Document ID: FAA-2007-0391-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Airbus Model A318-100 and A319-100 Series Airplanes; A320-111 Airplanes; A320-200 Series Airplanes; and A321-100 and A321-200 Series Airplanes
Posted Date: 2008-01-09T05:00Z

[Federal Register: January 9, 2008 (Volume 73, Number 6)]
[Proposed Rules]               
[Page 1558-1560]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09ja08-15]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0391; Directorate Identifier 2007-NM-271-AD]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A318-100 and A319-100 
Series Airplanes; A320-111 Airplanes; A320-200 Series Airplanes; and 
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 supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model A318-100 and A319-
100 series airplanes; A320-111 airplanes; A320-200 series airplanes; 
and A321-100 and A321-200 series airplanes. The existing AD currently 
requires a one-time inspection of the horizontal hinge pin of the 103VU 
electrical panel in the avionics compartment to determine if the hinge 
pin can move out of the hinge, and related investigative and corrective 
actions if necessary. This proposed AD would require installing a hinge 
pin stopper on the internal door of the 103VU electrical panel. This 
proposed AD results from a report indicating that electrical wire 
damage was found in the 103VU electrical panel due to contact between 
the hinge pin and the adjacent electrical wire harness. We are 
proposing this AD to prevent contact between the horizontal hinge pin 
and the adjacent electrical wire harness, which could result in damage 
to electrical wires, and consequent arcing and/or failure of associated 
systems.

DATES: We must receive comments on this proposed AD by February 8, 
2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov.
 Follow the instructions for submitting comments.

     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov
; or in person at the Docket Management Facility 

between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0391; 
Directorate Identifier 2007-NM-271-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov
, including any personal information you provide. We 

will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On January 26, 2006, we issued AD 2006-03-10, amendment 39-14474 
(71 FR 6665, February 9, 2006), for certain Airbus Model A318-100 and 
A319-100 series airplanes; A320-111 airplanes; A320-200 series 
airplanes; and A321-100 and A321-200 series airplanes. That AD requires 
a one-time inspection of the horizontal hinge pin of the 103VU 
electrical panel in the avionics compartment to determine if the hinge 
pin can move out of the hinge, and related investigative and corrective 
actions if necessary. That AD resulted from a report indicating that 
electrical wire damage was found in the 103VU electrical panel due to 
contact between the hinge pin and the adjacent electrical wire harness. 
We issued that AD to prevent contact between the horizontal hinge pin 
and the adjacent electrical wire harness, which could result in damage 
to electrical wires, and consequent arcing and/or failure of associated 
systems.

Actions Since Existing AD Was Issued

    Since we issued AD 2006-03-10, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has informed us that the inspections and applicable 
corrective actions specified in Airbus All Operators Telex 25A1440, 
dated February 15, 2005 (referred to in AD 2006-03-10 as the 
appropriate source of service information for the required actions), 
are not adequate to address the identified unsafe condition (i.e., 
contact between the horizontal hinge pin and the adjacent electrical 
wire harness,

[[Page 1559]]

which could result in damage to electrical wires, and consequent arcing 
and/or failure of associated systems).

Relevant Service Information

    Airbus has issued Service Bulletin A320-25-1535, dated April 27, 
2007. The service bulletin describes procedures for installing a hinge 
pin stopper on the internal door of the 103VU electrical panel. 
Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The EASA mandated 
the service information and issued airworthiness directive 2007-0214, 
dated August 7, 2007, to ensure the continued airworthiness of these 
airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

    These airplanes 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 FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, the EASA has kept the FAA informed of the 
situation described above. We have examined the EASA'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 2006-03-10. This proposed AD 
would require accomplishing the actions specified in the service 
bulletin described previously.

Costs of Compliance

    This proposed AD would affect about 658 Airbus Model A318-100 and 
A319-100 series airplanes; A320-111 airplanes; A320-200 series 
airplanes; and A321-100 and A321-200 series airplanes of U.S. registry. 
The new proposed actions would take about 1 work hour per airplane, at 
an average labor rate of $80 per work hour. Required parts would cost 
about $20 per airplane. Based on these figures, the estimated cost of 
the new actions specified in this proposed AD for U.S. operators is 
$65,800, or $100 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 
removing amendment 39-14474 (71 FR 6665, February 9, 2006) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2007-0391; Directorate Identifier 2007-NM-
271-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
8, 2008.

Affected ADs

    (b) This AD supersedes AD 2006-03-10.

Applicability

    (c) This AD applies to Airbus Model A318-111 and -112; A319-111, 
-112, -113, -114, -115, -131, -132, and -133; A320-111, -211, -212, 
-214, -231, -232, and -233; and A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes; certificated in any category; all 
manufactured serial numbers; except for those airplanes on which 
Airbus Modification 36115 has been done in production or Airbus 
Service Bulletin A320-25-1535, dated April 27, 2007, has been done 
in service.

Unsafe Condition

    (d) This AD results from a report indicating that electrical 
wire damage was found in the 103VU electrical panel due to contact 
between the hinge pin and the adjacent electrical wire harness. We 
are issuing this AD to prevent contact between the horizontal hinge 
pin and the adjacent electrical wire harness, which could result in 
damage to electrical wires, and consequent arcing and/or failure of 
associated systems.

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.

Installation

    (f) Within 18 months after the effective date of this AD, 
install a hinge pin stopper on the internal door of the 103VU 
electrical panel in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-25-1535, dated April 27, 2007.

Alternative Methods of Compliance (AMOCs)

    (g)(1) The Manager, International Branch, ANM-116, FAA, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

[[Page 1560]]

Related Information

    (h) European Aviation Safety Agency airworthiness directive 
2007-0214, dated August 7, 2007, also addresses the subject of this 
AD.

    Issued in Renton, Washington, on December 19, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-152 Filed 1-8-08; 8:45 am]

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