[Federal Register Volume 83, Number 34 (Tuesday, February 20, 2018)]
[Proposed Rules]
[Pages 7117-7120]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-03212]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 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.
 
 ========================================================================
 

  Federal Register / Vol. 83, No. 34 / Tuesday, February 20, 2018 / 
Proposed Rules  

[[Page 7117]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0111; Product Identifier 2017-NM-059-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2017-07-
07, for certain Airbus Model A330-200, A330-300, A340-200, and A340-300 
series airplanes. AD 2017-07-07 requires repetitive inspections of 
certain fastener holes, and related investigative and corrective 
actions if necessary. Since we issued AD 2017-07-07, we have determined 
that certain other airplanes could also be affected by the unsafe 
condition specified in AD 2017-07-07. This proposed AD would retain the 
requirements of AD 2017-07-07 and expand the applicability. We are 
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by April 6, 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--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: [email protected]; internet: http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Standards Branch, 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-2018-
0111; 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 Section, Transport Standards Branch, 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 proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0111; 
Product Identifier 2017-NM-059-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 2017-07-07, Amendment 39-18845 (82 FR 18547, April 20, 
2017) (``AD 2017-07-07''), for certain Airbus Model A330-200, A330-300, 
A340-200, and A340-300 series airplanes with manufacturer serial 
numbers (MSN) 0176 through 0915 inclusive. These airplanes have Airbus 
modification 44360 embodied in production. AD 2017-07-07 was prompted 
by a report of cracking at fastener holes located at frame (FR) 40 on 
the lower shell panel junction. AD 2017-07-07 requires repetitive 
inspections of certain fastener holes, and related investigative and 
corrective actions if necessary. Airbus then introduced the 
modification 55792 to reinforce the fuselage at FR40. We issued AD 
2017-07-07 to detect and correct cracking at FR40 on the lower shell 
panel junction; such cracking could lead to reduced structural 
integrity of the fuselage.
    Since we issued AD 2017-07-07, we have determined that airplanes in 
the post-modification 55792 configuration could be also affected by 
crack initiation and propagation at fastener holes located at FR40 on 
the lower shell panel junction.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0063, dated April 12, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A330-200, A330-
300, and A340-200 series airplanes, and Model A340-312 and -313 
airplanes. The MCAI states:

    During full scale fatigue test of the Frame (FR) 40 to fuselage 
skin panel junction, fatigue damage was found. Corrective actions 
consisted of in-service installation of an internal reinforcing 
strap on the related junction, as currently required by DGAC 
[Direction G[eacute]n[eacute]rale de l'Aviation Civile] France AD 
1999-448-126(B), which refers to Airbus Service Bulletin (SB) A340-
53-4104 Revision 02, and [DGAC] AD 2001-070(B), which refers to 
Airbus SB A330-53-3093 Revision 04; retrofit improvement of internal 
reinforcing strap fatigue life through recommended Airbus SB A330-
53-3145; and introducing a design improvement in production through 
Airbus mod 44360.

[[Page 7118]]

    After those actions were implemented, cracks were found on both 
left-hand (LH) and right-hand (RH) sides on internal strap, butt 
strap, keel beam fitting, or forward fitting FR40 flange. These 
findings were made during embodiment of a FR40 web repair on an A330 
aeroplane, and during keel beam replacement on an A340 aeroplane, 
where the internal strap was removed and a special detailed 
inspection (SDI) was performed on several holes.
    This condition, if not detected and corrected, could affect the 
structural integrity of the centre fuselage of the aeroplane.
    Prompted by these findings, Airbus issued SB A330-53-3215 and SB 
A340-53-4215, providing inspection instructions. Consequently, EASA 
issued AD 2014-0136 [which corresponds to FAA AD 2017-07-07] to 
require repetitive SDI (rototest) of 10 fastener holes located at 
the FR40 lower shell panel junction on both LH and RH sides and, 
depending on findings, accomplishment of applicable corrective 
action(s).
    Since that [EASA] AD was issued, prompted by the results of 
complementary fatigue analyses, it was determined that post-mod 
55792 aeroplanes could be also affected by crack initiation and 
propagation at this area of the fuselage. These analyses 
demonstrated that post-mod 55792 aeroplanes must follow the same 
maintenance program as aeroplanes in post-mod 55306 and pre-mod 
55792 configuration. Consequently, Airbus published SB A330-53-3215 
Revision 02 and SB A340-53-4215 Revision 02 to expand the 
Effectivity accordingly.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0136, which is superseded, which now 
also apply to aeroplanes in post-mod 55792 configuration [the 
applicability identifies airplanes in post-mod 44360 configuration].

