Airworthiness Directives; Airbus Model A300 Series Airplanes, 29449-29451 [E7-10218]
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Federal Register / Vol. 72, No. 102 / Tuesday, May 29, 2007 / Proposed Rules
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.
§ 39.13
[Amended]
rwilkins on PROD1PC63 with PROPOSALS
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
McDonnell Douglas: Docket No. FAA–2007–
28301; Directorate Identifier 2007–NM–
061–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by July 13, 2007.
Affected ADs
(b) None.
VerDate Aug<31>2005
18:04 May 25, 2007
Jkt 211001
Applicability
29449
Issued in Renton, Washington, on May 21,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10215 Filed 5–25–07; 8:45 am]
(c) This AD applies to the following
McDonnell Douglas airplanes, certificated in
any category:
(1) All Model MD–11 and MD–11F
airplanes.
(2) DC–10–10, DC–10–10F, DC–10–15, DC–
10–30 and DC–10–30F (KC–10A and KDC–
10), DC–10–40, DC–10–40F, MD–10–10F,
and MD–10–30F airplanes; as identified in
Boeing Alert Service Bulletin DC10–29A147,
dated February 9, 2007.
BILLING CODE 4910–13–P
Unsafe Condition
14 CFR Part 39
(d) This AD results from a report of damage
to the hydraulic system that occurred when
pieces of a ruptured tire from the left main
landing gear penetrated the wing trailing
edge access panel during takeoff. We are
issuing this AD to prevent damage to the
system 3 hydraulic piping, which could
result in loss of the hydraulic system.
[Docket No. FAA–2007–28300; Directorate
Identifier 2006–NM–292–AD]
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.
Modification
(f) Within 24 months after the effective
date of this AD, reroute system hydraulic
piping, install new pipe assemblies and
unions, and install redesigned support
brackets for system 3 hydraulic piping. Do
these actions in accordance with the
Accomplishment Instructions of McDonnell
Douglas Service Bulletin MD11–29A068,
Revision 1, dated February 9, 2007 (for
Model MD–11 and MD–11F airplanes), or
McDonnell Douglas Service Bulletin DC10–
29A147, dated February 9, 2007 (for Model
DC–10–10, DC–10–10F, DC–10–15, DC–10–
30 and DC–10–30F (KC–10A and KDC–10),
DC–10–40, DC–10–40F, MD–10–10F, and
MD–10–30F airplanes).
(g) Accomplishment before the effective
date of this AD of the modification required
by paragraph (f) of this AD in accordance
with McDonnell Douglas Alert Service
Bulletin MD11–29A068, dated January 23,
2007, is acceptable for compliance with the
requirements of paragraph (f) of this AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), 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.
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
The Chromic Acid Anodising (CAA) Lead
Fleet Program was established in 1989 to
observe corrosion/debonding behaviour of
CAA-treated panels. CAA lead fleet includes
the inspection of lap joints, circumferential
joints, stringers and doublers on selected
aircraft.
The findings in combination with
analytical corrosion investigations have been
analysed by the TC (type certificate) holder
and an appropriate inspection program for
debonding has been developed.
This airworthiness directive requires
inspection of the concerned areas to detect
any corrosion and/or debonding which could
affect the structural integrity. * * *
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by June 28, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
E:\FR\FM\29MYP1.SGM
29MYP1
29450
Federal Register / Vol. 72, No. 102 / Tuesday, May 29, 2007 / Proposed Rules
• 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.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
proposed AD, the regulatory evaluation,
any comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
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:
rwilkins on PROD1PC63 with PROPOSALS
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This proposed AD references the
MCAI and related service information
that we considered in forming the
engineering basis to correct the unsafe
condition. The proposed AD contains
text copied from the MCAI and for this
reason might not follow our plain
language principles.
