80 FR 38992 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 130 (July 8, 2015)

Page Range		38992-38995
FR Document		2015-16583
We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318, A319, and A321 series airplanes. This proposed AD was prompted by reports of in-flight loss of fixed and hinged main landing gear (MLG) fairings, and reports of post-modification MLG fixed fairing assemblies that have wear and corrosion. This proposed AD would require, for certain airplanes, repetitive replacements of the fixed fairing upper and lower attachment studs of both the right-hand (RH) and left-hand (LH) MLG; and repetitive inspections for corrosion, wear, fatigue, cracking, and loose studs of each forward stud assembly of the fixed fairing door upper and lower forward attachment of both RH and LH MLG; and replacement if necessary. This proposed AD also provides an optional terminating modification for the repetitive replacements of the fixed fairing upper and lower attachment studs. We are proposing this AD to prevent in-flight detachment of an MLG fixed fairing and consequent damage to the airplane.
Federal Register, Volume 80 Issue 130 (Wednesday, July 8, 2015)
[Federal Register Volume 80, Number 130 (Wednesday, July 8, 2015)]
[Proposed Rules]
[Pages 38992-38995]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-16583]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2458; Directorate Identifier 2014-NM-122-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A318, A319, and A321 series airplanes. This proposed AD 
was prompted by reports of in-flight loss of fixed and hinged main 
landing gear (MLG) fairings, and reports of post-modification MLG fixed 
fairing assemblies that have wear and corrosion. This proposed AD would 
require, for certain airplanes, repetitive replacements of the fixed 
fairing upper and lower attachment studs of both the right-hand (RH) 
and left-hand (LH) MLG; and repetitive inspections for corrosion, wear, 
fatigue, cracking, and loose studs of each forward stud assembly of the 
fixed fairing door upper and lower forward attachment of both RH and LH 
MLG; and replacement if necessary. This proposed AD also provides an 
optional terminating modification for the repetitive replacements of 
the fixed fairing upper and lower attachment studs. We are proposing 
this AD to prevent in-flight detachment of an MLG fixed fairing and 
consequent damage to the airplane.

DATES: We must receive comments on this proposed AD by August 24, 2015.

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, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

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-2015-
2458; 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 
Operations 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
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-2015-2458; 
Directorate Identifier 2014-NM-122-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 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 proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0001R1, dated January 15, 2015 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Model A318, A319, 
A320, and Model A321 series airplanes. The MCAI states:

    Several occurrences of in-flight loss of main landing gear (MLG) 
fixed and hinged fairings were reported. The majority of reported 
events occurred following scheduled maintenance activities. One 
result of the investigation was that a discrepancy between the 
drawing and the maintenance manuals was discovered. The maintenance 
documents were corrected to prevent mis-rigging of the MLG fixed and 
hinged fairings, which could induce fatigue cracking.
    Airbus issued Service Bulletin (SB) A320-52-1083, providing 
instructions for a one-time inspection of the MLG fixed fairing 
composite insert and the surrounding area, replacement of the 
adjustment studs at the lower forward position and adjustment to the 
new clearance tolerances. That SB was replaced by Airbus SB A320-52-
1100 (mod 27716) introducing a re-designed location stud, rod end 
and location plate at the forward upper and lower leg fixed-fairing 
positions. Subsequently, reports were received of post-mod 27716/
post-SB A320-52-1100 MLG fixed fairing assemblies with corrosion, 
which could also induce cracking.
    This condition, if not detected and corrected, could lead to 
further cases of in-flight detachment of a MLG fixed fairing, 
possibly resulting in injury to persons on the ground and/or damage 
to the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2014-
0096 [http://ad.easa.europa.eu/blob/easa_ad_2014_0096_superseded.pdf/AD_2014-0096_1] to require [for 
certain airplanes] repetitive detailed inspections (DET) of the MLG 
fixed fairings,

[[Page 38993]]

and, depending on findings, accomplishment of applicable corrective 
actions. That [EASA] AD also prohibited installation of certain MLG 
fixed fairing rod end assemblies and studs as replacement parts on 
aeroplanes incorporating Airbus mod 27716 in production, or modified 
in accordance with Airbus SB A320-52-1100 (any revision) in service.
    Since EASA AD 2014-0096 was issued, Airbus developed an 
alternative inspection programme to meet the AD requirements. In 
addition, a terminating action (mod 155648) was developed, which is 
to be made available for in service aeroplanes through Airbus SB 
A320-52-1165.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0096, which is superseded, and adds an 
optional terminating action for the repetitive inspections. For 
post-mod aeroplanes, i.e. incorporating Airbus mod 155648 in 
production, or modified by Airbus SB A320-52-1165 in service, the 
only remaining requirement is to ensure that pre-mod components are 
no longer installed.
    Prompted by these developments, EASA issued AD 2015-0001, 
retaining the requirements of EASA AD 2014-0096, which was 
superseded, and adding an optional terminating action for the 
repetitive inspections. For post-mod aeroplanes, i.e. incorporating 
Airbus mod 155648 in production, or modified by Airbus SB A320-52-
1165 in service, the only remaining requirement is to ensure that 
pre-mod components are no longer installed.
    Since that [EASA] AD was issued, it was discovered that a 
certain plate support, Part Number (P/N) D5285600620000 as listed in 
Table 3 of the [EASA] AD, remains part of the post SB A320-52-1165 
configuration and is therefore not affected by any prohibition of 
installation--paragraph (11) of the [EASA] AD. In addition, an error 
was detected in Table 1 of the [EASA] AD (missing P/N plate support) 
and paragraph (9) was found to be incorrectly worded.
    For the reasons described above, this [EASA] AD is revised to 
introduce the necessary corrections.

