83 FR 49265 - Airworthiness Directives; Airbus SAS Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 190 (October 1, 2018)

We are superseding Airworthiness Directive (AD) 2016-25-03, which applied to certain Airbus Model A300 F4-600R series airplanes. AD 2016-25-03 required repetitive high frequency eddy current (HFEC) inspections of the aft lower deck cargo door (LDCD) frame forks; a one- time check of the LDCD clearances; and a one-time detailed visual inspection of hooks, eccentric bushes, and x-stops; and corrective actions if necessary. This AD requires repetitive HFEC inspections of the aft LDCD frame forks; a one-time check of the LDCD clearances; and a one-time detailed visual inspection of hooks, eccentric bushes, and x-stops; and corrective actions if necessary. This AD was prompted by a report of two adjacent frame forks that were found cracked on the aft LDCD of two airplanes during scheduled maintenance, and the introduction of frame fork reinforcement or repair procedures that, when done, allow an extension of repetitive inspection intervals. We are issuing this AD to address the unsafe condition on these products.

[Federal Register Volume 83, Number 190 (Monday, October 1, 2018)]
[Rules and Regulations]
[Pages 49265-49269]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2018-21100]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
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under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 83, No. 190 / Monday, October 1, 2018 / Rules 
and Regulations

[[Page 49265]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0417; Product Identifier 2017-NM-132-AD; Amendment 
39-19440; AD 2018-20-06]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2016-25-03, 
which applied to certain Airbus Model A300 F4-600R series airplanes. AD 
2016-25-03 required repetitive high frequency eddy current (HFEC) 
inspections of the aft lower deck cargo door (LDCD) frame forks; a one-
time check of the LDCD clearances; and a one-time detailed visual 
inspection of hooks, eccentric bushes, and x-stops; and corrective 
actions if necessary. This AD requires repetitive HFEC inspections of 
the aft LDCD frame forks; a one-time check of the LDCD clearances; and 
a one-time detailed visual inspection of hooks, eccentric bushes, and 
x-stops; and corrective actions if necessary. This AD was prompted by a 
report of two adjacent frame forks that were found cracked on the aft 
LDCD of two airplanes during scheduled maintenance, and the 
introduction of frame fork reinforcement or repair procedures that, 
when done, allow an extension of repetitive inspection intervals. We 
are issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective November 5, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 5, 
2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
January 26, 2017 (81 FR 93801, December 22, 2016).

ADDRESSES: For service information identified in this final rule, 
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 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. It is also available on the 
internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2018-0417.

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-
0417; 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 final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2016-25-03, Amendment 39-18729 (81 FR 93801, 
December 22, 2016) (``AD 2016-25-03''). AD 2016-25-03 applied to 
certain Airbus Model A300 F4-600R series airplanes. The NPRM published 
in the Federal Register on May 25, 2018 (83 FR 24244). The NPRM was 
prompted by a report of two adjacent frame forks that were found 
cracked on the aft LDCD of two airplanes during scheduled maintenance, 
and the introduction of frame fork reinforcement or repair procedures 
that, when done, allow an extension of repetitive inspection intervals. 
The NPRM proposed to continue to require repetitive HFEC inspections of 
the aft LDCD frame forks; a one-time check of the LDCD clearances; and 
a one-time detailed visual inspection of hooks, eccentric bushes, and 
x-stops; and corrective actions if necessary. The NPRM also proposed to 
require revised corrective actions and compliance times. We are issuing 
this AD to address cracked or ruptured aft LDCD frames, which could 
allow loads to be transferred to the remaining structural elements. 
This condition could lead to the rupture of one or more vertical aft 
LDCD frames, which could result in reduced structural integrity of the 
aft LDCD.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0152R1, dated May 23, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus SAS 
Model A300 F4-600R series airplanes. The MCAI states:

    During scheduled maintenance at frames (FR) 61 and FR61A on the 
aft lower deck cargo door (LDCD) of two A300-600F4 aeroplanes, two 
adjacent frame forks were found cracked. Subsequent analysis 
determined that, in case of cracked or ruptured aft cargo door 
frame(s), loads will be transferred to the remaining structural 
elements. However, these secondary load paths will be able to 
sustain the loads for a limited number of flight cycles only.
    This condition, if not detected and corrected, could lead to the 
rupture of one or more vertical aft cargo door frame(s), resulting 
in reduced structural integrity of the aft cargo door.
    To address this unsafe condition, Airbus issued Alert Operators 
Transmission (AOT) A52W011-15 to provide inspection instructions, 
and, consequently, EASA issued AD 2015-0152 [which corresponds to 
FAA AD 2016-25-03] to require repetitive inspections of the aft LDCD 
frame forks and, depending on findings, the accomplishment of 
applicable corrective action(s).
    Since that [EASA] AD was issued, Airbus published Service 
Bulletin (SB) SB A300-52-6085 which provides frame fork

