
the fuselage.
This AD becomes effective April
20, 2007.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of April 20, 2007.
On October 19, 2005 (70 FR 57732,
October 4, 2005), the Director of the
Federal Register approved the
incorporation by reference of Airbus
DATES:
PO 00000
Frm 00011
Date
Fmt 4700
Sfmt 4700
June 8, 2005.
June 8, 2005.
April 22, 2005.
April 22, 2005.
July 18, 2006.
April 22, 2005.
June 13, 2005.
April 22, 2005.
Service Bulletin A330–53–3127,
Revision 01, dated November 21, 2003.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://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
E:\FR\FM\16MRR1.SGM
16MRR1
]]>Agencies
[Federal Register Volume 72, Number 51 (Friday, March 16, 2007)]
[Rules and Regulations]
[Pages 12550-12555]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-4734]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22036; Directorate Identifier 2005-NM-009-AD;
Amendment 39-14994; AD 2007-06-13]
RIN 2120-AA64
Airworthiness Directives; Airbus 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
Airplanes; Equipped With General Electric CF6-80A3 or CF6-80C2 Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus airplane models, as specified above. This AD requires
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 AD results from 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 issuing this AD to prevent
inadvertent deployment of thrust reversers in flight, which could
result in reduced controllability of the airplane.
DATES: This AD becomes effective April 20, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of April 20,
2007.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://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 street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to 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
[[Page 12551]]
Electric (GE) CF6-80A3 or CF6-80C2 engines. That NPRM was published in
the Federal Register on August 8, 2005 (70 FR 45595). That NPRM
proposed to 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.
Since the Issuance of the NPRM
We have received copies of the following Airbus service bulletins:
Airbus Service Bulletin A300-78-6024, Revision 01, dated
April 22, 2005. Revision 01 describes essentially the same procedures
specified in the original issue of the service bulletin, dated October
7, 2003 (referenced in the NPRM as one appropriate source of service
information). Revision 01 also adds technical notes referring to
certain Middle River Aircraft Systems (MRAS) proprietary data
491B1200200, 491B1200201, 491B1200202, and 491B1200203, Revision B,
dated September 9, 2003, which provide instructions to install the
electro-pneumatic locking bar devices in the nacelles on GE Model CF6-
80C2 engines with a full authority digital engine control (FADEC)
thrust reverser system, as additional sources of service information.
Airbus Service Bulletin A300-78-6025, Revision 01, dated
April 22, 2005. Revision 01 describes essentially the same procedures
specified in the original issue of the service bulletin, dated October
7, 2003 (referenced in the NPRM as one appropriate source of service
information). Revision 01 also adds technical notes referring to
certain MRAS proprietary data 491B1200202 and 491B1200203, both
Revision B, both dated September 9, 2003, as additional sources of
service information. The proprietary data provide instructions to
install the electro-pneumatic locking bar devices in the nacelles on GE
Model CF6-80C2 engines with a power management control (PMC) thrust
reverser system.
Airbus Service Bulletin A310-78-2023, Revision 01; and
Airbus Service Bulletin A310-78-2025, Revision 01; both dated April 22,
2005. These service bulletins were issued to advise operators of the
issuance of technical notes referenced in MRAS proprietary data
603A1000, 603A1001, 603A2000, 603A2001, and 603A2100. The proprietary
data provides instructions to install the electro-pneumatic locking bar
devices, as additional sources of service information. (Airbus Service
Bulletin A310-78-2023, dated October 7, 2003; and Airbus Service
Bulletin A310-78-2025, dated July 23, 2004; were referenced as
appropriate sources of service information in the NPRM.)
