
[Federal Register Volume 82, Number 107 (Tuesday, June 6, 2017)]
[Rules and Regulations]
[Pages 25940-25943]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-11290]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7262; Directorate Identifier 2015-NM-079-AD; 
Amendment 39-18912; AD 2017-11-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 98-13-14, for 
certain Airbus Model A320-211, -212, and -231 airplanes. AD 98-13-14 
required repetitive inspections of certain fastener holes of the aft 
fuselage, and corrective action if necessary. This new AD continues to 
require the actions in AD 98-13-14, with revised inspection compliance 
times. This AD was prompted by identification of cracks in the fastener 
holes of the former junction of the aft fuselage, which occurred during 
a fatigue test; and a determination that certain compliance times 
specified in AD 98-13-14 must be reduced. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective July 11, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of July 11, 
2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of July 
30, 1998 (63 FR 34556, June 25, 1998).

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-
7262.

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-
7262; 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 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

[[Page 25941]]

part 39 to supersede AD 98-13-14, Amendment 39-10602 (63 FR 34556, June 
25, 1998) (``AD 98-13-14''). AD 98-13-14 applied to certain Airbus 
Model A320 series airplanes (Model A320-211, -212, and -231 airplanes). 
Since we issued AD 98-13-14, an evaluation by the DAH indicates that 
the former junction of the aft fuselage is subject to fatigue damage.
    The NPRM published in the Federal Register on June 21, 2016 (81 FR 
40210). The NPRM was prompted by the identification of four cracks in 
the fastener holes in the area of the former junction at frame (FR) 68 
between stringers 4 and 5 (left- and right-hand sides), which occurred 
during a fatigue test, and a determination that certain compliance 
times specified in AD 98-13-14 must be reduced. The NPRM proposed to 
continue to require the actions in AD 98-13-14, with revised inspection 
compliance times. We are issuing this AD to prevent fatigue cracks from 
occurring or propagating in certain structures, which could adversely 
affect the 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 
2015-0084, dated May 13, 2015; corrected May 18, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''); to correct an unsafe condition for certain Airbus Model 
A320-211, -212, and -231 airplanes. The MCAI states:

    During a fatigue test campaign, four cracks were identified in 
the fastener holes of the former junction at frame (FR) 68 between 
stringers 4 and 5.
    This condition, if not detected and corrected, could lead to 
crack propagation, possibly resulting in reduced structural 
integrity of the fuselage.
    To address this unsafe condition, DGAC [Direction 
g[eacute]n[eacute]rale de l'aviation civile] France issued * * * [an 
AD, which corresponds to FAA AD 98-13-14] to require repetitive 
inspections and, depending on findings, the accomplishment of an 
applicable repair solution.
    That [DGAC] AD also provided modification of FR 68 [cold working 
of fastener and tooling holes] in accordance with Airbus Service 
Bulletin (SB) A320-53-1090 as optional terminating action.
    Following new analyses, the thresholds and inspection intervals 
have been reviewed and adjusted.
    For the reason described above, this [EASA] AD retains the 
requirements of DGAC France AD 96-298-093(B)R2 [http://ad.easa.europa.eu/ad/F-1996-298R2], which is superseded, and 
requires those actions within the new thresholds and intervals.
    This [EASA] AD was republished to correct a typographical error 
in the Reason.

    Repairs include doing applicable related investigative actions 
(i.e., rotating probe inspection of the hole to make sure the crack is 
removed and eddy current inspection of the cold expanded holes). 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-
7262.

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 to the comment.

Request To Update Service Information

    Airbus requested that Airbus Service Bulletin A320-53-1089, 
Revision 04, dated June 1, 2016, be referred to in the final rule. This 
service information replaces a certain nondestructive test manual (NTM) 
task, removes an eddy current inspection for a certain service bulletin 
task, and updates the service bulletin airplane effectivity.
    We agree with the request and have revised paragraphs (h) and (i) 
of this AD to refer to Airbus Service Bulletin A320-53-1089, Revision 
04, dated June 1, 2016. We have also added paragraph (k)(1)(iii) to 
this AD to provide credit for Airbus Service Bulletin A320-53-1089, 
Revision 03, dated March 18, 2015.