[[Page 49266]]

reinforcement instruction and SB A300-52-6086 which provides 
instruction to inspect the cargo door for cracks as well as frame 
fork replacement instructions having the inspection interval 
extended from 600 flight cycles (FC) to 1,200 FC.
    For the reason described above, this [EASA] AD is revised to 
introduce frame forks replacement or repair [or reinforcement] as an 
allowance to extend the inspection interval.

    Required actions include repetitive HFEC inspections of the aft 
LDCD frame forks and repair, reinforcement, or replacement if 
necessary; a one-time check of the LDCD clearances and adjustment if 
necessary; and a one-time detailed visual inspection of hooks, 
eccentric bushes, and x-stops for wear, and corrective actions if 
necessary. Corrective actions include blend-out, adjustment, and 
replacement of hooks, bushes and x-stops. 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-2018-0417.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comment received on the 
NPRM and the FAA's response to the comment.

Request To Incorporate Revised Service Bulletins

    FedEx Express requested that we revise the proposed AD to 
incorporate Airbus Service Bulletin A300-52-6085, Revision 01, dated 
May 2, 2018; and Airbus Service Bulletin A300-52-6086, Revision 01, 
dated May 29, 2018. FedEx Express also requested that we update table 1 
to paragraph (g) of the proposed AD with the revised compliance times 
specified in Airbus Service Bulletin A300-52-6086, Revision 01, dated 
May 29, 2018.
    We partially agree with the commenter's requested changes. We agree 
to incorporate Airbus Service Bulletin A300-52-6085, Revision 01, dated 
May 2, 2018; and Airbus Service Bulletin A300-52-6086, Revision 01, 
dated May 29, 2018; because the changes to the procedures in those 
documents are not significant. The changes include updating reference 
documents and figures and do not result in any additional work for 
airplanes modified using the previous issue. Therefore, we have revised 
this AD to refer to Airbus Service Bulletin A300-52-6085, Revision 01, 
dated May 2, 2018; and Airbus Service Bulletin A300-52-6086, Revision 
01, dated May 29, 2018, as the appropriate sources of service 
information for certain actions. We have also revised this AD to give 
credit for certain actions accomplished using Airbus Service Bulletin 
A300-52-6085, Revision 00, dated December 22, 2016; and Airbus Service 
Bulletin A300-52-6086, Revision 00, dated December 25, 2016.
    The updated compliance times in Airbus Service Bulletin A300-52-
6086, Revision 01, dated May 29, 2018, are substantively different from 
the compliance times specified in the proposed AD and would increase 
the scope of this AD without allowing for public notice and comment. 
Therefore, we have not changed this AD with regard to the compliance 
times specified in Airbus Service Bulletin A300-52-6086. However, under 
the provisions of paragraph (n)(1) of this AD, we will consider 
requests for approval of alternative compliance times if sufficient 
data are submitted to substantiate that the extension would provide an 
acceptable level of safety.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this final rule as proposed, except for minor editorial changes. We 
have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Alert Operators Transmission A52W011-15, Revision 00, 
including Appendices 1, 2, 3, and 4, dated July 23, 2015, which 
describes procedures for a check of the aft LDCD clearances ``U'' and 
``V'' between the latching hooks and the eccentric bush at frame FR60 
through FR64A and an adjustment of the latching hook; a detailed 
inspection to detect signs of wear of the hooks, eccentric bushes, and 
x-stops and corrective actions; and an HFEC inspection to detect 
cracking at all frame fork stations of the aft LDCD and a replacement 
of the frame fork.
     Service Bulletin A300-52-6085, Revision 01, dated May 2, 
2018, which describes procedures for reinforcing frame fork fastener 
holes, which include related investigative and corrective actions. The 
related investigative actions include a rotating probe inspection for 
cracking of the fastener holes and a check to determine the hole 
diameter. Corrective actions include repair and cold working the 
fastener holes.
     Service Bulletin A300-52-6086, Revision 01, dated May 29, 
2018, which describes procedures for a check of the aft LDCD clearances 
``U'' and ``V'' between the latching hooks and the eccentric bush at 
FR60 through FR64A and an adjustment of the latching hook; and HFEC 
inspection to detect cracking at all frame fork stations of the aft 
LDCD and a repair of the frame fork.
    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.

