AD 2006-07-05

[Federal Register Volume 71, Number 61 (Thursday, March 30, 2006)]
[Rules and Regulations]
[Pages 16025-16027]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 06-2961]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23142; Directorate Identifier 2005-NM-154-AD; 
Amendment 39-14532; AD 2006-07-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319-131, -132, and -133; 
A320-232 and -233; and A321-131, -231, and -232 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A319-131, -132, and -133; A320-232 and -233; and 
A321-131, -231, and -232 airplanes. This AD requires inspecting for 
cracks or failure of the primary load path components of the engine 
forward mount, and corrective action if necessary. This AD also 
requires removing, re-installing, and re-torquing the attachment bolts 
for the secondary load path. This AD results from a report that, during 
modification of certain engine forward mount assemblies of the left and 
right engines done at an engine shop visit, an incorrect torque was 
applied to the attachment bolts. We are issuing this AD to prevent 
structural failure of the secondary load path of the forward engine 
mount, which, if combined with failure of the primary load path, could 
result in separation of the engine from the airplane.

DATES: This AD becomes effective May 4, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 4, 2006.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a> 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 98055-4056; 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 <a href="http://dms.dot.gov">http://dms.dot.gov</a> 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

[[Page 16026]]

part 39 to include an AD that would apply to certain Airbus Model A319-
131, -132, and -133; A320-232 and -233; and A321-131 and -231 
airplanes. That NPRM was published in the Federal Register on December 
1, 2005 (70 FR 72088). That NPRM proposed to require inspecting for 
cracks or failure of the primary load path components of the engine 
forward mount, and corrective action if necessary. That NPRM also 
proposed to require removing, re-installing, and re-torquing the 
attachment bolts for the secondary load path.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received from 
one commenter.

Clarification of Applicability

    The commenter states that Airbus Model A321-232 airplanes are not 
identified in the applicability of the AD. The commenter notes that 
there have been nine of these airplanes delivered that are not U.S.-
registered.
    We infer that the commenter wants us to include Airbus Model A321-
232 airplanes in the applicability of the AD. We agree with the 
commenter. The proposed AD is applicable to Airbus Model A319-131, -
132, and -133; A320-232 and -233; and A321-131 and -231 airplanes. 
Model A321-232 airplanes have been approved, but are not yet identified 
in the type certificate data sheet (TCDS). Considering this approval, 
we have changed the applicability throughout the AD accordingly. 
Additionally, no Model A321-232 airplane is currently on the U.S. 
Register so no additional work is required for U.S. operators.

Clarification of Applicability in Paragraph (f) of the NPRM

    We note that paragraph (f) of the NPRM contains an error in 
referencing the airplane models on which the detailed inspection must 
be done. Our intent was to specify all of the airplane models 
identified in Airbus All Operators Telex A320-71A1036, Revision 1, 
dated June 28, 2005, as referenced in the applicability section; 
however, we inadvertently excluded Model A320-232 and -233 airplanes in 
paragraph (f). We have verified that the inspection has been 
accomplished on all affected models. Therefore, no additional work is 
required for U.S. operators. Adding these models to paragraph (f) will 
ensure that any affected airplane that is imported into the U.S. after 
the effective date of this AD is inspected, as required by this AD. We 
have added a new paragraph (f)(3) to the AD to include these models.

Conclusion

    We have carefully reviewed the available data, including the 
comment that has been received, and determined that air safety and the 
public interest require adopting the AD with the changes described 
previously. These changes will neither increase the economic burden on 
any operator nor increase the scope of the AD.