Additional Changes to the NPRM

    We have revised paragraphs (h)(2) and (h)(3) of this AD to remove 
references to the revision level and date of the service information 
that must be used for determining the compliance time, because 
operators might have used other versions for their most recent 
inspection. The number of affected U.S. registered airplanes has also 
been changed from 10 to 4. The total cost to operators has been changed 
accordingly.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these 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.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Airbus service information:
     Service Bulletin A320-53-1089, Revision 04, dated June 1, 
2016. This service information describes procedures for a special 
detailed rototest inspection for fatigue cracking of the frame junction 
holes and the adjacent tooling hole, as applicable, of the right- and 
left-hand former junctions at FR 68, and repair, including doing 
applicable related investigative actions.
     Service Bulletin A320-53-1090, Revision 02, dated December 
22, 1998. This service information describes procedures for modifying 
the airplane (cold working of fastener and tooling 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 4 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
----------------------------------------------------------------------------------------------------------------
Initial and repetitive             8 work-hours x $85             $0  $680 per inspection   $2,720 per
 inspections [retained from AD 98-  per hour = $680 per                cycle.                inspection cycle.
 13-14].                            inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

[[Page 25942]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                 Cost per
                Action                        Labor cost          Parts cost      product
--------------------------------------------------------------------------------------------
Repair...............................  52 work-hours x $85 per        $3,800          $8,220
                                        hour = $4,420.
----------------------------------------------------------------------------------------------------------------

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 removing Airworthiness Directive (AD) 
98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998), and adding 
the following new AD:

2017-11-13 Airbus: Amendment 39-18912; Docket No. FAA-2016-7262; 
Directorate Identifier 2015-NM-079-AD.

(a) Effective Date

    This AD is effective July 11, 2017.

(b) Affected ADs

    This AD replaces AD 98-13-14, Amendment 39-10602 (63 FR 34556, 
June 25, 1998) (``AD 98-13-14'').

(c) Applicability

    This AD applies to Airbus Model A320-211, -212, and -231 
airplanes, certificated in any category, manufacturer serial numbers 
(S/Ns) 0001 through 0123 inclusive, except those that have embodied 
Airbus Modifications 21780 and 21781 in production.

(d) Subject

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

(e) Reason

    This AD was prompted by identification of four cracks in the 
fastener holes of the former junction at frame (FR) 68 between 
stringers 4 and 5, which occurred during a fatigue test, and a 
determination that certain compliance times specified in AD 98-13-14 
must be reduced. We are issuing this AD to prevent fatigue cracks 
from occurring or propagating in certain structures, which could 
adversely affect the structural integrity of the airplane.

(f) Compliance

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

(g) Retained Repetitive Inspections and Repair, With Additional Methods 
of Approving Repairs

    This paragraph restates the requirements of paragraph (a) of AD 
98-13-14, with additional methods of approving repairs. For Model 
A320 series airplanes, as listed in Airbus Service Bulletins A320-
53-1089 and A320-53-1090, both dated November 22, 1995: Prior to the 
accumulation of 20,000 total flight cycles, or within 500 flight 
cycles after July 30, 1998 (the effective date of AD 98-13-14), 
whichever occurs later, perform a rotating probe inspection for 
fatigue cracking of the fastener holes and/or the adjacent tooling 
hole, as applicable, of the right- and left-hand former junctions at 
FR 68, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1089, dated November 22, 1995. 
Accomplishing an inspection required by paragraph (h) of this AD 
terminates the actions required by this paragraph.
    (1) If no crack is detected, accomplish either paragraph 
(g)(1)(i) or (g)(1)(ii) of this AD.
    (i) Repeat the inspection thereafter at intervals not to exceed 
20,000 flight cycles; or
    (ii) Prior to further flight following the accomplishment of the 
inspection required by paragraph (g) of this AD, cold work the 
fastener holes and/or the adjacent tooling hole of the right- and 
left-hand former junctions at FR 68, as applicable, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1090, dated November 22, 1995. Accomplishment of this cold 
working constitutes terminating action for the repetitive 
inspections required by paragraph (g)(1)(i) of this AD.
    (2) If any crack is detected, prior to further flight, repair in 
accordance with 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).

