[Federal Register Volume 83, Number 150 (Friday, August 3, 2018)]
[Proposed Rules]
[Pages 38091-38096]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16497]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0641; Product Identifier 2018-NM-032-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2017-22-
07, which applies to certain Airbus Model A319 series airplanes; Model 
A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2017-
22-07 requires repetitive inspections of the frame forks, and 
corrective actions if necessary. AD 2017-22-07 also includes optional 
modifications that constitute terminating action. Since we issued AD 
2017-22-07, an evaluation was done by the design approval holder (DAH) 
indicating that the frame forks and outer skin on the forward and aft 
cargo compartment doors are subject to widespread fatigue damage (WFD), 
and a determination was made that a modification of the frame forks 
must be accomplished. This proposed AD would require modifying certain 
forward and aft cargo compartment doors, and related investigative and 
corrective actions. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by September 17, 
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, 
Airworthiness Office--EIAS, 2 Rond Point Emile Dewoitine, 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 referenced 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://

[[Page 38092]]

www.regulations.gov by searching for and locating Docket No. FAA-2018-
0641; 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 NPRM, 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: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

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-2018-0641; 
Product Identifier 2018-NM-032-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 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 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    We issued AD 2017-22-07, Amendment 39-19087 (82 FR 56158, November 
28, 2017) (``AD 2017-22-07''), for certain Airbus Model A319 series 
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; 
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. AD 2017-22-07 requires repetitive inspections of the frame 
forks, and corrective actions if necessary. AD 2017-22-07 also includes 
optional modifications that constitute terminating action. AD 2017-22-
07 resulted from a report of cracks on frame forks and outer skin on 
the forward and aft cargo compartment doors. We issued AD 2017-22-07 to 
address cracks on the frame forks and outer skin on the forward and aft 
cargo compartment doors, which could lead to reduced structural 
integrity and failure of the cargo compartment door, possible 
decompression of the airplane, and injury to occupants.

Actions Since AD 2017-22-07 Was Issued

    Since we issued AD 2017-22-07, an evaluation was done by the DAH 
indicating that the frame forks and outer skin on the forward and aft 
cargo compartment doors are subject to WFD, and a determination was 
made that a modification of the frame forks must be accomplished.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2018-0024, dated January 29, 2018 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A319 series airplanes; Model A320-211, -212, -214, -216, -231, -232, 
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes. The MCAI states:

    During full scale fatigue test, cracks were found on frame forks 
and outer skin on forward and aft cargo doors. To improve the 
fatigue behaviour of the frame forks, Airbus introduced modification 
(mod) 22948 in production, and issued inspection Service Bulletin 
(SB) A320-52-1032 and mod SB A320-52-1042, both recommended. Since 
those actions were taken, further improved cargo compartment doors 
were introduced in production through Airbus mod 26213, on 
aeroplanes having [manufacturer serial number] MSN 0759 and up.
    In the frame of the Widespread Fatigue Damage (WFD) study, it 
was determined that repetitive inspection are necessary for aft and 
forward cargo compartment doors on aeroplanes that are in pre-mod 
26213 configuration. Failure to detect cracks would reduce the cargo 
door structural integrity.
    This condition, if not detected and corrected, could lead to 
cargo door failure, possibly resulting in decompression of the 
aeroplane and injury to occupants.
    To address this unsafe condition, Airbus issued SB A320-52-1171 
to provide instructions for repetitive special detailed inspections 
(SDI). This SB was later revised to correct the list of affected 
cargo doors. Airbus also issued SB A320-52-1170, introducing a door 
modification which would allow terminating the repetitive SDI[s].
    Consequently, EASA issued AD 2016-0187 [which corresponds to FAA 
AD 2017-22-07] to require repetitive SDI[s] of the affected cargo 
doors and, depending on findings, the accomplishment of applicable 
repairs. That [EASA] AD also included reference to SB A320-52-1170 
as optional terminating action.
    Since that [EASA] AD was issued, further investigations linked 
to the WFD analysis highlighted that, to meet the WFD requirements, 
it is necessary to require

[[Page 38093]]

embodiment of the terminating action modification.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2016-0187, which is superseded, and requires 
modification of all affected cargo doors, which constitutes 
terminating action for the repetitive SDI[s] required by this [EASA] 
AD.

