[Federal Register Volume 84, Number 88 (Tuesday, May 7, 2019)]
[Proposed Rules]
[Pages 19885-19888]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-09265]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0258; Product Identifier 2018-NM-134-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 96-25-04, 
which applies to certain Airbus SAS Model A320 series airplanes. AD 96-
25-04 requires repetitive inspections to detect chafing of the wire 
looms (bundles) in the wing and the horizontal stabilizer and in 
certain areas of the main landing gear (MLG) bays; repair or 
replacement, protection, and realignment, if necessary; installation of 
protective sleeves around the wire bundles; and realignment of bundles 
that are not guided centrally into the conduit end fittings. Since we 
issued AD 96-25-04, investigations identified issues with the 
previously installed protective sleeves. This proposed AD would 
partially retain the requirements of AD 96-25-04 and would require 
modification of the wing electrical installation, as specified in an 
European Aviation Safety Agency (EASA) AD, which will be incorporated 
by reference. We are proposing this AD to address the unsafe condition 
on these products.

DATES: We must receive comments on this proposed AD by June 21, 2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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 the incorporation by reference (IBR) material described in the 
``Related IBR material under 1 CFR part 51'' section in SUPPLEMENTARY 
INFORMATION, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, 
Germany; telephone +49 221 89990 1000; email ADs@easa.europa.eu; 
internet www.easa.europa.eu. You may find this IBR material on the EASA 
website at https://ad.easa.europa.eu. You may view this IBR material at 
the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, 
WA. For information on the availability of this material at the FAA, 
call 206-231-3195. It is also available in the AD docket on

[[Page 19886]]

the internet at http://www.regulations.gov.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0258; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (telephone 800-
647-5527) is in the ADDRESSES section. Comments will be available in 
the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2019-0258; 
Product Identifier 2018-NM-134-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM based on 
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 NPRM.

Discussion

    We issued AD 96-25-04, Amendment 39-9846 (61 FR 66881, December 19, 
1996) (``AD 96-25-04''), for certain Airbus SAS Model A320 series 
airplanes. AD 96-25-04 requires inspections of the wire looms (bundles) 
in the wing and the horizontal stabilizer and in certain areas of the 
MLG bays; repair or replacement, protection, and realignment, if 
necessary; installation of protective sleeves around the wire bundles; 
and realignment of bundles that are not guided centrally into the 
conduit end fittings. AD 96-25-04 resulted from a report that 
electrical short-circuiting could occur in the wire bundles in the MLG 
bays. We issued AD 96-25-04 to address electrical short-circuiting due 
to chafing of the wire bundles in the wing, horizontal stabilizer, or 
MLG bay.

Actions Since AD 96-25-04 Was Issued

    Since we issued AD 96-25-04, investigations identified issues with 
the previously installed protective sleeves. We have determined that a 
modification of the wing electrical installation, which includes a new 
protective sleeve, is necessary to address the identified unsafe 
condition.
    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2018-0200, dated September 6, 2018 
(``EASA AD 2018-0200'') (also referred to as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Airbus SAS Model A320-211, -212, and -231 
airplanes. The MCAI states:

    Several cases of wire chafing were reported by operators, 
occurring in the trailing edge areas of zones 574 and 674 (both 
left-hand and right-hand wing) at the breakout of the electrical 
bundle from the conduit.
    This condition, if not detected and corrected, could lead to a 
short circuit, possibly resulting in a fire in the concerned areas. 
It was also determined that this failure mode can also affect other 
wires installed on the wing, horizontal stabilizer and in the main 
landing gear (MLG) bays.
    To address this unsafe condition, Airbus issued SB [service 
bulletin] A320-24-1044 to provide instructions for inspection of the 
wires to detect chafing or signs of overheating, and SB A320-24-1045 
introducing protective sleeves on electrical cables to prevent 
chafing.
    Consequently, DGAC [Direction G[eacute]n[eacute]rale de 
l'Aviation Civile] France issued AD 91-182-020(B) (later revised) 
[which corresponds to FAA AD 96-25-04] to require those repetitive 
inspections, or applicable repairs depending on findings, and to 
install protective sleeves as terminating action for the repetitive 
inspections.
    Since [DGAC France] AD 91-182-020(B) R2 was issued, subsequent 
investigations identified, in those areas (zones 574 and 674), 
issues with the protective sleeves previously installed in 
production, through mod 22109, or in service through SB A320-24-
1045.
    Prompted by these findings, Airbus issued SB A320-92-1115, later 
revised, providing instructions for installation of a new protective 
sleeve on those cables localised in zones 574 and 674, and 
introduced in production (through mod 22626) new design electrical 
cables more resistant to chafing.
    For the reasons described above, this [EASA] AD partially 
retains the requirements of DGAC France AD 91-182-020(B) R2, which 
is superseded, and requires modification of the wing electrical 
installation [installation of new protective sleeves on the 
electrical cables, which includes an inspection of the cables and 
repair or replacement of damaged wires].

Explanation of Retained Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 96-25-04, this proposed AD would retain certain 
requirements of AD 96-25-04. Those requirements are referenced in EASA 
AD 2018-0200, which, in turn, is referenced in paragraph (g) of this 
proposed AD.

