AD 2018-20-02

[Federal Register Volume 83, Number 189 (Friday, September 28, 2018)]
[Rules and Regulations]
[Pages 48920-48924]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2018-20951]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0455; Product Identifier 2017-NM-121-AD; Amendment 
39-19436; AD 2018-20-02]
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 superseding Airworthiness Directive (AD) 98-18-24, 
which applied to certain Airbus SAS Model A320 series airplanes. AD 98-
18-24 required repetitive inspections to detect cracking in the inner 
flange of a certain door frame, and corrective actions, if necessary. 
AD 98-18-24 also provided an optional terminating action for the 
repetitive inspections. This AD continues to require the repetitive 
inspections of the inner flange of a certain door frame, with reduced 
repetitive inspection intervals, and corrective action if necessary. 
This AD was prompted by a report of cracks on the inner flange of a 
certain door frame, and by the results of a full scale fatigue test 
that indicated the intervals for the repetitive inspections required by 
AD 98-18-24 must be reduced. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective November 2, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 2, 
2018.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EIAS, 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 <a href="/cdn-cgi/l/email-protection#5c3d3f3f33293228723d352e2b332e283471393d2f1c3d352e3e292f723f3331"><span class="__cf_email__" data-cfemail="6c0d0f0f03190218420d051e1b031e180441090d1f2c0d051e0e191f420f0301">[email&#160;protected]</span></a>; 
internet <a href="http://www.airbus.com">http://www.airbus.com</a>. You may view this referenced service 
information at the FAA, Transport 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating 
Docket No. FAA-2018-0455.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2018-
0455; 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: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA; 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 98-18-24, Amendment 39-10740 (63 FR 49272, 
September 15, 1998) (``AD 98-18-24''). AD 98-18-24 applied to certain 
Airbus SAS Model A320 series airplanes. The NPRM published in the 
Federal Register on May 30, 2018 (83 FR 24690). The NPRM was prompted 
by a report of cracks on the inner flange of door frame 66 at stringer 
positions 18 and 20, and by the results of a full scale fatigue test 
that indicated the intervals for the repetitive inspections required by 
AD 98-18-24 must be reduced. The NPRM

[[Page 48921]]

proposed to continue to require the repetitive inspections of the inner 
flange of a certain door frame, with reduced repetitive inspection 
intervals, and corrective actions if necessary. We are issuing this AD 
to address fatigue cracking in the inner flange of door frame 66, 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 
2017-0128, dated July 24, 2017 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Airbus SAS Model A320-211 and A320-231 
airplanes. The MCAI states:

    During fatigue test on simulated flights, cracks developed on 
the inner flange of door frame 66 at stringer 18 and 20 positions. 
These cracks were located in the gusset plate attachment holes and 
were hidden by the plates.
    This condition, if not detected and corrected, could affect the 
structural integrity of the fuselage.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-53-1071, later revised, to provide 
instructions to inspect and repair the gusset plate attachment holes 
at frame 66, at stringers 18, 20 and 22 both left hand (LH) and 
right hand (RH) side of the fuselage (hereafter collectively 
referred to as ``the attachment holes'' in this [EASA] AD), and 
[Airbus] SB A320-53-1072, providing instructions for reworking of 
the attachment holes.
    Consequently, DGAC France issued [French] AD 1996-234-087, later 
revised [which corresponds to FAA AD 98-18-24], requiring repetitive 
inspections and, depending on findings, repair of the attachment 
holes, and including reference to a reworking procedure, which 
constitutes optional terminating action for the repetitive 
inspections of the attachment holes.
    Since that [French] AD was issued, based on results from a full 
scale fatigue test, it was determined that the inspection intervals 
must be reduced. Airbus issued SB A320-53-1071 Revision 03, 
modifying the inspection threshold and intervals, and not changing 
the inspection instructions.
    For the reason described above, this [EASA] AD retains the 
requirement of DGAC France AD 1996-234-087 R1, which is superseded, 
and requires reduction of the repetitive inspection interval.

    You may examine the MCAI in the AD docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2018-
0455.

