[Federal Register Volume 83, Number 154 (Thursday, August 9, 2018)]
[Proposed Rules]
[Pages 39377-39380]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16733]



[[Page 39377]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0705; Product Identifier 2018-NM-077-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 adopt a new airworthiness directive (AD) for 
certain Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes. This proposed AD was prompted by a report that 
during removal of left-hand (LH) gear rib 5, four failed fasteners were 
discovered. This proposed AD would require a one-time ultrasonic 
inspection of the LH and right-hand (RH) wing rib 5-to-rear spar 
attachments for cracked or failed fasteners, and if necessary, a 
detailed inspection of the gear rib 5 and spar web for cracks and 
damage, a rotating probe test of the gear rib and spar web bolt holes 
for cracks and damage, reaming the gear rib and the spar web bolt 
holes, and replacement of cracked or failed fasteners. We are proposing 
this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by September 24, 
2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus 
SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine No: 2, 31700 
Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax: +33 5 61 93 45 
80; email: <a href="/cdn-cgi/l/email-protection#57363e25203825233f3e3932242479166464677a1664636717363e253522247934383a"><span class="__cf_email__" data-cfemail="b7d6dec5c0d8c5c3dfded9d2c4c499f68484879af6848387f7d6dec5d5c2c499d4d8da">[email protected]</span></a>; internet: http://www.airbus.com. You may view this service information 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.

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-2018-
0705; 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 (phone: 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; phone 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-2018-0705; 
Product Identifier 2018-NM-077-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 because 
of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0102, dated April 27, 2018 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus SAS Model A321-111, -
112, -131, -211, -212, -213, -231, and -232 airplanes. The MCAI states:

    During removal of the left hand (LH) rib 5, two of the fasteners 
(bolts) attaching the rib to the wing inner rear spar were found to 
have failed and two more failed during their removal. Two of the 
bolts were found separated from the bolt shanks when the overcoat 
sealant was being removed, and the other two bolt heads broke away 
during removal.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the wing.
    To address this possible unsafe condition, Airbus issued 
[Service Bulletin] SB A320-57-1167 to provide inspection 
instructions. After that SB was issued, a potential manufacturing 
issue was identified on early production A321 [airplanes] concerning 
reports of fasteners ``jamming'' during installation on spar 
assemblies. A process change was introduced in production line, and 
SB A320-57-1167 was revised, changing the affected population to 
include all A321 aeroplanes delivered before the introduction of 
that process change.
    For the reasons described above, this [EASA] AD requires a one-
time special detailed [ultrasonic] inspection (SDI) of the wing rib 
5-to-rear spar attachments, both LH and right hand (RH) wings, [and 
if necessary, a detailed inspection of the gear rib 5 and spar web 
for cracks and damage (cracks along the length of the bolt or broken 
bolt), a rotating probe test of the gear rib and spar web bolt holes 
for cracks and damage (cracks in the bolt holes), reaming the gear 
rib and the spar web bolt holes] and, depending on findings, 
accomplishment of a repair [replacement of cracked or failed 
(broken) fasteners (bolts)]. This [EASA] AD also requires the 
reporting of findings.

    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-2018-
0705.

Related Service Information Under 1 CFR Part 51

    Airbus SAS has issued Service Bulletin A320-57-1167, Revision 01, 
dated January 16, 2018. This service information describes procedures 
for a one-time special detailed (ultrasonic) inspection of the LH and 
RH wing rib 5-to-rear spar attachments for cracked or failed (broken) 
fasteners (bolts), and if necessary, a detailed inspection of the gear-
rib-5 and spar web for cracks and damage (cracks along the length of 
the bolt or broken bolt), a rotating probe test of the gear rib and 
spar web bolt holes for cracks and damage (cracks in the bolt holes), 
reaming the gear rib and the spar web bolt holes, and replacement of 
the cracked or damaged (broken) fasteners (bolts). 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.

FAA's Determination

    This product has been approved by the aviation authority of another 
country, and is approved for operation

[[Page 39378]]

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 the relevant 
information and determined the unsafe condition described previously 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 the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the MCAI or Service 
Information.'' This proposed AD also would require sending the 
inspection results to Airbus SAS.

Differences Between This Proposed AD and the MCAI or Service 
Information

    The MCAI specifies credit for actions accomplished in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin A320-
57-1167, dated August 10, 2011. The MCAI also discusses a potential 
manufacturing issue that was identified on early production Model A321 
airplanes concerning reports of fasteners ``jamming'' during 
installation on spar assemblies. The corrective action specified in 
Airbus Service Bulletin A320-57-1167, dated August 10, 2011, includes 
the same process that produced ``jamming'' previously. Therefore, this 
proposed AD does not include credit for actions accomplished using the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1167, 
dated August 10, 2011.

Explanation of Change to Applicability

    We have revised the applicability of this AD to identify model 
designations as published in the most recent type certificate data 
sheet for the affected model.

