Airworthiness Directives; Airbus Model A340-211, -212, -311, and -312 Airplanes, 59233-59236 [05-20073]
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Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations
and series 2B airplanes, certificated in any
category, with batteries installed in the
nosecone.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2005–20–34 BAE Systems (Operations)
Limited (Formerly British Aerospace
Regional Aircraft): Amendment 39–
14331. Docket No. FAA–2005–22625;
Directorate Identifier 2003–NM–213–AD.
Effective Date
(a) This AD becomes effective October 27,
2005.
(d) This AD results from an accident in
which the nose landing leg, together with the
pintle webs, detached from the airplane. As
a result, the battery earth return cables were
severed from their earth posts. We are issuing
this AD to prevent loss of safety critical
services including fuel shut-off and nacelle
fire extinguishing services.
Compliance
Related Information
(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.
(h) British airworthiness directive 006–01–
003 also addresses the subject of this AD.
Battery Earth Post Relocation
Affected ADs
(b) None.
Applicability
(c) This AD applies to BAE Systems
(Operations) Limited Model HS 748 series 2A
Alternative Methods of Compliance
(AMOCs)
(g)(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.
Unsafe Condition
Authority: 49 U.S.C. 106(g), 40113, 44701.
59233
(f) Within 120 days after the effective date
of this AD, relocate the battery earth posts,
in accordance with the Accomplishment
Instructions of BAE Systems (Operations)
Limited Service Bulletin HS748–24–131,
Revision 1, dated June 16, 2003.
Material Incorporated by Reference
(i) You must use BAE Systems (Operations)
Limited Service Bulletin HS748–24–131,
Revision 1, dated June 16, 2003, to perform
the actions that are required by this AD,
unless the AD specifies otherwise. BAE
Systems (Operations) Limited Service
Bulletin HS748–24–131, Revision 1, dated
June 16, 2003, contains the following
effective pages:
Page number
Revision level
shown on page
Date shown on
page
1–12, 14 ........................................................................................................................................................
13 ..................................................................................................................................................................
1 .......................
Original .............
June 16, 2003.
January 20, 2003.
The Director of the Federal Register
approved the incorporation by reference of
this document in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact British
Aerospace Regional Aircraft American
Support, 13850 Mclearen Road, Herndon,
Virginia 20171, for a copy of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street SW., room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
September 28, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–20068 Filed 10–11–05; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22614; Directorate
Identifier 2005–NM–035–AD; Amendment
39–14324; AD 2005–20–27]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A340–211, –212, –311, and –312
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A340–211, –212, –311,
and –312 airplanes. This AD requires an
initial rotating probe inspection and
initial and repetitive ultrasonic
inspections for discrepancies of the first
fastener hole of the horizontal flange of
the keel beam on previously modified
airplanes, installation of new fasteners,
and corrective action if necessary. This
AD results from a report that certain
inspections done before accomplishing
the modification of the lower keel beam
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fitting and forward lower shell
connection, revealed cracking that was
outside the modification limits specified
in the service bulletin; the cracking was
repaired by installing a titanium
doubler. We are issuing this AD to find
and fix discrepancies of the fastener
holes of the horizontal flange of the keel
beam, which could result in reduced
structural integrity of the fuselage.
DATES: This AD becomes effective
October 27, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 27, 2005.
We must receive comments on this
AD by December 12, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking web
site: Go to https://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.
• Fax: (202) 493–2251.
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• 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.
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
98055–4056; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
´ ´
The Direction Generale de l’Aviation
Civile (DGAC), which is the
airworthiness authority for France,
notified us that an unsafe condition may
exist on certain Airbus Model A340–
211, –212, –311, and –312 airplanes.
The DGAC advises that certain
inspections done before accomplishing
the modification specified in Airbus
Service Bulletin A340–57–4036 (Airbus
Modification 43577), Revision 05, dated
March 14, 2000, revealed cracking that
was outside the modification limits
specified in that service bulletin. The
cracking was repaired by installing a
titanium doubler using certain repair
drawings. Subsequently, a detailed
structural analysis was done on the
repaired airplanes. It was determined by
the manufacturer that a specific
inspection program is necessary for the
repaired airplanes in order to maintain
structural integrity. Cracking of the
fastener holes of the horizontal flange of
the keel beam could result in reduced
structural integrity of the fuselage.
