[Federal Register Volume 70, Number 207 (Thursday, October 27, 2005)]
[Proposed Rules]
[Pages 61922-61924]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-21434]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22794; Directorate Identifier 2005-NM-097-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318-100 and A319-100 
Series Airplanes; Model A320-111 Airplanes; and Model A320-200, A321-
100, and A321-200 Series 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 all Airbus Model A318-100 and A319-100 series airplanes; Model 
A320-111 airplanes; and Model A320-200, A321-100, and A321-200 series 
airplanes. This proposed AD would require repetitive detailed 
inspections of the trimmable horizontal stabilizer actuator (THSA) 
attachments for proper clearances, and any crack, damage, or metallic 
particles; related corrective actions if necessary; and a report of the 
inspection results to the manufacturer. This proposed AD results from a 
report that during lab testing to verify the performance of the THSA's 
secondary load path with a simulated failure of the THSA's primary load 
path, the secondary load path's nut did not jam (as it was supposed to 
do.) We are proposing this AD to ensure the integrity of the THSA's 
primary load path, which if failed, could result in latent (undetected) 
loading and eventual failure of the THSA's secondary load path and 
consequent uncontrolled movement of the horizontal stabilizer and loss 
of control of the airplane.

DATES: We must receive comments on this proposed AD by November 28, 
2005.

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 proposed AD.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

[[Page 61923]]

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Include the docket number ``FAA-
2005-22794; Directorate Identifier 2005-NM-097-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 all Airbus Model A318-100, A319-100, 
A320, and A321 series airplanes. The DGAC advises that, during lab 
testing to verify the performance of the secondary load path of the 
trimmable horizontal stabilizer actuator (THSA) with a simulated loss 
of the THSA's primary load path, the secondary load path's nut did not 
jam the THSA (as it was supposed to do). The THSA was designed to jam 
in the event of a primary load path failure, to indicate to the 
flightcrew that a component of the THSA (the primary load path) had 
failed and would need repair. Without the jamming of the secondary load 
path's nut, there would be no indications of failure of the THSA 
primary load path, and it is possible that the airplane would continue 
to be unknowingly operated with a failed component and continuous 
loading of the secondary load path. The secondary load path is not 
designed to tolerate continued loading during multiple flights. In the 
event of a secondary load path failure in addition to a primary load 
path failure, the flightcrew would not be able to control the position 
of the THSA. This condition, if not corrected, could result in 
uncontrolled movement of the horizontal stabilizer and consequent loss 
of control of the airplane.

Relevant Service Information

    Airbus has issued Service Bulletin A320-27-1164, Revision 02, dated 
March 30, 2005. The service bulletin describes procedures for 
repetitive detailed inspections of the THSA attachments for proper 
clearances, and for any crack, damage, or metallic particles; related 
corrective actions if necessary; and a report of the inspection results 
to the manufacturer. The detailed inspections involve doing a check for 
the clearances between the secondary nut trunnions and junction plates 
at the lower THSA attachment; and doing a visual inspection of the 
upper THSA attachment structure/area for any crack, damage, or metallic 
particles. The corrective actions involve replacing the THSA if any 
clearance is not correct, or if any crack or damage is found; and 
contacting the manufacturer for further instructions if any metallic 
particles are found. The DGAC mandated the service information and 
issued French airworthiness directive F-2005-051, dated March 30, 2005, 
to ensure the continued airworthiness of these airplanes in France.

FAA's Determination and Requirements of the Proposed 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 airplanes of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Differences Between 
the Proposed AD and the Service Bulletin.''

Differences Between the Proposed AD and the Service Bulletin

    The service bulletin specifies that you may contact the 
manufacturer for instructions if any metallic particles are found, but 
this proposed AD would require you to repair the THSA using a method 
that we or the DGAC (or its delegated agent) approve. In light of the 
type of repair that would be required to address the unsafe condition, 
and consistent with existing bilateral airworthiness agreements, we 
have determined that, for this proposed AD, a repair we or the DGAC 
approve would be acceptable for compliance with this proposed AD.
    The service bulletin refers only to a ``check'' and a ``visual 
inspection'' for inspections of the THSA attachments for proper 
clearances; and for any crack, damage, or metal particles. We have 
determined that the procedures for both actions in the service bulletin 
should be described as ``detailed inspections.'' Note 1 has been 
included in this proposed AD to define this type of inspection.

Interim Action

    This is considered to be interim action. The inspection reports 
that are required by this AD will enable the manufacturer to obtain 
better insight into the nature, cause, and extent of the problem, and 
eventually to develop final action to address the unsafe condition. 
Once final action has been identified, the FAA may consider further 
rulemaking.

Costs of Compliance

    This proposed AD would affect about 700 airplanes of U.S. registry. 
The proposed actions 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 $45,500, or $65 
per airplane, per inspection cycle.

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.

[[Page 61924]]

    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-2005-22794; Directorate Identifier 2005-NM-
097-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by November 
28, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A318-111 and -112 
airplanes, Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes, Model A320-111 airplanes, Model A320-211, -212, -214, 
-231, -232, and -233 airplanes, Model A321-111, -112, and -131 
airplanes, and Model A321-211 and -231 airplanes, certificated in 
any category.

Unsafe Condition

    (d) This AD results from a report that during lab testing to 
verify the performance of the trimmable horizontal stabilizer 
actuator's (THSA's) secondary load path with a simulated failure of 
the THSA's primary load path, the secondary load path's nut did not 
jam (as it was supposed to do.) We are issuing this AD to ensure the 
integrity of the THSA's primary load path, which if failed, could 
result in latent (undetected) loading and eventual failure of the 
THSA's secondary load path and consequent uncontrolled movement of 
the horizontal stabilizer and loss of control of 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.

Repetitive Inspections and Corrective Action

    (f) Within 20 months since first flight, or within 600 flight 
hours after the effective date of this AD, whichever occurs later, 
do detailed inspections of the THSA attachments for proper 
clearances and any crack, damage, or metallic particles, and do 
related corrective actions as applicable, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-27-1164, 
Revision 02, dated March 30, 2005, except as described in paragraph 
(g) of this AD. Do corrective actions before further flight. 
Thereafter, repeat the inspections at intervals not to exceed 20 
months.

    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.''

    (g) If any metallic particles are detected during the inspection 
required by paragraph (f) of this AD: Before further flight, repair 
the damage according to a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Direction Generale de l'Aviation Civile (DGAC) (or its 
delegated agent).

Inspection Reports

    (h) Submit a report of the findings (both positive and negative) 
of the inspection required by paragraph (f) of this AD to Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, at the 
applicable time specified in paragraph (h)(1) or (h)(2) of this AD. 
The report must include the inspection results, a description of any 
discrepancies found, the airplane serial number, and the number of 
landings and flight hours on the airplane. Under the provisions of 
the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the 
Office of Management and Budget (OMB) has approved the information 
collection requirements contained in this AD and has assigned OMB 
Control Number 2120-0056.
    (1) If the inspection was done after the effective date of this 
AD: Submit the report within 30 days after the inspection.
    (2) If any inspection was accomplished prior to the effective 
date of this AD: Submit the report within 30 days after the 
effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(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

    (j) French airworthiness directive F-2005-051, dated March 30, 
2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on October 18, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-21434 Filed 10-26-05; 8:45 am]
BILLING CODE 4910-13-P