[Federal Register Volume 83, Number 74 (Tuesday, April 17, 2018)]
[Proposed Rules]
[Pages 16787-16792]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-07626]


 ========================================================================
 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
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  Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / 
Proposed Rules  

[[Page 16787]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0277; Product Identifier 2017-NM-124-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2017-15-
17, which applies 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 requires an inspection of the 
lower area of a certain frame radius for cracking, and corrective 
action if necessary. Since we issued AD 2017-15-17, we have determined 
that repetitive inspections and applicable corrective actions are 
necessary. This proposed AD would add new repetitive inspections of the 
lower area of a certain frame radius for cracking, and corrective 
actions if necessary. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by June 1, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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.

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 the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0277; 
Product Identifier 2017-NM-124-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued AD 2017-15-17, Amendment 39-18977 (82 FR 35644, August 1, 
2017) (``AD 2017-15-17''), for 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 was prompted by the detection of 
cracking that originated from the fastener holes in the forward fitting 
lower radius of frame (FR) 40. AD 2017-15-17 requires an inspection of 
the lower area of a certain frame radius for cracking, and corrective 
action if necessary. We issued AD 2017-15-17 to detect and correct 
cracking in the forward fitting lower radius of FR 40. Such cracking 
could reduce the structural integrity of the fuselage.
    Since we issued AD 2017-15-17, we have determined that new 
repetitive inspections of the lower area of a certain frame radius for 
cracking, and corrective actions are necessary.
    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 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

[[Page 16788]]

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 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.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-57-6120, including 
Appendices 1 through 7, 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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 94 airplanes of U.S. 
registry.
    The actions required by AD 2017-15-17, and retained in this 
proposed 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 would take about 4 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $31,960, or $340 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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

[[Page 16789]]

FR 35644, August 1, 2017), and adding the following new AD:

Airbus: Docket No. FAA-2018-0277; Product Identifier 2017-NM-124-AD.

(a) Comments Due Date

    We must receive comments by June 1, 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 airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD, on which Airbus Modification 10221 was embodied in 
production.
    (1) Airbus Model A300 B4-605R and B4-622R airplanes.
    (2) Airbus Model A300 C4-605R Variant F airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.

(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 (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 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, including 
Appendices 1 through 7, dated April 28, 2017; except where Airbus 
Service Bulletin A300-57-6120, including Appendices 1 through 7, 
dated April 28, 2017, specifies contacting Airbus for appropriate 
action, before further flight, obtain instructions using the 
procedures specified in paragraph (l) of this AD and accomplish 
those instructions.
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(i) Repetitive Inspections for Repaired Areas

    Within the compliance time values as 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, 
including Appendices 1 through 7, dated April 28, 2017; except where 
Airbus Service Bulletin A300-57-6120, including Appendices 1 through 
7, dated April 28, 2017, specifies contacting Airbus for appropriate 
action, before further flight, obtain instructions using the 
procedures specified in paragraph (l) of this AD and accomplish 
those instructions.
[GRAPHIC] [TIFF OMITTED] TP17AP18.011

(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, including Appendices 1 through 7, dated April 
28, 2017.

(k) Reporting

    Submit a report of the findings (both positive and negative) of 
each inspection required by paragraph (h) and (i) of this AD to 
Airbus, in accordance with the instructions of Airbus Service 
Bulletin A300-57-6120, including Appendices 1 through 7, 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) 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 (m)(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: 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 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 
paragraphs (g) and (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.

(m) 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

[[Page 16792]]

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.
    (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. 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.

    Issued in Des Moines, Washington, on March 30, 2018.
Chris Spangenberg,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-07626 Filed 4-16-18; 8:45 am]
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