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

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1071, Revision 03, dated 
July 20, 2017. This service information describes procedures for 
detailed inspections of the gusset plate attachment holes at door frame 
66 for cracking and corrective action.
    Airbus also issued Service Bulletin A320-53-1072, Revision 02, 
dated May 5, 2016. This service information describes procedures for 
modification of the gusset frame attachment at door frame 66.
    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 3 airplanes of U.S. registry.
    The actions required by AD 98-18-24, and retained in this AD, take 
about 8 work-hours per product, at an average labor rate of $85 per 
work-hour. Based on these figures, the estimated cost of the actions 
that are required by AD 98-18-24 is $680 per product.
    We estimate that it would take about 19 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $4,845, or $1,615 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.
    In addition, we estimate that the optional terminating action would 
take about 20 work-hours per product, at an average labor rate of $85 
per work-hour. Required parts costs would be about $60. Based on these 
figures, the estimated cost of the optional terminating action would be 
$1,760 per product.
    We also estimate that it would take about 1 work-hour per product 
to comply with the proposed reporting requirement in this AD. The 
average labor rate is $85 per hour. Based on these figures, we estimate 
the cost of reporting the inspection results on U.S. operators to be 
$255, or $85 per product.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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

[[Page 48922]]

delegated the authority to issue ADs applicable to transport category 
airplanes and associated appliances 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 removing Airworthiness Directive (AD) 
98-18-24, Amendment 39-10740 (63 FR 49272, September 15, 1998), and 
adding the following new AD:

2018-20-02 Airbus SAS: Amendment 39-19436; Docket No. FAA-2018-0455; 
Product Identifier 2017-NM-121-AD.

(a) Effective Date

    This AD is effective November 2, 2018.

(b) Affected ADs

    This AD replaces AD 98-18-24, Amendment 39-10740 (63 FR 49272, 
September 15, 1998) (``AD 98-18-24'').

(c) Applicability

    This AD applies to Airbus SAS Model A320-211 and Model A320-231 
airplanes, certificated in any category, serial numbers 0029, 0045, 
0046, 0049 through 0057 inclusive, 0059, 0064, and 0065.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of cracks on the inner flange 
of door frame 66 at stringer positions 18 and 20, and by the results 
of a full scale fatigue test that indicated the intervals for the 
repetitive inspections required by AD 98-18-24 must be reduced. We 
are issuing this AD to address fatigue cracking in the inner flange 
of door frame 66, 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) Retained Eddy Current Inspection, With No Changes

    This paragraph restates the requirements of paragraph (a) of AD 
98-18-24, with no changes. For Model A320 series airplanes on which 
Airbus Modification 21778 (reference Airbus Service Bulletin A320-
53-1072, dated November 7, 1995, as revised by Change Notice 0A, 
dated July 5, 1996) has not been accomplished: Prior to the 
accumulation of 20,000 total flight cycles, or within 1 year after 
October 20, 1998 (the effective date of AD 98-18-24), whichever 
occurs later: Perform a rotating probe eddy current inspection to 
detect cracking around the edges of the gusset plate attachment 
holes of the inner flange of door frame 66, left and right, at 
stringer positions P18, P20, and P22, in accordance with Airbus 
Service Bulletin A320-53-1071, dated November 7, 1995, as revised by 
Change Notice 0A, dated July 5, 1996. If any crack is detected, 
prior to further flight, repair in accordance with a method approved 
by the Manager, International Section, Transport Standards Branch, 
FAA. Repeat the inspection thereafter at intervals not to exceed 
20,000 flight cycles.

(h) Retained Optional Terminating Action, With No Changes

    This paragraph restates the optional terminating action of 
paragraph (b) of AD 98-18-24, with no changes. Modification of the 
gusset plate attachment holes of the inner flange of door frame 66, 
left and right (Airbus Modification 21778), in accordance with 
Airbus Service Bulletin A320-53-1072, dated November 7, 1995, as 
revised by Change Notice 0A, dated July 5, 1996, constitutes 
terminating action for the repetitive inspection requirements of 
paragraph (g) of this AD.

(i) New Requirement of This AD: Repetitive Inspections

    At the applicable compliance time specified in figure 1 to 
paragraph (i) of this AD, do a rotating probe eddy current 
inspection to detect cracking around the edges of the gusset plate 
attachment holes of the inner flange of door frame 66, left and 
right, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017. 
Repeat the inspection thereafter at intervals not to exceed 10,900 
flight cycles.

[[Page 48923]]

[GRAPHIC] [TIFF OMITTED] TR28SE18.001

(j) Corrective Actions

    (1) If, during any inspection required by paragraph (i) of this 
AD, any crack is found on a gusset plate attachment hole: Before 
further flight, repair the affected attachment hole, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1071, Revision 03, dated July 20, 2017, except as required 
by paragraph (n) of this AD.
    (2) If, during any inspection required by paragraph (i) of this 
AD, any crack is found on any other hole of the gusset plate: Before 
further flight, contact the Manager, International Section, 
Transport Standards Branch, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA); 
for approved repair instructions and accomplish those instructions 
accordingly. If approved by the DOA, the approval must include the 
DOA-authorized signature.

