[Federal Register Volume 71, Number 58 (Monday, March 27, 2006)]
[Proposed Rules]
[Pages 15065-15068]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-4409]


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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]
RIN 2120-AA64


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

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus Model A318, A319, A320, and A321 airplanes. This 
proposed AD would 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.

[[Page 15066]]

This proposed 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 proposing 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: We must receive comments on this proposed AD by April 26, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     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.
    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: 

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
24199; Directorate Identifier 2006-NM-025-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may examine the 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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on certain Airbus Model A318, A319, A320, 
and A321 airplanes. The DGAC advises that certain stainless steel ribs 
of the engine pylon may not have been heat-treated during manufacture, 
which could result in significantly reduced structural integrity of 
those ribs. This condition, if not corrected, could result in reduced 
structural integrity of the engine pylon, which could lead to 
separation of the engine from the airplane.

Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A320-54A1015, dated 
December 14, 2005. The AOT describes procedures for performing a one-
time inspection (hardness test) to determine the hardness of stainless 
steel ribs 7, 8, and 9 of the left- and right-hand engine pylons; and 
performing corrective actions if necessary. The corrective actions 
include installing reinforcing components on ribs 8 and 9, as 
applicable. Accomplishing the actions specified in the service 
information is intended to adequately address the unsafe condition.
    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 instructions of the AOT.
    The DGAC mandated the service information and issued French 
airworthiness directive F-2006-011 R1, dated January 18, 2006, to 
ensure the continued airworthiness of these airplanes in France.
    French airworthiness directive F-2006-011 R1 also specifies strict 
adherence to reduced speed limitations for flight in severe turbulence, 
as described in Airbus A318/319/320/321 Airplane Flight Manual (AFM) 
4.03.00 P 03.

FAA's Determination and Requirements of This AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require revising 
the Limitations section of the AFM to require strict adherence to 
reduced speed limitations for flight in severe turbulence and 
accomplishing the actions specified in the AOT described previously, 
except as discussed under ``Differences Between French Airworthiness 
Directive, Service Information, and This AD.'' The proposed AD would 
also require sending the inspection results to Airbus.

Differences Between French Airworthiness Directive, Service 
Information, and This AD

    French airworthiness directive F-2006-011 R1 requires, as of the 
effective date of that AD, that flightcrews strictly adhere to the 
requirement for operating at reduced speed in case of flight in severe 
turbulence, as specified in AFM 4.03.00 P03. This AD requires revising 
the Limitations section of the AFM to include this provision. To 
prevent immediate grounding of any airplane, this proposed AD would 
require revising the limitations of the AFM within 10 days after the 
effective date of this proposed AD to include this requirement of 
strict adherence to reduced speeds.
    AOT A320-54A1015 specifies hardness testing of ribs 7, 8, and 9. 
However, the AOT states that rib 7 is able to sustain certification 
loads even

[[Page 15067]]

if not heat-treated and no corrective action is available for rib 7. 
Since rib 7 does not contribute to the unsafe condition, this proposed 
AD would not require testing of rib 7.
    Although the AOT and French airworthiness directive refer to an 
``inspection'' of the spar box ribs, for clarity's sake, this proposed 
AD would refer to a ``hardness test'' as described in related Airbus 
Repair Instruction 546 12081, Issue B.
    Operators should note that, although the AOT and French 
airworthiness directive describe procedures for submitting certain 
findings to the manufacturer, this proposed AD would not require those 
actions.

Costs of Compliance

    This proposed AD would affect about 112 airplanes of U.S. registry. 
The proposed hardness test would 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 proposed 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 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.


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-24199; Directorate Identifier 2006-NM-
025-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by April 26, 
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.

Revise Limitations

    (f) Within 10 days after the effective date of this AD, revise 
the Limitations section of 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, or before further flight after a 
hard or overweight landing, whichever occurs first: 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:  Airbus AOT A320-54A1015, dated December 14, 2005, 
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) 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 any discrepant rib found 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 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 service bulletin 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

[[Page 15068]]

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 airworthiness directive F-2006-011 R1, dated January 
18, 2006, also addresses the subject of this AD.

    Issued in Renton, Washington, on March 13, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-4409 Filed 3-24-06; 8:45 am]
BILLING CODE 4910-13-P