82 FR 22904 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 96 (May 19, 2017)

Page Range		22904-22907
FR Document		2017-10032
We propose to adopt a new airworthiness directive (AD) for all Airbus Model A310-203, -221, -222, -304, -322, -324, and -325 airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the wing bottom skin at the main landing gear (MLG) reinforcing plate is subject to widespread fatigue damage (WFD). This proposed AD would require a modification of the wing bottom skin at the MLG reinforcing plate. We are proposing this AD to address the unsafe condition on these products.
Federal Register, Volume 82 Issue 96 (Friday, May 19, 2017)
[Federal Register Volume 82, Number 96 (Friday, May 19, 2017)]
[Proposed Rules]
[Pages 22904-22907]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-10032]


========================================================================
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. 82, No. 96 / Friday, May 19, 2017 / Proposed 
Rules

[[Page 22904]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0472; Directorate Identifier 2016-NM-148-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus 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 Model A310-203, -221, -222, -304, -322, -324, and -325 
airplanes. This proposed AD was prompted by an evaluation by the design 
approval holder (DAH) indicating that the wing bottom skin at the main 
landing gear (MLG) reinforcing plate is subject to widespread fatigue 
damage (WFD). This proposed AD would require a modification of the wing 
bottom skin at the MLG reinforcing plate. We are proposing this AD to 
address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 3, 2017.

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, 1 Rond Point Maurice Bellonte, 31707 
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 referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0472; 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0472; 
Directorate Identifier 2016-NM-148-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

    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 widespread fatigue damage. 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.

[[Page 22905]]

This approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0170, dated August 19, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A310-203, -221, -222, -304, -322, -324, and -325 airplanes. The MCAI 
states:

    In response to the FAA Part 26 rule, wing structural items of 
the Airbus A310 design that are deemed potentially susceptible to 
Widespread Fatigue Damage (WFD) have been assessed. The bottom skin 
at the main landing gear (MLG) reinforcing plate has been 
highlighted as an area susceptible to Multi Site Damage (MSD).
    This condition, if not corrected, could reduce the structural 
integrity of the wing.
    Airbus performed a detailed widespread fatigue damage tolerance 
analysis of the bottom skin at the MLG reinforcing plate, and 
concluded that a modification is necessary to the fastener holes at 
the inboard edge of the reinforcing plate forward of the rear spar. 
The modification consists of inspection [related investigative 
actions of a check and a rotating probe inspection] and a first 
oversize of the critical holes on the first two rows of fasteners 
[and corrective actions, e.g., repair]. Airbus modification 13751 
was introduced and Service Bulletin (SB) A310-57-2104 was issued to 
provide in-service modification instructions. The accomplishment of 
this modification at the specified time will recondition/renovate/
extend the life of the fastener holes in the bottom skin at the MLG 
reinforcing plate and prevent the development of MSD up to the 
Extended Service Goal (ESG).
    For the reasons described above, this [EASA] AD requires certain 
modifications to the wing bottom skin at the MLG reinforcing plate, 
forward of the wing rear spar [including related investigative 
actions of a check and a rotating probe inspection and corrective 
actions, e.g., repair].

    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-2017-
0472.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A310-57-2104, dated December 
15, 2015. The service information describes procedures for a 
modification of the left hand (LH) and right hand (RH) wing bottom skin 
at the MLG reinforcing plate, including related investigative actions 
and applicable corrective actions. 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 the same 
type design.

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

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                            Cost per       Cost on U.S.
                 Action                                           Labor cost                              Parts cost        product         operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification...........................  52 work-hours x $85 per hour = $4,420.......................         $12,000          $16,420         $131,360
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

[[Page 22906]]

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2017-0472; Directorate Identifier 2016-NM-
148-AD.

(a) Comments Due Date

    We must receive comments by July 3, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A310-203, -221, -222, -304, -
322, -324, and -325 airplanes, certificated in any category, all 
manufacturer serial numbers.

