Document ID: FAA-2016-9192-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-10-25T04:00Z

[Federal Register Volume 81, Number 206 (Tuesday, October 25, 2016)]
[Proposed Rules]
[Pages 73357-73360]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-25352]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9192; Directorate Identifier 2016-NM-038-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 
certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series 
airplanes. This proposed AD was prompted by a report of cracking at 
fastener holes located at a certain frame on the lower shell panel 
junction. This proposed AD would require repetitive inspections of 
certain fastener holes, and related investigative and corrective 
actions if necessary. We are proposing this AD to detect and correct 
cracking on the lower shell panel junction; such cracking could lead to 
reduced structural integrity of the fuselage.

DATES: We must receive comments on this proposed AD by December 9, 
2016.

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--EAL, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 
80; email airworthiness.A330-A340@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-
9192; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
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-2016-9192; 
Directorate Identifier 2016-NM-038-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0136, dated June 13, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330, A340-200, and A340-300 series airplanes. The MCAI states:

    During A330/A340 aeroplanes full scale fatigue test specimen in 
the FR40-to-fuselage skin panel junction, fatigue damage has been 
found. Corrective actions consisted of the following actions:

--In-service installation of an internal reinforcing strap on 
related junction required by DGAC [Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (DGAC)] France AD 1999-448-126(B) and AD 2001-
070(B),
--retrofit improvement of internal reinforcing strap fatigue life 
through recommended Airbus Service Bulletin (SB) A330-53-3145, and
--new design in production through Airbus modification 44360.

    The aeroplanes listed in the Applicability section of this AD 
are all aeroplanes post-mod 44360 and pre-mod 55792 (fuselage 
reinforcement at FR40 in production).
    Recently, during embodiment of a FR40 web repair on an A330 
aeroplane and during FR40 keel beam fitting replacement on an A340 
aeroplane, the internal strap was removed and rototest inspection 
was performed on several holes.
    Cracks were found on both left-hand (LH) and right-hand (RH) 
sides on internal strap, or butt strap, or keel beam fitting, or 
forward fitting FR40 flange.
    This condition, if not detected and corrected, could lead to 
crack propagation, possibly resulting in reduced structural 
integrity of the fuselage.
    For the reasons described above, this [EASA] AD requires 
repetitive rototest inspections of 10 fastener holes located at FR40 
lower shell panel junction on both LH and RH sides, and, depending 
on findings, accomplishment of the applicable corrective actions 
[which include oversizing, installing

[[Page 73358]]

fasteners and repair; and accomplishment of applicable related 
investigative actions, which include a rototest inspection for 
cracking after oversizing].

    The compliance time ranges between 20,000 flight cycles or 65,400 
flight hours and 20,800 flight cycles or 68,300 flight hours, depending 
on airplane utilization and configuration. The repetitive inspection 
interval ranges between 14,000 flight cycles or 95,200 flight hours and 
24,600 flight cycles or 98,700 flight hours, depending on airplane 
configuration. 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-2016-9192.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A330-53-3215, Revision 01, 
dated April 17, 2014; and Airbus Service Bulletin A340-53-4215, 
Revision 01, dated April 17, 2014. The service information describes 
procedures for repetitive rototest inspections of certain fastener 
holes, and corrective actions if necessary. These documents are 
distinct since they apply to different airplane models. 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 41 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                               Cost per
                  Action                                Labor cost               Parts cost    product                Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection...............................  41 work-hours x $85 per hour =                $0       $3,485  $142,885 per inspection cycle.
                                            $3,485 per inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of airplanes that might need 
these repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair.....................................  46 work-hours x $85 per hour =               $4,186          $8,096
                                              $3,910.
----------------------------------------------------------------------------------------------------------------

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-2016-9192; Directorate Identifier 2016-NM-
038-AD.

[[Page 73359]]

(a) Comments Due Date

    We must receive comments by December 9, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1) and (c)(2) of this AD, having serial 
numbers 0176 through 0915 inclusive.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of cracking at fastener holes 
located at frame (FR)40 on the lower shell panel junction. We are 
issuing this AD to detect and correct cracking at FR40 on the lower 
shell panel junction; such cracking could lead to reduced structural 
integrity of the fuselage.

