[Federal Register Volume 70, Number 230 (Thursday, December 1, 2005)]
[Proposed Rules]
[Pages 72085-72088]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-23514]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23143; Directorate Identifier 2005-NM-177-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318-100 Series Airplanes, 
Model A319-100 Series Airplanes, Model A320-111 Airplanes, Model A320-
200 Series Airplanes, and Model A321-100 Series Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model A319, A320, and 
A321 series airplanes. The existing AD currently requires repetitive 
inspections to detect wear of the inboard flap trunnions, and to detect 
wear or de-bonding of the protective half-shells; corrective actions, 
if necessary; and terminating action. This proposed AD would remove the 
repetitive inspections to detect wear of the inboard flap trunnions and 
to detect wear or de-bonding of the protective half-shells; and 
corrective actions if necessary. This proposed AD would add repetitive 
detailed inspections of the inboard flap trunnions for any wear marks 
and of the sliding panels for any cracking at the long edges, and 
corrective actions if necessary. This proposed AD would also add 
airplanes to the applicability. This proposed AD results from reports 
of wear damage to the inboard flap trunnions after incorporation of the 
terminating modification. We are proposing this AD to detect and 
correct wear of the inboard flap trunnions, which could lead to loss of 
flap surface control and consequently result in the flap detaching from 
the airplane. A detached flap could result in damage to the tail of the 
airplane.

DATES: We must receive comments on this proposed AD by January 3, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov

[[Page 72086]]

and follow the instructions for sending your comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; 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 ``Docket No. 
FAA-2005-23143; Directorate Identifier 2005-NM-177-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

    On November 20, 2000, we issued AD 2000-24-02, amendment 39-12009 
(65 FR 75603, December 4, 2000), for certain Airbus Model A319, A320, 
and A321 series airplanes. That AD requires repetitive inspections to 
detect wear of the inboard flap trunnions, and to detect wear or de-
bonding of the protective half-shells; corrective actions, if 
necessary; and terminating action. That AD resulted from issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. We issued that AD to prevent chafing and 
resultant wear damage on the inboard flap drive trunnions or on the 
protective half-shells, which could result in failure of the trunnion 
primary load path; this would adversely affect the fatigue life of the 
secondary load path and could lead to loss of the flap.

Actions Since Existing AD Was Issued

    Since we issued AD 2000-24-02, the Direction Generale de l'Aviation 
Civile (DGAC), which is the airworthiness authority for France, has 
notified us that operators have reported finding wear damage to the 
inboard flap trunnions after incorporating the terminating modification 
of AD 2000-24-02. Wear is caused when the sliding panel hook moves out 
of the protected area of the trunnion during flap operation. Wear of 
the inboard flap trunnion associated with a drive failure at track 2 or 
associated with a hard jam at track 1 could lead to loss of flap 
surface control. A free moveable flap could result in the flap 
detaching from the airplane. A detached flap could result in damage to 
the tail of the airplane.

Relevant Service Information

    Airbus has issued Service Bulletin A320-57-1133, dated July 28, 
2005. The service bulletin describes procedures for doing repetitive 
detailed inspections of the inboard flap trunnions for any wear marks 
and of the sliding panels for any cracking at the long edges, doing any 
corrective actions if necessary, and reporting inspection results to 
the manufacturer. The corrective actions include the following:
    <bullet> If the sliding panel is damaged, replacing the sliding 
panel with a new sliding panel at the next opportunity.
    <bullet> If the trunnion is damaged, reworking the trunnion to a 
smooth contour and measuring the maximum depth of rework.
    <bullet> If the maximum allowed damage limit of the trunnion has 
been exceeded, replacing the trunnion or flap before further flight.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the service information and issued French airworthiness directive F-
2005-139, dated August 3, 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 AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 2000-24-02 and would only 
continue to require accomplishing the modification (the terminating 
action of AD 2000-24-02). This proposed AD would also require 
repetitive detailed inspections of the inboard flap trunnions for any 
wear marks and of the sliding panels for any cracking at the long 
edges, and corrective actions if necessary.

Clarification of Applicability

    French airworthiness directive F-2005-139 is applicable to Airbus 
Model A318, A319, A320, and A321 airplanes, all serial numbers that 
have received Airbus modification 26495 in production or Airbus Service 
Bulletin A320-27-1117 in service. In this NPRM, however, we have 
excluded reference to Model A318-100 series airplanes that have 
accomplished Airbus Service Bulletin A320-27-1117 in service from the 
applicability, since that service bulletin does not apply to those 
airplanes. Also, this NPRM applies to all Model A319-100 series 
airplanes, Model A320-111 airplanes, Model A320-200 series airplanes, 
and Model A321-100 series airplanes. For all of these airplanes, either 
Airbus modification 26495 was accomplished in production or Airbus 
Service Bulletin A320-27-1117 was accomplished in

[[Page 72087]]

service (as required by AD 2000-24-02 or French airworthiness directive 
1996-271-092(B) R3, dated August 11, 1999). Therefore, for Model A319-
100 series airplanes, Model A320-111 airplanes, Model A320-200 series 
airplanes, and Model A321-100 series airplanes, it is not necessary to 
reference Airbus modification 26495 or Airbus Service Bulletin A320-27-
1117 in the applicability of the NPRM.