(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 the wing bottom skin at the main 
landing gear (MLG) reinforcing plate is subject to widespread 
fatigue damage (WFD). We are issuing this AD to prevent multi-site 
damage in the bottom skin at the MLG reinforcing plate, 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) Modification

    Within the compliance times defined in table 1 to paragraph (g) 
of this AD, table 2 to paragraph (g) of this AD, or table 3 to 
paragraph (g) of this AD, as applicable to airplane type and 
utilization: Do a modification of the left-hand (LH) and right-hand 
(RH) wing bottom skin at the MLG reinforcing plate, including all 
related investigative actions and applicable corrective actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-57-2104, dated December 15, 2015, except as required 
by paragraph (h) of this AD. All related investigative and 
applicable corrective actions must be done before further flight. 
For purposes of this AD, the term ``short range'' applies to 
airplanes with an average flight time (AFT) lower than 1.5 flight 
hours (FH) per flight cycle, and the term ``long range'' applies to 
airplanes with an average flight time equal to or higher than 1.5 FH 
per flight cycle. For determining the ``short range'' and ``long 
range'' airplanes, the AFT is the total accumulated flight hours, 
counted from take-off to touch-down, divided by the total 
accumulated flight cycles at the effective date of this AD.

  Table 1 to Paragraph (g) of This AD--Model A310-200 Series Airplanes
------------------------------------------------------------------------
 
------------------------------------------------------------------------
            Compliance Time (whichever occurs later, A or B)
------------------------------------------------------------------------
A............................  Before exceeding 28,800 flight cycles
                                (FC) or 57,600 FH, whichever occurs
                                first since first flight of the
                                airplane.
------------------------------------------------------------------------
B............................  Within 960 FC, or 1,920 FH, or 12 months,
                                whichever occurs first after the
                                effective date of this AD.
------------------------------------------------------------------------


 Table 2 to paragraph (g) of this AD--A310-300 ``short-range'' Airplanes
------------------------------------------------------------------------
 
------------------------------------------------------------------------
            Compliance Time (whichever occurs later, A or B)
------------------------------------------------------------------------
A............................  Before exceeding 27,700 FC or 77,700 FH,
                                whichever occurs first since first
                                flight of the airplane.
B............................  Within 920 FC, or 2,580 FH, or 12 months,
                                whichever occurs first after the
                                effective date of this AD.
------------------------------------------------------------------------


 Table 3 to paragraph (g) of this AD--A310-300 ``short-range'' Airplanes
------------------------------------------------------------------------
 
------------------------------------------------------------------------
            Compliance Time (whichever occurs later, A or B)
------------------------------------------------------------------------
A............................  Before exceeding 20,500 FC or 102,500 FH,
                                whichever occurs first since first
                                flight of the airplane.
B............................  Within 680 FC, or 3,420 FH, or 12 months,
                                whichever occurs first after the
                                effective date of this AD.
------------------------------------------------------------------------

(h) Exception to Service Information Specifications

    Where Airbus Service Bulletin A310-57-2104, dated December 15, 
2015, specifies to contact Airbus for appropriate action, and 
specifies that action as ``RC'' (Required for Compliance): Before 
further flight, accomplish corrective actions in accordance with the 
procedures specified in paragraph (i)(2) of this AD.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Branch, send it to the 
attention of the person identified in paragraph (j)(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 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (h) 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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0170, dated August 19, 
2016, for related information.

