AD 2017-12-10

[Federal Register Volume 82, Number 114 (Thursday, June 15, 2017)]
[Rules and Regulations]
[Pages 27408-27411]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-12170]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9571; Directorate Identifier 2016-NM-139-AD; 
Amendment 39-18925; AD 2017-12-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. This AD was prompted by a full scale fatigue test campaign 
on these airplanes in the context of the extended service goal. This AD 
requires inspections of the affected frame locations, and repair if 
necessary. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective July 20, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of July 20, 
2017.

ADDRESSES: For service information identified in this final rule, 
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 <a href="/cdn-cgi/l/email-protection#610002020e140f154f000813160e1315094c040012210008130314124f020e0c"><span class="__cf_email__" data-cfemail="7d1c1e1e12081309531c140f0a120f091550181c0e3d1c140f1f080e531e1210">[email&#160;protected]</span></a>; Internet 
<a href="http://www.airbus.com">http://www.airbus.com</a>. 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. It is also available on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
9571.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
9571; 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 AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-

[[Page 27409]]

5527) is Docket Management Facility, 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 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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A321 
series airplanes. The NPRM published in the Federal Register on 
February 21, 2017 (82 FR 11162). The NPRM was prompted by a full scale 
fatigue test campaign on these airplanes in the context of the extended 
service goal. The NPRM proposed to require inspections of the affected 
frame locations, and repair if necessary. We are issuing this AD to 
detect and correct cracking of the fastener holes at certain frame 
locations, which could result in reduced structural integrity of the 
fuselage.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0146, dated July 20, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A321 series airplanes. The MCAI states:

    Following the results of a new full scale fatigue test campaign 
on the A321 airframe in the context of the A321 extended service 
goal, it was identified that cracks could develop on the fastener 
holes of frame (FR) 35.1, FR 35.2, and FR 35.3 between stringers 
(STR) 29 and STR 32 and at the FR 35.2 to Slidebox junction (Triform 
fitting), both left hand (LH) and right hand (RH) sides.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the fuselage. Prompted by these findings, 
Airbus developed an inspection programme, published in Service 
Bulletin (SB) A320-53-1308, SB A320-53-1309, SB A320-53-1310, SB 
A320-53-1311, SB A320-53-1312 and SB A320-53-1313, each containing 
instructions for a different location. For the reasons described 
above, this [EASA] AD requires repetitive special detailed 
(rototest) inspections (SDI) of the affected frame locations and, 
depending on findings, accomplishment of a repair.
    This [EASA] AD is considered an interim action, pending the 
development of a permanent solution.

    You may examine the MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
9571.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. Attiya Jaura supported the 
NPRM.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed, except for minor editorial changes. We have 
determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus issued the following service information. This service 
information describes procedures for repetitive rototest inspections 
for cracking of the affected frame locations, and contacting Airbus for 
repair instructions. These service bulletins are distinct because they 
apply to different frame locations.
    <bullet> Airbus Service Bulletin A320-53-1308, dated November 4, 
2015.
    <bullet> Airbus Service Bulletin A320-53-1309, dated November 4, 
2015.
    <bullet> Airbus Service Bulletin A320-53-1310, dated November 4, 
2015.
    <bullet> Airbus Service Bulletin A320-53-1311, dated November 4, 
2015.
    <bullet> Airbus Service Bulletin A320-53-1312, dated November 4, 
2015.
    <bullet> Airbus Service Bulletin A320-53-1313, dated November 4, 
2015.
    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 176 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                    Labor cost            Parts cost      Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  54 work-hours x $85     $1,070 per         $5,660 per         $996,160 per
                                  per hour = $4,590 per   inspection cycle.  inspection cycle.  inspection
                                  inspection cycle.                                             cycle.
----------------------------------------------------------------------------------------------------------------

    We have no way to estimate the costs to do any necessary repairs 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
repairs.

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 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;

[[Page 27410]]

    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):

2017-12-10 Airbus: Amendment 39-18925; Docket No. FAA-2016-9571; 
Directorate Identifier 2016-NM-139-AD.

(a) Effective Date

    This AD is effective July 20, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a full scale fatigue test campaign on 
Airbus Model A321 series airplanes in the context of the extended 
service goal. It was determined that cracks could develop on the 
fastener holes of certain frames on the left-hand (LH) and right-
hand (RH) sides of the affected airplanes. We are issuing this AD to 
detect and correct cracking of the fastener holes at certain frame 
locations, which could result in reduced structural integrity of the 
fuselage.

