Document ID: FAA-2016-9498-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2017-07-19T04:00Z

[Federal Register Volume 82, Number 137 (Wednesday, July 19, 2017)]
[Rules and Regulations]
[Pages 33002-33004]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14588]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9498; Directorate Identifier 2016-NM-105-AD; 
Amendment 39-18958; AD 2017-14-14]
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 all 
Airbus Model A321 series airplanes. This AD was prompted by a 
determination from fatigue testing that cracks could develop in the 
cabin floor beam junction at certain fuselage frame locations. This AD 
requires repetitive inspections for cracking in the cabin floor beam 
junction at certain fuselage frame locations, and repair if necessary. 
We are issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective August 23, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 23, 
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: 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. It is also available on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-9498.

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-2016-
9498; 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: 
800-647-5527) 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 
December 16, 2016 (81 FR 91060). The NPRM was prompted by a 
determination from fatigue testing on the Model A321 airframe that 
cracks could develop in the cabin floor beam junction at certain 
fuselage frame locations. The NPRM proposed to require repetitive 
inspections for cracking in the cabin floor beam junction at certain 
fuselage frame locations, and repair if necessary. We are issuing this 
AD to detect and correct cracking in the cabin floor beam junction at 
certain fuselage frame locations, which could result in reduced 
structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0105, dated June 6, 2016 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition on all 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 in the cabin floor 
beam junctions at fuselage frame (FR) 35.1 and FR 35.2, on both left 
hand (LH) and right hand (RH) sides, also on aeroplanes operated in 
the context of design service goal.
    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) A320-53-1317, SB A320-
53-1318, SB A320-53-1319, and SB A320-53-1320, each containing 
instructions for a different location.
    For the reasons described above, this [EASA] AD requires 
repetitive detailed inspections (DET) of the affected cabin floor 
beam junctions [for cracking] and, depending on findings, 
accomplishment of a repair.
    This [EASA] AD is considered an interim action, pending 
development of a permanent solution.
* * * * *

    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-2016-
9498.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM and 
the FAA's response.

Request To Use Later Approved Service Information Revisions

    Delta Airlines (DAL) requested that we revise the proposed AD to 
permit use of later approved revisions of service information as we 
have done in previous alternative methods of compliance (AMOCs). DAL 
stated that Airbus service bulletins are EASA approved, and through the 
bi-lateral agreement with the European Union, these subsequent service 
bulletin revisions should be allowed to be used by U.S. operators 
without seeking an AMOC. DAL also explained that having the ability to 
utilize future service bulletin revisions without seeking an AMOC is 
more efficient and preserves the required level of safety. DAL added 
that they operate airplanes that are not listed in the service bulletin 
applicability, but are included in the proposed AD. DAL claimed that 
without a provision allowing later approved revisions, they might have 
to apply for multiple AMOCs as the service information is updated.
    We do not agree with DAL's request. We may not refer to any 
document that does not yet exist in an AD. In general terms, we are 
required by Office of the Federal Register (OFR) regulations to either 
publish the service document contents as part of the actual AD 
language; or submit the service document to the OFR for approval as 
``referenced'' material, in which case we may only refer to such 
material in the text of an AD. The AD may refer to the

[[Page 33003]]

service document only if the OFR approved it for ``incorporation by 
reference.'' See 1 CFR part 51.
    To allow operators to use later revisions of the referenced 
document (issued after publication of the AD), either we must revise 
the AD to reference specific later revisions, or operators must request 
approval to use later revisions as an AMOC under the provisions of 
paragraph (i)(1) of this AD.
    In addition, in accordance with 14 CFR part 39.27, if there is a 
conflict between an AD and service information, operators must follow 
the requirements of the AD. We have not changed this AD in this regard.

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

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information, which describes 
procedures for inspections for cracking on the frame to cabin floor 
beam junction at certain fuselage frame locations, and repairs. This 
service information is distinct because it applies to different 
locations on the airplanes.
     Airbus Service Bulletin A320-53-1317, dated December 15, 
2015 (FR 35.1 on the right-hand side).
     Airbus Service Bulletin A320-53-1318, dated October 9, 
2015 (FR 35.1 on the left-hand side).
     Airbus Service Bulletin A320-53-1319, dated October 9, 
2015 (FR 35.2 on the right-hand side).
     Airbus Service Bulletin A320-53-1320, dated October 9, 
2015 (FR 35.2 on the left-hand side).
    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 175 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...............  6 work-hours x $85 per                 $0  $510 per inspection   $89,250 per
                            hour = $510 per                            cycle.                inspection cycle.
                            inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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;
    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):

2017-14-14 Airbus: Amendment 39-18958; Docket No. FAA-2016-9498; 
Directorate Identifier 2016-NM-105-AD.

(a) Effective Date

    This AD is effective August 23, 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, 
all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination from fatigue testing on 
the Model A321 airframe that cracks could develop in the cabin floor 
beam junction at certain fuselage frame locations. We are issuing 
this AD to detect and correct cracking in the cabin floor beam 
junction at certain fuselage frame locations, which could result in 
reduced structural integrity of the airplane.

(f) Compliance

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

[[Page 33004]]

(g) Repetitive Inspections

    Before exceeding 36,900 total flight cycles since first flight 
of the airplane, or within 2,100 flight cycles after the effective 
date of this AD, whichever occurs later: Do a detailed inspection 
for cracking of the frame to cabin floor beam junction on the aft 
and forward sides at frame (FR) 35.1 and FR 35.2 on the left-hand 
and right-hand sides, in accordance with the Accomplishment 
Instructions of the Airbus service information specified in 
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD. Repeat the 
inspection of the frame to cabin floor beam junction on the aft and 
forward sides at FR 35.1 and FR 35.2 on the left-hand and right-hand 
sides thereafter at intervals not to exceed 15,300 flight cycles.
    (1) Airbus Service Bulletin A320-53-1317, dated December 15, 
2015 (FR 35.1 right-hand side).
    (2) Airbus Service Bulletin A320-53-1318, dated October 9, 2015 
(FR 35.1 left-hand side).
    (3) Airbus Service Bulletin A320-53-1319, dated October 9, 2015 
(FR 35.2 right-hand side).
    (4) Airbus Service Bulletin A320-53-1320, dated October 9, 2015 
(FR 35.2 left-hand side).

(h) Repair

    If any crack is found during any inspection required by 
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 actions required by paragraph 
(g) of this AD, unless otherwise specified in the instructions 
provided 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: 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 
Branch, ANM-116, Transport Airplane Directorate, FAA; or 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 AD 2016-0105, dated June 6, 2016, 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-2016-9498.
    (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. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (k)(3) and (k)(4) of this AD.

(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 A320-53-1317, dated December 15, 
2015.
    (ii) Airbus Service Bulletin A320-53-1318, dated October 9, 
2015.
    (iii) Airbus Service Bulletin A320-53-1319, dated October 9, 
2015.
    (iv) Airbus Service Bulletin A320-53-1320, dated October 9, 
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: account.airworth-eas@airbus.com; Internet: 
http://www.airbus.com.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 29, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-14588 Filed 7-18-17; 8:45 am]
BILLING CODE 4910-13-P