[[Page 22907]]

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-
2017-0472.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 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 Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on May 10, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10032 Filed 5-18-17; 8:45 am]
 BILLING CODE 4910-13-P
22904

Proposed Rules Federal Register
Vol. 82, No. 96

Friday, May 19, 2017

This section of the FEDERAL REGISTER Point Maurice Bellonte, 31707 Blagnac Discussion
contains notices to the public of the proposed Cedex, France; telephone +33 5 61 93 36 Fatigue damage can occur locally, in
issuance of rules and regulations. The 96; fax +33 5 61 93 44 51; email
purpose of these notices is to give interested small areas or structural design details,
account.airworth-eas@airbus.com; or globally, in widespread areas.
persons an opportunity to participate in the
Internet http://www.airbus.com. You Multiple-site damage is widespread
rule making prior to the adoption of the final
rules. may view this referenced service damage that occurs in a large structural
information at the FAA, Transport element such as a single rivet line of a
Airplane Directorate, 1601 Lind Avenue lap splice joining two large skin panels.
DEPARTMENT OF TRANSPORTATION SW., Renton, WA. For information on Widespread damage can also occur in
the availability of this material at the multiple elements such as adjacent
Federal Aviation Administration FAA, call 425–227–1221. frames or stringers. Multiple-site
Examining the AD Docket damage and multiple-element damage
14 CFR Part 39 cracks are typically too small initially to
[Docket No. FAA–2017–0472; Directorate You may examine the AD docket on be reliably detected with normal
Identifier 2016–NM–148–AD] the Internet at http:// inspection methods. Without
www.regulations.gov by searching for intervention, these cracks will grow,
RIN 2120–AA64
and locating Docket No. FAA–2017– and eventually compromise the
Airworthiness Directives; Airbus 0472; or in person at the Docket structural integrity of the airplane. This
Airplanes Management Facility between 9 a.m. condition is known as widespread
and 5 p.m., Monday through Friday, fatigue damage. It is associated with
AGENCY: Federal Aviation except Federal holidays. The AD docket general degradation of large areas of
Administration (FAA), DOT. contains this proposed AD, the structure with similar structural details
ACTION: Notice of proposed rulemaking regulatory evaluation, any comments and stress levels. As an airplane ages,
(NPRM). received, and other information. The WFD will likely occur, and will
street address for the Docket Operations certainly occur if the airplane is
SUMMARY: We propose to adopt a new office (telephone 800–647–5527) is in operated long enough without any
airworthiness directive (AD) for all the ADDRESSES section. Comments will intervention.
Airbus Model A310–203, –221, –222, be available in the AD docket shortly The FAA’s WFD final rule (75 FR
–304, –322, –324, and –325 airplanes. after receipt. 69746, November 15, 2010) became
This proposed AD was prompted by an effective on January 14, 2011. The WFD
evaluation by the design approval FOR FURTHER INFORMATION CONTACT: Dan rule requires certain actions to prevent
holder (DAH) indicating that the wing Rodina, Aerospace Engineer, structural failure due to WFD
bottom skin at the main landing gear International Branch, ANM–116, throughout the operational life of
(MLG) reinforcing plate is subject to Transport Airplane Directorate, FAA, certain existing transport category
widespread fatigue damage (WFD). This 1601 Lind Avenue SW., Renton, WA airplanes and all of these airplanes that
proposed AD would require a 98057–3356; telephone 425–227–2125; will be certificated in the future. For
modification of the wing bottom skin at fax 425–227–1149. existing and future airplanes subject to
the MLG reinforcing plate. We are SUPPLEMENTARY INFORMATION: the WFD rule, the rule requires that
proposing this AD to address the unsafe DAHs establish a limit of validity (LOV)
condition on these products. Comments Invited of the engineering data that support the
DATES: We must receive comments on structural maintenance program.
this proposed AD by July 3, 2017. We invite you to send any written
Operators affected by the WFD rule may
relevant data, views, or arguments about
ADDRESSES: You may send comments, not fly an airplane beyond its LOV,
this proposed AD. Send your comments
using the procedures found in 14 CFR unless an extended LOV is approved.
to an address listed under the The WFD rule (75 FR 69746,
11.43 and 11.45, by any of the following ADDRESSES section. Include ‘‘Docket No.
methods: November 15, 2010) does not require
FAA–2017–0472; Directorate Identifier
• Federal eRulemaking Portal: Go to identifying and developing maintenance
2016–NM–148–AD’’ at the beginning of actions if the DAHs can show that such
http://www.regulations.gov. Follow the
your comments. We specifically invite actions are not necessary to prevent
instructions for submitting comments.
comments on the overall regulatory,
• Fax: 202–493–2251. WFD before the airplane reaches the
• Mail: U.S. Department of economic, environmental, and energy LOV. Many LOVs, however, do depend
Transportation, Docket Operations, M– aspects of this proposed AD. We will on accomplishment of future
30, West Building Ground Floor, Room consider all comments received by the maintenance actions. As stated in the
W12–140, 1200 New Jersey Avenue SE., closing date and may amend this WFD rule, any maintenance actions
sradovich on DSK3GMQ082PROD with PROPOSALS

