Document ID: FAA-2019-0441-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus SAS Airplanes
Posted Date: 2019-06-17T04:00Z

[Federal Register Volume 84, Number 116 (Monday, June 17, 2019)]
[Proposed Rules]
[Pages 27990-27994]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-12664]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0441; Product Identifier 2019-NM-036-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 27991]]

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2000-03-
20 R1, which applies to all Airbus SAS Model A300 B4-601, B4-603, and 
B4-620, Model A300 B4-600R series, and Model A300 F4-605R airplanes. AD 
2000-03-20 R1 requires repetitive ultrasonic inspections to detect 
cracks on the forward fittings in the radius of a certain frame, 
adjacent to the tension bolts in the center section of the wings, and 
various follow-on actions. Since we issued AD 2000-03-20 R1, we have 
determined that the existing compliance times must be reduced. This 
proposed AD would retain the requirements of AD 2000-03-20 R1, add new 
airplanes to the applicability, and introduce new compliance times for 
the required inspections as specified in a European Aviation Safety 
Agency (EASA) AD, which will be incorporated by reference. We are 
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by August 1, 2019.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For the material identified in this proposed AD that will be 
incorporated by reference (IBR), contact the EASA, Konrad-Adenauer-Ufer 
3, 50668 Cologne, Germany; telephone +49 221 89990 1000; email 
ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this IBR 
material on the EASA website at https://ad.easa.europa.eu. You may view 
this IBR material 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 in the AD 
docket on the internet at http://www.regulations.gov.

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-2019-
0441; 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 NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations is listed above. 
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 proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2019-0441; 
Product Identifier 2019-NM-036-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM 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 NPRM.

Discussion

    We issued AD 2000-03-20 R1, Amendment 39-12298 (66 FR 34530, June 
29, 2001) (``AD 2000-03-20 R1''), for all Airbus SAS Model A300 B4-601, 
B4-603, and B4-620, Model A300 B4-600R series, and Model A300 F4-605R 
airplanes. AD 2000-03-20 R1 requires repetitive ultrasonic inspections 
to detect cracks on the forward fittings in the radius of frame 40, 
adjacent to the tension bolts in the center section of the wings, and 
various follow-on actions. AD 2000-03-20 R1 resulted from reports of 
cracking due to fatigue-related stress in the radius of frame 40 
adjacent to the tension bolts at the center/outer wing junction. We 
issued AD 2000-03-20 R1 to address fatigue cracking on the forward 
fittings in the radius of frame 40 adjacent to the tension bolts in the 
center section of the wings, which could result in reduced structural 
integrity of the wings.

Actions Since AD 2000-03-20 R1 Was Issued

    Since we issued AD 2000-03-20 R1, we have determined that the 
existing compliance times must be reduced.
    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2019-0044, dated March 7, 2019 
(``EASA AD 2019-0044'') (also referred to as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Airbus SAS Model A300 B4-600 series, Model A300 
B4-600R series, Model A300 F4-605R, and Model A300 C4-605R Variant F 
airplanes. The MCAI states:

    During sampling inspection on A300 fleet, cracks were reported 
in the radius of frame (FR) 40, adjacent to the tension bolts at the 
centre wing/outer wing.
    This condition, if not detected and corrected, could lead to a 
reduction of the residual strength of the structure and lead to 
extensive repairs.
    Prompted by these findings and to address this potential unsafe 
condition on A300-600 fleet, Airbus issued [service bulletin] SB 
A300-57-6062 to provide inspection instructions. Consequently, 
[Direction Generale de l'Aviation Civile] DGAC France published AD 
95-063-177 [which corresponds to FAA AD 2000-03-20 R1] for A300-600 
aeroplanes (except A300F4-622R), followed by AD 98-040-012 for A300-
600ST aeroplanes (both ADs later revised) to require initial and 
repetitive ultrasonic test (UT) and high-frequency eddy current 
(HFEC) inspections and, depending on findings, accomplishment of 
applicable corrective action(s). Depending on a crack finding, 
Airbus SB A300-57-6062 instructs to accomplish a repair per SB A300-
57-6084 to restore FR40 strength capability. That SB does not apply 
to A300-600ST aeroplanes.
    Since DGAC France AD 1998-040-012(B) R1 and AD F-1995-063-177 R5 
(EASA approval 2003-662) were issued, material data used in the 
frame of fatigue and damage tolerance analysis have been changed. It 
was determined that the existing threshold and interval values must 
be reduced. Consequently, Airbus revised SB A300-57-6062 to Revision 
05 to take into account the new thresholds and intervals. Airbus 
also issued SB A300-57-9036, specifically for A300-600ST aeroplanes.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 1998-040-012(B) R1 and AD F-1995-063-
177 R5, which are superseded, and introduces new thresholds and 
intervals for the required inspections [and adds Model A300 B4-622 
and A300 C4-605 R Variant F airplanes to the applicability].

    The initial compliance time for airplanes on which Airbus Service 
Bulletin A300-57-6048 has not been embodied is before 7,600 total 
flight

[[Page 27992]]

cycles. The initial compliance time for airplanes on which Airbus 
Service Bulletin A300-57-6048 has been embodied is before 11,100 total 
flight cycles.

Explanation of Retained Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 2000-03-20 R1, this proposed AD would retain all of 
the requirements of AD 2000-03-20 R1. Those requirements are referenced 
in EASA AD 2019-0044, which, in turn, is referenced in paragraph (g) of 
this proposed AD.