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–28300; Directorate Identifier
2006–NM–292–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
VerDate Aug<31>2005
18:04 May 25, 2007
Jkt 211001
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2006–0369,
dated December 12, 2006 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
Differences Between This AD and the
MCAI or Service Information
The Chromic Acid Anodising (CAA) Lead
Fleet Program was established in 1989 to
observe corrosion/debonding behaviour of
CAA-treated panels. CAA lead fleet includes
the inspection of lap joints, circumferential
joints, stringers and doublers on selected
aircraft.
The findings in combination with
analytical corrosion investigations have been
analysed by the TC (type certificate) holder
and an appropriate inspection program for
debonding has been developed.
This airworthiness directive requires
inspection of the concerned areas [including
repetitive inspections of certain areas] to
detect any corrosion and/or debonding which
could affect the structural integrity. * * *
If any discrepancies are found, repair
and follow-up actions (additional
inspections for debonding and corrosion
depth) are required. You may obtain
further information by examining the
MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin
A300–53–0378, dated September 4,
2006. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI. The compliance times for
the initial inspections range between
36,800 to 44,600 total flight cycles and
between 18 and 20 years since new. The
grace period for the initial inspections is
2,000 flight cycles or 2 years, whichever
occurs first. The compliance times for
the repairs range from before further
flight to within 2,000 flight cycles after
doing the inspection. The repetitive
inspection intervals range from 500
flight cycles to 3 years.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
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Frm 00005
Fmt 4702
Sfmt 4702
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a NOTE within the
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 12 products of U.S. registry.
We also estimate that it would take 102
work-hours per product to comply with
the basic requirements of this proposed
AD. The average labor rate is $80 per
work-hour. Based on these figures, we
estimate the cost of the proposed AD on
U.S. operators to be $97,920, or $8,160
per product.
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.
E:\FR\FM\29MYP1.SGM
29MYP1
Federal Register / Vol. 72, No. 102 / Tuesday, May 29, 2007 / Proposed Rules
Regulatory Findings
We 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 this 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.
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 FAA amends § 39.13 by adding
the following new AD:
Airbus: Docket No. FAA–2007–28300;
Directorate Identifier 2006–NM–292–AD.
Comments Due Date
(a) We must receive comments by June 28,
2007.
rwilkins on PROD1PC63 with PROPOSALS
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300
series aircraft, certificated in any category,
manufacturing serial numbers (MSN) 0105
through 0107, 0116, 0117, 0121, 0123
through 0126, 0128, 0129, 0133 through
0141, 0146 through 0152, 0154 through 0157,
0160, 0163, 0170, 0173, 0175 through 0177,
and 0180 through 0183.
Subject
(d) Fuselage.
VerDate Aug<31>2005
18:04 May 25, 2007
Jkt 211001
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
The Chromic Acid Anodising (CAA) Lead
Fleet Program was established in 1989 to
observe corrosion/debonding behaviour of
CAA-treated panels. CAA lead fleet includes
the inspection of lap joints, circumferential
joints, stringers and doublers on selected
aircraft.
The findings in combination with
analytical corrosion investigations have been
analysed by the TC (type certificate) holder
and an appropriate inspection program for
debonding has been developed.
This airworthiness directive requires
inspection of the concerned areas [including
repetitive inspections of certain areas] to
detect any corrosion and/or debonding which
could affect the structural integrity. * * *
If any discrepancies are found, repair and
follow-up actions (additional inspections for
debonding and corrosion depth) are required.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Except as provided by paragraphs (f)(2),
(f)(3), and (f)(4) of this AD: Do the initial and
repetitive inspections (including follow-up
actions), as applicable; and do all applicable
repairs; of the areas specified in paragraphs
(f)(1)(i), (f)(1)(ii), (f)(1)(iii), and (f)(1)(iv) of
this AD, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–0378, dated
September 4, 2006, and within the timescales
specified in paragraph 1.E.(2), the
Accomplishment Instructions, and the
figures of the service bulletin.
(i) The bonded doubler in the longitudinal
lap joint area between frame (FR)18 and FR80
(configurations 01 and 02 inspect FR18
through FR40; configuration 03 inspects
FR18 through FR80).
