[Federal Register: August 22, 2006 (Volume 71, Number 162)]
[Proposed Rules]
[Page 48838-48840]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22au06-10]
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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.
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[[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).
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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.
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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