Relevant Service Information
Airbus has issued Service Bulletin
A340–57–4087, dated November 21,
2003. The service bulletin describes
procedures for an initial rotating probe
inspection and initial and repetitive
ultrasonic inspections for discrepancies
(cracking, out-of-tolerance fastener
holes, and fastener damage) of the first
fastener hole of the horizontal flange of
the keel beam. If no cracking is found
during the rotating probe inspection, the
service bulletin describes procedures for
installation of a new fastener and
determining if the fastener hole is outof-tolerance. The corrective action for
any out-of-tolerance hole includes
reaming any out-of-tolerance fastener
holes to oversize and installing
oversized fasteners. The service bulletin
also describes procedures for repetitive
follow-on ultrasonic inspections for
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16:47 Oct 11, 2005
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cracking, and contacting Airbus for
repair instructions if cracking is found.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition. The DGAC mandated the
service information and issued French
airworthiness directive F–2005–007,
dated January 5, 2005, to ensure the
continued airworthiness of these
airplanes in France.
The service bulletin also specifies to
contact the manufacturer for disposition
of certain repair conditions and report
inspection findings to the manufacturer.
The service bulletin refers to Airbus
Service Bulletin A340–57–4036,
Revision 05, dated March 14, 2000, as
the source of service information for
accomplishing Airbus Modification
43577. The modification was previously
accomplished on all airplanes affected
by this AD.
FAA’s Determination and Requirements
of This 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 issuing this AD to
find and fix discrepancies of the
fastener holes of the horizontal flange of
the keel beam, which could result in
reduced structural integrity of the
fuselage. This AD requires
accomplishing the actions specified in
Service Bulletin A340–57–4087,
described previously, except as
discussed under ‘‘Difference Between
this AD, the French Airworthiness
Directive, and Service Bulletin A340–
57–4087.’’
Difference Between This AD, the French
Airworthiness Directive, and Service
Bulletin A340–57–4087
The French airworthiness directive
and the service bulletin specify
contacting the manufacturer for
disposition of certain repair conditions;
this AD requires the repair of those
conditions to be accomplished per a
method approved by either the FAA or
the DGAC (or its delegated agent). In
light of the type of repair that would be
required to address the identified unsafe
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condition, and in consonance with
existing bilateral airworthiness
agreements, the FAA has determined
that, for this AD, a repair approved by
either the FAA or the DGAC (or its
delegated agent) would be acceptable for
compliance with this AD.
Although the French airworthiness
directive allows for use of the
procedures specified in Airbus
Technical Disposition F57D03012810 or
582.0651/2002 for accomplishing the
first rotating probe inspection, this AD
does not allow for those documents to
be used. This difference has been
coordinated with the DGAC.
Clarification of Compliance Time
The service bulletin and French
airworthiness directive do not provide a
compliance time for the initial
ultrasonic inspection if no cracking is
found during the rotating probe
inspection; however, this AD requires
that the inspection be done within 1,480
flight cycles or 7,400 flight hours after
accomplishing the one-time rotating
probe inspection.
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
If an affected airplane is imported and
placed on the U.S. Register in the future,
it would take between 3 and 8 work
hours per airplane for the initial
inspections and about 2 work hours per
airplane for each repetitive inspection,
at an average labor rate of $65 per work
hour. Two kits would be required for
installing the new fasteners after
discarding the removed fasteners. Parts
cost is $190 for each kit. Based on these
figures, the estimated cost of the initial
actions would be between $575 and
$900 per airplane; and the estimated
cost of the repeat inspection is
estimated to be $130 per airplane, per
inspection cycle.
FAA’s Determination of the Effective
Date
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
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Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations
Comments Invited
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.
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2005–22614; Directorate Identifier
2005–NM–035–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
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 AD. Using the
search function of that 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 may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
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 the 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 AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
Examining the Docket
List of Subjects in 14 CFR Part 39
You may examine the 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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
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Regulatory Findings
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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
2005–20–27 Airbus: Amendment 39–14324.
Docket No. FAA–2005–22614;
Directorate Identifier 2005–NM–035–AD.
Effective Date
(a) This AD becomes effective October 27,
2005.
Affected ADs
(b) None.
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59235
Applicability
(c) This AD applies to Airbus Model A340–
211, –212, –311, and –312 airplanes,
certificated in any category, serial numbers
0006, 0007 (right-hand side only), 0008,
0013, 0020, 0024 (left-hand side only), 0027
through 0029 inclusive, 0031, 0033, 0035,
0038 through 0040 inclusive, 0043, 0047,
0049, and 0052.
