Airworthiness Directives; Airbus Model A310 Series Airplanes, 45952-45954 [E7-16118]
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45952
Federal Register / Vol. 72, No. 158 / Thursday, August 16, 2007 / Proposed Rules
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
Issued in Renton, Washington, on July 30,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–16104 Filed 8–15–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
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
proposed AD.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1622;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
14 CFR Part 39
Comments Invited
[Docket No. FAA–2007–28996; Directorate
Identifier 2006–NM–217–AD]
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2007–28996; Directorate
Identifier 2006–NM–217–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to 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 proposed 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.
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
Airbus Model A310 series airplanes.
This proposed AD would require
revising the Airworthiness Limitations
section of the Instructions for Continued
Airworthiness to incorporate new and
revised structural inspections and
inspection intervals. This proposed AD
results from issuance of new and
revised structural inspections and
inspection intervals. We are proposing
this AD to detect and correct fatigue
cracking, which could result in reduced
structural integrity of the airplane.
DATES: We must receive comments on
this proposed AD by September 17,
2007.
Use one of the following
addresses to submit comments on this
proposed 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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
rwilkins on PROD1PC63 with PROPOSALS
ADDRESSES:
VerDate Aug<31>2005
17:19 Aug 15, 2007
Jkt 211001
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located on the
ground floor of the West Building at the
DOT street address stated in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
PO 00000
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the Docket Management System receives
them.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, notified us that an unsafe
condition may exist on all Airbus Model
A310 series airplanes. The EASA
advises that Airbus has issued new and
revised structural inspections and
inspection intervals to detect and
correct fatigue cracking. This condition,
if not corrected, could result in reduced
structural integrity of the airplane.
Relevant Service Information
Airbus has issued A310
Airworthiness Limitation Items (ALI)
Document, AI/SE–M2/95A.0263/06,
Issue 6, dated April 2006 (approved by
the EASA on May 31, 2006) (hereafter
referred to as ‘‘Issue 6 of the ALI’’). That
ALI document describes fatigue-related
structural inspections arising from the
evaluation of damage tolerance and
widespread fatigue damage.
Airbus has also issued Temporary
Revision (TR) 6.1, dated November 2006
(approved by the EASA on December
12, 2006), to Issue 6 of the ALI. Airbus
TR 6.1 provides new and revised
inspections to address certification of
the new Model A310–300 weight
variant airplanes (Airbus Modification
13302). The applicability, limit of
validity, program rules, program notes,
and definitions stated in Issue 6 of the
ALI remain valid.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. The EASA mandated the
service information and issued
airworthiness directive 2006–0260,
dated August 25, 2006, to ensure the
continued airworthiness of these
airplanes in the European Union.
FAA’s Determination and Requirements
of the Proposed AD
This airplane model is manufactured
in France and is 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. As described
in FAA Order 8100.14A, ‘‘Interim
Procedures for Working with the
European Community on Airworthiness
Certification and Continued
Airworthiness,’’ dated August 12, 2005,
the EASA has kept the FAA informed of
the situation described above. We have
examined the EASA’s findings,
evaluated all pertinent information, and
determined that we need to issue an AD
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Federal Register / Vol. 72, No. 158 / Thursday, August 16, 2007 / Proposed Rules
for airplanes of this type design that are
certificated for operation in the United
States.
Therefore, we are proposing this AD,
which would require revising the
Airworthiness Limitations section (ALS)
of the Instructions for Continued
Airworthiness (ICA) to incorporate new
and revised structural inspections and
inspection intervals. The proposed AD
would also require sending certain
inspection results to Airbus.
Differences Between the Proposed AD
and the EASA Airworthiness Directive
Paragraph 1 of EASA airworthiness
directive 2006–0260 specifies to adhere
to the requirements defined in Issue 4,
5, or 6 of the A310 ALI Document, prior
to the effective date of EASA
airworthiness directive 2006–0260. This
proposed AD, instead, would require
revising the ALS of the ICA by
incorporating Issue 6 of the ALI within
3 months after the effective date.
Although paragraph 2 of EASA
airworthiness directive 2006–0260
mandates only Issue 6 of the ALI, this
proposed AD would require
incorporating both Issue 6 of the ALI
and Airbus TR 6.1 into the FAAapproved maintenance program. Airbus
issued TR 6.1 after issuance of EASA
airworthiness directive 2006–0260. We
have coordinated this difference with
the EASA.
rwilkins on PROD1PC63 with PROPOSALS
Costs of Compliance
This proposed AD would affect about
69 airplanes of U.S. registry. The
proposed actions would take about 2
work hours per airplane, at an average
labor rate of $80 per work hour. Based
on these figures, the estimated cost of
the proposed AD for U.S. operators is
$11,040, or $160 per airplane.