(ii) The bonded wing doublers between
stringer (STGR)22 LH/RH (left-hand/righthand) and STGR43 LH/RH for debonding
(configuration 01 of the service bulletin
only).
(iii) The bonded doublers in the
circumferential joint area between FR26 and
FR80 (configurations 01 and 02 inspect FR26
through FR40; configuration 03 inspects
FR26 through FR80).
(iv) The bonded doublers in the manhole
area between FR23 RH and FR24 RH and
between FR38.1 RH and FR38.2 RH.
(2) Where paragraph 1.E.(2) of Airbus
Service Bulletin A300–53–0378, dated
September 4, 2006, specifies a grace period
´
from CN (Consigne de Navigabilite) issuance,
this AD requires a grace period relative to the
effective date of this AD.
(3) Where paragraph 1.E.(2) of Airbus
Service Bulletin A300–53–0378, dated
September 4, 2006, specifies a threshold, this
AD requires that the inspections be done
within the specified threshold relative to the
first flight of the airplane.
(4) Where the Accomplishment
Instructions and figures of Airbus Service
Bulletin A300–53–0378, dated September 4,
2006, specify that inspections be done yearly,
this AD requires those inspections to be done
at intervals not to exceed 1 year.
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29451
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tom Stafford,
Aerospace Engineer; 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 227–1622; fax (425) 227–1149. 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,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2006–
0369, dated December 12, 2006; and Airbus
Service Bulletin A300–53–0378; dated
September 4, 2006, for related information.
Issued in Renton, Washington, on May 21,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10218 Filed 5–25–07; 8:45 am]
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 72, Number 102 (Tuesday, May 29, 2007)]
[Proposed Rules]
[Pages 29449-29451]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10218]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28300; Directorate Identifier 2006-NM-292-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
The Chromic Acid Anodising (CAA) Lead Fleet Program was
established in 1989 to observe corrosion/debonding behaviour of CAA-
treated panels. CAA lead fleet includes the inspection of lap
joints, circumferential joints, stringers and doublers on selected
aircraft.
The findings in combination with analytical corrosion
investigations have been analysed by the TC (type certificate)
holder and an appropriate inspection program for debonding has been
developed.
This airworthiness directive requires inspection of the
concerned areas to detect any corrosion and/or debonding which could
affect the structural integrity. * * *
The proposed AD would require actions that are intended to address
the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by June 28, 2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
[[Page 29450]]
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.
Federal eRulemaking Portal: https://www.regulations.gov.
Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov; or in person at the Docket Management Facility between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this proposed AD, the regulatory evaluation, any
comments received, and other information. The street address for the
Docket Office (telephone (800) 647-5227) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
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:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. This streamlined process will allow us to adopt
MCAI safety requirements in a more efficient manner and will reduce
safety risks to the public. This process continues to follow all FAA AD
issuance processes to meet legal, economic, Administrative Procedure
Act, and Federal Register requirements. We also continue to meet our
technical decision-making responsibilities to identify and correct
unsafe conditions on U.S.-certificated products.
This proposed AD references the MCAI and related service
information that we considered in forming the engineering basis to
correct the unsafe condition. The proposed AD contains text copied from
the MCAI and for this reason might not follow our plain language
principles.
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
28300; Directorate Identifier 2006-NM-292-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2006-0369, dated December 12, 2006 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
The Chromic Acid Anodising (CAA) Lead Fleet Program was
established in 1989 to observe corrosion/debonding behaviour of CAA-
treated panels. CAA lead fleet includes the inspection of lap
joints, circumferential joints, stringers and doublers on selected
aircraft.
The findings in combination with analytical corrosion
investigations have been analysed by the TC (type certificate)
holder and an appropriate inspection program for debonding has been
developed.