Unsafe Condition
(d) This AD results from a report that
certain inspections done before
accomplishing the modification of the lower
keel beam fitting and forward lower shell
connection revealed cracking that was
outside the modification limits specified in
the service bulletin; the cracking was
repaired by installing a titanium doubler. The
FAA is issuing this AD to find and fix
discrepancies of the fastener holes of the
horizontal flange of the keel beam, which
could result in reduced structural integrity of
the fuselage.
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.
Note 1: Airbus Service Bulletin A340–57–
4087, dated November 21, 2003, cites Airbus
Service Bulletin A340–57–4036, Revision 05,
dated March 14, 2000, as the source of
service information for accomplishing Airbus
Modification 43577.
Initial/Repetitive Nondestructive Test
Inspections/Repair
(f) Within 5,420 flight cycles or 26,200
flight hours after accomplishing Airbus
Modification 43577, whichever is first:
Perform an initial rotating probe inspection
for discrepancies of the first fastener hole of
the horizontal flange of the keel beam by
doing all the actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A340–57–4087, dated
November 21, 2003. If no cracking is found,
before further flight, inspect for correct
fastener diameter tolerance; if the fastener
diameter is out-of-tolerance, before further
flight, ream to oversize the fastener holes and
install oversize fasteners in accordance with
the Accomplishment Instructions of the
service bulletin.
(g) If no cracking is found during any
inspection required by paragraph (f) of this
AD: Within 1,480 flight cycles or 7,400 flight
hours, whichever is first, after accomplishing
the inspection: Perform an initial ultrasonic
inspection for discrepancies of the first
fastener hole of the horizontal flange of the
keel beam by doing all the actions in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A340–
57–4087, dated November 21, 2003. If no
cracking is found, repeat the ultrasonic
inspection thereafter at intervals not to
exceed 1,480 flight cycles or 7,400 flight
hours, whichever is first.
Repair Per the FAA or the Direction
´ ´
Generale De L’Aviation Civile (DGAC)
(h) If any cracking is found during any
inspection required by this AD: Before
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further flight, repair per a method approved
by either the Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA; or the DGAC (or its delegated agent).
Within 1,480 flight cycles or 7,400 flight
hours, whichever is first, after repair of any
cracking, perform an ultrasonic inspection as
required by paragraph (g) of this AD. Repeat
the ultrasonic inspection thereafter at
intervals not to exceed 1,480 flight cycles or
7,400 flight hours, whichever is first.
No Reporting Required
(i) Although Airbus Service Bulletin A340–
57–4087, dated November 21, 2003, specifies
submitting an inspection report to the
manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, International Branch,
ANM–116, 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
(k) French airworthiness directive F–2005–
007, dated January 5, 2005, also addresses the
subject of this AD.
Material Incorporated by Reference
(l) You must use Airbus Service Bulletin
A340–57–4087, including Appendix 01,
dated November 21, 2003, 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 this document
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 Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washington,
DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
September 28, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–20073 Filed 10–11–05; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Discussion
[Docket No. FAA–2005–21862; Directorate
Identifier 2005–NM–091–AD; Amendment
39–14333; AD 2005–20–36]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A320–111 Airplanes; and Model A320–
200, A321–100, and A321–200 Series
Airplanes
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 Model A320–111 airplanes; and
Model A320–200, A321–100, and A321–
200 series airplanes. This AD requires
installing a bonding lead between the
low pressure valve and the adjacent
pipe assembly in each wing. This AD
results from fuel system reviews
conducted by the manufacturer. We are
issuing this AD to prevent an ignition
source for fuel vapor in the wing, which
could result in fire or explosion in the
adjacent wing fuel tank.
DATES: This AD becomes effective
November 16, 2005.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of November 16, 2005.
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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
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
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(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
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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 A320–
111 airplanes; and Model A320–200,
A321–100, and A321–200 series
airplanes. That NPRM was published in
the Federal Register on July 19, 2005
(70 FR 41352). That NPRM proposed to
require installing a bonding lead
between the low pressure valve and the
adjacent pipe assembly in each wing.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment received.
Request to Allow Credit for Use of
Original Issue of Service Bulletin
One commenter requests that we give
credit for actions accomplished prior to
the effective date of the AD using Airbus
Service Bulletin A320–28–1055, dated
July 12, 1993. The commenter contends
that such credit is permitted by French
airworthiness directive F–2005–058,
dated April 13, 2005.
We agree with this request. We have
reviewed the original issue of the
service bulletin and determined that no
significant technical changes were made
in the issuance of Airbus Service
Bulletin A320–28–1055, Revision 1,
dated March 8, 1994. Therefore, we
have added new paragraph (g) to give
credit as specified and re-identified
existing paragraphs (g) and (h) to (h)(1)
and (i) in this AD.
