83 FR 47850 - Airworthiness Directives; Airbus SAS Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 184 (September 21, 2018)

We propose to adopt a new airworthiness directive (AD) for all Airbus SAS Model A330-223F and Model A330-243F 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 special detailed inspections (rototest) of certain fastener holes located at the lower shell junction of a certain frame on both left-hand (LH) and right-hand (RH) sides, and applicable related investigative and corrective actions. We are proposing this AD to address the unsafe condition on these products.

[Federal Register Volume 83, Number 184 (Friday, September 21, 2018)]
[Proposed Rules]
[Pages 47850-47852]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2018-20360]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0800; Product Identifier 2018-NM-107-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS 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 SAS Model A330-223F and Model A330-243F 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 special detailed inspections (rototest) of certain 
fastener holes located at the lower shell junction of a certain frame 
on both left-hand (LH) and right-hand (RH) sides, and applicable 
related investigative and corrective actions. We are proposing this AD 
to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by November 5, 
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 service information 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.

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-
0800; 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 (phone: 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, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3229.

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-2018-0800; 
Product Identifier 2018-NM-107-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 because 
of 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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2018-0146, dated July 12, 2018 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus SAS Model 
A330-223F and Model A330-243F airplanes. The MCAI states:

    During embodiment of a frame (FR) 40 web repair on an A330 
aeroplane, and during keel beam replacement on an A340 aeroplane, 
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.
    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, 
providing inspection instructions, and EASA issued AD 2014-0136 and, 
subsequently, AD 2017-0063 [which corresponds to FAA AD 2018-12-08, 
Amendment 39-19312 (83 FR 33821, July 18, 2018)] to require 
repetitive special detailed inspection (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).
    After those ADs were issued, it has been determined that A330 
Freighter aeroplanes are also affected by this potential unsafe 
condition. Consequently, Airbus published SB [service bulletin] 
A330-53-3215 Revision 03 to expand the Effectivity of that SB to 
these aeroplanes.
    For the reason described above, this AD requires 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) [which include 
oversizing, installing fasteners and repair; and accomplishment of 
applicable related investigative actions, which include a rototest 
inspection for cracking after oversizing].

    The initial compliance time is 16,200 flight cycles or 48,800 
flight hours, whichever occurs first since airplane first flight. The 
repetitive inspection interval is 13,700 flight cycles or 41,100 flight 
hours, whichever occurs first.
    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-
0800.

Related Service Information Under 1 CFR Part 51

    Airbus SAS has issued Service Bulletin A330-53-3215, Revision 03, 
dated January 22, 2018. This service information describes procedures 
for repetitive rototest inspections of certain fastener holes, and 
related investigative and corrective actions if necessary. 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

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our

[[Page 47851]]

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 the relevant information and determined the unsafe 
condition described previously 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 the service information described previously.

Costs of Compliance

    We estimate that this proposed AD affects 5 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
              Labor cost                  Parts cost         Cost per product          Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 42 work-hours x $85 per hour =                $0  Up to $3,570.............  Up to $17,850.
 $3,570.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required based on the results of any required 
actions. We have no way of determining the number of aircraft that 
might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
46 work-hours x $85 per hour = $3,910.          $3,690           $7,600
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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.
    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 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 adding the following new airworthiness 
directive (AD):

Airbus SAS: Docket No. FAA-2018-0800; Product Identifier 2018-NM-
107-AD.

(a) Comments Due Date

    We must receive comments by November 5, 2018.

(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; all 
manufacturer serial numbers.
    (1) Airbus SAS Model A330-223F airplanes.
    (2) Airbus SAS Model A330-243F airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of cracking on both left-hand 
(LH) and right-hand (RH) sides on the internal strap, butt strap, 
keel beam fitting, or forward fitting frame (FR) 40 flange. We are 
issuing this AD to address cracking at FR40 on the lower shell panel 
junction; such cracking could

[[Page 47852]]

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 
before exceeding the compliance time ``threshold'' defined in 
paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A330-53-
3215, Revision 03, dated January 22, 2018 (``A330-53-3215, R3''), 
depending on airplane utilization and configuration and to be 
counted from airplane first flight, and, thereafter, at intervals 
not to exceed the compliance times defined in paragraph 1.E., 
``Compliance,'' of A330-53-3215, R3, depending on airplane 
utilization and configuration.

(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 LH and RH 
sides, in accordance with the Accomplishment Instructions of A330-
53-3215, R3.
    (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, R3, except where A330-53-3215, R3 
specifies to contact Airbus for repair instructions, and specifies 
that action as Required for Compliance (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 SAS'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, R3, as applicable; and A330-53-3215, R3; 
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 SAS'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 SAS's EASA DOA indicates otherwise.

(i) No Reporting Requirement

    Although A330-53-3215, R3, specifies to submit certain 
information to the manufacturer, and specifies 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 paragraph (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 the effective date 
of this AD, using Airbus Service Bulletin A330-53-3215, dated June 
21, 2013; or Revision 01, dated April 17, 2014; or Revision 02, 
dated November 23, 2016.

(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 SAS's EASA DOA. If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as specified by 
paragraphs (g), (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 2018-0146, dated July 12, 2018, 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-2018-0800.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax: 206-231-3229.

    Issued in Des Moines, Washington, on September 11, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-20360 Filed 9-20-18; 8:45 am]
 BILLING CODE 4910-13-P