Airworthiness Directives; Airbus Airplanes, 24397-24399 [2018-11171]

Download as PDF 24397 Rules and Regulations Federal Register Vol. 83, No. 103 Tuesday, May 29, 2018 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0025. The Code of Federal Regulations is sold by the Superintendent of Documents. You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0025; 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: 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: DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0025; Product Identifier 2017–NM–101–AD; Amendment 39–19294; AD 2018–11–06] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A310–203, –221, –222, –304, –322, –324, and –325 airplanes. This AD was prompted by a design approval holder (DAH) evaluation indicating that the outer wing lower junction is subject to widespread fatigue damage (WFD). This AD requires modifying the fastener holes at certain locations, which includes related investigative actions and applicable corrective actions. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 3, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 3, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAW, 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.airwortheas@airbus.com; internet: http:// www.airbus.com. You may view this referenced 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. jstallworth on DSKBBY8HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 14:11 May 25, 2018 Jkt 244001 Examining the AD Docket 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 A310–203, –221, –222, –304, –322, –324, and –325 airplanes. The NPRM published in the Federal Register on February 8, 2018 (83 FR 5584) (‘‘the NPRM’’). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0122, dated July 18, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A310–203, –221, –222, –304, –308, –322, –324, and –325 airplanes. The MCAI states: In response to the FAA Part 26 rule, wing structural items of the Airbus A310 design were assessed regarding Widespread Fatigue Damage (WFD) phenomenon. One outcome was that the outer wing lower junction is prone to WFD at level of the first fasteners row, close to Rib 1 between Frame (FR) 40 and FR 47. This condition, if not corrected, could reduce the structural integrity of the wing. PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 Prompted by the conclusion of WFD analysis, Airbus issued Service Bulletin (SB) A310–57–2105 to provide modification instructions. The accomplishment of this modification at the specified time will recondition/renovate/extend the life of the fasteners holes at Rib 1, in order to reach the Limit Of Validity. For the reasons described above, this [EASA] AD requires cold working of the affected holes at Rib 1, stiffeners 1 to 14, on both outer wings between FR 40 and FR 47. Required actions include a modification of the fastener holes at rib 1, stiffeners 1 to 14, on both outer wings between FR 40 and FR 47 by coldworking. The modification includes related investigative actions and applicable corrective actions. The related investigative actions include a rotating probe test of the fastener holes for cracks and checking the hole diameter for certain diameters. The corrective action is repair. 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– 0025. Comments We gave the public the opportunity to participate in developing this final rule. We considered the comment received. FedEx 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: • 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 Airbus has issued Service Bulletin A310–57–2105, Revision 00, dated November 23, 2016. The service information describes procedures for a modification of the fastener holes at rib 1, stiffeners 1 to 14, on both outer wings between FR 40 and FR 47 by coldworking and includes related investigative actions and corrective actions. This service information is reasonably available because the E:\FR\FM\29MYR1.SGM 29MYR1 24398 Federal Register / Vol. 83, No. 103 / Tuesday, May 29, 2018 / Rules and Regulations 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 13 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Modification, including related investigative actions. 66 work-hours × $85 per hour = $5,610 ........ We estimate the following costs to do any necessary repair that will be Parts cost required based on the results of the inspection. We have no way of $24,200 Cost per product Cost on U.S. operators $29,810 $387,530 determining the number of aircraft that might need this repair: ON-CONDITION COSTS Action Labor cost Repair .............................................. 9 work-hours × $85 per hour = $765 ........................................................ jstallworth on DSKBBY8HB2PROD with RULES 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 to the Director of the System Oversight Division. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. 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 VerDate Sep<11>2014 14:11 May 25, 2018 Jkt 244001 Parts cost § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Cost per product $254 $1,019 2018–11–06 Airbus: Amendment 39–19294; Docket No. FAA–2018–0025; Product Identifier 2017–NM–101–AD. (a) Effective Date This AD is effective July 3, 2018. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Model A310– 203, –221, –222, –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 a design approval holder (DAH) evaluation indicating that the outer wing lower junction is subject to widespread fatigue damage (WFD). We are issuing this AD to prevent WFD at the outer wing lower junction, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification Before exceeding the compliance time specified in figure 1 to paragraph (g) of this AD, as applicable, or within 30 days after the effective date of this AD, whichever occurs later: Modify the fastener holes at rib 1, stiffeners 1 to 14, on both outer wings between frame (FR) 40 and FR 47, including doing all related investigative and applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310–57–2105, Revision 00, dated November 23, 2016, except as required by paragraph (h) of this AD. Do all related investigative and applicable corrective actions before further flight. E:\FR\FM\29MYR1.SGM 29MYR1 Federal Register / Vol. 83, No. 103 / Tuesday, May 29, 2018 / Rules and Regulations (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, 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 (j)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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 European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized 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 VerDate Sep<11>2014 14:11 May 25, 2018 Jkt 244001 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. Issued in Des Moines, Washington, on May 17, 2018. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. (j) Related Information [FR Doc. 2018–11171 Filed 5–25–18; 8:45 am] (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0122, dated July 18, 2017, 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–2018–0025. (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. BILLING CODE 4910–13–P (k) Material Incorporated by Reference Airworthiness Directives; Saab AB, Saab Aeronautics (Formerly Known as Saab AB, Saab Aerosystems) Airplanes (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 A310–57–2105, Revision 00, dated November 23, 2016. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 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 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/ibrlocations.html. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0450; Product Identifier 2018–NM–073–AD; Amendment 39–19295; AD 2018–11–07] RIN 2120–AA64 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. This AD requires a onetime inspection of the aileron bellcrank support brackets and a thickness measurement of the affected lug attaching the support bracket; repetitive inspections of the affected aileron bellcrank support brackets; and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD was prompted by the identification of a manufacturing defect on certain aileron bellcrank support brackets that resulted in the material thickness of the affected lug attaching the support bracket to the rear spar of the wing to be insufficient. We are issuing this AD to address the unsafe condition on these products. SUMMARY: E:\FR\FM\29MYR1.SGM 29MYR1 ER29MY18.000</GPH> jstallworth on DSKBBY8HB2PROD with RULES (h) Service Information Exception Where Airbus Service Bulletin A310–57– 2105, Revision 00, dated November 23, 2016, specifies to contact Airbus for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (i)(2) of this AD. 24399