Costs of Compliance

    We estimate that this AD affects 58 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
17 work-hours x $85 per hour = $1,445........................              $0           $1,445          $83,810
----------------------------------------------------------------------------------------------------------------

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

[[Page 49267]]



                 Estimated Costs of On-condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
Up to 65 work-hours x $85 per hour =           $10,000          $15,525
 $5,525...............................
------------------------------------------------------------------------

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 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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) 
2016-25-03, Amendment 39-18729 (81 FR 93801, December 22, 2016), and 
adding the following new AD:

2018-20-06 Airbus SAS: Amendment 39-19440; Docket No. FAA-2018-0417; 
Product Identifier 2017-NM-132-AD.

(a) Effective Date

    This AD is effective November 5, 2018.

(b) Affected ADs

    This AD replaces AD 2016-25-03, Amendment 39-18729 (81 FR 93801, 
December 22, 2016) (``AD 2016-25-03'').

(c) Applicability

    This AD applies to Airbus SAS Model A300 F4-605R and A300 F4-
622R airplanes, certificated in any category, on which Airbus SAS 
modification 12046 has been embodied in production. Modification 
12046 has been embodied in production on manufacturer serial numbers 
(MSNs) 0805 and above, except MSNs 0836, 0837, and 0838.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of two adjacent frame forks 
that were found cracked on the aft lower deck cargo door (LDCD) of 
two airplanes during scheduled maintenance, and the introduction of 
frame fork reinforcement or repair procedures that, when done, allow 
an extension of repetitive inspection intervals. We are issuing this 
AD to address cracked or ruptured aft LDCD frames, which could allow 
loads to be transferred to the remaining structural elements. This 
condition could lead to the rupture of one or more vertical aft LDCD 
frames, which could result in reduced structural integrity of the 
aft LDCD.

(f) Compliance

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

(g) Retained Inspection Requirements and On-Condition Actions, With 
Revised Compliance Times and New Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2016-25-03, with revised compliance times and new service 
information. At the applicable time specified in paragraph (h) of 
this AD, or before exceeding the threshold defined in table 1 to 
paragraph (g) of this AD, whichever occurs later: Do the actions 
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 
Repeat the high frequency eddy current (HFEC) inspection specified 
in paragraph (g)(3) of this AD thereafter at intervals not to exceed 
the applicable times specified in table 1 to paragraph (g) of this 
AD.
    (1) A one-time check of the aft LDCD clearances ``U'' and ``V'' 
between the latching hooks and the eccentric bush at FR60 through 
FR64A, in accordance with the instructions of Airbus Alert Operators 
Transmission A52W011-15, Revision 00, dated July 23, 2015; or the 
Accomplishment Instructions of Airbus Service Bulletin A300-52-6086, 
Revision 01, dated May 29, 2018. If any value outside tolerance is 
found, adjust the latching hook before further flight, in accordance 
with the instructions of Airbus Alert Operators Transmission 
A52W011-15, Revision 00, dated July 23, 2015; or the Accomplishment 
Instructions of Airbus Service Bulletin A300-52-6086, Revision 01, 
dated May 29, 2018.
    (2) A one-time detailed inspection to detect signs of wear of 
the hooks, eccentric bushes, and x-stops, in accordance with the 
instructions of Airbus Alert Operators Transmission A52W011-15, 
Revision 00, dated July 23, 2015. If any wear is found, do all 
applicable corrective actions before further flight, in accordance 
with the instructions of Airbus Alert Operators Transmission 
A52W011-15, Revision 00, dated July 23, 2015.
    (3) An HFEC inspection to detect cracking at all frame fork 
stations of the aft LDCD, in accordance with the instructions of 
Airbus Alert Operators Transmission A52W011-15, Revision 00, dated 
July 23, 2015; or the Accomplishment Instructions of Airbus Service 
Bulletin A300-52-6086, Revision 01, dated May 29, 2018, 2016. If any 
crack is found, before further flight, replace the cracked frame 
fork, in accordance with the instructions of Airbus Alert Operators 
Transmission A52W011-15, Revision 00,

