Document ID: FAA-2018-0705-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus SAS Airplanes
Posted Date: 2019-02-12T05:00Z

[Federal Register Volume 84, Number 29 (Tuesday, February 12, 2019)]
[Rules and Regulations]
[Pages 3285-3288]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-01522]

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 Rules and Regulations
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains regulatory documents 
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  Federal Register / Vol. 84, No. 29 / Tuesday, February 12, 2019 / 
Rules and Regulations  

[[Page 3285]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0705; Product Identifier 2018-NM-077-AD; Amendment 
39-19546; AD 2019-01-07]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. This AD was prompted by a report that during removal of 
left-hand (LH) gear rib 5, four failed fasteners were discovered. This 
AD requires 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 issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective March 19, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 19, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile 
Dewoitine No: 2, 31700 Blagnac Cedex, France; phone: +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 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 on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0705.

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 final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus SAS Model 
A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The 
NPRM published in the Federal Register on August 9, 2018 (83 FR 39377). 
The NPRM was prompted by a report that during removal of LH gear rib 5, 
four failed fasteners were discovered. The NPRM proposed to require a 
one-time ultrasonic inspection of the LH and 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 issuing this AD to address cracked or failed (broken) 
fasteners (bolts) of the rib 5-to-rear spar attachment, which could 
lead to reduced structural integrity of the wing.
    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.

Comments

    We gave the public the opportunity to participate in developing 
this final rule.

[[Page 3286]]

The following presents the comment received on the NPRM and the FAA's 
response to each comment.

Request To Include Revised Service Information

    American Airlines (AAL) requested that we include Airbus Service 
Bulletin A320-57-1167, Revision 02, dated August 14, 2018, as the 
required source of service information for the proposed AD. AAL pointed 
out that the revised service information was issued to add defueling/
access procedures in case of findings during the inspection. AAL also 
mentioned that including the later revised service information would 
reduce the number of future alternative method of compliance (AMOC) 
approval requests.
    We agree with the commenter's request. We have included Airbus 
Service Bulletin A320-57-1167, Revision 02, dated August 14, 2018, in 
this AD. We have determined that no additional work is required for 
compliance (RC) for airplanes that have accomplished the actions 
specified in Airbus Service Bulletin A320-57-1167, Revision 01, dated 
January 16, 2018. We have added paragraph (j) to this AD to provide 
credit for actions done before the effective date of this AD in 
accordance with Revision 01 of the referenced service information. We 
have also redesignated subsequent paragraphs accordingly.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this final rule with the changes described previously and minor 
editorial changes. We have determined that these minor changes:

     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than 
was already proposed in the NPRM.

    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related Service Information Under 1 CFR Part 51

    Airbus SAS has issued Service Bulletin A320-57-1167, Revision 02, 
dated August 14, 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.

Costs of Compliance

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

                                     Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
                                                                                    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
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting/revising the maintenance or inspection program.

    We estimate that it would take about 1 work-hour per product to 
comply with the reporting requirement in this 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
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

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 AD is 2120-
0056. The paperwork cost associated with this AD 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 AD 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

[[Page 3287]]

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 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

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2019-01-07 Airbus SAS: Amendment 39-19546; Docket No. FAA-2018-0705; 
Product Identifier 2018-NM-077-AD.

(a) Effective Date

    This AD is effective March 19, 2019.

(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 02, 
dated August 14, 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 address 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 02, dated August 14, 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 paragraphs (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 02, dated August 14, 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 02, 
dated August 14, 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 02, 
dated August 14, 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 02, dated August 14, 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 02, dated August 14, 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) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g), (h), and (i) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A320-57-1167, Revision 01, dated January 16, 2018.

(k) 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

[[Page 3288]]

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.

(l) 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 (m)(2) of this AD. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain 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 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.

(m) 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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3) and (n)(4) of this AD.

(n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-57-1167, Revision 02, dated 
August 14, 2018.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax: 
+33 5 61 93 44 51; email: account.airworth-eas@airbus.com; internet: 
http://www.airbus.com.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.;

    Issued in Des Moines, Washington, on January 10, 2019.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2019-01522 Filed 2-11-19; 8:45 am]
BILLING CODE 4910-13-P