[Federal Register Volume 83, Number 161 (Monday, August 20, 2018)]
[Rules and Regulations]
[Pages 42017-42022]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-17752]



========================================================================
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. 161 / Monday, August 20, 2018 / Rules 
and Regulations

[[Page 42017]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0277; Product Identifier 2017-NM-124-AD; Amendment 
39-19364; AD 2018-17-10]
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) 2017-15-17, 
which applied to certain Airbus Model A300 B4-600R series airplanes, 
Model A300 C4-605R Variant F airplanes, and Model A300 F4-600R series 
airplanes. AD 2017-15-17 required an inspection of the lower area of a 
certain frame (FR) radius for cracking, and corrective action if 
necessary. This AD requires new repetitive inspections of the forward 
fitting lower radius of a certain frame for cracking, and corrective 
actions if necessary. This AD was prompted by a determination that 
repetitive inspections and applicable corrective actions are necessary. 
We are issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective September 24, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 5, 
2017 (82 FR 35644, August 1, 2017).

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 <a href="/cdn-cgi/l/email-protection#563735353923382278373f24213924223e7b33372516373f243423257835393b"><span class="__cf_email__" data-cfemail="741517171b011a005a151d06031b06001c5911150734151d061601075a171b19">[email protected]</span></a>; 
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-2018-0277.

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-
0277; 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 in the ADDRESSES section.

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 to supersede AD 2017-15-17, Amendment 39-18977 (82 FR 35644, 
August 1, 2017) (``AD 2017-15-17''). AD 2017-15-17 applied to certain 
Airbus Model A300 B4-600R series airplanes, Model A300 C4-605R Variant 
F airplanes, and Model A300 F4-600R series airplanes. The NPRM 
published in the Federal Register on April 17, 2018 (83 FR 16787). The 
NPRM was prompted by a determination that new repetitive inspections of 
the lower area of a certain frame radius for cracking, and corrective 
actions are necessary. The NPRM proposed to require an inspection of 
the lower area of a certain frame radius for cracking, and corrective 
action if necessary. The NPRM also proposed to add new repetitive 
inspections of the lower area of a certain frame radius for cracking, 
and corrective actions if necessary. We are issuing this AD to detect 
and correct cracking in the forward fitting lower radius of a certain 
frame. Such cracking could reduce the structural integrity of the 
fuselage.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0158, dated August 25, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus SAS Model A300 B4-600R 
series airplanes, Model A300 C4-605R Variant F airplanes, and Model 
A300 F4-600R series airplanes. The MCAI states:

    Following a full stress analysis of the Frame (FR) 40 lower 
area, supported by a Finite Element Model (FEM), of the post-mod 
[modification] 10221 configuration, it was demonstrated that, for 
the FR40 forward fitting lower radius, a crack could occur after a 
certain number of flight cycles (FC).
    This condition, if not detected and corrected, could reduce the 
structural integrity of the fuselage.
    To address this potential unsafe condition, Airbus established 
that crack detection could be achieved through a special detailed 
inspection (SDI) using a high frequency eddy current (HFEC) method, 
and issued Alert Operators Transmission (AOT) A57W009-16 to provide 
those inspection instructions.
    Consequently, EASA issued AD 2016-0085 to require a one-time SDI 
of the FR40 lower area and, depending on findings, accomplishment of 
applicable corrective action(s). After that [EASA] AD was issued, 
further cracks were detected, originating from the fastener hole, 
and, based on these findings, it was determined that the inspection 
area must be enlarged, and Airbus issued AOT A57W009-16 Revision 
(Rev.) 01 accordingly. Consequently, EASA issued AD 2016-0179 [which 
corresponds to FAA AD 2017-15-17], retaining the requirements of 
EASA AD 2016-0085, which was superseded, to extend the area of 
inspection, and to require an additional inspection for aeroplanes 
that were previously inspected.
    The one-time SDI for high cycle A300-600 aeroplanes was intended 
to mitigate the highest risks within the fleet, pending development 
of instructions for repetitive inspections.
    Since EASA AD 2016-0179 was issued, Airbus published SB A300-57-
6120 * * * [for] the inspection programme for A300-600 * * * post-
mod 10221 * * * [airplanes]. The AOT one-time inspection is 
superseded by these repetitive inspection SBs. These SBs include 
alternative inspection methods and repair solutions in case of 
findings together with the associated inspection programme.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2016-0179, which is superseded, * * * and 
defines new inspections methods with

[[Page 42018]]

new compliance times, including repetitive inspections, depending on 
the aeroplane inspection status.

    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-
0277.

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 SAS has issued Service Bulletin A300-57-6120, dated April 
28, 2017. This service information describes procedures for repetitive 
inspections of the forward fitting lower radius of FR 40 for cracking, 
and corrective action. 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 94 airplanes of U.S. registry.
    The actions required by AD 2017-15-17, and retained in this AD, 
take about 4 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 2017-15-17 is $340 per product.
    We also estimate that it takes about 4 work-hours per product to 
comply with the new requirements of this AD, including 1 work-hour per 
product for reporting. 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 $39,950, or $425 per product.
    We have received no definitive data that enables us to provide cost 
estimates for the on-condition actions specified in this AD.

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 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 removing Airworthiness Directive (AD) 
2017-15-17, Amendment 39-18977 (82 FR 35644, August 1, 2017), and 
adding the following new AD:

2018-17-10 Airbus SAS: Amendment 39-19364; Docket No. FAA-2018-0277; 
Product Identifier 2017-NM-124-AD.