Airbus Service Bulletin A310-78-2022, Revision 02,
including Appendices 01 and 02, dated July 18, 2006. (The original
version of this service bulletin, dated January 7, 2003, was referenced
as an appropriate source of service information in the NPRM.) Revision
02 updates certain figures referenced in the original version of the
service bulletin.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Withdraw the NPRM
One commenter, American Airlines, states that it appears
inconsistent to invest a significant amount of money for additional
protection by installing electro-pneumatic locking bar devices (TRAS
lock system). The commenter points out that the FAA has previously
extended the inspection interval of current mandated inspections in
another existing AD that also addresses inadvertent thrust reverser
deployment.
We infer that American Airlines is questioning the cost benefit of
the additional protection that the AD provides, and would like us to
withdraw the NPRM. We acknowledge that, although we have extended the
inspection intervals due to positive results of past inspections, the
possibility still exists that a directional pilot valve (DPV) leak may
occur. This type of leak is a hidden failure that cannot be detected at
the system level, and could result in inadvertent thrust reverser
deployment. We have determined that installation of electro-pneumatic
locking bar devices will ensure an adequate measure of protection for
the system. No change is necessary to the AD in this regard.
Requests To Revise the Applicability
Two commenters, Tradewinds Airlines and GE Transportation, request
that the applicability stated in the NPRM be revised by removing Airbus
Model A300 B2 and B4 series airplanes. One commenter points out that
those models are not specified in the French airworthiness directive,
and that there are no service bulletins specified in the NPRM that are
applicable to those models.
We agree with the commenters. We acknowledge that the Model A300 B2
and B4 series airplanes are not equipped with the affected engines and
were inadvertently included in the NPRM. The applicability of this AD
is revised to remove those airplane models.
Another commenter, Airbus, requests that the associated
modification numbers for the corresponding service bulletins be added
to the applicability of the NPRM. Airbus suggests that adding the
associated modification numbers will make it easier for operators to
comply with the AD and will help operators to avoid having to request
alternative methods of compliance.
We partially agree with the commenter's request in this case. The
applicability of French airworthiness directive F-2004-165 excludes
airplanes on which Airbus Service Bulletins A310-78-2024; A310-78-2025;
A310-78-2022; A310-78-2023, A300-78-6022, Revision 1; A300-78-6025;
A300-78-6021 original issue or Revision 01; and A300-78-6024; have been
accomplished in-service, as well as certain modifications accomplished
during production. We agree that revising the applicability of the
final rule is necessary to exclude airplanes on which certain
modifications have been accomplished during production. However, as is
our standard practice, we have not excluded those airplanes that have
accomplished certain modifications in service in the applicability of
this final rule. Rather, this final rule includes requirements to
accomplish the actions specified in the service bulletins that clearly
identify the airplanes that the service bulletins affect. The
requirements of the specified service bulletins will ensure that the
actions required by this final rule are accomplished on all affected
airplanes. Operators must continue to operate the airplane in the
configuration required by this final rule unless an alternative method
of compliance is approved. We have, however, added a new Note 1 and
Table 2 to this final rule that provide a list of corresponding
modifications with the applicable service bulletins for ease of
reference for the operators. We have re-identified subsequent notes and
tables accordingly.
Requests To Revise the ``Costs of Compliance'' Section
Several commenters, including theAir Transport Association (ATA),
on behalf of one of its members, American Airlines, and FedEx and GE
Transportation, request that the estimated costs of complying with the
NPRM be revised to add additional work hours. American Airlines states
that the NPRM would require concurrent accomplishment of four service
bulletins that are not specified
[[Page 12552]]
in the NPRM. American Airlines estimates it will take 600 work hours
and $283,042 for parts per each of its airplanes, rather than the costs
estimated in the applicable service bulletins in the NPRM for various
airplane models. FedEx explains that the cost estimates in the NPRM are
not realistic because additional modification requirements are
necessary that are described in MRAS and Goodrich/Rohr technical
documents. One commenter, GE Transportation, also points out that
certain cost information is available in certain service information
that is not referred to in the NPRM.