    AD 2017-07-07 includes Model A340-311 airplanes in its 
applicability. Airbus Model A340-311 airplanes are not identified in 
the applicability of this proposed AD because those airplanes are not 
affected by the identified unsafe condition. All of those airplanes are 
in the pre-Airbus modification 44360 configuration. The MCAI does not 
include Model A340-311 airplanes in its applicability.
    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 
utilization and 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-2018-0111.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A330-53-3215, Revision 
02, dated November 23, 2016 (``A330-53-3215, R2''); and Airbus Service 
Bulletin A340-53-4215, Revision 02, dated November 23, 2016. This 
service information describes procedures for repetitive rototest 
inspections of certain fastener holes, and related investigative 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.

Differences Between This Proposed AD and the MCAI or Service 
Information

    The MCAI includes Model A340-211 airplanes in its applicability. 
Airbus Model A340-211 airplanes are not identified in the applicability 
of this proposed AD because those airplanes are not affected by the 
identified unsafe condition. All of those airplanes are in the pre-
Airbus modification 44360 configuration. We have coordinated this 
difference with EASA.
    Paragraph 1.E. ``Compliance,'' of A330-53-3215, R2, specifies 
weight variant (WV) 050 in the condition column of table 1, 
configuration 003. We have determined that for the purposes of this AD, 
WV060 and WV080 are also affected.

Costs of Compliance

    We estimate that this proposed AD affects 99 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
           Action                  Labor cost         Parts cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection.................  42 work-hours x $85                $0  $3,570 per inspection  $353,430 per
                              per hour = $3,570                      cycle.                 inspection cycle.
                              per inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair........................................  46 work-hours x $85 per hour =            $2,358          $6,268
                                                 $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

[[Page 7119]]

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) 
2017-07-07, Amendment 39-18845 (82 FR 18547, April 20, 2017), and 
adding the following new AD:

Airbus: Docket No. FAA-2018-0111; Product Identifier 2017-NM-059-AD.

(a) Comments Due Date

    We must receive comments by April 6, 2018.

(b) Affected ADs

    This AD replaces AD 2017-07-07, Amendment 39-18845 (82 FR 18547, 
April 20, 2017) (``AD 2017-07-07'').

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1) and (c)(2) of this AD, all 
manufacturer serial numbers on which Airbus Modification 44360 has 
been embodied in production.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-212, -213, -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) Compliance Times for the Actions Required by Paragraph (h) of This 
AD

    Accomplish the actions required by paragraph (h) of this AD at 
the times specified in paragraphs (g)(1) and (g)(2) of this AD, as 
applicable.
    (1) For airplanes having serial numbers 0176 through 0915 
inclusive: Within the compliance times defined in table 1 to 
paragraph (g)(1) of this AD, and, thereafter, at intervals not to 
exceed the compliance times defined in Airbus Service Bulletin A330-
53-3215, Revision 02, dated November 23, 2016 (``A330-53-3215, 
R2''); or Airbus Service Bulletin A340-53-4215, Revision 02, dated 
November 23, 2016 (``A340-53-4215, R2''); as applicable, depending 
on airplane utilization and configuration. As of the effective date 
of this AD, where paragraph 1.E. ``Compliance,'' of A330-53-3215, R2 
specifies weight variant (WV) 050 in the condition column of table 
1, configuration 003, for the purposes of this AD, WV060 and WV080 
are also included.
[GRAPHIC] [TIFF OMITTED] TP20FE18.000