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 comment
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 increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
This AD will affect about 403
airplanes of U.S. registry. The required
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]]>Agencies
[Federal Register Volume 70, Number 196 (Wednesday, October 12, 2005)]
[Rules and Regulations]
[Pages 59233-59236]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-20073]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22614; Directorate Identifier 2005-NM-035-AD;
Amendment 39-14324; AD 2005-20-27]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A340-211, -212, -311, and
-312 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Model A340-211, -212, -311, and -312 airplanes. This AD
requires an initial rotating probe inspection and initial and
repetitive ultrasonic inspections for discrepancies of the first
fastener hole of the horizontal flange of the keel beam on previously
modified airplanes, installation of new fasteners, and corrective
action if necessary. This AD results from a report that certain
inspections done before accomplishing the modification of the lower
keel beam fitting and forward lower shell connection, revealed cracking
that was outside the modification limits specified in the service
bulletin; the cracking was repaired by installing a titanium doubler.
We are issuing this AD to find and fix discrepancies of the fastener
holes of the horizontal flange of the keel beam, which could result in
reduced structural integrity of the fuselage.
DATES: This AD becomes effective October 27, 2005.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 27,
2005.
We must receive comments on this AD by December 12, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking web site: Go to https://
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.
Fax: (202) 493-2251.
[[Page 59234]]
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.
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 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
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 A340-211, -212, -
311, and -312 airplanes. The DGAC advises that certain inspections done
before accomplishing the modification specified in Airbus Service
Bulletin A340-57-4036 (Airbus Modification 43577), Revision 05, dated
March 14, 2000, revealed cracking that was outside the modification
limits specified in that service bulletin. The cracking was repaired by
installing a titanium doubler using certain repair drawings.
Subsequently, a detailed structural analysis was done on the repaired
airplanes. It was determined by the manufacturer that a specific
inspection program is necessary for the repaired airplanes in order to
maintain structural integrity. Cracking of the fastener holes of the
horizontal flange of the keel beam could result in reduced structural
integrity of the fuselage.
Relevant Service Information
Airbus has issued Service Bulletin A340-57-4087, dated November 21,
2003. The service bulletin describes procedures for an initial rotating
probe inspection and initial and repetitive ultrasonic inspections for
discrepancies (cracking, out-of-tolerance fastener holes, and fastener
damage) of the first fastener hole of the horizontal flange of the keel
beam. If no cracking is found during the rotating probe inspection, the
service bulletin describes procedures for installation of a new
fastener and determining if the fastener hole is out-of-tolerance. The
corrective action for any out-of-tolerance hole includes reaming any
out-of-tolerance fastener holes to oversize and installing oversized
fasteners. The service bulletin also describes procedures for
repetitive follow-on ultrasonic inspections for cracking, and
contacting Airbus for repair instructions if cracking is found.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The DGAC mandated
the service information and issued French airworthiness directive F-
2005-007, dated January 5, 2005, to ensure the continued airworthiness
of these airplanes in France.
The service bulletin also specifies to contact the manufacturer for
disposition of certain repair conditions and report inspection findings
to the manufacturer. The service bulletin refers to Airbus Service
Bulletin A340-57-4036, Revision 05, dated March 14, 2000, as the source
of service information for accomplishing Airbus Modification 43577. The
modification was previously accomplished on all airplanes affected by
this AD.
FAA's Determination and Requirements of This 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 issuing this AD to find and fix discrepancies of
the fastener holes of the horizontal flange of the keel beam, which
could result in reduced structural integrity of the fuselage. This AD
requires accomplishing the actions specified in Service Bulletin A340-
57-4087, described previously, except as discussed under ``Difference
Between this AD, the French Airworthiness Directive, and Service
Bulletin A340-57-4087.''
Difference Between This AD, the French Airworthiness Directive, and
Service Bulletin A340-57-4087
The French airworthiness directive and the service bulletin specify
contacting the manufacturer for disposition of certain repair
conditions; this AD requires the repair of those conditions to be
accomplished per a method approved by either the FAA or the DGAC (or
its delegated agent). In light of the type of repair that would be
required to address the identified unsafe condition, and in consonance
with existing bilateral airworthiness agreements, the FAA has
determined that, for this AD, a repair approved by either the FAA or
the DGAC (or its delegated agent) would be acceptable for compliance
with this AD.
Although the French airworthiness directive allows for use of the
procedures specified in Airbus Technical Disposition F57D03012810 or
582.0651/2002 for accomplishing the first rotating probe inspection,
this AD does not allow for those documents to be used. This difference
has been coordinated with the DGAC.
