Document ID: FAA-2018-0906-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus SAS Airplanes
Posted Date: 2018-11-05T05:00Z

[Federal Register Volume 83, Number 214 (Monday, November 5, 2018)]
[Proposed Rules]
[Pages 55294-55297]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-23817]

 ========================================================================
 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. 214 / Monday, November 5, 2018 / 
Proposed Rules  

[[Page 55294]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0906; Product Identifier 2018-NM-122-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus SAS Model A310-304, -322, -324, and -325 airplanes. This 
proposed AD was prompted by an evaluation by the design approval holder 
(DAH) indicating that certain skin stringer joints are subject to 
widespread fatigue damage (WFD). This proposed AD would require a 
rototest inspection of the fastener holes in the affected areas and 
repair if necessary, and modifying the fastener holes. We are proposing 
this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by December 20, 
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--EAW, Rond-Point Emile Dewoitine No: 2, 31700 
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 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-
0906; 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: Dan Rodina, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.

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-2018-0906; 
Product Identifier 2018-NM-122-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

    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 WFD. 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 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

[[Page 55295]]

development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    We are issuing this AD to address any cracking of the top wing skin 
stringer joints at rib 19, which could result in reduced structural 
integrity of the wing.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2018-0174, dated August 14, 2018 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus SAS Model 
A310-304, -322, -324, and -325 airplanes. The MCAI states:

    In response to US 14 CFR Part 26 concerning Widespread Fatigue 
Damage (WFD), Airbus assessed all wing structural items of the 
Airbus A310 design deemed potentially susceptible to WFD. The top 
[wing] skin stringer joints at rib 19 at level of the first fastener 
row were highlighted as an area of uniform stress distribution, 
indicating that cracks may develop in adjacent stringers at the same 
time, which is known as Multi Element Damage.
    This condition, if not corrected, could reduce the structural 
integrity of the wing.
    Prompted by the conclusion of WFD analysis, Airbus issued the 
[service bulletin] SB to provide modification instructions. The 
accomplishment of this modification at the specified time will 
extend the life of the fastener holes in the affected area in order 
to reach the Limit of Validity.
    For the reasons described above, this [EASA] AD requires a one-
time inspection of the [fastener] holes in the affected area, 
accomplishment of applicable corrective action(s) [contacting the 
manufacturer], depending on findings, and modification.

    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-
0906.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A310-57-2108, dated November 9, 
2017. This service information describes procedures for accomplishing a 
rototest inspection of the fastener holes in the affected areas and 
repair if necessary, and modifying the fastener holes. 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 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.

Explanation of Compliance Time

    The compliance time for the replacement specified in this proposed 
AD for addressing WFD was established to ensure that discrepant 
structure is replaced before WFD develops in airplanes. Standard 
inspection techniques cannot be relied on to detect WFD before it 
becomes a hazard to flight. We will not grant any extensions of the 
compliance time to complete any AD-mandated service bulletin related to 
WFD without extensive new data that would substantiate and clearly 
warrant such an extension.

Costs of Compliance

    We estimate that this proposed AD affects 14 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
43 work-hours x $85 per hour = 3,655.........................              $0           $3,655          $51,170
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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 and associated appliances 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.

[[Page 55296]]

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-2018-0906; Product Identifier 2018-NM-
122-AD.

(a) Comments Due Date

    We must receive comments by December 20, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS Model A310-304, -322, -324, 
and -325 airplanes, certificated in any category.

(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 top wing skin stringer joints at rib 19 
are subject to widespread fatigue damage (WFD). We are issuing this 
AD to address any cracking of the top wing skin stringer joints, 
which could result in reduced structural integrity of the wing.

(f) Compliance

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

(g) Definitions

    (1) The affected areas are defined as the top wing skin 
stringers, 9 to 15, at the stringer joints, outboard of rib 19, on 
both wings.
    (2) The average flight time (AFT) is defined as flight hours 
divided by flight cycles accumulated by an individual airplane since 
the airplane's first flight, specified in hours and hundredths of an 
hour. Refer to the Airbus A310 Maintenance Review Board Report 
Section D2 for guidance to determine the AFT.

(h) Inspection

    Within the applicable compliance times specified in figure 1 to 
paragraph (h) of this AD, accomplish a rototest inspection of the 
fastener holes in the affected areas in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2108, 
dated November 9, 2017.
[GRAPHIC] [TIFF OMITTED] TP05NO18.002

(i) Corrective Actions

    If, during the inspection required by paragraph (h) of this AD, 
any discrepancy (i.e., cracking or discrepant hole diameter) or 
existing repair is detected, before further flight, obtain 
corrective actions approved by the Manager, International Section, 
Transport Standards Branch, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus SAS's EASA Design Organization Approval 
(DOA); and accomplish the corrective actions within the compliance 
time specified therein. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(j) Modification

    If, during the inspection required by paragraph (h) of this AD, 
no existing repair or discrepancy is detected, before further 
flight, modify the fastener holes in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2108, 
dated November 9, 2017.

(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: 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 the 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): 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 Airworthiness Directive 2018-0174, dated August 14, 
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-2018-0906.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3225.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile Dewoitine

[[Page 55297]]

No: 2, 31700 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 Standards Branch, 2200 South 216th St., Des Moines, 
WA. For information on the availability of this material at the FAA, 
call 206-231-3195.

    Issued in Des Moines, Washington, on October 24, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-23817 Filed 11-2-18; 8:45 am]
 BILLING CODE 4910-13-P