We acknowledge that certain estimated costs were not included in
the NPRM. We have obtained the additional service information from
MRAS, but it does not contain estimated cost information. We also have
requested further information from one of the commenters, GE
Transportation, which has provided some new cost information figures to
us. We have revised the estimated costs of the AD by including the
estimated costs of accomplishing the MRAS service bulletins. We have
coordinated those estimated costs with Airbus.
Request To Clarify ``Relevant Service Information'' Section
GE Transportation suggests certain revised wording regarding the
work tasks described in the service bulletins specified in the
``Relevant Service Information'' section of the NPRM.
We consider that the descriptions of the work tasks in the NPRM
adequately describe those tasks. Since that section of the preamble in
the NPRM does not reappear in the final rule, no change to the AD is
necessary.
Request To Consider the Possibility of No Deployment
American Airlines requests that we consider the possibility that an
increase in risk of no deployment on landing may occur with the
modification installed. American Airlines states that the modification
could affect reliable operations in those airports restricted by short
runway lengths when employing the Minimum Equipment List provisions.
We acknowledge the commenter's concern. In its reassessment of
thrust reverser reliability, the manufacturer considered the
possibility of thrust reverser non-deployment on landing with the third
line of defense (TLOD) system installed. The reassessment showed that
the thrust reverser without the TLOD could inadvertently deploy in
flight under certain conditions, which could lead to decreased aircraft
controllability. We have determined that the basic two-line-of-defense
architecture does not adequately address the system's vulnerability to
damage and long-term maintainability. Therefore, the modification is
necessary to prevent the identified unsafe condition. In addition, we
have not seen an increase in occurrences of thrust reverser
nondeployments on landing for aircraft that have a TLOD or other thrust
reverser third lock-type system installed. No change to the AD is
necessary regarding this issue.
Request To Use Latest Service Bulletin Revisions
Several commenters, including the ATA, on behalf of one of its
members, American Airlines, and FedEx, note that new revisions of
certain service bulletins have been issued since the issuance of the
NPRM. The commenters are requesting that we mandate the new revisions,
which contain test procedures that will take less time for the
operators to accomplish.
We agree with the commenters. We have received certain newer
revisions of the service bulletins (described previously) from the
manufacturer and have specified those revisions in Table 3 of the AD.
Additionally, we received new revisions of the service bulletins
specified in Table 2 of the AD from the manufacturer. We have revised
Table 2 of the AD accordingly.
Explanation of Change to Applicability
We have revised the applicability of the AD to identify model
designations as published in the most recent type certificate data
sheet for the affected models.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither significantly
increase the economic burden on any operator nor increase the scope of
the AD.
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 are required to accomplish two
of the specified service bulletins.) The following table provides the
estimated costs for U.S. operators to comply with this AD at an average
labor rate per hour of $80.
Estimated Costs for Modifications (Listed by Applicable Service Bulletin)
----------------------------------------------------------------------------------------------------------------
Work Cost per Number of
Airbus service bulletins (SB) hours Parts airplane airplanes Cost per SB
----------------------------------------------------------------------------------------------------------------
A300-78-6021, Revision 02............................ 257 $19,652 $40,212 36 $1,447,632
A300-78-6024, Revision 01............................ 206 223,649 240,129 36 8,644,644
A300-78-6022, Revision 02............................ 289 19,220 42,340 34 1,439,560
A300-78-6025, Revision 01............................ 206 223,649 240,129 34 8,164,386
A310-78-2024, Revision 01............................ 262 19,119 40,079 31 1,242,449
A310-78-2025, Revision 01............................ 206 194,487 210,967 31 6,539,977
----------------------------------------------------------------------------------------------------------------
None of the airplanes required to accomplish the following service
bulletins are currently on the U.S. Register. The airplanes affected by
the following service bulletins are currently operated by non-U.S.
operators under foreign registry; therefore, they are not directly
affected by this AD action. However, we consider it necessary to
include these airplanes to ensure that the unsafe condition is
addressed if any affected airplane is imported and placed on the U.S.
