[Federal Register: December 10, 2007 (Volume 72, Number 236)]
[Rules and Regulations]
[Page 69598-69600]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10de07-13]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29117; Directorate Identifier 2007-NM-114-AD;
Amendment 39-15291; AD 2007-25-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This 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:
As a result of a Wide Spread Fatigue Damage (WFD) calculation on
A310 aircraft it was found that a modification of the upper fuselage
circumferential joint at FR (frame) 55/58 is necessary to enable the
aircraft to reach the Extended Service Goal (ESG).
The unsafe condition is failure of the circumferential joint of the
upper fuselage, which could result in reduced structural integrity of
the airplane. We are issuing this AD to require actions to correct the
unsafe condition on these products.
DATES: This AD becomes effective January 14, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 14,
2008.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov
or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on September 7, 2007
(72 FR 51386). That NPRM proposed to correct an unsafe condition for
the specified products. The MCAI states:
As a result of a Wide Spread Fatigue Damage (WFD) calculation on
A310 aircraft it was found that a modification of the upper fuselage
circumferential joint at FR (frame) 55/58 is necessary to enable the
aircraft to reach the Extended Service Goal (ESG).
As a consequence, this Airworthiness Directive (AD) requires the
reinforcement of the affected fuselage frame butt joint.
The unsafe condition is failure of the circumferential joint of the
upper fuselage, which could result in reduced structural integrity of
the airplane. You may obtain further information by examining the MCAI
in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
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 required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 67 products of U.S.
registry. We also estimate that it will take about 330 work-hours per
product to comply with the basic requirements of this AD. The average
labor rate is $80 per work-hour. Required parts will cost about $3,016
per product. Where the service information lists required parts costs
that are covered under warranty, we have assumed that there will be no
charge for these parts. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, we estimate the cost of this AD to the
U.S. operators to be $1,970,872, or $29,416 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.
Regulatory Findings
We 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 this AD:
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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov
; or in person at the
[[Page 69599]]
Docket Operations office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains the NPRM, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone (800)
647-5527) is in the ADDRESSES section. Comments will be available in
the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2007-25-09 Airbus: Amendment 39-15291. Docket No. FAA-2007-29117;
Directorate Identifier 2007-NM-114-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
14, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A310 series airplanes,
certificated in any category; all certified models; all serial
numbers; except airplanes that have received in-service application
of Airbus Service Bulletin A310-53-2125.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
As a result of a Wide Spread Fatigue Damage (WFD) calculation on
A310 aircraft it was found that a modification of the upper fuselage
circumferential joint at FR (frame) 55/58 is necessary to enable the
aircraft to reach the Extended Service Goal (ESG).
As a consequence, this Airworthiness Directive (AD) requires the
reinforcement of the affected fuselage frame butt joint.
The unsafe condition is failure of the circumferential joint of
the upper fuselage, which could result in reduced structural
integrity of the airplane.
Actions and Compliance
(f) Unless already done, do the following actions: Reinforce the
fuselage butt joint at FR 55/58 in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-53-2125,
including Appendix 01, dated January 9, 2007, at the applicable
compliance times listed in Table 1 (threshold) or Table 2 (grace
period) of this AD, whichever occurs later.
Table 1.--Compliance Thresholds
------------------------------------------------------------------------
Whichever occurs first after
the effective date of this AD
-------------------------------
Accumulated Accumulated
Airbus model time since time since
first flight first flight
(in flight (in flight
cycles) hours)
------------------------------------------------------------------------
A310-200 airplanes...................... 41,500 83,500
A310-300 airplanes with an average 33,000 93,500
flight time (AFT) < = to 4 hours........
A310-300 airplanes with an AFT > 4 hours 20,500 102,000
------------------------------------------------------------------------
Table 2.--Grace Periods
------------------------------------------------------------------------
Whichever occurs first after
the effective date of this AD
Airbus model -------------------------------
Flight cycles Flight hours
------------------------------------------------------------------------
A310-200 airplanes...................... 1,500 3,000
A310-300 airplanes with an AFT < = 4 1,200 3,400
hours..................................
A310-300 airplanes with an AFT > 4 hours 740 3,600
------------------------------------------------------------------------
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, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 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 2007-0111, dated April 25, 2007; and Airbus Service
Bulletin A310-53-2125, including Appendix 01, dated January 9, 2007;
for related information.
Material Incorporated by Reference
(i) You must use Airbus Service Bulletin A310-53-2125, including
Appendix 01, dated January 9, 2007, to do the actions required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of
[[Page 69600]]
this service information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
(3) You may review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call (202) 741-6030,
or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html
.
Issued in Renton, Washington, on November 23, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-23457 Filed 12-7-07; 8:45 am]
BILLING CODE 4910-13-P