    Required actions also include, for airplanes in Airbus pre-
modification 27716 and pre-Airbus Service Bulletin A320-52-1100 
configuration on which certain components have been installed, 
repetitive replacements of the fixed fairing upper and lower attachment 
studs of both the RH and LH MLG. An optional terminating modification 
also is provided for the repetitive replacements of the fixed fairing 
upper and lower attachment studs. The optional terminating modification 
includes a resonance frequency inspection for debonding of the 
composite insert and delamination of the honeycomb area around the 
insert, and applicable corrective actions if necessary; and 
installation of new studs, rod ends, and location plates at the forward 
upper and lower leg fixed-fairing positions. An additional optional 
terminating modification, for airplanes in pre-modification 27716 and 
pre-Airbus Service Bulletin A320-52-1100 configuration, includes 
installation of a locking device, new studs, rod ends, and location 
plates at the forward upper and lower leg fixed-fairing positions.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2458.

Related Service Information Under 1 CFR Part 51

     Airbus has issued Service Bulletin A320-52-1100, Revision 
01, dated March 12, 1999. This service information describes procedures 
for modification of the airplane to post-modification 27716 
configuration (by replacing the location stud, rod end, and location 
plate at the forward upper and lower leg fixed-fairing positions of the 
MLG door assemblies). The modification includes a resonance frequency 
inspection for debonding of the composite insert and delamination of 
the honeycomb area around the insert, and applicable corrective 
actions. Corrective actions include repairing the insert. The actions 
in this service information are an optional terminating modification.
     Airbus has also issued Service Bulletin A320-52-1163, 
dated February 4, 2014. This service information describes procedures 
for inspection of the fixed fairing forward attachments of the MLG door 
assemblies, and replacement of the fixed fairing upper and lower 
attachment studs of the RH and LH MLG door assemblies.
     Airbus has issued Service Bulletin A320-52-1165, dated 
November 3, 2014. This service information describes procedures for 
replacing the fairing attachment stud assemblies of the MLG door 
assembly with new assemblies. The actions in this service information 
are an optional terminating modification.
    This service information 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 of this 
AD.

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 and service 
information 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 these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S. 
registry.
    We also estimate that it would take about 18 work-hours per product 
to comply with the basic inspection requirements of this proposed AD. 
The average labor rate is $85 per work-hour. Required parts would cost 
about $4,110 per product. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $4,799,640, or $5,640 per 
product.
    We estimate that the optional terminating modification would take 
about 18 work-hours and require parts costing $4,110, for a cost of 
$5,640 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 18 work-hours and require parts costing $4,110, for a cost 
of $5,640 per product. We have no way of determining the number of 
aircraft that might need these actions.
    According to the manufacturer, some of the costs of this proposed 
AD might be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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 determined that this proposed AD would not have federalism 
implications

[[Page 38994]]

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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2015-2458; Directorate Identifier 2014-NM-
122-AD.

(a) Comments Due Date

    We must receive comments by August 24, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by reports of in-flight loss of fixed and 
hinged main landing gear (MLG) fairings, and reports of post-
modification MLG fixed fairing assemblies that have wear and 
corrosion. We are issuing this AD to prevent in-flight detachment of 
an MLG fixed fairing and consequent damage to the airplane.

(f) Compliance

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

(g) Repetitive Replacements

    For airplanes in pre-modification 27716 and pre-Airbus Service 
Bulletin A320-52-1100 configuration, with any of the components 
installed that are identified in paragraphs (g)(1) through (g)(5) of 
this AD: At the applicable compliance time specified in paragraph 
(h) of this AD, replace fixed fairing upper and lower attachment 
studs of both right-hand (RH) and left-hand (LH) MLG, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-52-1163, dated February 4, 2014. Repeat the replacements 
thereafter at intervals not to exceed 6,500 flight cycles.
    (1) Plate--support having part number (P/N) D5284024820000.
    (2) Plate--support having part number (P/N) D5284024820200.
    (3) Stud--adjustment having P/N D5284024420000.
    (4) Rod end assembly (lower) having P/N D5284000500000.
    (5) Rod end assembly (upper) having P/N D5284000600000.

(h) Compliance Times for the Requirements of Paragraph (g) of this AD

    Do the initial replacement required by paragraph (g) of this AD 
at the latest of the times specified in paragraphs (h)(1) through 
(h)(4) of this AD.
    (1) Before the accumulation of 6,500 total flight cycles since 
the airplane's first flight.
    (2) Within 6,500 flight cycles since the last installation of a 
pre-modification 27716 stud on the airplane.
    (3) Within 1,500 flight cycles after the effective date of this 
AD.
    (4) Within 8 months after the effective date of this AD.

(i) Repetitive Inspections

    For airplanes in post-modification 27716 or post-Airbus Service 
Bulletin A320-52-1100 configuration, with any of the components 
installed that are identified in paragraphs (i)(1), (i)(2), and 
(i)(3) of this AD: At the applicable compliance time specified in 
paragraph (j) of this AD, do a detailed inspection of the LH and RH 
stud assemblies of the fixed fairing door upper and lower forward 
attachments of both RH and LH MLG for indications of corrosion, 
wear, fatigue, cracking, and loose studs, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, 
dated February 4, 2014. Repeat the inspection thereafter at 
intervals not to exceed 12 months. Replacement of both RH and LH MLG 
forward stud assemblies on an airplane, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, 
dated February 4, 2014, extends the interval for the next detailed 
inspection to 72 months; and the inspection must be repeated 
thereafter at intervals not to exceed 12 months.
    (1) Stud--adjustment having P/N D5285600720000.
    (2) Rod end assembly (lower) having P/N D5285600400000.
    (3) Rod end assembly (upper) having P/N D5285600500000.

