[Federal Register Volume 84, Number 36 (Friday, February 22, 2019)]
[Rules and Regulations]
[Pages 5592-5595]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-02925]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0906; Product Identifier 2018-NM-122-AD; Amendment 
39-19561; AD 2019-03-09]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS 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 SAS Model A310-304, -322, -324, and -325 airplanes. This AD was 
prompted by an evaluation by the design approval holder (DAH) 
indicating that certain wing skin stringer joints are subject to 
widespread fatigue damage (WFD). This AD requires a rototest inspection 
of the fastener holes in the affected areas and repair if necessary, 
and modifying the fastener holes. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective March 29, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 29, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile 
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 
96; fax +33 5 61 93 44 51; email [email protected]; 
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-
0906.

Examining the AD Docket

    You may examine the AD docket on the internet at http://

[[Page 5593]]

www.regulations.gov by searching for and locating Docket No. FAA-2018-
0906; 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: Dan Rodina, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.

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 SAS Model A310-
304, -322, -324, and -325 airplanes. The NPRM published in the Federal 
Register on November 5, 2018 (83 FR 55294). The NPRM was prompted by an 
evaluation by the DAH indicating that certain wing skin stringer joints 
are subject to WFD. The NPRM proposed to require a rototest inspection 
of the fastener holes in the affected areas and repair if necessary, 
and modifying the fastener holes.
    We are issuing this AD to address any cracking of the top wing skin 
stringer joints at rib 19, which could result in 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 
2018-0174, dated August 14, 2018 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus SAS Model A310-304, -322, -
324, and -325 airplanes. The MCAI states:

    In response to US 14 CFR part 26 concerning Widespread Fatigue 
Damage (WFD), Airbus assessed all wing structural items of the 
Airbus A310 design deemed potentially susceptible to WFD. The top 
[wing] skin stringer joints at rib 19 at level of the first fastener 
row were highlighted as an area of uniform stress distribution, 
indicating that cracks may develop in adjacent stringers at the same 
time, which is known as Multi Element Damage.
    This condition, if not corrected, could reduce the structural 
integrity of the wing.
    Prompted by the conclusion of WFD analysis, Airbus issued the SB 
[Service Bulletin A310-57-2108, dated November 9, 2017] to provide 
modification instructions. The accomplishment of this modification 
at the specified time will extend the life of the fastener holes in 
the affected area in order to reach the Limit of Validity.
    For the reasons described above, this [EASA] AD requires a one-
time inspection of the [fastener] holes in the affected area, 
accomplishment of applicable corrective action(s) [contacting the 
manufacturer], depending on findings, and modification.

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-
0906.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this final rule 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 addressing 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

    Airbus has issued Service Bulletin A310-57-2108, dated November 9, 
2017. This service information describes procedures for accomplishing a 
rototest inspection of the fastener holes in the affected areas and 
repair if necessary, and modifying the fastener holes.
    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 14 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
----------------------------------------------------------------------------------------------------------------
43 work-hours x $85 per hour = $3,655........................              $0           $3,655          $51,170
----------------------------------------------------------------------------------------------------------------

    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.
    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

[[Page 5594]]

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):

2019-03-09 Airbus SAS: Amendment 39-19561; Docket No. FAA-2018-0906; 
Product Identifier 2018-NM-122-AD.

(a) Effective Date

    This AD is effective March 29, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS Model A310-304, -322, -324, 
and -325 airplanes, certificated in any category.

(d) Subject

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

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that top wing skin stringer joints at rib 19 
are subject to widespread fatigue damage (WFD). We are issuing this 
AD to address any cracking of the top wing skin stringer joints at 
rib 19, which could result in reduced structural integrity of the 
wing.

(f) Compliance

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

(g) Definitions

    (1) The affected areas are defined as the top wing skin 
stringers, 9 to 15, at the stringer joints, outboard of rib 19, on 
both wings.
    (2) The average flight time (AFT) is defined as flight hours 
(FH) divided by flight cycles (FC) accumulated by an individual 
airplane since the airplane's first flight, specified in hours and 
hundredths of an hour. Refer to the Airbus A310 Maintenance Review 
Board Report Section D2 for guidance on determining the AFT.

(h) Inspection

    Within the applicable compliance times specified in figure 1 to 
paragraph (h) of this AD, accomplish a rototest inspection of the 
fastener holes in the affected areas in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2108, 
dated November 9, 2017.
[GRAPHIC] [TIFF OMITTED] TR22FE19.015

(i) Corrective Actions

    If, during the inspection required by paragraph (h) of this AD, 
any discrepancy (i.e., cracking or discrepant hole diameter) or 
existing repair is detected, 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.

(j) Modification

    If, during the inspection required by paragraph (h) of this AD, 
no existing repair or discrepancy is detected, before further 
flight, modify the fastener holes in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2108, 
dated November 9, 2017.

(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: [email protected]. 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): 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.

[[Page 5595]]

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0174, dated August 14, 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-2018-0906.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3225.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) 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 A310-57-2108, dated November 9, 
2017.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email [email protected]; 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 February 7, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-02925 Filed 2-21-19; 8:45 am]
 BILLING CODE 4910-13-P