[[Page 7120]]


    (2) For all airplanes except those identified in paragraph 
(g)(1) of this AD: Before exceeding the applicable compliance time 
``threshold'' defined in paragraph 1.E., ``Compliance,'' of A330-53-
3215, R2; or A340-53-4215, R2; as applicable, depending on airplane 
utilization and configuration and to be counted from airplane first 
flight, and, thereafter, at intervals not to exceed the compliance 
times specified in paragraph 1.E., ``Compliance'' of A330-53-3215, 
R2; or A340-53-4215, R2; as applicable, depending on airplane 
utilization and configuration. Where paragraph 1.E. ``Compliance,'' 
of A330-53-3215, R2 specifies weight variant WV050 in the condition 
column of table 1, configuration 003, for the purposes of this AD, 
WV060 and WV080 are also included.

(h) Repetitive Inspections and Related Investigative and Corrective 
Actions

    At the applicable compliance times specified in paragraph (g) of 
this AD: Accomplish a special detailed inspection of the 10 fastener 
holes located at FR40 lower shell panel junction on both left-hand 
and right-hand sides, in accordance with the Accomplishment 
Instructions of A330-53-3215, R2; or A340-53-4215, R2; as 
applicable.
    (1) If, during any inspection required by the introductory text 
of paragraph (h) 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 A330-53-3215, R2; or A340-53-4215, R2; as 
applicable, except where A330-53-3215, R2; or A340-53-4215, R2; 
specifies to contact Airbus for repair instructions, and specifies 
that action as ``RC,'' this AD requires repair before further flight 
using a method approved by the Manager, International Section, 
Transport Standards Branch, FAA; or 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.
    (2) If, during any inspection required by the introductory text 
of paragraph (h) of this AD, the diameter of a fastener hole is 
found to be outside the tolerances of the transition fit as 
specified in A330-53-3215, R2; or A340-53-4215, R2; as applicable; 
and A330-53-3215, R2; or A340-53-4215, R2; specifies to contact 
Airbus for repair instructions, and specifies that action as ``RC,'' 
before further flight, repair using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA DOA. If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Accomplishment of corrective actions, as required by 
paragraph (h)(1) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (h) of this AD.
    (4) Accomplishment of a repair on an airplane, as required by 
paragraph (h)(2) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (h) of this AD for that airplane, unless the method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or EASA; or Airbus's EASA DOA indicates otherwise.

(i) No Reporting Requirement

    Although A330-53-3215, R2 and A340-53-4215, R2, specify to 
submit certain information to the manufacturer, and specify that 
action as ``RC,'' this AD does not include that requirement.

(j) Credit for Previous Actions

    This paragraph provides credit for the inspections required by 
the introductory text of (h) of this AD and the related 
investigative and corrective actions required by paragraph (h)(1) of 
this AD, if those actions were performed before May 25, 2017 (the 
effective date of AD 2017-07-07), using Airbus Service Bulletin 
A330-53-3215, dated June 21, 2013; or Revision 01, dated April 17, 
2014; or Airbus Service Bulletin A340-53-4215, dated June 21, 2013; 
or Revision 01, dated April 17, 2014; as applicable.

(k) 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 (l)(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 EASA; or Airbus's EASA 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)(1), (g)(2), (h)(1), (h)(2), and (i) 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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0063, dated April 12, 2017, 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-2018-0111.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; 
telephone: 425-227-1138; fax: 425-227-1149.
    (3) 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: [email protected]; 
internet: http://www.airbus.com. You may view this service 
information at the FAA, Transport Standards Branch, 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 February 9, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-03212 Filed 2-16-18; 8:45 am]
BILLING CODE 4910-13-P