(j) Compliance Times for the Requirements of Paragraph (i) of This AD

    Do the initial inspection required by paragraph (i) of this AD 
at the latest of the times specified in paragraphs (j)(1) through 
(j)(4) of this AD.
    (1) Before the accumulation of 72 months since the airplane's 
first flight.
    (2) Within 72 months since the last installation of a post-
modification 27716 assembly or since accomplishment of the actions 
specified in Airbus Service Bulletin A320-52-1100.
    (3) Within 1,500 flight cycles after the effective date of this 
AD.
    (4) Within 8 months after the effective date of this AD.

(k) Corrective Action

    If any indication of corrosion, wear, fatigue, cracking, or 
loose studs of any forward stud assembly is found during any 
inspection required by paragraph (i) of this AD, except as specified 
in paragraph (l) of this AD: Before further flight, replace the 
upper and lower fixed fairing forward attachment assemblies of the 
RH and LH MLG, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-52-1163, dated February 4, 2014; or 
Airbus Service Bulletin A320-52-1165, dated November 3, 2014.

(l) Corrective Action or Repetitive Inspections for Certain Corrosion 
Findings

    If any corrosion is found during any inspection required by 
paragraph (i) of this AD on any MLG fixed fairing forward attachment 
stud assembly (upper, lower, LH or RH), but the corroded stud is not 
loose: Do the action specified in paragraph (l)(1) or (l)(2) of this 
AD.
    (1) Before further flight, replace the affected assembly, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1163, dated February 4, 2014; or Airbus Service 
Bulletin A320-52-1165, dated November 3, 2014.
    (2) Within 4 months after finding corrosion, and thereafter at 
intervals not to exceed 4 months, do a detailed inspection for 
indications of corrosion, wear, fatigue, cracking, and loose studs 
of the forward stud assembly of the affected (RH or LH) MLG, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1163, dated February 4, 2014.

(m) Corrective Action for Inspections Specified in Paragraph (l)(2) of 
This AD

    If any indication of wear, fatigue, cracking, or loose studs of 
any forward stud assembly is found during any inspection required by

[[Page 38995]]

paragraph (l)(2) of this AD: Before further flight, replace the 
affected (RH or LH) MLG fixed fairing forward attachment assembly, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1163, dated February 4, 2014; or Airbus Service 
Bulletin A320-52-1165, dated November 3, 2014.

(n) Terminating Action

    (1) Replacement of parts on an airplane, as required by 
paragraph (g), (k), or (l)(1) of this AD, does not constitute 
terminating action for the repetitive inspections required by 
paragraph (i) of this AD, except as specified in paragraph (n)(3) of 
this AD.
    (2) The repetitive replacements required by paragraph (g) of 
this AD may be terminated by modification of the airplane to post-
modification 27716 configuration, including a resonance frequency 
inspection for debonding of the composite insert and delamination of 
the honeycomb area around the insert, and all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-52-1100, Revision 01, dated March 12, 
1999, provided all applicable corrective actions are done before 
further flight. Thereafter, refer to paragraph (i) of this AD to 
determine the compliance time for the next detailed inspection 
required by this AD.
    (3) Modification of an airplane, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1165, 
dated November 3, 2014, constitutes terminating action for actions 
required by paragraphs (g) through (m) of this AD for the airplane 
on which the modification is done.

(o) Exception to Certain AD Actions

    An airplane on which Airbus Modification 155648 has been 
embodied in production is not affected by the requirements of 
paragraphs (g) and (i) of this AD, provided that no affected 
component, identified by part number as listed paragraphs (g)(1) 
through (g)(5) and (i)(1) through (i)(3) of this AD, has been 
installed on that airplane since first flight of the airplane.

(p) Parts Installation Prohibition

    (1) For airplanes in pre-Airbus-Modification 27716 and pre-
Airbus-Service-Bulletin A320-52-1100 configuration: No person may 
install a component identified in paragraphs (g)(1) through (g)(5) 
of this AD on any airplane after doing the actions provided in 
paragraph (n)(2) of this AD.
    (2) For airplanes in post-Airbus-Modification 27716 and post 
Airbus Service Bulletin A320-52-1100 configuration: As of the 
effective date of this AD, no person may install a component 
identified in paragraphs (g)(1) through (g)(5) of this AD on any 
airplane.
    (3) For airplanes in pre-Airbus-Modification 155648 and pre-
Airbus-Service-Bulletin A320-52-1165 configuration: No person may 
install a component identified in paragraphs (g)(1) through (g)(5) 
and (i)(1) through (i)(3) of this AD on any airplane after doing the 
actions provided in paragraph (n)(3) of this AD.
    (4) For airplanes in post-Airbus-Modification 155648 and post-
Airbus-Service-Bulletin A320-52-1165 configuration: As of the 
effective date of this AD, no person may install a component 
identified in (g)(1) through (g)(5) and (i)(1) through (i)(3) of 
this AD on any airplane.

(q) Credit for Previous Actions

    This paragraph provides credit for optional actions provided by 
paragraph (n)(2) of this AD, if those actions were performed before 
the effective date of this AD using Airbus Service Bulletin A320-52-
1100, dated December 7, 1998, which is not incorporated by reference 
in this AD.

(r) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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 Branch, send it to ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. 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. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(s) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0001R1, dated January 15, 
2015, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-2458.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.