    The related investigative action is a high frequency eddy current 
(HFEC) rotating probe inspection for cracks. Corrective actions 
include, among other things, oversizing and cold-expanding any affected 
holes and 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-2018-0641.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Service Bulletin A320-52-1171, Revision 02, dated April 
10, 2017, which describes procedures for repetitive special detailed 
inspections of all frame forks in the beam 4 area of any affected door, 
and corrective actions.
     Service Bulletin A320-52-1042, Revision 2, dated January 
14, 1997, which describes procedures for modification of all affected 
forward and aft cargo compartment doors.
     Service Bulletin A320-52-1170, including Appendices 01 and 
02, dated September 5, 2016, which describes procedures for modifying 
all affected forward and aft cargo compartment doors, including 
oversize and cold working of riveting for all frame forks.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

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.
    Paragraphs (j)(2) and (j)(3) of AD 2017-22-07 allowed an optional 
terminating modification that could be done at any time. This proposed 
AD would still permit that optional terminating modification, but with 
new limitations on the compliance time, i.e., the optional modification 
must be done on or after the accumulation of 21,700 flight cycles since 
first installation of the door on an airplane in order to terminate the 
repetitive inspections. The repetitive inspections are not terminated 
if the modification is done before the accumulation of 21,700 flight 
cycles since first installation of the door on an airplane. These 
limitations match those in EASA AD 2018-0024, dated January 29, 2018.

Costs of Compliance

    We estimate that this proposed AD affects 88 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on  U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Modification....................  24 work-hours x     Up to $240........  Up to $2,280......  Up to $200,640.
                                   $85 per hour =
                                   $2,040.
Inspection......................  25 work-hours x     $0................  $2,125............  $187,000.
                                   $85 per hour =
                                   $2,125.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator.
    Subtitle VII: Aviation Programs, describes in more detail the scope 
of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

[[Page 38094]]

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2017-22-07, Amendment 39-19087 (82 FR 56158, November 28, 2017), and 
adding the following new AD:

Airbus: Docket No. FAA-2018-0641; Product Identifier 2018-NM-032-AD.

(a) Comments Due Date

    We must receive comments by September 17, 2018.

(b) Affected ADs

    This AD replaces AD 2017-22-07, Amendment 39-19087 (82 FR 56158, 
November 28, 2017) (``AD 2017-22-07'').

(c) Applicability

    This AD applies to Airbus Model A319-111, -112, -113, -114, -
115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -
216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, 
-211, -212, -213, -231, and -232 airplanes, certificated in any 
category, manufacturer serial numbers through 0758 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the frame forks and outer skin on the 
forward and aft cargo compartment doors are subject to widespread 
fatigue damage (WFD), and a determination that a modification of the 
frame forks must be accomplished. We are issuing this AD to address 
cracks on the frame forks and outer skin on the forward and aft 
cargo compartment doors, which could lead to reduced structural 
integrity and failure of the cargo compartment door, possible 
decompression of the airplane, and injury to occupants.

(f) Compliance

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

(g) Retained Definition of Affected Door, With No Changes

    This paragraph restates the definition in paragraph (g) of AD 
2017-22-07, with no changes. For the purpose of this AD, an 
``affected door'' is a forward or aft cargo compartment door, having 
any part number listed in table 1 to paragraph (g) of this AD, 
except a cargo compartment door on which Airbus Service Bulletin 
A320-52-1042 or Airbus Service Bulletin A320-52-1170 is embodied.
[GRAPHIC] [TIFF OMITTED] TP03AU18.000

(h) Retained Repetitive Special Detailed Inspection of Frame Forks, 
With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2017-22-07, with no changes. At the latest of the compliance times 
listed in paragraphs (h)(1) through (h)(4) of this AD: Do a special 
detailed inspection of all frame forks in the beam 4 area of any 
affected door as defined in paragraph (g) of this AD, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-52-1171, Revision 02, dated April 10, 2017, except as specified 
in paragraphs (l) and (m) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 3,000 flight cycles. A review 
of the airplane delivery or maintenance records is acceptable to 
identify any affected door installed on the airplane, provided that 
the cargo compartment door part number can be conclusively 
determined from that review.
    (1) Before exceeding 37,500 flight cycles since first 
installation of the door on an airplane.
    (2) Within 900 flight cycles after January 2, 2018 (the 
effective date of AD 2017-22-07), without exceeding 41,950 flight 
cycles since first installation of the door on an airplane.
    (3) Within 50 flight cycles after January 2, 2018 (the effective 
date of AD 2017-22-07), for a door having reached or exceeded 41,900 
flight cycles since first installation on an airplane.

[[Page 38095]]

    (4) Within 3,000 flight cycles since the last inspection of the 
door as specified in Airbus Service Bulletin A320-52-1032.

(i) Retained Corrective Actions, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2017-22-07, with no changes. If any crack is found during any 
inspection required by paragraph (h) of this AD, before further 
flight, do all applicable corrective actions in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, 
Revision 02, dated April 10, 2017, except as specified in paragraphs 
(l) and (m) of this AD. Accomplishment of applicable corrective 
actions does not constitute terminating action for the repetitive 
inspections.