This airworthiness directive requires inspection of the
concerned areas [including repetitive inspections of certain areas]
to detect any corrosion and/or debonding which could affect the
structural integrity. * * *
If any discrepancies are found, repair and follow-up actions
(additional inspections for debonding and corrosion depth) are
required. You may obtain further information by examining the MCAI in
the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin A300-53-0378, dated September 4,
2006. The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI. The compliance
times for the initial inspections range between 36,800 to 44,600 total
flight cycles and between 18 and 20 years since new. The grace period
for the initial inspections is 2,000 flight cycles or 2 years,
whichever occurs first. The compliance times for the repairs range from
before further flight to within 2,000 flight cycles after doing the
inspection. The repetitive inspection intervals range from 500 flight
cycles to 3 years.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 12 products of U.S. registry. We also estimate that
it would take 102 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $97,920, or $8,160 per product.
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.
[[Page 29451]]
Regulatory Findings
We 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 this 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2007-28300; Directorate Identifier 2006-NM-
292-AD.
Comments Due Date
(a) We must receive comments by June 28, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 series aircraft,
certificated in any category, manufacturing serial numbers (MSN)
0105 through 0107, 0116, 0117, 0121, 0123 through 0126, 0128, 0129,
0133 through 0141, 0146 through 0152, 0154 through 0157, 0160, 0163,
0170, 0173, 0175 through 0177, and 0180 through 0183.
Subject
(d) Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
The Chromic Acid Anodising (CAA) Lead Fleet Program was
established in 1989 to observe corrosion/debonding behaviour of CAA-
treated panels. CAA lead fleet includes the inspection of lap
joints, circumferential joints, stringers and doublers on selected
aircraft.
The findings in combination with analytical corrosion
investigations have been analysed by the TC (type certificate)
holder and an appropriate inspection program for debonding has been
developed.
This airworthiness directive requires inspection of the
concerned areas [including repetitive inspections of certain areas]
to detect any corrosion and/or debonding which could affect the
structural integrity. * * *
If any discrepancies are found, repair and follow-up actions
(additional inspections for debonding and corrosion depth) are
required.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Except as provided by paragraphs (f)(2), (f)(3), and (f)(4)
of this AD: Do the initial and repetitive inspections (including
follow-up actions), as applicable; and do all applicable repairs; of
the areas specified in paragraphs (f)(1)(i), (f)(1)(ii),
(f)(1)(iii), and (f)(1)(iv) of this AD, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-53-0378,
dated September 4, 2006, and within the timescales specified in
paragraph 1.E.(2), the Accomplishment Instructions, and the figures
of the service bulletin.
(i) The bonded doubler in the longitudinal lap joint area
between frame (FR)18 and FR80 (configurations 01 and 02 inspect FR18
through FR40; configuration 03 inspects FR18 through FR80).
(ii) The bonded wing doublers between stringer (STGR)22 LH/RH
(left-hand/right-hand) and STGR43 LH/RH for debonding (configuration
01 of the service bulletin only).
(iii) The bonded doublers in the circumferential joint area
between FR26 and FR80 (configurations 01 and 02 inspect FR26 through
FR40; configuration 03 inspects FR26 through FR80).
(iv) The bonded doublers in the manhole area between FR23 RH and
FR24 RH and between FR38.1 RH and FR38.2 RH.
(2) Where paragraph 1.E.(2) of Airbus Service Bulletin A300-53-
0378, dated September 4, 2006, specifies a grace period from CN
(Consigne de Navigabilit[eacute]) issuance, this AD requires a grace
period relative to the effective date of this AD.
(3) Where paragraph 1.E.(2) of Airbus Service Bulletin A300-53-
0378, dated September 4, 2006, specifies a threshold, this AD
requires that the inspections be done within the specified threshold
relative to the first flight of the airplane.
(4) Where the Accomplishment Instructions and figures of Airbus
Service Bulletin A300-53-0378, dated September 4, 2006, specify that
inspections be done yearly, this AD requires those inspections to be
done at intervals not to exceed 1 year.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN: Tom
Stafford, Aerospace Engineer; 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149.
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, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2006-0369, dated December 12, 2006; and Airbus Service
Bulletin A300-53-0378; dated September 4, 2006, for related
information.
Issued in Renton, Washington, on May 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-10218 Filed 5-25-07; 8:45 am]
BILLING CODE 4910-13-P