    Issued in Renton, Washington, on June 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-16583 Filed 7-7-15; 8:45 am]
 BILLING CODE 4910-13-P
38992 Federal Register / Vol. 80, No. 130 / Wednesday, July 8, 2015 / Proposed Rules

Aircraft Industries GmbH, using the contact modification for the repetitive Comments Invited
information in paragraph (h)(5) of this replacements of the fixed fairing upper
proposed AD. We invite you to send any written
and lower attachment studs. We are relevant data, views, or arguments about
(5) For Technify Motors service proposing this AD to prevent in-flight
information identified in this proposed AD, this proposed AD. Send your comments
contact Technify Motors GmbH,
detachment of an MLG fixed fairing and to an address listed under the
Platanenstrasse 14, D–09356 Sankt Egidien, consequent damage to the airplane. ADDRESSES section. Include ‘‘Docket No.
Germany; phone: +49–37204–696–0; fax: DATES: We must receive comments on FAA–2015–2458; Directorate Identifier
+49–37204–696–55; email: info@centurion- this proposed AD by August 24, 2015. 2014–NM–122–AD’’ at the beginning of
engines.com. For DAI service information ADDRESSES: You may send comments, your comments. We specifically invite
identified in this proposed AD, contact using the procedures found in 14 CFR comments on the overall regulatory,
Diamond Aircraft Industries GmbH, N. A.
Otto-Strasse 5, 2700 Wiener Neustadt,
11.43 and 11.45, by any of the following economic, environmental, and energy
Austria; phone: +43 2622 26700; fax: +43 methods: aspects of this proposed AD. We will
2622 26700 1369; email: airworthiness@ • Federal eRulemaking Portal: Go to consider all comments received by the
diamond-air.at. http://www.regulations.gov. Follow the closing date and may amend this
(6) You may view this service information instructions for submitting comments. proposed AD based on those comments.
at the FAA, Engine & Propeller Directorate, • Fax: 202–493–2251. We will post all comments we
12 New England Executive Park, Burlington, • Mail: U.S. Department of receive, without change, to http://
MA. For information on the availability of Transportation, Docket Operations, M– www.regulations.gov, including any
this material at the FAA, call 781–238–7125. 30, West Building Ground Floor, Room personal information you provide. We
Issued in Burlington, Massachusetts, on
W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each
June 26, 2015. Washington, DC 20590. substantive verbal contact we receive
• Hand Delivery: U.S. Department of about this proposed AD.
Ann C. Mollica,
Transportation, Docket Operations, M–
Acting Directorate Manager, Engine &
30, West Building Ground Floor, Room Discussion
Propeller Directorate, Aircraft Certification
W12–140, 1200 New Jersey Avenue SE., The European Aviation Safety Agency
Service.
Washington, DC, between 9 a.m. and 5 (EASA), which is the Technical Agent
[FR Doc. 2015–16586 Filed 7–7–15; 8:45 am]
p.m., Monday through Friday, except for the Member States of the European
BILLING CODE 4910–13–P
Federal holidays. Union, has issued EASA Airworthiness
For service information identified in Directive 2015–0001R1, dated January
this proposed AD, contact Airbus, 15, 2015 (referred to after this as the
DEPARTMENT OF TRANSPORTATION
Airworthiness Office—EIAS, 1 Rond Mandatory Continuing Airworthiness
Federal Aviation Administration Point Maurice Bellonte, 31707 Blagnac Information, or ‘‘the MCAI’’), to correct
Cedex, France; telephone +33 5 61 93 36 an unsafe condition for all Model A318,
14 CFR Part 39 96; fax +33 5 61 93 44 51; email A319, A320, and Model A321 series
account.airworth-eas@airbus.com; airplanes. The MCAI states:
[Docket No. FAA–2015–2458; Directorate Internet http://www.airbus.com. You
Identifier 2014–NM–122–AD] Several occurrences of in-flight loss of
may view this referenced service main landing gear (MLG) fixed and hinged
RIN 2120–AA64 information at the FAA, Transport fairings were reported. The majority of
Airplane Directorate, 1601 Lind Avenue reported events occurred following
Airworthiness Directives; Airbus SW., Renton, WA. For information on scheduled maintenance activities. One result
Airplanes the availability of this material at the of the investigation was that a discrepancy
between the drawing and the maintenance
AGENCY: Federal Aviation FAA, call 425–227–1221. manuals was discovered. The maintenance
Administration (FAA), DOT. Examining the AD Docket documents were corrected to prevent mis-
ACTION: Notice of proposed rulemaking rigging of the MLG fixed and hinged fairings,
You may examine the AD docket on which could induce fatigue cracking.
(NPRM). the Internet at http:// Airbus issued Service Bulletin (SB) A320–
SUMMARY: We propose to adopt a new www.regulations.gov by searching for 52–1083, providing instructions for a one-
and locating Docket No. FAA–2015– time inspection of the MLG fixed fairing
airworthiness directive (AD) for all composite insert and the surrounding area,
Airbus Model A318, A319, and A321 2458; or in person at the Docket
Management Facility between 9 a.m. replacement of the adjustment studs at the
series airplanes. This proposed AD was lower forward position and adjustment to the
prompted by reports of in-flight loss of and 5 p.m., Monday through Friday, new clearance tolerances. That SB was
fixed and hinged main landing gear except Federal holidays. The AD docket replaced by Airbus SB A320–52–1100 (mod
(MLG) fairings, and reports of post- contains this proposed AD, the 27716) introducing a re-designed location
modification MLG fixed fairing regulatory evaluation, any comments stud, rod end and location plate at the
assemblies that have wear and received, and other information. The forward upper and lower leg fixed-fairing
street address for the Docket Operations positions. Subsequently, reports were
corrosion. This proposed AD would received of post-mod 27716/post-SB A320–
require, for certain airplanes, repetitive office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will 52–1100 MLG fixed fairing assemblies with
replacements of the fixed fairing upper corrosion, which could also induce cracking.
and lower attachment studs of both the be available in the AD docket shortly This condition, if not detected and
right-hand (RH) and left-hand (LH) after receipt. corrected, could lead to further cases of in-
srobinson on DSK5SPTVN1PROD with PROPOSALS