Register in the future. The estimated costs apply to any affected
[[Page 12553]]
airplane should it be imported and placed on the U.S. Register in the
future.
Estimated Costs for Modifications for Certain Other Airplanes
------------------------------------------------------------------------
Work Cost per
Airbus service bulletin (SB) hours Parts airplane
------------------------------------------------------------------------
A310-78-2022............................. 275 19,652 41,652
A310-78-2023............................. 206 $223,649 $240,129
------------------------------------------------------------------------
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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 AD and placed it in the AD docket. 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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2007-06-13 Airbus: Amendment 39-14994. Docket No. FAA-2005-22036;
Directorate Identifier 2005-NM-009-AD.
Effective Date
(a) This AD becomes effective April 20, 2007.
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; except for those airplanes on which the following applicable
modifications have been incorporated in production: Airbus Modification
12348, 12349, 12350, 12514, and 12511.
Table 1.--Applicability
----------------------------------------------------------------------------------------------------------------
General Electric Airbus service
Airplane models engine model bulletin and revision Date
----------------------------------------------------------------------------------------------------------------
A300 B4-605R and F4-605R airplanes. CF6-80C2.............. A300-78-6024, Revision April 22, 2005.
01.
A300 B4-605R and F4-605R airplanes. CF6-80C2.............. A300-78-6021, Revision June 8, 2005.
02.
A300 B4-601, B4-603, B4-605R, and CF6-80C2.............. A300-78-6025, Revision April 22, 2005.
C4-605R Variant F airplanes. 01.
A300 B4-601, B4-603, B4-605R, and CF6-80C2.............. A300-78-6022, Revision June 8, 2005.
C4-605R Variant F airplanes. 02.
A310 airplanes..................... CF6-80C2.............. A310-78-2023, Revision April 22, 2005.
01.
A310 airplanes..................... CF6-80C2.............. A310-78-2022, Revision July 18, 2006.
02.
A310 airplanes..................... CF6-80A3.............. A310-78-2024, Revision June 13, 2005.
01.
A310 airplanes..................... CF6-80A3.............. A310-78-2025, Revision April 22, 2005.
01.
----------------------------------------------------------------------------------------------------------------
Note 1: We have provided a list of corresponding modifications
with the applicable Airbus service bulletins in Table 2 of this AD
for ease of reference for the operators.
Table 2.--Corresponding Modifications
------------------------------------------------------------------------
Airbus service bulletin Modifications
------------------------------------------------------------------------
A310-78-2022 and A300-78-6022............. 12348, 12350, 12351, and
12514.
A310-78-2023 and A300-78-6025............. 12512.
[[Page 12554]]
A310-78-2024.............................. 12552 and 12553.
A310-78-2025.............................. 12564.
A300-78-6021.............................. 12348, 12349, 12350, and
12514.
A300-78-6024.............................. 12511.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from 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 Lock Systems and Accomplishing Modifications
(f) For airplanes identified in the service bulletins specified in
Table 3 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 3.--Installing TRAS Lock Systems
----------------------------------------------------------------------------------------------------------------
General electric Airbus service
Airplane models engine model bulletin and revision Date
----------------------------------------------------------------------------------------------------------------
A300 B4-605R and F4-605R airplanes. CF6-80C2.............. A300-78-6024, Revision April 22, 2005.
01.
A300 B4-601, B4-603, B4-605R, and CF6-80C2.............. A300-78-6025, Revision April 22, 2005.
C4-605R Variant F airplanes. 01.
A310 airplanes..................... CF6-80C2.............. A310-78-2023, Revision April 22, 2005.
01.
A310 airplanes..................... CF6-80A3.............. A310-78-2025, Revision April 22, 2005.
01.