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
VerDate Aug<31>2005
17:19 Aug 15, 2007
Jkt 211001
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD 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, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Airbus: Docket No. FAA–2007–28996;
Directorate Identifier 2006–NM–217–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by September 17, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model
A310 series airplanes, certificated in any
category.
Note 1: This AD requires revisions to
certain operator maintenance documents to
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Fmt 4702
Sfmt 4702
45953
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance according
to paragraph (j) of this AD. The request
should include a description of changes to
the required inspections that will ensure the
continued damage tolerance of the affected
structure. The FAA has provided guidance
for this determination in Advisory Circular
(AC) 25.1529–1.
Unsafe Condition
(d) This AD results from issuance of new
and revised structural inspections and
inspection intervals. We are issuing this AD
to detect and correct fatigue cracking, which
could result in reduced structural integrity 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.
Revision of Airworthiness Limitations
Section (ALS) of the Instructions for
Continued Airworthiness (ICA)
(f) Within 3 months after the effective date
of this AD, do the actions specified in
paragraphs (f)(1) and (f)(2) of this AD.
(1) Revise the ALS of the ICA to
incorporate the structural inspections and
inspection intervals defined in Airbus A310
Airworthiness Limitations Items (ALI)
Document, AI/SE–M2/95A.0263/06, Issue 6,
dated April 2006 (approved by the EASA on
May 31, 2006) (hereafter referred to as ‘‘Issue
6 of the ALI’’). Accomplish the actions
specified in Issue 6 of the ALI at the times
specified in that ALI, except as provided by
paragraph (g) of this AD. Thereafter, except
as provided by paragraphs (f)(2) and (j) of this
AD, no alternative structural inspection
intervals may be approved. The actions
specified in Issue 6 of the ALI must be
accomplished in accordance with Issue 6 of
the ALI.
(2) Revise the ALS of the ICA to
incorporate the new and revised structural
inspections and inspection intervals defined
in Airbus Temporary Revision (TR) 6.1, dated
November 2006 (approved by the EASA on
December 12, 2006), to Issue 6 of the ALI.
Thereafter, except as provided by paragraph
(j) of this AD, no alternative structural
inspection intervals may be approved.
Exception to Issue 6 of the ALI
(g) The tolerance (grace period) for
compliance with Issue 6 of the ALI is within
1,500 flight cycles after the effective date of
this AD provided that none of the following
is exceeded:
(1) Thresholds or intervals in the operator’s
current approved maintenance schedule that
are taken from a previous ALI issue, if
existing, and are higher than or equal to those
given in Issue 6 of the ALI.
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45954
Federal Register / Vol. 72, No. 158 / Thursday, August 16, 2007 / Proposed Rules
(2) 18 months after the effective date of this
AD.
(3) 50 percent of the intervals given in
Issue 6 of the ALI.
(4) Any application tolerance specified in
Section D of Issue 6 of the ALI.
Corrective Actions
(h) Damaged, cracked, or corroded
structure detected during any inspection
done in accordance with Issue 6 of the ALI
must be repaired, before further flight, in
accordance with Issue 6 of the ALI; or in
accordance with other data meeting the
certification basis of the airplane that has
been approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, or the EASA (or
its delegated agent). Where Issue 6 of the ALI
specifies to contact Airbus for appropriate
action: Before further flight, repair the
damaged, cracked, or corroded structure
using a method approved by either the
Manager, International Branch, ANM–116, or
the EASA (or its delegated agent).
Reporting Requirement
(i) If any damage that exceeds the
allowable limits specified in Issue 6 of the
ALI is detected during any inspection
required by this AD: At the applicable time
specified in paragraph (i)(1) or (i)(2) of this
AD, submit a report of the finding to
Sebastien Aveilla, Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; fax +33 (0) 5 61–93–28–72; e-mail
sebastien.aveilla@airbus.com. The report
must include the ALI task reference, airplane
serial number, the number of flight cycles
and flight hours on the airplane,
identification of the affected structure,
location and description of the finding
including its size and orientation, and the
circumstance of detection and inspection
method used. 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 contained in this AD
and has assigned OMB Control Number
2120–0056.
(1) If the inspection was done after the
effective date of this AD: Submit the report
within 30 days after the inspection.
(2) If the inspection was accomplished
prior to the effective date of this AD: Submit
the report within 30 days after the effective
date of this AD.
rwilkins on PROD1PC63 with PROPOSALS
Alternative Methods of Compliance
(AMOCs)
(j)(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) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures 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.