(j) Terminating Modification

    Before the accumulation of 56,300 total flight cycles, but not 
before the accumulation of 21,700 total flight cycles since first 
installation of the affected door on an airplane: Modify all 
affected doors of an airplane, including accomplishment of all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1170, including Appendices 01 and 02, dated 
September 5, 2016. Accomplishing this modification constitutes 
terminating action for the repetitive inspections specified in 
paragraph (h) of this AD for that airplane, provided that, after 
modification, no affected door is re-installed on that airplane.

(k) Retained Optional Terminating Action, With Changes Related to 
Compliance

    This paragraph restates the requirements of paragraph (j) of AD 
2017-22-07, with changes related to compliance.
    (1) Modification of all affected doors of an airplane before the 
effective date of this AD, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-52-1042, Revision 2, 
dated January 14, 1997, constitutes terminating action for the 
repetitive inspections specified in paragraph (h) of this AD and a 
method of compliance for the modification required by paragraph (j) 
of this AD, for that airplane, provided that, after modification, no 
affected door is re-installed on that airplane. On or after the 
effective date of this AD, the modification required by paragraph 
(j) of this AD must be done.
    (2) Modification of all affected doors of an airplane including 
accomplishment of all applicable related investigative and 
corrective actions, if done before the effective date of this AD in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1170, dated September 5, 2016, except as specified 
in paragraph (l) of this AD, constitutes terminating action for the 
repetitive inspections specified in paragraph (h) of this AD and a 
method of compliance for the modification required by paragraph (j) 
of this AD, for that airplane, provided that, after modification, no 
affected door is re-installed on that airplane. On or after the 
effective date of this AD, the modification required by paragraph 
(j) of this AD must be done.
    (3) Modification of all affected doors on an airplane, in case 
of finding damaged frame forks, as specified in an Airbus Repair 
Design Approval Sheet (RDAS), if done before the effective date of 
this AD and done in accordance with a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
the European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA); constitutes terminating action for the 
repetitive inspection specified in paragraph (h) of this AD and a 
method of compliance for the modification required by paragraph (j) 
of this AD, for that airplane, provided that, after modification, no 
affected door is re-installed on that airplane. On or after the 
effective date of this AD, the modification required by paragraph 
(j) of this AD must be done.

(l) Retained Exception to Service Information

    This paragraph restates the requirements of paragraph (k) of AD 
2017-22-07, with no changes. Where Airbus Service Bulletin A320-52-
1170, including Appendices 01 and 02, dated September 5, 2016; or 
Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 
2017; 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 (p)(2) of this AD.

(m) Retained No Reporting Requirement

    This paragraph restates the requirements of paragraph (l) of AD 
2017-22-07, with no changes. Although Airbus Service Bulletin A320-
52-1171, Revision 02, dated April 10, 2017, specifies to submit 
certain information to the manufacturer, and specifies that action 
as ``RC,'' this AD does not include that requirement.

(n) Retained Credit for Previous Actions

    This paragraph restates the requirements of paragraph (m) of AD 
2017-22-07, with no changes.
    (1) This paragraph provides credit for the actions required by 
paragraphs (h) and (i) of this AD, if those actions were performed 
before January 2, 2018 (the effective date of AD 2017-22-07), using 
Airbus Service Bulletin A320-52-1171, dated October 29, 2015, 
provided that it can be conclusively determined that any part number 
D52371000018 was also inspected as specified in paragraph (h) of 
this AD.
    (2) This paragraph provides credit for the actions required by 
paragraphs (h) and (i) of this AD, if those actions were performed 
before January 2, 2018 (the effective date of AD 2017-22-07), using 
Airbus Service Bulletin A320-52-1171, Revision 01, dated September 
5, 2016.

(o) Parts Installation Limitation

    As of the effective date of this AD, no person may install, on 
any airplane, an affected door specified in paragraph (g) of this 
AD, unless less than 56,300 flight cycles have accumulated since 
first installation of the door on an airplane, and unless the door 
has been inspected in accordance with the requirements of paragraph 
(h) of this AD and all applicable corrective actions have been done 
in accordance with paragraph (i) of this AD.

(p) 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 (p)(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 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 specified in 
paragraphs (l) and (m) 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.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2018-0024, dated January 29, 
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-2018-0641.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 2 Rond Point Emile Dewoitine, 
31700 Blagnac Cedex, France; telephone: +33

[[Page 38096]]

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 July 24, 2018.

James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-16497 Filed 8-2-18; 8:45 am]
 BILLING CODE 4910-13-P