Clarification of Compliance Time
The service bulletin and French airworthiness directive do not
provide a compliance time for the initial ultrasonic inspection if no
cracking is found during the rotating probe inspection; however, this
AD requires that the inspection be done within 1,480 flight cycles or
7,400 flight hours after accomplishing the one-time rotating probe
inspection.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
If an affected airplane is imported and placed on the U.S. Register
in the future, it would take between 3 and 8 work hours per airplane
for the initial inspections and about 2 work hours per airplane for
each repetitive inspection, at an average labor rate of $65 per work
hour. Two kits would be required for installing the new fasteners after
discarding the removed fasteners. Parts cost is $190 for each kit.
Based on these figures, the estimated cost of the initial actions would
be between $575 and $900 per airplane; and the estimated cost of the
repeat inspection is estimated to be $130 per airplane, per inspection
cycle.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
[[Page 59235]]
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2005-
22614; Directorate Identifier 2005-NM-035-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
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 AD. Using the search function of that 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 may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the 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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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 the 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 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:
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):
2005-20-27 Airbus: Amendment 39-14324. Docket No. FAA-2005-22614;
Directorate Identifier 2005-NM-035-AD.
Effective Date
(a) This AD becomes effective October 27, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A340-211, -212, -311, and -
312 airplanes, certificated in any category, serial numbers 0006,
0007 (right-hand side only), 0008, 0013, 0020, 0024 (left-hand side
only), 0027 through 0029 inclusive, 0031, 0033, 0035, 0038 through
0040 inclusive, 0043, 0047, 0049, and 0052.
Unsafe Condition
(d) This AD results from a report that certain inspections done
before accomplishing the modification of the lower keel beam fitting
and forward lower shell connection revealed cracking that was
outside the modification limits specified in the service bulletin;
the cracking was repaired by installing a titanium doubler. The FAA
is issuing this AD to find and fix discrepancies of the fastener
holes of the horizontal flange of the keel beam, which could result
in reduced structural integrity of the fuselage.
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.
Note 1: Airbus Service Bulletin A340-57-4087, dated November 21,
2003, cites Airbus Service Bulletin A340-57-4036, Revision 05, dated
March 14, 2000, as the source of service information for
accomplishing Airbus Modification 43577.
Initial/Repetitive Nondestructive Test Inspections/Repair
(f) Within 5,420 flight cycles or 26,200 flight hours after
accomplishing Airbus Modification 43577, whichever is first: Perform
an initial rotating probe inspection for discrepancies of the first
fastener hole of the horizontal flange of the keel beam by doing all
the actions in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A340-57-4087, dated November 21, 2003. If no
cracking is found, before further flight, inspect for correct
fastener diameter tolerance; if the fastener diameter is out-of-
tolerance, before further flight, ream to oversize the fastener
holes and install oversize fasteners in accordance with the
Accomplishment Instructions of the service bulletin.
(g) If no cracking is found during any inspection required by
paragraph (f) of this AD: Within 1,480 flight cycles or 7,400 flight
hours, whichever is first, after accomplishing the inspection:
Perform an initial ultrasonic inspection for discrepancies of the
first fastener hole of the horizontal flange of the keel beam by
doing all the actions in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A340-57-4087, dated November
21, 2003. If no cracking is found, repeat the ultrasonic inspection
thereafter at intervals not to exceed 1,480 flight cycles or 7,400
flight hours, whichever is first.
Repair Per the FAA or the Direction G[eacute]n[eacute]rale De
L'Aviation Civile (DGAC)
(h) If any cracking is found during any inspection required by
this AD: Before
[[Page 59236]]
further flight, repair per a method approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the DGAC (or its delegated agent). Within 1,480 flight cycles or
7,400 flight hours, whichever is first, after repair of any
cracking, perform an ultrasonic inspection as required by paragraph
(g) of this AD. Repeat the ultrasonic inspection thereafter at
intervals not to exceed 1,480 flight cycles or 7,400 flight hours,
whichever is first.
No Reporting Required
(i) Although Airbus Service Bulletin A340-57-4087, dated
November 21, 2003, specifies submitting an inspection report to the
manufacturer, this AD does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, International Branch, ANM-116, 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
(k) French airworthiness directive F-2005-007, dated January 5,
2005, also addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Airbus Service Bulletin A340-57-4087, including
Appendix 01, dated November 21, 2003, 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 this document 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 Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Renton, Washington, on September 28, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-20073 Filed 10-11-05; 8:45 am]
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