(a) Effective Date

    This AD is effective September 24, 2018.

(b) Affected ADs

    This AD replaces AD 2017-15-17, Amendment 39-18977 (82 FR 35644, 
August 1, 2017) (``AD 2017-15-17'').

(c) Applicability

    This AD applies to Airbus SAS airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD, on which Airbus SAS Modification 10221 was embodied in 
production.
    (1) Airbus SAS Model A300 B4-605R and B4-622R airplanes.
    (2) Airbus SAS Model A300 C4-605R Variant F airplanes.
    (3) Airbus SAS Model A300 F4-605R and F4-622R airplanes.

[[Page 42019]]

(d) Subject

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

(e) Reason

    This AD was prompted by the detection of cracking that 
originated from the fastener holes in the forward fitting lower 
radius of frame (FR) 40. We are issuing this AD to detect and 
correct cracking in the forward fitting lower radius of FR 40. Such 
cracking could reduce the structural integrity of the fuselage.

(f) Compliance

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

(g) Definitions

    (1) For the purpose of this AD, the average flight time (AFT) 
can be established by dividing the flight hours (FHs) by the flight 
cycles (FCs) counted:
    (i) From first flight, for selecting the inspection threshold of 
the non-repaired area.
    (ii) From repair, for selecting the inspection threshold of the 
repaired area.
    (iii) From the last inspection, for selecting the inspection 
interval.
    (2) For the purpose of this AD, Group 1 airplanes are those 
airplanes already inspected in accordance with paragraph 4.2.2 in 
Alert Operators Transmission (AOT) A57W009-16, Revision 01, dated 
July 13, 2016, before the effective date of this AD. Group 2 
airplanes are those airplanes not inspected in accordance with 
paragraph 4.2.2 in AOT A57W009-16, Revision 01, dated July 13, 2016, 
as of the effective date of this AD.
    (3) For the purpose of this AD, inspection method A is a high 
frequency eddy current (HFEC) inspection of the radius and fastener 
area. Inspection method B is a HFEC inspection of the radius and 
fastener area and a rototest of the fastener hole. Both are defined 
as a special detailed inspection (SDI) in this AD.

(h) Repetitive Inspections for Non-Repaired Areas

    Within the compliance time values specified in table 1 to 
paragraph (h) of this AD (Group 1 airplanes) or table 2 to paragraph 
(h) of this AD (Group 2 airplanes), as applicable, and, thereafter, 
at intervals not exceeding the values specified in table 3 to 
paragraph (h) of this AD: Do a SDI for cracking of any non-repaired 
radius, fastener areas, and fastener holes, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6120, 
dated April 28, 2017; except where Airbus Service Bulletin A300-57-
6120, dated April 28, 2017, specifies contacting Airbus SAS for 
appropriate action, before further flight, obtain instructions using 
the procedures specified in paragraph (m)(2) of this AD and 
accomplish those instructions.

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(i) Repetitive Inspections for Repaired Areas

    Within the compliance time values specified in table 4 to 
paragraph (i) of this AD, and, thereafter, at intervals not 
exceeding those same values, do a SDI for cracking of the repaired 
radius, fastener areas, and fastener holes, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6120, 
dated April 28, 2017; except where Airbus Service Bulletin A300-57-
6120, dated April 28, 2017, specifies contacting Airbus SAS for 
appropriate action, before further flight, obtain instructions using 
the procedures specified in paragraph (m)(2) of this AD and 
accomplish those instructions.
[GRAPHIC] [TIFF OMITTED] TR20AU18.004

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(j) Corrective Action

    If any crack is found during any inspection required by 
paragraph (h) or (i) of this AD: Before further flight, repair in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6120, dated April 28, 2017.

(k) Reporting

    Submit a report of the findings (both positive and negative) of 
each inspection required by paragraphs (h) and (i) of this AD to 
Airbus SAS, in accordance with the instructions of Airbus Service 
Bulletin A300-57-6120, dated April 28, 2017, at the applicable time 
specified in paragraph (k)(1) or (k)(2) of this AD.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(l) Paperwork Reduction Act Burden Statement

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

(m) 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 (n)(2) of this AD. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#2910046867640418181f046864666a047b6c787c6c7a7d7a694f4848074e465f"><span class="__cf_email__" data-cfemail="0f36224e4142223e3e39224e42404c225d4a5e5a4a5c5b5c4f696e6e21686079">[email protected]</span></a>. 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: 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

[[Page 42022]]

the Manager, International Section, Transport Standards Branch, FAA; 
or the European Aviation Safety Agency (EASA); or Airbus SAS'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 
paragraphs (h) and (i) 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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0158, dated August 25, 
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-2018-0277.
    (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.

(o) 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.
    (3) The following service information was approved for IBR on 
September 5, 2017 (82 FR 35644, August 1, 2017).
    (i) Airbus Service Bulletin A300-57-6120, dated April 28, 2017.
    (ii) Reserved.
    (4) 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 <a href="/cdn-cgi/l/email-protection#86e7e5e5e9f3e8f2a8e7eff4f1e9f4f2eeabe3e7f5c6e7eff4e4f3f5a8e5e9eb"><span class="__cf_email__" data-cfemail="f796949498829983d9969e85809885839fda929684b7969e85958284d994989a">[email protected]</span></a>; 
internet http://www.airbus.com.
    (5) 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.
    (6) 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 August 9, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-17752 Filed 8-17-18; 8:45 am]
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