Agencies

[Federal Register Volume 83, Number 103 (Tuesday, May 29, 2018)]
[Rules and Regulations]
[Pages 24397-24399]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11171]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 83, No. 103 / Tuesday, May 29, 2018 / Rules 
and Regulations

[[Page 24397]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0025; Product Identifier 2017-NM-101-AD; Amendment 
39-19294; AD 2018-11-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A310-203, -221, -222, -304, -322, -324, and -325 
airplanes. This AD was prompted by a design approval holder (DAH) 
evaluation indicating that the outer wing lower junction is subject to 
widespread fatigue damage (WFD). This AD requires modifying the 
fastener holes at certain locations, which includes related 
investigative actions and applicable corrective actions. We are issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective July 3, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 3, 
2018.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 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 referenced 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-2018-0025.

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-
0025; 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: 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 Model A310-203, 
-221, -222, -304, -322, -324, and -325 airplanes. The NPRM published in 
the Federal Register on February 8, 2018 (83 FR 5584) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0122, dated July 18, 2017 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus Model A310-203, -221, -222, -304, -308, 
-322, -324, and -325 airplanes. The MCAI states:

    In response to the FAA Part 26 rule, wing structural items of 
the Airbus A310 design were assessed regarding Widespread Fatigue 
Damage (WFD) phenomenon. One outcome was that the outer wing lower 
junction is prone to WFD at level of the first fasteners row, close 
to Rib 1 between Frame (FR) 40 and FR 47.
    This condition, if not corrected, could reduce the structural 
integrity of the wing.
    Prompted by the conclusion of WFD analysis, Airbus issued 
Service Bulletin (SB) A310-57-2105 to provide modification 
instructions. The accomplishment of this modification at the 
specified time will recondition/renovate/extend the life of the 
fasteners holes at Rib 1, in order to reach the Limit Of Validity.
    For the reasons described above, this [EASA] AD requires cold 
working of the affected holes at Rib 1, stiffeners 1 to 14, on both 
outer wings between FR 40 and FR 47.

    Required actions include a modification of the fastener holes at 
rib 1, stiffeners 1 to 14, on both outer wings between FR 40 and FR 47 
by cold-working. The modification includes related investigative 
actions and applicable corrective actions. The related investigative 
actions include a rotating probe test of the fastener holes for cracks 
and checking the hole diameter for certain diameters. The corrective 
action is repair.
    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-
0025.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We considered the comment received. FedEx 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:
     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

    Airbus has issued Service Bulletin A310-57-2105, Revision 00, dated 
November 23, 2016. The service information describes procedures for a 
modification of the fastener holes at rib 1, stiffeners 1 to 14, on 
both outer wings between FR 40 and FR 47 by cold-working and includes 
related investigative actions and corrective actions. This service 
information is reasonably available because the

[[Page 24398]]

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modification, including related      66 work-hours x $85 per             $24,200         $29,810        $387,530
 investigative actions.               hour = $5,610.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repair that 
will be required based on the results of the inspection. We have no way 
of determining the number of aircraft that might need this repair:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair.....................................  9 work-hours x $85 per hour = $765.            $254          $1,019
----------------------------------------------------------------------------------------------------------------

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 to 
the Director of the System Oversight Division.

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):

2018-11-06 Airbus: Amendment 39-19294; Docket No. FAA-2018-0025; 
Product Identifier 2017-NM-101-AD.

(a) Effective Date

    This AD is effective July 3, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Model A310-203, -221, -222, -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 a design approval holder (DAH) 
evaluation indicating that the outer wing lower junction is subject 
to widespread fatigue damage (WFD). We are issuing this AD to 
prevent WFD at the outer wing lower junction, which could result in 
reduced structural integrity of the airplane.

(f) Compliance

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

(g) Modification

    Before exceeding the compliance time specified in figure 1 to 
paragraph (g) of this AD, as applicable, or within 30 days after the 
effective date of this AD, whichever occurs later: Modify the 
fastener holes at rib 1, stiffeners 1 to 14, on both outer wings 
between frame (FR) 40 and FR 47, including doing all related 
investigative and applicable corrective actions, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A310-57-
2105, Revision 00, dated November 23, 2016, except as required by 
paragraph (h) of this AD. Do all related investigative and 
applicable corrective actions before further flight.

[[Page 24399]]

[GRAPHIC] [TIFF OMITTED] TR29MY18.000

(h) Service Information Exception

    Where Airbus Service Bulletin A310-57-2105, Revision 00, dated 
November 23, 2016, specifies to contact Airbus for appropriate 
action, and specifies that action as ``RC'' (Required for 
Compliance): Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (i)(2) of this 
AD.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 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 (j)(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 European Aviation 
Safety Agency (EASA); or Airbus's EASA Design Organization Approval 
(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 2017-0122, dated July 18, 2017, 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-2018-0025.
    (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.

(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 A310-57-2105, Revision 00, dated 
November 23, 2016.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 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 May 17, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-11171 Filed 5-25-18; 8:45 am]
BILLING CODE 4910-13-P