[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 [email protected];
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: [email protected]. 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 [email protected]; 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