MLG; and repetitive inspections for FOR FURTHER INFORMATION CONTACT: flight detachment of a MLG fixed fairing,
corrosion, wear, fatigue, cracking, and Sanjay Ralhan, Aerospace Engineer, possibly resulting in injury to persons on the
loose studs of each forward stud International Branch, ANM–116, ground and/or damage to the aeroplane.
Transport Airplane Directorate, FAA, To address this potential unsafe condition,
assembly of the fixed fairing door upper EASA issued AD 2014-0096 [http://
and lower forward attachment of both 1601 Lind Avenue SW., Renton, WA
ad.easa.europa.eu/blob/easa_ad_2014_0096_
RH and LH MLG; and replacement if 98057–3356; telephone 425–227–1405; superseded.pdf/AD_2014-0096_1] to require
necessary. This proposed AD also fax 425–227–1149. [for certain airplanes] repetitive detailed
provides an optional terminating SUPPLEMENTARY INFORMATION: inspections (DET) of the MLG fixed fairings,

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Federal Register / Vol. 80, No. 130 / Wednesday, July 8, 2015 / Proposed Rules 38993

and, depending on findings, accomplishment terminating modification, for airplanes referenced above. We are proposing this
of applicable corrective actions. That [EASA] in pre-modification 27716 and pre- AD because we evaluated all pertinent
AD also prohibited installation of certain Airbus Service Bulletin A320–52–1100 information and determined an unsafe
MLG fixed fairing rod end assemblies and configuration, includes installation of a condition exists and is likely to exist or
studs as replacement parts on aeroplanes
incorporating Airbus mod 27716 in
locking device, new studs, rod ends, develop on other products of these same
production, or modified in accordance with and location plates at the forward upper type designs.
Airbus SB A320–52–1100 (any revision) in and lower leg fixed-fairing positions.
You may examine the MCAI in the Costs of Compliance
service.
Since EASA AD 2014–0096 was issued, AD docket on the Internet at http:// We estimate that this proposed AD
Airbus developed an alternative inspection www.regulations.gov by searching for affects 851 airplanes of U.S. registry.
programme to meet the AD requirements. In and locating Docket No. FAA–2015– We also estimate that it would take
addition, a terminating action (mod 155648) 2458. about 18 work-hours per product to
was developed, which is to be made available comply with the basic inspection
for in service aeroplanes through Airbus SB Related Service Information Under 1 requirements of this proposed AD. The
A320–52–1165. CFR Part 51 average labor rate is $85 per work-hour.
For the reasons described above, this • Airbus has issued Service Bulletin
[EASA] AD retains the requirements of EASA
Required parts would cost about $4,110
AD 2014–0096, which is superseded, and
A320–52–1100, Revision 01, dated per product. Based on these figures, we
adds an optional terminating action for the March 12, 1999. This service estimate the cost of this proposed AD on
repetitive inspections. For post-mod information describes procedures for U.S. operators to be $4,799,640, or
aeroplanes, i.e. incorporating Airbus mod modification of the airplane to post- $5,640 per product.
155648 in production, or modified by Airbus modification 27716 configuration (by We estimate that the optional
SB A320–52–1165 in service, the only replacing the location stud, rod end, and terminating modification would take
remaining requirement is to ensure that pre- location plate at the forward upper and about 18 work-hours and require parts
mod components are no longer installed. lower leg fixed-fairing positions of the costing $4,110, for a cost of $5,640 per
Prompted by these developments, EASA MLG door assemblies). The product.
issued AD 2015–0001, retaining the
requirements of EASA AD 2014–0096, which
modification includes a resonance In addition, we estimate that any
was superseded, and adding an optional frequency inspection for debonding of necessary follow-on actions would take
terminating action for the repetitive the composite insert and delamination about 18 work-hours and require parts
inspections. For post-mod aeroplanes, i.e. of the honeycomb area around the costing $4,110, for a cost of $5,640 per
incorporating Airbus mod 155648 in insert, and applicable corrective actions. product. We have no way of
production, or modified by Airbus SB A320– Corrective actions include repairing the determining the number of aircraft that
52–1165 in service, the only remaining insert. The actions in this service might need these actions.
requirement is to ensure that pre-mod information are an optional terminating According to the manufacturer, some
components are no longer installed. modification. of the costs of this proposed AD might
Since that [EASA] AD was issued, it was • Airbus has also issued Service be covered under warranty, thereby
discovered that a certain plate support, Part
Number (P/N) D5285600620000 as listed in
Bulletin A320–52–1163, dated February reducing the cost impact on affected
Table 3 of the [EASA] AD, remains part of 4, 2014. This service information individuals. We do not control warranty
the post SB A320–52–1165 configuration and describes procedures for inspection of coverage for affected individuals. As a
is therefore not affected by any prohibition of the fixed fairing forward attachments of result, we have included all costs in our
installation—paragraph (11) of the [EASA] the MLG door assemblies, and cost estimate.
AD. In addition, an error was detected in replacement of the fixed fairing upper
Table 1 of the [EASA] AD (missing P/N plate Authority for This Rulemaking
and lower attachment studs of the RH
support) and paragraph (9) was found to be and LH MLG door assemblies. Title 49 of the United States Code
incorrectly worded. • Airbus has issued Service Bulletin specifies the FAA’s authority to issue
For the reasons described above, this A320–52–1165, dated November 3, rules on aviation safety. Subtitle I,
[EASA] AD is revised to introduce the
2014. This service information describes section 106, describes the authority of
necessary corrections.
procedures for replacing the fairing the FAA Administrator. ‘‘Subtitle VII:
Required actions also include, for attachment stud assemblies of the MLG Aviation Programs,’’ describes in more
airplanes in Airbus pre-modification door assembly with new assemblies. detail the scope of the Agency’s
27716 and pre-Airbus Service Bulletin The actions in this service information authority.
A320–52–1100 configuration on which are an optional terminating We are issuing this rulemaking under
certain components have been installed, modification. the authority described in ‘‘Subtitle VII,
repetitive replacements of the fixed This service information is reasonably Part A, Subpart III, Section 44701:
fairing upper and lower attachment available because the interested parties General requirements.’’ Under that
studs of both the RH and LH MLG. An have access to it through their normal section, Congress charges the FAA with
optional terminating modification also course of business or by the means promoting safe flight of civil aircraft in
is provided for the repetitive identified in the ADDRESSES section of air commerce by prescribing regulations
replacements of the fixed fairing upper this AD. for practices, methods, and procedures
and lower attachment studs. The the Administrator finds necessary for
optional terminating modification FAA’s Determination and Requirements
safety in air commerce. This regulation
includes a resonance frequency of This Proposed AD
is within the scope of that authority
srobinson on DSK5SPTVN1PROD with PROPOSALS