Washington, DC 20590. proposed AD based on those comments. necessary to reach the LOV will be
• Hand Delivery: Deliver to Mail We will post all comments we mandated by airworthiness directives
address above between 9 a.m. and 5 receive, without change, to http:// through separate rulemaking actions.
p.m., Monday through Friday, except www.regulations.gov, including any In the context of WFD, this action is
Federal holidays. personal information you provide. We necessary to enable DAHs to propose
For service information identified in will also post a report summarizing each LOVs that allow operators the longest
this NPRM, contact Airbus SAS, substantive verbal contact we receive operational lives for their airplanes, and
Airworthiness Office—EAW, 1 Rond about this proposed AD. still ensure that WFD will not occur.

VerDate Sep<11>2014 18:29 May 18, 2017 Jkt 241001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\19MYP1.SGM 19MYP1
Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules 22905

This approach allows for an fasteners [and corrective actions, e.g., repair]. FAA’s Determination and Requirements
implementation strategy that provides Airbus modification 13751 was introduced of This Proposed AD
flexibility to DAHs in determining the and Service Bulletin (SB) A310–57–2104 was
issued to provide in-service modification This product has been approved by
timing of service information
instructions. The accomplishment of this the aviation authority of another
development (with FAA approval), modification at the specified time will country, and is approved for operation
while providing operators with certainty recondition/renovate/extend the life of the in the United States. Pursuant to our
regarding the LOV applicable to their fastener holes in the bottom skin at the MLG bilateral agreement with the State of
airplanes. reinforcing plate and prevent the Design Authority, we have been notified
The European Aviation Safety Agency development of MSD up to the Extended
Service Goal (ESG).
of the unsafe condition described in the
(EASA), which is the Technical Agent MCAI and service information
for the Member States of the European For the reasons described above, this
[EASA] AD requires certain modifications to referenced above. We are proposing this
Union, has issued EASA Airworthiness AD because we evaluated all pertinent
the wing bottom skin at the MLG reinforcing
Directive 2016–0170, dated August 19, plate, forward of the wing rear spar information and determined an unsafe
2016 (referred to after this as the [including related investigative actions of a condition exists and is likely to exist or
Mandatory Continuing Airworthiness check and a rotating probe inspection and develop on other products of the same
Information, or ‘‘the MCAI’’), to correct corrective actions, e.g., repair]. type design.
an unsafe condition for all Airbus
You may examine the MCAI in the Explanation of Compliance Time
Model A310–203, –221, –222, –304,
AD docket on the Internet at http://
–322, –324, and –325 airplanes. The The compliance time for the
www.regulations.gov by searching for
MCAI states: replacement specified in this proposed
and locating Docket No. FAA–2017–
In response to the FAA Part 26 rule, wing 0472. AD for addressing WFD was established
structural items of the Airbus A310 design to ensure that discrepant structure is
that are deemed potentially susceptible to Related Service Information Under 1 replaced before WFD develops in
Widespread Fatigue Damage (WFD) have CFR Part 51 airplanes. Standard inspection
been assessed. The bottom skin at the main
landing gear (MLG) reinforcing plate has We reviewed Airbus Service Bulletin techniques cannot be relied on to detect
been highlighted as an area susceptible to A310–57–2104, dated December 15, WFD before it becomes a hazard to
Multi Site Damage (MSD). 2015. The service information describes flight. We will not grant any extensions
This condition, if not corrected, could procedures for a modification of the left of the compliance time to complete any
reduce the structural integrity of the wing. hand (LH) and right hand (RH) wing AD-mandated service bulletin related to
Airbus performed a detailed widespread bottom skin at the MLG reinforcing WFD without extensive new data that
fatigue damage tolerance analysis of the plate, including related investigative would substantiate and clearly warrant
bottom skin at the MLG reinforcing plate, and actions and applicable corrective such an extension.
concluded that a modification is necessary to actions. This service information is
the fastener holes at the inboard edge of the Costs of Compliance
reinforcing plate forward of the rear spar. The
reasonably available because the
modification consists of inspection [related interested parties have access to it We estimate that this proposed AD
investigative actions of a check and a rotating through their normal course of business affects 8 airplanes of U.S. registry.
probe inspection] and a first oversize of the or by the means identified in the We estimate the following costs to
critical holes on the first two rows of ADDRESSES section. comply with this proposed AD:

ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators

Modification .......................................................... 52 work-hours × $85 per hour = $4,420 .. $12,000 $16,420 $131,360

Authority for This Rulemaking that is likely to exist or develop on 2. Is not a ‘‘significant rule’’ under the
Title 49 of the United States Code products identified in this rulemaking DOT Regulatory Policies and Procedures
specifies the FAA’s authority to issue action. (44 FR 11034, February 26, 1979);
rules on aviation safety. Subtitle I, 3. Will not affect intrastate aviation in
Regulatory Findings Alaska; and
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII: We determined that this proposed AD 4. Will not have a significant
Aviation Programs,’’ describes in more would not have federalism implications economic impact, positive or negative,
detail the scope of the Agency’s under Executive Order 13132. This on a substantial number of small entities
authority. proposed AD would not have a under the criteria of the Regulatory
We are issuing this rulemaking under substantial direct effect on the States, on Flexibility Act.
the authority described in ‘‘Subtitle VII, the relationship between the national List of Subjects in 14 CFR Part 39
Part A, Subpart III, Section 44701: Government and the States, or on the
General requirements.’’ Under that Air transportation, Aircraft, Aviation
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distribution of power and
section, Congress charges the FAA with safety, Incorporation by reference,
responsibilities among the various
promoting safe flight of civil aircraft in Safety.
air commerce by prescribing regulations levels of government.
For the reasons discussed above, I The Proposed Amendment
for practices, methods, and procedures
the Administrator finds necessary for certify this proposed regulation: Accordingly, under the authority
safety in air commerce. This regulation 1. Is not a ‘‘significant regulatory delegated to me by the Administrator,
is within the scope of that authority action’’ under Executive Order 12866; the FAA proposes to amend 14 CFR part
because it addresses an unsafe condition 39 as follows:

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22906 Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules

PART 39—AIRWORTHINESS (d) Subject modification of the left-hand (LH) and right-
DIRECTIVES Air Transport Association (ATA) of hand (RH) wing bottom skin at the MLG
America Code 57, Wings. reinforcing plate, including all related
■ 1. The authority citation for part 39 investigative actions and applicable
(e) Reason
continues to read as follows: corrective actions, in accordance with the
This AD was prompted by an evaluation by Accomplishment Instructions of Airbus
Authority: 49 U.S.C. 106(g), 40113, 44701. the design approval holder (DAH) indicating Service Bulletin A310–57–2104, dated
§ 39.13 [Amended] that the wing bottom skin at the main landing
December 15, 2015, except as required by
gear (MLG) reinforcing plate is subject to
■ 2. The FAA amends § 39.13 by adding widespread fatigue damage (WFD). We are paragraph (h) of this AD. All related
the following new airworthiness issuing this AD to prevent multi-site damage investigative and applicable corrective
directive (AD): in the bottom skin at the MLG reinforcing actions must be done before further flight.
plate, which could result in reduced For purposes of this AD, the term ‘‘short
Airbus: Docket No. FAA–2017–0472;
Directorate Identifier 2016–NM–148–AD. structural integrity of the wing. range’’ applies to airplanes with an average
flight time (AFT) lower than 1.5 flight hours
(a) Comments Due Date (f) Compliance
(FH) per flight cycle, and the term ‘‘long
We must receive comments by July 3, 2017. Comply with this AD within the range’’ applies to airplanes with an average
compliance times specified, unless already flight time equal to or higher than 1.5 FH per
(b) Affected ADs done.
flight cycle. For determining the ‘‘short
None.
(g) Modification range’’ and ‘‘long range’’ airplanes, the AFT
(c) Applicability Within the compliance times defined in is the total accumulated flight hours, counted
This AD applies to Airbus Model A310– table 1 to paragraph (g) of this AD, table 2 from take-off to touch-down, divided by the
203, –221, –222, –304, –322, –324, and –325 to paragraph (g) of this AD, or table 3 to total accumulated flight cycles at the
airplanes, certificated in any category, all paragraph (g) of this AD, as applicable to effective date of this AD.
manufacturer serial numbers. airplane type and utilization: Do a

TABLE 1 TO PARAGRAPH (g) OF THIS AD—MODEL A310–200 SERIES AIRPLANES

Compliance Time (whichever occurs later, A or B)

A ........................................... Before exceeding 28,800 flight cycles (FC) or 57,600 FH, whichever occurs first since first flight of the airplane.

B ........................................... Within 960 FC, or 1,920 FH, or 12 months, whichever occurs first after the effective date of this AD.

TABLE 2 TO PARAGRAPH (g) OF THIS AD—A310–300 ‘‘SHORT-RANGE’’ AIRPLANES

Compliance Time (whichever occurs later, A or B)

A ........................................... Before exceeding 27,700 FC or 77,700 FH, whichever occurs first since first flight of the airplane.
B ........................................... Within 920 FC, or 2,580 FH, or 12 months, whichever occurs first after the effective date of this AD.

TABLE 3 TO PARAGRAPH (g) OF THIS AD—A310–300 ‘‘SHORT-RANGE’’ AIRPLANES

Compliance Time (whichever occurs later, A or B)

A ........................................... Before exceeding 20,500 FC or 102,500 FH, whichever occurs first since first flight of the airplane.
B ........................................... Within 680 FC, or 3,420 FH, or 12 months, whichever occurs first after the effective date of this AD.

(h) Exception to Service Information appropriate. If sending information directly (3) Required for Compliance (RC): Except
Specifications to the manager of the International Branch, as required by paragraph (h) of this AD, if
Where Airbus Service Bulletin A310–57– send it to the attention of the person any service information contains procedures
2104, dated December 15, 2015, specifies to identified in paragraph (j)(2) of this AD. or tests that are identified as RC, those
contact Airbus for appropriate action, and Information may be emailed to: 9-ANM-116- procedures and tests must be done to comply
specifies that action as ‘‘RC’’ (Required for AMOC-REQUESTS@faa.gov. Before using with this AD; any procedures or tests that are
Compliance): Before further flight, any approved AMOC, notify your appropriate not identified as RC are recommended. Those
accomplish corrective actions in accordance principal inspector, or lacking a principal procedures and tests that are not identified
with the procedures specified in paragraph inspector, the manager of the local flight as RC may be deviated from using accepted
(i)(2) of this AD. standards district office/certificate holding methods in accordance with the operator’s
maintenance or inspection program without
(i) Other FAA AD Provisions district office.
obtaining approval of an AMOC, provided
(2) Contacting the Manufacturer: For any
The following provisions also apply to this the procedures and tests identified as RC can
AD: requirement in this AD to obtain corrective
be done and the airplane can be put back in
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(1) Alternative Methods of Compliance actions from a manufacturer, the action must an airworthy condition. Any substitutions or
(AMOCs): The Manager, International be accomplished using a method approved changes to procedures or tests identified as
Branch, ANM–116, Transport Airplane by the Manager, International Branch, ANM– RC require approval of an AMOC.
Directorate, FAA, has the authority to 116, Transport Airplane Directorate, FAA; or
approve AMOCs for this AD, if requested the European Aviation Safety Agency (j) Related Information
using the procedures found in 14 CFR 39.19. (EASA); or Airbus’s EASA Design (1) Refer to Mandatory Continuing
In accordance with 14 CFR 39.19, send your Organization Approval (DOA). If approved by Airworthiness Information (MCAI) EASA
request to your principal inspector or local the DOA, the approval must include the Airworthiness Directive 2016–0170, dated
Flight Standards District Office, as DOA-authorized signature. August 19, 2016, for related information.