VerDate Aug<31>2005
17:19 Aug 15, 2007
Jkt 211001
Related Information
(k) EASA airworthiness directive 2006–
0260, dated August 25, 2006, also addresses
the subject of this AD.
Issued in Renton, Washington, on August
2, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–16118 Filed 8–15–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28924; Directorate
Identifier 2007–NM–051–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–200C and –200F Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 747–200C and
–200F series airplanes. This proposed
AD would require, among other actions,
installing mounting brackets, support
angles, and moisture curtains in the
main equipment center. This proposed
AD results from reports of water
contamination in the electrical/
electronic units in the main equipment
center. We are proposing this AD to
prevent water contamination of the
electrical/electronic units, which could
cause the electrical/electronic units to
malfunction, and as a consequence,
could adversely affect the airplane’s
continued safe flight.
DATES: We must receive comments on
this proposed AD by October 1, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed 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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Marcia Smith, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6484; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2007–28924; Directorate
Identifier 2007–NM–051–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to 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 proposed 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 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 Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located on the
ground level of the West Building at the
DOT street address stated in the
E:\FR\FM\16AUP1.SGM
16AUP1
]]>Agencies
[Federal Register Volume 72, Number 158 (Thursday, August 16, 2007)]
[Proposed Rules]
[Pages 45952-45954]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-16118]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28996; Directorate Identifier 2006-NM-217-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Airbus Model A310 series airplanes. This proposed AD would
require revising the Airworthiness Limitations section of the
Instructions for Continued Airworthiness to incorporate new and revised
structural inspections and inspection intervals. This proposed AD
results from issuance of new and revised structural inspections and
inspection intervals. We are proposing this AD to detect and correct
fatigue cracking, which could result in reduced structural integrity of
the airplane.
DATES: We must receive comments on this proposed AD by September 17,
2007.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., 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 proposed AD.
FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2007-
28996; Directorate Identifier 2006-NM-217-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to 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 proposed 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 Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The
Docket Operations office (telephone (800) 647-5527) is located on the
ground floor of the West 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.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, notified us that
an unsafe condition may exist on all Airbus Model A310 series
airplanes. The EASA advises that Airbus has issued new and revised
structural inspections and inspection intervals to detect and correct
fatigue cracking. This condition, if not corrected, could result in
reduced structural integrity of the airplane.
Relevant Service Information
Airbus has issued A310 Airworthiness Limitation Items (ALI)
Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006 (approved by
the EASA on May 31, 2006) (hereafter referred to as ``Issue 6 of the
ALI''). That ALI document describes fatigue-related structural
inspections arising from the evaluation of damage tolerance and
widespread fatigue damage.
Airbus has also issued Temporary Revision (TR) 6.1, dated November
2006 (approved by the EASA on December 12, 2006), to Issue 6 of the
ALI. Airbus TR 6.1 provides new and revised inspections to address
certification of the new Model A310-300 weight variant airplanes
(Airbus Modification 13302). The applicability, limit of validity,
program rules, program notes, and definitions stated in Issue 6 of the
ALI remain valid.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The EASA mandated
the service information and issued airworthiness directive 2006-0260,
dated August 25, 2006, to ensure the continued airworthiness of these
airplanes in the European Union.
FAA's Determination and Requirements of the Proposed AD
This airplane model is manufactured in France and is 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. As described in FAA
Order 8100.14A, ``Interim Procedures for Working with the European
Community on Airworthiness Certification and Continued Airworthiness,''
dated August 12, 2005, the EASA has kept the FAA informed of the
situation described above. We have examined the EASA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD
[[Page 45953]]
for airplanes of this type design that are certificated for operation
in the United States.
Therefore, we are proposing this AD, which would require revising
the Airworthiness Limitations section (ALS) of the Instructions for
Continued Airworthiness (ICA) to incorporate new and revised structural
inspections and inspection intervals. The proposed AD would also
require sending certain inspection results to Airbus.
Differences Between the Proposed AD and the EASA Airworthiness
Directive
Paragraph 1 of EASA airworthiness directive 2006-0260 specifies to
adhere to the requirements defined in Issue 4, 5, or 6 of the A310 ALI
Document, prior to the effective date of EASA airworthiness directive
2006-0260. This proposed AD, instead, would require revising the ALS of
the ICA by incorporating Issue 6 of the ALI within 3 months after the
effective date.
