[Federal Register Volume 82, Number 203 (Monday, October 23, 2017)]
[Rules and Regulations]
[Pages 48910-48912]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-22563]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0480; Product Identifier 2016-NM-204-AD; Amendment 
39-19073; AD 2017-21-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and 
Model A300 C4-605R Variant F airplanes (collectively called Model A300-
600 series airplanes); and Model A310 series airplanes. This AD was 
prompted by a report of cracking in the door sill area of the aft cargo 
door. This AD requires repetitive inspections of the aft cargo door 
lower torsion box area, and corrective actions if necessary. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective November 27, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 27, 
2017.

ADDRESSES: For service information identified in this final rule, 
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 Standards Branch, 1601 Lind Avenue SW., Renton, 
WA. For information on the availability of this material at the FAA, 
call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0480.

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-
0480; 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 AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-5527) is Docket Management Facility, 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, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A300 
B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes); and Model A310 series airplanes. The NPRM published in the 
Federal Register on May 22, 2017 (82 FR 23166) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0241, dated December 6, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-
605R Variant F airplanes (collectively called Model A300-600 series 
airplanes); and Model A310 series airplanes. The MCAI states:

    Cracks were found on in-service aeroplane post mod 5438 in the 
door sill area, from frame (FR) 60 to FR63, including the sill beam 
flag, lock fitting, door sill web and torsion door panel. Two 
previous cases with less crack extent were also reported.
    This condition, if not detected and corrected, could lead to 
reduced structural integrity of the aeroplane.
    To address this unsafe condition, Airbus published Inspection 
Service Bulletin (SB) A310-53-2139 and SB A300-53-6179 to provide 
inspection instructions for the affected areas. Airbus published 
also Airbus SB A310-53-2141 and SB A300-53-6181 to provide 
modification instructions.
    Further analysis showed that aeroplanes pre-mod 5438, for which 
one or several lock fittings have been replaced by post mod 10319 
lock fittings, could also be affected. Airbus published SB A310-53-
2143 and SB A300-53-6185 to provide inspection instructions.
    For the reason described above, this [EASA] AD requires 
repetitive Special Detailed Inspections (SDI) of the aft cargo door 
lower torsion box area and, depending on findings, accomplishment of 
applicable corrective action(s).

    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-
0480.

Comment

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

Request To Clarify Terminating Action

    United Parcel Service (UPS) requested that the terminating action 
specified in paragraph (i) of the proposed AD be clarified to specify 
that the repair of a damaged fitting is terminating action for the 
repetitive inspections specified in paragraph (g) of the proposed AD 
for the repaired fitting location only. The commenter stated that this 
clarification would mitigate premature termination of repetitive 
inspections of the aft cargo door lower torsion box area.
    We agree with the commenter's request for the reasons provided by 
the commenter. We have revised paragraph (i) of this AD to specify that 
repair of a lock fitting as required by paragraph (h) of this AD 
constitutes terminating action for the repetitive inspections required 
by paragraph (g) of this AD for the repaired fitting location only.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the change described previously and minor editorial 
changes. We have determined that these minor changes:

[[Page 48911]]

     Are consistent with the intent that was proposed in the 
NPRM for correcting 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 AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A300-53-6185, dated February 
11, 2016; and Service Bulletin A310-53-2143, dated February 11, 2016; 
which describe, among other actions, repetitive inspections of the aft 
cargo door sill area for cracking. These documents are distinct since 
they apply to different airplane models. 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 18 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
           Action                  Labor cost         Parts cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection.................  12 work-hours x $85                $0  $1,020 per inspection  $18,360 per
                              per hour = $1,020                      cycle.                 inspection cycle.
                              per inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
a cost estimate for the on-condition corrective actions specified in 
this AD.

Authority for This Rulemaking

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

2017-21-02 Airbus: Amendment 39-19073; Docket No. FAA-2017-0480; 
Product Identifier 2016-NM-204-AD.

(a) Effective Date

    This AD is effective November 27, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD; certificated 
in any category; except those on which Airbus Modification 5438 was 
embodied in production.
    (1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (2) Model A300 B4-605R and B4-622R airplanes.
    (3) Model A300 F4-605R and F4-622R airplanes.
    (4) Model A300 C4-605R Variant F airplanes.
    (5) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a report of cracking in the door sill 
area of the aft cargo door. We are issuing this AD to detect and 
correct cracking of the door sill area of the aft cargo; such 
cracking could adversely affect the structural integrity of the 
airplane.

(f) Compliance

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

(g) Repetitive Inspections

    Within the applicable compliance time specified in table 1 to 
paragraph (g) of this AD: Do a high frequency eddy current (HFEC) 
inspection for cracking of the door sill area (including the sill 
beam flag, lock fitting, door sill web, and torsion door panel) of 
the aft cargo door lower torsion box area, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6185, 
dated February 11, 2016; or Service Bulletin A310-53-2143, dated 
February 11, 2016; as applicable. Repeat the HFEC inspection 
thereafter at intervals not to exceed 15,100 flight cycles.

[[Page 48912]]



         Table 1 to Paragraph (g) of This AD--Initial Inspection
------------------------------------------------------------------------
           Airplane configuration                  Compliance time
------------------------------------------------------------------------
Repaired (date known), post-Airbus           Before exceeding 25,800
 Modification 10319 lock fittings installed   flight cycles since the
 using Airbus Structural Repair Manual        lock fitting replacement.
 (SRM) Task 51-72-00.
Repaired (no record, date unknown), post-    Before exceeding 25,800
 Airbus Modification 10319 lock fittings      flight cycles from
 installed using Airbus SRM Task 51-72-00.    November 1, 1996.
Non-repaired airplane, or airplane repaired  No inspection required.
 with pre-Airbus Modification 10319 lock
 fittings using Airbus SRM Task 51-72-00.
------------------------------------------------------------------------

(h) Corrective Action

    If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, repair in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6185, dated February 11, 2016; or Service Bulletin 
A310-53-2143, dated February 11, 2016; as applicable; except, where 
Airbus Service Bulletin A300-53-6185, dated February 11, 2016; or 
Service Bulletin A310-53-2143, dated February 11, 2016; 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 (j)(2) of this AD.

(i) Terminating Action

    Repair of a lock fitting as required by paragraph (h) of this AD 
constitutes terminating action for the repetitive inspections 
required by paragraph (g) of this AD for the repaired fitting 
location only. All other post-Airbus Modification 10319 installed 
fittings are to be inspected as required by paragraph (g) of this 
AD.

(j) 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 manager of the International Section, send it to the 
attention of the person identified in paragraph (k)(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 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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0241, dated December 6, 2016, 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-2017-0480.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 
425-227-2125; fax 425-227-1149.

(l) 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.
    (i) Airbus Service Bulletin A300-53-6185, dated February 11, 
2016.
    (ii) Airbus Service Bulletin A310-53-2143, dated February 11, 
2016.
    (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.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (5) 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 Renton, Washington, on October 11, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-22563 Filed 10-20-17; 8:45 am]
BILLING CODE 4910-13-P