Clarification of Compliance Times for Corrective Actions

    Where Airbus Service Bulletin A320-57-1133 specifies replacing the 
sliding panel at the next opportunity, this proposed AD would require 
replacing it within 600 flight hours after the proposed inspection.
    If the trunnion is found damaged during any inspection, the service 
bulletin does not specify a compliance time for reworking the trunnion 
and measuring the maximum rework depth. This proposed AD would require 
those corrective actions before further flight after the proposed 
inspection.
    Where the service bulletin specifies contacting the manufacturer 
for a grace period assessment after replacing the trunnion or flap, 
this proposed AD would instead require contacting the FAA or DGAC for 
the grace period assessment.

Clarification of Inspection Terminology

    ``Visually examine'' as specified in Airbus Service Bulletin A320-
57-1133 is referred to as a ``detailed inspection'' in this proposed 
AD. We have included the definition for a detailed inspection in a note 
in the proposed AD.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Change to Existing AD

    This proposed AD would retain certain requirements of AD 2000-24-
02. Since AD 2000-24-02 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. Also, the requirements in 
paragraphs (a) through (e) of AD 2000-24-02 have not been retained in 
this proposed AD. As a result, the requirement in paragraph (f) of AD 
2000-24-02 corresponds to the requirement of paragraph (f) in this 
proposed AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                           Number of
                                                   Average                                                   U.S.-
              Action                 Work hours   labor rate          Parts          Cost per  airplane    registered              Fleet cost
                                                   per hour                                                airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Terminating modification (required           14          $65  Provided by           $910................          719  $654,290.
 by AD 2000-24-02).                                            manufacturer.
Detailed inspection (new proposed             2           65  None................  $130, per inspection          719  $93,470, per inspection cycle.
 action).                                                                            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.
    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 
removing amendment 39-12009 (65 FR 75603, December 4, 2000) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2005-23143; Directorate Identifier 2005-NM-
177-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by January 
3, 2006.

Affected ADs

    (b) This AD supersedes AD 2000-24-02.

Applicability

    (c) This AD applies to the airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A318-111 and -112 airplanes on which Airbus 
Modification 26495 has been incorporated in production.
    (2) All Airbus Model A319-111, -112, -113, -114, -115, -131, -
132, and -133 airplanes; Model A320-111 airplanes; Model

[[Page 72088]]

A320-211, -212, -214, -231, -232, and -233 airplanes; and Model 
A321-111, -112, and -131 airplanes.

Unsafe Condition

    (d) This AD results from reports of wear damage to the inboard 
flap trunnions after incorporation of the terminating modification. 
We are issuing this AD to detect and correct wear of the inboard 
flap trunnions, which could lead to loss of flap surface control and 
consequently result in the flap detaching from the airplane. A 
detached flap could result in damage to the tail 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.

Restatement of Certain Requirements of AD 2000-24-02

Modification

    (f) For 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; and Model A321-111, -112, and -
131 airplanes; except those on which Airbus Modification 26495 has 
been accomplished in production: Within 18 months after January 8, 
2001 (the effective date of AD 2000-24-02), modify the sliding panel 
driving mechanism of the flap drive trunnions, in accordance with 
Airbus Service Bulletin A320-27-1117, Revision 02, dated January 18, 
2000.


    Note 1: Accomplishment of the modification required by paragraph 
(f) of this AD before January 8, 2001, in accordance with Airbus 
Service Bulletin A320-27-1117, dated July 31, 1997; or Revision 01, 
dated June 25, 1999, is acceptable for compliance with that 
paragraph.

Requirements of this AD

Detailed Inspections

    (g) For all airplanes: At the latest of the applicable 
compliance times specified in paragraphs (g)(1), (g)(2), and (g)(3) 
of this AD, do a detailed inspection of the inboard flap trunnions 
for any wear marks and of the sliding panels for any cracking at the 
long edges, and do any corrective actions as applicable, by 
accomplishing all of the applicable actions specified in the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1133, 
dated July 28, 2005; except as provided by paragraph (h) of this AD. 
Any corrective actions must be done at the compliance times 
specified in Figures 5 and 6, as applicable, of the service 
bulletin; except as provided by paragraph (i) of this AD. Repeat the 
detailed inspections thereafter at intervals not to exceed 4,000 
flight hours.

    Note 2: 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.''


    (1) Before accumulating 4,000 total flight hours on the inboard 
flap trunnion since new.
    (2) Within 4,000 flight hours after accomplishing paragraph (f) 
of this AD.
    (3) Within 600 flight hours after the effective date of this AD.

No Reporting Requirement

    (h) Although Airbus Service Bulletin A320-57-1133, dated July 
28, 2005, specifies to submit certain information to the 
manufacturer, this AD does not include that requirement.

Compliance Times

    (i) Where Airbus Service Bulletin A320-57-1133, dated July 28, 
2005, specifies replacing the sliding panel at the next opportunity, 
replace it within 600 flight hours after the inspection required by 
paragraph (g) of this AD. If the trunnion is found damaged during 
any inspection required by paragraph (g) of this AD, do the 
corrective actions specified in the service bulletin before further 
flight. Where the service bulletin specifies contacting the 
manufacturer for a grace period assessment after replacing the 
trunnion or flap, contact the FAA or Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) for the grace 
period assessment.

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 14 CFR 
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-2005-139, dated August 3, 
2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on November 18, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-23514 Filed 11-30-05; 8:45 am]
BILLING CODE 4910-13-P