83 FR 55294 - Airworthiness Directives; Airbus SAS Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 214 (November 5, 2018)

Page Range		55294-55297
FR Document		2018-23817
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.
Federal Register, Volume 83 Issue 214 (Monday, November 5, 2018)
[Federal Register Volume 83, Number 214 (Monday, November 5, 2018)]
[Proposed Rules]
[Pages 55294-55297]
From the Federal Register Online  [www.thefederalregister.org]
[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
55294

Proposed Rules Federal Register
Vol. 83, No. 214

Monday, November 5, 2018

This section of the FEDERAL REGISTER Airworthiness Office—EAW, Rond- or globally, in widespread areas.
contains notices to the public of the proposed Point Emile Dewoitine No: 2, 31700 Multiple-site damage is widespread
issuance of rules and regulations. The Blagnac Cedex, France; telephone +33 5 damage that occurs in a large structural
purpose of these notices is to give interested 61 93 36 96; fax +33 5 61 93 44 51; email element such as a single rivet line of a
persons an opportunity to participate in the account.airworth-eas@airbus.com; lap splice joining two large skin panels.
rule making prior to the adoption of the final
rules.
internet http://www.airbus.com. You Widespread damage can also occur in
may view this service information at the multiple elements such as adjacent
FAA, Transport Standards Branch, 2200 frames or stringers. Multiple-site
DEPARTMENT OF TRANSPORTATION South 216th St., Des Moines, WA. For damage and multiple-element damage
information on the availability of this cracks are typically too small initially to
Federal Aviation Administration material at the FAA, call 206–231–3195. be reliably detected with normal
inspection methods. Without
Examining the AD Docket
14 CFR Part 39 intervention, these cracks will grow,
You may examine the AD docket on and eventually compromise the
[Docket No. FAA–2018–0906; Product
the internet at http:// structural integrity of the airplane. This
Identifier 2018–NM–122–AD]
www.regulations.gov by searching for condition is known as WFD. It is
RIN 2120–AA64 and locating Docket No. FAA–2018– associated with general degradation of
0906; or in person at Docket Operations large areas of structure with similar
Airworthiness Directives; Airbus SAS between 9 a.m. and 5 p.m., Monday structural details and stress levels. As
Airplanes through Friday, except Federal holidays. an airplane ages, WFD will likely occur,
AGENCY: Federal Aviation The AD docket contains this NPRM, the and will certainly occur if the airplane
Administration (FAA), DOT. regulatory evaluation, any comments is operated long enough without any
ACTION: Notice of proposed rulemaking received, and other information. The intervention.
(NPRM). street address for Docket Operations The FAA’s WFD final rule (75 FR
(phone: 800–647–5527) is in the 69746, November 15, 2010) became
SUMMARY: We propose to adopt a new ADDRESSES section. Comments will be effective on January 14, 2011. The WFD
airworthiness directive (AD) for all available in the AD docket shortly after rule requires certain actions to prevent
Airbus SAS Model A310–304, –322, receipt. structural failure due to WFD
–324, and –325 airplanes. This proposed FOR FURTHER INFORMATION CONTACT: Dan throughout the operational life of
AD was prompted by an evaluation by Rodina, Aerospace Engineer, certain existing transport category
the design approval holder (DAH) International Section, Transport airplanes and all of these airplanes that
indicating that certain skin stringer Standards Branch, FAA, 2200 South will be certificated in the future. For
joints are subject to widespread fatigue 216th St., Des Moines, WA 98198; existing and future airplanes subject to
damage (WFD). This proposed AD telephone and fax 206–231–3225. the WFD rule, the rule requires that
would require a rototest inspection of SUPPLEMENTARY INFORMATION: DAHs establish a limit of validity (LOV)
the fastener holes in the affected areas of the engineering data that support the
and repair if necessary, and modifying Comments Invited structural maintenance program.
the fastener holes. We are proposing this We invite you to send any written Operators affected by the WFD rule may
AD to address the unsafe condition on relevant data, views, or arguments about not fly an airplane beyond its LOV,
these products. this proposal. Send your comments to unless an extended LOV is approved.
DATES: We must receive comments on an address listed under the ADDRESSES The WFD rule (75 FR 69746,
this proposed AD by December 20, section. Include ‘‘Docket No. FAA– November 15, 2010) does not require
2018. 2018–0906; Product Identifier 2018– identifying and developing maintenance
ADDRESSES: You may send comments, NM–122–AD’’ at the beginning of your actions if the DAHs can show that such
using the procedures found in 14 CFR comments. We specifically invite actions are not necessary to prevent
11.43 and 11.45, by any of the following comments on the overall regulatory, WFD before the airplane reaches the
methods: economic, environmental, and energy LOV. Many LOVs, however, do depend
• Federal eRulemaking Portal: Go to aspects of this NPRM. We will consider on accomplishment of future
http://www.regulations.gov. Follow the all comments received by the closing maintenance actions. As stated in the
instructions for submitting comments. date and may amend this NPRM WFD rule, any maintenance actions
• Fax: 202–493–2251. because of those comments. necessary to reach the LOV will be
• Mail: U.S. Department of We will post all comments we mandated by airworthiness directives
Transportation, Docket Operations, M– receive, without change, to http:// through separate rulemaking actions.
30, West Building Ground Floor, Room www.regulations.gov, including any In the context of WFD, this action is
W12–140, 1200 New Jersey Avenue SE, personal information you provide. We necessary to enable DAHs to propose
Washington, DC 20590. will also post a report summarizing each LOVs that allow operators the longest
• Hand Delivery: Deliver to Mail substantive verbal contact we receive operational lives for their airplanes, and
address above between 9 a.m. and 5 about this NPRM. still ensure that WFD will not occur.
p.m., Monday through Friday, except This approach allows for an
Discussion implementation strategy that provides
Federal holidays.
For service information identified in Fatigue damage can occur locally, in flexibility to DAHs in determining the
this NPRM, contact Airbus SAS, small areas or structural design details, timing of service information

