[Federal Register Volume 82, Number 111 (Monday, June 12, 2017)]
[Proposed Rules]
[Pages 26874-26877]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-12056]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0533; Directorate Identifier 2016-NM-156-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 adopt a new airworthiness directive (AD) for all 
Airbus Model A300 B4-603 and A300 B4-622 airplanes; Model A300 B4-600R 
series airplanes; Model A300 C4-605R Variant F airplanes; Model A300 
F4-600R series airplanes; and Model A310-203, A310-221, A310-222, A310-
304, A310-322, A310-324, and A310-325 airplanes. This proposed AD was 
prompted by an evaluation by the design approval holder (DAH) that 
indicates that a section of the fuselage structure above the forward 
cargo door is subject to widespread fatigue damage (WFD). This proposed 
AD would require an inspection for cracks of the fastener and tooling 
holes at certain locations and a check of the diameter of the holes, 
and repair or modification of the affected fuselage structure 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 July 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NRPM, 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 Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA.

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-2017-
0533; 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-2017-0533; 
Directorate Identifier

[[Page 26875]]

2016-NM-156-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

    Structural fatigue damage is progressive. It begins as minute 
cracks, and those cracks grow under the action of repeated stresses. 
This can happen because of normal operational conditions and design 
attributes, or because of isolated situations or incidents such as 
material defects, poor fabrication quality, or corrosion pits, dings, 
or scratches. Fatigue damage can occur locally, in small areas or 
structural design details, or globally. Global fatigue damage is 
general degradation of large areas of structure with similar structural 
details and stress levels. Multiple-site damage is global damage that 
occurs in a large structural element such as a single rivet line of a 
lap splice joining two large skin panels. Global 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, in a condition known as WFD. 
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 transport 
category airplanes that will be certificated in the future. For 
existing and future airplanes subject to the WFD rule, the rule 
requires that 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.
    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.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive AD 2016-0178, dated September 12, 2016 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for all 
Airbus Model A300 series airplanes. The MCAI states:

    In the frame of the Widespread Fatigue Damage (WFD) analysis, 
some structural areas were identified as requiring embodiment of a 
structural modification.
    This condition, if not corrected, could reduce the fuselage 
structural integrity.
    To address this unsafe condition, Airbus issued Service Bulletin 
(SB) A310-53-2145 and SB A300-53-6187 to provide instructions for 
structural reinforcement of the fuselage frames (FR) between FR20 
Right Hand side (RH) and FR25 RH and the frame couplings between 
stringer (STGR) 20 RH and STGR23 RH, hereafter collectively referred 
to as `the affected fuselage structure' in this [EASA] AD.
    For the reason described above, this [EASA] AD requires 
accomplishment of a one-time special detailed inspection (SDI) of 
the fastener and tooling holes, and modification of the affected 
fuselage structure.

    The required actions include a rototest inspection for cracks of 
the fastener and tooling holes at certain locations and a check of the 
diameter of the holes, and repair or modification of the affected 
fuselage structure if necessary. 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-2017-0533.

Related Service Information Under 1 CFR Part 51

    Airbus issued the following service information:
     Airbus Service Bulletin A300-53-6187, Revision 00, dated 
May 31, 2016. This service information describes procedures for a 
rototest inspection for cracks of the fastener and tooling holes at 
certain locations, a check of the diameter of the holes, repair, and 
modification of the affected fuselage structure by reinforcing the 
frames between right hand FR 20 RH and FR 25 RH, or FR 21 RH and FR 25 
RH, depending on the configuration; and reinforcing the frame couplings 
between stringer STGR 20 RH and STGR 23 RH.
     Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016. This service information describes procedures for a 
rototest inspection for cracks of the fastener and tooling holes at 
certain locations, a check of the diameter of the holes, repair, and 
modification of the affected fuselage structure by reinforcing the 
frames between right hand FR20 RH and FR25 RH; and reinforcing the 
frame couplings between STGR 20 RH and STGR 23 RH.
    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 132 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 26876]]



                                                 Estimated Costs
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                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
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Inspection, check, repair, and       45 work-hours x $85 per              $2,360          $6,185        $816,420
 modification.                        hour = $3,825.
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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:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new Airworthiness 
Directive (AD):

Airbus: Docket No. FAA-2017-0533; Directorate Identifier 2016-NM-
156-AD.

(a) Comments Due Date

    We must receive comments by July 27, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes identified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Model A300 B4-603 and A300 B4-622 airplanes.
    (2) Model A300 B4-605R and A300 B4-622R airplanes.
    (3) Model A300 F4-605R and A300 F4-622R airplanes.
    (4) Model A300 C4-605R Variant F airplanes.
    (5) Model A310-203, -221, -222, -304, -322, -324, and -325 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder that indicates that a section of the fuselage structure above 
the forward cargo door is subject to widespread fatigue damage. We 
are issuing this AD to prevent reduced structural integrity of these 
airplanes due to the failure of certain structural components.

(f) Compliance

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

(g) Check and Rototest Inspection of Affected Fastener and Tooling 
Holes

    Before exceeding 42,500 flight cycles since the first flight of 
the airplane, do a check of the diameter of the fastener holes and 
tooling holes and a rototest inspection for cracks of all holes of 
removed fasteners and the tooling holes at the locations specified 
in, and in accordance with, the Accomplishment Instructions of 
Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 
2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016; as applicable.

(h) Repair of Detected Cracks

    If any condition specified in paragraph (h)(1) or (h)(2) of this 
AD is found, prior to further flight, repair in accordance with 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). 
Concurrently with the repair, unless the approved repair 
instructions specify otherwise, modify the affected structure, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6187, Revision 00, dated May 31, 2016; or Airbus 
Service Bulletin A310-53-2145, Revision 00, dated May 31, 2016; as 
applicable.
    (1) Any crack is found during the rototest inspection required 
by paragraph (g) of this AD.
    (2) Any hole diameter is greater than or equal to the maximum 
starting hole diameter specified in the Accomplishment Instructions 
of Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 
2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016; as applicable, is found during the check required by 
paragraph (g) of this AD.

(i) Modification

    If, during the actions required by paragraph (g) of this AD, no 
crack is found and the hole diameter is less than the maximum 
starting hole diameter specified in the Accomplishment Instructions 
of Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 
2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016; as applicable, before further flight, modify the 
affected fuselage structure, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-6187, Revision 00, 
dated May 31, 2016; or Airbus Service Bulletin A310-53-2145, 
Revision 00, dated May 31, 2016; as applicable.

(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 manager of the International Branch, send it to the 
attention of the person

[[Page 26877]]

identified in paragraph (k)(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: 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 EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): 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 AD 2016-0178, dated September 12, 2016, for related 
information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2017-0533.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-2125. Information may be 
emailed to: [email protected].
    (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 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 June 2, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-12056 Filed 6-9-17; 8:45 am]
 BILLING CODE 4910-13-P