(h) New Repetitive Inspection Requirement

    Within the compliance time specified in paragraph (h)(1), 
(h)(2), or (h)(3) of this AD, whichever occurs latest: Accomplish a 
special detailed rototest inspection for fatigue cracking of the 
frame junction holes and the adjacent tooling hole, as applicable, 
of the right- and left-hand former junctions at FR 68, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1089, Revision 04, dated June 1, 2016. Repeat the inspection 
thereafter at intervals not to exceed 3,800 flight cycles or 7,600 
flight hours, whichever occurs first, until a repair required by 
paragraph (i) of this AD is done or a modification specified in 
paragraph (j) of this AD is done. Accomplishing an inspection 
required by this paragraph terminates the inspections required by 
paragraph (g) of this AD.
    (1) Within 28,700 flight cycles or 57,400 flight hours since 
airplane first flight, whichever occurs first.
    (2) Within 3,800 flight cycles or 7,600 flight hours, whichever 
occurs first, since the most recent inspection done as specified in 
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1089.

[[Page 25943]]

    (3) Within 3,800 flight cycles or 7,600 flight hours after the 
effective date of this AD, whichever occurs first, without exceeding 
20,000 flight cycles since the most recent inspection done as 
specified in the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1089.

(i) New Repair Requirement

    If any crack is detected during any inspection required by 
paragraph (h) of this AD: Before further flight, repair, including 
doing all applicable related investigative actions, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1089, Revision 04, dated June 1, 2016. Do all applicable 
related investigative actions before further flight. Repair of an 
airplane in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1089, Revision 04, dated June 1, 
2016, constitutes terminating action for the repetitive inspections 
required by paragraph (h) of this AD.

(j) New Optional Modification

    Modification of an airplane, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1090, 
Revision 02, dated December 22, 1998, constitutes terminating action 
for the repetitive inspections required by paragraphs (g) and (h) of 
this AD, provided the modification is accomplished before further 
flight after accomplishing an inspection required by paragraph (h) 
of this AD and no cracks were detected.

(k) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraphs (h) and (i) of this AD, if those actions were performed 
before the effective date of this AD using the service information 
identified in paragraphs (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of 
this AD.
    (i) Airbus Service Bulletin A320-53-1089, Revision 01, dated 
June 4, 1998.
    (ii) Airbus Service Bulletin A320-53-1089, Revision 02, dated 
February 3, 2003.
    (iii) Airbus Service Bulletin A320-53-1089, Revision 03, dated 
March 18, 2015.
    (2) This paragraph provides credit for the actions required by 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using the service information identified 
in paragraphs (k)(2)(i) or (k)(2)(ii) of this AD.
    (i) Airbus Service Bulletin A320-53-1090, dated November 22, 
1995, which was incorporated by reference in AD 98-13-14, Amendment 
39-10602 (63 FR 34556, June 25, 1998).
    (ii) Airbus Service Bulletin A320-53-1090, Revision 1, dated 
June 10, 1998, which is not incorporated by reference in this AD.

(l) 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 manager of the International Branch, 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 
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): 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2015-0084, dated May 13, 2015; corrected May 18, 
2015; 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-2016-7262.
    (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.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(5) and (n)(6) 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 the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
July 11, 2017.
    (i) Airbus Service Bulletin A320-53-1089, Revision 04, dated 
June 1, 2016.
    (ii) Airbus Service Bulletin A320-53-1090, Revision 02, dated 
December 22, 1998. Pages 1, 2, 7, 8, 9, 10, and 11 of this document 
are identified as Revision 1, dated June 10, 1998; and pages 3, 4, 
5, and 6 of this document are identified as Revision 02, dated 
December 22, 1998.
    (4) The following service information was approved for IBR on 
July 30, 1998, AD 98-13-14, Amendment 39-10602 (63 FR 34556, June 
25, 1998).
    (i) Airbus Service Bulletin A320-53-1089, dated November 22, 
1995.
    (ii) Airbus Service Bulletin A320-53-1090, dated November 22, 
1995.
    (5) For service information identified in this AD, contact 
Airbus SAS, 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.
    (6) 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.
    (7) 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 May 23, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-11290 Filed 6-5-17; 8:45 am]
 BILLING CODE 4910-13-P


