Document ID: FAA-2017-0480-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2017-05-22T04:00Z

[Federal Register Volume 82, Number 97 (Monday, May 22, 2017)]
[Proposed Rules]
[Pages 23166-23169]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10140]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0480; Directorate Identifier 2016-NM-204-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 adopt 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 proposed AD was prompted by cracking in the door sill 
area of the aft cargo door. This proposed AD would require repetitive 
inspections of the aft cargo door lower torsion box area, and 
corrective actions if necessary. We are proposing this AD to address 
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 6, 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

[[Page 23167]]

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 account.airworth-eas@airbus.com; 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-
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 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-2017-0480; 
Directorate Identifier 2016-NM-204-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

    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.

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.

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.

Costs of Compliance

    We estimate that this proposed AD affects 18 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed 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           $18,360 per
                                    per hour = $1,020                    inspection cycle.    inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

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

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701:

[[Page 23168]]

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:

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-2017-0480; Directorate Identifier 2016-NM-
204-AD.

(a) Comments Due Date

    We must receive comments by July 6, 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 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.

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

(j) 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 (k)(2) of this AD. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
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

[[Page 23169]]

the DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(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 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 account.airworth-eas@airbus.com; 
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 12, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10140 Filed 5-19-17; 8:45 am]
BILLING CODE 4910-13-P