Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes

[Federal Register Volume 71, Number 172 (Wednesday, September 6, 2006)]
[Rules and Regulations]
[Pages 52421-52423]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-14623]


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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/federal_register/code_of_federal_regulations/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

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