(f) Compliance

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

(g) Repetitive Inspections and Related Investigative and Corrective 
Actions

    Within the compliance times defined in table 1 to paragraph (g) 
of this AD, and, thereafter, at intervals not to exceed the 
compliance times defined in Airbus Service Bulletin A330-53-3215, 
Revision 01, dated April 17, 2014; or Airbus Service Bulletin A340-
53-4215, Revision 01, dated April 17, 2014; as applicable, depending 
on airplane utilization and configuration: Accomplish a special 
detailed inspection of fastener holes located at FR40 lower shell 
panel junction on both left-hand (LH) and right-side (RH) sides, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3215, Revision 01, dated April 17, 2014; or Airbus 
Service Bulletin A340-53-4215, Revision 01, dated April 17, 2014; as 
applicable.

    Table 1 to Paragraph (g) of This AD--Compliance Time for Initial
                               Inspection
------------------------------------------------------------------------
                                     Compliance time (whichever occurs
                                               later, A or B)
------------------------------------------------------------------------
A................................  Before exceeding the compliance time
                                    ``threshold'' defined in table 1 of
                                    Airbus Service Bulletin A330-53-
                                    3215, Revision 01, dated April 17,
                                    2014; or Airbus Service Bulletin
                                    A340-53-4215, Revision 01, dated
                                    April 17, 2014; as applicable,
                                    depending on airplane utilization
                                    and configuration and to be counted
                                    from airplane first flight.
B................................  For Model A330 airplanes: Within
                                    2,400 flight cycles or 24 months,
                                    whichever occurs first after the
                                    effective date of this AD.
                                   For Model A340 airplanes: Within
                                    1,300 flight cycles or 24 months,
                                    whichever occurs first after the
                                    effective date of this AD.
------------------------------------------------------------------------

    (1) If, during any inspection required by paragraph (g) of this 
AD, any crack is detected, before further flight, accomplish all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3215, Revision 01, dated April 17, 2014; or Airbus 
Service Bulletin A340-53-4215, Revision 01, dated April 17, 2014; as 
applicable, except where Airbus Service Bulletin A330-53-3215, 
Revision 01, dated April 17, 2014; or Airbus Service Bulletin A340-
53-4215, Revision 01, dated April 17, 2014, specifies to contact 
Airbus for repair instructions, and specifies that action as ``RC'' 
(Required for Compliance), this AD requires repair before further 
flight 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).
    (2) If, during any inspection required by paragraph (g) of this 
AD, the hole diameter is not within tolerance of the transition fit 
as nominal, or first oversize, or second oversize, or next nominal, 
as applicable, and Airbus Service Bulletin A330-53-3215, Revision 
01, dated April 17, 2014; or Airbus Service Bulletin A340-53-4215, 
Revision 01, dated April 17, 2014, specifies to contact Airbus for 
repair instructions, and specifies that action as ``RC'' (Required 
for Compliance), before further flight, repair using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
    (3) Accomplishment of corrective actions, as required by 
paragraph (g)(1) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (g) of this AD.
    (4) Accomplishment of a repair on an airplane, as required by 
paragraph (g)(2) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (g) of this AD for that airplane, unless the method 
approved in accordance with the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA 
DOA indicates otherwise.

(h) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by the 
introductory text of paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A330-53-3215, dated June 21, 2013; or Airbus Service 
Bulletin A340-53-4215, dated June 21, 2013; as applicable.
    (2) This paragraph provides credit for the inspections and 
corrective actions required by paragraph (g) of this AD, if those 
actions were performed before the effective date of this AD using 
Airbus Technical Disposition (TD) Reference LR57D11023360, Issue B, 
dated July 12, 2011.

(i) 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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; 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. The 
AMOC approval letter must specifically reference this AD.
    (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 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 (g)(1) and (g)(2) 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

[[Page 73360]]

changes to procedures or tests identified as RC require approval of 
an AMOC.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0136, dated June 13, 2014, 
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-2016-9192.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@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 October 12, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-25352 Filed 10-24-16; 8:45 am]
 BILLING CODE 4910-13-P