(f) Compliance

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

(g) Repetitive Inspections of the Frames, Stringers, and Slidebox 
Junctions

    At the applicable time specified in table 1 to the introductory 
text of paragraph (g) of this AD, do a rototest inspection for 
cracking at frame (FR) 35.1, FR 35.2, and FR 35.3 on the LH and RH 
sides, in accordance with the Accomplishment Instructions of the 
Airbus service information specified in paragraphs (g)(1), (g)(2), 
(g)(3), (g)(4), (g)(5), and (g)(6) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 5,300 flight cycles.

Table 1 to the Introductory Text of Paragraph (g) of This AD--Inspection
                                Threshold
------------------------------------------------------------------------
   Airplane accumulated total flight
cycles at the effective date of this AD          Compliance time
------------------------------------------------------------------------
For airplanes with 18,300 total flight   Before exceeding 18,300 total
 cycles or less.                          flight cycles, or within 5,300
                                          flight cycles after the
                                          effective date of this AD,
                                          whichever occurs later.
For airplanes with more than 18,300      Before exceeding 23,600 total
 total flight cycles.                     flight cycles, or within 2,100
                                          flight cycles after the
                                          effective date of this AD,
                                          whichever occurs later.
------------------------------------------------------------------------

    (1) Airbus Service Bulletin A320-53-1308, dated November 4, 2015 
(FR 35.1 LH side).
    (2) Airbus Service Bulletin A320-53-1309, dated November 4, 2015 
(FR 35.1 RH side).
    (3) Airbus Service Bulletin A320-53-1310, dated November 4, 2015 
(FR 35.2 LH side).
    (4) Airbus Service Bulletin A320-53-1311, dated November 4, 2015 
(FR 35.2 RH side).
    (5) Airbus Service Bulletin A320-53-1312, dated November 4, 2015 
(FR 35.3 LH side).
    (6) Airbus Service Bulletin A320-53-1313, dated November 4, 2015 
(FR 35.3 RH side).

(h) Corrective Action

    If any crack is found during any inspection required by the 
introductory text to paragraph (g) of this AD: Before further 
flight, repair 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). Although the service information 
specified in paragraph (g) of this AD specifies to contact Airbus 
for repair instructions, and specifies that action as ``RC'' 
(Required for Compliance), this AD requires repair as specified in 
this paragraph. Repair of an airplane as required by this paragraph 
does not constitute terminating action for the repetitive 
inspections required by the introductory text to paragraph (g) of 
this AD for that airplane, unless specified otherwise in the repair 
instructions approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.

(i) 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 the attention of 
the person identified in paragraph (j)(2) of this AD. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#7a43573b3437574b4b4c573b37353957283f2b2f3f292e293a1c1b1b541d150c"><span class="__cf_email__" data-cfemail="6e57432f2023435f5f58432f23212d433c2b3f3b2b3d3a3d2e080f0f40090118">[email&#160;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 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus'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 (h) of this AD: If any service information contains 
procedures or 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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0146, dated July 20, 2016, 
for related information. This MCAI may be found in the AD docket on 
the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and 
locating Docket No. FAA-2016-9571.
    (2) For more information about this AD, 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.

[[Page 27411]]

(k) 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 A320-53-1308, dated November 4, 
2015.
    (ii) Airbus Service Bulletin A320-53-1309, dated November 4, 
2015.
    (iii) Airbus Service Bulletin A320-53-1310, dated November 4, 
2015.
    (iv) Airbus Service Bulletin A320-53-1311, dated November 4, 
2015.
    (v) Airbus Service Bulletin A320-53-1312, dated November 4, 
2015.
    (vi) Airbus Service Bulletin A320-53-1313, dated November 4, 
2015.
    (3) 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 <a href="/cdn-cgi/l/email-protection#355456565a405b411b545c47425a47415d1850544675545c475740461b565a58"><span class="__cf_email__" data-cfemail="503133333f253e247e313922273f2224387d353123103139223225237e333f3d">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (4) 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.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on June 2, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-12170 Filed 6-14-17; 8:45 am]
BILLING CODE 4910-13-P