Explanation of Change To Terminating Action Included in AD 96-25-04

    Note 2 of AD 96-25-04 indicated that accomplishment of the actions 
specified in Airbus Service Bulletin A320-24-1045, Revision 2, dated 
April 12, 1992, terminates the repetitive inspections specified in 
paragraphs (c) and (d) of AD 96-25-04 (which correspond to paragraphs 
(1) and (2) of EASA AD 2018-0200). However, this terminating action is 
not included in EASA AD 2018-0200, which would be incorporated by 
reference in the FAA AD.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2018-0200 describes procedures for repetitive inspections 
to detect chafing, signs of overheating, and misalignment of the wire 
looms (bundles) in the wing and the horizontal stabilizer and in 
certain areas of the MLG bays; repair or replacement, protection, and 
realignment, if necessary; realignment of bundles that are not guided 
centrally into the conduit end fittings; and modification of the wing 
electrical installation. This material is reasonably available because 
the interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section, and it is 
publicly available through the EASA website.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI referenced 
above. We are proposing this AD because we evaluated all pertinent 
information and determined an unsafe condition exists and is likely to 
exist or develop on other products of the same type design.

Proposed Requirements of This NPRM

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2018-0200 described previously, as incorporated by 
reference, except for any differences

[[Page 19887]]

identified as exceptions in the regulatory text of this AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA worked with Airbus and EASA to develop a process to 
use certain EASA ADs as the primary source of information for 
compliance with requirements for corresponding FAA ADs. As a result, 
EASA AD 2018-0200 will be incorporated by reference in the FAA final 
rule. This proposed AD would, therefore, require compliance with the 
provisions specified in EASA AD 2018-0200, except for any differences 
identified as exceptions in the regulatory text of this proposed AD. 
Service information specified in EASA AD 2018-0200 that is required for 
compliance with EASA AD 2018-0200 will be available on the internet 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2019-0258 after the FAA final rule is published.

Costs of Compliance

    We estimate that this proposed AD affects 27 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                      Estimated Costs for Required Actions
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                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
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Retained actions from AD 96-25-04..  62 work-hours x $85 per                  $0          $5,270        $142,290
                                      hour = $5,270.
New proposed actions...............  25 work-hours x $85 per                * $0           2,125         57, 375
                                      hour = $2,125.
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* We have received no definitive data on the parts costs.

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes and associated appliances to the 
Director of the System Oversight Division.

Regulatory Findings

    We 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 this 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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

0
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]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
96-25-04, Amendment 39-9846 (61 FR 66881, December 19, 1996), and 
adding the following new AD:

Airbus SAS: Docket No. FAA-2019-0258; Product Identifier 2018-NM-
134-AD.

(a) Comments Due Date

    We must receive comments by June 21, 2019.

(b) Affected ADs

    This AD replaces AD 96-25-04, Amendment 39-9846 (61 FR 66881, 
December 19, 1996) (``AD 96-25-04'').

(c) Applicability

    This AD applies to Airbus SAS Model A320-211, -212, and -231 
airplanes, certificated in any category, as identified in European 
Aviation Safety Agency (EASA) AD 2018-0200, dated September 6, 2018 
(``EASA AD 2018-0200'').

(d) Subject

    Air Transport Association (ATA) of America Code 24, Electrical 
power.

(e) Reason

    This AD was prompted by a report that electrical short-
circuiting could occur in the wire bundles in the wing, horizontal 
stabilizer or main landing gear (MLG) bays. This AD was also 
prompted by a determination that there were issues with protective 
sleeves previously installed as specified in AD 96-25-04. We are 
issuing this AD to address electrical short circuiting due to 
chafing of the wire bundles in the wing, horizontal stabilizer, or 
MLG bay, which could result in a fire.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2018-0200.

(h) Exceptions to EASA AD 2018-0200

    (1) For purposes of determining compliance with the requirements 
of this AD: Where EASA AD 2018-0200 refers to its

[[Page 19888]]

effective date, this AD requires using the effective date of this 
AD.
    (2) For purposes of determining compliance with the requirements 
of this AD: Where EASA AD 2018-0200 refers to ``the effective date 
of DGAC France AD 91-182-020 at original issue'' or refers to ``the 
effective date of DGAC France AD 91-182-020 at Rev.2,'' this AD 
requires using January 27, 1997 (the effective date of AD 96-25-04).
    (3) The ``Remarks'' section of EASA AD 2018-0200 does not apply 
to this AD.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (j)(2) of this AD. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's 
EASA Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): For any service information 
referenced in EASA AD 2018-0200 that contains RC procedures and 
tests: Except as required by paragraph (i)(2) of this AD, RC 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(j) Related Information

    (1) For information about EASA AD 2018-0200, contact EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
89990 6017; email ADs@easa.europa.eu; Internet www.easa.europa.eu. 
You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. You may view this EASA AD at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195. EASA AD 2018-0200 may be found in the AD docket on the 
internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2019-0258.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.

    Issued in Des Moines, Washington, on April 25, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-09265 Filed 5-6-19; 8:45 am]
 BILLING CODE 4910-13-P