VerDate Sep<11>2014 17:06 Nov 02, 2018 Jkt 247001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\05NOP1.SGM 05NOP1
Federal Register / Vol. 83, No. 214 / Monday, November 5, 2018 / Proposed Rules 55295

development (with FAA approval), fastener holes in the affected area in order to MCAI and service information
while providing operators with certainty reach the Limit of Validity. referenced above. We are proposing this
regarding the LOV applicable to their For the reasons described above, this AD because we evaluated all the
[EASA] AD requires a one-time inspection of
airplanes. the [fastener] holes in the affected area,
relevant information and determined
We are issuing this AD to address any accomplishment of applicable corrective the unsafe condition described
cracking of the top wing skin stringer action(s) [contacting the manufacturer], previously is likely to exist or develop
joints at rib 19, which could result in depending on findings, and modification. on other products of the same type
reduced structural integrity of the wing. You may examine the MCAI in the design.
The European Aviation Safety Agency AD docket on the internet at http:// Proposed Requirements of This NPRM
(EASA), which is the Technical Agent www.regulations.gov by searching for
for the Member States of the European and locating Docket No. FAA–2018– This proposed AD would require
Union, has issued EASA Airworthiness 0906. accomplishing the actions specified in
Directive 2018–0174, dated August 14, the service information described
Related Service Information Under 1 previously.
2018 (referred to after this as the
CFR Part 51
Mandatory Continuing Airworthiness Explanation of Compliance Time
Information, or ‘‘the MCAI’’), to correct Airbus has issued Service Bulletin
an unsafe condition for all Airbus SAS A310–57–2108, dated November 9, The compliance time for the
Model A310–304, –322, –324, and –325 2017. This service information describes replacement specified in this proposed
airplanes. The MCAI states: procedures for accomplishing a rototest AD for addressing WFD was established
inspection of the fastener holes in the to ensure that discrepant structure is
In response to US 14 CFR Part 26 replaced before WFD develops in
concerning Widespread Fatigue Damage
affected areas and repair if necessary,
and modifying the fastener holes. This airplanes. Standard inspection
(WFD), Airbus assessed all wing structural
items of the Airbus A310 design deemed service information is reasonably techniques cannot be relied on to detect
potentially susceptible to WFD. The top available because the interested parties WFD before it becomes a hazard to
[wing] skin stringer joints at rib 19 at level have access to it through their normal flight. We will not grant any extensions
of the first fastener row were highlighted as course of business or by the means of the compliance time to complete any
an area of uniform stress distribution, identified in the ADDRESSES section. AD-mandated service bulletin related to
indicating that cracks may develop in WFD without extensive new data that
adjacent stringers at the same time, which is FAA’s Determination would substantiate and clearly warrant
known as Multi Element Damage. This product has been approved by such an extension.
This condition, if not corrected, could the aviation authority of another
reduce the structural integrity of the wing. Costs of Compliance
Prompted by the conclusion of WFD
country, and is approved for operation
analysis, Airbus issued the [service bulletin] in the United States. Pursuant to our We estimate that this proposed AD
SB to provide modification instructions. The bilateral agreement with the State of affects 14 airplanes of U.S. registry. We
accomplishment of this modification at the Design Authority, we have been notified estimate the following costs to comply
specified time will extend the life of the of the unsafe condition described in the with this proposed AD:

ESTIMATED COSTS FOR REQUIRED ACTIONS
Cost per Cost on U.S.
Labor cost Parts cost product operators

43 work-hours × $85 per hour = 3,655 ....................................................................................... $0 $3,655 $51,170

We have received no definitive data is within the scope of that authority proposed AD would not have a
that would enable us to provide cost because it addresses an unsafe condition substantial direct effect on the States, on
estimates for the on-condition actions that is likely to exist or develop on the relationship between the national
specified in this proposed AD. products identified in this rulemaking Government and the States, or on the
action. distribution of power and
Authority for This Rulemaking This proposed AD is issued in responsibilities among the various
Title 49 of the United States Code accordance with authority delegated by levels of government.
specifies the FAA’s authority to issue the Executive Director, Aircraft
rules on aviation safety. Subtitle I, Certification Service, as authorized by For the reasons discussed above, I
section 106, describes the authority of FAA Order 8000.51C. In accordance certify this proposed regulation:
the FAA Administrator. Subtitle VII: with that order, issuance of ADs is 1. Is not a ‘‘significant regulatory
Aviation Programs, describes in more normally a function of the Compliance action’’ under Executive Order 12866;
detail the scope of the Agency’s and Airworthiness Division, but during 2. Is not a ‘‘significant rule’’ under the
authority. this transition period, the Executive
We are issuing this rulemaking under DOT Regulatory Policies and Procedures
Director has delegated the authority to (44 FR 11034, February 26, 1979);
the authority described in Subtitle VII, issue ADs applicable to transport
Part A, Subpart III, Section 44701: category airplanes and associated 3. Will not affect intrastate aviation in
‘‘General requirements.’’ Under that appliances to the Director of the System Alaska; and
section, Congress charges the FAA with Oversight Division. 4. Will not have a significant
promoting safe flight of civil aircraft in economic impact, positive or negative,
air commerce by prescribing regulations Regulatory Findings
on a substantial number of small entities
for practices, methods, and procedures We determined that this proposed AD under the criteria of the Regulatory
the Administrator finds necessary for would not have federalism implications
Flexibility Act.
safety in air commerce. This regulation under Executive Order 13132. This

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Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by December 20, 2018.
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.
FR Citation		83 FR 55294
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
83 FR 55294 - Airworthiness Directives; Airbus SAS Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 83, Issue 214 (November 5, 2018)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