Costs of Compliance

    We estimate that this proposed AD affects 29 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
16 work-hours x $85 per hour = $1,360........................              $0           $1,360          $39,440
----------------------------------------------------------------------------------------------------------------

    We estimate that it would take about 1 work-hour per product to 
comply with the proposed reporting requirement in this proposed AD. The 
average labor rate is $85 per hour. Based on these figures, we estimate 
the cost of reporting the inspection results on U.S. operators to be 
$2,465, or $85 per product.
    We estimate the following costs to do any necessary on-condition 
actions that would be required based on the results of any required 
actions. We have no way of determining the number of aircraft that 
might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                  Parts  cost        product
------------------------------------------------------------------------
20 work-hours x $85 per hour = $1,700.              $0           $1,700
------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this NPRM is 2120-
0056. The paperwork cost associated with this NPRM has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this NPRM is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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 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;

[[Page 39379]]

    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 SAS: Docket No. FAA-2018-0705; Product Identifier 2018-NM-
077-AD.

(a) Comments Due Date

    We must receive comments by September 24, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus SAS Model A321-111, -112, -131, -211, 
-212, -213, -231, and -232 airplanes, certificated in any category, 
as identified in Airbus Service Bulletin A320-57-1167, Revision 01, 
dated January 16, 2018.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a report that during removal of left-
hand (LH) gear rib 5, four failed fasteners (bolts attaching the 
gear rib to the wing inner rear spar) were discovered. We are 
issuing this AD to detect and correct cracked or failed (broken) 
fasteners (bolts) of the rib 5-to-rear spar attachment, which could 
lead to reduced structural integrity of the wing.

(f) Compliance

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

(g) Inspection of the Rib 5-to-Rear Spar Attachment Fasteners (Bolts)

    Within 30 months after the effective date of this AD, do a 
special detailed (ultrasonic) inspection of the LH and right-hand 
(RH) wing rib 5-to-rear spar attachment fasteners (bolts) for 
cracked or failed (broken) fasteners (bolts), in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1167, 
Revision 01, dated January 16, 2018.

(h) Replacement of Cracked or Failed Fasteners (Bolts)

    If any cracked or failed (broken) fastener (bolt) is found 
during any inspection required by paragraph (g) of this AD, before 
further flight, do the actions specified in paragraph (h)(1), 
(h)(2), (h)(3) and (h)(4) of this AD, as applicable.
    (1) Do a detailed inspection of the gear rib 5 and spar web for 
cracks and damage (cracks along the length of the bolt or broken 
bolt), in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-57-1167, Revision 01, dated January 16, 2018. 
If any crack or damage is found during any inspection required by 
this paragraph, before further flight, obtain corrective actions 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the European Aviation Safety Agency (EASA); or 
Airbus SAS's EASA Design Organization Approval (DOA); and accomplish 
the corrective actions within the compliance time specified therein. 
If approved by the DOA, the approval must include the DOA-authorized 
signature.
    (2) If no cracks or damage are found during any inspection 
required by paragraph (h)(1) of this AD: Do a rotating probe test of 
the gear rib and spar web bolt holes for cracks and damage (cracks 
in the bolt holes), in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-57-1167, Revision 01, 
dated January 16, 2018. If any crack or damage is found during any 
inspection required by this paragraph, before further flight, obtain 
corrective actions approved by the Manager, International Section, 
Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA; 
and accomplish the corrective actions within the compliance time 
specified therein. If approved by the DOA, the approval must include 
the DOA authorized signature.
    (3) If no cracks or damage are found during any inspection 
required by paragraph (h)(2) of this AD: Ream the gear rib and the 
spar web bolt holes, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-57-1167, Revision 01, 
dated January 16, 2018. If an oversize larger than 0.794 millimeter 
(0.0313 inch) is required, before further flight, obtain corrective 
actions approved by the Manager, International Section, Transport 
Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA; and 
accomplish the corrective actions within the compliance time 
specified therein. If approved by the DOA, the approval must include 
the DOA authorized signature.
    (4) Replace any cracked or failed fasteners (bolts) in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-57-1167, Revision 01, dated January 16, 2018.

(i) Reporting

    Within 90 days after the special detailed inspection required by 
paragraph (g) of this AD, or within 30 days after the effective date 
of this AD, whichever occurs later, report the inspection results 
(both positive and negative) to Airbus SAS in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1167, 
Revision 01, dated January 16, 2018. If operators have reported 
findings as part of obtaining any corrective actions approved by the 
EASA DOA, operators are not required to report those findings as 
specified in this paragraph.

(j) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 1 hour per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(k) 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 (l)(2) of this AD. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#221b0f636c6f0f1313140f636f6d610f7067737767717671624443430c454d54"><span class="__cf_email__" data-cfemail="437a6e020d0e6e7272756e020e0c006e1106121606101710032522226d242c35">[email protected]</span></a>. 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 corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or the EASA; or Airbus 
SAS's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (i) of this AD: If any service information contains 
procedures or

[[Page 39380]]

tests that are identified as RC, those 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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0102, dated April 27, 2018, 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-2018-0705.
    (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; phone and 
fax: 206-231-3223.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax: 
+33 5 61 93 45 80; email: <a href="/cdn-cgi/l/email-protection#02636b70756d70766a6b6c6771712c433131322f4331363242636b706077712c616d6f"><span class="__cf_email__" data-cfemail="5d3c342f2a322f29353433382e2e731c6e6e6d701c6e696d1d3c342f3f282e733e3230">[email protected]</span></a>; 
internet: http://www.airbus.com. You may view this service 
information 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.

    Issued in Des Moines, Washington, on July 27, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-16733 Filed 8-8-18; 8:45 am]
 BILLING CODE 4910-13-P


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