inspection for debonding of the This product has been approved by because it addresses an unsafe condition
composite insert and delamination of the aviation authority of another that is likely to exist or develop on
the honeycomb area around the insert, country, and is approved for operation products identified in this rulemaking
and applicable corrective actions if in the United States. Pursuant to our action.
necessary; and installation of new studs, bilateral agreement with the State of
rod ends, and location plates at the Design Authority, we have been notified Regulatory Findings
forward upper and lower leg fixed- of the unsafe condition described in the We determined that this proposed AD
fairing positions. An additional optional MCAI and service information would not have federalism implications

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38994 Federal Register / Vol. 80, No. 130 / Wednesday, July 8, 2015 / Proposed Rules

under Executive Order 13132. This (e) Reason in accordance with the Accomplishment
proposed AD would not have a This AD was prompted by reports of in- Instructions of Airbus Service Bulletin A320–
substantial direct effect on the States, on flight loss of fixed and hinged main landing 52–1163, dated February 4, 2014, extends the
gear (MLG) fairings, and reports of post- interval for the next detailed inspection to 72
the relationship between the national months; and the inspection must be repeated
Government and the States, or on the modification MLG fixed fairing assemblies
that have wear and corrosion. We are issuing thereafter at intervals not to exceed 12
distribution of power and months.
this AD to prevent in-flight detachment of an
responsibilities among the various MLG fixed fairing and consequent damage to (1) Stud—adjustment having P/N
levels of government. the airplane. D5285600720000.
For the reasons discussed above, I (2) Rod end assembly (lower) having P/N
certify this proposed regulation: (f) Compliance D5285600400000.
1. Is not a ‘‘significant regulatory Comply with this AD within the (3) Rod end assembly (upper) having P/N
action’’ under Executive Order 12866; compliance times specified, unless already D5285600500000.
2. Is not a ‘‘significant rule’’ under the done. (j) Compliance Times for the Requirements
DOT Regulatory Policies and Procedures (g) Repetitive Replacements of Paragraph (i) of This AD
(44 FR 11034, February 26, 1979); Do the initial inspection required by
For airplanes in pre-modification 27716
3. Will not affect intrastate aviation in paragraph (i) of this AD at the latest of the
and pre-Airbus Service Bulletin A320–52–
Alaska; and 1100 configuration, with any of the times specified in paragraphs (j)(1) through
4. Will not have a significant components installed that are identified in (j)(4) of this AD.
economic impact, positive or negative, paragraphs (g)(1) through (g)(5) of this AD: At (1) Before the accumulation of 72 months
on a substantial number of small entities the applicable compliance time specified in since the airplane’s first flight.
under the criteria of the Regulatory paragraph (h) of this AD, replace fixed fairing (2) Within 72 months since the last
Flexibility Act. upper and lower attachment studs of both installation of a post-modification 27716
right-hand (RH) and left-hand (LH) MLG, in assembly or since accomplishment of the
List of Subjects in 14 CFR Part 39 accordance with the Accomplishment actions specified in Airbus Service Bulletin
Instructions of Airbus Service Bulletin A320– A320–52–1100.
Air transportation, Aircraft, Aviation (3) Within 1,500 flight cycles after the
safety, Incorporation by reference, 52–1163, dated February 4, 2014. Repeat the
replacements thereafter at intervals not to effective date of this AD.
Safety. (4) Within 8 months after the effective date
exceed 6,500 flight cycles.
of this AD.
The Proposed Amendment (1) Plate—support having part number (P/
N) D5284024820000. (k) Corrective Action
Accordingly, under the authority (2) Plate—support having part number (P/
delegated to me by the Administrator, If any indication of corrosion, wear,
N) D5284024820200. fatigue, cracking, or loose studs of any
the FAA proposes to amend 14 CFR part (3) Stud—adjustment having P/N forward stud assembly is found during any
39 as follows: D5284024420000. inspection required by paragraph (i) of this
(4) Rod end assembly (lower) having P/N AD, except as specified in paragraph (l) of
PART 39—AIRWORTHINESS D5284000500000. this AD: Before further flight, replace the
DIRECTIVES (5) Rod end assembly (upper) having P/N upper and lower fixed fairing forward
D5284000600000. attachment assemblies of the RH and LH
■ 1. The authority citation for part 39 MLG, in accordance with the
(h) Compliance Times for the Requirements
continues to read as follows: of Paragraph (g) of this AD Accomplishment Instructions of Airbus
Authority: 49 U.S.C. 106(g), 40113, 44701. Service Bulletin A320–52–1163, dated
Do the initial replacement required by February 4, 2014; or Airbus Service Bulletin
§ 39.13 [Amended] paragraph (g) of this AD at the latest of the A320–52–1165, dated November 3, 2014.
times specified in paragraphs (h)(1) through
■ 2. The FAA amends § 39.13 by adding (h)(4) of this AD. (l) Corrective Action or Repetitive
the following new airworthiness (1) Before the accumulation of 6,500 total Inspections for Certain Corrosion Findings
directive (AD): flight cycles since the airplane’s first flight. If any corrosion is found during any
Airbus: Docket No. FAA–2015–2458; (2) Within 6,500 flight cycles since the last inspection required by paragraph (i) of this
Directorate Identifier 2014–NM–122–AD. installation of a pre-modification 27716 stud AD on any MLG fixed fairing forward
on the airplane. attachment stud assembly (upper, lower, LH
(a) Comments Due Date (3) Within 1,500 flight cycles after the or RH), but the corroded stud is not loose: Do
We must receive comments by August 24, effective date of this AD. the action specified in paragraph (l)(1) or
2015. (4) Within 8 months after the effective date (l)(2) of this AD.
of this AD. (1) Before further flight, replace the
(b) Affected ADs affected assembly, in accordance with the
(i) Repetitive Inspections
None. Accomplishment Instructions of Airbus
For airplanes in post-modification 27716 or Service Bulletin A320–52–1163, dated
(c) Applicability post-Airbus Service Bulletin A320–52–1100 February 4, 2014; or Airbus Service Bulletin
This AD applies to the Airbus airplanes configuration, with any of the components A320–52–1165, dated November 3, 2014.
identified in paragraphs (c)(1) through (c)(4) installed that are identified in paragraphs (2) Within 4 months after finding
of this AD, certificated in any category, all (i)(1), (i)(2), and (i)(3) of this AD: At the corrosion, and thereafter at intervals not to
manufacturer serial numbers. applicable compliance time specified in exceed 4 months, do a detailed inspection for
(1) Airbus Model A318–111, –112, –121, paragraph (j) of this AD, do a detailed indications of corrosion, wear, fatigue,
and –122 airplanes. inspection of the LH and RH stud assemblies cracking, and loose studs of the forward stud
(2) Airbus Model A319–111, –112, –113, of the fixed fairing door upper and lower assembly of the affected (RH or LH) MLG, in
srobinson on DSK5SPTVN1PROD with PROPOSALS