(k) Terminating Action for This AD

    (1) Repair of a gusset plate attachment hole area as required by 
paragraph (j)(1) of this AD terminates the repetitive inspections 
required by paragraph (i) of this AD for that attachment hole area 
on that airplane only.
    (2) Repair of any other hole of the gusset plate, as required by 
paragraph (j)(2) of this AD, does not terminate the repetitive 
inspections required by paragraph (i) of this AD for that airplane, 
unless specified otherwise in the repair instructions provided by 
the Manager, International Section, Transport Standards Branch, FAA; 
or the EASA; or Airbus's EASA DOA.
    (3) Accomplishing the initial inspection required by paragraph 
(i) of this AD terminates the inspections required by paragraph (g) 
of this AD.

(l) Optional Modification

    Modification of the gusset plate attachment holes of the inner 
flange of door frame 66, left and right, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1072, 
Revision 02, dated May 5, 2016, terminates the repetitive 
inspections required by paragraph (i) of this AD for that airplane.

(m) Reporting

    Report the results of the inspection required by paragraph (i) 
of this AD that are done on or after the effective date of this AD 
to Airbus Service Bulletin Reporting Online Application on Airbus 
World (<a href="https://w3.airbus.com/">https://w3.airbus.com/</a>), or submit the results to Airbus in 
accordance with the instructions of Airbus Service Bulletin A320-53-
1071, Revision 03, dated July 20, 2017. Submit the report within 30 
days after accomplishing the inspection required by paragraph (i) of 
this AD. The report must include the inspection results, a 
description of any discrepancies found, the airplane serial number, 
and the number of landings and flight hours on the airplane. If 
operators have reported findings as part of obtaining any corrective 
actions approved by the EASA DOA, operators are not required to 
report those findings as specified in this paragraph.

(n) Service Information Exception

    Where Airbus Service Bulletin A320-53-1071, Revision 03, dated 
July 20, 2017, 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 (q)(2) of this AD.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-53-
1071, Revision 01, dated July 4, 2002; or Airbus Service Bulletin 
A320-53-1071, Revision 02, dated May 5, 2016.
    (2) This paragraph provides credit for actions identified in 
paragraph (l) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-53-
1072, dated November 7, 1995, as revised by Change Notice 0A, dated 
July 5, 1996; or Airbus Service Bulletin A320-53-1072, Revision 01, 
dated July 4, 2002.

(p) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to

[[Page 48924]]

respond to, nor shall a person be subject to a penalty for failure 
to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection 
of information displays a current valid OMB Control Number. The OMB 
Control Number for this information collection is 2120-0056. Public 
reporting for this collection of information is estimated to be 
approximately 1 hour per response, including the time for reviewing 
instructions, completing and reviewing the collection of 
information. All responses to this collection of information are 
mandatory. Comments concerning the accuracy of this burden and 
suggestions for reducing the burden should be directed to the FAA 
at: 800 Independence Ave. SW, Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(q) Other FAA AD Provisions

    (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 (r)(2) of this AD. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#81b8acc0cfccacb0b0b7acc0cccec2acd3c4d0d4c4d2d5d2c1e7e0e0afe6eef7"><span class="__cf_email__" data-cfemail="cbf2e68a8586e6fafafde68a868488e6998e9a9e8e989f988badaaaae5aca4bd">[email&#160;protected]</span></a>.
    (i) 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.
    (ii) AMOCs approved previously for AD 98-18-24 are approved as 
AMOCs for the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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): Except as required by 
paragraph (n) 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.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0128, dated July 24, 2017, for related 
information. This MCAI may be found in the AD docket on the internet 
at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket 
No. FAA-2018-0455.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA; 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (s)(3) and (s)(4) of this AD.

(s) 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 A320-53-1071, Revision 03, dated 
July 20, 2017.
    (ii) Airbus Service Bulletin A320-53-1072, Revision 02, dated 
May 5, 2016.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EIAS, 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 <a href="/cdn-cgi/l/email-protection#9cfdfffff3e9f2e8b2fdf5eeebf3eee8f4b1f9fdefdcfdf5eefee9efb2fff3f1"><span class="__cf_email__" data-cfemail="85e4e6e6eaf0ebf1abe4ecf7f2eaf7f1eda8e0e4f6c5e4ecf7e7f0f6abe6eae8">[email&#160;protected]</span></a>; internet 
<a href="http://www.airbus.com">http://www.airbus.com</a>.
    (4) You may view this service information at the FAA, Transport 
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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Des Moines, Washington, on September 13, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-20951 Filed 9-27-18; 8:45 am]
BILLING CODE 4910-13-P