[Federal Register Volume 71, Number 162 (Tuesday, August 22, 2006)]
[Proposed Rules]
[Pages 48838-48840]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-13826]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 71, No. 162 / Tuesday, August 22, 2006 / 
Proposed Rules  

[[Page 48838]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25658; Directorate Identifier 2006-NM-054-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).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model A318, A319, A320, 
and A321 airplanes. The existing AD currently requires 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 add airplanes 
to the applicability in the existing AD and change the inspection type. 
This proposed AD results from a determination that certain airplanes 
must be included in the applicability of the AD, and that the 
inspection type must be revised. 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 September 21, 
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 proposed AD.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; 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-2006-25658; Directorate Identifier 2006-NM-054-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 February 6, 2006, we issued AD 2006-04-06, amendment 39-14487 
(71 FR 8439, February 17, 2006), for certain 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. That AD requires 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. 
That AD resulted from reports of wear damage to the inboard flap 
trunnions after incorporation of a terminating modification required by 
an earlier AD, which was superseded by AD 2006-04-06. We issued that 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.

Actions Since Existing AD Was Issued

    Since we issued AD 2006-04-06, we determined that we inadvertently 
excluded Airbus Model A321-200 airplanes from the applicability of the 
existing AD. This proposed AD emulates the French airworthiness 
directive by listing Airbus Model A318, A319, A320, and A321 airplanes 
in lieu of including the dash numbers, as done in the existing AD.
    In addition, in the existing AD we identified the inspection in 
paragraph (g) of the AD as a ``detailed'' inspection. Upon further 
review of the service bulletin, we have determined that the appropriate 
inspection type is ``general visual.'' We have revised paragraph (i) 
and the inspection definition in Note 4 of this proposed AD 
accordingly.

[[Page 48839]]

    We have changed paragraph (i) of the existing AD, paragraph (j) of 
this proposed AD, by adding the words ``if damaged'' to clarify that 
replacing the sliding panel is required at the specified time if that 
condition is found.

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. As described in this 
bilateral airworthiness agreement, the Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (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 2006-04-06 and would continue 
to require repetitive 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 of the existing AD, and would change 
the inspection type from detailed to general visual.

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Number of
                                Work     Average                          Cost per         U.S.-
            Action              hours   labor rate        Parts           airplane       registered   Fleet cost
                                         per hour                                        airplanes
----------------------------------------------------------------------------------------------------------------
Modification in AD 2006-04-06      14          $80  The manufacturer  $1,120..........          755     $845,600
                                                     states that it
                                                     will supply
                                                     required parts
                                                     to operators at
                                                     no cost.
Detailed inspection in AD           2           80  None............  $160, per                 755      120,800
 2006-04-06.                                                           inspection
                                                                       cycle.
General visual inspection           1           80  None............  $80, per                  741       59,280
 (new action).                                                         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.
    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 39-14487 (71 FR 8439, February 17, 2006) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-25658; Directorate Identifier 2006-NM-
054-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by September 
21, 2006.

Affected ADs

    (b) This AD supersedes AD 2006-04-06.

Applicability

    (c) This AD applies to Airbus Model A318, A319, A320, and A321 
airplanes; certificated in any category; on which Airbus 
Modification 26495 has been incorporated in production.

Unsafe Condition

    (d) This AD results from a determination that certain airplanes 
must be included in the applicability of the AD, and that the 
inspection type must be revised. 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 Requirements of AD 2006-04-06

Modification

    (f) For Model A319-111, -112, -113, -114, -115, -131, -132, and 
-133 airplanes; Model

[[Page 48840]]

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, amendment 39-12009), 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.

Detailed Inspections

    (g) For Model A318-111 and -112 airplanes; Model A319-111, -112, 
-113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -
212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, 
and -131 airplanes; on which Airbus Modification 26495 has been 
incorporated in production: At the latest of the 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 (m) 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 
paragraphs (j), (k), and (l) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 4,000 flight hours until the 
inspection required by paragraph (i) of this AD is done.

    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 March 24, 2006 (the effective 
date of AD 2006-04-06).

New Requirements of This AD

Modification

    (h) For Model A321-211 and -231 airplanes, except those on which 
Airbus Modification 26495 has been accomplished in production: 
Within 18 months after the effective date of this AD, 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 3: Accomplishment of the modification required by paragraph 
(h) of this AD before the effective date of this AD, 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.

General Visual Inspections

    (i) For all airplanes: At the time specified in paragraph (i)(1) 
or (i)(2) of this AD, as applicable, do a general visual inspection 
of the inboard flap trunnions for any wear marks and of the sliding 
panels for any cracking at the long edges, and do all applicable 
corrective actions, 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 (m) of this AD. All 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 paragraphs (j), (k), and (l) 
of this AD. Repeat the inspection thereafter at intervals not to 
exceed 4,000 flight hours. Accomplishment of the general visual 
inspection required by this paragraph terminates the detailed 
inspection requirement of paragraph (g) of this AD.

    Note 4: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

    (1) For airplanes on which the detailed inspection required by 
paragraph (g) of this AD has been done before the effective date of 
this AD: Inspect before accumulating 4,000 total flight hours on the 
inboard flap trunnion since new, or within 4,000 flight hours after 
accomplishing the most recent inspection required by paragraph (g) 
of this AD, whichever occurs later.
    (2) For airplanes other than those identified in paragraph 
(i)(1) of this AD: Inspect at the latest of the times specified in 
paragraphs (i)(2)(i), (i)(2)(ii), and (i)(2)(iii) of this AD.
    (i) Before accumulating 4,000 total flight hours on the inboard 
flap trunnion since new.
    (ii) Within 4,000 flight hours after accomplishing paragraph (f) 
of this AD.
    (iii) Within 600 flight hours after the effective date of this 
AD.

Compliance Times

    (j) Where Airbus Service Bulletin A320-57-1133, dated July 28, 
2005, specifies replacing the sliding panel at the next opportunity 
if damaged, replace it within 600 flight hours after the inspection 
required by paragraph (g) or (i) of this AD, as applicable.
    (k) If any damage to the trunnion is found during any inspection 
required by paragraph (g) or (i) of this AD, do the corrective 
actions specified in the service bulletin before further flight.

Grace Period Assessment

    (l) Where the service bulletin specifies contacting the 
manufacturer for a grace period assessment after replacing the 
trunnion or flap, contact the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation 
Safety Agency (EASA) (or its delegated agent) for the grace period 
assessment.

No Reporting Requirement

    (m) 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.

Alternative Methods of Compliance (AMOCs)

    (n)(1) The Manager, International Branch, ANM-116, 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

    (o) French airworthiness directive F-2005-139, dated August 3, 
2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on August 14, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-13826 Filed 8-21-06; 8:45 am]
BILLING CODE 4910-13-P