[Federal Register: September 6, 2006 (Volume 71, Number 172)]
[Rules and Regulations]
[Page 52421-52423]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06se06-9]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24199; Directorate Identifier 2006-NM-025-AD;
Amendment 39-14744; AD 2006-18-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318, A319, A320, and A321
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Model A318, A319, A320, and A321 airplanes. This AD
requires revising the Limitations section of the airplane flight manual
(AFM); performing a one-time hardness test of certain ribs of the left-
and right-hand engine pylons, as applicable, which would terminate the
AFM limitations; and performing related corrective actions if
necessary. This AD results from a report that certain stainless steel
ribs installed in the engine pylon may not have been heat-treated
during manufacture, which could result in significantly reduced
structural integrity of the pylon. We are issuing this AD to detect and
correct reduced structural integrity of the engine pylon, which could
lead to separation of the engine from the airplane.
DATES: This AD becomes effective October 11, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of October 11,
2006.
ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov
or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at http://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Airbus Model
A318, A319, A320, and A321 airplanes. That NPRM was published in the
Federal
[[Page 52422]]
Register on March 27, 2006 (71 FR 15065). That NPRM proposed to require
revising the Limitations section of the airplane flight manual (AFM);
performing a one-time hardness test of certain ribs of the left- and
right-hand engine pylons, as applicable, which would terminate the AFM
limitations; and performing related corrective actions if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received.
Request To Revise Hardness Test Requirement
The Air Transport Association (ATA), on behalf of its member,
Northwest Airlines (NWA), requests that we review the requirement for
the hardness test specified in the NPRM. NWA states that the NPRM
proposes a hardness test before further flight in the case of a hard or
overweight landing and further states that French airworthiness
directive F-2006-011 R1, dated January 18, 2006, which also addresses
the subject of this AD, did not have such a requirement. NWA asserts
that a requirement to visually inspect the airplane and pylons for
deformation after a hard landing already exists. NWA believes that, as
a hardness test requires special tooling and expertise that would not
likely be available at most locations where a hard landing might occur,
the hardness test is not appropriate and a visual inspection in
accordance with maintenance procedures should be accomplished instead.
We agree with NWA that a hardness test after a hard or overweight
landing is not necessary. Therefore, we have revised paragraph (g) of
the AD to remove the requirement for a hardness test after a hard or
overweight landing.
Clarification of Corrective Actions
To prevent possible confusion, we have revised paragraph (h) of the
AD to clarify that the specified corrective actions apply to discrepant
ribs discovered during the hardness test required by paragraph (g) of
the AD.
Supersedure of French Airworthiness Directive
The European Aviation Safety Agency (EASA) has issued airworthiness
directive 2006-0136, dated May 22, 2006. The EASA airworthiness
directive supersedes French airworthiness directive F-2006-011 R1,
dated January 18, 2006, which was referenced in the NPRM as the
applicable parallel airworthiness directive. The EASA airworthiness
directive contains no new or revised material that affects the
technical content of this AD; however, we have revised paragraph (k) of
this AD for clarity and traceability of information that applies to
this AD.
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 112 airplanes of U.S. registry. The
required hardness test will take about 1 work hour per airplane, at an
average labor rate of $65 per work hour. Based on these figures, the
estimated cost of the AD for U.S. operators is $7,280, or $65 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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2006-18-06 Airbus: Amendment 39-14744. Docket No. FAA-2006-24199;
Directorate Identifier 2006-NM-025-AD.
Effective Date
(a) This AD becomes effective October 11, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318, A319, A320, and A321
airplanes, certificated in any category; having a manufacturer
serial number as identified in Airbus All Operators Telex (AOT)
A320-54A1015, dated December 14, 2005 (referred to after this
paragraph as ``the AOT'').
Unsafe Condition
(d) This AD results from a report that certain stainless steel
ribs installed in the engine pylon may not have been heat-treated
during manufacture, which could result in significantly reduced
structural integrity of the pylon. We are issuing this AD to detect
and correct reduced structural integrity of the engine pylon, which
could lead to separation of the engine from 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.
[[Page 52423]]
Revise Limitations
(f) Within 10 days after the effective date of this AD, revise
the Limitations section of the Airbus A318/319/320/321 Airplane
Flight Manual (AFM) to include the following statement. This may be
done by inserting a copy of this AD into the AFM.
``In case of flight in severe turbulence, strictly adhere to
reduced speeds as defined in Aircraft Flight Manual 4.03.00 P 03.''
Note 1: When a statement identical to that specified in
paragraph (f) of this AD has been included in the general revisions
of the AFM, and the general revisions have been inserted into the
AFM, the copy of this AD may be removed from the Limitations section
of the AFM unless it has already been removed as specified in
paragraph (g) or (h) of this AD.
Hardness Test
(g) Within the compliance time specified in paragraph (g)(1) or
(g)(2) of this AD, as applicable: Perform a one-time hardness test
to determine the hardness of ribs 8 and 9 of the left- and right-
hand engine pylons, in accordance with the instructions of the AOT.
If no discrepant rib is found installed on the airplane, the
statement specified in paragraph (f) of this AD may be removed from
the Limitations section of the AFM.
(1) For airplanes equipped with CFM engines: Within 6 months
after the effective date of this AD.
(2) For airplanes equipped with IAE engines: Within 9 months
after the effective date of this AD.
Note 2: The AOT refers to Airbus Repair Instruction 546 12081,
Issue B, dated January 3, 2006, as an additional source of service
information for accomplishing the actions specified by the AOT.
Corrective Actions
(h) For any discrepant rib found during the hardness test
specified by paragraph (g) of this AD: Within the compliance time
specified in paragraph (h)(1) or (h)(2) of this AD, as applicable,
perform applicable corrective actions in accordance with the
instructions of the AOT. When corrective actions have been applied
to all discrepant ribs found on the airplane, the statement
specified in paragraph (f) of this AD may be removed from the
Limitations section of the AFM for that airplane.
(1) For airplanes equipped with CFM engines: Within 14 days
after accomplishing the hardness test required by paragraph (g) of
this AD.
(2) For airplanes equipped with IAE engines: Within 28 days
after accomplishing the hardness test required by paragraph (g) of
this AD.
No Reporting Requirement
(i) Although the AOT referenced in this AD specifies to submit
certain information to the manufacturer, this AD does not include
that requirement.
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) Before using any AMOC approved in accordance with Sec.
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) European Aviation Safety Agency airworthiness directive
2006-0136, dated May 22, 2006, also addresses the subject of this
AD.
Material Incorporated by Reference
(l) You must use Airbus All Operators Telex A320-54A1015, dated
December 14, 2005, 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 http://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 http://www.archives.gov/
[fxsp0]federal--register/[fxsp0]code--of--federal--
regulations/[fxsp0]ibr--locations.html.
Issued in Renton, Washington, on August 23, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-14623 Filed 9-5-06; 8:45 am]
BILLING CODE 4910-13-P