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Federal Register / Vol. 82, No. 96 / Friday, May 19, 2017 / Proposed Rules 22907

This MCAI may be found in the AD docket We must receive comments on this FAA–2016–7264; Directorate Identifier
on the Internet at http://www.regulations.gov SNPRM by July 3, 2017. 2015–NM–185–AD’’ at the beginning of
by searching for and locating Docket No. your comments. We specifically invite
FAA–2017–0472. ADDRESSES: You may send comments,
(2) For more information about this AD, using the procedures found in 14 CFR comments on the overall regulatory,
contact Dan Rodina, Aerospace Engineer, 11.43 and 11.45, by any of the following economic, environmental, and energy
International Branch, ANM–116, Transport methods: aspects of this SNPRM. We will
Airplane Directorate, FAA, 1601 Lind • Federal eRulemaking Portal: Go to consider all comments received by the
Avenue SW., Renton, WA 98057–3356; http://www.regulations.gov. Follow the closing date and may amend this
telephone 425–227–2125; fax 425–227–1149. instructions for submitting comments. SNPRM based on those comments.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
• Fax: 202–493–2251. We will post all comments we
Office—EAW, 1 Rond Point Maurice • Mail: U.S. Department of receive, without change, to http://
Bellonte, 31707 Blagnac Cedex, France; Transportation, Docket Operations, M– www.regulations.gov, including any
telephone +33 5 61 93 36 96; fax +33 5 61 30, West Building Ground Floor, Room personal information you provide. We
93 44 51; email account.airworth-eas@ W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each
airbus.com; Internet http://www.airbus.com. Washington, DC 20590. substantive verbal contact we receive
You may view this service information at the • Hand Delivery: U.S. Department of about this SNPRM.
FAA, Transport Airplane Directorate, 1601 Transportation, Docket Operations, M–
Lind Avenue SW., Renton, WA. For Discussion
information on the availability of this
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE., We issued an NPRM to amend 14 CFR
material at the FAA, call 425–227–1221. part 39 by adding an AD that would
Washington, DC, between 9 a.m. and 5
Issued in Renton, Washington, on May 10, apply to certain Airbus Model A330–
2017.
p.m., Monday through Friday, except
Federal holidays. 200, –200 Freighter, and –300 series
Michael Kaszycki, airplanes; and Model A340–500 and
For service information identified in
Acting Manager, Transport Airplane this SNPRM, contact Airbus SAS, –600 series airplanes. The NPRM
Directorate, Aircraft Certification Service. published in the Federal Register on
Airworthiness Office—EAL, 1 Rond
[FR Doc. 2017–10032 Filed 5–18–17; 8:45 am]
Point Maurice Bellonte, 31707 Blagnac June 21, 2016 (81 FR 40201) (‘‘the
BILLING CODE 4910–13–P
Cedex, France; telephone +33 5 61 93 36 NPRM’’). The NPRM was prompted by
96; fax +33 5 61 93 45 80; email a quality control review on the final
airworthiness.A330-A340@airbus.com; assembly line, which determined that
DEPARTMENT OF TRANSPORTATION the wrong aluminum alloy was used to
Internet http://www.airbus.com. You
may view this referenced service manufacture several structural parts.
Federal Aviation Administration The NPRM proposed to require a one-
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue time eddy current conductivity
14 CFR Part 39 measurement of certain cabin and cargo
SW., Renton, WA. For information on
[Docket No. FAA–2016–7264; Directorate the availability of this material at the compartment structural parts to
Identifier 2015–NM–185–AD] determine if an incorrect aluminum
FAA, call 425–227–1221.
RIN 2120–AA64 alloy was used, and replacement of any