–114, –115, –131, –132, and –133 airplanes. forward attachments of both RH and LH MLG accordance with the Accomplishment
(3) Airbus Model A320–211, –212, –214, for indications of corrosion, wear, fatigue, Instructions of Airbus Service Bulletin A320–
–231, –232, and –233 airplanes. cracking, and loose studs, in accordance with 52–1163, dated February 4, 2014.
(4) Airbus Model A321–111, –112, –131, the Accomplishment Instructions of Airbus
–211, –212, –213, –231, and –232 airplanes. Service Bulletin A320–52–1163, dated (m) Corrective Action for Inspections
February 4, 2014. Repeat the inspection Specified in Paragraph (l)(2) of This AD
(d) Subject thereafter at intervals not to exceed 12 If any indication of wear, fatigue, cracking,
Air Transport Association (ATA) of months. Replacement of both RH and LH or loose studs of any forward stud assembly
America Code 52, Doors. MLG forward stud assemblies on an airplane, is found during any inspection required by

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Federal Register / Vol. 80, No. 130 / Wednesday, July 8, 2015 / Proposed Rules 38995

paragraph (l)(2) of this AD: Before further (4) For airplanes in post-Airbus- Issued in Renton, Washington, on June 30,
flight, replace the affected (RH or LH) MLG Modification 155648 and post-Airbus- 2015.
fixed fairing forward attachment assembly, in Service-Bulletin A320–52–1165 Jeffrey E. Duven,
accordance with the Accomplishment configuration: As of the effective date of this
Manager, Transport Airplane Directorate,
Instructions of Airbus Service Bulletin A320– AD, no person may install a component
Aircraft Certification Service.
52–1163, dated February 4, 2014; or Airbus identified in (g)(1) through (g)(5) and (i)(1)
through (i)(3) of this AD on any airplane. [FR Doc. 2015–16583 Filed 7–7–15; 8:45 am]
Service Bulletin A320–52–1165, dated
November 3, 2014. BILLING CODE 4910–13–P
(q) Credit for Previous Actions
(n) Terminating Action This paragraph provides credit for optional
(1) Replacement of parts on an airplane, as actions provided by paragraph (n)(2) of this
required by paragraph (g), (k), or (l)(1) of this AD, if those actions were performed before SECURITIES AND EXCHANGE
AD, does not constitute terminating action the effective date of this AD using Airbus COMMISSION
for the repetitive inspections required by Service Bulletin A320–52–1100, dated
paragraph (i) of this AD, except as specified December 7, 1998, which is not incorporated 17 CFR Part 240
in paragraph (n)(3) of this AD. by reference in this AD.
(2) The repetitive replacements required by [Release No. 33–9862; 34–75344 File No.
(r) Other FAA AD Provisions S7–13–15]
paragraph (g) of this AD may be terminated
The following provisions also apply to this
by modification of the airplane to post-
AD: RIN 3235–AL70
modification 27716 configuration, including
(1) Alternative Methods of Compliance
a resonance frequency inspection for
debonding of the composite insert and
(AMOCs): The Manager, International Possible Revisions To Audit
Branch, ANM–116, Transport Airplane Committee Disclosures
delamination of the honeycomb area around
Directorate, FAA, has the authority to
the insert, and all applicable corrective AGENCY: Securities and Exchange
approve AMOCs for this AD, if requested
actions, in accordance with the using the procedures found in 14 CFR 39.19.
Accomplishment Instructions of Airbus
Commission.
In accordance with 14 CFR 39.19, send your ACTION: Concept release; request for
Service Bulletin A320–52–1100, Revision 01, request to your principal inspector or local
dated March 12, 1999, provided all Flight Standards District Office, as comments.
applicable corrective actions are done before appropriate. If sending information directly
further flight. Thereafter, refer to paragraph to the International Branch, send it to ATTN:
SUMMARY: The Commission is
(i) of this AD to determine the compliance Sanjay Ralhan, Aerospace Engineer, publishing this concept release to seek
time for the next detailed inspection required International Branch, ANM–116, Transport public comment regarding audit
by this AD. Airplane Directorate, FAA, 1601 Lind committee reporting requirements, with
(3) Modification of an airplane, in Avenue SW., Renton, WA 98057–3356; a focus on the audit committee’s
accordance with the Accomplishment telephone 425–227–1405; fax 425–227–1149. reporting of its responsibilities with
Instructions of Airbus Service Bulletin A320– Information may be emailed to: 9-ANM-116-
52–1165, dated November 3, 2014, respect to its oversight of the
AMOC-REQUESTS@faa.gov. Before using independent auditor. Some have