Costs of Compliance

    This AD affects about 131 airplanes of U.S. registry.
    The inspection takes about 2 work hours per airplane (1 work hour 
per engine), at an average labor rate of $65 per work hour. Based on 
these figures, the estimated cost of the inspection for U.S. operators 
is $17,030, or $130 per airplane.
    The removal, re-installation, and re-torquing takes about 8 work 
hours per airplane (4 work hours per engine), at an average labor rate 
of $65 per work hour. Based on these figures, the estimated cost of the 
adjustments for U.S. operators is $68,120, or $520 per airplane.
    If any Model A321-232 airplane is imported and placed on the U.S. 
Register in the future, it will take about 2 work hours per airplane 
for the inspection and 8 work hours per airplane for the removal, re-
installation, and re-torquing, at an average labor rate of $65 per work 
hour. Based on these figures, the estimated cost of the AD will be $750 
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):

2006-07-05 Airbus: Amendment 39-14532. Docket No. FAA-2005-23142; 
Directorate Identifier 2005-NM-154-AD.

Effective Date

    (a) This AD becomes effective May 4, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A319-131, -132, and -133 
airplanes; Model A320-232 and -233 airplanes; and Model A321-131, -
231, and -232 airplanes; certificated in any category; as identified 
in Airbus All Operators Telex (AOT) A320-71A1036, Revision 1, dated 
June 28, 2005.

[[Page 16027]]

Unsafe Condition

    (d) This AD results from a report that, during modification of 
certain engine forward mount assemblies of the left and right 
engines done at an engine shop visit, an incorrect torque was 
applied to the attachment bolts. We are issuing this AD to prevent 
structural failure of the secondary load path of the forward engine 
mount, which, if combined with failure of the primary load path, 
could result in 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.


    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Inspection and Corrective Action

    (f) Perform a detailed inspection for cracks or failure of the 
primary load path components of the engine forward mount by doing 
all the applicable actions in accordance with the procedures in 
Airbus AOT A320-71A1036, Revision 1, dated June 28, 2005. Perform 
the actions at the time specified in paragraph (f)(1), (f)(2), or 
(f)(3) of this AD, as applicable. Do any corrective action before 
further flight in accordance with the procedures in the AOT.
    (1) For Model A321-131, -231, and -232 airplanes: Do the 
inspection within 5 days after the effective date of this AD.
    (2) For Model A319-131, -132, and -133 airplanes: Do the 
inspection within 10 days after the effective date of this AD.
    (3) For Model A320-232 and -233 airplanes: Do the inspection 
within 10 days after the effective date of this AD.
    (g) For all airplanes: At the applicable time specified in 
paragraph (g)(1) or (g)(2) of this AD, remove, re-install, and re-
torque each of the attachment bolts of the engine forward mount 
assembly in accordance with the procedures in Airbus AOT A320-
71A1036, Revision 1, dated June 28, 2005.
    (1) If the inspection specified in paragraph (f) of this AD was 
accomplished after the effective date of this AD: Do the actions 
within 2,250 flight cycles after accomplishing the inspection.
    (2) If the inspection specified in paragraph (f) of this AD was 
accomplished before the effective date of this AD: Do the actions 
within 2,250 flight cycles after the effective date of this AD.

Actions Accomplished Previously

    (h) Inspections, adjustments or repairs done before the 
effective date of this AD in accordance with the procedures in 
Airbus AOT A320-71A1036, dated June 27, 2005, are acceptable for 
compliance with the corresponding actions required by this AD.

No Reporting Required

    (i) Although Airbus AOT A320-71A1036, Revision 1, dated June 28, 
2005, recommends that inspection results be reported 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) French emergency airworthiness directive UF-2005-117, dated 
June 29, 2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must use Airbus All Operators Telex A320-71A1036, 
Revision 1, dated June 28, 2005, to perform the actions that are 
required by this AD, unless the AD specifies otherwise. (Only page 1 
of the all operators telex contains the document number, revision 
number, and date of the document; no other page of the document 
contains this information.) 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 <a href="http://dms.dot.gov">http://dms.dot.gov</a>; 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 <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

    Issued in Renton, Washington, on March 17, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-2961 Filed 3-29-06; 8:45 am]
BILLING CODE 4910-13-P