----------------------------------------------------------------------------------------------------------------
Note 2: Airbus Service Bulletin A310-78-2025, Revision 01, dated
April 22, 2005, references draft Goodrich Service Bulletin 71-065 as
an additional source of service information. After the issuance of
Airbus Service Bulletin A310-78-2025, the Goodrich service bulletin
was reissued as Rohr Service Bulletin CF6-80A3-NAC-71-065, dated
April 28, 2005.
(g) For airplanes identified in the service bulletins specified in
Table 4 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 4 of this AD.
Table 4.--Prior or Concurrent Accomplishment
----------------------------------------------------------------------------------------------------------------
Airplanes equipped
Airplane models with General Electric Airbus service Date
engine model bulletin and revision
----------------------------------------------------------------------------------------------------------------
A300 B4-605R and F4-605R airplanes. CF6-80C2 (with full A300-78-6021, Revision June 8, 2005.
authority digital 02, including
engine control Appendices 01 and 02.
(FADEC)).
A300 B4-601, B4-603, B4-605R, and CF6-80C2 (without A300-78-6022, Revision June 8, 2005.
C4-605R Variant F airplanes. FADEC). 02, including
Appendices 01 and 02.
A310 airplanes..................... CF6-80C2 (without A310-78-2022 Revision June 18, 2006.
FADEC). 02, including
Appendices 01 and 02.
A310 airplanes..................... CF6-80A3.............. A310-78-2024 Revision June 13, 2005.
01, including
Appendices 01 and 02.
----------------------------------------------------------------------------------------------------------------
Actions Accomplished According to Previous Issues of Service Bulletins
(h) Actions accomplished in accordance with the following service
bulletins are acceptable for compliance with the requirements of this
AD, as applicable, if done before the effective date of this AD:
Table 5.--Service Bulletins Accomplished Previously
------------------------------------------------------------------------
Airbus service bulletin Revision level Date
------------------------------------------------------------------------
A300-78-6021................. Original........ April 8, 2003.
A300-78-6021................. 01.............. October 7, 2003.
A300-78-6022................. 01.............. January 7, 2003.
A300-78-6024................. Original........ October 7, 2003.
A300-78-6025................. Original........ October 7, 2003.
A310-78-2022................. Original........ January 7, 2003.
A310-78-2022................. 01.............. June 8, 2005.
[[Page 12555]]
A310-78-2023................. Original........ October 7, 2003.
A310-78-2024................. Original........ October 15, 2003.
A310-78-2025................. Original........ July 23, 2004.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(i)(1) 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.
(2) Before using any AMOC approved in accordance with 14 CFR 39.19
on any airplane to which the AMOC applies, notify the appropriate
principal inspector in the FAA Flight Standards Certificate Holding
District Office.
Related Information
(j) French airworthiness directive F-2004-165, dated October 13,
2004, also addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use the applicable Airbus service bulletins specified
in Table 6 of this AD to perform the actions that are required by this
AD, unless the AD specifies otherwise. The Director of the Federal
Register approved the incorporation by reference of these documents in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of
this service information. You may review copies at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-741-
6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Table 6.--Material Incorporated by Reference
------------------------------------------------------------------------
Airbus service bulletin Revision level Date
------------------------------------------------------------------------
A300-78-6021, including 02.............. June 8, 2005.
Appendices 01 and 02.
A300-78-6022, including 02.............. June 8, 2005.
Appendices 01 and 02.
A300-78-6024................. 01.............. April 22, 2005.
A300-78-6025................. 01.............. April 22, 2005.
A310-78-2022, including 02.............. July 18, 2006.
Appendices 01 and 02.
A310-78-2023................. 01.............. April 22, 2005.
A310-78-2024, including 01.............. June 13, 2005.
Appendices 01 and 02.
A310-78-2025................. 01.............. April 22, 2005.
------------------------------------------------------------------------
Issued in Renton, Washington, on March 5, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-4734 Filed 3-15-07; 8:45 am]
BILLING CODE 4910-13-P
