Document ID: FAA-2016-9572-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2017-03-13T04:00Z

[Federal Register Volume 82, Number 47 (Monday, March 13, 2017)]
[Proposed Rules]
[Pages 13405-13407]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03032]

 ========================================================================
 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. 82, No. 47 / Monday, March 13, 2017 / 
Proposed Rules  

[[Page 13405]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9572; Directorate Identifier 2016-NM-151-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) 2014-08-
02 for certain Airbus Model A300 B4-600 and A300 B4-600R series 
airplanes. AD 2014-08-02 requires modifying the profile of stringer 
run-outs of both wings, including a high frequency eddy current (HFEC) 
inspection of the fastener holes for defects, and repairs if necessary. 
Since we issued AD 2014-08-02, further analysis in the context of 
widespread fatigue damage (WFD) concluded that a shorter compliance 
time is necessary to meet specified requirements to address WFD. This 
proposed AD would retain the actions required by AD 2014-08-02 and 
would revise the compliance times. We are proposing this AD to address 
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by April 27, 2017.

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 account.airworth-eas@airbus.com; Internet: http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9572; 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 Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

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-2016-9572; 
Directorate Identifier 2016-NM-151-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

    Fatigue damage can occur locally, in small areas or structural 
design details, or globally, in widespread areas. Multiple-site damage 
is widespread damage that occurs in a large structural element such as 
a single rivet line of a lap splice joining two large skin panels. 
Widespread damage can also occur in multiple elements such as adjacent 
frames or stringers. Multiple-site damage and multiple-element damage 
cracks are typically too small initially to be reliably detected with 
normal inspection methods. Without intervention, these cracks will 
grow, and eventually compromise the structural integrity of the 
airplane. This condition is known as widespread fatigue damage. It is 
associated with general degradation of large areas of structure with 
similar structural details and stress levels. As an airplane ages, WFD 
will likely occur, and will certainly occur if the airplane is operated 
long enough without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that design 
approval holders (DAHs) establish a limit of validity (LOV) of the 
engineering data that support the structural maintenance program. 
Operators affected by the WFD rule may not fly an airplane beyond its 
LOV, unless an extended LOV is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.

[[Page 13406]]

    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    On April 2, 2014, we issued AD 2014-08-02, Amendment 39-17826 (79 
FR 21392, April 16, 2014) (``AD 2014-08-02''), for certain Airbus Model 
A300 B4-600 and A300 B4-600R series airplanes. AD 2014-08-02 was 
prompted by reports of cracks found in certain bottom wing skin 
stringers during full-scale fatigue testing and in service. AD 2014-08-
02 requires modifying the profile of stringer run-outs of both wings, 
including a high frequency eddy current inspection of the fastener 
holes for defects, and repairs if necessary. We issued AD 2014-08-02 to 
prevent cracking in the bottom wing skin stringers, which could result 
in reduced structural integrity of the wings.
    Since we issued AD 2014-08-02, further analysis in the context of 
WFD concluded that a shorter compliance time is necessary to meet 
specified requirements to address WFD.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0174, dated August 30, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 B4-600 and A300 B4-600R series airplanes. The MCAI states:

    During full-scale fatigue testing, cracks were detected in the 
bottom wing skin stringers at Rib 14. In addition, operators have 
also reported finding cracks in the same area on in-service 
aeroplanes.
    This condition, if not detected and corrected, could impair the 
structural integrity of the wings.
    Additional analysis results showed that the improved design of 
the stringer run-out was necessary for aeroplanes operating beyond 
the Extended Service Goal 1.
    To address this unsafe condition, Airbus issued Service Bulletin 
(SB) A300-57-6046 Revision 01 to provide modification instructions, 
and EASA issued AD 2013-0008 (later revised) [which corresponds to 
FAA AD 2014-08-02], to require the removal of the stringer end run-
out plate at stringer 19 on the bottom wing skin and a re-profiling 
modification of the stringers 10, 11, 12, 17 and 19.
    Since that [EASA] AD was issued, further analysis in the context 
of Widespread Fatigue Damage (WFD), concluded that a threshold 
reduction is necessary to meet the WFD requirements. Consequently, 
Airbus revised SB A300-57-6046 accordingly (now at Revision 03).
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2013-0008R1, which is superseded, but 
reduces the modification threshold, and introduces a pre-mod High 
Frequency Eddy Current (HFEC) inspection.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9572.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-57-6046, Revision 03, 
including Appendix 01, dated February 4, 2015. The service information 
describes procedures to modify the profile of stringer run-outs of both 
wings, including a HFEC inspection of the fastener holes for defects, 
and repairs. It also describes new compliance times for completing the 
modifications. 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 these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 29 airplanes of U.S. 
registry.
    The actions required by AD 2014-08-02, and retained in this 
proposed AD, take about 63 work-hours per product, at an average labor 
rate of $85 per work-hour. Required parts cost about $2,360 per 
product. Based on these figures (accounting for updated work-hour and 
parts cost estimates), the estimated cost of this proposed AD on U.S. 
operators is $7,715 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for any on-condition actions specified in this proposed 
AD. We have no way of determining the number of aircraft that might 
need this repair.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this 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:

[[Page 13407]]

    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) 
2014-08-02, Amendment 39-17826 (79 FR 21392, April 16, 2014), and 
adding the following new AD:

Airbus: Docket No. FAA-2016-9572; Directorate Identifier 2016-NM-
151-AD.

(a) Comments Due Date

    We must receive comments by April 27, 2017.

(b) Affected ADs

    This AD replaces AD 2014-08-02, Amendment 39-17826 (79 FR 21392, 
April 16, 2014) (``AD 2014-08-02'').

(c) Applicability

    This AD applies to Airbus Model A300-B4-601, B4-603, B4-620, and 
B4-622 airplanes, and Model A300-B4-605R and B4-622R airplanes, 
certificated in any category, except airplanes on which Airbus 
Modification 10324 or 10325 has been embodied in production.

(d) Subject

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

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the wing skin stringers are subject to 
widespread fatigue damage (WFD). We are issuing this AD to prevent 
cracking in the bottom wing skin stringers, 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) Retained Modification of Rib 14, With Revised Compliance Time and 
Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2014-08-02, with revised compliance time and service information. At 
the time specified in paragraph (g)(1) or (g)(2) of this AD, 
whichever occurs earlier, modify the profile of stringer run-outs at 
rib 14 of both wings, including a high frequency eddy current 
inspection of the fastener holes for defects and all applicable 
repairs, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-6046, Revision 02, dated June 21, 
2013; or Revision 03, including Appendix 01, dated February 4, 2015; 
except as required by paragraph (h) of this AD. Do all applicable 
repairs before further flight. As of the effective date of this AD, 
only Airbus Service Bulletin A300-57-6046, Revision 03, including 
Appendix 01, dated February 4, 2015, may be used.
    (1) Before the accumulation of 42,500 total flight cycles, or 
within 2,000 flight cycles after May 21, 2014 (the effective date of 
AD 2014-08-02), whichever occurs later.
    (2) Before the accumulation of 30,000 total flight cycles, or 
within 2,000 flight cycles after the effective date of this AD, 
whichever occurs later.

(h) Retained Exception to the Service Information, With Revised Service 
Information

    This paragraph restates the requirements of paragraph (h) of AD 
2014-08-02, with revised service information.
    (1) Where Airbus Mandatory Service Bulletin A300-57-6046, 
Revision 02, dated June 21, 2013, specifies to contact Airbus for 
repair instructions, this AD requires contacting the Manager, ANM-
116, International Branch, Transport Airplane Directorate, FAA, or 
the European Aviation Safety Agency (EASA) (or its delegated agent) 
for repair instructions and doing those repairs before further 
flight.
    (2) Where Airbus Service Bulletin A300-57-6046, Revision 03, 
including Appendix 01, dated February 4, 2015, specifies to contact 
Airbus for appropriate action: Before further flight, accomplish 
corrective actions in accordance with the procedures specified in 
paragraph (j)(2) of this AD.

(i) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g) of this AD, if those actions were performed before the effective 
date of this AD using the service information specified in paragraph 
(i)(1), (i)(2), or (i)(3) of this AD.
    (1) Airbus Service Bulletin A300-57-6046, Revision 01, dated 
April 18, 2011, which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A300-57-6046, dated January 18, 
1994, which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A300-57-6046, Revision 02, dated 
June 21, 2013, which was incorporated by reference in AD 2014-08-02.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: 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 Branch, ANM-116, Transport 
Airplane Directorate, 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 
paragraph (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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0174, dated August 30, 
2016, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-9572.
    (2) 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 account.airworth-eas@airbus.com; 
Internet: http://www.airbus.com. You may view this service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on January 12, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-03032 Filed 3-10-17; 8:45 am]
 BILLING CODE 4910-13-P