Although paragraph 2 of EASA airworthiness directive 2006-0260
mandates only Issue 6 of the ALI, this proposed AD would require
incorporating both Issue 6 of the ALI and Airbus TR 6.1 into the FAA-
approved maintenance program. Airbus issued TR 6.1 after issuance of
EASA airworthiness directive 2006-0260. We have coordinated this
difference with the EASA.
Costs of Compliance
This proposed AD would affect about 69 airplanes of U.S. registry.
The proposed actions would take about 2 work hours per airplane, at an
average labor rate of $80 per work hour. Based on these figures, the
estimated cost of the proposed AD for U.S. operators is $11,040, or
$160 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2007-28996; Directorate Identifier 2006-NM-
217-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by September
17, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model A310 series airplanes,
certificated in any category.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (j) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued damage tolerance of the affected structure. The FAA
has provided guidance for this determination in Advisory Circular
(AC) 25.1529-1.
Unsafe Condition
(d) This AD results from issuance of new and revised structural
inspections and inspection intervals. We are issuing this AD to
detect and correct fatigue cracking, which could result in reduced
structural integrity 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.
Revision of Airworthiness Limitations Section (ALS) of the Instructions
for Continued Airworthiness (ICA)
(f) Within 3 months after the effective date of this AD, do the
actions specified in paragraphs (f)(1) and (f)(2) of this AD.
(1) Revise the ALS of the ICA to incorporate the structural
inspections and inspection intervals defined in Airbus A310
Airworthiness Limitations Items (ALI) Document, AI/SE-M2/95A.0263/
06, Issue 6, dated April 2006 (approved by the EASA on May 31, 2006)
(hereafter referred to as ``Issue 6 of the ALI''). Accomplish the
actions specified in Issue 6 of the ALI at the times specified in
that ALI, except as provided by paragraph (g) of this AD.
Thereafter, except as provided by paragraphs (f)(2) and (j) of this
AD, no alternative structural inspection intervals may be approved.
The actions specified in Issue 6 of the ALI must be accomplished in
accordance with Issue 6 of the ALI.
(2) Revise the ALS of the ICA to incorporate the new and revised
structural inspections and inspection intervals defined in Airbus
Temporary Revision (TR) 6.1, dated November 2006 (approved by the
EASA on December 12, 2006), to Issue 6 of the ALI. Thereafter,
except as provided by paragraph (j) of this AD, no alternative
structural inspection intervals may be approved.
Exception to Issue 6 of the ALI
(g) The tolerance (grace period) for compliance with Issue 6 of
the ALI is within 1,500 flight cycles after the effective date of
this AD provided that none of the following is exceeded:
(1) Thresholds or intervals in the operator's current approved
maintenance schedule that are taken from a previous ALI issue, if
existing, and are higher than or equal to those given in Issue 6 of
the ALI.
[[Page 45954]]
(2) 18 months after the effective date of this AD.
(3) 50 percent of the intervals given in Issue 6 of the ALI.
(4) Any application tolerance specified in Section D of Issue 6
of the ALI.
Corrective Actions
(h) Damaged, cracked, or corroded structure detected during any
inspection done in accordance with Issue 6 of the ALI must be
repaired, before further flight, in accordance with Issue 6 of the
ALI; or in accordance with other data meeting the certification
basis of the airplane that has been approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
or the EASA (or its delegated agent). Where Issue 6 of the ALI
specifies to contact Airbus for appropriate action: Before further
flight, repair the damaged, cracked, or corroded structure using a
method approved by either the Manager, International Branch, ANM-
116, or the EASA (or its delegated agent).
Reporting Requirement
(i) If any damage that exceeds the allowable limits specified in
Issue 6 of the ALI is detected during any inspection required by
this AD: At the applicable time specified in paragraph (i)(1) or
(i)(2) of this AD, submit a report of the finding to Sebastien
Aveilla, Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France; fax +33 (0) 5 61-93-28-72; e-mail
sebastien.aveilla@airbus.com. The report must include the ALI task
reference, airplane serial number, the number of flight cycles and
flight hours on the airplane, identification of the affected
structure, location and description of the finding including its
size and orientation, and the circumstance of detection and
inspection method used. 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
contained in this AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection was done after the effective date of this
AD: Submit the report within 30 days after the inspection.
(2) If the inspection was accomplished prior to the effective
date of this AD: Submit the report within 30 days after the
effective date of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(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) To request a different method of compliance or a different
compliance time for this AD, follow the procedures 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.
Related Information
(k) EASA airworthiness directive 2006-0260, dated August 25,
2006, also addresses the subject of this AD.
Issued in Renton, Washington, on August 2, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-16118 Filed 8-15-07; 8:45 am]
BILLING CODE 4910-13-P