[[Page 49268]]

dated July 23, 2015; repair the cracked frame fork, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-52-6086, Revision 01, dated May 29, 2018; or reinforce the 
cracked frame fork, including doing all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-52-6085, 
Revision 01, dated May 2, 2018, except as required by paragraph (i) 
of this AD.
[GRAPHIC] [TIFF OMITTED] TR01OC18.004

(h) Retained Compliance Times, With No Changes

    At the later of the times specified in paragraphs (h)(1) and 
(h)(2) of this AD, do the actions required by paragraph (g) of this 
AD.
    (1) Before the accumulation of 4,500 total flight cycles.
    (2) At the applicable time specified by paragraph (h)(2)(i) or 
(h)(2)(ii) of this AD.
    (i) For airplanes that have accumulated 8,000 or more total 
flight cycles as of January 26, 2017 (the effective date of AD 2016-
25-03): Within 100 flight cycles after January 26, 2017.
    (ii) For airplanes that have accumulated fewer than 8,000 total 
flight cycles as of January 26, 2017 (the effective date of AD 2016-
25-03): Within 400 flight cycles after January 26, 2017.

(i) Service Information Exception

    Where Airbus Service Bulletin A300-52-6085, Revision 01, dated 
May 2, 2018, specifies to contact Airbus for appropriate action: 
Before further flight, accomplish corrective actions in accordance 
with the procedures specified in paragraph (n)(2) of this AD.

(j) No Terminating Action

    Accomplishment of corrective actions on an airplane as required 
by paragraph (g)(1) or (g)(2) of this AD, or repair, reinforcement, 
or replacement of a frame fork as required by paragraph (g)(3) of 
this AD, on the aft LDCD of an airplane does not constitute 
terminating action for the repetitive HFEC inspections required by 
paragraph (g)(3) of this AD for that airplane.

(k) Compliance Time Clarification

    After replacement, repair, or reinforcement of any frame fork on 
the aft LDCD of an airplane, as specified in paragraph (g)(3) of 
this AD, the next HFEC inspection as required by paragraph (g)(3) of 
this AD can be deferred for any frame fork that is replaced, 
repaired, or reinforced, but must be accomplished before exceeding 
6,800 flight cycles after the replacement, repair, or reinforcement 
of that frame fork.

(l) No Reporting

    Although the Accomplishment Instructions of Airbus Alert 
Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; 
and Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 
2018; specify to submit certain information to the manufacturer, 
this AD does not include that requirement.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g)(1) and (g)(3) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A300-52-6086, Revision 00, dated December 25, 2016.
    (2) This paragraph provides credit for actions required by 
paragraph (g)(3) of this AD, if those actions were performed before 
the effective date of this AD using Airbus Service Bulletin A300-52-
6085, Revision 00, dated December 22, 2016.

(n) Other FAA AD Provisions

    (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 (o)(2) of this AD. Information 
may be emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the European Aviation Safety Agency (EASA); or 
Airbus SAS's EASA Design Organization Approval (DOA). If approved by 
the DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (i) and paragraph (l) 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.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2015-0152R1, dated May 23, 2017, for related 
information. This MCAI may be found in the AD docket on the 
iInternet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2018-0417.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des

[[Page 49269]]

Moines, WA 98198; telephone and fax 206-231-3225.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(5) and (p)(6) of this AD.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
November 5, 2018.
    (i) Airbus Service Bulletin A300-52-6085, Revision 01, dated May 
2, 2018.
    (ii) Airbus Service Bulletin A300-52-6086, Revision 01, dated 
May 29, 2018.
    (4) The following service information was approved for IBR on 
January 26, 2017 (81 FR 93801, December 22, 2016).
    (i) Airbus Alert Operators Transmission A52W011-15, Revision 00, 
dated July 23, 2015, including the following appendices:
    (A) Appendix 1--Flowchart, undated.
    (B) Appendix 2--Reporting Sheet, undated. (The pages of Appendix 
2 are not numbered.)
    (C) Appendix 3--titled ``Technical Disposition,'' Ref. TD/K12/
L3/02978/2015, Issue B, dated July 21, 2015. (Appendix 3 is 
identified with an appendix number only on page 1 of Airbus Alert 
Operators Transmission A52W011-15, Revision 00, dated July 23, 
2015.)
    (D) Appendix 4--Part number identification for frame forks and 
bushings, undated.
    (ii) Reserved.
    (5) For service information identified in this AD, 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.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Des Moines, Washington, on September 21, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-21100 Filed 9-28-18; 8:45 am]
 BILLING CODE 4910-13-P