constitutes terminating action for actions any approved AMOC, notify your appropriate
required by paragraphs (g) through (m) of this principal inspector, or lacking a principal
expressed a view that the Commission’s
AD for the airplane on which the inspector, the manager of the local flight disclosure rules for this area may not
modification is done. standards district office/certificate holding result in disclosures about audit
(o) Exception to Certain AD Actions district office. The AMOC approval letter committees and their activities that are
must specifically reference this AD. sufficient to help investors understand
An airplane on which Airbus Modification (2) Contacting the Manufacturer: For any and evaluate audit committee
155648 has been embodied in production is requirement in this AD to obtain corrective
not affected by the requirements of performance, which may in turn inform
actions from a manufacturer, the action must those investors’ investment or voting
paragraphs (g) and (i) of this AD, provided be accomplished using a method approved
that no affected component, identified by decisions. The majority of these
by the Manager, International Branch, ANM–
part number as listed paragraphs (g)(1) 116, Transport Airplane Directorate, FAA; or disclosure requirements, which exist in
through (g)(5) and (i)(1) through (i)(3) of this the European Aviation Safety Agency their current form principally in Item
AD, has been installed on that airplane since (EASA); or Airbus’s EASA Design 407 of Regulation S–K, were adopted in
first flight of the airplane. Organization Approval (DOA). If approved by 1999. Since then, there have been
(p) Parts Installation Prohibition the DOA, the approval must include the significant changes in the role and
DOA-authorized signature. responsibilities of audit committees
(1) For airplanes in pre-Airbus-
Modification 27716 and pre-Airbus-Service- (s) Related Information arising out of, among other things, the
Bulletin A320–52–1100 configuration: No (1) Refer to Mandatory Continuing Sarbanes-Oxley Act of 2002, enhanced
person may install a component identified in Airworthiness Information (MCAI) EASA listing requirements for audit
paragraphs (g)(1) through (g)(5) of this AD on Airworthiness Directive 2015–0001R1, dated committees, enhanced requirements for
any airplane after doing the actions provided January 15, 2015, for related information. auditor communications with the audit
in paragraph (n)(2) of this AD. This MCAI may be found in the AD docket committee arising out of the rules of the
(2) For airplanes in post-Airbus- on the Internet at http://www.regulations.gov Public Company Accounting Oversight
Modification 27716 and post Airbus Service by searching for and locating Docket No. Board, and changes in practice, both
Bulletin A320–52–1100 configuration: As of FAA–2015–2458.
the effective date of this AD, no person may domestically and internationally.
(2) For service information identified in
install a component identified in paragraphs this AD, contact Airbus, Airworthiness DATES: Comments should be received on
(g)(1) through (g)(5) of this AD on any Office—EIAS, 1 Rond Point Maurice or before September 8, 2015.
srobinson on DSK5SPTVN1PROD with PROPOSALS

airplane. Bellonte, 31707 Blagnac Cedex, France; ADDRESSES: Comments may be
(3) For airplanes in pre-Airbus- telephone +33 5 61 93 36 96; fax +33 5 61 submitted by any of the following
Modification 155648 and pre-Airbus-Service- 93 44 51; email account.airworth-eas@
Bulletin A320–52–1165 configuration: No airbus.com; Internet http://www.airbus.com.
methods:
person may install a component identified in You may view this service information at the Electronic Comments
paragraphs (g)(1) through (g)(5) and (i)(1) FAA, Transport Airplane Directorate, 1601
through (i)(3) of this AD on any airplane after Lind Avenue SW., Renton, WA. For • Use the Commission’s Internet
doing the actions provided in paragraph information on the availability of this comment form (http://www.sec.gov/
(n)(3) of this AD. material at the FAA, call 425–227–1221. rules/concept.shtml); or

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Document Created: 2018-02-23 09:12:19
Document Modified: 2018-02-23 09:12:19
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by August 24, 2015.
Contact		Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149.
FR Citation		80 FR 38992
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
80 FR 38992 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 130 (July 8, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