Examining the AD Docket affected part with a serviceable part.
Airworthiness Directives; Airbus You may examine the AD docket on The European Aviation Safety Agency
Airplanes the Internet at http:// (EASA), which is the Technical Agent
www.regulations.gov by searching for for the Member States of the European
AGENCY: Federal Aviation Union, has issued EASA Airworthiness
Administration (FAA), DOT. and locating Docket No. FAA–2016–
7264; or in person at the Docket Directive 2017–0021, dated February 8,
ACTION: Supplemental notice of 2017 (referred to after this as the
Management Facility between 9 a.m.
proposed rulemaking (SNPRM); Mandatory Continuing Airworthiness
and 5 p.m., Monday through Friday,
reopening of comment period. Information, or ‘‘the MCAI’’), to correct
except Federal holidays. The AD docket
SUMMARY: We are revising an earlier contains this SNPRM, the regulatory an unsafe condition for certain Airbus
notice of proposed rulemaking (NPRM) evaluation, any comments received, and Model A330–200, –200 Freighter, and
for certain Airbus Model A330–200, other information. The street address for –300 series airplanes; and Model A340–
–200 Freighter, and –300 series the Docket Office (telephone: 800–647– 500 and –600 series airplanes. The
airplanes; and Model A340–500 and 5527) is in the ADDRESSES section. MCAI states:
–600 series airplanes. This action Comments will be available in the AD Following an Airbus quality control review
revises the NPRM by including new docket shortly after receipt. on the final assembly line, it was discovered
inspection locations for certain FOR FURTHER INFORMATION CONTACT: that wrong aluminum alloy was used to
airplanes, and removing incorrect part manufacture several structural parts.
Vladimir Ulyanov, Aerospace Engineer,
This condition, if not detected and
numbers. We are proposing this International Branch, ANM–116, corrected, could reduce the structural
airworthiness directive (AD) to address Transport Airplane Directorate, FAA, integrity of the aeroplane.
the unsafe condition on these products. 1601 Lind Avenue SW., Renton, WA To address this potential unsafe condition,
Since these actions impose an 98057–3356; telephone 425–227–1138; Airbus published [Service Bulletin] (SB)
additional burden over those proposed fax 425–227–1149. A330–53–3261, SB A330–53–3262, and SB
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in the NPRM, we are reopening the SUPPLEMENTARY INFORMATION: A340–53–5072, as applicable to aeroplane
comment period to allow the public the type/model, to provide instructions to
chance to comment on these proposed Comments Invited identify the affected parts. Consequently,
changes. EASA issued AD 2015–0206 to require a one-
We invite you to send any written time special detailed inspection (SDI) [eddy
DATES: The comment period for the relevant data, views, or arguments about current conductivity measurements] of
NPRM published in the Federal this proposed AD. Send your comments certain cabin and/or cargo compartment parts
Register on June 21, 2016 (81 FR 40201), to an address listed under the for material identification and, depending on
is reopened. ADDRESSES section. Include ‘‘Docket No. findings, replacement with serviceable parts.

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Document Created: 2018-11-08 08:47:26
Document Modified: 2018-11-08 08:47:26
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 July 3, 2017.
Contact		Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149.
FR Citation		82 FR 22904
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
82 FR 22904 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 82, Issue 96 (May 19, 2017)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