Explanation of Change to Credit Service Information

    Note 2 of AD 2000-03-20 R1 provides credit for inspections 
accomplished using Airbus Service Bulletin A300-57-6062, Revision 1, 
dated July 23, 1995. However, EASA AD 2019-0044 does not include credit 
for Airbus Service Bulletin A300-57-6062, Revision 1, dated July 23, 
1995. Therefore, this proposed AD would not include that credit.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2019-0044 describes procedures for initial and repetitive 
UT and HFEC inspections and applicable corrective actions. Corrective 
actions include reworking the fuselage lateral panel at frame 40, 
blending out around cracks, and repair. This material 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 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.

Proposed Requirements of this NPRM

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2019-0044 described previously, as incorporated by 
reference, except for any differences identified as exceptions in the 
regulatory text of this AD. This proposed AD also adds Model A300 B4-
622 and A300 C4-605 R Variant F airplanes to the applicability. This 
proposed AD also would require sending the inspection results to 
Airbus.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA worked with Airbus and EASA to develop a process to 
use certain EASA ADs as the primary source of information for 
compliance with requirements for corresponding FAA ADs. As a result, 
EASA AD 2019-0044 will be incorporated by reference in the FAA final 
rule. This proposed AD would, therefore, require compliance with the 
provisions specified in EASA AD 2019-0044, except for any differences 
identified as exceptions in the regulatory text of this proposed AD. 
Service information specified in EASA AD 2019-0044 that is required for 
compliance with EASA AD 2019-0044 will be available on the internet 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2019-0441 after the FAA final rule is published.

Costs of Compliance

    We estimate that this proposed AD affects 65 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                     Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2000-03-20  2 work-hours x $85 per hour              $0            $170         $11,050
 R1.                                  = $170.
New proposed actions...............  161 work-hours x $85 per                  0          13,685         889,525
                                      hour = $13,685.
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* Table does not include estimated costs for reporting.

    We estimate that it would take about 1 work-hour per product to 
comply with the proposed reporting requirement in this proposed 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 
$5,525, or $85 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 NPRM is 2120-
0056. The paperwork cost associated with this NPRM 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 NPRM 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 proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance

[[Page 27993]]

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 and associated appliances 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. Will not affect intrastate aviation in Alaska; and
    3. 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) 
2000-03-20 R1, Amendment 39-12298 (66 FR 34530, June 29, 2001), and 
adding the following new AD:

Airbus SAS: Docket No. FAA-2019-0441; Product Identifier 2019-NM-
036-AD.

(a) Comments Due Date

    We must receive comments by August 1, 2019.

(b) Affected ADs

    This AD replaces AD 2000-03-20 R1, Amendment 39-12298 (66 FR 
34530, June 29, 2001) (``AD 2000-03-20 R1'').

(c) Applicability

    This AD applies to Airbus SAS airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any 
category, as identified in European Aviation Safety Agency (EASA) 
2019-0044, dated March 7, 2019 (``EASA AD 2019-0044'').
    (1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (2) Model A300 B4-605R and B4-622R airplanes.
    (3) Model A300 F4-605R airplanes.
    (4) Model A300 C4-605R Variant F airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracking due to fatigue-
related stress in the radius of frame 40, adjacent to the tension 
bolts at the center/outer wing junction. We are issuing this AD to 
address fatigue cracking on the forward fittings in the radius of 
frame 40, adjacent to the tension bolts in the center section of the 
wings, which could result in reduced structural integrity of the 
wings.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2019-0044.

(h) Exceptions to EASA AD 2019-0044

    (1) For purposes of determining compliance with the requirements 
of this AD: Where EASA AD 2019-0044 refers to its effective date, 
this AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2019-0044 does not apply 
to this AD.
    (3) Paragraph (5) of EASA AD 2019-0044 specifies to report all 
inspection results to Airbus. For this AD, report all inspection 
results to Airbus Service Bulletin Reporting Online Application on 
Airbus World (https://w3.airbus.com/) at the applicable time 
specified in paragraph (h)(3)(i) or (h)(3)(ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (ii) 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.
    (4) For Model A300 B4-622 and A300 C4-605 R Variant F airplanes: 
The initial compliance time for the inspections required by EASA AD 
2019-0044 is at the applicable time specified in EASA AD 2019-0044, 
or within 12 months after the effective date of this AD, whichever 
occurs later.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (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 (j)(2) of this AD. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (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 2000-03-20 R1 are approved 
as AMOCs for the corresponding provisions of EASA AD 2019-0044 that 
are required by paragraph (g) of this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or 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): For any service information 
referenced in EASA AD 2019-0044 that contains RC procedures and 
tests: Except as required by paragraph (i)(2) of this AD, RC 
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.
    (4) 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.

[[Page 27994]]

(j) Related Information

    (1) For information about EASA AD 2019-0044, contact the EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
89990 6017; email ADs@easa.europa.eu; Internet www.easa.europa.eu. 
You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. You may view this EASA AD 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. EASA AD 2019-0044 may be found in the AD docket on the 
internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2019-0441.
    (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.

    Issued in Des Moines, Washington, on June 10, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-12664 Filed 6-14-19; 8:45 am]
 BILLING CODE 4910-13-P